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 2001050200060 20010502 00060 CE 2001 5 2 00114 1 20010318 G 7110 45A350271 COWLING BEECH BEECH MU300 400A 1155402 CE PWA JT15 JT15D5 52112 NE LT ENGINE BENT E DJFA O OTHER O OTHER CR CRUISE 1 EA 23 456CW 4448 RK56 COWLING ON LEFT HAND ENGINE BOTTOM INBOARD SIDE WAS BENT BACK DURING FLIGHT. THE CAUSE IS UNKNOWN, THESE COWLINGS ARE KN OWN TO HAVE THIS TYPE OF PROBLEM. 2 H 7 2 4F 4 F RT A16SW E25EA 2001080200248 20010802 00248 CE 2001 8 2 010204 1 20010723 G 7713 C4820020108 RELIEF VALVE CESSNA 210 T210N 2073456 CE CONT O520 TSIO520R 17040 SO MCAULY D3A34 D3A34C402 GL INDUCTION SYSTEM FAILED B R8RR K NONE O OTHER IN INSP/MAINT 1 SW 99 6506G 21064406 294271R 001099 A TCM REBUILT ENGINE WAS INSTALLED INTO THIS AIRCRAFT WITH ALL THE ASSOIATED NEW PARTS. THE AIRCRAFT COULD NOT ACHIVE 3 6.5 IN. AT 2700 RPM FOR TAKEOFF POWER. ALL INDICATING INSTRUMENTS WERE VERIFIED FOR CALIBRATION. WE INSTALLED THE OLD A BSOLUTE PRESSURE RELIEF VALVE AND OBTAINED 36.5 IN. EASILY. 1 H 7 1 3O 3 O 3A21 E8CE 5 C P47GL 2001080200250 20010802 00250 CE 2001 8 2 010726 1 20010726 G 7713 C4820020108 RELIEF VALVE CESSNA 210 T210N 2073456 CE CONT O520 TSIO520R 17040 SO MCAULY D3A34 D3A34C402 GL INDUCTION SYSTEM MALFUNCTIONED B R8RR K NONE O OTHER IN INSP/MAINT 1 SW 99 6506G 21064406 294271R 001099 AFTER A REBUILT TCM ENGINE WAS INSTALLED INTO THIS AIRFRAME A SECOND REBUILT ABSOLUTE PRESSURE RELIEF VALVE FROM CONSOLI DATED FUEL SYSTEMS, INC. WAS INSTALLED AND THE ENGINE WOULD NOT PRODUCE 36.5 IN OF MANIFOLD PRESSURE REQUIRED FOR TAKEOF F. REINSTALLED THE ORIGINAL RELIEF VALVE AND THE ENGINE PRODUCED 36.5 IN OF MANIFOLD PRESSURE. 1 H 7 1 3O 3 O 3A21 E8CE 5 C P47GL 2001100200006 20011002 00006 WP 2001 10 2 0109 1 20010906 G 5552 STOP DOUG DC8 DC862 3021970 WP RT ELEVATOR TAB LOOSE H O OTHER F FLT CONT AFFECTED CR CRUISE 1 SW 99 VP-BH 46111 AUTO PILOT PORPOSING IN LEVEL FLIGHT. DURING RT ELEVATOR CABLE ADJUSTMENT CHECKED TRAVEL TAB IN BOTH DIRECTION. WITH S TICK FULL FORWARD THE LEFT ELEVATOR TAB ONLY GOES UP. THE RIGHT ELEVATOR TAB STAYS AT THE SAME POSITION. AFTER TROUBLE S HOOTING WE FOUND THE STOP SCREW (THE UPPER ONE ) COMPLETELY LOOSE ON RIGHT SYSTEM, CAUSING THE RESTRICTING TRAVEL OF TAB IN TRAILING EDGE UP. AFTER CORRECTING ACTION, THE TRAVEL CHECK IS NORMAL 2 L 7 4 4F 4A25 2001112600003 20011126 00003 NE 2001 11 26 0115 2 20011115 G 7200 ENGINE AMD FALC50 FALCON50MYST 2730106 EU GARRTT TFE731 TFE73131C 01518 NE NR 1 FLAMED OUT H K NONE X ENGINE FLAMEOUT CR CRUISE 1 SW 99 BSA 196 APPROX 30 MINUTES INTO FLIGHT AT FL 390 COCKPIT HEAT CONTROL WAS MOVED FROM MANUAL TO AUTO. SHORTLY AFTER NR 1 ENG FLAM ED OUT. NO WARNING LIGHTS, NO VIBRATION. AN IMMEDIATE RELIGHT WAS PERFORMED AND SUCCESSFUL. ALL ENGINE PARAMETERS WER E NORMAL, FLIGHT CONTINUED TO DESTINATION. 2 L 7 3 4F 4 F A46EU E6WE 2002012400095 20020124 00095 SO 2002 1 24 0116 1 20011116 G 7830 LOCK GULSTM G1159 GIV 3980115 SO RROYCE TAY TAY6118 EU THRUST REVERSER FAULTY H A UNSCHED LANDING J WARNING INDICATION CL CLIMB 1 SW 99 VPBSF 1058 16171 WHILE PASSING THROUGH 2,500 FT MASTER WARNING RT THRUST REVERSER UNLOCKED. IMMEDIATELY REDUCED THROTTLES MESSAGE CLEARED . CONTINUED ON. WHEN PASSING THROUGH 4000 FT SAME WARNING AGAIN. RETURN TO BLOCKS. NORMAL APPROACH AND LANDING MADE. M AINTENANCE INSPECTION REVEILED FAULTY THRUST REVERSER INTERNAL LOCK . BOTH ACTUATORS REPLACED 2 L 7 2 4F 4 F RT A12EA E25NE 2001042400277 20010424 00277 WP 2001 4 24 01FDEA00289 1 20010419 G 3260 TARGET DOUG DC10 DC1010 3022110 WP RT MLG DOOR INOPERATIVE A FDEA A UNSCHED LANDING J WARNING INDICATION CL CLIMB 1 SO 25 389FE 46623 01-124 RT MLG RED LIGHT ILLUMINATED ON BOTH PANELS AFTER TAKE OFF. RECYCLED PER RED TABS, REMAIN ILLUMINATED. R/R TAR GET PER EO 8-3260-7-3304-B. AC OK FOR SERVICE. 2 L 7 3 4F A22WE 2001070200036 20010702 00036 WP 2001 7 2 01FDEA00398 1 20010605 G 3260 WARNING LIGHT DOUG DC10 DC1010 3022110 WP COCKPIT ILLUMINATED A FDEA O OTHER J WARNING INDICATION DE DESCENT 1 SO 25 389FE 46623 ON DESCENT RT MLG RED LIGHT ILLUM ON BOTH PANELS. ACCOMP RED TAB PROC. FERRIED A/C TO IND. 2 L 7 3 4F A22WE 2002012400096 20020124 00096 CE 2002 1 24 040521239 1 20011204 G 3211 501202015 SUPPORT BEECH 200 A200 1152921 CE MLG CRACKED H K NONE O OTHER IN INSP/MAINT 1 SO 21 1546 11996 BC58 LEFT HAND AND RIGHT HAND MAIN LANDING GEAR DRAG LEG SUPPORTS FOUND TO BE CRACKED DURING FLUORESCENT PENETRANT INSPECTION . INSPECTION ORDERED BY U.S. CUSTOMS SERVICE BASED ON REPORTS FROM U.S. ARMY OPERATORS. 1 L 7 2 4T A24CE 2002012400097 20020124 00097 CE 2002 1 24 040521239A 1 20011204 G 3211 501202015 SUPPORT BEECH 200 A200 1152921 CE MLG CRACKED H K NONE O OTHER IN INSP/MAINT 1 SO 21 72470 12534 BC04 LEFT HAND MAIN LANDING GEAR DRAG LEG SUPPORT FOUND TO BE CRACKED DURING FLUORESCENT PENETRANT INSPECTION. INSPECTION ORD ERED BY U.S. CUSTOMS SERVICE BASED ON REPORTS BY U.S. ARMY OPERATORS. 1 L 7 2 4T A24CE 2001080200253 20010802 00253 NE 2001 8 2 1 2 20010712 G 7261 642790041 TRANSMITTER SNIAS 350 AS350B2 8680813 EU TMECA ARRIEL ARRIEL1D NE OIL PRESSURE INOPERATIVE B S88R E D ENGINE SHUTDOWN RETURN TO BLOCK N FALSE WARNING TX TAXI/GRND HDL 1 SO 21 5202Y 3085 9564 NO ENGINE OIL PRESSURE INDICATION DURIN ENGINE START SEQUENCE.THE OIO PRESSURE TRANSMITTER WAS REPLACED ON MORE THAN ONE TIME, BUT THE NEW TRANSMITTER WERE BAD FROM OVERHAULED FACILITY. 1 G 7 1 3U 3 U H9EU E19EU 2001080200256 20010802 00256 SO 2001 8 2 100000 2 20010801 G 7414 WIRE PIPER J3 J3F65 7100536 SO CONT A65 A658 17003 SO MAGNETO CHAFED G O OTHER Y J ENGINE STOPPAGE WARNING INDICATION TO TAKEOFF 1 GL 07 40782 7496 DURING TAKE-OFF THE ENGINE QUIT. THE AIRCRAFT WAS DESTROYED. INVESTIGATION BY THE FAA INSPECTOR PROVED THAT THE PROBABL E CAUSE OF THE ENGINE FAILURE WAS ATTRIBUTED TO BOTH MAGNETO P-LEAD WIRES BEING GROUNDED OUT AGAINST A SCREW THAT SECURE D THE LEFT-HAND INNER AND OUTER WINDOW TRIM PIECES. 1 H 7 1 3O 3 O A692 E205 2001102600009 20011026 00009 CE 2001 10 26 1024016 1 20011022 G 3040 265318202071 WINDSHIELD RKWELL NA265 NA26565 7630107 CE GARRTT TFE731 TFE7313R1D 01518 WP COCKPIT ARCED B RE3R K NONE B SMOKE/FUMES/ODORS/SPARKS CR CRUISE 1 NM 01 6NR 1834 46529 PILOTS NOTICED INTERNAL ARCING IN WINDSHIELD AT UPPER EDGE ALONG HEAT ELEMENT BUS STRIP. ARCING CONTINUED FROM ONE SIDE AND PROGRESSED TO OPPOSITE SIDE AND BURNED BUS STRIP PARTIALLY THROUGH. WINDSHIELD CONTINUED TO HEAT UNTIL BUS STRIP B URNED COMPLETELY THROUGH WIDTH AT ONE LOCATION. WINDSHIELD WAS REPLACED PRIOR TO NEXT FLIGHT. REASON FOR ARCING IS MOS T LIKELY DELAMINATION IN UPPER EDGE OF WINDSHIELD IN BUS STRIP AREA. RECOMMEND PRE-FLIGHT VISUAL INSPECTION OF THIS ARE A FOR DELAMINATION AND EVIDENCE OF INTERNAL ARCING STARTING TO HAPPEN IN ANY AREA. IF REPLACEMENT IS REQUIRED, REPLACE WITH PPG BRAND WINDSHIELD. 2 L 7 2 4J 4 F A2WE E6WE 2002071900081 20020719 00081 CE 2002 7 19 102401868 1 20010923 G 3340 S13605L CIRCUIT BREAKER CESSNA 172 172R 2072401 CE EXTERIOR LIGHTS FAILED D S1XB A UNSCHED LANDING A FLAME/FIRE CL CLIMB 1 SO 17 2458G 17280893 THE TAIL LIGHT POSITIVE LEAD SHORTED TO GROUND BY CONTACT WITH A TINNERMAN NUT IN THE RUDDER. THERE WAS NO EVIDENCE OF TRAUMA TO THE WIRE. ONLY A PINPOINT OF CONTACT WAS EVIDENT THE NAV LIGHT BREAKER DID NOT TRIP AND THE WIRING BURNED FR OM THE TAIL TO THE CIRCUIT BREAKER PANEL, TAKING OUT HALF THE BUS WITH IT. THE FIRST WIRE BURNING STARTED A CASCADE OF SHORT CIRCUITS. THIS DOMINO EFFECT SEQUENTIALLY TOOK OUT ADDITIONAL CIRCUITS UNTIL THE MAIN BUSS BREAKER OPENED. 1 H 7 1 3O NT 3A12 2001080200259 20010802 00259 CE 2001 8 2 2 1 20010727 G 3232 99810057652 ACTUATOR BEECH 200 C12C CE PWA PT6 PT6* 52043 EA HARTZL HCB3T HCB3TN3 GL MLG DAMAGED B S88R K NONE O OTHER IN INSP/MAINT 1 SO 21 1547 1091 BC50 DURING A LANDING GEAR RETRACTION CHECK THE L/H LANDING GEAR WHENT FROM THE UP POSITION TO THE DOWN AND LOCK POSITION BY OT SELF. AFTER FURTHER INVESTIGATION FOUND THA THE L/H ACTUATOR SHAFT NUT HAD FAILED AND COMPLETLY CAME OF THE SHAFT, CA USING THE LANDING GEAR TO DROP TO THE DOWN AND LOCK POSITION. 1 L 7 2 4T 3 T A24CE E2NE 6 C P15EA 2001040900164 20010409 00164 CE 2001 4 9 20010124CW003 1 20010103 G 7120 10191012253 MOUNT BEECH B300 B300 1159232 CE PWA PT6 PT6* 52043 EA ENGINE CRACKED D K NONE O OTHER IN INSP/MAINT 1 EA 23 309M FL48 COWL ATTACH LUGS CRACKED ON ENGINE MOUNT. ALSO, CORROSION FOUND AT MOUNT TO FUSELAGE ATTACH POINT BOLTS AND SPACING WASHERS. 2 L 7 2 4T 3 T RT A24CE E2NE 2001041000002 20010410 00002 CE 2001 4 10 20010124CW006 2 20010124 G 7420 M750272 IGNITION LEAD PIPER PA34 PA34200T 7103406 SO CONT O360 TSIO360RB 17025 CE RT ENGINE SHORTED D K NONE O OTHER IN INSP/MAINT 1 NM 07 4166R 3449185 322077 NR2 AND NR6 CYLINDER IGNITION LEADS ON BOTTOM PLUGS SHORTED OUT, BEHIND IGNITION LEAD SPRING ASSEMBLY. 1 L 7 2 3O 3 O A7SO E9CE 2001041700097 20010417 00097 SO 2001 4 17 20010124CW007 2 20010124 G 8520 BEARING CESSNA 180 180B 2072606 CE CONT O520 IO520D 17032 SO CRANKCASE FAILED D K NONE O OTHER CR CRUISE 1 SW 99 9283R 18802211 22145373D BEARING FAILURE ON NR2 MAIN BEARING. CAUSED DAMAGE TO CRANKCASE, OIL PRESSURE DROPPED 20 PSI IN FLIGHT WITH NO OTHER IN DICATION. 1 H 7 1 3O 3 O 5A6 E5CE 2001050200001 20010502 00001 EU 2001 5 2 20010124CW008 1 20010109 G 6520 365A33600501 BEARING AEROSP SA365 SA365N1 8680668 EU TAIL ROTOR GRBX FAILED D K NONE O OTHER IN INSP/MAINT 1 EA 03 89SM 6282 MANUFACTURER TEARDOWN OF GEARBOX, FOUND PITCH CHANGE SHAFT DUPLEX BEARING FAILURE AND SHAFT SHEAR T/R BLADES IN-NEG-PITC H WITH NO CONTROL OF TAIL ROTOR.NOTE: NO T/R GEARBOXES INSTALLED ON ANY 365 IN OUR FLEET HAVE ELECTRONIC CHIP DETECTOR. 1 G 7 2 3U H10EU 2001050200002 20010502 00002 CE 2001 5 2 20010124CW009 1 20010124 G 2720 RUDDER CESSNA 182 182S 2072701 CE TAIL INTERFERENCE D K NONE O OTHER IN INSP/MAINT 1 SW 99 162TC 80164 WHEN CHECKING RUDDER TRAVEL, ELEVATOR WAS IN NEUTRAL POSITION. WHILE THE RUDDER WAS DEFLECTED FULL IN EITHER DIRECTION , THE ELEVATOR WOULD HIT THE RUDDER WHEN THE ELEVATOR WAS RAISED. THE RUDDER TRAVEL WAS RIGGED CORRECTLY PER MAINTENANC E MANUAL. THIS COULD CAUSE THE RUDDER AND ELEVATOR TO JAM IN FLIGHT. 1 H 7 1 3O NT 3A13 2001030100079 20010301 00079 EU 2001 3 1 20010124CW010 1 20010109 G 6520 3655A33600501 GEARBOX AEROSP AS365 AS365N2 8680815 EU TAIL ROTOR FAILED D K NONE O OTHER IN INSP/MAINT 1 EA 03 365DU 955 955 6425 GEARBOX REMOVED DUE TO FAILING SOAP/OIL ANALYSIS/ OF IRON-18.0 AND MAGNESIUM/ 73.2/SAMPLE TAKEN 12-18-00. PREVIOUS SAM PLE TAKEN 12-5-00 HAD IRON AT /3.8/ AND MAGNESIUM AT /10.9/ ALL VALVES ARE IN PARTS PER MILLION. 1 G 7 2 3U RT H10EU 2001050200005 20010502 00005 SO 2001 5 2 20010125CW002 1 20010102 G 2140 A23D04 REGULATOR PIPER PA31 PA31350 7103110 SO LYC O540 TIO540J2BD 41532 EA FWD HEATER LEAKING G WVBA K NONE K FLUID LOSS IN INSP/MAINT 1 SW 99 59764 317652037 PILOT REPORTED HEATER INOPERATIVE. UPON INSPECTION, FOUND FUEL PRESSURE REGULATOR LEAKING. UNIT WAS REPLACED, OPS GOOD . 1 L 7 2 3O 3 O A20SO E14EA 2001050200006 20010502 00006 SO 2001 5 2 20010125CW003 1 20010102 G 2140 A23D04 REGULATOR PIPER PA31 PA31350 7103110 SO LYC O540 TIO540J2BD 41532 EA FWD HEATER LEAKING G WVBA K NONE K FLUID LOSS IN INSP/MAINT 1 SW 99 27755 317852148 PILOT REPORTED HEATER OUTPUT DECREASES AFTER ABOUT 20 MIN. UPON INSPECTION, FOUND FUEL PRESSURE REGULATOR LEAKING. UN IT WAS REPLACED. OPS CHECK GOOD 1 L 7 2 3O 3 O A20SO E14EA 2001050200007 20010502 00007 SO 2001 5 2 20010125CW004 1 20010102 G 2140 44008 VALVE ELECTROSYS PIPER PA31 PA31350 7103110 SO LYC O540 TIO540J2BD 41532 EA MCAULY 3DF36C B3DF36C526 GL HEATER COMP LEAKING G K NONE K FLUID LOSS IN INSP/MAINT 1 SW 99 3527U 2346 2346 A98030019 317952141 DURING ROUTINE INSPECTION, FUEL WAS OBSERVED LEAKING FROM FUEL SOLENOID SHUT OFF VALVE. PART WAS REMOVED FROM SERVICE. 1 L 7 2 3O 3 O A20SO E14EA 5 C 2001050200008 20010502 00008 SO 2001 5 2 20010125CW006 1 20010109 G 2823 35640023564001 SELECTOR VALVE PIPER PA23 PA23250 7102308 SO LYC O540 IO540C4B5 41532 EA HARTZL HCE2Y HCE2YR2 GL FUEL SYSTEM LEAKING D K NONE K FLUID LOSS IN INSP/MAINT 1 SW 99 17WE 3615 277854118 AC WAS PUT IN UNHEATED HANGER WITH FULL FUEL TANKS, FOUND FUEL ON FLOOR UNDER BOTH WINGS, WAS FOUND TO BE LEAKING FROM O VERFLOW TUBES OF BOTH INBOARD FUEL TANKS WHICH WERE FULL. OUTBOARD TANKS WERE DOWN, ONLY CONNECTION BETWEEN IB AND OB TA NKS IS THROUGH FUEL SELECTOR VALVES. FUEL SELECTOR VALVES WERE FOUND, WHEN IN OFF POSITION, FUEL FLOW WAS NOT COMPLETEL Y SHUT OFF TO ENG SIDE OF VLV. AC HAD RECENT ANNUAL INSP. ALL OPS CHECKED GOOD. VALVE LOCATION IN IB AFT OF FIREWALLS. VALVES REMOVED AND SENT TO DUKES, VALVE MFG. SUSPECT ENVIRONMENTAL CHANGE OF AC TO FIND DEFECT OF VALVES. 1 L 7 2 3O 3 O 1A10 1E4 5 C P9EA 2001050200011 20010502 00011 CE 2001 5 2 20010125CW009 1 20010125 G 2701 35524656 CLIP BEECH 35 S35 1151532 CE CONTROL YOKE MISSING D K NONE O OTHER IN INSP/MAINT 1 SW 99 354D D7659 DURING ANNUAL INSPECTION OF AC A VISUAL INSPECTION WAS PERFORMED ON CHAIN INSIDE THE DUAL CONTROL YOKE. CHAIN MASTER LI NK PLATE AND CLIP WERE MISSING FROM LOWER LEFT CHAIN ATTACH POINT TO FITTING. RECOMMEND MORE ATTENTION IN THIS AREA UPO N ANNUAL INSPECTION/ 100 HOUR INSPECTION 1 L 7 1 3O 3A15 2001041800282 20010418 00282 NM 2001 4 18 20010125CW010 1 20010105 G 2910 65447821 HOUSING BOEING BOEING 737 737 UTILSYS NM HYDRAULIC MODULE CRACKED B K NONE O OTHER IN INSP/MAINT 1 NM 01 1110 HOUSING WAS NOTED TO BE CRACKED AT BOTH THE A AND B PORTS, DURING NON-DESTRUCTIVE INSPECTION. 2 L 7 2 4F RT A16WE 2001041700109 20010417 00109 NM 2001 4 17 20010125CW011 1 20010104 G 2782 69358521 SLEEVE BOEING BOEING 737 737 UTILSYS NM SLAT ACTUATOR FRACTURED B K NONE O OTHER IN INSP/MAINT 1 NM 01 7649K SLEEVE /145/ OF BLOCKING VALVE ASSEMBLY IS FRACTURED. PROBABLE CAUSE/ FATIGUE 2 L 7 2 4F RT A16WE 2001041700110 20010417 00110 NM 2001 4 17 20010125CW012 1 20010104 G 2910 65447821 HOUSING BOEING BOEING 737 737 UTILSYS NM HYDRAULIC MODULE LEAKING B K NONE K FLUID LOSS IN INSP/MAINT 1 NM 01 43127 43127 1134 UNIT NOTED TO HAVE A PIN HOLE LEAK ADJACENT TO OUTLET PORT NR4 AS PRESSURE WAS APPLIED DURING PROOF TEST. 2 L 7 2 4F RT A16WE 2001050200015 20010502 00015 EA 2001 5 2 20010129CW004 2 20010104 G 8550 06B26072 GASKET PIPER PA31 PA31350 7103110 SO LYC O540 TIO540J2BD 41532 EA OIL FILTER CUT B K NONE O OTHER IN INSP/MAINT 1 SW 99 35805 61 318052090 L663461A GASKET FOUND CUT UPON REMOVAL. POSSIBLY DUE TO INSTALLATION PROCEDURE. RECOMMEND MORE CARE IN INSTALLING ADAPTER PLATE TO PREVIENT COCKING ON INSTALLATION. MAKE SURE GASKET IS CENTERED ON PLATE. 1 L 7 2 3O 3 O A20SO E14EA 2001041800348 20010418 00348 EA 2001 4 18 20010129CW008 1 20010129 G 5330 SKIN CNDAIR CL600 CL6002B16 1900305 EA GE CF34 CF34* NE FUSELAGE CORRODED B K NONE O OTHER IN INSP/MAINT 1 WP 07 604WB 5125 AFTER REMOVAL OF SATCOMM ANTENNAS FROM FUSELAGE STATION 349, CORROSION WAS DISCOVERED UNDER ANTENNAS ON AIRCRAFT FUSELA GE SKIN SURFACE. AFTER REMOVAL OF CORROSION DAMAGE WAS BEYOND LIMITS, RESULTING IN SKIN REPLACEMENT ON BOTH SIDES. 2 L 7 2 4F 4 F RT A21EA E15NE 2001050200021 20010502 00021 CE 2001 5 2 20010129CW013 1 20010105 G 5210 DOOR CESSNA 182 182P 2075816 CE RT DOOR CRACKED D K NONE O OTHER IN INSP/MAINT 1 SW 99 7220H 18263011 FORWARD DOOR POST, INSPECT AND MOD. FOUND CRACK ON RT SIDE. THE SEB CALLS FOR INITIAL INSPECTION AT 4000 HOURS. I HAVE FOUND THIS CONDITION ON 3 AC. 2 OF THE 3 HAD LESS THAN 2000 HRS T/S. HISTORY ON BOTH IS NORMAL SERVICE AND NO PASST D AMAGE OR ABUSIVE USE. SUSPECT CRACKS ARE DUE TO STRESS RELIEVE FROM STRAINS APPLIED DURING ASSEMBLY MORE THAT TYPE OF US E. 1 H 7 1 3O NT TA13 2001050200022 20010502 00022 CE 2001 5 2 20010129CW014 1 20010108 G 5210 504300431273 DOOR FRAME BEECH 200 200BEECH 1152920 CE AFT DOOR CRACKED B K NONE O OTHER IN INSP/MAINT 1 EA 05 383JP 8204 BB615 REMOVED AND REPLACED AFT CABIN DOOR FRAME PRESSURATION PROBLEM. 1 L 7 2 4T A24CE 2001030700581 20010307 00581 CE 2001 3 7 20010129CW016 1 20010108 G 2710 TORQUE TUBE CESSNA 560 560XL CE PWA 545 PW545A NE AILERON CORRODED B DXTA K NONE O OTHER IN INSP/MAINT 1 SW 99 690QS 564 5605090 AFT AILERON SECTOR TORQUE TUBE CORRODED THE LENGTH OF THE TUBE BETWEEN THE UPPER AND LOWER BELLCRANKS. 2 L 7 2 4F 4 F RT A22CE E00059EN 2001041800370 20010418 00370 SO 2001 4 18 20010129CW018 1 20010109 G 3242 1331317 STATOR BFGOODRICH EMB 120 EMB120 3260201 SO BRAKE ASSY CRACKED B XC4R K NONE O OTHER IN INSP/MAINT 1 SO 05 0814A BRAKE ASSEMBLY PN 21661 FAILED PREMATURELY. NR2 STATOR CRACKED AT RELIEF HOLES. 25 PERCENT OF STATOR MISSING. HEAT ST ACK WARPED AND UNEVEN WEAR.NOTE OEM PARTS INSTALLED IN BRAKE ASSEMBLY AND THE MOST RECENT BRAKE CONFIGURATION PN 21661. 2 L 7 2 4T RT A31SO 2001041800372 20010418 00372 2001 4 18 20010129CW020 4 20010102 G 2565 SLIDE RAFT BFGOODRICH DOUG DC10 DC10 N/A-SDR NM CABIN MISINSTALLED B K NONE O OTHER IN INSP/MAINT 1 SO 19 DD041 FOUND 8 FT LONG BY 2 INCHES WIDE, RED WEBBING STRAP TIED AROUND THE FOLDED INFLATABLE SLIDE/RAFT. IF THE UNIT WERE TO B E USED IN AN EMERGENCY, THE SLIDE WOULD NOT HAVE DEPLOYED PROPERLY. 2 L 7 3 4F RT A22WE 2001050200029 20010502 00029 GL 2001 5 2 20010129CW025 3 20010106 G 6114 HCE2YR2RBSF HUB HARTZL PIPER PA23 PA23250 7102308 SO LYC O540 IO540* 41532 EA HARTZL HCE2Y HCE2YR2 GL PROPELLER LEAKING B K NONE K FLUID LOSS IN INSP/MAINT 1 SW 99 11JD 7841 860 BP6961 277405395 RL1279248A BP6961 PROPELLER WAS RECEIVED FOR NON-SCHEDULE REPAIR, OIL LEAK. DURING PRELIMINARY PROPELLER INSPECTION, PROPELLER WAS NOTED LEAKING BETWEEN HUB/PN D24772R/ AND CYLINDER/PN B24231. CYLINDER LIFTED OFFTHE HUB. PROPELLER ASSEMBLY WAS DISASSEMBLE D, VISUALLY INSPECTED, HUB AND CYLINDER REPLACED, REASSEMBLED AND BALANCED. PROPELLER GOVERNOR WAS REQUESTED FOR INSP. WOODWARD GOVERNOR MODEL NR A210721 WITH SERIAL NR 2455904 WAS RECEIVED FOR INSP.GOVERNOR PRESSURE RELIEF VALVE WAS INSP. AND GOVERNOR ASSY WAS BENCH CKD W/NO DEFECTS.REPAIRED PROPELLER AND GOVERNOR WAS REINSTALLED. PROPELLER AND GOV OPS CK GOOD. 1 L 7 2 3O 3 O 1A10 1E4 5 C P9EA 2001030700590 20010307 00590 EU 2001 3 7 20010130CW004 1 20010115 G 6321 L635M1025229 BRAKE UROCOP EC135 EC135P1 8680990 EU TRANSMISSION CRACKED B K NONE O OTHER IN INSP/MAINT 1 EA 03 511ME 138 0143 ROTOR BRAKE CHATTERING FOUND CRACKED ROTOR BRAKE DISC./ THIS IS SECOND EVENT. 1 G 7 2 3U O H88EU 2001030700592 20010307 00592 SW 2001 3 7 20010130CW005 1 20010116 G 6220 430010101101 YOKE BELL 430 430 1182150 SW MAIN ROTOR CRACKED B GS1R K NONE O OTHER IN INSP/MAINT 1 sw 99 430TX 49005 H.A.S. REPLACED WITH NEW YOKE FROM BELL HELICOPTER. A 1.5 LONG CRACK WAS FOUND ON TOP OF THE YOKE AT STATION 31. 1 G 7 2 3U RT H9SW 2001030700618 20010307 00618 SW 2001 3 7 20010130CW006 1 20010108 G 6510 407340339103 BEARING BELL BELL 407 407 SW T/R DRIVE SHAFT FAILED B K NONE O OTHER IN INSP/MAINT 1 sw 99 407JR 53245 T/ROTOR, D/SHAFT BEARING PN 407340339101 FAILED. RESULTING IN THE LOSS OF BALL BEARINGS, SEALS AND GREASE. DAMAGE TO THE FOLLOWING ITEMS WAS CAUSED BY BEARING FAILURE. BEARING WAS INSTALLED IN NR1 POSITION OF TAIL ROTOR HANGER BEARINGS. DAMAGED ITEMS TO FOLLOW: IMPELLER ASSY, FER OIL COOLER BLOWER, HOUSING, COVER , HANGER SUPPORT, BOTH BEARINGS, BOTH A DAPTERS ON FWD AND AFT END OF SHAFT.IMPROVEMENTS NEED TO BE MADE IN BEARING DURABILITY AND ABILITY TO RETAIN GREASE FROM BEING FORCED OUT BY SUCTION CAUSED FROM IMPELLER ROTATION. 1 G 7 1 3U O H2SW 2001030700620 20010307 00620 GL 2001 3 7 20010130CW008 1 20010116 G 5310 TUBE ENSTRM F28 280F 3300550 GL GEARBOX MOUNTS CRACKED D K NONE O OTHER IN INSP/MAINT 1 CE 01 199TV 5503 1510 4130 TUBING WAS FOUND CRACKED BETWEEN LEFT FORWARD GEARBOX MOUNT AND LEFT REAR GEARBOX MOUNT. PROBABLE CAUSE, METAL FAT IGUE. AC IS 20 YR OLD WITH 5503 HRS. AC DID HAVE HARD LANDING YEARS AGO AT LESS THAN 1000 HRS ON AIRFRAME. POSSIBLE FR AME WAS SUBJECTED TO ADDITIONAL STRESS FROM THE HARD LANDING. RECOMMEND OPERATORS TO INSPECT AIRFRAME TUBING IN THIS AR EA FOR POSSIBLE CRACKS. 1 G 7 1 3O H1CE 2001030700622 20010307 00622 EU 2001 3 7 20010130CW009 1 20010105 G 6520 365A33600501 GEARBOX AEROSP SA365 SA365N1 8680668 EU TMECA ARRIEL ARRIEL1C 60030 NE TAIL ROTOR FAILED B E ENGINE SHUTDOWN O OTHER IN INSP/MAINT 1 SW 07 911UF M539 6338 5065 INITIAL GRND RUN-UP, AFTER MJR INSP, A T/R GBX FAILURE WAS EXPERIENCED AFTER APPROX 15-20 MINUTES. AC JERKED SEVERAL T IMES ALONG THE YAW AXIS, WITH NR1 ENG RUNNING AT 68%NG AND NR2 AT 65%NG AN UNUSUAL NOISE WAS HEARD FRM TAIL ROTOR, SHUT DOWN WAS INITIATED, NOISE WORSENED. ROTOR BREAK WAS APPLIED WITHIN 10 REV OF COMING TO COMPLETE STOP FRM COAST DWN WI TH ROTOR BREAK APPLIED, LOUD SQUEALING AND GRINDING NOISE WAS EMITTING FROM THE TAIL ROTOR AND COAST DWN CAME TO A RAPID BUT NOT SUDDEN STOP. INITIAL INSP REVEALED METAL PARTICLES ON TAIL ROTOR CHIP PLUG, OIL AND SPREAD FLEX COUPLING AT TH E TAIL ROTOR OUTPUT FLNG FROM MAIN GBX. AFTER TR DWN & INSP, OUTER BRG OF INPUT HSG WAS DRY, GBX OIL LEVEL WAS FULL. 1 G 7 2 3U 3 U H10EU E19EU 2001040900111 20010409 00111 2001 4 9 20010202CW002 4 20010112 G 3100 4059013 PANEL DOUG MD11 MD11 3023602 NM COCKPIT INOPERATIVE D J A DUMP FUEL UNSCHED LANDING B SMOKE/FUMES/ODORS/SPARKS CL CLIMB 1 WP 03 105EV 48544 PILOT REPORTED ELECTRICAL BURNING ODOR DURING CLIMB, A IL 300, SMOKE APPEARED IN THE COCKPIT CAUSED FUEL DUMPED AND AIR RETURNED TO LAX. MAINTENANCE AND INSPECTION COCKPIT INDICATORS ALL C/B ARE CLOSED OPEN OVHD PANEL, MAINT PANEL AND AVIO NICS PANEL, EXAMINED ALL COMPARTMENT, IND ALL CONDITIONS ARE NORMAL, NO BURN SIGN WAS FOUND. REVIEW LAST FLIGHT FAULT, REPLACED SYSTEM CONTROL PANEL FOR SAFETY AND MAINTENANCE PREVENTION. 2 L 7 3 4F RT A22WE 2001050200033 20010502 00033 CE 2001 5 2 20010205CW004 1 20010105 G 5740 50110231 FITTING CESSNA 402 402C 207590R CE CONT O520 TSIO520VB 17040 SO MCAULY 3AF32C 3AF32C505 GL WING SPAR CORRODED D K NONE O OTHER IN INSP/MAINT 1 NE 05 401TJ 3000 402C0109 AFT SPAR REAR TOP WING ATTACH FITTING CORRODED. INSTALLED NEW FITTING. 1 L 7 2 3O 3 O A7CE E8CE 5 C P22EA 2001050200034 20010502 00034 SO 2001 5 2 20010205CW005 2 20010205 G 8530 637837 VALVE SPRING CESSNA 402 402C 207590R CE CONT O520 TSIO520VB 17040 SO NR 4 CYLINDER BROKEN D K NONE O OTHER IN INSP/MAINT 1 SW 99 305AT 1354 402C0030 519128 DURNING DETAILED INSPECTION OF LEFT ENGINE, COMPRESSION CHECK OF NR4 CYLINDER REVEALED LOW COMPRESSION. APPROX 80/20, U PON FURTHER INSPECTION THE OUTER SPRING OF THE INTAKE VALVE WAS FOUND TO BE BROKEN. 1 L 7 2 3O 3 O A7CE E8CE 2001050200035 20010502 00035 CE 2001 5 2 20010205CW006 1 20010205 G 7714 C6680160107 TACHOMETER CESSNA 402 402C 207590R CE INSTRUMENT PANEL MALFUNCTIONED D K NONE O OTHER IN INSP/MAINT 1 SW 01 2711X 94 402C0116 LEFT ENGINE TACH NEEDLE WOULD NOT PROCEED BEYOND 2300 RPM WHEN ENGINE WAS ACTUALLY AT 2700 RPM. 1 L 7 2 3O A7CE 2001050200036 20010502 00036 CE 2001 5 2 20010205CW007 1 20010116 G 2434 OHC315E ALTERNATOR CESSNA 172 172M 2072418 CE LYC O320 AEIO320E1B 41508 EA ENGINE SEPARATED D K NONE O OTHER IN INSP/MAINT 1 SW 01 9627Q 400 17265711 OHC ALTERNATOR, BOLTS HOLDING HOUSING TOGETHER, 2 BACKED OUT, LEFT HANGING BY INTACT SAFETY TO 3RD BOLT. 1 H 7 1 3O 3 O NT 3A12 1E12 2001050200037 20010502 00037 SO 2001 5 2 20010205CW008 2 20010115 G 7414 ROTOR SLICK CESSNA 210 210L 2073448 CE CONT O520 IO520L 17032 SO MAGNETO BROKEN D K NONE O OTHER IN INSP/MAINT 1 SO 15 93111 637 637 99061927 21060266 295010R ROTOR BROKE AT CAM AND GEAR LOCATION/DRIVE GEAR. 1 H 7 1 3O 3 O 3A21 E5CE 2001050200039 20010502 00039 SO 2001 5 2 20010205CW010 1 20010110 G 7160 87327002 VALVE PIPER PA28 PA28161 7102803 SO CARB AIR BOX WORN D K NONE O OTHER IN INSP/MAINT 1 NM 13 514MS 288316099 AIR VALVE IN CARB AIR BOX HAS BEEN REPLACED 3 TIMES WITH T/S : 1/327.3, 2/622.7, 3/186.4 ALL 3 REPLACEMENTS DUE TO WORN OR BROKEN ACTUATOR LEVER. THIS LEVER WAS ORIGINALLY A STEEL PART THAT SEEMED TO LAST FOREVER. THE AL APPEARS TO BE TO O SOFT. SUSPECT WHEN IT IS WELDED TO THE FHAFT ANY HEAT TREATMENT PRESENT, IS LOST. 1 L 7 1 3O 2A13 2001030700690 20010307 00690 2001 3 7 20010205CW011 4 20010104 G 2210 761039 TRIM SWITCH CENTURY PIPER PA31 PA31310 7103103 SO LYC O540 TIO540A2B 41532 EA PILOT YOLK SHORTED D A UNSCHED LANDING F FLT CONT AFFECTED CL CLIMB 1 CE 01 9007Y 3111 RL55061 AFTER TAKEOFF AUTOPILOT TRIM PITCHED UP. PILOT RETURNED TO AIRPORT AND HAD SAFE LANDING. FOUND TRIM SWITCH IN PILOTS Y OLK SHORTED OUT. FOUND TWO WIRES TOUCHING, CAUSING PITCH UP. RESOLDERED CONNECTOR AND INSULATED FROM OTHER TERMINALS. 1 L 7 1 3O 3 O RT A20SO E14EA 2001030700571 20010307 00571 SW 2001 3 7 20010205CW012 1 20010117 G 5302 206033004143 MOUNT BELL 206 206L3 1182108 SW TAIL BOOM CRACKED D K NONE O OTHER IN INSP/MAINT 1 SW 99 64PJ 6177 51100 CRACK FOUND UNDER TAIL ROTOR GEARBOX AT AFT, RIGHT, MOUNT HOLE. CRACK WAS NOT SEEN UNTIL GEARBOX WAS REMOVED TO PERFORM ASBCRACK WAS ONE INCH LONG, GOING FOR AND AFT THRU HOLE. 1 G 7 1 3U H2SW 2001030600071 20010306 00071 CE 2001 3 6 20010205CW013 1 20010109 G 2910 2407003487 HYDRAULIC LINE LEAR 25 25D 5170514 CE GE CJ610 CJ6108 30006 NE TAILCONE CHAFED D K NONE O OTHER IN INSP/MAINT 1 SW 05 25HF 295 PILOT LOST HYDRAULIC PRESSURE IN FLIGHT. INSPECTION REVEALED HYDRAULIC PRESSURE LINE FROM LEFT ENGINE TO AUXILLARY HYDR ALUIC PUMP MANIFOLD LINE, CHAFFED AT CLAMP, RECOMMENDED REMOVING CLAMPS ON THIS SPECIFIC HYDRAULIC LINE ON AIRCRAFT WITH THE SAME HYDRAULIC SYSTEM SETUP. 2 L 7 2 4J 4 J A10CE 1E16 2001032200117 20010322 00117 2001 3 22 20010205CW014 4 20010115 G 2561 KS9P0101105 LIFE VEST CELLS WORN B KQ1R K NONE O OTHER IN INSP/MAINT 1 EA 07 LIFE VEST FAILED TO MEET MFG RECOMMENDED TWO SDI CELL TEST. LIFE VEST DATE OF MFG JUNE 1983. FAIR WEAR AND TEAR 2001032200118 20010322 00118 2001 3 22 20010205CW015 4 20010105 G 2561 KS9P0101 LIFE VEST CELLS WORN B KQ1R K NONE O OTHER IN INSP/MAINT 1 EA 07 LIVE VEST FAILED MFG RECOMMENDED PSI TEST.NOVEMBER 1982/ FAIR WEAR AND TEAR. 2001030700573 20010307 00573 CE 2001 3 7 20010205CW016 1 20010104 G 5531 2707 RIB BBAVIA 8 8KCAB 2110612 CE VERTICAL STAB CRACKED B K NONE O OTHER IN INSP/MAINT 1 GL 21 68ND 2760 2760 66892 DURNING ANNUAL INSPECTION , TAIL FIN FABRIC WAS FOUND BUCKLING APPROX 1 INCH AFT OF TOP LEADING EDGE. UPON FABRIC REMOV AL FOR HIDDEN DAMAGE INSPECTION THE FIN RIB WAS FOUND TO BE CRACKED AND BUCKLED AT FWD ATTACHING WELD. FURTHER INSPECTI ON REVEALED AFT ATTACHING WELD TO BE CRACKED ALSO, SUSPECTED CAUSE TO BE EXCESSIVELY TIGHTENED DRAG WIRES. 1 H 7 1 3O A21CE 2001030700576 20010307 00576 SO 2001 3 7 20010205CW019 1 20010116 G 5753 BEARING GULSTM G1159 G1159B 3953535 SO LT FLAP TRACK BROKEN B K NONE O OTHER IN INSP/MAINT 1 CE 01 4NR 185 255 NOTICED INBOARD ROLLER BEARING ON LEFT FLAP TRACK, B, WAS MISSING THE OUTER CASING AND BEARING...ONLY STUD REMAINED, CAU SE IS UNKNOWN. RECOMMEND THAT ROLLER BEARINGS ARE VISUALLY INSP AT EACH PRE-FLIGHT INSPECTION AND MOVED WITH FINGERS TO CHECK FOR BINDING. NEW ROLLER/PN 1159SCC22821 WHICH SUPERCEEDS THE 1159CC2289 PURGED STOCK OF -9 BEARINGS. 2 L 7 2 4F RT A12EA 2001030700582 20010307 00582 CE 2001 3 7 20010206CW003 1 20010108 G 3720 C6685090101 INDICATOR CESSNA 182 182R 2072731 CE INSTRUMENT PANEL READS LOW B K NONE O OTHER IN INSP/MAINT 1 EA 21 4776T 4169 R18201762 WHILE COMPLYING WITH AD, 3.5 MINIMUM VACUUM COULD NOT BE OBTAINED, EVEN AT SEA LEVEL. TROUBLESHOOTING REVEALED VACUUM I NDICATOR WAS 2-2 1/2 IN HG LOW AND REGULATOR HAD BEEN MIS-ADJUSTED. INSTALLED NEW GAGE, WHICH WAS CALIBRATED, AND RESE T REGULATOR DOWN. STANDBY SYSTEM RETESTED, OK. 1 L 7 1 3O NT 3A13 2001030700678 20010307 00678 CE 2001 3 7 20010206CW005 1 20010112 G 5330 101120108601 SKIN BEECH 200 200BEECH 1152920 CE LT WING DEBONDED B K NONE O OTHER IN INSP/MAINT 1 GL 23 25KA BB783 LEFT WING UPPER INBOARD SKIN, ABOVE AUX. FUEL TANK, DEBONDING. INSTALLED DOUBLER. 1 L 7 2 4T A24CE 2001030700585 20010307 00585 EA 2001 3 7 20010206CW006 2 20010111 G 8530 LW16740 EXHAUST VALVE LYC BEECH 80 65A80 1152808 CE LYC O720 IO720A1B 41546 EA CYLINDER BROKEN B K NONE O OTHER IN INSP/MAINT 1 GL 15 134BA 216 LD202 147554A EXHAUST VALVE BROKEN IN HALF. 1 L 7 2 3O 3 O 3A20 1E15 2001030700587 20010307 00587 WP 2001 3 7 20010206CW007 2 20010115 G 7320 254911842 FUEL CONTROL GARRTT GULSTM 690TP 690A 0141722 SW GARRTT TPE331 TPE33110 01514 WP RT ENG MALFUNCTIONED B K NONE O OTHER IN INSP/MAINT 1 SO 03 81448 337 11327 P79656 WHILE DOING OVERSPEED GOVERNOR CHECK, ENGINE RPM STAYS ABOVE TAKEOFF, PROP GOVERNOR HIGH, AND WILL NOT REDUCE WHEN POWER LEVER AND CONDITION LEVER ARE RETARDED. THIS CONDITION ALSO PREVENTS THE PROP FROM COMING OFF THE LOCKS. TROUBLE SHOO TING HAS DETERMINED THAT THE INLET SENSOR AND THE PROP GOVERNOR ARE NOT THE CAUSE OF THIS MALFUNCTION ANDTHE FUEL CONTRO L IS, INDEED THE PROBLEM. REPLACED FUEL CONTROL, RAN AND ADJUSTED AS REQUIRED. 1 H 7 2 3T 4 T 2A4 E4WE 2001030700591 20010307 00591 SO 2001 3 7 20010206CW008 1 20010111 G 3242 1331317 STATOR EMB 120 EMB120 3260201 SO BRAKE ASSY CRACKED B K NONE O OTHER IN INSP/MAINT 1 SO 05 2579 BRAKE ASSEMBLY PN2-1661 FAILED PREMATURELY. NR 2 STATOR CRACKED THROUGH AT 1 RELIEF HOLE, BINDING ON TORQUE TUBE.NOTE: O EM PARTS INSTALLED IN BRAKE ASSEMBLY AND THE MOST RECENT BRAKE CONFIGURATION PN 2-1661. 2 L 7 2 4T RT A31SO 2001032200119 20010322 00119 2001 3 22 20010206CW010 4 20010113 G 2564 LIFE RAFT HOOVERIND DEFECTIVE B K NONE O OTHER IN INSP/MAINT 1 SO 19 L301 LIFE RAFT RECEIVED IN PACKAGED CONDITION. THE PACKAGE WAS OPENED AND FOUND THAT THE MOORING LINE WAS NOT CONNECTED TO T HE INFLATION VALVES PULL CABLE. WITHOUT MOORING LINE BEING CONNECTED TO THE INFLATION VALVES PULL CABLES, INFLATION OF THE LIFE RAFT WOULD NOT BE POSSIBLE, IF THE MOORING LINE WAS PULLED DURING A DEPLOYMENT. MAINTENANCE MANUALS SHOULD HA VE ATTENTION OF WORKING PERSONNEL. 2001041000005 20010410 00005 EU 2001 4 10 20010206CW012 1 20010115 G 6730 AC67244 SERVO DUNLOP AEROSP AS355 AS355F1 8680810 EU TAIL ROTOR CRACKED B K NONE O OTHER IN INSP/MAINT 1 NM 07 658 CRACKED DETECTED ON LOWER END OF SERVO BODY ABOVE END. CAP EDDY CURRENT TESTING. 1 G 7 2 3U H11EU 2001030700572 20010307 00572 EA 2001 3 7 20010206CW014 1 20010108 G 2752 BEARING EATON CNDAIR CL600 CL6002B19 EA FLAP ACTUATOR FAILED B K NONE O OTHER IN INSP/MAINT 1 GL 09 1385 THRUST BEARING FAILURE DUE TO LACK OF LUBRICATION AND POSSIBLE PRE-LOAD CONDITION. 2 L 7 2 4F RT A21EA 2001030700597 20010307 00597 SW 2001 3 7 20010207CW001 1 20010119 G 5320 206033110189 STIFFENER BELL 206 206L4 1182110 SW FUSELAGE CRACKED D K NONE O OTHER IN INSP/MAINT 1 SW 19 2036F 1169 52123 CRACK IN TOP OF RIGHT AFT VERTICAL TUNNEL FWD OF BOX BEAM. CRACK WAS FOUND IN THE RADIUS OF THE 206033110189 STIFFENER . MAY BE PRELOAD PROBLEM. 1 G 7 1 3U NC H2SW 2001030700598 20010307 00598 EA 2001 3 7 20010207CW002 2 20010122 G 7414 BL68291013 SHAFT D6LN3200 PIPER PA31 PA31350 7103110 SO LYC O540 TIO540J2BD 41532 EA MAGNETO LOOSE B K NONE O OTHER IN INSP/MAINT 1 SO 15 59905 364 J199901GR 317652135 THE GEAR AND SHAFT WERE FOUND LOOSE AND RETAINER WASHER WAS LOOSE AND RUBBING ON COIL FINGER. 1 L 7 2 3O 3 O A20SO E14EA 2001030700626 20010307 00626 CE 2001 3 7 20010209CW007 1 20010111 G 5412 05530311 FIREWALL CESSNA 172 172R 2072401 CE LYC IO360 IO360L2A EA FUSELAGE CRACKED D K NONE O OTHER IN INSP/MAINT 1 SW 99 9421Z 882 17280267 FOUND 1.8 IN LONG CRACK IN FIREWALL. CRACK IS LOCATED BEHIND COWL SHOCKMOUNT BRACKET AT RIGHT FIREWALL STEP. REPAIRED CRACK IN ACCORDANCE WITH SB. 1 H 7 1 3O 3 O NT 3A12 1E10 2001040900497 20010409 00497 CE 2001 4 9 20010209CW009 1 20010209 G 5410 505403042 BEAM CESSNA 421 421C 2076016 CE NACELLE CRACKED D K NONE O OTHER IN INSP/MAINT 1 SW 99 26603 0862 AC TOTAL TIME 4800 HRS , CRACK NOTED ON BOTH BEAMS RIGHT AND LEFT OUTBOARD SIDE OF EACH ENGINE. BOTH CRACKS APPROX 1.5 IN LONG. CRACKS IN RADIUS OF BEND OF TOP STRAP OF BEAM ASSEMBLY NEAR JUNCTION OF FORE AND AFT RUNNING ENGINE MOUNT BEAM S. 1 L 7 2 3O A7CE 2001032200121 20010322 00121 EU 2001 3 22 20010212CW002 1 20010102 G 5600 F10AZ60200AZ WINDSHIELD AMD FALC10 FALCON10 2730101 EU GARRTT TFE731 TFE731* 01518 WP RT FWD WINDSHLD CRACKED G O OTHER O OTHER CR CRUISE 1 GL 19 87TH 5660 178 AIRCRAFT DEPARTED CMI IN VFR CONDITIONS AND DURING CLIMB OUT THROUGH 15,000 FT, THE CO-PILOT''S FWD WINDSHIELD OUTER PAN E CRACKED. PILOT ELECTED TO RETURN TO CMI. AIRCRAFT LANDED WITHOUT INCIDENT. 2 L 7 2 4F 4 F A33EU E6WE 2001040900447 20010409 00447 2001 4 9 20010212CW003 4 20010108 G 3423 WIRE BEECH 36 A36 1151604 CE COMPASS CHAFED D K NONE O OTHER IN INSP/MAINT 1 SW 99 128JG E3332 AC FROM FACTORY WITH 18.4 HRS, DURING AN AVIONICS INSTALLATION, DISCOVERED WIRES FOR THE MAGNETIC COMPASS THAT PASS BETW EEN THE GLARESHIELD AND TOP OF INSTRUMENT PANEL ROUTED SO THEY WERE SANDWICHED AND CHAFING BETWEEN THE TWO. RELIEF SPOT IN TOP OF INSTRUMENT PANEL TO ROUTE OTHER WIRING THAT GOES TO GLARESHIELD, BELIEVE TO BE NEEDED ROUTING FOR COMPASS. DU E TO LENGTH OF THE WIRES BEING SHORT, COMPASS WIRES WILL NOT MAKE IT THROUGH THE RELIEFAND BE ABLE TO BE CONNECTED. WE FEEL THESE WIRES WERE MISROUTED DUE TO A MANUFACTURING ERROR. SUSPECT THE WIRE LOOM TO BE TOO SHORT. 1 L 7 1 3O 3A15 2001030600078 20010306 00078 EA 2001 3 6 20010213CW005 1 20010105 G 2752 601RR9310318 ACTUATOR CNDAIR CL600 CL6002B19 EA TE FLAPS LACK OF LUBE B K NONE O OTHER IN INSP/MAINT 1 GL 09 THRUST BEARING FAILURE DUE TO LACK OF LUBRICATION AND POSSIBLE PRE-LOAD CONDITION. 2 L 7 2 4F RT A21EA 2001032200126 20010322 00126 CE 2001 3 22 20010214CW001 1 20010118 G 2140 FR81D943ELB4500 HEATER BEECH 58 58 1152740 CE CONT O520 IO520* 17032 SO ERODED B DFZR O OTHER B SMOKE/FUMES/ODORS/SPARKS CR CRUISE 1 EA 09 922DN 11500 TH922 PILOT SMELLED CABIN HEATER GASES IN AIRCRAFT. INSPECTED FOUND CABIN HEATER(B4500) CERMA KOTE, COMBUSTION CAN WITH HOLE IN AFT AREA OF CAN BY REAR DRAIN. INSTALLED REBUILT HEATER. 1 L 7 2 3O 3 O 3A16 E5CE 2001032700196 20010327 00196 GL 2001 3 27 20010214CW002 3 20010122 G 6114 A24182 ROD HARTZL HARTZL HCC2Y HCC2YK1 GL PITCH ROD CRACKED B W59R K NONE O OTHER IN INSP/MAINT 1 WP 07 AW696 AW696 OBSERVED CRACK-LINE INDICATION DURING MAG PARTICLE TESTING. INDICATION APPEARS TO BE A LAMINATION IN MATERIAL DUE TO ST RAIGHTNESS OR INDICATION. 5 C P920 2001032700197 20010327 00197 2001 3 27 20010215CW002 4 20010109 G 3421 5546257001 CONNECTOR COLLINS OUTER SHELL CORRODED D K NONE O OTHER IN INSP/MAINT 1 GL 13 2193 EXCESSIVE CORROSION BUILDS UP ON PINS OF CONNECTOR, SPECIFICALLY PINS N AND P, WHICH RESULTS IN FLAGGING. 2001032600328 20010326 00328 EA 2001 3 26 20010215CW003 2 20010116 G 8530 AEL6510212 CYLINDER PIPER PA28 PA28181 7102807 SO LYC O360 O360A4M 41514 EA HEAD UNSERVICEABLE B MW2R K NONE O OTHER IN INSP/MAINT 1 GL 17 4350G 1081 288490058 L2749236A A CRACK RUNS FROM TOP SPARKPLUG HOLE AROUND OUTSIDE EXHAUST SEAT TO TOP SPARKPLUG AND CYLINDER WILL SPLIT IN TWO PIECES. 1 L 7 1 3O 3 O 2A13 E286 2001030700639 20010307 00639 SW 2001 3 7 20010215CW004 1 20010123 G 5320 206040338009 HANGER ASSY BELL BELL 206 206B3 1181506 SW TAILBOOM BEARING MISALIGNED B K NONE O OTHER IN INSP/MAINT 1 SO 09 67330 BP36 5138 MOUNTING HOLES MISALIGNED. PART MUST BE JIG DRILLED AND INSTALLED. THE JIG WAS MISALIGNED AT INSTALLATION. 1 G 7 1 3U H2SW 2001032100095 20010321 00095 CE 2001 3 21 20010215CW005 1 20010119 G 5210 1144002369 DOOR BEECH 1900 1900C 1154161 CE PWA PT6 PT6* 52043 EA BOTTOM AT HING CRACKED B S1FR K NONE O OTHER IN INSP/MAINT 1 SO 33 500PR 5682 UC139 BOTTOM OF DOOR .5 INCH FROM HINGE ATTACH POINT 3.5IN CRACK. 2 L 7 2 4T 3 T RT A24CE E2NE 2001032600154 20010326 00154 SO 2001 3 26 20010215CW007 1 20010122 G 2910 166 SNAP RING ELECTROL 166 GULSTM G44 G44 3951502 SO FCD 6440 6440* 26003 EA CYL PISTON BROKEN D O OTHER O OTHER NR NOT REPORTED 1 NM 10 69058 105 1291 SNAP RINGS RETAINING PISTONS IN PLACE SNAPED OFF. ONE RING SHOWS SIGNS OF RUST DAMAGE. PARTS LODGED IN CYLINDER-STOPPI NG PROPER OPERATION. RESULTING IN TOTAL FAILURE OF HYDRAULIC SYSTEM AND EMERGENCY SYSTEMS.CYLINDERS WERE MODIFIED TO AC CEPT ORINGS INSTEAD OF CHEVRON TYPE SEALS. SUSPECT ORING FAILURE, RESULTING IN OVER PSI AGAINST ORING ON RETURN PISTON, FORCING SNAP RING TO FAIL. 1 H 7 2 3I 3 I O A734 E216 2001032600311 20010326 00311 WP 2001 3 26 20010220CW001 1 20010107 G 6100 54H6077 PROPELLER CVAC 340 340CVAC 242270A WP ALLSN 501D 501D22 03005 GL HAMSTD 54H 54H60 NE VLV 2 HOUSING BLOWN G O OTHER K FLUID LOSS TO TAKEOFF 1 GL 23 391FL 841 278 550640 239764 AIRCRAFT WAS COLD SOAKED, OUTSIDE TEMPERATURE BEFORE DEPARTURE WAS 15 DEGREES. SUBMITTER FEELS THIS WAS A CONTRIBUTING FACTOR TO THIS SEAL BEING DEFECTIVE. COMPANY INITIATED PROCEDURES NOT TO CHANGE PROP BLADE ANGLE UNTIL MINIMUM OF 40 DE GREE OIL TEMPERATURE IS OBTAINED, DEFECTIVE SEAL REPLACED. AC RETURNED TO SERVICE. 2 L 7 2 4R 4 T 6A6 E282 6 C P906 2001032600327 20010326 00327 CE 2001 3 26 20010222CW001 1 20010125 G 7602 S12345 LEVER CESSNA 177 177B 2073708 CE LYC O360 O360* 41514 EA PANEL BROKEN D K NONE O OTHER IN INSP/MAINT 1 SW 01 16021 3292 17702479 MIXTURE CONTROL BROKE ON GROUND RUN UP. BREAK APPEARS TO BE DEFECT IN MATERIAL. 1 H 7 1 3O 3 O A13CE E286 2001041000007 20010410 00007 SO 2001 4 10 20010222CW002 1 20010123 G 2410 635796 COUPLER CONT PIPER PA34 PA34200T 7103406 SO CONT O360 TSIO360EB 17025 SO RT ENGINE FAILED D O OTHER H ELECT. POWER LOSS-50 PC CR CRUISE 1 SW 99 304CW 170 306527H 347870153 306527H RT ALTERNATOR FAILED IN FLIGHT AT NIGHT. ALTERNATOR FAILURE CAUSED BY DRIVE COUPLER FAILURE. 1 L 7 2 3O 3 O A7SO E9CE 2001032600329 20010326 00329 EU 2001 3 26 20010222CW003 1 20010118 G 7920 3033356 FUEL FILTER PILATS PC12 PC1245 EU PWA PT6 PT6A66 52043 NE DISCHG FUEL FLTR UNBONDED G K NONE O OTHER IN INSP/MAINT 1 CE 05 302PB 302 UPON 100 HOUR INSPECTION, REPLACEMENT OF ENGINE DISCHARGE FUEL FILTER. NEW FILTER FROM 100 HR KIT WAS NOT GLUED TOGETHE R. THE TOP AND BOTTOM OF FILTER WERE LOOSE AND COULD BE PULLED OFF. 1 L 7 1 3T 4 T RT A78EU E26NE 2001041000008 20010410 00008 EA 2001 4 10 20010222CW005 2 20010109 G 7414 103571651 COIL 56LSC200 GULSTM 500 500B 0141106 SW LYC O540 IO540* 41532 EA MAGNETO DAMAGED G K NONE O OTHER IN INSP/MAINT 1 SW 15 411JF 387 H279909ER 101435 269118 MAGNETO REMOVED FROM UNSERVICEABLE ENGINE. DURING INSPECTION TO DETERMINE SERVICEABILITY, FOUND COIL WIRE BROKEN AT PO INTS END JUST BEFORE SPADE CONNECTOR. 1 H 7 2 3O 3 O 6A1 1E4 2001032200129 20010322 00129 GL 2001 3 22 20010222CW006 1 20010110 G 2750 F659 TUBE AMTR VANS VANSRV6 05605AZ GL LYC O320 IO320* 41508 EA BELOW FLAP BROKEN D K NONE O OTHER IN INSP/MAINT 1 CE 07 3891P 117 23736 L1220627 FLAP ROD BROKE JUST BELOW UPPER BALL JOINT CAUSING FLAP TO RETRACT ON LANDING. THIS PART IS .3125 X .058 6061 T6 ALUMIN UM TUBING AND APPEARS TO BE WEAK AFTER THREADS ARE CUT IN ENDS. 1 L 7 1 3O 3 O EXPA1L71 1E12 2001032200130 20010322 00130 CE 2001 3 22 20010222CW009 1 20010108 G 8011 PM2401 STARTER CESSNA 172 172S 2072439 CE LYC IO360 IO360L2A EA ENGINE INOPERATIVE D O OTHER O OTHER IN INSP/MAINT 1 NM 03 949SP 773 773 172S8145 L2812051A PILOT ATTEMPTED ENGINE START, STARTER WOULD NOT ROTATE. MAINTENANCE FOUND STARTER HAD TWO TERMINALS MELTED WHERE THAT A TTACH TO COMMUTATOR BRUSHES. REPLACED STARTER, OPERATIONAL CHECKED SAT. 1 H 7 1 3O 3 O NT 3A12 1E10 2001032200131 20010322 00131 2001 3 22 20010222CW010 4 20010119 G 2310 551202621 STRINGER CESSNA 500 550 2076604 CE AFT BAG COMPT CRACKED C U1CM K NONE O OTHER IN INSP/MAINT 1 SW 17 26496 5215 5500607 DURING SCHEDULED INSPECTION, IT WAS FOUND THAT SUPPORT PN1455078519 HAD CAUSED THE STRINGER AT/FS428.5/ TO CRACK AND PUL L ATTACHING RIVETS LOOSE. THE AC, AT FACTORY, HAD ADDITIONAL EQUIPMENT RACKS INSTALLED. IT SHOULD BE NOTED THAT CLOSE R ATTENTION SHOULD BE PLACED ON INSPECTING THESE ATTACHMENT POINTS AS THEY MAY OR MAY NOT BE INCLUDED IN AREAS TO LOOK A T DURING SCHEDULED TIMES. 1 L 7 2 4F A22CE 2001032200133 20010322 00133 SW 2001 3 22 20010223CW001 1 20010117 G 5711 SPAR BBAVIA 7 7AC 2110102 SW CONT C90 C9012F 17009 SO MCAULY 1B90 1B90* GL 7TH RIB IB END CRACKED D K NONE O OTHER IN INSP/MAINT 1 GL 15 1205E 4262 7AC4762 45450712 CM7343 DURING INSPECTION, CRACK FOUND ORIGINATING FROM RIB NAIL RUNNING HORIZONTAL. SPAR INSTALLED 5/17/59 1 H 7 1 3O 3 O A759 E252 5 N P842 2001032200134 20010322 00134 EA 2001 3 22 20010223CW002 2 20010105 G 7322 25765362 SERVO CESSNA 172 172S 2072439 CE LYC IO360 IO360L2A EA FUEL SERVO VAPOR LOCK D O OTHER R PARTIAL RPM/PWR LOSS CR CRUISE 1 NM 03 567JW 163 70217008 172S8187 L2822651A ENGINE START, RUN UP AND TAKEOFF NORMAL, WHEN THROTTLE WAS RETARDED, ENGINE BEGAN TO RUN ROUGH WITH POPPING OUT EXHAUST . MIXTURE WAS READJUSTED WITH NO CHANGE. ADVANCED THROTTLE AND RETURNED TO HOME STATION. LANDING UNEVENTFUL. ENGINE RUN UP AFTER ENGINE HAD COOLED COMPLETELY INDICATED NO DEFECTS, ALL OPERATION NORMAL. MAINTENANCE INSPECTION OF ENGINE F OUND NO DEFECTS. CONCLUDED THAT FUEL VAPORIZATION CAUSED ROUGHNESS AT IDLE IN FLIGHT WITH INCREASED TEMPS, RETARDED THR OTTLE AND REDUCED AIRFLOW THRU ENG AS THIS HAS BEEN CONTINUING PROBLEM. COOLING MODIFICATIONS HAVE BEEN ACCOMPLISHED ON AC ENGINE TO INCLUDE INVERTING FUEL FLOW DIVIDER. 1 H 7 1 3O 3 O NT 3A12 1E10 2001032200143 20010322 00143 SO 2001 3 22 20010223CW003 1 20010131 G 3221 89137041 MOUNT PIPER PA46 PA46350P SO DRAGLNK FT AREA BROKEN B HE4R K NONE O OTHER IN INSP/MAINT 1 SO 11 DRAGLINK FITTING AT ENGINE MOUNT BROKEN LOOSE DUE TO HARD LANDING. NEEDS VISUAL INSPECTION OFTEN, POSSIBLE REINFORCEMENT FROM MFG. 1 L 7 1 3O RT A25SO 2001032200197 20010322 00197 CE 2001 3 22 20010223CW005 1 20010123 G 7722 2870 PROBE BEECH 58 58P 1152744 CE CONT O520 TSIO520LB 17040 SO NR1 CYL BROKEN D K NONE O OTHER IN INSP/MAINT 1 NE 01 4269S 650 TJ96 237296R CUSTOMER REPORTED NR1 EGT ON HIS GEM 1200, INOPERATIVE. UPON REMOVAL OF EGT PROBE, ABOUT HALF OF THE PROBE TIP WAS BROK EN OFF AND MISSING. THE ONLY PATH OF EXIT IS THROUGH THE TURBO CHARGER. FURTHER INSPECTION OF THE TURBO CHARGER REVEAL ED FOD DAMAGE TO THE VANES OF THE EXHAUST TURBINE. THE PROBE WAS REPLACED WITH NEW. THE TURBO WAS REPLACED WITH AN O/ H UNIT.NOTE: THESE TURBOS NOT ONLY SUPPLY BOOST TO ENGINE, BUT ALSO PRESSURIZE CABIN AT ALTITUDE. RECOMMEND AN INSPECT ION INTERVAL OR TIME/LIFE LIMIT. 1 L 7 2 3O 3 O A23CE E8CE 2001032200202 20010322 00202 SO 2001 3 22 20010227CW005 1 20010124 G 2913 HYC5005 POWERPACK PIPER PA28 PA28R201 7102816 SO LYC O360 IO360C1C 41514 EA MOTOR INOPERATIVE B PAID O OTHER O OTHER LD LANDING 1 EA 13 6320C 6861 28R7837157 WHEN LANDING GEAR WAS SELECTED DOWN, GEAR DID NOT EXTEND. EXTENDED LANDING GEAR USING EMERGENCY PROCEDURES. GEAR EXTEN DED AND LOCKED. LANDING MADE WITHOUT INCIDENT. FOUND HYDRAULIC POWER PAK MOTOR INOPERATIVE. INSTALLED OVERHAULED HYDR AULIC POWER PAK. GEAR RETRACTION TEST COMPLETED SATISFACTORY. 1 L 7 1 3O 3 O 2A13 1E10 2001032200205 20010322 00205 CE 2001 3 22 20010227CW007 1 20010202 G 8010 S1577 SOLENOID CESSNA 210 210N 2073453 CE CONT O520 TSIO520* 17040 SO STARTER SHORTED B BOE2 K NONE O OTHER IN INSP/MAINT 1 GL 19 7235F 21063038 AIRCRAFT CAME IN WITH DEAD BATTERY, FOUND BATTERY OVERHEATED. PUT TEST BATTERY IN AND IMMEDIATELY WENT HIGH DISCHARGE. WHEN STARTER WIRE REMOVED DISCHARGED STOPPED. STARTER WAS SHORTED OUT. UPON FURTHER INVESTIGATION, FOUND STARTER SOLE NOID CONTACTS WERE WELDED TOGETHER, CAUSING STARTER TO ALWAYS BE ON THUS SHORTING IT OUT. INSTALLED NEW STARTER RELAY, OVERHAULED STARTER AND INSTALLED NEW BATTERY. AIRCRAFT RUNUP AND ALTERNATOR CHECK OK. 1 H 7 1 3O 3 O 3A21 E8CE 2001032000104 20010320 00104 SO 2001 3 20 20010227SG001 2 20010129 G 7414 BL3492606 MAGNETO BEECH 95 95B55 1152729 CE CONT O470 IO470L 17026 SO ENGINE FAILED B K NONE L NO TEST IN INSP/MAINT 1 SW 99 931E 256 TC1009 1553646L PILOT REPORTED THAT THE MAGNETO WOULD FAIL ON RUN UP. TROUBLESHOT THE SYSTEM AND FOUND THE MAGNETO INTERIOR COATED IN BRONZE LIKE METAL FLAKES. DETERMINED THAT THE BLOCK BEARING HAD FAILED AND THE ROTOR HAD CHAFED THE POINTS DOWN. THE MA GNETOS HAD BEEN OVERHAULED BY TCM UNDER THEIR WO NO P53955. DISTRIBUTOR BLOCK PN 10-391586 1 L 7 2 3O 3 O RT 3A16 3E1 2001050200030 20010502 00030 SO 2001 5 2 20010227SG002 2 20010131 G 7314 6467681A1R PUMP TSIO520M CESSNA 206 TU206G 2073357 CE CONT O520 TSIO520M 17040 SO ENGINE LEAKING D K NONE K FLUID LOSS IN INSP/MAINT 1 SW 99 7PAAL 451 818076R U20604718 818076R ENGINE DRIVEN FUEL PUMP BEGAN LEAKING FROM SHAFT SEAL. 1 H 7 1 3O 3 O A4CE E8CE 2001050200032 20010502 00032 SO 2001 5 2 20010227SG004 2 20010115 G 7314 6467681A1 PUMP TSIO520M CESSNA 206 TU206G 2073357 CE CONT O520 TSIO520M 17040 SO ENGINE LEAKING D K NONE K FLUID LOSS IN INSP/MAINT 1 SW 99 HCBXK 15 U20604404 FUEL LEAK FROM PUMP DRAIN 1 H 7 1 3O 3 O A4CE E8CE 2001040900135 20010409 00135 NE 2001 4 9 20010227SG005 2 20010201 G 7314 31042681 PUMP CESSNA 500 550 2076604 CE PWA JT15 JT15D4 52112 NE ENGINE FAILED B K NONE O OTHER IN INSP/MAINT 1 SW 99 2GG 1848 PC 5500286 PCE70020 ENGINE OIL PUMP PN: 3104268-1 SN; A1178 WITH 1848.2 HOURS SINCE INSTALLATION FAILED. THE PUMP SEIZED AND CAUSED SHAFT TO SHEAR. PUMP WAS REPALCED WITH OVERHAULED UNIT. 1 L 7 2 4F 4 F A22CE E1NE 2001032200209 20010322 00209 CE 2001 3 22 20010228CW001 1 20010206 G 2840 535942 RESISTOR CESSNA 172 172R 2072401 CE LYC O360 IO360A1C 41514 EA RT SENDER DEFECTIVE B K NONE O OTHER IN INSP/MAINT 1 SO 15 434ER 244 17280655 DURING PHASE 1 INSPECTION, RT FUEL QUANTITY READING WAS ERRATIC. THE SHAFT BEARING OR SEAL WAS FOUND TO BE DEFECTIVE ON THE RT SENDER. THIS APPARENTLY ALLOWED GASOLINE INTO THE SENDER. 1 H 7 1 3O 3 O NT 3A12 1E10 2001040900229 20010409 00229 EA 2001 4 9 20010228CW002 2 20010201 G 8520 LW11026 CRANKCASE PIPER PA30 PA30 7103002 SO LYC O320 IO320B1A 41508 EA ENGINE CRACKED B K NONE K FLUID LOSS IN INSP/MAINT 1 SO 06 87CW 5168 301639 L349755A DURING ANNUAL INSPECTION, OIL LEAK NOTED AT CRANKCASE AREA FORWARD OF NR2 CYLINDER. AFTER CLEANING AN OBVIOUS 1.5 IN CR ACK WAS NOTED. ENGINE WAS REMOVED FOR REPAIRS. LT ENGINE TSMOH 1098.41, 1992 FIREWALL FORWARD, INC. 1 L 7 2 3O 3 O A1EA 1E12 2001032200210 20010322 00210 SO 2001 3 22 20010228CW003 2 20010201 G 8520 629288 CRANKCASE BEECH 35 M35 1151526 CE CONT O470 IO470C 17026 SO LT TOP CTR CRKCS CRACKED D K NONE K FLUID LOSS IN INSP/MAINT 1 SO 06 9748R 5874 D6229 DURING ANNUAL INSP, OIL LEAK NOTED AT TOP OF CRANKCASE, CLEANING AND RERUN, OIL LEAK RETURNED. FOUND 1.25 IN CRACK EXTE NDING FROM TOP CENTER CASE BOLT HOLE AT AREA WHERE FUEL FLOW DIVIDER BRACKET ATTACHES. CRACK IN NON-CRITICAL AREA AND W ITHIN CRACK LIMITATIONS EXCEPT OIL LEAK IN EXCESS. ENGINE REMOVED FOR REPAIRS/ CRANKCASE RECONDITIONED. 1 L 7 1 3O 3 O 3A15 E273 2001030700623 20010307 00623 SW 2001 3 7 20010228CW005 1 20010124 G 6420 YOKE BELL 407 407 SW ALLSN 250C 250C47B GL TAIL ROTOR OUT OF POSITION B K NONE O OTHER IN INSP/MAINT 1 NM 03 407LR 1854 53279 INBOARD BEARINGS 2EA WERE FOUND TO HAVE SHIFTED IN YOKE APPROXIMATELY .050 IN OFF CENTER. ONE YOKE BORE WAS WORN BEYOND LIMITS. 1 G 7 1 3U 3 U O H2SW E1GL 2001040900453 20010409 00453 SO 2001 4 9 20010228CW008 1 20010124 G 2140 A23D047 REGULATOR PIPER PA31 PA31350 7103110 SO LYC O540 TIO540J2BD 41532 EA HEATER LEAKING B FFSA K NONE O OTHER IN INSP/MAINT 1 AL 01 4501B 318052168 THIS FUEL REGULATOR WAS INSTALLED NEW, AND WHILE PRESSURE TESTING STATIC ON GROUND, IT WAS FOUND TO BE LEAKING FROM SCR EW ON TOP OF UNIT. 1 L 7 2 3O 3 O A20SO E14EA 2001032100132 20010321 00132 SO 2001 3 21 20010228CW010 1 20010116 G 3260 67411002 SWITCH PIPER PA28 PA28R201 7102816 SO LYC O360 IO360A1A 41514 EA LT LANDING GEAR INOPERATIVE B EASR O OTHER N FALSE WARNING LD LANDING 1 EA 23 6320C 563 28R783757 UPON EXTENSION OF LANDING GEAR, NO DOWN & LOCKED INDICATION NOTED ON LEFT LANDING GEAR. AIRCRAFT LANDED WITHOUT INCIDEN T. FOUND LEFT LANDING GEAR DOWN LIMIT SWITCH INTERMITTENT. INSTALLED NEW SWITCH. RETRACTION TEST COMPLETED SATISFACTO RY 1 L 7 1 3O 3 O 2A13 1E10 2001040900174 20010409 00174 2001 4 9 20010228CW011 4 20010201 G 2562 MN1300LR20 BATTERY ACK CESSNA 182 R182 2072734 CE LYC O540 IO540* 41532 EA ELT CORRODED B AMVR K NONE L NO TEST IN INSP/MAINT 1 CE 05 4135C 022105 R18200326 UPON INSPECTION OF ELT AND BATTERIES, WERE FOUND TO BE CORRODED AND SWELLING, THE BATTERY COMPARTMENT IS WET WITH A LIQU ID. COMPOSITION OF LIQUID UNKNOWN. ELT IS INSIDE TAIL SECTION OF AC AND NOT SUBJECT TO WATER EXPOSURE. 1 H 7 1 3O 3 O RT 3A13 1E4 2001040900228 20010409 00228 EA 2001 4 9 20010301CW001 2 20010126 G 8520 SL13790A SHAFT CESSNA 177 177A 2073706 CE LYC O360 O360* 41514 EA ENGINE ROCKERS DAMAGED D K NONE O OTHER IN INSP/MAINT 1 SO 14 70847 123 17701356 L1992336A ROUGH GRIND FINISH CAUSED ALMOST ALL 8 ROCKER ARM BUSHINGS TO WEAR AND CONTAMINATE OIL WITH BRASS, METAL PARTICLES. BUSH INGS AND ROCKER SHAFTS WERE DEFECTIVE FROM WEAR AND WERE REPLACED. 1 H 7 1 3O 3 O A13CE E286 2001030700569 20010307 00569 2001 3 7 20010301CW004 4 20010301 G 2562 E01 ELT BELL 206 206B3 1181506 SW ALLSN 250C 250C20 03013 GL CABIN CRACKED E AWTA K NONE O OTHER IN INSP/MAINT 1 WP 25 67PJ 300 3966 INSPECTING ELT, FOUND CASE TO BE IN MANY PIECES WITH CRACKS THROUGHOUT ENTIRE UNIT. PLASTIC SEEMS TO BE VERY SOFT AND B RITTLE. THIS IS SECOND ELT OF THIS MAKE AND MODEL THAT HAS BEEN FOUND IN THIS CONDITION DURING TESTING FOR NON OPERATIO N. 1 G 7 1 3U 3 U H2SW E4CE 2001032100135 20010321 00135 CE 2001 3 21 20010301CW006 1 20010130 G 3250 HM6 ROD END BEECH 90 65A90 1152908 CE PWA PT6 PT6* 52043 EA NOSE GEAR STRNG DISCONNECTED D O OTHER O OTHER TX TAXI/GRND HDL 1 SO 17 11FL 12250 LJ301 NOSE GEAR STEERING ARM BECAME DISCONNECTED DURING TAXI, SENDING AC INTO HARD RIGHT TURN. ROD END BALL AND BUSHING SEPA RATED FROM ROD END EYELET. NO ABNORMAL WEAR WAS NOTED. RECOMMEND INSTALLING LARGE DIAMETER WASHER UNDER HEAD OF BOLT F OR RETAINING ROD END EYELET IN CASE OF FAILURE. ROD END IS NOT PART OF NOSE GEAR OVERHAUL, SHOULD BE INSPECTED. 1 L 7 2 3T 3 T 3A20 E2NE 2001041000010 20010410 00010 CE 2001 4 10 20010301CW008 1 20010301 G 7920 CH48108 OIL FILTER CESSNA 210 210L 2073448 CE CONT O520 IO520* 17032 SO OIL SUMP DEFECTIVE G K NONE O OTHER IN INSP/MAINT 1 EA 23 2170S 21061131 PIECES OF SEALANT USED TO SEAL THE INLET AND OUTLET OF THE FILTER, INSIDE THE FILTER FLAKING OFF AND GOING DOWNSTREAM IN THE OIL SYSTEM. PIECES COULD GET INTO THE PRESSURE SYSTEM AND STARVE A BEARING FOR OIL. 1 H 7 1 3O 3 O 3A21 E5CE 2001032700231 20010327 00231 SO 2001 3 27 20010301CW009 1 20010301 G 7920 CH48110 OIL FILTER PIPER PA38 PA38112 7103812 SO LYC O320 O320* 41508 EA OIL SUMP FLAKING G K NONE O OTHER IN INSP/MAINT 1 EA 23 2602B 3879A0146 FOUND SEALANT MATERIAL IN OIL SUMP DURING NORMAL 50 HR OIL CHANGE. FOUND ON SUCTION SCREEN. SEALANT CAME FROM THE OIL FILTER. AREA THAT SEALS THE INLET TO THE OUTLET AREA OF THE FILTER IS FLAKING OFF AND GETTING STUCK IN THE FILTER AND O N THE OIL SUCTION SCREEN. 1 L 7 1 3O 3 O A18SO E274 2001032700232 20010327 00232 SO 2001 3 27 20010301CW010 1 20010301 G 7920 CH48110 OIL FILTER PIPER PA38 PA38112 7103812 SO LYC O235 O235* 41505 EA OIL SUMP DEFECTIVE G K NONE O OTHER IN INSP/MAINT 1 EA 23 2596E 3878A0483 SEALANT USED IN MANUFACTURE OF FILTER TO SEAL THE INLET AND OUTLET TO THE FILTER APPEARS TO BE FLAKING OFF. PIECES ARE BEING FOUND INSIDE THE FILTER ON THE PLEATS AND ON THE OIL SUMP SUCTION SCREEN. THESE PIECES COULD GET INTO THE PRESSUR E SYSTEM AND STARVE A BEARING FOR OIL. 1 L 7 1 3O 3 O A18SO E223 2001032700233 20010327 00233 CE 2001 3 27 20010301CW011 1 20010301 G 7920 CH48108 OIL FILTER CESSNA 210 T210N 2073456 CE OIL SUMP FLAKING G K NONE O OTHER IN INSP/MAINT 1 EA 23 5201A 21063305 PIECES OF THE SEALANT USED TO SEPARATE INLET AND OUTLET CHAMBERS INSIDE THE OIL FILTER ARE BREAKING OFF AND ARE BEING FO UND IN THE FILTER PLEATS AND IN THE SUMP ON THE SUCTION SCREEN. THESE PIECES COULD BLOCK AN OIL PASSAGE IN THE PRESSURE SYSTEM AND STARVE A BEARING FOR OIL. 1 H 7 1 3O 3A21 2001030500003 20010305 00003 CE 2001 3 5 20010302AP001 1 20010103 G 5712 12210624 BULKHEAD CESSNA 210 T210M 2073451 CE RT WING CRACKED B K NONE O OTHER IN INSP/MAINT 1 sw 99 6193 FOUND RIGHT WING INBOARD FLAP BELLCRANK BULKHEAD STA.54.75 CRACKED. CRACK WAS LOCATED LEFT LOWER CORNER OF BULKHEAD (LOO KING FWD) AND APPROX. 1.5 INCHES LONG. AIRCRAFT HAS ROBERTSON STOL KIT INSTALLED. SUSPECT HIGHER CABLE TENSIONS BECAUSE OF STOL KIT CONTRIBUTED TO THE CRACKING. THIS IS THE THIRD AIRCRAFT FOUND WITH THIS PROBLEM, ALL WITH SIMILAR AIRFRAME TOTAL TIME. 1 H 7 1 3O 3A21 2001030200059 20010302 00059 2001 3 2 20010302AP003 4 20010104 G 2215 275 MOUNT BEECH 36 36BEECH 1151602 CE SERVO MISINSTALLED G K NONE O OTHER IN INSP/MAINT 1 SO 13 111LJ E1822 SERVO MOUNT (KM-275) WAS FOUND INSTALLED INCORRECTLY NOT ALLOWING FULL ENGAGMENT WITH THE SERVO (KS-270). SERVO MOUNT W AS FOUND INSTALLED ON TOP OF SERVO MOUNTING SHELF AND SERVO WAS INSTALLED UNDERNEATH SERVO MOUNTING BRACKET. THE SERVO MOUNTING BRACKET (SHELF) WAS FOUND BETWEEN THE SERVO AND SERVO MOUNT. INSTALLATION INSTRUCTIONS CALLS FOR SERVO (KS-270 ) AND SERVO MOUNT (KS-270) BE INSTALLED UNDERNEATH SHELF. RESEARCH OF AIRCRAFT RECORDS DID NOT SHOW ANY MAINTENANCE THA T WOULD HAVE RESULTED IN THIS IMPROPER CONFIGURATION. SUSPECT INCORRECT INSTALLATION WAS DONE AT INITIAL INSTALLATION O F THE AUTOPILOT SYSTEM. 1 L 7 1 3O 3A15 2001030200060 20010302 00060 CE 2001 3 2 20010302AP007 1 20010109 G 8120 98510441 CHECK VALVE ALIDSG CESSNA 206 206CESSNA 2073302 CE TURBO INLET LEAKING D O OTHER K B FLUID LOSS SMOKE/FUMES/ODORS/SPARKS TX TAXI/GRND HDL 1 SW 99 PKMPP 704 704 BLO26610 U20603719 TURBO CHARGER OIL INLET DRAINS OIL INTO TURBOCHARGER AT SHUTDOWN. UPON REMOVAL AND INSPECTION, THE CHECH VALVE WAS FOUN D TO TAKE ONLY LIGHT AIR PRESSURE TO UNSEAT THE CHECK VALVE AND BLOW BOTH DIRECTIONS THROUGH THE CHECK VALVE. 1 H 7 1 3O A4CE 2001040900249 20010409 00249 CE 2001 4 9 20010302CW001 1 20010302 G 3210 3450A LANDING GEAR CESSNA 206 T206H CE MAINS COLLAPSED G O OTHER O OTHER NR NOT REPORTED 1 AL 01 7255T 4 T20608065 MAIN GEARS COLLAPSED ON FLOAT POND ENTRY / EXIT RAMP. INSPECTION FOUND RT AND LT MAIN GEAR ACTUATING CONTROL SHAFTS BRO KEN. REPLACED RT AND LT ACTUATING CONTROL SHAFTS ON MAIN GEAR ASSEMBLY. GEAR RETRACTION TESTS COMPLETED SATISFACTORY. 1 H 7 1 3O A4CE 2001040900254 20010409 00254 SO 2001 4 9 20010302CW003 2 20010108 G 7414 DRIVE GEAR CESSNA 150 150A 2071804 CE CONT O200 O200A 17020 SO MAGENTO BROKEN C K NONE W INADEQUATE Q C IN INSP/MAINT 1 WP 17 7141X 600 15059241 51063AR MAGNETO DRIVE GEAR BROKEN. BROKEN PIECE LODGED BETWEEN CAM GEAR AND GENERATOR GEAR, BREAKING GENERATOR SHAFT, DESTROYIN G GENERATOR, CAM GEAR AND OIL PUMP COVER. BOTH MAGNETO DRIVE GEARS WERE UNAPPROVED PARTS. PARTS INSTALLED. 1 H 7 1 3O 3 O 3A19 E252 2001040900077 20010409 00077 CE 2001 4 9 20010305CW004 1 20010212 G 3110 POTENTIOMETER CESSNA 172 172S 2072439 CE INSTRUMENT PANEL MISINSTALLED B ESMR K NONE W INADEQUATE Q C IN INSP/MAINT 1 SO 11 563SP 172S8416 REPORT THAT RADIO INDICATOR BACKLIGHTING AND RADIO CONTROL BACKLIGHTING HAD NOT WORKED SINCE DELIVERY OF AC. TROUBLESHO OTING, FOUND THAT PIN 1 OF JC005 WAS AT GROUND POTENTIAL, PREVENTING DIMMER POTENTIOMETER FROM FUNCTIONING PROPERLY. RE MOVED WIRE FROM CIRCUIT, WIRE THAT HOOKS INTO WARNING / CAUTION ANNUNCIATOR. RADIO LIGHTING WORKED CORRECTLY. THE WAY SWITCH WAS INTERGRATED INTO SYSTEM WAS CAUSING HARD GROUND CONDITION. 1 H 7 1 3O NT 3A12 2001032200215 20010322 00215 SO 2001 3 22 20010305CW011 1 20010123 G 7714 640925 ADAPTER PIPER PA34 PA34200T 7103406 SO CONT O360 TSIO360EB 17025 SO 90 TACH DR ADPT FAILED B O OTHER O OTHER NR NOT REPORTED 1 NE 01 2240D 88 347970032 807536L 90 DEGREE TACH DRIVE ADAPTER PUT ON AIRCRAFT. WHEN ADAPTER FAILS, THERE IS NO RPM INDICATION TO TACH. PROBLEM APPARENT LY VIBRATION INDUCED. SOME PROVISION SHOULD BE MADE TO REINFORCE UNIT OR RELOCATE IT TO AN AREA NOT AS PRONE TO VIBRATI ONS. 1 L 7 2 3O 3 O A7SO E9CE 2001032200216 20010322 00216 SO 2001 3 22 20010305CW012 1 20010125 G 7714 640925 ADAPTER PIPER PA34 PA34200T 7103406 SO CONT O360 TSIO360EB 17025 SO 90 TACH ADAPTER FAILED B O OTHER O OTHER NR NOT REPORTED 1 NE 01 2240D 121 347970032 807536R 90 DEGREE TACH DRIVE ADAPTER PUT ON AIRCRAFT. WHEN ADAPTER FAILS, THERE IS NO RPM INDICATION TO TACH. PROBLEM, APPARE NTLY VIBRATION INDUCED. SOME PROVISIONS SHOULD BE MADE TO REINFORCE UNIT , OR RELOCATE IT TO AN AREA NOT AS PRONE TO VI BRATIONS. 1 L 7 2 3O 3 O A7SO E9CE 2001040900019 20010409 00019 SO 2001 4 9 20010305CW013 1 20010123 G 7714 640925 ADAPTER PIPER PA34 PA34200T 7103406 SO TMECA ARRIEL ARRIEL1 60030 NE TACH GENERATOR FAILED B K NONE O OTHER IN INSP/MAINT 1 NE 01 2240D 274 347970032 807536R 90 DEGREE TACH ADAPTER PUT ON AIRCRAFT. WHEN ADAPTER FAILS, THERE IS NO RPM INDICATION TO TACH. PROBLEMS APPARENTLY VI BRATION INDUCED. SOME PROVISION SHOULD BE MADE TO REINFORCE UNIT, OR RELOCATE IT TO AN AREA NOT AS PRONE TO VIBRATION. 1 L 7 2 3O 3 U A7SO E19EU 2001040900052 20010409 00052 EA 2001 4 9 20010305CW014 2 20010305 G 8550 CH48110 OIL FILTER CESSNA 172 172 2072402 CE LYC O320 O320* 41508 EA ENGINE FLAKING D K NONE O OTHER IN INSP/MAINT 1 EA 23 737MP 17269524 UPON INSPECTION OF OIL FILTER AFTER 50 HRS USAGE, FILTER HOUSING DISASSEMBLED FOR INSPECTION AND GASKET / GLUE TYPE MAT ERIAL NOTED AT MATING FLANGES INSIDE. THIS MATERIAL NOTED IN FILTER ASSEMBLIES NUMBEROF TIMES AND ALSO DRAINED FROM OI L SUMPS, RECOMMEND MFG CHECK AMOUNT OF SEALANT USED AND DESIGN CRUSH TYPE SEAL USED INSTEAD OF MATERIAL THAT CAN FLAKE A WAY AND GO THROUGH OIL SYSTEM. 1 H 7 1 3O 3 O NT 3A12 E274 2001030600022 20010306 00022 SO 2001 3 6 20010306AP001 1 20010112 G 2820 67700322 FUEL LINE PIPER PA32 PA32301T 7103209 SO BAGGAGE AREA LEAKING D O OTHER B SMOKE/FUMES/ODORS/SPARKS CR CRUISE 1 SW 99 81573 328024004 PILOT REPORTED STRONG FUEL ODOR IN CABIN. INVESTIGATION REVEALED FUEL LEAKING FROM FLARELESS FITTING SLEEVE AT BULKHEAD FITTING AFT OF FIREWALL BELOW THE NOSE BAGGAGE AREA FLOOR. FUEL WAS CARRIED BACK INTO THE CABIN AREA INSIDE THE PLASTIC CHAFF SLEEVE COVERING THE LINE. THE PLASTIC CHAFF COVER WAS SPLIT IN THE CABIN AREA AND FUEL DRIPPED BEHIND THE SIDE PAN EL. REPLACED LINE ASSEMBLY. SUSPECT FLARELESS FITTING SLEEVE BECAME LOOSE DUE TO VIBRATION AND AGE. 1 L 7 1 3O A3SO 2001030600023 20010306 00023 CE 2001 3 6 20010306AP002 1 20010112 G 7160 BA4106 AIR FILTER CESSNA 150 150L 2071826 CE CONT O200 O200A 17020 SO ENGINE DAMAGED C K NONE O OTHER IN INSP/MAINT 1 SW 99 18033 15073748 669917A DURING ANNUAL INSPECTION THE AIR FILTER ASSEMBLY WAS REMOVED TO FACILITATE INSPECTION OF CARB AIRBOX AND HEAT VALVE. UP ON REMOVAL, IT WAS NOTED THAT THE AIR FILTER FRAME DID NOT HAVE THE GASKET RETAINER LIPS AS REQUIRED BY AD 96-09-06. TH E FILTER FRAME WAS MARKED WITH A MANUFACTURERS DATA LABEL IDENTIFYING IT AS A BA-4106 REVISION D. REVISION D IS TERMINA TING ACTION FOR THIS AD AND INDICATES THE PRESENCE OF THE GASKET RETAINING LIPS ON THE FRAME. THE MANUFACTURER, WHEN CO NTACTED, STATED THAT ALL REV. D FRAME ASSEMBLIES HAD A LETTER L METAL STAMPED IN THE LOWER FLANGE BEFORE ANODIZEING. TH IS IDENTIFICATION WAS MISSING.THE SUBMITTER SPECULATES THAT AN UNSCRUPULOUS MISCREANT OBTAINED A REVISION D LABEL IN O 1 H 7 1 3O 3 O 3A19 E252 2001040900138 20010409 00138 CE 2001 4 9 20010306CW001 1 20010101 G 2720 071230916AGW BELLCRANK CESSNA 188 A188B 2073005 CE CONT O520 IO520* 17032 SO RUDDER WORN D K NONE O OTHER IN INSP/MAINT 1 NM 09 4877Q 7758 18802613T RUDDER BELLCRANK PN 0712309-16AGW HAD EXTREME WEAR SEVERAL PLACES, BOTH SIDES. WHERE THEY ARE LOCATED THEY ARE DIFFICUL T TO INSPECT AND LUBERCATE. MADE INSPECTION PANEL TO BE ABLE TO GAIN ACCESS TO THIS VITAL AREA. FAILURE OF THIS PART W OULD POTENTIALLY CAUSE GROUND LOOP. 1 L 7 1 3O 3 O A9CE E5CE 2001040900216 20010409 00216 2001 4 9 20010312CW001 4 20010212 G 2562 ELT910 ELT LKHEED P3A P3A 5260103 NM CABIN UNSTABLE D K NONE O OTHER IN INSP/MAINT 1 SW 99 927AU 151369 ELT SELF ACTIVATED. THIS UNIT WAS SENT TO THE FACTORY FOR WARRANTY REPAIR FOR THE SAME DEFECT 2 MOS EARLIER. AIRCRAFT WAS SITTING ON RAMP WITH NO POWER. ELT WENT OFF AT 2AM. UNITS HAVE A POOR SELF ACTIVATION RATE. 2 L 7 4 4T RT A32NM 2001040900222 20010409 00222 SO 2001 4 9 20010312CW002 1 20010213 G 3244 217K221 TIRE GULSTM GV GV SO NLG FAILED B K NONE O OTHER IN INSP/MAINT 1 EA 11 NOSEWHEEL TIRE HAS SEPARATION OF TREAD FROM CARCUS. BONDING BETWEEN TREAD AND CARCUS DEBONDED. 2 L 7 2 4F RT A12EA 2001040900227 20010409 00227 NE 2001 4 9 20010312CW003 2 20010205 G 7250 2A0851 SEAL IAE V2500 V2500A1 NE NR 4 BEARING CRACKED B K NONE O OTHER IN INSP/MAINT 1 NE 03 PART RECEIVED FROM REPAIR STATION FOR PENETRANT INSPECTION. PART REJECTED 2ND TIME AT PENETRANT INSPECTION FOR INDICATI ONS AS MARKED IN RADIUS ADJACENT TO MACHINED FACES OF OIL PASSAGES. 4 F E311NE 2001040900225 20010409 00225 NE 2001 4 9 20010312CW004 2 20010130 G 7250 2A0847 SEAL IAE V2500 V2500A1 NE NR4 BEARING CRACKED B K NONE O OTHER IN INSP/MAINT 1 NE 03 PART RECEIVED FOR PENETRANT INSPECTION. PART REJECTED AT PENETRANT INSPECTION FOR TWO INDICATIONS AT BOTTOM OF COUNTERB ORES ON ID OF PART. 4 F E311NE 2001040900226 20010409 00226 NE 2001 4 9 20010312CW005 2 20010130 G 7250 2A0851 SEAL IAE V2500 V2500A1 NE NR4 BEARING CRACKED B K NONE O OTHER IN INSP/MAINT 1 NE 03 PART RECEIVED FOR PENETRANT INSPECTION. PART REJECTED AT PENETRANT INSPECTION FOR INDICATIONS AS MARKED IN RADIUS ADJAC ENT TO MACHINED FACES OF OIL PASSAGES. 4 F E311NE 2001040900102 20010409 00102 EU 2001 4 9 20010312CW009 1 20010129 G 5540 BRACKET EIRVON 20 PIK20D 5760206 EU RUDDER HINGE CRACKED D K NONE O OTHER IN INSP/MAINT 1 NM 01 7820D 20602 VIBRATION OF A HARD RUBBER TAIL DOLLY TIRE ASSISTS IN THE FORMATION OF THESE CRACKS. THIS STATEMENT MAY GIVE FALSE SENS E OF SECURITY TO OWNERS WHO ONLY USE PNEUMATIC TIRES, AS WAS THE CASE WITH THIS AIRCRAFT. THREE OF THE FOUR FLANGES WER E CRACKED AND WERE VERY HARD TO SEE, EVEN WITH A 5X MAGNIFICATION. CRACKS WERE HIDDEN UNDER EPOXI RESIN THAT HAD BEEN I N PLACE SINCE NEW. ANY RESIN AND USE OF DYE PENETRANT INSPECTION. 1 K 0 0 G31EU 2001040500111 20010405 00111 EU 2001 4 5 20010314CW001 1 20010218 G 2612 B332M FIRE DETECTOR BOLKMS 105 BO105CBS 5626008 EU ALLSN 250C 250C20B 03013 GL NR 1 ENGINE SHORTED E ALGA K NONE O OTHER IN INSP/MAINT 1 SW 03 5416F 794 836063 DURING PRESTART CHECK. AFT PROBE SHORTED TO ELBOW ON ENGINE AIR SYSTEM. 1 G 7 2 3U 3 U NC H3EU E4CE 2001040500112 20010405 00112 SW 2001 4 5 20010314CW002 1 20010217 G 6510 206061432121 HOUSING BELL 407 407 SW ALLSN 250C 250C47B GL BLOWER CRACKED E ALGA K NONE O OTHER IN INSP/MAINT 1 SW 03 577AL 53247 CAE847167 FOUND DURING ROUTINE MAINTENANCE. BLOWER HOUSING HAD CRACKED. 1 G 7 1 3U 3 U O H2SW E1GL 2001040500113 20010405 00113 SW 2001 4 5 20010314CW003 1 20010201 G 5320 NAS6606D70 BOLT BELL 214 214ST 1182106 SW GE CT7TS CT71 30030 NE FUSELAGE BROKEN E ALGA K NONE O OTHER IN INSP/MAINT 1 SO 03 392AL 28114 DURING DAILY INSPECTION, FOUND UPPER RETAINER BOLT, PN NAS6606D70, ON THE FWD NODAL BEAM ASSY HELPER SPRING BROKE, CRACK ING THE HELPER SPRING SIDE PLATE AND CAUSING CONTACT DAMAGE TO THE RIGHT TORSION ARM ASSEMBLY. NEED SCHEDULED INSPECTIO N OR RETIREMENT OF BOTH UPPER AND LOWER BOLTS DUE TO THE HIGH STRESS LOAD ON THESE PARTS. 2 G 7 2 4U 4 U H10SW E8NE 2001040500114 20010405 00114 EU 2001 4 5 20010314CW004 1 20010126 G 6520 365A33619721 FLANGE AEROSP AS365 AS365N2 8680815 EU TMECA ARRIEL ARRIEL1 60030 NE TAIL ROTOR G/B WORN E EGRA K NONE O OTHER IN INSP/MAINT 1 EA 17 272NE M538 6435 DURING T INSPECTION, FOUND BOLTS ATTACHING SLIDING FLANGE TO FLEXIBLE COUPLING HAVE LOW TORQUE. COTTER KEYS WERE INSTAL LED. SLIDING FLANGE AND FLEXIBLE COUPLING HAVE GROOVES WORN ON ATTACHING SURFACE. REPLACED SLIDING FLANGE, FLEXIBLE CO UPLING, AND ATTACH HARDWARE WITH NEW. 1 G 7 2 3U 3 U RT H10EU E19EU 2001032200221 20010322 00221 EU 2001 3 22 20010319CW005 1 20010222 G 2720 BRACKET PDP 503 SZD503 8821647 EU ATTACH BOLT CRACKED G K NONE O OTHER IN INSP/MAINT 1 WP 01 191CM B2198 RUDDER PULLEY CONTROL BRACKET CRACKED AT ATTACH BOLT LOCATIONS. THIS WAS DUE TO LACK OF VARNISH OF THE BRACKETS AND POS SIBLE SHRINKAGE OF MATERIAL. PRIOR TO INSPECTION OF AREA, PILOT REPORTED RUDDER FLUTTER AND STICKING. RECOMMEND INSPEC TION OF ALL AIRCRAFT FOR SIMILAR CONDITION. 1 K 0 0 RC G02CE 2001040500137 20010405 00137 SW 2001 4 5 20010319CW006 1 20010216 G 6310 47620669S CLUTCH BELL BELL 47 47G3B1 1181028 SW LYC O435 TVO435B1A 41516 EA M/R TRANSMISSION DAMAGED H ARUA A UNSCHED LANDING J WARNING INDICATION CR CRUISE 1 WP 11 48020 369 B123119 2812 67452C AIRCRAFT IN CRUISE AT 300 FT AGL CLUTCH SLIPPED AUTOROTATION PERFORMED DISASSEMBLED FOUND PARTIAL CONTACT OF CLUTCH/DRUM FACE. DRUM AT MAX LIMITS. MORE CAUTIOUS MEASUREMENT DURING OVERHAUL AND REQUIRED INSPECTION. 1 G 7 1 3O 3 O 2H3 1E13 2001032000001 20010320 00001 SO 2001 3 20 20010320AP001 1 20010119 G 2140 A23D047 REGULATOR PIPER PA31 PA31350 7103110 SO HEATER LEAKING C H DEACTIVATE SYST/CIRCUITS K FLUID LOSS IN INSP/MAINT 1 SW 99 318152176 THE PROBLEM THAT WE ARE HAVING IS WITH THE HEATER FUEL PRESSURE REGULATORS P/N A23D04-7.5 THEY START LEAKING FUEL AROUND THE HOUSEING. THE FIRST ONE STARTED LEAKING AFTER 180.9 HOURS OF HEATER OPERATION. INSTALLED NEW IN STOCK UNIT, AND IT LEAKED ON FIRST TEST FIRING. WE ALSO JUST HAD ANOTHER UNIT START LEAKING ON ONE OF OUR OTHER PIPER NAVIJO HEATER. THIS U NIT HAD 834.1 HEATER HOURS ON IT WHEN IT STARTED LEAKING. 1 L 7 2 3O A20SO 2001032000187 20010320 00187 2001 3 20 20010320AP002 4 20010215 G 6113 055032110 BULKHEAD CESSNA 172 172I 2072426 CE SPINNER BROKEN D K NONE O OTHER IN INSP/MAINT 1 SW 99 46230 17257123 SPINNER BULKHEAD WAS FOUND BROKEN AT END NEAR BLADE, WHERE LAST NUTPLATE IS LOCATED. THE BULKHEAD WAS REMOVED AND A NEW ONE ORDERED THROUGH API. THIS PART HAD BEEN REPLACED LESS THAN ONE YEAR EARLIER, APPROX 300 HOURS WERE ON THE PART. WHEN WE RECIEVED THE FACTORY NEW PART WE FOUND A CRACK/DEFECT IN THE EXACT SAME AREA AS WHERE THE BULKHEAD WE WERE REPLACING HAD BROKE. CESSNA PRODUCT SUPPORT WAS NOTIFIED BY US OF THIS PROBLEM, BUT THEY DID NOT SEE THAT IT WAS OF ANY CONCERN. WE STRONGLY FEEL DIFFERENTLY, AND WE BELIEVE THAT THE MACHINARY USED TO MAKE THIS PRODUCT COULD BE INDUCING DAMAGE THAT WILL CAUSE THE PART TO FAIL IN THE FUTURE. 1 H 7 1 3O NT 3A12 2001040900253 20010409 00253 GL 2001 4 9 20010321CW005 3 20010213 G 6114 C50462 PLATE MCAULY CESSNA 182 R182 2072734 CE LYC O540 O540* 41532 EA MCAULY 2D34C B2D34C214 GL PROPELLER HUB MISSING B W59R K NONE O OTHER IN INSP/MAINT 1 WP 07 2280T 776894 R18200016 L1928840A 776894 WHILE IN FLIGHT, THE C50462 SPINNER MOUNTING PLATES FAILED, RELEASING THE SPINNER FROM THE AIRCRAFT. THE PROPELLER BECA ME LOOSE ON THE CRANKSHAFT DUE TO THE MISSING PLATES. WAS DAMAGED BEYOND REPAIR DUE TO SEVERE FRETTING. A NUMBER OF TH E ATTACHING STUDS WERE SKIPPED AS WERE THE CRANKSHAFT BUSHINGS FROM THE SEVERE ABNORMAL LOADS IMPOSED UPON THEM. COMMON TO FIND THE C50462 PLATES CRACKED DURING OVERHAUL OR MINOR REPAIRS. HOWEVER, THIS IS FIRST OF IN-FLIGHT FAILURE KNOWN. 1 H 7 1 3O 3 O RT 3A13 E295 5 C P7EA 2001040900257 20010409 00257 GL 2001 4 9 20010321CW006 3 20010212 G 6111 A2202B RETAINER HARTZL PIPER PA23 PA23250 7102308 SO HARTZL HCE2Y HCE2YK2 GL PROP BLADE CRACKED B W59R K NONE O OTHER IN INSP/MAINT 1 WP 07 C23534 1537 MT INSPECTION REVIELD A CRACK APPROX .1250 INCH LONG ON BOTH SIDES OF RACE MATERIAL. PROPELLER WAS PURCHASED AS A OVERH AULED PROPELLER WITHOUT RECORDS. REPORTED LOST. PURCHASER SUBMITTED PROPELLER FOR OVERHAUL. IN ADDITION TO THIS CRACK ED PART, THE BLADES WERE FOUND TO BE 2 INCHES UNDER MINIMUM DIAMETER FOR THE INTENDED APPLICATION. 1 L 7 2 3O 1A10 5 C P9EA 2001040900466 20010409 00466 GL 2001 4 9 20010322CW012 1 20010219 G 2730 10680009 CARTRIDGE CIRRUS SR SR20 05628AJ GL CONT O360 IO360E 17025 SO HARTZL HCJ3Y PHCJ3YF1 GL ELEV CONTROL JAMMED B YDSR O OTHER J WARNING INDICATION TX TAXI/GRND HDL 1 GL 15 109CD 1195 1009 357116 JC13A ON RUN UP & PREPARING FOR FLIGHT, ELEVATOR DOWN AUTHORITY COULD NOT BE ACHIEVED UNDER NORMAL CONTROL PRESSURE. PILOT RE TURNED AND GROUNDED THE AIRCRAFT FOR MAINTENANCE. INVESTIGATION IDENTIFIED BINDING TO BE LOCATED WITHIN THE PITCH TRIM CARTRIDGE ASSEMBLY PN 10681004. DUE TO FOREIGN OBJECT INTRUSION INTO THE PITCH TRIM CARTRIDGE CUTOUT OPENING IN THE FOR M OF A SINGLE DISCARDED COTTER PIN TAILING. WHILE THE PRE-TAKEOFF PITCH TRIM TEST WAS BEING PERFORMED, AND THE ELEVATOR PLACED IN THE NOSE UP ATTITUDE, THE COTTER PIN LODGED. THE AFT SPRING RETAINER IN THE PLACE NOT ALLOWING IT TO RETURN WHEN TRIM WAS COMMANDED DOWN. 1 H 7 1 3O 3 O NC A00009CH E1CE 5 C P36EA 2001040900467 20010409 00467 SW 2001 4 9 20010322CW013 1 20010202 G 3340 2061531 CONNECTOR MOONEY M20 M20R 5870225 SW TAIL STROBE SHORTED B K NONE O OTHER IN INSP/MAINT 1 NE 05 91678 650 290129 DURING ANNUAL INSPECTION TAIL STROBE LIGHT WAS INOPERATIVE, ELECTRICAL ARCING ACROSS PINS IN CONNECTOR. CONNECTOR WAS LOCATED AT THE PIVOT POINT OF THE TAIL. (TAIL TO FUS MOUNTING AREA), REPLACED BURNT CONNECTOR. SYSTEM NO LONGER AS STRO BE SNAP SOUND AT THIS LOCATION. 1 L 7 1 3O RT 2A3 2001040900476 20010409 00476 EA 2001 4 9 20010322CW014 2 20010206 G 7414 M3548 ROTOR SLICK 4370 PIPER PA28 PA28181 7102807 SO LYC O360 O360A4M 41514 EA MAGNETO SHEARED B UC2R O OTHER R PARTIAL RPM/PWR LOSS TX TAXI/GRND HDL 1 GL 19 41487 98030708 2843179 L3628536A PILOT REPORTED RT MAGNETO TO BE INOPERATIVE DURING GROUND RUNUP. THE ASSIGNED TECHNICAN REMOVED THE RIGHT MAGNETO AND F OUND THE CAM SLOT ON THE ROTOR SHAFT COMPLETELY SHEARED OFF. CAUSE UNKNOWN POSSIBLE PART DEFECT. THIS MAGNETO WAS INSP ECTED EVERY 500 HOURS. 1 L 7 1 3O 3 O 2A13 E286 2001040900477 20010409 00477 EU 2001 4 9 20010322CW015 1 20010216 G 6510 E230397911 SPLINE ADAPTER AEROSP AS355 AS355F1 8680810 EU ALLSN 250C 250C20F 03013 GL GEARBOX CRACKED B Y3AR K NONE O OTHER IN INSP/MAINT 1 SW 03 911NW 555 555 5082 CAEC20F REMOVED ENGINE ASSEMBLY FOR OIL LEAKS. REMOVED COMPRESSOR AND TURBINE FROM GEAR BOX TO REPLACE SEALS AND ORINGS. INSPE CTION OF SPLINE ADAPTOR FOUND CRACK RUNNING APPROX 340 DEGREES AROUND ADAPTOR. TOTAL TIME ON PART IS 555.3 SINCE LAST O VERHAUL AT WHICH TIME THE ADAPTOR WAS REPLACED. CAUSE OF CRACK UNKNOWN AT THIS TIME. 1 G 7 2 3U 3 U H11EU E4CE 2001040900492 20010409 00492 EA 2001 4 9 20010323CW001 2 20010219 G 8530 AEL651024 CYLINDER PIPER PA28 PA28161 7102803 SO LYC O320 O320D3G 41508 EA ENGINE CRACKED B MW2R K NONE O OTHER IN INSP/MAINT 1 GL 17 778 778 287916130 L1017539A CYLINDER CRACKED SAME AS PREVIOUS CYLINDERS FROM TOP SPARK PLUG HOLE AROUND OUTSIDE EX SEAT TO BOTTOM SPARK PLUG HOLE. 1 L 7 1 3O 3 O 2A13 E274 2001040900078 20010409 00078 EA 2001 4 9 20010323CW002 2 20010126 G 7414 56LSC200 MAGNETO GULSTM 500 500B 0141106 SW LYC O540 IO540* 41532 EA ENGINE FAILED D K NONE O OTHER IN INSP/MAINT 1 SW 15 667CA 721 1468166 L328148 ENGINE WAS REMOVED FOR TBO DUE WHEN INSPECTED MAGS FOR SERVICEABLILITY. CAN HEAR CLICK INTERNALLY. DETERMIND MAG TO BE UNSERVICEABLE. PREVIOUS EXPERIENCE, SUSPECT LOOSE COIL DUE TO COIL WEAR AT POLAR SHOES. 1 H 7 2 3O 3 O 6A1 1E4 2001040900082 20010409 00082 CE 2001 4 9 20010323CW004 1 20010227 G 3252 1693800297 SHIMMY DAMPENER BEECH 23 B19 1151215 CE LYC O320 O320* 41508 EA MLG DEFECTIVE D O OTHER E VIBRATION/BUFFET TX TAXI/GRND HDL 1 NM 02 2048A 106 MB904 FOUND MULITUDE OF (AIR) POCKETS AND AIRCRAFT SHIMMIED EXCESSIVELY ON LANDING AND TAXI. 1 L 7 1 3O 3 O A1CE E274 2001040900200 20010409 00200 CE 2001 4 9 20010323CW005 1 20010214 G 2820 63B22623 VALVE CESSNA 172 172S 2072439 CE LYC IO360 IO360L2A EA FUEL DISTRIBUTIO INOPERATIVE D K NONE O OTHER IN INSP/MAINT 1 NM 11 74GW 665 665 172S8143 62813751A SERVO WAS CLEANED AND RECERTIFIED, WHICH PARTIALLY IMPROVED ENGINE PERFORMANCE. ENGINE STILL BACKFIRED AT 1300-1500 RPM . CLEANED INJECTORS, WITH NO CHANGE. REMOVED AND INSPECTED FUEL DISTRIBUTION VALVE. FOUND SMALL AMOUNT OF LINT PARTI ALLY BLOCKING PASSAGES AT NR3 CYLINDER PORT. CLEANED AND REASSEMBLED VALVE. RUNUP AND OPS CHECKS NORMAL. 1 H 7 1 3O 3 O NT 3A12 1E10 2001040900224 20010409 00224 CE 2001 4 9 20010323CW011 1 20010228 G 2510 C1650310101 CYLINDER CESSNA 182 182S 2072701 CE LYC O540 IO540* 41532 EA PILOT SEAT BROKEN H VPFG K NONE O OTHER IN INSP/MAINT 1 SO 07 63CE 1450 18280357 SEAT LOCK CYLINDER PN C1650310101 ON PILOTS SEAT. THE SHAFT ON CYLINDER BROKE WHERE IT GOES INTO THE FORK THAT ATTACHES TO SEAT BACK. 1 H 7 1 3O 3 O NT 3A13 1E4 2001040900505 20010409 00505 EU 2001 4 9 20010323CW014 1 20010215 G 5521 1090200059 RIB AGUSTA A109 A109A 0260109 EU ALLSN 250C 250C28 03013 GL LT ELEVATOR CRACKED D K NONE O OTHER IN INSP/MAINT 1 SW 99 25RX 2526 2526 7220 DURING A WIRING REPAIR TO THE LEFT NAVIGATION LIGHT, A CRACK WAS FOUND UNDER THE VIBRATION DAMPER WEIGHT. NO UNUSUAL VI BRATION HAD BEEN REPORTED PRIOR TO THE CRACK BEING DETECTED. A DAILY INSPECTION OF THE SYNCH ELEVATOR WOULD NOT HAVE RE VEALED THIS CRACK, UNTIL THE VIBRATION WEIGHT SEPERATES FROM THE ATTACHING RIB. RECOMMENDED AN INSPECTION BE INCLUDED I N THE MFG INSP PROGRAM TO REMOVE THE SYNCH ELEVATOR TIP CAP AND VISUALLY INSPECT THIS AREA. 1 G 7 2 3U 3 U H7EU E1GL 2001040900282 20010409 00282 CE 2001 4 9 20010323CW015 1 20010215 G 5347 161102105 LOCK CESSNA 172 172S 2072439 CE PILOTS SEAT BROKEN D K NONE O OTHER IN INSP/MAINT 1 NM 03 949SP 431 172S8145 PILOT REPORTED HIS SEAT LOCK PINS WOULD NOT RELEASE. MAINTENANCE FOUND THE PILOTS SEAT LOCK CONTROL WAS BROKEN. THIS S AME CONTROL WAS REPLACED 431.0 HOURS PRIOR FOR THE SAME PROBLEM. BOTH CONTROL ASSEMBLYS HAVE PN 1611020-05 REPLACE CONTR OL ASSEMBLY, OPERATIONAL CHECK SATISFACTORY. 1 H 7 1 3O NT 3A12 2001040900283 20010409 00283 CE 2001 4 9 20010323CW016 1 20010124 G 2510 161102105 CONTROL UNIT CESSNA 172 172S 2072439 CE COPILOT SEAT BROKEN D K NONE O OTHER IN INSP/MAINT 1 SW 99 494SP 981 981 172S8035 CO-PILOTS SEAT LOCK CONTROL ASSEMBLY WOULD NOT RELEASE SEAT LOCK PIN. MAINTENANCE FOUND THE RIGHT LOCK PIN CABLE BROKEN . REPLACED CONTROL ASSEMBLY PN161102105. THIS HAS BEEN A REOCCURRING PROBLEM ON NEW SEATS. 1 H 7 1 3O NT 3A12 2001040900293 20010409 00293 CE 2001 4 9 20010323CW017 1 20010108 G 8011 85009614 STARTER CESSNA 172 172S 2072439 CE LYC IO360 IO360L2A EA ENGINE INOPERATIVE D O OTHER J WARNING INDICATION TX TAXI/GRND HDL 1 SW 99 949SP 773 773 172S8145 L2812051A PILOT ATTEMPTED ENGINE START. FIRST FLIGHT OF THE DAY, STARTER WOULD NOT ROTATE. MAINTENANCE FOUND STARTER HAD TWO TER MINALS MELTED WHERE THEY ATTACH TO COMMUTATOR BRUSHES. REPLACED STARTER, OPERATIONAL CHECKED SAT. 1 H 7 1 3O 3 O NT 3A12 1E10 2001040900306 20010409 00306 SO 2001 4 9 20010323CW019 2 20010223 G 8520 653129 CRANKSHAFT CONT O360 IO360DB 17025 SO ENGINE CRACKED H K NONE O OTHER IN INSP/MAINT 1 SW 99 1863 808785R SUBJECT CRANKSHAFT HAS A 1.5 INCH CRACK IN NR6 ROD JOURNAL AT A 45 DEGREE ANGLE. ENGINE WAS REBUILT PRIOR TO MSB005C APP LICABILITY. CRANKSHAFT NOT APPLICABLE PER SN. 3 O E1CE 2001032700425 20010327 00425 CE 2001 3 27 20010326AP001 1 20010323 G 7602 5038901223 CONTROL UNIT BEECH 58 58 1152740 CE RIGHT MALFUNCTIONED B O OTHER O OTHER NR NOT REPORTED 1 SW 99 7MG 60 TH513 PILOT REPORTED THAT THE CONTROL WAS HARD TO MOVE. FOUND IN THE LOGS THAT THE INSTALLER HAD LUBED THE CONTROL. LUBRICATI ON WILL GUM UP THE DRY LUBE AND MAKE IT HARD TO MOVE. 1 L 7 2 3O 3A16 2001040900055 20010409 00055 EU 2001 4 9 20010326CW003 1 20010130 G 5711 D21200380 SPAR CAP WSK M18A M18A EU WSK ASZ62 ASZ62IRM18 NE WING CENTER BOX CRACKED B K NONE O OTHER IN INSP/MAINT 1 SO 09 51809 4229 1Z00915 DURING REPAIRS OF THE WING CENTER SECTION FOR CORROSION DAMAGE TO THE TRAILING EDGE SECTION OF THE WING AND DURING HIDDE N DAMAGE INSPECTION, FOUND .1250 INCH DEEP CRACK IN THE FORWARD LOWER SPAR CAP. THE CRACK RAN APPROX 24 INCHES INBOARD IN A SPANWISE DIRECTION FROM THE LEFT LOWER WING ATTACH FITTING. CRACK PASSED THROUGH 2 BOLT HOLES IN THE SPAR THAT ATT ACH THE LOWER WING ATTACH FITTING. CRACK IN SPAR CAP WAS CONFIRMED BY NDI INSP USING EDDIE CURRENT, AND DYE PENETRANT M ETHODS. LOWER SPAR CAP WAS REPLACED WITH NEW PZL PART AND WING CENTER SECTION WAS RETURNED TO SERVICE. RECOMMEDN A CLO SE INSPECTIONOF ALL WING ATTACH FITTINGS AND SPAR CAPS DURING ANY INSPECTION ON THIS AC. 1 L 7 1 3O 3 R NC A47EU E10NE 2001040900059 20010409 00059 SW 2001 4 9 20010326CW005 1 20010326 G 5711 SPAR BBAVIA 7 7EC 2110120 SW CONT C90 C90* 17009 SO RT WING CRACKED D K NONE O OTHER IN INSP/MAINT 1 GL 03 70824 7EC337 DURING ANNUAL INSPECTION, FOUND COMPRESSION CRACKS ON THE RIGHT WING REAR SPAR AT TOP LOCATION ON TOP SIDE OF SPAR. THI S COMPRESSION CRACK WAS HIDDEN UNDER OLD SPAR VARNISH AND WOULD HAVE BEEN MISSED IF TOP INSPECTION HOLES WERE NOT INSTAL LED. 1 H 7 1 3O 3 O A759 E252 2001040900395 20010409 00395 CE 2001 4 9 20010327CW009 1 20010108 G 2842 TRANSMITTER CESSNA 150 150A 2071804 CE CONT O200 O200A 17020 SO LT FUEL TANK DEFECTIVE D K NONE O OTHER IN INSP/MAINT 1 NM 03 8067F 4757 15064167 661557A AC LANDED SHORT OF RUNWAY AFTER ENGINE QUIT. AC HAD SUBSTANTIAL DAMAGE NO INJURIES. DETERMINED AC RAN OUT OF FUEL DUE TO FAULTY FUEL GUAGE. REMVD FUEL QUANTITY TRANSMITTER TO FUNCTION TEST. FOUND TWO RUB SPOTS ON FLOAT, REASON FOR CONTA CT BETWEEN FLOAT AND TANK APPEARS TO BE MISALIGNMENT OF FLOAT ARM. FOUND CONTACTOR DIMPLE HAD WORN THROUGH. CAUSE OF F UEL GUAGE TO STICK AT HALF TANK INDICATED COMBINATION OF FLOAT CONTACTING INSIDE OF FUEL TANK AND CONTACTOR BEING WORN T HROUGH. RESEARCHING LOG FOUND SENDING UNIT HAD BEEN REMOVED 1 YEAR PRIOR & NEW GASKET INSTALLED. RECOMMEND FOR RECURR ENCE PREVENTION: KNOWING SERVICE LIFE OF TRANSMITTERS & VERIFICATION OF NO INTERFERENCE OF FLOAT & INSIDE OF FUEL TANK. 1 H 7 1 3O 3 O 3A19 E252 2001040900407 20010409 00407 CE 2001 4 9 20010327CW010 1 20010129 G 7910 047051 ENGINE CESSNA 182 182P 2075816 CE CONT O470 O470S 17026 SO MCAULY 2A34C 2A34C203 GL NACELLE DEFECTIVE H K NONE L NO TEST IN INSP/MAINT 1 NM 11 96118 18263409 464601 744427 FACTORY NEW ENGINE GROUND TESTED ONLY. PROPELLER WILL NOT CYCLE. HAVE RECHECKED PROPELLER AND GOVERNOR. PROBLEM APPEA RS TO BE ENGINE OIL PRESSURE, INSUFFICIENT TO CYCLE PROPELLER. WARRANTY RETURN. 1 H 7 1 3O 3 O NT TA13 E273 5 C P3EA 2001040900482 20010409 00482 SO 2001 4 9 20010327CW011 1 20010208 G 8011 BRACKET PIPER PA28 PA28R201 7102816 SO LYC O360 IO360C1C6 41514 EA STARTER UNSECURE D K NONE O OTHER IN INSP/MAINT 1 WP 07 962PA 2844022 L2858251A THE FORWARD 1 FT STARTER ATTACH BOLT WHICH HOLDS THE ALTERNATOR BRACELET IS STRIPPING THE CASE OUT DUE TO VIBRATION. H ELICOILS ARE BEING INSTLLED BUT ARE NOT HOLDING. A SHELF NEEDS TO BE CUT INTO THE CASE TO SEAT A BOLT HEAD SO A NUT AND LOCK WASHER CAN BE INSTALLED. 1 L 7 1 3O 3 O 2A13 1E10 2001040900537 20010409 00537 NE 2001 4 9 20010328CW001 2 20010130 G 7322 5704931 CARBURETOR PWA R985 R985* 52008 NE HARTZL HCB3R HCB3R304 GL ENGINE LEAKING H K NONE K FLUID LOSS IN INSP/MAINT 1 AL 05 489 ENGINE FLOODED WITH FUEL AND DIED. FUEL LEAKING FROM CARBURETOR WHEN FUEL SELECTOR VALVE TURNED TO ON. 3 R 5E1 5 C P28EA 2001040900542 20010409 00542 EU 2001 4 9 20010328CW002 1 20010125 G 3213 AIR131368 PISTON JETAIR JETSTM JETSTM4101 1500501 EU MLG STRUT DAMAGED D FW1R K NONE O OTHER IN INSP/MAINT 1 NE 03 MLG STRUT RECEIVED WITH INTERNAL DAMAGE. UNIT RECEIVED W/O 5606 OIL BUT NO APPARENT DISASSEMBLY OF THE GEAR HAD OCCURED . (GLAND NUT AND FILL PLUGS INTACT). INTERNAL PARTS WERE DRY. THE FLUTTER VALVE WAS FOUND LOOSE IN THE TOP OF THE CYL INDER WITH THE UPPER CARRIER BEARING HELD IN PLACE BY THE CYLINDER LINER. THE CYLINDER LINER HAD TO BE MACHINED TO BE R EMOVED FROM THE CYLINDER. THE UNIT WAS SHIPPED FOR OVERHAUL AFTER THE AXLE WAS OVERHEATED WITH A WHEEL BEARING FAILURE. 2 L 7 2 4T RT A41NM 2001040900496 20010409 00496 CE 2001 4 9 20010328CW006 1 20010222 G 5620 10243016215 WINDOW BEECH 58 58P 1152744 CE CONT O520 TSIO520* 17040 SO CABIN FAILED B MQ3R A UNSCHED LANDING O OTHER CR CRUISE 1 WP 11 40PG 2666 TJ309 AIRCRAFT HAD BEEN CRUISING AT FL240 FOR 1 HOUR PLUS TEMP-40 DEGREE. ON DESCENT OUT OF FL200 THE LEFT MID CABIN WINDOW B LEW OUT OF AIRCRAFT, CABIN DEPRESSURIZATION. PILOT CONTINUED DESCENT TO LOWER ALTITUDE AND LANDED WITHOUT FURTHER INCID ENT. WINDOWS WEW INSPECTED IN NOVEMBER, 2000 AT 2636.9 HRS. AND WERE FOUND TO BE IN GOOD CONDITION. 1 L 7 2 3O 3 O A23CE E8CE 2001040900375 20010409 00375 EU 2001 4 9 20010328CW012 1 20010308 G 2913 704A33690004 BELT SNIAS 350 AS350BA 8680817 EU LYC LTS101 LTS101600A3 41560 NE HYD SYSTEM SEPARATED D O OTHER J WARNING INDICATION NR NOT REPORTED 1 WP 19 57717 237 1334 L43402CE HYDRAULIC BELT FAILED AT BOND LINE DURING FLIGHT WHICH LEAD TO PRECAUTIONARY LANDING. BELT CONDITION AND TENSION APPEAR ED NORMAL DURING PREFLIGHT. 1 G 7 1 3U 3 U NC H9EU E5NE 2001040900302 20010409 00302 NE 2001 4 9 20010328CW013 1 20010228 G 6510 7610105101041 BLADE SKRSKY S76 S76A 8143006 NE ALLSN 250C 250C30 03013 GL TAIL ROTOR DELAMINATED D MV1R K NONE O OTHER IN INSP/MAINT 1 EA 17 38 2436 760087 ON PRE-FLIGHT INSPECTION FOUND AN AREA OF DELAMINATION AT TAIL ROTOR BLADE STATION 27.00, 4.5 INCHES FROM LEADING EDGE O F TAIL ROTOR BLADE. ITS SIZE ABOUT .7500 INCH. BLADE REMOVED AND SENT FOR REPAIR. 1 G 7 2 3U 3 U H1NE E1GL 2001040900245 20010409 00245 EA 2001 4 9 20010402CW001 2 20010205 G 7414 S6LN1258 MAGNETO PIPER PA60 PA60602P 7106015 NM LYC O540 IO540* 41532 EA RT ENGINE BROKEN D K NONE L NO TEST IN INSP/MAINT 1 WP 01 858CH 124 608265006 RT ENGINE, LT MAGNETO POINT CAM FOLLOWER ARM BROKE AFTER 124.9 HOURS USE. MAGNETO OVERHAULED. INSTALLED 6-2-99 AT 2180. 1 HOURS. FAILED AND REMOVED AT 2305.0 HOURS. 1 M 7 2 3O 3 O RT A17WE 1E4 2001040900334 20010409 00334 CE 2001 4 9 20010403CW004 1 20010308 G 2435 23080005 STARTER GEN RAYTHN DH125 HAWKER800XP CE GARRTT TFE731 TFE731* 01518 WP LT ENGINE DESTROYED H A UNSCHED LANDING E VIBRATION/BUFFET CR CRUISE 1 SW 01 9292X 1081 563 258315 AT FLIGHT LEVAL 390, CREW FELT A VIBRATION IN THE AIRCRAFT, AIRCRAFT DIVERTED. MAINTENANCE FOUND LEFT ENGINE STARTER GE NERATOR DESTROYED. GENERATOR WAS REPLACED, GROUND CHECK NORMAL. THE GENERATOR CARRIES A TBO OF 1000 HOURS. THIS TIME IS RARELY ACHIEVED. 2 L 7 2 4F 4 F RT A3EU E6WE 2001040900336 20010409 00336 SO 2001 4 9 20010403CW006 1 20010131 G 2432 455211 CONTACTOR PIPER PA34 PA34220T 7103420 SO CONT O360 TSIO360* 17025 SO BATTERY DAMAGED B SO5R K NONE O OTHER IN INSP/MAINT 1 NE 03 292CA 543 3449017 BATTERY MASTER CONTACTOR INTERMITTANT. REMOVED AND INSPECTED CONTACTOR. FOUND BOTTOM COVER FULL OF WATER AND CONTACTS R USTED. INSTALLED NEW CONTACTOR, OPERATIONAL CHECK SATISFACTORY. INSPECTED AFT BAGGAGE DOOR SEAL AND SURROUNDING SKIN S EAMS FOR SOURCE OF WATER LEAK ONTO RELAY SHELF LOCATED BENEATH BAGGAGE FLOOR. NO LEAKS NOTED, CARPET AND INTERIOR DRY. SUSPECT GPU PLUG DOOR JUST FORWARD OF RELAY SHELF TO BE PROBABLE CAUSE FOR WATER INFILTERATION. 1 L 7 2 3O 3 O A7SO E9CE 2001040900338 20010409 00338 SO 2001 4 9 20010403CW008 1 20010315 G 3230 492303 VALVE PIPER PA44 PA44180 7104402 SO LYC O360 O360A1D 41514 EA MLG MALFUNCTIONED D O OTHER J WARNING INDICATION NR NOT REPORTED 1 SO 15 243AT 100 100 4496042 PILOTS REPORTED THAT LANDING GEAR WOULD NOT EXTEND, THEY THEN PULLED THE EMERGENCY EXTENSION VALVE AND THE GEAR LOWERED WITH THREE GREEN. UPON INSPECTION FOUND THE EMERGENCY GEAR EXTENSION VALVE TO BE, SPRAYING HYDRAULIC FLUID IN NOSE BEL OW HEATER. THIS IN TURN DEPLENISHED ALL FLUID IN RESERVOIR AND BURNED UP HYDRAULIC POWERPAK. SUSPECT INCORRECT ORING I N VALVE. 1 L 7 2 3O 3 O A19S0 E286 2001040900343 20010409 00343 SO 2001 4 9 20010403CW012 2 20010224 G 8520 ROD CESSNA 421 421B 2076014 CE CONT O520 TSIO520H 17040 SO RT ENGINE DEPARTED D K NONE O OTHER IN INSP/MAINT 1 GL 15 5988M 421B0231 AIRCRAFT ARRIVED WITH RIGHT ENGINE OIL LEAK. FOUND OIL LINE TO BE LEAKING. REPAIRED OIL LINE AND SERVICED BACK UP WITH OIL. ENGINE WAS RERUN AND A ROD CAME LOOSE AND PENETRATED THE CRANKCASE. NO OTHER INFORMATION WAS RECEIVED, EXCEPT TH AT THE ENGINE RAN OUT OF OIL DURING FLIGHT, WHICH PROBABLY CAUSED THE ROD TO SEPERATE. AN OVERHAULED ENGINE WAS RECEIV ED AND INSTALLED. 1 L 7 2 3O 3 O A7CE E8CE 2001040900344 20010409 00344 SO 2001 4 9 20010403CW013 1 20010222 G 3246 16105800 WHEEL PIPER PA23 PA23250 7102308 SO LYC O540 IO540* 41532 EA MLG BROKEN B K NONE O OTHER IN INSP/MAINT 1 GL 09 63954 3180 277854085 PILOT NOTICED RIGHT BRAKE GRABING WHILE TAXIING OUT FOR DEPARTURE. AFTER STOPPING TO INVESTIGATE, NOTICED A BULGE ON TH E INSIDE RIGHT WHEEL HALF. WHILE TAXIING BACK TO THE HANGER, THE BEAD AREA LET GO AND THE TIRE DEFLATED. AN 8 INCH PIE CE BROKE OFF AT THE BEAD. THE PILOT STATED THAT A RATHER HARD LANDING HAD OCCURED JUST BEFOR THIS FLIGHT BUT DID NOT CA USE ANY OTHER DAMAGE. 1 L 7 2 3O 3 O 1A10 1E4 2001040900345 20010409 00345 CE 2001 4 9 20010403CW014 1 20010220 G 5330 10704 SKIN RKWELL NA265 NA26565 7630107 CE FUSELAGE CRACKED B UVVR K NONE O OTHER IN INSP/MAINT 1 CE 03 74VC 1500 46517 UPON REMOVAL OF INOPERABLE GPS ANTENNA FROM AIRCRAFT, THE UPPER COVER SEPARATED FROM THE BASE OF ANTENNA, EXPOSING THE I NSIDE. THE INSIDE OF THE ANTENNA WAS FULL OF RUST FROM BASE. THE MOUNTING SURFACE OF THE ANTENNA WAS ALSO RUSTED, CAUS ING THE AIRCRAFT UPPER SOCK SKIN TO CORRODE. SUSPECT OVER TORQUE OF MOUNTING SCREWS CAUSED THE COVER TO CRACK, ALLOWING MOISTURE TO ENTER AND RUST ANTENNA FROM INSIDE OUT. RECOMMEND INSPECTING OF THESE TYPE ANTENNAS UPON INSTALLATION, TO ASSURE THAT SCREWS ARE NOT OVER TORQUED AND HAD CRACKS. 2 L 7 2 4J A2WE 2001040900348 20010409 00348 CE 2001 4 9 20010403CW016 1 20010226 G 5711 SPAR CAP CESSNA 150 150G 2071816 CE CONT O200 O200* 17020 SO RT WING CORRODED D K NONE O OTHER IN INSP/MAINT 1 CE 07 3232X 10054 15064632 CORROSION FOUND EXFOLIATING SPAR CAP OR RIGHT WING HEAVY CORROSION ON UPPER CABIN CARRY THRU STRUCTURE. VERTICAL STABIL IZER SKIN PILLOWED AND RIVETS POPPED. FOUND 15 RIVET HEADS PULLED THRU SKIN ON CANTED BULKHEAD AT FUSLAGE STATION 20.5 BOTTOM FUSELAGE. AIRCRAFT IS BEYOND ECONOMICAL REPAIR. A SEARCH OF AIRCRAFT REGISTRY SHOWS IT SPENT 18 YEARS IN FLORIDA AND REMAINDER ON EAST COAST. CURRENT OWNER PURCHASED AIRCRAFT AFTER BEING TOLD THAT IT HAD NO CORRROSION BY THE SELLER . 1 H 7 1 3O 3 O 3A19 E252 2001040900349 20010409 00349 CE 2001 4 9 20010403CW017 1 20010226 G 5711 SPAR CESSNA 150 150G 2071816 CE CONT O200 O200* 17020 SO RT WING CORRODED D K NONE O OTHER IN INSP/MAINT 1 CE 07 3232X 10054 15064632 CORROSION FOUND EXFOLIATING (1) SPAR CUP ON RIGHT WING HEAVY CORROSION ON UPPER CABIN (2) CARRY THRU STRUCTURE. (3) VER TICAL STABILIZER SKIN PILLOWED AND RIVETS POPPED. FOUND 15 RIVET HEADS PULLED THRU SKIN ON (4)CANTED BULKHEAD AT FUSELA GE STATION 20.5 BOTTOM FUSELAGE. AIRCRAFT IS BEYOND ECONOMICAL REPAIR. A SEARCH OF AIRCRAFT REGISTRY SHOWS IT SPENT 18 YEARS IN FLORIDA AND REMAINDER ON EAST COAST. CURRENT OWNER PURCHASED AIRCRAFT AFTER BEING TOLD THAT IT HAD ON CORROSI ON, BY THE SELLERS. 1 H 7 1 3O 3 O 3A19 E252 2001040900350 20010409 00350 CE 2001 4 9 20010403CW018 1 20010226 G 5532 SKIN CESSNA 150 150G 2071816 CE CONT O200 O200* 17020 SO VERTICAL STAB DAMAGED D K NONE O OTHER IN INSP/MAINT 1 CE 07 3232X 10054 15064632 CORROSION FOUND EXFOLIATING (1) SPAR CAP ON RIGHT WING HEAVY CORROSION ON (2) UPPER CABIN CARRY THRU STRUCTURE. (3) VER TICAL STABILIZER SKIN PILLOWED AND RIVETS POPPED. FOUND 15 RIVET HEADS PULLED THRU SKIN ON (4)CANTED BULKHEAD AT FUSELA GE STATION 20.5 BOTTOM FUSELAGE. AIRCRAFT IS BEYOND ECONOMICAL REPAIR. A SEARCH OF AIRCRAFT REGISTRY SHOWS IT SPENT 18 YEARS IN FLORIDA AND REMAINDER ON EAST COAST. CURRENT OWNER PURCHASED AIRCRAFT AFTER BEING TOLD THAT IT HAD NO CORROSI ON BY THE SELLERS. 1 H 7 1 3O 3 O 3A19 E252 2001040900203 20010409 00203 CE 2001 4 9 20010403CW019 1 20010226 G 5312 BULKHEAD CESSNA 150 150G 2071816 CE CONT O200 O200* 17020 SO FUSELAGE DAMAGED D K NONE O OTHER IN INSP/MAINT 1 CE 07 3232X 10054 15064632 CORROSION FOUND EXFOLIATING (1) SPAR CAP ON RIGHT WING HEAVY CORROSION ON (2) UPPER CABIN CARRY THRU STRUCTURE. (3) VE RTICAL STABILIZER SKIN PILLOWED AND RIVETS POPPED. FOUND 15 RIVET HEADS PULLED THRU SKIN ON (4)CANTED BULKHEAD AT FUSEL AGE STATION 20.5 BOTTOM FUSELAGE. AIRCRAFT IS BEYOND ECONOMICAL REPAIR. A SEARCH OF AIRCRAFT REGISTRY SHOWS IT SPENT 1 8 YEARS IN FLORIDA AND REMAINDER ON EAST COAST. CURRENT OWNER PURCHASED AIRCRAFT AFTER BEING TOLD THAT IT HAD NO CORROS ION BY THE SELLERS. 1 H 7 1 3O 3 O 3A19 E252 2001040900358 20010409 00358 CE 2001 4 9 20010404CW001 1 20010206 G 2720 6565007188 CONTROL CABLE CESSNA 500 550 2076604 CE COCKPIT MISINSTALLED D K NONE W INADEQUATE Q C IN INSP/MAINT 1 SW 99 829CB 1108 5500829 DURING PHASE 5 INSPECTION, PILOTS RIGHT FORWARD RUDDER CABLE FOUND INCORRECTLY ROUTED THROUGH ACCESS HOLE IN WEB INSTEAD OF CABLE GUIDE BELOW HOLE. CABLE HAD CHAFED INTO LOWER EDGE OF HOLE IN WEB AND DOUBLER. DOUBLER REPLACED AND WEB REPA IRED, CABLE REPLACED. 1 L 7 2 4F A22CE 2001040900359 20010409 00359 SO 2001 4 9 20010404CW002 1 20010228 G 5521 5423224 SPAR PIPER PA31 PA31350 7103110 SO ELEVATOR CRACKED B K NONE O OTHER IN INSP/MAINT 1 SO 05 350MN 3073 318152042 INSPECTION FOUND BOTH ELEVATOR SPARS CRACKED. INITIAL INSPECTION ADVISED AT 2500 HOURS TT. THIS WAS FIRST INSPECTION NO TE: TOTAL TIME 3073. 1 L 7 2 3O A20SO 2001040900328 20010409 00328 EA 2001 4 9 20010404CW003 2 20010219 G 8530 AEL6510241 CYLINDER PIPER PA28 PA28161 7102803 SO LYC O320 O320D3G 41508 EA ENGINE CRACKED B MW2R K NONE O OTHER IN INSP/MAINT 1 GL 17 4381L 834 288516016 L1341139A CYLINDER CRACKED SAME AS PREVIOUS CYLINDERS, FROM TOP SPARK PLUG HOLE AROUND OUTSIDE EX SEAT TO BOTTOM SPARK PLUG HOLE. 1 L 7 1 3O 3 O 2A13 E274 2001040900329 20010409 00329 EA 2001 4 9 20010404CW004 2 20010301 G 8530 AEL6510241 CYLINDER PIPER PA28 PA28161 7102803 SO LYC O320 O320D3G 41508 EA ENGINE CRACKED B MW2R K NONE O OTHER IN INSP/MAINT 1 GL 17 800KA 1013 288416019 L810539A CYLINDER CRACKED SAME AS PREVIOUS CYLINDERS FROM TOP SPARK PLUG HOLE AROUND OUTSIDE EX SEAT TO BOTTOM SPARK PLUG HOLE. 1 L 7 1 3O 3 O 2A13 E274 2001040900577 20010409 00577 SO 2001 4 9 20010405CW001 2 20010405 G 8530 646778 ROD CAP BEECH 58 58 1152740 CE CONT O520 IO520C 17032 SO CYLINDER 2 FAILED B CGHR K NONE O OTHER IN INSP/MAINT 1 GL 03 827TS 2206 895 TH836 267167R DURING CRUISE FLT RT ENG NR 2 CYL PISTON CONN ROD BROKE LOOSE FROM CRANKSHAFT, PENETRATED UPPER CRANKCASE. NR2 CYL SEP FROM ENGINE, RESTED IN COWLING. THE FORCE OF CONNECTING ROD COMING THROUGH THE CASE BROKE LEFT MAGNETO OFF ITS BASE AN D PUNCHED A HOLE IN THE UPPER COWL. PILOT SECURED ENGINE AND FLEW TO A MAINTENANCE BASE. UPON REMOVING PIECES AND LAYI NG THEM OUT ON TABLE IT WAS NOTICED ONE OF THE CONNECTING ROD CAP BOLTS DID NOT HAVE THE REMAINS OF A COTTER PIN IN EI THER OF THE SAFETING HOLES. BOLT HEAD HAD BEEN BROKEN OFF(SUSPECTED FROM THE HAMMERING WHEN THE NUT WAS LOOSE). IT WAS ALSO NOTED THAT THREADS OF SAME BOLT, NOT AS DAMAGED AS BOLT ON OTHER SIDE , INDICATING IT UNSCREWED ITSELF. 1 L 7 2 3O 3 O 3A16 E5CE 2001040900451 20010409 00451 NM 2001 4 9 20010406AP001 1 20010328 G 2510 600N6525501 SEAT BELT DOUG 600N 600N 3027377 NM COCKPIT BROKEN D K NONE O OTHER IN INSP/MAINT 1 SW 99 957SD RN011 THE SEAT RESTRAINT SYSTEM ROTARY BUCKLE ASSEMBLY FAILED WHEN THE SCREWS PULLED THROUGH THE BACK PLATE. OTHER SAME TYPE ASSEMBLIES INSPECTED FOUND CRACKED BACK PLATES IN 5 OF THE 6 INSPECTED. 1 G 7 1 3U NC H3WE 2001040900170 20010409 00170 NE 2001 4 9 20010406CW001 2 20010201 G 7314 3031632B PUMP CESSNA 500 550 2076604 CE PWA JT8 JT8D15 52051 NE RT ENGINE LEAKING B K NONE K FLUID LOSS IN INSP/MAINT 1 GL 15 2GG 1848 5500286 PCE70020 METAL FOUND IN FUEL PUMP FILTER. UPON DISASSEMBLY OF FUEL CONTROL / FUEL PUMP FOR REPLACEMENT OF FUEL PUMP FOUND BLUE D YE BETWEEN FUEL PUMP AND FUEL CONTROL INDICATING FUEL CONTROL BEARING WASHOUT DUE TO FUEL PUMP SHAFT SEAL LEAKAGE. THIS REQUIRED SENDING FUEL CONTROL OUT FOR REPAIR. 1 L 7 2 4F 4 F A22CE E2EA 2001040900092 20010409 00092 NE 2001 4 9 20010409AP001 1 20010205 G 2820 26700115 ADAPTER CONAER LA4 LA4200 5110310 NE FUEL SYSTEM CRACKED D K NONE K B FLUID LOSS SMOKE/FUMES/ODORS/SPARKS IN INSP/MAINT 1 SO 15 9WA 1455 0 520 FUEL SMELL IN CABIN, FUEL STAIN LEFT SIDE OF INTERNAL FUSELAGE AT AND BELOW ADAPTER. VISUALLY INSPECTED PART AND FOUND CRACK AT SUMP DRAIN VALVE FITTING. FUEL LEAKED INTO AND WAS STANDING IN THE HULL. LEAK DETECTED DURING REPAIR OF STRUC TURE IN THAT AREA. 1 H 7 1 3O 1A13 2001040900386 20010409 00386 GL 2001 4 9 20010409AP003 3 20010131 G 6114 HCC2YR2CLEUF HUB HARTZL PIPER PA44 PA44180 7104402 SO HARTZL HCC2Y HCC2YR2 GL PROPELLER ASSY CRACKED B O OTHER K FLUID LOSS IN INSP/MAINT 1 SW 99 3592 579 AU6092 AU6092 DURING PREFIGHT PILOT NOTICED GREASE ON BLADE. MECHANIC REMOVED SPINNER AND FOUND CRACK ON RADIUS OF THE HUB. 1 L 7 2 3O A19S0 5 C P920 2001040900387 20010409 00387 GL 2001 4 9 20010409AP004 3 20010131 G 6114 HCC2YR2 HUB HARTZL PIPER PA44 PA44180 7104402 SO HARTZL HCC2Y HCC2YR2 GL PROPELLER ASSY CRACKED B K NONE O OTHER IN INSP/MAINT 1 SW 99 3592 579 AU6092 AU6092 DURING PREFIGHT PILOT NOTICED GREASE ON BLADE. MECHANIC REMOVED SPINNER AND FOUND CRACK ON RADIUS OF THE HUB. 1 L 7 2 3O A19S0 5 C P920 2001040900168 20010409 00168 CE 2001 4 9 20010409CW001 1 20010226 G 5320 05132826 WEB CESSNA 172 172N 2072434 CE LYC O320 O320* 41508 EA FUSELAGE CORRODED D K NONE O OTHER IN INSP/MAINT 1 CE 07 733JC 17268322 CORROSION WAS FOUND ON RIGHT WEB AND STRINGER. REPLACED THESE PARTS LAST YEAR FOR SAME REASON. THE REPLACED HAD BEEN P AINTED WITH EXPOXY PRIMER PRIOR TO INSTALLATION. IT HAS BEEN NOTED THAT ALL PLACES THAT CORRODED BOTH TIME HAD BEEN IN DIRECT CONTACT WITH UPHOLSTERY THAT WAS INSTALLED 2.5 YEARS AGO. SUSPECT FABRIC WAS SPRAYED WITH SOME FORM OF FIRE RETA RDENT THAT IS CORROSIVE. 1 H 7 1 3O 3 O NT 3A12 E274 2001040900169 20010409 00169 CE 2001 4 9 20010409CW002 1 20010226 G 5313 05120376 STRINGER CESSNA 172 172N 2072434 CE LYC O320 O320* 41508 EA FUSELAGE CORRODED D K NONE O OTHER IN INSP/MAINT 1 CE 07 733JC 17268322 CORROSION WAS FOUND ON RIGHT WEB AND STRINGERS. REPLACED THESE PARTS LAST YEAR FOR SAME REASON. THE REPLACED PARTS HAD BEEN PAINTED WITH EPOXY PRIMER PRIOR TO INSTALLATION. IT HAS BEEN NOTED THAT ALL PLACES THAT CORRODED BOTH TIMES HAD B EEN IN DIRECT CONTACT WITH UPHOLSTERY THAT WAS INSTALLED 2.5 YEARS AGO. SUSPECTS FABRIC WAS SPRAYED WITH SOME FORM OF F IRE RETARDENT THAT IS CORROSIVE. 1 H 7 1 3O 3 O NT 3A12 E274 2001040900171 20010409 00171 CE 2001 4 9 20010409CW003 1 20010226 G 5313 05120374 STRINGER CESSNA 172 172N 2072434 CE LYC O320 O320* 41508 EA FUSELAGE CORRODED D K NONE O OTHER IN INSP/MAINT 1 CE 07 733JC 17268322 CORROSION WAS FOUND ON RIGHT WEB AND STRINGERS. REPLACED THESE PARTS LAST YEAR FOR SAME REASON. THE REPLACED PARTS HAD BEEN PAINTED WITH EPOXY PRIMER PRIOR TO INSTALLATION. IT HAS BEEN NOTED THAT ALL PLACES THAT CORRODED BOTH TIMES HAD B EEN IN DIRECT CONTACT WITH UPHOLSTERY THAT WAS INSTALLED 2.5 YEARS AGO. SUSPECT FABRIC WAS SPRAYED WITH SOME FORM OF F IRE RETARDANT THAT IS CORROSIVE. 1 H 7 1 3O 3 O NT 3A12 E274 2001040900324 20010409 00324 WP 2001 4 9 20010409CW010 2 20010228 G 7250 30606901 BLADE GARRTT TFE731 TFE7315R 01518 WP LP TURBINE DAMAGED D K NONE O OTHER IN INSP/MAINT 1 GL 19 6823 4994 91174 3RD LPT BLADE SEPARATED AT MIDSPAN CAUSING DAMAGE BEYOND LIMITS TO ALL 3RD LPT BLADES. ALSO DAMAGED THE EXHAUST NOZZLE A ND 3RD LPT NOZZLE BEYOND LIMITS. 4 F E6WE 2001040900330 20010409 00330 SO 2001 4 9 20010409CW011 2 20010409 G 8530 A20TK99 VALVE GUIDE CONT O520 IO520F 17032 SO CYLINDER STUCK D K NONE O OTHER IN INSP/MAINT 1 AL 03 500 RECEIVED 2 EA CYLINDERS FOR OVERHAUL UPON DISMANTLING WE FOUND BOTH EXHAUST VALVES STUCK . WE HAD TO DRIVE THEM OUT WIT H A DRIFT. SN NR 15130 EXHAUST GUIDE SIZE BOTTOM .433 TOP .4365 SN NR 15131 EXHAUST GUIDE SIZE BOTTOM .433 TOP .437 3 O E5CE 2001040900494 20010409 00494 SO 2001 4 9 20010409CW012 2 20010409 G 8530 A22EK99 VALVE GUIDE CONT O520 IO520F 17032 SO CYLINDER STUCK D K NONE O OTHER IN INSP/MAINT 1 AL 03 500 RECEIVED 2 EA CYLINDERS FOR OVERHAUL. UPON DISMANTLING, WE FOUND BOTH EXHAUST VALVES STUCK. WE HAD TO DRIVE THEM OUT W ITH A DRIFT. SN 15130 EXHAUST GUIDE SIZE BOTTOM .433 TOP .4365 SN 15131 EXHAUST GUIDE SIZE BOTT OM . 433 TOP .437 3 O E5CE 2001041000275 20010410 00275 EA 2001 4 10 20010409CW016 2 20010306 G 8530 L2744051A CYLINDER CESSNA 172 172R 2072401 CE LYC IO360 IO360L2A EA ENGINE CRACKED D A UNSCHED LANDING R PARTIAL RPM/PWR LOSS NR NOT REPORTED 1 CE 07 441CA 2010 17280441 L2744051 AIRCRAFT WAS 4 MILES FROM AIRPORT WHEN A LOUD BANG WAS HEARD AND THE ENGINE STARTED VIBRATING AND MISSING. PILOT PULLED POWER BACK TO IDLE AND LANDED SAFELY AT AIRPORT. INSPECTED ENGINE AND FOUND NR 3 ENGINE CYLINDER WITH A CRACK, HALF AR OUND CYLINDER. THIS CRACK STARTED AT THE 4TH FIN BACK FROM THE TOP SPARK PLUG HOLE AND PARRELLED THE FIN. DUE TO FREQU ENT USE ENGINE TBO IS 2200 HOURS. 1 H 7 1 3O 3 O NT 3A12 1E10 2001050200040 20010502 00040 CE 2001 5 2 20010410AP001 1 20010216 G 2820 43362 NEEDLE VALVE PREAIR MA45 CESSNA 182 182K 2072724 CE CONT O470 O470R 17026 SO CARBURETOR SEPARATED D O OTHER R PARTIAL RPM/PWR LOSS TX TAXI/GRND HDL 1 SW 99 3087Q 52 52 7509409 18258087 815939R OWNER REPORTED ROUGH IDLE AFTER LANDING, ASSUMED THE PROBLEM WAS RELATED TO CARB ICE ON THE GROUND. AIRCRAFT WAS BROUGH T IN FOR ANNUAL INSPECTION AND DURING PRE INSPECTION RUN UP CONFIRMED ROUGH IDLE, BUT SMOOTHED OUT WHEN CARB HEAT WAS A PPLIED. DURING INSPECTION FOUND THE CARBURATOR IDLE MIXTURE SCREW, SPRING, AND WASHER HAD FALLEN OUT. THE AIRCRAFT IS BASED AT A HIGH ALTITUDE (5883 FT) AIRPORT AND TO OBTAIN CORRECT IDLE MIXTURE SETTING THE IDLE MIXTURE SCREW HAS LIGHT C ONTACT WITH SETTING SPRING. CARBURETOR WAS SUPPLIED WITH FACTORY REMANUFACTURED ENGINE 52.04 HOURS AGO. 1 H 7 1 3O 3 O NT 3A13 E273 2001050200042 20010502 00042 CE 2001 5 2 20010410AP002 1 20010221 G 5315 12134083 FLOORBEAM CESSNA 210 2105 2073404 CE FUSELAGE CORRODED D K NONE O OTHER IN INSP/MAINT 1 SW 99 1825Z 3783 2050025 DURING ANNUAL INSPECTION DISCOVERED SEVERE INTERGRANULAR CORROSION ON LEFT 4 INCHES OF ANGLE. CORROSION OCCURED PRIMARI LY WHERE .25 IN. HI-SHEAR RIVITS ATTACH ANGLE TO BULKHEAD AND WING LIFT STRUT ATTACH FITTING. ANGLE WAS LESS THAN HALF ORIGINAL THICKNESS WHEN REMOVED. LIGHT SURFACE CORROSION NOTED IN ENTIRE AREA. THIS AREA IS VERY CRITICAL AND SHOULD BE INSPECTED VERY THOROUGHLY DURING ALL INPECTIONS.FLOORBOARDS REMOVED AND NEW PART INSTALLED. 1 H 7 1 3O 3A21 2001050200043 20010502 00043 CE 2001 5 2 20010410AP003 1 20010222 G 3010 BOOT CESSNA 441 441 2076020 CE RT WING LEAKING B K NONE O OTHER IN INSP/MAINT 1 SW 99 835MA 4410343 NOTED FUEL LEAK FROM BEHIND RT WING DE-ICE BOOT. AFTER PEELING BOOT BACK TO RESEARCH LEAK, NOTED NUMEROUS AREAS OF HEAV Y CORROSION. AIRCRAFT WAS FERRIED TO FACILITY FOR REPLACEMENT OF LEADING EDGE ASSEMBLY. 1 L 7 2 3T RT A28CE 2001041700148 20010417 00148 CE 2001 4 17 20010410AP004 1 20010222 G 5511 073261110 RIB CESSNA 182 R182 2072734 CE HORIZONTAL STAB CRACKED B K NONE O OTHER IN INSP/MAINT 1 SW 99 3621C 2249 0280 DURING AN ANNUAL INSPECTION FOUND THE RT HORIZONTAL STABILIZER INBOARD LEADING EDGE RIB CRACKED. DETECTED CRACK DUE TO EXCESSIVE SKIN PLAY AT RIB AND A WORKING FASTNER. CONFIRMED CRACK USING A BORESCOPE. DISASSEMBLED THE EMPENNAGE ENOUGH TO FACILITATE RIB REPLACEMENT. 1 H 7 1 3O RT 3A13 2001050200044 20010502 00044 CE 2001 5 2 20010410AP005 1 20010222 G 5730 SKIN CESSNA 441 441 2076020 CE RT WING CORRODED B K NONE O OTHER IN INSP/MAINT 1 SW 99 835MA 3320 3320 4410343 FOUND FUEL LEAK COMING FROM BEHIND THE RT WING DE-ICE BOOT. AFTER PEELING BACK BOOT TO LOCATE LEAK, NOTED SEVERAL AREAS OF HEAVY CORROSION ON LEADING EDGE. FERRIED AIRCRAFT TO FACILITY FOR LEADING EDGE REPLACEMENT. SUSPECT DE-ICE BOOT WA S INSTALLED USING IMPROPER PRACTICES ALLOWING MOISTURE TO GET IN BEHIND BOOT AND BECOME TRAPPED. 1 L 7 2 3T RT A28CE 2001050200045 20010502 00045 GL 2001 5 2 20010410AP006 1 20010223 G 5720 CUFF HOWARD DGA15 DGA15P 4690506 GL RT WING STRUT CORRODED D K NONE O OTHER IN INSP/MAINT 1 SW 99 36259 1770 THE STAINLESS STEEL CUFFS ARE ONLY ON THE RT WING STUTS AND THEY PROVIDE PROTECTION FOR THE STRUT WHEN OPENING/CLOSING T HE CABIN DOOR. THESE CUFFS ARE NOT BONDED TO THE WING STRUT BUT ARE WRAPPED AROUND THE STRUT AND CRIMPED IN PLACE. WHEN THE CUFFS WERE REMOVED FOR NON-ROUTINE INSPECTION IT WAS FOUND THAT THE WING STRUT WAS SEVERLY RUSTED AND PITTED IN THE AREA UNDER THE CUFFS. 1 H 7 1 3R A717 2001041900001 20010419 00001 NE 2001 4 19 20010410AP007 1 20010221 G 3246 5003929 WHEEL SKRSKY S70 S70 8143001 NE MLG CRACKED C K NONE O OTHER IN INSP/MAINT 1 sw 99 WHEEL ASSY SENT TO A CERTIFICATED REPAIR STATION FOR EDDY CURRENT INSPECTION. AFTER BUILD-UP, WHEEL AND TIRE ASSY WAS INFLATED TO 140 PSI AND LEFT FOR 12-24 HOUR LEAK CHECK. AFTER 36 HOURS TIRE PRESSURE WAS FOUND TO BE 30-40 PSI, AND A DAMAGED O-RING WAS SUSPECTED. UPON APPLYING 125 PSI, NITROGEN WAS HEARD ESCAPING. APPLYING LEAK DETECTOR REVEALED A C RACK AT LOWER PORTION OF INBOARD WHEEL HALF RETAINING BOLT HOLE. 2 G 7 2 4U H2NE 2001050200046 20010502 00046 EA 2001 5 2 20010410AP008 2 20010302 G 8530 STUD CESSNA 172 172N 2072434 CE LYC O320 O320H2AD 41508 EA NR 3 CYLINDER BROKEN D O OTHER E VIBRATION/BUFFET DE DESCENT 1 SW 99 1558E 1349 17271046 L109476 PILOT REPORTED BAD VIBRATION ON FINAL APPROACH. UPON INSPECTION IT WAS DISCOVERED THAT THREE OF FOUR OF THE TOP CYLINDE R HOLD DOWN STUDS ON THE NR 3 CYLINDER HAD BROKEN OFF AT THE ENGINE CASE. NO INTERNAL DAMAGE WAS FOUND. CAUSE UNKNOWN. 1 H 7 1 3O 3 O NT 3A12 E274 2001050200047 20010502 00047 CE 2001 5 2 20010410AP009 1 20010305 G 2750 45A620911 BELLCRANK BEECH MU300 400BEECH CE TE FLAPS CORRODED F K NONE O OTHER IN INSP/MAINT 1 SW 99 406TS 3661 RJ6 DURING ''A'' & ''B'' INSPECTION FOUND THAT BOTH INBOARD AND OUTBOARD FLAP BELL CRANKS ON BOTH WINGS HAD EXCCESSIVE PLAY. THIS CONDITION COULD BE OBSERVED WITH FULL CABLE TENSION WITH FLAPS IN FULL DOWN POSITION. WHEN EACH BELLCRANK WAS DIS SASSEMBLED FOUND BOTH BEARINGS, BOLT, STEEL INSERT AND ALUMINUM BELL CRANK TO HAVE HEAVY CORROSION. BOTH OUTBOARD BELL C RANKS HAD TO BE REPLACED. 2 H 7 2 4F RT A16SW 2001050200048 20010502 00048 SO 2001 5 2 20010410AP010 2 20010308 G 8530 PISTON CONT O550 TSIOL550B SO NR 4 CYLINDER BROKEN D K NONE O OTHER IN INSP/MAINT 1 SW 99 972 544 544 8020350 ON A FLIGHT FROM EL PASO TO 5T6 THE OIL PRESSURE STARTED TO FLUCTUATE , ON INSPECTION THE OIL FILTER WAS FULL OF ALUM. W HEN THE ENGINE WAS REMOVED & DISMANTLED NR 4 CYLINDER PISTON SKIRT WAS BROKEN OFF THERE WERE NO SIGHS OF ANY PARTS OUT O F ALLIGIMENT OR STUCK PISTON PIN THE CON. ROD NOT BENT THE CYL NO SIGNS OF OVER HEAT OR SUPPER COOLED THE RINGS NORMAL W EAR. 3 O E4SO 2001050200049 20010502 00049 CE 2001 5 2 20010410AP011 1 20010309 G 3233 20152 ACTUATOR CESSNA 172 172RG 2072438 CE MLG CRACKED B K NONE O OTHER IN INSP/MAINT 1 SW 99 5169V 7298 172RG0458 DURING ACCOMPLISHMENT OF CESSNA SEB 01-2, THE RT MAIN GEAR ACTUATOR WAS FOUND TO BE CRACKED IN THE SADDLE AREA AS OUTLIN ED IN THE SEB. REMOVED THE ACTUATOR FROM SERVICE AND INSTALLED A NEW ASSEMBLY. 1 H 7 1 3O 3A17 2001050200056 20010502 00056 CE 2001 5 2 20010410AP012 1 20010316 G 2510 051421515 SEAT BACK CESSNA 172 172S 2072439 CE COPILOTS SEAT BENT C K NONE O OTHER IN INSP/MAINT 1 SW 99 789EP 1007 172S8135 DURING PHASE 1 MAINTENANCE INSPECTION, CO-PILOTS SEAT BACK WAS RECLINED APPROXIMATELY 4 INCHES FROM FULL UPRIGHT POSITIO N. FOUND SEAT BACK FRAME P/N 0514215-15 WAS BENT AT THE TOP OF THE RIGHT ATTACH FORGING. 1 H 7 1 3O NT 3A12 2001050200057 20010502 00057 EA 2001 5 2 20010410AP013 2 20010316 G 7322 SERVO CESSNA 172 172S 2072439 CE LYC IO360 IO360L2A EA FUEL FLOW MALFUNCTIONED H K NONE O OTHER IN INSP/MAINT 1 SW 99 949SP 172S8145 L2812051A ENGINE RSA-5AD1 FUEL SERVO WILL NOT MEET SPECIFICATIONS. FUEL FLOW BELOW 1700 RPM IS TOO HIGH. IDLE SPEED AND MIXTURE C AN NOT BE SET TO MFG SPECIFICATIONS WITH SATISFACTORY ENGINE OPERATION. FUEL SERVO REMOVED, SENT FOR REPAIRS. MAJOR RE PAIRS ACCOMPLISHED AND SERVO REFLOWED TO PRECISION FLOW SHEET 30075-02 DATED 5 JAN 00. REINSTALLED FUEL SERVO, ADJUSTED IAW MFG SPECIFICATIONS, OPERATIONAL AND FLIGHT CHECKED SATISFACTORY. 1 H 7 1 3O 3 O NT 3A12 1E10 2001050200058 20010502 00058 EA 2001 5 2 20010410AP014 2 20010316 G 7322 25765362 FUEL CONTROL CESSNA 172 172S 2072439 CE LYC IO360 IO360L2A EA ENGINE MALFUNCTIONED H K NONE O OTHER IN INSP/MAINT 1 SW 99 567JW 610 172S8187 L2822651A ENGINE RSA-5AD1 FUEL SERVO WILL NOT MEET SPECIFICATIONS. FUEL FLOW BELOW 1700 RPM IS TOO HIGH. IDLE SPEED AND MIXTURE CAN NOT BE SET TO MFG SPECIFICATIONS WITH SATISFACTORY ENGINE OPERATION. FUEL SERVO REMOVED, SENT FOR REPAIRS. MAJOR R EPAIRS ACCOMPLISHED AND SERVO REFLOWED TO PRECISION FLOW SHEET 30075-02 DATED 5 JAN 00. REINSTALLED FUEL SERVO, ADJUSTE D IAW MFG SPECIFICATIONS, OPERATIONAL AND FLIGHT CHECKED SATISFACTORY. 1 H 7 1 3O 3 O NT 3A12 1E10 2001050200059 20010502 00059 EA 2001 5 2 20010410AP015 2 20010316 G 7322 25765361 FUEL CONTROL CESSNA 172 172S 2072439 CE LYC IO360 IO360L2A EA ENGINE MALFUNCTIONED H O OTHER O OTHER IN INSP/MAINT 1 SW 99 494SP 841 172S8035 L2790951A ENGINE RSA-5AD1 FUEL SERVO WILL NOT MEET SPECIFICATIONS. FUEL FLOW BELOW 1700 RPM IS TOO HIGH. IDLE SPEED AND MIXTURE CAN NOT BE SET TO MFG SPECIFICATIONS WITH SATISFACTORY ENGINE OPERATION. FUEL SERVO REMOVED, SENT FOR REPAIRS. MAJOR R EPAIRS ACCOMPLISHED AND SERVO REFLOWED TO PRECISION FLOW SHEET 30075-02 DATED 5 JAN 00. REINSTALLED FUEL SERVO, ADJUSTE D IAW MFG SPECIFICATIONS, OPERATIONAL AND FLIGHT CHECKED SATISFACTORY. RECOMMEND ALL RSA-5AD1 FUEL SERVO''S BE REFLOWED TO PRECISION FLOW SHEET 30075-02 IMMEDATELY. 1 H 7 1 3O 3 O NT 3A12 1E10 2001050200065 20010502 00065 CE 2001 5 2 20010410AP016 1 20010326 G 2510 161102105 CONTROL HOUSING CESSNA 172 172S 2072439 CE COCKPIT SEAT BROKEN D K NONE O OTHER IN INSP/MAINT 1 SW 99 948SP 1008 172S8144 DURING PHASE 3 INSPECTION FOUND PILOTS SEAT LOCK CONTROL ASSEMBLY P/N 1611021-05 BROKEN. ONE SEAT LOCK PIN WAS ENGAGED AND WOULD NOT RELEASE DUE TO THE ACTUATOR CABLE BROKEN. THIS IS THE 5TH SEAT CONTROL ASSEMBLY THAT HAS FAILED WITH A BR OKEN CABLE FOR THIS ORGANIZATION. REPLACED CONTROL ASSEMBLY. 1 H 7 1 3O NT 3A12 2001050200066 20010502 00066 EA 2001 5 2 20010410AP017 2 20010328 G 8530 CCST041CA CYLINDER LYC O320 O320D2J 41508 EA ENGINE CRACKED F A UNSCHED LANDING E VIBRATION/BUFFET CR CRUISE 1 SW 99 1310 CRACK IN CYLIDER EXTENDED FROM BOTH SPARK PLUG BOSSES TO THE EXHAUST SEAT. 3 O E274 2001050200068 20010502 00068 SO 2001 5 2 20010410AP019 1 20010315 G 7921 AE7010201K0240 HOSE PIPER PA31T PA31T2 7103127 SO PWA PT6 PT6A135 52043 NE LT ENGINE CRACKED C A UNSCHED LANDING J WARNING INDICATION CR CRUISE 1 SW 99 410CA 112 31T8166005 DURING CRUSE FLIGHT THE LT ENGINE LOW OIL PRESSURE WARNING SOUNDED ALERTING THE PILOT TO DROPPING OIL PRESURE. PILOT PER FORMED A PRECAUTIONARY ENGINE SHUTDOWN AND MADE A UNEVENTFUL LANDING. TECHNICICAN INSTALLED A NEW REPLACEMENT INLET OIL COOLER HOSE AND RETURNED AIRCRAFT TO SERVICE. 1 L 7 2 3T 4 T RT A8EA E4EA 2001050200069 20010502 00069 SO 2001 5 2 20010410AP021 2 20010403 G 8520 655004 CONNECTING ROD CONT O520 IO520D 17032 SO ENGINE GOUGED B K NONE O OTHER IN INSP/MAINT 1 SW 99 0 575948 FACTORY NEW ENGINE WITH 0 HRS TTIS WAS BEING DISASSEMBLED FOR CRANKSHAFT REPLACEMENT UNDER MSB 00-5. THE MAJORITY OF CO NNECTING ROD BOLTS COULD NOT BE REMOVED WITH REASONABLE PRESSURE AND HAD TO BE DRIVEN OUT OF THE CAP. INSPECTION REVEAL ED THAT THE ROD BOLTS EXHIBITED A BURR AND EVIDENCE OF GALLING ON THE SHANK AT THE POINT WHERE THE ROD AND CAP PARTING S URFACE WOULD BE. INSPECTION OF THE CAPS SHOWED DAMAGE EVIDENCED BY SIGNIFICANT GOUGING WHERE THE BOLTS HAD BEEN REMOVED , RENDERING THEM UNSERVICEABLE. 3 O E5CE 2001050200070 20010502 00070 EA 2001 5 2 20010410AP022 2 20010326 G 7321 DRIVE SHAFT BENDIX DPF2 PIPER PA31T PA31T 7103124 SO PWA PT6 PT6A28 EA FUEL CONTROL SHEARED G E ENGINE SHUTDOWN F FLT CONT AFFECTED CL CLIMB 1 GL 11 484SC A59060 31T7820022 PCE51554 ON CLIMBOUT FROM EANSVILLE, IN AT 12,500 THE PILOT NOTICED HE COULD NOT CONTROL THE RIGHT ENGINE WITH THE POWER LEVER. THE ENGINE WAS SHUT DOWN IN FLIGHT. THE TORQUE WAS REPORTED TO BE 1600 FT LBS AND THE PROPELLER SPEED WAS REPORTED TO B E 2200 RPM. NO OTHER ENGINE INDICATIONS WERE REPORTED. THE OUTSIDE AIR TEMPERATURE WAS -12 DEGREES C AND THE BAROMETRIC PRESSURE WAS 30.27. SHEARED FUEL CONTROL DRIVE SHAFT. 1 L 7 2 3T 4 T A8EA E4EA 2001050200071 20010502 00071 SO 2001 5 2 20010410AP023 1 20010327 G 3222 6528000 STRUT PIPER PA28 PA28140 7102802 SO NOSE GEAR CRACKED G K NONE O OTHER LD LANDING 1 GL 11 7373J 5518 2824728 THE STUDENT WAS ON HIS FINAL CROSS COUNTRY FLIGHT TO BLOOMINGTON, IN. THE TRAFFIC PATTERN AND FINAL APPROACH WAS NORMAL . THE PILOT FLARED AND TOUCHED THE MAIN GEAR FIRST ON RUNWAY 35 AT BMG. THE NOSE GEAR SETTLED ONTO THE RUNWAY, THE PIL OT REACHED FOR THE BRAKE HANDLE WHEN THE NOSE SETTLED LOWER THAN NORMAL AND THE PROPELLER STRUCK THE GROUND. THE PILOT STATED ALL FLIGHT CONTROLS, AND ENGINE CONTROLS WERE NORMAL. THE APPROACH AND LANDING, AS DESCRIBED BY THE PILOT WAS CO NFIRMED BY THE TOWER CONTROLLER ON DUTY AT THE TIME OF THE INCIDENT. THE NOSE GEAR INNER LOWER TUBE BROKE. INVESTIGATI ON REVEALED A POSSIBLE PRE-EXISTING CRACK RESULTING IN NOSE GEAR COLLAPSE. 1 L 7 1 3O 2A13 2001050200072 20010502 00072 CE 2001 5 2 20010410AP024 1 20010405 G 2810 1009200673 FLOAT VALVE BEECH 200 B200 1152922 CE RT NACELLE TANK BENT D K NONE O OTHER IN INSP/MAINT 1 SW 99 773TP 295 BB1722 THE FUEL VENT FLOAT VALVE IN THE TOP OF THE RT NACELLE TANK WAS IMPROPERLY INSTALLED. THE FLOAT PIVOT BRACKET WAS BENT. THIS WOULD PREVENT THE VALVE FROM SEATING PROPERLY. THIS WAS ALLOWING FUEL TO TRANSFER INTO THE AUX TANK WHEN EVER TH E MAIN TANK WAS FULL. 1 L 7 2 4T A24CE 2001041700096 20010417 00096 SO 2001 4 17 20010411CW001 2 20010319 G 8530 530851 LIFTER CESSNA 170 170A 2072304 CE CONT C145 C145* 17012 SO NR 5 CYLINDER BROKEN G K NONE O OTHER IN INSP/MAINT 1 SW 99 1228D 19782 AIRCRAFT SUFFERED A LOSS OF OIL PRESSURE. TEARDOWN OF THE ENGINE REVEALED THE HYDRAULIC LIFTER BODY ON THE NR 5 CYLINDE R HAD BROKEN. 1 H 7 1 3O 3 O A799 E253 2001041700013 20010417 00013 SO 2001 4 17 20010411CW012 2 20010206 G 7322 25765405 SERVO PIPER PA34 PA34220T 7103420 SO CONT O360 LTSIO360RB SO ENGINE CARB INOPERATIVE B O OTHER O OTHER NR NOT REPORTED 1 EA 07 4175D 69 3449191 322088 COULD NOT ADJUST OVERLY RIGHT MIXTURE. SENT FOR FACTORY SERVICE. INSTALLED ON AIRCRAFT STILL COULD NOT ADJUST. SENT B ACK TO FACTORY FOR REPAIRS. NOTE THESE UNITS ARE INSTALLED ON NEW AIRCRAFT, THIS IS 3RD SET OF SERVOS ON THIS AIRCRAFT . 1 L 7 2 3O 3 O A7SO E9CE 2001041700014 20010417 00014 SW 2001 4 17 20010411CW013 1 20010227 G 2450 727425 CIRCUIT BREAKER MOONEY M20 M20J 5870219 SW LYC O360 IO360A3B6 41514 EA MCAULY 2D34C B2D34C214 GL ELECTRICAL INOPERATIVE D O OTHER J WARNING INDICATION LD LANDING 1 SO 09 3758H 240930 L2556551A 993197 AIRCRAFT LANDING GEAR FAILED TO EXTEND AND AIRCRAFT LANDED GEAR UP. DURING REMOVAL OF AIRCRAFT FROM RUNWAY, IT WAS NOTE D, LANDING GEAR CONTROL CIRCUIT BREAKER WAS OUT. DURING OPERATION OF LANDING GEAR ON JACKS, SYSTEM OPERATED NORMALLY. NOT KNOWN IF CIRCUIT BREAKER WAS PULLED OR TRIPPED. NEW CIRCUIT BREAKER WAS INSTALLED AS PRECAUTIONARY MEASURE. 1 L 7 1 3O 3 O 2A3 1E10 5 C P7EA 2001041700070 20010417 00070 EA 2001 4 17 20010412CW002 2 20010307 G 7322 105009 CARBURETOR CESSNA 172 172M 2072418 CE LYC O320 O320E2D 41508 EA ENGINE DEFECTIVE B AMYR A UNSCHED LANDING R J PARTIAL RPM/PWR LOSS WARNING INDICATION NR NOT REPORTED 1 CE 05 12182 159 17261866 L3457327A DURING FLIGHT, AIRCRAFT WAS DOING TOUCH AND GO LANDINGS. PILOT PULLED BACK ON THROTTLE FOR MORE POWER BUT COULD NOT MOV E THROTTLE. LANDED SHORT OF RUNWAY, IN A FIELD. INVESTIGATION OF THROTTLE , FOUND CARBURETOR STUCK IN IDLE POSITION. REMOVED CARBURETOR AND FOUND COPPER BUTTERFLY RUBBING UP AGAINST INTERIOR OF THROTTLE ASSEMBLY. 1 H 7 1 3O 3 O NT 3A12 E274 2001041700075 20010417 00075 SO 2001 4 17 20010412CW005 1 20010111 G 5711 66762 SPAR PIPER PA28 PA28235 7102810 SO LYC O540 O540* 41532 EA WING CENTER BOX CORRODED B MI3R K NONE O OTHER IN INSP/MAINT 1 NM 09 32138 287510014 INSPECTION REVEALED MISSING RIVET HEADS, RUST. CORROSSION ON REAR SPAR AT CENTER SECTION JUNCTION. 1 L 7 1 3O 3 O 2A13 E295 2001041700077 20010417 00077 SO 2001 4 17 20010412CW007 1 20010111 G 5310 SPAR PIPER PA28 PA28235 7102810 SO LYC O540 O540* 41532 EA FUSELAGE CORRODED B MI3R K NONE O OTHER IN INSP/MAINT 1 NM 09 32138 287510014 AFT CARRY THROUGH SPAR AND BAGGAGE DOOR FRAME AND OPPOSITE SIDE ARE RUSTING AND CORRODING AND STEEL FITTINGS UNDER BAGGA GE COMPARTMENT FLOOR. PN 62448-00 PN 62448-01 PN 62618-00 PN 62619-00 PN 62529-00 65383-00 . 1 L 7 1 3O 3 O 2A13 E295 2001041700078 20010417 00078 SO 2001 4 17 20010412CW008 1 20010111 G 5310 DOOR FRAME PIPER PA28 PA28235 7102810 SO LYC O540 O540* 41532 EA FUSELAGE CORRODED B MI3R K NONE O OTHER IN INSP/MAINT 1 NM 09 32138 287510014 AFT CARRY THROUGH SPAR AND BAGGAGE DOOR FRAME AND OPPOSITE SIDE ARE RUSTING AND CORRODING AND STEEL FITTINGS UNDER BAGGA GE COMPARTMENT FLOOR. PN 62488-00 PN 62448-01 PN 62618-00 PN 62619-00 PN 62529-00 PN 65383-00. 1 L 7 1 3O 3 O 2A13 E295 2001041700080 20010417 00080 SO 2001 4 17 20010412CW009 2 20010301 G 8530 CYLINDER CESSNA 310 310J 2074226 CE CONT O470 IO470U 17026 SO LT ENGINE LEAKING B K NONE K FLUID LOSS IN INSP/MAINT 1 EA 23 515HW 310J0102 AIRCRAFT LANDED. OIL LEAKING FROM LEFT ENGINE. INSPECTION REVEALED NR 4 CYLINDER VALVE COVER BROKEN DUE TO VALVE ROCKE R ASSEMBLY BROKEN FROM CYLINDER BOSS. PROBABLE CAUSE STUCK VALVE OR METAL FATIGUE AT BOSS. 1 L 7 2 3O 3 O 3A10 3E1 2001041700081 20010417 00081 EA 2001 4 17 20010412CW010 2 20010301 G 8500 ENGINE PIPER PA31 PA31350 7103110 SO LYC O540 IO540* 41532 EA RIGHT MAKING METAL B K NONE O OTHER IN INSP/MAINT 1 EA 23 283GT 317952139 AIRCRAFT LANDED. RIGHT ENGINE SHUTDOWN IN FLIGHT, DUE TO LOSS OF OIL PRESSURE. INSPECTION REVEALED METAL CONTAMINATIO N. 1 L 7 2 3O 3 O A20SO 1E4 2001041700084 20010417 00084 EA 2001 4 17 20010413CW002 1 20010302 G 2752 SC14000062 BEARING EATON CNDAIR CL600 CL6002B19 EA FLAP ACTUATOR FAILED B VK6R O OTHER O OTHER NR NOT REPORTED 1 GL 09 1102 THRUST BEARING FAILURE DUE TO LACK OF LUBRICATION AND POSSIBLE PRELOAD CONDITION. 2 L 7 2 4F RT A21EA 2001041700085 20010417 00085 CE 2001 4 17 20010413CW003 1 20010220 G 3232 0842102 BELLCRANK CESSNA 320 320F 2074516 CE CONT O520 IO520* 17032 SO NLG BROKEN B OF1R K NONE O OTHER IN INSP/MAINT 1 EA 17 3452Q 3643 0052 LEFT NOSE GEAR DOOR ROD ATTACH CLEVIS PIN FELL OUT. UPON RETRACTION OF GEAR, LEFT NOSE DOOR FOULED THE RETRACTORY NOSE GEAR AND JAMMED. GEARBOX CONTINUED PULLING UNTIL 0842102 BELLCRANK BROKE. WHEN GEAR WAS EXTENDED NOSE GEAR WOULD NOT EXTEND. DOOR CLEVIS PINS WERE INSTALLED WITH AN 416 PINS INSTEAD OF COTTER PINS AS CALLED OUT BY IFC. 1 L 7 2 3O 3 O 3A25 E5CE 2001041700086 20010417 00086 EA 2001 4 17 20010413CW004 2 20010305 G 8520 69796 DOWEL PIN LYC IO360 IO360L2A EA NR 1 BEARING MISINSTALLED B NX42 K NONE W INADEQUATE Q C IN INSP/MAINT 1 SO 15 2173 L2776751A DURING ENGINE INSPECTION, IT WAS NOTED THAT THE NUMBER ONE MAIN BEARING DOWEL WAS INSTALLED BACKWARDS WITH IN THE CRANKC ASE BEARING DOWEL BORE. THE IMPROPERLY INSTALLED DOWEL PREVENTED THE NEW BEARING FROM FULLY SEATING WITHIN THE CRANKCAS E BORE. 3 O 1E10 2001041700087 20010417 00087 CE 2001 4 17 20010413CW005 1 20010321 G 5312 08130005 BULKHEAD CESSNA 310 310K 2074228 CE CONT O470 IO470* 17026 SO FUSELAGE CRACKED B K NONE O OTHER IN INSP/MAINT 1 WP 23 101JB 5921 310K0110 DURING REPLACEMENT OF AIRCRAFT HEATER DUCTING, MECHANIC NOTICED THE RIGHT BULKHEAD AT STA 29.93 UNDER HEATER WAS CRACKED . ALSO CHECKED LEFT SIDE BULKHEAD AT STA 29.93 AND FOUND THAT BULKHEAD CRACKED IN THE SAME LOCATION. NOTE THAT SUPPOR T FOR NOSE WHEEL STEERING PULLEY IS ATTACHED TO BULKHEAD NEAR CRACK. MOVEMENT OF PULLEY AND CABLE TENSION MAY CAUSE BUL KHEAD TO FLEX. RECOMMEND CHECKING CABLE TENSION DURING INSPECTION OF NOSE WHEEL STEERING SYSTEM. 1 L 7 2 3O 3 O 3A10 E1CE 2001041700088 20010417 00088 CE 2001 4 17 20010413CW006 1 20010321 G 5312 08130004 BULKHEAD CESSNA 310 310K 2074228 CE CONT O470 IO470* 17026 SO FUSELAGE CRACKED B K NONE O OTHER IN INSP/MAINT 1 WP 23 101JB 5921 310K0110 DURING REPLACEMENT OF AIRCRAFT HEATER, DUCTING MECHANIC NOTICED THE RIGHT BULKHEAD AT STA 29.93 UNDER HEATER WAS CRACKED . REMOVED HEATER TO GAIN ACCESS TO BULKHEAD. NOTE THAT SUPPORT FOR NOSE WHEEL STEERING PULLEY IS ATTACHED TO BULKHEAD NEAR CRACK. MOVEMENT OF PULLEY AND CABLE TENSION MAY CAUSE BULKHEAD TO FLEX. RECOMMEND CHECKING CABLE TENSION DURING INSPECTION OF NOSE WHEEL STEERING SYSTEM. 1 L 7 2 3O 3 O 3A10 E1CE 2001041700089 20010417 00089 SW 2001 4 17 20010413CW007 1 20010319 G 6730 41001554 HOUSING TEXTRON BELL 214 214B 1182100 SW SERVO ACTUATOR CRACKED B K NONE O OTHER IN INSP/MAINT 1 NM 07 1109B CRACKS DETECTED ON FLANGE MOUNTS. REPLACED SERVO UNIT FROM SURPLUS. 2 G 7 1 4U H6SW 2001041700102 20010417 00102 EU 2001 4 17 20010413CW010 1 20010129 G 2432 20VR4D BATTERY AMD FALC50 FALCON900 2700160 EU CELL BLOCK UNAPPROVED PART B JGVR K NONE W INADEQUATE Q C IN INSP/MAINT 1 CE 09 131 TWO UNAUTHORIZED CELLS INSTALLED IN BATTERY BLOCK. UNAUTHORIZED CELLS REPLACEMENTS PERFORMED USING UNACCEPTABLE PRACTIC ES. RECOMMEND REPLACEMENT OF ENTIRE CELL BLOCK. 2 L 7 3 4F RT A46EU 2001041700103 20010417 00103 EA 2001 4 17 20010413CW011 2 20010327 G 7414 10682016 GEAR LYC O540 O540* 41532 EA MAGNETO BROKEN D K NONE O OTHER IN INSP/MAINT 1 GL 23 HAVE FOUND 3 GEARS WITH 1 TOOTH BROKEN. WERE FOUND A 500 HOUR MAG INSPECTION AFTER ENGINE QUIT ON LANDING. FOUND 2 MOR E GEARS WITH SEVERAL TEETH MISSING. MAGNETO JUMPED INTERNAL TIME. 3 O E295 2001041700104 20010417 00104 CE 2001 4 17 20010413CW013 1 20010308 G 3233 ACTUATOR CESSNA 172 172R 2072401 CE LYC O360 O360F1A6 41514 EA MCAULY 2D34C B2D34C220 GL MLG DISTORTED D K NONE O OTHER IN INSP/MAINT 1 SW 15 6189R 8567 172RG0109 L2760936A 951813 FOUND CRACKS ON BOTH SIDES OF SADDLE SHAPED HOLE OF ACTUATOR BODY . 1 H 7 1 3O 3 O NT 3A12 E286 5 C P7EA 2001041700112 20010417 00112 CE 2001 4 17 20010416CW002 1 20010416 G 5540 STRUCTURE CESSNA 206 TU206G 2073357 CE CONT O520 TSIO520* 17040 SO RUDDER DAMAGED D K NONE O OTHER IN INSP/MAINT 1 GL 15 12TL U20606464 THE 206 SEAPLANE RUDDER ASSEMBLY IS PRONE TO DAMAGE AFT OF PN 12310661, DOUBLER AT THE BOTTOM OF THE RUDDER. DAMAGE OF THIS NATURE IS EVIDENT BY A KINK AT THE BOTTOM OF THE RUDDER ON BOTH SIDES. THIS DAMAGE IS CAUSED BY THE WIND WHEN A R UDDER LOCK IS NOT USED. IF RUDDER IS INSTALLED, A RUDDER LOCK SHOULD BE USED WHENEVER AIRCRAFT IS STORED OUTSIDE. ALSO , THIS AREA SHOULD BE CHECKED DURING PREFLIGHT. 1 H 7 1 3O 3 O A4CE E8CE 2001041700114 20010417 00114 SO 2001 4 17 20010416CW006 1 20010108 G 5740 ATTACH FITTING PIPER PA32 PA32RT300 7103215 SO LYC O540 IO540* 41532 EA LT WING CRACKED D K NONE O OTHER IN INSP/MAINT 1 EA 25 6873C 2451 32R7885034 INSPECTED AIRFRAME, FOUND THREE SEPARATE CRACKS IN THE LEFT WING FORWARD ATTACH FITTING AREA. 1 L 7 1 3O 3 O A3SO 1E4 2001041700115 20010417 00115 CE 2001 4 17 20010416CW007 1 20010119 G 5540 07126161 BULKHEAD CESSNA 182 182E 2072712 CE CONT O470 O470* 17026 SO RUDDER CRACKED D K NONE O OTHER IN INSP/MAINT 1 NM 03 9298X 4103 18253698 WHILE PERFORMING A PRE PURCHASE LOOKOVER, FOUND A STOP DRILLED CRACK IN THE UPPER RADIUS ABOVE THE LEFT RUDDER STOP BOL T. FURTHER INSPECTION FOUND ANOTHER CRACK RADIATING OUTWARD FROM THE UPPER OUTBOARD EDGE OF THE UPPER RIGHT LIGHTENING HOLE. 1 H 7 1 3O 3 O NT 3A13 E273 2001041700116 20010417 00116 NE 2001 4 17 20010416CW009 2 20010110 G 7321 324476810 FUEL CONTROL BEECH 200 B200 1152922 CE PWA PT6 PT6A42 52043 NE LT ENGINE INOPERATIVE D A UNSCHED LANDING X J ENGINE FLAMEOUT WARNING INDICATION NR NOT REPORTED 1 NM 09 63791 1769 BB1100 93649 DURING TRAINING FLIGHT IN AN EMERGENCY DECENT SIMILATION, THE LEFT ENGINE FLAMED OUT AND COULD NOT BE RESTARTED. REPLAC ED THE FUEL CONTROL AND OPERATION IS NORMAL. 1 L 7 2 4T 4 T A24CE E4EA 2001041700117 20010417 00117 CE 2001 4 17 20010416CW010 1 20010313 G 2750 500000863 CONTROL CABLE CESSNA 414 414A 2075907 CE CONT O520 TSIO520* 17040 SO TE FLAPS BROKEN D K NONE O OTHER IN INSP/MAINT 1 CE 09 414JK 6160 414A0626 CABLE SNAPPED BY FIRST PULLEY OUTBOARD OF FLAP MOTOR, RIGHT SIDE. NO EVIDENCE OF WEAR OR CORROSION. PULLEY WAS TURNIN G FREE. FAILURE CAUSED SPLIT FLAPS ON LANDING. 1 L 7 2 3O 3 O A7CE E8CE 2001041700118 20010417 00118 EA 2001 4 17 20010416CW011 2 20010223 G 7421 RHB37E SPARK PLUG CESSNA 206 T206H CE LYC O540 TIO540* 41532 EA ENGINE INOPERATIVE D K NONE O OTHER IN INSP/MAINT 1 GL 13 929MA 211 T20608107 L1031161A UPON ANNUAL INSPECTION, FOUND 2 SPARK PLUGS NOT WORKING. CERAMIC ON TERMINAL END WAS LOOSE INSIDE THE PLUG. REMOVED AN D REPLACED. 1 H 7 1 3O 3 O A4CE E14EA 2001041700119 20010417 00119 GL 2001 4 17 20010416CW012 2 20010325 G 7323 23057869 GOVERNOR HUGHES 369 369D 4470706 WP ALLSN 250C 250C20B 03013 GL ENGINE FAILED D K NONE O OTHER IN INSP/MAINT 1 WP 09 5187S C10968DV GOVERNOR FAILURES RANGE FROM 72 HOURS TO 1750 HOURS. 1 G 7 1 3U 3 U H3WE E4CE 2001041700120 20010417 00120 GL 2001 4 17 20010416CW013 2 20010325 G 7323 23057869 GOVERNOR HUGHES 369 369D 4470706 WP ALLSN 250C 250C20B 03013 GL ENGINE FAILED D K NONE O OTHER IN INSP/MAINT 1 WP 09 9106Z 800776D GOVERNOR FAILURES RANGE FROM 72 HOURS TO 1750 HOURS. 1 G 7 1 3U 3 U H3WE E4CE 2001041700121 20010417 00121 GL 2001 4 17 20010416CW014 2 20010325 G 7323 23057869 GOVERNOR HUGHES 369 369D 4470706 WP ALLSN 250C 250C20B 03013 GL ENGINE FAILED D K NONE O OTHER IN INSP/MAINT 1 WP 09 5200Y 1198D GOVERNOR FAILURES RANGE FROM 72 HOURS TO 1750 HOURS. 1 G 7 1 3U 3 U H3WE E4CE 2001041700222 20010417 00222 GL 2001 4 17 20010416CW015 2 20010325 G 7323 23057869 GOVERNOR HUGHES 369 369D 4470706 WP ALLSN 250C 250C20B 03013 GL ENGINE FAILED D K NONE O OTHER IN INSP/MAINT 1 WP 09 4575Z 370094D GOVERNOR FAILURES RANGE FROM 72 HOURS TO 1750 HOURS. 1 G 7 1 3U 3 U H3WE E4CE 2001041700226 20010417 00226 GL 2001 4 17 20010416CW016 2 20010325 G 7323 230578 GOVERNOR HUGHES 369 369D 4470706 WP ALLSN 250C 250C20 03013 GL ENGINE FAILED D K NONE O OTHER IN INSP/MAINT 1 WP 09 5108E 811075D GOVERNOR FAILURE RANGES FROM 72 HOURS TO 1750 HOURS. 1 G 7 1 3U 3 U H3WE E4CE 2001041700227 20010417 00227 CE 2001 4 17 20010416CW017 1 20010305 G 2450 VR515GA VOLT REGULATOR CESSNA 182 182Q 2072732 CE CONT O470 O470* 17026 SO ELECTRICAL FAILED D K NONE O OTHER IN INSP/MAINT 1 WP 23 4603N 36 18267280 VOLTAGE REGULATOR WAS INSTALLED, AIRCREW SQUAWKED LOW VOLTAGE WARNNG LIGHT REMAINED ON AT ALL POWER SETTINGS. TROUBLESH OOTING DETERMINED OUTPUT VOLTAGE WAS BELOW MINIMUM OUTPUT AND ERRATIC. VISUAL INSPECTION OF THE REGULATOR INDICATED NO SIGNS OF EXTERIOR DEFECTOR DAMANAGE. NO DISASSEMBLY WAS ATTEMPTED. 1 H 7 1 3O 3 O NT 3A13 E273 2001041700235 20010417 00235 EA 2001 4 17 20010416CW018 2 20010315 G 7322 MA3PA FLOAT CESSNA 150 152 2071835 CE LYC O235 O235L2C 41505 EA CARBURETOR CRACKED D VCTA K NONE O OTHER IN INSP/MAINT 1 EA 17 89061 442 442 15282616 1082315 DURING A 50 HOUR INSPECTION, PM CHECK ON AIRCRAFT RUN UP FOUND AIRCRAFT NOT SMOOTH RUN. AFTER CHECKING THE CARB, FOUND CRACKED FLOAT. MADE AIRCRAFT RUN RICH. THIS COULD TURN INTO A DANGER IN THE AIR. THIS REPLACEMENT OF THE OLDER, BETT ER BRASS FLOAT WAS NOT GOOD. 1 H 7 1 3O 3 O NT 3A19 E223 2001041700093 20010417 00093 CE 2001 4 17 20010417AP002 1 20010125 G 5711 SPAR BBAVIA 7 7KCAB 21101P3 CE WINGS DAMAGED P K NONE O OTHER IN INSP/MAINT 1 SW 99 6369N 2881 44 WOOD SPARS; NAILS OUT OF LEADING EDGE RIBS; WOODEN SPACERS WERE LEFTOUT OF FIRST FOUR IN-BOARD LEADINGEDGE RIBS; LEADING EDGE LOOSE; NAILSLOOSE; SOMEBODY HAD PATCHED UP BEFORE AND PUT SCREWS INSTEAD OF NAILS ON LEADING EDGE SPARS AND RIBS; SOME RIBS CRACKED; INNER RIB LACING CORDS BROKE; HAVE JUNKED WINGS AND REPLACING WITH NEW METAL SPAR WINGS LATER THIS Y EAR. 1 H 7 1 3O A759 2001041700146 20010417 00146 GL 2001 4 17 20010417AP003 1 20010411 G 5610 CANOPY AMTR LONGEZ LONGEZ 05690Z8 GL LYC O540 IO540* 41532 EA CANOPY LATCH FAILED G A UNSCHED LANDING O OTHER NR NOT REPORTED 1 SW 99 5439N 240 240 CANOPY SHATTERED IN FLIGHT, DEPARTED AIRCRAFT AND HIT PROP, DESTROYING PROP. PILOT MADE EMERGENCY LANDING. IT APPEARS TH E LONG-EZ CANOPY FRAME LATCH PASSED THROUGH THE FRAME AND RESTED ON THE GLASS. THE GLASS SHATTERED. 1 M 7 1 3O 3 O RT EXPA1M71 1E4 2001050200077 20010502 00077 CE 2001 5 2 20010417AP004 1 20010412 G 5210 ROD BEECH MU300 400A 1155402 CE PAX DOOR MISSING B O OTHER W INADEQUATE Q C TX TAXI/GRND HDL 1 GL 15 695TA RK310 CABIN DOOR WILL NOT OPEN FROM INSIDE OR OURSIDE. AFT PINS DO NOT RELEASE WHEN HANDLE IS MOVED. FOUND THE ACTUATING ROD M ISSING THE ROD END COTTER PIN. REINSTALLED THE PIN AND COTTER PINNED. OPERATION CHECK NORMAL. 2 H 7 2 4F RT A16SW 2001041700113 20010417 00113 SO 2001 4 17 20010417AP005 1 20010416 G 3213 7873804 STRUT PIPER PA32 PA32301 7103207 SO LT MLG CRACKED B K NONE O OTHER IN INSP/MAINT 1 CE 01 4291Y 3639 328306016 DURING ANNUAL INSPECTION FOUND LEFT LOWER MAIN GEAR STRUT CRACKED AT THE ATTACHMENT OF THE STRUT TO THE AXLE SHAFT. THE STRUT CASTING WAS CRACKED IN TWO DIFFERENT PLACES WITH ONE CRACK MEASURING OVER 1 INCH IN LENGTH. EXAMINATION OF THE RIG HT STRUT FOUND NO DAMAGE. REVIEW OF THE AIRCRAFT MAINTENANCE RECORDS REVEALED A LANDING ACCIDENT SEVERAL YEARS AGO. TECH NICIAN RECOMMENDS DURING INSPECTIONS TO PLAY CLOSE ATTENTION TO MAIN GEAR CASTING. 1 L 7 1 3O A3SO 2001042300337 20010423 00337 2001 4 23 20010418CW001 4 20010418 G 3422 GYRO CESSNA 182 182 2072702 CE CONT O470 O470* 17026 SO COCKPIT INOPERATIVE D K NONE O OTHER IN INSP/MAINT 1 SW 01 6312A 33112 DURING ROUTINE ANNUAL INSPECTION THE ELEVATOR WAS FOUND TO TRAVEL ONLY 19 DEGREE UP. THE TYPE CERTIFICATE CALLS FOR 25 DEGREE. INVESTIGATION FOUND THE D. G. MOUNTED DIRECTLY ABOVE THE CONTROL WHEEL TUBE. AS THE WHEEL WAS PULLED AFT THE A N3-10A BOLT CONTACTED THE D.G. STOPPING THE TRAVEL. 1 H 7 1 3O 3 O NT 3A13 E273 2001042400233 20010424 00233 CE 2001 4 24 20010418CW002 1 20010418 G 5412 FASTENER CESSNA 182 182 2072702 CE FIREWALL LOOSE D K NONE O OTHER IN INSP/MAINT 1 SW 01 5590B 33590 OWNER REPORTED 2 LOOSE RIVETS AT THE FIREWALL ATTACH POINT STA. 5. INVESTIGATION REVEALED 2 MISSING RIVET HEADS AN426A D4 AND A FURTHER 25 RIVET HEADS HELD ON BY PAINT ALONE. 1 OTHER RIVET HEAD HAD A STRANGE APPEARANCE, SCRAPING THE PAINT OFF REVEALED A BONDO MATERIAL FILLING THE HOLE. THE AIRPLANE HAD BEEN REPAINTED IN ABOUT 1988 BY PERSONS UNKNOWN. 1 H 7 1 3O NT 3A13 2001042400234 20010424 00234 CE 2001 4 24 20010418CW003 1 20010418 G 7120 HEAT SHIELD CESSNA 182 182 2072702 CE ENGINE MOUNT MISSING D K NONE O OTHER IN INSP/MAINT 1 SW 01 5590B 33590 THE ENGINE MOUNT HEAT SHIELDS HAD BEEN REMOVED AT SOME POINT ALLOWING HEAT DAMAGE REQUIRING 3 WELD REPAIRS. 1 H 7 1 3O NT 3A13 2001042400235 20010424 00235 CE 2001 4 24 20010418CW004 1 20010418 G 2432 WIRE CESSNA 182 182 2072702 CE CONT O470 O470* 17026 SO BATTERY DAMAGED D K NONE O OTHER IN INSP/MAINT 1 SW 01 5590B 33590 THE BATTERY CABLE WAS BARE IN MANY PLACES INCLUDING THE PENETRATION OF THE FIREWALL. IT HAD ALSO BEEN PENETRATED BY A S CREW THROUGH THE BELLY OF AIRCRAFT, JUST FORWARD OF THE BATTERY BOX. 1 H 7 1 3O 3 O NT 3A13 E273 2001042400257 20010424 00257 2001 4 24 20010418CW005 4 20010418 G 3422 GYRO CESSNA 182 182 2072702 CE COCKPIT MISINSTALLED D K NONE W INADEQUATE Q C IN INSP/MAINT 1 SW 01 5590B 33590 THE DIRECTIONAL GYRO WAS POWERED BY A WIRE OF THREE SIZES NR 12, NR 16 AND NR 18, SPLICED TOGETHER OVER A LENGTH OF 20 INCHES, THE LARGE END WAS BENT INTO A HOOK, TINNED WITH SOLDER AND CONNECTED TO THE AMMETER. 1 H 7 1 3O NT 3A13 2001042400259 20010424 00259 CE 2001 4 24 20010418CW007 1 20010402 G 2720 12606421 SPROCKET CESSNA CESSNA 206 206H 2073301 CE LYC O540 IO540* 41532 EA IDLER MALADJUSTMENT B YFRS K NONE O OTHER IN INSP/MAINT 1 SO 07 2446X 08097 EXCESSIVE LEFT RUDDER PETAL PRESSURE REQUIRED TO MAINTAIN STRAIGHT AND LEVEL FLIGHT. FOUND TRIM CHAIN TENSION ADJUSTMEN T IDLER SPROCKET SLIPPED IN ADJUSTMENT SLOT. TRIM CHAIN JUMPED POSITION ON STEERING BUNGEE GEAR, CAMPING LIMITED LEFT R UDDER TRIM. RUDDER TRIM RIGGING RESET, AIRCRAFT FLIGHT CHECKED, RUDDER CONTROL SYSTEM AND RUDDER TRIM OPERATION NORMAL. 1 H 7 1 3O 3 O RT A4CE 1E4 2001042400260 20010424 00260 CE 2001 4 24 20010418CW008 1 20010307 G 2497 WIRE CESSNA 150 150L 2071826 CE CONT O200 O200* 17020 SO INSTRUMENT PANEL CHAFED D K NONE O OTHER IN INSP/MAINT 1 WP 11 5427Q 15073327 WIRE SHIELDING CHAFED OTHER WIRES IN SAME BUNDLE CAUSING MULTIPLE SHORTS. OCCURRED IN FORMAL OPERATION. PROBABLE CAUSE WAS SHIELDING ON PB 10 TOUGHER THAN INSOLATION IN OTHER WIRES CAUSING SEVERE WEAR. TO PREVENT RECURRENCE PB 10 NEEDS A SLEEVE OR COVER OVER SHIELDING OR ISOLATE PB 10 FROM THE REST OF THE WIRE BUNDLE. 1 H 7 1 3O 3 O 3A19 E252 2001042400261 20010424 00261 CE 2001 4 24 20010418CW009 1 20010308 G 2432 S337711 SWITCH CESSNA 172 172S 2072439 CE COCKPIT INOPERATIVE D K NONE O OTHER IN INSP/MAINT 1 NM 03 789EP 1003 1003 172S8135 PILOT REPORTED AVIONICS MASTER SWITCH INOPERATIVE, WHEN BATTERY SWITCH IS TURNED ON, ALL AVIONICS LEFT IN ON POSITION P OWER UP REGARDLESS OF AVIONICS MASTER SWITCH POSITION. MAINTENANCE FOUND ONE SIDE OF AVIONICS MASTER SWITCH INOPERATIVE . REPLACED AVIONICS MASTER SWITCH. OPERATIONAL CHECKED SATISFACTORY. 1 H 7 1 3O NT 3A12 2001042400262 20010424 00262 CE 2001 4 24 20010418CW010 1 20010312 G 2510 051421224 SEAT BACK CESSNA 172 172S 2072439 CE COCKPIT BENT D K NONE O OTHER IN INSP/MAINT 1 NM 03 789EP 1003 1003 172S8135 MAINTENANCE FOUND RIGHT FROMT SEAT BACK RECLINED APPROXIMATELY 4 INCHES FROM NORMAL UPRIGHT POSITION. THE SEAT WAS REMO VED AND INSPECTED, FINDING THE SEAT BACK FRAME BENT. THE FRAME WAS BENT ON THE LEFT SIDE JUST ABOVE THE ATTACH FORGING PN 05142158. REPLACED SEAT BACK FRAME. 1 H 7 1 3O NT 3A12 2001042400263 20010424 00263 CE 2001 4 24 20010419CW001 1 20010314 G 2701 05600145 YOKE CESSNA 172 172P 2072436 CE LYC O320 O320D2J 41508 EA CONTROL COLUMN CORRODED D K NONE O OTHER IN INSP/MAINT 1 SO 09 97662 12525 17276219 MAINTENANCE TECH FOUND AREA BELOW PIVET BOLT EXCESSIVELY COVERED TO THE POINT OF EXFOLIATION. WHEN DRILLING THE INSPECT ION HOLE CALLED FOR, THE DRILL BIT ACTUALLY FELL THROUGH AFTER APPROXIMATELY 2 TURNS OF THE BIT. CENTRAL YOKE WAS REPLA CED AT THIS TIME. TECH STRONGLY RECOMMENDS THIS PROCEDURE SHOULD BECOME AN AIRWORTHINESS DIRECTIVE. 1 H 7 1 3O 3 O NT 3A12 E274 2001042400264 20010424 00264 SW 2001 4 24 20010419CW005 1 20010220 G 3210 110538 NUT BBAVIA 7 7GCBC 1220601 SW LYC O320 O320* 41508 EA MLG AXLE MISMANUFACTURED D K NONE W INADEQUATE Q C IN INSP/MAINT 1 EA 25 613PC 125598 FOUND NEW AXLE NUTS TO HAVE CHAMFER CUT ON INSIDE DIAMETER, WHERE NUT CONTACTS BEARING. CONTACTED MFG., CONFIRMED THAT NO CHAMFER SHOULD BE PRESENT ON INSIDE DIAMETER. 1 H 7 1 3O 3 O NC A759 E274 2001042000076 20010420 00076 EA 2001 4 20 20010419CW006 2 20010319 G 7414 10157120Y PINION GEAR BENDIX ROBSIN R44 R44 7640120 WP LYC O540 O540F1B5 41532 EA ENG LT MAGNETO MALFUNCTIONED D K NONE O OTHER IN INSP/MAINT 1 AL 01 71330 C049605 0542 ENGINE QUIT WHEN LEFT MAG WAS SELECTED DURING MAG CHECK AFTER START. RESTART WAS UNEVENTFUL. WITH MAG SWITCH IN BOTH, ENG WOULD NOT DEVELOP POWER, BEGAN BACKFIRING AND AFTERFIRING. ATTEMPT TO CHECK MAG TIMING, FOUND THE ENG LT MAG WOUL D ONLY TURN INTERMITTENT WITH ENG. MAG AND ALL SPARK PLUGS WERE REPLACED DUE TO HEAVY LEAD AND CARBON FOULING. LOWER PL UGS HAD LEAD BRIDGING GAP. ENG OPS CHECKED GOOD. PILOT REPORTED HISTORY OF DIFFICULT STARTING. LEFT MAG CONTAINS RET ARD POINTS. TEARDOWN FOUND WOODRUFF KEY SLOT IN PINION GEAR WORN TO A WIDTH OF 90 DEGREES ROTATION WITH OVER HALF OF MA TERIAL BETWEEN THE GEAR ID AND TEETH GROOVES WORN AWAY. TIMING GEAR TEETH WERE MISSING AND MAG CASE FILLED WITH DEBRIS. 1 G 7 1 3O 3 O H11NM E295 2001042400265 20010424 00265 EU 2001 4 24 20010419CW007 1 20010306 G 2420 P610151 ROTOR AUXILEC AEROSP ATR72 ATR72202 8680940 EU GENERATOR SHORTED B XC4R K NONE O OTHER IN INSP/MAINT 1 SO 19 1227 MAIN STATOR WINDINGS ON ROTOR ASSEMBLY SHORTED OUT AFTER 41.8 FLIGHT HOURS, SINCE OVERHAUL. THIS WAS A NEWLY MODIFIED R OTOR. THIS IS A POORLY DESIGNED ROTOR, PREVIOUS PN WAS P603744A, WHICH ALSO HAD A PROBLEM AND CAME APART WHILE IN OPERA TION. 2 H 7 2 4T RT A53EU 2001042000229 20010420 00229 SW 2001 4 20 20010419CW008 1 20010319 G 6730 41002437 LEVER TEXTRON BELL 214 214B 1182100 SW SERVO ACTUATOR CRACKED B K NONE O OTHER IN INSP/MAINT 1 NM 07 1228B CRACKING DETECTED ON TANG EDGE OF LEVER ASSEMBLY. 2 G 7 1 4U H6SW 2001042400273 20010424 00273 SW 2001 4 24 20010419CW012 1 20010402 G 5711 SPAR BBAVIA 7 7ECA 21101NN SW LYC O235 O235* 41505 EA RT WING CRACKED D K NONE O OTHER IN INSP/MAINT 1 SW 99 6309N 233 A LONGITUDINAL CRACK IN THE RIGHT FORWARD WOODEN WING SPAR, APPROXIMATELY 30 INCHES LONG. 1 H 7 1 3O 3 O A759 E223 2001042000282 20010420 00282 WP 2001 4 20 20010419CW013 1 20010316 G 6322 369A56553 BEARING HUGHES 369 369D 4470706 WP ALLSN 250C 250C20B 03013 GL BLOWER ASSY DAMAGED D O OTHER E VIBRATION/BUFFET TX TAXI/GRND HDL 1 NM 02 622PB 880318D 831268 DURING SHUTDOWN, A LOUD GRINDING AND POPPING WAS HEARD COMING FROM THE TRANSMISSION AREA. OIL COOLER BLOWER ASSY PN 369 025630-101 WAS REMOVED AND DISSASSEMBLED FOR INSPECTION. THE LOWER BLOWER BEARING PN 369A5655-3 HAD FAILED. IT IS SUS PECTED THAT THE BEARING CAGE FAILED AS NUMEROUS PIECES OF CAGE MATERIAL WAS RECOVERED. THIS BEARING HAS A RL OF 1200 HO URS. PART TT AT FAILURE WAS 515.4 BEARING RETAINED FOR 90 DAYS AS EXHIBIT. 1 G 7 1 3U 3 U H3WE E4CE 2001042400278 20010424 00278 NE 2001 4 24 20010420CW001 2 20010221 G 7230 COMPRESSOR PWA JT8 JT8D9A 52048 NE ENGINE DAMAGED D K NONE O OTHER IN INSP/MAINT 1 SO 19 48961 P667085 ENGINE WAS RECEIVED AT ENGINE SHOP FOR REPAIR DUE TO SUSPECTED OIL LEAK AS REPORTED BY THE CUSTOMER. DURING THE DISASS EMBLY OF THE HIGH COMPRESSOR MODULE, IT WAS DISCOVERED THAT THE COMPRESSOR DISKS STAGES NUMBER 8 AND 9 EXHIBITED A MELTI NG CONDITION DUE TO AN EXTREMELY HIGH HEAT EXPOSURE. THE C9 STAGE DISK BORE WAS MELTED COMPLETELY AND ROLLED OUT OF POS ITION. 4 F E2EA 2001042400280 20010424 00280 SO 2001 4 24 20010420CW003 1 20010315 G 3340 6446 FLUX DETECTOR STEC PIPER PA28 PA28181 7102807 SO LYC O360 O360A1D 41514 EA LT WING TIP MALFUNCTIONED B PIQR K NONE L NO TEST IN INSP/MAINT 1 EA 21 181LS 354 FV5842 2843227 FOUND LONGLIGHT AND STROBES PULLING HSI OFF HEADING IN EXCESS OF 10 DEGREES. NO PLACARDS INSTALLED OR REQUIRED TO NOTIF Y PILOT OF THIS CONDITION. 1 L 7 1 3O 3 O 2A13 E286 2001042400285 20010424 00285 CE 2001 4 24 20010420CW007 1 20010402 G 7170 AV171C47 O-RING CESSNA 182 182 2072702 CE QUICKDRAIN LEAKING G K NONE O OTHER IN INSP/MAINT 1 NM 07 200 THE QUICK DRAIN ORING THAT CAME WITH THE NEW QUICK DRAIN, SWELLED UP SO THAT IT IS PUSHED OUT OF THE GROOVE. OIL LEAKS PASSED IT EASILY. 1 H 7 1 3O NT 3A13 2001042400286 20010424 00286 GL 2001 4 24 20010420CW008 1 20010402 G 5210 LATCH AMTR LONGEZ LONGEZ 05690Z8 GL LYC O540 IO540* 41532 EA CANOPY FAILED H K NONE O OTHER IN INSP/MAINT 1 GL 23 5439N 98110139 CANOPY DEPARTED THE AIRCRAFT WHILE IN FLIGHT. CANOPY LATCH FAILED. 1 M 7 1 3O 3 O RT EXPA1M71 1E4 2001042300346 20010423 00346 EA 2001 4 23 20010420CW009 2 20010316 G 8520 LW11021 BEARING SCWZER 269 269D 8059501 EA LYC O360 HIO360D1A 41514 EA NR 2 DAMAGED D K NONE O OTHER IN INSP/MAINT 1 WP 15 7430F 187 150 1150452 RL2096751A AT 25 HOUR OIL CHANGE, FOUND METAL PARTICLES IN SUCTION SCREEN AND FILTER. ON INSPECTION, FOUND NR 2 MAIN BEARING HAD S PUN NEARLY CAUSING ENGINE FAILURE. CHECK SCREENS. 1 G 7 1 3U 3 O 0 4H12 1E10 2001042400289 20010424 00289 CE 2001 4 24 20010420CW011 1 20010309 G 2910 S217840105 HYDRAULIC LINE CESSNA 172 172RG 2072438 CE LYC O360 IO360A1A 41514 EA NOSE ACTUATOR BROKEN D K NONE O OTHER IN INSP/MAINT 1 GL 19 9864B 34151 172RG1060 NOSE GEAR UP HOSE PNS217840105 CAME OUT OF SWEDGE FITTING. 1 H 7 1 3O 3 O 3A17 1E10 2001042400308 20010424 00308 CE 2001 4 24 20010423CW004 1 20010330 G 7110 J744436 MOUNT CESSNA 172 172R 2072401 CE ENGINE COWLING TORN D CMXS K NONE O OTHER IN INSP/MAINT 1 CE 05 453CM 350 17280845 RUBBER TORN FROM MOUNTING PLATE. 1 H 7 1 3O NT 3A12 2001042400309 20010424 00309 CE 2001 4 24 20010423CW005 1 20010402 G 2701 0411257 UNIVERSAL JOINT CESSNA 172 172R 2072401 CE CONTROL WHEEL CORRODED D CMXS K NONE O OTHER IN INSP/MAINT 1 CE 05 455CM 399 17280847 PIVOTS RUSTY, WOULD NOT SWIVAL, U JOINT COVERED BY RUBBER BOOT. PILOT REPORTED AILERONS HARD TO MOVE. 1 H 7 1 3O NT 3A12 2001042400310 20010424 00310 EA 2001 4 24 20010423CW006 2 20010330 G 8520 LN18840 CAMSHAFT CESSNA 172 172R 2072401 CE LYC IO360 IO360L2A EA LOBES WORN D CMXS K NONE O OTHER IN INSP/MAINT 1 CE 05 467CM 590 17280859 LZ871551A CAMSHAFT WORN ON NR 5 LOBE. CYLINDERS NR 3 AND NR 4 INTAKE VALVE NOT OPENING FULLY. PILOT REPORTED ENGINE RUNNING R OUGH. 1 H 7 1 3O 3 O NT 3A12 1E10 2001042400317 20010424 00317 EA 2001 4 24 20010423CW013 2 20010326 G 7414 M3548 ROTOR SLICK PIPER PA28 PA28181 7102807 SO LYC O360 O360A4M 41514 EA MAGNETO BROKEN B UC2R K NONE O OTHER IN INSP/MAINT 1 GL 19 4148V 1653 98040879 2843178 L3625536A PILOT REPORTED EXCESSIVE MAG DROP. FOUND RIGHT MAGNETO ROTOR ASSEMBLY CAM SLOT TO BE BROKEN. 1 L 7 1 3O 3 O 2A13 E286 2001042400318 20010424 00318 SO 2001 4 24 20010423CW014 1 20010403 G 2421 ALE1003K PLATE ELECTROSYS PIPER PA28 PA28181 7102807 SO LYC O360 O360A4M 41514 EA ALTERNATOR BROKEN B UC2R K NONE O OTHER IN INSP/MAINT 1 GL 19 4146T 1709 8053286 2843168 L3620536A DURING ROUTINE MAINTENANCE THE ALTERNATOR END PLATE WAS FOUND WITH THE FORWARD ATTACH EAR BROKEN OFF. 1 L 7 1 3O 3 O 2A13 E286 2001050200280 20010502 00280 CE 2001 5 2 20010424CW001 1 20010131 G 2750 169524074 CONTROL CABLE BEECH 23 B24R 1151253 CE TE FLAPS FRAYED B K NONE O OTHER IN INSP/MAINT 1 GL 17 9321S MC341 DURING ANNUAL INSPECTION, CABLE WAS INSPECTED AND FOUND TO HAVE SEVERAL BROKEN STRANDS. AFTER FURTHER INSPECTION, FOUND THAT FLAP CABLE 169-524074 WAS CONTACTING A SCREW HEAD WHEN THE FLAPS ARE IN THE UP POSITION. RECOMMEND THAT PROTECTIV E TAPE BE PUT OVER THE SCREW AND TO MONITER FLAP CABLE EVERY 1000 HOURS. 1 L 7 1 3O A1CE 2001050300107 20010503 00107 WP 2001 5 3 20010424CW008 2 20010406 G 7200 30756392 SEAL GARRTT TFE731 TFE7315R 01518 WP NR 4 FAILED D K NONE O OTHER IN INSP/MAINT 1 GL 19 6972 P91222 NR 4 RUNNER FAILED CAUSING DAMAGE TO NEARBY COMPONENTS. 4 F E6WE 2001050200294 20010502 00294 CE 2001 5 2 20010425CW007 1 20010323 G 2710 1260141 TUBE CESSNA 182 R182 2072734 CE LYC O540 O540* 41532 EA AILERON CONTROL LOOSE B GSZR K NONE O OTHER IN INSP/MAINT 1 SW 19 6161S 6001 R18201633 DURING ANNUAL INSPECTION THE TWO ALUMINUM RIVETS SECURING THE FORWARD END OF SHAFT WERE FOUND LOOSE AND THE BUCK TAILS M ISSING . THE SQUARK TUBE PORTION OF ASSEMBLY APPEARS TO BE ALUMINUM. THE FORWARD THREADED END IS STEEL. THE FIT OF TH E TWO PARTS IS NOT VERY CLOSE. FOUND SHAFT ON FORWARD END OF TUBE WORN WERE IT IS INSTALLED IN BEARING BLOCK. IF THE T WO RIVETS HAD FALLEN OUT, IT COULD HAVE RESULTED IN TOTAL LOSS OF AILERON CONTROL.(PHOTOS) 1 H 7 1 3O 3 O RT 3A13 E295 2001050300396 20010503 00396 CE 2001 5 3 20010425CW009 1 20010402 G 2910 24411003 PIVOT CESSNA 172 172RG 2072438 CE LYC O360 O360* 41514 EA MLG CRACKED B WIWR K NONE O OTHER IN INSP/MAINT 1 WP 07 6623Z 172RG0240 BOTH PIVOTS WERE FOUND CRACKED. THE RIGHT PIVOT WAS NOT ONLY CRACKED BUT SHOWED SIGNS THAT THE SPLINNED END WAS STARTIN G TO TWIST OFF. BOTH PIVOTS CRACKS WERE VISABLE WITH THE NAKED EYE, AND NEITHER LEAKED BRAKE FLUID THROUGH THE CRACKS A ND INTO THE ACTUATOR. BOTH PIVOTS WERE ALSO THE OLDER ORIGINAL STYLE. 1 H 7 1 3O 3 O 3A17 E286 2001050300158 20010503 00158 SO 2001 5 3 20010426CW010 2 20010123 G 8530 CYLINDER HEAD CONT O520 IO520F 17032 SO ENGINE CRACKED B CY4R K NONE O OTHER IN INSP/MAINT 1 AL 03 1697 286416R CYLINDERS CRACKED ON THE INTAKE SEAT TO NOZZLE AND OR INJECTOR HOLE. CYLINDER SERIAL NUMBERS: (52L962936), 52L96293 7, 52L962938, 52L962799. 3 O E5CE 2001050300159 20010503 00159 SO 2001 5 3 20010426CW011 2 20010123 G 8530 CYLINDER HEAD CONT O520 IO520F 17032 SO ENGINE CRACKED B CY4R K NONE O OTHER IN INSP/MAINT 1 AL 03 1697 286416R CYLINDER HEADS CRACKED ON THE INTAKE SEAT TO NOZZLE AND OR INJECTOR HOLE. CYLINDER HEAD SERIAL NUMBERS: 52L962936, (5 2L962937), 52L962938, 52L962799. 3 O E5CE 2001050300160 20010503 00160 SO 2001 5 3 20010426CW012 2 20010123 G 8530 CYLINDER HEAD CONT O520 IO520F 17032 SO ENGINE CRACKED C CY4R K NONE O OTHER IN INSP/MAINT 1 AL 03 1697 286416R CYLINDER HEADS CRACKED ON THE INTAKE SEAT TO NOZZLE AND OR INJECTOR HOLE. CYLINDER HEAD SERIAL NUMBERS: 52L962936, 52L962937, (52L962938), 52L962799. 3 O E5CE 2001050300161 20010503 00161 SO 2001 5 3 20010426CW013 2 20010123 G 8530 CYLINDER HEAD CONT O520 IO520F 17032 SO ENGINE CRACKED B CY4R K NONE O OTHER IN INSP/MAINT 1 AL 03 1697 286416R CYLINDER HEADS CRACKED ON THE INTAKE SEAT TO NOZZLE AND OR INJECTOR HOLE. CYLINDER HEAD SERIAL NUMBERS: 52L962936, 5 2L962937, 52L962938, (52L962799). 3 O E5CE 2001050300229 20010503 00229 SO 2001 5 3 20010426CW015 2 20010213 G 8530 SA52000A20P CYLINDER HEAD CONT O520 IO520* 17032 SO ENGINE CRACKED B CY4R K NONE O OTHER IN INSP/MAINT 1 AL 03 1342 CYLINDERS HAVE CRACKS ADJACENT TO EXHAUST SEAT AND INTAKE SEATS BETWEEN FINS 14 AND 20. CYLINDER SERIAL NUMBERS: (52J9 76779), 52J976780, 52J976781, 52J976782, 52J976787, 52J976788. 3 O E5CE 2001050900003 20010509 00003 SO 2001 5 9 20010426CW016 2 20010213 G 8530 SA52000A20P CYLINDER HEAD CONT O520 IO520* 17032 SO ENGINE CRACKED B CY4R K NONE O OTHER IN INSP/MAINT 1 AL 03 1342 CYLINDER CRACKS ADJACENT TO EXHAUST SEAT AND INTAKE SEAT BETWEEN FINS 14 AND 20. CYLINDER SERIAL NUMBERS: 52J976779, (52J976780), 52J976781, 52J976782, 52J976787, 52J976788. 3 O E5CE 2001050300329 20010503 00329 SO 2001 5 3 20010426CW017 2 20010213 G 8530 SA52000A20P CYLINDER HEAD CONT O520 IO520* 17032 SO ENGINE CRACKED B CY4R K NONE O OTHER IN INSP/MAINT 1 AL 03 1342 CYLINDER CRACKS ADJACENT TO EXHAUST SEAT AND INTAKE SEATS BETWEEN FINS 14 AND 20. CYLINDER SERIAL NUMBERS: 352J976779, 52J976780, (52J976781), 52J976782, 52J976787, 52J976788. 3 O E5CE 2001050300330 20010503 00330 SO 2001 5 3 20010426CW018 2 20010213 G 8530 SA52000A20P CYLINDER HEAD CONT O520 IO520* 17032 SO ENGINE CRACKED B CY4R K NONE O OTHER IN INSP/MAINT 1 AL 03 1342 CYLINDER CRACKS ADJACENT TO EXHAUST SEAT AND INTAKE SEATS BETWEEN FINS 14 AND 20. CYLINDER SERIAL NUMBERS: 52J976779, 52J976780, 52J976781, (52J976782), 52J976787, 52J976788. 3 O E5CE 2001050300331 20010503 00331 SO 2001 5 3 20010426CW019 2 20010213 G 8530 SA52000A20P CYLINDER HEAD CONT O520 IO520* 17032 SO ENGINE CRACKED B CY4R K NONE O OTHER IN INSP/MAINT 1 AL 03 1342 CYLINDER CRACKS ADJACENT TO EXHAUST SEAT AND INTAKE SEATS BETWEEN FINS 14 AND 20. CYLINDER SERIAL NUMBERS: 52J976779, 52J976780, 52J976781, 52J976782, (52J976787), 52J976788. 3 O E5CE 2001050900004 20010509 00004 SO 2001 5 9 20010426CW020 2 20010213 G 8530 SA52000A20P CYLINDER HEAD CONT O520 IO520* 17032 SO ENGINE CRACKED B CY4R K NONE O OTHER IN INSP/MAINT 1 AL 03 1342 CYLINDER CRACKS ADJACENT TO EXHAUST SEAT AND INTAKE SEATS BETWEEN FINS 14 AND 20. CYLINDER SERIAL NUMBERS: 52J976779, 52J976780, 52J976781, 52J976782, 52J976787, (52J976788). 3 O E5CE 2001050300332 20010503 00332 SO 2001 5 3 20010426CW021 2 20010205 G 8530 SA52000A20P CYLINDER HEAD CONT O520 IO520* 17032 SO ENGINE CRACKED B CY2R K NONE O OTHER IN INSP/MAINT 1 AL 03 90193 1801 1801 CYLINDER HEADS CRACKED ON INTAKE SIDE ON EXTERIOR ADJACENT TO INTAKE SEAT. UNLIKE MANY OTHER CRACKED MILLINEUM CYLINDE RS THESE WERE ALSO CRACKED ON THE EXHAUST SIDE , VISIBLE FROM OUTSIDE BETWEEN FINS 18 TO 20. SERIAL NUMBERS: (52L9769 47), 52L976948, 52L976949, 52L976950, 52L976957, 52L976958. 3 O E5CE 2001050300333 20010503 00333 SO 2001 5 3 20010426CW022 2 20010205 G 8530 SA52000A20P CYLINDER HEAD CONT O520 IO520* 17032 SO ENGINE CRACKED B CY2R K NONE O OTHER IN INSP/MAINT 1 AL 03 90193 1801 1801 CYLINDER HEADS CRACKED ON INTAKE SIDE ON EXTERIOR ADJACENT TO INTAKE SEAT. UNLIKE MANY OTHER CRACKED MILLINEUM CYLINDER S THSES WERE ALSO CRACKED ON THE EXHAUST SIDE VISIBLE FROM OUTSIDE BETWEEN FINS 18 TO 20. SERIAL NUMBERS: 52L976947, (52L976948), 52L976949, 52L976950, 52L976957, 52L976958. 3 O E5CE 2001050300339 20010503 00339 SO 2001 5 3 20010426CW023 2 20010205 G 8530 SA52000A20P CYLINDER HEAD CONT O520 IO520F 17032 SO ENGINE CRACKED B CY2R K NONE O OTHER IN INSP/MAINT 1 AL 03 90193 1801 1801 240934R CYLINDER HEADS CRACKED ON INTAKE SIDE ON EXTERIOR OR ADJACENT INTAKE SEAT. UNLIKE MANY OTHER CRACKED MILLINEUM CYLINDER S THESE WERE ALSO CRACKED ON THE EXHAUST SIDE VISIBLE FROM OUTSIDE BETWEEN FINS 18 TO 20. SERIAL NUMBERS: 52L976947, 52L976948, (52L976949), 52L976950, 52L976957, 52L976958. 3 O E5CE 2001050300340 20010503 00340 SO 2001 5 3 20010426CW024 2 20010205 G 8530 SA52000A20P CYLINDER HEAD CONT O520 IO520F 17032 SO ENGINE CRACKED B CY2R K NONE O OTHER IN INSP/MAINT 1 AL 03 90193 1801 1801 240934R CYLINDER HEADS CRACKED ON INTAKE SIDE ON EXTERIOR ADJACENT TO INTAKE SEAT. UNLIKE MANY OTHER CRACKED MILLINEUM CYLINDER , THESE WERE ALSO CRACKED ON THE EXHAUST SIDE VISIBLE FROM OUTSIDE BETWEEN FINS 18 TO 20. CYLINDER SERIAL NUMBERS: 52L 976947, 52L976948, 52L976949, (52L976950), 52L976957, 52L976958. 3 O E5CE 2001050300335 20010503 00335 SO 2001 5 3 20010426CW025 2 20010205 G 8530 SA52000A20P CYLINDER HEAD CONT O520 IO520F 17032 SO ENGINE CRACKED B CY2R K NONE O OTHER IN INSP/MAINT 1 AL 03 90193 1801 1801 240934R CYLINDER HEADS CRACKED ON INTAKE SIDE ON EXTERIOR ADJACENT INTAKE SEAT. UNLIKE MANY OTHER CRACKED MILLINEUM CYLINDERS T HESE WERE ALSO CRACKED ON THE EXHAUST SIDE VISIBLE FROM OUTSIDE BETWEEN FINS 18 TO 20. 3 O E5CE 2001050300336 20010503 00336 SO 2001 5 3 20010426CW026 2 20010205 G 8530 SA52000A20P CYLINDER HEAD CONT O520 IO520F 17032 SO ENGINE CRACKED B CY2R K NONE O OTHER IN INSP/MAINT 1 AL 03 90193 1801 1801 240934R CYLINDER HEADS CRACKED ON INTAKE SIDE ON EXTERIOR ADJACENT TO INTAKE SEAT. UNLIKE MANY OTHER CRACKED MILLINEUM CYLINDER S THESE WERE ALSO CRACKED ON THE EXHAUST SIDE, VISIBLE FROM OUTSIDE BETWEEN FINS 18 TO 20. SERIAL NUMBERS: 52L976947, 52L976948, 52L976949, 52L976950, 52L976957, (52L976958). 3 O E5CE 2001050300141 20010503 00141 CE 2001 5 3 20010430CW001 1 20010327 G 2710 0400107159 CONTROL CABLE CESSNA 150 152 2071835 CE LYC O235 O235* 41505 EA AILERONS BROKEN D K NONE O OTHER IN INSP/MAINT 1 SO 15 93088 10573 15285398 DURING 100 HOUR INSPECTION, IT WAS DISCOVERED THAT THE LEFT AILERON CROSSOVER CABLE HAD A BROKEN STRAND AT A POINT 63.5 INCHES FROM THE TURNBUCKLE END. BROKEN STRAND WAS WHERE CABLE PARTED OVER A RUB BLOCK ATTACHED TO RIB AT WING STA. 56.8 75. 1 H 7 1 3O 3 O NT 3A19 E223 2001050300143 20010503 00143 CE 2001 5 3 20010430CW002 1 20010307 G 3230 LANDING GEAR BEECH 58 58 1152740 CE CONT O520 IO520C 17032 SO MAINS MALFUNCTIONED D BSYA O OTHER J WARNING INDICATION DE DESCENT 1 GL 07 21ES TH1123 AIRCRAFT COMING INTO AIRPORT, COULD NOT GET (3) GEAR DOWN AND LOCK LIGHTS. FOUND GEAR INDICATOR LIGHT SWITCH IN DIM POS ITION. PILOT COULD NOT SEE LIGHTS IN DAY FLIGHT. REPOSITIONED, CYCLED GEAR OPS CHECKS GOOD. 1 L 7 2 3O 3 O 3A16 E5CE 2001050300144 20010503 00144 CE 2001 5 3 20010430CW003 1 20010307 G 3230 08421043 BELLCRANK CESSNA 310 310R 2074245 CE NOSE GEAR BROKEN D BSYA O OTHER O OTHER NR NOT REPORTED 1 GL 07 6160X 310R1305 PILOT HEARD POPPING NOISE OUT OF GEAR, WHEN GEAR WAS RETRACTED. SELECTED GEAR DOWN AND DID A FLYBY. TOWER SAID NOSE G EAR HALF WAY DOWN, FLEW TO AIRPORT AND LANDED, NOSE GEAR COLLAPSED. LIFTED AIRCRAFT ON TO RUNWAY. NOSE GEAR SWUNG DOWN AND LOCKED, ZERO RESISTANCE, FOUND BELLCRANK BROKEN WHERE FORK BOLT GOES THROUGH. 1 L 7 2 3O 3A10 2001050300148 20010503 00148 SO 2001 5 3 20010430CW004 2 20010430 G 8550 ENGINE CESSNA 210 T210M 2073451 CE CONT O520 TSIO520* 17040 SO NACELLE LACK OF LUBE D K NONE O OTHER IN INSP/MAINT 1 GL 15 732UH 21061781 OWNER DISCOVERED A GREAT LOSS OF ENGINE OIL, FOLLOWING A COLD WEATHER FLIGHT. TEMPERATURE WAS 40 DEGREES C/F. AIR/OIL SEPARATOR INSTALLED PRIOR TO RECENT CYLINDER REPLACEMENT. 1 H 7 1 3O 3 O 3A21 E8CE 2001050300001 20010503 00001 CE 2001 5 3 20010430CW005 1 20010329 G 8011 6462751 STARTER CESSNA 310 310R 2074245 CE CONT O520 IO520* 17032 SO ENGINE FAILED D K NONE O OTHER IN INSP/MAINT 1 GL 17 90FC 396 310R1838 THIS STARTER WAS SUPPLIED WITH A ZERO TIME OVERHAULED ENGINE. THE ENGINE WAS INSTALLED JULY 20, 2000. STARTER FAILED M ARCH 23, 2001 AFTER ACCUMULATING ONLY 396.7 HOURS. DID NOT DISASSEMBLE STARTER DUE TO WARRANTY. 1 L 7 2 3O 3 O 3A10 E5CE 2001050300328 20010503 00328 CE 2001 5 3 20010430CW008 1 20010402 G 2910 244110010 PIVOT CESSNA 172 172RG 2072438 CE LYC O360 O360A1D 41514 EA RT MLG BROKEN D WIWR K NONE O OTHER IN INSP/MAINT 1 WP 07 9516B 2800 172RG0847 WHILE ON CHECK RIDE, THE RIGHT MAIN LANDING GEAR FAILED TO EXTEND. THE PILOT SUCCESSFULLY MANAGED TO LOCK THE GEAR IN P LACE BY LAYING ON THE FLOOR BEHIND THE PILOTS SEATS, USING HIS HEAD TO HOLD DOOR OPEN, REACHING OUT AND PULLED GEAR INTO POSITION. LANDED SAFELY. FOUND THE SPLINED PART OF THE PIVOT HAD COMPLETELY TWISTED OFF FROM THE REST OF THE PIVOT. NO HISTORY OF ANY BRAKE PROBLEMS, NOR REPORTS OF HARD LANDINGS WERE MADE. NO LEAKS WERE DETECTED WHILE PERFORMING THE A NNUAL INSPECTION. 1 H 7 1 3O 3 O 3A17 E286 2001050300265 20010503 00265 CE 2001 5 3 20010430CW012 1 20010402 G 7603 HOUSING CESSNA 172 172M 2072418 CE LYC O320 O320D2G 41508 EA THROTTLE CABLE CRACKED D K NONE O OTHER IN INSP/MAINT 1 NM 01 70323 3857 17267200 L937739A THROTTLE CABLE OUTER HOUSING DETERIORATED AND SEPARATED FROM SWEDGED FITTING AT CLAMP LOCATION AFT OF ENGINE. THIS ALLO WED THE OUTER HOUSING TO MOVE INSTEAD OF THE CARBURETOR CONTROL ARM AS THE THROTTLE CONTROL WAS MOVED. RECOMMEND CABLE REPLACEMENT WHEN ANY INDICATION OF CRACKING IN THE OUTER HOUSING BECOMES VISIBLE. 1 H 7 1 3O 3 O NT 3A12 E274 2001050100363 20010501 00363 CE 2001 5 1 20010501AP004 1 20010424 G 7830 23220258511 LEVER ARONCA RKWELL NA265 NA26580 7630108 CE THRUST REVERSER MISMANUFACTURED B JV2R K NONE O OTHER IN INSP/MAINT 1 SW 99 316EC 369 369 144 38038 ON 8/9/99 1EA. P/N232-20258-511 WAS INSTALLED ON L/H T/R. 2EA. P/N 232-20258-513 AND 2EA. 232-20258-514 LEVERS WERE INST ALLED ON R/H T/R DURING REPAIR OF THESE T/RS. IN JAN. 2001 THE CUSTOMER REPORTED PROBLEMS WITH THE LT T/R. INSPECTION O F BOTH T/RS REVEALED BROKEN DRIVE CABLES AND BENT LEVERS. IT WAS BELIEVED AT THIS TIME THAT THE LEVERS WERE NOT PER DRA WING AND REMAINING STOCK WAS RETURNED TO LEAR. LEAR RETURNED THE LEVERS AS BEING MANUFACTURED PER DRAWING. FURTHER INS PECTION AND DISCUSSION WITH LEAR ON 4/23/01 REVEALED THE PREVIOUSLY MENTIONED LEVERS INSTALLED NEW 8-20-99 WERE NOT MANU FACTURED IAW LEAR DRAWINGS. 2 L 7 2 4F A2WE 2001050300046 20010503 00046 CE 2001 5 3 20010501CW001 1 20010207 G 2140 FUEL CAP CESSNA 421 421C 2076016 CE CONT O520 GTSIO520F 17032 SO HEATER CRACKED D K NONE O OTHER IN INSP/MAINT 1 WP 09 12RJ 5280 421C0306 FUEL LEAK AT HEATER FUEL FILTER ASSEMBLY IN RIGHT WING. CAP ON TOP OF ASSEMBLY WAS FOUND TO HAVE CRACK IN THREADS. CAP IS MADE OF ALUMINUM. PART IS PRESUMED TO BE ORIGINAL EQUIPMENT. NO KNOW DISASSEMBLY IN SERVICE HISTORY. CAP WAS LOOS E IN SPITE OF LOCK TAB STILL BEING INTACT. 1 L 7 2 3O 3 O A7CE E7CE 2001050300112 20010503 00112 NE 2001 5 3 20010501CW006 2 20010313 G 8530 212359 CYLINDER SCWZER G164 G164A 3952704 EA PWA R1340 R1340AN1 52016 NE NR 2 ENGINE CRACKED G ZMIG K NONE O OTHER IN INSP/MAINT 1 SO 07 5076 1111 11091 NO RECORDS ON CYLINDERS. AIRCRAFT LOST POWER AFTER TAKE OFF AND LANDED LONG, RAN INTO WOODS (DESTROYED AIRCRAFT) PILO T UNHURT. INVESTIGATION REVEALED NR 2 ENGINE CYLINDER VAS CRACKED FROM THE INTAKE VALVE HOLE TO SPARK PLUG HOLE, ALMOS T COMPLETELY AROUND THE CYLINDER. 1 Q 7 1 3R 3 R 1A16 5E2 2001050300116 20010503 00116 SO 2001 5 3 20010501CW007 1 20010406 G 5210 LATCH PIPER PA23 PA23160 7102304 SO LYC O320 O320* 41508 EA PAX DOOR INOPERATIVE G K NONE O OTHER IN INSP/MAINT 1 WP 21 333PE 232007 DOOR CAME OPEN IN FLIGHT CAUSING AIRCRAFT TO LOOSE DIRECTIONAL CONTROL. GROUND INVESTIGATION REVEALED THAT LATCH MECHAN ISM WAS NOT LOCKING PROPERLY AT THE JAMS. 1 L 7 2 3O 3 O 1A10 E274 2001050300201 20010503 00201 CE 2001 5 3 20010501CW014 1 20010413 G 3000 SWITCH ASC BEECH 35 B35 1151506 CE LT BRAKE INOPERATIVE B LX5R O OTHER P NO WARNING INDICATION NR NOT REPORTED 1 GL 19 171CP 0854A FL244 LEFT BRAKE DEICE VALVE, SHOWING ITT RISE, LIGHT NOT ILLUMINATING. LIGHT SYSTEM CHECKS GOOD. BAD SWITCH ON VALVE. 1 L 7 1 3O A777 2001050300202 20010503 00202 CE 2001 5 3 20010501CW015 1 20010412 G 3000 SWITCH ASC BEECH B300 B300 1159232 CE LT BRAKE INOPERATIVE B LX5R O OTHER P NO WARNING INDICATION NR NOT REPORTED 1 GL 19 971LL 0831A FL267 LEFT BRAKE DEICE VALVE INDICATING LIGHT CIRCUIT OPEN IN VALVE. 2 L 7 2 4T RT A24CE 2001050300203 20010503 00203 CE 2001 5 3 20010501CW016 1 20010406 G 7160 075014433 AIR BOX CESSNA 182 182P 2075816 CE CONT O470 O470S 17026 SO ENGINE FAILED D K NONE O OTHER IN INSP/MAINT 1 NE 05 1408M 113 18264319 226296R DURING ANNUAL INSPECTION, IT WAS NOTED THAT THE RIVETS THAT SECURE THE CARB HEAT VALVE PLATE TO THE CONTROL CROSS SHAFT WER COMING LOOSE. THIS APPEARS TO HAVE BEEN CAUSE BY SEALING MATERIAL ON THE VALVE PLATE WHICH WAS NOT CORRECTLY TRIMME D. AS A RESULT, THE MATERIAL WOULD BIND IN A CARB HEAT NEEDED POSITION, MAKING IT DIFFICULT TO RETURN THE VALVE TO A NO CARB HEAT POSITION. 1 H 7 1 3O 3 O NT TA13 E273 2001050300204 20010503 00204 CE 2001 5 3 20010501CW017 1 20010501 G 2720 12604567 RUDDER BAR CESSNA 206 U206G 2073356 CE CONT O520 IO520* 17032 SO RUDDER PEDALS DAMAGED B CL4R O OTHER F FLT CONT AFFECTED NR NOT REPORTED 1 AL 03 9497R 3102 U20606876 PILOT SIDE LEFT RUDDER PEDAL COLLAPSED IN FLIGHT. SAFECOM FILED. APPEARS THAT TORQUE TUBE MAY HAVE BEEN DAMAGED BY MAI NTENANCE WHEN BUSHING WAS INSTALLED. 1 H 7 1 3O 3 O A4CE E5CE 2001050300206 20010503 00206 SO 2001 5 3 20010501CW019 2 20010303 G 8530 SA52000A1 CYLINDER CONT O520 IO520F 17032 SO NR 3 DESTROYED B O3OR K NONE O OTHER IN INSP/MAINT 1 AL 03 96 96 563729 NR 3 CYLINDER AND PISTON ASSEMBLY. REMOVED DUE TO LOW COMPRESSION AND COMPLAINT FROM PILOT OF RUNNING ROUGH. PISTON AP PEARS TO HAVE SEVERE PREIGNITION OR DETONATION. 3 O E5CE 2001050300207 20010503 00207 CE 2001 5 3 20010501CW020 1 20010412 G 2421 635796 COUPLING ELECTROSYS CESSNA 172 R172E 2072413 CE CONT IO360 IO360* 17025 CE ALTERNATOR DRIVE SLIPPED D K NONE O OTHER IN INSP/MAINT 1 SO 15 7907N B022733 R1720298 239770R AT ENGINE CHANGE, FRESH OVERHAUL ALT INSTALLED AFTER 9.0 HOURS OF OPERATION NOTED ERATIC ALTERNATOR OUTPUT. INSPECTED ALTERNATOR AND DETERMINED ALTERNATOR DRIVE COUPLING SLIPPING. REPLACED ALTERNATOR DRIVE COUPLING WITH OVERHAULED LIKE I TEM AND REINSTALLED ALTERNATOR ON AIRCRAFT. 1 H 7 1 3O 3 O 3A17 E1CE 2001050300209 20010503 00209 CE 2001 5 3 20010501CW022 1 20010412 G 3710 632617D BEVEL GEAR CONT CESSNA 337 337G 2075730 CE CONT O360 IO360GB 17025 SO VACUUM PUMP SHEARED D K NONE O OTHER IN INSP/MAINT 1 SO 15 726AS 725 7509 33701661 813014R A DETAILED INVESTIGATION OF THE STARTER DEIVE REVEALED THAT ALL TO THE GEAR TEETH WERE WORN EXCESSIVELY ON ONE OF THE BE VEL GEARS WHICH DRIVES THE VACUUM PUMP. THIS IS THE FIFTH FAILURE OF THIS GEAR THAT WE HAVE DETECTED. 1 H 7 2 3O 3 O A6CE E1CE 2001050300210 20010503 00210 SW 2001 5 3 20010501CW023 1 20010128 G 3213 530021000 DISK MOONEY M20 M20D 5870210 SW LYC O360 O360* 41514 EA MLG STRUT WORN D K NONE O OTHER IN INSP/MAINT 1 NE 03 1923Y 218 MAIN LANDING GEAR SHOCK DISCS WERE FOUND TO BE COMPRESSED BEYOND LIMITS. WHEN CHECKED PER THE MANUAL INSTEAD OF .1250 M AX CLEARANCE THER WAS .3750 INCH OF CLEARANCE. ALSO FOUND AN INCORRECT FITTING INSTALLED ON LEFT BRAKE THAT ALLOWED THE BRAKE HOSE TO INTERFEAR WITH THE INNER GEAR DOOR. 1 L 7 1 3O 3 O 2A3 E286 2001050300236 20010503 00236 SO 2001 5 3 20010502CW001 1 20010305 G 5280 4752932 HINGE PIPER PA31 PA31350 7103110 SO LYC O540 TIO540* 41532 EA MLG INNER DOOR CRACKED D K NONE O OTHER IN INSP/MAINT 1 AL 05 555FS 5393 317952046 INSPECTED HINGES, ONLY FORWARD HINGES ON BOTH DOORS HAD CRACKS ON INNER RADIUS APPROX .1250 TO .1875 INCH DEEP. REAR H INGES WERE NOT CRACKED, REPLACED ALL FOUR HINGES. SUSPECT CRACKS ARE CAUSED DUE TO LOCATION OF HYD ACTUATOR FORWARD OF FORWARD HINGE, CAUSING MORE STRESS ON FORWARD HINGE THAN ON REAR HINGE. 1 L 7 2 3O 3 O A20SO E14EA 2001050300247 20010503 00247 SW 2001 5 3 20010502CW005 1 20010402 G 6210 204011250113 BLADE BELL 204 UH1H 1181407 SW LYC T53 T53* 41549 NE MAIN ROTOR CRACKED D K NONE O OTHER IN INSP/MAINT 1 NM 01 340WN 2500 1648 6510081 LE17065BA A CRACK WAS NOTICED INSIDE DENT AFT OF THE SPAR ON THE TOP OF THE MAIN ROTOR BLADE. REMOVAL OF PAINT DETERMINED THE CRA CK TO BE IN EXCESS OF 6 INCHES LONG. THE ROTOR BLADE WAS DETERMINED TO BE UNSERVICEABLE AND REMOVED FROM SERVICE. 1 G 7 1 4U 4 U EXPA1G71 E1EA 2001050300023 20010503 00023 EU 2001 5 3 20010502CW009 1 20010106 G 6220 117775P BALL JOINT SNIAS 350 AS350B3 8680954 EU STARFLEX WORN B R7MA K NONE O OTHER IN INSP/MAINT 1 NM 07 52285 505 3251 WORN BEYOND SERVICEABLE LIMITS. REMOVED AND REPLACED WITH NEW UNIT, CORRECTED PROBLEM. 1 G 7 1 3U H9EU 2001050300389 20010503 00389 NE 2001 5 3 20010502CW010 1 20010320 G 7810 EXHAUST PIPE SKRSKY S76 S76A 8143006 NE RIGHT MISALIGNED B HEEA K NONE O OTHER IN INSP/MAINT 1 WP 09 5444X 760174 THE EXHAUST ASSEMBLY WAS SENT TO A REPAIR STATION FOR OVERHAUL. UPON REINSTALLATION IT WAS FOUND THAT THE RIGHT HAND EX HAUST PIPE CONTACTED THE NR 5 CYLINDER INTAKE PIPE. 1 G 7 2 3U H1NE 2001050300211 20010503 00211 CE 2001 5 3 20010503CW004 1 20010404 G 5310 05110006 DOOR FRAME CESSNA 172 172E 2072412 CE CONT O300 O300D 17022 SO FUSELAGE MISINSTALLED H K NONE W INADEQUATE Q C IN INSP/MAINT 1 NM 08 3658S 3222 17250858 24144DOD FUEL LINES RUBBING AND STRESSED DUE TO UPPER OUTBOARD DOOR FRAME PARTIALLY COVERING HOLE AND NOT ALLOWING CLEARANCE FOR FUEL LINE. CAUSE BY HOLE IN UPPER OB DOOR FRAMES NOT BEING CUT OUT TO ORIGINAL SIZE FOR CLEARANCE BY MFG. RECOMMENDATI ON IS TO ROUND OUT HOLE TO ORIGINAL OPENING TO ACCOMMODATE FUEL LINE. 1 H 7 1 3O 3 O NT 3A12 E253 2001050300213 20010503 00213 CE 2001 5 3 20010503CW005 1 20010404 G 5310 05110007 DOOR FRAME CESSNA 172 172E 2072412 CE CONT O300 O300D 17022 SO FUSELAGE MISINSTALLED H K NONE W INADEQUATE Q C IN INSP/MAINT 1 NM 08 3658S 3222 17250858 24144DOD FUEL LINES RUBBING AND STRESSED DUE TO UPPER OUTBOARD DOOR FRAME PARTIALLY COVERING HOLE AND NOT ALLOWING CLEARANCE FOR FUEL LINE. CAUSED BY THE HOLE IN DOOR FRAMES NOT BEING CUT OUT TO ORIGINAL SIZE FOR CLEARANCE BY MFG. RECOMMENDATION I S TO ROUND OUT HOLES TO ORIGINAL OPENING TO ACCOMMODATE FUEL LINE. 1 H 7 1 3O 3 O NT 3A12 E253 2001051500061 20010515 00061 EA 2001 5 15 20010503CW013 2 20010503 G 7414 4381 MAGNETO CESSNA 172 172M 2072418 CE LYC O320 O320* 41508 EA LEFT INOPERATIVE D K NONE O OTHER IN INSP/MAINT 1 GL 09 20421 17261276 PLASTIC SUPPORT FOR POINTS BROKEN, AND POINTS FAILED, FACTORY SEAL STILL ON MAGNETO. PILOT REPORTED ENGINE RUNNING ROU GH. MADE SAFE LANDING, CHECKED GOOD WITH REPLACEMENT MAGNETO. 1 H 7 1 3O 3 O NT 3A12 E274 2001051500080 20010515 00080 NE 2001 5 15 20010504CW002 2 20010227 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 REJECTED AT PENETRANT INSPECTION FOR INDICATIONS AS MARKED ON BOTTOM OF PART (SIDE OF BOSS). 4 F E311NE 2001051500082 20010515 00082 NE 2001 5 15 20010504CW003 2 20010329 G 7200 2A0851 SEAL IAE V2500 V2500A1 NE NR 4 BEARING CRACKED B KB1R K NONE O OTHER IN INSP/MAINT 1 NE 03 PART REJECTED AT PENETRANT INSPECTION FOR INDICATIONS AS MARKED ON AREA ADJACENT TO BOSS. 4 F E311NE 2001051500088 20010515 00088 NE 2001 5 15 20010504CW006 2 20010216 G 7230 787008 COMPRESSOR WHEEL PWA JT8 JT8D9A 52048 NE 8TH STAGE CRACKED W K NONE O OTHER IN INSP/MAINT 1 SW 99 26811 666322 AFTER ENGINE DISASSEMBLE, DURING INSPECTION ON EIGHTH STAGE DISK, A CRACK WAS DETECTED IN ONE OF THE TIE ROD HOLES. CRA CK EXTENDED RADIALLY OUTBOARD FROM THE HOLE TO DEPTH OF 0.35 IN., DUE TO OXIDATION AND HEAVY CORROSION. IN ORDER TO H AVE MORE INFORMATION, PART WAS SENT TO OEM FOR EVALUATION. PART WILL BE LOCALLY SCRAPPED. 4 F E2EA 2001051500091 20010515 00091 EA 2001 5 15 20010504CW008 2 20010330 G 7200 LW14820 SNAP RING PIPER PA31 PA31350 7103110 SO LYC O540 LTIO540J2BD 41533 EA COUNTERWEIGHT DEFECTIVE D K NONE O OTHER IN INSP/MAINT 1 NM 07 78GH 317852121 L247368A THIS ENGINE WAS RECEIVED ON 2/21/01 DUE TO A HOLE IN TOP OF ENGINE. DURING DISASSEMBLY IT WAS NOTED THAT THE CRANKSHAFT WAS BROKEN AT THE NR 1 ROD JOURNAL. THE SNAP RING AND PIN WERE MISSING FROM ONE OF THE COUNTERWEIGHTS. THE PIN UPON C OMING OUT WAS PINCHED BETWEEN THE NR 2 CONNECTING ROD AND CONNECTING ROD HAD THE CAP PULLED OFF FROM DEBREE FLYING AROUN D IN THE ENGINE. THE SNAP RING DID NOT HAVE ENOUGH TENTION TO KEEP IT EXPANDED IN PLACE ALLOWING IT TO COME OUT AND CAU SE CATASTROPHIC ENGINE FAILURE. 1 L 7 2 3O 3 O A20SO E14EA 2001051500092 20010515 00092 SW 2001 5 15 20010504CW009 1 20010320 G 3260 880013507 SWITCH MOONEY M20 M20J 5870219 SW LYC O360 IO360A3D6D 41514 EA AIRSPEED SEPARATED D K NONE O OTHER IN INSP/MAINT 1 NM 01 923DH 819 819 243368 L2671551A A/S SWITCH FAILED F/T 32-30-01, SWITCH WAS REMOVED AND SENT TO OEM VENDOR. SWITCH WAS PARTED FROM MOUNT. SWITCH WAS EXP OXED TO MOUNT AND RECALIBRATED. THE SWITCH WAS REINSTALLED AND PASSED. 1 L 7 1 3O 3 O 2A3 1E10 2001051500118 20010515 00118 SO 2001 5 15 20010507CW001 2 20010405 G 8550 C1650010102 SEPARATOR CESSNA 182 182H 2072718 CE CONT O470 O470* 17026 SO AIR/OIL CONTAMINATED B ZM3R K NONE O OTHER IN INSP/MAINT 1 WP 07 3495S 5686 18255895 OIL FILTER INSPECTION REVEALED EXCESSIVE AMOUNT OF CONTAMINATION. INVESTIGATION REVEALED AIR/OIL SEPERATOR INTERNAL SCR EEN COMING APART. YEARS OF VIBRATION MAY HAVE CAUSED SCREEN SEPARATION. FACTORY RECOMMENDS 100 HOURS CLEANING. THERE IS NO WAY TO INSPECT UNIT WITHOUT CUTTING IT OPEN. 1 H 7 1 3O 3 O NT 3A13 E273 2001051500119 20010515 00119 CE 2001 5 15 20010507CW003 1 20010418 G 2421 99105921 ALTERNATOR CESSNA 210 P210N 2073454 CE CONT O520 TSIO520* 17040 SO ENGINE MALFUNCTIONED C K NONE O OTHER IN INSP/MAINT 1 NM 10 456BR 15 P21000717 AIRCRAFT UNDER IMC WHEN LOW VOLT LIGHT CAME ON AND VOLTAGE DROP TO 23.0 VOLTS. PILOT SHUT EVERYTHING OFF AND DECLARED A N EMERGENCY WITH CASCADE APPROACH. LANDED WITHOUT INCIDENT. PART WAS UNDER WARRANTY SO COULD NOT DISASSEMBLE TO FIND O UT CAUSE OF FAILURE, PART IS PROPRIETARY FOR MFG. 1 H 7 1 3O 3 O 3A21 E8CE 2001051500120 20010515 00120 SO 2001 5 15 20010507CW004 2 20010413 G 7322 6397172 FUEL CONTROL CESSNA 185 A185F 2072821 CE CONT O550 IO550D 17042 SO CONTROL ARM DEFECTIVE B T9ZR K NONE O OTHER IN INSP/MAINT 1 NM 09 280 AIRCRAFT WAS INSPECTED FOR FUEL SYSTEM PROBLEMS. IT WAS DISCOVERED THAT THE CONTROL ARM ON THE THROTTLE BODY WAS SHIPPI NG ON THROUGH SHAFT. THIS CONDITION DID CAUSE THE AIRCRAFT TO ENCOUNTER A STOCK THROTTLE CONDITION, IN THE FULL THROTTL E POSITION. 1 H 7 1 3O 3 O 3A24 E3SO 2001051500128 20010515 00128 CE 2001 5 15 20010507CW010 1 20010423 G 5521 SPAR CESSNA 188 A188B 2073005 CE CONT O520 IO520* 17032 SO RT ELEVATOR CRACKED B K NONE O OTHER IN INSP/MAINT 1 NM 09 731CS 18802796T FOUND RIGHT ELEVATOR SPAR CRACKED AT OUTBOARD ATTACH POINT. HORIZONTAL STABILIZER HAD PREVIOUS REPAIRS WERE LOCATED DIR ECTLY FORWARD OF CRACK IN ELEVATOR SPAR. 1 L 7 1 3O 3 O A9CE E5CE 2001051500144 20010515 00144 CE 2001 5 15 20010507CW020 1 20010329 G 5753 05239016 SKIN CESSNA 172 172S 2072439 CE LYC O360 IO360A1A 41514 EA LEFT TE FLAP CRACKED D K NONE O OTHER IN INSP/MAINT 1 NM 07 476SP 1168 M2S8022 DURING A PHASE 2 INSPECTION PERFORMED, SEVERAL CRACKS WERE NOTICED ON THE TRAILING EDGE RIVETS ON THE LOWER LEFT FLAP SK IN, AT APPROX 2-3 FEET FROM THE INBOARD EDGE. 6 RIVETS HAD CRACKS STARTING TO FORM FROM THEM. THE CRACKS ARE ABOUT .12 50 TO .2500 OF AN INCH LONG. 1 H 7 1 3O 3 O NT 3A12 1E10 2001051600408 20010516 00408 CE 2001 5 16 20010508CW002 1 20010508 G 2750 26111447 BRACKET CESSNA 208 208B 2073701 CE FLAP BROKEN D K NONE O OTHER IN INSP/MAINT 1 SW 01 64BP 3789 0604 PRIMARY FLAP MOTOR DRIVE COUPLER FAILED. STAND BY SYSTEM USED TO EXTEND FLAPS. FLAP LIMIT SWITCHES NOT INCORPORATED IN STAND BY SYSTEM. OPERATIONAL SWITCH OF STAD BY SYSTEM HELD TOO LONG AND FLAP MOTOR CONTINUED TO RUN PAST LIMIT SWITCH LOCATION AND TWISTED FLAP DRIVE ASSEMBLY OUT OF MOUNTING BRACKET. RECOMMENDATION, PILOT BE MORE AWARE OF SYSTEM OPERATI ON OR INCORPORATE SWITCHES INTO STAND-BY SYSTEM. 1 H 7 1 3T A37CE 2001051600409 20010516 00409 EU 2001 5 16 20010508CW003 1 20010412 G 2121 M3348A MOTOR DYNAIR SAAB SF340 SF340A 7850100 EU FAN INOPERATIVE B O OTHER O OTHER NR NOT REPORTED 1 WP 05 162 ARMATURE ASSEMBLY SHOWS SIGNS OF AN INTERFERENCE FIT. RECOMMEND OVERHAUL ONLY TO APPROVED OVERHAUL MANUAL USING ONLY AP PROVED PARTS. 2 L 7 2 4T RT A52EU 2001051600547 20010516 00547 EU 2001 5 16 20010508CW004 1 20010412 G 2121 M3348A MOTOR DYNAIR SAAB SF340 SF340A 7850100 EU FAN WRONG PART B K NONE O OTHER IN INSP/MAINT 1 WP 05 170 FAN RETURNED TO MFG FOR UPGRADE TO C209-6901 CONFIGURATION, THE FAN WAS TESTED AND FOUND TO EXHIBIT EXCESSIVE VIBRATION. WHEN THE FAN WAS DISASSEMBLED, IT WAS DISCOVERED THAT THIS OVERHAULED UNIT HAS NOT BEEN OVERHAULED PER MFG OVERHAUL MA NUAL. THE ARMATURE AND STATOR FIELD WINDINGS ARE NOT OF MFG DESIGN. MFG OVERHAUL MANUAL DOES NOT ALLOW FOR REWINDING O F THE ARMATURE OR FIELD WINDINGS. THE ARMATURE ASSY HAS NUMBERS STAMPED INTO IT, WHICH CAUSES AN OUT OF ROUND CONDITION . ARMATURE HAS A COMMUTATOR THAT IS NOT MFG PART INSTALLED ON IT. THE IMPELLER IS AT THE WRONG LOCATION, CAUSING IT TO RUB AGAINST THE FRONT END BELL. THE FIELD WINDINGS HAVE A THERMAL SWITCH ADDED THAT IS NOT PER OVERHAUL MANUAL. 2 L 7 2 4T RT A52EU 2001051600548 20010516 00548 EU 2001 5 16 20010508CW005 1 20010412 G 2121 MOTOR DYNAIR SAAB SF340 SF340A 7850100 EU FAN UNAPPROVED PART B K NONE O OTHER IN INSP/MAINT 1 WP 05 174 MOTOR ASSEMBLY IS NOT A DYNAMIC AIR ENGINEERING PART. MOTOR ASSEMBLY DOES NOT MEET DAE DRAWING AND OVERHAUL MANUAL REQ UIREMENTS. 2 L 7 2 4T RT A52EU 2001051600552 20010516 00552 EU 2001 5 16 20010508CW006 1 20010412 G 2121 M3348A MOTOR DYNAIR SAAB SF340 SF340A 7850100 EU FAN UNAPPROVED PART B K NONE O OTHER IN INSP/MAINT 1 WP 05 225 FAN RETURNED TO DAE FOR UPGRADE TO C209-690D CONFIGURATION. THE FAN WAS TESTED AND FOUND TO EXHIBIT EXCESSIVE VIBRATION . WHEN THE FAN WAS DISASSEMBLED, IT WAS DISCOVERED THAT THIS OVERHAULED UNIT HAS NOT BEEN OVERHAULED PER THE DAE OVERHA UL MANUAL. THE ARMATURE AND STATOR FIELD WINDING ARE NOT OF DAE DESIGN. DAE OVERHAUL MANUAL DOES NOT ALLOW FOR THE REW INDING OF THE ARMATURE OR FIELD WINDINGS. THE ARMATURE ASSY HAS AN OVERSIZE COMMUTATOR INSTALLED WHICH MAKES THE BRUS HES EXTEND PAST THE DESIGNED LIMIT, THE IMPELLER IS AT THE WRONG LOCATION, AND ARMATURE IS NOT BALANCED. THE FIELD WIND INGS ARE REWOUND AND HAVE UNACCEPTABLE AIR GAP. 2 L 7 2 4T RT A52EU 2001051600553 20010516 00553 SO 2001 5 16 20010508CW008 2 20010402 G 7414 M1176 FRAME SLICK CESSNA 206 TU206G 2073357 CE CONT O520 TSIO520M 17040 SO MOUNTING FLANGE CRACKED B QY5R K NONE K FLUID LOSS IN INSP/MAINT 1 NE 01 232MT 1010441 U20606200 520356 OBSERVED AN OIL LEAK FROM MAG BASE. FOUND MOUNTING FLANGE CRACKED AROUND LOWER CLAMPING WASHER. REMOVED MAG AND FOUND APPROX 2 INCH PIECE OF MOUNTING FLANGE BROKEN OFF. 1 H 7 1 3O 3 O A4CE E8CE 2001051600421 20010516 00421 SO 2001 5 16 20010508CW009 2 20010402 G 7414 M3975 COIL SLICK CESSNA 206 TU206G 2073357 CE CONT O520 TSIO520* 17040 SO MAGNETO INOPERATIVE B QY5R K NONE O OTHER IN INSP/MAINT 1 NE 01 232MT 89070161 U20606200 MAGNETO INOPERATIVE BELOW 1,000 RPMS. OK AT 1,700 RPMS PER THE P.O.M. PILOTS HAD DONE A MAG CHECK AT IDLE WHICH LEAD TO THE DISCOVERY. OPENED MAGNETO FOR INSPECTION. TESTED COIL AND FOUND SECONDARY WINDING. RESISTANCE TOO HIGH BY FACT OR OF 10. 1 H 7 1 3O 3 O A4CE E8CE 2001051500171 20010515 00171 SW 2001 5 15 20010508CW013 1 20010416 G 6730 41001554 HOUSING BELL 214 214B 1182100 SW SERVO ACTUATOR GOUGED B QH5R K NONE O OTHER IN INSP/MAINT 1 NM 07 GOUGE PLUS LINER IND. BELOW GOUGE. 2 G 7 1 4U H6SW 2001052300019 20010523 00019 CE 2001 5 23 20010508CW016 1 20010413 G 3233 98820041 PISTON CESSNA 172 172RG 2072438 CE MLG ACTUATOR BROKEN D K NONE O OTHER NR NOT REPORTED 1 SO 13 9985B 10388 172RG1107 PISTON IN MAIN GEAR ACTUATOR BROKEN AT SECOND TOOTH FROM END. THIS LEFT GEAR TO SWING FREELY, NOT LOCKING DOWN. 1 H 7 1 3O 3A17 2001052300023 20010523 00023 SO 2001 5 23 20010508CW019 2 20010413 G 7322 6397172 THROTTLE BODY CESSNA 188 188B 2073007 CE CONT O520 IO520* 17032 SO ENGINE OUT OF ADJ B T9ZR K NONE O OTHER IN INSP/MAINT 1 SW 99 731CS 280 280 18802796T THROTTLE BODY AND METERING UNIT WAS FOUND TO BE OUT OF ADJUSTMENT, DURING INSPECTION THE CONTROL ARM AT THROTTLE BODY WA S FOUND LOOSE AND ROTATING ON SHAFT. NO ADJUSTMENT OF IDLE MIXTURE OR IDLE COULD BE PERFORMED DUE TO CHANGING CONDITION BETWEEN THROTTLE BODY AND METERING UNIT. 1 L 7 1 3O 3 O A9CE E5CE 2001052400131 20010524 00131 SO 2001 5 24 20010509CW002 1 20010326 G 2740 6270147 CONTROL CABLE PIPER PA28 PA28R201 7102816 SO STABILIZER OUT OF RIG B H1ES O OTHER F FLT CONT AFFECTED DE DESCENT 1 NE 01 2145M 460 290 28R7837069 TRIM CABLE JACKSCREW STOP PIN NOT CONTACTING TRIM DRUM BEFORE TURNBUCKLE FERRULE REACHING AFT PULLEY AND CABLE GUARD, PR EVENTING CABLE FROM MOVING. AC WAS IN FULL NOSE TRIM CONDITION, AC LANDED WITHOUT INCIDENT. TRIM CABLES WERE RE-RIGGED . 1 L 7 1 3O 2A13 2001052400004 20010524 00004 SW 2001 5 24 20010509CW009 1 20010413 G 5711 SPAR BBAVIA 7 7EC 2110120 SW CONT C90 C9012F 17009 SO RT WING CRACKED D K NONE O OTHER IN INSP/MAINT 1 GL 03 62667 7FC326 46889912 IN RECOVERING AIRFRAME, FOUND CRACK IN RIGHT WING REAR SPAR. AIRCRAFT WRECKED IN A NOSE OVER. NO LOG RECORD OF REPAIR TO REAR SPAR. 1 H 7 1 3O 3 O A759 E252 2001051000001 20010510 00001 CE 2001 5 10 20010510AP001 1 20010424 G 7830 23220258511 LEVER ARONCA RKWELL NA265 NA26580 7630108 CE THRUST REVERSER MISMANUFACTURED B JV2R K NONE W INADEQUATE Q C IN INSP/MAINT 1 SW 99 316EC 369 369 144 38038 ON 8/9/99 1EA. P/N232-20258-511 WAS INSTALLED ON LT T/R. 2EA. P/N 232-20258-513 AND 2EA. 232-20258-514 LEVERS WERE INSTA LLED ON RT T/R DURING REPAIR OF THESE T/R''''S. IN JAN. 2001 THE CUSTOMER REPORTED PROBLEMS WITH THE LT T/R. INSPECTION OF BOTH T/RS REVEALED BROKEN DRIVE CABLES AND BENT LEVERS. IT WAS BELIEVED AT THIS TIME THAT THE LEVERS WERE NOT PER D RAWING AND REMAINING STOCK WAS RETURNED. 2 L 7 2 4F A2WE 2001051000002 20010510 00002 CE 2001 5 10 20010510AP002 1 20010309 G 3240 ACM22740 VALVE RAYTHN DH125 HAWKER800 7450004 CE GARRTT TFE731 TFE7315BR WP MLG CONTAMINATED C D RETURN TO BLOCK O OTHER TX TAXI/GRND HDL 1 SO 11 1650 526 NR 1 TIRE FLAT SPOTTED, NR 2 TIRE FLAT SPOTTED AND DEFLATED, NR 3 TIRE FLAT SPOTTED. VISUAL INSPECTION FOUND NR 1 MODULA TOR VALVE CONTAMINATED WITH PAINT CHIPS AND SHAVINGS OF PLASTIC. FOUND NR 2 MODULATOR VALVE PISTON O-RING DECOMPOSED/CO NTAMINATED. REPLACED NR 1 AND 2 MODULATOR VALVE, BRAKE CONTROL VALVE, FLUSHED ENTIRE BRAKE SYSTEM HYDRAULIC LINES AND FU NCTIONALLY TESTED BRAKE CONTROL SYSTEM. 2 L 7 2 4F 4 F RT A3EU E6WE 2001051000003 20010510 00003 NM 2001 5 10 20010510AP003 1 20010425 G 3240 LINE AMD FALC50 FALCON2000 2730170 NM BRAKE SYSTEM LEAKING D K NONE K FLUID LOSS IN INSP/MAINT 1 SO 11 120HG 15 200055 RIGHT MLG BRAKE LINE WAS FOUND LEAKING FROM THE B NUT THAT CONNECTS THE LINE TO THE BRAKE CALIPER FITTING. THE BRAKE LIN E IS MADE OF CLEAR PLASTIC TUBING AND THE B NUT IS BRASS AND UTILIZES A BRASS COMPRESSION FITTING TO FORM THE SEAL AT TH E CALIPER FITTING. SUSPECT THE LEAK IS DUE TO THERMAL EXPANSION OF PLASTIC AND BRASS CAUSED BY ELEVATED BRAKE TEMPERATUR ES DURING SHORT FIELD BRAKING. SUGGEST THAT PLASTIC TUBING AND BRASS FITTINGS BE REMOVED AND REPLACED WITH AN STANDARD F ITTINGS AND MEDIUM PRESSURE HOSE THAT MEETS THE APPROPRIATE MIL SPEC. 2 K 7 3 4F RT A50NM 2001051000004 20010510 00004 NM 2001 5 10 20010510AP004 1 20010425 G 5210 DOOR AMD FALC50 FALCON2000 2730170 NM PAX LEAKING D K NONE O OTHER IN INSP/MAINT 1 SO 11 120HG 15 200055 FOUND INSTRUMENTS AND RADIO DISPLAYS FOGGED OVER DUE TO CABIN WATER-LEAKS. LEAKS FOUND AROUND CABIN DOOR. SUSPECT LEAKAG E DUE IMPROPER DOOR ALIGNMENT AND/OR SEALING DURING MAUFACTURING. THIS CONDITION IF NOT CORRECTED WILL CAUSE PREMATURE C ORROSION OF THE AIRCRAFT AND ELECTRICAL MALFUNCTION OF THE AVIONICS AND INSTRUMENTATION AS WELL AS DETERIORATION OF THE CABIN INTERIOR. SUBMITTER HAS OBSERVED THIS DISCREPANCY ON OTHER LIKE MODELS OF THIS AIRCRAFT. 2 K 7 3 4F RT A50NM 2001051000005 20010510 00005 CE 2001 5 10 20010510AP005 1 20010104 G 3242 AC65218 MAXARET RAYTHN DH125 HAWKER800 7450004 CE GARRTT TFE731 TFE7315BR WP WHEEL AXLE INOPERATIVE C K NONE O OTHER IN INSP/MAINT 1 SO 11 1640 788 258376 NR 1 AND 2 TIRES FOUND FLAT SPOTTED DURING POST-FLIGHT INSPECTION. NR 1 MAXARET UNIT DID NOT PASS ANTI-SKID FUNCTIONAL T EST. REPLACED NR 1 MAXARET UNIT WITH OVERHAULD UNIT. 2 L 7 2 4F 4 F RT A3EU E6WE 2001051000006 20010510 00006 CE 2001 5 10 20010510AP006 1 20010426 G 7810 1099500001 EXHAUST PIPE PWC BEECH 90 C90A 1152911 CE PWA PT6 PT6A21 52043 EA LT ENGINE BROKEN D K NONE O OTHER IN INSP/MAINT 1 NM 07 2354Y 546 LJ1532 PE0179 THE LEFT ENGINE LEFT TAIL PIPE BROKE AT THE LIP HEAT INLET TUBE. 1 L 7 2 3T 4 T RT 3A20 E4EA 2001051000007 20010510 00007 GL 2001 5 10 20010510AP007 1 20010327 G 3213 ATTACH FITTING AVIAT A1 A1B GL LYC O360 O360* 41514 EA LT MLG STRUT SHEARED G O OTHER O OTHER LD LANDING 1 NE 03 484C 2114 TACH 80.2 HOURS LEFT MAIN GEAR ATTACHMENT(FORWARD STRUT) SHEARED OFF AT FUSELAGE ATTACHMENT POINT DURING NORMAL LANDING OF AIRCRAFT. THE WELDED AREA THAT THE LH FORWARD STRUT ATTACHES TO THE FRAME LOOKS TO HAVE POSSIBLE INADEQUATE PENETRATI ON, POROUS AND CONSIDERED A COLD WELD. 1 H 7 1 3O 3 O NC A22NM E286 2001051000008 20010510 00008 EA 2001 5 10 20010510AP008 1 20010427 G 3040 F307 RESISTOR DHAV DHC6 DHC6300 2802606 EA WINDSHIELD WIPER BURNED M H DEACTIVATE SYST/CIRCUITS B SMOKE/FUMES/ODORS/SPARKS DE DESCENT 1 SW 99 680 WINDSHIELD WIPER DROPPING RESISTOR SHORTED TO GROUND THROUGH DEACTIVATED WINDSHIELD WASHER RESISTOR MOUNT. THE WIPER DRO PPING RESISTOR LEAD CHAFFED ON THE WINDSHIELD WASHER RESISTOR MOUNTING BRACKET. THIS RESULTED IN SMOKE IN THE COCKPIT DU RING DESCENT WHILE USING WINDSHIELD WIPERS IN THE SLOW MODE. DEHAVILLAND MODIFICATION (MOD 6/1827)DEACTIVATED THE WINDS HIELD WASHER OPTION BY REMOVING THE WASHER SWITCH FROM THE OVERHEAD PANEL AND STOWING OR CAPPING THE POWER WIRE TO THE W ASHER RESISTOR. 1 H 7 2 3T RT A9EA 2001052900001 20010529 00001 SO 2001 5 29 20010510CW001 1 20010308 G 2740 69623004 TUBE PIPER PA28 PA28140 7102802 SO LYC O320 O320* 41508 EA STABILIZER DEFECTIVE D K NONE W INADEQUATE Q C IN INSP/MAINT 1 SW 09 567OU 2826467 ON THE TUBE, WHERE BOLT HOLE IS DRILLED THAT MOUNTS TO THE FRONT BRACKET ON STABILATOR, A HOLE IS IN TUBE, (90 DEGREE AN GLE TO THE BOLT HOLE). IT APPEARS THIS HOLE HAS SLAG IN IT AND SLAG EXIST ON INTERIOR OF THE TUBE THAT HAS BEEN THERE W HEN THE PART WAS FABRICATED. THIS EXTRANEOUS HOLE IS AT THE HIGH STRESS POINT IN THE TUBE AND HAS NOT BEEN ON ANY OF TH E TUBES THAT HAVE BEEN INSPECTED FOR THE AD ON THE TUBES. HOLE WAS FOUND WHEN REMOVING THE THICK LAYER OF BLACK PAINT DOWN TO THE ZINC CHROMATE IN AREA THAT FITS INTO THE STABILATOR BRACKETS. THE AREA FIRST APPEARED AS A BLACK DOT OF PAI NT AND CLOSER EXAMINATION REVEALED A HOLE HAD BEEN DRILLED AND FILLED WITH SOME TYPE OF MATERIAL AND PAINTED TO COVER. 1 L 7 1 3O 3 O 2A13 E274 2001052400077 20010524 00077 SO 2001 5 24 20010511CW002 1 20010417 G 3222 6528000 FORK PIPER PA28 PA28181 7102807 SO NLG STRUT SHEARED D EEJA O OTHER O OTHER LD LANDING 1 NM 07 8285Y 288190023 THE AIRCRAFT WAS DOING A TOUCH AND GO, WHEN THE NOSE WHEEL STARTED TO SHIMMY. THE NOSE WHEEL FORK SHEARED OFF FROM THE LOWER STRUT TUBE. COULD NOT TELL IF THERE WAS A PREVIOUS CRACK IN THE TUBE. 1 L 7 1 3O 2A13 2001052400078 20010524 00078 NE 2001 5 24 20010511CW003 2 20010425 G 7250 2A0847 SEAL IAE V2500 V2500A1 NE NR 4 BEARING CRACKED B KB1R K NONE O OTHER IN INSP/MAINT 1 NE 01 PART RECEIVED FOR PENETRANT INSPECTION. PART REJECTED AT PENETRANT INSPECTION FOR INDICATION IN COUNTERBORE. 4 F E311NE 2001052400133 20010524 00133 EA 2001 5 24 20010511CW005 2 20010501 G 8520 CRANKCASE PIPER PA32 PA32R301T 7103220 SO LYC O540 TIO540S1AD 41532 EA HARTZL HCC3Y HCC3YR GL ENGINE CRACKED B BONR K NONE K FLUID LOSS IN INSP/MAINT 1 GL 19 8314B 2077 32R8129021 L748061A FM183 DURING ANNUAL INSPECTION, NOTICED OIL ON LEFT FORWARD SECTION OF ENGINE. REMOVED PROP GOVERNOR AND ENGINE BAFFLING. FO UND SMALL CRACK IN CRANKCASE, FORWARD OF NR 2 CYLINDER UPPER FORWARD HOLD DOWN NUT. CONDITION PROBABLY CAUSED BY AGE, ENGINE HAS NEVER BEEN OVERHAULED. 1 L 7 1 3O 3 O A3SO E14EA 5 C P25EA 2001051500332 20010515 00332 EU 2001 5 15 20010511CW007 1 20010419 G 6520 369025400 GEARBOX HUGHES 369 369FF EU ALLSN 250C 250C30 03013 GL TAIL ROTOR FAILED B E6HR O OTHER O OTHER TX TAXI/GRND HDL 1 NM 01 530HL 10003 1666 0066FF UPON SHUT DOWN, THE PILOT AND MECH NOTICE AN ODD NOISE COMING FROM THE TAIR ROTOR ACCOMPANIED BY A SLIGHT VIBRATION. AI RCRAFT WAS DUE FOR A 100 HR INSPECTION, SO T/R OIL WAS DRAINED AGAIN. THE CHIP PLUG HAD NO CHIPS BUT DID HAVE A BLACK P ASTE. PASTE WAS EXAMINED AND HAD EXTREMELY SMALL METALLIC PARTICLES IN IT. NOT ENOUGH TO ILLUMINATE CHIP LIGHT. GEARB OX WAS DISASSEMBLED FOR INSPECTION. INPUT GEAR SHAFT WAS FOUND TO BE SHEARED IN TWO PIECES. IT IS NO UNDERSTOOD WHY TH E GEARBOX DID NOT COMPLETELY FAIL BECOMING CATASTROPHIC. AIRCRAFT FLEW 3.5 HRS THIS DAY WITH NO EVIDENCE OF A PROBLEM. GEARSHAFT HAS BEEN SENT TO A LAB FOR TESTING AND MDHC HAS BEEN INFORMED. 1 G 7 1 3U 3 U H3WE E1GL 2001052400143 20010524 00143 CE 2001 5 24 20010511CW008 1 20010423 G 5312 07126161 BULKHEAD CESSNA 182 182L 2072726 CE FUSELAGE CRACKED D K NONE O OTHER IN INSP/MAINT 1 NM 01 42397 4787 18259003 FAILED INSPECTION DUE TO CRACKS IN CRITICAL AREAS, REPLACED. 1 H 7 1 3O NT 3A13 2001052400013 20010524 00013 EA 2001 5 24 20010511CW014 2 20010419 G 7322 30802 FLOAT PRECISION PIPER PA28 PA28181 7102807 SO LYC O360 O360A4M 41514 EA CARBURETOR DAMAGED B UC2R K NONE O OTHER IN INSP/MAINT 1 GL 19 41460 75072523 2843153 L3611936A DURING OVERHAUL THE CARBURETOR FLOAT WAS FOUND WITH ONE OF THE CHAMBERS HALF FULL OF 100 LOW LEAD. 1 L 7 1 3O 3 O 2A13 E286 2001052400029 20010524 00029 SW 2001 5 24 20010514CW003 1 20010507 G 3222 48838503 CYLINDER GULSTM 112 114ARKWELL 7630315 SW LYC O540 TIO540* 41532 EA NLG FAILED H K NONE O OTHER NR NOT REPORTED 1 SW 99 57BH 3800 14001 NOSE GEAR ACTUATING CYLINDER, PN 48838503, FAILED INTERNALLY, CAUSING NOSE GEAR COLLAPSE, RESULTING IN MINOR DAMAGE TO A IRCRAFT 1 L 7 1 3O 3 O A12SO E14EA 2001052400030 20010524 00030 CE 2001 5 24 20010514CW004 1 20010418 G 5510 95620010634 STABILIZER BEECH 95 95B55 1152729 CE CONT O470 IO470* 17026 SO RIGHT BENT D K NONE O OTHER IN INSP/MAINT 1 SW 09 1848W 4195 TC1534 DURING INSTALLATION OF RIGHT HAND ELEVATOR, IT WAS DISCOVERED THAT WHEN THE ELEVATOR WAS MOVED FROM FULL DOWN TO FULL U P, THE STABILIZER WOULD FLEX UPWARD .4375. INVESTIGATION DISCLOSED THAT THE STABILIZER WAS BENT DOWN 2 DEGREES AT THE CENTER HINGE( BOTH SPARS) A TRIPLE PATCH WAS FOUND ON THE LOWER REAR SKIN, STARTING 12 INCHES FROM THE TIP. NO RECORD OF THIS REPAIR CAN BE FOUND IN THE AIRCRAFT RECORDS. CORRECTIVE ACTION: REMOVED AND REPLACED STABILIZER. 1 L 7 2 3O 3 O RT 3A16 E1CE 2001051500506 20010515 00506 CE 2001 5 15 20010515AP002 1 20010514 G 5712 57222061 RIB CESSNA 441 441 2076020 CE LEFT CENTER WING CRACKED B K NONE O OTHER IN INSP/MAINT 1 SW 99 12DT 8620 4410040 DURING A SCHEDULED INSPECTION, THE LEFT WING CENTER SECTION CANTED RIB CAP (CWS 26.85 INCHES) WAS FOUND CRACKED. THE CAN TED RIB UPPER CAP (P/N: 5722206-1) WAS CRACKED AFT OF THE AFT MAIN SPAR AT FS 177.45, IN THE BEND RADIUS, AND RAN AFT AP PROXIMATELY 1.375 INCH. THE CRACK WAS FIRST NOTED USING VISUAL INSPECTION THEN VERIFIED WITH DYE PENETRANT. AFTER REMOVI NG THE RIB CAP, CLOSE EXAMINATION OF THE PART REVEALED THAT THE CAP WAS MANUFACTURED SO THAT THE BEND WAS PARALLEL WITH GRAIN OF THE METAL INSTEAD OF PERPENDICULAR WHICH COULD RESULT IN THIS TYPE OF FAILURE. CESSNA CURRENTLY DOES NOT HAVE A NY SPECIFIC INSPECTIONS RELATING TO THIS MATTER, THEREFORE,THIS AREA SHOULD BE CLOSELY CHECKED DURING INSPECTIONS. 1 L 7 2 3T RT A28CE 2001051500081 20010515 00081 EU 2001 5 15 20010515AP004 1 20010504 G 3233 AC11184 ACTUATOR FOKKER F27 F27MK400 4990626 EU MLG BINDING M O OTHER J WARNING INDICATION CL CLIMB 1 SW 99 8843 10652 LANDING GEAR UNSAFE LIGHT REMAINED ON AFTER SELECTION OF LANDING GEAR TO THE UP POSITION. MAIN LANDING GEAR UPLOCK ACTUA TOR WAS SLOW TO RETRACT TO LOCK THE GEAR IN THE UP POSITION AND TO EXTINQUISH THE UNSAFE LIGHT. THE ACTUATOR IS SPRING- LOADED TO THE RETRACT POSITION. 2 H 7 2 4T A817 2001051500083 20010515 00083 CE 2001 5 15 20010515AP005 1 20010504 G 7810 829415 EXHAUST HEADER CESSNA 421 421C 2076016 CE CONT O520 GTSIO520N 17032 SO WASTEGATE FLANGE DEFECTIVE B K NONE O OTHER IN INSP/MAINT 1 SW 99 6867D 31 421C1084 THIS UNIT IS MANUFACTURED IN TWO HALVES, WHERE THE UPPER & LOWER HALVES WELDED TOGETHER (AT THE WASTE GATE FLANGE) THERE IS A HOLE AT THE WELD AREA ON EACH SIDE. THE REPLACMENT PART HAS AN ADDITIONAL WELD IN THESE AREAS THAT ARE NOT PRESEN T ON THE DEFECTIVE PART. IT APPEARS THAT THE MANUFACTURING PROCESSES (WELDING)WERE NOT COMPLETED BEFORE THIS PART LEFT THE MANUFACTURE. THIS DEFECT WAS FOUND WHILE C\W THE EXHAUST PRESSURE TEST REQUIRMENTS OF AD 2000-01-16. 1 L 7 2 3O 3 O A7CE E7CE 2001051500093 20010515 00093 2001 5 15 20010515AP007 4 20010404 G 3421 7000466906 INDICATOR ATTITUDE FAILED D O OTHER W INADEQUATE Q C CR CRUISE 1 EA 03 1NA 25 AFTER A FEW FLIGHTS WITH THE RECENTLY INSTALLED ADI IN THE PILOTS POSITION, THE GLIDESLOPE INDICATOR FAILED IN THE CENTE R POSITION (INDICATING ON GLIDE PATH). INDICATOR REMAINED PARKED IN THIS POSITION FOR THE DURATION OF THE FLIGHT. REMO VED AND REPLACED UNIT. UNIT WAS OVERHAULED BY METRO AIRCRAFT INSTRUMENTS 2001052400066 20010524 00066 EA 2001 5 24 20010516CW001 2 20010511 G 8520 76220 STUD PIPER PA31 PA31350 7103110 SO LYC O540 TIO540J2BD 41532 EA NR 3 CLYINDER FRACTURED G A UNSCHED LANDING D A INFLIGHT SEPARATION FLAME/FIRE CR CRUISE 1 AL 01 45008 1097 318052167 L691661A AT CRUISE FLIGHT, THE NR 3 CYLINDER SEPARATED FROM THE ENGINE CASE, WHICH RESULTED IN AN INFLIGHT FIRE. THE ENGINE CASE , CYLINDER HOLD DOWN STUDS THROUGH BOLT STUDS AND NR 3 CONNECTING ROD WERE SENT FOR LAB INVESTIGATION. INVESTIGATION RE SULTS: THE PRIMARY CAUSE WHICH LED TO THE SEPARATION OF THE NR 3 CYLINDER WAS THAT THE THROUGH BOLT STUDS WERE MOST LIK ELY NOT PROPERLY TORQUED. 1 L 7 2 3O 3 O A20SO E14EA 2001052400003 20010524 00003 CE 2001 5 24 20010517CW009 1 20010427 G 2410 DOFF10300J ALTERNATOR CESSNA 177 177 2073704 CE LYC O360 O360* 41514 EA ENGINE SEIZED B R7LR K NONE O OTHER IN INSP/MAINT 1 WP 25 412WS 126 17701475 ALTERNATOR OVERHAULED, INSTALLED ON AC. FRONT BEARING BALL CAGE BROKE APART AND ALLOWED BALLS TO COLLECT ON ONE SIDE OF BEARING, LOCKING THE ALTERNATOR SHAFT. FAILURE OCCURRED ON 2/10/2001 AFTER 126 HOURS TSOH. 1 H 7 1 3O 3 O NT A13CE E286 2001052900037 20010529 00037 2001 5 29 20010518CW001 4 20010430 G 3421 GYRO MOONEY M20 M20F 5870214 SW COCKPIT CONTAMINATED B K NONE O OTHER IN INSP/MAINT 1 WP 27 9514M 4315 2383 670091 DURING ANNUAL INSPECTION, FOUND LIQUID IN WINDOW OF GYRO, DISCONNECTED LINE TO HAVE WATER FLOW OUT, REMOVED INSTRUMENT. OPENDED CASE AND FOUND LONG-TERM CORROSION ON ALL INTERNAL PARTS. REPLACED WITH OVERHAULED INSTRUMENT. NO OTHER INSTR UMENTS CONTAINED WATER MAY HAVE GOTTEN WATER THROUGH A LEAKING EXTERIOR COWL DECK. 1 L 7 1 3O 2A3 2001052900269 20010529 00269 CE 2001 5 29 20010523CW001 1 20010501 G 2710 051178217 YOKE CESSNA 172 172L 2072432 CE COCKPIT CORRODED D K NONE O OTHER AP APPROACH 1 SO 19 3802Q 3057 17259902 AIRCRAFT ON FINAL APPROACH, CONTROL YOKE FAILED AT APPROX 30 FT AGL. CONTROL YOKE FAILED JUST ABOVE PIVOT POINT BEHIND INSTRUMENT PANEL. CONTROL YOKE WAS EXTREMELY CORRODED AT FRACTURE POINT. 1 H 7 1 3O NT 3A12 2001052900271 20010529 00271 EU 2001 5 29 20010523CW002 1 20010407 G 6510 83A851BC3 BEARING SNIAS 350 AS350B2 8680813 EU T/R DRIVE SHAFT ROTATED C AALA K NONE O OTHER IN INSP/MAINT 1 SW 01 4035W 2671 2912 AT A SCHEDULED INSPECTION THE BEARING PN 83A851BC3 HAD ROTATED IN THE RUBBER BUSHING PN FA3819 APPROX .3750. WE HAVE BE EN COMPLYING WITH SB REGARDING THE GREASING AND INSPECTION OF THESE BEARINGS AND STILL HAD A BEARING TURN. THIS IS AN A REA THAT CALLS FOR SPECIAL ATTENTION DURING INSPECTIONS AND DAILY PRE FLIGHTS. AT THIS TIME WE ARE INSTALLING THE NEWER TYPE BEARINGS THAT THIS SB DOES NOT APPLY TO. 1 G 7 1 3U H9EU 2001052900272 20010529 00272 EU 2001 5 29 20010523CW003 1 20010410 G 6510 350A23106320 SEAL SNIAS 350 AS350B2 8680813 EU T/R DRIVE SHAFT MISSING C K NONE O OTHER IN INSP/MAINT 1 SW 01 4035W 2671 2912 2912 AT A SCHEDULED INSPECTION THE SELF ADHESIVE SEAL PN 350A-1063-20 WAS FOUND NOT TO BE INSTALLED. THIS IS A SEAL THAT IS INSTALLED FOR DISSIMILAR METAL CORROSION ON THE TAIL ROTOR DRIVE SHAFT HANGAR SUPPORT AND THE HANGAR BEARINGS. 1 G 7 1 3U H9EU 2001052900280 20010529 00280 CE 2001 5 29 20010523CW005 1 20010206 G 2780 3910104044 BEARING HELIO H295 H295 4300802 CE TORQUE TUBE CRACKED D K NONE O OTHER IN INSP/MAINT 1 NM 09 5479G 3782 1261 TORQUE TUBE BEARING MADE FROM NYLON MATERIAL HARDENS WITH AGE AND DURING OPERATION OF SLAT TORQUE TUBE. THE BEARING STA RTS TO CRACK AT RIVET HOLES THAT ATTACHES IT TO WING RIB. REPLACED WITH NEW PORTS. 1 H 7 1 3O 1A8 2001052900281 20010529 00281 CE 2001 5 29 20010523CW006 1 20010206 G 2780 3910104046 BEARING HELIO H295 H295 4300802 CE TORQUE TUBE CRACKED D K NONE O OTHER IN INSP/MAINT 1 NM 09 5479G 3782 1261 TORQUE TUBE BEARING MADE FROM NYLON MATERIAL HARDENS WITH AGE AND DURING OPERATION OF SLAT TORQUE TUBE THE BEARING START S TO CRACK AT RIVET HOLES THAT ATTACHES IT TO WING RIB. REPLACED WITH NEW PARTS. 1 H 7 1 3O 1A8 2001052900282 20010529 00282 SW 2001 5 29 20010524CW001 1 20010427 G 7603 63255555 THROTTLE ARM MOONEY M20 M20R 5870225 SW CONT O550 IO550* SO ENGINE WORN D K NONE O OTHER IN INSP/MAINT 1 GL 25 143TM 55 290242 684902 WHILE WARMING THE ENGINE FOR OIL CHANGE, NOTED THAT THERE WAS AN EXCESSIVE AMOUNT OF FREE PLAY IN THE THROTTLE LINKAGE. AFTER RUNNING THE ENGINE UP TO 1500 RPM, PULLED THROTTLE BACK TO IDLE, BUT THE ENGINE RPM DID NOT DECREASE. HAD TO USE THE MIXTURE CONTROL TO STOP ENGINE. INSPECTED THROTTLE LINKAGE AND FOUNDTHE THROTTLE ARM WAS LOOSE ON THE SHAFT. TORQ UE SEAL ON THE ATTACHING NUT WAS NOT BROKEN AND NUT DID NOT APPEAR TO HAVE MOVED SINCE INSTALLATION. REMOVED THE THROTT LE ARM AND FOUND THE SERRATIONS ON THE ARM WHERE THE ARM MEETS THE THROTTLE SHAFT WERE WORN AWAY. ATTACHING NUT WAS NOT TIGHTENED PROPERLY AT INSTALLATION. MFG SUPPLIED NEW THROTTLE ARM , INSTALLED IT USING PROPER TORQUE PER SB. 1 L 7 1 3O 3 O RT 2A3 E3SO 2001052900283 20010529 00283 NE 2001 5 29 20010524CW002 1 20010427 G 6520 643566409043 HOUSING SKRSKY S64 S64E 8142604 NE T/R GEARBOX CRACKED B JYDR K NONE O OTHER IN INSP/MAINT 1 NM 09 194AC 6386 64017 DURING TEARDOWN FOR OVERHAUL, A CRACK WAS VISUALLY NOTICED AT APPROX THE 2 OCLOCK POSITION(AS INSTALLED ON AIRCRAFT) IN THE STRADDLE MOUNT OF THE IDLER GEAR ALIGNMENT BEARING PN SB2154-1 OF CENTER HOUSING PN 6435-66409-043. FURTHER INSPECT ION AFTER REMOVAL OF BEARING RETAINER PN 6435-66427-103 REVEALED THE STRADDLE MOUNT WAS CRACKED IN HALF, PASSING THROUGH THE .275 IN DIAMETER HOLE FOR ROSAN STUD PN SF101-125A-6A. NO SECONDARY DAMAGE DUE TO THIS FAILURE WAS NOTED. 2 G 7 2 4U H4EA 2001052900290 20010529 00290 SO 2001 5 29 20010525CW001 1 20010226 G 5540 2344715 RUDDER HORN PIPER PA30 PA30 7103002 SO LYC O320 IO320B1A 41508 EA RUDDER CRACKED G K NONE O OTHER IN INSP/MAINT 1 WP 25 7129Y 4374 30151 REMOVED HORN DUE TO WEAR BETWEEN HORN AND RUDDER. FOUND CRACKS FROM MOUNT HOLES TO TOP OF RUDDER HORNS OF SAME PART NUM BER TO BE CRACKED IN A SIMILAR FASHION . 1 L 7 2 3O 3 O A1EA 1E12 2001052900336 20010529 00336 SW 2001 5 29 20010525CW005 1 20010525 G 2710 145520101 CONTROL CABLE NAVION NAVION L17B 6150108 SW AILERON FRAYED D K NONE O OTHER IN INSP/MAINT 1 SO 11 5335K NAV42235B UPON REMOVAL OF CABLES, FOUND FRAYED SECTION LOCATED JUST OUTBOARD OF THE AILERON ROLLERS (MID-WING ABOVE THE MAIN LANDI NG GEAR TRUNION). PROBABLE CAUSES INCLUDE ENVIRONMENTAL DAMAGE, TIME, AND INADEQUATE MAINTENCE OF ROLLERS. ROLLERS IN THIS AREA OF THIS AIRCRAFT WERE FROZEN. CABLES HAD BEEN COATED WITH GREASE IN THIS AREA OVER THE YEARS AND FORMED A SEM I-HARD SHELL WHICH COULD HAVE TRAPPED MOISTURE LEADING TO THE DAMAGE. RECOMMENDATIONS ARE TO MAINTAIN CABLES AND ROLLER S PROPERLY ESPECIALLY IN HARD TO REACH AREAS, AND THAT CABLES HAVE A FINITE LIFETIME. 1 L 7 1 3O A782 2001052900337 20010529 00337 SW 2001 5 29 20010525CW006 1 20010525 G 2730 1455201029 CONTROL CABLE NAVION NAVION L17A 6150106 SW ELEVATOR FRAYED D K NONE O OTHER IN INSP/MAINT 1 SO 11 5335K NAV42235 UPON REMOVAL OF CABLE, FOUND FRAYED SECTION LOCATED AT THE LOWERMOST POINT EXITING THE PULLEY. PROBABLE CAUSES INCLUDE ENVIRONMENTAL DAMAGE (WHEEL WELL AREA) AND TIME. AS PART OF ANNUAL, ALL CABLES IN THIS AIRCRAFT WERE BEING REPLACED DUE TO OVERALL AGE AND CONDITION WHEN THIS PROBLEM WAS FOUND. 1 L 7 1 3O A782 2001052900338 20010529 00338 CE 2001 5 29 20010525CW007 1 20010327 G 7602 C29950J0101 CONTROL CABLE CESSNA 210 210L 2073448 CE ENGINE BROKEN G A UNSCHED LANDING R PARTIAL RPM/PWR LOSS CR CRUISE 1 SO 05 1759X 367 210L60780 ENGINE STARTED TO SPAR DOWN IN FLIGHT. PILOT ATTEMPTED TO ADJUST MIXTURE, AFTER TURNING ON THE BOOST PUMPS. PILOT STAT ED, THE MIXTURE CABLE WAS LOOSE IN HIS HAND. ENGINE SHUT DOWN AND AIRCRAFT WAS LANDED , GEAR UP IN A FIELD. UPON EXAMI NATION, THE MIXTURE CABLE WAS FOUND BROKEN AT THE POINT IT ENTERED THE PROTECTIVE BARREL OF THE ROD END. CORROSION WAS EVIDENT. 1 H 7 1 3O 3A21 2001052900340 20010529 00340 SO 2001 5 29 20010529CW001 1 20010502 G 2740 62701113 CONTROL CABLE PIPER PA28 PA28161 7102803 SO STABILATOR FRAYED D K NONE O OTHER IN INSP/MAINT 1 EA 25 9182W 6559 2841130 LEFT FORWARD STABILATOR CABLE WORN AND FRAYING AT SPAR FAIRLEAD AND REAR SPAR PULLEY. DIFFICULT TO DETECT WITHOUT REMOV ING CABLE. 1 L 7 1 3O 2A13 2001052900341 20010529 00341 SO 2001 5 29 20010529CW003 1 20010508 G 2820 STCSA1480WE FUEL TANK PIPER PA23 PA23250 7102308 SO WING TIP BROKEN D K NONE O OTHER IN INSP/MAINT 1 SO 15 21551 274714 FIBERGLASS WINGTIP FUEL TANK STC SA1480WE HAS AN EDGE DISTANCE OF .2500 INCH SCREW HOLES WHICH BROKE FIBERGLASS OUT CAUS ING THE WINGTIP TO FALL OFF, WHILE AIRCRAFT WAS ON GROUND. FIBERGLASS TIP DOES NOT HAVE SUFFICIENT STRENGTH DUE TO FIB ERGLASS THICKNESS AND EDGE DISTANCE. 1 L 7 2 3O 1A10 2001060700044 20010607 00044 CE 2001 6 7 20010529CW007 1 20010423 G 3710 632617D GEAR CONT CESSNA 337 337H 2075732 CE VACUUM PUMP WORN D K NONE O OTHER IN INSP/MAINT 1 SO 15 729AS 725 33701938 A DETAINLED INVESTIGATION OF THE STARTER DRIVE REVEALED THAT ALL OF THE GEAR TEETH WERE WORN EXCESSIVELY ON ONE OF THE B EVEL GEARS WHICH DRIVES THE VACUUM PUMP. 1 H 7 2 3O A6CE 2001060700048 20010607 00048 CE 2001 6 7 20010529CW010 1 20010420 G 3230 08411132 SCREW CESSNA 414 414 2075908 CE MLG DAMAGED B AK6R K NONE O OTHER IN INSP/MAINT 1 SW 19 922AS 4803 4140033 UPON ANNUAL INSPECTION, FOUND ADJUSTING SCREW PN 084113-2, THREADS AT THE POINT OF PULLING OUT OF EYE BOLT END FITTINGS, PN 0841111-3. THIS IS THE 4TH DISCOVERY OF ADJUSTING SCREW AT THE POINT OF FAILURE WHICH, IF NOT HAD BEEN CORRECTED, W OULD BE IMMINENT GEAR FAILURE, SINCE THIS IS THE ONLY ITEM LOCKING THE MAIN GEAR INTO POSITION AFTER EXTENSION. 1 L 7 2 3O RT A7CE 2001060700049 20010607 00049 CE 2001 6 7 20010529CW011 1 20010405 G 3230 08411113 SCREW CESSNA 414 414 2075908 CE MLG DAMAGED B AK6R K NONE O OTHER IN INSP/MAINT 1 SW 19 922AS 4803 4140033 UPON ANNUAL INSPECTION, FOUND ADJUSTING SCREW, PN 084113-2, THREADS AT THE POINT OF PULLING OUT OF EYE BOLT END FITTINGS , PN 0841111-3,. THIS IS THE 4TH DISCOVERY OF ADJUSTING SCREW AT THE POINT OF FAILURE WHICH, IF NOT HAD BEEN SINCE THIS IS THE ONLY ITEM LOCKING THE MAIN GEAR INTO POSITION AFTER EXTENSION. 1 L 7 2 3O RT A7CE 2001071000059 20010710 00059 SW 2001 7 10 20010529CW014 1 20010313 G 7160 600382305 LATCH MOONEY M20 M20S 5870226 SW ALT AIR DOOR WORN B DY1R K NONE O OTHER IN INSP/MAINT 1 EA 13 2192N 250 300041 DURING ROUTINE OIL CHANGE, FOUND MAGNETIC LATCH FOR ALTERNATE AIR DOOR BOX VERY WORN AND AREA AROUND IT COVERED IN ALUMI NUM DUST. THE LATCH HOLDS THE DOOR IN THE CLOSED POSITION UNTIL THE AIR FILTER BECOMES CLOGGED WITH WATER/ICE (WHEN IN SUCH CONDITIONS) FORCING THE ALTERNATE AIR DOOR TO OPEN AUTOMATICALLY. WE ROUTINELY FIND THESE LATCHES VERY WORN AND ON THE VERGE OF COMING APART. THIS AIR BOX/LATCH SETUP IS USED ON SEVERAL MODELS, WHICH ALL HAVE THE SAME RECURRING WEAR PROBLEM. 1 L 7 1 3O RT 2A3 2001071000060 20010710 00060 CE 2001 7 10 20010530CW001 1 20010530 G 3220 NAS4645A15 BOLT CESSNA 177 177RG 2073709 CE NLG MISSING D K NONE O OTHER LD LANDING 1 SO 13 7537V 5311 0834 NOSE GEAR COLLAPSED ON LANDING ROLL OUT, DOWN LOCK LINK BOLT(LOWER) WAS FOUND MISSING PN NAS4645A15, NO MEANS OF SAFETY MAY BE USED WITH THIS DESIGN, ONLY LOCTITE CV SEALANT AS STATED IN SERVICE MANUAL. PART HAD 5311 HOURS. 1 H 7 1 3O A20CE 2001062000053 20010620 00053 WP 2001 6 20 20010531CW001 1 20010507 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 538 HA3044 DOUBLER DELAMINATION NO SIGNS OF CORROSION OR IMPACT WHICH MIGHT CAUSE DELAMINATION. CAUSE UNKNOWN 1 G 7 1 3O 4H11 2001062000054 20010620 00054 2001 6 20 20010531CW002 4 20010410 G 6122 D4718 DRIVE GEAR HARTZL PIPER PA44 PA44180 7104402 SO PROP GOVERNOR CRACKED B WIWR K NONE O OTHER IN INSP/MAINT 1 WP 07 4144C 1034 227YS 4496020 GOVERNOR WAS SUBMITTED FOR INSPECTION DUE TO AN ENGINE FIRE ON THE GROUND. DURING INSPECTION, THE DRIVE GEAR PN D 4718 WAS FOUND CRACKED IN THE DRIVE GEAR SPLINES THAT ENGAGE THE GOVERNOR DRIVE ON THE ENGINE. THE GEAR CONTAINS TWO CRACKS , ALMOST 180 DEGREES APART AND OVER .5000 INCH LONG. HAD THE ENGINE NOT CAUGHT FIRE, THIS GEAR MOST LIKELY WOULD HAVE F AILED IN SERVICE. 1 L 7 2 3O A19S0 2001062000055 20010620 00055 CE 2001 6 20 20010531CW003 1 20010425 G 2731 15703072 CIRCUIT BOARD CESSNA 206 TU206F 2073353 CE ELEV TRIM SYSTEM SHORTED D K NONE O OTHER NR NOT REPORTED 1 NM 08 8033Q 704 420603088 SHORT CIRCUIT RESULTED IN BURNED SPOT ON BOARD AND OPEN CIRCUIT. CAUSE APPEARS TO HAVE RESULTED FROM ELECTRICAL OVERLOA D TO CONNECTION. CAUSE FOR OVERLOAD-UNKNOWN. 1 H 7 1 3O A4CE 2001062000061 20010620 00061 SW 2001 6 20 20010601CW004 1 20010509 G 6510 407340339103 BEARING BELL 407 407 SW TAIL ROTOR SEIZED D YADA A UNSCHED LANDING E VIBRATION/BUFFET CR CRUISE 1 EA 19 70AP 786 53409 PILOT FELT EXCESSIVE VIBRATION AND HEADED BACK TO BASE, AFTER SHORT PERIOD VIBRATION INCREASED, PILOT LANDED IN FIELD. FOUND TAIL ROTOR HANGER BEARING SEIZED AND SPUN IN BEARING HOUSING. THE BEARING THAT FAILED IS THE FIRST BEARING AFT LO CATED JUST FORWARD OF OIL COOLER BLOWER. 1 G 7 1 3U O H2SW 2001062000066 20010620 00066 CE 2001 6 20 20010601CW009 1 20010511 G 3240 LINE BEECH 23 C23 1151242 CE BRAKE SYS LEAKING B K NONE K FLUID LOSS IN INSP/MAINT 1 GL 13 9743L M1371 MOST OF THE FLEXIBLE FLUID LINES IN THIS AIRCRAFT WERE FOUND TO BE STIFF. TWO OF THE BRAKE LINES WERE FOUND TO BE CHAFF ING ON THE FORWARD FIREWALL AREA AND WERE WORN SMOOTH ON THE OUTSIDE. BOTH OF THESE WERE LEAKING THROUGH THE HOSE. ALL OF THE FLEXIBLE FLUID LINES IN THE BRAKE SYSTEM WERE REPLACED. THE FLEXIBLE FLUID LINES BETWEEN THE FUEL TANKS AND SEL ECTOR VALVE WERE ALSO REPLACED. MOST OF THESE APPEARED TO BE ORIGINAL AND WERE ABOUT 30 YEARS OLD. THE FLEXIBLE LINES IN THE ENGINE COMPARTMENT ARE BEING REPLACED ALONG WITH ENGINE MAINTENANCE AT ANOTHER LOCATION. 1 L 7 1 3O A1CE 2001062000072 20010620 00072 CE 2001 6 20 20010604CW001 1 20010509 G 5712 RIB CESSNA 177 177RG 2073709 CE LT WING CRACKED B T9ZR K NONE O OTHER IN INSP/MAINT 1 NM 09 52472 177RG1196 DURING THE INSTALLATION OF SHOULDER HARNESS KITS, THE HEADLINER WAS REMOVED. CORROSION ON CARRY THRU SPAR FORE AND AFT TOP SPAR CAPS AND SKIN WAS NOTICED. CORROSION WAS ALSO PRESENT AT LEFT AND RIGHT ROOT RIBS. LEFT ROOT RIB HAD SMALL CR ACK. NO FURTHER ACTION TAKEN. 1 H 7 1 3O A20CE 2001062000073 20010620 00073 CE 2001 6 20 20010604CW002 1 20010405 G 7810 17540071 RISER CESSNA 172 172Q 2072437 CE LYC O360 O360* 41514 EA EXHAUST SYS CRACKED D K NONE O OTHER IN INSP/MAINT 1 CE 09 469NE 17275952 NR 3 EXHAUST RISER CRACKED AT FLANGE. NOTED: COMMON FAILURE, PER EXHAUST REPAIR STATION. 1 H 7 1 3O 3 O NT 3A12 E286 2001062000074 20010620 00074 EU 2001 6 20 20010604CW003 1 20010410 G 6120 21014 COLLAR SOCATA MS894 MS894A 8402842 EU FRNKLN 6AV350 6A350C1 27043 EA PROPELLER LOOSE D K NONE O OTHER IN INSP/MAINT 1 CE 09 43BF 11931 528663 PROBLEM REPORTED: PROP WOULD NOT CYCLE W/WARM ENGINE OIL. DISASSEMBLED ENGINE AND FOUND ONE SOCKET HAS SCREW .1562 THA T HOLDS THE TRANSFER COLLAR TOGETHER BROKEN ALLOWING THE COLLAR AND SEALS TO BECOME LOOSE ON CRANKSHAFT OIL TO ESCAPE AN D NOT ALL TO THE PROPELLER. NO IMPROPER REPAIR, PREVIOUS ACTIONS. 1 L 7 1 3O 3 O 7A14 E9EA 2001062500167 20010625 00167 NE 2001 6 25 20010604CW005 1 20010426 G 5610 S16206510421 TRACK SKRSKY S58T S58JT 8141807 NE PILOT WNDOW DEFECTIVE A O OTHER D INFLIGHT SEPARATION NR NOT REPORTED 1 GL 23 902CH 65 581539 TRACK ASSEMBLY ON PILOTS SLIDING WINDOW CAME APART ALLOWING WINDOW TO DEPART THE AIRCRAFT. WINDOW FRAME AND TRACK ASSEM BLY HAD ONLY 65 HOURS TT APPARENT DEFECTIVE TRACK ASSEMBLY. 2 G 7 2 4U 1H11 2001062500168 20010625 00168 CE 2001 6 25 20010604CW006 1 20010514 G 3220 0542106 SPRING CESSNA 170 170B 2072306 CE TAIL WHEEL BROKEN D O OTHER O OTHER NR NOT REPORTED 1 AL 01 3143A 300 25787 TAILWHEEL SPRING BROKE AT AN EXISTING CRACK. TAILWHEEL THEN DAMAGED THE LOWER SKINS OF THE RUDDER. 1 H 7 1 3O A799 2001062500172 20010625 00172 SW 2001 6 25 20010604CW012 1 20010522 G 2810 FUEL CELL MOONEY M20 M20F 5870214 SW FUEL SYSTEM CONTAMINATED G A UNSCHED LANDING R Y PARTIAL RPM/PWR LOSS ENGINE STOPPAGE CL CLIMB 1 GL 15 301LM 670323 ENGINE LOST POWER, THEN QUIT, DURING TAKEOFF CLIMB. AIRCRAFT MADE OFF AIRPORT LANDING. INVESTIGATION FOUND WATER IN THE RIGHT HAND FUEL SUMP. AIRCRAFT HAD BEEN PARKED OUTSIDE THROUGH HEAVY RAIN. 1 L 7 1 3O 2A3 2001062500174 20010625 00174 GL 2001 6 25 20010604CW015 3 20010319 G 6110 HCB37N5 CLAMP GULSTM 690TP 690A 0141722 SW HARTZL HCB3T HCB3TN5 GL PROPELLER CORRODED B K NONE O OTHER IN INSP/MAINT 1 SW 15 246T 560 373 11254 BV3280 CORROSION IN CLAMPS AND BEARING RACES, REJECTED ALL 3 CLAMPS AND 1 RACE. 1 H 7 2 3T 2A4 6 C P15EA 2001062500176 20010625 00176 GL 2001 6 25 20010604CW016 1 20010511 G 7160 191965910 HINGE BLANCA 17 1731A 1220435 GL LYC O540 IO540* 41532 EA HARTZL HCC3Y HCC3YR GL ALT AIR DOOR FAILED D K NONE O OTHER IN INSP/MAINT 1 EA 05 9505E 7532159 L1270848A DY270 PILOT DID NOT REPORT ANY ABNORMAL OPERATION. AIR BOX WAS REMOVED AT ANNUAL INSPECTION FOR SERVICING AND ALTERNATE AIR D OOR FELL ON FLOOR. ALL HINGE PIN SEGMENTS HAD FAILED. 1 L 7 1 3O 3 O A18CE 1E4 5 C P25EA 2001062600017 20010626 00017 NE 2001 6 26 20010605CW014 2 20010515 G 7314 640197 SHAFT NASH GE CFM56 CFM56* 13802 NE FUEL PUMP BROKEN B K NONE O OTHER IN INSP/MAINT 1 SO 17 FB78955 UPON DISASSEMBLY I FOUND THE SHAFT IN TWO PIECES. THE STANDARD 64-0197 SHAFT IS A SOLID ONE PIECE SHAFT. THE SHAFT THA T WAS REMOVED FROM THIS UNIT WAS MACHINED INTO TWO DIFFERENT PIECES, AND WAS HELD TOGETHER BY TWO PINS. THIS IS NOT A S TANDARD REPAIR. ONE OF THE FINS FAILED AND SHAFT SEPARATED. 4 F E2GL 2001062600018 20010626 00018 CE 2001 6 26 20010605CW015 1 20010502 G 5540 S100442A BUSHING CESSNA 172 172 2072402 CE RUDDER HINGE DAMAGED D K NONE O OTHER IN INSP/MAINT 1 WP 25 NEW RUDDER HINGE HOT BUSHING, MISSING LARGE CHUNK OUT OF BOTTOM END OF BUSHING. 1 H 7 1 3O NT 3A12 2001062600019 20010626 00019 CE 2001 6 26 20010605CW016 1 20010426 G 7714 S33291 TACHOMETER CESSNA 172 172R 2072401 CE COCKPIT OUT OF TOLERANCE D K NONE O OTHER IN INSP/MAINT 1 NM 01 NEW TACHOMETERS OUT OF MFG 50 RPM TOLERANCES. DIGITAL CHECKS OF FINE ADDITIONAL 172R AND 172S AIRCRAFT SHOWED TACH TO R EAD WITHIN PLUS OR MINUS 50 RPM. DISCOVERED WHEN DOING AD. 1 H 7 1 3O NT 3A12 2001062600020 20010626 00020 CE 2001 6 26 20010605CW017 1 20010516 G 2434 DOFF10300E ALTERNATOR CESSNA 337 337G 2075730 CE CONT O360 IO360G 17025 SO FWD ENGINE FAILED B N9VR O OTHER H ELECT. POWER LOSS-50 PC NR NOT REPORTED 1 SO 03 297DC 31 01697 352438 OWNER OF THIS AIRCRAFT EXPERIENCED FWD ENGINE ALTERNATOR FAILURE (AS INDICATOR BY FAILURE LIGHT) DURING FLIGHT. TECHNI CIAN AND OWNER REMOVED ALTERNATOR FROM ENGINE AND DISCOVERED THE DRIVE SHAFT SHEARED. THE GEAR RETAINING BOLT HAD RUBBE D INTERNALLY AND BUSTED A PIECE OF THE COTTER PIN OFF, WHICH WAS FOUND ON THE MAGNETIC OIL DRAIN PLUG. THE DRIVE GEAR A LSO DISPLAYED SIGNS OF WEAR. THE ALTERNATOR SHAFT FAILURE APPEARS TO BE A MATERIAL DEFECT. 1 H 7 2 3O 3 O A6CE E1CE 2001062800012 20010628 00012 2001 6 28 20010605CW018 4 20010504 G 2562 AK450 TRANSMITTER MOONEY M20 M20R 5870225 SW CONT O550 IO550* SO ELT FAILED B DY1R K NONE L NO TEST IN INSP/MAINT 1 EA 13 121RP 393 290141 DURING ANNUAL INSPECTION, PERFORMED ELT INSPECTION IAW FAR 91.207D, AND FOUND THAT ELT DOES NOT TRANSMIT A SIGNAL EVEN T HOUGH RED TRANSMIT LIGHT ON UNIT LIGHTS UP. UNIT TESTED USING 3 DIFFERENT ANTENNA SOURCES AND VERIFIED THAT ELT BATTERY IS GOOD. TRANSMIT LIGHT WORKS IN THE ON POSITION AND ARM POSITION WHEN THE G SWITCH IS ACTIVATED BUT STILL NO AUDIBLE SIGNAL HEARD FROM AIRCRAFT RADIOS OR A PORTABLE AM RADIO. 1 L 7 1 3O 3 O RT 2A3 E3SO 2001071600001 20010716 00001 SO 2001 7 16 20010605CW019 1 20010511 G 3260 SWITCH SWFTMS GC1B GC1B 9230104 SO CONT O360 IO360C 17025 SO COCKPIT DEFECTIVE G O OTHER N FALSE WARNING LD LANDING 1 GL 25 2429B 3729 060654R INVESTIGATION SUBSEQUENT GEAR UP LANDING, FINDS WIRES TO THROTTLE MICRO SWITCH FOR GEAR WARNING SYSTEM INCORRECTLY CONNE CTED. SWITCH FUNCTION INOPERATIVE. WHEN WIRES CORRECTLY CONNECTED TO SWITCH, FUNCTION RESTARTED. FLAG/SPADE CONNECTIN G EXTREMELY LOOSE, FELL OFF AT SLIGHTEST FORCE. WHEN CONNECTED, SWITCH DOES NOT ACTIVATED GEAR WARNING LIGHT UNTIL THRO TTLE IS PULLED HARD TO POST IDLE. (POOR WIRE CONNECTING, MISWIRED, AND MISRIGGED SWITCH. 1 L 7 1 3O 3 O NC A766 E1CE 2001062800013 20010628 00013 CE 2001 6 28 20010606CW001 1 20010517 G 2701 05600145 YOKE CESSNA 172 172P 2072436 CE COCKPIT CORRODED B R2JR K NONE O OTHER IN INSP/MAINT 1 EA 21 62258 8300 17275236 WHILE PERFORMING ANNUAL INSPECTION AND SB, FOUND ELEVATOR CONTROL YOKE CONTAINED RUSTY WATER, CAUSING EXCESSIVE CORROSIO N. IF THIS PART FAILS COMPLETE LOSS OF ELEVATOR CONTROL RESULTS. SB PERMITS DRILLING HOLE FOR RECURRING INSPECTION. S UGGEST SB SEB-01-3 BE MADE AN AD NOTE. 1 H 7 1 3O NT 3A12 2001062800014 20010628 00014 EA 2001 6 28 20010606CW002 2 20010515 G 8530 AL75089 PISTON RING CESSNA 172 172RG 2072438 CE LYC O360 O360* 41514 EA NR 3 CYLINDER BROKEN D K NONE O OTHER IN INSP/MAINT 1 EA 25 9746B 1110 172RG1009 AIRCRAFT WAS CONSUMING A LARGE QUANTITY OF OIL. UPON INSPECTION FOUND THE NR 3 CYLINDER OIL CONTROL RING LAND ELONGATED DUE TO A SMALL PIECE OF RING WHICH HAD BROKEN OFF AND BEGAN TO FLUTTER. PROBABLE CAUSE OF SHOCK COOLING. 1 H 7 1 3O 3 O 3A17 E286 2001062800015 20010628 00015 SO 2001 6 28 20010606CW003 1 20010412 G 5711 6405506 SPAR PIPER PA25 PA25235 7102504 SO LT WING CORRODED D K NONE O OTHER IN INSP/MAINT 1 CE 09 7031Z 252791 WING WAS BEING DISASSEMBLED FOR RIB REPLACEMENT. REINFORCEMENT PLATE WAS DRILLED OFF AND CORROSION FOUND ON AFT FACE OF SPAR WEB AND FACE OF REINFORCEMENT PLATE. CAUSE: MOISTURE WICKING BETWEEN PLATES AND LACK OF CORROSION PROTECTION. 1 L 7 1 3O 2A10 2001062800016 20010628 00016 SO 2001 6 28 20010606CW004 1 20010412 G 5720 6418800 DOUBLER PIPER PA25 PA25235 7102504 SO LT WING CORRODED D K NONE O OTHER IN INSP/MAINT 1 CE 09 7031Z 252791 WING WAS BEING DISASSEMBLED FOR RIB REPLACEMENT. REINFORCEMENT PLATE WAS DRILLED OFF AND CORROSION FOUND ON AFT FACE OF SPAR WEB AND FACE OF REINFORCEMENT PLATE. CAUSE: MOISTURE WICKING BETWEEN PLATES AND LACK OF CORROSION PROTECTION. 1 L 7 1 3O 2A10 2001071600007 20010716 00007 2001 7 16 20010608CW004 4 20010430 G 2210 AC66375 HOUSING SERVO CRACKED H QH5R K NONE O OTHER IN INSP/MAINT 1 NM 07 CRACKS IN SERVO BODY. 2001071600008 20010716 00008 2001 7 16 20010608CW005 4 20010430 G 2210 AS67244 HOUSING SERVO CRACKED H QH5R K NONE O OTHER IN INSP/MAINT 1 NM 07 CRACKS IN SERVO BODY. 2001071600009 20010716 00009 2001 7 16 20010608CW006 4 20010425 G 2210 AS66375 HOUSING SERVO CRACKED H QH5R K NONE O OTHER IN INSP/MAINT 1 NM 07 CRACK IN SERVO BODY. 2001071600010 20010716 00010 CE 2001 7 16 20010612CW001 1 20010403 G 7603 THROTTLE CABLE CESSNA 172 172M 2072418 CE ENGINE FAILED D TG3R K NONE O OTHER IN INSP/MAINT 1 NM 01 7603 3857 17267200 AFTER REMOVING ENGINE COWLING, INSP ENG CONTROLS, DISCOVERED THROTTLE CABLE HAD FAILED, DUE TO AGE. DESIGN IS SUCH THA T OUTER HOUSING, WHICH IS CONSTRUCTED OF PLASTIC, HAD DEVELOPED SMALL CRACKS. CRACKS WERE VISIBLE IN AREAS AFT OF POI NT OF FAILURE IN SECTION OF CABLE FORWARD OF THE FIREWALL. AT THE POINT IN THE CABLE THAT HAS A SWEDGED FITTING OVER T HE OUTER HOUSING INTENDED TO SECURE CABLE TO THE BRACKET THAT MOUNTS TO ENGINE, THE OUTER HOUSING PLASTIC HAD CRACKED TO THE POINT THAT PIECES FELL OUT OF THE SWEDGED FITTING. CLAMP HAD LOST ITS TENSION ON OUTER HOUSING AND ANY MOVEMENT OF THE THROTTLE CONTROL WOULD CAUSE THE OUTER HOUSING TO MOVE INSTEAD OF CARBURETOR CONTROL ARM. 1 H 7 1 3O NT 3A12 2001071600011 20010716 00011 NE 2001 7 16 20010612CW002 2 20010508 G 7250 2A0851 SEAL IAE V2500 V2500A1 NE NR4 BEARING CRACKED B KB1R K NONE O OTHER IN INSP/MAINT 1 NE 03 PART REJECTED A F.P. I. FOR LINEAR INDICATIONS ON BOSSES. 4 F E311NE 2001071600013 20010716 00013 2001 7 16 20010612CW004 4 20010507 G 2561 AV2A LIFE VEST CABIN FAILED B KQ1R K NONE O OTHER IN INSP/MAINT 1 EA 07 LIFE VEST FAILED. 2001071600014 20010716 00014 2001 7 16 20010612CW005 4 20010507 G 2561 KSE35L8 LIFE VEST CABIN FAILED B KQ1R K NONE L NO TEST IN INSP/MAINT 1 EA 07 LIFE VEST FAILED. 2001071600022 20010716 00022 CE 2001 7 16 20010612CW013 1 20010524 G 7603 12B57 THROTTLE ARM CESSNA 172 172N 2072434 CE LYC O320 O320H2AD 41508 EA COCKPIT CRACKED D K NONE O OTHER IN INSP/MAINT 1 SW 07 5302E 410 17271828 L812076T THROTTLE ARM FOUND CRACKED DURING 100 HOUR INSPECTION, FIRST APPEARED TO BE CASTING FLASH. PART REMOVED, DYE CHECKED AN D VERIFIED CRACKED. 1 H 7 1 3O 3 O NT 3A12 E274 2001071600023 20010716 00023 CE 2001 7 16 20010612CW014 1 20010501 G 3232 12810013 ACTUATOR CESSNA 172 172RG 2072438 CE MLG CRACKED D K NONE O OTHER IN INSP/MAINT 1 WP 09 6291R 8861 172RG0151 DURING INSPECTION, FOUND THE NECK OF ACTUATOR HOUSING BODY CRACKED .7500 WAY AROUND. ROLLER FOR INTERNAL PISTON ARM AND GEAR WAS SLIDING OUT. GEAR WAS PERFORMING NORMAL AT TIME FOUND(100 HOUR INSPECTION). 1 H 7 1 3O 3A17 2001071600024 20010716 00024 EA 2001 7 16 20010612CW015 2 20010515 G 8530 AL75089 RING CESSNA 172 172RG 2072438 CE LYC O360 O360F1A6 41514 EA NR 3 CYLINDER WORN D K NONE O OTHER IN INSP/MAINT 1 EA 25 9746B 1110 172RG1009 L2988836A AIRCRAFT WAS CONSUMING A LARGE QUANTITY OF OIL. UPON INSPECTION, FOUND THE NR 3 CYL OIL CONTROL RING LAND ELONGATED DUE TO A SMALL PIECE OF RING WHICH HAD PIECE OF RING WHICH HAD BROKEN OFF AND BEGAN TO FLUTTER. PROBABLE CAUSE: SHOCK COOL ING. 1 H 7 1 3O 3 O 3A17 E286 2001071600026 20010716 00026 CE 2001 7 16 20010612CW017 1 20010511 G 3240 0411549 BRACKET CESSNA 206 TU206G 2073357 CE LT MLG BROKEN D O OTHER O OTHER TX TAXI/GRND HDL 1 SO 01 206TT 3359 020605283 PILOT LOST LEFT BRAKE DURING TAXI. INSPECTION REVEALED MASTER CYLINDER LOWER ATTACH BRACKETS BROKEN. 1 H 7 1 3O A4CE 2001071600027 20010716 00027 CE 2001 7 16 20010612CW018 1 20010511 G 3240 0411550 BRACKET CESSNA 206 TU206G 2073357 CE LT MLG BROKEN D O OTHER O OTHER TX TAXI/GRND HDL 1 SO 01 206TT U20605283 PILOT LOST LEFT BRAKE DURING TAXI. INSPECTION REVEALED MASTER CYLINDER LOWER ATTACH BRACKETS BROKEN. INSPECTION OF OTH ER AIRCRAFT FOUND SAME PARTS BENT. 1 H 7 1 3O A4CE 2001071600029 20010716 00029 CE 2001 7 16 20010613CW002 1 20010526 G 2750 98600581 CONTROL CABLE CESSNA 210 T210L 2073449 CE T/E FLAP SLIPPED D K NONE F FLT CONT AFFECTED IN INSP/MAINT 1 CE 05 93344 21060371 DURING 100 HR INSPECTION, FOUND FLAPS NOT WORKING PROPERLY, FOUND CONTROL PUSH/PULL CABLE OUTER HOUSING WHERE HOUSING IS CLAMPED, SLIPPING IN CLAMP BUSHING. ORDER NEW CABLE FROM CESSNA, IT WAS TOO SHORT, CALLED CESSNA AND FOUND THEIR STOCK WAS MANUFACTURED WRONG. CESSNA HAD A NEW CABLE MADE. INSTALLED NEW CABLE. OPS CHECKED. NEW CABLE WAS BINDING, CAUSI NG WING RIB TO FLEX AND STRETCHED CABLE HOUSING. 1 H 7 1 3O 3A21 2001071700035 20010717 00035 SW 2001 7 17 20010613CW006 1 20010526 G 3020 189502 ARM BBAVIA 7 7GCBC 1220601 SW CARBURETOR HEAT WORN G K NONE O OTHER IN INSP/MAINT 1 CE 05 7650S 652 92876 AN4 BOLT ACTS AS TERMINAL END OF CARBURETOR HEAT CABLE AND IS FREE TO ROTATE IN HOLE DRILLED NEAR END OF SHAFT ASSY ARM OF CARB HEAT BUTTERFLY VALVE IN CARB AIR INTAKE BOX. FORE AND AFT MOVEMENT, RESULTING FROM CARB HEAT APP. HAS ELONGATED HOLE IN ARM AND CUT BOLT APPROX .7500 THRU ITS DIAMETER, ALLOWING APPROX .3125 FREE TRAVEL OF ARM AND FREE VERT DISPLAC EMENT OF CARB HEAT BUTTERFLY VALVE FROM FULLY CLOSED TO APPROX .5000 OPEN. REPAIR ACCOMPLISHED BY REAMING OUT HOLE ON A RM TO ACCEPT BUSHING TO RETAIN AN4 BOLT OR TO ACCEPT AN5 BOLT. THEREBY EXPANDING SURFACE BRG CONTACT BETWEEN ARM AND BO LT. FUTURE WEAR CAN BE MINIMIZED BY CONTINUED ATTENTION TO LUBRICATION OF BOLT. 1 H 7 1 3O NC A759 2001071600032 20010716 00032 CE 2001 7 16 20010613CW008 1 20010525 G 3233 12810003 ACTUATOR CESSNA 172 172RG 2072438 CE MLG CRACKED B K NONE O OTHER IN INSP/MAINT 1 SO 13 646B 172RG1116 FOUND ONE ACTUATOR CRACKED. 1 H 7 1 3O 3A17 2001071600033 20010716 00033 CE 2001 7 16 20010613CW009 1 20010525 G 3233 12810003 ACTUATOR CESSNA 172 172RG 2072438 CE MLG CRACKED B K NONE O OTHER IN INSP/MAINT 1 SO 13 9654B 172RG0947 FOUND ONE ACTUATOR CRACKED. 1 H 7 1 3O 3A17 2001072500070 20010725 00070 NE 2001 7 25 20010613CW010 2 20010601 G 7261 AS3209013 O-RING PWA PT6 PT6A67D NE ENGINE BROKEN F MASR K NONE O OTHER IN INSP/MAINT 1 SW 01 PART WAS REMOVED NEW FROM FLOOR STOCK. WHEN O-RING WAS REMOVED FROM SEALED PACKAGE IT WAS FOUND TO BE BRITTLE AND BROKE N INTO 4 PIECES. SEVERAL OTHER O-RINGS WERE CHECKED AND ALL WERE FOUND TO BE SERVICEABLE. 4 T E26NE 2001071600034 20010716 00034 NE 2001 7 16 20010613CW011 2 20010530 G 7250 3028601 BLADE PWA JT15 JT15D4 52112 NE ENGINE SEPARATED B O OTHER O OTHER NR NOT REPORTED 1 SW 15 61MA PCE70547 BACKGROUND: PCE 70547 SUSTAINED TYPICAL BLADE SEPARATION AND RESULTED DOWN STREAM DAMAGE. THE 3028601 BLADE HAS A 3500 HOUR TIME LIMIT ON THE JT15D-4 ENGINE. THE SEPARATION OCCURS APPROX 1800 HOURS OF OPERATION DEPENDING ON ENGINE OPERAT ION. INSP OF BLADES REVEALED AN AVERAGE GROWTH OF.007. 4 F E1NE 2001071600035 20010716 00035 NE 2001 7 16 20010613CW012 2 20010530 G 7250 3028601 BLADE PWA JD15 JT15D1A NE ENGINE SEPARATED B IY2R O OTHER O OTHER NR NOT REPORTED 1 SW 15 511AT 2717 PCE76579 BACKGROUND: THE 3028601 TURBINE BLADE INSTALLED ON THE JT15D-1A ENGINE HAVE A 3500 HOUR LIFE LIMIT. THIS TURBINE BLADE TENDS TO CRACK AT THE AIRFOIL AND BREAK CAUSING EXTENSIVE DOWNSTREAM FAILURE/DAMAGE. THE BLADE WILL TYPICALLY GROW IN EXCESS OF .007 INCH AND BREAK. THIS USUALLY HAPPENS BETWEEN THE 1800-3000 HOUR MARK, DEPENDING ON ENGINE OPERATION. 4 F E25EA 2001071600046 20010716 00046 CE 2001 7 16 20010613CW023 1 20010509 G 5711 SPAR CESSNA 177 177RG 2073709 CE WING CORRODED B T9ZR K NONE O OTHER IN INSP/MAINT 1 NM 09 52472 177R61196 DURING THE INSTALLATION OF SHOULDER HARNESS KITS THE HEAD LINER WAS REMOVED. CORROSION WAS PRESENT AT FORE AND AFT UPPE R, SPAR CAPS AND SKINS. OWNER WAS ADVISED. FURTHER INSPECTION FOUND CORROSION PRESENT UNDER LEAD SHEETS IN THE SAME AR EA. LEFT AND RIGHT ROOT RIB ASSEMBLIES ALSO HAD CORROSION PRESENT AS WELL AS A CRACK IN THE LEFT HAND ROOT RIB. PROPER INSPECTION PROCEDURE SHOULD HAVE CAUGHT THIS PRIOR TO REACHING THIS STAGE OF CORROSION. 1 H 7 1 3O A20CE 2001042400287 20010424 00287 CE 2001 4 24 2001085 1 20010419 G 2720 CONTROL UNIT BEECH 1900 1900D 1154162 CE RUDDER MALFUNCTIONED A GLBA A UNSCHED LANDING F FLT CONT AFFECTED CL CLIMB 1 CE 01 257GL UE257 UNCOMMANDED RUDDER BOOST IN FLIGHT, PENDING CORRECTIVE ACTION 2 L 7 2 4T RT A24CE 2002012400099 20020124 00099 CE 2002 1 24 2001112329 1 20011126 G 2910 465588001045 LINE RKWELL NA265 NA26565 7630107 CE HYD SYSTEM CRACKED B K NONE K FLUID LOSS IN INSP/MAINT 1 CE 01 6NR 4655 46529 MAINTENANCE PERSONNEL NOTICED FLUID LEAKAGE FROM BELLY PANEL AFT OF LANDING GEAR FOLLOWING PILOT'S COMPLETION OF "SPOILE R AUTO EXTEND" PREFLIGHT CHECK BY FLIGHT CREW. VISUAL INSPECTION DETERMINED SPOILER AUTO EXTEND LINE ASSEMBLY TO BE LEA KING PAST B-NUT AND SLEEVE WHERE IT CONNECTS TO SPOILER CONTROL DUMP VALVE. DEFECT WAS CRACK AT LIP OF DOUBLE FLARE. M OST PROBABLE CAUSE IS SUDDEN SHOCK FROM AUTO EXTEND ACTIONS AT LANDING AND DURING PREFLIGHT CHECKS. 2 L 7 2 4J A2WE 2001073000303 20010730 00303 EU 2001 7 30 2001F00015 2 20010605 G 7310 1159P20106 FUEL LINE GULSTM G1159 G1159 3953505 SO RROYCE SPEY SPEY5118 54523 EU RT ENGINE RUPTURED C O OTHER R PARTIAL RPM/PWR LOSS TO TAKEOFF 1 EA 09 80AG 164 RIGHT MAIN FUEL LINE RUPTURED ON TAKEOFF WHICH CAUSED ENGINE TO SPOOL DOWN TO FLIGHT IDLE. REPLACED FUEL LINE ON ENGINE . HP FUEL PUMP WAS ALSO DAMAGED AND REPLACED. ENGINE WAS BORESCOPED AND RETURNED TO SERVICE. 2 L 7 2 4F 4 F RT A12EA E2EU 2001071700036 20010717 00036 SO 2001 7 17 2001F00037 2 20010505 G 8520 SNAP RING CONT CESSNA 185 A185F 2072821 CE CONT O550 IO550* SO CRANKSHAFT MISSING D E ENGINE SHUTDOWN O OTHER IN INSP/MAINT 1 AL 05 18118 850 284276R 18503328 3-26-01 REMOVED NO. 1 AND 3 CYLINDERS TO COMPLY WITH CRANKSHAFT COUNTER WEIGHT AD. FACTORY TECH REP REMOVED AND INSPECT ED COUNTER WEIGHT AMOUNTING FLANGES (4), REPLACED COUNTER WEIGHTS AND ASSOCIATED PARTS, AND CYLINDERS AND ASSOCIATED PAR TS, 50 ENGINE HOURS LATER AFT COUNTER WEIGHT PIN FELL OUT DURING START UP. ENGINE DAMAGED SUBSTANTIAL. ENGINE REMOVED AND REPLACED. 1 H 7 1 3O 3 O 3A24 E3SO 2001071800128 20010718 00128 CE 2001 7 18 2001F00046 1 20010430 G 5751 65241263 SKIN CESSNA 500 550 2076604 CE AILERON CRACKED B K NONE O OTHER IN INSP/MAINT 1 SW 01 26621 7855 5500593 DURING A SCHEDULED PHASE INSPECTION THE LEFT AILERON WAS REMOVED. UPON REMOVAL THE LEADING EDGE SKIN AT THE WEIGHT ATTA CHMENT SCREWS WAS FOUND CRACKED. THIS HAD ALLOWED THE SKIN TO CRACK ABOVE AND BELOW A SCREW APPROX. .5000. THE RIGHT A ILERON WAS ALSO REMOVED AND TWO OF THESE LEADING EDGE WEIGHT SCREWS WERE ALSO FOUND LOOSE. 1 L 7 2 4F A22CE 2001080200261 20010802 00261 SO 2001 8 2 2001F00048 1 20010106 G 7120 8401002 MOUNT PIPER PA46 PA46310P 7104605 SO ENGINE DAMAGED C K NONE O OTHER IN INSP/MAINT 1 GL 19 25120 3890 468508097 FOUND ENGINE CONTROL CABLES CHAFFING ON THE ENGINE MOUNT DURING ENGINE CHANGE. DAMAGE WAS FOUND TO BE BEYOND LIMITS. S ENT MOUNT FOR REPAIR. ENGINE MOUNT WAS FOUND TO HAVE 6 CRACKS AND CORROSION BEYOND LIMITS . 1 L 7 1 3O RT A25SO 2001073000304 20010730 00304 SO 2001 7 30 2001F00062 2 20010202 G 8520 DRIVE GEAR BEECH 36 A36 1151604 CE CONT O520 IO520BA 17032 SO ENGINE FAILED A O OTHER O OTHER NR NOT REPORTED 1 CE 07 4456W 300 300 E537 122716R ENG HAD STARTER DRIVE FAILURE. INVESTIGATION, STARTER DRIVE HAD BEEN SWITCHED 5 TIMES IN 300 HRS. FOUND OIL GALLEY TO S TARTER DRIVE PLUGGED. SPLIT CRANKCASE, FOUND OIL GALLEY FROM REAR CAMSHAFT BRG SURFACE TO STARTER DRIVE BRG PLUGGED. THE PLUG WAS NOT IN PIECES BUT 1 SOLID PIECE OF SILICONE FROM JOURNAL TO STARTER DRIVE BRG. NO OTHER SILICONE WAS FOUN D IN ENGINE. SILICONE APPEARS TO HAVE BEEN ACTUALLY INJECTED INTO OIL GALLEY, PRIOR TO ENGINE ASSEMBLY. PREVIOUS OVERH AUL: ENG O/H 8 YEARS(300 HRS) AGO BY LOG BOOK AND STICKER. ALL BEARING SURFACES IN ENG DESTROYED, INCLUDING CRANKCASE A ND OIL PUMP. ENG OIL FILTER, SMALL AMT OF ALUMINUM. FOUND LG AMTS OF STEEL IN OIL SUMP FROM FAILED STARTER DRIVE. 1 L 7 1 3O 3 O 3A15 E5CE 2001071600057 20010716 00057 CE 2001 7 16 2001F00063 1 20010319 G 3310 76080241 OVERLAY LEAR 35 31A 5170531 CE COCKPIT CRACKED C A UNSCHED LANDING B SMOKE/FUMES/ODORS/SPARKS CR CRUISE 1 EA 03 70AE 707 188 DURING FLIGHT, PILOT OBSERVED SMOKE COMING FROM THE ENGINE INSTRUMENT PANEL LEFT ITT INDICATOR. PILOT DECLARED EMERGENC Y AND LANDED. INVESTIGATION REVEALED THAT THE LIGHTING OVERLAY HAD CRACKED AND WAS ARCING AT THE CRACK. NO ARCING TO T HE LOCAL STRUCTURE WAS FOUND. IT WAS DETERMINED THAT THE ENGINE INSTRUMENTS WERE NOT FLUSH WITH THE INSTRUMENT PANEL. ALLOWING A DEFLECTION IN THE OVERLAY. FURTHER INSPECTION FOUND MOST ALL OF THE ENGINE INSTRUMENT MOUNTING BRACKETS TO B E BENT AND BROKEN, POSSIBLY FROM OVER TIGHTENING. 2 L 7 2 4F RT A10CE 2001071600058 20010716 00058 2001 7 16 2001F00067 4 20010419 G 2562 AK450 ELT CESSNA 206 U206G 2073356 CE TAIL DEFECTIVE C K NONE O OTHER IN INSP/MAINT 1 WP 07 2PS 86 U20606916 ELT UNIT WEAK UPON TEST. REMOVED AND REPLACED BATTERIES (OLD WERE MISMATCHED) W/NEW, NO IMPROVEMENT. OUR GOVERNMENT R ADIO SHOP CHECKED UNIT. 1) FOUND DISSIMILAR METALS ON SOLDERING JOINTS(IE STEEL/SOLDER) 2) UNIT WAY OFF FREQUENCY. 1 H 7 1 3O A4CE 2001071700037 20010717 00037 2001 7 17 2001F00068 4 20010427 G 3418 SL29849147173 VANE LEAR 25 25B 5170511 CE STALL WARNING MALFUNCTIONED D K NONE O OTHER NR NOT REPORTED 1 GL 25 731CW 117 DOC HOWARD MACH II STC SYSTEM. AFTER A SCHEDULED 300 HOUR INSPECTION, AIRCRAFT WAS TEST FLOWN, FINDING AOA SYSTEM INOPE RATIVE. SYSTEM WAS TROUBLESHOT, FOUND TO BE SATISFACTORY ON GROUND. IN FLIGHT AOA REMAIN STEADY, NO STALL WARNING, PU SH/PULLER FUNCTIONING WHILE EXPERIENCING WING AND TAIL BUFFET. SAFETY RECOMMENDATION INITIATED. 2 L 7 2 4J A10CE 2001071600060 20010716 00060 CE 2001 7 16 2001F00070 1 20010516 G 5310 241127657 DOOR FRAME LEAR 35 35A 5170602 CE FUSELAGE CRACKED D K NONE O OTHER IN INSP/MAINT 1 EA 17 701DA 35A180 DURING ROUTINE INSPECTION FORWARD DOOR JAMB WAS FOUND CRACKS THE WIDTH OF THE DOOR JAMB IN LINE WITH THE HINGE SEAM. FU RTHER DISASSEMBLY FOUND ADDITIONAL CRACKS ON THE FORMED STEP RISER, DIRECTLY BELOW THE DOOR JAMB BETWEEN THE JAMB AND TH E DOOR SKIN. 2 L 7 2 4F A10CE 2001071700039 20010717 00039 EU 2001 7 17 2001F00071 1 20010524 G 3240 5713001501 CONTROL HANDLE ISRAEL 1124 1124 4500102 EU COCKPIT BROKEN D K NONE O OTHER NR NOT REPORTED 1 EA 03 351C 3000 264 PARKING BRAKE LEVER FELL OFF OF THE BRAKE CONTROL VALVE CAUSING THE PARKING BRAKE PORTION OF THE BRAKE CONTROL VALVE TO SPRING TO THE PARKING BRAKE POSITION LOCKING THE BRAKES. MAKING THE AIRCRAFT UNABLE TO MOVE. 2 M 7 2 4F A2SW 2001072500618 20010725 00618 EU 2001 7 25 2001F00091 1 20010601 G 2930 EVP310 VALVE UROCOP EC120 EC120B 8680987 EU HYD SERVO DEFECTIVE H O OTHER N FALSE WARNING TX TAXI/GRND HDL 1 WP 25 255SD 395 1102 DURING NORMAL RUNUP PROCEDURES, THE HYDRAULICS ARE SWITCHED OFF AS PART OF THE SYSTEM CHECK. UPON ACTIVATING THE HYDRAU LIC SWITCH ON THE COLLECTOR THE HYDRAULIC LIGHT ILLUMINATES BUT THE CONTROLS STILL HAD HYDRAULIC BOOST SUPPLIED BY THE A CCUMULATOR. THIS SHOULD NOT HAPPEN. ALL 3 SERVO ELECTROVALVES WERE REPLACED WHICH FIXED THE PROBLEM FOR 5 HOURS, THEN IT MALFUNCTIONED AGAIN. THE HYD POWER PACK WAS REPLACED FOR ANOTHER MAINTENANCE PROBLEM AND THAT ALSO RESOLVED THIS MAL FUNCTIONED. 1 G 7 2 3U NC R0001RD 2001072500620 20010725 00620 EU 2001 7 25 2001F00092 1 20010601 G 2930 EVP310 VALVE UROCOP EC120 EC120B 8680987 EU HYDRAULIC SERVO DEFECTIVE H O OTHER J WARNING INDICATION TX TAXI/GRND HDL 1 WP 25 255SD 395 1102 DURING NORMAL RUNUP PROCEDURES, THE HYDRAULICS ARE SWITCHED OFF AS PART OF THE SYSTEM CHECK. UPON ACTIVATING THE HYDRAU LIC SWITCH ON THE COLLECTOR THE HYD LIGHT ILLUMINATES BUT THE CONTROLS STILL HAD HYDRAULIC BOOST SUPPLIED BY THE ACCUMUL ATOR. THIS SHOULD NOT HAPPEN. ALL 3 SERVO ELECTROVALVES WERE REPLACED WHICH FIXED THE PROBLEM FOR 5 HOURS, THEN IT MAL FUNCTIONED AGAIN THE HYDRAULIC POWER PACK WAS REPLACED FOR ANOTHER MAINTENANCE PROBLEM AND THAT ALSO RESOLVED THIS MALFU NCTION. 1 G 7 2 3U NC R0001RD 2001071700040 20010717 00040 EU 2001 7 17 2001F00093 1 20010601 G 2913 EVP310 POWERPACK UROCOP EC120 EC120B 8680987 EU HYDRAULIC SYS MALFUNCTIONED C K NONE J WARNING INDICATION TX TAXI/GRND HDL 1 WP 25 255SD 395 1102 DURING NORMAL RUNUP PROCEDURES, THE HYDRAULICS ARE SWITCHED OFF AS PART OF THE SYSTEM CHECK. UPON ACTIVATING THE HYDRAU LIC SWITCH ON THE COLLECTOR THE HYDRAULIC LIGHT ILLUMINATES BUT THE CONTROLS STILL HAD HYDRAULIC BOOST SUPPLIED BY THE A CCUMULATOR. THIS SHOULD NOT HAPPEN. ALL 3 SERVO ELECTROVALVES WERE REPLACED WHICH FIXED THE PROBLEM FOR 5 HOURS, THEN IT MALFUNCTIONED AGAIN. THE HYDRAULIC POWER PACK WAS REPLACED FOR ANOTHER MAINTENANCE PROBLEM AND THAT ALSO RESOLVED TH IS MALFUNCTION. 1 G 7 2 3U NC R0001RD 2001072500622 20010725 00622 EU 2001 7 25 2001F00094 1 20010601 G 2930 GHC1004 POWERPACK UROCOP EC120 EC120B 8680987 EU HYD SYSTEM DEFECTIVE H O OTHER J WARNING INDICATION TX TAXI/GRND HDL 1 WP 25 255SD 400 1102 AFTER STARTING THE HELICOPTER THE CYELIC STICK FELT STIFF AND SLUGGISH WHEN MOVED IN ANY DIRECTION. AFTER RUNNING FOR S EVERAL MINUTES THE CONTROLS FELT BETTER BUT NOT NORMAL AFTER REPLACING THE HYDRAULIC POWER PACK THE PROBLEM WEN AWAY. T HE FILTER WAS REMOVED AND WHAT APPEARED TO BE VERY FINE METALLIC PARTICLES WERE PRESENT IN THE HYDRAULIC FLUID. 1 G 7 2 3U NC R0001RD 2001080200262 20010802 00262 SO 2001 8 2 2001F00097 1 20010627 G 3222 4533307 STRUT PIPER PIPER PA31T PA31T1 7103126 SO NLG LOOSE B K NONE O OTHER IN INSP/MAINT 1 GL 19 819SW 31T8104059 INCIDENT HAPPENED DUE TO NOSE GEAR STEERING ARM PN 4438600 ON TOP OF NOSE STRUT HOUSING, BECOMING LOOSE DUE TO ATTACHMEN T BOLTS FOR ARM BECOME LOOSE AND SHEARED OFF. AS A RESULT STEERING WAS MINIMAL AND UNCONTROLLABLE ON LANDING. 1 L 7 2 3T A8EA 2001072700003 20010727 00003 EA 2001 7 27 2001F00104 1 20010710 G 6310 NAS12254N BOLT SCWZER 269 269D 8059501 EA DRIVESHAFT LOOSE D R AUTOROTATION I F J FLT. ATTITUDE INST. FLT CONT AFFECTED WARNING INDICATION HO HOVERING 1 SW 17 296RL 0020 DURING PRACTICE AUTOROTATION, ENGINE POWERSHAFT TO KFLEX POWERTRAIN ADAPTER CAME LOOSE BY BACKING OUT, DURING OPERATION MAIN ROTOR WAS NO LONGER POWERED BY ENGINE. BOLT PIN NAS1225-4N IS A BOLT WITH A SMALL CIRCLE OF PLASTIC ON THREADS FOR LOCKING. EMERGENCY LANDING, NO DAMAGE. 1 G 7 1 3U 0 4H12 2001071700041 20010717 00041 NE 2001 7 17 2001F00108 2 20010612 G 8530 116734 CYLINDER DOUG DC3 DC3ASC3G 3021436 WP PWA R1830 R1830* 52020 NE ENGINE CRACKED G K NONE O OTHER IN INSP/MAINT 1 SW 17 12BA 79 10035 NR 13 CYLINDER BARREL CRACKED ALL THE WAY AROUND WHERE HEAD IS THREADED ONTO BARREL. CRACK BROKE COMPRESSION RINGS RESU LTING IN LOSS OF COMPRESSION. 2 L 7 2 4R 4 R A669 5E4 2001071700042 20010717 00042 CE 2001 7 17 2001F00109 1 20010620 G 5744 51155496 BRACKET CESSNA CESSNA 402 402C 207590R CE AILERON CRACKED D K NONE O OTHER IN INSP/MAINT 1 SW 01 57PB 402C0300 CRACKED AT AILERON YOLK ATTACH POINTS. 1 L 7 2 3O A7CE 2001071700044 20010717 00044 CE 2001 7 17 2001F00111 1 20010625 G 2510 SPRING AMSAFTYEQUIP CESSNA 182 182Q 2072732 CE HARNESS BROKEN C K NONE O OTHER NR NOT REPORTED 1 WP 23 4603N 2 6262 18267280 AIRCREW SQUAWKED COPILOT INERTIA REEL HARNESS LOCKED UP AND WOULD NOT RELEASE. AMT DETERMINED COIL SPRING WITHIN INERTI A REEL HOUSING HAD BROKEN LOOSE FROM ITS INSTALLED POSITION AND JAMMED THE ROLLER. DATE STAMP FOR THE INERTIA REEL ASSE MBLY WAS 0401(APR 01). BOTH PILOT AND COPILOT INERTIA REELS WERE INSTALLED ON THIS AIRCRAFT 1 JUNE 01. COPILOT HARNESS LOCKED UP ON 7 JUNE O1. ASSEMBLY WAS RETURNED TO MFG FOR REWORK, 21 JUNE 01. 1 H 7 1 3O NT 3A13 2001080100146 20010801 00146 EA 2001 8 1 2001F00113 2 20010605 G 8520 76148 CAMSHAFT PIPER PA31 PA31350 7103110 SO LYC O540 TIO540J2BD 41532 EA ENGINE CHIPPED C K NONE O OTHER IN INSP/MAINT 1 AL 05 555FS 1627 317952046 L861561A WHEN REMOVING NR 3 CYLINDER DUE TO LOW COMPRESSION, IT WAS NOTICED THAT THE LOBE ON THE CAMSHAFT FOR THE NR 3 INTAKE WAS CHIPPED. PEELING THE FACE OF THE INTAKE BODY WHICH RIDES ON THE LOBE REVEALED THAT IT ALSO WAS CHIPPED. BOTH OIL AND FILTER WERE CHANGED REGULARLY AT 50 HOURS. OBVIOUSLY ONE OF THE PARTS WAS OR BECAME CHIPPED AND CAUSED THE OTHER TO FAI L. 1 L 7 2 3O 3 O A20SO E14EA 2001071700046 20010717 00046 EA 2001 7 17 2001F00114 2 20010605 G 8520 72877 CAMSHAFT PIPER PA31 PA31350 7103110 SO LYC O540 TIO540J2BD 41532 EA ENGINE CHIPPED C K NONE O OTHER IN INSP/MAINT 1 AL 05 555FS 1627 317952046 L861561A WHEN REMOVING NR 3 CYLINDER DUE TO LOW COMPRESSION, IT WAS NOTICED THAT THE LOBE ON THE CAMSHAFT FOR THE NR 3 INTAKE WAS CHIPPED. PEELING THE FACE OF THE INTAKE BODY WHICH RIDES ON THE LOBE REVEALED THAT IT ALSO WAS CHIPPED. BOTH OIL AND FILTER WERE CHANGED REGULARLY AT 50 HOURS. OBVIOUSLY ONE OF THE PARTS WAS OR BECAME CHIPPED AND CAUSED THE OTHER TO FAI L. 1 L 7 2 3O 3 O A20SO E14EA 2001080100148 20010801 00148 NE 2001 8 1 2001F00118 3 20010702 G 6110 E3932 HUB BEECH 1900 1900D 1154162 CE PWA PT6 PT6* 52043 EA HARTZL HCE4A HCE4A3I NE BRG RETENTION SCORED B K NONE O OTHER IN INSP/MAINT 1 SO 17 49543 10465 3463 UE181 HJ440 PROPELLER WAS RECEIVED FOR O/H WITH EXCESSIVE GREASE LEAKAGE FROM ALL BLADES. PROP WAS DISASSEMBLED TO START O/H PROCES S. WHEN HUB UNIT WAS SPLIT, THERE WAS EXCESSIVE AMOUNTS OF GREASE INSIDE. UPON FURTHER INSPECTION, THE BEARING RACE HAD SHATTERED INTO SEVERAL PIECES, SCORING THE INSIDE RETENTION AREA. REWORK WAS BEYOND ALLOWABLE LIMITS. HUB WAS RETIRED FROM SERVICE. 2 L 7 2 4T 3 T RT A24CE E2NE 5 C P10NE 2001080800317 20010808 00317 CE 2001 8 8 2001F00164 1 20010622 G 2120 973800011 DUCT BEECH 100 B100 1152919 CE GARRTT TPE331 TPE331* 01514 WP CABIN PRESSURE FAILED G K NONE O OTHER IN INSP/MAINT 1 EA 21 78DA BE11 WHILE TROUBLESHOOTING POOR CABIN PRESSURIZATION, FOUND FAILED HOSE IN LEFT ENGINE AIR SUPPLY LINE TO CABIN. THIS CAUSED PRESSURIZATION TO WORK POORLY, BECAUSE THERE WAS NO INPUT TO CABIN FROM LEFT FLOW PACK. SUSPECT DUCT FAILED DUE TO AGE . 1 L 7 2 4T 3 T A14CE E2WE 2001081000154 20010810 00154 CE 2001 8 10 2001F00165 1 20010627 G 3222 35825174 ARM BEECH 95 95 1153402 CE NLG CRACKED G O OTHER O OTHER TX TAXI/GRND HDL 1 SO 09 DURING A RECENT INVESTIGATION OF AN INCIDENT OF A BEECH 95 THAT THE NOSE GEAR COLLAPSED ON ROLL OUT AFTER LANDING. IT W AS DISCOVERED THAT THE LANDING GEAR CRANK ARM PART NUMBER 35-825174 THAT ATTACHES TO THE LANDING GEAR TRANSMISSION BOX H AD CRACKED. THE CRACKED ARM ALLOWED THE ARM TO FLEX ADN ROTATE ON THE SPLINES OF THE TRANSMISSION SHAFT WHICH KEEPS THE PUSH PULL TUBE TO THE NOSE GEAR IN THE FORWARD POSITION. THIS ARM IS ALSO INSTALLED ON SEVERAL MODELS. PROBABLE CAUSE IS FATIGUE. RECOMMEND THAT ARM BE REMOVED AT THE NEXT INSPECTION AND INSPECTED WITH 10X MAGNIFIER. (ATTACHED PHOTOS) 1 L 7 2 3O 3A16 2001082200269 20010822 00269 SW 2001 8 22 2001F00205 1 20010712 G 5711 SPAR BBAVIA 7 7AC 2110102 SW CONT A65 A65* 17003 SO WING CRACKED D K NONE O OTHER IN INSP/MAINT 1 NM 01 83233 7AC1897 SPAR CRACKED 1 H 7 1 3O 3 O A759 E205 2001090500047 20010905 00047 2001 9 5 2001F00248 4 20010716 G 3418 S16729 DETECTOR CESSNA 182 182R 2072731 CE CONT O470 O470* 17026 SO WING INOPERATIVE D O OTHER O OTHER NR NOT REPORTED 1 EA 21 35VA 18268129 UPON INSTALLING NEW LIFT DETECTION NOTED THAT WHEN WIRED AS ORIGINALLY REMOVED FROM AIRCRAFT, WITH HEAT TURNED ON, DETEC TION WAS INOPERATIVE. GROUND FOR HEATER WAS INSTALLED ON COMMON FOR DETECTION; CAUSING A NO POTENTIAL WHEN HEATER TURNE D ON. 1 L 7 1 3O 3 O NT 3A13 E273 2001080100149 20010801 00149 WP 2001 8 1 2001FA0000001 2 20010515 G 8520 8976021 CAM CESSNA 441 441 2076020 CE GARRTT TPE331 TPE331* 01514 WP ENGINE MISMANUFACTURED B WTXR K NONE O OTHER IN INSP/MAINT 1 NM 07 4441T 4410133 AFTER INSTALLING NEWLY OVERHAULED ENGINE ON AIRCRAFT, FOUND THAT THE -30 P.P.C. COULD NOT BE RIGGED. REMOVED P.O.C. AND FOUND THAT THE CAM INSIDE, ALTHOUGH MARKED CORRECTLY (P/N 897602-1), THE CAM WAS MANUFACTURED WRONG. IT HAS THE WRONG CAM PROFILE. REF: SB TPE331-72-0904. 1 L 7 2 3T 3 T RT A28CE E2WE 2001080100150 20010801 00150 WP 2001 8 1 2001FA0000002 2 20010514 G 8520 8976021 CAM CESSNA 441 441 2076020 CE GARRTT TPE331 TPE331* 01514 WP ENGINE MISMANUFACTURED B WTXR K NONE O OTHER IN INSP/MAINT 1 NM 07 4441T 4410133 P77443C AFTER INSTALLING NEWLY OVERHAULED ENGINE ON AIRCRAFT, FOUND THAT THE -30 P.P.C. COULD NOT BE RIGGED. REMOVED THE P.P.C. AND FOUND THAT THE CAM INSIDE, ALTHOUGH MARKED WITH THE CORRECT P/N (8976021) WAS MANUFACTURED WRONG. IT HAS THE WRONG CAM PROFILE. REF: SB TPE331-72-0904. 1 L 7 2 3T 3 T RT A28CE E2WE 2001071800006 20010718 00006 NM 2001 7 18 2001FA0000003 1 20010501 G 3244 26107012 TIRE DORNER DO32 DO328100 2996000 NM RT MLG DEFLATED C K NONE O OTHER IN INSP/MAINT 1 SO 11 404SS 40 3090 DURING WALKAROUND INSPECTION AFTER LANDING IN KBHM, CREW DISCOVERED ROB MAIN LANDING GEAR TIRE WAS FLAT. THE WHEEL O-RI NG WAS FOUND PROTRUDING TOWARDS THE CENTER OF THE WHEEL. EIGHT OF THE TEN WHEEL THROUGH BOLTS WERE LOOSE. THE WHEEL WA S RETURNED TO THE OVERHAULER FOR EVALUATION AND OVERHAUL. 2 H 7 2 4T RT A45NM 2001072400003 20010724 00003 EU 2001 7 24 2001FA0000008 1 20010521 G 5540 RIVET ISRAEL 1124 1124 4500102 EU RUDDER CRACKED D K NONE O OTHER IN INSP/MAINT 1 SW 99 980S 1 401 CRACKS IN DIMPLES OF RIVETS ON SKIN OF RUDDER, LOOKS LIKE THEY HAVE BEEN THERE SINCE MANUFACTURE. FABRICATING NEW RIBS PER GALAXY AEROSPACE DRAWINGS AND DOING A SPAR SPLICE PER GALAXY. SUSPECT ALL RUDDERS THAT ARE MANUFACTURED THE SAME AS THIS ONE ARE ALSO CRACKED. 2 M 7 2 4F A2SW 2001071800007 20010718 00007 EU 2001 7 18 2001FA0000009 1 20010518 G 5330 SKIN AMD FALC50 FALCON50MYST 2730106 EU FUSELAGE CORRODED G BQVA K NONE O OTHER IN INSP/MAINT 1 EA 01 50TG 6133 117 CORROSION IN AREA OF AFT FUSELAGE SKINS AT ACU EXHAUST OUTLETS. WATER ENTRAPMENT. REPAIRED UNDER BOMBARDIER REO NR 601 -53-30-278. 2 L 7 3 4F A46EU 2001080100151 20010801 00151 NM 2001 8 1 2001FA0000012 1 20010521 G 3230 108510 HOUSING BOEING 727 727 UTILSYS NM AFT MOUNT BROKEN B IU6R K NONE O OTHER IN INSP/MAINT 1 NM 01 HOUSING HAS A BROKEN AFT MOUNT. PROBABLE CAUSE: MISHANDLED 2 L 7 3 4J RT A3WE 2001080100152 20010801 00152 NM 2001 8 1 2001FA0000013 1 20010521 G 2730 401606223 HOUSING MOOG BOEING 727 727* NM SEAL PLATE SURFC CRACKED B IU6R K NONE O OTHER IN INSP/MAINT 1 NM 01 1601D HOUSING ASSEMBLY IS CRACKED ON THE SEAL PLATE SURFACE. PROBABLE CAUSE: HOUSING ASSEMBLY IS MADE FROM MAGNESIUM ALLOY A ND IS EXTREMELY SUSCEPTIBLE TO DISSIMILAR METAL CORROSION AND CRACKS. 2 L 7 3 4F RT A3WE 2001080100153 20010801 00153 NM 2001 8 1 2001FA0000014 1 20010518 G 2730 401611572 BARREL MOOG BOEING 727 727* NM BARRELL BORE CORRODED B IU6R K NONE O OTHER IN INSP/MAINT 1 NM 01 1098 BARREL ASSEMBLY HAS PITTING AND EROSION IN MAIN BORE. PROBABLE CAUSE: DISSIMILAR CORROSION. 2 L 7 3 4F RT A3WE 2001080100154 20010801 00154 NM 2001 8 1 2001FA0000015 1 20010518 G 2730 401644557 HOUSING MOOG BOEING 727 727* NM SEAL SURF, HOLES CORRODED B IU6R K NONE O OTHER IN INSP/MAINT 1 NM 01 1098 HOUSING ASSEMBLY HAS PITTING AND CORROSION IN BOLT HOLES, CAP ASSEMBLIES, PORTS AND SEALING SURFACES. PROBABLE CAUSE: DISSIMILAR CORROSION. RECOMMENDATIONS: REPLACE MAGNESIUM HOUSING ASSEMBLIES WITH ALUMINUM ALLOY. 2 L 7 3 4F RT A3WE 2001080100155 20010801 00155 NM 2001 8 1 2001FA0000016 1 20010518 G 2730 401611572 HOUSING MOOG BOEING 727 727 UTILSYS NM CK VLV PORT, LAN CORRODED B IU6R K NONE O OTHER IN INSP/MAINT 1 NM 07 1098 ELBOW HOUSING HAS SEVERE CORROSION IN BOLT HOLES, CHEDK VALVE PORT, PACKING LANDS AND ON SEALING SURFACE FACE. PROBABLE CAUSE: DISSIMILAR CORROSION. RECOMMENDATIONS: REPLACE MAGNESIUM ELBOW WITH ALUMINUM ALLOY. 2 L 7 3 4J RT A3WE 2001080100156 20010801 00156 EA 2001 8 1 2001FA0000017 2 20010516 G 8520 LW19332 CONNECTING ROD PIPER PA32 PA32300 7103212 SO LYC O540 IO540K1A5 41532 EA NR 2 CYLINDER FAILED D K NONE O OTHER IN INSP/MAINT 1 NM 02 5640M 3240295 L1774848A NR 2 PISTON WAS REMOVED, CONNECTING ROD BUSHING WAS FOUND TO HAVE MOVED TO THE POSITION AS SHOWN IN PHOTO AND ONLY STOPP ED BY CONTACTING THE INSIDE OF PISTON PIN BOSS OF THE PISTON. BUSHING SHOWED EVIDENCE OF MOVING TORSIONALLY FROM PROPER POSITION IN REF. TO SPLIT LINE BUT DID NOT SHOW AMOUNT OF WEAR ON OD, NOT TURNING IN THE ROD AS CONTINUOUS CONDITION. SLIGHT DISCOLORATION OF PORTION OF BUSHING EXTENDING BEYOND ROD BOSS INDICATING IT HAD BEEN IN THIS POSITION FOR SOME HO URS. NO EVIDENCE OF DAMAGE TO PISTON BOSS OR PISTON PIN OD AND BUSHING ID. WHEN BUSHING WAS REMOVED FROM ROD, IT FRACT URED AS IN PHOTO. CORRESPONDING FRET LINE ON ROD BOSS ID AT POINT OF BUSHING FRACTURE. (ATTACHED PHOTO) 1 L 7 1 3O 3 O A3SO 1E4 2001072500625 20010725 00625 NM 2001 7 25 2001FA0000018 1 20010518 G 6310 A1902 BELT ROBSIN R22 R22BETAII 7640110 NM ROTOR DRIVE MALFUNCTIONED D O OTHER O OTHER NR NOT REPORTED 1 SW 17 7087X 488 2829 V-BELT, (PN A190-2) OF THE R22 DRIVE SYSTEM, MALFUNCTIONED BY COMING APART AND JUMPED OFF DRIVE PULLEYS, CAUSING LOSS OF DRIVE TO ROTOR DRIVE SYSTEM. 1 G 7 1 3O H10WE 2001080100157 20010801 00157 SW 2001 8 1 2001FA0000019 1 20010601 G 5711 SPAR BBAVIA 7 7CCM 21101MW SW WING SPAR CRACKED D K NONE O OTHER IN INSP/MAINT 1 GL 15 2762E 7AC6345 CRACK ON BOTTOM SURFACE OF SPAR, LEFT SIDE REAR. (BUTT) FOUND PRIOR TO CRACK INSPECTION AS PER AD OWNER DISCONTINUED AN NUAL INSPECTION PRIOR TO FULL INSPECTION. 1 H 7 1 3O A759 2001080100158 20010801 00158 SW 2001 8 1 2001FA0000020 1 20010607 G 5720 STRUT BBAVIA 7 7CCM 21101MW SW WING STRUT DEFECTIVE D K NONE O OTHER IN INSP/MAINT 1 GL 15 2762E 7AC6345 WING STRUTS HAD FILLED WITH WATER FROM SITTING OUTSIDE. RUST STAINS VISIBLE FROM OUTSIDE OF STUT. WHEN POKED WITH AIR AWL IT PUSHED A HOLE INTO STRUT AND DRAINED WATER. DRILLED A .0312 HOLE IN BOTTOM OF OTHER 3 STRUTS AND WATER CAME OUT IN EXCESS OF 1 CUP EACH. OWNER NOTIFIED OF UNAIRWORTHY CONDITION. 1 H 7 1 3O A759 2001080100159 20010801 00159 EA 2001 8 1 2001FA0000021 2 20010524 G 8530 AEL6510212 CYLINDER PIPER PA28 PA28181 7102807 SO LYC O360 O360A4M 41514 EA CYLINDER HEAD CRACKED B MW2R K NONE O OTHER IN INSP/MAINT 1 GL 17 4350G 1379 288490058 CRACKED FROM SPARK PLUG HOLE TO EX SEAT. 1 L 7 1 3O 3 O 2A13 E286 2001080100160 20010801 00160 EA 2001 8 1 2001FA0000022 2 20010524 G 8530 AEL6510241 CYLINDER PIPER PA28 PA28161 7102803 SO LYC O360 O360A4M 41514 EA ENGINE CRACKED B MW2R K NONE O OTHER IN INSP/MAINT 1 GL 17 2366W 823 288516046 CRACKED FROM TOP OF SPARK PLUG HOLE, AROUND OUTSIDE OF EX SEAT TO BOTTOM OF SPARK PLUG HOLE. 1 L 7 1 3O 3 O 2A13 E286 2001080100161 20010801 00161 CE 2001 8 1 2001FA0000023 1 20010530 G 3213 S3461111 BOLT CESSNA 172 172S 2072439 CE LEFT STRUT MISINSTALLED B K NONE O OTHER IN INSP/MAINT 1 CE 07 784SP 172S8711 BOLTS ARE INSTALLED BACKWARDS, POINTING FORWARD. 1 H 7 1 3O NT 3A12 2001080100162 20010801 00162 CE 2001 8 1 2001FA0000024 1 20010530 G 3213 S3461116 BOLT CESSNA 172 172S 2072439 CE RIGHT STRUT MISINSTALLED B K NONE O OTHER IN INSP/MAINT 1 CE 07 784SP 172S8711 BOLTS ARE INSTALLED BACKWARDS, POINTING FORWARD. 1 H 7 1 3O NT 3A12 2001080100163 20010801 00163 CE 2001 8 1 2001FA0000025 1 20010530 G 5753 AN311A BOLT CESSNA 172 172S 2072439 CE RT FLAP MISINSTALLED B K NONE O OTHER IN INSP/MAINT 1 CE 07 784SP 172S8711 BOLTS ARE INSTALLED BACKWARDS, POINTING OUTBOARD. 1 H 7 1 3O NT 3A12 2001080100164 20010801 00164 EA 2001 8 1 2001FA0000027 2 20010429 G 8500 AN657A BOLT LYC O320 O320E2A 41508 EA PROPELLER LOOSE C O OTHER O OTHER NR NOT REPORTED 1 GL 15 26RK 124 L2383927A PROPELLER BOLTS (AN6-57A) BROKE IN FLIGHT AT CRUISE POWER (2500 RPM) AT 7500 FT. MSL. NOTICED THAT ONE BOLT WAS MISSING AND THE NUT ON ANOTHER COULD BE REMOVED BY HAND. POSSIBLE THAT TWO NUTS, (MS 20365-624) LOOSENED CAUSING VIBRATION IN P ROPELLER WHICH CAUSED BOLT FAILURE . NOTE: THAT ONLY THE TWO NUTS THAT SEEMED TO BE LOOSE, WERE REPLACED 124 HOURS BEF ORE FAILURE. ALL OTHER NUTS WERE STILL INTACT. PROPELLER SEPARATED FROM ENGINE IN FLIGHT. 3 O E274 2001080100165 20010801 00165 CE 2001 8 1 2001FA0000028 1 20010601 G 5320 365550483 GUARD BEECH 36 A36 1151604 CE PULLEY CRACKED C WC7R K NONE O OTHER IN INSP/MAINT 1 GL 15 3243B 100 E3243 THIS IS THE SECOND OCCURENCE OF THE PULLEY GUARD CRACKING. THE AIRCRAFT TOTAL TIME 703.1. ON THE FIRST OCCURENCE THE G UARD HAD A LARGE CRACK AND A PIECE MISSING. THIS OCCURENCE THE ENTIRE GUARD WAS FOUND MISSING. 1 L 7 1 3O 3A15 2001080100166 20010801 00166 EA 2001 8 1 2001FA0000030 2 20010524 G 8550 LW1568B TUBE CESSNA 150 152 2071835 CE LYC O235 O235L2C 41505 EA OIL SUMP LOOSE B K NONE O OTHER IN INSP/MAINT 1 SO 13 4596P 2000 15284776 INDUCTION TUBE ATTACHED TO OIL SUMP BECAME LOOSE CAUSING ROUGH RUNNING ENGINE. ENGINE OIL SUMP REPLACED TO CORRECT PROB LEM. 1 H 7 1 3O 3 O NT 3A19 E223 2001080100167 20010801 00167 EA 2001 8 1 2001FA0000031 2 20010605 G 8530 AEL74230P010 GUIDE LYC O360 O360F1A6 41514 EA EXHAUST OUT OF TOLERANCE H K NONE O OTHER IN INSP/MAINT 1 EA 17 L2915236A CYLINDER HAD LOW COMPRESSION READINGS, 20/80. CYLINDER WAS REMOVED FROM ENGINE AND INSPECTED. EX. GUIDE WAS INSPECTED AND FOUND TO BE OUT OF SERVICE LIMITS. EX GUIDE ID WAS MEASURED, AND A READING OF .5325 WAS TAKEN. MAX SERVICE DIMENSI ON FOR A 300 HR CYLINDER EX GUIDE ID IS .5015/.5025 PER LYCOMING O/H MANUAL 60294-7-8. THIS CYLINDER HAD 236 HOURS SINC E OVERHAUL. 3 O E286 2001071800008 20010718 00008 SO 2001 7 18 2001FA0000035 1 20010620 G 5712 1159WM4007415G RIB GIV GULSTM G1159 GIV 3980115 SO LT WING CRACKED B K NONE O OTHER IN INSP/MAINT 1 SO 11 460QS 2298 2298 1360 1360 WHILE DOING A SCHEDULE VISUAL INSPECTION OF THE WING IT WAS NOTED A CRACK WAS IN RIB WEB. THE RIB IS LOCATED NEXT TO TH E LAST OUTBOARD LEFT WING. CRACK IS 7 INCH LONG ALONG THE THE BOTTOM SIDE THEN TURNS UP AT BOTH ENDS FOR 1 INCH. REMOV ED AND REPLACED WITH NEW RIB. 2 L 7 2 4F RT A12EA 2001080100169 20010801 00169 EA 2001 8 1 2001FA0000041 2 20010524 G 8550 LW15688 SUMP CESSNA 150 152 2071835 CE LYC O235 O235* 41505 EA SUMP ASSY, OIL FAILED B K NONE O OTHER IN INSP/MAINT 1 SO 13 4596P 15284776 INDUCTION TUBE ATTACHED TO OIL SUMP BECAME LOOSE CAUSING ROUGH RUNNING ENGINE. ENGINE OIL SUMP REPLACED TO CORRECT PROB LEM. 1 H 7 1 3O 3 O NT 3A19 E223 2001080100170 20010801 00170 CE 2001 8 1 2001FA0000042 1 20010601 G 5753 12210107 FLAP TRACK CESSNA 206 TU206G 2073357 CE WING LOOSE B K NONE O OTHER IN INSP/MAINT 1 GL 15 9851Z U20606701 THE LEFT HAND INBOARD FLAP TRACK IS WORKING LOOSE. THIS WAS INDICATED BY CRACKED COVE SKIN ATTACH BRACKETS. 1 H 7 1 3O A4CE 2001080100171 20010801 00171 SO 2001 8 1 2001FA0000043 1 20010525 G 7111 23810000 ALT AIR DOOR PIPER PA30 PA30 7103002 SO RIGHT ENGINE LOOSE D C ABORTED TAKEOFF R PARTIAL RPM/PWR LOSS TO TAKEOFF 1 GL 03 8379Y 301534 ON TAKEOFF ROLL, THE RIGHT ENGINE WOULD NOT DEVELOP FULL POWER. UPON FUTURE INVESTIGATION FOUND THE ALT AIR DOOR CAME L OOSE AND WAS BLOCKING THE EJECTOR INTAKE. UPON FINDING THIS WE INSPECTED THE LEFT ALT AIR BOX AND FOUND THE ALT AIR DOO R LAYING IN THE COWLING. 1 L 7 2 3O A1EA 2001080100173 20010801 00173 GL 2001 8 1 2001FA0000044 1 20010424 G 3230 5533525 PIN NAMER T6 SNJ4 6400414 GL MLG WORN G K NONE O OTHER IN INSP/MAINT 1 GL 15 7083C 2290 881447 BINDING OF PIN WOULD NOT ALLOW LEFT MAIN GEAR TO LOCK DOWN, CAUSING GEAR TO COLLAPSE ON LANDING. UPON INSPECTION, PIN D OES NOT APPEAR WORN. MANUAL DOES NOT CALL OUT FOR LUBING PIN. A SLIGHT OIL FILM ON PIN MAKES IT LOCK NORMAL. 1 L 7 1 3R A2575 2001080100174 20010801 00174 SO 2001 8 1 2001FA0000045 1 20010606 G 5540 6342004 RUDDER BAR PIPER PA32 PA32260 7103206 SO RUDDER CRACKED D K NONE O OTHER IN INSP/MAINT 1 AL 01 4803S 11045 321188 DURING 100 HOUR INSPECTION, FOUND LEFT RUDDER BAR CRACKED AT WELD WHERE STRAIGHT TUBE CONNECTS TO CARRY OVER TUBE. SPEC ULATE AGE AND USAGE CAUSED CRACK.. THIS COMPONENT HAS BEEN FOUND CRACKED SEVERAL TIMES IN THE PAST ON OTHER SIMILAR AIRC RAFT. LATER MODEL AIRCRAFT HAVE A REINFORCEMENT PLATE WELDED ON THIS AREA BY THE FACTORY. 1 L 7 1 3O A3SO 2001080200264 20010802 00264 CE 2001 8 2 2001FA0000046 1 20010615 G 6120 8976021 CAM CESSNA 441 441 2076020 CE GARRTT TPE331 TPE331* 01514 WP PITCH CONTROL MISMANUFACTURED B WTXR K NONE O OTHER IN INSP/MAINT 1 NM 07 P143091 RECEIVED A NEWLY OVERHAULED P.P.C. FROM MANUFACTURER, WAS UNABLE TO RIG. FOUND P.P.C. CAM HAD THE RIGHT PN BUT THE WRON G CAM PROFILE MANUFACTURE IN IT. REF: SB TPE331-72-0904. 1 L 7 2 3T 3 T RT A28CE E2WE 2001080100176 20010801 00176 SO 2001 8 1 2001FA0000047 1 20010505 G 7810 EXHAUST PIPE PIPER PA18 PA18150 7101828 SO ENGINE CRACKED D K NONE O OTHER IN INSP/MAINT 1 GL 03 4136E 538 187809082 FOUND WELD ON WYE PIPE CRACKED AT ANNUAL INSPECTION. (NO PARTS AVAILABLE AT THIS TIME) ALSO FOUND INNER BAFFLE ON SAME PIPE CRACKED. 1 H 7 1 3O 1A2 2001080100177 20010801 00177 2001 8 1 2001FA0000048 4 20010519 G 2320 CI248 ANTENNA CESSNA 182 T182 2072736 CE VHF ANTENNA BROKEN D K NONE O OTHER IN INSP/MAINT 1 GL 19 3525R 18280977 AIRCRAFT FLEW IN WITH BOTH VHF COMM ANTENNA BROKEN. AIRCRAFT TOTAL TIME WAS 5 HOURS. PROBABLE CAUSE NOT KNOWN. 1 L 7 1 3O 3A13 2001080100178 20010801 00178 2001 8 1 2001FA0000049 4 20010519 G 2320 CI248 ANTENNA CESSNA 182 T182 2072736 CE VHF ANTENNA BROKEN D K NONE O OTHER IN INSP/MAINT 1 GL 19 3525R 5 18280977 AIRCRAFT FLEW IN WITH BOTH ANTENNA BROKEN. AIRCRAFT TOTAL TIME WAS 5 HOURS. PROBABLE CAUSE NOT KNOWN. 1 L 7 1 3O 3A13 2001080100179 20010801 00179 CE 2001 8 1 2001FA0000052 1 20010606 G 5510 9664000093 PLATE BEECH 80 65B80 1152812 CE RUDDER CORRODED C K NONE O OTHER IN INSP/MAINT 1 EA 21 19CR 3278 LD372 DURING ANNUAL INSPECTION, UPPER AND MID RUDDER ATTACH FITTING PLATES (THESE CONTAIN THE BEARINGS) WERE FOUND TO BE SEVER ELY EXFOLIATED. THE UPPER RUDDER ATTACH PLATE EXFOLIATED TO THE POINT THAT THE ATTACH POINT HAD FAILED. THE RUDDER COU LD BE MOVED APPROXIMATELY SIX INCHES OUT OF ITS PLANE OF ROTATION DUE TO THE UPPER ATTACH POINT FAILURE. SUSPECT THAT I NSUFFICIENT OR INFREQUENT INSPECTION OF THE AERA ALLOWED THE CORROSION TO PROGRESS TO THE EXTENT OF ATTACH POINT FAILURE . 1 L 7 2 3O 3A20 2001071800009 20010718 00009 SO 2001 7 18 2001FA0000053 1 20010622 G 3250 74381 SWIVEL GULSTM GV GULFSTREAMGV 3980116 SO NLG RUPTURED B O OTHER K FLUID LOSS AP APPROACH 1 WP 05 1540 520 580 NOSE WHEEL STEERING SWIVEL, (AT NOSE LANDING GEAR ASSY) RUPTURED, DEPLETING THE LEFT HYDRAULIC RESERVOIR. NOTE: THIS RE SERVOIR PROVIDES HYDRAULIC POWER TO THE FLAPS, LEFT THRUST REVERSER AND THE BRAKES. 2 L 7 2 4F RT A12EA 2001080200266 20010802 00266 SO 2001 8 2 2001FA0000055 1 20010605 G 2730 42901002 TUBE PIPER PA31 PA31350 7103110 SO ELEVATOR CONTROL ELONGATED B R2JR K NONE O OTHER IN INSP/MAINT 1 EA 21 13FS 3692 318352024 WHILE C/W UNDER PANEL ITEMS ON ANNUAL CHECKLIST, FOUND ARM ON THE ELEVATOR CONTROL TUBE VERY LOOSE. DISASSEMBLY SHOWED HOLE WHERE ARM MOUNTS TO TUBE VERY ELONGATED. PART REPLACED WITH NEW PART. SUGGEST PHYSICALLY CHECKING EACH ARM FOR UN WANTED MOVEMENT WHEN DOING INSPECTION, NOT JUST VISUAL INSPECTION. 1 L 7 2 3O A20SO 2001080200267 20010802 00267 CE 2001 8 2 2001FA0000056 1 20010613 G 3233 12815041 ACTUATOR CESSNA 177 177RG 2073709 CE MLG FAILED D A UNSCHED LANDING J WARNING INDICATION CR CRUISE 1 SW 99 34072 177RG0960 DURING CRUISE FLIGHT PILOT REPORTED BUFFET AND LOSS OF GEAR UP INDICATION. PILOT SLOWED TO GEAR SPEED AND DESENDED TO V FR CONDITIONS AND RETURNED TO DEPARTURE AIRPORT. SELECTED GEAR DOWN AND COULD NOT GET GEAR DOWN INDICATION. EMERGENCY EXTENDED GEAR AND OBTAINED A GEAR DOWN INDICATION. UNEVENTFUL LANDING. ON INSPECTION FOUND THE LEFT MAIN GEAR DOWN LOC K ACTUATOR #1281504-1 HAD RUPTURED END SHAFT SEAL AND MOST OF HYDRAULIC FLUID HAD LEAKED FROM SYSTEM. DISSASEMBELED AND FOUND NO DEFECTS EXCEPT FAILED SEAL.REPLACED SEAL AND FUNTION TEST OK. 1 H 7 1 3O A20CE 2001080100180 20010801 00180 CE 2001 8 1 2001FA0000057 1 20010606 G 5320 9542001549 CHANNEL BEECH 35 V35A 1151544 CE FUSELAGE CORRODED B K NONE O OTHER IN INSP/MAINT 1 NE 05 8359N D8753 UPON REMOVAL OF THE LARGE FLOORBOARD AFT OF THE SPAR, IT WAS NOTED THAT THE TEW MIDDLE/CENTER CHANNEL ASSEMBLIES WERE CO RRODED. THE CORROSION WAS SO BAD THAT A TWO INCH AREA AND ONE INCH AREA ON THE OTHER THAT PROVIDES THE MOUNTING FOR THE SEAT RAILS WAS MISSING. THE CAUSE OF THE CORROSION BELIEVED TO BE DISIMILAR METAL CORRIOSION FROM THE SCREWS. LOOKED AT ALL THE OTHER SCREWS THAT SECURE THE CHANNELS AND STIFFENERS AND THEY WERE JUST STARTING TO CORRODE, SO THEY ALL GOT REPLACED. 1 L 7 1 3O 3A15 2001080100182 20010801 00182 GL 2001 8 1 2001FA0000058 1 20010327 G 3213 35017502 STRUT AVIAT A1 A1B GL MLG FAILED D K NONE O OTHER IN INSP/MAINT 1 NE 05 484C 2114 LANDING GEAR STRUT FAILED AT WELD DUE TO COMPLETE LACK OF WELD PENETRATION. LANDING GEAR SEPARATED FROM AIRCRAFT AT LAN DING. DUE TO WELD FAILURE. 1 H 7 1 3O NC A22NM 2001080100183 20010801 00183 SO 2001 8 1 2001FA0000059 1 20010616 G 3213 2468105 STRUT PIPER PA30 PA30 7103002 SO RT MLG CRACKED D K NONE O OTHER IN INSP/MAINT 1 SO 08 8418Y 7891 301570 RIGHT SIDE MAIN LANDING GEAR UPPER HOUSING CRACKED FROM BOLT HOLE WHERE BROKE LINE ATTACHES INTO THE INNER MOST AREA OF THE STRUT 1 INCH LONG ON EACH SIDE. LEAKING FLUID. POTENTIAL COMPLETE SEPARATION OF GEAR LEG. 1 L 7 2 3O A1EA 2001080100186 20010801 00186 SW 2001 8 1 2001FA0000060 1 20010611 G 2460 HARNESS MOONEY M20 M20K 5870220 SW FUSELAGE CHAFED B K NONE O OTHER IN INSP/MAINT 1 EA 23 252YC 251074 WHEN REPAIRING AVIONICS POWER SYSTEM, CB PANEL PULLED LOOSE AND OUT FOR MAINTENANCE. DISCREPANCY NOTED: FUSELAGE UNDER WINDSHIELD CHAFING POWER CABLES TO CB S AND RELAYS. NO CHAFE STRIP NOTED IN THIS AREA BEHIND CB PANEL AND CHAFING EVID ENCE ON LARGE POWER WIRES. GLARESHIELD REMOVAL TO INSPECT. PROBLEM NOT RELATED TO AVIONICS PROBLEM THAT WAS REPAIRED. 1 L 7 1 3O 2A3 2001080100187 20010801 00187 CE 2001 8 1 2001FA0000061 1 20010611 G 3210 084212219 LINK CESSNA 404 404 2075901 CE LINK ASSY DRAG BENT D K NONE O OTHER IN INSP/MAINT 1 SW 01 165SA 4040622 LINK ASSEMBLY DRAG. PN 0842122-19 1 L 7 2 3O RT A25CE 2001080100188 20010801 00188 CE 2001 8 1 2001FA0000062 1 20010611 G 2710 581510326CR CONTROL CABLE CESSNA 404 404 2075901 CE LT AFT AILERON INOPERATIVE D K NONE O OTHER IN INSP/MAINT 1 SW 01 165SA 4040622 LEFT HAND AFT AILERON CABLE. PN 5815103-26CR ( BLENDED ) 1 L 7 2 3O RT A25CE 2001080100201 20010801 00201 EA 2001 8 1 2001FA0000063 2 20010516 G 8550 06B23072 GASKET CESSNA 172 172N 2072434 CE LYC O320 O320* 41508 EA OIL FILTER FAILED D K NONE O OTHER IN INSP/MAINT 1 WP 19 737TC 17269654 AD2000-18-23 WAS C/W BY INSTALLING NEW GASKET PT NR 06B23072 UNDER 34 HOURS, GASKET BLEW OUT AND ALL THE OIL WAS BLOWN O UT. AIRCRAFT RETURNED TO AIRPORT SAFELY. INSPECTION OF GASKET REVELED THAT THE RUBBER GASKET HAD DESOLVED AND BECAME VERY SOFT. A NEW GASKET WAS INSTALLED AS PER INSTRUCTIONS IN THE SB. NO FURTHER PROBLEMS HAVE BEEN ENCOUNTERED WITH TH IS AIRCRAFT. 1 H 7 1 3O 3 O NT 3A12 E274 2001080100202 20010801 00202 CE 2001 8 1 2001FA0000064 1 20010614 G 2730 123460020 ELEVATOR CESSNA 182 182S 2072701 CE RT SIDE ELEVATOR WEAK D K NONE O OTHER IN INSP/MAINT 1 EA 25 132ME 276 18280690 WHILE PERFORMING AN ANNUAL INSPECTION ON THIS AIRCRAFT, SEVERAL WRINKLES AND LOOSE RIVETS WERE DISCOVERED ON BOTH ELEVAT ORS ALONG WHERE THE BALANCE TAB ATTACHES TO THE ELEVATOR SPAR. THE STRUCTURE AROUND THIS AREA APPEARED VERY WEAK AND FL EXIBLE. CESSNA WAS CONTACTED FOR TECHNICAL ASSISTANCE. AT CESSNAS REQUEST, NEW REPLACEMENT ELEVATORS WERE INSTALLED, A ND THE OLD ONES WERE RETURNED FOR AN ENGINEERING EVALUATION. ALL INSPECTORS ARE URGED TO VIGILANT FOR SUCH CONDITION ON OTHER AIRCRAFT OF THIS TYPE. 1 H 7 1 3O NT 3A13 2001080100203 20010801 00203 NE 2001 8 1 2001FA0000066 1 20010515 G 5540 27103 PUSHROD CONAER LA4 LA4200 5110310 NE AFT FUSELAGE CORRODED B K NONE O OTHER IN INSP/MAINT 1 EA 23 911CY 2194 532 REMOVED FORWARD LOWER ROD END FROM RUDDER PUSHROD ASSEMBLY, DUE TO VISIBLE CORROSION. FOUND EXTENSIVE CORROSION INTERNA LLY ON ARM AND ROD ASSEMBLY. 1 H 7 1 3O 1A13 2001080100204 20010801 00204 CE 2001 8 1 2001FA0000067 1 20010503 G 3222 35825174 ARM BEECH 95 95 1153402 CE NLG CRACKED G K NONE O OTHER IN INSP/MAINT 1 SO 09 2765Y TD136 UPON LANDING ROLL-OUT THE NOSE GEAR COLLAPSED. THE CRACK ON THE SPLINE PORTION OF ARM CAUSED THE ARM TO FLEX AND OPEN C AUSING MATING GEARS TO SEPARATE AND THE NOSE GEAR TO COLLAPSE. PROBABLE CAUSE IS FATIGUE. REOCCURRING INSPECTIONS ARE RECOMMENDED. 1 L 7 2 3O 3A16 2001071800010 20010718 00010 CE 2001 7 18 2001FA0000068 1 20010702 G 7930 30702464 INDICATOR RKWELL NA265 NA26565 7630107 CE GARRTT TFE731 TFE7313R1D 01518 WP RT ENGINE DEFECTIVE B K NONE N FALSE WARNING IN INSP/MAINT 1 CE 01 82CR 4950 46549 P83263 IN PROCESS OF PRE-FLIGHT INSPECTION NOTICED RIGHT ENGINE OIL FILTER BY-PASS INDICATOR PIN HAD POPPED. INSPECTED OIL FIL TER AND TOOK SOAP SAMPLE (NEW OIL FILTER INSTALLED). AFTER TEST RUN AND LEAK CHECK, NOTICED PIN PARTIALLY POPPED AGAIN. REMOVED BY-PASS INDICATOR ASSEMBLY AND NOTICED MINIMAL RESISTANCE FOR PIN EXTENSION. REPLACED ASSEMBLY WITH NEW UNIT. DEFECTIVE UNIT HAS ASSEMBLY DATE OF 3Q/87. ADDITIONALLY THE FOLLOWING NUMBERS APPEAR ON ASSEMBLY:99193SOCN307246-4 N AND MFR 05228-7579668. 2 L 7 2 4J 4 F A2WE E6WE 2001080100205 20010801 00205 CE 2001 8 1 2001FA0000069 1 20010614 G 2730 12346001 ELEVATOR CESSNA 182 182S 2072701 CE LT SIDE ELEVATOR WEAK D K NONE O OTHER IN INSP/MAINT 1 EA 25 132ME 18280690 WHILE PERFORMING AN ANNUAL INSPECTION ON THIS AIRCRAFT, SEVERAL WRINKLES AND LOOSE RIVETS WERE DISCOVERED ON BOTH ELEVAT ORS ALONG WHERE THE BALANCE TAB ATTACHES TO THE ELEVATOR SPAR. THE STRUCTURE AROUND THIS AREA APPEARED VERY WEAK AND FL EXIBLE. CESSNA WAS CONTACTED FOR TECHNICAL ASSISTANCE. AT CESSNAS REQUEST, NEW REPLACEMENT ELEVATORS WERE INSTALLED, A ND THE OLD ONES WERE RETURNED FOR AN ENGINEERING EVALUATION. ALL INSPECTORS ARE URGED TO BE VIGILANT FOR SUCH CONDITION ON OTHER AIRCRAFT OF THIS TYPE. 1 H 7 1 3O NT 3A13 2001080100207 20010801 00207 GL 2001 8 1 2001FA0000072 3 20010703 G 6110 SHAFT CESSNA 421 421C 2076016 CE CONT O520 GTSIO520H 17032 SO MCAULY 3AF34C 3AF34C92 GL PROPELLER SHAFT SHEARED D K NONE O OTHER IN INSP/MAINT 1 CE 07 421LF 421C0059 234899R 742786 AIRCRAFT PROPELLOR WENT INTO FEATHER ON APPROACH. AFTER LANDING, RESTARTED ENGINE AND PROPELLOR FELL OFF. PROP SHAFT S HEARED IN HALF. ENGINE HAD A PROP STRIKE 400 HOURS PREVIOUS. 1 L 7 2 3O 3 O A7CE E7CE 5 C P22EA 2001080100209 20010801 00209 CE 2001 8 1 2001FA0000074 1 20010531 G 7112 9691910016 AIR BOX BEECH 95 95B55 1152729 CE RT ENGINE CRACKED G K NONE O OTHER IN INSP/MAINT 1 SO 17 38088 2356 69 TC2366 RIGHT ENGINE AIRBOX DISPLAYS MORE THAN NORMAL WEAR DUE TO VIBRATION INDUCED CRACKING OF AIRBOX COMPONENTS. 1 L 7 2 3O RT 3A16 2001080100210 20010801 00210 SO 2001 8 1 2001FA0000075 1 20010509 G 2700 KSC270720V BEARING EMB 145 EMB145 SO HINGE BEARING FAILED G K NONE O OTHER IN INSP/MAINT 1 SW 13 DURING RECEIVING INSPECTION FLAT NUT IS TESTED ON HOUSING. WILL SPIN FREELY ON BUT THEN LOCKS UP 50 TO 80 PER CENT FAIL RATE. 2 L 7 2 4F RT T00011AT 2001071300015 20010713 00015 CE 2001 7 13 2001FA0000076 1 20010625 G 2434 DOFF10300J BRUSHES CESSNA 172 172M 2072418 CE ALTERNATOR WORN D O OTHER O OTHER NR NOT REPORTED 1 SW 01 9627Q 600 17265711 BRUSHES WORN TOTALLY OUT, ALLOWING SPRINGS AND WIRES TO DAMAGE ROTOR SLIP RINGS. POOR QUALITY BRUSHES NOT TO LAST LONGE R. 1 H 7 1 3O NT 3A12 2001080100211 20010801 00211 CE 2001 8 1 2001FA0000077 1 20010627 G 7603 359440465 THROTTLE BEECH 33 E33A 1151424 CE COCKPIT MISALIGNED G K NONE O OTHER IN INSP/MAINT 1 WP 23 464SR CE275 THE THROTTLE CONTROL KNOB BUTTON RETAINING SCREW LOOSENED ALLOWING THE THROTTLE CONTROL KNOB BUTTON TO MISALIGN AND JAM DURING THROTTLE APPLICATION. THE THROTTLE CONTROL KNOB BUTTON RETAINING SCREW WAS FOUND APPROX 8 TURNS LOOSE. 1 L 7 1 3O 3A15 2001080100212 20010801 00212 CE 2001 8 1 2001FA0000078 1 20010710 G 5312 07126161 BULKHEAD CESSNA 182 182L 2072726 CE FUSELAGE CRACKED B QRQR K NONE O OTHER IN INSP/MAINT 1 SW 05 3301R 4504 18258601 CRACKS IN THE UPPER OUTBOARD CORNERS OF THE RUDDER CABLE CUT-OUTS ON THE 0712616-1 BULKHEAD ASSEMBLY. AREA IN WHICH CRA CK OCCURS IS RELATIVELY THIN GAUGE MATERIAL THAT APPARENTLY PROVIDES LITTLE STRUCTURAL STRENGTH. THE FLANGES IN THIS AR EA DO LITTLE MORE THAN SERVE AS A FASTENING POINT FOR AN AERODYNAMIC FAIRING. IT IS DOUBTFUL IF THIS DEFECT IMPAIRS THE STRUCTURAL STRENGTH OF THE BULKHEAD ASSEMBLY AS THE 0712616-4 STIFFENER THAT ATTACHES TO THE -1 BULKHEAD IS MUCH HEAVIE R GAUGE MATERIAL. 1 H 7 1 3O NT 3A13 2001080100213 20010801 00213 SW 2001 8 1 2001FA0000080 1 20010710 G 5711 SPAR BBAVIA 7 7AC 2110102 SW LT WING CRACKED C K NONE O OTHER IN INSP/MAINT 1 GL 15 83280 1947 DURING INSPECTION, FOUND LT WING FORWARD SPAR CRACKED AT UNDERSIDE OF SPAR OUT BOUND OF LIFT STRUT ATTACH POINT. THIS W ING WILL BE REPAIRED WITH NEW SPAR INSTALLED. 1 H 7 1 3O A759 2001080100214 20010801 00214 SW 2001 8 1 2001FA0000081 1 20010625 G 5711 SPAR BBAVIA 7 7FC 2110124 SW WING CRACKED D K NONE O OTHER IN INSP/MAINT 1 WP 27 9052B 7FC140 BOTH FRONT SPARS HAD SEVERE CRACKS AT ATTACH POINTS INTO BUSHINGS. 1 H 7 1 3O A759 2001080200268 20010802 00268 NE 2001 8 2 2001FA0000082 1 20010405 G 5720 21610075 ANGLE CONAER LA4 LA4250 5110320 NE WING CRACKED D K NONE O OTHER IN INSP/MAINT 1 SO 14 1574 31 WHILE PREPARING PRE-PURCHASE CONDITION REPORT ON ABOVE AIRCRAFT. THE LEFT LOWER SPAR DOUBLER WAS FOUND CRACKED. VISUAL INSPECTION SHOWED LOWER SPAR ANGLE CRACKED. 1 H 7 1 3O 1A13 2001080100215 20010801 00215 NE 2001 8 1 2001FA0000083 1 20010405 G 5730 21610063 DOUBLER LAKEAC LAKE 250LAKE 5110322 NE WING CRACKED D K NONE O OTHER IN INSP/MAINT 1 SO 14 9224D 1574 31 WHILE PREPARING PRE-PURCHASE CONDITION REPORT ON ABOVE AIRCRAFT, THE LEFT LOWER SPAR DOUBLER WAS FOUND CRACKED. VISUAL INSPECTION SHOWED LOWER SPAR ANGLE CRACKED. 1 H 7 1 3O NC 1A13 2001080100224 20010801 00224 GL 2001 8 1 2001FA0000085 3 20010601 G 6110 C5046 PLATE CESSNA 182 R182 2072734 CE MCAULY 2D34C B2D34C218 GL AFT BLKHD ATTACH CRACKED C K NONE O OTHER IN INSP/MAINT 1 EA 21 THIS PROPELLER INSTALLATION UTILIZES 2 SPINNER AFT BULKHEAD ATTACH PLATES, PN A1639-9. BOTH PLATES WERE FOUND TO BE CRA CKED WITHIN 50 HR OF INSTALLATION OF PROP AFTER OVERHAUL. BECAUSE BULKHEAD ATTACHMENT PLATES ARE INSTALLED UNDER ATTACH MENT NUTS, PN A1639-9, THAT HOLDS THE PROP TO THE ENGINE IS SUBJECTED TO VERY HIGH CONTACT FORCES DUE TO THE SMALL SHOUL DER ON THE NUT(A1639-9). THE LIKELIHOOD OF THIS FAILURE WILL INCREASE WITH THE NUMBER OF TIMES THESE FASTENERS ARE TORQ UED. IPC CALLS FOR THE INSTALLATION OF A WASHER BETWEEN ATTACHMENT PLATE AND NUT, EXCEPT THERE IS NOT SUFFICIENT CLEARA NCE TO ALLOW THE INSTALLATION OF THE WASHER. 1 H 7 1 3O RT 3A13 5 C P7EA 2001080100225 20010801 00225 NE 2001 8 1 2001FA0000086 1 20010424 G 2752 MS28775115010 O-RING GERDES LAKEAC LAKE 250LAKE 5110321 NE SHAFT DETERIORATED G K NONE O OTHER IN INSP/MAINT 1 SO 17 CGPXH 1868 741 DURING LOCAL FLIGHT, PILOT NOTICED HYDRAULIC PUMP CYCLING CONSTANTLY. PILOT ELECTED TO LAND AND CHECK. LANDING GEAR WO ULD NOT FULLY EXTEND. PILOT COULD NOT GET LANDING GEAR FULLY UP OR DOWN. EMERGENCY LANDING MADE WITH PARTIAL GEAR ON G RASS STRIP WITH MINIMAL DAMAGE. FOUND T/E FLAP ACTUATOR SHAFT SEALS (3 ORINGS) LEAKING FLUID CAUSING LACK OF SUFFICIENT PRESSURE TO OPERATE GEAR AND FLAPS. 1 H 7 1 3O NC 1A13 2001080100227 20010801 00227 GL 2001 8 1 2001FA0000087 3 20010228 G 6110 C5152 COUNTERWEIGHT MCAULY CESSNA 208 208 2073702 CE MCAULY 3AF34C 3AF34C* GL ARM CRACKED G K NONE O OTHER IN INSP/MAINT 1 SO 23 LVWYZ 1720 952445 0522 DURING MAGNETIC PARTICLE INSPECTION, AN INDICATION WAS FOUND IN THE TRANSITION BETWEEN THE COUNTERWEIGHT ARM AND THE ATT ACHMENT AREA, WHERE IT JOINS THE BLADE ROOT. THE CRACK APPEARS LIKE A HAIR LINE BUT STRONG INDICATION, ONCE IT WAS GROU ND TO MAXIMUM DEPTH ALLOWABLE THE CRACK STARTED TO GROW IN WIDTH AS WELL AS CHANGED ITS DIRECTION BY 90 DEGREE, SO THE C RACK DEVELOPED A PATTERN TYPICAL FROM A FORGING FOLD. A PERIODICAL INSPECTION COULD BE A GOOD PREVENTATIVE TECHNIQUE. 1 H 7 1 3T NT A37CE 5 C P22EA 2001080200269 20010802 00269 CE 2001 8 2 2001FA0000091 1 20010525 G 5530 04310093 FITTING CESSNA 150 152 2071835 CE VERTICAL STAB CRACKED D K NONE O OTHER IN INSP/MAINT 1 NM 01 714TD 15279413 DURING ROUTINE 100 HR INSPECTION, MINOR CORROSION WS FOUND ON BOTH LEFT AND RIGHT VERTICAL STABILIZER ATTACH FITTINGS, A PPROX BS 200.4. UPON REMOVAL OF CORROSION, A CRACK WS FOUND IN THE RADIUS OF THE RIGHT FITTING APPROXIMENTLY .7500 OF TH E WAY ACROSS AND APPROX .50 PERCENT OF THE THICKNESS DEEP. PROBABLE CAUSE: ROUTINE STRESS SOLUTION: TIME LIFE REPLACE MENT OF ATTACH FITTINGS. 1 H 7 1 3O NT 3A19 2001080100229 20010801 00229 EA 2001 8 1 2001FA0000092 2 20010612 G 8530 O5K21114 CYLINDER CESSNA 150 152 2071835 CE LYC O235 O235L2C 41505 EA INTAKE ARM CRACKED D K NONE O OTHER IN INSP/MAINT 1 SO 13 66934 347 15281670 L2129415 DURING ROUTINE INSPECTION, FOUND NR 1 CYLINDER TO BE CRACKED ABOVE THE INTAKE VALVE GUARD AREA. WHEN PRESSURIZED, THE E NTIRE LENGTH OF THE CRACK PRODUCED BUBBLES. 1 H 7 1 3O 3 O NT 3A19 E223 2001080100230 20010801 00230 CE 2001 8 1 2001FA0000093 1 20010607 G 3232 98820152 ACTUATOR CESSNA 172 172RG 2072438 CE MLG CRACKED D K NONE O OTHER IN INSP/MAINT 1 SW 17 9515B 4503 172RG0846 DEFECT WAS DISCOVERED WHILE PERFORMING SB MAIN LANDING GEAR ACTUATOR INSPECTION. PART HAD CRACKED IN THE SUSPECTED AREA , THE SADDLE SHAPED HOLE AND CIRCUMFERENCE OF THE 2.28 INCH DIA. BORE AND STEP, NEAR THE ROLLER BEARING ASSEMBLY. THERE WAS NO EVIDENCE OF PILOT ERROR OR ABUSE. PART OTHERWISE INDICATED NORMAL WEAR. PROBABLE CAUSE: STRESS RISER INHERENT TO DESIGN, OR PART NOT DESIGNED TO BE STRONG ENOUGH. RECOMMENDATION: REDESIGN PART. 1 H 7 1 3O 3A17 2001080100231 20010801 00231 CE 2001 8 1 2001FA0000094 1 20010607 G 3232 98820152 ACTUATOR CESSNA 172 172RG 2072438 CE MLG CRACKED B K NONE O OTHER IN INSP/MAINT 1 GL 17 9515B 4503 172RG0846 DEFECT WAS DISCOVERED WHILE PERFORMING SB MAIN LANDING GEAR ACTUATOR INSPECTION. PART HAD CRACKED IN THE SUSPECTED AREA , THE SADDLE-SHAPED HOLE AND CIRCUMFERENCE OF THE 2.28 INCH DIA BORE AND STEP, NEAR THE ROLLER BEARING ASSY. THERE WAS NO EVIDENCE OF PILOT ERROR OR ABUSE. PART OTHERWISE INDICATED NORMAL WEAR. PROBABLE CAUSE: STRESS-RISER INHERNTTO DES IGN, OR PART NOT DESIGNED TO BE STRONG ENOUGH. RECOMMENDATION: REDESIGN PART. 1 H 7 1 3O 3A17 2001080100232 20010801 00232 CE 2001 8 1 2001FA0000095 1 20010102 G 2822 476411 PUMP CESSNA 310 310R 2074245 CE CONT O520 IO520M 17032 SO AFT OB WING TIP INTERMITTENT C K NONE O OTHER IN INSP/MAINT 1 GL 17 5336C 167 310R1542 ON THE LEFT SIDE OF AC, WE HAVE REPLACED THE CIRCULATING PUMP NUMEROUS TIMES WHILE RIGHT SIDE HAS BEEN FINE. MOST RECEN T DATES OF REPLACEMENT AS FOLLOWS: 12-9-99 TACH 3443.5, 9-18-2000 3715.3, 12-29-2000 3882.4. AS STATED EARLIER ALL 3 OF THESE WERE ON THE LEFT SIDE. ON 12-29-2000, WE INSPECTED THE WIRING AND BOTH INLET AND OUTLET HOSES/LINES FOR OBSTRUCT IONS. EACH PUMP WHEN REMOVED WAS VERY INTERMITTEN AND WOULD WORK WHEN THE CASING WAS TAPPED ON. PUMP NEEDS IMPROVEMENT . 1 L 7 2 3O 3 O 3A10 E5CE 2001080100233 20010801 00233 EU 2001 8 1 2001FA0000097 3 20010524 G 6111 6607132886 BLADE ROTOL ROTOL R4204 R130420412 EU OUTER SLEEVE CRACKED C MS1R K NONE O OTHER IN INSP/MAINT 1 EA 27 26510 5020 DR6869386 DR6869386 PROPELLER RECEIVED FOR OVERHAUL. BLADE SN 616 WAS FOUND TO HAVE A CRACKED OUTER SLEEVE AT ROOT END OF BLADE. BLADE REJ ECTED FROM FURTHER SERVICE. 6 C P890 2001080100235 20010801 00235 CE 2001 8 1 2001FA0000098 1 20010606 G 5530 RIB CESSNA 172 172 2072402 CE RUDDER BROKEN D K NONE O OTHER IN INSP/MAINT 1 NE 01 5838A 419 28438 UPPER RUDDER RIB WAS FOUND BROKEN AT THE OPENING FOR UPPER HINGE BOLT INSTALLATION ACCESS. THIS TYPE OF DAMAGE IS A REO CCURRING PROBLEM DUE TO A LACK OF PROPER GUST LOCKS FOR THE RUDDERS, WIND SLAPPING OF THE RUDDER WITH THE ARM OF THE BAL ANCE WEIGHT CAUSING CRACKS IN THE RIB WEAK POINT EVEN WITH THE ADDED DOUBLER. PROPER SECURING THE RUDDER WHEN OUTSIDE, MAY PREVENT FURTHER DAMAGE. 1 H 7 1 3O NT 3A12 2001080100236 20010801 00236 SO 2001 8 1 2001FA0000099 1 20010608 G 7820 8523304 MUFFLER PIPER PA32 PA32R301 7103218 SO LYC 0540 IO540K1G5D 41532 SO ENGINE CRACKED B EWGR K NONE O OTHER IN INSP/MAINT 1 SO 05 9265B 757 3246029 UPON REMOVAL OF HEATING SHROUDS FOR INSPECTION, FOUND SIDNIFICANT DISTORTION OF MUFFLER WAS CRACKED AT UPPER LEADING EDG E WELD. 1 L 7 1 3O 3 O A3SO 1E4 2001080100242 20010801 00242 CE 2001 8 1 2001FA0000100 1 20010618 G 2730 0411258 BELLCRANK CESSNA 150 150G 2071816 CE CONT O200 O200* 17020 SO ELEVATOR BLCRK ELONGATED D K NONE O OTHER IN INSP/MAINT 1 WP 28 3343J 3456 15066043 FOUND ELEVATOR BELLCRANKS CABLE ATTACH POINTS ELONGATED. RIGHT ATTACH WAS ELONGATED BY .215, LEFT ATTACH WAS ELONGATED BY .248, THE AN23-11 ATTACH BOLT IS .184. DRILLED OVERSIZE AND PUT NAS 75-3-004 STEEL BUSHING PRESSED IN, TO BRING BACK CORRECT TOLERANCE. 1 H 7 1 3O 3 O 3A19 E252 2001080100243 20010801 00243 SO 2001 8 1 2001FA0000101 1 20010628 G 7820 8523310 MUFFLER PIPER PA32 PA32R301 7103218 SO LYC 0540 IO540K1G5D 41532 SO RIGHT CRACKED B K NONE O OTHER IN INSP/MAINT 1 SO 05 9265B 757 3246029 UPON REMOVAL OF HEATING SHROUDS FOR INSPECTION, FOUND SIGNIFICANT DISTORTION OF MUFFLER CAN. THE MUFFLER WAS CRACKED AT UPPER LEADING EDGE WELD. 1 L 7 1 3O 3 O A3SO 1E4 2001080100244 20010801 00244 2001 8 1 2001FA0000102 4 20010604 G 3421 101490159 GYRO CESSNA 172 172R 2072401 CE LYC O360 IO360A1C 41514 EA ATTITUDE FAILED B OF1R K NONE O OTHER IN INSP/MAINT 1 EA 17 9453Z 294 17280193 GYRO TUMBLED IN FLIGHT AND WOULD NOT RE-ERECT. MAINTENANCE TROUBLESHOOTING REVEALED NO DEFECTS WITH INSTRUMENT AIR SYST EM. GYRO WAS REPLACED WITH A SERVICEABLE OVERHAULED UNIT. SYSTEM RETESTED AND REPLACEMENT GYRO FUNCTIONS NORMALLY. A IRCRAFT AND SYSTEM HAVE BEEN MAINTAINED AS PER MANUFACTURERS RECOMMENDATIONS SINCE NEW. 1 H 7 1 3O 3 O NT 3A12 1E10 2001080100245 20010801 00245 GL 2001 8 1 2001FA0000103 3 20010320 G 6110 SNAP RING MCAULY CESSNA 182 182P 2075816 CE CONT O470 O470R 17026 SO MCAULY 2A34C 2A34C203 GL NR 1& 2 BLDE RET FAILED D IT6R K NONE O OTHER IN INSP/MAINT 1 NM 01 5612J 74517 18263467 459837 EXTERNAL SNAP RING ON PROPELLER BLADE CAME OFF AFTER PREFLIGHT ENGINE HAD STOPPED ON INITIAL START, THEN WAS RESTARTED. SNAP RING CAME OFF BLADE SHANK BUT WAS RETAINED BY SPINNER. THEN AIRPLANE WAS FLOWN FOR 2 HOURS WITH FIVE TOUCH AND GO LANDINGS, WITHOUT FAILURE OF PROPELLER. PROPELLER WAS THEN REMOVED AND TAKEN BACK TO OVERHAUL SHOP WHERE TEAR-DOWN WAS COMPLETED. FINDING WAS SNAP-RING WAS NOT SEATED PROPERLY. THE BLADE TO PISTON LINK WAS DAMAGED AND REPLACED. THE PR OPELLER BLADE WAS DRESSED AT SHANK. 1 H 7 1 3O 3 O NT TA13 E273 5 C P3EA 2001080100246 20010801 00246 SO 2001 8 1 2001FA0000104 1 20010621 G 5711 6207006 SPAR PIPER PA32 PA32300 7103212 SO LYC O540 TIO540* 41532 EA OB OF MAIN GEAR CORRODED D K NONE O OTHER IN INSP/MAINT 1 WP 07 86CA 3194 3240957 WHILE RE-SKINNING THE LEFT UPPER INBOARD WING SKIN, WE FOUND CORROSION IMMEDIATELY OUT BOARD OF THE LEFT MAIN LANDING GE AR CASTING ON THE LOWER AFT SIDE OF THE MAIN SPAR INSIDE THE WING. THE CORROSION SEEING TO BE CENTRALIZED AROUND ONE RI VET AND RADIATING OUTWARD FROM THAT RIVET. THERE IS NO OTHER CORROSION IN THAT AREA OF THE WING. 1 L 7 1 3O 3 O A3SO E14EA 2001080100247 20010801 00247 SW 2001 8 1 2001FA0000106 1 20010702 G 5711 SPAR BBAVIA 7 7AC 2110102 SW CONT O200 O200A 17020 SO LIFT STRUT ATTCH CRACKED D K NONE O OTHER IN INSP/MAINT 1 SW 07 1703E 7AC5268 690748A FOUND A SMALL LONGITUDINAL CRACK BETWEEN THE PLYWOOD DOUBLER PLATE AT THE FORWARD LIFT STRUT ATTACH FITTING AND THE NEXT OUTBOARD RIB ALONG THE REAR FACE OF THE SPAR. WITH A MIRROR IN THE NEXT OUTBOARD RIB BAY, THE CRACK PROTRUDED ABOUT TH REE INCHES. WHEN THE FABRIC WAS REMOVED THE CRACK RAN FROM THREE INCHES INBOARD OF THE PLYWOOD DOUBLER AT THE LIFT STRU T ATTACH FITTING TO ABOUT THREE INCHES OUTBOARD OF THE SAME DOUBLER. THE CRACK WAS ONLY VISIBLE ON THE AFT FACE OF THE SPAR. 1 H 7 1 3O 3 O A759 E252 2001080100248 20010801 00248 EA 2001 8 1 2001FA0000107 2 20010626 G 8520 CRANKSHAFT PIPER PA60 PA60601P 7106012 NM LYC O540 TIO540* 41532 EA ENGINE BROKEN B GSZR C ABORTED TAKEOFF R PARTIAL RPM/PWR LOSS TO TAKEOFF 1 SW 19 377RC 140 61P057579632 L570161A ENGINE FAILED ON TAKE OFF. FACTORY REP. REPORTED BY PHONE THAT CRANKSHAFT HAD BROKEN. 1 M 7 2 3O 3 O RT A17WE E14EA 2001080100249 20010801 00249 CE 2001 8 1 2001FA0000108 1 20010627 G 3710 0701030807 HOSE CESSNA 182 182R 2072731 CE CONT O470 O470* 17026 SO VACUUM SYSTEM DISINTEGRATED B HX1R K NONE O OTHER IN INSP/MAINT 1 EA 25 9953H 18268139 CUSTOMER REPORTED LOW VACUUM INDICATION BUT GYROS RUNNING OK. INITIAL INVESTIGATION ALL HOSES LOOKED OK, HOWEVER WHEN H OSES WERE TOUCHED, FELL APART. THE ABOVE REFERENCED PN IS FOR ONE OF THE VACUUM GAUGE HOSES, HOWEVER ALL INSTRUMENT HOS E WERE OF THE SAME TYPE AND ALL FELL APART WHEN TOUCHED. BOTH GYROS WERE REMOVED FROM INLET FITTINGS (SCREENS ON INLET PORTS STOPPED MATERIAL FROM GETTING IN INSTRUMENTS). A TEMPORARY IN LINE FILTER WAS INSTALLED ON THE INLET SIDE OF VACU UM PUMP TO PREVENT MATERIAL FROM GOING INTO THE PUMP AND THE AIRCRAFT WAS GROUND RUN. NO DATES WERE FOUND ON THE HOSES. THE NUMBER 04A WAS ON SEVERAL HOSES EVERY 6 INCHES. THEY APPEAR TO BE ORIGINAL HOSES. 1 L 7 1 3O 3 O NT 3A13 E273 2001080100250 20010801 00250 SO 2001 8 1 2001FA0000112 1 20010627 G 3210 AN310A BOLT PIPER PA30 PA30 7103002 SO LYC O320 IO320* 41508 EA MLG BROKEN B K NONE O OTHER IN INSP/MAINT 1 SO 13 7993Y 301098 THE AN3-10A BOLT, HOLDING THE MAIN GEAR SPRING ATTACH BRACKET ON TO THE STRUT HOUSING, BROKE. IT CAUSED THE BRACKET TO JAM AGAINST THE GEAR FORWARD ATTACH FITTING AND WOULD NOT LET THE GEAR GO DOWN. AIRCRAFT LANDED WITH THE GEAR UNSAFE. 1 L 7 2 3O 3 O A1EA 1E12 2001080100251 20010801 00251 EA 2001 8 1 2001FA0000113 2 20010704 G 8530 AEL6510241 CYLINDER PIPER PA28 PA28161 7102803 SO LYC O320 O320* 41508 EA HEAD CRACKED B MW2R K NONE O OTHER IN INSP/MAINT 1 GL 17 4381L 306 288516016 L1341139A CYLINDER CRACKED FROM TOP SPARK PLUG HOLE AROUND OUTSIDE EXSEAT TO BOTTOM SPARK PLUG HOLE. 1 L 7 1 3O 3 O 2A13 E274 2001080100253 20010801 00253 EA 2001 8 1 2001FA0000114 2 20010709 G 8530 AEL6510241 CYLINDER PIPER PA28 PA28161 7102803 SO LYC O360 O360* 41514 EA CYLINDER HEAD CRACKED B MW2R K NONE O OTHER IN INSP/MAINT 1 GL 17 4328D 1293 288416019 CYLINDER CRACKED FROM TOP SPARK PLUG HOLE AROUND OUTSIDE EXSEAT TO BOTTOM SPARK PLUG HOLE. 1 L 7 1 3O 3 O 2A13 E286 2001072500615 20010725 00615 SW 2001 7 25 2001FA0000115 1 20010608 G 2810 206362002103 CAP BELL 407 407 SW FUEL CELL BINDING C K NONE K FLUID LOSS IN INSP/MAINT 1 EA 01 35 53444 FUEL FILLER CAP DOES NOT SEAT PROPERLY DUE TO CLOSE TOLERANCE BETWEEN AIRFRAME SPACERS AND CAP. THIS OCCURS 8 OR 9 TIME S OUT OF TEN CLOSURES. THE FUEL LEAKS DOWN THE SIDE OF THE AIRFRAME AND GETS SUCKED INTO AIR CONDITIONING FAN THRU COND ENSER. FUEL SPRAY BECOMES PRESSURIZED SPRAYING UP INTO AFT COMPARTMENTS BELOW BAGGAGE COMPARTMENT. AIRCRAFT INVERTERS A LSO WET WITH FUEL SPRAY, COULD BE SOURCE OF IGNITION AND POSSIBLE IN FLIGHT FIRE. RECOMMENDATION, OPEN UP CLEARANCE BETW EEN CAP DIAMETER AND AIRFRAME SPACERS. THIS AIRCRAFT HAS HAD PART 1 OF ASB 407-01-41 INCORPORATED. 1 G 7 1 3U O H2SW 2001072700260 20010727 00260 NE 2001 7 27 2001FA0000117 1 20010727 G 6321 7636309103102 DISK SKRSKY SKRSKY S76 S76C 8143008 NE TMECA ARRIEL ARRIEL2B NE ROTOR BRAKE CRACKED C K NONE E VIBRATION/BUFFET IN INSP/MAINT 1 EA 17 317MX 930 C207002824 760499 20523 DURING A SCHEDULED MAINTENANCE EVENT THE MAIN ROTOR BRAKE DISC WAS FOUND TO BE FRACTURED, COMPLETELY THROUGH, FROM THE O UTER TO THE INNER CIRCUMFERENCE, AND THERE WERE SOME VISUAL CRACKS EMANATING FROM AROUND THE MOUNTING HOLES. THE CREW H AD MENTIONED, THAT DURING ROTOR BRAKING, HAD FELT SOMETHING AND NOTICED AN INCREASE IN VIBRATION. THIS COMPONENT IS MOU NTED BETWEEN THE ENGINE INLETS, SURROUNDED BY NUMEROUS FUEL AND HYDRAULIC LINES, AND SHARES THE SAME DRIVE AS THE TAIL R OTOR. IF THIS WERE TO SEPARATE DURING GROUND OR FLIGHT OPERATIONS THE RESULT WOULD BE CATASTROPHIC. SIKORSKY AIRCRAFT (610-954-9613) WILL RECEIVE THE ASSEMBLY ON 7-29-01, AND FOWARD IT TO SIKORSKY ENGINEERING. 1 G 7 2 3U 3 U NC H1NE E00054EN 2001080100254 20010801 00254 GL 2001 8 1 2001FA0000118 1 20010706 G 2820 CHECK VALVE CIRRUS SR SR20 05628AJ GL CONT O550 IO550* SO RT HEADER TANK MISINSTALLED B NF2R K NONE O OTHER IN INSP/MAINT 1 GL 11 960CM 31 0041 685781 RIGHT FUEL QUANTITY GAUGE FALLS TO ZERO WHEN RIGHT TANK WAS SELECTED. FOUND FUEL QUANTITY TRANSMITTER WAS CORRECT, INBO ARD TRANSMITTER MOUNTED IN THE HEADER TANK WAS GOING TO ZERO WHEN FUEL WAS BEING USED FROM THE RIGHT TANK. CAUSE: THE FUEL INLET CHECK VALVE WAS GLUED CLOSED DURING ASSEMBLY OF THE AIRCRAFT. THE ENG WOULD USE MORE FUEL THAN THE RATE THE HEADER TANK COULD FILL, THIS CONDITION COULD CAUSE ENGINE STOPPAGE.DURING REPAIRS IT WAS FOUND THE NORMAL OPERATING SYST EM CAN NOT KEEP EITHER HEADER TANK FULL. FUEL QUANTITY INDICATION IS NOT ACCURATE WHEN ENGINE IS USING FUEL FROM THAT TA NK. 1 H 7 1 3O 3 O NC A00009CH E3SO 2001080100255 20010801 00255 EA 2001 8 1 2001FA0000119 2 20010718 G 8500 RJ0506041 DOOR RAJAYXXXXXXX MOONEY M20 M20D 5870210 SW LYC O360 O360* 41514 EA TURBO DOOR LOOSE D K NONE O OTHER IN INSP/MAINT 1 SO 09 191PA 500 248 DURING ANNUAL INSPECTION, PART WAS OBSERVED TO BE EXTREMELY LOOSE. REMOVED PART FROM ASSEMBLY. FOUND PORTION OF HINGE MISSING, HINGE PIN 95 PER CENT WORN THROUGH AND SIDE BRACKETS WORN 90 PER CENT THROUGH. REMOVED ASSEMBLY AND REPLACED D OOR AND FRAME WITH SERVICEABLE PART. FOUND BYPASS FLUTTER VALVE FOR CARB HEAT MISSING. INSTALLED NEW PART AND SECURED. 1 L 7 1 3O 3 O 2A3 E286 2001080100256 20010801 00256 CE 2001 8 1 2001FA0000120 2 20010712 G 7320 S29991 SWIVEL CESSNA 337 T337G 2075726 CE CONT IO360 IO360* 17025 CE MIXTURE CONTROL SEPARATED D K NONE O OTHER IN INSP/MAINT 1 WP 23 265 6 6 P3370232 INSTALLED BALL JOINT OR SWIVEL PN S2999-1 ON MIXTURE CONTROL CABLE FRONT AND REAR ENGINES AT TIME OF ENGINE INSTALLATION . A/C WAS TEST FLOWN AND FERRIED TO PAINT SHOP AND RETURNED. PREVIOUS TO ANY ADDITIONAL ADJUSTMENT AND WHILE IN THE CO CKPIT PERFORMING A MAINTENANCE CHECK AND OPERATING THE MIXTURE CONTROL, THE SWIVEL SEPARATED ON THE REAR ENGINE CABLE. FURTHER OPERATION, IT WAS NOTED THE FRONT ENGINE MIXTURE CONTROL BALL JOINT SWIVEL CAME APART. MFG WAS NOTIFIED. 1 H 7 2 3O 3 O A6CE E1CE 2001080100258 20010801 00258 CE 2001 8 1 2001FA0000121 1 20010711 G 2497 WIRE CESSNA 175 175 2072502 CE CONT O300 GO300* 17022 SO INST PANEL DEFECTIVE B K NONE O OTHER IN INSP/MAINT 1 NM 09 6651E 1904 56151 AIRCRAFT BROUGHT TO BE CLEAN-UP WIRING BEHIND INSTRUMENT PANEL. UPON FURTHER INSPECTION I IMMEDIATELY DISCONNECTED THE SHIPS BATTERY DUE TO THE FACT THE WIRING WAS IN SUCH A DISARRAY I COULD NOT BELIEVE IT WORKED AND IF SO WHY IT HAD NOT C AUSED A FIRE. IE: EXPOSED SOLDER SPLICES THAT WERE IN POWER FEED LINES. 4 DIFFERENT SPLICES PLUS 1 FUSE IN LESS THAN 1 6 INCHES IN THE AME 18AWG WIRE. FUSES IN LINE WITH FUSES, WIRE STRANDS TWISTED, POORLY SOLDERED AND HOOKED TO THE LINE SIDE OF MASTER SWITCH. ALL DEFECTS WERE CORRECTED AND AC APPROVED FOR RETURN TO SERVICE. 1 H 7 1 3O 3 O NT 3A17 E298 2001080100259 20010801 00259 CE 2001 8 1 2001FA0000122 1 20010621 G 2140 C3A051 HEATER BEECH 60 A60 1153604 CE LYC O541 TIO541* 41536 EA CABIN LEAKING D K NONE K FLUID LOSS IN INSP/MAINT 1 NM 08 81AG 323 323 P219 DURING PRESSURE DECAY TEST FOUND GASKETS. CANASTER A09077 AND NOZZLE 29D-28 LEAKING. REPLACED AND HEATER PASSED PRESSU RE DECAY TEST. 1 L 7 2 3O 3 O A12CE E10EA 2001080100260 20010801 00260 CE 2001 8 1 2001FA0000123 1 20010629 G 5711 5262 SPAR BBAVIA 7 7KCAB 21101P3 CE LYC O320 IO320* 41508 EA WING CRACKED G K NONE O OTHER IN INSP/MAINT 1 GL 13 86960 44674 DURING INSPECTION OF RIGHT WING, A CRACK WAS FOUND ON THE AFT SIDE OF THE FORWARD WOOD SPAR, 79 INCHES OUTBOARD FROM THE BUTT RIB. THE 5 INCH LONG, HORIZONTAL CRACK WAS LOCATED AT THE COMPRESSION MEMBER AND RAN THROUGH THE HOLES FOR THE DR AG WIRES. UNDETERMINED CAUSE. 1 H 7 1 3O 3 O A759 1E12 2001080200001 20010802 00001 SO 2001 8 2 2001FA0000128 1 20010711 G 2730 8283302 ROD PIPER PA46 PA46310P 7104605 SO ELEVATOR CONTROL CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 19 248SP 2321 468608024 ELEVATOR PUSH PULL CONTROL ROD VERY RUSTY AND PITTED. LOCATED IN TAIL SECTION WHERE MOISTURE AND CONTAMINATION ACCUMULA TE. 1 L 7 1 3O RT A25SO 2001080200138 20010802 00138 EA 2001 8 2 2001FA0000129 2 20010629 G 7310 SERVO PREAIR RSA5AD1 CESSNA 172 172S 2072439 CE LYC IO360 IO360L2A EA MCAULY 1A170 1A170E GL FUEL INJECTION MALFUNCTIONED C C ABORTED TAKEOFF R J PARTIAL RPM/PWR LOSS WARNING INDICATION TO TAKEOFF 1 SW 99 948SP 1119 70168504 172S8144 L2812651A SL029 RPM SET TO 1500 FOR PURGING FUEL VAPORS PRIOR TO TAXI, TAXI AND RUN UP WERE NORMAL. WHEN FULL THROTTLE WAS APPLIED FOR TAKE OFF THE ENGINE WOULD NOT DEVELOP FULL POWER. IT WOULD ONLY DEVELOP 2000 RPM. MAINTENANCE INSTALLED CLEAR FUEL LINE ON OUTLET LINE FROM FUEL INJECTION SERVO IAW PRECISION AIRMOTIVE TROUBLESHOOTING TECHNIQUES. THE THROTTLE AND MIXTURE WERE OPENED TO SIMULATE ENGINE OPERATION, VAPOR BUBBLES WERE OBSERVED FOR APPROXIMATELY 10 MINUTES FLOWING FROM THE FUEL SERVO. AFTER 10 MINUTES, THE LINE FILLED WITH FUEL AND THE ENGINE HAD COOLED. THE ENGINE WAS STARTED AND ALL OPERATIO N NORMAL WITH FULL POWER BEING DEVELOPED. AIRCRAFT RELEASED FOR TEST FLIGHT. TEST FLOWN SATISFACTORY. 1 H 7 1 3O 3 O NT 3A12 1E10 5 N P857 2001080200139 20010802 00139 CE 2001 8 2 2001FA0000130 1 20010629 G 7100 LW12427 CYLINDER CESSNA 172 172S 2072439 CE LYC IO360 IO360L2A EA MCAULY 1A170 1A170E GL ENGINE OVERHEATED D A UNSCHED LANDING R PARTIAL RPM/PWR LOSS CR CRUISE 1 SW 99 494SP 1116 172S8035 L2790951A SD013 PILOT REPORTED ENGINE STARTED RUNNING ROUGH IN FLIGHT AND LOOSING ALTITUDE. MADE EMERGANCY LANDING, WENT OFF END OF RUN WAY AND WENT UPSIDE DOWN. AIRCRAFT RIGHTED AND MOVED TO HANGER. MAINTENANCE FOUND #2 CYLINDER EXHAUST PUSHROD BENT IN HALF & BROKEN, THE PUSHROD HOUSING BENT AND PULLED LOOSE FROM CASE WITH SUBSIQUENT OIL LOSS. THE INTAKE PUSHROD & HOUSI NG WAS BENT. WHEN THE VALVE COVER WAS REMOVED BOTH VALVES WERE CLOSED AND NOT STUCK. THE VALVES WERE REMOVED FROM THE CYLINDER AND FELL OUT OF THE GUIDES FREELY, THEY WERE FREE OF CARBON DEPOSITES AROUND STEMS. BOTH VALVE SEATS WERE BURN ED & THE INTAKE VALVE WAS ALSO BURNED AROUND THE SEATING AREA. 1 H 7 1 3O 3 O NT 3A12 1E10 5 N P857 2001080200149 20010802 00149 CE 2001 8 2 2001FA0000131 1 20010703 G 5711 SPAR BBAVIA 7 7KCAB 21101P3 CE UNSECURE D K NONE O OTHER IN INSP/MAINT 1 SW 99 8680V 775 AIRCRAFT REGISTERED AS BELLANCA. MODEL IS 7KCAB. DESIGN NOW OWNED BY AMERICAN CHAMPION. WOOD SPAR WING INSPECTED IN AC CORDANCE WITH AD 2000-25-02. SEVERAL RIB/SPAR ATTACHMENT NAILS MISSING. PER SERVICE LETTER SL-417 THE SPAR "DAMAGE" C AUSED BY THE MISSING NAILS WAS NOT SIGNIFICANT ENOUGH TO REQUIRE REPAIR. NEW NAILS INSTALLED IN ACCORDANCE WITH INSTRU CTIONS FROM AMERICAN CHAMPION. 1 H 7 1 3O A759 2001080200150 20010802 00150 CE 2001 8 2 2001FA0000133 1 20010430 G 3110 04110591 SHOCK MOUNT CESSNA 210 210D 2073414 CE INSTR PANEL BROKEN C B EMER. DESCENT O OTHER DE DESCENT 1 SW 99 3738Y 3304 21058238 AFTER FLYING THROUGH TURBULANCE THE PILOT COULD NOT LEVEL OFF ATER A DECENT DUE TO LIMITED ELVEATOR CONTROL. A NOSE FIR ST LANDING WAS ACCOMPLISHED WITH THE AIRCRAFT/ENGINE RECEVING SUBSTANTIAL DAMAGE. INITIAL OBSERVATIONS REVEALED THE ELV EATORS ONLY GOING TO NEAR LEVEL FLIGHT POSITION. INVESTIGATION FOUND THAT THE HEADING SITUATION INDICATOR WAS MOUNTED D IRECTLY ABOVE THE CONTROL COLUMN WHICH WAS BEING HIT BY THE CONTROL COLUMN STOP. THE INSTRUMENT PANEL WAS RECONFIGURED TO ITS PRESENT LAYOUT IN 1994. THE INSTRUMENT PANEL SHOCK MOUNTS INTHE LOWER RIGHT AND LOWER CENTER WERE BROKEN. THE D ATES ON THE PANEL SHOCK MOUNTS WERE ALL PREVIOUS TO 1963, THE DATE THE AIRCRAFT WAS MANUFACTURED. 1 H 7 1 3O 3A21 2001080200172 20010802 00172 CE 2001 8 2 2001FA0000135 1 20010705 G 2421 DOFF10300FR ALTERNATOR CESSNA 172 R172G 2072421 CE CONT O360 IO360DB 17025 SO MISOVERHAULED C K NONE O OTHER IN INSP/MAINT 1 SW 99 7753L 170 R1720429 239773R DURING MAINTENANCE 100 HOUR INSPECTION, FOUND ALTERNATOR INTERNAL FAN SHIELD SEPERATED FROM FAN DUE TO SHEARED RIVITS AN D THE DRIVE SHAFT OIL SEAL WAS LEAKING. REPLACED ALTERNATOR WITH UNIT OVERHAULED BY DIFFERENT MANUFACTURER, OPERATIONAL CHECKED SATISFACTORY. 1 H 7 1 3O 3 O 3A17 E1CE 2001080200182 20010802 00182 CE 2001 8 2 2001FA0000136 1 20010705 G 3710 P10UCB86 FITTING CESSNA 182 182S 2072701 CE VACUUM SYSTEM BROKEN B D RETURN TO BLOCK J WARNING INDICATION TX TAXI/GRND HDL 1 WP 07 7260Q 16 18280957 THE PILOT REPORTED THAT THERE WAS ZERO VACUUM INDICATED ON THE GAUGE AND THAT THE HSI GYRO WOULD NOT ERECT. A VISUAL IN SPECTION BY A MAINTENANCE TECHNICIAN REVEALED THAT THE VACUUM SUPPLY LINE REDUCER FITTING WAS BROKEN IN TWO. 1 H 7 1 3O NT 3A13 2001080200184 20010802 00184 SO 2001 8 2 2001FA0000137 1 20010702 G 3260 8929103 DOWNLOCK SWITCH PIPER PA44 PA44180 7104402 SO MLG INOPERATIVE D K NONE O OTHER IN INSP/MAINT 1 SW 99 2490 4496013 WHILE CONDUCTING A SCHEDULED INSPECTION,THE TECHNICIAN DISCOVERED SEVERAL WIRES WERE BROKEN OF THE DOWN LIMIT SWITCH.THE RE WERE NO PROBLEMS REPORTED BY THE PILOT AT THIS TIME.ALSO WHEN PLACING THE AIRCRAFT ON JACKS AND PERFORMING A LANDING GEAR TEST THERE WERE NO PROBLEMS FOUND.EVERYTHING SEEMED NORMAL. WHEN THE LANDING GEAR WAS RETRACTED SEVERE TENSION OCC URED ON THE WIRES AND WERE THEREFORE PULLED FROM THE SWITCH ASSY.A PROBLEM COULD HAVE OCCURED IF ALL THE WIRES HAD BROKE N. BOTH THE LT AND RT DOWN LIMIT SWITCHES WERE REPLACED AND THE WIRES REROUTED. ATTENTION SHOULD BE PAID TO THE ROUTI NG OF THE WIRES,WHEN THE LANDING GEAR RETRACTS. 1 L 7 2 3O A19S0 2001080200187 20010802 00187 CE 2001 8 2 2001FA0000138 1 20010709 G 3242 BRAKE CESSNA 172 172M 2072418 CE MLG INOPERATIVE P D RETURN TO BLOCK O OTHER TX TAXI/GRND HDL 1 SW 99 12790 17262262 PRIOR TO TAXI THE PARKING BRAKE WAS FOUND INOP; HOWEVER, THE BRAKES OPERATED NORMALLY. THE AIRCRAFT WAS TAXIIED TO THE RUNUP AREA AND CONDUCTING THE RUNUP USING THE STANDARD BRAKES. AFTER RUNUP, THE PILOT WAS INSTRUCTED TO TAXI INTO POSITI ON AND HOLD. WHILE TAXIING INTO POSITION THE LEFT BRAKE FAILED. THE PILOT HAD THE COPILOT HID THE BRAKES ON THE RIGHT SE AT. THE LEFT BRAKE WAS INOP ALSO. THE AIRCRAFT VERRED RIGHT OFF THE APPROACH END OF THE RUNWAY STRIKING A RUNWAY LIGHT. AFTER SECURING THE ENGINE, THE PROPELLER WAS EXAMINED FOR STRIKES. ONE BLADE HAD SURFACE DAMAGE TO THE PAINT ON THE TIP. THE OTHER BLADE HAD A 3/16 INCH NICK ON THE LEADING EDGE ABOUT 2 INCHES FROM THE TIP AND THE TIP WAS BENT AFT ABOUT 1/2 1 H 7 1 3O NT 3A12 2001080200189 20010802 00189 CE 2001 8 2 2001FA0000139 1 20010709 G 3213 SA530348 PISTON CESSNA 172 172D 2072410 CE CONT O300 O300D 17022 SO STRUT CRACKED D K NONE O OTHER IN INSP/MAINT 1 EA 01 2051Y 840 17249551 24597R DURING REPAIRS TO CYCL NR 4 FOR LOW COMPRESSION FOUND 1INCH CRACK IN PISTON SKIRT STARTING AT BOTTOM OF PISTON. 1 H 7 1 3O 3 O NT 3A12 E253 2001080200194 20010802 00194 SW 2001 8 2 2001FA0000140 1 20010712 G 2810 SUMP GULSTM 680 680E 0141604 SW FUEL TANK CORRODED D K NONE O OTHER IN INSP/MAINT 1 SW 99 69278 4800 680E78150 MAIN FUEL SUMP REMOVED FROM ACFT. TO FACILITATE MAIN TANK REMOVAL FROM ACFT. VISUAL INSPECTION OF INSIDE OF PART REVEAL ED CONSIDERABLE CORROSION ON BOTTOM INSIDE SUMP. AFTER CLEANING, OBSERVED ONE AREA WHERE CORROSION THROUGH WALL TO OUTE RSKIN ON CASTING HAD ALMOST COMPLETE PENETRATION. UNABLE TO DETERMINE INTERNAL CORRODED CONDITION OF PART WHILE PART WA SINSTALLED ON ACFT. 1 H 7 2 3O 2A4 2001080200196 20010802 00196 SO 2001 8 2 2001FA0000141 2 20010426 G 7414 10682016 GEAR CONT D6LN3000 PIPER PA32 PA32RT300 7103215 SO LYC 0540 IO540K1G5D 41532 SO DISTRIBUTOR BROKEN G A UNSCHED LANDING Y J ENGINE STOPPAGE WARNING INDICATION CL CLIMB 1 EA 01 39503 32R7885224 L1795748A ON TAKE OFF AT APPROXIMATLEY 500 FEET THE ENGINE FAILED. THE AIRCRAFT LANDED IN GRASS AT END OF RUNWAY WITHOUT INCIDENT . INSPECTION SHOWED THAT BOTH DISTRIBUTOR GEARS HAD FAILED, TEETH MISSING. 1 L 7 1 3O 3 O A3SO 1E4 2001080200198 20010802 00198 EA 2001 8 2 2001FA0000142 2 20010512 G 8530 FRST14 CYLINDER LYC O720 IO720A1B 41546 EA ENGINE BROKEN B A UNSCHED LANDING D INFLIGHT SEPARATION NR NOT REPORTED 1 SW 99 278 BARREL TO HEAD SEPERATION DURING FLIGHT. 3 O 1E15 2001080200202 20010802 00202 GL 2001 8 2 2001FA0000143 1 20010713 G 3221 BUSHING CIRRUS CIRRUS SR SR20 05628AJ GL CONT O550 IO550* SO MLG LOOSE H O OTHER E VIBRATION/BUFFET TX TAXI/GRND HDL 1 EA 21 27 27 0021 0012 685745 ON LANDING, NOSE WHEEL HAD SEVERE OSCILLATION/SHIMMY. INSPECTION AFTER TAXI FOUND NOSE WHEEL FAIRING CRACKED AND TIRE D AMAGED AROUND CIRCUMFERENCE. FURTHER INSPECTION FOUND THAT THE BUSHING ON THE RIGHT BOTTOM NLG MOUNT TO THE ENGINE MOUN T SHIFTED OUT OF ITS SEAT IN THE NLG WISHBONE MOUNT CAUSING THE BOLT TO RIDE ON THE HOLE IN THE NLG WISHBONE MOUNT. WE BELIEVE THAT THE PROBLEM IS A RESULT OF POSTION/TYPE OF BUSHINGS ON ASSEMBLY. 1 H 7 1 3O 3 O NC A00009CH E3SO 2001080200204 20010802 00204 EA 2001 8 2 2001FA0000145 2 20010718 G 7313 25765362 SERVO CESSNA 172 172S 2072439 CE LYC IO360 IO360L2A EA FUEL INJECTOR FROZEN D C ABORTED TAKEOFF R J PARTIAL RPM/PWR LOSS WARNING INDICATION TO TAKEOFF 1 SW 99 949SP 1053 543 172S8145 L2812051A SECOND FLIGHT OF THE DAY, TEMP 89F, DA 9444. ENGINE START WAS DIFFICULT, TAXI AND ENGINE RUN UP NORMAL. AIRCRAFT TOOK T HE RUN WAY FOR TAKE OFF. WHEN THROTTLE WAS OPENED TO FULL POWER, ENGINE HAD POPPING NOISE AND WOULD ONLY DEVELOP 2000 RP M. TAKE OFF WAS ABORTED FOR LOW POWER. A CLEAR LINE WAS INSTALLED FROM THE FUEL INJECTION SERVO TO THE FLOW DIVIDER IAW PRECISION AIRMOTIVE TROUBLE SHOOTING MANUAL AND EXCESSIVE VAPOR IN THE LINE WAS DISPLACING THE FUEL WHEN THE ENGINE WAS RUN. THE ENGINE WAS ALLOWED TO COOL COMPLETELY AND RESTARTED, NO VAPOR WAS DETECTED AND ALL OPERATION WAS NORMAL INCLUD ING FUEL FLOW WITH THE ENGINE DEVELOPING FULL POWER. AIRCRAFT TEST FLOWN AND RELEASED. 1 H 7 1 3O 3 O NT 3A12 1E10 2001080200206 20010802 00206 SO 2001 8 2 2001FA0000146 2 20010724 G 8520 646778 CONNECTING ROD CONT O520 IO520C 17032 SO ENGINE GOUGED B K NONE O OTHER IN INSP/MAINT 1 SW 99 3 816945R FACTORY REBUILT ENGINE WITH 3.3 TTIS WAS BEING DISASSEMBLED FOR INSPECTION DUE TO A PROPELLER STRIKE. ONE OF THE #6 CON NECTING ROD BOLTS COULD NOT BE REMOVED WITH REASONABLE PRESSURE AND HAD TO BE DRIVEN OUT OF THE CAP. INSPECTION OF THE BOLT REVEALED THAT A BURR AND EVIDENCE OF GALLING HAD OCCURRED ON THE SHANK AT THE POINT WHERE ROD AND CAP PARTING SURFA CES MEET. THE CAP WAS DAMAGED WITH SIGNIFICANT GOUGING WHERE THE BOLT HAD TO BE DRIVEN OUT LEAVING IT UNSERVICEABLE. 3 O E5CE 2001080200208 20010802 00208 SW 2001 8 2 2001FA0000149 1 20010728 G 3246 40041 WHEEL AIRTRC AT300 AT301 0390103 SW MLG FATIGUED G C ABORTED TAKEOFF D INFLIGHT SEPARATION TO TAKEOFF 1 GL 21 4361S 5100 3010041 DURING TAKEOFF, RIGHT MAIN WHEEL HALF (OUTBOARD) SEPARATED. PILOT UNABLE TO REGAIN CONTROL AND WENT IN ROAD DITCH AND LA NDED INVERTED. MINOR INJURY TO PILOT. WHEEL NUT, BEARING AND SPACER WERE STILL ON AXLE UPON ARRIVAL AT ACCIDENT SCENE. O UTER BEARING RACE HAD PULLED THROUGH WHEEL HALF RACE SHOULDER AND ALL 9 WHEEL BOLTS WERE EITHER BROKE UNDER TENSION OR H AD NUTS PULLED OFF BOLTS LEAVING BOLTS INTACT WITH NUT THREADS STILL EMBEDDED IN BOLT THREADS. CAUSE OF WHEEL FAILURE UN KNOWN AT THIS TIME. IMPROPER WHEEL ASSEMBLY OR INSTALLATION OF OVERSIZE TIRES AND TOO MUCH AIR PRESSURE ARE POSSIBILITIE S OF FAILURE. 1 L 7 1 3R A9SW 2001080200210 20010802 00210 CE 2001 8 2 2001FA0000150 1 20010731 G 5712 57222062 RIB CESSNA 441 441 2076020 CE RT CENTER WING CRACKED B K NONE O OTHER IN INSP/MAINT 1 SW 99 2624D 4196 4410122 DURING A SCHEDULED INSPECTION, IT WAS NOTED THAT THE RH CENTER WING CANTED RIB CAP P/N: 5722206-2 (RH CWS26.85) HAD A VI SUALLY SUSPECT AREA ALONG THE BEND RADIUS BETWEEN THE CENTER WING MAIN SPAR (FS177.45) AND FS188.95". FURTHER INSPECTION USING FLUORESCENT PENETRANT REVEALED (2) CRACKS IN THE RADIUS, THE ORIGINAL SUSPECT AREA (FS185.35) AND ONE STARTING AT THE MAIN SPAR (FS177.45) PROTRUDING AFT. BOTH CRACKS ARE APPROXIMATELY .75" LONG. AFTER REMOVAL OF THE RIB CAP, CLOSE E XAMINATION OF THE PART REVEALED THAT THE CAP WAS MANUFACTURED SO THAT THE BEND WAS PARALLEL WITH THE GRAIN OF THE METAL INSTEAD OF PERPENDICULAR WHICH COULD RESULT IN THIS TYPE OF FAILURE. CESSNA CURRENTLY DOES NOT HAVE ANY SPECIFIC INSPECT 1 L 7 2 3T RT A28CE 2001080200213 20010802 00213 CE 2001 8 2 2001FA0000151 1 20010731 G 2800 FITTING LEAR 25 25B 5170511 CE DEFUEL SYSTEM CLOGGED B K NONE O OTHER IN INSP/MAINT 1 SW 99 751GA 122 WHILE DEFUELING THE AIRCRAFT PREPATORY TO PAINTING, IT WAS DISCOVERED THAT NO FLOW COULD BE ACHIEVED THROUGH THE RIGHT D EFUEL FITTING. THE DEFUEL WAS ACCOMPLISHED BY TRANSFERRING ALL OF THE FUEL TO THE LEFT TANK AND REMOVING IT THROUGH THA T VALVE. WHEN WE OPENED THE RIGHT TANK A SHOP RAG WAS FOUND PLUGGING THE DEFUEL PORT. IT HAD OBVIOUSLY BEEN LEFT IN TH E TANK DURING PRIOR MAINTENANCE. 2 L 7 2 4J A10CE 2001080200229 20010802 00229 SO 2001 8 2 2001FA0000154 2 20010426 G 7414 10682016 GEAR CONT D6LN3000 PIPER PA32 PA32RT300 7103215 SO LYC 0540 IO540K1G5D 41532 SO HARTZL HCC2Y HCC2YK1 GL DISTRIBUTOR BROKEN G A UNSCHED LANDING Y G ENGINE STOPPAGE MULTIPLE FAILURE TO TAKEOFF 1 EA 01 39503 D040001GR 32R7885224 L1795748A CH32104A AFTER TAKE OFF AT APPROX 500FT AGL, THE ENGINE STOPPED RUNNING. AIRCRAFT MADE EMERGENCY LANDING IN A FIELD WITH NO DAMA GE OR INJURIES. INSPECTION OF MAGNETO REVEALED THAT BOTH DISTRIBUTOR GEARS HAD FAILED. MAGNETO WAS REBUILT BY TCM 04/0 7/2000 AND INSTALLED ON 5/12/2000. 1 L 7 1 3O 3 O A3SO 1E4 5 C P920 2001080200231 20010802 00231 EA 2001 8 2 2001FA0000155 2 20010516 G 8520 SL13S19646 GEAR PIPER PA30 PA39 7103902 SO LYC O320 IO320B1A 41508 EA CRANKSHAFT DAMAGED B K NONE O OTHER IN INSP/MAINT 1 GL 21 DURING COMPLICANCE WITH AD 96-09-10 - COMPLIED ALSO WITH AD 91-14-22 CRANKSHAFT GEAR RETAINING BOLT. ORDERED NEW CRANKS HAFT GEARS PN SL13S19464 FOR LH AND RH ENGINES. WHEN INSTALLING NEW GEARS IT WAS DISCOVERED ONE HAD THE TIMING MARK ON T HE CORRECT TOOTH AND THE OTHER GEAR HAD THE TIMING MARK INSTALLED ONE TOOTH OFF. THESE ARE THE FIRST OF THESE GEARS WE HAVE PURCHACED. NOTIFIED SUPERIOR AIR PARTS 5-15-2001. SUGGEST ALL OPERATORS USING THIS GEAR LOOK FOR PROPER TIMING MA RKS ON THE GEAR BEFORE INSTALLATION- IMPROPERLY TIMED GEARS TRAINS COULD RESULT IN ENGINE DAMAGE AND STOPPAGE. 1 L 7 2 3O 3 O A1EA 1E12 2001080200236 20010802 00236 EA 2001 8 2 2001FA0000156 2 20010514 G 7314 RG9570R1 PUMP PWA PT6 PT6A6 52043 EA ENGINE LEAKING B D RETURN TO BLOCK K FLUID LOSS TX TAXI/GRND HDL 1 SW 99 451DM 164 PCEPRO212 PILOT REPORTED FUEL SMELL IN CABIN, LATER NOTIFIED FUEL LEAKING FROM ENGINE COMPARTMENT. TECHNICIAN FOUND LOW PRESSURE F UEL PUMP LEAKING AT RELIEF AND SCREWS LOOSE. PUMP REMOVED AND REPLACED WITH NEW UNIT. (REFERENCE TEXTRON LYCOMING AD 98- 18-12 AND TEXTRON LYCOMING SERVICE BULLETIN 529 DEALS WITH SAME PROBLEM FOUND WITH THIS PUMP OF SAME CRANE/LEARROMEC "AN " ROTARY FUEL PUMP MODEL SERIES.) 3 T E4EA 2001080200239 20010802 00239 GL 2001 8 2 2001FA0000157 3 20010517 G 6110 SNAP RING BEECH 58 58 1152740 CE CONT O550 IO550C SO MCAULY 3AF32C 3AF32C512 GL BLADE TO HUB DAMAGED B K NONE P NO WARNING INDICATION IN INSP/MAINT 1 SO 11 818JC 59 59 TH1620 L676535 L901873 THE AFOREMENTIONED AIRCRAFT ARRIVED FOR ENGINE OIL & FILTER CHANGE. UPON COMPLETION OF SERVICE, A PRE-ENGINE RUN / WALK AROUND INSPECTION WAS PERFORMED. DURING THIS WALK AROUND INSPECTION THERE WAS A CONSIDERABLE AMOUNT OF EXCESSIVE PLAY NO TED IN ONE OF THE RT PROPELLER BLADES. REMOVED THE RT PROPELLER SPINNER ASSEMBLY FOR FURTHER INVESTIGATIONS AND NOTED TH E SNAP RING THAT SECURES THE BLADE INTO THE PROPELLER HUB ASSEMBLY TO BE PARTIALLY INTACT WITH A SMALL PORTION ACTUALLY SECURING BLADE IN THE HUB ASSEMBLY. THE PROPELLER WAS IMMEDIATELY REMOVED AND ROUTED TO THE PREVIOUS OVERHAUL FACILITY F OR INSPECTION AND REPAIR. PROPELLER TSO: 51.9.PROBABLE CAUSE: IT APPEARS THAT THE SECURING SNAP RING WAS NOT CORRECTLY 1 L 7 2 3O 3 O 3A16 E3SO 5 C P22EA 2001080200242 20010802 00242 CE 2001 8 2 2001FA0000158 1 20010522 G 3010 2H598 VALVE CESSNA 310 T310R 2074246 CE DEICE SYSTEM INOPERATIVE D K NONE O OTHER IN INSP/MAINT 1 SW 99 310KH 310R1507 DURING INSTALLATION OF AIRCRAFT SURFACE KNOWN ICE KIT FOUND SURFACE DEICE FLOW VALVE #2H59-8 (MFG. BY PARKER HANNIFIN, A IRBORNE) S/N 9AT-83 TO CAUSE UNCOMMANDED DEICE BOOT INFLATIONS. INSTALLED SECOND NEW VALVE S/N 9AT-91 OBTAINED FROM A D IFFERENT DISTRIBUTOR WITH SAME RESULTS. SPOKE WITH AIRBORNE TECH SUPPORT AND WAS GIVEN A MANUFACTURES POST ASSEMBLY INS PECTION TEST PROCEDURE. TESTED THREE MORE VALVES FROM VARIOUS DISTRIBUTORS S/N 9AT-85, 6AT-48, 6AT-55 AND VARIFIED BOTH VISUALLY AND OPERATIONALLY THAT ALL WERE DEFECTIVE. DEFECT CAN BE SEEN AT TOP OF VALVE WHERE SOLENOID PLATE IS RIVETED T O BODY. A LARGE GAP EXISTS ALLOWING PRESSURE AIR ESCAPE CAUSING VALVE ACTUATION. NO ADDITIONAL SUPPLY OF VALVES AVAIL 1 L 7 2 3O 3A10 2001080200244 20010802 00244 CE 2001 8 2 2001FA0000159 1 20010501 G 8120 4709089011 WASTEGATE VALVE CESSNA 206 TU206G 2073357 CE CONT O520 TSIO520M 17040 SO ENGINE EXHAUST UNDERTORQUED D K NONE O OTHER IN INSP/MAINT 1 SW 99 FOUND THE 7 ACTUATOR TO BYPASS VALVE MOUNTING BOLTS (REF. GARRETT MANUAL TP30-4001-1 PG. 10-11 ITMES NR 7 AND 10) WITH L ITTLE TO NIL MEASURABLE TORQUE. THIS IS THE SECOND ACTUATOR ON WHICH WE HAVE DISCOVERED THIS PROBLEM. DURING INSTALLA TION INSPECTION, A WRENCH JUST HAPPENED TO BE PLACED ON THESE BOLTS WHICH WERE THEN OBSERVED TO BE LOOSE. 1 H 7 1 3O 3 O A4CE E8CE 2001080200245 20010802 00245 EA 2001 8 2 2001FA0000160 2 20010604 G 8530 RL499751A CYLINDER LYC O360 IO360B1E 41514 EA ENGINE SEPARATED G O OTHER Y ENGINE STOPPAGE CL CLIMB 1 SW 01 3708T 3500 THE NUMBER ONE CYLINDER HEAD SEPERATED FROM THE CYLINDER RESULTING IN AN ACCIDENT DESTROYING THE AIRCRAFT AND INJURING T HE PILOT. NOTE: THE ENGINE EXCEEDED THE MANUFACTURERS CALENDER TBO OF 12 YEARS AND 2000 HOURS. 3 O 1E10 2001080200246 20010802 00246 EU 2001 8 2 2001FA0000161 1 20010608 G 7100 UAE651 SEAL AMD FALCON FALCON20 2730103 EU LEFT ENG PYLON BROKEN C E ENGINE SHUTDOWN L NO TEST IN INSP/MAINT 1 EA 01 9728 325 WHILE PERFORMING POST MAINTENANCE ENGINE RUN FOR AN UNRELATED ACTION, THE LEFT ENGINE FAILED TO RESPOND TO THROTTLE MOVE MENT. UPON FURTHER INVESTIGATION THE LEFT ENGINE TORSION TUBE ASSY (P/N MY20571-53810) WAS FOUND BROKEN APPART INSIDE TH E ENGINE PYLON BETWEEN FUSELAGE STATION FR31 AND FR32. THE BREAK WAS LOCATED AT THE INBOARD SECTION OF THE TORSION TUBE IDENTIFIED AS A "SEAL" AS SHOWN IN FALCON 20 IPC CHAP, 76-10-20, PAGE 50-0, ITEM 50, P/N UAE651. INTEGRATED INTO THIS PART IS A METAL "UNIVERSAL-JOINT TYPE CONFIGURATION WHICH HAD CRACKED COMPLETELY THROUGH. 2 L 7 2 4F RT A7EU 2001080800318 20010808 00318 SW 2001 8 8 2001FA0000163 2 20010803 G 8520 4109 STUD WACO YMF YMF 9600412 EA JACOBP R755 R755* 35006 SW NR 4 CYLINDER BROKEN D K NONE O OTHER IN INSP/MAINT 1 WP 07 53WC 252 FSC062 FOUND BROKEN CYLINDER BASE STUD ON NR 4 CYLINDER. AFTER REMOVING BROKEN STUD, FOUND TWO OTHERS BENT, SENT STUDS FOR EV ALUATION TO SEE IF THEY MET DESIGN INTENT. THE STUDS DID NOT MEET SPECIFICATIONS. 1 Q 7 1 3R 3 R ATC542 TC237 2001080700004 20010807 00004 2001 8 7 2001FA0000164 4 20010425 G 6113 055032110 BULKHEAD CESSNA 172 172S 2072439 CE LYC IO360 IO360L2A EA MCAULY 1A170 1A170E GL PROP SPINNER CRACKED D K NONE O OTHER IN INSP/MAINT 1 AL 03 430CP 42 172S8692 L2938051A UPON A POSTFLIGHT INSPECTION, THE PROPELLER SPINNER BULKHEAD ASSEMBLY WAS DISCOVERED CRACKED. THE CORNER PORTION OF THE BULKHEAD WAS COMPLETELY RIPPED AWAY AND THE EDGE OF THE SPINNER WAS PEELING UP. PROBABLE CAUSE: MANUFACTURING DEFECT SUSPECTED. 1 H 7 1 3O 3 O NT 3A12 1E10 5 N P857 2001080700003 20010807 00003 CE 2001 8 7 2001FA0000165 1 20010804 G 2460 727725 CIRCUIT BREAKER BEECH 1900 1900D 1154162 CE COCKPIT FAILED B A UNSCHED LANDING B G SMOKE/FUMES/ODORS/SPARKS MULTIPLE FAILURE CR CRUISE 1 SW 99 84802 UE53 DURING FLIGHT, SMOKE WAS OBSERVED COMING FROM THE REAR OF A CB PANEL. CB'S PULLED PROGRESSIVELY TO IDENTIFY ONE CAUSING SMOKE. OTHERS RESET AFTER ISOLATING FAULTY ONE. AIRCRAFT LANDED. ON GROUND, FAILED CB REPLACED. FURTHER TROUBLE SHOOTING REVEALED. POWER WIRE TO WING ICE INSPECTION LIGHT CHAFFED AGAINST STRUCTURE NEAR LIGHT ASSY. WIRE REPAIRED. 2 L 7 2 4T RT A24CE 2001080800319 20010808 00319 GL 2001 8 8 2001FA0000166 2 20010531 G 7323 2526146 BEARING HONEYWELL SKRSKY S76 S76 8143010 NE ALLSN 250C 250C20B 03013 GL PT GOVERNOR DISINTEGRATED Z K NONE O OTHER IN INSP/MAINT 1 WP 23 PTYDC 652 BR31687 760220 SPOOL BEARING ASSEMBLY DISINTEGRATED. INNER AND OUTER RACES ARE ALL THAT REMAINS. NEARLY ALL EVIDENCE OF BALLS FROM BE ARING MISSING. REASON FOR FAILURE POSSIBLY DUE TO BEARING BALL RETAINER FAILURE. 1 G 7 2 3U 3 U H1NE E4CE 2001080800321 20010808 00321 EA 2001 8 8 2001FA0000167 2 20010201 G 8520 SL13885 MAIN BEARING CESSNA 185 A185E 2072818 CE LYC O540 TIO540* 41532 EA ENGINE DELAMINATED D K NONE O OTHER IN INSP/MAINT 1 WP 19 694BK 54 1851582 L474361A DURING SCHEDULED OIL AND FILTER CHANGE ON ENGINE REFERENCED, FOUND BEARING PARTICLES WITHIN OIL FILTER. DISASSEMBLED EN GINE TO FIND FRONT MAIN BEARING EXHIBITING DELAMINATION OF THE LINER SURFACE. FAULTY MANUFACTURING OF BEARING IS SUSPEC T. 1 H 7 1 3O 3 O 3A24 E14EA 2001081600096 20010816 00096 CE 2001 8 16 2001FA0000168 1 20010803 G 3230 358250944 PLUNGER BEECH 56 56TC 1152736 CE LYC O541 TIO541E1B4 41536 EA NLG FAILED G A UNSCHED LANDING O OTHER TO TAKEOFF 1 SW 01 5455U TG22 PILOT DEPARTED SANTA FE, NM AND RETRACTED GEAR. THE TOWER NOTICED THE NOSE GEAR STILL HANGING DOWN. PILOT LOWERED GEAR , THE MAINS LOCKED DOWN BUT THE NOSE DID NOT LOCK DOWN. PILOT LANDED AND THE NOSE GEAR COLLAPSED. THE AFT END ATTACH F ITTING OF THE PLUNGER ASSEMBLY (P/N 35-825094-4) FAILED. TOTAL TIME AND CYCLES ON THE NOSE GEAR IS UNKNOWN. 1 L 7 2 3O 3 O 3A16 E10EA 2001080800326 20010808 00326 2001 8 8 2001FA0000169 4 20010710 G 2561 KS9P0Z01 LIFE VEST CABIN FAILED B KQ1R K NONE O OTHER IN INSP/MAINT 1 EA 07 LIFE VEST FAILED MFG RECOMMENDED 2 PSI INFLATION TEST I/A/W MANUAL 25-60-1 DOM: NOVEMBER 1982 2001080800329 20010808 00329 SO 2001 8 8 2001FA0000170 1 20010706 G 7722 481389 PROBE PIPER PA46 PA46350P SO LYC O540 TIO540AE2A 41532 EA TIT SYSTEM FAILED D O OTHER O OTHER NR NOT REPORTED 1 WP 15 135CC 49 4636192 L1012361A PART FAILED IN 49 HOURS. THIS PART IS REPLACED DURING AN AD REQUIREMENT EVERY 250 HOURS BUT ONLY LASTED 49 HOURS. 1 L 7 1 3O 3 O RT A25SO E14EA 2001080800333 20010808 00333 CE 2001 8 8 2001FA0000171 1 20010706 G 2810 S23591 CHECK VALVE CESSNA 172 172R 2072401 CE LT FUEL TANK MISINSTALLED C O OTHER K FLUID LOSS NR NOT REPORTED 1 WP 09 361ES 1731 17280011 WHEN FUEL TANKS WERE FILLED TO ABOVE 35 GALLONS, HIGH AMBIENT TEMPERATURE CAUSED FUEL TO LEAK FROM VENT TUBE. REMOVED L EFT FUEL BAY INSPECTION PLATE AND FOUND THAT THE FUEL VENT TUBE INVERTED CHECK VALVE S2359-1 ALSO INVERTED FROM FACTORY. ROTATED 180 DEGREES TO CURRENT POSITION. INSPECTION PLATE SHOWED NO SIGN OF EVER BEEN REMOVED. 1 H 7 1 3O NT 3A12 2001080800336 20010808 00336 CE 2001 8 8 2001FA0000172 1 20010615 G 5210 051701912 HINGE PIN CESSNA 172 172R 2072401 CE CABIN DOOR BROKEN B K NONE O OTHER IN INSP/MAINT 1 EA 07 172WY 1722 17280334 DURING A PHASE II INSPECTION, FOUND LEFT AND RIGHT LOWER CABIN DOOR HINGE PINS, BROKEN. IT APPEARS THAT THE CABIN DOOR WAS NOT INSTALLED PROPERLY FROM THE FACTORY, CAUSING UNDUE STRAIN ON LOWER HINGES. 1 H 7 1 3O NT 3A12 2001080800339 20010808 00339 WP 2001 8 8 2001FA0000173 1 20010607 G 6510 DRIVE SHAFT ROBSIN R22 R22 7640102 WP TAIL ROTOR FAILED F YV3R K NONE O OTHER TX TAXI/GRND HDL 1 WP 05 DURING RUN-UP PRIOR TO TAKE-OFF, AN R22 TAIL ROTOR DRIVE CUT LOOSE AND SEVERED THE TAIL BOOM. HELICOPTER WAS ABOUT TO F LY TO A MAINTENANCE FACILITY FOR 100 HOUR INSPECTION. PRELIMINARY SURVEY INDICATES THAT THE INCIDENT WAS INITIATED BY T HE TAIL ROTOR DRIVE SHAFT DAMPER BREAKING OFF INSIDE THE TAIL BOOM. THIS ALLOWED THE DRIVE SHAFT TO WHIP, FRACTURE, AND CUT OFF THE TAIL BOOM. 1 G 7 1 3O H10WE 2001080800340 20010808 00340 EA 2001 8 8 2001FA0000174 1 20010601 G 4920 32020725 CHECK VALVE CNDAIR CL600 CL6002B16 1900305 EA GE CF34 CF341A NE APU DAMAGED D K NONE O OTHER IN INSP/MAINT 1 SW 05 604MU 5406 DURING REPLACEMENT OF THE CHECK VALVE, FOUND PIECES OF CHECK VALVE FLAPPERS, REPLACED WITH PN 320-2832-1-1 SN 635 OPERAT IONAL CHECKED SATISFACTORY. NOTE: ALL PIECES REMOVED. 2 L 7 2 4F 4 F RT A21EA E15NE 2001080800341 20010808 00341 CE 2001 8 8 2001FA0000175 1 20010530 G 7120 241302411 BRACKET CESSNA 172 172RG 2072438 CE LYC O360 VO360* 41514 EA ENGINE MOUNT CRACKED D K NONE O OTHER IN INSP/MAINT 1 GL 11 9578B 6324 172RG0895 DURING ENGINE CHANGE, THE ENGINE MOUNT WAS REMOVED FOR INSPECTION. MOUNT WAS REMOVED FOR INSPECTION. THE FIREWALL ATTA CH POINTS FOR THE ENGINE MOUNT WERE THEN INSPECTED. THE UPPER LEFT BRACKET WAS FOUND CRACKED AT THE ENGINE MOUNT BOLT H OLE. THE BRACKET INBOARD 2 RIVETS THAT ATTACH IT TO THE LONGERON HOT SECTION WERE MISSING. SUSPECT THIS CAUSED THE CRA CK. 1 H 7 1 3O 3 O 3A17 1E1 2001080800342 20010808 00342 SO 2001 8 8 2001FA0000176 1 20010627 G 3233 SFA2325 ACTUATOR PIPER PA32 PA32RT300T 7103216 SO LYC O540 TIO540* 41532 EA MLG LEAKING D K NONE K FLUID LOSS NR NOT REPORTED 1 WP 23 36202 55 32R7887028 L5351UA ACTUATOR LEAKS FLUID FROM SHAFT SEAL. SEAL PN 762-084 WAS FOUND SPLIT ON I.D. 1 L 7 1 3O 3 O A3SO E14EA 2001081000155 20010810 00155 EA 2001 8 10 2001FA0000177 2 20010713 G 8540 LW10284 GEAR PIPER PA31 PA31350 7103110 SO LYC O540 LTIO540* 41533 EA ENGINE BROKEN B DECR O OTHER O OTHER NR NOT REPORTED 1 GL 19 3556F 883 318052066 ONE TOOTH ON GEAR SEPARATED AND LODGED BETWEEN CRANKSHAFT GEAR AND OIL PUMP HOUSING. THIS CAUSED THE REMAINING TEETH OF THE CRANKSHAFT GEAR TO ROUND OFF AND DISENGAGE FROM THE OTHER GEARS. THIS ALSO CAUSED 2 IDLER GEARS AND THE OIL PUMP D RIVE GEAR TO SHEAR SEVERAL TEETH AS WELL. 1 L 7 2 3O 3 O A20SO E14EA 2001081000156 20010810 00156 SW 2001 8 10 2001FA0000178 1 20010611 G 3233 1020004 ACTUATOR MOONEY M20 M20M 5870222 SW LANDING GEAR FAILED D O OTHER J WARNING INDICATION NR NOT REPORTED 1 GL 09 321JL 741 270162 ACTUATOR FAILED BOTH MANUALLY AND ELECTRICALLY RESULTING IN A GEAR UP LANDING. 1 L 7 1 3O RT 2A3 2001081000158 20010810 00158 CE 2001 8 10 2001FA0000179 1 20010808 G 7160 05521644 AIR BOX CESSNA 172 172N 2072434 CE LYC O320 O320* 41508 EA ENGINE DAMAGED B EL6R K NONE O OTHER IN INSP/MAINT 1 EA 23 737MP 17269524 NOTED: DURING ANNUAL INSPECTION, CARBURETOR AIR BOX OUTLET/INLET FOR CARBURETOR HEAT SWEDGED ONTO AIR BOX. ROUND METAL FLANGE VIBRATING AND CHAFING WHERE SWEDGING DONE. GETS LOOSE AND CHAFES ITSELF TO PIECES. COULD EVENTUALLY BREAK, ALL OWING HOSE TO FALL OFF AND CARBURETOR TO INGEST THIN PIECES OF METAL. 1 H 7 1 3O 3 O NT 3A12 E274 2001081000159 20010810 00159 NE 2001 8 10 2001FA0000180 2 20010709 G 7321 FUEL CONTROL CESSNA 500 500CESSNA 2076602 CE PWA JD15 JT15D1A NE RT ENGINE MALFUNCTIONED D A UNSCHED LANDING R PARTIAL RPM/PWR LOSS CL CLIMB 1 EA 07 88GJ 5000155 PCE76335 DURING A CLIMB THROUGH FL 290, THE RIGHT ENGINE FAN SPEED DECREASED TO 82 PERCENT. ENGINE IGNITION WAS SELECTED ON TO N O EFFECT. AN EMERGENCY WAS DECLARED AND A SAFE LANDING WAS MADE. SUSPECT THAT THE FUEL CONTROL UNIT MALFUNCTIONED. 1 L 7 2 4F 4 F A22CE E25EA 2001081000161 20010810 00161 EA 2001 8 10 2001FA0000181 2 20010516 G 8550 06B23072 GASKET CESSNA 172 172N 2072434 CE LYC O320 O320H2AD 41508 EA ENGINE DEFECTIVE D O OTHER K J FLUID LOSS WARNING INDICATION NR NOT REPORTED 1 WP 19 737TC 17269654 L446076 AD 200-18-23 WAS C/W BY INSTALLING NEW GASKET PT 06B23072 UNDER OIL FILTER ADAPTER PLATE. WITHIN 34 HOURS, GASKET BLEW OUT AND ALL THE OIL WAS BLOWN OUT. AIRCRAFT RETURNED TO AIRPORT SAFELY. INSPECTION OF GASKET REVELED THAT THE RUBBER G ASKET HAD DISSOLVED AND BECAME VERY SOFT. A NEW GASKET WAS INSTALLED AS PER INSTRUCTIONS IN THE SB 543A, NO FURTHER PRO BLEMS HAVE BEEN ENCOUNTERED WITH THIS AIRCRAFT. 1 H 7 1 3O 3 O NT 3A12 E274 2001081000167 20010810 00167 CE 2001 8 10 2001FA0000182 1 20010614 G 3710 653487 GASKET CESSNA 182 182S 2072701 CE LYC O540 IO540AB1A5 EA VACCUUM PUMP MISSING D K NONE K FLUID LOSS IN INSP/MAINT 1 EA 25 132ME 276 18280690 L2728048A WHILE PERFORMING AN ANNUAL INSPECTION ON THIS AIRCRAFT, AND OIL LEAK WAS NOTICED COMING FROM THE LOWER VACUUM PUMP DRIVE PAD. FURTHER INSPECTION REVEALED THAT THE GASKET FOR THE PUMP WAS MISSING. A NEW GASKET WAS INSTALLED AND A LEAK CHEC K WAS PERFORMED. 1 H 7 1 3O 3 O NT 3A13 1E4 2001081000187 20010810 00187 EA 2001 8 10 2001FA0000185 1 20010423 G 2750 FLAP BLANCA 1413 14132 1201004 EA FRNKLN 6A4150 6A4150B3 27024 EA LT WING DEPARTED C O OTHER D INFLIGHT SEPARATION AP APPROACH 1 WP 07 74285 1398 13505 LT FLAP SEPARATED FROM A/C AT ABOUT 500 FT WHILE TURNING DOWNWIND TO AIRPORT. A/C WAS BEING CONFIGURED FOR LANDING AT TH E TIME OF SEPARATION. 80 MPH GEAR DOWN AND THE FLAP HANDLE WAS PULLED FOR FULL FLAP. AN IMPULSE WAS FELT IN THE HANDLE W HICH I FIRST THOUGHT WAS A BROKEN FLAP CABLE AND IMMEDIATELY RETRACTED THE FLAPS OR IN THIS CASE THE FLAP. THE A/C WAS S TABLE AND CONTROLLABLE SO MORE POWER WAS ADDED AND LANDED FASTER THAN NORMAL. MOISTURE HAD COLLECTED IN THIS AREA AND CO MPROMISED THE WOOD AND GLUE CAUSING THE FAILURE OF THE OUTBOARD HINGE RIB, INSPECTION AT THIS AREA IS ONLY POSSIBLE BY C UTTING A HOLE. THE INBOARD RIB OF THE FLAP FAILED, THIS WAS SECONDARY AFTER THE OUTBOARD HINGE SEPARATED FROM THE WING. 1 L 7 1 3O 3 O A773 E238 2001081600098 20010816 00098 CE 2001 8 16 2001FA0000186 1 20010809 G 5712 57222062 RIB CESSNA 441 441 2076020 CE RT WING CRACKED B K NONE O OTHER IN INSP/MAINT 1 AL 05 441DB 4410300 DURING A SCHEDULED INSPECTION THE LEFT AND RIGHT CANTED RIB CAPS P/N 5722206-1 AND 5722206-2 WERE FOUND CRACKED APPROXIM ATELY 1 INCH BEHIND THE FORWARD SPAR. WHILE ACCOMPLISHING THE REPAIR TO THIS AREA, ANOTHER CRACK WAS FOUND IN THE LEFT WING/FUSELAGE CLOSEOUT P/N 6720001-3. THE CLOSEOUT CANNOT BE SEEN UNTIL THE WING FAIRINGS ARE REMOVED, THUS IT CANNOT B E SEEN DURING NORMAL INSPECTION. 1 L 7 2 3T RT A28CE 2001081600099 20010816 00099 CE 2001 8 16 2001FA0000187 1 20010810 G 5720 ANGLE CESSNA 441 441 2076020 CE WING CRACKED C K NONE O OTHER IN INSP/MAINT 1 AL 05 441JC 4410156 DURING A SCHEDULED INSPECTION, THE LEFT CANTED RIB CAP P/N 5722206-1 WAS FOUND CRACKED APPROXIMATELY 1 INCH AFT OF THE F ORWARD WING SPAR. WHILE REPAIRING THIS CRACK THE UPPER WING TO FUSELAGE CLOSEOUT ANGLE P/N 5720001-3 WAS FOUND CRACKED. THESE CLOSEOUT ANGLES CANNOT BE SEEN UNLESS THE WING TO FUSELAGE FAIRINGS ARE REMOVED AND THUS ARE NEVER INSPECTED DUR ING NORMAL MAINTENANCE. 1 L 7 2 3T RT A28CE 2001081600100 20010816 00100 SO 2001 8 16 2001FA0000188 1 20010810 G 7430 103572101 IGNITION SWITCH PIPER PA28 PA28180 7102808 SO LYC O360 O360A4A 41514 EA INSTRUMENT PANEL FAILED D K NONE O OTHER TX TAXI/GRND HDL 1 SO 06 A NEW SWITCH WAS INSTALLED TO COMPLY WITH AD 76-07-12. THE NEW SWITCH WOULD NOT ENERGIZE THE STARTER CONTACTOR. A SECO ND SWITCH WAS ORDERED. 1 L 7 1 3O 3 O 2A13 E286 2001082000031 20010820 00031 EA 2001 8 20 2001FA0000189 2 20010720 G 8520 72877 LIFTER PIPER PA28 PA28140 7102802 SO LYC O320 O320E3D 41508 EA ENGINE BROKEN D K NONE O OTHER IN INSP/MAINT 1 NM 07 8715E 2600 287625149 L4434627A DURING TEAR DOWN FOR OVERHAUL A PIECE OF METAL WAS FOUND IN OIL SUMP. FURTHER INSPECTION FOUND THAT THE HEAD OF LIFTER BODY FOR NR 1 CYLINDER EXHAUST VALVE WAS HALF GONE. (PIECE IN OIL SUMP) FROM WEAR ON REMAINING PART, APPEARS THAT IT H AD BEEN THAT WAY FOR SEVERAL HOURS. PART HAD AT LEAST 2600 HOURS SINCE OVERHAUL. 1 L 7 1 3O 3 O 2A13 E274 2001082000032 20010820 00032 EA 2001 8 20 2001FA0000190 2 20010720 G 8530 SL17540 EXHAUST VALVE PIPER PA28 PA28140 7102802 SO LYC O320 O320E3D 41508 EA ENGINE BROKEN D A UNSCHED LANDING R PARTIAL RPM/PWR LOSS CR CRUISE 1 NM 07 8715E 2600 2600 287625149 L4434627A AIRCRAFT WAS ON A TRAINING FLIGHT, STEM BROKE AT VALVE HEAD. ENGINE LOST POWER BUT WAS ABLE TO LAND. ENGINE CHANGED. PROBABLE CAUSE OF BREAKAGE: OLD AGE. 1 L 7 1 3O 3 O 2A13 E274 2001082000033 20010820 00033 CE 2001 8 20 2001FA0000191 1 20010817 G 7112 17500117 SHROUD CESSNA 172 172N 2072434 CE LYC O320 O320* 41508 EA ENGINE CHAFED B EL6R K NONE O OTHER IN INSP/MAINT 1 EA 23 737MP 17269524 NOTED: DURING ANNUAL INSPECTION ON NUMEROUS AIRCRAFT, SCREEN INSIDE OF CARB HEAT SHROUD VIBRATING AND CHAFING ITSELF TO PIECES BE ALLOWED TO BE SUCK INTO THE CARB INLET. (SHROUD LOCATED ON CYLINDER STACK ASSEMBLY WITH CLAMPS). 1 H 7 1 3O 3 O NT 3A12 E274 2001082100025 20010821 00025 2001 8 21 2001FA0000192 4 20010820 G 2561 P0723105 LIFE VEST CABIN FAILED B KQ1R K NONE O OTHER IN INSP/MAINT 1 EA 07 LIFE VEST FAILED, MANUFACTURE RECOMMENDED 2 PSI CELL TEST IAW 21-60-7. DATE OF MFG. SEPT 1986. 2001082100026 20010821 00026 EA 2001 8 21 2001FA0000193 2 20010730 G 8520 LW13818 CRANKCASE PIPER PA28 PA28R201 7102816 SO LYC O360 IO360C1C 41514 EA ENGINE CRACKED D K NONE K FLUID LOSS IN INSP/MAINT 1 WP 27 9235G 2837055 L2545951A AT INSPECTION AN AREA OF OIL IS NOTICED BEHIND PROP- IT APPEARS TO LOOK LIKE THE SPLIT CASE SEAM IS LEAKING. CLEAN AREA AND USE NDT DEVELOPER. RUN-UP PLANE AND CRACK APPEARS. THERE ARE SEVERAL STYLES OF CASE FOR THIS ENGINE. BUT ON A CE RTAIN STYLE SEEMS TO CRACK. 1 L 7 1 3O 3 O 2A13 1E10 2001082100027 20010821 00027 SW 2001 8 21 2001FA0000194 1 20010806 G 3020 19940 CONTROL ARM BBAVIA 8 8GCBC 1220803 SW LYC O360 VO360* 41514 EA ENGINE FAULTY B RJWR O OTHER O OTHER NR NOT REPORTED 1 GL 15 437AC 182 39398 WHEN MOVING CARBURETOR HEAT CONTROL, CARB HEAT CONTROL ARM (PN 1-9940) CONTACTS JAM NUT ON THE THROTTLE CONTROL ROD CLEV IS (PN A31800), MOVING THE THROTTLE OUT OF POSITION. 1 H 7 1 3O 3 O A21CE 1E1 2001082300015 20010823 00015 NE 2001 8 23 2001FA0000195 2 20010703 G 8530 366249 CYLINDER AIRTRC AT300 AT301 0390103 SW PWA R1340 R1340* 52016 NE ENGINE CRACKED D K NONE O OTHER IN INSP/MAINT 1 CE 07 3164H 6375 3010539 THE NR 3 CYLINDER HEAD CRACKED AT THE ROCKER BOSS, ENGINE LOST POWER, AIRCRAFT EMERGENCY LANDED IN A FIELD. 2ND OCCURAN CE. 1 L 7 1 3R 3 R A9SW 5E2 2001082300022 20010823 00022 SO 2001 8 23 2001FA0000196 2 20010724 G 8500 ENGINE BEECH 95 95B55 1152729 CE CONT O470 IO470L 17026 SO ENGINE BAY FAILED B CGOR K NONE O OTHER IN INSP/MAINT 1 GL 03 5688K 200 TC765 1921768LR PILOT REPORTED SEVERE ENGINE VIBRATION FOLLOWING POWER REDUCTION ON INITIAL CLIMB-OUT AFTER DEPARTURE FROM AIRPORT. ENG INE SHUTDOWN AND FEATHERED. NOTED CATASTROPHIC LEFT ENGINE FAILURE UPON INITIAL INSPECTION. NR 5 CONNECTING ROD OBSERV ED WITH CLEAN BREAK THROUGH LARGE HOLE IN CRANKCASE; NR 6 CONNECTING ROD SEVERELY BENT. NR 5, NR 6 PISTONS DAMAGED SEV ERELY AND SEIZED IN CYLINDERS. OBSERVED CAMSHAFT BROKEN; FOUND PISTON PIN LOOSE WITH OTHER CRANKCASE AND CYLINDER BROK EN PARTS. EXACT FAIL MODE UNDETERMINED. ENGINE RECORDS NOT SUPPLIED. 1 L 7 2 3O 3 O RT 3A16 3E1 2001082300024 20010823 00024 EU 2001 8 23 2001FA0000197 2 20010616 G 8550 956470 LINE DIAMON DA20 DA20A1 GL ROTAX 912 ROTAX912 55555 EU OIL SUCTION BROKEN G K NONE O OTHER IN INSP/MAINT 1 SO 15 442PC 10042 4412740 OIL SUCTION LINE/ NR 3 CONNECTING ROD BROKE AT CRANKSHAFT. ROD PROTRUDED THROUGH ENGINE CASING. SB ADDRESSES SUBJECT O IL LINES TO BE INSPECTED FOR KINKS AND SHARP BENDS. ALSO, NONCOMPLIANCE COULD RESULT IN ENGINE DAMAGE. SUSPECT THAT OI L MAY HAVE BEEN RESTRICTED FROM ENTERING INTO ENGINE CASING DUE TO DEFECTIVE OIL LINES. DEFECTIVE OIL LINES. RECOMMEND AD AT 100 HR INTERVALS. 1 L 7 1 3O 3 I NT TA4CH EXPE3I 2001082300026 20010823 00026 EU 2001 8 23 2001FA0000198 2 20010616 G 8550 956476 LINE DIAMON DA20 DA20A1 GL ROTAX 912 ROTAX912 55555 EU OIL PRESS DEFECTIVE G K NONE O OTHER IN INSP/MAINT 1 SO 15 442PC 10042 4412740 OIL PRESSURE LINE-NR 3 CONNECTING ROD BROKE AT CRANKSHAFT. ROD PROTRUDED THROUGH ENGINE CASING. SERVICE INSTRUCTION AD DRESSES SUBJECT OIL LINES TO BE INSPECTED FOR KINKS AND SHARP BENDS. ALSO, NONCOMPLIANCE COULD RESULT IN ENGINE DAMAGE. SUSPECT OIL MAY HAVE BEEN RESTRICTED FROM ENTERING INTO ENGINE CASING DUE TO DEFECTIVE OIL LINES. RECOMMEND AD AT 100 HR INTERVALS. 1 L 7 1 3O 3 I NT TA4CH EXPE3I 2001082300027 20010823 00027 CE 2001 8 23 2001FA0000199 1 20010711 G 3233 98820152 ACTUATOR CESSNA 172 172RG 2072438 CE MLG CRACKED B LW5T K NONE O OTHER IN INSP/MAINT 1 GL 17 9515B 4503 172RG0846 BOTH ACTUATORS WERE INSPECTED IAW SB, CRACKS WERE FOUND IN THE AREA THAT ACCOMPLISHMENT INSTRUCTIONS INDICATED. PARTS WERE REMOVED FROM SERVICE. 1 H 7 1 3O 3A17 2001083001069 20010830 01069 SW 2001 8 30 2001FA0000200 1 20010712 G 2842 206379006101 TOTALIZER BELL 206 206L1 1182107 SW ALLSN 250B 250B* GL FUEL SYS INTERMITTENT D A UNSCHED LANDING N FALSE WARNING NR NOT REPORTED 1 GL 21 656NA 45391 TOT INDICATOR RED LIGHT FLASHED ON INTERMITTENTLY CAUSING PILOT TO MAKE PRECAUTIONARY LANDING. 1 G 7 1 3U 3 T H2SW E10CE 2001082300074 20010823 00074 CE 2001 8 23 2001FA0000202 1 20010627 G 3230 5081032019 SOCKET BEECH 1900 1900D 1154162 CE TORQUE ARM CRACKED B K NONE O OTHER IN INSP/MAINT 1 SO 19 9947 DURING LIQUID PENETRANT INSPECTION IAW MM NDT WE HAVE FOUND CRACKS ON THE LOWER LUGS WERE THE TORQUE ARM ATTACHED, DEPTH OF CRACKS ARE UNKNOWN, BUT VISUAL INSPECTION WILL REVEAL CRACKS WITH ANY USE OF MAGNIFICATION DEVICES OR PENETRANT DYE. WHEN WE RECEIVED UNITS, THEY NEVER HAVE THE DASH NUMBER JUST THE SERIES 50-810320. ALL SOCKETS SHOULD BE CONSIDERED. CAUSE IS UNKNOWN. 2 L 7 2 4T RT A24CE 2001082300075 20010823 00075 SO 2001 8 23 2001FA0000206 2 20010815 G 7414 1051324 SPRING CONT CESSNA 206 TU206G 2073357 CE CONT O520 TSIO520M 17040 SO IMPULSE COUPLING BROKEN D K NONE O OTHER IN INSP/MAINT 1 SW 99 PK-MP 11 E189909FR U20605864 818029R THE MAGNETO IMPULSE COUPLING SPRING BROKE ABOUT 6 INCHES FROM THE OUTER END OF THE SPRING. THE FAILURE WAS DISCOVERED B ECAUSE THE IMPULSE COUPLING WOULD NOT ENGAGE DURING THE ENGINE STARTING PROCESS. 1 H 7 1 3O 3 O A4CE E8CE 2001082300081 20010823 00081 CE 2001 8 23 2001FA0000207 1 20010815 G 3397 LF11 WIRE CESSNA 208 208 2073702 CE BEACON CHAFED D K NONE L NO TEST IN INSP/MAINT 1 SW 99 9Q-CA 9647 20800010 WIRES LF11 AND LF12 ARE ROUTED THROUGH THE VERTICAL STABILIZER WITHOUT PROTECTION OR SUPPORT. THESE WIRES POWER THE FLA SHING RED BEACON MOUNTED ON THE TOP OF THE FIN. BOTH WIRES CHAFED AGAINST THE EDGE OF THE HOLE IN THE STABILIZER RIB TH ROUGH WHICH THEY WERE ROUTED AND WORE THROUGH THE INSULATION CAUSING A SHORT CIRCUIT AND THE BREAKER TO OPEN. 1 H 7 1 3T NT A37CE 2001082300082 20010823 00082 GL 2001 8 23 2001FA0000208 1 20010810 G 3201 12446105 FAIRING CIRRUS SR SR20 05628AJ GL NLG LOOSE B ESMR K NONE O OTHER IN INSP/MAINT 1 SO 11 747CD 69 0047 BRACKETS THAT HOLD THE NOSE WHEEL FAIRING TO THE NOSE GEAR FORK PART NUMBER 1799-001, ARE HELD TO THE FORK BY BOLTS THAT ARE NOT DRILLED FOR SAFETY WIRE, THEY DO NOT THREAD INTO SELF LOCKING NUTS PLATES, NOR DO THEY CALL OUT FOR LOCK WASHER S. THE BOLTS LOOSEN UP, THE FAIRING MOVES AROUND, AND LEAVES THE AIRPLANE. EXAMINED OTHER SAME MODEL AIRCRAFT, AND FOU ND LOOSE FAIRINGS. BROUGHT THIS CONDITION TO THE OPERATORS ATTENTION. CONDITION NOTED BY: JACK D. TOBIN A&P 2250313. 1 H 7 1 3O NC A00009CH 2001082300083 20010823 00083 NE 2001 8 23 2001FA0000209 2 20010822 G 8530 11874 PUSHROD PWA R1340 R1340AN1 52016 NE EXHAUST FAILED G ISSG A UNSCHED LANDING Y ENGINE STOPPAGE NR NOT REPORTED 1 GL 27 21730 ENGINE FAILED DUE TO FAILURE OF NR 1 EXHAUST PUSHROD. UNEVENTFUL LANDING MADE. 3 R 5E2 2001083100005 20010831 00005 GL 2001 8 31 2001FA0000210 3 20010717 G 6111 FC8477A4 BLADE HARTZL HCC2Y HCC2YK2 GL PROPELLER CRACKED B ME4R A E UNSCHED LANDING ENGINE SHUTDOWN R E PARTIAL RPM/PWR LOSS VIBRATION/BUFFET CL CLIMB 1 SO 19 835 AU3069E PILOT REPORTED ON TAKE OFF THAT THE PROPELLER WOULD NOT MAKE FULL POWER. PILOT RETURNED TO THE FIELD. PRIOR TO TOUCHDO WN, PILOT EXPERIENCED A VIBRATION. IMMEDIATELY AFTER TOUCHDOWN, THE VIBRATION INCREASED SIGNIFICANTLY, AND THE ENGINE S HUT DOWN. A FIELD INSPECTION REVEALED THE PROPELLER TO BE OUT OF TRACK OVER ONE INCH (1 IN). THE PROPELLER WAS REMOVED AND SENT FOR INSPECTION/ EVALUATION. UPON DISASSEMBLY OF THIS PROPELLER A VISUAL INSPECTION REVEALED A LARGE CRACK APP ROXIMATELY 270 DEGREES AROUND THE NR 2 BLADE SHANK. THE HUB APPEARS TO BE CRACKED IN THE NR 2 BLADE ARM AS WELL. 5 C P920 2001090500048 20010905 00048 CE 2001 9 5 2001FA0000211 1 20010808 G 1100 PLACARD CESSNA 150 152 2071835 CE LYC O235 O235L2C 41505 EA CARBURETOR FOD C O OTHER C R F.O.D. PARTIAL RPM/PWR LOSS LD LANDING 1 GL 09 67464 42 42 15281850 L1402115 DURING TOUCH AND GO LANDING AS CARB HEAT WAS APPLIED, ENGINE LOST POWER. REMOVING CARB HEAT DID NOT IMPROVE PERFORMANCE . DURING INVESTIGATION AND CARB REMOVAL, FOUND STARTER LUBRICATION DECAL LODGED IN VENTURI. AFTER REMOVAL AND REINSTA LLATION OF CARB. ENGINE POWER RETURNED TO NORMAL. RECOMMEND THESE DECALS BE REMOVED PRIOR TO STARTER AND CARBURETOR IN STALLATION ON ENGINE. ( FOUND WARRANTY WARNING DECAL ON OVERHAULED CARB) 1 H 7 1 3O 3 O NT 3A19 E223 2001083100167 20010831 00167 EA 2001 8 31 2001FA0000212 2 20010813 G 8520 LW17162 CRANKSHAFT PIPER PA28 PA28180 7102808 SO LYC O360 O360A3A 41514 EA ENGINE BROKEN G O OTHER K J FLUID LOSS WARNING INDICATION NR NOT REPORTED 1 GL 03 8424W 1564 282651 L741036A CRANKSHAFT FRONT MAIN JOURNAL, FRACTURED AT THE REAR RADIUS OF THE CRANKSHAFT FLANGE. PROPELLER SEPARATED FROM THE AIRC RAFT. LOSS OF OIL AND OIL PRESSURE, ENGINE SEIZED UP AND QUIT. THIS CRANKSHAFT WAS PURCHASED BY THE AIRPLANES INSURANC E COMPANY AT THE LAST OVERHAUL, (6-4-99), HISTORY AND TOTAL TIME OF CRANKSHAFT IS UNKNOWN. CRANKSHAFT MAY HAVE BEEN SUB JECT TO A PRIOR PROPELLER STRIKE DAMAGE ACCIDENT, AS NOTED BY THE SPIRAL TYPE FRACTURE OF THE FRONT CRANKSHAFT JOURNAL. 1 L 7 1 3O 3 O 2A13 E286 2001083100168 20010831 00168 SO 2001 8 31 2001FA0000213 1 20010810 G 2752 452860 BEARING PIPER PA23 PA23250 7102308 SO LYC O540 TIO540* 41532 EA FLAP ACTUATOR BROKEN B O OTHER F FLT CONT AFFECTED AP APPROACH 1 SO 01 54828 277554125 FLAP ACTUATOR ROD END BEARING, BROKEN ON SHORT FINAL. REPLACED BEARING PN 452860. 1 L 7 2 3O 3 O 1A10 E14EA 2001090500049 20010905 00049 2001 9 5 2001FA0000214 4 20010606 G 2340 600591463 INTERPHONE CNDAIR CL604 CL604 EA EQUIP BAY UNSERVICEABLE D O OTHER O OTHER TX TAXI/GRND HDL 1 GL 09 15SP 570 5402 ON TAXI IN, CREW EXPERIENCED A LOUD CONTINUOUS SQUEAL IN THEIR HEADSETS AND ALSO OVER THE COCKPIT SPEAKERS. COMMUNICATI ON WAS IMPOSSIBLE WITH THE TOWER. OUR CUSTOMER SERVICE REP HAD US DISCONNECT THE HEADPHONE/MIC JACK ASSEMBLY IN THE AFT EQUIPMENT BAY. THE SQUEAL WENT AWAY. A NEW UNIT WAS ORDERED AND INSTALLED. A NEW UNIT WAS ORDERED AND INSTALLED. TH E SYSTEM IS ONLY ACTIVE WITH WEIGHT ON WHEELS , BUT IT COULD STILL POSE A SERIOUS COMMUNICATION PROBLEM ON THE GROUND AT A BUSY AIRPORT. 2 L 7 2 4F RT A21EA 2001090500050 20010905 00050 SO 2001 9 5 2001FA0000216 1 20010727 G 7920 63201000 LINE PIPER PA28 PA28180 7102808 SO LYC O360 O360* 41514 EA OIL SYSTEM CORRODED D O OTHER K FLUID LOSS NR NOT REPORTED 1 EA 13 7299W 1830 281121 ON THE THIRD FLIGHT AFTER UPDATING THE OIL PUMP IN THE ENGINE PER AD, AN OIL FILM WAS NOTED AT THE FIREWALL ADJACENT TO THE SPOT WHERE THE OIL PRESSURE LINE PASSES THROUGH A GROMMET (DISC, FIREWALL PN 63915-003). OIL WAS ALSO PRESENT ON TH E FIREWALL BLANKET ON THE INSIDE OF THE COCKPIT. AFTER DISASSEMBLING THE DISC A RETAINERS FROM THE FIREWALL, ABOUT 10-1 5 LBS PRESSURE WAS EXERTED ON THE ALUMINUM OIL LINE ASSEMBLY. IT SEPARATED INTO TWO PIECES DUE TO CORROSION OF THE META L, INSIDE THE AREA WHERE IT PASSES THROUGH THE DISC/RETAINER ASSEMBLY. THIS PART HAS A TOTAL TIME OF ONLY 1830 HOURS IT IS A 1963 AIRCRAFT. 1 L 7 1 3O 3 O 2A13 E286 2001083100169 20010831 00169 EA 2001 8 31 2001FA0000217 2 20010720 G 8530 72057 VALVE SEAT PIPER PA18 PA18150 7101828 SO LYC O360 O360* 41514 EA INTAKE PORT LEAKING D K NONE O OTHER IN INSP/MAINT 1 AL 05 272CC 9925CC L37352736A DURING COMPRESSION CHECK, LOW CYLINDER PRESSURE WAS DISCOVERED. LEAKAGE WAS DETERMINED TO BE BETWEEN NUMBER FOUR CYLIND ER INTAKE VALVE AND VALVE SEAT. AFTER REMOVING INTAKE VALVE, FURTHER INSPECTION REVEALED POOR CONDITION OF VALVE SEAT I N REGARDS TO A LACK OF A DISTINCT CONTACT WEAR PATTERN WITH VALVE. APPROXIMATELY ONLY ONE QUARTER OF THE DIAMETER OF TH E VALVE SEAT SHOWED CLEAN CONTACT WITH THE VALVE WHILE THE OTHER THREE QUARTERS APPEARED ROUGH WITH EVIDENCE OF COMPRESS ION BLOWBY. LEAKAGE CAUSED BY POOR SEAL BETWEEN VALVE AND SEAT DUE TO POSSIBLE IMPROPER VALVE SEAT INSTALLATION, VALVE LAPPING OR VALVE GUIDE BOSS NOT TRUE WITH VALVE SEAT FACE. 1 H 7 1 3O 3 O 1A2 E286 2001083100170 20010831 00170 CE 2001 8 31 2001FA0000218 1 20010718 G 5730 052301158 SKIN CESSNA 172 172N 2072434 CE LYC O320 O320* 41508 EA RT WING CORRODED B A5OR K NONE O OTHER IN INSP/MAINT 1 SO 09 2168E 7177 17271177 ON INSPECTION OF RIGHT WING ASSEMBLY, MECH NOTICED THAT A LOT OF RIVETS HAD POPPED FROM CORROSION UNDER THE LEADING EDGE SKIN AT THE FORWARD SPAR. THE WING WAS REMOVED FROM THE AIRCRAFT, BROUGHT TO THIS FACILITY FOR REPAIR. WING WAS DISAS SEMBLED FOR REPAIR AND CORROSION REMOVAL. THE WING WAS FOUND TO HAVE MORE THAN AVERAGE AMOUNT OF HEAVY CORROSION TO SKI NS, RIBS, SPARS AND STRINGERS. FOUR NOSE RIBS WHERE CORRODED THOUGH REQUIRING REPLACEMENTS. ALSO ALL SKINS WERE REPLAC ED. THE REMAINDER OF THE PARTS REQUIRED REMOVAL OF CORROSION, CLEANING AND TREATING OF PARTS. OWNER STATED THAT THE WI NG WAS NOT THAT BAD A YEAR AGO. 1 H 7 1 3O 3 O NT 3A12 E274 2001083100171 20010831 00171 CE 2001 8 31 2001FA0000219 1 20010621 G 5700 12NB108 NUT BEECH 95 95B55 1152729 CE CONT O470 IO470* 17026 SO WING CRACKED D K NONE O OTHER IN INSP/MAINT 1 SO 13 70CL TC2263 DURING INSPECTION FOR ANNUAL, CRITERION AND FREQUENCY FOR WING BOLT INSPECTION. RECEIVED NEW HARDWARE. SENT OUT HARDWA RE FOR MAGNETIC PARTICLE PROCESS PER MM. NDT PERSONAL INFORMED OF CONDITION OF NEW NUTS, STATING ROUGH INSIDE SURFACE A ND LINEAR INDICATION ON INSIDE APPEARING AS CRACK INDICATIONS. BOTH NUTS WERE RED TAGGED AND BOTH PARTS RETURNED WITH 8 130S FOR FURTHER INSPECTION. 1 L 7 2 3O 3 O RT 3A16 E1CE 2001083100172 20010831 00172 SO 2001 8 31 2001FA0000220 1 20010806 G 7820 6751700 MUFFLER PIPER PA32 PA32RT300 7103215 SO LYC 0540 IO540K1G5D 41532 SO ENGINE SPLIT D K NONE O OTHER NR NOT REPORTED 1 SW 07 3516M 2049 32R7885009 L1753348A THE CENTER MUFFLER HOUSING SPLIT OPEN AT THE UPPER WELD SEAM ALLOWING EXHAUST TO DAMAGE THE UPPER ALUMINUM MUFFLER ASSEM BLY SHROUD AND THE ENGINE INDUCTION COVER. SUGGEST THAT A VERY CLOSE INSPECTION BE DONE BY BOTH VISUAL AND PRESSURE CHE CK METHODS OF ALL MUFFLER AND EXHAUST STACK WELD SEAMS. 1 L 7 1 3O 3 O A3SO 1E4 2001083100173 20010831 00173 GL 2001 8 31 2001FA0000221 3 20010726 G 6110 2202 BEARING PIPER PA31 PA31350 7103110 SO LYC O540 TIO540J2BD 41532 EA HARTZL HCE3Y HCE3YR2A GL PROPELLER CRACKED B LU4R K NONE O OTHER IN INSP/MAINT 1 SO 17 35272 317952142 DJ8665A RELEVANT INDICATION 1 L 7 2 3O 3 O A20SO E14EA 5 C P33EA 2001083100174 20010831 00174 GL 2001 8 31 2001FA0000222 3 20010726 G 6110 3252L FORK PIPER PA31 PA31350 7103110 SO LYC O540 TIO540J2BD 41532 EA HARTZL HCE3Y HCE3YR2A GL PROPELLER CRACKED B LU4R K NONE O OTHER IN INSP/MAINT 1 SO 17 35272 317952142 DJ8665A RELEVANT INDICATION 1 L 7 2 3O 3 O A20SO E14EA 5 C P33EA 2001090500051 20010905 00051 EU 2001 9 5 2001FA0000223 1 20010712 G 6320 C632A2115101 HOUSING UROCOP EC120 EC120B 8680987 EU TMECA ARRIUS ARRIU2F NE MAIN ROTOR CORRODED D K NONE O OTHER IN INSP/MAINT 1 SW 09 120GB 597 597 1063 34076 MFG CONCESSION APPLIED TO MGB- INSTALLATION OF BEVEL GEAR AND BEVEL PINION GEAR. DISASSEMBLY OF MGB FOR MODIFICATION, CO RROSION WAS ON SUPPORT STUDS OF THE LOWER HOUSING AND THE BORES OF MAIN MODULE OF THE AFFECTED STUDS, INSP REVEALED CORR OSION IN THE BORES. CLEANED AND TREATED THE BORES AND STUDS TO ACCEPTABLE STANDARDS, RECORDS OF THE MGB WERE REVIEWED, I NDICATING THE COMPONENT WAS MANUFACTURED 8/98, WITH TOTAL TIME SINCE NEW-597.3 HOURS. THE OVERHAUL INTERVAL OF THE MGB I S 2000 HRS. THE MM WAS FOLLOWED FOR THE PROCEDURES OF DISASSEMBLY, ASSEMBLY AND COMPLETION OF THIS MODIFICATION, AND NO MENTION OF CORROSION IN THIS AREA OF THE MGB. FOLLOWED THE SPM FOR CORROSION CONTROL TO MAGNESIUM. PROBABLE CAUSE OF TH 1 G 7 2 3U 3 U NC R0001RD E34NE 2001091700136 20010917 00136 EU 2001 9 17 2001FA0000224 1 20010808 G 7600 C761A1014101 LEVER UROCOP EC120 EC120B 8680987 EU TMECA ARRIUS ARRIU2F NE ANTICIPATR LEVER MISINSTALLED D K NONE O OTHER IN INSP/MAINT 1 SW 09 162TA 1225 1001 AFTER INSTALLATION OF THE NEW ANTICIPATOR COMPONENTS UNDER THE CARGO COMPARTMENT FLOOR ON THE LEFT SIDE . WE COULD NOT ACHIEVE THE CRITERIA MENTIONED WITH ADJUSTMENTS AND TESTS. UPON FURTHER INSPECTION, WE DISCOVERED THE ANTICIPATOR LEVER SECURED TO THE COLLECTIVE SHAFT FORWARD OF THE INSTALLED SB WAS INSTALLED FROM FACTORY 180 FROM A NORMAL POSITION. WH ICH WHT NEW MODIFICATION WE INSTALLED, CAUSING THE ADJUSTMENTS FOR THE ANTICIPATOR AT THE FUEL CONTROL TO BE INCORRECT. ONCE THE ANTICIPATOR LEVER WAS REMOVED, AND INSTALLED CORRECTLY, WE WERE ABLE TO ACHIEVE CORRECT ADJUSTMENTS WITH THE A NTICIPATOR SIDE OF THE FUEL CONTROL UNIT. 1 G 7 2 3U 3 U NC R0001RD E34NE 2001083100175 20010831 00175 2001 8 31 2001FA0000225 4 20010717 G 6113 055032110 BULKHEAD CESSNA 172 172S 2072439 CE LYC O320 IO320* 41508 EA MCAULY 1A170 1A170E GL SPINNER CRACKED C K NONE O OTHER IN INSP/MAINT 1 AL 03 430CP 172S8692 L2938051A UC057 UPON A POSTFLIGHT INSPECTION, THE PROPELLER SPINNER BULKHEAD AND SPINNER ASSEMBLY WERE DISCOVERED CRACKED. THE CORNER P ORTION OF THE BULKHEAD WAS COMPLETELY RIPPED AWAY AND THE EDGE OF THE SPINNER WAS PEELING UP AND TORN. PROBABLE CAUSE: M ANUFACTURING DEFECT SUSPECTED. 1 H 7 1 3O 3 O NT 3A12 1E12 5 N P857 2001083100176 20010831 00176 CE 2001 8 31 2001FA0000226 1 20010728 G 5711 SPAR BEECH 55 95C55 1152708 CE CONT O520 IO520* 17032 SO LT WING CRACKED D K NONE O OTHER IN INSP/MAINT 1 SW 15 2764T TE372 CRACK DEVELOPED ON TOP OF LEFT WING. INVESTIGATION REVEALED LOWER FORWARD WING SPAR HINGES AND PINS WORN OUT RESULTING IN EXCESS OF MOVEMENT IN THE LEADING EDGE OF WINGS. NEW WING SPARS 1 L 7 2 3O 3 O 3A16 E5CE 2001083100177 20010831 00177 EA 2001 8 31 2001FA0000227 2 20010730 G 7200 PT6A41 ENGINE BEECH 200 200BEECH 1152920 CE PWA PT6 PT6A41 52043 EA LEFT FAILED G E ENGINE SHUTDOWN J WARNING INDICATION NR NOT REPORTED 1 EA 03 2025M 10206 1596 BB384 PCE80823 LEFT ENGINE SHUT DOWN DUE TO CHIP DETECTOR LIGHT ON ENGINE SURGING AND OIL PRESSURE FALLING OFF. ON INITIAL INSPECTION S USPECTS COMPRESSOR, NR1 OR NR 2 MAIN LINE BEARING FAILURE. 1 L 7 2 4T 4 T A24CE E4EA 2001083100178 20010831 00178 SO 2001 8 31 2001FA0000228 1 20010622 G 2740 62701114 CONTROL CABLE PIPER PA28 PA28161 7102803 SO STABILIZER FRAYED H CDHS K NONE O OTHER IN INSP/MAINT 1 EA 05 9182W 7000 2841130 RIGHT FORWARD STABILATOR CABLE- THIS LOCATION HAS SEVERAL PULLIES THAT DO NOT HAVE BEARINGS, WHEN THEY GET STUCK (NOT MU CH CABLE DEFLECTION AND THEREFORE NOT MUCH PRESSURE TO TURN THE PULLEY) THE CABLE WEARS THIN AND EVENTUALLY FRAYS. DIFF ICULT TO DETECT WITHOUT CLEANING CABLE AND CHECKING WITH FINGERNAIL OR RAG. THIS CABLE LOOKED FINE BUT HAD 50 PERCENT B ROKEN STRANDS WHEN IT WAS REMOVED AND BIRDGAGED. 1 L 7 1 3O 2A13 2001090500052 20010905 00052 2001 9 5 2001FA0000229 4 20010716 G 3418 S16729 DETECTOR CESSNA 182 182R 2072731 CE CONT O470 O470* 17026 SO LT WING INOPERATIVE D O OTHER O OTHER NR NOT REPORTED 1 EA 21 35VA 18268129 UPON INSTALLING NEW LIFT DETECTION, NOTED THAT WHEN WIRED AS ORIGINALLY REMOVED FROM AIRCRAFT, WITH HEAT TURNED ON, DETE CTION WAS INOPERATIVE. GROUND FOR HEATER WAS INSTALLED ON COMMON FOR DETECTION; CAUSING A NO POTENTIAL WHEN HEATER TUR NED ON. 1 L 7 1 3O 3 O NT 3A13 E273 2001083100179 20010831 00179 SO 2001 8 31 2001FA0000230 2 20010829 G 8540 632617 BEVEL GEAR CESSNA 337 337D 2075717 CE CONT O360 IO360CB 17025 SO ACCESSORY DRIVE FAILED D O OTHER O OTHER NR NOT REPORTED 1 WP 07 51WM 3371140 236532R TROUBLESHOT LOSS OF VACUUM ON REAR ENGINE AND DETERMINE ACCESSORY DRIVE ASSEMBLY GEAR BOX FOR VACUUM PUMP AND HYDRAULIC PUMP INOPERABLE. REMOVE AND DISASSEMBLED GEAR BOX AND FOUND BEVEL GEAR PN 632617 STRIPPED OF ALL GEAR TEETH. ENGINE HA D BEEN RECENTLY OVERHAULED. OIL LEVEL AT CORRECT CAPACITY. POSSIBLE CAUSE OF FAILURE MAY BE DUE TO IMPROPER GEAR MESH OF BEVEL GEARS FROM WORN OR INCORRECT SHOULDER THICKNESS ON BUSHING. MFG IS NOW AWARE OF THE GEAR MESH PROBLEM AND HAS CORRECTED IT VIA A SB AND ISSUED THE MODIFIED ADAPTER ACCESSORY DRIVE FOR REPLACEMENT. 1 H 7 2 3O 3 O A6CE E1CE 2001083100180 20010831 00180 SO 2001 8 31 2001FA0000231 2 20010816 G 7230 6375506 VALVE SEAT CESSNA 185 A185E 2072818 CE CONT O520 IO520* 17032 SO CYLINDER CRACKED D K NONE O OTHER IN INSP/MAINT 1 SO 00 70083 18501950 282858 DURING A ROUTINE COMPRESSION CHECK, A LEAK WAS FOUND IN THIS CYLINDER (AIR WAS ESCAPING FROM IN BETWEEN COOLING FINS). UPON REMOVAL OF CYLINDER, 2 CRACKS APPROX. 1 INCH AND .7500 INCH LONG, WERE FOUND TO BE EMANATING FROM THE EXHAUST VALVE SEAT. 1 H 7 1 3O 3 O 3A24 E5CE 2001083100181 20010831 00181 SO 2001 8 31 2001FA0000232 1 20010816 G 2434 78483000 STRUT PIPER PA28 PA28R200 7102811 SO ALTERNATOR CRACKED D O OTHER O OTHER NR NOT REPORTED 1 SO 17 318MC 926 28R35155 ALTERNATOR FRONT ATTACHMENT STRUT FOUND CRACKED. 1 L 7 1 3O 2A13 2001083100182 20010831 00182 CE 2001 8 31 2001FA0000233 1 20010717 G 3246 5010720 BOLT BEECH MU300 400A 1155402 CE PWA JT15 JT15D5 52112 NE MLG WHEEL BROKEN C WXHM O OTHER O OTHER NR NOT REPORTED 1 NM 01 440DS 1000 RK8 1 MAIN WHEEL TIE BOLT BROKE AND DEPARTED AIRCRAFT, RESULTING IN UNSEATING OF WHEEL HALF SEALING O-RING AND SUBSEQUENT LO SS OF AIR PRESSURE. BOLT WAS MAGNAFLUXED 14 HOURS PREVIOUS WITH NO DEFECTS NOTED. 2 H 7 2 4F 4 F RT A16SW E25EA 2001083100183 20010831 00183 EU 2001 8 31 2001FA0000234 1 20010702 G 6210 355A11002009 BLADE AEROSP AS355 AS355F2 8680812 EU ALLSN 250C 250C20 03013 GL MAIN ROTOR CRACKED E K NONE O OTHER IN INSP/MAINT 1 SO 17 42AT 2220 5462 FOUND CRACK ON PREFLIGHT. NO SURE CAUSE FOR CRACK. CRACK BEYOND LIMITS. 1 G 7 2 3U 3 U H11EU E4CE 2001083100184 20010831 00184 EA 2001 8 31 2001FA0000235 1 20010806 G 3222 6A0720401 LINK DHAV DHC2 DHC2MK3 2800107 EA NLG BROKEN D O OTHER E VIBRATION/BUFFET LD LANDING 1 NM 01 227N 1686TB UPON LANDING AT BFI, BOTH NOSE WHEEL BEGAN TO SHIMMY, PILOT PULLED NOSE WHEELS OFF OF RUNWAY UPON TOUCHDOWN AGAIN, SEVER E SHIMMY OCCURRED. RIGHT NOSE GEAR LINK RAM END BROKE ALLOWING GEAR TO DEPART FROM AIRCRAFT. 1 H 7 1 3T A806 2001091000210 20010910 00210 CE 2001 9 10 2001FA0000238 1 20010831 G 3233 2653361203 CLEVIS PIN RKWELL NA265 NA26565 7630107 CE GARRTT TFE731 TFE7313R1D 01518 WP MLG ACTUATOR CRACKED B K NONE O OTHER IN INSP/MAINT 1 CE 01 82CR 8760 600 46549 CRACKED PIN FOUND AS A RESULT OF CONDUCTING MAGNETIC PARTICLE INSPECTION OF MAIN LANDING GEAR ACTUATOR ROD CLEVIS PIN AN D ATTACHING HARDWARE IN ACCORDANCE WITH SMIP ATA CODE 323076. CRACK IS LOCATED IN RELIEF AREA RADIUS DIRECTLY UNDER CLE VIS PIN HEAD. 2 L 7 2 4J 4 F A2WE E6WE 2001090500053 20010905 00053 SO 2001 9 5 2001FA0000239 1 20010720 G 2842 O-RING PIPER PA31T PA31T 7103124 SO PWA PT6 PT6* 52043 EA FUEL PROBE LEAKING D O OTHER K FLUID LOSS TX TAXI/GRND HDL 1 NM 09 700LT 2260 31T7920046 AFTER FUELING AIRCRAFT, FUEL STARTED LEAKING FROM RIGHT NACELLE FUEL PROBE COVER. FOUND O-RING BETWEEN MOUNT PLATE AND TOP OF PROBE EXTRUDED IN 2 AREAS. FUEL WAS RUNNING OUT OF THOSE AREAS. DEFUELED AND REPLACED PROBE WITH SERVICEABLE UN IT. 1 L 7 2 3T 3 T A8EA E2NE 2001091000307 20010910 00307 SO 2001 9 10 2001FA0000240 1 20010801 G 2460 688498 RELAY PIPER PA46 PA46500TP SO PWA PT6 PT6* 52043 EA COCKPIT DAMAGED B NM4R H DEACTIVATE SYST/CIRCUITS B SMOKE/FUMES/ODORS/SPARKS NR NOT REPORTED 1 SO 15 71562 17 PILOT REPORTED SMOKE IN COCKPIT AND THEN CABIN FAN CIRCUIT BREAKER POPPED. FOUND LOAD BUS RELAY PN 688498 LOCATED BELOW RIGHT CIRCUIT BREAKER PANEL, WITH A HOLE BURNED IN IT. WITH CIRCUIT BREAKER PULLED, THE SMOKE WENT AWAY. PILOT RETURN ED AIRCRAFT TO FACTORY FOR REPAIR. 1 L 7 1 3O 3 T RT A25SO E2NE 2001090500110 20010905 00110 SW 2001 9 5 2001FA0000241 1 20010522 G 7160 646207 TUBE MOONEY M20 M20R 5870225 SW CONT O550 IO550G 17042 SO NR 6 CYLINDER CRACKED B EA6R K NONE O OTHER IN INSP/MAINT 1 NE 01 46WB 68 290226 679484 INDUCTION TUBE AT NR 6 CYLINDER IS COMPLETELY CRACKED AT FLANGED END. 1 L 7 1 3O 3 O RT 2A3 E3SO 2001090500111 20010905 00111 SO 2001 9 5 2001FA0000243 1 20010827 G 3230 3807802 DOWNLOCK BRACKET PIPER PA32 PA32R300 7103213 SO LYC O540 TIO540* 41532 EA NLG BROKEN G O OTHER J WARNING INDICATION CR CRUISE 1 AL 01 200HM 351 32R7680025 NOSE GEAR DROPPED OUT OF WHEEL WELL IN FLIGHT. FOUND DOWNLOCK BROKEN WHERE NOSE ACTUATOR ROD ATTACHES. THIS HAS HAPPEN ED ON MORE THAN ONE OCCASION WITH SAME TYPE OF AIRCRAFT IN THE PAST. 1 L 7 1 3O 3 O A3SO E14EA 2001090500112 20010905 00112 CE 2001 9 5 2001FA0000244 1 20010824 G 5753 0523920 BEARING CESSNA 206 U206G 2073356 CE CONT C85 C85* 17008 SO FLAP TRACK WORN B DVPR K NONE O OTHER IN INSP/MAINT 1 SO 03 9489Z 473 U20606525 INNER BEARING WAS PUSHED OUT TO ONE SIDE SHOWING EXCESSIVE WEAR. 1 H 7 1 3O 3 O A4CE E233 2001091000308 20010910 00308 CE 2001 9 10 2001FA0000245 1 20010906 G 5210 169420036147 STRUCTURE BEECH 23 C23 1151242 CE LYC O360 VO360* 41514 EA LT DOOR BROKEN D O OTHER E F VIBRATION/BUFFET FLT CONT AFFECTED AP APPROACH 1 EA 21 20087 8100 M2063 PILOTS REPORTED SEVERE BUFFET DURING SLOW FLIGHT, APPROACH TO LANDING, ROUND-OUT, AND FLARE. BUFFET WAS AGGRAVATED BY L EFT SLIP. FOUND BOTTOM DOOR GASKET MISSING AND FIBERGLASS DOOR STRUCTURE BROKEN AT LAST RIVET ON DIAGONAL GUSSET. THIS ALLOWED AIR ESCAPING FROM CABIN TO DISRUPT AIRFLOW OVER THE WING AND STABILATOR. FABRICATED HAT SECTION CHANNEL FROM 0.032 2024-T3, BONDED TO FIBERGLASS CHANNEL WITH HYSOL EA9309, AND RIVETED THROUGH OUTSIDE SKIN. INSTALLED NEW DOOR GAS KET. FOUND RIGHT CABIN DOOR BROKEN ALSO. SUSPECT CAUSE IS DUE TO PILOTS LEAVING DOORS OPEN AND UNATTENDED TO COOL CABI N AND WIND OPENING DOOR HARD AGAINST THE STOP. 1 L 7 1 3O 3 O A1CE 1E1 2001091000309 20010910 00309 CE 2001 9 10 2001FA0000246 1 20010906 G 7120 10598000021 CHANNEL BEECH 76 76 1153005 CE LYC O360 VO360* 41514 EA ENGINE MOUNT BROKEN B G2AR K NONE O OTHER IN INSP/MAINT 1 NE 05 6714R ME320 BOTH UPPER OUTBOARD ENGINE MOUNT CHANNELS BROKEN THROUGH JUST ABOVE NUT PLATE HOLE. MAY HAVE BEEN CAUSED BY STRESSES IM POSED BY THE COUNTER ROTATING ENGINES AND/OR UNREPORTED HARD LANDINGS. 1 L 7 2 3O 3 O A29CE 1E1 2001091300185 20010913 00185 SO 2001 9 13 2001FA0000247 1 20010706 G 2140 23D04 VALVE PIPER PA23 PA23250 7102308 SO LYC O540 TIO540* 41532 EA HEATER DEFECTIVE D K NONE K FLUID LOSS IN INSP/MAINT 1 EA 21 68SE 273780 AFTER COMPLYING WITH AD AND SB, VALVE WAS DEEMED AIRWORTHY AND REINSTALLED IN AIRCRAFT. CONNECTED A PRESSURE GAUGE TO VE RIFY THAT SETTING WAS CORRECT BECAUSE OF THE QUANTITY OF SOOT IN THE EXHAUST PIPE AND STREAM. WHILE REMOVING TEE FITTIN G AND GAUGE,THE FUEL DID NOT STOP DRIPPING FROM THE VALVE OUTLET. ENERGIZED THE FUEL PUMP BRIEFLY TO PRESSURIZE THE VALV E AND THE FUEL DID NOT STOP, PN OF VALVE IS NOT READABLE. IT APPEARS TO HAVE BEEN SALVAGED FROM ANOTHER AIRCRAFT BECAUSE THE PAINT ON IT DOES NOT MATCH THIS AIRCRAFT. NEW VALVE IN ORDER. 1 L 7 2 3O 3 O 1A10 E14EA 2001091000311 20010910 00311 NE 2001 9 10 2001FA0000248 2 20010708 G 7321 FUEL CONTROL CESSNA 500 500CESSNA 2076602 CE PWA JD15 JT15D1A NE RT ENGINE MALFUNCTIONED D O OTHER R PARTIAL RPM/PWR LOSS CL CLIMB 1 EA 07 88GJ 5000155 PCE76335 DURING A CLIMB THROUGH FL 290, THE RIGHT ENGINE FAN SPEED DECREASED TO 82 PERCENT. ENGINE IGNITION WAS SELECTED ON TO N O EFFECT. AND EMERGENCY WAS DECLARED AND A SAFE LANDING WAS MADE. SUSPECT THAT THE FUEL CONTROL UNIT MALFUNCTIONED. 1 L 7 2 4F 4 F A22CE E25EA 2001091000314 20010910 00314 EA 2001 9 10 2001FA0000250 2 20010814 G 7414 AB3571651 COIL MOONEY M20 M20E 5870212 SW LYC O360 IO360A1A 41514 EA MAGNETO CRACKED D K NONE O OTHER IN INSP/MAINT 1 SW 09 9240M 478 1193 L252751A WHILE REPAIRING LEFT BENDIX S20 SERIES MAGNETO, FOUND MAGNETO COIL CRACKED. REPLACED COIL WITH A NEW TCM COIL PN 10-357 165 COIL. ALSO FOUND CRACK IN DISTRIBUTOR BLOCK, REPLACED. 1 L 7 1 3O 3 O 2A3 1E10 2001091300186 20010913 00186 EA 2001 9 13 2001FA0000251 2 20010814 G 8550 IMPELLER MOONEY M20 M20E 5870212 SW LYC O360 IO360A1A 41514 EA OIL PUMP DAMAGED D K NONE O OTHER IN INSP/MAINT 1 SW 09 9240M 478 1193 L252751A OIL PUMP IMPELLERS S1B 524, FOUND OIL PUMP GEARS TO BE STEEL TYPE BUT NO DOCUMENTATION AS TO WHAT PN THE GEARS WERE. FO UND GEARS HAD FOREIGN MATERIAL HAD PASSED THROUGH THE OIL PUMP. OIL PUMP GEARS WERE NOT AIRWORTHY REGARDLESS OF PART NU MBERS. INSTALLED IMPELLER KIT PN 05K19423S. (ATTACHED PHOTOS) 1 L 7 1 3O 3 O 2A3 1E10 2001091300188 20010913 00188 EA 2001 9 13 2001FA0000252 2 20010814 G 8550 78531 HOUSING MOONEY M20 M20E 5870212 SW LYC O360 IO360A1A 41514 EA OIL PUMP GALLED D K NONE O OTHER IN INSP/MAINT 1 SW 09 9240M 478 1193 L252751A WHEN COMPLYING WITH AD, OIL PUMP IMPELLERS, S1B524, FOUND OIL PUMP BODY GALLED DUE TO FOREIGN MATERIAL PASSING THROUGH O IL PUMP ASSEMBLY. REPLACED OIL PUMP BODY WITH NEW PART. (PHOTOS ATTACHED) 1 L 7 1 3O 3 O 2A3 1E10 2001091000426 20010910 00426 2001 9 10 2001FA0000253 4 20010822 G 2561 AC2D21344101 LIFE VEST CABIN FAILED B KQ1R K NONE L NO TEST IN INSP/MAINT 1 EA 07 LIFE VEST FAILED MFG RECOMMENDED TWO(2) PSI INFLATION TEST IAW MM. DATE OF MFG: JAN 1988 2001091300189 20010913 00189 GL 2001 9 13 2001FA0000254 2 20010716 G 7261 2060405441 TUBE BELL 206 206L1 1182107 SW ALLSN 250B 250B* GL ENGINE CORRODED D K NONE K FLUID LOSS IN INSP/MAINT 1 EA 17 98KR 5885 45683 MAIN GEARBOX TO OIL COOLER TRANSFER TUBE LEAKING DUE TO CORROSION PITTING. AREA WHERE TUBE RUNS THRU AREA IS FILLED WIT H LOOSE FIBERGLASS SOUND PROOFING WHICH HOLDS MOISTURE AND CAUSES CORROSION. RECOMMEND REMOVING INSULATION FROM THESE A REAS. 1 G 7 1 3U 3 T H2SW E10CE 2001091000427 20010910 00427 NE 2001 9 10 2001FA0000255 2 20010725 G 8530 28160 VALVE SPRING WTHRLY 620 620B 9630605 CE PWA R985 R985AN1 52008 NE NR 1 CYLINDER BROKEN D A UNSCHED LANDING R PARTIAL RPM/PWR LOSS NR NOT REPORTED 1 NM 05 2035N 6170 1591 15642 ENGINE BEGAN BACKFIRING AND POWER DECREASED, AIRCRAFT LANDED AS A RESULT OF RUNNING THROUGH A FENCE. FOUND NR 1 CYLINDE R INTAKE VALVE SPRINGS BROKEN. REPLACED SPRINGS, OPERATION NORMAL. APPEARED TO BE SMALL RUST PITS IN BREAK AREAS. 1 L 7 1 3R 3 R NC A26WE 5E1 2001091300190 20010913 00190 EA 2001 9 13 2001FA0000256 2 20010724 G 7310 601800 GASKET PIPER PA46 PA46500TP SO PWA PT6 PT6* 52043 EA ENGINE LEAKING D O OTHER K FLUID LOSS CR CRUISE 1 EA 25 310JM 47 4697069 FUEL WAS LEAKING IN FLIGHT AND ON GROUND. GASKET ON FILTER ASSY. E6 BYPASS GASKET LEAKING. 1 L 7 1 3O 3 T RT A25SO E2NE 2001091300191 20010913 00191 CE 2001 9 13 2001FA0000257 1 20010802 G 5341 0512122 BLOCK CESSNA 175 175A 2072504 CE CONT O300 GO300* 17022 SO WING ATTACH CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 09 7912T 56612 DISSIMILAR METAL CORROSION ON WING ATTACH POINTS. BLOCK ARE ATTACHED TO FUSELAGE SPAR ASSEMBLY PN 05121246 WITH (4) AW3 20A BOLTS. REMOVE FOR INSPECTION. 1 H 7 1 3O 3 O 3A17 E298 2001091300219 20010913 00219 CE 2001 9 13 2001FA0000258 1 20010802 G 5341 0411129 BLOCK CESSNA 175 175A 2072504 CE CONT O300 GO300* 17022 SO WING ATTACH CORRODED B K NONE O OTHER IN INSP/MAINT 1 GL 09 7912T 2142 56612 DISSIMILAR METAL CORROSION ON WING ATTACH POINTS. BLOCKS ARE ATTACHED TO FUSELAGE SPAR ASSEMBLY. PN 0511162-S WITH (4) AN3-21A BOLTS. REMOVE FOR INSPECTION. 1 H 7 1 3O 3 O 3A17 E298 2001091300222 20010913 00222 CE 2001 9 13 2001FA0000259 1 20010703 G 5712 RIB BBAVIA 8 8KCAB 2110612 CE LYC O360 AEIO360H1A 41514 EA LT&RT WING DAMAGED D K NONE O OTHER IN INSP/MAINT 1 NE 05 80TA 1511 63280 L2167853A FOUND LOOSE AND/OR MISSING NAILS AT RIB/FRONT SPAR CONNECTION. 2 RIBS ON RT WING AND 2 RIBS ON LT WING FOUND DAMAGED WHI LE INSPECTING PER REGMENTS OF AD. 1 H 7 1 3O 3 O A21CE 1E10 2001091300225 20010913 00225 SO 2001 9 13 2001FA0000260 1 20010721 G 2434 LAY6421 BRUSHES PIPER PA32 PA32301 7103207 SO ALTERNATOR WORN G O OTHER O OTHER NR NOT REPORTED 1 NE 03 42993 328306025 ALTERNATOR BRUSHES WORN, BATTERY WEAK. 1 L 7 1 3O A3SO 2001091300226 20010913 00226 EA 2001 9 13 2001FA0000261 2 20010613 G 8550 70484 SCREEN CESSNA 172 172L 2072432 CE LYC O360 O360* 41514 EA OIL FILTER CRUSHED D K NONE O OTHER IN INSP/MAINT 1 NM 09 4250Q 120 17260150 L3603436A METAL IN FILTER. FOUND SCREEN CRUSHED (FROM FACTORY BUILDUP) ALLOWED METAL TO CONTAMINATE ENGINE. 1 H 7 1 3O 3 O NT 3A12 E286 2001091300228 20010913 00228 EA 2001 9 13 2001FA0000262 2 20010613 G 8520 CRANKCASE CESSNA 172 172L 2072432 CE LYC O360 O360* 41514 EA ENGINE MISMANUFACTURED D K NONE W INADEQUATE Q C IN INSP/MAINT 1 NM 09 4250Q 17260150 L3603436A TOOLING-MACHINE CHATTER LEFT ROUGH, UNFINISHED AREA FOR CYL BASE O-RING TO SEAT AGAINST ALL FOUR CASE CYLINDER HOLES. 1 H 7 1 3O 3 O NT 3A12 E286 2001091300229 20010913 00229 EA 2001 9 13 2001FA0000263 2 20010613 G 8530 LW11775 PISTON PIN CESSNA 172 172L 2072432 CE LYC O360 O360* 41514 EA ENGINE WORN D K NONE O OTHER IN INSP/MAINT 1 NM 09 4250Q 120 17260150 L3603436A METAL IN FILTER. PISTON PIN PLUG- EXCESSIVE WEAR. ONE PIN WORN DOWN .500 INCH. ALL PLUGS WORN. 1 H 7 1 3O 3 O NT 3A12 E286 2001091300230 20010913 00230 SO 2001 9 13 2001FA0000264 1 20010807 G 3080 A110240 PROBE PIPER PA28 PA28161 7102803 SO LYC O320 O320* 41508 EA CARB ICE DETECT DEFECTIVE D HE8M O OTHER N FALSE WARNING NR NOT REPORTED 1 CE 09 83416 658 288116160 L1082939A ICEMAN CARBURETOR, ICEMAN DETECTOR ALERTS EVEN WHEN THERE IS NO ICE. THERE APPEARS TO BE A MALFUNCTION OF THE PROBE. 1 L 7 1 3O 3 O 2A13 E274 2001091300231 20010913 00231 CE 2001 9 13 2001FA0000265 1 20010801 G 5753 052390 ROLLER CESSNA 172 172N 2072434 CE LYC O320 O320* 41508 EA T/R FLAP CRACKED D K NONE O OTHER IN INSP/MAINT 1 CE 09 738DB 5300 17269886 FLAP ROLLER FOUND NOT TURNING. REMOVED AND FOUND CRACKS. THIS IS NOT THE FIRST TIME THIS CONDITION WAS FOUND. LACK OF PROPER MAINTENANCE. DIRTY AND DRY ROLLER BEARINGS. 1 H 7 1 3O 3 O NT 3A12 E274 2001091300232 20010913 00232 SO 2001 9 13 2001FA0000266 1 20010807 G 3080 A110240 PROBE PIPER PA28 PA28161 7102803 SO LYC O320 O320* 41508 EA CARB ICE DETECT DEFECTIVE D HE8M O OTHER O OTHER NR NOT REPORTED 1 CE 09 47979 318 287816175 L779939A CARBURETOR ICE DETECTOR ALERTS EVEN WHEN THERE IS NO ICE. THERE APPEARS TO BE A MALFUNCTION OF THE PROBE. 1 L 7 1 3O 3 O 2A13 E274 2001091300234 20010913 00234 SW 2001 9 13 2001FA0000267 1 20010618 G 2710 730048503 TUBE MOONEY M20 M20K 5870220 SW CONT O520 TSIO520* 17040 SO AILERON CORRODED B EA6R K NONE O OTHER IN INSP/MAINT 1 NE 01 389CS 880 250860 FATAL INTERNAL CORROSION, CAUSED BY TRAPPED MOISTURE INSIDE PUSH PULL CONTROL TUBE FOR AILERON. CORROSION WAS FOUND DUR ING ANNUAL INSPECTION. 1 L 7 1 3O 3 O 2A3 E8CE 2001091300236 20010913 00236 SW 2001 9 13 2001FA0000268 1 20010820 G 7603 TCM646224A THROTTLE ARM MOONEY M20 M20R 5870225 SW CONT O550 IO550* SO COCKPIT WORN B EA6R K NONE O OTHER IN INSP/MAINT 1 NE 01 53WM 322 290191 679406 THE PRESSED IN BUSHING AT THE END OF THE THROTTLE ARM WAS WORN THRU. THE BRONZE SECTION. (ATTACHED PHOTO) 1 L 7 1 3O 3 O RT 2A3 E3SO 2001091400061 20010914 00061 CE 2001 9 14 2001FA0000269 1 20010912 G 3340 4502131REVR1 LANDING LIGHT CESSNA 650 650 2076802 CE EXTERIOR DEFECTIVE D K NONE L NO TEST IN INSP/MAINT 1 SO 01 733H 6500210 BOUGHT OVERHAULED LIGHT FROM CESSNA, (OVERHAULED BY GRIMES). RETRACTABLE LIGHT RETRACTS, EXTENDS, AND LIGHTS UP BUT WIL L NOT ADJUST TO ALLOW FOR PROPER ALIGNMENT OF THE BEAM OF LIGHT. THE BEAM OF LIGHT POINTS AT THE GROUND RATHER THAN OUT IN FRONT OF THE AIRPLANE. MAINTENANCE MANUAL INSTRUCTIONS WERE FOLLOWED BUT ADJUSTMENT PROCEDURES HAD NO EFFECT. THE OVERHAUL COULD NOT HAVE BEEN COMPLETED IN A CORRECT MANNER, THIS PART HAS ZERO TIME IN SERVICE. 2 L 7 2 4F A9NM 2001091400073 20010914 00073 CE 2001 9 14 2001FA0000270 1 20010912 G 3340 4502131 MOTOR CESSNA 650 650 2076802 CE LANDING LIGHT FAILED C K NONE O OTHER DE DESCENT 1 GL 10 733K 6500222 UNIT RECEIVED AND INSTALLED. OPERATED UNIT 3 CYCLES AND ON 4 EXTENSION UNIT WOULD NOT EXTEND AND MOTOR SEIZED AND SMELL ED OF BURNING ELECTRICAL WIRING. UNIT WAS PURCHASED THRU CESSNA AS AN OVERHAULED PART BY AN OUTSIDE VENDOR. THE UNIT HAS A HISTORY OF EARLY FAILURE AFTER OVERHAUL. THIS COMPANY HAS HAD FIVE WARRANTY ACTIONS CLAIMED ON THIS PART NUMBER. 2 L 7 2 4F A9NM 2001091400074 20010914 00074 CE 2001 9 14 2001FA0000271 1 20010912 G 3340 4502131 MOTOR CESSNA 650 650 2076802 CE LANDING LIGHT DEFECTIVE C K NONE O OTHER DE DESCENT 1 GL 10 733K 6500222 UNIT RECEIVED AND INSTALLED. WHEN LIGHT IS RETRACTED, UNIT CONTINUES TO RUN WITH A GRINDING NOISE AND MOTOR WILL NOT SH UT OFF. UNIT WAS NOT ADJUSTED ON INSTALLATION. UNIT WAS PURCHASED THRU CESSNA AS AN OVERHAULED PART BY AN OUTSIDE VEND OR. THE UNIT HAS A HISTORY OF EARLY FAILURE AFTER OVERHAUL. THIS COMPANY HAS HAD FIVE WARRANTY ACTIONS CLAIMED ON THIS PART NUMBER. 2 L 7 2 4F A9NM 2001091400076 20010914 00076 CE 2001 9 14 2001FA0000272 1 20010912 G 3340 4502131 LANDING LIGHT CESSNA 650 650 2076802 CE GARRTT TFE731 TFE731* 01518 WP EXTERIOR DAMAGED D K NONE W INADEQUATE Q C IN INSP/MAINT 1 SO 01 733H 6500210 RECEIVED THIS PART FROM CESSNA WITH UNDAMAGED PACKING. THE GROUND LUG WAS BENT, LOOSE AND HAD DAMAGED THREADS. THIS PA RT WAS PROPERLY PACKED WITH SPRAYED IN FOAM. THIS PART WAS DAMAGED PRIOR TO BEING PLACED IN THE BOX. 2 L 7 2 4F 4 F A9NM E6WE 2001091400078 20010914 00078 CE 2001 9 14 2001FA0000273 1 20010912 G 3340 4502131 MOTOR CESSNA 650 650 2076802 CE LANDING LIGHT FAILED D K NONE L NO TEST IN INSP/MAINT 1 SO 01 733H 113 113 6500210 RETRACTABLE LIGHT WOULD NOT EXTEND. IT SEEMS TO ME THAT AN AIRCRAFT PART SHOULD BE CAPABLE OF STAYING IN SERVICE FOR MO RE THAN 113.7 HOURS. 2 L 7 2 4F A9NM 2001091700139 20010917 00139 NM 2001 9 17 2001FA0000274 1 20010808 G 2760 654494715 HOUSING BOEING BOEING 737 737* NM SPOILER ACTUATOR CRACKED B IU6R K NONE O OTHER IN INSP/MAINT 1 NM 01 10268 HOUSING IS CRACKED ON THE OPPOSITE SIDE OF THE PORTS. INSTALL HOUSING PN 65-44947-15. NOTE: HOUSING IS PN 65-44947-15 AND IS THE REPLACEMENT TO SOLVE PROBLEMS OF CRACKS NOTED ON PREVIOUS HOUSING DASH NUMBERS PER SL. 2 L 7 2 4F RT A16WE 2001091700140 20010917 00140 NM 2001 9 17 2001FA0000275 1 20010808 G 2760 654494710 HOUSING BOEING 737 737* NM ACTUATOR CRACKED B IU6R K NONE O OTHER IN INSP/MAINT 1 NM 01 15735 HOUSING IS CRACKED ON THE LOWER SHOULDER NEAR BEARING MOUNT LUG. INSTALL HOUSING PN 65-44947-15. 2 L 7 2 4F RT A16WE 2001091700142 20010917 00142 NM 2001 9 17 2001FA0000276 1 20010808 G 2760 65C268636 HOUSING BOEING BOEING 737 737* NM ACTUATOR CRACKED B IU6D K NONE O OTHER IN INSP/MAINT 1 NM 01 30072 WN0009 HOUSING IS CRACKED AND BROKEN AT THREADED AREA. FATIGUE/OVERSTRESSED. 2 L 7 2 4F RT A16WE 2001091700148 20010917 00148 NM 2001 9 17 2001FA0000277 1 20010723 G 2730 401606223 HOUSING BOEING 727 727 UTILSYS NM SEAL PLATE CORRODED B IU6R K NONE O OTHER IN INSP/MAINT 1 NM 01 HOUSING ASSEMBLY IS CORRODED ON THE SEAL PLATE SURFACE, IN THE CHECK VALVE PORTS AND BOLT HOLES. HOUSING ASSEMBLY IS MA DE FROM MAGNESIUM ALLOY AND IS EXTREMELY SUSCEPTIBLE TO DISSIMILAR METAL CORROSION AND CRACKS. 2 L 7 3 4J RT A3WE 2001091700149 20010917 00149 NM 2001 9 17 2001FA0000278 1 20010716 G 2730 401606223 HOUSING MOOG BOEING 727 727* NM SEAL PLATE CORRODED B IU6R K NONE O OTHER IN INSP/MAINT 1 NM 01 1433D HOUSING ASSEMBLY IS CORRODED ON THE SEAL PLATE SURFACE, IN THE CHECK VALVE PORTS AND BOLT HOLES. HOUSING ASSEMBLY IS MA DE FROM MAGNESIUM ALLOY AND IS EXTREMELY SUSCEPTIBLE TO DISSIMILAR METAL CORROSION AND CRACKS. 2 L 7 3 4F RT A3WE 2001091700150 20010917 00150 NM 2001 9 17 2001FA0000279 1 20010716 G 2760 654494710 HOUSING BOEING BOEING 727 727 UTILSYS NM ACTUATOR CRACKED B IU6R K NONE O OTHER IN INSP/MAINT 1 NM 01 41454 0970 HOUSING IS CRACKED ON THE OPPOSITE SIDE OF THE PORTS. INSTALL HOUSING PN 65-44947-15. 2 L 7 3 4J RT A3WE 2001091700152 20010917 00152 NM 2001 9 17 2001FA0000280 1 20010716 G 2760 654494710 HOUSING BOEING BOEING 737 737 UTILSYS NM ACTUATOR CRACKED B IU6R K NONE O OTHER IN INSP/MAINT 1 NM 01 50886 0893 HOUSING IS CRACKED ON THE OPPOSITE SIDE OF THE PORTS. INSTALL HOUSING PN 65-44947-15. 2 L 7 2 4F RT A16WE 2001091700153 20010917 00153 NM 2001 9 17 2001FA0000281 1 20010717 G 3230 65179547 HOUSING BOEING BOEING 727 727 UTILSYS NM ACTUATOR CRACKED B IU6R K NONE O OTHER IN INSP/MAINT 1 NM 01 RC707 THE HOUSING HAD A CRACK IN THE CENTER OF THE BARREL. 2 L 7 3 4J RT A3WE 2001091700154 20010917 00154 CE 2001 9 17 2001FA0000282 1 20010811 G 3233 12416195F ACTUATOR CESSNA 210 210L 2073448 CE CONT O520 IO520* 17032 SO MLG CRACKED G K NONE O OTHER IN INSP/MAINT 1 SW 11 8137L 21060624 LEFT MAIN GEAR ACTUATOR CRACKED, RESULTING IN THE LOSS OF HYDRAULIC FLUID. AIRCRAFT MADE A GEAR UP LANDING, AIRCRAFT HA S SUBSTANTIAL DAMAGE TO HORIZONTAL STABILIZER AND ELEVATOR. 1 H 7 1 3O 3 O 3A21 E5CE 2001091700110 20010917 00110 SO 2001 9 17 2001FA0000286 2 20010825 G 7414 4301 MAGNETO CESSNA 150 150G 2071816 CE CONT O200 O200A 17020 SO ENGINE INOPERATIVE C A UNSCHED LANDING R PARTIAL RPM/PWR LOSS CL CLIMB 1 SW 99 2750S 15066650 54877A INSTALLED NEW LEFT AND RIGHT SIDE SLICK (UNISON) MAGNETOS AND IGNITION HARNESS. TEST RUN OK. ON FIRST FLIGHT AFTER 15 M IN. ENGINE POWER LOSS OCCURED. AFTER LANDING FOUND LEFT MAG INOP. REMOVED MAG AND FOUND THAT COIL INSULATION HAD BURNED THROUGH AND HIGH VOLTAGE WAS ARCING TO CASE OF MAG THROUGH COIL INSULATION. 1 H 7 1 3O 3 O 3A19 E252 2001091700112 20010917 00112 NE 2001 9 17 2001FA0000287 2 20010807 G 8500 ENGINE WSK M18 M18DROMADER 9810102 EU WSK PZL PZLM18 67203 NE WSK US132 US132000A NE NACELLE MALFUNCTIONED G K NONE O OTHER AG AGRICULTURE 1 SW 11 4206B 1Z00507 FLYING IN CRUISE WHEN BUTTERFLY ON INTAKE STARTED FLUCUATING. PULLED UP AND REDUCED POWER. APPROXIMATELY 10 SECONDS LATE R LOST POWER. ACFT. HIT LOW LEVEE SKIDDED ACROSS FIELD AND HIT SECOND LEVEE. UPON STRIKING SECOND LEVEE ACFT. ROLLED OVE R ON ITS NOSE AND SKIDDED TO A REST UPSIDE DOWN IN A RICE FIELD. 1 L 7 1 3O 4 R A47EU E10NE 5 C P4NE 2001091700120 20010917 00120 SO 2001 9 17 2001FA0000292 1 20010905 G 3220 AN3105MS24665 COTTER PIN PIPER PA28 PA28R201 7102816 SO NLG MISSING B A UNSCHED LANDING D J INFLIGHT SEPARATION WARNING INDICATION LD LANDING 1 GL 21 279ND 599 2844034 DURING A TRAINING FLIGHT, UPON GEAR RETRACTION THE CFI HEARD A THUMP FROM THE NOSE AREA.THE GEAR UNSAFE LIGHT DIDNT EXTI NGUISH. MLG EXTEND WAS ATTEMPTED , DIDNT RECEIVE A NLG DOWN AND LOCKED INDICATION. RETRACTION AND EMERGENCY EXTEND WAS A TTEMPTED. PERFORMED A FLYBY AND WERE INFORMED THE NLG WAS TRAILING. UPON LANDING THE NLG COLAPSED UPON INSPECT BY MAINT , IT WAS FOUND COTTERPINS WERE MISSING FROM THE NLG SPRING ARM ASSY PIVOT BOLT. ALLOWED THE BOLT TO BACK OUT OF POSITION ALLOW RELEIVING THE TENSION ON THE ARM NOT ALLOWING TO TRAVEL TO FULL DOWN AND LOCK. INSPECTION OF THE BOLT SHOWED NO E VIDENCE OF A BROKEN COTTER PIN OR DAMAGE TO THE THREADS OF THE BOLT. 3 WASHERS REMAINED ON THE THREAD SIDE OF THE BOLT. 1 L 7 1 3O 2A13 2001091700133 20010917 00133 NM 2001 9 17 2001FA0000294 1 20010907 G 6700 500N711311 CONTROL ROD DOUG 600N 600N 3027377 NM NOTAR FAN DAMAGED D K NONE O OTHER IN INSP/MAINT 1 SW 99 957SD RNO11 DURING REMOVAL OF THE AFT FAN (NOTAR) CONTROL ROD P/N 500N7113-11 WE FOUND SOME CONTACT DAMAGE. IT APPEARS THIS ROD IS M AKING CONTACT WITH THE FAN GEARBOX OUTPUT GEARSHAFT I.D. 1 G 7 1 3U NC H3WE 2001091700155 20010917 00155 GL 2001 9 17 2001FA0000295 1 20010726 G 7100 PISTON AMTR MONG MONG 0565379 GL ENGINE BURNED C K NONE O OTHER IN INSP/MAINT 1 GL 23 426RT 60 214 NR 1 PISTON ON 2 CYCLE EXPERIMENTAL POWER PLANT BURNED THRU RESULTING IN LOSS OF POWER, RESULTING IN CRASH. DTW 2001 05 6- C-NR 1 01LA0155. 1 Q 7 1 3O NC EXPA1Q71 2001091700135 20010917 00135 NM 2001 9 17 2001FA0000296 1 20010907 G 6700 500N711311 CONTROL ROD DOUG 600N 600N 3027377 NM NOTAR FAN DAMAGED D K NONE O OTHER IN INSP/MAINT 1 SW 99 958SD RNO18 DURING REMOVAL OF THE AFT FAN (NOTOR) CONTROL ROD P/N 500N7113-11 WE FOUND SOME CONTACT DAMAGE. IT APPEARS THIS ROD IS M AKING LIGHT CONTACT WITH THE FAN GEARBOX OUTPUT GEARSHAFT I.D. AND THE FAN SUPPORT SHAFT I.D. 1 G 7 1 3U NC H3WE 2001091700156 20010917 00156 NM 2001 9 17 2001FA0000297 1 20010829 G 6230 A4801 BOOT ROBSIN ROBSIN R22 R22BETAII 7640110 NM LYC O360 VO360* 41514 EA SWASHPLATE SPLIT D K NONE O OTHER IN INSP/MAINT 1 NM 02 2223P 153 3573 2962 FOUND SWASHPLATE BOOT SPLIT OPEN AT THE CENTER FOLD. SPLIT WAS APPROX 4 TO 6 INCHES IN LENGTH. 1 G 7 1 3O 3 O H10WE 1E1 2001091800001 20010918 00001 SO 2001 9 18 2001FA0000298 1 20010626 G 2720 62701008 CONTROL CABLE PIPER PA32 PA32301T 7103209 SO RUDDER BROKEN G K NONE O OTHER IN INSP/MAINT 1 EA 11 8108W 328024002 DURING ANNUAL INSPECTION, FOUND LEFT AFT RUDDER CABLE TURNBUCKLE THREADED SWAGED END BROKEN AT THREADED END THAT SCREWS INTO TURNBUCKLE BARREL. SAFETY WIRE WAS ONLY THING THAT PREVENTED COMPLETE LOSS OF RUDDER CONTROL. 1 L 7 1 3O A3SO 2001091900251 20010919 00251 GL 2001 9 19 2001FA0000300 2 20010623 G 7200 ENGINE BELL 206 206B 1181511 SW ALLSN 250C 250C20 03013 GL NACELLE MALFUNCTIONED C A UNSCHED LANDING X J ENGINE FLAMEOUT WARNING INDICATION CL CLIMB 1 SW 99 34698 4324 DEPARTING THE AIRPORT, THE ENGINE FLAMED OUT OR SURGED. THE ENGINE WAS RUN ON A TEST CELL. TEST CELL SHOWED: 1)A CYCLI NG ANTI-ICE VALVE SOLENOID. 2) A RICH FUEL FLOW. 3) A WARPED OUTER COMBUSTION CHAMBER. THIS TOGETHER, COULD CAUSE A SURGE. 1 G 7 1 3U 3 U H2SW E4CE 2001091900253 20010919 00253 GL 2001 9 19 2001FA0000301 2 20010727 G 7320 SPRING BENDIX BELL 206 206L3 1182108 SW ALLSN 250C 250C30P 03013 GL CONTROL ARM DEFECTIVE C K NONE O OTHER IN INSP/MAINT 1 SW 99 3209G 1694 330958 51567 895634 THE FUEL CONTROL OVERCENTER SPRING IS SO STRONG THAT IS WILL RUN THE RPM AND TOUQUE UP UNCOMMANDED. THIS TIME IT CAUSED AN OVER TORQUE OF 115 PERCENT FOR 1 SECOND. 1 G 7 1 3U 3 U H2SW E1GL 2001091900003 20010919 00003 SO 2001 9 19 2001FA0000302 1 20010702 G 7160 71713 TUBE PIPER PA44 PA44180 7104402 SO LYC O360 LO360E1A6 41514 EA NR 3 CYLINDER CRACKED C K NONE O OTHER IN INSP/MAINT 1 SW 15 9290P 1508 99 4496019 RL48371A FOUND NR 3 INTAKE TUBE LEAKING AT 100 HOUR INSPECTION. REMOVED TUBE AND FOUND A CRACK AT FLANGE CRACK APPEARS TO HAVE B EEN REPAIRED BUT WELD DOESNT COVER THE WHOLE CRACK. 1 L 7 2 3O 3 O A19S0 E286 2001091900001 20010919 00001 EA 2001 9 19 2001FA0000305 2 20010918 G 8510 LW13792 SEAL PIPER PA30 PA30 7103002 SO LYC O320 IO320B1A 41508 EA HARTZL HCE2Y HCE2YL2 GL ENGINE FAILED C A UNSCHED LANDING K FLUID LOSS CR CRUISE 1 SW 99 7331Y 80 30292 L76455 DURING A CROSS-COUNTRY FLIGHT BETWEEN CNO AND SPF (31 AUG 01 THRU 3 SEP 01), OIL STREAKS FROM THE NOSE BOWLS OF BOTH ENG INES INCREASED WITH EACH LEG. UPON RETURN TO CNO, COWLS AND PROPELLERS HAVE BEEN REMOVED. DURING INSPECTION OF ENGINE NOSE SEALS, BOTH SEALS HAVE BEEN "BLOWN OUT" OF THE CASE, AND ARE HANGING FROM THE CRANKSHAFT BETWEEN THE CASE AND PROP FLANGE. BOTH ENGINES HAVE 80 HOURS SINCE OVERHAUL BY LYCOMING. ENGINE OIL ANALYSIS WILL BE PERFORMED AND FILTERS CUT OPE N FOR INSPECTION. 1 L 7 2 3O 3 O A1EA 1E12 5 C P9EA 2001091900002 20010919 00002 CE 2001 9 19 2001FA0000307 1 20010918 G 5280 BRACKET BEECH 36 A36 1151604 CE MLG DOOR CRACKED A K NONE O OTHER IN INSP/MAINT 1 SO 15 373DR E3373 WHILE PERFORMING ANNUAL INSPECTION A CRACKED BRACKET WAS FOUND AT THE REAR RIGHT INBOARD GEAR DOOR HINGE. UPON REMOVING THE WING-TO-FUSELAGE CLOSEOUT PANEL IT WAS DISCOVERED THAT THE FORWARD TWO INBOARD GEAR DOOR HINGE BRACKETS WERE ALSO C RACKED. CAUSE UNKNOWN. 1 L 7 1 3O 3A15 2001092000003 20010920 00003 EA 2001 9 20 2001FA0000309 2 20010821 G 7313 INJECTOR CESSNA 172 172R 2072401 CE LYC IO360 IO360L2A EA ENGINE MALFUNCTIONED C O OTHER R PARTIAL RPM/PWR LOSS NR NOT REPORTED 1 SW 17 172RC 17280204 ENGINE FAILED TO DEVELOP FULL POWER AFTER LONG POWER OFF DECENT AT HIGH DENSITY ALTITUDE CONDITIONS. CORRECTIVE ACTIONS TAKEN: FUEL INJECTOR SERVO REPAIRED BY CRS/NE2R WO R01-042240. FLOW DIVIDER MODIFIED IAW SI. C/W SI AND SB. 1 H 7 1 3O 3 O NT 3A12 1E10 2001092000006 20010920 00006 SO 2001 9 20 2001FA0000310 1 20010904 G 2922 53E19600 VALVE PIPER PA32 PA32300 7103212 SO LYC O540 TIO540* 41532 EA THERMAL BYPASS MISMANUFACTURED D K NONE O OTHER IN INSP/MAINT 1 SW 99 4087R 1087 3240405 NUT CAME OFF THE THERMOSTATIC BYPASS VALVE AND FELL INTO THE OIL SUMP. CUSTOMER COMPLAINT, HIGH OIL TEMPERATURE. 1 L 7 1 3O 3 O A3SO E14EA 2001092000007 20010920 00007 CE 2001 9 20 2001FA0000311 1 20010822 G 8011 S1577A1 CONTACTOR CESSNA 182 R182 2072734 CE LYC O540 O540* 41532 EA STARTER FAILED D K NONE O OTHER IN INSP/MAINT 1 NE 03 4373R 138 R18200595 CONTACTOR FAILED/ CLOSED CAUSING STARTER TO BURN OUT. THIS IS SECOND FAILURE OF A NEW CONTACTOR IN LESS THAN 140 HOURS. (ONE STARTER CONTACTOR, ONE MASTER CONTACTOR) 1 H 7 1 3O 3 O RT 3A13 E295 2001092000012 20010920 00012 EU 2001 9 20 2001FA0000312 1 20010919 G 7160 430110217 MODULATOR BOLKMS 117 BK117B2 5626013 EU LYC LTS101 LTS101600A 41560 NE AIRFLOW LOOSE D K NONE O OTHER IN INSP/MAINT 1 NM 07 7059N 7154 WHILE TROUBLESHOOTING ENGINE FOR SURGING PROBLEM. AIRFLOW MODULATOR WAS CHANGED. FILTER ELBOW HAS TO BE TRANSFERED TO NEW MODULATOR. FOUND FILTER SCREEN TO BE LOOSE INSIDE ELBOW AT THIS TIME. BROKEN FILTER HAD NO EFFECT ON THIS SURGING PROBLEM. MUST INSPECT FILTER ELBOW WHEN CHANGING AIRFLOW MODULATOR. 1 G 7 2 3U 3 U NC H13EU E5NE 2001092400007 20010924 00007 EU 2001 9 24 2001FA0000313 1 20010530 G 3510 A1B0BR14 PRESSURE SWITCH STBROS SD3 SD330 8100602 EU OXYGEN SYSTEM LEAKING C U4FM K NONE O OTHER IN INSP/MAINT 1 NM 05 173Z 1 SH3116 WHILE SERVICING THE OXYGEN SYSTEM, THE HIGH PRESSURE TRANSDUCER SHAFT SEAL BLEW OUT. THIS PRESSURE SWITCH IS PART OF AN STC MODIFICATION TO CERTIFY THE AIRCRAFT AS A SD3-30, . THIS IS SECOND OCCURANCE OF THIS FAILURE. THE FIRST FAILURE W AS ASSUMED TO BE THAT THE WRONG PN, LOW PRESSURE TRANSDUCER HAD BEEN INSTALLED. UPON REPLACEMENT OF THE SECOND UNIT TAE MAXIMUM PRESSURE OF 750 PSIG IS FAR BELOW THE 1800 PSIG SYSTEM PRESSURE. 2 H 7 2 4T A41EU 2001092100002 20010921 00002 GL 2001 9 21 2001FA0000314 3 20010805 G 6110 HCE5N3 PROPELLER PIAGIO P180 P180 6960204 EU PWA PT6 PT6* 52043 EA HARTZL HCE5N HCE5N3 GL NR 2 DAMAGED C O OTHER E VIBRATION/BUFFET TX TAXI/GRND HDL 1 WP 11 705PA 347 127 1014 HF42 AIRCRAFT LANDED RENO, PILOTS NOTICED DIFFICULTY GETTING PROP INTO BETA AND SLIGHT VIBRATION DURING ROLLOUT. AT HANGER, PILOTS NOTICED LOWER NG ON NR 1 ENGINE ADN ON SHUTDOWN. NR 1 PROP STAYED IN A FLIGHT PITCH ANGLE WHILE NR 2 PROP WENT T O FEATHER PER NORMAL OPS. ON TEARDOWN AT PROP SHOP, NR 1 PROP WAS FOUND TO HAVE INTERNAL DAMAGE. 1 H 7 2 3O 3 T RT A59EU E2NE 5 C PZONE 2001092000027 20010920 00027 GL 2001 9 20 2001FA0000315 2 20010801 G 7230 6890550 SCROLL BELL 206 206B 1181511 SW ALLSN 250C 250C20B 03013 GL COMPRESSOR CRACKED B K NONE O OTHER IN INSP/MAINT 1 SW 09 108FH 4205 2770 CAE831748 WHILE TROUBLESHOOTING CAUSE OF HIGH TOT, AIR LEAK WAS DISCOVERED AROUND UPPER PORTION OF COMPRESSOR. FURTHER INVESTIGAT ION REVEALED A CRACK APPROXIMATELY 3.810 INCHES LONG IN AREA BETWEEN CUSTOMER BLEED AIR PORT AND FORWARD OF DIFFUSER. C RACK DID NOT ORIGINATE AROUND WELD. APPLYING HAND PRESSURE UPON BLEED AIR PORT, THE SCROLL MATERIAL CAN BE SEEN LIFTING UP. A COMBINATION OF VIBRATORY STRESS AND METAL FATIGUE ARE FACTORS. 1 G 7 1 3U 3 U H2SW E4CE 2001092000002 20010920 00002 CE 2001 9 20 2001FA0000316 1 20010919 G 7120 045100336 MOUNT CESSNA 150 152 2071835 CE LYC O235 O235L2C 41505 EA MCAULY 1A103 1A103TCM GL ENGINE GROOVED D K NONE O OTHER IN INSP/MAINT 1 SW 99 5362M 3357 1003 15284562 L2084215 R776391 1. DURING A ROUTINE INSPECTION, TWO ENGINE MOUNT DIAGONALS WERE FOUND TO HAVE WORN AREAS ON THEM CAUSED BY THE BATTERY T RAY FLEXING DOWN AGAINST THE MOUNT AND FROM A STAINLESS STEEL TAG ON THE OIL PRESSURE LINE.2. THE CLAMP THAT SUPPORTS TH E BATTERY TRAY ON THE MOUNT SHOULD BE CHECKED ON A REGULAR BASIS TO MAKE SURE IT IS TIGHT AND WILL NOT ALLOW ANY CONTACT WITH THE MOUNT.3. ALL LINES ADJECENT TO THE MOUNT SHOULD BE CHECKED TO ENSURE THAT NO TAGS WILL CAUSE ANY CONTACT WITH THE MOUNT. 1 H 7 1 3O 3 O NT 3A19 E223 5 N P50GL 2001092100003 20010921 00003 GL 2001 9 21 2001FA0000317 3 20010814 G 6110 B4459 PIN MCAULY CESSNA 402 402B 207590P CE CONT O520 TSIO520VB 17040 SO MCAULY 3AF32C 3AF32C87 GL PROPELLER CRACKED C LU4R K NONE O OTHER IN INSP/MAINT 1 SO 17 403GC 733162 402B0305 733162 PROPELLER SHOWS RELEVENT INDICATION. 1 L 7 2 3O 3 O A7CE E8CE 5 C P22EA 2001092100004 20010921 00004 EU 2001 9 21 2001FA0000318 1 20010830 G 5753 T700A5755060000 CARRIAGE SOCATA TBM TBM700 8682000 EU PWA PT6 PT6* 52043 EA LEFT FLAB IB WORN C VY2R K NONE O OTHER IN INSP/MAINT 1 EA 23 5HT 1950 9 AFTER REMOVAL OF LEFT FLAP, DISCOVERED LEFT INBOARD CARRIAGE, PART LISTED ABOVE AND ACTUATOR NUT COVER, PN T700A2750029 000, WORN FROM CONTACT WITH ACTUATOR NUT. WEAR APPEARS TO BE FROM WORN BUSHINGS IN CARRIAGE AND ACTUATOR NUT COVER AS W ELL AS WEAR IN LOCATOR PINS IN ACTUATOR NUT. FOUND SAME WEAR IN RIGHT INBOARD FLAP CARRIAGE, PN T700A5755060001 AND ACT UATOR NUT COVER COVER PN T700A2755063000 AND ACTUATOR NUT COVER PN T700A2750029000. 1 L 7 1 3T 3 T RT A60EU E2NE 2001092100005 20010921 00005 SO 2001 9 21 2001FA0000319 2 20010904 G 7414 GEAR CESSNA 207 207A 2073604 CE CONT O520 IO520F 17032 SO MAGNETO DAMAGED C K NONE O OTHER IN INSP/MAINT 1 AL 05 54GV 427 20700447 818885R DURING ENGINE RUN UP TO ANALYZE A FUEL FLOW PROBLEM, IT WAS DISCOVERED THAT THE RIGHT MAGNETO WAS DEAD. SUBSEQUENT INVE STIGATION REVEALED THAT THE RIGHT MAGNETO WAS INTERNALLY LOCKED AND FOUND THAT THE MAGNETO DRIVE GEAR AND THE ACCESSORY DRIVE GEAR WAS UNSERVICEABLE. MAGNETO BEING SENT TO MFG FOR EVALUATION. 1 H 7 1 3O 3 O A16CE E5CE 2001092100006 20010921 00006 CE 2001 9 21 2001FA0000320 1 20010820 G 3510 510010951 LINE CESSNA 425 425 2076018 CE PWA PT6 PT6* 52043 EA OXYGEN SYSTEM DETERIORATED C K NONE O OTHER IN INSP/MAINT 1 CE 07 900MS 5390 4250079 LEFT SIDE WALL WAS REMOVED TO INSTALL RADIO EQUIPMENT. THE VERTICAL DUCT FOR AIR TO OVERHEAD WEMAC SHOWED DEFINITE SIGN S OF BURNING AND SEVERE DETERIORATION. UPON FURTHER EXAMINATION, THE OXYGEN LINE CROSSING DUCT HAD SEVERE CORROSION WHE RE CONTACT BETWEEN THE LINE AND DUCT HAD OCCURRED, AND HAD 2 HOLES IN THE LINE. WHEN THE OXYGEN WAS TURNED ON, OXYGEN W AS SPRAYED ON DUCT AND BEHIND SIDEWALL OF AIRCRAFT. MANUFACTURED NEW LINE TO REPLACE CORRODED LINE. INSTALLED NEW DUCT . SPIRAL WRAPPED OXYGEN LINE WHERE CONTACT WITH DUCT OCCURS. 1 L 7 2 3T 3 T RT A7CE E2NE 2001092400008 20010924 00008 CE 2001 9 24 2001FA0000322 1 20010605 G 2421 99105921 ALTERNATOR CESSNA 206 U206G 2073356 CE ENGINE MALFUNCTIONED C O OTHER O OTHER NR NOT REPORTED 1 NE 02 9933Z 187 U20606754 OPERATOR REPORTED EXCESSIVE NOISE IN HEADSET FROM RADIOS. TROUBLESHOOTING FOUND NOISE DISAPPEARED WITH ALTERNATOR OFF L INE. FURTHER INVESTIGATION FOUND MAGNETIC COMPASS DEVIATION OF 20 DEGREES WITH ALTERNATOR ON LINE. ELECTRICAL SYSTEM W IRING GROUNDS, BONDING AND SHIELDING CHECKED. IN LINE NOISE FILTERS HAD NO AFFECT ON NOISE EMISSION. INSTALLED THREE ALTERNATORS, SN: A-160134, A-160136, AND A-160130 WITH NO CHANGES IN NOISE OR COMPASS DEVIATION. INSTALLED ALTERNATIVE MFG/ELECTRO SYSTEMS ALTERNATOR, PART NUMBER E3FF10300AA, WHICH ELIMINATED RADIO NOISE AND MAGNETIC COMPASS DEVIATION. 1 H 7 1 3O A4CE 2001092400009 20010924 00009 CE 2001 9 24 2001FA0000323 1 20010918 G 2752 505211516 PISTON BEECH BEECH B300 B300 1159232 CE FLAP ACTUATOR CRACKED C K NONE K FLUID LOSS IN INSP/MAINT 1 SW 99 988ME 4611 935A91 FL77 RIGHT OUTBOARD FLAP ACTUATOR CRACKED AT BASE OF PISTON WHERE THE END PLUG IS ATTACHED. THE CRACK WAS 1.5 INCHES LONG AN D RESULTED IN THE LOSS OF THE LUBRICATING OIL FROM OUT OF THE PISTON AND SCREW ASSEMBLY. THE LOSS OF OIL WAS THE FIRST INDICATION OF A PROBLEM, AND IT WAS WHILE INVESTIGATING THE OIL LEAK THAT THE CRACK WAS DISCOVERED.THIS CRACK COULD RESU LT IN A SIGNIFICANT LOSS OF STRUCTURAL STRENGTH OF THE ACTUATOR WHICH COULD RESULT IN THE STRUCTURAL FAILURE OF THE ACTU ATOR ASSEMBLY. 2 L 7 2 4T RT A24CE 2001092400002 20010924 00002 SW 2001 9 24 2001FA0000324 1 20010827 G 5313 17031725 STRINGER GULSTM 690TP 690D 3970405 SW LT WING INBD CORRODED B K NONE O OTHER IN INSP/MAINT 1 SW 99 120EK 5552 15026 WHILE REPLACING FUEL BAG, STRINGER 6A, LEFT WING INBOARD WAS FOUND TO BE AFFECTED BY GENERAL SURFACE AND PITTING CORROSI ON. THE CORROSION ON THE STRINGER WAS LOCATED BETWEEN WING STATION 24 AND 39, AND AFFECTED THE STRINGER UP TO AN APPROX IMATE DEPTH OF .08 INCHES. THE CORROSION WAS POSSIBLY CAUSED BY WATER BEING TRAPPED BETWEEN THE STRINGER AND THE FUEL B AGS. WATER MAY HAVE ENTERED THROUGH WING ACCESS PANELS LOCATED ABOVE FUEL BAGS. THE ADDITION OF DRAIN HOLES IN THIS AR EA, AND A POSITIVE SEAL ON UPPER WING INSPECTION PANELS MIGHT PREVENT THIS CORROSION FROM OCCURING. (M) 1 H 7 2 3T 2A4 2001092400003 20010924 00003 2001 9 24 2001FA0000325 4 20010824 G 6113 055032110 SPINNER CESSNA 172 172S 2072439 CE MCAULY 1A170 1A170E GL PROPELLER DAMAGED A K NONE O OTHER IN INSP/MAINT 1 SW 99 435ER 172S8652 NUTPLATE BROKEN OFF. CHANGED NUMEROUS SPINNERS AND BACK PLATES BECAUSE THE PRE-DRILLED HOLES DO NOT LINE UP WITH THE NU TPLATES ON THE SPINNER BACK PLATE. THIS IS A COMMON PROBLEM WITH THIS A/C MODEL R/S. (M) 1 H 7 1 3O NT 3A12 5 N P857 2001092400004 20010924 00004 CE 2001 9 24 2001FA0000326 1 20010811 G 5610 303 WINDSHIELD CESSNA 150 152 2071835 CE COCKPIT CRACKED B O OTHER O OTHER NR NOT REPORTED 1 SW 99 714TW 15279429 WINDSHIELD CRACKED DIRECTLY ABOVE COMPASS BLOCK AND SMALL SECTION 12 INCHES BY 6 INCHES WITH COMPASS ATTACHED. SUSPECT CRACK DEVELOPED ABOVE COMPASS BLOCK, PERHAPS BY FUELER LEANING ON WINDSHIELD, AND THEN CONTINUED TO DEVELOP CRACK UNTIL SECTION LOST INTERGRITY AND FELL INWARD INTO CABIN. (M) 1 H 7 1 3O NT 3A19 2001092400005 20010924 00005 GL 2001 9 24 2001FA0000327 1 20010829 G 7120 MOUNT CIRRUS SR SR20 05628AJ GL ENGINE DAMAGED D O OTHER O OTHER LD LANDING 1 SW 99 168CD 144 1079 MADE A HARD LANDING, THE AIRCRAFT HAD PORPOISED HITTING HARD ON 2ND OSC. UPON INSPECTION IT WAS FOUND THAT THE LDG SHOC K PUCKS WERE DEFORMED AND THE REBOUND PUCKS, ONE OF WHICH WAS MISSING, WITH THE MOUNT WASHERS BENT. ALSO, THE SHOCK PUC K MOUNT PLATE STUD'S WERE BENT, CLOSER INSPECTION REVEALED LIND SEED OIL AT THE WEB CLUSTER ADJACENT TO THE SHOCK MOUNT PLATE OF THE DIAGONAL SUPPORT TUBE, SHOCK MT SUPPORT TUBE AND A STIFFENER TUBE A DYE-PIN INSPECTION REVEALED A .5 INCH C RACK THROUGH THE WELD AT THE CLUSTER. (M) 1 H 7 1 3O NC A00009CH 2001092400006 20010924 00006 EA 2001 9 24 2001FA0000328 2 20010715 G 8500 BLOCK BEECH 23 B23 1151240 CE LYC O360 O360* 41514 EA ENGINE CRACKED G O OTHER Y J ENGINE STOPPAGE WARNING INDICATION AP APPROACH 1 SW 99 9815S M1799 2100436A AIRCRAFT WS ON FINAL APPROACH TO OCF, ENGINE WAS NOISY AND QUIT. AIRCRAFT MADE EMERGENCY LANDING ON HORSE RACE TRACK. OPENED COWLING, FOUND 3 INCH CRACK AFT, LEFT, TOPSIDE OF ENGINE BLOCK. ENGINE HAS 2776 HOURS SINCE OVERHAUL. 15 DAYS O UT OF ANNUAL INSPECTION. (M) 1 L 7 1 3O 3 O RT A1CE E286 2001092500002 20010925 00002 CE 2001 9 25 2001FA0000329 1 20010801 G 7603 AN54A BOLT BEECH 200 B200 1152922 CE PWA PT6 PT6A42 52043 NE ENGINE CONTROL BACKED OUT C K NONE O OTHER IN INSP/MAINT 1 NM 07 424RA 2393 BB1583 AN5-4A BOLT IN BOTTOM PIVOT POINT ROD ATTACHMENT BACKED OUT CAUSING LOSS OF ENGINE CONTROL. AN936B516 LOCK WASHER WAS P RESENT. 1 L 7 2 4T 4 T A24CE E4EA 2001092500003 20010925 00003 GL 2001 9 25 2001FA0000330 2 20010817 G 7230 230397911 SPLINE ADAPTER AGUSTA A109 A109A2 0260120 EU ALLSN 250C 250C20B 03013 GL COMPRESSOR ASSY FAILED C LN3R O OTHER X J ENGINE FLAMEOUT WARNING INDICATION NR NOT REPORTED 1 NM 01 55NW 15348 1814 7267 CAE834892 ENGINE SHUTDOWN DURING FLIGHT DUE TO FLAMEOUT. CAUSE: FAILURE OF SPLINED ADAPTER IN COMPRESSOR ASSEMBLY. 1 G 7 2 3U 3 U H7EU E4CE 2001092500004 20010925 00004 SO 2001 9 25 2001FA0000331 1 20010806 G 3230 PA402427 BOLT PIPER PA23 PA23250 7102308 SO LYC O540 IO540* 41532 EA DRAGLINK BROKEN G K NONE O OTHER IN INSP/MAINT 1 SO 15 63887 9000 277854032 BOLT SHEARED IN HALF, ALLOWING RIGHT MAIN LANDING GEAR TO COLLAPSE ON LANDING ROLL. BOLT SUSPECTED TO BE ORIGINAL. 1 L 7 2 3O 3 O 1A10 1E4 2001092500109 20010925 00109 2001 9 25 2001FA0000332 4 20010924 G 2565 1061323418 SLIDE BOEING 737 737 UTILSYS NM SERVICE DOOR FAILED B K NONE O OTHER IN INSP/MAINT 1 SW 15 23812 LT AFT SERVICE DOOR SLIDE FAILED TO FULLY INFLATE, WHILE COMPLYING WITH BOEING TASK CARD B25-61-35-C, OPERATIONAL CHECK OF ESCAPE SLIDE SYSTEMS. BOTTLE PSI WAS IN RED RANGE PRIOR TO TEST. 2 L 7 2 4F RT A16WE 2001092500001 20010925 00001 CE 2001 9 25 2001FA0000333 1 20010902 G 3244 505C66 TIRE BEECH 58 58P 1152744 CE MLG FAILED G O OTHER O OTHER TO TAKEOFF 1 SW 15 582TA 1208 905 TJ191 NOSE TIRE FAILED AND NOSE GEAR COLLAPSED. 1 L 7 2 3O A23CE 2001100100015 20011001 00015 CE 2001 10 1 2001FA0000337 1 20010813 G 3211 24900022 BUSHING CESSNA 172 172RG 2072438 CE LYC O360 O360F1A6 41514 EA GEAR ACTUATOR FAILED B K NONE O OTHER IN INSP/MAINT 1 SO 13 5199U 137 172RG0279 L1358536A BUSHING , INSTALLED ON MAIN GEAR ACTUATOR AS PART OF AD, HAS WORKED ITS WAY OUT OF HOUSING. PART HAS 137 HOURS SINCE I NSTALLED. THIS IS SECOND BUSHING FOUND BAD WITH FEW HOURS. 1 H 7 1 3O 3 O 3A17 E286 2001100100016 20011001 00016 CE 2001 10 1 2001FA0000338 1 20010730 G 3230 244110010 PIVOT CESSNA 172 172RG 2072438 CE LYC O360 VO360* 41514 EA RT MLG BROKEN B K NONE O OTHER IN INSP/MAINT 1 SO 13 9656B 921 172RG0949 RIGHT MAIN LANDING GEAR PIVOT PN 24411001-10 BROKEN, SHEARING OFF GEAR FROM PIVOT. THIS PART WAS INSTALLED ON 01/20/20 00, BEING THE NEW IMPROVED PIVOT. ON 05/28/2001 PIVOT WAS INSPECTED AND DYE PENTRANT FOR CRACKS PER AD AND SB. SERVICE KIT 172-151 INSTALLED. 113 HOURS LATER ON 07/27/2001 PIVOT BROKE. AIRCRAFT LANDED WITH NO DAMAGE. 1 H 7 1 3O 3 O 3A17 1E1 2001100200007 20011002 00007 2001 10 2 2001FA0000339 4 20010712 G 2562 LEAD BBAVIA 7 7EC 2110120 SW CONT C90 C90* 17009 SO ELT BATTERY SEVERED D K NONE L NO TEST IN INSP/MAINT 1 AL 01 4392C 7EC421 NEGATIVE LEAD FROM LOWER BATTERY COMPARTMENT TO TRANSMITTER WAS SEVERED DUE TO CORROSION. LOWER AND UPPER BATTERY. CON TACTS WERE CORRODED AND PLATING HAD FLAKED OFF. ONE OF THE EIGHT DURACELL BATTERIES WAS DEAD BUT NO CORROSION ON IT AND HAD NO BATTERY LEAKAGE. THIS FINDING WAS MADE DURING THE ANNUAL INSPECTION ON THIS AIRCRAFT. THE BATTERIES WERE ALL W ITHIN THEIR DUE DATES. 1 H 7 1 3O 3 O A759 E252 2001100100017 20011001 00017 CE 2001 10 1 2001FA0000340 1 20010801 G 2752 505212224 ACTUATOR BEECH 200 B200 1152922 CE PWA PT6 PT6* 52043 EA RT TE FLAPS CRACKED D K NONE O OTHER IN INSP/MAINT 1 SW 01 711HA 1818 BB1417 NORMAL FLIGHT OPERATION THE CENTER SHAFT OF THE ACTUATOR CRACKED THE ENTIRE LENGTH CAUSING FLAP BOUNCING SIMILAR TO BAD ROLLERS. RECOMMEND INSPECTING TOP AND BOTTOM OF ACTUATOR CENTER SHAFT DURING REGULAR PHASE INSPECTIONS. 1 L 7 2 4T 3 T A24CE E2NE 2001100100018 20011001 00018 CE 2001 10 1 2001FA0000341 1 20010822 G 7921 537312 PLATE CESSNA 310 310L 2074230 CE CONT O470 IO470D 17026 SO OIL COOLER WRONG PART G O OTHER W J INADEQUATE Q C WARNING INDICATION NR NOT REPORTED 1 NM 09 2209F 310L0009 ENGINE HAD LOST OIL PRESSURE DURING FLIGHT. AFTER A SAFE LANDING IT WAS DETERMINED THAT THE OIL HAD LEAKED OUT FROM THE BETWEEN THE OIL COOLER PLATE AND THE ENGINE. THE OIL COOLER PLATE ATTACHMENT NUTS WERE FOUND TO BE LOOSE. THE GASKET BETWEEN THE PLATE AND THE ENGINE WAS THE INCORRECT ONE. CONSULT THE APPROPRIATE PARTS BOOK AND INSTALL THE CORRECT PART . PROPERLY TORQUE ALL FASTENERS TO THE CORRECT SPECIFICATIONS. 1 L 7 2 3O 3 O 3A10 3E1 2001100100019 20011001 00019 CE 2001 10 1 2001FA0000342 1 20010806 G 2150 73838430 ACM CESSNA 750 750 2076810 CE ALLSN AE3007 AE3007C GL CABIN COOLING SEIZED G O OTHER J WARNING INDICATION NR NOT REPORTED 1 SW 11 750EC 1113 7500007 FORWARD AIR CYCLE MACHINE SEIZED DURING ROUTINE USAGE. PROBABLE CAUSE IS BEARING FAILURE. UNIT WAS OPERATED NORMALLY, AND WAS SERVICED AS SCHEDULED. 2 L 7 2 4J 4 F RT T00007WI TE6CH 2001100100020 20011001 00020 CE 2001 10 1 2001FA0000343 1 20010927 G 2910 6000100369 LINE LEAR 60 60LEAR 5170707 CE PWA 305 PW305A 52128 NE HYD SYSTEM FAILED G O OTHER K J FLUID LOSS WARNING INDICATION NR NOT REPORTED 1 WP 01 991DB 661 177 LEFT HYDRAULIC PRESSURE LINE FROM ENGINE TO HYDRAULIC MANIFOLD BROKE AT FLARE. 3 MILE FINAL EMPTIED HYDRAULIC RES INTO EQUIPMENT BAY/BAGGAGE COMPT. LINE REMOVED AND SENT TO MFG FOR EVALUATION. NOTE: RIGHT HYDRAULIC PRESSURE LINE REMOVED AND REPLACED AS WELL AND SENT IN FOR EVALUATION. 2 L 7 2 4F 4 F RT A10CE E35NE 2001100200008 20011002 00008 SO 2001 10 2 2001FA0000344 1 20010815 G 2121 313B57 ARMATURE DYNAMICAIR PIPER PA31 PA31P350 7103111 SO FAN WRONG PART G K NONE W INADEQUATE Q C IN INSP/MAINT 1 WP 23 CFZIC 702 FAN RETURNED TO MFG FOR OVERHAUL, THE FAN WAS DISASSEMBLED AND FOUND TO HAVE AN ARMATURE OF NOT MFG DESIGN. INSTALLED T HE ARMATURE LAMINATIONS ARE NOT COATED, ALLOWING THE ARMATURE TO RUST. THE WINDINGS HAVE EXCESSIVE COATING WHICH CAUSED THE ARMATURE TO RUB THE BRUSH HOLDER. THIS WAS COMPENSATED BY SOMEONE REPOSITIONING THE BRUSH HOLDER FURTHER AWAY FROM THE COMMUTATOR WHICH CAUSED AN IN ACCURATE BRUSH LOAD. 1 L 7 2 3O RT A8EA 2001100100036 20011001 00036 GL 2001 10 1 2001FA0000345 2 20010304 G 8510 BEARING AMTR LANCAR LANCAIRES GL AMTR CHEVY8 CHEVYV8 GL BELT DRIVE FAILED C O OTHER B SMOKE/FUMES/ODORS/SPARKS NR NOT REPORTED 1 WP 07 350N ES0261 1C947072 FLYING AT 5000 FEET, SAW SMOKE COME OUT OF FRONT OF COWL. PULLED POWER BACK. SMOKE QUIT. INCREASED POWER TO TRY TO MA KE AIRPORT. PROPELLER QUIT TURNING. AFTER CRASH, BELT MOSTLY GONE. LOOKS LIKE LOWER FRONT BEARING ON DRIVE SEIZED OR O VER HEATED AND CAUSED THE BELT TO FAIL. 1 L 7 1 3 V EXPA1L71 EXPE3V 2001100100038 20011001 00038 SO 2001 10 1 2001FA0000346 1 20010726 G 3213 6531904 CYLINDER PIPER PA28 PA28180 7102808 SO LYC O360 VO360* 41514 EA LANDING GEAR CRACKED C K NONE O OTHER IN INSP/MAINT 1 GL 13 15299 7733 287305051 CYLINDER, LANDING GEAR STUB AXLE AND OLEO PISTON ASSY 1 L 7 1 3O 3 O 2A13 1E1 2001100100039 20011001 00039 SO 2001 10 1 2001FA0000347 1 20010725 G 3213 7873805 AXLE PIPER PA28 PA28180 7102808 SO LYC O360 VO360* 41514 EA PISTON ASSY CRACKED C K NONE O OTHER IN INSP/MAINT 1 GL 13 15299 7733 287305051 CYLINDER, LANDING GEAR STUB, AXLE AND OLEO PISTON ASSY 1 L 7 1 3O 3 O 2A13 1E1 2001100100054 20011001 00054 CE 2001 10 1 2001FA0000348 1 20010727 G 2435 BEARING LUCAS LEAR 45 45LEAR 5170805 CE GARRTT TFE731 TFE731* 01518 WP STARTER GEN FAILED C O OTHER H J ELECT. POWER LOSS-50 PC WARNING INDICATION NR NOT REPORTED 1 GL 13 100KK 679 97514 065 AIRCRAFT EXPERIENCED RIGHT GENERATOR FAILURE. GENERATOR LINE CONTACTOR FAILED TO OPEN AUTOMATICLY AND CREW WAS UNABLE T O SELECT GENERATOR OFF. RIGHT AIRCRAFT MAIN POWER BUSS EXPERIENCED SPIKING WHICH RESULTED IN DAMAGING 3 OR THE MAIN POW ER DISTRIBUTION PANELS ALONG WITH MELTING THE SOLDER OUT OF THE STARTER/GENERATOR SPEED PICKUP CONNECTOR. CREW ENDED UP HAVING COMPLETE LOSS OF RIGHT MAIN BUSS AND ASSOCIATED SYSTEMS. 2 L 7 2 4F 4 F RT T00008WI E6WE 2001100100055 20011001 00055 EA 2001 10 1 2001FA0000349 2 20010723 G 8530 CYLINDER PIPER PA31 PA31P350 7103111 SO LYC O540 TIO540V2AD 41532 EA NR 5 DAMAGED C A UNSCHED LANDING R J PARTIAL RPM/PWR LOSS WARNING INDICATION CR CRUISE 1 EA 09 184JB 2307 31P8414049 L856061A WHILE IN CRUISE CONFIGURATION AT 16500 FEET, 32 INCH HG/2200 RPM THE PILOT NOTED A SHUTTER FOLLOWED BY A DROP IN MANIFOL D PRESSURE RESULTED. WITHIN 60 SECONDS THE MANIFOLD PRESSURE FLUCTUATED RAPIDLY, FOLLOWED BY A LOUD BANG. THE ENGINE W AS SECURED AND AN UNEVENTFUL LANDING FOLLOWED. INSPECTION OF THE ENGINE REVEALED THE NR 5 CYLINDER ASSEMBLY HAD SEPARAT ED FROM THE ENGINE. THE PISTON AND CONNECTING ROD WERE ATTACHED AND IN THE CYLINDER, THE ROD CAP HAD SEPARATED AND WAS FOUND IN THE CRANKCASE. 1 L 7 2 3O 3 O RT A8EA E14EA 2001100100056 20011001 00056 CE 2001 10 1 2001FA0000350 1 20010710 G 7713 47083621 CONTROLLER CESSNA 402 402C 207590R CE CONT O520 TSIO520* 17040 SO INTERNAL FAILED D K NONE O OTHER IN INSP/MAINT 1 SW 01 525RH 358 402C0525 823318R UNABLE TO CONTROL MANIFOLD PRESSURE 1 L 7 2 3O 3 O A7CE E8CE 2001100100057 20011001 00057 CE 2001 10 1 2001FA0000351 1 20010907 G 4990 3862332113 COVER GARRTT RAYTHN DH125 HAWKER800XP CE GARRTT TFE731 TFE7315BR WP APU OIL FILTER BROKEN C K NONE O OTHER IN INSP/MAINT 1 SW 09 811TA T601 258516 T601 WHEN REMOVING THE APU OIL FILTER COVER, THE RETAINING EARS THAT HOLD THE END OF THE COVER, THE RETAINING EARS THAT HOLD THE COVER IN PLACE BREAKS OFF. RECOMMEND MANUFACTURING A FILTER COVER WITH A HEX FITTING ON THE END OF THE COVER, IT WO ULD MAKE IT EASIER TO TWIST OFF THE COVER. 2 L 7 2 4F 4 F RT A3EU E6WE 2001100200009 20011002 00009 CE 2001 10 2 2001FA0000352 1 20010924 G 2460 BUSS CESSNA 172 172R 2072401 CE ELECTRICAL DAMAGED C A UNSCHED LANDING B SMOKE/FUMES/ODORS/SPARKS TO TAKEOFF 1 SW 99 2458G 870 17280893 PILOT REPORTED LOSS OF HALF OF AVIONICS BUSS, INCLUDING ONE NAV/COM AND GPS AND SMOKE AND A BAD ODOR IN THE COCKPIT. WIRE NR 2H1002 (22 GAUGE) BURNED FROM THE NAV. LIGHT C/B SWITCH TO PIN 11 OF THE JC001 CONNECTOR AND FROM PC001, PIN 11 TO JV001, PIN 1. THE RED LEAD FROM THE TAIL NAV LIGHT ASSEMBLY SHORTED OUT TO A NUT-PLATE ON THE RUDDER THAT HOLDS THE RUDDER TIP ON, BUT DOES NOT DISPLAY EVIDENCE OF OVERHEATING, OTHER THAT THE PINHEAD SIZED BURN MARK. 1 H 7 1 3O NT 3A12 2001100200010 20011002 00010 EU 2001 10 2 2001FA0000353 1 20010928 G 2720 PC43301A1 CONTROL CABLE RHNFLU EXT300 EA300L 70218DG EU RUDDER LOOSE D K NONE O OTHER IN INSP/MAINT 1 SW 99 25AP 66 66 094 ROUTINE ANNUAL INSPECTION REVEALED AFT RUDDER CABLE THIMBLE EYES WERE LOOSE IN THE LOOP AT THE ATTACHMENT TO THE RUDDER. THE THIMBLE COULD BE REMOVED FROM THE LOOP. THE NICROPRESS CRIMP WAS MADE TOO FAR FROM THE THIMBLE. REPLACED THE RUDDER CABLES WITH NEW ONES. 1 M 7 1 3O NC EA67U 2001100200012 20011002 00012 CE 2001 10 2 2001FA0000354 1 20010806 G 5753 0523921 ROLLER CESSNA 172 172N 2072434 CE TE FLAPS DAMAGED B A UNSCHED LANDING F FLT CONT AFFECTED NR NOT REPORTED 1 SW 99 737ME 17269516 AIRCRAFT RETURNED FROM FLIGHT WITH RIGHT FLAP DAMAGED. FLAP WAS STUCK AT ABOUT 20 DEGREES AND WAS TWISTED AND JAMMED IN TRACKS. FOUND INBOARD AFT. ROLLER WORN AND SPLITTING. INBOARD FLAP TRACK ALSO DAMAGED. SUSPECT WORN OUT FLAP ROLLER OR EXCESSIVE AIRCRAFT SPEED WHEN LOWERING FLAPS. RECOMMENDED YEARLY OR 500 HOURS FLAP ROLLER INSPECTION AND LUBE. (M) 1 H 7 1 3O NT 3A12 2001100200013 20011002 00013 SO 2001 10 2 2001FA0000355 1 20010817 G 2823 3138400 CONTROL CABLE PIPER PA23 PA23250 7102308 SO LYC O540 IO540* 41532 EA TANK SELECTOR BROKEN D K NONE O OTHER IN INSP/MAINT 1 NE 03 23TA 277854114 CABLE BROKE JUST BELOW SWIVEL FITTING OR THE RIGHT WING FUEL TANK SELECTOR HANDLE. RECOMMEND THAT THE AD INCLUDE THE FU EL SELECTOR CABLE ALSO BE INSPECTED. 1 L 7 2 3O 3 O 1A10 1E4 2001100200021 20011002 00021 EA 2001 10 2 2001FA0000356 2 20010829 G 8530 AEL6510241 CYLINDER HEAD PIPER PA28 PA28161 7102803 SO LYC O320 O320D3G 41508 EA ENGINE CRACKED B MW2R K NONE O OTHER IN INSP/MAINT 1 GL 17 2366W 953 288516046 R917539A CYLINDER CRACKED FROM TOP SPARK PLUG AROUND OUT SIDE OF EX SEAT TO BOTTOM SPARK PLUG HOLE. SAME AS ALL THE REST. 1 L 7 1 3O 3 O 2A13 E274 2001100200022 20011002 00022 SO 2001 10 2 2001FA0000357 1 20010830 G 7170 S6250 VALVE PIPER PA34 PA34200T 7103406 SO CONT O360 LTSIO360E 17025 SO OIL DRAIN MISINSTALLED D K NONE W INADEQUATE Q C IN INSP/MAINT 1 EA 13 44RK 347770296 THE OIL SUMP DRAIN PANEL (ON THE LOWER COWL) WAS INSTALLED BACKWARDS. THIS ALLOWED THE OIL DRAIN VALVE TO CONTACT THE P ANEL AND DEPRESS THE VALVE. CONTACT ONLY OCCURS WHEN THE ENGINE IS RUNNING. 1 L 7 2 3O 3 O A7SO E9CE 2001100200023 20011002 00023 EA 2001 10 2 2001FA0000358 2 20010912 G 8500 LW16819 CRANKCASE CESSNA 172 172N 2072434 CE LYC O320 O320* 41508 EA ENGINE CRACKED B NDDG K NONE O OTHER IN INSP/MAINT 1 EA 07 739LK 17270626 R839376T ENGINE FOUND TO BE CRACKED. THE FRACTURE OCCURRED ON THE LEFT HAND CASE HALF RUNNING FROM THE 9 OCLOCK POSSITION OF THE NR 2 CYLINDER PAD TO THE MAIN BEARING BOSS AREA. THIS CRACK WAS CAUSED BY POOR SCAVENGING OF AIR DURING THE CASTING PR OCESS. 1 H 7 1 3O 3 O NT 3A12 E274 2001100200024 20011002 00024 EA 2001 10 2 2001FA0000360 2 20010713 G 7414 MAGNETO PIPER PA28 PA28R201 7102816 SO LYC O360 IO360A1A 41514 EA ENGINE SEPARATED B MGFR A UNSCHED LANDING K J FLUID LOSS WARNING INDICATION NR NOT REPORTED 1 EA 23 47337 28R7737159 TRANSIENT PILOT LANDED WITH LOSS OF OIL PRESSURE. OIL WAS OVER AIRCRAFT BELLY AND ENGINE COMPARTMENT. INVESTIGATION FO UND RIGHT MAGNETO HANGING BY DISTRIBUTOR WIRES AND LEFT MAGNETO VERY LOOSE. AIRCRAFT ANNUAL APPROXIMATELY 20 HOURS PRIO R. CONCLUSION: MAGNETOS MAY NOT HAVE BEEN RETIGHTENED DURING ANNUAL-IF THEY WERE RETIMED. 1 L 7 1 3O 3 O 2A13 1E10 2001100200025 20011002 00025 CE 2001 10 2 2001FA0000361 1 20010920 G 5712 RIB CESSNA 210 T210L 2073449 CE CONT O520 TSIO520* 17040 SO LEFT WING CRACKED B BIOR K NONE O OTHER IN INSP/MAINT 1 EA 23 375AB 3505 21061352 LEFT WING RIB CRACKED WHERE LEFT FLAP BELLCRACK SUPPORT BRACKETS ARE MOUNTED, CRACK RUNS FROM INBOARD LOWER SUPPORT BRAC KET RIVET HOLE APPROX. ONE(1) INCH IN LENGTH DOWN AND TO THE LEFT. PROBABLE CAUSE: FLAPS EXTENDED AT TOO HIGH OF AN AI RSPEED. 1 H 7 1 3O 3 O 3A21 E8CE 2001100200027 20011002 00027 CE 2001 10 2 2001FA0000362 1 20010920 G 3246 3190 TUBE CESSNA 185 A185F 2072821 CE LYC O540 TIO540* 41532 EA FLOAT PUMP DISCONNECTED D O OTHER P NO WARNING INDICATION NR NOT REPORTED 1 AL 05 185JS 18503095 ONE AFT COMPARTMENT PUMP OUT TUBE WAS DISCONNECTED NOT ALLOWING THE WATER TO BE PUMP FROM FLOAT. AIRCRAFT SWAMPED RIGHT FLOAT ON TURN AND STARTED TO SINK. 1 H 7 1 3O 3 O 3A24 E14EA 2001100200028 20011002 00028 EA 2001 10 2 2001FA0000363 2 20010829 G 7414 SHAFT CESSNA 172 172K 2072430 CE LYC O320 O320* 41508 EA MAGNETO SHEARED D O OTHER R J PARTIAL RPM/PWR LOSS WARNING INDICATION NR NOT REPORTED 1 GL 13 7071G 521 17258771 PILOT REPORTED 700 RPM DROP ON LEFT MAGNETO. MAGNETO REMOVED AND INSPECTED. FOUND DRIVE SHAFT/ MAGNETO/ ROTOR SHEARED IN HALF. MAGNETO REPLACED. 1 H 7 1 3O 3 O NT 3A12 E274 2001100200001 20011002 00001 CE 2001 10 2 2001FA0000364 1 20010928 G 2810 6207010144 LINE CESSNA 650 650 2076802 CE HYD SYSTEM CHAFED B K NONE W K INADEQUATE Q C FLUID LOSS IN INSP/MAINT 1 GL 15 72ST 5921 6500072 THE AIRCRAFT WAS MANUFACTURED WITH THE HYDRAULIC PRESSURE AND RETURN LINES CONTACTING EACH OTHER. THE RETURN LINE EVENTU ALLY WORE THROUGH AND STARTED TO LEAK, THE PRESSURE LINE WAS ALSO SEVERLY WORN AND REQUIRED REPLACEMENT. THE REPAIR IS E XTENSIVE BECAUSE THE LINES ARE SWAGED REQUIREING THE REPLACEMENT OF MANY LINES AND FITTINGS. NOT ALL OF THESE LINES ARE AVAILABLE FROM CESSNA. THE AREA WHERE THE LINES ARE IN CONTACT CAN BE VERY DIFFICULT TO INSPECT. IN MOST CASES THE AREA IS ONLY VISIBLE WITH A MIRROR. THEY CHECKED ANOTHER CESSNA 650 THAT WAS IN THE SHOP AND IT HAD ONLY .010 BETWEEN THE LIN ES. IT WOULD BE ADVISABLE FOR OTHER OPERATORS OF THIS MODEL AIRCRAFT TO HAVE THESE LINES INSPECTED AT THE EARLIEST POSSI 2 L 7 2 4F A9NM 2001100200002 20011002 00002 CE 2001 10 2 2001FA0000365 1 20010813 G 2730 SCREW CESSNA 441 441 2076020 CE ELEVATOR CONTROL LOOSE B O OTHER F FLT CONT AFFECTED NR NOT REPORTED 1 SW 99 181MD 10133 4410295 EXCESS FRICTION IN PITCH, (ELEVATOR) CONTROL. DISASSEMBLY OF CONTROL, REVEALED RETAINING SCREW HAD BACKED OUT OF NYLON SLIDE. UNCONTAINED PARTS OCCASSIONALLY POSITIONED THEMSELVES THROUGH OUT NORMAL MOTION OF THE CONTROL SO AS TO CREATE E XCESS FRICTION. (M) 1 L 7 2 3T RT A28CE 2001100200003 20011002 00003 SO 2001 10 2 2001FA0000366 1 20010820 G 1400 TAPE PIPER PA28 PA28140 7102802 SO CARB SHROUD LOOSE B O OTHER R PARTIAL RPM/PWR LOSS NR NOT REPORTED 1 SW 99 9831W 2823335 PILOT COMPLAINED OF ROUGH RUNNING ENGINE LOW STATIC RPM ONLY OBTAINABLE BY LEANING MIXTURE, FOUND APPROX 1 SQUARE INCH O F TIN FOIL LODGED IN CARB VENTURI, EXAMINATION OF HEAT SHROUD ON EXHAUST PIPE RUB AREA WAS WRAPPED WITH ALUMINUM FOIL TA PE TO TAKE UP PLAY, MORE LOOSE FOIL READY TO DISLODGE AND MAKE ITS WAY TO SNUFF AIR IN CARB. (M) 1 L 7 1 3O 2A13 2001100200004 20011002 00004 2001 10 2 2001FA0000367 4 20010816 G 2312 VP10 ANTENNA BEECH 33 35C33 1151408 CE VHF SYSTEM CRACKED B O OTHER O OTHER AP APPROACH 1 SW 99 6124V CD856 A/C ARRIVED WITH AN ANTENNA 'FLUTTERS' SQUAK. UPON INSPECTION OF VHF COMM ANTENNA, IT WAS NOTED THAT THE ANTENNA WAS IN STALLED WITH NO SUPPORTING DOUBLER. UPON ANTENNA REMOVE, A 5.5 INCH RADIAL CRACK WAS DISCOVERED AROUND THE ANTENNA BASE . THE ADJOINING STRINGER IS ALSO CRACKED. THE SKIN UNDER THE ANTENNA AS CORRODED DUE TO NO SEALANT BEING APPLIED TO TH E ANTENNA BASE AFTER INSTALLATION. (M) 1 L 7 1 3O 3A15 2001100200005 20011002 00005 EA 2001 10 2 2001FA0000368 2 20010625 G 8530 EXHAUST VALVE PIPER PA28 PA28181 7102807 SO LYC O360 O360A4M 41514 EA ENGINE FAILED D A UNSCHED LANDING R J PARTIAL RPM/PWR LOSS WARNING INDICATION CR CRUISE 1 SW 99 47702 1147 287890120 THE AIRCRAFT WAS AT NORMAL CRUISE, THE PILOT STATED THAT IT STARTED TO LOSS POWER AND RAN ROUGH. AFTER LANDING AT A ALT ERNATE AIRPORT THE AIRCRAFT STOPPED RUNNING. AFTER PULLING THE CYLINDER, THE TOP OF THE EXHAUST VALVE WAS MISSING. THE STEM AND RETAINING CLIPS WHERE STILL IN PLACE. THE TOP OF THE VALVE HAD BEEN FOUND IN THE INTAKES. CAUSE OF THE MALFU NCTION UNKNOWN. TOTAL TIME ON THE VALVE IS 1146.8 HOURS. (M) 1 L 7 1 3O 3 O 2A13 E286 2001100300003 20011003 00003 GL 2001 10 3 2001FA0000370 1 20010829 G 5510 81611 TERMINAL AVIAT A1 A1B GL LYC O360 O360A1D 41514 EA HORIZONTAL STAB BROKEN B V2AR K NONE O OTHER IN INSP/MAINT 1 AL 03 711HY 2025 FORWARD HORIZONTAL STABILIZER STRUT UPPER TERMINAL WAS FOUND BROKEN ON PREFLIGHT. BREAK OCCURED ON .3125 (5/16) THREADE D PORTION AT UPPER END OF THREADS. 1 H 7 1 3O 3 O NC A22NM E286 2001100300004 20011003 00004 CE 2001 10 3 2001FA0000371 1 20011002 G 3230 LANDING GEAR CESSNA 177 177RG 2073709 CE LYC O360 IO360A1A 41514 EA MAINS FROZEN B BLBR K NONE O OTHER IN INSP/MAINT 1 GL 17 8253G 177RG0153 NOSE GEAR IN UP POSITION HAD HYDRAULIC LOCK. KEEPING THE NOSE GEAR IN THE UP POSITION EXTENDED GEAR, MAIN GEAR LOCKED D OWN, NOSE GEAR DID NOT FULLY EXTEND DUE TO HYDRAULIC LOCK IN THE RETURN LINE. 1 H 7 1 3O 3 O A20CE 1E10 2001100300005 20011003 00005 CE 2001 10 3 2001FA0000372 1 20010824 G 5312 24120043 BULKHEAD CESSNA 172 172RG 2072438 CE LYC O360 VO360* 41514 EA FUSELAGE CRACKED G K NONE O OTHER IN INSP/MAINT 1 WP 15 6190R 172RG0110 FOUND CRACKS ON RIGHT AND LEFT HAND SIDES OF BULKHEAD JUST FORWARD OF BATTERY. 1 H 7 1 3O 3 O 3A17 1E1 2001100300006 20011003 00006 CE 2001 10 3 2001FA0000373 1 20010829 G 2720 98820104 ROD CESSNA 172 172P 2072436 CE LYC O320 O320* 41508 EA PILOTS LT PEDAL FAILED B FFGR K NONE O OTHER IN INSP/MAINT 1 SO 33 51403 5726 17274308 ACTUATION ROD TO RUDDER PEDAL BROKE AT BASE OF THREADS AT FORK. THERE WAS NO DAMAGE TO RUDDER PEDAL OR BRAKE MOUNT FOUN D. 1 H 7 1 3O 3 O NT 3A12 E274 2001100300008 20011003 00008 2001 10 3 2001FA0000374 4 20010212 G 6122 MS914401 GASKET MCAULY AMTR VANS RV8 GL LYC O360 IO360A1B6 41514 EA GOVERNOR LEAKING D K NONE K FLUID LOSS IN INSP/MAINT 1 WP 27 88PV 010038 80024 GASKET PN MS914401 THAT IS SUPLIED WITH THE NEW GOVERNOR DOES NOT COVER THE FULL FACE MATING SURFACE OF THE GOVERNOR EXP OSING APPROX. .0625 INCH OF THE LOWER SCREW HOLE. THE LOWER SCREW HOLE INTERSECTS AN OIL PRESSURE CAVITY ON THE ENGINE MATING SERVICE. THE SHORT GASKET LEAKS OIL FROM LOW RPM. DURING AN INITIAL FLIGHT OVER 4 QUARTS OF OIL LEAKED IN LESS THAN 15 MINUTES OF FLIGHT. 1 L 7 1 3O 3 O NT EXPA1L71 1E10 2001100300001 20011003 00001 CE 2001 10 3 2001FA0000375 1 20011002 G 5753 FLAP CESSNA 172 172N 2072434 CE WING MISINSTALLED C K NONE W INADEQUATE Q C IN INSP/MAINT 1 SW 99 38PA 17270182 PROBLEMS FOUND AFTER RECENT PAINT AND INTERIOR:SEAT BELTS INSTALLED BACKWARDS,RIGHT FLAP INSTALLED WITHOUT ALL SPACERS R ESULTING IN DAMAGE TO FLAP,AILERON HINGE PINS NOT SECURED,NOSE TIRE INSTALLED BACKWARDS,FRONT COWLING SCREWS MISSING. 1 H 7 1 3O NT 3A12 2001100300002 20011003 00002 SO 2001 10 3 2001FA0000376 1 20011002 G 2400 467067 ISOLATOR PIPER PA28 PA28R201T 7102813 SO CONT O360 TSIO360FB 17025 SO HARTZL HCC2Y HCC2YF1 GL ELECTRICAL BURNED OUT D H DEACTIVATE SYST/CIRCUITS H ELECT. POWER LOSS-50 PC CR CRUISE 1 GL 27 3543M 3150 28R7803176 299526R AM1855 IN CRUISE FLIGHT NOTICED THE AMP GAUGE WAS SHOWING THE ALTERNATOR PUTTING OUT OVER 45 TO 50 AMPS. DME DROPPED OF LINE, LOST THE TRANSPONDER SIGNAL. VFR CONDITIONS AND CANCLED FLIGHT. LANDED AT THE CLOSEST AIRPORT. STARTED AIRCRAFT. RAD IOS WORKING. 30 TO 45 MIN INTO THE FLIGHT, AVIONICS STARTED TO DROP OFF LINE. MAINT. TECH FOUND BATTERY WAS DEAD. B ATTERY WAS CHARGED AND REINSTALLED. RUN UP OF THE AIRCRAFT SHOWED NO ALT PROBLEM AT ALL AND BUSS VOLTAGE WAS 13.75 BUT STILL HAD 35AMP DRAW. ONE OF FOUR PLASTIC INSULATOR THAT INSULATES THE DIODE & COOLER ASSEMBLY FROM THE HOLD DOWN SCREWS HAD POSSABLY BEEN TIGHTENED TO TIGHT. METAL DIODE ASSY WAS SHORTED TO GROUND. REPLACED THE SCREW AND INSULATOR. 1 L 7 1 3O 3 O 2A13 E9CE 5 C P920 2001100400001 20011004 00001 EU 2001 10 4 2001FA0000377 1 20010903 G 5751 212111407 LINK CASA C212 C212200 2410304 EU GARRTT TPE331 TPE331* 01514 WP ATTACH BOLT CRACKED C K NONE O OTHER IN INSP/MAINT 1 SO 15 316ST 289 DURING ROUTINE INSPECTION FOUND RIGHT AILERON OUTBOARD HINGE LOOSE. THE OUTBOARD LINK WAS CRACKED AT THE WING ATTACH BO LT LOWER LUG. NO DAMAGE TO THE WING OR AILERON WAS FOUND. 2 H 7 2 4T 3 T RT A43EU E2WE 2001100400002 20011004 00002 2001 10 4 2001FA0000378 4 20010927 G 3497 2H1002 WIRE CESSNA 172 172R 2072401 CE NAVIGATION LIGHT BURNED C XVES K NONE L NO TEST IN INSP/MAINT 1 SO 19 2458G 874 17280893 PILOT REPORTED LOSS OF HALF AVIONICS BUSS, SMOKE AND BAD ODOR IN COCKPIT. T/S, FOUND WIRE BURNT FROM NAV LIGHT C/B SWI TCH TO PIN 11 OF THE JC001 CONNECTOR AND FROM PC001, PIN 11 TO JV001, PIN 1. RED LEAD FROM TAIL NAV LIGHT HOUSING SHORT ED OUT TO NUT-PLATE ON RUDDER THAT HOLDS RUDDER TIP ON, BUT DOES NOT DISPLAY EVIDENCE OF OVERHEATING, OTHER THAN PINHEAD SIZED BURN MARK. SEVERAL OTHER WIRES WERE DAMAGED WHEN WIRE NR 2H1002 MELTED. NOTE: ALL THREE NAV-LAMPS FEED INTO A SINGLE TWO FOOT LENGTH OF 22 GAUGE WIRE BEFORE CONNECTING THE 5 AMP BREAKER. MOST OF LENGTH OF WIRE TO TAIL IS DAMAGE D, LAST SECTION TO BREAKER IS BURNED BARE. THIS SECTION THAT MELTED INTO ADJACENT WIRES IN BUNDLE. ONCE WIRE BURNED TH 1 H 7 1 3O NT 3A12 2001100400003 20011004 00003 CE 2001 10 4 2001FA0000379 1 20010909 G 5320 PANEL CESSNA 177 177B 2073708 CE LYC O360 O360* 41514 EA TRANSPONDER LOOSE C K NONE O OTHER IN INSP/MAINT 1 SW 09 13519 17702432 OWNER/OPERATOR REPORTED THAT CONTROL YOKE WOULD NOT PULL BACK TO RAISE THE ELEVATOR. ON INSPECTION IT WAS FOUND THAT TH E PANEL MOUNT TRAY FOR THE TRANSPONDER ON THE RIGHT SIDE OF THE PANEL HAD DROPPED .2500 OF INCH AND WAS CONTAINING AND R ESTRICTING AFT MOVEMENT OF THE CONTROL YOKE. THE AIRCRAFT COULD NOT ROTATE ON TAKEOFF AND IT WAS A CLOSE CALL. AN ADDI TIONAL SUPPORT WAS INSTALLED ON THE BACK OF THE TRAY. AVIONICS INSTALLER OVER-LOOKED THE POSSIBILITY OF THE TRAY DROPPI NG DOWN. UNDER PANEL AREA SHOULD BE INSPECTED AT EACH ANNUAL, 100 HOUR AND AFTER NEW AVIONICS INSTALLATION. 1 H 7 1 3O 3 O A13CE E286 2001100900025 20011009 00025 CE 2001 10 9 2001FA0000380 1 20010911 G 3240 5100106159 LINE CESSNA 414 414A 2075907 CE CONT O520 TSIO520* 17040 SO BRAKE ASSY CHAFED G K NONE K FLUID LOSS IN INSP/MAINT 1 CE 05 414AN 4224 414A0819 BRAKE LINE ROUTED UNDER THE CO-PILOTS SEAT PEDESTAL AREA IS CHAFFING ON HEAT DUCT TUBING. SLIDING A 193-6 LOW PRESSURE HOSE OVER THE BRAKE LINE WILL KEEP THE BRAKE LINE FROM DEVELOPING A HOLE. 1 L 7 2 3O 3 O A7CE E8CE 2001100900026 20011009 00026 CE 2001 10 9 2001FA0000381 1 20010911 G 3240 5100106159 LINE CESSNA 414 414A 2075907 CE BRAKE ASSY CHAFED G K NONE O OTHER IN INSP/MAINT 1 CE 05 2702L 4375 414A0608 RIGHT BRAKE LINE ROUTED UNDER CO-PILOT SEAT PEDISTAL AREA IS CHAFFING ON HEAT DUCT TUBING. SLIDING A 193-6 LOW PRESSURE HOSE OVER THE BRAKE LINE WILL KEEP THE BRAKE LINE FROM DEVELOPING A HOLE. 1 L 7 2 3O A7CE 2001100900027 20011009 00027 CE 2001 10 9 2001FA0000382 1 20010906 G 3240 BOLT CESSNA 172 172RG 2072438 CE LYC O360 O360F1A6 41514 EA BRAKE CYLINDER MISSING D K NONE O OTHER IN INSP/MAINT 1 SW 07 81JD 4577 172RG1184 L3108636A LEFT LANDING GEAR WOULD NOT EXTEND IN FLIGHT. AIRCRAFT WAS HOISTED UP AND THE GEAR EXTENDED AND LOCKED. FOUND A BOLT M ISSING FROM THE LEFT BRAKE CYLINDER. PERFORMED SEVERAL GEAR RETRACTIONS AND OPS CHECKED OK. 1 H 7 1 3O 3 O 3A17 E286 2001100900023 20011009 00023 CE 2001 10 9 2001FA0000383 1 20010929 G 2410 646655A1 DRIVE GEAR TELEDYNECRIT CESSNA 421 421C 2076016 CE CONT O520 GTSIO520L 17032 SO ALTERNATOR DAMAGED B A UNSCHED LANDING E H VIBRATION/BUFFET ELECT. POWER LOSS-50 PC CR CRUISE 1 SW 99 112MJ 421C0907 292300R L. ALTERNATOR FAILED DURING FLIGHT AND A VIBRATION WAS NOTED ABOUT 20 MINUTES LATER. THE ENGINE OIL PRESSURE DROPPED AB OUT 25 PSI AND A PRECAUTIONARY LANDING WAS MADE. UPON REMOVAL OF THE ALTERNATOR IT WAS DISCOVERED THE DRIVE HUB WAS NEA RLY DESTROYED AND THE DRIVE GEAR BOLTS WERE MISSING AND THE GEAR WAS LOOSE ON THE BULLGEAR SHAFT. THE REMNANTS OF THE D RIVE GEAR WERE LOCATED IN THE OIL PAN ALONG WITH THE CASTLE NUT AND COTTER PIN. (SEE PHOTO)THIS IS THE SECOND OCCURRENCE OF THIS TYPE FAILURE IN THE PAST 2 WEEKS, THE OTHER WAS ON THE I. ENGINE OF A 421C WITH ABOUT 1400 HOURS ON THE ENGINE AND LESS THAN 100 HOURS ON THE ALTERNATOR SMOH. NEITHER ALTERNATOR EXHIBITED ANY BEARING PROBLEMS. WE HAVE BEEN UNABL 1 L 7 2 3O 3 O A7CE E7CE 2001121900121 20011219 00121 GL 2001 12 19 2001FA0000384 2 20011005 G 7230 230397911 ADAPTER ALLSN AEROSP AS355 AS355F1 8680810 EU ALLSN 250C 250C20F 03013 GL COMP COUPLING CORRODED B K NONE O OTHER IN INSP/MAINT 1 SW 99 2450 CAC30224P 5030 CAE840216 COUPLING HAS EXCESSIVE FRETTING WEAR ON OD SURFACE. CONTINUED OPERATION MAY HAVE CAUSED FAILURE. SAME CONDITION NOTED ON OTHER COUPLINGS OF THE SAME PART NUMBER. THIS PART NUMBER IS CURRENTLY UNDER INVESTIGATION BY ROLLS-ROYCE (ALLISON E NGINE COMPANY)DUE TO FAILURES OF LIKE PARTS. 1 G 7 2 3U 3 U H11EU E4CE 2001100900024 20011009 00024 SO 2001 10 9 2001FA0000385 2 20011003 G 8530 646279 PISTON CESSNA 175 175A 2072504 CE CONT O300 GO300C 17022 SO MCAULY 1B175 1B175MFC GL ENGINE CRACKED D K NONE O OTHER IN INSP/MAINT 1 SW 99 56291 12558OC 8464 WHILE PREPARING TO INSTALL A NEW STEEL CYLINDER AND PISTON, NOTICED THAT THE NEW PISTON WAS CRACKED ALL THE WAY THROUGH THE FOURTH RING GROOVE. THE PISTON SKIRT WAS ALSO BULGED IN THE AREA OF THE CRACK. 1 H 7 1 3O 3 O 3A17 E298 5 N P857 2001101500077 20011015 00077 2001 10 15 2001FA0000386 4 20010918 G 2300 S2870 SWITCH CESSNA 182 182S 2072701 CE LYC O540 IO540* 41532 EA PILOT PTT INOPERATIVE B LC1R O OTHER O OTHER NR NOT REPORTED 1 EA 07 3261M 548 18280347 THE PILOTS SIDE PUSH TO TALK SWITCH WENT BAD WITH ONLY 548.0 TACH TIME. REPLACE THE BAD SWITCH WITH A NEW ONE. THE NEW SWITCH WAS BAD ALSO, THEN REPLACED THE NEW SWITCH THE SECOND NEW SWITCH TESTED OK. WHEN INSTALLING SWITCHES, WAS CAREF UL NOT TO OVERHEAT SWITCH. 1 H 7 1 3O 3 O NT 3A13 1E4 2001101500079 20011015 00079 SW 2001 10 15 2001FA0000387 1 20010709 G 5711 SPAR BBAVIA 7 7CCM 21101MW SW CONT C90 C90* 17009 SO WING CRACKED D K NONE O OTHER IN INSP/MAINT 1 NM 01 2959E 7AC6545 DURING INSPECTION TO COMPLY WITH AD, CRACKS WERE FOUND INBOARD AND LEFT FRONT SPAR, INBOARD END RIGHT REAR SPAR. .001 F EELER GAGE COULD BE INSERTED .1250 OR MORE INTO CRACKS. 1 H 7 1 3O 3 O A759 E252 2001101500087 20011015 00087 2001 10 15 2001FA0000388 4 20010711 G 6113 055032110 BULKHEAD CESSNA 172 172S 2072439 CE LYC IO360 IO360L2A EA MCAULY 1A170 1A170* GL SPINNER CRACKED D K NONE O OTHER IN INSP/MAINT 1 NM 01 3526J 72 172S8829 THE AREA AROUND THE NUTPLATE NEAREST TO THE PROPELLER ON THE AFT SPINNER BULKHEAD HAD CRACKED AND BROKEN FREE OF THE BUL KHEAD IN FLIGHT. THE SECTION OF THE SPINNER ATTACHED TO THE BROKEN PIECE WAS PULLED AWAY FROM THE BULKHEAD. THE SPINNE R HAD STARTED TO DEVELOPE CRACKES ALONG THE BEND RADIUS. BOTH THE SPINNER AND AFT SPINNER BULKHEAD WERE REPLACE WITH FA CTORY NEW. 1 H 7 1 3O 3 O NT 3A12 1E10 5 N P857 2001101500090 20011015 00090 SO 2001 10 15 2001FA0000389 1 20010418 G 7120 1020691 SUPPORT AMRGEN AA1 AA1 0630610 SO LYC O320 O320E2G 41508 EA MOUNT CORRODED D K NONE O OTHER IN INSP/MAINT 1 NM 01 5985L 2229 AA10285 CORROSION DISCOVERED IN UPPER SURFACES OF BOTH LEFT AND RIGHT SUPPORTS. DETECTED BY PREPING THE SUPPORTS FOR PAINT WITH A STAINLESS STEEL WIRE BRUSH AND SLIGHT RAISED LINE WAS NOTICED. PICKING REVEALED A LARGE AREA OF POWDER CORROSION AND EXFOLIATION BELOW THE SURFACE. THE OTHER SUPPORT WAS PICKED AT, THOUGHT THE SURFACE LOOKED OK AND IT WAS ALSO CORRODED AS MUCH AS THE FIRST ONE. THE SUPPORTS MUST BE REPLACED WHICH IS WELL COVERED IN THE AIRCRAFT MM. INNERGRANULAR CORRO SION IS USUALLY THE RESULT OF DEFECTIVE HEAT TREATING DURING MANUFACTURING AND THIS PART IS USED ON ALL MODELS OF THIS P RODUCT LINE. 1 L 7 1 3O 3 O A11EA E274 2001101500091 20011015 00091 SO 2001 10 15 2001FA0000390 2 20010922 G 7322 NA53B CARBURETOR BBAVIA 7 7AC 2110102 SW CONT A65 A65* 17003 SO ENGINE INOPERATIVE G K NONE O OTHER IN INSP/MAINT 1 EA 13 85122 7AC3855 ENGINE FAILURE, BELIEVE DUE TO FUEL STARVATION. GOOD FUEL FLOW UP TO CARBURETOR. NO CONTAMINATION FOUND WITH GASCOLATO R. UPON CARBURETOR DISASSEMBLY FOUND VERY FINE DIRT IN CARBURETOR FUEL STRANER AND FLOAT CHAMBER. ALSO, FOUND MAIN AIR BLEED JET NEARLY TOTALLY OBSTRUCTED WITH GUMMY LIKE FOREIGN MATTER. PROBABLE CAUSE: FUEL FLOW IMBALANCE. ONE EITHER OBSTRUCTION OF AIR JET OR FUEL JET. 1 H 7 1 3O 3 O A759 E205 2001101500093 20011015 00093 CE 2001 10 15 2001FA0000391 1 20010903 G 5312 07126167 BULKHEAD CESSNA 182 182N 2072730 CE CONT O470 O470R 17026 SO REAR FUSELAGE CRACKED G K NONE O OTHER IN INSP/MAINT 1 WP 19 9024G 6880 18260564 451652 IN COMPLYING WITH AD, (CRACKS AND LOOSE BOLTS IN FIN AND RUDDER) CRACKS WERE FOUND IN THE AREA IN THE AFT BULKHEAD BETWE EN THE RUDDER CABLE CUTOUT AND THE BULKHEAD FLANGE. 1 CRACK EACH SIDE, BULKHEAD WAS REPLACED. 1 H 7 1 3O 3 O NT 3A13 E273 2001101500094 20011015 00094 CE 2001 10 15 2001FA0000392 1 20010816 G 8011 BEARING ELECTROSYS BEECH 76 76 1153005 CE LYC O360 O360A1G6D EA FWD BUSHING DEPARTED B HUNR K NONE O OTHER IN INSP/MAINT 1 NM 01 6013M A040394 ME102 L2555136A IN STARTER DRIVE END CASTING, THE (FORWARD) BUSHING DEPARTED FROM THE CASTING THIS IS THE FORWARD PIVOT BUSHING/BEARING FOR THE BENDIX DRIVE SHAFT. 432.24 HOURS OF FLIGHT TRAINING, OVERHAULED BY MFG. 1 L 7 2 3O 3 O A29CE E286 2001101500023 20011015 00023 CE 2001 10 15 2001FA0000393 1 20010927 G 2730 380210417005 SUPPORT RKWELL NA265 NA26580 7630108 CE FUSELAGE BROKEN B K NONE O OTHER IN INSP/MAINT 1 SW 99 380GK 38044 DURING SCHEDULED INSPCTION FOUND SMALL PIECE OF A BEARING BOSS IN HELL HOLE. UPON INVESTIGATION FOUND ELEVATOR TORQUE T UBE SUPPORT MISSING PIECE. ALSO FOUND RT SUPPORT CRACKED IN THE SAME POSITION. REPLACED BOTH RT AND LT ELEVATOR SUPPORT BRACKETS. 2 L 7 2 4F A2WE 2001101500026 20011015 00026 EU 2001 10 15 2001FA0000394 1 20011010 G 2510 350A77125807 SEAT SNIAS 350 AS350B2 8680813 EU COCKPIT CRACKED B O OTHER O OTHER NR NOT REPORTED 1 CA 6098U 2718 COCKPIT SEAT CRACKED 1 G 7 1 3U H9EU 2001101500065 20011015 00065 EA 2001 10 15 2001FA0000395 2 20011008 G 7313 LW18265 INJECTOR CESSNA 172 172S 2072439 CE LYC IO360 IO360L2A EA MCAULY 1A170 1A170E GL ENGINE CLOGGED B A UNSCHED LANDING R PARTIAL RPM/PWR LOSS CL CLIMB 1 WP 07 428SA 597 27 172S8547 L2914851A UC063 PILOT REPORTED THAT DURING CLIMBOUT THE ENGINE BEGAN RUNNING ROUGH, AT WHICH TIME HE RETURNED TO THE AIRPORT (PHX). TEC HNICIAN COULD NOT DUPLICATE THE MALFUNCTION ON A GROUND RUN UP. THE FUEL INJECTOR NOZZLES WERE REMOVED & INSPECTED AND T HE NR 2 INJECTOR WAS FOUND TO BE PLUGGED. THE INJECTOR NOZZLES WERE CLEANED & REINSTALLED. THE ENGINE RUNUP WAS NORMAL AND SMOOTH, AND THE AIRCRAFT WAS FLOWN BACK TO PHOENIX. 1 H 7 1 3O 3 O NT 3A12 1E10 5 N P857 2001101500068 20011015 00068 GL 2001 10 15 2001FA0000396 1 20011010 G 7160 DUCT CIRRUS SR SR22 GL AIR BOX LOOSE D K NONE O OTHER IN INSP/MAINT 1 NE 01 2345B 27 0077 ALTERNATE ENGINE AIR BOX ATTACHED TO ENGINE THROTTLE BODY WITH ONE HOSE CLAMP AND CUSHION CLAMP AT FACTORY. MAINTENANCE MANUAL FIG 71-601 CORRECTLY SHOWS TWO HOSE CLAMPS AND ONE CUSHION CLAMP WHICH ACTS AS SUPPORT FOR ALTERNATE AIR CONTROL CABLE. LACK OF SECOND HOSE CLAMP ALLOWS ALTERNATE AIR BOX TO ROTATE CAUSING DUCT DAMAGE. 1 H 7 1 3O NC A00009CH 2001101500069 20011015 00069 CE 2001 10 15 2001FA0000397 1 20011011 G 5313 CM32091 STRINGER CESSNA 500 550 2076604 CE FUSELAGE DAMAGED B K NONE O OTHER IN INSP/MAINT 1 GL 07 205SC 9156 9156 5500156 DURING AN AVIONICS INSTALLATION EVENT WITH THE AIRCRAFTS' INTERIOR REMOVED IT WAS NOTED THAT THE FUSELAGES' UPPER CROWN SKIN, ABOUT THE CENTERLINE HAD BEEN PREVIOUSLY MODIFIED AT ONE TIME TO "BLANK OUT" A ANTENNA INSTALLATION NO LONGER IN U SE. EXTREMELY POOR WORKMANSHIP AND NON STANDARD PRACTICES WERE EXHIBITED IN THE INSTALLATION OF TWO INTERNAL DOUBLERS, T HAT INCLUDED LARGE HOLES CUT IN THE UPPER CENTERLINE STRINGER ABOUT BL 0.00 AT APPROX. FUSELAGE STATION 240.00. THE TWO HOLES CREATED SIGNIFICANT VOIDS IN THE "T"S' FLANGE, IN CONTACT WITH THE FUSELAGE SKIN, WHICH WERE UNREINFORCED. 1 L 7 2 4F A22CE 2001103100104 20011031 00104 CE 2001 10 31 2001FA0000398 1 20010928 G 7603 1023890091 THROTTLE CABLE BEECH 58 58P 1152744 CE CONT O520 TSIO520* 17040 SO RT THROTTLE CHAFED C O OTHER O OTHER NR NOT REPORTED 1 SW 99 145Z 242 TJ289 PILOT COMPLAINED, RIGHT THROTTLE VERY STIFF, THROTTLE HAD BEEN REPLACED FOUR MONTHS EARLIER FOR SAME REASON. UPON REMOV AL IT WAS DISCOVERED THAT THE CABLE, WHICH WAS COVERED WITH FIRE SLEEVE, HAD BEEN CHAFFING ON THE LOWER PART OF THE TURB OCHARGER COMPRESSOR HOUSING CLAMP, WHERE IT HAD CHAFFED THE CABLE HAD INDICATIONS OF BEING OVERHEATED. CABLE SHOULD HAV E BEEN ROUTED ABOVE THE EXHAUST WHERE IT WOULD HAVE BEEN PROTECTED BY THE EXHAUST HEAT SHIELD. WHEN REPLACING PARTS WIT H NO CLEAR GUIDANCE ON ROUTING, NEED TO MAKE SURE TO FOLLOW INSTALLATION GUIDE. 1 L 7 2 3O 3 O A23CE E8CE 2001103100105 20011031 00105 CE 2001 10 31 2001FA0000399 1 20010901 G 2710 BRACKET CESSNA 206 P206D 2073338 CE CONT O520 IO520* 17032 SO AILERON PULLEY MISMANUFACTURED C K NONE W INADEQUATE Q C IN INSP/MAINT 1 WP 25 8734Z P2060534 DURING ANNUAL INSPECTION, THE ABSENCE OF THE SAFETY COTTER PIN (-23) WAS NOTED (PORT SIDE) (AILERON PULLEY BRACKET) CONS TRUCTION OF THE BRACKET WAS SUCH THAT A COTTER PIN COULD NOT HAVE BEEN INSERTED AT THE FACTORY. (SEE DIAGRAM) 1 H 7 1 3O 3 O A4CE E5CE 2001103100107 20011031 00107 CE 2001 10 31 2001FA0000400 1 20010828 G 3242 1138932 STATOR CESSNA 500 550 2076604 CE PWA JT15 JT15D4 52112 NE RT MLF BRAKE BROKEN C O OTHER O OTHER TX TAXI/GRND HDL 1 WP 19 26496 5500607 FOLLOWING A NORMAL LANDING AND ROLL OUT FOR A RIGHT TURN ON TO THE TAXI WAY THE RIGHT MAIN WHEEL LOCKED UP. AFTER JACKI NG THE MAIN WHEEL AND PULLING THE TIRE, A PIECE OF STATOR WAS FOUND COMPLETE BROKEN OUT OF THE STATOR CAUSING THE WHEEL TO LOCK. THIS BRAKE ASSY AND THE LEFT HAD BOTH BEEN CHANGED AT THE SAME TIME. SB AND MFG WERE DONE ELIMINATING THE NEE D TO SEPARATE THE BRAKE ASSYS FOR INSPECTION. AS CAN BE SEEN BOTH STATORS WERE CLOSE TO FAILURE. THE LEFT ASSY WAS OPE NED UP AND STATORS WERE CRACKED TO POINT WHERE FAILURE WAS MATTER OF TIME. BOTH BRAKES HAD 585 LANDINGS. 1 L 7 2 4F 4 F A22CE E1NE 2001110100056 20011101 00056 SO 2001 11 1 2001FA0000401 1 20010618 G 3710 72979 GEAR AMRGEN AA1 AA1B 0631206 SO LYC O235 O235C2C 41505 EA VACUUM PUMP WORN G O OTHER K FLUID LOSS NR NOT REPORTED 1 EA 07 1409R 3165 AA1B0509 L1197115 REMOVE VACUUM PUMP DRIVE SHAFT GEAR, OIL LEAKING INTO VACUUM PUMP, WORN SPOT ON SHAFT DAMAGED OIL SEAL CAUSING OIL LEAK . 1 L 7 1 3O 3 O A11EA E223 2001112800065 20011128 00065 SO 2001 11 28 2001FA0000402 2 20011002 G 8550 OIL FILTER EXTRA EA400 EA400 EU CONT O550 TSIOL550C SO ENGINE CHAFED G O OTHER K J FLUID LOSS WARNING INDICATION NR NOT REPORTED 1 WP 07 14EX 15 AIRCRAFT EXPERIENCED AT TOTAL ENGINE FAILURE DUE TO LOSS OF OIL PRESSURE. THE CAUSE WAS TO A B-NUT ON A T-FITTING LOCAT ED ON THE METERED PRESSURE TEST PORT FOR THE THROTTLE BODY HAD WORN A HOLE THRU THE OIL FILTER HOUSING. THE THROTTLE HO USING IS MOUNTED ON RUBBER TUBING AND MOVES THRU VIBRATION AND MAKING CONTACT. THERE NEEDS TO BE MORE CLEARANCE BETWEEN THE FITTING AND OIL FILTER. 1 H 7 1 3O 3 O RT A43CE E4SO 2001103100109 20011031 00109 EA 2001 10 31 2001FA0000403 2 20010731 G 8530 EXHAUST VALVE MOONEY M20 M20J 5870219 SW LYC O360 IO360A1A 41514 EA NR 1 CYLINDER BROKEN C O OTHER O OTHER NR NOT REPORTED 1 WP 19 1084Z 1964 241132 NR 1 CYLINDER BROKEN, AN EXHAUST VALVE WHICH DESTROYED THE PISTON AND CYLINDER HEAD. ALSO, FOUND NR 1 INTAKE TUBE SEAL PN 77569, TORN AND TWISTED WHICH COULD HAVE CAUSED A LEAN MIXTURE ON THAT CYLINDER. 1 L 7 1 3O 3 O 2A3 1E10 2001103100110 20011031 00110 CE 2001 10 31 2001FA0000404 1 20011001 G 7120 265102215 MOUNT CESSNA 208 208B 2073701 CE PWA PT6 PT6A11 52043 NE ENGINE CRACKED D K NONE O OTHER IN INSP/MAINT 1 WP 11 9750B 208B0100 DURING NON ROUTINE INSPECTION OF ENGINE MOUNT, A CRACK WAS FOUND IN THE WELD OF THE LOWER RIGHT ATTACH POINT (RING TO AI RCRAFT SUPPORT) SHIMMY DAMPENER WAS IN GOOD CONDITION WITH NO LEAKS DETECTED. NOSE GEAR BUSHINGS WERE ALSO SATISFACTOR Y. 1 H 7 1 3T 3 T A37CE E4EA 2001103100111 20011031 00111 SO 2001 10 31 2001FA0000405 2 20010926 G 7414 6310 MAGNETO BEECH 33 F33A 1151425 CE CONT O520 IO520BB 17032 SO ENGINE FAILED G K NONE O OTHER IN INSP/MAINT 1 WP 07 5519A 497 CE1337 820453R MAGNETO REMOVED FROM ENGINE FOR 500 HOUR INSPECTION IN ACCORDANCE WITH THE MM. REMOVED THE REAR COVER OF MAGNETO AND FO UND A GRAY COLOR POWDER ON THE CAP AND AROUND THE COIL. THIS WAS FOUND ON THE MAGNETOS THAT HAD FAILED IN FLIGHT WITH A BOUT THE SAME FLIGHT TIME ON THEM. MFG WAS INFORMED OF FAILURES. 1 L 7 1 3O 3 O 3A15 E5CE 2001103100112 20011031 00112 NM 2001 10 31 2001FA0000406 1 20010829 G 3250 ROD UNIVAR 415 415C 0420302 NM CONT C75 C75* 17005 SO NLG STEERING BROKEN D K NONE O OTHER TX TAXI/GRND HDL 1 GL 19 94157 1480 STEERING ROD KNUCKLE BROKE AS AIRCRAFT WAS BEING REPOSITIONED AFTER LOG. THIS ROD HAS BROKEN NUMEROUS TIMES IN THE PAST , KNOW OF 3 RODS BREAKING IN THE PAST. 1 L 7 1 3O 3 O A718 E233 2001103100113 20011031 00113 EU 2001 10 31 2001FA0000407 2 20010904 G 7421 NCKB8ES SPARK PLUG AMTR AVID AVIDFLYERHH 95708FU GL ROTAX 532 ROTAX532 55555 EU ENGINE BROKEN G A UNSCHED LANDING O OTHER NR NOT REPORTED 1 AL 03 47065 063 THE CERAMIC PORTION OF THE SPARK PLUG BROKE COMPLETELY AROUND AND ALLOWED THE SPARK PLUG WIRE TO FALL OFF WITH THE PIECE OF CERAMIC INSIDE THE WIRE AND CAP. ENGINE WOULD NOT MAINTAIN POWER ON 1 CYLINDER CAUSING FORCED LANDING AND DAMAGE TO AIRCRAFT. 1 H 7 1 3O 3 I NC EXPA1H71 EXPE3I 2001103100114 20011031 00114 GL 2001 10 31 2001FA0000408 1 20010119 G 3244 TIRE AMTR EAGLE CHRISEAGLE2 GL LYC O360 IO360A1C 41514 EA LANDING GEAR FAILED C O OTHER O OTHER NR NOT REPORTED 1 SW 09 316 419 TIRE FAILURE, STRIPPED RIB. CAUSE: UNDETERMINED, PENDING EVALUATION BY MFG. 1 Q 7 1 3O 3 O EXPA1Q71 1E10 2001103100115 20011031 00115 SO 2001 10 31 2001FA0000409 1 20010904 G 7820 0990D113 MUFFLER AMRGEN AA1 AA1 0630610 SO LYC O235 O235C 41505 EA ENGINE CRACKED D K NONE O OTHER IN INSP/MAINT 1 SO 13 5903L 2330 AA10203 DURING ANNUAL INSPECTION, MUFFLER WAS FOUND CRACKED IN THE AREA WHERE TAIL PIPE IS WELDED TO CAN. 742 HOURS SINCE LAST INSPECTION. (ATTACHED PHOTOS) 1 L 7 1 3O 3 O A11EA E223 2001110100057 20011101 00057 EA 2001 11 1 2001FA0000410 2 20010223 G 8520 SEAL AMTR LONGEZ LONGEZ 05690Z8 GL LYC O235 O235L2C 41505 EA ENGINE BLEW OUT G A UNSCHED LANDING K FLUID LOSS NR NOT REPORTED 1 GL 03 93RF 675 1787L ENGINE CRANKCASE BREATHER HOSE MAY HAVE ICED UP CAUSING CRANKCASE PRESSURE TO BUILDUP, BLOWING CRANKSHAFT SEAL OUT OF CR ANKCASE. ALL ENGINE SEIZED UP AND QUIT. PILOT MADE AND EMERGENCY LANDING, NO DAMAGE TO AIRCRAFT. 1 M 7 1 3O 3 O RT EXPA1M71 E223 2001103100116 20011031 00116 2001 10 31 2001FA0000411 4 20011004 G 2300 S28701 SWITCH CESSNA 182 182S 2072701 CE LYC O540 IO540* 41532 EA COCKPIT FAILED C K NONE O OTHER NR NOT REPORTED 1 EA 07 3261M 18280347 PUSH TO TALK SWITCH FAILED AFTER 1 HOUR OF OPERATION. HAS HAPPENED FOUR TIMES IN A ROW. 1 H 7 1 3O 3 O NT 3A13 1E4 2001112800066 20011128 00066 SW 2001 11 28 2001FA0000412 1 20010830 G 7810 6422209052 TAB MOONEY M20 M20K 5870220 SW CONT O360 TSIO360LB 17025 SO ENGINE BROKEN B TZ3R O OTHER R PARTIAL RPM/PWR LOSS NR NOT REPORTED 1 WP 01 231EC 65 250167 247414R SECURING/ATTACHING TAB WELDED TO EXHAUST RISER ASSEMBLY FOR CYLINDER NR 4 BROKE OFF CAUSING SUDDEN LOSS OF ENGINE MANIFO LD PRESSURE AND POWER RESULTING IN IMMEDIATE LANDING OF AIRCRAFT. (NR 4 CYLINDER RISER SEPARATED FROM NR 6 RISER WHEN T AB BROKE. 1 L 7 1 3O 3 O 2A3 E9CE 2001110100060 20011101 00060 GL 2001 11 1 2001FA0000413 1 20010829 G 5730 STRUCTURE BLANCA 1419 14193A 1220408 GL CONT O470 IO470* 17026 SO WING DETERIORATED D K NONE W INADEQUATE Q C IN INSP/MAINT 1 SO 09 8507R 2619 4269 DURING ANNUAL INSPECTION, IN THE AREA OF THE WING WALK, WOOD DETERIORATION WAS FOUND AT THE AFT, IB UPPER SKIN SEPARATED FROM THE FORWARD EDGE, OB EDGE AND AFT TRAILING EDGE, THE ENTIRE WING WALK AREA FABRIC WAS LOOSE FROM THE STRESSED SKIN PANELS THE OWNER THEN, NOT BELIEVING SB REQUIRED AND NOT WILLING TO PROPERLY REMOVE THE EFFECTED SKIN, A CABINET MAKER AND HIMSELF SLIP IN ON AN OFF DAY. THE DAMAGE THAT WAS DONE TO THE SPAR THREE DIFFERENT SPOTS AT WS 6 TO WS 10.5 SEVERE LY DAMAGED THE SPAR DUE TO COMPRESSION CAUSED BY THE CHISEL. WHAT WAS TO BE SKIN CHANGE, NOW INCLUDES SPAR CHANGE/SPLIC E. SENT PICTURES TO MFG WAS INFORMED DAMAGE WAS SEVERE. 1 L 7 1 3O 3 O 1A3 E1CE 2001110100058 20011101 00058 CE 2001 11 1 2001FA0000414 1 20010921 G 2821 07560058 FUEL STRAINER CESSNA 182 R182 2072734 CE LYC O540 O540* 41532 EA FUEL SYSTEM BACKED OUT D K NONE O OTHER IN INSP/MAINT 1 NM 03 4447R 5648 R18200601 DURING ANNUAL INSPECTION NOTICED FUEL STRAINER STANDPIPE HAD BACKED OUT AND WAS ABLE TO PULL IT OUT OF TOP ASSEMBLY WITH FINGERS. 1 H 7 1 3O 3 O RT 3A13 E295 2001103100117 20011031 00117 SW 2001 10 31 2001FA0000415 1 20011004 G 5711 SPAR BBAVIA 7 7GCBC 1220601 SW LYC O320 O320* 41508 EA RT WING CRACKED D K NONE O OTHER IN INSP/MAINT 1 NM 03 5074X 2714 40 WHILE INSPECTING WING SPARS IN COMPLIANCE WITH AD, THE FRONT SPAR IN THE RIGHT WING WAS FOUND TO HAVE A COMPRESSION CRA CK AT THE BUTT END AND THE REAR SPAR IN THE LEFT WING WAS FOUND TO HAVE A LONGITUDINAL CRACK APPROXIMATELY 14 INCHES INB OARD FROM THE TIP. 1 H 7 1 3O 3 O NC A759 E274 2001110100059 20011101 00059 CE 2001 11 1 2001FA0000416 1 20011011 G 3220 22430151 CLAMP CESSNA 182 R182 2072734 CE LYC O540 O540* 41532 EA NLG BENT D O OTHER O OTHER UK UNKNOWN 1 GL 25 2063S 2954 R18201292 NOSE GEAR FAILED TO EXTEND, BUT FELL OUT WHEN AIRCRAFT WAS LIFTED FROM RUNWAY. ON JACKS, GEAR OPS WAS NORMAL. THIS CLA MP WAS BENT WHICH MAY HAVE ALLOWED SHIMMY DAMPENER TO JAM THE GEAR. MAY HAVE BEEN DAMAGED FROM TUG OVER TURNING THE GEA R. 1 H 7 1 3O 3 O RT 3A13 E295 2001110100061 20011101 00061 CE 2001 11 1 2001FA0000417 1 20010830 G 3213 AN310S NUT CESSNA 421 421B 2076014 CE CONT O520 GTSIO520F 17032 SO RT MLG FAILED D K NONE O OTHER TX TAXI/GRND HDL 1 SO 09 781SL 149 421B0343 AIRCRAFT WAS TAXING FROM THE MAIN RUNWAY TO THE GATE, PILOT FELT AND HEARD BUMPING NOISE UPON MAKING A RIGHT TURN. AS H E WAS MAKING RIGHT TURN ONTO RAMP TORQUE LINKS SEPARATED CAUSING THE RIGHT WHEEL AND PISTON ASSEMBLY TO ROTATE ABOUT 135 DEGREES, CAUSING DAMAGE TO THE TO THE OB GEAR DOOR. THE NUT STRIPPED ITS THREADS, SHEARED THE COTTER KEY AND DEPARTED THE AIRCRAFT. BOLT REMAINED IN UPPER TORQUE LINK. NEW MLG SCISSORS WASHER REPLACEMENT KIT WAS INSTALLED, KIT DOES NOT INCLUDE A NEW NUT AND SUGGEST USING OLD NUT. NEW NUT WAS USED. THE LEFT GEAR BOLT WAS INSPECTED AND FOUND NUT WAS WOB BLY ON BOLT THREADS. NEW KITS AND NUT WERE INSTALLED ON BOTH SIDES. 1 L 7 2 3O 3 O A7CE E7CE 2001103000109 20011030 00109 NM 2001 10 30 2001FA0000419 1 20010820 G 3240 511531 HOUSING PNEUDRAULICS BOEING 737 737 UTILSYS NM SHUTTLE VALVE CRACKED B IU6R K NONE O OTHER IN INSP/MAINT 1 NM 01 3488 HOUSING IS CRACKED INSIDE THE MOUNTING BOLT HOLE. FATIGUE, DEFECT IN THE CASTING OF THE HOUSING AND/OR OVER TORQUE OF B OLT ON INSTALLATION. 2 L 7 2 4F RT A16WE 2001103000110 20011030 00110 NM 2001 10 30 2001FA0000420 1 20010821 G 3240 511531 HOUSING PNEUDRAULICS BOEING 737 737 UTILSYS NM SHUTTLE VALVE CRACKED B IU6R K NONE O OTHER IN INSP/MAINT 1 NM 01 339 HOUSING IS CRACKED ALONG THE TOP CASTING SEAM. FATIGUE, DEFECT IN THE CASTING OF THE HOUSING AND/OR OVER TORQUE OF BOLT ON INSTALLATION. 2 L 7 2 4F RT A16WE 2001103000111 20011030 00111 NM 2001 10 30 2001FA0000421 1 20010821 G 3240 511531 HOUSING PNEUDRAULICS BOEING 737 737 UTILSYS NM SHUTTLE VALVE CRACKED B IU6R K NONE O OTHER IN INSP/MAINT 1 NM 01 788 HOUSING IS CRACKED INSIDE THE MOUNTING BOLT HOLE. FATIGUE, DEFECT IN THE CASTING OF THE HOUSING AND/OR OVER TORQUE OF B OLT ON INSTALLATION. 2 L 7 2 4F RT A16WE 2001103000112 20011030 00112 NM 2001 10 30 2001FA0000422 1 20010821 G 2761 654494713 HOUSING BOEING BOEING 737 737 UTILSYS NM SPOILER ACTUATOR BROKEN B IU6R K NONE O OTHER IN INSP/MAINT 1 NM 01 9858 HOUSING BEARING LUG IS BROKEN ON BOTH SIDES OF BEARING. 2 L 7 2 4F RT A16WE 2001103000113 20011030 00113 NM 2001 10 30 2001FA0000423 1 20010821 G 2761 654494715 HOUSING BOEING 727 727 UTILSYS NM SPOILER ACTUATOR CRACKED B IU6R K NONE O OTHER IN INSP/MAINT 1 NM 01 4621 HOUSING IS CRACKED ALONG FIRST SHOULDER ON SAME SIDE AS PORTS. 2 L 7 3 4J RT A3WE 2001103000114 20011030 00114 NM 2001 10 30 2001FA0000424 1 20010821 G 2761 654494713 HOUSING BOEING BOEING 737 737 UTILSYS NM SPOILER ACTUATOR CRACKED B IU6R K NONE O OTHER IN INSP/MAINT 1 NM 01 4468 HOUSING IS CRACKED ALONG FIRST SHOULDER ON SAME SIDE AS PORTS. 2 L 7 2 4F RT A16WE 2001103000115 20011030 00115 NM 2001 10 30 2001FA0000425 1 20010821 G 2761 654494710 HOUSING BOEING BOEING 737 737 UTILSYS NM SPOILER ACTUATOR CRACKED B IU6R K NONE O OTHER IN INSP/MAINT 1 NM 01 43737 0785 HOUSING IS CRACK ON ID OF PORT. 2 L 7 2 4F RT A16WE 2001103000116 20011030 00116 NM 2001 10 30 2001FA0000426 1 20010821 G 2761 654494713 HOUSING BOEING BOEING 737 737 UTILSYS NM SPOILER ACTUATOR CRACKED B IU6R K NONE O OTHER IN INSP/MAINT 1 NM 01 8143 HOUSING IS CRACKED ALONG THE SECOND SHOULDER OPPOSITE THE PORTS. 2 L 7 2 4F RT A16WE 2001103000117 20011030 00117 NM 2001 10 30 2001FA0000427 1 20010821 G 2761 654494710 HOUSING BOEING BOEING 737 737 UTILSYS NM SPOILER ACTUATOR CRACKED B IU6R K NONE O OTHER IN INSP/MAINT 1 NM 01 45922 15683 4348 HOUSING IS CRACKED UNDER THE RETRACT PORT. 2 L 7 2 4F RT A16WE 2001110100062 20011101 00062 NE 2001 11 1 2001FA0000429 2 20010926 G 7250 769104 TURBINE PWA JT8 JT8D15 52051 NE ENGINE CRACKED B W9DR K NONE O OTHER IN INSP/MAINT 1 NE 03 7914 THE 4TH STAGE TURBINE DISK BALANCE WEIGHT FLANGE HAS MULTIPLE CRACKS (APPROX. 80) INITIATING FROM THE SCALLOP AND BALANC E WEIGHT HOLES. CRACK LENGTH VARIES FROM .001 TO .5 INCH. IT WAS NOTED THAT ONE CRACK IS PROGRESSING PAST ONE OF THE T WO OIL DRAIN HOLES AND INTO THE RADIUS OF THE DISK OUTER RIM. 4 F E2EA 2001103100119 20011031 00119 2001 10 31 2001FA0000430 4 20011008 G 2561 PO723E105P LIFE VEST CABIN FAILED B KQ1R K NONE O OTHER IN INSP/MAINT 1 EA 07 LIFE VEST FAILED, MFG RECOMMENDED 2 PSI CELL TEST IAW MANUAL. 2001103100120 20011031 00120 GL 2001 10 31 2001FA0000431 3 20010828 G 6110 1851 BEARING HARTZL PWA PT6 PT6A34 52043 EA HARTZL HCB3T HCB3TN3 GL PROPELLER ASSY CRACKED B LU4R K NONE O OTHER IN INSP/MAINT 1 SO 17 BU16907 BU16907 RELEVANT INDICATION. 4 T E4EA 6 C P15EA 2001103100121 20011031 00121 2001 10 31 2001FA0000432 4 20010809 G 2564 R0097104 LIFE RAFT CABIN POROUS B ALGR K NONE O OTHER IN INSP/MAINT 1 SW 03 LIFE RAFT TOO POROUS. 2001110100070 20011101 00070 SW 2001 11 1 2001FA0000433 1 20010831 G 2910 41002418 CYLINDER TEXTRON BELL 214 214B1 1182105 SW SERVO ACTUATOR CRACKED B B80R O OTHER O OTHER NR NOT REPORTED 1 NM 07 7513 1371 1885B SURFACE MATERIAL DEFECT/CRACK. 2 G 7 1 4U H6SW 2001110100063 20011101 00063 GL 2001 11 1 2001FA0000434 3 20010905 G 6110 C4503 FORK HARTZL HCC4Y HCC4YR2 GL PROPELLER CRACKED B ME4R K NONE O OTHER IN INSP/MAINT 1 SO 19 1113 FH596 PROPELLER WAS RECEIVED FOR STANDARD 60 MONTH OVERHAUL IAW MFG SL. CURRENT PROPELLER TIMES ARE: TTSN1113.80 TSO N/A. TH IS IS THE PROPELLERS FIRST OVERHAUL. DURING THE INSPECTION OF THE PROPELLER COMPONENTS, FOR PART NUMBER C-4503, SERIAL NUMBER N0901 WAS FOUND CRACKED IN THE FORWARD INBOARD EAR. ALSO, THE CORRESPONDING BLADE, PART NUMBER FC7663D6Q WITH S ERIAL NUMBER H37377 HAS A BENT BLADE PIN AND BEARING RACE PART NUMBER A-2202 WAS FRETTED. HARTZELL PROPELLER WAS NOTIFI ED VIA PHONE. ALL CONDEMNED PARTS WERE RED TAGGED AND ENTERED ON MFG FORM 101DA BEFORE RETURNING TO CUSTOMER. THE REMA INING PARTS CHECK GOOD. PROPELLER WAS REASSEMBLED WITH REPLACEMENT PARTS AND RETURNED TO SERVICE. 5 C P52GL 2001110100069 20011101 00069 SW 2001 11 1 2001FA0000437 1 20010831 G 2910 41002418 CYLINDER TEXTRON BELL 214 214B1 1182105 SW SERVO ACTUATOR CRACKED B B80R O OTHER O OTHER NR NOT REPORTED 1 NM 07 7513 1371 1885B SURFACE MATERIAL DEFECT/CRACKED. 2 G 7 1 4U H6SW 2001110100068 20011101 00068 2001 11 1 2001FA0000441 4 20010814 G 3421 5546257001 CONNECTOR COLLINS VERTICAL GYRO CORRODED B M71R O OTHER N FALSE WARNING NR NOT REPORTED 1 SW 15 6055 EXCESSIVE CORROSION ON CONNECTOR BETWEEN PINS N,P, AND M. THIS RESULTED IN ATTITUDE INDICATOR FLAGGING AND SHOWING IMPR OPER ATTITUDES. 2001110100067 20011101 00067 2001 11 1 2001FA0000442 4 20010914 G 2561 S5600AV2A LIFE VEST CABIN FAILED B KQ1R K NONE O OTHER IN INSP/MAINT 1 EA 07 LIFE VEST TYPE AV-2(A) MFG MARCH 1983 FAILED. MFG RECOMMENDED 2 PSI CELL TEST I/A/W 25-60-55. 2001110100071 20011101 00071 GL 2001 11 1 2001FA0000443 3 20010913 G 6111 S90AT2 BLADE MCAULY 2A34C 2A34C66 GL PROPELLER CRACKED B ME4R K NONE O OTHER IN INSP/MAINT 1 SO 19 MCAULEY BLADE PART S90AT-2 WITH SERIAL NUMBER OD044YSC WAS RECEIVED FOR OVERHAUL. BLADE TIMES ARE UNKNOWN. BLADE RECEI VED AS A SINGLE BLADE WITH FERRULE INSTALLED. AFTER FERRULE REMOVAL, DURING BLADE BUTT, FLORESCENT PENETRATE INSPECTION , BLADE WAS DISCOVERED CRACKED IN THE LAST THREAD, FORWARD SIDE, FROM 1:00 TO 5:00 O'CLOCK POSITION. BLADE WAS RED TAGG ED. 5 C P3EA 2001110500035 20011105 00035 2001 11 5 2001FA0000444 4 20010727 G 3421 5546257001 CONNECTOR COLLINS VERTICAL GYRO CORRODED B M71R O OTHER N FALSE WARNING NR NOT REPORTED 1 SW 15 6224 EXCESSIVE CORROSION ON CONNECTOR BETWEEN PINS N AND P. CORROSION CAUSED BY INTERNAL CONDENSATION. THIS IS RESULTED IN ATTITUDE INDICATOR FLAGGING AND SHOWING IMPROPER ATTITUDES. 2001110100111 20011101 00111 2001 11 1 2001FA0000445 4 20010921 G 2561 KS9P0101 LIFE VEST CABIN FAILED B KQ1R K NONE O OTHER IN INSP/MAINT 1 EA 07 LIFE VEST FAILED. THE MFG RECOMMEDNDED CELL PRESSURE TEST IAW 25-60-01. DOM: JUNE 1980 2001110100112 20011101 00112 GL 2001 11 1 2001FA0000446 3 20010925 G 6114 1A103TCM6958 HUB MCAULY 1A103 1A103TCM GL PROPELLER CRACKED B ME4R K NONE O OTHER IN INSP/MAINT 1 SO 19 DURING INSPECTION, PROPELLER HUB WAS FOUND TO HAVE FORGING LAP IN HUB AREA. 5 N P50GL 2001110100113 20011101 00113 2001 11 1 2001FA0000448 4 20010926 G 2561 KS9P0101 LIFE VEST CABIN FAILED B KQ1R K NONE O OTHER IN INSP/MAINT 1 EA 07 LIFE VEST FAILED. THE MFG RECOMMENDED TWO PSI TEST IAW MANUAL. DOM FEB 1982 2001110100114 20011101 00114 2001 11 1 2001FA0000449 4 20010922 G 2561 KS9P0101H02 LIFE VEST CABIN FAILED B KQ1R K NONE O OTHER IN INSP/MAINT 1 EA 07 LIFE VEST FAILED. THE MFG RECOMMENDED 2 PSI CELL TEST IAW MANUAL. DOM JAN 1981 2001110100115 20011101 00115 SW 2001 11 1 2001FA0000450 1 20010925 G 6410 406016100119 BLADE BELL 407 407 1182206 SW ALLSN 250C 250C47B GL TAIL ROTOR DEBONDED B IIFR K NONE O OTHER IN INSP/MAINT 1 SW 03 407AK 53269 FOUND OVAL SHAPED AREA ON OUTSIDE OF TAIL ROTOR BLADE DEBONDED. 11 INCHES FROM BLADE ROOT TO 17 INCHES FROM BLADE ROOT. 1 INCH FROM TRAILING EDGE TO 3 INCHES FROM TRAILING EDGE OF BLADE. 1 G 7 1 3U 3 U O H2SW E1GL 2001110500049 20011105 00049 EU 2001 11 5 2001FA0000451 1 20010925 G 6210 117150041 BLADE BOLKMS 117 BK117A1 5626010 EU MAIN ROTOR DELAMINATED B YIVR K NONE O OTHER IN INSP/MAINT 1 SW 19 6969 M/R BLADE WAS RECEIVED FOR INSP AND EVAL. ABRASION STRIP CRACK WAS IDENTIFIED AT BLADE STATION 2305. PORTION OF ABRASI ON STRIP WAS REMOVED TO ALLOW EVALUATION OF UNDERLYING SURFACE. SKIN WAS ALSO CRACKED WITH DELAMINATION SURROUNDING ARE A. REVIEW OF BLADE RECORDS INDICATE THAT MFG PERFORMED REPAIR ON INNER WEIGHT 1 AND 2, CRACK IN ABRASION STRIP FROM A DRILL MARK ON INSIDE OF ABRASION STRIP IN AREA OF THIS REFERENCED REPAIR. REPAIR PERFORMED BY MFG IS FOR INSTALLATION O F PINS THROUGH INNER WEIGHTS 1 AND 2. THREE DRILL MARKS ON INSIDE SURFACE OF ABRASION STRIP THAT LINE UP WITH PINS INST ALLED FROM UPPER SURFACE. 1 G 7 2 3U H13EU 2001110100116 20011101 00116 GL 2001 11 1 2001FA0000453 3 20010911 G 6110 840118 TUBE HARTZL HCB5M HCB5MP3 GL PROPELLER CRACKED B ME4R K NONE O OTHER IN INSP/MAINT 1 SO 19 445 EVA2042 PROPELLER WAS FOR RECEIVED FOR STANDARD 60 MONTH OVERHAUL. CURRENT PROPELLER TIMES ARE TTSN 445.0 AND TSO N/A. THIS IS THE PROPELLER`S FIRST OVERHAUL. DURING THE INSPECTION OF THE PROPELLER COMPONENTS, HUB PART NUMBER 840-118, SERIAL NUM BER EVA2042 WITH PILOT TUBE PART NUMBER B-4020 WAS FOUND CRACKED IN NR 1 BLADE POSITION, 1.00 INCH FROM THE HUB SHOULDER FROM 11:00 TO 1:00 POSITION. THE CRACKED PILOT TUBE WAS REMOVED AND REPLACED AND THE HUB CHECKED SERVICEABLE, AFTER RE PAIR. THE CORRESPONDING BLADE, NR 1 CHECK SERVICEABLE WITH NO DEFECTS NOTED. PROPELLER WAS REASSEMBLED AFTER OVERHAUL AND RETURNED TO SERVICE. 6 C P44GL 2001110500036 20011105 00036 EA 2001 11 5 2001FA0000454 2 20011004 G 7322 CARBURETOR CESSNA 150 152 2071835 CE LYC O235 O235L2C 41505 EA ENGINE DEFECTIVE D A UNSCHED LANDING R PARTIAL RPM/PWR LOSS CL CLIMB 1 SW 03 49445 15283460 RL1860315 PILOT TOOK OFF IN AIRCRAFT, TURNED DOWNWIND AND ENGINE STARTED RUNNING ROUGH AND LOSING POWER. PILOT LANDED AC AND ENGI NE QUIT AS HE PULLED OFF RUNWAY. ALL SYSTEMS CHECKED POINTED TO INSTALLED NEW REBUILT CARBURETOR AND ENGINE FUNCTIONED NORMALLY. PROBABLE CAUSE FLOAT STICKING IN CARBURETOR. RECOMMENDATIONS TO PREVENT RECURRENCE. CARBURETOR RETURNED TO MFG FOR EVALUATION. 1 H 7 1 3O 3 O NT 3A19 E223 2001110100117 20011101 00117 NE 2001 11 1 2001FA0000455 2 20011009 G 8530 CYLINDER MAULE MT7235 MT7235 5470209 SO LYC O540 IO540W1A5 41532 NE ENGINE SEPARATED D O OTHER O OTHER CR CRUISE 1 WP 11 390AT 18028C L2559148A CRUISE FLIGHT. SUSPECT MFG DEFECTIVE CYLINDER WALL. NITRIDE CYLINDER. CYLINDER SEPARATION. 1 H 7 1 3O 3 O NC 3A23 1E4 2001110100118 20011101 00118 CE 2001 11 1 2001FA0000456 1 20010815 G 3240 5100106159 LINE CESSNA 414 414A 2075907 CE CONT O520 TSIO520* 17040 SO BRAKE SYS CHAFED C O OTHER K FLUID LOSS NR NOT REPORTED 1 CE 05 36887 4094 414A0835 RIGHT BRAKE LINE HAD A HOLE CHAFFED IN IT FROM BEING IN CONTACT WITH THE LINE HEATER DUCT LINE UNDER THE CO-PILOTS SEAT. THE BRAKE LINE RUNS UNDER THE HEAT DUCT AND IS VERY DIFFICULT TO SEE. THIS IS AN ORIGINAL PART. 1 L 7 2 3O 3 O A7CE E8CE 2001110100119 20011101 00119 EA 2001 11 1 2001FA0000457 2 20011016 G 8520 CRANKSHAFT UNIVAR 108 1083 9230408 NM FRNKLN 6A4165 6A4165* 27025 EA ENGINE BROKEN D MS2R O OTHER R PARTIAL RPM/PWR LOSS CR CRUISE 1 CE 09 833C 378 1083833 911174017 CRANKSHAFT BROKEN IN FLIGHT, LANDED WITHOUT INCIDENT. CRANKSHAFT BROKEN ON THE FORWARD SIDE OF JOURNAL NR 1 CYLINDER. 1 H 7 1 3O 3 O A767 E238 2001110100120 20011101 00120 SO 2001 11 1 2001FA0000458 2 20010928 G 8520 SA628488 LIFTER CESSNA 206 TU206G 2073357 CE CONT O520 TSIO520* 17040 SO ENGINE SPALLED D K NONE O OTHER IN INSP/MAINT 1 WP 01 5424Y 326 U20605287 512594 DURING ROUTINE OIL CHANGE, METAL WAS FOUND IN FILTER. ENGINE WAS REMOVED AND DISASSEMBLED. CAUSE WAS FOUND TO BE LIFTE R FACE AND CAM LOBE SPALLING ON CYLINDER CAM LOBES NR5 AND NR6 INTAKE. NO CORROSION NOTED. TWO OTHER INTAKE LIFTERS EX HIBIT PREMATURE WEAR, REMAINING CAM LOBES CHECK. OKAY FOR WEAR. CAMSHAFT WAS INSTALLED. 1 H 7 1 3O 3 O A4CE E8CE 2001110500037 20011105 00037 SO 2001 11 5 2001FA0000459 2 20010928 G 8530 SA643766 CYLINDER CESSNA 210 T210M 2073451 CE CONT O520 TSIO520* 17040 SO ENGINE OUT OF TOLERANCE D O OTHER W INADEQUATE Q C NR NOT REPORTED 1 WP 01 761RD 336 21062450 269614R CUSTOMER COMPLAINED OF INTERMITTENT ROUGHNESS. REMOVAL OF CYLINDERS REVEALED STICKING INTAKE VALVES. GUIDE TO VALVE TO LERANCE TOO TIGHT, BELOW MFG MINIMUM LIMITS. MFG CLAIMS TOLERANCE TOO TIGHT FROM NORMAL OPERATION. NO BUILD UP NOTED O F ANY KIND ON VALVE STEM OR INSIDE DIAMETER OF VALVE GUIDE. TOLERANCE WAS INCORRECTLY MACHINED AT PART/CYLINDER MANUFAC TURE OR ASSEMBLY. RECOMMEND DISASSEMBLY AND INSPECTION OF NEW CYLINDER ASSEMBLIES TO CHECK TOLERANCES. 1 H 7 1 3O 3 O 3A21 E8CE 2001110500038 20011105 00038 WP 2001 11 5 2001FA0000460 2 20011022 G 7260 30702123 GEARSHAFT HONEYWELL GARRTT TFE731 TFE7313 01518 WP ENGINE SEPARATED B IY2R E ENGINE SHUTDOWN O OTHER CL CLIMB 1 SW 15 7629 P2528 P83190 83190 WAS REMOVED FROM SABRE 65 DUE TO AN IN-FLIGHT SHUTDOWN DURING CLIMB. TRANSFER HORIZONTAL BEVEL GEARSHAFT EXHIBITE D SEPARATED GEAR TEETH, THUS CAUSING IFSD DUE TO NO AGB ROTATION. 4 F E6WE 2001121100010 20011211 00010 SO 2001 12 11 2001FA0000461 1 20011021 G 5102 45 FITTING BALWKS FIRE FIREFLY715 1050518 SO FUEL SYSTEM LEAKING B F65R K NONE O OTHER IN INSP/MAINT 1 SW 15 3214V 104 THIS SET OF FUEL HOSES WERE OBTAINED FROM THE HOLDER OF A PMA. THEY WERE INSTALLED IN MAY OF 1998. THE HOSE WAS FOUND TO BE LEAKING AT THE CONNECTION WHERE THE RUBBER HOSE MEETS THE FITTING. THE LEAK DOES NOT APPEAR TO BE CAUSED BY MISHA NDLING BUT BY A POOR FITTING. 1 B 0 0 A14SO 2001110500039 20011105 00039 SO 2001 11 5 2001FA0000462 2 20011017 G 8530 CYLINDER CESSNA 421 421B 2076014 CE CONT O520 GTSIO520C 17032 SO ENGINE MALFUNCTIONED G A UNSCHED LANDING E VIBRATION/BUFFET NR NOT REPORTED 1 GL 17 421CR 421B0224 LEFT ENGINE EXPERIENCED A VIBRATION. PILOT ELECTED TO LAND . REPLACED NR 2 CYLINDER. CLEANED VALVE GUIDES ON REMAININ G CYLINDERS. REPLACED SPARK PLUG ON NR 1 CYLINDER. FLIGHT CHECK GOOD. 1 L 7 2 3O 3 O A7CE E7CE 2001110500040 20011105 00040 EU 2001 11 5 2001FA0000463 1 20010924 G 2730 ELEVATOR GROB ASTIR G102IIIB 1660106 EU TAIL FLUTTER C O OTHER F FLT CONT AFFECTED CR CRUISE 1 WP 11 49JJ 5606CB WHILE CRUISING IN LEVEL FLIGHT AT 100 KTS, INDICATED, 5000 MSL, THE PILOT INITIATED A CLIMB ESTIMATED BETWEEN 2.0-2.5 G` S. AS SOON AS THE CLIMB WAS INITIATED FLUTTER WAS NOTED IN THE PITCH MOTION OF THE STICK (ELEVATOR FLUTTER). BACK PRES SURE WAS RELAXED AND THE FLUTTER STOPPED. THE GLIDER LANDED WITHOUT FURTHER INCIDENT. GLIDER IS CURRENTLY BEING EXAMIN ED AT MFG. 1 K 0 0 RC G33EU 2001110500041 20011105 00041 WP 2001 11 5 2001FA0000465 1 20011012 G 3246 152058 WHEEL BENDIX DOUG DC8 DC8* WP LANDING GEAR CRACKED B INWR K NONE O OTHER IN INSP/MAINT 1 SO 19 H3501OB NON DESTRUCTIVE TESTING INSPECTION SHOWED CRACK INDICATION AT BASE OF THE VALVE. 2 L 7 4 4J F 4A25 2001112800068 20011128 00068 2001 11 28 2001FA0000466 4 20011004 G 2562 7A1169SHARC7 SWITCH ELT INOPERATIVE D K NONE L NO TEST IN INSP/MAINT 1 GL 15 1385 WOULD NOT ACTIVATE - G SWITCH DEFECTIVE. WILL ACTIVATE IF TURNED ON, USING MECHANICAL SWITCH. 2001112800069 20011128 00069 2001 11 28 2001FA0000467 4 20010824 G 3422 060001701 GYRO COCKPIT DEFECTIVE B M2QA K NONE O OTHER IN INSP/MAINT 1 SO 09 OUT OF BOX FAILURE, SLOW TO ERECT. AFTER AIR IS DISCONNECTED GYRO ROLLS OVER 120 DEGREES. 2001112800070 20011128 00070 CE 2001 11 28 2001FA0000468 1 20010329 G 2752 51152401 GEAR CESSNA 421 421B 2076014 CE CONT O520 GTSIO520K 17032 SO FLAP ACTUATOR DAMAGED G K NONE O OTHER AP APPROACH 1 SW 11 421HM 3100 421B0029 ON FINAL, THE FLAPS MADE A LOUD POPPING SOUND. REMOVE FLAP ACTUATOR AND FOUND THAT THE GEAR BOX HAD ONE GEAR WITH THE T EETH MISSING. 1 L 7 2 3O 3 O A7CE E7CE 2001112800071 20011128 00071 EA 2001 11 28 2001FA0000469 2 20011003 G 7414 10068 GEAR AMTR HDWIND HEADWIND GL FRNKLN 4AC176 4AC176B* 27006 EA MAGNETO BROKEN G A UNSCHED LANDING Y ENGINE STOPPAGE CL CLIMB 1 NM 09 3948 2000 AB7 FOLLOWING TAKEOFF, AT ABOUT 200 FT, ENGINE FAILED. AIRCRAFT LANDED IN FIELD WITHOUT FURTHER INCIDENT. SUBSEQUENT INSPE CTION REVEALED CAM GEAR, WHICH DRIVE BOTH MAGNETO GEARS, HAD SHATTERED. CAM GEAR IS MADE OF MICARTA (FIBER) MATERIAL. 1 H 7 1 3O 3 O EXPA1H71 TC221 2001112800074 20011128 00074 EA 2001 11 28 2001FA0000472 2 20010912 G 8520 SL13212M03 BEARING LYC O360 HIO360D1A 41514 EA ENGINE FAILED B K NONE O OTHER IN INSP/MAINT 1 GL 03 331 L1195451A ENGINE WAS REMOVED DUE TO METAL CONTAMINATION. FOUND NR 3 CONNECTING ROD BEARING FAILED. THE ENGINE DID NOT EXHIBIT SI GNS OF OIL STARVATION. CAUSE FOR THIS FAILURE COULD BE DELAMINATION OF THE ROD BEARING. 3 O 1E10 2001120300056 20011203 00056 SO 2001 12 3 2001FA0000477 1 20011015 G 2121 313B57 ARMATURE PIPER PA31 PA31P350 7103111 SO FAN IMPROPER D K NONE L NO TEST IN INSP/MAINT 1 WP 23 347 FAN WAS TESTED AND FOUND NOT TO RUN, FAN WAS DISASSEMBLED AND FOUND TO HAVE A BRUSH LEAD WIRE CUT. THIS CAUSED THE FAN TO FAIL. THE FAN HAS AN ARMATURE IN IT THAT IS NOT OF MFG DESIGN AND DOES NOT MEET MFG SPECIFICATIONS. THE ARMATURE LA MINATIONS ARE NOT PROTECTED AND THE WIRE IS NOT WOUND PER MFG SPECIFICATIONS. 1 L 7 2 3O RT A8EA 2001120300057 20011203 00057 EA 2001 12 3 2001FA0000478 2 20010623 G 7322 IO323 ACCELL PUMP CESSNA 182 R182 2072734 CE LYC O540 IGO540* 41532 EA CARBURETOR STIFF D O OTHER O OTHER NR NOT REPORTED 1 SW 03 5284T R18201848 L2201140 THE CARB HAD TO BE CHANGED BECAUSE OF STIFF THROTTLE. THE CAUSE BEING THE ACCELERTOR PUMP, LINKAGE RODS. PRECISION SIL -MS-1CW. HAD NO EFFECT ON THE PUMP RODS. 1 H 7 1 3O 3 O RT 3A13 1E11 2001120300058 20011203 00058 EA 2001 12 3 2001FA0000479 2 20011024 G 7322 103235 ACCELL PUMP CESSNA 182 R182 2072734 CE LYC O540 O540J3C5 41532 EA CARBURETOR STIFF D O OTHER O OTHER NR NOT REPORTED 1 SW 03 6485T R18202039 CARBURETOR CHANGED BECAUSE OF ACCELERATOR PUMP STIFFNESS. PRECISION SIL CW AND HAD NO EFFECT ON EITHER CARBURETOR. 1 H 7 1 3O 3 O RT 3A13 E295 2001120300059 20011203 00059 NM 2001 12 3 2001FA0000480 1 20010717 G 5610 5717623097 WINDOW BOEING 737 737317 138447P NM GE CFM56 CFM56* 13802 NE COCKPIT CRACKED G K NONE O OTHER IN INSP/MAINT 1 SO 15 253DV 23800 AIRCRAFT PARKED ON HOT RAMP WITH INTERIOR REFLECTIVE SHADES INSTALLED IN THE COCKPIT. PRIOR TO PREFLIGHT, CREW STARTED APU FOR AIR CYCLE MACHINE(AIR CONDITIONING), UPON REMOVAL OF SUN SHADES IN THE COCKPIT, THE NR 2 PILOT WINDOW INNER PANE SHATTERED. 2 L 7 2 4F 4 F RT A16WE E2GL 2001120300060 20011203 00060 WP 2001 12 3 2001FA0000481 2 20010810 G 7321 89711012 FCU CESSNA 441 441 2076020 CE GARRTT TPE331 TPE33110 01514 WP LT ENGINE FAULTY G O OTHER O OTHER NR NOT REPORTED 1 WP 07 687AE 1313 4410087 P77369 ENGINE WOULD NOT REDUCE FUEL FLOW IN EITHER COMPUTER MODE OR MANUAL MODE TO ALLOW A NORMAL LANDING. THE AIRCRAFT HAD TO BE LANDED SINGLE ENGINE INSTALLING A REPAIRED FUEL CONTROL UNIT CURED THE FAULT. 1 L 7 2 3T 4 T RT A28CE E4WE 2001120300061 20011203 00061 WP 2001 12 3 2001FA0000482 2 20010810 G 7321 89711019 FCU CESSNA 441 441 2076020 CE GARRTT TPE331 TPE33110 01514 WP LT ENGINE MISREPAIRED D K NONE W J INADEQUATE Q C WARNING INDICATION IN INSP/MAINT 1 WP 07 687AE 990 4410087 P77369 UNIT WAS INSTALLED AFTER REPAIR BY MFG. UPON APPLYING POWER TO THE FUEL CONTROL AIRCRAFT HAD THE LEFT MONOPOLE FAIL LIG HT ILLUMINATED. FOUND THE WIRING AT THE FUEL CONTROL ELECTRICAL CONNECTOR MISSOLDERED, RESOLDERED WIRING AT THE CONNECT OR UNIT OPERATIONALLY CHECKED GOOD. 1 L 7 2 3T 4 T RT A28CE E4WE 2001120300062 20011203 00062 WP 2001 12 3 2001FA0000483 2 20010810 G 7321 89711012 FCU CESSNA 441 441 2076020 CE GARRTT TPE331 TPE33110 01514 WP LT ENGINE FAULTY D O OTHER O OTHER NR NOT REPORTED 1 WP 07 689AE 4798 4410281 ENGINE WOULD NOT OPERATE NORMALLY IN COMPUTER MODE. ENGINE SPEED WAS NOT BEING REGULATED PROPERLY BY FUEL CONTROL TORQUE MOTOR ENGINE OPERATED NORMALLY IN MANUAL MODE. OVERHAULED FUEL CONTROL WAS INSTALLED AND ENGINE OPERATED NORMALLY IN B OTH COMPUTER AND MANUAL MODES. 1 L 7 2 3T 4 T RT A28CE E4WE 2001120300063 20011203 00063 SO 2001 12 3 2001FA0000484 1 20010906 G 2612 512T130B150001 THERMOSWITCH GULSTM GV GV 3980116 SO RROYCE BR700 BR700710A110 NE FIRE DETECTION WRONG PART G O OTHER W N INADEQUATE Q C FALSE WARNING NR NOT REPORTED 1 SO 03 15UC 263 589 FOUND THERMAL SWITCH PN 512T130B150001 INSTALLED. REMOVED SWITCH AND INSTALLED PN GAS850DF512-250 REV B. THIS SWITCH C ORRECTED PROBLEM. THE REMOVED SWITCH CAUSED (FIRE WARNING LIGHT FOR THE LEFT AFT DUCT) TO COME ON. NO LEAKS NOTED. TH E SWITCH REMOVED WAS NOT CORRECT PART NUMBER. 2 L 7 2 4F 4 F RT A12EA E00057EN 2001112000091 20011120 00091 NE 2001 11 20 2001FA0000485 1 20011101 G 2421 28B135145AM GENERATOR SKRSKY S61 S61N 8142104 NE NR 2 ENGINE FAILED C K NONE B J SMOKE/FUMES/ODORS/SPARKS WARNING INDICATION CR CRUISE 1 SW 99 91158 363 61424 A BURNING SMELL WAS DETECTED IN FLIGHT. FOLLOWED BY THE NR 2 AC GEN DROPPING OFF-LINE. THE REST OF THE FLIGHT CONTINUE D NORMALLY. 2 G 7 2 4U 1H15 2001120300064 20011203 00064 EA 2001 12 3 2001FA0000487 2 20011009 G 7322 229164 TUBE PRECISION CESSNA 172 172L 2072432 CE LYC O320 O320E2D 41508 EA CARBURETOR SEPARATED C O OTHER O OTHER DE DESCENT 1 AL 05 7564G 1618 CK49483 17259264 R4279327A DURING DECENT, THE PILOT WAS UNABLE TO REDUCE POWER. USING THE MIXTURE CONTROL, THE PILOT MADE AN UNEVENTFUL LANDING. MAINTENANCE PERSONNEL FOUND THE ACCELERATOR DISCHARGE TUBE LAYING ON THE BOTTOM OF THE INTAKE AIRBOX. IT WAS DETERMINED THAT THE ACCELERATOR DISCHARGE TUBE SEALANT (LOCKTITE) HAD FAILED, CAUSING IT TO SEPARATE FROM THE ACCELERATOR DISCHARG E PORT. THIS CAUSED THE DISCHARGE TUBE TO LIFT UP THROUGH THE BOOST VENTURI BLOCKING ANY MOVEMENT OF THE THROTTLE VALVE . 1 H 7 1 3O 3 O NT 3A12 E274 2001120300065 20011203 00065 NM 2001 12 3 2001FA0000488 1 20011023 G 5302 HS54825H18 BOLT DOUG 600N 600N 3027377 NM ALLSN 250C 250C47B GL TAILBOOM BROKEN C K NONE O OTHER IN INSP/MAINT 1 WP 05 959SD RN019 DURING PREFLIGHT PILOT FOUND TAILBOOM BOLT MOVED. MAINTENANCE REMOVED COVER FOUND BOLT SAFETIED, BUT BROKEN 2.5 THREADS FROM SHANK BOLT REMOVED AND REINSTALLED 265.2 HOURS BEFORE. 1 G 7 1 3U 3 U NC H3WE E1GL 2001120300066 20011203 00066 EA 2001 12 3 2001FA0000489 2 20011101 G 8520 LW13884 MAIN BEARING CESSNA 182 182S 2072701 CE LYC O540 IO540AB1A5 EA ENGINE DELAMINATED E K NONE O OTHER IN INSP/MAINT 1 GL 03 61US 60 18280935 L2783748C FRONT MAIN BEARING DELAMINATION. DEFECT AREA WAS ABOUT THE SIZE OF A DIME. THERE WAS EVIDENCE OF SUBSURFACE FLAWS IN T HE SURROUNDING AREA. THE CAUSE WOULD BE IMPROPER MANUFACTURING. 1 H 7 1 3O 3 O NT 3A13 1E4 2001112900065 20011129 00065 GL 2001 11 29 2001FA0000490 3 20011025 G 6110 C4503 FORK BEECH 55 E55 1152732 CE CONT O550 IO550C SO HARTZL HCC4Y HCC4YF2 GL PROPELLER CRACKED B LU4R K NONE O OTHER IN INSP/MAINT 1 SO 17 7226R 211 TE1013 GL87 RELEVANT INDICATION(CRACK) FOUND BY NON DESTRUCTIVE TEST INSPECTION. 1 L 7 2 3O 3 O 3A16 E3SO 5 C P52GL 2001112900067 20011129 00067 GL 2001 11 29 2001FA0000491 3 20011025 G 6110 C4503 FORK BEECH 55 E55 1152732 CE CONT O550 IO550C SO HARTZL HCC4Y HCC4YF2 GL PROPELLER CRACKED B LU4R K NONE O OTHER IN INSP/MAINT 1 SO 17 7226R 211 TE1013 RELEVANT INDICATION (CRACK) FOUND BY NON DESTRUCTIVE TEST INSPECTION. 1 L 7 2 3O 3 O 3A16 E3SO 5 C P52GL 2001112900068 20011129 00068 GL 2001 11 29 2001FA0000492 3 20011022 G 6111 V8433N10 BLADE PIPER PA23 PA23250 7102308 SO LYC O540 O540* 41532 EA HARTZL HCA2 HCA2MVK2 GL PROPELLER CRACKED B LU4R K NONE O OTHER IN INSP/MAINT 1 SO 17 63ZZ 272421 JH652 CRACK FOUND IN BLADE SHANK BETWEEN TWO SHOULDERS APPROX 2 INCHES IN LENGTH. THREE HUNDRED HOURS EST SINCE LAST INSPECTI ON. 1 L 7 2 3O 3 O 1A10 E295 5 C P24EA 2001120300067 20011203 00067 CE 2001 12 3 2001FA0000493 1 20011023 G 5312 05121411 BULKHEAD CESSNA 170 170B 2072306 CE CONT O300 O300* 17022 SO FUSELAGE CRACKED B K NONE O OTHER IN INSP/MAINT 1 EA 05 3511C 2246 26554 BULKHEAD CRACKED AT LOWER RIGHT CORNER WHERE STEERING CABLE PULLEY BRACKET ATTACHES. 1 H 7 1 3O 3 O A799 E253 2001120300068 20011203 00068 2001 12 3 2001FA0000494 4 20011023 G 2300 TED93010 CONNECTOR CESSNA 172 172R 2072401 CE LYC O360 IO360B1E 41514 EA COMM SYSTEM LOOSE B I97R O OTHER O OTHER NR NOT REPORTED 1 CE 07 35331 17281037 COM 1 AND COM 2 INTERMITTENTLY INOPERATIVE. UPON INSPECTION FOUND SMALL COLLARS THAT COME WITH 90 DEGREE CONNECTOR LOOS E IN THE REAR OF BOTH COM 1 AND COM 2 COAX CONNECTORS. 1 H 7 1 3O 3 O NT 3A12 1E10 2001120300069 20011203 00069 EA 2001 12 3 2001FA0000497 2 20011022 G 8520 CRANKCASE GULSTM 500 500B 0141106 SW LYC O540 IO540E1A5 41532 EA ENGINE CRACKED E O OTHER K J FLUID LOSS WARNING INDICATION NR NOT REPORTED 1 SW 15 127KH 672 500B102738 CRANKCASE WAS CRACKED AT NR 2 UPPER CYLINDER STUD AND LEAD INTO OIL PRESSURE GALLEY. ENGINE LOST OIL PRESSURE AND WAS F EATHERED. 1 H 7 2 3O 3 O 6A1 1E4 2001120300070 20011203 00070 CE 2001 12 3 2001FA0000498 1 20011025 G 5330 PANEL CESSNA 210 210A 2073408 CE CONT O470 IO470* 17026 SO FUSELAGE CRACKED D K NONE O OTHER IN INSP/MAINT 1 SO 13 9419X 3395 21057719 WHILE AC WAS IN SHOP FOR PROP/ENGINE BALANCING, CRACK APPROX 4.5 INCHES LONG WAS FOUND ON REAR PANEL OF LOWER FORWARD FU SELAGE STRUCTURE. PANEL PN 12530181. PANEL WAS REPAIRED BY ADDITION OF DOUBLER AS SHOWN ON 377. CRACK WAS LOCATED ON S HEET METAL ABOVE WHEEL WELL. 1 H 7 1 3O 3 O RT 3A21 E1CE 2001112000092 20011120 00092 CE 2001 11 20 2001FA0000499 1 20011108 G 2822 2017002 PUMP RKWELL NA265 NA26565 7630107 CE FUEL SYS FAILED B K NONE J WARNING INDICATION CR CRUISE 1 CE 01 82CR 1407 1407 46549 PILOTS REPORTED THAT IN CRUISE FLIGHT LEFT LOW FUEL PRESSURE ANNUNCIATOR ILLUMINATED AND LEFT FUEL PUMP CIRCUIT BREAKER POPPED A FEW SECONDS LATER. AFTER LANDING, MAINTENANCE CREW REENGAGED CIRCUIT BREAKER, AND PUMP RAN, BUT WAS EXTREMELY NOISY. THERE WERE NO PREVIOUS INDICATIONS SUGGESTING IMMINENT PUMP FAILURE. MANDATORY OVERHAUL FREQUENCY OF PUMP IS 20 00 HOURS, THIS PUMP HAD 1,407 HOURS TOTAL TIME AND SINCE INSTALLATION APRIL 99. SPECULATE THAT AN INTERNAL BEARING FAIL ED BASED ON THE NOISE PUMP MADE AND THE FACT THAT THERE WAS NO METAL PARTICLE CONTAMINATION IN THE OUTPUT LINE OR IN LIN E FILTER. PUMP SENT TO OVERHAUL FACILITY TO DETERMINE ACTUAL FAILURE. 2 L 7 2 4J A2WE 2001120300071 20011203 00071 SW 2001 12 3 2001FA0000500 1 20011028 G 5711 SPAR CAP MOONEY M20 M20C 5870208 SW LYC O360 O360* 41514 EA WING CORRODED D K NONE O OTHER IN INSP/MAINT 1 SO 13 9671M 3514 670007 DURING ANNUAL INSPECTION, WING CARRY THROUGH SPAR WAS FOUND TO HAVE EXFOLIATION CORROSION ON TOP SPAR CAP. 1 L 7 1 3O 3 O 2A3 E286 2001120300072 20011203 00072 EU 2001 12 3 2001FA0000501 1 20011101 G 3242 AH52430 BRAKE ASSY HWKSLY DH125 DH1253ARA 423013P EU RROYCE VIPER VIPER522 54552 EU MLG FAILED D O OTHER O OTHER LD LANDING 1 CE 03 230TS NA700 REPLACE BRAKE ASSEMBLIES UPON 3RD LANDING (TAXING THE NEXT DAY) BRAKES FAILED. 2 L 7 2 4J 4 J A3EU E3EU 2001120300073 20011203 00073 CE 2001 12 3 2001FA0000503 1 20011106 G 5313 31120111 STRINGER LEAR 35 31A 5170531 CE GARRTT TFE731 TFE731* 01518 WP FUSELAGE CRACKED D K NONE O OTHER IN INSP/MAINT 1 SW 11 370SC 4814 070 THE RIB IS CRACKED IN 3 EACH PLACES WERE IT ATTACHES TO SKIN CRACKS ORIGINATE FROM RIVETS AND CRACKING TOWARDS OTHER RIV ETS. 2 L 7 2 4F 4 F RT A10CE E6WE 2001120300074 20011203 00074 SO 2001 12 3 2001FA0000505 2 20011029 G 7324 6314272A20 FLOW DIVIDER BEECH 33 F33A 1151425 CE CONT O520 IO520BB 17032 SO ENGINE DEFECTIVE C VJ3R O OTHER O OTHER NR NOT REPORTED 1 WP 07 5582X 887 CE1353 820397R ENGINE RUN ROUGH AND SOMETIME WOULD NOT SHUT DOWN. THE FUEL FLOW DIVIDER WOULD STICK OPEN, LETTING CONTINUOUS FUEL FLOW TO THE ENGINE. THE FLOW DIVIDER WAS REMOVED AND REPLACED WITH A NEW ONE, OPERATION OF ENGINE CHECKED OUT NORMAL. 1 L 7 1 3O 3 O 3A15 E5CE 2001120300075 20011203 00075 SO 2001 12 3 2001FA0000506 2 20011029 G 7414 M3004 BRUSHES SLICK BEECH 33 F33A 1151425 CE CONT O520 IO520BB 17032 SO MAGNETO WORN C VJ3R K NONE O OTHER IN INSP/MAINT 1 WP 07 8268T 998 00051554 CE1547 820321 MAGNETO REMOVED FROM ENGINE FOR 500 HOUR INSPECTION IAW MM. REMOVED THE REAR COVER AND THE DISTRIBUTOR BLOCK FROM MAGNE TO AND FOUND THE CARBON BRUSH WORN. CARBON DUST WAS FOUND ON THE FLAT PART OF THE CAP. WHERE IT LOOKS LIKE A SMALL SPA RK LINE TO GROUND. THE WEAR ON THIS BRUSH IS ABOVE NORMAL FOR 500 HOURS. (PN M3004 BRUSH). 1 L 7 1 3O 3 O 3A15 E5CE 2001120300076 20011203 00076 SO 2001 12 3 2001FA0000507 2 20011029 G 7414 M3004 BRUSHES BEECH 33 F33A 1151425 CE CONT O520 IO520BB 17032 SO MAGNETO WORN C VJ3R K NONE O OTHER IN INSP/MAINT 1 WP 07 38071 504 CE935 820386R MAGNETO REMOVED FROM ENGINE FOR 500 HOUR INSPECTION IAW MM. REMOVED THE REAR COVER AND THE DISTRIBUTOR BLOCK FROM MAGNE TO AND FOUND THE CARBON BRUSH WORN. CARBON DUST WAS FOUND ON THE FLAT PART OF THE CAP. WHERE IT LOOKS LIKE A SMALL SPA RK LINE TO GROUND. THE WEAR ON THIS BRUSH IS ABOVE NORMAL FOR 500 HOURS. (PN M3004 BRUSH) 1 L 7 1 3O 3 O 3A15 E5CE 2001120300077 20011203 00077 SO 2001 12 3 2001FA0000508 2 20011029 G 7414 BRUSHES SLICK BEECH 33 F33A 1151425 CE CONT O520 IO520BB 17032 SO MAGNETO WORN C VJ3R K NONE O OTHER IN INSP/MAINT 1 WP 07 38071 504 K3823 CE935 820386R MAGNETO REMOVED FROM ENGINE FOR 500 HOUR INSPECTION IAW MM. REMOVED THE REAR COVER AND THE DISTRIBUTOR BLOCK FROM MAGNE TO AND FOUND THE CARBON BRUSH WORN. CARBON DUST WAS FOUND ON THE FLAT PART OF THE CAP. WHERE IT LOOKS LIKE A SMALL SPA RK LINE TO GROUND. THE WEAR ON THIS BRUSH IS ABOVE NORMAL. 1 L 7 1 3O 3 O 3A15 E5CE 2001120300078 20011203 00078 SO 2001 12 3 2001FA0000509 2 20011029 G 7414 M3004M BRUSHES SLICK BEECH 33 F33A 1151425 CE CONT O520 IO520BB 17032 SO MAGNETO WORN C VJ3R K NONE O OTHER IN INSP/MAINT 1 WP 07 8268T 998 00051555 CE1547 820321 MAGNETO REMOVED FROM ENGINE FOR 500 HOUR INSPECTION IAW MM. REMOVED THE REAR COVER AND THE DISTRIBUTOR BLOCK FROM MAGNE TO AND FOUND THE CARBON BRUSH WORN. CARBON DUST WAS FOUND ON THE FLAT PART OF THE CAP. WHERE IT LOOKS LIKE A SMALL SPA RK LINE TO GROUND. THE WEAR ON THIS BRUSH IS ABOVE NORMAL FOR 500 HOURS. (PN M3004M BRUSH) 1 L 7 1 3O 3 O 3A15 E5CE 2001120300079 20011203 00079 SO 2001 12 3 2001FA0000510 2 20011029 G 7414 M3004 BRUSHES SLICK BEECH 33 F33A 1151425 CE CONT O520 IO520BB 17032 SO MAGNETO WORN C VJ3R K NONE O OTHER IN INSP/MAINT 1 WP 07 5521A 455 01042023 CE1338 820460R MAGNETO REMOVED FROM ENGINE FOR 500 HOUR INSPECTION IAW MM. REMOVED THE REAR COVER AND THE DISTRIBUTOR BLOCK FROM MAGNE TO AND FOUND THE CARBON BRUSH WORN. CARBON DUST WAS FOUND ON THE FLAT PART OF THE CAP. WHERE IT LOOKS LIKE A SMALL SPA RK LINE TO GROUND. THE WEAR ON THIS BRUSH IS ABOVE NORMAL FOR 500 HOURS. (PN M3004 BRUSH) 1 L 7 1 3O 3 O 3A15 E5CE 2001120300080 20011203 00080 SO 2001 12 3 2001FA0000511 2 20011029 G 7314 64621216A PUMP BEECH 33 F33A 1151425 CE CONT O520 IO520BB 17032 SO ENGINE LEAKING C VJ3R O OTHER K FLUID LOSS NR NOT REPORTED 1 WP 07 5582X 887 CE1353 820397R LEAKING FUEL FROM CASE DRAIN. 1 L 7 1 3O 3 O 3A15 E5CE 2001120300081 20011203 00081 CE 2001 12 3 2001FA0000512 1 20011108 G 2131 13035616 CONTROLLER CESSNA 500 550 2076604 CE PWA JT15 JT15D4 52112 NE CABIN PRESSURE MISREPAIRED C U1UM K NONE W INADEQUATE Q C IN INSP/MAINT 1 SW 01 5314J 3685 5500663 UPON INSTALLATION OF A REPAIRED CABIN PRESSURE RATE CONTROLLER IT WAS FOUND THAT THE AC WOULD NOT TEST OR PRESSURIZE ON THE GROUND. AFTER CHECKING THE ATTACHING SYSTEMS THE CANNON PLUG ON THE CONTROLLER WAS DISCONNECTED AND INSPECTED. AT INSPECTION IT WAS FOUND THAT THE CANNON PLUG PINS WERE PUSHED BACK FAR ENOUGH AND ALSO BENT SO AS NO CONNECTION COULD BE MADE. IT WAS ALSO NOTED THAT ON THE INSIDE OF THE CANNON PLUG THE INSULATION ON THE WIRES HAD NOT BEEN STRIPPED BACK. THE WIRES WERE JUST CRIMPED TO THE PINS AND PUT IN TO THE CANON PLUG. 1 L 7 2 4F 4 F A22CE E1NE 2001120300083 20011203 00083 GL 2001 12 3 2001FA0000514 1 20011030 G 2820 FUEL LINE BLANCA 17 1731ATC 1220437 GL LYC O540 TIO540* 41532 EA FUEL SYSTEM CORRODED B FB6R A UNSCHED LANDING K FLUID LOSS NR NOT REPORTED 1 NM 01 39828 1678 7331044 AIRCRAFT EXPERIENCED A MASSIVE FUEL LEAK INSIDE OF CABIN AREA CAUSING AN INFLIGHT EMERGENCY. DETERMINED FUEL LEAK CAUSE D BY CORROSION OF FUEL LINE FROM FIRE WALL TO FUEL PRESSURE INDICATOR. CORROSION CAUSED BY DISSIMILAR METAL OXIDATION W HERE FUEL LINE WAS ROUTED AGAINST STEEL RIBBED DEFROSTER HOSE. ALUMINUM FUEL LINE RUBBED THROUGH OUTER MATERIAL OF DEFR OSTER HOSE RESULTING IN ALUMINUM TO STEEL CONTACT. SUSPECT CONDITION EXISTED SINCE MANUFACTURE OF AIRCRAFT. EXTREME HA ZARD TO FLIGHT. 1 L 7 1 3O 3 O A18CE E14EA 2001120300108 20011203 00108 CE 2001 12 3 2001FA0000518 1 20011031 G 5530 RIVET BEECH 58 58P 1152744 CE CONT O520 TSIO520* 17040 SO VERTICAL STAB BROKEN B FE6R K NONE O OTHER IN INSP/MAINT 1 NM 11 145Z TJ289 RIVET HEAD MISSING ON EXTENSION FITTING OF VERTICAL STABILIZER FORWARD SPAR JUST ABOVE AREA WHERE SPAR IS BOLTED TO FUSE LAGE BULKHEAD. THERE IS NO EVIDENCE OF CORROSION OR CRACKING OF STRUCTURE IMMEDIATELY SURROUNDING RIVET LOCATION. RIVE T APPEARS TO HAVE FAILED IN TENSION. ADJACENT RIVETS APPEAR SOUND. 1 L 7 2 3O 3 O A23CE E8CE 2001120300109 20011203 00109 CE 2001 12 3 2001FA0000519 1 20011031 G 5330 1024400291 SKIN BEECH 58 58P 1152744 CE CONT O520 TSIO520* 17040 SO FUSELAGE CRACKED B FE6R K NONE O OTHER IN INSP/MAINT 1 NM 11 145Z 7165 TJ289 FOUND ONE INCH LONG CRACK IN AFT UPPER FUSELAGE SKIN AT BASE OF VERTICAL FIN. CRACK STARTS AT LEFT FORWARD STABILIZER S PAR EXTENSION CUTOUT AND EXTENDS UPWARD. SUSPECT LACK OF PROPER RADIUS IN CORNER OF CUTOUT CREATED A STRESS RISER WHICH CAUSED THE SKIN TO CRACK DURING NORMAL FLEXING OF AFT FUSELAGE. 1 L 7 2 3O 3 O A23CE E8CE 2001120300110 20011203 00110 CE 2001 12 3 2001FA0000520 1 20011031 G 5730 1021000115 SKIN BEECH 58 58P 1152744 CE CONT O520 TSIO520* 17040 SO WING CRACKED B FE6R K NONE O OTHER IN INSP/MAINT 1 NM 11 145Z 7165 TJ289 LOWER INBOARD LEADING EDGE SKIN CRACKED BETWEEN FUEL TANK DRAIN FITTING HOLE AND REAR EDGE OF SKIN. CRACK IS THROUGH AN D AREA APPROXIMATELY 2 INCHES WIDE THAT HAS NO RIVET CONNECTING SKIN TO FRONT SPAR STRUCTURE. NORMAL FLEXING OF WING AP PEARS TO BE STRESSING THE SKIN IN THIS AREA. THIS IS THE THIRD BARON FOUND WITH THIS PROBLEM. 1 L 7 2 3O 3 O A23CE E8CE 2002012400101 20020124 00101 SO 2002 1 24 2001FA0000521 1 20011030 G 2710 6270102TO13 CONTROL CABLE PIPER PA28 PA28140 7102802 SO AILERON & RUDDER CORRODED D K NONE O OTHER IN INSP/MAINT 1 EA 23 2471 2821855 CONTROL CABLES FOUND TO HAVE CORRODED END FITTINGS AS DESCRIBED IN NTSB LETTER OF APRIL 16, 2001 TO FAA. AILERON, RUDDER ,AND STABILATOR CABLES ALL REPLACED WITH NEW. MECHANIC NEEDS TO USE A LOW POWER(5X OR 10X) MAGNIFING GLASS TO SEE PITTIN G CLEARLY. 1 L 7 1 3O 2A13 2001112000093 20011120 00093 EA 2001 11 20 2001FA0000522 1 20011030 G 3230 DRAG BRACE FRCHLD 22 22C7A 3370104 EA LANDING GEAR FAILED C O OTHER O OTHER UK UNKNOWN 1 SW 99 DRAG BRACE FAILURE. 1 H 7 1 3I ATC438 2002012400102 20020124 00102 CE 2002 1 24 2001FA0000524 1 20011105 G 5511 123262224 SPAR CESSNA CESSNA 210 T210N 2073456 CE ELEVATOR CRACKED G K NONE O OTHER IN INSP/MAINT 1 NM 04 843YT 4546 100 21063334 THE FRONT SPAR,ATTACHMENT BRACKET,UPPER AND LOWER SPARS, AND DOUBLERS OF THE HORIZONAL STABILIZER WAS CRACKED. 1 H 7 1 3O 3A21 2002012400103 20020124 00103 CE 2002 1 24 2001FA0000525 1 20011105 G 5521 123262226 SPAR CESSNA CESSNA 210 T210N 2073456 CE ELEVATOR CRACKED G K NONE O OTHER IN INSP/MAINT 1 NM 04 843YT 4546 100 21063334 ELEVATOR SPAR CRACKED,ATTACHMENT BRACKET, AND DOUBLERS ALSO CRACKED. 1 H 7 1 3O 3A21 2002012400104 20020124 00104 CE 2002 1 24 2001FA0000526 1 20011105 G 5521 123262227 SPAR CESSNA CESSNA 210 T210N 2073456 CE ELEVATOR CRACKED G K NONE O OTHER IN INSP/MAINT 1 NM 04 843YT 4546 100 21063334 ELEVATOR FRONT SPAR, DOUBLERS, AND ATTACHMENT CRACKED.AIRCRAFT USED IN PIPELINE PATROL. 1 H 7 1 3O 3A21 2002012500003 20020125 00003 SO 2002 1 25 2001FA0000528 1 20011105 G 2140 A23D04 VALVE PIPER PA23 PA23250 7102308 SO HEATER LEAKING D K NONE K FLUID LOSS IN INSP/MAINT 1 GL 13 17WE 3692 277854118 WHILE PERFORMING THE INSPECTION OF THE HEATER FUEL REGULATOR VALVE P/N A23D04 (PIPER P/N 461-731) AS REQUIRED BY AD 2001 -17-13, THE VALVE WAS FOUND TO LEAK BY VISUAL INSPECTION. THE LEAKAGE WAS NOT EVIDENT UNTIL THE VALVE WAS REMOVED FROM THE SHROUD. THE VALVE WAS REPLACED WITH A NEW VALVE AS REQUIRED. 1 L 7 2 3O 1A10 2002012500004 20020125 00004 CE 2002 1 25 2001FA0000529 1 20011105 G 5753 ARM CESSNA 172 172 2072402 CE TE FLAPS WORN C K NONE O OTHER IN INSP/MAINT 1 GL 15 4124F 3451 46024 DURING AN ANNUAL INSPECTION, ALL FOUR OF THE FLAP ARMS HAD WEAR FROM THE ROLLERS. THE DAMAGE ON 3 OF THE ARMS WAS ABLE TO BE BLENDED WITH LESS THAN .020 OF MATERIAL REMOVAL AND WERE SERVICEABLE AS PER SERVICE BULLETIN. THE DAMAGE TO THE RT INBOARD ARM WAS UNABLE TO BE BLENDED OUT WITHIN LIMITS. A NEW FLAP ARM KIT P/N SK180-44-1 WAS ORDERED. UPON RECEIPT THE NEW PARTS WERE INSPECTED AND IT WAS FOUND THAT ONE OF THE RIVETS HAD NOT BEEN BUCKED AT ALL AND 3 OTHERS HAD SHOP HE ADS THAT WERE NOT BUCKED TO THE PROPER DIMENSIONS. THE RIVETS WERE SQUEEZED TO THE PROPER DIMENSIONS AND THE NEW ARM AS SEMBLY INSTALLED. 1 H 7 1 3O NT 3A12 2002012900002 20020129 00002 GL 2002 1 29 2001FA0000530 1 20011104 G 5510 TIE BOLT AVIAT A1 A1B 2210406 GL LYC O360 O360* 41514 EA HARTZL HCC2Y HCC2YK1 GL HORIZONTAL STAB SHEARED C K NONE O OTHER IN INSP/MAINT 1 GL 15 500 5 L3732036A CH33963B AVIAT HUSKY A1B. BROKEN TIE-ROD BOLT DISCOVERED DURING A POST-FLIGHT PILOT'S INSPECTION. THIS PART ATTACHES THE STRUT ( LEFT SIDE STRUT (1 OF 3) = LOWER, ANTERIOR)TO THE LEADING EDGE OF THE HORIZONTAL STABILIZER. UNABLE TO PROVIDE AVIAT PN AS THEIR PARTS CATALOG IS NOT REVISED FROM EARLIER HUSKY MODELS TO SHOW THIS PART AND/OR PROVIDE A NUMBER. 1 H 7 1 3O 3 O NC A22NM E286 5 C P920 2002012500005 20020125 00005 CE 2002 1 25 2001FA0000531 1 20011108 G 3230 08411132 SCREW CESSNA 340 340A 2076405 CE CONT O520 TSIO520NB 17040 SO MCAULY 3AF32C 3AF32C93 GL DOWNLOCK BROKEN B BIGR O OTHER O OTHER TX TAXI/GRND HDL 1 NM 09 115BH 7169 340A1531 DOWNLOCK ADJUSTING SCREW BROKE FOR REASONS UNKNOWN.THIS ALLOWED LEFT MAIN GEAR TO LOSE DOWNLOCK TENSION. LEFT MAIN LANDI NG GEAR RETRACTED UNTIL IT STOPPED AGAINST INBOARD GEAR DOOR. THIS ALLOWED PROP TO HIT THE GROUND AND DAMAGE TO LEFT FLA PS OCCURED. 1 L 7 2 3O 3 O 3A25 E8CE 5 C P22EA 2002012500006 20020125 00006 NE 2002 1 25 2001FA0000532 2 20011108 G 8550 3020907 DIPSTICK CESSNA 500 550 2076604 CE PWA JT15 JT15D4 52112 NE ENGINE BROKEN B D RETURN TO BLOCK K J FLUID LOSS WARNING INDICATION LD LANDING 1 SW 15 43SA 4951 1471 5500086 PCE71655 FAILURE OF OIL DIPSTICK AT ATTACHMENT LOCK NUT CAUSING LOSS OF OIL AND LOWER THAN NORMAL OIL PRESSURE. 1 L 7 2 4F 4 F A22CE E1NE 2001120500073 20011205 00073 SW 2001 12 5 2001FA0000534 1 20011016 G 6310 3039080 GEARBOX BELL 412 412 1182202 SW PWA PT6T PT6T3B 52045 NE ENGINE MAKING METAL C E A ENGINE SHUTDOWN UNSCHED LANDING J WARNING INDICATION CR CRUISE 1 WP 19 412DE 2690 248 36033 APPORXIMATELY 45 MINUTES INTO CRUISE FLIGHT A NR 2 ENGINE CHIP LIGHT ILLUMINATED. THE NR 2 ENGINE WAS SHUTDOWN AND THE AIRCRAFT RETURNED TO BASE AND PERFORMED A RUN ON LANDING DUE TO INSUFFICIENT POWER FOR HOVERING. THE MAINTENANCE TECHNI CIANS PULLED THE NR 2 ENGINE CHIP DETECTORS AND FOUND SIGNIFICANT METAL DEBRIS ON THE ENGINE/COMBINING GEARBOX CHIP DETE CTOR AND IN THE OIL FILTER. THE ENGINE OIL WAS SUBSEQUENTLY DRAINED. THE OIL SYSTEM WAS FLUSHED AND THE FILTER REPLACED. THE CHIP DETECTOR WAS CLEANED OF ALL DEBRIS AND THE HELICOPTER WAS RUN FOR 5 MINUTES ON THE GROUND. THE HELICOPTER WA S SHUT DOWN AFTER 5 MINUTES AND AGAIN METAL DEBRIS WAS FOUND ON THE ENGINE/COMBINING GEARBOX CHIP DETECTOR AND IN THE OI 1 G 7 2 4U 4 U H4SW E22EA 2002012500021 20020125 00021 CE 2002 1 25 2001FA0000535 1 20011016 G 5620 1014400421 WINDOW BEECH 200 B200 1152922 CE CARGO BAY CRACKED C O OTHER O OTHER CR CRUISE 1 WP 19 185XP 3185 BB952 LEFT HAND BAGGAGE COMPARTMENT WINDOW OUTER PANE CRACKED WHILE IN CRUISE FLIGHT. INNER PLY REMAINED INTACT AND FLIGHT CO NTINUED UNPRESSURIZED TO HOME BASE WITHOUT FURTHER INCIDENT. 1 L 7 2 4T A24CE 2001120500074 20011205 00074 GL 2001 12 5 2001FA0000536 2 20011003 G 7412 23064130 EXCITER BELL 407 407 1182206 SW ALLSN 250C 250C47B GL ENGINE FAILED D C ABORTED TAKEOFF S AFFECT SYSTEMS TO TAKEOFF 1 SW 99 17SP 245 53444 847487 ENGINE FAILED TO START. IGNITORS WERE NOT HEARD AS NORMALLY HEARD. IGNITOR WAS REPLACED WITH NEGATIVE RESULTS. IGNITION EXCITOR REPLACED WITH NEW, RESOLVING DESCREPANCY. 1 G 7 1 3U 3 U O H2SW E1GL 2002012500023 20020125 00023 EA 2002 1 25 2001FA0000537 2 20011019 G 8550 78531 HOUSING LYC O320 O320E3D 41508 EA OIL PUMP CRACKED B K NONE O OTHER IN INSP/MAINT 1 WP 07 2981 589 L3400727A UPON DIASSEMBLING THE OIL PUMP, A MINIMUM OF 4 CRACKS WERE FOUND EMANATING RADIALLY FROM THE IMPELLER SHAFT BORE EXTENDI NG THROUGH THE PUMP BODY. NO EVIDENCE OF FOREIGN OBJECTS PASSING THROUGH THE PUMP GEARS WAS FOUND. 3 O E274 2002012500026 20020125 00026 GL 2002 1 25 2001FA0000539 1 20011024 G 2821 FUEL FILTER AMTR KIS KISTR1 056201W GL AMTR SUBURU SUBURU GL FUEL SYSTEM CLOGGED G K NONE O OTHER IN INSP/MAINT 1 GL 09 6 INTREGAL FUEL TANK, FIBERGLASS DUSTY FIBERS CLOGGED FUEL FILTER ENOUGH TO DEGRADE POWER. FORCED LANDING DUE TO LACK OF P OWER. AIRCRAFT HAD 6 HOURS SINCE INITAL FLIGHT. IT APPEARS THAT FIBERS FROM INSIDE THE FIBERGLASS FUEL TANK MIGRATED I N THE FIRST FEW HOURS OF OPERATION AND CLOGGED THE IN-LINE FUEL FILTER. 1 L 7 1 3O 3 O NT EXPA1L71 EXPE3O 2001120500075 20011205 00075 NM 2001 12 5 2001FA0000540 1 20011026 G 5302 500N31296 ANGLE DOUG 600N 600N 3027377 NM FUSELAGE CRACKED D K NONE O OTHER IN INSP/MAINT 1 SW 99 957SD 2125 RN011 INSPECTED RT UPPER TAILBOOM ATTACH FITTING ON FUSELAGE . WE FOUND A CRACK IN ANGLE P/N 500N3129-6. THIS ANGLE CAN ONLY BE SEEN BY REMOVAL OF THE RIVETED PANEL ON THE SIDE OF THE FUSELAGE. WE HAVE FOUND CRACKS ON ALL 3 OF OUR 600N MODELS . 1 G 7 1 3U NC H3WE 2001120500076 20011205 00076 NM 2001 12 5 2001FA0000541 1 20011026 G 5302 500N31296 ANGLE DOUG 600N 600N 3027377 NM TAIL BOOM CRACKED D K NONE O OTHER IN INSP/MAINT 1 SW 99 958SD 2219 RN018 DURING INSPECTION OF THE RT UPPER TAILBOOM MOUNT WE FOUND P/N 500N3129-6 ANGLE CRACKED. TO INSPECT, YOU MUST REMOVE THE RIVETED CLOSURE ,ON THE SIDE OF THE FUSELAGE. WE HAVE FOUND CRACKS ,ON ALL 3, OF OUR 600N MODELS. 1 G 7 1 3U NC H3WE 2001120500077 20011205 00077 NM 2001 12 5 2001FA0000542 1 20011026 G 5302 500N3422 FITTING DOUG 600N 600N 3027377 NM TAIL BOOM CRACKED D K NONE O OTHER IN INSP/MAINT 1 SW 99 959SD 1993 RN019 AFTER THE PILOT REPORTED UNUSUAL TAILBOOM MOVEMENT DURING HIS PREFLIGHT IHSPECTION , ONE OF OUR MECHANICS REMOVE THE TAI LBOOM ATTACHMENT FAIRING. HE FOUND THE RT UPPER TAILBOOM ATTACH BOLT HAD FRACTURED , AND THE BOLT HEAD WAS HELD ONLY BY SAFETY WIRE.WE THEN REMOVED THE RIVETED CLOSURE COVERING THE NUTPLATE AND ATTACH FITTING. WE FOUND FITTING, P/N 500N3422 ,CRACKED AND ANGLE P/N 500N3129-6 ,ALSO CRACKED. WE HAVE GROUNDED ALL 3 OF OUR 600N MODELS , AND HAVE FOUND CRACKS O N ALL 3 ANGLES . 1 G 7 1 3U NC H3WE 2002012500029 20020125 00029 CE 2002 1 25 2001FA0000543 1 20011030 G 5712 57222061 RIB CESSNA 441 441 2076020 CE GARRTT TPE331 TPE3318 01514 WP LT CENTER WING CRACKED B K NONE P NO WARNING INDICATION IN INSP/MAINT 1 SO 15 84LJ 5155 4410084 DURING A SCHEDULED INSPECTION, IT WAS NOTED THAT THE LEFT WING CENTER SECTION CANTED RIB CAP P/N: 5722206-1 (LCWS 26.85) HAD A VISUALLY SUSPECT AREA ALONG THE BEND RADIUS BETWEEN THE CENTER WING MAIN SPAR (FS 177.45) AND FS 188.95. FURTHER INSPECTION USING FLUORESCENT PENETRANT REVEALED (2) CRACKS IN THE RADIUS. BOTH CRACKS ARE APPROXIMATELY 1INCH LONG. AFTE R REMOVAL OF THE RIB CAP, CLOSE EXAMINATION OF THE PART REVEALED THAT THE CAP WAS MANUFACTURED WITH THE BEND RADIUS PARA LLEL TO THE GRAIN OF THE METAL RESULTING IN A GRAIN SEPARATION TYPE CRACK. 1 L 7 2 3T 4 T RT A28CE E4WE 2002012500030 20020125 00030 CE 2002 1 25 2001FA0000544 1 20011030 G 5712 57222061 RIB CESSNA 441 441 2076020 CE LT CENTER WING CRACKED B K NONE O OTHER IN INSP/MAINT 1 SO 15 84LJ 5155 4410084 DURING A SCHEDULED INSPECTION, IT WAS NOTED THAT THE RIGHT WING CENTER SECTION CANTED RIB CAP P/N: 5722206-2 (RCSW 26.85 ) HAD A VISUALLY SUSPECT AREA ALONG THE BEND RADIUS AFT OF THE CENTER WING MAIN SPAR (FS 177.45). FURTHER INSPECTION USI NG FLUORESCENT PENETRANT CONFIRMED A 1INCH CRACK. AFTER REMOVAL OF THE RIB CAP, CLOSE EXAMINATION OF THE PART REVEALED T HAT THE CAP WAS MANUFACTURED WITH THE BEND RADIUS PARALLEL TO THE GRAIN OF THE METAL RESULTING IN A GRAIN SEPERATION TYP E CRACK. 1 L 7 2 3T RT A28CE 2001120300111 20011203 00111 SO 2001 12 3 2001FA0000545 2 20011025 G 7414 6320 MAGNETO CESSNA 340 340A 2076405 CE CONT O520 TSIO520NB 17040 SO ENGINE CORRODED C O OTHER O OTHER NR NOT REPORTED 1 NE 05 340KG 1200 340A1505 R278307R PILOT NOTED INTERMITTENT ROUGH ENGINE AND FLUCTUATING EGT. DURING SUBSEQUENT TROUBLE SHOOTING, NOTED ONLY ONE IMPULSE C OUPLING SOUND. WHEN PULLING ENGINE THROUGH WITH SPARK PLUGS OUT AND TIMING WAS WAY OFF. UPON REMOVAL FOUND THAT COULD BARELY TURN THE MAGNETO BY HAND. WHEN MAGNETO WAS OPENED, THERE WAS RUST SHOWING ON ROTOR AND COIL WEDGE WAS LOOSE. 1 L 7 2 3O 3 O 3A25 E8CE 2001120300112 20011203 00112 2001 12 3 2001FA0000546 4 20011026 G 6113 055032111 BULKHEAD CESSNA 172 172S 2072439 CE SPINNER BROKEN D K NONE O OTHER IN INSP/MAINT 1 NM 08 753GW 287 172S8753 REAR SPINNER BULKHEAD WAS FOUND BROKEN AT NUTPLATE NEAREST TO AFT SIDE OF NR 1 BLADE. MATERIAL HAD COMPLETELY SEPARATED FROM BULKHEAD AND ALLOWED THE SPINNER TO BEND OUTWARD FROM CENTRIFUGAL FORCE. SPINNER WAS NOT OBVIOUSLY DAMAGED. THIS BULKHEAD WAS INSTALLED ON THIS AIRCRAFT AT 153.3 HOURS ACTT. THE SPINNER WAS ALSO REPLACED AT THIS TIME DUE TO CRACKIN G, THE SPINNER WAS REPLACED A SECOND TIME AT 394.7 HOURS ACCT DUE TO CRACKS FROM THE BLADE CUTOUT. AT THIS TIME THE BUL KHEAD WAS INSPECTED WITH NO SIGNS OF CRACKING. 1 H 7 1 3O NT 3A12 2001120300113 20011203 00113 EA 2001 12 3 2001FA0000547 2 20010905 G 7310 LW120980140 FUEL LINE MOONEY M20 M20J 5870219 SW LYC O360 IO360A1A 41514 EA ENGINE CRACKED D K NONE O OTHER NR NOT REPORTED 1 EA 21 10719 1068 243141 FOUND THREE CRACKED FUEL INJECTOR LINES. CRACKS ARE LOCATED AT THE SILVER SWEAT JOINT IN THE FILLET. IT IS AS THOUGH T HE JOINT WAS NOT PROPERLY PREPARED OR THE FLUX WAS NOT EFFECTIVE. TWO OF THE TUBES HAD ONLY 1068.2 HOURS SINCE NEW. 1 L 7 1 3O 3 O 2A3 1E10 2001120300114 20011203 00114 EA 2001 12 3 2001FA0000548 2 20010905 G 7310 LW129980104 FUEL LINE BEECH 23 A2324 1151226 CE LYC O360 IO360A1A 41514 EA ENGINE CRACKED D K NONE O OTHER NR NOT REPORTED 1 EA 21 3601Q 1068 MA226 FOUND THREE CRACKED FUEL INJECTOR LINES. THE CRACKS ARE LOCATED AT THE SILVER SWEAT JOINT IN THE FILLET. IT IS AS THOU GH THE JOINT WAS NOT PROPERLY PREPARED OR THE FLUX WAS NOT EFFECTIVE. TWO OF THE TUBES HAD ONLY 1068.2 HOURS SINCE NEW. 1 L 7 1 3O 3 O A1CE 1E10 2001120300115 20011203 00115 SO 2001 12 3 2001FA0000549 1 20010921 G 7810 LW13027 ADAPTER PIPER PA31 PA31P 7103120 SO LYC O541 TIGO541E1A 41539 EA ENGINE BROKEN B E A ENGINE SHUTDOWN UNSCHED LANDING R PARTIAL RPM/PWR LOSS NR NOT REPORTED 1 WP 07 651SC 31P7630006 L34362 FLANGE ON LEFT ENGINE OUTBOARD ADAPTER BROKE OFF OF ADAPTER. EXHAUST GASES LEAKED FROM SYSTEM CAUSING TURBOCHARGER OUTP UT TO DROP. PILOT SHUT DOWN ENGINE AND RETURNED TO AIRPORT. 1 L 7 2 3O 3 O A8EA E19EA 2001120300116 20011203 00116 SW 2001 12 3 2001FA0000550 1 20011101 G 2730 200190202 SWITCH MOONEY M20 M20K 5870220 SW CONT O360 TSIO360* 17025 SO ELEVATOR TRIM STUCK C O OTHER F FLT CONT AFFECTED NR NOT REPORTED 1 WP 21 5262M 251183 DURING TRIM ADJUSTMENT, PILOT EXPERIENCED AN UNCOMMANDED NOSE DOWN ATTITUDE. GROUND INVESTIGATION REVEALED THAT THE ELE VATOR TRIM SWITCH HAD STUCK IN THE NOSE DOWN POSITION. 1 L 7 1 3O 3 O 2A3 E9CE 2001120300117 20011203 00117 SO 2001 12 3 2001FA0000551 2 20011114 G 8550 ADAPTER CESSNA 182 182B 2072706 CE CONT O470 O470L 17026 SO ENGINE DEFECTIVE C K NONE J WARNING INDICATION IN INSP/MAINT 1 NM 08 7179E 52179 816510L4 NO OIL PRESSURE UPON ENGINE START UP. OIL PUMP, SUCTION TUBE, AND CONNECTIONS CHECKED OK. REMOVED FILTER ADAPTER, INST ALLED FILTER SCREEN ENGINE HAD PROPER OIL PRESSURE. NO APPARENT DAMAGE TO FILTER ADAPTER. 1 H 7 1 3O 3 O NT 3A13 E273 2001121000109 20011210 00109 CE 2001 12 10 2001FA0000552 1 20011108 G 2436 S23731 CONNECTOR CESSNA 210 T210N 2073456 CE CONT O520 TSIO520* 17040 SO VOLTAGE REG LOOSE B O OTHER H ELECT. POWER LOSS-50 PC CR CRUISE 1 GL 21 6410N 21062986 AIRCRAFT LOST ELECTRICAL POWER IN FLIGHT. PLUG THAT CONNECTED VOLTAGE REGULATOR/ WARNING INDICATOR TO ALTERNATOR DID NO T LOCK AND VIBRATED LOOSE. BECAUSE THE LOW VOLTAGE INDICATOR DIE NOT ILLUMINATE AND THE AMMETER IS ON THE FAR RIGHT SID E OF CABIN, PILOT WAS UNAWARE OF PROBLEM UNTIL RADIO COMMUNICATION FAILED. 1 H 7 1 3O 3 O 3A21 E8CE 2001120500078 20011205 00078 EU 2001 12 5 2001FA0000553 1 20010925 G 6210 117150041 BLADE BOLKMS 117 BK117A1 5626010 EU MAIN ROTOR CRACKED B YIVR K NONE O OTHER IN INSP/MAINT 1 SW 19 6969 M/R BLADE WAS RECD AT MFG FOR INSP AND EVAL. ABR STRIP CRACK WAS ID AT BLADE STAT 2305. PORTION OF ABR STRIP WAS REMOV ED TO ALLOW EVAL OF UNDERLYING SURFACE. SKIN WAS CRACKED WITH DELAM SURROUNDING AREA. REVIEW OF BLADE RECORDS INDICATE MFG REPAIR ON INNER WEIGHT 1 AND 2. CRACK IN ABR STRIP PROPAGATED FROM A DRILL MARK ON INSIDE OF ABR STRIP IN AREA OF THIS REF REPAIR. REPAIR PERFORMED FOR INSTALL OF PINS THROUGH INNER WEIGHTS 1 AND 2. THREE DRILL MARKS ON INSIDE SURFA CE OF ABRASION STRIP THAT LINE UP PINS. PINS ARE INSTALLED FROM UPPER SURFACE, AND IS OBVIOUS THAT HOLES WERE DRILLED T OO DEEP ALLOWING DRILL TO MARK INSIDE OF LWR LEG OF ABR STRIP. CUST REPORTED HAVING OTHER BLADES THAT DEVELOPED ABRASIO 1 G 7 2 3U H13EU 2001120300119 20011203 00119 SO 2001 12 3 2001FA0000554 1 20011105 G 2810 FUEL CAP PIPER PA22 PA22108 7102204 SO LYC O235 O235* 41505 EA RT WING IMPROPER PART D O OTHER W INADEQUATE Q C NR NOT REPORTED 1 EA 09 4855Z 228430 (2) PILOTS HAD FUEL STARVATION. BOTH PILOTS, ON LANDING, CHECK RIGHT WING TANKS AND HEARD HISSING SOUND. EXAMINED CAP S AND FOUND NOW VENT HOLES. BOTH CAPS SEEMED NEW AND MADE OF ALUMINUM. CHANGED CAPS TO VENTED STYLE, HAD NO FURTHER TR OUBLE. 1 H 7 1 3O 3 O 1A6 E223 2001120300120 20011203 00120 EA 2001 12 3 2001FA0000555 2 20011107 G 8520 LS13521 BEARING PIPER PA28 PA28181 7102807 SO LYC O360 O360A4M 41514 EA ENGINE FAILED G K NONE O OTHER IN INSP/MAINT 1 EA 25 8458H 450 288290053 L2777436A WHILE ACCOMPLISHING 50 HOUR INSPECTION, METAL WAS FOUND IN FILTER. TEAR DOWN OF ENGINE REVEALED THAT BEARING PART FAILE D. BATCH NUMBER ON BEARING WAS 5-99. 1 L 7 1 3O 3 O 2A13 E286 2001120300121 20011203 00121 SO 2001 12 3 2001FA0000557 2 20011115 G 8520 CRANKSHAFT CIRRUS SR SR20 05628AJ GL CONT O360 IO360E 17025 SO ENGINE FAILED C A UNSCHED LANDING O OTHER CR CRUISE 1 SO 05 76CP 410 1054 357182 IN FLIGHT ENGINE FAILURE, CRANKSHAFT COUNTERWEIGHT AND DOUBLE ROD FAILURE, BLEW TWO ROD THROUGH CASE.(K) 1 L 7 1 3O 3 O NT A00009CH E1CE 2001120300122 20011203 00122 EA 2001 12 3 2001FA0000558 2 20011026 G 8520 STUD PIPER PA18 PA18 7101802 SO LYC O235 O235C1 41505 EA ENGINE BROKEN D O OTHER O OTHER NR NOT REPORTED 1 CE 07 7278K 18185 611315 BROKEN CYLINDER BASE STUDS, 5 STUDS BROKEN ON NR 1 CYLINDER, FOUND MIS-TORQUED ON NR 2, NR 3, AND NR 4, ALSO.(K) 1 H 7 1 3O 3 O 1A2 E223 2001120300123 20011203 00123 SO 2001 12 3 2001FA0000564 1 20010827 G 3230 3807802 DOWNLOCK PIPER PA32 PA32R300 7103213 SO LYC O540 IO540* 41532 EA NLG BROKEN D O OTHER O OTHER CR CRUISE 1 AL 01 200HM 351 32R7680025 NOSE GEAR DROPPED OUT OF WHEEL WELL INFLIGHT. FOUND DOWNLOCK BROKEN WHERE NOSE ACTUATOR ROD ATTACHES. THIS HAS HAPPENE D ON MORE THAN ONE OCCASION WITH SAME TYPE OF AIRCRAFT IN THE PAST. SUSPECT MFG. IS MAKING PART FROM SUBSTANDARD MATERI AL. THIS PROBLEM HAS JUST BEEN HAPPENING IN THE PREVIOUS YEAR. THIS PART WAS INSTALLED NEW ABOUT 350 HOUR PREVIOUSLY.( K) 1 L 7 1 3O 3 O A3SO 1E4 2001120300125 20011203 00125 SO 2001 12 3 2001FA0000565 2 20011112 G 7414 M3006 BEARING SLICK CESSNA 182 182Q 2072732 CE CONT O470 O470U 17026 SO MAGNETO FAILED B CS3R K NONE O OTHER IN INSP/MAINT 1 WP 17 6204N 99082637 18267796 PILOT REPORTED RIGHT MAGNETO INOPERATIVE ON RUNUP. REMOVED RIGHT MAGNETO FOUND VERY HAD TO TURN. DISASSEMBLED MAGNETO AND FOUND DRIVE END BEARING FAILED. 1 H 7 1 3O 3 O NT 3A13 E273 2001120300126 20011203 00126 SO 2001 12 3 2001FA0000566 2 20011116 G 7414 DISTRIBUTOR BLK SLICK BEECH 33 F33A 1151425 CE CONT O520 IO520B 17032 SO MAGNETO INOPERATIVE B VJ3R K NONE O OTHER IN INSP/MAINT 1 WP 07 5585Y 463 01042020 CE1389 820461R MAGNETO REMOVED FROM ENGINE FOR 500 HOUR INSPECTION IAW THE MM. REMOVED THE REAR COVER AND THE DISTRIBUTOR BLOCK FROM M AGNETO. DISTRIBUTOR BLOCK ASSEMBLY SENT TO MFG. FOR INSPECTION. NEW DISTRIBUTOR BLOCK ASSEMBLY INSTALLED IN MAGNETO.(K ) 1 L 7 1 3O 3 O 3A15 E5CE 2001120600139 20011206 00139 SO 2001 12 6 2001FA0000567 2 20011115 G 7414 DISTRIBUTOR BLK SLICK BEECH 33 F33A 1151425 CE CONT O520 IO520B 17032 SO MAGNETO INOPERATIVE B VJ3R K NONE O OTHER IN INSP/MAINT 1 WP 07 1569P 522 01040901 CE1300 820454R MAGNETO REMOVED FROM ENGINE FOR 500 HOUR INSPECTION IAW MM. REMOVED THE REAR COVER AND THE DISTRIBUTOR BLOCK FROM MAGNE TO. DISTRIBUTOR BLOCK ASSEMBLY INSTALLED IN MAGNETO.(K) 1 L 7 1 3O 3 O 3A15 E5CE 2001120600140 20011206 00140 SO 2001 12 6 2001FA0000568 2 20011115 G 7414 DISTRIBUTOR BLK SLICK BEECH 33 F33A 1151425 CE CONT O520 IO520B 17032 SO MAGNETO INOPERATIVE B VJ3R K NONE O OTHER IN INSP/MAINT 1 WP 07 4609M 504 00033035 CE772 820261R MAGNETO REMOVED FROM ENGINE FOR 500 HOUR INSPECTION IAW MM. REMOVED THE REAR COVER AND THE DISTRIBUTOR BLOCK FROM MAGNE TO. DISTRIBUTOR BLOCK ASSEMBLY SENT TO MFG. FOR INSPECTION. NEW DISTRIBUTOR BLOCK ASSEMBLY INSTALLED IN MAGNETO.(K) 1 L 7 1 3O 3 O 3A15 E5CE 2001120600141 20011206 00141 SO 2001 12 6 2001FA0000569 2 20011115 G 7414 DISTRIBUTOR BLK SLICK BEECH 33 F33A 1151425 CE CONT O520 IO520B 17032 SO MAGNETO INOPERATIVE B VJ3R K NONE O OTHER IN INSP/MAINT 1 WP 07 1569P 522 01040864 CE1300 820454R MAGNETO REMOVED FROM ENGINE FOR 500 HOUR INSPECTION IAW MM. REMOVED THE REAR COVER AND THE DISTRIBUTOR BLOCK FROM MAGNE TO. DISTRIBUTOR BLOCK ASSEMBLY INSTALLED IN MAGNETO. 1 L 7 1 3O 3 O 3A15 E5CE 2001120600142 20011206 00142 SO 2001 12 6 2001FA0000570 2 20011115 G 7414 DISTRIBUTOR BLK SLICK BEECH 33 F33A 1151425 CE CONT O520 IO520B 17032 SO MAGNETO INOPERATIVE B VJ3R K NONE O OTHER IN INSP/MAINT 1 WP 07 4609M 504 00033043 CE772 820261R MAGNETO REMOVED FROM ENGINE FOR 500 HOUR INSPECTION IAW MM. REMOVED THE REAR COVER AND THE DISTRIBUTOR BLOCK FROM MAGNE TO. DISTRIBUTOR BLOCK ASSEMBLY SENT TO MFG. FOR INSPECTION. NEW DISTRIBUTOR BLOCK ASSEMBLY INSTALLED IN MAGNETO.(K) 1 L 7 1 3O 3 O 3A15 E5CE 2001120600143 20011206 00143 CE 2001 12 6 2001FA0000571 1 20011116 G 5510 MS210783 NUT PLATE CESSNA 172 172R 2072401 CE LYC O360 IO360A1A 41514 EA HORZ STAB BROKEN D DF2S K NONE O OTHER IN INSP/MAINT 1 SW 15 869CP 2355 17280641 DURING 100 HOUR INSPECTION, TECHNICIAN FOUND LOWER ELEVATOR STOP NUTPLATE BROKEN AND FIBER LOCK PORTION OF PART SEPARATE D FROM THE REST OF NUTPLATE DETAIL REPEATED ELEVATOR CONTACT WITH STOP BOLT WHEN AIRCRAFT IS PARKED AND CONTROL LOCK IS IN, SUCH AS IN WINDY CONDITIONS.(K) 1 H 7 1 3O 3 O NT 3A12 1E10 2001120300127 20011203 00127 EA 2001 12 3 2001FA0000572 2 20011106 G 8520 77672 LIFTER BEECH 60 60 1153602 CE LYC O541 TIO541E1C4 41536 EA ENGINE SPALLED D K NONE O OTHER IN INSP/MAINT 1 WP 07 33LB 132 132 P74 L163859 UPON REMOVAL OF PUSH RODS AND PUSH ROD TUBES FOR RESEAL, THE LIFTERS WERE REMOVED FOR BLEEDING. THE LIFTERS WERE INSPEC TED AND WERE FOUND TO HAVE SEVERE SPALLING. MFG WAS NOTIFIED AND ENGINES ARE TO BE REMOVED AND SENT BACK FOR REPAIR. EN GINES HAVE 132.4 HRS TT. CAMSHAFT IS ALSO WORN. 1 L 7 2 3O 3 O A12CE E10EA 2001120300128 20011203 00128 EU 2001 12 3 2001FA0000573 2 20011023 G 8520 996920 BEARING AMTR AVDFLY AVIDFLYER GL ROTAX 277 ROTAX277 55555 EU ENGINE FAILED G O OTHER R PARTIAL RPM/PWR LOSS CR CRUISE 1 NM 08 94RS 260 260 3 6913440 ENGINE FAILED IN-FLIGHT DUE TO FAILURE OF CONNECTING ROD ROLLER BEARINGS ON CRANKSHAFT ASSEMBLY. CAUSE UNKNOWN. 1 H 7 1 3O 3 X EXPA1H71 EXPE3X 2001120600144 20011206 00144 EA 2001 12 6 2001FA0000576 2 20011126 G 8520 CRANKSHAFT CESSNA 206 206CESSNA 2073302 CE LYC O540 TIO540* 41532 EA ENGINE FAILED C O OTHER O OTHER NR NOT REPORTED 1 SO 11 919LL T20608174 L1044761A CONFIRMED BY ENGINE MANUFACTURER-ENGINE CRANKSHAFT FAILED AT NR 5 CRANKPIN. 1 H 7 1 3O 3 O A4CE E14EA 2001120600145 20011206 00145 EA 2001 12 6 2001FA0000577 2 20011114 G 7310 LW120980210 FUEL LINE CESSNA 182 182S 2072701 CE LYC O540 IO540AB1A5 EA ENGINE CHAFED B VDNR K NONE K FLUID LOSS IN INSP/MAINT 1 SW 09 931SJ 316 18280931 L2781648A DURING 100 HOUR INSPECTION, DISCOVERED NR2 CYLINDER FUEL INJECTION LINE LEAKING WHILE ACCOMPLISHING MFG SB. FUEL LINE S UPPORT CLAMP HAD BECOME LOOSE AND CAUSED LINE TO CONTACT NR2 CYLINDER FINS, WHICH WORE 6 GROOVES IN LINE. 1 H 7 1 3O 3 O NT 3A13 1E4 2001120600146 20011206 00146 CE 2001 12 6 2001FA0000578 1 20011115 G 5512 12326003 SKIN CESSNA 210 210D 2073414 CE CONT O520 IO520A 17032 SO HORIZ STAB DAMAGED D K NONE O OTHER IN INSP/MAINT 1 EA 13 210KE 1710 21058505 715920 DURING AN ANNUAL INSPECTION THE RIGHT INBOARD SKIN HAD EXCESSIVE OIL CANNING WHEN FLEXED. WHEN FAIRING, PN 12124265 AND 12124266 (RIGHT AND LEFT) WERE REMOVED, THE RIGHT UPPER SKIN SURFACE UNDER FAIRING WAS CHAFFED THROUGH 4 INCHES IN LENG TH THE LEFT SKIN IN SAME LOCATION WAS CHAFFED 50 PER CENT. .020 SKIN. REPLACED AFFECTED SKINS AND REMOVED SHARP EDGE O N FAIRING AND USED ANTI-CHAFE TAPE. 1 H 7 1 3O 3 O 3A21 E5CE 2001120600147 20011206 00147 CE 2001 12 6 2001FA0000579 1 20011115 G 5512 12326004 SKIN CESSNA 210 210D 2073414 CE CONT O520 IO520A 17032 SO HORIZ STAB DAMAGED D K NONE O OTHER IN INSP/MAINT 1 EA 13 210KE 1710 21058505 112413R DURING AN ANNUAL INSPECTION THE RIGHT INBOARD SKIN HAD EXCESSIVE OIL CANNING WHEN FLEXED. WHEN FAIRING, PN 12124265 AND PN 12124266 (RIGHT AND LEFT) WERE REMOVED, THE RIGHT UPPER SKIN SURFACE UNDER FAIRING WAS CHAFFED THROUGH 4 INCHES IN L ENGTH THE LEFT SKIN IN SAME LOCATION WAS CHAFFED 50 PER CENT. REPLACED AFFECTED SKINS AND REMOVED SHARP EDGE ON FAIRING AND USED ANTI-CHAFE TAPE. 1 H 7 1 3O 3 O 3A21 E5CE 2001121000110 20011210 00110 CE 2001 12 10 2001FA0000580 1 20011031 G 3411 S10711 PITOT LINE CESSNA 182 182S 2072701 CE PITOT/STATIC SYS BURNED D K NONE O OTHER IN INSP/MAINT 1 EA 25 9472F 296 18280201 PITOT HEAT INSULATION, BURN MARKS WERE FOUND ON PITOT PRESSURE LINE. CONDITION RESULTS FROM HAVING PLASTIC LINE CONNEC TED TO HEATED PITOT MAST. THE SB CORRECTS THIS BY ADDING PLASTIC SPIRAL WRAP TO LINE AND POWER WIRES AT THE PITOT MAST. THIS PREVENTS PITOT LINE FROM DIRECTLY CONTACTING HOT PARTS OF PITOT MAST, BUT SPIRAL WRAP INSULATION IS MADE OF SAME MATERIAL AS ORIGINAL PITOT LINE AND SUBJECT TO SAME HEAT DAMAGE. 1 H 7 1 3O NT 3A13 2001120600148 20011206 00148 CE 2001 12 6 2001FA0000581 1 20011103 G 8120 4664120004 BEARING CESSNA 414 414A 2075907 CE CONT O520 TSIO520* 17040 SO TURBOCHARGER DRAGGING D E ENGINE SHUTDOWN R PARTIAL RPM/PWR LOSS NR NOT REPORTED 1 EA 17 84DA 2278 414A0519 AIRCRAFT LANDED WITH LEFT ENGINE FEATHER AND SECURED. PILOT REPORTED LOW MANIFOLD PRESSURE. INSPECTION REVEALED LEFT T URBOCHARGER BEARINGS DRAGGING. REPLACED TURBOCHARGER WITH OVERHAUL UNIT. ENGINE OPERATIONALLY CHECKED OK. COMPONENT AG E SUSPECTED AS CAUSE BUT LOGBOOKS WERE UNAVAILABLE . TT 2278 1 L 7 2 3O 3 O A7CE E8CE 2001121000111 20011210 00111 SO 2001 12 10 2001FA0000582 1 20011114 G 2140 A2300475 REGULATOR PIPER PA31 PA31350 7103110 SO LYC O540 TIO540* 41532 EA CABIN HEATER LEAKING D K NONE K FLUID LOSS IN INSP/MAINT 1 SO 05 3581C 142 318052091 THE HEATER FUEL REGULATOR, WAS INSTALLED NEW, IN OUR AIRCRAFT. AD`S HAVE BEEN COMPLIED WITH. DURING ROUTINE HEATER INS PECTION AND CHECK, FOUND NEW TYPE REGULATOR SEEPING FUEL AROUND HOUSING SEAL. 1 L 7 2 3O 3 O A20SO E14EA 2001121000112 20011210 00112 WP 2001 12 10 2001FA0000583 1 20011005 G 2434 WIRE ELECTROSYS RYAN ST3 ST3KR 7830502 WP CONT O360 TSIO360KB 17025 SO ALTERNATOR MISSING B TZ3R K NONE W J INADEQUATE Q C WARNING INDICATION IN INSP/MAINT 1 WP 01 2022 9032694 1054 NEW EXCHANGE ALTERNATOR SUPPLIED. ALTERNATOR OUTPUT OK. PANEL INOPERATIVE LIGHT STAYS ILLUMINATED. INSPECTION OF ALT ERNATOR REVEALED MISSING LEAD WIRE FROM STATOR TO STATOR. ALT LIGHT TERMINAL ON ALTERNATOR. ALTERNATOR REQUIRES ADDITI ONAL LEAD WIRE FOR AIRCRAFT WITH PANEL DOWN OPERATIVE LIGHT CONNECTED TO STATOR TERMINAL ON ALTERNATOR. 1 L 7 1 3R 3 O A749 E9CE 2001121000113 20011210 00113 EA 2001 12 10 2001FA0000584 2 20011114 G 8530 LW12429 CYLINDER PIPER PA25 PA25 7102502 SO LYC O540 TIO540C1A 41532 EA ENGINE DELAMINATED B YYBR K NONE O OTHER IN INSP/MAINT 1 GL 03 L529661A LYCOMING CYLINDER PN LW12429 WITH A CERMINILL COATING FROM ECI DELAMINATED. THE AREA WAS ABOUT 1.5 INCHES IN LENGTH AND ABOUT .250 WIDE AT THE TOP OF THE CYLINDER BORE, ABOVE THE PISTON RING TRAVEL. THE PROBABLE CAUSE WAS CORROSION UNDER THE CERMINILL COATING. THIS IS A PLATING DEFECT. THE ECI BATCH NUMBER ON THE CYLINDERS ARE 46463-3, 46463-10, 40739-3D, AND 40739-6D. 1 L 7 1 3O 3 O 2A10 E14EA 2001121000114 20011210 00114 SO 2001 12 10 2001FA0000585 1 20011124 G 5102 GL0115721688 FUEL LINE BALWKS FIRE FIREFLY715 1050518 SO FUEL SYSTEM LEAKING B F65R O OTHER W INADEQUATE Q C NR NOT REPORTED 1 SW 15 3214V 110 F7912 THIS SET OF FUEL HOSES WERE OBTAINED FROM THE HOLDER OF A PMA. THEY WERE INSTALLED IN MAY. THE HOSE WAS FOUND TO BE LEA KING AT THE CRIMP CONNECTION AT THE END OF THE HOSE. THE LEAK DOES NOT APPEAR TO BE CAUSED BY MISHANDLING, BUT BY A POO R CRIMP JOB. THIS IS THE SECOND HOSE FROM THIS SET THAT HAVE STARTED LEAKING FROM THE SAME LOCATION. 1 B 0 0 A14SO 2001121000115 20011210 00115 CE 2001 12 10 2001FA0000586 1 20010430 G 2720 04115261 MOUNT CESSNA 150 152 2071835 CE LYC O235 O235* 41505 EA RUDDER PEDAL CRACKED D O OTHER O OTHER NR NOT REPORTED 1 NM 17 49792 8393 15283517 PILOTS RIGHT HAND LOW RUDDER PEDAL ASSEMBLY MOUNT CRACKED AROUND WELD CAUSING ON GROUND LOSS OF DIRECTIONAL CONTROL AND MADE BRAKING DIFFICULT. 1 H 7 1 3O 3 O NT 3A19 E223 2001121000116 20011210 00116 EA 2001 12 10 2001FA0000587 2 20011102 G 8520 69373 BEARING CESSNA 150 152 2071835 CE LYC O235 O235L2C 41505 EA CONNECTING ROD DEBONDED D K NONE O OTHER IN INSP/MAINT 1 NM 07 714VV 1076 15279475 L1843715 PLATING ON BEARING UNBONDED FORM BACKING (ROD SIDE NOT THE CAP SIDE) DATE CODE ON BACK OF BEARING IS 200. 1 H 7 1 3O 3 O NT 3A19 E223 2001121000117 20011210 00117 SO 2001 12 10 2001FA0000588 1 20011120 G 2710 62701124 CONTROL CABLE PIPER PA28 PA28181 7102807 SO AILERON WORN B UC2R K NONE O OTHER IN INSP/MAINT 1 GL 19 41487 2125 2843179 DURING A ROUTINE INSPECTION, SUBSTANTIAL WEAR WAS FOUND WHERE THE AILERON BALANCE CABLE RUNS THROUGH THE RIGHT SIDE OF T HE FUSELAGE. CABLE WEAR WAS PROBABLY CAUSED BY IMPROPER CABLE ALIGNMENT DURING ASSEMBLY BY MFG. THIS IS THE SECOND OCC URRENCE OF THIS TYPE OF DEFECT FOUND IN OUR FLEET.(K) 1 L 7 1 3O 2A13 2001121000118 20011210 00118 SO 2001 12 10 2001FA0000589 2 20011126 G 8520 642396 CRANKSHAFT CESSNA 414 414A 2075907 CE CONT O520 TSIO520NB 17040 SO ENGINE BROKEN B VA1R O OTHER O OTHER NR NOT REPORTED 1 SW 19 717BD 2059 414A0337 521140 CRANKSHAFT BROKE IN 3 SECTIONS, HAD 595.9 SMOH. NO SIGNS OF OIL STARVATION. 1 L 7 2 3O 3 O A7CE E8CE 2001121000119 20011210 00119 NE 2001 12 10 2001FA0000590 1 20011017 G 7922 NUT LAKEAC LAKE 250LAKE 5110322 NE LYC O540 TIO540* 41532 EA VERNATHERM MISSING D K NONE O OTHER IN INSP/MAINT 1 SO 15 59CA 616 129 L29861A REMOVED VERNATHERM TO COMPLY WITH MFG SB (CHECK NUT TIGHTNESS). WHEN VALVE REMOVED, THE NUT WAS MISSING. AFTER A THROU GH SEARCH THE NUT WAS FOUND IN THE INBOARD HOSE, OIL COOLER END OF THE COPILOT SIDE OF OIL COOLER (2 OIL COOLER ARE ON THIS INSTALLATION).(K) 1 H 7 1 3O 3 O NC 1A13 E14EA 2001121100011 20011211 00011 GL 2001 12 11 2001FA0000591 3 20010611 G 6111 8381010 CLAMP HARTZL HCA2 HCA2MVK2 GL PROPELLER CRACKED B ME4R K NONE O OTHER IN INSP/MAINT 1 SO 19 1928 H1766 PROPELLER RECEIVED FOR STANDARD OVERHAUL, DUE TO TIME IAW MFG SL. (TSO)1982.9. AFTER PROPELLER DISASSEMBLY, THE FOLLOWI NG COMPONENTS ARE CONDEMNED: BLADE (PN MV8433-4, SN 36637R) DAMAGED IN COLD ROLLED AREA DUE TO CLAMPS. BLADE (PN MV8433 -4, SN C85096R) DAMAGED IN COLD ROLLED AREA DUE TO CLAMPS. CLAMP (PN 838-1010, SN 44) CRACKED THROUGH THE INNER CLAMP AT TACHMENT HOLE. CLAMP (PN 838-1010, SN 57) CRACKED THROUGH INNER CLAMP ATTACH. HOLE. PILOT INDICATED NO ABNORMAL OP. 5 C P24EA 2001121100012 20011211 00012 GL 2001 12 11 2001FA0000592 3 20010611 G 6111 8381010 CLAMP HARTZL HCA2 HCA2MVK2 GL PROPELLER CRACKED B ME4R K NONE O OTHER IN INSP/MAINT 1 SO 19 1928 H1766 PROPELLER RECEIVED FOR STANDARD OVERHAUL, DUE TO TIME. (TSO) 1982.9. AFTER PROPELLER DISASSEMBLY, THE FOLLOWING COMPONE NTS ARE CONDEMNED: BLADE (PN MV8433-4, SN 36637R) DAMAGED IN COLD ROLLED AREA DUE TO CLAMPS. BLADE (PN MV8433-4, SN C85 096R) DAMAGED IN COLD ROLLED AREA DUE TO CLAMPS. CLAMP (PN 838-1010, SN44) CRACKED THROUGH THE INNER CLAMP ATTACHMENT HO LE. CLAMP (PN 838-1010, SN57) CRACKED THROUGH INNER CLAMP ATTACHMENT HOLE. PILOT INDICATED NO ABNORMAL OP. 5 C P24EA 2001121000120 20011210 00120 CE 2001 12 10 2001FA0000593 1 20011121 G 3246 WHEEL CESSNA 182 R182 2072734 CE LYC O540 O540* 41532 EA LANDING GEAR CRACKED B K NONE O OTHER IN INSP/MAINT 1 EA 07 9979C R18200495 CRACK, 1.25 INCHES IN LENGTH, EMANATING FROM BOLT HOLE. 1 H 7 1 3O 3 O RT 3A13 E295 2001121000121 20011210 00121 SO 2001 12 10 2001FA0000594 1 20010724 G 2820 1442800 GASCOLATOR PIPER PA28 PA28* SO LYC O360 O360* 41514 EA ENGINE CRACKED G O OTHER A FLAME/FIRE TX TAXI/GRND HDL 1 WP 07 DURING ENGINE START, AN INDUCTION FIRE STARTED WHEN THE CARBURETOR BACKFIRED. THE FIRE COULD NOT BE EXTINGUISHED AND DE STROYED THE AIRCRAFT. DURING AN INVESTIGATION THE GASCOLATOR COVER WAS FOUND CRACKED. IT APPEARS THE FUEL LEAKING FROM THE COVER APPEARS TO HAVE FED THE FIRE THAT DESTROYED THE AIRCRAFT. 1 L 7 1 3O 3 O 2A13 E286 2001121000122 20011210 00122 CE 2001 12 10 2001FA0000595 1 20010710 G 3213 BUSHING CESSNA CESSNA 310 310J 2074226 CE CONT O470 O470M 17026 SO TORQUE LINK SEPARATED D O OTHER O OTHER TO TAKEOFF 1 SW 17 RIGHT MAIN LANDING GEAR UPPER AND LOWER TORQUE LINKS BECAME DISCONNECTED FROM EACH OTHER DURING TAKEOFF ROLL. IT APPEAR S THAT A PRESSED IN BUSHING, SEPARATED FROM THE LOWER TORQUE LINK ALLOWING THE BOLT HEAD AND WASHER TO PASS THROUGH THE ENLARGED HOLE NORMALLY OCCUPIED BY THE BUSHING. CATALOG INDICATES THAT A SPECIAL WASHER IS REQUIRED UNDER THE BOLT HEAD . THE SPECIAL WASHER HAS A LARGER OUTSIDE DIAMETER THAN THE STANDARD AN WASHER WHICH WAS FOUND INSTALLED. MM INSTRUCTI ON DO NOT REQUIRE INSTALLATION OF SPECIAL WASHER. 1 L 7 2 3O 3 O 3A10 E273 2001121000123 20011210 00123 EU 2001 12 10 2001FA0000597 1 20011120 G 3230 7733690395 RELAY SOCATA TB20 TB20TRINIDAD 8680695 EU LYC O540 IO540* 41532 EA LANDING GEAR FAILED G O OTHER O OTHER NR NOT REPORTED 1 WP 25 1871S 336 1871 LANDING GEAR FAILED TO EXTEND. CIRCUIT BREAKER FOUND OPEN. INVESTIGATION FOUND LANDING GEAR UP, RELAY POINTS WELDED CL OSED. 1 L 7 1 3O 3 O RT A51EU 1E4 2001121000124 20011210 00124 CE 2001 12 10 2001FA0000598 1 20010817 G 3260 LENS BEECH 200 200BEECH 1152920 CE PWA PT6 PT6A60A 52043 NE INSTRUMENT PNL LOOSE D L ABORTED APPROACH N FALSE WARNING AP APPROACH 1 GL 17 339AJ BB339 PILOT REPORTED THAT UPON SETUP FOR APPROACH AND GEAR DOWN SELECTION WAS MADE WITH GEAR SWITCH. THAT AN INDICATION FOR B OTH MAIN GEAR WERE DOWN AND LOCKED, BUT NO INDICATION OF THE NOSE GEAR DOWN AND LOCKED. AIRCRAFT DIVERTED AND VERIFIED WITH ATC THAT NOSE GEAR WAS DOWN. CAUSE: NOSE GEAR GREEN LAMP SOCKET LENS CAME LOOSE. AIRCRAFT LANDED INCIDENT FREE. PLACED AIRCRAFT ON JACKS, RECHECKED EMERGENCY GEAR EXTENSION OPERATION AND RIGGING PER MM. PERFORMED NORMAL EXTENSION A ND RETRACTION. TIGHTENED NOSE LAMP LENS FUNCTIONAL TEST OF ALL WORK PERFORMED CHECKS, OK. 1 L 7 2 4T 4 T A24CE E4EA 2001121000125 20011210 00125 CE 2001 12 10 2001FA0000599 1 20011023 G 5521 043200121 SPAR CESSNA 150 152 2071835 CE LYC O235 O235* 41505 EA ELEVATOR CRACKED D K NONE O OTHER IN INSP/MAINT 1 WP 07 94584 6515 15285738 REMOVED ELEVATOR TO REPAIR WORN OUTBOARD HINGE BUSHINGS, AFTER ELEVATOR WAS REMOVED FOUND THE ELEVATOR SPAR CRACKED UNDE R THE OUTBOARD HINGE WHERE IT ATTACHES TO THE SPAR, REPLACED SPAR WITH NEW. 1 H 7 1 3O 3 O NT 3A19 E223 2001121000126 20011210 00126 SO 2001 12 10 2001FA0000600 1 20010817 G 3246 16106900 WHEEL PIPER PA23 PA23250 7102308 SO LYC O540 TIO540* 41532 EA LT MLG CRACKED D K NONE O OTHER IN INSP/MAINT 1 EA 21 68SE 273780 DURING ANNUAL INSPECTION, FOUND LEFT INNER MAIN WHEEL HALF CRACKED IN THE BEAD AREA ORIGINATING FROM BRAKE ATTACHMENT PL ATE RIVETS. 1 L 7 2 3O 3 O 1A10 E14EA 2001121000134 20011210 00134 EA 2001 12 10 2001FA0000601 2 20011126 G 7414 IO68256013 GEAR PIPER PA32 PA32R300 7103213 SO LYC O540 IO540K1A5 41532 EA MAGNETO BROKEN D K NONE O OTHER IN INSP/MAINT 1 AL 01 200HM 481 32R7680025 DURING INSPECTION FOUND A DISTRIBUTOR GEAR TOOTH BROKEN AND LAYING IN MAG CAP. THIS IS AN ONGOING PROBLEM. THIS MAG HA S PLASTIC GEARS AND HAS BEEN FOUND IN THIS CONDITION ON NUMEROUS MAGNETOS OF THIS TYPE IN THE PAST. 1 L 7 1 3O 3 O A3SO 1E4 2001121000135 20011210 00135 SO 2001 12 10 2001FA0000602 1 20011116 G 5280 3807601 BRACE PIPER PA32 PA32R300 7103213 SO LYC O540 TIO540* 41532 EA NLG DOOR BROKEN D K NONE O OTHER IN INSP/MAINT 1 AL 01 40449 473 32R7780519 INSPECTION FOUND RIGHT NOSE GEAR DOOR BRACE BROKEN AT REAR ATTACH POINT. ALSO CRACKED OUT FROM RIVETS AT AFT END OF BRA CE. 1 L 7 1 3O 3 O A3SO E14EA 2001121000136 20011210 00136 SO 2001 12 10 2001FA0000603 1 20011126 G 5280 3807601 BRACE PIPER PA32 PA32R300 7103213 SO LYC O540 IO540* 41532 EA NLG DOOR BROKEN D K NONE O OTHER IN INSP/MAINT 1 AL 01 200HM 481 32R7680025 INSPECTION FOUND RIGHT NOSE GEAR DOOR BRACE CRACKED AT REAR ATTACH POINT. THIS IS A COMMON PROBLEM FOUND ON THIS MODEL AIRCRAFT. 1 L 7 1 3O 3 O A3SO 1E4 2002012500039 20020125 00039 SO 2002 1 25 2001FA0000604 2 20011205 G 8530 501867 WASHER MOONEY M20 M20K 5870220 SW CONT O360 TSIO360GB 17025 SO ENGINE CYLINDER MISSING D K NONE W INADEQUATE Q C IN INSP/MAINT 1 SW 09 231ND 250207 309202 WHILE TROUBLESHOOTING A FUEL FLOW PROBLEM, AN OIL LEAK MANIFESTED AT NR 6 EXHAUST ROCKER COVER. WHEN COVER REMOVED, THE TAB WASHERS WERE FOUND MISSING FROM THE ROCKER SHAFT STUDS. ALL COVERS WERE REMOVED AND THE SAME CONDITION FOUND. A CHEC K OF MAINTENANCE RECORDS REVALED A "TOP OVERHAUL" WAS ACCOMPLISHED 14.7 HOURS PREVIOUS. SUBMITTER SUSPECTS WASHERS WERE LEFT OFF DURING REASSEMBLY. THE TAB WASHERS SERVE TO SAFETY THE ROCKER SHAFT RETAINING NUTS. LOSS OF THE RETAINING NUTS COULD RESULT IN CATASTROPHIC ENGINE FAILURE AND UNPLANNED TERMINATION OF FLIGHT. SUBMITTER FAILS TO COMPREHEND OVERLOOKI NG THIS CRITICAL PART. INSTALLED 501867 WASHERS ON ALL ROCKER SHAFT STUDS AND SECURED. 1 L 7 1 3O 3 O 2A3 E9CE 2002012500040 20020125 00040 SO 2002 1 25 2001FA0000605 1 20011205 G 7120 3872902 MOUNT PIPER PA32 PA32R301 7103218 SO ENGINE CRACKED B K NONE O OTHER IN INSP/MAINT 1 SO 05 4369M 1877 32R8413022 ENGINE TRUSS WELD ASSY FOUND CRACKED AT STEERING ARM ATTACH POINT 1 L 7 1 3O A3SO 2002012500041 20020125 00041 SO 2002 1 25 2001FA0000606 1 20011205 G 7120 3872919 MOUNT PIPER PA32 PA32R301 7103218 SO ENGINE CRACKED B K NONE O OTHER IN INSP/MAINT 1 SO 05 395HP 873 3213085 ENGINE TRUSS WELD ASSEMBY FOUND CRACKED AT STEERING ARM ATTACH POINT. 1 L 7 1 3O A3SO 2002012500043 20020125 00043 SO 2002 1 25 2001FA0000607 2 20011114 G 7414 6310 MAGNETO CESSNA 182 182E 2072712 CE CONT O470 O470R 17026 SO RT & LT FAILED C A UNSCHED LANDING R J PARTIAL RPM/PWR LOSS WARNING INDICATION CR CRUISE 1 SO 11 3390Y 231 18254390 ENGINE RAN A LITTLE ROUGH WHEN STARTED. RAN SMOOTHLY AFTER WARMING UP. A 45 MIN FLIGHT WAS MADE AND THEN ENGINE WAS SHU T DOWN. THE ENGINE STARTED AGAIN WITH NO PROBLEM. ABOUT 45 MINUTES INTO THE NEXT LEG, THE ENGINE BEGAN RUNNING ROUGH A ND MISSING. INITIALLY, CARBURATOR ICE WAS SUSPECTED AND CARB HEAT WAS APPLIED. AFTER ABOUT 15 MIN OF FULL CARB HEAT, T HE ENGINE APPEARED TO RUN SMOOTHLY. RETURNED TO HOME AIPORT (30 MIN) AND LANDED WITH NO PROBLEM. CARB ICE WAS NOT EXP ECTED AS THE HUMIDITY WAS LOW (20 PERCENT). ANOTHER SOURCE FOR THE ENGINE ROUGHNESS WAS LOOKED FOR. IT WAS DISCOVERED THAT ENGINE WOULD NOT START. IGNITION WAS CHECKED AND IT WAS DISCOVERED THE BOTH MAGNETOS IMPULSE COUPLINGS HAD FAILED 1 H 7 1 3O 3 O NT 3A13 E273 2002012500046 20020125 00046 EU 2002 1 25 2001FA0000608 1 20011206 G 2820 L24266701320000 SUPPORT ZLIN 242 Z242L 9970204 EU LYC O360 AEIO360A1B6 41514 EA FUEL SERVO BROKEN B A UNSCHED LANDING F FLT CONT AFFECTED CR CRUISE 1 SO 15 147FS 1135 0735 L2842451A EYE SCREW, IS A SUPPORT STRUT WHICH ATTACHES TO THE EXHUST STACK AT ONE END AND THE FUEL SERVO TO ENGINE SUMP ATTACHMENT STUDS AT THE OTHER END. THE STRUT FELL BETWEEN THE THROTTLE ARM AND SUMP. THIS PREVENTED THE ENGINE FROM BEING ABLE TO REDUCE POWER BELOW 1500 RPM. CONDITION REPORTED BY PILOT AND FOUND BY MECHANIC. SUBMITTER REPLACED PART AND SECURED STRU T AT AN ADDITIONAL POINT IN CASE THE REPLACEMANT PART BREAKS AGAIN. THIS ADJUSTMENT WOULD PREVENT THE STRUT FROM FALLING INTO THE CONTROL LINKAGE IF THE PROBLEM REOCCURES. 1 L 7 1 3O 3 O 0 A76EU 1E10 2002012500047 20020125 00047 GL 2002 1 25 2001FA0000609 1 20011016 G 3201 BRACKET CIRRUS SR SR20 05628AJ GL MLG FAIRING BROKEN B ESMR K NONE O OTHER IN INSP/MAINT 1 SO 11 155CD 264 1058 BOTH LEFT AND RIGHT MAIN LANDING GEAR INBOUARD FAIRING BRACKETS BROKEN, CAUSING FAIRING TO BE VERY LOOSE. GAUGE OF META L IS TOO THIN FOR THIS HIGH VIBRATION APPLICATION. 1 L 7 1 3O NT A00009CH 2002012500049 20020125 00049 GL 2002 1 25 2001FA0000610 1 20011016 G 6120 50597001 BEARING CIRRUS SR SR20 05628AJ GL HARTZL HCC3Y PHCC3YF1 GL PROP GOVERNOR BROKEN B ESMR K NONE O OTHER IN INSP/MAINT 1 SO 11 155CD 264 1058 PROPELLER GOVERNOR CABLE EXTREMELY STIFF WITH POSSIBLE BROKEN WIRE INSIDE OUTER SHROUD. THIS CAUSED THE THROTTLE LEVER BEARING, WHERE THE ROD END FOR THE PROP GOVERNOR CABLE ATTACHES TO THE THROTTLE LEVER, TO BREAK APART. THE STRENGTH OF THE BEARING FOR THIS APPLICATION IS QUESTIONABLE. THE THROTTLE LEVER PN 10007-001 ALSO HAD TO BE REPLACED. 1 L 7 1 3O NT A00009CH 5 C P25EA 2002012500051 20020125 00051 CE 2002 1 25 2001FA0000611 1 20011010 G 2400 S2800275 CONNECTOR CESSNA 172 172R 2072401 CE J BOX INADEQUATE B ESMR K NONE O OTHER IN INSP/MAINT 1 SO 11 109PH 1411 17280802 CONNECTOR PB017, PN: S2800-275, WHICH ATTACHES SHIP WIRING TO J2 OF POWER JUCTION BOX MC01-2A, HAD INADEQUATE CRIMPS OF BOTH WIRE ENDS ATTACHING WIRES TO SOCKETS. SOCKET "A" HAD AN OPEN CIRCUIT WHICH CAUSED LOSS OF BUSS NR 2 H1014. WHEN PULLED ON, THE WIRES EASILY CAME OUT OF THE CONNECTOR. CORRECTIVE ACTION WAS TO CRIMP & SOLDER THE CONNECTOR. 1 H 7 1 3O NT 3A12 2002012500056 20020125 00056 CE 2002 1 25 2001FA0000612 1 20011123 G 3240 BRAKE ASSY CESSNA 188 A188B 2073005 CE MLG MALFUNCTIONED G K NONE O OTHER TX TAXI/GRND HDL 1 SW 01 9541J 18803819T THE PILOT STARTED THE AIRCRAFT ENGINE, THE AIRCRAFT STARTED TO ROLL, AT WHICH TIME THE PILOT APPLIED THE BRAKES. THE L EFT BRAKE WAS OPERATIONAL BUT THE RIGHT WAS FLAT. THIS CAUSED THE AIRCRAFT TO SWERVE TO THE LEFT HITTING A CESSNA CARAVA N DAMAGING BOTH AIRCRAFT. THE BRAKE SYSTEM WAS INSPECTED, RESERVOIR FOUND TO BE FULL, NO LEAKS FOUND. SUSPECT AIR IN TH E BRAKE SYSTEM. 1 L 7 1 3O A9CE 2002012500064 20020125 00064 2002 1 25 2001FA0000614 4 20011124 G 3120 S17111 PRESSURE SWITCH CESSNA 172 172N 2072434 CE LYC O320 O320H2AD 41508 EA MCAULY 1C160 1C160DTM GL FUEL SYSTEM LEAKING D K NONE K FLUID LOSS IN INSP/MAINT 1 EA 21 5444J 5595 17273798 RL96576T 731908 ON ANNUAL INSPECTION FOUND OIL DRIPPING ON RIGHT SIDE OF AFT FIREWALL IN CABIN. TRACED TO LEAKING HOUR METER OIL PRESSU RE SWITCH. SWITCH WAS LEAKING INTERNALLY. REPLACED SWITCH. 1 H 7 1 3O 3 O NT 3A12 E274 5 N P910 2002012500066 20020125 00066 SO 2002 1 25 2001FA0000615 1 20011127 G 5750 6270114 CONTROL CABLE PIPER PA28 PA28140 7102802 SO TE FLAPS CORRODED D K NONE O OTHER IN INSP/MAINT 1 EA 23 2821855 NEW FLAP CABLE (62701-14) ORDERED TO REPLACE EXISTING FLAP CABLE THAT CORRODED ON MS21260 END FITTING WAS ALSO FOUND TO BE PITTED AND CORRODED. 1 L 7 1 3O 2A13 2002012500068 20020125 00068 SO 2002 1 25 2001FA0000616 1 20011129 G 5330 PANEL GULSTM G1159 GIV 3980115 SO FUSELAGE CRACKED B K NONE O OTHER IN INSP/MAINT 1 SO 11 464QS 1264 PANEL (107-CLB-5) LOCATED ON THE LOWER PORTION OF THE FUSELAGE PRESSURE VESSEL AFT OF THE MAIN WHEEL WELL CRACKING AROUN D A VHF ANTENNA MOUNTING NUTPLATE ATTACHED TO THE PANEL. 2 L 7 2 4F RT A12EA 2002012500069 20020125 00069 CE 2002 1 25 2001FA0000617 1 20011130 G 2121 09040022 FAN CESSNA 425 425 2076018 CE COCKPIT FLOOR FAILED B O OTHER O OTHER CR CRUISE 1 GL 09 5PP 30 0198 AIRCRAFT RETURNED FROM FLIGHT WITH CABIN BLOWER OPERATING BUT NOT MOVING ANY AIR. GAINED ACCESS TO BLOWER ASSEMBLY UNDE R CO-PILOT FLOOR. FOUND ALL FAN BLADES TO BE BROKEN OFF. THIS IS THE SECOND TIME THIS HAS HAPPENED IN LESS THAN TWO MO NTHS. CHECKED MOTOR FOR SECURITY AND LOOSENESS, CHECKED GOOD. CHECKED FAN HUB FOR SECURITY AND LOOSENESS ON MOTOR SHAF T AND FOUND THAT IT WAS TIGHT. INSTALLING TECHNICIAN SAID THAT HE SPECIFICALLY CHECKED FOR BLADE CLEARANCE AROUND HOUSI NG WHEN THIS FAN WAS INSTALLED AND IT WAS FINE. HIGHLY SUSPECT DEFECTIVE FAN BLADE AT MANUFACTURE. RECOVERED ALL BROKE N BLADES AND INSPECTED. FOUND ONE WITH WHAT APPEARED TO BE A CLEAN BREAK AT BASE. SUSPECT THAT ONE DEFECTIVE BLADE BRO 1 L 7 2 3T RT A7CE 2002012500072 20020125 00072 CE 2002 1 25 2001FA0000618 1 20011130 G 5510 17052 BRACKET PIPER PA23 PA23150 7102303 CE HORIZONTAL STAB CRACKED D K NONE O OTHER IN INSP/MAINT 1 NM 09 AFTER REMOVING THE PAINT FROM THE ELEVATOR HINGE BRACKETS, DISCOVERED THAT BOTH ELEVATOR HINGE BRACKETS ON THE RIGHT SID E OF THE HORIZONTAL STABILIZER WERE CRACKED THROUGH THE BEARING BORE BOSS, BETWEEN THE BORE AND THE OUTER EDGE OF THE BR ACKET. THE CAUSE OF THE CRACK IS UNKNOWN. 1 L 7 2 3O RT 1A10 2002012500078 20020125 00078 SO 2002 1 25 2001FA0000620 1 20011203 G 3234 CONTROL HANDLE EMB 120 EMB120 3260201 SO MLG FAILED C O OTHER O OTHER NR NOT REPORTED 1 SW 99 LANDING GEAR CONTROL LEVER FAILURE. 2 L 7 2 4T RT A31SO 2002012500087 20020125 00087 2002 1 25 2001FA0000621 4 20011203 G 2210 065001790100 ROLL SERVO BEECH 58 58 1152740 CE AUTO PILOT MALFUNCTIONED C O OTHER F FLT CONT AFFECTED NR NOT REPORTED 1 SO 05 378 378 TH1947 OPERATOR THAT ROLL CONTROL BECAME RESTRICTED AND DIFFICULT DURING FLIGHT. INVESTIGATION REVEALED THAT THE PRIMARY ROLL S ERVO WAS FOUND TO BE CAUSING RESTRICTION TO CAPSTAN. THIS SERVO WAS REMOVED AND HAS AUDIBLE SOUND OF OBJECTS FLOATING LO OSE INTERNALLY. 1 L 7 2 3O 3A16 2002012500088 20020125 00088 SW 2002 1 25 2001FA0000622 1 20011204 G 2820 LINE MOONEY M20 M20J 5870219 SW FUEL SYSTEM LEAKING C K NONE K FLUID LOSS IN INSP/MAINT 1 EA 21 MOONEY 201 M20J: OWNER REPORTED LOW FUEL PRESSURE. FOUND AEROQUIP LINE LEAKING THROUGH BODY OF INNER TUBE STOCK. THIS LINE HAS A STAINLESS STEEL BRAID COVERING FULL LENGTH. HOSE HAD A CURE DATE 3RD QUARTER 1995 WITH MANUFACTURED DATE JAN 1998. HOSE IS CONNECTED TO FUEL INJECTOR AND FUEL PRESSURE SENDER. HOSE WAS LEAKING SUBSTANCIAL AMOUNTS OF FUEL ABOVE EX HAUST SYSTEM AND ENGINE OPERATION WAS NOT AFFECTED. 1 L 7 1 3O 2A3 2002012500089 20020125 00089 2002 1 25 2001FA0000623 4 20011203 G 2210 065001790100 ROLL SERVO AMTR KITFOX KITFOXIV 05620EP GL AUTO PILOT MALFUNCTIONED C A UNSCHED LANDING F FLT CONT AFFECTED CR CRUISE 1 NM 11 316R 378 OPEREATOR ENCOUTERED RESTRICTED ROLL AUTHORITY. PRIMARY AP SERVO WAS FOUND TO BE CAUSING RESTICTED CAPSTAN MOVEMENT. SOU NDS LIKE LOOSE PARTS AR FLOATING AROUND INSIDE SERVO BODY 1 H 7 1 3I NC EXPA 2001121000137 20011210 00137 SO 2001 12 10 2001FA0000629 1 20011116 G 5280 3807601 BRACE PIPER PA32 PA32R300 7103213 SO LYC O540 IO540* 41532 EA NLG DOOR BROKEN D K NONE O OTHER IN INSP/MAINT 1 AL 01 200HM 32R7680025 INSPECTION FOUND RIGHT NOSE GEAR DOOR BRACE BROKEN AT REAR ATTACH POINT. ALSO CRACKED OUT FROM RIVETS AT AFT END OF BRA CE. 1 L 7 1 3O 3 O A3SO 1E4 2001121000138 20011210 00138 SO 2001 12 10 2001FA0000630 1 20011116 G 5280 3807601 BRACE PIPER PA32 PA32R300 7103213 SO LYC O540 IO540* 41532 EA NLG DOOR BROKEN D K NONE O OTHER IN INSP/MAINT 1 AL 01 97CR 1075 32R7780078 INSPECTION FOUND RIGHT NOSE GEAR DOOR BRACE BROKEN AT REAR ATTACH POINT. ALSO CRACKED OUT FROM RIVETS AT AFT END OF BRA CE. 1 L 7 1 3O 3 O A3SO 1E4 2001121000139 20011210 00139 SO 2001 12 10 2001FA0000631 1 20011116 G 5280 3807601 BRACE PIPER PA32 PA32R300 7103213 SO LYC O540 TIO540* 41532 EA NLG DOOR BROKEN D K NONE O OTHER IN INSP/MAINT 1 AL 01 8506F 97 32R7780107 INSPECTION FOUND RIGHT NOSE GEAR DOOR BRACE BROKEN AT REAR ATTACH POINT. ALSO CRACKED OUT FROM RIVETS AT AFT END OF BRA CE. 1 L 7 1 3O 3 O A3SO E14EA 2001121000140 20011210 00140 SO 2001 12 10 2001FA0000632 1 20011116 G 5280 3807601 BRACE PIPER PA32 PA32R300 7103213 SO LYC O540 TIO540* 41532 EA NLG DOOR BROKEN D K NONE O OTHER IN INSP/MAINT 1 AL 01 8506F 297 32R7780107 INSPECTION FOUND RIGHT NOSE GEAR DOOR BRACE AT REAR ATTACH POINT. ALSO CRACKED OUT FROM RIVETS AT AFT END OF BRACE. 1 L 7 1 3O 3 O A3SO E14EA 2001121000141 20011210 00141 SO 2001 12 10 2001FA0000633 1 20011116 G 5280 3807601 BRACE PIPER PA32 PA32R300 7103213 SO LYC O540 TIO540* 41532 EA NLG DOOR BROKEN D K NONE O OTHER IN INSP/MAINT 1 AL 01 8506F 93 32R7780107 INSPECTION FOUND RIGHT NOSE GEAR DOOR BRACE BROKEN AT REAR ATTACH POINT. ALSO CRACKED OUT FROM RIVETS AT AFT END OF BRA CE. 1 L 7 1 3O 3 O A3SO E14EA 2001121000142 20011210 00142 SO 2001 12 10 2001FA0000634 1 20011116 G 5280 3807601 BRACE PIPER PA32 PA32R300 7103213 SO NLG DOOR BROKEN D K NONE O OTHER IN INSP/MAINT 1 AL 01 4352F 369 32R7680441 INSPECTION FOUND RIGHT NOSE GEAR DOOR BRACE BROKEN AT REAR ATTACH POINT. ALSO CRACKED OUT FROM RIVETS AT AFT END OF BRA CE. 1 L 7 1 3O A3SO 2001121000143 20011210 00143 SO 2001 12 10 2001FA0000635 1 20011116 G 5280 3807601 BRACE PIPER PA32 PA32R300 7103213 SO NLG DOOR BROKEN D K NONE O OTHER IN INSP/MAINT 1 AL 01 4352F 103 32R7680441 INSPECTION FOUND RIGHT NOSE GEAR DOOR BRACE BROKEN AT REAR ATTACH POINT. ALSO CRACKED OUT FROM RIVETS AT AFT END OF BRA CE. 1 L 7 1 3O A3SO 2001121000144 20011210 00144 SO 2001 12 10 2001FA0000636 1 20011116 G 5280 3807601 BRACE PIPER PA32 PA32R300 7103213 SO NLG DOOR BROKEN D K NONE O OTHER IN INSP/MAINT 1 AL 01 4352F 321 32R7680441 INSPECTION FOUND RIGHT NOSE GEAR DOOR BRACE BROKEN AT REAR ATTACH POINT. ALSO CRACKED OUT FROM RIVETS AT AFT END OF BRA CE. 1 L 7 1 3O A3SO 2001121000145 20011210 00145 SO 2001 12 10 2001FA0000637 1 20011116 G 5280 3807601 BRACE PIPER PA32 PA32R300 7103213 SO LYC O540 TIO540* 41532 EA NLG DOOR BROKEN D K NONE O OTHER IN INSP/MAINT 1 AL 01 40449 153 32R7780519 INSPECTION FOUND RIGHT NOSE GEAR DOOR BRACE BROKEN AT REAR ATTACH POINT. ALSO CRACKED OUT FROM RIVETS AT AFT END OF BRA CE. 1 L 7 1 3O 3 O A3SO E14EA 2001121000146 20011210 00146 SO 2001 12 10 2001FA0000638 1 20011116 G 5280 3807601 BRACE PIPER PA32 PA32R300 7103213 SO LYC O540 TIO540* 41532 EA NLG DOOR BROKEN D K NONE O OTHER IN INSP/MAINT 1 AL 01 40449 53 32R7780519 INSPECTION FOUND RIGHT NOSE GEAR DOOR BRACE BROKEN AT REAR ATTACH POINT. ALSO CRACKED OUT FROM RIVETS AT AFT END OF BRA CE. 1 L 7 1 3O 3 O A3SO E14EA 2001121100013 20011211 00013 SO 2001 12 11 2001FA0000639 2 20011129 G 7414 DISTRIBUTOR BLK BEECH 33 F33A 1151425 CE CONT O520 IO520B 17032 SO MAGNETO FAILED B VJ3R K NONE O OTHER IN INSP/MAINT 1 WP 07 1556A 449 01040866 CE1318 820455R MAGNETO REMOVED FROM ENGINE FOR 500 HOUR INSPECTION IAW THE MM. REMOVED THE REAR COVER AND THE DISTRIBUTOR BLOCK FROM M AGNETO. DISTRIBUTOR BLOCK ASSEMBLY SENT TO MFG FOR INSPECTION. NEW DISTRIBUTOR BLOCK ASSEMBLY INSTALLED IN MAGNETO. 1 L 7 1 3O 3 O 3A15 E5CE 2001121100014 20011211 00014 SO 2001 12 11 2001FA0000640 2 20011128 G 7414 DISTRIBUTOR BLK BEECH 33 F33A 1151425 CE CONT O520 IO520B 17032 SO MAGNETO FAILED B VJ3R K NONE O OTHER IN INSP/MAINT 1 WP 07 5530A 998 00050438 CE1342 813779R MAGNETO REMOVED FROM ENGINE FOR 500 HOUR INSPECTION IAW THE MM. REMOVED THE REAR COVER AND THE DISTRIBUTOR BLOCK FROM M AGNETO. NEW DISTRIBUTOR BLOCK ASSEMBLY INSTALLED IN MAGNETO. 1 L 7 1 3O 3 O 3A15 E5CE 2001121100015 20011211 00015 SO 2001 12 11 2001FA0000641 2 20011128 G 7414 DISTRIBUTOR BLK SLICK BEECH 33 F33A 1151425 CE CONT O520 IO520B 17032 SO MAGNETO FAILED B VJ3R K NONE O OTHER IN INSP/MAINT 1 WP 07 5540P 01040863 CE1335 820456R MAGNETO REMOVED FROM ENGINE FOR 500 HOUR INSPECTION IAW MM. REMOVED THE REAR COVER AND THE DISTRIBUTOR BLOCK FROM MAGNE TO. DISTRIBUTOR BLOCK ASSEMBLY SENT TO MFG FOR INSPECTION. NEW DISTRIBUTOR BLOCK ASSEMBLY INSTALLED IN MAGNETO. 1 L 7 1 3O 3 O 3A15 E5CE 2001121100016 20011211 00016 SO 2001 12 11 2001FA0000642 2 20011129 G 7414 DISTRIBUTOR BLK BEECH 33 F33A 1151425 CE CONT O520 IO520B 17032 SO MAGNETO FAILED B VJ3R K NONE O OTHER IN INSP/MAINT 1 WP 07 8240T 695 00070052 CE1542 820387R MAGNETO REMOVED FROM ENGINE FOR 500 HOUR INSPECTION IAW THE MM. REMOVED THE REAR COVER AND THE DISTRIBUTOR BLOCK ASSEMB LY FROM MAGNETO. DISTRIBUTOR BLOCK ASSEMBLY SENT TO MFG FOR INSPECTION. NEW DISTRIBUTOR BLOCK ASSEMBLY, INSTALLED IN M AGNETO. 1 L 7 1 3O 3 O 3A15 E5CE 2001121100017 20011211 00017 2001 12 11 2001FA0000643 4 20011026 G 2561 FV353500137 LIFE VEST CABIN FAILED B KQ1R K NONE O OTHER IN INSP/MAINT 1 EA 07 LIFE VEST, TYPE FV-35. MFG AVG 1986 FAILED THE MFG. RECOMMENDED 2 PSI CELL TEST IAW MM. 2001121100111 20011211 00111 CE 2001 12 11 2001FA0000644 1 20011130 G 6120 PIN CESSNA 414 414A 2075907 CE CONT O520 TSIO520* 17040 SO MCAULY 3AF32C 3AF32C93 GL PROPELLER BROKEN B FG6R E A ENGINE SHUTDOWN UNSCHED LANDING W E INADEQUATE Q C VIBRATION/BUFFET NR NOT REPORTED 1 NM 11 30EE 5064 1690 414A0443 746886 PILOT NOTICED SEVERE VIBRATION IN LEFT ENGINE, SHUTDOWN AND ATTEMPTED FEATHER, WOULD NOT FEATHER, LANDED. FOUND 1 BLADE IN FEATHER AND FREE TO ROTATE. INSPECTION REVEALED 1 ACTUATING PIN HAD FRACTURED IN THREADS. PIN HOLE IN FERRULE NOT DRILLED AND TAPPED DEEP ENOUGH TO ALLOW PIN TO TIGHTEN ON WASHER. FATIGUE TO THREADS LED TO FAILURE.(K) 1 L 7 2 3O 3 O A7CE E8CE 5 C P22EA 2001121100112 20011211 00112 NE 2001 12 11 2001FA0000645 3 20011107 G 6111 6607132886 BLADE ROTOL R389 R3894123F25 NE PROPELLER CRACKED B MS1R K NONE O OTHER IN INSP/MAINT 1 EA 27 28857 6741 DR61587 PROPELLER RECEIVED FOR ROUTINE OVERHAUL. AT TEARDOWN, FOUND BLADE (PN 6607132886 SN 2) CRACKED IN OUTER SLEEVE APPROXI MATELY 2.5 INCHES LONG. BLADE REJECTED FROM FURTHER SERVICE. 6 C P30NE 2001121100113 20011211 00113 SO 2001 12 11 2001FA0000646 2 20011025 G 8530 652956 VALVE CESSNA 182 182 2072702 CE CONT O470 O470L 17026 SO ENGINE WORN B CY4R O OTHER O OTHER NR NOT REPORTED 1 AL 03 5670B 153 33670 069841R CYLINDER REMOVED DUE TO LOW COMPRESSION. VALVE STEM WORN TO 0.005. 1 H 7 1 3O 3 O NT 3A13 E273 2001121100115 20011211 00115 NE 2001 12 11 2001FA0000647 3 20011129 G 6114 660714200 HUB ROTOL R389 R3894123F25 NE PROPELLER CRACKED B MS1R K NONE O OTHER IN INSP/MAINT 1 EA 27 7522 DR6178587 PROPELLER RECEIVED FOR OVERHAUL. AT TEAR DOWN, FOUND HUB ASSEMBLY CRACKED ON BLADE BEARING FACE AT HUB SPLIT LINE NR 4 BLADE PORT. HUB ASSEMBLY REJECTED FROM FURTHER SERVICE. 6 C P30NE 2001121100116 20011211 00116 NE 2001 12 11 2001FA0000648 3 20011129 G 6111 6607132886 BLADE ROTOL R389 R3894123F25 NE PROPELLER CRACKED B MS1R K NONE O OTHER IN INSP/MAINT 1 EA 27 25344 833 DR694884 PROPELLER WAS REMOVED FROM AIRCRAFT TO CORRECT GREASE LEAK. AT DISASSEMBLY, BLADE (SN 279) WAS FOUND TO BE CRACKED ON O UTER SLEEVE AT ROOT END. BLADE REJECTED FROM FURTHER SERVICE. 6 C P30NE 2001121200091 20011212 00091 SO 2001 12 12 2001FA0000649 2 20010717 G 8530 SA52000A20P CYLINDER CESSNA 207 207A 2073604 CE CONT O520 IO520F 17032 SO ENGINE CRACKED B CY4R K NONE O OTHER IN INSP/MAINT 1 AL 03 1500 240860 CYLINDER CRACKED ON INTAKE AND EXHAUST SEATS. 1 H 7 1 3O 3 O A16CE E5CE 2001121200092 20011212 00092 SO 2001 12 12 2001FA0000650 2 20010717 G 8530 SA52000A20P CYLINDER CESSNA 207 207A 2073604 CE CONT O520 IO520F 17032 SO ENGINE CRACKED B CY4R K NONE O OTHER IN INSP/MAINT 1 AL 03 1500 240860 CYLINDER CRACKED ON INTAKE AND EXHAUST SEATS. 1 H 7 1 3O 3 O A16CE E5CE 2001121200093 20011212 00093 SO 2001 12 12 2001FA0000651 2 20010717 G 8530 SA52000A20P CYLINDER CESSNA 207 207A 2073604 CE CONT O520 IO520F 17032 SO ENGINE CRACKED B CY4R K NONE O OTHER IN INSP/MAINT 1 AL 03 1500 240860 CYLINDER CRACKED ON INTAKE AND EXHAUST SEATS. 1 H 7 1 3O 3 O A16CE E5CE 2001121200094 20011212 00094 SO 2001 12 12 2001FA0000652 2 20010717 G 8530 SA52000A20P CYLINDER CONT O520 IO520F 17032 SO ENGINE CRACKED B CY4R K NONE O OTHER IN INSP/MAINT 1 AL 03 1500 CRACKED ON INTAKE AND EXHAUST SEATS. 3 O E5CE 2001121200095 20011212 00095 SO 2001 12 12 2001FA0000653 2 20010717 G 8530 SA52000A20P CYLINDER CESSNA 207 207A 2073604 CE CONT O520 IO520F 17032 SO ENGINE CRACKED B CY4R K NONE O OTHER IN INSP/MAINT 1 AL 03 1500 CYLINDER CRACKED ON INTAKE AND EXHAUST SEAT. 1 H 7 1 3O 3 O A16CE E5CE 2001121200096 20011212 00096 SO 2001 12 12 2001FA0000654 2 20010716 G 8530 SA52000A20P CYLINDER CESSNA 207 207A 2073604 CE CONT O520 IO520F 17032 SO ENGINE CRACKED B CY4R K NONE O OTHER IN INSP/MAINT 1 AL 03 1648 240860 CYLINDER CRACKED ALL THE WAY AROUND AT THE VALVE SEAT LINE AND BURNED THROUGH THE EXHAUST PORT SIDE. 1 H 7 1 3O 3 O A16CE E5CE 2001121200097 20011212 00097 EA 2001 12 12 2001FA0000655 2 20011106 G 8520 77672 LIFTER BEECH 60 60 1153602 CE LYC O541 TIO541E1C4 41536 EA ENGINE SPALLED B EKGR K NONE O OTHER IN INSP/MAINT 1 WP 07 33LB 132 P74 L104559 UPON REMOVAL OF PUSH RODS AND PUSH ROD TUBES FOR RESEAL. THE LIFTERS WERE REMOVED FOR BLEEDING. THE LIFTERS WERE INSPE CTED AND WERE FOUND TO HAVE SEVERE SPALLING. MFG WAS NOTIFIED AND ENGINES ARE TO BE REMOVED AND SENT BACK FOR REPAIR. ENGINES HAVE 132.4 HOURS TT. CAMSHAFT IS ALSO WORN. 1 L 7 2 3O 3 O A12CE E10EA 2001121200098 20011212 00098 2001 12 12 2001FA0000656 4 20011126 G 6122 A21107 IDLER GEAR MCAULY CESSNA 182 182K 2072724 CE CONT O470 O470* 17026 SO PROP GOVERNOR CRACKED B LU4R K NONE O OTHER IN INSP/MAINT 1 SO 17 2544R 70647 18258244 RELEVANT INDICATION. (CRACK) 1 H 7 1 3O 3 O NT 3A13 E273 2001121300084 20011213 00084 EA 2001 12 13 2001FA0000657 2 20011130 G 7414 M3007 IMPULSE COUPLING SLICK CESSNA 150 152 2071835 CE LYC O235 O235L2C 41505 EA LT & RT MAGNETOS WORN D UL9G O OTHER O OTHER NR NOT REPORTED 1 GL 15 6436P 15285013 L2223415 INSTALLED NEW M3007 IMPULSE COUPLINGS ON BOTH MAGNETOS. BOTH COUPLINGS CAME OUT OF BOXES DATED 5/25/01. INITIAL OPERAT ION WAS FINE. IMPULSE COUPLINGS INTERMITTENT SNAPPING. REMOVED MAGNETOS, INSPECTED COUPLINGS PAWLS SHOWED NOTICEABLE WE AR AT CONTACT POINT WITH STRIKER PIN. ALSO LOOSENESS AT PIVOT PIN ATTACH. SUSPECT BAD BATCH OF METAL OR HEAT TREATMENT . INSTALLED NEW IMPULSE COUPLING ASSEMBLIES OPERATIONAL CHECK, FINE. DEFECTIVE IMPULSE COUPLINGS TIME IN SERVICE 93 HO URS/ 119 HOURS 1 H 7 1 3O 3 O NT 3A19 E223 2001121400057 20011214 00057 CE 2001 12 14 2001FA0000658 1 20011103 G 7160 BA8110 GASKET CESSNA 180 180K 2072624 CE CONT O470 O470U 17026 SO AIR FILTER LOOSE D K NONE O OTHER IN INSP/MAINT 1 SW 09 20379 450 18053185 THIS AIR FILTER ASSEMBLY HAS THE MANUFACTURING DEFECT DESCRIBED IN AD. WITH THE GASKET COMING LOOSE. FOUND IT DURING AN NUAL INSPECTION AND DISCOVERED THAT IT (BA 8110) IS NOT COVERED BY THE AD. 1 H 7 1 3O 3 O 5A6 E273 2001121400058 20011214 00058 SO 2001 12 14 2001FA0000659 1 20011204 G 2720 9621200 TORQUE TUBE PIPER PA34 PA34200T 7103406 SO CONT O360 TSIO360* 17025 SO RUDDER DAMAGED B R2JR K NONE O OTHER IN INSP/MAINT 1 EA 21 2190K 4230 347970096 WHILE INSPECTING RUDDER ON ANNUAL INSPECTION THE INSPECTOR FOUND LOOSENESS AT THE RUDDER TORQUE TUBE ATTACH BOLTS. TEAR DOWN INSPECTION SHOWED BOLT HOLES OVERSIZE AND ELONGATED. NEW PARTS INSTALLED BECAUSE (AN 174) BOLTS WERE LARGEST SIZE BOLTS PERMITTED. MFG SB REFERS TO THIS PROBLEM. 1 L 7 2 3O 3 O A7SO E9CE 2001121400059 20011214 00059 SO 2001 12 14 2001FA0000660 1 20011204 G 5210 47958008 SNUBBER PIPER PA31T PA31T 7103124 SO CABIN DOOR FAILED D K NONE W INADEQUATE Q C IN INSP/MAINT 1 SO 11 311AC 10 31T8120016 RECEIVED 2 DIFFERENT SNUBBERS AND INSTALLED. NEITHER HAD ANY SNUBBING ACTION. NEW PARTS FROM THE FACTORY. 1 L 7 2 3T A8EA 2001121400073 20011214 00073 CE 2001 12 14 2001FA0000661 1 20011120 G 3710 CH442CW8 COUPLING CESSNA 340 340A 2076405 CE CONT O520 TSIO520NB 17040 SO VACUUM PUMP SHEARED D O OTHER O OTHER NR NOT REPORTED 1 NM 02 2741R 230 340A0922 503320 PNEUMATIC PUMP COUPLING SHEARED AFTER 230.7 HOURS OF OPERATION. 1 L 7 2 3O 3 O 3A25 E8CE 2001121400074 20011214 00074 CE 2001 12 14 2001FA0000662 1 20011011 G 3710 CH442CW8 PUMP CESSNA 340 340A 2076405 CE CONT O520 TSIO520NB 17040 SO PNEUMATIC SYS SHEARED D O OTHER O OTHER NR NOT REPORTED 1 NM 02 2741R 113 340A0922 519294 PNEUMATIC PUMP SHEARED AFTER 113 HOURS OF OPERATION. PUMP COULD BE ROTATED WHEN REMOVED. COUPLING SHOWED SIGNS OF HEAT (MELTED EDGES). 1 L 7 2 3O 3 O 3A25 E8CE 2001121700078 20011217 00078 SO 2001 12 17 2001FA0000664 1 20011118 G 2720 408424 RUDDER PEDAL PIPER PA18 PA18135 7101820 SO COCKPIT WORN D K NONE O OTHER IN INSP/MAINT 1 WP 21 9952Q 3700 183579 DURING DISASSEMBLY FOR REBUILD ALL AND RUDDER PEDALS WERE FOUND TO BE DAMAGED DUE TO THE RETURN SPRING(40494100) CUTTING THROUGH LOWER HINGE SHAFT, WALL. ALL HAD BEEN WELD REPAIRED BUT WERE AGAIN WORN THROUGH, ALL REPLACED NEW AND APPEAR T O HAVE SAME WALL THICKNESS. AS THE WEAR PROGRESSES THE POTENTIAL FOR BINDING EXISTS. 1 H 7 1 3O 1A2 2001121700079 20011217 00079 SO 2001 12 17 2001FA0000665 1 20011118 G 2720 404825 RUDDER PEDAL PIPER PA18 PA18135 7101820 SO COCKPIT WORN D K NONE O OTHER IN INSP/MAINT 1 WP 21 9952Q 3700 183579 DURING DISASSEMBLY FOR REBUILD ALL 4 RUDDER PEDALS WERE FOUND TO BE DAMAGED DUE TO THE RETURN SPRING (40941-00) CUTTING THROUGH LOWER HINGE SHAFT WALL. ALL 4 HAD BEEN WELD REPAIRED BUT WERE AGAIN WORN THROUGH. ALL REPLACED NEW AND APPEAR TO HAVE SAME WALL THICKNESS. AS THE WEAR PROGRESSES THE POTENTIAL FOR BINDING EXISTS. 1 H 7 1 3O 1A2 2001121700080 20011217 00080 SO 2001 12 17 2001FA0000666 1 20011204 G 5343 95554000 BRACKET PIPER PA34 PA34200 7103405 SO LYC O360 IO360A1A 41514 EA FUSELAGE WORN D K NONE O OTHER IN INSP/MAINT 1 SO 15 66BL 347250285 DURING PERFORMANCE OF 100 HOUR INSPECTION AND COMPLIANCE WITH AD. DURING GEAR RETRACTION NOTICED MOVEMENT OF NOSE GEAR SUPPORT CENTER ATTACH BOLT. AFTER INVESTIGATION AND INSTALLATION OF ACCESS PANEL ON BELLY OF AIRCRAFT FOUND BRACKET PAR T 95554-000 LOOSE AND WORN EXCESSIVELY INSTALLED NEW FACTORY PARTS. AIRCRAFT TOTAL TIME 9750.2 1 L 7 2 3O 3 O A7SO 1E10 2001121700081 20011217 00081 SO 2001 12 17 2001FA0000667 1 20011204 G 5343 95554000 BRACKET PIPER PA34 PA34200 7103405 SO LYC O360 IO360A1A 41514 EA FUSELAGE CRACKED D K NONE O OTHER IN INSP/MAINT 1 SO 15 1056U 347250040 DURING PERFORMANCE OF 100 HOUR INSPECTION AND COMPLIANCE WITH AD. DURING GEAR, RETRACTION NOTICED MOVEMENT, OF NOSE GEA R SUPPORT CENTER ATTACH BOLT AFTER INVESTIGATION AND INSTALLATION OF ACCESS PANEL ON BELLY OF AIRCRAFT FOUND BRACKET PAR T 95554-000 CRACKED AND FITTING PART 95555-000 LOOSE AND WORN EXCESSIVELY. INSTALLED NEW FACTORY PARTS AIRCRAFT. TOTAL TIME 4793.9 1 L 7 2 3O 3 O A7SO 1E10 2001121700082 20011217 00082 SO 2001 12 17 2001FA0000668 2 20011201 G 8530 EXHAUST VALVE CESSNA 207 207A 2073604 CE CONT O520 IO520F 17032 SO ENGINE STUCK D O OTHER R PARTIAL RPM/PWR LOSS NR NOT REPORTED 1 AL 05 17GN 20700693 EXHAUST VALVE APPARENTLY STUCK OPEN, WAS STRUCK BY PISTON AND IN TURN SLIGHTLY BENT AT THE STEM. THIS INADVERTENTLY CAU SE THE VALVE TO STICK IN A CLOSED POSITION THERE BY BENDING THE EXHAUST PUSHROD SLIGHTLY. 1 H 7 1 3O 3 O A16CE E5CE 2001121700083 20011217 00083 CE 2001 12 17 2001FA0000669 1 20011201 G 3060 26700696 RESISTOR CESSNA 208 208B 2073701 CE PWA PT6 PT6* 52043 EA PROP ANTI-ICE FAILED D O OTHER O OTHER NR NOT REPORTED 1 AL 05 715HE 208B0603 PROPELLER ANTI-ICE VARISTOR MELTED PLUGS. PLUGS SEEM TO OPEN AND WEAR CAUSING INTERMITTENT POWER TO BRUSH BLOCK, DUE MO ST LIKELY TO VIBRATION. CHANGING CONNECTORS WOULD FIX PROBLEM. 1 H 7 1 3T 3 T A37CE E2NE 2001121900081 20011219 00081 CE 2001 12 19 2001FA0000670 1 20011120 G 3211 FRAME BEECH 76 76 1153005 CE RT MLG CRACKED B ZM3R K NONE O OTHER IN INSP/MAINT 1 WP 07 819ER 4724 ME199 DURING ANNUAL INSPECTION, THE RIGHT MAIN LANDING GEAR A-FRAME WAS FOUND CRACKED HALF WAY AROUND THE CIRCUMFERENCE OF THE A FRAME TUBE IN THE AREA WHERE RECURRING INSPECTION WAS REQUIRED BY AD. THIS A-FRAME DID NOT REQUIRE RECURRING INSPECT ION BECAUSE IT WAS (PN 105-810023-76) WHICH ELIMINATED THE RECURRING INSPECTION REQUIREMENT. THE A-FRAME HAD 4724.2 HRS 1 L 7 2 3O A29CE 2001121900082 20011219 00082 SO 2001 12 19 2001FA0000671 1 20011114 G 7820 MUFFLER MAULE MX7 MXT7180A 5460187 SO LYC O340 O340* 41510 EA ENGINE CRACKED G K NONE O OTHER IN INSP/MAINT 1 SW 17 54CH 300 21028C 3562336A WELD SHOULD BE INSPECTED EACH 100 HOURS OR EVERY OIL CHANGE. CRACK COULD BRING EXHAUST GAS INTO CABIN. POOR DESIGN OF MUFFLER AND NOT SUPPORTED PROPERLY. 1 H 7 1 3O 3 O NC 3A23 E277 2002012500090 20020125 00090 CE 2002 1 25 2001FA0000672 1 20011129 G 5320 EYEBOLT CESSNA 170 170B 2072306 CE LYC O340 O340* 41510 EA FUSELAGE MISINSTALLED D K NONE W INADEQUATE Q C IN INSP/MAINT 1 AL 01 4669C 25613 FLOAT EQUIPPED, LIFTING EYES WERE INSTALLED IN THE WRONG POSITION. RESULTING IN DRILLING THROUGH THE MAIN FORWARD WING SPAR AND LEAVING APPROXIMATELY EDGE DISTANCE. BETWEEN THE FORWARD SPAR ATTACH BOLT AND EDGE OF SPAR. (EYES SHOULD BE IN SIDE CABIN TOP RIVET LINE) (K) 1 H 7 1 3O 3 O A799 E277 2001121900083 20011219 00083 NM 2001 12 19 2001FA0000673 1 20011108 G 2730 401611557 HOUSING MOOG BOEING 727 727* NM FEEL CONTROL CORRODED B IU6R K NONE O OTHER IN INSP/MAINT 1 NM 01 335 HOUSING ASSEMBLY HAS HEAVY PITTING AND CORROSION IN THE BOLT HOLES, PORTS, CAP ASSEMBLIES AND ON THE SEALING SURFACES. DISSIMILAR METAL CORROSION. 2 L 7 3 4F RT A3WE 2001121900084 20011219 00084 NM 2001 12 19 2001FA0000674 1 20011112 G 2730 401611565 HOUSING MOOG BOEING 727 727* NM FEEL CONTROL CORRODED B IU6R K NONE O OTHER IN INSP/MAINT 1 NM 01 335 ELBOW HOUSING HAS SEVERE CORROSION IN THE BOLT HOLES, CHECK VALVE PORT, PACKING LANDS AND ON THE SEALING SURFACE. DISSI MILAR METAL CORROSION. 2 L 7 3 4F RT A3WE 2001121900085 20011219 00085 NM 2001 12 19 2001FA0000675 1 20011112 G 2730 4016146202 CAP MOOG BOEING 727 727* NM FEEL CONTROL CORRODED B IU6R K NONE O OTHER IN INSP/MAINT 1 NM 01 335 CAP ASSEMBLY HAS SEVERE CORROSION IN THE PACKING GROOVE, THE INTERIOR AND EXTERIOR SURFACES. DISSIMILAR METAL CORROSION . 2 L 7 3 4F RT A3WE 2001121900086 20011219 00086 NM 2001 12 19 2001FA0000676 1 20011112 G 2730 4016146302 CAP MOOG BOEING 727 727 UTILSYS NM FEEL CONTROL CORRODED B IU6R K NONE O OTHER IN INSP/MAINT 1 NM 01 335 CAP ASSEMBLY HAS SEVERE CORROSION IN THE PACKING GROOVE, THE INTERIOR AND EXTERIOR SURFACES. DISSIMILAR METAL CORROSION . 2 L 7 3 4J RT A3WE 2002012500091 20020125 00091 NM 2002 1 25 2001FA0000677 1 20011108 G 3220 4400612 COIL PLESSEY BOEING 727 727* NM MOTOR BRAKE SHORTED B IU6R K NONE O OTHER IN INSP/MAINT 1 NM 01 901 21201 BRAKE COILS ARE SHORTED AND BURNED. UNDER NORMAL OPERATION THE VIBRATION INCURRED HAS BEEN FOUND TO CAUSE ABRADING BETW EEN THE BRAKE COILS AND STUDS WHICH RESULTS IN A SHORT AND ARCING OF THE BRAKE COILS. REDUCE THE SIZE OF THE COIL WINDI NGS OR DIAMETER OF THE STUDS TO ALLOW FOR GREATER CLEARANCE BETWEEN THE TWO. (NOTE: THIS MALFUNCTION APPLIES TO BOTH NEW AND REWOUND COIL ASSEMBLIES. 2 L 7 3 4F RT A3WE 2002012500092 20020125 00092 NM 2002 1 25 2001FA0000678 1 20011108 G 3220 4400613 COIL PLESSEY BOEING 727 727* NM MOTOR BRAKE SHORTED B IU6R K NONE O OTHER IN INSP/MAINT 1 NM 01 901 21201 BRAKE COILS ARE SHORTED AND BURNED. UNDER NORMAL OPERATION THE VIBRATION INCURRED HAS BEEN FOUND TO CAUSE ABRADING BETW EEN THE BRAKE COILS AND STUDS WHICH RESULTS IN A SHORT AND ARCING OF THE BRAKE COILS. REDUCE THE SIZE OF THE COIL WINDI NGS OR DIAMETER OF THE STUDS TO ALLOW FOR GREATER CLEARANCE BETWEEN THE TWO. 2 L 7 3 4F RT A3WE 2001123100160 20011231 00160 NM 2001 12 31 2001FA0000679 1 20011120 G 3240 511531 HOUSING BOEING 737 737* NM SHUTTLE VALVE CRACKED B IU6R K NONE O OTHER IN INSP/MAINT 1 NM 01 HOUSING IS CRACKED INSIDE ONE OF THE BOLT MOUNTING HOLES. FATIGUE, DEFECT IN THE IN THE CASTING OF THE HOUSING AND /OR OVERTORQUING OF BOLT ON INSTALLATION. 2 L 7 2 4F RT A16WE 2001123100161 20011231 00161 NM 2001 12 31 2001FA0000680 1 20011120 G 2923 654468311 HOUSING BOEING 737 737* NM HYDRAULIC SYS CRACKED B IU6R K NONE O OTHER IN INSP/MAINT 1 NM 01 HOUSING CRACKED IN PORT NR 1 WHILE APPLYING PRESSURE DURING TESTING. HOUSING HAD LIQUID PENETRANT INSPECTION ACCOMPLISH ED PRIOR TO TESTING, WITH NO DEFECTS NOTED. MATERIAL THICKNESS OF PORT NR 1 IS THIN. FATIGUE AND POSSIBLY THE INSTALLA TION AND TORQUING OF THE FITTING COULD CONTRIBUTE OVER A PERIOD OF TIME. 2 L 7 2 4F RT A16WE 2001123100162 20011231 00162 CE 2001 12 31 2001FA0000681 1 20011126 G 5312 04500391791 BULKHEAD CESSNA 150 150F 2071814 CE CONT O200 O200* 17020 SO FUSELAGE CRACKED D K NONE O OTHER IN INSP/MAINT 1 GL 13 6937F 350 15063537 SINCE MFG. WENT TO PLASTIC BULKHEAD, THEY CRACK ABOUT EVERY 200 HOURS. 1 H 7 1 3O 3 O 3A19 E252 2002012500093 20020125 00093 SO 2002 1 25 2001FA0000682 2 20010614 G 8550 640849 COVER SWFTMS GC1B GC1B 9230104 SO CONT C125 C125 17011 SO OIL FILTER FAILED D A UNSCHED LANDING K Y J FLUID LOSS ENGINE STOPPAGE WARNING INDICATION NR NOT REPORTED 1 NM 13 2432B 3732 62791R WHILE AIRCRAFT WAS IN FLIGHT ALL ENGINE OIL WAS PUMPED OVERBOARD CAUSING CATASTROPHIC ENGINE FAILURE. LOSS OF ENGINE OI L WAS DUE TO FAILURE OF THREADS ON MAGNESIUM CRANKCASE COVER ASSEMBLY. THE THREADS FAILED WHERE THE OIL FILTER ADAPTER THREADS INTO THE CRANKCASE COVER ASSEMBLY. TO PREVENT REOCCURRENCE, REMOVE THREADED TYPE CONTINENTAL OIL FILTER ASSEMBL Y FROM SERVICE. 1 L 7 1 3O 3 O NC A766 E236 2001123100163 20011231 00163 CE 2001 12 31 2001FA0000683 1 20011211 G 5610 NH2401691 WINDOW RAYTHN DH125 HAWKER800XP 7150012 CE GARRTT TFE731 TFE731* 01518 WP COCKPIT DELAMINATED D K NONE O OTHER IN INSP/MAINT 1 WP 07 910JD 655 258420 WINDOW DELAMINATED AT THE CENTER HEATING ELEMENT. POSSIBLE SHORT AT INTERNAL WIRING TO HEATING ELEMENT. THE DELAMINATI ON AREA IS IN THE BOTTOM CENTER. THE UNIT IS BEING SENT TO MFG FOR FURTHER EVALUATION. 2 L 7 2 4F 4 F RT A3EU E6WE 2001123100164 20011231 00164 SO 2001 12 31 2001FA0000684 2 20011204 G 7414 10357586 DISTRIBUTOR GEAR CONT CESSNA 402 402C 207590R CE CONT O520 TSIO520VB 17040 SO MAGNETO BROKEN D A UNSCHED LANDING R PARTIAL RPM/PWR LOSS CL CLIMB 1 NM 05 402NQ K099814ER 402C0093 AT FIRST POWER REDUCTION AFTER TAKE OFF RIGHT ENGINE STARTED RUNNING ROUGH. PILOT SUSPECTED A MAGNETO AND ISOLATED PROB LEM TO THE RIGHT MAGNETO. PILOT RETURNED TO THE AIRPORT WITH RIGHT ENGINE RUNNING ON JUST THE LEFT MAGNETO. UPON REMOV AL AND DISASSEMBLY OF MAGNETO, THE DISTRIBUTOR GEAR WAS FOUND WITH BROKEN TEETH AND NOT TURNING, RESULTING IN THE MAGNET O FAILING TO FUNCTION, NO OTHER DEFECTS FOUND. DISASSEMBLED LEFT MAGNETO AND NO FAULTS FOUND, POINTS CHECKED GOOD AND N O ADJUSTMENTS NEEDED. NO REASON FOUND FOR FAILURE OF DISTRIBUTOR GEAR IN RIGHT MAGNETO. 1 L 7 2 3O 3 O A7CE E8CE 2001123100165 20011231 00165 EA 2001 12 31 2001FA0000685 2 20011211 G 8530 VALVE SEAT ENSTRM F28 280C 3300505 GL LYC O360 HIO360E1AD 41514 EA ENGINE LOOSE G O OTHER R PARTIAL RPM/PWR LOSS NR NOT REPORTED 1 EA 17 123MT 1063 NUMBER 4 CYLINDER HAD AN INTAKE VALVE SEAT COME LOOSE AND THE PISTON HAD BROKEN RINGS. SUBSEQUENT LOSS OF POWER. 1 G 7 1 3O 3 O H1CE 1E10 2001123100166 20011231 00166 CE 2001 12 31 2001FA0000686 1 20011211 G 2510 05142132 CYLINDER CESSNA 172 172R 2072401 CE SEAT FAILED B WIWR O OTHER O OTHER NR NOT REPORTED 1 WP 07 181MW 3500 17280181 SEAT LOCK CYLINDER FAILED TO LOCK IN POSITION WITH NORMAL SEATBACK PRESSURE. CABLE ADJUSTMENT WITHIN LIMITS. FAILURE O CCURRED DURING NORMAL USE. 1 H 7 1 3O NT 3A12 2002012500095 20020125 00095 EU 2002 1 25 2001FA0000687 1 20010628 G 7830 BRACKET AMD FALC50 FALCON50MYST 2730106 EU GARRTT TFE731 TFE731* 01518 WP T/R DOOR BROKEN D O OTHER J WARNING INDICATION TX TAXI/GRND HDL 1 SO 11 500AF 7225 170 AFTER LANDING, THE CREW TRIED TO STOW THE THRUST REVERSER HAD A TRANSIT LIGHT ON IN THE COCKPIT. A VISUAL INSPECTION R EVELED THE RIGHT THRUST REVERSER DOOR (PN C41B30212-39 SN 2287) HINGE ARM HAD BROKE BETWEEN THE LOWER HINGE BEARING AND THE DOOR. ALSO DAMAGED WERE A SUPPORT BRACKET (PNF50B583001024) AND THE RIGHT UPPER BUSHING. A NEW BRACKET WAS INSTALL ED AND THE BUSHING WAS REPLACED WITH AN OVERSIZED BUSHING. A ROD BEARING AND ALL HINGE BOLTS FOR BOTH LEFT AND RIGHT DO ORS WERE REPLACED. 2 OTHER CASES OF CRACKS WERE FOUND IN THE AREA OF OUT THRUST REVERSER HINGE FAILURE. THE PROBABLE C AUSE FOR FAILURE WAS FATIGUE. 2 L 7 3 4F 4 F A46EU E6WE 2001123100167 20011231 00167 CE 2001 12 31 2001FA0000688 2 20010316 G 7314 LW15473 PUMP CONT IO360 IO360* 17025 CE ENGINE FAILED C XBTR K NONE L NO TEST IN INSP/MAINT 1 SW 15 966336A ON 16 MAR O1 BPA RETURNED TO SERVICE (PN IO360, SN 966336A) AFTER SATISFACTORY TEST AFTER OVERHAUL. THE ENGINE WAS SUBS EQUENTLY INSTALLED AT ANOTHER FACILITY. THE MECHANIC NOTIFIED US BY PHONE THAT FUEL WOULD NOT FLOW THRU THE FUEL PUMP E VEN WITH THE USE OF THE WOBBLE PUMP, THAT FUEL PRESSURE FROM THE WOBBLE PUMP WAS AVAILABLE AT THE ENGINE NEW AT INSTALLA TION IN FACILITY AND IS AFFECTED BY SB. THIS IS IN DIRECT CONFLICT WITH THE FIELD REPORTS OF FAILURE QUOTED ABOVE. THI S IS A DEFINITE SAFETY OF FLIGHT ITEM. COMPLETE STOPPAGE OF THE ENGINE CAN AND IS LIKELY TO OCCUR WITH NO REMEDIAL ACTI ON AVAILABLE TO THE PILOT. 3 O E1CE 2002011700038 20020117 00038 2002 1 17 2001FA0000689 4 20011024 G 6122 LINE CESSNA 208 208 2073702 CE ENGINE CRACKED A HSYA C ABORTED TAKEOFF R PARTIAL RPM/PWR LOSS TO TAKEOFF 1 NM 05 903FF B0003 AIRCRAFT WOULD NOT MAKE TAKEOFF POWER, RESULTED IN RTO. CRACKED PY LINE BETWEEN FUEL CONTROL AND PROP GOV. REMOVED AND REPLACED PY RIGHT LINE GOING TO PROP AND PERFORMED A SUCCESSFUL OPERATIONAL AND LEAK CHECK. (M) 1 H 7 1 3T NT A37CE 2002011600149 20020116 00149 SO 2002 1 16 2001FA0000690 1 20011113 G 2910 HYDRAULIC LINE EMB 120 EMB120ER 3260203 SO HYDRAULIC SYS CHAFED A HSYA O OTHER K J FLUID LOSS WARNING INDICATION CR CRUISE 1 NM 05 223AS 120021 BLUE HYDRAULIC FLUID LOSS. BLUE SYSTEM HYDRAULIC LINE CHAFFED THROUGH. REPAIRED LINE WITH PERMISSIVE IAW EMB-120 MM 20 -10-01 AND A SUCCESSFUL LEAK CHECK WAS PERFORMED. (M) 2 L 7 2 4T RT A31SO 2001123100168 20011231 00168 2001 12 31 2001FA0000691 4 20011214 G 3422 6446 FLUX DETECTOR PIPER PA46 PA46500TP 7104622 SO PWA PT6 PT6* 52043 EA DIRECTIONAL SYS FAILED B O OTHER O OTHER NR NOT REPORTED 1 EA 07 164ST 4697064 AFTER 10-30 HOURS OF AIRCRAFT OPERATION FLUX VALVE IS FAILING. SUSPECT THE PROBLEM IS VIBRATION RELATED. NEED TO REPLA CE HORIZONTAL STABILIZER IF PROBLEM CANNOT BE ISOLATED. 1 L 7 1 3O 3 T RT A25SO E2NE 2002020100020 20020201 00020 EA 2002 2 1 2002F00003 1 20010911 G 5320 858947 SUPPORT CNDAIR CL604 CL604 1900301 EA WATER SEP CRACKED H K NONE O OTHER IN INSP/MAINT 1 WP 28 TCDHE 5358 THE FLANGE OF THE WATER SEPARATOR SUPPORT ASSEMBLY WAS CRACKED IN TWO PLACES. 2 L 7 2 4F RT A21EA 2002020100021 20020201 00021 NE 2002 2 1 2002F00036 3 20011218 G 6111 RFC11M1R6A BLADE HAMSTD 14RF 14RF9 NE PROPELLER CRACKED B K NONE O OTHER IN INSP/MAINT 1 NM 01 3085 TWO CRACK INDICATIONS ON THE BLADE SHANK. ONE IN THE FILLET AREA AND THE OTHER IN THE BLADE BUTT AREA. INDICATIONS WERE PARALLEL AND 2 TO 3 INCHES IN LENGTH. 6 C P11NE 2002012500100 20020125 00100 GL 2002 1 25 2002FA0000000 3 20011212 G 6114 D4883C55 HUB MCAULY 2AF34C 2AF34C55 GL PROPELLER CRACKED B ME4D K NONE O OTHER IN INSP/MAINT 1 SO 15 815861 DURING INSPECTION HUB WAS FOUND TO BE CRACKED IN THREADS. HUB HAS BEEN SCRAPPED. 5 C P5EA 2002012500102 20020125 00102 SO 2002 1 25 2002FA0000001 2 20011113 G 8530 35967 SEAT CONT O520 IO520* 17032 SO ENG CYLINDER CRACKED B CY4R K NONE O OTHER IN INSP/MAINT 1 AL 03 116 818927R FOUND SEAT CRACKED DURING CLYINDER INSPECTION AT 116.7 HOURS SINCE FACTORY REMANUFACTURE. 3 O E5CE 2002012500103 20020125 00103 SO 2002 1 25 2002FA0000002 1 20011129 G 3411 PITOT LINE PIPER PA28 PA28181 7102807 SO LEFT WING DETERIORATED B NS4R K NONE O OTHER IN INSP/MAINT 1 SO 35 9290N 481 2843108 DURING 24 MONTH IFR RECERTIFCATION, STATIC SYSTEM HAD WIDE OPEN LEAK. DURING TROUBLESHOOTING, PITOT SYSTEM FOUND TO HAV E WIDE OPEN LEAK ALSO. FOUND BOTH HOLES SPLIT AND DETERIORATED AT JUNCTION FROM PITOT/STATIC PROBE TO METAL LINES IN LE FT WING. NOTE: THIS AIRCRAFT IS LOCATED IN HIGH CORROSION ENVIRONMENT (SALT AIR). SUGGEST USE OF FUEL LINE, INSTEAD OF VACCUM LINE. 1 L 7 1 3O 2A13 2002012500104 20020125 00104 CE 2002 1 25 2002FA0000003 1 20011127 G 7714 S25502 CABLE CESSNA 172 172S 2072439 CE LYC O360 IO360A1A 41514 EA TACHOMETER BROKEN G K NONE O OTHER IN INSP/MAINT 1 GL 11 917MA 1139 172S8270 TACHOMETER CABLE BROKE, JUST AFT OF ENGINE. 1 H 7 1 3O 3 O NT 3A12 1E10 2002012500105 20020125 00105 SW 2002 1 25 2002FA0000004 1 20011216 G 8011 S8111 CONTACTOR BBAVIA 402 402CHAMP 2110204 SW CONT O200 O200A 17020 SO FIELD COIL BROKEN C K NONE O OTHER IN INSP/MAINT 1 EA 25 9957Y 32 40213 UNABLE TO OPERATE AIRCRAFT. STARTER CONTACTOR RELAY INOPERATIVE UPON DISASSEMBLY, FOUND FIELD COIL WIRE WHERE IT ATTAC HES TO POSITIVE CONNECTOR BROKEN OFF. 1 L 7 2 3O 3 O A3CE E252 2002012500106 20020125 00106 CE 2002 1 25 2002FA0000005 1 20011220 G 7602 63255536 ARM CESSNA 337 337H 2075732 CE CONT O360 IO360GB 17025 SO MIXTURE CONTROL WORN D K NONE O OTHER IN INSP/MAINT 1 NE 02 1258S 33701894 352804 DURING ANNUAL INSPECTION FOUND MIXTURE ARM ROD END ATTACHING BOLT LOOSE. ATTEMPTED TO TIGHTEN BOLT BUT FOUND THERE WAS STILL PLAY. DISASSEMBLED ROD END ATTACHING BOLT AND A STEEL SERRATED BEARING INSERT FELL OUT OF THE BRONZE MIXTURE ARM. THIS WAS CAUSED BY THE ROD END ATTACHING BOLT BEING TOO LOOSE. SPHERICAL BALL ROD END ATTACHING BOLTS SHOULD BE TIGHT TO ALLOW THE ROD END TO ROTATE AROUND THE BALL. 1 H 7 2 3O 3 O A6CE E1CE 2002012500107 20020125 00107 CE 2002 1 25 2002FA0000006 1 20011201 G 3220 22430151 CLAMP CESSNA 182 TR182 2072735 CE LYC O540 O540* 41532 EA SHIMMY DAMPER BROKEN D K NONE O OTHER IN INSP/MAINT 1 GL 23 737HU R18200832 THIS CLAMP HOLDS THE SHIMMY DAMPNER IN POSITION ON THE NOSE GEAR BARRELL WITH A PIN WELDED INSIDE THE CLAMP. PIN WAS FO UND BROKEN AND THIS ALLOWED THE CLAMP TO SHIFT WHICH CAUSED THE SHIMMY DAMPNER TO HIT THE GEAR WELL AND SOME TIMES LOCK THE GEAR IN THE UP POSITION. A SLIP MARK HELPS TO FIND THIS PROBLEM ON PREFLIGHT INSPECTION AND ANNUALS. I DO NOT THIN K THIS PIN GETS BROKEN IN NORMAL USE BUT COULD VERY EASILY BE BROKEN BY USE OF A LARGE TUG. 1 H 7 1 3O 3 O 3A13 E295 2002012500108 20020125 00108 EA 2002 1 25 2002FA0000007 2 20011215 G 7322 78A110 LOCK PRECISION CESSNA 172 172M 2072418 CE LYC O320 O320* 41508 EA CARB BOWL INOPERATIVE D K NONE O OTHER IN INSP/MAINT 1 SW 01 20 CARBURETOR BOWL SCREWS LOOSE WITH TAB LOCKS IN PLACE. LOCKS DO NOT HELP SCREWS SECURELY LETTING SCREW LOOSEN SLIGHTLY C AUSING POOR RUNNING ENGINE AND FUEL LEAK, POTENTIAL FIRE HAZARD. IMPROVE FIT OF LOCK TO HOUSING. 1 H 7 1 3O 3 O NT 3A12 E274 2002012500109 20020125 00109 CE 2002 1 25 2002FA0000009 1 20011212 G 3230 GEARBOX CESSNA 402 402B 207590P CE CONT O520 TSIO520E 17040 SO MLG WORN D K NONE O OTHER IN INSP/MAINT 1 WP 13 5403M 17891 402B0003 DURING GEAR EXTENSION, PILOT REPORTED A LOUD NOISE. REPORTED 3 GREEN LIGHTS FOR DOWN AND LOCK GEAR INDICATION, AND EME RGENCY LANDING ASSISTANCE WAS REQUESTED, AIRCRAFT LANDED SAFELY AND TAXIED TO THE MAINTENANCE FACILITY, UPON INSPECTION OF THE LANDING GEAR SYSTEM, THE REDUCTION GEAR UNIT WAS FOUND TO BE WORN AND THE CAUSE OF THE LOUD NOISE. TOOTHED PART OF THE UNIT WAS REPLACED GEAR UP AND DOWN. CHECKS WERE PERFORMED, IAW MM AND FOUND TO BE IN LIMITS. AIRCRAFT LOG BOOK ENTRY WAS MADE AND RELEASED TO SERVICE. 1 L 7 2 3O 3 O A7CE E8CE 2002012500110 20020125 00110 SO 2002 1 25 2002FA0000010 2 20011210 G 8530 534398 EXHAUST ROCKER CESSNA 182 182L 2072726 CE CONT O470 O470R 17026 SO ENGINE MISMANUFACTURED D K NONE W INADEQUATE Q C IN INSP/MAINT 1 NM 02 42862 189 18259222 THE INSTALLED EXHAUST ROCKERS WERE PN 534398. THEY EXPLAINED THAT THOSE ROCKERS DID NOT HAVE THE HOLE DRILLED TO SQUIRT OIL ON THE EXHAUST VALVE STEM. THE NEW EXHAUST ROCKER HAS THAT SQUIRTER HOLE TO AID IN LUBRICATION. THIS WAS CAUSE OF FAILURE, PER MFG. NEW EXHAUST ROCKER IS PN 641682 (2 PIECE BUSHING) OR PN 652130 (1 PIECE BUSHING). SOME REPAIR SHOPS MODIFY OLD PART NUMBER ROCKER ARM BY DRILLING THE SQUIRTER HOLE. OLD ROCKER ARMS (PN 534398) WERE INSTALLED IN THE ENGI NE FOR AT LEAST THE PREVIOUS 1400 HOURS PRIOR TO THE OVERHAUL AND DID NOT CAUSE PREMATURE VALVE OR GUIDE WEAR. 1 H 7 1 3O 3 O NT 3A13 E273 2002012500111 20020125 00111 SO 2002 1 25 2002FA0000011 2 20011210 G 8530 643767 GUIDE CESSNA 182 182L 2072726 CE CONT O470 O470R 17026 SO CYLINDER WORN D K NONE O OTHER IN INSP/MAINT 1 NM 02 42862 189 18259222 COMPRESSION TEST INDICATED NR 1 AND NR 2 CYLINDERS HAVE EXHAUST LEAKS. REMOVED CYLINDERS AND DIMENSIONALLY INSPECTING VALVES AND GUIDES. SEVERE WEAR OF BOTH GUIDE AND VALVE. 1 H 7 1 3O 3 O NT 3A13 E273 2002012500112 20020125 00112 SO 2002 1 25 2002FA0000012 2 20011210 G 8530 652956 VALVE CONT CESSNA 182 182L 2072726 CE CONT O470 O470R 17026 SO CYLINDER WORN D K NONE O OTHER IN INSP/MAINT 1 NM 02 42862 189 18259222 COMPRESSION TEST INDICATED NR 1 AND NR 2 CYLINDERS HAVE EXHAUST LEAKS. REMOVED CYLINDERS AND DIMENSIONALLY INSPECTING V ALVES AND GUIDES. SEVERE WEAR OF BOTH GUIDE AND VALVE. 1 H 7 1 3O 3 O NT 3A13 E273 2002012500113 20020125 00113 CE 2002 1 25 2002FA0000013 1 20011112 G 7120 45A34361005 MOUNT BEECH MU300 400A 1155402 CE PWA JT15 JT15D5 52112 NE ENGINE CRACKED D K NONE O OTHER IN INSP/MAINT 1 SO 11 712TA 2799 RK186 WHILE PERFORMING A ROUTINE SCHEDULED INSPECTION, INSPECTORS NOTED THE LT FORWARD ENGINE MOUNT TO BE CRACKED. 2 H 7 2 4F 4 F RT A16SW E25EA 2002012500114 20020125 00114 EA 2002 1 25 2002FA0000015 2 20011024 G 8520 75089 PISTON LYC O320 O320D2G 41508 EA ENGINE MISMANUFACTURED D K NONE O OTHER IN INSP/MAINT 1 SO 01 DURING INSTALLATION OF NEW PISTON AND RINGS. IT WAS NOTED THAT ONE OF THE PISTONS WOULD ONLY SLIDE INTO THE BARREL HALF WAY. PISTON SKIRT OD WERE CHECKED, OK AT 5.1175 OD. THE PROBLEM WAS FOUND TO BE THE OD OF THE PISTON JUST BELOW THE P ISTON PIN WAS MEASURED TO BE 5.1255 ON THE PISTON THAT DID NOT FIT, THIS IS MUCH LARGER THAN THE SAME OD OF PISTONS THAT DID FIT WHICH WAS MEASURED TO BE 5.1025. 3 O E274 2002012500115 20020125 00115 EU 2002 1 25 2002FA0000016 1 20011211 G 2910 HOSE BRAERO DH125 HS125700A 4230170 EU GARRTT TFE731 TFE731* 01518 WP HYD SYSTEM CORRODED G K NONE O OTHER IN INSP/MAINT 1 SO 17 731DL NA0234 HEAVY CORROSION BUILD UP UNDER OUTER PLASTIC SLEEVE ON EXTERIOR HYDRAULIC SYSTEM FLEX HOSES MOSTLY IN THE LANDING GEAR A REA DUE TO WATER OR DISSIMILAR METAL. THIS ONLY NOTED ON 700 SERIES AIRCRAFT. REC. SB OR SL TO LOOK FOR BULGING AT MET AL BRAID HOSE WHERE HOSE MEETS THE (B) NUT FITTING. 2 L 7 2 4F 4 F A3EU E6WE 2002012500118 20020125 00118 EU 2002 1 25 2002FA0000017 1 20011214 G 3230 259UM95 TORQUE LINK BRAERO 1000 HAWKER1000 7450005 EU MLG CRACKED B RO3R K NONE O OTHER IN INSP/MAINT 1 CE 03 DURING OVERHAUL, INSPECTION PROCESSES ARE IDENTIFYING CRACKS IN THE FLANGE / WEBBING AREAS OF THE STEEL TORQUE LINKS (PN 25-9UM9-5) FOR THE MAIN LANDING GEAR. CRACKS HAVE BEEN FOUND ON FOUR(4) OF THE LINKS, WHICH HAVE BETWEEN 3967 AND 5603 CYCLES SINCE REPLACEMENT. 2 L 7 2 4F RT A3EU 2002012500119 20020125 00119 CE 2002 1 25 2002FA0000018 1 20011212 G 2421 BOLT PRESTOLITE CESSNA 421 421B 2076014 CE CONT O520 GTSIO520H 17032 SO ALTERNATOR LOOSE D K NONE O OTHER IN INSP/MAINT 1 GL 07 421PK 44 A119964 421B0830 22441373H ALTERNATOR THRU BOLT CAME OUT AND ARCED ON STATOR TERMINAL. INSPECTED ALTERNATOR AND REINSTALLED ALTERNATOR BOLT. CHEC KED TORQUE ON REMAINING BOLTS. SUGGEST BENDING LOCK TABS OVER PROPERLY AFTER TORQUING BOLTS. 1 L 7 2 3O 3 O A7CE E7CE 2002012500120 20020125 00120 SO 2002 1 25 2002FA0000019 1 20011218 G 5530 1610303 BRACKET PIPER PA23 PA23250 7102308 SO LYC O540 IO540* 41532 EA VERTICAL STAB CRACKED B K NONE O OTHER IN INSP/MAINT 1 WP 17 6249Y 3132 273487 L1981948 VERTICAL STAB BRACKET CRACKED, OCCURRED DURING NORMAL OPERATING CONDITIONS AND WAS DISCOVERED AT APPROX. 3130 ACTT. 1 L 7 2 3O 3 O 1A10 1E4 2002012500121 20020125 00121 SO 2002 1 25 2002FA0000020 1 20011218 G 5530 1610302 BRACKET PIPER PA23 PA23250 7102308 SO LYC O540 IO540* 41532 EA VERTICAL STAB CRACKED D K NONE O OTHER IN INSP/MAINT 1 WP 17 6249Y 3132 273487 VERICAL STAB BRACKET CRACKED, OCCURRED DURING NORMAL OPERATING CONDITIONS AND WAS DISCOVERED AT APPROX 3130 AC TT. 1 L 7 2 3O 3 O 1A10 1E4 2002012500122 20020125 00122 SO 2002 1 25 2002FA0000021 2 20011126 G 8520 CONNECTING ROD CESSNA 172 172H 2072424 CE CONT O300 O300* 17022 SO ENGINE FAILED D O OTHER R PARTIAL RPM/PWR LOSS DE DESCENT 1 EA 23 3910R 17255410 NUMBER THREE CYLINDER CONNECTING ROD AND CAP FAILED AT CRANKSHAFT. THE CONNECTING ROD THEN FELL DOWN TO THE BOTTOM OF T HE CYLINDER BORE AND WAS STRUCK REPEATEDLY BY THE CRANKSHAFT UNTIL ENGINE WAS SHUTDOWN. THE FAILURE OCCURRED AFTER FINA L POWER REDUCTION DURING A ROUTINE LANDING. THE PILOT DESCRIBED HEARING A LOUD BANG FOLLOWED BY A LOSS OF POWER. CAUSE OF FAILURE UNDETERMINABLE. 1 H 7 1 3O 3 O NT 3A12 E253 2002012500124 20020125 00124 EU 2002 1 25 2002FA0000022 1 20011012 G 6520 350A33109100 GEAR AEROSP AS355 AS355* EU T/R GEARBOX MISALIGNED B FF6R K NONE O OTHER IN INSP/MAINT 1 NM 08 UNABLE TO ESTABLISH ACCEPTABLE GEAR PATTERN ON PINION. 1 G 7 2 3U H11EU 2002012500125 20020125 00125 SO 2002 1 25 2002FA0000023 2 20011113 G 8520 BEARING CESSNA 402 402B 207590P CE CONT O520 TSIO520EB 17040 SO LT ENGINE FAILED D E A ENGINE SHUTDOWN UNSCHED LANDING R J PARTIAL RPM/PWR LOSS WARNING INDICATION NR NOT REPORTED 1 SO 17 3748C 1166 402B0606 815069R IN FLIGHT FAILURE OF LT ENGINE NR 2 ROD BEARING FAILED CAUSING CASE DAMAGE. ROUGH RUNNING AND OIL LOSS. PILOT SHUT DOW N ENGINE AND MADE A SUCCESSFUL LANDING TBO IS 1400 HR. ENGINE HAD 1166.9 SINCE FACTORY REMANUFACTURE. 1 L 7 2 3O 3 O A7CE E8CE 2002012500126 20020125 00126 CE 2002 1 25 2002FA0000024 1 20011214 G 6120 C2995060102 CONTROL CABLE CESSNA 182 182M 2072728 CE CONT O470 O470R 17026 SO PROPELLER BROKEN G K NONE O OTHER IN INSP/MAINT 1 CE 01 71398 3695 18259607 2000529R PILOT COMPLAINED THAT THE PROPELLER CONTROL WAS HARD TO MOVE. WHEN TECHNICIAN INVESTIGATED, THE CONTROL CABLE BROKE AND CAME OFF IN TECHNICIAN`S HAND. REMOVED AND REPLACED CONTROL WITH NEW PART. 1 H 7 1 3O 3 O NT 3A13 E273 2002012500131 20020125 00131 EU 2002 1 25 2002FA0000026 1 20011203 G 2435 23091004 STARTER GEN ISRAEL GALAXY GALAXY 4500307 EU ENGINE FAILED G O OTHER O OTHER NR NOT REPORTED 1 GL 25 35BP 016 STARTER GEN FAILED. 2 L 7 2 4F RT A53NM 2002012500132 20020125 00132 EU 2002 1 25 2002FA0000027 1 20011214 G 4930 FB9682 FUEL BOWL HWKSLY DH125 HS125600A 4230158 EU GARRTT TFE731 TFE731* 01518 WP APU CONTAMINATED D K NONE O OTHER IN INSP/MAINT 1 NE 05 800NM 256027 DURING SCHEDULED INSPECTION AND FILTER CHANGE, EXCESSIVE CONTAMINATION FOUND IN FILTER BOWL ASSEMBLY. 2 L 7 2 4J 4 F A3EU E6WE 2002012500133 20020125 00133 CE 2002 1 25 2002FA0000028 1 20010714 G 2810 41424 FUEL CELL CESSNA 414 414 2075908 CE CONT O520 TSIO520* 17040 SO RT WING ROTTED D K NONE O OTHER IN INSP/MAINT 1 SW 17 127BC 4140519 RIGHT OUTBOARD WING FUEL CELL (PN 4142-4) REPLACES (PN 5026102-4). FUEL CELL IS 11 YEARS OLD. MPG, DATE 2-90. FUEL CE LL CAME APART (TOTALLY ROTTEN AND BRITTLE) AT TOP OF FILLER NECK. FUEL CELL WAS MADE OF DIFFERENT MATERIAL, NOT OF THE NORMAL RUBBER. BAD TANK FOUND. 1 L 7 2 3O 3 O RT A7CE E8CE 2002011800031 20020118 00031 SW 2002 1 18 2002FA0000029 1 20010730 G 6220 222012104101 PITCH HORN BELL 230 230 1182149 SW ALLSN 250C 250C30 03013 GL MAIN ROTOR CRACKED D K NONE O OTHER IN INSP/MAINT 1 NM 09 230LF 2714 23017 CRACK FOUND ON MAIN ROTOR GRIP AT BOLT HOLE WHERE GRIP ATTACHES TO PITCH HORN. CRACK EXTENDED FROM BOLT HOLE FOR 1.5 FE ET TO OUTSIDE OF GRIP. 1 G 7 2 3U 3 U NC H9SW E1GL 2002012500134 20020125 00134 EU 2002 1 25 2002FA0000030 1 20010101 G 5320 4A53360284001 FITTING ISRAEL GALAXY GALAXY 4500307 EU DOOR STRUT BROKEN D K NONE O OTHER IN INSP/MAINT 1 GL 25 83EJ 1100 009 FITTING HOLDS CABIN ENTRANCE DOOR AIR SPRING. SPRING GIVES DOOR SUPPORT DURING OPENING. DOOR SUPPORT DURING OPENING, F ITTING BROKE ALLOWING DOOR WEIGHT TO HAVE TO BE SUPPORTED BY CREW. PART TT 1100 HRS 2 L 7 2 4F RT A53NM 2002012500135 20020125 00135 EU 2002 1 25 2002FA0000031 1 20010101 G 8011 23091004 STARTER ISRAEL GALAXY GALAXY 4500307 EU ENGINE FAILED D K NONE O OTHER IN INSP/MAINT 1 GL 25 83EJ 009 STARTERS ARE FAILING WITH ONLY 200 TO 300 HOURS. 2 L 7 2 4F RT A53NM 2002012500137 20020125 00137 CE 2002 1 25 2002FA0000032 1 20011228 G 3211 513210P24 BUSHING CESSNA 402 402B 207590P CE CONT O520 TSIO520E 17040 SO MLG BRACE CORRODED D K NONE O OTHER IN INSP/MAINT 1 WP 13 98692 402B1050 L275471R BEARING PART OF BUSHING, NOT TAKING GREASE. DISASSEMBLE AND PHYSICALLY INSPECT BOTH. FOUND CORRODED 1 L 7 2 3O 3 O A7CE E8CE 2002012500138 20020125 00138 SO 2002 1 25 2002FA0000035 1 20011214 G 7714 598881 PICKUP PIPER PA32 PA32R301T 7103220 SO LYC O540 TIO540* 41532 EA ENGINE TACH MISMANUFACTURED C K NONE O OTHER IN INSP/MAINT 1 WP 07 298AT 418 3257069 L1006661A REMOVED MAGS FOR 500 HR INSPECTION, NYLON GEARS IN LT MAG DETERORATING, FROSTED APPEARANCE ON BOTH DISTRIB AND CAM GEARS . MAG HAS ELECT TACH PICK UP IN PLACE OF NORMAL MAG VENT. 1 L 7 1 3O 3 O A3SO E14EA 2002012500139 20020125 00139 CE 2002 1 25 2002FA0000036 1 20011228 G 3310 0713247200 RHEOSTAT CESSNA 172 172H 2072424 CE CONT O300 O300* 17022 SO CABIN BURNED D K NONE L NO TEST IN INSP/MAINT 1 GL 19 3297L 17256197 SMOKE IN COCKPIT, COMING FROM OVERHEAD. TURNED OFF RADIO LIGHT RHEOSTAT AND INSTRUMENT LIGHT RHEOSTAT. SMOKE THEN QUIT . INVESTIGATION FOUND RADIO LIGHT RHEOSTAT WAS OVERHEATING AND SMOKING. RHEOSTAT WAS REMOVED. 1 H 7 1 3O 3 O NT 3A12 E253 2002012800001 20020128 00001 EU 2002 1 28 2002FA0000038 1 20010606 G 2121 M3348A MOTOR DYNAMICAIR SAAB SF340 SF340A 7850100 EU GE CT7TP CT75A 30030 NE FAN MISREPAIRED D K NONE W INADEQUATE Q C IN INSP/MAINT 1 WP 15 69LP 217 340AO69 FAN RETURNED TO MFG FOR UPGRADE TO C209-6901) CONFIGURATION. FAN WAS DISAS AND FOUND TO BE NOT OVERHAULED PER REQUIRED MM. ARMAT AND WINDINGS NOT OF MFG DESIGN. MM DOES NOT ALLOW FOR REWINDING OF ARMAT FIELD WINDINGS, OR REPLACEMENT OF P ARTS OTHER THAN LISTED. ARMAT ASSY STACK LENGTH IS TOO SHORT, THE IMPELLER IS GLUED ON, COMMUTATOR IS UNDERSIZE AND AIR GAP BETWEEN IMPELLER AND WINDINGS IS TOO SMALL. VENT HOLES IN MTR ARE ENLARGED CAUSING REDUC AIR FLOW THROUGH MTR CAUS ING BRUSH HOLDERS TO OVERHEAT. END BELL IS MODI NOT TO REQMT. THREADED BAR WAS USED TO HOLD MOTOR TO HOUSING INSTEAD O F REQUIRED BOLTS. FILTER IS REWORKED (UNSERVICABLE PART). POS STUD IS LOOSE AND NOT MAKING ELECTRIC CONTACT. 2 L 7 2 4T 4 T RT A52EU E8NE 2002012800003 20020128 00003 CE 2002 1 28 2002FA0000040 1 20011206 G 3230 PIVOT ASSY CESSNA 182 R182 2072734 CE LT MLG CRACKED D K NONE K FLUID LOSS IN INSP/MAINT 1 SW 15 757KP R18201242 FORWARD BEARING AREA OF LEFT MAIN GEAR PIVOT WAS DETERMINED TO BE CRACKED AND LEAKING BREAK FLUID. THE PIVOT ASSEMBLY W AS REPLACED WITH A USED SERVICEABLE PIVOT ASSEMBLY OF THE SAME PART NUMBER. 1 H 7 1 3O RT 3A13 2002012800004 20020128 00004 SO 2002 1 28 2002FA0000041 1 20010821 G 3220 40336000 DRAG LINK PIPER PA31 PA31350 7103110 SO LYC O540 TIO540* 41532 EA NLG BROKEN B BX4R K NONE O OTHER IN INSP/MAINT 1 NM 03 114SA 13729 318052053 RIGHT NOSE GEAR DRAB LINK FAILED JUST FORWARD OF WHERE GEAR ACTUATOR ATTACHES. 1 L 7 2 3O 3 O A20SO E14EA 2002012800005 20020128 00005 GL 2002 1 28 2002FA0000042 1 20011113 G 5210 6E21 HOOK ZENITH AMTR CH601 ZODIAC GL CANOPY LOCK MALFUNCTIONED D O OTHER D INFLIGHT SEPARATION NR NOT REPORTED 1 GL 17 324DZ 18 63682 NO FLAW FOUND ON LOCK HOOK. CANOPY SEPARATED FROM FUSELAGE IN STRAIGHT AND LEVEL FLIGHT. 1 L 7 1 3O NC EXPA1L71 2002012800006 20020128 00006 EA 2002 1 28 2002FA0000043 2 20010418 G 8500 ENGINE GIPPLD GA200 GA200 EU LYC O540 O540A1D5 41532 EA NACELLE FAILED C E ENGINE SHUTDOWN R J PARTIAL RPM/PWR LOSS WARNING INDICATION LD LANDING 1 SW 15 280GA 451 2009825F ENGINE ACTED AS THOUGH CARBURETOR ICE WAS BEING CLEARED WITH CARBURETOR HEAT ON. LANDED UNEVENTFULLY. AT TOUCHDOWN, CO ULD HEAR A LOUD SQUEAK. AT ENGINE SHUT DOWN, ENGINE STOPPED AS THOUGH A BRAKE WAS APPLIED. PROP WAS DIFFICULT TO TURN BY HAND. ALUMINUM AND FERROUS METAL WAS FOUND IN OIL SCREEN, FILTER AND OIL COOLER. 1 L 7 1 3O 3 O NC A00001LA E295 2002011600001 20020116 00001 NE 2002 1 16 2002FA0000044 2 20010707 G 7200 TIE ROD PWA JT8 JT8D15A 52051 NE SIXTH STAGE FAILED W K NONE O OTHER IN INSP/MAINT 1 EA 01 GCEAF 686373 CREW REPORTED HIGH VIBRATION IN CRUISE AT FL 330. GROUND RUNS CARRIED OUT AND VIBRATION CONFIRMED. ENG HEARD TO BE MAK ING A METALLIC SCRAPING SOUND WHEN TURNED BACKWARDS. SIG DAMAGE WAS FOUND WHILE BORESCOPING. INSP OF 6TH STAGE REVEALE D THAT REAR TIEROD HAD FAILED AND WAS STUCK IN GASPATH BETWEEN C6 BALDES AND INTERMEDIATE CASE VANES. ONE TIE ROD FAILE D IN 4TH STG LAND. FRNT REMAINED IN PLACE WHILE REAR PART MOVED AFT. REAR END OF TIEROD MANAGED TO COME OUT OF TIEROD HOLE. BROKEN OFF TIEROD PART CAME OUT OF TIEROD HOLE, THEN PUNCTURED INTERM CASE WHILE TIEROD HEAD STAYED IN CONTACT WI TH C6 DISK OUTER RIM. EXTENSIVE SECONDARY DAM CAUSED TO AIRFOILS DOWN STREAM OF C6 BY BROKEN OFF FRAGMENTS OF BLD LOCKS 4 F E2EA 2002012800007 20020128 00007 CE 2002 1 28 2002FA0000045 1 20010403 G 3252 0842102 SHIMMY DAMPENER CESSNA 310 310J 2074226 CE NLG DAMAGED G O OTHER O OTHER TX TAXI/GRND HDL 1 SO 15 63GG 4878 310J0152 PILOT MADE A HARD LEFT TURN CAUSEING DAMAGE TO THE NOSE GEAR AREA. BENT ROD ON THE SHIMMY DAMPER CAUSING INTERNAL DAMAG E TO THE COMPONENT. 1 L 7 2 3O 3A10 2002011800032 20020118 00032 SW 2002 1 18 2002FA0000048 1 20010804 G 6420 47LM2505 UNIVERSAL JOINT BELL 47 47G5 1181032 SW ALLSN 250C 250C* GL TAIL ROTOR FAILED C LPGG K NONE O OTHER IN INSP/MAINT 1 GL 21 2251W 559 7965 CAE801089B WAS INVOLVED IN AERIAL APPLICATION, ON A SPRAY RUN PILOT NOTICED THAT HE WAS PICKING UP VIBRATION IN TAIL ROTOR CONTROL PEDALS AND CEASED SPRAY OPERATIONS. CAME IN FOR LANDING AND AT HOVER IS WHEN THE U-JOINT FAILED. HELICOPTER TURNED 180 DEGREES BEFORE LANDING. NO DAMAGE TO AIRCRAFT. PART THAT FAILED INSPECTED DAILY. LUBRICATED EVERY 10-15 HOURS. AFTE R EXAMINING FAILED U-JOINT, FOUND THAT ONLY HALF OF JOINT WAS RECEIVING ANY GREASE. DONT KNOW HOW LONG THIS CONDITION O F NO GREASE WAS HAPPENING. 1 G 7 1 3O 3 U 2H3 E4CE 2002012800009 20020128 00009 NM 2002 1 28 2002FA0000049 1 20010705 G 3240 SHUTTLE VALVE DHAV DHC8 DHC8202 2809007 NM PWA PW120 PW123 NE MLG BRAKE MALFUNCTIONED D D RETURN TO BLOCK A FLAME/FIRE TX TAXI/GRND HDL 1 WP 07 347PH 9490 65 480 RT OUTBOARD BRAKE LOCKED UP DURING TAXI AND CAUSED BRAKE FIRE. VALVE WAS PLACED ON TEST STAND AND REPEATEDLY TESTED VIG OROUSLY FOR 50 MINUTES PER OEMS ATP. NO PROBLEMS WERE NOTED. VALVE WAS THEN TORN DOWN AND INSPECTED. ONLY IRREGULARIT Y FOUND WAS LOOSE SCREEN IN FILTER FITTING ON INLET PORT. THIS COULD HAVE CAUSED PROBLEM ON OUTLET PORT. IT IS INCONC LUSIVE AS TO THIS VALVE CAUSING THE LOCKUP, BUT FILTER WAS REPLACED AND ONCE AGAIN VALVE TESTED GOOD. ALL FILTERS ON AL L VALVES NEED TO BE VERY THOROUGHLY INSPECTED. 2 H 7 2 4T 4 T RT A13NM E20NE 2002012800010 20020128 00010 SO 2002 1 28 2002FA0000051 1 20011031 G 5520 5161802 BALANCE WEIGHT PIPER PA31T PA31T1 7103126 SO ELEVATOR CRACKED D K NONE O OTHER IN INSP/MAINT 1 NM 09 824VA 4825 31T8104039 DURING INSPECTION, FOUND RIGHT ELEVATOR BALANCE WEIGHT HAD A CRACK IN TO LEAD WEIGHT BEHIND THE REAR MOUNTING BOLT. WIT H WEIGHT REMOVED THE CRACK COULD BE EXPANDED BY HAND. (K) 1 L 7 2 3T A8EA 2002012800011 20020128 00011 EA 2002 1 28 2002FA0000052 2 20011230 G 7322 CF30766 FLOAT MARVELSCHEBX CESSNA 150 152 2071835 CE LYC O235 O235* 41505 EA CARBURETOR FAILED G O OTHER Y J ENGINE STOPPAGE WARNING INDICATION LD LANDING 1 NE 03 65463 CR15647 15281566 ON LANDING THE ENGINE QUIT. FUEL WAS OBSERVED LEAKING FROM THE AIRCRAFT. DURING DISASSEMBLY OF THE CARBURETOR IT WAS N OTED BOTH FLOATS WERE FILLED WITH FUEL CAUSING FUEL TO POUR THRU THE VENT. THE MANUFACTURE DATE OF THE FLOAT WAS 4/92. 1 H 7 1 3O 3 O NT 3A19 E223 2002012800012 20020128 00012 CE 2002 1 28 2002FA0000053 1 20010122 G 5610 10138402522 WINDSHIELD BEECH 300 300BEECH 1152930 CE PWA PT6 PT6A60A 52043 NE COCKPIT CRACKED D K NONE O OTHER IN INSP/MAINT 1 NM 02 200WB 140 FA5 WINDSHIELD DEVELOPED CRACK IN OUTER PLY AT LOWER CENTER CORNER, CRACKING APPEARED CIRCUMFRONTIAL AT APPROXIMATELY 5 FEE T 6 INCHES. WINDSHIELD WAS INSTALLED WITH MFG KIN NR 101-5041-1S. 2 L 7 2 4T 4 T A24CE E4EA 2002012800015 20020128 00015 CE 2002 1 28 2002FA0000056 1 20010109 G 2750 PIN CESSNA 501 501 2076603 CE PWA JT15 JT15D1 52060 NE TE FLAP GEARBOX SHEARED B BGSR K NONE O OTHER IN INSP/MAINT 1 EA 21 597CS 5010293 THE SHEAR PIN CONNECTING THE FLAP DRIVE MOTOR TO THE FLAP GEARBOX SHEARED OFF AS THE CREW ATTEMPTED TO POSITION FLAPS TO 2ND POSITION. AFTER INVESTIGATION, THE FLAP GEAR BOX WAS DETERMNED TO BE DEFECTIVE. 1 L 7 2 4F 4 F A27CE E1NE 2002011800019 20020118 00019 EU 2002 1 18 2002FA0000067 1 20011022 G 7810 0292808700 EXHAUST STACK SNIAS 350 AS350BA 8680817 EU ENGINE CRACKED A O OTHER O OTHER NR NOT REPORTED 1 WP 19 270SH 958 1864 ENGINE EXHAUST IS CRACKED. INSTALLED SERVICEABLE EXHAUST STACK. (M) 1 G 7 1 3U NC H9EU 2002011800020 20020118 00020 EU 2002 1 18 2002FA0000068 1 20011018 G 6410 350A33215300 BEARING SNIAS 350 AS350* EU TAIL ROTOR CUT A O OTHER O OTHER NR NOT REPORTED 1 WP 19 115SH 640 3141 BEARING HAS DEEP CUT, DELAMINATION. REPLACED WITH NEW BEARING. (M) 1 G 7 1 3U H9EU 2002011800021 20020118 00021 2002 1 18 2002FA0000069 4 20011017 G 3422 RCA15BR1 GYRO SNIAS 350 AS350BA 8680817 EU COCKPIT INOPERATIVE A O OTHER O OTHER NR NOT REPORTED 1 WP 19 230SH 11 2337 DIRECTIONAL GYRO INOPERATIVE. REPLACED WITH SERVICEABLE UNIT. (M) 1 G 7 1 3U NC H9EU 2002011800022 20020118 00022 2002 1 18 2002FA0000070 4 20011011 G 3422 RCA15BK1 GYRO SNIAS 350 AS350BA 8680817 EU COCKPIT PRECESSES A O OTHER O OTHER NR NOT REPORTED 1 WP 19 230SH 319 2337 DIRECTIONAL GYRO PRECESSES CONTINUOUSLY. REPLACED WITH SERVICABLE UNIT. (M) 1 G 7 1 3U NC H9EU 2002011800023 20020118 00023 EU 2002 1 18 2002FA0000071 1 20011016 G 3110 704A47270101 INDICATOR SNIAS 350 AS350BA 8680817 EU COCKPIT INTERMITTENT A O OTHER O OTHER NR NOT REPORTED 1 WP 19 37SH 1221 2300 FUEL PSI READING INTERMITTENT. FURTHER TROUBLESHOOTING FOUND BAD GROUND WIRE, THIS UNIT IS TO BE RESTOCKED. INSTALLED SERVICEABLE INSTRUMENT CLUSTER. (M) 1 G 7 1 3U NC H9EU 2002011800024 20020118 00024 SW 2002 1 18 2002FA0000072 1 20010828 G 6510 407340339101 BEARING BELL 407 407 1182206 SW MAIN ROTOR WORN B O OTHER O OTHER NR NOT REPORTED 1 SW 03 404AL 53479 BEARING SHOWING SIGNS OF WEAR AND BEGINNING SIGNS OF OVERTEMP. SCRAPPED BEARING. (M) 1 G 7 1 3U O H2SW 2002011800025 20020118 00025 NE 2002 1 18 2002FA0000073 2 20010807 G 7250 23053299 TURBINE WHEEL SKRSKY S76 S76 8143010 NE ALLSN 250C 250C40B 03032 NE ENGINE CORRODED B O OTHER O OTHER NR NOT REPORTED 1 SW 03 707AL 1110 760189 TURBINE CAME IN FOR SHOP VISIT FOR LOW POWER. BEGAN DISASSEMBLY OF TURBINE, REMOVED OUTER COMBUSTION CASE AND FOUND SUL FIDATION ON 1ST STAGE WHEEL. HAD ONE BLADE MISSING AND SEVERAL BROKEN BLADES. THIS TURBINE HAD A ROLLS ROYCE LINER. H AVE WHEELS TESTED FOR PROPER COATING. (M) 1 G 7 2 3U 3 U H1NE E1GL 2002011800026 20020118 00026 SW 2002 1 18 2002FA0000074 1 20011002 G 5330 206010200133 SKIN BELL 206 206B 1181511 SW FUSELAGE CORRODED B K NONE O OTHER IN INSP/MAINT 1 SW 03 5743B 3310 3056 DISCOVERED DURING ROUTINE AIRFRAME INSPECTION, LOWER SKIN CORRODED AND SEPARATED BENEATH OUTBOARD GRIP FINGER DOUBLER. (M) 1 G 7 1 3U H2SW 2002011800027 20020118 00027 GL 2002 1 18 2002FA0000075 2 20010822 G 7250 6895801 TURBINE WHEEL BELL 206 206L1 1182107 SW ALLSN 250C 250C28B 03013 GL ENGINE CORRODED B O OTHER O OTHER NR NOT REPORTED 1 SW 03 2025G 987 45690 WHEN TURBINE CAME IN FOR NR 3 AND NR 4 WHEEL CHANGE AND VISUAL INSPECTION ON TURBINE HOT END. NR 1 WHEEL SHOWED EARLY A TTACH OF SULFIDATION. HAVE WHEEL TESTED FOR PROPER COATING. (M) 1 G 7 1 3U 3 U H2SW E1GL 2002011800028 20020118 00028 EU 2002 1 18 2002FA0000076 1 20010808 G 6320 4649010006 CASE UROCOP EC135 EC135T1 5620026 EU M/R GEARBOX DAMAGED A O OTHER O OTHER NR NOT REPORTED 1 EA 03 511ME 547 0143 FOUND HOLE IN MAIN GEARBOX CASING. (M) 1 G 7 2 3U H88EU 2002012800017 20020128 00017 2002 1 28 2002FA0000078 4 20010918 G 3197 PQ876SW RING CESSNA 172 172M 2072418 CE LYC O320 O320* 41508 EA WIRE BURNED D K NONE O OTHER IN INSP/MAINT 1 GL 13 1368U 317 17267039 PART WAS INSTALLED AROUND TACH AND CONNECTED TO REOSTATE FOR THE INSTRUMENT LIGHTS. IT SHORTED OUT THE SYSTEM AND BURNE D OUT REOSTATE-S2091-5 AND POWER TRANSISTER 2N3055. THIS CAUSED NO INSTRUMENT LIGHTS IN AIRCRAFT. OWNER NOTICED NO LIG HTS AND NOTIFIED TECHNICIAN. TROUBLESHOOTING THE SYSTEM TECH FOUND THAT WIRES ON TOP OF RING WAS TOUCHING ONE ANOTHER, CAUSING A DIRECT SHORT. 1 H 7 1 3O 3 O NT 3A12 E274 2002012800018 20020128 00018 EA 2002 1 28 2002FA0000079 2 20010930 G 7414 M3635 IMPULSE COUPLING SLICK PIPER PA25 PA25235 7102504 SO LYC O540 O540B2C5 41532 EA MAGNETO SEPARATED D E ENGINE SHUTDOWN D K INFLIGHT SEPARATION FLUID LOSS TX TAXI/GRND HDL 1 EA 33 8903L 230 255364 L121180 DURING GROUND RUN, OPERATOR NOTED A LOUD BANG AND SUDDEN OIL LEAKAGE. AFTER SHUT DOWN FOUND THAT LT MAGNETO CAME OFF TH E ACCESSORY HOUSING, CAUSING OIL LEAK. BANG WAS CAUSED BY MAG HOUSING WHICH CAME APART AT UPPER ATTACHMENT AREA (ATACHM ENT LUG). 1 L 7 1 3O 3 O 2A10 E295 2002012800019 20020128 00019 WP 2002 1 28 2002FA0000083 1 20011016 G 7922 53E22144 VERNATHERM ROBSIN R44 R44 7640120 WP LYC O540 O540F1B5 41532 EA OIL COOLER STUCK D O OTHER M J OVER TEMP WARNING INDICATION NR NOT REPORTED 1 NE 05 8353K 797 0348 L2507840A HIGH OIL TEMPERATURES, AT RED LINE 245 DEGREES, VERIFIED BY DECREASE IN OIL PRESSURE. FOUND VALVE STUCK, NOT EXTENDING. REMOVED AND REPLACED WITH NEW PART. OPS CHECKED GOOD. 1 G 7 1 3O 3 O H11NM E295 2002012800022 20020128 00022 CE 2002 1 28 2002FA0000088 1 20011211 G 5210 07110271 HANDLE CESSNA 182 182D 2072710 CE CONT O470 O470* 17026 SO CREW DOOR STRIPPED D K NONE O OTHER IN INSP/MAINT 1 WP 01 9109X 18253509 WHILE INVESTIGATING A COMPLAINT OF A DEFECTIVE DOOR LATCH IT WAS DISCOVERED THAT THE INTERNAL SPLINES OF THE DOOR HANDLE WERE STRIPPED. 1 H 7 1 3O 3 O NT 3A13 E273 2002012800023 20020128 00023 CE 2002 1 28 2002FA0000089 1 20011119 G 5260 STRUT CESSNA 310 310Q 2074242 CE CONT O470 IO470* 17026 SO AIRSTAIR BROKEN D K NONE O OTHER IN INSP/MAINT 1 NE 02 8TC 310Q0264 MAINTENANCE PERSONNEL ATTEMPTED TO BOARD AIRCRAFT WHEN MOUNTING STEP STRUT ASSEMBLY BROKE AWAY. WELD ASSEMBLY (PN 08119 46-23) FAILED COMPLETELY AT UPPER STEP. INDICATIONS OF A PRE EXISTING CRACK AROUND ONE THIRD OF THE CIRCUMFERENCE OF TH E TUBE. NO SIGNS OF RUST BLEED THROUGH AT THE EXTERIOR PAINT. STEP MOUNTING SCREW SPACERS MISSING AT UPPER STEP. 1 L 7 2 3O 3 O 3A10 E1CE 2002012800031 20020128 00031 NM 2002 1 28 2002FA0000091 1 20010627 G 2612 088131007 SWITCH BOEING 737 737* NM FIRE DETECTION SHORTED B O OTHER O OTHER NR NOT REPORTED 1 SW 99 XAAEX 6 32774 SWITCHES SHORTED INTERNALLY. SHOULD RETURN TO N/O CONDITION. LOOKS LIKE MICROSWITCH FAILED INTERNALLY IN ASSY. REMOVE D AND REPLACED SWITCHES, RETESTED NO MALFUNCTION OR DEFECTS NOTED. FIRE BELL CUTOUT SWITCHES AND SYSTEM OPS CHECKED GOO D. (M) 2 L 7 2 4F RT A16WE 2002012800033 20020128 00033 CE 2002 1 28 2002FA0000092 1 20011219 G 2730 676033215 TIE ROD CESSNA 750 750 2076810 CE RT ELEVATOR STIFF C K NONE O OTHER IN INSP/MAINT 1 NM 09 551AM 262 262 7500155 DURING INSPECTION AND PERFORMANCE, BEARING ROD END LUBRICATION, P/N 676033215 TIE ROD, INTERCONNECTING THE TWO OUTBOARD ELEVATOR BELLCRANKS, WAS FOUND TIGHT AND NOT ABLE TO ROTATE SLIGHTLY ABOUT ITS LONGITUDINAL AXIS. IT WAS DISCOVERED THA T THE ROD ENDS, WHICH ARE RIVETED TO THE MAIN TUBE AND NOT ADJUSTABLE, WERE MISALIGNED WITH EACH OTHER---NOT IN THE SAM E PLANE. WHEN ATTACHED TO THE BELLCRANKS, THE ROD ENDS WERE PINCHED AGAINST THE BELLCRANK EARS INSTEAD OF JUST THE SPHER ICAL BEARING. NO DAMAGE WAS NOTED ON THE BELLCRANK EARS, HOWEVER, FUTURE PROBLEMS MIGHT ARISE AS THE TIE ROD AND OTHER P USHROD AND BUNGEE ROD ENDS IN THIS SYSTEM ARE SUBJECT TO ROD END BEARING CORROSION. TIE ROD WAS REPLACED WITH NEW PART W 2 L 7 2 4J RT T00007WI 2002012400033 20020124 00033 GL 2002 1 24 2002FA0000095 1 20011210 G 3213 3525151004 FORK AMTR GLASAR GLASAIRIISTD 05602E5 GL MLG BROKEN G O OTHER O OTHER LD LANDING 1 GL 07 225S 918 40 DURING LANDING THE AIRCRAFT VEERED OFF TO THE RIGHT SIDE OF THE RUNWAY. AN INSPECTION REVELED A RIGHT HALF FORK WAS BROK EN. THE WHEEL ATTACHES TO THIS HALF FORK WHICH ATTACHES TO THE MAIN STRUT. PER A GLASAIR REPRESENATIVE, MFG. OF THE GLAS AIR KITS FOR AMATUERBUILDERS, THIS PART IS NOW MADE OF STEEL. THE CAST ALUMINUM HALF FORK, SUCH AS THE BROKEN PART, WAS REPLACED BY THE STEEL HALF FORK ABOUT 8-10 YEARS AGO. AN UPGRADE WAS MADE AVAILABLE TO ALL THE PREVIOUS KITS FROM GLASA IR. 1 L 7 1 3O RT EXPA1L71 2002012800037 20020128 00037 EA 2002 1 28 2002FA0000096 2 20011210 G 8550 ENGINE AMRGEN AG5B AG5B 3990100 SO LYC O360 O360A4K 41514 EA SNSNCH 76E 76EM8 EA NACELLE LEAKING F O OTHER K FLUID LOSS NR NOT REPORTED 1 EA 09 999TE 68 10201 L3776336A ENGINE DEVELOPED OIL LEAK AT THE TOP OF THE CASE NEAR THE ACCESSORY CASE. LEAK BEGAN DURING INITIAL ENGINE RUN. LEAK I S APPX 1/8 QT PER 6 HRS. LEAK COULD NOT BE FIXED WITHOUT REMOVING ENGINE. 1 L 7 1 3O 3 O NT 1L71 E286 5 N P4EA 2002012400038 20020124 00038 SO 2002 1 24 2002FA0000100 2 20010921 G 7414 K3823 DISTRIBUTOR SLICK 6310 CESSNA 206 U206G 2073356 CE CONT O550 IO550F 17042 SO MAGNETO BURNED D D RETURN TO BLOCK R PARTIAL RPM/PWR LOSS TX TAXI/GRND HDL 1 SW 99 PK-MP 9 00111980 U20606987 MAGNETO FAILED - WOULD NOT RUN AT ALL. THE DISTRIBUTOR GEAR SUPPORT WAS FOUND TO BE BADLY BURNED FROM SPARKS GOING FROM THE THE SHAFT TO GROUND ON THE M3485 BEARING CAP BY ARCING ACROSS THE SUPPORT. SUPPORT IS BADLY MELTED. M3215 CARBON BRUSH IS BURNED ALSO. DISTRIBUTOR BLOCK AND GEAR ARE COATED WITH A WHITE DEPOSIT MATERIAL WHICH IS ALSO SEEN SPATTERED INSIDE THE MAGNETO HOUSING AND ON THE COIL. 1 H 7 1 3O 3 O A4CE E3SO 2002012400039 20020124 00039 SO 2002 1 24 2002FA0000101 2 20010925 G 7414 K3823 DISTRIBUTOR SLICK 6310 CESSNA 206 U206G 2073356 CE CONT O550 IO550F 17042 SO MAGNETO BURNED D D RETURN TO BLOCK R PARTIAL RPM/PWR LOSS TX TAXI/GRND HDL 1 SW 99 PKMPT 12 00111983 U20606987 MAGNETO FAILED - WOULD NOT RUN AT ALL. THE DISTRIBUTOR GEAR SUPPORT WAS FOUND TO BE BADLY BURNED SHOWING DEEP TRACKING FROM SPARKS GOING FROM THE SHAFT TO GROUND ON THE M3485 BEARING CAP BY ARCING ACROSS THE SUPPORT. SUPPORT HAS A DEEP TR ACK BURNED ACROSS IT. DISTRIBUTOR BLOCK AND GEAR ARE COATED WITH A WHITE DEPOSIT MATERIAL WHICH IS ALSO SEEN SPATTERED INSIDE THE MAGNETO HOUSING AND ON THE COIL. MAGNETO WAS SUPPLIED AS PART OF A FACTORY REBUILT ENGINE. 1 H 7 1 3O 3 O A4CE E3SO 2002012400040 20020124 00040 2002 1 24 2002FA0000103 4 20010809 G 2564 R0097104 LIFE RAFT CABIN DAMAGED B O OTHER L NO TEST NR NOT REPORTED 1 SW 03 DURING 1ST 8 MONTH INSPECTION, LIFE RAFT HAS TOO MUCH POROSITY. RECOMMENDATION BETTER COATING OF FABRIC AND MORE INTENS IVE INSPECTION AFTER MANUFACTURING OF RAFT. (M) 2002012400041 20020124 00041 SO 2002 1 24 2002FA0000105 2 20010810 G 8550 6420B5415R HOUSING CESSNA 402 402C 207590R CE CONT O520 TSIO520* 17040 SO SCAV PUMP FRACTURED D E ENGINE SHUTDOWN K FLUID LOSS AP APPROACH 1 SW 99 121PB 1482 402C0507 ON FINAL APPROACH, CREW NOTICED OIL LEAKING FROM LEFT ENGINE COWL. OIL PRESSURE AND TEMPERATURE WERE INDICATING NORMAL. CREW SHUT DOWN LEFT ENGINE AS A PRECAUTION AND LANDED WITHOUT INCIDENT. MAINTENANCE FOUND SCAVENGE PUMP HOUSING FRACT URED AND LEAKING. TEAR DOWN REVEALED SCAVENGE PUMP DRIVEN GEAR FAILED, CAUSING THE HOUSING TO CRACK. MAINTENANCE REMOV ED AND REPLACED STARTER ADAPER OIL FILER AND CHANGED OIL. AIRCRAFT RETURNED TO SERVICE. (M) 1 L 7 2 3O 3 O A7CE E8CE 2002012400042 20020124 00042 EA 2002 1 24 2002FA0000106 2 20010801 G 7414 BEARING AMRGEN AG5B AG5B 3990100 SO LYC O360 VO360* 41514 EA MAGNETO FAILED B O OTHER O OTHER NR NOT REPORTED 1 SW 99 1194T 10083 MAGNETO FORWARD BEARING SEIZED BENDING SHAFT AND DRIVE GEAR ROAD OVER ENGINE ACCESSORY DRIVE GEAR CHIPPING DRIVE GEAR AN D PUTTING ENGINE OUT OF TIME SHUTTING ENGINE DOWN WHEN TAXIING AND ENGINE WOULD NOT RESTART. (M) 1 L 7 1 3O 3 O NT 1L71 1E1 2002012400044 20020124 00044 CE 2002 1 24 2002FA0000107 1 20011212 G 3710 H67402A3 SHUTTLE VALVE CESSNA 401 401 207590C CE VACUUM SYSTEM FAILED B E D ENGINE SHUTDOWN RETURN TO BLOCK J WARNING INDICATION TX TAXI/GRND HDL 1 SW 99 3264Q 1577 4010064 AFTER STARTING THE RT ENGINE & THE LT ENGINE IS OFF. THE RT VACUUM SYSTEM PULLED BOTH LT & RT ORANGE INDICATOR BULLETS O N THE VACUUM GAUGE INDICATING THAT THE LT VACUUM SYSTEM IS WORKING, BUT THE LT ENGINE IS SHUT DOWN. CAUSE: THE LT SHUTTL E/CHECK VALVE FOR THE WING DEICE BOOTS STUCK OPEN ALLOWING THE RT VACUUM PUMP TO SUCK DOWN THE LT SYSTEM THROUGH THE LT VACUUM PUMP GIVING A FALSE OPERATIONAL INDICATION. 1 L 7 2 3O A7CE 2002012400049 20020124 00049 SO 2002 1 24 2002FA0000109 2 20011207 G 7414 K3823 DISTRIBUTOR SLICK 6310 CESSNA 206 U206F 2073333 CE CONT O550 IO550F 17042 SO MAGNETO BURNED C D RETURN TO BLOCK R PARTIAL RPM/PWR LOSS TX TAXI/GRND HDL 1 SW 99 PKMPR 2 00111980 U20603398 284921 MAGNETO HAD FAILED 9.3 HOURS AFTER BEING SUPPLIED AS A PART OF A FACTORY REBUILT ENGINE. IT WAS DISASSEMBLED AND THE DI STRIBUTOR, COIL, CAPACITOR AND BREAKER WERE REPLACED. MAGNETO WAS CHECKED OK. 2.5 HOURS AFTER THIS REPAIR THE MAGNETO FAILED AGAIN. THE DISTRIBUTOR GEAR SUPPORT WAS FOUND TO BE BADLY BURNED SHOWING DEEP TRACKING FROM APARKS GOING FROM TH E SHAFT TO GROUND ON THE M3485 BEARING CAP BY ARCING ACROSS THE SUPPORT. SUPPORT HAS A DEEP TRACK BURNED ACROSS IT AND IS PARTLY BURNED AWAY. 1 H 7 1 3O 3 O A4CE E3SO 2002012400050 20020124 00050 SO 2002 1 24 2002FA0000110 2 20011207 G 7414 K3823 DISTRIBUTOR SLICK 6230 CESSNA 206 TU206G 2073357 CE CONT O520 TSIO520M 17040 SO MAGNETO BURNED D D RETURN TO BLOCK R PARTIAL RPM/PWR LOSS TX TAXI/GRND HDL 1 SW 99 PKMPY 449 00091743 U20606904 818183R MAGNETO WAS SUPPLIED AS PART OF A TCM FACTORY REBUILT ENGINE. IT FAILED AND UPON INSPECTION IT WAS DISCOVERED THAT THE DISTRIBUTOR GEAR SUPPORT WAS BADLY BURNED BY SPARKS GOING FROM THE COIL TERMINAL TO GROUND ON THE M3485 BEARING CAP BY A RCING ACROSS THE SHELF OF THE SUPPORT. SUPPORT HAS A DEEP TRACK BURNED ACROSS IT. 1 H 7 1 3O 3 O A4CE E8CE 2002012400052 20020124 00052 SO 2002 1 24 2002FA0000111 1 20011221 G 3230 7954302 BOLT PIPER PA28 PA28151 7102805 SO DRAG LINK FAILED D A UNSCHED LANDING D INFLIGHT SEPARATION CL CLIMB 1 SW 99 43125 4395 6 287415430 JUST AFTER TAKEOFF, THE GREASE BOLT (P/N 79543-02) FAILED AND ALLOWED THE UPPER AND LOWER TORQUE LINKS TO SEPARATE. THI S ALLOWED THE STUB AXLE, OLEO TUBE, AND RIGHT WHEEL AND BRAKE ASSEMBLY TO FALL OFF THE AIRCRAFT. THE BRAKE LINE BROKE A LLOWING EVERYTHING TO FALL FREE. THE ASSEMBLY WAS RECOVERED AND THE TORQUE LINKS FOUND TO BE INTACT. THE GREASE BOLT WAS NOT RECOVERED, SO THE EXACT LOCATION OF THE FAILURE IS UNKNOWN. THIS AIRCRAFT HAS BEEN USED FOR TRAINING EXTENSIVEL Y, SO STRESSES ON THE GEAR ARE HIGHER THAN IN NORMAL USE. ANY SIDE LOAD ON THE GEAR STRESSES THE GREASE BOLT, SO PERHAP S A LANDING WHILE YAWED CRACKED THE BOLT, CAUSING A FAILURE ON THE NEXT FLIGHT. 1 L 7 1 3O 2A13 2002012400062 20020124 00062 CE 2002 1 24 2002FA0000112 1 20011227 G 3340 W31X100010 SWITCH CESSNA 172 172S 2072439 CE INSTRUMENT PANEL FAILED D K NONE L NO TEST IN INSP/MAINT 1 NM 03 1429 172S8135 PRE-RUN FOR MAINTENANCE FOUND TAXI LIGHT ON WITH SWITCH IN THE OFF POSITION. MAINTENANCE FOUND TAXI LIGHT SWITCH FAILED IN THE ON POSITION. REPLACED SWITCH AND FUNCTIONAL CHECKED SAT. 1 H 7 1 3O NT 3A12 2002012400063 20020124 00063 EU 2002 1 24 2002FA0000113 1 20011108 G 2613 OVERHEAT LOOP BRAERO DH125 BAE125800A 1500285 EU AFT E/E BAY FAILED D K NONE L NO TEST IN INSP/MAINT 1 GL 07 12F 258182 DURING A 5 YEAR FUNCTIONAL TEST OF THE REAR EQUIPMENT BAY OVERHEAT DETECT SYSTEM, THE FUNCTIONAL TEST FAILED. FOUND FUSE F36(3AMP) ON THE ZK PANEL BLOWN. THE FLIGHT CREW HAS NO WAY OF KNOWING THEIR OVERHEAT DETECT SYSTEM IS INOP, BECAUSE TH E COCKPIT TEST CIRCUIT, WHICH TESTED OK, IS NOT WIRED THROUGH THIS FUSE. THIS COULD BE A POTENTIALLY DANGEROUS SITUATION . 2 L 7 2 4F RT A3EU 2002012400082 20020124 00082 CE 2002 1 24 2002FA0000124 1 20011219 G 2120 ODOR RAYTHN DH125 HAWKER800XP 7150012 CE GARRTT TFE731 TFE7315BR WP COCKPIT DETECTED B E ENGINE SHUTDOWN B SMOKE/FUMES/ODORS/SPARKS CL CLIMB 1 WP 07 833QS 258433 107407 DURING CLIMB AT FL240, PILOTS NOTICED "BURNING" SMELL FOLLOWED BY A HUMMING SOUND FROM THE LEFT-HAND SIDE OF AIRCRAFT. P ILOT ELECTED TO SHUTDOWN ENGINE. 2 L 7 2 4F 4 F RT A3EU E6WE 2002012800046 20020128 00046 EU 2002 1 28 2002FA0000136 1 20010116 G 2435 150SG10095 BRUSHES UROCOP EC120 EC120B 8680987 EU TMECA ARRIUS ARRIU2F NE STARTER GEN WORN C K NONE O OTHER IN INSP/MAINT 1 WP 25 255SD 200 1618 1102 34117 DEFECT FOUND DURING SCHEDULED MAINTENANCE, 100 HOUR INSPECTION. LARGE QUANTITY OF CARBON DUST NOTICED AROUND STARTER G ENERATOR. FURTHER INSPECTION FOUND BRUSHES WORN BEYOND LIMITS. 1 G 7 2 3U 3 U NC R0001RD E34NE 2002013000008 20020130 00008 SW 2002 1 30 2002FA0000143 1 20011231 G 5302 206033004045 SUPPORT BELL 206 206L 1181522 SW TAILBOOM MISMANUFACTURED B ALGR K NONE W INADEQUATE Q C IN INSP/MAINT 1 SW 03 TRIED TO PUT SUPPORT IN FIXTURE TO LOCATE TO TAILBOOM. RADIUS BEND IS TOO WIDE. BETTER QUALITY CONTROL AT MFG. 1 G 7 1 3U H2SW 2002013000009 20020130 00009 SW 2002 1 30 2002FA0000144 1 20011231 G 5302 206033004045 SUPPORT BELL 206 206L 1181522 SW TAILBOOM MISMANUFACTURED C ALGR K NONE W INADEQUATE Q C IN INSP/MAINT 1 SW 03 TRIED TO PUT SUPPORT IN FIXTURE TO LOCATE TO TAILBOOM. RADIUS BEND IS TOO WIDE. BETTER QUALITY CONTROL AT MFG. 1 G 7 1 3U H2SW 2002013000010 20020130 00010 SW 2002 1 30 2002FA0000145 1 20011231 G 5302 206033004045 SUPPORT BELL 206 206L 1181522 SW TAILBOOM MISMANUFACTURED C ALGR O OTHER W INADEQUATE Q C NR NOT REPORTED 1 SW 03 TRIED TO PUT SUPPORT IN FIXTURE TO LOCATE TO TAILBOOM. RADIUS BEND IS TOO WIDE. BETER QUALITY CONTROL AT MFG. 1 G 7 1 3U H2SW 2002013000093 20020130 00093 NM 2002 1 30 2002FA0000149 1 20011218 G 5346 SUPPORT PIPER PA60 PA60601 7106010 NM MLG CRACKED D K NONE O OTHER IN INSP/MAINT 1 WP 01 700US 14000 610652796214 DURING ROUTINE MAINTENANCE TO REPLACE MAIN TIRES, THE AIRCRAFT WAS JACKED. THE NOSE LANDING GEAR HAD EXCESSIVE MOVEMENT . THE NOSE LANDING GEAR ACTUATOR SUPPORT STRUCTURE WAS FOUND CRACKED IN NUMEROUS MEMBERS OF THE SUPPORT STRUCTURE AND C RACKED THROUGH PREVIOUS REPAIRS. 1 M 7 2 3O RT A17WE 2002013000094 20020130 00094 NM 2002 1 30 2002FA0000150 1 20011218 G 5531 22000000 RIB PIPER PA60 PA60601 7106010 NM VERTICAL STAB CRACKED D K NONE O OTHER IN INSP/MAINT 1 WP 01 700US 610652796214 DURING ANNUAL INSPECTION THE VERTICAL STABILIZER LOWER FORWARD RIB WAS FOUND CRACKED AT THE 90 DEGREE BEND ADJACENT TO T HE FORWARD SPAR. THIS AREA NEEDS CLOSE INSPECTION. 10X MAGNIFYING GLASS SHOULD HELP. 1 M 7 2 3O RT A17WE 2002020500043 20020205 00043 SO 2002 2 5 2002FA0000154 2 20011231 G 8530 641320 CYLINDER HEAD PIPER PA34 PA34200T 7103406 SO CONT O360 TSIO360EB 17025 SO LT ENGINE SEPARATED B DYTR E A ENGINE SHUTDOWN UNSCHED LANDING R PARTIAL RPM/PWR LOSS NR NOT REPORTED 1 SO 15 2931L 105 347970387 DURING LEVEL FLIGHT THE LEFT ENGINE STARTED RUNNING VERY ROUGH. ENGINE FEATHERED AND AIRCRAFT RETURNED TO AIRPORT. ENG INE UNCOWLED AND NR 5 CYLINDER HEAD WAS FOUND SEPARATED FROM BARREL. 1 L 7 2 3O 3 O A7SO E9CE 2002031200004 20020312 00004 SO 2002 3 12 2002FA0000160 1 20010116 G 2710 62701123 WIRE ROPE PIPER PA32 PA32300 7103212 SO PWA PT6 PT6A67B 52043 NE LT AILERON WORN B UC2R K NONE O OTHER IN INSP/MAINT 1 GL 19 4145R 2227 3240495 LEFT AILERON BALANCE CABLE, DURING A ROUTINE INSPECTION, THE LEFT AILERON BALANCE CABLE WAS FOUND WORN WHERE THE CABLE PASSES OVER THE CENTER PULLEY IN THE MIDDLE OF THE FUSELAGE. 1 L 7 1 3O 4 T A3SO E26NE 2002031200034 20020312 00034 GL 2002 3 12 2002FA0000210 3 20011201 G 6111 R10115255 BLADE HARTZL HCB3R HCB3R304 GL PROPELLER BROKEN B F3PR O OTHER O OTHER NR NOT REPORTED 1 SW 15 1015 EMA1094 BLADE LOST APPROXIMATELY 11 INCHES INBOARD FROM TIP. HAD PREVIOUS KNOWN GROUND STRIKE ALL BLADES. REMOVED SUBJECT BLAD ES AND HUB FROM SERVICE. REPLACED WITH NEW. 2 OTHER BLADES SHOW SIGNS OF STRAIGHTING 02-01-2002 5 C P28EA 2002031200036 20020312 00036 CE 2002 3 12 2002FA0000212 1 20011226 G 5751 0322709 BRACKET CESSNA 195 195A 2073110 CE JACOBS R755 L4* 35003 EA AILERON HINGE CORRODED D K NONE O OTHER IN INSP/MAINT 1 CE 03 195CN 16062 R7557 BOTH BRACKETS CRACKED ALL THE WAY ACROSS BEARING BOSS, SEVERELY CORRODED AND MOUNTING LEG OF ONE BRACKET BROKEN OFF. TH E PROBLEM WITH THESE BRACKETS IS THE HIGHLY REAACTIVE MAGNESIUM WHICH THEY ARE MADE OF. THIS IS A HIGHLY CRITICAL COMPO NENET AND SHOULD BE INSPECTED CLOSELY OR REPLACED. 1 H 7 1 3R 3 R A790 TC121 2002031200037 20020312 00037 CE 2002 3 12 2002FA0000213 1 20011226 G 5751 03227091 BRACKET CESSNA 195 195A 2073110 CE JACOBS R755 L4* 35003 EA AILERON HINGE CRACKED D K NONE O OTHER IN INSP/MAINT 1 CE 03 195CN 16062 R7557 BOTH BRACKETS CRACKED ALL THE WAY ACROSS BEARING BOSS, SEVERLY CORRODED AND MOUNTING LEG OF ONE BRACKET BROKEN OFF. THE PROBLEM WITH THESE BRACKETS IS THE HIGHLY REACTIVE MAGNESIUM WHICH THEY ARE MADE OF. THIS IS A HIGHLY CRITICAL COMPONE NT AND SHOULD BE INSPECTED CLOSELY OR REPLACED. 1 H 7 1 3R 3 R A790 TC121 2002031200045 20020312 00045 EA 2002 3 12 2002FA0000221 2 20010125 G 8530 LS32000WA21P CYLINDER PIPER PA18 PA18150 7101828 SO LYC O320 O320* 41508 EA ENGINE CRACKED B CY4R K NONE O OTHER IN INSP/MAINT 1 AL 03 7477L 665 187509060 L4155427A ENGINE INSTALLED IN FEBRUARY 1997. AT APPROXIMATELY 665 HOURS, TWO CYLINDERS WERE CRACKED THROUGH THE FINS OUTSIDE THE EXHAUST PORT, ADJACENT TOTHE EXHAUSE SEAT. 1 H 7 1 3O 3 O 1A2 E274 2002031200053 20020312 00053 CE 2002 3 12 2002FA0000229 1 20010401 G 3222 35825005 BOLT BEECH 35 N35 1151528 CE CONT O470 IO470* 17026 SO NLG BENT D K NONE O OTHER IN INSP/MAINT 1 SW 01 1228Z 5040 D6688 DURING ANNUAL INSPECTION, CHECKING NOSE GEAR BOLT. BOLT WAS BENT. 1 L 7 1 3O 3 O 3A15 E1CE 2002031200055 20020312 00055 CE 2002 3 12 2002FA0000231 1 20010530 G 5320 PLATE BBAVIA 11 11AC 0191102 CE CONT A65 A65* 17003 SO RT SPAR DELAMINATED D K NONE O OTHER IN INSP/MAINT 1 EA 25 9540E 1685 11AC1178 FWD REINFORCING PLATE ON RIGHT REAR SPAR AT STRUT ATTACH FITTING WAS FOUND DELAMINATING AND SEPARATING FROM SPAR AT BOND AREA. PROBABLE CAUSE IS ATTACK BY MOISTURE AND THIN OR POOR QUALITY WOOD SURFACE FINISH. RECOMMEND MORE PRECAUTION WH EN FINISHING WOOD STRUCTURES. PART TOTAL 1685 HOURS. 1 H 7 1 3O 3 O A761 E205 2002031200056 20020312 00056 SW 2002 3 12 2002FA0000232 1 20010815 G 5720 FLANGE BBAVIA 7 7ECA 21101NN SW LYC O290 O290* 41506 EA WING RIB LOOSE D K NONE O OTHER IN INSP/MAINT 1 SW 07 57679 1515 99974 FOUND LOOSE NAILS LESS THAN .1250 OUT ON SECOND RIB OUTBOARD OF STRUT AFT SPAR. FIRST AND SECOND RIB INBOARD OF STRUT A ND FIRST RIB OUTBOARD OF STRUT AND FRONT SPAR ALL ON RIGHT WING. LEFT WING, FOUND LOOSE NAILS MORE THAN .1250 OR MISSIN G ON 1ST AND 2ND RIB OUTBOARD OF STRUT ON FRONT SPAR. ONE NAIL MISSING ON 1ST RIB INBOARD OF STRUT ON FRONT SPAR. ONE LOOSE LESS THAN .1250 ON SECOND RIB INBOARD OF STRUT ON FRONT SPAR. NO CRACKS FOUND IN EITHER WING. 1 H 7 1 3O 3 O A759 E229 2002022500016 20020225 00016 CE 2002 2 25 2002FA0000233 1 20010828 G 2530 DRAIN VALVE RKWELL NA265 NA26565 7630107 CE GARRTT TFE731 TFE7313R1D 01518 WP GALLEY CRACKED C O OTHER K F FLUID LOSS FLT CONT AFFECTED CR CRUISE 1 GL 07 45H 7367 4652 AIL TRIM LIGHT ILLUM DURING CRUISE FLIGHT. PILOT ATTEMPTED TO FREE FROZEN CONTROLS BY SLAMMING CONTROL WHEEL TO LEFT. CO NTROLS WERE FREE BUT BINDING. CONTROLS FROZE WHEN PIC SLAMMED CONTROL WHEEL LEFT, CONTROL WHEEL STUCK IN LEFT POSITION. CAUSING AN CONTINUOUS TURN OF A/C. DIVERTED TO ENROUTE AIRPORT. AT LOW ALTITUDE CONTROLS WARMED UP AND AILERONS WERE REL EASED. MECHANIC LOOKED AT A/C AND NO PROBLEM NOTED WITH CONTROLS. TRIP WAS CONTINUED WITH NO PROBLEMS. UPON RETURN TO H OME BASE A/C WAS REINSPECTED. A CRACKED DRAIN FITTING IN THE GALLEY WAS ALLOWING WATER FROM ICE BIN DRAIN TO LEAK INTO A P SERVO AND FREEZE. FITTING WAS REPLACED. NO PROBLEMS NOTED SINCE FITTING REPLACED. 2 L 7 2 4J 4 F A2WE E6WE 2002031200058 20020312 00058 CE 2002 3 12 2002FA0000235 1 20010925 G 5711 5271 SPAR BBAVIA 7 7KCAB 21101P3 CE LYC O320 IO320* 41508 EA WING CRACKED D K NONE O OTHER IN INSP/MAINT 1 SW 09 8615V 2230 50475 WING MAIN SPAR, TOP OF SPAR OUTBOARD OF STRUT FITTING. 1 H 7 1 3O 3 O A759 1E12 2002031200059 20020312 00059 SW 2002 3 12 2002FA0000236 1 20011017 G 5711 5271 SPAR BBAVIA 7 7GCBC 1220601 SW LYC O320 O320* 41508 EA WING CRACKED D K NONE O OTHER IN INSP/MAINT 1 NM 03 8807 1632 47373 FOUND A CRACK AT THE SPAR BUTT ON THE RIGHT FORWARD SPAR WHILE COMPLYING WITH AD. THE CRACK WAS CLOSE TO THE WING ATTAC H FITTING WHICH LIMITED THE ABILITY TO FULLY INSPECT THE CRACK WITHOUT MAJOR DISASSEMBLY. A PIECE OF .020 INCH SAFETY W IRE WAS ABLE TO GO INTO THE CRACK .5000 INCH. ( A FEELER GUAGE COULD NOT BE USED DUE TO THE LOCATION IN REFERENCE TOTHE ATTACHMENT BARCKET). THE CRACK APPEARED TO START FROM JUST BELOW THE WING ATTACHMENT BOLT AND GO TOWARD THE LOWER ATTA CHMENT BOLT. 1 H 7 1 3O 3 O NC A759 E274 2002031200060 20020312 00060 SW 2002 3 12 2002FA0000237 1 20010813 G 1400 FASTENER BBAVIA 7 7GCBC 1220601 SW LYC O320 O320* 41508 EA RT WING LOOSE D K NONE O OTHER IN INSP/MAINT 1 EA 25 38WK 3617 113379 RIGHT WING: 16 LOOSE NAILS, 3 VERY LOOSE, 1 MISSING LEFT WING: 9 LOOSE NAILS, 0 VERY LOOSE, 0 MISSING. 1 H 7 1 3O 3 O NC A759 E274 2002031200061 20020312 00061 SW 2002 3 12 2002FA0000238 1 20010507 G 5711 5263 SPAR BBAVIA 7 7GCAA 21101N8 SW LYC O320 O320A2D 41508 EA WING CRACKED D VE6R K NONE O OTHER IN INSP/MAINT 1 CE 03 5038A 37679 L4862927A INSPECTED AIRCRAFT AS PER AD, FOUND LEFT AFT SPAR HAS COMPRESSION CRACK AT OUTBOARD END OF DOUBLER PLATES FOR STRUT ATTA CH FITTING. 1 H 7 1 3O 3 O A759 E274 2002031200062 20020312 00062 SW 2002 3 12 2002FA0000239 1 20010627 G 5711 5262 SPAR BBAVIA 7 7ECA 21101NN SW LYC O235 O235* 41505 EA WINGS CRACKED D K NONE O OTHER IN INSP/MAINT 1 WP 25 2763G 1762 459 DURING ANNUAL INSPECTION, WING SPAR INSPECTION IAW AD., FOUND LONGITUDINAL CRACKS IN THE AREA OF WING STRUT ATTACH POINT S. RIGHT FORWARD SPAR LONGITUDINAL CRACK OBSERVED FROM MISSING CENTER RIB NAIL, INBOARD FROM THE STRUT ATTACH DOUBLER A PPROXIMATELY 2 INCH LONG, ANOTHER OUTBOARD FROM STRUT ATTACH DOUBLER UPPER BOLT HOLE APPROXIMATELY 3 INCHES LONG. LEFT FORWARD SPAR, OUTBOARD RIB FROM STRUT ATTACH DOUBLER, A RIB NAIL WAS PREVIOUSLY REPLACED AND LONGITUDINAL CRACK IN BOTH DIRECTIONS FROM NAIL POSITION (CENTER NAIL) APPROXIMATELY 2 INCHES LONG. THIS IS WHERE THE INSPECTION WAS TERMINATED. DID NOT CUT ANY HOLES OR INSPECT THE REST OF THE SPAR DUE TO REJECTION OF THE WING SPARS. 1 H 7 1 3O 3 O A759 E223 2002031200063 20020312 00063 SW 2002 3 12 2002FA0000240 1 20010103 G 5711 SPAR BBAVIA 7 7AC 2110102 SW CONT A65 A65* 17003 SO RT WING CRACKED D K NONE O OTHER IN INSP/MAINT 1 SO 05 4221E 7AC7151 1) RIGHT WING FRONT SPAR BETWEEN 3RD AND 4TH RIB ON FORWARD FACE OF SPAR A CRACK CROSSING 3 ANNUAL RINGS APPROXIMATELY 4 INCHES IN LENGTH. 2) LEFT WING LOOSE OR MISSING NAILS IN FRONT SPAR AS 3RD AND 4TH RIBS LOOSE OR MISSING NAILS IN FRON T AND REAR SPARS ADJACENT TO STRUT ATTACH FITTING AND OUTBOARD OF SAME. 1 H 7 1 3O 3 O A759 E205 2002031200064 20020312 00064 SW 2002 3 12 2002FA0000241 1 20010103 G 5711 SPAR BBAVIA 7 7AC 2110102 SW CONT A65 A65* 17003 SO RT WING CRACKED D K NONE O OTHER IN INSP/MAINT 1 SO 05 83946 7AC2628 1) RIGHT WING/ CRACKS PROPAGATING FROM BOLT HOLES ADJACENT TO FUSELAGE ATTACHMENT FROM AND REAR. 2) CRACK OUTBOARD OF R EAR LIFT STRUT REAR SPAR (RIGHT WING) 3) LEFT WING REAR SPAR (ORIGINAL FACTORY SPAR) EDGE GLUED JOINT DELAMINATED FROM ATTACH FITTING OUT TO AILERON 1ST INBOARD RIB. 1 H 7 1 3O 3 O A759 E205 2002031200065 20020312 00065 SW 2002 3 12 2002FA0000242 1 20010615 G 5711 SAR5263L SPAR BBAVIA 7 7GCAA 21101N8 SW LYC O320 O320A2B 41508 EA LT WING FAILED D K NONE O OTHER IN INSP/MAINT 1 EA 23 7591F 5025 21070 L3018827A CRACK IN REAR SPAR OF LEFT WING OUTBOARD OF DOUBLER AT SPAR ATTACH FITTING. WING HAS HIT GROUND BEFORE WHEN INBOARD LAN DING GEAR BOLT FAILED. TIP OF FORWARD SPAR HAS REPAIR AND DOUBLER. 1 H 7 1 3O 3 O A759 E274 2002031200066 20020312 00066 SW 2002 3 12 2002FA0000243 1 20010517 G 1400 FASTENER BBAVIA 7 7ECA 21101NN SW CONT O200 O200* 17020 SO SPAR MISSING D K NONE O OTHER IN INSP/MAINT 1 SW 17 9510S 2572 7ECA275 APPROXIMATELY 8 RIB ATTACH NAILS WERE FOUND MISSING ON EACH WING. (BOTH SPARS) SCRATCHES AND GOUGES WERE FOUND ON LEFT REAR SPAR MID AREA. THESE WERE APPARENTLY MADE BY REPAIRMAN SLIDING RIBS DOWN SPAR, DURING THE LAST REPAIR OF WING. B OTH WINGS WILL HAVE COVER REMOVED FOR FURTHER INSPECTION AND REPAIR. 1 H 7 1 3O 3 O A759 E252 2002031200067 20020312 00067 CE 2002 3 12 2002FA0000244 1 20010517 G 1400 FASTENER BBAVIA 8 8KCAB 2110612 CE LYC O360 AEIO360* EA RIB MISSING D K NONE O OTHER IN INSP/MAINT 1 SO 09 2561Z 1290 35377 APPROXIMATELY 10 RIB NAILS WERE MISSING ON EACH WING. NAIL HOLES WERE NOT ELONGATED. NO OTHER DAMAGE WAS FOUND. THE G ENERAL LOCATION OF MISSING NAILS WERE AT STRUT ATTACH AREAS. 1 H 7 1 3O 3 O A21CE 1E10 2002031200068 20020312 00068 CE 2002 3 12 2002FA0000245 1 20010630 G 5711 SA5263R SPAR BBAVIA 7 7KCAB 21101P3 CE LYC O320 IO320* 41508 EA RT WING CRACKED D K NONE O OTHER IN INSP/MAINT 1 WP 09 8643 3161 35473 L495755A AIRFRAME TOTAL TIME 3161 DURING THE ANNUAL INSPECTION AND WHILE COMPLYING WITH AD INSTRUCTIONS. IT WAS DISCOVERED THAT THE RIGHT WING REAR SPAR HAD AN 8 INCHES LONG LONGITUDINAL CRACK AT THE REAR STRUT ATTACH POINT. ITS SUSPECTED THAT THE AIRFRAME HIGH TIME COULD BE THE CAUSE. 1 H 7 1 3O 3 O A759 1E12 2002031200069 20020312 00069 SW 2002 3 12 2002FA0000246 1 20010718 G 5711 SPAR BBAVIA 7 7FC 2110124 SW CONT C90 C90* 17009 SO RT WING DEFECTIVE D FYUG K NONE O OTHER IN INSP/MAINT 1 SO 15 9898B 218 CRACK VISIBLE MIDWAY FROM TOP TO BOTTOM OF RIGHT WING FRONT SPAR FROM 44 INCHES INBOARD ALONG SPAR TO APPROXIMATELY 130 INCHES FROM INBOARD. WOOD APPEARS TO BE IN GOOD CONDITION OTHER WISE. DEFECT DISCOVERED DURING SPAR INSPECTION IN COMP LIANCE WITH AD. AIRCRAFT WAS NOT DAMAGED OR UNAIRWORTHY IN ANY OTHER WAY. 1 H 7 1 3O 3 O A759 E252 2002031200070 20020312 00070 CE 2002 3 12 2002FA0000247 1 20011226 G 5751 BRACKET CESSNA 195 195B 2073112 CE JACOBS R755 R7557 35003 EA IB AILERON CRACKED D K NONE O OTHER IN INSP/MAINT 1 CE 03 195BA 16069 BOTH BRACKETS CRACKED COMPLETELY ACROSS BEARING BOSSES. THIS IS A RECURRING AND EXTENSIVE PROBLEM THAT IS POTENTIALLY V ERY CRITICAL FOR CONTROLLABILITY OF THE AIRCRAFT. WE WERE ABLE TO BREAK THE INBOARD END OF AN AILERON LOOSE FROM THE AI RCRAFT WITH APPROXIMATELY 40 LBS OF FORCE EXERTED BY HAND ON THE AILERON WITH A BEARING BOSS CRACKED ON THE HINGE BRACKE T. 1 H 7 1 3R 3 R A790 5E11 2002031200071 20020312 00071 CE 2002 3 12 2002FA0000248 1 20011226 G 5751 03227091 BRACKET CESSNA 195 195B 2073112 CE JACOBS R755 R7557 35003 EA AILERON HINGE CRACKED D K NONE O OTHER IN INSP/MAINT 1 CE 03 195BA 16069 BOTH BRACKETS CRACKED COMPLETELY ACROSS BEARING BOSSES. THIS IS A RECURRING AND EXTENSIVE PROBLEM THAT IS POTENTIALLY V ERY CRITICAL FOR CONTROLLABILITY OF THE AIRCRAFT. WE WERE ABLE TO BREAK THE INBOARD END OF AN AILERON LOOSE FROM THE AI RCRAFT WITH APPROXIMATELY 40 LBS OF FORCE EXERTED BY HAND ON THE AILERON WITH A BEARING BOSS CRACKED ON THE HINGE BRACKE T. 1 H 7 1 3R 3 R A790 5E11 2002031200073 20020312 00073 CE 2002 3 12 2002FA0000250 1 20010125 G 5711 SPAR BBAVIA 7 7KCAB 21101P3 CE LYC O320 IO320* 41508 EA WING CRACKED D K NONE O OTHER IN INSP/MAINT 1 SO 11 6369N 2881 44 WOODEN SPARS, NAILS OUT OF LEADING EDGE RIBS, WOODEN SPACERS WERE LEFT OUT OF FIRST FOUR INBOARD LEADING EDGE RIBS. LEA DING EDGE LOOSE, NAILS LOOSE. HAD BEEN PATCHED BEFORE, HAD PUT SCREWS INSTEAD OF NAILS ON LEADING EDGE SPARS AND RIBS. SOME RIBS CRACKED, INNER RIB LACING CORDS BROKEN, HAVE SCRAPPED WINGS AND REPLACING WITH NEW METAL SPAR WINGS. 1 H 7 1 3O 3 O A759 1E12 2002031200074 20020312 00074 SW 2002 3 12 2002FA0000251 1 20010717 G 5711 5270 SPAR BBAVIA 7 7GCBC 1220601 SW LYC O320 O320* 41508 EA WING CRACKED D K NONE O OTHER IN INSP/MAINT 1 CE 09 2546Z 979 99877 DETECTED COMPRESSION CRACK AT TOP OF AFT SPAR ON THE OUTBOARD END OF LIFT STRUT DOUBLER PLATE. CRACK PROGRESSED DOWN A FT SIDE ABOUT 1 INCH. LONGITUDINAL CRACK WAS ALSO FOUND IN AFT SPAR LAST 12 INCHES NEAR TIP. CRACK WAS IN CENTER OF SP AR. WHEN THE WING WAS DISASSEMBLED FOR SPAR REPLACEMENT, LONGITUDINAL CRACKS WERE FOUND ON FRONT SPAR UNDER THE DOUBLER PLATES FOR THE FUSELAGE TO WING ATTACH FITTINGS. THESE CRACKS WERE NOT DETECTED UNTIL THE PLATE WAS REMOVED. CRACKS W ERE BETWEEN THE BOLT HOLES FOR THE DOUBLER PLATE. THIS WING SUSTAINED A TIP STRIKE, AND WAS REPAIRED. SUBMITTER SPECUL ATES THAT COMPRESSION CRACK AND OTHER DAMAGE OCCURRED AT THIS TIME. 1 H 7 1 3O 3 O NC A759 E274 2002031200076 20020312 00076 SW 2002 3 12 2002FA0000253 1 20010403 G 5711 SPAR BBAVIA 7 7ECA 21101NN SW LYC O235 O235* 41505 EA RT WING CRACKED D TVMR K NONE O OTHER IN INSP/MAINT 1 EA 05 6309N 2214 233 WHILE COMPLYING WITH AD, A LONGITUDINAL CRACK IN THE RIGHT FOREWARD WOODEN WING SPAR APPROXIMATELY 30 INCHES LONG. 1 H 7 1 3O 3 O A759 E223 2002031200078 20020312 00078 SW 2002 3 12 2002FA0000255 1 20010801 G 1400 FASTENER BBAVIA 7 7ECA 21101NN SW LYC O235 O235* 41505 EA FWD & REAR SPARS MISSING D K NONE O OTHER IN INSP/MAINT 1 CE 09 86983 3566 103174 NUMEROUS RIB NAILS MISSING OR BACKED OUT FARTHER THAN .1250 ON FORWARD AND AFT WING SPARS, LEFT AND RIGHT WINGS. INSPEC TED SPARS AND REPLACED SUCH NAILS. 1 H 7 1 3O 3 O A759 E223 2002031200079 20020312 00079 SW 2002 3 12 2002FA0000256 1 20010626 G 5711 SPAR BBAVIA 7 7GCB 2110130 SW LYC O320 O320* 41508 EA RT WING CRACKED G K NONE O OTHER IN INSP/MAINT 1 GL 07 9866Y 64 LONGITUDINAL CRACK LOCATED AT ROOT END OF FRONT WING SPAR IN RIGHT WING. CRACK RUNS FROM BUTT END OF SPAR THROUGH THE T WO TOP BOLT HOLES OF THE SPAR TO FUSELAGE ATTACHMENT BRACKET. CRACK COULD BE SEEN IN THE BUTT END GRAIN AND BY REMOVING THE FUSELAGE ATTACHMENT BRACKET AND THE BUSHINGS FROM THE BOLT HOLES. 1 H 7 1 3O 3 O A759 E274 2002031200082 20020312 00082 SW 2002 3 12 2002FA0000258 1 20010718 G 5711 SPAR BBAVIA 7 7EC 2110120 SW RT WING CRACKED C K NONE O OTHER IN INSP/MAINT 1 SO 15 9898B 218 WING SPAR, CRACK VISIBLE MIDWAY FROM TOP TO BOTTOM OF NIGHT WING FRONT SPAR FROM 44 INCHES INBOARD ALONG SPAR TO APPROXI MATELY 1130 INCHES FORM INBOARD. WOOD APPEARS TO BE IN GOOD CONDITION OTHERWISE. DEFECT DISCOVERED DURING SPAR INSPECT ION IN COMPLIANCE WITH AD. AIRCRAFT WAS NOT DAMAGED OR UNAIRWORTHY IN ANY OTHER WAY. 1 H 7 1 3O A759 2002031200086 20020312 00086 SW 2002 3 12 2002FA0000263 1 20010129 G 5711 SPAR BBAVIA 7 7GCAA 21101N8 SW LT WING CRACKED D K NONE O OTHER IN INSP/MAINT 1 CE 07 CGFJD 92 WINGS REMOVED FROM AC, THE REPAIR ON THE LT REAR SPAR STRUT ATTACH POINT. ALL FABRIC COVERING REMOVED, LT REAR SPAR HAD A 1 INCH X 16 INCHES LONG .1250 PLYWOOD STRIP GLUED TO THE TOP OF THE SPAR WHICH HID THE CRACK TO BUSHING HOLE. IT WOU LD APPEAR THAT CRACK, 4 .7500 AND ADDING THE 1 INCH X 16 INCH STRIP ON TOP. GLUING WAS LESS THAN ACCEPTABLE. 2 INCH CRACK ON THE LT SPAR REMOVED FROM THE RIB FLANGE AND THE RIB MOVED, DETECTION OF THE CRACK IS NEXT TO IMPOSSIBLE. THE 1 INCH COMPRESSION FAILURE ON THE RIGHT SPAR IS BESIDE EDGE OF THE .1250 PLYWOOD REINFORCEMENT. CRACK IS VISIBLE WITH GO OD LIGHT, CRACK DOES NOT GO COMPLETELY ACROSS THE .7500 INCH THICKNESS AND NO LINE VISIBLE ON THE OPPOSITE SIDE. 1 H 7 1 3O A759 2002031200087 20020312 00087 CE 2002 3 12 2002FA0000264 1 20010313 G 2760 26270522 SOLENOID LEAR 35 35A 5170602 CE GARRTT TFE731 TFE731* 01518 WP SPOILER MANIFOLD INTERMITTENT B WIBR K NONE O OTHER IN INSP/MAINT 1 SW 11 10AH 657 SPOILER OPERATION INTERMITTENT. MAINIFOLD ASSEMBLY HAS TWO SOLENOIDS, APPEARS THAT ONE MAY BE STICKING OR HAVE AN ELECT RICAL PROBLEM. 2 L 7 2 4F 4 F A10CE E6WE 2002031200089 20020312 00089 SO 2002 3 12 2002FA0000267 2 20011201 G 8520 SA640518 PISTON CESSNA 182 182M 2072728 CE CONT O470 O470R 17026 SO NR 5 CYL FAILED G A UNSCHED LANDING Y ENGINE STOPPAGE CL CLIMB 1 WP 19 71298 280 18259567 CASTROSPHOIC ENGINE FAILURE AFTER TAKEOFF. EMERGENCY LANDING WAS EXECUTED WITHOUT INCIDENT. ENGINE WAS DISASSEMBLED, R EVEALING NR 5 PISTON DISINTEGRATED. ENGINE HAD BEEN OVERHAULED APPROXIMATELY 280 HOURS AND 3.5 YEARS PRIOR TO FAILURE. ALL PISTONS HAD BEEN REPLACED WITH NEW AT OVERHAUL. PARTS WERE SUBMITTED TO THE MANUFACTURER FOR ANALYSIS. 1 H 7 1 3O 3 O NT 3A13 E273 2002031300009 20020313 00009 GL 2002 3 13 2002FA0000294 1 20010722 G 2821 FUEL FILTER AMTR GLASAR GLASAIR 05618GT GL LYC O360 IO360A1A 41514 EA ENGINE FUEL CLOGGED C K NONE O OTHER IN INSP/MAINT 1 WP 23 14WQ 2172 IN LINE FUEL FILTER INSTALLED BETWEEN FUEL SELECTOR VALVE AND BOOST PUMP. CLOGGED WITH RUST DEBRIS, AND RESTRICTED FLOW TO ENGINES. 1 L 7 1 3O 3 O RT EXPA1L71 1E10 2002031300014 20020313 00014 GL 2002 3 13 2002FA0000299 2 20011220 G 7323 23065125 GOVERNOR ALLSN 250C 250C30 03013 GL ENGINE INOPERATIVE B AC2R K NONE O OTHER IN INSP/MAINT 1 SW 03 11056 890384 VERY SENSITIVE, COULD NOT MATCH TORQUES AND SHAFT IS RACHETY. REPLACED WITH SERVICEABLE PART. 3 U E1GL 2002031300017 20020313 00017 EA 2002 3 13 2002FA0000304 2 20011126 G 7414 1068256013 MAGNETO PIPER PA32 PA32R300 7103213 SO LYC O540 IO540* 41532 EA ENGINE BROKEN D K NONE O OTHER IN INSP/MAINT 1 AL 05 200HM 32R7680025 DURING INSPECTION FOUND A DISTRIBUTOR GEAR TOOTH BROKEN AND LAYING IN MAGNETO CAP. THIS MAGNETO HAS PLASTIC GEARS AND H AS BEEN FOUND IN THIS CONDITION ON NUMEROUS MAGNETOS OF THIS TYPE. 1 L 7 1 3O 3 O A3SO 1E4 2002031300121 20020313 00121 CE 2002 3 13 2002FA0000338 1 20010918 G 3310 PQ876SW LIGHT CESSNA 172 172M 2072418 CE LYC O320 O320* 41508 EA COCKPIT SHORTED D K NONE L NO TEST IN INSP/MAINT 1 GL 13 1368U 17267039 THE PART WAS INSTALLED AROUND THE TACH AND CONNECTED TO THE RHEOSTAT FOR THE INSTRUMENT LIGHTS. AFTER A COUPLE OF YEARS IT SHORTED OUT THE SYSTEM. IT BURNED OUT THE RHEOSTAT S2091-5 AND THE POWER TRANSISTOR 2N3055. THIS CAUSED NO INSTRUM ENT LIGHT IN THE AIRCRAFT. THIS HAPPENED IN THE DAY TIME AND NOT AT NIGHT IFR. THE OWNER NOTICED NO LIGHTS AND NOTIFIE D HIS TECHNICIAN. AFTER TROUBLESHOOTING THE SYSTEM HE FOUND THAT THE WIRES ON THE TOP OF THE LITE RING WERE TOUCHING ON E ANOTHER, CAUSING A DIRECT SHORT. CALLED MFG, THEY INQUIRED, WHEN THIS RING WAS INSTALLED. THEY SAID TO REMOVE IT FR OM THE AIRCRAFT AND SEND IT BACK TO THEM, THEY WOULD REPLACE IT FREE OF CHARGE, BECAUSE THIS IS AN OLD STYLE RING. 1 H 7 1 3O 3 O NT 3A12 E274 2002032700076 20020327 00076 CE 2002 3 27 2002FA0000345 1 20010402 G 2810 051600918 FUEL TANK CESSNA 172 172S 2072439 CE LYC O360 IO360A1A 41514 EA FUSELAGE CRACKED D O OTHER K FLUID LOSS TX TAXI/GRND HDL 1 SO 05 272RP 613 172S8405 DURING GROUND RUN, DETECTED FUEL SMELL IN COCKPIT. REMOVED FORWARD FLOOR PANS AND OBSERVED FUEL PUDDLE AND STAIN. INSP ECTION REVEALED STAINING ON RESERVOIR TANK. DEFUELED AIRCRAFT AND REMOVED RESERVOIR TANK. STRIPPED PAINT FROM SUSPECTE D CRACK AREA. DYE PEN INSPECTION REVEALED 1 INCH CRACK ON LOWER AFT WELD BEAD. REPLACED WITH NEW PART, SUSPECTED CAUSE : STRESS DUE TO UPPER MOUNT HOLE NOT ALIGNED WITH NUT PLATE. 1 H 7 1 3O 3 O NT 3A12 1E10 2002032700094 20020327 00094 SW 2002 3 27 2002FA0000347 1 20010625 G 5711 SPAR BBAVIA 7 7ECA 21101NN SW CONT O200 O200* 17020 SO RT WING CRACKED B K NONE O OTHER IN INSP/MAINT 1 GL 05 CFQYQ 1905 128 TROUBLE AREA IN THE REGION OF LIFT STRUT ATTACHMENT POINT, REMOVED VARNISH AND SMALL AMOUNT OF WOOD, COULD IDENTIFY SMA LL CRACK IN THE GLUE JOINT ON REAR FACE OF RT REAR WING SPAR. ALSO DETECTED ON UPPER EDGE OF RT REAR SPAR A TOTAL OF 5 COMPRESSION TYPE CRACKS. TWO ACTUAL SPLITS WERE REVEALED STARTING AT THE REINFORCING PLYWOOD PLATE. FOLLOWED EDGE GRAI N OF WOOD FRO ABOUT 2 AND 3 INCHES. TWO OF THESE CRACKS EXTENDED DOWN THROUGH SPAR, AT PLYWOOD PLATE EDGE, A DISTANCE OF ABOUT 40-50 PER CENT OF THE WING SPAR. SUGGEST: ALL PLYWOOD REINFORCING PLATES HAVE THEIR VERTICAL EDGES CHAMFERED(T APERED) AT LEAST .7500 INCH, HELP IN REDUCING STRESS RISER CRATED AT VERTICAL EDGE OF REINFORCING PLATE. 1 H 7 1 3O 3 O A759 E252 2002040500007 20020405 00007 CE 2002 4 5 2002FA0000443 1 20011203 G 3110 04131267 RHEOSTAT CESSNA 182 182 2072702 CE CONT O470 O470* 17026 SO INSTRUMENT PANEL SHORTED D O OTHER B SMOKE/FUMES/ODORS/SPARKS NR NOT REPORTED 1 NM 05 5379B 3026 33379 FLYING LOW THRU MOUNTAIN PASS, TRIED TO TURN ON INSTRUMENT LIGHTS. MUCH SMOKE IN CABIN, TURNED OFF MASTER. FOUND RESI STOR WINDINGS FAILED, CONTACT ARM BURNED THRU TO CASE, ALSO CIRCUT BREAKER DID NOT OPEN. FOUND PLASTIC TRIM PANEL HOLE HAD EGG SHAPE, BUTTON COULD NOT POP OUT. REMOVE BACK OF SWITCH AND INSPECT. BETTER TO REPLACE WITH PUSH-PULL SWITCH AN D CHECK CIRCUIT BREAKERS. 1 H 7 1 3O 3 O NT 3A13 E273 2002042500054 20020425 00054 GL 2002 4 25 2002FA0000524 1 20011119 G 7120 MOUNT CIRRUS SR SR22 2130001 GL CONT O550 IO550* SO ENGINE CHAFED B MNGR K NONE O OTHER IN INSP/MAINT 1 SW 05 730CD 101 0053 DURING THE 100 HOUR INSPECTION, A FUEL LINE CLAMP WAS FOUND CHAFING ON THE ENGINE MOUNT. THE CLAMP HAD CHAFED APPROXIMA TELY .006 INTO ONE OF THE ENGINE MOUNT TUBES. THE CLAMP FOR THIS LINE APPEARS TO BE TOO LONG, ALLOWING IT TO CONTACT TH E MOUNT TUBE. THE ENGINE MOUNT WAS REPLACED AND THE CLAMP ATTACH BRACKET WAS SHORTENED SO AS TO PREVENT A REOCCURANCE O F THIS CONDITION. THIS AREA SHOULD BE GIVEN A CLOSE INSPECTION FOR CHAFING AND THE CLAMP REPOSITIONED OR THE BRACKET SH ORTENED. 1 L 7 1 3O 3 O NT A00009CH E3SO 2002050600134 20020506 00134 CE 2002 5 6 2002FA0000560 1 20010117 G 2140 FR13E55IEL4500 COMBUST CHAMBER CESSNA 421 421C 2076016 CE CONT O520 GTSIO520* 17032 SO HEATER CRACKED D K NONE L NO TEST IN INSP/MAINT 1 GL 13 6798V 531 421C1254 OWNER REQUESTED PRESSURE DECAY TEST IAW AD. PRESSURE COULD NOT BE MAINTAINED. REMOVED HEATER, DISCOVERED LARGE CRACK AT AFT, LOWER WALL OF COMBUSTION CHAMBER, ALONG WELD LINE. THIS HEATER WAS INSTALLED 11/1/99 WITH ONLY 531.3 TT HEAT ER HOURS ON PART. FACTORY REBUILT UNIT INSTALLED WITH NEW CERAMIC COATED LINER TO PREVENT CRACKING. HEATER WAS REPLACE D WITH FACTORY WARRANTY UNIT, AND SENT BACK TO FACTORY FOR EXCHANGE. 1 L 7 2 3O 3 O A7CE E7CE 2002051400039 20020514 00039 WP 2002 5 14 2002FA0000582 1 20010420 G 6310 369D25146 BEARING RACE HUGHES 369 369D 4470706 WP M/R TRANSMISSION CRACKED B EOOR K NONE O OTHER IN INSP/MAINT 1 AL 03 C6PHC 180257D REMOVED MAIN ROTOR TRANSMISSION FOR AN OIL LEAK. FOUND FORWARD TAIN ROTOR O/P ASSEMBLY PINION BEARING INNER RACE. CRAC KED. REPLACED BEARING ASSEMBLY. 1 G 7 1 3U H3WE 2002052300105 20020523 00105 CE 2002 5 23 2002FA0000665 1 20011120 G 5410 STRUCTURE CESSNA 411 411A 2075904 CE CONT O520 GTSIO520C 17032 SO NACELLE CORRODED B A5OR K NONE O OTHER IN INSP/MAINT 1 SO 09 333SF 3788 4110260 DURING INSPECTION OF THE WING NACELLE BAGGAGE COMPARTMENT STRUCTURE CORROSION WAS DISCOVERED UNDER THE TRIM AND CARPETS. UPON REMOVAL OF THE NACELLE BAGGAGE COMPARTMENT TRIM AND CARPETS SEVER SURFACE CORROSION WAS DISCOVERED. MAJOR SECTIO N OF THE NACELLE STRUCTURE IN BOTH WINGS WAS DAMAGED BY CORROSION. THE PROBABLE CAUSE OF THIS CORROSION WAS THE USE OF TRIM ADHESIVE DIRECTLY ON THE AIRCRAFT STRUCTURE. THE TRIM ADHESIVE ACTED LIKE AN ACID ON THE SKINS, RIBS, ANGELS AND B ULKHEADS OF THE NACELLE. RECOMMEND ONLY APPROVED ADHESIVES BE USED TO INSTALL TRIM AND CARPETS. 1 L 7 2 3O 3 O A7CE E7CE 2002072900009 20020729 00009 EA 2002 7 29 2002FA0000860 2 20010925 G 7414 BL68256013 MAGNETO PIPER PA32 PA32RT300T 7103216 SO LYC O540 TIO540S1AD 41532 EA ENGINE CRACKED G O OTHER R J PARTIAL RPM/PWR LOSS WARNING INDICATION CL CLIMB 1 GL 25 39945 17 32R7887172 AIRCRAFT ON CLIMBOUT FROM AIRPORT, LOST ENGINE POWER AND CRASHED. INVESTIGATION CONCLUDED MAGNETO FAILED DUE TO FATIGUE CRACK IN HOUSING CAUSING MAGNETO HOUSING TO SEPARATE FROM ENGINE. 1 L 7 1 3O 3 O A3SO E14EA 2002082600057 20020826 00057 CE 2002 8 26 2002FA0000987 1 20010801 G 3213 9530489 AXLE HELIO H295 H295 4300802 CE LYC O480 GO480* 41527 EA MLG BROKEN G O OTHER O OTHER LD LANDING 1 AL 01 50718 1268 RIGHT GEAR AXLE BROKE (MAIN) ON LANDING, CAUSING SUBSTANTIAL DAMAGE TO FUSELAGE GEAR ATTACH AREA. 1 H 7 1 3O 3 O 1A8 E275 2002091900002 20020919 00002 CE 2002 9 19 2002FA0001052 1 20011203 G 3110 04131267 RHEOSTAT CESSNA 182 182 2072702 CE CONT O470 O470* 17026 SO INTERNAL SHORTED D O OTHER B SMOKE/FUMES/ODORS/SPARKS NR NOT REPORTED 1 NM 05 5379B 3026 33379 FLYING LOW THROUGH A MOUNTAIN PASS TRIED TO TURN ON INSTRUMENTS LIGHTS. SMOKE IN CABIN. TURNED OFF MASTER. FOUND RES ISTOR WINDINGS FAILED. CONTACT ARM BURNED THRU TO CASE. ALSO CIRCUIT BREAKER DID NOT OPEN. 1 H 7 1 3O 3 O NT 3A13 E273 2003010600012 20030106 00012 CE 2003 1 6 2002FA0001387 1 20010701 G 2720 12600211 BELLCRANK CESSNA 180 180K 2072624 CE CONT O470 O470J 17026 SO RUDDER PEDALS BENT D O OTHER F FLT CONT AFFECTED NR NOT REPORTED 1 NM 02 64426 2067 18052897 AIRCRAFT WAS INVOLVED IN AN ACCIDENT ON LANDING DUE TO LOSS OF CONTROL. CFI WAS FLYING FROM THE RT SEAT. AIRCRAFT LEFT THE RUNWAY TO THE RT EVEN THOUGH PILOT APPLIED FULL LT RUDDER. DURING INSPECTION. DISCOVERED THAT THE LT RUDDER PEDA L WOULD UNLOCK (STOWABLE PEDALS) WHEN FIRM PRESSURE WAS APPLIED, DUE TO BENT BELLCRANK. 1 H 7 1 3O 3 O 5A6 E273 2003021800083 20030218 00083 2003 2 18 2003FA0000125 4 20010711 G 6113 055032111 BULKHEAD CESSNA 172 172S 2072439 CE SPINNER CRACKED B IBIR O OTHER O OTHER NR NOT REPORTED 1 EA 27 740SP 126 172S8671 SPINNER AFT BULKHEAD, CRACKED. 1 H 7 1 3O NT 3A12 2003031200048 20030312 00048 NM 2003 3 12 2003FA0000184 1 20010623 G 6320 900D1400005101 TRANSMISSION DOUG MD900 MD900 3027375 NM PWC PW207 PW207E NE MAIN ROTOR MAKING METAL D K NONE O OTHER IN INSP/MAINT 1 EA 11 3PD 56 90000085 MAIN TRANSMISSION PRODUCING METAL CHIPS. CHIP SIZE EXCEED MAINTENANCE MANUAL LIMITS. 1 G 7 2 3U 3 U NC H19NM E42NE 2003031300001 20030313 00001 NM 2003 3 13 2003FA0000186 1 20010724 G 6220 900C2010186101 DRIVE LINK DOUG MD900 MD900 3027375 NM PWC PW207 PW207E NE MAIN ROTOR WORN D K NONE O OTHER IN INSP/MAINT 1 EA 11 3PD 107 90000085 MAIN ROTOR UPPER DRIVE LINK BEARING PLAY EXCEEDS MAINTENANCE MANUAL LIMITS. 1 G 7 2 3U 3 U NC H19NM E42NE 2003031300002 20030313 00002 NM 2003 3 13 2003FA0000187 1 20010726 G 6220 900C2010186101 DRIVE LINK DOUG MD900 MD900 3027375 NM PWC PW207 PW207E NE MAIN ROTOR WORN D K NONE O OTHER IN INSP/MAINT 1 EA 11 902PD 90000084 MAIN ROTOR UPPER DRIVE LINK BEARING PLAY EXCEEDS MAINTENANCE MANUAL LIMITS. 1 G 7 2 3U 3 U NC H19NM E42NE 2003031300003 20030313 00003 NM 2003 3 13 2003FA0000188 1 20010906 G 2910 071142258 INDICATOR DOUG MD900 MD900 3027375 NM PWC PW207 PW207E NE FILTER BYPASS DEFECTIVE D K NONE O OTHER IN INSP/MAINT 1 EA 11 3PD 90000085 AFTER INSTALLING NEW HYDRAULIC FILTER, THE RETURN SIDE BYPASS INDICATOR POPPED WITH NO PRESSURE APPLIED. AFTER RESETTIN G THE INDICATOR, INDICATOR POPPED AGAIN. REPLACED IMPENDING BY-PASS INDICATOR PN 071142-258. OPS CHECK GOOD. 1 G 7 2 3U 3 U NC H19NM E42NE 2003031300004 20030313 00004 NM 2003 3 13 2003FA0000190 1 20010917 G 2910 AC3676F1 FILTER DOUG MD900 MD900 3027375 NM PWC PW207 PW207E NE HYD SYSTEM CONTAMINATED D K NONE O OTHER IN INSP/MAINT 1 EA 11 902PD 90000084 BYPASS PIN POPPED ON NR 1 HYDRAULIC RETURN FILTER. REMOVED FILTER AND INSPECTED FOR CONTAMINATION. REPLACED FILTER. O PS AND LEAK CHECK GOOD. 1 G 7 2 3U 3 U NC H19NM E42NE 2003031300012 20030313 00012 GL 2003 3 13 2003FA0000218 1 20010905 G 4900 427CK1 BATTERY BOMBDR BD700 BD7001A10 1390006 GL RROYCE BR700 BR700710A220 09500 NE APU FAULTY C O OTHER O OTHER NR NOT REPORTED 1 SO 11 226HD 168 9022 12201 AIRCRAFT WAS CONNECTED TO EXTERNAL AIRCRAFT POWER CART, AND POWERED UP. A LOUD POP WAS HEARD COMING FROM AFT EQUIPMENT BAY OF AIRCRAFT. DURING INVESTIGATION, ANOTHER POP WAS HEARD. ACCESSED APU BATTERY. FOUND IT TO BE DAMAGED AND SMOKIN G. FOUND SEVERAL CELLS BURNED AND HEAT BLANKET BURNED, ALSO. SUSPECT BATTERY CHARGER TO BE FAULTY. BOTH COMPONENTS R EPLACED. REMOVED ITEMS, SENT FOR EVALUATION. NO DAMAGE TO AIRCRAFT. THE COCKPIT INDICATION AT TIME OF INCIDENT SHOWED (APU BATT FAIL) TEMPERATURE AND VOLTAGE WERE NORMAL. 2 L 7 2 4F 4 F RT T00003NY E00061EN 2003040900063 20030409 00063 SO 2003 4 9 2003FA0000324 2 20011116 G 8520 SA639193 BUSHING CONT A50 A502 17002 SO CRANK C/WEIGHT MISMANUFACTURED B JZYR O OTHER W INADEQUATE Q C NR NOT REPORTED 1 NM 09 WHILE CHECKING THE SIZE OF THE NEW MFG SA639193 BUSHINGS PRIOR TO INSTALLATION IN THE COUNTERWEIGHTS I FOUND TWO NEW STA NDARD SIZE BUSHINGS THAT WERE APPROXIMATELY .002 SMALL IN THE OUTER DIAMETER. 3 O E190 2003050700158 20030507 00158 CE 2003 5 7 2003FA0000400 1 20010816 G 3230 12416308 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 136 P21000417 LT AND RT MAIN LANDING GEAR SHELL BUMPER DEBONDS. THE BUMPER EDGES CURL OVER PREVENTING MAIN GEAR STRUT FROM MAKING FUL L DOWN TRAVEL. THIS CONDITION PREVENTS MAIN GEAR STRUT FROM CONTACTING DOWNLOCKS AND PROPER DOWNLOCK SWITCH ACTUATION, THEREFORE, AN UNSAFE CONDITION IT APPEARS THAT MFG MAY HAVE CHANGED THE COMPOSITION OF THE SHELL BUMPER MATERIAL WHICH D OES NOT HAVE GOOD BONDING QUALITIES. (PHOTO) 1 H 7 1 3O 3 O 3A21 E8CE 2003091700006 20030917 00006 CE 2003 9 17 2003FA0000755 1 20011229 G 2701 05117821 CONTROL COLUMN CESSNA 185 A185F 2072821 CE CONT O520 IO520* 17032 SO COCKPIT CRACKED D O OTHER O OTHER NR NOT REPORTED 1 AL 05 185AF 2126 18502236 A CRACK WAS FOUND ON THE AFT SIDE, ASCENDING UP FROM THE BASE OF THE CONTROL COLUMN (CONTROL U ASSY). THE CRACK MEASURE D APPROXIMATELY 6 INCHES AND HAD SPREAD APART APPROXIMATELY .5000 INCH JUST ABOVE THE ELEVATOR PUSH-PULL TUBE BEARING AN D EXTENDED UP THROUGH THE PIVOT BEARING. SIGNIFICANT AMOUNTS OF RUST WERE NOTED INSIDE THE COLUMN AT THE BASE OF THE CR ACK. IT SHOULD BE NOTED THE AIRCRAFT IS INSTALLED ON AMPHIBIAN FLOATS. POSSIBLE CAUSE OF CRACK COULD BE CONTRIBUTED TO WATER COLLECTING IN THE BOTTOM OF THE COLUMN AND FREEZING. 1 H 7 1 3O 3 O 3A24 E5CE 2003111400050 20031114 00050 EA 2003 11 14 2003FA0001091 2 20010601 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 260MM 5186 FOUND CRACKED CRANKSHAFT FLANGE. INSTALLED 3 BLADE PROP TO DECREASE STRESS ON CRANKSHAFT. 1 Q 7 1 3O 3 O NC A8SO 1E4 5 C P920 2003111400045 20031114 00045 EA 2003 11 14 2003FA0001092 2 20010701 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 260GR 5059 FOUND CRACKED CRANKSHAFT FLANGE. INSTALLED 3 BLADE MT PROP TO DECREASE STRESS ON CRANKSHAFT.(K) 1 Q 7 1 3O 3 O NC A8SO 1E4 5 C P920 2004100400096 20041004 00096 CE 2004 10 4 2004FA0000742 1 20010109 G 1430 NUT BEECH 35 V35B 1151548 CE CONT O520 IO520BA 17032 SO MCAULY 3A32C 3A32C76 GL RUDDER CRACKED D O OTHER O OTHER NR NOT REPORTED 1 WP 07 4572A 3452 D9150 ON ANNUAL INSPECTION OF RUDDERS AT THE CENTER ATTACH FITTING AFT SPAR MOUNT, SLIGHT RUST WAS NOTED. FURTHER INSPECTION REVEALED 5 OUT OF THE 8 ATTACH NUTS ON THE SPAR ATTACH WERE CRACKED THROUGH TO THE BOLT THREADS. THESE NUTS ARE CRACKED ONLY O THE BOTTOM AREA OF NUT. LOOKING DOWN AT THE ATTACH NUTS WILL NOT SHOW CRACKS. TELL TALE RUST ON THE BOLT THREA DS IS THE ONLY TOP SIDE INDICATOR. RECOMMEND THAT NAS679A NUT BE INSPECTED OR REPLACED WITH MS21042 OR MS21083N. THESE NUTS ARE USED IN OTHER LOCATIONS ON THE PLANE. EXPOSED NUTS ARE MORE SUSCEPTIBLE TO CRACKING. 1 L 7 1 3O 3 O 3A15 E5CE 5 C P21EA 2002012800051 20020128 00051 2002 1 28 223527605 4 20011203 G 2562 BP1010 BATTERY NARCO 10 CESSNA 150 150J 2071820 CE CONT O200 O200A 17020 SO MCAULY 1A100 1A100* GL ELT LEAKING P K NONE O OTHER IN INSP/MAINT 1 SO 11 60830 10 10 19503 15070606 250894 G1018 ON DOING A PRE FLIGHT INSPECTION I FOUND THAT ACID WAS LEAKING FROM THE ELT BATTERY. FURTHER INSPECTION SHOWS THAT ACID LEAKING FROM THE PACK HAD DESTROYED THE ELT ELECTRONICS MODULE, THE MOUNTING BASE WAS EATEN THROUGH AS WAS THE CARPET AN D THE ACID WAS ATTACKING THE FLOOR OF THE BAGGAGE COMPARTMENT. 1 H 7 1 3O 3 O 3A19 E252 5 N P918 2002012800054 20020128 00054 SO 2002 1 28 3372 1 20011203 G 5102 WEB BALWKS F11B BALWKS FIREFY FIREFLY11B 1050140 SO UPPER ENVELOPE DAMAGED B O OTHER O OTHER NR NOT REPORTED 1 NM 03 7244W 171 30 003 F11B003 HOT AIR BALLOON ENVELOPE TOP GIRDLE 1INCH WEBBING STRETCHED. TOP ENVELOPE FABRIC PANELS DO NOT STRETCH, CAUSING SEVERE STITCH-HOLE ELONGATION DAMAGE TO FABRIC ALONG ALL TOP PANEL VERTICAL SEAMS, EXTENDING FROM TOP GIRDLE DOWNWARD 6-12 INCH ES. 1 B 0 0 A14SO 2001050200067 20010502 00067 SO 2001 5 2 58392816R 1 20010319 G 5712 RIB PIPER PA28 PA28R200 7102811 SO LT WING CRACKED P K NONE O OTHER IN INSP/MAINT 1 SW 99 2816R 28R35297 INSPECTION OF AIRCRAFT IN MAINT HANGAR REVEALED TWO INCH CRACK ON LT WING AT APPROX WS 49.25, AROUND SINGLE RIVET, SKIN HAD BULGED AROUND RIVET AND CRACKED FORE AND AFT. INSPECTION IN WHEEL WELL SHOWED THAT RIVETS ATTACHING FLANGE TO FALSE REAR SPAR AND RIB TO FALSE REAR SPAR HAD SHEARED, HEADS GONE, SOME PORTION OF RIVETS LEFT, LEAVING NO STRENGTH BELOW ARE A OF SKIN. INSPECTION INSIDE INSPECTION PANEL IMMEDIATELY AFT OF THAT AREA REVEALED CRACKED RIB AT JOIN WITH FALSE REAR SPAR. CLOSE INSPECTION SHOWS EVIDENCE THAT THERE WAS DAMAGE SOME TIME AGO WHICH HAD BEEN WORKING ITSELF DURING FLIGHT OP S (ALUM. DUST AROUND FAILURE AND SEAMS, DIRT AND GREASE AT PLACES WHERE RIVET HEADS WERE GONE). 1 L 7 1 3O 2A13 2001050300237 20010503 00237 2001 5 3 65BA046A 4 20010413 G 2300 RHEOSTAT PIPER PA32 PA32300 7103212 SO LYC O540 IO540K1A5 41532 EA RADIO FAILED H GSBA K NONE O OTHER IN INSP/MAINT 1 AL 01 76RL 15481 327540024 L1737448A RETURNING FROM A FLIGHT, PILOT SHUT DOWN ENGINE, RADIO MASTER, THE A/C MASTER. WHEN MASTER WAS SHUT OFF, PILOT HEARD A POP FROM THE RIGHT SIDE OF PANEL. HE CHECKED BREAKERS, NOTICED NONE BLOWN, BUT SMELLED; NOTICE SMOKE COMING FROM BEHI ND PANEL TO LEFT OF CIRCUIT BREAKERS. WHEN INVESTIGATED, FOUND RHEOSTAT ASSEMBLY WIRING AND COMPONENTS BURNT FOR CABIN LIGHT CONTROLS. PART WAS REPLACED WITH SERVICABLE ASSEMBLY. 1 L 7 1 3O 3 O A3SO 1E4 2001050200055 20010502 00055 CE 2001 5 2 951141 1 20010314 G 2910 124F0016CL0532 HOSE CESSNA 500 550 2076604 CE HYD PUMP BURST B R8RR A UNSCHED LANDING J WARNING INDICATION CR CRUISE 1 WP 07 3262M 2572 5500652 DURING FLIGHT BOTH THE HYDRAULIC FLOW LIGHTS AND THE HYDRAULIC RESERVEOIR LOW LEVEL LIGHT ILLUMNINATED. FOUND THE PRESSU RE LINE FROM THE NR 1 HYDRAULIC PUMP BURST APPROX. 18 INCHES FROM THE PUMP. THERE WERE NO CHAFF MARKS ON THE HOSE, SUSPE CT INTERNAL FAILURE OF THE HOSE. THE INCIDENT IS STILL UNDER INVESTIGATION. 1 L 7 2 4F A22CE 2001092400010 20010924 00010 NE 2001 9 24 A244583 2 20010826 G 7310 430137601C TUBE BOLKMS 117 BK117A3 5626015 EU LYC LTS101 LTS101650B1 41560 NE FUEL MANIFOLD CRACKED D O OTHER K J FLUID LOSS WARNING INDICATION NR NOT REPORTED 1 SO 15 911WJ 7050 L45178 MINUTE CRACK DEVELOPED IN MANIFOLD RIGID TRANSFER TUBE, CAUSING INFLIGHT FUEL LEAK. ALLOW USE OF FLEXIBLE TRANSFER TUBE FUEL MANIFOLDS ON LTS101650B1. 1 G 7 2 3U 3 U H13EU E5NE 2001050700572 20010507 00572 GL 2001 5 7 AC2A072773 2 20010110 G 7250 6898683 NOZZLE BELL 206 206L3 1182108 SW ALLSN 250C 250C30S 03013 GL 4TH STAGE DEBONDED H AC2A K NONE O OTHER IN INSP/MAINT 1 FS 01 17238 51492 MAIN ROTOR BLADES FAILED TO TURN BY SPECIFIED N1 SPEED UPON STARTING ENGINE. IT WAS DETERMINED THAT SOMETHING INSIDE OF TURBINE WAS RUBBING DUE TO SOUND COMING FROM TURBINE WHEN ROTOR WAS TURNED BACKWARDS. TURBINE WAS REMOVED AND DISASSEMBL ED. IT WAS FOUND THAT THE 4TH STAGE NOZZLE #4 BLADE PATH HAD DISBONDED AND WAS RUBBING THE #4 TURBINE WHEEL OUTER DIAMET ER KNIFE EDGES CREATING DRAG THAT WAS CAUSING PROBLEM WITH MAIN ROTOR NOT TURNING ON START. DISBONDING WAS IN APPROXIMA TELY 25 SEPARATE SPOTS SPACED AROUND CIRCUMFRENCE OF BLADE PATH, WITH THE LARGEST SPOT BEING AROUND ONE QUARTER INCH IN DIAMETER, ROUGHLY ROUND IN SHAPE AND RAISED ENOUGH TO CONTACT THE WHEEL OUTER DIAMETER. THIS CONDITION WOULD APPEAR TO B 1 G 7 1 3U 3 U H2SW E1GL 2001050700573 20010507 00573 SW 2001 5 7 AC2A072774 1 20010110 G 2432 RG222 BATTERY BELL 206 206L3 1182108 SW MAIN DISCHARGED H AC2A K NONE L NO TEST IN INSP/MAINT 1 FS 01 7159H 676 51397 PART IS WEAK. REPLACED BATTERY 1 G 7 1 3U H2SW 2001050700574 20010507 00574 SW 2001 5 7 AC2A072775 1 20010111 G 2432 RG222 BATTERY BELL 206 206L3 1182108 SW MAIN DISCHARGED H AC2A K NONE L NO TEST IN INSP/MAINT 1 FS 01 17238 807 51492 PART IS WEAK. REPLACED BATTERY 1 G 7 1 3U H2SW 2001050700575 20010507 00575 NE 2001 5 7 AC2A072776 1 20010112 G 2430 A1077B RELAY SKRSKY S76 S76A 8143006 NE BATTERY SHORTED H AC2A O OTHER O OTHER NR NOT REPORTED 1 FS 01 7266K 760283 PART CIRCUIT-SHORTED. REPLACED RELAY 1 G 7 2 3U H1NE 2001050700576 20010507 00576 NE 2001 5 7 AC2A072777 1 20010122 G 6320 7635109082105 CHIP DETECTOR SKRSKY S76 S76A 8143006 NE ENGINE LEAKING H AC2A K NONE K FLUID LOSS IN INSP/MAINT 1 FS 01 5403C 760141 PART LEAKS AT CONNECTOR. REPLACED CHIP DETECTOR 1 G 7 2 3U H1NE 2001050700577 20010507 00577 EU 2001 5 7 AC2A072778 1 20010125 G 2435 230321825 STATOR BOLKMS 105 BO105S 5626006 EU STARTER GEN GROUNDED H AC2A O OTHER O OTHER NR NOT REPORTED 1 FS 01 8775 8034 775 PART IS CIRCUIT-GROUNDED. REPLACED STATOR. 1 G 7 2 3U H3EU 2001050700578 20010507 00578 EU 2001 5 7 AC2A072779 1 20010125 G 2435 230322111 ARMATURE BOLKMS 105 BO105S 5626006 EU STARTER GEN GROUNDED H AC2A O OTHER O OTHER NR NOT REPORTED 1 FS 01 8776 776 PART IS CIRCUIT-GROUNDED. REPLACED ARMATURE 1 G 7 2 3U H3EU 2001050700579 20010507 00579 EU 2001 5 7 AC2A072780 1 20010125 G 2435 230322111 ARMATURE BOLKMS 105 BO105S 5626006 EU STARTER GEN GROUNDED H AC2A O OTHER O OTHER NR NOT REPORTED 1 FS 01 8775 775 PART IS CIRCUIT-GROUNDED. REPLACED ARMATURE. 1 G 7 2 3U H3EU 2001050700580 20010507 00580 GL 2001 5 7 AC2A072781 2 20010130 G 7230 23039791 SPLINE ADAPTER 6890550 BELL 206 206B3 1181506 SW ALLSN 250C 250C* GL COMPRESSOR CORRODED H AC2A K NONE O OTHER IN INSP/MAINT 1 FS 01 21460 1562 41256 4075 COMPRESSOR WAS REMOVED TO FACILITATE GEARBOX MAINTENANCE. SPLINE ADAPTER WEAR WAS CHECKED WITH GO-NO-GO GAUGE AND WAS FO UND TO BE WORN. SPLINE ADAPTER WAS REMOVED AND WAS FOUND TO HAVE A RING OF CORROSION PITTING AROUND OUTSIDE CIRCUMFRENCE OF ADAPTER .650 INCH FORWARD OF AFT END OF ADAPTER. LOCATION OF CORROSION IS AT THE POINT WHERE THE ADAPTER SEATS INTO THE IMPELLER AT THE JUNCTION OF THE AFT END OF THE IMPELLER AND THE ADAPTER. CORROSION IS AT THE SAME LOCATION WHERE A P REVIOUS SPLINE ADAPTER FAILED HERE AT CHEVRON RESULTING IN AN IN FLIGHT ENGINE FAILURE AND UNSCHEDULED LANDING. SPLINE A DAPTER FIT AND INSTALLATION WAS IN ACCORDANCE WITH MAINTENANCE INSTRUCTIONS. SPLINE ADAPTER WAS REPLACED. COMPRESSOR I 1 G 7 1 3U 3 U H2SW E4CE 2001050700581 20010507 00581 GL 2001 5 7 AC2A072782 2 20010130 G 7230 23039791 SPLINE ADAPTER 6890550 BOLKMS 105 BO105S 5626006 EU ALLSN 250C 250C20B 03013 GL COMPRESSOR CORRODED H AC2A K NONE O OTHER IN INSP/MAINT 1 FS 01 59588 756 41394 780 COMPRESSOR WAS REMOVED DUE TO F.O.D. SPLINE ADAPTER WAS REMOVED IN ORDER TO DISASSEMBLE COMPRESSOR ROTOR FOR REPAIR. SPL INE ADAPTER WAS FOUND TO HAVE A RING OF CORROSION AROUND OUTSIDE CIRCUMFRENCE OF ADAPTER .650 INCH FROM REAR END OF ADAP TER. CORROSION IS AT THE POINT WHERE THE ADAPTER SEATS INTO THE IMPELLER AT THE JUNCTION OF THE ADAPTER AND THE REAR END OF THE IMPELLER. CORROSION IS AT THE SAME LOCATION WHERE CHEVRON PREVIOUSLY HAD AN ADAPTER FAIL THAT RESULTED IN AN IN FLIGHT ENGINE FAILURE AND UNSCHEDULED LANDING. SPLINE ADAPTER FIT AND INSTALLATION WERE IN ACCORDANCE WITH MAINTENANCE I NSTRUCTIONS. SPLINE ADAPTER WAS REPLACED. COMPRESSOR IS STILL IN SPARES AT THIS TIME AND HAS NOT BEEN RETURNED TO SERVIC 1 G 7 2 3U 3 U H3EU E4CE 2001050700582 20010507 00582 GL 2001 5 7 AC2A072783 2 20010213 G 7210 23063371 SEAL BELL 206 206L3 1182108 SW ALLSN 250B 250B* GL GEARBOX LEAKING H AC2A A UNSCHED LANDING K J FLUID LOSS WARNING INDICATION CR CRUISE 1 FS 01 7159J 51408 AIRCRAFT WAS GROUND RUN AND LEAK CHECKED FOLLOWING ENGINE CHANGE. NO LEAKS FOUND. AIRCRAFT RETURNED AFTER 20 MINUTE TE ST FLIGHT. OIL WAS FOUND IN THE ENGINE PAN. OIL LEAKING FROM STARTER-GENERATOR SEAL ON ENGINE GEARBOX. REPLACED SEAL. UPON INSPECTION OF SEAL, IT WAS FOUND TO HAVE A TEAR OR CUT HALF WAY AROUND THE INSIDE CIRCUMFERENCE OF THE SEAL. 1 G 7 1 3U 3 T H2SW E10CE 2001050700583 20010507 00583 NE 2001 5 7 AC2A072784 2 20010311 G 7532 23005366 BLEED VALVE BELL 430 430 1182150 SW ALLSN 250C 250C40B 03032 NE ENGINE LOOSE H AC2A K NONE O OTHER IN INSP/MAINT 1 FS 01 430CH 46 49037 844154 BLEED VALVE HOUSING WAS LOOSE. REPLACED DIAPHRAGM. REASSAMBLED AND PERFORMED TEST. 1 G 7 2 3U 3 U RT H9SW E1GL 2001051500109 20010515 00109 CE 2001 5 15 AC2A072785 1 20010311 G 7810 12502642 EXHAUST PIPE CESSNA 206 U206G 2073356 CE CONT O520 IO520F 17032 SO ENGINE CRACKED H AC2A K NONE O OTHER IN INSP/MAINT 1 FS 01 5357 EXHAUST COLLECTOR FOUND CRACKED REPLACED WITH NEW COLLECTOR 1 H 7 1 3O 3 O A4CE E5CE 2001050700584 20010507 00584 NE 2001 5 7 AC2A072786 2 20010327 G 7320 AN8378J ELBOW BELL 430 430 1182150 SW ALLSN 250C 250C40B 03032 NE ENGINE LEAKING H AC2A K NONE K FLUID LOSS IN INSP/MAINT 1 FS 01 430CV 46 49072 844154 FUEL LEAK ON LINE FROM CEFA TO HMU. FOUND ELBOW ON CEFA HAD A MILLING MARK ON FACE OF FLANGE. REPLACED ELBOW. 1 G 7 2 3U 3 U RT H9SW E1GL 2001050700585 20010507 00585 NE 2001 5 7 AC2A072787 2 20010327 G 7261 6871937 LINE BELL 430 430 1182150 SW ALLSN 250C 250C40B 03032 NE ENGINE LEAKING H AC2A K NONE K FLUID LOSS IN INSP/MAINT 1 FS 01 430CV 46 49072 844154 OIL LEAK ON INBOARD SIDE OF NR 1 ENGINE. FOUND TUBE ASSY FROM CHECK VALVE TO GEAR BOX HOUSING WOULD NOT SEAT PROPERLY. R EPLACED TUBE ASSY. 1 G 7 2 3U 3 U RT H9SW E1GL 2001050700586 20010507 00586 SW 2001 5 7 AC2A072788 1 20010331 G 2432 RG222 BATTERY BELL 206 206L3 1182108 SW MAIN WEAK H AC2A K NONE O OTHER IN INSP/MAINT 1 FS 01 7159J 319 51408 PART IS WEAK. REPLACED BATTERY WITH A NEW PART 1 G 7 1 3U H2SW 2001050700587 20010507 00587 2001 5 7 AC2A072789 4 20010402 G 3416 1042011968E ALTIMETER SKRSKY S76 S76A 8143006 NE COCKPIT OUT OF TOLERANCE H AC2A K NONE L NO TEST IN INSP/MAINT 1 FS 01 5403C 760141 VIBRATOR INOP,AUTOPILOT CORRECTION POTENTIOMETER OUT OF TOLERANCE AND OFF FLAG STICKS. REPLACED INST. 1 G 7 2 3U H1NE 2001050700588 20010507 00588 NE 2001 5 7 AC2A072790 1 20010405 G 2435 03600923 BEARING 23081018 SKRSKY S76 S76A 8143006 NE DRIVE END DETERIORATED H AC2A O OTHER O OTHER NR NOT REPORTED 1 FS 01 5401G 907 3361 760137 PART IS DETERIORATED. BEARING CAGE FAILED ALLOWING ALL BALLS TO GROUP TOGETHER. NO BALLS WERE LOST OR DETERIORATED OVERH AULED STARTER - GENERATOR AND REPLACED BEARINGS. 1 G 7 2 3U H1NE 2001050700589 20010507 00589 2001 5 7 AC2A072791 4 20010416 G 2210 065001580211 COMPUTER BELL 430 430 1182150 SW COCKPIT FAILED H AC2A K NONE L NO TEST IN INSP/MAINT 1 FS 01 430CV 105 49072 AFCS PIT CAUTION LIGHT DURING AP2 TEST. AP2 & SAS2 CAUTION LIGHT REMAINS ON AFTER COMPLETION OF TEST. AFCS PIT CAUTION LIGHT ILLUMINATES WHEN IN AP2. REPLACED WITH NEW PART. 1 G 7 2 3U RT H9SW 2001051000139 20010510 00139 SW 2001 5 10 AC2A072803 1 20010101 G 6220 430010101101 YOKE BELL 430 430 1182150 SW ROTOR HEAD CRACKED H AC2A K NONE O OTHER IN INSP/MAINT 1 FS 01 430CH 2862 49037 SPAN-WISE CRACK ON TOP APPROX 12 INCHES FROM CENTER. REPLACED. 1 G 7 2 3U RT H9SW 2001051000140 20010510 00140 SW 2001 5 10 AC2A072804 1 20010101 G 6220 430010101101 YOKE BELL 430 430 1182150 SW MAIN ROTOR CRACKED H AC2A K NONE O OTHER IN INSP/MAINT 1 FS 01 430CH 2862 49037 SPAN-WISE CRACK 12 INCHES FROM CENTER. REPLACED. 1 G 7 2 3U RT H9SW 2001051000141 20010510 00141 SW 2001 5 10 AC2A072805 1 20010101 G 6410 222016001131 BLADE BELL 430 430 1182150 SW TAIL ROTOR CRACKED H AC2A K NONE O OTHER IN INSP/MAINT 1 FS 01 430CH 1742 49037 FEATHERING BEARINGS CRACKED. FEATHERING BEARINGS WERE REPLACED BEFORE THIS AT TIME 589.4. THE BLADE HAS 1152.8 SINCE R EPLACEMENT OF BEARINGS. REPLACED BLADE 1 G 7 2 3U RT H9SW 2001051000142 20010510 00142 SW 2001 5 10 AC2A072806 1 20010101 G 6510 430044100101 DRIVE SHAFT BELL 430 430 1182150 SW TAIL ROTOR CORRODED H AC2A K NONE O OTHER IN INSP/MAINT 1 FS 01 430CH 2862 49037 CORROSION AROUND FLANGE AREA. DRIVE SHAFTS WERE NR 2 & 3 AND AREA OF CORROSION WAS NEAR WHERE OILCOOLER COWLING AND TAI L DRIVE SHAFT COWLING MEET. REPLACED DRIVE SHAFTS. 1 G 7 2 3U RT H9SW 2001051000143 20010510 00143 SW 2001 5 10 AC2A072807 1 20010101 G 6220 430310101105 SHEAR RESTRAINT BELL 430 430 1182150 SW MAIN ROTOR DELAMINATED H AC2A K NONE O OTHER IN INSP/MAINT 1 FS 01 430CH 2862 49037 DELAMINATING FROM SHAFT REPLACED SHEAR RESTRAINT. 1 G 7 2 3U RT H9SW 2001051000144 20010510 00144 SW 2001 5 10 AC2A072808 1 20010101 G 6300 430010212101 RESTRAINT BELL 430 430 1182150 SW MAIN ROTOR DRIVE DEBONDED H AC2A K NONE O OTHER IN INSP/MAINT 1 FS 01 430CH 2862 49037 ELASTOMERIC DEBONDING REPLACED RESTRAINT 1 G 7 2 3U RT H9SW 2001051000145 20010510 00145 SW 2001 5 10 AC2A072809 1 20010101 G 6710 222382001107 ACTUATOR BELL 430 430 1182150 SW FLIGHT CONTROL LEAKING H AC2A K NONE K FLUID LOSS IN INSP/MAINT 1 FS 01 430CH 2862 49037 LEAKING, REPLACED ACTUATOR. 1 G 7 2 3U RT H9SW 2001051000146 20010510 00146 SW 2001 5 10 AC2A072810 1 20010101 G 7120 430360051101 MOUNT BELL 430 430 1182150 SW ENGINE WORN H AC2A K NONE O OTHER IN INSP/MAINT 1 FS 01 430CH 2862 49037 REAR ENGINE MOUNT BEARING AT DECK WORN. BALL (P/N 230-360-101-103) NOT WORN. ROD END BODY (P/N 230-360-101-105) WAS WOR N. REPLACED MOUNT 1 G 7 2 3U RT H9SW 2001051000147 20010510 00147 SW 2001 5 10 AC2A072811 1 20010101 G 6210 430015001123 BLADE BELL 430 430 1182150 SW MAIN ROTOR CRACKED H AC2A K NONE O OTHER IN INSP/MAINT 1 FS 01 430CH 1370 49037 CRACKED INBOARD TRIM TAB REPLACED TRIM TAB 1 G 7 2 3U RT H9SW 2001051000148 20010510 00148 SW 2001 5 10 AC2A072812 1 20010129 G 7921 230365001101 BLOWER BELL 430 430 1182150 SW ALLSN 250C 250C40B 03032 NE OIL COOLER DEFECTIVE H AC2A K NONE O OTHER IN INSP/MAINT 1 FS 01 430CH 693 49037 BEARING MAKES CLICKING SOUND AND CORROSION NEAR REAR NUT. PART WAS NEVER INSTALLED ON AIRCRAFT DUE TO THIS. 1 G 7 2 3U 3 U RT H9SW E1GL 2001051000149 20010510 00149 SW 2001 5 10 AC2A072813 1 20010202 G 7810 206064300005 EXHAUST STACK BELL 206 206L3 1182108 SW ENGINE CRACKED H AC2A K NONE O OTHER IN INSP/MAINT 1 FS 01 31079 296 51526 CRACKED. 1 G 7 1 3U H2SW 2001051000150 20010510 00150 SW 2001 5 10 AC2A072814 1 20010205 G 7810 206064300005 EXHAUST STACK BELL 206 206L3 1182108 SW ENGINE CRACKED H AC2A K NONE O OTHER IN INSP/MAINT 1 FS 01 53702 90 51249 CRACKED. 1 G 7 1 3U H2SW 2001051000151 20010510 00151 SW 2001 5 10 AC2A072815 1 20010220 G 2910 70053H000A100A HOSE BELL 206 206L3 1182108 SW HYD SYSTEM LEAKING H AC2A B A EMER. DESCENT UNSCHED LANDING K J FLUID LOSS WARNING INDICATION CR CRUISE 1 FS 01 17592 51535 AT CRUISE TO LEEVILLE (LA) HELIPORT, THE PILOT HEARD A LOUD GRINDING NOISE FOLLOWED BY COMPLETE HYDRAULIC FAILURE. THE PILOT PERFORMED THE EMERGENCY PROCEDURE THEN CONFIRMED IT WITH THE BOOK WITH NO CORRECTION TO THE EMERGENCY. PILOT PER FORMED A SHALLOW APPROACH WITH A SLIGHT RUN ON LANDING, AND SHUT DOWN THE AIRCRAFT. REPLACED HYDRAULIC LINE P/N 70-053H0 00A100A. 1 G 7 1 3U H2SW 2001051000152 20010510 00152 SW 2001 5 10 AC2A072817 1 20010223 G 3340 AN33201 RELAY BELL 206 206B3 1181506 SW LANDING LIGHT FAILED H AC2A O OTHER O OTHER NR NOT REPORTED 1 FS 01 7131U 9 4111 RELAY FAILED AFTER 41 DAYS ON THE AIRCRAFT. THE LANDING LIGHT WAS INOPERABLE. 1 G 7 1 3U H2SW 2001051000153 20010510 00153 SW 2001 5 10 AC2A072818 1 20010306 G 7810 206064300005 EXHAUST STACK BELL 206 206L3 1182108 SW ENGINE CRACKED H AC2A K NONE O OTHER IN INSP/MAINT 1 FS 01 7159H 441 51397 CRACKED. REPLACED PART. 1 G 7 1 3U H2SW 2001051000154 20010510 00154 SW 2001 5 10 AC2A072819 1 20010311 G 6210 4300150037101 EROSION SHIELD 430015001123 BELL 430 430 1182150 SW MAIN ROTOR BLADE DAMAGED H AC2A K NONE O OTHER IN INSP/MAINT 1 FS 01 430CV A1118 49072 EROSION TAPE FOR MAIN ROTOR BLADE WAS FOUND BUBBLED. FUTHER INSPECTION FOUND BUBBLE WAS FULL OF WATER. THERE WAS NO SIGN OF AREA OF ENTRY. REPLACED EROSION TAPE. 1 G 7 2 3U RT H9SW 2001051500110 20010515 00110 SW 2001 5 15 AC2A072820 1 20010311 G 6230 430010105105 PLATE 430010100113 BELL 430 430 1182150 SW MAIN ROTOR LOOSE H AC2A K NONE O OTHER IN INSP/MAINT 1 FS 01 46 A166 CLAMP PLATE WAS NOT SHIMED PROPERLY ON SHEAR RESTRAINT. RESHIMED CLAMP PLATE. 1 G 7 2 3U RT H9SW 2001051000155 20010510 00155 SW 2001 5 10 AC2A072821 1 20010311 G 5210 LATCH BELL 430 430 1182150 SW CREW DOOR OUT OF ADJ H AC2A K NONE O OTHER IN INSP/MAINT 1 FS 01 430CV 46 49072 CABIN DOOR WAS EXTREMELY HARD TO OPEN AND WOULD NOT CLOSE PROPERLY. AJUSTED DOOR LATCHES. 1 G 7 2 3U RT H9SW 2001051000156 20010510 00156 SW 2001 5 10 AC2A072822 1 20010311 G 7500 230025203101 TUBE BELL 430 430 1182150 SW ENGINE BLEED AIR CHAFED H AC2A K NONE O OTHER IN INSP/MAINT 1 FS 01 430CV 46 49072 CUSTOMER BLEED AIR TUBE HAD A WORN SPOT FROM THE UPPER ENGINE COWLING(PN 230-061-803-104). REPLACED TUBE ASSY AND REPAIR ED COWLING. 1 G 7 2 3U RT H9SW 2001051000157 20010510 00157 SW 2001 5 10 AC2A072823 1 20010311 G 5320 222035165164 CLIP BELL 430 430 1182150 SW FUSELAGE MISINSTALLED H AC2A K NONE O OTHER IN INSP/MAINT 1 FS 01 430CV 46 49072 TAIL ROTOR DRIVE SHAFT COVER (PN 222-035-165-179) WAS RUBBING TAIL ROTOR DRIVE SHAFT SUPPORT BEARING SUPPORT (PN 430-035 -164-105). CAUSE OF RUBBING WAS FORWARD TAIL ROTOR DRIVE SHAFT COWLING CLIP (PN 222-025-165-164) WAS INSTALLED TO CLOSE TOGETHER AND DID NOT GIVE SUFFICIENT CLEARENCE FOR SUPPORT. ADDED SPACER PAD BETWEEN DRIVE SHAFT COVER AND CLIP. 1 G 7 2 3U RT H9SW 2001051000158 20010510 00158 SW 2001 5 10 AC2A072824 1 20010311 G 6200 2006508083 BOLT BELL 430 430 1182150 SW MAIN ROTOR CORRODED H AC2A K NONE O OTHER IN INSP/MAINT 1 FS 01 430CV 46 49072 WHILE REMOVING MAIN ROTOR YOKES WATER CAME OUT OF AREA OF MAIN ROTOR DRIVE BUSHINGS AND MAIN ROTOR BOLTS. DRIVE PLATE WA S FOUND NOT TO BE SEALED PROPERLY AND 2 MAIN ROTOR BOLTS WERE FOUND TO HAVE CORROSION PITTING. REPLACED BOLTS AND SEALED PROPERLY. 1 G 7 2 3U RT H9SW 2001051000159 20010510 00159 SW 2001 5 10 AC2A072825 1 20010325 G 6520 222342402101 SEAL 222042001103 BELL 430 430 1182150 SW TAIL ROTOR G/B LEAKING H AC2A K NONE K FLUID LOSS IN INSP/MAINT 1 FS 01 430CV 46 A270 49072 TAIL ROTOR GEAR BOX WAS LEAKING FROM OUT PUT SEAL. WHEN SEAL WAS RENOVED IT WAS DISCOVERED THAT THE SEAL LIP HAD SEALENT MIL-S-8784 ON IT. THIS SEALENT IS USED ON THE OUTER SURFACE OF THE SEAL WHEN INSTALLING. REPLACED SEAL. 1 G 7 2 3U RT H9SW 2001051000160 20010510 00160 SW 2001 5 10 AC2A072826 1 20010403 G 3213 206323017 CROSSTUBE BELL 206 206L3 1182108 SW LANDING GEAR CORRODED H AC2A K NONE O OTHER IN INSP/MAINT 1 FS 01 31079 602 51526 PART HAS INTERGRANULAR CORROSION SEVERAL PLACES ON TUBE. THIS FORWARD CROSSTUBE HAD ONLY 602 HOURS SINCE INSTALLATION, THE CORROSION WAS EXTENSIVE AND BEYOND LIMITS. REPLACED CROSSTUBE WITH NEW PART. 1 G 7 1 3U H2SW 2001051000161 20010510 00161 2001 5 10 AC2A072827 4 20010416 G 3425 430375002107 DISPLAY BELL 430 430 1182150 SW EFIS FAILED H AC2A O OTHER O OTHER NR NOT REPORTED 1 FS 01 430CV 105 49072 SCREEN WENT BLANK IN FLIGHT. REPLACED PART. 1 G 7 2 3U RT H9SW 2001051000162 20010510 00162 SW 2001 5 10 AC2A072828 1 20010416 G 2436 222375060115 VOLT REGULATOR BELL 430 430 1182150 SW ELECTRICAL DEFECTIVE H AC2A K NONE O OTHER IN INSP/MAINT 1 FS 01 430CH 49037 REGULATOR WAS INOPERATIVE WHEN WE RECEIVED IT FROM BELL. EXCHANGING THIS PART FOR A NEW ONE. 1 G 7 2 3U RT H9SW 2001051000163 20010510 00163 SW 2001 5 10 AC2A072829 1 20010419 G 2910 70012H000Y264 HOSE BELL 430 430 1182150 SW TRANSMISSION CHAFED H AC2A K NONE O OTHER IN INSP/MAINT 1 FS 01 430CV 122 49072 PART IS CHAFED. LINE CHAFED ON TRANSMISSION COWLING. INSTALLED NEW LINE. REPOSITIONED ELBOW FOR NEW LINE TO CLEAR TRAN SMISSION COWLING. 1 G 7 2 3U RT H9SW 2001051000164 20010510 00164 SW 2001 5 10 AC2A072830 1 20010426 G 2622 40000MODLE11211 EXTINGUISHER BELL 206 206L3 1182108 SW CABIN DISCHARGED H AC2A K NONE O OTHER IN INSP/MAINT 1 FS 01 17237 301 51478 FIRE EXTINGUISHER HAD LOW WEIGHT. REPLACED WITH NEW FIRE EXTINGUISHER. 1 G 7 1 3U H2SW 2001051000165 20010510 00165 SW 2001 5 10 AC2A072831 1 20010426 G 7810 206064300005 EXHAUST STACK BELL 206 206L3 1182108 SW ENGINE CRACKED H AC2A K NONE O OTHER IN INSP/MAINT 1 FS 01 6533U 187 51439 PART IS CRACKED. REPLACED WITH NEW EXHAUST. 1 G 7 1 3U H2SW 2001051000166 20010510 00166 SW 2001 5 10 AC2A072832 1 20010426 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 815 51535 CRACKED. REPLACED EXHAUST ASSY. 1 G 7 1 3U H2SW 2001051000179 20010510 00179 GL 2001 5 10 AC2A072834 2 20010306 G 7323 23065123 GOVERNOR BOLKMS 105 BO105S 5626006 EU ALLSN 250C 250C20B 03013 GL NR 1 ENGINE DEBONDED H AC2A A UNSCHED LANDING J WARNING INDICATION CL CLIMB 1 FS 01 5366Y 8130 782 PILOT REPORTED N2 OVERSPEED UNCONTROLLABLE WITH RPM TRIM MOTOR. NR 1 ENGINE RETURNED TO FLIGHT IDLE. FUEL JETTISONED, AND PILOT PERFORMED RUN-ON LANDING. REMOVED GOVERNOR AND FOUND DRIVE SPLINE DISENGAGED FROM GOVERNOR SHAFT. GOVERNOR REP LACEMENT FIXED PROBLEM. 1 G 7 2 3U 3 U H3EU E4CE 2001051000180 20010510 00180 GL 2001 5 10 AC2A072835 2 20010319 G 7323 23004831 GOVERNOR BOLKMS 105 BO105S 5626006 EU ALLSN 250C 250C20B 03013 GL ENGINE DEBONDED H AC2A K NONE O OTHER IN INSP/MAINT 1 FS 01 5366Y 1888 782 UNBONDED SHAFT. 1 G 7 2 3U 3 U H3EU E4CE 2001051000181 20010510 00181 GL 2001 5 10 AC2A072836 2 20010319 G 7323 23065123 GOVERNOR BOLKMS 105 BO105S 5626006 EU ALLSN 250C 250C20B 03013 GL ENGINE CRACKED H AC2A K NONE O OTHER IN INSP/MAINT 1 FS 01 8776 11601 776 CHECKED DRIVE COUPLING AND FOUND DEFECTIVE. 1 G 7 2 3U 3 U H3EU E4CE 2001051000182 20010510 00182 GL 2001 5 10 AC2A072837 2 20010319 G 7323 23065123 GOVERNOR BELL 206 206B3 1181506 SW ALLSN 250C 250C20B 03013 GL ENGINE DEBONDED H AC2A K NONE O OTHER IN INSP/MAINT 1 FS 01 7131U 9381 4111 DRIVE COUPLING DEBONDED. 1 G 7 1 3U 3 U H2SW E4CE 2001051000183 20010510 00183 GL 2001 5 10 AC2A072838 2 20010425 G 7323 23065123 GOVERNOR BOLKMS 105 BO105S 5626006 EU ALLSN 250C 250C20B 03013 GL NR 2 ENGINE BROKEN H AC2A K NONE O OTHER IN INSP/MAINT 1 FS 01 8775 7744 775 POTTING ON END OF DRIVE GEAR IS BROKEN LOOSE. REMOVED GOVERNOR. 1 G 7 2 3U 3 U H3EU E4CE 2001091900004 20010919 00004 SW 2001 9 19 AC2A075785 1 20010502 G 6310 206040272101 SEAL BELL 206 206L3 1182108 SW INPUT SHAFT LEAKING H AC2A K NONE O OTHER IN INSP/MAINT 1 FS 01 17237 614 51478 PARTS ARE LEAKING GREASE. REPLACED SEALS. 1 G 7 1 3U H2SW 2001091900005 20010919 00005 EU 2001 9 19 AC2A075786 1 20010502 G 7810 59528AELPSW3 CLAMP BOLKMS 105 BO105S 5626006 EU EXHAUST STACK CRACKED H AC2A K NONE O OTHER IN INSP/MAINT 1 FS 01 59588 286 780 PART WAS FOUND CRACKED WHILE WHILE PERFORMONG NDT INSPECTION AS PER ASB BO-105-60-107. REPLACED CLAMP. 1 G 7 2 3U H3EU 2001091900006 20010919 00006 GL 2001 9 19 AC2A075787 2 20010502 G 7323 23065123 GOVERNOR BOLKMS 105 BO105S 5626006 EU ALLSN 250C 250C20B 03013 GL NR 1 ENGINE CRACKED H AC2A K NONE O OTHER IN INSP/MAINT 1 FS 01 5366Y 7199 782 836103 EPOXY DEBONDED ON GOVERNOR DRIVE SHAFT. REMOVED FROM SERVICE AND SENT IN FOR WARRANTY REPAIR. 1 G 7 2 3U 3 U H3EU E4CE 2001091900007 20010919 00007 EU 2001 9 19 AC2A075788 1 20010507 G 6340 32005007 TACH GENERATOR BOLKMS 105 BO105S 5626006 EU TRANSMISSION DEFECTIVE H AC2A C ABORTED TAKEOFF J WARNING INDICATION TO TAKEOFF 1 FS 01 826MB 18 771 PART IS DEFECTIVE. ROTOR INDICATIONS WERE ZERO ON CRANK-UP REPLACED TACH/GEN 1 G 7 2 3U H3EU 2001091900008 20010919 00008 EU 2001 9 19 AC2A075789 1 20010507 G 6240 32005007 TACH GENERATOR BOLKMS 105 BO105S 5626006 EU MAIN ROTOR DEFECTIVE H AC2A A UNSCHED LANDING E VIBRATION/BUFFET CR CRUISE 1 FS 01 826MB 2 771 PART IS DEFECTIVE.CAUSED HIGH RPM AUDIO TO SOUND DURING NORMAL OPERATION. REPLACED TACH/GEN 1 G 7 2 3U H3EU 2001091900009 20010919 00009 EU 2001 9 19 AC2A075790 1 20010507 G 7714 32005023 TACH GENERATOR BOLKMS 105 BO105S 5626006 EU NR 1 ENGINE ERRATIC H AC2A C ABORTED TAKEOFF J WARNING INDICATION TO TAKEOFF 1 FS 01 826MB 771 PART IS INDICATIONS.N1 INDICATIONS WERE IRRATIC. REPLACED TACH/GEN. 1 G 7 2 3U H3EU 2001091900010 20010919 00010 EU 2001 9 19 AC2A075791 1 20010507 G 6340 KDW021A WARNING SYSTEM BOLKMS 105 BO105S 5626006 EU ROTOR RPM MALFUNCTIONED H AC2A O OTHER N FALSE WARNING NR NOT REPORTED 1 FS 01 826MB 771 PART IS INDICATIONS. PILOT EXPERIENCED "HI RPM" LIGHT AND AUDIO DURING NORMAL OPERATION. REPLACED RPM WARNING BOX. 1 G 7 2 3U H3EU 2001091900011 20010919 00011 EU 2001 9 19 AC2A075792 1 20010507 G 6240 22021002 WARNING SYSTEM BOLKMS 105 BO105S 5626006 EU ROTOR RPM MALFUNCTIONED H AC2A O OTHER N FALSE WARNING CR CRUISE 1 FS 01 826MB 771 PART IS INDICATIONS.LOUD STATIC IN HEAD SET AND "HI AUDIO" INDICATIONS DURING NORMAL OPERATION. REPLACED RPM WARNING BOX 1 G 7 2 3U H3EU 2001091900012 20010919 00012 SW 2001 9 19 AC2A075793 1 20010507 G 7810 206064300005 EXHAUST STACK BELL 206 206L3 1182108 SW ENGINE CRACKED H AC2A K NONE O OTHER IN INSP/MAINT 1 FS 01 17237 597 51478 FOUND CRACKED AT REAR SEAM. REMOVED AND REPLACED STACK. 1 G 7 1 3U H2SW 2001091900013 20010919 00013 SW 2001 9 19 AC2A075795 1 20010512 G 3246 206323017 CROSSTUBE BELL 206 206L3 1182108 SW MLG CORRODED H AC2A K NONE O OTHER IN INSP/MAINT 1 FS 01 17238 1199 51492 PART IS CORRODED. REMOVED,REPLACED FORWARD CROSS TUBE 1 G 7 1 3U H2SW 2001091900014 20010919 00014 SW 2001 9 19 AC2A075796 1 20010514 G 6410 222312753103 BEARING 222016001131 BELL 430 430 1182150 SW T/R BLADE CRACKED H AC2A K NONE O OTHER IN INSP/MAINT 1 FS 01 430CH 501 A1712 49037 BEARINGS ARE CRACKED. REPLACED BEARINGS WITH NEW. 1 G 7 2 3U RT H9SW 2001091900015 20010919 00015 SW 2001 9 19 AC2A075797 1 20010518 G 7810 206064300005 EXHAUST STACK BELL 206 206L3 1182108 SW ENGINE CRACKED H AC2A K NONE O OTHER IN INSP/MAINT 1 FS 01 53702 434 51249 FOUNDED CRACKED AT REAR SEAM. REMOVED AND REPLACED STACK. 1 G 7 1 3U H2SW 2001091900016 20010919 00016 NE 2001 9 19 AC2A075798 1 20010518 G 2435 230811011 ARMATURE 23081002 SKRSKY S76 S76A 8143006 NE SHORTED H AC2A K NONE O OTHER IN INSP/MAINT 1 FS 01 643 PART IS CIRCUIT-SHORTED. REMOVED DEFECTIVE PART AND INSTALLED A SERVICABLE PART. 1 G 7 2 3U H1NE 2001091900017 20010919 00017 SW 2001 9 19 AC2A075799 1 20010529 G 7430 1064BH1436 SWITCH BELL 430 430 1182150 SW IGNITION SHORTED H AC2A O OTHER O OTHER NR NOT REPORTED 1 FS 01 430CV 263 49072 MICRO SWITCH FAILED TO ENGAGE ENGINE STARTER OR HOLDING COIL. REPLACED SWITCH. 1 G 7 2 3U RT H9SW 2001091900019 20010919 00019 SW 2001 9 19 AC2A075800 1 20010529 G 5210 NAS5623R7A CAM FOLLOWER BELL 430 430 1182150 SW DOOR CRACKED H AC2A O OTHER O OTHER NR NOT REPORTED 1 FS 01 430CV 258 49072 BEARING RACE CRACKED. INSIDE OF BEARING FALLING APART.. REPLACED CAMFOLLOWER. 1 G 7 2 3U RT H9SW 2001091900020 20010919 00020 SW 2001 9 19 AC2A075801 1 20010607 G 6510 430010124103 BUSHING BELL 430 430 1182150 SW MAIN ROTOR WORN H AC2A K NONE O OTHER IN INSP/MAINT 1 FS 01 430CH 2268 49037 PART IS WORN EXCESSIVELY. ALL EIGHT M/R DRIVE BUSHINGS ARE WORN BEYOND LIMITS ALLOWED IN BHT-430-CR&O-2. 1 G 7 2 3U RT H9SW 2001091900021 20010919 00021 SW 2001 9 19 AC2A075803 1 20010612 G 6230 430310461101 BEARING BELL 430 430 1182150 SW SWASHPLATE RATCHETING H AC2A K NONE O OTHER IN INSP/MAINT 1 FS 01 430CH 49037 WITH SWASHPLATE INSTALLED ON ACFT. BEARING FELT RATCHETY. BEARING WAS THE NEW UPDATED STLYE. REMOVED AND REPLACED BEARI NG. 1 G 7 2 3U RT H9SW 2001091900022 20010919 00022 SW 2001 9 19 AC2A075804 1 20010612 G 6220 MS1652245 PIN BELL 430 430 1182150 SW MAIN ROTOR BROKEN H AC2A K NONE O OTHER IN INSP/MAINT 1 FS 01 430CH 3447 49037 FOUND SHEAR RESTRAINT LOOSE AND UPON DISASSEMBLY FOR INSP. FOUND PIN BROKEN. REPLACED BROKEN PIN AND WORN RESTRAINT. 1 G 7 2 3U RT H9SW 2001091900023 20010919 00023 SW 2001 9 19 AC2A075805 1 20010612 G 6220 430310101107 RESTRAINT 430010100113 BELL 430 430 1182150 SW MAIN ROTOR LOOSE H AC2A K NONE O OTHER IN INSP/MAINT 1 FS 01 430CH 585 A123 49037 FOUND LOOSE ON INSP. AND UPON DISASSEMBLY FOUND ROLL PIN BROKEN WHICH ALLOWED MOVEMENT IN CLAMP-UP. REPLACED RESTRAINT A ND PIN. 1 G 7 2 3U RT H9SW 2001091900025 20010919 00025 NE 2001 9 19 AC2A075810 1 20010625 G 6320 7635109082105 CHIP DETECTOR SKRSKY S76 S76A 8143006 NE M/R GEARBOX SHORTED H AC2A K NONE O OTHER IN INSP/MAINT 1 FS 01 7266F 760273 PART IS CIRCUIT-SHORTED. REPLACED WITH SERVICEABLE PART 1 G 7 2 3U H1NE 2001091900026 20010919 00026 SW 2001 9 19 AC2A075812 1 20010626 G 7810 206064300005 EXHAUST STACK BELL 206 206L3 1182108 SW ALLSN 250C 250C* GL ENGINE CRACKED H AC2A K NONE O OTHER IN INSP/MAINT 1 FS 01 715CC 1539 51380 EXHAUST IS CRACKED. REPLACED WITH NEW. 1 G 7 1 3U 3 U H2SW E4CE 2001091900027 20010919 00027 GL 2001 9 19 AC2A075813 2 20010628 G 7261 6870032 FILTER ALLSN 250C 250C20B 03013 GL ENGINE OIL DETERIORATED H AC2A K NONE O OTHER IN INSP/MAINT 1 FS 01 PART IS DETERIORATED. THE OUTSIDE SCREEN IS EATEN AWAY EXPOSING THE MORE COARSE SCREEN. REPLACED FILTER ASSY. 3 U E4CE 2001091900030 20010919 00030 NE 2001 9 19 AC2A075814 2 20010702 G 7532 23005366 BLEED VALVE BELL 430 430 1182150 SW ALLSN 250C 250C40B 03032 NE ENGINE LOOSE H AC2A O OTHER R J PARTIAL RPM/PWR LOSS WARNING INDICATION NR NOT REPORTED 1 FS 01 430CV 374 49072 POWER ASSURANCE LOW NR 1 ENGINE. FOUND NR 1 ENGINE BLEED VALVE BODY BOLTS LOOSE. REPLACED WITH REPAIRED BLEED VALVE. 1 G 7 2 3U 3 U RT H9SW E1GL 2001091900031 20010919 00031 EU 2001 9 19 AC2A075815 1 20010709 G 6320 4638304001 SUN GEAR BOLKMS 105 BO105S 5626006 EU M/R GEARBOX FLAKING H AC2A K NONE O OTHER IN INSP/MAINT 1 FS 01 8775 673 775 DRIVE SIDE TOP CORNER OF TOOTH FLAKING. REPAIRED. 1 G 7 2 3U H3EU 2001091900035 20010919 00035 GL 2001 9 19 AC2A075817 2 20010712 G 7230 23056634 GEARSHAFT SKRSKY S76 S76A 8143006 NE ALLSN 250C 250C* GL ENGINE WORN H AC2A K NONE O OTHER IN INSP/MAINT 1 FS 01 5403C 702 760141 EXCESSIVE SPLINE WEAR ON AFT END. REPLACED WITH NEW. 1 G 7 2 3U 3 U H1NE E4CE 2001091900037 20010919 00037 GL 2001 9 19 AC2A075818 2 20010712 G 7230 23031922 GEARSHAFT BELL 206 206B3 1181506 SW ALLSN 250C 250C* GL SPUR GEAR WORN H AC2A K NONE O OTHER IN INSP/MAINT 1 FS 01 7131U 962 4111 EXCESSIVELY WORN SPLINES. REPLACED WITH NEW. 1 G 7 1 3U 3 U H2SW E4CE 2001091900038 20010919 00038 SW 2001 9 19 AC2A075819 1 20010728 G 2435 230321827 STATOR 23081018 BELL 206 206L3 1182108 SW STARTER GEN SHORTED H AC2A K NONE O OTHER IN INSP/MAINT 1 FS 01 17238 3794 51492 PART IS CIRCUIT-GROUNDED. REPLACED DEFECTIVE PART 1 G 7 1 3U H2SW 2001091900039 20010919 00039 SW 2001 9 19 AC2A075820 1 20010728 G 2435 230811011 ARMATURE BELL 206 206L3 1182108 SW STARTER GEN SHORTED H AC2A K NONE O OTHER IN INSP/MAINT 1 FS 01 17238 51492 PART IS CIRCUIT-GROUNDED. 1 G 7 1 3U H2SW 2001091900050 20010919 00050 NE 2001 9 19 AC2A075821 1 20010729 G 2435 23081002 STARTER GEN SKRSKY S76 S76A 8143006 NE ENGINE LOOSE H AC2A K NONE O OTHER IN INSP/MAINT 1 FS 01 7266K 9962 760283 PART IS LOOSE. DRIVE SHAFT BECAME LOOSE WHEN FRICTION RING DISINTAGRATED. REPLACED STARTER GENERATOR. 1 G 7 2 3U H1NE 2001091900064 20010919 00064 SW 2001 9 19 AC2A075822 1 20010808 G 7931 222375077113 TRANSMITTER BELL 430 430 1182150 SW ENGINE OIL MALFUNCTIONED H AC2A K NONE O OTHER IN INSP/MAINT 1 FS 01 430CV 535 49072 INDICATOR READS 12 PSI WITHOUT ENGINE WARNING. REPLACED WITH NEW TRANSMITTER. 1 G 7 2 3U RT H9SW 2001091900085 20010919 00085 SW 2001 9 19 AC2A075823 1 20010811 G 5311 206033107121 FRAME BELL 206 206L3 1182108 SW FUSELAGE CRACKED H AC2A K NONE O OTHER IN INSP/MAINT 1 FS 01 7159H 9831 51397 FRAME IS CRACKED. REPLACED WITH NEW PART. 1 G 7 1 3U H2SW 2001091900087 20010919 00087 SW 2001 9 19 AC2A075824 1 20010811 G 5320 206033107055 STIFFENER BELL 206 206L3 1182108 SW FUSELAGE CRACKED H AC2A K NONE O OTHER IN INSP/MAINT 1 FS 01 7159H 9831 51397 STIFFENER IS CRACKED. REPLACED WITH NEW PART. 1 G 7 1 3U H2SW 2001091900088 20010919 00088 SW 2001 9 19 AC2A075825 1 20010811 G 5320 206033107051 CLIP BELL 206 206L3 1182108 SW FUSELAGE CRACKED H AC2A K NONE O OTHER IN INSP/MAINT 1 FS 01 7159H 9831 51397 CLIP IS CRACKED. REPLACED WITH NEW PART. 1 G 7 1 3U H2SW 2001091900089 20010919 00089 SW 2001 9 19 AC2A075826 1 20010811 G 5311 206033107121 FRAME BELL 206 206L3 1182108 SW FUSELAGE CRACKED H AC2A K NONE O OTHER IN INSP/MAINT 1 FS 01 7159J 10161 51408 FRAME IS CRACKED. REPLACED WITH NEW PART 1 G 7 1 3U H2SW 2001091900090 20010919 00090 SW 2001 9 19 AC2A075827 1 20010811 G 5320 206033107051 CLIP BELL 206 206L3 1182108 SW FUSELAGE CRACKED H AC2A K NONE O OTHER IN INSP/MAINT 1 FS 01 7159J 10161 51408 CLIP IS CRACKED. REPLACED WITH NEW PART. 1 G 7 1 3U H2SW 2001091900091 20010919 00091 SW 2001 9 19 AC2A075828 1 20010811 G 5320 206033107055 STIFFENER BELL 206 206L3 1182108 SW FUSELAGE CRACKED H AC2A K NONE O OTHER IN INSP/MAINT 1 FS 01 7159J 10161 51408 STIFFENER IS CRACKED. REPLACED WITH NEW PART. 1 G 7 1 3U H2SW 2001091900092 20010919 00092 SW 2001 9 19 AC2A075829 1 20010811 G 5320 206033107055 STIFFENER BELL 206 206L3 1182108 SW FUSELAGE CRACKED H AC2A K NONE O OTHER IN INSP/MAINT 1 FS 01 31079 8884 51526 PART IS CRACKED. REPLACED WITH NEW PART. 1 G 7 1 3U H2SW 2001091900093 20010919 00093 SW 2001 9 19 AC2A075830 1 20010811 G 5320 206033107053 STIFFENER BELL 206 206L3 1182108 SW FUSELAGE CRACKED H AC2A K NONE O OTHER IN INSP/MAINT 1 FS 01 31079 8884 51526 STIFFENER IS CRACKED. REPLACED WITH NEW PART. 1 G 7 1 3U H2SW 2001091900094 20010919 00094 SW 2001 9 19 AC2A075831 1 20010811 G 5320 206033107056 STIFFENER BELL 206 206L3 1182108 SW FUSELAGE CRACKED H AC2A K NONE O OTHER IN INSP/MAINT 1 FS 01 31079 8884 51526 STIFFENER IS CRACKED. REPLACED WITH NEW PART. 1 G 7 1 3U H2SW 2001091900095 20010919 00095 SW 2001 9 19 AC2A075832 1 20010811 G 5320 206033107055 STIFFENER BELL 206 206L3 1182108 SW FUSELAGE CRACKED H AC2A K NONE O OTHER IN INSP/MAINT 1 FS 01 17237 8707 51478 STIFFENER IS CRACKED. REPLACED WITH NEW PART. 1 G 7 1 3U H2SW 2001091900096 20010919 00096 SW 2001 9 19 AC2A075833 1 20010811 G 5320 206033107056 STIFFENER BELL 206 206L3 1182108 SW FUSELAGE CRACKED H AC2A K NONE O OTHER IN INSP/MAINT 1 FS 01 17237 8707 51478 STIFFENER IS CRACKED. REPLACED WITH NEW PART. 1 G 7 1 3U H2SW 2001091900097 20010919 00097 SW 2001 9 19 AC2A075834 1 20010811 G 5320 206033107055 STIFFENER BELL 206 206L3 1182108 SW FUSELAGE CRACKED H AC2A K NONE O OTHER IN INSP/MAINT 1 FS 01 17592 8963 51535 STIFFENER IS CRACKED. REPAIRED WITH DER APPROVAL. 1 G 7 1 3U H2SW 2001091900098 20010919 00098 SW 2001 9 19 AC2A075835 1 20010811 G 5320 206033107056 STIFFENER BELL 206 206L3 1182108 SW FUSELAGE CRACKED H AC2A K NONE O OTHER IN INSP/MAINT 1 FS 01 17592 8964 51535 STIFFENER IS CRACKED. REPAIRED WITH DER APPROVAL. 1 G 7 1 3U H2SW 2001091900099 20010919 00099 SW 2001 9 19 AC2A075836 1 20010813 G 7931 222375077113 TRANSMITTER BELL 430 430 1182150 SW ALLSN 250C 250C* GL ENGINE OIL MALFUNCTIONED H AC2A K NONE O OTHER IN INSP/MAINT 1 FS 01 430CV 534 49072 INDICATOR READS 10 PSI STACTICLY. REPLACED WITH NEW PART. 1 G 7 2 3U 3 U RT H9SW E4CE 2001091900100 20010919 00100 SW 2001 9 19 AC2A075837 1 20010814 G 5320 206033107055 STIFFENER BELL 206 206L3 1182108 SW FUSELAGE CRACKED H AC2A K NONE O OTHER IN INSP/MAINT 1 FS 01 17238 8992 51492 STIFFENER IS CRACKED. REPLACED WITH NEW PART. 1 G 7 1 3U H2SW 2001091900101 20010919 00101 SW 2001 9 19 AC2A075838 1 20010814 G 5320 206033107056 STIFFENER BELL 206 206L3 1182108 SW FUSELAGE CRACKED H AC2A K NONE O OTHER IN INSP/MAINT 1 FS 01 17238 8992 51492 STIFFENER IS CRACKED. REPLACED WITH NEW PART. 1 G 7 1 3U H2SW 2001091900102 20010919 00102 SW 2001 9 19 AC2A075839 1 20010814 G 5320 206033107052 CLIP BELL 206 206L3 1182108 SW FUSELAGE CRACKED H AC2A K NONE O OTHER IN INSP/MAINT 1 FS 01 17238 8992 51492 CLIP IS CRACKED. REPLACED WITH NEW PART. 1 G 7 1 3U H2SW 2001091900103 20010919 00103 GL 2001 9 19 AC2A075840 2 20010821 G 7200 ENGINE BELL 430 430 1182150 SW ALLSN 250C 250C* GL NR 2 DAMAGED H AC2A K NONE O OTHER IN INSP/MAINT 1 FS 01 430CV 49072 DURING A DAILY SERVICEABILITY CHECK THE NR 2 ENGINE WAS FOUND TO BE DAMAGED. SUSPECT CAUSE OF DAMAGE WAS THE FAILURE OF CAMLOC BLADE ASSY P/N: 40G2-1. THE ENGINE WAS DISASSEMBLED . THE COMPRESSOR WAS REMOVED AND DISASSEMBLED, THE TURBI NE ASSY REMOVED. THE COMPRESSOR SCROLL WAS REMOVED AND SENT OUT FOR REPAIR. 1 G 7 2 3U 3 U RT H9SW E4CE 2001091900124 20010919 00124 SW 2001 9 19 AC2A075841 1 20010827 G 2150 2730502 VALVE BELL 430 430 1182150 SW A/C PACK FAILED H AC2A K NONE O OTHER IN INSP/MAINT 1 FS 01 430CV 573 49072 VALVE POPS CIRCUIT BREAKER. REPLACED WITH NEW PART. 1 G 7 2 3U RT H9SW 2001091900125 20010919 00125 SW 2001 9 19 AC2A075842 1 20010828 G 2150 5861653 TURBINE BELL 430 430 1182150 SW ALLSN 250C 250C* GL ENGINE FROZEN H K NONE O OTHER IN INSP/MAINT 1 FS 01 430CV 569 49072 COOLING TURBINE FROZEN. IT WOULD NOT TURN. REPLACED WITH NEW PART. 1 G 7 2 3U 3 U RT H9SW E4CE 2001091900126 20010919 00126 SW 2001 9 19 AC2A075845 1 20010904 G 6720 BEARING BELL 430 430 1182150 SW P/C LINK WORN H AC2A K NONE O OTHER IN INSP/MAINT 1 FS 01 430CV 600 49072 OUTBOARD BEARINGS WORN. REPLACED WITH NEW LINKS. 1 G 7 2 3U RT H9SW 2001091900127 20010919 00127 SW 2001 9 19 AC2A075846 1 20010904 G 2150 2730502 VALVE BELL 430 430 1182150 SW A/C PACK FAILED H AC2A K NONE O OTHER IN INSP/MAINT 1 FS 01 430CV 600 49072 ECU BREAKER POPPED. REPLACED WITH NEW VALVE. 1 G 7 2 3U RT H9SW 2001091900128 20010919 00128 SW 2001 9 19 AC2A075847 1 20010904 G 7170 6854255 DRAIN VALVE BELL 430 430 1182150 SW ENGINE LEAKING H AC2A K NONE O OTHER IN INSP/MAINT 1 FS 01 430CV 600 49072 VALVE IS EXCESSIVELY LEAKING. 1 G 7 2 3U RT H9SW 2001091900129 20010919 00129 SW 2001 9 19 AC2A075848 1 20010904 G 2913 222380009105 PUMP BELL 430 430 1182150 SW HYD SYSTEM LEAKING H AC2A K NONE O OTHER IN INSP/MAINT 1 FS 01 430CV 478 49072 LEAKING AT INPUT SEAL. REPLACED PUMP. 1 G 7 2 3U RT H9SW 2001091900132 20010919 00132 SW 2001 9 19 AC2A075849 1 20010905 G 6520 222012714001 BEARING BELL 430 430 1182150 SW TAIL ROTOR BRINELLED H AC2A K NONE O OTHER IN INSP/MAINT 1 FS 01 430CV 600 49072 INNER RACE WORN. IT WAS BRINNELING. REPLACED WITH NEW. 1 G 7 2 3U RT H9SW 2001091900136 20010919 00136 SW 2001 9 19 AC2A075852 1 20010905 G 6420 222312753103 BEARING 222012701125 BELL 430 430 1182150 SW T/R BLADE CRACKED H AC2A K NONE O OTHER IN INSP/MAINT 1 FS 01 430CV 600 A649 49072 CRACKED BEARINGS. REPLACED THE FOUR BEARINGS. 1 G 7 2 3U RT H9SW 2001091900139 20010919 00139 SW 2001 9 19 AC2A075853 1 20010905 G 6310 214040812001 SEAL 222044002101 BELL 430 430 1182150 SW DEFORMED H AC2A K NONE O OTHER IN INSP/MAINT 1 FS 01 430CV 600 A218 49072 DURING 600 HOUR INSPECTION, DISASSY. COUPLING FOUND SEAL DEFORMED. REPLACED SEAL. 1 G 7 2 3U RT H9SW 2001091900142 20010919 00142 GL 2001 9 19 AC2A075854 2 20010905 G 7320 23065147 FUEL CONTROL SKRSKY S76 S76A 8143006 NE ALLSN 250C 250C30S 03013 GL NR 1 ENGINE MALFUNCTIONED H AC2A O OTHER J WARNING INDICATION LD LANDING 1 FS 01 5402T 12214 760140 ENGINE WENT TO 40.6 PERCENT N1 UPON LANDING. REPLACED FUEL CONTROL. 1 G 7 2 3U 3 U H1NE E1GL 2001091900144 20010919 00144 SW 2001 9 19 AC2A075855 1 20010908 G 5320 206033107055 STIFFENER BELL 206 206L3 1182108 SW FUSELAGE CRACKED H AC2A K NONE O OTHER IN INSP/MAINT 1 FS 01 53702 12265 51249 STIFFENER IS CRACKED. REPLACED WITH NEW PART. 1 G 7 1 3U H2SW 2001091900146 20010919 00146 SW 2001 9 19 AC2A075856 1 20010908 G 5320 206033107056 STIFFENER BELL 206 206L3 1182108 SW FUSELAGE CRACKED H AC2A K NONE O OTHER IN INSP/MAINT 1 FS 01 53702 12265 51249 STIFFENER IS CRACKED. REPLACED WITH NEW PART. 1 G 7 1 3U H2SW 2001091900147 20010919 00147 SW 2001 9 19 AC2A075857 1 20010908 G 5320 206033107055 STIFFENER BELL 206 206L3 1182108 SW FUSELAGE CRACKED H AC2A K NONE O OTHER IN INSP/MAINT 1 FS 01 6533U 9821 51439 STIFFENER IS CRACKED. REPLACED WITH NEW PART. 1 G 7 1 3U H2SW 2001091900152 20010919 00152 SW 2001 9 19 AC2A075858 1 20010908 G 5320 206033107056 STIFFENER BELL 206 206L3 1182108 SW FUSELAGE CRACKED H AC2A K NONE O OTHER IN INSP/MAINT 1 FS 01 6533U 9821 51439 STIFFENER IS CRACKED. REPLACED WITH NEW PART. 1 G 7 1 3U H2SW 2001091900153 20010919 00153 SW 2001 9 19 AC2A075859 1 20010908 G 5312 206033107107B BULKHEAD BELL 206 206L3 1182108 SW FUSELAGE CORRODED H AC2A K NONE O OTHER IN INSP/MAINT 1 FS 01 6533U 9821 51439 BULKHEAD IS CORRODED. REPLACED WITH NEW PART. 1 G 7 1 3U H2SW 2001091900154 20010919 00154 SW 2001 9 19 AC2A075860 1 20010913 G 5311 206032308003 FRAME BELL 206 206L3 1182108 SW FUSELAGE CRACKED H AC2A K NONE O OTHER IN INSP/MAINT 1 FS 01 6533U 9821 51439 FRAME IS CRACKED. REPLACED WITH NEW PART. 1 G 7 1 3U H2SW 2001091900155 20010919 00155 SW 2001 9 19 AC2A075861 1 20010913 G 5340 206031329003 FITTING BELL 206 206L3 1182108 SW FUSELAGE CRACKED H AC2A K NONE O OTHER IN INSP/MAINT 1 FS 01 6533U 9821 51439 FITTING IS CRACKED. REPLACED WITH NEW PART. 1 G 7 1 3U H2SW 2001091900159 20010919 00159 SW 2001 9 19 AC2A075862 1 20010914 G 6220 430310101105 SHEAR RESTRAINT BELL 430 430 1182150 SW ROTOR SYSTEM DELAMINATED H AC2A K NONE O OTHER IN INSP/MAINT 1 FS 01 430CH 3732 49037 SHEAR RESTRAINT DELAMINATED FROM CENTER PIN AND CAUSED DAMAGE TO CLAMP PLATE P/N 430-010-105-105. 1 G 7 2 3U RT H9SW 2001091900161 20010919 00161 SW 2001 9 19 AC2A075863 1 20010918 G 2432 RG222 BATTERY BELL 206 206L3 1182108 SW MAIN BATTERY WILL NOT TEST H AC2A K NONE L NO TEST IN INSP/MAINT 1 FS 01 17237 153 51478 BATTERY FAILED TEST. REPLACED BATTERY. CHARGED BATTERY. PERFORMED CAPACITY CHECK. BATTERY FAILED CAPACITY 1 G 7 1 3U H2SW 2001101500096 20011015 00096 SW 2001 10 15 AC2A076110 1 20010917 G 6320 40621 CLIP 430061829101 BELL 430 430 1182150 SW XMSN COWL CRACKED H AC2A K NONE O OTHER IN INSP/MAINT 1 FS 01 430CV 600 49072 PART IS CRACKED. SOME REMOVED TO REDUCE RISK OF ENG. F.O.D. R & R CLIPS 1 G 7 2 3U RT H9SW 2001101500098 20011015 00098 SW 2001 10 15 AC2A076111 1 20010917 G 1400 214165 RECEPTACLE BELL 430 430 1182150 SW UPPER FAIRING WORN H AC2A K NONE O OTHER IN INSP/MAINT 1 FS 01 430CV 600 49072 PREMATURE WEAR R&R RECEPTICLE 1 G 7 2 3U RT H9SW 2001101500100 20011015 00100 SW 2001 10 15 AC2A076112 1 20010918 G 1400 430031517135 STRAP BELL 430 430 1182150 SW LT FUSELAGE CRACKED H AC2A K NONE O OTHER IN INSP/MAINT 1 FS 01 430CV 600 49072 CRACKED IN BENT RADIUS. REMOVED AND REPLACED 1 G 7 2 3U RT H9SW 2001101500102 20011015 00102 SW 2001 10 15 AC2A076113 1 20010918 G 5411 230069900150 FRAME BELL 430 430 1182150 SW FIREWALL CRACKED H AC2A K NONE O OTHER IN INSP/MAINT 1 FS 01 430CV 600 49072 CRACKS IN FRAME. REMOVED AND REPLACED FRAME ASSY. 1 G 7 2 3U RT H9SW 2001101500103 20011015 00103 SW 2001 10 15 AC2A076114 1 20010919 G 2510 222320823121 SEAT BELT BELL 430 430 1182150 SW COCKPIT DAMAGED H AC2A K NONE O OTHER IN INSP/MAINT 1 FS 01 430CV 600 49072 SEAT BELT WAS UNTHREADING. REPLACED WITH NEW SEAT BELT. 1 G 7 2 3U RT H9SW 2001101500105 20011015 00105 SW 2001 10 15 AC2A076115 1 20010919 G 6310 222060084101 PRESSURE SWITCH BELL 430 430 1182150 SW M/R GEARBOX INOPERATIVE H AC2A K NONE O OTHER IN INSP/MAINT 1 FS 01 430CV 600 49072 PRESSURE SWITCH IS INOPERABLE. REPLACED WITH NEW SWITCH. 1 G 7 2 3U RT H9SW 2001101500106 20011015 00106 SW 2001 10 15 AC2A076116 1 20010924 G 7810 206064300005 EXHAUST STACK BELL 206 206L3 1182108 SW ENGINE CRACKED H AC2A K NONE O OTHER IN INSP/MAINT 1 FS 01 715CC 306 51380 CRACKED. REPLACED WITH NEW EXHAUST STACK. 1 G 7 1 3U H2SW 2001101500107 20011015 00107 SW 2001 10 15 AC2A076117 1 20011001 G 2520 222020742133 CUSHION BELL 430 430 1182150 SW CABIN SEAT DAMAGED H AC2A K NONE O OTHER IN INSP/MAINT 1 FS 01 430CV 670 49072 FOAM WAS BUSTED AND SEPARATED FROM FRAME. REPLACED SEAT CUSHION. 1 G 7 2 3U RT H9SW 2002012300020 20020123 00020 SW 2002 1 23 AC2A077049 1 20011013 G 3213 206323017 CROSSTUBE BELL 206 206L3 1182108 SW MLG CORRODED H AC2A K NONE O OTHER IN INSP/MAINT 1 FS 01 7159H 10143 51397 THE MANUFACTURED DATE IS JAN. 2001 WITH 619 HOURS. TWO SPOTS OF CORROSION WERE FOUND UNDER THE SUPPORT CLAMPS. THE CROSS TUBE WAS REPLACED. 1 G 7 1 3U H2SW 2002012300021 20020123 00021 SW 2002 1 23 AC2A077050 1 20011015 G 2120 3136171 SOLENOID BELL 430 430 1182150 SW DIVERTER VALVE STUCK H AC2A K NONE O OTHER IN INSP/MAINT 1 FS 01 430CV 694 49072 DIVERTER VALVE NOT OPENING OR CLOSING. TOO MUCH COLD AIR COMING OUT OF LOWER VENTS. REPLACED WITH NEW SOLENOID. IT FIX ED PROBLEM. 1 G 7 2 3U RT H9SW 2002012300022 20020123 00022 SW 2002 1 23 AC2A077051 1 20011022 G 5320 206033107055 STIFFENER BELL 206 206L3 1182108 SW FUSELAGE CRACKED H AC2A K NONE O OTHER IN INSP/MAINT 1 FS 01 715CC 10225 51380 STIFFENER IS CRACKED. REPLACED WITH NEW PART. 1 G 7 1 3U H2SW 2002012300023 20020123 00023 SW 2002 1 23 AC2A077052 1 20011022 G 5320 206033107053 STIFFENER BELL 206 206L3 1182108 SW FUSELAGE CRACKED H AC2A K NONE O OTHER IN INSP/MAINT 1 FS 01 715CC 10225 51380 STIFFENER IS CRACKED. REPLACED WITH NEW PART. 1 G 7 1 3U H2SW 2002012300024 20020123 00024 SW 2002 1 23 AC2A077053 1 20011022 G 5320 206033107056 STIFFENER BELL 206 206L3 1182108 SW FUSELAGE CRACKED H AC2A K NONE O OTHER IN INSP/MAINT 1 FS 01 715CC 10225 51380 STIFFENER IS CRACKED. REPLACED WITH NEW PART. 1 G 7 1 3U H2SW 2002012300025 20020123 00025 SW 2002 1 23 AC2A077054 1 20011022 G 5320 206033107054 STIFFENER BELL 206 206L3 1182108 SW FUSELAGE CRACKED H AC2A K NONE O OTHER IN INSP/MAINT 1 FS 01 715CC 10225 51380 STIFFENER IS CRACKED. REPLACED WITH NEW PART. 1 G 7 1 3U H2SW 2002012300026 20020123 00026 SW 2002 1 23 AC2A077055 1 20011022 G 5320 206033107052 CLIP BELL 206 206L3 1182108 SW FUSELAGE CRACKED H AC2A K NONE O OTHER IN INSP/MAINT 1 FS 01 715CC 10225 51380 CLIP IS CRACKED. REPLACED WITH NEW PART. 1 G 7 1 3U H2SW 2002012300027 20020123 00027 SW 2002 1 23 AC2A077056 1 20011024 G 3212 206073926103 VALVE BELL 206 206L3 1182108 SW MLG FAILED H AC2A K NONE O OTHER IN INSP/MAINT 1 FS 01 17237 234 51478 VAVLE FAILING AFTER ONLY 234 HOURS. 1 G 7 1 3U H2SW 2002012300028 20020123 00028 SW 2002 1 23 AC2A077057 1 20011024 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 712 51408 EXHAUST STACK CRACKED. REPLACED WITH NEW . 1 G 7 1 3U H2SW 2002012300029 20020123 00029 SW 2002 1 23 AC2A077058 1 20011024 G 7810 206064300005 EXHAUST STACK BELL 206 206L3 1182108 SW ENGINE CRACKED H AC2A K NONE O OTHER IN INSP/MAINT 1 FS 01 53702 312 51249 EXHAUST STACK CRACKED. REPLACED WITH SERVICEABLE. 1 G 7 1 3U H2SW 2002012300035 20020123 00035 SW 2002 1 23 AC2A077536 1 20011205 G 7810 206064300005 EXHAUST STACK BELL 206 206L3 1182108 SW ENGINE CRACKED H AC2A K NONE O OTHER IN INSP/MAINT 1 FS 01 715CC 205 51380 EXHAUST STACK CRACKED. REPLACED WITH NEW. 1 G 7 1 3U H2SW 2002012300036 20020123 00036 SW 2002 1 23 AC2A077537 1 20011205 G 3040 222325001027 ARM BELL 430 430 1182150 SW WINDSHILD WIPER BROKEN H AC2A K NONE O OTHER IN INSP/MAINT 1 FS 01 430CV 804 49072 WINDSHIELD WIPER GUIDE ARM IS BROKEN. REPLACED WITH NEW PART. 1 G 7 2 3U RT H9SW 2002012300039 20020123 00039 SW 2002 1 23 AC2A077539 1 20011211 G 7500 23056648 TUBE BELL 430 430 1182150 SW BLEED AIR CHAFED H AC2A K NONE O OTHER IN INSP/MAINT 1 FS 01 430CV 205 49072 ENGINE COWL ASSY P/N: 430-061-804-101 FORWARD HINGE P/N: 230-061-808-101 IS RUBBING ON BLEED AIR TUBE P/N: 23056648 WHEN COWLING IS OPENED. REPLACED TUBE. PROBLEM WILL CONTINUE DUE TO DESIGN OF COWLING HINGE. 1 G 7 2 3U RT H9SW 2002012300040 20020123 00040 SW 2002 1 23 AC2A077540 1 20011211 G 6730 065001620200 SERVO BELL 430 430 1182150 SW MAIN ROTOR YAW MALFUNCTIONED H AC2A K NONE O OTHER IN INSP/MAINT 1 FS 01 430CV 943 49072 WHEN FD IS COUPLED IN HDG & ALT THE A/C GOES INTO A CLIMBING RIGHT TURN WITH FULL LEFT PEDAL APPLIED. REPLACED WITH NEW YAW SERVO. 1 G 7 2 3U RT H9SW 2002012300042 20020123 00042 SW 2002 1 23 AC2A077541 1 20011226 G 3040 222325001028 ARM BELL 430 430 1182150 SW WINDSHIED WIPER BROKEN H AC2A K NONE O OTHER IN INSP/MAINT 1 FS 01 430CV 953 49072 LOWER MOUNTING POINT BROKEN. THE MATERIAL THAT THIS PART IS MADE OF IS VERY SUSEPTIBLE TO CORROSION. CORROSION CAUSED T HIS PART TO FAIL. UPPER ROD END CORRODED VERY EASILY ALSO. REPLACED WITH NEW PART. 1 G 7 2 3U RT H9SW 2002012300043 20020123 00043 SW 2002 1 23 AC2A077542 1 20011226 G 6410 222312753103 BEARING 222016001131 BELL 430 430 1182150 SW T/R BLADE CRACKED H AC2A K NONE O OTHER IN INSP/MAINT 1 FS 01 430CV 281 A1901 49072 TAIL ROTOR BLADE BEARINGS WERE CRACKED. REPLACED TWO BEARINGS. 1 G 7 2 3U RT H9SW 2002012300044 20020123 00044 NE 2002 1 23 AC2A077543 1 20011226 G 7600 23065125 GOVERNOR SKRSKY S76 S76 8143010 NE ALLSN 250C 250C30 03013 GL ENGINE MALFUNCTIONED H AC2A K NONE O OTHER IN INSP/MAINT 1 FS 01 11057 890384 GOVERNOR VERY SENSITIVE, COULD NOT MATCH TORQUES & SHAFT IS RACHETY. REPLACED WITH SERVICEABLE PART. 1 G 7 2 3U 3 U H1NE E1GL 2002012300045 20020123 00045 NE 2002 1 23 AC2A077544 1 20011227 G 7921 28E252 THERMOSTAT SKRSKY S76 S76A 8143006 NE OIL COOLER INACCURATE H AC2A O OTHER N FALSE WARNING CR CRUISE 1 FS 01 5401G 760137 HIGH ENGINE OIL TEMPERATURE IN FLIGHT. REPLACED THERMOSTAT. CURED PROBLEM. 1 G 7 2 3U H1NE 2001082300084 20010823 00084 CE 2001 8 23 AMB20011 1 20010814 G 3244 22X80010 TIRE CESSNA 500 550 2076604 CE MLG FAILED B K NONE O OTHER IN INSP/MAINT 1 SW 17 753CC 5500109 DURING A DAILY INSPECTION THE SIDE WALL WAS FOUND TORN OUT WHERE THE SIDE WALL AND TIRE TRED ARE BONDED TOGOTHER. THERE IS ANOTHER AREA APROX. 6 INCHES AWAY FROM THIS TEAR, WHERE YOU CAN SEE THAT THE RUBBER IS ALSO STARTING TO SEPERATE. THE INNER AREA OF THE TEAR HAS SOFT RUBBBER COMMING OUT IT HAS THE CONTIENCY AND FEEL OF RUBBER THAT HAS NOT FULLY CURED. T HIS TIRE WAS PULLED FROM SERVICE AND A REPLACEMENT INSTALLED. WE ARE GOING TO SUBMIT THIS TO GOOD YEAR FOR THEM TO EVALU ATE. 1 L 7 2 4F A22CE 2001011105977 20010111 05977 NM 2001 1 11 ANCF200100004 1 20010107 G 2751 CONNECTOR BOEING 767 767259 1385136 NM PWA 4056 PW4056 NE TE FLAPS DIRTY W ANCF O OTHER O OTHER CL CLIMB 1 SW 99 986AN 24835 AFTER T/O BOTH FLAP POINTERS WERE ON 1° WITH THE FLAP LEVER IN UP POSITION, AIRCRAFT RETURNED TO MEX. CLEANED CONNECTORS AT FSEU PERFORMED BITE TEST AND OPERATIONAL TEST IAW AMM 27-58-05 TEST OK, COULD NOT DUPLICATED FAULT, FLAP/SLAT VISUAL CHECK OK. 2 L 7 2 4F 4 F RT A1NM E24NE 2001072600248 20010726 00248 NM 2001 7 26 ANCF200100010 1 20010609 G 2824 VALVE BOEING 767 767259 1385136 NM FUEL SYSTEM FAILED W ANCF A UNSCHED LANDING J WARNING INDICATION CR CRUISE 1 SO 23 986AN 24835 DURING CRUISE 1:30 HOURS AFTER T/O FUEL CROSSFEED VALVE LIGHT REMAINED ILLUMINATED WHEN VALVE SELECTED OPEN. EICAS MESS AGE FUEL CROSSFEED DISPLAYED. AIRCRAFT RETURNED TO MAD. PERFORMED PROCEDURE IAW FIM 28-22-00/101 FIG 108 BLOCKS 1, 2 A ND 14. REPLACED FUEL CROSSFEED VALVE, PERFORMED TEST WITH SATISFACTORY RESULTS. AIRCRAFT WAS RETURNED TO SERVICE. 2 L 7 2 4F RT A1NM 2001080200270 20010802 00270 NE 2001 8 2 AO1R200100001 2 20010717 G 7230 794909 COMPRESSOR WHEEL PWA JT9 JT9D* NE ENGINE FRETTED B K NONE W INADEQUATE Q C IN INSP/MAINT 1 SW 99 16393 695739 EXCESSIVE FRETTING DAMAGE ON BLADE SLOT PRESSURE FACES BEYOND LIMITS IN ACCORDANCE WITH JT9D OHM P/N 646028 SECTION 72-3 5-04 REV 109 FRETTING CHECKS 0.0024". REPAIR ORDER RECEIVED FROM P&W SMMO REQUESTED INSPECT TO THE LATEST REVISION OF E/ M 646028 DIMENSIONAL INSPECT PART AND REPORT FINDINGS TO JEFF FISCUS. PART WAS RECEIVED IN OVERHAUL CONDITION. 4 F E20EA 2001080200271 20010802 00271 NE 2001 8 2 AO1R200100002 2 20010717 G 7230 500110801 COMPRESSOR WHEEL PWA JT9 JT9D* NE ENGINE FRETTED B K NONE W INADEQUATE Q C IN INSP/MAINT 1 SW 99 31003 715441 EXCESSIVE FRETTING DAMAGE ON BLADE SLOT PRESSURE FACES BEYOND LIMITS IN ACCORDANCE WITH JT9D OHM P/N 646028 SECTION 72-3 5-04 REV 109 FRETTING CHECKS 0.0024". FRONT SNAP AND SHOULDER ARE OVERSIZE 0.002", REAR SNAP AND SHOULDER ARE OVERSIZE 0 .002" AND OUT OF ROUND 0.004". REPAIR ORDER RECEIVED FROM P&W SMMO REQUESTED INSPECT TO THE LATEST REVISION OF E/M 64602 8 DIMENSIONAL INSPECT PART AND REPORT FINDINGS TO JEFF FISCUS. PART WAS RECEIVED IN OVERHAUL CONDITION. 4 F E20EA 2001040200081 20010402 00081 NE 2001 4 2 AU010001 2 20010102 G 7310 226311001 PIPE BAC 146 146100A 1500260 EU LYC ALF502 ALF502R5 41580 NE ENGINE FUEL CHAFED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) ENGINE FUEL PIPE FROM FLOW DIVIDED TO FUEL MANIFOLD CHAFED ON COMBUSTOR HOUSING. 2 H 7 4 4F 4 F RT A49EU E6NE 2001040200082 20010402 00082 CE 2001 4 2 AU010002 1 20010103 G 3221 5842000211 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 PINS CRACKED. FOUND DURING INSPECTION IAW CESSNA SB MEB88-5R2. 1 L 7 2 3O 3 O A7CE E8CE 5 C P22EA 2001040200083 20010402 00083 CE 2001 4 2 AU010003 1 20010102 G 3231 08411066 ARM CESSNA 310 310R 2074245 CE CONT O520 IO520M 17032 SO MCAULY 3AF32C 3AF32C87 GL MLG DOOR CRACKED W O OTHER J WARNING INDICATION LD LANDING 1 AU S (AUS) RT MAIN LANDING GEAR INNER DOOR BELLCRANK IDLER ARM CRACKED. 1 L 7 2 3O 3 O 3A10 E5CE 5 C P22EA 2001040200084 20010402 00084 2001 4 2 AU010004 4 20010104 G 2211 065006401 COMPUTER REIMS 406 F406 EU PWA PT6 PT6A112 52043 NE MCAULY 3G34C7 3GFR34C701 GL AUTOPILOT FAULTY W O OTHER B J SMOKE/FUMES/ODORS/SPARKS WARNING INDICATION NR NOT REPORTED 1 AU S 3823 (AUS) AUTOPILOT COMPUTER SUSPECT FAULTY. 1 L 7 2 3T 3 T RT A54EU E4EA 5 C P60GL 2001040200269 20010402 00269 EA 2001 4 2 AU010005 1 20010107 G 5230 HANDLE CNDAIR CL600 CL6002B19 EA GE CF34 CF343B1 NE CARGO DOOR MALFUNCTIONED W A UNSCHED LANDING N FALSE WARNING CL CLIMB 1 AU S (AUS) CARGO DOOR MASTER CAUTION LIGHT ILLUMINATED. INVESTIGATION FOUNDTHE CARGO DOOR HANDLE PARTIALLY RELEASED. A FUNCTI ONAL CHECK OF THE DOOR LATCHING SYSTEM COULD FIND NO FAULT. SUSPECT THAT THEHANDLE WAS INCORRECTLY STOWED. 2 L 7 2 4F 4 F RT A21EA E15NE 2001040200085 20010402 00085 CE 2001 4 2 AU010006 1 20010103 G 5540 10164001419 FITTING BEECH 200 200BEECH 1152920 CE PWA PT6 PT6A42 52043 NE HARTZL HCD4N3 HCD4N3A GL RUDDER CORRODED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) RUDDER CENTER HINGE ASSEMBLY ATTACHMENT FITTING CORRODED. 1 L 7 2 4T 4 T A24CE E4EA 5 C STC 2001040200086 20010402 00086 SO 2001 4 2 AU010007 1 20010106 G 3230 DOWNLOCK PIPER PA34 PA34200 7103405 SO LYC O360 IO360C1E6 41514 EA HARTZL HCC2Y HCC2YK2 GL MLG CONTAMINATED W O OTHER J WARNING INDICATION LD LANDING 1 AU S (AUS) LT MAIN LANDING GEAR DOWNLOCK ARM JAMMED BY A STONE PREVENTING LANDING GEAR FROM CORRECTLY LOCKING IN THE DOWN POS ITION. 1 L 7 2 3O 3 O A7SO 1E10 5 C P920 2001040200087 20010402 00087 SO 2001 4 2 AU010008 2 20010103 G 8530 631996 RETAINER CESSNA 172 R172K 2072431 CE CONT O360 IO360HB 17025 SO MCAULY 2A34C 2A34C203 GL ENGINE CYLINDER CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) NR 3 CYLINDER ROCKER HAT REMOVED TO REPAIR OIL LEAK. THE ROCKER PIN RETAINER WAS FOUND TO CRACKED. ON FURTHER INSP ECTION OTHER ROCKER PIN RETAINERS SHOWED SIGNS OF INCIPIENT FAILURE. 1 H 7 1 3O 3 O 3A17 E1CE 5 C P3EA 2001040200088 20010402 00088 EU 2001 4 2 AU010009 2 20010104 G 7321 0164168190 FUEL CONTROL SNIAS AS332 AS332L 8680809 EU TMECA MAKILA MAKILA1A 60040 EU NR 1 ENGINE MALFUNCTIONED W A UNSCHED LANDING J WARNING INDICATION CL CLIMB 1 AU S (AUS) NR 1 ENGINE FUEL CONTROL UNIT FAULTY. INVESTIGATION FOUND THE PPNG OF THE FCU INTERNAL CIRCUIT TO BE OPEN CIRCUIT ED. 2 G 7 2 4U 4 U H4EU E12NE 2001040200089 20010402 00089 WP 2001 4 2 AU010010 2 20010110 G 7261 31080801 PIPE SWRNGN SA227 SA227AC 8780603 SW GARRTT TPE331 TPE33111U 01514 WP ROTOL R321 R321482F8 GL RT ENGINE OIL CHAFED W K NONE K FLUID LOSS IN INSP/MAINT 1 AU S (AUS) RT ENGINE OIL PIPE LEAKING DUE TO CONTINUED CHAFING WITH ANOTHERPIPE. 2 L 7 2 4T 4 T RT A8SW E4WE 6 C P61GL 2001040200270 20010402 00270 CE 2001 4 2 AU010011 1 20010110 G 2897 4410174 WIRE CESSNA C441 CESSNA 441 441 2076020 CE GARRTT TPE331 TPE331* 01514 WP HARTZL HCB3T HCB3TN5 GL BOOST PUMP CHAFED W K NONE O OTHER IN INSP/MAINT 1 AU S 4410174 (AUS) LT FUEL TANK BOOST PUMP WIRING CHAFED THROUGH TO BARE WIRE. 1 L 7 2 3T 3 T RT A28CE E2WE 6 C P15EA 2001040200090 20010402 00090 2001 4 2 AU010012 4 20010103 G 2565 7A146723 SLIDE BOEING 747 747438 NM RROYCE RB211 RB211524G19 NE PAX DOOR DAMAGED W K NONE O OTHER IN INSP/MAINT 1 AU S 12456 (AUS) NR 4 LT MAIN DOOR ESCAPE SLIDE TORN. 2 L 7 4 4F 4 F RT A20WE E30NE 2001040200091 20010402 00091 NM 2001 4 2 AU010013 1 20010109 G 2510 SEAT BACK BOEING 737 737476 NM CFMINT CFM56 CFM563C 13802 EU COCKPIT BROKEN W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) OBSERVERS SEAT BACK REST SEPARATED FROM SEAT BASE DUE TO A BROKEN BRACKET. 2 L 7 2 4F 4 F RT A16WE E21EU 2001040200092 20010402 00092 NM 2001 4 2 AU010014 1 20010109 G 7830 1275084 ARM RROYCE RB211524G BOEING 747 747438 NM RROYCE RB211 RB211524G19 NE THRUST REVERSER DAMAGED W K NONE J WARNING INDICATION IN INSP/MAINT 1 AU S 31016 (AUS) NR 2 ENGINE THRUST REVERSER COWL POSITION (TRCP) RESOLVER ARM DISCONNECTED AT ADJUSTMENT TURNBUCKLE AND ATTACHED B Y ONLY ONE THREAD AT THE RESOLVER. SAFETY WASHER LOCKTABS PARTIALLY BENT AND RESOLVER APPEARS TO HAVE SUFFERED CONTACT D AMAGE. 2 L 7 4 4F 4 F RT A20WE E30NE 2001040200093 20010402 00093 NM 2001 4 2 AU010015 1 20010109 G 2823 737M28500011 VALVE BOEING 737 737476 NM CFMINT CFM56 CFM563C 13802 EU FUEL SELECTOR FAILED W O OTHER O OTHER NR NOT REPORTED 1 AU S 3161 (AUS) NR 1 ENGINE FUEL SHUTOFF VALVE FAILED IN THE CLOSED POSITION. 2 L 7 2 4F 4 F RT A16WE E21EU 2001040200094 20010402 00094 NM 2001 4 2 AU010016 1 20010110 G 3260 841005 PSEU DHAV DHC8 DHC8102 2809003 NM PWA 120 PW120A NE HAMSTD 14SF 14SF7 NE MLG FAULTY W A UNSCHED LANDING N FALSE WARNING CL CLIMB 1 AU S (AUS) PROXIMITY SENSE ELECTRICAL UNIT (PSEU) FAULTY. 2 H 7 2 4T 4 T RT A13NM E20NE 6 C P7NE 2001040200095 20010402 00095 SO 2001 4 2 AU010017 1 20010109 G 7920 2W127984S190 HOSE PIPER PA31 PA31350 7103110 SO LYC O540 TIO540J2BD 41532 EA HARTZL HCE3Y HCE3YR2 GL ENGINE OIL DETERIORATED W O OTHER K B J FLUID LOSS SMOKE/FUMES/ODORS/SPARKS WARNING INDICATION LD LANDING 1 AU S (AUS) RT ENGINE TURBOCHARGER OIL RETURN HOSE DETERIORATED AND LEAKING.HOSE FAILED PRESSURE TESTING. THE HOSE HAD BEEN AF FECTED BY THE HEAT FROM THE TURBOCHARGER. 1 L 7 2 3O 3 O A20SO E14EA 5 C P33EA 2001040200097 20010402 00097 EU 2001 4 2 AU010018 1 20010111 G 2760 BUSHING FOKKER F28 F28MK4000 4990810 EU RROYCE SPEY SPEY55515 54521 EU DRAG CONTROL CORRODED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) SPEED BRAKE CABLE INPUT QUADRANT CORRODED. THE FOLLOWING ITEMSWERE FOUND DETERIORATED: GROOVE OF PULLEY ASSEMBLY. WEB ADJACENT TO STOP PIN HOLE OF BRACKET. INTERNAL SPLINE OF LEVER. EXTERNAL SPLINE ON SHAFT AND BUSHING. BEARING AND F OUND CORRODED AND ROUGH TO ROTATE 2 L 7 2 4F 4 F RT A20EU E2EU 2001040200098 20010402 00098 CE 2001 4 2 AU010019 1 20010104 G 3230 51420025 DRAG BRACE CESSNA 402 402C 207590R CE CONT O520 TSIO520VB 17040 SO MCAULY 3AF32C 3AF32C87 GL MLG CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) NOSE LANDING GEAR DRAG BRACE CRACKED IN AREA ADJACENT TO THE ACTUATOR ATTACHMENT LUG. 1 L 7 2 3O 3 O A7CE E8CE 5 C P22EA 2001040200099 20010402 00099 CE 2001 4 2 AU010020 1 20010112 G 3221 5842000211 PIN CESSNA 441 441 2076020 CE GARRTT TPE331 TPE3318 01514 WP HARTZL HCB3T HCB3TN5 GL NLG TRUNNION CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) NOSE LANDING GEAR TRUNNION PIN CRACKED. FOUND DURING INSPECTION IAW CESSNA SB CQB00-3. 1 L 7 2 3T 4 T RT A28CE E4WE 6 C P15EA 2001040200100 20010402 00100 CE 2001 4 2 AU010021 1 20010103 G 5210 1313232C12 PIN BEECH 200 200BEECH 1152920 CE PWA PT6 PT6A42 52043 NE HARTZL HCB3T HCB3TN3 GL PAX DOOR SHEARED W O OTHER O OTHER CR CRUISE 1 AU S (AUS) DOOR HOOK CLEVIS PIN SHEARED. DOOR DIFFICULT TO OPEN. 1 L 7 2 4T 4 T A24CE E4EA 6 C P15EA 2001040200101 20010402 00101 EU 2001 4 2 AU010022 1 20010112 G 2910 24Q2395 HOSE BRAERO 748 HS7482B 1500248 EU RROYCE DART DART5322L 54509 EU HYDRAULIC SYS CRACKED W O OTHER K J FLUID LOSS WARNING INDICATION CR CRUISE 1 AU S (AUS) RT GEARBOX MOUNTED HYDRAULIC PUMP OUTLET HOSE END FITTING CRACKED ON FLARED OLIVE. 2 L 7 2 3T 4 T A24EU E297 2001040200102 20010402 00102 SO 2001 4 2 AU010023 1 20010115 G 3230 40336000 DRAG BRACE PIPER PA31 PA31350 7103110 SO LYC O540 TIO540J2BD 41532 EA HARTZL HCE3Y HCE3YR2 GL NLG CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) NOSE LANDING GEAR DRAG BRACE ACTUATOR ATTACHMENT LUGS CRACKED. FOUND USING VISUAL AND CONFIRMED USING NDI. 1 L 7 2 3O 3 O A20SO E14EA 5 C P33EA 2001040200103 20010402 00103 EU 2001 4 2 AU010024 1 20010116 G 3213 200877682 PIN BAC 146 146100A 1500260 EU LYC ALF502 ALF502R5 41580 NE RT MLG FRACTURED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) RT MAIN LANDING GEAR WHEEL LEVER TO OLEO ATTACHMENT PIN FRACTURED AND MIGRATED. 2 H 7 4 4F 4 F RT A49EU E6NE 2001040200104 20010402 00104 GL 2001 4 2 AU010025 2 20010112 G 7230 9380M28P05 TURBINE WHEEL GE GE CF6 CF680C2* GL ENGINE OUT OF TOLERANCE W K NONE O OTHER IN INSP/MAINT 1 AU S 6513 (AUS) HIGH PRESSURE COMPRESSOR ROTOR SPOOL NR 3 STAGE TO NR 9 STAGE OUTSIDE OF LIMITS AS PER AD/CF6/41, AD/CF6-43, FAA A D FAD 99-24-15 AND FAA AD FAD 2000-16-12. 4 F E23EA 2001040200105 20010402 00105 NM 2001 4 2 AU010026 1 20010112 G 8011 9702038 CLAMP GE CF680C2 BOEING 767 767338 1385151 NM GE CF6 CF680C2* GL STARTER FAILED W O OTHER J WARNING INDICATION CL CLIMB 1 AU S 4159 9702038 (AUS) RT ENGINE STARTER CLAMP BROKEN AND STARTER LOOSE. SEAL CUT. 2 L 7 2 4F 4 F RT A1NM E23EA 2001040200106 20010402 00106 NM 2001 4 2 AU010027 1 20010111 G 2910 AV13J5147 VALVE BOEING 737 737376 NM CFMINT CFM56 CFM563C 13802 EU HYDRAULIC SYS SEIZED W K NONE O OTHER IN INSP/MAINT 1 AU S 25973 (AUS) HYDRAULIC STANDBY MODULE SHUTOFF VALVE SEIZED. 2 L 7 2 4F 4 F RT A16WE E21EU 2001040200107 20010402 00107 NE 2001 4 2 AU010028 2 20010103 G 8500 ENGINE DHAV DHC2 DHC2MK1 2800102 EA PWA R985 R985AN14B 52008 NE NACELLE SEIZED W A UNSCHED LANDING E Y VIBRATION/BUFFET ENGINE STOPPAGE CL CLIMB 1 AU S (AUS) ENGINE RAN ROUGH AND THEN SEIZED. LIMITED INFORMATION PROVIDED. 1 H 7 1 3R 3 R A806 5E1 2001040200108 20010402 00108 EA 2001 4 2 AU010029 2 20010116 G 7310 25765311 FLOW DIVIDER CESSNA 182 182S 2072701 CE LYC O540 IO540AB1A5 EA MCAULY 3D36C B3D36C431 GL FUEL DIST CORRODED W A UNSCHED LANDING J WARNING INDICATION CL CLIMB 1 AU S 92 (AUS) ENGINE FUEL FLOW DIVIDED CORRODED. PARTICLES OF CORROSION BLOCKING FUEL INJECTORS. AIRCRAFT HAD BEEN CONTAMINATED WITH EDAAND DECONTAMINATED IAW AD/GEN/80 AND MANUFACTURERS INSTRUCTIONS. 1 H 7 1 3O 3 O NT 3A13 1E4 5 C 2001040200109 20010402 00109 SO 2001 4 2 AU010030 1 20010113 G 2150 MS21346221 SWITCH EMB 120 EMB120 3260201 SO PWA 118 PW118A NE HAMSTD 14SF 14SF9 NE AIR CONDITIONING FAULTY W O OTHER J WARNING INDICATION CR CRUISE 1 AU S (AUS) AIR CONDITIONING SYSTEM CROSS BLEED VALVE SWITCH FAULTY. 2 L 7 2 4T 4 T RT A31SO E20NE 6 N P11NE 2001040200110 20010402 00110 NM 2001 4 2 AU010031 1 20010104 G 2530 CA16371 CONNECTOR DHAV DHC8 DHC8102 2809003 NM PWA 120 PW120A NE HAMSTD 14SF 14SF7 NE GALLEY DAMAGED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) LIQUID HEATER CONNECTORS DAMAGED DUE TO OVERHEATING. 2 H 7 2 4T 4 T RT A13NM E20NE 6 C P7NE 2001040200111 20010402 00111 NM 2001 4 2 AU010032 1 20010104 G 2530 CA16731 CONNECTOR DHAV DHC8 DHC8102 2809003 NM PWA 120 PW120A NE HAMSTD 14SF 14SF7 NE GALLEY DAMAGED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) LIQUID HEATER CONNECTORS DAMAGED DUE TO OVERHEATING. 2 H 7 2 4T 4 T RT A13NM E20NE 6 C P7NE 2001040200112 20010402 00112 NM 2001 4 2 AU010033 1 20010114 G 7830 DOOR RROYCE RB211524D4 BOEING 747 747338 NM RROYCE RB211 RB211524D419 54555 NE THRUST REVERSER DAMAGED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) NR 1 ENGINE BLOCKER PARTIALLY MISSING. DAMAGE TO CORONA AND COLD STREAM DUCT AT 10 OCLOCK POSITION. 2 L 7 2 4F 4 F RT A20WE E12EU 2001040200113 20010402 00113 2001 4 2 AU010034 4 20010115 G 2330 311038 CONTROL BOX BOEING 767 767338 1385151 NM GE CF6 CF680C2* GL ENTERTAIN SYS FAILED W K NONE O OTHER IN INSP/MAINT 1 AU S 311038 (AUS) SEAT 5A HARNESS PLUG TO SEAT ELECTRONICS BOX ARCING. ARCING CONTINUED WITH PLUG DISCONNECTED. NO CIRCUIT BREAKERS POPPED. 2 L 7 2 4F 4 F RT A1NM E23EA 2001040200114 20010402 00114 NM 2001 4 2 AU010035 1 20010116 G 7830 DOOR RROYCE RB211524G BOEING 747 747438 NM RROYCE RB211 RB211524G19 NE THRUST REVERSER DAMAGED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) NR 1 ENGINE THRUST REVERSER NR 9 BLOCKER DOOR PARTLY MISSING. DAMAGE TO CORONA WITH A 76.2MM BY 25.4MM (3IN BY 1IN ) HOLE ADJACENT TO BLOCKER DOOR POSITION. DAMAGE ALSO TO LT COMBUSTION FAIRING AND INTEGRATED NOZZLE ASSEMBLY. 2 L 7 4 4F 4 F RT A20WE E30NE 2001040200141 20010402 00141 SO 2001 4 2 AU010036 1 20010116 G 2752 1202001 ACTUATOR PIPER PA31 PA31350 7103110 SO LYC O540 TIO540J2BD 41532 EA HARTZL HCE3Y HCE3YR2 GL TE FLAP WORN W O OTHER J WARNING INDICATION LD LANDING 1 AU S (AUS) FLAP MOTOR BRUSHES AND COMMUTATOR WORN. MOTOR INOPERATIVE. 1 L 7 2 3O 3 O A20SO E14EA 5 C P33EA 2001040400001 20010404 00001 NE 2001 4 4 AU010038 3 20010111 G 6111 7922141 TAPE HAMSTD SFA13MIOA DHAV DHC8 DHC8102 2809003 NM PWA 120 PW120A NE HAMSTD 14SF 14SF7 NE PROPELLER BLADE LOOSE W O OTHER O OTHER CL CLIMB 1 AU S (AUS) LT PROPELLER BLADE LEADING EDGE TAPE LOOSE ON ONE BLADE. 2 H 7 2 4T 4 T RT A13NM E20NE 6 C P7NE 2001040200121 20010402 00121 EU 2001 4 2 AU010039 1 20010116 G 2770 A78300401 LOCK FOKKER F28 F28MK4000 4990810 EU RROYCE SPEY SPEY55515 54521 EU ELEVATOR CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) ELEVATOR GUSTLOCK HOUSING MOUNTING LUGS CRACKED. FOUND DURING INSPECTION IAW AD/F28/72 AMDT1. SUSPECT CAUSED BY LO OSE MOUNT.BOLTS. 2 L 7 2 4F 4 F RT A20EU E2EU 2001040200122 20010402 00122 CE 2001 4 2 AU010040 1 20010116 G 3221 5842000211 PIN CESSNA 441 441 2076020 CE GARRTT TPE331 TPE3318 01514 WP HARTZL HCB3T HCB3TN5 GL NLG TRUNNION CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) NOSE LANDING GEAR TRUNNION PIN CRACKED. 1 L 7 2 3T 4 T RT A28CE E4WE 6 C P15EA 2001040200123 20010402 00123 NE 2001 4 2 AU010041 2 20010107 G 7310 21631001 PIPE BAG BAE146 BAE146200A 1500266 EU LYC ALF502 ALF502R5 41580 NE FUEL DIST WORN W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) NR 3 ENGINE LT PRIMARY FUEL PIPE CHAFING ON COMBUSTOR CASE IN AREA OF THE FORWARD FLANGE OF THE CUSTOMER BLEED FLA NGE. 2 H 7 4 4F 4 F RT A49EU E6NE 2001040200124 20010402 00124 EU 2001 4 2 AU010042 1 20010104 G 7603 CABLE LYC IO540K1B5 BNORM BN2 BN2A26 1520226 EU LYC O540 IO540K1B5 41532 EA HARTZL HCC2Y HCC2YK2 GL POWER LEVER LOOSE W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) ENGINE THROTTLE CABLE OUTER CONDUIT DISCONNECTED AT FIREWALL. THE NUT SECURING THE CONDUIT HAD NO LOCKWIRE. 1 H 7 2 3O 3 O A17EU 1E4 5 C P920 2001040200125 20010402 00125 EU 2001 4 2 AU010043 1 20010105 G 7602 CABLE LYC IO540K1B5 BNORM BN2 BN2A26 1520226 EU LYC O540 IO540K1B5 41532 EA HARTZL HCC2Y HCC2YK2 GL MIXTURE CONTROL MISINSTALLED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) ENGINE MIXTURE CONTROL INNER CABLE ONLY ENGAGED IN THE ENGINE CONTROL END BY APPROXIMATELY 1.5 TURNS. 1 H 7 2 3O 3 O A17EU 1E4 5 C P920 2001040200126 20010402 00126 EU 2001 4 2 AU010044 1 20010110 G 6120 CONTROL CABLE HARTZL HCC2YK2 BNORM BN2 BN2A26 1520226 EU LYC O540 IO540K1B5 41532 EA HARTZL HCC2Y HCC2YK2 GL PROP CONTROL SEIZED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) RT PROPELLER CSU CONTROL CABLE OUTER CONDUIT WORN THROUGH WITHTHE INNER CABLE CATCHING ON THE WORN AREA. CONTROL S EIZED. 1 H 7 2 3O 3 O A17EU 1E4 5 C P920 2001040200127 20010402 00127 NE 2001 4 2 AU010045 2 20010117 G 7260 3022375 SEAL PILATS PC12 PC12 7090550 EU PWA PT6 PT6A67B 52043 NE HARTZL HCE4A HCE4A3D GL ENGINE FAILED W K NONE K FLUID LOSS IN INSP/MAINT 1 AU S (AUS) NR 4 ACCESSORY DRIVE SEAL MIGRATED OUT OF SEAL CARRIER PNO 3007737 ALLOWING APPROXIMATELY 3.5 LITRES OF OIL TO LEA K FROM THE ENGINE DRIVEN LOW PRESSURE FUEL PUMP DRIVE SPLINE DRAIN. 1 L 7 1 3T 4 T RT A78EU E26NE 5 C P210NE 2001040200128 20010402 00128 SW 2001 4 2 AU010046 1 20010122 G 3233 MS28775116 SEAL EA1568 GULSTM 500 500S 0141107 SW LYC O540 IO540E1B5 41532 EA HARTZL HCA3V HCA3VK2 GL MLG ACTUATOR WORN W O OTHER K FLUID LOSS DE DESCENT 1 AU S 2020 (AUS) MAIN LANDING GEAR RETRACTION ACTUATOR SEAL WORN. 1 H 7 2 3O 3 O 6A1 1E4 5 C P6EA 2001040200129 20010402 00129 SO 2001 4 2 AU010047 2 20010111 G 7314 SEAL CESSNA 402 402C 207590R CE CONT O520 TSIO520VB 17040 SO FUEL PUMP FAILED W C ABORTED TAKEOFF K J FLUID LOSS WARNING INDICATION TO TAKEOFF 1 AU S (AUS) LT ENGINE DRIVEN FUEL PUMP SEAL FAILED. FUEL LEAKING FROM VENT. 1 L 7 2 3O 3 O A7CE E8CE 2001040200130 20010402 00130 EU 2001 4 2 AU010048 1 20010108 G 5711 SPAR BAC 146 146300A 1500267 EU LYC ALF502 ALF502R5 41580 NE LT & 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 CORROSIONIN AREAS OUTBOARD OF RIB NR 13. HEAVY STAINING FOU ND IN WING TANKS SUSPECTED FROM CLADOSPORIUM RESINAE. 2 H 7 4 4F 4 F RT A49EU E6NE 2001040200131 20010402 00131 NM 2001 4 2 AU010049 1 20010122 G 3242 26056623 BRAKE BOEING 747 747338 NM RROYCE RB211 RB211524D419 54555 NE LT WING MLG FAILED W K NONE O OTHER IN INSP/MAINT 1 AU S 7020 (AUS) LT FORWARD WING LANDING GEAR NR 2 POSITION BRAKE FAILED. 2 L 7 2 4F 4 F RT A20WE E12EU 2001040200132 20010402 00132 NM 2001 4 2 AU010050 1 20010119 G 2432 401767 BATTERY BOEING 737 737376 NM CFMINT CFM56 CFM563C 13802 EU BATTERY BAY DISCHARGED W O OTHER H J ELECT. POWER LOSS-50 PC WARNING INDICATION NR NOT REPORTED 1 AU S 4 (AUS) MAIN AIRCRAFT BATTERY DISCHARGED. 2 L 7 2 4F 4 F RT A16WE E21EU 2001040200133 20010402 00133 EU 2001 4 2 AU010051 1 20010118 G 7722 897476 COMPENSATOR BAG JETSTM JETSTM3201 1500217 EU GARRTT TPE331 TPE33112UHR WP ROTOL R333 R333482F12 GL EGT/TIT INDICATO OUT OF TOLERANCE W C ABORTED TAKEOFF N FALSE WARNING TO TAKEOFF 1 AU S (AUS) LT ENGINE EGT COMPENSATOR OUT OF TOLERANCE. 2 L 7 2 4T 4 T RT A56EU E4WE 6 C P61GL 2001040200134 20010402 00134 NM 2001 4 2 AU010052 1 20010123 G 2400 S010488308 RELAY DHAV DHC8 DHC8102 2809003 NM PWA 120 PW120A NE HAMSTD 14SF 14SF7 NE ELECTRICAL SEPARATED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) RELAY BASE SEPARATED AT PRODUCTION BREAK ALLOWING THE RELAY CONTACTS TO COME AWAY FROM THE RELAY. BASE MANUFACTURE R CLOVER. THE RELAYS ARE USED IN NUMEROUS AREAS. 2 H 7 2 4T 4 T RT A13NM E20NE 6 C P7NE 2001040200135 20010402 00135 NE 2001 4 2 AU010053 2 20010118 G 7321 8063023 FUEL CONTROL STBROS SD3 SD360 8100606 EU PWA PT6 PT6A67R 52043 NE HARTZL HCA6A HCA6A3 NE RT ENGINE FAULTY W O OTHER J WARNING INDICATION LD LANDING 1 AU S (AUS) RT ENGINE FUEL CONTROL UNIT FAULTY. 2 H 7 2 4T 4 T A41EU E26NE 6 C P14NE 2001040200136 20010402 00136 WP 2001 4 2 AU010054 1 20010121 G 3234 630294W PISTON LKHEED 1049 C121C 5262118 WP WRIGHT R3350 R3350* 67040 EA HAMSTD 43E 43E60 NE MLG STRUT BROKEN W C ABORTED TAKEOFF J WARNING INDICATION TO TAKEOFF 1 AU S (AUS) LANDING GEAR SELECTOR VALVE PISTONS (2OFF4) BROKEN ACROSS SHANK IN AN O-RING SEAL GROOVE. BROKEN PISTON JAMMED IN PORT. 2 L 7 4 4R 4 R 6A5 E272 6 C P871 2001040200137 20010402 00137 SO 2001 4 2 AU010055 2 20010125 G 8520 632043 CONNECTING ROD CESSNA 404 404CESSNA 2075901 CE CONT O520 GTSIO520M 17032 SO MCAULY 3AF34C 3AF34C74 GL ENGINE FAILED W C ABORTED TAKEOFF K J FLUID LOSS WARNING INDICATION TO TAKEOFF 1 AU S 847 (AUS) LT ENGINE NR 5 CYLINDER CONNECTING ROD SEPARATED FROM CRANKSHAFT AND PENETRATED THE CRANKCASE. 1 L 7 2 3O 3 O A25CE E7CE 5 C P22EA 2001040200138 20010402 00138 EU 2001 4 2 AU010056 1 20010128 G 5753 7257830022 FITTING 7257800504 SAAB SF340 340B 7860101 EU GE CT7TP CT79B 30030 NE ROTOL R390 R3904123F27 NE TE FLAP CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S 1114 (AUS) RT FLAP ASSEMBLY OUTBOARD FITTING AFT ATTACHMENT LUG CRACKED. CRACK APPEARS TO HAVE EMANATED FROM THE BOLT/BUSHING HOLE AND PROGRESSED THROUGH ONE SIDE OF THE LUG. FOUND DURING VISUAL INSPECTION IAW SB-340-57-037. 2 L 7 2 4T 4 T RT A52EU E8NE 6 C P31NE 2001040200139 20010402 00139 EA 2001 4 2 AU010057 2 20010119 G 8530 17C21191 KEY ROBSIN R44 R44 7640120 WP LYC O540 O540F1B5 41532 EA ENGINE BROKEN W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) NR 5 CYLINDER EXHAUST VALVE KEY BROKEN WITH DAMAGE TO TAPPET AND SOCKET. SUSPECT TAPPET DAMAGED AT MANUFACTURE CAU SING INCORRECT VALVE CLEARANCE. 1 G 7 1 3O 3 O H11NM E295 2001040200140 20010402 00140 SW 2001 4 2 AU010058 1 20010127 G 2133 A6009 ADAPTER SWRNGN SA227 SA227* SW GARRTT TPE331 TPE33112UA 01514 WP MCAULY 4HFR34 4HFR34C652 NE PRESSURE REG FAILED W A UNSCHED LANDING J WARNING INDICATION CL CLIMB 1 AU S (AUS) CABIN PRESSURISATION SYSTEM OUTFLOW VALVE SUCTION FITTING FAILED. 2 L 7 2 4T 4 T RT A5SW E4WE 6 C 3PNE 2001040200271 20010402 00271 SW 2001 4 2 AU010059 1 20010123 G 6510 2006505008 BOLT BELL 412 412 1182202 SW PWA PT6T PT6T3B 52045 NE TAIL ROTOR DRIVE WORN W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) TAIL ROTOR DRIVESHAFT TO TAIL ROTOR GEARBOX INPUT COUPLING BOLT SEPARATED. MARKS ON BOLT INDICATE THAT IT HAD BEEN LOOSE FOR SOME TIME. 1 G 7 2 4U 4 U H4SW E22EA 2001040200272 20010402 00272 SW 2001 4 2 AU010060 1 20010113 G 7334 42D218 PRESSURE SWITCH BELL 412 412 1182202 SW PWA PT6T PT6T3B 52045 NE FUEL PRESSURE LEAKING W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) NR 2 ENGINE FUEL PRESSURE SWITCH LEAKING FUEL FROM SOLDERED JOINT AT BASE OF CONNECTOR PLUG CONNECTOR. 1 G 7 2 4U 4 U H4SW E22EA 2001040200273 20010402 00273 SW 2001 4 2 AU010061 1 20010113 G 7334 42D218 PRESSURE SWITCH BELL 412 412 1182202 SW PWA PT6T PT6T3B 52045 NE FUEL PRESSURE LEAKING W K NONE K FLUID LOSS IN INSP/MAINT 1 AU S (AUS) FUEL PRESSURE SWITCH LEAKING FROM SOLDERED JOINT AT BASE OF CONNECTOR PLUG FITTING. 1 G 7 2 4U 4 U H4SW E22EA 2001040200274 20010402 00274 2001 4 2 AU010063 4 20010101 G 2565 B732560135 CABLE BOEING 737 737377 NM GE CFM56 CFM563B1 13802 NE ESCAPE SLIDE FRAYED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) L2 DOOR SLIDE ATTACHMENT CABLE FRAYED IN LOOP AREA. 2 L 7 2 4F 4 F RT A16WE E2GL 2001040200275 20010402 00275 NM 2001 4 2 AU010064 1 20010109 G 2897 6130024 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 2001040200276 20010402 00276 EU 2001 4 2 AU010065 1 20010123 G 5343 FITTING AIRBUS 320 A320211 3930320 EU CFMINT CFM56 CFM565A1 NE MLG CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) RT MAIN LANDING GEAR DOOR ACTUATOR FITTING AND CONNECTING STRIP CRACKED IN TWO PLACES. CRACK LENGTHS 20MM (0.78IN) IN FORWARD FLANGE AND 28MM (1.102IN) IN AFT FLANGE. CONNECTION STRAP CRACKED FROM FASTENER HOLE. CRACK LENGTH 5MM (0.19 6IN). FOUND DURING NDI INSPECTION IAW SB A320-53A1135 AND AN ENGINEERING RELEASE A32-53-40-9B. 2 L 7 2 4F 4 F RT A28NM E29NE 2001040200277 20010402 00277 CE 2001 4 2 AU010066 1 20010120 G 5511 07326022 SPAR CESSNA 185 A185F 2072821 CE CONT O520 IO520D 17032 SO MCAULY D3A34 D3A34C401 GL HORIZONTAL STAB CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) HORIZONTAL STABILISER REAR SPAR CRACKED IN AREA BEHIND THERE INFORCED HINGE BRACKET CRACK LENGTH 50MM (1.96IN). CA USED BY SEVERE CORROSION ON THE DOUBLER BRACKET SECURING THE ATTACHMENT HINGE PNO 0732101-11. 1 H 7 1 3O 3 O 3A24 E5CE 5 C P47GL 2001040200278 20010402 00278 CE 2001 4 2 AU010067 1 20010131 G 3213 10581002375NLH FRAME BEECH 76 76 1153005 CE MLG CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) LT MAIN LANDING GEAR A FRAME CRACKED. 1 L 7 2 3O A29CE 2001040200279 20010402 00279 CE 2001 4 2 AU010068 1 20010131 G 3213 10581002376RH FRAME BEECH 76 76 1153005 CE MLG CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) RT MAIN LANDING GEAR A FRAME CRACKED. 1 L 7 2 3O A29CE 2001040200280 20010402 00280 SO 2001 4 2 AU010069 1 20010128 G 3250 PIN EMB 120 EMB120 3260201 SO PWA 118 PW118A NE HAMSTD 14SF 14SF9 NE NLG STEERING LOOSE W D RETURN TO BLOCK O OTHER TX TAXI/GRND HDL 1 AU S (AUS) NOSE WHEEL STEERING RELAY BOX CONNECTOR PIN LOOSE. 2 L 7 2 4T 4 T RT A31SO E20NE 6 N P11NE 2001040200281 20010402 00281 2001 4 2 AU010070 4 20010124 G 2565 7A126130 SLIDE BOEING 747 747SP38 NM PAX DOOR FAULTY W K NONE O OTHER IN INSP/MAINT 1 AU S 12818 (AUS) RT MAIN ENTRY DOOR SLIDE FAILED TO CORRECTLY DEPLOY DURING TEST. THE SLIDE CAUGHT ON THE DOOR STRUCTURE SUSTAINING A SMALL PUNCTURE AND DAMAGING THE LOWER BUSTLE. 2 L 7 4 4F RT A20WE 2001040200282 20010402 00282 EU 2001 4 2 AU010071 1 20010202 G 7931 PDCR3301028 TRANSMITTER BAG BAE146 BAE146200A 1500266 EU LYC ALF502 ALF502R5 41580 NE OIL PRESSURE FAULTY W O OTHER J WARNING INDICATION CR CRUISE 1 AU S 3153 (AUS) NR 3 ENGINE OIL PRESSURE TRANSMITTER FAULTY. 2 H 7 4 4F 4 F RT A49EU E6NE 2001040200283 20010402 00283 NE 2001 4 2 AU010072 2 20010203 G 7321 8061963 FMU BOEING 717 717200 1383700 NM RROYCE BR700 BR700715A130 NE FUEL CONTROL FAULTY W O OTHER J WARNING INDICATION DE DESCENT 1 AU S (AUS) NR 2 ENGINE FUEL METERING UNIT (FMU) AND ELECTRONIC ENGINE CONTROLLER (EEC) FAULTY. 2 L 7 2 4F 4 F TR A6WE E00061EN 2001040200284 20010402 00284 NE 2001 4 2 AU010073 2 20010203 G 7321 114E6112G117 EEC BOEING 717 717200 1383700 NM RROYCE BR700 BR700715A130 NE FUEL CONTROL FAULTY W O OTHER J WARNING INDICATION DE DESCENT 1 AU S (AUS) NR 2 ENGINE ELECTRONIC ENGINE CONTROLLER (EEC) FAULTY. SEE ALSO MDR 01/0072. 2 L 7 2 4F 4 F TR A6WE E00061EN 2001040200285 20010402 00285 NE 2001 4 2 AU010074 3 20010129 G 6111 RFC11U1R6A BLADE EMB 120 EMB120 3260201 SO PWA 118 PW118A NE HAMSTD 14RF 14RF9 NE PROPELLER DAMAGED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) LT PROPELLER BLADE DAMAGED BY MISSING SPINNER ATTACHMENT SCREW. THREE SCREWS MISSING FROM SPINNER. ONE SCREW WAS F OUND EMBEDDED IN THE PROPELLER BLADE. MAINTENANCE HAD BEEN CARRIED OUT ON THE PROPELLER PRIOR TO THE FLIGHT. 2 L 7 2 4T 4 T RT A31SO E20NE 6 C P11NE 2001040200286 20010402 00286 EA 2001 4 2 AU010075 1 20010203 G 3213 BLOCK DHAV DHC6 DHC6300 2802606 EA MLG FAILED W O OTHER J WARNING INDICATION LD LANDING 1 AU S (AUS) RT MAIN LANDING GEAR COMPRESSION BLOCKS FAILED WITH RESULTANT DAMAGE TO THE FUSELAGE. BLOCKS FAILED DUE TO RT MLG CONTACTING A RIDGE ON THE AIRSTRIP. 1 H 7 2 3T RT A9EA 2001040200287 20010402 00287 EA 2001 4 2 AU010076 2 20010112 G 7414 K3984 CAPACITOR SLICK 4381 CESSNA 150 152 2071835 CE LYC O235 O235L2C 41505 EA MCAULY 1A103 1A103TCM GL LT MAGNETO BROKEN W K NONE O OTHER IN INSP/MAINT 1 AU S 2068 97020839 (AUS) LT MAGNETO CAPACITOR CONNECTING WIRE BROKEN DUE TO LOOSE BEARING CAP. FURTHER INVESTIGATION FOUND THE BEARINGS TO BE DRY AND AN UNKNOWN SUBSTANCE UNDER THE BEARING CAP HOLD-DOWN PLATES WHICH PREVENTED THE CAP BEING PROPERLY SECURED. 1 H 7 1 3O 3 O NT 3A19 E223 5 N P50GL 2001040200288 20010402 00288 SO 2001 4 2 AU010077 2 20010206 G 8550 GEAR CONT O520 TSIO520K 17040 SO SCAV PUMP FAULTY W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) ENGINE OIL SCAVENGE PUMP GEAR FAULTY. ROCKWELL HARDNESS TEST GAVE A READING OF 34 WHICH IS BELOW SPECIFICATION. 3 O E8CE 2001040200289 20010402 00289 NM 2001 4 2 AU010078 1 20010112 G 5330 SKIN BOEING 747 747238B 1384828 NM FUSELAGE CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) FUSELAGE SKIN CRACKED AT TWO FASTENER HOLES IMMEDIATELY FORWARD OF THE FRAME AT STN 980. 2 L 7 4 4F A20WE 2001040200290 20010402 00290 GL 2001 4 2 AU010079 3 20010128 G 6114 737568 HUB LYC O360 O360A2A 41514 EA MCAULY 2D36C 2D36C14 GL PROPELLER DAMAGED W C ABORTED TAKEOFF D INFLIGHT SEPARATION TO TAKEOFF 1 AU S (AUS) PROPELLER HUB FAILED DUE TO CRACK ORIGINATING IN THE ROOT OF THEBLADE RETAINING THREAD. PROPELLER BLADE SEPARATED FROM HUB. 3 O E286 5 C P901 2001040200291 20010402 00291 NM 2001 4 2 AU010080 1 20010127 G 7110 PANEL RROYCE RB211524D4 BOEING 747 747238B 1384828 NM RROYCE RB211 RB211524D419 54555 NE COWLING MISSING W K NONE O OTHER IN INSP/MAINT 1 AU S 15288 (AUS) NR 1 ENGINE NR 1 AND NR 3 & 4 ACOUSTIC PANELS MISSING. 2 L 7 4 4F 4 F A20WE E12EU 2001040200292 20010402 00292 NM 2001 4 2 AU010081 1 20010127 G 2910 13206001 SWITCH BOEING 767 767238 NM PWA JT9 JT9D7R4E 52054 NE HYDRAULIC SYS FAULTY W O OTHER J WARNING INDICATION CR CRUISE 1 AU S (AUS) LT HYDRAULIC TAIL SHUTOFF VALVE SWITCH MODULE FAULTY. 2 L 7 2 4F 4 F RT A1NM E3NE 2001040200293 20010402 00293 CE 2001 4 2 AU010082 1 20010205 G 3213 10581002376RH FRAME BEECH 76 76 1153005 CE MLG CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) RT MAIN LANDING GEAR A FRAME CRACKED. 1 L 7 2 3O A29CE 2001040200294 20010402 00294 CE 2001 4 2 AU010083 1 20010205 G 3213 10581002375LH FRAME BEECH 76 76 1153005 CE MLG CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) LT MAIN LANDING GEAR A FRAME CRACKED. 1 L 7 2 3O A29CE 2001040200295 20010402 00295 NM 2001 4 2 AU010084 1 20010130 G 2741 WIRE BOEING 747 747438 NM RROYCE RB211 RB211524G19 NE STABILIZER DAMAGED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) LT STABILISER POSITION ROTARY VARIABLE DISPLACEMENT TRANSDUCER(RVDT) PLUG DM7884 HAD CHAFED WIRING ADJACENT TO PLU G. 2 L 7 4 4F 4 F RT A20WE E30NE 2001040200296 20010402 00296 NM 2001 4 2 AU010085 1 20010131 G 2120 UNKNOWN BOEING 767 767338 1385151 NM RROYCE RB211 RB211524* NE AIR CONDITIONING ODOR W O OTHER B SMOKE/FUMES/ODORS/SPARKS CL CLIMB 1 AU S (AUS) FUMES IN CABIN. INVESTIGATION CONTINUING INTO CAUSE. 2 L 7 2 4F 4 F RT A1NM E12EU 2001040300151 20010403 00151 NM 2001 4 3 AU010086 1 20010130 G 5730 113T161331 PANEL BOEING 767 767338 1385151 NM GE CF6 CF680C2* GL LT WING FAILED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) PANEL 551VB LOCATED ON LT WING LOWER SURFACE AFT OF THE LT MAIN LANDING GEAR MISSING A CENTRE SECTION APPROXIMATE LY 6 FEET LONG. 2 L 7 2 4F 4 F RT A1NM E23EA 2001040300152 20010403 00152 NM 2001 4 3 AU010087 1 20010128 G 2910 65C268393152 PIPE BOEING 737 737376 NM CFMINT CFM56 CFM563C 13802 EU HYDRAULIC SYS CHAFED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) HYDRAULIC SYSTEM A ENGINE DRIVEN PUMP HYDRAULIC LINE CHAFED BY LOWER AILERON PCU. 2 L 7 2 4F 4 F RT A16WE E21EU 2001040300153 20010403 00153 CE 2001 4 3 AU010088 1 20010202 G 5510 10562000025 HINGE BEECH 76 76 1153005 CE HORIZONTAL STAB LOOSE W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) ELEVATOR CENTER BEARING SUPPORT BLOCK MOVING IN CLAMPING FLANGES DUE TO APPROXIMATELY 0.127MM TO 0.254MM (0.005IN TO 0.010IN) ELONGATION OF THE RIVET HOLES. 1 L 7 2 3O A29CE 2001040300154 20010403 00154 SO 2001 4 3 AU010089 1 20010205 G 2910 D100366 FITTING EMB 120 EMB120 3260201 SO PWA 118 PW118A NE HAMSTD 14RF 14RF9 NE HYDRAULIC SYS LEAKING W O OTHER K FLUID LOSS CR CRUISE 1 AU S (AUS) HYDRAULIC FITTING LOCATED IN LT OUTBOARD NACELLE LEAKING UNDERPRESSURE. 2 L 7 2 4T 4 T RT A31SO E20NE 6 C P11NE 2001040300155 20010403 00155 EU 2001 4 3 AU010090 1 20010119 G 3610 LOOP AIRBUS 310 A310324 3930206 EU PWA 4152 PW4152 NE PNEUMATIC DIST FAULTY W D RETURN TO BLOCK J WARNING INDICATION TX TAXI/GRND HDL 1 AU S (AUS) WING LOOP A PNEUMATIC SYSTEM INOPERATIVE. 2 L 7 2 4F RT A35EU E24NE 2001040300156 20010403 00156 EU 2001 4 3 AU010091 1 20010202 G 3610 DUCT AIRBUS 310 A310324 3930206 EU PWA 4152 PW4152 NE PNEUMATIC DIST LEAKING W O OTHER J WARNING INDICATION NR NOT REPORTED 1 AU S (AUS) NR 1 BLEED AIR SYSTEM LEAKING. 2 L 7 2 4F RT A35EU E24NE 2001040300157 20010403 00157 EU 2001 4 3 AU010092 1 20010202 G 5270 SWITCH FOKKER F28 F28MK1000 4990808 EU RROYCE SPEY SPEY55515 54521 EU DOOR WARNING CONTAMINATED W O OTHER N FALSE WARNING NR NOT REPORTED 1 AU S (AUS) FORWARD CARGO DOOR MICROSWITCH CONTAMINATED WITH DIRT AND PAINT. 2 L 7 2 4F 4 F RT A20EU E2EU 2001040300158 20010403 00158 EU 2001 4 3 AU010094 1 20010131 G 5270 SWITCH FOKKER F28 F28MK1000 4990808 EU RROYCE SPEY SPEY55515 54521 EU DOOR WARNING OUT OF ADJ W O OTHER N FALSE WARNING CR CRUISE 1 AU S (AUS) SERVICE DOOR MICROSWITCH OUT OF ADJUSTMENT. 2 L 7 2 4F 4 F RT A20EU E2EU 2001040300159 20010403 00159 EU 2001 4 3 AU010095 1 20010130 G 3610 DUCT FOKKER F28 F28MK1000 4990808 EU RROYCE SPEY SPEY55515 54521 EU PNEUMATIC DIST LEAKING W O OTHER N FALSE WARNING NR NOT REPORTED 1 AU S (AUS) TAIL SECTION PNEUMATIC DUCT LEAK WARNING. INVESTIGATION COULD FIND NO LEAKS. 2 L 7 2 4F 4 F RT A20EU E2EU 2001040300163 20010403 00163 EU 2001 4 3 AU010096 1 20010129 G 5270 SWITCH FOKKER F28 F28MK1000 4990808 EU RROYCE SPEY SPEY55515 54521 EU DOOR WARNING OUT OF ADJ W A UNSCHED LANDING N FALSE WARNING CL CLIMB 1 AU S (AUS) SERVICE DOOR WARNING LIGHT ILLUMINATED. SUSPECT MICROSWITCHES OUT OF ADJUSTMENT. 2 L 7 2 4F 4 F RT A20EU E2EU 2001040300164 20010403 00164 EU 2001 4 3 AU010097 1 20010128 G 5270 SWITCH FOKKER F28 F28MK1000 4990808 EU RROYCE SPEY SPEY55515 54521 EU DOOR WARNING STUCK W A UNSCHED LANDING N FALSE WARNING CR CRUISE 1 AU S (AUS) CARGO DOOR MICROSWITCHES STICKING INTERMITTENTLY. 2 L 7 2 4F 4 F RT A20EU E2EU 2001040300165 20010403 00165 EU 2001 4 3 AU010098 1 20010128 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) FORWARD BATTERY OVERTEMPERATURE. 2 L 7 2 4F 4 F RT A20EU E2EU 2001040300166 20010403 00166 EU 2001 4 3 AU010099 1 20010126 G 5270 SWITCH FOKKER F28 F28MK1000 4990808 EU RROYCE SPEY SPEY55515 54521 EU DOOR WARNING OUT OF ADJ W A UNSCHED LANDING N FALSE WARNING CR CRUISE 1 AU S (AUS) FORWARD SERVICE DOOR MICROSWITCH OUT OF ADJUSTMENT. 2 L 7 2 4F 4 F RT A20EU E2EU 2001040300167 20010403 00167 EU 2001 4 3 AU010100 1 20010125 G 5312 BULKHEAD FOKKER F28 F28MK1000 4990808 EU RROYCE SPEY SPEY55515 54521 EU FUSELAGE CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) REAR PRESSURE BULKHEAD CRACKED. 2 L 7 2 4F 4 F RT A20EU E2EU 2001040300168 20010403 00168 EU 2001 4 3 AU010101 1 20010120 G 3230 UPLOCK FOKKER F28 F28MK1000 4990808 EU RROYCE SPEY SPEY55515 54521 EU RT MLG LOOSE W A UNSCHED LANDING N FALSE WARNING CL CLIMB 1 AU S (AUS) RT MAIN LANDING GEAR DOOR UPLOCK HOOK LOOSE. 2 L 7 2 4F 4 F RT A20EU E2EU 2001040300169 20010403 00169 EU 2001 4 3 AU010102 1 20010105 G 5270 SWITCH FOKKER F28 F28MK1000 4990808 EU RROYCE SPEY SPEY55515 54521 EU DOOR WARNING STUCK W C ABORTED TAKEOFF N FALSE WARNING TO TAKEOFF 1 AU S (AUS) CARGO DOOR MICROSWITCHES STICKING INTERMITTENTLY. 2 L 7 2 4F 4 F RT A20EU E2EU 2001040300170 20010403 00170 SO 2001 4 3 AU010103 1 20010202 G 2731 41734078 CONTROL CABLE PIPER PA31 PA31350 7103110 SO LYC O540 TIO540J2BD 41532 EA HARTZL HCE3Y HCE3YR2 GL ELEVATOR TAB WORN W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) ELEVATOR TRIM CABLE SEVERELY WORN IN THE AREA AROUND THE TRIM SERVO. ALL WIRE STRANDS BROKEN EXCEPT FOR TWO. 1 L 7 2 3O 3 O A20SO E14EA 5 C P33EA 2001040300171 20010403 00171 EA 2001 4 3 AU010104 2 20010202 G 8550 LW13383 BAFFLE PIPER PA31 PA31350 7103110 SO LYC O540 LTIO540J2BD 41533 EA HARTZL HCE3Y HCE3YR2 GL ENGINE SUMP LOOSE W K NONE O OTHER IN INSP/MAINT 1 AU S 691 (AUS) ENGINE SUMP BAFFLE RIVET MISSING. THREE REMAINING RIVETS LOOSE. METAL IN OIL SYSTEM CAME FROM WORKING RIVETS. 1 L 7 2 3O 3 O A20SO E14EA 5 C P33EA 2001040300172 20010403 00172 EU 2001 4 3 AU010105 2 20010205 G 7261 9584 ENGINE FOKKER F28 F28MK4000 4990810 EU RROYCE SPEY SPEY55515 54521 EU OIL PRESSURE LOW W O OTHER E K J VIBRATION/BUFFET FLUID LOSS WARNING INDICATION NR NOT REPORTED 1 AU S (AUS) NO2 ENGINE LOW OIL PRESSURE. ENGINE REMOVED AND AWAITING STRIPREPORT. 2 L 7 2 4F 4 F RT A20EU E2EU 2001040300173 20010403 00173 NM 2001 4 3 AU010106 1 20010105 G 5310 STRUCTURE BOEING 727 727277 138408S NM PWA JT8 JT8D15 52051 NE FUSELAGE CORRODED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) NUMEROUS AREAS OF CORROSION FOUND DURING CPCP INSPECTION IAWAD/B727/128. 2 L 7 3 4F 4 F RT A3WE E2EA 2001040300174 20010403 00174 NM 2001 4 3 AU010107 1 20010130 G 2520 11 BOLT BOEING 737 737377 NM GE CFM56 CFM563B1 13802 NE SEAT BELT LOOSE W K NONE O OTHER IN INSP/MAINT 1 AU S 4006 (AUS) SEAT BELT ATTACHMENT BOLT LOOSE AT SEAT 11E. FOUND DURING INSPECTION IAW ER B73-25-20-246. 2 L 7 2 4F 4 F RT A16WE E2GL 2001040300175 20010403 00175 NE 2001 4 3 AU010108 2 20010207 G 7200 0292005250 ENGINE SKRSKY S76 S76C 8143008 NE TMECA ARRIEL ARRIEL1S 60030 NE NR 1 SEIZED W K NONE O OTHER IN INSP/MAINT 1 AU S 1738 (AUS) NR 1 ENGINE INTERNAL FAILURE. INSPECTION FOUND COMPRESSOR SEIZED AND SEVERAL TURBINE BLADES MISSING/BROKEN. 1 G 7 2 3U 3 U NC H1NE E19EU 2001040300176 20010403 00176 NM 2001 4 3 AU010109 1 20010123 G 3230 113T1110 FITTING BOEING 767 767277 NM GE CF6 CF680A 30025 NE MLG CORRODED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) LT AND RT MAIN LANDING GEAR SIDE STRUT SWIVEL ASSEMBLY FITTINGS COORODED IN AREA BENEATH BUSHING FLANGE. 2 L 7 2 4F 4 F RT A1NM E13NE 2001040300177 20010403 00177 CE 2001 4 3 AU010110 1 20010214 G 5330 101120108604 SKIN BEECH 200 200BEECH 1152920 CE PWA PT6 PT6A42 52043 NE MCAULY 4HFR34 4HFR34C754 NE FUSELAGE DEBONDED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) TOP SKIN DISBONDED. 1 L 7 2 4T 4 T A24CE E4EA 6 C 3PNE 2001040300178 20010403 00178 EU 2001 4 3 AU010111 1 20010211 G 5102 GATES HOSE COLT 160 160A 8970104 EU BALLOON REPORTS FAULTY W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) OUTER SKIN OF THE LPG HOSE RUPTURED. 1 B 0 3BEU 2001040300179 20010403 00179 EA 2001 4 3 AU010112 1 20010122 G 5553 C6TFM102227 FITTING DHAV DHC6 DHC6300 2802606 EA VERTICAL STAB CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) VERTICAL STABILISER FORWARD ADAPTER FITTING RIGHT HAND ATTACHMENT LUG CRACKED. 1 H 7 2 3T RT A9EA 2001040300180 20010403 00180 SO 2001 4 3 AU010113 1 20010208 G 2823 480700 PIN PIPER PA23 PA23250 7102308 SO LYC O540 IO540C4B5 41532 EA HARTZL HCE2Y HCE2YK2 GL FUEL SELECTOR BROKEN W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) LT FUEL SELECTOR ROLL PINS (2OFF) BROKEN. 1 L 7 2 3O 3 O 1A10 1E4 5 C P9EA 2001040300181 20010403 00181 CE 2001 4 3 AU010114 1 20010206 G 2731 BOLT CESSNA 402 402C 207590R CE CONT O520 TSIO520VB 17040 SO MCAULY 3AF32C 3AF32C93 GL FLIGHT CONTROL WORN W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) EXCESSIVE TRIM TAB FREE-PLAY DUE TO WORN AFT PUSHROD BOLT. 1 L 7 2 3O 3 O A7CE E8CE 5 C P22EA 2001040300182 20010403 00182 EU 2001 4 3 AU010115 1 20010129 G 7933 J03040C CONNECTOR FOKKER F28 F28MK0100 4990807 EU RROYCE TAY TAY62015 04564 NE OIL TEMP CONTAMINATED W O OTHER E K J VIBRATION/BUFFET FLUID LOSS WARNING INDICATION CL CLIMB 1 AU S (AUS) NR 1 ENGINE OIL TEMPERATURE PROBE CONNECTOR PLUG LOOSE AND CONTAMINATED. 2 L 7 2 4F 4 F RT E25NE 2001040300183 20010403 00183 NM 2001 4 3 AU010116 1 20010122 G 2910 82910010113 PIPE DHAV DHC8 DHC8102 2809003 NM PWA 120 PW120A NE HAMSTD 14SF 14SF7 NE HYDRAULIC SYS FRACTURED W C ABORTED TAKEOFF K J FLUID LOSS WARNING INDICATION TO TAKEOFF 1 AU S (AUS) HYDRAULIC PIPE FRACTURED ON RADIUS AT STA. 110.0. LOSS OF HYDRAULIC FLUID. 2 H 7 2 4T 4 T RT A13NM E20NE 6 C P7NE 2001040300184 20010403 00184 WP 2001 4 3 AU010117 1 20010130 G 5720 157 FITTING DHAVXX DH82 DH82AROBRTSN 2801002 WP DHAVXX GIPSY GIPSYMAJOR1 20004 WP LT WING FAILED W K NONE O OTHER IN INSP/MAINT 1 AU S 157 (AUS) LT WING FRONT LOWER INTERPLANE STRUT ATTACHMENT FITTING BROKEN AWAY DUE TO WOOD ROT. 1 Q 7 1 3I 3 I A8EU A8EU 2001040300185 20010403 00185 NM 2001 4 3 AU010118 1 20010120 G 3260 UPLOCK 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) RT MAIN LANDING GEAR UPLOCK SENSOR OUT OF ADJ. 2 H 7 2 4T 4 T RT A13NM E20NE 6 C P7NE 2001040300186 20010403 00186 CE 2001 4 3 AU010119 1 20010206 G 8011 PM2407 STARTER CESSNA 404 404CESSNA 2075901 CE CONT O520 GTSIO520M 17032 SO MCAULY 3FF32 3FF32C501 GL LT ENGINE FAILED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) LT ENGINE STARTER MOTOR FAULTY. ONE NEGATIVE BRUSH MISSING WITH THE OTHER NEGATIVE BRUSH LOOSE IN THE BRUSH HOLDER AND EVIDENCE OF SEVERE ARCING AROUND THE BRUSH/PIGTAIL SECURING SCREW. BOTHPOSITIVE BRUSHES WERE LOOSE AND THE BRUSH HO LDERS WITHSEVERE ARCING AROUND THE SECURING SCREW. 1 L 7 2 3O 3 O A25CE E7CE 5 C P45GL 2001040300187 20010403 00187 NE 2001 4 3 AU010120 2 20010216 G 7200 ENGINE BEECH 200 200BEECH 1152920 CE PWA PT6 PT6A42 52043 NE HARTZL HCB3T HCB3TN3 GL ENGINE BAY MAKING METAL W K NONE O OTHER IN INSP/MAINT 1 AU S 4811 (AUS) ENGINE CHIP DETECTOR CONTAMINATED BY METAL CHIP. SUSPECT CHIP WAS A PART OF A TAB WASHER. 1 L 7 2 4T 4 T A24CE E4EA 6 C P15EA 2001040300188 20010403 00188 CE 2001 4 3 AU010121 1 20010115 G 5511 04320016 RIB CESSNA 150 150M 2071830 CE CONT O200 O200A 17020 SO MCAULY 1A102 1A102OCM GL HORIZONTAL STAB CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) HORIZONTAL STABILISER FORWARD ATTACHMENT RIBS CRACKED. 1 H 7 1 3O 3 O 3A19 E252 5 N P918 2001040300189 20010403 00189 CE 2001 4 3 AU010122 1 20010115 G 5511 043200146 RIB CESSNA 150 150M 2071830 CE CONT O200 O200A 17020 SO MCAULY 1A102 1A102OCM GL HORIZONTAL STAB CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) HORIZONTAL STABILISER FORWARD ATTACHMENT RIBS CRACKED. 1 H 7 1 3O 3 O 3A19 E252 5 N P918 2001040300190 20010403 00190 EU 2001 4 3 AU010124 2 20010206 G 7321 0164168200 FUEL CONTROL SNIAS AS332 AS332L 8680809 EU TMECA MAKILA MAKILA1A 60040 EU NR 2 ENGINE FAULTY W A UNSCHED LANDING E J VIBRATION/BUFFET WARNING INDICATION CR CRUISE 1 AU S 258 (AUS) NR 2 ENGINE FUEL CONTROL UNIT FAULTY. 2 G 7 2 4U 4 U H4EU E12NE 2001040300193 20010403 00193 SO 2001 4 3 AU010126 1 20010206 G 5243 12007993614 DOOR EMB 120 EMB120 3260201 SO PWA 118 PW118A NE HAMSTD 14RF 14RF9 NE HYDRAULIC BAY SEPARATED W O OTHER D INFLIGHT SEPARATION NR NOT REPORTED 1 AU S (AUS) RT HYDRAULIC BAY DOOR FAILED AND SEPARATED DURING FLIGHT. DOORHAD BEEN OPENED FOR MAINTENANCE BEFORE FLIGHT AND IT IS SUSPECTED THAT IT WAS NOT PROPERLY CLOSED AND LATCHED. 2 L 7 2 4T 4 T RT A31SO E20NE 6 C P11NE 2001040300194 20010403 00194 NM 2001 4 3 AU010127 1 20010204 G 7603 CABLE RROYCE RB211524D4 BOEING 747 747SP38 NM RROYCE RB211 RB211524D419 54555 NE POWER LEVER DAMAGED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) ENGINE THRUST CONTROL SYSTEM CABLES, PULLEYS AND FITTINGS DAMAGED. FOUND DURING INSPECTION IAW AD/B747/229 AND FAA AD/2000-05-30 AMDT39-11640. 2 L 7 4 4F 4 F RT A20WE E12EU 2001040300195 20010403 00195 CE 2001 4 3 AU010128 1 20010201 G 2701 05131679 WHEEL CESSNA 182 182C 2072708 CE CONT O470 O470L 17026 SO HARTZL HCA2X BHCA2XF1 GL CONTROL COLUMN CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) BOTH CONTROL WHEELS CRACKED FROM BOTTOM RIVET HOLE. 1 H 7 1 3O 3 O NT 3A13 E273 5 C P908 2001040300196 20010403 00196 NM 2001 4 3 AU010129 1 20010202 G 2612 51291001 FIRE LOOP BOEING 747 747338 NM RROYCE RB211 RB211524D419 54555 NE APU BAY MALFUNCTIONED W F A ACTIVATE FIRE EXT. UNSCHED LANDING N FALSE WARNING CL CLIMB 1 AU S (AUS) APU LOWER DOOR FIRE DETECTOR LOOP HAD HIGH RESISTANCE. FALSE WARNING INDICATION RESULTED IN DISCHARGE OF FIRE BOTT LE. 2 L 7 2 4F 4 F RT A20WE E12EU 2001040300197 20010403 00197 NM 2001 4 3 AU010130 1 20010202 G 2910 HOSE BOEING 737 737376 NM CFMINT CFM56 CFM563C 13802 EU HYDRAULIC SYS FAILED W K NONE K FLUID LOSS IN INSP/MAINT 1 AU S (AUS) LT MAIN LANDING GEAR DOWNLOCK HYDRAULIC HOSE SPLIT. LOSS OF HYDRAULIC FLUID. 2 L 7 2 4F 4 F RT A16WE E21EU 2001040300198 20010403 00198 NM 2001 4 3 AU010131 1 20010110 G 3260 841005 PSEU DHAV DHC8 DHC8102 2809003 NM PWA 120 PW120A NE HAMSTD 14SF 14SF7 NE MLG FAULTY W A UNSCHED LANDING N FALSE WARNING CL CLIMB 1 AU S (AUS) LANDING GEAR PROXIMITY SWITCH ELECTRONIC UNIT (PSEU) FAULTY. 2 H 7 2 4T 4 T RT A13NM E20NE 6 C P7NE 2001040300200 20010403 00200 SO 2001 4 3 AU010132 2 20010202 G 8530 EXHAUST VALVE CESSNA 206 U206F 2073333 CE CONT O520 IO520F 17032 SO MCAULY 3A32C D3A32C90 GL ENGINE LEAKING W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) ENGINE EXHAUST VALVE LEAKING. 1 H 7 1 3O 3 O A4CE E5CE 5 C P21EA 2001040300201 20010403 00201 SO 2001 4 3 AU010133 1 20010207 G 5320 12043522001LH BEAM EMB 120 EMB120 3260201 SO PWA 118 PW118A NE HAMSTD 14SF 14SF9 NE CABIN CORRODED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) FLIGHT ATTENDANT SEAT SUPPORT FRAMES CORRODED. 2 L 7 2 4T 4 T RT A31SO E20NE 6 N P11NE 2001040300202 20010403 00202 SO 2001 4 3 AU010134 1 20010207 G 5320 12025916001RH BEAM EMB 120 EMB120 3260201 SO PWA 118 PW118A NE HAMSTD 14SF 14SF9 NE CABIN CORRODED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) FLIGHT ATTENDANTS SEAT SUPPORT FRAMES CORRODED. 2 L 7 2 4T 4 T RT A31SO E20NE 6 N P11NE 2001040300203 20010403 00203 EU 2001 4 3 AU010135 1 20010203 G 7712 P66230C ENGINE BAG JETSTM JETSTM3201 1500217 EU GARRTT TPE331 TPE33112UHR WP ROTOL R333 R333482F12 GL LEFT OUT OF ADJ W C ABORTED TAKEOFF R J PARTIAL RPM/PWR LOSS WARNING INDICATION TO TAKEOFF 1 AU S (AUS) LT ENGINE RPM ROLLBACK. SUSPECT CAUSED BY NR 1 TORQUE BRIDGE PIT OUT OF ADJUSTMENT. 2 L 7 2 4T 4 T RT A56EU E4WE 6 C P61GL 2001040300204 20010403 00204 SO 2001 4 3 AU010136 1 20010206 G 2133 2091G010800 OUTFLOW VALVE EMB 120 EMB120 3260201 SO PWA 118 PW118A NE HAMSTD 14SF 14SF9 NE CABIN PRESSURE FAULTY W A UNSCHED LANDING J WARNING INDICATION CL CLIMB 1 AU S 4884 (AUS) PRESSURISATION SYSTEM OUTFLOW VALVE FAULTY. 2 L 7 2 4T 4 T RT A31SO E20NE 6 N P11NE 2001040300205 20010403 00205 SO 2001 4 3 AU010137 1 20010126 G 2751 487927 SWITCH PIPER PA31 PA31350 7103110 SO LYC O540 TIO540J2BD 41532 EA HARTZL HCE3Y HCE3YR2 GL LT WING TE FLAPS FAILED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) LH WING FLAP UPLIMIT MICROSWITCH FAILED. 1 L 7 2 3O 3 O A20SO E14EA 5 C P33EA 2001040300206 20010403 00206 CE 2001 4 3 AU010138 1 20010220 G 3510 1013800491 HOSE BEECH 200 200BEECH 1152920 CE PWA PT6 PT6A42 52043 NE MCAULY 4HFR34 4HFR34C754 NE CREW OXYGEN SPLIT W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) COPILOTS OXYGEN HOSE FAILED. HOSE HAD BEEN INCORRECTLY FITTED WITH A TIGHT RADIUS. 1 L 7 2 4T 4 T A24CE E4EA 6 C 3PNE 2001040300207 20010403 00207 GL 2001 4 3 AU010139 2 20010123 G 7210 6877180 GEARBOX BELL 206 206B 1181511 SW ALLSN 250C 250C20B 03013 GL ENGINE MAKING METAL W A UNSCHED LANDING J WARNING INDICATION CR CRUISE 1 AU S (AUS) ENGINE GEARBOX OUT OF LIMITS. CHIP DETECTORS CONTAMINATED WITHMETAL PARTICLES. 1 G 7 1 3U 3 U H2SW E4CE 2001040300208 20010403 00208 EU 2001 4 3 AU010140 1 20010119 G 5302 332A2400200001 STRUCTURE SNIAS AS332 AS332L 8680809 EU TMECA MAKILA MAKILA1A 60040 EU TAIL BOOM CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) TAIL BOOM CRACKED IN AREA OF PYLON DECK. 2 G 7 2 4U 4 U H4EU E12NE 2001040300209 20010403 00209 SO 2001 4 3 AU010141 1 20010213 G 7112 BAFFLE PIPER PA31 PA31350 7103110 SO LYC O540 TIO540J2BD 41532 EA HARTZL HCE3Y HCE3YR2 GL ENGINE AIR DAMAGED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) ENGINE BAFFLES DAMAGED. FOUND DURING INSPECTION IAW AD/PA31/96REQ1. 1 L 7 2 3O 3 O A20SO E14EA 5 C P33EA 2001040300210 20010403 00210 EA 2001 4 3 AU010142 2 20010119 G 8530 LW16740 EXHAUST VALVE PIPER PA31 PA31350 7103110 SO LYC O540 TIO540J2BD 41532 EA HARTZL HCE3Y HCE3YR2 GL ENGINE WORN W K NONE O OTHER IN INSP/MAINT 1 AU S 1146 (AUS) LH ENGINE EXHAUST VALVES (2OFF) ERODED. RT ENGINE EXHAUST VALVES(4OFF) ERODED. 1 L 7 2 3O 3 O A20SO E14EA 5 C P33EA 2001040300211 20010403 00211 NE 2001 4 3 AU010143 2 20010215 G 7200 RB211524G ENGINE BOEING 747 747438 NM RROYCE RB211 RB211524G19 NE NR 4 FIRE W F A ACTIVATE FIRE EXT. UNSCHED LANDING A J FLAME/FIRE WARNING INDICATION CL CLIMB 1 AU S 16202 (AUS) NR 4 ENGINE FIRE. INVESTIGATION FOUND FIRE/HEAT DAMAGE TO WIRING AND CLAMPS IN AREA OF COMBUSTION CHAMBER COWLING. 2 L 7 4 4F 4 F RT A20WE E30NE 2001040300212 20010403 00212 NM 2001 4 3 AU010144 1 20010216 G 2741 WIRE DHAV DHC8 DHC8102 2809003 NM PWA 120 PW120A NE HAMSTD 14SF 14SF7 NE HORIZONTAL STAB WORN W O OTHER J WARNING INDICATION NR NOT REPORTED 1 AU S (AUS) HORIZONTAL STABILISER SURFACE POSITION INDICATOR WIRE CHAFED ANDSHORT CIRCUITING INSIDE CONDUIT LOCATED BETWEEN TH E FORWARD SPAROF THE HORIZONTAL STABILISER AND THE RT ELEVATOR SYNCHRO. 2 H 7 2 4T 4 T RT A13NM E20NE 6 C P7NE 2001040300213 20010403 00213 NE 2001 4 3 AU010146 2 20010208 G 7321 CPW3111697503B EEC DHAV DHC8 DHC8202 2809007 NM PWA 120 PW123D 52152 NE HAMSTD 14SF 14SF23 NE LT ENGINE OUT OF ADJ W C ABORTED TAKEOFF R J PARTIAL RPM/PWR LOSS WARNING INDICATION TO TAKEOFF 1 AU S (AUS) LT ENGINE ELECTRONIC UNIT AUTO-FEATHER OPERATION FUNCTION OUT OF ADJUSTMENT. UNIT HAD BEEN ADJUSTED ON THE PREVIOU S NIGHT WITHOUTCHECKING THE AUTO-FEATHER FUNCTION. 2 H 7 2 4T 4 T RT A13NM E20NE 6 C P7NE 2001040300214 20010403 00214 CE 2001 4 3 AU010147 1 20010221 G 3213 10581002376 FRAME BEECH 76 76 1153005 CE MLG CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) RT MAIN LANDING GEAR A FRAME CRACKED. 1 L 7 2 3O A29CE 2001032600495 20010326 00495 NM 2001 3 26 AU010148 1 20010217 G 2910 DSC252A40230 PIPE DHAV DHC8 DHC8102 2809003 NM PWA 120 PW120A NE HAMSTD 14SF 14SF7 NE HYDRAULIC, MAIN LEAKING W K NONE O K OTHER FLUID LOSS IN INSP/MAINT 1 AU S (AUS) HYDRAULIC LINE LOCATED IN RH WHEEL BAY CONTAINED A PINHOLE LEAK. 2 H 7 2 4T 4 T RT A13NM E20NE 6 C P7NE 2001032600012 20010326 00012 SO 2001 3 26 AU010149 2 20010123 G 8520 652560 CRANKCASE CONT IO520L CESSNA 210 210N 2073453 CE CONT O520 IO520L 17032 SO MCAULY D3A34 D3A34C404 GL RECIPROCATING EN CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S 415 567731 (AUS) CRANKCASE CRACKED IN NUMEROUS PLACES. INSPECTION FOUND EXCESSIVE FRETTING ON THE SECOND AND THIRD MAIN BEARING SAD DLE FACES WHEN VIEWED FROM THE REAR. LOCTITE OR SIMILAR WAS FOUND ON THE BEARING SADDLE FACES. THE MAIN THROUGH BOLTS WE RE OF THE OLDER SIX POINTNUTS. THE HYDRAULIC LIFTERS FITTED IN THE EXHAUST POSITIONS WERE PNO 646288 INSTEAD OF PNO 6462 77. THE OIL PICKUP SCREEN SUCTION SCREEN WAS THE INCORRECT TYPE AS REQUIRED BY SB M87-11 REV2. NO OVERHAUL HISTORY COULD BE FOUND FOR THE FUEL PUMP OR THE FCU. PERSONNEL/MAINTENANCE ERROR. WRONG PART. 1 H 7 1 3O 3 O 3A21 E5CE 5 C P47GL 2001032600013 20010326 00013 EA 2001 3 26 AU010150 2 20010213 G 8530 LW16703 CYLINDER LYC O235L2C PIPER PA38 PA38112 7103812 SO LYC O235 O235L2C 41505 EA SNSNCH 72C 72CK EA RECIPROCATING EN CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S 810 L1609315 (AUS) ENGINE NO2 CYLINDER CRACKED AT BASE. OIL LEAKING FROM CRACK. 1 L 7 1 3O 3 O A18SO E223 5 N P9045 2001032700417 20010327 00417 NM 2001 3 27 AU010151 1 20010109 G 5280 28489 DOOR BOEING 737400 BOEING 757 757* NM CFMINT CFM56 CFM563C 13802 EU LANDING GEAR DOO CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S 10341 28489 (AUS) RT MAIN LANDING GEAR STRUT DOOR CRACKED THROUGH LOWER ATTACHMENT BOLT HOLDER. 2 L 7 2 4F 4 F RT A2NM E21EU 2001032700418 20010327 00418 SO 2001 3 27 AU010152 1 20010213 G 3242 RFS1015 DISK BFGOODRICH 214791 EMB 120 EMB120 3260201 SO PWA 118 PW118A NE HAMSTD 14RF 14RF9 NE BRAKE BROKEN W K NONE O OTHER IN INSP/MAINT 1 AU S 0671 (AUS) BRAKE ROTATING DISC (CARRIER AND LINING ASSEMBLY) BROKEN. 2 L 7 2 4T 4 T RT A31SO E20NE 6 C P11NE 2001032700419 20010327 00419 SO 2001 3 27 AU010153 1 20010213 G 5330 120056 SKIN EMB 120 EMB120 3260201 SO PWA 118 PW118A NE HAMSTD 14RF 14RF9 NE FUSELAGE CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) SKIN SURROUNDING THE COPILOTS WINDOW FRAME CRACKED. 2 L 7 2 4T 4 T RT A31SO E20NE 6 C P11NE 2001032700420 20010327 00420 NM 2001 3 27 AU010154 1 20010202 G 5753 6546435274SP SKIN BOEING 737 7374Q8 NM CFMINT CFM56 CFM563C 13802 EU TE FLAPS DELAMINATED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) RT AFT OUTER FLAP TRAILING EDGE DELAMINATING AT INBOARD AFT CORNER. 2 L 7 2 4F 4 F RT A16WE E21EU 2001040300001 20010403 00001 EA 2001 4 3 AU010155 2 20010219 G 7310 420218 SWITCH BELL 412 412 1182202 SW PWA PT6T PT6T3 52045 EA FUEL BYPASS LEAKING W K NONE K FLUID LOSS IN INSP/MAINT 1 AU S (AUS) FUEL FILTER BYPASS SWITCH LEAKING FROM SWITCH BODY IN THE AREA WHERE THE ELECTRICAL CONNECTOR IS SOLDERED TO THE SWITCH. FUEL WAS SEEN RUNNING INTO THE ENGINE INTAKE PLENUM. A REPLACEMENT SWITCH HAD POOR SOLDERING OF THE CONNECTOR IN THE SAME AREA ASTHE FAILED ITEM. 1 G 7 2 4U 4 U H4SW E22EA 2001040300002 20010403 00002 EU 2001 4 3 AU010156 1 20010211 G 7714 2454401 SENSOR AEROSP SA365 SA365C 8680667 EU TMECA ARRIEL ARRIEL1A 60030 NE ENGINE FAULTY W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) ENGINE OVERSPEED SENSOR FAULTY. 1 G 7 2 3U 3 U H10EU E19EU 2001032700421 20010327 00421 CE 2001 3 27 AU010157 1 20010202 G 2410 646655 GEAR CESSNA ALTERNATOR CESSNA 310 310R 2074245 CE CONT O520 IO520M 17032 SO MCAULY 3AF32C 3AF32C87 GL DC GENERATOR-ALT DAMAGED W K NONE O OTHER IN INSP/MAINT 1 AU S 185 EO030305377 (AUS) LH ENGINE ALTERNATOR DRIVE GEAR DAMAGED AND OUTER SHELL DISTORTED. EVIDENCE OF VICE MARKS ON OUTSIDE OF SHELL. FUR THERDAMAGE FOUND:-1. OIL SEAL INSTALLED BACKWARDS.2. SUPPRESSOR CAPACITOR LOOSE INSIDE OF ALTERNATOR AND SCREW LOOSE. 3. PITTING IN CASE HARDENING ON THE SLIP RING END OF THE ROTOR SHAFT. 4. STATOR CORE LAMINATIONS BADLY DISTORTED RENDERING CORE UNSERVICEABLE. THE ROTOR IN ALTERNATOR AT TIME OF STRIP DOWN INSPECTION SHOWED NO SIGNS OF CONTACT WITH STATOR PO LES.PERSONNEL/MAINTENANCE ERROR. 1 L 7 2 3O 3 O 3A10 E5CE 5 C P22EA 2001032700422 20010327 00422 CE 2001 3 27 AU010158 1 20010222 G 5280 08411066 BRACKET CESSNA 310 310R 2074245 CE CONT O520 IO520M 17032 SO MCAULY 3AF32C 3AF32C87 GL LANDING GEAR DR BROKEN W K NONE O D OTHER INFLIGHT SEPARATION LD LANDING 1 AU S 5203 (AUS) LH MAIN LANDING GEAR DOOR BRACKET FAILED. 1 L 7 2 3O 3 O 3A10 E5CE 5 C P22EA 2001040300003 20010403 00003 EU 2001 4 3 AU010159 1 20010212 G 7722 21186009 COMPUTER BAG JETSTM JETSTM3201 1500217 EU GARRTT TPE331 TPE33112UHR WP MCAULY 4HFR34 4HFR34C653 NE ENGINE FAULTY W A UNSCHED LANDING N FALSE WARNING CL CLIMB 1 AU S (AUS) LT ENGINE SINGLE RED LINE COMPUTER FAULTY. 2 L 7 2 4T 4 T RT A56EU E4WE 6 C 3PNE 2001040300004 20010403 00004 EU 2001 4 3 AU010160 1 20010223 G 7160 TU195MM660MMCC HOSE BNORM BN2 BN2B20 1520302 EU LYC O540 IO540K1B5 41532 EA HARTZL HCC2Y HCC2YK2 GL ENG AIR INTAKE FAILED W C ABORTED TAKEOFF R J PARTIAL RPM/PWR LOSS WARNING INDICATION TO TAKEOFF 1 AU S (AUS) NR 1 ENGINE INTAKE HOSE LOCATED BETWEEN THE AIR FILTER AND THE FCU COLLAPSED DUE TO LOOSE INNER SUPPORT WIRE. 1 H 7 2 3O 3 O A17EU 1E4 5 C P920 2001040500255 20010405 00255 NE 2001 4 5 AU010161 2 20010222 G 7530 216035037 ACTUATOR LYC ALF502R5 BAG BAE146 BAE146200A 1500266 EU LYC ALF502 ALF502R5 41580 NE COMPRESSOR BLEED FAULTY W O OTHER E VIBRATION/BUFFET AP APPROACH 1 AU S XRC8122 (AUS) NR 3 ENGINE BLEED BAND ACTUATOR FOLLOWUP ARM RETAINING CLIP AND PIN MISSING ALLOWING THE FOLLOWUP ARM AND THE OPER ATING LEVER TO FOUL EACH OTHER WHICH RESULTED IN THE BLEED BAND REMAINING CLOSED. 2 H 7 4 4F 4 F RT A49EU E6NE 2001040500256 20010405 00256 EU 2001 4 5 AU010162 1 20010221 G 2450 A2043C POWER UNIT SAAB SF340 340B 7860101 EU GE CT7TP CT79B 30030 NE ROTOL R375 R3754123F21 NE AC POWER DIST FAULTY W O OTHER H B J ELECT. POWER LOSS-50 PC SMOKE/FUMES/ODORS/SPARKS WARNING INDICATION NR NOT REPORTED 1 AU S (AUS) RT POWER DISTRIBUTION UNIT (PDU) FAULTY. STARTER-GENERATOR WOULDNOT DISENGAGE AND AN OVERTEMPERATURE WAS OBSERVED WITH SMOKE COMING FROM THE COWLS. THE FIRE BOTTLE WAS DISCHARGED AS APRECAUTION. 2 L 7 2 4T 4 T RT A52EU E8NE 6 C P17NE 2001040500257 20010405 00257 WP 2001 4 5 AU010163 2 20010228 G 7210 851 GEARBOX BAG JETSTM JETSTM3201 1500217 EU GARRTT TPE331 TPE33112UHR WP MCAULY 4HFR34 4HFR34C653 NE LEFT ENGINE MAKING METAL W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) LT ENGINE REMOVED DUE TO SUSPECT DISTRESS IN THE GEARBOX AND VIBRATION. OIL ANALYSIS FOUND METAL CONTAMINATION. 2 L 7 2 4T 4 T RT A56EU E4WE 6 C 3PNE 2001040500258 20010405 00258 CE 2001 4 5 AU010164 1 20010222 G 2710 50452133 TUBE CESSNA 310 310R 2074245 CE CONT O520 IO520M 17032 SO MCAULY 3AF32C 3AF32C87 GL AILERON CONTROL CORRODED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) OUTBOARD PUSH-PULL TUBE LOCATED IN RT WHEEL WELL CORRODED INTERNALLY. 1 L 7 2 3O 3 O 3A10 E5CE 5 C P22EA 2001040500259 20010405 00259 SW 2001 4 5 AU010165 1 20010226 G 5712 273102336 RIB SWRNGN SA227 SA227AC 8780603 SW GARRTT TPE331 TPE33111U 01514 WP ROTOL R321 R321482F8 GL RT WING CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) RT WING RIB CRACKED IN BEND RADIUS. RIB FORMS THE INNER WALL OF THE BATTERY BOX. CRACK LENGTH 203.2MM (8IN). 2 L 7 2 4T 4 T RT A8SW E4WE 6 C P61GL 2001040500260 20010405 00260 SW 2001 4 5 AU010166 1 20010226 G 5712 273102336 RIB SWRNGN SA227 SA227AC 8780603 SW GARRTT TPE331 TPE33111U 01514 WP ROTOL R321 R321482F8 GL LT WING CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) LT WING RIB CRACKED IN BEND RADIUS. RIB FORMS THE INNER WALL OF THE BATTERY BOX. CRACK LENGTH 76.2MM (3IN). 2 L 7 2 4T 4 T RT A8SW E4WE 6 C P61GL 2001040500261 20010405 00261 EU 2001 4 5 AU010167 1 20010223 G 7714 AG34 TACH GENERATOR BAG JETSTM JETSTM3201 1500217 EU GARRTT TPE331 TPE33112UHR WP MCAULY 4HFR34 4HFR34C653 NE ENGINE FAULTY W O OTHER P NO WARNING INDICATION CL CLIMB 1 AU S (AUS) TACHO-GENERATOR ZERO OUTPUT. INVESTIGATION ALSO FOUND BROKENWIRE STRANDS AT THE ENGINE WIRING DISCONNECT SPLICE. 2 L 7 2 4T 4 T RT A56EU E4WE 6 C 3PNE 2001040500262 20010405 00262 EU 2001 4 5 AU010168 2 20010219 G 7230 COMPRESSOR FOKKER F28 F28MK4000 4990810 EU RROYCE SPEY SPEY55515 54521 EU NR 1 ENGINE DAMAGED W O OTHER E VIBRATION/BUFFET CL CLIMB 1 AU S (AUS) NO1 ENGINE VIBRATION. BORESCOPE INSPECTION FOUND DAMAGE TO THESEVENTH STAGE HPC. 2 L 7 2 4F 4 F RT A20EU E2EU 2001040500263 20010405 00263 EU 2001 4 5 AU010169 1 20010218 G 2133 566920 OUTFLOW VALVE FOKKER F28 F28MK0100 4990807 EU RROYCE TAY TAY62015 04564 NE CABIN COOLING SY FAILED W O OTHER J WARNING INDICATION CR CRUISE 1 AU S 4585 (AUS) AVIONICS COOLING SYSTEM OUTFLOW VALVE FAILED. 2 L 7 2 4F 4 F RT E25NE 2001040500264 20010405 00264 CE 2001 4 5 AU010170 1 20010201 G 3260 JE1 SWITCH CESSNA 310 310R 2074245 CE CONT O520 IO520M 17032 SO MCAULY 3AF32C 3AF32C87 GL MLG WORN W O OTHER N FALSE WARNING LD LANDING 1 AU S (AUS) RT MAIN LANDING GEAR MICROSWITCH ARM WORN. ARM BROKE OFF DURING FLIGHT. 1 L 7 2 3O 3 O 3A10 E5CE 5 C P22EA 2001040500265 20010405 00265 2001 4 5 AU010172 4 20010305 G 3423 COMPASS CESSNA 150 150B 2071806 CE CONT O200 O200A 17020 SO MCAULY 1A100 1A100MCM GL COCKPIT OUT OF ADJ W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) COMPASS SWING OUT OF DATE. NO COMPASS CORRECTION CARD FITTED. 1 H 7 1 3O 3 O 3A19 E252 5 N P918 2001040500266 20010405 00266 SO 2001 4 5 AU010173 1 20010228 G 5511 40122002 SPAR PIPER PA31350 PIPER PA31 PA31350 7103110 SO LYC O540 TIO540J2BD 41532 EA HARTZL HCE3Y HCE3YR2 GL HORIZONTAL STAB CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S 311274 (AUS) HORIZONTAL STABILISER SPAR CRACKED. FOUND DURING INSPECTION IAW PIPER MSB 1007. WHEN INSPECTED IAW AD/PA31/97 AMDT 2 NO CRACKS WERE FOUND DUE TO CRACKS BEING HIDDEN BY THE ELEVATOR OUTBOARD HINGE ATTACHMENT FITTING. 1 L 7 2 3O 3 O A20SO E14EA 5 C P33EA 2001040500267 20010405 00267 SO 2001 4 5 AU010174 1 20010228 G 5511 40122003 SPAR PIPER PA31350 PIPER PA31 PA31350 7103110 SO LYC O540 TIO540J2BD 41532 EA HARTZL HCE3Y HCE3YR2 GL HORIZONTAL STAB CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S 311274 (AUS) HORIZONTAL STABILISER SPAR CRACKED. FOUND DURING INSPECTION IAW PIPER MSB 1007. WHEN INSPECTED IAW AD/PA31/97 AMDT 2 NO CRACKS WERE FOUND DUE TO CRACKS BEING HIDDEN BY THE ELEVATOR OUTBOARD HINGE ATTACHMENT FITTING. 1 L 7 2 3O 3 O A20SO E14EA 5 C P33EA 2001040500268 20010405 00268 CE 2001 4 5 AU010175 1 20010223 G 2752 08615582 GEAR CESSNA 402 402C 207590R CE CONT O520 TSIO520VB 17040 SO TE FLAP ACTUATOR WORN W O OTHER F FLT CONT AFFECTED LD LANDING 1 AU S (AUS) FLAP ACTUATOR TRANSFER GEAR STRIPPED. 1 L 7 2 3O 3 O A7CE E8CE 2001040500269 20010405 00269 EA 2001 4 5 AU010176 2 20010225 G 7414 4370 SHAFT PIPER PA28 PA28161 7102803 SO LYC O320 O320D3G 41508 EA SNSNCH 74D 74DM EA MAGNETO FAILED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) MAGNETO SHAFT BROKEN IN AREA WHERE THE POINTS CAM ATTACHES. 1 L 7 1 3O 3 O 2A13 E274 5 N P88614 2001040500270 20010405 00270 SO 2001 4 5 AU010177 2 20010308 G 8500 IO470L ENGINE BEECH 95 95B55 1152729 CE CONT O470 IO470L 17026 SO MCAULY 2AF34C 2AF34C55 GL RIGHT FAILED W C ABORTED TAKEOFF E Y J VIBRATION/BUFFET ENGINE STOPPAGE WARNING INDICATION TO TAKEOFF 1 AU S 1450 20139971L (AUS) RT ENGINE CATASTROPHIC FAILURE. 1 L 7 2 3O 3 O RT 3A16 3E1 5 C P5EA 2001040500271 20010405 00271 WP 2001 4 5 AU010178 1 20010204 G 2436 15891A VOLT REGULATOR DOUG DC4 C54E 3021530 WP PWA R2000 R2000* 52023 NE HAMSTD 23E 23E50 NE DC SYSTEM OVERHEATED W A UNSCHED LANDING B J SMOKE/FUMES/ODORS/SPARKS WARNING INDICATION CR CRUISE 1 AU S R704 (AUS) NR 2 GENERATOR VOLTAGE REGULATOR FAULTY. 2 L 7 4 4R 4 R A762 5E5 6 C P603 2001040500272 20010405 00272 SO 2001 4 5 AU010179 2 20010219 G 8530 649166 CYLINDER CESSNA 210 210L 2073448 CE CONT O520 IO520L 17032 SO MCAULY 3A32C D3A32C88 GL ENGINE CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S 397 270089R (AUS) NR 1 AND NR 3 CYLINDERS CRACKED FROM UPPER SPARK PLUG HOLE. CRACK LENGTHS APPROXIMATELY 25.4MM (1IN). BOTH CYLINDE RS ARE P0.015IN. 1 H 7 1 3O 3 O 3A21 E5CE 5 C P21EA 2001040500273 20010405 00273 SO 2001 4 5 AU010180 2 20010220 G 8520 CRANKCASE CESSNA 172 172B 2072406 CE CONT O300 O300C 17022 SO MCAULY 1C172 1C172EM GL ENGINE CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) ENGINE IN AN EXTREMELY POOR CONDITION. DEFECTS INCLUDE CRACKED CRANKCASE, WORN CRANKSHAFT, WORN GEARS, WORN CYLIND ERS AND VALVES. 1 H 7 1 3O 3 O NT 3A12 E253 5 N P910 2001040500274 20010405 00274 NE 2001 4 5 AU010181 3 20010227 G 6111 RFC11U16A BLADE EMB 120 EMB120 3260201 SO PWA 118 PW118A NE HAMSTD 14RF 14RF9 NE PROPELLER DAMAGED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) LT PROPELLER NR 1 BLADE DAMAGED BY FOD. LEADING EDGE SHEATH HAD APIECE MISSING APPROXIMATELY 10MM (0.393IN) IN DIA METER. THE LEFT FRONT PASSENGER WINDOW BEHIND THE GALLEY HAD A LARGE IMPACT MARK APPROXIMATELY 12MM (0.472IN) IN DIAMETE R. 2 L 7 2 4T 4 T RT A31SO E20NE 6 C P11NE 2001040500275 20010405 00275 EA 2001 4 5 AU010182 2 20010307 G 8520 68606 CRANKSHAFT FUJI FA200 FA200160 3730101 WP LYC O320 O320D2A 41508 EA MCAULY 1C172 1C172MGM GL ENGINE CORRODED W K NONE O OTHER IN INSP/MAINT 1 AU S L639239A (AUS) CRANKSHAFT INTERNAL BORE CORRODED. FOUND DURING INSPECTION IAWAD/LYC/102 AMDT2 PART 1 AND PART 2. 1 L 7 1 3O 3 O A4PC E274 5 N P910 2001040500276 20010405 00276 SW 2001 4 5 AU010183 1 20010307 G 6230 206040002109 MAST BELL 206 206B 1181511 SW ALLSN 250C 250C20B 03013 GL MAIN ROTOR DAMAGED W O OTHER E VIBRATION/BUFFET NR NOT REPORTED 1 AU S (AUS) MAIN ROTOR MAST SUBJECTED TO TORSIONAL DAMAGE DURING N2 LOCKUP ON START. 1 G 7 1 3U 3 U H2SW E4CE 2001040500277 20010405 00277 EA 2001 4 5 AU010184 2 20010307 G 8520 L639239A PUSHROD FUJI FA200 FA200160 3730101 WP LYC O320 O320D2A 41508 EA MCAULY 1C172 1C172MGM GL ENGINE MISINSTALLED W K NONE W INADEQUATE Q C IN INSP/MAINT 1 AU S L639239A (AUS) ENGINE PUSHRODS AND TAPPETS INCORRECTLY FITTED DURING ASSEMBLY FOLLOWING A BULK STRIP FOLLOWING A PROPELLER STRIKE . METAL CONTAMINATION OF ENGINE. 1 L 7 1 3O 3 O A4PC E274 5 N P910 2001040500278 20010405 00278 SO 2001 4 5 AU010185 1 20010308 G 8120 4091709001 TURBOCHARGER PIPER PA31 PA31350 7103110 SO LYC O540 TIO540J2BD 41532 EA HARTZL HCE3Y HCE3YR2 GL RT ENGINE FAULTY W O OTHER E K J VIBRATION/BUFFET FLUID LOSS WARNING INDICATION CR CRUISE 1 AU S 1 (AUS) RT ENGINE TURBOCHARGER FAULTY. LOSS OF ENGINE OIL (4LITRES). 1 L 7 2 3O 3 O A20SO E14EA 5 C P33EA 2001040500279 20010405 00279 NE 2001 4 5 AU010186 3 20010305 G 6111 RFC11MIRGADE BLADE EMB 120 EMB120 3260201 SO PWA 118 PW118A NE HAMSTD 14RF 14RF9 NE PROPELLER CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S 4860 (AUS) PROPELLER BLADE NICKEL SHEATH CRACKED. CRACK LENGTH APPROXIMATELY 50.8MM (2IN) LOCATED ON THE FACE APPROXIMATELY 5 0.8MM (2IN) FROMTHE BLADE HEATER. 2 L 7 2 4T 4 T RT A31SO E20NE 6 C P11NE 2001040500280 20010405 00280 EA 2001 4 5 AU010188 1 20010311 G 5610 NP1393225 WINDSHIELD CNDAIR CL600 CL6002B19 EA GE CF34 CF343B1 NE COCKPIT CRACKED W D RETURN TO BLOCK O OTHER TX TAXI/GRND HDL 1 AU S 9910H4795 (AUS) CAPTAINS SIDE WINDOW OUTER PANE SHATTERED. 2 L 7 2 4F 4 F RT A21EA E15NE 2001040500281 20010405 00281 CE 2001 4 5 AU010189 1 20010225 G 2750 WIRE CESSNA 404 404CESSNA 2075901 CE CONT O520 GTSIO520M 17032 SO MCAULY 3FF32 3FF32C501 GL TE FLAPS BROKEN W O OTHER F FLT CONT AFFECTED LD LANDING 1 AU S (AUS) FLAP PRESELECT MICROSWITCH WIRE BROKEN. 1 L 7 2 3O 3 O A25CE E7CE 5 C P45GL 2001040500282 20010405 00282 SO 2001 4 5 AU010190 1 20010312 G 5210 41420002 HINGE PIPER PA31 PA31350 7103110 SO LYC O540 TIO540J2BD 41532 EA HARTZL HCE3Y HCE3YR2 GL PAX DOOR CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) TOP CABIN DOOR FORWARD HINGE FAILED DUE TO CORROSION INDUCED CRACKING. 1 L 7 2 3O 3 O A20SO E14EA 5 C P33EA 2001040500283 20010405 00283 EA 2001 4 5 AU010191 2 20010110 G 7250 ENGINE EMB 110 EMB110P1 3260122 SO PWA PT6 PT6A34 52043 EA HARTZL HCB3T HCB3TN3 GL TURBINE SECTION DAMAGED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) ENGINE SKI JUMP SEVERELY CRACKED AND DISTORTED IN AREA AROUND NR 3 BEARING COVER. SOME PIECES OF THE EXHAUST CASIN G HAVE COMPLETELY BROKEN AWAY CAUSING DAMAGE TO THE POWER TURBINE DISC AND BLADES. POWER TURBINE STATOR CRACKED THROUGH THE INNER BAND. 1 L 7 2 4T 4 T A21SO E4EA 6 C P15EA 2001040500284 20010405 00284 2001 4 5 AU010192 4 20010312 G 3497 WIRE BAG BAE146 BAE146100A 1500260 EU LYC ALF502 ALF502R5 41580 NE NAVIGATION UNIT LOOSE W O OTHER J WARNING INDICATION CR CRUISE 1 AU S (AUS) NR 2 COMPASS SYSTEM FAULTY. INVESTIGATION FOUND A LOOSE WIRE TERMINAL AND NUT ON THE RT FLUX VALVE TERMINAL BLOCK LOCATED AT THE RH OUTER WING TRAILING EDGE. 2 H 7 4 4F 4 F RT A49EU E6NE 2001040500285 20010405 00285 SO 2001 4 5 AU010193 2 20010306 G 7314 PUMP BEECH 58 58 1152740 CE CONT O520 IO520C 17032 SO MCAULY 3AF34C 3AF34C502 GL ENGINE CONTAMINATED W O OTHER E VIBRATION/BUFFET CR CRUISE 1 AU S (AUS) RT ENGINE DRIVEN FUEL PUMP ADJUSTABLE ORIFICE CONTAMINATED WITH A SMALL PARTICLE. 1 L 7 2 3O 3 O 3A16 E5CE 5 C P22EA 2001040500286 20010405 00286 NE 2001 4 5 AU010194 2 20010310 G 7323 430121204 DRIVE SHAFT BOLKMS 117 BK117B1 5626012 EU LYC LTS101 LTS101750B1 41560 NE GOVERNOR SHEARED W O OTHER E VIBRATION/BUFFET CR CRUISE 1 AU S 2238 (AUS) NR 1 ENGINE POWER TURBINE GOVERNOR DRIVE COUPLING SHEARED. 1 G 7 2 3U 3 U H13EU E5NE10 2001040500287 20010405 00287 CE 2001 4 5 AU010195 1 20010314 G 2820 5892000017 LINE BEECH 58 58 1152740 CE CONT O520 IO520C 17032 SO MCAULY 3AF34C 3AF34C502 GL FUEL DIST LOOSE W O OTHER E Y J VIBRATION/BUFFET ENGINE STOPPAGE WARNING INDICATION LD LANDING 1 AU S 7522 (AUS) RT ENGINE MAIN FUEL LINE FLARE NUT DISCONNECTED ON AFT SIDE OFFIREWALL. PERSONNEL/MAINTENANCE ERROR. 1 L 7 2 3O 3 O 3A16 E5CE 5 C P22EA 2001040500288 20010405 00288 NE 2001 4 5 AU010196 2 20010312 G 7323 8210161E GOVERNOR PWA PW120A DHAV DHC8 DHC8102 2809003 NM PWA 120 PW120A NE HAMSTD 14SF 14SF7 NE NR 1 ENGINE FAULTY W C ABORTED TAKEOFF E R J VIBRATION/BUFFET PARTIAL RPM/PWR LOSS WARNING INDICATION TO TAKEOFF 1 AU S 2248689 (AUS) NR 1 ENGINE OVERSPEED GOVERNOR FAULTY. THE GOVERNOR WAS A NEWLY FITTED ITEM WITH NO HOURS SINCE OVERHAUL. 2 H 7 2 4T 4 T RT A13NM E20NE 6 C P7NE 2001040500289 20010405 00289 NM 2001 4 5 AU010197 1 20010226 G 4900 211734219 GCU BOEING 767 767338 1385151 NM GE CF6 CF680C2* GL APU FAILED W K NONE O OTHER IN INSP/MAINT 1 AU S 18690 (AUS) APU GENERATOR CONTROL UNIT (GCU) FAULTY. INVESTIGATION FOUND THETOP COVER COOLING HOLES BLOCKED WITH DUST. 2 L 7 2 4F 4 F RT A1NM E23EA 2001040500290 20010405 00290 NM 2001 4 5 AU010198 1 20010222 G 2840 BACJ40A204 JUMPER BOEING 747 747438 NM RROYCE RB211 RB211524G19 NE FUEL WIRING MISSING W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) FUEL CROSSFEED MANIFOLDS IN CENTER WING TANK HAD MISSING BONDINGJUMPERS. 2 L 7 4 4F 4 F RT A20WE E30NE 2001040500291 20010405 00291 NM 2001 4 5 AU010199 1 20010227 G 2910 65C268393061 LINE BOEING 737 737376 NM CFMINT CFM56 CFM563C 13802 EU HYDRAULIC SYSTEM LEAKING W K NONE K FLUID LOSS IN INSP/MAINT 1 AU S (AUS) HYDRAULIC B SYSTEM RESERVOIR TO STANDBY SYSTEM SUPPLY LINE LEAKING. LOSS OF HYDRAULIC FLUID. 2 L 7 2 4F 4 F RT A16WE E21EU 2001040500292 20010405 00292 NM 2001 4 5 AU010200 1 20010223 G 2782 1267625 ACTUATOR BOEING 747 747438 NM RROYCE RB211 RB211524G19 NE SLATS JAMMED W A UNSCHED LANDING F FLT CONT AFFECTED CL CLIMB 1 AU S 41940 (AUS) RH OUTBOARD LEADING EDGE FLAP DRIVE ACTUATOR JAMMED. 2 L 7 4 4F 4 F RT A20WE E30NE 2001040500293 20010405 00293 NM 2001 4 5 AU010201 1 20010224 G 2530 GENM2585013 OVEN BOEING 737 737476 NM CFMINT CFM56 CFM563C 13802 EU GALLEY BURNED W D RETURN TO BLOCK B SMOKE/FUMES/ODORS/SPARKS TX TAXI/GRND HDL 1 AU S 221 (AUS) REAR GALLEY OVEN FAN MOTOR BURNT. 2 L 7 2 4F 4 F RT A16WE E21EU 2001040500294 20010405 00294 NM 2001 4 5 AU010202 1 20010223 G 3250 NUT BOEING 747 747238B 1384828 NM RROYCE RB211 RB211524D419 54555 NE NLG STEERING UNLOCKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) LT AND RT NOSE GEAR STEERING CABLES DID NOT HAVE SPLIT PINS FITTED THROUGH CASTELLATED NUTS. BOTH NUTS WERE ONLY F INGER TIGHT AND THE LT NUT WAS HELD BY ONLY TWO THREADS.PERSONNEL/MAINTENANCE ERROR. 2 L 7 4 4F 4 F A20WE E12EU 2001040500295 20010405 00295 NM 2001 4 5 AU010203 1 20010220 G 3320 LIGHT BOEING 747 747438 NM RROYCE RB211 RB211524G19 NE CABIN CONTAMINATED W O OTHER B SMOKE/FUMES/ODORS/SPARKS DE DESCENT 1 AU S (AUS) CROSSOVER CEILING LIGHT LOCATED AT DOOR NR 5 RT HAD SEVERAL PIECES OF TISSUE STUFFED INTO THE LIGHT. THE TISSUE HA D BEGUN TO SMOULDER. THE CROSSOVER LIGHT LENS AND ASSOCIATED METAL GRILL ASSEMBLY WAS MISSING. 2 L 7 4 4F 4 F RT A20WE E30NE 2001040500296 20010405 00296 2001 4 5 AU010204 4 20010220 G 2565 7A146913 RESERVOIR BOEING 747 747438 NM RROYCE RB211 RB211524G19 NE ESCAPE SLIDE DISCHARGED W K NONE O OTHER IN INSP/MAINT 1 AU S 5336 GJ1033 (AUS) NO5 LH MAIN ENTRY DOOR EMERGENCY ESCAPE SLIDE INFLATION RESERVOIR PRESSURE BELOW LIMITS. 2 L 7 4 4F 4 F RT A20WE E30NE 2001040500297 20010405 00297 NM 2001 4 5 AU010205 1 20010217 G 3320 SOCKET BOEING 747 747338 NM RROYCE RB211 RB211524D419 54555 NE LIGHT BURNED W O OTHER B SMOKE/FUMES/ODORS/SPARKS CL CLIMB 1 AU S (AUS) SIDEWALL WASH LIGHT SOCKET LOCATED AT SEAT 25 HJK BURNED OUT AND ARCING DUE TO WATER CONTAMINATION. AREA AROUND SE ATS FOUND TO BE SOAKING WET DUE TO BLOCKAGE OF RT SIDE UPPER DECK DOOR DRAINBLOCKAGE ALLOWING WATER LEAKAGE. AIRCRAFT HA D BEEN ON THE GROUNDDURING A SEVERE RAIN STORM. 2 L 7 2 4F 4 F RT A20WE E12EU 2001040500298 20010405 00298 NM 2001 4 5 AU010206 1 20010219 G 2823 737M28500011 SHUTOFF VALVE 737M2850001X BOEING 737 737476 NM CFMINT CFM56 CFM563C 13802 EU FUEL SELECTOR FAILED W O OTHER R J PARTIAL RPM/PWR LOSS WARNING INDICATION NR NOT REPORTED 1 AU S (AUS) NR 2 ENGINE FUEL SHUTOFF VALVE FAILED. 2 L 7 2 4F 4 F RT A16WE E21EU 2001040500299 20010405 00299 NM 2001 4 5 AU010207 1 20010207 G 3244 B2700 TIRE BOEING 747 747238B 1384828 NM LT MLG SEPARATED W O OTHER D INFLIGHT SEPARATION NR NOT REPORTED 1 AU S 2096 (AUS) LT BODY MAIN LANDING GEAR FRONT INBOARD WHEEL TIRE (4F) HAD TREAD MISSING. 2 L 7 4 4F A20WE 2001040500300 20010405 00300 NM 2001 4 5 AU010208 1 20010309 G 2910 AS11506K0264 HOSE BOEING 767 767338 1385151 NM GE CF6 CF680C2* GL HYDRAULIC SYSTEM FAILED W K NONE K FLUID LOSS IN INSP/MAINT 1 AU S (AUS) NR 4 BRAKE HYDRAULIC HOSE FAILED. 2 L 7 2 4F 4 F RT A1NM E23EA 2001040500301 20010405 00301 NM 2001 4 5 AU010209 1 20010305 G 2610 CONNECTOR BOEING 747 747238B 1384828 NM DETECTION SYSTEM LOOSE W K NONE P NO WARNING INDICATION IN INSP/MAINT 1 AU S (AUS) FIRE WARNING SYSTEM CARD A8 NOT SEATING CORRECTLY DUE TO REAR CONNECTOR ADRIFT FROM HOUSING. 2 L 7 4 4F A20WE 2001040500302 20010405 00302 2001 4 5 AU010210 4 20010306 G 2565 D31591475 SLIDE BOEING 737 737476 NM CFMINT CFM56 CFM563C 13802 EU PAX DOOR FAILED W K NONE L NO TEST IN INSP/MAINT 1 AU S 5661 (AUS) NR 1 RT MAIN ENTRY DOOR ESCAPE SLIDE FAILED TO FULLY DEPLOY. INVESTIGATION FOUND THAT THE SLIDE EXHAUST VALVE WAS STUCK OPEN AND THE VALVE ELEMENT HAD BROKEN AWAY FROM THE VALVE BODY. 2 L 7 2 4F 4 F RT A16WE E21EU 2001040500303 20010405 00303 NM 2001 4 5 AU010211 1 20010304 G 2610 WARNING HORN BOEING 767 767338 1385151 NM GE CF6 CF680C2* GL DETECTION SYSTEM INOPERATIVE W K NONE L NO TEST IN INSP/MAINT 1 AU S (AUS) FIRE TEST WARNING BELL INOPERATIVE. 2 L 7 2 4F 4 F RT A1NM E23EA 2001040500304 20010405 00304 EU 2001 4 5 AU010213 1 20010320 G 7712 SELOC29EC INDICATOR FOKKER F27 F27MK50 EU PWA PWA120 PW125B NE ENGINE TORQUE MALFUNCTIONED W C ABORTED TAKEOFF J WARNING INDICATION TO TAKEOFF 1 AU S 3921 (AUS) LT ENGINE TORQUE INDICATOR SUSPECT FAULTY. 2 H 7 2 4T 4 T RT A817 E20NE 2001040500305 20010405 00305 2001 4 5 AU010214 4 20010223 G 6113 C19042 SPINNER GROB G115 G115 EU LYC O360 O360A1F6 41514 EA HARTZL HCF2Y HCF2YR1 GL PROPELLER DEBONDED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) PROPELLER SPINNERS (7OFF) FOUND TO HAVE DISBONDED OR POOR BONDING BETWEEN THE INTERNAL FORWARD SUPPORT BULKHEAD AN D THE SPINNER WALL. THE SPINNERS WERE NEW ASSEMBLIES BEING INSPECTED ON RECEIPT FROM THE MANUFACTURER. 1 L 7 1 3O 3 O NT A57EU E286 5 C P27EA 2001040500306 20010405 00306 NE 2001 4 5 AU010215 2 20010316 G 8530 114650 CYLINDER DOUG DC3 DC3CS1C3G 3021458 WP PWA R1830 R183092 52020 NE HAMSTD 23E 23E50 NE ENGINE SEPARATED W O OTHER E Y J VIBRATION/BUFFET ENGINE STOPPAGE WARNING INDICATION CR CRUISE 1 AU S 381 (AUS) RT ENGINE NNR 1 CYLINDER UPPER BARREL AND HEAD SEPARATED. DAMAGE TO PISTON, RINGS, BARREL, INDUCTION TUBE AND PUSH ROD TUBE. OIL FILTER METAL CONTAMINATION. 2 L 7 2 4R 4 R A669 5E4 6 C P603 2001040500307 20010405 00307 EU 2001 4 5 AU010216 1 20010312 G 7921 PLUG GARRTT 7997 BAG JETSTM JETSTM3201 1500217 EU GARRTT TPE331 TPE33112UHR WP ROTOL R333 R333482F12 GL DOOR ACTUATOR CONTAMINATED W C ABORTED TAKEOFF E N VIBRATION/BUFFET FALSE WARNING TO TAKEOFF 1 AU S 7921 (AUS) LT ENGINE OIL COOLER DOOR ACTUATOR PLUG CONTAMINATED. 2 L 7 2 4T 4 T RT A56EU E4WE 6 C P61GL 2001040500308 20010405 00308 CE 2001 4 5 AU010217 1 20010313 G 3233 12810013 ACTUATOR CESSNA 172 172RG 2072438 CE LYC O360 O360F1A6 41514 EA MCAULY 2D34C B2D34C220 GL MLG CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S 6006 (AUS) RT MAIN LANDING GEAR ACTUATOR BODY CRACKED. FOUND FOLLOWING INSPECTION IAW SEB01-2. 1 H 7 1 3O 3 O 3A17 E286 5 C P7EA 2001040500309 20010405 00309 NE 2001 4 5 AU010218 2 20010307 G 7321 CONNECTOR PWA 7397 EMB 120 EMB120 3260201 SO PWA 118 PW118A NE HAMSTD 14SF 14SF9 NE EEC CONTAMINATED W C ABORTED TAKEOFF E J VIBRATION/BUFFET WARNING INDICATION TO TAKEOFF 1 AU S (AUS) LT ENGINE TORQUE SIGNAL CONDITIONER AND ENGINE ELECTRONIC CONTROL (EEC) ELECTRICAL CONNECTORS CONTAMINATED WITH OI L. 2 L 7 2 4T 4 T RT A31SO E20NE 6 N P11NE 2001040500310 20010405 00310 GL 2001 4 5 AU010219 3 20010306 G 6111 A22173QTY2 BLOCK HARTZL HCM2YR1BF BEECH 23 C24R 1151254 CE LYC O360 IO360A1B6 41514 EA HARTZL HCM2Y HCM2YR GL PROPELLER BLADE CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S 1240 EN273 (AUS) PROPELLER PITCH CHANGE BLOCKS CRACKED. PITCH CONTROL FORK WORNEXCESSIVELY. HUB PRELOAD PLATE DAMAGED DUE TO PREVIO US FOREIGN OBJECT STRIKE. 1 L 7 1 3O 3 O A1CE 1E10 5 C P43GL 2001040500311 20010405 00311 SO 2001 4 5 AU010220 2 20010223 G 8520 629680 COLLAR CESSNA 310 310R 2074245 CE CONT O520 IO520M 17032 SO ENGINE MISMANUFACTURED W O OTHER K J FLUID LOSS WARNING INDICATION LD LANDING 1 AU S (AUS) LT ENGINE CRANKSHAFT OIL TRANSFER COLLAR HAD INCORRECT CLEARANCE. THE MEASURED CLEARANCE WAS 0.0254MM (0.001IN) WI TH THE CORRECTMANUFACTURERS LIMITS BEING 0.127MM TO 0.4572MM (0.005IN TO0.0018IN). 1 L 7 2 3O 3 O 3A10 E5CE 2001040500312 20010405 00312 CE 2001 4 5 AU010221 1 20010225 G 3260 ICH16 DOWNLOCK SWITCH CESSNA 404 404CESSNA 2075901 CE CONT O520 GTSIO520M 17032 SO MCAULY 3FF32 3FF32C501 GL MLG FAULTY W O OTHER P NO WARNING INDICATION DE DESCENT 1 AU S (AUS) LT MAIN LANDING GEAR DOWNLOCK MICROSWITCH WIRE BROKEN. 1 L 7 2 3O 3 O A25CE E7CE 5 C P45GL 2001040500313 20010405 00313 EU 2001 4 5 AU010222 1 20010112 G 5330 11207 PLATE FOKKER F28 F28MK4000 4990810 EU RROYCE SPEY SPEY55515 54521 EU FUSELAGE CORRODED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) LOWER LT FUSELAGE PANEL 95B REBATE PLATE CONTAINED SEVERE EXFOLIATION CORROSION (LEVEL2). 2 L 7 2 4F 4 F RT A20EU E2EU 2001040500314 20010405 00314 2001 4 5 AU010223 4 20010304 G 6122 PCE21275 GOVERNOR PWA PT6A20 PILATS PC6 PC6 7090102 EU PWA PT6 PT6A20 52043 EA HARTZL HCB3T HCB3TN3 GL PROPELLER FAILED W D RETURN TO BLOCK J WARNING INDICATION TX TAXI/GRND HDL 1 AU S PCE21275 (AUS) PROPELLER REVERSE GOVERNOR IDLER GEAR BEARING COLLAPSED. METALCONTAMINATION OF ENGINE. 1 H 7 1 3O 3 T 7A15 E4EA 6 C P15EA 2001040500315 20010405 00315 EA 2001 4 5 AU010224 2 20010202 G 7261 RELIEF VALVE EMB 110 EMB110P1 3260122 SO PWA PT6 PT6A34 52043 EA HARTZL HCB3T HCB3TN3 GL ENGINE CONTAMINATED W C ABORTED TAKEOFF E R J VIBRATION/BUFFET PARTIAL RPM/PWR LOSS WARNING INDICATION TO TAKEOFF 1 AU S (AUS) RT ENGINE OIL PRESSURE RELIEF VALVE CONTAMINATED BY A PIECE OF O-RING SEAL. 1 L 7 2 4T 4 T A21SO E4EA 6 C P15EA 2001040500316 20010405 00316 EU 2001 4 5 AU010226 2 20010113 G 7250 2425 STATOR SNIAS AS332 AS332L 8680809 EU TMECA MAKILA MAKILA1A 60040 EU TURBINE SECTION CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) ENGINE FIRST STAGE TURBINE NOZZLE GUIDE VANE INNER RING CRACKED.CRACK RAN FOR APPROXIMATELY 270 DEGREES OF CIRCUMF ERENCE. 2 G 7 2 4U 4 U H4EU E12NE 2001040500317 20010405 00317 CE 2001 4 5 AU010227 1 20010312 G 5321 SCREW BEECH 58 58 1152740 CE CONT O520 IO520C 17032 SO MCAULY 3AF32C 3AF32C512 GL FLOOR PANEL UNAPPROVED PART W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) INCORRECT LENGTH SCREW FITTED TO PILOTS FLOOR PANEL. LONG SCREW CUT A GROOVE IN PIPE. 1 L 7 2 3O 3 O 3A16 E5CE 5 C P22EA 2001040500318 20010405 00318 EA 2001 4 5 AU010228 2 20010313 G 7314 AN9296J CAP LYC O360A1F6 GROB G115 G115 EU LYC O360 O360A1F6 41514 EA ENGINE FUEL PUMP CONTAMINATED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) ELECTRIC FUEL PUMP OUTLET T FITTING BLANKING CAP CONTAMINATED WITH SWARF. THE BLANKING CAPS ARE FITTED DURING MODI FICATION IAW EO E121-01 REV1. 1 L 7 1 3O 3 O NT A57EU E286 2001040500319 20010405 00319 CE 2001 4 5 AU010229 1 20010320 G 3211 10581002376 FRAME BEECH 76 76 1153005 CE FUSELAGE CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) LH AND RH MAIN LANDING GEAR A FRAMES CRACKED. 1 L 7 2 3O A29CE 2001040500320 20010405 00320 WP 2001 4 5 AU010230 1 20010315 G 6420 C1281 HUB ROBSIN R44 R44 7640120 WP LYC O540 O540F1B5 41532 EA TAIL ROTOR CORRODED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) TAIL ROTOR HUB CONTAINED STRESS CORROSION AND CRACKING FROM THE TEETER BEARING RACES. 1 G 7 1 3O 3 O H11NM E295 2001040500321 20010405 00321 CE 2001 4 5 AU010232 1 20010320 G 3211 10581002375 FRAME BEECH 76 76 1153005 CE FUSELAGE CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) LT AND RT MAIN LANDING GEAR A-FRAMES CRACKED. 1 L 7 2 3O A29CE 2001040500322 20010405 00322 CE 2001 4 5 AU010233 1 20010319 G 7810 EXHAUST PIPE BEECH 200 200BEECH 1152920 CE PWA PT6 PT6A42 52043 NE HARTZL HCD4N3 HCD4N3A GL ENGINE FAILED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) ENGINE EXHAUST DUCT FAILED IN AREA AROUND NR 3 BEARING COVER SUPPORT. 1 L 7 2 4T 4 T A24CE E4EA 5 C STC 2001040500323 20010405 00323 CE 2001 4 5 AU010234 1 20010320 G 3211 10581002376 FRAME BEECH 76 76 1153005 CE FUSELAGE CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) RT MAIN LANDING GEAR A-FRAME CRACKED. 1 L 7 2 3O A29CE 2001040500324 20010405 00324 NM 2001 4 5 AU010235 1 20010316 G 2752 734374D ACTUATOR DHAV DHC8 DHC8* NM TE FLAPS LACK OF LUBE W O OTHER F FLT CONT AFFECTED NR NOT REPORTED 1 AU S (AUS) RH FLAP INBOARD ACTUATOR BALLSCREW NUT BADLY WORN. INVESTIGATION FOUND MISSING BALLS IN JACKSCREW AND SEVERE DAMAG E TO THE FORCE LIMITER. SUSPECT CAUSED BY LACK OF LUBRICATION. 2 H 7 2 4T RT A13NM 2001040500325 20010405 00325 EU 2001 4 5 AU010237 1 20010303 G 2432 BATTERY FOKKER F28 F28MK4000 4990810 EU RROYCE SPEY SPEY55515 54521 EU E/E BAY OVERHEATED W O OTHER M J OVER TEMP WARNING INDICATION NR NOT REPORTED 1 AU S (AUS) AFT BATTERY OVERHEATED. 2 L 7 2 4F 4 F RT A20EU E2EU 2001040500326 20010405 00326 EU 2001 4 5 AU010238 1 20010223 G 2910 PIPE FOKKER F28 F28MK1000 4990808 EU RROYCE SPEY SPEY55515 54521 EU HYDRAULIC SYSTEM CHAFED W O OTHER N FALSE WARNING CL CLIMB 1 AU S (AUS) HYDRAULIC PIPES LOCATED IN LT WHEEL WELL RUBBING ON LANDING GEARDOOR PREVENTING REAR UPLOCK SWITCH FROM ACTIVATING . 2 L 7 2 4F 4 F RT A20EU E2EU 2001040500327 20010405 00327 EU 2001 4 5 AU010239 1 20010222 G 2910 HYDRAULIC SYSTEM FOKKER F28 F28MK1000 4990808 EU RROYCE SPEY SPEY55515 54521 EU NR 2 LOW W K NONE K J FLUID LOSS WARNING INDICATION IN INSP/MAINT 1 AU S (AUS) NR 2 HYDRAULIC SYSTEM LOW QUANTITY. INVESTIGATION COULD FIND NOEVIDENCE OF LEAKS. SUSPECT SYSTEM NOT REPLENISHED. 2 L 7 2 4F 4 F RT A20EU E2EU 2001040500328 20010405 00328 EU 2001 4 5 AU010240 1 20010119 G 2612 FIRE LOOP AIRBUS 310 A310324 3930206 EU PWA 4152 PW4152 NE LT ENGINE FAULTY W D RETURN TO BLOCK N FALSE WARNING TX TAXI/GRND HDL 1 AU S (AUS) LT ENGINE FIRE LOOP A FAULTY. 2 L 7 2 4F RT A35EU E24NE 2001040500329 20010405 00329 EU 2001 4 5 AU010241 1 20010206 G 2131 CONTROLLER FOKKER F28 F28MK4000 4990810 EU RROYCE SPEY SPEY55515 54521 EU CABIN PRESSURE FAULTY W O OTHER J WARNING INDICATION CL CLIMB 1 AU S (AUS) CABIN PRESSURISATION SYSTEM FAULTY. 2 L 7 2 4F 4 F RT A20EU E2EU 2001040500330 20010405 00330 EU 2001 4 5 AU010242 1 20010306 G 2913 PUMP FOKKER F28 F28MK1000 4990808 EU RROYCE SPEY SPEY55515 54521 EU HYDRAULIC SYS LEAKING W C ABORTED TAKEOFF K J FLUID LOSS WARNING INDICATION TO TAKEOFF 1 AU S (AUS) NR 2 HYDRAULIC SYSTEM ENGINE DRIVEN PUMP SILENCER LEAKING INTERNALLY. 2 L 7 2 4F 4 F RT A20EU E2EU 2001040500331 20010405 00331 EU 2001 4 5 AU010243 1 20010226 G 5610 WINDOW FOKKER F28 F28MK1000 4990808 EU RROYCE SPEY SPEY55515 54521 EU COCKPIT STUCK W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) CAPTAINS SLIDING WINDOW STUCK OPEN. INVESTIGATION FOUND WORN TRACK AND UPPER ROLLER. 2 L 7 2 4F 4 F RT A20EU E2EU 2001040900389 20010409 00389 SO 2001 4 9 AU010245 2 20010216 G 8530 682995 CYLINDER BEECH 36 A36 1151604 CE CONT O550 IO550B SO ENGINE CORRODED W K NONE O OTHER IN INSP/MAINT 1 AU S 243 (AUS) ENGINE CYLINDERS PNO 649358, LIFTERS PNO 646277 AND CAMSHAFT PNO649322A1 CONTAINED PITTING CORROSION. ENGINE HAS O NLY 242.6 HOURS TOTAL TIME SINCE NEW. 1 L 7 1 3O 3 O 3A15 E3SO 2001040900390 20010409 00390 SO 2001 4 9 AU010246 2 20010301 G 8520 CONNECTING ROD CESSNA 402 402CESSNA 207590K CE CONT O520 TSIO520VB 17040 SO MCAULY 3AF32C 3AF32C505 GL ENGINE SEPARATED W O OTHER E VIBRATION/BUFFET CR CRUISE 1 AU S 85 (AUS) RT ENGINE NR 2 AND NR 4 CONNECTING ROD BIG ENDS FAILED. CRANKCASE HOLES AND MAGNETOS SEPARATED. 1 L 7 2 3O 3 O A7CE E8CE 5 C P22EA 2001040900391 20010409 00391 CE 2001 4 9 AU010247 1 20010115 G 8120 C1650040604 SEAL CONT TSIO520VB CESSNA 402 402C 207590R CE CONT O520 TSIO520VB 17040 SO TURBOCHARGER LEAKING W K NONE O OTHER IN INSP/MAINT 1 AU S 183 (AUS) LT ENGINE VAPC LEAKING OIL PAST PISTON DUE TO INTERNAL SEAL FAILURE. 1 L 7 2 3O 3 O A7CE E8CE 2001040900392 20010409 00392 SW 2001 4 9 AU010248 1 20010321 G 5540 304566 STRUCTURE AIRTRC AT802 AT802A SW PWA PT6 PT6A65AG 52043 NE HARTZL HCB5M HCB5MP3 GL RUDDER DAMAGED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) RUDDER CRACKED AND SKIN DEFORMED IN UPPER AREA WHERE THE BALANCEHORN ATTACHES TO THE RUDDER STRUCTURE. 1 L 7 1 3T 4 T NC A19SW E4EA 6 C P44GL 2001040900393 20010409 00393 SW 2001 4 9 AU010249 1 20010319 G 7120 9388013 MOUNT AIRTRC AT802 AT802A SW PWA PT6 PT6A65AG 52043 NE HARTZL HCB5M HCB5MP3 GL ENGINE FAILED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) LT SIDE ENGINE MOUNT RUBBER ISOLATION MOUNTS FAILED. ENGINE LOW ON LT SIDE CAUSING CHAFING OF THE FIRE SEALS ON TH E BEARER. 1 L 7 1 3T 4 T NC A19SW E4EA 6 C P44GL 2001040900394 20010409 00394 EA 2001 4 9 AU010250 2 20010323 G 8530 G4299 COLLET LYC BEECH 65 A658200 1152805 CE LYC O480 GSO480B1A6 41529 EA HARTZL HCB3Z HCB3Z202 GL LT ENGINE FAILED W O OTHER E VIBRATION/BUFFET DE DESCENT 1 AU S 20 (AUS) LT ENGINE NR 6 CYLINDER VALVE COLLETS FAILED. INLET VALVE DROPPED. METAL CONTAMINATION OF OIL SYSTEM. OTHER COLLET S INSPECTED HADSIGNS OF ABNORMAL WEAR. SUSPECT UNAPPROVED PARTS. 1 L 7 2 3O 3 O 3A20 E284 5 C P907 2001040500332 20010405 00332 CE 2001 4 5 AU010251 1 20010322 G 2701 05600144 CONTROL COLUMN CESSNA 172 172N 2072434 CE LYC O320 O320H2AD 41508 EA MCAULY 1C160 1C160DTM GL COCKPIT CONTAMINATED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) CONTROL YOKE CONTAMINATED INTERNALLY WITH WATER. FOUND DURING INSPECTION IAW CESSNA SEB 01-3 1 H 7 1 3O 3 O NT 3A12 E274 5 N P910 2001040500333 20010405 00333 EA 2001 4 5 AU010252 2 20010312 G 7414 PIN BNORM BN2 BN2A21 1520221 EU LYC O540 IO540K1B5 41532 EA HARTZL HCC2Y HCC2YR2 GL IMPULSE COUPLING FAILED W O OTHER E K J VIBRATION/BUFFET FLUID LOSS WARNING INDICATION LD LANDING 1 AU S (AUS) RT ENGINE MAGNETO IMPULSE COUPLING PIN MIGRATED OUT, ALLOWING THE FLANGE SECURING PIN AND FLANGE TO FAIL. LOSS OF ENGINE OIL. 1 H 7 2 3O 3 O A17EU 1E4 5 C P920 2001040500334 20010405 00334 2001 4 5 AU010253 4 20010319 G 3416 28702501 ALTIMETER BEECH 1900 1900C 1154161 CE PWA PT6 PT6A65B 52043 EA COCKPIT FAILED W O OTHER O OTHER CL CLIMB 1 AU S (AUS) ALTIMETER INTERNAL FAILURE. 2 L 7 2 4T 4 T RT A24CE E4EA 2001040500335 20010405 00335 NE 2001 4 5 AU010254 2 20010326 G 7321 6068T72P09 HMU SAAB SF340 340B 7860101 EU GE CT7TP CT79B 30030 NE ROTOL R375 R3754123F21 NE FUEL CONTROL FAULTY W O OTHER E R J VIBRATION/BUFFET PARTIAL RPM/PWR LOSS WARNING INDICATION CL CLIMB 1 AU S (AUS) RT ENGINE HYDROMECHANICAL UNIT (HMU) FAULTY. 2 L 7 2 4T 4 T RT A52EU E8NE 6 C P17NE 2001040500336 20010405 00336 EA 2001 4 5 AU010255 2 20010313 G 7414 4370 MAGNETO PIPER PA28 PA28181 7102807 SO LYC O360 O360A4M 41514 EA RIGHT FAILED W O OTHER E R J VIBRATION/BUFFET PARTIAL RPM/PWR LOSS WARNING INDICATION NR NOT REPORTED 1 AU S (AUS) RT MAGNETO FAILED. 1 L 7 1 3O 3 O 2A13 E286 2001040500337 20010405 00337 CE 2001 4 5 AU010256 1 20010313 G 5512 SKIN CESSNA 210 210N 2073453 CE CONT O520 IO520L 17032 SO MCAULY D3A34 D3A34C404 GL HORIZONTAL STAB CHAFED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) LT AND RT HORIZONTAL STABILIZER LOWER SKINS CHAFED BY THE GAP SEAL STRIP / ANGLE AT THE FUSELAGE TO STABILISER JUN CTION.REDUCTION IN SKIN THICKNESS FROM 0.635MM (0.025IN) TO 0.33MM(0.013IN). 1 H 7 1 3O 3 O 3A21 E5CE 5 C P47GL 2001040500338 20010405 00338 EU 2001 4 5 AU010257 1 20010213 G 5711 SPAR BAG BAE146 BAE146100A 1500260 EU LYC ALF502 ALF502R5 41580 NE LT & RT WING CORRODED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) LT AND RT WING FORWARD AND AFT SPAR LOWER FLANGES CORRODED. 2 H 7 4 4F 4 F RT A49EU E6NE 2001040500339 20010405 00339 EU 2001 4 5 AU010258 1 20010212 G 5711 SPAR BAG BAE146 BAE146100A 1500260 EU LYC ALF502 ALF502R3A 41580 NE LT & RT WING CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) LT AND RT WING FORWARD AND AFT LOWER SPAR CAPS CRACKED IN AREABETWEEN RIBS NR 13 AND NR 18. CORROSION ALSO FOUND O N LOWER SKINS AT RIB BAYS NR 13 TO NR 18. 2 H 7 4 4F 4 F RT A49EU E6NE 2001040500340 20010405 00340 EU 2001 4 5 AU010259 1 20010212 G 5730 SKIN BAG BAE146 BAE146100A 1500260 EU LYC ALF502 ALF502R5 41580 NE LT WING CORRODED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) LT WING LOWER SKIN CORRODED AT RIB BAYS NR 14 TO NR 16. RT WING LOWER SKIN CORRODED AT RIB BAYS NR 14 AND NR 15. 2 H 7 4 4F 4 F RT A49EU E6NE 2001040500341 20010405 00341 NM 2001 4 5 AU010260 1 20010318 G 2897 W60000818R WIRE BOEING 747 747438 NM RROYCE RB211 RB211524G19 NE FUEL SYSTEM SHORTED W O OTHER N FALSE WARNING CL CLIMB 1 AU S (AUS) FUEL SYSTEM CONTROL VALVE WIRE PNO W6400-008-18R LOCATED IN NR 4 STRUT KNEE CAP DISCONNECT PLUG D14300P CHAFED AND SHORT CIRCUITING TO GROUND. 2 L 7 4 4F 4 F RT A20WE E30NE 2001040500342 20010405 00342 NM 2001 4 5 AU010261 1 20010309 G 3242 26088127 BRAKE BOEING 767 767338 1385151 NM GE CF6 CF680C2* GL RT MLG DELAMINATED W K NONE O OTHER IN INSP/MAINT 1 AU S 15104 (AUS) RT MAIN LANDING GEAR NR 7 BRAKE STATORS DELAMINATED. 2 L 7 2 4F 4 F RT A1NM E23EA 2001040500343 20010405 00343 NM 2001 4 5 AU010262 1 20010318 G 3242 26088127 BRAKE BOEING 767 767338 1385151 NM GE CF6 CF680C2* GL LT MLG FAILED W K NONE O OTHER IN INSP/MAINT 1 AU S 13318 (AUS) LT NR 4 MAIN WHEEL BRAKE ASSEMBLY ROTORS DISINTEGRATED. 2 L 7 2 4F 4 F RT A1NM E23EA 2001040500344 20010405 00344 EU 2001 4 5 AU010263 1 20010325 G 2160 7828602 CONTROL VALVE SAAB SF340 340B 7860101 EU GE CT7TP CT79B 30030 NE ROTOL R375 R3754123F21 NE CABIN TEMP SEIZED W C ABORTED TAKEOFF B J SMOKE/FUMES/ODORS/SPARKS WARNING INDICATION TO TAKEOFF 1 AU S 16660 (AUS) DUAL TEMPERATURE CONTROL VALVE SEIZED IN OPEN POSITION. 2 L 7 2 4T 4 T RT A52EU E8NE 6 C P17NE 2001040500345 20010405 00345 NE 2001 4 5 AU010264 2 20010323 G 7321 6078T55P18 FUEL CONTROL GE CNDAIR CL600 CL6002B19 EA GE CF34 CF343B1 NE RT ENGINE LEAKING W K NONE K FLUID LOSS IN INSP/MAINT 1 AU S (AUS) RT ENGINE FUEL CONTROL UNIT LEAKING FROM THE AREA OF THE THROTTLE CONTROL INPUT ARM. 2 L 7 2 4F 4 F RT A21EA E15NE 2001040500346 20010405 00346 GL 2001 4 5 AU010265 3 20010325 G 6111 660715698 EROSION SHIELD ROTOL 6607152727 FOKKER F27 F27MK50 EU PWA PWA120 PW125B NE ROTOL R352 R3526123F1 GL PROPELLER BLADE SEPARATED W O OTHER D INFLIGHT SEPARATION CL CLIMB 1 AU S 1779 F50470 (AUS) PROPELLER BLADE EROSION SHIELD SEPARATED. 2 H 7 2 4T 4 T RT A817 E20NE 6 C P16NG 2001040500347 20010405 00347 EU 2001 4 5 AU010266 2 20010324 G 7321 B12597 AMPLIFIER FOKKER F28 F28MK1000 4990808 EU RROYCE SPEY SPEY55515 54521 EU FUEL CONTROL FAULTY W C ABORTED TAKEOFF E J VIBRATION/BUFFET WARNING INDICATION TO TAKEOFF 1 AU S 7419 (AUS) NR 1 ENGINE POWER FLUCTUATIONS. ENGINE CONTROL AMPLIFIER AND TEMPERATURE CONTROL ACTUATOR CHANGED. 2 L 7 2 4F 4 F RT A20EU E2EU 2001040500348 20010405 00348 EU 2001 4 5 AU010267 1 20010324 G 2913 COUPLING FOKKER F28 F28MK4000 4990810 EU RROYCE SPEY SPEY55515 54521 EU HYDRAULIC PUMP CRACKED W K NONE K FLUID LOSS IN INSP/MAINT 1 AU S (AUS) NR 1 HYDRAULIC SYSTEM HYDRAULIC PUMP PRESSURE LINE ELBOW COUPLING THREADED SECTION CRACKED AND LEAKING. LOSS OF HY DRAULIC FLUID. 2 L 7 2 4F 4 F RT A20EU E2EU 2001040500349 20010405 00349 SW 2001 4 5 AU010268 1 20010320 G 6210 206015001117AS BLADE BELL 206 206L 1181522 SW ALLSN 250C 250C30 03013 GL MAIN ROTOR CORRODED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) MAIN ROTOR BLADE CORRODED IN AREA BETWEEN PAINT AND LEADING EDGESTRIP ON UNDERSIDE OF BLADE. CORROSION DEPTH APPRO XIMATELY 1.52MM (0.060IN). FOUND BEFORE FITMENT. 1 G 7 1 3U 3 U H2SW E1GL 2001040500350 20010405 00350 EU 2001 4 5 AU010269 1 20010309 G 5270 WARNING SYSTEM FOKKER F28 F28MK4000 4990810 EU RROYCE SPEY SPEY55515 54521 EU PAX DOOR INTERMITTENT W O OTHER N FALSE WARNING NR NOT REPORTED 1 AU S (AUS) PASSENGER DOOR WARNING LIGHT INTERMITTENT IN OPERATION. INVESTIGATION COULD FIND NO FAULT. 2 L 7 2 4F 4 F RT A20EU E2EU 2001040500351 20010405 00351 2001 4 5 AU010270 4 20010310 G 3442 20412170413 RADAR FOKKER F28 F28MK1000 4990808 EU RROYCE SPEY SPEY55515 54521 EU WEATHER FAULTY W C ABORTED TAKEOFF F FLT CONT AFFECTED TO TAKEOFF 1 AU S 780 2673 (AUS) RADAR RECEIVE/TRANSMIT UNIT FAULTY. 2 L 7 2 4F 4 F RT A20EU E2EU 2001040500352 20010405 00352 2001 4 5 AU010271 4 20010312 G 2212 637SUE1 WARNING SYSTEM FOKKER F28 F28MK1000 4990808 EU RROYCE SPEY SPEY55515 54521 EU ALTITUDE CONTROL FAILED W A UNSCHED LANDING P NO WARNING INDICATION CR CRUISE 1 AU S (AUS) ALTITUDE ALERT SYSTEM FAILED. ALTITUDE PRESELECT COUPLER CHANGED. 2 L 7 2 4F 4 F RT A20EU E2EU 2001040500353 20010405 00353 EU 2001 4 5 AU010272 2 20010314 G 7200 RB18355515H ENGINE FOKKER F28 F28MK4000 4990810 EU RROYCE SPEY SPEY55515 54521 EU NR 1 VIBRATES W C ABORTED TAKEOFF E J VIBRATION/BUFFET WARNING INDICATION TO TAKEOFF 1 AU S (AUS) NR 1 ENGINE VIBRATION AND NOISE. 2 L 7 2 4F 4 F RT A20EU E2EU 2001040500354 20010405 00354 CE 2001 4 5 AU010273 1 20010316 G 3260 FASTENER CESSNA 404 404CESSNA 2075901 CE CONT O520 GTSIO520M 17032 SO MCAULY 3FF32 3FF32C501 GL MLG UPLOCK FAILED W O OTHER N FALSE WARNING CR CRUISE 1 AU S (AUS) LANDING GEAR UPLOCK ASSEMBLY HI-LOK FASTENERS FAILED. BRACKETS TORN AWAY FROM SPAR BOX. 1 L 7 2 3O 3 O A25CE E7CE 5 C P45GL 2001040500355 20010405 00355 EU 2001 4 5 AU010274 1 20010321 G 2720 NB45961 LEVER BNORM BN2 BN2B20 1520302 EU LYC O540 IO540K1B5 41532 EA HARTZL HCC2Y HCC2YK2 GL RUDDER CONTROL S LOOSE W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) RUDDER CONTROL RT IDLER LEVER LOOSE AND CATCHING ON FUSELAGE FRAME OPENING. 1 H 7 2 3O 3 O A17EU 1E4 5 C P920 2001040500356 20010405 00356 2001 4 5 AU010276 4 20010317 G 6122 1680640 PICKUP WOODWARD 89741016 BAG JETSTM JETSTM3201 1500217 EU GARRTT TPE331 TPE33112UHR WP MCAULY 4HFR34 4HFR34C653 NE PROP GOVERNOR FAULTY W C ABORTED TAKEOFF J WARNING INDICATION TO TAKEOFF 1 AU S 2330240 (AUS) LT ENGINE GOVERNOR MAGNETIC PICKUP (MONOPOLE) OUTPUT VOLTAGEUNSTABLE. 2 L 7 2 4T 4 T RT A56EU E4WE 6 C 3PNE 2001040500357 20010405 00357 GL 2001 4 5 AU010277 3 20010320 G 6110 991996 SPACER MCAULY B3DF36C527 PIPER PA31 PA31350 7103110 SO LYC O540 LTIO540J2BD 41533 EA MCAULY 3DF36C B3DF36C526 GL PROPELLER ASSY MISINSTALLED W K NONE W INADEQUATE Q C IN INSP/MAINT 1 AU S 597 991996 (AUS) RT PROPELLER SPACER INCORRECTLY FITTED. 1 L 7 2 3O 3 O A20SO E14EA 5 C 2001050700400 20010507 00400 EU 2001 5 7 AU010278 1 20010303 G 2550 A25LT CARGO HOOK BOLKMS 117 BK117B1 5626012 EU LYC LTS101 LTS101750B1 41560 NE CARGO AREA FAULTY W O OTHER D INFLIGHT SEPARATION CL CLIMB 1 AU S (AUS) CARGO HOOK FAILED AND RELEASED LOAD. INVESTIGATION FOUND SCREWLOCATED ON THE LOWER LH SIDE OF THE COVER WAS INTERF ERING WITHTHE RETURN OF THE LEVER AND LATCH ASSEMBLY RESULTING IN INTERMITTENT OPERATION OF THE LATCH. EXCESSIVE PLAY IN LINK AND PINS CONTRIBUTED TO THE PROBLEM. 1 G 7 2 3U 3 U H13EU E5NE10 2001051000071 20010510 00071 EA 2001 5 10 AU010279 2 20010326 G 8520 LW12596 BOLT PIPER PA31 PA31350 7103110 SO LYC O540 TIO540J2BD 41532 EA HARTZL HCE3Y HCE3YR2 GL ENGINE BROKEN W O OTHER E F K VIBRATION/BUFFET FLT CONT AFFECTED FLUID LOSS DE DESCENT 1 AU S (AUS) LT ENGINE CONNECTING ROD BOLT FAILED. ENGINE SUMP HOLED. 1 L 7 2 3O 3 O A20SO E14EA 5 C P33EA 2001050700401 20010507 00401 SW 2001 5 7 AU010281 1 20010322 G 6220 471202527 GRIP BELL 47 47G5A 1181034 SW LYC O435 VO435B1A 41516 EA MAIN ROTOR HEAD CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S 577 NC5779 (AUS) MAIN ROTOR GRIP CRACKED IN SECOND, THIRD AND FOURTH THREADS. FOUND DURING EDDY CURRENT INSPECTION. X-RAY INSPECTIO N RESULTSWERE INCONCLUSIVE. 1 G 7 1 3O 3 O 2H3 E279 2001051000072 20010510 00072 SW 2001 5 10 AU010282 1 20010128 G 7931 2719153003 TRANSDUCER SWRNGN SA227 SA227* SW GARRTT TPE331 TPE33112UA 01514 WP MCAULY 4HFR34 4HFR34C652 NE ENGINE OIL PRESS FAILED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) ENGINE OIL PRESSURE TRANSDUCER FAILED FOLLOWING FITMENT. 2 L 7 2 4T 4 T RT A5SW E4WE 6 C 3PNE 2001051000073 20010510 00073 SW 2001 5 10 AU010284 1 20010314 G 2121 071040370001 COOLING FAN SWRNGN SA227 SA227* SW GARRTT TPE331 TPE33112UA 01514 WP MCAULY 4HFR34 4HFR34C652 NE AIR DISTRIBUTION FAILED W O OTHER B SMOKE/FUMES/ODORS/SPARKS CR CRUISE 1 AU S (AUS) AVIONICS COOLING FAN FAILED. CIRCUIT BREAKER POPPED. 2 L 7 2 4T 4 T RT A5SW E4WE 6 C 3PNE 2001051100004 20010511 00004 EU 2001 5 11 AU010285 1 20010329 G 2910 AE7064588 HOSE SAAB SF340 340B 7860101 EU GE CT7TP CT79B 30030 NE ROTOL R375 R3754123F21 NE HYDRAULIC SYSTEM RUPTURED W C ABORTED TAKEOFF K J FLUID LOSS WARNING INDICATION TO TAKEOFF 1 AU S (AUS) NOSE LANDING GEAR ACTUATOR FLEXIBLE DOWN LINE RUPTURED. LOSS OF HYDRAULIC FLUID. 2 L 7 2 4T 4 T RT A52EU E8NE 6 C P17NE 2001051100005 20010511 00005 SO 2001 5 11 AU010286 1 20010205 G 2436 VSF7203S REGULATOR PIPER PA23 PA23250 7102308 SO LYC O540 IO540* 41532 EA DC SYSTEM MALFUNCTIONED W O OTHER H ELECT. POWER LOSS-50 PC CR CRUISE 1 AU S (AUS) REGULATOR OVERVOLTAGE. CHARGING SYSTEM TRIPPED. 1 L 7 2 3O 3 O 1A10 1E4 2001051100006 20010511 00006 2001 5 11 AU010287 4 20010325 G 6122 8210004 GOVERNOR HARTZL HCB3TN3 DHAV DHC6 DHC6300 2802606 EA PWA PT6 PT6A27 52043 EA HARTZL HCB3T HCB3TN3 GL PROP GOVERNOR FAULTY W A UNSCHED LANDING O OTHER CL CLIMB 1 AU S 103231ST (AUS) RT PROPELLER GOVERNOR FAULTY. 1 H 7 2 3T 4 T RT A9EA E4EA 6 C P15EA 2001051100007 20010511 00007 SO 2001 5 11 AU010288 1 20010325 G 2750 CONTROLLER EMB 120 EMB120 3260201 SO PWA 118 PW118A NE HAMSTD 14SF 14SF9 NE TE FLAPS FAULTY W C ABORTED TAKEOFF F FLT CONT AFFECTED TO TAKEOFF 1 AU S (AUS) OUTBOARD FLAP DISAGREEMENT WARNING. INSPECTION COULD FIND NOFAULTS. 2 L 7 2 4T 4 T RT A31SO E20NE 6 N P11NE 2001051100008 20010511 00008 NE 2001 5 11 AU010289 2 20010312 G 7250 3053556220 BEARING GE CFM565A1 AIRBUS 320 A320211 3930320 EU CFMINT CFM56 CFM565A1 NE TURBINE SECTION SPALLED W E A ENGINE SHUTDOWN UNSCHED LANDING E VIBRATION/BUFFET CL CLIMB 1 AU S (AUS) NR 2 ENGINE NR 4 BEARING OUTER RACE SEVERELY SPALLED. 2 L 7 2 4F 4 F RT A28NM E29NE 2001051100009 20010511 00009 EU 2001 5 11 AU010290 1 20010328 G 6123 HTE123542A PRESSURE SWITCH HARTZL HCA6A3 STBROS SD3 SD360 8100606 EU PWA PT6 PT6A67R 52043 NE HARTZL HCA6A HCA6A3 NE PROP FEATHER FAULTY W C ABORTED TAKEOFF J WARNING INDICATION TO TAKEOFF 1 AU S (AUS) LH PROPELLER AUTOFEATHER SYSTEM PRESSURE SWITCH FAULTY. 2 H 7 2 4T 4 T A41EU E26NE 6 C P14NE 2001051100010 20010511 00010 CE 2001 5 11 AU010291 1 20010323 G 5740 0811351 FITTING CESSNA 402C CESSNA 402 402C 207590R CE CONT O520 TSIO520VB 17040 SO MCAULY 3AF32C 3AF32C505 GL WING SPAR CORRODED W K NONE O OTHER IN INSP/MAINT 1 AU S 4020625 (AUS) WING SPAR CAP FITTING CONTAINED SEVERE EXFOLIATION CORROSION ON THE FORWARD FACE. 1 L 7 2 3O 3 O A7CE E8CE 5 C P22EA 2001051100011 20010511 00011 NE 2001 5 11 AU010292 2 20010403 G 7310 230350901 PIPE LYC ALF502R3A BAG BAE146 BAE146200A 1500266 EU LYC ALF502 ALF502R3A 41580 NE ENGINE FUEL DIST FRACTURED W K NONE K FLUID LOSS IN INSP/MAINT 1 AU S (AUS) ENGINE FUEL PIPE FRACTURED. FUEL LEAKING. 2 H 7 4 4F 4 F RT A49EU E6NE 2001051100012 20010511 00012 NM 2001 5 11 AU010293 1 20010331 G 3244 A21580664 TIRE 161U00011 BOEING 747 747438 NM RROYCE RB211 RB211* 54555 NE MLG FAILED W C ABORTED TAKEOFF J WARNING INDICATION TO TAKEOFF 1 AU S A21580664 (AUS) RH BODY LANDING GEAR OUTBOARD REAR NR 6R TIRE SHREDDED. DAMAGE CAUSED TO BODY FAIRING PANELS 194BR, 194CR, 194GR, RT WING LANDING GEAR DOOR AND HINGE, NR 5R WHEEL, RH BODY LANDING GEAR TRUCK POSITIONING ACTUATOR HYDRAULIC LINE, NR 13 AND NR 14 BRAKELINES. NUMEROUS FUSELAGE DENTS ALSO EVIDENT. 2 L 7 4 4F 4 F RT A20WE A12EU 2001051100013 20010511 00013 NM 2001 5 11 AU010294 1 20010401 G 2434 727810C GENERATOR BOEING 767 767338 1385151 NM GE CF6 CF680C2* GL APU FAILED W O OTHER H J ELECT. POWER LOSS-50 PC WARNING INDICATION NR NOT REPORTED 1 AU S 52 (AUS) APU GENERATOR FAILED. 2 L 7 2 4F 4 F RT A1NM E23EA 2001051100014 20010511 00014 NM 2001 5 11 AU010295 1 20010403 G 5410 FAIRING BOEING 747 747400 NM GE CF6 CF680C2* GL NACELLE MISSING W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) NR 2 ENGINE RT COLD STREAM C DUCT MISSING UPPER INBOARD DUCT TO STRUT FILLET FAIRING. 2 L 7 4 4F 4 F RT A20WE E23EA 2001051100015 20010511 00015 EU 2001 5 11 AU010296 1 20010318 G 7712 1090729245 TRANSMITTER AGUSTA A109 A109A 0260109 EU ALLSN 25OC 250C20R GL ENGINE FAULTY W A UNSCHED LANDING E R VIBRATION/BUFFET PARTIAL RPM/PWR LOSS CR CRUISE 1 AU S (AUS) ENGINE TORQUE TRANSMITTER FAULTY. 1 G 7 2 3U 3 U H7EU E4CE 2001051100016 20010511 00016 NM 2001 5 11 AU010297 1 20010406 G 5742 FITTING BOEING 767 767277 NM GE CF6 CF680A 30025 NE WING CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) RT WING PYLON ATTACHMENT FITTING OUTBOARD LUG CRACKED. CRACK PENETRATES THE FULL THICKNESS OF THE LUG AND EXTENDSA PPROXIMATELY 25.4MM (1IN) ALONG THE INBOARD FACE AND APPROXIMATELY 12.7MM (0.5IN) ALONG THE OUTBOARD FACE. FOUND USING E DDY CURRENT INSPECTION IAW BSB 767-57A0070 AND ERB76-57-40-18. 2 L 7 2 4F 4 F RT A1NM E13NE 2001051100017 20010511 00017 NM 2001 5 11 AU010298 1 20010409 G 5742 FITTING BOEING 767 767277 NM GE CF6 CF680A 30025 NE WING CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) LT WING PYLON ATTACHMENT FITTING OUTBOARD LUG CRACKED. FOUND DURING VISUAL INSPECTION IAW ER B76-57-40-19. 2 L 7 2 4F 4 F RT A1NM E13NE 2001051100018 20010511 00018 GL 2001 5 11 AU010299 3 20010320 G 6111 C4451 FERRULE MCAULY 3AF32C75 BEECH 95 95B55 1152729 CE CONT O470 IO470L 17026 SO MCAULY 3AF32C 3AF32C75 GL PROPELLER BLADE CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S 1500 (AUS) PROPELLER BLADE FERRULE CRACKED AROUND BEARING SHELF ORIGINATINGFROM A PREVIOUSLY DRILLED ACTUATING PIN HOLE. CRAC K LENGTH 50.8MM (2IN). 1 L 7 2 3O 3 O RT 3A16 3E1 5 C P22EA 2001051100019 20010511 00019 SO 2001 5 11 AU010300 1 20010326 G 2752 3203001007 ACTUATOR EMB 120 EMB120 3260201 SO PWA 118 PW118A NE HAMSTD 14SF 14SF9 NE TE FLAPS FAILED W C ABORTED TAKEOFF F J FLT CONT AFFECTED WARNING INDICATION TO TAKEOFF 1 AU S (AUS) LT OUTBOARD FLAP ACTUATOR FAULTY. 2 L 7 2 4T 4 T RT A31SO E20NE 6 N P11NE 2001051100020 20010511 00020 NM 2001 5 11 AU010302 1 20010326 G 5511 SPAR BOEING 737 73733A 1384673 NM GE CFM56 CFM563B1 13802 NE HORIZONTAL STAB CORRODED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) RT HORIZONTAL STABILIZER REAR SPAR UPPER CHORD CORRODED AT STN 267.50. LT HORIZONTAL STABILISER REAR SPAR UPPER CH ORD CORRODED AT STN 258. 2 L 7 2 4F 4 F RT A16WE E2GL 2001051100021 20010511 00021 CE 2001 5 11 AU010303 1 20010331 G 3260 JE6 ACTUATOR CESSNA 340 340CESSNA 2076404 CE CONT O520 TSIO520K 17040 SO MCAULY 3AF32C 3AF32C87 GL LANDING GEAR BROKEN W O OTHER N FALSE WARNING DE DESCENT 1 AU S (AUS) RT MAIN LANDING GEAR MICROSWITCH ACTUATOR FAILED. 1 L 7 2 3O 3 O 3A25 E8CE 5 C P22EA 2001051100022 20010511 00022 CE 2001 5 11 AU010304 1 20010330 G 2434 ALT9422 ALTERNATOR CESSNA 310 310R 2074245 CE CONT O520 IO520M 17032 SO MCAULY 3AF32C 3AF32C87 GL DC SYSTEM FAILED W K NONE O OTHER IN INSP/MAINT 1 AU S 46 (AUS) ENGINE DRIVEN ALTERNATOR SUSPECT REAR BEARING FAILED. DAMAGE TO ENGINE CRANKSHAFT DRIVE GEAR. 1 L 7 2 3O 3 O 3A10 E5CE 5 C P22EA 2001051100023 20010511 00023 NM 2001 5 11 AU010305 1 20010403 G 1100 ASM321032A PLACARD BOEING 737 737377 NM GE CFM56 CFM563B1 13802 NE MLG MISSING W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) TIRE INFLATION PLACARD MISSING. 2 L 7 2 4F 4 F RT A16WE E2GL 2001051100024 20010511 00024 NM 2001 5 11 AU010306 1 20010404 G 7997 WIRE BOEING 747 747438 NM RROYCE RB211 RB211524G19 NE NR 3 ENGINE WORN W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) NR 3 ENGINE OIL PRESSURE INDICATION FAILED. INVESTIGATION FOUNDA SHORT CIRCUIT IN THE WING ROOT/ENGINE DISCONNECT DUE TO WIRECHAFING AT ACCESS PANEL 611BB. 2 L 7 4 4F 4 F RT A20WE E30NE 2001051100025 20010511 00025 NM 2001 5 11 AU010308 1 20010404 G 2910 BACF8A06EN0700B HOSE BOEING 767 767238 NM PWA JT9 JT9D7R4E 52054 NE HYDRAULIC SYSTEM LEAKING W K NONE K FLUID LOSS IN INSP/MAINT 1 AU S (AUS) RT MAIN LANDING GEAR TILT ACTUATOR HYDRAULIC HOSE LEAKING. 2 L 7 2 4F 4 F RT A1NM E3NE 2001051100026 20010511 00026 NM 2001 5 11 AU010309 1 20010404 G 2910 AS11506K0280 HOSE BOEING 767 767330 NM RROYCE RB211 RB211524* NE HYDRAULIC SYSTEM LEAKING W K NONE K FLUID LOSS IN INSP/MAINT 1 AU S (AUS) RT MAIN LANDING GEAR FLEXIBLE BRAIDED BRAKE HOSE HOLED ANDLEAKING. 2 L 7 2 4F 4 F RT A1NM E12EU 2001051100027 20010511 00027 EU 2001 5 11 AU010310 1 20010314 G 2920 MS24142D1 RELAY SAAB SF340 340B 7860101 EU GE CT7TP CT79B 30030 NE ROTOL R375 R3754123F21 NE HYDRAULIC SYSTEM FAULTY W O OTHER K J FLUID LOSS WARNING INDICATION LD LANDING 1 AU S (AUS) AUXILIARY HYDRAULIC CONTROL RELAY FAULTY. 2 L 7 2 4T 4 T RT A52EU E8NE 6 C P17NE 2001051100028 20010511 00028 NM 2001 5 11 AU010311 1 20010324 G 5230 6941730 BUNGEE CORD BOEING 737 737377 NM GE CFM56 CFM563B1 13802 NE CARGO DOOR BROKEN W A UNSCHED LANDING J WARNING INDICATION CR CRUISE 1 AU S (AUS) AFT CARGO DOOR RELEASE LANYARD HANDLE JAMMED UNDER DOOR SEAL. INVESTIGATION FOUND THE LANYARD BUNGEE CORD BROKEN. 2 L 7 2 4F 4 F RT A16WE E2GL 2001051100029 20010511 00029 SO 2001 5 11 AU010312 1 20010330 G 5740 4511500 FITTING PIPER PA31 PA31350 7103110 SO LYC O540 TIO540J2BD 41532 EA HARTZL HCE3Y HCE3YR2 GL WING SPAR CORRODED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) LT AND RT UPPER MAIN SPAR ATTACHMENT FITTINGS CORRODED ANDPARTIALLY EXFOLIATED. WHEN THE FITTINGS WERE REMOVED THE ATTACHMENT RIVETS WERE FOUND TO BE SHEARED. 1 L 7 2 3O 3 O A20SO E14EA 5 C P33EA 2001051100030 20010511 00030 SO 2001 5 11 AU010313 1 20010330 G 5740 4511500 FITTING PIPER PA31 PA31350 7103110 SO LYC O540 TIO540J2BD 41532 EA HARTZL HCE3Y HCE3YR2 GL WING SPAR CORRODED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) LT AND RT UPPER MAIN SPAR ATTACHMENT FITTINGS CORRODED ANDPARTIALLY EXFOLIATED. 1 L 7 2 3O 3 O A20SO E14EA 5 C P33EA 2001051100031 20010511 00031 SO 2001 5 11 AU010314 1 20010330 G 5720 BRACKET PIPER PA31 PA31350 7103110 SO LYC O540 TIO540J2BD 41532 EA HARTZL HCE3Y HCE3YR2 GL WING SPAR CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) FORWARD SPAR ATTACHMENT BRACKET LOCATED AT STN 104.6 CRACKED ONFORWARD AND REAR SIDES. 1 L 7 2 3O 3 O A20SO E14EA 5 C P33EA 2001051100032 20010511 00032 SO 2001 5 11 AU010315 1 20010330 G 5720 BRACKET PIPER PA31 PA31350 7103110 SO LYC O540 TIO540J2BD 41532 EA HARTZL HCE3Y HCE3YR2 GL WING SPAR CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) FORWARD SPAR ATTACHMENT BRACKET LOCATED AT STN104.6 CRACKED ONFORWARD AND REAR SIDES. 1 L 7 2 3O 3 O A20SO E14EA 5 C P33EA 2001051100033 20010511 00033 CE 2001 5 11 AU010316 1 20010319 G 2434 902015 BEARING PRESTOLITE ALU9405 CESSNA 310 310R 2074245 CE CONT O520 IO520M 17032 SO MCAULY 3AF32C 3AF32C87 GL DC GENERATOR FAILED W A UNSCHED LANDING H J ELECT. POWER LOSS-50 PC WARNING INDICATION CR CRUISE 1 AU S 4E000070 (AUS) RT ENGINE ALTERNATOR BEARING FAILED. 1 L 7 2 3O 3 O 3A10 E5CE 5 C P22EA 2001051100034 20010511 00034 SO 2001 5 11 AU010317 1 20010314 G 5280 4752932 HINGE PIPER PA31 PA31350 7103110 SO LYC O540 TIO540J2BD 41532 EA HARTZL HCE3Y HCE3YR2 GL MLG DOOR CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) RT MAIN LANDING GEAR INBOARD DOOR FORWARD HINGE CRACKED. FOUNDDURING INSPECTION IAW AD/PA31/93 AMDT1. 1 L 7 2 3O 3 O A20SO E14EA 5 C P33EA 2001051100035 20010511 00035 SO 2001 5 11 AU010319 2 20010330 G 8530 VALVE GUIDE CESSNA 206 U206G 2073356 CE CONT O520 IO520F 17032 SO MCAULY D3A34 D3A34C404 GL ENINE WORN W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) NR 2 AND NR 6 CYLINDER EXHAUST VALVE GUIDES WORN. 1 H 7 1 3O 3 O A4CE E5CE 5 C P47GL 2001051100036 20010511 00036 NM 2001 5 11 AU010320 1 20010409 G 7910 OIL SYSTEM DHAV DHC8 DHC8102 2809003 NM PWA 120 PW120A NE HAMSTD 14SF 14SF7 NE ENGINE LOW W C ABORTED TAKEOFF E K J VIBRATION/BUFFET FLUID LOSS WARNING INDICATION TO TAKEOFF 1 AU S (AUS) NO1 ENGINE OIL LEVEL LOW. SUSPECT OIL LEVEL HAD NOT BEEN TOPPED UP DURING PREFLIGHT INSPECTION. PERSONNEL/MAINTENA NCE ERROR. 2 H 7 2 4T 4 T RT A13NM E20NE 6 C P7NE 2001051100037 20010511 00037 NE 2001 5 11 AU010321 2 20010410 G 7320 226332003 PIPE LYC ALF502R3A BAG BAE146 BAE146100A 1500260 EU LYC ALF502 ALF502R3A 41580 NE FUEL CONTROL LOOSE W A UNSCHED LANDING E R VIBRATION/BUFFET PARTIAL RPM/PWR LOSS CR CRUISE 1 AU S (AUS) NO3 ENGINE P3 SENSE LINE TO FCU LOOSE. THE AIRCRAFT HAD A NO3 ENGINE AND FCU CHANGED THE PREVIOUS DAY. PERSONNEL/M AINTENANCEERROR. 2 H 7 4 4F 4 F RT A49EU E6NE 2001051100038 20010511 00038 NM 2001 5 11 AU010322 1 20010410 G 5742 MOUNT BOEING 767 767277 NM GE CF6 CF680A 30025 NE WING CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) LH WING FITTING OUTBOARD LUG CRACKED DIAGONALLY ACROSS THE UPPERFLANGE FACE THROUGH THE LUG FILLET RADIUS. THE CRA CK WAS FOUNDVISUALLY AND CONFIRMED USING NDI. FOUND DURING INSPECTION IAW ERB76-57-40-19. 2 L 7 2 4F 4 F RT A1NM E13NE 2001051100039 20010511 00039 NM 2001 5 11 AU010323 1 20010409 G 5742 FITTING BOEING 767 767277 NM GE CF6 CF680A 30025 NE WING CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) RT WING FITTING OUTBOARD LUG CRACKED AROUND THE INBOARD AFT CORNER OF THE LUG APPROXIMATELY 10MM (0.393IN) FORWARD AND 5MM (0.196IN) OUTBOARD. CRACK CONFIRMED USING NDI. FOUND DURING INSPECTION IAW ER B76-57-40-18. 2 L 7 2 4F 4 F RT A1NM E13NE 2001051100040 20010511 00040 SO 2001 5 11 AU010324 1 20010317 G 5280 DOOR EMB 110 EMB110P2 3260124 SO PWA PT6 PT6A34 52043 EA HARTZL HCB3T HCB3TN3 GL LANDING GEAR DISCONNECTED W C ABORTED TAKEOFF D INFLIGHT SEPARATION TO TAKEOFF 1 AU S (AUS) NOSE LANDING GEAR DOORS DISCONNECTED ON TAKEOFF PREVENTING NOSE LANDING GEAR FROM RETRACTING. SUSPECT DOORS INCORR ECTLY ATTACHED. PERSONNEL/MAINTENANCE ERROR. 1 L 7 2 4T 4 T A21SO E4EA 6 C P15EA 2001051100041 20010511 00041 CE 2001 5 11 AU010325 1 20010326 G 3230 57412026 UPLOCK CESSNA 402 402C 207590R CE CONT O520 TSIO520VB 17040 SO MCAULY 3AF32C 3AF32C505 GL LANDING GEAR BROKEN W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) LH MAIN LANDING GEAR UPLOCK HOOK BROKEN. HOOK WAS AN OLD TYPE. 1 L 7 2 3O 3 O A7CE E8CE 5 C P22EA 2001051100042 20010511 00042 CE 2001 5 11 AU010326 1 20010410 G 3230 45825080 DRAG BRACE BEECH 58 58 1152740 CE CONT O520 IO520C 17032 SO MCAULY 3AF34C 3AF34C502 GL LANDING GEAR CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) NOSE LANDING GEAR AFT DRAG BRACE CRACKED FROM SEALING RIVET. 1 L 7 2 3O 3 O 3A16 E5CE 5 C P22EA 2001051500001 20010515 00001 GL 2001 5 15 AU010327 1 20010320 G 2701 LS52RS BEARING PAC CT4 CT4A 05623UC GL CONT O360 IO360HB 17025 SO HARTZL HCC2Y BHCC2YF1 GL CONTROL COLUMN WORN W O OTHER F FLT CONT AFFECTED NR NOT REPORTED 1 AU S (AUS) RT CONTROL COLUMN TORQUE TUBE BEARING WORN. 1 Q 7 1 3I 3 O RT A9PC E1CE 5 C P920 2001051500002 20010515 00002 CE 2001 5 15 AU010328 1 20010329 G 2434 ALT9422 ALTERNATOR CESSNA 310 310R 2074245 CE CONT O520 IO520M 17032 SO MCAULY 3AF32C 3AF32C87 GL DC SYSTEM FAILED W O OTHER H J ELECT. POWER LOSS-50 PC WARNING INDICATION CR CRUISE 1 AU S (AUS) RT ALTERNATOR DISINTEGRATED. SEVERE INTERNAL DAMAGE. SUSPECTCAUSED BY BEARING FAILURE. 1 L 7 2 3O 3 O 3A10 E5CE 5 C P22EA 2001051500003 20010515 00003 NM 2001 5 15 AU010329 1 20010407 G 5710 DRAIN VALVE BOEING 747 747238B 1384828 NM RROYCE RB211 RB211524D419 54555 NE WING CLOGGED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) DRAINS LOCATED IN WING CENTRE SECTION AFT CAVITY AT BS 1241 WERE BLOCKED BY FOREIGN MATERIALS WITH EIGHT TO TEN LI TRES OF WATER PRESENT. TIDE MARKS ALSO PRESENT ON SURROUNDING STRUCTURE INDICATING EVIDENCE OF GREATER QUANTITIES OF WAT ER RETENTION. 2 L 7 4 4F 4 F A20WE E12EU 2001051500004 20010515 00004 NM 2001 5 15 AU010331 1 20010413 G 3520 S417T40127 GENERATOR BOEING 737 737377 NM GE CFM56 CFM563B1 13802 NE PAX OXYGEN FAILED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) OXYGEN GENERATORS LOCATED ABOVE SEATS 9LT, 11LT, 13LT, 15LT AND 17LT HAD THE RELEASE PIN LOCATED IN THE SAFETY PIN HOLE. 2 L 7 2 4F 4 F RT A16WE E2GL 2001051500005 20010515 00005 NM 2001 5 15 AU010332 1 20010407 G 2424 734284F GCU BOEING 767 767338 1385151 NM GE CF6 CF680C2* GL AC REGULATOR FAULTY W O OTHER H ELECT. POWER LOSS-50 PC DE DESCENT 1 AU S 21473 (AUS) RH GENERATOR CONTROL UNIT (GCU) FAULTY. 2 L 7 2 4F 4 F RT A1NM E23EA 2001051500006 20010515 00006 SO 2001 5 15 AU010333 2 20010406 G 8530 539647 PISTON PIN CESSNA 182 182Q 2072732 CE CONT O470 O470U 17026 SO MCAULY 2A34C 2A34C203 GL ENGINE FAULTY W K NONE O OTHER IN INSP/MAINT 1 AU S 343 (AUS) DURING PRE-PURCHASE INSPECTION IT WAS FOUND THAT THE LOG BOOK ENTRY INDICATED THAT ONLY ONE NEW PISTON PIN HAD BEE N FITTED ANDTHAT THE OTHER FIVE HAD BEEN INSPECTED BY MAGNETIC PARTICLE INSPECTION AND REFITTED. AD/CON/62 AND TCM SB M8 7-11 REV 2STATES THAT NEW PISTON PINS BE FITTED. OVERHAUL FACILITY STATES THAT ALL OF THE PISTON PINS WERE REPLACED. AN ANOMALY EXISTS BETWEEN THE LOG BOOK AND THE OVERHAUL FACILITY. 1 H 7 1 3O 3 O NT 3A13 E273 5 C P3EA 2001051500007 20010515 00007 NM 2001 5 15 AU010334 1 20010315 G 5230 1U1168 ACTUATOR BOEING 727 72777C 1380420 NM PWA JT8 JT8D15 52051 NE CARGO DOOR FAULTY W K NONE O OTHER IN INSP/MAINT 1 AU S 495 (AUS) MAIN CARGO DOOR REAR ACTUATOR EYE END BEARING MIGRATED RESULTING IN DISTORTION OF THE EYE END. MINOR DAMAGE TO RET RACTION ARM. 2 L 7 3 4F 4 F A3WE E2EA 2001051500008 20010515 00008 NM 2001 5 15 AU010335 1 20010405 G 2910 BACH30B01H326R HOSE BOEING 747 747238B 1384828 NM RROYCE RB211 RB211524D419 54555 NE HYDRAULIC SYSTEM LEAKING W O OTHER K J FLUID LOSS WARNING INDICATION CR CRUISE 1 AU S (AUS) LT WING MAIN LANDING GEAR DOOR ACTUATOR FLEXIBLE HOSE LEAKING.LOSS OF HYDRAULIC FLUID. NR 4 ENGINE DRIVEN HYDRAULI C PUMP CHANGED DUE TO OPERATION WITH LOW HYDRAULIC QUANTITY. 2 L 7 4 4F 4 F A20WE E12EU 2001051500009 20010515 00009 NM 2001 5 15 AU010336 1 20010409 G 2750 CONTROLLER BOEING 737 73733A 1384673 NM GE CFM56 CFM563B1 13802 NE TE FLAPS FAULTY W O OTHER F J FLT CONT AFFECTED WARNING INDICATION AP APPROACH 1 AU S (AUS) DURING APPROACH FLAPS RAN TO 20 DEGREES ON SELECTION OF 25DEGREES. SELECTION TO 30 DEGREES SAW NO FURTHER MOVEMENT . INVESTIGATION COULD FIND NO FAULTS. SUSPECT CAUSED BY MOISTURE IN FLAP DRIVES. 2 L 7 2 4F 4 F RT A16WE E2GL 2001051500010 20010515 00010 WP 2001 5 15 AU010337 1 20010108 G 5730 3787 SKIN DH82A DHAVXX DH82 DH82AROBRTSN 2801002 WP DHAVXX GIPSY GIPSYMAJOR1 20004 WP WINGS PEELING W K NONE O OTHER IN INSP/MAINT 1 AU S 73 (AUS) FABRIC COVERING ON WINGS AND TAIL SURFACES HAD PAINT PEELING DUETO PROOFING NOT PENETRATING FABRIC. ALL RIB STITCH ING TAPES LOOSE AND NOT ATTACHED TO FABRIC. 1 Q 7 1 3I 3 I A8EU A8EU 2001051500011 20010515 00011 WP 2001 5 15 AU010338 1 20010108 G 5711 H347377 SPAR DHAVXX DH82 DH82AROBRTSN 2801002 WP DHAVXX GIPSY GIPSYMAJOR1 20004 WP WING CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S 73 (AUS) LT UPPER WING MAIN SPAR CRACKED IN SEVERAL PLACES. FURTHER INSPECTION FOLLOWING FABRIC REMOVAL FOUND THAT THE SPAR HAD BEEN DRESSED WITH FILLER AND PAINT UNDER WHICH MORE CRACKS WERE FOUND. 1 Q 7 1 3I 3 I A8EU A8EU 2001051500012 20010515 00012 WP 2001 5 15 AU010339 1 20010108 G 5521 SPAR DHAVXX DH82 DH82AROBRTSN 2801002 WP DHAVXX GIPSY GIPSYMAJOR1 20004 WP ELEVATOR CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S 73 (AUS) LT ELEVATOR SPAR CRACKED. FOLLOWING FABRIC REMOVAL THE SPAR WAS FOUND TO BE CRACKED IN SEVERAL PLACES INCLUDING AR EAS WHICH HAD BEEN BOUND WITH FABRIC. 1 Q 7 1 3I 3 I A8EU A8EU 2001051500013 20010515 00013 EU 2001 5 15 AU010340 1 20010406 G 2400 SPLICE BAG BAE146 BAE146300A 1500267 EU LYC ALF502 ALF502R5 41580 NE ELECTRICAL POWER BURNED W O OTHER B SMOKE/FUMES/ODORS/SPARKS NR NOT REPORTED 1 AU S (AUS) APU GENERATOR IN LINE SPLICE LOCATED IN THE FORWARD CARGO COMPARTMENT ROOF LINING OVERHEATED AND BURNED. 2 H 7 4 4F 4 F RT A49EU E6NE 2001051500014 20010515 00014 NM 2001 5 15 AU010341 1 20010409 G 3230 65B0154020 ACTUATOR BOEING 747 747SP38 NM RROYCE RB211 RB211524D419 54555 NE MLG FAILED W K NONE O OTHER IN INSP/MAINT 1 AU S 8931 (AUS) RT WING LANDING GEAR DOWNLOCK ACTUATOR SUFFERED A CATASTROPHIC FAILURE. THE FAILURE OCCURRED DURING THE FIRST OPER ATION OF THE ACTUATOR WHICH HAD JUST BEEN FITTED FOLLOWING MAINTENANCE. 2 L 7 4 4F 4 F RT A20WE E12EU 2001051500015 20010515 00015 NE 2001 5 15 AU010342 2 20010407 G 7200 ENGINE BAC 146 146200A 1500266 EU LYC ALF502 ALF502R5 41580 NE NR 4 FLAMED OUT W O OTHER E X VIBRATION/BUFFET ENGINE FLAMEOUT DE DESCENT 1 AU S (AUS) NR 4 ENGINE FLAMEOUT. LIMITED INFORMATION PROVIDED. 2 H 7 4 4F 4 F A49EU E6NE 2001051500016 20010515 00016 NE 2001 5 15 AU010343 2 20010416 G 7261 ST307607 KEY DHAV DHC8 DHC8102 2809003 NM PWA 120 PW120A NE HAMSTD 14SF 14SF7 NE NR 1 ENGINE MISSING W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) NR 1 ENGINE AC GENERATOR OIL SYSTEM SCAVENGE PUMP WOODRUFF KEY NOT FITTED. KEY WAS FOUND LOOSE IN THE BOTTOM OF TH E PUMP HOUSING.SUSPECT KEY FELL OUT DURING ASSEMBLY WITHOUT BEING NOTICED. 2 H 7 2 4T 4 T RT A13NM E20NE 6 C P7NE 2001051500017 20010515 00017 EU 2001 5 15 AU010344 1 20010410 G 3234 MOTOR BAG BAE146 BAE146300A 1500267 EU LYC ALF502 ALF502R5 41580 NE MLG FAULTY W O OTHER J WARNING INDICATION CL CLIMB 1 AU S (AUS) LANDING GEAR SELECTOR VALVE ACTUATOR MOTOR FAULTY. 2 H 7 4 4F 4 F RT A49EU E6NE 2001051500018 20010515 00018 EU 2001 5 15 AU010345 1 20010416 G 2421 IDG BAG BAE146 BAE146200A 1500266 EU CFMINT CFM56 CFM565A1 NE AC GENERATOR FAILED W O OTHER H J ELECT. POWER LOSS-50 PC WARNING INDICATION CL CLIMB 1 AU S (AUS) INTEGRATED DRIVE GENERATOR (IDG) FAILED. 2 H 7 4 4F 4 F RT A49EU E29NE 2001051500019 20010515 00019 NM 2001 5 15 AU010346 1 20010412 G 2133 MOTOR BOEING 737 737377 NM GE CFM56 CFM563B1 13802 NE OUTFLOW VALVE FAILED W O OTHER O OTHER DE DESCENT 1 AU S (AUS) AIRCRAFT PRESSURISATION SYSTEM OUTFLOW VALVE ELECTRIC MOTOR FAILED. OUTFLOW VALVE FAILED TO OPEN. 2 L 7 2 4F 4 F RT A16WE E2GL 2001051500020 20010515 00020 SO 2001 5 15 AU010347 2 20010407 G 8530 ROCKER BOSS CESSNA 206 U206E 2073350 CE CONT O520 IO520F 17032 SO HARTZL HCC3Y HCC3YF1 GL ENGINE CRACKED W C ABORTED TAKEOFF E R VIBRATION/BUFFET PARTIAL RPM/PWR LOSS TO TAKEOFF 1 AU S (AUS) ENGINE CYLINDER ROCKER HATS (2OFF) CRACKED AT PUSHROD END. EVIDENCE OF ROCKER HAT CONTACT ON THREE OTHER CYLINDERS . 1 H 7 1 3O 3 O A4CE E5CE 5 C P25EA 2001051500021 20010515 00021 NM 2001 5 15 AU010348 1 20010417 G 2910 AS4624J0300SS HOSE BOEING 767 767338 1385151 NM GE CF6 CF680C2* GL HYDRAULIC SYSTEM LEAKING W K NONE K FLUID LOSS IN INSP/MAINT 1 AU S (AUS) RT MAIN LANDING GEAR CENTER SYSTEM TILT RETURN HOSE LEAKING. 2 L 7 2 4F 4 F RT A1NM E23EA 2001051500022 20010515 00022 NM 2001 5 15 AU010349 1 20010414 G 2910 HOSE BOEING 767 767330 NM RROYCE RB211 RB211524* NE HYDRAULIC SYSTEM SPLIT W K NONE K FLUID LOSS IN INSP/MAINT 1 AU S (AUS) RT MAIN LANDING GEAR UPLINE PRESSURE HOSE SPLIT. 2 L 7 2 4F 4 F RT A1NM E12EU 2001051500023 20010515 00023 NE 2001 5 15 AU010350 2 20010318 G 7397 WIRE BOEING 747 747438 NM RROYCE RB211 RB211524G19 NE FUEL CONTROL WORN W O OTHER E VIBRATION/BUFFET CL CLIMB 1 AU S (AUS) NR 4 ENGINE FUEL SYSTEM WIRE CHAFED AND SHORT CIRCUITING. WIRE W6400-008-18R WAS LOCATED IN NR 4 STRUT KNEECAP DIS CONNECT PLUGD14300P. 2 L 7 4 4F 4 F RT A20WE E30NE 2001051500024 20010515 00024 2001 5 15 AU010351 4 20010409 G 2565 101651303 SLIDE BOEING 767 767204 NM GE CF6 CF680A 30025 NE ESCAPE SLIDE MISINSTALLED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) ESCAPE SLIDE FITTED TO DOOR LT 1 INCORRECTLY FITTED FOLLOWINGHEAVY MAINTENANCE. INSPECTION FOUND THAT THE SLIDE BA R WAS IN THE STOWED (TRANSPORT) POSITION AND WAS NOT CONNECTED TO THE GIRT BAR. FURTHER INVESTIGATION FOUND THAT THE ESC APE SLIDES ONTHE OTHER THREE DORS (LH2, RH1 AND RH2) WERE SIMILARLY INCORRECTLY FITTED. PERSONNEL/MAINTENANCE ERROR. 2 L 7 2 4F 4 F RT A1NM E13NE 2001051500025 20010515 00025 CE 2001 5 15 AU010352 1 20010409 G 2710 35521189 CONTROL CABLE BEECH 35 S35 1151532 CE CONT O520 IO520B 17032 SO HARTZL HCC3Y PHCC3YF1 GL AILERON CONTROL BROKEN W O OTHER F FLT CONT AFFECTED LD LANDING 1 AU S (AUS) AILERON THREADED CABLE AND FITTING SEPARATED APPROXIMATELY MIDWAY BETWEEN THE THREADED END AND THE SWAGED NUT. 1 L 7 1 3O 3 O 3A15 E5CE 5 C P25EA 2001051500026 20010515 00026 EA 2001 5 15 AU010353 2 20010413 G 8520 L2363440A GEAR BNORM BN2 BN2A8 1520209 EU LYC O540 O540E4C5 41532 EA HARTZL HCC2Y HCC2YK2 GL ENGINE CRANK FAILED W A UNSCHED LANDING E VIBRATION/BUFFET CR CRUISE 1 AU S (AUS) CRANKSHAFT DRIVE GEAR FAILED. 1 H 7 2 3O 3 O A17EU E295 5 C P920 2001051500027 20010515 00027 NM 2001 5 15 AU010354 1 20010405 G 5320 WEB BOEING 747 747338 NM FUSELAGE CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) LT VERTICAL BEAM WEB OF NOSE WHEEL STRUCTURE CRACKED FROM INSULATION BLANKET STUD HOLE AT BS 320. FOUND DURING INS PECTION IAW EI 747-053-0041 REV5. 2 L 7 2 4F RT A20WE 2001051500028 20010515 00028 2001 5 15 AU010355 4 20010417 G 2565 61621469 SLIDE BOEING 737 737476 NM CFMINT CFM56 CFM563C 13802 EU PAX DOOR MISINSTALLED W K NONE O OTHER IN INSP/MAINT 1 AU S 875 (AUS) MAIN ENTRY DOOR ESCAPE SLIDE SAFETY PIN INSTALLED. 2 L 7 2 4F 4 F RT A16WE E21EU 2001051500029 20010515 00029 NM 2001 5 15 AU010356 1 20010417 G 2752 734374D ACTUATOR DHAV DHC8 DHC8103 1386005 NM PWA 120 PW123D 52152 NE HAMSTD 14SF 14SF23 NE TE FLAPS WORN W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) TRAILING EDGE FLAP ACTUATORS (3OFF) HAD EXCESSIVE BACKLASH. 2 H 7 2 4T 4 T RT A13NM E20NE 6 C P7NE 2001051500030 20010515 00030 NM 2001 5 15 AU010357 1 20010417 G 2752 734374D ACTUATOR DHAV DHC8 DHC8103 1386005 NM PWA PW121 PW121 52124 NE HAMSTD 14SF 14SF7 NE TE FLAPS WORN W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) TRAILING EDGE FLAP ACTUATORS (2OFF) HAD EXCESSIVE BACKLASH. 2 H 7 2 4T 4 T RT A13NM E20NE 6 C P7NE 2001051500031 20010515 00031 NM 2001 5 15 AU010358 1 20010417 G 2752 734374D ACTUATOR DHAV DHC8 DHC8315 2809010 NM TE FLAPS WORN W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) TRAILING EDGE FLAP ACTUATORS (6OFF) HAD EXCESSIVE BACKLASH. 2 H 7 2 4T RT A13NM 2001051500032 20010515 00032 NM 2001 5 15 AU010359 1 20010417 G 2752 734374D ACTUATOR DHAV DHC8 DHC8* NM TE FLAPS WORN W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) TRAILING EDGE FLAP ACTUATORS (6OFF) HAD EXCESSIVE BACKLASH. 2 H 7 2 4T RT A13NM 2001051500033 20010515 00033 SO 2001 5 15 AU010360 1 20010419 G 5280 4752932 HINGE PIPER PA31 PA31 7103102 SO LYC O540 TIO540A1A 41532 EA HARTZL HCE3Y HCE3YR2 GL MLG DOOR CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) LT MAIN LANDING GEAR INBOARD DOOR FORWARD HINGE ARM CRACKED ONINNER RADIUS. FOUND DURING DYE PENETRANT INSPECTION IAW PIPER MSB 682. 1 L 7 2 3O 3 O A20SO E14EA 5 C P33EA 2001051500034 20010515 00034 2001 5 15 AU010361 4 20010417 G 2565 D31591475 SLIDE BOEING 737 737476 NM CFMINT CFM56 CFM563C 13802 EU PAX DOOR FAULTY W K NONE O OTHER IN INSP/MAINT 1 AU S 8870 (AUS) MAIN ENTRY DOOR ESCAPE SLIDE FAILED TO INFLATE DUE TO DAMAGE TO THE ASPIRATOR FLAPPER VALVE SUPPORT BRIDGE. INVEST IGATION FOUND THE BRIDGE TO BE LOOSE AND TWISTED PREVENTING THE FLAPPER VALVE HALVES FROM SEATING. 2 L 7 2 4F 4 F RT A16WE E21EU 2001051500035 20010515 00035 EU 2001 5 15 AU010362 1 20010331 G 2130 K1813 RELAY FOKKER F28 F28MK0100 4990807 EU RROYCE TAY TAY62015 04564 NE PRESSURE CONTROL FAILED W C ABORTED TAKEOFF O OTHER TO TAKEOFF 1 AU S (AUS) PRESSURISATION SYSTEM FAULTY. SUSPECT CAUSED BY HIGH RESISTANCE ACROSS CONTACTS IN RELAYS K1813, K1261, K1819 AND K1821 IN THEGROUND/FLIGHT RELAY BOX. 2 L 7 2 4F 4 F RT E25NE 2001051500036 20010515 00036 CE 2001 5 15 AU010363 1 20010412 G 3244 22X775X10X10 TIRE CESSNA 441 441 2076020 CE GARRTT TPE331 TPE3318 01514 WP HARTZL HCB3T HCB3TN5 GL LT MLG LEAKING W K NONE O OTHER IN INSP/MAINT 1 AU S 119 (AUS) LT MAIN WHEEL TYRE CONTAINED A SLOW LEAK FROM ONE OF THE SIDEWALL VENT HOLES. 1 L 7 2 3T 4 T RT A28CE E4WE 6 C P15EA 2001051500037 20010515 00037 SO 2001 5 15 AU010364 2 20010410 G 8520 632043 CONNECTING ROD CONT GTSIO510M CESSNA 404 404CESSNA 2075901 CE CONT O520 GTSIO520M 17032 SO MCAULY 3FF32 3FF32C501 GL ENGINE DAMAGED W K NONE O OTHER IN INSP/MAINT 1 AU S 1598 272103R (AUS) NR6 CONNECTING ROD RUBBING ON COUNTERWEIGHT. ROD WAS OUT OF ALIGNMENT WITH THE BIG END AND SMALL END AXIS. INSPECT ION FOUND THAT THREE COUNTERWEIGHTS HAD MATERIAL GROUND FROM THE BOTTOM SURFACE. THE CRANKCASE WAS ALSO UNSERVICEABLE DU E TO THE BREAKUP OF THE SECOND REAR LT SIDE BEARING SADDLE. 1 L 7 2 3O 3 O A25CE E7CE 5 C P45GL 2001051500038 20010515 00038 EU 2001 5 15 AU010365 1 20010327 G 7933 INDICATOR FOKKER F28 F28MK0100 4990807 EU RROYCE TAY TAY62015 04564 NE ENGINE OIL FAULTY W C ABORTED TAKEOFF E K J VIBRATION/BUFFET FLUID LOSS WARNING INDICATION TO TAKEOFF 1 AU S (AUS) NR 1 ENGINE OIL TEMPERATURE INDICATION SYSTEM FAULTY. WIRING AND INSULATION CHECKED WITH NO FURTHER PROBLEMS. CONN ECTORS CLEANED AND INSPECTED. PROBLEM HAS NOT REOCCURRED. 2 L 7 2 4F 4 F RT E25NE 2001051500039 20010515 00039 SO 2001 5 15 AU010366 1 20010403 G 6123 CONNECTOR EMB 120 EMB120 3260201 SO PWA 118 PW118A NE HAMSTD 14SF 14SF7 NE AUTOFEATHER SYS FAULTY W O OTHER J WARNING INDICATION TO TAKEOFF 1 AU S (AUS) AUTOFEATHER SYSTEM FAULTY. INSPECTION OF THE SYSTEM AND CLEANING OF CONNECTOR PLUGS CARRIED OUT. NO DEFECTS EVIDEN T. 2 L 7 2 4T 4 T RT A31SO E20NE 6 C P7NE 2001051500040 20010515 00040 SO 2001 5 15 AU010367 1 20010223 G 3221 6705403 TRUNNION PIPER PA32 PA32R300 7103213 SO LYC O540 IO540K1G5 41532 EA HARTZL HCC2Y HCC2YK1 GL NLG FRACTURED W O OTHER P NO WARNING INDICATION LD LANDING 1 AU S (AUS) NOSE LANDING GEAR TRUNNION FRACTURED THROUGH THE DRAG LINKATTACHMENT BOLT HOLE. 1 L 7 1 3O 3 O A3SO 1E4 5 C P920 2001051500041 20010515 00041 NE 2001 5 15 AU010368 2 20010330 G 8530 L2144448A CYLINDER PIPER PA60 PA60602P 7106015 NM LYC O540 IO540AA1A 41532 NE HARTZL HCC3Y HCC3YR2 NE ENGINE DAMAGED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) RT ENGINE CYLINDERS AND PISTONS DAMAGED BY DETONATION. 1 M 7 2 3O 3 O RT A17WE 1EA 5 C P25EA 2001050700402 20010507 00402 NE 2001 5 7 AU010369 1 20010420 G 5531 7620105501101 SPAR CAP SKRSKY S76 S76C 8143008 NE TMECA ARRIEL ARRIEL1S 60030 NE VERTICAL STAB CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) VERTICAL STABILISER FORWARD RH SPAR CAP ANGLE LOCATED AT VS117.25 CRACKED IN THE AREA WHERE THE RIVETS ATTACH THE TOP RIB TO THEANGLE. 1 G 7 2 3U 3 U NC H1NE E19EU 2001051500042 20010515 00042 NM 2001 5 15 AU010370 1 20010422 G 5610 8SC00430780205 WINDSHIELD DHAV DHC8 DHC8102 2809003 NM PWA 120 PW120A NE HAMSTD 14SF 14SF7 NE COCKPIT CRACKED W O OTHER O OTHER LD LANDING 1 AU S (AUS) CAPTAINS WINDSHIELD OUTER PANE CRACKED. CRACK ORIGINATED AT THE HEATER ELEMENT. 2 H 7 2 4T 4 T RT A13NM E20NE 6 C P7NE 2001051500043 20010515 00043 EA 2001 5 15 AU010371 2 20010418 G 8550 LW13388 SEAL PIPER PA31 PA31350 7103110 SO LYC O540 LTIO540J2BD 41533 EA HARTZL HCE3Y HCE3YR2 GL ENGINE DETERIORATED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) ENGINE OIL FILTER CONVERTER PLATE SEAL DETERIORATED. REFER TO AD/LYC105. 1 L 7 2 3O 3 O A20SO E14EA 5 C P33EA 2001051500044 20010515 00044 NM 2001 5 15 AU010372 1 20010421 G 3260 11300105 UPLOCK DHAV DHC8 DHC8102 2809003 NM PWA 120 PW120A NE HAMSTD 14SF 14SF7 NE LT MLG FAULTY W O OTHER J WARNING INDICATION CL CLIMB 1 AU S (AUS) LT MAIN LANDING GEAR UPLOCK LATCHING SPRINGS FAULTY. 2 H 7 2 4T 4 T RT A13NM E20NE 6 C P7NE 2001051500045 20010515 00045 NM 2001 5 15 AU010373 1 20010420 G 2910 9741735 HOSE BOEING 747 747438 NM RROYCE RB211 RB211524G19 NE HYDRAULIC SYSTEM FAILED W O OTHER J WARNING INDICATION AP APPROACH 1 AU S (AUS) NR 1 HYDRAULIC PUMP PRESSURE HOSE FAILED. LOSS OF HYDRAULIC FLUID. 2 L 7 4 4F 4 F RT A20WE E30NE 2001051500046 20010515 00046 NM 2001 5 15 AU010374 1 20010422 G 7160 12788 PANEL BOEING 747 747338 NM RROYCE RB211 RB211524G19 NE AIR INTAKE DELAMINATED W O OTHER E VIBRATION/BUFFET TO TAKEOFF 1 AU S 1749 (AUS) NR 1 ENGINE ICE IMPACT PANEL DELAMINATED FROM THE 5 OCLOCK POSITION THROUGH TO THE 11 OCLOCK POSITION. DELAMINATED MATERIAL WAS CAUGHT IN THE INLET GUIDE VANES. BOROSCOPE INSPECTION FOUND NIL INTERNAL DAMAGE. 2 L 7 2 4F 4 F RT A20WE E30NE 2001051500047 20010515 00047 NM 2001 5 15 AU010375 1 20010420 G 2910 HYDRAULIC SYSTEM BOEING 737 737377 NM A SYSTEM LOW W O OTHER K FLUID LOSS LD LANDING 1 AU S (AUS) HYDRAULIC A SYSTEM QUANTITY AND PRESSURE LOST. 2 L 7 2 4F RT A16WE 2001051500048 20010515 00048 NM 2001 5 15 AU010376 1 20010420 G 2750 CONTROLLER BOEING 737 737377 NM TE FLAPS FAULTY W O OTHER F FLT CONT AFFECTED LD LANDING 1 AU S (AUS) FLAPS FAILED TO MOVE PAST 15 DEGREES. 2 L 7 2 4F RT A16WE 2001051500049 20010515 00049 2001 5 15 AU010377 4 20010420 G 2565 7A13946 SLIDE BOEING 767 767338 1385151 NM GE CF6 CF680C2* GL PAX DOOR MISINSTALLED W K NONE W INADEQUATE Q C IN INSP/MAINT 1 AU S 10430 GV198 (AUS) NR 1 LH MAIN ENTRY DOOR ESCAPE SLIDE SAFETY PIN INSTALLED. PERSONNEL/MAINTENANCE ERROR. 2 L 7 2 4F 4 F RT A1NM E23EA 2001051500050 20010515 00050 WP 2001 5 15 AU010378 1 20010418 G 5511 SPAR DHAVXX DH82 DH82AROBRTSN 2801002 WP DHAVXX GIPSY GIPSYMAJOR1 20004 WP HORIZONTAL STAB DAMAGED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) HORIZONTAL STABILISER REAR SPAR DAMAGED. 1 Q 7 1 3I 3 I A8EU A8EU 2001051500051 20010515 00051 EU 2001 5 15 AU010379 1 20010406 G 2760 P308450070 SWITCH BAC 146 146200A 1500266 EU LYC ALF502 ALF502R5 41580 NE DRAG CONTROL FAULTY W O OTHER F J FLT CONT AFFECTED WARNING INDICATION CR CRUISE 1 AU S (AUS) LT AND RT OUTBOARD SPOILER MICROSWITCHES FAULTY. 2 H 7 4 4F 4 F A49EU E6NE 2001051500052 20010515 00052 2001 5 15 AU010380 4 20010422 G 3423 COMPASS BOEING 737 737377 NM COCKPIT FAULTY W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) BUBBLE IN COMPASS FLUID. FOUND DURING INSPECTION IAW AD/INST/9. 2 L 7 2 4F RT A16WE 2001051500053 20010515 00053 2001 5 15 AU010381 4 20010423 G 3423 COMPASS BOEING 737 737377 NM COCKPIT FAULTY W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) AIR BUBBLE IN STANDBY COMPASS. FOUND DURING INSPECTION IAWAD/INST/9. 2 L 7 2 4F RT A16WE 2001050700403 20010507 00403 GL 2001 5 7 AU010382 2 20010426 G 7250 6898785 SHAFT SKRSKY S76 S76A 8143006 NE ALLSN 250C 250C30 03013 GL TURBINE CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S 3464 CAG90756 (AUS) ENGINE GEARBOX POWER TAKEOFF SHAFT CRACKED. SUSPECT CAUSED BY OVERTIGHTENING OF THE POWER OUTPUT ADAPTER. 1 G 7 2 3U 3 U H1NE E1GL 2001051500054 20010515 00054 NM 2001 5 15 AU010383 1 20010424 G 5313 STRINGER BOEING 767 767204 NM GE CF6 CF680A 30025 NE FUSELAGE CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) STRINGER 32L LOCATED AT STN 1085 CRACKED. CRACK LENGTH 114.3MM(4.5IN). 2 L 7 2 4F 4 F RT A1NM E13NE 2001051500055 20010515 00055 2001 5 15 AU010385 4 20010423 G 2312 RADIO AIRBUS 320 A320211 3930320 EU CFMINT CFM56 CFM565A1 NE VHF SYSTEM FAILED W O OTHER O OTHER DE DESCENT 1 AU S (AUS) VHF SYSTEM FAULTY. 2 L 7 2 4F 4 F RT A28NM E29NE 2001051500056 20010515 00056 SO 2001 5 15 AU010386 1 20010402 G 2750 487377 SPRING PIPER PA32 PA32300 7103212 SO LYC O540 IO540K1A5 41532 EA HARTZL HCC2Y HCC2YK1 GL TE FLAPS BROKEN W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) FLAP RETURN SPRING FAILED AT ATTACHMENT HOOK. 1 L 7 1 3O 3 O A3SO 1E4 5 C P920 2001051500057 20010515 00057 NM 2001 5 15 AU010387 1 20010426 G 2751 2061141 INDICATOR BOEING 737 73733A 1384673 NM TE FLAPS FAULTY W O OTHER J WARNING INDICATION AP APPROACH 1 AU S (AUS) FLAP POSITION INDICATOR FAULTY. 2 L 7 2 4F RT A16WE 2001051500058 20010515 00058 CE 2001 5 15 AU010388 1 20010412 G 3260 7401CGE SWITCH CESSNA 402 402B 207590P CE CONT O520 TSIO520E 17040 SO MCAULY 3AF32C 3AF32C87 GL MLG INTERMITTENT W K NONE N FALSE WARNING LD LANDING 1 AU S (AUS) MAIN LANDING GEAR WARNING LIGHT DIMMER SWITCH INTERMITTENT IN OPERATION. 1 L 7 2 3O 3 O A7CE E8CE 5 C P22EA 2001051500059 20010515 00059 NE 2001 5 15 AU010389 2 20010423 G 7320 78639010 HMU EMB 120 EMB120 3260201 SO PWA 118 PW118A NE HAMSTD 14SF 14SF9 NE RT ENGIEN FAULTY W O OTHER E R J VIBRATION/BUFFET PARTIAL RPM/PWR LOSS WARNING INDICATION CR CRUISE 1 AU S (AUS) RT ENGINE HYDROMECHANICAL UNIT (HMU) FAULTY. 2 L 7 2 4T 4 T RT A31SO E20NE 6 N P11NE 2001080700080 20010807 00080 NM 2001 8 7 AUS20010391 1 20010430 G 5313 STRINGER BOEING 767 767277 NM GE CF6 CF680A 30025 NE FUSELAGE MAIN, L CORRODED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) STRINGER 39L LOCATED BELOW THE FLOOR IN THE AFT CARGO AREACORRODED BETWEEN BS 1285 AND BS 1307. 2 L 7 2 4F 4 F RT A1NM E13NE 2001080800001 20010808 00001 EU 2001 8 8 AUS20010392 1 20010425 G 2430 GENERATOR AIRBUS 320 A320* EU CFMINT CFM56 CFM565A1 NE DC GENERATING SY FAULTY W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) DC GENERATION SYSTEM FAULTY. 2 L 7 2 4F 4 F RT A46NM E29NE 2001080800002 20010808 00002 NM 2001 8 8 AUS20010393 1 20010426 G 2720 PCU BOEING 737 737376 NM CFMINT CFM56 CFM563C 13802 EU RUDDER CONTROL FAULTY W K NONE F FLT CONT AFFECTED CL CLIMB 1 AU S (AUS) RUDDER CONTROL SYSTEM FAULTY. NUMEROUS ITEMS IN THE CONTROL SYSTEM WERE REPLACED TO CORRECT THE PROBLEM. INVESTIGA TION IS CONTINUING INTO THE REPLACED ITEMS. ITEMS REPLACED WERE DFDR PNO 2100-4043-00, RUDDER PCU PNO 65C37053-9, STANDB Y RUDDERPCU PNO 1U1150-3 AND YAW DAMPER COUPLER PNO 4030952-906. 2 L 7 2 4F 4 F RT A16WE E21EU 2001080800003 20010808 00003 NM 2001 8 8 AUS20010394 1 20010424 G 7110 UL26237 FAIRING RROYCE RB211524G BOEING 747 747438 NM RROYCE RB211 RB211524G19 NE ENGINE COWLING SEPARATED W C ABORTED TAKEOFF E VIBRATION/BUFFET TO TAKEOFF 1 AU S 13461 13043 (AUS) NR 3 ENGINE LT AND RT GAS GENERATOR FAIRINGS PNO UL26237 AND PNO UL23239 SEPARATED FROM ENGINE. DAMAGE TO NR 3 ENG INE INTEGRATEDNOZZLE AREA AND RT C' FLAP. 2 L 7 4 4F 4 F RT A20WE E30NE 2001080700081 20010807 00081 SO 2001 8 7 AUS20010395 1 20010426 G 2430 460620 FILTER PIPER 460620 PIPER PA31 PA31350 7103110 SO LYC O540 TIO540J2BD 41532 EA HARTZL HCE3Y HCE3YR2 GL DC GENERATING SY INTERMITTENT W K NONE H ELECT. POWER LOSS-50 PC CR CRUISE 1 AU S (AUS) LH NOISE FILTER INTERMITTENT IN OPERATION. 1 L 7 2 3O 3 O A20SO E14EA 5 C P33EA 2001080800007 20010808 00007 NM 2001 8 8 AUS20010396 1 20010428 G 3260 SENSOR BOEING 737 737377 NM LANDING GEAR FAILED W A UNSCHED LANDING N FALSE WARNING CL CLIMB 1 AU S (AUS) AIR SENSING TEST CARD FAILED. 2 L 7 2 4F RT A16WE 2001080800016 20010808 00016 NM 2001 8 8 AUS20010398 1 20010429 G 3520 S417T40127 GENERATOR BOEING 737 737377 NM PASSENGER OXYGEN MISINSTALLED W K NONE W INADEQUATE Q C IN INSP/MAINT 1 AU S (AUS) OXYGEN GENERATORS LOCATED IN THE FLIGHT ATTENDANT SERVICE UNITADJACENT TO CABIN DOORS L1 AND L2 HAD THE RELASE PIN S LOCATED INTHE SAFETY PIN HOLES. PERSONNEL/MAINTENANCE ERROR. 2 L 7 2 4F RT A16WE 2001080700082 20010807 00082 NM 2001 8 7 AUS20010399 1 20010502 G 3230 EO3600491750S SPRING ROTOL ACTUATOR DHAV DHC8 DHC8102 2809003 NM PWA 120 PW120A NE HAMSTD 14SF 14SF7 NE LANDING GEAR RET FAILED W K NONE O OTHER IN INSP/MAINT 1 AU S DCL30093 (AUS) UPLOCK ACTUATOR SPRING (1OFF2) BROKEN AT THE BASE OF THE UPPERATTACHMENT HOOK. 2 H 7 2 4T 4 T RT A13NM E20NE 6 C P7NE 2001080800018 20010808 00018 NM 2001 8 8 AUS20010400 1 20010501 G 7110 13453 PANEL RROYCE RB211524H36 BOEING 767 767338 1385151 NM RROYCE RB211 RB211524* NE ENGINE COWLING SEPARATED W K NONE O OTHER IN INSP/MAINT 1 AU S 11290 13453 (AUS) NR 1 ENGINE ACOUSTIC PANEL TRAILING EDGE SECTION SEPARATED FROMTHE AIRCRAFT. NR 5 BLOCKER DOOR REPLACED DUE TO DAM AGE. NR 7, NR 8 AND NR 9 BLOCKER DOORS HAD MINOR SKIN DAMAGE. NR 7 DEFLECTOR BOX CASCADE VANE DAMAGED. 2 L 7 2 4F 4 F RT A1NM E12EU 2001080800020 20010808 00020 EU 2001 8 8 AUS20010401 1 20010416 G 2450 SPLICE BAG BAE146 BAE146200A 1500266 EU LYC ALF502 ALF502R5 41580 NE AC POWER DIST OVERHEATED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) GENERATOR FEEDER INLINE SPLICE OVERHEATING. FOUND DURINGINSPECTION IAW TSI 146-24-003. 2 H 7 4 4F 4 F RT A49EU E6NE 2001080700083 20010807 00083 NM 2001 8 7 AUS20010402 1 20010503 G 3230 EO3600491750S SPRING ROTOL ACTUATOR DHAV DHC8 DHC8102 2809003 NM PWA 120 PW120A NE HAMSTD 14SF 14SF7 NE LANDING GEAR RET BROKEN W K NONE O OTHER IN INSP/MAINT 1 AU S DCL30293DCL2 (AUS) LH AND RH MAIN LANDING GEAR UPLOCK ACTUATOR SPRINGS BROKEN. 2 H 7 2 4T 4 T RT A13NM E20NE 6 C P7NE 2001080800021 20010808 00021 NM 2001 8 8 AUS20010403 1 20010502 G 5730 SKIN BOEING 737 73733A 1384673 NM WING CORRODED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) LT AND RT WING UPPER SKIN LOWER SURFACES AND TOP STRINGERS IN AREA BETWEEN WS557 AND WS583. CORROSION ALSO EVIDENT ON RH REAR SPAR LOWER FLANGE IN AREA BETWEEN WS576 AND WS580. 2 L 7 2 4F RT A16WE 2001080800022 20010808 00022 EU 2001 8 8 AUS20010404 1 20010420 G 5320 D5337061320200 FITTING AIRBUS 320 A320* EU CFMINT CFM56 CFM565A1 NE FUSELAGE CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) MAIN LANDING GEAR DOOR ACTUATOR FITTINGS (KEEL BEAM) CRACKED. CRACKS FOUND IN LH AFT FITTING PNO D5337061320200 RH AFT AND LH FORWARD FITTINGS PNO D5337961320300. CRACKS EMANATE FROM THE TOPTWO FASTENER HOLES IN THE VERTICAL FLANGE. F OUND DURING INSPECTION IAW ER A32-53-40-9C (SB A320-53-1135). 2 L 7 2 4F 4 F RT A46NM E29NE 2001080700084 20010807 00084 WP 2001 8 7 AUS20010405 1 20010421 G 7920 R14 FILTER LYC O320B2C ROBSIN R22 R22 7640102 WP LYC O320 O320B2C 41508 EA ENGINE OIL DISTR LEAKING W K NONE E K VIBRATION/BUFFET FLUID LOSS TO TAKEOFF 1 AU S (AUS) ENGINE OIL FILTER O' RING SEAL POPPED OUT ALLOWING OIL TO BE PUMPED OVERBOARD. THE RYCO R14 OIL FILTER IS FITTED T O SOME R22 AIRCRAFT BY AN ENGINEERING ORDER. 1 G 7 1 3O 3 O H10WE E274 2001080700085 20010807 00085 NM 2001 8 7 AUS20010406 1 20010430 G 7110 LK73708 PANEL RROYCE RB211524D419 BOEING 747 747238B 1384828 NM RROYCE RB211 RB211524D419 54555 NE ENGINE COWLING S SEPARATED W K NONE O D OTHER INFLIGHT SEPARATION IN INSP/MAINT 1 AU S 7466 12679 (AUS) NO4 ENGINE VIGV CONTROLLER ACCESS PANEL SEPARATED. DAMAGE CAUSEDTO THE REAR FAN CASE ACOUSTIC LINER. 2 L 7 4 4F 4 F A20WE E12EU 2001080800023 20010808 00023 EA 2001 8 8 AUS20010407 2 20010430 G 7310 689 LINE PILATS PC6 PC6 7090102 EU PWA PT6 PT6A20 52043 EA HARTZL HCB3T HCB3TN3 GL FUEL DIST CONTAMINATED W O OTHER E X VIBRATION/BUFFET ENGINE FLAMEOUT LD LANDING 1 AU S (AUS) ENGINE FAILED DUE TO LACK OF FUEL. INVESTIGATION FOUND AIR IN THE FUEL LINE BETWEEN THE FUEL HEATER AND THE FCU. S USPECT CAUSED BYPOOR VENTING OF THE FUEL HEADER TANK. AD/PC6/42 (PC-6-SB-171) ISENTERED INTO THE LOG BOOK AS HAVING BEEN COMPLIED WITH BUT HASNOT BEEN CARRIED OUT. THE AD AND SB INTRODUCES A VENTING SYSTEM TO THE HEADER TANK. PERSONNEL/MAIN TENANCE ERROR. 1 H 7 1 3O 3 T 7A15 E4EA 6 C P15EA 2001080700086 20010807 00086 SO 2001 8 7 AUS20010408 2 20010510 G 8550 CH48109 FILTER CONT TSIO520VB CESSNA 402 402C 207590R CE CONT O520 TSIO520VB 17040 SO MCAULY 3AF32C 3AF32C505 GL RECIPROCATING EN FAULTY W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) ENGINE OIL FILTER ELEMENT END CAP MISSING. 1 L 7 2 3O 3 O A7CE E8CE 5 C P22EA 2001080800024 20010808 00024 NE 2001 8 8 AUS20010409 3 20010503 G 6110 PROPELLER BAG JETSTM JETSTM3201 1500217 EU GARRTT TPE331 TPE33112UHR WP MCAULY 4HFR34 4HFR34C653 NE RIGHT OUT OF BALANCE W O OTHER E VIBRATION/BUFFET CL CLIMB 1 AU S (AUS) RT PROPELLER OUT OF BALANCE. PROPELLER HAD BEEN RECENTLY REPLACED BUT HAD NOT BEEN BALANCE CHECKED FOLLOWING FITME NT. 2 L 7 2 4T 4 T RT A56EU E4WE 6 C 3PNE 2001080700087 20010807 00087 2001 8 7 AUS20010410 4 20010513 G 3416 WL1107AMMS4 ALTIMETER BAC 146 146200A 1500266 EU LYC ALF502 ALF502R5 41580 NE ALTIMETER, BAROM FAILED W K NONE I FLT. ATTITUDE INST. CL CLIMB 1 AU S 24008 AF756 (AUS) CAPTAINS ALTIMETER FAILED. 2 H 7 4 4F 4 F A49EU E6NE 2001080800025 20010808 00025 SO 2001 8 8 AUS20010411 1 20010507 G 3260 SWITCH PIPER PA31 PA31350 7103110 SO LYC O540 TIO540J2BD 41532 EA HARTZL HCE3Y HCE3YR2 GL MLG OUT OF ADJ W K NONE N FALSE WARNING CL CLIMB 1 AU S (AUS) NOSE LANDING GEAR UP LIMIT SWITCH OUT OF ADJUSTMENT. 1 L 7 2 3O 3 O A20SO E14EA 5 C P33EA 2001080800026 20010808 00026 CE 2001 8 8 AUS20010412 1 20010423 G 5320 MS21047L3 NUT CESSNA 303 T303 2073820 CE CONT O520 TSIO520AE 17040 SO MCAULY 3AF32C 3AF32C506 GL FUEL CELL WRONG PART W K NONE W INADEQUATE Q C IN INSP/MAINT 1 AU S (AUS) LH WING FUEL TANK LEAKING. INVESTIGATION FOUND THAT THE FUEL TANK PANEL ANCHOR NUTS WERE THE INCORRECT TYPE. THE C ORRECT NUTS PNO NAS1473A3 ANCHOR NUTS ARE SEALED BUT THE FITTED ANCHOR NUTS PNO MS21047L3 ARE UNSEALED. MANUFACTURING ER ROR. UNAPPROVED PART. PERSONNEL/MAINTENANCE ERROR. 1 L 7 2 3O 3 O A34CE E8CE 5 C P57GL 2001080700088 20010807 00088 NM 2001 8 7 AUS20010413 1 20010511 G 6322 A1851 BRACKET ROBSIN R22 R22BETA NM LYC O320 O320B2C 41508 EA ROTORCRAFT COOLI CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) COOLING FAN SCROLL BRACKET CRACKED. CRACK ORIGINATED AT A SIDESCREWDRIVER NOTCH. FOUND DURING INSPECTION IAW AD/R2 2/24. 1 G 7 1 3O 3 O H10WE E274 2001080800027 20010808 00027 CE 2001 8 8 AUS20010414 1 20010504 G 5720 RIVET CESSNA 337 337 2075702 CE CONT O360 IO360D 17025 SO WING LOOSE W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) LT WING STRUT ATTACHMENT RIB TO OUTBOARD TIP RIVETS LOOSE AND MISSING. LEADING EDGE HAD BEEN REPLACED IN 1972. 1 H 7 2 3O 3 O A6CE E1CE 2001080800029 20010808 00029 CE 2001 8 8 AUS20010415 1 20010504 G 3246 WHEEL CESSNA 337 337 2075702 CE CONT O360 IO360D 17025 SO MLG CORRODED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) NOSE AND MAIN WHEEL HALVES (5OFF6) CORRODED WITH BEARINGS SPINNING IN THE WHEEL HALVES. CORROSION ALSO FOUND IN AR EA OF THE FELT SEALS. 1 H 7 2 3O 3 O A6CE E1CE 2001080800030 20010808 00030 SO 2001 8 8 AUS20010416 2 20010504 G 8550 FILTER CESSNA 337 337 2075702 CE CONT O360 IO360D 17025 SO ENGINE CONTAMINATED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) METAL CONTAMINATION OF THE REAR ENGINE OIL FILTER. SUSPECT MAIN BEARING FAILURE. 1 H 7 2 3O 3 O A6CE E1CE 2001080800032 20010808 00032 CE 2001 8 8 AUS20010417 1 20010504 G 5311 FRAME CESSNA 337 337 2075702 CE CONT O360 IO360D 17025 SO FUSELAGE CORRODED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) RT ROOF SUPPORT FORMER LOWER EDGE CONTAINED INTERGRANNULARCORROSION. 1 H 7 2 3O 3 O A6CE E1CE 2001080800033 20010808 00033 CE 2001 8 8 AUS20010418 1 20010504 G 5310 RIVET CESSNA 337 337 2075702 CE CONT O360 IO360D 17025 SO FUSELAGE DAMAGED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) NOSE LANDING GEAR WHEEL PAN/FIREWALL STRUCTURE RIVETS PULLED. FAILED RIVETS LOCATED IN THE AFT LT TOP CORNER. 1 H 7 2 3O 3 O A6CE E1CE 2001080800034 20010808 00034 CE 2001 8 8 AUS20010419 1 20010504 G 2720 TORQUE TUBE CESSNA 337 337 2075702 CE CONT O360 IO360D 17025 SO RUDDER CONTROL DAMAGED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) RUDDER PEDAL TORQUE TUBE CLAMP SUPPORT STRUCTURE CRACKED ANDWORKING. LOOSE RIVETS AND DAMAGE CAUSED BY BELLCRANK. 1 H 7 2 3O 3 O A6CE E1CE 2001080800057 20010808 00057 CE 2001 8 8 AUS20010420 1 20010504 G 2823 SELECTOR VALVE CESSNA 337 337 2075702 CE CONT O360 IO360D 17025 SO FUEL SYSTEM FAULTY W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) FRONT AND REAR FUEL SELECTORS FAULTY. FUEL CAN'T BE TURNED OFF. SUSPECT FAULTY SEALS. 1 H 7 2 3O 3 O A6CE E1CE 2001080800067 20010808 00067 EU 2001 8 8 AUS20010421 1 20010514 G 2621 57333012 FIRE BOTTLE BAG BAE146 BAE146100A 1500260 EU LYC ALF502 ALF502R5 41580 NE NR 3 ENGINE MISINSTALLED W K NONE W INADEQUATE Q C IN INSP/MAINT 1 AU S (AUS) NR 3 ENGINE FIRE BOTTLE FIRING SWITCH WIRING CONTAINED TWO INLINESPLICES FITTED WITH SMALLER GAUGE WIRES. UNAPPROV ED MODIFICATION. PERSONNEL/MAINTENANCE ERROR. 2 H 7 4 4F 4 F RT A49EU E6NE 2001080700089 20010807 00089 CE 2001 8 7 AUS20010422 1 20010515 G 2701 07606331 BEARING CESSNA 182 R182 2072734 CE LYC O540 O540J3C5 41532 EA MCAULY 2D34C B2D34C214 GL CONTROL COLUMN S FAILED W K NONE F FLT CONT AFFECTED CR CRUISE 1 AU S 3847 (AUS) COPILOTS CONTROL COLUMN BEARING BLOCK NEEDLE ROLLER BEARING WORNOUT AND THE ROLLERS DISLODGED DUE TO LACK OF LUBRI CATION. THE ROLLER BEARING SHAFT GROOVED FROM VIBRATION INDUCED WEAR. 1 H 7 1 3O 3 O RT 3A13 E295 5 C P7EA 2001080800080 20010808 00080 2001 8 8 AUS20010423 4 20010507 G 3425 7003360941 INDICATOR DHAV DHC8 DHC8102 2809003 NM PWA 120 PW120A NE HAMSTD 14SF 14SF7 NE AHRS FAILED W O OTHER F FLT CONT AFFECTED CL CLIMB 1 AU S (AUS) NR 1 ATTITUDE HEADING REFERENCE SYSTEM (AHRS) FAILED. 2 H 7 2 4T 4 T RT A13NM E20NE 6 C P7NE 2001080800081 20010808 00081 2001 8 8 AUS20010424 4 20010503 G 3416 6223890002 TRANSCEIVER BAG BAE146 BAE146100A 1500260 EU LYC ALF502 ALF502R5 41580 NE ALTIMETER INTERMITTENT W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) RADIO ALTIMETER TRANSCEIVER INTERMITTENT OPERATION. INVESTIGATION FOUND THE FAULT WAS DUE TO A STRAY VOLTAGE ON A SPARE PIN IN THETRANSCEIVER DUE TO A WIRE FITTED BY A PREVIOUS OPERATOR. THEMODIFICATION WAS NOT NOTIFIED TO THE MANUFAC TURER AND THE WIRINGDIAGRAMS WERE NOT AMENDED. PERSONNEL/MAINTENANCE ERROR. 2 H 7 4 4F 4 F RT A49EU E6NE 2001080800083 20010808 00083 SO 2001 8 8 AUS20010425 1 20010507 G 5510 717002 HINGE PIPER PA31 PA31350 7103110 SO LYC O540 TIO540J2BD 41532 EA HARTZL HCE3Y HCE3YR2 GL HORIZONTAL STAB MISINSTALLED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) LT AND RT HORIZONTAL STABILISER OUTBOARD HINGES FITTED WITH ONLYTWO RIVETS ON THE TOP AND BOTTOM WHEN THE PIPER MO DIFICATION KITPNO 766-646 WHEN THE CORRECT NUMBER SHOULD BE FOUR RIVETS.PERSONNEL/MAINTENANCE ERROR. 1 L 7 2 3O 3 O A20SO E14EA 5 C P33EA 2001080800084 20010808 00084 CE 2001 8 8 AUS20010426 1 20010507 G 5551 12326231 FITTING CESSNA 206 U206F 2073333 CE CONT O520 IO520F 17032 SO MCAULY 3A32C D3A32C90 GL HORIZONTAL STAB CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) LT AFT TAILPLANE ATTACHMENT REINFORCEMENT CRACKED. 1 H 7 1 3O 3 O A4CE E5CE 5 C P21EA 2001080700090 20010807 00090 EU 2001 8 7 AUS20010427 1 20010506 G 5553 13708F2 HINGE BAG JETSTM JETSTM3201 1500217 EU GARRTT TPE331 TPE33112UA 01514 WP MCAULY 4HFR34 4HFR34C653 NE VERTICAL STABILI BROKEN W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) RUDDER CENTRE HINGE BRACKET CENTRE LUG FAILED DUE TO CORROSION. 2 L 7 2 4T 4 T RT A56EU E4WE 6 C 3PNE 2001080700091 20010807 00091 EU 2001 8 7 AUS20010428 1 20010506 G 5554 1379036F403 HINGE BAG JETSTM JETSTM3201 1500217 EU GARRTT TPE331 TPE33112UA 01514 WP MCAULY 4HFR34 4HFR34C653 NE RUDDER/TAB, ATTA CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) RUDDER CENTRE HINGE CRACKED. SUSPECT CAUSED BY EXTRA LOADS DUE TO FAILURE OF THE FIN MOUNTED HALF OF THE HINGE. SE E MDR 01/0427. 2 L 7 2 4T 4 T RT A56EU E4WE 6 C 3PNE 2001080700092 20010807 00092 NM 2001 8 7 AUS20010429 1 20010424 G 6310 A1843 BEARING ROBSIN R22 R22BETA NM LYC O320 O320B2C 41508 EA ENGINE/TRANSMISS SPALLED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) UPPER BEARING ROUGH. ONE BALL BADLY SPALLED. 1 G 7 1 3O 3 O H10WE E274 2001080700093 20010807 00093 EU 2001 8 7 AUS20010430 1 20010504 G 5711 D53 FLANGE PARTEN P68B PARTEN P68 P68B EU LYC O360 IO360A1B6 41514 EA HARTZL HCC2Y HCC2YK2 GL WING SPAR CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S D53 (AUS) AFT WING SPAR WEB FLANGE CRACKED ON THE LH SIDE IN THE AREA OUTBOARD OF THE ATTACHMENT FITTING. FOUND DURING INSPE CTION IAW AD/P68/22, AD/P68/45 AND SB 65. 1 H 7 2 3O 3 O A31EU 1E10 5 C P920 2001080700094 20010807 00094 CE 2001 8 7 AUS20010431 1 20010115 G 5347 121040821 SEAT TRACK CESSNA 206 U206F 2073333 CE CONT O520 IO520F 17032 SO MCAULY 3A32C D3A32C90 GL SEAT/CARGO ATTAC CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) SEAT TRACKS CRACKED THROUGH STOP PIN HOLES. 1 H 7 1 3O 3 O A4CE E5CE 5 C P21EA 2001080700095 20010807 00095 CE 2001 8 7 AUS20010432 1 20010115 G 5312 12121365 BULKHEAD CESSNA 206 U206F 2073333 CE CONT O520 IO520F 17032 SO MCAULY 3A32C D3A32C90 GL FUSELAGE MAIN, B CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) HORIZONTAL STABILISER ATTACHMENT BULKHEAD CRACKED THROUGH TOP RIVET HOLE. CRACK LENGTH 19.05MM (0.75IN). 1 H 7 1 3O 3 O A4CE E5CE 5 C P21EA 2001080700096 20010807 00096 CE 2001 8 7 AUS20010433 1 20010115 G 5753 12210107 FLAP TRACK CESSNA 206 U206F 2073333 CE CONT O520 IO520F 17032 SO MCAULY 3A32C D3A32C90 GL TRAILING EDGE FL CORRODED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) FLAP TRACKS CONTAINED EXFOLIATION AND INTERGRANNULAR CORROSIONLOCATED IN THE FORWARD END OF THE LOWER SLOT. 1 H 7 1 3O 3 O A4CE E5CE 5 C P21EA 2001080800086 20010808 00086 NE 2001 8 8 AUS20010434 2 20010103 G 8520 3592 LINK ROD DHAV DHC2 DHC2MK1 2800102 EA PWA R985 R985AN14B 52008 NE ENGINE BROKEN W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) NR 9 CYLINDER LINKROD BROKEN. SEVERE INTERNAL DAMAGE PREVENTED ESTABLISHING THE CAUSE OF THE FAILURE. 1 H 7 1 3R 3 R A806 5E1 2001080700097 20010807 00097 EA 2001 8 7 AUS20010435 2 20010503 G 7310 L142368A HOSE LYC LTIO540J2BD PIPER PA31 PA31350 7103110 SO LYC O540 LTIO540J2BD 41533 EA HARTZL HCE3Y HCE3YR2 GL ENGINE FUEL DIST FAULTY W K NONE O OTHER IN INSP/MAINT 1 AU S L142368A (AUS) FUEL HOSES LOCATED BETWEEN THE FCU AND THE FLOW DIVIDER DID NOT HAVE FIRESLEEVES FITTED. PERSONNEL/MAINTENANCE ERR OR. 1 L 7 2 3O 3 O A20SO E14EA 5 C P33EA 2001080700098 20010807 00098 EU 2001 8 7 AUS20010437 1 20010506 G 5553 13708F1 BRACKET BAG JETSTM JETSTM3201 1500217 EU GARRTT TPE331 TPE33112UA 01514 WP MCAULY 4HFR34 4HFR34C653 NE VERTICAL STABILI CORRODED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) RUDDER HINGE BRACKET CONTAINED EXFOLIATION CORROSION IN THE AREAOF THE BONDING LEAD ATTACHMENT. 2 L 7 2 4T 4 T RT A56EU E4WE 6 C 3PNE 2001080800087 20010808 00087 SO 2001 8 8 AUS20010438 1 20010401 G 3220 LANDING GEAR PIPER PA31 PA31 7103102 SO LYC O540 TIO540A2C 41532 EA HARTZL HCE3Y HCE3YR2 GL NLG COLLAPSED W O OTHER O OTHER NR NOT REPORTED 1 AU S (AUS) NOSE LANDING GEAR COLLAPSED. INSPECTION COULD FIND NO DEFECTS WITH THE SYSTEM. SUSPECT INCORRECT TECHNIQUE. 1 L 7 2 3O 3 O A20SO E14EA 5 C P33EA 2001080800089 20010808 00089 EU 2001 8 8 AUS20010439 1 20010504 G 7920 70009K000V332A HOSE AGUSTA 206AGS 206AAGUSTA 0260301 EU ALLSN 250C 250C20B 03013 GL ENGINE OIL LEAKING W A UNSCHED LANDING E K VIBRATION/BUFFET FLUID LOSS CR CRUISE 1 AU S (AUS) ENGINE OIL HOSE LEAKING IN AN AREA APPROXIMATELY 100MM (4IN) FROM THE FORWARD UNION END. 1 G 7 1 3U 3 U EXPA1G71 E4CE 2001080700099 20010807 00099 SO 2001 8 7 AUS20010440 1 20010427 G 7170 CCA1550 DRAIN VALVE LYC O320D3G PIPER PA28 PA28161 7102803 SO LYC O320 O320D3G 41508 EA SNSNCH 74D 74DM EA ENGINE DRAINS LEAKING W K NONE O OTHER TO TAKEOFF 1 AU S (AUS) AIRCRAFT RETURNED TO AIRSTRIP AFTER TAKEOFF FOR A FORCED LANDING. FUEL STAINS FOUND DOWN THE SIDE OF THE AIRCRAFT EMANATING FROMTHE DRAIN VALVE. INSPECTION OF THE VALVE COULD FIND NO DEFECTSAND THE VALVE WAS CLOSED. ENGINE DRAIN VALVE SUSPECT LEFT PARTIALLY OPEN ALLOWING FUEL LEAKAGE AND THEN CLOSED ON LANDING. 1 L 7 1 3O 3 O 2A13 E274 5 N P88614 2001080800091 20010808 00091 EU 2001 8 8 AUS20010441 1 20010420 G 5343 D5337061320300 FITTING AIRBUS 320 A320* EU CFMINT CFM56 CFM565A1 NE LANDING GEAR CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) MAIN LANDING GEAR DOOR ACTUATOR FITTINGS (3OFF4) CRACKED FROM THE TOP TWO FASTENER HOLES IN THE VERTICAL FLANGE. F ITTINGS CRACKED ARE PNO D5337061320200 (LH AFT) AND PNO D5337061320300 (RH AFTAND LH FORWARD). FOUND DURING INSPECTION I AW ER A32-53-40-9C(SB A320-53-1135). 2 L 7 2 4F 4 F RT A46NM E29NE 2001080700100 20010807 00100 SO 2001 8 7 AUS20010442 1 20010321 G 3397 WIRE BA08006281 EMB 120 EMB120 3260201 SO PWA 118 PW118A NE HAMSTD 14RF 14RF9 NE PASSENGER COMPAR WORN W K NONE B SMOKE/FUMES/ODORS/SPARKS IN INSP/MAINT 1 AU S (AUS) CABIN LIGHTING SYSTEM INVERTER OUTPUT WIRING CHAFING AGAINST GASPER AIR DUCT CAUSING THE WIRING LOOM AND DUCT INSU LATION TO BURN. 2 L 7 2 4T 4 T RT A31SO E20NE 6 C P11NE 2001080800093 20010808 00093 NM 2001 8 8 AUS20010443 1 20010417 G 3520 DOOR BOEING 737 737377 NM PASSENGER OXYGEN MISINSTALLED W K NONE W INADEQUATE Q C IN INSP/MAINT 1 AU S (AUS) FORWARD TOILET OXYGEN SYSTEM DROP-DOWN DOOR HAD WHITE SILASTICMATERIAL ACROSS THE FORWARD OUTBOARD CORNER PREVENTI NG IT FORM OPENING. THE SILASTIC HAD BEEN USED ON THE TOILET CEILING PANEL AND HAD BEEN SMEARED ACROSS THE OXYGEN PANEL DOOR. 2 L 7 2 4F RT A16WE 2001080700101 20010807 00101 EU 2001 8 7 AUS20010444 1 20010407 G 2822 PUMP FOKKER F28 F28MK1000 4990808 EU RROYCE SPEY SPEY55515 54521 EU FUEL BOOST PUMP FAILED W K NONE O OTHER TO TAKEOFF 1 AU S (AUS) AFT BOOST PUMP FAILED. CIRCUIT BREAKER RESET AND PUMP OPERATEDNORMALLY SINCE. 2 L 7 2 4F 4 F RT A20EU E2EU 2001080800095 20010808 00095 NM 2001 8 8 AUS20010445 1 20010430 G 3230 658005118 DRAG BRACE BOEING 737 73733A 1384673 NM LANDING GEAR CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S 21713 (AUS) NOSE LANDING GEAR UPPER DRAG BRACE CRACKED AT RETRACTION ACTUATOR ATTACHMENT. CRACK WAS DETECTED VISUALLY. 2 L 7 2 4F RT A16WE 2001080700102 20010807 00102 EU 2001 8 7 AUS20010446 1 20010417 G 7830 22100009519 CABLE PWA PW4152 AIRBUS 310 A310324 3930206 EU PWA 4152 PW4152 NE THRUST REVERSER DISTORTED W K NONE O OTHER LD LANDING 1 AU S (AUS) NO1 ENGINE THRUST REVERSER MASTER ACTUATOR FLEXIBLE CABLE DRIVE TO SPLITTER GEARBOX KINKED AND TWISTED. 2 L 7 2 4F RT A35EU E24NE 2001080700103 20010807 00103 EU 2001 8 7 AUS20010447 1 20010430 G 3260 DOOR FOKKER F28 F28MK4000 4990810 EU RROYCE SPEY SPEY55515 54521 EU LANDING GEAR POS FALSE INDICATION W K NONE O N OTHER FALSE WARNING NR NOT REPORTED 1 AU S (AUS) RH MAIN LANDING GEAR DOOR INDICATIONS INCORRECT. INVESTIGATIONCOULD FIND NO FAULT WITH THE SYSTEM. DEFECT NOT CONF IRMED. 2 L 7 2 4F 4 F RT A20EU E2EU 2001080700104 20010807 00104 EU 2001 8 7 AUS20010448 1 20010430 G 3242 50002685 BRAKE FOKKER F28 F28MK4000 4990810 EU RROYCE SPEY SPEY55515 54521 EU BRAKE LEAKING W K NONE O K OTHER FLUID LOSS IN INSP/MAINT 1 AU S 58 DEC6976 (AUS) NO2 BRAKE UNIT LEAKING FLUID. 2 L 7 2 4F 4 F RT A20EU E2EU 2001080800096 20010808 00096 EA 2001 8 8 AUS20010450 2 20010501 G 8530 LW12993 CYLINDER PIPER PA32 PA32R300 7103213 SO LYC O540 IO540K1G5 41532 EA HARTZL HCC2Y HCC2YK1 GL ENGINE LEAKING W K NONE K FLUID LOSS IN INSP/MAINT 1 AU S 145 (AUS) ENGINE CYLINDERS IN POOR CONDITION. OIL LEAKING PAST VALVE STEMS. 1 L 7 1 3O 3 O A3SO 1E4 5 C P920 2001080700105 20010807 00105 EA 2001 8 7 AUS20010451 2 20010420 G 8520 71907 WASHER LYC IO540E1B5 GULSTM 500 500S 0141107 SW LYC O540 IO540E1B5 41532 EA HARTZL HCC3Y HCC3YR2 NE RECIPROCATING EN FAILED W K NONE E VIBRATION/BUFFET CR CRUISE 1 AU S L1111148 (AUS) RH ENGINE COUNTERWEIGHT RETAINING WASHER PNO 71907 HAD FAILED ALLOWING THE COUNTERWEIGHT ROLLER PNO 72797 TO MIGRA TE ANDCONTACT NO5 CYLINDER CONNECTING ROD AND CAUSING IT TO FAIL WHICHCAUSED SEVERE DAMAGE TO THE CRANKCASE. THE RETAINI NG CIRCLIPPNO LW14820 REMAINED IN POSITION. 1 H 7 2 3O 3 O 6A1 1E4 5 C P25EA 2001080800098 20010808 00098 EU 2001 8 8 AUS20010452 1 20010430 G 3241 95427193 SENSOR FOKKER F28 F28MK1000 4990808 EU RROYCE SPEY SPEY55515 54521 EU WHEEL SPEED FAILED W O OTHER O OTHER NR NOT REPORTED 1 AU S 351 JUL74569 (AUS) NR 2 WHEEL SPEED GENERATOR FAILED. 2 L 7 2 4F 4 F RT A20EU E2EU 2001080700106 20010807 00106 EA 2001 8 7 AUS20010453 1 20010417 G 2432 CONNECTOR DHAV DHC6 DHC6 2802606 EA BATTERY/CHARGER MELTED W K NONE H ELECT. POWER LOSS-50 PC NR NOT REPORTED 1 AU S (AUS) BATTERY SHUNT GROUND CONNECTION MELTED. 1 H 7 2 3T RT A9EA 2001080700107 20010807 00107 EU 2001 8 7 AUS20010455 1 20010505 G 3260 GC1016 RELAY FOKKER F28 F28MK1000 4990808 EU RROYCE SPEY SPEY55515 54521 EU LANDING GEAR POS FAULTY W K NONE O OTHER CL CLIMB 1 AU S (AUS) RH GROUND/FLIGHT RELAY FAULTY. LH AND RH MLG GROUND FLIGHTSWITCHES CONTAMINATED. 2 L 7 2 4F 4 F RT A20EU E2EU 2001080700108 20010807 00108 CE 2001 8 7 AUS20010456 1 20010406 G 5343 07900065 BRACKET CESSNA 185 A185F 2072821 CE CONT O520 IO520D 17032 SO MCAULY D3A34 D3A34C403 GL LANDING GEAR ATT CORRODED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) MAIN LANDING GEAR ATTACHMENT BRACKET SEVERELY CORRODED. 1 H 7 1 3O 3 O 3A24 E5CE 5 C P47GL 2001080700109 20010807 00109 CE 2001 8 7 AUS20010457 1 20010406 G 5343 07900066 BRACKET CESSNA 185 A185F 2072821 CE CONT O520 IO520D 17032 SO MCAULY D3A34 D3A34C403 GL LANDING GEAR ATT CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) MAIN LANDING GEAR ATTACHMENT BRACKET CRACKED. MLG LEG LOOSE ATWEDGES. 1 H 7 1 3O 3 O 3A24 E5CE 5 C P47GL 2001080700110 20010807 00110 NM 2001 8 7 AUS20010458 1 20010405 G 6510 A0413 ARM ROBSIN TAILCONE ROBSIN R22 R22BETA NM LYC O320 O320B2C 41508 EA TAIL ROTOR DRIVE FAILED W K NONE F FLT CONT AFFECTED NR NOT REPORTED 1 AU S 1057 (AUS) TAIL ROTOR DRIVESHAFT DAMPENER ARM FAILED ALLOWING TAIL ROTOR DRIVESHAFT TO WHIP AND BREAK AND CAUSING DESTRUCTION OF THE TAILCONE ASSEMBLY PNO A023-20. 1 G 7 1 3O 3 O H10WE E274 2001080800100 20010808 00100 EU 2001 8 8 AUS20010459 1 20010505 G 3260 SWITCH FOKKER F28 F28MK1000 4990808 EU RROYCE SPEY SPEY55515 54521 EU LANDING GEAR STUCK W O OTHER O OTHER CL CLIMB 1 AU S (AUS) MAIN LANDING GEAR GROUND/FLIGHT SWITCHES STICKY. 2 L 7 2 4F 4 F RT A20EU E2EU 2001080800102 20010808 00102 EU 2001 8 8 AUS20010461 2 20010508 G 7200 ENGINE FOKKER F28 F28MK4000 4990810 EU RROYCE SPEY SPEY55515 54521 EU NACELLE MALFUNCTIONED W C ABORTED TAKEOFF E R VIBRATION/BUFFET PARTIAL RPM/PWR LOSS TO TAKEOFF 1 AU S (AUS) INCORRECT TAKEOFF THRUST SET BY PILOT. PERSONNEL ERROR. 2 L 7 2 4F 4 F RT A20EU E2EU 2001080800106 20010808 00106 NM 2001 8 8 AUS20010463 1 20010505 G 7331 AS21515 BOLT RROYCE R211524D419 BOEING 747 747SP38 NM RROYCE RB211 RB211524D419 54555 NE FLOW INDICATOR WRONG PART W O OTHER K FLUID LOSS NR NOT REPORTED 1 AU S 6100 12647 (AUS) NR 2 ENGINE FUEL FLOW TRANSMITTER INLET GASKET LEAKING. LOOSEBOLTS RETIGHTENED BUT THE LEAK CONTINUED. FURTHER INV ESTIGATION FOUND THAT THE MOUNTING BOLTS WERE PNO AS21515 INSTEAD OF THE CORRECT PNO AS21514. FITMENT OF THE INCORRECT B OLTS HAD DAMAGED THE THREADS IN THE TRANSMITTER REQUIRING REPLACEMENT. UNAPPROVEDPART. PERSONNEL/MAINTENANCE ERROR. 2 L 7 4 4F 4 F RT A20WE E12EU 2001080700111 20010807 00111 EU 2001 8 7 AUS20010464 1 20010505 G 3230 LANDING GEAR FOKKER F28 F28MK1000 4990808 EU RROYCE SPEY SPEY55515 54521 EU LANDING GEAR RET FAULTY W K NONE O OTHER CL CLIMB 1 AU S (AUS) LANDING GEAR WOULD NOT RETRACT. 2 L 7 2 4F 4 F RT A20EU E2EU 2001080700112 20010807 00112 EU 2001 8 7 AUS20010465 1 20010511 G 2752 BOLT FOKKER F28 F28MK4000 4990810 EU RROYCE SPEY SPEY55515 54521 EU TRAILING EDGE FL SHEARED W K NONE F K FLT CONT AFFECTED FLUID LOSS CL CLIMB 1 AU S (AUS) FLAP MOTOR ASSEMBLY BODY BOLT SHEARED AND BODY HALVES SEPARATED AT JOINT. LOSS OF HYDRAULIC FLUID. 2 L 7 2 4F 4 F RT A20EU E2EU 2001080700113 20010807 00113 EU 2001 8 7 AUS20010466 1 20010505 G 3220 200725209LOWER TORQUE LINK FOKKER F28 F28MK4000 4990810 EU RROYCE SPEY SPEY55515 54521 EU NOSE/TAIL LANDIN CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S DCS6809LOWER (AUS) NOSE LANDING GEAR LOWER TORQUE LINK CRACKED IN GREASE NIPPLEHOLE. FOUND USING VISUAL INSPECTION AND CONFIRMED USIN G EDDYCURRENT INSPECTION. 2 L 7 2 4F 4 F RT A20EU E2EU 2001080700114 20010807 00114 EU 2001 8 7 AUS20010468 1 20010507 G 2760 CONNECTOR FOKKER F28 F28MK1000 4990808 EU RROYCE SPEY SPEY55515 54521 EU DRAG CONTROL SYS LOOSE W K NONE F J FLT CONT AFFECTED WARNING INDICATION TO TAKEOFF 1 AU S (AUS) RH OUTBOARD LIFT DUMPER BELLCRANK INLOCK CONNECTOR LOOSE. 2 L 7 2 4F 4 F RT A20EU E2EU 2001080700115 20010807 00115 EU 2001 8 7 AUS20010469 1 20010505 G 3220 200725209UPPER TORQUE LINK FOKKER F28 F28MK4000 4990810 EU RROYCE SPEY SPEY55515 54521 EU NOSE/TAIL LANDIN CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S DCS6808UPPER (AUS) NOSE LANDING GEAR UPPER TORQUE LINK CRACKED IN GREASE NIPPLEHOLE. FOUND USING VISUAL INSPECTION AND CONFIRMED USIN G EDDYCURRENT INSPECTION. 2 L 7 2 4F 4 F RT A20EU E2EU 2001080700116 20010807 00116 CE 2001 8 7 AUS20010470 1 20010407 G 3222 998200005 SHOCK ABSORBER BEECH 9782000061 BEECH 200 200BEECH 1152920 CE NOSE/TAIL LANDIN FAULTY W K NONE O K OTHER FLUID LOSS IN INSP/MAINT 1 AU S (AUS) NOSE LANDING GEAR SHOCK ABSORBER INNER O' RING SEAT OVERSIZE ALLOWING THE O' RING TO MOVE ON THE HOUSING AND LEAK. 1 L 7 2 4T A24CE 2001080800107 20010808 00107 EA 2001 8 8 AUS20010471 1 20010511 G 3220 LANDING GEAR DHAV DHC6 DHC6 2802606 EA NLG FOD W O OTHER C F.O.D. LD LANDING 1 AU S (AUS) NOSE LANDING GEAR FAILED WHEN THE NOSE WHEEL CONTACTED A ROCK ONLANDING. TYRE DEFLATED AND NOSE WHEEL SHATTERED. N LG FORK FAILEDAT THE OLEO AND THE REMAINDER OF THE NLG BENT BACK CAUSING DAMAGE TO THE BULKHEAD, ATTACHMENT FITTINGS AND SURROUNDINGLOWER FUSELAGE STRUCTURE. FIBREGLASS NOSE CONE ALSO BADLY DAMAGED. 1 H 7 2 3T RT A9EA 2001080700117 20010807 00117 GL 2001 8 7 AUS20010472 2 20010426 G 7230 23007196 SEAL ALLSN 250C30P BELL 206 206L1 1182107 SW ALLSN 250C 250C30P 03013 GL TURBINE ENGINE C CORRODED W K NONE O OTHER IN INSP/MAINT 1 AU S 1371 CAC91190 (AUS) COMPRESSOR REAR DIFFUSER LABYRINTH SEAL EXCESSIVELY CORRODED. 1 G 7 1 3U 3 U H2SW E1GL 2001080800109 20010808 00109 NM 2001 8 8 AUS20010473 1 20010504 G 7110 LK47717 FAIRING RROYCE RB21152436 BOEING 767 767* NM RROYCE RB211 RB211524* NE ENGINE COWLING MISSING W O OTHER D INFLIGHT SEPARATION NR NOT REPORTED 1 AU S 18631 13462 (AUS) NR 2 ENGINE LT A' FRAME TO FAN CASE AFT LOWER FAIRING MISSING. 2 L 7 2 4F 4 F RT A1NM E12EU 2001080800111 20010808 00111 CE 2001 8 8 AUS20010474 1 20010427 G 5540 51310103 BEARING CESSNA 404 404CESSNA 2075901 CE CONT O520 GTSIO520M 17032 SO MCAULY 3FF32 3FF32C501 GL RUDDER MISINSTALLED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) LOWER RUDDER HINGE BEARING INCORRECTLY INSTALLED. PERSONNEL/MAINTENANCE ERROR. 1 L 7 2 3O 3 O A25CE E7CE 5 C P45GL 2001080800113 20010808 00113 NM 2001 8 8 AUS20010476 1 20010511 G 7110 13043 PANEL RROYCE RB211524G BOEING 747 747438 NM RROYCE RB211 RB211524G19 NE ENGINE COWLING SEPARATED W K NONE O OTHER IN INSP/MAINT 1 AU S 13720 13043 (AUS) NR 3 ENGINE OGV INFILL PANELS MISSING BETWEEN 4 O'CLOCK AND 6O'CLOCK POSITIONS. DAMAGE TO LH COMPRESSOR CORE PANEL , IP COMPRESSOR BLEED VALVE CONTROL UNIT AIR SENSE PROBE, THRUST REVERSER CORONA AND NO5 AND NO6 THRUST REVERSER BLISTER FAIRINGS. 2 L 7 4 4F 4 F RT A20WE E30NE 2001080800115 20010808 00115 NM 2001 8 8 AUS20010477 1 20010506 G 2761 NAS161210 O-RING 15425001 BOEING 767 767338 1385151 NM GE CF6 CF680C2* GL DRAG ACTUATOR DAMAGED W A UNSCHED LANDING K J FLUID LOSS WARNING INDICATION CL CLIMB 1 AU S 501 (AUS) NR 8 SPOILER POWER CONTROL ACTUATOR (PCA) FILTER BOSS O' RING SEAL DAMAGED AND LEAKING. 2 L 7 2 4F 4 F RT A1NM E23EA 2001080800117 20010808 00117 NM 2001 8 8 AUS20010478 1 20010505 G 2620 301000223 EXTINGUISHER BOEING 767 767* NM CABIN DAMAGED W K NONE O OTHER IN INSP/MAINT 1 AU S 25012 (AUS) FIRE EXTINGUISHERS LOCATED IN THE MID CABIN LT AND RT TOILETS AND AFT CABIN RT TOILET HAD IMPACT DAMAGE TO THE FUS EABLE TIP AREA. FOUND DURING INSPECTION IAW 767-A2-25-006. 2 L 7 2 4F RT A1NM 2001080700118 20010807 00118 WP 2001 8 7 AUS20010479 1 20010406 G 6310 269A55907 RETAINER HUGHES 269 269C 4470504 WP LYC O360 HO360C1A 41514 EA ENGINE/TRANSMISS WORN W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) THERMOFIT SLEEVE WORN ON RETAINER. 1 G 7 1 3O 3 O 4H12 E286 2001080800119 20010808 00119 EU 2001 8 8 AUS20010480 1 20010505 G 2121 D92098 COOLING FAN BAG BAE146 BAE146100A 1500260 EU LYC ALF502 ALF502R5 41580 NE AIR DISTRIBUTION FAILED W O OTHER B SMOKE/FUMES/ODORS/SPARKS CL CLIMB 1 AU S 7028 411467 (AUS) CABIN FAN FAILED. INVESTIGATION FOUND BOTH FORE AND AFT FAN MOTOR SHAFT BEARINGS FAILED. THE MOTOR ALSO FAILED ELE CTRICALLY WITHSIGNS OF OVERHEATING. BEARING PNO S38SS6CXOG33 AND PNOS100SS6CXOG33. 2 H 7 4 4F 4 F RT A49EU E6NE 2001080800121 20010808 00121 EU 2001 8 8 AUS20010482 1 20010425 G 7160 TU195MM660MMCC HOSE LYC IO540 BNORM BN2 BN2A 1520204 EU LYC O540 IO540* 41532 EA ENG AIR INTAKE COLLAPSED W C ABORTED TAKEOFF E R VIBRATION/BUFFET PARTIAL RPM/PWR LOSS TO TAKEOFF 1 AU S (AUS) ENGINE INDUCTION HOSE COLLAPSED. 1 H 7 2 3O 3 O A17EU 1E4 2001080800123 20010808 00123 NM 2001 8 8 AUS20010483 1 20010501 G 3242 S160T400510 BRAKE BOEING 767 767338 1385151 NM GE CF6 CF680C2* GL NR 1 FAILED W O OTHER O OTHER NR NOT REPORTED 1 AU S 3932 QF56035 (AUS) NR 1R BRAKE FAILED. INSPECTION FOUND THAT THE REAR STATOR PLATEWAS DAMAGED WITH EVIDENCE OF REAR STATOR BREAKUP. N O1R WHEEL ALSO DAMAGED TO THE FAILED BRAKE. 2 L 7 2 4F 4 F RT A1NM E23EA 2001080700119 20010807 00119 NM 2001 8 7 AUS20010484 1 20010514 G 3242 214747300 BRAKE 6558256238 BOEING 737 737376 NM CFMINT CFM56 CFM563C 13802 EU BRAKE LEAKING W K NONE O B OTHER SMOKE/FUMES/ODORS/SPARKS LD LANDING 1 AU S (AUS) LH OUTBOARD AND LH INBOARD BRAKES LEAKING FLUID FROM ACTUATINGPISTONS. TYRES CONTAMINATED WITH HYDRAULIC FLUID. 2 L 7 2 4F 4 F RT A16WE E21EU 2001080700120 20010807 00120 2001 8 7 AUS20010485 4 20010424 G 2230 COMPUTER AIRBUS 310 A310324 3930206 EU PWA 4152 PW4152 NE AUTOTHROTTLE SYS FAULTY W K NONE E R VIBRATION/BUFFET PARTIAL RPM/PWR LOSS CL CLIMB 1 AU S (AUS) THROTTLE CONTROL COMPUTER (TCC) FAULTY. 2 L 7 2 4F RT A35EU E24NE 2001080800124 20010808 00124 EU 2001 8 8 AUS20010486 1 20010331 G 5270 SWITCH FOKKER F28 F28MK1000 4990808 EU RROYCE SPEY SPEY55515 54521 EU DOOR WARNING OUT OF ADJ W O OTHER N FALSE WARNING NR NOT REPORTED 1 AU S (AUS) SERVICE DOOR MICROSWITCH OUT OF ADJUSTMENT. 2 L 7 2 4F 4 F RT A20EU E2EU 2001080800126 20010808 00126 EU 2001 8 8 AUS20010487 1 20010331 G 4920 38075411 APU FOKKER F28 F28MK1000 4990808 EU RROYCE SPEY SPEY55515 54521 EU APU BAY FAULTY W O OTHER B SMOKE/FUMES/ODORS/SPARKS NR NOT REPORTED 1 AU S 415 (AUS) APU FAULTY. FUMES IN CABIN. 2 L 7 2 4F 4 F RT A20EU E2EU 2001080700121 20010807 00121 EU 2001 8 7 AUS20010489 1 20010401 G 5753 SEAL FOKKER F28 F28MK1000 4990808 EU RROYCE SPEY SPEY55515 54521 EU TRAILING EDGE FL SEPARATED W K NONE D F INFLIGHT SEPARATION FLT CONT AFFECTED CR CRUISE 1 AU S (AUS) OUTBOARD TRAILING EDGE FLAP RUBBER SEAL SEPARATED. 2 L 7 2 4F 4 F RT A20EU E2EU 2001080700122 20010807 00122 EU 2001 8 7 AUS20010490 1 20010409 G 3610 6272482 CONTROLLER AIRBUS 310 A310324 3930206 EU PWA 4152 PW4152 NE PNEUMATIC DISTRI FAULTY W K NONE O OTHER CR CRUISE 1 AU S 7141 111C589 (AUS) NO1 PNEUMATIC SYSTEM CONTROLLER FAULTY. 2 L 7 2 4F RT A35EU E24NE 2001080700123 20010807 00123 NM 2001 8 7 AUS20010491 1 20010423 G 3260 SENSOR DHAV DHC8 DHC8* NM PWA 120 PW123D 52152 NE LANDING GEAR POS CONTAMINATED W K NONE O N OTHER FALSE WARNING TO TAKEOFF 1 AU S (AUS) MAIN LANDING GEAR DOOR SENSORS AND CONNECTORS CONTAMINATED. 2 H 7 2 4T 4 T RT A13NM E20NE 2001080800128 20010808 00128 EU 2001 8 8 AUS20010492 1 20010411 G 7603 THROTTLE PWA PW4152 AIRBUS 310 A310324 3930206 EU PWA 4152 PW4152 NE LT & RT ENGINE FAULTY W O OTHER E R VIBRATION/BUFFET PARTIAL RPM/PWR LOSS CL CLIMB 1 AU S (AUS) LT AND RT ENGINE THROTTLES REDUCED TOWARDS IDLE. INTERMITTENT DEFECT. CAUSE COULD NOT BE IDENTIFIED. SEE MDR 01/04 85 FORFURTHER INFORMATION. 2 L 7 2 4F RT A35EU E24NE 2001080700124 20010807 00124 SO 2001 8 7 AUS20010493 1 20010501 G 3233 452383 ROD END PIPER ACTUATOR PIPER PA31 PA31350 7103110 SO LYC O540 TIO540J2BD 41532 EA HARTZL HCE3Y HCE3YR2 GL LANDING GEAR ACT CONTAMINATED W K NONE O N OTHER FALSE WARNING LD LANDING 1 AU S (AUS) RH MAIN LANDING GEAR ACTUATOR RODEND CONTAMINATED AND DRY.SUSPECT CAUSED BY EXHAUST GASES FROM TAILPIPE. 1 L 7 2 3O 3 O A20SO E14EA 5 C P33EA 2001080700125 20010807 00125 NE 2001 8 7 AUS20010494 2 20010516 G 7261 PIPE PWA PW120A DHAV DHC8 DHC8102 2809003 NM PWA 120 PW120A NE HAMSTD 14SF 14SF7 NE TURBINE ENGINE O BROKEN W K NONE E X VIBRATION/BUFFET ENGINE FLAMEOUT CR CRUISE 1 AU S (AUS) ENGINE NO6/NO7 BEARING OIL FEED PIPE BROKEN. ENGINE SEIZED WITH EVIDENCE OF FIRE. 2 H 7 2 4T 4 T RT A13NM E20NE 6 C P7NE 2001080800131 20010808 00131 NM 2001 8 8 AUS20010495 1 20010515 G 4920 38042812 APU BOEING 737 737377 NM CFMINT CFM56 CFM563B2 13802 EU APU BAY FAULTY W K NONE L NO TEST IN INSP/MAINT 1 AU S 3989 (AUS) APU FAILED PERFORMANCE MONITORING TEST. EGT ROSE TO 800 DEGREES. 2 L 7 2 4F 4 F RT A16WE E21EU 2001080800132 20010808 00132 GL 2001 8 8 AUS20010496 1 20010407 G 2752 464300 MOTOR PAC CT4 CT4B GL CONT O360 IO360HB 17025 SO HARTZL HCC2Y BHCC2YF1 GL TE FLAPS FAILED W O OTHER F FLT CONT AFFECTED NR NOT REPORTED 1 AU S (AUS) FLAP MOTOR BURNED OUT. 1 L 7 1 3O 3 O RT A9PC E1CE 5 C P920 2001080800166 20010808 00166 CE 2001 8 8 AUS20010498 1 20010508 G 5500 STRUCTURE CESSNA 401 401A 207590D CE CONT O520 TSIO520E 17040 SO MCAULY 3AF32C 3AF32C505 GL EMPENNAGE CORRODED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) EXTENSIVE SURFACE CORROSION THROUGHOUT THE FIN AND TAIL ASSEMBLY. 1 L 7 2 3O 3 O A7CE E8CE 5 C P22EA 2001080800170 20010808 00170 NE 2001 8 8 AUS20010499 2 20010510 G 7230 17284 GUIDE VANE FOKKER F28 F28MK0100 4990807 EU RROYCE TAY TAY65015 54557 NE ENGINE OUT OF ADJ W A UNSCHED LANDING E VIBRATION/BUFFET CR CRUISE 1 AU S (AUS) RT ENGINE VIBRATION. POWER INCREASE LED TO HIGH ITT WITH LOW N1 AND LOW EPR WITH LOW N2. INVESTIGATION FOUND THE A CCELERATION TIME SLOW DUE TO IGV SCHEDULING OUT OF ADJUSTMENT. 2 L 7 2 4F 4 F RT E25NE 2001080800172 20010808 00172 NM 2001 8 8 AUS20010500 1 20010517 G 3260 864202 PROXIMITY SENSOR DHAV DHC8 DHC8102 2809003 NM PWA 120 PW120A NE HAMSTD 14SF 14SF7 NE LANDING GEAR OUT OF ADJ W A UNSCHED LANDING N FALSE WARNING CL CLIMB 1 AU S (AUS) LT MAIN LANDING GEAR DOOR PROXIMITY SWITCH OUT OF ADJUSTMENT. 2 H 7 2 4T 4 T RT A13NM E20NE 6 C P7NE 2001080800173 20010808 00173 NM 2001 8 8 AUS20010501 1 20010516 G 2910 MS21904W16 ELBOW BOEING 747 747SP38 NM RROYCE RB211 RB211524D419 54555 NE HYDRAULIC SYSTEM CRACKED W O OTHER K FLUID LOSS NR NOT REPORTED 1 AU S (AUS) HYDRAULIC SYSTEM LEAKING FROM CRACKED PRESSURE LINE ELBOW LOCATED UNDER NO3 STRUT REAR SAILBOAT. LOSS OF HYDRAULIC FLUID. 2 L 7 4 4F 4 F RT A20WE E12EU 2001080800175 20010808 00175 NM 2001 8 8 AUS20010502 1 20010517 G 7110 13082 PANEL RROYCE RB211524H36 BOEING 767 767* NM RROYCE RB211 RB211524* NE ENGINE COWLING SEPARATED W K NONE O OTHER IN INSP/MAINT 1 AU S 43385 13082 (AUS) RH ENGINE BULLNOSE SECTION LOCATED AFT OF THE ACOUSTIC PANELMISSING FROM AREA BETWEEN NO4 AND NO7 BLOCKER DOORS. T HE MISSINGPIECE WAS APPROXIMATELY 2 METERS (6FT) IN LENGTH. DAMAGE CAUSED TO THREE BLOCKER DOORS, COMBUSTOR FAIRING AND BLISTER FAIRING. 2 L 7 2 4F 4 F RT A1NM E12EU 2001080800178 20010808 00178 NM 2001 8 8 AUS20010503 1 20010515 G 7110 12756 LINER RROYCE RB211524D419 BOEING 747 747238B 1384828 NM RROYCE RB211 RB211524D419 54555 NE ENGINE COWLING MISSING W O OTHER E R J VIBRATION/BUFFET PARTIAL RPM/PWR LOSS WARNING INDICATION NR NOT REPORTED 1 AU S 6756 12756 (AUS) NR 1 ENGINE LOW POWER. INVESTIGATION FOUND ONE SECTION OF FRONTFAN ACOUSTIC LINING BETWEEN 2 O'CLOCK AND 4 O'CLOCK AREAS MISSING AND ONE AREA OF ICE IMPACT PANEL BETWEEN 1 O'CLOCK AND 5 O'CLOCKAREAS MISSING WITH LOOSE MATERIAL STILL T RAPPED BY THEENGINE. 2 L 7 4 4F 4 F A20WE E12EU 2001080700126 20010807 00126 CE 2001 8 7 AUS20010504 1 20010508 G 5554 513300031 BRACKET CESSNA 401 401A 207590D CE CONT O520 TSIO520E 17040 SO MCAULY 3AF32C 3AF32C505 GL RUDDER/TAB, ATTA CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) RUDDER LOWER HINGE BRACKET CRACKED AT CORNERS. 1 L 7 2 3O 3 O A7CE E8CE 5 C P22EA 2001080800179 20010808 00179 NM 2001 8 8 AUS20010505 1 20010501 G 2934 20044000001 TRANSMITTER BOEING 737 7374Y0 1384705 NM CFMINT CFM56 CFM563C 13802 EU HYD QTY IND FAULTY W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) HYDRAULIC SYSTEM B' OIL QUANTITY TRANSMITTER FAULTY. 2 L 7 2 4F 4 F RT A16WE E21EU 2001080800181 20010808 00181 EU 2001 8 8 AUS20010506 1 20010520 G 2612 HC924H4913002 FIRE LOOP BAG BAE146 BAE146200A 1500266 EU LYC ALF502 ALF502R5 41580 NE NR 1 ENGINE WORN W A UNSCHED LANDING N FALSE WARNING CL CLIMB 1 AU S 20594 (AUS) NR 1 ENGINE FIRE DETECTOR WIRING LOOM CHAFED. 2 H 7 4 4F 4 F RT A49EU E6NE 2001080800203 20010808 00203 NE 2001 8 8 AUS20010507 2 20010521 G 7261 ENGINE DHAV DHC8 DHC8102 2809003 NM PWA 120 PW120A NE HAMSTD 14SF 14SF7 NE LT & RT LACK OF LUBE W C ABORTED TAKEOFF K E J FLUID LOSS VIBRATION/BUFFET WARNING INDICATION TO TAKEOFF 1 AU S (AUS) LT AND RT ENGINES LOW ON OIL. 2 H 7 2 4T 4 T RT A13NM E20NE 6 C P7NE 2001080700127 20010807 00127 NM 2001 8 7 AUS20010508 1 20010517 G 3233 980044503 BEARING PIPER PA60 PA60600A 7106002 NM LYC O540 IO540K1J5 41532 EA HARTZL HCC3Y HCC3YR2 NE LANDING GEAR ACT BROKEN W K NONE O J OTHER WARNING INDICATION DE DESCENT 1 AU S (AUS) LH MAIN LANDING GEAR ACTUATOR RODEND BEARING FRACTURED. 1 M 7 2 3O 3 O RT A17WE 1E4 5 C P25EA 2001080800205 20010808 00205 CE 2001 8 8 AUS20010509 1 20010118 G 5347 50150191 SEAT TRACK CESSNA 402 402C 207590R CE CONT O520 TSIO520VB 17040 SO CABIN FRACTURED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) PILOTS SEAT TRACK CHANNELS PNO 5015019-1 AND PNO 5015019-3CRACKED THROUGH MOUNT HOLES. ONE CHANNEL HAD BEEN REMANU FACTUREDFROM A LIGHTER MATERIAL AND WAS ALSO SECURED USING COMMERCIAL POP RIVETS. UNAPPROVED PART. PERSONNEL/MAINTENANCE ERROR. 1 L 7 2 3O 3 O A7CE E8CE 2001080800206 20010808 00206 NM 2001 8 8 AUS20010510 1 20010516 G 5310 PANEL BOEING 747 747SP38 NM RROYCE RB211 RB211524D419 54555 NE FUEL CELL LOOSE W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) NO1 MAIN FUEL TANK INTERNAL RIB ACCESS/BAFFLE PANEL LOOSE. THEPANEL WAS FOUND UNSECURED ON THE FLOOR WITH THE MOUN TING SCREWS CONTAINED IN A CANVAS SCREW BAG ATTACHED TO THE PANEL. THE AREA HAD RECENTLY BEEN ACCESSED DURING D4 INSPECT ION.PERSONNEL/MAINTENANCE ERROR. 2 L 7 4 4F 4 F RT A20WE E12EU 2001080800209 20010808 00209 NM 2001 8 8 AUS20010511 1 20010520 G 3246 162T16211 WASHER BOEING 767 767338 1385151 NM GE CF6 CF680C2* GL WHEEL MISSING W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) WHILE CHANGING THE RH NOSEWHEEL DUE TO FOD IT WAS NOTED THAT THENUT SPACER (WASHER) WAS MISSING. THE LT NOSEWHEEL WAS ALSOCHECKED WHERE IT WAS FOUND THAT THE WASHER WAS ALSO MISSING. 2 L 7 2 4F 4 F RT A1NM E23EA 2001080700128 20010807 00128 NM 2001 8 7 AUS20010512 1 20010521 G 3242 215211400 BRAKE BOEING 737 737476 NM CFMINT CFM56 CFM563C 13802 EU BRAKE LEAKING W K NONE O B OTHER SMOKE/FUMES/ODORS/SPARKS LD LANDING 1 AU S 3134 (AUS) LH INBOARD BRAKE UNIT LEAKING FROM PISTON ASSEMBLY. 2 L 7 2 4F 4 F RT A16WE E21EU 2001080700129 20010807 00129 NM 2001 8 7 AUS20010513 1 20010521 G 2520 22303001 STUD BOEING 737 737476 NM CFMINT CFM56 CFM563C 13802 EU PASSENGER COMPAR LOOSE W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) PASSENGER SEAT 9ABC LOOSE DUE TO INBOARD SEAT LEG FLOOR SPREADERSTUD UNSCREWING FROM ANCHOR NUT. 2 L 7 2 4F 4 F RT A16WE E21EU 2001080700130 20010807 00130 NM 2001 8 7 AUS20010514 1 20010508 G 5230 6546921528 DOOR BOEING 737 737376 NM CFMINT CFM56 CFM563C 13802 EU CARGO/BAGGAGE DO CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S 42473 1359 (AUS) FORWARD CARGO DOOR CRACKED ON THE INSIDE RADIUS OF THE AFT LOWERCORNER EMANATING UPWARDS FROM THE LOWER CROSS BEAM ATTACHMENT POINT. CRACK LENGTH APPROXIMATELY 25.4MM (1IN). 2 L 7 2 4F 4 F RT A16WE E21EU 2001080700131 20010807 00131 NM 2001 8 7 AUS20010515 1 20010510 G 5511 SPAR BOEING 737 7374Q8 NM CFMINT CFM56 CFM563C 13802 EU HORIZONTAL STABI DAMAGED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) RH HORIZONTAL STABILISER LOWER FORWARD SPAR DAMAGED. 2 L 7 2 4F 4 F RT A16WE E21EU 2001080700132 20010807 00132 CE 2001 8 7 AUS20010516 1 20010412 G 8011 SA539800M015 SPRING CONT IO520A CESSNA 206 U206 2073306 CE CONT O520 IO520A 17032 SO HARTZL HCC3Y HCC3YF1 GL ENGINE STARTER FAILED W K NONE O OTHER IN INSP/MAINT 1 AU S 2 552408 (AUS) STARTER CLUTCH SPRING FAILED CAUSING DAMAGE TO THE CRANKSHAFT,CAMSHAFT GEAR AND ATTACHING HARDWARE. ROCKWELL HARDN ESS TESTREVEALED INCONSISTANT HARDNESS. 1 H 7 1 3O 3 O A4CE E5CE 5 C P25EA 2001080700133 20010807 00133 NM 2001 8 7 AUS20010517 1 20010402 G 7500 09880645 SEAL GARRTT HP6DUCT BOEING 757 75723A 1384967 NM RROYCE RB211 RB211535E4 54555 NE ENGINE BLEED AIR FAILED W K NONE E J VIBRATION/BUFFET WARNING INDICATION CL CLIMB 1 AU S 09880645 (AUS) RH ENGINE HP6 DUCT SEALS FAILED AND LEAKING. 2 L 7 2 4F 4 F RT A2NM E12EU 2001080800211 20010808 00211 NM 2001 8 8 AUS20010518 1 20010508 G 4930 36080004 FCU BOEING 737 737377 NM CFMINT CFM56 CFM563B2 13802 EU APU ENGINE FAULTY W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) APU FUEL CONTROL UNIT FAULTY. 2 L 7 2 4F 4 F RT A16WE E21EU 2001080800212 20010808 00212 SW 2001 8 8 AUS20010519 1 20010521 G 3234 CA3108E12S200210 CONNECTOR SWRNGN SA226 SA226TC 8780404 SW GARRTT TPE331 TPE33110UA 01514 WP HARTZL HCB3T HCB3TN5 GL LANDING GEAR FAULTY W O OTHER O OTHER DE DESCENT 1 AU S (AUS) LANDING GEAR SELECTOR VALVE CANNON PLUG WIRE BROKEN. 2 L 7 2 4T 4 T RT A8SW E4WE 6 C P15EA 2001080800214 20010808 00214 NE 2001 8 8 AUS20010520 2 20010519 G 7260 17287 GEARBOX FOKKER F28 F28MK0100 4990807 EU RROYCE TAY TAY65015 54557 NE TURBINE ENGINE MAKING METAL W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) LH ENGINE HIGH SPEED GEARBOX CHIP DETECTOR AND OIL FILTER CONTAMINATED WITH FINE METAL PARTICLES. FILTER DIFFERENT IAL PRESSURE POP-UP INDICATOR OPERATED. 2 L 7 2 4F 4 F RT E25NE 2001080800218 20010808 00218 2001 8 8 AUS20010522 4 20010522 G 3460 4058650904 CDU BOEING 747 747438 NM RROYCE RB211 RB211524G19 NE COCKPIT FAILED W A UNSCHED LANDING B O SMOKE/FUMES/ODORS/SPARKS OTHER CR CRUISE 1 AU S 21528 89020332 (AUS) RT FLIGHT MANAGEMENT COMPUTER CONTROL DISPLAY UNIT (CDU) FAILED. SMOKE IN COCKPIT AND ELECTRICAL BURNING SMELL WIT H RT CDU KEYPADWARM TO TOUCH. 2 L 7 4 4F 4 F RT A20WE E30NE 2001080800219 20010808 00219 NE 2001 8 8 AUS20010525 2 20010523 G 7200 6058T82GO1 ENGINE SAAB SF340 340B 7860101 EU GE CT7TP CT79B 30030 NE ROTOL R390 R3904123F27 NE RIGHT FAILED W C ABORTED TAKEOFF E X VIBRATION/BUFFET ENGINE FLAMEOUT TO TAKEOFF 1 AU S 13931 (AUS) RT ENGINE FAILED. INVESTIGATION FOUND SOME DAMAGE TO THE FIRSTSTAGE COMPRESSOR WHEEL AND THE CENTRE BODY RETAINING SCREW STUDSSHEARED. BORESCOPE INSPECTION FOUND MAJOR DAMAGE TO THE FIRST STAGE IGVS AND COMPRESSOR WHEEL WITH ONE COMPR ESSOR BLADE MISSING ABOUT HALF OF THE AXIAL LENGTH. DOWNSTREAM DAMAGE TO OTHER IGVS AND COMPRESSOR STAGES. THERE IS ALSO SEVERE HEAT DISTRESS DAMAGETO THE FIRST AND SECOND STAGE GAS GENERATOR TURBINES AND NOZZLESAS WELL AS THE FIRST STAGE P OWER TURBINE AND NOZZLE. POWERTURBINE COOLING AIR UPPER AND LOWER TRANSFER TUBES SEPARATED AT WELDS. FOUR RETENTION SCRE WS ON THE CENTRE BODY HAVE SHEARED OFF. 2 L 7 2 4T 4 T RT A52EU E8NE 6 C P31NE 2001080800220 20010808 00220 NE 2001 8 8 AUS20010526 2 20010521 G 7321 FFR105MK4S REGULATOR RROYCE RB211524D4 BOEING 747 747338 NM RROYCE RB211 RB211524D419 54555 NE FUEL CONTROL FAULTY W O OTHER E VIBRATION/BUFFET AP APPROACH 1 AU S 2196 12775 (AUS) NR 3 ENGINE FUEL FLOW REGULATOR (FFR) FAULTY. 2 L 7 2 4F 4 F RT A20WE E12EU 2001080800221 20010808 00221 EA 2001 8 8 AUS20010527 2 20010412 G 8530 LW13622 VALVE NEWZE FU24 FU24954 WP LYC O720 IO720A1B 41546 EA ENGINE WORN W K NONE O OTHER IN INSP/MAINT 1 AU S 394 (AUS) NO2 CYLINDER INLET VALVE DAMAGED IN THE COLLETT RECESS AREA.VALVE STEM CAP SEPARATED AND ONLY ONE COLLETT HALF WAS RETAININGTHE VALVE SPRING. METAL PARTICLES FROM THE DAMAGED VALVE WERE FOUND IN THE OIL FILTER AND PARTICLES OF THE MIS SING COLLETT WERE FOUND IN THE SUCTION FILTER. 1 L 7 1 3O 3 O A9PC 1E15 2001080800222 20010808 00222 EA 2001 8 8 AUS20010528 2 20010418 G 8530 15F1995758 PUSHROD NEWZE FU24 FU24954 WP LYC O720 IO720A1B 41546 EA ENGINE DISTORTED W A UNSCHED LANDING E R VIBRATION/BUFFET PARTIAL RPM/PWR LOSS CR CRUISE 1 AU S (AUS) NR 7 CYLINDER EXHAUST VALVE PUSHROD BENT AND PUSHROD SHROUDDAMAGED CAUSING OIL LEAK. INVESTIGATION FOUND THE VALVE STEM CAP SEPARATED AND THE PISTON SUFFERING FROM SLIGHT IMPACT DAMAGE WITH THE EXHAUST VALVE. METAL CONTAMINATION OF OI L FILTER. 1 L 7 1 3O 3 O A9PC 1E15 2001080800223 20010808 00223 NM 2001 8 8 AUS20010529 1 20010507 G 2722 65C370539 PCU BOEING 737 737377 NM CFMINT CFM56 CFM563B2 13802 EU RUDDER ACTUATOR FAULTY W K NONE O OTHER IN INSP/MAINT 1 AU S 35274 1899AC (AUS) RUDDER POWER CONTROL UNIT (PCU) INTERNAL LEAK. FOUND DURING INSPECTION IAW ER B73-27-20-15 AND BOEING SL 737-SL-27 -119. WORKSHOP INSPECTION FOUND THE LEAK WITHIN LIMITS. 2 L 7 2 4F 4 F RT A16WE E21EU 2001080800224 20010808 00224 NM 2001 8 8 AUS20010532 1 20010316 G 4920 38420723 TURBINE GARRTT GTCP85129H BOEING 737 73733A 1384673 NM CFMINT CFM56 CFM563B2 13802 EU APU CORE ENGINE FAILED W O OTHER E VIBRATION/BUFFET NR NOT REPORTED 1 AU S 3480 (AUS) APU TURBINE WHEEL DISINTEGRATED. SUSPECT CAUSED WAS A BI-HUBFAILURE OF THE TURBINE WHEEL DUE TO UNDETECTABLE HANIU M OXIDE INCLUSION FORMED DURING THE CASTING PROCESS. 2 L 7 2 4F 4 F RT A16WE E21EU 2001080800225 20010808 00225 NM 2001 8 8 AUS20010533 1 20010305 G 4920 38420723 TURBINE GARRTT GTCP85129K BOEING 737 73733A 1384673 NM CFMINT CFM56 CFM563B2 13802 EU APU CORE ENGINE FAILED W O OTHER E VIBRATION/BUFFET NR NOT REPORTED 1 AU S 4146 (AUS) APU TURBINE WHEEL DISINTEGRATED. SUSPECT CAUSED BY TENSILEOVERLOAD ORIGINATING FROM AN UNDETECTABLE SINGLE HAFNIUM OXIDEDROSS CASTING INCLUSION. 2 L 7 2 4F 4 F RT A16WE E21EU 2001080800226 20010808 00226 NE 2001 8 8 AUS20010534 2 20010207 G 7250 230353601 BEARING LYC ALF502R5 BAG BAE146 BAE146300A 1500267 EU LYC ALF502 ALF502R5 41580 NE TURBINE SECTION FAILED W K NONE O OTHER IN INSP/MAINT 1 AU S 20481 (AUS) NO2 ENGINE NO6 BEARING FAILED. CONTAMINATION OF ENGINE OILSYSTEM. 2 H 7 4 4F 4 F RT A49EU E6NE 2001080800227 20010808 00227 EU 2001 8 8 AUS20010535 1 20010426 G 5711 SPAR BAG BAE146 BAE146100A 1500260 EU LYC ALF502 ALF502R3A 41580 NE LT & RT WING CORRODED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) LT AND RT WING FORWARD AND AFT SPAR LOWER FLANGES CORRODED IN AREA BETWEEN RIB 13 AND RIB 18. 2 H 7 4 4F 4 F RT A49EU E6NE 2001080800228 20010808 00228 EU 2001 8 8 AUS20010536 1 20010330 G 5711 SPAR BAG BAE146 BAE146200A 1500266 EU LYC ALF502 ALF502R5 41580 NE WING CORRODED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) LT AND RT WING FORWARD AND AFT SPAR LOWER FLANGES CORRODED IN THE AREA BETWEEN RIB 13 AND RIB 18. 2 H 7 4 4F 4 F RT A49EU E6NE 2001080800229 20010808 00229 EU 2001 8 8 AUS20010537 1 20010301 G 5711 SPAR BAG BAE146 BAE146200A 1500266 EU LYC ALF502 ALF502R5 41580 NE WING CORRODED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) LT AND RT WING FORWARD AND AFT SPAR LOWER FLANGES CORRODED IN THE AREA BETWEEN RIB 13 AND RIB 18. 2 H 7 4 4F 4 F RT A49EU E6NE 2001080800231 20010808 00231 2001 8 8 AUS20010538 4 20010528 G 3130 RECORDER BAG BAE146 BAE146200A 1500266 EU LYC ALF502 ALF502R5 41580 NE DATA UNSERVICEABLE W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) OPERATIONAL CHECK AND CALIBRATION CHECK OF FLIGHT DATA RECORDER (FDR) NOT CARRIED OUT. PERSONNEL/MAINTENANCE ERROR . 2 H 7 4 4F 4 F RT A49EU E6NE 2001080800232 20010808 00232 EU 2001 8 8 AUS20010539 1 20010528 G 5330 SKIN BAG BAE146 BAE146200A 1500266 EU LYC ALF502 ALF502R5 41580 NE FUSELAGE CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) FUSELAGE SKIN CRACKED IN THE AREA BETWEEN FR 35 AND FR 36 ATSTRINGER LOCATIONS 2L AND 3L. CRACK LENGTH 558.8MM (22 IN). 2 H 7 4 4F 4 F RT A49EU E6NE 2001080700134 20010807 00134 NM 2001 8 7 AUS20010540 1 20010526 G 3234 4105DA VALVE BOEING 737 737476 NM CFMINT CFM56 CFM563C 13802 EU LANDING GEAR SEL FAULTY W K NONE O OTHER LD LANDING 1 AU S 2087 (AUS) LANDING GEAR CONTROL SELECTOR VALVE FAULTY. 2 L 7 2 4F 4 F RT A16WE E21EU 2001080800234 20010808 00234 NE 2001 8 8 AUS20010541 2 20010526 G 7321 6068T72P09 HMU GE CT79B SAAB SF340 340B 7860101 EU GE CT7TP CT79B 30030 NE ROTOL R375 R3754123F21 NE ENGINE FAULTY W A UNSCHED LANDING E VIBRATION/BUFFET CL CLIMB 1 AU S (AUS) HYDROMECHANICAL UNIT (HMU) SUSPECT FAULTY. WORKSHOP INVESTIGATION AND TESTING COULD FIND NO FAULTS. 2 L 7 2 4T 4 T RT A52EU E8NE 6 C P17NE 2001080800236 20010808 00236 NM 2001 8 8 AUS20010543 1 20010426 G 2751 2061141 INDICATOR BOEING 737 73733A 1384673 NM TE FLAPS FAULTY W O OTHER F FLT CONT AFFECTED AP APPROACH 1 AU S 44431 903 (AUS) FLAP POSITION INDICATOR GAVE CONFLICTING LH AND RH FLAP POSITIONS ALTHOUGH THERE WAS NO EFFECT ON ROLL CONTROL. IN SPECTION OF THE INDICATOR REVEALED MINOR FAULTS BUT THE INDICATOR WAS OK AND NOTLIKELY TO HAVE CAUSED THE FAULT. 2 L 7 2 4F RT A16WE 2001080700135 20010807 00135 WP 2001 8 7 AUS20010544 1 20010522 G 6320 A0061 GEARBOX ROBSIN R22 R22 7640102 WP LYC O320 O320B2C 41508 EA MAIN ROTOR GEARB CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S 0375 (AUS) MAIN ROTOR GEARBOX CRACKED IN LOWER AREA. 1 G 7 1 3O 3 O H10WE E274 2001080800237 20010808 00237 CE 2001 8 8 AUS20010545 1 20010512 G 2120 CM361210B130 DUCT CESSNA 441 441 2076020 CE CABIN COOLING DETERIORATED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) AIRCYCLE MACHINE DUCT DETERIORATED. 1 L 7 2 3T RT A28CE 2001080800238 20010808 00238 NM 2001 8 8 AUS20010546 1 20010523 G 2133 VALVE BOEING 737 73733A 1384673 NM CABIN PRESSURE FAILED W O OTHER O OTHER CR CRUISE 1 AU S (AUS) PRESSURISATION SYSTEM AUTOMATIC FLOW CONTROL VALVE FAILED TO CLOSE. 2 L 7 2 4F RT A16WE 2001080800240 20010808 00240 NM 2001 8 8 AUS20010547 1 20010214 G 2760 BACC2A3A01853FG CONTROL CABLE BOEING 737 73733A 1384673 NM DRAG CONTROL SYS FAILED W O OTHER F FLT CONT AFFECTED DE DESCENT 1 AU S (AUS) NR 3 FLIGHT SPOILER CONTROL CABLE BROKEN IN THE AREA OF WBL 73.00LT. THE CABLE FAILED APPROXIMATELY 203.2MM (8IN) OUTBOARD OF THETURNBARREL. THE FAILURE WAS A RESULT OF RUST (CORROSION) AND WEAR SUSPECT DUE TO INADEQUATE REAPPLICATION OF PROTECTIVE INHIBITNG FLUID. 2 L 7 2 4F RT A16WE 2001080800242 20010808 00242 NM 2001 8 8 AUS20010548 1 20010529 G 4920 737M49503011 APU BOEING 737 737476 NM CFMINT CFM56 CFM563C 13802 EU APU BAY FAULTY W O OTHER B SMOKE/FUMES/ODORS/SPARKS NR NOT REPORTED 1 AU S 2976 (AUS) APU FAULTY. SMOKE AND FUMES IN CABIN. OIL IN BLEED DUCT. 2 L 7 2 4F 4 F RT A16WE E21EU 2001080700136 20010807 00136 2001 8 7 AUS20010549 4 20010528 G 2565 65C1990115 CABLE BOEING 737 737476 NM CFMINT CFM56 CFM563C 13802 EU ESCAPE SLIDE FRAYED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) LH AND RH AFT MAIN ENTRY DOOR ESCAPE SLIDE RELEASE CABLES CONTAINED BROKEN STRANDS. FOUND DURING INSPECTION IAW AD /B737/42, FAA AD 90-12-11 AND EI 734-025-0086 REV09. 2 L 7 2 4F 4 F RT A16WE E21EU 2001080800243 20010808 00243 2001 8 8 AUS20010550 4 20010528 G 2565 80330033 CABLE 7A126110 BOEING 747 747SP38 1384817 NM RROYCE RB211 RB211524D419 54555 NE ESCAPE SLIDE OUT OF ADJ W K NONE L NO TEST IN INSP/MAINT 1 AU S 1328 G112 (AUS) NO1 RH DOOR SLIDE FAILED TO DEPLOY DURING TEST. INVESTIGATION FOUND THE DOOR EMERGENCY POWER RESERVOIR FIRING CABL E OUT OFADJUSTMENT AND FAILING TO RUPTURE THE DISC OF THE EPS BOTTLE. THE EPS CABLE WAS ADJUSTED AND THE SLIDE DEPLOYED NORMALLY. 2 L 7 4 4F 4 F RT A20WE E12EU 2001080800244 20010808 00244 NM 2001 8 8 AUS20010551 1 20010531 G 3520 S417T40127 GENERATOR BOEING 737 737377 NM CFMINT CFM56 CFM563B2 13802 EU PASSENGER OXYGEN MISINSTALLED W K NONE W INADEQUATE Q C IN INSP/MAINT 1 AU S (AUS) NR 3 TOILET AND PSU 21L OXYGEN GENERATORS HAD THE RELEASE PINS INCORRECTLY INSTALLED IN THE SAFETY PIN HOLES.PERSO NNEL/MAINTENANCE ERROR. 2 L 7 2 4F 4 F RT A16WE E21EU 2001080700137 20010807 00137 CE 2001 8 7 AUS20010552 1 20010426 G 5711 501100037 SPAR CAP BEECH 65 A658200 1152805 CE LYC O480 IGSO480A1B6 41529 EA HARTZL HCB3Z HCB3Z202 GL WING SPAR CORRODED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) RH WING UPPER SPAR CAP CORRODED IN THE AREA OF THE FORWARD HINGEEDGE AND FORWARD CAP FLANGE. 1 L 7 2 3O 3 O 3A20 E284 5 C P907 2001080800245 20010808 00245 NM 2001 8 8 AUS20010554 1 20010531 G 3320 60B4002615 TRANSFORMER BOEING 747 747238B 1384828 NM CABIN FAULTY W O OTHER B SMOKE/FUMES/ODORS/SPARKS CR CRUISE 1 AU S (AUS) SIDE WALL LIGHT BALLAST LOCATED IN THE AREA ABOVE SEAT 23J BURNTAND DAMAGED. INVESTIGATION FOUND PIN 14 OF PLUG D2 292P IN THE LIGHTING TRANSFORMER PNO 60B40026-15 DAMAGED. 2 L 7 4 4F A20WE 2001080800248 20010808 00248 SO 2001 8 8 AUS20010555 1 20010530 G 2621 89777601 SQUIB EMB 120 EMB120 3260201 SO PWA 118 PW118A NE HAMSTD 14RF 14RF9 NE FIRE BOTTLE UNAPPROVED PART W K NONE W INADEQUATE Q C IN INSP/MAINT 1 AU S (AUS) APU FIRE BOTTLE SQUIB FAULTY (MODIFIED). THE FIRING DEVICE HAD BEEN CUT OFF AND THE SQUIB USED AS A TRANSPORT BLAN K. THE SQUIB HAD NOT BEEN REPLACED WHEN THE FIRE BOTTLE WAS FITTED TO THE AIRCRAFT. UNAPPROVED PART. 2 L 7 2 4T 4 T RT A31SO E20NE 6 C P11NE 2001080700138 20010807 00138 SW 2001 8 7 AUS20010556 1 20010528 G 3213 ED12758 PIN GULSTM 500 500S 0141107 SW LYC O540 IO540E1B5 41532 EA HARTZL HCC3Y HCC3YR2 NE MAIN LANDING GEA CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) MAIN LANDING GEAR CLEVIS PIN CRACKED FROM BOLT HOLE. FOUND DURING INSPECTION IAW SL 376. 1 H 7 2 3O 3 O 6A1 1E4 5 C P25EA 2001080700139 20010807 00139 2001 8 7 AUS20010557 4 20010518 G 3452 74LS02 TRANSPONDER NARCO AT150 CESSNA 210 T210M 2073451 CE CONT O520 TSIO520R 17040 SO MCAULY D3A34 D3A34C402 GL ATC TRANSPONDER FAULTY W K NONE O OTHER DE DESCENT 1 AU S 18821 (AUS) TRANSPONDER GIVING FALSE ALTITUDE READINGS. 1 H 7 1 3O 3 O 3A21 E8CE 5 C P47GL 2001080700140 20010807 00140 EU 2001 8 7 AUS20010558 1 20010519 G 8012 P90018 VALVE GARRTT TPE3312201A STBROS SC7 SC7SERIES3 8100512 EU GARRTT TPE331 TPE3312201A WP HARTZL HCB3T HCB3TN5 GL ENGINE START VAL FAULTY W K NONE E M VIBRATION/BUFFET OVER TEMP NR NOT REPORTED 1 AU S P90018 (AUS) START PRESSURE REGULATOR INTERNAL FAULT. EGT OVERTEMP ON START. OVERTEMP INSPECTION FOUND NO DEFECTS WITH THE ENGI NE. 1 H 7 2 3T 4 T NT A15EU E3WE 6 C P15EA 2001080700141 20010807 00141 WP 2001 8 7 AUS20010559 2 20010524 G 7240 P90018 GASKET GARRTT TPE3312201A STBROS SC7 SC7SERIES3 8100512 EU GARRTT TPE331 TPE3312201A WP HARTZL HCB3T HCB3TN5 GL TURBINE ENGINE C FAILED W K NONE E R VIBRATION/BUFFET PARTIAL RPM/PWR LOSS CL CLIMB 1 AU S P90018 (AUS) LH ENGINE IGNITER PLUG BLANK GASKET FAILED. 1 H 7 2 3T 4 T NT A15EU E3WE 6 C P15EA 2001080800249 20010808 00249 NM 2001 8 8 AUS20010560 1 20010507 G 2722 65C370539 PCU BOEING 737 737377 NM RUDDER ACTUATOR LEAKING W K NONE O OTHER IN INSP/MAINT 1 AU S 35274 1899AC (AUS) RUDDER POWER CONTROL UNIT (PCU) LEAKING INTERNALLY. 2 L 7 2 4F RT A16WE 2001080700142 20010807 00142 EU 2001 8 7 AUS20010561 1 20010527 G 2820 SWITCH FOKKER F28 F28MK0100 4990807 EU RROYCE TAY TAY62015 04564 NE AIRCRAFT FUEL DI FAULTY W K NONE K FLUID LOSS TO TAKEOFF 1 AU S (AUS) FUELLING CONTROL PANEL POWER SWITCH FAULTY. PANEL POWER REMAINEDON WITH THE SWITCH IN THE OFF' POSITION. INVESTIGA TION FOUND THE ACCESS PANEL CAM OPERATING THE PANEL POWER SWITCH WHEN THE PANEL IS CLOSED WAS OUT OF ADJUSTMENT AND NOT OPERATING THESWITCH. 2 L 7 2 4F 4 F RT E25NE 2001080800251 20010808 00251 NE 2001 8 8 AUS20010562 2 20010531 G 7200 6058T87G01 ENGINE SAAB SF340 SF340A 7850100 EU GE CT7TP CT75A2 30030 NE ROTOL R354 R3544123F13 NE RIGHT OVERHEATED W A UNSCHED LANDING E M VIBRATION/BUFFET OVER TEMP CR CRUISE 1 AU S (AUS) RT ENGINE OVERTEMPED DURING START UP AFTER INTENTIONAL SHUTDOWN. OVERTEMP WAS ABOVE 1000 DEGREES FOR 9 SECONDS. PE RSONNEL ERROR. 2 L 7 2 4T 4 T RT A52EU E8NE6 6 C P61GL 2001080800253 20010808 00253 NM 2001 8 8 AUS20010563 1 20010420 G 2752 5701802 JACKSCREW BOEING 737 737377 NM TE FLAPS CORRODED W O OTHER F FLT CONT AFFECTED AP APPROACH 1 AU S 18978 2773 (AUS) NR 3 TRAILING EDGE FLAP JACKSCREW CORRODED. SPALLING ON SCREWJACKBALL AND NUT. SUSPECT INCORRECT LUBRICANT USED. 2 L 7 2 4F RT A16WE 2001080800254 20010808 00254 EU 2001 8 8 AUS20010564 1 20010531 G 3213 350A41107620 SKID SHOE SNIAS 350 AS350BA 8680817 EU TMECA ARRIEL ARRIEL1B 6OO30 NE MAIN LANDING SEPARATED W O OTHER D INFLIGHT SEPARATION LD LANDING 1 AU S (AUS) RT SIDE SKID HEEL AND ATTACHMENT RING SEPARATED FROM AIRCRAFT. 1 G 7 1 3U 3 U NC H9EU E19EU 2001080800256 20010808 00256 NM 2001 8 8 AUS20010565 1 20010602 G 3240 BRAKE BOEING 747 747238B 1384828 NM RROYCE RB211 RB211524D419 54555 NE PARKING BRAKE FAULTY W D RETURN TO BLOCK O OTHER TX TAXI/GRND HDL 1 AU S (AUS) PARKING BRAKES WOULD NOT RELEASE. 2 L 7 4 4F 4 F A20WE E12EU 2001080700143 20010807 00143 NM 2001 8 7 AUS20010566 1 20010602 G 3230 651781914 ACTUATOR 654462514 BOEING 737 737376 NM CFMINT CFM56 CFM563C 13802 EU LANDING GEAR RET FAILED W K NONE O N OTHER FALSE WARNING AP APPROACH 1 AU S 29119 SC478 (AUS) NOSE LANDING GEAR DOWNLOCK ACTUATOR FAILED AT RODEND. 2 L 7 2 4F 4 F RT A16WE E21EU 2001080800257 20010808 00257 SW 2001 8 8 AUS20010567 1 20010604 G 3230 OAS54535 DRAG BRACE SWRNGN SA227 SA227AC 8780603 SW ROTOL R321 R321482F8 GL LANDING GEAR CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) MAIN LANDING GEAR DRAG BRACE CRACKED IN UPPER GREASE FITTING SPOT FACE WEB. FOUND DURING FLUORESCENT DYE PENETRANT INSPECTION IAW AD/SWSA/226/89 AND SB 227-32-043. 2 L 7 2 4T RT A8SW 6 C P61GL 2001080800259 20010808 00259 EU 2001 8 8 AUS20010568 1 20010525 G 2910 D2907019000200 MANIFOLD AIRBUS 320 A320* EU CFMINT CFM56 CFM565A1 NE HYDRAULIC SYSTEM CRACKED W K NONE K FLUID LOSS IN INSP/MAINT 1 AU S (AUS) HYDRAULIC POWER TRANSFER UNIT (PTU) MANIFOLD CRACKED AND LEAKING IN AREA OF CHECK VALVE MOUNTING FLANGE. 2 L 7 2 4F 4 F RT A46NM E29NE 2001080800261 20010808 00261 NM 2001 8 8 AUS20010569 1 20010602 G 3250 CONTROL UNIT BOEING 767 767338 1385151 NM GE CF6 CF680C2* GL NLG STEERING MALFUNCTIONED W D RETURN TO BLOCK J WARNING INDICATION TX TAXI/GRND HDL 1 AU S (AUS) AIRCRAFT STEERING SYSTEM INTERMITTENT IN OPERATION. THE CABLESAND PULLEYS WERE CHECKED OK AND THE RUDDER PEDAL INT ERCONNECT MECHANISM WAS LUBRICATED. 2 L 7 2 4F 4 F RT A1NM E23EA 2001080800263 20010808 00263 SW 2001 8 8 AUS20010570 1 20010531 G 2160 BYLB504371 VALVE SWRNGN SA227 SA227AC 8780603 SW GARRTT TPE331 TPE33111U 01514 WP HARTZL HCB3T HCB3TN5 GL CABIN TEMP SEIZED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) MIXING VALVE ACTUATOR FAILED. 2 L 7 2 4T 4 T RT A8SW E4WE 6 C P15EA 2001080800265 20010808 00265 SO 2001 8 8 AUS20010571 2 20010522 G 8520 466080 CRANKCASE CESSNA 182 182Q 2072732 CE CONT O470 O470U 17026 SO MCAULY 2A34C 2A34C203 GL ENGINE MISOVERHAULED W K NONE W INADEQUATE Q C IN INSP/MAINT 1 AU S (AUS) ENGINE CRANKCASE HALVES ASSEMBLED WITH A CONSIDERABLE AMOUNT OF SEALANT BETWEEN THE MATING FACES OF THE MAIN BEARI NG PEDESTALS. THIS RESULTED IN CRANKCASE FRETTING AND BEARING MOVEMENT. PERSONNEL/MAINTENANCE ERROR. INCORRECT ASSEMBLY. 1 H 7 1 3O 3 O NT 3A13 E273 5 C P3EA 2001080800266 20010808 00266 NM 2001 8 8 AUS20010572 1 20010531 G 3246 165T01100530 WHEEL BOEING 767 767338 1385151 NM GE CF6 CF680C2* GL MLG LOOSE W K NONE O OTHER IN INSP/MAINT 1 AU S 1154 (AUS) NR 1 MAIN WHEEL TIRE REMOVED FOR WEAR. DURING REMOVAL THE WHEELNUT RETENTION BOLTS, WASHER AND NUTS WERE FOUND TO BE ADRIFT AND THE WHEEL NUT WAS LOOSE AND BACKED OFF APPROXIMATELY FIVE TURNS.THE ANTI-SKID TRANSDUCER HOUSING WAS DAMAG ED. THE WHEEL NUT HAD IMPACT DAMAGE AND WHEEL NUT WASHER HAD EVIDENCE OF GALLING. NR 1 FRONT WHEEL ASSEMBLY REPLACED.ALS O REPLACED WERE THE ANTI-SKIDTRANSDUCER PNO 140-025-2, HUB CAP PNO 165T0101-107, WHEEL RETENTION NUT PNO 161T1204-1 ALON G WITH RETENTION BOLTS WASHERS AND NUTS. 2 L 7 2 4F 4 F RT A1NM E23EA 2001080800267 20010808 00267 NM 2001 8 8 AUS20010573 1 20010603 G 7603 CABLE RROYCE RB211524D4 BOEING 747 747338 NM RROYCE RB211 RB211524D419 54555 NE POWER LEVER WORN W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) DURING INSPECTION OF ENGINE THRUST CONTROL CABLES, FITTINGS AND PULLEYS IAW EI 743-076-0002 REV01 FIVE SEPARATE AR EAS OF CABLEWEAR WERE FOUND. FOUND DURING INSPECTION IAW AD/B747/229 AND FAAAD 2000-05-30 AMDT 39-11640. 2 L 7 2 4F 4 F RT A20WE E12EU 2001080800268 20010808 00268 WP 2001 8 8 AUS20010574 2 20010605 G 7210 31071627 GEAR SWRNGN SA227 SA227* SW GARRTT TPE331 TPE33112UHR WP MCAULY 4HFR34 4HFR34C652 NE RT ENGINE FAILED W E ENGINE SHUTDOWN E J VIBRATION/BUFFET WARNING INDICATION CR CRUISE 1 AU S 2490 (AUS) RT ENGINE FAILED. ENGINE OIL SYSTEM HEAVILY CONTAMINATED WITH METAL. INVESTIGATION FOUND FAILURE OF THE SUN/BULL G EAR.APPROXIMATELY 12 PERCENT OF THE BULL GEAR RIM HAD SEPARATED. DISASSEMBLY OF THE BULL GEAR FROM THE SUN GEAR REVEALED SEVERE FRETTING BETWEEN THE SUN GEAR REAR RACE FACE TO BULL GEAR INNER FORWARDINNER RACE FACE AND IN THE SUN GEAR TO BU LL GEAR SPLINES. 2 L 7 2 4T 4 T RT A5SW E4WE 6 C 3PNE 2001080800269 20010808 00269 CE 2001 8 8 AUS20010575 1 20010522 G 2933 51170071R SIGHT GLASS CESSNA 402 402C 207590R CE CONT O520 TSIO520VB 17040 SO MCAULY 3AF32C 3AF32C93 GL HYD QUANTITY SPLIT W K NONE K FLUID LOSS IN INSP/MAINT 1 AU S (AUS) HYDRAULIC SYSTEM SIGHT TUBE SPLIT. PARTIAL LOSS OF HYDRAULICFLUID. SIGHT TUBE HAD ONLY RECENTLY BEEN REPLACED. 1 L 7 2 3O 3 O A7CE E8CE 5 C P22EA 2001080700144 20010807 00144 CE 2001 8 7 AUS20010576 1 20010418 G 2932 991028710 PRESSURE SWITCH CESSNA 402 402C 207590R CE CONT O520 TSIO520VB 17040 SO MCAULY 3AF32C 3AF32C93 GL HYDRAULIC PRESSU FAULTY W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) HYDRAULIC PRESSURE SWITCH FAULTY. 1 L 7 2 3O 3 O A7CE E8CE 5 C P22EA 2001080700145 20010807 00145 SO 2001 8 7 AUS20010577 2 20010521 G 7414 IMPULSE COUPLING CONT IO520F CESSNA 206 U206G 2073356 CE CONT O520 IO520F 17032 SO MCAULY 3A32C D3A32C90 GL MAGNETO/DISTRIBU WORN W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) LH MAGNETO IMPULSE COUPLING WORN BEYOND LIMITS. FOUND DURINGINSPECTION IAW AD/ELEC/68. 1 H 7 1 3O 3 O A4CE E5CE 5 C P21EA 2001080700146 20010807 00146 CE 2001 8 7 AUS20010578 1 20010529 G 2410 646655 COUPLING CESSNA 402 402C 207590R CE CONT O520 TSIO520VB 17040 SO MCAULY 3AF32C 3AF32C93 GL ALTERNATOR-GENER FAULTY W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) RH ALTERNATOR ELASTOMER DRIVE COUPLING SLIPPING. FOUND DURING INSPECTION IAW MEB 01-3. 1 L 7 2 3O 3 O A7CE E8CE 5 C P22EA 2001080700147 20010807 00147 EA 2001 8 7 AUS20010579 2 20010604 G 7414 ES10357426 DISTRIBUTOR BENDIX 101630509 PIPER PA24 PA24250 7102404 SO LYC O540 O540A1D5 41532 EA MCAULY 2D36C 2D36C28 GL MAGNETO/DISTRIBU FAULTY W K NONE E VIBRATION/BUFFET TO TAKEOFF 1 AU S A34026 (AUS) MAGNETO DISTRIBUTOR BLOCK CENTRAL BUSH LOOSE ALLOWING THE DISTRIBUTOR GEAR TO PARTIALLY DISENGAGE AND SHEAR THE TE ETH. 1 L 7 1 3O 3 O 1A15 E295 5 C P901 2001080700148 20010807 00148 NM 2001 8 7 AUS20010580 1 20010424 G 3520 417T42050 OXYGEN MASK BOEING 767 767204 NM GE CF6 CF680A 30025 NE PASSENGER OXYGEN FAULTY W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) PASSENGER OXYGEN MASKS (7OFF) SUSPECT FAULTY. FOUND DURINGINSPECTION IAW AD/B767/125. 2 L 7 2 4F 4 F RT A1NM E13NE 2001080800270 20010808 00270 NM 2001 8 8 AUS20010581 1 20010406 G 2450 941D3352 CIRCUIT BREAKER BOEING 737 737377 NM AC POWER DISTRIB FAILED W A UNSCHED LANDING H ELECT. POWER LOSS-50 PC CL CLIMB 1 AU S 42099 (AUS) NR 1 GENERATOR BREAKER FAILED. 2 L 7 2 4F RT A16WE 2001080700149 20010807 00149 NE 2001 8 7 AUS20010582 2 20010227 G 7321 77390010 FCU LYC ALF502R5 BAC 146 146200A 1500266 EU LYC ALF502 ALF502R5 41580 NE FUEL CONTROL/TUR FAULTY W K NONE E VIBRATION/BUFFET NR NOT REPORTED 1 AU S 7600 F12203 (AUS) NO1 ENGINE FUEL CONTROL UNIT FAULTY. 2 H 7 4 4F 4 F A49EU E6NE 2001080800271 20010808 00271 NM 2001 8 8 AUS20010583 1 20010605 G 5610 NAS71037 SCREW DHAV DHC8 DHC8102 2809003 NM PWA 120 PW120A NE HAMSTD 14SF 14SF7 NE WINDOW WRONG PART W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) FLIGHT DECK SIDE WINDOW REPLACEMENT BOLTS TOO LONG. SB DHC8-56-05 SPECIFIES SCREW PNO NAS7103-7 WHICH WHEN FITTED ARE TOO LONG ANDBECOME SHANK BOUND. CONTACT WITH THE AIRCRAFT MANUFACTURER FOUND THAT THE SCREWS SHOULD BE PNO NAS7103-6 . THE RETORQUE PERIOD REQUIREMENT IN THE SERVICE BULLETIN IS ALSO SUSPECT BEING STATEDAS AFTER 24 HOURS'. 2 H 7 2 4T 4 T RT A13NM E20NE 6 C P7NE 2001080800272 20010808 00272 NM 2001 8 8 AUS20010584 1 20010605 G 2910 B4706640192 HOSE BOEING 737 737377 NM HYDRAULIC SYSTEM LEAKING W A UNSCHED LANDING K J FLUID LOSS WARNING INDICATION CL CLIMB 1 AU S (AUS) LH MAIN LANDING GEAR UPLOCK ACTUATOR HOSE LEAKING. METALCONTAMINATION OF NO1 HYDRAULIC PUMP FILTERS. 2 L 7 2 4F RT A16WE 2001080800273 20010808 00273 NM 2001 8 8 AUS20010585 1 20010601 G 2621 301000223 EXTINGUISHER BOEING 767 767338 1385151 NM GE CF6 CF680C2* GL LAVATORY MISSING W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) NO AUTOMATIC FIRE EXTINGUISHER FITTED TO THE FORWARD MID LAVATORY M-37. FOUND DURING INSPECTION IAW CAA AD GENERAL /48 AND FAA AD74-08-09. 2 L 7 2 4F 4 F RT A1NM E23EA 2001080700150 20010807 00150 SO 2001 8 7 AUS20010586 1 20010515 G 8120 4066109020 TURBOCHARGER LYC TIO540A2C PIPER PA31 PA31 7103102 SO LYC O540 TIO540A2C 41532 EA HARTZL HCE3Y HCE3YR2 GL EXHAUST TURBOCHA FAILED W K NONE E VIBRATION/BUFFET CR CRUISE 1 AU S 415 (AUS) LH ENGINE TURBOCHARGER LEAKING OIL. SUSPECT BEARING OR SEAL DAMAGED. AIRCRAFT HAD BEEN OUT OF SERVICE FOR APPROXIM ATELY NINEMONTHS FOR A SPAR REPLACEMENT. 1 L 7 2 3O 3 O A20SO E14EA 5 C P33EA 2001080700151 20010807 00151 SO 2001 8 7 AUS20010587 2 20010604 G 8550 S19644 DRAIN VALVE CONT IO520F CESSNA 207 207 2073602 CE CONT O520 IO520F 17032 SO MCAULY 2A34C D2A34C58 GL RECIPROCATING EN CRACKED W K E NONE ENGINE SHUTDOWN E K VIBRATION/BUFFET FLUID LOSS NR NOT REPORTED 1 AU S (AUS) ENGINE OIL DRAIN VALVE SHAFT CRACKED RADIALLY. OIL LEAKING ON SHUTDOWN. 1 H 7 1 3O 3 O A16CE E5CE 5 C P3EA 2001080800274 20010808 00274 EU 2001 8 8 AUS20010588 1 20010601 G 7930 154 CONNECTOR AEROSP AS365 AS365N2 8680815 EU TMECA ARRIEL ARRIEL1A 60030 NE CHIP DETECTOR FAULTY W A UNSCHED LANDING N FALSE WARNING CR CRUISE 1 AU S (AUS) NR 2 ENGINE CHIP DETECTOR WIRING FAULTY. 1 G 7 2 3U 3 U RT H10EU E19EU 2001080800275 20010808 00275 EU 2001 8 8 AUS20010589 1 20010528 G 3510 MC1012100 OXYGEN MASK AMD FALC50 FALCON900 2700160 EU COCKPIT LEAKING W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) PILOTS OXYGEN MASK LEAKING AT OXYGEN SUPPLY QUICK DISCONNECT. THIS DEFECT WAS RECEIVED FROM NO34 SQUADRON RAAF AND IS FOR INFORMATION ONLY. AIRCRAFT SERIAL A26-073. 2 L 7 3 4F RT A46EU 2001080800276 20010808 00276 EU 2001 8 8 AUS20010590 1 20010604 G 3240 C24837010 MANIFOLD AIRBUS 320 A320* EU CFMINT CFM56 CFM565A1 NE LANDING GEAR CRACKED W K NONE K FLUID LOSS IN INSP/MAINT 1 AU S 29336 B728 (AUS) LT BRAKE MANIFOLD LEAKING. INVESTIGATION FOUND A CRACK LOCATEDBETWEEN PORT A (SUPPLY LINE) AND FILTER CHAMBER. 2 L 7 2 4F 4 F RT A46NM E29NE 2001080800277 20010808 00277 SO 2001 8 8 AUS20010591 2 20010517 G 8530 EXHAUST VALVE CESSNA 206 U206G 2073356 CE CONT O520 IO520F 17032 SO ENGINE STUCK W K NONE O OTHER IN INSP/MAINT 1 AU S 141 (AUS) NR 2 CYLINDER EXHAUST VALVE STICKING IN VALVE GUIDE. FURTHER INSPECTION FOUND ALL EXHAUST VALVES STICKING AND ALL EXHAUST PUSHRODS BENT. SUSPECT VAVLE TO GUIDE CLEARANCE INSUFFICIENT AT MANUFACTURE. 1 H 7 1 3O 3 O A4CE E5CE 2001080700152 20010807 00152 NM 2001 8 7 AUS20010592 1 20010528 G 5610 NP15790114 WINDSHIELD DHAV DHC8 DHC8* NM FLIGHT COMPARTME CRACKED W K NONE O OTHER CR CRUISE 1 AU S (AUS) RH WINDSHIELD CRACKED. 2 H 7 2 4T RT A13NM 2001080700153 20010807 00153 SW 2001 8 7 AUS20010593 1 20010529 G 5302 206023119063 SUPPORT BELL 206 206L3 1182108 SW ALLSN 250C 250C30P 03013 GL ROTORCRAFT TAIL CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) HORIZONTAL STABILISER UPPER LH SUPPORT CRACKED LONGITUDINALLY ALONG BEND RADIUS. CRACK LENGTH 30MM (1.181IN). 1 G 7 1 3U 3 U H2SW E1GL 2001080700154 20010807 00154 SW 2001 8 7 AUS20010594 1 20010530 G 5302 206032400027 BULKHEAD BELL 206 206L3 1182108 SW ALLSN 250C 250C30P 03013 GL ROTORCRAFT TAIL CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) TAILBOOM BULKHEAD CRACKED ALONG THE BEND RADIUS OUTER CIRCUMFERENCE AT THE TOP RH BOLT ATTACHMENT INTERCOSTAL. CRA CKLENGTH 10MM (0.393IN). 1 G 7 1 3U 3 U H2SW E1GL 2001080800278 20010808 00278 EU 2001 8 8 AUS20010595 1 20010517 G 2760 SWITCH FOKKER F28 F28MK1000 4990808 EU RROYCE SPEY SPEY55515 54521 EU DRAG CONTROL OUT OF ADJ W O OTHER F FLT CONT AFFECTED LD LANDING 1 AU S (AUS) LIFT DUMPER MANIFOLD NR 2 BYPASS SWITCH OUT OF ADJUSTMENT. 2 L 7 2 4F 4 F RT A20EU E2EU 2001080800279 20010808 00279 NE 2001 8 8 AUS20010597 2 20010518 G 7310 FILTER DHAV DHC8 DHC8* NM PWA PW120 PW123 NE ENGINE FUEL CONTAMINATED W C ABORTED TAKEOFF E J VIBRATION/BUFFET WARNING INDICATION TO TAKEOFF 1 AU S (AUS) NR 2 HP OUTLET FUEL FILTER CONTAMINATED WITH A DARK BROWN SLUDGE. 2 H 7 2 4T 4 T RT A13NM E20NE 2001080700155 20010807 00155 EU 2001 8 7 AUS20010598 1 20010519 G 3241 95427193 GENERATOR FOKKER F28 F28MK1000 4990808 EU RROYCE SPEY SPEY55515 54521 EU BRAKE ANTISKID S FAULTY W K NONE O P OTHER NO WARNING INDICATION LD LANDING 1 AU S 3588 OCT7043 (AUS) RH INBOARD WHEEL SPEED GENERATOR FAULTY. 2 L 7 2 4F 4 F RT A20EU E2EU 2001080700156 20010807 00156 EU 2001 8 7 AUS20010601 1 20010526 G 2410 GENERATOR FOKKER F28 F28MK4000 4990810 EU RROYCE SPEY SPEY55515 54521 EU ALTERNATOR-GENER FAILED W K NONE H ELECT. POWER LOSS-50 PC CR CRUISE 1 AU S (AUS) NO1 GENERATOR FAILED. SUSPECT FAULTY CONSTANT SPEED DRIVE SWITCH. 2 L 7 2 4F 4 F RT A20EU E2EU 2001080700157 20010807 00157 EU 2001 8 7 AUS20010602 1 20010530 G 2421 976J2555 GENERATOR FOKKER F28 F28MK4000 4990810 EU RROYCE SPEY SPEY55515 54521 EU AC GENERATOR-ALT FAILED W K NONE H ELECT. POWER LOSS-50 PC DE DESCENT 1 AU S 397 MC823 (AUS) NO2 (RH) GENERATOR FAILED. 2 L 7 2 4F 4 F RT A20EU E2EU 2001080700158 20010807 00158 EU 2001 8 7 AUS20010603 1 20010526 G 5330 SKIN FOKKER F28 F28MK1000 4990808 EU RROYCE SPEY SPEY55515 54521 EU FUSELAGE MAIN, P CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) TOP FUSELAGE SKIN CRACKED IN AREA BETWEEN STN3845 AND STN4875.CRACK LENGTH 406.4MM (16IN). 2 L 7 2 4F 4 F RT A20EU E2EU 2001080800280 20010808 00280 WP 2001 8 8 AUS20010604 2 20010604 G 7250 31038381 ROTOR BAG JETSTM JETSTM3201 1500217 EU GARRTT TPE331 TPE33112UHR WP MCAULY 4HFR34 4HFR34C653 NE TURBINE SECTION DAMAGED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) RT ENGINE T3 TURBINE BLADE DAMAGED. 2 L 7 2 4T 4 T RT A56EU E4WE 6 C 3PNE 2001080800281 20010808 00281 NM 2001 8 8 AUS20010605 1 20010221 G 2540 10101000BA VALVE BOEING 737 737377 NM LAVATORIES FAULTY W K NONE O OTHER IN INSP/MAINT 1 AU S 3340 (AUS) TOILET DRAIN VALVE FAULTY. FOUND DURING TESTING IAW ER B73-30-11. 2 L 7 2 4F RT A16WE 2001080700159 20010807 00159 NM 2001 8 7 AUS20010607 1 20010520 G 2750 7321870011 VALVE BOEING 767 767277 NM GE CF6 CF680A 30025 NE TRAILING EDGE FL FAILED W K NONE F J FLT CONT AFFECTED WARNING INDICATION CL CLIMB 1 AU S 93043 (AUS) FLAP/SLAT SHUTOFF VALVE FAILED. 2 L 7 2 4F 4 F RT A1NM E13NE 2001080800282 20010808 00282 EU 2001 8 8 AUS20010608 1 20010607 G 2910 AE7064588 HOSE SAAB SF340 340B 7860101 EU GE CT7TP CT79B 30030 NE ROTOL R375 R3754123F21 NE HYDRAULIC SYSTEM FAILED W C ABORTED TAKEOFF K J FLUID LOSS WARNING INDICATION TO TAKEOFF 1 AU S 21142 (AUS) NOSE LANDING GEAR HYDRAULIC UP LINE FAILED. LOSS OF HYDRAULIC FLUID. 2 L 7 2 4T 4 T RT A52EU E8NE 6 C P17NE 2001080800283 20010808 00283 SO 2001 8 8 AUS20010609 2 20010525 G 8530 641917 CYLINDER CESSNA 150 150F 2071814 CE CONT O200 O200A 17020 SO MCAULY 1A100 1A100MCM GL ENGINE CRACKED W A UNSCHED LANDING E VIBRATION/BUFFET CR CRUISE 1 AU S 1500 (AUS) ENGINE CYLINDER ROCKER SHAFT SUPPORT CRACKED AND SEPARATED FROM CYLINDER HEAD. 1 H 7 1 3O 3 O 3A19 E252 5 N P918 2001080800284 20010808 00284 EA 2001 8 8 AUS20010611 2 20010613 G 8530 PISTON RING PIPER PA28 PA28180 7102808 SO LYC O360 O360A3A 41514 EA ENGINE FAILED W K NONE O OTHER IN INSP/MAINT 1 AU S 1015 (AUS) NR 3 CYLINDER FIRST AND SECOND PISTON RINGS BROKEN. PISTON LANDERODED. NR 4 CYLINDER NO1 PISTON RING BROKEN. PISTO N RINGS WERECAST IRON IN CHROME CYLINDERS. SMALL AMOUNT OF ALUMINIUM ALLOYMETAL IN OIL FILTER. 1 L 7 1 3O 3 O 2A13 E286 2001080700160 20010807 00160 CE 2001 8 7 AUS20010612 1 20010608 G 5610 WINDSHIELD CESSNA 421C CESSNA 421 421C 2076016 CE CONT O520 GTSIO520M 17032 SO MCAULY 3FF32 3FF32C501 GL FLIGHT COMPARTME FAULTY W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) WINDSHIELD LEAKING. HEATING SYSTEM PIPES BROKEN CAUSING EXCESSHEAT AND WARPING OF WINDSHIELD. 1 L 7 2 3O 3 O A7CE E7CE 5 C P45GL 2001080800285 20010808 00285 CE 2001 8 8 AUS20010613 1 20010612 G 6120 5052447815 SPRING BEECH 1900 1900C 1154161 CE PWA PT6 PT6A65B 52043 EA HARTZL HCB4M HCB4MP3 GL PROPELLER BROKEN W O OTHER O OTHER NR NOT REPORTED 1 AU S (AUS) LH PROPELLER PITCH CONTROL LEVER FEATHER DETENT FEEL SPRING BROKEN. 2 L 7 2 4T 4 T RT A24CE E4EA 6 C P56GL 2001080700161 20010807 00161 SO 2001 8 7 AUS20010614 2 20010612 G 7421 RHB32E SPARK PLUG CONT TSIO520VB CESSNA 402 402C 207590R CE CONT O520 TSIO520VB 17040 SO MCAULY 3AF32C 3AF32C93 GL SPARK PLUG/IGNIT CORRODED W K NONE E VIBRATION/BUFFET CR CRUISE 1 AU S (AUS) LH ENGINE SPARK PLUG CORRODED AND FOULED. 1 L 7 2 3O 3 O A7CE E8CE 5 C P22EA 2001080800286 20010808 00286 NM 2001 8 8 AUS20010615 1 20010508 G 4930 36080004 FCU BOEING 737 737377 NM APU ENGINE FAULTY W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) APU FUEL CONTROL UNIT FAULTY. INVESTIGATION FOUND PISTON ANDSHAFT SET IN TIMER WORN. THE GOVERNOR SHAFT WAS WORN. FLYWEIGHT TOES WORN. PACKINGS AND SEALS FLAT AND WORN. 2 L 7 2 4F RT A16WE 2001080800287 20010808 00287 NM 2001 8 8 AUS20010616 1 20010426 G 2822 6075504 PUMP BOEING 747 747238B 1384828 NM FUEL BOOST PUMP LEAKING W K NONE K FLUID LOSS IN INSP/MAINT 1 AU S 7670 069714832A (AUS) NR 3 AFT FUEL BOOST PUMP LEAKING FROM AREA BEHIND ELECTRICAL CONNECTOR. 2 L 7 4 4F A20WE 2001080800288 20010808 00288 NM 2001 8 8 AUS20010617 1 20010415 G 5320 WEB BOEING 747 747238B 1384828 NM FUSELAGE CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) NOSE WHEEL WELL UPPER WEB LOCATED AT STN291 CRACKED AT RBL19 ANDLBL19. 2 L 7 4 4F A20WE 2001080700162 20010807 00162 NM 2001 8 7 AUS20010618 1 20010420 G 5313 146T30037 STRINGER BOEING 767 767277 NM GE CF6 CF680A 30025 NE FUSELAGE MAIN, L CORRODED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) STRINGER 39L BADLY CORRODED IN THE AREA LOCATED BETWEEN BS1285AND BS1307. APPROXIMATELY 304.8MM (12IN) OF THE HAT SECTIONED STRINGER LOWER CHANNEL WAS SEVERELY CORRODED WITH PORTIONS OF THE CHANNEL TOTALLY DESTROYED. 2 L 7 2 4F 4 F RT A1NM E13NE 2001080800289 20010808 00289 NE 2001 8 8 AUS20010619 2 20010616 G 7200 ENGINE BAG BAE146 BAE146100A 1500260 EU LYC ALF502 ALF502R5 41580 NE NR 2 LEAKING W K NONE B SMOKE/FUMES/ODORS/SPARKS IN INSP/MAINT 1 AU S (AUS) NR 2 ENGINE LEAKING CONTAMINATED AIR INTO CABIN. 2 H 7 4 4F 4 F RT A49EU E6NE 2001080800290 20010808 00290 CE 2001 8 8 AUS20010620 1 20010612 G 2752 100384040 MOTOR BEECH 200 200BEECH 1152920 CE PWA PT6 PT6A42 52043 NE MCAULY 4HFR34 4HFR34C754 NE TE FLAPS BURNED OUT W A UNSCHED LANDING F FLT CONT AFFECTED DE DESCENT 1 AU S 514 (AUS) TRAILING EDGE FLAP ELECTRIC MOTOR WINDINGS BURNT OUT. SUSPECT CAUSED BY FAILURE OF DYNAMIC BRAKE. 1 L 7 2 4T 4 T A24CE E4EA 6 C 3PNE 2001080700163 20010807 00163 CE 2001 8 7 AUS20010621 1 20010608 G 3213 45815237 PIN BEECH 58 58 1152740 CE CONT O520 IO520C 17032 SO MCAULY 3AF32C D3AF32C35 GL MAIN LANDING GEA CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) LH AND RH MAIN LANDING GEAR LOWER TORQUE LINK PINS CRACKED IN THE POSITIONING HOLES. 1 L 7 2 3O 3 O 3A16 E5CE 5 C P22EA 2001080800291 20010808 00291 EU 2001 8 8 AUS20010622 1 20010616 G 5330 SKIN BAG BAE146 BAE146200A 1500266 EU LYC ALF502 ALF502R3A 41580 NE FUSELAGE CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) FUSELAGE SKIN CRACKED IN AREA LOCATED IMMEDIATELY AFT OF FRAME 29 BENEATH THE WING ROOT DOUBLER. FOUND DURING INSP ECTION IAWISB53-144 AND AD/BAE146/70. 2 H 7 4 4F 4 F RT A49EU E6NE 2001080800292 20010808 00292 NE 2001 8 8 AUS20010623 2 20010613 G 7230 230318706 SEAL BAC 146 146200A 1500266 EU LYC ALF502 ALF502R5 41580 NE ENGINE LEAKING W O OTHER B SMOKE/FUMES/ODORS/SPARKS NR NOT REPORTED 1 AU S 4333 (AUS) NR 2 ENGINE OIL LEAKING IN BLEED BAND AREA. OIL SMELL IN COCKPIT.SUSPECT CAUSED BY NO1 OIL SEAL WORN AND LEAKING. 2 H 7 4 4F 4 F A49EU E6NE 2001080800293 20010808 00293 EU 2001 8 8 AUS20010624 1 20010607 G 3240 C24837010 MANIFOLD AIRBUS 320 A320* EU CFMINT CFM56 CFM565A1 NE LANDING GEAR CRACKED W K NONE K FLUID LOSS IN INSP/MAINT 1 AU S B353 (AUS) LT MAIN LANDING GEAR BRAKE SERVO MANIFOLD LEAKING FROM AREA OFFILTER CAP. INVESTIGATION FOUND A 19.05MM (0.75IN) C RACK IN THE FILTER CHAMBER THREADS. 2 L 7 2 4F 4 F RT A46NM E29NE 2001080700164 20010807 00164 CE 2001 8 7 AUS20010625 1 20010603 G 2720 07331131 CLIP CESSNA 182 182Q 2072732 CE CONT O470 O470U 17026 SO MCAULY 2A34C 2A34C203 GL RUDDER CONTROL S FAILED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) RH RUDDER STOP T' CLIP PNO 733113-1 TO SUPPORT PNO 1231021-8 ATTACHMENT RIVETS (2OFF) PNO MS20426-AD4 SHEARED. SUS PECT CAUSED BY WIND GUSTS. 1 H 7 1 3O 3 O NT 3A13 E273 5 C P3EA 2001080800294 20010808 00294 NM 2001 8 8 AUS20010626 1 20010615 G 5330 149T7500145 PANEL BOEING 767 767338 1385151 NM GE CF6 CF680C2* GL FUSELAGE MISSING W O OTHER D INFLIGHT SEPARATION NR NOT REPORTED 1 AU S (AUS) FUSELAGE PANEL MISSING FROM LH WING ROOT AREA LOCATED FORWARD OFTHE LH OFF-WING ESCAPE SLIDE DOOR. SCORE MARKS EVI DENT ON ADJACENT WING TO BODY FAIRING AND FUSELAGE AT STN1131. 2 L 7 2 4F 4 F RT A1NM E23EA 2001080800295 20010808 00295 NM 2001 8 8 AUS20010627 1 20010618 G 7500 65B899268 DUCT BOEING 747 747438 NM RROYCE RB211 RB211524G19 NE ENGINE BLEED AIR FAILED W A UNSCHED LANDING M J OVER TEMP WARNING INDICATION CR CRUISE 1 AU S (AUS) NR 3 ENGINE STRUT DUCT HOLED AND DEFORMED. INVESTIGATION COULD FIND NO HEAT DAMAGE IN THE STRUT. 2 L 7 4 4F 4 F RT A20WE E30NE 2001080700165 20010807 00165 CE 2001 8 7 AUS20010629 1 20010608 G 5711 0001100132 SPAR CAP BEECH 58 BEECH 58 58 1152740 CE CONT O520 IO520C 17032 SO MCAULY 3AF32C D3AF32C35 GL WING SPAR CORRODED W K NONE O OTHER IN INSP/MAINT 1 AU S TH181 (AUS) RH WING UPPER SPAR CAP CONTAINED PITTING CORROSION IN AN AREA LOCATED 355.6MM (14IN) OUTBOARD OF THE ENGINE NACELL E. THE PITTED AREA MEASURES APPROXIMATELY 152.4MM (6IN) SPANWISE AND 19.05MM(0.75IN) CHORDWISE. DEPTH OF CORROSION APPRO XIMATELY 0.508MM(0.020IN). FOUND FOLLOWING STRIPPING FOR REPAINT. 1 L 7 2 3O 3 O 3A16 E5CE 5 C P22EA 2001080700166 20010807 00166 NM 2001 8 7 AUS20010630 1 20010127 G 2910 13206001 SWITCH 13206XXX BOEING 767 767238 NM PWA JT9 JT9D7R4E 52054 NE HYDRAULIC SYSTEM FAULTY W K NONE J WARNING INDICATION CR CRUISE 1 AU S (AUS) LH HYDRAULIC TAIL SHUTOFF VALVE SWITCH MODULE FAULTY. 2 L 7 2 4F 4 F RT A1NM E3NE 2001080800296 20010808 00296 NM 2001 8 8 AUS20010631 1 20010619 G 2720 2417001007 MODULE BOEING 747 747SP38 NM RROYCE RB211 RB211524D419 54555 NE RUDDER CONTROL LEAKING W K NONE K FLUID LOSS IN INSP/MAINT 1 AU S 18014 105 (AUS) RUDDER CONTROL MODULE LEAKING. 2 L 7 4 4F 4 F RT A20WE E12EU 2001080800297 20010808 00297 CE 2001 8 8 AUS20010632 1 20010611 G 5343 12116013 FITTING CESSNA 206 U206G 2073356 CE CONT O520 IO520F 17032 SO LANDING GEAR CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) LH OUTBOARD LANDING GEAR ATTACHMENT FITTING CRACKED. CRACK LENGTH 19.05MM (0.75IN). 1 H 7 1 3O 3 O A4CE E5CE 2001080700167 20010807 00167 EA 2001 8 7 AUS20010633 2 20010530 G 8520 38125015 STUD LYC TIO540J2BD PIPER PA31 PA31350 7103110 SO LYC O540 TIO540J2BD 41532 EA HARTZL HCE3Y HCE3YR2 GL RECIPROCATING EN BROKEN W K NONE O E K OTHER VIBRATION/BUFFET FLUID LOSS IN INSP/MAINT 1 AU S L778561A (AUS) LH ENGINE NO3 CYLINDER HOLDDOWN STUDS BROKEN. CYLINDER WAS HELD IN PLACE BY THE THROUGH BOLTS ONLY. 1 L 7 2 3O 3 O A20SO E14EA 5 C P33EA 2001080800298 20010808 00298 EU 2001 8 8 AUS20010634 1 20010619 G 6220 350A31190703 STARFLEX AEROSP 355A310002 SNIAS 350 AS350B3 8680954 EU TMECA ARRIEL ARRIEL2B NE MAIN ROTOR HEAD DEBONDED W O OTHER F FLT CONT AFFECTED LD LANDING 1 AU S M1803 (AUS) MAIN ROTOR STAR BEARING BUSH DEBONDED AND MOVED OUTBOARD ALLOWING THE MAIN ROTOR BLADE TO LAG AND CAUSE LATERAL VI BRATION. 1 G 7 1 3U 3 U H9EU E00054EN 2001080800299 20010808 00299 NM 2001 8 8 AUS20010635 1 20010618 G 2150 7744694 ACM BOEING 747 747438 NM RROYCE RB211 RB211524G19 NE CABIN COOLING SY FAULTY W D RETURN TO BLOCK F B FLT CONT AFFECTED SMOKE/FUMES/ODORS/SPARKS TX TAXI/GRND HDL 1 AU S 668 (AUS) NR 1 AIRCONDITIONING SYSTEM AIR CYCLE MACHINE FAULTY. 2 L 7 4 4F 4 F RT A20WE E30NE 2001080800301 20010808 00301 NE 2001 8 8 AUS20010636 2 20010617 G 8520 MASTER ROD DOUG DC3 DC3CS1C3G 3021458 WP PWA R1830 R183092 52020 NE HAMSTD 23E 23E50 NE ENGINE FAILED W C ABORTED TAKEOFF E K VIBRATION/BUFFET FLUID LOSS TO TAKEOFF 1 AU S (AUS) RT ENGINE NR 5 CYLINDER MASTER ROD FAILED AT BASE. LOSS OF ENGINEOIL. 2 L 7 2 4R 4 R A669 5E4 6 C P603 2001080800302 20010808 00302 EU 2001 8 8 AUS20010637 1 20010607 G 3240 C24837010 MANIFOLD AIRBUS 320 A320* EU CFMINT CFM56 CFM565A1 NE LANDING GEAR CRACKED W K NONE K FLUID LOSS IN INSP/MAINT 1 AU S B353 (AUS) LH MAIN LANDING GEAR BRAKE SERVO MANIFOLD CRACKED. INVESTIGATIONFOUND A CRACK IN THE FILTER CHAMBER THREADS. CRACK LENGTH 19.05MM (0.75IN). 2 L 7 2 4F 4 F RT A46NM E29NE 2001080800303 20010808 00303 EU 2001 8 8 AUS20010638 1 20010510 G 5343 D5337061320200 FITTING AIRBUS 320 A320* EU CFMINT CFM56 CFM565A1 NE LANDING GEAR CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) MAIN LANDING GEAR DOOR ACTUATOR FITTINGS CRACKED FROM FASTENERHOLES. FOUND DURING INSPECTION IAW SB A320-53-1135 A ND ANSETT ERA32-53-40-9C. 2 L 7 2 4F 4 F RT A46NM E29NE 2001080800304 20010808 00304 NM 2001 8 8 AUS20010639 1 20010617 G 7110 3859741B12130620 BRACKET GE CF680C2 BOEING 767 767338 1385151 NM GE CF6 CF680C2* GL ENGINE COWLING BROKEN W K NONE O OTHER IN INSP/MAINT 1 AU S R648117 (AUS) NR 1 ENGINE INBOARD THRUST REVERSER COWL V' BAND HOOK BRACKET BROKEN. 2 L 7 2 4F 4 F RT A1NM E23EA 2001080700168 20010807 00168 SW 2001 8 7 AUS20010640 1 20010603 G 2460 A1077V RELAY BELL 206 206L1 1182107 SW ALLSN 250C 250C30 03013 GL DC POWER DISTRIB FAILED W K NONE H ELECT. POWER LOSS-50 PC CR CRUISE 1 AU S (AUS) GENERATOR LINE CONTACT RELAY FAULTY. 1 G 7 1 3U 3 U H2SW E1GL 2001080800305 20010808 00305 SW 2001 8 8 AUS20010641 1 20010606 G 2910 2281032135 PIPE SWRNGN SA227 SA227AC 8780603 SW GARRTT TPE331 TFE33112UHR WP ROTOL R321 R321482F8 GL HYDRAULIC SYSTEM WORN W A UNSCHED LANDING F FLT CONT AFFECTED CR CRUISE 1 AU S (AUS) HYDRAULIC PIPE CHAFING AGAINST ADJOINING PIPE. LOSS OF HYDRAULICSYSTEM FLUID. 2 L 7 2 4T 4 T RT A8SW E4WE 6 C P61GL 2001080700169 20010807 00169 SW 2001 8 7 AUS20010642 1 20010614 G 5740 AN616 BOLT BBAVIA 7 7GCAA 21101N8 SW LYC O320 O320A2D 41508 EA SNSNCH 74D 74DM EA WING, ATTACH FIT CORRODED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) LOWER RH SIDE STRUT LOWER BOLT SEIZED. FOLLOWING BOLT REMOVAL ITWAS FOUND TO BE VERY RUSTED AND PITTED. 1 H 7 1 3O 3 O A759 E274 5 N P88614 2001080700170 20010807 00170 CE 2001 8 7 AUS20010643 1 20010601 G 2720 530040050 CONTROL CABLE CESSNA 340 340A 2076405 CE CONT O520 TSIO520N 17040 SO MCAULY 3AF32C 3AF32C93 GL RUDDER CONTROLS FRAYED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) YAW DAMPER CABLE FRAYED AND STRANDS BROKEN IN AREA WHERE THECABLE PASSES INTO THE TERMINAL FITTING AT THE RUDDER B ELLCRANK. 1 L 7 2 3O 3 O 3A25 E8CE 5 C P22EA 2001080800307 20010808 00307 NM 2001 8 8 AUS20010644 1 20010620 G 2131 7120977 CONTROLLER BOEING 747 747338 NM RROYCE RB211 RB211524D419 54555 NE CABIN PRESSURE FAULTY W A UNSCHED LANDING J WARNING INDICATION CR CRUISE 1 AU S 79G1173 (AUS) PRESSURISATION SYSTEM OUTFLOW VALVES SLIGHTLY OPEN. INVESTIGATION COULD FIND NO CAUSE OF THE DEFECT. THE CABIN PRE SSURE CONTROLLERWAS REPLACED BUT FOUND TO SERVICEABLE WHEN WORKSHOP TESTED. 2 L 7 2 4F 4 F RT A20WE E12EU 2001080700171 20010807 00171 CE 2001 8 7 AUS20010645 1 20010612 G 2434 BEARING ALV9510R CESSNA 421 421C 2076016 CE CONT O520 GTSIO520N 17032 SO MCAULY 3FF32 3FF32C501 GL DC GENERATOR-ALT FAILED W K NONE H ELECT. POWER LOSS-50 PC CR CRUISE 1 AU S 18 (AUS) LH ALTERNATOR. INVESTIGATION FOUND REAR BEARING COLLAPSED CAUSING DRIVE ADAPTER FAILURE AND METAL CONTAMINATION OF THE ENGINE. 1 L 7 2 3O 3 O A7CE E7CE 5 C P45GL 2001080700172 20010807 00172 CE 2001 8 7 AUS20010647 1 20010621 G 3710 212CW PUMP AIRBORNE 212CW BEECH 55 D55 1152730 CE CONT O520 IO520C 17032 SO MCAULY 2AF34C 2AF34C55 GL VACUUM DISTRIBUT FAILED W K NONE I FLT. ATTITUDE INST. NR NOT REPORTED 1 AU S 23J119 (AUS) LH ENGINE DRIVEN VACUUM PUMP ROTOR SEIZED AND DRIVESHAFT SHEARED. 1 L 7 2 3O 3 O 3A16 E5CE 5 C P5EA 2001080700173 20010807 00173 EA 2001 8 7 AUS20010648 2 20010531 G 8540 67583 GEAR LYC VO540C2A HILLER UH12 UH12E 4360122 WP LYC O540 VO540C2A 41532 EA RECIPROCATING EN FAILED W K NONE E Y VIBRATION/BUFFET ENGINE STOPPAGE NR NOT REPORTED 1 AU S L146243 (AUS) ENGINE DRIVE GEAR PNO 67583 HAD SHEARED ALL THE BOLTS ATTACHING IT TO ACCESSORY DRIVE PNO 67609. 1 G 7 1 3O 3 O 4H11 E304 2001080800315 20010808 00315 NM 2001 8 8 AUS20010649 1 20010621 G 3244 A2409 TIRE BOEING 747 747438 NM RROYCE RB211 RB211524G19 NE MLG FAILED W C ABORTED TAKEOFF O OTHER TO TAKEOFF 1 AU S 9652 (AUS) LT REAR INBOARD MAIN BODY GEAR TYRE (NO4) FAILED. DAMAGE CAUSED TO FUSELAGE AND FAIRINGS AND LANDING GEAR WIRING L OOM. 2 L 7 4 4F 4 F RT A20WE E30NE 2001080700174 20010807 00174 SW 2001 8 7 AUS20010650 1 20010623 G 5313 206031314037 LONGERON BELL 206L1 BELL 206 206L1 1182107 SW ALLSN 250C 250C30P 03013 GL FUSELAGE MAIN, L CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S 10824 45323 (AUS) FUSELAGE LONGERON CRACKED BETWEEN TWO RIVETS. 1 G 7 1 3U 3 U H2SW E1GL 2001080800316 20010808 00316 EU 2001 8 8 AUS20010652 1 20010622 G 5610 NP1701012 WINDSHIELD BAG BAE146 BAE146300A 1500267 EU LYC ALF502 ALF502R5 41580 NE COCKPIT FAILED W K NONE O OTHER IN INSP/MAINT 1 AU S 96249H6419 (AUS) RT A' WINDSHIELD ASSEMBLY OUTER PANE SHATTERED. 2 H 7 4 4F 4 F RT A49EU E6NE 2001080800320 20010808 00320 EU 2001 8 8 AUS20010653 1 20010607 G 5210 FGFB222030060A2 CLEVIS AMD FALC50 FALCON900 2700160 EU GARRTT TFE731 TFE7315BR WP PAX/CREW DOOR CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) MAIN ENTRY DOOR COMPENSATING SPRING CLEVIS CRACKED ACROSS ALL THREE CABLE ATTACHMENT LUGS. AIRCRAFT SERIAL NUMBER A26-074.FLEET INSPECTION FOUNDTHE CLEVIS CRACKED ON ALL OTHER AIRCRAFTIN THE RAAF FLEET. THIS DEFECT WAS RECEIVED FROM T HE RAAF AND ISENTERED FOR INFORMATION ONLY. 2 L 7 3 4F 4 F RT A46EU E6WE 2001080800322 20010808 00322 2001 8 8 AUS20010655 4 20010626 G 3418 18617RX DETECTOR REIMS 406 F406 EU PWA PT6 PT6A112 52043 NE MCAULY 3G34C7 3GFR34C701 GL STALL WARNING SY FAULTY W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) LIFT DETECTOR FAULTY. SWITCH OPERATES IN OPPOSITE SENSE. 1 L 7 2 3T 3 T RT A54EU E4EA 5 C P60GL 2001080800323 20010808 00323 2001 8 8 AUS20010656 4 20010620 G 3418 18617RX DETECTOR REIMS 406 F406 EU PWA PT6 PT6A112 52043 NE MCAULY 3G34C7 3GFR34C701 GL STALL WARNING FAULTY W K NONE O OTHER IN INSP/MAINT 1 AU S 263 (AUS) LIFT DETECTOR FAULTY. DETECTOR MICROSWITCH OPERATES IN OPPOSITE SENSE. SWITCH SPRING LOADED UP. PERSONNEL/MAINTENA NCE ERROR.MANUFACTURING ERROR. 1 L 7 2 3T 3 T RT A54EU E4EA 5 C P60GL 2001080800324 20010808 00324 NE 2001 8 8 AUS20010657 2 20010625 G 7250 UL36853 SUPPORT RROYCE RB211524G BOEING 747 747438 NM RROYCE RB211 RB211524G19 NE TURBINE SECTION LEAKING W K NONE K FLUID LOSS IN INSP/MAINT 1 AU S 576 13044 (AUS) ENGINE HP/IP TURBINE BEARING SUPPORT OIL PIPE LEAKING AT SUPPORTATTACHMENT. 2 L 7 4 4F 4 F RT A20WE E30NE 2001080800325 20010808 00325 EU 2001 8 8 AUS20010658 1 20010430 G 5343 D5337061320200 FITTING D53370613203 AIRBUS 320 A320* EU CFMINT CFM56 CFM565A1 NE LANDING GEAR CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) MAIN LANDING GEAR DOOR ACTUATOR FITTINGS (4OFF) CRACKED FROM THEUPPER TWO FASTENER HOLES IN THE VERTICAL FLANGE. 2 L 7 2 4F 4 F RT A46NM E29NE 2001080800327 20010808 00327 NM 2001 8 8 AUS20010659 1 20010503 G 5755 656718613 FITTING BOEING 737 737377 NM SPOILERS FRACTURED W K NONE O OTHER IN INSP/MAINT 1 AU S MA2489 (AUS) LT INBOARD GROUND SPOILER CENTRE OUTBOARD HINGE FITTING HAD A MISSING PIECE ALLOWING THE HINGE BEARING TO LOOSEN I N THE FITTING. 2 L 7 2 4F RT A16WE 2001080700175 20010807 00175 NM 2001 8 7 AUS20010660 1 20010615 G 6310 A1681 PLATE ROBSIN R22 R22BETA NM LYC O360 O360J2A 41514 EA ENGINE/TRANSMISS CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) CLUTCH SEAL PLATE CRACKED IN MORE THAN ONE PLACE ON BOTH SIDES. 1 G 7 1 3O 3 O H10WE E286 2001080800328 20010808 00328 EU 2001 8 8 AUS20010661 1 20010510 G 5343 D5337061320200 FITTING AIRBUS 320 A320* EU CFMINT CFM56 CFM565A1 NE LANDING GEAR CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) MAIN LANDING GEAR DOOR ACTUATOR ATTACHMENT FITTINGS (4OFF)CRACKED FROM TOP TWO FASTENER HOLES IN THE VERTICAL FLAN GE. 2 L 7 2 4F 4 F RT A46NM E29NE 2001080700176 20010807 00176 SO 2001 8 7 AUS20010662 1 20010626 G 5540 4004009 TORQUE TUBE PIPER PA31 PA31 7103102 SO LYC O540 TIO540A2C 41532 EA HARTZL HCE2Y HCE2YK2 GL RUDDER STRUCTURE CORRODED W K NONE O OTHER IN INSP/MAINT 1 AU S 7066 (AUS) RUDDER TORQUE TUBE CORRODED BOTH INTERNALLY AND EXTERNALLY. 1 L 7 2 3O 3 O A20SO E14EA 5 C P9EA 2001080700177 20010807 00177 NM 2001 8 7 AUS20010663 1 20010625 G 3230 DSC1831 RELAY DHAV DHC8 DHC8102 2809003 NM PWA 120 PW120A NE HAMSTD 14SF 14SF7 NE LANDING GEAR RET FAULTY W K NONE O OTHER DE DESCENT 1 AU S (AUS) LANDING GEAR DOOR SEQUENCE CONTROL RELAY K12 FAULTY. DURING FUNCTION CHECKS RELAY K13 PNO DSC183-2 WAS ALSO FOUND TO BE FAULTY. 2 H 7 2 4T 4 T RT A13NM E20NE 6 C P7NE 2001080800330 20010808 00330 NM 2001 8 8 AUS20010664 1 20010308 G 5210 BACB10FK6F6HS ROLLER BOEING 737 73733A 1384673 NM PAX DOOR SEIZED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) PASSENGER DOOR R1 SEQUENCING CAM ROLLER SEIZED AND DISINTEGRATEDPREVENTING CORRECT OPERATION OF DOOR. 2 L 7 2 4F RT A16WE 2001080700178 20010807 00178 CE 2001 8 7 AUS20010665 1 20010426 G 3243 98820104 CYLINDER CESSNA 182 182S 2072701 CE LYC O540 IO540AB1A5 EA MCAULY 3D36C B3D36C431 GL MASTER CYLINDER/ LEAKING W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) RH BRAKE MASTER CYLINDER LEAKING AT ELBOW FITTING. INVESTIGATIONFOUND THAT THE ELBOW HAD NOT BEEN FULLY SCREWED IN AND THESEALING O' RING WAS DISPLACED ONTO THE THREADS OF THE ELBOW INSTEAD OF FITTING INTO THE SEAL RECESS DUE TO THE B' NUTCOVERING THE RECESS. 1 H 7 1 3O 3 O NT 3A13 1E4 5 C 2001080800331 20010808 00331 NE 2001 8 8 AUS20010666 2 20010624 G 7260 208315905 MOUNT BAC 146 146100A 1500260 EU LYC ALF502 ALF502R5 41580 NE ENGINE BROKEN W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) NR 1 ENGINE CSD MOUNTING RING MOUNTING BOSSES (5OFF) BROKEN AWAY. 2 H 7 4 4F 4 F RT A49EU E6NE 2001080800332 20010808 00332 NM 2001 8 8 AUS20010667 1 20010628 G 7830 13169 DOOR RROYCE RB211524G BOEING 747 747438 NM RROYCE RB211 RB211524G19 NE THRUST REVERSER FAILED W K NONE O OTHER IN INSP/MAINT 1 AU S 12575 13169 (AUS) NR 3 ENGINE NR 10 THRUST REVERSER BLOCKER DOOR PARTLY MISSING WITH DAMAGE TO THE CORONA LOCATED AFT OF THE DOOR PO SITION AND A SMALL TEAR ON THE CORONA ACOUSTIC PANEL. 2 L 7 4 4F 4 F RT A20WE E30NE 2001080800334 20010808 00334 NE 2001 8 8 AUS20010668 2 20010628 G 7200 RB211524D419 ENGINE BOEING 747 747338 NM RROYCE RB211 RB211524D419 54555 NE NR 2 VIBRATES W A UNSCHED LANDING E F VIBRATION/BUFFET FLT CONT AFFECTED CR CRUISE 1 AU S 254 (AUS) NR 2 ENGINE EXCESSIVE VIBRATION. ENGINE INSPECTED IAW MAINTENANCEMANUALS WITH NO FAULTS FOUND. HPC STAGES 5/6 BORO SCOPED AND FOUND OK. AIRCRAFT RETURNED TO SERVICE. 2 L 7 2 4F 4 F RT A20WE E12EU 2001080700179 20010807 00179 NM 2001 8 7 AUS20010669 1 20010620 G 5230 6546921225 DOOR BOEING 737 737476 NM CFMINT CFM56 CFM563C 13802 EU CARGO/BAGGAGE DO CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S 35309 001895 (AUS) FORWARD CARGO DOOR CRACKED IN THE RADIUS OF THE FORWARD OUTBOARDCORNER ANGLE. CRACK LENGTH 35.56MM (1.4IN). FOUND DURINGINSPECTION IAW EI 737-052-0003, FAA AD2000-07-06 AND AD/B737/142. 2 L 7 2 4F 4 F RT A16WE E21EU 2001080800335 20010808 00335 SO 2001 8 8 AUS20010670 1 20010627 G 5741 401187 BOLT PIPER PA28 PA28161 7102803 SO LYC O320 O320D3G 41508 EA SNSNCH 74D 74DM EA WING LOOSE W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) LT WING REAR SPAR ATTACHMENT BOLTS LOOSE WITH NUT HOLDING BY ONLY THREE THREADS. SUSPECT NUTS NOT TIGHTENED AT LAS T MAINTENANCE INSPECTION FOLLOWING WORK CARRIED OUT IN THE AREA.PERSONNEL/MAINTENANCE ERROR. 1 L 7 1 3O 3 O 2A13 E274 5 N P88614 2001080800337 20010808 00337 NM 2001 8 8 AUS20010671 1 20010626 G 3520 335841 COMPENSATOR BOEING 747 747238B 1384828 NM RROYCE RB211 RB211524D419 54555 NE PASSENGER OXYGEN CORRODED W K NONE O OTHER IN INSP/MAINT 1 AU S 10501 (AUS) NO6 PASSENGER OXYGEN BOTTLE THERMAL COMPENSATOR SWAGED FITTINGCORRODED. AIRCRAFT IS REGISTERED DQ-FJE. 2 L 7 4 4F 4 F A20WE E12EU 2001080800338 20010808 00338 NM 2001 8 8 AUS20010672 1 20010628 G 5753 7337515505 PIN BOEING 767 767204 NM GE CF6 CF680A 30025 NE TE FLAPS MISSING W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) FLAP BYPASS VALVE ROTARY ACTUATOR PIN MIGRATED OUT OF POSITIONLEVER. 2 L 7 2 4F 4 F RT A1NM E13NE 2001080700180 20010807 00180 SW 2001 8 7 AUS20010673 1 20010621 G 2841 1820002 INDICATOR GULSTM 500 500B 0141106 SW LYC O540 IO540E1B5 41532 EA HARTZL HCA3V HCA3VK4 GL FUEL QUANTITY IN FAILED W K NONE I FLT. ATTITUDE INST. CR CRUISE 1 AU S 1 (AUS) TRIPLE GAUGE FAILED AND FILLED WITH FUEL. 1 H 7 2 3O 3 O 6A1 1E4 5 C P6EA 2001080700181 20010807 00181 CE 2001 8 7 AUS20010674 1 20010619 G 3213 51411021 BARREL CESSNA 402 402C 207590R CE MAIN LANDING GEA CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) MAIN LANDING GEAR LOWER TORQUE LINK ATTACHMENT LUGS CRACKED.FOUND DURING FLUORESCENT MAGNETIC PARTICLE INSPECTION IAW MEB 89-2R1. LOWER ATTACHMENT LUGS ARE NOT CALLED FOR IN THISINSPECTION. 1 L 7 2 3O A7CE 2001080800347 20010808 00347 EU 2001 8 8 AUS20010675 1 20010628 G 6220 206010102121 GRIP BELL AGUSTA 206AGS 206AAGUSTA 0260301 EU ALLSN 250C 250C20B 03013 GL MAIN ROTOR HEAD DAMAGED W K NONE O OTHER IN INSP/MAINT 1 AU S 583 GDLM11933 (AUS) MAIN ROTOR GRIP BLADE BOLT BORES DAMAGED. INVESTIGATION FOUND THAT THE MAIN ROTOR BLADE BUFFER PAD WAS DISLODGED D URING BLADE INSTALLATION. THE BLADE BOLT WAS FORCED IN CAUSING THE EDGE OFTHE BUFFER PAD INTO THE BLADE BOLT HOLE. DAMAG E CAUSED TO BLADE BOLT PNO 206-010-152-003 AND MAIN ROTOR BLADE PNO 206-010-200-033. PERSONNEL/MAINTENANCE ERROR. 1 G 7 1 3U 3 U EXPA1G71 E4CE 2001080800350 20010808 00350 NM 2001 8 8 AUS20010676 1 20010630 G 4920 APU BOEING 747 747338 NM RROYCE RB211 RB211524D419 54555 NE APU BAY FIRE W K NONE A FLAME/FIRE IN INSP/MAINT 1 AU S (AUS) FOLLOWING APU BATTERY FITMENT AND WHILE INSTALLATION CHECKS WERE CARRIED OUT ON THE THERMAL SWITCH, A FLASH FIRE O CCURRED WHICH SET FIRE TO THE THERMAL BLANKET LOCATED UNDER THE APU BATTERY TRAY AND ALSO CAUSED FLASH BURNS TO MAINTENA NCE PERSONNEL. THEFIRE WAS CONTAINED AND QUICKLY EXTINGUISHED. THE FIRE MAY HAVE BEEN CAUSED BY COMBINATION OF AN IGNITI ON SOURCE FROM A PREVIOUSLY UNDISCOVERED BROKEN/CHAFFED WIRING IN LOOM ADJACENT TO APU BATTERY TRAY AND USE OF AN UNAPPR OVED COOLANT SOURCE THAT WAS INFLAMMABLE. 2 L 7 2 4F 4 F RT A20WE E12EU 2001080700182 20010807 00182 CE 2001 8 7 AUS20010677 1 20010627 G 5753 052390134 FLAP CESSNA 182 R182 2072734 CE LYC O540 O540J3C5 41532 EA MCAULY 2D34C B2D34C214 GL TRAILING EDGE FL DAMAGED W K NONE F FLT CONT AFFECTED TO TAKEOFF 1 AU S (AUS) RH TRAILING EDGE FLAP TOP AND BOTTOM SKINS, LEADING EDGE SKIN AND SPAR DAMAGED. INVESTIGATION FOUND THE DAMAGE WAS CAUSED BY THEINBOARD FORWARD FLAP ROLLER JAMMING DUE TO EXCESSIVE WEAR OF THEFLAP TRACK AND ROLLERS. 1 H 7 1 3O 3 O RT 3A13 E295 5 C P7EA 2001080700183 20010807 00183 CE 2001 8 7 AUS20010678 1 20010626 G 5610 10132402522 WINDSHIELD BEECH 200 200BEECH 1152920 CE PWA PT6 PT6A42 52043 NE MCAULY 4HFR34 4HFR34C754 NE FLIGHT COMPARTME CRACKED W K NONE O OTHER CR CRUISE 1 AU S (AUS) RH WINDSHIELD INNER PANE CRACKED. 1 L 7 2 4T 4 T A24CE E4EA 6 C 3PNE 2001080800352 20010808 00352 NE 2001 8 8 AUS20010679 3 20010629 G 6114 660714255 HUB ROTOL R3904123F SAAB SF340 340B 7860101 EU GE CT7TP CT79B 30030 NE ROTOL R390 R3904123F27 NE PROPELLER CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S 5054 DRG1268390 (AUS) PROPELLER HUB CRACKED IN AREA AROUND TWO OF THE MOUNT BOLT HOLES. FOUND USING EDDY CURRENT INSPECTION IAW AD/PR/33 . 2 L 7 2 4T 4 T RT A52EU E8NE 6 C P31NE 2001080700184 20010807 00184 NM 2001 8 7 AUS20010680 1 20010701 G 2750 285T004953 FSEU BOEING 767 767238 NM PWA JT9 JT9D7R4E 52054 NE TRAILING EDGE FL FAULTY W K NONE F J FLT CONT AFFECTED WARNING INDICATION LD LANDING 1 AU S 6848 (AUS) FLAP/SLAT ELECTRONIC UNIT (FSEU) SUSPECT FAULTY. 2 L 7 2 4F 4 F RT A1NM E3NE 2001080800353 20010808 00353 NM 2001 8 8 AUS20010681 1 20010621 G 7603 CABLE RROYCE RB211524D4 BOEING 747 747238B 1384828 NM RROYCE RB211 RB211524D419 54555 NE POWER LEVER WORN W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) ENGINE THRUST CONTROL CABLE GUARDS AND COVERS CRACKED/DAMAGED.GUARDS ARE FOR CABLES T1, T2, T3, T4A, T4B, STN940 T O STN960 LT AND RT. CABLE PULLEY FOR CABLE T3A CRACKED AND CABLE T3A WORN AT RT WING INBOARD LOCATION 352.00. FOUND DURI NG INSPECTION IAW EI 742-076-0005 REV02, CASA AD/B747/299 AND FAA AD 2000-05-30 AMDT 39-11640. AIRCRAFT IS FOREIGN REGIS TRATION DQ-FJE. 2 L 7 4 4F 4 F A20WE E12EU 2001080800354 20010808 00354 NM 2001 8 8 AUS20010682 1 20010626 G 2530 GENM2585015 OVEN BOEING 737 737400 NM CFMINT CFM56 CFM563C 13802 EU GALLEY FAULTY W O OTHER B SMOKE/FUMES/ODORS/SPARKS CR CRUISE 1 AU S 19905 (AUS) OVEN C207 CONTAMINATED. WHEN THE OVEN WAS OPERATED A LARGE AMOUNT OF SMOKE WAS GENERATED DUE TO EXCESS OIL IN THE OVEN COMPARTMENT. 2 L 7 2 4F 4 F RT A16WE E21EU 2001080700185 20010807 00185 NE 2001 8 7 AUS20010683 2 20010704 G 7260 310623101 SHAFT PWA PW123D DHAV DHC8 DHC8202 2809007 NM PWA 120 PW123D 52152 NE HAMSTD 14SF 14SF23 NE TURBINE ENGINE A SHEARED W K NONE O OTHER IN INSP/MAINT 1 AU S 123308 (AUS) NO2 ENGINE ACCESSORY GEARBOX TOWER SHAFT SHEARED AT THE MATINGPOINT WITH GEAR CAUSING THE SHEARED STUB TO JAM BETW EEN THE DRIVESHAFT BEVEL GEARS. SUSPECT CAUSED BY INCORRECT ASSEMBLYPROCEDURE DURING PRODUCTION. 2 H 7 2 4T 4 T RT A13NM E20NE 6 C P7NE 2001080800355 20010808 00355 GL 2001 8 8 AUS20010684 1 20010530 G 5710 STRUCTURE AMTR MK1 MK1 05620JY GL WING DELAMINATED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) INTERNAL DELAMINATION OF WING/FUEL TANK. SEVERE FUEL LEAKAGE. THE AIRCRAFT IS A HOMEBUILT AND IT IS SUSPECTED THAT INCORRECTTECHNIQUES WERE USED IN THE CONSTRUCTION. 1 H 7 1 3O NC EXPA1H71 2001080800356 20010808 00356 SO 2001 8 8 AUS20010685 2 20010621 G 8530 654961 CYLINDER CESSNA 206 U206G 2073356 CE CONT O520 IO520F 17032 SO MCAULY 3A32C D3A32C90 GL ENGINE LEAKING W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) NR 2 CYLINDER LEAKING PAST EXHAUST VALVE AND PISTON RINGS. 1 H 7 1 3O 3 O A4CE E5CE 5 C P21EA 2001080700186 20010807 00186 CE 2001 8 7 AUS20010686 1 20010622 G 3710 1H59 VALVE AIRBORNE 1H59 CESSNA 402 402B 207590P CE CONT O520 TSIO520E 17040 SO MCAULY 3AF32C 3AF32C87 GL VACUUM DISTRIBUT FAULTY W K NONE I FLT. ATTITUDE INST. CR CRUISE 1 AU S 8A (AUS) RH VACUUM SYSTEM MANIFOLD CHECK VALVE FAULTY. 1 L 7 2 3O 3 O A7CE E8CE 5 C P22EA 2001080800357 20010808 00357 SO 2001 8 8 AUS20010687 1 20010704 G 2432 1406902 LEAD PIPER PA31 PA31350 7103110 SO LYC O540 TIO540J2BD 41532 EA HARTZL HCE3Y HCE3YR2 GL BATTERY/CHARGER FRACTURED W O OTHER H ELECT. POWER LOSS-50 PC NR NOT REPORTED 1 AU S (AUS) BATTERY POSITIVE LEAD LOCATED INSIDE THE BATTERY BOX FRACTURED. 1 L 7 2 3O 3 O A20SO E14EA 5 C P33EA 2001080800362 20010808 00362 EA 2001 8 8 AUS20010688 2 20010617 G 8530 LW12966 CYLINDER PIPER PA31 PA31350 7103110 SO LYC O540 TIO540J2BD 41532 EA HARTZL HCE3Y HCE3YR2 GL ENGINE FAILED W A UNSCHED LANDING E VIBRATION/BUFFET CR CRUISE 1 AU S 1677 (AUS) ENGINE CYLINDER HEAD SEPARATED FROM BARREL IN THREADED AREA. 1 L 7 2 3O 3 O A20SO E14EA 5 C P33EA 2001080800363 20010808 00363 EA 2001 8 8 AUS20010689 2 20010622 G 8530 LW13532 CYLINDER GULSTM 500 500S 0141107 SW LYC O540 IO540E1B5 41532 EA HARTZL HCC3Y HCC3YR2 NE ENGINE DAMAGED W K NONE O OTHER IN INSP/MAINT 1 AU S 632 (AUS) ENGINE CYLINDER HOLED IN AREA ADJACENT TO TOP SPARK PLUG HOLE. 1 H 7 2 3O 3 O 6A1 1E4 5 C P25EA 2001080800364 20010808 00364 2001 8 8 AUS20010690 4 20010702 G 3418 18617 DETECTOR REIMS 406 F406 EU PWA PT6 PT6A112 52043 NE MCAULY 3G34C7 3GFR34C701 GL STALL WARNING FAULTY W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) LIFT DETECTOR FAULTY. INVESTIGATION FOUND THAT THE AIRCRAFT WIRING (WIRE NO A2K4S-20P3) HAD BEEN CUT APPROXIMATELY 76.2MM (3IN) UP FROM THE FORWARD SIDE CONSOLE CONNECTOR AND CONNECTED TO THE STALL WARNING HORN. PERSONNEL/MAINTENANCE ERROR. UNAPPROVED MODIFICATION. 1 L 7 2 3T 3 T RT A54EU E4EA 5 C P60GL 2001080800365 20010808 00365 NE 2001 8 8 AUS20010691 2 20010707 G 7200 200304004 ENGINE BAG BAE146 BAE146200A 1500266 EU LYC ALF502 ALF502R5 41580 NE NR 2 MALFUNCTIONED W O OTHER E K VIBRATION/BUFFET FLUID LOSS DE DESCENT 1 AU S (AUS) NR 2 ENGINE HAD NO OIL PRESSURE. LIMITED INFORMATION PROVIDED. 2 H 7 4 4F 4 F RT A49EU E6NE 2001080800366 20010808 00366 SW 2001 8 8 AUS20010692 1 20010706 G 3210 2751540003 PIN SWRNGN SA227 SA227* SW GARRTT TPE331 TPE33112UA 01514 WP MCAULY 4HFR34 4HFR34C652 NE LANDING GEAR SHEARED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) RH MAIN LANDING GEAR UPPER TORQUE LINK PIN SHEARED. 2 L 7 2 4T 4 T RT A5SW E4WE 6 C 3PNE 2001080700187 20010807 00187 CE 2001 8 7 AUS20010693 1 20010709 G 7602 5038901019 CABLE CONT IO470L BEECH 95 95B55 1152729 CE CONT O470 IO470L 17026 SO MCAULY 2AF34C 2AF34C55 GL MIXTURE CONTROL FAILED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) LH ENGINE MIXTURE CUTOFF CONTROL CABLE WORN AND BROKEN AT A POINT 190MM (7.48IN) FROM THE ENGINE END ATTACHMENT BE ARING. 1 L 7 2 3O 3 O RT 3A16 3E1 5 C P5EA 2001080800367 20010808 00367 WP 2001 8 8 AUS20010694 2 20010630 G 7210 310703710 GEAR SWRNGN SA227 SA227* SW GARRTT TPE331 TPE33112UHR WP MCAULY 4HFR34 4HFR34C652 NE GEARBOX WORN W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) ENGINE SUN/BULL GEAR TEETH AND CORRESPONDING HIGH SPEED PINIONGEARSHAFT TEETH WORN. FOUND DURING ENGINE DISASSEMBL Y FOLLOWING SOAP ANALYSIS WHICH SHOWED CARBON STEEL FINES. SERVICE BULLETIN A72-2062 HAD NOT BEEN COMPLIED WITH. 2 L 7 2 4T 4 T RT A5SW E4WE 6 C 3PNE 2001080800368 20010808 00368 2001 8 8 AUS20010695 4 20010624 G 3414 1013840743 INDICATOR BEECH 200 200BEECH 1152920 CE PWA PT6 PT6A41 52043 EA HARTZL HCB3T HCB3TN3 GL COCKPIT OUT OF ADJ W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) AIRSPEED INDICATOR READING 5 KNOTS OUT OVER THE ENTIRE RANGE. FOUND DURING INSPECTION IAW AD/INST/9 AMDT5. 1 L 7 2 4T 4 T A24CE E4EA 6 C P15EA 2001080800369 20010808 00369 EU 2001 8 8 AUS20010696 1 20010703 G 7810 4606AC CLAMP ALLSN 250C20B AGUSTA 206AGS 206AAGUSTA 0260301 EU ALLSN 250C 250C20B 03013 GL ENGINE COLLECTOR CRACKED W K NONE B SMOKE/FUMES/ODORS/SPARKS IN INSP/MAINT 1 AU S (AUS) ENGINE EXHAUST STACK CLAMP LOOSE DUE TO A FRACTURE ORIGINATINGFROM THE ATTACHMENT LUG SECURING RIVET. COWLING DISC OLOURED AND BURNT. 1 G 7 1 3U 3 U EXPA1G71 E4CE 2001080800370 20010808 00370 EU 2001 8 8 AUS20010697 1 20010627 G 7120 9448121409 MOUNT PILATS PC12 PC12 7090550 EU PWA PT6 PT6A67B 52043 NE HARTZL HCE4A HCE4A3D GL ENGINE SEPARATED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) ENGINE SHOCK MOUNT RUBBERS SEPARATED FROM METAL BACKING ALLOWINGENGINE TO SLUMP. SUSPECT MANUFACTURING FAULT. 1 L 7 1 3T 4 T RT A78EU E26NE 5 C P210NE 2001080700188 20010807 00188 SO 2001 8 7 AUS20010698 2 20010626 G 8530 PISTON RING CONT IO520F CESSNA 206 U206G 2073356 CE CONT O520 IO520F 17032 SO MCAULY D3A34 D3A34C404 GL RECIPROCATING EN WORN W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) NO3 CYLINDER PISTON RINGS WORN AND LEAKING. 1 H 7 1 3O 3 O A4CE E5CE 5 C P47GL 2001080800371 20010808 00371 CE 2001 8 8 AUS20010699 1 20010705 G 2797 WIRE CESSNA 441 441 2076020 CE GARRTT TPE331 TPE3318 01514 WP HARTZL HCB3T HCB3TN5 GL FLIGHT CONTROLS BROKEN W O OTHER F FLT CONT AFFECTED LD LANDING 1 AU S (AUS) FLAP SELECTOR LOOM WIRE BROKEN FROM CRIMP TO FLAP MICROSWITCH. 1 L 7 2 3T 4 T RT A28CE E4WE 6 C P15EA 2001080700189 20010807 00189 SO 2001 8 7 AUS20010700 1 20010705 G 2840 8004804 HOSE PIPER PA31 PA31350 7103110 SO LYC O540 TIO540J2BD 41532 EA HARTZL HCE3Y HCE3YR2 GL FUEL INDICATING LEAKING W K NONE O K OTHER FLUID LOSS IN INSP/MAINT 1 AU S (AUS) FUEL PRESSURE HOSE TO FUEL FLOW GAUGE LEAKING UNDER PRESSURE. 1 L 7 2 3O 3 O A20SO E14EA 5 C P33EA 2001080800372 20010808 00372 NM 2001 8 8 AUS20010701 1 20010704 G 5520 85520271003 STOP DHAV DHC8 DHC8202 2809007 NM PWA 120 PW123D 52152 NE HAMSTD 14SF 14SF23 NE ELEVATOR DETERIORATED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) ELEVATOR BUMPER RUBBER DETERIORATED AND PERISHED. FOUND DURINGINSPECTION IAW AD/DHC-8/078. 2 H 7 2 4T 4 T RT A13NM E20NE 6 C P7NE 2001080800373 20010808 00373 EU 2001 8 8 AUS20010702 1 20010601 G 2130 CONTROLLER FOKKER F28 F28MK1000 4990808 EU RROYCE SPEY SPEY55515 54521 EU CABIN PRESSURE ERRATIC W O OTHER O OTHER CL CLIMB 1 AU S (AUS) PRESSURISATION SYSTEM ERRATIC IN OPERATION. INVESTIGATION FOUND THAT THE AIR FILTER AND VENTURI LINES WERE TRANSPO SED AT THE PRESSURISATION CONTROLLER CONNECTIONS. PERSONNEL/MAINTENANCEERROR. 2 L 7 2 4F 4 F RT A20EU E2EU 2001080700190 20010807 00190 EU 2001 8 7 AUS20010703 1 20010601 G 2910 PIPE FOKKER F28 F28MK1000 4990808 EU RROYCE SPEY SPEY55515 54521 EU HYDRAULIC SYSTEM LEAKING W K NONE O K OTHER FLUID LOSS IN INSP/MAINT 1 AU S (AUS) UTILITY HYDRAULIC SYSTEM SUCTION PIPE CONTAINED A PIN HOLE LEAK.LOSS OF HYDRAULIC FLUID. 2 L 7 2 4F 4 F RT A20EU E2EU 2001080700191 20010807 00191 EU 2001 8 7 AUS20010704 1 20010601 G 3234 LEVER FOKKER F28 F28MK1000 4990808 EU RROYCE SPEY SPEY55515 54521 EU LANDING GEAR SEL STUCK W K NONE O OTHER TO TAKEOFF 1 AU S (AUS) LANDING GEAR LEVER OBSTRUCTED IN DOWN POSITION. 2 L 7 2 4F 4 F RT A20EU E2EU 2001080700192 20010807 00192 EU 2001 8 7 AUS20010705 1 20010527 G 3610 DUCT FOKKER F28 F28MK1000 4990808 EU RROYCE SPEY SPEY55515 54521 EU PNEUMATIC DISTRI MISALIGNED W K NONE J WARNING INDICATION CL CLIMB 1 AU S (AUS) LH BLEED AIR SYSTEM LEAKING AT ENGINE HP OUTLET CHECK VALVE DUCT. INVESTIGATION FOUND THE DUCT MATING SURFACES TO BE BADLY ALIGNED. 2 L 7 2 4F 4 F RT A20EU E2EU 2001080800374 20010808 00374 2001 8 8 AUS20010706 4 20010625 G 2565 CABLE BOEING 737 737377 NM CFMINT CFM56 CFM565B4 NE ESCAPE SLIDE FRAYED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) FORWARD GALLEY DOOR ESCAPE SLIDE RELEASE CABLE FRAYED. FOUNDDURING INSPECTION IAW AD/B737/042. 2 L 7 2 4F 4 F RT A16WE E38NE 2001080700193 20010807 00193 NE 2001 8 7 AUS20010707 2 20010509 G 7250 9234M22G07 SUPPORT GE CF680A BOEING 767 767277 NM GE CF6 CF680A 30025 NE TURBINE SECTION CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) ENGINE FIRST STAGE HPT INNER NOZZLE SUPPORT CRACKED. TURBINEDAMAGE AND METAL IN TAILPIPE. 2 L 7 2 4F 4 F RT A1NM E13NE 2001080800375 20010808 00375 EU 2001 8 8 AUS20010708 1 20010707 G 3260 SWITCH STBROS SD3 SD360 8100606 EU PWA PT6 PT6A67R 52043 NE HARTZL HCA6A HCA6A3 NE LANDING GEAR OUT OF ADJ W O OTHER N FALSE WARNING LD LANDING 1 AU S (AUS) NOSE LANDING GEAR MICROSWITCH OUT OF ADJUSTMENT. 2 H 7 2 4T 4 T A41EU E26NE 6 C P14NE 2001080800376 20010808 00376 NM 2001 8 8 AUS20010709 1 20010701 G 2540 VALVE BOEING 737 737377 NM CFMINT CFM56 CFM565B4 NE LAVATORIES BROKEN W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) FORWARD TOILET DRAIN VALVE POPPET BROKEN. INNER POPPET WASMISSING. 2 L 7 2 4F 4 F RT A16WE E38NE 2001080800377 20010808 00377 NM 2001 8 8 AUS20010710 1 20010706 G 2910 AS154A06NN0336T HOSE BOEING 737 737377 NM CFMINT CFM56 CFM563B2 13802 EU HYDRAULIC SYSTEM RUPTURED W K NONE K FLUID LOSS NR NOT REPORTED 1 AU S (AUS) NOSE LANDING GEAR EXTENSION FLEXIBLE HOSE RUPTURED. LOSS OF SYSTEM A' HYDRAULIC FLUID. 2 L 7 2 4F 4 F RT A16WE E21EU 2001080800378 20010808 00378 EU 2001 8 8 AUS20010711 1 20010627 G 5610 WINDSHIELD AIRBUS 320 A320* EU CFMINT CFM56 CFM565A1 NE COCKPIT CRACKED W A UNSCHED LANDING O OTHER CR CRUISE 1 AU S (AUS) FRONT LH WINDSHIELD CRACKED FOLLOWING FAILURE OF WINDSHIELD HEATING. 2 L 7 2 4F 4 F RT A46NM E29NE 2001080900003 20010809 00003 EU 2001 8 9 AUS20010712 1 20010703 G 5415 BOLT BAG BAE146 BAE146300A 1500267 EU LYC ALF502 ALF502R5 41580 NE PYLON CORRODED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) WING/PYLON BOLT CORRODED UNDER HEAD. FOUND DURING INSPECTION IAWER BA6-54-40-4. 2 H 7 4 4F 4 F RT A49EU E6NE 2001080900004 20010809 00004 2001 8 9 AUS20010713 4 20010614 G 2210 AUTOPILOT SYS BAC 146 146200A 1500266 EU LYC ALF502 ALF502R5 41580 NE COCKPIT FAULTY W A UNSCHED LANDING F FLT CONT AFFECTED CL CLIMB 1 AU S (AUS) AUTOPILOT FAULTY. 2 H 7 4 4F 4 F A49EU E6NE 2001080900005 20010809 00005 EU 2001 8 9 AUS20010714 1 20010704 G 5415 BOLT BAG BAE146 BAE146300A 1500267 EU LYC ALF502 ALF502R5 41580 NE NACELLE CORRODED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) WING/PYLON BOLTS (3OFF) CORRODED UNDER THE HEAD AND ON THE BOLT SHANK. FOUND DURING INSPECTION IAW ER BA6-54-40-4 REV E. 2 H 7 4 4F 4 F RT A49EU E6NE 2001080700194 20010807 00194 SO 2001 8 7 AUS20010716 2 20010703 G 8530 654004 EXHAUST VALVE CONT O200A CESSNA 150 150L 2071826 CE CONT O200 O200A 17020 SO MCAULY 1A102 1A102OCM GL RECIPROCATING EN ERODED W K NONE O OTHER IN INSP/MAINT 1 AU S 205622 (AUS) ALL ENGINE EXHAUST VALVES EXHIBITED SEVERE EROSION BETWEEN THEVALVE STEM AND VALVE HEAD. 1 H 7 1 3O 3 O 3A19 E252 5 N P918 2001080700195 20010807 00195 EA 2001 8 7 AUS20010717 2 20010613 G 8520 L801776 CRANKCASE LYC O320H2AD CESSNA 172 172N 2072434 CE LYC O320 O320H2AD 41508 EA MCAULY 1C160 1C160DTM GL RECIPROCATING EN FAULTY W K NONE O OTHER IN INSP/MAINT 1 AU S L801776 (AUS) CRANKCASE INCORRECTLY LINE BORED REDUCING DECK HEIGHT BY 1.016MM(0.040IN). THIS ALLOWED NO3 PISTON TO CONTACT THE CYLINDER HEAD.METAL CONTAMINATION OF ENGINE. PERSONNEL/MAINTENANCE ERROR. 1 H 7 1 3O 3 O NT 3A12 E274 5 N P910 2001080900006 20010809 00006 NE 2001 8 9 AUS20010718 2 20010708 G 7321 FFR105MK2S REGULATOR RROYCE RB211524D4 BOEING 747 747338 NM RROYCE RB211 RB211524D419 54555 NE FUEL CONTROL FAULTY W A UNSCHED LANDING E R J VIBRATION/BUFFET PARTIAL RPM/PWR LOSS WARNING INDICATION CR CRUISE 1 AU S 9145 B1734 (AUS) NO2 ENGINE FUEL FLOW REGULATOR FAULTY. 2 L 7 2 4F 4 F RT A20WE E12EU 2001080900007 20010809 00007 NM 2001 8 9 AUS20010719 1 20010710 G 3242 S160T400510 BRAKE MESSIER MAINWHEEL BOEING 767 767338 1385151 NM GE CF6 CF680C2* GL NR 2 FIRE W D RETURN TO BLOCK A FLAME/FIRE TX TAXI/GRND HDL 1 AU S 2667 QF15175 (AUS) NR 2 RT BRAKE FIRE. FIRE SELF-EXTINGUISHED. 2 L 7 2 4F 4 F RT A1NM E23EA 2001080700196 20010807 00196 EA 2001 8 7 AUS20010720 2 20010703 G 7321 25244405 FCU BENDIX DPF2 DHAV DHC6 DHC6300 2802606 EA PWA PT6 PT6A27 52043 EA HARTZL HCB3T HCB3TN3 GL FUEL CONTROL/TUR FAULTY W K NONE E VIBRATION/BUFFET DE DESCENT 1 AU S A48954 (AUS) FUEL CONTROL UNIT FAULTY. INVESTIGATION FOUND THE PY RESTRICTOR PARTIALLY BLOCKED BY SUSPECTED PAINT FLAKES. 1 H 7 2 3T 4 T RT A9EA E4EA 6 C P15EA 2001080700197 20010807 00197 CE 2001 8 7 AUS20010721 1 20010702 G 3710 HOSE CESSNA 210 210R 2073458 CE CONT O520 IO520L 17032 SO MCAULY 3AF32C 3AF32C87 GL VACUUM DISTRIBUT DETERIORATED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) INSTRUMENT VACUUM HOSES LOCATED BEHIND THE INSTRUMENT PANEL DETERIORATED. HOSES ARE BRANDED IMPERIAL EASTMAN REDI- SEAL. 1 H 7 1 3O 3 O RT 3A21 E5CE 5 C P22EA 2001080900009 20010809 00009 NM 2001 8 9 AUS20010722 1 20010706 G 3040 HEATER 8SC004301 DHAV DHC8 DHC8106 NM PWA PW121 PW121 52124 NE HAMSTD 14SF 14SF7 NE WINDSHIELD FAULTY W A UNSCHED LANDING B SMOKE/FUMES/ODORS/SPARKS CR CRUISE 1 AU S (AUS) LT WINDSHIELD HEATING TERMINAL BLOCK OVERHEATING. NO EVIDENCE OFHEAT DAMAGE TO THE WINDSHIELD. 2 H 7 2 4T 4 T RT A13NM E20NE 6 C P7NE 2001080900010 20010809 00010 2001 8 9 AUS20010723 4 20010711 G 3460 4081600930 DISPLAY BOEING 737 737724 NM CFMINT CFM56 CFM565A1 NE FMC FAULTY W A UNSCHED LANDING O OTHER CR CRUISE 1 AU S (AUS) NR 1 DISPLAY ELECTRONIC UNIT (DEU) FAULTY. 2 L 7 2 4F 4 F RT A16WE E29NE 2001080700198 20010807 00198 GL 2001 8 7 AUS20010724 1 20010525 G 6220 281432015 BEARING ENSTRM F28 280C 3300505 GL LYC O360 HIO360E1AD 41514 EA MAIN ROTOR HEAD FAILED W K NONE F FLT CONT AFFECTED TO TAKEOFF 1 AU S (AUS) MAIN ROTOR HEAD LAMIFLEX BEARING FAILED. SUSPECT CAUSED BY GREASE CONTAMINATION. 1 G 7 1 3O 3 O H1CE 1E10 2001080700199 20010807 00199 EA 2001 8 7 AUS20010725 2 20010624 G 8520 BOLT LYC IO540K1G5 PIPER PA32 PA32R301 7103218 SO LYC O540 IO540K1G5 41532 EA HARTZL HCC2Y HCC2YK1 GL RECIPROCATING EN FAILED W K NONE E R VIBRATION/BUFFET PARTIAL RPM/PWR LOSS DE DESCENT 1 AU S (AUS) CYLINDER HOLDDOWN BOLTS FAILED. 1 L 7 1 3O 3 O A3SO 1E4 5 C P920 2001080700200 20010807 00200 SO 2001 8 7 AUS20010726 1 20010706 G 3242 93956 PLATE EMB 120 EMB120 3260201 SO PWA 118 PW118A NE HAMSTD 14SF 14SF9 NE BRAKE WORN W K NONE O OTHER IN INSP/MAINT 1 AU S 0480 (AUS) LH OUTBOARD BRAKE WORN TO LIMITS. STRIP INSPECTION FOUND THAT WEAR PLATES HAD SPREAD PAST THE OUTER DIAMETER OF TH E BRAKE PLATES AND CONTACTED THE WHEEL PNO 3-1544. 2 L 7 2 4T 4 T RT A31SO E20NE 6 N P11NE 2001080900011 20010809 00011 NE 2001 8 9 AUS20010727 2 20010710 G 7200 ENGINE BAG BAE146 BAE146200A 1500266 EU LYC ALF502 ALF502R5 41580 NE NR 3 FAILED W A UNSCHED LANDING K E J FLUID LOSS VIBRATION/BUFFET WARNING INDICATION CR CRUISE 1 AU S (AUS) NR 3 ENGINE OIL PRESSURE LOSS. 2 H 7 4 4F 4 F RT A49EU E6NE 2001080900013 20010809 00013 NM 2001 8 9 AUS20010728 1 20010711 G 3242 S160T400510 BRAKE BOEING 767 767338 1385151 NM GE CF6 CF680C2* GL NR 3 MLG LEAKING W K NONE O OTHER IN INSP/MAINT 1 AU S 2907 (AUS) NR 3 MAIN LANDING GEAR BRAKE LEAKING. FURTHER INVESTIGATION SHOWED EVIDENCE OF DISINTEGRATION OF THE REAR STATOR. 2 L 7 2 4F 4 F RT A1NM E23EA 2001080900014 20010809 00014 NM 2001 8 9 AUS20010729 1 20010711 G 2910 K2231 LINE ABEX PUMP BOEING 737 737724 NM CFMINT CFM56 CFM565A1 NE HYDRAULIC SYSTEM DISCONNECTED W K NONE O OTHER IN INSP/MAINT 1 AU S K2231 (AUS) HYDRAULIC SUPPLY LINE FOUND DISCONNECTED. SUSPECT LINE NOTRECONNECTED FOLLOWING MAINTENANCE. SYSTEM A' HYDRAULIC P UMP INTERNAL FAILURE DUE TO LACK OF FLUID. PERSONNEL/MAINTENANCE ERROR. 2 L 7 2 4F 4 F RT A16WE E29NE 2001080900016 20010809 00016 NE 2001 8 9 AUS20010731 2 20010712 G 7200 0292005250 ENGINE SKRSKY S76 S76C 8143008 NE TMECA ARRIEL ARRIEL1S 60030 NE NACELLE FAILED W A UNSCHED LANDING E T J VIBRATION/BUFFET ENGINE CASE PENETRATION WARNING INDICATION CR CRUISE 1 AU S (AUS) ENGINE SUFFERED SEVERE INTERNAL FAILURE. COMPRESSOR AND TURBINE SEIZED. GAS GENERATOR AND POWER TURBINE BLADES BAD LY DAMAGED. EXTERNAL DAMAGE ALSO EVIDENT. 1 G 7 2 3U 3 U NC H1NE E19EU 2001080900017 20010809 00017 SW 2001 8 9 AUS20010732 1 20010309 G 6120 86913019 BETA SWITCH HARTZL HCB3TN5 SWRNGN SA226 SA226TC 8780404 SW GARRTT TPE331 TPE331* 01514 WP HARTZL HCB3T HCB3TN5 GL PROPELLER FAULTY W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) PROPELLER BETA SWITCH FAULTY. 2 L 7 2 4T 3 T RT A8SW E2WE 6 C P15EA 2001080900019 20010809 00019 WP 2001 8 9 AUS20010733 2 20010705 G 7261 3199741 VALVE SWRNGN SA226 SA226TC 8780404 SW GARRTT TPE331 TPE3313UW 01514 WP HARTZL HCB3T HCB3TN5 GL ENGINE STUCK W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) OIL VENT VALVE STUCK OPEN. 2 L 7 2 4T 4 T RT A8SW E4WE 6 C P15EA 2001080700201 20010807 00201 EU 2001 8 7 AUS20010734 1 20010622 G 2710 CONTROL CABLE REIMS 406 F406 7535723 EU PWA PT6 PT6A112 52043 NE MCAULY 3G34C7 3GFR34C701 GL AILERON CONTROL WORN W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) LH AND RH AILERON CABLES (4OFF) LOCATED IN WING WORN. 1 L 7 2 3T 3 T RT A54EU E4EA 5 C P60GL 2001080900020 20010809 00020 NM 2001 8 9 AUS20010735 1 20010715 G 7714 WIRE DHAV DHC8 DHC8102 2809003 NM PWA 120 PW120A NE HAMSTD 14SF 14SF7 NE ENGINE INDICATOR FAULTY W D RETURN TO BLOCK E N VIBRATION/BUFFET FALSE WARNING TX TAXI/GRND HDL 1 AU S 35105 (AUS) NR 1 ENGINE ITT GAUGE FLUCTUATING. SUSPECT WIRING PROBLEM. 2 H 7 2 4T 4 T RT A13NM E20NE 6 C P7NE 2001080900025 20010809 00025 2001 8 9 AUS20010736 4 20010711 G 2565 63800103 LIFE RAFT CABIN MISINSTALLED W K NONE W INADEQUATE Q C IN INSP/MAINT 1 AU S 10392 (AUS) DURING SERVICING OF LIFERAFT IT WAS FOUND THAT THE PACKING STRAP WAS STILL IN PLACE AROUND THE CIRCUMFERENCE OF TH E RAFT. STRAP WOULD PROBABLY PREVENTED CORRECT DEPLOYMENT. LIFERAFT HAD BEEN IN SERVICE FOR APPROXIMATELY THREE YEARS. P ERSONNEL/MAINTENANCEERROR. 2001080700202 20010807 00202 SO 2001 8 7 AUS20010737 2 20010714 G 7414 1051676 CAPACITOR BENDIX 107902016 CESSNA 337 T337G 2075726 CE CONT O360 TSIO360C 17025 SO MCAULY 2AF34C D2AF34C303 GL MAGNETO/DISTRIBU UNSERVICEABLE W K NONE O OTHER IN INSP/MAINT 1 AU S A98935 (AUS) MAGNETO CAPACITOR FAULTY. CAPACITOR LEAD LOOSE. 1 H 7 2 3O 3 O A6CE E9CE 5 C P5EA 2001080900027 20010809 00027 NE 2001 8 9 AUS20010738 2 20010712 G 7323 12664 GOVERNOR BOEING 747 747338 NM RROYCE RB211 RB211524D419 54555 NE NR 2 ENGINE FAULTY W D RETURN TO BLOCK R J PARTIAL RPM/PWR LOSS WARNING INDICATION TX TAXI/GRND HDL 1 AU S (AUS) NR 2 ENGINE RPM DECREASED AND EGT INCREASED. VIGV AIR FLOW CONTROL UNIT PNO 754-1-32148-019A AND PUMP AND GOVERNOR UNIT (PAG) PNOPAC102MK4S CHANGED. 2 L 7 2 4F 4 F RT A20WE E12EU 2001080900029 20010809 00029 NE 2001 8 9 AUS20010739 2 20010712 G 7260 1765MK1 HOUSING BOEING 747 747438 NM RROYCE RB211 RB211524G19 NE GENERATOR FAILED W A UNSCHED LANDING E K J VIBRATION/BUFFET FLUID LOSS WARNING INDICATION CR CRUISE 1 AU S (AUS) NR 4 ENGINE DEDICATED GENERATOR DAMAGED AND ADRIFT FROM ADAPTER GEARBOX. LOSS OF ENGINE OIL. 2 L 7 4 4F 4 F RT A20WE E30NE 2001080900030 20010809 00030 EU 2001 8 9 AUS20010740 1 20010716 G 3040 S2653010 CIRCUIT BREAKER BAC 146 146100A 1500260 EU LYC ALF502 ALF502R3A 41580 NE WINDSHIELD HEAT FAULTY W O OTHER B SMOKE/FUMES/ODORS/SPARKS DE DESCENT 1 AU S (AUS) LT A' SCREEN HEAT CIRCUIT BREAKER FAULTY. INVESTIGATION FOUND THE CIRCUIT BREAKER BURNED OUT ON A' PHASE. 2 H 7 4 4F 4 F RT A49EU E6NE 2001080700203 20010807 00203 NM 2001 8 7 AUS20010741 1 20010716 G 2520 SEAT BOEING 737 737476 NM CFMINT CFM56 CFM563C 13802 EU PASSENGER COMPAR LOOSE W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) PASSENGER SEAT 10ABC LOOSE IN TRACKS. 2 L 7 2 4F 4 F RT A16WE E21EU 2001080900032 20010809 00032 NM 2001 8 9 AUS20010742 1 20010716 G 5330 149T76086 PANEL BOEING 767 767338 1385151 NM GE CF6 CF680C2* GL FUSELAGE SEPARATED W O OTHER D INFLIGHT SEPARATION NR NOT REPORTED 1 AU S (AUS) ADP ACCESS PANEL/DOOR 195SL MISSING. DAMAGE TO FUSELAGE PANELS195LL, 195QL AND 195NL. 2 L 7 2 4F 4 F RT A1NM E23EA 2001080700204 20010807 00204 SO 2001 8 7 AUS20010743 1 20010519 G 3213 79543002 BOLT PIPER PA32 PA32260 7103206 SO LYC O540 O540E4B5 41532 EA HARTZL HCC2Y HCC2YK1 GL MAIN LANDING GEA FAILED W K NONE O OTHER LD LANDING 1 AU S (AUS) LH MAIN LANDING GEARLOWER LEG SEPARATED FROM UPPER LEG. SUSPECT CAUSED BY FAILURE OF THE CENTRE TORQUE LINK BOLT. LOWER LEG HOLED LH FLAP DURING SEPARATION. 1 L 7 1 3O 3 O A3SO E295 5 C P920 2001080900033 20010809 00033 EA 2001 8 9 AUS20010744 1 20010712 G 5610 NP1393225 WINDSHIELD CNDAIR CL600 CL6002B19 EA GE CF34 CF343B1 NE COCKPIT CRACKED W O OTHER O OTHER DE DESCENT 1 AU S 99343H5435 (AUS) LT PILOTS SIDE WINDSHIELD INNER PLY CRACKED DIAGONALLY FROM THE FORWARD LOWER CORNER. 2 L 7 2 4F 4 F RT A21EA E15NE 2001080900034 20010809 00034 NM 2001 8 9 AUS20010745 1 20010716 G 5753 69577055 FAIRING BOEING 737 737400 NM CFMINT CFM56 CFM565A1 NE TE FLAPS BROKEN W O OTHER F FLT CONT AFFECTED DE DESCENT 1 AU S (AUS) NR 3 TRAILING EDGE FLAP CANOE/FAIRING ASSEMBLY INBOARD END DOORPOSITION DATA BROKEN OFF AND JAMMING FLAP. 2 L 7 2 4F 4 F RT A16WE E29NE 2001080900036 20010809 00036 CE 2001 8 9 AUS20010746 1 20010713 G 3246 16110900 WHEEL CESSNA 441 441 2076020 CE GARRTT TPE331 TPE3318 01514 WP HARTZL HCB3T HCB3TN5 GL MLG WORN W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) MAIN LANDING GEAR WHEEL INNER HALF WORN IN BEARING BORE. BEARING SPINNING IN HUB. 1 L 7 2 3T 4 T RT A28CE E4WE 6 C P15EA 2001080900037 20010809 00037 NM 2001 8 9 AUS20010747 1 20010717 G 3520 117003 GENERATOR BOEING 767 767277 NM GE CF6 CF680A 30025 NE PASSENGER OXYGEN MISINSTALLED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) OXYGEN GENERATORS LOCATED AT SEATS 24AB, 25AB, 27AB AND 30FG HADTHE RELEASE PINS INCORRECTLY INSTALLED. 2 L 7 2 4F 4 F RT A1NM E13NE 2001080700205 20010807 00205 CE 2001 8 7 AUS20010748 1 20010717 G 5521 0532001103 RIB CESSNA 172 172G 2072420 CE CONT O300 O300C 17022 SO MCAULY 1C172 1C172EM GL ELEVATOR, SPAR/R CORRODED W K NONE O OTHER IN INSP/MAINT 1 AU S 8881 (AUS) ELEVATOR END RIB EXTENSIVELY CORRODED. 1 H 7 1 3O 3 O NT 3A12 E253 5 N P910 2001080900038 20010809 00038 SO 2001 8 9 AUS20010749 1 20010711 G 3260 MS3126E106P CONNECTOR EMB 120 EMB120 3260201 SO PWA 118 PW118A NE HAMSTD 14SF 14SF9 NE LANDING GEAR SHORTED W O OTHER O OTHER NR NOT REPORTED 1 AU S (AUS) RT LANDING GEAR AIR/GROUND PROXIMITY SENSOR ELECTRICAL CONNECTORMOISTURE CONTAMINATION AND SHORT CIRCUIT. 2 L 7 2 4T 4 T RT A31SO E20NE 6 N P11NE 2001080900039 20010809 00039 SO 2001 8 9 AUS20010750 1 20010713 G 3260 XAIN103 RELAY EMB 120 EMB120 3260201 SO PWA 118 PW118A NE HAMSTD 14SF 14SF9 NE LANDING GEAR FAULTY W A UNSCHED LANDING N FALSE WARNING CL CLIMB 1 AU S (AUS) GROUND/FLIGHT RELAY BOX RELAY K0290 FAULTY. 2 L 7 2 4T 4 T RT A31SO E20NE 6 N P11NE 2001080700206 20010807 00206 NE 2001 8 7 AUS20010751 2 20010717 G 7321 7863911028 HMU PWA PW120A DHAV DHC8 DHC8102 2809003 NM PWA 120 PW120A NE HAMSTD 14SF 14SF7 NE FUEL CONTROL/TUR UNSERVICEABLE W K NONE E VIBRATION/BUFFET CL CLIMB 1 AU S 2034 F26904 (AUS) RH ENGINE HYDRO MECHANICAL UNIT (HMU) FAULTY. 2 H 7 2 4T 4 T RT A13NM E20NE 6 C P7NE 2001080900040 20010809 00040 NM 2001 8 9 AUS20010752 1 20010718 G 2822 6072101 PUMP BOEING 747 747438 NM RROYCE RB211 RB211524G19 NE FUEL SYSTEM MISINSTALLED W K NONE W INADEQUATE Q C IN INSP/MAINT 1 AU S (AUS) TRANSFER PUMP CONNECTORS INCORRECTLY WIRED. THE PUMPS HAD WIRINGSWAPPED AT PIN 2 AND PIN 3. THE WIRES WERE RECONNE CTED IN THE BELIEF THAT THE WIRING CONFIGURATION WAS INCORRECT. THE AIRCRAFTHAD BEEN SUPPLIED WITH THE WIRING IN A NON-S TANDARD FORMAT. INVESTIGATION FOUND THAT SOME AIRCRAFT HAD BEEN WIRED DIFFERENTLY AT MANUFACTURE. THIS WIRING CHANGE WAS NOT INCORPORATED IN THESERVICE BULLETIN. 2 L 7 4 4F 4 F RT A20WE E30NE 2001080900041 20010809 00041 NM 2001 8 9 AUS20010753 1 20010717 G 2822 6072101 PUMP BOEING 747 747438 NM RROYCE RB211 RB211524G19 NE FUEL SYSTEM MISINSTALLED W K NONE O OTHER IN INSP/MAINT 1 AU S 210 (AUS) HORIZONTAL STABILISER FUEL TANK RT TRANSFER / JETTISON PUMP WIRINGCONNECTIONS AT PIN 2 AND PIN 3 REVERSED AT PUMP CONNECTOR PLUGDM7863. WIRING WAS CORRECT AS PER WIRING DIAGRAM BUT INCORRECT AS PER BSB 747-28-2217 FIG10. INVESTIGATION FOUND THAT SOME AIRCRAFT HAD BEEN WIRED DIFFERENTLY AT MANUFACTURE. THIS WIRING CHANGE WAS NOT INCORPORATED IN THE SERV ICE BULLETIN. 2 L 7 4 4F 4 F RT A20WE E30NE 2001080900042 20010809 00042 2001 8 9 AUS20010754 4 20010706 G 6122 B41832 FLYWEIGHT HARTZL F624L PROP GOVERNOR BROKEN W K NONE O OTHER IN INSP/MAINT 1 AU S B1798T (AUS) ENGINE CONSTANT SPEED UNIT FLYWEIGHT ASSEMBLY BROKEN. 2001080700207 20010807 00207 CE 2001 8 7 AUS20010755 1 20010705 G 5551 1016200191 FITTING BEECH 200 200BEECH 1152920 CE PWA PT6 PT6A41 52043 EA HARTZL HCB3T HCB3TN3 GL HORIZONTAL STABI CORRODED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) HORIZONTAL STABILISER AFT UPPER FITTING CONTAINED SEVEREINTERGRANNULAR CORROSION. NDI CARRIED OUT ON FITTING FOLLO WINGREMOVAL FOUND THREE CRACKS BETWEEN THE BOLT HOLES. 1 L 7 2 4T 4 T A24CE E4EA 6 C P15EA 2001080900048 20010809 00048 CE 2001 8 9 AUS20010756 1 20010710 G 3230 1068100111 UPLOCK CABLE 358150722 BEECH 58 58 1152740 CE CONT O520 IO520C 17032 SO HARTZL HCJ3Y PHCJ3YF2 GL LANDING GEAR LOOSE W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) RT MAIN LANDING GEAR DOWNLOCK CABLE LOOSE. FURTHER INVESTIGATION FOUND THAT THE UPLOCK BLOCK HAD BEEN CONTACTED BY THE UPLOCK ROLLER AND HAD BEEN MOVED OUT OF POSITION. UPLOCK CABLE RETAINING NUTS HAD TORN THROUGH NR 1 WING RIB. 1 L 7 2 3O 3 O 3A16 E5CE 5 C P36EA 2001080900050 20010809 00050 CE 2001 8 9 AUS20010757 1 20010710 G 3230 35810142 SHAFT BEECH 58 58 1152740 CE CONT O520 IO520C 17032 SO HARTZL HCJ3Y PHCJ3YF2 GL LANDING GEAR MISINSTALLED W K NONE W INADEQUATE Q C IN INSP/MAINT 1 AU S (AUS) LANDING GEAR ACTUATOR MANUAL EXTENSION HANDLE SHAFT INSTALLED 120 DEGREES OUT OF POSITION PREVENTING CORRECT OPERA TION OF HANDLE. 1 L 7 2 3O 3 O 3A16 E5CE 5 C P36EA 2001080900052 20010809 00052 CE 2001 8 9 AUS20010758 1 20010710 G 3242 HOSE BEECH 58 58 1152740 CE CONT O520 IO520C 17032 SO HARTZL HCJ3Y PHCJ3YF2 GL BRAKE FOULED W K NONE W INADEQUATE Q C IN INSP/MAINT 1 AU S (AUS) LT AND RT MAIN LANDING GEAR BRAKE LINES FOULING ON LANDING GEAR DOORS DURING RETRACTION. INVESTIGATION FOUND THAT THE BRAKE HOSES WERE APPROXIMATELY 53.975MM (2.125IN) LONGER THAN THOSE FITTED TO SIMILAR AIRCRAFT. IN ADDITION THE BRAC KETS PNO 35-815264-1 AND PNO 35-815264-2 WHICH ATTACH THE HOSES TO THE MLG LEGS WERE FITTED TO THE WRONG SIDES. PERSONNE L/MAINTENANCE ERROR. 1 L 7 2 3O 3 O 3A16 E5CE 5 C P36EA 2001080700208 20010807 00208 CE 2001 8 7 AUS20010759 1 20010705 G 8000 08504691 CONTACTOR CONT GTSIO520L CESSNA 421 421C 2076016 CE CONT O520 GTSIO520L 17032 SO MCAULY 3FF32 3FF32C501 GL ENGINE STARTING STUCK W K NONE E B VIBRATION/BUFFET SMOKE/FUMES/ODORS/SPARKS NR NOT REPORTED 1 AU S (AUS) LH ENGINE STARTER CONTACTOR STUCK CLOSED. LH ALTERNATOR DAMAGED.STARTER MOTOR TERMINAL POST DAMAGED. 1 L 7 2 3O 3 O A7CE E7CE 5 C P45GL 2001080900055 20010809 00055 EU 2001 8 9 AUS20010760 2 20010714 G 7200 ENGINE FOKKER F28 F28MK4000 4990810 EU RROYCE SPEY SPEY55515 54521 EU LEFT FAULTY W O OTHER J WARNING INDICATION NR NOT REPORTED 1 AU S (AUS) LT ENGINE OIL CONSUMPTION EXCESSIVE AT APPROXIMATELY 0.8 LITRES TO 1 LITRE PER HOUR. 2 L 7 2 4F 4 F RT A20EU E2EU 2001080900062 20010809 00062 NM 2001 8 9 AUS20010761 1 20010718 G 2621 35207900M SQUIB BOEING 747 747SP38 NM RROYCE RB211 RB211524D419 54555 NE FIRE BOTTLE WRONG PART W K NONE O OTHER IN INSP/MAINT 1 AU S 15092 (AUS) NR 1 MAIN CARGO FIRE EXTINGUISHER BOTTLE FORWARD AND AFT SQUIBSCROSS CONNECTED. 2 L 7 4 4F 4 F RT A20WE E12EU 2001080900068 20010809 00068 GL 2001 8 9 AUS20010762 2 20010712 G 7261 23038160 OIL SYSTEM HUGHES 500N 500N 3027374 SW ALLSN 25OC 250C20R GL ENGINE BLOCKED W J DUMP FUEL E B VIBRATION/BUFFET SMOKE/FUMES/ODORS/SPARKS DE DESCENT 1 AU S (AUS) NR 6 AND NR 7 BEARING OIL SCAVENGE PORT PARTIALLY BLOCKED BY CARBON DEPOSITS. OIL TYPE HAD BEEN CHANGED FROM MOBIL 254 TO MOBIL 291. 1 G 7 1 3U 3 U NC H3WE E4CE 2001080900069 20010809 00069 NE 2001 8 9 AUS20010763 2 20010715 G 7200 ENGINE BAG BAE146 BAE146200A 1500266 EU LYC ALF502 ALF502R5 41580 NE NR 3 LEAKING W A UNSCHED LANDING B SMOKE/FUMES/ODORS/SPARKS CL CLIMB 1 AU S (AUS) NR 3 ENGINE HP COMPRESSOR CONTAMINATED WITH OIL. FUMES IN CABIN. 2 H 7 4 4F 4 F RT A49EU E6NE 2001080700209 20010807 00209 SW 2001 8 7 AUS20010764 1 20010718 G 6322 209062502101 FAN BLADE BELL 412 412 1182202 SW PWA PT6T PT6T3B 52045 NE ROTORCRAFT COOLI FAILED W K NONE E K VIBRATION/BUFFET FLUID LOSS CR CRUISE 1 AU S (AUS) NO1 ENGINE OIL COOLER BLOWER FAN BLADES SEPARATED FROM HUB. 1 G 7 2 4U 4 U H4SW E22EA 2001080700210 20010807 00210 SW 2001 8 7 AUS20010765 1 20010608 G 8120 BEARING PWA R1340AN1 GULSTM G73 G73 3951802 SW PWA R1340 R1340AN1 52016 NE HAMSTD 23D 23D40 NE EXHAUST TURBOCHA FAILED W K NONE E VIBRATION/BUFFET TX TAXI/GRND HDL 1 AU S 1159 (AUS) RH ENGINE FAILED. CAUSED BY FAILURE OF SUPERCHARGER SUPPORT BEARING. 1 H 7 2 3R 3 R A783 5E2 6 C P719 2001080900071 20010809 00071 EU 2001 8 9 AUS20010766 1 20010719 G 7700 CONNECTOR BAG BAE146 BAE146300A 1500267 EU LYC ALF502 ALF502* 41580 EA INDICATOR LOOSE W A UNSCHED LANDING N FALSE WARNING CL CLIMB 1 AU S (AUS) NR 4 ENGINE VIBRATION HARNESS PLUG LOOSE. 2 H 7 4 4F 4 F RT A49EU E6NE 2001080900072 20010809 00072 NM 2001 8 9 AUS20010767 1 20010722 G 3620 PRESSURE SWITCH BOEING 767 767338 1385151 NM GE CF6 CF680C2* GL PNEUMATIC SYS CONTAMINATED W A UNSCHED LANDING J WARNING INDICATION CL CLIMB 1 AU S (AUS) PNEUMATIC SYSTEM OVERPRESSURE SWITCHES CONTAMINATED WITH WATER. 2 L 7 2 4F 4 F RT A1NM E23EA 2001080900073 20010809 00073 NM 2001 8 9 AUS20010768 1 20010215 G 2910 BACH8AEE0250T HOSE BOEING 737 737377 NM CFMINT CFM56 CFM563B2 13802 EU HYDRAULIC SYSTEM RUPTURED W A UNSCHED LANDING K J FLUID LOSS WARNING INDICATION CL CLIMB 1 AU S (AUS) LT MAIN LANDING GEAR ACTUATOR UP HOSE BURST. LOSS OF SYSTEM A' HYDRAULIC FLUID. 2 L 7 2 4F 4 F RT A16WE E21EU 2001080900074 20010809 00074 NM 2001 8 9 AUS20010769 1 20010705 G 7112 SHROUD LYC O320B2C ROBSIN R22 R22BETA NM LYC O320 O320B2C 41508 EA AIR BAFFLE MISINSTALLED W A UNSCHED LANDING E K VIBRATION/BUFFET FLUID LOSS CR CRUISE 1 AU S (AUS) ENGINE TO OIL COOLER WORN AND HOLED BY RUBBING ON CARBURETTOR HEAT SHROUD. 1 G 7 1 3O 3 O H10WE E274 2001080900075 20010809 00075 NE 2001 8 9 AUS20010770 3 20010724 G 6114 660714259 HUB SAAB SF340 340B 7860101 EU GE CT7TP CT79B 30030 NE ROTOL R390 R3904123F27 NE PROPELLER CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S 6574 (AUS) PROPELLER HUB SUSPECT CRACKED AROUND THE MOUNTING BOLT HOLE LOCATED AT THE 6.30 POSITION. FOUND DURING EDDY CURREN T INSPECTION IAW AD/PR/33. 2 L 7 2 4T 4 T RT A52EU E8NE 6 C P31NE 2001080700211 20010807 00211 NE 2001 8 7 AUS20010771 2 20010726 G 7260 MOUNT LYC ALF502R5 BAC 146 146200A 1500266 EU LYC ALF502 ALF502R5 41580 NE TURBINE ENGINE A DAMAGED W K NONE H ELECT. POWER LOSS-50 PC CR CRUISE 1 AU S (AUS) NO4 INTEGRATED DRIVE GENERATOR (IDG) BROKEN AWAY FROM GEARBOX DUE TO FAILURE OF THE MOUNT. 2 H 7 4 4F 4 F A49EU E6NE 2001080700212 20010807 00212 SO 2001 8 7 AUS20010772 1 20010721 G 3260 922AA2YA6PZ722 SENSOR EMB 120 EMB120 3260201 SO PWA 118 PW118A NE HAMSTD 14SF 14SF9 NE LANDING GEAR POS FAULTY W K NONE O N OTHER FALSE WARNING LD LANDING 1 AU S (AUS) LH MAIN LANDING GEAR DOWNLOCK PROXIMITY SENSOR INTERNAL FAULT. 2 L 7 2 4T 4 T RT A31SO E20NE 6 N P11NE 2001080900076 20010809 00076 EA 2001 8 9 AUS20010773 2 20010723 G 7324 2538993 GASKET LYC IO720A1B LYC O720 IO720A1B 41546 EA FUEL DIVIDER FAULTY W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) FLOW DIVIDER GASKET FAULTY. NEW ITEM FROM MANUFACTURER. 3 O 1E15 2001080700213 20010807 00213 NM 2001 8 7 AUS20010774 1 20010323 G 2920 59855 VALVE SUNDSTRANDEM 729550C BOEING 767 767277 NM GE CF6 CF680A 30025 NE HYDRAULIC SYSTEM CRACKED W K NONE J K WARNING INDICATION FLUID LOSS DE DESCENT 1 AU S 49754 129 (AUS) RAM AIR TURBINE (RAT) MODULE LEAKING DUE TO CRACKED CHECK VALVE. 2 L 7 2 4F 4 F RT A1NM E13NE 2001080900084 20010809 00084 EU 2001 8 9 AUS20010775 1 20010726 G 3242 5008744 DISK 50079961 FOKKER F27 F27MK50 EU PWA PWA120 PW125B NE ROTOL R352 R3526123F1 GL BRAKE CRACKED W D RETURN TO BLOCK O OTHER TX TAXI/GRND HDL 1 AU S JAN8761 (AUS) BRAKE ROTATING DISC FAILED. A PART OF THE FAILED DISC PUNCTURED THE WHEEL INNER HALF AND DEFLATED THE TUBE. INVEST IGATION FOUND NO DISCOLOURATION BUT FOUND THAT THE SLOTS HAD SPREAD FLATTENING THE OUTER CIRCUMFERENCE BETWEEN THE DRIVE RECESSES. THE THREE ROTATING DISCS ON THE BRAKE UNIT HAD CRACKS EMINATING FROM THEEXPANSION SLOTS. 2 H 7 2 4T 4 T RT A817 E20NE 6 C P16NG 2001080700214 20010807 00214 NE 2001 8 7 AUS20010776 2 20010709 G 7260 MOUNT LYC ALF502R5 BAC 146 146200A 1500266 EU LYC ALF502 ALF502R5 41580 NE TURBINE ENGINE A FAILED W K NONE H ELECT. POWER LOSS-50 PC CR CRUISE 1 AU S (AUS) NO4 CSD MOUNT FAILED. IDG ASSEMBLY SEPARATED FROM GEARBOX. 2 H 7 4 4F 4 F A49EU E6NE 2001080700215 20010807 00215 SO 2001 8 7 AUS20010777 2 20010725 G 7310 641486 PIPE CONT GTSIO520M CESSNA 404 404CESSNA 2075901 CE CONT O520 GTSIO520M 17032 SO MCAULY 3FF32 3FF32C501 GL ENGINE FUEL DIST FRACTURED W K NONE E VIBRATION/BUFFET CR CRUISE 1 AU S 1012 (AUS) RH ENGINE NO6 CYLINDER FUEL INJECTION LINE NIPPLE BROKEN OFF. 1 L 7 2 3O 3 O A25CE E7CE 5 C P45GL 2001080700216 20010807 00216 CE 2001 8 7 AUS20010778 1 20010723 G 7810 24540250 CLAMP CONT TSIO520P CESSNA 210 P210N 2073454 CE CONT O520 TSIO520P 17040 SO MCAULY D3A34 D3A34C402 GL ENGINE COLLECTOR BROKEN W K NONE O E R OTHER VIBRATION/BUFFET PARTIAL RPM/PWR LOSS IN INSP/MAINT 1 AU S (AUS) ENGINE FORWARD LH EXHAUST CLAMP BROKEN. FORWARD AIRFRAMESTRUCTURE, COWL AND NOSE TYRE TORCHED. 1 H 7 1 3O 3 O 3A21 E8CE 5 C P47GL 2001080900086 20010809 00086 CE 2001 8 9 AUS20010779 1 20010723 G 5512 07326133781 STRUCTURE CESSNA 185 CESSNA 185 185 2072802 CE CONT O520 IO520D 17032 SO MCAULY 2A34C D2A34C58 GL HORIZONTAL STAB DAMAGED W K NONE O OTHER IN INSP/MAINT 1 AU S 1850271 (AUS) HORIZONTAL STABILISER TIP DAMAGED. 1 H 7 1 3O 3 O NC 3A24 E5CE 5 C P3EA 2001080900090 20010809 00090 EU 2001 8 9 AUS20010781 1 20010626 G 2742 MC103 ACTUATOR FOKKER F28 F28MK4000 4990810 EU RROYCE SPEY SPEY55515 54521 EU STABILIZER LEAKING W O OTHER K J FLUID LOSS WARNING INDICATION DE DESCENT 1 AU S 110 (AUS) STABILIZER ACTUATOR LEAKING. LOSS OF HYDRAULIC FLUID. 2 L 7 2 4F 4 F RT A20EU E2EU 2001080700217 20010807 00217 EU 2001 8 7 AUS20010782 1 20010701 G 3411 DRAIN VALVE FOKKER F28 F28MK1000 4990808 EU RROYCE SPEY SPEY55515 54521 EU PITOT/STATIC SYS STUCK W K NONE I FLT. ATTITUDE INST. NR NOT REPORTED 1 AU S (AUS) PITOT STATIC SYSTEM DRAIN LINE VALVE STUCK IN OPEN POSITION. 2 L 7 2 4F 4 F RT A20EU E2EU 2001080700218 20010807 00218 EU 2001 8 7 AUS20010784 1 20010705 G 5210 CABLE FOKKER F28 F28MK4000 4990810 EU RROYCE SPEY SPEY55515 54521 EU PAX DOOR BROKEN W O OTHER O OTHER NR NOT REPORTED 1 AU S (AUS) PASSENGER DOOR DECLUTCH CABLE TERMINAL END BROKEN. 2 L 7 2 4F 4 F RT A20EU E2EU 2001080700219 20010807 00219 2001 8 7 AUS20010785 4 20010715 G 3460 B471ABM3 COMPUTER AIRBUS 310 A310304 EU PWA 4152 PW4152 NE FLIGHT MANAGEMEN FAULTY W K NONE F FLT CONT AFFECTED TO TAKEOFF 1 AU S 4363 303 (AUS) FLIGHT AUGMENTATION COMPUTER FAULTY. 2 L 7 2 4F RT A35EU E24NE 2001080900097 20010809 00097 EU 2001 8 9 AUS20010786 1 20010722 G 2910 296801 REDUCER FOKKER F28 F28MK1000 4990808 EU RROYCE SPEY SPEY55515 54521 EU HYDRAULIC SYSTEM CRACKED W O OTHER K FLUID LOSS NR NOT REPORTED 1 AU S 55929 640 (AUS) LANDING GEAR HYDRAULIC SYSTEM PRESSURE REDUCER CRACKED. LOSS OF HYDRAULIC FLUID. 2 L 7 2 4F 4 F RT A20EU E2EU 2001080900098 20010809 00098 EU 2001 8 9 AUS20010787 1 20010724 G 5270 BOSS FOKKER F28 F28MK1000 4990808 EU RROYCE SPEY SPEY55515 54521 EU DOOR WARNING SYS OUT OF ADJ W O OTHER N FALSE WARNING NR NOT REPORTED 1 AU S (AUS) SERVICE / EMERGENCY DOOR STRIKER BOSS LOOSE AND MISALIGNED. 2 L 7 2 4F 4 F RT A20EU E2EU 2001080700220 20010807 00220 SW 2001 8 7 AUS20010788 1 20010630 G 5313 206031314125 LONGERON BELL 206L1 BELL 206 206L1 1182107 SW ALLSN 250C 250C30P 03013 GL FUSELAGE MAIN, L CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S 45323 (AUS) FUSELAGE UPPER FORWARD LONGERON CRACKED. 1 G 7 1 3U 3 U H2SW E1GL 2001080700221 20010807 00221 SW 2001 8 7 AUS20010789 1 20010630 G 5320 206032307031 ANGLE BELL 206L1 BELL 206 206L1 1182107 SW ALLSN 250C 250C30P 03013 GL FUSELAGE, MISCEL CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S 45323 (AUS) FUSELAGE ANGLE CRACKED. 1 G 7 1 3U 3 U H2SW E1GL 2001080900099 20010809 00099 NM 2001 8 9 AUS20010790 1 20010730 G 2910 BACC27AC12121006 FITTING BOEING 747 747430 1384942 NM RROYCE RB211 RB211524* NE HYDRAULIC SYSTEM CRACKED W K NONE K FLUID LOSS IN INSP/MAINT 1 AU S (AUS) LTBODY LANDING GEAR RETRACTION ACTUATOR LINE UNION CRACKED AND LEAKING. HYDRAULIC PIPE ALSO LEAKING. 2 L 7 4 4F 4 F RT A20WE E12EU 2001090500195 20010905 00195 SO 2001 9 5 AUS20010791 1 20010724 G 2752 CONNECTOR EMB 120 EMB120 3260201 SO PWA 118 PW118A NE HAMSTD 14SF 14SF9 NE FLAP ACTUATOR CONTAMINATED W K NONE F J FLT CONT AFFECTED WARNING INDICATION DE DESCENT 1 AU S (AUS) RT OUTBOARD FLAP ACTUATOR ELECTRICAL CONNECTOR CONTAMINATED WITH MOISTURE. 2 L 7 2 4T 4 T RT A31SO E20NE 6 N P11NE 2001090500196 20010905 00196 EU 2001 9 5 AUS20010793 1 20010710 G 2913 716988 PUMP BAG BAE146 BAE146200A 1500266 EU LYC ALF502 ALF502R5 41580 NE HYDRAULIC PUMP WORN W K NONE O OTHER IN INSP/MAINT 1 AU S 3740 (AUS) ENGINE DRIVEN HYDRAULIC PUMP INTERNAL AND EXTERNAL DRIVE SPLINES WORN EXCESSIVELY. 2 H 7 4 4F 4 F RT A49EU E6NE 2001090500197 20010905 00197 EA 2001 9 5 AUS20010797 2 20010801 G 8530 LW12933 COLLET LYC O540 IO540K1G5 41532 EA CYLINDER INCORRECT W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) ENGINE CYLINDER KIT PN 05K21102 FAULTY. CYLINDER PN LW012993 CONTAINED ONE CORRECT AND ONE INCORRECT (SMALLER) VAL VE RETAINING COLLET FITTED TO THE EXHAUST VALVE. THE INCORRECT COLLET HAD DAMAGED THE VALVE STEM RENDERING IT UNSERVICEA BLE. 3 O 1E4 2001090500204 20010905 00204 WP 2001 9 5 AUS20010798 2 20010724 G 7261 31032173 PUMP CESSNA 441 441 2076020 CE GARRTT TPE331 TPE331* 01514 WP HARTZL HCB3T HCB3TN5 GL OIL SYSTEM CRACKED W K NONE K E FLUID LOSS VIBRATION/BUFFET NR NOT REPORTED 1 AU S 90 (AUS) LT ENGINE OIL PUMP HOUSING CRACKED. 1 L 7 2 3T 3 T RT A28CE E2WE 6 C P15EA 2001090500054 20010905 00054 EU 2001 9 5 AUS20010799 1 20010725 G 5344 350A25122726 HINGE SNIAS 350 AS350BA 8680817 EU TMECA ARRIEL ARRIEL1A 60030 NE FUSELAGE DOOR HI BROKEN W K NONE D INFLIGHT SEPARATION CR CRUISE 1 AU S (AUS) DOOR HINGE BROKEN. 1 G 7 1 3U 3 U NC H9EU E19EU 2001090500231 20010905 00231 CE 2001 9 5 AUS20010800 1 20010726 G 7603 1317652F ROD END BEECH 200 200BEECH 1152920 CE PWA PT6 PT6A42 52043 NE HARTZL HCB3T HCB3TN5 GL POWER LEVER OUT OF ADJ W K NONE W INADEQUATE Q C IN INSP/MAINT 1 AU S (AUS) LT ENGINE POWER LEVER CABLE TO POWER INPUT LEVER ROD END OUT OF ADJUSTMENT AND THE LOCKNUT WAS LOOSE. THE ROD END AND LOCKNUT HAD NOT BEEN CORRECTLY INSTALLED FOLLOWING FCU CHANGE.PERSONNEL/MAINTENANCE ERROR. 1 L 7 2 4T 4 T A24CE E4EA 6 C P15EA 2001090500232 20010905 00232 NM 2001 9 5 AUS20010801 1 20010729 G 3242 26056623 ROTOR BOEING 747 747338 NM RROYCE RB211 RB211524D419 54555 NE BRAKE FAILED W K NONE O OTHER IN INSP/MAINT 1 AU S 13222 (AUS) NR 7 MAIN BODY WHEEL BRAKE ROTOR SEGMENT FAILED. 2 L 7 2 4F 4 F RT A20WE E12EU 2001091300255 20010913 00255 NM 2001 9 13 AUS20010802 1 20010731 G 2530 41610015 COFFEEMAKER BOEING 767 767330 NM GALLEY FAULTY W O OTHER B SMOKE/FUMES/ODORS/SPARKS CL CLIMB 1 AU S 0632 (AUS) FORWARD GALLEY CENTRE COFFEE MAKER FAULTY. DURING RECTIFICATION OF THE FAULT IT WAS FOUND THAT THE COFFEEMAKER WAS THE INCORRECT PART NUMBER FOR FITMENT TO THIS MODEL AIRCRAFT. UNAPPROVED PART. 2 L 7 2 4F RT A1NM 2001090500055 20010905 00055 NM 2001 9 5 AUS20010803 1 20010731 G 3230 273T63041 ACTUATOR BOEING 273T63016 BOEING 767 767204 NM GE CF6 CF680A 30025 NE LANDING GEAR RET FAULTY W K NONE O N OTHER FALSE WARNING TO TAKEOFF 1 AU S 40536 00164 (AUS) LH MAIN LANDING GEAR FORWARD DRAG BRACE DOWNLOCK ACTUATOR FAULTY. INVESTIGATION FOUND THE ACTUATOR PISTON ROD DETA CHED FROM THE ACTUATOR BODY DUE TO FAILURE OF THE PISTON ROD IN THE THREADEDAREA WHICH ENGAGES THE PISTON RETAINING NUT. 2 L 7 2 4F 4 F RT A1NM E13NE 2001091300261 20010913 00261 NE 2001 9 13 AUS20010804 2 20010726 G 7310 40885 CONTROL UNIT BOEING 747 747338 NM RROYCE RB211 RB211524* NE FUEL DIST LEAKING W K NONE K FLUID LOSS IN INSP/MAINT 1 AU S 3474 (AUS) NR 4R REFUEL VALVE CONTROL UNIT HOUSING LEAKING. 2 L 7 2 4F 4 F RT A20WE E12EU 2001091300267 20010913 00267 CE 2001 9 13 AUS20010805 1 20010726 G 3230 3581507715 BRACKET BEECH 36 A36 1151604 CE LANDING GEAR CORRODED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) RT MAIN LANDING GEAR UPLOCK BRACKET CORRODED AT PIVOT POINT. 1 L 7 1 3O 3A15 2001091300268 20010913 00268 SO 2001 9 13 AUS20010806 1 20010730 G 2910 RESERVOIR EMB 120 EMB120 3260201 SO PWA 118 PW118A NE HAMSTD 14SF 14SF9 NE HYDRAULIC SYSTEM LEAKING W O OTHER K FLUID LOSS NR NOT REPORTED 1 AU S (AUS) LOSS OF FLUID FROM GREEN HYDRAULIC SYSTEM. SUSPECT CAUSED BY INCORRECT BRAKING SEQUENCE. 2 L 7 2 4T 4 T RT A31SO E20NE 6 N P11NE 2001091300269 20010913 00269 EA 2001 9 13 AUS20010807 2 20010724 G 8500 L575861A ENGINE PIPER PA31 PA31350 7103110 SO LYC O540 TIO540J2BD 41532 EA HARTZL HCE3Y HCE3YR2 GL LEFT FAILED W O OTHER E R F VIBRATION/BUFFET PARTIAL RPM/PWR LOSS FLT CONT AFFECTED CL CLIMB 1 AU S 1041 (AUS) LT ENGINE POWER LOSS AND VIBRATION. 1 L 7 2 3O 3 O A20SO E14EA 5 C P33EA 2001091300270 20010913 00270 SO 2001 9 13 AUS20010808 1 20010510 G 2730 BOLT PIPER PA31 PA31350 7103110 SO LYC O540 TIO540J2BD 41532 EA HARTZL HCE3Y HCE3YR2 GL ELEVATOR CONTROL UNAPPROVED PART W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) ELEVATOR PUSHROD BOLTS INCORRECT TYPE AS REQUIRED BY AD/PA31/121AMDT1. UNAPPROVED PART. PERSONNEL/MAINTENANCE ERRO R. 1 L 7 2 3O 3 O A20SO E14EA 5 C P33EA 2001090500056 20010905 00056 EA 2001 9 5 AUS20010809 2 20010428 G 7310 FILTER LYC TIO540J2BD PIPER PA31 PA31350 7103110 SO LYC O540 TIO540J2BD 41532 EA HARTZL HCE3Y HCE3YR2 GL ENGINE FUEL DIST LEAKING W K NONE B SMOKE/FUMES/ODORS/SPARKS CR CRUISE 1 AU S (AUS) RH ENGINE FUEL FILTER SEAL LEAKING. 1 L 7 2 3O 3 O A20SO E14EA 5 C P33EA 2001091300271 20010913 00271 SO 2001 9 13 AUS20010810 1 20010515 G 5210 4225000 HANDLE PIPER PA31 PA31350 7103110 SO LYC O540 TIO540J2BD 41532 EA HARTZL HCE3Y HCE3YR2 GL PAX DOOR MISREPAIRED W K NONE W INADEQUATE Q C IN INSP/MAINT 1 AU S (AUS) CABIN DOOR INNER HANDLE HAD UNAPPROVED REPAIR. HANDLE HAD BEENWELDED IN TWO PLACES. PERSONNEL/MAINTENANCE ERROR. U NAPPROVED REPAIR. 1 L 7 2 3O 3 O A20SO E14EA 5 C P33EA 2001090500057 20010905 00057 SO 2001 9 5 AUS20010811 1 20010424 G 7920 3999502 HOSE LYC TIO540J2BD PIPER PA31 PA31350 7103110 SO LYC O540 TIO540J2BD 41532 EA HARTZL HCE3Y HCE3YR2 GL ENGINE OIL DISTR DETERIORATED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) ENGINE OIL PRESSURE HOSE LOCATED BETWEEN VERNATHERM AND OIL COOLER INCORRECTLY ROUTED CAUSING PREMATURE DETERIORAT ION DUE TOHEAT DAMAGE. PERSONNEL/MAINTENANCE ERROR. 1 L 7 2 3O 3 O A20SO E14EA 5 C P33EA 2001090500058 20010905 00058 EA 2001 9 5 AUS20010812 2 20010419 G 7310 74134 FILTER LYC TIO540J2BD PIPER PA31 PA31350 7103110 SO LYC O540 TIO540J2BD 41532 EA HARTZL HCE3Y HCE3YR2 GL ENGINE FUEL DIST LEAKING W K NONE O K OTHER FLUID LOSS IN INSP/MAINT 1 AU S (AUS) FUEL FILTER LEAKING. FILTER BOWL LOOSE. 1 L 7 2 3O 3 O A20SO E14EA 5 C P33EA 2001090500059 20010905 00059 EA 2001 9 5 AUS20010813 2 20010212 G 7310 74134 FILTER LYC TIO540J2BD PIPER PA31 PA31350 7103110 SO LYC O540 TIO540J2BD 41532 EA HARTZL HCE3Y HCE3YR2 GL ENGINE FUEL DIST LEAKING W K NONE O K OTHER FLUID LOSS IN INSP/MAINT 1 AU S (AUS) FUEL FILTER BOWL LEAKING. 1 L 7 2 3O 3 O A20SO E14EA 5 C P33EA 2001091300272 20010913 00272 SO 2001 9 13 AUS20010814 1 20010419 G 7603 24894 CABLE LYC TIO540J2BD PIPER PA31 PA31350 7103110 SO LYC O540 TIO540J2BD 41532 EA HARTZL HCE3Y HCE3YR2 GL POWER LEVER MISRIGGED W K NONE W INADEQUATE Q C IN INSP/MAINT 1 AU S (AUS) THROTTLE CABLE INCORRECTLY ASSEMBLED AND RIGGED.PERSONNEL/MAINTENANCE ERROR. 1 L 7 2 3O 3 O A20SO E14EA 5 C P33EA 2001090500060 20010905 00060 SO 2001 9 5 AUS20010815 1 20010329 G 3230 UPLOCK PIPER PA31 PA31350 7103110 SO LYC O540 TIO540J2BD 41532 EA HARTZL HCE3Y HCE3YR2 GL LANDING GEAR RET SHEARED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) LH MAIN LANDING GEAR UPLOCK EYE SHEARED. 1 L 7 2 3O 3 O A20SO E14EA 5 C P33EA 2001090500061 20010905 00061 SO 2001 9 5 AUS20010816 1 20010410 G 7603 2489402 CABLE LYC TIO540J2BD PIPER PA31 PA31350 7103110 SO LYC O540 TIO540J2BD 41532 EA HARTZL HCE3Y HCE3YR2 GL POWER LEVER SEPARATED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) RH ENGINE THROTTLE CABLE SECTIONS LOCKWIRED TOGETHER. PERSONNEL/MAINTENANCE ERROR. 1 L 7 2 3O 3 O A20SO E14EA 5 C P33EA 2001091700185 20010917 00185 SO 2001 9 17 AUS20010817 1 20010412 G 7603 24894 ROD END LYC TIO540J2BD PIPER PA31 PA31350 7103110 SO LYC O540 TIO540J2BD 41532 EA HARTZL HCE3Y HCE3YR2 GL POWER LEVER WRONG PART W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) RT ENGINE CONTROL ARM RODEND INCORRECTLY ASSEMBLED ON THE WRONG SIDE OF THE ARM CAUSING LOAD ON THE CABLE BALL END . 1 L 7 2 3O 3 O A20SO E14EA 5 C P33EA 2001090500062 20010905 00062 SO 2001 9 5 AUS20010818 1 20010412 G 7920 3999505 HOSE LYC TIO540J2BD PIPER PA31 PA31350 7103110 SO LYC O540 TIO540J2BD 41532 EA HARTZL HCE3Y HCE3YR2 GL ENGINE OIL DISTR DETERIORATED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) ENGINE OIL COOLER HOSE DETERIORATED DUE TO BEING INCORRECTLYROUTED CLOSE TO TURBOCHARGER. HOSE ALSO HAD EXCESSIVE BENDRADIUS. 1 L 7 2 3O 3 O A20SO E14EA 5 C P33EA 2001090500063 20010905 00063 SO 2001 9 5 AUS20010819 1 20010412 G 7810 EXHAUST PIPE LYC TIO540J2BD PIPER PA31 PA31350 7103110 SO LYC O540 TIO540J2BD 41532 EA HARTZL HCE3Y HCE3YR2 GL ENGINE COLLECTOR CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) ENGINE EXHAUST SYSTEM TRANSITIONS HOLED AND CRACKED. 1 L 7 2 3O 3 O A20SO E14EA 5 C P33EA 2001091700187 20010917 00187 SO 2001 9 17 AUS20010820 1 20010412 G 7810 EXHAUST PIPE LYC TIO540J2BD PIPER PA31 PA31350 7103110 SO LYC O540 TIO540J2BD 41532 EA HARTZL HCE3Y HCE3YR2 GL ENGINE COLLECTOR MISINSTALLED W K NONE W INADEQUATE Q C IN INSP/MAINT 1 AU S (AUS) LT TAILPIPE INCORRECTLY FITTED TO TURBOCHARGER CAUSING BURNING OF THE EXHAUST CLAMP. 1 L 7 2 3O 3 O A20SO E14EA 5 C P33EA 2001090500064 20010905 00064 SO 2001 9 5 AUS20010821 1 20010412 G 7810 GASKET LYC TIO540J2BD PIPER PA31 PA31350 7103110 SO LYC O540 TIO540J2BD 41532 EA HARTZL HCE3Y HCE3YR2 GL ENGINE COLLECTOR MISSING W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) RH ENGINE TURBOCHARGER EXHAUST TRANSITIONS FITTED WITHOUT A CRUSH GASKET. PERSONNEL/MAINTENANCE ERROR. 1 L 7 2 3O 3 O A20SO E14EA 5 C P33EA 2001090500065 20010905 00065 EA 2001 9 5 AUS20010823 2 20010803 G 7313 74151 INJECTOR LYC IO540K1B5 BNORM BN2 BN2A20 1520220 EU LYC O540 IO540K1B5 41532 EA HARTZL HCC2Y HCC2YK2 GL FUEL INJECTOR NO BLOCKED W K NONE E A VIBRATION/BUFFET FLAME/FIRE LD LANDING 1 AU S (AUS) NO1 ENGINE FUEL INJECTOR NOZZLE PARTIALLY BLOCKED. 1 H 7 2 3O 3 O A17EU 1E4 5 C P920 2001090500067 20010905 00067 CE 2001 9 5 AUS20010825 1 20010710 G 5712 08221757 RIB CESSNA 310 310R 2074245 CE CONT O520 IO520M 17032 SO MCAULY 3AF32C 3AF32C87 GL WING, RIB/BULKHE CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) WING RIBS LOCATED IN LH WHEEL BAY CRACKED AS INDICATED IN CESSNASERVICE LETTER ME76-2. 1 L 7 2 3O 3 O 3A10 E5CE 5 C P22EA 2001090500068 20010905 00068 CE 2001 9 5 AUS20010826 1 20010731 G 7920 111F4176S0220 HOSE LYC O320E2D CESSNA 172 172M 2072418 CE LYC O320 O320E2D 41508 EA MCAULY 1C160 1C160DTM GL ENGINE OIL DISTR LEAKING W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) ENGINE OIL COOLER HOSE POROUS AND LEAKING IN THE AREA ON THEOUTSIDE OF THE BEND AT THE ENGINE END. FIRE SLEEVINGCO NTAMINATED. HOSE MANUFACTURED 30 DECEMBER 1996. 1 H 7 1 3O 3 O NT 3A12 E274 5 N P910 2001090500069 20010905 00069 SO 2001 9 5 AUS20010827 1 20010419 G 7920 HOSE LYC TIO540J2BD PIPER PA31 PA31350 7103110 SO LYC O540 TIO540J2BD 41532 EA HARTZL HCE3Y HCE3YR2 GL ENGINE OIL DISTR DETERIORATED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) TURBOCHARGER OIL SUPPLY LINE DETERIORATED. 1 L 7 2 3O 3 O A20SO E14EA 5 C P33EA 2001091700191 20010917 00191 SO 2001 9 17 AUS20010828 1 20010805 G 3260 487862 SWITCH PIPER PA31 PA31350 7103110 SO LYC O540 TIO540J2BD 41532 EA HARTZL HCE3Y HCE3YR2 GL MLG OUT OF ADJ W O OTHER J WARNING INDICATION DE DESCENT 1 AU S (AUS) LT AND RT MAIN LANDING GEAR DOOR MICROSWITCHES OUT OF ADJUSTMENT. 1 L 7 2 3O 3 O A20SO E14EA 5 C P33EA 2001090500070 20010905 00070 SO 2001 9 5 AUS20010829 1 20010424 G 7920 HOSE LYC TIO540J2BD PIPER PA31 PA31350 7103110 SO LYC O540 TIO540J2BD 41532 EA HARTZL HCE3Y HCE3YR2 GL ENGINE OIL DISTR DETERIORATED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) TURBOCHARGER OIL PRESSURE HOSE INCORRECTLY ROUTED. HOSE DETERIORATED DUE TO HEAT. HOSE LOOSE ON END FITTING.PERSON NEL/MAINTENANCE ERROR. 1 L 7 2 3O 3 O A20SO E14EA 5 C P33EA 2001090500071 20010905 00071 SO 2001 9 5 AUS20010830 1 20010402 G 7112 BAFFLE LYC TIO540J2BD PIPER PA31 PA31350 7103110 SO LYC O540 TIO540J2BD 41532 EA HARTZL HCE3Y HCE3YR2 GL ENGINE AIR BAFFL MISSING W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) LOWER ENGINE BAFFLE MISSING. 1 L 7 2 3O 3 O A20SO E14EA 5 C P33EA 2001091700192 20010917 00192 EA 2001 9 17 AUS20010831 2 20010727 G 8530 CYLINDER PIPER PA31 PA31350 7103110 SO LYC O540 TIO540J2BD 41532 EA HARTZL HCE3Y HCE3YR2 GL ENGINE FAILED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) LT ENGINE NR 2 CYLINDER FAILED. 1 L 7 2 3O 3 O A20SO E14EA 5 C P33EA 2001090500072 20010905 00072 SO 2001 9 5 AUS20010832 1 20010727 G 2140 HEATER PIPER PA31 PA31350 7103110 SO LYC O540 TIO540J2BD 41532 EA HARTZL HCE3Y HCE3YR2 GL HEATING SYSTEM FAILED W K NONE B SMOKE/FUMES/ODORS/SPARKS NR NOT REPORTED 1 AU S (AUS) HEATER FAILED. SPARKING BEHIND INSTRUMENT PANEL CAUSED BY FOREIGN OBJECT FALLING ACROSS TERMINALS. 1 L 7 2 3O 3 O A20SO E14EA 5 C P33EA 2001091700193 20010917 00193 EA 2001 9 17 AUS20010833 2 20010727 G 8530 CYLINDER PIPER PA31 PA31350 7103110 SO LYC O540 TIO540J2BD 41532 EA HARTZL HCE3Y HCE3YR2 GL ENGINE FAILED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) LT ENGINE NR 2 CYLINDER FAILED. 1 L 7 2 3O 3 O A20SO E14EA 5 C P33EA 2001091700195 20010917 00195 EA 2001 9 17 AUS20010834 2 20010529 G 8530 CYLINDER PIPER PA31 PA31350 7103110 SO LYC O540 TIO540J2BD 41532 EA HARTZL HCE3Y HCE3YR2 GL ENGINE FAILED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) LT ENGINE NR 2 CYLINDER FAILED. 1 L 7 2 3O 3 O A20SO E14EA 5 C P33EA 2001091700197 20010917 00197 SW 2001 9 17 AUS20010836 1 20010801 G 2910 212076176001 PIPE BELL 412 412 1182202 SW PWA PT6T PT6T3 52045 EA HYDRAULIC SYSTEM CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) HYDRAULIC PIPE CRACKED IN RADIUS. 1 G 7 2 4U 4 U H4SW E22EA 2001091700199 20010917 00199 SO 2001 9 17 AUS20010837 1 20010609 G 5751 62373000 DOUBLER PIPER PA28 PA28140 7102802 SO AILERONS CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) RT AILERON DOUBLER CRACKED. 1 L 7 1 3O 2A13 2001091700202 20010917 00202 NE 2001 9 17 AUS20010839 2 20010731 G 7321 12773 FUEL CONTROL BOEING 747 747238B 1384828 NM RROYCE RB211 RB211524D419 54555 NE NR 4 ENGINE FAULTY W E ENGINE SHUTDOWN E K VIBRATION/BUFFET FLUID LOSS DE DESCENT 1 AU S 6396 (AUS) NR 4 ENGINE FUEL FLOW REGULATOR FAULTY. AIRCRAFT IS FOREIGN REGISTRATION DQ-FJE. 2 L 7 4 4F 4 F A20WE E12EU 2001090500073 20010905 00073 CE 2001 9 5 AUS20010840 1 20010614 G 3230 98820152 ACTUATOR CESSNA 172 172RG 2072438 CE LYC O360 O360F1A6 41514 EA MCAULY 2D34C B2D34C220 GL LANDING GEAR RET UNSERVICEABLE W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) MAIN LANDING GEAR ACTUATOR FAULTY. 1 H 7 1 3O 3 O 3A17 E286 5 C P7EA 2001091700207 20010917 00207 CE 2001 9 17 AUS20010843 1 20010803 G 5540 51310103 HINGE CESSNA 441 441 2076020 CE RUDDER MISMANUFACTURED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) LOWER RUDDER HINGE BRACKET INSTALLED UPSIDE DOWN. FOUND DURINGINSPECTION IAW CESSNA CQB00-2 R1. MANUFACTURING ERRO R. 1 L 7 2 3T RT A28CE 2001091700208 20010917 00208 2001 9 17 AUS20010844 4 20010713 G 6122 5AA228 GOVERNOR LKHEED 1049 C121C 5262118 WP WRIGHT R3350 R3350* 67040 EA HAMSTD 43E 43E60 NE PROPELLER FAULTY W C ABORTED TAKEOFF O OTHER TO TAKEOFF 1 AU S (AUS) NR 4 ENGINE GOVERNOR FAULTY. 2 L 7 4 4R 4 R 6A5 E272 6 C P871 2001091700210 20010917 00210 NE 2001 9 17 AUS20010845 2 20010714 G 8500 ENGINE DOUG DC3 C47B 3021467 WP PWA R1830 R183092 52020 NE HAMSTD 23E 23E50 NE LEFT MAKING METAL W O OTHER E K VIBRATION/BUFFET FLUID LOSS CR CRUISE 1 AU S (AUS) LT ENGINE OIL FILTER METAL CONTAMINATION. ENGINE CHANGED. 2 L 7 2 4R 4 R A669 5E4 6 C P603 2001090500074 20010905 00074 GL 2001 9 5 AUS20010846 2 20010728 G 7230 6898607 BEARING ALLSN 250C20F AEROSP AS355 AS355F1 8680810 EU ALLSN 250C 250C20F 03013 GL TURBINE ENGINE C DAMAGED W K NONE E J VIBRATION/BUFFET WARNING INDICATION DE DESCENT 1 AU S CAC40345 (AUS) NO2 ENGINE NO1 BEARING FAILED. 1 G 7 2 3U 3 U H11EU E4CE 2001091700214 20010917 00214 NE 2001 9 17 AUS20010848 2 20010626 G 7230 SEAL BAG BAE146 BAE146300A 1500267 EU LYC ALF502 ALF502R5 41580 NE TURBINE ENGINE LEAKING W O OTHER B SMOKE/FUMES/ODORS/SPARKS DE DESCENT 1 AU S (AUS) NR 1 ENGINE OIL LEAKING AROUND BLEED BAND AREA. NR 1 SEAL LEAKING. 2 H 7 4 4F 4 F RT A49EU E6NE 2001091700215 20010917 00215 NM 2001 9 17 AUS20010850 1 20010807 G 6310 A1902 BELT ROBSIN R22 R22BETA NM LYC O320 O320B2C 41508 EA TRANSMISSION FRAYED W O OTHER E VIBRATION/BUFFET CR CRUISE 1 AU S 7390 (AUS) REAR DRIVE BELT FRAYED, SPLIT AND ROLLED OFF PULLEY. 1 G 7 1 3O 3 O H10WE E274 2001091700217 20010917 00217 SO 2001 9 17 AUS20010851 1 20010723 G 3260 SWITCH PIPER PA24 PA24250 7102404 SO LYC O540 O540A1A 41532 EA MCAULY 2D36C 2D36C28 GL MLG MISINSTALLED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) RT MAIN LANDING GEAR DOWN LIMIT MICROSWITCH INCORRECTLY WIRED.WHEN THE NLG MICROSWITCH WIRES WERE DISCONNECTED THE DOWN LIGHT WAS STILL ON. INVESTIGATION FOUND THE RT LANDING GEAR MICROSWITCH WIRING WAS INCORRECT. PERSONNEL/MAINTENANC E ERROR. 1 L 7 1 3O 3 O 1A15 E295 5 C P901 2001091700219 20010917 00219 SW 2001 9 17 AUS20010852 1 20010802 G 6210 212015501115 BLADE BELL 212 212 1181420 SW PWA PT6T PT6T3B 52045 NE MAIN ROTOR DELAMINATED W O OTHER O OTHER CR CRUISE 1 AU S (AUS) MAIN ROTOR BLADE SKIN DELAMINATED AT THE BLADE TIP JUST AFT OFTHE D' SPAR. AREA OF DELAMINATION 55MM BY 75MM (2IN BY 3IN). 1 G 7 1 4U 4 U H4SW E22EA 2001091700222 20010917 00222 NM 2001 9 17 AUS20010855 1 20010803 G 5311 A0202 FRAME ROBSIN R22 R22BETA NM LYC O320 O320B2C 41508 EA FUSELAGE CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) UPPER FUSELAGE FRAME CRACKED. FOUND DURING MAGNETIC PARTICLE INSPECTION. 1 G 7 1 3O 3 O H10WE E274 2001091700223 20010917 00223 CE 2001 9 17 AUS20010856 1 20010808 G 2434 ALV9501R ALTERNATOR CESSNA 404 404CESSNA 2075901 CE ENGINE FAILED W O OTHER H ELECT. POWER LOSS-50 PC NR NOT REPORTED 1 AU S (AUS) ALTERNATOR FAILED IN FLIGHT. INVESTIGATION FOUND THE ALTERNATOR HOUSING ASSEMBLY BOLTS LOOSE WITH TWO OF THE BOLTS HAVING COMPLETELY SEPARATED AND LAYING IN THE BOTTOM OF THE ENGINE COWL. REAR BEARING COLLAPSED. INCORRECT TAB WASHERS USED. TAB WASHERS WERE FOR USE ON A 6.35MM (0.25IN) BOLT WHEREAS THE BOLTS USED ONTHE ALTERNATOR WERE 4.762MM (0.185IN). UNAPPROVED PART. PERSONNEL/MAINTENANCE ERROR. 1 L 7 2 3O A25CE 2001091700224 20010917 00224 EU 2001 9 17 AUS20010857 1 20010716 G 5730 SKIN BAG BAE146 BAE146100A 1500260 EU LYC ALF502 ALF502R5 41580 NE LT WING CORRODED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) LT WING LOWER SKIN CORRODED IN AREA BETWEEN RIB 13 AND RIB 15.CORROSION WAS BEYOND ALLOWIABLE LIMITS. 2 H 7 4 4F 4 F RT A49EU E6NE 2001091700226 20010917 00226 CE 2001 9 17 AUS20010858 1 20010809 G 3233 1CH1066 SWITCH TEIJINSEIKI 99101393 CESSNA 441 441 2076020 CE GARRTT TPE331 TPE3318 01514 WP HARTZL HCB3T HCB3TN5 GL MLG ACTUATOR OUT OF ADJ W K NONE O OTHER IN INSP/MAINT 1 AU S 1851 (AUS) NOSE LANDING GEAR ACTUATOR POSITION SWITCH INCORRECTLY ADJUSTED.PERSONNEL/MAINTENANCE ERROR. 1 L 7 2 3T 4 T RT A28CE E4WE 6 C P15EA 2001091700228 20010917 00228 NM 2001 9 17 AUS20010859 1 20010809 G 5270 284A3539 SWITCH BOEING 737 737* NM CFMINT CFM56 CFM565A1 NE DOOR WARNING FAULTY W C ABORTED TAKEOFF N FALSE WARNING TO TAKEOFF 1 AU S (AUS) LT OVERWING EXIT WARNING SWITCH FAULTY. 2 L 7 2 4F 4 F RT A16WE E29NE 2001090500077 20010905 00077 CE 2001 9 5 AUS20010860 1 20010713 G 2434 ALV9510R ALTERNATOR CESSNA 404 404CESSNA 2075901 CE CONT O520 GTSIO520M 17032 SO MCAULY 3FF32 3FF32C501 GL DC GENERATOR-ALT FAILED W K NONE H ELECT. POWER LOSS-50 PC CR CRUISE 1 AU S 100 9011080 (AUS) ALTERNATOR ROTOR SHAFT WORN IN AREA OF FORWARD ARMATURE SLIPRING. 1 L 7 2 3O 3 O A25CE E7CE 5 C P45GL 2001091700229 20010917 00229 NE 2001 9 17 AUS20010861 2 20010807 G 7421 CH34055 IGNITER BELL 412 412 1182202 SW PWA PT6T PT6T3B 52045 NE ENGINE FAILED W O OTHER B SMOKE/FUMES/ODORS/SPARKS CL CLIMB 1 AU S (AUS) NR 1 ENGINE LOWER IGNITER CENTRE CORE MISSING. P3 AIR LEAKING INTO ENGINE BAY. 1 G 7 2 4U 4 U H4SW E22EA 2001091700232 20010917 00232 NM 2001 9 17 AUS20010862 1 20010201 G 5311 FRAME BOEING 767 767277 NM GE CF6 CF680A 30025 NE FUSELAGE CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) RT BULKHEAD OUTER CHORD LOCATED AT BS1809.5 CRACKED IN AREA OFLOWER TWO FASTENERS IN INSPECTION AREA 1. 2 L 7 2 4F 4 F RT A1NM E13NE 2001090500078 20010905 00078 CE 2001 9 5 AUS20010863 1 20010810 G 7931 PIPE CONT O470R CESSNA 182 182H 2072718 CE CONT O470 O470R 17026 SO MCAULY 2A34C 2A34C66 GL ENGINE OIL PRESS CORRODED W K NONE O OTHER IN INSP/MAINT 1 AU S 7167 (AUS) ENGINE OIL PRESSURE PIPE FROM FIREWALL TO GAUGE CORRODED IN AREAOF CONTACT WITH SOUNDPROOFING MATERIAL. PIPE IS MA NUFACTURED FROM ALUMINIUM. 1 H 7 1 3O 3 O NT 3A13 E273 5 C P3EA 2001091800002 20010918 00002 EU 2001 9 18 AUS20010864 1 20010813 G 6410 109813201107 BLADE AGUSTA A109 A119 0261102 EU PWA PT6T PT6T3 52045 EA TAIL ROTOR CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S 113 (AUS) TAIL ROTOR BLADE CRACKED ON INNER FACE. THE CRACK LENGTH RUNS FOR ALMOST THE FULL CHORD OF THE BLADE. FOUND DURING INSPECTION IAW AD/119/1 PT1. 1 G 7 2 3U 4 U H7EU E22EA 2001090500079 20010905 00079 NM 2001 9 5 AUS20010865 1 20010323 G 2920 59855 VALVE BOEING 767 767277 NM GE CF6 CF680A 30025 NE HYDRAULIC SYSTEM CRACKED W K NONE K FLUID LOSS DE DESCENT 1 AU S 49754 129 (AUS) RAM AIR TURBINE (RAT) MODULE CHECK VALVE CRACKED. LOSS OF HYDRAULIC FLUID. INVESTIGATION FOUND THAT THE HEX HEAD S EPARATEDFROM THE CHECK VALVE BODY DUE TO A FRACTURE BETWEEN THE UPPER O' RING GROOVE AND THE INTERNAL BODY THREAD RELIEF . 2 L 7 2 4F 4 F RT A1NM E13NE 2001091800004 20010918 00004 NM 2001 9 18 AUS20010867 1 20010313 G 5312 BULKHEAD BOEING 737 737377 NM FUSELAGE CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) FORWARD PRESSURE BULKHEAD LOCATED AT BS178 CRACKED IN TWO LOCATIONS. ONE CRACK FOUND IN LBL 5.7 LOCATED THROUGH IN SULATIONBLANKET HOLE. CRACK LENGTH 15.875MM (0.625IN). ONE CRACK FOUND IN RBL 17.1 LOCATED THROUGH INSULATION BLANKET HO LE. CRACK LENGTH15.875MM (0.625IN). FOUND DURING HIGH FREQUENCY EDDY CURRENTINSPECTION. 2 L 7 2 4F RT A16WE 2001091800005 20010918 00005 SO 2001 9 18 AUS20010868 1 20010716 G 2912 756164 SPRING PIPER PA23 PA23250 7102308 SO LYC O540 IO540K1A5 41532 EA HYDRAULIC FILTER MISSING W K NONE W INADEQUATE Q C IN INSP/MAINT 1 AU S (AUS) HYDRAULIC FILTER SPRING MISSING. 1 L 7 2 3O 3 O 1A10 1E4 2001091800006 20010918 00006 SO 2001 9 18 AUS20010869 1 20010716 G 3242 16405700 DISK CLEVELAND 16405700 PIPER PA23 PA23250 7102308 SO LYC O540 IO540K1A5 41532 EA BRAKE WORN W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) BRAKE DISCS WORN BELOW MINIMUM THICKNESS. BOTH DISCS ALSO EXHIBITED EVIDENCE OF RADIAL HEAT STRESS CRACKING. 1 L 7 2 3O 3 O 1A10 1E4 2001090500081 20010905 00081 SO 2001 9 5 AUS20010871 1 20010808 G 2910 PIPE PIPER PA31 PA31 7103102 SO LYC O540 TIO540A2C 41532 EA HARTZL HCE3Y HCE3YR2 GL HYDRAULIC SYSTEM FRACTURED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) HYDRAULIC PIPE FRACTURED. PIPE IS LOCATED IN RH NOSE AREA. 1 L 7 2 3O 3 O A20SO E14EA 5 C P33EA 2001091800007 20010918 00007 CE 2001 9 18 AUS20010872 1 20010814 G 3244 29X111010PR TIRE CESSNA 208 208B 2073701 CE PWA PT6 PT6A114A 52043 NE MCAULY 3AF34C 3GFR34C703 GL MLG FAULTY W O OTHER O OTHER LD LANDING 1 AU S (AUS) MAIN LANDING GEAR TIRE SUSPECT FAULTY. DURING LANDING THE TIRE EXHIBITED EXCESSIVE SIDEWARD DEFLECTION COUPLED WIT H MINIMAL CLEARANCE CAUSED THE INSIDE WALL OF THE TIRE TO CONTACT THE BRAKE ASSEMBLY. 1 H 7 1 3T 3 T A37CE E4EA 5 C P60GL 2001090500082 20010905 00082 CE 2001 9 5 AUS20010873 1 20010612 G 5343 244110010 PIVOT CESSNA 172 172RG 2072438 CE LYC O360 O360F1A6 41514 EA MCAULY 2D34C B2D34C220 GL LANDING GEAR ATT FAULTY W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) MAIN LANDING GEAR PIVOTS FAILED PROVISIONS OF CESSNA SERVICEBULLETIN SEB 90-1 REVISION3. 1 H 7 1 3O 3 O 3A17 E286 5 C P7EA 2001091800008 20010918 00008 NE 2001 9 18 AUS20010874 2 20010625 G 7250 2303713 SEAL LYC ALF502R5 BAC 146 146200A 1500266 EU LYC ALF502 ALF502R5 41580 NE TURBINE SECTION LEAKING W O OTHER O OTHER NR NOT REPORTED 1 AU S (AUS) NR 1 ENGINE NR 9 BEARING SEAL LEAKING. SUSPECT FUMES ENTERING CABIN AND CAUSING CREW PROBLEMS. 2 H 7 4 4F 4 F A49EU E6NE 2001090500083 20010905 00083 EA 2001 9 5 AUS20010875 2 20010813 G 8520 SL13884M06 BEARING LYC IO540E1B5 GULSTM 500 500S 0141107 SW LYC O540 IO540E1B5 41532 EA HARTZL HCC3Y HCC3YR2 NE RECIPROCATING EN DELAMINATED W K NONE O OTHER IN INSP/MAINT 1 AU S 118 L595548 (AUS) ENGINE FRONT MAIN BEARING DEFECTIVE. BEARING MATERIAL APPEARS TOBE DELAMINATED FROM BEARING SHELL. METAL CONTAMINA TION OF OIL SYSTEM. SUSPECT MANUFACTURING FAULT. 1 H 7 2 3O 3 O 6A1 1E4 5 C P25EA 2001091800009 20010918 00009 NE 2001 9 18 AUS20010876 2 20010726 G 7230 230318706 SEAL BAC 146 146200A 1500266 EU LYC ALF502 ALF502R5 41580 NE TURBINE ENGINE WORN W O OTHER B SMOKE/FUMES/ODORS/SPARKS DE DESCENT 1 AU S (AUS) NR 3 ENGINE LEAKING OIL FROM BLEED BAND AREA. FUMES ENTERING CABIN THROUGH AIR CONDITIONING SYSTEM. INVESTIGATION FOUND NO1 BEARINGSEAL AND FACE PLATE ASSEMBLY WORN. 2 H 7 4 4F 4 F A49EU E6NE 2001091800010 20010918 00010 EU 2001 9 18 AUS20010877 1 20010509 G 2120 HOSE GROB G115 G115C 1660303 EU LYC O360 O360A1F6 41514 EA HARTZL HCF2Y HCF2YR1 GL AIR DISTRIBUTION CHAFED W O OTHER B SMOKE/FUMES/ODORS/SPARKS CL CLIMB 1 AU S (AUS) AVIONICS COOLING SCAT HOSE CHAFED ON PRINTED CIRCUIT BOARD. HOSEINNER WIRE SHORT CIRCUITED CAUSING HOSE TO BURN. 1 L 7 1 3O 3 O NT A57EU E286 5 C P27EA 2001090500084 20010905 00084 SO 2001 9 5 AUS20010878 1 20010515 G 5753 12021940001 BRACKET EMB 120 EMB120 3260201 SO PWA 118 PW118A NE HAMSTD 14SF 14SF9 NE TRAILING EDGE FL BROKEN W K NONE F J FLT CONT AFFECTED WARNING INDICATION TO TAKEOFF 1 AU S (AUS) LH OUTBOARD FLAP SHROUD INBOARD ROLLER AND BRACKET BROKEN OFF CAUSING FLAP TRACK TO FOUL ON SHROUD. 2 L 7 2 4T 4 T RT A31SO E20NE 6 N P11NE 2001090500087 20010905 00087 EA 2001 9 5 AUS20010882 2 20010801 G 8520 CRANKCASE LYC TIO540J2BD PIPER PA31 PA31350 7103110 SO LYC O540 TIO540J2BD 41532 EA HARTZL HCE3Y HCE3YR2 GL RECIPROCATING EN DAMAGED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) ENGINE CRANKCASE DAMAGED. NO3 CYLINDER EXHAUST TAPPET BODY ALSO DAMAGED. 1 L 7 2 3O 3 O A20SO E14EA 5 C P33EA 2001091800013 20010918 00013 EA 2001 9 18 AUS20010885 2 20010813 G 7250 3010311 ENGINE DHAV DHC6 DHC6100 EA PWA PT6 PT6A20 52043 EA HARTZL HCB3T HCB3TN3 GL RIGHT MISREPAIRED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) FOLLOWING REPAIR FOR OVERTEMP AND FOD IN THE USA THE RT ENGINE WAS FITTED AND PREPARED FOR STARTING. THE ENGINE WA S WOUND OVER WITHOUT LIGHTING UP AND AN INTERNAL RUBBING NOISE WAS HEARD. THE ENGINE WAS PARTIALLY DISMANTLED AND INSPEC TION FOUND THE COMPRESSOR TURBINE RUBBING ON SEGMENTS IN SMALL EXIT DUCT.FURTHER STRIPPING AND INSPECTION FOUND ABRASIVE MATERIAL IN THE COMBUSTION CHAMBER. INSPECTION ALSO FOUND THAT THE POWER TURBINE LOCK WIRING WAS CARRIED OUT WITH STAIN LESS STEEL LOCKWIRE INSTEAD OF ICONEL LOCKWIRE. THE ITT PROBES WERE FOUND TO BE FINGER TIGHT AND INCORRECTLY SECURED. PE RSONNEL/MAINTENANCE ERROR. UNAPPROVED PART. 1 H 7 2 3T 3 T A9EA E4EA 6 C P15EA 2001091800014 20010918 00014 NM 2001 9 18 AUS20010886 1 20010117 G 3230 BACB10A554 BEARING BOEING 737 737377 NM CFMINT CFM56 CFM563B2 13802 EU NLG SEIZED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) NOSE LANDING GEAR MANUAL EXTENSION RELEASE MECHANISM TORQUE SHAFT BEARINGS SEIZED. 2 L 7 2 4F 4 F RT A16WE E21EU 2001091800015 20010918 00015 EU 2001 9 18 AUS20010888 1 20010805 G 2731 NB45C1867 ROD END BNORM BN2 BN2B20 1520302 EU LYC O540 IO540K1B5 41532 EA HARTZL HCC2Y HCC2YK2 GL ELEVATOR TAB WORN W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) ELEVATOR TRIM TAB DRIVE ROD END WORN. INSPECTION FOUND THE LEFT THREADED LOCKNUT STRIPPED. 1 H 7 2 3O 3 O A17EU 1E4 5 C P920 2001090500088 20010905 00088 CE 2001 9 5 AUS20010889 1 20010816 G 2910 581710219 PIPE CESSNA 404 404CESSNA 2075901 CE CONT O520 GTSIO520M 17032 SO MCAULY 3FF32 3FF32C501 GL HYDRAULIC SYSTEM CRACKED W K NONE K FLUID LOSS CR CRUISE 1 AU S (AUS) MAIN LANDING GEAR EXTENSION SYSTEM HYDRAULIC PIPE CRACKED INBEND. LOSS OF HYDRAULIC FLUID. 1 L 7 2 3O 3 O A25CE E7CE 5 C P45GL 2001090500089 20010905 00089 NE 2001 9 5 AUS20010890 2 20010811 G 7230 SEAL LYC ALF502R5 BAC 146 146200A 1500266 EU LYC ALF502 ALF502R5 41580 NE TURBINE ENGINE C LEAKING W K NONE B SMOKE/FUMES/ODORS/SPARKS TO TAKEOFF 1 AU S (AUS) NO1 ENGINE NO9 BEARING SEAL LEAKING. FUMES IN CABIN. 2 H 7 4 4F 4 F A49EU E6NE 2001090500090 20010905 00090 NE 2001 9 5 AUS20010892 2 20010817 G 7321 324476812 FCU PWA PT6A42 BEECH 200 200BEECH 1152920 CE PWA PT6 PT6A42 52043 NE HARTZL HCD4N3 HCD4N3A GL FUEL CONTROL/TUR UNSERVICEABLE W K NONE E VIBRATION/BUFFET CR CRUISE 1 AU S 3597 (AUS) LH ENGINE FUEL CONTROL UNIT FAULTY. 1 L 7 2 4T 4 T A24CE E4EA 5 C STC 2001091800017 20010918 00017 SW 2001 9 18 AUS20010893 1 20010712 G 6420 206011812001 TRUNNION BELL 206011810 BELL 206 206B3 1181506 SW ALLSN 250C 250C20B 03013 GL TAIL ROTOR HEAD CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S 2400 AAG00543 (AUS) TAIL ROTOR TRUNNION SUSPECT CRACKED. TRUNNION GAVE A POSITIVE CRACK INDICATION USING BOTH MPI AND FPI INSPECTIONS. 1 G 7 1 3U 3 U H2SW E4CE 2001091800018 20010918 00018 GL 2001 9 18 AUS20010894 2 20010614 G 7250 23063354 ENGINE DOUG 600N 600N 3027377 NM ALLSN 250C 250C47B GL NACELLE OVERHEATED W E ENGINE SHUTDOWN E M VIBRATION/BUFFET OVER TEMP NR NOT REPORTED 1 AU S (AUS) TURBINE OVER TEMPERATURE DURING ENGINE SHUTDOWN. 1 G 7 1 3U 3 U NC H3WE E1GL 2001090500091 20010905 00091 EU 2001 9 5 AUS20010895 1 20010601 G 7710 LINE RROYCE SPEY55515 FOKKER F28 F28MK1000 4990808 EU RROYCE SPEY SPEY55515 54521 EU POWER INDICATING LOOSE W K NONE E R VIBRATION/BUFFET PARTIAL RPM/PWR LOSS TO TAKEOFF 1 AU S (AUS) NO2 ENGINE THRUST FEED SENSE LINE TO GAUGE LOOSE. 2 L 7 2 4F 4 F RT A20EU E2EU 2001091800019 20010918 00019 EU 2001 9 18 AUS20010897 1 20010605 G 3232 AH533 ACTUATOR FOKKER F28 F28MK1000 4990808 EU RROYCE SPEY SPEY55515 54521 EU MLG DOOR CRACKED W O OTHER K J FLUID LOSS WARNING INDICATION LD LANDING 1 AU S 6320 (AUS) LT MAIN LANDING GEAR DOOR AFT ACTUATOR CRACKED AND LEAKING. LOSS OF HYDRAULIC FLUID. 2 L 7 2 4F 4 F RT A20EU E2EU 2001090500092 20010905 00092 EU 2001 9 5 AUS20010898 1 20010621 G 3230 LEVER FOKKER F28 F28MK1000 4990808 EU RROYCE SPEY SPEY55515 54521 EU LANDING GEAR RET STUCK W K NONE O F OTHER FLT CONT AFFECTED TO TAKEOFF 1 AU S (AUS) LANDING GEAR RETRACTION LEVER STUCK IN DOWN POSITION. CIRCUIT BREAKER L8 POPPED. 2 L 7 2 4F 4 F RT A20EU E2EU 2001091800020 20010918 00020 EU 2001 9 18 AUS20010899 1 20010726 G 7931 642514172 TRANSMITTER AMD FALC50 FALCON900 2700160 EU GARRTT TFE731 TFE7315R 01518 WP ENGINE OIL PRESS FAILED W O OTHER E K VIBRATION/BUFFET FLUID LOSS NR NOT REPORTED 1 AU S 266 (AUS) NR 3 ENGINE OIL PRESSURE TRANSMITTER FAULTY. 2 L 7 3 4F 4 F RT A46EU E6WE 2001091800023 20010918 00023 EU 2001 9 18 AUS20010902 2 20010627 G 7250 BLADE BOEING 737 737400 NM CFMINT CFM56 CFM563C 13802 EU TURBINE SECTION CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S 20631 (AUS) NR 1 ENGINE HIGH PRESSURE TURBINE BLADE CRACKED FROM HOLE. FOUND DURING BOROSCOPE INSPECTION IAW EI 737-72-525. 2 L 7 2 4F 4 F RT A16WE E21EU 2001091900166 20010919 00166 SO 2001 9 19 AUS20010903 1 20010515 G 2710 CONTROL UNIT PIPER PA31 PA31350 7103110 SO LYC O540 TIO540J2BD 41532 EA HARTZL HCE3Y HCE3YR2 GL AILERON LOOSE W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) AILERON CONTROL SYSTEM HAD EXCESSIVE PLAY. INVESTIGATION FOUNDUNIVERSAL PNO 46203-02 WORN COMPLETELY THROUGH BUSH PNO 453-824 AND INTO BRACKET PNO 29197-02 MOUNTED ON FORWARD BULKHEAD. 1 L 7 2 3O 3 O A20SO E14EA 5 C P33EA 2001090500093 20010905 00093 EA 2001 9 5 AUS20010904 2 20010814 G 8520 L1959448 STUD LYC IO540E1B5 GULSTM 500 500S 0141107 SW LYC O540 IO540E1B5 41532 EA HARTZL HCA3V HCA3VK2 GL RECIPROCATING EN SHEARED W K NONE O K OTHER FLUID LOSS IN INSP/MAINT 1 AU S 1340 L1959448 (AUS) LH ENGINE NO4 CYLINDER HOLDDOWN STUDS (3OFF) SHEARED. FOLLOWING REMOVAL OF THE CYLINDER THE CRANKCASE WAS FOUND TO BE CRACKED THROUGH THE AREA OF THE HOLDDOWN STUDS. 1 H 7 2 3O 3 O 6A1 1E4 5 C P6EA 2001090500094 20010905 00094 CE 2001 9 5 AUS20010908 1 20010712 G 2711 AN36A BOLT BEECH 58 58 1152740 CE CONT O520 IO520C 17032 SO HARTZL HCJ3Y PHCJ3YF2 GL AILERON TAB CONT WORN W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) ELEVATOR TRIM TAB ACTUATOR TO TRIM TAB ROD ATTACHMENT BOLTS WORN. FOUND DURING INSPECTION IAW AD/B55/59. 1 L 7 2 3O 3 O 3A16 E5CE 5 C P36EA 2001090500099 20010905 00099 WP 2001 9 5 AUS20010919 2 20010731 G 7314 8974007 PUMP GARRTT TPE33112UA BAG JETSTM JETSTM3201 1500217 EU GARRTT TPE331 TPE33112UA 01514 WP MCAULY 4HFR34 4HFR34C653 NE ENGINE FUEL PUMP UNSERVICEABLE W K NONE O OTHER IN INSP/MAINT 1 AU S 4306 P6012 (AUS) ENGINE FUEL PUMP HOUSING CRACKED IN AREA OF CONCENTRIC SHAFTSUPPORT. 2 L 7 2 4T 4 T RT A56EU E4WE 6 C 3PNE 2001090500101 20010905 00101 NE 2001 9 5 AUS20010921 2 20010628 G 7230 PCE93406 COMPRESSOR PWA PT6A42 BEECH 200 200BEECH 1152920 CE PWA PT6 PT6A42 52043 NE HARTZL HCB3T HCB3TN3 GL TURBINE ENGINE C FOD W K NONE E B VIBRATION/BUFFET SMOKE/FUMES/ODORS/SPARKS TO TAKEOFF 1 AU S PCE93406 (AUS) ENGINE COMPRESSOR EXTENSIVELY DAMAGED BY FOD. INVESTIGATION FOUND A DAMAGED WASHER IN THE COWL. SUSPECT CAME FROM BOLT SECURING COMPRESSOR SCREEN REMOVED DURING MAINTENANCE PRIOR TO THISFLIGHT. PERSONNEL/MAINTENANCE ERROR. 1 L 7 2 4T 4 T A24CE E4EA 6 C P15EA 2001091900180 20010919 00180 CE 2001 9 19 AUS20010923 1 20010814 G 3244 29X111010PR TIRE CESSNA 208 208B 2073701 CE PWA PT6 PT6A114A 52043 NE MCAULY 3AF34C 3GFR34C703 GL MLG FAULTY W O OTHER O OTHER LD LANDING 1 AU S (AUS) MAIN LANDING GEAR TYRE HAD EXCESSIVE SIDEWARDS DEFLECTION DURING LANDING CAUSING THE TYRE TO CONTACT THE BRAKE ASS EMBLY. TYRE SIZE 29X11.0X10 10PLY. 1 H 7 1 3T 3 T A37CE E4EA 5 C P60GL 2001090500103 20010905 00103 WP 2001 9 5 AUS20010925 1 20010824 G 6520 369A54083 SHAFT HUGHES 369A5400 HUGHES 369 369HS 4470728 WP ALLSN 250C 250C20 03013 GL TAIL ROTOR GEARB DISTORTED W K NONE O OTHER IN INSP/MAINT 1 AU S 344 B222 (AUS) TAIL ROTOR GEARBOX OUTPUT SHAFT BEARINGS BREAKING UP AND SHAFTRUNOUT EXCESSIVE. SHAFT RUNOUT APPROXIMATELY 0.457MM (0.018IN). MAXIMUM RUNOUT 0.0254MM (0.001IN). 1 G 7 1 3U 3 U H3WE E4CE 2001091900185 20010919 00185 2001 9 19 AUS20010927 4 20010205 G 2565 D30665101MOD SLIDE AIRBUS 320 A320* EU CFMINT CFM56 CFM565A1 NE CABIN FAILED W K NONE L NO TEST IN INSP/MAINT 1 AU S 5003 (AUS) SLIDERAFT SEAL FAILED DURING INFLATION TEST. SEAL SEPARATION OCCURRED IN THE UPPER CHAMBER AT THE INTERSECTION OF THE UPPERAND SIDE TUBES. LENGTH OF TEAR 304.8MM (12IN). SLIDE HAD BEEN SENT TO WORKSHOP FOR REPAIR FOLLOWING AN INCIDENT WITH MOBILE STAIRS. 2 L 7 2 4F 4 F RT A46NM E29NE 2001090500105 20010905 00105 EA 2001 9 5 AUS20010930 2 20010822 G 7322 30804 FLOAT FACET MA4SPA CESSNA 172 172M 2072418 CE LYC O320 O320E2D 41508 EA MCAULY 1C160 1C160DTM GL FUEL CONTROL/REC DAMAGED W K NONE O OTHER IN INSP/MAINT 1 AU S 163 BL198636 (AUS) CARBURETTOR FLOAT CONTAMINATED WITH FUEL CAUSING CARBURETTOR TO FLOOD. 1 H 7 1 3O 3 O NT 3A12 E274 5 N P910 2001090500106 20010905 00106 GL 2001 9 5 AUS20010932 1 20010726 G 8120 3BT5EE10J2 TURBOCHARGER LYC HIO360E1AD ENSTRM F28 F28C 3300407 GL LYC O360 HIO360E1AD 41514 EA EXHAUST TURBOCHA FOD W K NONE O OTHER TO TAKEOFF 1 AU S (AUS) ENGINE TURBOCHARGER INGESTED A NUT FROM THE AIR STATIC TUBE LOCATED INSIDE THE AIR CLEANER. FOD. 1 G 7 1 3O 3 O H1CE 1E10 2001092000029 20010920 00029 CE 2001 9 20 AUS20010934 1 20010823 G 5531 07310292 SPAR CESSNA 185 185F 2072820 CE CONT O470 O470R 17026 SO VERTICAL STAB CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S PN073100149 (AUS) VERTICAL STABILISER REAR SPAR ASSEMBLY CRACKED IN TWO AREAS ADJACENT TO THE FUSELAGE BULKHEAD ATTACHMENT POINT. 1 H 7 1 3O 3 O 3A24 E273 2001090500107 20010905 00107 CE 2001 9 5 AUS20010935 1 20010810 G 3230 HMX5FG ROD END CESSNA 310 310R 2074245 CE CONT O520 IO520M 17032 SO MCAULY 3AF32C 3AF32C87 GL LANDING GEAR RET BROKEN W K NONE O E OTHER VIBRATION/BUFFET TO TAKEOFF 1 AU S (AUS) LH LANDING GEAR INBOARD RETRACTION ROD OUTBOARD RODEND BALL SOCKET FRACTURED. 1 L 7 2 3O 3 O 3A10 E5CE 5 C P22EA 2001090500108 20010905 00108 SO 2001 9 5 AUS20010936 2 20010827 G 8520 CRANKSHAFT CONT IO520F CESSNA 206 U206G 2073356 CE CONT O520 IO520F 17032 SO MCAULY 3A32C D3A32C90 GL RECIPROCATING EN BROKEN W K NONE E VIBRATION/BUFFET NR NOT REPORTED 1 AU S (AUS) CRANKSHAFT BROKEN AT NO4 MAIN BEARING JOURNAL. 1 H 7 1 3O 3 O A4CE E5CE 5 C P21EA 2001091900194 20010919 00194 SO 2001 9 19 AUS20010938 2 20010214 G 8530 PISTON CESSNA 172 R172K 2072431 CE CONT O360 IO360K 17025 SO MCAULY 2A34C 2A34C203 GL ENGINE DAMAGED W O OTHER E K VIBRATION/BUFFET FLUID LOSS CR CRUISE 1 AU S (AUS) NR 2 CYLINDER PISTON HOLED IN AREA OF RING GROOVES. EXCESSIVE CRANKCASE PRESSURE VENTED OIL THROUGH THE BREATHER. LOSS OF OIL PRESSURE CAUSED NR 1 CYLINDER CONNECTING ROD BIGEND FAILURE. INVESTIGATION FOUND A PIECE OF BROKEN PISTON RI NG HAD BEEN WORKING IN THE RING GROOVE CAUSING FAILURE OF THE LAND. 1 H 7 1 3O 3 O 3A17 E1CE 5 C P3EA 2001091900197 20010919 00197 SW 2001 9 19 AUS20010939 1 20010827 G 5620 412670101 WINDOW BELL 412 412 1182202 SW PWA PT6T PT6T3 52045 EA COCKPIT FAILED W O OTHER E VIBRATION/BUFFET DE DESCENT 1 AU S (AUS) LT SLIDING DOOR REAR WINDOW FAILED. MINOR DAMAGE TO HF RADIO ANTENNA CONNECTOR AND HORIZONTAL STABILISER. 1 G 7 2 4U 4 U H4SW E22EA 2001091900203 20010919 00203 NM 2001 9 19 AUS20010941 1 20010401 G 5310 STRUCTURE BOEING 737 737377 NM FUSELAGE CORRODED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) CORROSION CONTROL INSPECTION FOUND AREAS OF LEVEL 2 CORROSION.FOUND DURING INSPECTION IAW AD/B737/52 AMDT2. 2 L 7 2 4F RT A16WE 2001091900204 20010919 00204 NM 2001 9 19 AUS20010942 1 20010401 G 5310 STRUCTURE BOEING 737 73733A 1384673 NM FUSELAGE CORRODED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) CORROSION CONTROL INSPECTION FOUND AREAS OF LEVEL 2 CORROSION.FOUND DURING INSPECTION IAW AD/B737/52 AMDT2. 2 L 7 2 4F RT A16WE 2001090500109 20010905 00109 SO 2001 9 5 AUS20010943 2 20010820 G 8520 634503 BEARING CONT GTSIO520H CESSNA 421 421B 2076014 CE CONT O520 GTSIO520H 17032 SO MCAULY 3AF34C 3AF34C92 GL RECIPROCATING EN FAILED W K NONE O OTHER IN INSP/MAINT 1 AU S 600 235015R (AUS) ENGINE OIL FILTER CONTAMINATED WITH METAL. INVESTIGATION FOUNDNO1 AND NO2 BEARINGS HAD COMPLETELY FAILED WITH THE BEARING SHELLS BROKEN IN HALF. TRANSVERSE CRACKS WERE FOUND AROUND THECRANKSHAFT NO2 MAIN JOURNAL WITH CATASTROPHIC FAIL URE IMMINENT. 1 L 7 2 3O 3 O A7CE E7CE 5 C P22EA 2001091900237 20010919 00237 CE 2001 9 19 AUS20010944 1 20010824 G 3260 727725 CIRCUIT BREAKER BEECH 200 B200C 1152924 CE PWA PT6 PT6A42 52043 NE MLG INDICATOR FAULTY W O OTHER N FALSE WARNING DE DESCENT 1 AU S (AUS) LANDING GEAR INDICATION SYSTEM CIRCUIT BREAKER HAD HIGH RESISTANCE. 1 L 7 2 4T 4 T A24CE E4EA 2001101500028 20011015 00028 CE 2001 10 15 AUS20010947 1 20010824 G 7602 MC98620661 LEVER CONT IO520F CESSNA 206 U206G 2073356 CE CONT O520 IO520F 17032 SO MCAULY 3A32C D3A32C90 GL MIXTURE CONTROL FAILED W K NONE O OTHER CL CLIMB 1 AU S (AUS) MIXTURE CONTROL VERNIER FAILED. CENTRE KNOB AND SHAFT SEPARATED FROM MIXTURE CONTROL. 1 H 7 1 3O 3 O A4CE E5CE 5 C P21EA 2002010800002 20020108 00002 GL 2002 1 8 AUS20010948 1 20010825 G 3211 AN531A BOLT AMTR MK1 MK1 05620JY GL MLG BROKEN W O OTHER O OTHER LD LANDING 1 AU S (AUS) LANDING GEAR REAR MOUNT BOLT FAILED DURING HEAVY LANDING. MINOR DAMAGE TO REAR OF SPAR. 1 H 7 1 3O NC EXPA1H71 2001101500030 20011015 00030 EA 2001 10 15 AUS20010952 2 20010829 G 7310 3011849 PIPE PWA PT6A34 EMB 110 EMB110P2 3260124 SO PWA PT6 PT6A34 52043 EA HARTZL HCB3T HCB3TN3 GL ENGINE FUEL DIST CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) PIPE LOCATED BETWEEN FCU AND START CONTROL VALVE CRACKED AT FITTING. 1 L 7 2 4T 4 T A21SO E4EA 6 C P15EA 2002010800006 20020108 00006 CE 2002 1 8 AUS20010955 1 20010823 G 2612 473275 DETECTOR BEECH 200 B200C 1152924 CE PWA PT6 PT6A42 52043 NE FIRE DETECTION UNSERVICEABLE W O OTHER N O FALSE WARNING OTHER CR CRUISE 1 AU S (AUS) FIRE DETECTOR FAULTY. 1 L 7 2 4T 4 T A24CE E4EA 2001101500031 20011015 00031 NM 2001 10 15 AUS20010956 1 20010904 G 3520 28003101 LANYARD BOEING 767 767238 NM PWA JT9 JT9D7R4E 52054 NE PASSENGER OXYGEN MISSING W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) OXYGEN MASKS LOCATED AT SEATS 26J/K HAD MISSING LANYARDS (3OFF). 2 L 7 2 4F 4 F RT A1NM E3NE 2001101500033 20011015 00033 EU 2001 10 15 AUS20010960 1 20010820 G 5720 BRACKET PARTEN P68 PARTEN P68 P68B EU LYC O360 IO360A1B6 41514 EA HARTZL HCC2Y HCC2YR2 GL WING, MISCELLANE CORRODED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) LH WING LEADING EDGE TOP FORWARD ATTACHMENT BRACKET CORRODED. 1 H 7 2 3O 3 O A31EU 1E10 5 C P920 2001101500034 20011015 00034 GL 2001 10 15 AUS20010962 1 20010822 G 3710 215CC PUMP PAC CT4 CT4B GL CONT O360 IO360HB 17025 SO HARTZL HCC2Y BHCC2YF1 GL VACUUM DISTRIBUT FAILED W K NONE I FLT. ATTITUDE INST. NR NOT REPORTED 1 AU S 11609 (AUS) VACUUM PUMP SEIZED AND DRIVE SHAFT SHEARED. 1 L 7 1 3O 3 O RT A9PC E1CE 5 C P920 2002010800009 20020108 00009 CE 2002 1 8 AUS20010963 1 20010828 G 2434 SEAL CESSNA 402 402C 207590R CE CONT O520 TSIO520VB 17040 SO MCAULY 3AF32C 3AF32C93 GL DC GENERATOR-ALT LEAKING W K NONE K FLUID LOSS IN INSP/MAINT 1 AU S 9 (AUS) LT ENGINE DRIVEN ALTERNATOR DRIVE SEAL LEAKING. INVESTIGATION FOUND THAT THE SEAL WAS INCORRECTLY FITTED. 1 L 7 2 3O 3 O A7CE E8CE 5 C P22EA 2001101500035 20011015 00035 CE 2001 10 15 AUS20010964 1 20010903 G 5730 552212126 SPLICE CESSNA 550 CESSNA 500 550 2076604 CE PWA JT15 JT15D4 52112 NE WING, PLATES/SKI CORRODED W K NONE O OTHER IN INSP/MAINT 1 AU S 550054 (AUS) RH WING SKIN SPLICE CORRODED. AREAS OF SPLICE ASSEMBLY DISBONDED. 1 L 7 2 4F 4 F A22CE E1NE 2002010800010 20020108 00010 NM 2002 1 8 AUS20010965 1 20010904 G 3242 AS11506K0346 HOSE BOEING 737 737400 138449A NM CFMINT CFM56 CFM563B1US GL BRAKE FAILED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) NR 2 BRAKE HOSE FRACTURED AND LEAKING. 2 L 7 2 4F 4 F RT A16WE E2GL 2002010800015 20020108 00015 NE 2002 1 8 AUS20010970 2 20010905 G 7230 MS9390290 PIN LYC ALF502 ALF502R3A 41580 NE ENGINE MISINSTALLED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) ENGINE FAN DISC RETAINING NUT LOCK CUP WASHER LOCKING PINS FLUSHWITH SHAFT MAKING LOCKING MECHANISM NON FUNCTIONAL . THE FAN HAD BEEN REMOVED TO SERVICE ANOTHER ENGINE. 4 F E6NE 2001101500036 20011015 00036 CE 2001 10 15 AUS20010971 1 20010822 G 5610 10138402521 WINDSHIELD BEECH 200 200BEECH 1152920 CE PWA PT6 PT6A42 52043 NE MCAULY 4HFR34 4HFR34C754 NE FLIGHT COMPARTME FAILED W K NONE O OTHER CL CLIMB 1 AU S (AUS) LH WINDSHIELD SHATTERED. 1 L 7 2 4T 4 T A24CE E4EA 6 C 3PNE 2002010800016 20020108 00016 NE 2002 1 8 AUS20010972 2 20010829 G 7260 PLE94397 GEARBOX BEECH 200 B200C 1152924 CE PWA PT6 PT6A42 52043 NE HARTZL HCD4N3 HCD4N3A GL ENGINE ACCESSORY DISCONNECTED W O OTHER E J VIBRATION/BUFFET WARNING INDICATION CL CLIMB 1 AU S (AUS) ENGINE ACCESSORY GEARBOX DECOUPLED PREVENTING ACCESSORIES FROM OPERATING. 1 L 7 2 4T 4 T A24CE E4EA 5 C STC 2001101500037 20011015 00037 SO 2001 10 15 AUS20010973 2 20010820 G 8520 634503 BEARING CONT GTSIO520M CESSNA 404 404CESSNA 2075901 CE CONT O520 GTSIO520M 17032 SO MCAULY 3FF32 3FF32C501 GL RECIPROCATING EN BROKEN W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) ENGINE MAIN BEARING BROKEN INTO SEVERAL PIECES. METAL CONTAMINATION OF OIL SYSTEM. BEARING WAS A GENUINE CONTINENT ALITEM. 1 L 7 2 3O 3 O A25CE E7CE 5 C P45GL 2001101500038 20011015 00038 SO 2001 10 15 AUS20010974 2 20010820 G 8520 634503 BEARING CONT GTSIO520M CESSNA 404 404CESSNA 2075901 CE CONT O520 GTSIO520M 17032 SO MCAULY 3FF32 3FF32C501 GL RECIPROCATING EN BROKEN W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) ENGINE MAIN BEARING BROKEN INTO THREE PIECES. METAL CONTAMINATION OF ENGINE. 1 L 7 2 3O 3 O A25CE E7CE 5 C P45GL 2002010800018 20020108 00018 EU 2002 1 8 AUS20010977 1 20010807 G 2913 2912 MOTOR PILATS PC12 PC12 7090550 EU PWA PT6 PT6A67B 52043 NE HARTZL HCE4A HCE4A3D GL HYDRAULIC PUMP DIRTY W O OTHER O OTHER DE DESCENT 1 AU S (AUS) LANDING GEAR HYDRAULIC POWER PACK ELECTRIC MOTOR FAULTY.INVESTIGATION FOUND LIGHT CORROSION IN COMMUTATOR END OF M OTOR. THE MOTOR WAS ALSO DIRTY WITH THE BRUSHES STICKING IN THE BRUSH HOLDERS. HYDRAULIC RETURN FILTER DIRTY. 1 L 7 1 3T 4 T RT A78EU E26NE 5 C P210NE 2001101500040 20011015 00040 CE 2001 10 15 AUS20010979 1 20010901 G 7602 MC98620661 SHAFT CONT IO520F CESSNA 206 U206G 2073356 CE CONT O520 IO520F 17032 SO MCAULY 3A32C D3A32C90 GL MIXTURE CONTROL SEPARATED W K NONE O OTHER CR CRUISE 1 AU S (AUS) MIXTURE CONTROL VERNIER FAILED CAUSING CENTRE KNOB AND 177.8MM(7IN) OF SHAFT TO SEPARATE FROM MIXTURE CONTROL. 1 H 7 1 3O 3 O A4CE E5CE 5 C P21EA 2002010800021 20020108 00021 NE 2002 1 8 AUS20010981 2 20010903 G 7240 9560151480 SWIVEL SKRSKY S76 S76A 8143006 NE TMECA ARRIEL ARRIEL1S 60030 NE COMBUST CHAMBER LOOSE W O OTHER E B VIBRATION/BUFFET SMOKE/FUMES/ODORS/SPARKS NR NOT REPORTED 1 AU S (AUS) NR 1 ENGINE COMBUSTION CHAMBER P2 AIR TAP SWIVEL UNION ASSEMBLY CONE LOOSE. 1 G 7 2 3U 3 U H1NE E19EU 2001101500042 20011015 00042 EA 2001 10 15 AUS20010986 2 20010829 G 7414 10349234 GEAR CONT BL3493704 PIPER PA32 PA32300 7103212 SO LYC O540 IO540K1G5 41532 EA HARTZL HCC2Y HCC2YK1 GL MAGNETO/DISTRIBU BROKEN W K NONE E VIBRATION/BUFFET NR NOT REPORTED 1 AU S 727 A250007FR (AUS) LH MAGNETO FAULTY. INSPECTION FOUND THAT ONE OF THE COILRETAINING WEDGES PNO 10-349219 WAS ADRIFT INSIDE THE CASE. THEDISTRIBUTOR GEAR PNO 10-349234 WAS FOUND TO HAVE THREE TEETHMISSING. SUSPECT WEDGE JAMMED GEAR CAUSING TEETH TO STRI P AND ALLOW THE INTERNAL TIMING TO CHANGE. 1 L 7 1 3O 3 O A3SO 1E4 5 C P920 2001101500044 20011015 00044 CE 2001 10 15 AUS20010990 1 20010904 G 7810 K9695000277 EXHAUST PIPE CONT IO520C BEECH 55 95C55 1152708 CE CONT O520 IO520C 17032 SO MCAULY 3AF32C 3AF32C75 GL ENGINE COLLECTOR FAULTY W K NONE I FLT. ATTITUDE INST. NR NOT REPORTED 1 AU S (AUS) LH ENGINE EXHAUST PIPE HELD ON BY REAR CLAMP ONLY AND TOUCHINGFIREWALL. HEAT AFFECTED PLASTIC JOINER TUBE FOR PITO T SYSTEMLOCATED BEHIND FIREWALL. 1 L 7 2 3O 3 O 3A16 E5CE 5 C P22EA 2002010800025 20020108 00025 CE 2002 1 8 AUS20010991 1 20010829 G 5220 DOOR CESSNA 310 310R 2074245 CE CONT O520 IO520M 17032 SO MCAULY 3AF32C 3AF32C87 GL EMERGENCY EXIT SEPARATED W A UNSCHED LANDING D INFLIGHT SEPARATION CR CRUISE 1 AU S (AUS) EMERGENCY EXIT SEPARATED DURING FLIGHT. NO DAMAGE TO AIRCRAFT. 1 L 7 2 3O 3 O 3A10 E5CE 5 C P22EA 2001101500045 20011015 00045 GL 2001 10 15 AUS20010992 1 20010803 G 7820 MUFFLER CONT IO360HB PAC CT4 CT4B GL CONT O360 IO360HB 17025 SO HARTZL HCC2Y BHCC2YF1 GL ENGINE NOISE SUP CRACKED W K NONE O OTHER CR CRUISE 1 AU S (AUS) RH MUFFLER CRACKED. CARBON MONOXIDE FUMES IN COCKPIT. 1 L 7 1 3O 3 O RT A9PC E1CE 5 C P920 2001101500046 20011015 00046 GL 2001 10 15 AUS20010993 1 20010908 G 5720 TAPE PAC CT4 CT4B GL CONT O360 IO360HB 17025 SO HARTZL HCC2Y BHCC2YF1 GL WING, MISCELLANE SEPARATED W K NONE O OTHER CR CRUISE 1 AU S (AUS) LH WING ROOT SEALING TAPE SEPARATED. CARBON MONOXIDE FUMESENTERED COCKPIT. 1 L 7 1 3O 3 O RT A9PC E1CE 5 C P920 2001101500047 20011015 00047 CE 2001 10 15 AUS20010994 1 20010831 G 3213 50450182 WASHER CESSNA 402 402CESSNA 207590K CE CONT O520 TSIO520E 17040 SO MCAULY 3AF32C 3AF32C87 GL MAIN LANDING GEA MISSING W K NONE O OTHER LD LANDING 1 AU S (AUS) LH MAIN LANDING GEAR TORQUE LINK CENTRE PIVOT WASHER NOT FITTED.TORQUE LINKS SEPARATED ALLOWING AIRCRAFT TO GROUND LOOP. 1 L 7 2 3O 3 O A7CE E8CE 5 C P22EA 2001101500048 20011015 00048 CE 2001 10 15 AUS20010997 1 20010915 G 7120 5854002 MOUNT CONT GTSIO520M CESSNA 404 404CESSNA 2075901 CE CONT O520 GTSIO520M 17032 SO MCAULY 3FF32 3FF32C501 GL ENGINE MOUNT SEC CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) ENGINE MOUNT CROSS MEMBER CRACKED. 1 L 7 2 3O 3 O A25CE E7CE 5 C P45GL 2001101500049 20011015 00049 2001 10 15 AUS20010998 4 20010906 G 2565 D31591478 SLIDE ESCAPE SLIDE FAULTY W K NONE O J OTHER WARNING INDICATION IN INSP/MAINT 1 AU S 225 2321 (AUS) ESCAPE SLIDE TEST LIGHTS FAILED TO ILLUMINATE DURING TEST.INSPECTION FOUND SWITCH PIN LANYARD TOO LONG. 2002010800028 20020108 00028 CE 2002 1 8 AUS20010999 1 20010605 G 2810 33400512 FUEL TANK BEECH 95 95B55 1152729 CE CONT O470 IO470L 17026 SO FUSELAGE DETERIORATED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) FUEL TANKS DETERIORATED. FUEL SYSTEM AND FUEL FILTERS CONTAMINATED WITH FOAM MATERIAL. 1 L 7 2 3O 3 O RT 3A16 3E1 2001101500050 20011015 00050 EU 2001 10 15 AUS20011004 1 20010918 G 2913 99101371 PUMP REIMS 406 F406 EU PWA PT6 PT6A112 52043 NE MCAULY 3G34C7 3GFR34C701 GL HYDRAULIC PUMP, FAILED W K NONE K FLUID LOSS CL CLIMB 1 AU S 1107 (AUS) HYDRAULIC PUMP FAULTY. INVESTIGATION FOUND THE PUMP CIRCLIP GROOVE WORN ALLOWING THE CIRCLIP TO SEPARATE AND THE S PLINE ADAPTER PNO 24100-646 TO DISENGAGE FROM THE ENGINE DRIVE. 1 L 7 2 3T 3 T RT A54EU E4EA 5 C P60GL 2002010800033 20020108 00033 CE 2002 1 8 AUS20011006 1 20010912 G 3260 S13771 SWITCH CESSNA 210 210N 2073453 CE CONT O520 IO520L 17032 SO MCAULY D3A34 D3A34C404 GL MLG DOWNLOCK FAULTY W O OTHER P NO WARNING INDICATION DE DESCENT 1 AU S (AUS) RT MAIN LANDING GEAR DOWNLOCK MICROSWITCH WIRE BROKEN FROM SWITCH BODY. 1 H 7 1 3O 3 O 3A21 E5CE 5 C P47GL 2001101500051 20011015 00051 CE 2001 10 15 AUS20011007 1 20010830 G 3230 MS16562130 PIN CESSNA 340 340CESSNA 2076404 CE CONT O520 TSIO520K 17040 SO MCAULY 3AF32C 3AF32C87 GL LANDING GEAR RET SHEARED W K NONE O OTHER LD LANDING 1 AU S (AUS) LANDING GEAR UPPER MANUAL EMERGENCY EXTENSION SYSTEM INTERCONNECT SHAFT SPROCKET ROLL PIN SHEARED. 1 L 7 2 3O 3 O 3A25 E8CE 5 C P22EA 2001101500052 20011015 00052 SO 2001 10 15 AUS20011008 2 20010916 G 8597 WIRE CONT IO520F CESSNA 206 U206G 2073356 CE CONT O520 IO520F 17032 SO MCAULY 3A32C D3A32C90 GL RECIPROCATING EN WORN W K NONE E A VIBRATION/BUFFET FLAME/FIRE CR CRUISE 1 AU S (AUS) ELECTRICAL WIRES (2OFF) LOCATED IN ENGINE COMPARTMENT CHAFING ONSOLID FUEL LINE. WIRES ARCED AND BLEW A SMALL HOLE IN THE FUELLINE RESULTING IN A FIRE IN THE ENGINE COMPARTMENT. INADEQUATEMAINTENANCE. PERSONNEL/MAINTENANCE ERROR. 1 H 7 1 3O 3 O A4CE E5CE 5 C P21EA 2001101500053 20011015 00053 EA 2001 10 15 AUS20011009 2 20010915 G 8520 CRANKCASE LYC TIO540J2BD PIPER PA31 PA31350 7103110 SO LYC O540 TIO540J2BD 41532 EA HARTZL HCE3Y HCE3YR2 GL RECIPROCATING EN CRACKED W K NONE O E B OTHER VIBRATION/BUFFET SMOKE/FUMES/ODORS/SPARKS IN INSP/MAINT 1 AU S (AUS) RH ENGINE NO4 CYLINDER HOLDDOWN STUDS (2OFF) BROKEN. CRANKCASECRACKED VERTICALLY UP FROM TOP STUD. CRACK LENGTH 76 .2MM (3IN). 1 L 7 2 3O 3 O A20SO E14EA 5 C P33EA 2002010800034 20020108 00034 SO 2002 1 8 AUS20011010 2 20010910 G 7414 K3823 DISTRIBUTOR CESSNA 206 U206F 2073333 CE CONT O520 IO520F 17032 SO MCAULY 3A32C D3A32C90 GL MAGNETO BURNED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) MAGNETO DISTRIBUTOR BLOCK BADLY BURNT DUE TO TRACKING FROM DISTRIBUTOR WHEEL SPRING TO MAGNETO HOUSING. 1 H 7 1 3O 3 O A4CE E5CE 5 C P21EA 2002010800035 20020108 00035 EA 2002 1 8 AUS20011011 2 20010819 G 7414 K3823 DISTRIBUTOR LYC O540 IO540K1A5 41532 EA HARTZL HCC2Y HCC2YR1 GL MAGNETO BURNED W O OTHER E VIBRATION/BUFFET LD LANDING 1 AU S (AUS) MAGNETO DISTRIBUTOR BLOCK BADLY BURNT BY TRACKING FROM SPRING INDISTRIBUTOR WHEEL TO MAGNETO HOUSING. 3 O 1E4 5 C P920 2001101500056 20011015 00056 SW 2001 10 15 AUS20011017 1 20010921 G 5730 PLATE GULSTM 500 500S 0141107 SW LYC O540 IO540E1A5 41532 EA HARTZL HCA3X HCA3XK2 GL WING, PLATES/SKI CORRODED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) EXTERNAL SPAR CAP SUPPORT PLATE RH SIDE CORRODED IN AREA OF JOINT BETWEEN TWO PLATES. EVIDENCE OF CORROSION IN SIM ILAR AREA ON LH SIDE. 1 H 7 2 3O 3 O 6A1 1E4 5 C P913 2001101500057 20011015 00057 SO 2001 10 15 AUS20011018 1 20010922 G 2140 461731 REGULATOR PIPER PA31 PA31350 7103110 SO LYC O540 TIO540J2BD 41532 EA HARTZL HCE3Y HCE3YR2 GL HEATING SYSTEM LEAKING W K NONE B SMOKE/FUMES/ODORS/SPARKS NR NOT REPORTED 1 AU S (AUS) FUEL PRESSURE REGULATOR DIAPHRAGM LEAKING WHEN CABIN HEATER TURNS OFF. 1 L 7 2 3O 3 O A20SO E14EA 5 C P33EA 2002010800040 20020108 00040 GL 2002 1 8 AUS20011019 1 20010918 G 2821 FILTER NAMER NA260 T28* GL WRIGHT R1820 R1820* 67020 EA HAMSTD 43D 43D50 NE FUEL SYSTEM CONTAMINATED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) AIRCRAFT FUEL FILTER CONTAMINATED. CONTAMINATION ALSO FOUND IN CARBURETTOR FUEL FILTER. 1 L 7 1 4R 4 R 1A18 5E10 6 C P8879 2002010800044 20020108 00044 CE 2002 1 8 AUS20011022 1 20010914 G 5751 NAS2219 SCREW BEECH 58 58 1152740 CE CONT O520 IO520C 17032 SO MCAULY 3AF34C 3AF34C502 GL LT AILERON MISINSTALLED W O OTHER W INADEQUATE Q C CR CRUISE 1 AU S (AUS) LT AILERON ATTACHMENT SCREWS INCORRECTLY LOCATED. AILERON HAD PREVIOUSLY BEEN REMOVED FOR ACCESS AND SCREWS HAD MI SSED THE ANCHOR NUTS DURING REPLACEMENT. PERSONNEL/MAINTENANCE ERROR. 1 L 7 2 3O 3 O 3A16 E5CE 5 C P22EA 2002010800045 20020108 00045 SO 2002 1 8 AUS20011023 1 20010921 G 3260 487862ALT1CH214 SWITCH PIPER PA31 PA31350 7103110 SO LYC O540 TIO540J2BD 41532 EA HARTZL HCE3Y HCE3YR2 GL MLG DOWLOCK OUT OF ADJ W O OTHER P O NO WARNING INDICATION OTHER LD LANDING 1 AU S (AUS) LT MAIN LANDING GEAR DOWNLOCK MICROSWITCH OUT OF ADJUSTMENT. 1 L 7 2 3O 3 O A20SO E14EA 5 C P33EA 2001101500058 20011015 00058 EA 2001 10 15 AUS20011024 2 20010925 G 7250 310103702 DUCT PWA PT6A27 AMTR MK1 MK1 05620JY GL PWA PT6 PT6A27 52043 EA TURBINE SECTION CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S 1448 PS41991100 (AUS) ENGINE POWER SECTION EXHAUST DUCT EXTENSIVELY CRACKED. AIRCRAFT IS FOREIGN REGISTRATION 5W-FAY. 1 H 7 1 3O 4 T NC EXPA1H71 E4EA 2001101500059 20011015 00059 CE 2001 10 15 AUS20011026 1 20010917 G 2434 DOFF10300R ALTERNATOR CESSNA 172 172N 2072434 CE LYC O360 O360A4M 41514 EA SNSNCH 76E 76EM8 EA DC GENERATOR-ALT FAILED W K NONE H ELECT. POWER LOSS-50 PC CR CRUISE 1 AU S 5110753 (AUS) ALTERNATOR OUTPUT TERMINAL FRACTURED AND ADJACENT WIRING MELTED. 1 H 7 1 3O 3 O NT 3A12 E286 5 N P4EA 2001120400069 20011204 00069 SO 2001 12 4 AUS20011032 1 20010924 G 5711 3516808 SPAR PIPER PA28161 PIPER PA28 PA28161 7102803 SO LYC O320 O320D3G 41508 EA SNSNCH 74D 74DM EA WING SPAR CORRODED W K NONE O OTHER IN INSP/MAINT 1 AU S 288216109 (AUS) LH AND RH WING SPARS PNO 35168-08 (LH) AND PNO 35168-09 (RH)CONTAINED SEVERE EXFOLIATION CORROSION. 1 L 7 1 3O 3 O 2A13 E274 5 N P88614 2002011400003 20020114 00003 EA 2002 1 14 AUS20011033 2 20010914 G 8520 SL743001 BEARING GIPPLD GA200 GA200 EU LYC O540 IO540K1A5 41532 EA HARTZL HCC2Y HCC2YR1 GL ENGINE FAILED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) CONNECTING ROD BIG END BEARING MATERIAL FLAKING OFF FROM BEARING BASE. 1 L 7 1 3O 3 O NC A00001LA 1E4 5 C P920 2001120400070 20011204 00070 EA 2001 12 4 AUS20011034 2 20010927 G 8520 STUD LYC TIO540J2BD PIPER PA31 PA31350 7103110 SO LYC O540 TIO540J2BD 41532 EA HARTZL HCE3Y HCE3YR2 GL RECIPROCATING EN FAILED W K NONE E VIBRATION/BUFFET NR NOT REPORTED 1 AU S 218 (AUS) LH ENGINE NO1 CYLINDER HOLDDOWN STUDS FAILED. CRANKCASE CRACKED IN TOP RIGHT STUD HOLE. 1 L 7 2 3O 3 O A20SO E14EA 5 C P33EA 2002010800061 20020108 00061 SO 2002 1 8 AUS20011035 2 20010912 G 8530 PISTON CONT O520 IO520M 17032 SO ENGINE MISMANUFACTURED W K NONE W INADEQUATE Q C IN INSP/MAINT 1 AU S (AUS) NEW CYLINDER KIT FAULTY. OIL HOLES NOT DRILLED IN PISTON DURING MANUFACTURE. 3 O E5CE 2001120400071 20011204 00071 CE 2001 12 4 AUS20011036 1 20010928 G 2710 S1997610 BEARING CESSNA 206 U206G 2073356 CE CONT O520 IO520F 17032 SO MCAULY 3A32C D3A32C90 GL AILERON CONTROL FAILED W K NONE F FLT CONT AFFECTED TO TAKEOFF 1 AU S (AUS) LH AILERON OUTBOARD BELLCRANK UPPER AND LOWER BEARINGS STIFF DUETO LACK OF LUBRICATION AND CORROSION. SUSPECT INAD EQUATE SEALINGOF RUBBER BUNG ON TOP OF WING ALLOWED WATER TO WASH OUT THE LUBRICATION FROM THE BEARINGS. 1 H 7 1 3O 3 O A4CE E5CE 5 C P21EA 2001120400072 20011204 00072 CE 2001 12 4 AUS20011037 1 20010929 G 5312 07126161 BULKHEAD CESSNA 182 182K 2072724 CE CONT O470 O470R 17026 SO MCAULY 2A34C 2A34C66 GL FUSELAGE MAIN, B CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) AFT TAILCONE BULKHEAD CRACKED IN AREA AT TOP OF RUDDER CABLECUTOUT. 1 H 7 1 3O 3 O NT 3A13 E273 5 C P3EA 2001120400073 20011204 00073 CE 2001 12 4 AUS20011038 1 20010929 G 5511 SPAR CESSNA 182 182K 2072724 CE CONT O470 O470R 17026 SO MCAULY 2A34C 2A34C66 GL HORIZONTAL STABI CORRODED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) TAILPLANE REAR SPAR CONTAINED SEVERE EXFOLIATION CORROSION IN THREE SEPARATE AREAS. SUSPECT CORROSION CAUSED BY WA TER INGRESS.PNO 1232610-3 (X2), PNO 0732603-2 AND PNO 1232114-1 AFFECTED. OTHER PARTS ALSO FOUND CORRODED WAS RIB PNO 12 31006-1 INTHE FIN AND THE LEFT HAND ELEVATOR TORQUE TUBE AND INBOARD ADAPTOR PNO 0734110-3 AND PNO 0734110-7. THE AFFE CTED AREAS WERE NOT PRIMED DURING MANUFACTURE AND THE AIRCRAFT SPENT A CONSIDERABLE AMOUNT OF ITS LIFE IN THE OPEN IN CO ASTAL AREAS. 1 H 7 1 3O 3 O NT 3A13 E273 5 C P3EA 2001120400074 20011204 00074 EA 2001 12 4 AUS20011039 2 20010924 G 8530 73111 EXHAUST VALVE LYC IO360A1B6D MOONEY M20 M20J 5870219 SW LYC O360 IO360A1B6 41514 EA HARTZL HCC2Y HCC2YK1 GL RECIPROCATING EN FAILED W K NONE E VIBRATION/BUFFET CR CRUISE 1 AU S 1462 L1721451A (AUS) ENGINE NO3 CYLINDER EXHAUST VALVE FAILED. 1 L 7 1 3O 3 O 2A3 1E10 5 C P920 2002010800076 20020108 00076 CE 2002 1 8 AUS20011042 1 20010907 G 3233 358251722 ARM BEECH 58 58 1152740 CE CONT O520 IO520C 17032 SO MLG ACTUATOR CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) LANDING GEAR RETRACTION MOTOR ARM CRACKED. 1 L 7 2 3O 3 O 3A16 E5CE 2001120400076 20011204 00076 NM 2001 12 4 AUS20011043 1 20010705 G 7810 320006519 TAILPIPE LYC IO540S1A5 PIPER PA60 PA60601 7106010 NM LYC O540 IO540S1A5 41532 EA HARTZL HCC3Y HCC3YR2 NE ENGINE COLLECTOR CRACKED W K NONE E B J VIBRATION/BUFFET SMOKE/FUMES/ODORS/SPARKS WARNING INDICATION CR CRUISE 1 AU S (AUS) RH ENGINE TAILPIPE CRACKED ALLOWING HOT EXHAUST GAS TO ACTIVATE FIRE WARNING SYSTEM. 1 M 7 2 3O 3 O RT A17WE 1E4 5 C P25EA 2001120400078 20011204 00078 CE 2001 12 4 AUS20011045 1 20010918 G 5730 552212126 SKIN CESSNA C550 CESSNA 500 550 2076604 CE PWA JT15 JT15D4 52112 NE WING, PLATES/SKI CORRODED W K NONE O OTHER IN INSP/MAINT 1 AU S 5500054 (AUS) RH WING SKIN SPLICE CORRODED. SUBSEQUENT INVESTIGATION REVEALED EXTENSIVE DEBONDING. ULTRASONIC INSPECTION OF LH W ING FOUND SIMILAR RESULTS. 1 L 7 2 4F 4 F A22CE E1NE 2002010800078 20020108 00078 CE 2002 1 8 AUS20011047 1 20011001 G 2810 FUEL CELL CESSNA 402 402A 207590M CE CONT O520 TSIO520E 17040 SO MCAULY 3AF32C 3AF32C87 GL LEFT CONTAMINATED W K NONE O OTHER IN INSP/MAINT 1 AU S 54 (AUS) LH FUEL SYSTEM CONTAINED SIGNIFICANT AMOUNTS OF SOLID CONTAMINATION. SUSPECT CONTAMINATION IS FROM FUEL STORAGE SY STEM. 1 L 7 2 3O 3 O A7CE E8CE 5 C P22EA 2002010800079 20020108 00079 WP 2002 1 8 AUS20011048 1 20010918 G 5711 U2727MK2 SPAR DHAVXX DH82 DH82AROBRTSN 2801002 WP DHAVXX GIPSY GIPSYMAJOR1 20004 WP AMTR C8289 C8289 GL WING DAMAGED W K NONE O OTHER IN INSP/MAINT 1 AU S BATCHNO48601 (AUS) ALL FOUR WINGS PNO U2727 MK2 (LT LOWER), PNO U2728 MK2 (RT LOWER), PNO U2729 MK2 (LT UPPER) AND PNO U2730 MK2 (RT UPPER) WERE REJECTED FOLLOWING REBUILD. NUMEROUS HOLES DRILLED IN ALL FOUR WING SPARS WERE OVERSIZE OR DRILLED IN A FIGU RE 8. AILERON BELLCRANK CONTROL BOX ALSO CRACKED. PERSONNEL/MAINTENANCE ERROR. 1 Q 7 1 3I 3 I A8EU A8EU 5 N EXPP5N 2002010800080 20020108 00080 CE 2002 1 8 AUS20011049 1 20010926 G 2460 W31X100050 CIRCUIT BREAKER CESSNA 441 441 2076020 CE DC POWER FAILED W O OTHER O OTHER NR NOT REPORTED 1 AU S (AUS) NR 1 AVIONICS SWITCH / CIRCUIT BREAKER FAILED INTERNALLY. SUSPECT CAUSED BY RAIN WATER CORROSION DUE TO LOCATION O F CIRCUIT BREAKER BELOW THE LT OPENING WINDOW. 1 L 7 2 3T RT A28CE 2001120400080 20011204 00080 EA 2001 12 4 AUS20011053 2 20010715 G 8530 EXHAUST VALVE LYC O235L2C CESSNA 150 152 2071835 CE LYC O235 O235L2C 41505 EA MCAULY 1A103 1A103TCM GL RECIPROCATING EN FAILED W K NONE E VIBRATION/BUFFET CR CRUISE 1 AU S (AUS) NO3 CYLINDER EXHAUST VALVE HEAD SEPARATED FROM VALVE STEM CAUSING MAJOR DAMAGE TO CYLINDER AND PISTON. SUSPECT CAU SED BY CORROSIONAND EROSION DAMAGE. INVESTIGATION FOUND TWO OF THE OTHER THREEEXHAUST VALVES IN SIMILAR CONDITION WITH T HE LAST EXHAUST VALVE NOT AS BADLY ERODED BUT STILL CONSIDERED UNSERVICEABLE. FURTHER INVESTIGATION FOUND THE CAMSHAFT A ND CAM FOLLOWERS PITTED AND WORN DUE TO CORROSION.AIRCRAFT IS ONLY OPERATED FOR APPROXIMATELY 20 TO 50 HOURS PER YEAR. 1 H 7 1 3O 3 O NT 3A19 E223 5 N P50GL 2002010800085 20020108 00085 WP 2002 1 8 AUS20011055 1 20010930 G 5311 269A2234 FRAME HUGHES 269 269C 4470504 WP LYC O360 HIO360D1A 41514 EA FUSELAGE CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) FUSELAGE FRAME CRACKED AT LT CLUSTER. FOUND VISUALLY AND CONFIRMED USING DYE PENETRANT INSPECTION. AIRCRAFT HAD OP ERATED FOR 192.2 HOURS SINCE AD/HU269/57 AMDT2 WAS CARRIED OUT.AD/HU269/57 AMDT2 IS CARRIED OUT EVERY 200 HOURS. 1 G 7 1 3O 3 O 4H12 1E10 2001120400082 20011204 00082 CE 2001 12 4 AUS20011057 1 20010715 G 2700 CABLE CESSNA 150 152 2071835 CE LYC O235 O235L2C 41505 EA MCAULY 1A103 1A103TCM GL FLIGHT CONTROL S CORRODED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) SEVERAL FLIGHT CONTROL CABLES RUSTY. THE FOLLOWING CABLES WEREFOUND TO BE UNSERVICEABLE:- 1. PNO 0400107-41 AILERO N CABLE (2OFF)2. PNO 0400107-21 BALANCE CABLE 3. PNO 0400107-45 FLAP CABLE4. PNO 0400107-46 FLAP CABLES 5. PNO 0400107-3 0 TRIM CABLE6. PNO 0400107-57 TRIM CABLE7. PNO 0400107-49 RUDDER CABLE 1 H 7 1 3O 3 O NT 3A19 E223 5 N P50GL 2001120400083 20011204 00083 EA 2001 12 4 AUS20011059 2 20011003 G 8520 LW13827 CRANKCASE LYC LTIO540J2BD PIPER PA31 PA31350 7103110 SO LYC O540 LTIO540J2BD 41533 EA HARTZL HCE3Y HCE3YR2 GL RECIPROCATING EN CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) RH ENGINE CRANKCASE CRACKED ON NO5 CYLINDER BASE PAD IN THE 8 O'CLOCK POSITION. 1 L 7 2 3O 3 O A20SO E14EA 5 C P33EA 2002010800095 20020108 00095 GL 2002 1 8 AUS20011060 2 20011004 G 7230 23064577A VANE DOUG 600N 600N 3027377 NM ALLSN 250C 250C47B GL COMPRESSOR CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) COMPRESSOR SCROLL ASSEMBLY RT TURNING VANE CRACKED. A PIECE OF THE VANE APPROXIMATELY 38.1MM BY 17.78MM (1.5IN BY 0.7IN) WAS MISSING. A SMALL PIECE OF THE LT VANE ALSO APPEARS TO BE MISSING. 1 G 7 1 3U 3 U NC H3WE E1GL 2001120400089 20011204 00089 CE 2001 12 4 AUS20011076 1 20011012 G 5751 122005312 BRACKET CESSNA 207 207 2073602 CE CONT O520 IO520F 17032 SO MCAULY D3A34 D3A34C404 GL AILERONS CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) RH AILERON INBOARD AND OUTBOARD HINGE BRACKETS CRACKED ANDDISTORTED. 1 H 7 1 3O 3 O A16CE E5CE 5 C P47GL 2002011400004 20020114 00004 EU 2002 1 14 AUS20011077 1 20010928 G 5551 GA538021233 BRACKET GIPPLD GA8 GA8 EU LYC O540 IO540K1A5 41532 EA HARTZL HCC2Y HCC2YR1 GL HORIZONTAL STAB SHEARED W O OTHER F FLT CONT AFFECTED CL CLIMB 1 AU S 745 (AUS) RT HORIZONTAL STABILISER ATTACHMENT BRACKET RIVETS SHEARED. 1 H 7 1 3O 3 O NT 1E4 5 C P920 2002010800114 20020108 00114 SO 2002 1 8 AUS20011078 2 20011010 G 8530 SA10200A20P CYLINDER CESSNA 150 150H 2071818 CE CONT O200 O200A 17020 SO AMTR C8289 C8289 GL ENGINE CRACKED W O OTHER E R VIBRATION/BUFFET PARTIAL RPM/PWR LOSS NR NOT REPORTED 1 AU S (AUS) NR 2 CYLINDER CRACKED FOR APPROXIMATELY 80 PERCENT OF CIRCUMFERENCE ATTHE BASE OF THE THREAD ON THE CYLINDER BARRE L BETWEEN THE TOP BARREL FIN AND THE BOTTOM FIN ON THE CYLINDER HEAD. 1 H 7 1 3O 3 O 3A19 E252 5 N EXPP5N 2001120400090 20011204 00090 CE 2001 12 4 AUS20011079 1 20011011 G 2612 303267 AMPLIFIER BEECH 200 200BEECH 1152920 CE PWA PT6 PT6A42 52043 NE MCAULY 4HFR34 4HFR34C754 NE FIRE DETECTION FAULTY W K NONE E B J VIBRATION/BUFFET SMOKE/FUMES/ODORS/SPARKS WARNING INDICATION CR CRUISE 1 AU S 0079 (AUS) LH ENGINE FIRE WARNING SYSTEM CONTROL AMPLIFIER SUSPECT FAULTY. 1 L 7 2 4T 4 T A24CE E4EA 6 C 3PNE 2002010800122 20020108 00122 EA 2002 1 8 AUS20011082 2 20011010 G 8520 LW17828 CRANKSHAFT PIPER PA36 PA36375 7103620 SO LYC O720 IO720D1C 41546 EA ENGINE BROKEN W K NONE E VIBRATION/BUFFET IN INSP/MAINT 1 AU S (AUS) ENGINE CRANKSHAFT BROKEN IN WEB LOCATED FORWARD OF MAIN BEARING JOURNAL BETWEEN NO5/NO6 AND NO7/NO8 CYLINDER BANKS . ONE CONNECTING ROD CRACKED. 1 L 7 1 3O 3 O A10SO 1E15 2001120400091 20011204 00091 SO 2001 12 4 AUS20011083 2 20010906 G 7322 626813 PIN CONT 6297032 CESSNA 210 210L 2073448 CE CONT O520 IO520L 17032 SO MCAULY 3A32C D3A32C88 GL FUEL CONTROL/REC MISSING W K NONE E VIBRATION/BUFFET NR NOT REPORTED 1 AU S G148205RA (AUS) FUEL CONTROL UNIT FUEL METERING LEVER TO SHAFT ATTACHMENT PIN MISSING. 1 H 7 1 3O 3 O 3A21 E5CE 5 C P21EA 2001120400092 20011204 00092 GL 2001 12 4 AUS20011085 1 20011009 G 7603 07431031 SHAFT CONT IO360HB PAC CT4 CT4B GL CONT O360 IO360HB 17025 SO HARTZL HCC2Y BHCC2YF1 GL POWER LEVER BROKEN W K NONE E VIBRATION/BUFFET TX TAXI/GRND HDL 1 AU S (AUS) THROTTLE LAYSHAFT CABLE CONNECTION FITTING BROKEN. 1 L 7 1 3O 3 O RT A9PC E1CE 5 C P920 2001120400093 20011204 00093 CE 2001 12 4 AUS20011086 1 20010214 G 5511 04320016 RIB CESSNA 150M CESSNA 150 150M 2071830 CE CONT O200 O200A 17020 SO AMTR C8289 C8289 GL HORIZONTAL STABI CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) HORIZONTAL STABILISER RIBS PNO 0432001-6 AND PNO 0432001-36 CRACKED FROM FORWARD ATTACHMENT POINT NUTPLATE RIVETS. 1 H 7 1 3O 3 O 3A19 E252 5 N EXPP5N 2001120400094 20011204 00094 EA 2001 12 4 AUS20011087 2 20011015 G 8520 640761A BEARING LYC TIO540J2BD 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 640761A (AUS) DURING LH ENGINE STRIP FOR REPAIR TO A CRACKED CRANKCASE, THE CENTRE MAIN BEARING WAS FOUND TO BE BADLY WORN AND T HE LOCATING LUGS WERE BADLY DAMAGED. THE CRANKSHAFT WAS ALSO FOUND TO BEDAMAGED ON THE FORWARD AND REAR SURFACES CONTACT ED BY THE BEARING DUE TO EXTREME LONGITUDINAL MOVEMENT OF THE BEARING. SEALANT WASFOUND ON THE BEARING WEBS. THE THROUGH STUD SEALING O'RINGS BETWEEN THE CRANKCASE HALVES WERE MISSING. TO STOP THE OIL LEAK SILK THREAD AND LOCTITE 515 WAS A ROUND THE THROUGH BOLT HOLES. NON-APPROVED REPAIR. PERSONNEL/MAINTENANCE ERROR. 1 L 7 2 3O 3 O A20SO E14EA 5 C P33EA 2002011000002 20020110 00002 CE 2002 1 10 AUS20011088 1 20010822 G 2434 ES4118 BRUSHES CESSNA 172 172M 2072418 CE LYC O320 O320E2D 41508 EA MCAULY 1C160 1C160DTM GL DC GENERATOR-ALT WORN W O OTHER H ELECT. POWER LOSS-50 PC CR CRUISE 1 AU S (AUS) ALTERNATOR BRUSHES WORN PREMATURELY. 1 H 7 1 3O 3 O NT 3A12 E274 5 N P910 2001120400095 20011204 00095 SO 2001 12 4 AUS20011091 2 20010911 G 8520 654811 BOLT CONT IO470L BEECH 95 95B55 1152729 CE CONT O470 IO470L 17026 SO HARTZL HCC3Y PHCC3YF2 GL RECIPROCATING EN BROKEN W K NONE E VIBRATION/BUFFET DE DESCENT 1 AU S 27214R (AUS) LH ENGINE NO4 CYLINDER CONNECTING ROD BOLT BROKEN. COWLING HOLED. 1 L 7 2 3O 3 O RT 3A16 3E1 5 C P25EA 2002011000005 20020110 00005 SO 2002 1 10 AUS20011092 1 20010925 G 2720 0106Y10 SERVO PIPER PA46 PA46500TP 7104622 SO RUDDER CONTROL FAULTY W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) YAW DAMPER SERVO FAULTY. DUST COVER OVER THE MOTOR COLLECTING WATER (CONDENSATION). THE MOISTURE DRAIN HOLE IS LOC ATED AT THE 12 O'CLOCK POSITION INSTEAD OF THE 6 O'CLOCK POSITION. AS A RESULT THE SERVO MOTOR IS BADLY CORRODED AND BUR NT. 1 L 7 1 3O RT A25SO 2002011000006 20020110 00006 SO 2002 1 10 AUS20011093 1 20010925 G 5712 102718005 RIB PIPER PA46 PA46500TP 7104622 SO RT WING CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) RT WING LEADING EDGE RIB CRACKED IN STIFFENER. 1 L 7 1 3O RT A25SO 2001120400096 20011204 00096 EU 2001 12 4 AUS20011094 1 20011019 G 2612 173462410 FIRE DETECTOR BOLKMS 117 BK117B2 5626013 EU LYC LTS101 LTS101750B1 41560 NE FIRE DETECTION FAULTY W K NONE E J B VIBRATION/BUFFET WARNING INDICATION SMOKE/FUMES/ODORS/SPARKS NR NOT REPORTED 1 AU S 173462600 (AUS) NO2 ENGINE FIRE DETECTOR ACTIVATION. FIRE BOTTLE OPERATED.INVESTIGATION FOUND THAT THE AIRCRAFT WAS IN AN UNUSUAL NOSE HIGH TURN AT THE TIME WHICH HAS IN THE PAST CAUSED THE FIRE DETECTOR TO ACTIVATE FOR SHORT PERIODS. 1 G 7 2 3U 3 U NC H13EU E5NE10 2002011000007 20020110 00007 GL 2002 1 10 AUS20011095 3 20011020 G 6114 HUB AMTR VANS RV8 GL AMTR CHEVY8 CHEVYV8 GL AMTR C8289 C8289 GL PROPELLER CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S 317 (AUS) PROPELLER HUB CRACKED. FOUND DURING INSPECTION IAW AIRCRAFT MANUFACTURERS ALERT. 1 L 7 1 3O 3 V NT EXPA1L71 EXPE3V 5 N EXPP5N 2002011000010 20020110 00010 SO 2002 1 10 AUS20011098 2 20011012 G 8520 571043 CRANKCASE BEECH 58 58 1152740 CE CONT O520 IO520C 17032 SO HARTZL HCJ3Y PHCJ3YF2 GL ENGINE DAMAGED W O OTHER E VIBRATION/BUFFET CR CRUISE 1 AU S 11 (AUS) ENGINE CRANKCASE HOLED IN AREA OF NR 5 AND NR 6 CYLINDERS. 1 L 7 2 3O 3 O 3A16 E5CE 5 C P36EA 2001120400097 20011204 00097 SO 2001 12 4 AUS20011099 1 20011019 G 5610 7929616 WINDSHIELD PIPER PA28 PA28161 7102803 SO LYC O320 O320D3G 41508 EA SNSNCH 74D 74DM EA FLIGHT COMPARTME UNAPPROVED PART W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) LH WINDSHIELD INCORRECT PART. WINDSHIELD THICKNESS OF 2.5146MM(0.100IN) INSTEAD OF 6.858MM (0.270IN). EXCESSIVE SI LASTIC SEALER USED TO FILL GAPS CAUSED BY POOR FIT. PERSONNEL/MAINTENANCE ERROR. UNAPPROVED PART. 1 L 7 1 3O 3 O 2A13 E274 5 N P88614 2002011000013 20020110 00013 EU 2002 1 10 AUS20011102 1 20010621 G 3246 C201801202A WHEEL AMD FALC50 FALCON900 2700160 EU MLG CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) MAIN WHEEL INBOARD HALF CRACKED ADJACENT TO BRAKE TANG. FOUND DURING EDDY CURRENT INSPECTION. 2 L 7 3 4F RT A46EU 2002011000014 20020110 00014 EU 2002 1 10 AUS20011103 1 20010626 G 3246 C201801202A WHEEL AMD FALC50 FALCON900 2700160 EU GARRTT TFE731 TFE7315R 01518 WP MLG CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S U285 (AUS) MAIN WHEEL INBOARD HALF CRACKED ADJACENT TO BRAKE TANG. FOUND DURING EDDY CURRENT INSPECTION. 2 L 7 3 4F 4 F RT A46EU E6WE 2002011000015 20020110 00015 EU 2002 1 10 AUS20011104 1 20010714 G 3246 C201801202A WHEEL AMD FALC50 FALCON900 2700160 EU MLG CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S U1010 (AUS) MAIN WHEEL INBOARD HALF CRACKED ADJACENT TO BRAKE TANG. FOUND DURING EDDY CURRENT INSPECTION. 2 L 7 3 4F RT A46EU 2001120400098 20011204 00098 GL 2001 12 4 AUS20011106 1 20011019 G 3710 PUMP PAC CT4 CT4B GL CONT O360 IO360HB 17025 SO HARTZL HCC2Y BHCC2YF1 GL VACUUM DISTRIBUT FAILED W K NONE I FLT. ATTITUDE INST. AP APPROACH 1 AU S (AUS) VACUUM PUMP FAILED AND DRIVE SHAFT SHEARED. 1 L 7 1 3O 3 O RT A9PC E1CE 5 C P920 2001120400099 20011204 00099 CE 2001 12 4 AUS20011107 1 20011012 G 5744 122005317 BRACKET CESSNA 206 U206G 2073356 CE CONT O520 IO520F 17032 SO MCAULY 3A32C D3A32C90 GL WING, CONTROL SU CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) INBOARD AILERON BRACKET BROKEN INTO TWO PIECES. 1 H 7 1 3O 3 O A4CE E5CE 5 C P21EA 2002011000018 20020110 00018 CE 2002 1 10 AUS20011108 1 20011012 G 5711 65110387 SPAR CAP CESSNA 500 550 2076604 CE PWA JT15 JT15D4 52112 NE LT & RT WING DEBONDED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) LT AND RT WING SPAR CAPS DEBONDED AND CORRODED. FOUND DURING ULTRASONIC INSPECTION IAW JWP/2531/01 AND JWP/2503/01 . 1 L 7 2 4F 4 F A22CE E1NE 2002011000019 20020110 00019 EU 2002 1 10 AUS20011109 1 20011024 G 6410 109813201111 BLADE AGUSTA A109 A119 0261102 EU TAIL ROTOR CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) TAIL ROTOR BLADE CRACKED IN AREA OF DOUBLER WHERE THE FINGERS ARE BLENDED INTO THE BLADE SKIN. CRACKS FOUND USING THE NAKED EYE AND CONFIRMED USING DYE PENETRANT INSPECTION. 1 G 7 2 3U H7EU 2002011000021 20020110 00021 SO 2002 1 10 AUS20011110 1 20011008 G 5540 4004626 STRUCTURE PIPER PA31 PA31 7103102 SO LYC O540 TIO540A2B 41532 EA HARTZL HCE3Y HCE3YR2 GL RUDDER CORRODED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) RUDDER CORRODED IN AREA BETWEEN TORQUE TUBE AND LOWER END CAP. 1 L 7 2 3O 3 O A20SO E14EA 5 C P33EA 2002011000023 20020110 00023 NE 2002 1 10 AUS20011112 2 20011019 G 7230 COMPRESSOR BEECH 200 B200C 1152924 CE PWA PT6 PT6A42 52043 NE ENGINE FOD W O OTHER E B VIBRATION/BUFFET SMOKE/FUMES/ODORS/SPARKS CL CLIMB 1 AU S (AUS) ENGINE FIRST STAGE COMPRESSOR DAMAGE. FOD. 1 L 7 2 4T 4 T A24CE E4EA 2002011000024 20020110 00024 CE 2002 1 10 AUS20011113 1 20011008 G 5310 57111455 DOOR FRAME CESSNA 441 441 2076020 CE FUSELAGE CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) LOWER CABIN DOOR FRAME CRACKED IN AREA ADJACENT TO AFT HINGEPOINT. 1 L 7 2 3T RT A28CE 2001120400100 20011204 00100 CE 2001 12 4 AUS20011114 1 20011022 G 2741 03101243 PIN CESSNA 55657544 CESSNA 500 550 2076604 CE PWA JT15 JT15D4 52112 NE STABILIZER POSIT WORN W K NONE F J FLT CONT AFFECTED WARNING INDICATION TO TAKEOFF 1 AU S (AUS) ELEVATOR TRIM INDICATOR SKIPPED GROOVES ON TRIM WHEEL GIVINGINCORRECT TRIM POSITION INDICATION. BOTH WHEEL FUSE PL UGS BLEWDUE TO EXCESSIVE BRAKING. 1 L 7 2 4F 4 F A22CE E1NE 2002011000025 20020110 00025 CE 2002 1 10 AUS20011116 1 20011001 G 5751 122005217 BRACKET CESSNA 206 U206E 2073350 CE CONT O520 IO520F 17032 SO HARTZL HCC3Y HCC3YF1 GL LT AILERON CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) LT AILERON HINGE BRACKET CRACKED AND BROKEN AT LOWER ATTACHMENT POINTS. LT INBOARD AND RT OUTBOARD BRACKETS ALSO C RACKED. SPAR AND RIB ALSO CRACKED. 1 H 7 1 3O 3 O A4CE E5CE 5 C P25EA 2002011400005 20020114 00005 EA 2002 1 14 AUS20011117 2 20010925 G 7414 GEAR GIPPLD GA200 GA200 EU LYC O540 O540A1D5 41532 EA MCAULY 1A200 1A200FA GL MAGNETO FAILED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) MAGNETO TIMING GEAR DRIVESHAFT FAILED. 1 L 7 1 3O 3 O NC A00001LA E295 5 N P874 2002011000026 20020110 00026 SO 2002 1 10 AUS20011120 2 20010821 G 7414 IMPULSE COUPLING BEECH 58 58 1152740 CE CONT O520 IO520C 17032 SO MAGNETO MISSING W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) RT ENGINE RT MAGNETO IMPULSE COUPLING NOT INSTALLED. 1 L 7 2 3O 3 O 3A16 E5CE 2002011000028 20020110 00028 CE 2002 1 10 AUS20011121 1 20010821 G 5610 964200291 WINDSHIELD BEECH 58 58 1152740 CE CONT O520 IO520C 17032 SO COCKPIT CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) WINDSHIELD CRACKED AND INCORRECTLY INSTALLED. 1 L 7 2 3O 3 O 3A16 E5CE 2002011000029 20020110 00029 CE 2002 1 10 AUS20011122 1 20010821 G 2720 9652400029P CONTROL CABLE BEECH 58 58 1152740 CE CONT O520 IO520C 17032 SO RUDDER MISINSTALLED W K NONE W INADEQUATE Q C IN INSP/MAINT 1 AU S (AUS) RT REAR RUDDER CABLE INCORRECTLY ROUTED. CABLE EXCESSIVELY WORN. 1 L 7 2 3O 3 O 3A16 E5CE 2002011000030 20020110 00030 CE 2002 1 10 AUS20011123 1 20010821 G 5340 951100172 FITTING BEECH 58 58 1152740 CE CONT O520 IO520C 17032 SO FUSELAGE DAMAGED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) LT REAR LOWER BATHTUB FITTING DAMAGED. 1 L 7 2 3O 3 O 3A16 E5CE 2002011000031 20020110 00031 CE 2002 1 10 AUS20011124 1 20010215 G 7921 8526250 OIL COOLER CESSNA 172 172RG 2072438 CE LYC O360 O360F1A6 41514 EA MCAULY 2D34C B2D34C220 GL ENGINE MISREPAIRED W K NONE W INADEQUATE Q C IN INSP/MAINT 1 AU S (AUS) ENGINE OIL COOLER CONTAINED UNAUTHORISED REPAIRS AND WELDING. 1 H 7 1 3O 3 O 3A17 E286 5 C P7EA 2002011000036 20020110 00036 EA 2002 1 10 AUS20011125 2 20010215 G 7310 240001046 LINE CESSNA 172 172RG 2072438 CE LYC O360 O360F1A6 41514 EA MCAULY 2D34C B2D34C220 GL FUEL DIST MISREPAIRED W K NONE W INADEQUATE Q C IN INSP/MAINT 1 AU S (AUS) ENGINE FUEL PRIMER LINE CHAFED THROUGH AND THEN INCORRECTLY REPAIRED. ELECTRICAL TAPE HAD BEEN WRAPPED AROUND THE LINE TO STOP FUEL LEAKS. 1 H 7 1 3O 3 O 3A17 E286 5 C P7EA 2002011000037 20020110 00037 CE 2002 1 10 AUS20011126 1 20010215 G 2820 240001058 LINE CESSNA 172 172RG 2072438 CE LYC O360 O360F1A6 41514 EA MCAULY 2D34C B2D34C220 GL FUEL DIST MISREPAIRED W K NONE W INADEQUATE Q C IN INSP/MAINT 1 AU S (AUS) MAIN FUEL SUPPLY LINE CHAFED THROUGH BY COWL FLAP CABLE. NYLONWRAP USED TO PROTECT WORN AREA. 1 H 7 1 3O 3 O 3A17 E286 5 C P7EA 2001120400103 20011204 00103 CE 2001 12 4 AUS20011127 1 20010215 G 2910 248000119 PIPE CESSNA 172 172RG 2072438 CE LYC O360 O360F1A6 41514 EA MCAULY 2D34C B2D34C220 GL HYDRAULIC SYSTEM WORN W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) HYDRAULIC PRESSURE LINE WORN. LINE WAS INADEQUATELY SECURED.PERSONNEL/MAINTENANCE ERROR. 1 H 7 1 3O 3 O 3A17 E286 5 C P7EA 2002011000038 20020110 00038 CE 2002 1 10 AUS20011128 1 20010124 G 5321 04102361 FLOOR PANEL CESSNA 150 152 2071835 CE LYC O235 O235L2C 41505 EA MCAULY 1A103 1A103TCM GL CABIN FLOOR CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) FLOOR CRACKED EXCESSIVELY. 1 H 7 1 3O 3 O NT 3A19 E223 5 N P50GL 2002011000039 20020110 00039 CE 2002 1 10 AUS20011129 1 20010319 G 5321 04102361 FLOOR PANEL CESSNA 150 152 2071835 CE LYC O235 O235L2C 41505 EA MCAULY 1A103 1A103TCM GL CABIN FLOOR CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) FUSELAGE FLOOR CRACKED EXCESSIVELY. 1 H 7 1 3O 3 O NT 3A19 E223 5 N P50GL 2002011000043 20020110 00043 SO 2002 1 10 AUS20011134 2 20010719 G 8520 630066A CRANKSHAFT AMTR VANS RV8 GL CONT O200 O200* 17020 SO AMTR C8289 C8289 GL ENGINE CRACKED W O OTHER E VIBRATION/BUFFET NR NOT REPORTED 1 AU S 38 (AUS) CRANKSHAFT CRACKED. SUSPECT CAUSED BY UNREPORTED PROPELLER STRIKE. CAM DRIVE BOLTS SHEARED. NO EVIDENCE OF LOCKWIR ING ON BOLTS. 1 L 7 1 3O 3 O NT EXPA1L71 E252 5 N EXPP5N 2002011000044 20020110 00044 CE 2002 1 10 AUS20011135 1 20011023 G 2435 03601018 BEARING LEARSIEGLER CESSNA 441 441 2076020 CE GARRTT TPE331 TPE3318 01514 WP HARTZL HCB3T HCB3TN5 GL STARTER GEN FAILED W O OTHER E VIBRATION/BUFFET CR CRUISE 1 AU S 5135 (AUS) STARTER-GENERATOR BEARINGS FAILED. 1 L 7 2 3T 4 T RT A28CE E4WE 6 C P15EA 2001120400104 20011204 00104 EU 2001 12 4 AUS20011136 1 20011025 G 5730 SKIN MUDRY 10 CAP10B 0950102 EU LYC O360 AEIO360B2F 41514 EA HOFMAN HO29 HO29HM180 EU WING, PLATES/SKI FRACTURED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) LH WING LOWER SKINFRACTURED BETWEEN SPARS ADJACENT TO NO3 RIB.CRACK LENGTH 600MM (23.6IN). 1 L 7 1 3O 3 O A36EU 1E10 5 N P3EU 2002011000045 20020110 00045 SO 2002 1 10 AUS20011137 1 20011025 G 3231 BOLT PIPER PA31 PA31350 7103110 SO LYC O540 TIO540J2BD 41532 EA HARTZL HCE3Y HCE3YR2 GL LT MLG DOOR WRONG PART W K NONE W INADEQUATE Q C IN INSP/MAINT 1 AU S (AUS) LT MAIN LANDING GEAR TO LANDING GEAR DOOR FORWARD ROD BOLT FAILED. INSPECTION OF REMAINING THREE ATTACHMENT BOLTS FOUND THEM TO BE THE INCORRECT PART. 1 L 7 2 3O 3 O A20SO E14EA 5 C P33EA 2001120400105 20011204 00105 SO 2001 12 4 AUS20011138 1 20011025 G 3260 SWITCH PIPER PA31 PA31350 7103110 SO LYC O540 TIO540J2BD 41532 EA HARTZL HCE3Y HCE3YR2 GL LANDING GEAR POS FAULTY W K NONE O OTHER CL CLIMB 1 AU S (AUS) MAIN LANDING GEAR SQUAT SWITCH WIRE BROKEN. 1 L 7 2 3O 3 O A20SO E14EA 5 C P33EA 2001120400106 20011204 00106 CE 2001 12 4 AUS20011139 1 20011024 G 5230 HINGE CESSNA 402 402B 207590P CE CONT O520 TSIO520E 17040 SO MCAULY 3AF32C 3AF32C87 GL CARGO/BAGGAGE DO FAILED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) LH REAR NOSE BAGGAGE DOOR AFT HINGE FAILED DURING DOOR CLOSURE. DOOR STAY WAS BENT SLIGHTLY. 1 L 7 2 3O 3 O A7CE E8CE 5 C P22EA 2001120400107 20011204 00107 CE 2001 12 4 AUS20011140 1 20011012 G 2823 SL60043 LEVER CESSNA 208 208B 2073701 CE PWA PT6 PT6A114A 52043 NE MCAULY 3AF34C 3GFR34C703 GL FUEL SELECTOR/SH BROKEN W K E NONE ENGINE SHUTDOWN O OTHER NR NOT REPORTED 1 AU S (AUS) FUEL CONDITION LEVER BROKE AT THE LOWER BEND IN THE CONTROL KNOBARM. 1 H 7 1 3T 3 T A37CE E4EA 5 C P60GL 2002011000046 20020110 00046 SO 2002 1 10 AUS20011142 1 20011022 G 3250 BOLT PIPER PA31 PA31350 7103110 SO LYC O540 TIO540J2BD 41532 EA HARTZL HCE3Y HCE3YR2 GL NLG STEERING SHEARED W O OTHER W INADEQUATE Q C LD LANDING 1 AU S (AUS) NOSE WHEEL STEERING BRACKET TO NOSE LEG ATTACHMENT BOLTS (2OFF3) SHEARED. INVESTIGATION OF NLG LEG FOUND ONE OF TH E BOLTS HOLES WAS FITTED WITH A HELICOIL INSERT. SUSPECT UNAPPROVED PART. 1 L 7 2 3O 3 O A20SO E14EA 5 C P33EA 2001120400109 20011204 00109 SO 2001 12 4 AUS20011144 1 20011026 G 2820 5052012035 TUBE PIPER PA31350 PIPER PA31 PA31350 7103110 SO LYC O540 TIO540J2BD 41532 EA HARTZL HCE3Y HCE3YR2 GL AIRCRAFT FUEL DI CORRODED W K NONE O K OTHER FLUID LOSS IN INSP/MAINT 1 AU S 317652119 (AUS) FUEL CROSSFEED PIPE LOCATED BELOW CABIN FLOOR CORRODED INTERNALLY PRODUCING A SMALL PIN HOLE LEAK. LEAKING FUEL CO NTAMINATED THESURROUNDING INSULATION. 1 L 7 2 3O 3 O A20SO E14EA 5 C P33EA 2002011000048 20020110 00048 SO 2002 1 10 AUS20011145 1 20011028 G 2844 6770055 LINE PIPER PA28 PA28161 7102803 SO LYC O320 O320* 41508 EA AMTR C8289 C8289 GL FUEL PRESS IND FAILED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) RIGID COPPER FUEL LINE TO GAUGE FRACTURED. SUSPECT INADEQUATE SUPPORT. 1 L 7 1 3O 3 O 2A13 E274 5 N EXPP5N 2002011000049 20020110 00049 EA 2002 1 10 AUS20011146 1 20010609 G 3230 6A09000097 HOSE DHAV DHC2 DHC2* 2800108 EA PWA R985 R985AN1 52008 NE HAMSTD 2D 2D30 NE FLOAT STRUT FAILED W O OTHER K J FLUID LOSS WARNING INDICATION LD LANDING 1 AU S (AUS) RT LANDING GEAR HYDRAULIC HOSE CHAFED INSIDE FLOAT STRUT. HOSE BURST. LOSS OF HYDRAULIC FLUID. AIRCRAFT IS A FLOAT PLANE. 1 H 7 1 3R 3 R A806 5E1 5 C P206 2002011000050 20020110 00050 CE 2002 1 10 AUS20011148 1 20011023 G 5311 0024300536 FRAME BEECH 58 58 1152740 CE CONT O520 IO520C 17032 SO FUSELAGE CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) RT EXIT FRAME CRACKED. 1 L 7 2 3O 3 O 3A16 E5CE 2002011000051 20020110 00051 CE 2002 1 10 AUS20011149 1 20011016 G 3230 00241003217 BRACKET BEECH 58 58 1152740 CE CONT O520 IO520C 17032 SO NLG CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) NOSE LANDING GEAR ALIGNMENT GUIDE BRACKET CRACKED. 1 L 7 2 3O 3 O 3A16 E5CE 2002011000052 20020110 00052 CE 2002 1 10 AUS20011150 1 20011016 G 3233 9581001723 WORM GEAR BEECH 58 58 1152740 CE CONT O520 IO520C 17032 SO MLG CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) LANDING GEAR GEARBOX / ACTUATOR HOURS UNKNOWN (2000 HOURS OVERHAUL). LANDING GEAR GEARBOX FOUND TO HAVE NO OIL. GE AR ACTUATOR WORM DRIVE PNO 35-810076-3 FOUND TO HAVE FATIGUE CRACKS (MECHANICAL HANDLE ATTACHMENT END). 1 L 7 2 3O 3 O 3A16 E5CE 2001120400110 20011204 00110 SO 2001 12 4 AUS20011152 1 20011026 G 3245 TUBE PIPER PA31 PA31350 7103110 SO LYC O540 TIO540J2BD 41532 EA HARTZL HCE3Y HCE3YR2 GL TIRE TUBE PUNCTURED W K NONE O OTHER LD LANDING 1 AU S (AUS) NOSEWHEEL TYRE AND TUBE PUNCTURED. 1 L 7 2 3O 3 O A20SO E14EA 5 C P33EA 2002011000054 20020110 00054 SO 2002 1 10 AUS20011153 1 20011027 G 3260 SWITCH PIPER PA31 PA31350 7103110 SO LYC O540 TIO540J2BD 41532 EA HARTZL HCE3Y HCE3YR2 GL RT MLG DOWNLOCK STUCK W O OTHER N FALSE WARNING LD LANDING 1 AU S (AUS) RT MAIN LANDING GEAR DOWNLOCK MICROSWITCH STICKING. 1 L 7 2 3O 3 O A20SO E14EA 5 C P33EA 2001120400111 20011204 00111 NE 2001 12 4 AUS20011154 2 20011012 G 7230 SEAL LYC LTS101 BOLKMS 117 BK117B1 5626012 EU LYC LTS101 LTS101750B1 41560 NE TURBINE ENGINE C LEAKING W K NONE E VIBRATION/BUFFET CR CRUISE 1 AU S (AUS) ENGINE NO1 CARBON SEAL LEAKING. 1 G 7 2 3U 3 U H13EU E5NE10 2001120400112 20011204 00112 SO 2001 12 4 AUS20011157 2 20011030 G 8530 646657 STUD CONT TSIO520VB CESSNA 402 402C 207590R CE CONT O520 TSIO520VB 17040 SO MCAULY 3AF32C 3AF32C93 GL RECIPROCATING EN MISSING W K NONE E VIBRATION/BUFFET CL CLIMB 1 AU S (AUS) RH ENGINE NO4 CYLINDER EXHAUST STUDS (4OFF) MISSING ALLOWINGEXHAUST GAS TO BE DIRECTED ONTO THE CHT PROBE. 1 L 7 2 3O 3 O A7CE E8CE 5 C P22EA 2001120400113 20011204 00113 EA 2001 12 4 AUS20011158 2 20011030 G 7414 S4LN200 MAGNETO LYC O360A1D MOONEY M20 M20C 5870208 SW LYC O360 O360A1D 41514 EA MCAULY 2D34C 2D34C53 GL MAGNETO/DISTRIBU FAULTY W K NONE O E R OTHER VIBRATION/BUFFET PARTIAL RPM/PWR LOSS IN INSP/MAINT 1 AU S 915094919614 (AUS) MAGNETOS INTERMITTENT IN OP. INSP FOU NDFOLLOWING FAULTS ON BOTH UNITS:-1. CAPACITORS FOUND TO LEAKING ELECT.LY.2. SPUR GEAR FOUND TO BE OF NYLON TYPE WHICH HAS BEEN OBSOLETE FOR MANY YRS&REQD AS PER BENDIX MASTER MANUAL TO BE REPL. 3. DISTRIBUTOR BLOCK CONTAMINATED WITH FOREIGN MATERIAL &CRACKS WERE FOUND RADIATING OUT FROM THE ELECTRODES& THERE EVI DENCE OF TRACKING ALONG THESE CRACKS4. INTERNAL TIMING FOUND TO BE SET AT 6 DEGS MOST LIKELY DUE TO CAM FOLLOWER WEAR O N CONTACTS AS CONTACT GAPAT 0.1778MM (0.007IN).THESE VALUES COMPARED TOACCEPTABLE LIMITS OF 10 DEGS +/-2 DEGS&CONTACT G APOF APPROX 0.4064MM (0. 016IN) SUGGESTS THAT THESE MAGNETOS HAVE NOT BEEN REMVD FOR SOME TIME.01115830- 1 L 7 1 3O 3 O 2A3 E286 5 C P7EA 2002011000064 20020110 00064 EU 2002 1 10 AUS20011160 1 20011029 G 2932 9738114306 SWITCH PILATS PC12 PC12 7090550 EU PWA PT6 PT6A67B 52043 NE HARTZL HCE4A HCE4A3D GL HYD PRESSURE FAILED W O OTHER K J FLUID LOSS WARNING INDICATION CL CLIMB 1 AU S (AUS) HYDRAULIC PRESSURE SWITCH FAILED. 1 L 7 1 3T 4 T RT A78EU E26NE 5 C P210NE 2001120400115 20011204 00115 EA 2001 12 4 AUS20011163 2 20011103 G 8520 L206168A STUD LYC LTIO540J2BD PIPER PA31 PA31350 7103110 SO LYC O540 LTIO540J2BD 41533 EA HARTZL HCE3Y HCE3YR2 GL RECIPROCATING EN CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S 1723 L206168A (AUS) RH ENGINE CYLINDER HOLDDOWN STUDS CRACKED. 1 L 7 2 3O 3 O A20SO E14EA 5 C P33EA 2002011000065 20020110 00065 EU 2002 1 10 AUS20011164 1 20011106 G 5302 109037043205 STRUCTURE AGUSTA A109 A119 0261102 EU TAIL BOOM CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) TAIL BOOM CRACKED. 1 G 7 2 3U H7EU 2002011000066 20020110 00066 NE 2002 1 10 AUS20011165 2 20010210 G 7321 105MK2S REGULATOR BOEING 747 747338 NM RROYCE RB211 RB211524D419 54555 NE NR 4 FUEL FLOW FAULTY W O OTHER O OTHER NR NOT REPORTED 1 AU S 2766 (AUS) NR 4 ENGINE FUEL FLOW REGULATOR (FFR) FAULTY. INVESTIGATION FOUND THE CAUSE TO BE FAILURE OF THE VMO QUILLSHAFT CU P WASHER DUE TO HIGH CYCLE FATIGUE. 2 L 7 2 4F 4 F RT A20WE E12EU 2002011000068 20020110 00068 2002 1 10 AUS20011168 4 20011105 G 3460 09601820038 CAPACITOR MOONEY M20 M20J 5870219 SW LYC O360 IO360A3B6 41514 EA MCAULY 2D34C B2D34C214 GL FLT MANAGEMENT BURNED OUT W O OTHER B J SMOKE/FUMES/ODORS/SPARKS WARNING INDICATION CL CLIMB 1 AU S (AUS) NAVCOM CAPACITOR C491 BURNT. 1 L 7 1 3O 3 O 2A3 1E10 5 C P7EA 2001120400117 20011204 00117 SO 2001 12 4 AUS20011169 2 20011017 G 8520 632018 GEAR CONT IO520M CESSNA 310 310R 2074245 CE CONT O520 IO520M 17032 SO MCAULY 3AF32C 3AF32C87 GL RECIPROCATING EN LOOSE W K NONE O H J OTHER ELECT. POWER LOSS-50 PC WARNING INDICATION IN INSP/MAINT 1 AU S 721 811610R (AUS) RH ENGINE ALTERNATOR DRIVE GEAR TO CRANKSHAFT ATTACHMENT BOLTSPNO 649205 LOOSE AND GEAR PNO 632018 LOOSE AND TEETH DAMAGED. ALTERNATOR BEARINGS FAILED. METAL CONTAMINATION OF OIL FILTER. 1 L 7 2 3O 3 O 3A10 E5CE 5 C P22EA 2002011000069 20020110 00069 SW 2002 1 10 AUS20011170 1 20011101 G 2710 705541 CONTROL ROD AIRTRC AT802 AT802 0390305 SW AILERON CONTROL BENT W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) LT AILERON CONTROL ROD BENT. SUSPECT CAUSED BY WIND GUST. 1 L 7 1 3T NC A19SW 2002011000070 20020110 00070 NM 2002 1 10 AUS20011171 1 20011106 G 4920 38002981 APU BOEING 767 767* NM APU BAY FAILED W O OTHER E VIBRATION/BUFFET NR NOT REPORTED 1 AU S 3562 P1022 (AUS) APU FAILED TO START. 2 L 7 2 4F RT A1NM 2001120400119 20011204 00119 CE 2001 12 4 AUS20011174 1 20011108 G 5711 SPAR BEECH 95 95B55 1152729 CE CONT O470 IO470L 17026 SO MCAULY 2AF34C 2AF34C55 GL WING SPAR CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) WING RH FORWARD SPAR WEB CRACKED AROUND BEND RADIUS AND FORWARD FACE. FOUND DURING INSPECTION IAW BEECH SB 2269 RE V1 ANDAD/BEECH55/62 AMDT4. 1 L 7 2 3O 3 O RT 3A16 3E1 5 C P5EA 2001120400120 20011204 00120 CE 2001 12 4 AUS20011175 1 20011102 G 7820 125025116 MUFFLER CONT IO520F CESSNA 207 207 2073602 CE CONT O520 IO520F 17032 SO MCAULY D3A34 D3A34C404 GL ENGINE NOISE SUP FAILED W K NONE O E R OTHER VIBRATION/BUFFET PARTIAL RPM/PWR LOSS IN INSP/MAINT 1 AU S (AUS) RH EXHAUST MUFFLER INTERNAL BAFFLE COLLAPSED PARTIALLY BLOCKING MUFFLER AND CAUSING LOSS OF ENGINE PERFORMANCE. 1 H 7 1 3O 3 O A16CE E5CE 5 C P47GL 2001120400121 20011204 00121 CE 2001 12 4 AUS20011176 1 20011107 G 3230 08411132 SCREW CESSNA 310R CESSNA 310 310R 2074245 CE CONT O520 IO520M 17032 SO MCAULY 3AF32C 3AF32C87 GL LANDING GEAR RET BROKEN W K NONE O OTHER LD LANDING 1 AU S (AUS) RH MAIN LANDING GEAR DOWNLOCK ADJUSTING SCREW FAILED IN THREADEDAREA. RH MLG COLLAPSED. 1 L 7 2 3O 3 O 3A10 E5CE 5 C P22EA 2002011000078 20020110 00078 SO 2002 1 10 AUS20011181 1 20011009 G 2140 A99100009 COMBUST CHAMBER PIPER PA31 PA31350 7103110 SO LYC O540 TIO540J2BD 41532 EA HARTZL HCE3Y HCE3YR2 GL HEATING SYSTEM DISTORTED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) HEATER COMBUSTION TUBE DISTORTED IN AREA OF FIRST AIR REVERSAL. SUSPECT CAUSED BY FAILURE OF TUBE MATERIAL TO COPE WITH THE HIGHTEMPERATURE OF THE HEATER. 1 L 7 2 3O 3 O A20SO E14EA 5 C P33EA 2002011000079 20020110 00079 SO 2002 1 10 AUS20011182 2 20011106 G 8550 O-RING CESSNA 402 402B 207590P CE CONT O520 TSIO520E 17040 SO MCAULY 3AF32C 3AF32C87 GL ENGINE FAILED W D RETURN TO BLOCK E K VIBRATION/BUFFET FLUID LOSS TX TAXI/GRND HDL 1 AU S (AUS) RT ENGINE UPPER APC OIL FITTING O' RING SEAL FAILED AND LEAKING. 1 L 7 2 3O 3 O A7CE E8CE 5 C P22EA 2001120400124 20011204 00124 SO 2001 12 4 AUS20011183 1 20011102 G 8120 LH1398RH170 HOUSING CONT TSIO360E PIPER PA34 PA34200T 7103406 SO CONT O360 TSIO360E 17025 SO HARTZL HCC2Y BHCC2YF2 GL EXHAUST TURBOCHA CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S 339 LH1398RH170 (AUS) LH AND RH ENGINE TURBOCHARGER TURBINE HOUSINGS CRACKED. FOUND DURING INSPECTION IAW AD/TURBO/1. LH ENGINE - CONTIN ENTAL TSIO-360-E - SERIAL NUMBER 307156 TSO 338.6 HOURS - TSLSV 119.6 HOURS RH ENGINE - CONTINENTAL LTSIO-360-E - SERIAL NUMBER 306161TSO 338.6 HOURS - TSLSV 119.6 HOURS 1 L 7 2 3O 3 O A7SO E9CE 5 C P920 2001120400125 20011204 00125 CE 2001 12 4 AUS20011184 1 20011102 G 7110 1019100251 COWLING PWA PT6A41 BEECH 200 200BEECH 1152920 CE PWA PT6 PT6A41 52043 EA HARTZL HCB3T HCB3TN3 GL ENGINE COWLING S SEPARATED W K NONE D INFLIGHT SEPARATION CL CLIMB 1 AU S (AUS) LH ENGINE FORWARD UPPER COWL ASSEMBLY SEPARATED IN FLIGHT. PILOTHAD RECENTLY PERFORMED MAINTENANCE ON THE COWL. MI NOR DAMAGE TO COWLS AND LEADING EDGE CAUSED BY COWL SEPARATION. PERSONNEL/MAINTENANCE ERROR. 1 L 7 2 4T 4 T A24CE E4EA 6 C P15EA 2001120400127 20011204 00127 EA 2001 12 4 AUS20011186 2 20011107 G 8520 LW11021 BEARING LYC IO320B1A PIPER PA30 PA30 7103002 SO LYC O320 IO320B1A 41508 EA HARTZL HCE2Y HCE2YL2 GL RECIPROCATING EN FAILED W K NONE O OTHER IN INSP/MAINT 1 AU S 285 L246155A (AUS) CONNECTING ROD BIGEND BEARING MATERIAL SEPARATED FROM BEARING SHELL. 1 L 7 2 3O 3 O A1EA 1E12 5 C P9EA 2002011000080 20020110 00080 SW 2002 1 10 AUS20011187 1 20011102 G 6410 212010750105 BLADE BELL 412 412 1182202 SW PWA PT6T PT6T3B 52045 NE TAIL ROTOR CONTAMINATED W K NONE O OTHER IN INSP/MAINT 1 AU S 281 (AUS) TAIL ROTOR BLADE CORE CONTAMINATED WITH WATER. FOUND DURING X-RAY INSPECTION AFTER BLADE WAS UNABLE TO BE BALANCED AND WAS FOUND TO BE 66 GRAMS HEAVIER THAN THE MASTER BLADE. 1 G 7 2 4U 4 U H4SW E22EA 2002011000081 20020110 00081 SO 2002 1 10 AUS20011188 2 20011107 G 8530 EXHAUST VALVE CESSNA 310 310R 2074245 CE CONT O520 IO520M 17032 SO MCAULY 3AF32C 3AF32C87 GL ENGINE BURNED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) NR 1 AND NR 3 CYLINDER EXHAUST VALVES BURNED AND ERRODED. 1 L 7 2 3O 3 O 3A10 E5CE 5 C P22EA 2001120400132 20011204 00132 EU 2001 12 4 AUS20011195 1 20011110 G 5311 FASTENER BAC 146 146200A 1500266 EU LYC ALF502 ALF502R5 41580 NE FUSELAGE MAIN, F SHEARED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) FRAME 29 RH SIDE HILOK FASTENER SHEARED IN AREA ADJACENT TO STRINGER NO11. 2 H 7 4 4F 4 F A49EU E6NE 2001120400134 20011204 00134 CE 2001 12 4 AUS20011197 1 20011113 G 5341 NAS15035M BOLT BEECH 95 95B55 1152729 CE CONT O470 IO470L 17026 SO MCAULY 2AF34C 2AF34C55 GL FUSELAGE, WING A CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) WING ATTACHMENT BOLT CRACKED. FURTHER INVESTIGATION FOUND THATTHE WASHER HAD BEEN INCORRECTLY FITTED WITH THE WASH ER BEVELLED EDGE FACING AWAY FROM THE BOLT HEAD. THE WASHER WAS ALSO DAMAGED. FOUND DURING INSPECTION IAW AD/BEECH55/79 AMDT1.PERSONNEL/MAINTENANCE ERROR. 1 L 7 2 3O 3 O RT 3A16 3E1 5 C P5EA 2001120400136 20011204 00136 NM 2001 12 4 AUS20011199 1 20010404 G 3230 BACF8A06EN0700B HOSE BOEING 767 767238 1385114 NM PWA JT9 JT9D7R4E 52054 NE LANDING GEAR RET LEAKING W K NONE O K OTHER FLUID LOSS IN INSP/MAINT 1 AU S (AUS) RH MAIN LANDING GEAR TILT ACTUATOR HYDRAULIC HOSE LEAKING. 2 L 7 2 4F 4 F RT A1NM E3NE 2001120400137 20011204 00137 CE 2001 12 4 AUS20011201 1 20011113 G 7430 A3600 IGNITION SWITCH LYC O360F1A6 CESSNA 172 172RG 2072438 CE LYC O360 O360F1A6 41514 EA MCAULY 2D34C B2D34C220 GL IGNITION SWITCHI WORN W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) IGNITION SWITCH CONTACTS WORN BEYOND LIMITS AS DETAILED INSEB91-5. 1 H 7 1 3O 3 O 3A17 E286 5 C P7EA 2002011000087 20020110 00087 EU 2002 1 10 AUS20011205 1 20011102 G 2752 9787320003 PDU PILATS PC12 PC12 7090550 EU PWA PT6 PT6A67B 52043 NE HARTZL HCE4A HCE4A3D GL TE FLAPS FAILED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) FLAP POWER DRIVE UNIT (PDU) FAILED. INTERNAL THERMAL SWITCH TRIPPED. 1 L 7 1 3T 4 T RT A78EU E26NE 5 C P210NE 2001120400139 20011204 00139 CE 2001 12 4 AUS20011207 1 20011016 G 3411 PIPE CESSNA 402 402C 207590R CE CONT O520 GTSIO520E 17032 SO MCAULY 3AF32C 3AF32C87 GL PITOT/STATIC SYS CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) ALTITUDE ENCODER STATIC PIPE CRACKED. FOUND DURING INSPECTION IAW AD/RAD/43 AND AD/RAD/47. 1 L 7 2 3O 3 O A7CE E7CE 5 C P22EA 2002011000090 20020110 00090 2002 1 10 AUS20011212 4 20011104 G 6122 L16694SIA CLAMP BEECH 23 C24R 1151254 CE LYC O360 IO360A1B6 41514 EA HARTZL HCM2Y HCM2YR GL PROP GOVERNOR MISSING W O OTHER K F FLUID LOSS FLT CONT AFFECTED CR CRUISE 1 AU S 1070 (AUS) PROPELLER GOVERNOR OIL LINE CRACKED AT FLANGE IN AREA OF ATTACHMENT TO THE GOVERNOR. LOSS OF ENGINE OIL CAUSED ENG INE TO SEIZE. INVESTIGATION FOUND THAT THE TWO CLAMPS REQUIRED BYAD/LYC/86 AMDT2 WERE NOT FITTED. PERSONNEL/MAINTENANCE ERROR. 1 L 7 1 3O 3 O A1CE 1E10 5 C P43GL 2001120400142 20011204 00142 SO 2001 12 4 AUS20011213 1 20011103 G 7332 633869 LINE CONT LTSIO360E PIPER PA34 PA34200T 7103406 SO CONT O360 LTSIO360E 17025 SO HARTZL HCC2Y BHCC2YF2 GL FUEL PRESSURE IN CRACKED W K NONE E R VIBRATION/BUFFET PARTIAL RPM/PWR LOSS CL CLIMB 1 AU S 1513 304379 (AUS) RH ENGINE FUEL PUMP SENSE LINE CRACKED APPROXIMATELY 10MM (0.393IN) FROM THE FLARED END. 1 L 7 2 3O 3 O A7SO E9CE 5 C P920 2002011000091 20020110 00091 SO 2002 1 10 AUS20011214 1 20011101 G 3233 452729 BEARING PIPER PA28 PA28R201 7102816 SO CONT IO360 IO360* 17025 CE MCAULY 2D34C B2D34C213 GL MLG ACTUATOR CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) NOSE LANDING GEAR ACTUATOR BEARING CRACKED AND BROKEN. 1 L 7 1 3O 3 O 2A13 E1CE 5 C P7EA 2001120400143 20011204 00143 CE 2001 12 4 AUS20011215 1 20010903 G 3233 12810013 ACTUATOR CESSNA 172 172RG 2072438 CE LYC O360 O360F1A6 41514 EA MCAULY 2D34C B2D34C220 GL LANDING GEAR ACT CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) LH AND RH MAIN LANDING GEAR ACTUATOR BODIES CRACKED IN AREA INDICATED BY SEB 01-2 FIG1 PAGE4. 1 H 7 1 3O 3 O 3A17 E286 5 C P7EA 2001120400144 20011204 00144 CE 2001 12 4 AUS20011216 1 20010903 G 3230 24411001 PIVOT CESSNA 172 172RG 2072438 CE LYC O360 O360F1A6 41514 EA MCAULY 2D34C B2D34C220 GL LANDING GEAR RET CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) LH AND RH MAIN LANDING GEAR PIVOT ASSEMBLIES CRACKED IN INSPECTION AREA 1B OF SEB 90-1 REV3. 1 H 7 1 3O 3 O 3A17 E286 5 C P7EA 2001120400145 20011204 00145 CE 2001 12 4 AUS20011219 1 20011106 G 3213 12412021 FITTING CESSNA 207 207 2073602 CE CONT O520 IO520F 17032 SO MCAULY D3A34 D3A34C404 GL MAIN LANDING GEA CRACKED W K NONE O OTHER LD LANDING 1 AU S (AUS) RH MAIN LANDING GEAR FITTING CRACKED AND RUBBING ON BRAKE DISC. 1 H 7 1 3O 3 O A16CE E5CE 5 C P47GL 2001120400146 20011204 00146 SO 2001 12 4 AUS20011220 1 20011030 G 2810 VALVE PIPER PA31 PA31350 7103110 SO LYC O540 TIO540J2BD 41532 EA HARTZL HCE3Y HCE3YR2 GL FUEL STORAGE MISSING W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) RH MAIN FUEL CELL RH FLAPPER VALVE DOOR MISSING. 1 L 7 2 3O 3 O A20SO E14EA 5 C P33EA 2002011000097 20020110 00097 SO 2002 1 10 AUS20011221 1 20011110 G 3230 LANDING GEAR PIPER PA31 PA31350 7103110 SO LYC O540 TIO540J2BD 41532 EA HARTZL HCE3Y HCE3YR2 GL NOSE OUT OF ADJ W O OTHER N FALSE WARNING CL CLIMB 1 AU S (AUS) NOSE LANDING GEAR OUT OF ADJUSTMENT. NLG NOT COMPLETELY ENGAGING WITH UPLOCK HOOK DURING RETRACTION. 1 L 7 2 3O 3 O A20SO E14EA 5 C P33EA 2002011000098 20020110 00098 SO 2002 1 10 AUS20011222 1 20011111 G 3260 487862 SWITCH PIPER PA31 PA31350 7103110 SO LYC O540 TIO540J2BD 41532 EA HARTZL HCE3Y HCE3YR2 GL NLG UPLOCK INTERMITTENT W O OTHER N FALSE WARNING CL CLIMB 1 AU S (AUS) NOSE LANDING GEAR UPLOCK MICROSWITCH INTERMITTENT IN OPERATION. 1 L 7 2 3O 3 O A20SO E14EA 5 C P33EA 2002011000102 20020110 00102 WP 2002 1 10 AUS20011224 2 20011112 G 7261 11405700182 HOUSING CESSNA 441 441 2076020 CE GARRTT TPE331 TPE3318 01514 WP HARTZL HCB3T HCB3TN5 GL OIL PUMP CRACKED W O OTHER E K VIBRATION/BUFFET FLUID LOSS CR CRUISE 1 AU S 333 (AUS) ENGINE OIL PUMP HOUSING CRACKED. 1 L 7 2 3T 4 T RT A28CE E4WE 6 C P15EA 2001120400148 20011204 00148 CE 2001 12 4 AUS20011225 1 20011120 G 5741 082255014 FITTING CESSNA 310 310R 2074245 CE CONT O520 IO520M 17032 SO MCAULY 3AF32C 3AF32C87 GL WING, FUSELAGE A CORRODED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) RH WING UPPER FORWARD ATTACHMENT FITTING CONTAINED INTERGRANNULAR CORROSION IN THE UPPER SURFACES AND TWO AREAS OF PITTINGCORROSION. FOUND DURING INSPECTION IAW AD/C310/53. 1 L 7 2 3O 3 O 3A10 E5CE 5 C P22EA 2002011000103 20020110 00103 NE 2002 1 10 AUS20011226 2 20011113 G 7200 ENGINE BEECH 200 B200C 1152924 CE PWA PT6 PT6A42 52043 NE NACELLE MALFUNCTIONED W O OTHER F FLT CONT AFFECTED NR NOT REPORTED 1 AU S (AUS) NEWLY INSTALLED ENGINE FAILED TO CORRECTLY CONTROL PROPELLER. 1 L 7 2 4T 4 T A24CE E4EA 2001120400149 20011204 00149 CE 2001 12 4 AUS20011227 1 20011108 G 5312 0512187 BULKHEAD CESSNA 172 172M 2072418 CE LYC O320 O320E2H 41508 EA MCAULY 1C160 1C160DTM GL FUSELAGE MAIN, B CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) BULKHEAD CRACKED. FOUND DURING INSPECTION IAW CESSNA SEB 97-1 AND AAC 1-95. 1 H 7 1 3O 3 O NT 3A12 E274 5 N P910 2002011400007 20020114 00007 CE 2002 1 14 AUS20011228 1 20011119 G 2701 05131822 WHEEL CESSNA 172 172D 2072410 CE CONT O300 O300C 17022 SO MCAULY 1C172 1C172EM GL CONTROL COLUMN FAILED W A UNSCHED LANDING F FLT CONT AFFECTED CL CLIMB 1 AU S (AUS) PILOTS CONTROL WHEEL BROKE INTO SEVERAL PIECES. INVESTIGATION FOUND THE COPILOTS CONTROL WHEEL CRACKED BEYOND LIMI TS. 1 H 7 1 3O 3 O NT 3A12 E253 5 N P910 2002011400008 20020114 00008 GL 2002 1 14 AUS20011230 3 20011119 G 6114 C471698 HUB CESSNA 188 A188A 2073008 CE MCAULY 2A34C D2A34C98 GL PROPELLER CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) PROPELLER HUB CRACKED IN AREA OF NR 1 BLADE SOCKET. FOUND DURING EDDY CURRENT INSPECTION. 1 L 7 1 3O A9CE 5 C P3EA 2001120400152 20011204 00152 SO 2001 12 4 AUS20011237 1 20011108 G 5541 4006805 SPAR PIPER PA31 PA31 7103102 SO LYC O540 TIO540A2B 41532 EA HARTZL HCE3Y HCE3YR2 GL RUDDER, SPAR/RIB CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) RUDDER FORWARD SPAR CRACKED. FOUND DURING INSPECTION IAWAD/PA31/129. 1 L 7 2 3O 3 O A20SO E14EA 5 C P33EA 2002011400013 20020114 00013 GL 2002 1 14 AUS20011238 2 20011114 G 7230 6858348 BLADE HUGHES 369 369HS 4470728 WP ALLSN 250C 250C18 03011 GL COMPRESSOR FAILED W O OTHER E VIBRATION/BUFFET TO TAKEOFF 1 AU S 1483 (AUS) SECOND STAGE COMPRESSOR BLADES (2OFF) FAILED). MAJOR DOWNSTREAM DAMAGE. SEVERAL OTHER SECOND STAGE ROTOR BLADES WE RE FOUND TO BECRACKED FROM THE TRAILING EDGE. 1 G 7 1 3U 3 U H3WE E4CE 2002011400014 20020114 00014 CE 2002 1 14 AUS20011239 1 20011121 G 3297 6508012202 WIRE HARNESS CESSNA 500 S550 2076607 CE PWA JT15 JT15D1 52060 NE MLG INTERMITTENT W O OTHER N FALSE WARNING LD LANDING 1 AU S (AUS) LT ANTISKID TRANSDUCER WIRING HAD AN INTERMITTENT FAULT. NO BRAKING DURING LANDING RESULTED IN EMERGENCY BRAKING SYSTEM OPERATION. RH TYRE FAILED DUE TO WHEEL SKIDDING. RT MAIN WHEEL HUB ALSO DAMAGED. 1 L 7 2 4F 4 F RT A22CE E1NE 2001120400153 20011204 00153 CE 2001 12 4 AUS20011241 1 20011109 G 5412 402B0622 BEAM CESSNA 402 402B 207590P CE CONT O520 TSIO520E 17040 SO MCAULY 3AF32C 3AF32C93 GL NACELLE/PYLON, B CORRODED W K NONE O OTHER IN INSP/MAINT 1 AU S 402B0622 (AUS) ENGINE BEAMS AND CANTED BULKHEADS CORRODED BEYOND LIMITS. FOUND DURING NDT INSPECTION. 1 L 7 2 3O 3 O A7CE E8CE 5 C P22EA 2001120400154 20011204 00154 CE 2001 12 4 AUS20011242 1 20011109 G 3221 584200111 TRUNNION CESSNA 402B CESSNA 402 402B 207590P CE CONT O520 TSIO520E 17040 SO MCAULY 3AF32C 3AF32C93 GL NOSE/TAIL LANDIN CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S 402B0622 (AUS) NOSE LANDING GEAR TRUNNION CRACKED. 1 L 7 2 3O 3 O A7CE E8CE 5 C P22EA 2001120400155 20011204 00155 SO 2001 12 4 AUS20011243 2 20010914 G 8520 6419311075 BOLT CONT IO520M CESSNA 310 310R 2074245 CE CONT O520 IO520M 17032 SO MCAULY 3AF32C 3AF32C87 GL RECIPROCATING EN BROKEN W K NONE E VIBRATION/BUFFET CR CRUISE 1 AU S 637 574058 (AUS) LH ENGINE CRANKCASE THOUGH BOLT BROKEN. SEE ALSO MDR 01/1244. 1 L 7 2 3O 3 O 3A10 E5CE 5 C P22EA 2001120400156 20011204 00156 SO 2001 12 4 AUS20011244 2 20010914 G 8520 6461401 STUD CONT IO520M CESSNA 310 310R 2074245 CE CONT O520 IO520M 17032 SO MCAULY 3AF32C 3AF32C87 GL RECIPROCATING EN BROKEN W K NONE E VIBRATION/BUFFET CL CLIMB 1 AU S 574058 (AUS) LH ENGINE CYLINDER HOLDDOWN STUD BROKEN. CRANKCASE CRACKED. SEE ALSO MDR 01/1243. 1 L 7 2 3O 3 O 3A10 E5CE 5 C P22EA 2001120400157 20011204 00157 NE 2001 12 4 AUS20011245 2 20011001 G 7321 164448480 FCU TMECA 164448480 SNIAS 350 AS350B 8680801 EU TMECA ARRIEL ARRIEL1B 6OO30 NE FUEL CONTROL/TUR FAULTY W K NONE O K OTHER FLUID LOSS IN INSP/MAINT 1 AU S A444B (AUS) FUEL CONTROL UNIT LEAKING. FUEL LEAKING FROM FCU DRAIN WITH BOOST PUMP ON AND ENGINE NOT RUNNING. 1 G 7 1 3U 3 U H9EU E19EU 2001120400158 20011204 00158 NE 2001 12 4 AUS20011246 2 20011003 G 7321 164448480 FCU TMECA 164448480 SNIAS 350 AS350B 8680801 EU TMECA ARRIEL ARRIEL1B 6OO30 NE FUEL CONTROL/TUR FAULTY W K NONE E VIBRATION/BUFFET NR NOT REPORTED 1 AU S 8 98B (AUS) FCU FAULTY. ENGINE HUNG ON START. 1 G 7 1 3U 3 U H9EU E19EU 2002011400017 20020114 00017 2002 1 14 AUS20011250 4 20011123 G 2561 P0640101 LIFE VEST CABIN MISMARKED W K NONE W INADEQUATE Q C IN INSP/MAINT 1 AU S (AUS) OVERHAULED LIFE JACKETS INCORRECTLY MARKED. LIFE JACKETS ARE EITHER INFANT OR ADULT FIT ITEMS BUT ARE ALL MARKED ON THE OUTSIDE OF THE STORAGE BAGS AS KSE-35L8 WHICH ARE ADULT FIT ITEMS. THE INFANT FIT JACKETS SHOULD BE MARKED P0640 .101. THE INCORRECT MARKING ON THE STORAGE BAGS COULD RESULT IN THE INCORRECT ITEM BEING USED IN AN EMERGENCY. THE OVE RHAUL FACILITYHAS BEEN NOTIFIED AND WILL CORRECTLY MARK ALL LIFE JACKETS FROM NOW ON. INCORRECTLY MARKED LIFE JACKETS I N THE SYSTEM WILL BE IDENTIFIED AND CORRECTLY MARKED BY MAINTENANCE. 2001120400160 20011204 00160 WP 2001 12 4 AUS20011251 1 20011119 G 3213 269A3150 DAMPER HUGHES 269 269C 4470504 WP LYC O360 HIO360D1A 41514 EA MAIN LANDING GEA LOOSE W K NONE O OTHER LD LANDING 1 AU S (AUS) LH REAR LANDING GEAR DAMPER UPPER CAP UNSCREWED AND SEPARATED FROM PISTON. SUSPECT CAUSED BY VIBRATION. 1 G 7 1 3O 3 O 4H12 1E10 2001120400161 20011204 00161 SO 2001 12 4 AUS20011252 1 20011113 G 3230 9564308 BRACKET PIPER PA44 PA44180 7104402 SO LYC O360 O360E1A6 41514 EA HARTZL HCC3Y HCC3YR2 NE LANDING GEAR RET CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) LH MAIN LANDING GEAR DOWNLOCK BRACKET CRACKED. 1 L 7 2 3O 3 O A19S0 E286 5 C P25EA 2001120400162 20011204 00162 EA 2001 12 4 AUS20011253 2 20011113 G 8520 LW16508 CAMSHAFT LYC O360E1A6 PIPER PA44 PA44180 7104402 SO LYC O360 O360E1A6 41514 EA HARTZL HCC3Y HCC3YR2 NE RECIPROCATING EN UNSERVICEABLE W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) LH ENGINE CAMSHAFT NO1 AND NO4 TAPPETS UNSERVICEABLE. FOUND DURING INSPECTION IAW PIPER MSB 446D. 1 L 7 2 3O 3 O A19S0 E286 5 C P25EA 2001120400163 20011204 00163 SO 2001 12 4 AUS20011254 1 20011113 G 5712 7847506 RIB PIPER PA44 PA44180 7104402 SO LYC O360 O360E1A6 41514 EA HARTZL HCC3Y HCC3YR2 NE WING, RIB/BULKHE CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) WING RIB CRACKED. RIB SUPPORTS UNDERCARRIAGE DOWNLOCK. 1 L 7 2 3O 3 O A19S0 E286 5 C P25EA 2001120400164 20011204 00164 SO 2001 12 4 AUS20011255 1 20011113 G 5712 7847507 RIB PIPER PA44 PA44180 7104402 SO LYC O360 O360E1A6 41514 EA HARTZL HCC3Y HCC3YR2 NE WING, RIB/BULKHE CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) WING RIB CRACKED. RIB SUPPORTS UNDERCARRIAGE DOWNLOCK. 1 L 7 2 3O 3 O A19S0 E286 5 C P25EA 2001120400165 20011204 00165 SO 2001 12 4 AUS20011256 1 20011113 G 3230 9564309 BRACKET PIPER PA44 PA44180 7104402 SO LYC O360 O360E1A6 41514 EA HARTZL HCC3Y HCC3YR2 NE LANDING GEAR RET CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) RH MAIN LANDING GEAR UPLOCK BRACKET CRACKED. 1 L 7 2 3O 3 O A19S0 E286 5 C P25EA 2002011400018 20020114 00018 CE 2002 1 14 AUS20011257 1 20011030 G 2752 45521212607 ACTUATOR BEECH 58 58 1152740 CE CONT O520 IO520C 17032 SO TE FLAP MISINSTALLED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) RT WING FLAP ACTUATOR INCORRECTLY INSTALLED. 1 L 7 2 3O 3 O 3A16 E5CE 2002011400019 20020114 00019 CE 2002 1 14 AUS20011258 1 20011030 G 5720 00243002027 FITTING BEECH 58 58 1152740 CE CONT O520 IO520C 17032 SO MLG ACTUATOR CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) LANDING GEAR ACTUATOR SUPPORT FITTING CRACKED. 1 L 7 2 3O 3 O 3A16 E5CE 2002011400020 20020114 00020 CE 2002 1 14 AUS20011259 1 20011030 G 3233 45521212604 ACTUATOR BEECH 58 58 1152740 CE CONT O520 IO520C 17032 SO MLG ACTUATOR MISINSTALLED W K NONE W INADEQUATE Q C IN INSP/MAINT 1 AU S (AUS) LT MAIN LANDING GEAR ACTUATOR INCORRECTLY FITTED. 1 L 7 2 3O 3 O 3A16 E5CE 2002011400021 20020114 00021 CE 2002 1 14 AUS20011260 1 20011105 G 2752 355212133 ATTACH FITTING BEECH 58 58 1152740 CE CONT O520 IO520C 17032 SO TE FLAP ACTUATOR CORRODED W K NONE O OTHER IN INSP/MAINT 1 AU S 204 (AUS) TRAILING EDGE FLAP ACTUATOR INTERNALLY CORRODED. ATTACHMENT LUG ALSO CORRODED. 1 L 7 2 3O 3 O 3A16 E5CE 2002011400022 20020114 00022 CE 2002 1 14 AUS20011261 1 20011105 G 2752 3536415157 BRUSH HOLDER BEECH 58 58 1152740 CE CONT O520 IO520M 17032 SO TE FLAP ACTUATOR CRACKED W K NONE W INADEQUATE Q C IN INSP/MAINT 1 AU S 120 (AUS) TRAILING EDGE FLAP ACTUATOR MOTOR BRUSH HOLDER ASSEMBLIES CRACKED. EXCESSIVE HEAT THROUGH FIELD WINDINGS. INSUFF ICIENT GREASE OF INCORRECT TYPE IN GEARBOX ASSEMBLY. UNAPPROVED PART. 1 L 7 2 3O 3 O 3A16 E5CE 2002011400023 20020114 00023 CE 2002 1 14 AUS20011262 1 20011105 G 2520 SEAT BEECH 58 58 1152740 CE CONT O520 IO520C 17032 SO PASSENGER COMPAR UNSERVICEABLE W K NONE W INADEQUATE Q C IN INSP/MAINT 1 AU S (AUS) CABIN SEATS UNSERVICEABLE. PARTS MISSING. REAR SEAT LUMBAR SUPPORTS CRACKED. VARIOUS SEAT ASSEMBLIES MODIFIED. PER SONNEL/MAINTENANCE ERROR. 1 L 7 2 3O 3 O 3A16 E5CE 2002011400024 20020114 00024 CE 2002 1 14 AUS20011263 1 20011105 G 2820 002920000191 LINE BEECH 58 58 1152740 CE CONT O520 IO520C 17032 SO FUEL DIST CHAFED W K NONE W INADEQUATE Q C IN INSP/MAINT 1 AU S (AUS) FUEL CROSSFEED LINE LOCATED IN RT WHEEL BAY CHAFING ON UNDERCARRIAGE DOWNLOCK BACKUP CABLE. SUSPECT LINE INADEQUAT ELY SECURED. PERSONNEL/MAINTENANCE ERROR. 1 L 7 2 3O 3 O 3A16 E5CE 2002011400025 20020114 00025 CE 2002 1 14 AUS20011264 1 20011105 G 2820 00292000077 LINE BEECH 58 58 1152740 CE CONT O520 IO520C 17032 SO FUEL DIST CHAFED W K NONE W INADEQUATE Q C IN INSP/MAINT 1 AU S (AUS) CROSSFEED FUEL LINE LOCATED IN LT WHEEL WELL CHAFING ON UNDERCARRIAGE ACTUATOR CONTROL ROD. THE FUEL LINE HAD BEEN COVERED WITH A PLASTIC SLEEVE AFTER THE DAMAGE HAD OCCURRED. SUSPECT CAUSED BY INADEQUATE SECURING OF FUEL LINE. PERSO NNEL/MAINTENANCE ERROR. 1 L 7 2 3O 3 O 3A16 E5CE 2002011400026 20020114 00026 CE 2002 1 14 AUS20011266 1 20011123 G 3297 WIRE CESSNA 310 310R 2074245 CE CONT O520 IO520M 17032 SO MCAULY 3AF32C 3AF32C87 GL MLG DOWNLOCK MISINSTALLED W A UNSCHED LANDING W N INADEQUATE Q C FALSE WARNING CL CLIMB 1 AU S (AUS) RT MAIN LANDING GEAR DOWNLOCK MICROSWITCH WIRING INCORRECTLY ROUTED CAUSING A STRAIN ON THE MICROSWITCH. 1 L 7 2 3O 3 O 3A10 E5CE 5 C P22EA 2002011400027 20020114 00027 EU 2002 1 14 AUS20011267 1 20011123 G 3233 C243532 ACTUATOR SNIAS AS332 AS332L 8680809 EU TMECA MAKILA MAKILA1A 60040 EU RT MLG LEAKING W O OTHER K J FLUID LOSS WARNING INDICATION DE DESCENT 1 AU S 7803 (AUS) RT MAIN LANDING GEAR ACTUATOR HYDRAULIC UNIT FAULTY. 2 G 7 2 4U 4 U H4EU E12NE 2001120400166 20011204 00166 EA 2001 12 4 AUS20011268 2 20011122 G 7310 5011849 PIPE PWA PT6A34 EMB 110 EMB110P2 3260124 SO PWA PT6 PT6A34 52043 EA HARTZL HCB3T HCB3TN3 GL ENGINE FUEL DIST CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) PIPE LOCATED BETWEEN FCU AND START CONTROL VALVE CRACKED AT FITTING. 1 L 7 2 4T 4 T A21SO E4EA 6 C P15EA 2002010400040 20020104 00040 CE 2002 1 4 AUS20011271 1 20011119 G 2731 455260053 SPROCKET BEECH 55 E55 1152732 CE CONT O520 IO520C 17032 SO MCAULY 3AF32C 3AF32C75 GL ELEVATOR TAB CON WORN W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) ELEVATOR TRIM TAB ACTUATOR SPROCKET SHAFT BADLY WORN. 1 L 7 2 3O 3 O 3A16 E5CE 5 C P22EA 2002010400041 20020104 00041 NE 2002 1 4 AUS20011272 1 20011129 G 3260 7655200904045 WIRE SKRSKY S76 S76C 8143008 NE TMECA ARRIEL ARRIEL1S 60030 NE LANDING GEAR POS BROKEN W K NONE O N OTHER FALSE WARNING DE DESCENT 1 AU S (AUS) RH MAIN LANDING GEAR DOWNLOCK SENSOR HARNESS WIRE BROKEN. 1 G 7 2 3U 3 U NC H1NE E19EU 2002011400030 20020114 00030 CE 2002 1 14 AUS20011273 1 20011006 G 3246 PANEL CESSNA 206 U206G 2073356 CE CONT O520 IO520F 17032 SO MCAULY D3A34 D3A34C404 GL FLOAT COVER SEPARATED W O OTHER D F INFLIGHT SEPARATION FLT CONT AFFECTED NR NOT REPORTED 1 AU S (AUS) RIGHT HAND FLOAT HATCH COVER SEPARATED IN FLIGHT. THE COVER CONTACTED THE RIGHT HAND TAILPLANE CAUSING CONSIDERABL E DAMAGE AND CONTROL PROBLEMS. VIBRATION CAUSED FAILURE OF SEVERAL HYDRAULIC LINES IN THE RIGHT HAND FLOAT. LOSS OF HYDR AULIC FLUID THEN LEAD TO ONLY PARTIAL LANDING GEAR EXTENSION. 1 H 7 1 3O 3 O A4CE E5CE 5 C P47GL 2002011400035 20020114 00035 2002 1 14 AUS20011279 4 20011023 G 3414 610400106 INDICATOR CESSNA 340 340CESSNA 2076404 CE CONT O520 TSIO520K 17040 SO MCAULY 3AF32C 3AF32C93 GL AIRSPEED READS HIGH W A UNSCHED LANDING O OTHER CL CLIMB 1 AU S (AUS) AIRSPEED INDICATOR FAULTY. INDICATOR WAS READING 180 KNOTS WHEN THE AIRCRAFT WAS STATIONARY. PITOT AND STATIC LI NES CHECKED WITH NO FAULTS. ARTIFICIAL HORIZON ALSO TOPPLING IN FLIGHT. 1 L 7 2 3O 3 O 3A25 E8CE 5 C P22EA 2002011400036 20020114 00036 SW 2002 1 14 AUS20011280 1 20011129 G 2720 472105 CONTROL CABLE GULSTM 112 114 7630314 SW LYC O540 IO540T4B5 41532 EA HARTZL HCC2Y HCC2YR1 GL RUDDER MISINSTALLED W K NONE W INADEQUATE Q C IN INSP/MAINT 1 AU S (AUS) LT RUDDER CONTROL CABLE INCORRECTLY ROUTED UNDER SUPPORT BRACKET. CABLE RUBBING ON PULLEY SUPPORT BRACKET. ELEVAT OR TRIM CABLE ALSO INCORRECTLY ROUTED AND FOULING ON STRUCTURE. PERSONNEL/MAINTENANCE ERROR. 1 L 7 1 3O 3 O A12SO 1E4 5 C P920 2002010400043 20020104 00043 EU 2002 1 4 AUS20011281 1 20011127 G 3240 BRAKE PARTEN P68 P68B 6780104 EU LYC O360 IO360A1B6 41514 EA HARTZL HCC2Y HCC2YK2 GL LANDING GEAR BRA MISSING W K NONE O C OTHER F.O.D. TX TAXI/GRND HDL 1 AU S (AUS) AIRCRAFT NOSE SPAT AND PITOT TUBE DAMAGE WHEN AIRCRAFT RAN INTO THE SIDE OF THE HANGAR WHILE BEING TAXIED FOR REFU ELLING. INVESTIGATION FOUND THAT THE PILOT WAS SITTING IN THE RH SEAT AND THAT THE BRAKES HAD BEEN REMOVED FROM THE RH S IDE POSITION. THE REMOVAL OF THE BRAKES HAD NOT BEEN PLACARDED. PERSONNEL/MAINTENANCE ERROR. 1 H 7 2 3O 3 O A31EU 1E10 5 C P920 2002010400044 20020104 00044 NM 2002 1 4 AUS20011282 1 20011124 G 2820 5324 VALVE BOEING 737 7374Q8 138447Q NM CFMINT CFM56 CFM563C 13802 EU AIRCRAFT FUEL DI FOD W K NONE O OTHER CR CRUISE 1 AU S 5324 (AUS) FUEL SYSTEM NON-RETURN VALVE JAMMED OPEN BY FOD CAUSING A FUELIMBALANCE BETWEEN NO1 AND NO2 TANKS. INVESTIGATION F OUND APLASTIC BLANK WAS JAMMING THE VALVE OPEN. SUSPECT FOD WAS A BLANKING CAP FROM BOOST PUMP PRESSURE LINE. BOOST PUMP HAD BEEN REPLACED PRIOR TO RECEIPT BY VIRGIN BLUE. PERSONNEL/MAINTENANCE ERROR. FOD. 2 L 7 2 4F 4 F RT A16WE E21EU 2002011400037 20020114 00037 SO 2002 1 14 AUS20011283 1 20011203 G 5220 40979 DOOR PIPER PA31 PA31350 7103110 SO LYC O540 TIO540J2BD 41532 EA HARTZL HCE3Y HCE3YR2 GL EMERGENCY EXITS SEPARATED W A UNSCHED LANDING D J INFLIGHT SEPARATION WARNING INDICATION CL CLIMB 1 AU S (AUS) CABIN EMERGENCY EXIT DOOR SEPARATED FROM AIRCRAFT. INVESTIGATIONOF THE LATCH MECHANISM FOUND THAT THE LATCH HAD NO T BEEN FULLY ENGAGING FOR A CONSIDERABLE TIME. LATCHES HAD ONLY BEEN CLOSING APPROXIMATELY 30 DEGREES INSTEAD OF THE FUL L 90 DEGREES. CLOSEINSPECTION OF THE HANDLE ASSEMBLY SHOWED THAT IT WAS BENT IN THEAREA WHERE THE VERTICAL TUBE IS WELDE D TO THE BELLCRANK CROSSTUBE RESULTING IN LIMITED TRAVEL OF THE DOOR LATCHES. 1 L 7 2 3O 3 O A20SO E14EA 5 C P33EA 2002011400045 20020114 00045 SO 2002 1 14 AUS20011293 2 20011129 G 8530 EXHAUST VALVE CESSNA 206 U206G 2073356 CE CONT O520 IO520F 17032 SO MCAULY 3A32C D3A32C90 GL NR 1 CYLINDER LEAKING W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) NR 1 CYLINDER EXHAUST VALVE LEAKING PAST VALVE SEAT. 1 H 7 1 3O 3 O A4CE E5CE 5 C P21EA 2002010400047 20020104 00047 EU 2002 1 4 AUS20011294 1 20011209 G 2120 COOLING FAN REIMS 406 F406 7535723 EU PWA PT6 PT6A112 52043 NE MCAULY 3G34C7 3GFR34C701 GL AIR DISTRIBUTION FAILED W K NONE B SMOKE/FUMES/ODORS/SPARKS CL CLIMB 1 AU S (AUS) SURVEILLANCE RADAR COOLING FAN FAILED. 1 L 7 2 3T 3 T RT A54EU E4EA 5 C P60GL 2002010400048 20020104 00048 EU 2002 1 4 AUS20011298 1 20010904 G 3150 1097811 WARNING SYSTEM FOKKER F28 F28MK4000 4990810 EU RROYCE SPEY SPEY55515 54521 EU CENTRAL WARNING FAULTY W K NONE F N FLT CONT AFFECTED FALSE WARNING TO TAKEOFF 1 AU S (AUS) UNSAFE CONFIGURATION WARNING SOUNDED. INVESTIGATION COULD FIND NO CAUSE FOR THE PROBLEM. LH ELEVATOR BYPASS SWITCH CHANGED AS A PRECAUTION. 2 L 7 2 4F 4 F RT A20EU E2EU 2002010400051 20020104 00051 EA 2002 1 4 AUS20011304 2 20011203 G 7322 229164 NOZZLE LYC O320H2AD CESSNA 172 172N 2072434 CE LYC O320 O320H2AD 41508 EA MCAULY 1C160 1C160DTM GL FUEL CONTROL/REC MISSING W K NONE E R VIBRATION/BUFFET PARTIAL RPM/PWR LOSS TO TAKEOFF 1 AU S 501 CK10488V (AUS) CARBURETTOR DISCHARGE NOZZLE MISSING. 1 H 7 1 3O 3 O NT 3A12 E274 5 N P910 2002011400055 20020114 00055 EU 2002 1 14 AUS20011309 1 20011206 G 2731 ACTUATOR REIMS 406 F406 7535723 EU PWA PT6 PT6A112 52043 NE MCAULY 3G34C7 3GFR34C701 GL ELEVATOR TAB CONTAMINATED W O OTHER W INADEQUATE Q C NR NOT REPORTED 1 AU S (AUS) ELEVATOR TRIM TAB ACTUATORS LUBRICATED WITH THE INCORRECT GREASE. ACTUATORS FREEZING IN FLIGHT. MAINTENANCE MANUAL SPECIFIES "TRIBOLUBE" ONLY. PERSONNEL/MAINTENANCE ERROR. UNAPPROVED PART. 1 L 7 2 3T 3 T RT A54EU E4EA 5 C P60GL 2002010400054 20020104 00054 EU 2002 1 4 AUS20011310 1 20011206 G 5343 571304013 CHANNEL REIMS 406 F406 7535723 EU PWA PT6 PT6A112 52043 NE MCAULY 3G34C7 3GFR34C701 GL LANDING GEAR ATT CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) NOSE LANDING GEAR ACTUATOR ATTACHMENT STRUCTURE CHANNEL CRACKED.FOUND DURING INSPECTION IAW AD/F406/7. 1 L 7 2 3T 3 T RT A54EU E4EA 5 C P60GL 2002011400056 20020114 00056 NE 2002 1 14 AUS20011311 2 20011206 G 7420 IGNITION LEAD REIMS 406 F406 7535723 EU PWA PT6 PT6A112 52043 NE MCAULY 3G34C7 3GFR34C701 GL RT ENGINE CHAFED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) RT IGNITER LEAD ON BOTH ENGINES CHAFING ON FUEL LINE TO FLOW DIVIDER. 1 L 7 2 3T 3 T RT A54EU E4EA 5 C P60GL 2002010400055 20020104 00055 WP 2002 1 4 AUS20011318 1 20011211 G 6310 269A55177 BRACKET HUGHES 269 269C 4470504 WP LYC O360 HIO360D1A 41514 EA ENGINE/TRANSMISS CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) LOWER DRIVE PULLEY SUPPORT BRACKET CRACKED. ONE ATTACHMENT LUGSEPARATED. 1 G 7 1 3O 3 O 4H12 1E10 2002010400056 20020104 00056 CE 2002 1 4 AUS20011319 1 20011211 G 7810 265401415 EXHAUST PIPE PWA PT6A114A CESSNA 208 208B 2073701 CE PWA PT6 PT6A114A 52043 NE MCAULY 3AF34C 3GFR34C703 GL ENGINE COLLECTOR CRACKED W K NONE B SMOKE/FUMES/ODORS/SPARKS LD LANDING 1 AU S PCE19248 (AUS) ENGINE PRIMARY EXHAUST DUCT CRACKED AND HOLED. HOLE WAS APPROXIMATELY228.6MM (9IN) BY 146MM (5.75IN). ESCAPING EXH AUSTGAS DAMAGED OIL COOLER SHROUD RUBBERS AND DISCOLOURED THE PAINT ON THE LOWER RH COWL. 1 H 7 1 3T 3 T A37CE E4EA 5 C P60GL 2002011400061 20020114 00061 NE 2002 1 14 AUS20011320 2 20011209 G 7420 CH5339907 IGNITION LEAD BEECH 200 B200C 1152924 CE PWA PT6 PT6A42 52043 NE ENGINE SHORTED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) IGNITER LEAD INSULATION SHORT. 1 L 7 2 4T 4 T A24CE E4EA 2002011400062 20020114 00062 EU 2002 1 14 AUS20011324 1 20010811 G 2421 WARNING SYSTEM FOKKER F28 F28MK1000 4990808 EU RROYCE SPEY SPEY55515 54521 EU AC GENERATOR FALSE ACTIVATION W A UNSCHED LANDING N FALSE WARNING CR CRUISE 1 AU S (AUS) NR 2 GENERATOR HIGH INLET TEMPERATURE. INVESTIGATION COULD FIND NO CAUSE FOR THE PROBLEM. PLUGS AND CONNECTORS CLE ANED. 2 L 7 2 4F 4 F RT A20EU E2EU 2002011400066 20020114 00066 NM 2002 1 14 AUS20011330 1 20011123 G 6210 BLADE ROBSIN R22 R22MARINER 7640115 NM LYC O320 O320B2C 41508 EA MAIN ROTOR CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) MAIN ROTOR BLADES SUSPECT CRACKED. 1 G 7 1 3O 3 O H10WE E274 2002010400059 20020104 00059 EA 2002 1 4 AUS20011331 2 20010903 G 7414 10357584 GEAR LYC O320B2C ROBSIN R22 R22BETA 7640110 NM LYC O320 O320B2C 41508 EA MAGNETO/DISTRIBU BROKEN W K NONE O OTHER IN INSP/MAINT 1 AU S 400 (AUS) MAGNETO GEAR TEETH BROKEN. 1 G 7 1 3O 3 O H10WE E274 2002011400067 20020114 00067 CE 2002 1 14 AUS20011336 1 20011210 G 2450 7270530 CIRCUIT BREAKER CESSNA 208 208B 2073701 CE PWA PT6 PT6A114A 52043 NE MCAULY 3AF34C 3GFR34C703 GL AC DISTRIBUTION FAILED W O OTHER B J SMOKE/FUMES/ODORS/SPARKS WARNING INDICATION CR CRUISE 1 AU S (AUS) NR 1 AVIONICS BUS CIRCUIT BREAKER/SWITCH INTERNAL FAILURE. 1 H 7 1 3T 3 T A37CE E4EA 5 C P60GL 2002011400068 20020114 00068 CE 2002 1 14 AUS20011337 1 20011211 G 2820 314200 VALVE BEECH 58 58 1152740 CE CONT O520 IO520C 17032 SO FUEL DIST CORRODED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) FUEL SYSTEM CHECK VALVE EXCESSIVELY CORRODED AND CONTAMINATED DUE TO WATER IN FUEL CROSSFEED LINE. 1 L 7 2 3O 3 O 3A16 E5CE 2002011400069 20020114 00069 CE 2002 1 14 AUS20011338 1 20011211 G 2820 60292000031 LINE BEECH 58 58 1152740 CE CONT O520 IO520C 17032 SO FUEL DIST CORRODED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) FUEL LINE EXCESSIVELY COORODED DUE TO WATER CONTAMINATION. 1 L 7 2 3O 3 O 3A16 E5CE 2002011400070 20020114 00070 CE 2002 1 14 AUS20011340 1 20011211 G 2450 70HF10 DIODE BEECH 200 B200C 1152924 CE PWA PT6 PT6A42 52043 NE AC POWER DIST FAILED W O OTHER G MULTIPLE FAILURE TX TAXI/GRND HDL 1 AU S (AUS) NR 2 BUS SYSTEM FEED DIODES FAILED. 1 L 7 2 4T 4 T A24CE E4EA 2002011400071 20020114 00071 SO 2002 1 14 AUS20011341 1 20011214 G 5342 553266 BOLT PIPER PA34 PA34200T 7103406 SO CONT O360 TSIO360E 17025 SO HARTZL HCC2Y BHCC2YF2 GL HORIZONTAL STAB BROKEN W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) STABILISER ATTACHMENT FITTING BOLTS BENT (2OFF) AND BROKEN(2OFF). INVESTIGATION FOUND THAT THE BOLTS WERE THE INCO RRECT TYPE. THE PART NUMBER OF THE INCORRECT BOLTS WAS PNO NAS425-3-7.UNAPPROVED PART. PERSONNEL/MAINTENANCE ERROR. 1 L 7 2 3O 3 O A7SO E9CE 5 C P920 2002011400075 20020114 00075 SO 2002 1 14 AUS20011347 2 20011211 G 8530 639272P1O CYLINDER BEECH 55 95C55 1152708 CE CONT O520 IO520C 17032 SO MCAULY 3AF32C 3AF32C75 GL RT ENGINE SEPARATED W A UNSCHED LANDING E VIBRATION/BUFFET CR CRUISE 1 AU S 456 (AUS) RT ENGINE NR 4 CYLINDER AND PISTON SEPARATED IN FLIGHT. RT ENGINE COWL SEPARATED ALONG HINGE. 1 L 7 2 3O 3 O 3A16 E5CE 5 C P22EA 2002011400078 20020114 00078 NE 2002 1 14 AUS20011350 1 20011212 G 6210 7615009000046 BLADE SKRSKY S76 S76A 8143006 NE ALLSN 250C 250C30 03013 GL MAIN ROTOR CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) MAIN ROTOR BLADE CRACKED. 1 G 7 2 3U 3 U H1NE E1GL 2002010400067 20020104 00067 EA 2002 1 4 AUS20011357 2 20011214 G 7414 104001678 CAM BENDIX S6LN1227 BNORM BN2 BN2A20 1520220 EU LYC O540 IO540K1B5 41532 EA HARTZL HCC2Y HCC2YK2 GL MAGNETO/DISTRIBU FAILED W K NONE O OTHER IN INSP/MAINT 1 AU S C0891 (AUS) MAGNETO CAM PIVOT PIN HAD EXCESSIVE PLAY. PIN HAD APPROXIMATELY 0.508MM (0.020IN) OF PLAY. MAXIMUM PLAY 0.3556MM ( 0.014IN). 1 H 7 2 3O 3 O A17EU 1E4 5 C P920 2002011400085 20020114 00085 CE 2002 1 14 AUS20011361 1 20011213 G 3260 574122215 HOOK CESSNA 441 441 2076020 CE LT MLG UPLOCK FAILED W C ABORTED TAKEOFF O OTHER TO TAKEOFF 1 AU S (AUS) LT MAIN LANDING GEAR UPLOCK HOOK FAILED AT PIVOT POINT. 1 L 7 2 3T RT A28CE 2002011400088 20020114 00088 2002 1 14 AUS20011365 4 20011218 G 2350 IU396002 AUDIO PANEL DHAV DHC6 DHC6300 2802606 EA PWA PT6 PT6A27 52043 EA HARTZL HCB3T HCB3TN3 GL COCKPIT FAILED W A UNSCHED LANDING B SMOKE/FUMES/ODORS/SPARKS CL CLIMB 1 AU S 1446 (AUS) AUDIO PANEL FAILED. SUSPECT INTERNAL TRANSFORMER BURNT. 1 H 7 2 3T 4 T RT A9EA E4EA 6 C P15EA 2002011400089 20020114 00089 EU 2002 1 14 AUS20011366 1 20011121 G 5523 BURKLIN12H3668 CAP GROB G115 G115C 1660303 EU LYC O360 O360A1F6 41514 EA HARTZL HCF2Y HCF2YR1 GL ELEVATOR DISLODGED W O OTHER F FLT CONT AFFECTED LD LANDING 1 AU S (AUS) ELEVATOR BALANCE HORN BLANKING CAP DISLODGED AND RESTRICTED ELEVATOR MOVEMENT. FOD. 1 L 7 1 3O 3 O NT A57EU E286 5 C P27EA 2002011400091 20020114 00091 EA 2002 1 14 AUS20011369 2 20011218 G 8530 IO540K1B5 ROCKER GIPPLD GA200 GA200 EU LYC O540 IO540K1B5 41532 EA HARTZL HCC2Y HCC2YR1 GL ENGINE MISINSTALLED W K NONE W INADEQUATE Q C IN INSP/MAINT 1 AU S (AUS) ENGINE ROCKER COVER GASKETS INCORRECTLY FITTED. FOLLOWING REMOVAL OF THE ROCKER COVERS IT WAS FOUND THAT THE ROCKE RS WERE ALSO INCORRECTLY FITTED. SOME INLET ROCKERS WERE FITTED TO EXHAUST POSITIONS AND VICE VERSA. NR 5 CYLINDER EXHAU ST VALVE ALSO HAD EXCESSIVE CLEARANCE OF 3.2MM (0.126IN) WHEN THE RECOMMENDED CLEARANCE WAS BETWEEN 0.711MM (0.028IN) AN D 2.032MM (0.080IN).THE ENGINE HAD JUST BEEN RECEIVED FROM OVERHAUL AND WAS BEING BUILT UP TO QEC STATUS. PERSONNEL/MAIN TENANCE ERROR. 1 L 7 1 3O 3 O NC A00001LA 1E4 5 C P920 2002020500150 20020205 00150 EA 2002 2 5 AUS20011373 2 20011218 G 8520 SL13885M10 BEARING LYC IO720B1B GULSTM 680 680FL 0141608 SW LYC O720 IO720B1B 41546 EA HARTZL HCB3Z HCB3Z302 GL RECIPROCATING EN DELAMINATED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) ENGINE NO1 MAIN BEARING DELAMINATED. METAL CONTAMINATION OF OIL FILTER. 1 H 7 2 3O 3 O 2A4 1E15 5 C P907 2002020500152 20020205 00152 SO 2002 2 5 AUS20011375 1 20011219 G 3213 AN3104 NUT PIPER PA34 PA34200 7103405 SO LYC O360 IO360C1E6 41514 EA HARTZL HCC2Y HCC2YK2 GL MAIN LANDING GEA MISSING W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) LH MAIN LANDING GEAR TORQUE LINK CONNECTING BOLT NUT MISSING. 1 L 7 2 3O 3 O A7SO 1E10 5 C P920 2002020500153 20020205 00153 SO 2002 2 5 AUS20011376 2 20011219 G 7414 103493504 MAGNETO CONT IO520F CESSNA 207 207 2073602 CE CONT O520 IO520F 17032 SO MCAULY D3A34 D3A34C404 GL MAGNETO/DISTRIBU WORN W K NONE O OTHER IN INSP/MAINT 1 AU S 807 (AUS) RH MAGNETO COUPLING PINS WORN EXCESSIVELY. 1 H 7 1 3O 3 O A16CE E5CE 5 C P47GL 2002020500154 20020205 00154 SO 2002 2 5 AUS20011378 1 20011214 G 3213 6531904 CYLINDER PIPER PA28 PA28161 7102803 SO LYC O320 O320D3G 41508 EA SNSNCH 74D 74DM EA MAIN LANDING GEA BROKEN W K NONE O OTHER LD LANDING 1 AU S (AUS) AFTER A HEAVY LANDING THE LH LANDING GEAR WAS FOUND TO BE LOWER THAN THE RH GEAR AND SITTING AT AN ODD ANGLE. INVE STIGATION FOUND THAT THE LH MAIN LANDING GEAR CYLINDER TORQUE LINK ATTACHMENT LUGS BROKEN OFF. 1 L 7 1 3O 3 O 2A13 E274 5 N P88614 2002020500155 20020205 00155 EA 2002 2 5 AUS20011379 2 20011212 G 8520 LW11021 BEARING LYC IO540E1B5 GULSTM 500 500U 0141108 SW LYC O540 IO540E1B5 41532 EA HARTZL HCA3X HCA3XK2 GL RECIPROCATING EN DELAMINATED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) NO3 MAIN BEARING SHELL DELAMINATED AND SHEDDING LARGE FLAKES OF BEARING MATERIAL. METAL CONTAMINATION OF OIL FILTE R. BEARING HADA MANUFACTURERS STAMP (ML-KS) DATE 2-00. 1 H 7 2 3O 3 O 6A1 1E4 5 C P913 2002020500156 20020205 00156 EA 2002 2 5 AUS20011380 2 20011218 G 7414 104001678 CAM BENDIX 10349370A PIPER PA32 PA32300 7103212 SO LYC O540 IO540K1A5 41532 EA HARTZL HCC2Y HCC2YK1 GL MAGNETO/DISTRIBU WORN W K NONE O OTHER IN INSP/MAINT 1 AU S D299916FR (AUS) MAGNETO IMPULSE CAM PAWL PIVOTS WORN TO LIMITS. 1 L 7 1 3O 3 O A3SO 1E4 5 C P920 2002020500157 20020205 00157 SO 2002 2 5 AUS20011382 2 20011010 G 8530 646640 EXHAUST VALVE CONT IO360K CESSNA 172 R172K 2072431 CE CONT O360 IO360K 17025 SO MCAULY 2A34C 2A34C203 GL RECIPROCATING EN WORN W K NONE E VIBRATION/BUFFET NR NOT REPORTED 1 AU S 1459 (AUS) EXHAUST VALVE GUIDE WORN EXCESSIVELY. INVESTIGATION FOUND SPRINGCAP RIDING UP ON VALVE AND CONTACTING ROCKER ARM D UE TO WORNCOLLETS. 1 H 7 1 3O 3 O 3A17 E1CE 5 C P3EA 2002020600003 20020206 00003 CE 2002 2 6 AUS20011384 1 20011205 G 7810 31015828 EXHAUST STACK CESSNA 441 441 2076020 CE GARRTT TPE331 TPE3318 01514 WP HARTZL HCB3T HCB3TN5 GL ENGINE CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) ENGINE EXHAUST DUCT CRACKED AT AFT FLANGE ATTACHMENT WELD. 1 L 7 2 3T 4 T RT A28CE E4WE 6 C P15EA 2002020500158 20020205 00158 CE 2002 2 5 AUS20011385 1 20011130 G 7430 C2925010100 IGNITION SWITCH CONT IO520F CESSNA 206 U206G 2073356 CE CONT O520 IO520F 17032 SO MCAULY 3A32C D3A32C90 GL IGNITION SWITCHI WORN W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) IGNITION SWITCH TERMINALS WORN BEYOND LIMITS. 1 H 7 1 3O 3 O A4CE E5CE 5 C P21EA 2002020600004 20020206 00004 CE 2002 2 6 AUS20011386 1 20011218 G 3260 GE327 BULB CESSNA 340 340CESSNA 2076404 CE CONT O520 TSIO520K 17040 SO MCAULY 3AF32C 3AF32C87 GL MLG INDICATOR BURNED OUT W O OTHER P NO WARNING INDICATION LD LANDING 1 AU S (AUS) NOSE LANDING GEAR DOWN AND LOCKED LIGHT BULBS (2OFF) BLOWN. 1 L 7 2 3O 3 O 3A25 E8CE 5 C P22EA 2002020600006 20020206 00006 EA 2002 2 6 AUS20011388 2 20011227 G 7321 312275805 FUEL CONTROL AGUSTA A109 A119 0261102 EU PWA PT6 PT6B36 52043 EA ENGINE CONTAMINATED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) FUEL CONTROL UNIT CONTAMINATED WITH BRONZE PARTICLES. 1 G 7 2 3U 4 U H7EU E4EA 2002020600008 20020206 00008 WP 2002 2 6 AUS20011390 1 20011211 G 7921 111F4178D0440 HOSE GARRTT TPE3316252M FLTCHR 24 FU24AIRPTS 3530202 WP GARRTT TPE331 TPE3316252M 01514 NE ENG OIL COOLER DETERIORATED W O OTHER E K VIBRATION/BUFFET FLUID LOSS NR NOT REPORTED 1 AU S (AUS) ENGINE OIL COOLER FAILED FROM OVER-PRESSURISATION. INVESTIGATION FOUND PARTICLES OF RUBBER IN THE OIL COOLER BLOCK ING THE RETURN OIL FLOW TO THE OIL TANK. THE RUBBER PARTICLES APPEAR TO HAVE COME FROM INTERNAL FAILURE OF OIL HOSE PNO 111F417-8D0440. THE BLOCKAGE OF THE OIL COOLER CAUSED AN OVER-PRESSURISATION OF APPROXIMATELY 300 PSI. 1 L 7 1 3O 4A12 E2WE 2002020600009 20020206 00009 WP 2002 2 6 AUS20011393 2 20011227 G 8530 802 EXHAUST VALVE DHAVXX DH82 DH82AROBRTSN 2801002 WP DHAVXX GIPSY GIPSYMAJOR1 20004 WP NR 2 CYLINDER FAULTY W O OTHER E VIBRATION/BUFFET NR NOT REPORTED 1 AU S (AUS) NR 2 CYLINDER EXHAUST VALVE FAULTY. 1 Q 7 1 3I 3 I A8EU A8EU 2002020500161 20020205 00161 EA 2002 2 5 AUS20011394 2 20011217 G 7414 10401678 CAM BENDIX S6LN1227 BNORM BN2 BN2A20 1520220 EU LYC O540 IO540K1B5 41532 EA HARTZL HCC2Y HCC2YK2 GL MAGNETO/DISTRIBU WORN W K NONE O OTHER IN INSP/MAINT 1 AU S K069918FR (AUS) MAGNETO IMPULSE CAM WORN BEYOND LIMITS. 1 H 7 2 3O 3 O A17EU 1E4 5 C P920 2002020500162 20020205 00162 EU 2002 2 5 AUS20011395 1 20011113 G 2742 ACTUATOR FOKKER F28 F28MK4000 4990810 EU RROYCE SPEY SPEY55515 54521 EU STABILIZER ACTUA FAILED W K NONE F FLT CONT AFFECTED CR CRUISE 1 AU S (AUS) STABILISER ACTUATOR FAILED. 2 L 7 2 4F 4 F RT A20EU E2EU 2002020500163 20020205 00163 EU 2002 2 5 AUS20011396 1 20011116 G 2742 ACTUATOR FOKKER F28 F28MK4000 4990810 EU RROYCE SPEY SPEY55515 54521 EU STABILIZER ACTUA FAULTY W K NONE F J FLT CONT AFFECTED WARNING INDICATION CL CLIMB 1 AU S (AUS) STABILISER ACTUATOR SUSPECT FAULTY. 2 L 7 2 4F 4 F RT A20EU E2EU 2002020500166 20020205 00166 SW 2002 2 5 AUS20011399 1 20010826 G 2510 206031121023 WEB BELL 206L3 BELL 206 206L3 1182108 SW ALLSN 250C 250C30 03013 GL FLIGHT COMPARTME CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) COPILOTS SEAT WEB CRACKED. 1 G 7 1 3U 3 U H2SW E1GL 2002020600011 20020206 00011 EU 2002 2 6 AUS20011400 1 20010804 G 2821 CLAMP BNORM BN2 BN2A26 1520226 EU GASCOLATOR MISMANUFACTURED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) GASCOLATOR FILTER BOWL UNSECURELY CLAMPED. INVESTIGATION FOUND INADEQUATE DEPTH OF HOLE PREVENTED FULL ENGAGEMENT OF ONE LEG OFTHE SADDLE CLAMP. 1 H 7 2 3O A17EU 2002020600013 20020206 00013 WP 2002 2 6 AUS20011402 2 20010616 G 7261 31080261 SCAVENGE PUMP SWRNGN SA227 SA227* SW GARRTT TPE331 TPE33112UHR WP ENGINE SEIZED W O OTHER E K VIBRATION/BUFFET FLUID LOSS CR CRUISE 1 AU S 2521 (AUS) RT ENGINE TURBINE SCAVENGE PUMP SHAFT SEIZED AND TEETH STRIPPED FROM SCAVENGE PUMP GEAR PNO 3108028-1 AND DRIVESHA FT SPUR GEARPNO 3102270-4. 2 L 7 2 4T 4 T RT A5SW E4WE 2002020600014 20020206 00014 CE 2002 2 6 AUS20011403 1 20011129 G 7120 121343316 MOUNT CESSNA 206 U206F 2073333 CE CONT O520 IO520* 17032 SO ENGINE CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) LT AND RT REAR ENGINE MOUNT SUPPORT BRACKETS CRACKED FROM REAR INBOARD BEND RADIUS. NUMEROUS RIVETS IN SURROUNDING STRUCTURE FRETTING. 1 H 7 1 3O 3 O A4CE E5CE 2002020500167 20020205 00167 SW 2002 2 5 AUS20011404 1 20011123 G 5521 206023119007 SPAR BELL 206 206L3 1182108 SW ELEVATOR, SPAR/R CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S 6357 AO00972 (AUS) ELEVATOR SPAR CRACKED. CRACK LENGTH 82.5MM (3.25IN). 1 G 7 1 3U H2SW 2002020600015 20020206 00015 EA 2002 2 6 AUS20011405 2 20011126 G 7250 BLADE DHAV DHC6 DHC6200 2802620 EA PWA PT6 PT6A20 52043 EA HARTZL HCB3T HCB3TN3 GL TURBINE SECTION FAILED W A UNSCHED LANDING E VIBRATION/BUFFET CL CLIMB 1 AU S (AUS) LT ENGINE INTERNAL FAILURE. INITIAL REPORTS INDICATE POWER TURBINE BLADE FAILURE. 1 H 7 2 3T 3 T RT A9EA E4EA 6 C P15EA 2002020600016 20020206 00016 SO 2002 2 6 AUS20011406 1 20010721 G 3242 PBA920 PAD EMB 110 EMB110* SO BRAKE MISSING W K NONE O OTHER IN INSP/MAINT 1 AU S 2564 (AUS) BRAKE PRESSURE PLATE WORN. BOTH BRAKE PADS ON PRESSURE PLATE MISSING. SUSPECT PAD HAD SEPARATED FROM PLATE CAUSING THE OTHER PAD TO SEPARATE AS WELL. 1 L 7 2 4T RT A21SO 2002020500168 20020205 00168 EU 2002 2 5 AUS20011407 1 20010723 G 2410 CSD FOKKER F28 F28MK4000 4990810 EU RROYCE SPEY SPEY55515 54521 EU ALTERNATOR-GENER DISCONNECTED W K NONE J WARNING INDICATION CR CRUISE 1 AU S (AUS) NO1 CONSTANT SPEED DRIVE (CSD) DISCONNECTED IN FLIGHT. 2 L 7 2 4F 4 F RT A20EU E2EU 2002020500169 20020205 00169 EU 2002 2 5 AUS20011408 1 20010727 G 2163 LINE FOKKER F28 F28MK4000 4990810 EU RROYCE SPEY SPEY55515 54521 EU CABIN TEMPERATUR LEAKING W K NONE O J OTHER WARNING INDICATION CR CRUISE 1 AU S (AUS) TURBINE BYPASS VALVE DOWNSTREAM SENSE LINE LEAKING. 2 L 7 2 4F 4 F RT A20EU E2EU 2002020500170 20020205 00170 EA 2002 2 5 AUS20011411 2 20011215 G 8520 13F17751 CRANKSHAFT LYC LTIO540J2BD PIPER PA31 PA31350 7103110 SO LYC O540 LTIO540J2BD 41533 EA HARTZL HCE3Y HCE3YR2 GL RECIPROCATING EN SHEARED W K NONE E VIBRATION/BUFFET CR CRUISE 1 AU S L209668A (AUS) ENGINE CRANKSHAFT SHEARED AT NO6 BEARING JOURNAL. INTERNAL DAMAGE TO ENGINE. 1 L 7 2 3O 3 O A20SO E14EA 5 C P33EA 2002020500171 20020205 00171 CE 2002 2 5 AUS20011412 1 20011224 G 7160 265895716 LEVER PWA PT6A114A CESSNA 208 208B 2073701 CE PWA PT6 PT6A114A 52043 NE MCAULY 3AF34C 3GFR34C703 GL ENGINE AIR INTAK CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) ENGINE INERTIAL SEPARATOR SELECTION LEVER CRACKED AT MID POINT. 1 H 7 1 3T 3 T A37CE E4EA 5 C P60GL 2002020600018 20020206 00018 EU 2002 2 6 AUS20011415 1 20010811 G 3620 INDICATOR FOKKER F28 F28MK1000 4990808 EU RROYCE SPEY SPEY55515 54521 EU PNEUMATIC SYS STUCK W O OTHER J WARNING INDICATION CL CLIMB 1 AU S (AUS) NR 1 HIGH PRESSURE VALVE SWITCH INDICATOR STICKING. 2 L 7 2 4F 4 F RT A20EU E2EU 2002020600032 20020206 00032 WP 2002 2 6 AUS20011439 2 20011224 G 7261 31032173 HOUSING CESSNA 441 441 2076020 CE GARRTT TPE331 TPE3318 01514 WP HARTZL HCB3T HCB3TN5 GL ENG OIL PUMP CRACKED W O OTHER K J FLUID LOSS WARNING INDICATION CR CRUISE 1 AU S (AUS) ENGINE OIL PUMP HOUSING CRACKED. 1 L 7 2 3T 4 T RT A28CE E4WE 6 C P15EA 2002020600033 20020206 00033 SO 2002 2 6 AUS20011440 2 20011224 G 8530 CYLINDER BEECH 55 E55 1152732 CE CONT O520 IO520C 17032 SO MCAULY 2AF34C 2AF34C55 GL ENGINE CRACKED W O OTHER E F VIBRATION/BUFFET FLT CONT AFFECTED CR CRUISE 1 AU S 636 (AUS) RT ENGINE NR 2 AND NR 4 CYLINDERS CRACKED IN AREA OF HEAD / BARRELJOINT. 1 L 7 2 3O 3 O 3A16 E5CE 5 C P5EA 2002020500178 20020205 00178 SO 2002 2 5 AUS20011441 2 20011224 G 8530 CONNECTING ROD CONT GTSIO520M CESSNA 404 404CESSNA 2075901 CE CONT O520 GTSIO520M 17032 SO MCAULY 3FF32 3FF32C501 GL RECIPROCATING EN FAILED W K NONE E VIBRATION/BUFFET CL CLIMB 1 AU S 127 (AUS) NO5 CONNECTING ROD FAILED. NO1, NO2 AND NO4 MAIN BEARINGS OVERHEATED. SIGNS OF OVERHEATING ON ALL BIGEND BEARINGS. INVESTIGATION INDICATES INCORRECT MACHINING OF CRANKCASE OILPASSAGES IN MAIN BEARING SUPPORT. 1 L 7 2 3O 3 O A25CE E7CE 5 C P45GL 2002020600051 20020206 00051 NM 2002 2 6 AUS20011445 1 20010326 G 2432 18850 BATTERY BOEING 767 767300 1385204 NM RROYCE RB211 RB211524* NE MAIN OVERHEATED W O OTHER M J OVER TEMP WARNING INDICATION NR NOT REPORTED 1 AU S (AUS) MAIN BATTERY OVERHEATED. INVESTIGATION COULD FIND NO CAUSE FOR THE DEFECT AND THE BATTERY HAS OPERATED OK SINCE. T HE BATTERY CHARGER WAS ALSO REMOVED FOR TESTING WITH NO FAULT FOUND. 2 L 7 2 4F 4 F RT A1NM E12EU 2002020500180 20020205 00180 EA 2002 2 5 AUS20011446 1 20011208 G 3213 BLOCK DHAV DHC6 DHC6300 2802606 EA MAIN LANDING GEA FAILED W K NONE O OTHER LD LANDING 1 AU S (AUS) RH MAIN LANDING GEAR COMPRESSION BLOCKS FAILED. DAMAGE CAUSED TOTHE FUSELAGE LOCATED INBOARD OF THE RH MLG. 1 H 7 2 3T RT A9EA 2002020600053 20020206 00053 EU 2002 2 6 AUS20011451 2 20010611 G 7250 BLADE FOKKER F28 F28MK1000 4990808 EU RROYCE SPEY SPEY55515 54521 EU TURBINE SECTION DAMAGED W C ABORTED TAKEOFF E R J VIBRATION/BUFFET PARTIAL RPM/PWR LOSS WARNING INDICATION TO TAKEOFF 1 AU S (AUS) NR 1 ENGINE HP TURBINE BLADES (6OFF) DAMAGED. 2 L 7 2 4F 4 F RT A20EU E2EU 2002020600056 20020206 00056 EA 2002 2 6 AUS20011452 2 20011212 G 8530 LW13820 CONNECTING ROD LYC O360 O360A4M 41514 EA NR 2 CYLINDER MISMANUFACTURED W K NONE W INADEQUATE Q C IN INSP/MAINT 1 AU S 120 (AUS) FOLLOWING BULK STRIP DUE TO FAILURE OF THE NR 2 CYLINDER CONNECTING ROD IT WAS FOUND THAT THE OIL GALLERY SUPPLYIN G NR 2 MAIN BEARING WAS NOT DRILLED INTO THE MAIN OIL GALLERY. 3 O E286 2002020600057 20020206 00057 NE 2002 2 6 AUS20011453 2 20010112 G 7230 9380M28P05 COMPRESSOR GE CF6 CF680C2B6 30025 NE ENGINE CRACKED W K NONE O OTHER IN INSP/MAINT 1 AU S 6513 (AUS) HPC ROTOR SPOOL 3-9 GAVE CRACK INDICATIONS DURING ULTRASONIC INSPECTION IAW EI GEN-072-1792R05. FURTHER INSPECTION AT MANUFACTURER FOLLOWING ENGINE STRIP COULD NOT CONFIRM THE CRACKING. 4 F E13NE 2002020500183 20020205 00183 SW 2002 2 5 AUS20011454 1 20011228 G 3222 AN723 BOLT SCOTT CITABRIATYP BBAVIA 7 7GCAA 21101N8 SW LYC O320 O320A2D 41508 EA AMTR C8289 C8289 GL NOSE/TAIL LANDIN FAILED W K NONE O OTHER TX TAXI/GRND HDL 1 AU S (AUS) TAIL WHEEL ATTACHMENT BOLT FAILED. TAIL WHEEL SEPARATED FROM TAIL LEAF SPRING. 1 H 7 1 3O 3 O A759 E274 5 N EXPP5N 2002020500184 20020205 00184 SW 2002 2 5 AUS20011455 1 20011217 G 6320 2060401223 GEAR BELL 206040002025 BELL 206 206B 1181511 SW ALLSN 250C 250C20 03013 GL MAIN ROTOR GEARB DAMAGED W K NONE J WARNING INDICATION CR CRUISE 1 AU S 707 BKW841 (AUS) MAIN TRANSMISSION SUN GEAR TEETH (2OFF) CHIPPED WITH SUBSTANTIALSECONDARY DAMAGE. METAL CONTAMINATION OF TRANSMISS ION. SUSPECTPNO 206-040-122-3 GEAR IS NOT TO BE USED IN A PNO 206-040-002-025 MODEL TRANSMISSION AS PER TB 206-75-12. 1 G 7 1 3U 3 U H2SW E4CE 2002020500185 20020205 00185 SO 2002 2 5 AUS20011456 1 20011219 G 5753 RIB PIPER PA28 PA28140 7102802 SO LYC O320 O320E2A 41508 EA SNSNCH 74DM M74DM EA TRAILING EDGE FL CORRODED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) LH AND RH FLAP NOSE RIBS SEVERELY CORRODED. SUSPECT CAUSED BY DISSIMILAR METAL CONTACT BETWEEN RIBS AND HINGE BRAC KETS. CORROSION WAS ALSO FOUND ON THE LOWER RUDDER RIB WHERE IT CONTACTED THE CONTROL HORN (DISSIMILAR METALS CORROSION) . THE LOWER SECTION OF THE FIN AND ON THE TOP FUSELAGE SKIN UNDER THE FIN ALSO CONTAINS CORROSION. THE CORROSION ON THE FUSELAGE SKIN AND IN THE FIN WAS CAUSED PRIMARILY BY THE ACCUMULATION OF DEBRIS IN THE LOWER HALF OF THE FIN (MUD, WASPS NESTS) THAT ALLOWEDPROLONGED MOISTURE CONTACT IN THIS AREA. THE AIRCRAFT IS LOCATEDIN A CORROSIVE SEACOAST ENVIRONMENT. 1 L 7 1 3O 3 O 2A13 E274 5 N P88614 2002020500186 20020205 00186 SO 2002 2 5 AUS20011457 1 20011219 G 5711 SPAR PIPER PA28 PA28140 7102802 SO LYC O320 O320E2A 41508 EA SNSNCH 74DM M74DM EA WING SPAR CORRODED W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) LH AND RH WING REAR SPAR ATTACHMENT POINTS CORRODED AS DESCRIBEDIN AD/PA28/40. INSPECTION WAS CARRIED OUT IAW AD/P A28/40 WHICHWAS NOT DUE FOR ANOTHER TWO YEARS. 1 L 7 1 3O 3 O 2A13 E274 5 N P88614 2002020600058 20020206 00058 SW 2002 2 6 AUS20011458 1 20011220 G 2560 BL7505 CABLE BELL 407 407 1182206 SW ALLSN 250C 250C47B GL RESCUE HOIST FAILED W O OTHER D INFLIGHT SEPARATION HO HOVERING 1 AU S (AUS) RESCUE HOIST CABLE BROKE IN AN AREA APPROXIMATELY 100MM (4IN) ABOVE RESCUE HOOK ATTACHMENT POINT. 1 G 7 1 3U 3 U O H2SW E1GL 2002020500187 20020205 00187 SO 2002 2 5 AUS20011459 2 20011212 G 8530 EXHAUST VALVE CONT TSIO520VB CESSNA 402 402C 207590R CE CONT O520 TSIO520VB 17040 SO MCAULY 3AF32C 3AF32C505 GL RECIPROCATING EN LEAKING W K NONE O OTHER IN INSP/MAINT 1 AU S (AUS) ENGINE EXHAUST VALVE LEAKING DURING COMPRESSION TEST. 1 L 7 2 3O 3 O A7CE E8CE 5 C P22EA 2002020500188 20020205 00188 NE 2002 2 5 AUS20011460 3 20011202 G 6110 2D30 PROPELLER HAMSTD 2D30 SCWZER G164 G164A 3952704 EA PWA R985 R985AN1 52008 NE HAMSTD 2D 2D30 NE PROPELLER ASSEMB FAULTY W K NONE O OTHER IN INSP/MAINT 1 AU S 119789 (AUS) THE FOLLOWING DEFECTS WERE FOUND ON THE PROPELLER WHEN RECEIVED FOR OVERHAUL:-1. ZERO BEARING TENSION ON BOTH BLAD ES2. REAR BARREL HALF HAS BEEN DRILLED, TAPPED AND GREASE NIPPLES FITTED. NO CERTIFICATION COULD BE FOUND TO SUBSTANTIA TE THIS MODIFICATION WHICH HAD BEEN CARRIED OUT WHEN THE PROPELLER WASDISMANTLED AS THE BARREL HALF HAD BEEN REPLATED AF TER THE MODIFICATION HAD BEEN CARRIED OUT 3. NON-MATCHING PART NUMBER BLADES FITTED 4. EXCESSIVE WEAR IN CYLINDER COUNT ERWEIGHTBUSH BORESPERSONNEL/MAINTENANCE ERROR. UNAPPROVED MODIFICATION. 1 Q 7 1 3R 3 R 1A16 5E1 5 C P206 2002020600059 20020206 00059 2002 2 6 AUS20011463 4 20011228 G 2210 0119244TF CONTROLLER BNORM BN2 BN2B20 1520302 EU LYC O540 IO540K1B5 41532 EA HARTZL HCC2Y HCC2YK2 GL AUTOPILOT SYSTEM FAULTY W O OTHER O OTHER NR NOT REPORTED 1 AU S (AUS) AUTOPILOT CONTROL PROGRAMMER FAULTY. 1 H 7 2 3O 3 O A17EU 1E4 5 C P920 2001080200272 20010802 00272 2001 8 2 B3OR20010003 4 20010130 G 2215 10150004717 SERVO BEECH 200 C12C CE ELEVATOR BINDING B B3OR A UNSCHED LANDING F E FLT CONT AFFECTED VIBRATION/BUFFET CR CRUISE 1 SW 03 1553 BC30 DURING A FLIGHT, THE PILOT EXPERIENCED SLUGGISH ELEVATOR CONTROL WHEEL MOVEMENT. ELEVATOR CONTROL WOULD MOVE FREELY IN N OSE UP DIRECTION BUT THE MOVEMENT IN THE NOSE DOWN DIRECTION WOULD SOMETIMES BE HARD TO MOVE AND THEN EASY TO MOVE. THIS CAUSED SEVERE PITCH OSCILLATION. PILOT FOUND THAT IF HE MOVED THE CONTROL SLOWLY, ALL WAS OK. AIRCRAFT LANDED WITHOUT I NCIDENT. INVESTIGATION FOUND THE ELEVATOR AUTOPILOT SERVO INTERMITENTLY LOCKING UP IN THE THE NOSE DOWN DIRECTION CAUSIN G THE PILOT TO HAVE TO FIGHT THE SERVO CLUTCH. REPLACED SERVO MOTOR. ALTHOUGH THIS IS A MILITARY AIRCRAFT, THE SAME SERV O IS INSTALLED IN OTHER RAYTHEON A200 AIRCRAFT. 1 L 7 2 4T A24CE 2001080200273 20010802 00273 EU 2001 8 2 B3OR20010004 1 20010621 G 7722 0301037070 THERMOCOUPLE SNIAS 350 AS350B2 8680813 EU TMECA ARRIEL ARRIEL1D NE ENGINE OUT OF TOLERANCE B B3OR E ENGINE SHUTDOWN R PARTIAL RPM/PWR LOSS TX TAXI/GRND HDL 1 SW 03 5204X 802 20 3099 9570 AIRCRAFT HAD SUFFERED A SERIES OF HUNG STARTS, ENGINE WOULD HANG UP AT 30%. IF THE ENGINE WOULD START, IT WOULD BE A SLO W START. USUALLY, THE PILOT WOULD REACH THE STARTER TIME LIMIT OF 45 SEC'S BEFORE THE ENGINE WOULD START AND BE SELF-SUS TAINING,AND HE WOULD HAVE TO ABORT THE START SEQUENCE. TROUBLE SHOOTING FOUND THE INJECTORS WERE "DRIBBLEING" FUEL INSTE AD OF A SMOOTH,EVEN,FAN PATTERN. CHANGED THE OVERSPEED AND DRAIN VALVE. AFTER HAVING THE SAME RESULTS: SLOW/HUNG STARTS, CALLED A TURBOMECCA TECH REP.HE SUGGESTED THAT WE CHECK THE T4 HARNESS.HARNESS WAS OHMED OUT, ONE PROBE SHOWED AN OPEN PROBE. REPLACED T4 HARNESS, GROUND RUN AIRCRAFT HAD 3 SUCCESSFUL STARTS. OPS CHECK WAS NORMAL. THE SLOW START HUNG START 1 G 7 1 3U 3 U H9EU E19EU 2001080200274 20010802 00274 CE 2001 8 2 B3OR20010005 1 20010629 G 3260 S13771 SWITCH CESSNA 210 T210N 2073456 CE MLG IMPROPER PART B B3OR K NONE J WARNING INDICATION IN INSP/MAINT 1 SW 03 6621A 21063559 DURING INSTALLATION OF MAIN LANDING GEAR ACTUATORS AFTER COMPLIANCE WITH SEB01-2, A MAIN LANDING GEAR DOWN INDICATION SW ITCH WAS FOUND DAMAGED. THE SWITCH, P/N S1377-1 FROM THE ILLUSTRATED PARTS MANUL, WAS ORDERED FROM CESSNA. WHAT WAS RECE IVED HAD THE CORRECT P/N ON THE PACKAGING BUT THE P/N ON THE PART WAS P6-340005. CESSNA WAS CONTACTED AND WE WERE INFORM ED THAT THIS IS THE REPLACEMENT PART. AN ATTEMPT WAS MADE TO PUT THE PART IN THE AIRCRAFT TO NO AVAIL. THE SHAPE OF THE OLD SWITCH HOUSING IS BASICALLY RECTANGULAR WITH A SHAVED OFF CORNER. THE NEW SWITCH HAD NO SHAVED OFF CORNER. THE NEW S WITCH WOULD CONTACT A FORK ASSEMBLY IN THE GEAR. CESSNA WAS NOTIFIED AND THEY RECALLED THE SWITCHES. AS OF 7-11-2001, CE 1 H 7 1 3O 3A21 2001080200275 20010802 00275 EU 2001 8 2 B3OR20010006 1 20010709 G 6730 AC67032 SERVO SNIAS 350 AS350B2 8680813 EU HYD SYSTEM LEAKING B B3OR K NONE K FLUID LOSS IN INSP/MAINT 1 SW 03 5204X 808 3099 DURING A PREFLIGHT INSPECTION, HYDRAULIC FLUID WAS FOUND UNDER THE FORWARD PORTION IF THE TAIL BOOM. INVESTIGATION FOUND TAIL ROTOR SERVO LEAKING. AREA WAS CLEANED AND HYDRAULIC POWER UNIT WAS RUN ON AIRCRAFT TO LOCATE LEAK. SERVO WAS LEAKI NG FROM THE SHAFT TWICE THE ALLOWABLE LEAK RATE AND THE SERVO WAS ALSO LEAKING FROM A NON SERVICABLE PLUG ON THE HOUSING . UNIT WAS REPLACED WITH SERVICABLE UNIT. 1 G 7 1 3U H9EU 2001101500109 20011015 00109 CE 2001 10 15 B3OR20010009 1 20011006 G 2730 MS27645A4 BEARING CESSNA 500 550 2076604 CE ELEVATOR CORRODED B B3OR K NONE O OTHER IN INSP/MAINT 1 SW 03 2649 5513 150 5500607 THE ELEVATOR WAS REMOVED TO FACILLITATE OTHER MAINTENANCE. UPON REMOVAL OF THE RIGHT HAND ELEVATOR, THE INBOARD ELEVATOR BEARING, INNER RACE CAME OFF WITH THE INBOARD MOUNT BOLT. DURING THE REMOVAL OF THE ELEVATOR, THE BALL BEARINGS FELL OU T OF THE OUTER RACE. UPON FURTHER INVESTIGATION, THE INNER AND OUTER RACE HAD RUST AND RUST POWDER ON THE INNER AND OUTE R SURFACES OF THE RACES. THE INNER RACE WAS NOT "SEIZED" TO THE MOUNT BOLT. SOME OF THE BALL BEARINGS WERE MISSING, WHIL E SOME SHOWED SIGNS OF CORROSION AND METAL TO METAL CONTACT, SOME WERE NOT FOUND AT ALL. THE BARING, P/N MS27645-A4, WAS REPLACED WITH A NEW BEARING AND STAKED IN ACCORDANCE WITH CESSNA MAINTENANCE INSTRUCTIONS. 1 L 7 2 4F A22CE 2001080900256 20010809 00256 GL 2001 8 9 BB1 3 20010720 G 6110 RB2000 BLADE AMTR PULSAR SUPERPULSAR GL CONT O240 IO240B 17063 SO AMTRRX BK BK063 GL PROPELLER SEPARATED G A UNSCHED LANDING D INFLIGHT SEPARATION TO TAKEOFF 1 WP 23 601 806949 EXPERIMENTAL AMATEUR BUILT AIRCRAFT, INITIAL FLIGHT WITH NEW NON-CERTIFICATED VARIABLE PITCH PROPELLER MANUFACTURED BY A EROTEK AUCKLAND, NEW ZEALAND. BOTH COMPOSITE BLADES SEPARATED SIMULTANEOUSLY ON TAKE OFF AT 500 FT. AGL. INSPECTION RE VEALED THAT THE BLADE FAILURE OCCURRED AT THE BOND BETWEEN THE BLADES AND THE RETAINING PLUG, TEARING THROUGH THE DOWEL PIN HOLES. SUSPECT A DESIGN AND/OR MANUFACTURING DEFECT. 1 L 7 1 3O 3 O NT EXPA1L71 E7SO 5 N EXPP5N 2001050200061 20010502 00061 CE 2001 5 2 BF8R0320 1 20010320 G 3245 0923150 VALVE BEECH 76 76 1153005 CE TUBE VALVE SCORED B K NONE O OTHER IN INSP/MAINT 1 WP 28 6627U ME214 DEFECTIVE VALVE CORE MATING SEAL. 1 L 7 2 3O A29CE 2001080200286 20010802 00286 SO 2001 8 2 BIER0056 1 20010510 G 7100 LW12892 THRUST PLATE PIPER PA28 PA28236 7102815 SO LYC O540 O540* 41532 EA ROCKER ARM SHAFT BROKEN B BIEA K NONE O OTHER IN INSP/MAINT 1 EA 21 43595 1435 400 288411018 L2107240A AT 400 HR VALVE INSPECTION FOUND ROCKER ARM SHAFT THRUST BUTTONS BRITTLE AND CRACKED. SUBMITTER RECOMMENDATION: STRESS THE IMPORTANCE OF THE 400 HR VALVE INSPECTION. 1 L 7 1 3O 3 O 2A13 E295 2001080200295 20010802 00295 EA 2001 8 2 BIER200103057 2 20010703 G 7322 105217 CARBURETOR GROB G115 G115C 1660303 EU LYC O320 O320D1A 41508 EA ENGINE LOOSE B BIER K NONE O OTHER IN INSP/MAINT 1 EA 21 331AC 400 90 82021C L1803039A FOUND FUEL BOWL ATTACH SCREWS LOOSE WITH SUBSEQUENT FUEL LEAK AT BOWL GASKET, REQUIRED CARBURETOR REPLACEMENT DUE TO SCR EW HOLE ELONGATION. SUBMITTER NOTES: LYCOMING SB 366, DATED SEPT 14, 1973 REFERENCES THIS FOR MARVEL-SCHEBLER CARBURETOR S, WITH NO MENTION OF FACETS. SUBMITTER RECOMMENDS ANNUAL/250 HR SCREW TORQUE CHECK AS A MINIMUM INSPECTION INTERVAL. 1 L 7 1 3O 3 O NT A57EU E274 2001032000183 20010320 00183 SO 2001 3 20 BJ3RE000007 2 20010226 G 8530 SA643873 EXHAUST VALVE CONT CESSNA 310 310Q 2074242 CE CONT O470 IO470VO 17026 SO ENGINE WORN B K NONE O OTHER IN INSP/MAINT 1 SW 99 69604 46 46 310Q0812 14953672V DURING AN IRAN INSPECTION, IT WAS NOTICED THAT THE AMOUNT OF VALVE SHOWING ABOVE THE KEEPER WAS LESS ON ONE CYINDER THAN ON THE OTHERS. UPON DISASSEMBLY IT WAS FOUND THAT #3 CYLINDER EXHAUST VALVE WAS 1/16TH INCH SHORTER THAN THE OTHER VAL VES. A SLIGHT MUSHROOMING LIP WAS ABLE TO BE FELT AROUND THE TOP OF THE VALVE. IT APPEARS THAT THIS IS THE SAME TYPE OF WEAR AS INDICATED IN CSB98-1B ON CONTINENTAL VALVES. 1 L 7 2 3O 3 O 3A10 3E1 2001030500093 20010305 00093 NM 2001 3 5 CA010105006 1 20010103 G 2761 65448517 HOUSING BOEING 65448517 BOEING 737 737217 1384464 NM PWA JT8 JT8D17 52049 NE SPOILER ACTUATOR BROKEN W K NONE O OTHER IN INSP/MAINT 1 CA 3251 (CAN) DURING INSPECTION, 17C CHECK OF NR 4 GROUND SPOILER, SPOILER FOUND TO BE LOOSE. FOUND NR 4 SPOILER ACTUATOR, BODY END THAT ENCLOSED THE BEARING, BROKEN AWAY. ACTUATOR REPLACED AS PER WORK CARD 51160. 2 L 7 2 4F 4 F A16WE E2EA 2001011100074 20010111 00074 EU 2001 1 11 CA010105010 1 20010103 G 2621 FIRE BOTTLE AIRBUS 310 A310304 EU GE CF6 CF680C2* GL ENGINE DISCHARGED W A UNSCHED LANDING B J SMOKE/FUMES/ODORS/SPARKS WARNING INDICATION CL CLIMB 1 CA (CAN) A/C 212, DEC 17/2000, FLT 92577, YQM, LOG SEQUENCE 0292319. DURING CLIMB, MAIN DECK (FWD AND MID) SMOKE WARNING OC CURRED. SMELL AND SMOKE AND MIST WAS DETECTED IN COCKPIT. FIRE BOTTLES WERE DISCHARGED AND AIRCRAFT RETURNED TO YMQ. AFT ER CREW DEBRIEF, MIST AND ODOR WAS ATTRIBUTED TO INGESTION OF GLYCOL INTO PNEUMATIC SYSTEM DURING DEICE IN YMQ. FIRE BOT TLES WERE REPLACED AS PER WORK CARDS 26-210-005, AND 26-130-103. AIRCRAFT SERVICEABLE. 2 L 7 2 4F 4 F RT A35EU E23EA 2001030500107 20010305 00107 2001 3 5 CA010110005 4 20010110 G 2562 400010 ELT ROBSIN R22 R22BETA NM LYC O320 O320B2C 41508 EA CABIN FAILED W K NONE L NO TEST IN INSP/MAINT 1 CA (CAN) DURING ANNUAL INSPECTION, THIS ELT FAILED BECAUSE OF BORDERLINE OUTPUT POWER AND NO G SWITCH. THE ELT WAS RETURNED TO THE MANUFACTURER FOR REPAIR. 1 G 7 1 3O 3 O H10WE E274 2001030600028 20010306 00028 EU 2001 3 6 CA010111019 1 20010103 G 3060 3E32602 HARNESS BFGOODRICH PILATS PC12 PC1245 EU HARTZL HCE4A HCE4A3D GL ANTI-ICE SYSTEM FAULTY W K NONE L NO TEST IN INSP/MAINT 1 CA 1351 (CAN) ONE PROPELLER FOUND NOT TO BE HEATING WHILE PERFORMING SCHEDULED PROPELLER DEICER TEST. TROUBLESHOOTING LEAD US TO FIND AN OPEN WIRE IN THE HARNESS. PART ORDERED. 1 L 7 1 3T RT A78EU 5 C P210NE 2001030600046 20010306 00046 EA 2001 3 6 CA010116027 1 20010103 G 5610 WINDSHIELD CNDAIR CL600 CL6002B19 EA GE CF34 CF343A1 30015 NE COCKPIT FAILED W O OTHER O OTHER CR CRUISE 1 CA 95144H8592 (CAN) IN CRUISE, THE F/OS FRONT WINDSHIELD SHATTERED AT 31,000 FEET.THE MAINTENANCE REPLACED THE WINDSHIELD AND RETURNED THE AIRCRAFT TO SERVICE. 2 L 7 2 4F 4 F RT A21EA E15NE 2001030600047 20010306 00047 EA 2001 3 6 CA010116028 1 20010101 G 5610 WINDSHIELD CNDAIR CL600 CL6002B19 EA COCKPIT FAILED W K NONE O OTHER AP APPROACH 1 CA 00231H5852 (CAN) ON APPROACH TO YUL, THE F/OS FRONT WINDSHIELD SHATTERED AT 6,000 FEET.THE MAINTENANCE REPLACED THE WINDSHIELD AND RETURNED THE AIRCRAFT TO SERVICE. 2 L 7 2 4F RT A21EA 2001033000066 20010330 00066 NM 2001 3 30 CA010129018 1 20010104 G 2750 65162266 SWITCH BOEING 727 72722 1384002 NM PWA JT8 JT8D7B 52053 NE KRUGER FLAP FAILED W A UNSCHED LANDING J WARNING INDICATION CL CLIMB 1 CA (CAN) AFTER DEPARTER&UPON FLAP RETRACTION, NR 5 LEADING EDGE FLAP IN TRANSIT LIGHT ILLUMINATED. FUEL DUMPED & A/C RETURN ED TO AIRPORT OF DEPTR: MAINT CHANGED OUT FLAP SWITCH, P/N 40174 & SYS TESTED & FUNCTIONED NORMALLY. A/C DEPARTED & SAME FAULT RECURRED. MAINT REPL NR 5 LEADING EDGE FLAP ACTUATOR, P/N 65-17818-20 & LEADING EDGE POS CNTL MODEL, P/N 65-60212 -11, AS PRECAUTIONARY MEASURE: SYS AGAIN TESTED AS PER THE MM& OPALLY CHECKED SEVERAL TIMES W/O FAULT. A/C RT-SRV. DISCR EPANCY RETURNED ON NEXT DEPTR: A/C RETURNED AGAIN FOR MAINT TROUBLESHOOTING. FINAL RPT: L/E FLAP POS SWITCHES SWAPP ED B ETWEEN 5 & 3 FLAP. WIRING FROM COCKPIT T 2 L 7 3 4F 4 F A3WE E2EA 2001033000067 20010330 00067 2001 3 30 CA010130007 4 20010120 G 2200 065006415 COMPUTER BENDIX 220 PILATS PC12 PC1245 EU AUTOPILOT FAILED W O OTHER J WARNING INDICATION CL CLIMB 1 CA 1964 (CAN) IN THE CLIMB, SHORTLY AFTER ENGAGING AUTOPILOT, AUTOPILOT DISENGAGED FOR NO APPARENT REASON. AFTER A SUCCESSFUL RE TEST, REENGAGING IS POSSIBLE WITH NO FURTHER PROBLEMS. THIS PROBLEM HAS OCCURRED IN THE RECENT PAST.THE AUTOFLIGHT COMPU TER WAS REPLACED FOR TROUBLESHOOTING AND ITS PERFORMANCE WILL BE MONITORED. 1 L 7 1 3T RT A78EU 2001033000068 20010330 00068 EU 2001 3 30 CA010130009 1 20010103 G 5510 9412259360 BUSHING PILATS 5551012036 PILATS PC12 PC1245 EU HORIZONTAL STAB FAILED W K NONE O OTHER IN INSP/MAINT 1 CA 1351 1351 272 (CAN) HORIZONTAL STABILIZER HAS MOVEMENT OF .003 AT ATTACHMENT POINTS, WHEN TIP OF STAB IS MOVED IN A UP AND DOWN MOTION . THIS AIRCRAFT HAS BEEN LIKE THIS SINCE NEW. AS PER PILATUS, 0 TOLERANCE ALLOWED AT ATTACHMENT POINT. BUSHINGS WERE REP LACED WITH NO IMPROVEMENT. BOLTS PLACED ON ORDER TO TRY TO ILLIMINATE THE PLAY. 1 L 7 1 3T RT A78EU 2001033000069 20010330 00069 EA 2001 3 30 CA010130011 2 20010105 G 7200 ENGINE DHAV DHC6 DHC6 2802606 EA PWA PT6 PT6A27 52043 EA RIGHT FAILED W E A ENGINE SHUTDOWN UNSCHED LANDING J WARNING INDICATION CR CRUISE 1 CA (CAN) RT ENGINE SHUT DOWN DUE TO LOW OIL PRESSURE. AFTER REACHING CRUISING ALTERNATE RT ENGINE LOW OIL PRESSURE CAPTION APPEARED. LOW OIL PRESSURE GAUGE INDICATION OBSERVED. PRECAUTIONARY ENGINE SHUT DOWN. DIVERTED BACK TO AIRFIELD. 1 H 7 2 3T 4 T RT A9EA E4EA 2001033000070 20010330 00070 NM 2001 3 30 CA010130012 1 20010101 G 3040 07802 WINDSHIELD DHAV DHC8 DHC8102 2809003 NM PWA 120 PW120 NE COCKPIT FAILED W O OTHER O OTHER CR CRUISE 1 CA 10554 (CAN) LEFT WINDSHIELD SHATTERED INFLIGHT. AIRCRAFT LANDED. WINDSHIELD REPLACED IN ACCORDANCE WITH DHC8 MM 56-10-11. RAN AIRCRAFT OPERATIONS CHECKED, OK. AIRCRAFT RETURNED TO SERVICE. NOTE PCA A0101001 2 H 7 2 4T 4 T RT A13NM E20NE 2001033000071 20010330 00071 GL 2001 3 30 CA010131009 1 20010101 G 7160 653885 FLANGE DIAMON DA20 DA20C1 2990001 GL CONT O240 IO240B 17063 SO SNSNCH W69EK W69EK63 EA INTAKE PIPE CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 569 (CAN) FLANGE CRACKED. 1 L 7 1 3O 3 O NT TA4CH E7SO 5 N TA4CH 2001033000072 20010330 00072 EA 2001 3 30 CA010131015 1 20010105 G 5753 F35 SEALANT DHAV DHAV DHC7 DHC7103 2802710 EA PWA PT6 PT6A50 52043 EA HAMSTD 24PF 24PF305 GL UNDER NR 4 FLAP PEELING W K NONE O OTHER IN INSP/MAINT 1 CA 10482 (CAN) THE SEALANT USED UNDER THE NR 4 FLAP TRACK AS PER AD CF-87-04, SB 7-57-30 WAS FOUND PEELING OFF. 10481.68 HOURS H AVE ACCUMULATED ON THIS AIRCRAFT AFTER INITIAL APPLICATION BACK IN OCTOBER OF 1987. THIS AIRCRAFT HAS BEEN OPERATING IN ASIA. 2 H 7 4 4T 4 T A20EA E4EA 6 C P1NE 2001033000073 20010330 00073 SO 2001 3 30 CA010131016 1 20010105 G 8120 46C1983985 TURBOCHARGER PIPER PA46 PA46350P SO LYC O540 TIO540AE2A 41532 EA ENGINE FAILED W O OTHER O OTHER CR CRUISE 1 CA 159 (CAN) PILOT REPORTED LOSS IN MANIFOLD PRESSURE FOUND TURBOCHARGER TURBINE MISSING A BLADE AND TURBO SEIZED. 1 L 7 1 3O 3 O RT A25SO E14EA 2001033000074 20010330 00074 2001 3 30 CA010131017 4 20010104 G 2562 0004006A BATTERY LEIGH SHARC7H2184 ELT WRONG PART W K NONE W INADEQUATE Q C IN INSP/MAINT 1 CA 132428 (CAN) ELT WAS SUBMITTED FOR ANNUAL RECERT. UNAPPROVED BATTERY WAS CERTIFIED WITH ELT NOV.1/2000 - ELT AS SUCH IS NOT TC APPROVED. AND INSTALLED HORIZONTALLY IN AIRCRAFT (CESSNA, AS PER CUSTOMER), AND THE G SWITCH IS INSTALLED FOR A VERTICAL MOUNT INSIDE THE UNIT. ELT RETURNED AS IS, CUSTOMER ADVISED TO FIND ALTERNATE REPLACEMENT. 2001033000075 20010330 00075 CE 2001 3 30 CA010131018 1 20010110 G 5511 12326194 RIB CESSNA 183260029 CESSNA 210 T210M 2073451 CE CONT O520 TSIO520R 17040 SO MCAULY D3A34 D3A34C402 GL HORIZONTAL STAB CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) DURING A 50 HOUR INSPECTION OF THE HORIZONTAL STAB, THE 4 RIBS WERE FOUND TO BE LOOSE & CRACKED. THIS IS DONE BY S QUEEZING THE NOSE RIBS (WITH A MODERATE AMOUNT OF PRESSURE) AND LISTEN FOR CLICKING SOUNDS & FEELING OF LOOSE RIVETS. TH EREFORE, THE LOWER SKIN WAS PEELED BACK THE 4 RIBS WERE REMOVED AND REPLACED WITH NEW RIBS. THE SKIN WAS RIVETED BACK ON . STAB WAS INSTALLED AND AIRCRAFT WAS RETUNED TO SERVICE. 7 B&C S.D. FOUND DUING 50 HOUR INSPECTION. NO ACTION REQUIED B Y FLIGHT CREW. 1 H 7 1 3O 3 O 3A21 E8CE 5 C P47GL 2001033000085 20010330 00085 EA 2001 3 30 CA010202005 1 20010107 G 3244 256K433 TIRE 60085123 CNDAIR CL601 CL6012A12 1900303 EA GE CF34 CF341A NE MLG FAILED W O OTHER O OTHER TO TAKEOFF 1 CA 249 (CAN) ON TAKEOFF CREW HEARD MUFFLED BANG. NO AIRCRAFT CONTROL PROBLEMS NOTED. CONTINUED TO DESTINATION LANDED WITHOUT IN CIDENT. DURIG POST FLIGHT FOUND THE NR 3 TIRE HAD LOST ALL TREAD. THE TIRE WAS STILL INFLATED. DAMAGE TO RIGHT INBOARD F LAPS LOWER SURFACE AND THE RIGHT MAIN LANDING GEAR INBOARD WEIGHT ON WHEEL ANTI-SKID HARNESS. 2 L 7 2 4F 4 F RT A21AE E15NE 2001033000087 20010330 00087 EA 2001 3 30 CA010202008 1 20010103 G 5610 WINDSHIELD CNDAIR CL600 CL6002B19 EA GE CF34 CF343B1 NE COCKPIT FAILED W A UNSCHED LANDING O OTHER CR CRUISE 1 CA (CAN) THE CREW REPORTED THAT THE CAPTS FRONT WINDSHIELD SHATTERED IN CRUISE. THE LANDING WAS UNEVENTFUL.THE MAINTENANCE REPLACED THE WINDSHIELD. 2 L 7 2 4F 4 F RT A21EA E15NE 2001033000088 20010330 00088 EA 2001 3 30 CA010202011 1 20010103 G 2752 ACTUATOR CNDAIR CL600 CL6002B19 EA GE CF34 CF343A1 30015 NE RT FLAP FAILED W O OTHER J WARNING INDICATION AP APPROACH 1 CA (CAN) THE CREW REPORTED THE FLAP FAIL CAUTION MESSAGE WHICH APPEARED ON APPROACH (SELECTIION OF 45 DEGREES, STOPPED AT 3 7). THE MAINTENANCE REPLACED THE RT OUTBOARD FLAP INBOARD ACTUATOR 2 L 7 2 4F 4 F RT A21EA E15NE 2001033000089 20010330 00089 EA 2001 3 30 CA010202013 1 20010106 G 2612 47259701 FIRE DETECTOR CNDAIR CL600 CL6002B19 EA GE CF34 CF343B1 NE NR 1 ENGINE FAILED W O OTHER N FALSE WARNING DE DESCENT 1 CA (CAN) DURING DESCENT INTO MEMPHIS, THE CREW ON AIRCRAFT 7416 SHUT DOWN ENGINE NR 1 PER THE EMERGENCY PROCEDURES DUE TO T HE POSTING OF AN INTERMITTENT LT ENGINE FIRE MESSAGE ON THE EICAS. DURING TROUBLESHOOTING THE MECHANICS FOUND THE FIRE D ETECTION UNIT UNDER THE LT CONSOLE SHORTED AND CONTAMINATED (COFFEE) WITH LIQUID. A NEW CONTROLLER AND BOTTLE WAS INSTAL LED AND THE SYSTEM SUCCESSFULLY TESTED PER THE AMM. 2 L 7 2 4F 4 F RT A21EA E15NE 2001033000090 20010330 00090 NE 2001 3 30 CA010202022 2 20010107 G 7210 GEARBOX CNDAIR CL600 CL6002B19 EA GE CF34 CF343B1 NE NR 2 ENGINE FAILED W E A ENGINE SHUTDOWN UNSCHED LANDING E J VIBRATION/BUFFET WARNING INDICATION NR NOT REPORTED 1 CA (CAN) NR 2 ENGINE VIBRATION FLUCTUATION INDICATED .4 TO .7 MILS APPROXIMITELY 3 TO 5 MIN. LATER, NR 2 ENGINE SHUT DOWN U NCOMMANDED. PERFORMED QRH PROCEDURE & DIVERTED INTO NEXT AIRPORT (ISO), THE FLIGHT CREW DECLARED EMERGENCY (UNEVENTFUL). FOUND METAL IN CHIP DETECTOR (SUSPECT GEARBOX - INTERNAL) NOT CONFIRMED. REPLACEMENT OF ENGINE S/N 807528 IN PROGRESS. 2 L 7 2 4F 4 F RT A21EA E15NE 2001033000091 20010330 00091 EA 2001 3 30 CA010205006 1 20010111 G 3040 NP1393215 WINDSHIELD CNDAIR CL600 CL6002B19 EA GE CF34 CF343B1 NE COCKPIT CRACKED W O OTHER O OTHER CR CRUISE 1 CA 1566 (CAN) THE CREW REPORTED THAT THE LT WINDSHIELD CORE PLY CRACKED DURING FLIGHT.THE MAINTENANCE REPLACED THE WINDSHIELD. 2 L 7 2 4F 4 F RT A21EA E15NE 2001033000092 20010330 00092 EA 2001 3 30 CA010205008 1 20010101 G 5610 NP1393215 WINDSHIELD CNDAIR CL600 CL6002B19 EA GE CF34 CF343B1 NE COCKPIT CRACKED W O OTHER O OTHER CR CRUISE 1 CA (CAN) THE CREW REPORTED THAT THE RT WINDSHIELD CARACKED IN FLIGHT. THE MAINTENANCE REPLACED THE RT WINDSHIELD. 2 L 7 2 4F 4 F RT A21EA E15NE 2001040200252 20010402 00252 SO 2001 4 2 CA010206004 2 20010104 G 8530 628309 VALVE GUIDE CESSNA 150 150M 2071830 CE CONT O200 O200A 17020 SO EXHAUST VALVE WORN W E D ENGINE SHUTDOWN RETURN TO BLOCK R J PARTIAL RPM/PWR LOSS WARNING INDICATION TX TAXI/GRND HDL 1 CA 1439 (CAN) ENGINE RAN VERY ROUGH AT START UP.CYLINDER NR 3 REMOVED DUE TO LOW COMPRESSION. EXHAUST GUID WORN CAUSING CARBON T O JAM VALVE IN OPEN POSITION. CYLINDER RELACED DUE TO ABOVE PROBLEM. 1 H 7 1 3O 3 O 3A19 E252 2001040300124 20010403 00124 EU 2001 4 3 CA010208013 1 20010123 G 2431 RG390E BATTERY BRAERO DH125 BAE125800A 1500285 EU GARRTT TFE731 TFE7315R 01518 WP MAIN BATTERY OVERHEATED W O OTHER M B OVER TEMP SMOKE/FUMES/ODORS/SPARKS TX TAXI/GRND HDL 1 CA 407 (CAN) ENGINE ROTATION TOO SLOW AT START ATTEMPTS FOR SUCCESSFUL ENGINE LIGHT OFF. BATTERY VENTED EXCESSIVE AMOUNTS OF SMOKE AND VAPOR (STEAM AND ACID GAS) DUE TO SEVERAL SUCCESSIVE FAILED ENGINE START ATTEMPTS WITHOUT ALLOWING SUFFICIENT RECHARGING BY AIRCRAFT ELECTRICAL SYSTEM. HOT BATTERIES REMOVED FROM AIRCRAFT. STRUCTURE NEUTRALIZED AND RINSED WITH FR ESH WATER. - NEW BATTERIES FITTED. 2 L 7 2 4F 4 F RT A3EU E6WE 2001040300125 20010403 00125 NE 2001 4 3 CA010208014 1 20010124 G 6220 7610308010103 HUB SKRSKY S76 S76A 8143006 NE ALLSN 250C 250C30S 03013 GL MAIN ROTOR CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 3985 3985 (CAN) DURING THE POST FLIGHT INSPECTION BY AME A FINE LINE WAS NOTICED ON THE UPPER DAMPER ATTACH LUG. THE LUG WAS PAIN T STRIPPED AND A DEFINITE CRACK CAN BE SEEN. STARTING NEAR THE BOLT HOLE PROGRESSING INBOARD FOR APPROXIMATELY 1 1/4 INC H. THE MAIN ROTOR HUB WAS REPLACED. 1 G 7 2 3U 3 U H1NE E1GL 2001040300126 20010403 00126 SW 2001 4 3 CA010208016 1 20010122 G 6220 471202527 GRIP BELL 47 47J2 1181104 SW LYC O435 TVO435* 41516 EA MAIN ROTOR CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 2261 31 (CAN) AIRCRAFT IS BEING IMPORTED INTO CANADA. CRACKS IN ROOT OF THREADS FOUND DURING EDDY CURRENT INSPECTION. 1 G 7 1 3O 3 O 2H1 1E13 2001040300127 20010403 00127 EU 2001 4 3 CA010209002 1 20010124 G 2612 FIRE DETECTOR FOKKER F28 F28MK1000 4990808 EU NR 2 ENGINE INTERMITTENT W F A ACTIVATE FIRE EXT. UNSCHED LANDING N FALSE WARNING CL CLIMB 1 CA (CAN) FLT 8473SHORTLY AFTER DEPARTURE OUT OF KELOWNA (YLW), FLT CREW REPORTED THAT NR 2 ENGINE FIRE WARNING CAME ON. NR 2 ENGINE SHUTDOWN & BOTH FIRE BOTTLES WERE DISCHARGED. PILOTS REPORTED THAT FIRE WARNING LIGHTS REMAINED ON AFTER THE BO TTLES WERE DISCHARGED. A/C ROUTED TO VANCOUVER (YVR) DUE TO WEATHER MINS IN INTERIOR. REMAINDER OF FLT UNEVENTFUL & A/C LANDED IN YVR WITH NO FURTHER INCIDENTS TO REPORT. MAINT INSPECTION AFTER LANDING CONFIRMED FAULTY INDICATOR ONLY. CRA FLEET RELIABILITY DEPT CREATED WORK PACKAGE FOR INDICATION PROBLEM. 2 L 7 2 4F RT A20EU 2001040300128 20010403 00128 SO 2001 4 3 CA010209003 1 20010209 G 6310 ENGINE PIPER PA31 PA31P 7103120 SO LYC O541 TIGO541E1A 41539 EA NACELLE FAILED W O OTHER J WARNING INDICATION DE DESCENT 1 CA 1231 (CAN) ENGINE LOSSED MANIFOLD PRESSURE FOLLOWED BY LOSS OF OIL PRESSURE. VISUAL INSPECTION REVEALS CRACKED CASE. 1 L 7 2 3O 3 O A8EA E19EA 2001040300129 20010403 00129 WP 2001 4 3 CA010209004 1 20010112 G 2435 230321183 BELL ASSY LUCAS 23032018 HUGHES 369 369D 4470706 WP ALLSN 250C 250C20B 03013 GL STARTER GEN UNAPPOVED PART W K NONE O OTHER IN INSP/MAINT 1 CA 1177 2514 (CAN) STARTER GEN RECEIVED FOR OVERHAUL. FOUND THE ADE (COMM END) END BELL ASSEMBLY TO BE 3, WHICH ACCORDING TO THE OEM IS AN OLD, OBSOLETED PART THAT WAS APPLICABLE ONLY TO THE 23032-005 STARTER-GENERATOR, WHICH IS ITSELF OBSOLETE, UNSUPPO RTED AND NOT LISTED IN THE OVERHAUL MANUAL. THE ASSEMBLY IS ALSO CORRODED AND CRACKED AROUND THE MOUNTING HOLES. THE COR RECT ASSY IS P/N 23032-1423. A CORRECT ASSY WAS INSTALLED DURING OVERHAUL, ALONG WITH THE CORRECT BEARING RETAINER AND F AN COVER.THE OFFENDING PARTS ARE BEING TRANSMITTED TO THE AIRCRAFT OPERATOR FOR FOLLOW-UP. 1 G 7 1 3U 3 U H3WE E4CE 2001040300130 20010403 00130 SW 2001 4 3 CA010209006 1 20010129 G 2435 230791281 BRUSHES LUCAS 230790001 SWRNGN SA227 SA227AC 8780603 SW GARRTT TPE331 TPE33111U 01514 WP ROTOL R321 R321482F8 GL STARTER GEN UNAPPOVED PART W K NONE O OTHER IN INSP/MAINT 1 CA 499 10020 (CAN) DURING SCHEDULED MAINTENANCE, AT BRUSH INSPECTION IT WAS FOUND THAT THE BRUSHES INSTALLED IN THIS STARTER-GENERATO R WERE. THIS BRUSH IS ONLY APPROVED FOR THE STARTER GEN MODELS 23079-009 AND 23079-000-2.THE BRUSHES WERE REMOVED AND RE PLACED WITH FAA-PMA LONG LIFE BRUSH PART NO.M23088-1320, WHICH IS APPROVED FOR THIS STARTER-GENERATOR MODEL 23079-000-1 WHEN USED ON THE FAIRCHILD SA227AC AIRCRAFT. THE STARTER GEN WAS RETURNED TO SERVICE. 2 L 7 2 4T 4 T RT A8SW E4WE 6 C P61GL 2001040300131 20010403 00131 EU 2001 4 3 CA010209007 1 20010131 G 3240 9595601511 BRAKE PILATS PC12 PC1245 EU PWA PT6 PT6A67B 52043 NE HARTZL HCE4A HCE4A3D GL LT MLG FROZEN W O OTHER O OTHER LD LANDING 1 CA (CAN) TAKEOFF IN FT ST. JOHN IN POWDER SNOW MAY HAVE CAUSED MOISTURE TO ENTER LT BRAKE ASSEMBLY. DURING FLIGHT TO FT NEL SON, BRAKE FROZE. ON LANDING IN FT. NELSON LT TIRE WOULD NOT ROTATE AND TIRE FLAT SPOTTED AND BLEW. AIRCRAFT WAS STOPPED ON RUNWAY AND MAINTENANCE WAS CALLED. TIRE AND WHEEL ASSEMBLY WAS REPLACED AND GEAR ASSEMBLY INSPECTED FOR DAMAGE. THIS IS THE 3RD SUCH INCIDENT IN THE LAST 12 MONTHS. 1 L 7 1 3T 4 T RT A78EU E26NE 5 C P210NE 2001040300132 20010403 00132 NE 2001 4 3 CA010209009 2 20010116 G 7230 4036T24P01 BLADE LEAR 25 25B 5170511 CE GE CJ610 CJ6106 30006 NE ENGINE SEPARATED W A UNSCHED LANDING J WARNING INDICATION CL CLIMB 1 CA 2264 2264 (CAN) AIRCRAFT IN CLIMB FL110, LOUD BANG HEARD, RT FIRE WARNING ACTIVATED. POWER REDUCED, FUEL SHUT OFF, FIRE WARNING DE -ACTIVATED. AIRCRAFT RETURNED TO DEPARTURE AIRPORT AND SINGLE ENGINE LANDING CARRIED OUT WITHOUT FURTHER INCIDENT. GROUN D INSPECTION REVEALED THAT FINAL STAGE TURBINE HAD LOST ONE BLADE (CONTAINMENT RING DAMAGED BUT NOT PENETRATED) RESULTAN T IMBALANCE CAUSED SEVERE DAMAGE TO REMAINING BLADES AND SHROUD AND CAUSED EXHAUST TAIL PIPE TO SEPARATE AT MOUNTING FLA NGE. HOT GASES RELASED INSIDE COWLING CAUSED FIRE WARNING TO ACTIVATE. ENGINE OVERHAUL AGENCY MAY HAVE MORE INFORMATION AFTER THEIR ANALYSIS. 2 L 7 2 4J 4 J A10CE 1E16 2001040300133 20010403 00133 SW 2001 4 3 CA010209015 1 20010121 G 5610 412669001100 WINDOW BELL 212 212 1181420 SW PWA PT6T PT6T3 52045 EA COCKPIT FAILED W A UNSCHED LANDING O OTHER CR CRUISE 1 CA (CAN) WHILE IN STRAIGHT AND LEVEL FLIGHT A LOUD BANG WAS HEARD. IT WAS DISCOVERED THAT THE RT REAR SLIDING DOOR WINDOW H AD SHATTERED. AN UNEVENTFUL LANDING WAS CARRIED OUT. ALLL PIECES WERE RECOVERED. 1 G 7 1 4U 4 U H4SW E22EA 2001040300134 20010403 00134 EU 2001 4 3 CA010209017 1 20010131 G 3310 MS24149A1 RELAY BRAERO DH125 HS125700A 4230170 EU GARRTT TFE731 TFE7313R 01518 WP LIGHTING FAILED W O OTHER J WARNING INDICATION TX TAXI/GRND HDL 1 CA (CAN) AFTER TAXI IN AT YVR THE NR 2 AC INVERTER FAIL LIGHT ILLUMINATED AS WELL AS XS2 BUSS FAIL LIGHT ILLUMINATED. RESET THE NR 2 INVERTER SWITCH FAILED TO RESET THE SYSTEM. MAINTENANCE TROUBLESHOOT THE PROBLEM BACK TO A FAULTY RELAY WITHIN THE CABIN LIGHTING SYSTEM. FURTHER INVESTIGATION FOUND THE LIGHTING RELAY CHATTERING, CAUSED A FLUCTUATING VOLTAGE ON T HE XS2 BUSS RESULTING IN THE NR 2 INVERTER TRIPPING OFF LINE. AFTER TRACING THE HISTORY OF THIS PROBLEM IT WAS FOUND THA T IN MORE THAN ONE OCCASIION THE CABIN LIGHTING HAS CAUSED A TOTALFAILURE OF THE AIRCRAFTS RIGHT AC BUSS THUS LEAVING CO NCERNS AS TO HOW A SECONDARY SYSTEM CAN FAIL A PRIMARY SYSTEM ON THE AIRCRAFT. 2 L 7 2 4F 4 F A3EU E6WE 2001040300136 20010403 00136 CE 2001 4 3 CA010212005 1 20010123 G 5312 24120651 BULKHEAD CESSNA 172 172RG 2072438 CE LYC O360 O360F1A6 41514 EA MCAULY 2D34C B2D34C220 GL FUSELAGE CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 10545 (CAN) DURING INSPECTION OF AIRCRAFT FOLLOWING A GEAR UP LANDING, THE TWO BULKHEADS RUNNING VERTICALLY IN FRONT OF CABIN DOORS WERE FOUND CRACKED AT FLOOR LEVEL. THE CRACK IS LOCATED AT THE CUT OUT FOR THE HEAT DISCHARGE DUCT. THESE CRACKS W ERE NOT CAUSED BY THE GEAR UP LANDING. 1 H 7 1 3O 3 O 3A17 E286 5 C P7EA 2001040300137 20010403 00137 CE 2001 4 3 CA010212006 1 20010123 G 5312 05120122 BULKHEAD CESSNA 172 172P 2072436 CE LYC O320 O320D2J 41508 EA FUSELAGE CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 15904 (CAN) DURING ROUTINE CESSNA PROGRESSIVE CARE INSPECTION, THE BULKHEAD AT THE BACK END OF THE BAGGAGE COMPARTMENT STATION 108 WAS FOUND TO BE CRACKED AT BOTH LOWER CORNERS, AND THE UPPER RIGHT CORNER. THE CRACKS ARE APPROXIMATELY 2 INCHES LO NG. THIS AIRCRAFT IS USED FOR FLIGHT TRAINING AND ON OCCASION BANNER TOWING. 1 H 7 1 3O 3 O NT 3A12 E274 2001040300138 20010403 00138 EA 2001 4 3 CA010212007 1 20010125 G 2701 C3CF3913 CONTROL COLUMN DHAV DHC3 DHC3 2800202 EA PWA PT6 PT6A34 52043 EA COCKPIT CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) WHILE CARRYING OUT AIRWORTHINESS DIRECTIVE CF-82-34 WE FOUND A CRACK IN THE LOWER WELD ASSEMBLY OF THE AILERON CON TROL COLUMN LOCATED AT THE CUT HOLE FOR THE AILERON CHAIN. THE CRACK WAS APPROXIMATELY 1/4 INCH LONG. 1 H 7 1 3R 4 T A815 E4EA 2001040300139 20010403 00139 NE 2001 4 3 CA010212011 2 20010118 G 7200 ENGINE BOEING 727 727225 1384077 NM PWA JT8 JT8D7B 52053 NE NR 1 FAILED W A UNSCHED LANDING K J FLUID LOSS WARNING INDICATION CR CRUISE 1 CA (CAN) ENROUTE TO CPH FROM EMA NR 1 ENGINE OIL QUANTITY SLOWLY DECREASED TO 1 GALLON AT WHICH POINT THE INFLIGHT SHUT DOW N WAS PERFORMED. THE A/C LANDED WITHOUT INCIDENT AT CPH. THE ENGINE MAINTAINED POSITIVE OIL PRESSUE FOR THE 20-25 MINUTE PERIOD OF WINDMILL CONDITION. THE ENGINE WAS REMOVED AND IS ENROUTE FOR ASSESSMENT. 2 L 7 3 4F 4 F A3WE E2EA 2001040300078 20010403 00078 2001 4 3 CA010212033 4 20010123 G 2562 R889V BATTERY CESSNA 150 150L 2071826 CE CONT O200 O200A 17020 SO ELT UNAPPOVED PART W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) ELT SENT IN FOR RECERTIFICATION. WAS EQUIPPED WITH A NON-APPROVED BATTERY PACK ARTEX . ONLY APPROVED BATTERY IS TE CHNISONIC. BATTERY REPLACED AND ELT RECERTIFIED. 1 H 7 1 3O 3 O 3A19 E252 2001040300080 20010403 00080 CE 2001 4 3 CA010213003 1 20010118 G 7160 HOSE CESSNA 150 150 2071802 CE CONT O200 O200* 17020 SO CARB HEAT CONTAMINATED W C ABORTED TAKEOFF R E PARTIAL RPM/PWR LOSS VIBRATION/BUFFET TO TAKEOFF 1 CA (CAN) DURING THE WINTER MONTHS WE ARE RECEIVING COMPLAINTS OF A SERIOUS NATURE. UPON TAKEOFF, USUALLY THE FIRST ONE, THE AIRCRAFT RUNS VERY ROUGH. I HAVE EXPERIENCED THIS PERSONALLY. WE HAVE DETERMINED THAT SNOW COLLECTS IN THE SCAT HOSE TH AT PROVIDES AIR FOR CARB HEAT. THIS SNOW MELTS AFTER THE ENGINE HAS WARMED UP AND UPON SELECTION OF CARB HEAT THE ENGINE WANTS TO QUIT. WE HAVE REMEDIED THIS ON SEVERAL AIRCRAFT BYMAKING A SMALL HOLE IN THE LOW SPOT OF THE SUBJECT SCAT HOSE , USING A SOLDERING IRON. 1 H 7 1 3O 3 O NT 3A19 E252 2001040300081 20010403 00081 EA 2001 4 3 CA010213004 1 20010119 G 3310 2LFV4090600AA COAX CNDAIR CL600 CL600* EA INSTRUMENT PANEL BURNED W H A DEACTIVATE SYST/CIRCUITS UNSCHED LANDING B SMOKE/FUMES/ODORS/SPARKS CR CRUISE 1 CA (CAN) PILOT REPORTED CENTER INSTRUMENT PANEL FLOOD LIGHTING INOPERATIVE WITH BRIGHT/DIM POTENTIOMETER. KNOB SWITCHED OFF AND LIGHTING OPERATED WITH BRIGHT/DIM SWITCH. INVESTIGATION AREVEALED THAT CABLE ASSY, CONNECTOR PIN AT INVERTER END WA S BURNED OFF.CABLE ASSY AND INVERTER/POWER SUPPLY. THE CONNECTOR WAS PROBABLY NOT SEATED CORRECTLY AT ONE TIME, BUT AT T IME OF INVESTIGATION THE CONNECTOR WAS PROPERLY INSTALLED. ARCING AT THE INVERTER CONNECTOR PIN COULD HAVE RESULTED IN A N OVERHEAT AND/OR FIRE CONDITION. 2 L 7 2 4F RT A21EA 2001032700204 20010327 00204 EA 2001 3 27 CA010213005 1 20010203 G 3244 256K433 TIRE CNDAIR CL601 CL6012A12 1900303 EA SIDEWALL BULGED W O OTHER O OTHER IN INSP/MAINT 1 CA 199 93170620 (CAN) BULGE IN TIRE SIDEWALL/TREAD RADIUS EDGE. IT APPEARS THAT AIR IS LEAKING INTO THE RADIUS AND GETTING TRAPPED BETWE EN PLIES. THIS IS THE THIRD TIRE THAT I KNOW OF WITH THIS PROBLEM. 2 L 7 2 4F RT A21AE 2001032700205 20010327 00205 SO 2001 3 27 CA010213006 2 20010126 G 8530 CYLINDER HEAD CONT 642344 CESSNA 421 421B 2076014 CE CONT O520 GTSIO520H 17032 SO MCAULY 3AF34C 3AF34C92 GL SP PLUG-INJECTR CRACKED W O OTHER O OTHER IN INSP/MAINT 1 CA 100 (CAN) AT 100 HOUR INSPECTION IN NOVEMBER 2000, FOUND FOUR CYLINDERS WITH SIMILAR CRACKS. AT NEXT 100 HOUR INSPECTION IN JANUARY 2001 FOUND SIX MORE CYLINDERS WITH CRACKS IN SAME LOCATION (BETWEEN SPARK PLUG HOLE AND INJECTOR HOLE). CYLINDER S REPLACED AFTER DETECTING CRACKS. PAST EXPERIENCE SHOWS THAT CRACKS ARE VERY COMMON IN THIS AREA.2001-02-15 TC: PART #S , TSN, ADDITIONAL CONTRIBUTING FACTORS WERE NOT GIVEN. 1 L 7 2 3O 3 O A7CE E7CE 5 C P22EA 2001032700206 20010327 00206 SO 2001 3 27 CA010213008 1 20010122 G 5280 4752932 HINGE PIPER PA31 PIPER PA31 PA31 7103102 SO LYC O540 TIO540A2C 41532 EA IN RADIUS CRACKED W O OTHER O OTHER IN INSP/MAINT 1 CA 317712043 (CAN) DURING INSPECTION AS PER AIRWORTHINESS DIRECTIVE 200-25-01,(2)TWO GEAR DOOR HINGES FOUND CRACKED. HINGES REPLACED. 1 L 7 2 3O 3 O A20SO E14EA 2001032700207 20010327 00207 EA 2001 3 27 CA010213009 1 20010124 G 2701 C2CF834A CONTROL COLUMN DHAV DHAV DHC2 DHC2MK1 2800102 EA PWA R985 R985AN14B 52008 NE AT WELD CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 15576 497 (CAN) COMPLETED INSPECTION AS PER SB 2/28 AND AD CF-84-01R1, FOUND CRACK IN WELD. 128 HOURS SINCE LAST INSPECTION.SUBMIT TER FEELS LACK OF MAINTENANCE MAY BE RESPONSIBLE FOR THIS CRACK BEING NOTED EARLY. 1 H 7 1 3R 3 R A806 5E1 2001032700209 20010327 00209 EA 2001 3 27 CA010213018 1 20010125 G 2760 ACTUATOR CNDAIR CL600 CL6002B19 EA GE CF34 CF343B1 NE ACTUATOR LUG BROKEN W O OTHER F FLT CONT AFFECTED AP APPROACH 1 CA (CAN) ON APPROACH, AT LAST FLP SELECTION, A/C ROLLED TO THE RIGHT FOLLOWED BY FLT SPLR DEPLOY CAUTION MESSAGE.CREW DECLA RED EMERGENCY AND LANDED WITHOUT ANY FURTHER EVENT. MAINTENANCE FOUND FLIGHT SPOILER PANEL ACTUATOR LUG BROKEN. PANEL RE PLACED. AIRCRAFT RETURNED TO SERVICE. AD IN PROGRESS 2 L 7 2 4F 4 F RT A21EA E15NE 2001032700210 20010327 00210 EA 2001 3 27 CA010213019 1 20010124 G 2611 SMOKE DETECTOR CNDAIR CL600 CL6002B19 EA GE CF34 CF341A NE LAV SMOKE DETCTR FAULTY W O OTHER N FALSE WARNING AP APPROACH 1 CA (CAN) ON SHORT FINAL, SMOKE TOILET CAUTION MESSAGE CAME ON. CREW DECLARED AN EMERGENCY AND LANDED WITHOUT ANY FURTHER EV ENT.LAV SMOKE DETECTOR FOUND FAULTY & REPLACED. 2 L 7 2 4F 4 F RT A21EA E15NE 2001040300084 20010403 00084 EA 2001 4 3 CA010213020 1 20010124 G 2740 ACTUATOR CNDAIR CL600 CL6002B19 EA GE CF34 CF343B1 NE HORIZONTAL STAB FAILED W C ABORTED TAKEOFF J WARNING INDICATION TO TAKEOFF 1 CA (CAN) DURING TAKEOFF ROLL, CONFIG TRIM AND CONFIG STAB WARNINGS APPEARED. CREW REJECTED TAKEOFF AND RETURNED TO BLOCKS.H STA AND MCU REPLACED. AIRCRAFT RETURNED TO SERVICE. 2 L 7 2 4F 4 F RT A21EA E15NE 2001032700211 20010327 00211 EA 2001 3 27 CA010213021 1 20010124 G 2740 STABILIZER CNDAIR CL600 CL6002B19 EA GE CF34 CF343B1 NE HORIZ STAB FAILED W O OTHER F FLT CONT AFFECTED CL CLIMB 1 CA (CAN) ON CLIMBOUT, STAB AND MACH TRIM DISENGAGED AT 8.2 UNITS AT NOSE UP TRIM. WOULD NOT RE-ENGAGE. AIRCRAFT PERFORMED A FLAP 20 DEGREES PER QRH WITHOUT ANY FURTHER EVENT. MAINTENANCE REPLACED THE HORIZONTAL STAB TRIM PANEL AND RETURNED AIR CRAFT TO SERVICE. 2 L 7 2 4F 4 F RT A21EA E15NE 2001032700212 20010327 00212 EA 2001 3 27 CA010213023 1 20010125 G 5610 WINDSHIELD CNDAIR CL6002B19 CNDAIR CL600 CL6002B19 EA GE CF34 CF343B1 NE F/O WINDSHIELD CRACKED W A UNSCHED LANDING D INFLIGHT SEPARATION CR CRUISE 1 CA 7037 (CAN) IN CRUISE FLIGHT, F/O WINDSHIELD SHATTERED. NO INFO ON ALTITUDE OR IF EMERGENCY WAS DECLARED. AIRCRAFT RETURNED IN TO SERVICE AFTER WINDSHIELD REPLACEMENT. 2 L 7 2 4F 4 F RT A21EA E15NE 2001032700213 20010327 00213 EA 2001 3 27 CA010213024 1 20010117 G 5610 NP1393219 WINDSHIELD CNDAIR CL600 CL6002B19 EA GE CF34 CF343B1 NE L/H WINDSHIELD CRACKED W D RETURN TO BLOCK O OTHER TX TAXI/GRND HDL 1 CA 00201H3495 (CAN) DURING TAXI, CAPTAIN WINDSHIELD CRACKED.AIRCRAFT RETURNED INTO SERVICE AFTER WINDSHIELD REPLACEMENT. 2 L 7 2 4F 4 F RT A21EA E15NE 2001032700214 20010327 00214 EA 2001 3 27 CA010213025 1 20010113 G 5610 NP1393216 WINDSHIELD CNDAIR CL600 CL6002B19 EA GE CF34 CF343B1 NE R/H WINDSHIELD CRACKED W O OTHER O OTHER CL CLIMB 1 CA 99298H2154 (CAN) CREW RPORTED THAT PASSING FLT 160 AT A DIFFERENTIAL CABIN PRESSURE 6,4, R/H WINDSHIELD CRACKED. NO INFO IF EMERGEN CY WAS DECLARED.AIRCRAFT RETURNED INTO SERVICE AFTER WINDSHIELD REPLACEMENT. 2 L 7 2 4F 4 F RT A21EA E15NE 2001040300085 20010403 00085 EA 2001 4 3 CA010213027 1 20010213 G 5730 PANEL CNDAIR CL600 CL6002B19 EA GE CF34 CF343B1 NE RT AND LT WING CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) WHILE JACKING AIRCRAFT, MAINTENANCE FOUND TWO CRACKS ON AFT SECTION OF LOWER WING PLANK. ONE ON THE LT AND ONE ON THE RT SIDE, AT WS 148, NEAR THE WING JACKING POINTS. REPAIR ACTIVE, AIRCRAFT WILL RETURN INTO SERVICE SOON. 2 L 7 2 4F 4 F RT A21EA E15NE 2001032700215 20010327 00215 EA 2001 3 27 CA010213028 1 20010130 G 7800 NAS6303U4 BOLT GE CF343B1 CNDAIR CL600 CL6002B19 EA GE CF34 CF343B1 NE DELTA BRCKET POS SHEARED W O OTHER O OTHER IN INSP/MAINT 1 CA 3100 (CAN) MAINTENANCE FOUND THE L/H EXHAUST NOZZLE CRACKED DURING A CHECK INSPECTION. DURING REPLACEMENT OF THE EXHAUST NOZZ LE, MAINTENANCE FOUND TWO (OUT OF THREE) DELTA BRACKETS ATTACH BOLTS SHEARED, AT 2 AND 10 OCLOCK POSITION.FAULTY PARTS R EPLACED PER AMM. 2 L 7 2 4F 4 F RT A21EA E15NE 2001032700216 20010327 00216 EA 2001 3 27 CA010213032 1 20010129 G 5610 WINDSHIELD CNDAIR CL600 CL6002B19 EA GE CF34 CF343B1 NE L/H WINDSHIELD CRACKED W O OTHER O OTHER CR CRUISE 1 CA (CAN) DURING CUSTOMER ACCEPTANCE FLIGHT, IN CRUISE, L/H WINDSHIELD CRACKED. L/H WINDSHIELD REMOVED AND REPLACED. 2 L 7 2 4F 4 F RT A21EA E15NE 2001040300086 20010403 00086 EA 2001 4 3 CA010214004 1 20010201 G 5210 601R31765303 STRUCTURE CNDAIR CL600 CL6002B19 EA GE CF34 CF343B1 NE PAX DOOR LATCH CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) DURING A ROUTINE E3 (1200 HOURS) INSPECTION WHEN REMOVING THE PASSENGER DOOR SIDE PANELS A CRACK WAS FOUND IN THE PASSENGER DOOR LATCH BOX ASSEMBLY 601R31765-3/03. THE AIRCRAFT REMAINED GROUNDED UNTIL A NEW LATCH BOX WAS INSTALLED. FO LLOWING THE REPLACEMENT OF THE FAULTY COMPONENT, THE AIRCRAFT WAS THEN RELEASED TO SERVICE. 2 L 7 2 4F 4 F RT A21EA E15NE 2001040300087 20010403 00087 EA 2001 4 3 CA010214008 2 20010112 G 8500 ENGINE PIPER PA28 PA28R200 7102811 SO LYC O360 IO360C1C 41514 EA ENGINE BAY FAILED W A UNSCHED LANDING Y J ENGINE STOPPAGE WARNING INDICATION CR CRUISE 1 CA 687 (CAN) ENGINE HAD STOPPED / SEIZED AFTER THE ENGINE HEATER PLATE WHICH HAD BEEN INSTALLED THE DAY BEFORE THE FLIGHT WAS D ISLODGED WHEN THE NOSE LANDING GEAR DRAG LINK CONTACTED WITH THE PLATE IN GEAR UP POSITION. THE PLANE LANDED THE PILOT D IDNT NOTICE ANYTHING. ON THE SECOND FLIGHT WHEN SELECTING GEAR UP THE PLATE WAS PUSHED ON THE QUICK DRAIN BY THE LANDING GEAR AND ALLOWED THE ENGINE OIL TO DRAIN COMPLETELY. ENGINE STOPPED THE PILOT HAD TO MAKE A FORCED LANDING IN A FIELD. ONLY MINOR DAMAGES WERE MADE TO THE PLANE. 1 L 7 1 3O 3 O 2A13 1E10 2001040300089 20010403 00089 SW 2001 4 3 CA010214011 1 20010119 G 2510 502565213 SHOULDER BELT HUGHES 269 269C1 8059504 SW LYC O360 HO360C1A 41514 EA COCKPIT FAILED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) MAIN STRAP SHREADED.REPLACED SHOULDER STRAP. 1 G 7 1 3O 3 O O 4H12 E286 2001040300091 20010403 00091 CE 2001 4 3 CA010214027 1 20010125 G 5753 0621229 HINGE CESSNA 305 305A 2074002 CE CONT O470 O47011 17026 SO LT WING TE FLAPS CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 3667 (CAN) WING FLAP HINGE INBOARD FOUND CRACKED AT BOTH LOWER FLANGES THAT ATTACH TO THE SPAR. PART REPLACED WITH NEW. 1 H 7 1 3O 3 O 5A5 E269 2001040400014 20010404 00014 CE 2001 4 4 CA010219009 1 20010129 G 2750 05235372 ROD CESSNA 172 172N 2072434 CE LYC O320 O320D2J 41508 EA TE FLAPS BENT W K NONE O OTHER IN INSP/MAINT 1 CA 9627 (CAN) FLAP ROD BENT. 1 H 7 1 3O 3 O NT 3A12 E274 2001040400017 20010404 00017 EU 2001 4 4 CA010219018 1 20010201 G 2611 72111211000 SMOKE DETECTOR BAG JETSTM JETSTM3101 1500215 EU GARRTT TPE331 TPE33110UG 01514 WP ROTOL R333 R333482F12 GL CARGO POD FAILED W A UNSCHED LANDING N FALSE WARNING CR CRUISE 1 CA (CAN) JUST AFTER TAKEOFF OUT OF LA RONGE HEADING NORTH APPROXIMATELY 80 MILES, THE BAGGAGE POD SMOKE ALARM WENT OFF. THE AIRSCREW TURNED AROUND, & DECLARED AN EMERGENCY TO LANDED BACK IN YVC. MAINTENANCE FOUND NO SMOKE OR FIRE IN THE POD. T HE SMOKE DETECTOR WAS REMOVED, THE LENSE WAS CLEANED, DETECTOR REINSTALLED AND TESTED S. THIS IS AN ONGOING PROBLEM WITH THIS UNIT IN THAT IF THE LENSE (SENSOR) GET A LITTLE DUSTY, IT WILL GIVE FALSE INDICATION. AIRCRAFT WAS REKEASED FOR SE RVICES. 2 L 7 2 4T 4 T RT A21EU E4WE 6 C P61GL 2001040400019 20010404 00019 EA 2001 4 4 CA010219021 2 20010205 G 8500 ENGINE PIPER PA31 PA31350 7103110 SO LYC O540 TIO540J2BD 41532 EA RIGHT FAILED W A UNSCHED LANDING R J PARTIAL RPM/PWR LOSS WARNING INDICATION CL CLIMB 1 CA 821 (CAN) AFTER TAKEOFF OUT OF URANIUM CITY PILOT HAD TO RETURN TO AIRPORT AFTER EXPERIENCING LOSS OF POWER ON RT ENGINE. MA INTENANCE INVESTIGATED AND FOUND THAT THE ACCESSORY CASE COMPONENT DRIVE GEARS WOULD NOT TURN. ALSO FOUND OIL FILTER FUL L OF METAL. MATINTENANCE SUSPECTS THAT ONE OF THE DRIVE GEARS IN THE ACCESSORY CASE HAS LET GO. ENGINE IS BEING SENT TO PRO AERO ENGINES FOR STRIP DOWN AND REPAIR. FURTHER REPORT TO FOLLOW. 1 L 7 2 3O 3 O A20SO E14EA 2001040400023 20010404 00023 NM 2001 4 4 CA010222010 1 20010205 G 2720 82700544001 CONTROL CABLE DHAV DHC8 DHC8* NM PWA 120 PW120 NE RUDDER BROKEN W D RETURN TO BLOCK F FLT CONT AFFECTED TX TAXI/GRND HDL 1 CA (CAN) AFTER ENGINE STARTING, BEFORE TAXIING OUT FOR TAKEOFF, CREW CHECKED CNTLS FOR FREEDOM OF MOVEMENT. AT THAT TIME, P ILOT FOUND THAT RUDDER PEDALS WERE NOT HAVING ANY RESISTANCE WHEN MOVED&WITH BOTH ENGINES RUNNING HE COULD NO T SEE ANY RUDDER MOVEMENT ON AFCS IND. AT TIME HE CALLED OFF FLT, SHUTDOWN ENGINES&CALLED MAINT. MAINTENACE CREW ARRIVED ATTHE SCE NE FOUND RUDDER CABLE ASSY BROKEN. DETAILED INSP IN THE AREA REVEALED RUDDER CABLE ASSY NEXT TO 1ST ONE - DAMAGED, CORRO DED, WITH 30 PERCENT OF DIAMETER, WIRES BROKEN. LOOKING TO GET ACCESS TO ALL INVOLVED AREA, THOROUGH INSP REVEALED PORT SIDE ELEV CABLE ASSY 2 H 7 2 4T 4 T RT A13NM E20NE 2001040400024 20010404 00024 NM 2001 4 4 CA010222011 1 20010206 G 4940 8Z7591125 BRACKET DHAV DHC8 DHC8* NM PWC 150 PW150A EA APU DAMAGED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) DURING TROUBLESHOOTING FOR APU FAILED START, THE GROUND CABLE FROM APU SHUNT WAS FOUND SEPARATED FROM 4900-GS10 (S TN X792) ON BRACKET. THE ATTACHMENT BRACKET WAS FOUND BURNT AS WELL AS THE CABLE CONNECTION. SYD WAS ISSUED AND THE CAB LE WAS REPAIRED AND INSTALLED. BASED ON THE INFORMATION PROVIDED BY THE OPERATOR, IT IS BELIEVED THAT THE MOST PROBABLE CAUSE OF DAMAGE WAS IMPROPER INSTALLATION TORQUING OF THE GROUND STUD AND ATTACHING HARDWARE. 2 H 7 2 4T 4 T RT A13NM E00062EN 2001040400025 20010404 00025 CE 2001 4 4 CA010222015 1 20010212 G 2752 D14500462 TRANSMISSION CESSNA 208 208B 2073701 CE PWA PT6 PT6A114A 52043 NE MCAULY 3AF34C 3GFR34C703 GL TE FLAPS FAILED W D RETURN TO BLOCK F FLT CONT AFFECTED TX TAXI/GRND HDL 1 CA (CAN) AFTER LANDING THE PILOTS SELECTED FLAPS TO THE UP POSITION AND THE FLAP CIRCUIT BREAKER POPPED. THE FLAP CIRCUIT B REAKER WAS RESET AND THE FLAPS WERE SELECTED UP NORMALLY. WHEN THE FLAPS WERE RESELECTED TO THE DOWN POSITION THE CIRCUI T BREAKER POPPED AGAIN. THE FLAP TRANSMISSION AND MOTOR ASSEMBLY WERE REPLACED AND THE AIRCRAFT RETURNED TO SERVICE. 1 H 7 1 3T 3 T A37CE E4EA 5 C P60GL 2001040400026 20010404 00026 CE 2001 4 4 CA010222016 1 20010212 G 7160 NAS561C410 ROLL PIN CESSNA 26520251 CESSNA 208 208B 2073701 CE PWA PT6 PT6A114A 52043 NE MCAULY 3AF34C 3GFR34C703 GL BELLCRANK BROKEN W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) DURING THE ROUTINE 100 HOUR INSPECTION THE AIRCRAFT ENGINEER FOUND THAT THE ROLL PINS, QUANTITY 4, SECURING THE BE LL CRANK TO THE AIR BYPASS DUCT FOR THE ENGINE, WERE LOOSE. UPON RMEOVAL WE FOUND THAT ALL FOUR PINS WERE BROKEN. PIN RE PLACED WITH NEW. 1 H 7 1 3T 3 T A37CE E4EA 5 C P60GL 2001040400028 20010404 00028 CE 2001 4 4 CA010223002 1 20010206 G 6100 BLADE MCAULY 1C172MDM CESSNA 172 172 2072402 CE CONT O300 O300A 17022 SO MCAULY 1C172 1C172MDM GL PROPELLER CORRODED W K NONE O OTHER IN INSP/MAINT 1 CA 765 633 71581 (CAN) EXTRA WORK REQUIRED TO REMOVE CORROSION FROM BLADE FACE (CAMBER FACE) IN ACCORDANCE WITH MCCAULEY MANUAL 730720. 1 H 7 1 3O 3 O NT 3A12 E253 5 N P910 2001040400032 20010404 00032 NM 2001 4 4 CA010223007 1 20010131 G 2435 23088002B STARTER GEN DHAV DHC8 DHC8102 2809003 NM PWA 120 PW120A NE HAMSTD 14SF 14SF7 NE NR 2 ENGINE DISINTEGRATED W D RETURN TO BLOCK E VIBRATION/BUFFET TX TAXI/GRND HDL 1 CA 15963 773 611A (CAN) A VIBRATION WAS FELT DURING START-UP ON NR 2 ENGINE AND THEN DURING TAXI THE NR 2 D.C. GENERATOR LIGHT CAME ON. TH E CREW WERE UNABLE TO SUCCESSFULLY RESET THE NR 2 GENERATOR AND RETURNED TO THE GATE. INVESTIGATION REVEALED THE NR 2 GE NERATOR FAN END BEARING HAD FAILED. STARTER GENERATOR REPLACED. 2 H 7 2 4T 4 T RT A13NM E20NE 6 C P7NE 2001040400033 20010404 00033 NM 2001 4 4 CA010223008 1 20010120 G 2910 82970010391 LINE DHAV DHC8 DHC8102 2809003 NM PWA 120 PW120A NE HAMSTD 14SF 14SF7 NE HYDRAULIC SYS LEAKING W O OTHER K J FLUID LOSS WARNING INDICATION TX TAXI/GRND HDL 1 CA 31326 (CAN) UPON ARRIVAL AT THE GATE HYDRAULIC FLUID WAS NOTICED TO BE LEAKING FROM THE LT WHEEL WELL AREA. INVESTIGATION REVE ALED THAT THE AFT NR 1 DOOR CLOSE LINE WAS LEAKING.LINE REPLACED. 2 H 7 2 4T 4 T RT A13NM E20NE 6 C P7NE 2001040400034 20010404 00034 NM 2001 4 4 CA010223010 1 20010120 G 2910 82950010277 LINE DHAV DHC8 DHC8102 2809003 NM PWA 120 PW120A NE HAMSTD 14SF 14SF7 NE HYDRAULIC SYS LEAKING W K NONE O OTHER IN INSP/MAINT 1 CA 25366 (CAN) A PUDDLE OF HYDRAULIC FLUID WAS NOTICED AROUND THE LT MAIN WHEEL AREA. INVESTIGATION REVEALED THAT THE LEAK WAS CO MING FROM THE LT OUTBOARD ROLL SPOILER LIFT DUMP LINE.LINE REPLACED. 2 H 7 2 4T 4 T RT A13NM E20NE 6 C P7NE 2001040400038 20010404 00038 CE 2001 4 4 CA010226002 1 20010215 G 2431 A876K TERMINAL CESSNA 560 560XL CE PWA 545 PW545A NE BATTERY FAILED W K NONE O OTHER IN INSP/MAINT 1 CA 474 (CAN) AIRCRAFT ARRIVED AT ST. HUBERT (YHU) PILOTS SHUT DOWN ENGINES AND APU, HAD NO POWER ON AIRCRAFT WITH BATTERY SWITC H ON BATTERY. PILOT TOOK SWITCH AND TOGGLED IT TO OFF AND THEN TO EMERGENCY POWER AND STILL NO POWER ON AIRCRAFT. UNABLE TO PUT BATTERY ON LINE. 2 L 7 2 4F 4 F RT A22CE E00059EN 2001040400039 20010404 00039 EA 2001 4 4 CA010226005 1 20010203 G 4990 APU CNDAIR CL600 CL6002B19 EA GE CF34 CF343B1 NE APU BAY LEAKING W O OTHER K J FLUID LOSS WARNING INDICATION AP APPROACH 1 CA (CAN) THE CREW REPORTED THE SMOKE TOILET CAUTION MESSAGE AT 9000 FEET. SMOKE WAS VISIBLE WHEN BLEED WAS TRANSFERRED IN C ABIN AND COCKPIT WHEN BLEEDS WERE TRANSFERRED TO APU. AIRCRAFT DID AN EMERGENCY LANDING.THE MAINTENANCE FOUND OIL COMING FROM COMPRESSOR DRAIN OF THE APU. APU WAS DEFERRED TO BE REPLACED LATER. 2 L 7 2 4F 4 F RT A21EA E15NE 2001040400040 20010404 00040 EA 2001 4 4 CA010226008 1 20010206 G 5610 601R3303312 WINDSHIELD CNDAIR CL600 CL6002B19 EA GE CF34 CF343B1 NE COCKPIT FAILED W O OTHER O OTHER CR CRUISE 1 CA (CAN) THE RT WINDSHIELD SHATTERED IN CRUISE DURING THE FLIGHT NR 5.THE MAINTENANCE REPLACED THE WINDSHIELD. 2 L 7 2 4F 4 F RT A21EA E15NE 2001040400041 20010404 00041 EA 2001 4 4 CA010226009 1 20010206 G 5610 601R330339 WINDSHIELD CNDAIR CL600 CL6002B19 EA GE CF34 CF343B1 NE COCKPIT FAILED W O OTHER O OTHER CL CLIMB 1 CA (CAN) THE LT WINDSHIELD SHATTERED IN CRUISE AT 35,000 DURING THE FLIGHT NR 5.THE MAINTENANCE REPLACED THE WINDSHIELD. 2 L 7 2 4F 4 F RT A21EA E15NE 2001040400042 20010404 00042 EA 2001 4 4 CA010226010 1 20010202 G 5610 NP1393222 WINDOW CNDAIR CL600 CL6002B19 EA GE CF34 CF343A1 30015 NE COCKPIT CRACKED W O OTHER O OTHER CR CRUISE 1 CA (CAN) THE RT WINDOW CRACKED IN CRUISE. THE MAINTENANCE REPLACED THE WINDOW. 2 L 7 2 4F 4 F RT A21EA E15NE 2001040400043 20010404 00043 EA 2001 4 4 CA010226011 2 20010205 G 7414 4347 MAGNETO HUGHES 269 269C1 8059504 SW LYC O360 HO360C1A 41514 EA ENGINE FAILED W O OTHER E VIBRATION/BUFFET TX TAXI/GRND HDL 1 CA 576 (CAN) AIRCRAFT HARD TO START. RETARD LOW INTENSITY SPARK. REPLACED MAGNETO. 1 G 7 1 3O 3 O O 4H12 E286 2001040400044 20010404 00044 SW 2001 4 4 CA010226012 1 20010125 G 8011 SAZ4401 RELAY HUGHES 269 269C1 8059504 SW LYC O360 HO360C1A 41514 EA STARTER FAILED W O OTHER O OTHER TX TAXI/GRND HDL 1 CA (CAN) ENGAGEMENT INTERMITTENT DUE TO VIBRATION. REPLACED STARTER RELAY. 1 G 7 1 3O 3 O O 4H12 E286 2001040400046 20010404 00046 EA 2001 4 4 CA010226018 2 20010101 G 7414 4250R MAGNETO CESSNA 172 172M 2072418 CE LYC O320 O320E2D 41508 EA MCAULY 1C160 1C160DTM GL ENGINE FAILED W O OTHER R J PARTIAL RPM/PWR LOSS WARNING INDICATION CR CRUISE 1 CA 525 (CAN) ENGINE STARTING RUNNING ROUGH IN CRUISE FLIGHT PILOT RETURNED TO STATION. GROUND RUN INDICATED EXCESSIVE RPM LOSS ON RT MAGNETO. MAGNETO REPLACED AND FOLLOW UP GROUND RUN CARRIED OUT RESULTING IN NORMAL RPM (STATIC) AND RT RPM DROP WI THIN LIMITS. NO APPARENT EXTERNAL PROBLEMS WITH MAGNETO COULD BE IDENTIFIED. AN SC REPORT MAY FOLLOW SHOULD WE CHOOSE TO HAVE THE MAGNETO OVERHAULED. 1 H 7 1 3O 3 O NT 3A12 E274 5 N P910 2001040400047 20010404 00047 WP 2001 4 4 CA010226020 2 20010201 G 7412 103784005C EXCITER GULSTM 690TP 690D 3970405 SW GARRTT TPE331 TPE331* 01514 WP ROTOL R306 R306382F7 GL LT ENGINE SHORTED W O OTHER O OTHER TX TAXI/GRND HDL 1 CA 5 (CAN) LT ENGINE WOULD NOT START. NO IGNITION. IGNITION SYSTEM CHECKED AND THE EXCITER WAS FOUND TO BE AT FAULT. 1 H 7 2 3T 3 T 2A4 E2WE 6 C P8EU 2001040400048 20010404 00048 NM 2001 4 4 CA010228008 1 20010206 G 6320 A0061 GEARBOX ROBSIN R22 R22BETA NM LYC O360 O360J2A 41514 EA MAIN ROTOR FAILED W A UNSCHED LANDING J WARNING INDICATION CR CRUISE 1 CA 1747 (CAN) MAIN ROTOR GEARBOX CHIP DETECTOR LIGHT ACTIVATED IN FLIGHT. PILOT LANDED ON GROUND LIGHT WENT OUT. CHIP DETECTOR R EMOVED AT MAINTENANCE FACILITY. FUZZ PARTICULATE FOUND, DETECTOR CLEANED, INSPECTED, REINSTALLED. HELICOPTER GROUND RUN ON GROUND FOR 30 MINUTES WITH NO LIGHT INDICATION. GEARBOX OIL REPLACED AT CUSTOMER REQUEST. 1 G 7 1 3O 3 O H10WE E286 2001040400049 20010404 00049 EU 2001 4 4 CA010228009 1 20010227 G 5302 SKIN SNIAS 350 AS350BA 8680817 EU TAILBOOM WRONG PART W O OTHER W INADEQUATE Q C LD LANDING 1 CA 14116 (CAN) - TAILBOOM COLLAPSED AFTER LANDING. - TAIL ROTOR DRIVE DISCONNECTED, FAILING DAMAGE.- LOWER FORWARD SKIN BUCKLED A ND FRACTURED BETWEEN NR 3 AND 4 BEARING. - FAILURE ANALYSIS FOUND WRONG SKIN THICKNESS.- MEASURES 0.0325 INCH, SHOULD BE 1.0MM (0.03937 INCH). - OPERATOR INSPECTED FLEET OF 6 OTHERS AND FOUND AIRCRAFT S/N 2495 ALSO HAS INCORRECT SKIN. - BOO MS ARE FACTORY ORIGINAL - NO REPAIR HISTORY. - EUROCOPTER USA ADN HAWAII FAA NOTIFIED. 1 G 7 1 3U NC H9EU 2001040400050 20010404 00050 NE 2001 4 4 CA010301002 2 20010103 G 7310 226311001 LINE HONEYWELL BAG BAE146 BAE146200A 1500266 EU LYC ALF502 ALF502R5 41580 NE ENGINE FUEL MISREPAIRED W K NONE W INADEQUATE Q C IN INSP/MAINT 1 CA (CAN) DURING RECEIPT OF A LOANER ENGINE, IT WAS NOTED THAT ONE OF THE INSTALLED LINES FROM THE FLOW DIVIDER TO THE FUEL MANIFOLD HAD AN UNAPPROVED WELD REPAIR ACCOMPLISHED ON IT. THE LINE WAS REPLACED. 2 H 7 4 4F 4 F RT A49EU E6NE 2001040400051 20010404 00051 NM 2001 4 4 CA010301004 1 20010127 G 2910 82950010175 LINE DHAV DHC8 DHC8102 2809003 NM PWA 120 PW120A NE HAMSTD 14SF 14SF7 NE HYDRAULIC SYS LEAKING W K NONE K FLUID LOSS IN INSP/MAINT 1 CA (CAN) DURING ROUTINE INSPECTION, HYDRAULIC FLUID WAS FOUND LEAKING FROM THE LT WING INBOARD FLAP CANOE. INVESTIGAITON RE SULTED IN REPLACEMENT OF A LEAKING FLIGHT SPOILER UNLOAD LINE. 2 H 7 2 4T 4 T RT A13NM E20NE 6 C P7NE 2001040400052 20010404 00052 EA 2001 4 4 CA010301005 1 20010209 G 7112 311269001 ADAPTER DHAV DHC8 DHC8311 1386006 EA PWA PW120 PW123 NE HAMSTD 14SF 14SF15 NE VENTURI CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) DURING SCHEDULED INSPECTION OF THE R/H ENGINE, THE ENGINE BLEED AIR VENTURI ADAPTER WAS FOUND TO HAVE A V SHAPED C RACKED ON THE OUTSIDE OF THE 90 DEGREE BEND OF THE VENTURI. THE VEE HAD OPENED UP, ALLOWING BLEED AIR TO BE DUMPED INTO THE ENGINE COMPARTMENT. THE ADAPTER WAS REPLACED AND THE AIRCRAFT WAS RETURNED TO SERVICE. (THIS AREA OF THE ADAPTER IS COVERED WITH A SHROUD, MAKING INSPECITON A DELIBERATE ACTION.) 2 H 7 2 4T 4 T RT A13NM E20NE 6 C P7NE 2001040400196 20010404 00196 NE 2001 4 4 CA010301017 2 20010117 G 7200 ENGINE BOEING 767 7673S1 1385211 NM GE CF6 CF680C2B2 30025 NE RIGHT FAILED W E ENGINE SHUTDOWN Y ENGINE STOPPAGE LD LANDING 1 CA 32338 32338 720611 (CAN) ON FINAL INTO YYZ, RIGHT ENGINE SHUTDOWN, 4 MINUTES TO LANDING. ENGINE SHUTDOWN CHECKLIST COMPLETED. LANDED WITHOU T INCIDENT. ON INSPECTION OF RT ENGINE METAL FOUND IN TAILPIPE. RT ENGINE REPLACED. OFF PART NUMBER 6-7200-9-0002, SERIA L NUMBER 2611.2001-03-06 TC: EXPECT OPERATOR TO FOLLOW-UP WHEN TEAR DOWN AVAILABLE. 2 L 7 2 4F 4 F RT A1NM E13NE 2001040400199 20010404 00199 NE 2001 4 4 CA010301029 1 20010216 G 6210 S611520107 BLADE SKRSKY S61 S61N 8142104 NE GE CT58 CT581401 30011 NE MAIN ROTOR DEBONDED W K NONE O OTHER IN INSP/MAINT 1 CA 8770 (CAN) AIRCRAFT LANDED TO REFUEL. IT WAS NOTED THAT DURING A WALKAROUND THAT, A ROTOR BLADE POCKET HAD BECOME DEBONDED. A TEMPORARY REPAIR WAS MADE AND THE AIRCRAFT WAS FLOWN BACK TO BASE. 2 G 7 2 4U 4 U 1H15 1E3 2001040400200 20010404 00200 EA 2001 4 4 CA010301030 1 20010301 G 2750 72740196011 TUBE DHAV DHC7 DHC7103 2802710 EA PWA PT6 PT6A50 52043 EA HAMSTD 24PF 24PF305 GL FLAP DRIVE WORN W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) DURING INSPECTION, SEVERE WEARING WAS NOTED ON OUTBOARD FLAP DRIVE SECONDARY DRIVE TUBE P/N 72740196-011 BY THE ST EADY BEARINGS. UNABLE TO DETECT WEAR PROPERLY UNLESS STEADY BEARING REMOVED. WEAR WAS FOUND ON BOTH SIDES OF FLAP DRIVE SYSTEM. MAXIMUM WEAR FOUND 0.0265 INCH. TUBE THICKNESS APPROXIMATELY 0.040. BOTH WORN TUBES REPLACED WITH SERVICEABLE UN ITS. 2 H 7 4 4T 4 T A20EA E4EA 6 C P1NE 2001040400201 20010404 00201 NE 2001 4 4 CA010301031 1 20010209 G 2910 3935 SHUTOFF VALVE SKRSKY S76 S76A 8143006 NE ALLSN 250C 250C30S 03013 GL ACTUATOR LEAKING W E D ENGINE SHUTDOWN RETURN TO BLOCK K J FLUID LOSS WARNING INDICATION TX TAXI/GRND HDL 1 CA 162 (CAN) ON START UP THE NR 1 SERVO JAM WARNING LIGHT WOULD NOT EXTINGUISH WHEN NORMAL HYDRAULIC PRESSURE WAS REACHED. THE FLIGHT CREW SHUT DOWN AND UPON EXITING THE AIRCRAFT SAW HYDRAULIC FLUID UNDER THE AIRCRAFT. THE ENGINEER FOUND THE NR 1 HYDRAULIC SYSTEM FLUID LOW WHICH CAUSED THE NR 1 SERVO JAM LIGHT TO STAY ON. FURTHER INVESTIGATION FOUND THE TAIL SERVO SHUT OFF VALVE LEAKING FROM THE ELECTRICAL ACTUATOR BODY. THE VALVE WAS REPLACED, NR 1 HYDRAULIC SYSTEM REPLENISHED AND BLED. THE AIRCRAFT WAS TEST FLOWN AND THEN RETURNED TO SERVICE. 1 G 7 2 3U 3 U H1NE E1GL 2001040400202 20010404 00202 EA 2001 4 4 CA010301032 1 20010213 G 3246 901230602 FITTING DHAV DHC2 DHC2MK1 2800102 EA PWA R985 R985AN14B 52008 NE LT FLOAT CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) CORROSION AND STRESS CRACK DEVELOPED ON THE TAPER HOLE OF THE SPREADER BAR ATTACH FITTING LT FLOAT AFT SPREADER AT TACH P/N 901-23060-2 WAS REMOVED AND QUARANTINED. REPLACEMENT P/N S1901-23060-2 INSTALLED AS PER STC SF-92-7. 1 H 7 1 3R 3 R A806 5E1 2001040400203 20010404 00203 EA 2001 4 4 CA010301033 1 20010213 G 3246 901230602 FITTING DHAV DHC2 DHC2MK1 2800102 EA PWA R985 R985AN14B 52008 NE LT FLOAT CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) CORROSION AND STRESS CRACK DEVELOPED ON THE TAPER HOLE OF THE SPREADER BAR ATTACH FITTING RT FLOAT FORWARD SPREADE R ATTACH WAS REMOVED AND QUARANTINED. REPLACEMENT P/N S1901-23060-2 INSTALLED AS PER STC SF-92-7. 1 H 7 1 3R 3 R A806 5E1 2001040400204 20010404 00204 EA 2001 4 4 CA010301035 2 20010216 G 8540 LW10292 IDLER GEAR PIPER PA31 PA31350 7103110 SO LYC O540 TIO540J2BD 41532 EA ENGINE WORN W K NONE O OTHER IN INSP/MAINT 1 CA 820 (CAN) THE IDLER GEAR BETWEEN THE CRANKSHAFT AND THE CAMSHAFT GEAR DISENGAGED DUE TO FRACTURING OF THE CRANKCASE AND ACCE SSORY CASE. THESE FRACTURES ARE DIRECTLY OPPOSITE THE CRAN GEAR AND WOULD INDICATE THAT A SOLID OBJECT WENT IN BETWEEN T HE CRANK GEAR AND IDLER GEAR. THE UPPER ROW OF TEETH ON THE IDLER, DRIVES THE MAGNETO AND THERE IS ONE TOOTH MISSING. TH IS MISSING TOOTH IS PROBABLY WHAT WENT IN BETWEEN THE GEARS. 1 L 7 2 3O 3 O A20SO E14EA 2001040400205 20010404 00205 EA 2001 4 4 CA010301036 2 20010212 G 7250 3027102 TURBINE BLADES PWA PT6T PT6T3 52045 EA ENGINE WRONG PART W K NONE W INADEQUATE Q C IN INSP/MAINT 1 CA 3000 (CAN) POWER TURBINE SECTION DISASSEMBLED FOR EVALUATION. POWER TURBINE BLADES SHOWED A DIFFERENT CONFIG THAN P/N 302710 2 POWER TURBINE BLA DES NORMALLY FOUND ON THIS MODEL ENGINE. ALSO PART NO (P/N 3013102) STAMPED ON BLADES WAS CROSSED OU T & P/N 3027102 WAS ENGRAVED. P&W WAS NOTIFIED & RESPONDED THAT SUBJECT BLADES WERE APPLICABLE TO A PT6A ENGINE & NOT PT 6T. THEY ALSO STATED THAT THERE IS NO APPRD MODS THAT WOULD ALLOW 3013102 BLADES TO BE REIDENTIFIED. P&WSTATES BLADES MU ST BE REMVD FROM SERVICE. 2001-03-05 TC: FORWAEDED TO MAINT & MFG S.U.P. 4 U E22EA 2001040400229 20010404 00229 CE 2001 4 4 CA010302006 1 20010214 G 5312 07126161 BULKHEAD CESSNA 182 182H 2072718 CE CONT O470 O470R 17026 SO MCAULY 2A34C 2A34C50 GL VERTICAL STAB CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 4269 (CAN) CRACK ABOVE LT RUDDER STOP BOLT LOCATION ON (BULKHEAD) FLANGE BEND RADIUS DIRECTLY ABOVE BOLT. A/C HANGARED FOR LA ST 15 YRS & NOT SUBJECTED TO WIND. REMOVAL & INSP SHOWS POOR STANDARD PRACTISE OF DRIVING 90 DEGS STIFFENER INTO BEND RA DIUS OF FLANGE (ASSY IS SANDWICH OF STIFFENERS). THUS WHEN RUDDER STOP BOLT JAM NUT IS TIGHTENED, STIFFENER CUTS INTO BE ND RADIUS. REPL PART WORSE&REJECTED (NEW). NEW BULKHEAD STIFFENER PLAC ED SO AS TO RIDE UP BEND RADIUS ENOUGH TO FIT 0.0 15 FEELER GAUGE. ASSY MANUFACTURED & RIVETED WITH GAP. FEW STROKES WITH FILE WOULD MATCH BEND RADIUS & NOT CAUSE PROBLEM DURING MANUFACTURE: SK210-161-1 WILL BE INST (SEB99-12R1). 1 H 7 1 3O 3 O NT 3A13 E273 5 C P3EA 2001040400207 20010404 00207 EU 2001 4 4 CA010302007 1 20010214 G 2912 583400 FILTER 704A44633025 SNIAS 350 AS350B2 8680813 EU TMECA ARRIEL ARRIEL1D NE HYD SYSTEM CLOGGED W A UNSCHED LANDING F FLT CONT AFFECTED HO HOVERING 1 CA 257 (CAN) - UPON HOVERING IN AERIAL LONG LINE WORK. THE PILOT NOTICED SOME FEEDBACK IN CYCLIC CONTROLS WHEN INPUTING AGGRESS IVE MOVEMENTS (I.E. WINDY CONDITIONS). HE IMMEDIATELY ABORTED THE TASK AT HAND AND LANDED.- ON INSPECTION OF HYDRAULIC F ILTER FOUND A BLACK DEPOSIT IN FILTER MEDIA.- THIS IS ABNORMAL CONSIDERING THE 500 HR FILTER LIFE, AND TAFT OF 257.2 HOU RS. - POSSIBLE CAUSE: DEPOSITS INSIDE HYDRAULIC LINES AND COMPONENTS AT TIME OF MANUFACTURE AND HIGH DETERGENT ATTRIBUTE S OF AEROSHELL FLUID 41). 1 G 7 1 3U 3 U H9EU E19EU 2001040400210 20010404 00210 CE 2001 4 4 CA010302010 1 20010131 G 3230 ALM50 CURRENT LIMITER BEECH 200 200BEECH 1152920 CE PWA PT6 PT6A41 52043 EA HARTZL HCD4N3 HCD4N3A GL MLG FAILED W O OTHER J WARNING INDICATION AP APPROACH 1 CA (CAN) AIR NUNAVUT KING AIR WAS ON APPROACH TO IGALUIT AT NIGHT. FLIGHT CREW SELECTED GEAR, THEY RECEIVED AN UNSAFE GEAR INDICATION AND HAD TO USE GEAR EMERGENCY EXTENSION METHOD, AFTER WHICH GAVE 3 GREEN GEAR DOWN AND LOCKED INDICATION. THE AIRCRAFT LANDED WITHOUT FURTHER INCIDENT. AN INSPECTION OF LANDING GEAR SYSTEM WAS ACCOMPLISHED. IT WAS DISCOVERED THAT R/H GENERATOR BUS POWER LIMITER HAD FAILED. MAINTENANCE WAS UNSUCCESSFUL AT FINDING A CAUSE FOR LIMITER FAILURE. NEW PO WER LIMITER INSTALLED. GEAR SWINGS ACCOMPLISHED AS PER AVIA DESIGNS MAINTENANCE MANUAL. AIRCRAFT RETURNED TO SERVICE. 1 L 7 2 4T 4 T A24CE E4EA 5 C STC 2001040400211 20010404 00211 EU 2001 4 4 CA010302012 1 20010302 G 6240 1179405303 INDICATOR BOLKMS 117 BK117A4 5626017 EU LYC LTS101 LTS101650B1 41560 NE TRIPLE TACH FAULTY W A UNSCHED LANDING N FALSE WARNING CR CRUISE 1 CA 12 468 (CAN) NR (ROTOR RPM) NEEDLE STARTED TO READ LOW. PILOTS RECOGNIZED THIS AS AN INDICATION PROBLEM. PILOTS LANDED AT BASE WITHOUT INCIDENT. PROBLEM WAS CORRECTED BY INSTALLING A SERVICEABLE TACHOMETER. 1 G 7 2 3U 3 U H13EU E5NE 2001040400213 20010404 00213 CE 2001 4 4 CA010302014 1 20010209 G 3040 10138402522 WINDSHIELD BEECH B300 B300 1159232 CE PWA PT6 PT6A60A 52043 NE COCKPIT CRACKED W A UNSCHED LANDING O OTHER CR CRUISE 1 CA 1205 98108H3288 (CAN) WHILE IN CRUISE FLIGHT AT FL310 AND OAT -46 DEGREES C, A LOUD BANG WAS HEARD AND THE RT WINDSHIELD CRACKED. (WINDS HIELD HEAT HAD BEEN ON FOR THE ENTIRE FLIGHT (1 HOUR PLUS)). FLIGHT CREW REFERENCED ABNORMAL OCCURRENCE IN POH AND MADE AN UNSCHEDULED, UNEVENTFUL LANDING IN YYC. AIRCRAFT GROUNDED FOR WINDSHIELD REPLACEMENT. NOTE: SIMILAR OCCURRENCE TO LT WINDSHIELD FAILURE IN OCTOBER 1999. 2 L 7 2 4T 4 T RT A24CE E4EA 2001040400221 20010404 00221 NM 2001 4 4 CA010306015 1 20010128 G 2120 UNKNOWN DHAV DHC8 DHC8* NM PWC 150 PW150A EA CABIN ODOR W A UNSCHED LANDING B SMOKE/FUMES/ODORS/SPARKS CL CLIMB 1 CA (CAN) DURING A TAKEOFF A SMELL WAS NOTED AND INCREASE DRAMATICALLY DURING THE CLIMB. CREW NOTED THAT THERE WAS NO VISIBL E SIGN OF SMOKE. CREW RETURNED TO BASE FOR INVESTIGATION. MAINTENANCE CARRIED OUT AN APU START, BLEED ON, SMELL PRESENT FOR 2 MIN. THEN DISAPPEARED. ENGINE RUN PERFORMED NO SMELL. DC CONTACTOR BOXES CHECKED, NO FAULT. AREA AROUND WATER BOIL ER INSPECTED, NO FAULT. EPCU CHECKED FOR FAULT CODES, NO FAULT. CDS CHECKED, NO FAULT. ENGINE RUN PERFORMED AGAIN, NO FA ULT. AIRCRAFT RETURNED TO SERVICE. 2 H 7 2 4T 4 T RT A13NM E00062EN 2001040500066 20010405 00066 CE 2001 4 5 CA010307004 1 20010220 G 3246 C1630030201 WHEEL MCAULY CESSNA 172 172M 2072418 CE LYC O320 O320E2D 41508 EA NLG DAMAGED W D RETURN TO BLOCK O OTHER TX TAXI/GRND HDL 1 CA (CAN) REPORTED TO MAINTENANCE OF CLICKING NOISE FROM FRONT AREA DURING TAXI. INSPECTION REVEALED THREE (3) THRU BOLTS MI SSING ON WHEEL RIM RESULTING IN DAMAGE TO NOSE FORK. TWO OF THREE REMAINING BOLTS FOUND LOOSE. SUSPECT INCORRECT TORQUE ON WHEEL BOLTS. 1 H 7 1 3O 3 O NT 3A12 E274 2001040500067 20010405 00067 SW 2001 4 5 CA010307007 1 20010214 G 6230 206010332121 BEARING BELL 206040002007 BELL 206 206B 1181511 SW ALLSN 250C 250C20 03013 GL MAST CORRODED W K NONE O OTHER IN INSP/MAINT 1 CA 4456 1461 NOF4734 (CAN) SEVERE PITTING OF LOWER BEARING JOURNAL INNER RACE AT LOWER PORTION OF MAST ASSEMBLY. 1 G 7 1 3U 3 U H2SW E4CE 2001040500072 20010405 00072 SW 2001 4 5 CA010307013 1 20010109 G 6510 206040102103 COVER BELL 206 206L 1181522 SW ALLSN 250C 250C20B 03013 GL T/R COUPLING GROOVED W K NONE O OTHER IN INSP/MAINT 1 CA 15 (CAN)WHEN REINSTALLING A MAIN DRIVESHAFT AFTER A INPUT TRANSMISSION SEAL REPLACEMENT, FOUND THAT THE TRANSMISSION END OF THE SHAFT COULD NOT MOVE. OPENED THE COUPLING END FOUND THAT SPRINGS WAS NOT INSTALLED PROPERLY. THE COVER WAS GROOVE D. INSPECTED THE INNER AND OUTER COUPLING ON BOTH END OF DRIVESHAFT ASSEMBLY. NO MORE DAMAGE FOUND 15.0 HOUR SINCE LAST INSPECTION. COMPLETED THE SHAFT INSPECTION AFTER REPLACING THE COVER AND THE SPRING THAT WERE DAMAGED BY NEW PARTS. A/C WAS RETURNED TO SERVICE. 1 G 7 1 3U 3 U H2SW E4CE 2001040500074 20010405 00074 WP 2001 4 5 CA010307015 1 20010225 G 6310 ENGINE LKHEED 1011 1011385114 WP RROYCE RB211 RB21122B02 54555 NE ENGINE FAILED W A UNSCHED LANDING O OTHER CL CLIMB 1 CA 47592 (CAN) AFTER TAKEOFF ENGINE NR 3 VIBS INCREASED TO 2.5 UNITS, THROTTLE RETARDED TO KEEP BELOW LIMITS. AIRCRAFT RETURNED T O MAINTENANCE BASE YMX. TROUBLESHOOTING CARRIED OUT AS PER MM 79-00-00 PAGE 121, ENGINE RUNS CARRIED OUT AS PER TEST NR 21 VIBRATIONS WITHIN LIMITS, AIRCRAFT RETURNED TO SERVICE.SUSPECT OIL FINDING. 2 L 7 3 4F 4 F A23WE E12EU 2001040500076 20010405 00076 NE 2001 4 5 CA010307017 2 20010218 G 7200 ENGINE LKHEED 1011 1011385115 5265015 WP RROYCE RB211 RB21122B02 54555 NE NR 2 VIBRATION W K NONE O OTHER IN INSP/MAINT 1 CA 44530 (CAN) AFTER TAKEOFF (DURING FIRST STAGES OF CLIMB) THE NR 2 ENGINE VIBRATION INCREASED, FLIGHT CREW SHUTDOWN ENGINE IN A CCORDANCE WITH OPERATING PROCEDURE AND RTURNED TO BASE. MAINTENANCE PERFORMED TEST 21 IN ACCORDANCE WITH ROLLS ROYCE PRO CEDURES, ENGINE VIBRATIONS RETURNED TO NORMAL, AIRCRAFT RETURNED TO SERVICE. NO FURTHER REPORTED INCIDENTS.MAINTENANCE S USPECT OIL HIDING AS CAUSE OF ENGINE VIBRATION . 2 L 7 3 4F 4 F A23WE E12EU 2001040500077 20010405 00077 EA 2001 4 5 CA010307018 1 20010220 G 3232 BRACE CNDAIR CL600 CL6002B16 1900305 EA GE CF34 CF343B1 NE MLG DOOR SHEARED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) AIRCRAFT 604-54F05 WITH TSN OF 611.3 HOURS AND 304 CYCLES HAS BEEN FOUND TO HAVE A BROKEN TRUNNION PIN AT L/H MLG SIDE BRACE ACTUATOR INBOARD END.THIS WAS FOUND AS THE AIRCRAFT WAS ON JACKS AND A TECHNICIAN NOTICED THAT THE GEAR MOVED . THE FORWARD ATTACH NUT WAS SHEARED OFF AND LAYING ON TOP OF THE WING. THIS ALLOWED THE PIN TO MIGRATE APPROXIMATELY 0. 3 INCHES AFT, ALLOWING THE GEAR TO MOVE. PART REPLACED. BROKEN PART RETURNED TO BOMBARDIER FOR ANALYSIS.UNDER INVESTIGAT ION 2 L 7 2 4F 4 F RT A21EA E15NE 2001040500078 20010405 00078 EA 2001 4 5 CA010307021 1 20010219 G 5610 NP1393215 WINDSHIELD CNDAIR CL600 CL6002B19 EA GE CF34 CF343B1 NE COCKPIT CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) DURING THE PRE-FLIGHT INSPECTION, IT WAS NOTICED THAT THE CAPTAINS WINDSHIELD WAS CRACKED. THE AIRCRAFT RETURNED T O SERVICE AFTER REPLACEMENT OF THE WINDSHIELD. 2 L 7 2 4F 4 F RT A21EA E15NE 2001040500079 20010405 00079 NE 2001 4 5 CA010307024 2 20010219 G 7200 ENGINE CNDAIR CL600 CL6002B19 EA GE CF34 CF343B1 NE NR 2 FAILED W O OTHER J WARNING INDICATION DE DESCENT 1 CA (CAN) PILOT REPORT IN DESCENT: AUDIT ENGINE OIL AND MASTER WARNING. ENGINE NR 2 OIL PRESSURE RAPIDLY DROPPED TO 0 PSI. C REW INITATED AN IN-FLIGHT SHUTDOWN PROCEDURE, AIRCRAFT LANDED WITHOUT INCIDENT. MAINTENANCE FOUND PARTICLE ON NR 2 CHIP DETECTOR. AT THE TIME OF WRITING THE CAUSE FOR THE LOSS OIL PRESSURE HAS NOT BEEN DETERMINDED. THE CUSTOMER AND THE MANU FACTURER WILL CONTINUE THE INVESTIGATION. 2 L 7 2 4F 4 F RT A21EA E15NE 2001040500080 20010405 00080 EA 2001 4 5 CA010307026 1 20010219 G 5730 601R10046 PANEL CNDAIR CL600 CL6002B19 EA GE CF34 CF34* NE LT WING CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 18652 (CAN) DURING A SERVICE CHECK, THE MECHANIC FOUND A SUSPECTED CRACK N THE LT WING LOWER SKIN AT WING STATION WS 148.019. THE CRACK WAS CONFIRMED WITH LPI AND EDDY CURENT NDT. THE REPAIR WAS CARRIED OUT PER REPAIR ENGINEERING ORDER 601R-57-21 -130. THE AIRCRAFT SUBSEQUENTLY RETURNED TO SERVICE. 2 L 7 2 4F 4 F RT A21EA E15NE 2001040500081 20010405 00081 EA 2001 4 5 CA010307027 1 20010219 G 5730 601R10046 PANEL CNDAIR CL600 CL6002B19 EA GE CF34 CF343A1 30015 NE WING CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 13895 (CAN) DURING A C CHECK INSPECTION, A CRACK WAS FOUND IN THE LOWER WING PLANK AT WING STATION WS 148.019.AT THE TIME OF R EPORT, THE AIRCRAFT WAS STILL IN C CHECK. REPAIR ENGINEERING ORDER (REO) 601R-57-21-130 WILL BE APPLIED PRIOR TO RETURNI NG THE AIRCRAFT INTO SERVICE. 2 L 7 2 4F 4 F RT A21EA E15NE 2001040500082 20010405 00082 EA 2001 4 5 CA010307028 1 20010219 G 5600 NP1393215 WINDOW CNDAIR CL600 CL6002B19 EA GE CF34 CF343B1 NE COCKPIT CRACKED W D RETURN TO BLOCK O OTHER TX TAXI/GRND HDL 1 CA (CAN) WHILE MANOEUVRING ON THE GROUND, THE LT SIDE WINDOW WAS FOUND CRACKED. THE WINDOW WAS REPLACED AND THE AIRCRAFT RE TURNED INTO SERVICE. 2 L 7 2 4F 4 F RT A21EA E15NE 2001040500083 20010405 00083 NE 2001 4 5 CA010307030 2 20010221 G 7200 ENGINE CNDAIR CL600 CL6002B19 EA GE CF34 CF343A1 30015 NE LEFT FAILED W A UNSCHED LANDING E VIBRATION/BUFFET CL CLIMB 1 CA (CAN) ENGINE VIBRATION DURING CLIMB OUT AND LEVEL FLIGHT (FL230). MAXIMUM VALUE WAS 3.3 MILS. LATER FLUCTUATION BETWEEN 2.3 AND 3.3 MILS. ENGINE SHUT DOWN IN FLIGHT. SINGLE ENGINE OPERATION AS PER QRH. CHANGE LEFT ENGINE. REASON: HIGH N1 VI BRATION. 2 L 7 2 4F 4 F RT A21EA E15NE 2001040500084 20010405 00084 EA 2001 4 5 CA010307033 1 20010222 G 5270 601R317001 SENSOR CNDAIR CL600 CL6002B19 EA GE CF34 CF343B1 NE PASSENGER DOOR OUT OF ADJ W A UNSCHED LANDING N FALSE WARNING CL CLIMB 1 CA (CAN) DURING CLIMB CREW RECD PASSENGER ENTRANCE DOOR WARNING MESSAGE PAX DR LATCH (AMBER) & PASSENGER DOOR (WARNING) EIC AS MESSAGES. A/C RETURNED TO DEPTR AIRPORT&LANDED W/O INCID.&LATER FERRIED TO MAINT BA SE. MAINT FINDINGS: 1. PSEU FAULT LOG 2 RECORDED S47 & S46;2. FLT CREW RPT EICAS MESSAGES EXTINGUISHED BELOW 7000 ASI; 3. GREEN ALIGNMENT MARKS ON CAM LA TCHES NOT WITHIN RANGE WHEN INNER DOORHANDLE IS SLOWLY ENGAGED; 4. PROX SENSOR PSSMB GAP .068 INCH, .018 INCH BEYOND LIM ITS;5. A/C RECORDS SHOWN HAVE BEEN NO ADJUSTMENT MADE TO PSSMB SENSOR OR DOOR MECHANISM WITHIN PAST 30 DAYS. RECTIFICATI ON 1. PROX SENSOR PSSMB GAP ADJUSTED WITHIN LIMITS;2. INNER DOOR HANDLE STOP ADJUSTED;3. DOOR MECHANISM LUBRICATED A 2 L 7 2 4F 4 F RT A21EA E15NE 2001040500090 20010405 00090 EA 2001 4 5 CA010308007 1 20010202 G 4920 49100011 APU CNDAIR CL600 CL6002B19 EA GE CF34 CF343A1 30015 NE APU BAY DAMAGED W K NONE B SMOKE/FUMES/ODORS/SPARKS IN INSP/MAINT 1 CA (CAN) SMELL OF FUEL AND SMOKE IN AIRCRAFT AFTER APU STARTED ON DESCENT. EMERGENCY RESPONSE CALLED. FLIGHT LANDED AND TAX IED TO THE GATE WITHOUT FURTHER INCIDENT. APU REPLACED OPERATION AND LEAK CHECK CARRIED OUT AND SYSTEM CHECKED SERVICEAB LE. 2 L 7 2 4F 4 F RT A21EA E15NE 2001040500091 20010405 00091 EA 2001 4 5 CA010308010 1 20010212 G 2910 AE3660010K0270 LINE CNDAIR CL600 CL6002B16 1900305 EA HYDRAULIC SYSTEM CHAFED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) DURING A 60 MONTH/2400 HOUR INSPECTION, THE FLEXIBLE HYDRAULIC LINE (SUCTION TO THE ENGINE DRIVEN PUMP) OF THE NR 1 SYSTEM WAS FOUND TO HAVE CHAFED A HOLE THROUGH FUEL SHROUD SUPPLY LINE TO THE EDP.HYDRAULIC LINE P/N: AE3660010K0270FU EL SHROUD P/N: 601R62701-45 ACTT: 2261.5TOTAL LANDINGS: 1082 2 L 7 2 4F RT A21EA 2001040500092 20010405 00092 NM 2001 4 5 CA010308011 1 20010208 G 2497 WIRE BOEING 737 7372Q9 138448M NM PWA JT8 JT8D9A 52048 NE FIREWALL CHAFED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) WIRE W200-453-06 CHAFED THROUGH INSULATION AND WIRE. LENGTH & WIDTH OF CHAFE IS 3/8 INCH, DEPTH 1/8 INCH. APPEARS TO HAVE RUBBED AGAINST COWLING AT SOME TIME. HOWEVER, AT TIME OF DISCOVERY, IT WAS NOT APPARENT WHAT THE WIRE HAD CHAFED . THERE HAD BEEN NO REPORTED ELECTRICAL POWER DEFECT. THE HARNESS HAS BEEN REPLACED WITH PARTICULAR EMPHASIS TO CORRECT ROUTING AND CLAMPING. 2 L 7 2 4F 4 F A16WE E2EA 2001040500093 20010405 00093 NM 2001 4 5 CA010308012 1 20010219 G 2761 654456113 ACTUATOR BOEING 737 737201 1384454 NM PWA JT8 JT8D9A 52048 NE SPOILER LEAKING W O OTHER K FLUID LOSS DE DESCENT 1 CA (CAN) AT APPROXIMATELY 20 MINUTES OUT, THE A SYSTEM HYDRAULIC LIGHT ILLUMINATED. THE HYDRAULIC FLUID GAUGE WAS CHECKED A ND FOUND TO BE EMPTY. THE USE OF ALTERNATE FLAP AND GEAR EXTENSION WAS REQUIRED. THE AIRCRAFT LANDED WITHOUT INCIDENT. T HE FIRE DEPARTMENT WAS ALERTED AND STANDING BY AS A PRECAUTION MEASURE. MAINTENANCE FOUND THE LEFT INBOARD FLIGHT SPOILE R ACTUATOR LEAKING. 2 L 7 2 4F 4 F A16WE E2EA 2001040500094 20010405 00094 CE 2001 4 5 CA010308013 1 20010212 G 5510 10138000110 BOOT BEECH B300 BEECH B300 B300 1159232 CE PWA PT6 PT6A60A 52043 NE HORIZ STAB DEICE DETACHED W A UNSCHED LANDING J WARNING INDICATION CL CLIMB 1 CA 3880 FL26 (CAN) AIRCRAFT WAS IN CLIMBOUT FROM ST.JOHNS AIRPORT, AT 22,000 FEET, AIRSPEED 140 KNOTS, RATE OF CLIMB 1,800 F.P.M., PI LOT EXPERIENCED SEVERE BUFFETING TO THE POINT THAT A/C WAS ABOUT TO STALL. STALL WARNING DID NOT ACTIVATE, A/C WAS PLACE D IN LEVEL FLIGHT AND BUFFETING STOPPED. A/C RETURNED TO ST. JOHNS FOR MAINTENANCE. UPON INSPECTION MAINTENANCE DISCOVER ED THAT THE RIGHT DE-ICER BOOT HAD DETACHED FROM THE HORIZONTAL STABILIZER ON THE OUTBOARD END. NEW DE-ICER BOOTS WRE IN STALLED ON THE LEFT AND RIGHT SIDE, A/C WAS TEST FLOWN ALL FLIGHT CHARACTERISTICS NORMAL. 2 L 7 2 4T 4 T RT A24CE E4EA 2001040500095 20010405 00095 2001 4 5 CA010313009 4 20010226 G 8300 BP252 GEARBOX KAMOV KA32 KA32A1 SW ACCESSORY MAKING METAL W A UNSCHED LANDING J WARNING INDICATION HO HOVERING 1 CA 148 L20011007K (CAN) CAUTION SYSTEM - GEARBOX CHIP LIGHT, SMALL FLAT FLAKES FOUND IN OIL. 1 G 7 2 4U NC 2001040500096 20010405 00096 SW 2001 4 5 CA010313014 1 20010228 G 6220 471401241 TUBE BELL 47 47G2 1181008 SW LYC O435 VO435A1F 41516 EA MAIN ROTOR CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 79 (CAN) DURING DAILY INSPECTION ON MAIN CONTROL STABILIZER BAR AS PER AD 74-08-02. PILOT FOUND STABILIZER BAR TUBE WAS CRA CKED. 1 G 7 1 3O 3 O H1 E279 2001040500097 20010405 00097 NM 2001 4 5 CA010313015 1 20010304 G 2913 570347 PUMP DHAV DHC8 DHC8102 2809003 NM PWA 120 PW120A NE HAMSTD 14SF 14SF7 NE HYD SYSTEM FAILED W A UNSCHED LANDING J WARNING INDICATION CR CRUISE 1 CA 13770 3804 MX452601C (CAN) HYDRAULIC PUMP FAILED CAUSING FAILURE OF NR 1 HYDRAULIC SYSTEM. 2 H 7 2 4T 4 T RT A13NM E20NE 6 C P7NE 2001040500098 20010405 00098 CE 2001 4 5 CA010313016 1 20010209 G 2435 SBC9401 RELAY PRESTOLITE MHB4016 BEECH 76 76 1153005 CE LT STARTER FAILED W A UNSCHED LANDING J WARNING INDICATION CL CLIMB 1 CA 10775 30000047 (CAN) LT ENGINE STARTER REMAINED ON AFTER SWITCHING STARTER OFF. STARTER RELAY HAD STUCK ON DUE TO ERRODED CONTACTS. STA RTER SUBSEQUENTLY OVERHEATED AND FUSED ITSELF. THIS CONDITION CAUSED ALL ELECTRICAL POWER AVAILABLE FROM THE AIRCRAFT CH ARGING SYSTEM AND BATTERY TO GO TO THE STARTER AS A DEAD SHORT, THEREFORE ALL ELECTRICAL SYSTEMS WENT COMPLETELY DEAD IN APPROXIMATELY 30 SECONDS. 1 L 7 2 3O A29CE 2001040500099 20010405 00099 CE 2001 4 5 CA010313017 1 20010215 G 7721 RHM38E SPARK PLUG BEECH 76 76 1153005 CE LYC O360 O360A1G6D EA ENGINE DAMAGED W A UNSCHED LANDING R PARTIAL RPM/PWR LOSS CR CRUISE 1 CA 300 (CAN) IN CRUISE PILOT REPORT RT ENGINE SURGING, THEN COMPLETELY ROUGH RUNNING. ENGINE SHUTDOWN, AIRCRAFT LANDED SAFELY. COMPRESSION TEST REVEALED ONE WEAK CYLINDER 50/80 PSI. BOTH SPARK PLUGS IN THAT CYLINDER SHORTED DUE TO BEING PEENED OVE R BY FOREIGN OBJECT BOUNCING BACK AND FORTH IN CYLINDER. SUSPECT CERAMIC PIECE FROM A PLUG CAME OFF AND DID DAMAGE, HOWE VER PIECE NOT FOUND, NEW CYLINER ASSEMBLY INSTALLED, SPARK PLUGS ARE RECONDITIONED IN HOUSE USING CHAMPION PLUG CLEANER/ TESTER. 1 L 7 2 3O 3 O A29CE E286 2001040500149 20010405 00149 EA 2001 4 5 CA010313019 2 20010228 G 7414 10382681 CAPACITOR BENDIX D6LH3200 PIPER PA31 PA31350 7103110 SO LYC O540 TIO540J2BD 41532 EA MAGNETO FAILED W K NONE R PARTIAL RPM/PWR LOSS TX TAXI/GRND HDL 1 CA 124 (CAN) AIRCRAFT HAD FLOWN 2-3 HOURS ENGINE SHUT DOWN TO UNLOAD PASSENGERS. PILOT STARTED 1 ENGINE BUT 2ND WOULD NOT START . PROBLEM WAS INVESTIGATED AND CAPACITOR FOUND U/S. CAPACITOR REPLACED AND ENGINE STARTED. WE HAVE HAD 3 SUCH CASES IN T HE LAST MONTH. WE HAE TESTED THE U/S CAPACITORS AS PER MANUFACTURERS INSTRUCTIONS AND CAPACITORS CHECK OUT SERVICEABLE. WE HAVE ALSO NOTICED THAT POINTS ARE NOT LASTING AS LONG IN THE MAGS. ALL CAPACITORS WERE REPLACED AS PER TELEDYNE CSB 6 62A. 1 L 7 2 3O 3 O A20SO E14EA 2001040500154 20010405 00154 CE 2001 4 5 CA010313024 1 20010309 G 2431 BATTERY CESSNA 172 172L 2072432 CE LYC O320 O320E2D 41508 EA MCAULY 1C160 1C160CTM GL MAIN BATTERY FAILED W A UNSCHED LANDING H G J ELECT. POWER LOSS-50 PC MULTIPLE FAILURE WARNING INDICATION CR CRUISE 1 CA (CAN) PILOT ENCOUNTERED COMPLETE (GREATER THAN 50 PERCENT) ELECT. FAILURE IN FLT. AFTER ATTEMPTING TO GET A/C RADIOS TO TRANSMIT/RECEIVE, PILOT SQUAKED RADIO FAILURE CODE. FURTHER ATTEMTPS AT GETTING OTHER ELECT. SYSS TO FUNCTION, PILOT FO UND THAT ALL ELECT. SYS WAS UNSERVICEABLE. A/C RETURNED TO POINT OF DEPTR & THEN CONTACTED TOWER ON LAND LINE.AFTER BRIE F INSP , FOUND THAT A/C BATTERY COMPLETELY DISCHARGED. BATTERY (NEW & INST NOV.2000) ELECTROLYTE LEVEL INSP OK, BATTERY CHARGED OVERNIGHT. AFTER BATTERY CHARGED, GROUND RUN/FUNCTION CHECKED. NOTED WITH CHARGING SYS COMPLETELY LOADED UP, CHA RGE IND. WEAK. SUSPECT BATTERY VOLTAGE INITY LOW & CHARGING SYS UNABLE TO KEEP UP WITH DE 1 H 7 1 3O 3 O NT 3A12 E274 5 N P910 2001040500155 20010405 00155 EU 2001 4 5 CA010313025 1 20010226 G 5302 3160S451010060 GUARD AEROSP SA316 SA315B 8680615 EU TMECA ARTST3 ARTOUSTE3B 60003 EU TAIL ROTOR CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 2714 (CAN) WHILE CLEANING AIRCRAFT, AME FOUND CRACK COMING FROM UNDER BOTTOM CLAMP.NEW TAIL ROTOR GUARD WAS INSTALLED. 1 G 7 1 4U 3 U H1IN E11N 2001040500159 20010405 00159 CE 2001 4 5 CA010314003 1 20010226 G 5610 10138402522 WINDSHIELD BEECH B300 B300 1159232 CE PWA PT6 PT6A60A 52043 NE COCKPIT CRACKED W A UNSCHED LANDING O OTHER CR CRUISE 1 CA 5 (CAN) WHILE IN CRUISE FLIGHT AT FL310 AND OAT -50 DEGREES C, FLIGHT CREW OBSERVED RT WINDSHIELD OUTER PANE CRACK DEVELOP . CRACK WAS DIAGONAL IN LOWER INBOARD CORNER (APPROXIMATELY 6 INCHES). POH ABNORMAL CHECKLIST FOLLOWED AND FLIGHT RETURN ED TO POINT OF DEPARTURE. 2 L 7 2 4T 4 T RT A24CE E4EA 2001040500161 20010405 00161 WP 2001 4 5 CA010314007 2 20010312 G 7230 31037081 BEARING MTSBSI MU2 MU2B60 5780460 CE GARRTT TPE331 TPE33110 01514 WP COMPRESSOR WRONG PART W K NONE W INADEQUATE Q C IN INSP/MAINT 1 CA (CAN) GARRETT SB 72-0634 DATED AUG 17 1989 (OPTIONAL COMPLIANCE) LISTED COMPRESSOR BEARING P/N 3103708-1 AS REPL FOR P/N 3101405-1. BULLETIN APPLICABLE TO ALL MODELS OF TPE 331 ENGINE WHICH PREV HAD P/N 3101405-1 BEARING. SUBSEQUENT REVISIO N NR 1 TO SB DATED APR 27, 1990 DELETED SOME ENGINE MODELS FROM EFFECTIVITY LIST. ENGINE MODEL DELETED FROM LIST, HOWEVE R IT NOT RECOMMENDED TO REMOVE ANY P/N 3103708-1 BEARINGS INST IN COMPLIANCE WITH T HE 1ST ISSUE OF SB- IN NOV 1998 P/N 3103708-1 BEARING INST INTO ENGINE. SUBSEQUENET REVIEW OF LIFE LIMITED COMPONENTS IN ENGINE, AGAINST REQMTS OF SB 72-018 0 TBO REQMTS, INDICATED PART NO LONGER LISTED ON APPLICABLE LIFE LIMIT TABLES. 1 H 7 2 3T 4 T RT A10SW E4WE 2001040500162 20010405 00162 NE 2001 4 5 CA010314009 3 20010218 G 6114 7827015 HUB DHAV DHC8 DHC8101 2809002 NM PWA 120 PW120A NE HAMSTD 14SF 14SF7 NE LT PROPELLER CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 9085 (CAN) DURING ROUTINE MAINTENANCE CHECK, FOUND LEFT PROPELLER ASSEMBLY HAD EVIDENCE OF OIL LEAK. UPON FURTHER INVESTIGATI ON LEAK WAS FOUND TO BE COMING FROM NR 4 BLADE. AFTER REMOVING THE LEFT NR 4 BLADE THE OUTER BEARING RACE WITHIN THE PRO PELLER HUB WAS FOUND TO BE CRACKED AND GALLED.LEFT PROPELLER HUB, PROPELLER ACTUATOR, AND 3 BLADES WERE REPLACED DUE TO OIL CONTAMINATION AND AN ADDITIONAL BEARING RACE FOUND GALLED. AIRCRAFT RETURNED TO SERVICE. 2 H 7 2 4T 4 T RT A13NM E20NE 6 C P7NE 2001040500167 20010405 00167 SO 2001 4 5 CA010314023 1 20010223 G 5620 45099013 WINDOW PIPER PA31T PA31T2 7103127 SO PWA PT6 PT6A135 52043 NE FUSELAGE BROKEN W A UNSCHED LANDING D INFLIGHT SEPARATION CL CLIMB 1 CA 12355 (CAN) - THE AIRCRAFT WAS CLIMBING THROUGH 16,000 FEET WHEN THE CABIN PRESSURIZATION WAS LOST. - THE PILOTS INITIATED EME RGENCY DESCENT TO 10,000 FEET AND DECLARED EMERGENCY. - THE CAUSE FOR DEPRESSURIZATION WAS FOUND TO BE A BROKEN WINDOW I N THE CABIN AREA (3RD WINDOW ON LT SIDE).- AIRCRAFT LANDED SAFELY WITH NO FURTHER INCIDENTS. 1 L 7 2 3T 4 T RT A8EA E4EA 2001040500168 20010405 00168 EA 2001 4 5 CA010314024 1 20010121 G 2730 22D1174A CONTROL CABLE SCWZER SG2 SGS233A 8051606 EA ELEVATOR FRAYED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) BEARING ASSEMBLY AFT END OF TORQUE TUBE ASSEMBLY, LT MOUNT NUTCONTACTING CABLE. SUSPECT ANGLE BLOCK (FAIRLEAD) AF T END OF TORQUE TUBE ASSEMBLY AMPLIFIED DAMAGE TO CAUSE CABLE WEAR IN EXCESS OF 50 PERCENT. FURTHER INVESTIGATION ONGOI NG BY SCHWEIZER. 1 K 0 0 G2EA 2001040500169 20010405 00169 EU 2001 4 5 CA010314026 1 20010227 G 2133 9599091131 REGULATOR PILATS PC12 PC1245 EU PWA PT6 PT6A67B 52043 NE HARTZL HCE4A HCE4A3D GL CABIN PRESSURE CONTAMINATED W K NONE O OTHER IN INSP/MAINT 1 CA 2649 (CAN) SAFETY VALVE FAILED TON OPEN WHEN CARRYING OUT 1500 HOUR PRESSURIZATION CHECK. FAILED SAFETY VALVE WAS REMOVED AND VALVE AND SENSE LINE WERE FOUND CONTAMINATED WITH JET FUEL. FUEL APPEARED TO HAVE COME FROM A PREVIOUSLY SEEPING FUEL F ILTER BOWL SEAL AND HAD ENETRED THE OUTFLOW VALVE WHERE THE AMBIENT PRESSURE SENSE LINE PROTRUDES THROUGH THE PRESSURE B ULKHEAD (APPROX 12 -14 INCHES AFT OF THE FUEL BOWL). 1 L 7 1 3T 4 T RT A78EU E26NE 5 C P210NE 2001040500170 20010405 00170 SW 2001 4 5 CA010314027 1 20010223 G 3222 STRUT GULSTM 112 112 0144701 SW LYC O360 IO360C1D6 41514 EA HARTZL HCE2Y HCE2YR1BF GL NLG CONTAMINATED W O OTHER J WARNING INDICATION LD LANDING 1 CA 1711 1711 (CAN) A/C HAD UNCOMMANDED NOSE GEAR RETRACTION UPON LDG. IT NOTICED DURING POWER PACK PRESSURE TEST THAT 700PSI ON UP SI DE WHEN GEAR EXTENDING & THAT PRESSURE WOULD NOT DECREASE BELOW 50-100 PSI WHEN GEAR WAS FULLY EXTENDED.RESIDUAL PRESSU RE PREVENTING DETENT PINS FROM ENGAGING. HYDRAULIC POWER PACK REMOVED & DISASSEMBLED. FOUND ONE 8 OF INCH OF BLACK SLUD GE & 1 X 5 INCH PIECE OF PAPER IN RESERVOIR.VALVE BODY ALSO DISSASSEMBLED. FOUND GEAR UP CHECK VALVE O-RING HARD & BRITT LE & SEATS OF MOST OF VALVES COVERED WITH SLIMY GOO. NOSE GEAR ACTUATOR DISASSEMBLED. MAIN PRESSURE O-RING MS28775-117 NOTICED TO BE ROLLED. 1 L 7 1 3O 3 O A12SO 1E10 5 C P9EA 2001040500221 20010405 00221 EA 2001 4 5 CA010320010 1 20010308 G 5610 NP1393212 WINDSHIELD CNDAIR CL600 CL6002B19 EA GE CF34 CF343B1 NE COCKPIT CRACKED W A UNSCHED LANDING O OTHER CR CRUISE 1 CA (CAN) RT WINDSHIELD INNER PLY FOUND CRACKED, UNIT REPLACED AND AIRCRAFT BACK IN SERVICE. 2 L 7 2 4F 4 F RT A21EA E15NE 2001040500222 20010405 00222 EA 2001 4 5 CA010320013 1 20010308 G 3234 HANDLE CNDAIR CL600 CL6002B19 EA GE CF34 CF343A1 30015 NE MLG SELECTOR FAILED W A UNSCHED LANDING J WARNING INDICATION CL CLIMB 1 CA (CAN) DURING CLIMBOUT LANDING GEAR WOULD NOT RETRACT, ANTI-SKID FAIL MESSAGE SHOW ON EICAS. MAINTENANCE REPLACED LANDING GEAR HANDLE AND AIRCRAFT BACK IN SERVICE. 2 L 7 2 4F 4 F RT A21EA E15NE 2001040500223 20010405 00223 2001 4 5 CA010320014 4 20010308 G 3417 8220371140 ADC CNDAIR CL600 CL6002B19 EA GE CF34 CF343B1 NE E/E BAY FAILED W A UNSCHED LANDING J WARNING INDICATION CR CRUISE 1 CA (CAN) DURING CRUISE STABILIZER TRIM CH2 AND MACH TRIM FAILED. MAINTENANCE REPLACED ADC AND AIRCRAFT BACK IN SERVICE. 2 L 7 2 4F 4 F RT A21EA E15NE 2001040500224 20010405 00224 CE 2001 4 5 CA010320018 1 20010228 G 2820 120010679 LINE CESSNA 206 U206G 2073356 CE CONT O550 IO550F 17042 SO FUEL DISTRIBUT CHAFED W K NONE O OTHER IN INSP/MAINT 1 CA 1970 (CAN) LINE ASSEMBLY - FUEL, STRAINER TO ELBOW FOUND CHAFING AGAINST RT NOSE GEAR STEERING BOOT.1.50 INCH X 0/032 INCH TU BING FOUND WORN BY 0/018 INCH ON ONE SIDE. PART HAS BEEN REPLACED WITH A NEW LINE ASSEMBLY - FUEL AND PROTECTED WITH NYL ON SPIRAL WRAP. 1 H 7 1 3O 3 O A4CE E3SO 2001040500227 20010405 00227 EU 2001 4 5 CA010320021 1 20010214 G 2910 LINE AIRBUS 310 A310304 EU GE CF6 CF680C2A5 NE HYDRAULIC SYS LOOSE W A UNSCHED LANDING J WARNING INDICATION CR CRUISE 1 CA (CAN) PILOT OBSERVED GREEN SYSTEM HYDRAULICS WAS LOOSING FLUID. AIRCRAFT DIVERTED TO YYT. HYDRAULIC LINE IN NR 1 ENGINE PYLONFOUND LOOSE. LINE TIGHTENED AND LEAK CHECK CARRIED OUT SERVICEABLE. 2 L 7 2 4F 4 F RT A35EU E13NE 2001040500233 20010405 00233 SO 2001 4 5 CA010322002 1 20010208 G 3242 LINER PIPER PA34 PA34200T 7103406 SO CONT O360 TSIO360EB 17025 SO BRAKES DESTROYED W K NONE W INADEQUATE Q C IN INSP/MAINT 1 CA 43 (CAN) WHILE CONDUCTING A GENERAL WALK AROUND FOR A PRE-PURCHASE, THE INBOARD PRESSURE PLATE SIDE OF THE BRAKE CALIPERS, THE BRAKE LINERS WERE TOTALLY DESTROYED, RESULTING IN THE STEEL PRESSURE PLATE TO COME IN FULL CONTACT WITH THE BRAKE DI SC WHICH CREATED DEEP GROOVES AND SIGNIFICANT AMOUNT OF HEAT TO DISCOLOR THE PRESSURE PLATES AND DISCS. 1 L 7 2 3O 3 O A7SO E9CE 2001040500239 20010405 00239 NM 2001 4 5 CA010322012 1 20010317 G 4920 COMPRESSOR BOEING 737 737281 138448P NM PWA JT8 JT8D17 52049 NE APU MAKING METAL W K NONE O OTHER IN INSP/MAINT 1 CA 41944 881 (CAN) THE AIRCRAFT WAS CLIMBING OUT OF VANCOUVER WHEN THE APU DID AN AUTO SHUT DOWN AND THE APU FIRE HANDLE ILLUMINATED. THE FIRE HANDLE WAS PULLED BUT THE BOTTLE WAS NOT DISCHARGED DUE TO THE FIRE INDICATION GOING OUT. THE AIRCRAFT RETURNE D TO VANCOUVER WHERE THE APU AREA WAS INSPECTED AND NO EVIDENCE OF A FIRE WAS DISCOVERED. THE APU WAS PLACED ON MEL AND THE AIRCRAFT WAS RELEASED TO SERVICE. FURTHER INVESTIGATION LATER IN THE DAY FOUND THAT THERE WAS METAL FRAGMENTS FOUND IN THE INTAKE OF THE APU AND THE APU WAS REMOVED FROMTHE AIRCRAFT. IT WILL BE RETURNED TO THE OVERHAUL FACILITY FOR DISA SSEMBLY AND REPAIR. 2 L 7 2 4F 4 F A16WE E2EA 2001040500240 20010405 00240 EU 2001 4 5 CA010323002 1 20010217 G 2701 AS2219 CONTROL CABLE SIREN S1609 SNIAS 350 AS350B2 8680813 EU TMECA ARRIEL ARRIEL1D NE CARGO HOOK BROKEN W O OTHER O OTHER CL CLIMB 1 CA 876 (CAN) MANUAL / EMERGENCY RELEASE CABLE SHEATH BROKEN AWAY FROM FERRULE / SLEEVE WHERE CABLE ASSEMBLY ATTACHES TO THE CAR GO HOOK.THE CARGO SUSPENSION SYSTEM (SWING) ALLOWS FOR A LOT OF MOVEMENT OF THE CARGO HOOK. THERE APPEARS TO BE A LOT OF FLEXING OF THE CABLE ASSY WHERE IT ATTACHES TO THE CARGO HOOK LEADING TO FAILURE OF THE CABLE SHEATH.THIS FAILURE RESUL TED IN AN UNCOMMANDED LOAD RELEASE. 1 G 7 1 3U 3 U H9EU E19EU 2001040500241 20010405 00241 NE 2001 4 5 CA010323003 2 20010309 G 7530 2496722 WASHER BENDIX 153212A DHAV DHC8 DHC8* NM PWA 120 PW120 NE VALVE SEALS CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA RF4252 (CAN) COMPRESSION WASHER CRACKED AND JAMMED BETWEEN THE VALVE SEAL AND SEALING SURFACE PREVENTING THE A SIDE FROM COLOSI NG. 2 H 7 2 4T 4 T RT A13NM E20NE 2001040500243 20010405 00243 EA 2001 4 5 CA010323005 1 20010314 G 5530 C6TFM102529 ADAPTER DHAV DHC6 DHC6 2802606 EA VERTICAL STAB FAILED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) LOWER LT MOUNTING / MATING SURFACE INCORRECTLY MACHINED. SURFACE WAS MACHINED CYLINDRICALLY INSTEAD OF SPHERICAL C ONVEX. IF INSTALLED THE MATING SURFACES WOULD NOT MATCH CAUSING STRESS AND POSSIBLE FAILURE OF THE MOUNT. CONCERNED THAT MORE WERE PRODUCED AND INSTALLED FROM THE SAME BATCH. 1 H 7 2 3T RT A9EA 2001040500244 20010405 00244 SO 2001 4 5 CA010323006 1 20010307 G 7721 LW16740 EXHAUST VALVE PIPER PA31 PA31350 7103110 SO LYC O540 TIO540J2BD 41532 EA NR 5 CYLINDER BROKEN W K NONE O OTHER IN INSP/MAINT 1 CA 1724 (CAN) PILOT REPORTED HIGH OIL TEMP VERNATHERN REPLACED AND ON GROUND RUN ENGINE RAN ROUGH. LARGE AMOUNT OF OIL NOTED COM ING FROM SNIFFLE VALVE MIXED WITH FUEL. SPARK PLUGS REMOVED AND FOUND THOSE REMOVED FROM NR 5 CYLINDER WERE DAMAGED. REM OVED CYLINDER AND FOUND 1/3 OF VALVE FACE (EXHAUST) MISSING. REPLACED CYLINDER AND CHECKED ALL SCREENS AND FILTERS. 1 L 7 2 3O 3 O A20SO E14EA 2001040500246 20010405 00246 CE 2001 4 5 CA010323008 1 20010302 G 5751 991300003 SKIN BEECH 100 100BEECH 1152916 CE PWA PT6 PT6A28 EA RT AILERON CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 13438 (CAN) WHEN CHECKING SB 57-3148 IT WAS NOTICED THAT THIS AILERON WAS ALSO CRACKED AS PER SB 57-3148. KIT 109-4011-1 INSTA LLED. 1 L 7 2 3T 4 T A14CE E4EA 2001040500249 20010405 00249 CE 2001 4 5 CA010323011 1 20010313 G 5610 11450431S WINDSHIELD BEECH 1900 1900D 1154162 CE PWA PT6 PT6A67D NE HARTZL HCE4A HCE4A3I NE COCKPIT CRACKED W O OTHER O OTHER DE DESCENT 1 CA 7057 (CAN) ON DESCENT IN YWG PILOT HEARD SNAPING AND CRACKING AS THE OUTER LAYER OF LT WINDSHIELD SHATTERED. THEY DESCENDED T O YWG ASKING FOR PRIORITY LANDING WITHOUT INCIDENT. 2 L 7 2 4T 4 T RT A24CE E26NE 5 C P10NE 2001040500250 20010405 00250 CE 2001 4 5 CA010323013 1 20010315 G 7603 S351 CLAMP CESSNA CESSNA 172 172M 2072418 CE LYC O320 O320E2D 41508 EA THROTTLE CABLE LOOSE W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) THROTTLE SHEAF HAD VIBRATED LOOSE FROM CONNECTING CLAMP WHICH LEFT NO CONTROL FOR THROTTLE ADJUSTMENT. THROTTLE CA BLE WAS RE-POSITIONED IN THE SHEAF AND NEW HARDWARE WAS INSTALLED.AIRCRAFT WAS GROUND UN AND ALL PARAMETERS NORMAL. 1 H 7 1 3O 3 O NT 3A12 E274 2001041600458 20010416 00458 SO 2001 4 16 CA010402004 1 20010306 G 7810 5005500 EXHAUST STACK PIPER PA31T PA31T 7103124 SO PWA PT6 PT6A28 EA ENGINE CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) AFTER A FLIGHT, THE PILOTS REPORTED A CRACK AT THE INNER WELD SEAM OF THE LE OUTBOARD EXHAUST STACK. 1 L 7 2 3T 4 T A8EA E4EA 2001041600459 20010416 00459 CE 2001 4 16 CA010402005 1 20010310 G 5310 05121871 DOOR FRAME CESSNA 172 172M 2072418 CE LYC O320 O320E3D 41508 EA FUSELAGE CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 8970 (CAN) LOWER AFT DOOR POSTS INSPECTED PER SEB 97-1 AND FOUND LT CRACKED. INSTALLED SERVICE KITS SK172-149-1 AND -2 TO COR RECT. 1 H 7 1 3O 3 O NT 3A12 E274 2001041600460 20010416 00460 NM 2001 4 16 CA010402006 1 20010309 G 5720 82710038101 FITTING DHAV DHC8 DHC8102 2809003 NM PWA 120 PW120A NE HAMSTD 14SF 14SF7 NE RUDDER PEDAL CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 28935 (CAN) THE PART WAS CRACKED TWO-THIRDS OF THE CIRCUMFERENCE AROUND THE RAISED BOSS (CASTING) NEAR THE RADIUS. THE TOP END FITTING WAS REPLACED IN ACCORDANCE WITH THE MAINTENANCE MANUAL AND CHECKED - SERVICEABLE. 2 H 7 2 4T 4 T RT A13NM E20NE 6 C P7NE 2001041600466 20010416 00466 EA 2001 4 16 CA010403003 1 20010313 G 5340 601350061 BEAM 60135006 CNDAIR CL600 CL6002B19 EA GE CF34 CF341A NE FUSELAGE CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) DURING C-CHECK A CRACK WAS FOUND IN THE ENGINE SUPPORT BEAM LOWER WEB BETWEEN FS 625.30 AND FS 640.00 NEAR LBL 36. 20. THE CRACK WAS LOCATED IN THE CORNER OF ACCESS PANEL (P/N 601-35006-39) LANDING AND ENDED NEAR THE PANEL EDGE. 2 L 7 2 4F 4 F RT A21EA E15NE 2001041600467 20010416 00467 EA 2001 4 16 CA010403004 1 20010313 G 5610 601R330339 WINDSHIELD CNDAIR CL600 CL6002B19 EA GE CF34 CF343B1 NE COCKPIT CRACKED W O OTHER O OTHER DE DESCENT 1 CA (CAN) PILOT REPORT LT WINDSHIELD INNER PLY BOTTOM LOWER CORNER CRACKED. WINDSHIELD REMOVED AND REPLACED. 2 L 7 2 4F 4 F RT A21EA E15NE 2001041600468 20010416 00468 EA 2001 4 16 CA010403006 1 20010314 G 4920 APU CNDAIR CL600 CL6002B19 EA GE CF34 CF343A1 30015 NE APU BAY FIRE W F ACTIVATE FIRE EXT. A FLAME/FIRE TX TAXI/GRND HDL 1 CA (CAN) APU CAUGHT FIRE ON THE GROUND AFTER LANDING.FIRE WAS EXTINGUISHED BUT RELIT. FIRE DEPARTMENT EXTINGUISHED IT FOR G OOD. APU WAS REPLACED. 2 L 7 2 4F 4 F RT A21EA E15NE 2001041600469 20010416 00469 EA 2001 4 16 CA010403007 1 20010314 G 5730 PANEL CNDAIR CL600 CL6002B19 EA GE CF34 CF343B1 NE LT WING CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) LT WING PLANK CRACKED AT WS 148.019 FOR ABOUT 1.2 INCHES LONG. THE RT HAS NO CRACK. THEY WILL PERFORM THE REO 601R -57-21-130. 2 L 7 2 4F 4 F RT A21EA E15NE 2001041700098 20010417 00098 EA 2001 4 17 CA010403011 1 20010306 G 7603 C3CE12 CABLE DHAV DHC3 DHC3 2800202 EA PWA R1340 R1340* 52016 NE THROTTLE BROKEN W O OTHER O OTHER TX TAXI/GRND HDL 1 CA (CAN) DURING THE PRE-FLIGHT RUN-UP, THE THROTTLE CONTROL WAS NOT RESPONDING PROPERLY. INVESTIGATION FOUND THAT THE FLEX CABLE WAS BROKEN INSIDE THE TUBING. 1 H 7 1 3R 3 R A815 5E2 2001041700099 20010417 00099 EA 2001 4 17 CA010403012 1 20010305 G 7721 357285 CYLINDER DHAV DHC3 DHC3 2800202 EA PWA R1340 S3H1G 52016 NE NR 3 CRACKED W O OTHER E VIBRATION/BUFFET CR CRUISE 1 CA 1184 (CAN) DURING A FLIGHT THE PILOT WAS FEELING AN ENGINE VIBRATION. HE REDUCED POWER AND CONTINUED HIS FLIGHT. ON MAINTENAN CE THE NR 3 CYLINDER WAS FOUND CRACK FROM FRONT SPARK PLUG HOLE TO THE REAR. 1 H 7 1 3R 3 R A815 E142 2001041700130 20010417 00130 NE 2001 4 17 CA010403013 2 20010312 G 8530 357285 HOUSING DHAV DHC3 DHC3 2800202 EA PWA R1340 S3H1G 52016 NE ROCKER BROKEN W A UNSCHED LANDING E VIBRATION/BUFFET CR CRUISE 1 CA 1199 (CAN) DURING A FLIGHT, THE PILOT FELT AN ENGINE VIBRATION AND POWER REDUCTION. HE LANDED ON A LAKE. MAINTENANCE FOUND A CYLINDER WITH ROCKER HOUSING BROKEN. 1 H 7 1 3R 3 R A815 E142 2001041700131 20010417 00131 CE 2001 4 17 CA010403014 1 20010312 G 5520 50350055 FITTING CESSNA 402 402C 207590R CE CONT O520 TSIO520VB 17040 SO LT ELEVATOR CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 12195 (CAN) - LEFT ELEVATOR FITTING FOUND CRACKED AT UPPER HOLE. NEW FITTING P/N 5035005-3 INSTALLED. 1 L 7 2 3O 3 O A7CE E8CE 2001041700132 20010417 00132 SO 2001 4 17 CA010403015 1 20010219 G 3242 492152 VALVE PIPER PA44 PA44180 7104402 SO PARKING BRAKE BENT W O OTHER O OTHER AP APPROACH 1 CA 3818 (CAN) PILOT REPORTED PARK BRAKE APPLYING ITSELF. NOTICED ONCE ON TAKEOFF ONCE ON LANDING. CONFIRMED BY APPLYING SLIGHT PRESSURE TO PARK BRAKE SELECTOR TO THE OFF POSITION. UNIT REPLACED WITH SERVICEABLE UNIT, WHICH WAS SERVICED WITH NEW O -RINGS AND SYSTEM BLED GROUND CHECKED OK. 1 L 7 2 3O A19S0 2001041700133 20010417 00133 EA 2001 4 17 CA010404002 1 20010305 G 3231 83231014003 ROD DHAV DHC8 DHC8311 1386006 EA PWA PW120 PW123 NE HAMSTD 14SF 14SF15 NE LT MLG DOOR BROKEN W K NONE O OTHER IN INSP/MAINT 1 CA 22260 (CAN) ON WALKAROUND INSPECTION, THE LT AFT OUTBOARD MLG DOOR ACTUATING ROD WAS FOUND TO BE BROKEN. THE DOOR OPENING ASSI ST SPRING PN 83231020-003VP WAS ALSO FOUND BROKEN. THE SPRING HAD FRACTURED IN THE MID COIL AREA AND SPECULATION IS THAT THE BROKEN SPRING FOULED THE DOOR ACTUATING ROD DURING THE LAST LANDING GEAR EXTENSION, KINKING AND BREAKING THE ROD. R OD AND SPRING WERE REPLACED AND THE AIRCRAFT WAS RETURNED TO SERVICE. 2 H 7 2 4T 4 T RT A13NM E20NE 6 C P7NE 2001041700134 20010417 00134 EA 2001 4 17 CA010404003 1 20010308 G 2820 DSC33810D FITTING DHAV DHC8 DHC8311 1386006 EA PWA PW120 PW123 NE HAMSTD 14SF 14SF15 NE FUEL SYSTEM LEAKING W O OTHER K J FLUID LOSS WARNING INDICATION CR CRUISE 1 CA (CAN) THE FLIGHT CREW REPORTED THE NR 1 -FUEL LOW PRESS- CAUTION LIGHT WOULD ILLUMINATE AS SOON AS THE AUXILIARY FUEL PUMP WAS SELECTED OFF, BUT THE LIGHT WOULD GO OUT AT LOW POWER SETTINGS. MAINTENANCE INVESTIGATION REVEALED THAT A FITT ING ON THE MOTIVE FLOW LINE INSIDE THE FUEL TANK COLLECTOR BAY WAS LEAKING AND LIMITING THE OUTPUT FROM THE EJECTOR PUMP S IN THE FUEL TANK. THE O-RINGS INSIDE THE FITTING WERE REPLACED AND THE AIRCRAFT WAS RETURNED TO SERVICE. TTAF 22,271 T CAF 32,957. 2 H 7 2 4T 4 T RT A13NM E20NE 6 C P7NE 2001041700136 20010417 00136 EA 2001 4 17 CA010404005 1 20010313 G 2130 7G959 PRESSURE SWITCH DHAV DHC8 DHC8311 1386006 EA PWA PW120 PW123 NE HAMSTD 14SF 14SF15 NE NR 1 ENGINE FAILED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) THE FLIGHT CREW REPORTED THAT THEY HAD NO HIGH BLEED ON EITHER ENGINE. MAINTENANCE INVESTIGATION REVEALED THAT THE NR 1 ENGINE HIGH PRESSURE >65 PSI SWITCH WAS OUT OF TOLERANCE AND REPLACED IT. THE AIRCRAFT WAS RETURNED TO SERVICE. TH E NR 1 & 2 ENGINE HIGH BLEED SWITCHES OPERATE IN SERIES THROUGH A COMMON DELAY RELAY, THUS FAILURE OF ONE SWITCH WILL IN HIBIT SWITCHING ON BOTH ENGINES. 2 H 7 2 4T 4 T RT A13NM E20NE 6 C P7NE 2001041700137 20010417 00137 NM 2001 4 17 CA010404006 1 20010319 G 3231 83232086001 ROD END DHAV DHC8 DHC8102 2809003 NM PWA 120 PW120A NE HAMSTD 14SF 14SF7 NE MLG DOOR BROKEN W O OTHER O OTHER CL CLIMB 1 CA (CAN) THE FLIGHT CREW REPORTED AN AIRFRAME HOWL AFTER TAKEOFF AND LANDING GEAR RETRACTION. MAINTENANCE INVESTIGATION REV EALED A BROKEN ACTUATING ROD FOR THE RT AFT NOSE LANDING GEAR DOOR. 2 H 7 2 4T 4 T RT A13NM E20NE 6 C P7NE 2001041700138 20010417 00138 NE 2001 4 17 CA010404007 2 20010312 G 7200 ENGINE BOEING 737 737217 1384464 NM PWA JT8 JT8D17A 52049 NE NR 2 VIBRATION W A UNSCHED LANDING E VIBRATION/BUFFET CR CRUISE 1 CA 47894 930 (CAN) A/C 722, MAR 12/2001, YQX, LOG SEQUENCE 0295200. TOP OF DESCENT WHEN THRUST LEVERS RETARDED, NR 2 ENGINE VIBRATION WAS INDICATING 2 MILS ON INLET AND 3.5 ON TURBINE. NR 2 START LEVER WAS VIBRATING. TRIED ENGINE ANTI-ICE AND THROTTLE M OVEMENT, WITH NO CHANGE IN VIBRATIONS. ENGINE NR 2 THRUST LEVER RETARDED AND VIBS THEN REDUCED, BUT REMAINED RUMBLING UN TIL ENGINE WAS SHUTDOWN. AIRCRAFT DIVERTED TO GANDER. NR 2 ENGINE WAS REPLACED AS PER WORK CARD 1125-2. 2 L 7 2 4F 4 F A16WE E2EA 2001041700143 20010417 00143 WP 2001 4 17 CA010405002 1 20010328 G 6210 369D21100523 BLADE HUGHES 369 369D 4470706 WP ALLSN 250C 250C20B 03013 GL MAIN ROTOR CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 2269 (CAN) UPPER AND LOWER SKIN CRACKED AT STN 36.5. CRACKED FROM TRAILING EDGE TOWARDS LEADING EDGE 4.25 INCHES. 1 G 7 1 3U 3 U H3WE E4CE 2001041700024 20010417 00024 CE 2001 4 17 CA010405005 1 20010302 G 3000 1143800465 HOSE BEECH 1900 1900C 1154161 CE PWA PT6 PT6A65B 52043 EA LT BRAKE ASSY BLOWN W O OTHER J WARNING INDICATION CR CRUISE 1 CA (CAN) PILOT REPORTED LT BRAKE DEICE FAIL LIGHT CAME ON IN FLIGHT. DEICE SYSTEM WAS TURNED OFF AND AIRCRAFT CONTINUED TO DESTINATION. UPON MAINTENANCE INVESTIGATION, THE FLEXIBLE BLEED AIR HOSE ASSY CARRYING HOT AIR TO BRAKE ASSY WAS FOUND B LOWN. THE LINE WAS REPLACED AND THE AIRCRAFT RETURNED TO SERVICE. 2 L 7 2 4T 4 T RT A24CE E4EA 2001041700029 20010417 00029 SO 2001 4 17 CA010406008 2 20010321 G 8500 ENGINE CESSNA 421 421C 2076016 CE CONT O520 GTSIO520M 17032 SO RIGHT FAILED W E A ENGINE SHUTDOWN UNSCHED LANDING R J PARTIAL RPM/PWR LOSS WARNING INDICATION CR CRUISE 1 CA 95 (CAN) PILOT/OWNER REPORTED NORMAL PRE-TAKEOFF START/RUN-UP PROCEDURES. NORMAL TAKEOFF WABASCA, ALBERTA, IN ROUTE, EXPER IENCED A SURGE (OVERBOOST) RT ENGINE. ADJUSTED POWER BACK TO CRUISE, LT AND RT. WHILE ADJUSTING MIXTURE - RIGHT ENGINE ' 'THE ENGINE BLEW UP''. ENGINE SHUT DOWN AND PROPELLER FEATHERING PROCEDURES CARRIED OUT. PILOT ELECTED TO CONTINUE FLIGH T TO CYEG. ENGINE TO BE REMOVED AND SENT FOR INVESTIGATION/REPAIR - FURTHER REPORT PENDING. 1 L 7 2 3O 3 O A7CE E7CE 2001041700031 20010417 00031 EA 2001 4 17 CA010406010 2 20010316 G 8520 11F20022D3 CRANKCASE PIPER PA31 PA31350 7103110 SO LYC O540 TIO540J2BD 41532 EA RT ENGINE CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 4946 1340 (CAN) DURING ROUTINE 50 HR INSP, BROKEN CYLINDER HOLD DOWN STUD FOUND SITTING IN BOTTOM OF ENGINE COWLING. LATER INVEST. , BROKEN STUDS ORIG LOCATION LOCATED ON FRONT INNER CYLINDER OF RT ENGINE. UPON CONSULTATION WITH AERO RECIP ENGINES OF WINNIPEG, MANBITOBA, REMOVAL OF CYLINDER COMPLETED FOR FURTHER INVEST. ONCE REMOVED, IT FOUND THAT BROKEN STUD NOT THROU GH BOLT BUT NORMAL SHORT STUD. ANY FURTHER DISCUSSION ABAUG FURTHER REPAIRS OF HOLD DOWN STUD HALTED ONCE LARGE CRACK OF AT LEAST 6 IN FOUND AHEAD OF AFFECTED CYLINDER ON CRANK CASE. CRACK WOULD POSSIBLY NOT HAVE BEEN DETECTED AS IT NOT AL ALL CLEARLY VISIBLE UNTIL REMOVAL OF CYLINDER. 1 L 7 2 3O 3 O A20SO E14EA 2001041700032 20010417 00032 CE 2001 4 17 CA010406011 1 20010316 G 2435 23085001 STARTER GEN BEECH B300 B300 1159232 CE PWA PT6 PT6A60A 52043 NE RIGHT FAILED W O OTHER H J ELECT. POWER LOSS-50 PC WARNING INDICATION CR CRUISE 1 CA 288 2518 (CAN) WHILE IN CRUISE FLIGHT THE RT GENERATOR FELL OFF LINE AND WOULD NOT RESET. AIRCRAFT CONTINUED TO FUEL STOP AIRPORT . MAINTENANCE DISCOVERED FAULTY STARTER/GENERATOR WITH OBVIOUS DAMAGE TO FORWARD (DRIVE SPLINE END) BEARING. GENERATOR S ENT FOR OVERHAUL WITH REQUEST FOR BEARING EVALUATION. 2 L 7 2 4T 4 T RT A24CE E4EA 2001041700044 20010417 00044 SO 2001 4 17 CA010409010 2 20010329 G 7314 64621011A3 PUMP CESSNA 340 340A 2076405 CE CONT O520 TSIO520NB 17040 SO LT ENGINE FUEL FAILED W C ABORTED TAKEOFF J WARNING INDICATION TO TAKEOFF 1 CA 445 (CAN) LT ENGINE WOULD NOT RUN WITHOUT AUXILIARY ELECTRIC FUEL PUMP ON HIGH. FUEL PUMP AT DRIVE REPLACED, GROUND CHECKED OK. 1 L 7 2 3O 3 O 3A25 E8CE 2001041700045 20010417 00045 CE 2001 4 17 CA010409017 1 20010227 G 3240 AE2463509GO150 HOSE CESSNA 500 560CESSNA 2076750 CE PWA JT15 JT15D5 52112 NE MLG BRAKES LEAKING W O OTHER K J FLUID LOSS WARNING INDICATION AP APPROACH 1 CA 1214 (CAN) FLIGHT CREW REPORTED RT BRAKE SOFT, AND BRAKE PRESSURE LOW WARNING ON, CREW LANDED AIRCRAFT NORMALLY USING THRUST REV. AND BRAKES. MAINTENANCE FOUND LEAKING BRAKE HOSE, HOSE REPLACED, BRAKE SYSTEM BLEED.HOSE DATE: AEROQUIP TELFLON HOS E (FOR SKYDROL BRAKE FLUID) A/PT 04-98, 3000 PSI. 2 L 7 2 4F 4 F RT A22CE E25EA 2001041700046 20010417 00046 CE 2001 4 17 CA010409018 1 20010326 G 5510 04320049 BRACKET CESSNA 150 152 2071835 CE LYC O235 O235L2C 41505 EA HORIZONTAL STAB CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 9135 (CAN) FOUND DURING INSPECTION FOR 80-11-04 NUTPLATES FOR CRACKS, ALSO TRANSPORT CANADA SDA AV-2000-06. 1 H 7 1 3O 3 O NT 3A19 E223 2001041700047 20010417 00047 CE 2001 4 17 CA010409019 1 20010321 G 5510 04320041 BRACKET CESSNA 150 150F 2071814 CE CONT O200 O200A 17020 SO HORIZONTAL STAB CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 5116 (CAN) FOUND DURING INSPECTION FOR 80-11-04 NUTPLATES FOR CRACKS. ALSO SDA AV-2000-06. AFFTER REMOVAL OF BRACKET ALSO FOU ND REAR SPAR REINFORCEMENT P/N 0432001-15 CRACKED (HOLES ARE ALSO ELONGATED) ALONG TOPSIDE, AFTER REMOVAL OF REAR SPAR. REINFORCEMENT BOTH L/H AND R/H SPARS P/N 0432001-56. 1 H 7 1 3O 3 O 3A19 E252 2001041700048 20010417 00048 CE 2001 4 17 CA010409020 1 20010326 G 5510 04320049 BRACKET CESSNA 150 152 2071835 CE LYC O235 O235L2C 41505 EA MCAULY 1A103 1A103TCM GL HORIZONTAL STAB CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 13221 (CAN) FOUND DURING INSPECTION FOR 80-11-04 NUTPLATES FOR CRACKS, ALSO TRANSPORT CANADA SDA AV-2000-06. 1 H 7 1 3O 3 O NT 3A19 E223 5 N P50GL 2001041700049 20010417 00049 2001 4 17 CA010410006 4 20010322 G 3418 COMPUTER CNDAIR CL600 CL6002B19 EA GE CF34 CF343B1 NE STALL WARNING FAILED W O OTHER J WARNING INDICATION CL CLIMB 1 CA (CAN) STALL FAIL MESSAGE AFTER GEAR UP. MAINTENANCE CARRY LRU DIAGNOSTICS AND OPERATIONAL CHECK, NO FAULT FOUND AT THIS TIME AND AIRCRAFT BACK IN SERVICE. 2 L 7 2 4F 4 F RT A21EA E15NE 2001041700050 20010417 00050 EA 2001 4 17 CA010410008 1 20010322 G 5610 WINDOW CNDAIR CL600 CL6002B19 EA GE CF34 CF343B1 NE COCKPIT FAILED W O OTHER O OTHER CR CRUISE 1 CA (CAN) DURING CRUISE SIDE WINDOW SHATTERED, CREW DIVERTED AND MADE AN UNEVENTFUL LANDING. MAINTENANCE REMOVED AND REPLACE D SIDE WINDOW. 2 L 7 2 4F 4 F RT A21EA E15NE 2001041700051 20010417 00051 EA 2001 4 17 CA010410009 1 20010322 G 4920 APU CNDAIR CL600 CL6002B19 EA GE CF34 CF343A1 30015 NE APU BAY FAILED W F ACTIVATE FIRE EXT. A FLAME/FIRE IN INSP/MAINT 1 CA (CAN) APU SELECTED DURING DESCENT, FIRST TIME DID NOT START, PILOT RESELECT APU START. SECOND TIME APU START WITHOUT ANY INCIDENT. AIRCRAFT PULLED UP TO THE GATE, MAINTENANCE MET PILOT AT THE AIRCRAFT, ENGINE HAD BEEN SHUTDOWN WITH THE APU RUNNING. MAINTENANCE FOUND FIRE COMING OUT OF THE EXHAUST, PILOT EXECUTED THE FIRE EMERGENCY MEMORY ITEMS AND CONTACTED THE FIRE DEPARTMENT. FIRE DEPARTMENT SHOWED UP AND SPRAYED THE APU COMPARTMENT WITH EXTINGUISHANT.APU AND APU FIRE SYSTE M DEFERRED AND AIRCRAFT RETURNED TO SERVICE. 2 L 7 2 4F 4 F RT A21EA E15NE 2001041700052 20010417 00052 EA 2001 4 17 CA010410010 1 20010322 G 3040 601R330339 WINDSHIELD CNDAIR CL600 CL6002B19 EA GE CF34 CF343B1 NE COCKPIT FAILED W O OTHER O OTHER TX TAXI/GRND HDL 1 CA 1353 (CAN) AFTER LANDING CREW REPORT LT WINDSHIELD SHATTERED. MAINTENANCE REMOVED AND REPLACED WINDSHIELD AND AIRCRAFT BACK I N SERVICE. 2 L 7 2 4F 4 F RT A21EA E15NE 2001041700053 20010417 00053 EA 2001 4 17 CA010410012 1 20010322 G 2421 755469B IDG CNDAIR CL600 CL6002B19 EA GE CF34 CF343A1 30015 NE NR 1 DAMAGED W E A ENGINE SHUTDOWN UNSCHED LANDING J WARNING INDICATION CR CRUISE 1 CA 13233 13233 (CAN) DURING CRUISE, CREW NOTED AN IDG NR 1 FAULT MESSAGE, FOLLOWED BY OIL PRESSURE FLUCTUATIONS, OIL PRESSURE WARNING. THE ENGINE WAS SHUT DOWN AND THE AIRCRAFT MADE AN UNEVENTFUL SINGLE ENGINE LANDING. MAINTENANCE INVSTIGATION SUGGEST THA T IDG DISCONNECT DID NOT ACTIVE. IDG, ACCESSARY GEAR BOX AND LUBE/SCAVENGE PUMP WERE REMOVED AND REPLACED. OIL FILTER AN D OIL SAMPLE WERE SENT FOR ANALYSIS.AIRCRAFT HAS RETURNED IN SERVICE. 2 L 7 2 4F 4 F RT A21EA E15NE 2001041700054 20010417 00054 EA 2001 4 17 CA010410014 1 20010324 G 5610 NP1393216 WINDSHIELD CNDAIR CL600 CL6002B19 EA GE CF34 CF343B1 NE COCKPIT FAILED W O OTHER O OTHER CR CRUISE 1 CA 2877 (CAN) ENROUTE ATLANTA TO COLUMBIA SC, FIRST OFFICERS WINDSHIELD SHATTERED. CREW LANDED UNEVENTFULLY IN COLUMBIA.THE DAMA GE TO THE WINDSHIELD IS ON THE INNER SURFACE AND GLASS FRAGMENTS WERE FOUND ON THE GLARESHIELD BY MAINTENANCE. WINDSHIEL D WAS REPLACED AND TESTED I.A.W. AMM. 2 L 7 2 4F 4 F RT A21EA E15NE 2001041700055 20010417 00055 EA 2001 4 17 CA010410023 1 20010330 G 5610 NP1393215 WINDSHIELD CNDAIR CL600 CL6002B19 EA GE CF34 CF343B1 NE COCKPIT CRACKED W O OTHER O OTHER DE DESCENT 1 CA 40 (CAN) ON DESCENT INTO WICHITA THE LT WINDSHIELD CRACKED. AIRCRAFT WAS FERRIED TO MEMPHIS AND THE WINDSHIELD WAS REPLACED . 2 L 7 2 4F 4 F RT A21EA E15NE 2001041700056 20010417 00056 EA 2001 4 17 CA010410025 1 20010402 G 5610 NP1393212 WINDSHIELD CNDAIR CL600 CL6002B19 EA GE CF34 CF343B1 NE COCKPIT CRACKED W O OTHER O OTHER TX TAXI/GRND HDL 1 CA (CAN) THE RT WINDSHIELD MIDDLE PLY WAS FOUND CARACKED AIRCRAFT ON PARKING. THE AIRCRAFT DID A FERRY FLIGHT TO MORLAIX. T HE WINDSHIELD WAS REPLACED AT THE MAINTENANCE BASE AS PER AMM 56-11-01. 2 L 7 2 4F 4 F RT A21EA E15NE 2001041700057 20010417 00057 EA 2001 4 17 CA010410027 1 20010402 G 5210 601R3189233 ROD CNDAIR CL600 CL6002B19 EA GE CF34 CF343B1 NE PAX DOOR FAILED W O OTHER O OTHER TX TAXI/GRND HDL 1 CA (CAN) IN PITT DURING TURN AROUND, FLT ATTENDANT & CREW WERE UNABLE TO CLOSE MAIN PASSENGER DOOR. AFTER MULTIPLE ATTEMPT S CREW WERE ABLE TO CLOSE DOOR BUT WERE UNABLE TO RE-OPEN FROM INSIDE. NORTHWEST AIRLINK MAINT, ENGINEERING & BOMBARDIE R FSR WERE SENT TO PITT TO VERIFY REPORTED EVENT. IT NOTICED THAT WHEN ATTEMPTING TO SLOWLY CLOSE DOOR FROM INSIDE HANDL E WOULD JAM HALF WAY. WHILE HAVING HANDLE HALF WAY, TORQUE TUBES GREEN LINES WERE ALIGNED, WITH SECONDARY LOCK ALIGNM ENT LINE OFF BY APPROX 3/4 OF AN INCH. FLAPPER DOOR ALSO NOT FULLY CLOSED. LATCH BOX ASSY & ACTUATING RODS HAD NO VISUAL DEFECTS.THE RIG PINS WERE INST PER AMM. THE CNTL ROD ASSY 2 L 7 2 4F 4 F RT A21EA E15NE 2001041700058 20010417 00058 EA 2001 4 17 CA010410030 1 20010403 G 5610 601R2303310 WINDSHIELD CNDAIR CL600 CL6002B19 EA GE CF34 CF343B1 NE COCKPIT CRACKED W O OTHER O OTHER DE DESCENT 1 CA (CAN) THE RT WINDSHIELD INNER PLY CRACKED WHILE THE AIRCRAFT WAS IN DESCENT. THE WINDSHIELD WAS REPLACED AND THE AIRCRAF T RETURNED TO SERVICE. 2 L 7 2 4F 4 F RT A21EA E15NE 2001041700059 20010417 00059 SO 2001 4 17 CA010411003 1 20010315 G 5341 4A0021001 TAPER PIN EMB 110 EMB110P1 3260122 SO PWA PT6 PT6A34 52043 EA WING CORRODED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) AIRCRAFT TT: 18965.4 HRS CYC: 24946 PART TT: APP. 7200 HRS. IF REPLACED AT LAST C12 INSP. TAPER PIN CONE BUSHINGS ALSO AFFECTED. PIN DID NOT COME OUT WITH MANUFACTURERS SPECIAL TOOL PRESS. NEW PINS AND CONES REQUIRED. PIN HAD TO BE D RILLED AND CUT BY MACHINIST.IT APPEARS ITL P/N 1027251T2, MASTINOK 6856K JOINTING COMPOUND MADE BY PRC PESOTO INTERNATIO NAL HAS NOT BEEN UTILIZED AT INSTALLATION AS SPECIFIED. 1 L 7 2 4T 4 T A21SO E4EA 2001041700060 20010417 00060 EA 2001 4 17 CA010411004 1 20010312 G 5300 SKIN FRCHLD F27 F27F 3373008 EA RROYCE DART DART5297E 54507 EU FUSELAGE CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 36671 (CAN) CRACK FOUND AT TOP REAR CORNER OF FRONT CARGO DOOR FRAME (FUSELAGE). THE PROBLEM IS ONE BAD FLUSH RIVET CRACK FROM RIVET TO SKIN EDGE. CRACK FOUND ON DAILY INSPECTION.REPAIR DONE AT STATION 181.102 AND 14 INCH ABOVE W.L. 0 LINE. 2 H 7 2 4T 4 T 7A1 E297 2001041700061 20010417 00061 CE 2001 4 17 CA010411008 1 20010316 G 2822 RG34720A PUMP BEECH 200 200BEECH 1152920 CE PWA PT6 PT6A41 52043 EA FUEL BOOST LEAKING W K NONE K FLUID LOSS IN INSP/MAINT 1 CA 853 (CAN) CARRYING OUT A DAILY INSPECTION ON MARCH 16, AFTER RETURNING FROM A TRAINING FLIGHT. FOUND THAT THE ENGINE DRIVEN FUEL BOOST PUMP P/N 91-38003 THAT IS MOUNTED ON THE REAR OF ENGINE S/N PCE-81053 WAS LEAKING FUEL AROUND THE BASE OF THE VALVE THAT IS INSTALLED ON THE FUEL BOOST PUMP.ORDERED A NEW FUEL PUMP FROM TC STORES IN OTTAWA INSTALLED ON AIRCRAFT A ND FOUND IT TO BE SERVICEABLE FOR FLIGHT, NO LEAK FOUND. 1 L 7 2 4T 4 T A24CE E4EA 2001041700062 20010417 00062 EA 2001 4 17 CA010411011 2 20010326 G 7230 COMPRESSOR PWA PT6 PT6A28 EA ENGINE FAILED W K NONE C F.O.D. IN INSP/MAINT 1 CA (CAN) THE COMPRESSOR HAD SUSTAINED FOD. AFTER REPAIR, PT AND CT VANE AREA ADJUSTMENT, THE ENGINE WAS RELEASED WITH SIMIL AR TO NEW PERFORMANCE. 4 T E4EA 2001050700356 20010507 00356 NE 2001 5 7 CA010411013 2 20010316 G 7260 311196801 TOWERSHAFT PWA 120 PW120A NE SPIRAL GEAR FRACTURED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) THE CAUSE OF THE IN FLIGHT SHUTDOWN WAS A FRACTURED TOWERSHAFT, RESULTING IN A LOSS OF DRIVE TO THE FUEL AND OIL P UMPS. FAILURE ANALYSIS OF THE TOWERSHAFT INDICATES THAT THE FRACTURE RESULTED FROM FATIGUE AT THE OUTER SURFACE, LEADING TO A TWISTED DUCTILE FRACTURE WITH THE CENTRE OF THE SHAFT FAILING IN TENSILE MODE.THERE WERE NO IDENTIFIED WORKMANSHIP ERRORS RELATED TO THE FAILURE OF THE TOWERSHAFT. 2001-04-12 TC: NO DEFINITE RESULT OF FAILURE WAS DETERMINED. 4 T E20NE 2001050700360 20010507 00360 SW 2001 5 7 CA010423005 1 20010328 G 6420 BEARING 212010704107 BELL 212 212 1181420 SW PWA PT6T PT6T3 52045 EA TRUNNION FAILED W K NONE S AFFECT SYSTEMS IN INSP/MAINT 1 CA 185 AFS3682FM (CAN) BAD BRINNELLING, TEFLON WORN AWAY.(FLAPPING BEARINGS) 1 G 7 1 4U 4 U H4SW E22EA 2001050700361 20010507 00361 SW 2001 5 7 CA010423006 1 20010406 G 6220 206010189001 BEARING BELL 206011100021 BELL 206 206B 1181511 SW ALLSN 250C 250C20B 03013 GL MAIN ROTOR FAILED W K NONE O OTHER IN INSP/MAINT 1 CA 980 JILM11164 (CAN) FAILURE OF ROLLER BEARING CAGE CAUSED ROLLERS TO BUNCH UP AND MISALIGN WITH RACES, SCORING RACES, ROLLERS AND HUB. FAILURE WAS DETECTED BY AN ENGINEER OBSERVING PIECES OF METAL IN THE PURGED GREASE. PRIOR TO DISASSEMBLY NO RESTRICTED M OTION WAS DETECTED, HOWEVER, PIECES OF FAILED CAGE SHOWED EVIDENCE OF BEING SQUASHED BETWEEN ROLLERS AND RACES. THIS COU LD POTENTIALLY CAUSE A SEIZURE OF THE GRIP FEATHERING MOTION. 1 G 7 1 3U 3 U H2SW E4CE 2001050700362 20010507 00362 CE 2001 5 7 CA010423007 1 20010315 G 5610 10138402521 WINDSHIELD BEECH B300 B300 1159232 CE PWA PT6 PT6* 52043 EA COCKPIT BROKEN W O OTHER O OTHER CR CRUISE 1 CA (CAN) AIRCRAFT IN CRUISE FLIGHT 29,000 FEET ALTITUTE OAT 45 WEATHER CLEAR NO TURBULENCE. SIMULTANEOUS LOUD BANG AND LT ( PILOTS) WINDSHIELD (INNER PANE)INSTANT SPIDER WEB CRACKS. 2 L 7 2 4T 3 T RT A24CE E2NE 2001050700363 20010507 00363 WP 2001 5 7 CA010423009 1 20010316 G 6320 269D2512311 GEAR DOUG 369D25100505 HUGHES 369 369D 4470706 WP ALLSN 250C 250C20B 03013 GL M/R TRANSMISSION BROKEN W K NONE J WARNING INDICATION IN INSP/MAINT 1 CA 2214 U0312 (CAN) MAIN ROTOR TRANSMISSION REMOVED FOR MAKING METAL. UPON DISASSEMBLY IT WAS DISCOVERED THAT ON INPUT GEAR TOOTH HAD BROKEN OFF. THE TOOTH WAS FOUND IN THE SCAVENGE PUMP INTAKE.REMNANTS OF THE TOOTH WERE FOUND IN THE SCAVANGE SPRAY TUBE. 1 G 7 1 3U 3 U H3WE E4CE 2001050700364 20010507 00364 NM 2001 5 7 CA010423011 1 20010322 G 6210 A1561 BOOT ROBSIN A0052 ROBSIN R22 R22BETA NM LYC O320 O320B2C 41508 EA MAIN ROTOR BLADE LEAKING W K NONE O OTHER IN INSP/MAINT 1 CA 393 (CAN) AIRCRAFT PARKED OVERNIGHT WITH COVERS AND HEATERS ON THE ENGINE. OVERNIGHT TEMP -35C. PILOT HAD LEFT PRINCE GEORGE , B.C., THE PREVIOUS DAY AND TEMP WAS ABOUT +5C AT CYXS. PILOT NOTED NO DEFECTS THE MORNING OF DEPARTURE ON HIS PRE-FLIG HT AND AS HE REMOVED THE COVERS AND HEATERS. HE NOTED THAT OAT GAUGE READ -27 WHEN HE STARTED THE AIRCRAFT ON A WALK ARO UND AFTER ARRIVING BACK TO PRINCE GEORGE, HE NOTED OIL ON THE ROTOR HEAD AND THE PYLON. REMOVED THE ROTOR BLADES AND FOU ND THE INNER CLAMPS FOR THE BOOT LOOSE, TIGHTENED THEM AND REPLACED THE OIL. SUSPECT THAT WITH THE COLD WEATHER, THE BOO TS GOT STIFF AND THEN SLIPPED ON THE SPINDLE. AIRCRAFT HAD BEEN OPERATED OUT OF WARM HANGAR PRIOR. 1 G 7 1 3O 3 O H10WE E274 2001050700365 20010507 00365 EU 2001 5 7 CA010423012 1 20010329 G 2910 3408360821 HARNESS BAG JETSTM JETSTM4112 EU GARRTT TPE331 TPE33110 01514 WP ROTOL R333 R333482F12 GL OVERRIDE SWITCH BROKEN W A UNSCHED LANDING F FLT CONT AFFECTED CL CLIMB 1 CA (CAN) DURING CLIMB, THE FLAPS WOULD NOT OPERATE WITH THE CONTROL SWITCH. THE HYDRAULIC OVERRIDE HANDLE HAD TO BE USED TO FUNCTION THE FLAPS UP AND DOWN.THE OVERRIDE SWITCH WIRING HARNESS (P/N 340-4263110) WAS FOUND TO BE AT FAULT, ONE WIRE WAS BROKEN, THE RECOIL SPRING WAS BROKEN WHICH PROBABLY CAUSED THE WIRE TO BREAK DUE TO A LACK OF SUPPORT FROM THE SPRIN G. 1 L 7 2 4T 4 T RT A196 E4WE 6 C P61GL 2001050700367 20010507 00367 WP 2001 5 7 CA010423018 1 20010401 G 6210 500P2100101 BLADE HUGHES 369 369D 4470706 WP ALLSN 250C 250C20B 03013 GL MAIN ROTOR FAILED W K NONE O OTHER IN INSP/MAINT 1 CA 1711 A393 (CAN) BOND VOIDS BEYOND LIMITS LOW SIDE OF BLADE. LETTER SENT TO FAA DATED 24 APR 01 EXPRESSING TRANSPORT CANADA CONCERN S.(CADIS PROJECT REPORT 20010079. (CROSS REFER TO SDR 20010423019) 1 G 7 1 3U 3 U H3WE E4CE 2001050700368 20010507 00368 WP 2001 5 7 CA010423019 1 20010409 G 6210 500P2100101 BLADE HUGHES 369 369D 4470706 WP ALLSN 250C 250C20B 03013 GL MAIN ROTOR FAILED W K NONE O OTHER IN INSP/MAINT 1 CA 2120 A048 (CAN) BOND VOIDS BEYOND LIMITS LOW SIDE OF BLADE. LETTER SENT FAA DATED 24 APR 01 EXPRESSING TC CONCERNS. (CADIS PROJECT REPORT20010079). CROSS REFER TO SDR 20010423018. 1 G 7 1 3U 3 U H3WE E4CE 2001050700369 20010507 00369 EA 2001 5 7 CA010424002 2 20010316 G 7314 SHAFT SUNDSTRANDAI 02527730007 BELL 212 212 1181420 SW PWA PT6T PT6T3 52045 EA FUEL PUMP FAILED W O OTHER X J ENGINE FLAMEOUT WARNING INDICATION CR CRUISE 1 CA 4463 PE3224 (CAN) THE NR 2 ENGINE FLAMED OUT. AFTER THE PILOT LANDED THE AIRCRAFT SUCCESSFULLY, REMOVE THE AFCU, MFCU AND ENGINE DRI VEN FUEL PUMP. I FOUND THE FUEL PUMP SPLINES WITH NO LUBRICATION AND WORN WELL BEYOND LIMITS. (NOTE: THE SPLINED ADAPTER WAS SPINNING FREELY ON PUMP INPUT SPLINES.) 1 G 7 1 4U 4 U H4SW E22EA 2001050700370 20010507 00370 CE 2001 5 7 CA010424003 1 20010409 G 5510 043200146 RIB CESSNA 150 152 2071835 CE LYC O235 O235L2C 41505 EA STABILIZER CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) DURING INSPECTION STABILIZER RIB 0432001-46 LT, CRACKED. 1 H 7 1 3O 3 O NT 3A19 E223 2001050700372 20010507 00372 SW 2001 5 7 CA010425004 1 20010405 G 2435 230321380 BRUSHES LEARSIEGLER 23032018 BELL 206 206B 1181511 SW ALLSN 250C 250C20 03013 GL STARTER GEN BROKEN W K NONE O OTHER IN INSP/MAINT 1 CA 324 4666 (CAN) STARTER-GENERATOR WAS INSPECTED BECAUSE OF PREVIOUS HISTORY OF PROBLEMS IN THIS AR4A. UPON INSPECTION FOUND 3 BRUS H LEADS BROKEN OFF BRUSHES AND 3 SPRINGS BROKEN. THE STARTER GENERATOR HAS BEEN REMOVED FOR OVERHAUL. STARTER-GENERATOR LAST OVERHAULED AT CANADIAN AERO ACCESS, CALGARY AND INSTALLED ON AIRCRAFT AT 12445.8 BRUSHES HAD BEEN REPLACED AT 12653 .3STARTER-GENERATOR REMOVED AT 12769.8 1 G 7 1 3U 3 U H2SW E4CE 2001050700374 20010507 00374 EU 2001 5 7 CA010426002 1 20010327 G 2750 B001 SHAFT PILATS PC12 PC1245 EU PWA PT6 PT6A67B 52043 NE HARTZL HCE4A HCE4A3D GL TE FLAPS SHEARED W C B ABORTED TAKEOFF EMER. DESCENT B A SMOKE/FUMES/ODORS/SPARKS FLAME/FIRE AP APPROACH 1 CA 1898 (CAN) ON SELECTION OF FLAPS DOWN, FLAPS CAUTION ON C.A.W.S. PANEL CAME ON. FLAPS WERE RESET & TRIED AGAIN. FLAPS CAUTION CAME ON AGAIN. A/C LANDED W/O FLAP. MULTIPLE RESETS WERE THEN TRIED ON GROUND WHICH WOULD CAUSE F LAP CCT BREAKER ON B ATTERY BUS TO POP. TROUBLE SHOOTING REVEALED 2 INIT E203 CODES (MORE THAT 20 TURNS DIFFERENCE BETWEEN L/H & R/H ROTATION SENSORS, THEN MULTIPLE E208 CODES (OVERLOAD CB POPPED), & E203 CODES AGAIN. AS AIRCRAF T WASHED SHORTLY BEFORE DEPTR, I T IS FELT THAT R/H FLAP FROZE IN FLT CAUSING INIT E203 CODE. SUBSEQUENT RESETS CAUSED R/H INBOARD FLEX SHAFT TO SWELL & JAM IN ITS HOUSING CAUSING E208 CODES. DURING TROUBLE SHOOTING AFTER MORE RESETS, FLEX SHAFT EVENTUALLY BROKE CAU 1 L 7 1 3T 4 T RT A78EU E26NE 5 C P210NE 2001050700375 20010507 00375 EU 2001 5 7 CA010426003 1 20010328 G 3252 5322012262 STRAP PILATS PC12 PC1245 EU PWA PT6 PT6A67B 52043 NE HARTZL HCE4A HCE4A3D GL NLG BROKEN W K NONE O OTHER IN INSP/MAINT 1 CA 495 (CAN) NOSE GEAR BONDING STRAP P/N 532.20.12.262 WAS WRAPPED AROUND SHOCK STRUT P/N 571.10.12.353 AND HAD BENT THE STRUT SOME 70 DEGREES UP FROM ITS NORMAL POSITION. THE STRUT COULD NO LONGER OPEN AND CLOSE THE OIL COOLER DOOR UPON GEAR RETR ACTION. BONDING STRAP REQUIRED REPLACEMENT AS WELL AS THE STRUT. BONDING STRAP APPEARS TO BE A BIT LONGER THAN REQUIRED TO ALLOW FOR THE NOSE WHEEL ASSEMBLE TO TURN, THEREFORE CAUTION IS ADVISED WHEN INSTALLING BONDING STRAP TO ENSURE THAT THE BONDING STRAP WILL NOT SAG ONTO THE SHCOK STRUT ASSEMBLE. FIVE GEAR CYCLES COMPLETED AND AIRCRAFT WAS RETURNED TO SE RVICE. NO FURTHER ACTION WAS REQUIRED. 1 L 7 1 3T 4 T RT A78EU E26NE 5 C P210NE 2001050700378 20010507 00378 NM 2001 5 7 CA010426010 1 20010303 G 5230 85230480104 SUPPORT DHAV DHC8 DHC8103 1386005 NM PWA 120 PW120 NE HAMSTD 14SF 14SF7 NE COUNTER BALANCE CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) WE HAD AN INSPECTION OF THE BAGGAGE DOOR ON ONE OF OUR DASH 8S, S/N 357, PER TASK 5230/51 AND DURING THAT INSPECT ION, WE FOUND THE AFT COUNTER BALANCE SUPPORT P/N 85230480-104 WAS CRACKED. I AM SUBMITING A STRUCTURAL DEFECT REPORT FO R S/N 257. AIRCRAFT S/N 357 WAS DONE ON 3-3-01 AND HAD A TAT 16.286.6 AND TCY 26, 179. PART REPLACED. 2 H 7 2 4T 4 T RT A13NM E20NE 6 C P7NE 2001050700379 20010507 00379 NM 2001 5 7 CA010426019 1 20010403 G 3251 89923 LINK 8900115 DHAV DHC8 DHC8102 2809003 NM PWA 120 PW120A NE HAMSTD 14SF 14SF7 NE STEERING ACTU SPLIT W K NONE O OTHER IN INSP/MAINT 1 CA 22097 1081 DCL2388900 (CAN) DURING AN INSPECTION, THE NOSEWHEEL STEERING ACTUATOR TELESCOPING ADJUSTABLE LINK WAS FOUND SPLIT (PULLED APART) A ND THE ATTACH LOCKING BOLT FOR THE LINK WAS MISSING (P/N NAS 1304-7D).THE STEERING ACTUATOR ASSEMBLY WAS REPLACED AND AL L FURTHER CHECKS COMPLETED. 2 H 7 2 4T 4 T RT A13NM E20NE 6 C P7NE 2001050700380 20010507 00380 EA 2001 5 7 CA010426025 2 20010320 G 8520 LW16812 LIFTER PIPER PA44 PA44180 7104402 SO LYC O360 O360* 41514 EA ENGINE WORN W K NONE O OTHER IN INSP/MAINT 1 CA 651 (CAN) PILOT REPORTED VIBRATION ON LT & RT ENGINE ON RUN-UP. INSPECTED BOTH ENGINES, FOUND GOOD COMPRESSION, NO BROKEN EN GINE MOUNT (COMMON ON THIS AIRCRAFT). REMOVED LIFTERS FOUND BADLY DAMAGED, DAMAGE ON CAMSHAFT AS WELL. FRONT SURFACE MIS SING PIECES ON LIFTERS. BOTH ENGINES REMOVED (& PROP FOR FLUSHING) SEND TO LEAVENS AVIATION FOR REPAIR. NOTE: LIFTERS IN SPECTED ON 500 HOUR SINCE OVERHAUL, NO DAMAGE AT THAT TIME. DAMAGE OCCUR WITHIN 150 HR SINCE THAT INSPECTION. 1 L 7 2 3O 3 O A19S0 E286 2001050700381 20010507 00381 EA 2001 5 7 CA010426026 1 20010403 G 3244 0276970 TIRE CNDAIR CL604 CL604 EA MLG FAILED W K NONE O OTHER IN INSP/MAINT 1 CA 534 9181P00282 (CAN) A/C DEPARTED TOLUCA, MENCO & LANDED AT TORONTO. UPON ARRIVAL IT NOTED THAT NR 3 MAIN WHEEL TIRE MISSING ITS TREAD. GTAA OPS STAFF RPTED NO DEBRIS ON LDG RWY. THEREFORE SEPARATION, MOST LIKELY OCCURRED ON TAKEOFF FROM TOLUCA. BASED ON ATMOSPHERIC CONDITION AT TIME OF DEPTR, IT CALCULATED THAT ACTUAL SPEED SEEN BY WHEELS 162 KNOTS. IS WELL BELOW RATED SP EED FOR TIRE: TIRE SHOWED NO SIGNS OF DAMAGE THAT WOULD HAVE LED TO SEPARATION. ALSO, TIRES ARE REGULARLY CHECKED FOR CO RRECT TIRE PXS. AS RESULT OF SEPARATION, INBOARD RT FLAP INBD RT FLAP VANE&LOWER FWD SECTION OF RT PYLON, SUFFERED MINOR DENTS. ALSO RT MLG W.O.W. HARNESS BRACKET THAT AFFIXES TO CEILING OF GEAR BAY BECAME DISBONDED AS RESULT OF IMPACT. 2 L 7 2 4F RT A21EA 2001050700382 20010507 00382 WP 2001 5 7 CA010426031 2 20010330 G 7412 103784005 EXCITER CESSNA 441 441 2076020 CE GARRTT TPE331 TPE33110 01514 WP IGNITION SYS FAILED W O OTHER O OTHER TX TAXI/GRND HDL 1 CA 893 (CAN) ENGINE WOULD NOT START. FOUND IGNITION EXCITER UNSERVICEABLE. REPLACED UNIT. 1 L 7 2 3T 4 T RT A28CE E4WE 2001050700385 20010507 00385 NE 2001 5 7 CA010430008 2 20010307 G 7200 ENGINE AIRBUS 320 A320211 3930320 EU CFMINT CFM56 CFM565A1 NE RIGHT FAILED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) RT ENGINE HAD A RUMBLE SOUND AND WAS THROWING FLAMES OUT THE EXHAUST. CREW REPORTED COMPRESSOR STALL.ENGINE REMOVE D FOR INVESTIGATION. REPLACED ENGINE. 2 L 7 2 4F 4 F RT A28NM E29NE 2001050700389 20010507 00389 NE 2001 5 7 CA010430016 2 20010407 G 7200 ENGINE LKHEED 1011 1011385114 WP RROYCE RB211 RB21122B02 54555 NE NR 1 FAILED W E A ENGINE SHUTDOWN UNSCHED LANDING E J VIBRATION/BUFFET WARNING INDICATION CR CRUISE 1 CA 49254 (CAN) DRUING FLIGHT ENGINE NR 1 EXPERIENCED A SUDDEN VIBS INCREASE TO 3.5 UNITS ON BOTH CHANNELS A & B, WARNING LIGHTS C AME ON, ENGINE SHUT DOWN WAS ACCOMPLISHED.MCD CHECKS WAS C/O NOT DAMAGED, ENGINE BORESCOPE WAS C/O NO DAMAGE FOUND. FAN BLADES REMOVED CLEANED AND RE-INSTALLED, FAN CLAPPERS LUB.FAN TRIM BALANCE TO BE ACCOMPLISHED. 2 L 7 3 4F 4 F A23WE E12EU 2001050700391 20010507 00391 WP 2001 5 7 CA010430018 1 20010321 G 5230 1586301113 HANDLE LKHEED 1011 10113853 5265020 WP RROYCE RB211 RB211524B402 54555 NE CARGO DOOR OUT OF ADJ W A UNSCHED LANDING N FALSE WARNING CL CLIMB 1 CA (CAN) AT 9,000 FEET, DURING CLIMB, ON F/E ANNUNICATOR PANEL CARGO DOOR LIGHTS ILLUMINATE, AIRCRAFT RETURNED TO MAIN BASE . FOUND T HANDLE ADJUSTMENT OUT OF RIG, ADJUSTED IN ACCORDANCE WITH MAINTENANCE MANUAL 52-35-01 AND PROXIMITY SENSOR IN ACCORDANCE WITH 52-71-03. 2 L 7 3 4F 4 F A23WE E12EU 2001050700392 20010507 00392 EA 2001 5 7 CA010430022 1 20010406 G 5210 LOCK CNDAIR CL600 CL6002B19 EA GE CF34 CF343B1 NE PAX DOOR OUT OF ADJ W D RETURN TO BLOCK O OTHER TX TAXI/GRND HDL 1 CA (CAN) FLIGHT ATTENDANT REPORTED THAT SHE WAS UNABLE TO CLOSE AND LOCK THE PASSENGER DOOR. MAINTENANCE FOUND THE SECONDAR Y LOCK PAWL TO BE FOULING AGAINST THE TORQUE TUBE, TORQUE TUBE AND SECONDARY LOCK PAWL OUT OF ADJUSTMENT. THEY DID A PAS SENGER DOOR ADJUSTMENT PER THE AMM. AIRCRAFT RETURNED TO SERVICE. 2 L 7 2 4F 4 F RT A21EA E15NE 2001050700393 20010507 00393 EA 2001 5 7 CA010430024 1 20010407 G 5210 HANDLE CNDAIR CL600 CL6002B19 EA GE CF34 CF343B1 NE PAX DOOR JAMMED W D RETURN TO BLOCK O OTHER TX TAXI/GRND HDL 1 CA (CAN) WHILE AT THE GATE, AFTER BOARDING, THE FLIGHT ATTENDANT REPORTED THAT SHE WAS UNABLE TO CLOSE THE PASSENGER DOOR. THE FLIGHT ATTENDANT REPORTED THAT THE HANDLE WOULD JAM HALF WAY WHEN CLOSING.THE AIRCRAFT WAS BROUGHT TO THE HANGAR AND MAINTENANCE WERE UNABLE TO INSTALL THE RIG PINS. THE DOOR WAS RIGGED PER THE AMM AND THE AIRCRAFT RETURNED TO SERVICE. 2 L 7 2 4F 4 F RT A21EA E15NE 2001050700394 20010507 00394 EA 2001 5 7 CA010430025 1 20010407 G 5610 601R3303310 WINDSHIELD CNDAIR CL600 CL6002B19 EA GE CF34 CF343B1 NE COCKPIT FAILED W O OTHER O OTHER DE DESCENT 1 CA 00165H9933 (CAN) FIRST OFFICERS WINDSHIELD SHATTERED. CABIN DIFFERENTIAL PRESSURE 7.3. NO PRESSURE LOSS. REPLACED WINDSHIELD. 2 L 7 2 4F 4 F RT A21EA E15NE 2001050700395 20010507 00395 EA 2001 5 7 CA010501002 1 20010412 G 5210 BUSHING CNDAIR CL600 CL6002B19 EA GE CF34 CF343B1 NE PAX DOOR FAILED W D RETURN TO BLOCK O OTHER TX TAXI/GRND HDL 1 CA (CAN) WHEN THE AIRCRAFT ARRIVED IN THE HANGAR THE MECHANICS WERE UNABLE TO OPEN THE PASSENGER DOOR. THE BUSHING FROM THE CASTING FOR THE TORQUE TUBE WERE FOUND TO BE MIGRATED. THE BUSHING WERE RE-INSTALLED AND THE DOOR RIGGING C/OUT. 2 L 7 2 4F 4 F RT A21EA E15NE 2001050700396 20010507 00396 EA 2001 5 7 CA010501005 1 20010412 G 5610 NP1393216 WINDSHIELD CNDAIR CL600 CL6002B19 EA GE CF34 CF343B1 NE COCKPIT FAILED W O OTHER O OTHER CR CRUISE 1 CA (CAN) FIRST OFFICERS WINDSHIELD SHATTERED IN FLIGHT, NO CABIN PRESSURIZATION LOSS.WINDSHIELD REPLACED. 2 L 7 2 4F 4 F RT A21EA E15NE 2001050700397 20010507 00397 NE 2001 5 7 CA010501006 2 20010412 G 7200 4121T03G01 ENGINE CNDAIR CL600 CL6002B19 EA GE CF34 CF34* NE NR 2 FAILED W D RETURN TO BLOCK J WARNING INDICATION TX TAXI/GRND HDL 1 CA (CAN) ON TAXI WITH THE THROTTLE ON IDLE POSITION THE ITT ON ENGINE NR 2 INCREASED SUDDENLY UP TO 1093 CELSIUS. THE ENGIN E SHUT DOWN BY ITSELF.BASE ON THE INSPECTION RESULTS GE RECOMMANDS TO REPLACE THE FMU AND ENGINE RUN IN ORDER TO CONTINU E TO OPERATE THE ENGINE. 2 L 7 2 4F 4 F RT A21EA E15NE 2001050700398 20010507 00398 EA 2001 5 7 CA010501008 1 20010416 G 5610 WINDSHIELD CNDAIR CL600 CL6002A12 1900304 EA COCKPIT CRACKED W O OTHER O OTHER AP APPROACH 1 CA (CAN) R/H WINDSHIELD CRACKED WHILE ON APPROACH. MAINTENANCE REMOVED AND REPLACED RT WINDSHIELD WITH NEW UNIT. AIRCRFT BA CK IN SERVICE. 2 L 7 2 4F RT A21EA 2001050700399 20010507 00399 EA 2001 5 7 CA010501015 1 20010417 G 5610 601R330339 WINDSHIELD CNDAIR CL600 CL6002B19 EA GE CF34 CF343B1 NE COCKPIT CRACKED W O OTHER O OTHER LD LANDING 1 CA (CAN) UPON TOUCH DOWN, CAPTAINS WINDSHIELD INNER PLY CRACKED. WINDSHIELD REPLACED. 2 L 7 2 4F 4 F RT A21EA E15NE 2001051000067 20010510 00067 EA 2001 5 10 CA010501017 1 20010129 G 5610 601R330339 WINDSHIELD CNDAIR CL600 CL6002B19 EA COCKPIT FAILED W O OTHER O OTHER CR CRUISE 1 CA 11 (CAN) AT 17,000 FEET, 280 KTS - LT WINDSHIELD STARTED TO CRACK AND THEN SHATTERED. 2 L 7 2 4F RT A21EA 2001051000068 20010510 00068 EA 2001 5 10 CA010501021 1 20010205 G 5610 601R330339 WINDSHIELD CNDAIR CL600 CL6002B19 EA GE CF34 CF343B1 NE COCKPIT FAILED W O OTHER O OTHER CL CLIMB 1 CA 7 (CAN) CLIMBING THROUGH 31,000 FEET - 7 MACH, 8.2 P.S.I. LT WINDSHIELD SHATTERED. 2 L 7 2 4F 4 F RT A21EA E15NE 2001051500334 20010515 00334 NM 2001 5 15 CA010502004 1 20010405 G 2750 655280726 MODULE BOEING 737 737296 1384486 NM PWA JT8 JT8D9A 52048 NE TE FLAPS DEFECTIVE W D RETURN TO BLOCK N FALSE WARNING TX TAXI/GRND HDL 1 CA 1264 (CAN) AS THE POWER LEVERS WERE ADVANCED FOR TAKEOFF AT 1.2 EPR A WARNING HORN SOUNDED. THE TAKEOFF WAS REJECTED AND THE AIRCRAFT PROCEEDED BACK TO THE GATE WITHOUT INCIDENT. MAINTENANCE REPLACED THE FLAP/SLAT POSITION ACCESSORY UNIT P/N 65- 52807-26 S/N D00235. 2 L 7 2 4F 4 F RT A16WE E2EA 2001051500344 20010515 00344 CE 2001 5 15 CA010503011 1 20010427 G 2810 FUEL CELL BEECH 1900 1900C 1154161 CE PWA PT6 PT6A65B 52043 EA RT WING LEAKING W O OTHER K FLUID LOSS CL CLIMB 1 CA 17749 (CAN) A/C DEPARTED SMITHERS, BC ENROUTE TO VANCOUVER. AT APPROX 15 MIN. OUT A PASSENGER NOTED TO CREW THAT RT WING HAD A SMALL LEAK OF FUEL COMING FROM A RIVET HEAD JUST O/B OF ENGINE NACELLE. THE CREW HAD NO IND.S OUT OF ORDINARY BUT AFTE R CONFERRING WITH MAINT OVER RADIO THEY ELECTED TO RETURN TO SMITHERS AS A PRECAUTIOINARY MEASURE: EMERG SRVCS WHERE STA NDING BY & THE A/C MADE AN UNEVENTFUL LDG. LEAK WAS ONLY EVIDENT BY SOME WEEPING ON R/H WING & MUST HAVE BEEN GREATER W ITH WING LOADING & AIRPRESSURES IN FLT.MAINT DEFUELED A/C ANDINVESTIGATED INTERNAL AREAS OF WING. SOME RIVETS WHERE SEAL ED IN AREA OF WEEPING & A LEAK CHECK CARRIED OUT. 2 L 7 2 4T 4 T RT A24CE E4EA 2001051500345 20010515 00345 CE 2001 5 15 CA010503012 1 20010416 G 3222 12434262 TORQUE LINK CESSNA 210 210L 2073448 CE CONT O520 IO520L 17032 SO NOSE GEAR CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) UPPER NOSE GEAR TORQUE LINK FOUND CRACKED HALF WAY UP PART AS SHOW. CRACK WAS IN TWO LOCATIONS ABOUT 1/4 INCH LONG . PART HAD NOT FAILED.THIS IS THE SECOND PART FOUND CRACKED ON CESSNA 210 AIRCRAFT, BOTH IN THE SAME LOCATION. 1 H 7 1 3O 3 O 3A21 E5CE 2001051500346 20010515 00346 CE 2001 5 15 CA010503013 1 20010418 G 3222 12434262 TORQUE LINK CESSNA 210 T210K 2073447 CE CONT O520 TSIO520H 17040 SO MCAULY 3A32C D3A32C88 GL NOSE GEAR CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) UPPER NOSE GEAR TORQUE LINK FOUND CRACKED AS SHOWN. CRACK WAS IN TWO LOCATIONS ABOUT 1/8 INCH LONG. PART HAD NOT F AILED.THIS IS THE SECOND PART FOUND CRACKED ON CESSNA 210 AIRCRAFT, BOTH IN THE SAME LOCATION. 1 H 7 1 3O 3 O 3A21 E8CE 5 C P21EA 2001051500347 20010515 00347 NE 2001 5 15 CA010503015 1 20010323 G 2421 31176002 SHAFT SKRSKY S76 S76C 8143008 NE TMECA ARRIEL ARRIEL2B NE GENERATOR WORN W K NONE O OTHER IN INSP/MAINT 1 CA 237 (CAN) AIRCRAFT GENERATOR TURNS AT 12,000 RPM IS DRIVEN BY THE MAIN TRANSMISSION OF HELICOPTER & FAN CAME LOOSE ON SHAFT, RETENTION NUT MS21042-4 HAD SELF LOCKING FRICTION STILL WITHIN LIMITS. FAN IS A FIT ON SHAFT BY NUT TORQUE ONLY, NUT MU ST NOT HAVE BEEN ON TIGHT ENOUGH, EVEN THOUGH NUT FRICTION WAS WITHIN LIMITS. FAN BEGAN TO VIBRATE AND A HIGH FREQUENCY VIBRATION WAS FELT. FAN COST IS US$4,900.00 FOR A SIMPLE FAN BLADE WITH REQUIRED AN EXCHANGE GENERATOR COST US$13,000. 1 G 7 2 3U 3 U NC H1NE E00054EN 2001051500348 20010515 00348 NM 2001 5 15 CA010503016 1 20010414 G 2920 231840 POWER UNIT DHAV DHC8 DHC8102 2809003 NM PWA 120 PW120A NE HAMSTD 14SF 14SF7 NE HYD SYSTEM FAILED W K NONE O OTHER IN INSP/MAINT 1 CA MX467234 (CAN) WHILE USING STANDBY POWER UNIT DURING ROUTINE MAINTENANCE, IT WAS DISCOVERED THAT UNIT WAS NOT PRODUCING PRESSURE. UNIT REPLACED WITH SERVICEABLE AND AIRCRAFT RETURNED TO SERVICE. 2 H 7 2 4T 4 T RT A13NM E20NE 6 C P7NE 2001051500349 20010515 00349 NE 2001 5 15 CA010503017 1 20010418 G 6320 SB3151A1 BEARING SKRSKY S61 S61N 8142104 NE GE CT58 CT581401 30011 NE MAIN ROTOR GB FAILED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) INPUT BEARING FAILED DURING THE INITIAL RUN IN PROCEDURE. INVESTIGATION SHOWED THAT BEARING PUSHER TOOL WAS IMPROP ERLY USED CAUSING DEFORMATION OF BEARING CAGE AT OVERHAUL. TOOL WAS REMOVED FROM SHOP TO PREVENT POSSIBLE REOCCURRENCE. 2 G 7 2 4U 4 U 1H15 1E3 2001051500350 20010515 00350 EA 2001 5 15 CA010504002 3 20010411 G 6110 PROPELLER PIPER PA22 PA22135 7102206 SO LYC O320 O320B2A 41508 EA SNSNCH 74DM M74DM EA ENGINE CORRODED W K NONE O OTHER IN INSP/MAINT 1 CA 2480 336 (CAN) HEAVY CORROSION THRU-OUT INTER PROPELLER, .040TH OFF MATERIAL. REMOVED TO REMOVE CORROSION. 1 H 7 1 3O 3 O 1A6 E274 5 N P88614 2001051500351 20010515 00351 EU 2001 5 15 CA010504004 1 20010419 G 6520 369D25434 SHAFT 369D25400 HUGHES 369 369FF EU ALLSN 250C 250C30 03013 GL T/R GEARBOX BROKEN W K NONE O OTHER IN INSP/MAINT 1 CA 2673 1076 (CAN) - METAL GENERATION, SCHEDULED 100 HOUR INSPECTION.- GEARBOX REMOVED AND SENT FOR REPAIR. - TEARDOWN INSPECTION FOU ND THAT THE INPUT GEARSHAFT HAD FAILED INBOARD OF THE INPUT GEAR.- THIS GEARBOX HAD BEEN REPAIRED ON 3 PREVIOUS OCCASION S FOR CLOUDY OIL/SLUDGE IN OIL.- THE FAILED SHAFT HAS BEEN SENT FOR METALLURGICAL INSPECTIONS. 1 G 7 1 3U 3 U H3WE E1GL 2001060400001 20010604 00001 EU 2001 6 4 CA010504007 1 20010323 G 5530 SD3316384XAA FITTING STBROS SD360 STBROS SD3 SD360 8100606 EU PWA PT6 PT6A65R 52043 EA VERTCAL STAB CORRODED W K NONE O OTHER IN INSP/MAINT 1 CA 28800 SH3633 (CAN) DURING MID-LIFE STRUCTURAL INSPECTION THE ABOVE CLEAT WAS FOUND TO BE EXFOLIATED IN VARIOUS SPOTS BETWEEN THE WEBS . IT IS LIKELY THAT STANDING WATER COULD SIT IN THE WEB AREAS AND SPEED UP THE CORROSION PROCESS. THE VERTICAL STAB WAS REMOVED TO OBTAIN ACCESS TO THE CLEAT. THE CLEAT WAS REPLACED AND THE VERTICAL STAB REINSTALLED. 2 H 7 2 4T 4 T A41EU E4EA 2001051500355 20010515 00355 CE 2001 5 15 CA010504009 1 20010405 G 5552 MS20253P25120 PIN CESSNA 550 CESSNA 500 550 2076604 CE LT ELEVATOR HING MISMANUFACTURED W K NONE W INADEQUATE Q C IN INSP/MAINT 1 CA 2339 2339 5500807 (CAN) FOUND ELEVATOR TRIM TAB HING PIN SHORT IN LENGTH ON LEFT SIDE ELEVATOR. 1 L 7 2 4F A22CE 2001051500356 20010515 00356 CE 2001 5 15 CA010504010 1 20010408 G 2720 03101965 SPRING CESSNA 172 172M 2072418 CE LYC O320 O320E2D 41508 EA MCAULY 1C160 1C160DTM GL RUDDER DISCONNECTED W A UNSCHED LANDING F FLT CONT AFFECTED CR CRUISE 1 CA (CAN) LT RUDDER AND BRAKE PEDAL RETURN SPRING P/N 0310196-5 BECAME DISLODGED FROM FRONT ANCHOR POINT BRACKET P/N 510128 IN FORWARD CENTRE TUNNEL ASSEMBLY P/N 0591301-11.THIS ALLOWED THE LEFT BRAKE & RUDDER PEDAL TO MOVE FULL FWD. THE PEDALS WOULD NOT RETURN TO NEUTRAL POSITION. ALSO NO LEFT BRAKE WAS AVAILABLE DUE TO ANGLE OF PEDALS.BY ROLLING THE SPRING P/N 0310196-5, ONE EIGHTY DEGREES & HOOKING IT OUT THROUGH BRACKET P/N 0510128 INSTEAD OF IN THROUGH THE BRACKET WOULD PREV ENT THE SPRINGS P/N 0310196-3 L/H AND P/N 0310196-12 FROM BECOMING DISLODGED. BY DOING THIS THE GEOMENTRY OF THE SPRINGS ARE NOT ALTERED.NO EVIDENCE OF WEAR WAS VISIBLE ON ANY OF THE ABOVE MENTIONED PARTS. 1 H 7 1 3O 3 O NT 3A12 E274 5 N P910 2001051500357 20010515 00357 EU 2001 5 15 CA010504012 1 20010420 G 2550 AS2219 CABLE SNIAS 350 AS350B2 8680813 EU CARGO HOOK BROKEN W K NONE P NO WARNING INDICATION IN INSP/MAINT 1 CA (CAN) THE METAL SHEATH THAT FORMS THE OUTER COVER OF THE MANUAL EMERGENCY RELEASE CABLE FOUND BROKEN. THE SHEATH WAS BRO KEN WHERE THE RELEASE CABLE ATTACHES TO THE CARGO HOOK. THIS IS A CARGO SWING INSTALLATIION WHERE THE CARGO HOOK IS ATTA CHED TO A FRAME THAT IS SUSPENDED FROM THE HELICOPTER BY FOUR CABLES. THERE IS A SUBSTANTIAL AMOUNT OF MOTION/MOVEMENT O F THE CARGO HOOK RELATIVE TO THE HELICOPTER. THE RELEASE CABLE UNDERGOES A LOT OF FLEXING, LEADING TO FATIGUE FAILURE AT CABLE ATTACHMENT. 1 G 7 1 3U H9EU 2001051500361 20010515 00361 EU 2001 5 15 CA010504018 1 20010409 G 6510 BB1B649781A BEARING 11731521 BOLKMS 117 BK117A4 5626017 EU LYC LTS101 LTS101650B1 41560 NE TAIL ROTOR DRIVE ROUGH W K NONE O OTHER IN INSP/MAINT 1 CA 4574 443 (CAN) HEARD CLICKING NOISE DURING DAILY INSPECTION WHILE TURNING MAIN ROTOR.DISCOVERED ROUGH NR 3 TAIL ROTOR DRIVESHAFT BEARING, BEARING CAUSED RUBBER SLEEVE ON SHAFT TO SPIN. DAMAGE TO SHAFT BEYONG LIMITS. SUSPECT INTERNAL CORROSION DUE TO HISTORY OF THIS PART SITTING IN STORAGE FOR A LONG TIME. 1 G 7 2 3U 3 U H13EU E5NE 2001051500362 20010515 00362 EU 2001 5 15 CA010504020 1 20010415 G 6510 350A236534451 BRACKET SNIAS 350 AS350B2 8680813 EU TMECA ARRIEL ARRIEL1D NE T/R BEARING CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 4216 (CAN) UPON INSPECTION, THE EIGINEER NOTICED A CRACK ON THE NR 5 T/R HANGAR BEARING SUPPORT BRACKET. 1 G 7 1 3U 3 U H9EU E19EU 2001051500363 20010515 00363 EU 2001 5 15 CA010504021 1 20010415 G 2913 350A35107000 BRACKET SNIAS 350 AS350B2 8680813 EU TMECA ARRIEL ARRIEL1D NE HYD PUMP MOUNT CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 4216 (CAN) UPON INSPECTION THE ENGINEER NOTICED A CRACK ON THE HYDRAULIC PUMP MOUNTING BRACKET. THE CRACK SEEMS TO ORIGINATE FROM TOOL MARKS CAUSED BY MAINTENANCE. 1 G 7 1 3U 3 U H9EU E19EU 2001051500370 20010515 00370 SO 2001 5 15 CA010507006 1 20010213 G 3245 600X6 TUBE MICHEL 6006 PIPER PA31 PA31350 7103110 SO LYC O540 TIO540J2BD 41532 EA NLG TIRE FAILED W D RETURN TO BLOCK O OTHER TX TAXI/GRND HDL 1 CA 68 (CAN) NOSE TIRE DEFLATED. TUBE FOUND DEFECTIVE WITH HOLE IN SIDEWALL. MANUFACTURE NOTIFIED. 1 L 7 2 3O 3 O A20SO E14EA 2001051500371 20010515 00371 SO 2001 5 15 CA010507007 1 20010227 G 3245 600X6 TUBE MCCREARY 6006 PIPER PA31 PA31350 7103110 SO LYC O540 TIO540J2BD 41532 EA NLG TIRE FAILED W D RETURN TO BLOCK O OTHER TX TAXI/GRND HDL 1 CA 20 (CAN) NOSE WHEEL DEFLATED.TUBE WAS FOUND DEFECTIVE WITH PIN HOLE IN SIDEWALL. MANUFACTURE NTIFIED. 1 L 7 2 3O 3 O A20SO E14EA 2001051500372 20010515 00372 SW 2001 5 15 CA010507008 1 20010409 G 6320 F506A OIL CAP BELL F506A BELL 206 206L 1181522 SW ALLSN 25OC 250C20R GL LOCKING PINS LOOSE W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) LOCKING PINS IN TRANSMISSION OIL FILTER CAP ASSEMBLY CAME LOOSE AND FELL OUT OF TRANSMISSION OIL FILLER CAP ASSEMB LY. REPLACED WITH NEW OIL FILTER CAP ASSEMBLY 1 G 7 1 3U 3 U H2SW E4CE 2001051500377 20010515 00377 EA 2001 5 15 CA010507015 1 20010507 G 2731 M3414 ROD END DHAV DHC3 DHC3 2800202 EA PWA PT6 PT6A135 52043 NE BEARING WORN W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) FOUND ROD END WORN EXCESSIVELY ON INSPECTION 200 HOURS AFTER STC SA99-219/ST01243NY WAS INSTALLED. 1 H 7 1 3R 4 T A815 E4EA 2001051500388 20010515 00388 CE 2001 5 15 CA010508007 1 20010418 G 2612 302157 FIRE DETECTOR BEECH 100 A100 1152915 CE PWA PT6 PT6A28 EA NR 1 ENGINE SHORTED W O OTHER N FALSE WARNING DE DESCENT 1 CA 69428 (CAN) DURING DESCENT NR 1 ENG FIRE INDICATION ILLUMINATED. ENGINE WAS SHUT DOWN. INSPECTION DETERMINED NO ACTUAL FIRE. T HE ERRONEOUS FIRE INDICATION COULD NOT BE DUPLICATED ON GROUND. BASED ON PREVIOUS TROUBLE SHOOTING ALL THE WIRING FOR TH E FIRE DETECTIONS WAS SPRAYED WITH WATER. WHEN THE WIRING WAS MOVED, OR THE WIRE BUNDLE SQUEEZED, THE FIRE INDICATION IL LUMINATED. INVESTIGATION REVEALED THAT THE WIRING FOR THESE DETECTIONS ARE SUSCEPTABLE TO MOISTURE AND SUBSEQUENTLY WILL SHORT OUT BRINGING ON THE FALSE INDICATION. 1 L 7 2 3T 4 T A14CE E4EA 2001051500389 20010515 00389 SO 2001 5 15 CA010508008 1 20010405 G 5730 62061804 SKIN PIPER PA28 PA28161 7102803 SO LYC O320 O320D3G 41508 EA WING CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) UPON INSPECTION ON SCHEDULED #50, FOUND REAR WALK SKIN FLEX TOO MUCH ON ONE SPOT. OPEN INSPECTION PANEL, FOUND CRA CK DOUBLER, ON ENFORCED SKIN (THAT IS SANDWICH SKIN). CRACK LENGTH 5 INCHES.SKIN ORDERED, TO BE REPLACE. 1 L 7 1 3O 3 O 2A13 E274 2001051500390 20010515 00390 2001 5 15 CA010508009 4 20010424 G 2562 E0109 BRACKET CESSNA 150 152 2071835 CE LYC O235 O235L2C 41505 EA ELT LOOSE W K NONE O OTHER IN INSP/MAINT 1 CA 401 029168 (CAN) MOUNTING BRACKET FOR PORTABLE ANTENNA HAS LOOSE FIT AND ALLOWS ANTENNA TO FALL OUT. MS 28775-009 O-RING USED TO RE TAIN ANTENNA. 1 H 7 1 3O 3 O NT 3A19 E223 2001051500392 20010515 00392 NM 2001 5 15 CA010508011 1 20010420 G 5730 SKIN BOEING 727 72725C 138400H NM PWA JT8 JT8D7B 52053 NE WINGLET DELAMINATED W K NONE O OTHER IN INSP/MAINT 1 CA 3840 3840 (CAN) DURING ROUTING C CHECK INSPECTION , FOUND EVIDENCE OF DELAMINATION AT UPPER CHORD, 8 INCHES LONG, 6 1/2 INCHES FOR WARD OF AFT MOUNT FITTING. WINGLET REMOVED AND RETURNED TO WINGLET SYSTEM FOR EVALUATION AND POSSIBLE RECTIFICATION. WIN GLET SYSTEMS PROVIDED REPLACEMENT WINGLET FOR INSTALLATIOIN TO AIRCRAFT. 2 L 7 3 4F 4 F A3WE E2EA 2001051500393 20010515 00393 EA 2001 5 15 CA010508013 1 20010212 G 7120 C2EM4A MOUNT DHAV DHC2 DHC2* 2800108 EA PWA R985 R985AN14B 52008 NE ENGINE CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 8689 (CAN) THE ENGINE WAS CHANGED IN THE AIRCRAFT. UPON INSPECTION, THE ENGINE MOUNT WAS FOUND TO BE CRACKED AROUND THE LORD MOUNT PADS. THE MOUNT ASSEMBLY P/N C2EM4-A WAS REPLACED WITH A REPAIRED PART. 1 H 7 1 3R 3 R A806 5E1 2001051500394 20010515 00394 EA 2001 5 15 CA010508014 1 20010508 G 5312 C2FS533 FORMER DHAV DHC2 DHC2* 2800108 EA PWA R985 R985AN14B 52008 NE BULKHEAD CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 9689 (CAN) THE INSPECTION REQUIRED BY CF-98-38 BULKHEAD CRACKS STA. 288 WAS CARRIED OUT ON THE AIRCRAFT. THE BULKHEAD AND THE CHANNEL ASSEMBLY WERE FOUND TO BE CRACKED. P/N C2FS533 FORMER WAS REPLACED WITH A NEW PART. P/N C2FS4045A CHANNEL ASSEM BLY WAS REPLACED WITH A NEW PART. 1 H 7 1 3R 3 R A806 5E1 2001051500396 20010515 00396 EA 2001 5 15 CA010509002 1 20010423 G 5711 75710099 SPAR CAP DHAV DHAV DHC7 DHC7102 2802708 EA PWA PT6 PT6A50 52043 EA HAMSTD 24PF 24PF305 GL LT & RT WING CHAFED W K NONE O OTHER IN INSP/MAINT 1 CA 24387 (CAN) WE HAVE FOUND CHAFING AT YW279 LT & RT ON THE WING REAR SPAR CAP, BEHIND THE NR 1 AND NR 4 NACELLES. THIS CHAFING IS CAUSED BY A WIRE BUNDLE IN BOTH LOCATIONS. WE HAVE SEEN THIS DAMAGE IN THEE EARLIER MAINTENANCE PROJECTS, ON THE FOLL OWING AIRCRAFT: (1) DHC-7 S/N 037 (GFOF) TSN: 30142.1 CSN: 42908(2) DHC-7 S/N 63 (GCEV) TSN: 33390.4 CSN: 32682(3) DHC- 7 S/N 81 (KWZV) TSN: 32198.4 CSN: 30818IN ALL CASES, THE DAMAGE WAS ADDRESSED WITH A REPAIR SCHEME PROVIDED BY DEHAVILL AND. 2 H 7 4 4T 4 T A20EA E4EA 6 C P1NE 2001051500397 20010515 00397 EA 2001 5 15 CA010509003 1 20010423 G 5711 75710099 SPAR CAP DHAV DHAV DHC7 DHC7102 2802708 EA PWA PT6 PT6A50 52043 EA HAMSTD 24PF 24PF305 GL LT & RT WING CHAFED W K NONE O OTHER IN INSP/MAINT 1 CA 30142 (CAN) WE HAVE FOUND CHAFING AT YW279 LT & RT ON THE WING REAR SPAR CAP, BEHIND THE NR 1 AND NR 4 NACELLES. THIS CHAFING IS CAUSED BY A WIRE BUNDLE IN BOTH LOCATIONS. WE HAVE SEEN THIS DAMAGE IN THREE EARLIER MAINTENANCE PROJECTS, ON THE FOL LOWING AIRCRAFT:(1) DHC-7 S/N 036 (GJPI) TSN: 24386.6 CSN: 43093(2) DHC-7 S/N 63 (GCEV) TSN: 33390.4 CSN: 32682(3) DHC- 7 S/N 81 (KWZV) TSN: 32198.4 CSN: 30818IN ALL CASES, THE DAMAGE WAS ADDRESSED WITH A REPAIR SCHEME PROVIDED BY DEHAVILL AND. 2 H 7 4 4T 4 T A20EA E4EA 6 C P1NE 2001051500398 20010515 00398 EA 2001 5 15 CA010509004 1 20010423 G 5711 75710099 SPAR CAP DHAV DHAV DHC7 DHC7103 2802710 EA PWA PT6 PT6A50 52043 EA HAMSTD 24PF 24PF305 GL LT & RT WING CHAFED W K NONE O OTHER IN INSP/MAINT 1 CA 33390 (CAN) WE HAVE FOUND CHAFING AT YW279 LT & RT ON THE WING REAR SPAR CAP, BEHIND THE NR 1 AND NR 4 NACELLES. THIS CHAFING IS CAUSED BY A WIRE BUNDLE IN BOTH LOCATIONS. WE HAVE SEEN THIS DAMAGE IN THREE EARLIER MAINTENANCE PROJECTS, ON THE FOL LOWING AIRCRAFT:(1) DHC-7 S/N 036 (GJPI) TSN: 24386.6 CSN: 43093 (2) DHC-7 S/N 037 (GFOF) TSN: 30142.1 CSN: 42908 (3) DHC-7 S/N 81 (KWZV) TSN: 32198.4 CSN: 30818 IN ALL CASES, THE DAMAGE WAS ADDRESSED WITH A REPAIR SCHEME PROVIDED BY DE HAVILLAND. 2 H 7 4 4T 4 T A20EA E4EA 6 C P1NE 2001051500399 20010515 00399 EA 2001 5 15 CA010509005 1 20010423 G 5711 75710099 SPAR CAP DHAV DHAV DHC7 DHC7103 2802710 EA PWA PT6 PT6A50 52043 EA HAMSTD 24PF 24PF305 GL LT & RT WING CHAFED W K NONE O OTHER IN INSP/MAINT 1 CA 32198 (CAN) WE HAVE FOUND CHAFING AT YW279 LT & RT ON THE WING REAR SPAR CAP, BEHIND THE NR 1 AND NR 4 NACELLES. THIS CHAFING IS CAUSED BY A WIRE BUNDLE IN BOTH LOCATIONS. WE HAVE SEEN THIS DAMAGE IN THREE EARLIER MAINTENANCE PROJECTS, ON THE FOL LOWING AIRCRAFT:(1) DHC-7 S/N 036 (GJPI) TSN: 24486.6 CSN: 43093(2) DHC-7 S/N 037 (GFOF) TSN: 30142.1 CSN: 42908(3) DHC- 7 S/N 63 (GCEV) TSN: 33390.4 CSN: 32682IN ALL CASES, THE DAMAGE WAS ADDRESSED WITH A REPAIR SCHEME PROVIDED BY DEHAVILL AND. 2 H 7 4 4T 4 T A20EA E4EA 6 C P1NE 2001051500405 20010515 00405 CE 2001 5 15 CA010509015 1 20010417 G 2720 04115261 TORQUE TUBE CESSNA 150 152 2071835 CE LYC O235 O235L2C 41505 EA CABLE ARM CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 9133 (CAN) CRACK FOUND IN WELD FROM TORQUE TUBE TO CABLE ARM. THE CRACK WAS APPROXIMATELY 1/8 INCH LONG AT THE END OF THE WEL D. 1 H 7 1 3O 3 O NT 3A19 E223 2001051500407 20010515 00407 SW 2001 5 15 CA010510003 1 20010403 G 6710 206010355003 TUBE 206010355001 BELL 206 206L 1181522 SW ALLSN 25OC 250C20R GL PITCH LINK ASSY CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 14068 DI035 (CAN) CRACK WAS VISIBLE TO NAKED EYE EMINATING FROM LOWER INSERT FAYING SURFACE AND EXTENDING VERTICALLY UPWARD 0.4 INCH ES. SOME CORROSION PRESENT. REPLACED BOTH PITCH LINK ASSEMBLY WITH LINK ASSY P/N 206-010-360-005. SUSPECT THEY ARE ORIGI NAL WHICH MEANS 14,068 HOURS. 1 G 7 1 3U 3 U H2SW E4CE 2001051500408 20010515 00408 CE 2001 5 15 CA010510004 1 20010417 G 2400 2050421 CONNECTOR CESSNA 208 208B 2073701 CE PWA PT6 PT6A114A 52043 NE MCAULY 3AF34C 3GFR34C703 GL ELECTRICAL CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 193 (CAN) THIS CONNECTOR HAS BEEN FOUND TO BE EASILY DAMAGED WHEN IT IS REQUIRED TO REMOVE OR INSERT A CONTACT IN IT. NEW RE PLACEMENT PARTS OFTEN ARRIVE DAMAGED AS WELL. WHILE NOT A PROBLEM IN TYPICAL OPERATION IT DOES ALLOW FOR THE POSSIBILITY AT THE TERMINAL BEING HELD IN PLACE ONLY BY THE SEALING COMPOUND. THERE IS A SPECIFIC TOOL FOR INSERTING THESE CONTACTS BUT EVEN WITH EXTREME CARE, IT IS VERY EASY TO DAMAGE THE CONNECTOR. CONNECTOR P/N 205042-1, 205043-1 1 H 7 1 3T 3 T A37CE E4EA 5 C P60GL 2001051500409 20010515 00409 EA 2001 5 15 CA010510005 1 20010420 G 5315 60035031159 FLOORBEAM CNDAIR CL601 CL6012A12 1900303 EA GE CF34 CF34* NE FUSELAGE CORRODED W K NONE O OTHER IN INSP/MAINT 1 CA 5393 (CAN) DURING A CORROSION INSPECTION EXCESSIVE CORROSION AND EXFOLIATION WAS FOUND ON THE TOP SURFACE OF TWO FLOOR BEAMS IN THE AREA UNDER THE LAVATORY AND WATER SYSTEMS FILL CANISTERS. FS 559 TO FS 621. 2 L 7 2 4F 4 F RT A21AE E15NE 2001051500411 20010515 00411 EU 2001 5 15 CA010510007 1 20010412 G 7830 9055M20P272 CLAMP 9118M85G02 AIRBUS 300 A300B4203 3930306 EU GE CF6 CF650C2 30018 NE THRUST REVERSER BROKEN W C ABORTED TAKEOFF M OVER TEMP TO TAKEOFF 1 CA (CAN) - ON TAKEOFF REW NOTICED 3/4 KNOB THROTTLE STAGGER. - DURING CLIMB NR 2 ENGINE LOOP B LIGHT ON. - IN CRUISE NOTICE D NACELLE TEMP RISING.- UPON LANDING FOUND NR 2 ENGINE T/R BLOW OUT PANEL HANGING DOWN. - NR 2 CORE COWLS OPENED, FOUND REMAINS OF CLAMP IN T/R RT COWL. - CLAMP REPLACED WITHOUT FURTHER INCIDENT. 2 L 7 2 4F 4 F RT A35EU E23EA 2001051500412 20010515 00412 CE 2001 5 15 CA010510008 1 20010417 G 5541 04330106 SPAR CESSNA 04330101 CESSNA 150 152 2071835 CE LYC O235 O235L2C 41505 EA RUDDER CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 9133 (CAN) 4 CRACKS WERE FOUND ORIGINATING FROM A 1.0 INCH DIA. LIGHTENING HOLE, 1.50 INCH BELOW UPPER RUDDER HINGE BRACKET. NOTE: REPLACEMENT SPAR WITH THE SAME P/N FROM CESSNA DOES NOT HAVE THIS LIGHTENING HOLE. 1 H 7 1 3O 3 O NT 3A19 E223 2001051500413 20010515 00413 CE 2001 5 15 CA010510009 1 20010416 G 5510 04320049 BRACKET CESSNA 043200159 CESSNA 150 152 2071835 CE LYC O235 O235L2C 41505 EA HORIZONTAL STAB CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 9133 (CAN) 2 CRACKS FOUND AT WELDED EDGE.2 CRACKS FOUND AT ANCHOR NUT HOLE.1 CRACK WELD CRACKED. 1 CORNER NOT WELDED. 1 H 7 1 3O 3 O NT 3A19 E223 2001051500414 20010515 00414 CE 2001 5 15 CA010510010 1 20010417 G 2720 04115261 TORQUE TUBE CESSNA 150 152 2071835 CE LYC O235 O235L2C 41505 EA MCAULY 1A103 1A103TCM GL CABLE ARM CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) CRACK FOUND IN WELD FROM TORQUE TUBE TO CABLE ARM. CRACK WAS APPROXIMATELY 0.125 INCH LONG AT THE END OF WELD. 1 H 7 1 3O 3 O NT 3A19 E223 5 N P50GL 2001051500422 20010515 00422 NE 2001 5 15 CA010511002 2 20010330 G 7321 6078T55P18 FUEL CONTROL WOODWARD CNDAIR CL600 CL6002B19 EA GE CF34 CF343B1 NE RT ENGINE FAILED W E ENGINE SHUTDOWN J WARNING INDICATION CR CRUISE 1 CA 485 WYG99820 (CAN) CREW REPORTED THAT THEY HAD 3 UNCOMMANDED OVERSPEEDS OF RIGHT ENGINE N1 DURING FLT. 1ST 104.5 PERCENT N1 FOR 5.7 S EC ICAS N1 ICON TURNED RED. PILOT PULLED THROTTLE BACK & ENGINE DID NOT COME BACK FOR 3 TO 4 SEC. PILOT ADVANCED THROTTL E BACK TO CRUISE POWER & 2ND OVERSPEED HAPPENED. IT 103.3 PERCENT N1 FOR 6.1 SEC N1 ICON TURNED RED. THROTTLE PULLED BA CK & WITH 2 TO 3 2ND DELAY BEFORE ENGINE CAME BACK IN SPEED. N1 SPEED SWITCH TURNED OFF&ENGINE SPEED ADVANCED BACK TO CR UISE POWER. 3RD OVERSPEED THEN HAPPENED AT 99.1 PERCENT FOR 0.7 SEC. PILOT REDUCED THROTTLE & TURNED A/C BACK TO DEPTR A IRPORT.MAIN FUEL CNTL REPLACED & A/C RT-SRV.2001-05-11 TC: INVESTIGATING 2 L 7 2 4F 4 F RT A21EA E15NE 2001051500423 20010515 00423 EA 2001 5 15 CA010511005 1 20010419 G 5400 A33721 ROD CNDAIR CL600 CL6002B19 EA GE CF34 CF343B1 NE NACELLE DOOR LOOSE W A UNSCHED LANDING E VIBRATION/BUFFET CR CRUISE 1 CA (CAN) AIRCRAFT ENROUTE TO MONTERREY, THE CREW WERE UNABLE TO RETARD THE LEFT HAND THROTTLE LOWER THAN 95 PERCENT. THE CR EW RETURNED TO MEMPHIS AND CARRIED OUT QRH ABNORMAL 1-14. MECHANICS FOUND THE HOLD OPEN STRUT OF THE LT ENGINES UPPER C ORE COWL JAMMED BETWEEN THE FUEL CONTROL UNIT INPUT SHAFT AND THE COWLING. THE STRUT WAS REMOVED (DMI) AND THE AIRCRAFT RETURNED TO SERVICE.DURING THE PRELIMINARY INVESTIGATION THE BALL WITHIN THE PIN BLC38C11SL5C4 WAS FOUND TO BE MISSING. THE STRUT STOWING END, BRACKET 228-50182-585 AND THE CLIP 228-50583-101 WILL BE VERIFIED UPON INSTALLATION OF NEW ROD TO CONCLUDE THE INVESTIGATION. 2 L 7 2 4F 4 F RT A21EA E15NE 2001051500424 20010515 00424 EA 2001 5 15 CA010511008 1 20010419 G 2910 AE2460010H0264 LINE CNDAIR CL600 CL6002B19 EA GE CF34 CF343B1 NE HYD SYSTEM CHAFED W A UNSCHED LANDING K J FLUID LOSS WARNING INDICATION CL CLIMB 1 CA (CAN) UPON CLIMBING, CREW RECEIVED A HYDRAULIC NR 1 LOW PRESSURE MESSAGE, ASSOCIATED WITH A NR 1 SYSTEM, QUANTITY INDICA TING ZERO PERCENT. AIRCRAFT DIVERTED TO BIRMINGHAM. MAINTENANCE FOUND A CHAFED STEEL BRAIDE HYDRAULIC LINE IN AFT FUSE. THE LINE IS THE PESSURE LINE AT THE BULKHEAD. THE RUBBER HAD WORN OFF CLAMP P/N M85052-2-8. LINE REPLACE, ADP NR 1 REPLA CED, OPS CHECK GOOD, AIRCRAFT RETURNED TO SERVICE. 2 L 7 2 4F 4 F RT A21EA E15NE 2001051500425 20010515 00425 NE 2001 5 15 CA010511012 2 20010425 G 7260 GEAR CNDAIR CL600 CL6002B19 EA GE CF34 CF343B1 NE NR 2 ENGINE FAILED W E A ENGINE SHUTDOWN UNSCHED LANDING J WARNING INDICATION CR CRUISE 1 CA (CAN) NR 2 ENGINE OIL PRESSURE DROPPED TO APPROXIMATELY 18 PSI WITH LOW OIL PRESSURE WARNING. ENGINE SHUTDOWN PER QRH. N R 2 ENGINE REPLACED DUE TO GEAR MATERIAL ON THE CHIP DETECTOR. 2 L 7 2 4F 4 F RT A21EA E15NE 2001051500426 20010515 00426 EA 2001 5 15 CA010511014 1 20010426 G 5610 NP1393215 WINDSHIELD CNDAIR CL600 CL6002B19 EA GE CF34 CF343B1 NE COCKPIT CRACKED W O OTHER O OTHER AP APPROACH 1 CA (CAN) LT WINDSHIELD CRACKED DURING THE APPROACH. WINDSHIELD REPLACED AND RETURNED TO SERVICE. 2 L 7 2 4F 4 F RT A21EA E15NE 2001051500427 20010515 00427 EA 2001 5 15 CA010511016 1 20010426 G 5610 NP1393219 WINDSHIELD CNDAIR CL600 CL6002B19 EA GE CF34 CF343B1 NE COCKPIT FRACTURED W O OTHER O OTHER DE DESCENT 1 CA (CAN) CAPTAINS WINDSHIELD EXPERIENCED A PLY FRACTURE DURING DESCENT. WINDSHIELD REPLACE, AIRCRAFT RETURNED TO SERVICE. 2 L 7 2 4F 4 F RT A21EA E15NE 2001051500428 20010515 00428 EA 2001 5 15 CA010511018 1 20010429 G 7120 BEAM CNDAIR CL600 CL6002B19 EA GE CF34 CF343A1 30015 NE ENGINE SUPPORT CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) DURING C-CHECK SEVEN CRACKS WERE FOUND IN THE ENGINE SUPPORT BEAM. TWO CRACKS WERE LOCATED ON THE LOWER WEB AT FS 640.0 NAR LBL9.0. FIVE CRACKS WERE LOCATED ON THE UPPER WEB AT FS640.0 BETWEEN LBL9.0 AND RB122.0.REPAIR ONGOING IAW REO 601R-53-61-340. 2 L 7 2 4F 4 F RT A21EA E15NE 2001051500429 20010515 00429 EA 2001 5 15 CA010511019 1 20010429 G 5610 NP1393226 WINDOW CNDAIR CL600 CL6002B19 EA GE CF34 CF343A1 30015 NE COCKPIT CRACKED W O OTHER O OTHER LD LANDING 1 CA (CAN) ON LANDING COPILOTS SIDE WINDOW CRACKED.REPLACED COPILOTS SIDE WINDOW. AIRCRAFT RETURNED TO SERVICE. 2 L 7 2 4F 4 F RT A21EA E15NE 2001051500430 20010515 00430 EA 2001 5 15 CA010511020 1 20010429 G 7603 2100140007 GEARBOX CNDAIR CL600 CL6002B19 EA GE CF34 CF343B1 NE ENGINE CONTROLS FAILED W O OTHER O OTHER TX TAXI/GRND HDL 1 CA 3961 3217 (CAN) RIGHT ENGINE WILL NOT SHUT DOWN USING POWER LEVER.REPLACED THE THROTTLE CONTROL GEAR BOX ASSEMBLY. ENGINE RUNS CAR RIED OUT, NO FAULTS FOUND.AIRCRAFT RETURNED TO SERVICE. 2001-05-11 TC: REQUESTING DETAILED INFORMATION FROM ORIGINATOR. 2 L 7 2 4F 4 F RT A21EA E15NE 2001051500431 20010515 00431 EA 2001 5 15 CA010511021 1 20010429 G 7720 6030T40P01 HARNESS CNDAIR CL600 CL6002B19 EA GE CF34 CF343B1 NE ITT INDICATOR INOPERATIVE W C ABORTED TAKEOFF N FALSE WARNING TO TAKEOFF 1 CA (CAN) CREW ABORTED TAKEOFF DUE TO NR 2 ENGINE OVER TEMPERATURE. MAINTENANCE FOUND ITT THERMOCOUPLE HARNESS PARTIALLY INO PERATIVE. REPLACED HARNESS. NO FURTHER FAULTS FOUND. AIRCRAFT RETURNED TO SERVICE. 2 L 7 2 4F 4 F RT A21EA E15NE 2001051500432 20010515 00432 NE 2001 5 15 CA010511023 2 20010416 G 7230 BRR17740 BLADE RROYCE M33119 BOEING 717 717200 1383700 NM RROYCE BR700 BR700715A130 NE HP COMPRESSOR BROKEN W A UNSCHED LANDING E Y J VIBRATION/BUFFET ENGINE STOPPAGE WARNING INDICATION CL CLIMB 1 CA 2821 1797 (CAN) AIRTRAN A/C 702, NR 1 ENGINE S/N 13121 EXPERIENCED SHUTDOWN ON CLIMB OUT OF RALIEGH DURHAM AT 9,000 FT. ENGINE RPT EDLY MADE RMBLING NOISE&LOST POWER & RAN DOWN, ENGINE SUB-IDLE BEFORE SHUTDOWN, VIBRATION HIGH BUT NOT AMBER, SURGE LIGH T CAME ON. GROUND INSP REVEALED NO METAL IN TAIL PIPE&NO EVIDENCE OF EXTERNAL DAMAGE OR BIRDSTRIKE. WEATHER AT TIME OF EVENT CLEAR&SUNNY. ON GROUND, PRELIM GROUND-RUN PERFORMED&EVM ROSE TO 4.0 UNITS N2 BY 72% N2. PHYSICAL VIBRATION FELT,&R UN STOPPED. BORESCOPE PERFORMED&HP1 COMPRESSOR BLADE FOUND BROKEN OFF MID SPAN, PLUS EXCESSIVE HP1 COMPRESSOR DAMAGE. EN GINE CHANGE HAS BEEN CALLED FOR. DETAILS OF TROUBLE SHOOTING:ENGINE BORESCOPE PERFORMED IN RALIEGH DURHAM ON 16/04 2 L 7 2 4F 4 F TR A6WE E00061EN 2001061400002 20010614 00002 SO 2001 6 14 CA010511025 1 20010402 G 5712 SUPPORT PIPER PA28 PA28140 7102802 SO LYC O320 O320E2A 41508 EA BOLT ATTACHMENT CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) THE CRACK IS CAUSED BY THE ATTACHMENT OF THE SUPPORT ON THE EDGE WITH AN AN3-4A BOLT. 1 L 7 1 3O 3 O 2A13 E274 2001061400003 20010614 00003 EA 2001 6 14 CA010511026 1 20010421 G 7500 ACTUATOR CNDAIR CL604 CL604 EA GE CF34 CF343B1 NE BLEED AIR SYSTEM FAILED W K NONE M J OVER TEMP WARNING INDICATION IN INSP/MAINT 1 CA 2683 (CAN) OVERHEAT OF THE ACCUMULATOR, THE ELECTRIC WIING, LOWER ENGINE FAIRING AND THE LOWER CENTRAL PART OF THE NACELLE DU E TO DE-COUPLING OF THE COMPRESSED AIR INTAKE AND THE 10TH STAGE HOT AIR PORTION. THIS COUPLING IS IN A HARD TO READ ARE A AND IS HARD TO TIGHT AND HAS NO RETAINING WIRE. THIS IS THE 3RD INCIDENT THAT I NOTICE OF THIS SORT. 2 L 7 2 4F 4 F RT A21EA E15NE 2001061400004 20010614 00004 SW 2001 6 14 CA010511027 1 20010115 G 6220 HUB BELL 64A BELL 47 47G4A 1181031 SW LYC O540 VO540B1B3 41532 EA MAIN ROTOR CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 1543 192 CH116 (CAN) FOUND CRACKED IN THREADED AREA AFTER EDDY CURRENT INSPECTION WHILE CARRYING OUT AD, CF-1988-08R1. 1 G 7 1 3O 3 O 2H3 E304 2001061400010 20010614 00010 NM 2001 6 14 CA010515004 1 20010420 G 3240 ISOLATION VALVE BOEING 737 7372Q9 138448M NM PWA JT8 JT8D9A 52048 NE MLG LEAKING W D RETURN TO BLOCK K FLUID LOSS TX TAXI/GRND HDL 1 CA 1731 0575 (CAN) AIRCRAFT LOST A SYSTEM HYDRAULIC FLUID UPON TAXIING TO THE TERMINAL. CREW HAD TO USE DIFFERENTIAL BRAKING TO GET T O GATE. AFTER INVESTIGATION IT WAS DETERMINED THAT THE MAIN GEAR ISOLATION VALVE P/N 65-44581-6, S/N 0575 WAS LEAKING. 2 L 7 2 4F 4 F A16WE E2EA 2001061400011 20010614 00011 EA 2001 6 14 CA010515005 1 20010410 G 3510 RHEOSTAT DHAV DHC6 DHC6300 2802606 EA PWA PT6 PT6A27 52043 EA COCKPIT OVERHEATED W H A DEACTIVATE SYST/CIRCUITS UNSCHED LANDING B SMOKE/FUMES/ODORS/SPARKS CR CRUISE 1 CA 9250 9250 (CAN) OXYGEN REGULATOR IN COPILOT POSITION WAS REPLACED WITH OVERHAULED UNIT. INTERNAL LIGHTING WIRES FOR THIS UNIT WERE CONNECTED IMPROPERLY (POLARITY REVERSED).AS A RESULT THE RHEOSTAT WHICH CONTROLS LIGHT INTENSITY FOR THE COPILOTS INSTR UMENT LIGHTING WAS SHORTED TO GROUND. THE 5 AMP CIRCUIT BREAKER THAT PROTECTS THIS LIGHTING RHEOSTAT DID NOT POP AND CAU SED THIS RHEOSTAT (RATED AT 2.7 AMPS MAX .7 MIN.) TO OVERHEAT AND CAUSE SOME SMOKE IN THE COCKPIT AREA. 1 H 7 2 3T 4 T RT A9EA E4EA 2001061400012 20010614 00012 EU 2001 6 14 CA010515008 1 20010419 G 2910 SOLENOID VALVE BOLKMS 105 BO105C 5626005 EU ALLSN 250C 250C20B 03013 GL HYD SYSTEM FAILED W K NONE J WARNING INDICATION IN INSP/MAINT 1 CA (CAN) HYD BLOCK LIGHT CAME ON IN FLIGHT. PILOT RETURNED TO BASE AND CALLED OUT RESCUE CREW. LANDED WITHOUT DIFFICULTY. S OLENOID VALVE REPLACED AND AIRCRAFT RETURNED TO SERVICE ON APRIL 20. AIRCRAFT TEST FLOWN FOR 30 MINUTES AND NO FURTHER L IGHT REPORTS. 1 G 7 2 3U 3 U H3EU E4CE 2001061400013 20010614 00013 SW 2001 6 14 CA010515009 1 20010327 G 6700 TUBE BELL 206 206B 1181511 SW ALLSN 250C 250C20B 03013 GL TRANSMISSION CHAFED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) TUBE ASSY (XMSN) FOUND CHAFED IN VERTICAL TUNNEL. ONE OF THE CONTROL TUBES CHAFED THE TUBE WITH EVERY CONTROLLED I NPUT. TUBE ASSY REPLACED. 1 G 7 1 3U 3 U H2SW E4CE 2001061400014 20010614 00014 SW 2001 6 14 CA010515010 1 20010327 G 6510 BEARING BELL 206 206B 1181511 SW ALLSN 250C 250C20B 03013 GL T/R DRIVESHAFT CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) 2 TAIL ROTOR DRIVESHAFT BEARINGS HAVE GREASE HOUSINGS CRACKED. BOTH BEARINGS ROUGH, EXCESSIVE GREASE SQUEEZE OUT. BOTH BEARINGS REPLACED. 1 G 7 1 3U 3 U H2SW E4CE 2001061400015 20010614 00015 EU 2001 6 14 CA010515011 1 20010413 G 6310 ENGINE SNIAS 350 AS350BA 8680817 EU TMECA ARRIEL ARRIEL1B 6OO30 NE NACELLE FAILED W K NONE O OTHER IN INSP/MAINT 1 CA 6349 1876 878 (CAN) AIRCRAFT LANDED AND SHUTDOWN. AFTER APPROXIMATELY 10 MIN WHEN ATTEMPTING A RESTART AT APPROXIMATELY 15 PERCENT NG AND T4 -400 DEGREES C A LOUD RINGING NOISE WAS HEARD FROM THE ENGINE COMPARTMENT AND START STALLED - START WAS ABORTED. AFTER SOME TROUBLESHOOTING THE ENGINE WAS REMOVED AND RETURNED TO THE MANUFACTURER FOR FURTHER EVALUATION. 1 G 7 1 3U 3 U NC H9EU E19EU 2001061400016 20010614 00016 2001 6 14 CA010515013 4 20010412 G 2312 POWERPACK NARCO 661 GRUMAV TBM TBM3EAIRTRD 3950310 EA WRIGHT R2600 R260020 67050 EA HAMSTD 23E 23E50 NE VHF COMM BURNED W A UNSCHED LANDING B SMOKE/FUMES/ODORS/SPARKS CR CRUISE 1 CA (CAN) SHORTLY AFTER TAKEOFF THE PILOT DETECTED THE SMELL OF SMOKE IN THE COCKPIT. HE ELECTED TO RETURN TO Fredericton AI RPORT AND DID A NORDO APPROACH AND LANDED SAFELY. MAINTENANCE FOUND THAT THE POWERPACK RESISTOR HAD BURNED AND THEREBY C UTOUT NR 1 RADIO. THE BURNED MP-10 POWER PACK RESISTOR WAS CAUSED BY A FAILED VOLTAGE REGULATOR (BENDIX P/N TYPE 1589) W HICH RESULTED IN AN UNCONTROLLED VOLTAGE SITUATION. 1 L 7 1 4R 4 R L82 TC176 6 C P603 2001061400017 20010614 00017 CE 2001 6 14 CA010515014 1 20010404 G 6310 ENGINE BEECH 1900 1900C 1154161 CE PWA PT6 PT6A65B 52043 EA R GEARBOX FAILED W K NONE O OTHER IN INSP/MAINT 1 CA 25153 1475 (CAN) ENGINE SPOOL DOWN NOTED TO BE VERY SHORT HIGH RESISTANCE TO TURNING REDUCTION GEAR BOX THROUGH PROP BLADES AND INT ERNAL RUBBING DETECTED INDICATING INTERNAL PROBLEMS. - CAUSE TO BE DETERMINED UPON ENGINE TEAR DOWN. - ENGINE WAS INVOLV ED IN A PROP STRIKE 10 DAYS (64 FLIGHT HOURS) EARLIER AND HAD JUST BEEN RETURNED TO REGULAR MAINTENANCE INTERVALS AFTER COMPLETING THE REQUIRED INCREASED INSPECTIONS REQUIRED BY THE ENGINE MANUFACTURER. - ENGINE TEAR DOWN SHOULD INDICATE TH AT THE PROP STRIKE WAS THE CAUSE. 2 L 7 2 4T 4 T RT A24CE E4EA 2001061400018 20010614 00018 EU 2001 6 14 CA010518002 1 20010126 G 6210 BLADE SNIAS 350 AS350B2 8680813 EU MAIN ROTOR CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 2100 (CAN) DURING ROUTINE DAILY INSPECTION, MAIN ROTOR BLADE WAS FOUND TO HAVE TWO CRACKS ON THE UPPER SKIN AT STA 1177 AND S TA 1182, RUNNING IN A CORD WISE DIRECTION. UPON REMOVED OF PART AND FURTHER INSPECTION, IT WAS DETERMINED THAT BLADE WAS NOT REPAIRABLE AS PER EUROCOPTER INSTRUCTION. 1 G 7 1 3U H9EU 2001061400020 20010614 00020 EU 2001 6 14 CA010518003 1 20010430 G 2822 PUMP SNIAS 350 AS350B2 8680813 EU TMECA ARRIEL ARRIEL1D NE FUEL BOOST FAILED W K NONE O OTHER IN INSP/MAINT 1 CA 216 23455 (CAN) NR 2 FUEL BOOST PUMP WAS FOUND TO BE EXCESSIVELY NOISY DURING POST FLIGHT INSPECTION. PUMP WAS REMOVED FOR REPAIR AS THIS NOISE IS A SIGN OF IMPENDING FAILURE. REPLACEMENT PUMP INSTALLED. 1 G 7 1 3U 3 U H9EU E19EU 2001061400027 20010614 00027 EU 2001 6 14 CA010518009 1 20010326 G 2822 PUMP SNIAS 350 AS350BA 8680817 EU TMECA ARRIEL ARRIEL1B 6OO30 NE FUEL BOOST INTERMITTENT W O OTHER J WARNING INDICATION AP APPROACH 1 CA 670 (CAN) PILOT NOTED FUEL PRESSURE INTERMITTENT/FLUCTUATING, NORMAL LANDING WAS CARRIED OUT. FUEL PUMP WAS REPLACED TO CORR ECT PROBLEM. 1 G 7 1 3U 3 U NC H9EU E19EU 2001073000006 20010730 00006 2001 7 30 CA010518010 4 20010503 G 6113 PLATE MOONEY SA8659SW MOONEY M20 M20F 5870214 SW LYC O360 IO360A1A 41514 EA HARTZL HCC2Y HCC2YK1 GL SPINNER CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 100 (CAN) CRACK & FAILURE OF FLANGE OF BACKING PLATE THAT HAS BLADE ROOT CLOSING FAIRING ATTACHED.A PORTION OF FAIRING REMAI NED ATTACHED TO SPINNER WHICH SEVERELY DAMAGED NOSE BOWL FAIING LEAVING BACKING PLATE&FAIRING DEBRIS INSIDE ENGINE COWL. THERE WAS SOME MINOR DAMAGE TO PROP BLADES ABOUT FOOT FROM ROOT. SPINNER REMAINED ATTACHED&SECURE: CRACK APPEARED TO BEG IN NEAR FWD EDGE OF FLANGE OF BOTH BACKING PLATE&FAIRING ATTACHMENT. PERHAPS ABOUT 1/2 INCH&REST OF FAILURE APPEARED TO HAVE BEEN EXTREMELY RAPID. 1 L 7 1 3O 3 O 2A3 1E10 5 C P920 2001061400033 20010614 00033 2001 6 14 CA010522010 4 20010427 G 2213 CONTROL CABLE DHAV DHC8 DHC8311 1386006 EA PWA PW120 PW123 NE HAMSTD 14SF 14SF15 NE AILERON FRAYED W K NONE O OTHER IN INSP/MAINT 1 CA 22429 (CAN) THE FLIGHT CREW REPORTED THAT THE ROLL CONTROL FELT HEAVIER THAN STANDARD FOR TYPE. MAINTENANCE INVESTIGATION REVE ALED THAT THE R/H UPPER AILERON CONTROL CABLE WAS FRAYED AT THE STEEL PULLEY, WING STATION YW 256.0, JUST OUTBOARD OF TH E ENGINE NACELLE. THE CABLE WAS REPLACED AND THE AIRCRAFT WAS RETURNED TO SERVICE. TTAF 22,429 HOURS, TCAF 33,043. 2 H 7 2 4T 4 T RT A13NM E20NE 6 C P7NE 2001061400034 20010614 00034 EU 2001 6 14 CA010522011 1 20010429 G 3200 PROXIMITY SENSOR BAG BAE146 BAE146200A 1500266 EU LYC ALF502 ALF502R5 41580 NE MLG FAILED W O OTHER N FALSE WARNING TX TAXI/GRND HDL 1 CA 15239 13602 (CAN) THE FLIGHT CREW REPORTED THE L/H RED "GEAR UNSAFE" LIGHT ILLUMINATED ACCOMPANIED BY GEAR HORN, STICK SHAKER, AND M ANUAL SPOILER FAULT WHILE AT THE GATE AFTER SWITCHING FROM GROUND POWER TO APU. MAINTENANCE INVESTIGATION REVEALED AN OP EN CIRCUIT IN THE L/H MAIN GEAR SIDESTAY PROXIMITY SENSOR. THE SIDESTAY ASSEMBLY WAS REPLACED AND THE AIRCRAFT WAS RETUR NED TO SERVICE. 2 H 7 4 4F 4 F RT A49EU E6NE 2001061400035 20010614 00035 NM 2001 6 14 CA010522013 1 20010506 G 2420 CONNECTOR DHAV DHC8 DHC8102 2809003 NM PWA 120 PW120A NE HAMSTD 14SF 14SF7 NE NR 2 GENERATOR LEAKING W C ABORTED TAKEOFF J WARNING INDICATION TO TAKEOFF 1 CA 6070 161 (CAN) THE FLIGHT CREW REPORTED ILLUMINATION OF THE NR 2 A/C. GENERATOR LIGHT ON TAKEOFF. AN UNSCHEDULED LANDING WAS AC COMPLISHED AND THE GENERATOR WAS REPLACED. OIL WAS FOUND IN THE MAIN ELECTRICAL CONNECTOR OF THE UNSERVICEABLE GENERATOR . THIS UNIT HAD BEEN REPAIRED 161 HOURS PREVIOUS TO THIS OCCURRENCE. 2 H 7 2 4T 4 T RT A13NM E20NE 6 C P7NE 2001061400036 20010614 00036 NE 2001 6 14 CA010522016 1 20010501 G 6220 PLATE SKRSKY S61102000304 SKRSKY S61 S61N 8142104 NE GE CT58 CT581401 30011 NE MAIN ROTOR HEAD CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 14100 1508 A9835 (CAN) ON POST FLIGHT INSPECTION A CRACK WAS FOUND EXTENDING UPWARD FROM BIFILAR ATTACH BOLT HOLE ON MAIN ROTOR HUB UPPER PLATE. MAIN ROTOR HEAD REMOVED FROM SERVICE. ON DISASSEMBLY, SHIM CHECK WAS CARRIED AS PER SB 61B10-46, AND FOUND TO BE WITHIN ACCEPTABLE TOLERANCE. NO NOTABLE CORROSION WAS FOUND IN THE PLATE BOLT. SIKORSKY HAS BEEN NOTIFIED. 2 G 7 2 4U 4 U 1H15 1E3 2001061400038 20010614 00038 CE 2001 6 14 CA010522019 1 20010508 G 7721 CYLINDER CESSNA 172 172 2072402 CE CONT O300 O300B 17022 SO NR 1 SEPARATED W O OTHER O OTHER AP APPROACH 1 CA 2103 (CAN) NR 1 CYLINDER BARREL BROKE LEAVING CYLINDER BAS ATTACHED TO CRANKCASE AND CYLINDER ATACHED BY EXHAUST AND INTAKE. APPROXIMATELY 1" OF CYLINDER IS STILL ATTACHED TO CRANKCASE. PISTON AND CONNECTING ROD ARE DESTROYED. BOTH CASE HAVES AN D REAR CASE IS DESTROYED. A SUCCESSFUL FORCED LANDING WAS MADE AT PRINCE GEORGE AIRPORT. 1 H 7 1 3O 3 O NT 3A12 E253 2001061400040 20010614 00040 SW 2001 6 14 CA010522025 1 20010501 G 3210 CROSSTUBE BELL 212 212 1181420 SW PWA PT6T PT6T3 52045 EA MLG BROKEN W O OTHER O OTHER LD LANDING 1 CA (CAN) HELICOPTER WAS ON A HELI SKIING JOB. THE JOB DESCRIPTION IS LOW HOURS BUT LOTS OF LANDINGS IN SNOW. THE PILOT HAD A RATHER ABRUPT LANDING ON ONE OF THE LANDING SITES (NOT HARD BUT NOT SMOOTH). AT THE NEXT LANDING THE PILOT HEARD A LOU D BANG AND IT WAS NOTED THAT THE SKID TUBE ON THE LEFT SIDE OF THE AIRCRAFT WAS NO LONGER PARALLEL WITH THE AIRCRAFT, TH E SKID TUBE WAS DETACHED FROM THE REAR CROSS TUBE BUT STILL ATTACHED TO THE FRONT CROSS TUBE, A CRIB OR SUPPORT WAS BUIL T TO ALLOW THE AIRCRAFT TO LAND AND SHUT DOWN WITH NO INCIDENT. THE HELICOPTER HAD BROKEN THE LOW AFT CROSS TUBE NEAR TH E SKID TUBE ATTACHMENT SADDLE ON THE LEFT SIDE. 1 G 7 1 4U 4 U H4SW E22EA 2001061400042 20010614 00042 SW 2001 6 14 CA010523004 1 20010410 G 3040 WINDSHIELD FRCHLD SA227 SA227DC 3377521 SW GARRTT TPE331 TPE33112UHR WP MCAULY 4HFR34 4HFR34C652 NE COCKPIT CRACKED W O OTHER O OTHER CR CRUISE 1 CA 1790 (CAN) DURING CRUISE FLIGHT AT 24,000 FEET, WITH CABIN PRESSURE APPROXIMATELY 6 PSI, THE LT WINDSHIELD OUTER PANEL CRACKE D. THE CREW ELECTED TO DIVERT TO THE NEAREST AIRFIELD, REDUCE ALTITUDE TO 10,000 FEET, AND DEPRESSURIZE THE CABIN AS A P RECAUTION.IT WAS NOTED THAT THE FAIRCHILD 227 FLIGHT MANUAL DOES NOT GIVE ANY DIRECTIVES FOR ACTION IN THE CASE OF A CRA CKED WINDSHIELD, THEREFORE THE CREW TOOK ACTION BASED ON EXPERIENCE ON OTHER SIMILAR TYPES OF AIRCRAFT.FAIRCHILD WILL BE CONTACTED TO REQUEST AN AMENDMENT TO THE FLIGHT MANUAL PROCEEDURES SECTION TO COVER THIS SITUATION. 2 L 7 2 4T 4 T RT A18SW E4WE 6 C 3PNE 2001061400043 20010614 00043 CE 2001 6 14 CA010523006 1 20010514 G 1100 PLACARD CESSNA 206 U206F 2073333 CE CONT O520 IO520F 17032 SO COCKPIT REVERSED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) THE DECAL ON THE ELEVATOR TRIM WHEEL APPEARS TO HAVE BEEN FABRICATED. WHEN IT WAS INSTALLED, THE "NOSE UP" AND "NO SE DOWN" DECALS WERE REVERSED. WHEN THE PILOT THOUGHT HE WAS TRIMMING THE NOSE DOWN, HE WAS ACTUALLY TRIMMING IT UP. THE LOCATION OF THE DECALS WAS CORRECTED. 1 H 7 1 3O 3 O A4CE E5CE 2001072600023 20010726 00023 EU 2001 7 26 CA010523010 1 20010502 G 2913 704A33690004 BELT SNIAS 350 AS350BA 8680817 EU TMECA ARRIEL ARRIEL1B 6OO30 NE HYD PUMP FAILED W A UNSCHED LANDING J F WARNING INDICATION FLT CONT AFFECTED CR CRUISE 1 CA 190 (CAN) WHILE IN CRUISE FLIGHT THE PILOT LOST HYDRAULIC PRESSURE. SLOWED THE A/C AND LANDED. HYDRAULIC PUMP BELT BROKEN. 1 G 7 1 3U 3 U NC H9EU E19EU 2001073000007 20010730 00007 EU 2001 7 30 CA010523011 1 20010430 G 6320 1171206301 BEVEL GEAR KAWSKI 1171201001 BOLKMS 117 BK117B1 5626012 EU LYC LTS101 LTS101750B1 41560 NE TRANSMISSION MAKING METAL W K NONE J WARNING INDICATION IN INSP/MAINT 1 CA 3733 KA0225 (CAN) MINOR "PEPPER" METAL, SHINY, WITHIN OPERATIONAL LIMITS WOULD OCCASIONALLY ACTIVATE OR FLICKER CAUTION LIGHT."PEPPE R" FOUND IN BOTH FILTERS, MAINLY NR 1 SIDE. REMOVAL OF INSPECTION COVER REVEALED DEGENERATION OF SURACE OF BEVEL GEAR. 1 G 7 2 3U 3 U H13EU E5NE10 2001073000008 20010730 00008 SO 2001 7 30 CA010523012 1 20010420 G 5320 1712124 CHANNEL PIPER PA23 PA23 7102302 SO FUSELAGE CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 4221 (CAN) DURING ANNUAL 100 HOUR INSPECTION OF THE TAIL AREA, NOTICED THAT THE CHANNEL THAT SUPPORTS THE LOWER RUDDER SUPPOR T AND RUDDER STOP BRACKET WAS CRACKED. THIS WAS THE RESULT OF THE RUDDER BEING FORCED HARD AGAINST THE RUDDER STOPS BY W IND. 1 L 7 2 3O 1A10 2001073000009 20010730 00009 SO 2001 7 30 CA010523013 1 20010420 G 3220 1904600 DRAG LINK PIPER PA23 PA23 7102302 SO NLG BROKEN W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) DURING ANNUAL 100 HOUR INSPECTION FOUND NOSE GEAR LOWER DRAG LINK BROKEN IN THE DOWN LOCK AREA. 1 L 7 2 3O 1A10 2001072600024 20010726 00024 WP 2001 7 26 CA010523015 1 20010426 G 6210 369D21100517 BLADE HUGHES 369 369D 4470706 WP ALLSN 250C 250C20B 03013 GL MAIN ROTOR DAMAGED W O OTHER O OTHER IN INSP/MAINT 1 CA 2111 (CAN) DURING HIS DI, THE PILOT NOTICED ADHESIVE MISSING FROM ONE MAIN ROTOR BLADE ROOT FITTING. MAINTENANCE WAS ADVISED. THE BLADE WAS REMOVED AND CHECKED AS PER DN188. THE ROOT FITTING FAILED THAT INSPECTION. THE REST OF THE BLADES WERE AL SO INSPECTED AND FOUND SERVICEABLE. THE BLADE WAS RETURNED TO THE MANUFACTURER. A SERVICEABLE BLADE WAS INSTALLED AND TH E AIRCRAFT RETURNED TO SERVICE. 1 G 7 1 3U 3 U H3WE E4CE 2001073000011 20010730 00011 SO 2001 7 30 CA010523017 1 20010427 G 3230 455180 RELEASE CABLE PIPER PA30 PA30 7103002 SO LYC O320 IO320B1A 41508 EA MLG STIFF W O OTHER J WARNING INDICATION CL CLIMB 1 CA (CAN) - LANDING GEAR FAILED TO RETRACT ON CLIMB OUT & BREAKERS POPPED.- GEAR FAILED TO EXTEND WHEN BREAKER RESET & SELEC TED DOWN, NO GREEN LIGHT TO INDICATE GEAR DOWN AND LOCKED.- PILOT COULD NOT RELEASE EMERGENCY GEAR EXTENSION HANDLE.- RT GEAR COLLAPSED ON ROLL OUT. - TELEFLEX CABLES FOUND TO BE VERY STIFF IN CONDUIT/SLEEVE, LUBRICATION FREED UP ACTION CON SIDERABLY. 1 L 7 2 3O 3 O A1EA 1E12 2001072600026 20010726 00026 GL 2001 7 26 CA010523019 2 20010329 G 7230 6890550 COMPRESSOR BELL 206 206B 1181511 SW ALLSN 250C 250C20B 03013 GL ENGINE FAILED W O OTHER O OTHER TX TAXI/GRND HDL 1 CA (CAN) THE COMPRESSOR WAS FRESHLY OVERHAUL WITH A TSO OF 1.1, CSO .3 AIRCRAFT FAILED TO START. PROBLEM FOUND TO BE COMPRE SSOR LOCKED UP. MANUFACTURE CALLED AND INDICATED PROBLEM TO BE POSSIBLE REAR BEARING DIFFUSOR DUE TO THE TIGHT TOLERANCE S. 1 G 7 1 3U 3 U H2SW E4CE 2001072600030 20010726 00030 WP 2001 7 26 CA010523020 1 20010424 G 5511 369D23623 SPAR HUGHES 369 369D 4470706 WP ALLSN 250C 250C20B 03013 GL HORIZONTAL STAB CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 5657 (CAN) UPON SHOP REPAIR OF THIS STABILIZER FOR SKIN CRACKS, DOUBLER CRACKS AND LOOSE RIVETS. IT WAS OBSERVED, THAT THE AF T SPAR IS CRACKED ALMOST ALL THE WAY THROUGH, 2.5 INCHES FROM THE INBOARD END. WE ALSO SUSPECT ANOTHER CRACK AT ANOTHER LOCATION ON THE SAME SPAR, BUT HAVE NOT CONFIRMED IT. THESE STABILIZERS HAVE JUST HAD THEIR RETIREMENT LIFE EXTENDED. TH IS STABILIZER HAS BEEN REMOVED FROM SERVICE. 1 G 7 1 3U 3 U H3WE E4CE 2001073000012 20010730 00012 EA 2001 7 30 CA010523024 2 20010427 G 7414 66M19385 CLAMP BENDIX 1068291018 PIPER PA31 PA31350 7103110 SO LYC O540 TIO540J2BD 41532 EA MAGNETO WORN W K NONE O OTHER IN INSP/MAINT 1 CA 207 825199 (CAN) DURING A ROUTINE INSPECTION, IT WAS NOTED THAT EXCESSIVE OIL WAS LEAKING AROUND THE MAGNETO GASKET. UPON REMOVAL O F THE MAGNETO, IT WAS NOTED THAT THE MAGNETO HAD ABNORMAL AMOUNT OF WEAR IN THE MAGNETO CLAMP AREA. FURTHER INVESTIGATIO N REVEALED ONE OF THE HOLD DOWN CLAMPS WAS GROUND AWAY IN THE FACE CONTACT AREA, RESULTING IN THE MAGNETO HANGING ON THE CASE BY ONE CLAMP. BOTH THE MAGNETO AND CLAMPS WERE REMOVED AND SENT TO THE OVERHAUL FACILITY FOR REPLACEMENT. 1 L 7 2 3O 3 O A20SO E14EA 2001073000013 20010730 00013 EA 2001 7 30 CA010523030 1 20010425 G 2760 3310961 BELLCRANK SCWZER SG2 SGS233A 8051606 EA DRAG CONTROL CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 4155 (CAN) AN INSPECTION WAS CALLED FOR AS INSRUCTED IN A SPECIAL INSPECTION DND C-12-382-000/NS-016. UPON INSPECTION OF SUBJ ECT PART, IT WAS DETERMINED THAT THE PART HAD REJECTABLE INDICATIONS. SUBJECT PART WAS SENT FOR REPAIRS AND RETURNED TO SERVICE. FURTHER INSTRUCTION PENDING QUALITY ENGINEERING TEST ESTABLISHMENT FINDINGS. 1 K 0 0 G2EA 2001073000014 20010730 00014 EA 2001 7 30 CA010523031 1 20010425 G 2760 3313661 BELLCRANK SCWZER SG2 SGS233A 8051606 EA DRAG CONTROL CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 2897 (CAN) AN INSPECTION WAS CALLED FOR AS INSTRUCTED IN A SPECIAL INSPECTION DND C-12-382-000/NS-016. UPON INSPECTION OF SUB JECT PART, IT WAS DETERMINED THAT THE PART HAD REJECTABLE INDICATIONS. SUBJECT PART WAS SENT FOR REPAIRS AND ETURNED TO SERVICE. FURTHER INSTRUCTION PENDING QUALITY ENGINEERING TEST ESTABLISHMENT FINDINGS. 1 K 0 0 G2EA 2001073000015 20010730 00015 EA 2001 7 30 CA010523032 1 20010425 G 2760 3310961 BELLCRANK SCWZER SG2 SGS233A 8051606 EA DRAG CONTROL CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 3142 (CAN) AN INSPECTION WAS CALLED FOR AS INSTRUCTED IN A SPECIAL INSPECTION DND C-12-382-000/NS-016. UPON INSPECTION OF SUB JECT PART, IT WAS DETERMINED THAT THE PART HAD REJECTABLE INDICATIONS. SUBJECT PART WAS SENT FOR REPAIRS AND RETURNED TO SERVICE. FURTHER INSTRUCTION PENDING QUALITY ENGINEERING TEST ESTABLISHMENT FINDINGS. 1 K 0 0 G2EA 2001073000019 20010730 00019 EA 2001 7 30 CA010529003 1 20010505 G 2910 C3CF6139 LINE DHAV DHC3 DHC3 2800202 EA PWA PT6 PT6A34 52043 EA HARTZL HCB3T HCB3TN3 GL HYD SYSTEM BROKEN W O OTHER K FLUID LOSS LD LANDING 1 CA (CAN) ON LANDING THE PILOT PUMPED THE FLAPS DOWN, WHEN THE FLAPS REACHED THE DOWN POSITION THE HYDRAULIC LINE TO THE FLA P SELECTOR BROKE, LEAKING HYDRAULIC FLUID ON TO THE FLOOR. THE PILOT LANDED THE AIRCRAFT WITHOUT INCIDENT. UPON INVESTIG ATION THE AME FOUND THAT THE HYDRAULIC LINE FROM THE HYDRAULIC FILTER TO THE FLAP SELECTOR HAD BROKEN OFF AT THE SELECTO R. SUSPECT THAT THE PROBLEM WAS THAT THE HYDR AULIC LINE NUT WAS OVERTORQUED AT ONE TIME WHICH CAUSED THE FLAIR TO EVENT FULLY BREAK OFF. THE LINE WAS REPAIRED AND THE AIRCRAFT RETURNED TO SERVICE.. . 1 H 7 1 3R 4 T A815 E4EA 6 C P15EA 2001073000020 20010730 00020 EU 2001 7 30 CA010529004 1 20010507 G 2822 MS345613273P CONNECTOR BRAERO 748 HS7482A 4231001 EU RROYCE DART DART5342 EU ROTOL R4304 R2124304 EU FUEL PRESS SYS SHORTED W O OTHER J WARNING INDICATION CR CRUISE 1 CA 664 (CAN) THE PORT FUEL PRESSURE WARNING LIGHT WAS INITY RPTED FLICKERING IN FLT, LATER CAME ON STEADY. LIGHT REMAINED ON WH EN CREW SELECTED POWER OFF DURING POST FLT SHUTDOWN ON RAMP.INVEST. REVEALED THAT PORT FWD WING ROOT BREAK CONNECTOR PL3 HAD DEVELOPED AN INTERNAL SHORT BETWEEN PINS 4, 5 & 24 (NOTE: THIS A/C HAS AERO CONSULTING SRVCS "CONNECTOR MOD" NOC38 550 INCORPORATED). THIS ALLOWED 24 VDC PORT BATTERY BUS BAR C/B 5 (5 AMP) THROUGH PIN 24 TO FEED PINS 4 & 5 (PORT FUEL L OW PRESSURE SWITCH/WARNING LIGHT CCT) PIN 5 BEING F103 (3 AMP) CENTRE BUSS BAR NORMAL FEED TO PORT FUEL LOW PRESSURE SWI TCH & PIN 4 BIENG LOAD SIDE OF PORT FUEL LOW PRESSURE SWITCH ALSO CONNECTED TO PORT LOW FUEL PRESSURE IND. LIGHT. PL3 W 2 L 7 2 3T 4 T A24EU A196 6 C P899 2001070500005 20010705 00005 EU 2001 7 5 CA010529005 1 20010429 G 2421 740119G IDG AIRBUS 320 A320212 EU CFMINT CFM56 CFM565A3 NE IDG OVERSERVICED W A UNSCHED LANDING H ELECT. POWER LOSS-50 PC CL CLIMB 1 CA 1970 (CAN) 35,000 CLIMBING - LOSS GEN #2 LOSS GEN #2 AND AC #2 RETURNED TO AIRPORT FOUND IDG (INTERGRATED DRIVE GENERATOR) #2 OVERSERVICED.IDG #2 REPLACED. . LEAK CHECKED AND OPS CHECKED SERVICEABLE. ALL BUS TRANSFERS NORMAL, SERVICEABLE.. .. . . . 2 L 7 2 4F 4 F RT A28NM E29NE 2001073000021 20010730 00021 EU 2001 7 30 CA010529006 1 20010426 G 2910 S43500272 MANIFOLD AIRBUS 320 A320232 3930326 EU IAE V2527 V2527A5 NE HYD SYSTEM LEAKING W H DEACTIVATE SYST/CIRCUITS K FLUID LOSS DE DESCENT 1 CA 23300 1588 (CAN) YELLOW SYSTEM LOW LEVEL ECAM ON DESCENT INTO YYC - MAJOR HYDRAULIC LEAK EVIDENT AT BLOCK IN ON RAMP. FOUND YELLOW LEAK MEASUREMENT MANIFOLD LEAKING. REPLACED HYDRAULIC LEAK MEASUREMENT MANIFOLD. SYSTEM CHECKS SERVICEABLE IAW 29-19-41- 401.. . . . 2 L 7 2 4F 4 F RT A28NM E40NE 2001073000036 20010730 00036 NE 2001 7 30 CA010529007 2 20010327 G 8550 12345 TUBE NAMER T6 HARVARDMK4 1922828 GL PWA R1340 S3H1 52016 NE HAMSTD 12D 12D40 NE OIL TRANSFER BENT W K NONE O OTHER IN INSP/MAINT 1 CA 378 (CAN) ENGINE SUMP WAS REQD TO BE REMVD FROM ENGINE TO FACILITATE CYLINDER REMOVAL. UPON REMOVAL OF SUMP, IT WAS DISCOVER ED THAT DAMAGE HAD OCCURRED TO OIL TRANSFER TUBES FROM SUMP TO CRANKCASE. THIS HAD BEEN CAUSED BY IMPROPER ASSY OF ENGIN E AT AN EARLIER REPAIR. 1 L 7 1 3R 3 R EXPA1L71 E143 5 C P257 2001073000038 20010730 00038 GL 2001 7 30 CA010529009 1 20010327 G 5741 ATTACH FITTING NAMER T6 HARVARDMK4 1922828 GL WING IMPROPER PART W K NONE W INADEQUATE Q C IN INSP/MAINT 1 CA 8496 (CAN) OUTER WING ATTACHMENT HARDWARE CONSISTS OF 224 NUTS AND BOLTS FOR BOTH WINGS. APPROXIMATELY 40% OF THE NUTS USEDWE RE OF A TYPE USED IN SHEAR APPLICATIONS (NAS679). CORRECT HARDWARE SHOULD HAVE BEEN AN365-428 AND AN365-524 NUTS AS CALL ED FOR IN THE HARVARD PART LIST. HARDWARE WAS REPLACED AS REQUIRED. 1 L 7 1 3R EXPA1L71 2001073000041 20010730 00041 GL 2001 7 30 CA010529010 1 20010327 G 5522 662200110 SKIN NAMER T6 HARVARDMK4 1922828 GL ELEVATOR MISREPAIRED W K NONE O OTHER IN INSP/MAINT 1 CA 84960 (CAN) ELEVATOR COVERING WAS OBSERVED DURING NORMAL INSPECTION TO HAVE CRACKING OF THE DOPE FINISH. FURTHER INVESTIGATION DISCOVERED BODY FILLER BETWEEN TWO SEPARATE DOPING AND PAINTING PROCESSES. UPON REMOVAL OF ELEVATOR, THE BALANCE CHECK CONFIRMED AN EXTREME TAIL HEAVINESS (IN EXCESS OF TWO POUNDS BEYOND ALLOWABLE LIMITS) OF BOTH ELEVATORS. ELEVATORS WERE REPLACED WITH SERVICEABLE SPARES. . . 1 L 7 1 3R EXPA1L71 2001073000045 20010730 00045 EU 2001 7 30 CA010529013 1 20010515 G 5532 202473 SKIN PILATS PC12 PC1245 EU PWA PT6 PT6A67B 52043 NE HARTZL HCE4A HCE4A3D GL VERTICAL STAB CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 4528 4528 (CAN) SMOKING WAS NOTICED AT THE ETOP R/H VERTICAL STAB SKIN. FURTHER INSPECTION REVEALED THAT THE REPAIR PATCH PREVIOUS LY INSTALLED IAW PILATUS TECH MEMO EC-12-TM-540 WAS CRACKED AT APPROXIMATELY THE SAME LOCATION AS THE ORIGINAL SKIN CRAC KED. THE FIRST REPAIR WAS CARRIED OUT AT 880.8 HOURS AND 1103 CYCLES. THE SECOND REPAIR CARRIED OUT AT 4528.4 HOURS AND 5315 CYCLES UNDER TECH MEMO EC-12TM-939.. . 1 L 7 1 3T 4 T RT A78EU E26NE 5 C P210NE 2001073000048 20010730 00048 GL 2001 7 30 CA010529015 3 20010515 G 6114 7724981 PLATE DHAV DHC7 DHC7102 2802708 EA PWA PT6 PT6A50 52043 EA HAMSTD 24PF 24PF305 GL PROPELLER CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 5000 (CAN) DURING LPI OF BARREL PLATE IT FOUND TO HAVE A CRACK THAT GOES ACROSS PACKING GROOVE FOR PACKING THAT SEALS BARREL PLATE TO BARREL. THIS PACKING SEALS BARREL LUBRICATING OIL INTO BARREL.THE BARREL PLATE IS ITEM #682.IPL FIGURE #1A, CMM 61-13-01,REVISION 10.AFTER WE FOUND THIS BARREL PLATE CRACKED WE EXAMINED ANOTHER PROP FROM A DIFFERENT OPERATOR THAT & IT WAS ALSO FOUNDWITH A CRACKED BARREL PLATE.WE THEN CHECKED A 2ND BARREL PLATE FROM 2ND OPERATOR & IT ALSO HAD A VERY SMALL CRACK STARTING.THE 1ST OPERATOR THEN SENT 2 MORE BARREL ASSY TO TRY & SALVAGE THE BARREL PLATES FROM THEM & BARREL PLATES WERE ALSO FOUND CRACKED.THE 2ND REPL BARREL ASSY WAS REMVD FROM SERVICE WITH TIME SINCE LAST MAJOR INSP OF 6,32 2 H 7 4 4T 4 T A20EA E4EA 6 C P1NE 2001073000051 20010730 00051 SO 2001 7 30 CA010529016 1 20010427 G 7120 V961312 ISOLATOR PIPER 1607305 PIPER PA23 PA23250 7102308 SO LYC O540 IO540C4B5 41532 EA HARTZL HCE2Y HCE2YR2 GL ENGINE MOUNT LOOSE W K NONE O OTHER IN INSP/MAINT 1 CA 665 274721 (CAN) TO KEEP FRONT OF ENGINE FROM CONTACTING COWL, ADDITIONAL P/N 85012-101 WASHERS WERE FOUND UNDER LOWER CORD MOUNTS TO RAISE FRONT OF ENGINE. . . . 1 L 7 2 3O 3 O 1A10 1E4 5 C P9EA 2001073000053 20010730 00053 SW 2001 7 30 CA010529017 1 20010427 G 1100 PLACARD RKWELL 700 700 7630520 SW LYC O540 TIO540R2AD 41532 EA HARTZL HCE3Y HCE3YR2A GL ENGINE OIL DAMAGED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) WHEN ADDING OIL TO ENGINE WE NOTICED THAT EXTERNAL MARKING ON LITRE CONTAINER SAID "EXXON AVIATION OIL 100". WE CH ECKED THE CARTON CONTAINING 12 LITRES AND IT READ "EXXON AVIATION OIL EE100". ONE INDICATED ASHLESS DISPERSANT OIL AND O NE INDICATED STRAIGHT MINERAL OIL. DISTRIBUTOR FOR OIL CONFIRMED PROBLEM AND TOOK BACK ALL PRODUCT IN QUESTION. . . . . 1 L 7 2 3O 3 O A12SW E14EA 5 C P33EA 2001073000056 20010730 00056 EU 2001 7 30 CA010529020 1 20010430 G 2550 S160919 SPACER SIREN S16096 SNIAS 350 AS350B1 8680811 EU TMECA ARRIEL ARRIEL1D NE CARGO HOOK CORRODED W K NONE O OTHER IN INSP/MAINT 1 CA 843 843 898 (CAN) WHEN THE HOOK ARRIVED AT E.C.L., THE SCREW AND NUT WHICH TIGHTEN THE SPACER (P/N S1609-19) HAD BEEN LOOSENED. IT W AS TIGHTENED TO PERFORM INCOMING TESTS. THE CAM WHICH RELEASES THE LOAD BEAM WOULD NOT FUNCTION UNDER LIGHT LOAD (12 LBS ). AS THE LOAD WAS INCAREASED THE CAM WOULD BE PUSHED OUT OF THE PATH OF THE LOAD BEAM, BUT THE CAM WOULD NOT RETURN. WH EN THIS OCCURES THE HOOK WILL NO LONGER HOLD A LOAD.. 1 G 7 1 3U 3 U H9EU E19EU 2001073000058 20010730 00058 NM 2001 7 30 CA010529021 1 20010415 G 3320 BA080061 BALLAST DHAV DHC8 DHC8102 2809003 NM PWA 120 PW120A NE HAMSTD 14SF 14SF7 NE LIGHTS FAILED W O OTHER B SMOKE/FUMES/ODORS/SPARKS TX TAXI/GRND HDL 1 CA 3403 (CAN) WHEN THE FLIGHT CREW ARRIVED AT THE AIRCRAFT (ON GATE WITH EXTERNAL POWER ON) THEY REPORTED A BURNING SMELL IN THE CABIN. THEY IMMEDIATELY TURNED OFF THE AIRCRAFT POWER. MAINTENANCE FOUND THE OVERHEADLIGHTING BALLAST FOR ROW 1 - R/H, HAD OVERHEATED AND BURNED OUT. THE BALLAST AND BULB WERE REPLACED AND CHECKED - SERVICEABLE. . .. . 2 H 7 2 4T 4 T RT A13NM E20NE 6 C P7NE 2001073000060 20010730 00060 NM 2001 7 30 CA010529022 1 20010423 G 2910 82950010271 TUBE DHAV DHC8 DHC8102 2809003 NM PWA 120 PW120A NE HAMSTD 14SF 14SF7 NE HYD SYSTEM LEAKING W O OTHER K FLUID LOSS TX TAXI/GRND HDL 1 CA 25945 (CAN) DURING A WALK-AROUND, THE FLIGHT CREW NOTED FLUID LEAKING FROM THE R/H WING. MAINTENANCE FOUND THE HYDRAULIC TUBE (PRESSURE) TO THE R/H INBOARD ROLL SPOILER ACTUATOR LEAKING (PIN HOLE). THE HYDRAULIC TUBE WAS REPLACED AND ALL CHECKS C OMPLETED. . . . . 2 H 7 2 4T 4 T RT A13NM E20NE 6 C P7NE 2001073000061 20010730 00061 SO 2001 7 30 CA010529023 2 20010425 G 8530 646605 NUT CONT 646742 CESSNA 337 337G 2075730 CE CONT O360 IO360D 17025 SO MCAULY 2AF34C D2AF34C306 GL CYLINDER SECTION DAMAGED W E ENGINE SHUTDOWN D R INFLIGHT SEPARATION PARTIAL RPM/PWR LOSS TX TAXI/GRND HDL 1 CA 1432 (CAN) AFTER LANDING PILOT WAS TAXIING FOR SHUTDOWN WHEN HE HEARD A BANKING NOISE AND REAR ENGINE ROUGHNESS. INSPECTION R EVEALED A DENT IN VALVE COVER. COVER REMOVED AND FOUND BOTH ROCKER SHAFT HOLD DOWN STUDS SHEARED. IT HAS BEEN NOTED BEFO RE ON OTHER AIRCRAFT THAT ROCKER SHAFT HOLD DOWN NUTS HAVE BEEN STRIPING EASILY EVEN WITH TELEDYNE CONTINENTAL NEW ROCKE R SHAFT HOLD DOWN NUTS TORQUE VALVES. . . 1 H 7 2 3O 3 O A6CE E1CE 5 C P5EA 2001073000073 20010730 00073 SW 2001 7 30 CA010530009 1 20010510 G 2550 9307U BEARING 52800200 BELL 212 212 1181420 SW PWA PT6T PT6T3 52045 EA CARGO HOOK SEIZED W K NONE O OTHER IN INSP/MAINT 1 CA CAL909 (CAN) DURING AN OPS CHECK IT WAS DISCOVERED THAT THE UPPER HOUSING NR 76 TO LOWER HOUSING NR 100, LOCK NR 79 WAS DISLODG ED. FURTHER INVESTIGATION FOUND THAT THE BEARING NR 98 (WHICH ALLOWS THE CARGO HOOK TO ROTATE UNDER LOAD) WAS SEIZED DUE TO CORROSION. THERE ARE SEVERAL POSSIBLE AREAS THAT MOISTURE COULD ENTER THIS AREA. ONE WAS THE MANUAL RELEASE CABLE AN D THE SEALANT AROUND IT WAS IN POOR CONDITION. THIS HOLE THROUGH THE UPPER HOUSING IN DETAILED IN THE PICTURE PROVIDED. THE HOOK ASSEMBLY IS BIENG REPLACED. TSO OF HOOK ASSY IS 9 MONTHS.. 1 G 7 1 4U 4 U H4SW E22EA 2001073000081 20010730 00081 EA 2001 7 30 CA010531003 1 20010422 G 2750 865D1007 DRIVE UNIT CNDAIR CL600 CL6002B19 EA GE CF34 CF343A1 30015 NE TE FLAPS FAULTY W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) FLAP FAIL CAUTION MESSAGE DISPLAY ON EICAS (ENGINE INDICATIONS AND CREW AL ERT SYSTEM), QRH PERFORM WITH A NORMAL LANDING. RESET DONE AND FOUND SERVICEABLE BUT DEFECT RE-OCCURRED. FECU (FLAP ELECTRONIC CONTROL UNIT) CHANGED AS A PREVE NTIVE MEASURE WITHOUT ANY SUCCESS, THE DEFECT RE-OCCURRED, AFTER FURTHER INVESTIGATION, MAINTENANCE FOUND TO BE THE PDU (POWER DRIVE UNIT) TO BE AT FAULT. REPLACED POWER DRIVE UNIT AND ALSO ADJUSTED #6 & 7 POTENTIOMETERS FECU AND PDU WIRING CHECK (NIL FAULT DETECTED). FLAP RIGGED AND OPERATIONAL CHECK CARRIED OUT... 2 L 7 2 4F 4 F RT A21EA E15NE 2001070500006 20010705 00006 EU 2001 7 5 CA010531004 1 20010428 G 5210 D5311253800000 BEARING AIRBUS AIRBUS 320 A320211 3930320 EU CFMINT CFM56 CFM565A1 NE DOOR HINGE SEIZED W K NONE O OTHER DE DESCENT 1 CA (CAN) PASSENGER DOOR L1 NOISEY DURING DECENT, WHEN DOOR OPENED ON ARRIVAL, , DOOR JAMMED. FOUND DOOR HINGE BEARING TO FR AM, SEIZING. REPLD UPP ER & LOWER HINGE BEARINGS, OP CHECKED NORMAL.. . . . . . 2 L 7 2 4F 4 F RT A28NM E29NE 2001073000083 20010730 00083 NM 2001 7 30 CA010531005 1 20010414 G 2150 EO390DD03S2B11B RECEPTACLE AIRBUS A319 A319114 NM FUSLEAGE FAULTY W O OTHER B SMOKE/FUMES/ODORS/SPARKS CR CRUISE 1 CA (CAN) FORWARD CABIN CONDITION TRIM AIR VALVE SYSTEM AT FAULT, ECAM MESSAGE, LONG HISTORY, MINIMUM EQUIPMENT LIST 21-63-0 2 APPLIED. ON TROUBLESHOOTING, FOUND TRIM AIR VALVE CONNECTOR 1941VC RECEPTACLE & 1941VCA PLUG FOR ZONE CONTROLLER DAMAG ED, BURNT PINS. ON TROUBLESHOOTING FOUND SHORT BETWEEN PIN 11A OF CONNECTOR AB AN PIN 5A OF AA CONNECTOR OF 8HK ZONE TEM PERATURE CONTROLLER. PULLING ON CONNECTOR 1941VC CAUSED ARCING AND DAMAGE TO CONNECTOR 1941VC AND VCA. THE FAULTY RECEPT ACLE AND PLUG IS LOCATED BELOW CABIN FLOOR AT STATION 1290. REPLACED CONNECTOR 1941VC AND 1941 VCA, FORWARD CABIN CONDIT ION TRIM AIR SYSTEM TESTED, OPERATION NORMAL. 2 L 7 2 4F RT A28NM 2001073000084 20010730 00084 WP 2001 7 30 CA010531006 1 20010428 G 3320 TERMINAL BLOCK LKHEED 1011 10113853 5265020 WP RROYCE RB211 RB211524B402 54555 NE ROW 23 OVERHEATED W O OTHER B SMOKE/FUMES/ODORS/SPARKS TX TAXI/GRND HDL 1 CA (CAN) ON ARRIVAL CREW REPORTE SMOKE AT ROW 23 LT CEILING. FOUND LUMINARE TERMINAL BLOCK OVERHEATED. LUMINARE ASSY REPLAC ED AND TERMINAL BLOCK REPLACED AIRCRAFT RETURNED TO SERVICE. 2 L 7 3 4F 4 F A23WE E12EU 2001073000086 20010730 00086 WP 2001 7 30 CA010531007 1 20010508 G 4900 74275 FUEL BOWL PWC ST6 LKHEED 1011 1011385114 WP RROYCE RB211 RB21122B02 54555 NE FUEL FILTER CRACKED W D RETURN TO BLOCK J WARNING INDICATION TX TAXI/GRND HDL 1 CA 74275 (CAN) DURING THE TAXI IN THE AIRCRAFT LOST APPROXIMATELY 600 LBS OF FUEL. MAINTENANCE FOUND FUELLEAK FROM APU. UPON INSP ECTION FOUND THAT THE FUEL WAS COMING FROM THE LOW PRESSURE FUEL FILTER BOWL CRACKED AT MOUNTING FLANGE. BOWL REPLACED A ND AIRCRAFT RETURNED TO SERVICE. BOWL MUST HAVE BEEN INSTALLED COCKED EYED AND THE BOLT WAS USED TO OVER TORQUE THE FLAN GE TO SEAT THE BOWL PROPERLY. . . . . 2 L 7 3 4F 4 F A23WE E12EU 2001070500007 20010705 00007 WP 2001 7 5 CA010531008 1 20010428 G 2400 2621TB9 TERMINAL BLOCK LKHEED 1011 10113853 5265020 WP RROYCE RB211 RB211524B402 54555 NE 317 BB FAILED W K NONE P NO WARNING INDICATION IN INSP/MAINT 1 CA (CAN) FOLLOWING APU WARNING HORN RCCB TRIPPED OFF FOUND 5 WIRES WHERE THE INSULATION WAS BROKEN AND RELATED TERMINAL BUS CHEMICALLY DESTROYED BY SKYDROLL. APU FIRE-EX BOTTLE SQUIB WS INTERMITTENT DUE TO DAMAGE. REPLACED TERMINAL BLOCK AND R EPAIRED WIRING AND AREA CLEAN FROM SKYDROLL AND INSPECTED FOR LEAKS. NO LEAKS WERE NOTED, AIRCRAFT RETURNED TO SERVICE. . . . . 2 L 7 3 4F 4 F A23WE E12EU 2001073000088 20010730 00088 CE 2001 7 30 CA010621003 1 20010524 G 2421 7565T ALTERNATOR CESSNA 305 305A 2074002 CE CONT O470 O47011 17026 SO MCAULY 1A200 1A200FM GL ENGINE FAILED W O OTHER H J ELECT. POWER LOSS-50 PC WARNING INDICATION CR CRUISE 1 CA 6 (CAN) ALTERNATOR WS REMOVE TO CHECK FOR INSTALLATION OF NUT AND SPLINE DRIVE. COTTER PINE WAS BROKEN AND NUT WAS BACKED OFF ON SPLINE. BOTH THE NUT AND COTTER PIN WS FOUND INSIDE THE ENGINE SPLINE GEAR. ALTERNATOR WAS SENT TO MANUFACTURER F OR OBSERVATIONS. 1 H 7 1 3O 3 O 5A5 E269 5 N P874 2001073000089 20010730 00089 CE 2001 7 30 CA010621004 1 20010518 G 2421 7565T ALTERNATOR CESSNA 305 305A 2074002 CE CONT O470 O47011 17026 SO MCAULY 1A200 1A200FM GL ENGINE FAILED W O OTHER H J ELECT. POWER LOSS-50 PC WARNING INDICATION CR CRUISE 1 CA 32 (CAN) ALTERNATOR WENT OFF LINE AND WOULD NO LONGER SUPPLY POWER. THE ALTERNATOR WAS REMOVED FOR REPLACEMENT. THE ALTERNA TOR WAS RETURNED TO THE MANUFACTURER FOR WARRANTY CONDSIDERATION. THE MANUFACTURER 9SKYTRONICS) CONTACTED ME AND INFORME D ME THAT THE ROTORS AND STATORS WERE FRIED. THE REASON WAS UNKNOWN. RAM AIR WAS CONNECTED AND FUNCTIONING. 1 H 7 1 3O 3 O 5A5 E269 5 N P874 2001073000091 20010730 00091 CE 2001 7 30 CA010621005 1 20010420 G 2421 7565T ALTERNATOR CESSNA 305 305A 2074002 CE CONT O470 O47011 17026 SO MCAULY 1A200 1A200FM GL ENGINE FAILED W K NONE O OTHER IN INSP/MAINT 1 CA 32 (CAN) ALTERNATOR WAS REMOVED TO CHECK FOR INSTALLATION OF NUT ON SPLINE DRIVE. COTTOR PIN WAS BROKEN AND NUT WAS BACKED OFF THE SPLINE. BOTH THE NUT AND COTTER PIN WAS FOUND INSIDE THE ENGINE SPLINE GEAR. ALTERNATOR WAS SENT TO MANUFACTURER FOR OBSERVATIONS. 1 H 7 1 3O 3 O 5A5 E269 5 N P874 2001073000093 20010730 00093 CE 2001 7 30 CA010621006 1 20010425 G 2421 7565T ALTERNATOR CESSNA 305 305A 2074002 CE CONT O470 O47011 17026 SO MCAULY 1A200 1A200FM GL ENGINE FAILED W O OTHER H J ELECT. POWER LOSS-50 PC WARNING INDICATION CR CRUISE 1 CA 4 (CAN) ALTERNATOR WENT OFF LINE AND WOULD NO LONGER SUPPLY POWER. THE ALTERNATOR WAS REMOVED FOR REPLACEMENT. IT WAS NOTE D THAT THE ALTERATOR DID HAVE A NUT INSTALLED ON THE SPLINE DRIVE. THE SPLINE DRIVE WAS NOTED TO BE SHEARED. THE ALTERNA TOR WAS RETURNED TO THE MANUFACTURER FOR WARRANTY CONSIDERATION. 1 H 7 1 3O 3 O 5A5 E269 5 N P874 2001073000094 20010730 00094 CE 2001 7 30 CA010621007 1 20010419 G 2421 7565T ALTERNATOR CESSNA 305 305A 2074002 CE CONT O470 O47011 17026 SO MCAULY 1A200 1A200FM GL DRIVE GEAR FAILED W O OTHER H J ELECT. POWER LOSS-50 PC WARNING INDICATION CR CRUISE 1 CA 295 (CAN) ALTERNATOR WENT OFF LINE AND WOULD NO LONGER SUPPLY POWER. THE ALTERNATOR WS REMOVED FOR REPLACEMENT. IT WAS NOTED THAT THE ALTERNATOR DID NOT HAVE A NUT INSTALLED ON SPLINE DRIVE. THE SPLINE DRIVE WAS NOTED TO BE SHEARED. THE ALTERNA TOR WAS RETURNED TO THE MANUFACTURER FOR WARRANTY CONSIDERATIONS. 1 H 7 1 3O 3 O 5A5 E269 5 N P874 2001073000110 20010730 00110 EA 2001 7 30 CA010621016 1 20010601 G 7603 3011094 PIN DHAV DHC3 DHC3 2800202 EA PWA PT6 PT6A34 52043 EA HARTZL HCB3T HCB3TN3 GL POWER LEVER MAKING METAL W O OTHER E VIBRATION/BUFFET TO TAKEOFF 1 CA 16 16 (CAN) AT T/O POWER LEVER GOT NOTICIABLY DIFFICULT TO MOVE, EVENTUALLY SEIZING COMPLETELY AT LANDING. APPEARS TO BE MATER IAL FAILURE OF PIN 1 H 7 1 3R 4 T A815 E4EA 6 C P15EA 2001073000119 20010730 00119 CE 2001 7 30 CA010621018 1 20010515 G 3242 1338932 STATOR BFGOODRICH 215286 CESSNA 500 550 2076604 CE PWA JT15 JT15D4 52112 NE RT BRAKE BROKEN W D RETURN TO BLOCK O OTHER TX TAXI/GRND HDL 1 CA 637 0534 (CAN) WHEN AIRCRAFT WAS TAXING FOR TAKE-OFF PILOTS REPORTED A LOUD NOISE AND THE AIRCRAFT BECAME DIFFICULT TO TAXI. THE PILOTS MADE AN ATTEMPT TO RETURN TO THE HANGAR BUT WERE UNABLE TO DO SO. MAINTENANCE PERSONNEL WERE CALLED, ANDUPON INSP ECTION OF THE R/H BRAKE, DISCOVERED THAT A STATOR DISC HAD FAILED AND JAMMED THE MAIN WHEEL. THE BROKEN STATOR WAS REMOV ED AND THE AIRCRAFT WAS TOWED BACK TO THE HANGAR AND REPAIRED AS REQUIRED. 1 L 7 2 4F 4 F A22CE E1NE 2001073000120 20010730 00120 EA 2001 7 30 CA010621020 1 20010515 G 3246 31279 WHEEL CNDAIR CL215 CL2151A10 EA NLG GOUGED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) UPON DISASSEMBLY OF NOSE WHEELS A SHARP DEEP GOUGE WAS FOUND IN THE VICINITY OF THE ONE WHEEL HALF. AFTER BLENDING THE DAMAGE WAS BEYOND THE LIMITS STATED IN THE B.F.G MANUAL. THE GAUGE APPEARED TO HAVE BEEN MADE DURING THE PREVIOUS D ISASSEMBLY SUBSEQUENTLY FOUR OTHER WHEELS HAVE BEEN FOUND WITH THE SAME DAMAGE. THE WHEELS WERE REPLACED WITH SERVICEABL E UNITS. 2 H 7 2 4R A14EA 2001073000122 20010730 00122 SO 2001 7 30 CA010621024 1 20010508 G 3242 1107252132 HOSE EMB 110 EMB110P1 3260122 SO PWA PT6 PT6A34 52043 EA HARTZL HCB3T HCB3TN3 GL BRACK ASSY BLOCKED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) BRAKES ON 4TH SIDE WERE REPORTED GRABBING AND OCCASSIONALLY NOT RELEASING PROPERLY. BRAKE UNIT, SHUTTLE VALVE AND BRAKE PRESSURE REDUCER WERE ALL REPLACED WITH NO SUCCESSFUL RESULT. IT WAS DISCOVERED THAT THE ABOVE BRAKE HOSE HAD DETE RIORATED INSIDE AND A SMALL PIECE OF RUBBER WAS ACTING LIKE A FLAPPER/CHECK VALUVE, RESTRICTING THE PROPER FLOW OF FLUID IN BOTH DIRECTIONS. 4 BRAKES WERE REPLACED AND THE AIRCRAFT RETURNED TO SERVICE. 1 L 7 2 4T 4 T A21SO E4EA 6 C P15EA 2001073000123 20010730 00123 WP 2001 7 30 CA010621026 1 20010524 G 7921 369H5656 PULLEY DOUG 369H5656 HUGHES 369 369HS 4470728 WP ALLSN 250C 250C20 03013 GL OIL COOLER FAILED W K NONE O OTHER IN INSP/MAINT 1 CA HL9936 (CAN) OIL COOLER PULLEY IS MADE UP OF A SPLINE BELT PULLEY WITH A METAL RING THAT IS "STAKED" ONTO THE PULLEY. THE RING WAS FOUND AROUND THE ENGINE OUTPUT DRIVE SHAFT AFTER GROUND RUNNING THE A/C. A NEW PART WAS USED TO COMPARE THE STAKING MARKS ON THE OLD PULLEY. THE NEW PULLEY HAS 4 LARGE STAKE MARKS COMPARED TO 8 SMALLER STAKE MARKS ON THE OLD PULLEY. 1 G 7 1 3U 3 U H3WE E4CE 2001073000125 20010730 00125 CE 2001 7 30 CA010621027 1 20010526 G 3242 1338932 STATOR BFGOODRICH 215286 CESSNA 500 550 2076604 CE PWA JT15 JT15D4 52112 NE BRAKE ASSY CRACKED W O OTHER D INFLIGHT SEPARATION LD LANDING 1 CA 670 2164 (CAN) UPON LANDING IN QUESNEL B.C, WHEN THE PILOT APPLIED BRAKE HE FELT THE AIRCRAFT VIBRATE AND SHUTTER WHEN LH BRAKE A PPLIED. THEY TAXIED TO THE RAMP AND NOTIFIED MAINTENANCE AFTER SHUTDOWN. INVESTIGATIONBY MAINTENANCE FOUND THAT THE BRAK E WEAR PINS STILL INDICATED THERE WAS LIFE REMAINING ON THE BRAKES, HOWEVER THE BRAKE WAS WORN TO THE LIMITS AND THE INB D STATOR WAS CRACKED THROUGH. THE BRAKE ASSEMBLY WAS REPLACED WITH AN OVERHAUL UNIT AND THE A IRCRAFT WAS RETURNED TO SE RVICE. 1 L 7 2 4F 4 F A22CE E1NE 2001073000127 20010730 00127 CE 2001 7 30 CA010621028 1 20010520 G 3213 5081032017 AXLE BEECH 1900 1900D 1154162 CE PWA PT6 PT6A67D NE HARTZL HCE4A HCE4A3I NE MLG CRACKED W O OTHER J WARNING INDICATION LD LANDING 1 CA 1583 1583 (CAN) CREW REPORTED A HARD LANDING ON MAY 20/01 DURING LANDINGT. THE A/C WS INSPECTED WHERE THE MAINTENANCE STAFF NOTED WHAT WERE POSSIBLY CRACKS IN THE MAIN LANDING GEAR AXLE HOUSING. NDT WAS PERFORMED AND CONFIRMED THE PRESENCE OF CRACKS ONBOTH THE LEFT HAND AND RT SIDE. THE LOWER OLD AXLE ASSEMBLIES ARE CURRENTLY BEING REPLACED 2 L 7 2 4T 4 T RT A24CE E26NE 5 C P10NE 2001073000129 20010730 00129 EA 2001 7 30 CA010621034 1 20010606 G 7921 1893013 REGULATOR 21563113805 CNDAIR CL215 CL2151A10 EA OIL COOLER STUCK W E ENGINE SHUTDOWN J WARNING INDICATION CR CRUISE 1 CA (CAN) #2 ENGINE SHUT DOWN IN FLIGHT DUE TO HIGH OIL TEMPERATURE AND DECREASING OIL PRESSURE. MAIN OIL SCREEN INSPECTED A ND NO CONTAMINATS WERE PRESENT. THE OIL COOLER REGULATOR WAS STUCK IN THE CLOSED POISITION. THE OIL COOLER REGULATOR WAS REPLACED, AIRCRAFT WAS GROUND RUN AND LEAK CHECKED SERVICEABLE. AIRCRAFT RETURNED TO SERVICE. 2 H 7 2 4R A14EA 2001073000147 20010730 00147 CE 2001 7 30 CA010622003 1 20010529 G 3240 114800851143880 BRAKE BEECH 1900 1900D 1154162 CE PWA PT6 PT6A67D NE HARTZL HCE4A HCE4A3I NE MLG MALFUNCTIONED W O OTHER J WARNING INDICATION LD LANDING 1 CA (CAN) PILOT DEPARTED CALGARY ON ROUTE TO PENTICTON. AT SOME POIN WHILE AIRBOURNE THE PARKING BRAKE WAS ENGAGED. DURING T OUCHDOWN IN PENTICTON NR 2,3,& 4 MAIN TIRES BLEW. THE A/C VEERED TO THE RIGHT, THE PILOTS MAINTAINED CONTROL AND THE A/C STOPPED AT SOME POINT ON THE RUNWAY. AS A RESULT OF THE TIRES BLOWING NR 3 & 4 MAIN WHEELS AND BRAKES WERE DAMAGED BEYO ND REPAIR. A MAINTENANCE CREW WAS FLOWN TO PENTICTON WHERE THE A/C WA JACKED UP, TIRES AND BRAKES REMOVED, NR 1 & 2 BRAK E ASSEWMBLIES WERE FOUND SERVICABLE. NR 3 & 4 BRAKE ASSEMBLIES WERE REPLACED. ALL FOUR MAIN WHEEL ASSY'S WERE REPLACED. THE A/C WAS THEN RETURNED TO SERVICE. 2 L 7 2 4T 4 T RT A24CE E26NE 5 C P10NE 2001073000148 20010730 00148 EA 2001 7 30 CA010622004 2 20010531 G 7261 GARLOCK SEAL BEECH 1900 1900C 1154161 CE PWA PT6 PT6A65B 52043 EA HARTZL HCB4M HCB4MP3 GL LT ENGINE FAILED W E A ENGINE SHUTDOWN UNSCHED LANDING K FLUID LOSS CL CLIMB 1 CA (CAN) LT ENGINE LOST OIL PRESSURE DURING CLIMB OUT OF AFTER APPROX. 20 MINUTES. PILOT SECURED ENGINE WHEN OIL PRESSURE W AS IN YELLOW ARC OF OIL GAUGE. AIRCRAFT LANDED UNEVENTUALLY ATER RETURNING TO YUR. MAINTENANCE FOUND THAT MOST OF THE OI L HAD BEEN EJECTED OVERBOARD THROUGH THE FUEL PUMP CASE DRAIN. GARLOCK SEAL AND CARRIER SEAL WERE REPLACED TWICE WITHOUT RESULTS. IVESTIGATION STILL IN PROGRESS. LT ENGINE POWER SECTION AND OIL COOLER WERE REPLACED THE 2 DAYS BEFORE. OIL LE AK WAS ALSO REPORTED 1 DAY BEFORE AND THE THRMAL BYPASS VALCE WAS REPLACED. GROUND RUS CHECKED SERVICEABLE. 2 L 7 2 4T 4 T RT A24CE E4EA 6 C P56GL 2001073000177 20010730 00177 SW 2001 7 30 CA010622018 1 20010528 G 3310 60647 POTENTIOMETER AIRTRC AT802 AT802 0390305 SW PWA PT6 PT6A67A 52043 NE HARTZL HCB5M HCB5MP3 GL COCKPIT SPARKS W O OTHER B SMOKE/FUMES/ODORS/SPARKS CR CRUISE 1 CA 545 (CAN) IN FLT, A/C EXPERIENCED "SHOWER OF SPARKS" EMINATING FROM L OWER INSTRUMENT LIGHTING DIMMER POTENTIMETER. DURING A PPROACH PILOT TRIED TO ADJUST THELOWER INSTRUMENT DIMMER THESPAR KS FLEW UPON LDG.THE INST WAS INSP/IT WAS NOTED THAT SO LDERED CONNECTION OF BOTH UPPER & LOWER INSTRUMENT DIMMER POTTS WERE CONTACTING EACHOTHER. SINC E THERE IS NO POSITIVE E NGAGEMENT OF POTENTIOMETER TO INSTRUMNET PANEL. IF ATTACH NUT ON POTENTIOMETER BECOMES SLIGHT LOOSE, POT ROTATE & CONTA CT ADJACENT POT. BOTH POTENTIOMETERS WERE RE-SECURED IN ASAFE POS AND CHECKED FOR CORRECT OP/OTHER DAMAGE TO SYS. FLEET CHECK. ONLY ONE OTHER A/C HAD A LOOSE POTENTIOMETER. 1 L 7 1 3T 4 T NC A19SW E26NE 6 C P44GL 2001073000179 20010730 00179 EA 2001 7 30 CA010622019 1 20010522 G 2752 MS28775142 SEAL 215750108 CNDAIR CL215 CL2151A10 EA FLAP ACTUATOR LEAKING W O OTHER K FLUID LOSS IN INSP/MAINT 1 CA H358 (CAN) A/C HAD BEEN ON GROUND 45 MINS WIHT NO SIGN OF FLUID LEAK. SUDDEN HYDRAULIC FLUID STARTED TO LEAK FROM R/H FLAP AC TUATOR & FLAPS DROOPED TO APPROX. 10 DEGS. FLUID WAS COMING F ROM LOWER END SEAL. ACTUATOR WAS CLEANED & FLAPS WERE CYCL ED 20 TIMES WITH NO FURTHER SIGNS OF LEAKAGE. A/C WAS RT-SRV. A/C WAS PARKED FOR NIGHT WITH NO S IGNS O F LEAKS. UPON DA ILY INSPS NEXT MORNING FLAPS WERE FOUND SAGGED TO APPROX. 10 DEGS/ PUDDLE OF HYD. FLUID FOUND BELOW R/H FLAP ACTUATOR. F LAPS WERE CYCLED WITH THEAUX FLUID PU MP/ A STREAM OF FLUID EMITTED FROM LOWER END OF ACTUATOR ON 1ST CYCLE ONLY.NO SIGN S OF LEAKAGE FOLLOWING 10 CYCLES. 2 H 7 2 4R A14EA 2001073000181 20010730 00181 CE 2001 7 30 CA010622021 1 20010608 G 5347 50150193 CHANNEL CESSNA 501509797 CESSNA 402 402B 207590P CE CONT O520 TSIO520E 17040 SO MCAULY 3AF32C 3AF32C87 GL SEAT SUPPORT CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 5890 5890 (CAN) BROUGHT THE A/C IN TO ADJUST THE LOW FUEL PRESS ON THE AUX FUEL PUMP. TO D0SO YOU MUST REMOVE THE PILOT SEAT & ADJ UST A RESISTOR UNDER THE PILOT SEAT SUPPORT ASSY. THAT IS WHEN NOTICED THE CRACKIN THE LOWER R/H SEAT SUPPORT ASSY BOTTO M CHANNEL 1 L 7 2 3O 3 O A7CE E8CE 5 C P22EA 2001073000183 20010730 00183 EA 2001 7 30 CA010622024 2 20010421 G 8530 75838 VALVE GUIDE LYC LW12966 PIPER PA31 PA31 7103102 SO LYC O540 TIO540J2BD 41532 EA HARTZL HCC4Y HCC4YR2 GL CYLINDER WORN W K NONE O OTHER IN INSP/MAINT 1 CA 41 (CAN) ON THE 1ST EVENT INSPECTION AFTER ENGINE WAS INSTALLED FOUND NR 5 CYLINDER FAILED COMPRESSION CHECK WITH 15/80. PR OGRESSIVE AIR IN KAMLOOPS SUSPECTS GUIDE WORN. RETURNED CYLIDER TO THEM FOR WARRANTY CONSIDERATION. 1 L 7 2 3O 3 O A20SO E14EA 5 C P52GL 2001073000185 20010730 00185 CE 2001 7 30 CA010622025 1 20010605 G 3213 504100036 ATTACH FITTING CESSNA 401 401 207590C CE CONT O520 TSIO520E 17040 SO MLG CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) DURING AN INSPECTION, THE LOWER SCISSOR ATTACH LUG WAS FOUND CRACKED. THE CRACK WAS FOUNDONLY AROUND THE SMALLER L UG. THE RT LANDING GEAR AXLE ASSE MBLY WAS REPLACED. 1 L 7 2 3O 3 O A7CE E8CE 2001073000188 20010730 00188 CE 2001 7 30 CA010622028 1 20010605 G 5743 52920048 DOUBLER CESSNA 401 401 207590C CE CONT O520 TSIO520E 17040 SO MLG CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) WHILE COMPLETING AN INSPECTION A CRACK WAS FOUND ON THE RT MAIN LANDING GEAR DOUBLER. A WING RIB IMPROVEMENT KIT ( SK414-8E) WAS PREVIOUSLY INSTALLED. DOUBLER P/N 5292004-8 WAS PART OF THE KIT. IT WAS THIS DOUBLER THAT WAS AGA IN FOUND CRACKED. THE DOUBLER WAS REPLACED. 1 L 7 2 3O 3 O A7CE E8CE 2001073000196 20010730 00196 EA 2001 7 30 CA010622029 1 20010512 G 7810 311178001 EXHAUST STACK DHAV DHC3 DHC3 2800202 EA PWA PT6 PT6A34 52043 EA LT ENGINE CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 870 870 (CAN) ON A 100 HOUR INSPECTION A CRACK WAS FOUND ON THE LT EXHAUST STACK MOUNTI NG FLANG OF THE TURBINE_EXHAUST DUCT. DU E TO THE FACT THAT THERE WAS SO LITTLE TIME ON THE ENGINE I CALLED P&W AND THEY SENT A REP. & A NEW PART FOR OUR AIRCRAF T. THE REP DID NOT KNOW WAY OUR EXHAUST WOULD CRACK. WE ARE NOW LOOKING AT THE EXHAUST AT 50 HOURS INTERVALS FOR THE NEX T LITLE WHILE TO SEE IF WE GET ANY MORE CRACKS. 1 H 7 1 3R 4 T A815 E4EA 2001073000198 20010730 00198 EU 2001 7 30 CA010622032 1 20010530 G 2560 AFG0314294 SEAT BELT SNIAS 350 AS350B 8680801 EU TMECA ARRIEL ARRIEL1B 6OO30 NE COCKPIT DAMAGED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) INERTIA REELS, EACH 2 WERE RE-WEBBED BY AN UNAUTHORIZED REPAIR FACILITY IN CANADA. IT IS UNKNOWN IF WEBBING / THRE AD MEETS REQUIRMENT SPECIFICATIONS / IF THE HARNESS ASSY WOULD TENSUKE TEST TO PROPER FOR MATERIAL / STITCH PATTERN. PAR TS WERE RE-WEBBED AND CERTIFIED WITH PROPER MATERIALS AND TC24-0045 CONFORMITY CERTIFICATIONS ISSUED PARTS RETURNED TO S ERVICE. 1 G 7 1 3U 3 U H9EU E19EU 2001073000199 20010730 00199 SO 2001 7 30 CA010622033 2 20010604 G 7314 6462121 PUMP CESSNA 185 A185E 2072818 CE CONT O520 IO520D 17032 SO MCAULY D3A34 D3A34C403 GL FUEL SYSTEM LEAKING W K NONE K FLUID LOSS IN INSP/MAINT 1 CA 570 (CAN) THE PILOT NOTED FUEL DRIPPING FROM THE OVERBOARD DRAIN TUBE. MAINTENANCE DISCOVERED FUEL COMING FROM THE FUEL PUMP SEAL DRAIN. THERE IS A CRITICAL SERVICE BULLETIN C53 01-01. ALTHOUGH THE PART NUMBER DID NOT MATCH THE BASIC FUEL PUMP WAS IDENTIFIED BY THE PRESENCE OF TWO ROUND BOSSES LOCATED ON OPPOSITE SIDES OF THE FUEL PUMP HOUSING OWNER /AME SHOULD BE ALERT TO ANY FUEL LEAKAGE IN THIS AREA. 1 H 7 1 3O 3 O 3A24 E5CE 5 C P47GL 2001073000200 20010730 00200 EA 2001 7 30 CA010622034 1 20010515 G 2510 FDC2700 SEAT BELT DHAV DHC6 DHC6300 2802606 EA PWA PT6 PT6A27 52043 EA HARTZL HCB3T HCB3TN3 GL COCKPIT DAMAGED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) 10 PAX LAP BELT ASSY'S WERE REPAIRED AND CERTIFIED BY UNAUTHORIZED REPAIR FACILITY. UNKNOWN IF WEBBING MATERIAL AN D THREAD MEETS SPECIFICATION. UNKNOWN IF STITCH PATTERN WILL TENSILE TEST TO REQUIRED LIMIT. LAP BELTS WERE RE-WEBBED TO PROPER 1500 LB CINFIGURATION WITH CERTIFIED MATERIALS. TENSILE TEST TO 1500 LSB CARRIED OUT. PROPER TAGS WERE INSTALLED ON BELTS AND 24-0045 CONFORMITY CERTIFICATIONISSUED. PARTS RETURNED TO SERVICE. 1 H 7 2 3T 4 T RT A9EA E4EA 6 C P15EA 2001073000201 20010730 00201 EU 2001 7 30 CA010622035 1 20010606 G 5280 137414B416 DOOR BAG JETSTM JETSTM3101 1500215 EU GARRTT TPE331 TPE33110UG 01514 WP MCAULY 4HFR34 4HFR34C652 NE MLG BENT W O OTHER O OTHER LD LANDING 1 CA (CAN) THE GEAR WAS SELECTED DOWN FOR LANDING. A VIBRATION WAS FELT AND THE AIRCRAFT DELVELOPED A SLIGHT YAW TO THE RIGHT . THE YAW WAS TRIMMED OUTAND THE LA NDING CONTINUED. AFTER LANDING IT WAS DISCOVERED THAT THE RT GEAR DOOR WAS HANGING L OOSE. ON INSPECTION IT WAS FOUND THAT THE ROD CONNECTINGTHE DOOR TO THE GEAR HAD FAILED IN COMPRESSION AND THE AFT HINGE WAS BROKEN. THE DOOR WAS BENT OUTWARD FROM A POINT ABOUT 7 INCHES INBOARD OF THE HINGE LINE. IT APPEARS THAT THE DOOR H UNG UP ON THE EDGE OF THE LANDING GEAR BAY. THE ACTION OF THE GEAR LOWERING PUSHED DOWN ON THE DOOR CAUSING IT TO BEND O UTWARDS AND EVENTUALLY BREAK THE OPERATING ROD. 2 L 7 2 4T 4 T RT A21EU E4WE 6 C 3PNE 2001073000202 20010730 00202 SO 2001 7 30 CA010622036 2 20010507 G 8520 6419311075 BOLT CESSNA 402 402B 207590P CE CONT O520 TSIO520E 17040 SO MCAULY 3AF32C 3AF32C505 GL LT ENGINE BROKEN W K NONE O OTHER IN INSP/MAINT 1 CA 973 (CAN) UPON INSPECTION (EVENT 1 & 2), TAKING THE COWLING OFF ON LEFT ENGINE, A NUT WITH PART OF THE THRU BOLT HIT THE FLO OR, FURTHER INSPECTION FOUND THE LEFT THRU BOLT HAS SNAPPED. 1 L 7 2 3O 3 O A7CE E8CE 5 C P22EA 2001073000203 20010730 00203 SO 2001 7 30 CA010622037 1 20010705 G 3320 10002719 LIGHT EMB 110 EMB110P1 3260122 SO PWA PT6 PT6A34 52043 EA HARTZL HCB3T HCB3TN3 GL CABIN SPARKS W K NONE B SMOKE/FUMES/ODORS/SPARKS IN INSP/MAINT 1 CA (CAN) CUSTOMER REPORTED SPARKS FROM LOOSE OVERHEAD LIGHT IN 7TH ROW, LEFT SIDE. 1 L 7 2 4T 4 T A21SO E4EA 6 C P15EA 2001073000204 20010730 00204 EU 2001 7 30 CA010625001 1 20010613 G 3210 200877664 PIN BAG BAE146 BAE146200A 1500266 EU LYC ALF502 ALF502R5 41580 NE MLG DAMAGED W K NONE O OTHER IN INSP/MAINT 1 CA 28020 7342 (CAN) LARGE SECTION OF CHROME MISSING FROM DIAMETER "A" PIN (PARENT METAL CORRODED UNDER AREA OF MISSING CHROME) DEFECT FOUND REMOVAL OF PIN WHEN RETRACTION ACTUATOR REPLACEMENT WAS REQUIRED. PIN REPLACED. ADDITIONAL INFORMATION & PICTURES E-MAILED TO STEVE DUDKA AT TRANSPORT CANADA. 2 H 7 4 4F 4 F RT A49EU E6NE 2001073000206 20010730 00206 NM 2001 7 30 CA010625002 1 20010611 G 5330 SKIN BOEING 737 737201 1384454 NM PWA JT8 JT8D9A 52048 NE FUSELAGE CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 51026 (CAN) CRACKED FUSELAGE SKIN LEFT SIDE, BETWEEN FUSELAGE STATIONS 747 ABD 767, STRINGER 17L. REPAIRED AS PER SRM 53-30-3, TABLE 1, METHOD 1 PAGES 87,88 & 88A. 2 L 7 2 4F 4 F A16WE E2EA 2001073000208 20010730 00208 NM 2001 7 30 CA010625004 1 20010611 G 5330 SKIN BOEING 737 737296 1384486 NM PWA JT8 JT8D9A 52048 NE FUSELAGE CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 52471 (CAN) CRACK IN FUSELAGE SKIN LEFT SIDE, BETWEEN FUSELAGE STATIONS 747 AND 767, STRINGER 17L. REPAIRED AS PER SRM 53-30-3 , TABLE 1, METHOD 1, PAGES 87,88 & 88A. 2 L 7 2 4F 4 F RT A16WE E2EA 2001073000228 20010730 00228 CE 2001 7 30 CA010625005 1 20010616 G 6120 11538900215 CONTROL CABLE HARTZL HCB3TN3G BEECH 200 200BEECH 1152920 CE PWA PT6 PT6A41 52043 EA HARTZL HCB3T HCB3TN3 GL RT ENGINE BROKEN W O OTHER E VIBRATION/BUFFET CR CRUISE 1 CA BUA20464 (CAN) WHILE OPERATING IN CRUISE FLIGHT, A SELECTION OF THE PROPELLOR LEVER CONTROL FOR THE RIGHT ENGINE WAS MADE WITH NO CHANGE IN PROP RPM. ANOTHER SETTING WAS TRIED WITH NO RESPONSE. THE RPM REAMINED AT 1900. THE FLIGHT ROUTIG WAS CANCELL ED AND TH AIRCRAFT RETURNED FOR MAINTENANCE INSPECTION. MAI NTENANCE DETERMINED THAT THE PROPELLER CONTROL PUSH/PULL CAB LE ASSEMBLY HAD BROKEN ABOUT 3 INCHES INSIDE OF THE HOUSING AT THE COCKPIT LEVER END. THERE WERE NO PREVIOUS INDICATIONS OR REPORTS OF A STIFF OR ROUGH PROP LEVER CONTROL. THE BROKEN CABLE ASSY WAS REMOVED FOR REPLACEMENT WITH A NEW ASSEMBL Y. 1 L 7 2 4T 4 T A24CE E4EA 6 C P15EA 2001073000277 20010730 00277 CE 2001 7 30 CA010625010 1 20010531 G 5610 10138402522 WINDSHIELD BEECH 300 300BEECH 1152930 CE PWA PT6 PT6A60A 52043 NE HARTZL HCB4M HCB4MP3 GL COCKPIT FAILED W O OTHER O OTHER CR CRUISE 1 CA 1241 (CAN) A/C WAS ENROUTE AT FL. 310, WINDHIELD ANTI-ICE WAS SE LECTED ON.SUDDENLY A LOUD CRACK WAS HEARD AND THE CO-PILOTS WINDHIELD SHATTERED AND THE INNER PANE INTO MANY SMALL PIECES. CR EW FOLOWED CHECKLIST FOR CRAKED WIND AND A/C DESENDED TO 12,000 FT ASL AND LANDED. CO-PILOTS WINDSHIELD ASSYWAS REPALACED AND IT WAS CONFIRM ED THAT THE H.P AND L.P HEAT ELEM ENTS AND CONTROL SENSOR ON THE FAILED WINDSHIELD PANEL WERE SERVICEABLE. LATEST WINDSHIELD AVAILABLE P/N 101-384025-2 4 INCORPORATING NEW INTERLAYER MATERIAL (PPG-12) INSTALLED, TO REPLACE FAILED WINDSHIELD. 2 L 7 2 4T 4 T A24CE E4EA 6 C P56GL 2001073000278 20010730 00278 SW 2001 7 30 CA010625011 1 20010516 G 5311 FRAME AIRTRC AT802 AT802 0390305 SW FUSELAGE WORN W K NONE O OTHER IN INSP/MAINT 1 CA 50 (CAN) ON INSPECTION THE RUDDER CABLE AND RUDER TRIM CABLE WERE FOUND TO BE RUBBING ON THE CUT-OUT IN THE BULKHEAD AT THE FS 180. 1 L 7 1 3T NC A19SW 2001073000306 20010730 00306 SO 2001 7 30 CA010625013 1 20010605 G 5751 6237601 DOUBLER PIPER PA28 PA28140 7102802 SO LYC O320 O320E2A 41508 EA SNSNCH 74D 74DM EA AILERON CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) DURING ANNUAL INSPECTION CRACKS WERE NOTED ALONG THE BEND RADIUS OF PARTS (REFER PHOTOS ATTACHED). SUSPECT DAMAGE WAS CAUSED FROM CONTROLS NOT BEING PROPERLY SECURED ALLOWING AILERONS TO WORK UP ANDDOWN DURING WINDY CONDITION S._P/N'S 66767-00 & 66767-01. 1 L 7 1 3O 3 O 2A13 E274 5 N P88614 2001073000307 20010730 00307 SW 2001 7 30 CA010625014 1 20010607 G 3246 40279 WHEEL AIRTRC AT802 AT802 0390305 SW MLG CORRODED W K NONE O OTHER IN INSP/MAINT 1 CA 25 (CAN) UPON DISASSEMBLY OF WHEEL MAINTENANCE DISCOVERED SERIOUS CORROSION AT THE TOP AND BOTTOM OF THE OUTER BEARING RACE . 1 L 7 1 3T NC A19SW 2001073000308 20010730 00308 SO 2001 7 30 CA010625015 1 20010525 G 2140 COMBUSTION LINER JANITROL 90D381 PIPER PA44 PA44180 7104402 SO LYC O360 O360E1A6 41514 EA HARTZL HCC2Y HCC2YR2 GL HEATER CRACKED W B A EMER. DESCENT UNSCHED LANDING O OTHER CL CLIMB 1 CA 283 4791851 (CAN) PILOT SMELLED A STRANGE BURING SMELL IN COCKPIT WHICH LAST APPROX. 30 SEC AND DISAPPEARED. SHORTLY FOLLOWING SHE S TARTED FEELING A FLOATING SENSATION /TRANSFERRED CONTROL TO STUDENT/WITHIN 30 SEC THE STUDENT FEELING SAME EFFECTS.THE P ILOT THAN DECLARED EMERGENCY AND REGAINED CONTROL FLIGHT WAS IMC. WE OPENED THE STORM WINDOW SHUT OFF HEATER/CHECKED THE CO DETECTIR WHICH INDICATED NORMAL. WITHIN 30SEC WE FELT BETTER WITH THE FRESH AIR AND LANDED WIT HOUT INCIDENT. INSPEC TION SHOWED AIRCRAFT HEATING SYSTEM REVEALED A 2.5-3 INCH CRACK IN THE COMBUSTION HEATER CAN, IN THE AFT WELDED LID. HEA TER W AS REPLACED. NEXT DUE FOR PRESSURE DECAY TEST AT 500HR. HEATER HOBBS TIME. 1 L 7 2 3O 3 O A19S0 E286 5 C P920 2001073000309 20010730 00309 CE 2001 7 30 CA010625016 1 20010530 G 5751 50130016 HINGE BRACKET BEECH 90 C90A 1152911 CE PWA PT6 PT6A21 52043 EA HARTZL HCD4N3 HCD4N3A GL RT AILERON MISINSTALLED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) PILOT FOUND AILERON SECURED ONLY BY OUTBOARD HINGE AND PUSHROD DURING WALK AROUND INSPECTION. THE SCREWS FOR THE I NBOARD AND MIDDLE HINGE BRACKETS WERE IN PLACE, BUT NOT THROUGH THE BRACKETS. THE AILERON WAS REMOVED IN NOV 98 FOR PAIN T. THE A/C WENT THROUGH A FULL PHASE 1-4 INSPECTION IN OCT. 99. THE A/C WENT THROUGH ANOTHER FULLPHASE 1-4 INSPECTION IN FEB 2001 WHO ALSO CONDUCTED THE EXPORT C OFA.CANADIAN APPROVAL WAS THEN CARRIED OUT IN TORONTO. P/N'S 50-130016 & 50-13 0021. 1 L 7 2 3T 4 T RT 3A20 E4EA 5 C STC 2001073000310 20010730 00310 SO 2001 7 30 CA010625017 1 20010605 G 5740 62102000 BRACKET PIPER PA28 PA28140 7102802 SO LYC O320 O320E2A 41508 EA SNSNCH 74D 74DM EA WING CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) AILERON SUPPORT BRACKET AT BOLT HOLE WERE FOUND CRACKED WITH THE RIGHT HAN D PART COMPLETLY BROKEN AS PER PHOTO. S USPECT CAUSE-CONTROLS NOT SECURED BUT ALLOWED TOFLOP AROUND DURING WINDY CONDITIONS, PROBABLY OVER A PERIOD OF TIME._P/N 'S 62102-000(LEFT) 62102-001(RIGHT) 1 L 7 1 3O 3 O 2A13 E274 5 N P88614 2001073000311 20010730 00311 NE 2001 7 30 CA010625019 3 20010509 G 6114 78230101 BEARING 14SF7 DHAV DHC8 DHC8102 2809003 NM PWA 120 PW120A NE HAMSTD 14SF 14SF7 NE PROP HUB GOUGED W K NONE O OTHER IN INSP/MAINT 1 CA 10500 8992 (CAN) SUSPECT ELECTRICAL ARCING OR DELAMINATION OF CHROME COATING FROM SUB SURFACE STRUCTURE. 2 H 7 2 4T 4 T RT A13NM E20NE 6 C P7NE 2001073000312 20010730 00312 EA 2001 7 30 CA010625024 2 20010509 G 7200 PT6A41 ENGINE BEECH 200 200BEECH 1152920 CE PWA PT6 PT6A41 52043 EA HARTZL HCB3T HCB3TN3 GL RIGHT FAILED W E A ENGINE SHUTDOWN UNSCHED LANDING R J PARTIAL RPM/PWR LOSS WARNING INDICATION CR CRUISE 1 CA 8808 980 (CAN) ABOUT 1 HR INTO FLT CREW NOTED A SLIGHT FLUNCTUATION IN RT ENGINE TORQUE ALONG WITH A REDUCTION IN ENGINE NG SPEED . ITT ALSO INCREASED 50 DEGS HIGHER THAN NORMAL FOR CRUISE POWER.THE CREW MONITORE ENGINE PARAMETERS & NOTED A FURTHER D ECREASE IN NG TO BELOW NORMAL OP LIMITS WITH INCREASES IN ITT. REW ELECTED TO SHUTDOWN ENGINE IN ACCORD WITH AFM AND SOP 'S & RETURNED TO MAIN BASE FOR FURTHER INVEST.. A/C LANDED W/O FURTHER INCID..MAINT INSP OF ENGINE REVEALED THAT ACCESSO RY SECTION /GAS GEN GROUP HAVE SIGNS OF INTERNAL DAMAGED AS INDICATED BY INABILITY TO ROTATE SEVERAL OF DRIVES. NO FURTH ER TEAR DOWN OF ENGINE WILL TAKE 1 L 7 2 4T 4 T A24CE E4EA 6 C P15EA 2001073000313 20010730 00313 SW 2001 7 30 CA010625025 1 20010430 G 2150 BEARING SWRNGN SA227 SA227AC 8780603 SW ROTOL R321 R321482F8 GL COOLING TURBINE SEIZED W E D ENGINE SHUTDOWN RETURN TO BLOCK B SMOKE/FUMES/ODORS/SPARKS TX TAXI/GRND HDL 1 CA (CAN) AFTER LDG /DURING TAXI TO TERMINAL BLDG CREW NOTICED A SMOKY HAZE IN FWD CABIN& COCKPIT AREA. THEY IMMEDIATELY TUR NED OFF LEFT & RIGHT BLEED AIR SWITCHES & THEN ELECTED TO SHUTDOWN ENGINES WHEN THEY DIDN'T SEE ANY NOTICEABLE CHANGE WI TH SWITCHES SELECTED OFF.THE CREW & PASSENGERS DEPLANED A/C W/O FURTHER INCID.. MAINT RETURNED A/C TO TH HANGAR & BEGAN AN INSP INTO CAUES OF INCID.. IT WAS DETERMINED THAT LEFT AIR-COND, COOLING TURBINE WAS INOPERATIVE & HAD SEIZED. IT APP EARS THAT BEARING IN THEUNIT IS AT FAULT, RESULTING IN AN IMBALANCE IN ROTATING IMPELLER. THIS RESULTED IN IMPELLER RUBB ING ON SHROUD CAUSING IT TO FAIL 2 L 7 2 4T RT A8SW 6 C P61GL 2001073000314 20010730 00314 CE 2001 7 30 CA010625026 1 20010529 G 7120 MOUNT CESSNA 180 180A 2072604 CE CONT O470 O470K 17026 SO MCAULY 2A34C 2A34C66 GL LT ENGINE CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 3199 (CAN) ENG MOUNT FOUND CRACKED ON UPPER LT STRUT. 1 H 7 1 3O 3 O 5A6 E273 5 C P3EA 2001073000315 20010730 00315 NM 2001 7 30 CA010625028 1 20010614 G 3241 CONNECTOR BOEING 737 737281 138448P NM PWA JT8 JT8D17 52049 NE MLG BRAKE MISINSTALLED W K NONE W INADEQUATE Q C IN INSP/MAINT 1 CA 187 (CAN) IN TROUBLE SHOOTING A HISTORY OF INTERMITTENT ANTI-SKID PROBLEMS IT WAS DISCOVERED THAT THE HYDRAULIC BRAKE PRESSU RE LINES FROM THE AIRFRAME TO THE TOP OF THE R.H LANDING GEAR SWIVELS THE CONNECTORSTOTHE WHEEL SPEED TRANSDUCERS WERE S WAPPED TO THE OPPOSITE WHEEL. THE A/C WAS RESTORED TO NORMAL. NO FURTHER PROBLEMS OCCURRED. THE FAULT HISTORY INDICATED ON GEAR INSTALLATION AT T THIRD PARTY A.M.O.THE OVER HAULER WAS ADVISED AND IS IMPLEMENTING CHANGES IN THEIR PROCEDURES. 2 L 7 2 4F 4 F A16WE E2EA 2001073000316 20010730 00316 EU 2001 7 30 CA010625029 1 20010613 G 7110 5711012367 HINGE PILATS PC12 PC1245 EU PWA PT6 PT6A67B 52043 NE HARTZL HCE4A HCE4A3D GL ENGINE COWL CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 6560 (CAN) DURING AN INSPECTION OF THE FLAP ASSY FOR THE OIL COOLER DOR A 1" CRACK WASFOUND DBETWEEN THE MOUNTING HOLES AND T HE HINGE. NEW PART WAS INSTALLED. 1 L 7 1 3T 4 T RT A78EU E26NE 5 C P210NE 2001073000318 20010730 00318 GL 2001 7 30 CA010625031 2 20010606 G 7230 6890550 BEARING BELL 206 206B 1181511 SW ALLSN 250C 250C20 03013 GL ENGINE FAILED W A UNSCHED LANDING E VIBRATION/BUFFET NR NOT REPORTED 1 CA 6228 2980 (CAN) PILOT FELT ENGINE VIBRATION, 30 MINUTES INTO THE FLIGHT, WITH CLIMB OF T.O.O. TURN BACK FOR LANDING. ENGINE OIL PR ESS FLACTUATE. 6FT ABOVE GROUND THE ENGINE QUIT. THE PILOT DID LOWER AUTOROTATION, NO DAMAGE TO AIRCRAFT AND NO ONE GOT INJURED. INITIAL INSPECTATION WAS DONE AND FOUND THAT COMPRESSOR BLADES WERE DAMAGED AND NR 1 BEARING AND SEAT FAILED. ENGINE ASSY REMOVE /REPLACED /SENT FOR EVALUATION. 1 G 7 1 3U 3 U H2SW E4CE 2001073000319 20010730 00319 CE 2001 7 30 CA010625033 1 20010518 G 3234 998100753 BRACKET 11581102011 BEECH 90 F90 1152909 CE PWA PT6 PT6A135 52043 NE SWITCH MOUNT MISMANUFACTURED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) SWITCH MOUNT FLANGE NOT BENT PROPERLY PER DRAWING TO OBTAIN 90 DEGREE RELATIONSHIP WITH PIVOT POINT. THIS RESULTS IN A SMALLER RANGE OF ADJUSTMENT. SWITCH P/N 622EN51 (HONEYWELL) INTERNAL SPRING IS SOSTIFF(3-6LBS) THE BRACKET FLEXES E XCESSIVELY AS THE SWITCH IS BEING ACTIVATED. THIS ALSO RESULTS IN REDUCING RANGE OF ADJUSTMENT. HAVE TALKED TO RAYTHEON TECH SUPPORT. 1 L 7 2 4T 4 T A31CE E4EA 2001073000320 20010730 00320 EA 2001 7 30 CA010625034 2 20010518 G 7414 10682056 DISTRIBUTOR BLK BENDIX D6LN3200 PIPER PA31 PA31 7103102 SO LYC O540 TIO540J2BD 41532 EA HARTZL HCC4Y HCC4YR2 GL DUAL MAGNETO WORN W A UNSCHED LANDING E J VIBRATION/BUFFET WARNING INDICATION CR CRUISE 1 CA 1335 4072013 (CAN) PILOT EXPERIENCED ROUGH RUNNING ENGINE SHORTLY AFTER TAKEOFF. INSPECTION OF THE MAGNETO REVEALED A SEVERLY WORN BR ONZE BUSHING ON THE DISTRIBUTOR BLOCK. ROUGH RUNNING WAS ATTRIBUTED TO INTERNAL CONTAMINATION OF THE MAGNETO WITH FINE B RONZE FILINGS, PARTIALLY SHORTING THE CONTACTS. 1 L 7 2 3O 3 O A20SO E14EA 5 C P52GL 2001073000321 20010730 00321 NM 2001 7 30 CA010625035 1 20010625 G 3246 2601450 WHEEL BOEING 737 737200 1384453 NM MLG CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 467 (CAN) DURING TEAR DOWN FOR OVERHAUL CRACK WERE DISCOVERED EMANTAING FROM THE BEARING CUP BORE AND EXTENDING INTO THE SPO KE WEBS ABD REACHING TO WITHIN 1" OF SPLITTING THE HUB. THE PART WAS BER'D THE LAST OVERHAUL INCLUDED LIQUID PENETRANT I NSPECTION AND HIGH FREQUENCY EDDY CURRENT INSPECTION AT WHICH TIMENO ANOMALIES WERE INDICATED. 2 L 7 2 4F A16WE 2001073000322 20010730 00322 CE 2001 7 30 CA010625037 1 20010514 G 3213 14504A20100J WASHER CESSNA 208B CESSNA 208 208B 2073701 CE PWA PT6 PT6A114A 52043 NE MCAULY 3AF34C 3GFR34C703 GL TRUNNION BROKEN W K NONE O OTHER IN INSP/MAINT 1 CA 2255 26410081 (CAN) DURING INSPECTION, MAINTENANCE FOUND THE PIN SECURING THE MAIN LANDING GEAR SPRING (LEG) HAD MOVED AFT APPROXIMATE LY 3/4 OF AN INCH.MAINTENANCE CONCLUDED WASHER (ITEM 28-FORWARD) WAS DISHED AND FRACTUR ED DUE TO OVERTORQUING OF BOLT ( ITEM 30) AND NUT.T HE TWO WASHERS (ITEM28) ARE FOR THE PURPOSE OF RETAINING PIN (ITEM 27) WITHIN ITS BORE. REF:FIGURE 01 ,32-10-00 OF THE 208 IPC 1 H 7 1 3T 3 T A37CE E4EA 5 C P60GL 2001073000323 20010730 00323 CE 2001 7 30 CA010625038 1 20010522 G 5521 115610010169 RIB BEECH 115610010347 BEECH 100 100BEECH 1152916 CE PWA PT6 PT6A28 EA ELEVATOR CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 8742 (CAN) WHEN REMOVING RH ELEVATOR FOR INSTALLATION OF UPDATE KIT # 100-4005-1SWAS FOUND INBOARD RIB CRACKED TWO PLACES AT FORWARD END. RIB REPLACED WITH FACTORY NEW. 1 L 7 2 3T 4 T A14CE E4EA 2001073000324 20010730 00324 CE 2001 7 30 CA010625039 1 20010606 G 2750 12602442 TUBE CESSNA 12602441 CESSNA 206 U206G 2073356 CE CONT O520 IO520F 17032 SO MCAULY D3A34 D3A34C404 GL TE FLAP BROKEN W K NONE O OTHER IN INSP/MAINT 1 CA 6441 (CAN) FOUND DURING A SCHEDULED 200 HOUR INSPECTATION. TUBE ASSY BROKE AT A POINT OF APPROX. 3/8" OUTBOARD OF THE INBOARD ROD END. (AT THE BASE OF THE THREADS). TUBE THEN RESTED ON TOP OF THE FLAP MOTOR AND BELLCRANK. 1 H 7 1 3O 3 O A4CE E5CE 5 C P47GL 2001073000325 20010730 00325 EA 2001 7 30 CA010625043 2 20010515 G 8530 16T19468 EXHAUST VALVE LW12966 PIPER PA31 PA31350 7103110 SO LYC O540 TIO540J2BD 41532 EA ENGINE DAMAGED W K NONE O OTHER IN INSP/MAINT 1 CA J3151 (CAN) ON GROUND RUN PILOT REPORTED R/H ENGINE RUNNING ROUGH. MAINTENANCE FOUND #2CYLINDER, EXHAUST VALVE SEAT DISLODGED, DAMAGING THE PISTON. ENGINE HAD METAL CONTAMINATION. ENGINE FIREWALL FORWARD REPLACEDWITH O/H UNIT AND COMPONENTS AND H OSES. CYLINDER ASSY HAD 596.4 HOURS SINCE REPAIR. 1 L 7 2 3O 3 O A20SO E14EA 2001073000326 20010730 00326 EA 2001 7 30 CA010625044 2 20010611 G 8520 T10540J2BD CONNECTING ROD CONT TIO540J2BD PIPER PA31 PA31350 7103110 SO LYC O540 TIO540J2BD 41532 EA ENGINE FAILED W C ABORTED TAKEOFF E VIBRATION/BUFFET TO TAKEOFF 1 CA 2418 L798161A (CAN) ON TAKEOFF FROM YVG (VERMILION) THE PILOT NOTICED THE LH ENGINE STARTED TO RUN ROUGH AND LOSE POWER. THE ENGINE TH EN STARTED TO VIBRATE BADLY AT WHICH POINT THE PILOT STOPPED AND FEATHERED THE # 1 ENGINE. THE AIRCRAFT RETURNED TO VERM ILION WHERE MAINTENANCE CHANGED THE #1 ENGINE. UPON INSPECTION, MAINTENANCE FOUND THE # 6 CYLINDER CONNECTING ROD DETATC HED FROM PISTON. SUBSEQUENT ROTATION OF ENGINEAND CONNECTING ROD CAUSED SEVERE DAMAGE TO CRANKCASE AND CAMSHAFT VISIBLE THROUGH HOLE IN CRANKCASE ABOVE # 5 CYLINDER CASUING ENGINE STOPPAGE. THE ABOVE ENGINE WAS RUNNING ON CONDITION. WE ARE PRESENTLY REVIEWING OUR ON CONDITION PROCEDURES. 1 L 7 2 3O 3 O A20SO E14EA 2001073000327 20010730 00327 NM 2001 7 30 CA010625046 1 20010530 G 2612 FIRE DETECTOR BOEING 737 7372H4 138448C NM PWA JT8 JT8D9A 52048 NE APU SHORTED W F ACTIVATE FIRE EXT. J WARNING INDICATION CR CRUISE 1 CA (CAN) IN CRUISE 15 MIN AFTER APU SHUT DOWN. APU FIRE WARNING OCCURED. FIRE HANDLED PULLED AND BOTTLE DISCHARED. FIRE IND ICATION TERMINATED. AFTER APPROX. 30 SEC. FIRE TEST CARRIED OUT, ALL INDICATIONS NORMAL. FLIGHT CONTINUED NO FURTHER PRO BLEM. INVESTIGATION ON GROUND FOUND NO EVIDENCE OF FIRE OR OVER HEATING DAMAGE TROUBLE SHOOTING OF LOOPS AND WIRING FOUN D NO FAULTS. A/C DISPATCH WITH MEL ON DISCHARGED BOTTLE AND MEL ON FIRE DETECTION SYSTEM.. 2 L 7 2 4F 4 F A16WE E2EA 2001073000328 20010730 00328 SW 2001 7 30 CA010625047 1 20010525 G 5302 205030899009 SKIN BELL BELL 204 204B 1181404 SW LYC T53 T5313B 41549 NE TAIL BOOM CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) CRACK IN SKIN DUE TO BROKEN STIFFENER INSIDE FIN. APPROX LOCATION IS FSTA 444.75, WATERINE 85 RIGHT BUTTLINE 3.0. STIFFENER P/N 205-030-899-036 ALSO RIB P/N 204-030-827-015 WAS DAMAGED BY BROKEN STIFFENER. 1 G 7 1 4U 4 U H1SW E17EA 2001073000330 20010730 00330 NE 2001 7 30 CA010625051 2 20010622 G 7323 4301121204 GOVERNOR BOLKMS 117 BK117A4 5626017 EU LYC LTS101 LTS101650B1 41560 NE POWER TURBINE FAILED W K NONE O OTHER IN INSP/MAINT 1 CA 1005 (CAN) TORQUE SPLITS COULD NOT BE BROUGHT INTO SPLE WITH ALLOWABLE AIRFRAME ADJUSTMENTS AND PERCENTAGE OF SPLITTING WOULD VARY AT EACH CYCLE. 1 G 7 2 3U 3 U H13EU E5NE 2001073000331 20010730 00331 CE 2001 7 30 CA010625052 1 20010614 G 2710 35524238124 RETAINER BEECH 55 95A55 1152704 CE CONT O470 IO470L 17026 SO MCAULY 2AF36C 2AF36C39 GL AILERON MISSING W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) DURING SCHEDULED MAINTENANCE IT WAS FOUND THAT THE LOWER CONTROL ARM RETAINER WAS MISSING. UPON FURTHER INVESTIGAT ION, IT WAS FOUND LYING IN THE BELLY OF THE AIRPLANE. IT WAS ALSO NOTED THAT THE UPPERCONTROL ARM RETAINER WAS ATTACHED WITH ONLY ONE OF TWO SCREWS WAS THE INCORRECT STYLE. 1 L 7 2 3O 3 O 3A16 3E1 5 C P911 2001073000335 20010730 00335 CE 2001 7 30 CA010626006 1 20010524 G 3212 5801 SWITCH CESSNA 185 A185F 2072821 CE CONT O520 IO520D 17032 SO MCAULY 2A34C D2A34C58 GL FLOAT FAILED W O OTHER J WARNING INDICATION AP APPROACH 1 CA (CAN) ON GEAR EXTENSIONFOR LANDING IN PRINCE ALBERT SASK. THE RH MAIN GEAR DOWN INDICATOR LIGHT DID NOT ILLUMINATE. AFTE R TESTING THE SYSTEM AND HAVING THE SAME RESULTS, THE PILOT ELECTED TO LAND AND DID SOWITHOUT INCIDENT. ON THE GROUND, T ESTING REVEALED THAT THE PROXIMITY SWITCH FOR THE RH MAIN GEAR WOULD FAIL INTERMITTANTLY. AS A PRECAUTION THE OTHER SWIT CHES WERE ALSO TESTED AND THE LH NOSE WHEEL A LSO FAILEDINTERMITTANTLY. NEW SWITCHES HAVE BEEN ORDERED TO REPLACE THE FA ULTY ONES. BOTH SWITCHES ARE THE SAME PART NUMBER. AS A MATTER OF INTEREST THE LANDING GEAR HAD BEEN SWUNG AS MANY AS TH IRTY TIMES THAT DAY BEFORE WITHOUT FAILURE WHILE TROUBLE SHOOTING A DIFFERENT DISCREPENCY. 1 H 7 1 3O 3 O 3A24 E5CE 5 C P3EA 2001073000336 20010730 00336 NM 2001 7 30 CA010626007 1 20010527 G 6210 369D21102523 BLADE DOUG 600N 600N 3027377 NM ALLSN 250C 250C47M 03013 GL MAIN ROTOR CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 642 (CAN) A/C STOPPED FOR REFUELING, DUE TO THE TQ EVENTS THAT HAD BEEN ACCUMULATED, (160) THE PILOTS CARRIED OUT A BLADE TO RQUE EVENT INSPECTION I.A.W. SB600N-031. THEY FOUND THE WHITE BLADE TO BE CRACKED, BOTTOM SIDE, 12.5" O/B OF THE LAST BO LT ON THE BLADE GRIP, 2.25" I/B OF THE SERIAL # DATA PLATE, MID WAY IN THE BLADE, CRACK WAS MEASURED TO BE .75" LONG, BU T THE PILOTS CONFIRMED THAT THE CRACK WAS LONGER WITH THE BLADE SUPPORTED OFF THE DROOP STOP RING, AND WAS SAID TO RUN T O .25" FROM THE TRAILING EDGE, ESTIMATING THE CRACK TO BE 2.5" TO 3.0" LONG IN LENGTH. 1 G 7 1 3U 3 U NC H3WE E1GL 2001073000337 20010730 00337 NM 2001 7 30 CA010626008 1 20010612 G 2520 2A0590174 TUBE BOEING 757 757236 NM RROYCE RB211 RB211535E437 54555 NE SEAT CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) TORQUE TUBE CRACKED WHERE THE CUTOUT HAS BEEN MADE FOR THE WIRING TO GO THROUGHT. THIS IS THE SECOND SEAT WE FIND WITH THE SAME PROBLEM. 2 L 7 2 4F 4 F RT A2NM E12EU 2001073100040 20010731 00040 EA 2001 7 31 CA010626019 1 20010530 G 3610 320207231 CHECK VALVE CNDAIR CL600 CL6002B16 1900305 EA GE CF34 CF343B1 NE APU FAILED W A UNSCHED LANDING J WARNING INDICATION CL CLIMB 1 CA (CAN) DURING APU BLEED TRANSITION TO ENGINES THE APU LCV FAIL LIGHT CAME ON AND OPEN LIGHT REMAINED ON. ABOUT 15 SECONDS THE RT FIRE INDICATION APPEARED, CREW THROTTLED BACK JUST BELOW 70 PERCENT N1 AND THE FIRE WENT OUT. CREW SHUTDOWN ENGI NE AND DECLARED EMERGENCY AND LANDED UNEVENTUALLY AT LAX. FOLLOW UP: FOUND LCV AND FIRE LOOP BAD. ALSO FOUND THE FLAPPER S FOR THE CHECK VALVE ABOVE THE LCV MISSING. FOUND BOTH FLAPPERS OF CHECK VALVE, ALSO FOUND RT STATER DAMAGE POSSIBLE FR OM CHECK VALVE PIECES. PARTS REPLACED AND RETURNED TO SERVICE. 2 L 7 2 4F 4 F RT A21EA E15NE 2001073100041 20010731 00041 EA 2001 7 31 CA010626020 1 20010417 G 7110 ACCESS DOOR CNDAIR CL600 CL6002B19 EA GE CF34 CF343B1 NE NOSE COWL MISSING W O OTHER D INFLIGHT SEPARATION LD LANDING 1 CA (CAN) AFTER AIRCRAFT LANDED AT CHICAGO O'HARE, IT WAS NOTICED T HAT THE NOSE COWL LOWER ACCESS PANEL (228-50081-142) WAS ON THE RUNWAY. OTHER DAMAGED PARTS WERE NOSE COWL UPPER ACCESS PANEL 228-50080-158 AND COVER ASSEMBLY 228-50793-120. PR IOR TO THIS EVENT THE AIRCRAFT WAS DOWN FOR ROUTINE MAINTENANCEAN D WORK WAS PERFORMED ON THE THRUST REVERSER SYST EM DU E TO A MMEL. 2 L 7 2 4F 4 F RT A21EA E15NE 2001073100043 20010731 00043 EA 2001 7 31 CA010626022 1 20010528 G 2421 GENERATOR DHAV DHC8 DHC8311 1386006 EA PWA PW120 PW123 NE HAMSTD 14SF 14SF15 NE NR 1 FAILED W A UNSCHED LANDING H J ELECT. POWER LOSS-50 PC WARNING INDICATION CL CLIMB 1 CA 9014 (CAN) SHORTLY AFTER TAKEOFF, NR 1 AC GENERATOR FAILURE WARNING CAME UP. THE GENERATOR SYSTEM WAS RESETED IAW THE FMP, WI THOUT SUCCESS. THE GENERATOR WAS THEN DEACTIVATED AND ISOLATED IAW THE FMP.THE GENERATOR WS REPALCED AN THE AIRCRAFT WS RELEASED FOR SERVICE WITHOUT FURTHER INCIDENTS. 2 H 7 2 4T 4 T RT A13NM E20NE 6 C P7NE 2001070500013 20010705 00013 NM 2001 7 5 CA010626024 1 20010430 G 7830 312N53217 DUCT BOEING LJ76579 BOEING 757 757236 NM RROYCE RB211 RB211535E437 54555 NE JOINT SLEEVE LEAKING W H DEACTIVATE SYST/CIRCUITS J WARNING INDICATION NR NOT REPORTED 1 CA (CAN) #1 ENG THRUST REVERSER DEACTIVATED AS PER MEL. INVESTIGATION FOUND THE PYLON MOUNTED FAN THRUSR REVERSER ELECTRICA L HARNESS PN LJ6579 AND LJ 76580 MELTED AND HEAVELY DAMAGED. HOT AIR LEAK FROM HP2 ANDHP7 BLEED AIR DUCT PN 312N5321-7 A ND 312N5306-1 ALSO CAUSED LH THRUST REVERSER HYD LINES AND PROTECTION SLEEVE TO OVERHEAT. #1 THRUST REVERSER UPPER FEEDB ACK CABLE FOUND DAMAGED AND SEIZED AND FAILED THE STIFFNESS CHECK, PARTS REPLACED. 2 L 7 2 4F 4 F RT A2NM E12EU 2001073100044 20010731 00044 CE 2001 7 31 CA010626026 1 20010502 G 2823 M83248110111 O-RING CESSNA 206 T206H CE LYC O540 TIO540AJ1A EA FUEL SELECTOR LEAKING W O OTHER K B FLUID LOSS SMOKE/FUMES/ODORS/SPARKS LD LANDING 1 CA 104 (CAN) DURING APPROACH AND LANDING A FUEL ODOR WAS APPARENT. INVESTIGATION OF THE REPORTED SNAG REVEALED THAT THE FUEL SE LECTOR WAS LEAKING AND SOME FUEL HAD ACCUMULATED IN THE FUSELAGE, UNDER THE CABIN F LOOR. 1 H 7 1 3O 3 O A4CE E14EA 2001073100045 20010731 00045 NM 2001 7 31 CA010626027 1 20010607 G 2400 FCC4008 RELAY BOEING 737 7372E1 138448F NM PWA JT8 JT8D9A 52048 NE COCKPIT FAILED W A UNSCHED LANDING J WARNING INDICATION CL CLIMB 1 CA (CAN) DURING CLIMB OUT, ALL LIGHTS ON FORWARD PANEL, AND GLARESHIELD ILLUMINATED. AIRCRAFT RETURNED WITHOUT INCIDENT. WH ILE TROUBLE SHOOTING THE R33 RELAY WAS INTERCHARGED WITH THE R41 AND THIS SOLVED THEUNSERVICEABILITY. A NE W R33 RELAY W AS INSTALLED AND SYSTEM WAS TESTED SERVICEABLE. NO FURTHER INCIDENT DURING SUBSEQUENT FLIGHT. 2 L 7 2 4F 4 F A16WE E2EA 2001073100046 20010731 00046 EA 2001 7 31 CA010626028 1 20010612 G 3244 TIRE CNDAIR CL601 CL6012A12 1900303 EA GE CF34 CF343A 30015 NE MLG FAILED W C ABORTED TAKEOFF O OTHER TO TAKEOFF 1 CA (CAN) THREAD SEPARATION ON TAKEOFF WHICH INDUCED DAMAGE TO WHEEL WELL AREA. 2 L 7 2 4F 4 F RT A21AE E15NE 2001073100047 20010731 00047 EA 2001 7 31 CA010626029 1 20010613 G 5246 215310326 WEB CNDAIR CL215 CL2151A10 EA PWA R2800 CA3 52026 NE WATER DOOR CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) FOLLOWING THE INCIDENT REPORTED ON A/C CL215-1A10 S/N 1076 (SDR DATED 00-08-24) BOMBARDIER AMO 35-95 DECIDED TO CA RRY OUT A SPECIAL INSPECTION ON HIS FLEET. THE WEB P/N 215-31032-6 HAS BEEN FOUND CRACKED BEHIND RH AND LH UPLOCK SPIGOT S AND WATER DOOR ACTUATOR SPIGOTS IN WATER SYSTEM APPROX. FS368.5 ON VARIOUS A/C AND VARIOUS DEGREE. BOMBARDIER ENGINEER ING HAS PRODUCED DIFFERNET REPAIR ENGINEERING ORDERS AND TWO GENERAL REAPIR APPLICABLE TO ALL CL215. REO 215-53-10-75 (W ATER DOOR ACTUATOR MOUNTING LUGS) AND 215-53-10-093 (UPLOCK ACTUATOR MOUNTING LUGS. THE FOLLOWING A/C HAVE BEEN INSPECTE D AND REPAIRED 2 H 7 2 4R 4 R A14EA E231 2001073100056 20010731 00056 NE 2001 7 31 CA010626043 2 20010520 G 7261 SUMP CNDAIR CL600 CL6002B19 EA GE CF34 CF343A1 30015 NE ENGINE COKED W E ENGINE SHUTDOWN Y J ENGINE STOPPAGE WARNING INDICATION AP APPROACH 1 CA (CAN). NR 2 ENGINE SHUT WITHOUT PILOT'S INPUT DURING THE APPROACH PHASE OF THE FLIGHT, APPROX 3500 FEET. UPON INSPECTION , MAINTNANCE NOTED: OIL DETECTED IN THE TAILPIPE, ENGINE QUANTITY CHECKED AND FOUND DEPLETED, AND SUMP B SCREEN COKED UP . ENGINE REPLACED AND A/C RETURNED TO SERVICE. 2 L 7 2 4F 4 F RT A21EA E15NE 2001073100057 20010731 00057 NM 2001 7 31 CA010626044 1 20010617 G 3260 DOWNLOCK SENSOR BOEING 737 7372H4 138448C NM PWA JT8 JT8D9A 52048 NE NLG FAILED W A UNSCHED LANDING N FALSE WARNING AP APPROACH 1 CA (CAN) NOSE GEAR TRANSIT LIGHT ILLUMINATED WHEN GEAR SELECTED DOWN. CREW CYCLED GEAR A COUPLE OF TIMES WITH NO RESULTS. A VISUAL CHECK THROUGH FLOOR HOLE VIEWER ATTEMPTED. NOSE GEAR VIEWER HARD TO DETERMINE VISUAL ON RED LINES FOR A LOCKED C ONDITION.THE CREW OPTED TO RETURN TO STATION OF ORIGIN WITH AN UNEVENTFUL LANDING. THE A/C WAS FERRIED TO THE MAIN BASE FOR MAINTENANCE. MAINTTENANCE TESTED AND CONSEQUENTLY REPLACED THE NLG DOWN LOCK SENSOR. AS A PRECAUTION THE NLG VIEWER WAS CLEANED AND THE DOWNLOCK INDICATOR ARROWS WERE REPAINTED. 2 L 7 2 4F 4 F A16WE E2EA 2001073100058 20010731 00058 EA 2001 7 31 CA010626045 1 20010619 G 3244 299K631 TIRE CNDAIR CL600 CL6002B19 EA GE CF34 CF343B1 NE MLG FAILED W A UNSCHED LANDING J WARNING INDICATION CL CLIMB 1 CA (CAN) AFTER TAKE OFF AT GEAR RETRACTION, THE CREW NOTED A LEFT MAIN LANDING GEAR DISAGREEMENT. THE AIRCRAFT RETURNED AND LANDED WITHOUT INCIDENT. MAINTENANCE PERSONNEL INSPECTED ANDFOUND THAT THE TREADHAD SEPARATED FROM THE LEFT INBOARD MAI N GEAR TIRE DURING THE TAKE OFF ROLL. COLLATERAL DAMAGE TO THE LEFT INBOARD FLAP AND MAIN GEAR DOOR BELL CRANK WERE ALSO OTED. THE FLAP ASSEMBLY P/N 601R14002-1 AND THE LEFT MAIN GEAR DOOR BELL CRANK P/N 601R31185-15 WERE ALSO REPLACED. 2 L 7 2 4F 4 F RT A21EA E15NE 2001070500014 20010705 00014 EA 2001 7 5 CA010626046 1 20010619 G 5610 WINDSHIELD PPG NP1393219 CNDAIR CL600 CL6002B19 EA GE CF34 CF343B1 NE WINDSHIELD CRACKED W A UNSCHED LANDING O OTHER CL CLIMB 1 CA 5572 98343H4828 (CAN) PASSING THROUGH 8,000 FT. THE WINDSHIELD DEVELOPED A CRACK AND SHATTERED. AFTER THE EVENT THE AIRCRAFTIMMEDIATELY RETURNED FORA WINDSHIELD REMOVAL AND REPLACEMENT. 2 L 7 2 4F 4 F RT A21EA E15NE 2001073100060 20010731 00060 EA 2001 7 31 CA010626049 1 20010524 G 5720 STRUCTURE CNDAIR CL600 CL6002B19 EA GE CF34 CF34* NE RT WING DAMAGED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) DURING PREFLIGHT INSPECTION MECHANIC OBSERVED THAT THE RT WING TIP HAD BEEN DAMAGED BY CONTACT WITH A HARD OBJECT 9LIKE A RUNWAY) THE WINGTIP FAIRING HAD BEEN GROUND DOWN TO THE UNDERLYING STRUCTURE AND ALSO DAMAGE THE WING EXTENSION LOWER SKIN. WING EXTENSION LOWER SKIN AND WING TIP FAIRING REPLACED WITH NEW PARTS. SKIN DOUBLER REPAIRED PER REO 601R-5 7-31-279. 2 L 7 2 4F 4 F RT A21EA E15NE 2001073100061 20010731 00061 EA 2001 7 31 CA010626050 1 20010524 G 2751 TRANSMITTER CNDAIR CL600 CL6002B19 EA GE CF34 CF343A1 30015 NE TE FLAP FAILED W O OTHER N FALSE WARNING AP APPROACH 1 CA (CAN) ON APPROACH AFTER SELECTING FLAP DOWN, CREW NOTICED THAT THE FLAP INDICATION WAS DIFFERENT FROM LEFT TO RIGHT. MAI NTENANCE INSPECTED FLAP SYSTEM AMD FOUND FUNCTIONING NORMALLY. RT FLAP POSITION TRANSMITTER WAS DEFERRED PER MEL. 2 L 7 2 4F 4 F RT A21EA E15NE 2001073100063 20010731 00063 2001 7 31 CA010627008 4 20010612 G 3416 215T5100876 NIPPLE BOMBDR CNDAIR CL215 CL2156B11215 EA STATIC PORT WRONG PART W K NONE W INADEQUATE Q C IN INSP/MAINT 1 CA (CAN) A NIPPLE FITTING INSTALLED AT THE STATIC PORT OF THE ALTIMETER WAS FOUND TO BE THE WRONG TYPE HAVING AN OPENING OF .032 INCH INSTEAD OF THE RECOMMENDED .008 INCH. THIS COULD HAVE CAUSED PROBLEMS IN CALIBRATING THE ALTIMETER ABD FURTHE R MORE , SHOULD FITTINGS DIFFER FROM PILOT TO CO-PILOT SIDE, THE INDICATIONS WILL LAG IN CLIMB ABD DESCENT BUT WILL BE C ORRECT AT LEVEL FLIGHT. A BOMBARDIER SERVICE PROBLEM 34-12-00-001 WAS OPENED UP IN ORDER TO CORRECT THIS DISCREPENCY. 2 H 7 2 4T RT A14EA 2001073100066 20010731 00066 NM 2001 7 31 CA010627010 1 20010527 G 2612 CONNECTOR BOEING 737 737201 1384454 NM PWA JT8 JT8D9A 52048 NE NR 2 ENGINE DIRTY W O OTHER N FALSE WARNING CR CRUISE 1 CA (CAN) WHIE ENROUTE TO YYC, NR 2 ENGINE FIRE WARNING LIGHT AND BELL CAME ON. NO EVERHEAT LIGHT CAME ON. ENGINE SECURED AN D AIRCRAFT LANDED IN YYC WITHOUT INCIDENT. ALL CONNECTOR PLUGS CHECKED AND CLEANED. MEL 26-2 RAISED. DMI 29776. FIRE BOT TLES REPLACED IAW MM 26-21-11. NO FURTHER INCIDENT DURING SUBSEQUENT FLIGHT. 2 L 7 2 4F 4 F A16WE E2EA 2001073100068 20010731 00068 NM 2001 7 31 CA010627011 1 20010507 G 5242 SWITCH BOEING 737 7372E1 138448F NM PWA JT8 JT8D9A 52048 NE E/E BAY DOOR OBSTRUCTED W O OTHER D INFLIGHT SEPARATION DE DESCENT 1 CA (CAN) DURING FLIGHT, E& E BAY DOOR OPENED AND AIRCRAFT LANDED WITHOUT INCIDENT. E& E BAY DOOR SWITCH STICKER WAS JAMMING THE SWITCH IN THE DEPRESSED MODE. THE OBSTRUCTION WAS REMOVED AND THE DOOR CLOSED. INDICATION TESTED IAW MM 2-71-00 AND CHECKED SERVICEABLE. NO FURTHER INCIDENT SUBSEQUENT FLIGHT. 2 L 7 2 4F 4 F A16WE E2EA 2001073100069 20010731 00069 NM 2001 7 31 CA010627012 1 20010515 G 5414 PANEL BOEING 737 7372E1 138448F NM PWA JT8 JT8D9A 52048 NE RT NACELLE MISSING W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) DURING A MAINTENANCE CHECK, IT WAS OBSERVED THAT THE RT AFT NACELLE PANEL WAS MISSING. SERVICEABLE PANEL WAS INSTA LLED. NO FURTHER INCIDENT DURING SUBSEQUENT FLIGHT. 2 L 7 2 4F 4 F A16WE E2EA 2001073100070 20010731 00070 2001 7 31 CA010627013 4 20010501 G 2312 STATIC WICK BOEING 737 7372H4 138448C NM PWA JT8 JT8D9A 52048 NE COMM SYSTEM WORN W O OTHER O OTHER DE DESCENT 1 CA (CAN) DURING DECEND AND FLYING THROUGH PRECIPITATION, BOTH VHF RADIOS HAD HEAVY STATIC. AIRCRAFT LANDED WITHOUT INCIDENT . 5 STATIC DISCHARGERS WERE FOUND OUT OF LIMITS. ALL REPLACED IAW MM 23-61-00. NO FU RTHER INCIDENT DURING SUBSEQUENT FL IGHT. 2 L 7 2 4F 4 F A16WE E2EA 2001070500015 20010705 00015 NM 2001 7 5 CA010627014 1 20010509 G 3700 BACH30BC060332 LINE BOEING 737 7372A9C 1384495 NM PWA JT8 JT8D9A 52048 NE RH PITOT STATIC WORN W K NONE O OTHER CR CRUISE 1 CA (CAN) AT CRUISE, FIRST OFFIER'S AIRSPEED INDICATION WASERRATIC, AIRCRAFT LANDED WITHOUT INCIDENT. FOUND PITOT STATIC LIN ES WORN. LINES REPLACED AND TESTED SERICEABLE IAW MM34-11-0. NO FURTHER INCIDENT DURING SUBSEQUENT FLIGHT. 2 L 7 2 4F 4 F A16WE E2EA 2001073100071 20010731 00071 WP 2001 7 31 CA010627015 1 20010528 G 5610 WINDSHIELD HUGHES 369 369D 4470706 WP ALLSN 250C 250C20B 03013 GL COCKIT CRACKED W A UNSCHED LANDING O OTHER CR CRUISE 1 CA (CAN) DURING FLIGHT F5890 FROM MADRID TO LYON, INCRUISE CO-PILOT WINDSHIELD INNER PLY CRACKED, UNSCHEDULED LANDING IN BI ARRITZ. RT WINDSHIELD REPLACED. A/C RETURNED TO SERVICE. 1 G 7 1 3U 3 U H3WE E4CE 2001073100073 20010731 00073 EA 2001 7 31 CA010627021 1 20010529 G 7120 WEB BOMBDR 60135006 CNDAIR CL600 CL6002B19 EA GE CF34 CF343B1 NE ENGINE SUPPORT CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 19301 (CAN) DURING "C" CHECK, SIX CRACKS WERE FOUND INTHE ENGINE SUPPORT BEAM. TWO CRACKS WERE LOCATED ON THE LOWER WEB AT FS 640.0 BETWEEN LBL 9.5 AND RBL 9.5. FOUR CRACKS WERE LOCATED ON THE UPPER WEB AT FS 640 BETWEEN LBL 9.5 REPAIR PERFORMED PER REO 601R-53-61-345. 2 L 7 2 4F 4 F RT A21EA E15NE 2001073100075 20010731 00075 NE 2001 7 31 CA010627025 2 20010612 G 7261 PUMP CNDAIR CL600 CL6002B19 EA GE CF34 CF343B1 NE ENGINE OIL FAILED W E ENGINE SHUTDOWN J WARNING INDICATION CR CRUISE 1 CA (CAN) NR 2 ENGINE OIL PRESSRE BEGAN TO FLUCTATE DURING CRUISE. THE PRESSURE DROP FOLLOWED BY AN INCFREASE IN OIL TEMP. T HE PILOT INITIATED AN IN FLIGHT SHUTDOWN. ENGINE OIL PUMP REPLACED. 2 L 7 2 4F 4 F RT A21EA E15NE 2001073100077 20010731 00077 NE 2001 7 31 CA010627032 2 20010517 G 7261 ENGINE CNDAIR CL600 CL6002B19 EA GE CF34 CF343B1 NE OIL SYSTEM MALFUNCTIONED W A UNSCHED LANDING J WARNING INDICATION CR CRUISE 1 CA (CAN) DURING CRUISE FLIGHT CREW REPORTED LOW OIL PRESSURE AND ASSOCIATED WITH HIGH OIL TEMPERATURE. ENGINE REPLACED AND A/C RETURNED TO SERVICE. 2 L 7 2 4F 4 F RT A21EA E15NE 2001073100078 20010731 00078 NE 2001 7 31 CA010627034 2 20010619 G 7261 OIL SYSTEM CNDAIR CL600 CL6002B19 EA GE CF34 CF343B1 NE ENGINE FLUCTUATES W E A ENGINE SHUTDOWN UNSCHED LANDING J WARNING INDICATION CR CRUISE 1 CA (CAN) A/C IN CRUISE AT FL.310, CREW NOTICED FLUCTATION IN OIL PRESSURE WITH A LOSS OF OIL PRESSURE. ENGINE SHUT DOWN BY THE FLIGHT CREW AND LANDED IN PHOENIX. INVESTIGATING AT THIS POINT SHOWS OIL TANK AS GOOD. OIL LEVEL IN GEARBOX IS GOOD. GE ON WING SUPPORT IS ON SITE TO HELP WITH INVESTIGATION. FSR HAS REQUESTED THAT THE MDC BE DOWNLOADED AND THE DFDR BE DOWNLOADED. 2 L 7 2 4F 4 F RT A21EA E15NE 2001073100080 20010731 00080 SW 2001 7 31 CA010627040 1 20010627 G 5302 206031418005 SUPPORT BRACKET BELL 206031004 BELL 206 206B 1181511 SW ALLSN 250C 250C20 03013 GL TAIL BOOM BROKEN W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) THE FLANGE FOR THE VERTICAL FIN UPPER ATTACHMENT BOLT IS SEPARATED FROM SUPPORT DUE TO CRACK. 1 G 7 1 3U 3 U H2SW E4CE 2001073100082 20010731 00082 CE 2001 7 31 CA010627042 1 20010622 G 2434 7565T1 ALTERNATOR CESSNA 305 305A 2074002 CE CONT O470 O47011B 17026 SO ENGINE FAILED W K NONE O OTHER IN INSP/MAINT 1 CA 6 (CAN) ALTERNATOR REMOVED FROM AIRCRAFT AFTER PILOT REPORTED NO INDICATION OF CHARGE AFTER HIS LAST LANDING. AFTER MAKING A FEW TEST, IT WAS DETERINED THAT THE ALTERNATOR WAS FAULTY. THIS NEW ALTERNATOR WAS INSTALLED ON THE AIRCRAFT AS A REP LACEMENT FOR THE PREVIOUS DEFECTIVE ALTERNATOR. UPON REMOVAL OF THE DEFECTIVE ASSEMBLY NO EXTERIOR DAMAGES WAS FOUND THA T COULD HAVE LEAD TO THE FAILURE. SOMETHING INSIDE THE ALTERNATOR HAD FAILED BUT SINCE THE ALTERNATOR IS PARTIALLY SEAL ED AND IS ON WARRANTY COVERAGE NO FURTHER ACTION WAS TAKEN TO INVESTIGATE TH FAILED ASSEMBLY. 1 H 7 1 3O 3 O 5A5 E269 2001073100084 20010731 00084 CE 2001 7 31 CA010627043 1 20010621 G 2434 7565T1 ALTERNATOR CESSNA 305 305C 2074014 CE CONT O470 O47011B 17026 SO ENGINE FAILED W K NONE O OTHER IN INSP/MAINT 1 CA 1 (CAN) ALTERNATOR REMOVED FROM AIRCRAFT AFTER PILOT REPORTED NO INDICATION OF CHARGE AFTER HIS LAST LANDING. AFTER MAKING A FEW TEST, IT WAS DETERMINED THAT THE ALTERNATOR WAS FAULTY. THIS NEW ALTERNATOR WAS INSTALLED ON THE AIRCRAFT AS A RE PLACEMENT FOR THE PREVIOUS DEFECTIVE ALTERNATOR. UPON REMOVAL OF THE DEFECTIVE ASSEMBLY, A SMALL PIECE FELL OFF BY VENT DUCT OF THE SHROUD OF THE ALTERNATOR. LOOKING CLOSELY AT THE PIECE IT WAS DETERMINED THAT THIS SMALL PIECE WAS A DIODE. THE DIODE SEEMED NOT DAMAGED OTHER THAN BEING UNSOLDERED FROM THE INTERNAL PART OF THE ALTERNATOR. IT WAS CERTAINLY NOT SOLDERED PROPERLY AND FAILED WITH THE VIBRATIONS OF THE AIRCRAFT. THE P/N OF THE DIODE COULD BE SEEN EASILY.PN. MR2504W0 1 H 7 1 3O 3 O 5A5 E269 2001073100099 20010731 00099 CE 2001 7 31 CA010627044 1 20010622 G 2434 7565T1 ALTERNATOR CESSNA 305 305A 2074002 CE CONT O470 O47011 17026 SO ENGINE FAILED W K NONE O OTHER IN INSP/MAINT 1 CA 4 (CAN) ALTERNATOR REMOVED FROM AIRCRAFT AFTER PILOT REPORTED NO INDICATION OF CHARGE AFTER HIS LAT LANDING. AFTER MAKING A FEW TESTS, IT WAS DETERMINED THAT THE ALTERNATOR WAS FAULTY. THIS OVERHAULED ALTERNATOR WS INSTALLED ON THE AIRCRAFT A S A REPLACEMENT FOR THE PREVIOUS DEFECTIVE ALTERNATOR. UPON REMOVAL OF THE DEFECTIVE ASSEMBLY, SMALL PIECES COULD BE HEA RD MOVING INSIDE THE ALTERNATOR. THE ALTERNATOR WAS SHAKEN TO TRY AND REMOVE THESE PIECES BY THE SHROUD AIR VENT BUT NON E FELL OUT. SINCE THE ALTERNATOR IS PARTIALLY SEALED AND IS ON WARRANTY COVERAGE NO FURTHER ACTION WAS TAKEN TO INVESTIG ATE THE FAILED PIECES. 1 H 7 1 3O 3 O 5A5 E269 2001073100101 20010731 00101 EA 2001 7 31 CA010627046 1 20010626 G 7120 SUPPORT BRACKET GE CF343A1 CNDAIR CL600 CL6002B19 EA GE CF34 CF343A1 30015 NE ENGINE CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 00 (CAN) BOMBARDIER AEROSPACE HAS JUST RECEIVED A REPORTALE SDR EVENT WHICH WE ARE REQUIRED TO REPORT ON. DURING INSPECTION OF ENGINE SUPPORT BEAM IAW SB A601R-53-059, MAINTENANCE FOUND CRACKS. REPAIR ENGINEERING ORDER PROGRESS, SHOULD BE PROV IDED TO THE OPERATOR SOON. 2 L 7 2 4F 4 F RT A21EA E15NE 2001073100102 20010731 00102 EA 2001 7 31 CA010627047 1 20010622 G 7120 SUPPORT BRACKET GE CF343A1 CNDAIR CL600 CL6002B19 EA GE CF34 CF343A1 30015 NE ENGINE CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 00 (CAN) DURING INSPECTION OF ENGINE SUPPORT BEA IAW SB A601R-53-059, MAINTENANCE FOUND CRACKS. REPAIR ENGINEERING ORDER PR OVIDED, REPAIR IN PROGRESS. 2 L 7 2 4F 4 F RT A21EA E15NE 2001073100103 20010731 00103 EA 2001 7 31 CA010627048 1 20010622 G 7120 SUPPORT BRACKET GE CF343A1 CNDAIR CL600 CL6002B19 EA GE CF34 CF343A1 30015 NE ENGINE CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 00 (CAN) DURING INSPECTION OF ENGINE SUPPORT BEAM IAW SB A601R-53-059, MAINTENANCE FOUND CRACKS. REPAIR ENGINEERING ORDER P ROVIDED, REPAIR IN PROGRESS. 2 L 7 2 4F 4 F RT A21EA E15NE 2001073100105 20010731 00105 SW 2001 7 31 CA010627051 1 20010627 G 2121 21036012 BLOWER GULSTM 690TP 690 0141720 SW GARRTT TPE331 TPE3315251K NM HARTZL HCB3T HCB3TN5 GL AIR DISTRIBUTION SEIZED W O OTHER B SMOKE/FUMES/ODORS/SPARKS NR NOT REPORTED 1 CA 40 (CAN) SMOKE ENTERED COCKPIT AFTER ORBITING FIRE FOR 20 MINUTES. GROUND BLOWER RESET CIRCUIT BREAKER TRIPPED OFF. COCKPIT CHECKED FOR DAMAGED WIRING. ENGINE BLEED AIR SUPPLY WAS INSPECTED FOR OIL CONTAMINATION NO DEFECTS NOTED. GROUND BLOWER INTAKE WAS INSPECTED NO OBSTRUCTION WAS NOTED. GROUND BLOWER UNIT REPLACED FUNCTION TESTED. THE AIRCRAFT WAS RETURNED T O SERVICE. 1 H 7 2 3T 4 T 2A4 E2WE 6 C P15EA 2001073100107 20010731 00107 SW 2001 7 31 CA010627052 1 20010519 G 6320 212040233001 TUBE BELL 212 212 1181420 SW PWA PT6 PT6A34 52043 EA TRANSMISSION OIL CRACKED W E A ENGINE SHUTDOWN UNSCHED LANDING K J FLUID LOSS WARNING INDICATION CR CRUISE 1 CA (CAN) DURING CRUISE 300 FT AGL, MAIN TRANSMISSION OIL PRESS WAS NOTICED FLUCTUATING. AN IMMEDIATE PRECAUTIONARY LANDING WAS CARRIED OUT. A/C WAS INTERMEDIATELY SHUT DOWN. UPON INVESTIGATION TUBE ASSY P/N 212-040-233-001 IN HELL HOLE WAS FOU ND LEAKING. TUBE REPLACED TRANSMISSION FILTER WAS INSPECTED NO CONTAMINATION WAS FOUND. 6 LITRES OF OIL WAS ADDED. (12 L MAX CAPACITY) AIRCRAFT GROUND RUN & RETURNED TO SERVICE. 1 G 7 1 4U 4 T H4SW E4EA 2001073100109 20010731 00109 CE 2001 7 31 CA010627053 1 20010625 G 5720 MS2001426 BOLT BEECH 55 95A55 1152704 CE CONT O470 IO470L 17026 SO MCAULY 2AF36C 2AF36C39 GL WING FAILED W K NONE O OTHER IN INSP/MAINT 1 CA 630 (CAN) UPON MPI IT WAS FOUND THAT 2 OF 4 WING BOLTS FAILED INSPECTION. IT WAS THANDETERMINED TO CHANGE ALL THE BOLTS. LOG ENTRY INDICATES BOLTS WERE LAST CHANGED IN 1992. THER IS NO RECORD OF BOLT INSPECTION SINCE THAT TIME ALTHOUGH INSPECTI ON IS CALLED FOR AFTER 5 YEARS. 1 L 7 2 3O 3 O 3A16 3E1 5 C P911 2001073100110 20010731 00110 SO 2001 7 31 CA010627054 1 20010608 G 3222 6705403 TRUNNION PIPER PA28 PA28RT201T 7102817 SO CONT O360 TSIO360FB 17025 SO HARTZL HCC3Y PHCC3YF1 GL NLG CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 2474 (CAN) WHILE INSPECTING SHIMMEY DAMPENER AS PART OF 100 HOUR INSPECTION. IT WAS DISCOVERED THAT THE NLG TRUNNION ASSEMBLY WAS CRACKED AT SHIMMEY DAMPENE R ATTACH POINT. 1 L 7 1 3O 3 O 2A13 E9CE 5 C P25EA 2001073100111 20010731 00111 CE 2001 7 31 CA010627055 1 20010615 G 3234 1013841379 SWITCH BEECH 200 B200 1152922 CE PWA PT6 PT6A42 52043 NE HARTZL HCB3T HCB3TN3 GL COCKPIT INTERMITTENT W O OTHER J WARNING INDICATION CL CLIMB 1 CA 6147 (CAN) WHEN LANDING GEAR SELECTED UP AFTER TAKE OFF, GEAR DID NOT RETRACT. GEAR SELECTED BACK DOWN WITH NORMAL DOWN AND L OCKED INDICATION ON ALL GEAR. NORMAL LANDING CARRIED OUT WITHOUT INCIDENT. TROUBLESHOOTING FOUND INTERMITTENT MIRCOSWITC H CONTACTS IN LANDING GEAR SELECTOR SWITCH ASSEMBLY WHEN HANDLE SELECTED UP. ASSEMBLY REPLACED AND GEAR SWINGS COMPLETED . NO FURTHER FAULTS. 1 L 7 2 4T 4 T A24CE E4EA 6 C P15EA 2001073100112 20010731 00112 CE 2001 7 31 CA010627056 1 20010626 G 5610 10138402515 WINDSHIELD BEECH 200 200BEECH 1152920 CE PWA PT6 PT6A41 52043 EA HARTZL HCB3T HCB3TN3 GL COCKPIT FAILED W B EMER. DESCENT O OTHER CR CRUISE 1 CA 3218 (CAN) AIRCRAFT WAS IN LEVEL FLIGHT AT 24000 FEET ON AUTOPILOT WHEN LT WINDSHIELD SHATTERED. FLIGHT CREW DEPRESSURIZED AN D DESCENDED. AIRCRAFT RETURNED WITHOUR FURTHER INCIDENT. 1 L 7 2 4T 4 T A24CE E4EA 6 C P15EA 2001073100114 20010731 00114 CE 2001 7 31 CA010627057 1 20010529 G 5510 2332051 GUSSET LEAR 263200032 LEAR 35 35LEAR 5170600 CE GARRTT TFE731 TFE73122B 01518 WP HORIZONTAL STAB CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 14818 35002 (CAN) WHILE CARRYING OUT A ROUTINE INSPECTION (PHASE C6-1200HRS) ON THE HORIZONTAL STABILIZER "GUSSET" A CRACK WAS DISCO VERED IN THE GUSSET ERNINATING FROM THE EDGE OF THE LIGHTENING HOLE. THE INSPECTION SPECIFIES SCRUTINY OF THESEGUSSETS F OR CRACKS ON AIRCRAFT THAT DID NOT INCORPORATE AN EXTRA DOUBLER INSTALLED PER SSK 954. THIS AIRCRAFT DID NOT INCORPORATE THE DOUBLER. THE CRACK IS SMALL (.141 INCH LONG AND DIFFICULT TO SEE. IT WAS CONFIRMED USING HIGH FREQUENCY EDDY CURREN T. THERE IS A SMALL SCRATCH ON THE WEB OF THE GUSSET AT THE CRACK SITE. THE STABILIZER WAS REMOVED TO INSTALL LEAR SPECI AL SERVICES KIT 954 IN PLACE OF THE CRACKED GUSSET. 2 L 7 2 4F 4 F A10CE E6WE 2001073100116 20010731 00116 NM 2001 7 31 CA010627059 1 20010627 G 3213 STABILIZER DHAV DHC8 DHC8101 2809002 NM PWA 120 PW120 NE HAMSTD 14SF 14SF7 NE MLG BROKEN W O OTHER O OTHER AP APPROACH 1 CA (CAN) PORT MAIN LANDING GEAR FAILED TO LOCK DOWN WHEN SELECTED DOWN FOR LANDING. GEAR WAS CYCLED AND LOCKED DOWN ON SECO ND ATTEMPT. ON INSPECTION, THE LEFT SPRING ON THE PORT MLG STABILIZER STRUT WAS FOUND BROKEN. AS THIS IS NOT AN LRU, PER MISSION WAS OBTAINED TO FERRY AIRCRAFT TO MAIN BASE WITH GEAR LOCKED DOWN. AIRCRAFT FERRIED TO BASE FOR REPAIRS. PORT MA IN LANDING GEAR STABILIZER ASSY CHANGED IAW 32-10-26 GEAR RETRACTION CHECK CARRIED OUT SATISFACTORY. 2 H 7 2 4T 4 T RT A13NM E20NE 6 C P7NE 2001073100117 20010731 00117 CE 2001 7 31 CA010627060 1 20010615 G 7120 075100125 MOUNT CESSNA 180 180C 2072608 CE CONT O470 O470L 17026 SO MCAULY 2A34C 2A34C66 GL ENGINE CRACKED W O OTHER O OTHER NR NOT REPORTED 1 CA 6950 (CAN) UPPER LT VERTICAL TUBING CRACKED AT LOWER GUSSET 1 H 7 1 3O 3 O 5A6 E273 5 C P3EA 2001073100120 20010731 00120 CE 2001 7 31 CA010627061 1 20010614 G 3260 1303640489 CIRCUIT BOARD BEECH B300 B300 1159232 CE PWA PT6 PT6A60A 52043 NE HARTZL HCB4M HCB4MP3 GL MLG INDICATOR FAILED W L ABORTED APPROACH N FALSE WARNING LD LANDING 1 CA 5106 (CAN) ON APPROACH AIRCRAFT LOSS ALL GREEN ADVISORY LIGHTS AIRCRAFT MADE 3 FLY BY'S TO VERIFY GEAR DOWN & LOCKED. AIRCRAF T LANDED WITHOUT INCIDENT. THE LANDING GEAR LIGHTS ARE DIMMED THROUGH THE ABOVE P.C. BOARD. 2 L 7 2 4T 4 T RT A24CE E4EA 6 C P56GL 2001070500016 20010705 00016 SO 2001 7 5 CA010627062 2 20010618 G 8530 648049 PISTON CONT I0360 CESSNA 337 337G 2075730 CE CONT O360 IO360G 17025 SO MCAULY 2AF34C D2AF34C306 GL PISTON BROKEN W O OTHER R PARTIAL RPM/PWR LOSS IN INSP/MAINT 1 CA 1350 352436 (CAN) ON A GROUND RUN-UP PRIOR TO A SCHEDULED INSPECTION A PARTIAL POWER LOSS WAS DETECTED. A MOTO-STAT WAS CARRIED OUT AND #6 CYL. HAD VERY LOW COMPRESSION. A FILTER CHECK WAS CARRIED OUT AND SUBSTANIAL METAL PARTS, ALM, CHROME AND STEEL W ERE FOUND THAT ARE CONSISTANT WITH A PISTON FAILURE. THE ENGINE HAS BEEN REMOVED FROM SERVICE. STRIP REPORT TO FOLLOW. 1 H 7 2 3O 3 O A6CE E1CE 5 C P5EA 2001073100121 20010731 00121 EA 2001 7 31 CA010627063 2 20010621 G 7310 76778 MANIFOLD PIPER PA31 PA31 7103102 SO LYC O540 TIO540A2B 41532 EA HARTZL HCE3Y HCE3YR2A GL FUEL SYSTEM CRACKED W K NONE K FLUID LOSS IN INSP/MAINT 1 CA 2407 (CAN) ON INSPECTION OF AD 93-02-05 FUEL INJECTOR LINES AND CLAMPS IT WAS NOTED THAT FUEL WAS LEAKING WITH BASE OF FITTIN G IN MANIFOLD. UPON REMOVAL OF MANIFOLD IT WAS TOWED TO BE CRACKED BETWEEN BOTH LT & TOP FITTING. 1 L 7 2 3O 3 O A20SO E14EA 5 C P33EA 2001073100122 20010731 00122 CE 2001 7 31 CA010628002 1 20010614 G 2510 041405410 RELEASE SYSTEM CESSNA 04140711 CESSNA 150 152 2071835 CE LYC O235 O235L2C 41505 EA MCAULY 1A103 1A103TCM GL SEAT SHEARED W D RETURN TO BLOCK O OTHER TX TAXI/GRND HDL 1 CA 11600 80173 (CAN) 3 OF 4 LATCH PINS CONTROLLING SEAT NIGHT FOUND SHEARED AT ENGAGEMENT HOLE ALLOWING SEAT TO DROP AND TILT. 1 H 7 1 3O 3 O NT 3A19 E223 5 N P50GL 2001073100135 20010731 00135 EA 2001 7 31 CA010628012 1 20010511 G 6120 12350 TUBE DHAV DHC3 DHC3 2800202 EA PWA R1340 R1340* 52016 NE HAMSTD 23D 23D40 NE PROPELLER OIL BROKEN W K NONE O OTHER IN INSP/MAINT 1 CA 274 (CAN) COULD NOT CYCLE PROPELLER. FOUND OIL TRANSFER TUBE IN NOSE CASE BROKEN AT ATTACH POINT IN CENTRE OF TUBE. ONE TUBE REPLACED AT 274 HOURS SINCE OVERHAUL AND ANOTHER TUBE WAS REPLACED WITH 243 HOURS SINCE REPLACEMENT. THESE ARE 2 SEPARA TE OCCURANCES. 1 H 7 1 3R 3 R A815 5E2 6 C P719 2001073100138 20010731 00138 SO 2001 7 31 CA010628014 1 20010522 G 3097 WIRE PIPER PA31T PA31T 7103124 SO PWA PT6 PT6A28 EA HARTZL HCB3T HCB3TN3 GL COCKPIT MELTED W H DEACTIVATE SYST/CIRCUITS B SMOKE/FUMES/ODORS/SPARKS CR CRUISE 1 CA 9259 (CAN) DURING CRUISE, WITH ENGINE AND WINDSHIELD HEAT SELECTED. SMOKE WAS OBSERVED COMING FROM THE RIGHT FORWARD CIRCUIT BREAKER PANEL. AT THIS POINT THE RIGHT ENGINE AND WINDSHIELD DEICE SYSTEMS WERE TURNED OFF AND THE SMOKE DISSAPPEARED. T HE AIRCRAFT LANDED SAFELY AT ITS DESTINATION. MAINTENANCE THEN DISCOVERED THAT 2 WIRES, BEHIND THE CIRCUIT BREAKER PANEL WERE MELTED : ONE BEING RIGHT INLET DEICE ANDTHE OTHER RIGHT WINDSHIELD HEAT. CORROSION WAS FOUND AT THE SPLICES, WHICH CAUSED EXCESSIVE HEAT. 1 L 7 2 3T 4 T A8EA E4EA 6 C P15EA 2001073100139 20010731 00139 SW 2001 7 31 CA010628016 1 20010606 G 2750 12395 PULLEY BBAVIA 8 8GCBC 1220803 SW LYC O360 O360C2E 41514 EA MCAULY 1A200 1A200* GL FLAP SYSTEM SEIZED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) LT AND RT PULLEYS FOUND SEIZED AT WING ROOT(100 HOUR INSP.) BOTH CABLES FREYED AND UNSERVICEABLE. (LT/RT) AT POSIT ION OF PULLEY.SOLID ALUMINUM PULLEYS, NO BEARING , DIFFICULT TO KEEP LUBRICATED. HIGH POTENTIAL FOR INFLIGHT FLAP CABLE FAILURE. 1 H 7 1 3O 3 O A21CE E286 5 N P874 2001073100144 20010731 00144 CE 2001 7 31 CA010628023 1 20010524 G 2823 1013890253 SHUTOFF VALVE BEECH 90 C90A 1152911 CE PWA PT6 PT6A21 52043 EA HARTZL HCB3T HCB3TN3 GL FUEL SYSTEM FAILED W D RETURN TO BLOCK L NO TEST TX TAXI/GRND HDL 1 CA (CAN) FAILED.PILOTS CHECK FOR LEAKING SHUTOFF VALVE AS PER FLT. MANUAL PROCEDURES. NEW VALVE INSTALLED CHECKED OK. 1 L 7 2 3T 4 T RT 3A20 E4EA 6 C P15EA 2001073100181 20010731 00181 CE 2001 7 31 CA010628029 1 20010511 G 5511 07321014 SPAR CESSNA 185 A185F 2072821 CE CONT O520 IO520D 17032 SO MCAULY 2A34C D2A34C58 GL HORIZONTAL STAB CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 2572 (CAN) DURING ANNUAL INSPECTION FOUND PLAY IN HORIZONTAL STABILIZER TO ELINMINATE PLAY REPLACE ALL HARDWARE AND BUSHING I N ASS. DURING LUBRICATING OF ELEVATOR HINGES DISCOVERED CRACK ON STABILIZER HINGE REINFORCEMENT. THIS REINFORCEMENT IS R IVETED ON MAIN SPARE. STABILIZER HINGE IS BOLTED THROUGH MAIN SPARE AND REINFORCEMENT. A/C CONFIGURATION: SEAPLANE STRAI GHT FLOATS 1 H 7 1 3O 3 O 3A24 E5CE 5 C P3EA 2001073100184 20010731 00184 SO 2001 7 31 CA010628037 1 20010525 G 3246 16205700 WHEEL PIPER PA44 PA44180 7104402 SO LYC O360 O360E1A6 41514 EA HARTZL HCC2Y HCC2YR2 GL MLG CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 5266 (CAN) FLANGE OF OUTER WHEEL HALFFOUND CRACKED (4 INCHES) ALONG FLANGE WHERE TIRE BEAD SEATS. 1 L 7 2 3O 3 O A19S0 E286 5 C P920 2001073100205 20010731 00205 EU 2001 7 31 CA010628038 1 20010520 G 2612 6493950730 FIRE LOOP AIRBUS 320 A320212 EU CFMINT CFM56 CFM565A3 NE NR 2 ENGINE DAMAGED W K NONE N FALSE WARNING IN INSP/MAINT 1 CA (CAN) PRF MESSAGE CHECK ENGINE NR 2 FIRE LOOP "B". THIS DEFECT WAS UNDER INVESTIGATION BY MAINTENANCE PERSONNEL AND ALSO DEFFERED UNDER MEL 26-12-01 CATEGORY "C" AS A RESULT OF THIS PFR MESSAGE. FIRE LOOP "B" REPLACEMENT WAS SCHEDULED WHILE OPERATING THE "C" DUCT FOR LOOP REPLACEMENT IT WAS NOTICED FOR DAMAGE TO THE NR 2 ENGINE RT "C" DUCT HEAT SHIELD. THE D AMAGE HAS BEEN CAUSE BY A MISSING "PISTON RING" (P/N336-510-710-0 OR 649-395-073-0 POST SB).MAINTENANCE PERSONNEL INSTAL LED NEW PISTON RING, BUT AIRCRAFT WAS GROUNDED DUE TO THE EXTENSIVE DAMAGE TO THE 32 ENGINE RT "C" DUCT HEAT SHIELD. A T EMPORARY RE PAIR HAS BEEN ACCOMPLISHED TO THE HEAT SHIELD WITH A REPETITIVE INSPECTION EVERY "A" CHECK GRANTED BY BF GOO 2 L 7 2 4F 4 F RT A28NM E29NE 2001073100213 20010731 00213 EA 2001 7 31 CA010628039 2 20010628 G 8530 LW19340 CAMSHAFT GULSTM 500 500S 0141107 SW LYC O540 IO540E1B5 41532 EA HARTZL HCA3V HCA3VK2 GL ENGINE WORN W K NONE E VIBRATION/BUFFET CR CRUISE 1 CA 1440 (CAN) ENGINE HAD BEEN HARD TO START, LOW STATIC RPM AND HIGH MANIFOLD PRESSURE. ENGINE INSP. REVEALED THAT THE CAMSHAFT LOBE THAT DRIVES NR 5&6 CYL INTAKE VALVES WERE WORN. FURTHER TEAR DOWN OF ENGINE REVEALED NO FURTHER ABNORMAL WEAR OR CO RROSION. 1 H 7 2 3O 3 O 6A1 1E4 5 C P6EA 2001073100215 20010731 00215 SO 2001 7 31 CA010628042 1 20010527 G 2910 3036 HOSE PIPER PA31 PA31 7103102 SO LYC O540 TIO540A2B 41532 EA HARTZL HCE3Y HCE3YR2A GL HYD SYSTEM RUPTURED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) HYDRAULIC HOSE RUPTURE AT FITTING P/N MS24590-4. FITTING M524590-4 HAD WORN INTERNAL THREADS WHEN HOSE WAS MANUFAC TURED. HOSE AND FITTING SEPARATED ON GEAR CYCLE. 1 L 7 2 3O 3 O A20SO E14EA 5 C P33EA 2001073100217 20010731 00217 SW 2001 7 31 CA010628043 1 20010520 G 5711 SPAR BBAVIA 7 7CCM 21101MW SW CONT C90 C9012F 17009 SO SNSNCH 76AK M76AK EA WING CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) TO CARRY OUT AD 2000-25-02, ADDITIONAL HOLES WERE CUT IN EACH LOWER WING PANEL. NO PROBLEMS WERE FOUND. REMOVED WI NG ROOT FAIRINGS AND FABRIC ON TOP OF BOTH WINGS JUST TO BE SURE IN WING ROOT AREA. FOUND BOTH FWD SPAR ROOT ATTACH POIN TS CRACKED AT THE ENDS. ALSO ONE LONG CRACK APPROX. 1 INCH DOWN FROM TOP TO BOTTOM OF SPAR APPROX. 4 FT LONG BETWEEN ROO T /STRUT WHICH WAS NOT SEEN UNTIL FABRIC WAS COMPLETELY REMOVED. THE OTTAWA AIRWORTHINESS OFFICE WAS CONTACTED. 1 H 7 1 3O 3 O A759 E252 5 N 1P210 2001073100220 20010731 00220 SO 2001 7 31 CA010628045 1 20010520 G 7603 2489403 CONTROL CABLE PIPER PA30 PA30 7103002 SO LYC O320 IO320B1A 41508 EA HARTZL HCE2Y HCE2YL2 GL THROTTLE FAILED W E A ENGINE SHUTDOWN UNSCHED LANDING R J PARTIAL RPM/PWR LOSS WARNING INDICATION CL CLIMB 1 CA 5141 5141 (CAN) THROTTLE CONTROL CABLE BROKE AT ENGINE END RESULTING IN LOSS OF ENGINE POWER SELECTION CAPABILITY. SUBSEQUENTLY, A LL ENGINE CONTROL /CABLES ON BOTH ENGINES WERE REPLACED. 1 L 7 2 3O 3 O A1EA 1E12 5 C P9EA 2001073100244 20010731 00244 NM 2001 7 31 CA010628062 1 20010528 G 3260 189915 UPLOCK SENSOR BOEING 727 727223 1384074 NM PWA JT8 JT8D15 52051 NE MLG FAILED W O OTHER N FALSE WARNING CR CRUISE 1 CA (CAN) RED LEFT GEAR ANNUNCIATOR ON FORWARD PANEL ILLUMINATED IN FLIGHT WITH LANDING GEAR SELECTOR UP AND OFF. ALL OTHER LANDING GEAR ANNUNICATION (INCLUDING DOOR ANNUNICATORS) EXTINGUISHED. RED LEFT GEAR ANNUNICATOR EXTINGUISHED WITH ILLUMI NATION OF GREEN LEFT GEAR LIGHT WHEN LANDING GEAR SELECTED DOWN. LEFT MAIN LANDING GEAR UP-LOCK SENSOR REPLACED IN ACCOR DANCE WITH MAINTENANCE MANUAL AND TESTED SERVICEABLE. NO FURTHER DEFECTS NOTED IN THE LAST TWO FLIGHT LEGS. 2 L 7 3 4F 4 F A3WE E2EA 2001070500020 20010705 00020 NM 2001 7 5 CA010628064 1 20010322 G 3040 WINDSHIELD TRIPLEX 0780306 DHAV DHC8 DHC8102 2809003 NM PWA 120 PW120 NE HAMSTD 14SF 14SF7 NE WINDSHIELD CRACKED W O OTHER O OTHER CR CRUISE 1 CA 13748 TH2078 (CAN) BOMBARDIER AEROSPACE REGIONAL AIRCRAFT HAS JUST RECEIVED A REPORTABLE SDR EVENT WHICH WE ARE REQUIRED TO REPORT ON MARCH 22/01. IN CRUISE FLIGHT AT 15,000FT. THE FIRST OFFICERS WINDSCREEN CRACKED AND BECAME TOTALLY DISTORTED. EMERGENC Y DECLARED AND FLIGHT DIVERTED TO BASE LANDED WITHOUT INCIDENT. MAINTENANCE REPLACED FIRST OFFICERS WINDSHIELD IN ACCORD ANCE WITH DEHAVILLAND DASH 8 MAINTENANCE MANUAL OPERATIONAL CHECK OF WINDSHIELD GOOD. AIRCRAFT RETURNED TO SERVICE. 2 H 7 2 4T 4 T RT A13NM E20NE 6 C P7NE 2001073100249 20010731 00249 EU 2001 7 31 CA010629006 3 20010514 G 6110 697071003 BLADE ROTOL 697071003 DHAV DHC8 DHC8* NM PWC 150 PW150A EA ROTOL R4304 R4304* EU PROPELLER BURNED W O OTHER C F.O.D. AP APPROACH 1 CA (CAN) BOMBARDIER AEROSPACE REGIONAL AIRCRAFT HAS JUST RECEIVED A REPORTABLE SDR WEVENT WHICH WE ARE REQUIRED TO REPORT O N MAY 5/01. DURING APPROACH, THE PILOT REPORTED THAT THE R/H PROPELLER SUSTAINED A LIGHTENING STRIKE. INSPECTION OF THE PROPELLER UPON LANDING SHOWED A BURN MARK ON ONE BLADE APPROX 3MM IN WIDTH FROM TIP, CENTRE OF BLADE. IAW THE AMM THE PR OPELLER ASSY, HUB ANDBETA TUBE HAVE TO BE REMOVED AND SENT TO DOWTY FOR INVESTIGATION. NEW ASSY, INSTALLED AND AIRCRAFT RETURNED TO SERVICE. 2 H 7 2 4T 4 T RT A13NM E00062EN 6 C P890 2001073100251 20010731 00251 EA 2001 7 31 CA010629009 1 20010522 G 2710 SERVO COLLINS 6222366001 DHAV DHC6 DHC6300 2802606 EA PWA PT6 PT6* 52043 EA AILERON FAILED W A UNSCHED LANDING F FLT CONT AFFECTED CR CRUISE 1 CA (CAN) DURING FLIGHT, AILERON CONTROL LOST DUE TO AILERON SERVO SERVO PRIMARY JAMMED. AIRCRAFT RETURNED TO BASE. SERVO WA S REPLACED. AIRCRAFT RETURNED TO SERVICE. 1 H 7 2 3T 3 T RT A9EA E2NE 2001073100254 20010731 00254 2001 7 31 CA010629017 4 20010323 G 3417 ADC DHAV DHC8 DHC8301 NM PWA PW120 PW123 NE HAMSTD 14SF 14SF23 NE E/E BAY FAILED W A UNSCHED LANDING H J ELECT. POWER LOSS-50 PC WARNING INDICATION CR CRUISE 1 CA (CAN) DURING CLIMB, AT APPROX. 6000FT, RDADC FAIL. BOTH ADVISORY DISPLAYS RESE T LIGHT WAS ON. SAT 2 WAS SHOWING DASHES . ALTITUDE SELECT BLANK. BASIC PITCH MESSAGE ON. VSI 2 SHOWED 0. ALT PRESELECT BLANK. YAW DAMPER FAIL. AP DISCONNECTED E GPWS FAIL. RNAV MESSAGE "ADC FAIL" TRUE AIRSPEED INOP. ON ECP, "NR 2 ENG ECU FLAGGED. NO CHANGE WHEN L DADC WAS MADE MAS TER. FLT ABORTED. A/C RETURNED TO BASE.ON GROUND: NO FAULT CODES IN FLT FAULT SUMMARY. UNABLE TO DUPLICATE THEFAULT ON G ROU ND #2 AIR DATA COMPUTER REPLD. CHECKED WATER DRAINS..OK PITOT/STATIC LEAK TESTOK/PURGED PITOT/STATIS LINES...OK A/C RETURN TO SERVI 2 H 7 2 4T 4 T RT A13NM E20NE 6 C P7NE 2001073100256 20010731 00256 EA 2001 7 31 CA010629019 2 20010426 G 7321 25244405 FUEL CONTROL BEECH 100 A100 1152915 CE PWA PT6 PT6A28 EA HARTZL HCD4N3 HCD4N3A GL ENGINE FAILED W O OTHER O OTHER AP APPROACH 1 CA 3514 (CAN) RT POWER LEVER IS VERY DIFFICULT TO SCHEDULE SUBTLE POWER CHANGES. IE. WHEN ATTEPTING TO SELECT A CHANGE OF 100 FT /LBS RESULTING TORQUE CHANGE COULD BE AS MUCH AS 400FT/LBS. THIS RESULTS IN AN OSCILLATION OF POWER LEVER MOVEMENT TO GE T DESIRED POWER OUTPUT. THIS IS ESPECIALLY APPARENT WHEN LANDING WITH GUSTING WINDS. R/H FUEL CONTROL UNIT REPLACED. S/N OFF A7414.S/N ON A7968. TEARDOWN REPORT INDICATED GOVERNOR HYSTERESIS WAS 180 RPM. MAX ALLOWABLE IS 50 RPM. DRIVE BODY ALSO FOUND TO BE DIRTY/SOOTY. THIS WOULD CAUSE FCU TO RESPOND SLOWLY AND INTERMITTENTLY. 1 L 7 2 3T 4 T A14CE E4EA 5 C STC 2001073100259 20010731 00259 EA 2001 7 31 CA010629020 2 20010604 G 7230 SEAL SOCATA TBM TBM700 8682000 EU PWA PT6 PT6A6A 52043 EA HARTZL HCE4N HCE4N3 NE ACTUATOR MISINSTALLED W K NONE O OTHER IN INSP/MAINT 1 CA 29 (CAN) INERTIA ACTUATOR MOTOR P/N 200N6071017220 WAS REPLD 29.9 HRS PRIOR TO FAILURE . NEW ACTUATOR WAS BEING INST WHEN N OTICES INERTIA APOATOR DEFLECTOR BEING CUT WHILE MANU MOVING. UNIT WAS REMOVED FROM HC & WHILE INVESTIGATING NOTICED SEA L THAT HAD UNEVEN MASHINGS FROM WEAR. WHEN DISLOCATED CREATED SAME PROBLEM OF DEFLECTOR BEING CAUGHT & REQ A LOT OF FORC E TO MOVE. THAT COND ITION TOOK OUT NEW MOTOR. EMPIRE PERFORMANCE DROPPED IN FLT & A/C ALTITUDE LIMITED. INCORRECT INST OF INERTIA SEPARATOR SEAL DISCLOSED CAUSING PROC FAILURE OF MOTOR DUE TO EXCESSIVE PRESSURE SUGGESTED CONNECTIVE ACTION- AFTER REMOVAL & REINSTATIN OF INERTIA SEPARATOR DISCONNECT WATER FROM ASSY & MANU CHECK. 1 L 7 1 3T 3 T RT A60EU E4EA 5 C P10NE 2001073100261 20010731 00261 EU 2001 7 31 CA010629023 1 20010511 G 2434 HED60CR132200 BRUSHES BOSCH 5243212158 PILATS PC12 PC1245 EU PWA PT6 PT6A67B 52043 NE HARTZL HCE4A HCE4A3D GL GENERATOR WORN W O OTHER J WARNING INDICATION CR CRUISE 1 CA 222 100037 (CAN) THE NR 2 GENERATOR CAUTION LIGHT ILLUMINATED ON THE CAWS PANEL. THE PILOT NOTED THAT THE NR 2 GENERATOR OUTPUT WAS FLUCTUATING BETWEEN A 60AMP DISCHARGE AND A 20 AMP POSITIVE CHARGE. HE TURNED THE GENERATOR OFF, THEN RE-SELECTED IT TO THE ON POSITION.THE RESET WAS SCESSFUL FOR APPROX. 20 MINUTES AT WHICH TIME FOR APPROX 20 MINUTES, THE PROBLEM REOCCURR ED. MAINTENANCE FOUND THAT THE BRUSHES WERE WORN WELL BEYOND A SERVICEABLE LIMIT. A NEW SET OF BRUSHES WAS INSTALED AND THE AIRCRAFT GROUND RUN. NO FURTHER PROBLEMS NOTED. 1 L 7 1 3T 4 T RT A78EU E26NE 5 C P210NE 2001073100263 20010731 00263 EU 2001 7 31 CA010629024 1 20010518 G 2434 HED60CR132200 BRUSHES BOSCH 5243212158 PILATS PC12 PC1245 EU PWA PT6 PT6A67B 52043 NE HARTZL HCE4A HCE4A3D GL GENERATOR WORN W O OTHER J WARNING INDICATION CR CRUISE 1 CA 12 100037 (CAN) THE NR 2 GEN CAUTION LIGHT ILLUMINATED ON CAWS PANEL. PILOT ALSO NOTED THAT A VERY LOUD SQUEALING SOUND COULD BE H EARD IN HEADSET. CAUTION LIGHT THEN ILLUMINATED & PILOT THEN SELECTED NR 2 GEN SWITCH TO OFF POS. GEN WAS THEN RE-SELECT ED TO ON POS, WITH SAME RESULT AS NOTED ABOVE. GEN #2 WAS THEN SELECTED TO OFF POS, & THEAIRCRA FT RETURNED TO BASE. ONC E AGAIN MAINTENACE FOUND THAT POST SB- "24-016" BRUSHES HAD FAILED WELL BEFORE THEIR LIFE LIMIT WAS REACHED. A EW SET OF POST S/B BRUSHES WAS INSTAND AIRCRAFT GROUND RUN, WITH NO FURTHER DEFECTS BEING NOTED. AS MENTION IN OUR PREVIOUS SDR 1 1-05-2001. MAINT HAS INSTITUED A VOLUNTARY 1 L 7 1 3T 4 T RT A78EU E26NE 5 C P210NE 2001073100264 20010731 00264 NE 2001 7 31 CA010629025 2 20010522 G 7321 8063041 FUEL CONTROL PILATS PC12 PC1245 EU PWA PT6 PT6A67B 52043 NE HARTZL HCE4A HCE4A3D GL ENGINE FAILED W O OTHER O OTHER TX TAXI/GRND HDL 1 CA 1215 (CAN) WHEN TRYING TO START ENGINE, THE ENGINE WOULD NOT ACCELERATE ABOVE APPROXIMATELY 35-39 PERCENT THE FUEL CONTROL UN IT WAS REPLACED, AND THE AIRCRAFT WAS RETURNED TO SERVICE 1 L 7 1 3T 4 T RT A78EU E26NE 5 C P210NE 2001073100265 20010731 00265 EU 2001 7 31 CA010629026 1 20010528 G 2434 9789601090 BRUSHES 5243212158 PILATS PC12 PC1245 EU PWA PT6 PT6A67B 52043 NE HARTZL HCE4A HCE4A3D GL GENERATOR WORN W K NONE O OTHER IN INSP/MAINT 1 CA 94 100318 (CAN) DURING A 100 HOUR INSPECTION, THE BRUSH ASSEMBLY WAS REMOVED TO VERIFY THE CONDITION. THE BRUSH ASSEMBLY WAS WORN EXCESSIVELY AND HAS BEEN REPLACED. 1 L 7 1 3T 4 T RT A78EU E26NE 5 C P210NE 2001073100267 20010731 00267 EU 2001 7 31 CA010629027 1 20010518 G 5270 9733024202 ARM PILATS PC12 PC1245 EU PWA PT6 PT6A67B 52043 NE HARTZL HCE4A HCE4A3D GL DOOR SWITCH BROKEN W D RETURN TO BLOCK N FALSE WARNING TX TAXI/GRND HDL 1 CA 1572 (CAN) ON CLOSING THE CARGO DOOR THE UNLOCKED WARNING LIGHT IN THE COCKPIT FAILED TO EXTINGUISH. ON INVESTIGATION THE ROL LER SPRING ON THE MICRO SWITCH WAS BROKEN. 1 L 7 1 3T 4 T RT A78EU E26NE 5 C P210NE 2001073100268 20010731 00268 EU 2001 7 31 CA010629029 1 20010518 G 2434 9789601090 BRUSHES 5243212158 PILATS PC12 PC1245 EU PWA PT6 PT6A67B 52043 NE HARTZL HCE4A HCE4A3D GL GENERATOR WORN W O OTHER J WARNING INDICATION AP APPROACH 1 CA 370 100092 (CAN) #2 GENERATOR FAIL LIGHT CAME ON DURING FLIGHT. AN INSPECTION OF THE BRUSHES SHOWED ONE TO HAVE SUFFERED SIGNS OF A RCING. 1 L 7 1 3T 4 T RT A78EU E26NE 5 C P210NE 2001073100271 20010731 00271 EU 2001 7 31 CA010629032 1 20010514 G 2710 5271012115 CONTROL CABLE PILATS PC12 PC1245 EU PWA PT6 PT6A67B 52043 NE HARTZL HCE4A HCE4A3D GL AILERON DEFECTIVE W K NONE O OTHER IN INSP/MAINT 1 CA 1993 (CAN) WHEN INSPECTING CONTROL CABLES AS PER 2000HR/5YR. INSPECTION REQUIREMENT, SOME ABNORMALITIES WERE NOTED ON THE 2 F ORWARD AILERON CONTROL CABLES. ON ONE OF THE BUNDLES OF STRANDS IT APPEARED AS IF 2 OR 3 OF THE INDIVIDAL STRANDS WERE S EPARATED FROM EACHOTHER WITH A SLIGHT KINK. THIS PATTERN REPEATED ITSELF EVERY 4 OR 5 INCHES. THIS ABNORMALITY IS ONLY A FEW MILLIMETERS IN LENGTH. THE 115 CABLE HASSEVERVAL OF THESE SUSPICIOUS SPOTS AND THE 116 HAS ONLY A FEW. THE CABLES H AVE BEEN REPLACED WITH NEW PILATUS PARTS AND THE SUSPECT CABLES HAVE BEEN FORWARDED TO OUR REGIONAL SUPERVISOR FOR FURTH ER EVALUATION. 1 L 7 1 3T 4 T RT A78EU E26NE 5 C P210NE 2001073100272 20010731 00272 2001 7 31 CA010629033 4 20010514 G 3425 071014393100 CONTROL PANEL PILATS PC12 PC1245 EU PWA PT6 PT6A67B 52043 NE HARTZL HCE4A HCE4A3D GL COCKPIT MALFUNCTIONED W O OTHER H ELECT. POWER LOSS-50 PC CR CRUISE 1 CA 1993 (CAN) HDG CONTROL KNOB FEELS SCRATCHY, CAUSING INTERMITTENT RED FLAG ON HDG SYMBOL ON EFIS.PANEL REPLACED. 1 L 7 1 3T 4 T RT A78EU E26NE 5 C P210NE 2001073100274 20010731 00274 2001 7 31 CA010629036 4 20010530 G 2210 SERVO HONEYWELL 7002260922 DHAV DHC8 DHC8301 NM PWA PW120 PW123 NE HAMSTD 14SF 14SF23 NE AUTOPILOT FAILED W C ABORTED TAKEOFF F FLT CONT AFFECTED TO TAKEOFF 1 CA 00105873 (CAN) ELEVATOR HEAVY OPERATION AFTER TAKE OFF. FLIGHT WAS ABORTED. LANDING WAS UNEVENTFUL. MAINTENANCE TESTS REVEALED TH AT THE AUTO PILOT ELEVATOR SERVO MOTOR'S CLUTCH WAS STILL ENGAGED. ELEVATOR ACTUATOR SERVO MOTOR IS BEING REPLACED. 2 H 7 2 4T 4 T RT A13NM E20NE 6 C P7NE 2001073100277 20010731 00277 NE 2001 7 31 CA010629038 2 20010517 G 7261 3033990 LINE DHAV DHC8 DHC8101 2809002 NM PWA 120 PW120 NE HAMSTD 14SF 14SF7 NE OIL SUPPLY FRACTURED W F A ACTIVATE FIRE EXT. UNSCHED LANDING A J FLAME/FIRE WARNING INDICATION CR CRUISE 1 CA (CAN) AN INCID. OCCURRED ON CLIMB OUT. PILOTS RPT THAT NR 1 ENGINE TRQ DROPPED TO 30 PERCENT, PILOTS PULLED & RESET CCT BREAKER. 30 2NDS AFTER TRQ DROP WAS NOTICED NR 1 OIL PX DROPPED TO 0 PSI & FIRE IND. FOR NR 1 ENG. ILLUMINATED. PILOTS BLEW 1 FIRE BOTTLE AFTER ENGINE SHUTDO WN 28 SEC LATER FIRE IND. EXTINGUISHED A/C RETURNED TO BASE W/O INCID.. NR 1 ENGI NE IS SEIZED WITH PROP UNFEATHERED. UPON INSP OF ENGINE, OIL SUPPLY LINE TO NR 6 BEARI NG FOUND FRACTURED. FIRE WAS CONT AINED WITHIN NACELLE FIREWALL, HOWEVER THERE HAS BEEN HEAT DAMAGE TO STRUCTURE: 2 H 7 2 4T 4 T RT A13NM E20NE 6 C P7NE 2001073100279 20010731 00279 EU 2001 7 31 CA010629039 1 20010629 G 2913 501310000 PRESSURE SWITCH VICKERS 887673 AIRBUS 320 A320232 3930326 EU IAE V2527 V2527A5 NE HYD PUMP FAILED W A UNSCHED LANDING J WARNING INDICATION CL CLIMB 1 CA 528 528 MX632028 (CAN) DEPARTED YUL FOR KEF. WHILE IN CLIMB THE ENGINE NR 2 YELLOW HYDRAULIC PUMP FAULT LIGHT ILLUMINATED. THE PUMP WAS DE-ACTIVATED AND THE AIRCRAFT DIVERTED TO YHZ. MAINTENANCE TROUBLESHOOTING LOCATED A HYDRAULIC LEAK FROM THE HYDRAULIC P UMP NR 2 PRESSURE SWITCH. THE SWITCH ASSY WAS REPLACED AND THE AIRCRAFT RETURNED TO SERVICE. 2 L 7 2 4F 4 F RT A28NM E40NE 2001073100281 20010731 00281 WP 2001 7 31 CA010629040 1 20010608 G 3231 28B4028 TORQUE TUBE CVAC PBY5 PBY5A 2421208 WP PWA R1830 R183092 52020 NE MLG DOOR CORRODED W K NONE O OTHER IN INSP/MAINT 1 CA 6960 (CAN) NOSE GEAR DOOR TORQUE TUBES REMOVED FOR INSPECTION DUE TO THE PROMPTING OF A SERVICE DIFFICULTY ADVISORY. THE COND ITION PREDICTED IN THE ADVISORY (CORROSION) WAS FOUND TO EXIST IN A FAIRLY ADVANCED STAGE, PARTICULARLY AROUND THE TAPER PINS AND HOLES. THESE TUBES HAVE BEEN MODIFIED WITH GREASE FITTINGS TO FACILITATE FILLING THE TUBES WITH GREASE, HOWEVE R, AN INCOMPLETE FIL HAD IN FACT MADE THE PROBLEM WORSE. THE PLUGS OF GREASE HAD IN FACT CREATED POCKETS WHERE MOSITURE WAS TRAPPED, WORSENING THE PROBLEM. NEW TUBES WERE FABRICATED AND INSTALLED WITH NEW HARDWARE. AS THE ADVISORY POINTS OU T, FAILURE DURING WATER LANDING COULD HAVE FATAL CONSEQUENCES IF THE DOOR COLLAPSE. 2 H 7 2 4R 4 R 2548 5E4 2001073100282 20010731 00282 NE 2001 7 31 CA010629043 2 20010317 G 7321 324485318 FUEL CONTROL DHAV DHC8 DHC8201 2809001 NM PWA PW120 PW123 NE HAMSTD 14SF 14SF23 NE RT ENGINE FAILED W A UNSCHED LANDING E J VIBRATION/BUFFET WARNING INDICATION CR CRUISE 1 CA 30 (CAN) THE NR 2 ENGINE POWER COULD NOT BE ADJUSTED AFTER TAKEOFF TO SET POWER. THEAIRCRAFT EXPERIENCED MODERATE TURBULENC E BETWEEN 20 TO 21 THOUSAND FEET. THE ENGINE WAS STUCK AT ABOUT 88 PERCENT TORQUE AND FUEL FLOW WAS ABOUT 610 TO 640 LBS PER HOUR. AT ENGINE SHUTDOWN AN OVER TORQUE WA S NOTED BUT IT IS NOT KNOWN HOW MUCH OVER. WITH THE POWER LEVER AT FLIGH T IDLE THE FUEL FLOW WAS STILL NOTED TO BE 610 TO 640LB 2 H 7 2 4T 4 T RT A13NM E20NE 6 C P7NE 2001073100285 20010731 00285 NM 2001 7 31 CA010703002 1 20010611 G 5330 SKIN BOEING 737 737296 1384486 NM PWA JT8 JT8D9A 52048 NE FUSELAGE CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 52471 (CAN) CRACK IN FUSELAGE SKIN LEFT SIDE BETWEEN FUSELAGE STATIONS 747 AND 767, STRINGER 17L REPAIRED AS PER SRM 53-30-3, TABLE 1, METHOD 1, PAGES 87,88 & 88A. 2 L 7 2 4F 4 F RT A16WE E2EA 2001073100302 20010731 00302 NM 2001 7 31 CA010703007 1 20010612 G 5610 WINDSHIELD DHAV DHC8 DHC8* NM PWC 150 PW150A EA COCKPIT CRACKED W A UNSCHED LANDING O OTHER CR CRUISE 1 CA (CAN) CO-PILOTS WINDSHIELD CRACKED IN CRUISE. A/C THEN DESCENDED, SLOWED AND REDUCED PRESSURIZATION. A/C LANDED UNEVENT FUL. WINDSHIELD REPLACED. 2 H 7 2 4T 4 T RT A13NM E00062EN 2001073100308 20010731 00308 EU 2001 7 31 CA010703013 1 20010614 G 6410 355A12005004 BLADE SNIAS 355A12005004 SNIAS 350 AS350B3 8680954 EU TMECA ARRIEL ARRIEL2B NE TAIL ROTOR FAILED W A UNSCHED LANDING C F.O.D. CL CLIMB 1 CA 1528 6964 (CAN) T/R BLADES WERE SUBJECTED TO A MINOR CONTACT ON THE OUTBOARD SKIN AREA WITH A PINE BOUGHT IN SLOW FORWARD FLIGHT, A/C THEN LANDED TO INSPECT THE BLADES. BLADES WERE REMOVED TO HAVE CRACKS IN THE FILLER AROUND THE EDGE OF THE TABS REPA IRED ( WARRANTY WORK) AND ALSO TO FURTHER INSPECT AND REPAIR MINOR BLADE DAMAGE. 1 G 7 1 3U 3 U H9EU E00054EN 2001073100309 20010731 00309 EU 2001 7 31 CA010703015 1 20010628 G 2560 504202201 BUCKLE AMSAFTYEQUIP 504202403 PILATS PC12 PC1245 EU PWA PT6 PT6A67B 52043 NE HARTZL HCE4A HCE4A3D GL SEAT BELT BROKEN W K NONE O OTHER IN INSP/MAINT 1 CA 1240 AFG0598790 (CAN) CO-PILOTS SEAT BELT BUCKLE WOULD NOT UNLATCH WHEN OPERATED. 1 L 7 1 3T 4 T RT A78EU E26NE 5 C P210NE 2001073100319 20010731 00319 SO 2001 7 31 CA010703026 1 20010614 G 2730 71056003 SPRING PIPER PA31 PA31350 7103110 SO LYC O540 TIO540J2BD 41532 EA ELEVATOR BROKEN W D RETURN TO BLOCK F FLT CONT AFFECTED TX TAXI/GRND HDL 1 CA 632 (CAN) AFTER LANDING, THE PILOT NOTED UNUSUALY LIGHT ELEVATOR.UPON SHUTDOWN, THE ELEVATOR WAS INSPECTED AND IT WAS NOTED THAT THE SPRING WAS BROKEN. UPON INSPECTION OF RECORDS, THE PART WAS FOUND TO HAVE 632HOURS SINCE REPLACEMENT AS PER AWD 98-08-18. THE PART HAS BEEN RETAINED IF FUTURE INSPECTION IS REQUIRED. 1 L 7 2 3O 3 O A20SO E14EA 2001073100325 20010731 00325 CE 2001 7 31 CA010703032 1 20010622 G 8011 654472 BUSHING CESSNA 421 421C 2076016 CE CONT O520 GTSIO520L 17032 SO MCAULY 3FF32 3FF32C501 GL STARTER SHAFT WORN W K NONE O OTHER IN INSP/MAINT 1 CA 375 (CAN) DURING SCHEDULED COMPLIANCE WITH CSB-94-4C THE STARTER SHAFT BUSHING WAS FOUND TO BE LOOSE IN THE ENGINE CASE. 1 L 7 2 3O 3 O A7CE E7CE 5 C P45GL 2001070500021 20010705 00021 NE 2001 7 5 CA010703034 2 20010617 G 7210 130000405 BEARING HONEYWELL T5313B BELL 205 205A1 1181414 SW LYC T53 T5313B 41549 NE BEARING BROKEN W A UNSCHED LANDING J WARNING INDICATION CR CRUISE 1 CA 1413 LE07592 (CAN) ENGINE CHIP LT CAME ON. METAL CHIPS WERE FOUND IN CHIP PLUG & FILTER. REPLACED ENGINE. INVESTIGATION SHOWS BEARING P/N 1-300-004-05 CAGE WAS BROKEN & INNER/ OUTER RACE BEARING SURFACE HAD FLAKE DAMAGE. 1 G 7 1 4U 4 U H1SW E17EA 2001073100327 20010731 00327 CE 2001 7 31 CA010703035 1 20010615 G 2434 6682 RETAINER SKYTRONICS 7565T1 CESSNA 305 305C 2074014 CE CONT O470 O47011 17026 SO ALTERNATOR BROKEN W K NONE O OTHER IN INSP/MAINT 1 CA 113 0201123 (CAN) ALTERNATOR REMOVED FROM A/C ENGINE FOR INVEST. & TO SEE IF RETAINER CUP WS DAMAGED. SMALL PIECES OF METAL & RUBBER FELL OFF ACCESSORIES CASE UPON REMOVAL OF ALTNR. LOOKING AT ALTERNATOR SPLINE GEAR & DRIVE SHAFT, EVIDENCE OF DAMAGES W ERE FOUND. RETAINING CUP WAS SHREDDED IN PIECES & ONLY ONE RUBBER BUSHING LEFT IN PLACE. AT TIME OF REMOVAL ALTNR WAS CH ARGING PRO PERLY INDICATING THAT SHAFT OF ROTOR WAS STILL TURNING. RETAINING CUP & RUBBER BUSHINGS ARE MOUNTED BETWEEN S PLINE GEAR DRIVING SHAFT & ROTOR SHAFT OF ALTNR. THIS INSTATION IS DESIGNED TO SHEAR OFF & PREVENT DAMAGES TO ENGINE IN CASE WHERE AN ALTNR. THIS INST IS DESIGNED TO SHEAR OFF 1 H 7 1 3O 3 O 5A5 E269 2001073100328 20010731 00328 CE 2001 7 31 CA010703036 1 20010615 G 2434 6682 RETAINER SKYTRONICS 7564T1 CESSNA 305 305C 2074014 CE CONT O470 O47011B 17026 SO ALTERNATOR CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 44 0201124 (CAN) ALTERNATOR REMOVED FROM AIRCRAFT ENGINE FOR INVESTIGATION AND TO SEE F RETAINER CUP WAS DAMAGED. LOOKING AT THE AL TERNATOR SPLINE EAR AMD DRIVE SHAFT, EVIDENCE OF DAMAGES WERE FOUND. THE RETAINING CUPWAS CRACKED WHERE THE RUBBER BUSHI NGS ARE SEATED. THE RETAINING CUP AND RUBBER BUSHINGS ARE MOUNTED BETWEEN THE SPLINE GEAR DRIVING SHAFT AND THE ROTOR SH AFT OF THE ALTERNATOR. THE INSTALLATION IS DE SIGNED TO SHEAR OFF AND PREVENT DAMAGES TO THE ENGINE IN THE CASE WHERE AN ALTERNATOR SHAFT WOULD SEIZE UP. IN THIS CASE, A FE WMORE HOUR FLIGHT WOULD HAD CERTAINLY CAUSED THE TOTAL BREAK OF THE CRACKED RETAINER CUP AND FAILURE OF THE ALTERNATOR. 1 H 7 1 3O 3 O 5A5 E269 2001073100330 20010731 00330 CE 2001 7 31 CA010703037 1 20010615 G 2434 6682 RETAINER SKYTRONICS 7565T1 CESSNA 305 305A 2074002 CE CONT O470 O47011 17026 SO ALTERNATOR CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 50 0201120 (CAN) ALTERNATOR REMOVED FROM A/C ENGINE FOR INVESTIGATION AND TO SEE IF RETAINER CUP WAS DAMAGED. LOOKING AT THE ALTERN ATOR SPLINE GEAR AND DRIVE SHAFT, EVIDENCE OF DAMAGES WERE FOUND. THE RETAINING CUP WAS CRACKED WHERE THE RUBBER BUSHING S ARE SEATED. THE RETAINING CUP AND RUBBER BUSHINGS ARE MOUNTED BETWEEN THE SPLINE GEAR DRIVING SHAFT AND THE ROTOR SHAF T OF THE ALTERNATOR. THE INSTALLATION IS DESIGNED TO SHEAR OFF AND PREVENT DAMAGES TO THE ENGINE IN THE CASE WHERE AN AL TERNATOR SHAFT WOULD SEIZE UP. IN THIS CASE, A FEW MORE HOU OF FLIGHT WOULD HAD CERTAINLY CAUSED THE TOTAL BREAK OF THE CRACKED RETAINER CUP AND THE FAILURE OF THE ALTERNATOR. 1 H 7 1 3O 3 O 5A5 E269 2001073100336 20010731 00336 CE 2001 7 31 CA010703038 1 20010614 G 2434 6682 RETAINER SKYTRONICS 7565T1 CESSNA 305 305A 2074002 CE CONT O470 O47011B 17026 SO ALTERNATOR FAILED W K NONE O OTHER IN INSP/MAINT 1 CA 76 0201121 (CAN) ALTERNATOR REMOVED FROM A/C ENGINE FOR INST ON A NEW ENGINE FOR THIS A/C. NO PILOT RPTED LOSS OF CHARGE BEFORE ENG INE WAS STOPPED FOR HIS TBO. SMALL PIECES OF METAL & RUBBER FELL OFF THE ACCESSORIES CASE UPON REMOVAL OF ALTNR. LOOKING CLOSELY TO ALTNR SPLINE GEAR & DRIVE SHAFT, EVIDENCE OF DAMAGES WERE FOUND. RETAINING CUP & RUBBER BUSHINGS WERE COMPLE TELY SHREDED. SPLINE GEAR LUGS WERE ALSO BROKEN OFF & THIS PARTICULAR ALTNR, ROTOR SHAFT SHEARED. RETAINING CUP & RUBBER BUSHINGS ARE MOUNTED BETWEEN SPLINE GEAR DRIING SHAFT & THEROTOR SHAFTOF ALTERNATOR. THIS INST IS DESIGNED TO SHEAR OFF & PREVENT DAMAGES TO ENGINE IN CASE WHERE AN ALTNR SHAFT 1 H 7 1 3O 3 O 5A5 E269 2001073100337 20010731 00337 CE 2001 7 31 CA010703039 1 20010613 G 2434 6682 RETAINER CUP SKYTRONICS 7565T1 CESSNA 305 305A 2074002 CE CONT O470 O47011B 17026 SO ALTERNATOR FAILED W K NONE O OTHER IN INSP/MAINT 1 CA 73 0201126 (CAN) ALTERNATOR REMOVED FROM A/C AFTER PILOT REPORTED NO INDICATION OF CHARGE AFTER HIS LAST LANDING. SMALL PIECES OF M ETAL AND RUBBER FELL OFF THE ACCESSORIES CASE UPON REMOVAL OF ALTERNATOR. LOOKING CLOSELY TO THE ALTERNATOR SPLINE GEAR AND DRIVE SHAFT, EVIDENCE OF DAMAGES WERE FOUND. THE RETAINING CUP AND TH RUBBER BUSHINGS WERE COMPLETLY SHREDDED. THE S PLINE GEAR LUGS WERE ALSO BROKEN.THE RETAININGCUP AND RUBBER BUSHINGS ARE MOUNTED BETWEEN THE SPLINE GEAR DRIVING SHAFT AND THE ROTOR SHAFT OF THE ALTERNATOR. THIS INSTALLATION IS DESIGNED TO SHEAR OFF AND PREVENT DAMAGES TO THE ENGINE IN T HE CA S WHERE AN ALTERNAOTR SHAFT WOULD SEIZE UP. IN THIS CASE, THE ALTERNATOR SHAFT COULD BE TURNED FREEY 1 H 7 1 3O 3 O 5A5 E269 2001073100340 20010731 00340 EA 2001 7 31 CA010704011 1 20010627 G 7120 BEAM GE CF343B1 CNDAIR CL600 CL6002B19 EA GE CF34 CF343B1 NE ENGINE SUPPORT CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) CRACKS WERE FOUND DURING ENGINE SUPPORT BEAM INSPECTION, AS PER SB601R-53-059. 2 L 7 2 4F 4 F RT A21EA E15NE 2001070500022 20010705 00022 NE 2001 7 5 CA010704015 2 20010627 G 7200 CARBON SEAL GE CF343B1 CNDAIR CL600 CL6002B19 EA GE CF34 CF343B1 NE CARBON SEAL FAILED W G O2 MASK DEPLOYED B SMOKE/FUMES/ODORS/SPARKS CR CRUISE 1 CA (CAN) BOMBARDIER AEEROSPACE HAS JUST RECEIVED A REPORTABLE SDR EVENT WHICH WE ARE REQUIRED TO REPORT ON. WHILE IN CRUISE FLIGHT THE CREW COULD SMELL AND SEE SMOKE.OXYGEN MASKS WERE DONNED BY THE CREW ANDTHEPAX MASKS WERE DEPLOYED. FLIGHT WA S DIVERTED. UPON INVESTIGATION THE ENGINE #1 CARBON SEAL WAS FOUND TO HAVE COME APART. 2 L 7 2 4F 4 F RT A21EA E15NE 2001073100345 20010731 00345 EA 2001 7 31 CA010704024 1 20010629 G 5320 PLATE CNDAIR CL600 CL6002B19 EA GE CF34 CF343B1 NE FUSELAGE CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) DURING C CHECK, MAINTENANCE FOUND A CRACK LOCATED IN THE PLATE ASSY. RBL 45.00 AT THE JOINT WITH THE FLOOR BEAM SU PPORT ANGLE AT PRESSURE BULKHEAD FS 621.00 THE CRACK WAS CONFIRMED USING NDT INSPECTION. 2 L 7 2 4F 4 F RT A21EA E15NE 2001073100348 20010731 00348 2001 7 31 CA010704028 4 20010629 G 3160 CONTROL UNIT CNDAIR CL600 CL6002B19 EA GE CF34 CF343B1 NE NR 2 FAILED W A UNSCHED LANDING O OTHER CL CLIMB 1 CA (CAN) DURING CLIMB PILOT REPORTED EICAS MESSAGE DCU NR 2 AUR AL FAIL, APR FAIL AND FLUCTATION OF ENGINE PARAMET ERS 9N1, N2 & ITT) ON BOTH ENGINES. THEY SELECTED THE APR SWITCH OFF AND THE FLUCTUATIONS WENT AWAY, FLIGHT CONTINUED TO NICE. IT CAME BACK AT 40 NM OF MONTPELLIER. BASED ON MDC CODES MAINTENANCE FOUN DCU NR 2 DEFECTIVE. REPLACED DCU NR 2, AIRCRAFT BACK IN SERVICE. 2 L 7 2 4F 4 F RT A21EA E15NE 2001072500555 20010725 00555 WP 2001 7 25 CA010706004 1 20010429 G 3200 1523153115 SWITCH LKHEED 1011 10113851 5265010 WP RROYCE RB211 RB21122B02 54555 NE SWITCH FAILED W A UNSCHED LANDING J WARNING INDICATION CL CLIMB 1 CA (CAN) AFTER DEPARTURE FROM YMX, THE TRUCK LIGHT CAME ON, NORMAL PROCEDURES WHERE NOT TO RETRACT THE GEAR, CREW DUMPED FU EL AND RETURNED TO BASE. FOUND TRUCK SWITCH AT FAULT, COMPLETE ACTUATOR REP LACED AND AIRCRAFT RELEASED FOR A FLIGHT TES T, SYSTEM CHECKED SERVICEABLE AND AIRCRAFT RETURNED TO SERVICE. 2 L 7 3 4F 4 F A23WE E12EU 2001073100352 20010731 00352 WP 2001 7 31 CA010706006 1 20010428 G 4970 2621TB9 TERMINAL BLOCK LKHEED 1011 10113853 5265020 WP RROYCE RB211 RB211524B402 54555 NE APU DESTROYED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) FOLLOWING APU WARNING HORN RCCB TRIPPED OFF FOUND 5 WIRES WHEE THE INSOLATION WAS BROKEN AND RELATED TERMINAL BUS CHEMICALLY DESTROYED BY SKYDROLL. APU FIRE-EX BOTTLE SQUIB WAS INTERMITTENT DUE TO DAMAGE. REPLACED TB AND REPAIRED WIRI NG AND AREA CLEAN FROM SKYDROL AND INSPECTED FOR LEAKS. NO LEAKS WERE NOTED, AIRCRAFT RETURNED TO SERVICE. 2 L 7 3 4F 4 F A23WE E12EU 2001072500556 20010725 00556 WP 2001 7 25 CA010706007 1 20010428 G 3320 TERMINAL BLOCK LKHEED 1011 10113853 5265020 WP RROYCE RB211 RB211524B402 54555 NE ROW 23 L/H CEILI OVERHEATED W K NONE B SMOKE/FUMES/ODORS/SPARKS TX TAXI/GRND HDL 1 CA (CAN) ON ARRIVAL CREW REPORTED SMOKE AT ROW 23 L/H CEILING. FOUND LUMINARE TERMINAL BLOCK OVERHEATED. LUMINARE ASSEMBLY REPLACED AND TERMINAL BLOCK REPLACED. AIRCRAFT RETURNED TO SERVICE. 2 L 7 3 4F 4 F A23WE E12EU 2001073100353 20010731 00353 EU 2001 7 31 CA010706008 1 20010508 G 7120 S5411020001000 MOUNT AEROSP ATR42 ATR42320 8680930 EU PWA PW121 PW121 52124 NE HAMSTD 14SF 14SF5 NE LT ENGINE WORN W K NONE O OTHER IN INSP/MAINT 1 CA 18491 (CAN) LEFT ATACHMENT FOR LOWER NACELLE IS WORN AND HOLE ARE ELONGATED. ENGINE MOUNT TO BE REPLACED BEFORE FURTHER FLIGHT . 2 H 7 2 4T 4 T RT A53EU E20NE 6 C P7NE 2001073100354 20010731 00354 CE 2001 7 31 CA010706009 1 20010505 G 5310 50430043865 DOOR FRAME BEECH 100 B100 1152919 CE FUSELAGE CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) DOOR FRAME AFT FOUND CRACKED AROUND REAR BAYONET. 1 L 7 2 4T A14CE 2001073100355 20010731 00355 SW 2001 7 31 CA010706014 1 20010430 G 6410 206011809109 PITCH HORN BELL 206 206L 1181522 SW ALLSN 250C 250C20B 03013 GL TAIL ROTOR LOOSE W K NONE O OTHER IN INSP/MAINT 1 CA 730 (CAN) DURING A DAILY INSPECTION, WE DISCOVERED THAT THE TORQUE OF THE BOLTS HOLDING THE PITCH HORN TO THE TAIL ROTOR BLA DE WAS LOOSE. THE LOCKWIRE WAS STILLIN PLACE BUT THE 2 BOLTS WERE NO LONGER TORQUED.DURING THE DISMANTLING NO OTHER ANOR MALITIES. THE PITCH HORN AND THE TAIL ROTOR BLADE WERE DISMANTLED, CLEANED, CHECKED AND REASSEMBLED IN ACCORDANCE TO THE (BELL HELICOPTER T EXTRON) COMPONENT REPAIR& OVERHAUL MANUAL CHAPTER 4. IF THIS DISCREPANCY HAD NOT BEEN FOUND, IT MIGH T HAVE RESULTED IN A TAIL ROTOR CONTROL LOSS. 1 G 7 1 3U 3 U H2SW E4CE 2001073100356 20010731 00356 EA 2001 7 31 CA010706015 1 20010305 G 2910 LINE CNDAIR CL600 CL6002B19 EA GE CF34 CF343B1 NE HYD SYSTEM LEAKING W O OTHER K J FLUID LOSS WARNING INDICATION CR CRUISE 1 CA (CAN) PILOT REPORT: HYDRAULIC SYSTEM NR 2 LOW PRESSURE MESSAGE DURING CRUISE. FOUND HYDRAULIC SYSTEM NR 2 EMPTY OF FLUID . MAINTENANCE FINDING: FOUND FITTING OF FILL LINE LEAKING (REF IPC 29-11-00-5-270). FOUND FITTING ADAPTER WRONG INSTALLE D ON FILL LINE. INSTALLED SWAGE ADAPTER. REFILLED HYDRAULIC AND REPLACED UNSERVICEABLE EDP. 2 L 7 2 4F 4 F RT A21EA E15NE 2001073100357 20010731 00357 EA 2001 7 31 CA010706016 1 20010505 G 5610 WINDSHIELD CNDAIR CL600 CL6002B19 EA GE CF34 CF343B1 NE COCKPIT CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) FOUND THE CAPTAIN WINDSHIELD INNER PLY CRACKED ON AN UNSCHEDULED MAINTENANCE INSPECTION. WINDSHIELD REPLACED, AIRC RAFT BACK IN SERVICE. 2 L 7 2 4F 4 F RT A21EA E15NE 2001072500557 20010725 00557 EA 2001 7 25 CA010706017 1 20010513 G 7732 ENGINE GE CF343B1 CNDAIR CL600 CL6002B19 EA GE CF34 CF343B1 NE R/H ENGINE FAILED W A UNSCHED LANDING E VIBRATION/BUFFET TO TAKEOFF 1 CA EBU7114 (CAN) ON TAKEOFF R/H ENGINE N2 VIBRATION EXCEEDED LIMITS, IN FLIGH T ENGINE SHUT DOWN CARRIED OUT AND AIRCRAFT RETURNED FOR TROUBLSHOOTING 2 L 7 2 4F 4 F RT A21EA E15NE 2001072500558 20010725 00558 EA 2001 7 25 CA010706018 1 20010513 G 5610 601R330333 WINDSHIELD CNDAIR CNDAIR CL600 CL6002B19 EA GE CF34 CF343A1 30015 NE L/H WINDSHIELD CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 95039H2892 (CAN) LEFT WINDSHIELD CRACKED. WINDSHIELD REPLACED. 2 L 7 2 4F 4 F RT A21EA E15NE 2001073100358 20010731 00358 EA 2001 7 31 CA010706019 1 20010513 G 5610 601R33033 WINDSHIELD CNDAIR CL600 CL6002B19 EA GE CF34 CF343B1 NE COCKPIT FAILED W O OTHER O OTHER CR CRUISE 1 CA (CAN) AT FL330 THE CAPTAIN'S WINDSHIELD SHATTERED. NO CONFIRMATION IF PIECES OF WINDOW DEPARTED AIRCRAFT. REMOVED AND RE PLACED CAPTAIN'S WINDSHIELD IN ACCORDANCE WITH AMM 54-11-01. 2 L 7 2 4F 4 F RT A21EA E15NE 2001073100360 20010731 00360 EA 2001 7 31 CA010706020 1 20010326 G 2460 M81381 HARNESS CNDAIR CL601 CL6012A12 1900303 EA ELECTRICAL CHAFED W K NONE O OTHER IN INSP/MAINT 1 CA 7194 (CAN) A TECHNICIAN WAS WORKING IN AFT FUSELAGE SECTION,PAINTING AROUND APU EXHAUST OUTLET WHEN HE 1ST SMELLED SMOKE.HE T HEN SAW A WIRE BUNDLE ERUPTING INTO SPARKS & FIRE EVEN THOUGH THERE WAS NO CONTACT WITH WIRE BUNDLE WHEN EVENT OCCURRED. THE BATTERY WAS CONNECTED BUT A/C POWER WAS OFF.IT IS ASSUMED THAT THERE WAS AN EXISTING CHAFING CONDITION & THAT WIRE B UNDLE HAD BEEN DISTURBEDDURING APU EXHAUST REMOVAL.ONE CCT BREAKER POPPED ON JB-4 & IT WAS NOT NOTED BY TECH.17 WIRES HA VE BEEN DAMAGED WHERE SOME WERE POWERED BY BATTERY DIRECT BUS.SOME OTHER A/C INSP FOR CHAF ING CONDITIO N & A/C 3025 WIR ING WAS ROUTED SLIGHTLY DIFFERENT.THE CUSTOMER MADE SOME TEMP SPLICES & WILL REPL ALL DAMAGED WIRES SHORTLY. 2 L 7 2 4F RT A21AE 2001073100362 20010731 00362 SW 2001 7 31 CA010711002 1 20010625 G 6230 20601033217 MAST BELL 206 206B 1181511 SW ALLSN 250C 250C20B 03013 GL MAIN ROTOR DAMAGED W K NONE O OTHER IN INSP/MAINT 1 CA 9863 2715 (CAN) WHEN REASSEMBLED 1/2 OF THE SPLIT CONE ASSEMBLY HAD NOT SEATED PROPERLY IN THE GROVE IN THE MAST. MAIN ROTOR MAST NUT TORQUE CHECK WAS CARRIED OUT AFTER 1.3 HOURS OF OPERATION AND TORQUE LOSS WAS NOTED. WHEN DISASSEMBLED AGAIN DAMAGE TO THE SPLINE WAS FOUND. MAIN ROTOR MAST AND SPLIT CONES WERE REPLACED. 1 G 7 1 3U 3 U H2SW E4CE 2001073100365 20010731 00365 EU 2001 7 31 CA010711008 1 20010627 G 2910 HTE400005 CHECK VALVE BAG JETSTM JETSTM3101 1500215 EU GARRTT TPE331 TPE33110UG 01514 WP ROTOL R333 R333482F12 GL HYD SYSTEM CRACKED W O OTHER K FLUID LOSS AP APPROACH 1 CA (CAN) PILOTS WERE NOT ABLE TO EXTEND LANDING GEAR. GEAR WAS PUMPED DOWN (EMERGENCY EXTENSION). AIRCRAFT LANDED WITHOUT I NCIDENT. CHECK VALVE WAS FOUND CRACKED, ALLOWING FLUID TO EXCAPE SYSTEM. NO PHYSICAL DAMAGE THAT COULD CAUSE CRACK WAS E VIDENT. PART REPLACED. SYSTEM CHECKED AND SERVICED AND AIRCRAFT RETURNED TO SERVICE. 2 L 7 2 4T 4 T RT A21EU E4WE 6 C P61GL 2001080100031 20010801 00031 NM 2001 8 1 CA010711014 1 20010622 G 5310 85310776111 WINDOW POST DHAV DHC8 DHC8103 1386005 NM COCKPIT CORRODED W K NONE O OTHER IN INSP/MAINT 1 CA 25978 (CAN) L/H AND R/H FLIGHT COMPARTMENT WINDSHIELD FRAMS P/N 85310776-111 AND P/N 85310776-112 ARE CORRODED AT THE BOTTM OF THE FRAMES. THIS CORROSION WAS FOUND DURING THE SCHEDULED MAINTENANCE GROUND RUNS, PRESSURIZATION LEAK CHECK. A STREAM OF WATER SPOUTED FROM THE L/H WINDSHIELD CORNER. WINDSHIELDS WERE REMOVED AND DURING FURTHER CLEANING AND INSPECTION COR ROSION WAS FOUND ON THE LOWER PORTION OF THE FRAMES. 2 H 7 2 4T RT A13NM 2001080100062 20010801 00062 EA 2001 8 1 CA010711015 1 20010628 G 2460 CE934641 TERMINAL BLOCK DHAV DHC8 DHC8311 1386006 EA PWA PW120 PW123 NE ELECTRICAL OVERHEATED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) TERMINAL BLOCK 2449-TB3 SHOWS SIGN OF OVERHEATING DUE TO CORROSION ON AFT SIDE OF REAR PRESSURE BULKHEAD. THE OVER HEATING OF THE TERMINAL BLOCK RESULTED IN IGNITION OF THE INSULATION ON THE TERMINAL LUG OF FEEDER CABLE 2449-37A0-1. TH E OVERHEATING AND CORROSION WERE FOUND WHEN COMPLYNG WITH DASH 8 SERVICE BULLETIN 8-24-48. 2 H 7 2 4T 4 T RT A13NM E20NE 2001080100065 20010801 00065 EA 2001 8 1 CA010713003 1 20010629 G 8011 NUT DHAV DHC7 DHC7102 2802708 EA PWA PT6 PT6A50 52043 EA HAMSTD 24PF 24PF305 GL STARTER GEN SHEARED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) DURING SCHEDULED MAINTENANCE, FOUND THAT THE NR 4 STARTER/GENERATOR COULD ROTATE 1/4 TURN ON IT'S MOUNT. THE SELF LOCKING NUT ON THE CLAMP HAD NO FRICTION AND BACKED OFF. THE CLAMP WAS LOOSE. THE STARTER HAD SHEARED THE ALIGNMENT PIN. WE REPLACED THE NUT, THE STARTER/GENERATOR AND THE MOUNT. 2 H 7 4 4T 4 T A20EA E4EA 6 C P1NE 2001080100067 20010801 00067 2001 8 1 CA010713011 4 20010704 G 2562 MX1300 BATTERY DHAV DHC2 DHC2MK1 2800102 EA PWA R985 R985AN1 52008 NE ELT WRONG PART W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) DURING BATTERY DUE DATE INSPECTION IT WAS FOUND THAT THE ELT HAD INCORRECT BATTERIES INSTALLED. INSTALLED CORRECT BATTERIES. 1 H 7 1 3R 3 R A806 5E1 2001080100077 20010801 00077 EU 2001 8 1 CA010723001 1 20010621 G 3020 21175789 COMPUTER HONEYWELL BAG BAE146 BAE146200A 1500266 EU LYC ALF502 ALF502R5 41580 NE ENGINE ANTI-ICE MALFUNCTIONED W O OTHER J W WARNING INDICATION INADEQUATE Q C IN INSP/MAINT 1 CA 22539 45209 (CAN) DURING A MAINTENANCE ENGINE RUN, THE NR 1 ANTI-ICE VALVE CIRCUIT BREAKER POPPED AND WOULD NOT RESET. MAINTENANCE R EPLACED THE JUST INSTALLED THRUST MODULATION SYSTEM (TMS) COMPUTER, AND THE PROBLEM WENT AWAY. APPARENTLY, A FAULT IN TH E TMS COMPUTER BLEW THE CIRCUIT BREAKER IN THE OTHER SYSTEM. 2 H 7 4 4F 4 F RT A49EU E6NE 2001072500560 20010725 00560 NM 2001 7 25 CA010723003 1 20010626 G 2910 AN937D6 FITTING BOMBDR AN937D6 DHAV DHC8 DHC8102 2809003 NM PWA 120 PW120A NE HAMSTD 14SF 14SF7 NE FITTING CRACKED W O OTHER K FLUID LOSS IN INSP/MAINT 1 CA (CAN) THE FLIGHT CREW REPORTED A FLUID LEAK FROM THE R/H WING ROOT DURING WALKAROUND. MAINTENANCE INVESTIGATION REVEALED A CRACKED HYDRAULIC "CROSS" FITTING, P/N AN 937 D6. THE FITTING WAS REPLACED AND THE AIRCRAFT WAS RETURNED TO SERVICE. 2 H 7 2 4T 4 T RT A13NM E20NE 6 C P7NE 2001080100080 20010801 00080 NM 2001 8 1 CA010723004 1 20010704 G 2910 DSX252B4012 LINE 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 CA (CAN) THE FLIGHT CREW REPORTED FLUID LEAKING FROM THE NOSEGEAR AREA DURING WALK AROUND. MAINTENANCE INVESTIGATION REVEAL ED THAT THE HYDRAULIC FLEX LINE FOR THE NLG DRAG LINK ACTUATOR "UP" SELECTION WAS LEAKING AT THE AREA OF MAXIMUM FLEX, A DJUCENT TO THE FITTING. THE LINE WAS REPLACED AND THE AIRCRAFT WAS RETURNED TO SERVICE. 2 H 7 2 4T 4 T RT A13NM E20NE 6 C P7NE 2001080100082 20010801 00082 NE 2001 8 1 CA010723041 2 20010714 G 7200 ENGINE LKHEED 1011 10113853 5265020 WP RROYCE RB211 RB211524B402 54555 NE NR 1 DAMAGED W E ENGINE SHUTDOWN R PARTIAL RPM/PWR LOSS DE DESCENT 1 CA (CAN) NR 1 ENGINE STALLED ON TOP OF DESCENT INTO YYZ DURING DECELERATION, ENGINE WAS SHUT DOWN. STALL INSPECTION, ENGINE BOROSCOPE DISCOVERED THAT 1 HP COMPRESSOR BLADE BROKEN OFF AND DAMAGED REMAINING HP COMPRESSOR. 2 L 7 3 4F 4 F A23WE E12EU 2001080100110 20010801 00110 EU 2001 8 1 CA010723043 1 20010716 G 2824 VALVE AIRBUS 310 A310 EU GE CF6 CF680C2A5 NE FUEL TRANSFER FAILED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) ETOP REQUIRED REPORTING. AIRCRAFT COULD NOT TRANSFER ALL THE FUEL FROM CENTER TANK. FQIS RESET AND BITE CHECKED SE RVICEABLE. THIS IS A RECURRING DEFECT WHERE THE FQIS IS REST AND THE DEFECT RETURND A COUPLE OF FLIGHTS LATER ADDITIONAL TROUBLE SHOOTING REQUIRED. 2 L 7 2 4F 4 F RT A35EU E13NE 2001080900101 20010809 00101 NE 2001 8 9 CA010724004 2 20010708 G 7260 4002TO2P03 BEARING SKRSKY S61 S61N 8142104 NE GE CT58 CT581401 30011 NE ACCESSORY DRIVE MAKING METAL W A UNSCHED LANDING J WARNING INDICATION CL CLIMB 1 CA 265 (CAN) INVESTIGATION OF A CHIP LIGHT ON FORWARD CHIP PLUG SHOULD A BUILD UP OF BLACK FUZZY PASTE WITH SOME INDICATION OF FERROUS MATERIAL. ENGINE WAS REMOVED AND DISASSEMBLED. SUBSTANCIAL WEAR WAS FOUND ON ACCESSORY DRIVE GEAR BOX IMPUT PIST ON BEARINGS. PARTS WERE ROUTED TO LAB FOR FURTHER INVESTIGATION. 2 G 7 2 4U 4 U 1H15 1E3 2001080900103 20010809 00103 NE 2001 8 9 CA010724008 2 20010705 G 7210 214040214001 LINER BELL 212040005005 BELL 214 214B1 1182105 SW LYC T55 T5508D 41555 NE GEARBOX UNSERVICEABLE W A UNSCHED LANDING J WARNING INDICATION HO HOVERING 1 CA 7151 1476 AMG28031 (CAN) AFTER RECEIVING CHIP IND. FROM REDUCTION GEARBOX FILTER REMVD FOR INSP. OIL IN FILTER & BOWL FOUND TO BE BLACK WIT H FERROUS MATERIAL PRESENT. REDUCTION GEARBOX THEN REMOVED & INIT INSP REVEALED THAT GEARBOX INPUT GEAR NUT P/N 214-040 -236-001 HAD LOST TORQUE & BACKED OFF OF IMPUT GEAR&INTO SIX ENGINE OUTPUT SHAFT SEAL HOUSING BOLTS P/N MS9566-12. BOTH INPUT GEAR NUT & SIX SEAL HOUSING BOLTS WERE FOUND TO BE SCRAP. IT WAS NOTED THAT APPROX ONE HR EARLIER REDUCTION GEARBO X REMVD TO FACILITATE REPL OF ENGINE OUTPUT SHAFT SEAL HOUSING RE-SHIMMED TO ACCOMMODATE NEW OUTPUT SHAFT (PART OF TORQU E KIT). 2 G 7 1 4U 4 U H6SW E4NE 2001080900109 20010809 00109 NE 2001 8 9 CA010724009 2 20010716 G 8530 399356 ROCKER BOSS AIRTRC AT400 AT401B 0370207 SW PWA R1340 R1340AN1 52016 NE HAMSTD 23D 23D40 NE EXHAUST VALVE CRACKED W A UNSCHED LANDING E VIBRATION/BUFFET NR NOT REPORTED 1 CA 538 (CAN) THE EXHAUST VALVE ROCKER ARM BOSS CRACKED THROUGH THE PIVOT BOLT HOLES WHICH ALLOWED THE ROCKER ARM TO MOVE WITHOU T OPENING THE EXHAUST VALVE, SEVERLY REDUCING ENGINE POWER. FROM DISCUSSIONS WITH SEVERAL AME'S THE CONSENSUS IS THAT OV ERTORQUING OF THE PIVOT BOLT, AT SOME TIME IN THE PAST, COULD CAUSE FATIQUE IN THIS AREA. THIS CYLINDER HAS HAD NO REPAI RS SINCE LAST OVERHAUL. 1 L 7 1 3R 3 R NC A17SW 5E2 6 C P719 2001080900111 20010809 00111 2001 8 9 CA010724011 4 20010710 G 6113 05503671 SPINNER CESSNA 172 172L 2072432 CE LYC O320 O320E2D 41508 EA MCAULY 1C160 1C160DTM GL PROPELLER CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 9127 (CAN) CRACK IN PROPELLER CUTOUT OPENING IN SPINNER NOTED DURING PREFLIGHT INSPECTION. AIRCRAFT WAS GROUNED FOR REPAIRS. 1 H 7 1 3O 3 O NT 3A12 E274 5 N P910 2001080900112 20010809 00112 SW 2001 8 9 CA010724012 1 20010712 G 5320 206031200118 STRAP BELL 206 206B 1181511 SW ALLSN 250C 250C20 03013 GL FUSELAGE CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) WHILE INSTALLING ELECTRICAL EQUIPMENT, A CRACK WAS FOUND ON THE AFT OUTBOARD RADIUS, STATION 100.8. THE CRACK STAR TED FROM THE EDGE OF THE STRAP AT A TOOLING MARK MADE EITHER DURING MANUFACTURE OR PREVIOUS INSTALLATION. THE CRACK IS A PPROXIMATELY 2 1/2 INCHS LONG, MOVING FORWARD AND OUTBOARD. THE STRAP WAS REPLACED. 1 G 7 1 3U 3 U H2SW E4CE 2001080900114 20010809 00114 SW 2001 8 9 CA010724015 1 20010708 G 6220 BEARING BELL 205 205A1 1181414 SW LYC T53 T5313B 41549 NE M/R ROD END WORN W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) WHILE PERFORMING REGULAR MAINTENANCE (DAILY INSPECTION) EXCESSIVE PLAY WAS OBSERVED IN THE M/R DAMPER RODEND ON ON E OF THE DAMPER ASSEBLIES. FURTHER INVESTIGATION REVEALED THAT THE TEFLON LINER (APPROX. 50%) WAS EXTRUDING FROM THE BEA RING. THE BEARING WAS REPLACED AND THE A/C RETURNED TO SERVICE. 1 G 7 1 4U 4 U H1SW E17EA 2001080900116 20010809 00116 CE 2001 8 9 CA010724023 1 20010710 G 2720 ARM CESSNA 188 A188 2073004 CE CONT O520 IO520D 17032 SO MCAULY 2A34C D2A34C98 GL RUDDER BROKEN W K NONE O OTHER IN INSP/MAINT 1 CA 4200 (CAN) RUDDER PEDAL PEDASTAL BROKEN ON LANDING. FOUND THE PEDAL ARM BROKEN DUE TO CORROSION 1 L 7 1 3O 3 O A9CE E5CE 5 C P3EA 2001080900118 20010809 00118 NM 2001 8 9 CA010724026 1 20010714 G 3246 26045641 WHEEL BOEING 727 727260 NM PWA JT8 JT8D17 52049 NE MLG CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 59 (CAN) DURING SERVICE CHECK, NR 1 MAIN WHEEL TIRE PRESSURE FOUND TO BE 40 PSI PRESSURE DETECTED TO BE LEAKING AT WHEEL HU B. NR 1 AND 2 MAIN WHEEL ASSEMBLIES REPLACED, NO FURTHER FAULTS AFTER 8 FLIGHT SEGMENTS. 2 L 7 3 4F 4 F RT A3WE E2EA 2001080900120 20010809 00120 NM 2001 8 9 CA010724027 1 20010718 G 3244 26045611 TIRE BOEING 727 727223 1384074 NM PWA JT8 JT8D15 52051 NE MAIN WHEEL ASSY FLAT W K NONE O OTHER IN INSP/MAINT 1 CA 366 (CAN) NR 3 MAIN WHEEL TIRE FOUND FLAT ON WALKAROUND INSPECTION. MAIN WHEEL REPLACED. NO FURTHER FAULTS ON NEXT FIVE FLIG HT SEGMENTS. 2 L 7 3 4F 4 F A3WE E2EA 2001080900121 20010809 00121 SW 2001 8 9 CA010724031 1 20010607 G 5302 206032400027 BULKHEAD BELL 206031004FM BELL 206 206L 1181522 SW ALLSN 25OC 250C20R GL TAIL BOOM CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 13108 AOKP00649 (CAN) THE TAIL BOOM WAS REMOVED FOR 1200 HOUR INSPECTION. CRACKS WERE FOUND AROUND THE TOP LEFT ATTACH BOLT HOLE SHIM PA RT 206-032-400-117, WHEN THE BULK HEAD WAS REMOVED CRACKS WERE FOUND ALONG THE TOP EDGE OF THE MATING SURFACE OF THE BU LK HEAD AND BOLT ATTACH FITTING PART 206-032-409-001 AND THE RADIUS WHERE THE BULK HEAD ATTACHED TO THE SKIN. THE BULK HEAD WAS REPLACED WITH NEW BELL HELICOPTER PART AS PER THE STRUCTURAL REPAIR MANUAL. 1 G 7 1 3U 3 U H2SW E4CE 2001080900123 20010809 00123 SW 2001 8 9 CA010724032 1 20010607 G 5340 206030111003 FITTING BELL 206 206L 1181522 SW ALLSN 25OC 250C20R GL FUSELAGE CORRODED W K NONE O OTHER IN INSP/MAINT 1 CA 13109 (CAN) THE FITTING WAS FOUND CORRODED ON 1200 HOUR INSPECTION AND NEW PART 206-033-173-001 WAS INSTALLED. THE ORIGINAL P ART IS MANUFACTURED FROM MAGNESIUM WHERE THE NEW PART IS ALUMINUM SO AFTER 13109 OF FLYING ON A AIRCRAFT MANUFACTURED IN 1978 THIS WOULD NOT BE UNUSUAL. WE SHOULD GET MUCH BETTER SERVICE FROM THE ALUMINUM FITTING. 1 G 7 1 3U 3 U H2SW E4CE 2001080900125 20010809 00125 SW 2001 8 9 CA010724033 1 20010523 G 2140 46D36 SWITCH BELL 206 206L3 1182108 SW ALLSN 250C 250C30P 03013 GL HEATER CONTROL MISSING W O OTHER O OTHER CR CRUISE 1 CA (CAN) WHILE IN CRUISE FLIGHT ALL EXPERIENCED A NO HEAT CONDITION. ON INSPECTION, FOR SWITCH WAS REMOVED AND RUDDER PAD O N THE END OF THE PLUNGER WAS FANNED DEBONDED & LODGED IN ORIFICE CAUSING HEATER NOT TO WORK. 1 G 7 1 3U 3 U H2SW E1GL 2001080900126 20010809 00126 WP 2001 8 9 CA010724034 1 20010710 G 6410 269A603523 BLADE HUGHES 269 269C 4470504 WP LYC O360 HIO360D1A 41514 EA TAIL ROTOR CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 3380 (CAN) ON DAILY INSPECTION OUTBOARD PART OF BLADE SKIN WAS FOUND TO BE CRACKED. CRACK IS FORMED AROUND TIP BLOCK ON BLADE . THE CRACK IS APPROX. 3 INCHES LONG, STARTING FROM BEHIND ABRASION STRIP TO ABOUT MIDDLE OF BLADE. 1 G 7 1 3O 3 O 4H12 1E10 2001080900127 20010809 00127 WP 2001 8 9 CA010724035 1 20010710 G 6410 269A603523 BLADE HUGHES 269 269C 4470504 WP LYC O360 HIO360D1A 41514 EA TAIL ROTOR DAMAGED W K NONE O OTHER IN INSP/MAINT 1 CA 2890 (CAN) ON INSPECTION OF OPPOSITE TAIL ROTOR BLADE, THIS TAIL ROTOR BLADE WAS FOUND TO HAVE NO ABRAISON STRIP ON LEADING E DGE OF BLADE. FURTHER INSPECTION REVEALED THAT FILLER WAS USED UNDER PAINT TO BUILD UP EDGE. BOTH BLADES WERE REMOVED AN D SENT TO SCHWEIZER A/C CORP FOR FURTHER INVESTIGATION. 1 G 7 1 3O 3 O 4H12 1E10 2001080900129 20010809 00129 SW 2001 8 9 CA010724036 1 20010709 G 6510 206040272101 SEAL BELL 206 206B 1181511 SW ALLSN 250C 250C20 03013 GL T/R DRIVE SHAFT DAMAGED W K NONE K FLUID LOSS IN INSP/MAINT 1 CA (CAN) ON PRE-FLIGHT INSPECTION, GREASE LEAKAGE ON FORWARD COUPLING ON INPUT DRIVESHAFT WAS NOTED. FURTHER INSPECTION REV EALED THATTHE FORWARD SEAL ASSY HAD FAILED AND ALL THE GREASE IN THE FORWARD COUPLING WAS THROWN OUT WHICH CAUSED AN OVE RHEAT CONDITION. A MORE DETAILED PRE-FLIGHT INSPECTION OF FORWARD AND AFT SEAL ASSEMBLIES FOR RIPS, TEARS AND GREASE LEA KAGE WILL HELP PREVENT AN OVERHEAT CONDITION OR TOTAL DRIVESHAFT FAILURE 1 G 7 1 3U 3 U H2SW E4CE 2001080900130 20010809 00130 CE 2001 8 9 CA010725005 1 20010705 G 5540 04331401 RUDDER HORN CESSNA 150 152 2071835 CE LYC O235 O235L2C 41505 EA MCAULY 1A103 1A103TCM GL VERITICAL STAB CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) UPON COMPLYING WITH AD CF-2000-20 RE. RUDDER INSPECTION, FOUND LOWER RIB P/N 0431004-24 CRACKED. LEVER RUDDER FAIR ING HAD TO BE REMOVED IN ORDER TO REPAIR RIB. UPON FAIRING REMOVAL, FOUND RUDDER HORN CRACKED IN TWO PLACES AT RADIUS. I FEEL THIS DAMAGE WAS CAUSED FRIN WIND DAMAGE AND NO RUDDER LOCK INSTALLED. 1 H 7 1 3O 3 O NT 3A19 E223 5 N P50GL 2001080900137 20010809 00137 SW 2001 8 9 CA010725006 1 20010621 G 3020 8943822 TUBE SWRNGN SA227 SA227AC 8780603 SW GARRTT TPE331 TPE33111U 01514 WP MCAULY 4HFR34 4HFR34C652 NE ANTI-ICE SYS CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) DURING ENGINE CHANGE EGT AND FF WERE HIGH AND RIGGING WAS DIFFICULT. BLEED AIR LEAK WAS FOUND AND THE LINE REPLACE D. ENGINE PARAMETERS WERE NOW NORMAL AND RIGGING WAS ACCOMPLISHED. THE CRACKED TUBE ALSO CAUSED THE ENGINE COWL TO HEAT UP, POSSIBLE FIRE CONSIDERATION. 2 L 7 2 4T 4 T RT A8SW E4WE 6 C 3PNE 2001080900138 20010809 00138 NE 2001 8 9 CA010725007 3 20010710 G 6111 78030S0CN8173881 SEAL CNDAIR CL215 CL2156B11415 EA PWA PW120 PW123 NE HAMSTD 14SF 14SF15 NE PROP SEAL BROKEN W K NONE K FLUID LOSS IN INSP/MAINT 1 CA 4 4 (CAN) THE PROPELLER BLADE SEAL HAD SPRING INSIDE OF IT AND THE TWO ENDS ARE WELDED TOGETHER BY THE MANUFACTURE. THE SPRI NG BROKE AT THE WELDED JOINT CAUSING OIL TO LEAK OUT OF THE HUB AT THE BLADE ROOT. IT WAS NOTICED DURING A D.I AFTER THE FLIGHT. THE SEAL AND SPRING ASSY WAS REPLACED AND THE A/C RETURNED TO SERVICE. 2 H 7 2 4T 4 T RT A14EA E20NE 6 C P7NE 2001080900162 20010809 00162 EU 2001 8 9 CA010725008 1 20010717 G 2910 9603001261 SELECTOR VALVE PILATS PC12 PC1245 EU PWA PT6 PT6A67B 52043 NE HARTZL HCE4A HCE4A3D GL HYD SYSTEM LEAKING W O OTHER J WARNING INDICATION LD LANDING 1 CA 1713 HG40288 (CAN) PILOTS REPORTED A INTERMITTENT PROBLEM WITH THE HYDRAULIC LIGHT COMING ON WHEN LANDING. THIS INDICATES THE HYDRAUL IC PUMP CYCLED 6 TIMES IN 1 HOUR. AFTER SERVICING THE SYSTEM THE PROBLEM WOULD STILL OCCUR. IT WAS DECIDED TO CHANGE THE HYDRAULIC SERVICE SELECTOR VALVE. THE PROBLEM DID NOT RETURN AFTER THIS. 1 L 7 1 3T 4 T RT A78EU E26NE 5 C P210NE 2001080900164 20010809 00164 EU 2001 8 9 CA010725010 1 20010719 G 2822 9688411404 PUMP PILATS PC12 PC1245 EU PWA PT6 PT6A67B 52043 NE HARTZL HCE4A HCE4A3D GL FUEL BOOST UNSERVICEABLE W O OTHER J WARNING INDICATION DE DESCENT 1 CA 1458 1458 (CAN) BOOST PUMP FAILED CAUSING FUEL IMBALANCE. AIRCRAFT LANDED AND PUMP REPLACED. 1 L 7 1 3T 4 T RT A78EU E26NE 5 C P210NE 2001080900170 20010809 00170 EU 2001 8 9 CA010725013 1 20010710 G 2752 9787320001 DRIVE GEAR PILATS PC12 PC1245 EU PWA PT6 PT6A67B 52043 NE HARTZL HCE4A HCE4A3D GL TE FLAPS FAILED W O OTHER F FLT CONT AFFECTED AP APPROACH 1 CA 2126 (CAN) PILOTS REPORTED FLAP SYSTEM 1 AMP CIRCUIT BREAKER ON BATTERY BUS TRIPPED WHEN FLAP SELECTED DOWN. THE SYSTEM WOULD FUNCTION NORMAL IF THEY KEPT THE AIR SPEED BELOW 140 KNOTS. THE FAILURE COULD NOT BE DUPLICATED ON THE GROUND. THE FLAP POWER DRIVE UNIT WAS REPLACED. THE AIRCRAFT WAS FLOWN AND FLAPS EXTENDED AT MAX EXTENSION SPEED AND SYSTEM FUNTIONED NO RMAL. 1 L 7 1 3T 4 T RT A78EU E26NE 5 C P210NE 2001080900171 20010809 00171 EU 2001 8 9 CA010725014 1 20010710 G 2510 9593001216 SEAT BACK PILATS PC12 PC1245 EU PWA PT6 PT6A67B 52043 NE HARTZL HCE4A HCE4A3D GL COCKPIT CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 2135 (CAN) THE SEAT WAS REMOVED TO REPAIR BROKEN UP/DOWN ADJUSTMENT AND THE SEAT BACK WAS FOUND CRACKED. THE CRACKS WERE FOUN D TO BE ONLY IN THE PLASTIC PART OF THE ALUMINUM STRAPS WERE NOT CRACKED, THE PART WAS REPLACED WITH A NEW UNIT. 1 L 7 1 3T 4 T RT A78EU E26NE 5 C P210NE 2001080900172 20010809 00172 EA 2001 8 9 CA010725019 1 20010705 G 7120 MOUNT CNDAIR CL600 CL6002B19 EA GE CF34 CF343B1 NE ENGINE CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) DURING SUPPORT BEAM INSPECTION, AS PER SB601R-53-059, CRACKS WERE FOUND AT BL0 AND LBL36. 2 L 7 2 4F 4 F RT A21EA E15NE 2001080900173 20010809 00173 EU 2001 8 9 CA010725020 1 20010704 G 6720 LINER SNIAS 350 AS350BA 8680817 EU TMECA ARRIEL ARRIEL1B 6OO30 NE T/R BEARING CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) THE BEARING LINER WAS FOUND CRACKED IN BOTH TAIL ROTOR PITCH LINKS. THE SAME PROBLEM HAS BEEN REPORTED IN THE PAST . 1 G 7 1 3U 3 U NC H9EU E19EU 2001080900175 20010809 00175 SW 2001 8 9 CA010725021 1 20010703 G 2550 204075157001 SLIP RING BELL 212 212 1181420 SW PWA PT6T PT6T3B 52045 NE CARGO HOOK DEBONDED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) PILOT REPORTED PROBLEMS WITH ELECTRICAL RELEASE ON CARGO HOOK ASSEMBLY. SUSPENSION ASSEMBLY LATER DISASSEMBLED AND FOUND THAT INNER RING ON SLIP RING ASSEMBLY HAD DISBONDED PREVENTING PROPER CONTACT. THE SLIP RING ASSEMBLY WAS REPLACE D WITH NEW PART AND UNIT REASSEMBLED. THE SUSPENSION ASSEMBLY WAS REINSTALLED IN THE AIRCRAFT AND SYSTEMCHECKED SERVICEA BLE. THE SLIP RING ASSEMBLY ( THAT IS; DEBONDING AND PITTING) IS A COMMON SOURCE OF PROBLEMS WITH THE SUSPENSION ASSEMBL Y. 1 G 7 1 4U 4 U H4SW E22EA 2001080900178 20010809 00178 SW 2001 8 9 CA010725022 1 20010703 G 7500 ARM BELL 206 206L 1181522 SW ALLSN 250C 250C20R2 GL ACTUATOR DAMAGED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) FOUND NUT OF ACTUATOR ARM LOOSE IN ARM. UNIT REPLACED AND AIRCRAFT RETURNED TO SERVICE AFTER ADJUSTMENTS. 1 G 7 1 3U 3 U H2SW E4CE 2001080900179 20010809 00179 SW 2001 8 9 CA010725023 1 20010703 G 5302 206031329003 FITTING BELL 206 206L 1181522 SW ALLSN 250C 250C20R2 GL TAIL BOOM CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) THE FITTING HAD TO BE REPLACED DUE TO CRACK. IT APPEARS TO HAVE CRACKED DUE TO INCORRECT INSTALLATION. THERE WAS A 100 INCH GAP BETWEEN THE LONGERON AND THE FITTING AND THIS PLACED THE FITTING UNDER STRESS. THE FITTING WAS REPLACED BY A NEW PART WITH CARE TAKEN TO ENSURE NO GAP WAS PRESENT ON THE NEW PART INSTALLATION. 1 G 7 1 3U 3 U H2SW E4CE 2001080900181 20010809 00181 EU 2001 8 9 CA010725024 1 20010704 G 6710 350A371508 ROD END SNIAS 350 AS350D 8680803 EU LYC LTS101 LTS101600A2 41560 NE MAIN ROTOR SEPARATED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) DURING POST FLIGHT INSPECTION OF AIRCRAFT IT WAS NOTICED THAT THE MAIN ROTOR PITCH LINK ROD AND RETAINER HAD SEPAR ATED FROM ROD END. PILOT CONFIRMED THAT ON PREVIOUS FLIGHT HE HAD STARTED TO EXPERIENCE A MAIN ROTOR VIBRATION. MAIN ROT OR AND SWASHPLATE ASSEMBLIES INSPECTED BY MAINTENANCE. NO OTHER DAMAGE FOUND. THE MAIN AIRCRAFT WAS FLIGHT TESTED AND RE TURNED TO SERVICE. 1 G 7 1 3U 3 U H9EU E5NE 2001080900183 20010809 00183 NE 2001 8 9 CA010725026 2 20010626 G 8510 16475 CASE DHAV DHC2 DHC2MK1 2800102 EA PWA R985 R985AN14B 52008 NE ENGINE LEAKING W K NONE K FLUID LOSS IN INSP/MAINT 1 CA 562 (CAN) SMALL OIL LEAK ON NOSE SECTION. REMOVED NOSE SECTION AND DISCOVERED CRACK RADIATING FROM BOLT HOLE IN BEARING BORE OF FRONT ENGINE CASE. REMOVED ENGINE FOR REPLACEMENT. 1 H 7 1 3R 3 R A806 5E1 2001080900184 20010809 00184 SW 2001 8 9 CA010725031 1 20010703 G 2810 206063688001 HOSE 206063600 BELL 206 206L 1181522 SW ALLSN 250C 250C20R2 GL FUEL SYSTEM LEAKING W K NONE K FLUID LOSS IN INSP/MAINT 1 CA (CAN) DURING REFUELING OPERATION, FUEL WAS OBSERVED LEAKING FROM TANK VENT HOSE ASSEMBLY WHEN TANK WAS FILLED TO CAPACIT Y. HOSE APPEARS TO HAVE DETERIORATED WITH AGE ALLOWING FUEL TO LEAK. DUE TO THIS DEFECT ANOTHER AIRCRAFT WAS VERIFIED BY PRESSURE TESTING THE VENT HOSE ASSEMBLY. IT WAS ALSO FOUND TO BE LEAKING. BOTH AIRCRAFT HOSES WERE REPLACED AND SYSTEMS CHECKED SERVICEABLE. MANUFACTURER OF AIRCRAFT CURRENTLY DOES NOT HAVE A RETIREMENT OR TEST SCHEDULE FOR THESE FLEXIBLE HOSES. 1 G 7 1 3U 3 U H2SW E4CE 2001080900191 20010809 00191 NE 2001 8 9 CA010725032 1 20010705 G 3231 7625100702043 LINK SKRSKY S76 S76A 8143006 NE ALLSN 250C 250C30S 03013 GL MLG DOOR SHEARED W O OTHER J WARNING INDICATION LD LANDING 1 CA 1882 (CAN) DURING MAIN LANDING GEAR RETRACTION AND EXTENSION PILOTS NOTED A SLIGHT YAW. THEY ASSUMED IT TO BE CASUED BY DIFFE RNECE IN RETRACTION RATES OF LANDING GEAR. UPON LANDING AT BASE, THE ENGINEER NOTED THAT THE GEAR DOOR WAS LOWER THAN TH E RIGHT. INVESTIGATION REVEALED THAT THE LANDING GEAR DOOR LINK WAS REPLACED WITH A NEW ONE AND THE SYSTEM WAS FUNCTION CHECKED SERVICEABLE. AIRCRAFT RETURNED TO SERVICE. 1 G 7 2 3U 3 U H1NE E1GL 2001080900196 20010809 00196 NE 2001 8 9 CA010725033 1 20010705 G 2910 7665103004041 TUBE SKRSKY S76 S76A 8143006 NE ALLSN 250C 250C30S 03013 GL HYD SYSTEM LEAKING W H DEACTIVATE SYST/CIRCUITS K J FLUID LOSS WARNING INDICATION CR CRUISE 1 CA (CAN) APPROX. 10 MINS AFTER TAKEOFF UNUSUAL LOW WHISTLING SOUND NOTICED BY ONE OF PILOTS, FOLLOWED SHORTLY THEREAFTER BY NR 2 SERVO WARMING LIGHT ILLUMINATING & NR 2 HYDRAULIC PRESSURE CYCLING BETWEEN 1000 & 3000PSI. SWITCHED OFF #2 SERVO S WITCH AT WHICH TIME HYDRAULIC PRESSURE IND. RETURNED TO NORMAL (INDICATIVE OF LEAK AFT OF SERVO SHUTOFF VALVE. EMERG CHE CKLIST FOR "LOSS OF HYD. PRESSURE" PREFORMED. PILOTS REVERSED COURSE&CARRIED OUT PRECAUTIONARY LDG W/O INCID.. POST FLT INSP REVEALED FLUID LEAKING OUT OF BELLY AREA AFT OF BAGGAGE COMPT & NR 2 HYDRAULIC RESERVOIR BELOW MIN.LEVEL. MAINT INV EST. FOUND FLUID LEAK FROM PINHOLE IN NR 2 TAIL ROTORPRESSURE TUBE. TUBE REPL ALONG WITH HYDRAULIC PUMP DUE TO 1 G 7 2 3U 3 U H1NE E1GL 2001080900199 20010809 00199 EA 2001 8 9 CA010726001 1 20010715 G 7120 60135006 MOUNT CNDAIR CL600 CL6002B19 EA GE CF34 CF343B1 NE ENGINE CRACKED W K NONE K FLUID LOSS IN INSP/MAINT 1 CA 19370 (CAN) DURING AN OPPORTUNITY INSPECTION OF THE ENGINE BEAM, CRACKS WERE FOUND ON THE CENTER SECTION. (REF ASB 601R-53-069 .) 2 L 7 2 4F 4 F RT A21EA E15NE 2001080900200 20010809 00200 EA 2001 8 9 CA010726006 1 20010705 G 7120 MOUNT CNDAIR CL600 CL6002B19 EA GE CF34 CF343B1 NE ENGINE CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) DURING AN OPPORTUNITY INSPECTION OF THE ENGINE SUPPORT BEAM, CRACKS WERE FOUND ON THE CENTER SECTION. SEE ASB 2 L 7 2 4F 4 F RT A21EA E15NE 2001080900206 20010809 00206 EU 2001 8 9 CA010726008 1 20010703 G 6220 350A37116200 YOKE SNIAS 350 AS350BA 8680817 EU TMECA ARRIEL ARRIEL1B 6OO30 NE MAIN ROTOR BROKEN W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) ONE OF THE THREE DROOP RESTRAINT STOP YOKES WERE FOUND BROKEN IN TWO PIECES. MAIN ROTOR HEAD AND BLADES INSPECTED AND NO ADDITIONAL DAMAGE FOUND. YOKE REPLACED. 1 G 7 1 3U 3 U NC H9EU E19EU 2001080900207 20010809 00207 NE 2001 8 9 CA010726012 1 20010705 G 3200 7655200904046 HARNESS SKRSKY S76 S76A 8143006 NE ALLSN 250C 250C30S 03013 GL MLG BROKEN W O OTHER D INFLIGHT SEPARATION CR CRUISE 1 CA (CAN) DURING CRUISE, RED LANDING GEAR UNSAFE LIGHT FLICKERING INTERNITTENTLY WITH A CORRESPONDING "CLUNKING" IN THE AIRF RAME FELT THROUGH THE COLLECTIVE STICK. UPON RETURN FROM FLIGHT MAINTENACE PUT AIRCRAFT ON JACKS AND THE LANDING GEARWAS OPERATED TO SIMULATE THE CONDITION. THE FAULT WAS TRACED TO THE LEFT MAIN DOWN LOCK WIRING HARNESS. THE HARNESS WAS REP LACED WITH A NEW ONE. THE SYSTEM WAS FUNCTION TESTED SERVICEABLE AND THE AIRCRAFT WAS RETURNED TO SERVICE. 1 G 7 2 3U 3 U H1NE E1GL 2001080900213 20010809 00213 CE 2001 8 9 CA010726014 1 20010620 G 7603 K30B22HT WIRE GARRTT TFE73122B LEAR 35 35LEAR 5170600 CE GARRTT TFE731 TFE73122B 01518 WP ENGINE FAILED W C ABORTED TAKEOFF H ELECT. POWER LOSS-50 PC TO TAKEOFF 1 CA P74114C (CAN) ON TAKE OFF ROLL, ENGINE SLUGGISH, R/H FUEL COMPUTER LIGHT ON (COMPUTER KICKED OFF), ABORT TAKEOFF, CAME BACK TO M AINTENACE HANGAR (MAIN BASE). N2 MONOPOLE FAULT APPEARS, CODE 14 ON DITAL ENGINE COMPUTER DOWNLOAD. WIRE K30B22HT SUSPEC TED TO CAUSE THE FAULT BETWEEN CONNECTORS P360 & P358. WIRE REPLACED WITH NEW ONE. GROUND RUN CARRIED OUT. HIGH SPEED TA XIING CARRIED OUT. NO MORE FAULT FOUND. A/C RETURNED TO SERVICE. 2 L 7 2 4F 4 F A10CE E6WE 2001080900217 20010809 00217 WP 2001 8 9 CA010726024 1 20010606 G 6310 369D25351 SPRAG CLUTCH HUGHES 369 369D 4470706 WP ALLSN 250C 250C20B 03013 GL TRANSMISSION BROKEN W K NONE O OTHER IN INSP/MAINT 1 CA 392 (CAN) O/R CLUTCH ASSY WAS REMOVED FOR O/H. UPON O/H INSPECTION IT WAS FOUND THAT THE SPRAG ASSY HAD ONE BROKENSPRAG. THE BROKEN PIECE WAS RECOVERED FROM INSIDE THE ASSEMBLY. 1 G 7 1 3U 3 U H3WE E4CE 2001080900218 20010809 00218 2001 8 9 CA010726025 4 20010726 G 3457 114DD26 RELAY CESSNA 208 208B 2073701 CE PWA PT6 PT6A114A 52043 NE MCAULY 3AF34C 3GFR34C703 GL GPS UNSERVICEABLE W A UNSCHED LANDING H ELECT. POWER LOSS-50 PC CR CRUISE 1 CA (CAN) HSI LT/RT DEVIATION REAMINS CENTERED WHEN GPS IS SELECTED WITH NO FAILURE WARNING/INDICATION GPS LAMP REMAINED ON, GPS & TO FROM FLAGS REMAINED VALID). RELAY K2 IN AVIONICS J-BOX #1 FAILED TO ENERGIZE WHEN GPS WAS SELECTED. REPLACED K 2. NOTE: TC ENGINEERING REQUIRES THAT THE GPS LAMP BE INTERLOCKED THROUGH ALL RELAYS. IF A SINGLE RELAY WERE TO FAIL, TH E GPS LAMP WOULD EXTINGUISH. TH 208/B SWITCHING SYSTEM WAS APPROVED IN THE USA WITHOUT SUCH INTERLOCKS. HSI (GS) VERTICA L DEVIATION POINTER IS DRIVEN DURING GPS SELF TEST. FOUND GPS VERTICAL DEVIATION WIRES CONNECTED TO CESSNA J-BOX. CAPPED AND STOWED GPS VERTICAL DEVIATION WIRES AT AVIONICS J-BOX #2. 1 H 7 1 3T 3 T A37CE E4EA 5 C P60GL 2001080900219 20010809 00219 EU 2001 8 9 CA010726026 1 20010724 G 3411 0851HL PROBE AIRBUS 330 A330322 3930325 EU PWA 4168 PW4168 NE PITOT SYSTEM BLOCKED W C ABORTED TAKEOFF N FALSE WARNING TO TAKEOFF 1 CA (CAN) A/C ARRIVED WITH CAPTS. AIRSPEED READING INCORRECTLY. MTCE SWAPPED ADIRU #1 INTO #3 POSITION TO DEFER WITH LEAST A MOUNT OF IMPACT. A/C DEPARTED AND REJECTED T/O. ADM WAS OBTAINED FROM AIR CANADA AND INSTALLED IN A/C SSV. AVIONICS WAS CALLED IN TO C/O PITOT STATIC CHECK. FAULT STILL PRESENT. PITOT LINE REMOVED BETWEEN CAPT. PITOT PROBES AND ADM AND FOUN D BLOCKED. DEBRIS REMOVED FROM LINE AND PROBE SYST. TESTED SERVICEABLE WITH PITOT STATIC TEST SET. A/C DECLARED SERVICEA BLE 7:30 HOURS. 2 L 7 2 4F 4 F RT A46NM E36NE 2001080900221 20010809 00221 SW 2001 8 9 CA010726027 1 20010726 G 6510 407340339103 BEARING 4070403031 BELL 407 407 SW ALLSN 250C 250C47B GL FAN SHAFT NOISY W K NONE O OTHER IN INSP/MAINT 1 CA 1256 (CAN) AFTER NORMAL UNEVENTFUL FLT, PILOT SHUTDOWN A/C&NOTICED NOISE COMING FROM TAIL ROTOR DRIVE TRAINN DURING COAST DOW N. SUBSEQUENT INSP REVEALED THATT HE GREASE EMANATING FROM AFT FAN SHAFT BEARING BLACK WITH METALLICPARTICLES, BEARING R OUGH WHEN ROTATED USING DRIVE TRAIN BY HAND&MORE PLAY IN BEARING THAN IS NORMALLY FELT WHEN LOADED IN LATERAL&FORE&AFT D IRECTION BY HAND. NO ANCILLARY DAMAGE. BEARING WS REPL WITH NEW BEFOREFURTHER FLT. HAVE BEEN OTHER FAILURES OF TYPE ON B ELL 407 RESULTING IN TC AD CF-2000-02 REQ 25 HR INSP&LUBE OF THESE BEARINGS. PLEASE NOTE THAT BEARING FAILED 13.7 HRS AF TER SUCH INSP.THE INSP AT THAT TIME DID NOT REVEAL ANY PAR 1 G 7 1 3U 3 U O H2SW E1GL 2001080900222 20010809 00222 SW 2001 8 9 CA010726028 1 20010724 G 6510 407340339103 BEARING 407040303101 BELL 407 407 SW ALLSN 250C 250C47B GL FAN SHAFT DISINTEGRATED W A UNSCHED LANDING O OTHER CL CLIMB 1 CA 1233 (CAN) SHORTLY AFTER TAKEOFF, ABOUT 400 FT ABOVE GROUND, A/C SOUND & VIBRATION LEVELS SUDDENLY CHANGED FROM NORMAL TO HEA VY VIBRATION THROUGHOUT WHOLE A/C WITH OSCILLATING, DRONING NOSIE. AS WELL, PILOT NOTICED PULSING FEEDBACK SE NSATION FR OM ANTITORQUE PEDALS. PILOT IMMEDIATELY ABORTED CLIMB&CARRIED OUT PRECAUTIONARY DESCENT&NORMAL LDG W/O INCID.. TAIL ROTO R CNTL AUTH NEVER LOST. AFTER ENGINE SHUTDOWN, INSP REVEALED COMPLETELY FAILED FWD FAN SHAFT BEARING WITH DISINTIGRATED BEARING CAGES & BALLS EJECTED INTO IMPELLER. ANCILLARY DAMAGE TO IMPELLER, SHAFT&OIL COOLER BLOWER HOUSING. THER HAVE BE EN OTHER FAILURES OF TYPE ON BELL 407 RES ULTING IN TC AD CF-2000-02 REQ 1 G 7 1 3U 3 U O H2SW E1GL 2001080900223 20010809 00223 EU 2001 8 9 CA010726034 1 20010725 G 6520 350A33212900 PLATE 350A33200403 SNIAS 350 AS350BA 8680817 EU TMECA ARRIEL ARRIEL1B 6OO30 NE TAIL ROTOR WORN W K NONE O OTHER IN INSP/MAINT 1 CA 428 V231292 (CAN) BLACK PAINT INDEX MARKS MISALIGNED AND OUTBAOARD SPACER FREE TO ROTAT. UNIT IS POST MOD 07-6554 PART 2.B.3 AND POS T MOD 07-6551. RECEIVED IN SHOP, DOUBLE LOCKING OF NUT VERIFIED ALL VISIBLE ELEMENTS INBOARD OF BEARING FELT TIGHT AND S ECURE, NUT UNLOCKED AND TORQUE APPLIED. NUT ROTATED 30 DEGREES PRIOR TO ACHIEVING MINIMUM TORQUE LOAD. UNIT DISASSEMBLED , ALL SPACERS AND BEARING INNER RACE EXHIBITED SIGNS OF ROTATION. BEARING INNER RACE HAS WORN THROUGH THE D148 VARISH AN D INTO PARENT MATERIAL OF ROTATING PLATE (350A33-2129-00). 1 G 7 1 3U 3 U NC H9EU E19EU 2001080900224 20010809 00224 EU 2001 8 9 CA010726035 1 20010725 G 2400 350A61131201 CIRCUIT BOARD SNIAS 350 AS350BA 8680817 EU TMECA ARRIEL ARRIEL1B 6OO30 NE BUCKET RELEASE CORRODED W O OTHER O OTHER NR NOT REPORTED 1 CA (CAN) UNABLE TO PERFORM WATER BUCKET OPERATIONS (FIRE SUPPRESSION) DUE TO ELECTRICAL DEFECT. TROUBLESHOOTING CARRIED OUT ON SYSTEM AND PRINTED CIRCUIT BOARD 25 IDENTIFIED AS CAUSE DUE TO HAEAVY CORROSION ON CONTACT POINTS OF BOARD. BOARD WA S REPLACED WITH NEW UNIT AND SYSTEM CHECKED SERVICEABLE. THIS BOARD ALSO CONTROLS OTHER AIRCRAFT SYSTEMS SUCH AS COMMUNI CATIONS, CARGO HOOK OPERATIONS, ETC. IT IS CURRENTLY NOT PART OF THE MANUFACTURE'S INSPECTION PROGRAM AS A POINT OF INSP ECTION. 1 G 7 1 3U 3 U NC H9EU E19EU 2001080900226 20010809 00226 NM 2001 8 9 CA010726036 1 20010716 G 2720 401602728A COMPUTER BOEING 727 727172C 1384058 NM PWA JT8 JT8D7B 52053 NE FEEL SYSTEM CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) POST INSTALLATION DURING FUNCTIONAL TEST THE UNIT DISCOVERED TO BE LEAKING. AFTER REMOVAL OF THE FEEL COMPUTER IT WAS NOTICED THAT A CRACK APPROX. 3 INCHES IN LENGTH WAS WMITTING FROM THE ACTUATOR MOUNTING COVER. THE CRACK ITSELF IS L OCATED ON THE CHAMBER. THIS UNIT WAS RECENTLY OVERHAULED BY AVBORNE ACCESSORY GROUP INC. 2 L 7 3 4F 4 F A3WE E2EA 2001080900227 20010809 00227 WP 2001 8 9 CA010726038 1 20010630 G 7920 6843698 INSULATOR ALLSN 501D13D CVAC 440 440 2422902 WP ALLSN 501D 501D13D 03004 GL INSULATOR DAMAGED W K NONE O OTHER IN INSP/MAINT 1 CA 705276 (CAN) FOUND INSULATOR MISSING ON SERVICE CHECK NEW PART INSTALLED. NO OTHER PROBLEM FOUND AND A/C RETURNED TO SERVICE. L T ENGINE REAR SCAVENGE PUMP INSULATOR WAS MISSING IT HAD BEEN REPORTED BY GROUND PEOPLE THAT A PART FALL FROM AIRCRAFT O N APPRAOCH TO LAND IN WINNIPEG. NORMAL INSPECTION CALL TO VERIFY PRESENCE OF INSULATOR. 2 L 7 2 4R 4 T 6A6 E282 2001080900228 20010809 00228 SW 2001 8 9 CA010727001 1 20010704 G 6510 R34665 TURBINE 2040625401 BELL 205 205A1 1181414 SW LYC T53 T5313B 41549 NE COOLER BLOWER CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 9209 322 417 (CAN) VIBRATION ON BLOWER ASSY. EXAMINE BLOWER ASSY & FOUND TWO CRACKS ON THE ROOT OF TWO BLADE. 1 G 7 1 4U 4 U H1SW E17EA 2001080900229 20010809 00229 EA 2001 8 9 CA010727008 1 20010607 G 6310 269A55593 SHAFT 259A55593 SCWZER 269 269D 8059501 EA LYC O360 HIO360D1A 41514 EA ENGINE ADAPTER BROKEN W K NONE O OTHER IN INSP/MAINT 1 CA 4138 5424 (CAN) BROKEN TEETH ON SHAFT ON ENGINE ADAPTER SIDE. REPLACE SHAFT. 1 G 7 1 3U 3 O 0 4H12 1E10 2001080900230 20010809 00230 EA 2001 8 9 CA010727009 1 20010707 G 6320 CR3687 SEAL SCWZER 269 269D 8059501 EA LYC O360 HIO360D1A 41514 EA MAIN ROTOR LEAKING W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) OIL SEAL LEAKING IN RPM CABLE. REPLACE OIL SEAL PN CR 3687. 1 G 7 1 3U 3 O 0 4H12 1E10 2001080900233 20010809 00233 EA 2001 8 9 CA010727010 1 20010607 G 6220 269A1227817 BEARING SCWZER 269 269D 8059501 EA LYC O360 HIO360D1A 41514 EA MAIN ROTOR WORN W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) BEARING WORN INSIDE. REPLACE ALL 3 GRIP BEAR IN SET. 1 G 7 1 3U 3 O 0 4H12 1E10 2001080900234 20010809 00234 EA 2001 8 9 CA010727011 1 20010707 G 6220 269A1231 BEARING 269A12215 SCWZER 269 269D 8059501 EA LYC O360 HIO360D1A 41514 EA MAIN ROTOR RATCHETING W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) BEARING RACHET WHEN INSPECTION. REPLACE BEARING. 1 G 7 1 3U 3 O 0 4H12 1E10 2001080900235 20010809 00235 EA 2001 8 9 CA010727014 1 20010707 G 2140 269A4799003 BRACKET 269A4799001 SCWZER 269 269D 8059501 EA LYC O360 HIO360D1A 41514 EA HEATER CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) BRACKET CRACK . REPLACE BRACKET. 1 G 7 1 3U 3 O 0 4H12 1E10 2001080900239 20010809 00239 SW 2001 8 9 CA010727015 1 20010607 G 5302 206032400027 BULKHEAD 206032400177 BELL 206 206L 1181522 SW ALLSN 25OC 250C20R GL TAIL BOOM CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 13108 AOKP00649 (CAN) THE TAIL BOOM WAS REMOVED FOR 1200 HOUR INSPECTION. CRACKS WERE FOUND AROUND THE TOP LEFT ATTACH BOLT HOLE SHIM PA RT # 206-032-400-117. WHEN THE BULKHEAD WAS REMOVED, CRACKS WERE FOUND ALONG THE TOP EDGE OF THE MATING SURFACE OF THE B ULKHEAD AND BOLT ATTACHMENT FITTING #206-032-409-001, AND THE RADIUS WHERE THE BULKHEAD ATTACHES TO THE SKIN. THE BULKHE AD WAS REPLACED WITH NEW BHTC PART AS PER THE SRM. 1 G 7 1 3U 3 U H2SW E4CE 2001080900241 20010809 00241 NM 2001 8 9 CA010727016 1 20010718 G 3244 TIRE BOEING 727 727227 1384078 NM PWA JT8 JT8D9A 52048 NE MLG FAILED W O OTHER O OTHER LD LANDING 1 CA (CAN) THE NR 1 TIRE THREAS SEPARATED FROM THE CARCASS DURING T/O ROTATION. DAMAGE ON EXTERIOR OF THE WING DOOR. THE NR 2 TIRE FAILED ON TAXI INTO RAMP IN YYC. 2 L 7 3 4F 4 F A3WE E2EA 2001080900242 20010809 00242 GL 2001 8 9 CA010727017 2 20010720 G 7210 GEARBOX CVAC 340 340CVAC 242270A WP ALLSN 501D 501D22 03005 GL ENGINE LEAKING W A UNSCHED LANDING K J FLUID LOSS WARNING INDICATION CL CLIMB 1 CA (CAN) DURING CLIMB THROUGH FL170 AFTER DEPARTURE NOTICED NR 2 GEAR BOX OIL PRESSURE FLICKERING. OIL PRESSURE WAS STILL I N THE GREEN RANGE AND THE POWER SECTION OIL PRESSURE WAS NORMAL. ENGINE SHUT DOWN AND AIRCRAFT DIVERTED INTO YYZ. 2 L 7 2 4R 4 T 6A6 E282 2001080700223 20010807 00223 NM 2001 8 7 CA010727020 1 20010718 G 2910 271N61191 HYDRAULIC LINE 273N20025 BOEING 757 75723A 1384967 NM RROYCE RB211 RB211535E437 54555 NE RUPTURED @ MIDPT LEAKING W D RETURN TO BLOCK K FLUID LOSS TX TAXI/GRND HDL 1 CA (CAN) AIRCRAAFT RETURNED TO THE GATE, AFTER PUSH BACK, DUE TO A HYDRAULIC LEAK AT THE L/H MAIN LANDING GEAR DOWNLOCK AC TUATOR SUPPLY FLEX LINE. LINE WAS FOUND RUPTURED AT MID POINT. LINE WAS REPLACED AND AIRCRAFT WAS RETURNED TO SERVICE. 2 L 7 2 4F 4 F RT A2NM E12EU 2001080900243 20010809 00243 NM 2001 8 9 CA010727023 1 20010727 G 2730 BUSHING 2827001011 BOEING 767 767233 NM PWA JT9 JT9D7R4D 52054 NE ACTUATOR LOOSE W O OTHER O OTHER CR CRUISE 1 CA (CAN) BUFFETING FELT THROUGH THE FLIGHT AND INCREASE IN FREQUENCY DURING CLIMB OUT. THE LEFT ELEVATOR WAS INDICATING LOW ER THAN THE RIGHT AND WOULD FLUCTUATE UPWARD. INVESTIGATION REVEALED LEFT END OUTBOARD POWER ACTUATOR (P.C.A.) EYE END B USHING LOOSE AND SUPPORT TRUNNION LOOSE. REPLACED ACTUATOR AND TRUNNION. 2 L 7 2 4F 4 F RT A1NM E3NE 2001080700224 20010807 00224 WP 2001 8 7 CA010727026 1 20010711 G 2751 0070J TRANSMITTER DOUG DC9 DC932 3022066 WP PWA JT8 JT8D7 52053 NE TRANSMITTER FAILED W O OTHER O OTHER AP APPROACH 1 CA (CAN) STALL WARNING OCCURRED SEVERAL TIMES DURING APPROACH WITH SPEED ABOVE 220 KTS. REPLACED FLAP POSITION TRANSMITTER. 2 L 7 2 4F 4 F A6WE E2EA 2001080700225 20010807 00225 NM 2001 8 7 CA010727027 1 20010705 G 2912 2705579 CLAMP BOEING 737 737296 1384486 NM PWA JT8 JT8D9A 52048 NE CLAMP W D RETURN TO BLOCK K FLUID LOSS TO TAKEOFF 1 CA (CAN) HYDRAULIC LOSS OF SYSTEM A AFTER TAKE OFF, AIRCRAFT RETURNED. BROKEN CLAMP ON THE RETURN FILTER BOWL. NEW CLAMP IN STALLED, AND FILTER ELEMENT CHANGED. 2 L 7 2 4F 4 F RT A16WE E2EA 2001080700226 20010807 00226 NM 2001 8 7 CA010727029 1 20010704 G 4910 732138701 ACTUATOR 732138701 BOEING 767 767233 NM PWA JT9 JT9D7R4D 52054 NE ACTUATOR W K NONE O OTHER CR CRUISE 1 CA (CAN) BUFFETING FELT THROUGH THE FLIGHT AND INCREASED IN FREQUENCY DURING CLIMB OUT. FOUND TO BE THE APU DOOR ACTUATOR A T FAULT. HALF INCH PLAY IN ACTUATOR BEARING AND SEAL DAMAGE. REPLACED THE APU DOOR ACTUATOR. 2 L 7 2 4F 4 F RT A1NM E3NE 2001080900244 20010809 00244 CE 2001 8 9 CA010727034 1 20010719 G 3310 041312610 RHEOSTAT CESSNA 172 172D 2072410 CE CONT O300 O300D 17022 SO COCKPIT FAILED W K NONE B SMOKE/FUMES/ODORS/SPARKS IN INSP/MAINT 1 CA (CAN) WHILE PERFORMING THE ANNUAL INSPECTION OF THE ELCTRICAL SYSTEM THE RHEOSTAT BEGAN SMOKING. 1 H 7 1 3O 3 O NT 3A12 E253 2001080900245 20010809 00245 NE 2001 8 9 CA010727035 2 20010727 G 7532 SWITCH 3192100 SNIAS 350 AS350BA 8680817 EU TMECA ARRIEL ARRIEL1B 6OO30 NE BLEED VALVE FAILED W K NONE L NO TEST IN INSP/MAINT 1 CA 2831 283 670 (CAN) LOST SIGNAL FROM BLEED VALVE WHICH WORKS CORRECTLY. FOUND SWITCH LEAF AND ROLLER WAS BROKEN. 1 G 7 1 3U 3 U NC H9EU E19EU 2001080900246 20010809 00246 CE 2001 8 9 CA010727036 1 20010723 G 3230 244110010 PIVOT CESSNA 172 172RG 2072438 CE LYC O360 O360F1A6 41514 EA MCAULY 2D34C B2D34C220 GL MLG CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 6300 (CAN) DURING INSPECTION CARRIED OUT IAW AD 2001-06-06, BOTH PIVOT ASSMEBLIES WERE FOUND CRACKED 1 H 7 1 3O 3 O 3A17 E286 5 C P7EA 2001080900247 20010809 00247 CE 2001 8 9 CA010730001 1 20010723 G 3233 98820152 ACTUATOR CESSNA 172 172RG 2072438 CE LYC O360 O360F1A6 41514 EA MCAULY 2D34C B2D34C220 GL LANDING GEAR CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 6300 (CAN) DURING INSPECTION REQUIRED BY CESSNA SEB 01-2 BOTH ACTUATORS WERE FOUND CRACKED 1 H 7 1 3O 3 O 3A17 E286 5 C P7EA 2001080900249 20010809 00249 CE 2001 8 9 CA010730002 1 20010723 G 3233 99820152 ACTUATOR CESSNA 172 172RG 2072438 CE LYC O360 O360F1A6 41514 EA MCAULY 2D34C B2D34C220 GL LANDING GEAR CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 8600 (CAN) DURING INSPECTION CARRIED OUT IAW CESSNA SEB01-2, BOTH LANDING GEAR ACTUATORS WERE FOUND CRACKED. 1 H 7 1 3O 3 O 3A17 E286 5 C P7EA 2001082300087 20010823 00087 CE 2001 8 23 CA010808002 1 20010729 G 6310 105199 CARBURETOR CESSNA 150 152 2071835 CE LYC O235 O235L2C 41505 EA ENGINE MALFUNCTIONED W A UNSCHED LANDING J WARNING INDICATION CR CRUISE 1 CA 650 (CAN) ENGINE STARTED LOSING POWER WHILE IN CRUISE AT 2500 FT & 30 SEC LATER QUIT RUNNING. PILOT INSTRUCTOR MADE A FORCED LANDING IN HAY FIELD. ENGINE WOULD NOT START AGAIN. CARBURATOR WAS REPLACED AND ENGINE STARTED TO RUN NORMALLY AND AIRC RAFT WAS FLOWN OFF FIELD. NOTE: LAST SUMMER A SIMILAR INCIDENT OCCURRED ON ANOTHER OF OUR C-152'S EXCEPT THAT THE ENGINE DID NOT QUIT COMPLETELY AND HE LANDED AT ON AIRPORT. 1 H 7 1 3O 3 O NT 3A19 E223 2001082300093 20010823 00093 SW 2001 8 23 CA010808003 1 20010706 G 6320 2060400321 BEARING 20604000005 BELL 206 206B 1181511 SW ALLSN 250C 250C20 03013 GL TRANSMISSION SPALLED W A UNSCHED LANDING J WARNING INDICATION CR CRUISE 1 SW 99 7617 2233 B12150 (CAN) TRANSMISSON REMOVED FROM A/C DUE TO METAL CONTAMINATION AND EXCESSIVE NOISE. ON DISASSEMBLY, MAIN INPUT GEAR SHAFT P/N 206040040003 WAS FOUND TO HAVE VERTICAL PLAY. AFTER REMOVING THE SHAFT AND THE DUPLEX THRUST BEARING P/N 2060400321 THE TOP BEARING OF THE THRUST BEARING WAS FOUND TO BE BADLY SPALLED ON ALL THE BALLS. THE VERTICAL MOVEMENT OF THE SHAF T AND RING GEAR ALSO CAUSED EXCESSIVE WEAR OF THE PINON AND RING GEAR. 1 G 7 1 3U 3 U H2SW E4CE 2001082300095 20010823 00095 NM 2001 8 23 CA010808032 1 20010726 G 5246 LJ76872 DOOR BOEING 757 757236 NM RROYCE RB211 RB211535E437 54555 NE ENGINE OIL MISSING W K NONE D INFLIGHT SEPARATION IN INSP/MAINT 1 CA (CAN) AIRCRAFT ARRIVED ON STATION WITH NR 2 ENGINE OIL SERVICING DOOR MISSING. ROLLS ROYCE SERVICE BULLETIN RB 211-71-B5 92 WAS INCORPORATED ON THE DOOR. A NEW ACCESS DOOR WAS INSTALLED. NEW SPRING CLIP FROM GOODRICH WILL BE INSTALL WHEN MOD IFICATION BECOME AVAILABLE AS PER FIELD TECHNICAL STATUS ISSUE 12. 2 L 7 2 4F 4 F RT A2NM E12EU 2001082300100 20010823 00100 WP 2001 8 23 CA010808060 1 20010801 G 5280 1512449107 ROD LKHEED 1011 1011385114 WP RROYCE RB211 RB21122B02 54555 NE MLG DOOR STIFF W A UNSCHED LANDING D INFLIGHT SEPARATION CL CLIMB 1 SW 99 (CAN) AFTER TAKE OFF, LEFT HAND NOSE GEAR DOOR WOULD NOT RETRACT. AIRCRAFT RETURNED TO THE STATION. FOUND THE LEFT HAND GEAR DOOR ROD ACTUATOR VERY STIFF. UNIT WAS SERVICED AS PER MAINTENANCE MANUAL AND CHECKED SERVICEABLE AS PER OVERHAUL M ANUAL. SYSTEM WAS VERIFIED AND FOUND SERVICEABLE DURING TEST FLIGHT. 2 L 7 3 4F 4 F A23WE E12EU 2001082300101 20010823 00101 GL 2001 8 23 CA010809001 2 20010725 G 7230 23033721 COMPRESSOR WHEEL C20B6890550 BELL 206 206B 1181511 SW ALLSN 250C 250C20B 03013 GL ENGINE DAMAGED W K NONE O OTHER IN INSP/MAINT 1 SW 99 5069 1695 CAC35783 (CAN) DURING AN SCHEDULED INSP THE 1ST STAGE COMPRESSOR WAS NOTED TO HAVE F.O.D. AFTER REMOVING THE CASE HAVLES FOR FURT HER INSPECTION. IT WAS FOUND NO DAMAGE WENT FURTHER DOWN THAN THE 1ST STAGE. THE DAMAGE WAS INSPECTED AND BLENDED OUT IA W MAINTENANCE MANUAL. THIS F.O.D. WAS UNDETERMINED ON WHAT AND HOW, SINCE THERE WAS A PART SEP. INSTALLED. 1 G 7 1 3U 3 U H2SW E4CE 2001082300103 20010823 00103 GL 2001 8 23 CA010809002 2 20010724 G 7323 1056058312 SPRING BOLKMS 105 BO105S 5626006 EU ALLSN 250C 250C20B 03013 GL NR 2 ENGINE CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) DURING A POWER ASSURANCE CHECK NR 2 ENGINE HAD TOT AND TORQUE FLUCTUATIONS. ENGINE POWER RETURNED TO OPERATIVE LIM ITS AND A/C LANDED AT MAINTENACE FACILITY. DURING POST FLIGHT INSPECTION, SPRING WAS FOUND TO BE CRACKED OFF FROM GOVERN OR ARM. NEW ONE INSTALLED. 1 G 7 2 3U 3 U H3EU E4CE 2001082300104 20010823 00104 CE 2001 8 23 CA010809003 1 20010725 G 2150 1155550259 SHAFT BEECH 1900 1900C 1154161 CE PWA PT6 PT6A65B 52043 EA A/C PACK SHEARED W K NONE O OTHER IN INSP/MAINT 1 CA 593 (CAN) QUILL SHAFT IN AIR CONDITIONING COMPRESSOR DRIVE SHEARED AT SHEAR POINT BEHIND SPLINE. SHAFT REPLACED & AIRCRAFT R ETURNED TO SERVICE. 2 L 7 2 4T 4 T RT A24CE E4EA 2001082300105 20010823 00105 GL 2001 8 23 CA010809005 2 20010718 G 7250 23065833 TURBINE BLADES ALLSN 250C 250C20B 03013 GL ENGINE SEPARATED W E A ENGINE SHUTDOWN UNSCHED LANDING J WARNING INDICATION NR NOT REPORTED 1 CA 373 373 (CAN) AFTER AN INFLIGHT SHUTDOWN, THE ENGINE WAS DISMANTLED AT THE VANCOUVER SERVICE CENTRE OF STANDARD AERO. THE LOCAL TSB, ROLLS ROYCE AND CUSTOMER WERE ALL PRESENT DURING THE TEARDOWN INVESTIGATION. IN THE DISMANTLING OF THE TURBINE ASSE MBLY, THE 3RD STAGE TURBINE WHEEL WAS MISSING ONE ENTIRE BLADE. THE BLADE HAD SEPARATED AND CAUSED SIGNIFICANT DOWNSTREA M DAMAGE. THE EXACT CAUSE OF THE FAILURE IS CONSIDERED UNKNOWN. IN CONJUNCTION WITH THE TSB IN VANCOUVER, THE FAILED PAR TS WILL BE FORWARDED TO ROLL ROYCE IN INDIANAPOLIS FOR A FULL METALURGICAL INVESTIGATION. 3 U E4CE 2001082300107 20010823 00107 WP 2001 8 23 CA010809006 1 20010725 G 2913 EA501828 PUMP CVAC 440 440 2422902 WP ALLSN 501D 501D13 03004 GL HYD SYSTEM FAILED W A UNSCHED LANDING B SMOKE/FUMES/ODORS/SPARKS DE DESCENT 1 CA 1297 (CAN) EMERGENCY LANDING WITH SMOKE IN COCKPIT. FOUND ELECTRIC HYDRAULIC PUMP BYPASSING THRU CASE DRAIN AND PUMP DEVELOPI NG 2,700 PSI ONLY. AFTER INSPECTION AIRCRAFT WAS FERRIED TO MAINTENANCE BASE WITH GEAR DOWN AND PUMP OFF. AC PUMP REPLAC ED. MULTIPLE GEAR RETRACTION C/O AND FLAP MOVEMENT USING AC HYDRAULIC PUMP. PRESSURE AND TEMPERATURE WITHIN LIMIT. AIRCR AFT RETURN TO SERVICE. 2 L 7 2 4R 4 T 6A6 E282 2001082300108 20010823 00108 SW 2001 8 23 CA010809007 1 20010724 G 6310 206040272101 SEAL 206040015103 BELL 206 206B 1181511 SW ALLSN 250C 250C20B 03013 GL DRIVESHAFT DETERIORATED W O OTHER D INFLIGHT SEPARATION LD LANDING 1 CA A2001964 (CAN) ON LANDING AN ABNORMAL NOISE WAS HEARD FROM ENGINE COMPARTMENT. ENGINE WAS SHUT DOWN AND IT WAS DISCOVER THAT THE FORWARD COUPLER OF THE ENGINE -TRANSMISSION X HAD HEATED UP. THE SEAL HAD RUPTURED ALLOWING THE GREASE TO EXIT HEAT UP T HE COUPLER AND FURTHER MELT THE SEAL. ALL 4 TEMPLATES ON THE COUPLER HAD TURNED BLACK INDICATING AN OVERTEMP CONDITION. AT THE DAILY INSPECTION/PREFLIGHT THERE WERE NO SIGNS OF GREASE LACKING FROM THE COUPLER AND ALL 4 TEMPLATES WERE NORMAL . THIS VISUAL INSPECTION WAS CARRIED OUT BY THE PILOT 1.6FLT LVS PRIOR TO DISCOVERY OF THE FAULT. 1 G 7 1 3U 3 U H2SW E4CE 2001082300109 20010823 00109 WP 2001 8 23 CA010809008 1 20010724 G 7921 A1855 BRACKET ROBSIN C2361 ROBSIN R44 R44 7640120 WP LYC O540 O540F1B5 41532 EA SCROLL ASSY BROKEN W K NONE O OTHER IN INSP/MAINT 1 CA 841 (CAN) UPON REMOVING THE SCROLL TO CORRECT A CLUTCH ACTUATOR SWITCH THAT WAS NOT FUNCTIONING, THE BROKEN A185-5 BRACKET W AS DISCOVERED. SUSPECT FAN IMBALANCE TO BE THE CAUSE OF THIS DEFECT. 1 G 7 1 3O 3 O H11NM E295 2001082300110 20010823 00110 WP 2001 8 23 CA010809009 1 20010724 G 6200 V31001 SWITCH ROBSIN C0511 ROBSIN R44 R44 7640120 WP LYC O540 O540F1B5 41532 EA ACTUATOR WORN W K NONE O OTHER IN INSP/MAINT 1 CA 841 0312 (CAN) AT 100 HR INSPECTION, TEST OF ACTUATOR SWITCHES-ONE SWITCH FAILED THE TEST. INSPECTION OF THE SWITCH REVEALED THAT THE ACTUATOR BUTTON ON THE SWITCH WAS WORN TO ABOUT 1/2 OF IT'S ORIGINAL HEIGHT. INSTALLED A NEW SWITCH. SUSPECT FAN IM BALANCE TO BE THE CAUSE OF THIS WEAR. 1 G 7 1 3O 3 O H11NM E295 2001082300111 20010823 00111 NM 2001 8 23 CA010809014 1 20010710 G 3211 NAS679A5 NUT BOEING B273201602 BOEING 727 72722 1384002 NM PWA JT8 JT8D7B 52053 NE SUPPORT ASSY SPLIT W K NONE O OTHER IN INSP/MAINT 1 CA 2031 (CAN) UPON SCHEDULED MLG REMOVAL FOUND NUT P/N NAS679A5 ON RT SUPPORT ASSY TRUNNION SPLIT ON ONE SIDE. 2 L 7 3 4F 4 F A3WE E2EA 2001082300137 20010823 00137 GL 2001 8 23 CA010809016 2 20010722 G 7230 CASE 6890550 BELL 206 206L 1181522 SW ALLSN 250C 250C20J 03013 GL ENGINE DAMAGED W O OTHER D R INFLIGHT SEPARATION PARTIAL RPM/PWR LOSS IN INSP/MAINT 1 CA 4168 982 CAC41685 (CAN) ON WINDUP FROM GROUND IDLE TO FLIGHT IDLE, THE PILOT HEARD A POPPING NOISE AND A STEADY SOUND OF RUSHING AIR. THE TURBINE OUTLET TEMPERATURE (TOT) HAD CLIMBED INTO THE YELLOW ARC. DURING TROUBLLE SHOOTING THE COMPRESSOR CASE HALF WAS MISSING AND STATOR (NEXT TO THE SPLIT LINE) AT THE 4TH STAGE STATION LINE. THIS STATOR WENT BACK AND DAMAGED THE REMAINI NG STATORS AND WHEELS. COMPRESSOR WAS REPLACED AND THE AIRCRAFT RETURNED TO SERVICE. 1 G 7 1 3U 3 U H2SW E4CE 2001092000047 20010920 00047 SO 2001 9 20 CA010809018 1 20010726 G 2133 1036383 OUTFLOW VALVE PIPER PA42 PA42 7104202 SO PWA PT6 PT6A41 52043 EA CABIN PRESSURE DIRTY W B EMER. DESCENT W INADEQUATE Q C CR CRUISE 1 CA 310 (CAN) AT FLIGHT LEVEL 22000, CABIN LOST PRESSURE. AN EMERGENCY DESCENT WAS CARRIED OUT AND THE REMAINDER OF THE FLIGHT W AS NORMAL. UPON INSPECTION THE OUTFLOW VALVE WAS FOUND TO BE LOOSE AND DIRTY. THE VALVE WAS CLEANED & TIGHTENED, THEN A SATISFACTORY TEST FLIGHT WAS CARRIED OUT. 1 L 7 2 4T 4 T A23SO E4EA 2001081400013 20010814 00013 NE 2001 8 14 CA010810001 1 20010422 G 5320 BULKHEAD SKRSKY SKRSKY S76 S76A 8143006 NE TMECA ARRIEL ARRIEL1S1 60030 NE L/H SIDE ST.215 CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 11668 (CAN) CRACKED FOUND AT ST.215 L/H SIDE BULKHEAD 7.5 INCHES BELOW WATERLINE 121. EXTENDING FROM M6B SUPPORT TO MAIN BULKH EAD ELECTRICAL PLUG. 1 G 7 2 3U 3 U H1NE E19EU 2001092000048 20010920 00048 SW 2001 9 20 CA010810005 1 20010723 G 6410 206016201133 BLADE BELL 206 206B 1181511 SW ALLSN 250C 250C20 03013 GL TAIL ROTOR DENTED W K NONE O OTHER IN INSP/MAINT 1 CA 106 (CAN) DURING A DAILY INSPECTION THE PILOT NOTICED A DENT ON THE LEADING EDGE OF THE NOTED T/R BLADE. UPON INSPECTION THE DAMAGE WAS MEASURED AND FOUND TO BE IN LIMITS. FURTHER TO THE INVESTIGATION IT WAS FOUND THAT A SCREW HAD COME LOOSE FR OM THE GEARBOX FAIRING INTO THE T/R BLADE PATH. NO OTHER DAMAGE WAS NOTED. 1 G 7 1 3U 3 U H2SW E4CE 2001092000049 20010920 00049 WP 2001 9 20 CA010810006 1 20010801 G 3246 C2411 CROSSTUBE ROBSIN C0148 ROBSIN R44 R44 7640120 WP LYC O540 O540F1B5 41532 EA MLG CHAFED W K NONE O OTHER IN INSP/MAINT 1 CA 1355 (CAN) 2 CHAFED MARKS APPROX 1/16" DEEP, 3/8" APART & 1/2" LONG, MADE BY THE WIRES OF THE SEAT HOSE THAT IS ATTACHED TO T HE CABIN HEATER SHROUD ON THE OUTLET SIDE. HEATER SHROUD IS NOT A TIGHT FIT TO THE MUFFLER & I HAVE IN THE PAST NOTED WE AR ON THE MUFFLER SUPPORT RINGS FOR THE SHROUD. THERE IS ROOM FOR THE SHROUD TO ROTATE UNTIL THE SEAT HOSE & CLAMP TOUCH ES & WEARS THE AFT CROSS TUBE. AFT CROSS TUBE REPLACED. 1 G 7 1 3O 3 O H11NM E295 2001092000050 20010920 00050 CE 2001 9 20 CA010810007 1 20010518 G 2612 302158 FIRE DETECTOR BEECH 99 99 1154002 CE PWA PT6 PT6A20 52043 EA LT ENGINE INTERMITTENT W E ENGINE SHUTDOWN N FALSE WARNING AP APPROACH 1 CA (CAN) ON SHORT FINAL, THE FIRE DETECTION SYSTEM ON THE LEFT ENG ACTIVATED. THE PILOT ELECTED TO SHUTDOWN THE ENG & CONTI NUED WITH THE LANDING. NO OTHER INDICATIONS, SUCH AS SMOKE OR FLAMES, WERE NOTICED. ON INSPECTION THE LOWER AFT FIRE DET ECTOR (NR 3) WAS FOUND TO BE INTERMITTENTLY INDICATING A FIRE WHEN THERE WAS NO FIRE. THE DETECTOR WAS REPLACED WITH A S ERVICEABLE UNIT & THE A/C WAS RETURNED TO SERVICE. THERE IS AN AD ON THIS UNIT, PYROTECTOR 78-14-09, WHICH INCLUDES TEST ING THE SYSTEM EVERY 100 HOURS. THIS AD HAD BEEN CARRIED OUT ABOUT 25 HOURS AGO WITH NO INDICATION OF ANY PROBLEMS. THIS IS THE FIRST TIME WE HAVE HAD A FALSE FIRE INDICATION FROM ONE OF THESE UNITS. 1 L 7 2 3T 3 T A14CE E4EA 2001092000053 20010920 00053 SW 2001 9 20 CA010810013 1 20010625 G 5711 SPAR BBAVIA 7 7ECA 21101NN SW AMTR CUSHMN O200 05645 GL MCAULY 1A100 1A100ACM GL WING CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) BOTH WINGS WERE STRIPPED OF FABRIC & L/E MATERIAL REMVD DURING INSP. BOTH WING TIPS WERE REMVD ALONG WITH FUEL TAN KS & AILERON BELLCRANKS. SPARS WERE BLOWN WITH COMPRESSED AIR THEN WASHED DOWN WITH MILD SOAP & WARM WATER. THE INSP THE N PROCEEDED USING HIGH INTENSITY LAMP & LARGE MAGNIFYING GLASS. AFTER REMOVING VARNISH IN LIFT STRUT ATTACHMENT POINT, I COULD IDENTIFY VERY SMALL CRACK IN GLUE JOINT ON REAR FACE OF RIGHT REAR WING SPAR. USING LIGHT & MAGNIFYING GLASS, I D ETECTED ON UPPER EDGE OF RIGHT REAR SPAR, TOTAL OF 5 COMPRESSION TYPE CRACKS WHICH UNDER NORMAL LIGHTING CONDITIONS COUL D NOT BE SEEN. 2 ACTUAL SPLITS WERE REVEALED STARTING AT REINFORCING PLYWOOD PLATE. THESE SPLITS FOLLOWED EDGE GRAIN OF 1 H 7 1 3O 3 O A759 EXPA3O 5 N P918 2001092000055 20010920 00055 EU 2001 9 20 CA010813003 1 20010731 G 2431 23491 BATTERY BRAERO DH125 BAE125800A 1500285 EU GARRTT TFE731 TFE731* 01518 WP NR 2 OVERHEATED W A UNSCHED LANDING J WARNING INDICATION CR CRUISE 1 CA 35 (CAN) DURING CRUISE NR 2 BATTERY OVERHEAT INDICATED IN COCKPIT, CREW DIVERTED TO CYXU, BATTERY WAS REPLACED WITH SERVICA BLE UNIT AND AIRCRAFT PROCEEDED WITH NO ADDITIONAL FAULTS. FAULTY BATTERY WAS FORWARDED FOR REPAIR/DEEP CYCLE. 2 L 7 2 4F 4 F RT A3EU E6WE 2001092000057 20010920 00057 EA 2001 9 20 CA010813005 2 20010703 G 7230 BLADE BEECH 100 A100 1152915 CE PWA PT6 PT6A28 EA HARTZL HCB4T HCB4TN3 GL COMPRESSOR SEPARATED W C ABORTED TAKEOFF R PARTIAL RPM/PWR LOSS TO TAKEOFF 1 CA (CAN) ON TAKEOFF PARTIAL LOSS OF POWER EXPERIENCED ON RT ENGINE. TAKEOFF ABORTED. UPON SUBSEQENT TEAR DOWN WITH A PRATT & WHITNEY REPRESENTATIVE PRESENT, IT HAS BEEN DETERMINED THAT A COMPRESSOR TURBINE BLADE SEPARATED AND DAMAGED COMPONENT S DOWNSTREAM IN ENGINE. 1 L 7 2 3T 4 T A14CE E4EA 6 C P40EA 2001092000059 20010920 00059 CE 2001 9 20 CA010813009 1 20010630 G 5310 50430043867 DOOR FRAME BEECH 100 100BEECH 1152916 CE PWA PT6 PT6A28 EA HARTZL HCD4N3 HCD4N3A GL FUSELAGE CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 21552 (CAN) DOOR FRAME FORWARD 50-430043-867 CRACKED ON LOWER BAYONNET HOLE TO SCREW HOLE AND 1/2" BEYOND. OTHER SCREW HOLE TO BAYONNET HOLE. DOOR FRAME AFT 50-430043-865 CRACKED ON UPPER BAYONNET HOLE TO SCREW HOLE ONE ONLY. 1 L 7 2 3T 4 T A14CE E4EA 5 C STC 2001092000061 20010920 00061 EU 2001 9 20 CA010813011 1 20010716 G 2750 ONL3120146X77 BOLT Z4243430000 ZLIN 242 Z242L 9970204 EU LYC O360 AEIO360A1B6 41514 EA FLAP CONTROL BENT W K NONE O OTHER IN INSP/MAINT 1 CA 3046 (CAN) DURING A 100/500 HOUR INSPECTION THE LT FLAP BELLCRANK BOLT WAS FOUND TO BE BENT. THE BOLT WAS REPLACED WITH A NEW ONE. IT IS SUSPECTED THAT A STUDENT PILOT EXTENDED THE FLAPS ABOVE THE MAXIMUM SPEED ALLOWED FOR FLAP EXTENSION. THE MA INTENANCE SCHEDULE ALREADY HAS AN ADDITIONAL INSPECTION ON THE FLAP BOLTS AND THE INSTRUCTORS AND STUDENTS WERE AGAIN RE MINDED OF THE PROPER PROCEDURE USING THE FLAPS. 1 L 7 1 3O 3 O 0 A76EU 1E10 2001092000068 20010920 00068 NM 2001 9 20 CA010813012 1 20010721 G 5310 DOOR FRAME BOEING 727 72722 1384002 NM PWA JT8 JT8D7B 52053 NE FUSELAGE CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) FWD FRAME OF AFT CARGO DOOR CRACKED AT BS1057, STR.24. CRACK MEASURED 1.5 INCHES. 2 L 7 3 4F 4 F A3WE E2EA 2001092000073 20010920 00073 CE 2001 9 20 CA010813013 1 20010720 G 2800 57181061 HARNESS CESSNA 441 441 2076020 CE FUEL SYSTEM CHAFED W D RETURN TO BLOCK B SMOKE/FUMES/ODORS/SPARKS TX TAXI/GRND HDL 1 CA (CAN) DURING INVESTIGATION OF INTERMITTENT BOOST PUMP FOUND CHAFED SPOT ON WIRE HARNESS INSIDE FUEL TANK. MAGNIFIED VIEW SHOWED EVIDENCE OF ELECTRICAL CONTACT BETWEEN WIRE AND STRUCTURE OF FUEL TANK. 1 L 7 2 3T RT A28CE 2001092000075 20010920 00075 SO 2001 9 20 CA010813014 1 20010720 G 3244 10320400 BOLT CLEVELAND 40106 PIPER PA31T PA31T 7103124 SO PWA PT6 PT6A28 EA WHEEL CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 795 795 (CAN) ON AN EVENT NR 2 INSPECTION IT WAS FOUND THAT THE RIGHT MAIN WHEEL P/N 40-106 WAS MISSING 1 THROUGH BOLT ((P/N 103 .20400 (AN5-35A))AND ANOTHER BESIDE THE MISSING BOLT BROKEN IN TWO AND PROTRUDING FORWARD THE BRAKE CALIPER. THE ROTATIO N OF THE WHEEL CAUSED THE HEAD OF THE BOLT TO CAUSE CONSIDERABLE DAMAGE TO THE TORQUE PLATE. (P/N 075-12800). 1 L 7 2 3T 4 T A8EA E4EA 2001092000076 20010920 00076 2001 9 20 CA010813016 4 20010715 G 3420 1242102011 INDICATOR PILATS PC12 PC1245 EU PWA PT6 PT6A67B 52043 NE HARTZL HCE4A HCE4A3D GL AHRU FAILED W O OTHER H ELECT. POWER LOSS-50 PC CR CRUISE 1 CA 462 1545 (CAN) DURING STRAIGHT AND LEVEL FLIGHT THE PILOTS AHRU DISPLAY WENT BLANK. THE PILOT CYCLED THE CIRCUIT BREAKERS, AND TH E UNIT CAME BACK ON. THE UNIT HAS BEEN REPLACED. 1 L 7 1 3T 4 T RT A78EU E26NE 5 C P210NE 2001092000079 20010920 00079 2001 9 20 CA010813017 4 20010724 G 3420 1242102011 INDICATOR PILATS PC12 PC1245 EU PWA PT6 PT6A67B 52043 NE HARTZL HCE4A HCE4A3D GL AHRU FAILED W O OTHER H ELECT. POWER LOSS-50 PC CR CRUISE 1 CA 476 (CAN) DURING STRAIGHT AND LEVEL FLIGHT THE CO-PILOTS AHRU DISPLAY WENT BLANK. THE PILOT CYCLED THE AVIONICS POWER, AND T HE UNIT CAME BACK ON. THE UNIT HAS BEEN REPLACED. 1 L 7 1 3T 4 T RT A78EU E26NE 5 C P210NE 2001092000081 20010920 00081 EU 2001 9 20 CA010813018 1 20010724 G 2434 9789601090 BRUSH HOLDER BOSCH 5243212158 PILATS PC12 PC1245 EU PWA PT6 PT6A67B 52043 NE HARTZL HCE4A HCE4A3D GL GENERATOR WORN W K NONE O OTHER IN INSP/MAINT 1 CA 102 100318 (CAN) DURING A 100 HOUR INSPECTION, THE BRUSH ASSEMBLY WAS REMOVED TO VERIFY THE CONDITION. THE BRUSH ASSEMBLY WAS WORN EXCESSIVELY, AND HAS BEEN REPLACED. 1 L 7 1 3T 4 T RT A78EU E26NE 5 C P210NE 2001092000086 20010920 00086 SW 2001 9 20 CA010813021 1 20010725 G 2810 71493 STRUCTURE BBAVIA 8 8GCBC 1220803 SW LYC O360 O360C2E 41514 EA FUEL CELL CRACKED W K NONE K FLUID LOSS IN INSP/MAINT 1 CA (CAN) - FUEL TANK CRACKING. - POSSIBLY DUE TO TOO LIGHT GUAGE OF MATERIAL & NO INTERNAL BAFFLES INTANK. CRACKS USUALLY O CCUR AT END OF STIFFENER INDENTS. - WE AVERAGE 2-3 FUEL TANK FAILURE DUE TO CRACKING PER FLYING SEASON. 1 H 7 1 3O 3 O A21CE E286 2001092000087 20010920 00087 SW 2001 9 20 CA010813022 1 20010801 G 2823 110660 SHUTOFF VALVE BBAVIA 8 8GCBC 1220803 SW LYC O360 O360C2E 41514 EA FUEL SYSTEM FAILED W D RETURN TO BLOCK Y ENGINE STOPPAGE TX TAXI/GRND HDL 1 CA (CAN) - THREADED COLLAR THAT SECURES VALVE SHAFT IN BODY CAME LOOSE AND DETACHED ITSELF FROM SHUTOFF BALL INSIDE VALVE. FOR SOME REASON THE VALVE WAS OR WENT INTO THE CLOSED POSITION & STARVED THE ENGINE FOR FUEL DURING TAXI OUT FOR DEPARTU RE. - THERE IS NOTHING PROVIDED TO SECURE THE COLLAR SO THAT IT WILL NOT LOOSEN. 1 H 7 1 3O 3 O A21CE E286 2001092000091 20010920 00091 CE 2001 9 20 CA010813024 1 20010809 G 3220 030A39313 BOLT MTSBSI MU2 MU2B36A 5780413 CE GARRTT TPE331 TPE3315 01514 WP NLG CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) THE NOSE LANDING GEAR DRAG STRUT ATTACH BOLT WAS FOUND CRACKED AT SCHEDULED NDT INSPECTION OF BOLT. THIS BOLT HAD BEEN MAGNETIC PARTICAL INSPECTED EVERY 2000 HOURS. 1 H 7 2 3T 4 T A10SW E4WE 2001092000093 20010920 00093 NM 2001 9 20 CA010814003 1 20010726 G 2900 TC125UK00ZY1 INDICATOR BOEING 767 767333 NM PWA 4060 PW4060 52119 NE HYD PRESSURE LEAKING W A UNSCHED LANDING K J FLUID LOSS WARNING INDICATION CR CRUISE 1 CA (CAN) ENROUTE FROM TEL AVIV TO TORONTO AFTER THE LT SYSTEM WAS TOPPED OFF (IN TLV) LOSS OF HYDRAULIC FLUID OF THE L/H SY STEM, THE A/C RE-ROUTED AND ASK FOR AN EMERGENCY LANDING. A/C LANDED SAFELY WITHOUT FURTHER INCIDENT. FOUND TO BE A LEAK AT THE DIFFERENTIAL INDICATOR PRESSURE DRAIN CASE MODULE FILTER (AROUND THE POP OUT). REPLACED THE PRESSURE CASE DRAIN FILTER MODULE DIFFERENTIAL PRESSURE INDICATOR. 2 L 7 2 4F 4 F RT A1NM E24NE 2001092000094 20010920 00094 EU 2001 9 20 CA010814005 1 20010718 G 2740 47147400 ACTUATOR AIRBUS A340 A340313 EU CFMINT CFM56 CFM565C4 13802 NE HORIZONTAL STAB FAILED W K NONE F FLT CONT AFFECTED IN INSP/MAINT 1 CA (CAN) ON MAINTENANCE CHECK FOUND TRIM HORIZONTAL STABILIZER ACTUATOR BALLNUT TRANSFER TUBE DISCONNECTED FROM BALLNUT. RE PLACED TRIM HORIZONTAL STABILIZER ACTUATOR AND SYSTEM TESTED. 2 L 7 4 4F 4 F RT A197 E37NE 2001092000096 20010920 00096 EU 2001 9 20 CA010814006 1 20010718 G 3244 TIRE AIRBUS 320 A320211 3930320 EU CFMINT CFM56 CFM565A1 NE MLG SEPARATED W A UNSCHED LANDING D INFLIGHT SEPARATION CL CLIMB 1 CA (CAN) #3 MAIN WHEEL TIRE CAP SEPARATION ON TAKEOFF. AIR TURN BACK TO AIRPORT. AIRCRAFT SUSTAINED DAMAGE TO #2 ENGINE FAN BLADES, ENGINE INTAKE ACOUSTIC PANELS, R/H INBOARD TRAILING EDGE FLAP. ONE LINE OF THE YELLOW HYDRAULIC SYSTEM BROKE IN AREA OF R/H MAIN LANDING GEAR AREA. THE R/H HORIZONTAL STABILIZER DENTED AND HOLE ON THE UPPER SURFACE OF THE R/H WING ABOVE THE MAIN LANDING GEAR (R/H).REPAIRS WILL BE ACCOMPLISHED AFTER ENGINEERING EVALUATION.FINAL REEPORT FOR FIXES WILL BE PRODUCED AT A LATER DATE. 2 L 7 2 4F 4 F RT A28NM E29NE 2001082800072 20010828 00072 CE 2001 8 28 CA010814020 1 20010615 G 2131 13035616 CONTROLLER 13035616 CESSNA 500 550 2076604 CE PWA JT15 JT15D4 52112 NE INTERNAL W B G EMER. DESCENT O2 MASK DEPLOYED W INADEQUATE Q C DE DESCENT 1 CA 207 79327 (CAN) PRESSURIZATION PROBLEMS OCCURRED SHORTLY AFTER TAKEOFF BACK TO OTTAWA (CONTROL). ON DESCENT THROUGH 23,000 FEET. C REW EXPERIENCED RAPID DEPRESSURIZATION. MASKS WERE DONNED AND DESCENT ACCELERATED TO BELOW 10,000 FT. MAINTENANCE DETERM INED THE CAUSE TO BE THE PRESSURIZATION CONTROLLER, CONTROLLER REPLACED. NO FURTHER ACTION REQUIRED. 1 L 7 2 4F 4 F A22CE E1NE 2001092000098 20010920 00098 CE 2001 9 20 CA010814021 1 20010807 G 2130 41EN496 SQUAT SWITCH CESSNA 500 550 2076604 CE PWA JT15 JT15D4 52112 NE CABIN PRESSURE WORN W B G EMER. DESCENT O2 MASK DEPLOYED W INADEQUATE Q C DE DESCENT 1 CA (CAN) WHILE IN DESCENT FROM FL330, AND DESCENDING THROUGH 15,000 FT CABIN ALTITUDE STARTED TO INCREASE RAPIDLY. AIRCRAFT DIVERTED TO CYQM FOR MAINTENANCE. WHILE AT 10,000 FT CABIN ALTITUDE RECOVERED. WHEN THROTTLES REDUCED FROM 88 TO 70 PE RCENT N1, CABIN PRESSURIZATION WAS LOST AGAIN. MAINTENANCE DETERMINED THAT THE L/H SQUAT SWITCH WAS AT FAULT UNIT REPLAC ED, NO FURTHER ACTION. 1 L 7 2 4F 4 F A22CE E1NE 2001092000100 20010920 00100 CE 2001 9 20 CA010814022 1 20010802 G 2710 0510105217 CONTROL CABLE CESSNA CESSNA 172 172I 2072426 CE LYC O320 O320E2D 41508 EA MCAULY 1C172 1C172MTM GL AILERON CONTROL FRAYED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) AIRCRAFT DAMAGE ON LANDING AT PICTOU ISLAND. AIRCRAFT BEING STRIPPED FOR REPAIR WHEN THE CABLE, ABOVE WAS FOUND FR AYED WHERE IT PASSES OVER THE PULLEY. LT SIDE TOP OF FUSELAGE. 1 H 7 1 3O 3 O NT 3A12 E274 5 N P910 2001092000104 20010920 00104 NM 2001 9 20 CA010815001 1 20010709 G 2433 2299 TRANSFORMER BOEING 737 737201 1384454 NM PWA JT8 JT8D9A 52048 NE E&E BAY FAULTY W O OTHER H ELECT. POWER LOSS-50 PC CR CRUISE 1 CA (CAN) AT CRUISE, A SNAPPING NOISE WAS HEARD. NR 1 TR CB POPPED. NR 1 MAIN FUEL TANK AFT FUEL BOOST PUMP CB POPPED ALONG WITH NUMEROUS C/P LIGHTS. #1 ENGINE OIL TEMP INDICATOR, CAPT'S AUX. PITOT STATIC AND NO SMOKING & FASTEN SEAT BELT SIGNS ALL NOT OPERATING. AS A PRECAUTION, ATC NOTIFIED FOR DIRECT DESTINATION IN CASE OF FURTHER ELECTICAL PROBLEMS. ON INITI AL DESCENT, THE TR BUS SUDDENLY POWERED BACK UP AGAIN & AIRCRAFT LANDED WITHOUT INCIDENT #1 TR REPLACED IAW MM 24-21-0 A ND CHECKED SERVICEABLE. NO FURTHER PROBLEM DURING SUBSEQUENT FLIGHT. 2 L 7 2 4F 4 F A16WE E2EA 2001092000105 20010920 00105 NM 2001 9 20 CA010815002 1 20010716 G 2822 2580003 PUMP BOEING 737 737201 1384454 NM PWA JT8 JT8D9A 52048 NE FUEL BOOST FAILED W O OTHER O OTHER CR CRUISE 1 CA (CAN) 1. EXTENGUISHED. NR 1 115 VAC TR BUS INOP. AIRCRAFT LANDED WITHOUT INCIDENT. MAIN FUEL TANK, AFT FUEL BOOST PUMP U NSERVICEABLE. BOOST PUMP CHANGED IAW MM 28-22-41. NO FURTHER INCIDENT DURING SUBSEQUENT FLIGHT. 2 L 7 2 4F 4 F A16WE E2EA 2001092000106 20010920 00106 EU 2001 9 20 CA010815003 1 20010713 G 5240 A5247514700800 DOOR AIRBUS 310 A310304 EU GE CF6 CF680C2A5 NE LAV SERVICE MISSING W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) 1. DURING THE TURNAROUND IT WAS OBSERVED THAT THE MID LAV SERVICING PANEL DOOR WAS MISSING. 2. DMI 35881 WAS RAISE D UNDER CDL 52-4. AIRCRAFRT RELEASED FOR FLIGHT.3. NO FURTHER INCIDENT DURING SUBSEQUENT FLIGHT. 2 L 7 2 4F 4 F RT A35EU E13NE 2001092000107 20010920 00107 EU 2001 9 20 CA010815004 1 20010720 G 5270 WARNING SYSTEM AIRBUS 310 A310304 EU GE CF6 CF680C2B2 30025 NE CARGO DOOR FALSE ACTIVATION W O OTHER N FALSE WARNING CL CLIMB 1 CA (CAN) 1. DURING TAKEOFF, ECAM WARNING FOR BULK CARGO DOOR INDICATION. AIRCRAFT RETURNED TO GATE. SYSTEM CHECKED AND MEL 52-7-0 APPLIED. AIRCRAFT RELEASED FOR FLIGHT. 2. NO PROBLEM DURING SUBSEQUENT FLIGHT. 3. UPON ARRIVAL TO HOME BASE, BULK CARGO DOOR INDICATION CHECKED SERVICEABLE AND MEL 52-7-0 CLEARED.4. NO FURTHER PROBLEM DURING SUBSEQUENT FLIGHT. 2 L 7 2 4F 4 F RT A35EU E13NE 2001092000108 20010920 00108 EU 2001 9 20 CA010815005 1 20010620 G 3150 20662155 CONTROLLER AIRBUS 310 A310304 EU GE CF6 CF680C2B2 30025 NE ECAM FAILED W O OTHER B SMOKE/FUMES/ODORS/SPARKS CR CRUISE 1 CA 1893 (CAN) 1. AT CRUISE, ECAM CONTROLLER SHOWED SIGNS OF BEING ERRATIC, FLASHING THEN TURNED BLACK. SMOKE STARTED FOR 10 SECO NDS WITH ELECTRICAL SMELL. CB POPPED AND SMOKE STOPPED. NOT ENOUGH SMOKE TO DON O2 MASKS. 2. PHONE PATCH MADE TO DISPATC H REGARDING PROBLEM. AIRCRAFT CONTINUED WITH FLIGHT WHILE MONITORING SITUATION. 3. ON ARRIVAL, #1 ECAM CONTROLLER REPLAC ED AND CHECKED SERVICEABLE IAW MM 31-51-00. 4. NO FURTHER PROBLEM DURING SUBSEQUENT FLIGHT. 2 L 7 2 4F 4 F RT A35EU E13NE 2001092000110 20010920 00110 CE 2001 9 20 CA010815012 1 20010801 G 5540 1156400006 HINGE BEECH 99 99 1154002 CE PWA PT6 PT6A28 EA HARTZL HCB3T HCB3TN3 GL RUDDER LOOSE W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) UPPER RUDDER HINGE BRACKET RIVETS LOOSE DUE TO FLIGHT CONTROL FLUTTER.SCREWS WERE LOOSE IN THE CENTER HINGE ALSO. PC/TSO/TSN ARE UNKNOWN, NOT 0.0. 1 L 7 2 3T 4 T A14CE E4EA 6 C P15EA 2001092000112 20010920 00112 CE 2001 9 20 CA010817002 1 20010814 G 5710 10140243S BOLT BEECH 99 99 1154002 CE PWA PT6 PT6A28 EA WING DAMAGED W K NONE O OTHER IN INSP/MAINT 1 CA 11181 11181 (CAN) BOLT FOUND WITH MECHANICAL THREAD DAMAGE UPON INSPECTION 1 L 7 2 3T 4 T A14CE E4EA 2001092000113 20010920 00113 SO 2001 9 20 CA010817003 1 20010626 G 3260 INDICATOR PIPER PA23 PA23250 7102308 SO LYC O540 IO540C4B5 41532 EA MLG FAILED W L ABORTED APPROACH N FALSE WARNING AP APPROACH 1 CA (CAN) WHILE LANDING THE LT WHEEL LIGHT DID NOT COME ON. AFTER VERIFICATION WITH THE MIRABLE TOWER WHO CONFIRMED 3 WHEELS OUT. THE AIRCRAFT RETURNED TO ST-HUBERT WITH THE LANDING GEAR DOWN. THE LIGHT CAME ON WHILE ONROUTE TO ST-HUBERT. 2 ELE CTRICAL TERMINALS WERE REPLACED AND THE GROUND WAS CLEANED FOLLOWED BY MANY RETRACTIONS AND THE SYSTEM WAS CHECKED SERVI CEABLE. 1 L 7 2 3O 3 O 1A10 1E4 2001092000114 20010920 00114 NE 2001 9 20 CA010820009 2 20010619 G 8500 114651 CYLINDER HEAD CVAC PBY5 PBY5A 2421208 WP PWA R1830 R183092 52020 NE ENGINE CRACKED W A UNSCHED LANDING R J PARTIAL RPM/PWR LOSS WARNING INDICATION CL CLIMB 1 CA 248 (CAN) NO. 11 CYLINDER HEAD CRACKED CYLINDER REPLACED. A/C RETURNED TO SERVICE. ON A TRAINING FLIGHT FLIGHT, ONE WATER PI CK UP WAS CARRIED OUT, LOAD WAS DROPPED ON TARGET, WHILE GOING BACK FOR A SECOND LOAD, THE MAP SHOWED A SUBSTANTIAL SPEE D. VISUAL CHECKS OF THE ENGINES WAS DONE AND A SUBSTANTAIL OIL LEAK ON THE RIGHT ENGINE WAS FOUND. ENGINE WAS SHUT DOWN, SOON AS POSSIBLE. 2 H 7 2 4R 4 R 2548 5E4 2001092000115 20010920 00115 CE 2001 9 20 CA010820010 1 20010807 G 2841 774000419 TRANSMITTER CESSNA 150 150J 2071820 CE FUEL QTY STUCK W D RETURN TO BLOCK H J ELECT. POWER LOSS-50 PC WARNING INDICATION TX TAXI/GRND HDL 1 CA 116 (CAN) TRANSMITTER LEVER PIVOT HAS BECOME SOMEWHAT STIFF, RESULTING IN INACCURATE FUEL LEVEL INDICATIONS. PART WAS REPLAC ED. THIS PART IS PART OF CESSNA SERVICE KIT SK-150-65. THE KIT WAS MADE NECESSARY BY THE UNAVAILABILITY OF THE ORIGINAL STEWART- WARNER SYSTEM PARTS. THIS UNIT IS MADE BY ROCHESTER. HOLDING PARTS FOR 21 DAYS. AFTER WHICH IT WILL BE RETURNED FOR WARRANTY. 1 H 7 1 3O 3A19 2001092000116 20010920 00116 SO 2001 9 20 CA010820012 1 20010726 G 3297 WIRE PIPER PA44 PA44180 7104402 SO MLG BROKEN W O OTHER P NO WARNING INDICATION AP APPROACH 1 CA (CAN) AS PILOT SELECTED GEAR DOWN ON APPROACH "GEAR WARNING" CCT BREAKER TRIPPED&UNSAFE LIGHT DID NOT ILLUMINATE DURING GEAR EXTENSION. PILOT NOTICED THAT HE HAD 3 GREEN LIGHTS INDICATING GEAR DOWN&LOCKED. AIRCRAFT LANDED W/O INCID.. MANTEN ANCE FOUND L.H. DOWNLOCK SWITCH WITH WIRES PULLED OUT OF SWITCH BODY. DOWNLOCK SWITCHES TURN OFF GEAR WARNING SYS WHEN A LL 3 SWITCHES ARE ENGAGED. PULLED WIRES WERE SHORTING OUT&WHEN TH E GEAR SELECTED DOWN BREAKER WOULD TRIP.WHEN LDG GEAR RETRACTS WIRES RUB ON GEAR LEG,&IF SWITCH IS INST W/O ANY SLACK IN WIRES THEY CAN BE PULLED OUT OF SWITCH. WIRES WERE WR APPED WITH SPIRAL WRAPAND SWITCH INST WITH ENOUGH SLACK IN THE 1 L 7 2 3O A19S0 2001092000117 20010920 00117 SO 2001 9 20 CA010820014 1 20010727 G 2740 4296102 SCREW PIPER 4269200 PIPER PA18 PA18 7101802 SO LYC O320 O320A2B 41508 EA STABILIZER BROKEN W K NONE F FLT CONT AFFECTED TX TAXI/GRND HDL 1 CA 2725 (CAN) STABILIZER TRIM FOUND NOT WORKING ON PILOT'S WALK AROUND. DISASSEMBLE AND FOUND SCREW BROKEN IN HALF, JAMMED IN TH E YOKE HOUSING. 1 H 7 1 3O 3 O 1A2 E274 2001092000118 20010920 00118 EU 2001 9 20 CA010821003 1 20010807 G 3010 3D248526 TIMER PILATS PC12 PC1245 EU PWA PT6 PT6A67B 52043 NE HARTZL HCE4A HCE4A3D GL AIRFOIL DEICER MALFUNCTIONED W K NONE L NO TEST IN INSP/MAINT 1 CA 471 (CAN) ON THE SCHEDULED AIRFOIL DEICER SYSTEM INSPECTION, IT WAS DISCOVERED THAT THE NORMAL INFLATION SEQUENCE WOULD WORK PROPERLY ONLY 1 TIME OUT OF THREE. IT WAS DETERMINED THAT THE TIMER WAS FUNCTIONING IN AN INTERMITTENT MANNER. DEICER C AUTION LIGHT WOULD COME ON INDICATING SEQUENCE MALFUNCTION. THE TIMER WAS REPLACED WITH A SERVICEABLE UNIT. 1 L 7 1 3T 4 T RT A78EU E26NE 5 C P210NE 2001092000119 20010920 00119 CE 2001 9 20 CA010821005 1 20010811 G 2434 7565T1 ALTERNATOR CESSNA 305 305A 2074002 CE CONT O470 O47011 17026 SO ENGINE FAILED W O OTHER N FALSE WARNING CR CRUISE 1 CA 446 151 (CAN) ALTERNATOR WENT OFF LINE. UPON REMOVAL OF THE ALTERNATOR WAS NOTICED THAT THE SPLINE GEAR WAS SHEARED. THE DRIVE S HAFT WAS ALSO SHEARED IN THE THREADED PORTION, JUST BELOW THE CASTLE NUT. THE CASTLE NUT WAS STILL INTACT ON THE TIP OF THE THREADED SHAFT WITH THE COTTER PIN INTACT. THIS PARTICULAR UNIT HAS BEEN SENT TO DND TEST FACILITIES TO DETERMINE TH E EXACT CAUSE OF FAILURE. 1 H 7 1 3O 3 O 5A5 E269 2001092000120 20010920 00120 CE 2001 9 20 CA010821010 1 20010808 G 3221 NA5130514DH BOLT CESSNA 208 208B 2073701 CE PWA PT6 PT6A114A 52043 NE MCAULY 3AF34C 3GFR34C703 GL NLG BROKEN W E C ENGINE SHUTDOWN ABORTED TAKEOFF D R INFLIGHT SEPARATION PARTIAL RPM/PWR LOSS TO TAKEOFF 1 CA 4347 (CAN) ON TAKE OFF PILOT BEARD A BANG. THIS WAS FOLLOWED BY A NOTICEABLE LOSS OF NOSE WHEEL CONTROL (STREERING). TAKE OFF WAS ABORTED, INSPECTION REVEALED ONE OF THE NOSE GEAR FORK ATTACH BOLTS WAS BROKEN. 1 H 7 1 3T 3 T A37CE E4EA 5 C P60GL 2001092000121 20010920 00121 CE 2001 9 20 CA010821011 1 20010813 G 2720 0411307 ARM CESSNA 206 U206G 2073356 CE CONT O550 IO550F 17042 SO RUDDER CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 2965 (CAN) DURING A 200 HOUR ANNUAL INSPECTION, THE PILOT R/H RUDDER PEDAL ARM FOUND LOOSE. THE ARM WAS CRACKED IN TWO PLACES : FROM EACH OF THE ATTACH BOLT HOLES TO THE BOTTOM OF THE TUBE. 1 H 7 1 3O 3 O A4CE E3SO 2001092100008 20010921 00008 WP 2001 9 21 CA010822013 2 20010730 G 7250 TPE33110UG514H ENGINE BAG JETSTM JETSTM3101 1500215 EU GARRTT TPE331 TPE33110UG 01514 WP ROTOL R333 R333482F12 GL NACELLE DAMAGED W E ENGINE SHUTDOWN X ENGINE FLAMEOUT LD LANDING 1 CA 3319 (CAN) ON LANDING IN FORT MCMURRAY ON THE MORNING OF 30 JULY, 01 AN UNCOMMANDED ENGINE SHUTDOWN OCCURRED. THE PILOT REPOR TED THAT THE ENGINE SHUT DOWN WHEN THE WHEEL TOUCHED THE GROUND, OR SHORTLY THEREAFTER. HE PULLED THE STOP FEATHER LEVER FOR THAT ENGINE AND CONTINUED THE LANDING. ON INVESTIGATION OF THE ENGINE, WE COULD NOT FIND ANYTHING WRONG EXTERNALLY, BUT THE ENGINE WOULD NOT START. WE REMOVED THE ENGINE FROM THE AIRCRAFT AND FOUND EVIDENCE THAT INTERNAL DAMAGE HAD OCC URRED. THE THIRD STAGE APPEARS TO HAVE BEEN RUBBING. 2 L 7 2 4T 4 T RT A21EU E4WE 6 C P61GL 2001092100011 20010921 00011 WP 2001 9 21 CA010823003 1 20010727 G 2120 LS11088B614 DUCT LKHEED 1011 10113853 5265020 WP RROYCE RB211 RB211524B402 54555 NE CABIN AIR SPLIT W C ABORTED TAKEOFF O OTHER TO TAKEOFF 1 CA (CAN) AIRCRAFT REJECTED TAKE OFF AT 80 KTS DUE A LOUD NOISE IN COCKPIT. FOUND THE #2 ZONE TRIP MANIFOLD DUCT HOSE COUPLI NG SPLIT. THE COUPLING WAS REPAIRED AS PER MAINTENANCE MANUAL AND SUBSEQUENTELY THE HOSE COUPLING WAS REPLACED AT THE NI GHT LAYOVER. 2 L 7 3 4F 4 F A23WE E12EU 2001092100016 20010921 00016 GL 2001 9 21 CA010823015 3 20010815 G 6110 A4643 SPACER TMPSON NAVION NAVIONA 6150104 SW MCAULY 2A34C D2A34C98 GL PROPELLER CORRODED W K NONE O OTHER IN INSP/MAINT 1 CA 43 (CAN) PART CORRODED AND INSTALLED UPSIDE DOWN. 1 L 7 1 3O A782 5 C P3EA 2001092100017 20010921 00017 SO 2001 9 21 CA010827004 2 20010809 G 7414 M3820 DISTRIBUTOR BLK SLICK 6310 CESSNA 206 TU206G 2073357 CE CONT O520 TSIO520M 17040 SO MCAULY 2AF34C D2AF34C* GL MAGNETO BURNED W K NONE O OTHER IN INSP/MAINT 1 CA 106 01012755 (CAN) BOTH MAGNETOS WERE REMOVED IN ERROR FOR 500 HR INSP ONLY LH WAS DUE WHEN RH MAGNETO WAS DISASSEMBLIED BY LEGGAT AV IATION. THE BEARING BAR P/N M3004 WAS BURNED THROUGH AT HIGH TENSION BRUSH AREA OF DISTRIBUTER BLOCK NO PROBLEM WAS EVER FOUND ON MAGNETO CHECK. 1 H 7 1 3O 3 O A4CE E8CE 5 C P5EA 2001092100018 20010921 00018 EU 2001 9 21 CA010827008 1 20010812 G 7930 1D1 CHIP DETECTOR SNIAS 350 AS350B2 8680813 EU TMECA ARRIEL ARRIEL1D NE ENGINE ACTIVATED W A UNSCHED LANDING J WARNING INDICATION CR CRUISE 1 CA (CAN) ENGINE CHIP LIGHT IN FLIGHT. CHIPS FOUND ON UPPER ELECTRICAL CHIP PLUG, MO5 AND ENGINE OIL TANK PLUGS. ENGINE REMO VED FOR EVALUATION. 1 G 7 1 3U 3 U H9EU E19EU 2001092100019 20010921 00019 SW 2001 9 21 CA010827009 1 20010814 G 6410 BLADE BELL 206011810013 BELL 206 206L1 1182107 SW ALLSN 250C 250C28B 03013 GL TAIL ROTOR TORN W A UNSCHED LANDING F D FLT CONT AFFECTED INFLIGHT SEPARATION NR NOT REPORTED 1 CA 2585 MOT3141 (CAN) WHILE IN FLIGHT THE T/R COULING FILLER COVER DEPARTED AND STRUCK THE TAIL ROTOR BLADE CAUSING A 2 CM TEAR OR HOLE IN ONE BLADE ABOUT 2/3 OF THE WAY DOWN. JUST AFT OF THE LEADING EDGE. THE A/C LANDED SAFELY. NO OTHER DAMAGES WAS FOUND. NEW COVER TO T/R ASSY INSTALLED A/C RETURNED TO SERVICE. 1 G 7 1 3U 3 U H2SW E1GL 2001092100025 20010921 00025 NE 2001 9 21 CA010828021 1 20010827 G 6510 76361040078101 COUPLER SKRSKY 763610520104 SKRSKY S76 S76A 8143006 NE ALLSN 250C 250C30S 03013 GL TAIL ROTOR CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 171 (CAN) DURING INSP OF TAIL ROTOR DRIVESHAFT ASSY IT NOTED THAT FLEX COUPLING BETWEEN INTERMEDIATE GEARBOX & NR 5 TAIL ROT OR DRIVESHAFT HAD CRACKED LAMINATE. COUPLING REMOVED & INSP. IT HAD ONE CRACKED LAMINATE (OUTTER LAMINATE OF PACK) & CRA CK LOCATED BETWEEN 2 OF FLANGE ATTACHEMNT BOLT HOLES. CRACK RUNS COMPLETLELY THROUGH LAMINATE IN STRAIGHT LINE FROM OUTT ER EDGE TO INNER EDGE. IS NO APPARENT SURFACE DEFECT THAT WOULD APPEAR SURFACE DEFECT THAT WOULD APPEAR TO BE CAUSE IF C RACK. PART HAS BEEN SENT TO SIKORSKY A/C PRODUCT SAFETY DEPARTMENT FOR EVALUATION. SIKORSKY A/C FIELD SERVICE REPRESENTA TIVE STATED THAT HAS BEEN PREVIOUS CASES OF THESE COUPLINGS CRACKING. 1 G 7 2 3U 3 U H1NE E1GL 2001092100033 20010921 00033 CE 2001 9 21 CA010828023 1 20010814 G 2730 TORQUE TUBE BEECH 1156100103 BEECH 99 99 1154002 CE PWA PT6 PT6A28 EA HARTZL HCB3T HCB3TN3 GL ELEVATOR CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA NA (CAN) UPON PERFORMING THE SB2145 ON THE COMPONENT.FIRST INSPECTION FROM FACTORY, WE DO IT UPON ARRIVAL FOR QUALITY REASO NS. A CRACK WAS FOUND DURING THE LPI PROCESS.THE CRACK TRAVELS FROM INSIDE THE HOLE TO APROX. 4MM OUTSIDE THE HOLE RUNN ING AXIAL ALONG THE TUBE. TUBE WAS REJECTED. 1 L 7 2 3T 4 T A14CE E4EA 6 C P15EA 2001092100035 20010921 00035 CE 2001 9 21 CA010829009 1 20010819 G 2810 052600750 FUEL TANK CESSNA 172 172N 2072434 CE LYC O320 O320H2AD 41508 EA MCAULY 1C160 1C160DTM GL FUSELAGE CRACKED W K NONE K FLUID LOSS IN INSP/MAINT 1 CA 4055 (CAN) TANK WOULD ALWAYS POP OR OIL CAN AS IT WAS FILLED, LEAK WOULD ONLY OCCUR WHEN TANK WAS FUELLED RIGHT TO THE TOP. I T IS BELIEVED THAT THE REPETITIVE OIL CANNING OF THE TANK CAUSED A FATIQUE CRACK TO START. THE TANK WAS REPAIRED AND THE UPPER SURFACE WAS CONTOURED BACK TO ITS ORIGINAL SHAPE SO IT WILL NOT OIL CAN ANY LONGER. 1 H 7 1 3O 3 O NT 3A12 E274 5 N P910 2001092100047 20010921 00047 CE 2001 9 21 CA010830007 1 20010823 G 2435 23079004 STARTER GEN CESSNA 441 441 2076020 CE GARRTT TPE331 TPE3318 01514 WP HARTZL HCB3T HCB3TN5 GL RT ENGINE FAILED W E H ENGINE SHUTDOWN DEACTIVATE SYST/CIRCUITS H ELECT. POWER LOSS-50 PC TX TAXI/GRND HDL 1 CA 84 (CAN) PILOT WAS TAXING WHEN HE LOST TOTAL POWER TO NO. 2 BUS. INVESTIGATION FOUND THAT THE R/H GENERATOR COOLING FAN BL ADES TOTALLY CRACKED OFF AND FLEW INTO THE GENERATOR WINDINGS, DESTROYING ALL WORKING CAPABLITY OF STARTER GENERATOR. TH IS CAUSED A GCU FAILURE AND A NO. 2 BUS CURRENT LIMITER TO BLOW AS WELL. 1 L 7 2 3T 4 T RT A28CE E4WE 6 C P15EA 2001092100048 20010921 00048 EU 2001 9 21 CA010830009 1 20010823 G 2160 9599020135 CONTROL VALVE PILATS PC12 PC1245 EU PWA PT6 PT6A67B 52043 NE HARTZL HCE4A HCE4A3D GL TEMP CONTROL SEIZED W D RETURN TO BLOCK J WARNING INDICATION TX TAXI/GRND HDL 1 CA 3783 3783 (CAN) AFTER STARTUP THE PILOT SELECTED COOL SETTING ON THE ENVIRONMENTAL CONTROL SYSTEM (ECS). THE SYSTEM BLEW COOL AIR FOR APPROX 25 SECONDS, THEN BLEW HOT AIR. AFTER APPROX 1 MINUTE THE SYSTEM SHUTDOWN AND AN AMBER LIGHT INDICATING ECS FA ILURE APPEARED ON THE CAWS DISPLAY. THE SYSTEM AND DETERMINED THAT THE TEMP CONTROL VALVE WAS NOT FUNCTIONING. AFTER REP LACEMENT OF THE PART AND RUNUP, THE SYSTEM WORKED NORMALLY. AIRCRAFT WAS RETURNED TO SERVICE. 1 L 7 1 3T 4 T RT A78EU E26NE 5 C P210NE 2001092100049 20010921 00049 EU 2001 9 21 CA010830017 1 20010713 G 3246 AHA1489 WHEEL BAG BAE146 BAE146200A 1500266 EU LYC ALF502 ALF502R5 41580 NE MLG CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 3234 699 (CAN) THE WHEEL HAD BEEN REMOVED DUE TO THE TIRE BEING WORN TO LIMITS. DURING THE CLEANING PROCESS, TWO CRACKS WERE DISC OVERED VISUALLY. THEY RAN FROM THE LIGHTENING HOLES TO UNDER THE WHEEL BEARING OUTTER RACE. PICTURES ARE AVAILABLE. THE WHEEL HALF HAD BEEN N.D.T. INSPECTED AT LAST TIRE REPLACEMENT MAR 28/01. 2 H 7 4 4F 4 F RT A49EU E6NE 2001092100055 20010921 00055 GL 2001 9 21 CA010830020 2 20010828 G 7313 2306045 NOZZLE BELL 206 206B 1181511 SW ALLSN 250C 250C20B 03013 GL ENGINE WARPED W K NONE O OTHER IN INSP/MAINT 1 CA 535 (CAN) THERE WERE INTERMITTENT START DELAYS ON A/C AT VARIOUS TIMES DURING OPAL SORTIES. IT DETERMINED THAT POOR FITTING 1ST STAGE NOZZLE CAUSED START DELAY. TURBINE REPD WITH INST OF NEW 1ST STAGE NOZZLE P/N 23062753 S/N KD258711; NEW NOZZ LE SHIELD P/N 23073533&2 NEW POSING PLUGS P/N 23009573. NOZZLE TBO 535.6 HRS, NOZZLE SHIELD TBO U/K 535.6 HRS SINCE INSP . POS PLUG TSN U/K TBO U/K TIME SINCE INSP 535.6 HRS. FINDINGS PRIOR TO THE REPLACED OF AFOREMENTIONED PARTS; 1ST STAGE NOZZLE P/N 23060450, NOZZLE SHIELD P/N 6890040 APPEARED TO BE WARPED WHEN PLACED ON LEVELING PLATE THAT MAY HAVE CONTRIB UTED TO POOR FIT OF BOTH ENGINE COMPONENTS. ONE ADDITIONAL OBSERVATIO N MODS TO LOWER POSING PL 1 G 7 1 3U 3 U H2SW E4CE 2001092100059 20010921 00059 SO 2001 9 21 CA010831004 1 20010821 G 7120 3743701 FASTENER PIPER PA34 PA34220T 7103420 SO CONT O360 TSIO360KB 17025 SO MCAULY 3AF32C 3AF32C508 GL FITTING MISSING W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) 1. FITTING, ASSY OUTBOARD LOWER ENGINE MOUNT. ONE MISSING FASTENER ON OUTBOARD LOWER SIDE FITTING (P/N: 37437-01). 2. FITTING, ASSY INBOARD LOWER ENGINE MOUNT. ONE MISSING FASTENER ON INBOARD LOWER SIDE OF FITTING (P/N: 37442-01) 1 L 7 2 3O 3 O A7SO E9CE 5 C P22EA 2001092100062 20010921 00062 EA 2001 9 21 CA010831005 2 20010815 G 7210 GEARBOX BELL 212 212 1181420 SW PWA PT6T PT6T3 52045 EA MAIN ROTOR DAMAGED W A UNSCHED LANDING J WARNING INDICATION CR CRUISE 1 CA (CAN) ON RAMP AFTER M/R HEAD CHANGE MASTER CAUTION LIGHT ACTIVATED&ENGINE CHIP LIGHT ACTIVATED. ENGINEER FOUND ON REAR C HIP DETECTOR FOR ENGINE MINOR FUZZ. ENGINER CLEANED CHIP DETECTOR & REINSTALLED ENGINEER INSPECTED FILTERS & FOUND NO DI SCREPANCY. A/C GROUND RUN&NO CHIP LIGHTS OCCURRED. AFTER TRACK & BALANCE. COUPLE HRS LATER ANOTHER ENGINE CHIP LIGHT. TI ME MASSIVE AMOUNTS OF METAL. A/C SHUTDOWN. METAL GENERATION MAYBE COMING FROM NR 2 POWER SECTION OR COMBINING GEARBOX. O NCE POWER SECTION REMVD BEARING CAGE OF NR 5 DUPLEX BEARING IN TRANSITION AREA OF POWER SECTION&COMBINING GEARBOX. COMBI NING GEARBOX REPLACED. TSO OF COMBINING GEARBOX 2126 HRS. 1 G 7 1 4U 4 U H4SW E22EA 2001092100065 20010921 00065 CE 2001 9 21 CA010831006 1 20010817 G 2820 TUBE CESSNA 206 U206G 2073356 CE CONT O550 IO550F 17042 SO MCAULY D3A34 D3A34C402 GL FUEL SYSTEM LEAKING W L ABORTED APPROACH K R J FLUID LOSS PARTIAL RPM/PWR LOSS WARNING INDICATION CR CRUISE 1 CA (CAN) NR 5 CYLINDER FUEL DISTRIBUTION TUBE RUPTURED DURING CRUISE FLIGHT. TUBE BREAK IS AT THE CONNECTION TO FUEL DISTRI BUTOR VALVE. CONNECTION POINT A CYLINDER REMAINED INTACT. FAILURE OCCURRED AT FLANGE END WHERE TUBE FLARE END IS BRAZED TO TUBE ASSY. NO POSITIVE CAUSE IDENTIFIED. VIBRATION AND CYCLES MAY HAVE CONTRIBUTED TO FAILURE. POSSIBLE FLAW WITH BRA ZING OF TUBE ASSY. 1 H 7 1 3O 3 O A4CE E3SO 5 C P47GL 2001092100068 20010921 00068 CE 2001 9 21 CA010831007 1 20010803 G 7120 NAS148A94 BOLT CESSNA 208 208B 2073701 CE PWA PT6 PT6A114A 52043 NE MCAULY 3AF34C 3GFR34C703 GL ENGINE MOUNT DAMAGED W K NONE W INADEQUATE Q C IN INSP/MAINT 1 CA 3800 (CAN) ON ENGINE REMOVAL, MAINTENACE FOUND ENGINE MOUNT BOLT PART NO. NAS 148A94 (S3461-64) AT LEFT, LOWER ENGINE MOUNT B RACKET. (ITEM 27)- THREADBOUND DUE TO WASHER PART NO. MS20002C8 NOT INSTALLED AT FACTORY ASSEMBLY. MAINTENACE ALSO FOUND INCORRECT WASHERS PART NO. AN960-616L INSTALLED ON ENGINE MOUNT BOLTS AT RIGHT LOWER BRACKET (ITEM 28) AND TOP CENTER B RACKET (ITEM 26)- INSTEAD OF WASHERS PART NO. MS20002C8. THE THREE REMAINING CESSNA 208B AIRCRAFT IN THE FLEET WERE INSP ECTED FOR THE SAME CONDITION WITH NO DISCREPANCIES NOTED. 1 H 7 1 3T 3 T A37CE E4EA 5 C P60GL 2001091700030 20010917 00030 WP 2001 9 17 CA010831010 1 20010822 G 6210 369D21100523 MAIN ROTOR HUGHES 369D21200503 HUGHES 369 369D 4470706 WP ALLSN 250C 250C20B 03013 GL LWR SKIN ROOT CRACKED W O OTHER O OTHER IN INSP/MAINT 1 CA 3340 2544 (CAN) 1 1/2"- 2" CHORDWISE CRACKS IN LOWER ROOT DOUBLER ADJACENT TO OUTBOARD END OF ROOT END FITTING. TWO BLADES FROM SA ME SET WITH SIMILAR CRACKS S/N'S 009999-K068,-K070. *TORQUE EVENTS CALCULATED BY TSNX20 (REF: BOEING SERVICE BULLETIN SB 369D195R3) 1 G 7 1 3U 3 U H3WE E4CE 2001092100074 20010921 00074 CE 2001 9 21 CA010831012 1 20010802 G 2434 BRUSHES CESSNA 991059111 CESSNA 172 172R 2072401 CE LYC IO360 IO360L2A EA ALTERNATOR FAILED W O OTHER H W ELECT. POWER LOSS-50 PC INADEQUATE Q C TX TAXI/GRND HDL 1 CA 472 A149997 (CAN) - AIRCRAFT ALTERNATOR FAILED. - ALTERNATOR INTERIOR INSPECTION REVEALED A BROKEN BRUSH BLOCK ASSEMBLY CAUSED BY A INCORRECT INSTALLATION. 1 H 7 1 3O 3 O NT 3A12 1E10 2001092100075 20010921 00075 CE 2001 9 21 CA010831013 1 20010816 G 2434 9910591111 BRUSHES CESSNA 9910591111 CESSNA 172 172R 2072401 CE LYC IO360 IO360L2A EA ALTERNATOR BROKEN W K NONE H W ELECT. POWER LOSS-50 PC INADEQUATE Q C TX TAXI/GRND HDL 1 CA 445 A150018 (CAN) - AIRCRAFT ALTERNATOR FAILED. - ALTERNATOR INTERIOR INSPECTION REVEALED A BROKEN BRUSH BLOCK ASSEMBLY CAUSED BY A INCORRECT INSTALLATION 1 H 7 1 3O 3 O NT 3A12 1E10 2001092100076 20010921 00076 EU 2001 9 21 CA010831014 1 20010824 G 5610 9598110108 WINDSHIELD PILATS PC12 PC1245 EU PWA PT6 PT6A67B 52043 NE HARTZL HCE4A HCE4A3D GL COCKPIT FAILED W C ABORTED TAKEOFF O OTHER TO TAKEOFF 1 CA 132 (CAN) ON TAKE-OFF AT FT ST. JOHN, CO-PILOTS WINDSHIELD SHATTERED JUST AT ROTATION, PILOT ABORTED TAKEOFF AND TAXIED BACK TO RAMP. WINDSHIELD WAS REPLACED 132 HRS PRIOR. 1 L 7 1 3T 4 T RT A78EU E26NE 5 C P210NE 2001092100077 20010921 00077 EU 2001 9 21 CA010831016 1 20010828 G 7712 5771112104 TUBE PILATS PC12 PC1245 EU PWA PT6 PT6A67B 52043 NE HARTZL HCE4A HCE4A3D GL GEARBOX OIL LEAKING W K NONE K FLUID LOSS IN INSP/MAINT 1 CA (CAN) PART TIME NOT KNOWN. METAL CLAMP ON LINE CHAFED THROUGH OIL LINE.TUBE WAS FOR TORQUE TRANSDUCER. FIG 01, 77-10-00 ITEM 10 MOST OF THESE LINES HAVE CLAMPS WITHOUT RUBBER INSERTS. THEY ARE METAL ON METAL. 1 L 7 1 3T 4 T RT A78EU E26NE 5 C P210NE 2001092100079 20010921 00079 NE 2001 9 21 CA010831018 2 20010831 G 7314 RG9570R1M COVER PILATS PC12 PC1245 EU PWA PT6 PT6A67B 52043 NE HARTZL HCE4A HCE4A3D GL FUEL PUMP LOOSE W K NONE K FLUID LOSS IN INSP/MAINT 1 CA 2761 2761 (CAN) COVER SCREWS WERE FOUND WITH INSUFICIENT TORQUE AS PER FOCA AD HB 2001-500. COVER SCREWS WERE TORQUED TO SPECIFICA TIONS AND SAFTIED AS PERSB28-009NO SIGNS OF FUEL LEAKAGE OR EXTRUDED GASKET MATERIAL WAS FOUND. 1 L 7 1 3T 4 T RT A78EU E26NE 5 C P210NE 2001092100080 20010921 00080 NE 2001 9 21 CA010831019 2 20010824 G 7314 RG9570R1 PUMP PILATS PC12 PC1245 EU PWA PT6 PT6A67B 52043 NE HARTZL HCE4A HCE4A3D GL ENGINE LEAKING W K NONE K FLUID LOSS IN INSP/MAINT 1 CA 1020 (CAN) INSPECTION OF THE ENGINE DRIVEN FUEL PUMP AS PER PILATUS AWD HB2001-500 AND SB 28-009 REVEALED THAT FUEL PUMP WAS LEAKING AND EXTRUDED GASKET MATERIAL WAS FOUND. THE TORQUE OF THE SCREWS WAS CHECKED. 1/8TH TO 1/4 TURNS WERE NEEDED TO TORQUE THE SCREWS TO THE SPECIFIED TORQUE OF 23 IN LB TO 25 IN LB. THE PUMP WAS REPLACED. 1 L 7 1 3T 4 T RT A78EU E26NE 5 C P210NE 2001092100082 20010921 00082 NM 2001 9 21 CA010905008 1 20010717 G 2540 214861 SLEEVE BOEING 747 747475 NM GE CF6 CF680C2B6F 30025 NE DUMP VALVE SHORTED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) A/C 381 M FOUND DURING UNRELATED ROUTINE MAINT IN AREA. EVIDENCE OF FIRE DAMAGE CAUSED BY SHORTED LEAD AT WASTER T ANK DUMP VALVE HEATER SLEEVE. FIRE TRACK WAS FOLLOWED FROM SOURCE FWD THROUGH LIGHTNING HOLE OF ADJACENT STRUCTURE, & UP WARD ALONG FRAME TO STRINGER 3 FEET FROM AFT DUMP VALVE LOCATION. INSP OF STRUCTURE CARRIED OUT, NIL DEFECTS TO STRUCTUR E FOUND. INSULATION BLANKETS REMVD & REPLD DUE TO BURN DAMAGE OF OUTER LAYER. AREA CLEANED OF DUST. AREA RPTECTED. A/C R ELEASED FOR SERVICE. BOEING FIELD REP INFORMED. AIR CANADA ENGINEERING TO INVESTIGATE & LIASE WITH BOEING CUSTOMER REPS FOR SOLUTION & FURTHER INSP REQMTS. FLEET CAMPAIGN TO INSPECT AFFECTED AREA IS UNDER CONSIDERATION. 2 L 7 4 4F 4 F RT A20WE E13NE 2001092100085 20010921 00085 NE 2001 9 21 CA010906006 2 20010902 G 7320 311989203 FUEL CONTROL PILATS PC12 PC1245 EU PWA PT6 PT6A67B 52043 NE HARTZL HCE4A HCE4A3D GL ENGINE INTERMITTENT W C ABORTED TAKEOFF X J ENGINE FLAMEOUT WARNING INDICATION TO TAKEOFF 1 CA 2556 2556 (CAN) A/C IN QUESTION IN RED LAKE & ON ITS BACKTRACK.EVERYTHING INDICATING NORMAL.FLT IDLE ASKED FOR & WHEN LEVER SET FO R FLT IDLE IT NOTICED GEN 1 LIGHT CAME ON. ENGINE IN PROCESS OF FLAME OUT & CONTINUED UNTIL STOPPED. MAINT CONTACTED & I NSP ENGINE FROM FRONT TO BACK WITH ASSISTANCE OF PRAT REP. BOROSCOPE, CHIP DETECTOR INSP, RUNUPS, NOTHING VIABLE COULD B E FOUND TO EXPLAIN EVENTS EXCEPT THAT IT WAS FCU AS IT CNTLS FUEL. PRATT BACKED UP THINKING & FCU REPL. THE STARTER GEN REPLACED ALSO. ALL GROUND RUNS CHECKED WITHIN MFGS PARAMETERS.A/C FERRIED TO THUNDER BAY & ENGINE REPLACED FOR OTHER RE ASONS. 1 L 7 1 3T 4 T RT A78EU E26NE 5 C P210NE 2001092100103 20010921 00103 EU 2001 9 21 CA010906017 1 20010719 G 5530 5357500020000 BOLT AIRBUS 320 A320211 3930320 EU CFMINT CFM56 CFM565A1 NE VERTICAL STAB LOOSE W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) DURING H-CHECK AND ACCOMPLISHING AIRCRAFT MAINTENANCE MANUAL TASK 53-51-00-210-009 FOUND THREE BOLTS LOOSE AS WELL AS CORRODED NUT FOR THE TAIL CONE ATTACHMENT.BOLTS RETORQUED AND NUTS REPLACED. 2 L 7 2 4F 4 F RT A28NM E29NE 2001092100104 20010921 00104 NM 2001 9 21 CA010906019 1 20010729 G 8012 97910211 VALVE BOEING 737 737275 1384485 NM PWA JT8 JT8D17 52049 NE STARTER FAILED W C ABORTED TAKEOFF J WARNING INDICATION TO TAKEOFF 1 CA (CAN) TWO AIR TURN BACK DUE TO A #1 START VALVE OPEN LIGHT ILLUMINATED DURING FLIGHT. ACCOMPLISHED #1 ENGINE FAILURE SHU TDOWN TWICE.AFTER THE FIRST INCIDENT, THE STARTER, START VALVE AND ACTUATOR PRESSURE SWITCH WERE CHANGED, & THE SECOND T IME THE START VALVE & THE PRESSURE SWITCH WAS REPLACED. IT WAS DETERMINED THAT THE FIRST START VALVE WAS A ROGUE UNIT. T HE FINAL FIX WAS THE REPLACEMENT OF THE STARTER VALVE. 2 L 7 2 4F 4 F A16WE E2EA 2001092100105 20010921 00105 NE 2001 9 21 CA010906020 2 20010807 G 7230 1211313010 ACTUATOR AIRBUS 320 A320211 3930320 EU CFMINT CFM56 CFM565A1 NE ENGINE FAILED W E ENGINE SHUTDOWN D R INFLIGHT SEPARATION PARTIAL RPM/PWR LOSS DE DESCENT 1 CA (CAN) COMPRESSOR STALL 25 MINUTES BEFORE LANDING IN TORONTO, AIRCRAFT DECLARED AN EMERGENCY LANDING, THE CREW RE-STARTED THE ENGINE AND LANDED SAFELY WITH NO INCIDENT. AIRCRAFT REMOVED FROM SERVICE FOR TROUBLESHOOTING AND RECTIFICATION.FOUN D TO BE THE VARIABLE STATOR ACTUATOR AT FAULT.REPLACED THE VARIABLE STATOR ACTUATOR. 2 L 7 2 4F 4 F RT A28NM E29NE 2001092100107 20010921 00107 NE 2001 9 21 CA010907001 1 20010826 G 6230 LINK SKRSKY S76 S76A 8143006 NE MAIN ROTOR WRONG PART W K NONE W INADEQUATE Q C IN INSP/MAINT 1 CA (CAN) DURING A MAIN GEARBOX BUILDUP AND PRIOR TO INSTALLATION OF THE STATIONARY SCISSORS ASSEMBLY, THE ENGINEER NOTICED THE UPPER LINK OF STATIONARY SCISSORS WAS ASSEMBLED 180 DEGREES OUT OF POSITION. THE ENGINEER CORRECTED THIS CONDITION P RIOR TO INSTALLING THE SCISSORS ASSEMBLY ON THE MAIN GEARBOX. UNCORRECTED, THIS WOULD LIMIT THE VERTICALMOVEMENT (DOWN) OF THE SWASHPLATE. 1 G 7 2 3U H1NE 2001092100131 20010921 00131 WP 2001 9 21 CA010907007 1 20010823 G 6210 369A10045 PIN HUGHES 369 369D 4470706 WP ALLSN 250C 250C20B 03013 GL M/R BLADE SHEARED W K NONE O OTHER IN INSP/MAINT 1 CA 5295 (CAN) WHILE CARRYING OUT HIS DAILY INSPECTION, THE PILOT NOTICED THE NUT LOOSE ON THE BLADE PIN UPON INSPECTION THE THRE ADED PORTION OF THE BLADE PIN WAS SHEARED. 1 G 7 1 3U 3 U H3WE E4CE 2001092100134 20010921 00134 CE 2001 9 21 CA010907010 1 20010823 G 5313 05131324 STRINGER CESSNA 172 172K 2072430 CE LYC O320 O320E2D 41508 EA MCAULY 1A175 1A175* GL FUSELAGE CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 13201 (CAN) DURING ROUTINE MAINTENANCE INSPECTION, IT WAS DISCOVERED THAT THE RIGHT HAND ENGINE RAIL WAS CRACKED. P/N 0513132- 4 STRINGER ASSEMBLY IN FUSELAGE FRONT SECTION STRUCTURE ASSEMBLY WAS REPLACED. 1 H 7 1 3O 3 O NT 3A12 E274 5 N P857 2001091700033 20010917 00033 CE 2001 9 17 CA010907020 1 20010719 G 5230 NAS561F824 ROLL PIN CESSNA 208B CESSNA 208 208B 2073701 CE PWA PT6 PT6A114A 52043 NE MCAULY 3AF34C 3GFR34C703 GL ROLL PIN BENT W K NONE O OTHER CR CRUISE 1 CA 13231 208B0305 (CAN) IT APPEARS SOMEONE TRIED TO UNLATCH THE UPPER CARGO DOOR WITHOUT PUSHING (ITEM #41) RELEASE KNOB TO RELEASE THE IN NER HANDLE FROM THE LOCK PLATE (ITEM #46) EXCESSIVE FORCE WAS APPLIED THUS DAMAGING MECHANISM (ROLL PIN ITEM #2), WITH T HIS CONDITION, IF THE INNER HANDLE WAS POSITIONED IN THE LOCK PLATE THEN THE LOCK PINS WOULD BE RETRACTED ALLOWING THE D OOR TO COME OPEN. DOOR WARNING SYSTEM CHECKED AFTER REPAIRS AND FUNCTIONED NORMALLY. PILOT REPORTED THAT DOOR WARNING LI GHT CAME ON JUST PRIOR TO OPENING. 1 H 7 1 3T 3 T A37CE E4EA 5 C P60GL 2001092100143 20010921 00143 EA 2001 9 21 CA010910003 2 20010822 G 7230 3013511 COMPRESSOR WHEEL DHAV DHC6 DHC6100 EA PWA PT6 PT6A20 52043 EA ENGINE FAILED W O OTHER M J OVER TEMP WARNING INDICATION TX TAXI/GRND HDL 1 CA 3543 (CAN) HOT START LACK OF POWER.HOT SECTION REMOVED FROM POWER OLANT. SERVICEABLE HOT SECTION INSTALLED AIRCRAFT RUN CARRI ED OUT. FOUND SATISFACTORY. SHROUD P/N 3020259STATOR ASSY P/N 3018490 1 H 7 2 3T 3 T A9EA E4EA 2001092400012 20010924 00012 NM 2001 9 24 CA010910007 1 20010624 G 3220 141T991113 SPRING BOEING 767 767233 NM PWA JT9 JT9D7R4D 52054 NE SPIN BRAKE MISSING W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) ON WALK AROUND IN YYZ, FOUND RIGHT HAND NOSE WHEEL SPIN BRAKE SPRING MISSING. INSTALLED SPIN BRAKE SPRING. 2 L 7 2 4F 4 F RT A1NM E3NE 2001092100021 20010921 00021 NM 2001 9 21 CA010910009 1 20010810 G 8011 449188 SEAL PWA JT8D17A BOEING 737 7372T7 1384482 NM PWA JT8 JT8D17A 52049 NE STARTER LEAKING W O OTHER O OTHER CR CRUISE 1 CA 702788 (CAN) NR 2 LOW OIL PRESSURE FLICKERING FOR THE LAST 4 MINUTES OF FLIGHT WITH THE PRESSURE GAUGE IN AND OUT OF CAUTION RA NGE. TEMPERATURE NORMAL, ENGINE OPERATED AT REDUCED THRUST AND SHUTDOWN AFTER LANDING. FOUND TO BE THE STARTER DRIVE P AD CARBON SEAL TO BE LEAKING (AROUND 200 ML/15 MINUTES). REPLACED SEAL. 2 L 7 2 4F 4 F RT A16WE E2EA 2001092400014 20010924 00014 SW 2001 9 24 CA010911002 1 20010910 G 6330 209040110015 STUD BELL 212040001059 BELL 212 212 1181420 SW PWA PT6T PT6T3B 52045 NE TRANSMISSION MISSING W O OTHER O OTHER NR NOT REPORTED 1 CA ABW50227 (CAN) FOUND BOKEN OFF STUD ON THE LIFT LINK TRANSMISSION MOUNT. ON THE TRANSMISSION THE LEFT REAR STUD HAD BROKEN OFF. T HEY FOUND THIS DEFECT WHILE CHANGING A SERVO. 1 G 7 1 4U 4 U H4SW E22EA 2001092400015 20010924 00015 SW 2001 9 24 CA010912003 1 20010819 G 5302 206031329103S FITTING BELL 206 206L 1181522 SW ALLSN 25OC 250C20R GL TAILBOOM CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) ROUTINE INSPECTION UPPER LEFT TAIL ATTACH FITTING FOUND CRACKED.REPLACED AS PER BELL STRUCTURAL REPAIR MANUAL 6-21 4, BUT NUMEROUS REPORTS OF CRACKS IN THIS LH UPPER FITTING AREA OF TAILBOOM/FUSELAGE INTERFACE. 1 G 7 1 3U 3 U H2SW E4CE 2001092400017 20010924 00017 CE 2001 9 24 CA010912007 1 20010820 G 5310 50420013451 CROSSBEAM BEECH 90 C90A 1152911 CE PWA PT6 PT6A21 52043 EA HARTZL HCB3T HCB3TN3 GL LWR FWD SILL CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 2617 2617 (CAN) IT WAS FOUND THAT AN INDIVIDUAL HAD REMOVED MATERIAL FROM THE DOUBLER & CROSS-TIE IN AN EFFORT TO ELIMINATE CONTAC T WITH THE EMERGENCY EXCAPE HATCH.CRACKS WERE FOUND PROPAGATING FROM THE SHARP CORNER OF THIS RADIUS. WE ALSO DISCOVERED DURING THE REMOVAL OF THIS PART, THAT IT WAS INSTALLED WITH A PRE LOAD DURING THE RIVETING PROCESS. I AM SURE THIS HELP ED THE CRACKS TO FORM.NO REFERENCES OR DATA WAS FOUND TO SUPPORT THE WORK DONE, BUT IT CLEARLY DID NOT FOLLOW STANDARD P RACTICES. 1 L 7 2 3T 4 T RT 3A20 E4EA 6 C P15EA 2001092400026 20010924 00026 2001 9 24 CA010912016 4 20010912 G 3425 HARNESS PILATS PC12 PC1245 EU PWA PT6 PT6A67B 52043 NE HARTZL HCE4A HCE4A3D GL FLIGHT CONTROL CHAFED W K NONE O OTHER IN INSP/MAINT 1 CA 3197 3197 (CAN) WHILE MOVING THE ELEVATOR CONTROL, A SLIGHT "CATCH" COULD BE FELT.INVESTIGATION REVEALED THAT WHEN PULLED BACK, TH E AILERON CROSSOVER TIE ROD P/N 941.93.43.415 ON THE CONTROL COLUMN, CAME INTO CONTACT WITH THE WIRING HARNESS ON THE BA CK OF THE MULTI FUNCTION DISPLAY (MFD). THE SCREWS HOLDING THE MFD CONNECTOR TO THE BACK OF THE MFD TRAY WERE ALSO PULL ED OUT. THE WIRING HARNESS OF THE MFD WAS INSPECTED FOR CHAFFING AND REPOSITIONED AND FASTENED. NEW SCREWS WERE INSTALL ED TO HOLD THE MFD CONNECTOR TO THE TRAY. 1 L 7 1 3T 4 T RT A78EU E26NE 5 C P210NE 2001092400027 20010924 00027 CE 2001 9 24 CA010912017 1 20010904 G 5342 04321671 STIFFENER CESSNA 150 150J 2071820 CE LYC O320 O320E2D 41508 EA MCAULY 1C172 1C172TM GL STAB ATTACH CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 4671 (CAN) COMMON PROBLEM ON OLDER CESSNA 150 SERIES, MANUFACTURER HAS BEEN REPLACED THIS PART WITH A NEW IMPROVE PART P/N 04 32169-1 ALSO INCLUDING NEW IMPROVE BULKHEAD ASSY P/N 0412177-2. 1 H 7 1 3O 3 O 3A19 E274 5 N P910 2001092400028 20010924 00028 WP 2001 9 24 CA010912018 1 20010905 G 6520 369D25400B GEARBOX HUGHES 369 369D 4470706 WP ALLSN 250C 250C20B 03013 GL TAIL ROTOR MAKING METAL W A UNSCHED LANDING J WARNING INDICATION CL CLIMB 1 CA 13075 426 (CAN) DURING A HELICOPTER ENGINE PERFORMANCE CHECK AT 2000 FT CRUISE, THE TAIL ROTOR GEARBOX CHIP LIGHT ILLUMINATED AND STAYED LIT. AFTER LANDING AT BASE, THERE WAS METAL FLAKES PRESENT ON CHIP DETECTOR. T/R GEARBOX WAS FLUSHED, CHIP DETECT OR CLEANED, & RE-INSTALLED. AIRCRAFT WAS GROUND RUN FOR 10 MIN AND SHUTDOWN.T/R GEARBOX CHIP DETECTOR REMOVED AGAIN.META L WAS FOUND ON DETECTOR - T/R GEARBOX REMOVED FROM AIRCRAFT. 1 G 7 1 3U 3 U H3WE E4CE 2001092400029 20010924 00029 SW 2001 9 24 CA010913001 1 20010904 G 6210 TRIM TAB BELL 407015001117 BELL 407 407 SW ALLSN 250C 250C47B GL M/R BLADE DEBONDED W K NONE O OTHER IN INSP/MAINT 1 CA 400 400 A348 (CAN) DURING SCHEDULED AIRFRAME PERIODIC INSP TRIM TAB ON PARTICULAR MAIN ROTOR BLADE FOUND TO HAVE SEVERE DEBONDING WHI CH INITIALLY SHOWED UP AS CRACKS IN FILLER MATERIAL AROUND TRIM TAB EDGES. CLOSER INSP REVEALED SEVERE DEBONDING & COMPR OMISE OF TRIM TAB ATTACHMENT SECURITY. MAIN ROTOR BLADE REPLACED WITH NEW FROM BELL HELICOPTER. MAIN ROTOR BLADE S/N A-3 48 HAD TOTAL TIME SINCE NEW OF 2052.5. IT HAD BEEN INSP & REPLACED AT BELL HELICOPTER AT TOTAL TIME SINCE NEW OF 1652.2 AT WHICH TIME TRIM TAB REPLACED. (TIME SINCE REPAIR & TRIM TAB REPLACED 400.3). IT IS QUITE COMMON TO SEE MINOR CRACKING IN FILLER MATERIAL SURROUNDING TRIM TAB. 1 G 7 1 3U 3 U O H2SW E1GL 2001092400030 20010924 00030 CE 2001 9 24 CA010913004 1 20010912 G 3243 99123057 VALVE CESSNA 500 S550 2076607 CE PWA JT15 JT15D4 52112 NE BRAKE FAILED W O OTHER J WARNING INDICATION TX TAXI/GRND HDL 1 CA 7984 (CAN) FOLLOWING AN UNEVENTFUL LANDING AND WHILE TAXING AFTER THE LANDING ROLL OUT, THE CREW ENCOUNTERED A BRAKE FAILURE AND HAD TO APPLY THE EMERGENCY BRAKE IN ORDER TO STOP THE AIRCRAFT. MAINTENANCE TROUBLESHOOTING AND INSPECTION OF THE SY STEM DETERMINED THAT THE POWER BRAKE -ANTI SKID VALVE ASSEMBLY HAD FAILED. THE VALVE ASSY WAS REPLACED AND ALL TESTS CON DUCTED IN ACCORDANCE WITH THE MM AND THE AIRCRAFT RELEASED. 1 L 7 2 4F 4 F RT A22CE E1NE 2001092400031 20010924 00031 CE 2001 9 24 CA010914002 1 20010824 G 5343 05411212 CASTING CESSNA 182 182A 2072704 CE CONT O470 O470L 17026 SO MCAULY 2A34C 2A34C66 GL REAR GEAR CUTOUT CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 6293 (CAN) SUPPORT CASTING HAD CRACK FROM RADIUS OF CUTOUT FOR GEAR REARWARD. 0541153 U-BOLT WAS ALSO BROKEN AND REPLACED. 1 H 7 1 3O 3 O NT 3A13 E273 5 C P3EA 2001092400042 20010924 00042 EU 2001 9 24 CA010914004 1 20010910 G 2750 ONL312014 BOLT Z4243430000 ZLIN 242 Z242L 9970204 EU LYC O360 AEIO360A1B6 41514 EA FLAP BELLCRANK BENT W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) DURING A 100/500 HOUR INSPECTION THE LT FLAP BELLCRANK BOLT (P/N ONL3120.146X77)WAS FOUND TO BE BENT. THE BOLT WAS REPLACED WITH A NEW ONE. IT IS SUSPECTED THAT A STUDENT PILOT EXTENDED THE FLAPS ABOVE THE MAXIMUM SPEED ALLOWED FOR FL AP EXTENSION. THE MAINTENANCE SCHEDULE ALREADY HAS AN ADDITIONAL INSPECTION ON THE FLAP BOLTS AND THE INSTRUCTORS AND ST UDENTS WERE AGAIN REMINDED OF THE PROPER PROCEDURE USING THE FLAPS. 1 L 7 1 3O 3 O 0 A76EU 1E10 2001092400059 20010924 00059 EU 2001 9 24 CA010917001 1 20010913 G 2434 HEDCR132200 BRUSHES BOSCH 5243212158 PILATS PC12 PC1245 EU PWA PT6 PT6A67B 52043 NE HARTZL HCE4A HCE4A3D GL GENERATOR WORN W K NONE H J ELECT. POWER LOSS-50 PC WARNING INDICATION CR CRUISE 1 CA 3296 3296 (CAN) THE NR 2 GENERATOR CAUTION LIGHT ILLUMINATED ON CAWS PANEL. EIS INDICATED THAT NR 2 GENERATOR HAD COME OFF LINE.TH E PILOT THEN RE-SELECTED GENERATOR SWITCH TO ON POS,&HAD SAME SEQUENCE OF EVENTS OCCUR AGAIN. NR 2 GENERATOR WE AS LEFT OFF LINE FOR REMAINDER OF FLT. GENERATOR BRUSHES WERE REMOVED, & INSPECTED BY MAINTENACE STAFF. BRUSHES WERE FOUND TO H AVE WORN BEYOND SERVICEABLE LIMITS. ONE BRUSH WORN TO POINT WERE CONTACT NOT OCCURRING WITH ARMATURE:THE GENERATOR PREV IOUS INSTALLATION ON A/C REMOVED DUE TO (4) PREMATURE FAILURES OF BRUSH ASSY.THE CURRENT GENERATOR INSTALLED AS "NEW". IS 1ST SET OF BRUSHES TO FAIL ON INSTALLED GENERATOR. MAINTENANCE STAFF HAS NOW IMPLEMENTED. 1 L 7 1 3T 4 T RT A78EU E26NE 5 C P210NE 2001092400083 20010924 00083 EU 2001 9 24 CA010917006 1 20010917 G 2434 HEDCR132200 BRUSHES 9789601090 PILATS PC12 PC1245 EU PWA PT6 PT6A67B 52043 NE HARTZL HCE4A HCE4A3D GL GENERATOR WORN W H DEACTIVATE SYST/CIRCUITS H ELECT. POWER LOSS-50 PC CR CRUISE 1 CA 3373 NA (CAN) NR 2 GENERATOR FAILED IN CRUISE FLIGHT. NR 2 GENERATOR WAS TURNED OFF, AND AIRCRAFT RETURNED TO BASE. INVESTIGATI ON REVEALED NR 2 GENERATOR BRUSHES WORN. NR 2 GENERATOR BRUSH HOLDER ASSEMBLY P/N 978.96.01.090 REPLACED WITH NEW, AIRCR AFT GROUND RUN AND CHECKED SERVICEABLE. 1 L 7 1 3T 4 T RT A78EU E26NE 5 C P210NE 2001092500090 20010925 00090 SW 2001 9 25 CA010921005 1 20010902 G 2910 MS28775212 O-RING BELL 212076007003 BELL 205 205A1 1181414 SW LYC T53 T5313B 41549 NE PISTON SPLIT W A UNSCHED LANDING K FLUID LOSS HO HOVERING 1 CA 615 VH9812 (CAN) O-RING ON ACCUMULATOR SPLIT CAUSING HYDRAULIC FLUID LOSS. SUBSEQUENTLY THE PILOT TURNED THE #2 HYDRAULIC SYSTEM OF F AND LANDED THE AIRCRAFT. FURTHER INVESTIGATION REVEALED THAT THE #2 HYDRAULIC RESERVOIR WAS COMPLETELY DRY. THE ACCUMU LTOR WAS DISASSEMBLED AND INSPECTED REVEALING THAT THE PISTON O-RING HAD SPLIT THE O-RING WAS REVEALED AND THE REASSEMBL ED ACCUMULATOR RETURNED TO SERVICE. 1 G 7 1 4U 4 U H1SW E17EA 2002011400094 20020114 00094 NE 2002 1 14 CA010925001 2 20010916 G 7200 ENGINE PWA PT6 PT6A67B 52043 NE NACELLE MAKING METAL W O OTHER O OTHER NR NOT REPORTED 1 CA (CAN) SILVER PLATLETS WERE FOUND IN AN OIL SAMPLE TAKEN AT THE 100 HOUR MARK OF NEWLY INSTALL ENGINE. ENGINE WAS FLUSHED AND FILTER REPLACED. AFTER ANOTHER 40 HOURS OF SERVICE ON THE ENGINE IT WAS INSPECTED AGAIN AND UPON VISUAL INSPECTION IT WAS FOUND THAT THERE WAS STILL SILVER PLATLETS IN THE OIL FILTER AND WAS NOW GENERATING FERROUS METAL. IT WAS INITIA LLY BELIEVED THAT IT WAS JUST JUNK FROM ENGINE ASSEMBLY. THIS CONFIRMED THAT THE ENGINE WAS INDEED GENERATING METAL. EN GINE REMOVED AND SERVICIBLE ENGINE INSTALLED. 4 T E26NE 2002011400095 20020114 00095 2002 1 14 CA010926001 4 20010924 G 3421 INDICATOR PILATS PC12 PC1245 7090551 EU PWA PT6 PT6A67B 52043 NE HARTZL HCE4A HCE4A3D GL EADI / EHSI FAILED W O OTHER H ELECT. POWER LOSS-50 PC CR CRUISE 1 CA (CAN) CREW REPORTED JUST PRIOR TO LEVELING AT FL250, THE NR 1 EADI (UPPER PILOT WAS FLAGGED WITH "ATITUDE FAIL" .SUBSEQU ENTLY, THE FLIGHT DIRECTOR AND AUTOPILOT KICKED OFF LINE.CREW SELECTED NR 2 AHRS AND FLIGHT CONTINUED UNEVENTFULLY TO TH E NEXT DESTINATION. ON THE SUBSEQUENT START THE NR 1 AHRS WAS RESELECTED WITH NO PROBLEMS. FAILURE COULD NOT BE DUPLICA TED. 1 L 7 1 3T 4 T RT A78EU E26NE 5 C P210NE 2002011400101 20020114 00101 EU 2002 1 14 CA010927001 1 20010926 G 3230 5322012072 DRAG LINK PILATS PC12 PC1245 7090551 EU PWA PT6 PT6A67B 52043 NE HARTZL HCE4A HCE4A3D GL NLG BROKEN W O OTHER D J INFLIGHT SEPARATION WARNING INDICATION DE DESCENT 1 CA (CAN) FAILURE OF PN 532.20.12.072 NOSE GEAR DRAG LINK ON 25TH JUNE 2001. SENT IT OUT FOR INDEPENDENT FAILURE ANALYSIS & CAME BACK WITH CORROSION PITTING AS CAUSE FOR COMPROMISED STRUCTURAL STRENGTH. 1 L 7 1 3T 4 T RT A78EU E26NE 5 C P210NE 2002011400105 20020114 00105 CE 2002 1 14 CA011001002 1 20010928 G 3097 2601048200 CONNECTOR CESSNA 208 208 2073702 CE PWA PT6 PT6A114 52043 NE MCAULY 3AF34C 3GFR34C703 GL ELECTRICAL PANEL BURNED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) DURING AN INSPECTION OF THE AREA BEHIND THE ELECTRICAL PANEL BY THE PILOTS LEFT FOOT. A WIRE CONNECTOR WAS FOUND BURNED. THE WIRE CONNECTOR BETWEEN THE PROP ANTI-ICE WIRE HA-20 EXITING FROM THE CIRCUIT BREAKER PANEL AND THE WIRE HA-2 1 GOING TO THE PROP TIMER WAS FOUND BURNED AND DISTORTED FROM HEAT. ON CLOSER EXAMINATION IT WAS FOUND THE TERMINAL ON T HE WIRE HAD BEEN CRIMPED IMPROPERLY AND WAS ALLOWED TO MAKE CONTACT WITH THE PLACTIC CONNECTOR HOUSING. THE CONNECTOR WA S REPLACED AND THE AIRCRAFT WAS RETURNED TO SERVICE. 1 H 7 1 3T 3 T NT A37CE E4EA 5 C P60GL 2002011400114 20020114 00114 GL 2002 1 14 CA011002001 2 20010924 G 7321 23034702 FCU BELL 206 206B 1181511 SW ALLSN 250C 250C20 03013 GL ENGINE FAILED W A UNSCHED LANDING X ENGINE FLAMEOUT NR NOT REPORTED 1 CA (CAN) FUEL CONTROL WAS REPAIRED. FUEL CONTROL WAS INSTALLED ON BELL 206B DUE TO THE OLD ONE NEARING OVERHAUL. AFTER GROU ND RUNS A TEST FLIGHT WAS CARRIED OUT ON AIRCRAFT. AFTER THE TEST FLIGHT THROTTLE WAS DECREASED TO FLIGHT IDLE WHEN THE ENGINE ALMOST FLAMED OUT. ON THE THROTTLE ROLL DOWN THE NG RPM WENT TO 25 PERCENT (NORMAL IDLE SPEED 61PERCENT TO 63 PER CENT NG) NG RPM WOULD NOT RESPOND TO THROTTLE MOVEMENT. INSTALLED ANOTHER FUEL CONTROL AND DEFECT WENT AWAY. 1 G 7 1 3U 3 U H2SW E4CE 2002011400116 20020114 00116 SW 2002 1 14 CA011002002 1 20010917 G 7712 6856362 PISTON RROYCE 6894171 BELL 206 206B 1181511 SW ALLSN 250C 250C20 03013 GL TORQUE METER CLOGGED W K NONE O OTHER IN INSP/MAINT 1 CA CAG800082 (CAN) TORQUE INDICATOR ON THE GROUND READ 70 PERCENT TORQUE THEN CLIMBED TO 90 PERCENT TORQUE WITHOUT ADVANCING THE THRO TTLE OR INCREASING THE POWER. TORQUE INDICATOR REPLACED, DEFECT DID NOT GO AWAY. REPLACED THE ENGINE GEARBOX. IT WAS NOT ED THAT THE BLEED ORFICE WAS PLUGGED WHICH WOULD LEAD TO AN ADVANCE OF TORQUE INDICATION WITH NO INCREASE IN POWER. 1 G 7 1 3U 3 U H2SW E4CE 2002011400118 20020114 00118 SW 2002 1 14 CA011002003 1 20010915 G 6320 23034787 BEARING RROYCE 6886442 BELL 206 206B 1181511 SW ALLSN 250C 250C20 03013 GL M/R GEARBOX FAILED W A UNSCHED LANDING J WARNING INDICATION CR CRUISE 1 CA CAG34833 (CAN) PILOT REPORTED A CHIP LIGHT & A LOUD GRINDING NOISE COMING FROM THE ENGINE REGION. THE PILOT MADE A PRECAUTIONARY LANDING TO A LANDING SIGHT. THE CHIP PLUGS WERE REMOVED & FOUND LARGE AMOUNT OF FLAKES. ON THE INVESTIGATION FOUND THE T WO AND A HALF BEARING FAILED IN THE ENGINE GEARBOX. THE GEARBOX HAS 12264.1 TSN AND 2675.0 TSO. WHEN THE 2 1/2 BEARING F AILED IT CUT A GROOVE IN THE SPUR ADAPTER GEAR SHAFT RACE. 1 G 7 1 3U 3 U H2SW E4CE 2002011400121 20020114 00121 SO 2002 1 14 CA011002004 1 20010927 G 3260 BRACKET PIPER PA31 PA31350 7103110 SO LYC O540 TIO540J2BD 41532 EA RT MLG UPLOCK FAILED W L ABORTED APPROACH J WARNING INDICATION LD LANDING 1 CA 11788 (CAN) RT MAIN GEAR FAILED TO EXTEND. THIS WAS DUE TO RIVETS ATTACHING UPLOCK BRACKETS P/N 40616-01 & 40616-02 SHEARING. THIS MAY HAVE BEEN DUE TO CORROSION. THIS ALLOWED W8 OF LDG GEAR TO PULL RIVETS THROUGH 2 ANGLES P/N 40625-00. AS A RESU LT OF THIS, A MISALIGNMENT OF UPLOCK HOOK WITH UPLOCK ROLLER CAUSED UPLOCK HOOK TO JAM. THIS PREVENTED GEAR FROM EXTENDI NG. PILOT WAS ABLE TO FREE GEAR BY APPLYING POSITIVE & NEGATIVE G LOADS ON GEAR. GEAR THEN EXTENDED NORMALLY. UPLOCK BRA CKETS HAD BEEN MODIFIED WHEN BOUNDARY LAYER RESEARCH STC-SA 00202SE SUPER CHIEF II WAS INST & AGAIN WHEN BOUNDARY LAYER RESEARCH SB- BLR 105 WAS COMPLIED WITH. 1 L 7 2 3O 3 O A20SO E14EA 2002011400122 20020114 00122 CE 2002 1 14 CA011002005 1 20011020 G 2897 WIRE BEECH 99 99 1154002 CE PWA PT6 PT6A27 52043 EA COCKPIT PANEL BURNED W C ABORTED TAKEOFF B J SMOKE/FUMES/ODORS/SPARKS WARNING INDICATION TO TAKEOFF 1 CA (CAN) DURING TAKE OFF THE CREW OBSERVED A LOW FUEL PRESSUE LIGHT INDICATION ACCOMPANIED BY THE TRIP OFF OF THE CIRCUIT B REAKER SWITCH FOR THE LT SECONDARY PUMP.SMOKE WAS EMINATING FROM BEHIND THE LOWER LEFT PANEL AT THE SAME TIME. THE TAKE OFF WAS ABORTED AND THE AIRCRAFT WAS SHUTDOWN ON THE RUNWAY. MAINTENANCE FOUND A TERMINAL ON THE CB/SWITCH THAT APPEARED TO BE LOOSE WHICH IS BELIEVED TO GENERATED THE WIRING OVERTEMP. THE DAMAGED WIRE AND CB/SWITCH WERE REPLACED.THE CB WAS EXAMINED AND FOUND TO HAVE NO INTERNAL ANOMOLIES 1 L 7 2 3T 4 T A14CE E4EA 2002011500001 20020115 00001 SW 2002 1 15 CA011002006 1 20010916 G 6220 D2B20000B LIMITER KAMOV KA32 KA32A1 SW MAIN ROTOR CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) CRACK DISCOVERED DURING POST FLIGHT INSPECTION. FURTHER INVESTIGATION FOUND LEAD AND LAG DRAG HINGE BEARINGS WERE VERY STIFF IN TWO OF THE 3 ROTOR HEAD SLEEVES. 1 G 7 2 4U NC 2002011400229 20020114 00229 EA 2002 1 14 CA011002007 2 20010916 G 7530 3027249 BLEED VALVE DHAV DHC6 DHC6100 2802610 EA PWA PT6 PT6A20 52043 EA ENGINE FAILED W D RETURN TO BLOCK J WARNING INDICATION TO TAKEOFF 1 CA (CAN) DROP IN ENGINE TORQUE, PROP LEVER PUSHED FORWARD, TEMPED OUT AT 35 LBS TORQUE. 1 H 7 2 3T 3 T RT A9EA E4EA 2002011500002 20020115 00002 SW 2002 1 15 CA011002009 1 20010727 G 5302 2060313291 FITTING BELL 206 206B 1181511 SW ALLSN 250C 250C20 03013 GL TAILBOOM CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 12293 (CAN) TAILBOOM FITTING LT FUSELAGE SIDE FOUND CRACKED VERTICALLY 1 INCH IN LENGTH. NEW PART ORDERED AND INSTALLED. 1 G 7 1 3U 3 U H2SW E4CE 2002011500003 20020115 00003 CE 2002 1 15 CA011002010 1 20010908 G 5312 12128582 BULKHEAD CESSNA 206 206CESSNA 2073302 CE CONT O520 IO520F 17032 SO MCAULY 2A34C D2A34C58 GL FUSELAGE CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) CRACKS IN AFT FUSELAGE BULKHEAD. 1 H 7 1 3O 3 O A4CE E5CE 5 C P3EA 2002011500004 20020115 00004 SO 2002 1 15 CA011003001 1 20011002 G 6120 B3807 NUT HARTZL HCE2YR2RBS PIPER PA23 PA23250 7102308 SO LYC O540 IO540* 41532 EA HARTZL HCE2Y HCE2YR2 GL PROPELLER MISINSTALLED W K NONE W INADEQUATE Q C IN INSP/MAINT 1 CA BP9803B (CAN) THIS IS 2ND OCCURANCE OF PROBLEM. PROP INSTALLED ON OTHER ENGINE HAD SAME PROBLEM. BOTH PROPS WERE NEW WITH ASSY DATES OF 11-13-97&12-18-97, SHIPPED 4/16/98. PROP CHECKED AS PRECAUTIONARY MEASURE: NUT IS SOLID STEEL SELF LOCKING NUT , THAT HOLDS PISTON TO PISTON ROD. IF NUT COMES LOOSE, PISTON COMES OFF OF ROD & PROP HAS UNCOMANDED FEATHER WITH NO WAY TO UNFEATHER PROP. PISTON SEALS PITCH CHANGE OIL ON ROD. OTHER PROP SER BP9804B, NUT HAD COME COMPLETELY LOOSE. PROP RE MVD&CHECKED. NUT NOT LOOSE ON PISTON ROD, TORQUE OF NUT CHECKED&NO MOVEMENT FOUND. 1 L 7 2 3O 3 O 1A10 1E4 5 C P9EA 2002011500005 20020115 00005 GL 2002 1 15 CA011003002 2 20010904 G 7321 BEARING BELL 47 47G4 1181030 SW ALLSN 250C 250C20B 03013 GL FCU FAILED W A UNSCHED LANDING J WARNING INDICATION IN INSP/MAINT 1 CA 330031 (CAN) INITIAL PROBLEM ENCOUNTERED WAS A CHANGE IN IDLE SPEED. IDLE WAS ADJUSTED, AIRCRAFT WAS TEST FLOWN & NBO PROBLEMS EXISTED.NEXT DAY AIRCRAFT IDLE SPEED HAD CHANGED. IDLE WAS ADJUSTED & RIGGING CHECKED. AIRCRAFT WAS RUN & TEST FLOWN. WH ILE AIRCRAFT WAS RETURNING TO SIGHT IT BEGAN N1 FLUCTUATIONS. THE PILOT LANDED & PULLED COLLECTIVE, FLUCTUATION STOPPED. RETURNED A/C TO A MAINTENANCE FACILITY. AT THIS TIME HE HAD TO REDUCE TO THROTTLE TO PREVENT ENGINE OVERSPEED. FUEL CO NTROL WAS REMOVED. UPON REMOVAL A LARGE AMOUNT OF METAL FLAKES FELL FROM THE F.C.U. DRIVE BEARING HAD FAILED & THE SHAFT WAS FREE FLOATING. 1 G 7 1 3O 3 U 2H3 E4CE 2001101500063 20011015 00063 WP 2001 10 15 CA011003004 1 20010921 G 6310 A1902 V-BELT LYC ROBSIN R22 R22 7640102 WP LYC O320 O320B2C 41508 EA FRONT ENGINE TORN W O OTHER D INFLIGHT SEPARATION CR CRUISE 1 CA (CAN) BELTS SENT TO R.H.C. FOR INVESTIGATION. THEIR RESPONSE WAS THAT THE BELTS WERE DRY AND CAUSED SMALL CRACKS IN THE RUBBER WHERE THE BELTS ARE RIDING ON THE SHEAVE. 1 G 7 1 3O 3 O H10WE E274 2002011500006 20020115 00006 EA 2002 1 15 CA011003006 2 20010924 G 7313 LW18853 INJECTOR PIPER PA31 PA31 7103102 SO LYC O540 TIO540J2BD 41532 EA HARTZL HCC4Y HCC4YR2 GL RT ENG NR 3 CYL LOOSE W O OTHER R J PARTIAL RPM/PWR LOSS WARNING INDICATION NR NOT REPORTED 1 CA (CAN) PILOT REPORTED INTERMITTENT SLIGHT POWER LOSS & ROUGH RUNNING AT CRUISE POWER, GROUND POWER RUNS SHOWED NORMAL. IN SPECTION OF RT ENGINE FOUND NR 3 CYLINDER FUEL INJECTOR "LOOSE" IN CYLINDER HOUSING AND FUEL STAINING AROUND THE AREA. F UEL INJECTOR THREADS & CYLINDER THREADS WERE DAMAGED. IT WAS NOTED THE FUEL INJECTOR LINES WERE PROPERLY CLMAPED AS OUTL INED IN AD 93-02-05 (SB 342). INSPECTION OF THE OTHER INJECTORS FOUND NO PROBLEMS. SUSPECT VIBRATION TO HAVE CAUSED THE INJECTOR TO LOOSEN. NO UNUSUAL VIABRATION REPORTED PREVIOUS TO THIS. 1 L 7 2 3O 3 O A20SO E14EA 5 C P52GL 2002011500007 20020115 00007 SW 2002 1 15 CA011003009 1 20010917 G 5320 206063107005 LEG ASSY BELL 206 206L 1181522 SW ALLSN 25OC 250C20R GL ENGINE BAY CORRODED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) WHILE CARRYING OUT A 100 HOUR INSPECTION THE ENGINEER NOTICED A HILOCK COLLAR IN THE ENGINE BAY. UPON INVESTIGATIO N IT WAS NOTED THAT THE HI-LOCK PIN HAD CORRODED THROUGH & THE COLLAR FELL OFF. LEG ASSEMBLY REPLACED WITH NEW. 1 G 7 1 3U 3 U H2SW E4CE 2002011500008 20020115 00008 SW 2002 1 15 CA011003010 1 20010913 G 6730 412076670101 BEARING BELL 212 212 1181420 SW PWA PT6T PT6T3 52045 EA UNIVERSAL FAILED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) AME WAS COMPLETING A DAILY INSPECTION WHEN HE PULLED THE LT SERVO BRUSH TUBE AND FELT PLAY. UPON INVESTIGATION A B EARING IN THE UNIVERSAL HAD FAILED. 1 G 7 1 4U 4 U H4SW E22EA 2002011500009 20020115 00009 SO 2002 1 15 CA011003013 2 20010523 G 8520 CRANKSHAFT CESSNA 337 T337H 2075733 CE CONT O360 TSIO360H 17025 SO MCAULY 2AF34C D2AF34C308 GL ENGINE FAILED W A UNSCHED LANDING Y J ENGINE STOPPAGE WARNING INDICATION CR CRUISE 1 CA (CAN) INFLIGHT CATASTRPHIC FAILURE, CRANKSHAFT, AT LEAST 2 RODS, HOLE IN TOP OF CRANKCASE, CONTINUED FLIGHT ON, REAR ENG INE TO VIKING AIRPORT (ALBERTA). 1 H 7 2 3O 3 O A6CE E9CE 5 C P5EA 2002011500010 20020115 00010 CE 2002 1 15 CA011003014 1 20010914 G 2750 0512128 BRACKET CESSNA 185 A185F 2072821 CE CONT O520 IO520D 17032 SO MCAULY 3A32C D3A32C90 GL TE FLAPS BROKEN W D RETURN TO BLOCK O OTHER TX TAXI/GRND HDL 1 CA 10325 (CAN) FLAPS WOULD NOT EXTEND PROPERLY FOR TAKEOFF. PILOT LEFT FLAPS IN UP POSITION AND RETURNED TO BASE. BRACKET IS MOUN TED TO LOWER BULKHEAD USING 4 SCREWS AND LOCKNUTS ON THE 4 MOUNT TABS. BOTH INBOARD TABS ON BRACKET HAD FAILED AT THE BE ND RADIUS, ALLOWING THE BRACKET TO BEND FORWARD AND BIND THE CABLE ON THE COTTER PIN THAT KEEPS THE CABLE IN THE PULLEY GROOVE. NO OTHER DAMAGE WAS DONE TO THE STRUCTURE OR CABLE. 1 H 7 1 3O 3 O 3A24 E5CE 5 C P21EA 2002011500011 20020115 00011 CE 2002 1 15 CA011003015 1 20010916 G 7120 85921701 SPACER J961358 CESSNA 401 401B 207590E CE CONT O520 TSIO520EB 17040 SO ENGINE MOUNT WRONG PART W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) WHILE INSTALLING NEW ENGINE NOTICED THAT ENGINE ATTACH BOLTS WERE TOO SHORT. PART NR OF BOLTS WERE CORRECT. ENGIN E MOUNTS WERE FOUND TO BE PROBLEM. SPACERS IN ENGINE MOUNT KITS WERE WRONG LENGTH & WRONG PART NR. 1 L 7 2 3O 3 O A7CE E8CE 2002011500012 20020115 00012 CE 2002 1 15 CA011003016 1 20010903 G 2133 47061 VALVE CESSNA 441 441 2076020 CE CABIN PRESSURE FAILED W A UNSCHED LANDING B J SMOKE/FUMES/ODORS/SPARKS WARNING INDICATION CL CLIMB 1 CA (CAN) DURING AIRCRAFT CLIMB, THE EMERGENCY PRESSURIZATION VALVE OPENED ALLOWING UNCONDITIONAL BLEED AIR INTO THE CABIN. CABIN TEMPERATURE INCREASED AT AN UNCONTROLED RATE. AIRCRAFT RETURNED TO THE AIRPORT FROM WHICH IT DEPARTED. THE EMERGEN CY PRESSURIZATION VALVE WAS REPLACED. AIRCRAFT GROUND RUN "S". 1 L 7 2 3T RT A28CE 2002011500014 20020115 00014 NM 2002 1 15 CA011004001 1 20010729 G 2910 8297000269 LINE DHAV DHC8 DHC8301 NM PWA PW120 PW123 NE HAMSTD 14SF 14SF23 NE HYD SYSTEM CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) DURING 20 FH MAINTENANCE INSPECTION, MAINTENANCE FOUND HYDRAULIC FLUID LEAKING AROUND FS UNLOADING VALVE IN ENGINE NR 2 NACELLE. THE LINE P/N 8297000-269 IS REPORTED TO HAVE A CRACKED CRYOFLARE FITTING. 2 H 7 2 4T 4 T RT A13NM E20NE 6 C P7NE 2002011500016 20020115 00016 NM 2002 1 15 CA011004003 1 20010728 G 2910 82970009267 LINE DHAV DHC8 DHC8* NM PWA PW120 PW123 NE HAMSTD 14SF 14SF23 NE HYD SYSTEM CHAFED W K NONE K FLUID LOSS IN INSP/MAINT 1 CA (CAN) DURING 20 FH INSPECTION, MAINTENANCE FOUND EVIDENCE OF HYDRAULIC LEAK IN THE LT ENGINE NACELLE. THE LINE P/N 82970 009-267 (FS UNLOADING VALVE TO RETURN MANIFOLD) AND LINE P/N 82970009-157 (RESERVOIR TO HYDRAULIC SOV) CHAFED TOGETHER.T HE TWO LINES WERE REPLACED.TSN/CSN 896.05/793 2 H 7 2 4T 4 T RT A13NM E20NE 6 C P7NE 2002011500017 20020115 00017 NE 2002 1 15 CA011004004 2 20010918 G 8530 ST90P10ER CYLINDER HEAD DHAV DHC2 DHC2* 2800108 EA PWA R985 R985AN14B 52008 NE ENGINE CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) CRACK FOUND ON CYLINDER HEAD FROM EXHAUST PORT TO FRONT SPARK PLUG WHILE PERFORMING AD 78-08-07. 1 H 7 1 3R 3 R A806 5E1 2002020700002 20020207 00002 EA 2002 2 7 CA011004005 1 20010927 G 5523 VALTOCC113618 ATTACH FITTING DHAV C3TE1213 DHAV DHC3 DHC3 2800202 EA PWA PT6 PT6A135 52043 NE ELEVATOR SERVO CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) DURING INSPECTIONS FOUND THAT ELEVATOR SERVO TAB HAD TWO SHEARED OFF RIVETS UPPER FORWARD ENGINE AT ARM ATTACHMENT BLOCK AND CRACK AT LOWER BETWEEN RIVET HOLES ON ELEVATOR SERVO TAB. 1 H 7 1 3R 4 T A815 E4EA 2001101500064 20011015 00064 CE 2001 10 15 CA011004008 1 20011003 G 3610 S189148 CLAMP CESSNA CM357024 CESSNA 500 500CESSNA 2076602 CE PWA JD15 JT15D1A NE CLAMP LOOSE W B EMER. DESCENT O OTHER CL CLIMB 1 CA (CAN) CLIMBING THROUGH FLIGHT LEVEL 290, AIRCRAFT CABIN STARTED TO RAPIDLY CLIMB. FLIGHT CREW INITIATED A RAPID DECENT T O 10,000 FEET. AIRCRAFT LANDED WITHOUT FURTHER INCIDENT. MAINTENANCE FOUND CLAMP ON CABIN BLEED AIR SUPPLY LINE LOOSE AN D THE AIR SUPPLY LINE HAD BECOME DISCONNECTED. THE AIRCRAFT HAD RECENTLY HAD MAINTENANCE PERFORMED ON THE BLEED AIR SYST EM. ALL OTHER CLAMPS IN THE BLEED AIR SYSTEM WERE CHECKED FOR SECURITY WITH NO FURTHER PROBLEM FOUND. 1 L 7 2 4F 4 F A22CE E25EA 2002011500020 20020115 00020 CE 2002 1 15 CA011004010 1 20010829 G 6100 CA462220W BOLT MCAULY 1C160DTM755 CESSNA 172 172M 2072418 CE LYC O320 O320E2D 41508 EA MCAULY 1C160 1C160DTM GL PROPELLER BROKEN W K NONE O OTHER IN INSP/MAINT 1 CA 729634 (CAN) ONE OF THE 6 BOLTS ATTACHING THE PROPELLER TO THE ENGINE CRANK SHAFT FLANGE BROKE AT THE TOP OF THE THREADED AERA ON INITIAL TORQUE.THE PROPELLER HAD A PLACARD INDICATING TORQUE SPED FOR 1/2" BOLTS. PROLLER IS ATTACHED WITH 7/16" BOLT S. IT IS SUSPECTED THAT THE BOLTS HAVE BEEN OVER TORQUED ON PREVIOUS INSTALLATIONS. PLACARD WAS REMOVED FROM THE PROPELL ER AND BOLTS TORQUED TO THE PROPER TORQUE SPEC FOR 7/16 BOLTS. 1 H 7 1 3O 3 O NT 3A12 E274 5 N P910 2002011500025 20020115 00025 SO 2002 1 15 CA011004016 1 20011004 G 7120 12351015 MOUNT PIPER PA18 PA18A150 7101837 SO LYC O320 O320A2B 41508 EA ENGINE BROKEN W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) ENGINE MOUNT RIGHT DIAGNEL ARM FOUND BROKEN APPROX 2" FROM UPPER RIGHT FIREWALL ATTACH POINT. ENGINE MOUNT REMOVED AND REPLACED WITH NEW 1 H 7 1 3O 3 O 1A2 E274 2002011500026 20020115 00026 CE 2002 1 15 CA011004017 1 20010918 G 7160 04500704 SEAL CESSNA 04500521 CESSNA 150 152 2071835 CE LYC O235 O235L2C 41505 EA AIRBOX TORN W C ABORTED TAKEOFF R J PARTIAL RPM/PWR LOSS WARNING INDICATION TO TAKEOFF 1 CA (CAN) - AIRCRAFT ROUGH RUNNING, NOT PRODUCING FULLPOWER. AIR BOX REMOVED AND BUTTERFLY SEAL FOUND UNSERVICEABLE. A SM ALL PIECE A SEAL WAS FOUND IN CARB. VENTURI. A NEW AIR DOOR SEAL WAS INSTALLED.- AIRCRAFT GROUND RUN & CHECKED OK. 1 H 7 1 3O 3 O NT 3A19 E223 2002011500028 20020115 00028 CE 2002 1 15 CA011005001 1 20010923 G 3510 17201041 REGULATOR SCOTT BEECH 90 C90A 1152911 CE PWA PT6 PT6A21 52043 EA OXYGEN BOTTLE MISMARKED W O OTHER L NO TEST LD LANDING 1 CA (CAN) CREW REPORTED O2 SYSTEM NOT FUNCTIONING CORRECTLY. ON INVESTIGATION MAINTENANCE DISCOVERED REGULATOR WAS INSTALLED 180 DEGREES OUT OF RIG. ON FURTHER EXAMINATION REGULATOR VALVE WAS FOUND TO ROTATE 360 DEGREES FOR MULTI-POSITION INSTA LLATIONS. O2 BOTTLE HAD RECENTLY BEEN INSTALLED & HAD FLOWN ONE FLIGHT BEFORE BEING SNAGGED. THE POTENTIAL FOR SERIOUS I NCIDENT AT ALTITUDE COUPLED WITH A DEPRESSURIZATION IS HIGH WITH THIS TYPE OF INSTALLATION. THE VALVE IS NOT "MURPHY PRO OF" & REQUIRES EXTREME CARE AND ATTENTION ON INSTALLATION AS THE VALVE ON THE REGULATOR IS ALSO POORLY MARKED FOR ON & O FF POSITION. 1 L 7 2 3T 4 T RT 3A20 E4EA 2002011500029 20020115 00029 SW 2002 1 15 CA011005002 1 20010926 G 6320 204040701103 BEVEL GEAR BELL 212040001123 BELL 212 212 1181420 SW PWA PT6T PT6T3 52045 EA TRANSMISSION BROKEN W K NONE O OTHER IN INSP/MAINT 1 CA ABW40395 (CAN) METAL PARTICLES FOUND IN SUMP FILTER AT 50 HOUR INSPECTION. TRANSMISSION REMOVED AND SENT FOR OVERHAUL. WHEN ROTOR BRAKE QUILL WAS REMOVED I NOTICED HEAVY WEAR ON THE TEETH OF THE PINION. INSPECTION OF THE SPIRAL BEVEL GEAR REVEALED T WO BROKEN TEETH AND HEAVY WEAR MARKS ON BACK SIDE OF ALL REMAINING TEETH. 1 G 7 1 4U 4 U H4SW E22EA 2002011600003 20020116 00003 CE 2002 1 16 CA011005003 1 20010919 G 2436 VR600A VOLT REGULATOR CESSNA 150 150M 2071830 CE CONT O200 O200A 17020 SO MCAULY 1A102 1A102OCM GL DC ELECTRICAL INOPERATIVE W O OTHER J WARNING INDICATION CR CRUISE 1 CA (CAN) INCOMPATIBILITY BETWEEN PARTS.IT HAS BEEN DISCOVERED THAT SEVERAL SUPPLIERS HAVE BEEN INFORMED THAT VOLTAGE REGULA TORS LAMAR DGR 6 & ELECTROSYS VR600A ARE COMPATIBLE & INTERCHANGEABLE. IN ACTUALFACT LAMAR DGR6 IS INTERCHANGEABLE WITH THE ELECTROSYS VR600. NOTE: VR600 VOLTAGE REGULATORS ARE NO LONGER AVAILABLE. NOTE: ELECTROSYS VR600A HAS BUILT IN OVER -VOLTAGE PROTECTION CCT.WHEN INSTING ELECTROSYS VR600A FOR 1ST TIME, INST INSTRUCTION REQUI RE YOU TO COMPLETELY REMOVE OVER-VOLTAGE SWITCH P/N C593001-010 FROM A/C. 1 H 7 1 3O 3 O 3A19 E252 5 N P918 2002011500030 20020115 00030 CE 2002 1 15 CA011005004 1 20010921 G 2710 262400724 BELLCRANK CESSNA 208 208B 2073701 CE PWA PT6 PT6A114A 52043 NE MCAULY 3AF34C 3GFR34C703 GL AILERON WORN W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) DURING SCHEDULED MAINTENANCE, EXCESSIVE PLAY WAS FOUND BETWEEN THE RT OUTBOARD AILERON BELL CRANK AND THE RESPECTI VE AILERON PUSH / PULL TUBE. FURTHER INVESTIGATION REVEALED THAT THE ATTACH POINT HOLE DIMENSIONS WERE BEOND ACCEPTABLE LIMITS. BELL CRANK WAS REPLACED WITH A NEW ASSEMBLY. 1 H 7 1 3T 3 T A37CE E4EA 5 C P60GL 2002011500039 20020115 00039 SW 2002 1 15 CA011011007 1 20010831 G 5302 206020123008 STRUCTURE BELL 206 206B 1181511 SW ALLSN 250C 250C20 03013 GL TAILBOOM V FIN VIBRATION W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) PART CAUSING HIGH VIBRATION IN T/R SYSTEM. REPLACED VERTICAL FIN. 1 G 7 1 3U 3 U H2SW E4CE 2002011500040 20020115 00040 SW 2002 1 15 CA011011008 1 20010831 G 5302 206020121006 FITTING BELL 206 206B 1181511 SW ALLSN 250C 250C20 03013 GL TAILBOOM V FIN CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) PART CRACK AT REAR RIVET. REPLACED FITTING. 1 G 7 1 3U 3 U H2SW E4CE 2002011500041 20020115 00041 SW 2002 1 15 CA011011009 1 20010916 G 2822 1C274 PUMP BELL 206 206B 1181511 SW ALLSN 250C 250C20 03013 GL FUEL BOOST FAILED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) PUMP NOT WORKING MOTOR UNSERVICEABLE. REPLACED PUMP ASSEMBLY. 1 G 7 1 3U 3 U H2SW E4CE 2002011500042 20020115 00042 EU 2002 1 15 CA011011010 1 20010917 G 2911 704A34240015 ACCUMULATOR SNIAS 350 AS350BA 8680817 EU TMECA ARRIEL ARRIEL1B 6OO30 NE HYD SYSTEM LEAKING W K NONE K FLUID LOSS IN INSP/MAINT 1 CA (CAN) PART LEAKING. PART REPLACED. 1 G 7 1 3U 3 U NC H9EU E19EU 2002011500043 20020115 00043 GL 2002 1 15 CA011011011 2 20010918 G 7210 4638001001 GEARBOX BOLKMS 105 BO105S 5626006 EU ALLSN 250C 250C20B 03013 GL ENGINE MAKING METAL W A UNSCHED LANDING J WARNING INDICATION CR CRUISE 1 CA (CAN) PIC CALLED IN A MAGNETIC LITE ON. A/C LANDED AT SCHOOL. AME INSPECTED MAG PLUG, 1 SMALL FLAKE AND 1 THIN HAIR. A/C RUN UP CARRIED OUT NO FURTHER INDICATION. A/C FLOWN APPROX 8 MILES TO MIRIMICHI AIRPORT AND HOVERED AROUND RAMP AREA FO R APPROX 80 MINUTES. NO FURTHER INDICATION. AME ELECTED TO CHANGE MGB OIL AND INSPECT MGB FINE OIL FILTER. FILTER FOUND TO CONTAIN NUMEROUS PIECES OF MATERIAL AND DRAINED OIL WAS SHINY. A/C REMOVED FROM SERVICE AND TRANSPORTED BACK TO MAIN TENANCE FACILITY. 1 G 7 2 3U 3 U H3EU E4CE 2002011500044 20020115 00044 CE 2002 1 15 CA011011012 1 20010919 G 7120 05510171 MOUNT CESSNA 172 172L 2072432 CE LYC O320 O320E2D 41508 EA MCAULY 1C160 1C160CTM GL ENGINE CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) ENGINE MOUNT WAS FOUND CRACKED DURING 50 HOUR INSPECTION. NO CRACKS WERE NOTICED AT THE PREVIOUS INSPECTION AND TH E CRACK SHOWED NEW MATERIAL. THIS WOULD INDICATE DETERIORATION DURING THE LAST 50 HOUR. 1 H 7 1 3O 3 O NT 3A12 E274 5 N P910 2002011500047 20020115 00047 EU 2002 1 15 CA011011015 1 20011003 G 2710 5271212075 STOP PILATS 5271212003 PILATS PC12 PC1245 7090551 EU PWA PT6 PT6A67B 52043 NE HARTZL HCE4A HCE4A3D GL BELLCRANK MISSING W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) WHILE CARRING OUT ANNUAL INSPECTION IT WAS NOTED THAT THIS AILERON BELLCRANK STOP ON THE LEFT HAND WING WAS MISSIN G. LOOKING AT THE STOP ON THE RIGHT HAND WING IT APPEARS TO BE JUST A PLASTIC STOP PUSHED INTO A HOLE IN THE WING STRUC TURE. 1 L 7 1 3T 4 T RT A78EU E26NE 5 C P210NE 2002011500048 20020115 00048 EU 2002 1 15 CA011011022 1 20011002 G 2897 RR53710K WIRE PILATS PC12 PC1245 7090551 EU PWA PT6 PT6A67B 52043 NE HARTZL HCE4A HCE4A3D GL BOOST PUMP PINCHED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) ON REMOVAL OF THE BOOSTER PUMP, IT WAS FOUND THAT THE WIRE HARNESS, WHICH IS PART OF THE PUMP HAD APPEARED TO HAVE BEEN TRAPPED BETWEEN THE BOOSTER PUMP MOUNTING PLATE & THE AIRFRAME. THIS HAS CAUSED ONE WIRE OF THE HARNESS TO BE CRIM PED FLAT & THE INTERNAL COPPER CONDUCTOR TO BE EXPOSED.THE BOOSTER PUMP WAS CHANGED. 1 L 7 1 3T 4 T RT A78EU E26NE 5 C P210NE 2002011500049 20020115 00049 SW 2002 1 15 CA011012001 1 20011002 G 6410 212010750105 BLADE BELL 212 212 1181420 SW PWA PT6T PT6T3 52045 EA TAIL ROTOR DELAMINATED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) ON A DAILY INSPECTION THE ENGINEER WAS INSPECTING THE TAIL ROTOR BLADES, ON T/R BLADE S/N A-11101 HE FOUND A DELAM INATION AT THE TIP. A REPLACEMENT T/R HUB ASSEMBLY WAS ORDERED (TSN 729.9 OF S/N A-11101) AT TTSN 413.9 T/R BLADE WAS R EMOVED DUE TO DELAMINATION AND TO CARRY OUT SB 212-00-111 REV.A (SB 205-00-80 REV.A) T/R BLADE TIP BLOCK RETENTION MODIF ICTION. 1 G 7 1 4U 4 U H4SW E22EA 2002011500050 20020115 00050 CE 2002 1 15 CA011012002 1 20011011 G 3210 LANDING GEAR BEECH 100 A100 1152915 CE PWA PT6 PT6A28 EA RIGHT FAILED W C ABORTED TAKEOFF J WARNING INDICATION TO TAKEOFF 1 CA (CAN) AFTER TAKE-OFF RT GEAR INDICATION INDICATED RT GEAR NOT RETRACTED. GEAR WAS CYCLED DOWN AND THEN INDICATED NOT DO WN AND LOCKED. SUBSEQUENT RE-CYCLE PRODUCED SAME RESULT (NO GREEN FOR RT SIDE AND INTRANSIT LIGHT ON IN GEAR HANDLE). O BSERVATION DURING AIRCRAFT FLY-BY SHOWED GEAR IN DOWN AND LOCKED POSITION. ON THE LANDING ROLL, RT GEAR RETRACTED UNDER THE WEIGHT OF THE AIRCRAFT. INVESTIGATION UNDERWAY. 1 L 7 2 3T 4 T A14CE E4EA 2002011500169 20020115 00169 SW 2002 1 15 CA011012003 1 20011002 G 5320 205030163095 CAP BELL 205 205A1 1181414 SW LYC T53 T5317A 41549 NE FUSELAGE CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) ON A TURN AROUND CHECK AFTER REFUELING THE AIRCRAFT, AN ENGINEER FOUND A CRACK ON THE EXPOSED SIDE OF THE LEFT BEA M CAP THAT IS LOCATED NEAR THE FORWARD VERTICAL WALL. 1 G 7 1 4U 4 U H1SW E17EA 2002011500055 20020115 00055 NE 2002 1 15 CA011012008 1 20010529 G 6710 1565202535 SERVO VALVE SKRSKY S64 S64E 8142604 NE PWA JFTD12 JFTD12A4A 52047 NE MAIN ROTOR FAILED W H A DEACTIVATE SYST/CIRCUITS UNSCHED LANDING F FLT CONT AFFECTED AP APPROACH 1 CA (CAN) A/C IN LOGGING OPS NEAR SAYWARD, BC. AS PILOT MADE HIS APPROACH TO LOG LDG& INITIATED FLARE TO SLOW DOWN HIS APPRO ACH, A/C'S NOSE ABRUPTLY PITCHED UP & CONTINUED TO DO SO EVEN WITH FULL FWD CYCLIC APPLIED. A/C FINALLY LEVELED OFF THEN BEGAN VIOLENTLY PITCHING UP & DOWN. CNTL OF A/C REGAINED BY SHUTTING OFF 1ST STAGE HYDRAULIC SYS. WITH SYS REMAINING TU RNED OFF PILOT SET DOWN LOAD OF LOGS & THEN RETURNED TO SERVICE LANDING MAKING UNEVENTFUL LDG. AFTER LDG PILOT CARRIED O UT FULL HYDRAULIC SERVO CHECK & FOUND CYCLIC COULD NOT BE MOVED FWD WITH 1ST STAGE HYDRAULIC SYS ON. MAIN ROTOR TANDEM S ERVO INST IN FOR & AFT POS WAS REPL & A/C RT-SRV. 2 G 7 2 4U 4 U H4EA E15EA 2002011500056 20020115 00056 WP 2002 1 15 CA011012009 1 20010927 G 6520 369D25430 SHAFT 369D25400 HUGHES 369 369D 4470706 WP ALLSN 250C 250C20B 03013 GL T/R GEARBOX BROKEN W K NONE W INADEQUATE Q C IN INSP/MAINT 1 CA 0298 (CAN) GEARBOX RECEIVED FROM CUSTOMER WITH COMPLAINT OF T/R VIBRATION AND METAL GENERATION. ON STRIP DOWN THE OUTPUT GEAR SHAFT WAS REMOVED AND THE OUTPUT JOURNAL AND THE END OF THE OUTPUT GEARSHAFT WERE FOUND INSIDE OF THE ALIGNMENT BEARING. THE OUTPUT GEARSHAFT HAD FAILED.THIS THE SECOND OCCURRENCE OF THIS TYPE, THE FIRST OCCURRED 1997-03-05. 1 G 7 1 3U 3 U H3WE E4CE 2002011500057 20020115 00057 EA 2002 1 15 CA011016001 1 20011016 G 2120 C6VF11181 SCREEN DHAV DHC6 DHC6300 2802606 EA PWA PT6 PT6A27 52043 EA EXPANSION CHAMB BROKEN W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) DURING MAINTENACE TO CHANGE A GROUND BLOWER THE EXPANSION CHAMBER WAS REMOVED TO GAIN ACCESS TO THE BLOWER. A RAT TLE WAS NOTICED INSIDE THE CHAMBER . INVESTATION REVEALED THE INTERNAL SCREEN HAD SEPERATED FROM THE FILTER SCREEN. THIS CONDITION COULD POSSIBLY LET FOREIGN OBJECTS INTO THE HEATING SYSTEM.THE AFFECTED PART WAS REPLACED WITH A NEW ITEM .TH E NEW PART WILL BE INSPECTED PERIODICALLY TO CHECK FOR CONDITION 1 H 7 2 3T 4 T RT A9EA E4EA 2002011500058 20020115 00058 WP 2002 1 15 CA011016002 1 20011016 G 6310 369D25351 SPRAG CLUTCH HUGHES 369 369D 4470706 WP ALLSN 250C 250C20B 03013 GL CLUTCH ASSY CHIPPED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) ON 300 HOUR (SLING TIME OF 221.1 HOURS) INSPECTION THE SPRAG ASSEMBLY WAS FOUND TO HAVE ONE BROKE SPRAG 1 G 7 1 3U 3 U H3WE E4CE 2002011500059 20020115 00059 EU 2002 1 15 CA011017002 1 20011011 G 6720 350A33105803 BELLCRANK SNIAS 350 AS350B2 8680813 EU TMECA ARRIEL ARRIEL1D NE T/R GEARBOX WORN W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) TAIL ROTOR PITCH CONTROL PUSH-PULL TUBE ROD END BEARING STAKING SLEEVE WORE A CIRCULAR GROOVE INTO THE EAR / CLEVI S OF THE BELLCRANK THAT IS MOUNTED ON THE T/R GEARBOX. 1 G 7 1 3U 3 U H9EU E19EU 2002011500060 20020115 00060 EA 2002 1 15 CA011017003 2 20010921 G 7414 GEAR BENDIX S6LN1208 PIPER PA31 PA31 7103102 SO LYC O540 TIO540A2B 41532 EA MAGNETO SEIZED W E A ENGINE SHUTDOWN UNSCHED LANDING J WARNING INDICATION CR CRUISE 1 CA 8215200 (CAN) RT ENGINE SHUTDOWN IN FLIGHT, AT TOP OF CLIMB AT ABOUT 8,500 FT. PILOT COULD NOT RESTART. INSPECTION ON GROUND THE GEAR TRAIN IN ACCESSORY CASE WAS OBSERVED NOT TO TURN. THE LEFT MAG WAS REMOVED AND FOUND TO BE SEIZED. THE GEAR ON REA R OF CRANKSHAFT HAD TEETH MISSING LOCATING DOWEL SHEARED AND RETAINER BOLT BROKEN. NO DAMAGE TO NEXT GEAR IN TRAIN WAS O BSERSVED. ENGINE SENT FOR REPAIR / OVERHAUL. MAG SUBMITTED TO OAE TO DETERMINE CAUSE OF FAILURE. 1 L 7 2 3O 3 O A20SO E14EA 2002011500086 20020115 00086 SO 2002 1 15 CA011017006 1 20010504 G 3230 452440 BEARING PIPER PA31 PA31 7103102 SO LYC O540 TIO540A2B 41532 EA NLG UPLOCK SEIZED W O OTHER J WARNING INDICATION AP APPROACH 1 CA (CAN) - NOSE WHEEL WOULD NOT COME DOWN FOR LANDING, CONFIGURATION. A/C LANDED ON MAINS WITH NOSE WHEEL FULLY RETRACTED. UPON INSPECTION NOSE WHEEL UPLOCK BEARING FOUND SEIZED WHICH RESULTED IN NOSE WHEEL NOT DISENGAGING FROM UPLOCKED POSITI ON. - BEARING WAS SERVICED AT PREVIOUS 100 HOUR INSPECTION AND A/C DUE FOR ANOTHER 100 HOUR INSPECTION. - SUSPECTED CAUS E: A WET SPRING ALSO, OPERATOR'S FLIGHTS ARE MOSTLY DONE OFF OF GRAVEL STRIPS. THERE WAS A LARGE ACCUMULATION OF SAND & SILT ON LANDING GEAR. OPERATOR REGULARLY PRESSURE WASHED GEAR AND GREASE JOINTS AND HINGES. BUT UPLOCK WAS OVERLOOKED AN D NOT CHECKED REGULARLY ON WALK AROUNDS.BEARING ARE NOW INSPECTED ON A/C DAILY PREFLIGHT INSPECTIONS. 1 L 7 2 3O 3 O A20SO E14EA 2002011500088 20020115 00088 SO 2002 1 15 CA011017007 2 20010922 G 8530 CH71HER VALVE SEAT CESSNA 185 A185F 2072821 CE CONT O520 IO520D 17032 SO MCAULY 2A34C D2A34C58 GL CYLINDER HEAD CRACKED W A UNSCHED LANDING E J VIBRATION/BUFFET WARNING INDICATION CL CLIMB 1 CA (CAN) - NR 6 CYLINDER ASSEMBLY CRACKED FROM EXHAUST VALVE SEAT TO INJECTOR PORT TO INTAKE VALVE SEAT. - INJECTOR AND FUE L FLOW AND PRESSURE NORMAL SO CAUSE UNKNOWN.- CYLINDER REPLACED. 1 H 7 1 3O 3 O 3A24 E5CE 5 C P3EA 2002011500090 20020115 00090 CE 2002 1 15 CA011017008 1 20011001 G 2731 26612158 SCREW CESSNA 26612151 CESSNA 208 208B 2073701 CE PWA PT6 PT6A114A 52043 NE MCAULY 3AF34C 3GFR34C703 GL TRIM ACTUATOR DAMAGED W O OTHER F FLT CONT AFFECTED DE DESCENT 1 CA (CAN) FLIGHT CREW REPORTED JAMMED ELEVATOR TRIM. INSPECTION REVEALED DAMAGED SCREW THREADS ON THE ELEVATOR TRIM ACTUATOR (PARTS ENCLOSED).SCREW P/N 2661215-8 INTERNAL SCREW P/N 2661215-6 1 H 7 1 3T 3 T A37CE E4EA 5 C P60GL 2002011500131 20020115 00131 NM 2002 1 15 CA011017016 1 20010627 G 7930 APT761000100DW TRANSMITTER DHAV DHC8 DHC8* NM PWA PW120 PW123 NE HAMSTD 14SF 14SF23 NE OIL PRESSURE FAILED W E ENGINE SHUTDOWN O OTHER DE DESCENT 1 CA (CAN) DURING DESCENT CREW REPORTED NR 2 ENGINE OIL PRESSURE DROPPED BELOW 55 PSID. ENGINE POWER WAS REDUCED AND PROP FEA THERED AS PER FM. NH REMAINED ABOVE 75 PERCENT ON FINAL SO ENGINE WAS SHUTDOWN. NO REPORT ON NR 2 ENGINE OIL PRESSURE WA RNING LIGHT ON.ON GROUND, MAINTENANCE REPLACED BOTH THE OIL PRESSURE TRANSMITTER AND PRESSURE GAUGE. ENGINE GROUND RUN O K. AIRCRAFT RETURNED TO SERVICE. 2 H 7 2 4T 4 T RT A13NM E20NE 6 C P7NE 2002011500136 20020115 00136 CE 2002 1 15 CA011018008 1 20010721 G 2823 1013890253 SHUTOFF VALVE BEECH 90 C90A 1152911 CE PWA PT6 PT6A21 52043 EA FUEL SHUTOFF STUCK W O OTHER L NO TEST TX TAXI/GRND HDL 1 CA (CAN) DURING PILOT'S PRE-FLIGHT INSPECTION LT FUEL FIREWALL VALVE WOULD NOT CLOSE. 1 L 7 2 3T 4 T RT 3A20 E4EA 2002011500147 20020115 00147 CE 2002 1 15 CA011018009 1 20011011 G 3260 WIRE BEECH 100 100BEECH 1152916 CE PWA PT6 PT6A28 EA LT MLG DOWNLOCK BROKEN W L ABORTED APPROACH N FALSE WARNING AP APPROACH 1 CA (CAN) NO DOWN AND LOCK INDICATION FOR THE RT MAIN LANDING GEAR. FOLLOWING A MANUAL EXTENSION THE AIRCRAFT LANDED WITH OU T INCIDENT. INSPECTION REVEALED A BROKEN WIRE ON THE RT MAIN DOWN AND LOCK SWITCH. REPAIRS CARRIED OUT. LANDING GEAR FUN CTION CHECKED SERVICEABLE 1 L 7 2 3T 4 T A14CE E4EA 2002011500149 20020115 00149 EA 2002 1 15 CA011018011 2 20011001 G 7322 CF30766 FLOAT MARVELSCHEBX 105009 CESSNA 172 172 2072402 CE LYC O320 O320* 41508 EA CARBURETOR WORN W K NONE O OTHER IN INSP/MAINT 1 CA BL2213803 (CAN) CARBURETOR WOULD "FLOOD WHILE AT REST", CARBURETOR BULK DISMANTLED, TOP HALF INVERTED, FOUND FLOAT HEIGHT NON EXIS TENT, SHOULD BE 7/32. REMOVED FLOAT FOR INSPECTION. FOUND ADJUSTMENT TAB SEVERELY WORN FROM NEEDLE VALVE. REPLACED DEFEC TIVE FLOAT WITH NEW PILYMER FLOAT. 1 H 7 1 3O 3 O NT 3A12 E274 2002011500150 20020115 00150 CE 2002 1 15 CA011018012 1 20010928 G 5520 12346391 RIB CESSNA 123463324 CESSNA 206 U206G 2073356 CE CONT O520 IO520F 17032 SO MCAULY D3A34 D3A34C404 GL ELEVATOR CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) THE INBOARD NUTPLATE WITH PART OF THE RIB HAD COMPLETELY SEPARATED ALLOWING THE COUNTERWEIGHT TO MOVE FREELY FORWA RD AND AFT IN ELEVATOR HORN. 1 H 7 1 3O 3 O A4CE E5CE 5 C P47GL 2002011500151 20020115 00151 SO 2002 1 15 CA011018013 1 20011017 G 3010 25S5D508419 BOOT EMB 110 EMB110P1 3260122 SO PWA PT6 PT6A34 52043 EA DEICE SYSTEM DAMAGED W O OTHER D INFLIGHT SEPARATION AP APPROACH 1 CA (CAN) ON APPROACH A VIBRATION WAS FELT BY THE FLIGHT CREW. VISUAL INSPECTION BY THE FLIGHT CREW REVEALED THE OB LEFT HAN D WING DEICE BOOT WAS RIPPED AND FLAPING AGAINST THE WING. THE AIRCRAFT LANDED WITH OUT INCIDENT, HOWEVER A PORTION OF T HE DEICE BOOT SEPERATED FROM THE AIRCRAFT. THERE WAS NO DAMAGE INFLICTED UPON THE AIRCRAFT. 1 L 7 2 4T 4 T A21SO E4EA 2002011500152 20020115 00152 CE 2002 1 15 CA011018014 1 20010928 G 2720 0411307 TUBE CESSNA 206 U206G 2073356 CE CONT O520 IO520F 17032 SO MCAULY D3A34 D3A34C404 GL RUDDER ARM CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) TUBE CRACKED FROM BOLT HOLE TO LOWER EDGE OF TUBE. 1 H 7 1 3O 3 O A4CE E5CE 5 C P47GL 2002011500153 20020115 00153 CE 2002 1 15 CA011018015 1 20010928 G 2701 126014215 TUBE CESSNA 126014015 CESSNA 206 U206G 2073356 CE CONT O520 IO520F 17032 SO MCAULY D3A34 D3A34C404 GL CONTROL COLUMN CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) ONE OF 3 BOLT HOLES ATTACHING CONTROL WHEEL TO TUBE CRACKED FROM HOLE TO EDGE OF TUBE. 1 H 7 1 3O 3 O A4CE E5CE 5 C P47GL 2002011500154 20020115 00154 NE 2002 1 15 CA011018016 2 20010920 G 7220 555225056 RIVET CESSNA 500 550 2076604 CE PWA JT15 JT15D4 52112 NE INLET LOOSE W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) AIRCRAFT DOWN FOR PHASE 5 INSPECTION. L/H ENGINE - 2 RIVET IN THE 5 O'CLOCK POSITION AND 3 RIVETS AT 7 O'CLOCK POS ITION HAD THE HEADS PULLED 1/3 TO 2/3 AROUND THE SHANK DIAMETER.R/H ENGINE 5 TO 6 RIVETS IN THE 3 TO 6 O'CLOCK POSITION HAD THE HEADS PULLED 1/4 TO 2/3 AROUND THE SHANK DIAMETER.ALL BAD RIVETS REPLACED. 1 L 7 2 4F 4 F A22CE E1NE 2002011500155 20020115 00155 CE 2002 1 15 CA011018017 1 20011005 G 5320 50420013451 CROSSTUBE BEECH 90 C90A 1152911 CE PWA PT6 PT6A21 52043 EA FUSELAGE CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) IT WAS FOUND THAT SOME ONE HAD REMOVED MATERIAL FROM THE CROSS TIE MEMBER, PROBABLY TO DEAL WITH SOME FIT AND CLEA RANCE PROBLEM. SUBSEQUENT TO THIS WE HAVE FOUND A CRACK PROPAGATING FROM THE RADIUS FORWARD TO THE BULKHEAD. THIS AIRCRA FT WAS BEING INSPECTED IN PREPARATION FOR A C OF A APPLICATION. 1 L 7 2 3T 4 T RT 3A20 E4EA 2002020700044 20020207 00044 CE 2002 2 7 CA011018018 1 20011005 G 7500 31A4121 MANIFOLD CESSNA 500 550 2076604 CE BLEED AIR SYS CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) SEVERAL CRACKS (SEVEN) FOUND AROUND RING WHERE RADIUS MEETS TUBE. 1 L 7 2 4F A22CE 2002011500156 20020115 00156 CE 2002 1 15 CA011018020 1 20011001 G 5330 SKIN CESSNA 500 550 2076604 CE PWA JT15 JT15D4 52112 NE FUSELAGE CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) DURING SCHEDULED MAINTENANCE CESSNA 550 PHASE "5" AND PHASE "49" INSPECTIONS, OF THE R/H F.S. 287.78 SKIN SEAM, A 1.5" LONG CRACK WAS FOUND CENTERED ABOUT 115.25 (W.L.). - CESSNA INFORMATION: THIS HAVE OCCUR ON SOME AIRCRAFT, FOLLOWIN G REPAINTING. - OUR AIRCRAFT S/N 550-0702 HAVE ORIGINAL PAINT. 1 L 7 2 4F 4 F A22CE E1NE 2002011500157 20020115 00157 CE 2002 1 15 CA011018021 1 20011007 G 2121 WIRE HARNESS CESSNA 500 550 2076604 CE PWA JT15 JT15D4 52112 NE VENT BLOWER CHAFED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) LARGE WIRE BUNDLE TOO CLOSE TO VENT BLOWER MOTOR. 1 L 7 2 4F 4 F A22CE E1NE 2001110800004 20011108 00004 CE 2001 11 8 CA011018024 1 20010920 G 2422 3P639CP589BH WIRE CESSNA 3P639CP589BL CESSNA 500 500CESSNA 2076602 CE PWA JD15 JT15D1A NE SPLICE SHORTED W H DEACTIVATE SYST/CIRCUITS H ELECT. POWER LOSS-50 PC TX TAXI/GRND HDL 1 CA (CAN) DURING A ROUTINE FLIGHT, ON ARRIVAL AT YYZ #2 INVERTER FAILED. SYSTEM WAS CHECKED AND FINDINGS WERE THAT THE 115 V AC OUTPUT FOR THE R/H BUS, RUNNING BETWEEN THE INVERTER AND THE FRONT PRESSURE BULKHEAD THE WIRE WAS FOUND SHORTED. THER E WAS EVIDENCE OF CORROSION AND ARCING ADJACENT TO A CRIMP SPLICE IN WIRE #3P639-CP589BH. (SEE ACCOMPANYING DIAGRAM). IT APPEARS THAT THE INSULATION MAY HAVE BROKEN DOWN ON ONE WIRE ADJACENT TO THE SPLICE, WHICH CAUSED A SHORT CIRCUIT AND A RCING WHICH CONTINUED TO DETERIORATE THE INSULATION, CAUSING FAILURE IN THE CIRCUIT. 1 L 7 2 4F 4 F A22CE E25EA 2001110800005 20011108 00005 CE 2001 11 8 CA011019001 1 20011018 G 2436 51539012N GCU CESSNA 208 208B 2073701 CE PWA PT6 PT6A114A 52043 NE MCAULY 3AF34C 3GFR34C703 GL GCU W K NONE J WARNING INDICATION CR CRUISE 1 CA (CAN) DURING CRUISE, PILOT NOTICED STANDBY POWER ON ANNUNCIATOR FLASHING FOLLOWED SHORTLY BY THE STANDBY POWER INOP ANNU NCIATOR ON STEADILY.THIS WAS FOLLOWED BY THE GENERATOR OFF ANNUNCIATOR ILLUMINATING.BOTH GENERATOR POWER AND STANDBY POW ER COULD BE RETURNED ON LINE BY CYCLING THE STANDBY POWER SWITCH AND THE GENERATOR RESET SWITCH.SYSTEM WAS TESTED ON THE GROUND WITH A MIN/MAX RECORDING VOLTMETER. EACH ILLUMINATION OF THE ANNUNCIATOR LIGHT CORRESPONDED WITH A VOLTAGE SPIK E TO 34+ VOLTS. GENERATOR CONTROL UNIT WAS REPLACED AND SYSTEM CHECKED NORMALLY. 1 H 7 1 3T 3 T A37CE E4EA 5 C P60GL 2002011500164 20020115 00164 CE 2002 1 15 CA011019013 1 20011019 G 5751 122005312 BRACKET CESSNA 206 U206G 2073356 CE CONT O520 IO520F 17032 SO AILERON CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 10617 10617 (CAN) DURING INSPECTION THE RT INBOARD AILERON BRACKET WAS FOUND CRACKED AT BOTH I/B & O/B UPPER ATTACH POINTS. {WHERE THE BRACKET ATTACHES TO THE REAR SPAR} BRACKET REPLACED 1 H 7 1 3O 3 O A4CE E5CE 2002011600006 20020116 00006 NM 2002 1 16 CA011019022 1 20010521 G 7930 APT761000100DW TRANSMITTER DHAV DHC8 DHC8102 2809003 NM PWA 120 PW120A NE HAMSTD 14SF 14SF7 NE ENG OIL PRESSURE FAILED W E ENGINE SHUTDOWN O OTHER CR CRUISE 1 CA (CAN) ENGINE OIL PRESSURE DROPPED TO BETWEEN 44-55 PSI DURING FLIGHT. THE ENGINE POWER WAS REDUCED AND PROPELLER WAS SEL ECTED TO START FEATHER. OIL PRESSURE TRANSMITTER REPLACED, FUNCTION AND LEAK CHECKED SERVICEABLE. 2 H 7 2 4T 4 T RT A13NM E20NE 6 C P7NE 2002011600007 20020116 00007 NM 2002 1 16 CA011019023 1 20010524 G 8011 2431K2 CONTACTOR DHAV DHC8 DHC8102 2809003 NM PWA 120 PW120A NE HAMSTD 14SF 14SF15 NE STARTER STUCK W E H ENGINE SHUTDOWN DEACTIVATE SYST/CIRCUITS B H SMOKE/FUMES/ODORS/SPARKS ELECT. POWER LOSS-50 PC TX TAXI/GRND HDL 1 CA (CAN) STARTER DID NOT DISENGAGE AFTER ENGINE START, SMOKE WAS NOTICED COMING FROM THE STARBOARD ENGINE. ELECTRICAL POWER WAS REMOVED AND THE ENGINE SHUTDOWN. THE START CONTACTOR WAS STUCK CLOSED. - STARTER GENERATOR REPLACED. - GENERATOR CO ANTROL UNIT REPLACED. - START CONTACTOR REPLACED. 2 H 7 2 4T 4 T RT A13NM E20NE 6 C P7NE 2001110800007 20011108 00007 EU 2001 11 8 CA011023001 1 20011016 G 7700 9752902015 DISPLAY PILATS PC12 PC1245 7090551 EU PWA PT6 PT6A67B 52043 NE HARTZL HCE4A HCE4A3D GL DISPLAY W K NONE O OTHER LD LANDING 1 CA 062 (CAN) EIS DISPLAY LIGHTING IS VERY DIM, BARELY READABLE.IT WAS ALSO INTERMITTENTLY FLASHING FROM BRIGHT TO DIM. ACQ DIS PLAY REPLACED WITH ASERVICEABLE UNIT. A/C TIME SINCE NEW 435.2 CYCLES SINCE NEW 493 THE ACQUISITION DISPLAY HAS 135.3 HO URS. 1 L 7 1 3T 4 T RT A78EU E26NE 5 C P210NE 2002011600010 20020116 00010 EU 2002 1 16 CA011023002 1 20011017 G 7700 9752902015 DISPLAY PILATS PC12 PC1245 7090551 EU PWA PT6 PT6A67B 52043 NE HARTZL HCE4A HCE4A3D GL COCKPIT FAILED W A UNSCHED LANDING H ELECT. POWER LOSS-50 PC CR CRUISE 1 CA 018 (CAN) LOWER HALF OF EIS PANEL WOULD GO BLANK INTERMITTENTLY. TORQUE ITT, NG AND FUEL INDICATION TAPES REMAINED NORMAL. ALL OTHER INSTRUMENTS WERE AFFECTED, EITHER FLASHING, DISAPPEARING TOTALLY AND/OR INDICATING ERRONEOUS INFORMATION.YELLO W AND RED CAUTION LIGHTS WOULD INNUMINATE. WHEN "MENU" WAS SELECTED, THE TOP ROW WOULD GO BLANK AS PER NORMAL, BUT THE TRANSFERRED INFORMATION WOULD NOT SHOW UP ON THE ALTERNATE SCREENS.WHEN "TEST" WAS DEPRESSED EVERYTHING TESTED NORMAL. PANEL WOULD RETURN TO NORMAL AFTER SUBSEQUENT POWER UPS. 1 L 7 1 3T 4 T RT A78EU E26NE 5 C P210NE 2002011600011 20020116 00011 CE 2002 1 16 CA011023003 1 20011015 G 3230 08411102 LINK CESSNA 414 414 2075908 CE CONT O520 LTSIO520AE 17040 SO MLG SHEARED W L ABORTED APPROACH J WARNING INDICATION AP APPROACH 1 CA 10000 (CAN) DURING CROSS WIND LANDING APPEARENT SIDE LOAD ON LT MAIN U/C STRUT CAUSED THE THREADED PORTION OF THE LINK ASSEMBL Y TO SHEAR ALLOWING GEAR TO RETRACK. LT PROPELLER BLADES STRUCK GROUND PILOT APPLIED POWER AND ABORTED LANDING. AFTERBU RNING OFF FUEL. ATTEMPTED TO RECYCLE GEAR, NOSE AND RT GEAR INDICATED LOCKED LT INDICATED UNLOCKED. WHEN GEAR WAS RECYCL ED LT GEAR FREE FELL INTO LOCKED POSITION AND A/C LANDED WITHOUT FURTHER DAMAGE. 1 L 7 2 3O 3 O RT A7CE E8CE 2002011600013 20020116 00013 EA 2002 1 16 CA011025002 1 20010614 G 2910 DSC152D8025426 HOSE DHAV DHC7 DHC7103 2802710 EA PWA PT6 PT6A50 52043 EA HAMSTD 24PF 24PF305 GL HYD SYSTEM MISMARKED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) A HYDRAULIC HOSE, P/N DSC152D8-0254-260 WAS ORDERED FROM THE COMPANIES STORES DEPARTMENT. THE INFORMATION ON THE PACKAGING INDICATED 3000 PSI WORKING PRESSURE.THE INFORMATION BAND CRIMPED AROUND THE HOSE INDICATED 1000 PSI WORKING PR ESSURE. THE HOSE, ALONG WITH 3 OTHERS IDENTIFIED THE SAME WAY WERE RETURED TO THE SUPPLIER.THE SUPPLIER NOTIFIED THE HO SE MANUFACTURER, AND CHECKED THIER STOCK FOR LIKE HOSES.THE SUPPLIER INDICATED THAT AFTER A SEARCH, ONLY THE FOUR HOSES IN QUESTION WERE MISLABLED. 2 H 7 4 4T 4 T A20EA E4EA 6 C P1NE 2002011600015 20020116 00015 GL 2002 1 16 CA011026001 1 20010717 G 3297 4533516 WIRE NAMER T6 HARVARDMK4 1922828 GL PWA R1340 R1340AN1 52016 NE MLG INDICATOR BROKEN W O OTHER J WARNING INDICATION LD LANDING 1 CA (CAN) DURING PRE-LANDING CHECK, THE PILOT NOTICED THAT THE RT LANDING GEAR INDICATOR PIN WAS NOT SHOWING ALL THE WAY DOW N. ALL OTHER GEAR INDICATIONS WERE NORMAL. (GREEN LIGHT AND VISUAL INDICATION). INVESTIGATION REVEALED THAT THE LANDING GEAR INDICATOR CABLE WAS PULLING OUT OF THE TERMINAL END. THIS RESULTED IN A CABLE THAT WAS SLIGHTLY LONGER AND THEREF ORE GIVING THE ERRONEOUS INDICATION. A NEW CABLE WAS INSTALLED. 1 L 7 1 3R 3 R EXPA1L71 5E2 2002020800001 20020208 00001 GL 2002 2 8 CA011026002 1 20010717 G 3260 4533516 CABLE NAMER T6 HARVARDMK4 1922828 GL PWA R1340 R1340AN1 52016 NE MLG INDICATOR BROKEN W O OTHER N FALSE WARNING LD LANDING 1 CA (CAN) DURING PRE-LANDING CHECK, THE PILOT NOTICED THAT THE RT LANDING GEAR INDICATOR WAS NOT SHOWING ALL THE WAY DOWN. A LL OTHER GEAR INDICATIONS WERE NORMAL. (GREEN LIGHT AND VISUAL INDICATION). INVESTIGATION REVEALED THAT THE LANDING GEA R INDICATOR CABLE WAS PULLING OUT OF THE TERMINAL END. THIS RESULTED IN A CABLE THAT WAS SLIGHTLY LONGER AND THEREFORE GIVING THE ERRONEOUS INDICATION. A NEW CABLE WAS INSTALLED. 1 L 7 1 3R 3 R EXPA1L71 5E2 2002020800002 20020208 00002 GL 2002 2 8 CA011026003 1 20010717 G 3260 4533516 CABLE NAMER T6 HARVARDMK4 1922828 GL PWA R1340 R1340AN1 52016 NE MLG INDICATOR BROKEN W O OTHER N FALSE WARNING LD LANDING 1 CA (CAN) DURING PRE-LANDING CHECK, THE PILOT NOTICED THAT THE RT LANDING GEAR INDICATOR WAS NOT SHOWING ALL THE WAY DOWN. A LL OTHER GEAR INDICATIONS WERE NORMAL. (GREEN LIGHT AND VISUAL INDICATION). INVESTIGATION REVEALED THAT THE LANDING GEA R INDICATOR CABLE WAS PULLING OUT OF THE TERMINAL END. THIS RESULTED IN A CABLE THAT WAS SLIGHTLY LONGER AND THEREFORE GIVING THE ERRONEOUS INDICATION. A NEW CABLE WAS INSTALLED. 1 L 7 1 3R 3 R EXPA1L71 5E2 2002011600016 20020116 00016 2002 1 16 CA011026004 4 20010828 G 3460 KFC295 COMPUTER BEECH 95 95B55 1152729 CE CONT O470 IO470L 17026 SO FLIGHT DIRECTOR MALFUNCTIONED W O OTHER H ELECT. POWER LOSS-50 PC CR CRUISE 1 CA (CAN) PILOT REPORTED THE INABILITY TO CANCEL THE 'FD' FLIGHT DIRECTOR ANNUNCIATOR LIGHT ON THE AUTOPILOT ANNUNCIATOR PAN EL. COMMAND BARS ON ADI WOULD NOT DROP OUT OF VIEW. FLIGHT DIRECTOR COMPUTER REMOVED AND REPAIR. 1 L 7 2 3O 3 O RT 3A16 3E1 2002011600017 20020116 00017 SO 2002 1 16 CA011029001 1 20011014 G 3210 14445 BALL JOINT EMB 110 EMB110P1 3260122 SO PWA PT6 PT6A34 52043 EA TORQUE LINK DAMAGED W O OTHER D INFLIGHT SEPARATION LD LANDING 1 CA (CAN) ON ROLL OUT FOLLOWING LANDING THE BALL JOIINT ASSEMBLEY PULLED OUT OF THE UPPER TORQUE LINK. THIS CAUSED THE RIGHT MAIN WHEEL TO TURN 180 DEGREES. REPAIRS REQUIRED THE REPLACEMENT OF BOTH THE UPPER TORQUE LINK AND THE BALL JOINT ASSEM BLY 1 L 7 2 4T 4 T A21SO E4EA 2002011600018 20020116 00018 CE 2002 1 16 CA011029003 1 20010915 G 5510 26320273 SUPPORT CESSNA CESSNA 208 208 2073702 CE PWA PT6 PT6A114A 52043 NE MCAULY 3AF34C 3GFR34C703 GL HORIZONTAL STAB CORRODED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) DURING AN ANNUAL INSPECTION, WHEN THE HORIZONTAL STABALIZER WAS REMOVED TO CARRY OUT A REPLACEMENT OF A SPAR CAP. CORROSION (PITTING) WAS NOTED IN ONE OF THE FORWARD SUPPORTS AND BOTH OF THE AFT SUPPORTS. NO DAMAGE IS ALLOWED TO CASTI NGS OR FITTINGS. 3 OF THE 4 ATTACH SUPPORTS REQUIRED REPLACEMENT AS PER FACTORY RECOMMENDATION. 1 H 7 1 3T 3 T NT A37CE E4EA 5 C P60GL 2002011600019 20020116 00019 CE 2002 1 16 CA011029005 1 20010915 G 5343 26111379 FITTING CESSNA 208 208 2073702 CE PWA PT6 PT6A114A 52043 NE MCAULY 3AF34C 3GFR34C703 GL MLG CORRODED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) DURING AN ANNUAL INSPECTION PITTING WAS NOTED ON BOTH OF THE FORWARD AND BOTH OF THE AFT LANDING GEAR ATTACH FITT INGS. WHILE ATTEMPTING TO REMOVE THIS CORROSION THE DAMAGE WAS FOUND TO BE TOO SEVERE TO ATTEMPT. THE LANDING GEAR WAS R EMOVED AND MORE CORROSION WAS NOTICED IN THE AREA THAT THE GEAR ATTACHES TO THE FITTING. ALL FOUR MAIN LANDING GEAR FITT INGS WERE REPLACED AS PER VERBAL INSTRUCTIONS FROM FACTORY TECH. REP. 1 H 7 1 3T 3 T NT A37CE E4EA 5 C P60GL 2002011600020 20020116 00020 CE 2002 1 16 CA011029006 1 20010915 G 2731 26612151 ACTUATOR CESSNA 208 208 2073702 CE PWA PT6 PT6A114A 52043 NE MCAULY 3AF34C 3GFR34C703 GL ELEVATOR TRIM CORRODED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) WHILE PERFORMING AN ANNUAL INSPECTION ON THIS CESSNA CARAVAN THE ELEVATOR TRIM JACKS WAS NOTED TO HAVE SIGNIFICANT CORROSION ON SEVERAL OF THE PARTS. THE FOLLOWING PARTS REQUIRED REPLACEMENT HOUSING P/N 2661215-2/BEARINGS P/N 6361620- 6 AND MS27641-66/PINS P/N MS35675-12/ROD ENDS P/N S2629-1. THESE TRIM ACTUATORS HAD BEEN SIGNED AS INSPECTED LESS THAN 1 00 HOURS PRIOR TO THIS FINDING. 1 H 7 1 3T 3 T NT A37CE E4EA 5 C P60GL 2002011600021 20020116 00021 CE 2002 1 16 CA011029007 1 20010915 G 5347 261106014 SEAT TRACK CESSNA 208 208 2073702 CE PWA PT6 PT6A114A 52043 NE MCAULY 3AF34C 3GFR34C703 GL FUSELAGE CORRODED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) WHILE PERFORMING AN ANNUAL INSPECTION THE AREA AT THE AFT END OF NR 2 / 3 / 4 SEAT RAIL UNDER THE FLOOR AT FS 283. 85 WAS NOTED TO HAVE SEVERE CORROSION ON THE STIFFENER P/N 2611131-3 AND THE DOUBLERS P/N 2611192-4 AS WELL AS THE SEAT RAIL. THE CORROSION WAS CLEANED AS REQUIRED FROM THE STRUCTURE AND SEAT RAILS NR 2 AND NR 4. THE STIFFENER, DOUBLERS AND NR 3 SEAT RAIL, AS WELL AS THE ATTACHING HARDWARE WAS REPLACED. 1 H 7 1 3T 3 T NT A37CE E4EA 5 C P60GL 2002011600022 20020116 00022 CE 2002 1 16 CA011029008 1 20010915 G 5550 263440221 HINGE CESSNA 208 208 2073702 CE PWA PT6 PT6A114A 52043 NE MCAULY 3AF34C 3GFR34C703 GL EMPENNAGE CORRODED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) WHILE PERFORMING AN ANNUAL INSPECTION ON THIS AIRCRAFT, EXCESSIVE MOVEMENT WAS NOTED FROM THE OUTBOARD AND CENTRE HINGE BEARINGS FOR THE R/H ELEVATOR. WHEN THE HINGE SUPPORTS WERE DISMANTLED TO REPLACE THE BEARINGS, CORROSION WAS FOUN D ON BOTH HALVES OF THE INBOARD AND CENTRE HINGE SUPPORTS. THE HINGE SUPPORTS AS WELL AS THE BEARINGS WERE REPLACED AS P ER FACTORY RECOMMENDATION. 1 H 7 1 3T 3 T NT A37CE E4EA 5 C P60GL 2002011600023 20020116 00023 CE 2002 1 16 CA011029009 1 20010915 G 5312 2612591 BULKHEAD CESSNA 208 208 2073702 CE PWA PT6 PT6A114A 52043 NE MCAULY 3AF34C 3GFR34C703 GL FUSELAGE CORRODED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) DURING AN ANNUAL INSPECTION ON THIS AIRCRAFT AN AREA OF CORROSION WAS FOUND ON THE AFT CANTED BULKHEAD AT STATION 427.88 AFT LEFT WL 1 OR 2 INCHES OFF CENTRE. THE CORRORION WAS REMOVED AND THE DAMAGE WAS FOUND TO BE THROUGH 50 PERCENT OF THE MATERIAL. THE AFT BULKHEAD WASREPLACED PER THE 208 S.R.M. 1 H 7 1 3T 3 T NT A37CE E4EA 5 C P60GL 2002011600024 20020116 00024 CE 2002 1 16 CA011029010 1 20010915 G 5511 26320233 SPAR CAP CESSNA 208 208 2073702 CE PWA PT6 PT6A114A 52043 NE MCAULY 3AF34C 3GFR34C703 GL HORIZONTAL STAB CORRODED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) DURING AN ANNUAL INSPECTION OF THIS AIRCRAFT, SEVERE CORROSION WAS NOTED ON THE AFT UPPER TRAILING EDGE SPAR CAP O N THE HORIZONTAL STABILIZER AT APPROXIMATELY SS 80.60 LEFT HAND AND ARIGHT HAND SIDES. THE CORROSION HAS GONE THROUGH TH E SPAR CAP BUT HAD NOT YET DAMAGED THE WEB. THIS CORROSION WAS NOT INITIALLY NOTICED DUE TO THE FACT THE CORROSION HAD B EEN PAINTED OVER THE ENTIRE SPAR CAP WAS REPLACED. 1 H 7 1 3T 3 T NT A37CE E4EA 5 C P60GL 2002011600025 20020116 00025 EU 2002 1 16 CA011029011 1 20011015 G 6520 770441 CARBON SEAL SNIAS 350 AS350B 8680801 EU TMECA ARRIEL ARRIEL1B 6OO30 NE TAIL ROTOR GB CRACKED W E ENGINE SHUTDOWN K FLUID LOSS TX TAXI/GRND HDL 1 CA (CAN) DURING A GROUND RUN ON OIL LEAK WAS DETECTED FROM THE TAIL ROTOR GEAR BOX. AIRCRAFT WAS SHUT DOWN LEAK INVESTIGATE D. OIL LEAK FROM INPUT MAG SEAL. SEAL AND HOUSING REMOVED. THE STATIONARY PORTION OF SEAL FOUND TO HAVE MULTIPLE CRACKS. MAG SEAL WAS PREVIOUSLY REMOVED DUE TO SMALL LEAK. SEAL WAS "RE-SEATED" AND REINSTALLED. POSSIBLE CAUSE WAS INCORRECT I NSTALLATION OF SEAL.A NEW CARBON MAG SEAL WAS INSTALLED. AIRCRAFT WAS GROUND RUN AND NO FURTHER LEAK PRESENT. 1 G 7 1 3U 3 U H9EU E19EU 2002011600026 20020116 00026 CE 2002 1 16 CA011029012 1 20010802 G 5550 07321008 HINGE CESSNA 07326004 CESSNA 180 180J 2072622 CE CONT O470 O470S 17026 SO HORIZONTAL STAB CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) DURING 100 HOUR INSPECTION FOUND LT OUTBOARD ELEVATOR BEARING LOOSE. REMOVED LT ELEVATOR TO CHANGE BEARING. WITH E LEVATOR REMOVED, FOUND LT OUTBOARD HINGE ASSEMBLY TO BE CORRODED AND CRACKED WHERE BEARING IS INSTALLED. 1 H 7 1 3O 3 O 5A6 E273 2002011600027 20020116 00027 EA 2002 1 16 CA011029013 1 20011012 G 2560 RING 4494701 DHAV DHC2 DHC2MK1 2800102 EA PWA R985 R985AN14B 52008 NE SEAT BELT CORRODED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) CORROSION LOCATED UNDER THE ('D' RING) WHERE SEAT BELT WEBBING CONTACTS ALUMINIUM D-RING. 1 H 7 1 3R 3 R A806 5E1 2002011600028 20020116 00028 NE 2002 1 16 CA011029014 2 20011009 G 8520 128511 CONNECTING ROD DHAV DHC2 DHC2MK1 2800102 EA PWA R985 R985AN14B 52008 NE HARTZL HCB3R HCB3R304 GL ENGINE BROKEN W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) WHILE IN CRUISE AT 2,000 FEET A LOUD REPORT WAS HEARD FROM THE ENGINE. FOLLOWED WAS EXTREME ENGINE VIBRATION. POWE R WAS REDUCED TO IDLE. THE AIRCRAFT WAS LANDED. UPON INVESTIGATION IT WAS DETERMINED THAT NR 5 AND NR 1 CONNECTING RODS WERE BROKEN. ENGINE CHANGED. 1 H 7 1 3R 3 R A806 5E1 5 C P28EA 2002011600029 20020116 00029 NE 2002 1 16 CA011029015 2 20011003 G 8530 CYLINDER HEAD DHAV DHC2 DHC2MK1 2800102 EA PWA R985 R985AN1 52008 NE ENGINE CRACKED W A UNSCHED LANDING R E PARTIAL RPM/PWR LOSS VIBRATION/BUFFET CR CRUISE 1 CA (CAN) CYLINDER HEAD CRACKED. 1 H 7 1 3R 3 R A806 5E1 2002011600030 20020116 00030 EU 2002 1 16 CA011029016 1 20011005 G 5302 350A23002021 SKIN SNIAS 350 AS350BA 8680817 EU TMECA ARRIEL ARRIEL1B 6OO30 NE TAILBOOM CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) A 6 INCH LONG CRACK FOUND ON TAILBOOM FWD UPPER SKIN UNDER N5 BEARING MOUNT SUPPORT AT BOOM STA A868. TAILBOOM INS T IN EUROCOPTER APPRD AS350/355 TAILBOM REPAIR FIXTURE FOR REPL OF UPPER SKIN&FOUND N5SUPPORT HAD BADLY MISALIGN TO FIXT URE: N5 BEARING MOUNT SUPPORT HAD BEEN PREV REPL IN FIELD BY OPERATOR PER EUROCOPTER AS350 REPAIR MANUAL CHAPT 53.10.40. 773.A 2ND TAILBOOMN FOUND WITH SIMILAR DEFECT, ALSO N 5 BEARING MOUNT SUPPORT HAD BADLY MISALIGN TO FIXTURE: N5 BEARING MOUNT SUPPORT HAD BEEN PREV REPL IN FIELD.WE FEEL THAT MAIN REASON SKIN CRACKED MISALIGNMENT OF #5 BEARING MOUNT WHICH R EPL IN FIELD W/O USE OF FIXTURE: 1 G 7 1 3U 3 U NC H9EU E19EU 2002011600031 20020116 00031 EU 2002 1 16 CA011029017 1 20011025 G 6520 350A33105803 LEVER SNIAS 350 AS350B 8680801 EU TMECA ARRIEL ARRIEL1B 6OO30 NE TAIL ROTOR CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) THE TAIL ROTOR CONTROL LEVER MAYBE THE SAME AIRFRAME TIME BUT WE ARE NOT 100 PERCENT SURE. THE TAILROTOR CONTROL L EVER HAD A DEFECT OF WEAR ON INSIDE EAR. UPON REMOVAL MAINTENANCE ENGINEER FOUND CRACKS IN THE WEBBING, TOP SIDE AT T/R SPIDER ATTACHMENT POINT. 1 G 7 1 3U 3 U H9EU E19EU 2002011600034 20020116 00034 EU 2002 1 16 CA011029020 1 20010514 G 6410 355A12004008 SKIN SNIAS 350 AS350BA 8680817 EU TMECA ARRIEL ARRIEL1B 6OO30 NE T/R BLADE CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) 131 MM CRACK ORIGINATING FROM THE RIVET HOLE FOR THE TRAILING EDGE TAB ON BOTH THE UPPER AND LOWER SURFACE.SDR NO. 20010112018 AND 2019 ADDRESSES THIS SAME DEFECT.SINCE DISCOVERY OF THIS DEFECT EUROCOPTER FRANCE HAS ISSUED INFO TELEX 00000035 REQUIRING A BEFORE FLIGHT/BETWEEN FLIGHT /AFTER FLIGHT AN 500 HOUR/24 MONTH INSPECTION OF THIS AREA FOR CRACKIN G. 1 G 7 1 3U 3 U NC H9EU E19EU 2002011600035 20020116 00035 SO 2002 1 16 CA011030001 1 20011004 G 5713 6208603 STRINGER PIPER PA28 PA28140 7102802 SO LYC O320 O320E3D 41508 EA WING BROKEN W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) FLANGES AT END OF STRINGER ARE CRACKING. EVENTUALLY THE ENTIRE END OF STRINGER WILL SEPARATE. EACH WING HAS TWO ST RINGERS ON INBOARD BOTTOM SKIN. BOTH ARE BROKEN ON THE RIGHT WING. LEFT WING IS OKAY. IT IS VERY DIFFICULT TO INSPECT TH IS AREA ON NEWER PA28'S. IT IS TOTALLY IMPOSSIBLE ON OLDER PA28'S DUE TO LACK OF INSPECTION PANEL.I HAVE SEEN THIS BEFOR E, ABOUT TWO YEARS AGO. BUT, IT WAS ON A PA34-200 TWIN. IT LOOKED LIKE AN ONE TIME EVENT, PECULIAR TO THAT AIRCRAFT. NOW I SEE IT AGAIN ON A SIMILAR WING BUT, IT HAS CROSSED MODEL LINES.#11 PART AVAILABLE. "NO", BUT PICTURES WERE TAKEN WITH A DIGITAL CAMERA. THEY ARE IN MY COMPUTER AND CAN BE E-MAILED IF YOU WISH. 1 L 7 1 3O 3 O 2A13 E274 2002011600036 20020116 00036 EA 2002 1 16 CA011030002 1 20011016 G 5311 C6FSM142236 FRAME DHAV DHC6 DHC6300 2802606 EA PWA PT6 PT6A27 52043 EA FUSELAGE CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) CRACK FOUND IN SIDE FRAME AT RT. STATION 218.125 RUNNING ON AN ANGLE FROM TOP OF FRAME. NOTE PART IS POST MOD 6/14 62 AS DIRECTED BY CF-78-17R1. DHC SB 6/371 REV.B.PLEASE SEE PHOTOS. 1 H 7 2 3T 4 T RT A9EA E4EA 2002011600037 20020116 00037 SO 2002 1 16 CA011030003 1 20011015 G 2912 AN62341 FILTER HOUSING PIPER PA31 PA31350 7103110 SO LYC O540 TIO540J2BD 41532 EA RT ENG FIRE WALL CRACKED W O OTHER K FLUID LOSS DE DESCENT 1 CA (CAN) THE PILOT REPORTED THAT THE LANDING GEAR WOULD NOT EXTEND WHEN SELECTED DOWN. THE EMERGENCY HAND PUMP SUCCESSFULLY EXTENDED THE GEAR TO INDICATE 3 GREEN. LOW HYDRAULIC FLUID LEVEL WAS FOUND TO BE THE CAUSE OF THE PROBLEM DUE TO A CRAC K IN THE THREADS OF THE RT HYDRAULIC FILTER BOWL. THE CRACK IS MOST LIKELY CAUSED BY OVER TIGHTENING THE BOWL, ALTHOUGH IT HAD BEEN IN PLACE 32.5 HOURS BEFORE THE GEAR PROBELM OCCURRED. 1 L 7 2 3O 3 O A20SO E14EA 2002011600038 20020116 00038 SO 2002 1 16 CA011030004 1 20011015 G 2140 A07D32 SWITCH JANITROL B4050 PIPER PA31 PA31350 7103110 SO LYC O540 TIO540J2BD 41532 EA HEATER OVERHEATED W F A ACTIVATE FIRE EXT. UNSCHED LANDING B I SMOKE/FUMES/ODORS/SPARKS FLT. ATTITUDE INST. CR CRUISE 1 CA 4B11145 (CAN) THE AIRCRAFT WAS IN LEVEL FLIGHT. THE AFT HEATER WAS BROUGHT ON LINE. A SHORT TIME LATER, THE PASSENGERS NOTED SMO KE AND SPARK'S COMING FROM THE OUTLET. THE HEATER WAS SHUT DOWN AND THE CABIN FIRE EXTINGUISHER WAS DISCHARGED INTO THE INLET. THE AIRCRAFT LANDED AND MAINTENANCE DISCOVERED THE CYCLE SWITCH HAD MALFUNCTION. 1 L 7 2 3O 3 O A20SO E14EA 2002011600039 20020116 00039 CE 2002 1 16 CA011030005 1 20011009 G 5743 082210045 BRACKET CESSNA CESSNA 401 401B 207590E CE CONT O520 TSIO520EB 17040 SO MLG CRACKED W A UNSCHED LANDING D INFLIGHT SEPARATION CL CLIMB 1 CA (CAN) DURING RETRACTION OF GEAR AFTER TAKEOFF PILOT HEARD A BANG. UPON LANDING AT BASE THE AIRCRAFT WAS INSPECTED AND TH E RT FORWARD GEAR DOOR HINGE BRACKET WAS FOUND TO BE CRACKED. 1 L 7 2 3O 3 O A7CE E8CE 2002011600041 20020116 00041 GL 2002 1 16 CA011030007 2 20011009 G 7250 A23037403 SHAFT ALLSN 250C 250C20B 03013 GL ENGINE FAILED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) THIS TURBINE WAS RECD FOR ROUTINE SCHED MAINT. THERE WAS NO SERVICE COMPLAINT. ON DISASSY, TURBINE PT ROTOR NUT FO UND UNTHREADED FROM PT INNER SHAFT. SCORING EVIDENCE ON THE PT INNER SHAFT INDICATES NUT UNTHREADED DURING OP. NUT HAD B EEN STAKED AT 2 PLACES DURING ASSY. LOCKING DIMPLES ON PMA PT INNER SHAFT APPEAR UNDERSIZED WHICH PREVENTS PROPER LOCKI NG OF NUT ASSY. WHEN NUT UNTHREADED, CLAMPING LOAD BETWEEN NR 3 & NR 4 TURBINE WHEELS WAS COMPROMISED. AS A ARESULT, CUR VIC COUPLES ON TURBINE WHEELS SHOW EVIDENCE OF MOVEMENT & FRETTING. TIME ON TURBINE IS AS FOLLOWS:TSN: 10494.0 HRS, TSO: 3476.2 HRS NOTE: PT INNER SHAFT IS A PMA PART. 3 U E4CE 2002011600042 20020116 00042 EU 2002 1 16 CA011031001 1 20011030 G 3397 WIRE PILATS PC12 PC1245 7090551 EU PWA PT6 PT6A67B 52043 NE HARTZL HCE4A HCE4A3D GL LT WING STROBE CHAFED W H DEACTIVATE SYST/CIRCUITS H ELECT. POWER LOSS-50 PC CR CRUISE 1 CA (CAN) DURING CRUISE, THE STROBE LIGHT CIRCUIT BREAKER POPPED. THE CIRCUIT BREAKER WAS NOT RESET IN FLIGHT. INVESTIGATIO N REVEALED A CHAFED WIRE (P/N L08E20) IN THE LEFT HAND WING. THE WIRE WAS REPAIRED AND THE AIRCRAFT RETURNED TO SERVICE . 1 L 7 1 3T 4 T RT A78EU E26NE 5 C P210NE 2002011600045 20020116 00045 EU 2002 1 16 CA011031005 2 20011019 G 8520 861115 DIAPHRAGM DIAMON DA20 DA20A1 2990000 GL ROTAX 912 ROTAX912 55555 EU CYLINDER SWOLLEN W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) DURING 200 HR INSP OIL FOUND BETWEEN NR 1 & 3 CYLINDERS. COMPRESSION CHECK CARRIED OUT TO DETERMINE CYLINDER THAT PRODUCING OIL. BOTH CYLINDERS PRODUCED NORMAL COMPRESSION READINGS. WHEN BOTTOM SPARK PLUGS WERE REMVD ONE FROM CYLINDER NR 3 FOUND TO HAVE EVIDENCE ON BURNED OIL. NR 3 CYLINDER ASSY & PISTON REMVD. PISTON HEAD COVERED IN BURNED OIL RESIDUE . PISTON HEAD HAD ALSO HAD SMALL PORTIONS OF ITS SURFACE CHIPPED AWAY. DURING THE PREVIOUS INSP (50 HR) NR 1 CYLINDER AS SY & PISTON WERE REPL. IT BELIEVED THAT FAILURE OF NR 1 PISTON RESULTED FROM FAILURE OF PISTON RING. 1 L 7 1 3O 3 I NT TA4CH EXPE3I 2002011600065 20020116 00065 SW 2002 1 16 CA011031012 1 20011018 G 2750 12395 PULLEY BBAVIA 8 8GCBC 1220803 SW LYC O360 O360C2E 41514 EA FLAP SYSTEM WORN W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) - LT & RT PULLEYS INBOARD & OUTBOARD ALL FOUND WORN.- LT & RT CABLES FRAYED UNSERVICEABLE AND REPLACED. - CABLES F RAYED AT PULLEYS ON OUTBOARD POSITION.- SOLID ALUMINUM PULLEYS WITH SMALL RADIUS AND SEIZE EASILY CAUSING EXCESSIVE CABL E WEAR. 1 H 7 1 3O 3 O A21CE E286 2002011600066 20020116 00066 SO 2002 1 16 CA011031013 1 20011004 G 3213 4033600 LINK PIPER PA31T PA31T 7103124 SO PWA PT6 PT6A28 EA NLG DRAG BRACE CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) UPON INSPECTION, A CRACK WAS FOUND AT NOSE GEAR LINK ATTACH POINT. 1 L 7 2 3T 4 T A8EA E4EA 2002011600067 20020116 00067 SO 2002 1 16 CA011031014 1 20011006 G 7120 4000707 MOUNT PIPER PA31 PA31 7103102 SO LYC O540 TIO540A2C 41532 EA HARTZL HCE3Y HCE3YR2A GL LT & RT ENGINE WORN W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) DURING INSPECTION OF THE ENGINE MOUNT FOUND CUT MARKS ON LOWER TRUSS MEMBERS OF THE MOUNT. AFTER SOME INVESTIGATIO N FOUND THAT THE CUTS WERE MADE BY COWL FLAPS OF RESPECTIVE ENGINES. NO EVIDENCE OF COWL FLAP MISRIGGING OR DAMAGE ON CO WL FLAPS. THE WEAR MARKS FOUND WERE ABOUT 1/2 THE WALL THICKNESS OF TUBES. TUBES WERE REPAIRED IAW AC43-13 AND AIRCRAFT RETURNED TO SERVICE. 1 L 7 2 3O 3 O A20SO E14EA 5 C P33EA 2002011600082 20020116 00082 SO 2002 1 16 CA011031015 1 20011006 G 5414 4166300 SKIN PIPER PA31 PA31 7103102 SO LYC O540 TIO540A2C 41532 EA HARTZL HCE3Y HCE3YR2A GL ENG NACELLES CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) DURING INSPECTION NOTICED SMOKING & LOOSE RIVETS AROUND INBOARD SIDE OF LT AND RT ENGINE NACELLE JUST AFT OF FIREW ALL. REMOVED LOWER ACCESS PANEL AND FOUND THAT BOTH LT & RT INBOARD NACELLE PLATES P/N 41663-00 (LT) AND 41663-01 (RT) W ERE CRACKED FROM L/E OF PLATE TO AFT END. THIS PLATE CREATE A WRAP AROUND L/E SKIN AND ATTACHES NACELLE STRUCTURE TO SKI N. PART REQUIRED TO BE REPLACED SINCE THERE IS NOT MUCH ROOM TO BE REPAIRED. 1 L 7 2 3O 3 O A20SO E14EA 5 C P33EA 2002011600085 20020116 00085 CE 2002 1 16 CA011031016 1 20011011 G 2823 1013890255 SHUTOFF VALVE BEECH 90 C90A 1152911 CE PWA PT6 PT6A21 52043 EA BOOST PUMP STUCK W D RETURN TO BLOCK L NO TEST TX TAXI/GRND HDL 1 CA (CAN) PILOT CLOSED THE VALVE, BOOST PUMP ON, LOW FUEL PRESSURE LIGHT WENT OFF, MEANING THE FUEL IS LEAKING BY THE VALVE. 1 L 7 2 3T 4 T RT 3A20 E4EA 2002011600086 20020116 00086 GL 2002 1 16 CA011031017 1 20011005 G 6520 28135255R GEARBOX ENSTRM F28 280 3300502 GL LYC O360 HIO360C1A 41514 EA TAIL ROTOR DAMAGED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) DURING ROUTINE 100 HOUR INSPECTION OIL DRAINED FROM T/R GEARBOX, FOUND EXCESSIVE SLUG & METAL PARTICLES ON CHIP DR AIN PLUG. FLUSHED GEARBOX. ADDED FRESH OIL. DISCONNECT INPUT SHAFT & ROTATED INPUT GEAR WITH T/R ATTACHED TO OUTPUT SIDE . NOISE NOTED FROM INPUT SIDE OF GEAR. ASSEMBLY REMOVED FROM SERVICE AND RETURNED TO ENSTROM FOR WARRANTY AND EVALUATION . REPORT OF FINDINGS REQUESTED. 1 G 7 1 3O 3 O H1CE 1E10 2002011600087 20020116 00087 CE 2002 1 16 CA011031018 1 20010928 G 2842 TRANSMITTER CESSNA 206 U206G 2073356 CE CONT O520 IO520F 17032 SO MCAULY D3A34 D3A34C404 GL FUEL INDICATOR CORRODED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) BOTH LT AND RT SENDING UNITS FOUND SEVERELY CORRODED WITH CORROSION DEBRIS IN TANKS. ALUMINUM 3/8 INCH FUEL LINES FROM TANKS TO TRANSFER PUMPS WRE ALSO FOUND CORRODED. 1 H 7 1 3O 3 O A4CE E5CE 5 C P47GL 2002011600088 20020116 00088 CE 2002 1 16 CA011031019 1 20010928 G 5751 122008516 SKIN CESSNA 206 U206G 2073356 CE CONT O520 IO520F 17032 SO MCAULY D3A34 D3A34C404 GL LT AILERON CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) 7 OUT OF 11 SCREW HOLES FOR MOUNTING BALANCE WEIGHT FOUND CRACKED. LT AILERON INSPECTED AND ONE CRACK FOUND. 1 H 7 1 3O 3 O A4CE E5CE 5 C P47GL 2002011600089 20020116 00089 NE 2002 1 16 CA011031021 1 20011031 G 5551 ATTACH FITTING CONAER LA4 LA4200 5110310 NE LYC O360 IO360A1B 41514 EA HORIZONTAL STAB MISMANUFACTURED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) AD 98-10-12, HORIZONTAL STAB ATTACHMENT FITTING NO OF NEW CUSTOMERS A/C HAVE BEEN INSPECTED AT COMPANY & ARE NOT I N COMPLIANCE WITH AD, ALTHOUGH ITS BEEN PREVIOUSLY SIGNED OFF. MOST INSPECTIONS REVEAL THAT CLEARANCE I S LESS THAN THE REQUIRED 5/32 INCH. OTHER A/C HAVE HAD FITTING RADIUS REWORKED INSTEAD OF DOUBLER FLANGE.COMPLIANCE IS ALSO BEING ACCOM PLISHED W/O REMOVAL OF STAB FOR FITTING INSP, AS EVIDENT IN REWORK WHICH I S CAUSING GOUGING & MORE DAMAGE TO SPAR DOUBL ER&FITTING RADIUS. VISUAL & L. P. INSPECTIONS ARE ALSO NOT COMPLETED ON FITTING RADIUS TO DOUBLER MATING SURFACES. MANY A/C ARE STILL CONSIDERED AIRWORTHY & ARE NOT IN COMPLIANCE. 1 H 7 1 3O 3 O 1A13 1E10 2002011600090 20020116 00090 SO 2002 1 16 CA011031024 1 20011005 G 3020 86245834 HEATER PIPER PA44 PA44180 7104402 SO LYC O360 O360A1H 41514 EA CARBURETOR BROKEN W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) DURING A ROUTINE ENGINE INSPECTION OF THE LT ENGINE, THE CARB AIR BOX WAS FOUND BROKEN AT THE HEATED AIR INTAKE PI PE. THE COMPLETE CIRCUMFERENCE OF THE WELD ON THE RT END OF THE BOX HAD BROKEN. THE ONLY REASON THE PART STAYED WITH THE AIRCRAFT WAS THE CLAMP ON THE HOSE CONNECTING IT TO THE HEAT INTAKE SHROUD. THE PART WAS REMOVED FOR REPAIR. A SECOND A IRCRAFT WAS FOUND TO HAVE THE SAME PROBLEM. THE PILOT'S WHO FLY THE AIRCRAFT WERE INFORMED THAT IF THEY DO NOT GET A DRO P IN RPM WHEN SELECTING CARB HEAT DURING THEIR RUN-UP NOTIFY MAINTENANCE AND A CHECK OF THE CARB HEAT SYSTEM WILL BE CAR RIED OUT. 1 L 7 2 3O 3 O A19S0 E286 2002011600091 20020116 00091 EU 2002 1 16 CA011031025 1 20011005 G 7120 L24263100000 MOUNT ZLIN 242 Z242L 9970204 EU LYC O360 AEIO360A1B6 41514 EA RT ENGINE CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) DURING A 100 HOUR INSPECTION A CRACK WAS FOUND ON THE UPPER RT MOUNT WEB. THE MOUNT WAS REMOVED FOR FURTHER INSPEC TION AND IT WAS NOTICED THAT THE CRACK WAS ABOUT 1 INCH IN LENGTH. MAINTENANCE HAS BEEN INSTRUCTED TO PAY SPECIAL ATTENT ION TO THIS AREA DURING 50 AND 100 HOUR INSPECTIONS FOR ANY SIGN OF STRESS OR TINY CRACKS.NOTE: ILLUSTRATION ATTACHED. 1 L 7 1 3O 3 O 0 A76EU 1E10 2002011600092 20020116 00092 SW 2002 1 16 CA011031026 1 20010928 G 5302 205032821023 BULKHEAD BELL 212 212 1181420 SW PWA PT6T PT6T3 52045 EA TAILBOOM CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) DURING A SCHEDULED MAINTENANCE INSPECTION THE CRACK WAS DISCOVERED. HEADQUARTERS HAS RECEIVED THE PARTICULARS AND IS PREPARING A REPAIR SCHEME. 1 G 7 1 4U 4 U H4SW E22EA 2002011600093 20020116 00093 CE 2002 1 16 CA011031027 1 20011031 G 3246 16218000 WHEEL BEECH 99 99 1154002 CE PWA PT6 PT6A28 EA MLG CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) WHEEL HALF WAS REMOVED DUE TO CUTS IN THE RUBBER. UNIT DISASSENBLED AND DYE PEN INSPECTED. CRACK INDICATIONS WER E FOUND ON THE INSIDE OF THE OUTER WHEEL HALF. UNIT SCRAPPED OUT PART TIME AND CYCLES ARE UNKNOWN. 1 L 7 2 3T 4 T A14CE E4EA 2002011600127 20020116 00127 EA 2002 1 16 CA011101011 1 20011015 G 5410 601350061 WEB CNDAIR CL600 CL6002B19 1900309 EA GE CF34 CF343B1 NE SUPPORT BEAM CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) TWO CRACKS FOUND ON ENGINE SUPPORT BEAM AT THE LOWER WEB FS 630, LBL 36, RBL 36 WHILE PERFORMING SB A601R-53-059. AREA TO BE REPAIRED IAW REO 601R-53-61-361. 2 L 7 2 4F 4 F RT A21EA E15NE 2002011600128 20020116 00128 CE 2002 1 16 CA011101012 1 20011031 G 3260 903610373 DOWNLOCK SWITCH BEECH 90 C90A 1152911 CE PWA PT6 PT6A21 52043 EA MLG FAILED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) HIGH RESISTANCE (2.9 OHM) ENCOUNTERED ON CONTACTS AT CONNECTOR A210 PI PINS D TO E WHILE DOING PHASE 1 INSPECTION DUES ITEM CAMP CARD 321171 (CONTINUITY CHECK R/H DOWNLOCK MICRO SW) MICRO SW REPLACED AND RETRACTION TEST CARRIED OUT. 1 L 7 2 3T 4 T RT 3A20 E4EA 2002011700001 20020117 00001 SO 2002 1 17 CA011102002 1 20011018 G 5553 9556300 SPAR PIPER PA34 PA34200 7103405 SO LYC O360 IO360C1E6 41514 EA VERICAL STAB FAILED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) FAILURE OF RIVETS SECURING LOWER 4 INCHES OF SPAR FLANGES TO FITTING P/N 63501-00. FOUR RIVETS HAD FAILED ON LT SI DE AND ONE RIVET FAILED ON RT SIDE. 1 L 7 2 3O 3 O A7SO 1E10 2002011700002 20020117 00002 EU 2002 1 17 CA011102003 1 20011017 G 6220 350A37124520 SCREW AEROSP 355A31000109 SNIAS 350 AS350BA 8680817 EU TMECA ARRIEL ARRIEL1B 6OO30 NE STARFLEX BROKEN W K NONE O OTHER IN INSP/MAINT 1 CA M1429 (CAN) DURING REPLACEMENT OF STARFLEX, DISCOVERY OF ONE OF TWELVE BOLT FOUND BROKEN. PRESENCE OF RUST ON THE BROKEN SECTI ON, SHOWS THAT THE DEFECT OCCURRED A LONG PERIOD BEFORE DISCOVERY.BECAUSE OFTHE DESIGN OF THE HEAD, THERE WAS NO POSSIBL E WAY TO LOSE ANY PART. NOTE THAT RETIREMENT OF STARFLEX AND BROKEN SCREW IS 2200 HOURS.ATTACHMENT SCREW P/N 350A37-1245 -20, S/N 28998 1 G 7 1 3U 3 U NC H9EU E19EU 2002011700003 20020117 00003 WP 2002 1 17 CA011102005 1 20010815 G 7921 C1861 HUB ROBSIN R44 R44 7640120 WP LYC O540 O540F1B5 41532 EA COOLER FAN CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) PART C186-1 FOUND CRACKED WHILE REPLACING MICROSWITCH V3-1001. THE FAN WAS REMOVED AND THE HUB WAS FOUND CRACKED. THE FAN SHAFT ASSEMBLY C007-5 WAS CORRODED. THE FAN TORQUE WAS FOUND ACCEPTABLE (450-550 FT LBS).\PIECE C186-1 WAS REPLA CED AND THE FAN SHAFT C007-5 WAS RETURNED TO ROBINSON FOR OVERHAUL. THE SECOND PROBLEM WAS REPORTED ON 3 OTHER HELICOPTE RS IN THE LAST 2/3 YEARS. THE THIRD ONE WAS FOUND CRACK FREE BUT CORRODED. 1 G 7 1 3O 3 O H11NM E295 2002011700004 20020117 00004 EA 2002 1 17 CA011102006 2 20010506 G 8530 SPRING CESSNA 182 R182 2072734 CE LYC O540 O540J3C5 41532 EA MCAULY 2D34C B2D34C218 GL INTAKE VALVE BROKEN W A UNSCHED LANDING E R J VIBRATION/BUFFET PARTIAL RPM/PWR LOSS WARNING INDICATION CR CRUISE 1 CA (CAN) ENGINE VIBRATION WHILE IN FLIGHT. AFTER INSPECTION, THE NR 2 ENGINE CYLINDER WAS FOUND WITHOUT COMPRESSION. THE AD MISSION VALVE WAS FOUND INOPERATIVE. A NEW CYLINDER WAS INSTALLED AND SUCCESSFUL ENGINE TESTS WERE CARRIED OUT. THE CYLI NDER WAS SENT TO A REPAIR SHOP FOR INSPECTION AND REPAIR (INTAKE VALVE SPRING BROKEN). 1 H 7 1 3O 3 O RT 3A13 E295 5 C P7EA 2002011700005 20020117 00005 CE 2002 1 17 CA011102007 1 20010731 G 2720 031019613 SPRING CESSNA 150 150M 2071830 CE CONT O200 O200A 17020 SO RUDDER CONTROL BROKEN W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) DURING A PRE-FLIGHT INSPECTION, THE PILOT SAW THE RUDDER TURNED WHILE THE FRONT WHEEL WAS STRAIGHT AND THE PEDALS WERE OFF-CENTERED. AN INSPECTION DETERMINED THE RIGHT SPRING WAS MISSING AND FOUND BELOW IN THE FUSELAGE. 1 H 7 1 3O 3 O 3A19 E252 2002011700006 20020117 00006 EA 2002 1 17 CA011102008 2 20010802 G 8510 LW14675 CRANKCASE CESSNA 182 R182 2072734 CE LYC O540 O540J3C5 41532 EA MCAULY 2D34C B2D34C214 GL ENGINE CRACKED W B A EMER. DESCENT UNSCHED LANDING R J PARTIAL RPM/PWR LOSS WARNING INDICATION CR CRUISE 1 CA (CAN) THE PILOT NOTICED AFTER AN HOUR OF FLIGHT THAT THE OIL PRESSURE WAS DROPPING. HE PERFORMED A PRECAUTIONARY LANDING ON THE ROAD WITHOUT ANY PROBLEM. AFTER INSPECTION OF THE ENGINE, A CRACK WAS FOUND ON THE ENGINE BLOCK BETWEEN NR 1 AND 3 CYLINDERS. THE ENGINE WAS REMOVED AND SENT TO A REPAIR SHOP. 1 H 7 1 3O 3 O RT 3A13 E295 5 C P7EA 2002020800006 20020208 00006 CE 2002 2 8 CA011102009 1 20011031 G 2720 031019613 SPRING CESSNA 150 152 2071835 CE LYC O235 O235L2C 41505 EA RUDDER BROKEN W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) THIS IS SECOND OCCURANCE OF SAME DEFECT IN 1205 HRS/18 MONTHS. HAS ALSO OCCURED ON OTHER 152 IN OUR FLEET. OBSER VED DURING WALK-AROUND BY NEXT PILOT (RUDDER SWINGS FREELY WITHOUT NORMAL RESISTENCE). OUR AMO SAYS THAT BROKEN SPRING C OULD INTERFERE WITH FLIGHT CONTROLS DURING FLIGHT. 1 H 7 1 3O 3 O NT 3A19 E223 2002011700007 20020117 00007 CE 2002 1 17 CA011105001 1 20011031 G 7810 265400610 FLANGE CESSNA 208 208B 2073701 CE PWA PT6 PT6A114A 52043 NE MCAULY 3AF34C 3GFR34C703 GL EXHAUST SYSTEM CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) THE EXHAUST FLANGE WAS FOUND CRACKED AT THE FORWARD RADIUS IN 3 SPOTS. THERE IS A HOLE IN THE FLANGE THAT LINES UP WITH THE THREADS OF A BOLT FROM THE OIL COOLER. THIS HOLE DID NOT LINE UP WITH THE BOLT AND PRODUCED STRESS ON THE FLAN GE RESULTING IN THE CRACKS. THE FLANGE WAS REPLACED AND THE BOLT FROM THE OIL COOLER WAS SHORTENED SO IT DOES NOT INTERF ERE WITH THE FLANGE. 1 H 7 1 3T 3 T A37CE E4EA 5 C P60GL 2002011700008 20020117 00008 SW 2002 1 17 CA011105002 1 20010925 G 6320 206040526001 TUBE BELL 206040004101 BELL 206 206L 1181522 SW ALLSN 25OC 250C20R GL TRANSMISSION CORRODED W K NONE O OTHER IN INSP/MAINT 1 CA BMC45132 (CAN) DURING TRANSMISSION 1500 HOUR INSPECTION CORROSION AND PITTING FOUND ON THE FLARE OF THE TUBE ASSEMBLY. 1 G 7 1 3U 3 U H2SW E4CE 2002011700009 20020117 00009 SW 2002 1 17 CA011105003 1 20010921 G 2910 70012J220W234 LINE BELL 212 212 1181420 SW PWA PT6T PT6T3 52045 EA HYD SYSTEM LEAKING W D RETURN TO BLOCK K FLUID LOSS TX TAXI/GRND HDL 1 CA (CAN) DURING RUN UP THE SUBJECT LINE STARTED LEAKING, THIS WAS REPORTED BY PASSENGERS IN AIRCRAFT WHO NOTICED HYDRULIC F LUID LEAKING INTO CABIN FROM OVERHEAD.AIRCRAFT WAS SHUT DOWN AND THE AME LOCATED THE LEAKING LINE ON NR 2 HYDRAULIC SYST EM. THIS LINE WAS LAST PRESSURE TESTED 10/98. NEW LINE WILL BE INSTALLED PRIOR TO AIRCRAFT RETURN TO SERVICE. 1 G 7 1 4U 4 U H4SW E22EA 2002011700010 20020117 00010 CE 2002 1 17 CA011105004 1 20011104 G 2752 99105863RX ACTUATOR CESSNA 208 208B 2073701 CE PWA PT6 PT6A114A 52043 NE TE FLAPS STUCK W A UNSCHED LANDING F FLT CONT AFFECTED DE DESCENT 1 CA (CAN) PILOT REPORTED IN FLIGHT FAILURE OF FLAP SYSTEM LOCKED IN ONE POSITION. RETURNED TO MAINTENANCE BASE AND REPLACED FLAP ACTUATOR. AIRCRAFT RETURNED TO SERVICE. 1 H 7 1 3T 3 T A37CE E4EA 2002011700011 20020117 00011 NE 2002 1 17 CA011105005 2 20010526 G 7261 LABYRINTH SEAL SKRSKY S76 S76A 8143006 NE TMECA ARRIEL ARRIEL1S 60030 NE ENGINE FAILED W E ENGINE SHUTDOWN B J SMOKE/FUMES/ODORS/SPARKS WARNING INDICATION TX TAXI/GRND HDL 1 CA (CAN) TEARDOWN REPORTS - SEVERE FAILURE OF LABYRINTH SEAL. SMALL DIAMETER ROTATING LABYRINTH SEAL ALMOST COMPLETELY DISI NTEGRATED. SMALL PIECES RECOVERED. OUTER TWO ROTAING SEALS SEPERATED FROM LABYRINTH SHAFT. ACRO AEROSPACE W/O 21-8077PAR TS SHIPPED TO TURBOMECA FRANCE FOR ANALYSIS. 1 G 7 2 3U 3 U H1NE E19EU 2002011700012 20020117 00012 SO 2002 1 17 CA011105006 2 20011001 G 7321 632558 LINK ROD CONT IO470VO CESSNA 310 310Q 2074242 CE CONT O470 IO470VO 17026 SO MCAULY 3AF32C 3AF32C87 GL FCU DISCONNECTED W O OTHER E J VIBRATION/BUFFET WARNING INDICATION AP APPROACH 1 CA 170718R (CAN) ON APPROACH PILOT NOTICED ROUGHNESS FROM LEFT ENGINE AND UPON LANDING REPORTED THAT THE LEFT ENGINE WOULD NOT IDLE UNLESS MIXTURE PULLED BACK HALFWAY. INSPECTION REVEALED THAT THE COTTER PIN WHICH HOLD THE MIXTURE INTERCONNECT ROD TO THE THROTTLE VALVE HAD BROKEN AND THE ARM FELL OFF ALLOWING NO MIXTURE ADJUSTMENT WITH THROTTLE MOVEMENT AS REQUIRED. NE W COTTER PIN INSTALLED, AIRCRAFT GROUND RUN AND CHECKED SERVICEABLE. ADDITIONAL CHECK CARRIED OUT TO ALL CYLINDERS, COMP RESSION AND BORESCOPE REVEALED NO APPARENT DAMAGE CAUSED AIRCRAFT RETURNED TO SERVICE. 1 L 7 2 3O 3 O 3A10 3E1 5 C P22EA 2002011700013 20020117 00013 CE 2002 1 17 CA011105014 1 20010731 G 3250 07430118 ARM CESSNA 172 172M 2072418 CE LYC O320 O320E2D 41508 EA NLG STEERING CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) THIS PROBLEM WAS DISCOVERED DURING THE AIRCRAFTS ANNUAL INSPECTION. THE CRACK IS ALL OF THE WAY THROUGH THE FORWAR D SIDE OF THE ARM, VERTICALLY ORIENTED AND PASSES THROUGH THE GREASE FITTING HOLE.IT APPEARS TO HAVE ORIGINATED AT THE F ILLET FORMED BY THE RIGHT SIDE OF THE STEERING STOP LUG, AND THE UPPER MACHINED SURFACE OF THE ARM. ALL RELEVANT STEERIN G PARTS ARE SERVICEABLE AND THERE IS NO APPARENT CAUSE FOR THE CRACK. 1 H 7 1 3O 3 O NT 3A12 E274 2002011700014 20020117 00014 EA 2002 1 17 CA011105015 2 20011015 G 8500 CASE CESSNA 172 172M 2072418 CE LYC O320 O320E2D 41508 EA ENGINE CRACKED W K NONE K FLUID LOSS IN INSP/MAINT 1 CA (CAN) CRACK FOUND IN CASE AROUND FORWARD UPPER THROUGH BOLT. 1 H 7 1 3O 3 O NT 3A12 E274 2002011700015 20020117 00015 EU 2002 1 17 CA011105016 1 20011005 G 6320 4638001009 GEARBOX BOLKMS 105 BO105C 5626005 EU ALLSN 250C 250C20B 03013 GL MAIN ROTOR MAKING METAL W E ENGINE SHUTDOWN J WARNING INDICATION TX TAXI/GRND HDL 1 CA (CAN) ON ENGINE START UP - PILOT REPORTED MGB CHIP LIGHT ON, PULSED OFF AND 4 SECONDS LATER LIGHT BACK ON. ENGINE SHUT D OWN, MAG PLUG PULLED 2 SMALL FLAKED AND SOME FUZE ON PLUG. FINE OIL FILTER REMOVED AND FOUND TO BE CONTAMINATED WITH NUM EROUS, VARIOUS SIZED PARTICLES. AIRCRAFT REMOVED FROM SERVICE PENDING MGB CHANGE. 1 G 7 2 3U 3 U H3EU E4CE 2001110800008 20011108 00008 EU 2001 11 8 CA011105017 1 20011015 G 2913 62052RSIMT47CR BEARING AEROSP 350A35013004 SNIAS 350 AS350B 8680801 EU TMECA ARRIEL ARRIEL1B 6OO30 NE INTERNAL BROKEN W A L UNSCHED LANDING ABORTED APPROACH F J FLT CONT AFFECTED WARNING INDICATION CL CLIMB 1 CA (CAN) DURING TAKEOFF/CLIMB OUT OF A WOODED AREA, THE PILOT GOT A HYDRAULIC LIGHT INDICATION. HE LATER REPORTED THAT THE AIRCRAFT HAD A COMPLETE HYDRAULIC FAILURE. THE CAUSE OF THE FAILURE WAS DUE TO A BEARING FAILURE IN THE HYDRAULIC DIVE P ULLEY, THE CAGE OR THE BEARING HAD BROKEN APART CAUSING THE PULLEY ASSEMBLY TO SEIZE AND THE HYDRAULIC BELT TO BREAK. TH E AIRCRAFT LANDED WITHOUT FURTHER INCIDENT. 1 G 7 1 3U 3 U H9EU E19EU 2002011700016 20020117 00016 SO 2002 1 17 CA011105018 1 20010816 G 3230 455180 STRUCTURE PIPER PA30 PA30 7103002 SO LYC O320 IO320B1A 41508 EA MLG GALLED W O OTHER R PARTIAL RPM/PWR LOSS LD LANDING 1 CA (CAN) IT WOULD APPEAR, UPON INVESTIGATION THAT A PIECE OF MATERIAL FROM THE INNER ATTACHMENT (TELEFLEX) BROKE AND BECAME LODGED BETWEEN IT AND THE OUTER PORTION (SLIDE) AND CAUSED GALLING/SCORING WHICH JAMMED THE U/C AND WOULD NOT ALLOW GEA R TO EXTEND. AFTER MUCH EFFORT THE GEAR WAS EXTENDED AND THE AIRCRAFT LANDED WITHOUT INCIDENT. 1 L 7 2 3O 3 O A1EA 1E12 2002020800055 20020208 00055 NE 2002 2 8 CA011107001 1 20011004 G 3246 5003450 WHEEL SKRSKY S76 S76A 8143006 NE ALLSN 250C 250C30S 03013 GL NLG CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) WHEEL SUBASSEMBLY FOUND CRAKED WHILE INVESTIGATING SLOW LEAK. 1 G 7 2 3U 3 U H1NE E1GL 2002011700017 20020117 00017 EU 2002 1 17 CA011108001 1 20011029 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 (CAN) DURING INSPECTION A CRACK WAS FOUND ON THE LOWER SURFACE OF THE BLADE AT STN. 1003. CRACK LENGTH WAS APPROXIMATELY 155.52 MM STARTING 111.46 FROM THE LEADING EDGE TRAVELLING CORDWISE TO 33.02 MM FROM THE TRAILING EDGE. 1 G 7 1 3U 3 U H9EU E19EU 2002011700018 20020117 00018 NE 2002 1 17 CA011108002 2 20011023 G 8530 71166 EXHAUST VALVE BEECH 18 TC45G 1151016 CE PWA R985 R985AN14B 52008 NE ENGINE FAILED W O OTHER R J PARTIAL RPM/PWR LOSS WARNING INDICATION LD LANDING 1 CA (CAN) NR 1 EXHAUST VALVE HEAD BROKE OFF CONTACTING PISTON AND BENDING CONNECTING ROD. 1 L 7 2 3R 3 R A765 5E1 2002011700019 20020117 00019 CE 2002 1 17 CA011108003 1 20011106 G 2730 505244325 BRACKET BEECH 100 A100 1152915 CE PWA PT6 PT6A28 EA ELEVATOR CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 15320 15320 (CAN) WHILE CONDUCTING THE INSPECTION OF THE ELEVATOR PULLEY BRACKETS IAW BEECH SB 2150 ELEVATOR PULLEY BRACKET PART NR 50-524432-5 AND 50-524432-7 WERE FOUND CRACKED. SERVICE KIT NR 90-4098-1 S INSTALLED IN ACCORDANCE WITH BEECH SB 2150 R EVLL 1 L 7 2 3T 4 T A14CE E4EA 2002011700021 20020117 00021 NM 2002 1 17 CA011108007 1 20011029 G 7602 600035549 CONTROL CABLE PIPER PA60 PA60600 7106001 NM LYC O540 IO540K1J5 41532 EA MIXTURE CONTROL SEPARATED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) DURING ANNUAL INSPECTION THE ENGINES WERE BEING REMOVED FOR REPLACEMENT. DURING INSPECTION OF THE ENGINE CONTROLS, BOTH THE LT MIXTURE CONTROL CABLE P/N 600035-549 AND RIGHT HAND MIXTURE CONTROL CABLE P/N 600035-547 WERE FOUND TO BE S EPARATED AT THE SWAGED END. THE LT CABLE HAD A TIME OF 2125.8 HOURS SINCE NEW. TIME ON R/H CABLE UNKNOWN. THE CABLES WER E REPLACED WITH SERVICEABLE UNITS. 1 M 7 2 3O 3 O RT A17WE 1E4 2002011700027 20020117 00027 EA 2002 1 17 CA011108011 2 20011029 G 7414 1038291018 MAGNETO PIPER PA31 PA31350 7103110 SO LYC O540 TIO540J2BD 41532 EA RT ENGINE DAMAGED W E A ENGINE SHUTDOWN UNSCHED LANDING R J PARTIAL RPM/PWR LOSS WARNING INDICATION CR CRUISE 1 CA (CAN) DURING CRUISE FLIGHT THE RT ENGINE SURGED ONCE AND THEN FAILED. CREW BELIEVE RPM REMAINED NORMAL BUT MANIFOLD PRES SURE DROPPED TO 20 INCH HG THEN BACK UP AND AGAIN DOWN TO 20 INCH. ELECTRIC FUEL PUMP WERE TRIED BUT DID NOT HELP SO ENG INE WAS SHUT DOWN AND NORMAL LANDING CARRIED OUT ON ONE ENGINE. 1 L 7 2 3O 3 O A20SO E14EA 2002020800057 20020208 00057 EA 2002 2 8 CA011108012 2 20011031 G 8520 STD1065 DOWEL PIN BNORM BN2 BN2A 1520204 EU LYC O540 O540E4C5 41532 EA CRANKSHAFT SHEARED W E ENGINE SHUTDOWN R PARTIAL RPM/PWR LOSS CR CRUISE 1 CA (CAN) DURING CRUISE JUST PRIOR TO LANDING IN YVR, LT ENGINE BEGAN TO RUN VERY ROUGH WITH MOST OR ALL POWER LOSS. PILOT SHUT ENGINE DOWN AND LANDED NORMALLY IN YVR. PRELIMINARY INVESTIGATION FOUND BOTH VALVE AND MAG TIMING TO HAVE ALTERED S IGNIFCANTLY. 1 H 7 2 3O 3 O A17EU E295 2002011700028 20020117 00028 EU 2002 1 17 CA011108013 1 20011107 G 3097 3E23602 WIRE PILATS PC12 PC1245 7090551 EU PWA PT6 PT6A67B 52043 NE HARTZL HCE4A HCE4A3D GL DEICE HARNESS BROKEN W K NONE L NO TEST IN INSP/MAINT 1 CA (CAN) PILOT REPORTED PROP DE-ICE SYSTEM OPERATING INTERMITTENTLY. INVESTIGATION REVEALED THAT THE GROUND WIRE IN THE HAR NESS BETWEEN THE BACKING PLATE TERMINAL BLOCK AND THE BLADE DE-ICER BOOT WAS BROKEN INTERNALLY. WITH FEATHERING AND UNFE ATHERING OF THE PROPELLOR THE HARNESS IS CONSTANTLY BENDING THE WIRES CAUSING THE BREAKAGE. THE WIRE APPEARS TO HAVE MAD E CONTACT WITH THE TWO BROKEN ENDS CAUSING THE WIRE ENDS TO ARC TOGETHER THUS GIVING THE INTERMITTENT OPERATION OF THE S YSTEM. THE HARNESS WAS REPLACED WITH NEW AND SYSTEM FUNCTIONED NORMALLY. 1 L 7 1 3T 4 T RT A78EU E26NE 5 C P210NE 2002011700029 20020117 00029 EU 2002 1 17 CA011109002 1 20010808 G 3240 NB73A4354 LINE BNORM BN2 BN2A27 1520227 EU LYC O540 O540E4C5 41532 EA RT MLG BRAKE CHAFED W D RETURN TO BLOCK K J FLUID LOSS WARNING INDICATION TX TAXI/GRND HDL 1 CA 17401 (CAN) ONE OF THE TWO BRAKE LINES THAT RUN DOWN THE LEG CHAFED THROUGH AT THE TOP CLAMP. BRAKES WERE SOFT ON THAT SIDE. 1 H 7 2 3O 3 O A17EU E295 2002011700030 20020117 00030 SO 2002 1 17 CA011109003 1 20011109 G 3230 4204200 LINK PIPER PA31 PA31350 7103110 SO LYC O540 TIO540J2BD 41532 EA MLG BROKEN W O OTHER D INFLIGHT SEPARATION LD LANDING 1 CA (CAN) LINK FAILED AFTER TAKEOFF AND GEAR WOULD NOT COME UP. FORTUNATELY IT WENT BACK DOWN AND AIRCRAFT LANDED NORMALLY. IT COULD HAVE BEEN WORSE VERY EASILY. I WAS ALSO INFORMED BY OPERATOR THAT THIS IS THE SECOND TIME THAT THIS HAS HAPPENE D. 1 L 7 2 3O 3 O A20SO E14EA 2002011700036 20020117 00036 SO 2002 1 17 CA011109004 1 20010917 G 3242 753407 BOLT CLEVELAND 3095A PIPER PA31 PA31350 7103110 SO LYC O540 TIO540J2BD 41532 EA BRAKE ASSY BROKEN W O OTHER D INFLIGHT SEPARATION LD LANDING 1 CA (CAN) UPPER TORQUE PIN (ANCHOR PIN) FAILED ALLOWING BRAKE TO ROTATE INTO BACK OF MAIN LANDING GEAR STRUT. ALSO INSIDE SU RFACE OF MAIN WHEEL SCORED. PIPER ANCHOR BOLT P/N 753-407 CLEVELAND ANCHOR BOLT P/N 69-4 1 L 7 2 3O 3 O A20SO E14EA 2002011700037 20020117 00037 CE 2002 1 17 CA011109006 1 20011023 G 5330 97400021101 SKIN BEECH 100 100BEECH 1152916 CE PWA PT6 PT6A28 EA FUSELAGE CHAFED W K NONE O OTHER IN INSP/MAINT 1 CA 10337 (CAN) DUE TO THE ANGLE OF CONTACT BETWEEN THE WING CENTRE SECTION TO FUSELAGE FILLET P/N 50-420023-37 AND -38 AND THE FU SELAGE SKIN P/N 97-400021-101 AND -102 WHEN THE RIVETS WORK LOOSE IN THE FILLET IT IS ALLOWED TO CHAFE INTO THE FUSELAGE SKIN. THIS SKIN IS A PRESSURE SKIN AND REQUIRES ENGINEERING APPROVED FOR REPAIRS.TO REDUCE RECURRENCE OF THIS PROBLEM T HERE SHOULD BE AN ANTI-CHAFE MEDIUM BETWEEN FILLET AND SKIN, I.E. PRC 1422-B 1/2 AND RIVETS SHOULD BE KEPT IN TOP CONDIT ION, FIXING ANY DEFECTS AS THEY OCCUR. 1 L 7 2 3T 4 T A14CE E4EA 2002011700039 20020117 00039 SW 2002 1 17 CA011109007 1 20011024 G 6520 204001739003 SEGMENT BELL 204 204B 1181404 SW LYC T53 T5311B 41549 NE T/R G/B CHAIN MISSING W K NONE W INADEQUATE Q C IN INSP/MAINT 1 CA (CAN) UPON INSTALLATION OF THE NEW CHAIN, THE ENGINEER NOTICED A SPACE BETWEEN SOME CHAIN LINKS. CHAIN IS MISSING A SEGM ENT. 1 G 7 1 4U 4 U H1SW E1EA 2002011700040 20020117 00040 EU 2002 1 17 CA011109008 1 20011009 G 6710 350A2705510602 FRICTION RING SNIAS 350 AS350D 8680803 EU LYC LTS101 LTS101600A2 41560 NE MAIN ROTOR FAILED W O OTHER D INFLIGHT SEPARATION NR NOT REPORTED 1 CA (CAN) LOCK PIN NR 10 EITHER NOT PROPERLY INSTALLED OR CAME LOOSE ALLOWING NUT NR 9 TO VIBRATE LOOSE FROM LOWER THREAD PO RTION OF COLLAR NR 8, THIS ALLOWED THE ENTIRE FRICTION ASSY TO BE LIFTED BY HAND. THIS COULD EASILY THEN CAUSE BINDING O R LIMIT CYCLIC MOVEMENT. COLLAR NR 8 IS DRILLED TO ACCEPT THE LOCK RING. ALL PARTS EXAMINED AND REINSTALLED TO ENSURE PR OPER LOCKING EFFECTIVENESS. 1 G 7 1 3U 3 U H9EU E5NE 2002011700041 20020117 00041 WP 2002 1 17 CA011109010 2 20011009 G 7261 8971973 DRIVE SHAFT GARRTT TPE331 TPE33110UA 01514 WP SCAVE PUMP DAMAGED W K NONE W INADEQUATE Q C IN INSP/MAINT 1 CA (CAN) ON INSPECTION OF PARTS REMOVED FROM P-63110 AT TIME OF OVERHAUL IT WAS NOTED THAT THE FRONT SCAVENGE PUMP DRIVE SH AFT SAFTY COLLER IS 0.210 SMALLER THAN THE REPLACEMENT PART THIS CAN ALLOW THE SHAFT TO ENTER THE PUMP TO FAR AND ALLOW THE FUEL DRIVE SYSTEM TO UNCOUPPLE. ON SDR 20001206012 THE SAME PROBLEM WAS NOTED ON ENGINE S/N P-63111. 4 T E4WE 2002011700042 20020117 00042 SO 2002 1 17 CA011109014 1 20011013 G 5710 FASTENER EMB 110 EMB110P1 3260122 SO PWA PT6 PT6A34 52043 EA LT MLG SHEARED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) DURING A 12C INSPECTION (7200 HOUR) MAINTENANCE PERSONNEL FOUND SEVERAL SHEARED HILOCKS ON THE LEFT HAND WING AT R IB NR 6.THE LEFT HAND LANDING GEAR WAS REMOVED AND AREA INSPECTED, NO STRUCTURAL DAMAGE WAS FOUND. 22 HILOCKS WERE REPLA CED AND GEAR REINSTALLED. THE SAME INSPECTION WAS COMPLETED ON THE RIGHT HAND SIDE AND NO DEFECTS WERE NOTED. A GEAR SWI NG WAS COMPLETED AND AIRCRAFT WAS RETURNED TO SERVICE. 1 L 7 2 4T 4 T A21SO E4EA 2002011700052 20020117 00052 EU 2002 1 17 CA011113007 1 20011113 G 3060 3E23602 WIRE PILATS PC12 PC1245 7090551 EU PWA PT6 PT6A67B 52043 NE HARTZL HCE4A HCE4A3D GL DEICE HARNESS BROKEN W O OTHER J WARNING INDICATION CR CRUISE 1 CA (CAN) DURING PROP DEICE OPERATION THE SYSTEM INDICATED A FAILURE.UPON INVESTIGATION / TROUBLESHOOT IT WAS FOUND THE HAR NESS P/N 3E23060-2 HAD AN INTERNAL BREAK WITH LITTLE OR NO CONTINUITY WHILE MOVING THE HARNESS AS INSTALLED.PART WAS REM OVED NEW ONE INSTALLED SYSTEM TESTED SERVICEABLE. 1 L 7 1 3T 4 T RT A78EU E26NE 5 C P210NE 2002020800059 20020208 00059 EA 2002 2 8 CA011113017 1 20010111 G 5410 60135006 SUPPORT CNDAIR CL600 CL6002B19 1900309 EA GE CF34 CF343A1 30015 NE PUMP CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 12120 (CAN) FOUND THREE CRACKS DURING CHECKS. CRACKED AT FS 630 & 640, LT & RT BL 36 & 00. 2 L 7 2 4F 4 F RT A21EA E15NE 2001121200011 20011212 00011 EU 2001 12 12 CA011114001 1 20011001 G 5230 D2586 LATCH DART D350600042 SNIAS 350 AS350D 8680803 EU LYC LTS101 LTS101600A3 41560 NE LATCH FAILED W B EMER. DESCENT D D INFLIGHT SEPARATION INFLIGHT SEPARATION CR CRUISE 1 CA (CAN) PRIOR TO COMMENCING HIS FLT PILOT HAD REMVD SEAT CUSHIONS&STOWED THESE IN SIDE CARGO COMPT POD. DURING FLT POD "DO OR OPEN" LIGHT ILLUMINATED WHICH FOLLOWED BY LOUD BANG&SEVERE VIBRATIONS. PILOT IMMEDIATELY LANDED&FOUND THAT R/H POD DO OR HAD OPENED&SEAT CUSHION HAD FALLEN OUT STRIKING TAILBOOM&TAIL ROTOR WHILE IN FLT. REAR LATCH INSIDE LOCK BROKEN&SUBST ANTIAL DAMAGE TO A/C. FWD LATCH APPEARED UNDAMAGED BUT NOT POSITIVELY LATCHED. IT APPEARS THAT FWD LATCH MAY HAVE ALLOW ED FRONT EDGE OF POD DOOR TO OPEN IN FLT AFTER WHICH PRESSURE FROM SLIPSTREAM PROBABLY BROKE REAR LATCH DUE TO EXCESSIVE PRESSURE B EING EXERTED ON DOOR. ALLOWED DOOR T 1 G 7 1 3U 3 U H9EU E5NE 2002011700072 20020117 00072 CE 2002 1 17 CA011114014 1 20011011 G 7120 045111432 MOUNT CESSNA 150 150M 2071830 CE CONT O200 O200A 17020 SO ENGINE CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) DURING A 50 HOUR INSPECTION THE ENGINE MOUNT WAS FOUND CRACKED. THE SUPPORT WAS REPLACED. 1 H 7 1 3O 3 O 3A19 E252 2002011700073 20020117 00073 SO 2002 1 17 CA011114015 1 20011024 G 5751 6210500 HINGE PIPER PA32 PA32300 7103212 SO LYC O540 IO540K1A5 41532 EA LT AILERON CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) DURING AN INSPECTION AN ONE AND A HALF INCH CRACK WAS DETECTED ON THE DOUBLER HINGE OUTSIDE OF THE LEFT AILERON. 1 L 7 1 3O 3 O A3SO 1E4 2002021100005 20020211 00005 EU 2002 2 11 CA011114016 1 20011102 G 6320 4619302046 BEARING BOLKMS 105 BO105CBS 5626008 EU ALLSN 250C 250C20B 03013 GL M/R GEARBOX PEELING W O OTHER J WARNING INDICATION NR NOT REPORTED 1 CA (CAN) CHIP LIGHT INDICATION.GEARBOX DISASSEMBLED FOR INVESTIGATION.BEARING PLATING FOUND PEELING.REPLACED WITH NEW 1 G 7 2 3U 3 U NC H3EU E4CE 2002020500122 20020205 00122 EU 2002 2 5 CA011114017 1 20011114 G 6320 4619310072 BEARING BOLKMS 4619002003 BOLKMS 105 BO105CBS 5626008 EU ALLSN 250C 250C20B 03013 GL INPUT DEFECTIVE W O OTHER J WARNING INDICATION IN INSP/MAINT 1 CA 1112 (CAN) BOTH INNER AND OUTER RACE OF BEARING DISPLAYED MODERATE PITTING AND PEELING 1 G 7 2 3U 3 U NC H3EU E4CE 2002011700076 20020117 00076 NE 2002 1 17 CA011114018 1 20011030 G 7712 9609000254 BEARING SKRSKY S76 S76A 8143006 NE TMECA ARRIEL ARRIEL1S1 60030 NE TORQUEMETER FAILED W L ABORTED APPROACH J WARNING INDICATION AP APPROACH 1 CA (CAN) SUBJECT: ESN 15051- PARTICLES ANALYSIS. WE HAVE RECEIVED THE ANALYSIS RESULTS OF THE PARTICLES FOUND ON THE MODULE 05 S/N¦ 03199¦ MAGNETIC PLUG . THE PARTICLES¦ ARE 100 C6 MATERIAL AND HAVE AS THE ORIGIN ONE OF THE HYDRAULIC TORQUEM ETER BEARINGS ("TRIPLEX") . 1 G 7 2 3U 3 U H1NE E19EU 2002011700078 20020117 00078 SW 2002 1 17 CA011116001 1 20011107 G 5210 90000949722 PUSHROD GULSTM 690TP 690A 0141722 SW GARRTT TPE331 TPE3315251K NM PAX DOOR BENT W O OTHER O OTHER CL CLIMB 1 CA (CAN) DURING CLIMBOUT THE AIRCRAFT PRESSURIZATION REDUCED FROM 4.8 PSI TO 3.5 PSI. UPON INVESTIGATION IT WAS NOTED THAT THE LOWER AFT ENTRANCE DOOR BAYONET WAS NOT EXTENDING INTO THE AIRFRAME. THE TWO PUSHRODS P/N'S 900009-49-7.22 AND 90000 9-49-9.70 WERE FOUND BENT WHICH CAUSED THE BAYONET NOT TO EXTEND INTO THE AIRFRAME. THE PUSHRODS WERE REPLACED AND THE C ABIN DOOR MECHANISM WAS RE-RIGGED. DOOR OPERATIION WAS CHECKED, THE DOOR SEAL WAS INSPECTED AND A PRESSURIZATION CHECK W AS COMPLETED AND CHECKED SERVICEABLE. THE AIRCRAFT WAS RETURNED TO SERVICE. 1 H 7 2 3T 4 T 2A4 E2WE 2002021100006 20020211 00006 2002 2 11 CA011116002 4 20011107 G 6122 A20609 CONTROL ARM MCAULY C290D3RT9 CESSNA 185 A185E 2072818 CE CONT O520 IO520D 17032 SO MCAULY 2A34C D2A34C58 GL PROP GOVERNOR MISINSTALLED W K NONE O OTHER IN INSP/MAINT 1 CA 010596 (CAN) GOVERNOR WOULD NOT CYCLE PROP BELOW 1500 RPM. CONTROL ARM INSTALLED IN THE INCORRECT POSITION ON CONTROL SHAFT. 1 H 7 1 3O 3 O 3A24 E5CE 5 C P3EA 2002011700080 20020117 00080 SW 2002 1 17 CA011116003 1 20011023 G 6230 269A21725 SUPPORT HUGHES 269 269C1 8059504 SW LYC O360 HO360C1A 41514 EA M/R MAST CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) AFT MAIN ROTOR MAST SUPPORT (TAILBOOM TO M/R GEARBOX MAST). 1 G 7 1 3O 3 O O 4H12 E286 2002011700082 20020117 00082 SW 2002 1 17 CA011116004 1 20011107 G 6230 269A21725 SUPPORT HUGHES 269 269C1 8059504 SW LYC O360 HO360C1A 41514 EA M/R MAST CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) AFT MAIN ROTOR MAST SUPPORT (TAILBOOM TO MAIN ROTOR GEARBOX MAST) 1 G 7 1 3O 3 O O 4H12 E286 2002011700090 20020117 00090 EA 2002 1 17 CA011116005 1 20011023 G 7714 659450105 INDICATOR DHAV DHC2 DHC2MK1 2800102 EA PWA R985 R985AN14B 52008 NE ENG TRIPLE GAUGE EXPLODED W O OTHER O OTHER LD LANDING 1 CA (CAN) ENGINE TRIPLE GAUGE EXPLODED: - CASE SPLIT (TOTAL CIRCUMFERENCE). - 1 LARGE PORTION OF CASE BROKEN OFF. - FRONT GL ASS FACE PLATE SHATTERED OUTWARD SLIGHTLY INJURING PASSENGER IN CO-PILOT SEAT. 1 H 7 1 3R 3 R A806 5E1 2002011700091 20020117 00091 NE 2002 1 17 CA011116006 1 20011029 G 6220 7610308010049 HUB SKRSKY S76 S76C 8143008 NE TMECA ARRIEL ARRIEL2B NE M/R DAMPER CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) A CRACK APPROXIMATELY 2.5 CM, EXTENDING INBOARD FROM BUSHING BORE ON UPPER LUG OF RED MAIN ROTOR DAMPER SUPPORT. 1 G 7 2 3U 3 U NC H1NE E00054EN 2002011700092 20020117 00092 SW 2002 1 17 CA011116007 1 20010908 G 3212 108839 REGULATOR BELL 222 222U 1182140 SW LYC LTS101 LTS101750C1 41560 NE MLG FLOAT LEAKING W K NONE L NO TEST IN INSP/MAINT 1 CA (CAN) AIRCRAFT BELL 222U POP-OUT FLOAT SYSTEM CHARGED TO 3000 PSI AFTER CHANGING FLOAT BOTTLE. SYSTEM LEAKED APPROXIMATE LY 200 PSI OVER A 12 HOUR PERIOD. BY REMOVING THE LINES TO AIR BAG IT WAS CONFIRMED THAT AIR WAS LEAKING THROUGH SHEAR H EAD BY SMALL CRACKS. THE SHEAR HEAD IS TO MAINTAIN 3000 PSI IN THE FLOAT BOTTLE TILL FLOATS ARE DEPLOYED. 1 G 7 2 3U 3 U H9SW E5NE 2002011700093 20020117 00093 EU 2002 1 17 CA011116009 1 20010711 G 6220 704A33633160 BUSHING AEROSP 350A31190701 SNIAS 350 AS350B1 8680811 EU TMECA ARRIEL ARRIEL1D NE M/R SPIDER DEBONDED W K NONE O OTHER IN INSP/MAINT 1 CA M1012 (CAN) BOLT P/N 22208BC10001GL BACKED OUT ALLOWING DEBONDED BUSHING P/N 704A33-633-160 TO MOVE OUTWARD APPROXIMATELY 1/4 INCH ON THE OUTBOARD END OF THE RED ARM. DAMAGE WAS DISCOVERED ON A DAILY INSPECTION. PILOT HAD COMPLAINED OF VIBRATION ON GROUND WHILE RUNNING.ON REPLACEMENT OF THE STAR, BEARING P/N 11-7775P IN THE FREQUENCY ADAPTER WAS FOUND WITH EXCESSI VE PLAY ON THE SAME ARM. 1 G 7 1 3U 3 U H9EU E19EU 2002011700094 20020117 00094 EU 2002 1 17 CA011116010 1 20011109 G 6720 350A33105803 BELLCRANK AEROSP 350A33105803 SNIAS 350 AS350B2 8680813 EU TMECA ARRIEL ARRIEL1D NE T/R CONTROL CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) AS PER A COMPANY MEMO TO CHECK THIS LEVER/BELLCRANK FOUND ANOTHER ONE CRACKED IN THE SAME REGION (SEE ATTACHED DOC UMENT). NOTE: THE FIRST SDR SUBMITTED THE ARROWS WERE POINTING IN THE WRONG REGION. THE ARROWS SHOULD BE MORE OUTBOARD F ROM WHERE THEY WERE POINTING. THIS WAS C-FSPR DATED 01/10/25 CONTROL NUMBER UNKNOWN.SDR CONTROL #20011029017 (C-FSPR) 1 G 7 1 3U 3 U H9EU E19EU 2002021100007 20020211 00007 2002 2 11 CA011116011 4 20011029 G 3422 200DC GYRO HUGHES 369 369D 4470706 WP ALLSN 250C 250C20B 03013 GL COCKPIT SHORTED W O OTHER B SMOKE/FUMES/ODORS/SPARKS AP APPROACH 1 CA 2909 (CAN) ON FINAL FOR LANDING, PILOT AND PASSENGERS NOTICED AN ELECTRICAL SMELL, SECONDS LATER WHITE SMOKE FILLED THE CABI N COMING FROM BEHIND INSTRUMENT PANEL. ALL CIRCUIT BREAKERS WERE PULLED AND AIRCRAFT SHUT DOWN. INSPECTION REVEALED DIRE CTIONAL GYRO HAD SHORTED INTERNALLY AND MELTED DOWN. 1 G 7 1 3U 3 U H3WE E4CE 2002011700095 20020117 00095 NM 2002 1 17 CA011116012 1 20011115 G 2910 82970010249 LINE 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 CA 30700 (CAN) THE FLIGHT CREW NOTICED FLUID LEAKING FROM THE LEFT NACELLE DURING THEIR WALK-AROUND INSPECTION.MAINTENANCE FOUND THE "MLG DOWN PRESSURE" HYDRAULIC TUBE LEAKING FROM A PIN HOLE UNDER THE EXHAUST SHROUD. THE RIGID TUBE WAS TEMPORARILY REPLACED WITH TWO FLEXIBLE HOSES AS PER AMM 20-50-52. THE SYSTEM WAS TOPPED UP AND LEAK CHECKED PRIOR TO RETURNING THE A IRCRAFT TO SERVICE. 2 H 7 2 4T 4 T RT A13NM E20NE 6 C P7NE 2002011700096 20020117 00096 CE 2002 1 17 CA011116013 1 20011105 G 2752 C145350 ACTUATOR CESSNA 208 208B 2073701 CE PWA PT6 PT6A114A 52043 NE MCAULY 3AF34C 3GFR34C703 GL TE FLAPS SEIZED W O OTHER O OTHER DE DESCENT 1 CA (CAN) ON APPROACH FLAPS SELECTED FROM 10 TO 20 AS FLAPS TRAVELLED THROUGH APPROXIMATELY 15 DEGREES THE FORWARD FLAP MOTO R FAILED AND BROKE FREE OF THE TRANSMISSION/JACKSCREW ASSY. THIS CAUSED THE FLAP ACTUATOR ASSEMBLY TO BRAKE FREE OF THE ATTACHING STRUCTURE, THUS CAUSING THE FLAP TO RAPIDLY RETRACT TO THE STOWED POSITION. 1 H 7 1 3T 3 T A37CE E4EA 5 C P60GL 2002011700097 20020117 00097 SO 2002 1 17 CA011116014 2 20011106 G 7314 6462121 PUMP CESSNA 185 A185F 2072821 CE CONT O520 IO520D 17032 SO MCAULY 2A34C D2A34C58 GL FUEL FAILED W A UNSCHED LANDING Y J ENGINE STOPPAGE WARNING INDICATION CL CLIMB 1 CA (CAN) DURING CLIMB AFTER TAKEOFF FROM RUNWAY 16 AT YYC WHEN THE PILOT ADJUSTED THROTTLE AND MIXTURE THE ENGINE STOPPED P RODUCING POWER. AN EMERGENCY LANDING WAS CARRIED OUT ON THE END OF RUNWAY 16. 1 H 7 1 3O 3 O 3A24 E5CE 5 C P3EA 2002020500123 20020205 00123 SW 2002 2 5 CA011116015 1 20011101 G 6320 204040135001 BEARING BELL 212040001123 BELL 212 212 1181420 SW PWA PT6T PT6T3B 52045 NE BEARING FAILED W A UNSCHED LANDING J WARNING INDICATION DE DESCENT 1 CA ABW40334 (CAN) WHILE IN DESCENT TO THE LANDING AREA THE MAIN ROTOR TRANSMISSION CHIP LIGHT ILLUMINATED. THE PILOT MAINTAINED ITS APPROACH AND LANDED. UPON INSPECTION ON THE CHIP DETECTOR METAL WAS FOUND AND THEN THE WAFFER FILLER WAS CHECKED WHERE M ORE METAL WAS FOUND. MAIN ROTOR TRANSMISSION CHANGED. 1 G 7 1 4U 4 U H4SW E22EA 2002021100008 20020211 00008 CE 2002 2 11 CA011116016 1 20010611 G 3221 TAIL WHEEL CESSNA 180 180H 2072618 CE CONT O470 O470* 17026 SO MCAULY 2A34C 2A34C66 GL MLG SEPARATED W O OTHER W D INADEQUATE Q C INFLIGHT SEPARATION CL CLIMB 1 CA (CAN) AFTER TAKEOFF FROM ROUGH STRIP ON HERSEL ISLAND, PILOT HEARD LOUD BANGING SOUND. HE WAS ABLE TO SEE TAIL WHEEL MIS SING. ON LANDING AT AKLAVIK, STEERING CONTROL LOST. MINOR DAMAGE TO TAIL STRINGER. NEW TAIL WHEEL ASSEMBLY INSTALLED WI TH PROPER AIRCRAFT BOLTS. THE AIRCRAFT RETURNED TO SERVICE. THE CAUSE WAS FOUND TO BE A NON AIRCRAFT BOLT HOLDING ASSEMB LY ON. 1 H 7 1 3O 3 O 5A6 E273 5 C P3EA 2002011700098 20020117 00098 EA 2002 1 17 CA011116017 2 20011102 G 8520 LW1594485 CRANKSHAFT CESSNA 172 172N 2072434 CE LYC O320 O320H2AD 41508 EA ENGINE CORRODED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) CORROSION FOUND UNDERNEATH URETHABOND COATING APPLIED BY FACTORY AT OVERHAUL AS PER SB 505B AND SB 530A AND AD 98- 02-08.CRANKSHAFT HAS BEEN RETURNED TO FACTORY FOR WARRANTY CONSIDERATION AND INSPECTION. 1 H 7 1 3O 3 O NT 3A12 E274 2002011700099 20020117 00099 CE 2002 1 17 CA011116018 1 20011108 G 5610 10138402521 WINDSHIELD BEECH 200 200BEECH 1152920 CE PWA PT6 PT6A41 52043 EA COCKPIT CRACKED W O OTHER O OTHER CR CRUISE 1 CA (CAN) THE AIRCRAFT WAS IN CRUISE AT FLIGHT LEVEL 290, APPROXIMATELY 50 MILES NW OF SUDBURY, ONTARIO, ENROUTE FROM THUNDE R BAY TO THETFORD MINES, QUEBEC, WHEN THE LT WINDSHIELD INNER PANE SHATTERED. THE CREW REDUCED PRESSURIZATION TO 4 PSI D IFFERENTIAL PRESSURE AS PER FLIGHT MANUAL PROCEDURES AND DIVERTED TO QUEBEC CITY.THE CREW REPORTED THAT THE WINDSHIELD H EAT WAS IN THE "HIGH" SELECTION AND THAT THE OAT WAS -36 DEGREES C AT THE TIME OF THE OCCURRENCE. 1 L 7 2 4T 4 T A24CE E4EA 2002011700101 20020117 00101 CE 2002 1 17 CA011116020 1 20011106 G 5610 101384002522 WINDSHIELD BEECH 200 200BEECH 1152920 CE PWA PT6 PT6A41 52043 EA HARTZL HCD4N3 HCD4N3A GL COCKPIT FAILED W O OTHER O OTHER AP APPROACH 1 CA (CAN) ON APPROACH INTO CIGAR LAKE, SASKATCHEWAN (JWY) THE RIGHT HAND WINDSHIELD INNER PANE SHATTERED IN A LATTICE LIKE M ODE. THE NETWORK OF CRACKS EXTENDED OVER THE ENTIRE INNER SURFACE OF THE SHIELD AND AN ORIGINATING POINT OR CAUSE COULD NOT BE DETERMINED. 1 L 7 2 4T 4 T A24CE E4EA 5 C STC 2002011700103 20020117 00103 SW 2002 1 17 CA011119001 1 20010914 G 6510 2060403255 SHAFT BELL 206 206B 1181511 SW ALLSN 250C 250C20 03013 GL T/R DRIVE GROOVED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) ONLY APPLIES TO A/C EQUIPPED WITH CASEY HEATER & ATTACHED DUCTING. DURING GROUND RUN CHECKS AFTER OPS CHECK (600 H R) INBOARD HEATING DUCT CONTACTED SHAFT ASSY P/N 206-040-325-5 & ADAPTER P/N 206-040-328-003 HEATING DUCT (HOSE) WASTORN & WIRE IN HEATER (HOSE) BROKE & CONTACTED THEAFT END OF SHAFT & ADAPTER CAUSING DEEP GROOVES IN BOTH.DURING INSP BOTH S HAFT/COUPLING ADAPTER & BLOWER ASSY WERE REMOVED, & DRIVE SHAFT BEARING WERE REPLACED. DURING THE REMOVAL OR REINSTALLAT ION OF SHAFT OR BLOWER ASSY HEATER DUCT (HOSE) WHICH HAD BEEN REMVD FOR MAINT ACTION MUST HAVE BEEN SQUEEZED, OR SLIGHTL Y DEFORMED,&WHEN REINST, CLEARANCE BETWEEN SHAFT/COUPLING ADAPTER NOT OBTAINED. 1 G 7 1 3U 3 U H2SW E4CE 2002011700105 20020117 00105 CE 2002 1 17 CA011119002 1 20011029 G 2720 03101965 SPRING CESSNA 172 172N 2072434 CE LYC O320 O320H2AD 41508 EA MCAULY 1C160 1C160DTM GL RUDDER BROKEN W A UNSCHED LANDING D F INFLIGHT SEPARATION FLT CONT AFFECTED CR CRUISE 1 CA (CAN) SHORTLY AFTER TAKEOFF & DRING CRUISE EXCESSIVE LT RUDDER WAS AREQD TO KEEP A/C STRAIGHT. PILOT CALLED THUNDER BAY TOWER, & REPORTED RUDDER PROBLEMS & DIFFICULTY CNTLLING AIRCRAFT. PILOT REQED TO LAND WITH EMERG VEHICLES READY. A/C LAN DED SAFELY & TAXIED BACK TO COLLEGE HANGAR. ON MECHANICAL INVESTIGATION, IT FOUND THAT LT RUDDER SPRING HAD BROKEN AT TO RQUE TUBE END, & WAS HANGING OFF FRONT BRACKET END. (UNDER FLOOR AT PILOTS FEET) THE SPRING WAS CHANGED, RIGGING & RUDDE R TRAVEL WERE CHECKED, & A/C WAS RELEASED BACK TO SERVIC E.AGE OF SPRING COULD BE A CONTRIBUTING FACTOR IN THIS CASE AS THERE IS NOT A HIGH STRESS LOAD ON THIS PART. 1 H 7 1 3O 3 O NT 3A12 E274 5 N P910 2002011700107 20020117 00107 SW 2002 1 17 CA011119004 1 20011031 G 6210 407015001107 BLADE BELL 407 407 1182206 SW ALLSN 250C 250C47B GL MAIN ROTOR CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) DURING AIRFRAME PERIODIC INSP 3.5 INCH DIAGNAL CRACK ON LOWER SKIN OF SUBJECT BLADE FOUND AT BLADE STATION 71.0-73 .0.ATTEMPTS TO DRESS OUT CRACK WITH LIGHT SANDING REVEALED SUSPECT LACK OF FIBERGLASS MATTING USED IN CONSTRUCTION OF BL ADE TYPE. EVIDENCED BY FURTHER EXPLORATORY SANDING GOING THROUGH GEL ADHESIVE COATING & FILLER MATERIAL & ENDING AT HONE YCOMB CORE W/O 1ST ENCOUNTERING FIBERGLASS CLOTH MATTING. 1 G 7 1 3U 3 U O H2SW E1GL 2002011700112 20020117 00112 EU 2002 1 17 CA011120001 1 20011111 G 2434 9789601090 BRUSH HOLDER PILATS PC12 PC1245 7090551 EU PWA PT6 PT6A67B 52043 NE HARTZL HCE4A HCE4A3D GL GENERATOR WORN W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) DURING A 100 HOUR INSPECTION, THE BRUSH ASSEMBLY WAS REMOVED TO VERIFY THE CONDITION. THE BRUSH ASSEMBLY WAS WORN EXCESSIVELY, AND HAS BEEN REPLACED. 1 L 7 1 3T 4 T RT A78EU E26NE 5 C P210NE 2002021100010 20020211 00010 EU 2002 2 11 CA011120002 1 20011116 G 2750 9787320015 FCU PILATS PC12 PC1245 7090551 EU PWA PT6 PT6A67B 52043 NE HARTZL HCE4A HCE4A3D GL TE FLAPS MALFUNCTIONED W D RETURN TO BLOCK H ELECT. POWER LOSS-50 PC TX TAXI/GRND HDL 1 CA (CAN) THE PILOT REPORTED AN AMBER FLAPS LIGHT ON THE CAWS PANEL WHEN THE AIRCRAFT POWER WAS TURNED ON. THE AIRCRAFT WAS ON THE GROUND OUTSIDE FOR APPROXIMATELY THREE HOURS, OUTSIDE TEMPERATURE WAS -20C. ONCE TEH AIRCRAFT HAD BEEN WARMED U P IT WAS POSSIBLE TO CARRY OUT A FLAP RESET ON THE FLAP SYSTEM, AND THE SYSTEM FUNCTIONED NORMALLY AFTER THE RESET.THE F LAP CONTROL AND WARNING UNIT WAS REMOVED FROM THE AIRCRAFT AND PLACED IN A FREEZER FOR TWO HOURS, AFTER REMOVING THE UNI T FROM THE FREEZER AND RE-INSTALLING IT IN THE AIRCRAFT IT WAS POSSIBLE TO DUPLICATE THE SAME FAILURE AND RESET SENARIO. THE FCWU HAS BEEN REPLACED. 1 L 7 1 3T 4 T RT A78EU E26NE 5 C P210NE 2002011700113 20020117 00113 SW 2002 1 17 CA011120003 1 20011002 G 2720 12364 CABLE BBAVIA 8 8GCBC 1220803 SW LYC O360 O360C2E 41514 EA RUDDER FRAYED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) BOTH LT AND RT CABLES FRAYED JUST INCHES FWD OF BAGGAGE COMPARTMENT PULLEYS. 1 H 7 1 3O 3 O A21CE E286 2002011700117 20020117 00117 CE 2002 1 17 CA011120009 1 20010827 G 7120 04112816 MOUNT CESSNA 170 170A 2072304 CE CONT C145 C1452 17012 SO LT ENGINE CORRODED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) LT UPPER ENGINE MOUNT BRACKET AFT OF FIREWALL EXTREME CORROSION (HALF OF BRACKET MISSING) VERY DIFFICULT TO SEE DU E TO INSULATION COVERING ON FIREWALL. 1 H 7 1 3O 3 O A799 E253 2002011700118 20020117 00118 CE 2002 1 17 CA011120010 1 20011109 G 5610 5042006937 WINDSHIELD BEECH 100 B100 1152919 CE COCKPIT CRACKED W O OTHER O OTHER CR CRUISE 1 CA (CAN) WHILE AT CRUISE ALTITUDE THE NR 1 (PILOT'S) WINDSHIELD STARTED CRAZING AND CONTINUED PROGRESSIVELY UNTIL OUTWARD V ISION WAS SEVERELY IMPAIRED. CABIN PRESSURIZATION WAS LOWERED, WINDSHIELD HEAT WAS DISCONTINUED AND THE AIRCRAFT CONTINU ED ON TO DESTINATION. THE UNSERVICEABLE WINDSHIELD WAS REMOVED. A NEW WINDSHIELD WAS INSTALLED. THE AIRCRAFT WAS RETURNE D TO SERVICE. 1 L 7 2 4T A14CE 2002021100012 20020211 00012 CE 2002 2 11 CA011120011 1 20011115 G 5753 5016000310 RIB BEECH 100 A100 1152915 CE PWA PT6 PT6A28 EA HARTZL HCB3T HCB3TN3 GL TE FLAP CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 15323 15323 (CAN) WHILE CONDUCTING A PREFLIGHT INSPECTION A CRACK IN THE FLAP SKIN WAS DETECTED. THE CRACK WAS LOCATED AROUND THE FL AP ACTUATOR ATTACH BRACKET. FURTHER INVESTIGATION REVEALED THAT BOTH THE FLAP SKIN AND THE NOSE RIB OF THE LT I/B FLAP WERE CRACKED. FURTHER INVESTIGATION REVEALED THAT THE LT O/B FLAP WAS CRACKED IN THE SAME AREA BUT TO A LESSER DEGREE. THE NOSE RIBS IN BOTH THE LT INBOARD AND OUT BOARD ALONG WITH ASSOCIATED FLAP SKINS. 1 L 7 2 3T 4 T A14CE E4EA 6 C P15EA 2002011700120 20020117 00120 EA 2002 1 17 CA011120013 2 20011108 G 8520 LW1594470 CRANKSHAFT CESSNA 172 172N 2072434 CE LYC O320 O320H2AD 41508 EA ENGINE CORRODED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) CORROSION FOUND UNDERNEATH PROTECTIVE COATING APPLIED BY FACTORY AT OVERHAUL AS PER LYCOMING SB 505B AND 530A AND AD 98-02-08.CRANKSHAFT HAS BEEN RETURNED TO FACTORY FOR WARRANTY CONSIDERATION AND INSPECTION. 1 H 7 1 3O 3 O NT 3A12 E274 2002011700122 20020117 00122 NE 2002 1 17 CA011121001 2 20011004 G 8530 STUD AYRES S2 S2RNORMAL 7630202 SO PWA R1340 R1340AN1 52016 NE ENGINE SHEARED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) NR 1 AND 5 CYLINDERS BASE RETAINING STUDS SHEARED. 1 L 7 1 3R 3 R NC A3SW 5E2 2002021100015 20020211 00015 SO 2002 2 11 CA011121002 2 20011112 G 7322 S123019 CONTROL CABLE CESSNA 150 150J 2071820 CE CONT O200 O200A 17020 SO CARB HEAT BROKEN W O OTHER E VIBRATION/BUFFET AP APPROACH 1 CA (CAN) PILOT APPLIED CARB HEAT ON DOWNWIND AND KNOB SHAFT ASSEMBLY CAME OUT IN HER HAND. PUSH / PULL WIRE HAD BROKEN ABOU T 3 INCHES PAST THE END OF THE SHAFT. EXAMINATION OF THE BREAK INDICATED A LONG STANDING CRACK ABOUT 2/3 OF THE WAY THR OUGH THE WIRE. THERE ARE NO SHARP BENDS AT THIS POINT, THOUGH THE CABLE IS CURVED SOMEWHAT. NO EVIDENCE OF PREVIOUS TRAU MA TO THE WIRE.THE AIRCRAFT WAS LANDED IN NORMAL FASHION AND SHUT DOWN. 1 H 7 1 3O 3 O 3A19 E252 2002021100016 20020211 00016 GL 2002 2 11 CA011121004 2 20011109 G 7323 252476914 GOVERNOR BELL 206 206B 1181511 SW ALLSN 250C 250C20B 03013 GL ENGINE FAILED W A UNSCHED LANDING R J PARTIAL RPM/PWR LOSS WARNING INDICATION HO HOVERING 1 CA (CAN) THE HELICOPTER WAS INVOLVED IN FOREST INVENTORY WORK AT LOW ALTITUDE AT NEAR GROSS WEIGHT AT SLOW SPEED WHEN PILOT NOTICED HIS ROTOR RPM DROPING, LOW ROTOR WARNING AND AN INDICATION OF 95 PERCENT. HE MANAGED TO DROP COLLECTIVE AND LAN D IN A SMALL CLEARING.THE GOVERNOR WAS REPLACED, AIRCRAFT RUN-UP AND OPERATIONAL CHECKED, OK. 1 G 7 1 3U 3 U H2SW E4CE 2002011700124 20020117 00124 EA 2002 1 17 CA011121005 1 20011115 G 5320 C2FS3282A STRUT DHAV DHC2 DHC2MK1 2800102 EA PWA R985 R985AN14B 52008 NE WINDOW FRAME CORRODED W K NONE O OTHER IN INSP/MAINT 1 CA 14676 (CAN) THE AIRCRAFT WAS UNDERGOING SCHEDULED MAINTENANCE.THE RIGHT HAND WINDSHIELD WAS BEING REPLACED. THE RIGHT FRONT FU SELAGE STRUT ASSY WAS FOUND CORRODED UNDER THE WINDSHIELD SUPPORT ASSY. THIS STRUT ASSY WAS EXAMINED IN ACCORDANCE WITH CF-98-37R1 IN FEBRUARY OF THIS YEAR. THE AREA CORRODED IS NOT ACCESSIBLE UNLESS THE WINDSHIELD IS REMOVED. 1 H 7 1 3R 3 R A806 5E1 2002011700129 20020117 00129 SO 2002 1 17 CA011121008 1 20011116 G 3230 401195 BOLT PIPER PA42 PA42720 7104212 SO PWA PT6 PT6A61 52043 EA MLG BROKEN W O OTHER R J PARTIAL RPM/PWR LOSS WARNING INDICATION LD LANDING 1 CA (CAN) FLT CREW WERE UNABLE TO EXTEND LT MLG THROUGH NORMAL (HYDRAULIC) OR EMERG (HYDRAULIC/PNEUMATIC) MEANS PRIOR TO LDG . LOSS OF HYDRAULIC FLUID EVIDENT AROUND TRAILING EDGE OF LT WING & FLAP AREAS. NOSE & RT MLG WERE RETRACTED & A/C MADE SUCCESSFUL GEAR UP LDG. INVESTIGATION. DETERMINED LT MLG ACTUATING CYLINDER TOP BOLT HAD BROKEN. ALLOWED CYLINDER TO SLI DE DOWN RAM WHEN GEAR INITIALLY SELECTED DOWN, INSTEAD OF RAM RETRACTING INTO STATIONARY CYLINDER. CYLINDER MOVEMENT BRO KE LOWER FITTING THAT IS COMMON TO BOTH HYDRAULIC&PNEUMATIC SYS PRESSURES, RESULTING IN OVERBOARD LOSS OF HYDRAULIC FLUI D A ND ANY PENUMATIC PRESSURE: 1 L 7 2 4T 4 T A23SO E4EA 2002011700130 20020117 00130 SO 2002 1 17 CA011121009 1 20011116 G 3230 668346 WIRE HARNESS PIPER PA42 PA42720 7104212 SO PWA PT6 PT6A61 52043 EA MLG DISCONNECTED W H DEACTIVATE SYST/CIRCUITS R L PARTIAL RPM/PWR LOSS NO TEST LD LANDING 1 CA (CAN) PILOT ACTIVATED LDG GEAR EMERG BLOWDOWN PNEUMATIC SYS SWITCH DURING LDG GEAR EXTENSION MFLFUNCTION. LATER GROUND I NSP DETERMINED THAT PENUMATIC SYS (LT MLG) HAD NOT PROPERLY ACTIVATED. SYS SHOULD HAVE FIRED T HE NITROGEN BOTTLE EXPLOS IVE SQUIB (ON LDG GEAR NOT DOWN & LOCKED) WHEN 28 VOLTS WERE APPLIED BY PUSHING EMERG GEAR EXTENTION SWITCH. VOLTAGE CHE CK CONDUCTED AT L/H SQUIB CONNECTOR SHOWED ONLY 0 TO 4 VOLTS WHEN SWITCH ACTIVATED&GEAR UNLOCKED. TROUBLESHOOTING DISCOV ERED WIRE LEADING FROM SWITCH TO BE ATTACHED BY ONLY ONE OR 2 STRANDS&PROTECTIVE HEAT SHRINK (VISUALLY NORMAL BUT DISCON NECTED IMMEDIATELY UPON TOUCHING WIRE). 1 L 7 2 4T 4 T A23SO E4EA 2002011700131 20020117 00131 SO 2002 1 17 CA011121013 1 20011112 G 3222 6531904 CYLINDER PIPER PA28 PA28140 7102802 SO LYC O320 O320E3D 41508 EA TORQUE LINK FAILED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) - UPON INSPECTION OF AIRCRAFT FOR A REPORTED HARD LANDING TORQUE LINK LUGS FOUND TO HAVE FAILED (UPPER).- UPON REM OVAL IT APPEARS OUTBOARD LUG TO HAVE BEEN CRACKED FOR SOMETIME. INBOARD LUG HAD A SMALL CRACK ALSO ABOUT 20 PERCENT OR A REA. - AREA COVERED BY FAIRING, TO INSPECT FAIRING HAS TO BE REMOVED.- S.L. 760 COVERS INSPECTION OF THIS AREA.OLEO CYLI NDER P/N 65319-04 HAS BEEN SUPERCEDED BY 65490-00. 1 L 7 1 3O 3 O 2A13 E274 2002021100028 20020211 00028 SO 2002 2 11 CA011121014 1 20011119 G 3260 1459500001 DOWNLOCK SWITCH EMB 110 EMB110P1 3260122 SO PWA PT6 PT6A34 52043 EA LT MLG FAILED W O OTHER O OTHER LD LANDING 1 CA (CAN) DURING DESCENT INTO YMO THE CREW SELECTED GEAR DOWN AND DID NOT GET A LT MAIN GEAR DOWN AND LOCKED INDICATION. THE LANDING GEAR WAS CYCLED A FEW TIMES AND GEAR DOWN AND LOCKED WAS CONFIRMED WITH INDICATION OF DOWN AND LOCKED. AS A PRE CAUTION THE CREW ELECTED TO RETURN AND DECLARE AN EMERGENCY. THE CREW SUBSEQUENTIALLY PERFORMED AN UNEVENTFUL LANDING. U PON INVESTIGATION BY MAINTENANCE PERSONNEL IT WAS DETERMINED THAT THE LT DOWNLOCK SWITCH PLUNGER HAD FAILED. THE DOWNLOC K WAS REPLACED AND GEAR SWINGS COMPLETED SERVICEABLE. THE AIRCRAFT WAS RELEASED FOR RETURN TO SERVICE. 1 L 7 2 4T 4 T A21SO E4EA 2002011700137 20020117 00137 CE 2002 1 17 CA011122006 1 20011120 G 3260 41EN16 SWITCH BEECH 99 99A 1154003 CE PWA PT6 PT6A28 EA MLG INTERMITTENT W A UNSCHED LANDING N FALSE WARNING CL CLIMB 1 CA (CAN) AIRCRAFT DEPARTED AIRPORT AND COULD NOT RETRACT GEAR. AIRCRAFT DEVERTED TO HOME BASE AND LANDED WITHOUT INCIDENT. THE SAFETY SWITCH WAS FOUND INTERMITTTANT ON THE RIGHT HAND GEAR TORQUE KNEES.SWITCH WAS REPLACED AND AIRCRAFT RETURNED TO SERVICE. NOTE: PART TIME IS UNKNOWN 1 L 7 2 3T 4 T A14CE E4EA 2002011800002 20020118 00002 2002 1 18 CA011123001 4 20011116 G 6113 055032110 PLATE CESSNA 05503671 CESSNA 172 172S 2072439 CE LYC IO360 IO360L2A EA MCAULY 1A170 1A170E GL PROP SPINNER BROKEN W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) THE CORNER SECTION OF SPINNER AT LEADING EDGE OF PROPELLER BLADE CUT-OUT BADLY BENT (PEELED BACK) BY CENTRIFUGAL F ORCE. THIS WAS CAUSED BY THE ADJACENT CORNER SECTION OF THE BACKPLATE (AROUND ANCHOR NUT) BREAKING OFF DURING OPERATION. CESSNA HAS RECOGNIZED THIS PROBLEM AND ISSUED MOD KIT MK172-61-01 UNDER SB01-61-01. NEW BACKPLATE DESIGN AND P/N INCORP ORATED AS PER LISTED KIT AND SB NUMBERS. 1 H 7 1 3O 3 O NT 3A12 1E10 5 N P857 2002021100077 20020211 00077 EU 2002 2 11 CA011126001 1 20011122 G 6320 4638302023 BEARING BOLKMS 105 BO105CBS 5626008 EU ALLSN 250C 250C20B 03013 GL M/R GEARBOX DAMAGED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) OUTER AND INNER RACE OF BEARING DISPLAY MODERATE PITTING AND PEELING.ONE BALL DISPLAYS HEAVY PITTING 1 G 7 2 3U 3 U NC H3EU E4CE 2002011800005 20020118 00005 GL 2002 1 18 CA011126002 2 20011123 G 7250 6006T87G13 NOZZLE GE CT58 CT58* 30011 GL ENGINE CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) THE BAFFLE OF THE 3RD STAGE NOZZLE WAS REMOVED TO INVESTIGATE THE CAUSE OF AIR LEAKAGE. VISUAL AND NDT INSPECTION REVEALED CRACKS IN THE SHEET METAL OF THE SUMP ABOVE THE AIR TUBE LOCATION.TELCON WITH GE ON NOV. 21 REGARDING THE CRAC KS AND THE LACK OF REPAIRABLE OR SERVICEABLE LIMITS IN THIS AREA. THE PARTS HAVE BEEN FORWARDED TO GE FOR THEIR INVESTI GATION. 4 OF 5 NOZZLES CHECKED HAD SIMILAR CRACKS. 4 U 1E3 2002021100078 20020211 00078 CE 2002 2 11 CA011126003 1 20011010 G 5552 1156200219 HINGE BEECH BEECH 99 99 1154002 CE PWA PT6 PT6A27 52043 EA LT ELEVATOR CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 39106 39106 (CAN) DURING ROUTINE INSPECTION, CRACK WAS FOUND ON ELEVATOR HINGE. PART WAS REPLACED AND AIRCRAFT RETURNED TO SERVICE. PART AVAILABLE FOR INSPECTION IN QUARANTINE.PART TSO/TSN/CYCLES ARE AIRCRAFT FIGURES. 1 L 7 2 3T 4 T A14CE E4EA 2002021100082 20020211 00082 SW 2002 2 11 CA011127001 1 20011113 G 6310 CL422501 CLUTCH BELL 20604023013 BELL 206 206B 1181511 SW ALLSN 250C 250C20B 03013 GL FREEWHEEL UNIT BROKEN W K NONE K FLUID LOSS IN INSP/MAINT 1 CA B12468 (CAN) FREEWHEEL UNIT SENT IN FOR REPAIR OWNER REPORTS: LEAKING AND ROUGH TO TURN ONCE REMOVED. FREEWHEEL DISASSEMBLED AN D CLUTCH CAGE FOUND CRACKED AND A PIECE BROKEN OFF. THE INNER RACE AND OUTER RACE BOTH FOUND WORN BEYOND LIMITS. BELL HE LICOPTER PRODUCT SUPPORT TECH REP CONTACTED AND HE WILL BE HERE THURSDAY NOVEMBER 15, 2001 TO VIEW THE DAMAGED UNIT. 1 G 7 1 3U 3 U H2SW E4CE 2002011800006 20020118 00006 EA 2002 1 18 CA011127002 2 20010927 G 7414 4771 MAGNETO CESSNA 172 172P 2072436 CE LYC O320 O320D2J 41508 EA MCAULY 1C160 1C160DTM GL ENGINE FAILED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) ON LANDING ROLL PILOTS REPORTED A GRINDING NOISE FROM THE ENGINE. - THEY TAXIED OFF THE RUNWAY AND SHUT DOWN. AIRC RAFT PUSHED TO HANGAR.- INITIAL INVESTIGATION SHOWED DEAD LT MAGNETO (TIMING INDICATOR). - MAGNETO REMOVED, SHAFT BENT A ND GEAR GROUND BY ENGINE DRIVE GEAR. 1 H 7 1 3O 3 O NT 3A12 E274 5 N P910 2002011800007 20020118 00007 GL 2002 1 18 CA011127004 2 20011115 G 7250 6898731 SUPPORT BELL 206 206B 1181511 SW ALLSN 250C 250C20 03013 GL ENGINE LEAKING W E A ENGINE SHUTDOWN UNSCHED LANDING B SMOKE/FUMES/ODORS/SPARKS NR NOT REPORTED 1 CA (CAN) TURBINE ASSY WAS RECD IN FOR SMOKING ON SHUTDOWN. SMOKING WAS ENCOUNTERED APPROX 7 2NDS AFTER THROTTLE WAS ROLLED TO OFF POS.UPON DISASSY & INSPECTION OF PT SUPPORT IT FOUND THAT INNER DIAMETER (DIA.S) SHOULDER WIDTH WAS INSUFFICIENT FOR PROPER SEALING OF U-RING GASKET. AS A RESULT, THERE WAS A LOSS OF LABYRINTH SEAL PRESSURE & AN INCREASE IN AIR PRESS URE WITHIN POWER TURBINE SUPPORT OIL SUMP, ALLOWING OIL FROM 6 & 7 BEARING AREA TO ENTER GAS PATH. NOTE: SHOULDER WIDTH OF INNER DIAMETER SHOULD BE INSP TO ENSURE SUFFICIENT SURFACEAREA EXISTS FOR PROPER SEALING OF U-RING GASKET (PRINT DIM. FOR SHOULDER WIDTH UNAVAILABLE).P/N 6898731;S/N MK18387 1 G 7 1 3U 3 U H2SW E4CE 2002021200002 20020212 00002 SW 2002 2 12 CA011127005 1 20011116 G 2750 B10006 COUPLING AIRTRC AT802 AT802 0390305 SW FLAP DRIVE SPLIT W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) DURING ANNUAL INSPECTION THE FLAP DRIVE RUBBER COUPLING WAS FOUND TO BE SPLIT, EARLIER IN THE OPERATING SEASON A L OOSE WIRE ON THE FLAPS DOWN SWITCH CAUSED THE FLAPS TO OVERTRAVEL AND BOTTOM OUT THE ACTUATOR. EXPERIENCE HAS SHOWN THAT WHEN THIS SITUATION HAPPENS, THE RUBBER COUPLING IS DAMAGED FROM THE SUDDEN STOPPAGE. THE RUBBER COUPLING SHOULD BE INS PECTED ANY TIME AN OVERTRAVEL IS EXPERIENCED. 1 L 7 1 3T NC A19SW 2002021200003 20020212 00003 CE 2002 2 12 CA011127006 1 20011126 G 5730 SKIN BEECH 90 C90 1152913 CE PWA PT6 PT6A21 52043 EA LT WING CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) ON A RECENT ROUTINE INSPECTION ON LJ886 A CRACK WAS FOUND ON THE LT UPPER WING SKIN AT STA 175 AND WL 81 SEEN FROM THE UNDERSIDE IN THE WHEELWELL. THE AFT NACELLE FAIRING WAS REMOVED AND ANOTHER CRACK WAS FOUND AT STA 182 AND WL70.TH E AFT NACELLE FAIRING OF THE RT WING WAS REMOVED AND SUBSEQUENTLY TWO MORE CRACKS IN THE SAME LOCATIONS DESCRIBED ON THE LT WING WERE FOUND. 1 L 7 2 3T 4 T 3A20 E4EA 2002011800008 20020118 00008 EU 2002 1 18 CA011127009 1 20011022 G 2434 5243212137 DRIVE SHAFT PILATS PC12 PC1245 7090551 EU PWA PT6 PT6A67B 52043 NE HARTZL HCE4A HCE4A3D GL NR 2 GENERATOR WORN W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) WHILE CARRYING OUT REPLACEMENT OF GEN 2 DRIVE ASSY OUTER BEARING FOR 3000 HR REQUIREMENTS, IT WAS NOTED THAT THE D RIVE SHAFT WAS WORN AT THE BEARING JOURNAL AND THE BEARING WAS LOOSE ON THE SHAFT. THE DRIVE SHAFT HAD TO BE REPLACED. 1 L 7 1 3T 4 T RT A78EU E26NE 5 C P210NE 2002021200004 20020212 00004 EU 2002 2 12 CA011127010 1 20011120 G 2497 350A311851 STRAP SNIAS 350 AS350B2 8680813 EU ELECTRICAL FRAYED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) THREE BONDING STRAPS ARE FRAYED HALFWAY THROUGH. 1 G 7 1 3U H9EU 2002021200005 20020212 00005 CE 2002 2 12 CA011127011 1 20011120 G 5343 36653RH FITTING CESSNA 180 180J 2072622 CE CONT O470 O470S 17026 SO MCAULY 2A34C 2A34C203 GL FUSELAGE CORRODED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) INTERGRANULAR CORROSION ON FUSELAGE FITTING. 1 H 7 1 3O 3 O 5A6 E273 5 C P3EA 2002021200006 20020212 00006 EU 2002 2 12 CA011127012 1 20011120 G 2750 9740338111 CONTACTOR PILATS PC12 PC1245 7090551 EU PWA PT6 PT6A67B 52043 NE HARTZL HCE4A HCE4A3D GL TE FLAP PDU SHORTED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) WHILE LOWERING THE FLAPS DURING ROUTINE MAINTENANCE, THE FLAP POWER DRIVE UNIT (PDU )WAS LABOURING. THE FLAP DRIVE SHAFTS WERE DISCONNECTED AT THE PDU, BUT THE PDU WAS STILL LABOURING. THE PDU WAS REPLACED, BUT THE CONDITION STILL P ERSISTED. THE K670 CONTACTOR WAS REPLACED AND THE PDU OPERATED NORMALLY. THE SUSPECT K670 CONTACTOR WAS TAKEN APART AND DISCOVERED THAT THE CONTACTS WERE BADLY BURNED. 1 L 7 1 3T 4 T RT A78EU E26NE 5 C P210NE 2002021200024 20020212 00024 EA 2002 2 12 CA011128008 1 20010722 G 2432 CELL MARATHON MA300H DHAV DHC6 DHC6300 2802606 EA PWA PT6 PT6A27 52043 EA BATTERY DEFORMED W H DEACTIVATE SYST/CIRCUITS B H M SMOKE/FUMES/ODORS/SPARKS ELECT. POWER LOSS-50 PC OVER TEMP TX TAXI/GRND HDL 1 CA 9802292 (CAN) SMOKE WAS VISIBLE IN THE BAGGAGE COMPARTMENT WHEN OPENED ON THE RAMP. ONE CELL WITHIN THE BATTERY WAS FOUND TO BE DEFORMED FROM HEAT. 1 H 7 2 3T 4 T RT A9EA E4EA 2002021200028 20020212 00028 CE 2002 2 12 CA011128016 1 20011030 G 5411 90120003 ANGLE BEECH 90 C90A 1152911 CE PWA PT6 PT6A21 52043 EA LT & RT NACELLE CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) INSIDE LT AND RT MAIN LANDING GEAR WELLS, OUTBOARD SIDE WALL, ANGLE AT CORNER OF SIDE WALL AND FORWARD FACE OF MAI N SPAR WEB, LOWER END OF ANGLE. POSSIBLE NEED TO REMOVE PAINT TO NOTE CRACK. BOTH CRACKS APPROX. .75 INCHES IN LENGTH. 1 L 7 2 3T 4 T RT 3A20 E4EA 2002021200054 20020212 00054 CE 2002 2 12 CA011128017 1 20011114 G 3500 503800573 HOSE BEECH 100 A100 1152915 CE PWA PT6 PT6A28 EA OXYGEN SYS BROKEN W B EMER. DESCENT O OTHER CR CRUISE 1 CA (CAN) HOSE BROKE CAUSING LOSS OF PRESSURIZATION, REPLACED HOSE AND FLIGHT TESTED SERVICEABLE. 1 L 7 2 3T 4 T A14CE E4EA 2002021200055 20020212 00055 SO 2002 2 12 CA011128018 1 20011120 G 2910 4083300 LINE PIPER PA31 PA31350 7103110 SO LYC O540 TIO540J2BD 41532 EA HYD POWERPACK BROKEN W O OTHER J WARNING INDICATION AP APPROACH 1 CA (CAN) ON APPROACH PILOT SELECTED GEAR DOWN WITH NO INDICATION OF ANY MOVEMENT OF THE GEAR. MANUALLY HAND PUMPED GEAR WI TH NO SUCCESS. AFTER SEVERAL ATTEMPTS AND BURNING OFF EXCESS FUEL MADE A GEAR UP LANDING WITH NO DIFFICULTY. ON INSPECT ION FOUND THE GEAR DOWN LINE AT THE POWER PACK BROKEN AT THE FLARE. REPAIRED LINE INSTALLED AND GEAR FUNCTIONED NORMALLY AFTER FILLING WITH FLUID. 1 L 7 2 3O 3 O A20SO E14EA 2002021200056 20020212 00056 SW 2002 2 12 CA011130001 1 20011108 G 2750 12395 PULLEY BBAVIA 8 8GCBC 1220803 SW LYC O360 O360C2E 41514 EA TE FLAPS SEIZED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) - LT & RT PULLEYS AT WING ROOT FOUND SEIZED AND WORN. - BOTH FLAP CABLES FRAYED AT THAT POSITION. - SMALL ALUMINUM PULLEYS, HARD TO LUBRICATED AND PROVIDE A TIGHT DEFLECTING RADIUS FOR CABLES. 1 H 7 1 3O 3 O A21CE E286 2002021200057 20020212 00057 SW 2002 2 12 CA011130002 1 20011108 G 2750 19023 CONTROL CABLE BBAVIA 8 8GCBC 1220803 SW LYC O360 O360C2E 41514 EA TE FLAPS FRAYED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) - LT & RT UPPER FLAP CABLES FRAYED AT WING ROOT PULLEYS. BOTH LT & RT PULLEYS FOUND SEIZED AND WORN. 1 H 7 1 3O 3 O A21CE E286 2002021200058 20020212 00058 SW 2002 2 12 CA011130003 1 20011109 G 2750 12395 PULLEY BBAVIA 8 8GCBC 1220803 SW LYC O360 O360C2E 41514 EA TE FLAPS SEIZED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) LT & RT PULLEYS AT WING ROOT FOUND SEIZED AND WORN. BOTH FLAP CABLES FRAYED AT SAME LOCATION. 1 H 7 1 3O 3 O A21CE E286 2002021200059 20020212 00059 SW 2002 2 12 CA011130004 1 20011109 G 2750 19023 CONTROL CABLE BBAVIA 8 8GCBC 1220803 SW LYC O360 O360C2E 41514 EA TE FLAPS FRAYED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) - LT & RT UPPER FLAP CABLES FRAYED AT WING ROOT PULLEYS. BOTH LT & RT PULLEYS FOUND SEIZED AND WORN. 1 H 7 1 3O 3 O A21CE E286 2002021200060 20020212 00060 SW 2002 2 12 CA011130005 1 20011109 G 2810 714941R FUEL TANK BBAVIA 8 8GCBC 1220803 SW LYC O360 O360C2E 41514 EA RT OUTBOARD CRACKED W K NONE K FLUID LOSS IN INSP/MAINT 1 CA (CAN) RT OUTBOARD TANK CRACKED, LOWER SIDE, AT THE END OF REINFORCING INDENT, ON PREVIOUSLY REPAIRED WELD. 1 H 7 1 3O 3 O A21CE E286 2002021200061 20020212 00061 SW 2002 2 12 CA011130006 1 20011124 G 6500 407340339103 BEARING BELL 407040303101 BELL 407 407 1182206 SW ALLSN 250C 250C47B GL FAN SHAFT FAILED W A UNSCHED LANDING E J VIBRATION/BUFFET WARNING INDICATION CR CRUISE 1 CA (CAN) WHILE ON 5TH SCENIC TOUR OF DAY, AT 2,500 FT ASL IN QUIET MODE CRUISE, A/C SOUND & VIBRATION LEVEL SUDDENLY CHANGE D FROM NORMAL TO LOUD WITH HEAVY VIBRATION FROM TAIL ROTOR DRIVE AREA. PILOT IMMEDIATELY RETURNED A/C TO NORMAL MODE CR UISE RPM & EXITED SCENIC ROUTE. HE RETURNED DIRECTLY TO MAIN BASE AT PQ3 WITH PRECAUTIONARY LDG & SHUTDOWN WITHOUT FURTH ER INCIDENT. TAIL ROTOR CONTROL AUTHORITY NEVER LOST. AFTER ENGINE SHUTDOWN, INSPECTION REVEALED A COMPLETELY FAILED FW D FAN SHAFT BEARING WITH DISINTEGRATED BEARING CAGE. 1 G 7 1 3U 3 U O H2SW E1GL 2002021200064 20020212 00064 SO 2002 2 12 CA011130012 1 20011121 G 3260 487312 SPRING PIPER PIPER PA23 PA23250 7102308 SO LYC O540 IO540C4B5 41532 EA DOWNLOCK BROKEN W L ABORTED APPROACH J WARNING INDICATION AP APPROACH 1 CA (CAN) - RIGHT HAND MAIN LANDING GEAR INDICATION FAILED IN FLIGHT. - PILOT RECYCLED GEAR AND LIGHT APPEARED TO WORK. - IN SPECTION REVEALED A BROKEN DOWNLOCK SPRING. 1 L 7 2 3O 3 O 1A10 1E4 2002021200065 20020212 00065 CE 2002 2 12 CA011130014 1 20011121 G 7820 04504004 MUFFLER CESSNA 150 150M 2071830 CE CONT O200 O200A 17020 SO ENG EXHAUST CRACKED W A UNSCHED LANDING O OTHER CR CRUISE 1 CA (CAN) A NOISE WAS HEARD IN CRUISE. MUFFLER FOUND CRACKED BEFORE RISER. 1 H 7 1 3O 3 O 3A19 E252 2002021200069 20020212 00069 EA 2002 2 12 CA011203001 2 20011127 G 7414 1068291013 CASE BENDIX 1068291013 PIPER PA31 PA31350 7103110 SO LYC O540 TIO540J2BD 41532 EA MAGNETO BROKEN W K NONE O OTHER IN INSP/MAINT 1 CA 85410122T (CAN) CASE FLANGE BROKEN UNDER UPPER RETAINER. 1 L 7 2 3O 3 O A20SO E14EA 2002021200072 20020212 00072 EU 2002 2 12 CA011203005 1 20011203 G 6320 461920400146382 BEARING BOLKMS 105 BO105CBS 5626008 EU ALLSN 250C 250C20B 03013 GL M/R GEAR BOX PEELING W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) BOTH THE PLANETARY AXLE AND ROLLER BEARING PLATING PEELING. 1 G 7 2 3U 3 U NC H3EU E4CE 2002021200074 20020212 00074 SW 2002 2 12 CA011205001 1 20011204 G 5712 21588 RIB BBAVIA 8 8GCBC 1220803 SW LYC O360 O360C2E 41514 EA LT WING CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) 3 RIBS RT, 2 RIBS LT WING FOUND CRACKED AT UPPER CORNER OF FLANGE WHERE RIB ATTACHES TO REAR SPAR. ALL RIBS LOCA TED CLOSEST INBOARD AT WING ROOT, AND ALL RIBS CRACKED EXACTLY THE SAME. 1 H 7 1 3O 3 O A21CE E286 2002021200104 20020212 00104 CE 2002 2 12 CA011205003 1 20011204 G 5744 0523921 BUSHING CESSNA 0523919 CESSNA 180 180J 2072622 CE CONT O470 O470S 17026 SO TE FLAP SUPPORT CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) WHILE PREFORMING A FLAP SUPPORT INSPECTION, A CRACK WAS FOUND ON THE FLAP ROLLER BUSHING (LT REAR). THE CYLINDRIC AL BUSHING WAS SPLIT IN HALF AND ONLY BECAME APPARENT WHEN THE BUSHING WAS REMOVED FROM THE FLAP ROLLER ASSEMBLY. 1 H 7 1 3O 3 O 5A6 E273 2002021200105 20020212 00105 CE 2002 2 12 CA011205004 1 20011204 G 2720 05121602 BRACKET CESSNA 180 180J 2072622 CE CONT O470 O470S 17026 SO CABLE PULLEY CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) DURING A ROUTINE 100 HOUR INSPECTION THE RUDDER CABLE PULLEY BRACKETS THAT ARE LOCATED AT THE BATTERY BOX BULKHEAD , WERE BOTH FOUND TO BE CRACKED AT THE TOP ATTACH POINT (RIVET). BOTH BRACKETS WERE REPLACED. 1 H 7 1 3O 3 O 5A6 E273 2002021200106 20020212 00106 EA 2002 2 12 CA011205005 1 20011204 G 3250 C2UT473 TORQUE TUBE DHAV DHC2 DHC2MK1 2800102 EA PWA R985 R985AN14B 52008 NE TAIL WHEEL CRACKED W D RETURN TO BLOCK O OTHER TX TAXI/GRND HDL 1 CA (CAN) INVESTIGATION REVEALED A SHEARED TAIL WHEEL STEERING TORQUE TUBE ASSEMBLY (WATER RUDDER). INTERNAL CORROSION WAS PRESENT INSIDE THE TUBE ASSEMBLY. NO ABNORMAL CONDITION PRESENT ON THE EXTERNAL PORTION OF THE TUBE.THE TORQUE TUBE FAIL URE TOOK PLACE AT THE WELDED JUNCTION OF THE SPLINE SHAFT AND TUBE ASSEMBLY. 1 H 7 1 3R 3 R A806 5E1 2002021200107 20020212 00107 EA 2002 2 12 CA011205006 1 20011115 G 6123 CONTROL UNIT DHAV DHC8 DHC8311 1386006 EA PWA PW120 PW123 NE HAMSTD 14SF 14SF15 NE NR 2 ENGINE MALFUNCTIONED W H A DEACTIVATE SYST/CIRCUITS UNSCHED LANDING E J VIBRATION/BUFFET WARNING INDICATION CL CLIMB 1 CA (CAN) PRIOR TO TAKE-OFF, AUTOFEATHER ARMING BAULKED, ACTIVATED ON RE-SELECTION. ON TAKE-OFF, AFTER GEAR UP SELECTION , NR 2 ENGINE INITIATED UNCOMMANDED AUTOFEATHER (TORQUE 125 PERCENT PLUS). CREW DE-SELECTED AUTOFEATHER WITHIN FOUR SECO NDS, TORQUE RETURNED TO NORMAL. AIRCRAFT RETURNED TO BASE, AND ENGINE / PROP CHANGE CARRIED OUT. ENGINE TORQUE PROBE, HA RNESS AND TSCU SHIPPED TO OEM FOR ANALYSIS, 2 H 7 2 4T 4 T RT A13NM E20NE 6 C P7NE 2002021200108 20020212 00108 EU 2002 2 12 CA011207002 1 20011207 G 7170 6859172 TUBE BOLKMS 105 BO105C 5626005 EU ALLSN 250C 250C20B 03013 GL FUEL DRAIN CHAFED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) DRAIN LINE CHAFING ON FUEL CONTROL TO FUEL PUMP BY PASS TUBE IS 99 PERCENT CHAFED. 1 G 7 2 3U 3 U H3EU E4CE 2002021200114 20020212 00114 EU 2002 2 12 CA011207004 1 20011022 G 2920 MVT1001 SELECTOR VALVE AIRBUS 330 A330342 EU RROYCE RB211 RB211TRENT77 NE HYD SYSTEM CRACKED W K NONE K FLUID LOSS IN INSP/MAINT 1 CA (CAN) THE AIRCRAFT ARRIVED TO YYZ, WITH THE "YELLOW" HYDRAULIC SYSTEM EMPTY. FOUND RT ELEVATOR, OUTBOARD SERVO (F.I. N.3CS2) SELECTOR VALVE HOUSING CRACKED. 1 L 7 2 4F 4 F RT A46NM E39NE 2002021200118 20020212 00118 EU 2002 2 12 CA011209002 1 20011129 G 3251 C247820001 SOLENOID VALVE C248560014 AIRBUS 330 A330342 EU RROYCE RB211 RB211TRENT77 NE NLG STEERING BROKEN W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) DURING DEACTIVATION OF THE NOSE LANDING GEAR STEERING SYSTEM, THE NOSE WHEELS TURNED 90 DEGREES RIGHT WITHOUT ANY STEERING INPUT WHEN STEERING / ANTI-SKID SWITCH WAS TURNED OFF. AT THAT MOMENT THE THE AIRCRAFT CONDITION WAS:-STEERING BY-PASS PIN INSTALLED IN TOW POSITION.-BOTH ENGINE MASTER SWITCH OFF. -GREEN ELECTRICAL HYDRAULIC PUMP ON.-UPON REMOVING AND OPENING THE SOLENOID VALVE ASSY , WE DISCOVERED THAT THE LINER (MADE OF ALUMINIUM ALLOY) WAS BROKEN (SHEARED). 1 L 7 2 4F 4 F RT A46NM E39NE 2002021200131 20020212 00131 CE 2002 2 12 CA011210009 1 20011029 G 7170 A1090 DRAIN VALVE BEECH 99 99 1154002 CE PWA PT6 PT6A20 52043 EA RT ENGINE BROKEN W O OTHER K J FLUID LOSS WARNING INDICATION CR CRUISE 1 CA (CAN) DURING THE LATTER PART OF A FLIGHT THE RT NACELLE WAS SHOWING A DECLINE IN DUEL CAPACITY ABOVE NORMAL. WHEN REACHI NG THE DESTINATION IT WAS DISCOVERED THAT FUEL WAS ESCAPING FROM THE RT FUEL MANIFOLD DRAIN. UPON FURTHER INVESTIGATION IT WAS FOUND THAT THE CENTRE PORTION OF THE DRAIN VALVE HAD BROKEN OFF AND FALLEN OUT. 1 L 7 2 3T 3 T A14CE E4EA 2002021200133 20020212 00133 GL 2002 2 12 CA011210010 2 20011130 G 7323 DRIVE SHAFT ALIDSG 252476914 BELL 206 206B 1181511 SW ALLSN 250C 250C20B 03013 GL GOVERNOR DAMAGED W K NONE W INADEQUATE Q C IN INSP/MAINT 1 CA 17611 (CAN) PILOT REPORTED IN NORMAL LEVEL CRUISE FLIGHT AT LOW TO MEDIUM TORQUE SETTING. HE FELT, HEARD AND NOTICED A POWER S URGE AND GAUGE FLUCTUATION APPROX. 2 PERCENT N1. THIS WOULD OCCUR FOR JUST A SECOND AND WOULD ONLY OCCASIONALLY HAPPEN 1 TIME OR SEVEERAL TIMES IN A 1 HOUR PERIOD. THE A/C RETURNED BACK TO BASE AFTER COMPLETING HIS WORK AND WAS DUE FOR 100 HR INSPECTION, THE GOVERNOR WAS REMOVED FOR INSPECTION AND THE DRIVE END AND CIRCLIP WERE FOUND LOOSE AND READY TO FALL OFF. THIS GOVERNOR HAS BEEN REMOVED 3 PREVIOUS TIMES FOR SURGING, DROOPING AND THE LAST TIME FOR THE DRIVESHAFT END FAI LURE. 1 G 7 1 3U 3 U H2SW E4CE 2002021200134 20020212 00134 NE 2002 2 12 CA011210012 2 20011126 G 8520 CONNECTING ROD DHAV DHC2 DHC2MK1 2800102 EA PWA R985 R985AN14B 52008 NE ENGINE FAILED W A UNSCHED LANDING E Y VIBRATION/BUFFET ENGINE STOPPAGE CR CRUISE 1 CA (CAN) THE A/C WAS ESTABLISHED IN CRUISE WHEN THE PILOT NOTICED ENGINE VIBRATION FOR APPROXIMATELY 5 SECONDS. THIS WAS FO LLOWED BY AN ABRUPT ENGINE STOPPAGE. THE PILOT SAFELY GLIDED TIME A/C TO A NEARBY RIVER. UPON ENGINE TEARDOWN THE NR 1 & 2 CONNECTING RODS WERE BROKEN & THE NR 1 WRIST PIN BENT. 1 H 7 1 3R 3 R A806 5E1 2002021200136 20020212 00136 CE 2002 2 12 CA011210013 1 20011122 G 3397 20GAUGE WIRE CESSNA 208 208B 2073701 CE PWA PT6 PT6A114A 52043 NE MCAULY 3AF34C 3GFR34C703 GL EXTERIOR LIGHTS SHORTED W O OTHER H ELECT. POWER LOSS-50 PC NR NOT REPORTED 1 CA (CAN) NAV. LIGHT CIRCUIT BREAKER WAS FOUND POPPED THE WIRES TO THE LIGHT IN THE TAIL CONE WERE SHORTED TOGETHER. THESE 2 WIRES SHORTED PORTION WERE REMOVED AND THE WIRES SPLICED TOGETHER. THERE ARE TIE-WRAPS HOLDING THE WIRES TO THE SIDE OF THE TAIL CONE. 1 H 7 1 3T 3 T A37CE E4EA 5 C P60GL 2002021200146 20020212 00146 SW 2002 2 12 CA011210017 1 20011203 G 5532 410008173 SKIN GULSTM 690TP 690A 0141722 SW GARRTT TPE331 TPE3315251K NM VERTICAL STAB CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) DURING INSPECTION OF THE AIRCRAFT, CRACKS WERE NOTED ON THE VERTICAL STABILIZER SKIN. THE CRACKS WERE LOCATED A T THE FIRST FASTENER ABOVE THE DOUBLER AT THE CENTRE SPAR. THE LONGEST CRACK MEASURED .75 INCHES IN LENGTH. A X-RAY INSP ECTION WAS ACCOMPLISHED IN THE AREA OF THE DOUBLER AND 2 CRACKS WERE NOTED ON THE SKIN AT THE FASTENER THAT WAS UNDERNEA TH THE DOUBLER. THE DOUBLER WAS REMOVED FROM THE AIRCRAFT TO INSPECT THE AREA NO FURTHER DAMAGE WAS NOTED. 1 H 7 2 3T 4 T 2A4 E2WE 2002021200149 20020212 00149 SW 2002 2 12 CA011210018 1 20011203 G 2810 5129811 LINE AIRTRC AT802 AT802 0390305 SW PWA PT6 PT6A67A 52043 NE FUEL SYSTEM CHAFED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) DURING INSPECTION THE AIR CONDITIONER DRIVE ASSY WAS BEING REMOVED FOR LUBRICATION. IT WAS NOTED THAT THE FIRE SLE EVING OF THE FLEX FUEL PRESSURE LINE, HAD BEEN WORN THROUGH. FURTHER INVESTIGATION REVEALED THAT THE STEEL FITTING ATTA CHING THE FUEL LINE TO THE FUEL PUMP ASSY. HAD COME LOOSE AND ALLOWED THE FUEL LINE TO CONTACT THE AIR CONDITIONING SYST EM COMPRESSOR PULLEY. THE OUTER RUBBER OF THE FUEL LINE WAS ALSO DAMAGED. THE LINE WILL BE REPLACED WITH A SERVICEABLE UNIT, AND THE REST OF THE AIRTRACTOR FLEET WILL BE INSPECTED PRIOR TO FURTHER FLIGHT. 1 L 7 1 3T 4 T NC A19SW E26NE 2002021200155 20020212 00155 EU 2002 2 12 CA011210020 1 20011207 G 2434 5243212137 DRIVE SHAFT PILATS PC12 PC1245 7090551 EU PWA PT6 PT6A67B 52043 NE HARTZL HCE4A HCE4A3D GL NR 2 GENERATOR WORN W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) 3000 HR. REPLACEMENT OF OUTER DRIVE SHAFT BEARING WAS CARRIED OUT. ON DISASSEMBLY OF DRIVE HOUSING ASSEMBLY, THE INNER BEARING MOUNTING SURFACE OF DRIVE SHAFT WAS FOUND WORN DUE TO DRIVE SHAFT SPINNING IN THE INNER RACE OF THE BEARI NG.A NEW DRIVE SHAFT WAS INSTALLED AND AFTER 4 HRS. OF OPERATION, GENERATOR NR 2 FAILED.IT WAS FOUND THAT THE NEW DRIVE SHAFT INSTALLED HAD SHEARED AFTER THE SPLINE DRIVE. 1 L 7 1 3T 4 T RT A78EU E26NE 5 C P210NE 2002021200161 20020212 00161 GL 2002 2 12 CA011211001 2 20011207 G 7321 6859172 DRAIN LINE BOLKMS 105 BO105C 5626005 EU ALLSN 250C 250C20B 03013 GL FUEL CONTROL CHAFED W K NONE K FLUID LOSS IN INSP/MAINT 1 CA (CAN) DRAIN LINE CHAFING ON FUEL CONTROL TO FUEL PUMP BYPASS TUBE P/N 6859172 TUBE IS 99 PERCENT CHAFED. 1 G 7 2 3U 3 U H3EU E4CE 2002021200174 20020212 00174 SW 2002 2 12 CA011211002 1 20011122 G 6510 204040612001 BOLT BELL 212040004003 BELL 212 212 1181420 SW PWA PT6T PT6T3 52045 EA QUILL ASSY BENT W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) THIS BOLT HOLDS THE TAIL ROTOR DRIVESHAFT COUPLING TO THE INPUT QUILL OF THE 90 DEGREE GEARBOX. WHEN THE BOLT WAS REMOVED FOR SCHEDULED MAINTENANCE (GREASE REPACKING). IT WAD NOTICED THAT IT WAS NOT THE NORMAL COLOR (BLACK) THAN IT WA S NOTICED THAT IT WAS DISTORTED AROUND THE FLANGE RADIUS. EVEN CLOSER INSPECTION SHOWS THAT THE BOLT DUE TO THE BEND IN THE FLANGE IS NOW LONGER. THE BOLT SHOWS SIGNS OF STRETCHING AND TOOL MARKS MAY INDICATE THAT IT WAS MANUFACTURED BY SOM EONE OTHER THAN THE ORIGINAL MANUFACTURE. THERE IS NO PART NO. WRITTEN ON THIS PART AS THERE IS A NEW ONE. I BELIEVE THI S IS AN UNAPPROVED PART (BOGUS). PART HELD FOR INVESTIGATION. 1 G 7 1 4U 4 U H4SW E22EA 2002021200176 20020212 00176 EA 2002 2 12 CA011211003 1 20010516 G 7603 C2CE67A CONTROL CABLE DHAV DHC2 DHC2MK1 2800102 EA PWA R985 R985AN14B 52008 NE FUEL SELECTOR FRAYED W K NONE O OTHER IN INSP/MAINT 1 CA 15315 15315 (CAN) CABLE FRAYED WHERE IT BENDS AROUND FUEL SELECTORPULLEY. ITEM NOTED DURING ANNUAL INSPECTION. IT IS ADVISEABLE TO H AVE SOMEONE MOVE THE FUEL SELECTOR CONTROL WHILE INSPECTING TO ACCESS AS MUCH OF CABLE AS POSSIBLE AS ITS INSTALLED. 1 H 7 1 3R 3 R A806 5E1 2002021200179 20020212 00179 CE 2002 2 12 CA011211004 1 20010614 G 2720 0510105173 CONTROL CABLE CESSNA 185 A185F 2072821 CE CONT O520 IO520D 17032 SO MCAULY D3A34 D3A34C403 GL RUDDER FRAYED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) FWD (CARRY-THROUGH) CABLE REMOVED TO CARRY OUT AN INSPECTION ON IT'S CONDITION DUE TO THE FACT THAT IT IS IMPOSSIB LE TO FEEL OR SEE MOST OF THE CABLE AS IT'S INSTALLED IN THE A/C. INSPECTION REVEALED FRAYED SECTION WHERE CABLE GOES AR OUND THE PULLEY SUGGEST REMOVING ALL SIMILAR CABLE AT TAT 5000HRS TO COMPLETE INSPECTION. 1 H 7 1 3O 3 O 3A24 E5CE 5 C P47GL 2002021200180 20020212 00180 CE 2002 2 12 CA011211005 1 20010520 G 5511 07326032 CHANNEL CESSNA 185 A185F 2072821 CE CONT O520 IO520D 17032 SO MCAULY D3A34 D3A34C403 GL HORIZONTAL STAB CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) CHANNEL FOUND CRACKED DIRECTLY BEHIND LT STAB HINGE REINFORCEMENT, WHICH WAS ALSO CRACKED. FURTHER INVESTIGATION REVEALED CRACKED SPAR ALSO IN SAME AREA. 1 H 7 1 3O 3 O 3A24 E5CE 5 C P47GL 2002021300001 20020213 00001 GL 2002 2 13 CA011211009 1 20010516 G 2720 C2CF741AND CONTROL CABLE DHAV DHC1 DHC1B2 2801736 GL RUDDER FRAYED W K NONE O OTHER IN INSP/MAINT 1 CA 13345 13345 (CAN) CONTROL CABLE NOTED TO BE FRAYED AFT OF IT'S ATTACHMENT TO THE LT RUDDER PEDAL. 1 L 7 1 3O EXPA1L71 2002021300004 20020213 00004 SW 2002 2 13 CA011211013 1 20011204 G 3222 STRUT HUGHES 500N 500N 3027374 SW ALLSN 250C 250C20R2 GL MLG CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) CRACK FOUND ON UPPER PART OF STRUT AROUND THE BRACE ATTACHMENT HOLE. 1 G 7 1 3U 3 U NC H3WE E4CE 2002021300005 20020213 00005 SW 2002 2 13 CA011211014 1 20011204 G 3222 STRUT HUGHES 500N 500N 3027374 SW ALLSN 25OC 250C20R GL MLG CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) CRACK FOUND ON UPPER PART OF STRUT AROUND THE BRACE ATTACHMENT HOLE. 1 G 7 1 3U 3 U NC H3WE E4CE 2002021300006 20020213 00006 SW 2002 2 13 CA011211015 1 20011204 G 3222 STRUT HUGHES 500N 500N 3027374 SW ALLSN 25OC 250C20R GL MLG CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) CRACK FOUND ON UPPER PART OF STRUT AROUND THE BRACE ATTACHMENT HOLE. 1 G 7 1 3U 3 U NC H3WE E4CE 2002021300007 20020213 00007 SW 2002 2 13 CA011211016 1 20011123 G 3222 STRUT HUGHES 500N 500N 3027374 SW ALLSN 25OC 250C20R GL MLG CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) CRACK FOUND ON UPPER PART OF STRUT AROUND THE BRACE ATTACHMENT HOLE. 1 G 7 1 3U 3 U NC H3WE E4CE 2002021300008 20020213 00008 SW 2002 2 13 CA011211017 1 20011204 G 3222 STRUT HUGHES 500N 500N 3027374 SW ALLSN 25OC 250C20R GL MLG CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) CRACK FOUND ON UPPER PART OF STRUT AROUND THE BRACE ATTACHMENT HOLE. 1 G 7 1 3U 3 U NC H3WE E4CE 2002020500128 20020205 00128 EA 2002 2 5 CA011211018 2 20011205 G 7320 A5222690 THROTTLE CABLE BELL A5222640 BELL 47 47G2 1181008 SW LYC O435 VO435A1E 41516 EA BELOW RH ENGINE FROZEN W B EMER. DESCENT F FLT CONT AFFECTED CR CRUISE 1 CA (CAN) THROTTLE FROZEN AT CRUISE POWER WHEN HELICOPTER CLIMBED THROUGH FREEING LEVEL AT APPROXIMATE 3,000'. THE CABLE BEC AME UNSTUCK WHEN THE HELICOPTER RETURNED TO A LOWER LEVEL. BY THIS TIME THE PILOT (FLIGHT INSTRUCTOR) CARRIED OUT AN AUT O ROTATION TO ABBOTSFORD AIRPORT AND HOVER TAXIED BACK TO THE HANGAR. 1 G 7 1 3O 3 O H1 E279 2002021300009 20020213 00009 CE 2002 2 13 CA011211019 1 20010508 G 5521 07346041 RIB CESSNA 185 A185F 2072821 CE CONT O520 IO520D 17032 SO MCAULY D3A34 D3A34C403 GL LT ELEVATOR CORRODED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) LEAD BALANCE WEIGHT ATTACHES TO AFFECTED RIB AND CORROSION FORMED DUE TO DISSIMILAR METAL. AREA IMPOSSIBLE TO INS PECT UNLESS ELEVATOR TIP SKIN IS REMOVED TO ACCESS RIB. UPON REPLACEMENT OF RIB, 1 H 7 1 3O 3 O 3A24 E5CE 5 C P47GL 2002021300017 20020213 00017 EA 2002 2 13 CA011212002 2 20011203 G 8530 AEL6510241 CYLINDER CESSNA 172 172P 2072436 CE LYC O320 O320D2J 41508 EA ENGINE CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) DURING A REGULAR MAINTENANCE INSPECTION THE CYLINDERS WERE VISUALLY CHECKED USING A BORESCOPE, CRACKS WERE NOTED AT THE SPARK PLUGS PORTS OF NR 1 & 2 CYLINDERS. ALL CYLINDERS WERE REMOVED AND REPLACED. 1 H 7 1 3O 3 O NT 3A12 E274 2002021300018 20020213 00018 CE 2002 2 13 CA011212003 1 20011202 G 5610 5042006938 WINDSHIELD BEECH 100 B100 1152919 CE COCKPIT CRACKED W A UNSCHED LANDING O OTHER CR CRUISE 1 CA (CAN) WINDSHELD CRACKED / CRAZED DURING CRUISE FLIGHT. THE CREW LOWERED CABIN PRESSURE, DISCOUNTINUED HEAT AND LANDED W ITHOUT FURTHER INCIDENT. MAINTENANCE FOUND THE INNER LAMINATE LAYER OF THE WINDSHIELD PRC SEALED TO THE WINDOW FRAME STR UCTURE WHICH PREVENTED FREE FLOATING OF THE WINDSHIELD WITHIN THE WINDOW FRAME CREATING STRESS TO THE INNER LAMINATE LAY ER WHICH-EVENTUALLY CRACKED. A NEW WINDSHIELD ASSY WAS INSTALLED. 1 L 7 2 4T A14CE 2002021300019 20020213 00019 CE 2002 2 13 CA011212004 1 20011211 G 2140 DIAPHRAGM CESSNA 401 401 207590C CE CONT O520 TSIO520E 17040 SO HEATER FUEL PUMP DAMAGED W K NONE K FLUID LOSS IN INSP/MAINT 1 CA (CAN) FUEL WAS NOTICED LEAKING FROM THE HEATER FUEL PUMP VENT LINE. THE FUEL PUMP WAS DISMANTLED AND THE DIAPHRAM WAS F OUND TO HAVE FAILED CAUSING FUEL TO LEAK DOWN TO THE BEARING, REMOVING ALL LUBRICATION AN ALSO FALLING. THE FUEL PUMP WA S REPLACED. 1 L 7 2 3O 3 O A7CE E8CE 2002021300020 20020213 00020 CE 2002 2 13 CA011214001 1 20011214 G 7931 PTI052287579522 OIL FILTER BEECH 90 C90A 1152911 CE PWA PT6 PT6A21 52043 EA ENGINE OIL DAMAGED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) WHEN REPLACING INBD O-RING, FOUND VERY SHARP EDGE IN OIL FILTER BODY DAMAGING O-RING EVERY TIME. 1 L 7 2 3T 4 T RT 3A20 E4EA 2002021300021 20020213 00021 CE 2002 2 13 CA011217001 1 20011011 G 3233 115380103 BEARING BEECH 100 A100 1152915 CE PWA PT6 PT6A28 EA MLG ACTUATOR FAILED W O OTHER J WARNING INDICATION CL CLIMB 1 CA (CAN) ON CLIMBOUT RT GEAR DID NOT INDICATE UP & LOCKED & INTRANSIT LIGHT ILLUMINATED. GEAR EXTENDED, THIS TIME GEAR D ID NOT INDICATE DOWN & LOCKED & INTRANSIT LIGHT REMAINED ILLUMINATED. UPON LDG RT MAIN GEAR COLLAPSED. LDG GEAR ACTUAT OR REMOVED & SENT TO TSB LAB FOR ANALYSIS. IT DETERMINED THAT THRUST BEARING IN ACTUATOR WAS INSTALLED BACKWARDS. RESU LTING FAILURE OF THRUST BEARING CAUSED TEETH ON PINION & RING GEAR TO FAIL. 1 L 7 2 3T 4 T A14CE E4EA 2002021300023 20020213 00023 EU 2002 2 13 CA011217004 1 20011212 G 2434 5243212137 DRIVE SHAFT PILATS PC12 PC1245 7090551 EU PWA PT6 PT6A67B 52043 NE HARTZL HCE4A HCE4A3D GL NR 2 GENERATOR WORN W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) DURING ROUTINE 3000 HOUR INSPECTION THE DRIVE SHAFT WAS FOUND TO BE WORN AT THE FWD END OF THE SHAFT. THIS CAUSED THE SHAFT TO WOBBLE EVEN WITH THE NEW BEARING IN PLACE.FWD BEARING WAS NOT SIEZED OR STIFF.NEW SHAFT AND BEARINGS INSTA LLED. 1 L 7 1 3T 4 T RT A78EU E26NE 5 C P210NE 2002021300024 20020213 00024 SO 2002 2 13 CA011217005 1 20011028 G 3710 61183 GASKET PIPER PA31 PA31 7103102 SO LYC O540 TIO540A2C 41532 EA VACUUM PUMP TORN W E A ENGINE SHUTDOWN UNSCHED LANDING K FLUID LOSS CR CRUISE 1 CA (CAN) PILOT EXPERIENCED OIL PRESSURE LOSS RT ENGINE WHILE INCRUISE. SHUTDOWN AND A/C LANDED WITH NO OTHER INCIDENT. ENGI NE WAS REMOVED. INSPECTION FOUND ONE LOOSE VACUUM PUMP RETENSION NUT. WHEN PUMP AND ADAPTOR REMOVED GASKET FOUND TORN AR EA NEAR LOOSE NUT. THIS AREA COVERS AN OIL JET WHICH IS NOT USED FOR THIS VACUUM PUMP INSTALLATION. 1 L 7 2 3O 3 O A20SO E14EA 2002021300029 20020213 00029 WP 2002 2 13 CA011217011 2 20011120 G 7250 31081251 BLADE GARRTT TPE331 TPE33110UA 01514 WP ENGINE ERODED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) BORESCOPE INSPECTION REVILED ERODED BLADES AT FUEL NOZZLE CHANGE. 4 T E4WE 2002021300030 20020213 00030 EU 2002 2 13 CA011217013 1 20011212 G 2435 23085024 STARTER GEN PILATS PC12 PC1245 7090551 EU PWA PT6 PT6A67B 52043 NE HARTZL HCE4A HCE4A3D GL ENGINE WRONG PART W D RETURN TO BLOCK W INADEQUATE Q C TX TAXI/GRND HDL 1 CA (CAN) STARTER- GEN REMOVED PREMATURELY AT 950 HRS TSO DUE TO UNIT BEING VERY NOISY AT LOWER RPMS. UNIT TAKEN TO AMO FOR OVERHAUL. ON DISASSEMBLY, IT WAS NOTICED THAT UNIT DOES NOT PHYSICALLY CORRESPOND WITH MANUFACTURE`S STARTER-GEN. 1 L 7 1 3T 4 T RT A78EU E26NE 5 C P210NE 2002021300032 20020213 00032 SO 2002 2 13 CA011217016 1 20011210 G 2140 88D9310 COMBUST CHAMBER JANITROL 90D382 PIPER PA44 PA44180 7104402 SO HEATER CRACKED W K NONE L NO TEST IN INSP/MAINT 1 CA A95080021 (CAN) THE COMBUSTION TUBE LEAK RATE WAS GREATER THAN ALLOWED AMOUNT. THE HEATER ASSEMBLE WAS REMOVED AND THE COMBUSTIO N TUBE WAS REMOVED FROM THE HEATER ASSEMBLY. ANOTHER DECAY TEST WAS CARRIED OUT ON THE COMBUSTION TUBE AND WAS FOUND TO HAVE A 1 INCH CRACK ON THE AFT FACE. THE COMBUSTION TUBE WAS SENT OUT FOR REPAIR. IT IS FELT THAT THE HEATER CRACKED DUE TO THE CONSTANT HEATING AND COOLING DURING REGULAR CYCLES OF THE HEATER OPERATIONS. 1 L 7 2 3O A19S0 2002021300033 20020213 00033 CE 2002 2 13 CA011217017 1 20011207 G 3213 30A04000100 STRUT CESSNA 180 180J 2072622 CE CONT O470 O470R 17026 SO MCAULY 2A34C 2A34C201 GL MLG BROKEN W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) 1/4 INCH RETAINER PIN BROKE AT COTTER PIN HOLE ON RT SHOCK STRUT ASSY. WHEN THE RETAINER PIN FALLS OUT THE LANDING GEAR FALLS DOWN. 1 H 7 1 3O 3 O 5A6 E273 5 C P3EA 2002021300034 20020213 00034 EA 2002 2 13 CA011217018 2 20011130 G 8520 LW18840 CAMSHAFT ZLIN 242 Z242L 9970204 EU LYC O360 AEIO360A1B6 41514 EA ENGINE WORN W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) DURING SCHEDULED 50 HOUR INSPECTION THAT CONTAINED TASKS REQUIRED TO COMPLY WITH THE ENGINE ON THE CONDITIONS PROG RAM ESTABLISHED FOR THE ENGINE BEING INSPECTED, A MODERATE AMOUNT OF VERY SMALL METAL PARTICLES WERE FOUND IN THE OIL FI LTER ELEMENT DURING INSPECTION. NUMBER ONE CYLINDER WAS REMOVED IN ORDER TO INVESTIGATE THE SOURCE OF THE SOURCE OF THE METAL CONTAMINATION. WITH THE CYLINDER REMOVED IT WAS OBSERVED THAT THE FRONT LOBE OF THE ENGINE CAM SHAFT WAS WORN ABNO RMALLY AND THE CAM FOLLOWER WAS VERY BADLY SPALLED. THE ENGINE WAS REMOVED FROM THE AIRCRAFT AND SENT OUT FOR REPAIR. 1 L 7 1 3O 3 O 0 A76EU 1E10 2002021300035 20020213 00035 NM 2002 2 13 CA011217019 1 20011101 G 6320 A0061 GEARBOX ROBSIN R22 R22BETA 7640110 NM LYC O320 O320B2C 41508 EA MAIN ROTOR MAKING METAL W E A ENGINE SHUTDOWN UNSCHED LANDING J WARNING INDICATION CR CRUISE 1 CA (CAN) OCT23 AT 1290 HRS M/R OIL CHANGED (500 HR CHANGE. OCT 30 IN CRUISE FLIGHT MAIN ROTOR CHIP LIGHT -M/R CHIP PLUG REM OVED AND CLEANED OCT 31. OCT 31 MADE ANOTHER FLIGHT 1.1 HRS NO CHIP LIGHT. NOV.1 ON START UP CHIP LIGHT ON M/R AGAIN. SH UT-DOWN AND INSPECTED-FOUND NUMEROUS CHIPS AGAIN. M/R TRANSISSION REMOVED AND SENT TO ROBINSON FOR REPAIR OVERHAUL WAS R EQUIRED. NO REPORT ON WHAT PART FAILED. 1 G 7 1 3O 3 O H10WE E274 2002021300053 20020213 00053 EA 2002 2 13 CA011217025 1 20011217 G 3411 CONNECTOR KOLLSMAN 518B02 DHAV DHC2 DHC2MK1 2800102 EA PWA R985 R985AN14B 52008 NE PITOT HEAD FAILED W K NONE L NO TEST IN INSP/MAINT 1 CA 21548 3342 (CAN) DURING A ROUTINE INSPECTION , WHEN THE PITOT HEATER SWITCH WAS SELLECTED THE CIRCUIT BREAKER WOULD POP. INVESTIG ATION REVEALED THAT THE FEMALE ELECTRICAL CONNECTER TO THE PITOT HEAD HAD FAILED CAUSING A DIRECT SHORT. THE FEMALE PIN CONNECTER WAS REPLACED WITH A NEW UNIT. 1 H 7 1 3R 3 R A806 5E1 2002021300054 20020213 00054 EA 2002 2 13 CA011218002 1 20011128 G 7603 C6EC12551 THROTTLE CABLE DHAV DHC6 DHC6300 2802606 EA PWA PT6 PT6A27 52043 EA LT ENGINE FAILED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) DURIING A ROUTINE EMMA CHECK 46, THE LT ENGINE THROTTLE CABLE TURNBUCKLE END WAS FOUND FRACTURED AND WAS ONLY HELD TOGETHER BY LOCKWIRING. CABLE REPLACED. 1 H 7 2 3T 4 T RT A9EA E4EA 2002021300065 20020213 00065 EA 2002 2 13 CA011218009 1 20011129 G 2720 VALLT2CF1029R1 CONTROL CABLE DHAV DHC2 DHC2MK1 2800102 EA PWA PT6 PT6A34 52043 EA HARTZL HCB3T HCB3TN3 GL RUDDER FRAYED W A UNSCHED LANDING F FLT CONT AFFECTED NR NOT REPORTED 1 CA (CAN) FOUND THE FORWARD RUDDER CABLE TO BE SHOWING WEAR AT THE LOCATION AT THE FAIRLEAD AT STATION 8.00. THE CABLE WAS REPLACED WITH A NEW UNIT AND THE CABLE RUN WAS CHECKED THROUGH THE FAIRLEAD. 1 H 7 1 3R 4 T A806 E4EA 6 C P15EA 2002021300068 20020213 00068 2002 2 13 CA011218012 4 20011217 G 2562 ELT SAFETY EQUIP FAILED W K NONE L NO TEST IN INSP/MAINT 1 CA (CAN) DURING ANNUAL RECERTIFICATION ELT WAS FOUND TO HAVE NO TRANSMIT. UNIT WAS RETURNED TO THE MANUFACTURER FOR REPAIR . 2002021300069 20020213 00069 2002 2 13 CA011218013 4 20011217 G 2562 SWITCH POINTER 400010 ELT FAILED W K NONE L NO TEST IN INSP/MAINT 1 CA 408494 (CAN) DURING ANNUAL RECERTIFICATION ELT G-SWITCH FAILED TO ACTIVATE UNIT. UNIT WAS RETURNED TO THE MANUFACTURER FOR REPA IR. 2002021300070 20020213 00070 SO 2002 2 13 CA011219003 1 20011130 G 7603 2489418 THROTTLE CABLE PIPER PA31 PA31350 7103110 SO LYC O540 TIO540J2BD 41532 EA LT ENGINE FAILED W E A ENGINE SHUTDOWN UNSCHED LANDING R J PARTIAL RPM/PWR LOSS WARNING INDICATION CR CRUISE 1 CA (CAN) UPON REACHING CRUISE ALTITUDE, WHILE ATTEMPTING TO SET CRUISE POWER LEFT THROTTLE CABLE JAMMED AT 38 INCHES MANIF OLD PRESSURE. MTCE INSP REVEALED. LE THROTTLE CABLE SEIZED UPON ATTEMPTS TO FREE CABLE, CABLE BROKE APPROX. 1 INCH INSI DE CABLE FROM QUADRANT SWAGE CONNECTION. 1 L 7 2 3O 3 O A20SO E14EA 2002021300072 20020213 00072 CE 2002 2 13 CA011219004 1 20011205 G 3220 124340215 TRUNNION CESSNA 210 P210N 2073454 CE CONT O520 TSIO520P 17040 SO MCAULY D3A34 D3A34C402 GL MLG CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) NOSE LANDING GEAR LOWER TRUNNION FOUND CRACKED. 1 H 7 1 3O 3 O 3A21 E8CE 5 C P47GL 2002021300074 20020213 00074 EA 2002 2 13 CA011219005 2 20011123 G 7322 1060301 CARBURETOR HUGHES 269 269C1 8059504 SW LYC O360 HO360C1A 41514 EA ENGINE MALFUNCTIONED W O OTHER R PARTIAL RPM/PWR LOSS NR NOT REPORTED 1 CA (CAN) ENGINE ROUGH AND SLOW AT RECOVERY FROM AUTOROTATOR. REPLACE CARBURATOR. 1 G 7 1 3O 3 O O 4H12 E286 2002021300077 20020213 00077 CE 2002 2 13 CA011219006 1 20010520 G 5312 07421155 BULKHEAD CESSNA 185 A185F 2072821 CE CONT O520 IO520D 17032 SO MCAULY D3A34 D3A34C403 GL CARGO BAY CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) CRACK NOTED ON LT BULKHEAD DURING INSPECTION WITH MIRROR. BULHEAD IS LOCATED DIRECTLY ADJACENT TO BAGGAGE DOOR. 1 H 7 1 3O 3 O 3A24 E5CE 5 C P47GL 2002021300078 20020213 00078 CE 2002 2 13 CA011219007 1 20011212 G 1100 PLACARD CESSNA 208 208B 2073701 CE PWA PT6 PT6A114A 52043 NE MCAULY 3AF34C 3GFR34C703 GL COCKPIT MISSING W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) AIRSPEED LIMIT PLACARD NOT INSTALLED ON COMPANY PER T.C. A37CE. 1 H 7 1 3T 3 T A37CE E4EA 5 C P60GL 2002021300081 20020213 00081 CE 2002 2 13 CA011219008 1 20011203 G 2720 05430224 TUBE CESSNA 150 152 2071835 CE LYC O235 O235L2C 41505 EA RUDDER JAMMED W A UNSCHED LANDING F FLT CONT AFFECTED CL CLIMB 1 CA (CAN) A/C HAS 15120.6 T.AT. TIME ON PART UNKNOWN, MAY BE ORIG. UPON TAXI TO HOLD LINE, PILOT TURNED FULL LEFT THEN FULL RIGHT TO CHECK BRAKES & STEERING. PILOT APPLIED FULL POWER AFTER T/O CLEARENCE & HAD TO KEEP GREATER THAN NORMAL RIGHT R UDDER TO KEEP A/C STRAIGHT. WHEELS LEFT GROUND AT 70K A/C IMMEDIATLY YAWED HARD LEFT. PILOT PUT IN FULL RIGHT RUDDER & A ILERON TO COMBAT, RUDDER STAYED JAMMED HARD LEFT. A/C LANDED ON GRASS & HIT DITCH CAUSING EXTENSIVE ENGINE, PROP & FUSEL AGE DAMAGE. AME & TSB DISCOVERED THAT RT STEERING PUSH-PULL ROD COULD HAVE JAMMED IN SHORTENED POS&AS OLEO EXTENDED, IT PULLED LT RUDDER PEDAL IN, IN TURN DEFLECTING RUDDER FULL LEFT. WASHER THAT USUALLY SLIDES FREELY IN S TEERING TUBE 1 H 7 1 3O 3 O NT 3A19 E223 2002021300082 20020213 00082 NE 2002 2 13 CA011219009 1 20011209 G 2910 7665103004073 LINE SKRSKY S76 S76A 8143006 NE TMECA ARRIEL ARRIEL1S1 60030 NE HYD SYSTEM CHAFED W K NONE K FLUID LOSS IN INSP/MAINT 1 CA (CAN) DURING POST FLIGHT WALK AROUND FLIGHT CREW NOTICED HYD FLUID LEAKING OUT OF COWLING. COWL WAS REMOVED. HYD RESEVOI R WAS 1/2 FULL AND A/C GROUND RUN A LEAK WAS DETECTED UNDER A CLAMP OF NR 2 SYSTEM PRESSURE LINE. THE LINE WAS REPLACED WITH A NEW PART, NR 2 SYSTEM HYD OIL TOPPED UP TO FULL MARK. A/C GROUND RUN & LEAK CHECKED SERVICEABLE & RETURNED TO SER VICE. 1 G 7 2 3U 3 U H1NE E19EU 2002021300093 20020213 00093 2002 2 13 CA011220001 4 20011219 G 6122 NUT MCAULY C290D4MT4 CESSNA 210 210R 2073458 CE CONT O520 IO520L 17032 SO MCAULY D3A34 D3A34C404 GL RELIEF VALVE LEAKING W K NONE K FLUID LOSS IN INSP/MAINT 1 CA 980085 (CAN) DURING ROUTINE GROUND MAINTENCE OIL WAS DISCOVERED EMINATING FROM THE ENGINE COWLING. INVESTIGATION WHICH INCLUDE D WASHING DOWN THE AREA AND A RUN UP REVEALED OIL LEAKING FROM THE RELIEF VALVE ADJUSTMENT NUT. REPLACED PROPELLOR GOVE RNOR, RAN ENGINE NO LEAKS FOUND.NO PART NUMBER AVAILABLE FOR THE ADJUSTMENT NUT/RELIEF VALVE 1 H 7 1 3O 3 O RT 3A21 E5CE 5 C P47GL 2002021300094 20020213 00094 SO 2002 2 13 CA011220002 1 20011217 G 3213 HINGE PIPER PA31 PA31350 7103110 SO LYC O540 TIO540J2BD 41532 EA LT MAIN GEAR CRACKED W A UNSCHED LANDING J WARNING INDICATION CL CLIMB 1 CA 16538 (CAN) AFTER T/O SELECTED GEAR UP, THE HANDLE RETURNED WITH A RED LIGHT. THE GEAR WAS RECYCLED, WITH NO CHANGE.GEAR SELE CTED DOWN AND AIRCAFT LANDED WITHOUT INCIDENT. PART TIMES AND CYCLES FROM AIRCRAFT TIME. 1 L 7 2 3O 3 O A20SO E14EA 2002021300100 20020213 00100 WP 2002 2 13 CA011220003 1 20011218 G 6700 BUNGEE CYLINDER ROBSIN R44 R44 7640120 WP CYCLIC FAILED W O OTHER O OTHER CR CRUISE 1 CA (CAN) PLIOT COMPLAINED OF HEAVY AFT CYCLIC FORCES.INVESTIGATION REVEALED CYCLIC BUNGEE TO BE DISCONNECTED FROM AFT ATTAC H POINT ON PUSH ROD P/N C121-9 AT C317-1 BELLCRANK. SUSPECT DISCONNECTION IS DUE TO COLD OPERATING ENVIRONMENT AT THIS T IME. LOCAL TEMERATURES REACHED BELOW -25 DEGREES C.BUNGEE MATERIAL MAY STIFFEN WHEN COLD CAUSING A LOS OF ELASTICITY A ND ALLOWING THE DISCONNECTION. THIS AIRCRAFT HAS THE UPDATED STYLE BUNGEE ATTACHMENT CLIP. 1 G 7 1 3O H11NM 2002021300101 20020213 00101 WP 2002 2 13 CA011220004 1 20011219 G 6700 BUNGEE CYLINDER ROBSIN R44 R44 7640120 WP CYCLIC FAILED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) DURING 100 HOUR INSPECTION, BOTH AFT BUNGEES WERE FOUND TO BE DISCONNECTED AT THE AFT PUSH PULL TUBE C121-9 AT THE C317-1 BELLCRANK.SUSPECT DISCONNECTION IS DUE TO COLD OPERATING ENVIRONMENT AT THIS TIME. LOCAL TEMPERATURES REACHED B ELOW -25 DEGREES C. BUNGEE MATERIAL MAY STIFFEN WHEN COLD CAUSING A LOSS OF ELASTICITY AND ALLOWING FOR DISCONNECTION.NO TE THIS AIRCRAFT HAS THE UPDATED STYLE BUNGEE ATTACHMENT CLIP. 1 G 7 1 3O H11NM 2002021300103 20020213 00103 CE 2002 2 13 CA011221001 1 20010520 G 5511 07321014 BRACKET CESSNA 12320008 CESSNA 185 A185F 2072821 CE CONT O520 IO520D 17032 SO MCAULY D3A34 D3A34C403 GL HORIZONTAL STAB CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) CRACK NOTED FROM RETAINER'S EDGE TO INBOARD ATTACHMENT SCREW HOLE AS VIEWED FROM THE LT SIDE OF A/C. ANOTHER CRAC K NOTED IN BOTTOM BEND RADIUS OF BRACKET AND EXTENDING ALONG THE BEND FOR APPROX. 1 INCH. PROBABLE CAUSE IS FROM CARRYIN G EXTERNAL LOADS ON THE SIDE OF THE A/C SUCH AS CANOES, SMALL BOATS ETC. 1 H 7 1 3O 3 O 3A24 E5CE 5 C P47GL 2002021300107 20020213 00107 SW 2002 2 13 CA011221004 1 20011203 G 5343 71470101R TUBE BBAVIA 8 8GCBC 1220803 SW LYC O360 O360C2E 41514 EA MLG BROKEN W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) TUBE FOUND BROKEN THROUGH APPROXIMATELY AT WELD TO RT FORWARD END OF LDG FITTING. 1 H 7 1 3O 3 O A21CE E286 2002021400005 20020214 00005 CE 2002 2 14 CA011221007 1 20011205 G 3222 030A39313 BOLT MTSBSI MU2 MU2B36 5780412 CE NLG CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) THE NOSE LANDING GEAR DRAG STRUT ATTACH BOLT WAS FOUND CRACKED. THIS BOLT HAD BEEN MAGNETIC PARTICAL INSPECTED EVE RY 2000 HOURS. 1 H 7 2 3T RT A10SW 2002021400006 20020214 00006 CE 2002 2 14 CA011221008 1 20011220 G 7920 017A4710127 LINE MTSBSI MTSBSI MU2 MU2B36 5780412 CE OIL COOLER CHAFED W K NONE W K INADEQUATE Q C FLUID LOSS IN INSP/MAINT 1 CA (CAN) THE OIL LINE RUNNING FROM THE OIL COOLER WAS FOUND CHAFED BY A SCREW THAT WAS TOO LONG IN A PANEL ON THE SIDE OF T HE NACELLE. THE LINE WAS REPLACED AND THE SCREW WAS REPLACED WITH A SHORTER ONE 1 H 7 2 3T RT A10SW 2002021400012 20020214 00012 CE 2002 2 14 CA011231003 1 20011224 G 2460 5036430821 DIODE BEECH 100 A100 1152915 CE PWA PT6 PT6A28 EA BUSS FEEDER BURNED W O OTHER O OTHER AP APPROACH 1 CA (CAN) PILOT HAD MULTIPLE FAILURES WHEN COMING IN TO LAND, SOME EXTERIOR AND INTERIOR LIGHTS WOULD NOT WORK AND THE LAND ING GEAR WOULD NOT COME DOWN. THE PILOT EXTENDED THE GEAR MANUALLY AND LANDED WITHOUT INCIDENT. MAINTENANCE FOUND THE RT NR 1 BUSS FEEDER DIODE BURNT. THE RT NR 1 BUSS FEEDER DIODE WAS REPLACED, NR 2 BUSS FEEDER DIODE WAS REPLACED AND THE RT NR 1 BUSS FEEDER WIRE CONNECTOR PIN WAS ALSO REPLACED AT THE RT CIRCUIT BREAKER PANEL. BEECHCRAFT HAS AN INSPECTION EVERY 800 HOURS THAT WOULD HAVE IDENTIFIED THE PROBLEM DIODE BEFORE THIS HAPPENED, THIS AIRCRAFT WAS 150 HOURS AWAY FROM THAT INSPECTION. I SUBMITTED ANOTHER SDR ON THIS SUBJECT SEE CONTROL NUMBER 19991230038 1 L 7 2 3T 4 T A14CE E4EA 2002021400014 20020214 00014 EU 2002 2 14 CA020102001 1 20011211 G 6410 BLADE SNIAS 350 AS350B3 8680954 EU TMECA ARRIEL ARRIEL2B NE TAIL ROTOR CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 6875 (CAN) 35 MM CRACK IN BLADE SKIN ON TAIL ROTOR. 1 G 7 1 3U 3 U H9EU E00054EN 2002021400016 20020214 00016 CE 2002 2 14 CA020102003 1 20011120 G 5510 05320019 SPAR CESSNA 0532001201 CESSNA 172 172B 2072406 CE CONT O300 O300D 17022 SO HORIZONTAL STAB CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) AT ANNUAL INSPECTION THE CENTRE SECTION OF THE STABILIZER SPAR WAS FOUND TO BE BUCKLED AND CRACKED AT THE CENTRE L IGHTENING HOLE, WHERE THE TRIM CABLES RUN THROUGH. THERE WERE TWO CRACKS ABOUT 2 IN. LONG, RUNNING FROM THE BOTTOM RIGHT AND TOP LEFT SIDES OF THE HOLE, WITH CORRESPONDING BUCKLING. THE CRACKS WOULD OPEN AND CLOSE AS PRESSURE WAS APPLIED TO THE TIP OF THE STABILIZER - UP OR DOWN. THE STABILIZER HAD ONLY A SLIGHT LOSS OF STIFFNESS - SO THE PROBLEM WAS ONLY NO TICED BY VISUAL INSPECTION OF THE AFFECTED AREA. THE STABILIZER WAS REMOVED AND REPAIRED. 1 H 7 1 3O 3 O NT 3A12 E253 2002021400017 20020214 00017 EU 2002 2 14 CA020103001 1 20011201 G 6320 4638302023 BEARING 4638001010 BOLKMS 105 BO105CBS 5626008 EU ALLSN 250C 250C20B 03013 GL M/R GEARBOX SPALLED W K NONE O OTHER IN INSP/MAINT 1 CA 1159 (CAN) GEARBOX RECEIVED FROM THE USA FOR INVESTIGATION OF METAL CONTAMINATION. UPON DISASSEMBLY THE SUBJECT BEARING SHOWS SIGNS OF EXCESSIVE PEELING ON ONE BALL, 75 PERCENT OF AREA AFFECTED. ANOTHER BALL ALSO STARTING TO PEEL. ONE HALF OF S PLIT INNER RACE HAD SPALLING OVER 10 PERCENT OF BEARING SURFACE. 1 G 7 2 3U 3 U NC H3EU E4CE 2002021400018 20020214 00018 EU 2002 2 14 CA020103003 1 20011209 G 2916 PPEV3008EA3B POWERPACK PILATS PC12 PC1245 7090551 EU PWA PT6 PT6A67B 52043 NE HARTZL HCE4A HCE4A3D GL HYD SYSTEM CRACKED W K NONE K FLUID LOSS IN INSP/MAINT 1 CA (CAN) DURING A DAILY INSPECTION BY MAINTENANCE STAFF AT THE COMPLETION OF SCHEDULED FLIGHT. HYDRAULIC FLUID WAS FOUND A T LH WING ROOT, BOTTOM OF WING,WHERE ACCESS PANEL IS LOCATED FOR HYDRAULIC POWER PACK. THE AMOUNT OF FLUID LOST DID NOT EFFECT OPERATION OF SYSTEM. THE LEAK WAS DETERMINED TO BE A CRACK IN THE RESEVOIR OF THE HYDRAULIC POWER PACK STARTING A T THE TOP OF RESEVOIR AND TRAVELLING DOWN TO THE BOTTOM OF RESEVOIR WHERE THE ELECTRIC MOTOR IS MOUNTED. HYDRAULIC POWER PACK WAS REPLACED AND AIRCRAFT RETURNED TO SERVICE. 1 L 7 1 3T 4 T RT A78EU E26NE 5 C P210NE 2002020500133 20020205 00133 EA 2002 2 5 CA020103004 2 20011211 G 7414 1038255514 MAGNETO LYC CESSNA 172 172N 2072434 CE LYC O320 O320H2AD 41508 EA MCAULY 1C160 1C160DTM GL ROTOR & GEAR FAILED W A UNSCHED LANDING R PARTIAL RPM/PWR LOSS CR CRUISE 1 CA (CAN) THE AIRCRAFT ENGINE HAD JUST UNDERGONE AN ON CONDITION INSPECTION AND HAD MET ALL REQUIRED PARAMETERS, INCLUDING F ULL POWER CHECK. ONE SIDE OF THE DUAL MAG FAILED ON FIRST FLIGHT POST INSPECTION. UPON DISSASSEMBLY OF DISTRIBUTION BLOC K. SEVERAL ROTOR TEETH WERE FOUND BROKEN OFF. THE ROTOR BEARING WAS FOUND WITH EXCESSIVE WEAR AND THE DISTRIBUTOR CONTAC TS APPEAR TO HAVE TOUCHED. 1 H 7 1 3O 3 O NT 3A12 E274 5 N P910 2002021400019 20020214 00019 GL 2002 2 14 CA020103005 3 20011201 G 6114 MS20073XXXX BOLT CESSNA 150 150M 2071830 CE CONT O200 O200A 17020 SO MCAULY 1A102 1A102OCM GL PROPELLER WRONG PART W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) WHILE REMOVING MCCAULEY PROP FOR 5 YEARS CORRISON INSPECTION IT WAS NOTED THAT PROP BOLTS WERE TO SHORT APPROX 4 T HREADS ON ALL BOLTS WERE SECURING THE PROP. NEW BOLT KIT A2513-77 INSTALLED & LOCKED. 1 H 7 1 3O 3 O 3A19 E252 5 N P918 2002021400020 20020214 00020 NE 2002 2 14 CA020103006 2 20011213 G 7230 350A070867 SEAL SNIAS 350 AS350BA 8680817 EU LYC LTS101 LTS101600A3 41560 NE COMPRESSOR DESTROYED W A UNSCHED LANDING R J PARTIAL RPM/PWR LOSS WARNING INDICATION CR CRUISE 1 CA (CAN) A/C IN CRUISE. FLYING IN SNOW, VISIBILITY 1 MILE, TEMP -2 DEGS. ON 1ST FLT OF DAY. AFTER 25 MIN FROM TAKEOFF, A/C HAD LIGHT COMPRESSOR STALL. THEN HAS A SERIES OF LARGE ONES. HAD SOME RPM DROP. ON INSPECTION AFTER LDG. FOUND 2 OF INTAKE SEALS INCLUDING RETAINING STRIPS & CLIPS IN INTAKE BOX. ONE RETAINING STRIP & CLIPS & ALSO ONE RUBBER SEAL MISSI NG. AXIALCOMPRESSOR WHEEL BLADES ARE SEVERELY DAMAGED. ENGINE IS PRESENTLY REMOVED.. 1 G 7 1 3U 3 U NC H9EU E5NE 2002022800001 20020228 00001 EA 2002 2 28 CA020103010 1 20011220 G 7921 OIL COOLER GENELC CF343B1 CNDAIR CL600 CL6002B19 1900309 EA GE CF34 CF343B1 NE LEFT ENGINE LEAKING W K NONE K FLUID LOSS AP APPROACH 1 CA 872259 (CAN) A/C ON APPROACH WHEN CREW NOTED LEFT OIL PRESSURE FLUCTUATING. CREW RPTED PRESSURE FLUCTUATING UP TO 25 PSI&AVERAG ING 30 PSI LOWER THAN RIGHT ENGINE. NO MENTION OF WARNINGS OR OTHER ACTION TAKEN. MAINT FOUND LEFT ENGINE TO BE 5 QTS LO W OF OIL. ENGINE SERVICED&RUN WITH AG AXIS LEAK PORTS OPEN. GE REP&FSR WITNESSED MUCH FLUID NOTED FROM J AXIS PORT, CONS IDERABLE STREAM COMING FROM IT&ENGINE SHUTDOWN. THISENGINE OF CONFIG THAT DID NOT HAVE CARBON SEAL&RUNNER ON THAT SHAFT. O RINGS WERE REPL&PUMP REINST ENGINE SERVICED PER GE RECOMMENDATIONS&RUN AGAIN. TIME WHEN OIL TANK CAP REMVD, QUART OR MORE OF OIL CAME OUT OF IT. THROUGH FURTHE 2 L 7 2 4F 4 F RT A21EA E15NE 2002021400025 20020214 00025 SO 2002 2 14 CA020103013 1 20011030 G 5280 4752932 HINGE PIPER 4752932 PIPER PA31 PA31 7103102 SO LYC O540 TIO540A2C 41532 EA HARTZL HCE3Y HCE3YR2A GL MLG DOOR CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) MAIN LANDING GEAR DOOR HINGES CRACKED. 1 L 7 2 3O 3 O A20SO E14EA 5 C P33EA 2002021400038 20020214 00038 EU 2002 2 14 CA020103017 1 20011205 G 3150 972813201 DISPLAY PILATS PC12 PC1245 7090551 EU PWA PT6 PT6A67B 52043 NE HARTZL HCE4A HCE4A3D GL COCKPIT MALFUNCTIONED W O OTHER N FALSE WARNING CR CRUISE 1 CA (CAN) MISC. WARNINGS LITES ILLUMINATED ALONG WITH MASTER CAUTION EVEN THOUGH ALL SYSTEMS WERE FUNCTIONING NORMALLY. ALSO CAWS DISPLAY WOULD NOT PASS LITE TEST. CAWS DISPLAY REPLACED. 1 L 7 1 3T 4 T RT A78EU E26NE 5 C P210NE 2002021400039 20020214 00039 EU 2002 2 14 CA020103018 1 20011224 G 3150 9752902014 PANEL PILATS PC12 PC1245 7090551 EU PWA PT6 PT6A67B 52043 NE HARTZL HCE4A HCE4A3D GL COCKPIT FAILED W O OTHER N FALSE WARNING CR CRUISE 1 CA (CAN) EIS GIVING FALSE READING FOR ITT. EIS PANEL REPLACED. 1 L 7 1 3T 4 T RT A78EU E26NE 5 C P210NE 2002021400040 20020214 00040 EA 2002 2 14 CA020104001 1 20011126 G 2731 AN3C6A BOLT DHAV DHC2 DHC2MK1 2800102 EA PWA R985 R985AN14B 52008 NE ELEVATOR TRIM SHEARED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) DURING 100 HR INSP REMOVED PUSH/PULL ROD FOR MAINTENANCE. RE-INSTALLED PUSH / PULL ROD AT LATER TIME WITH PREV IOUSLY REMOVED HARDWARE. WORK WAS CHECKED DURING INDEPENDENT INSPECTION. BOLT WAS FOUND SHEARED THE FOLLOWING DAY AFTE R SITTING OVERNIGHT IN THE HANGAR, THE BOLT HEAD HAD SHEARED CLEAN OFF AND WAS FOUND ON THE HANGAR FLOOR. PART RETURNED TO SEALAND AVIATION FOR EVALUATION. 1 H 7 1 3R 3 R A806 5E1 2002021400041 20020214 00041 EA 2002 2 14 CA020104002 2 20011214 G 7261 PT1052287579522 OIL FILTER BEECH 90 C90A 1152911 CE PWA PT6 PT6A21 52043 EA ENGINE OIL MISMANUFACTURED W K NONE W INADEQUATE Q C IN INSP/MAINT 1 CA (CAN) WHEN REPLACING INBD O-RING VERY SHARP EDGE IN OIL FILTER BODY DAMAGING O-RING EVERY TIME. 1 L 7 2 3T 4 T RT 3A20 E4EA 2002021400042 20020214 00042 SW 2002 2 14 CA020104003 1 20011128 G 7930 31039721 CHIP DETECTOR GULSTM 690TP 690A 0141722 SW GARRTT TPE331 TPE3315251K NM NR 2 ENGINE CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) UPON REINSTALLATION OF THE CHIP DETECTOR DRAIN VALVE BODY IN ENGINE NR 1 BEFORE TORQUE VALVE WAS OBTAINED (75 IN L B) , THE NUT PORTION WHICH INCLUDES A RECEPTICLE FOR THE CHIP DETECTOR SEVERED OFF. INSPECTION OF THE PART SHOWED PRESE NCE OF PREVIOUS CRACKING AROUND THE RADIUS. THE VALVE BODY WAS REMOVED FROM NR 2 ENGINE AND FOUND IT WAS ALSO CRACKED A ROUND THE RADIUS OF THE NUT. THE REMAINING AIRCRAFT IN THE FLEET WILL BE INSPECTED FOR ANY DAMAGE IN THIS AREA. 1 H 7 2 3T 4 T 2A4 E2WE 2002021400043 20020214 00043 EU 2002 2 14 CA020104004 1 20011211 G 2432 WIRE SNIAS 350 AS350B2 8680813 EU TMECA ARRIEL ARRIEL1D NE BATTERY BURNED W O OTHER B SMOKE/FUMES/ODORS/SPARKS LD LANDING 1 CA (CAN) JUST PRIOR TO LDG PILOT SMELLED SOMETHING LIKE PLASTIC OR RATHER BURNING BUT NOT SMOKE. AFTER SHUTTING DOWN, PIL OT COULD SEE SMOKE INSIDE TAILBOOM & STRONG SMOKE OF SOMETHING ELECTICAL SMOKING IN MAIN CARGO BAY, PILOT INVESTIGATED FURTHER TO FIND SOURCE & FOUND NOTHING OUT OF ORDINARY. PILOT TRIED START WHEN GUIDE & PASSENGER COULD SEE 3 SPARKS UND ER BELLY OF A/C. FURTHER INVESTIGATION LEAD TO BATTERY BAY. ONE OF WIRE CONNECTORS ON POSITIVE POST OF BATTERY GOT WELD ED TO BATTERY CASE. BOTTOM OF BATTERY CASE BURNT&SOURCE TO GROUND TO AIRFRAME. ARE 2 WIRES OR CABLES TO POSITIVE POST OF BATTERY. 1 G 7 1 3U 3 U H9EU E19EU 2002021500011 20020215 00011 2002 2 15 CA020104012 4 20011130 G 3421 GYRO BOEING 737 737275 1384485 NM PWA JT8 JT8D9A 52048 NE COCKPIT FAILED W C ABORTED TAKEOFF O OTHER TO TAKEOFF 1 CA 49328 49328 (CAN) ON TAKE OFF FROM EDMONTON, ELECTRICAL SPIKE MOMENTARILY FLAG CAPT.'S ADI AUTOPILOT, WHEN SELECTED ON TRIPPED, TRIE D ONE MORE TIME AND WITH LIGHT PRESSURE ON ELEVATOR ON AUTOPILOT TRIPPED AGAIN. NUMBER 1 VERTICAL GYRO AND AIR DATA COMP UTER REPLACED. SYSTEM CHECKED SERVICEABLE. 2 L 7 2 4F 4 F A16WE E2EA 2002021500027 20020215 00027 NE 2002 2 15 CA020104021 2 20011231 G 7323 LN9367GE12N2 BEARING BOLKMS 117 BK117B1 5626012 EU LYC LTS101 LTS101750B1 41560 NE TURBINE GOVERNOR CONTAMINATED W C ABORTED TAKEOFF E J VIBRATION/BUFFET WARNING INDICATION TO TAKEOFF 1 CA (CAN) LACK OF DROOP COMPENSATION OBSERVED BY PILOTS. ENGINEERING NOTIFIED. ENGINEERING DISCOVERED A BINDING BEARING IN T HE N2 CONTROL SYSTEM, LOCATED IN CABIN CEILING. BEARING WAS CLEANED OF DIRT, LUBRICATED AND FUNCTION TESTED SERVICABLE. 1 G 7 2 3U 3 U H13EU E5NE10 2002021500029 20020215 00029 NE 2002 2 15 CA020104022 2 20011231 G 7323 LN9367GE5DN2 BEARING BOLKMS 117 BK117B1 5626012 EU LYC LTS101 LTS101750B1 41560 NE TURBINE GOVERNOR WORN W C ABORTED TAKEOFF E J VIBRATION/BUFFET WARNING INDICATION TO TAKEOFF 1 CA (CAN) WHEN INSPECTING THE N2 DROOP SNAG(PLEASE SEE PREVIOUS SDR ON SAME DAY), THE BALL WAS DISCOVERED TO BE WORN THROUGH THE SOCKET. THE ARM ASSY WAS REPLACED BY A SERVICABLE UNIT AND THE HELICOPTER WAS RETURNED TO SERVICE. 1 G 7 2 3U 3 U H13EU E5NE10 2002021500030 20020215 00030 SW 2002 2 15 CA020104023 1 20011227 G 6230 OIL JET BELL 212 212 1181420 SW PWA PT6T PT6T3 52045 EA M/R MAST MISLOCATED W K NONE W INADEQUATE Q C IN INSP/MAINT 1 CA (CAN) DURING INSTALLATION OF MAIN ROTOR MAST ASSEMBLY IT WAS VISUALLY IDENTIFIED THAT THE OIL JET WAS LOCATED IN THE WRO NG POSITION FOR CONNECTION OF OIL SUPPLY LINE. PART WAS REPLACED WITH SERVICEABLE UNIT. 1 G 7 1 4U 4 U H4SW E22EA 2002021500034 20020215 00034 EA 2002 2 15 CA020108002 2 20011127 G 8530 AEL6510241 CYLINDER CESSNA 172 172P 2072436 CE LYC O320 O320D2J 41508 EA ENGINE CRACKED W A UNSCHED LANDING E R VIBRATION/BUFFET PARTIAL RPM/PWR LOSS CL CLIMB 1 CA (CAN) DURING CLIMB THE PILOT NOTICE A LOSS OF POWER AND ENGINE VIBRATION. RETURNED TO BASE. MAINTENANCE FOUND NR 3 CYLI NDER CRACKED AT THE EXHAUST VALVE. THIS IS THE 3RD CYLINDER ON 2 DIFFERENT ENGINES TO CRACK IN THIS PLACE. ALL CYLINDE RS REMOVED AND RETURNED TO SUPPLIER. OVERHAULED CYLINDERS INSTALLED AND AIRCRAFT RETURNED TO SERVICE. 1 H 7 1 3O 3 O NT 3A12 E274 2002021500035 20020215 00035 EA 2002 2 15 CA020108003 2 20011214 G 7314 025323300 PUMP PIPER PA42 PA42 7104202 SO PWA PT6 PT6A41 52043 EA FUEL SYS STRIPPED W A UNSCHED LANDING X Y J ENGINE FLAMEOUT ENGINE STOPPAGE WARNING INDICATION CR CRUISE 1 CA (CAN) ENGINE SHUT DOWN IN CRUISE FLIGHT. AIRCRAFT MADE AN UNSCHEDULED LANDING TROUBLESHOOTING REVEALED NO FUEL FLOW TO DIVIDER. HIGH PRESSURE FUEL PUMP REMOVED. FUEL PUMP SPLINES FUND TO BE STRIPPED. PUMP REPLACED. 1 L 7 2 4T 4 T A23SO E4EA 2002021500036 20020215 00036 EU 2002 2 15 CA020109001 1 20011203 G 5302 11203025221 FLANGE BOLKMS 117 BK117A1 5626010 EU TAILBOOM CORRODED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) TAILBOOM SENT FROM A CUSTOMER IN THE USA FOR REPAIR OF A DAMAGED SKIN. DURING DISASSEMBLY THE TAILBOOM TO FUSELAG E ATTACHMENT RING FOUND CORRODED. AT THE 1:00 AND 11:00 O'CLOCK POSITION DEPTH 1 MM AT THE 2:00 AND 10:00 O'CLOCK POSI TION 0.2 MM AT THE 6:00 O'CLOCK POSITION DEPTH OF 0.6MM. 1 G 7 2 3U H13EU 2002021500037 20020215 00037 EA 2002 2 15 CA020109002 2 20011102 G 8520 LW1594485 CRANKSHAFT LYC O320 O320H2AD 41508 EA MAIN JOURNAL CORRODED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) CORROSION FOUND UNDER URETHABOND COATING APPLIED BY FACTORY AT OVERHAUL AS PER SB 505B AND SB 530A AND AD 98-02-0 8.CRANKSHAFT HAS BEEN RETURNED TO FACTORY FOR WARRANTY CONSIDERATION AND INSPECTION. 3 O E274 2002021500039 20020215 00039 EA 2002 2 15 CA020109005 2 20011214 G 7261 PT6A27 ENGINE BEECH 99 99A 1154003 CE PWA PT6 PT6A27 52043 EA HARTZL HCB3T HCB3TN3 GL NR 2 CONTAMINATED W A UNSCHED LANDING J WARNING INDICATION CL CLIMB 1 CA 14795 (CAN) OIL CONTAMINATION NR 2 LIGHT ILLUMINATED AFTER TAKEOFF, DURING CLIMB OUT. RETUNED FOR LANDING. LANDING WAS UNEVE NTFUL. MAINTENANCE INSPECTION REVEALED OIL CONTAMINATED WITH METAL PARTICLES. 1 L 7 2 3T 4 T A14CE E4EA 6 C P15EA 2002021500041 20020215 00041 SO 2002 2 15 CA020109006 1 20011221 G 2140 COMBUSTION LINER PIPER PA31 PA31325 7103105 SO LYC O540 LTIO540F2BD 41533 EA HEATER BURNED W O OTHER B SMOKE/FUMES/ODORS/SPARKS CR CRUISE 1 CA (CAN) PILOT SMELLED FUMES IN THE CABIN. HE SHUT OFF THE JANITROL HEATER. HEATER WAS REMOVED AND INSPECTED FOUND A HOL E BURNED THROUGH COMBUSTION TUBE. INSTALLED NEW OVERHAULED HEATER. 1 L 7 2 3O 3 O A20SO E14EA 2002022800002 20020228 00002 EU 2002 2 28 CA020110003 1 20011223 G 2420 IDG HAMSTD AIRBUS 320 A320211 3930320 EU CFMINT CFM56 CFM565A1 NE IDG OVERHEATED W H DEACTIVATE SYST/CIRCUITS J WARNING INDICATION AP APPROACH 1 CA (CAN) @1 IDG OIL PRESSURE AND OVERHEAT ON ON DESCENT TO YVR. TEMPERATURE GRADUALLY RISING (PULSATING GREEN) ECAM ACTION CARRIED OUT. IDG DISCONNECTED PRIOR LANDING.IDG FOUND OVERSERVICED. MEL 24-20-01 APPLIED. OIL STILL FLUCTUATING.IDG REPL ACED AS PER AMM 24-21-51. 2 L 7 2 4F 4 F RT A28NM E29NE 2002021500093 20020215 00093 SW 2002 2 15 CA020112001 1 20011203 G 2810 71493 FUEL TANK BBAVIA 8 8GCBC 1220803 SW LYC O360 O360C2A 41514 EA LT WING LEAKING W K NONE K FLUID LOSS IN INSP/MAINT 1 CA (CAN) FUEL LEAK DISCOVERED BY VISIAL INSPECTION AT FABRIC DRAIN HOLES IN TE OF WING. INBOARD FUEL TANK OF LEFT WING R EMOVED AND PIN HOLE FOUND IN THE WELD WHERE DRAIN BOSS WHERE FUEL HOSE ATTACHES. BOSS REWELDED AND PRESSURE TESTED TANK . NO FURTHER LEAKS FOUND. 1 H 7 1 3O 3 O A21CE E286 2002021500094 20020215 00094 SO 2002 2 15 CA020114001 1 20010812 G 8120 LW12463 SEAL GARRTT LW12463 PIPER PA31 PA31350 7103110 SO LYC O540 TIO540J2BD 41532 EA RT ENGINE LEAKING W O OTHER B SMOKE/FUMES/ODORS/SPARKS CL CLIMB 1 CA AG020227 (CAN) TURBO OIL SEAL LEAKING (EXHAUST SIDE). ABORT TAKEOFF. LOST POWER ON RT AND SMOKE. 1 L 7 2 3O 3 O A20SO E14EA 2002021500100 20020215 00100 NE 2002 2 15 CA020114008 2 20011116 G 7200 ENGINE PWA JD15 JT15D1A NE LT OR RT FAILED W O OTHER R J PARTIAL RPM/PWR LOSS WARNING INDICATION NR NOT REPORTED 1 CA (CAN) ENGINE WAS UNABLE TO ACHIEVE THE RATED POWER WITHIN THE SPECIFIED TEMPERATURE LIMITS. THE OPERATOR DECIDED TO PER FORM AN HSI AND REMOVED THE HOT SECTION COMPONENTS FOR SHIPMENT TO ATLANTIC TURBINES FACILITY IN ATLANTA. AT THIS POINT IT WAS NOTED THAT THE ENGINE HAD SUSTAINED AN HP TURBINE BLADE FAILURE WITH CONSIDERABLE FOD. THE HP & LP TURBINE COMPON ENTS WERE FORWARDED TO ATLANTIC TURBINES FOR INVESTIGATION AND RESTORATION TO SERVICEABLE CONDITION. 4 F E25EA 2002021500101 20020215 00101 EA 2002 2 15 CA020114009 2 20011130 G 7200 ENGINE PWA PT6 PT6A41 52043 EA LT OR RT FAILED W O O OTHER OTHER Y J ENGINE STOPPAGE WARNING INDICATION NR NOT REPORTED 1 CA (CAN) ENGINE WAS SENT TO ATI FOR INVESTIGATION AND REPAIR AFTER THE OPERATOR REPORTED THAT ENGINE HAD BEEN SHUT DOWN IN FLIGHT. THE OPERATOR REPORTED THAT DURING THE APPROACH THE PILOT HAD NOTICED THE TURBINE INTERSTAGE TEMPERATURE HAD INCR EASED TO 950 DEGREES C, AND HAD SHUT DOWN THE ENGINE AND LANDED ON THE ONE REMAINING ENGINE. THE OPERATOR HAS SPLIT THE ENGINE, NOTED EXTENSIVE INTERNAL DAMAGE, AND RE-ASSEMBLED THE UNIT PRIOR TO SHIPMENT TO ATI. 4 T E4EA 2002021500102 20020215 00102 CE 2002 2 15 CA020116001 1 20011130 G 3310 A91641 BRACKET CESSNA 310 310R 2074245 CE CONT O520 IO520MB 17032 SO MCAULY 3AF32C 3AF32C87 GL LIGHT BROKEN W F ACTIVATE FIRE EXT. A FLAME/FIRE AP APPROACH 1 CA (CAN) FIRE IN COCKPIT ON DESCENT FROM FLIGHT TO AIRPORT. SMOKE EMITING FROM RT DASH BY PROP DE-ICE GAUGE. SMOKE TURNED TO FLAME AND EXTINGUISHER EXERCISED. EXAMINATION REVEALED POST LIGHT PLASTIC BROKEN AND FELL DOWN TO METER. LINE POST LIGHT SHORTED ON METER TERMINAL. POST LIGHT SOCKET PLASTIC HEATED UP AND PLASTIC CAUGHT FIRE. 1 L 7 2 3O 3 O 3A10 E5CE 5 C P22EA 2002021500106 20020215 00106 GL 2002 2 15 CA020116007 3 20011106 G 6114 PROPELLER MOONEY M20 M20C 5870208 SW LYC O360 O360A1D 41514 EA HARTZL HCC2Y HCC2YR1 GL FORWARD DAMAGED W K NONE L NO TEST IN INSP/MAINT 1 CA (CAN) OWNER DISCOVERED PROP WOULD NOT CYCLE AT PRE-FLIGHT INSPECTION. AIRCRAFT WAS BROUGHT TO THE SHOP AND THE SPINNER WAS REMOVED. GREASE FITTINGS WERE REMOVED AND OIL BEGAN TO RUN OUT. PROP WAS REMOVED AND SENT FOR INSPECTION. 1 L 7 1 3O 3 O 2A3 E286 5 C P920 2002021900056 20020219 00056 SO 2002 2 19 CA020117010 1 20011120 G 2460 454709 CIRCUIT BREAKER PIPER PA28 PA28181 7102807 SO LYC O360 O360A4M 41514 EA COCKPIT BROKEN W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) AT A ROUTINE 100 HOUR ANNUAL INSPECTION IT WAS DISCOVERED THAT TWO CIRCUIT BREAKERS HAD BROKEN REAR ATTACHMENT L UG AT THE BUS BAR ATTACH POINT. 1 L 7 1 3O 3 O 2A13 E286 2002021900125 20020219 00125 EU 2002 2 19 CA020117017 1 20011210 G 5240 A2151060200200 DOOR AIRBUS 310 A310 EU GE CF6 CF680C2A5 NE FUELING PANEL MISSING W O OTHER D INFLIGHT SEPARATION LD LANDING 1 CA (CAN) FOUND REFUELING PANEL DOOR MISSING ON ARRIVAL TO "VRA". REFUELING DOOR AND AN AIR INLET PANEL WERE REPLACED. 2 L 7 2 4F 4 F RT A35EU E13NE 2002021900126 20020219 00126 WP 2002 2 19 CA020117018 1 20011204 G 2780 CONTROL VALVE LKHEED 1011 10113853 5265020 WP RROYCE RB211 RB211524B402 54555 NE LE FLAPS MALFUNCTIONED W A UNSCHED LANDING F J FLT CONT AFFECTED WARNING INDICATION CL CLIMB 1 CA (CAN) ON FERRY FLIGHT TSC 2257 FROM CUN-YMX , DURING TAKE OFF , SLAT SYSTEM LOCKED IN EXTEND POSITION , BUT FLAPS RAIS ED FULL UP. FLAP RED LIGHT WAS ILLUMINATED ON THE FLAP POSITION INDICATOR (PILOTS CENTER INSTRUMENTS PANEL) AND SLAT MON ITOR INDICATED SLATS AT 30 DEGREES.-AIRCRAFT RETURNED TO "CUN".-ON GROUND , POP OUT INDICATOR FOUND OK ON BOTH WING FOR BRAKE INDICATOR. -C/B RESETTED , SYSTEM TEST C/OUT IN ACCORDANCE WITH M.M. 27-81-00. NO FAULTS FOUND.-NO DEFECTS WERE RE PORTED AFTER TAKE OFF. 2 L 7 3 4F 4 F A23WE E12EU 2002021900127 20020219 00127 EU 2002 2 19 CA020118001 1 20011220 G 2780 4907905 CONTROL UNIT AIRBUS 310 A310300 3930305 EU GE CF6 CF680C2A5 NE LE FLAPS MALFUNCTIONED W O OTHER J WARNING INDICATION AP APPROACH 1 CA (CAN) MANY INDICATIONS (DEFECTS REPORTED) OF SLATS / FLAPS SYSTEM NR 1 & 2 FAULTS HAVE BEEN REPORTED ON AIRCRAFT, HAVI NG SEVERAL MAINTENANCE ACTION C/OUT FROM 2001-11-25 TO 2001-12-20 AND THE FINAL RECTIFICATION BEING THE REPLACEMENT OF T HE LAT FLAP CONTROL COMPUTER (SFCC); _DATE 2001-12-20 ; FLAPS SYS NR 2 FAULT WITH SPEED LIMIT ON RT SIDE PFD SLATS AND FLAPS MOVE AT HALF SPEED ALL MTCE ACTIONS C/O AND "O" OPERATION FOR FLIGHT CREW PLACED ON DMI AS PER MEL 27-18 A C T I ON TA KE N SFCC 2 REPLACED IAW 27-51-18 AND BITE TEST PERFORMED.CHECKED SERVICEABLE. 2 L 7 2 4F 4 F RT A35EU E13NE 2002021900128 20020219 00128 SW 2002 2 19 CA020118003 1 20010725 G 6230 2060400365 BEARING BELL 20601033217 BELL 206 206B 1181511 SW ALLSN 250C 250C20 03013 GL MAIN ROTOR MAST SPALLED W K NONE O OTHER IN INSP/MAINT 1 CA FAJF56057 (CAN) UPON INSPECTION 3 BALL BEARINGS, FOUND EXCESSIVELY SPALLED AND INNER RACE SHOWED 3 SIGNS OF PITTING IN 3 AREAS. B EARING WAS SCRAPPED. 1 G 7 1 3U 3 U H2SW E4CE 2002021900129 20020219 00129 SW 2002 2 19 CA020118004 1 20010725 G 6230 20601033217 MAST BELL 206 206B 1181511 SW ALLSN 250C 250C20 03013 GL MAIN ROTOR CORRODED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) UPON 1500 HOUR INSPECTION OF MAST BEARING RETAINING NUT REMOVAL. PRC SEALANT WAS REMOVED FROM THE LOWER MAST THREA DS TO UNCOVER CORROSION PITTING WELL IN EXCESS OF CORROSION TOLERANCES. MAST WAS SCRAPPED. 1 G 7 1 3U 3 U H2SW E4CE 2002021900130 20020219 00130 EU 2002 2 19 CA020118005 1 20011221 G 2910 AE71112111 LINE AIRBUS 330 A330243 3930330 EU RROYCE RB211 RB211TRENT77 NE HYD SYSTEM MISINSTALLED W K NONE W INADEQUATE Q C IN INSP/MAINT 1 CA 41063 (CAN) -DURING CURRENT C03 /A06 HEAVY MAINT VISIT , NR 2 HYDRAULIC PUMP PRESSURE TUBE POSED WITH NO CLEARANCE WITH RESPEC T TO THE FUEL / OIL HEAT EXCHANGER HOUSING (ADJACENT TO THE FUEL INLET). AFTER NUMEROUS TIMES OF REPOSING LINE PER AMM G UIDELINES , MIN CLEARANCE OF 0.100 INCH COULD NOT BE ACHIEVED. 2 L 7 2 4F 4 F RT A46NM E39NE 2002021900132 20020219 00132 EU 2002 2 19 CA020118007 1 20011207 G 2913 974976 PUMP AIRBUS 330 A330243 3930330 EU RROYCE RB211 RB211TRENT77 NE HYD SYSTEM FAILED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) NR 2 ENGINE, YELLOW HYDRAULIC PUMP, SUCTION LINE CONNECTOR LOOSE AT MOUNTING PUMP. THE PUMP WAS REPLACED I.A. W. AMM 29-11-51 2 L 7 2 4F 4 F RT A46NM E39NE 2002021900139 20020219 00139 NM 2002 2 19 CA020121008 1 20011115 G 5521 657378436 SPAR BOEING 737 737217 1384464 NM PWA JT8 JT8D17 52049 NE RT ELEVATOR CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) RT ELEVATOR REAR SPAR AT TRIM TAB ATTACHMENT POINT FOUND CRACKED. ELEVATOR REMOVED FOR REPAIR, LOCATION OF DAMAG ED LOCATED AT STATION 66.54 REPLACED ELEVATOR. DAMAGE REPAIRED AS PER SRM 2 L 7 2 4F 4 F A16WE E2EA 2002022000002 20020220 00002 EU 2002 2 20 CA020121012 1 20011218 G 2910 AE7111216 LINE AIRBUS 330 A330243 3930330 EU RROYCE RB211 RB211TRENT77 NE HYD SYSTEM WORN W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) - DURING CURRENT C03 /A06 HEAVY MAINTENANCE VISIT, ENGINE NR 2, A HYDRAULIC LINE, WAS FOUND TO BE RUBBING HARD AGAINST THE AIR OIL HEAT EXCHANGER, THE RUBBER PROTECTIVE COATING WAS GOUGED (BUT NOT THROUGH ), STILL WITHIN REPAIRA BLE LIMITS. 2 L 7 2 4F 4 F RT A46NM E39NE 2002022000005 20020220 00005 2002 2 20 CA020122003 4 20011219 G 3197 WIRE BEECH 1900 1900D 1154162 CE PWA PT6 PT6A67D NE HARTZL HCE4A HCE4A3I NE INSTRUMENT PANEL BINDING W O OTHER O OTHER DE DESCENT 1 CA (CAN) ON DESCENT INTO ST. JOHN'S, YYT, PILOT NOTICED THAT HE HAD NO AURAL WARNINGS FOR DECISION, H8, ALTITUDE, ALERT, OVERSPEED, GEAR WARNING OR STALL WARNING. MAINT INSPECTED PLUGS FOR AURAL AMPLIFIERS & NOTHING APPEAR TO BE WRONG. WI RING INSP & FOUND 2 WIRES HAD BEEN CHAFED BY LARGE PLASTIC TYWRAPS. ONE WIRE (CODE 24A22) FOR 28VDC INPUT OF AURAL ANNUN CIATOR AMPLIFIER, P/N 207 & AN OTHER WIRE AT PLUG W314P8 FOR CO-PILOTS SPEAKERS. WIRING REPLACED BY MEANS OF BUTTSPLICES . OPAL CHECKS WERE CARRIED OUT FOR APPLICABLE WARNINGS & CHECKED SERVICEABLE. WIRES IN QUESTION WERE TIE WRAPPED AT A PO INT WHERE BUNDLE WAS BENDING. IF TIE WRAPS HAD TO BE 1CM ON EITHER SIDE OF BEND THIS WOULD NOT HAVE HAPPENED. 2 L 7 2 4T 4 T RT A24CE E26NE 5 C P10NE 2002020500147 20020205 00147 2002 2 5 CA020122004 4 20011115 G 3400 ELT1104 ELT ARTEX BEECH 1900 1900D 1154162 CE PWA PT6 PT6A67D NE HARTZL HCE4A HCE4A3I NE ELT FAILED W O OTHER O OTHER IN INSP/MAINT 1 CA 57781 (CAN) ELT REMOTE SWITCH INDICATOR LIGHT ON IN THE HANGAR WITH NO SIGNAL BEING RECEIVED ON COMM FREQUENCY 121-5. ELT AND WIRING INSPECTED AT ZONE 312, WIRES W3150-12, W3150-13 AND W3150-15 FOUND CHAFED AND GROUNDING OUT. PLASTIC TYWRAP AND P LASTIC CLAMP CUTTING INTO WIRING. WIRING SPLICED AND SPIRAL WRAP INSTALLED AROUND WIRE BUNDLE AND PROTRUDING THROUGH CLA MP TO ENSURE FAULT WOULD NOT RE-OCCUR. ELT UNIT REPLACED AND OPERATIONAL CHECK CARRIED OUT. 2 L 7 2 4T 4 T RT A24CE E26NE 5 C P10NE 2002022000013 20020220 00013 CE 2002 2 20 CA020124003 1 20011212 G 3242 30146 HOUSING BEECH 100 100BEECH 1152916 CE PWA PT6 PT6A28 EA BRAKE ASSY DAMAGED W O OTHER K R FLUID LOSS PARTIAL RPM/PWR LOSS LD LANDING 1 CA 18687 (CAN) THE PILOT REPORTED WHEN STOPPING AT THE RAMP THE LT BRAKE PEDAL WENT TO THE FLOOR. UPON INSPECTION THE LT FWD CAL IPER WAS FOUND DRAGING ON THE GROUND. IT WAS DISCOVERED AFTER THE MISSING PARTS WERE OBTAINED AFT THE TAXI-WAY, THAT TH E BOLT HOLDING THE DOWL PIN INTO THE CALIPER HAD WORKED LOOSE, & THE DOWL PIN UNSCREWED OUT OF THE CALIPER DISENGAGING T HE CALIPER FROM THE BACK PLATE. (HOWEVER THE BOLT WAS STILL CORRECTLY LOCKWIRED IN POSITION.) THE CALIPER THEN FELL DOWN HITTING THE GROUND AND DISINTEGRATING. INSPECTION OF THE BOLTS ASSEMBLED THERE IS NO INDICATION THAT THE DOWL PIN IS LO OSE OR NOT, MISLEADING THE INSPECTOR TO THINK ALL IS OK. 1 L 7 2 3T 4 T A14CE E4EA 2002022000061 20020220 00061 EU 2002 2 20 CA020129004 1 20011114 G 2520 NAS110436 BOLT ISRAEL 1125 ASTRASPX 4500205 EU SEAT BELT FAILED W O OTHER O OTHER DE DESCENT 1 CA (CAN) UPON DEPLANING OF A/C AT DESTINATION, PASSENGER NOTIFIED CAPTAIN THAT OUTBOARD PORTION (LATCH SIDE) OF HIS SEAT BE LT HAD BECOME DETACHED FROM HIS SEAT WHEN HE ATTEMPTED TO SECURE IT FOR DESCENT INTO AIRPORT. HE HAD THEN MOVED TO ONE O F UNOCCUPIED SEATS IN PREPARATION FOR LDG. MAINT DISCOVERED THAT NUT & SPACER-BUSHING WERE MISSING FROM SEAT BACK PIVOT / SHACKLE RESTRAINT BOLT, WHICH HAD ALLOWED SEAT BELT SHACKLE TO COME DETACHED FROM SEAT (S/N 15065) 2 L 7 2 4F RT A16NM 2002022000065 20020220 00065 EA 2002 2 20 CA020130002 1 20011212 G 2710 CONTROL CABLE CNDAIR CL215 CL2156B11215 EA AILERONS WORN W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) AILERON CABLE WORN BEYOND LIMITS. 2 H 7 2 4T RT A14EA 2002022000069 20020220 00069 CE 2002 2 20 CA020130006 1 20011121 G 2433 D2FF10B379AA RECTIFIER FORD POFF10300F CESSNA 150 150M 2071830 CE CONT O200 O200A 17020 SO MCAULY 1A102 1A102OCM GL ALTERNATOR WORN W A UNSCHED LANDING H ELECT. POWER LOSS-50 PC AP APPROACH 1 CA A146794 (CAN) ALTERNATOR RECTIFIER FAILED CAUSING ELECTRICAL FAILURE DURING FLIGHT. 1 H 7 1 3O 3 O 3A19 E252 5 N P918 2002032100092 20020321 00092 NM 2002 3 21 CA020131007 1 20011128 G 2140 4100S02801 ADAPTER DHAV DHC8 DHC8* NM PWC 150 PW150A EA ENGINE BURNED W O OTHER J WARNING INDICATION AP APPROACH 1 CA 75 (CAN) DURING THE FINAL APPROACH OF FLIGHT 5632 ON THE 28 NOVEMBER 2001, THE PILOT OF AIRCRAFT DHC8400 S/N 4027, REPORTED THAT THE ENGINE ADAPTER NR 1 CL CAME ON AND THE C/B POPPED. INVESTIGATION FOUND THE NR 1 HEATER INTAKE ADAPTER IN BURN ED CONDITION. 2 H 7 2 4T 4 T RT A13NM E00062EN 2002022000077 20020220 00077 NE 2002 2 20 CA020131008 2 20011209 G 7314 324485317 FUEL CONTROL DHAV DHC8 DHC8301 NM PWA PW120 PW123 NE HAMSTD 14SF 14SF23 NE NR 2 ENGINE FAILED W E A ENGINE SHUTDOWN UNSCHED LANDING Y E J ENGINE STOPPAGE VIBRATION/BUFFET WARNING INDICATION CL CLIMB 1 CA (CAN) ON TAKEOFF ROLL NR 2 ENGINE CAUTION LIGHT FLICKERED. WERE NO ABNORMAL IND.S. AFTER TAKEOFF AT 600 FT MSL NR 2 ENGI NE MANUAL CAUTION LIGHT ILLUMINATED FOLLOWED BY COMPLETE FAILURE OF NR 2 ENGINE. ENGINE AUTO-FEATHERED, ALL ENGINE PARA METERS INDICATED ZERO EXCEPT ITT WHICH AT 126. ENGINE FAILURE / FIRE SHUTDOWN DRILL CARRIED OUT. LDG COMPLETED SUCCESSFU LLY. ALSO NOTED, THAT DURING TAXI PILOT NOTICED EEC LIGHT ILLUMINATED ACCOMPANIED BY MILT TQ SUR GE&THEN RETURNED TO NRO MAL. MAINT FINDINGS: ENGINE EXTERNALLY INSP, PRE-COOLER DISCOVERED CRACKED BUT NOT ENOUGH TO BE CONTRIBUTING FACTOR AS B LEEDS HAD NOT BEEN SELECTED ON. ENGINE OIL FILTERS CHECKED - NO FAULTS FOUND. 2 H 7 2 4T 4 T RT A13NM E20NE 6 C P7NE 2002032100095 20020321 00095 NM 2002 3 21 CA020131010 1 20011205 G 2613 10109601 SWITCH DHAV DHC8 DHC8* NM PWC 150 PW150A EA OVERHEAT SENSOR FAILED W E F ENGINE SHUTDOWN ACTIVATE FIRE EXT. N FALSE WARNING AP APPROACH 1 CA (CAN) DURING APPROACH TO BASE AT 2,500 THE NR 1 ENGINE INDICATED A FIRE CONDITION. ONCE ENGINE SECURED, (PER IAC) T-HAND LE INDICATION EXTINGUISHED. CONTINUED WITH CHECK LIST (DID NOT FIRE BOTTLES), FIRE INDICATION REAPPEARED (T-HANDLE LIGHT & BELL). FIRED BOTH BOTTLES ACCOMPLISHED SAFE EMERGENCY LANDING WITHOUT INCIDENT. NO ENGINE INSTRUMENT OR OTHER VISUAL INDICATIONS WERE OBSERVED, BUT DUE TO WEATHER COULD NOT VISUALLY OBSERVE NR 1 ENGINE NACELLE. INVESTIGATION FOUND FAIL ED CLOSED FIRE/OVERHEAT SENSOR SWITCH, INTERNAL WARNING SWITCH CLOSED AS MEASURED ACROSS PINS A & D.1343.0 HOURS/1841 CY CLES. 2 H 7 2 4T 4 T RT A13NM E00062EN 2002030800066 20020308 00066 SO 2002 3 8 CA020211013 1 20010709 G 8011 636058 WORM GEAR CONT PIPER PA36 PA36285 7103610 SO LYC O540 IO540K1G5 41532 EA STARTER CLUTCH BROKEN W O OTHER O OTHER TX TAXI/GRND HDL 1 CA (CAN) THE PILOT COULD NOT START THE ENGINE. NOTED THAT ALTHOUGH THE STARTER APPEARED TO SPIN, IT WAS NOT TURNING THE E NGINE. THE AME INVESTIGATED AND DETERMINED THAT THE PROBLEM WAS INTERNAL. THE ENGINE WAS DISMANTLED TO REVEAL THE START ER WORM GEAR BROKEN IN 3 PLACES. PREVIOUSLY, THE ENGINE HAD BEEN KICKING BACK EXCESSIVELY ON STARTUP. IT WAS FOUND THAT THE MAGNETO SHOWER OF SPARKS WAS WIRED TO THE ADVANCE POINTS RATHER THAN THE RETARD AND THIS COULD HAVE WEAKENED THE WO RM GEAR TO THE POINT OF SUBSEQUENT FAILURE. 1 L 7 1 3O 3 O A10SO 1E4 2002031100004 20020311 00004 EA 2002 3 11 CA020219001 2 20011213 G 8520 LW19340 CAMSHAFT PIPER PA31 PA31350 7103110 SO LYC O540 TIO540* 41532 EA HARTZL HCE3Y HCE3YR2A GL ENGINE WORN W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) IN THE PROCESS OF PREFORMING A CYLINDER CHANGE, THE MECHANIC WAS UNABLE TO GET THE REQ'D VALVE CLEARANCE WITH THE APPLICABLE PUSHROD LENGHTS. UPON REMOVAL OF THE CYLINDER AND FURTHER INVESTIGATION, IT WAS DETERMINED THAT THE CAM LOBE WAS TOO WORN TO ALLOW THE LONGEST AVAILIABLE PUSHROD TO BRING THE VALVE CLEARANCE INTO LIMITS. THE ENGINE WAS SUBSEQUENT LY REMOVED FROM THE AIRCRAFT AND SENT TO A SERCICE FACILITY FOR REPAIR. 1 L 7 2 3O 3 O A20SO E14EA 5 C P33EA 2002031100027 20020311 00027 SO 2002 3 11 CA020226006 1 20010608 G 7931 77808 SPRING PIPER PA31 PA31350 7103110 SO LYC O540 TIO540J2BD 41532 EA OIL PRESSURE ADJ WEAK W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) OVERHAULED ENGINE INSTALLED, TEST RUN COMPLETED SATISFACTORY, ON TEST FLIGHT OIL PRESSURE DROPPED TO 65 P.S.I. AIR CRAFT LANDED AND OIL PRESSURE READJUSTED TO 75 P.S.I., BUT WAS AT MAX ADJUSTING LIMITS. REPLACEMENT ADJUSTMENT SPRING IN STALLED AND OIL SCREEN CHECKED AND METAL WAS EVIDENT AT THIS TIME, AFTER A PERIOD OF TIME THE ENGINE WAS REMOVED AND SEN T BACK TO OVERHAUL FACILITY FOR REPAIR. NO CAUSE OF CONTAMINATION WAS FOUND. 1 L 7 2 3O 3 O A20SO E14EA 2002031100028 20020311 00028 SO 2002 3 11 CA020226007 1 20011204 G 3700 442CW6 PUMP PIPER PA31 PA31350 7103110 SO LYC O540 TIO540J2BD 41532 EA VACUUM SYS FAILED W E ENGINE SHUTDOWN K FLUID LOSS TX TAXI/GRND HDL 1 CA (CAN) VACUUM PUMP INSTALLED ON ENGINE, TEST SHOWED EXCESSIVE OIL LEAK AT MOUNT BASE. OIL PRESSURE ON ENGINE WENT TO "0" INDICATED AND ENGINE WAS SHUT DOWN. REPLACEMENT PUMP INSTALLED AND OIL SCREEN DETECTED METAL IN ENGINE. 1 L 7 2 3O 3 O A20SO E14EA 2002032500015 20020325 00015 CE 2002 3 25 CA020227008 1 20010130 G 3241 CONNECTOR LEAR 35 35LEAR 5170600 CE GARRTT TFE731 TFE73122B 01518 WP ANTI-SKID SYSTEM DAMAGED W K NONE H ELECT. POWER LOSS-50 PC LD LANDING 1 CA (CAN) ON A BASE INSPECTION IT WAS NOTED THAT THE NR 1 AND NR 2 TIRES HAD FLAT SPOTS FROM SKIDDING. THERE WAS NO REPORTED ANTI-SKID FAILURE LIGHT ILLUMINATION. INVESTIGATION REVEALED THAT THE LT ANTI-SKID CONTROL VALVE WAS NOT RELEASING THE PRESSURE TO THE SKIDDING WHEEL. CONNECTOR PIN "G" ON THE CONTROL VALVE WAS FOUND TO HAVE CORRODED TO THE POINT THAT IT BROKEN OFF INSIDE THE CONNECTOR PLUG. THIS CIRCUIT CONTROLS THE RETURN SHUT-OFF SOLENOID IN THE VALVE. THE FAILURE LOGIC IN THE ANTI-SKID CONTROL BOX CHECKS THE OPERATION OF THE WHEEL TRANSDUCERS BUT DOES NOT INDICATE A FAILURE OF THE VALVE . THE CONTROL VALVE IS LOCATED IN THE WHEEL WELL WHERE IT IS SUBJECT TO WATER CONTAMINATION. 2 L 7 2 4F 4 F A10CE E6WE 2002032500025 20020325 00025 EU 2002 3 25 CA020228011 1 20011212 G 5730 PANEL AIRBUS 300 A300B4203 3930306 EU GE CF6 CF650C2 30018 NE RT WING SEPARATED W O OTHER D INFLIGHT SEPARATION TO TAKEOFF 1 CA (CAN) THIS IS BRIEF DESCRIPTION OF EVENTS LEADING UP TO INCID. OF PANEL 691AT, LOCATED ON RT UPPER WING, EXITING A/C MSN 183 AT TAKEOFF ON 8 DEC 2001.ON 11 NOV 01, PANEL REMOVED TO PERFORM INSP OF LOW SPEED AILERON HINGEBOLTS FOR CORROSION. INSPECTION COMPLETED & PANEL REINSTALLED SAME DAY. 2 L 7 2 4F 4 F RT A35EU E23EA 2002051300010 20020513 00010 WP 2002 5 13 CA020322008 1 20011207 G 5540 STRUCTURE NAMER B25 B25J 6400710 WP WRIGHT R2600 R260035 67050 EA RT RUDDER CONTAMINATED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) RT RUDDER WAS FOUND TO HAVE APROXIMATELY TWO GALLONS OF WATER INSIDE DUE TO A PLUGGED DRAIN GROMMET. FURTHER INSP ECTION FOUND DETERIORATED COTTON TAPES FROM AN OLD CECONITE FABRIC RE-COVERING JOB. RUDDER REMOVED AND RECOVERED 2 M 7 2 4R 4 R AL2 PAGE42 2002041100022 20020411 00022 NM 2002 4 11 CA020402006 1 20010430 G 2131 7612608 CONTROLLER BOEING 737 7372H4 138448C NM PWA JT8 JT8D9A 52048 NE CABIN PRESSURE FAILED W A UNSCHED LANDING J WARNING INDICATION CL CLIMB 1 CA (CAN) AIRCRAFT CABIN PRESSURIZATION FAILED ON CLIMB. AUTO FAIL WARNING LIGHT ILLUMINATED. CREW TRANSFERED TO STANDBY M ODE BUT AIRCRAFT WOULD NOT PRESSURE. AIRCRAFT RETURNED AND LANDED WITHOUT INCIDENT.MAINTENANCE CHANGED THE CABIN PRESSUR E CONTROLLER IAW MM 21-31-21 AND THE SYSTEM FUNCTION CHECKED SERVICEABLE.AIRCRAFT RETURNED TO SERVICE WITH NO FURTHER IN CIDENTS TO REPORT. 2 L 7 2 4F 4 F A16WE E2EA 2002050300024 20020503 00024 EA 2002 5 3 CA020402008 1 20011213 G 3246 GY22623 BOLT CNDAIR CL604 CL604 1900301 EA WHEEL ASSY BROKEN W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) IN THE PROCESS OF PERFORMING A D.I. THE ENGINEER FOUND A MISSING BOLT ON THE NR 4 MAIN WHEEL ASSY. UPON REMOVAL OF THE WHEEL THE HEAD OF THE BOLT AND HALF OF THE SHANK WHERE STILL IN THE INBOARD WHEEL HALF. THE THREADED END OF THE BOL T AND NUT WERE LATER FOUND BY THE HANGAR WALL. AS A RESULT THE WHEEL ASSY WAS REPLACED WITH A SERVICABLE UNIT AND REPA IRED AS PER M.M. 2 L 7 2 4F RT A21EA 2002050300027 20020503 00027 CE 2002 5 3 CA020405002 1 20011115 G 3213 740017 STRUT CESSNA 185 185C 2072808 CE CONT O470 IO470F 17026 SO MLG CRACKED W O OTHER O OTHER NR NOT REPORTED 1 CA (CAN) AS A PRECAUTION DUE TO NOT KNOWING THE HISTORY. THE MAIN LANDING GEAR LEGS WERE SENT FOR MAGNAFLUXING. TWO LONGI TUDINAL CRACKS OF ABOUT ONE AND ONE QUARTER INCH LONG WERE DETECTED ON THE LOWER THIRD OF THE LEFT HAND GEAR LEG. NOTE: PART CYCLES, PART TSN AND PART TSO TO BE DESREGARDED. 1 H 7 1 3O 3 O 3A24 3E1 2002050300029 20020503 00029 GL 2002 5 3 CA020405008 2 20010413 G 7210 NUT BELL 206 206B 1181511 SW ALLSN 250C 250C20B 03013 GL GEARBOX WORN W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) TORQUEMETER GEARSHAFT NUT WORN. 1 G 7 1 3U 3 U H2SW E4CE 2002050300030 20020503 00030 GL 2002 5 3 CA020405009 2 20010524 G 7314 1C2710FR PUMP BELL 206 206B 1181511 SW ALLSN 250C 250C20B 03013 GL FUEL BOOST INOPERATIVE W K NONE L NO TEST IN INSP/MAINT 1 CA (CAN) AFT BOOST PUMP NOT FUNCTIONAL. 1 G 7 1 3U 3 U H2SW E4CE 2002050300033 20020503 00033 GL 2002 5 3 CA020405013 2 20011004 G 7240 2303910 CASE BELL 206 206L1 1182107 SW ALLSN 250C 250C28 03013 GL COMBUST CHAMBER CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) CRACKED ARMPIT ON COMBUSTION CASE. 1 G 7 1 3U 3 U H2SW E1GL 2002050300034 20020503 00034 GL 2002 5 3 CA020405014 2 20011122 G 7250 23008593 NOZZLE BELL 206 206L1 1182107 SW ALLSN 250C 250C28B 03013 GL TURBINE SECTION BURNED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) HOT END INSPECTION REVEALED THE FIRST STAGE NOZZLE BURNT BEYOND ACCEPTABLE LIMITS. 1 G 7 1 3U 3 U H2SW E1GL 2002050300035 20020503 00035 NM 2002 5 3 CA020405015 1 20010411 G 8011 MZ4222 STARTER ROBSIN R22 R22BETA 7640110 NM LYC O320 O320B2C 41508 EA ENGINE INOPERATIVE W O OTHER O OTHER TX TAXI/GRND HDL 1 CA (CAN) STARTER NOT FUNCTIONAL. 1 G 7 1 3O 3 O H10WE E274 2002050300036 20020503 00036 NM 2002 5 3 CA020405016 1 20010601 G 2841 TRANSMITTER ROBSIN R22 R22BETA 7640110 NM LYC O320 O320B2C 41508 EA FUEL QTY IND INOPERATIVE W K NONE L NO TEST IN INSP/MAINT 1 CA (CAN) FUEL GAUGE INOPERATIVE REPLACE TRANSMITTER. 1 G 7 1 3O 3 O H10WE E274 2002050300037 20020503 00037 NM 2002 5 3 CA020405017 1 20010912 G 7921 A30915 PLATE ROBSIN R22 R22BETA 7640110 NM LYC O320 O320B2C 41508 EA OIL COOLER CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) OIL COOLER MOUNTING PLATE CRACKED. 1 G 7 1 3O 3 O H10WE E274 2002050300038 20020503 00038 SW 2002 5 3 CA020405018 1 20010706 G 2822 10274 PUMP BELL 206 206B 1181511 SW ALLSN 250C 250C20 03013 GL FUEL BOOST INOPERATIVE W K NONE L NO TEST IN INSP/MAINT 1 CA (CAN) FORWARD BOOST PUMP INOPERATIVE. 1 G 7 1 3U 3 U H2SW E4CE 2002050300039 20020503 00039 SW 2002 5 3 CA020405019 1 20010804 G 2435 23032018 STARTER GEN BELL 206 206B 1181511 SW ALLSN 250C 250C20 03013 GL ENGINE INOPERATIVE W O OTHER O OTHER TX TAXI/GRND HDL 1 CA (CAN) STARTER GENERATOR INOPERATIVE. 1 G 7 1 3U 3 U H2SW E4CE 2002050300040 20020503 00040 SW 2002 5 3 CA020405020 1 20010425 G 6230 204011430001 BEARING BELL 204011400127 BELL 212 212 1181420 SW PWA PT6T PT6T3B 52045 NE SWASHPLATE WORN W K NONE O OTHER IN INSP/MAINT 1 CA JI199175 (CAN) SWASHPLATE BEARING WORN BEYOND LIMITS. 1 G 7 1 4U 4 U H4SW E22EA 2002050300041 20020503 00041 NE 2002 5 3 CA020405021 2 20010728 G 7310 FLEX LINE BELL 212 212 1181420 SW PWA PT6T PT6T3B 52045 NE FUEL SYSTEM LEAKING W K NONE K FLUID LOSS IN INSP/MAINT 1 CA (CAN) LEAK AT CROSSOVER FLEX LINE TO AUXILIARY TANK CONNECTION. 1 G 7 1 4U 4 U H4SW E22EA 2002050300042 20020503 00042 SW 2002 5 3 CA020405022 1 20010503 G 6210 206010152003 BOLT BELL 206010200133 BELL 206 206B 1181511 SW ALLSN 250C 250C20 03013 GL M/R BLADE WORN W K NONE O OTHER IN INSP/MAINT 1 CA A498 (CAN) EXCESSIVE WEAR ON THE MAIN ROTOR BLADE BOLT SHANK. 1 G 7 1 3U 3 U H2SW E4CE 2002050300043 20020503 00043 GL 2002 5 3 CA020405023 2 20011119 G 7250 6878496 NOZZLE BELL 206 206B 1181511 SW ALLSN 250C 250C20 03013 GL TURBINE SECTION CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) FIRST STAGE NOZZLE FOUND CRACKED BEYOND ACCEPTABLE LIMITS. 1 G 7 1 3U 3 U H2SW E4CE 2002050300044 20020503 00044 SW 2002 5 3 CA020405024 1 20010708 G 2910 206076031013 SERVO BELL 206 206B 1181511 SW ALLSN 250C 250C20B 03013 GL HYD SYSTEM INOPERATIVE W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) FEEDBACK IN THE FLIGHT CONTROLS. HYDRAULIC SERVO FAILED. 1 G 7 1 3U 3 U H2SW E4CE 2002042600060 20020426 00060 SW 2002 4 26 CA020405025 1 20011114 G 5302 206030446001F BULKHEAD BELL 206B BELL 206 206B 1181511 SW ALLSN 250C 250C20B 03013 GL T/R GEARBOX BAY CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA BCJN07389 (CAN) CRACK FOUND DURING INSPECTION IN AFT LT TAIL ROTOR GEARBOX MOUNTING AREA. 1 G 7 1 3U 3 U H2SW E4CE 2002050300045 20020503 00045 GL 2002 5 3 CA020405026 2 20011128 G 7323 252466714 GOVERNOR BELL 206 206B 1181511 SW ALLSN 250C 250C20B 03013 GL ENGINE INOPERATIVE W O OTHER O OTHER TX TAXI/GRND HDL 1 CA (CAN) GOVERNOR WILL NOT HOLD 100 PERCENT IN FLIGHT. 1 G 7 1 3U 3 U H2SW E4CE 2002050600012 20020506 00012 2002 5 6 CA020411006 4 20010816 G 6113 055032110 BULKHEAD CESSNA 055032110 CESSNA 172 172P 2072436 CE LYC O320 O320D2J 41508 EA MCAULY 1C160 1C160DTM GL SPINNER CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) AFT SPINNER BULKHEAD CRACKED AT RADIUS OF PROP CUT OUT. 1 H 7 1 3O 3 O NT 3A12 E274 5 N P910 2002061200105 20020612 00105 NM 2002 6 12 CA020508014 1 20011027 G 2435 11521062 STARTER GEN DHAV DHC8 DHC8* NM PWC 150 PW150A EA ENGINE FAILED W A UNSCHED LANDING O OTHER CR CRUISE 1 CA (CAN) AT FL250 NR 2 STALL SYS & PUSHER SYS CAUTION LTS CAME ON. ACTION ACC QRH. WITHING NEXT 2 MINS SEVERAL OTHER CAUTIO N ITS CAME ON FOLLOWED BY NR 2 FMS/PFD/MFD MALFS&COMPLETE RT SIDE WITH OUT LIGHTING (COCKPIT & LDG/APPR LTS). ALSO STBY PRESSURE & HYD QTY NR 2 WERE INDICATING ZERO. DECISION TO DIVERT MADE. LDG UNEVENTFUL FOLLOWED BY NORMAL DISEMBARKATION. UPON COMPLETING "AFTER LDG CHECKLIST" RT SIDE LIGHTS CAME ON AGAIN & MOST CAUTION LTS & MESSAGES WENT OUT. AIRCRAFT GRO UNDED FOR INSP. NR 2 DC STARTER GEN REPLACED. EPCU READOUT CARRIED OUT - NO FINDINGS, OPS TEST OF MAIN 28V DC GENERATION SYS&DC BUS CONTACTOR K21 CARRIED OUT - WITHOUT FINDINGS. GCU REPLACED. EPCU REPLACED. GCU RETURN ED NFF, EPCU RETURNED 2 H 7 2 4T 4 T RT A13NM E00062EN 2002080700234 20020807 00234 EA 2002 8 7 CA020715006 1 20010621 G 5610 601R330335 WINDSHIELD CNDAIR CL600 CL6002B19 1900309 EA COCKPIT FAILED W A UNSCHED LANDING O OTHER CR CRUISE 1 CA (CAN) CAPTAIN`S WINDSHIELD SHATTERED WHILE IN CRUISE AT 35,000 FEET. PRESSURIZATION WAS NORMAL. FLIGHT DIVERTED TO TXK. 2 L 7 2 4F RT A21EA 2002091800047 20020918 00047 SO 2002 9 18 CA020905004 1 20010830 G 8120 BEARING GARRTT LW12463 PIPER PA31 PA31350 7103110 SO LYC O540 LTIO540J2BD 41533 EA TURBOCHARGER STIFF W A UNSCHED LANDING R J PARTIAL RPM/PWR LOSS WARNING INDICATION CR CRUISE 1 CA LBR0200 (CAN) MANIFOLD PRESSURE FLUCTUATING.TURBOCHARGER TURBINE WHEEL FOUND STIFF TO SPIN. 1 L 7 2 3O 3 O A20SO E14EA 2002120600023 20021206 00023 CE 2002 12 6 CA021101007 1 20011030 G 7160 109910029115 SKIN BEECH 90 C90A 1152911 CE PWA PT6 PT6A21 52043 EA AIR INLET CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) ENGINE AIR INLET COWLING FOUND CRACKED ALONG STIFFENER RIVET LINE. 1 L 7 2 3T 4 T RT 3A20 E4EA 2002120600051 20021206 00051 EA 2002 12 6 CA021108007 2 20010731 G 7414 67542 BEARING PIPER PA23 PA23250 7102308 SO LYC O540 IO540C4B5 41532 EA LT MAGNETO DESTROYED W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) RT ENGINE, LT MAGNETO ENGINE HOURS: 745.2 DAMAGE WAS DISCOVERED DURING ROUTINE SCHEDULED MAGNETO REPLACEMENT. WHEN THE MAGNETO WAS REMOVED THE MAGNETO GEAR RETAINER ASSY AND BEARING PULLED OUT OF THE ENGINE TOGETHER WITH THE DRIVE CO UPLING.UPON FURTHER INSPECTION IT WAS DISCOVERED THAT THE GEAR RETAINER ASSY BEARING WAS DESTROYED AND REQUIRED REPLACE MENT. THE BEARING RECESS WAS INSPECTED AND CHECKED O.K. THE BEARING WAS REPLACED WITH NEW AND ASSEMBLY WAS REINSTALLED. NO FURTHER ACTION. 1 L 7 2 3O 3 O 1A10 1E4 2003071800092 20030718 00092 SO 2003 7 18 CA030709005 2 20010806 G 8520 BUSHING CESSNA 180 180H 2072618 CE CONT O470 O470R 17026 SO MCAULY 2A34C 2A34C203 GL COUNTERWEIGHT WORN W K NONE O OTHER IN INSP/MAINT 1 CA (CAN) ENGINE REMOVED FROM VIBRATION. ENGINE COUNTERWEIGHT BUSHINGS WORN OUT. 1 H 7 1 3O 3 O 5A6 E273 5 C P3EA 2003102100073 20031021 00073 EA 2003 10 21 CA030922001 1 20011016 G 5610 NP1393225 WINDOW CNDAIR CL600 CL6002B19 1900309 EA GE CF34 CF343A1 30015 NE COCKPIT FAILED W O OTHER O OTHER CR CRUISE 1 CA (CAN) CAPT'S SIDE WINDOW SHATTERED AT 29000 FT. LANDED AT SCHEDULED DESTINATION. WINDOW REPLACED. AIRCRAFT RETURNED T O SERVICE. 2 L 7 2 4F 4 F RT A21EA E15NE 2004012600098 20040126 00098 SW 2004 1 26 CA031117009 1 20010601 G 3243 206031301025 SUPPORT BELL 206 206B 1181511 SW ALLSN 250C 250C20 03013 GL FUSELAGE CRACKED W K NONE O OTHER IN INSP/MAINT 1 CA 11430 (CAN) WHILE PERFORMING AN AW CHECK, CRACKS WERE SUSPECTED IN AFT CROSS TUBE SUPPORT AREA. AFTER PAINT STRIPPING CRACKS CONFIRMED AS FOLLOWS. A SMALL HAIRLINE CRACK WAS FOUND ON THE FWD LEG OF THE LT CROSS TUBE SUPPORT. CRACK IS JUST OUTB OARD OF 90 DEGREE ANGLE. CRACK STARTS AT BOTTOM OF SUPPORT & EXTENDS VERTICAL TO FIRST RIVET & THEN VEERS INBOARD & VERT ICAL. CRACK IS APPROX. 1 INCH IN LENGTH. A SMALL HAIRLINE CRACK ALSO FOUND JUST BELOW FWD LEG OF THE RT CROSS TUBE SUPPO RT. CRACK IS JUST BELOW THIS LEG & RUNS HORIZONTAL & IS ABOUT 1/2 INCH LONG. BELL HELICOPTER IS AWARE OF CRACKS IN THIS AREA & HAS MADE AN UPGRADE TO THESE PARTS. NEW PARTS ARE OF A MUCH THICKER MATERIAL TO PREVENT CRACKING. 1 G 7 1 3U 3 U H2SW E4CE 2005041800078 20050418 00078 NE 2005 4 18 CA041018011 2 20010813 G 7261 01R311159601 TUBE DHAV DHC8 DHC8102 2809003 NM PWA 120 PW120A NE HAMSTD 14SF 14SF7 NE GAS GENERATOR CRACKED W E D ENGINE SHUTDOWN RETURN TO BLOCK K B FLUID LOSS SMOKE/FUMES/ODORS/SPARKS TX TAXI/GRND HDL 1 CA 35615 120097 (CAN) DURING TAXI OUT TO RUNWAY CREW NOTICED AN ODOR WHICH ALSO SET OFF THE LAVATORY SMOKE DETECTOR. AIRCRAFT RETURNED T O GATE. TROUBLESHOOTING BY MAINTENANCE REVEALED SMOKE WAS ENTERING INTO CABIN WHEN BLEED AIR SELECTED ON, NR 1 ENGINE. E NGINE WAS REPLACED. ENGINEERING REPORT BY FROM ENGINE TEARDOWN INDICATED THAT THE OIL PRESSURE SUPPLY TUBE FOR THE NR 5 BEARING AREA WAS CRACKED AT A WELD SEAM IN THE GASGENERATOR CASE. ENGINE WAS REPAIRED. REPORT AVAILABLE IF REQUIRED. 2 H 7 2 4T 4 T RT A13NM E20NE 6 C P7NE 2005050300118 20050503 00118 SW 2005 5 3 CA050228010 1 20010324 G 6320 BP252 GEARBOX KAMOV KA32 KA32A1 SW AMTR VK1A KLIMOVK1A GL MAIN ROTOR MAKING METAL W A UNSCHED LANDING J WARNING INDICATION CR CRUISE 1 CA (CAN) GEARBOX CHIP LIGHT, GEARBOX REPLACED. 1 G 7 2 4U 4 J NC EXPE4J 2005050300116 20050503 00116 SW 2005 5 3 CA050228011 1 20010714 G 6320 BP252 GEARBOX KAMOV KA32 KA32A1 SW MAIN ROTOR MAKING METAL W A UNSCHED LANDING J WARNING INDICATION CR CRUISE 1 CA (CAN) GEARBOX CHIP LIGHT, GEARBOX REPLACED. 1 G 7 2 4U NC 2001083100189 20010831 00189 2001 8 31 CAXR106173 4 20010629 G 3425 5040122902 INDICATOR UROCOP EC120 EC120B 8680987 EU TMECA ARRIUS ARRIU2F NE INSTRUMENT PNL FAILED C CAXR O OTHER O OTHER NR NOT REPORTED 1 WP 15 408DC 259 1151 ATTITUDE INDICATOR - INSTRUMENT FAILED, INOPERATIVE. RMA NR 031964 1 G 7 2 3U 3 U NC R0001RD E34NE 2001030600090 20010306 00090 NM 2001 3 6 COOSDR000033 1 20010215 G 5320 TORQUE BOX BOEING 727 727225 1384077 NM PWA JT8 JT8D15 52051 NE NLG WW FATIGUED B EE4Y K NONE O OTHER IN INSP/MAINT 1 EA 25 8887Z 21856 COOPESA REPORTED THE NOSE WHEEL WELL TORQUE BOX LOWER CHORD LBL 19, WL 148 CHORD WITH CORROSION. REPLACED THE SUBJECT C HORD. PROBABLE CAUSE OF CORROSION WAS FATIGUE. 2 L 7 3 4F 4 F A3WE E2EA 2001050900288 20010509 00288 SO 2001 5 9 CWA1 2 20010118 G 7260 632617 GEAR CONT CESSNA 337 337G 2075730 CE CONT O360 IO360GB 17025 SO ACCESSORY DRIVE WORN D K NONE L NO TEST IN INSP/MAINT 1 GL 13 72361 188 188 33701568 244627R DURING RUN-UP, FOLLOWING ANNUAL INSPECTION, NO VACUUM INDICATION OBSERVED FROM REAR ENGINE. REMOVED PUMP FOR REPLACEMEN T AND OBSERVED DRIVE ON ENGINE DID NOT TURN WITH PROPELLER. REMOVED ACCESSORY DRIVE COVER AND FOUND NO TEETH LEFT ON DR IVING BEVEL GEAR. DRIVEN GEAR WAS NOT WORN. 1 H 7 2 3O 3 O A6CE E1CE 2001030700595 20010307 00595 SW 2001 3 7 E27R1730 1 20010112 G 5310 3107041310704 CHANNEL GULSTM 690TP 690A 0141722 SW WING ROOT CRACKED B E27R K NONE O OTHER IN INSP/MAINT 1 WP 07 921ST 10645 11200 DURING PRESSURAZATION LEAK CHECKS, THE CABIN WAS FOUND TO HVE TWO LARGE LEAKS IN LT AND RT WING ROOT AREA. ON EXAM OF T HE SUSPECT AREAS IT WAS FOUND THAT THE LT AND RT SUPPORT CHANNELS PN310704-1 AND 310704-2 HAD FAILED FROM FS 144 WL10 TO FS 175 WL 14. THE FAILURE IS IN THE FORM OF A CRACK ON THE VERTICAL OB PORTION OF THE CHANNELS FROM RIVET TO RIVET. T HIS FAILURE ALLOWED THE AIRCRAFT SKIN TO PULL AWAY FROM ITS SUPPORTING STRUCTURE ABOVE THE PICTURE WINDOWS IN EXCESS OF .25 IN. 1 H 7 2 3T 2A4 2001032600430 20010326 00430 SW 2001 3 26 E27R730 1 20010122 G 5300 3107041 CHANNEL GULSTM 690TP 690A 0141722 SW GARRTT TPE331 TPE331* 01514 WP LT & RT FAILED B E27R K NONE O OTHER IN INSP/MAINT 1 WP 07 921ST 10545 11200 DURING PRESSURIZATION LEAK CHECKS, THE CABIN WAS FOUND TO HAVE TWO LARGE LEAKS IN THE LEFT AND RIGHT WING ROOT AREA. ON EXAMINATION OF THE SUSPECT AREAS IT WAS FOUND THAT THE LEFT AND RIGHT SUPPORT CHANNELS PN 3107041 & 3107042 HAD FAILED FROM FS 144 WL TO FS 175 WL 14, THE FAILURE ALLOWED THE AIRCRAFT SKIN TO PULL AWAY FROM ITS SUPPORTING STRUCTURE ABOVE T HE PICTURE WINDOWS IN EXCESS OF .25. 1 H 7 2 3T 3 T 2A4 E2WE 2001032600431 20010326 00431 WP 2001 3 26 E27R7302 2 20010122 G 7210 3103435 GEAR GULSTM 690TP 690A 0141722 SW GARRTT TPE331 TPE33110 01514 WP BULL GEAR FAILED B E27R O OTHER O OTHER CR CRUISE 1 WP 07 48AZ 6991 1612 11307 P79291C BULL GEAR FOUND TO HAVE SHED APPROX 6 IN OF TEETH IN 2 SEGMENTS CAUSING EXTENSIVE DAMAGE TO GEAR BOX COMPONENTS AND CASE . WHICH RESULTED IN AN IN FLIGHT SHUTDOWN. 1 H 7 2 3T 4 T 2A4 E4WE 2001050700351 20010507 00351 SO 2001 5 7 ER00101 1 20010502 G 2710 5540802 CONTROL CABLE PIPER PA31T PA31T1 7103126 SO PWA PT6 PT6A11 52043 NE FUSELAGE CROSSED W K NONE O OTHER IN INSP/MAINT 1 SW 99 2480X 2655 200 8104026 DURING SCHEDULED INSPECTION, THE RIGHT HAND AILERON INTERCONNECT CABLE WAS FOUND TO BE CROSSED OVER THE PRIMARY RUDDER C ONTROL CABLE (PT NO 46845-0)AT THE UNDERFLOOR SECTION AFT OF THE CABIN DOOR. THERE IS NO WEAR APPARENT AT THIS TIME, TH E AIRCRAFT LOG BOOKS ARE BEING INSPECTED IN AN ATTEMPT TO ASCERTAIN WHEN THE SYSTEM WAS LAST DISTURBED. 1 L 7 2 3T 3 T A8EA E4EA 2001072600065 20010726 00065 EU 2001 7 26 ERAA072935 1 20010420 G 6310 4638302093 SHAFT BOLKMS 105 BO105S 5626006 EU FREEWHEEL LEAKING H ERAA K NONE O OTHER IN INSP/MAINT 1 FS 01 426EH 552 SHAFT HAS 36.9 HRS TSO AND IS CAUSING INPUT SEAL TO LEAK EVEN WITH THE NEW IMPROVED SEAL INSTALLED. 1 G 7 2 3U H3EU 2001072600066 20010726 00066 NE 2001 7 26 ERAA072936 1 20010424 G 8000 60692032 BLOWER SKRSKY S76 S76A 8143006 NE ENGINE INOPERATIVE H ERAA O OTHER O OTHER NR NOT REPORTED 1 FS 01 577EH 760222 PART IS INOPERABLE. MOTOR WON'T START WITH BLOWER ON. HAVE TO TAP ON PLUG CONNECTOR BOX TO START. INSTALLING NEW BL OWER SOLVED PROBLEM. TSO IS ONLY 47.1 HRS. RETURNING TO CORPORATE ROTABLE ON REPAIR ORDER # RW-883735 REQUESTING WARR ANTY REPAIR. 1 G 7 2 3U H1NE 2001072600067 20010726 00067 NE 2001 7 26 ERAA072937 1 20010501 G 7120 0292108940 SUPPORT SKRSKY S76 S76A 8143006 NE TMECA ARRIEL ARRIEL1 60030 NE ENGINE BROKEN H ERAA K NONE O OTHER IN INSP/MAINT 1 FS 01 578EH 2147 760099 3016 FRONT SUPPORT IS BROKEN IN HALF. PART HAS 2147.0 HRS ON IT. THIS INFORMATION FOR FAA SDR REPLACED WITH NEW SUPPORT. 1 G 7 2 3U 3 U H1NE E19EU 2001072600068 20010726 00068 EU 2001 7 26 ERAA072938 1 20010501 G 6320 4638001007 TRANSMISSION BOLKMS 105 BO105A EU M/R GEARBOX MAKING METAL A ERAA K NONE O OTHER IN INSP/MAINT 1 AL 03 290EH 12460 S850 TRANSMISSION MAKING METAL. REMOVED SLIP RING CARRIER, FOUND LT BEVEL GEAR BREAKING DOWN. FOUND OIL PUMP DAMAGED FROM M ETAL CONTAMINATION. PUMP SENT OUT FOR REPAIR. THIS INFORMATION FOR FAA SDR. ACTION TAKEN: REPAIRED TRANSMISSION I/A/W REM 103, INST'D NEW L/H INPUT PINION & BEVEL GEAR, SERVICEABLE OIL PUMP. COMPLIED WITH FREEWHEEL INSPECTION I/A/W REM 103. NEXT INSPECTION DUE IN 600 HRS. ASSEMBLED TRANSMISSION AND ADJUSTED PATTERN AND BACKLASH. 1 G 7 2 3U H3EU 2001072600069 20010726 00069 EU 2001 7 26 ERAA073270 1 20010516 G 2435 230321825 STATOR BOLKMS 105 BO105S 5626006 EU GENERATOR CHAFED H ERAA K NONE O OTHER IN INSP/MAINT 1 FS 01 153EH S572 ARMATURE RUBBING INSIDE STATOR. ISSUED TO AC 153EH BUT COULD NOT BE INSTALLED DUE TO PROBLEM WHEN TRYING TO INSTALL IN GENERATOR. 1 G 7 2 3U H3EU 2001072600076 20010726 00076 SW 2001 7 26 ERAA073271 1 20010521 G 2822 SCREW BELL 412 412 1182202 SW PWA PT6T PT6T3B 52045 NE VALVE STRIPPED H K NONE O OTHER IN INSP/MAINT 1 FS 01 419EH 1881 33043 SCREW IS STRIPPED. SCREWS STRIPPED OR BACKING OUT OF VALVE BODY. NOTE: SCREWS WERE LOCK WIRED. T 1 G 7 2 4U 4 U H4SW E22EA 2001072600077 20010726 00077 EU 2001 7 26 ERAA073274 1 20010531 G 3246 10550103 SKID BOLKMS 105 BO105S 5626006 EU MLG MISOVERHAULED H ERAA K NONE W INADEQUATE Q C IN INSP/MAINT 1 FS 01 125EH S562 SKID TUBE ISSUED TO AC 125EH BUT COULD NOT BE INSTALLED. SKID TUBE WAS OVERHAULED AND RETURNED WITH NUT PLATES NOT LI NING UP WITH SKID SHOES. 1 G 7 2 3U H3EU 2001072600079 20010726 00079 EU 2001 7 26 ERAA073275 1 20010601 G 3246 10550103 SKID BOLKMS 105 BO105A EU MLG MISOVERHAULED H ERAA K NONE W INADEQUATE Q C IN INSP/MAINT 1 FS 01 148EH 703 SKID TUBE ISSUED TO AC 148EH BUT COULD NOT BE INSTALLED. SKID TUBE WAS OVERHAULED AND RETURNED WITH NUT PLATES NOT LI NING UP WITH SKID SHOES. 1 G 7 2 3U H3EU 2001080200300 20010802 00300 SW 2001 8 2 ERAA074613 1 20010612 G 2433 2010001 CONVERTER BELL 412 412 1182202 SW ELECTRICAL MALFUNCTIONED H ERAA K NONE O OTHER IN INSP/MAINT 1 FS 01 412EH 16 33001 NEW CONVERTER REC'D FROM ANCHORAGE ORDERED FROM BENZ AIRBORNE. UNIT WILL NOT ADJUST LOW ENOUGH. ONLY HAS 15.5 HRS SINC E NEW. RETURNING TO BENZ ON ERA REPAIR ORDER RW-884522 REQUESTING WARRANTY REPAIR. 1 G 7 2 4U H4SW 2001080200301 20010802 00301 2001 8 2 ERAA074614 4 20010612 G 3444 066303102 ALTIMETER SKRSKY S76 S76A 8143006 NE RADAR FAILED H ERAA K NONE O OTHER IN INSP/MAINT 1 FS 01 576EH 760212 RADAR ALTIMETER WAS OVERHAULED BY FREESCAN 2 / 2001 AND RET'D TO ERA . INSTALLED ON AIRCRAFT AND HAD TO REMOVE DUE TO BEING TOTALLY INOPERABLE. RETURNING TO FREESCAN ON ERA REPAIR ORDER RW-884523 REQUESTING WARRANTY REPAIR. 1 G 7 2 3U H1NE 2001080200306 20010802 00306 SW 2001 8 2 ERAA074615 1 20010612 G 7714 412075010109 INDICATOR BELL 412 412 1182202 SW TRIPLE TACH READS HIGH H ERAA K NONE O OTHER IN INSP/MAINT 1 FS 01 418EH TRIPLE TACH REM'D FROM AIRCRAFT AFTER 111.3 HRS AFTER O/H WITH ROTOR NEEDLE READING 5 PERCENT HIGH. 1 G 7 2 4U H4SW 2001080200309 20010802 00309 EU 2001 8 2 ERAA074616 1 20010613 G 6320 4638001007 TRANSMISSION BOLKMS 105 BO105A EU MAIN ROTOR CONTAMINATED H ERAA K NONE O OTHER IN INSP/MAINT 1 FS 01 290EH 12460 S850 TRANSMISSION IS CONTAMINATED BY TRASH FROM OIL COOLER. REMOVED ALL OIL JETS TO FLUSH OUT ALL OIL PASSAGES. REMOVED TO P CASE & CENTER HOUSING, CLEANED AND FLUSHED ALL OIL JETS AND OIL PASSAGES, REPAIRED ACCEDSSORY DRIVE, REASSEMBLED TRANS MISSION WITH NEW O-RINGS IAW REM 103. 1 G 7 2 3U H3EU 2001080200312 20010802 00312 EU 2001 8 2 ERAA074617 1 20010613 G 6420 10531714 HEAD BOLKMS 105 BO105S 5626006 EU TAIL ROTOR BINDING H ERAA K NONE O OTHER IN INSP/MAINT 1 FS 01 131EH 11983 559 T/R ASSY IS BINDING. REPAIRED, PARTIAL DISASSEMBLY, VISUALLY INSPECTED. FOUND NO CAUSE FOR BINDING, INST'D NEW GRIP BU SHINGS AND SEALS. CHECKED FRICTION FORCES 10N AND 17N (MAX 25N) REASSEMBLED T/R ASSY AND MARVEL BALANCED ALL WORK IAW BO105 MM 32, MARVEL MANUAL REM 301. 1 G 7 2 3U H3EU 2001080200315 20010802 00315 EU 2001 8 2 ERAA074618 1 20010613 G 6420 10531714 HEAD BOLKMS 105 BO105S 5626006 EU TAIL ROTOR BINDING H ERAA K NONE O OTHER IN INSP/MAINT 1 FS 01 131EH 13133 559 THIS INFORMATION FOR FAA SDR. CC: AMERICAN EUROCOPTER CORP. T/R ASSY IS BINDING. ACTION TAKEN: FOUND INNER SLEEVE AND BLADE MOUNTING, FORK BEARING BUSHINGS COATED WITH TEFLON FILM REPAIRED FOR BINDING. DISASSEMBLED, CLEANED, VISUALLY I NSPECTED, REASSEMBLED WITH NEW SEALS AND BALANCED. ALL WORK DONE IAW MBB-BO105 REM 301, MM CHAP 34 & 107 & MARVEL BOOK. . 1 G 7 2 3U H3EU 2001080200319 20010802 00319 GL 2001 8 2 ERAA074619 2 20010613 G 7313 6890040 NOZZLE BOLKMS 105 BO105S 5626006 EU ALLSN 250C 250C20B 03013 GL FUEL INJECTION MISREPAIRED H ERAA K NONE O OTHER IN INSP/MAINT 1 FS 01 296EH S849 1ST STAGE NOZZLE SHIELD RET'D FROM OVERHAUL AT DALLAS AIRMOTVE, ISSUED TO AIRCRAFT BUT COULD NOT BE INSTALLED DUE TO NOT BEING WELDED ALL THE WAY AROUND. 1 G 7 2 3U 3 U H3EU E4CE 2001080200326 20010802 00326 2001 8 2 ERAA074620 4 20010614 G 2312 4120073010 CONTROL HEAD BELL 412 412 1182202 SW COCKPIT MISREPAIRED H ERAA K NONE W INADEQUATE Q C IN INSP/MAINT 1 FS 01 167EH 33089 CONTROL HEAD MODIFIED INCORRECTLY. WAS MODIFIED TO S INSTEAD OF A. 1 G 7 2 4U H4SW 2001080300013 20010803 00013 EU 2001 8 3 ERAA074621 1 20010615 G 6420 10531714 HEAD BOLKMS 105 BO105S 5626006 EU TAIL ROTOR BINDING H ERAA K NONE O OTHER IN INSP/MAINT 1 FS 01 131EH 3137 559 T/R ASSY IS BINDING. FOUND NO ABNORMAL WEAR OR DEFECTS. DISASSEMBLED, CLEANED AND INSPECTED BUSHINGS ON INNER SLEEVE. REMOVED AND REPLACED BUSHINGS AND SEAKS IN BLADE MOUNTING FORKS. REASSEMBLED AND BALANCED. ALL WORK DONE IAW MBB BO10 5 REM 301, MBB-BO105 MM CHAPTERS 34& 107 AND MARVEL BOOK. 1 G 7 2 3U H3EU 2001080300072 20010803 00072 EU 2001 8 3 ERAA074622 1 20010615 G 6420 10531714 HEAD BOLKMS 105 BO105S 5626006 EU TAIL ROTOR STIFF H ERAA K NONE O OTHER IN INSP/MAINT 1 FS 01 128EH 12475 572 THIS INFORMATION FOR FAA SDR. CC: AMERICAN EUROCOPTER CORP. T/R ASSY HAS STIFF PEDALS. FOUND NO ABNORMAL WEAR OR DEFE CTS ACTION TAKEN: DISASSEMBLED, CLEANED AND INSPECTED BUSHINGS ON INNER SLEEVE, REPLACED SEALS AND BUSHIGS IN BLADE MOU NTING FORKS REASSEMBLED AND BALANCED. ALL WORK DONE IAW MBB BO105 REM301, MBB BO105MM CHAPTERS 34 & 107 AND MARVEL BOO K. 1 G 7 2 3U H3EU 2001080300073 20010803 00073 EU 2001 8 3 ERAA074623 1 20010615 G 6420 10531714 HEAD BOLKMS 105 BO105S 5626006 EU TAIL ROTOR STIFF H ERAA K NONE O OTHER IN INSP/MAINT 1 FS 01 13133 THIS INFORMATION FOR FAA SDR. CC: AMERICAN EUROCOPTER CORP. STIFF T/R PEDALS AT 100% FOUND NO CAUSE FOR BINDING. ACTI ON TAKEN: DISASSEMBLED, CLEANED & VISUALLY INSPECTED. REASSEMBLED USING NEW BUSHINGS & SEALS. C/W FRICTION CHECK (TE STED 3N & 44) & MARVEL BALANCED. ALL WORK IAW BO105 REM 301 & MM CH 33 & 34 & MARVEL BOOK. 1 G 7 2 3U H3EU 2001080300075 20010803 00075 EU 2001 8 3 ERAA074624 1 20010618 G 6420 10531714 HEAD BOLKMS 105 BO105S 5626006 EU TAIL ROTOR STIFF H ERAA K NONE O OTHER IN INSP/MAINT 1 FS 01 127EH 12841 571 T/R ASSY HAS HEAVY LEFT PEDAL. ACTION TAKEN: REPAIRED, DISASSEMBLED, CLEANED, VISUALLY INSPECTED. INSTALLED NEW GRIP BUSHINGS AND SEALS. INST'D SERVICEABLE CONTROL LEVERS. REASSEMBLED AND BALANCED ALL WORK IAW BO105 REM 301 MM 33,34. 1 G 7 2 3U H3EU 2001080300077 20010803 00077 SW 2001 8 3 ERAA074626 1 20010619 G 6520 212040004009 GEARBOX BELL 412 412 1182202 SW TAIL ROTOR MAKING METAL H ERAA K NONE O OTHER IN INSP/MAINT 1 FS 01 417EH 13445 33031 GEARBOX IS MAKING METAL. BEARINGS BREAKING DOWN. ACTION TAKEN: OVERHAULED, DISASSEMBLED, CLEANED, VISUALLY INSPECTED AN D NDT. C/W TB 412-99-157. INSTALLED NEW BEARINGS OP SHAFT, EXCLUDER ASSY AND ALL SEALING ELEMENTS. REASSEMBLED 90 DEG REE GEARBOX AND CHECKED BACKLASH. .009, .009, .009 REPACKED COUPLING WITH GREASE DATED GREASE DATED NOV. 12, 1999. 1 G 7 2 4U H4SW 2001080300078 20010803 00078 GL 2001 8 3 ERAA074627 2 20010619 G 7230 250C20B COMPRESSOR BOLKMS 105 BO105S 5626006 EU ALLSN 250B 250B* GL ENGINE SEIZED H ERAA K NONE O OTHER IN INSP/MAINT 1 FS 01 296EH 12458 S849 COMPRESSOR LOCKED UP. PLASTIC ON CASE 1/2 MISSING. ACTION TAKEN: INSTALLED SERVICEABLE CASE. 1 G 7 2 3U 3 T H3EU E10CE 2001080300079 20010803 00079 EA 2001 8 3 ERAA074628 2 20010621 G 7230 COMPRESSOR BELL 412 412 1182202 SW PWA PT6T PT6T3 52045 EA ENGINE FAILED H ERAA K NONE O OTHER IN INSP/MAINT 1 FS 01 421EH 13292 33067 AFTER 451.2 HRS T.S.O. C-BOX REMOVED FROM AIRCRAFT DUE TO HIGH OIL PRESSURE. 1 G 7 2 4U 4 U H4SW E22EA 2001092100155 20010921 00155 NE 2001 9 21 ERAA074826 1 20010718 G 6730 BH185R154 SERVO SKRSKY S61 S61N 8142104 NE FLUCTUATES H ERAA K NONE O OTHER IN INSP/MAINT 1 FS 01 563EH 61808 INSTALLED ON A/C AND HAD TO REMOVE DUE TO GAUGE FLUCTUATING. RETURNING ON ERA REPAIR ORDER # RW -885179 REQUESTING WARR ANTY REPAIR. 2 G 7 2 4U 1H15 2001092100157 20010921 00157 EU 2001 9 21 ERAA074827 1 20010718 G 6310 4638302093 SHAFT BOLKMS 105 BO105A EU FREEWHEEL UNIT LEAKING H ERAA K NONE O OTHER IN INSP/MAINT 1 FS 01 291EH S842 FREEWHEEL SHAFT IS CAUSING INPUT SEAL TO LEAK. NEEDS SPECIAL COATING REPLACED. WAS PURCHASED NEW 2/14/00. RETURNING ON ERA REPAIR ORDER 885185 REQUESTING WARRANTY EXCHANGE. 1 G 7 2 3U H3EU 2001092100161 20010921 00161 EU 2001 9 21 ERAA074828 1 20010720 G 6520 4619002003 GEARBOX BOLKMS 105 BO105S 5626006 EU TAIL ROTOR DAMAGED H ERAA K NONE O OTHER IN INSP/MAINT 1 FS 01 134EH 2837 635 BEARINGS SCORED AND INPUT BUSHING FRETTING. DISASSEMBLED, VISUALLY INSPECTED. REPLACED ALL FIVE BEARINGS, INPUT BUSHING , ALL O RINGS, ALL SEALING RINGS, BOTH SEALS, ONE SCREW AND THE LOCKING PLATE. REASSEMBLED, SET GEAR DISTANCE, BACKLASH & PATTERN PRO-SEALED. REPAIRED IAW BO-105 REM-304. COMPLIED WITH ASB BO-105-30-111. COPY SENT TO AMERICAN EUROCOPTER CORP. 1 G 7 2 3U H3EU 2001092100162 20010921 00162 EU 2001 9 21 ERAA074829 1 20010723 G 6410 10531980 BLADE BOLKMS 105 BO105S 5626006 EU TAIL ROTOR FLAKING H ERAA K NONE O OTHER IN INSP/MAINT 1 FS 01 152EH 2306 S701 SEVERE PAINT AND RUBBER FLAKEING. SENT TO AEC FOR REPAIR AND INSTALLED ON AIRCRAFT 1-22-01. RETURNING ON ERA REPAIR O RDER# RW-885245 REQUESTING WARRANTY REPAIR. 1 G 7 2 3U H3EU 2001092100163 20010921 00163 EU 2001 9 21 ERAA074830 1 20010730 G 3212 307561 SQUIB VALVE BOLKMS 105 BO105S 5626006 EU MLG CORRODED H ERAA K NONE O OTHER IN INSP/MAINT 1 FS 01 133EH 881 598 SQUIB VALVE CORRODED. VALVE BODY IS BULGING (OR PERTRUDING) AS INDICATED ON VALVE. CORRECTIVE ACTION: SQUIB VALVE RE MOVED FROM AIRCRAFT AND TAGGED AS UNSERVICEABLE. 1 G 7 2 3U H3EU 2001092100165 20010921 00165 GL 2001 9 21 ERAA074831 2 20010801 G 7320 252464430N FUEL CONTROL BOLKMS 105 BO105S 5626006 EU ALLSN 250C 250C20B 03013 GL ENGINE MISOVERHAULED H ERAA K NONE O OTHER IN INSP/MAINT 1 FS 01 293EH 6921 S844 FUEL CONTROL OVERHAULED BY HONEYWELL 2/23/01. UNIT IS SLOW STARTING AND HANGS AT 55 PERCENT. RETURNING ON ERA REPAIR OR DER RW-885436 REQUESTING WARRANTY REPAIR. 1 G 7 2 3U 3 U H3EU E4CE 2001092100167 20010921 00167 SW 2001 9 21 ERAA074832 1 20010802 G 5260 LA11A2129 ACTUATOR BELL 412 412 1182202 SW STEP FAILED H ERAA K NONE O OTHER IN INSP/MAINT 1 FS 01 SPARE STEP ACTUATOR WAS REPAIRED BY ITT AND RET'D TO ERA 5/30/2001. COULD NOT BE USED ON AIRCRAFT BECAUSE UNIT WOULD NOT RETR ACT. RETURNING ON ERA REPAIR ORDER RW-885450 REQUESTING WARRANTY REPAIR. 1 G 7 2 4U H4SW 2001092100168 20010921 00168 SW 2001 9 21 ERAA075871 1 20010802 G 5260 LA11A2129 ACTUATOR BELL 412 412 1182202 SW STEP FAILED A ERAA K NONE O OTHER IN INSP/MAINT 1 AL 03 SPARE STEP ACTUATOR WAS REPAIRED BY ITT AND RET'D TO ERA 5/30/2001. COULD NOT BE USED ON AIRCRAFT BECAUSE UNIT WOULD NOT RETR ACT. RETURNING ON ERA REPAIR ORDER# RW-885450 REQUESTING WARRANTY REPAIR. 1 G 7 2 4U H4SW 2001092400093 20010924 00093 EU 2001 9 24 ERAA075875 1 20010809 G 6310 4638302093 SHAFT BOLKMS 105 BO105S 5626006 EU FREEWHEEL UNIT LEAKING H ERAA K NONE K FLUID LOSS IN INSP/MAINT 1 FS 01 294EH 615 S675 FREEWHEEL SHAFT LEAKS. WAS SENT TO ZF FOR OVERHAUL 1/26/01 AND WAS INSTALLED ON AIRCRAFT 8/04/01. AFTER 18.2 HRS, UN IT CAUSING INPUT SEAL TO LEAK. SPECIAL COATING WORN. RETURNING TO ZF ON ERA REPAIR ORDER RW-885574 REQUESTING WARRANTY REPAIR. 1 G 7 2 3U H3EU 2001092400095 20010924 00095 EU 2001 9 24 ERAA075876 1 20010822 G 6310 4638302093 SHAFT BOLKMS 105 BO105S 5626006 EU FREEWHEEL UNIT LEAKING H ERAA K NONE K FLUID LOSS IN INSP/MAINT 1 FS 01 294EH 457 S846 FREEWHEEL SHAFT PREVIOUSLY SENT TO ZF 4/2001 FOR REPAIR FOR SAME PROBLEM, CAUSING LEAKING OF INPUT SEALS. REF MMIR ERA A 0001202. RETURNING ON ERA REPAIR ORDER RW-885812 REQUESTING WARRANTY REPAIR. ALSO RETURNING (2) INPUT SEALS THAT AR E LEAKING WITH THE SAME AMOUNT OF HOURS AS FREEWHEEL SHAFT. ATTN: HERBERT BODENMILLER 1 G 7 2 3U H3EU 2001122600001 20011226 00001 SW 2001 12 26 ERAA076643 1 20010921 G 7500 3032247 AIR FILTER BELL 412 412 1182202 SW ENGINE DEBONDED H ERAA K NONE O OTHER IN INSP/MAINT 1 FS 01 412EH 106 33001 PART IS DEBONDED. THIS PARTICULAR AIR FILTER HAD 106.0 HRS BUT HAVE TRIED SEVERAL OTHERS AND IMMEDIATELY AIR FILTERS BE GAN TO BREAK DOWN AND DEBOND. 1 G 7 2 4U H4SW 2001122600002 20011226 00002 EU 2001 12 26 ERAA076644 1 20010921 G 6310 4638302093 SHAFT BOLKMS 105 BO105S 5626006 EU FREEWHEEL UNIT LEAKING H ERAA K NONE O OTHER IN INSP/MAINT 1 FS 01 426EH 245 552 FREEWHEEL SHAFT CAUSES INPUT SEAL TO LEAK. SPECIAL COATING NEEDS TO BE REPLACED. ONLY HAS 245.1 HRS SINCE LAST RETURNED TO ZF. LAST RETURNED ON WARRANTY CLAIM. 1 G 7 2 3U H3EU 2001122600003 20011226 00003 SW 2001 12 26 ERAA076647 1 20010927 G 7500 3032247 AIR FILTER BELL 412 412 1182202 SW PWA PT6T PT6T3B 52045 NE ENGINE DEBONDED H ERAA K NONE O OTHER IN INSP/MAINT 1 FS 01 422EH 33068 CPPS62136 PART IS DEBONDED. FILTER PURCHASED FROM PUR FLOW MFG. IMMEDIATELY COME APART AFTER INSTALLATION. 1 G 7 2 4U 4 U H4SW E22EA 2001122600004 20011226 00004 SW 2001 12 26 ERAA076648 1 20010927 G 7500 3032247 AIR FILTER BELL 412 412 1182202 SW PWA PT6T PT6T3B 52045 NE ENGINE DEBONDED H ERAA K NONE O OTHER IN INSP/MAINT 1 FS 01 164EH 33004 PART IS DEBONDED. THIS INFORMATION FOR FAA SDR ONLY. PURCHASED FROM PUR FLOW MFG. 1 G 7 2 4U 4 U H4SW E22EA 2001122600005 20011226 00005 SW 2001 12 26 ERAA076649 1 20010928 G 7500 3032247 AIR FILTER BELL 412 412 1182202 SW NR 1 & 2 ENGINES DEBONDED H ERAA K NONE O OTHER IN INSP/MAINT 1 FS 01 412EH 33001 PART IS DEBONDED. INSTALLED ON NR 1 AND NR 2 ENGINE BUT BOTH FILTERS DEBONDED AND FELL APART IMMEDIATIATELY. 1 G 7 2 4U H4SW 2001122600006 20011226 00006 SW 2001 12 26 ERAA076650 1 20010928 G 7500 3032247 AIR FILTER BELL 412 412 1182202 SW NR 2 ENGINE DEBONDED H ERAA K NONE O OTHER IN INSP/MAINT 1 FS 01 412EH 33001 PART IS DEBONDED. INSTALLED ON NR 2 ENGINE BUT FILTER FELL APART. THIS INFO FOR FAA SDR. FILTERS PURCHASED FROM PU R-FLOW MFG. 1 G 7 2 4U H4SW 2001122600007 20011226 00007 NE 2001 12 26 ERAA076652 1 20011003 G 3040 40008330202 INDICATOR SKRSKY S61 S61N 8142104 NE RADAR UNIT CONTAMINATED H ERAA K NONE O OTHER IN INSP/MAINT 1 FS 01 561EH 135 61471 RADAR INDICATOR HAS WATER DAMAGE. UNIT HAD BLANK SCREEN AND WOULD NOT COME ON.MAJOR WATER DAMAGE WS FOUND IN UNIT. ACT ION TAKEN: REMOVED CORROSION, REPAIRED TRACES, ALIGNED AND TESTED. THIS INFORMATION FOR FAA SDR. 2 G 7 2 4U 1H15 2001122600008 20011226 00008 2001 12 26 ERAA076653 4 20011003 G 3440 40008330208 INDICATOR SKRSKY S61 S61N 8142104 NE RADAR UNIT CONTAMINATED H ERAA K NONE O OTHER IN INSP/MAINT 1 FS 01 561EH 1073 61471 RADAR INDICATOR HAS WATER DAMAGE. UNIT WOULD NOT COME ON. FOUND WATER DAMAGE. ACTION TAKEN : REMOVED CORROSION, REPL ACED BLOWN RESISTOR AND TESTED UNIT. 2 G 7 2 4U 1H15 2001122600009 20011226 00009 2001 12 26 ERAA076654 4 20011003 G 3440 40008330208 INDICATOR SKRSKY S61 S61N 8142104 NE RADAR CONTAMINATED H ERAA K NONE O OTHER IN INSP/MAINT 1 FS 01 561EH 831 61471 RADAR INDICATOR HAS WATER DAMAGE. INOPERABLE. UNIT HAS WATER DAMAGE ACTION TAKEN: REPLACED BLOWN RESISTOR, REMOVED CO RROSION AND TESTED. 2 G 7 2 4U 1H15 2001122600024 20011226 00024 GL 2001 12 26 ERAA076655 2 20011003 G 7320 252466715H GOVERNOR BOLKMS 105 BO105S 5626006 EU ALLSN 250C 250C20B 03013 GL ENGINE MALFUNCTIONED H ERAA O OTHER O OTHER NR NOT REPORTED 1 FS 01 292EH 13707 562 GOVERNOR OCCASIONALLY DROOPS IN FLIGHT. TEST RESULTS CONFIRM SNAG OF DROOP. UNIT WAS DOOPING BY 250 RPM @ T.P. 3.01 EC CENTRIC SHAFT FOUND CORRODED AND WORN BEYOND LIMITS ON LOBES. BEARINGS PN 2520503 AND 2523237 FOUND TO BE ROUGH AND DRY . ACTION TAKEN: ABOVE PARTS REPLACED WITH NEW AND UNIT WAS REPAIRED AND TESTED SERVICEABLE IAW HONEYWELL OH FORM 15-109 5A. THIS INFORMATION FOR FAA SDR. 1 G 7 2 3U 3 U H3EU E4CE 2001122600025 20011226 00025 GL 2001 12 26 ERAA076656 2 20011003 G 7320 252466715H GOVERNOR BOLKMS 105 BO105S 5626006 EU ALLSN 250C 250C20B 03013 GL ENGINE MALFUNCTIONED H ERAA O OTHER O OTHER NR NOT REPORTED 1 FS 01 153EH 11164 S572 NR 1 GOVERNOR IS SLOW,NR HIGH WITH REDUCED POWER. TEST RESULTS INDICATE GOVERNOR WAS DROOPING OFF SLIGHTLY (100 RPM) SE VERAL INTERNAL BEARINGS PN 2520503 & 2523237 FOUND DRY AND ROUGH. THROTTLE BUSHING WORN ALLOWING SHAFT TO HAVE EXCESSIV E PLAY. ECCENTRIC SHAFT CORRODED AND WORN BEYOND LIMITS. ACTION TAKEN: REPAIRED AND TESTED SERVICEABLE IAW HONEYWELL O HM 15--1095A. ABOVE PARTS REPLACED. CEB A-1353 R1 FOUND N/AB, UNIT S/N, CEB A-1361R1 FOUND C/W. 1 G 7 2 3U 3 U H3EU E4CE 2001122600026 20011226 00026 GL 2001 12 26 ERAA076657 2 20011003 G 7320 2524667 GOVERNOR BOLKMS 105 BO105S 5626006 EU ALLSN 250C 250C20B 03013 GL WORN H ERAA O OTHER O OTHER NR NOT REPORTED 1 FS 01 149EH 8461 S705 SPLINES ON DRIVESHAFT OF GOVERNOR IS WORN. MAX GOVERING DROOPS OFF 300 RPM TO EARLY. THROTTLE BUSHING VERY SLOPPY WORN SPLINES ON DRIVESHAFT AS WELL AS THE MATING FACE OF THE SPOOL BEARING EXHIBITED HEAVY WEAR FROM THE GOVERNOR WEIGHT FEE T. ECCENTRIC SHAFT AND CAM LEVER WERE FOUND SEIZED TOGETHER N THE DRIVE BODY BY CORROSION. AFTER CLEANING THEY WERE BO TH PITTED AND WORN BEYOND LIMITS ACTION TAKEN: OVERHAULED. NOTE: THE CONDITION OF THIS GOVERNOR SEEMS TO INDICATE A V IBRATION PROBLEM ON THE A/C, POTENTIALLY STARTER GENERATOR ON GEARBOX. CEB'S 1347 R1, A-1361R1 AND GT320. C/W CEB A-1353 R1 FOUND N/A BY UNIT S/N. THIS INFORMATION FOR FAA SDR 1 G 7 2 3U 3 U H3EU E4CE 2001122600027 20011226 00027 EU 2001 12 26 ERAA076658 1 20011004 G 6210 1051410110 BOLT BOLKMS 105 BO105S 5626006 EU MAIN ROTOR WORN H ERAA K NONE O OTHER IN INSP/MAINT 1 FS 01 149EH S705 PRIMARY BLADE BOLTS HAS WORN PLATING. ACTION TAKEN : CLEANED & C/W VISUAL & NDT INSPECTION. SCRAPPED 3 BOLTS DUE TO M ECHANICAL DAMAGE. THIS INFORMATION FOR FAA SDR. 1 G 7 2 3U H3EU 2001122600028 20011226 00028 EU 2001 12 26 ERAA076663 1 20011005 G 6210 10515170 BLADE BOLKMS 105 BO105A EU MAIN ROTOR DEBONDED H ERAA K NONE O OTHER IN INSP/MAINT 1 FS 01 135EH 11317 S675 M/R BLADE IS DEBONDED. LEADING EDGE DEBONDING, POTTING NEEDS CHANGING. ACTION TAKEN: ALL ABRASION STRIPS VOID, HEAVY ERROSION ON ABRASION STRIP, P.U. FILM DETERIORATION, PAINT PEELING, HARDWARE CORRODED SWEEP OUT -13.21MM, NOSE AND NECK SHELLS CRACKED SKIN CRACKED @ NECK SHELL, SKIN DEBONDED @ NECK AREA. REPAIRED. THIS INFORMATION FOR FAA SDR. 1 G 7 2 3U H3EU 2001122600029 20011226 00029 EU 2001 12 26 ERAA076664 1 20011009 G 6210 10515170 BLADE BOLKMS 105 BO105A EU MAIN ROTOR DEBONDED H ERAA K NONE O OTHER IN INSP/MAINT 1 FS 01 135EH 11319 S675 BLADE IS DEBONDING ON LEADING EDGE. POTTING NEEDS CHANGING NOSE AND NECK SHELLS CRACKED @ NECK DOWN AREA, SKIN CRACK AN D VOIDED @ NECK AREA, TEFLON MISSING FROM MAIN BUSHING, DRAG BUSHING HAS FRAYED AND MISSING TEFLON, DAMPNER WRAP VOID LO WER SURFACE, ALL ABRASION STRIPS VOID @ SCARF JOINTS, HEAVY ERROSION ON OUTBOARD ABRASION STRIP, MINOR CORROSION ON THE TABS. DU DISKS MISSING, MINOR CORROSION ON PENDULUM ARM, SWEEP OUT 10.34MM ACTION TAKEN: REPLACED NR 1 OUTBOARD ABRASI ON STRIP, REPLACED PT REINSTALLED NR 2,3,4 ABRASION STRIPS, REPLACED DU DISKS REPLACE MAIN BUSHING, REPLACED DRAG BUSHIN G, REM'D AND TREAT CORROSION OR TRIM TABS, PERFORM SMALL SKIN REPAIR @ NECK, REPLACED NOSE AND NECK SHELLS, REPLACED DAM 1 G 7 2 3U H3EU 2001122600031 20011226 00031 EU 2001 12 26 ERAA076665 1 20011009 G 6210 10515170 BLADE BOLKMS 105 BO105A EU MAIN ROTOR DEBONDED H ERAA K NONE O OTHER IN INSP/MAINT 1 FS 01 135EH 11428 S675 BLADE IS DEBONDING ON LEADING EDGE. POTTING NEEDS CHANGING. ALL ABRASI9ON STRIPS VOID SCARF JOINT, NR 1 ABRASION STRI P ERROSION NOSE AND NECK SHELL CRACKED AT FITTING, SKIN AT ROOT AREA CRACKED ROVING FILLER SEPERATED, UPPER SURFACE AT T RAILING EDGE, DAMPNER VOID, MINOR ERROSION ON TRIM TABS, TEFLON LINING ON BUSHING FRAYED AND MISSING SWEEP OUT OF TOLERA NCE 9.6MM. ACTION TAKEN: REPAIRED AS PER FORM 8130-3 BLOCK, 13 . THIS INFORMATION FOR FAA SDR. 1 G 7 2 3U H3EU 2001122700004 20011227 00004 2001 12 27 ERAA076667 4 20011009 G 3450 D120P2T INDICATOR BELL 412 412 1182202 SW COCKPIT CORRODED H ERAA K NONE O OTHER IN INSP/MAINT 1 FS 01 412EH 483 33001 PART IS CORRODED. CONNECTOR CORRODED, PIN MISSING, DIRTY INSIDE AND ALSO OUT OF CALIBRATION. ACTION TAKEN: OVERHAULED, REPAIRED LEAKS, TREATED METAL, CALIBRATED AND FUNCTIONALLY TESTED OK TO 20,000 FEET. COMPLIED WITH AIRWORTHINESS DIREC TIVES AS PER MFG PUB 7421 REV A JAN. 1993. 1 G 7 2 4U H4SW 2001122700005 20011227 00005 2001 12 27 ERAA076668 4 20011009 G 3450 D120P2T INDICATOR SKRSKY S61 S61N 8142104 NE COCKPIT MISMANUFACTURED H ERAA K NONE O OTHER IN INSP/MAINT 1 FS 01 561EH 360 61471 PART MISSING. FILTER MISSING ON PORT; TAKEN FROM STOCK. CONNECTOR PLATE BROKEN, CORROSION ON INSIDE OF BASE AND CASE , UNIT LEAKS, AND NEEDS ADJUSTMENT. ACTION TAKEN: REPAIRED, CLEANED CORROSION, REPLACED CONNECTOR PLATE, FIXED LEAKS, A DJUSTED AND FUNCTRIONALLY TESTED OK TO 20,000 FEET. C/W AIRWORTHINESS DIRECTIVES OR SB'S AS PER TSM 7421 REV A JAN 1993 . 2 G 7 2 4U 1H15 2001122700006 20011227 00006 2001 12 27 ERAA076669 4 20011009 G 3450 D120P2T INDICATOR BOLKMS 105 BO105A EU COCKPIT CORRODED H ERAA K NONE O OTHER IN INSP/MAINT 1 FS 01 291EH S842 PART IS CORRODED. CONNECTOR INSERTS PULLED OUT . CONNECTOR PLATE BROKEN, CORROSION ON CASE INSIDE AND ON BASE, UNIT LE AKS AND OUT OF ADJUSTMENT. ACTION TAKEN: REPAIRED, CLEANED CORROSION, REPLACED CONNECTOR PLATE, FIXED LEAKS, AND FUNCTI ONALLY TESTED OK TO 20,000 FEET. C/W AIRWORTHINESS DIRECTIVES OR SB'S AS PER TSM 7421 REV A JAN 1993. 1 G 7 2 3U H3EU 2001122700007 20011227 00007 SW 2001 12 27 ERAA076670 1 20011009 G 5302 STRUCTURE BELL 412 412 1182202 SW TAILBOOM CRACKED H ERAA K NONE O OTHER IN INSP/MAINT 1 FS 01 415EH 6871 ADW06067 33009 NO. 2 BULKHEAD CRACKED ABOVE ROOF PANEL. STINGER BULKHEAD UPPER SUPPORT ANGLE CRACKED. STIFFNER P/N 212-030-099-028 C RACKED. ROOF PANEL PN 205-032-815-127 HAS CORROSION & SEPERATED. VERTICAL FIN SUPPORT BULKHEADS PN 212-030-127-029 AND 021 CRACKED. L/H LOWER VERTICAL FIN SKIN CRACKED FWD BULKHEAD PN 212-030-143-009 SEPERATED. ACTION TAKEN: REPLACED STI FFNER PN 212-030-99-028. REPLACED ROOF PANEL & REPLACED FWD BULKHEAD PANEL. REPLACED BOTH VERTICAL FIN SUPPORT BULKHEA DS. FABRICATED L/H LOWER VERTICAL FIN SKIN. REPAIRED NO 2 BULKHEAD ABOVE ROOF PANEL. FABRICATED STINGER BULKHEAD SUPP ORT ANGLE. C/W AIRWORTHINESS DIRECTIVES OR SB'S AS PER ASB 412-90-49 PART II. THIS INFORMATION FOR FAA SDR. 1 G 7 2 4U H4SW 2001122700008 20011227 00008 EU 2001 12 27 ERAA076671 1 20011009 G 5302 STRUCTURE BOLKMS 105 BO105S 5626006 EU TAIL BOOM CRACKED H ERAA K NONE O OTHER IN INSP/MAINT 1 FS 01 127EH 571 TAILBOOM IS CRACKED. RT SKIN CRACKED PN 105-30251-56, LT CONTOUR SKIN PN 105-30101-14 CRACKED, SPAR PN 105-30401-16-00 1 CRACKED, 90 DEGREE GEARBOX FITTING PN 105-30402-12 HAS CORROSION, STRINGER PN 105-30251-25 IS CRACKED, STRINGER PN 105 -30251-26 IS CRACKED, FRAME SHEET PN 105-30401-29 IS CRACKED, SPAR PN 105-30412-03 HAS CORROSION. ACTION TAKEN: FAB R/ H SKIN AND FAB NEW CONTOUR SKIN, REPLACEC TWO STRINGERS AND CHANGED THE FITTING PN 105-30402-12, REPLACED SPAR PN 105-30 401-16-001 AND SPAR PN 105-30412-003 WITH NEW SPECS. REPLACED FRAME SHEET PN 105-30401-29 WITH NEW. 1 G 7 2 3U H3EU 2001122700009 20011227 00009 GL 2001 12 27 ERAA076672 2 20011009 G 7200 250C20B ENGINE BOLKMS 105 BO105S 5626006 EU ALLSN 250C 250C20B 03013 GL GEARBOX MAKING METAL H ERAA K NONE O OTHER IN INSP/MAINT 1 FS 01 426EH 13405 552 ENGINE IS MAKING METAL. G.B. SN CAG-36092 PTO GEAR PITTED. ACTION TAKEN: INSTALLED SERVICEABLE GEAR BOX. 1 G 7 2 3U 3 U H3EU E4CE 2001122700010 20011227 00010 GL 2001 12 27 ERAA076673 2 20011009 G 7200 6898735 ENGINE BOLKMS 105 BO105S 5626006 EU ALLSN 250C 250C20B 03013 GL NACELLE MALFUNCTIONED H ERAA O OTHER M J OVER TEMP WARNING INDICATION NR NOT REPORTED 1 FS 01 426EH 11039 552 TURBINE RUNS HOT, LOW POWER. STRETCHED NR 1 BLADES. ACTION TAKEN: INSTALLED NEW NR 1 & 2 WHEEL & NR 2 NOZZLE. 1 G 7 2 3U 3 U H3EU E4CE 2001122700011 20011227 00011 GL 2001 12 27 ERAA076674 2 20011009 G 7200 ENGINE BOLKMS 105 BO105S 5626006 EU ALLSN 250C 250C20B 03013 GL NACELLE MAKING METAL H ERAA K NONE O OTHER IN INSP/MAINT 1 FS 01 298EH 5449 S845 ENGINE IS MAKING METAL. HAS METAL ON MAG PLUGS. 2 1/2 BEARING INNER RFACE HAS METAL. GROOVES ON SEVERAL ROLLERS. ACT ION TAKEN: DISASSEMBL3D ENGINE CAE-836436, TURBINE, COMPRESSOR, GEARBOX. CHANGED 11/2 BEARING SN MR55741, INSTALLED MP7 5985, GEARSHAFT SN 69437 INSTALLED CI21-543. C/W AIRWORTGHINESS DIRECTIVES OR SB'S AS PER CEB-1298. SEAL ON GEARBOX ASS Y - PRESSURE OIL FITTINGS. 1 G 7 2 3U 3 U H3EU E4CE 2001122700012 20011227 00012 SW 2001 12 27 ERAA076675 1 20011009 G 3213 212321103 CROSSTUBE BELL 412 412 1182202 SW MLG CORRODED H ERAA K NONE O OTHER IN INSP/MAINT 1 FS 01 FORWARD CROSSTUBE HAS CORROSION. ACTION TAKEN: CROSSTUBE IS SCRAPPED. 1 G 7 2 4U H4SW 2001122700013 20011227 00013 SW 2001 12 27 ERAA076676 1 20011011 G 6220 412010145103 DAMPER BELL 412 412 1182202 SW MAIN ROTOR SEPARATED H ERAA K NONE O OTHER IN INSP/MAINT 1 FS 01 168EH 4949 33067 SEPERATED, UNABLE TO BALANCE MAIN ROTOR. ACTION TAKEN: RETIRED & SCRAPPED BOTH DAMPER SETS IAW 412 CR&O. 1 G 7 2 4U H4SW 2001122700014 20011227 00014 SW 2001 12 27 ERAA076677 1 20011011 G 6220 412010145103 DAMPER BELL 412 412 1182202 SW MAIN ROTOR SEPARATED H ERAA K NONE O OTHER IN INSP/MAINT 1 FS 01 168EH 225 33067 SEPERATED, UNABLE TO BALANCE MAIN ROTOR. ACTION TAKEN: RETIRED & SCRAPPED BOTN DAMPER SETS IAW 412 CR&O. THIS INFOR MATION FOR FAA SDR. 1 G 7 2 4U H4SW 2001122700015 20011227 00015 SW 2001 12 27 ERAA076678 1 20011011 G 6220 412010145103 DAMPER BELL 412 412 1182202 SW MAIN ROTOR CRACKED H ERAA K NONE O OTHER IN INSP/MAINT 1 FS 01 419EH 5488 33043 DAMPER SET IS CRACKED. FOUND SETS WORN & CRACKED ACTION TAKEN: RETIRED & SCRAPPED IAW 412 CR&O, THIS INFORMATION FOR FAA SDR. 1 G 7 2 4U H4SW 2001122700016 20011227 00016 SW 2001 12 27 ERAA076679 1 20011011 G 6220 412010145103 DAMPER BELL 412 412 1182202 SW MAIN ROTOR CRACKED H ERAA K NONE O OTHER IN INSP/MAINT 1 FS 01 419EH 6519 33043 DAMPER SET IS WEAK/ WORN / CRACKED. ACTION TAKEN: DAMPER SET WAS RETIRED & SCRAPPED IAW 412 CR&O. THIS INFORMATION FOR FAA SDR. 1 G 7 2 4U H4SW 2001122700017 20011227 00017 SW 2001 12 27 ERAA076680 1 20011011 G 6410 212011701003FM BLADE BELL 412 412 1182202 SW TAIL ROTOR DAMAGED H ERAA K NONE O OTHER IN INSP/MAINT 1 FS 01 422EH 4048 33068 TAIL ROTOR BLADE A-11090 HAS VOID AT TIP, TRUNNION IS ROUGH. TAIL ROTOR BLADE SENT TO CTI FOR REPAIR. TRUNNION, TRUNNI ON HOUSING ASSYS SCRAPPED. ACTION TAKEN: INST'D NEW TRUNNION, TRUNNION HOUSINGS, BEARINGS, & SEALS, INSTALLED SERVICEAB LE TAIL ROTOR BLADE. ASSEMBLED, BALANCED & LUBED T/R ASSY IAW 412 CR& O & T.B. 412-95-134. C/W AIRWORTHINESS DIRECTIVE S OR SB'S AS PER TB 412-95-134. THIS INFORMATION FOR FAA SDR. 1 G 7 2 4U H4SW 2001122700018 20011227 00018 SW 2001 12 27 ERAA076681 1 20011011 G 6320 412040002103 TRANSMISSION BELL 412 412 1182202 SW MAIN ROTOR CORRODED H ERAA K NONE O OTHER IN INSP/MAINT 1 FS 01 164EH 8992 33004 TRANSMISSION DUE 3100 HOUR INSPECTION. LOWER SPIDER BREAKING, UPPER SUN GEAR BREAKING, MAIN INPUT LINER, MAIN CASE HAS EXCESSIVE CORROSION DAMAGE, MAIN INPUT QUILL ALIGNMENT MARKS BEARING PINION OFF, RING GEAR OUTER SURFACE RUSTING, MAIN I NPUT BEARING SLEEVE RUSTED. ACTION TAKEN: SENT TO ERA REPAIR STATION ALASKA FOR INSPECTION. THIS INFORMATION FOR FAA S DR. 1 G 7 2 4U H4SW 2001122700020 20011227 00020 EU 2001 12 27 ERAA076682 1 20011012 G 5302 STRUCTURE BOLKMS 105 BO105A EU TAILBOOM CRACKED H ERAA K NONE O OTHER IN INSP/MAINT 1 FS 01 290EH 5756 S850 TAILBOOM REMOVED FROM AIRCRAFT DUE TO CRACKED SKIN RT SIDE BASE OF VERTICAL FIN. FOUND RUSTED, CORRODED & PITTED TAIL S KID BRACKETS. CORRODED FWD MOUNTING FLANGES. CORROSION & PITTED SPOTS ON 90 DEGREE GEARBOX FITTING BOLT HOLES. ACTION TAKEN: INSTALLED NEW TAILSKID BRACKETS, FWD & AFT, INSTALLED NEW 90 DEGREE GEARBOX FITTING AND REPLACED FWD MOUNT FLANG E. FABRICATED & INSTALLED NEW R/H FWD SKIN, PLUS VALVE MOUNT BRACKETS & DOUBLER AND CLEARED ALL OTHER MAINTENANCE DESCR EPANCIES IN BLUE WORK FORMS OF WORK ORDER C298015. THIS INFORMATION IS FOR FAA SDR. 1 G 7 2 3U H3EU 2002012300049 20020123 00049 SW 2002 1 23 ERAA076683 1 20011012 G 3212 412050045107 CROSSTUBE BELL 412 412 1182202 SW MLG CORRODED A ERAA K NONE O OTHER IN INSP/MAINT 1 AL 03 412EH 33001 AFT CROSSTUBE IS CORRODED. ACTION TAKEN: PART WAS SCRAPPED. 1 G 7 2 4U H4SW 2002012300050 20020123 00050 SW 2002 1 23 ERAA076684 1 20011012 G 5520 205030856113 SKIN BELL 412 412 1182202 SW RT ELEVATOR CRACKED H ERAA K NONE O OTHER IN INSP/MAINT 1 FS 01 167EH 33089 RT ELEVATOR SKIN CRACKED. FOUND SPAR TO BE UNBONDED AT FLANGE & ROOT RIB TO BE CORRODED BEYOND LIMITS. ACTION TAKEN: R E-MANUFACTURER OUTER SKIN, REPLACED SPAR & ROOT RIBS & REASSEMBLED. C/W AIRWORTHINESS DIRECTIVES OR SB'S AS PER TB-412- 83-31. THIS INFORMATION IS FOR FAA SDR. 1 G 7 2 4U H4SW 2002012300052 20020123 00052 GL 2002 1 23 ERAA077281 1 20011022 G 6410 332A12005001 BLADE AMTR PURE PUREAIR GL TAIL ROTOR DAMAGED H ERAA K NONE O OTHER IN INSP/MAINT 1 FS 01 170EH 286 2016 TAIL ROTOR BLADE HAS AN INTERNAL NOISE AND SUSPECT THAT THERE MAY BE SOMETHING LOOSE INSIDE. 1 H 7 1 3O EXPA1H71 2002012300055 20020123 00055 EU 2002 1 23 ERAA077284 1 20011029 G 6410 PAINT BOLKMS 105 BO105S 5626006 EU T/R BLADE CRACKED H ERAA K NONE O OTHER IN INSP/MAINT 1 FS 01 293EH 1540 587588 559 TAIL ROTOR BLADE PAINT IS CRACKED AND VOIDED ON END CAP. 1 G 7 2 3U H3EU 2002012300058 20020123 00058 NE 2002 1 23 ERAA077285 1 20011031 G 5320 BUSHING SKRSKY S61 S61N 8142104 NE BATTERY ABSORBER WORN H ERAA K NONE O OTHER IN INSP/MAINT 1 FS 01 563EH 61808 BUSHINGS WORN. 2 G 7 2 4U 1H15 2002012300062 20020123 00062 EU 2002 1 23 ERAA077292 1 20011115 G 6520 4619311033 BEARING BOLKMS 105 BO105S 5626006 EU T/R XMSN FAILED H ERAA K NONE O OTHER IN INSP/MAINT 1 FS 01 133EH 598 BEARING ROLLER FALLS OUT OF CAGE. 1 G 7 2 3U H3EU 2002012300074 20020123 00074 NE 2002 1 23 ERAA077293 2 20011115 G 7311 STRUCTURE BELL 412 412 1182202 SW PWA PT6T PT6T3B 52045 NE COOLER BLOWER CORRODED H ERAA K NONE O OTHER IN INSP/MAINT 1 FS 01 417EH 8358 5100712 33031 VANE GUIDE ASSY HAS PITTING & CORROSION. COATING ASSY HAS MECHANICAL DAMAGE ON OUTER LIP. SLIGHT CORROSION ON LOCK PLA TE. SPACER FAILED DUE TO MECHANICAL DAMAGE. IMPELLAR HAS CRACKED BLADES. ACTION TAKEN: DISASSEMBLED & STRIPPED PAINT. COMPLIED WITH VISUAL & NDT INSPECTIONS. REMOVED & TREATED SLIGHT CORROSION. HAD VARIOUS PARTS PAINTED. REASSEMBLED & OVERHAULED USING NEW COATING ASSY., IMPELLAR, GUIDE VANE ASSY, NEW BEARINGS, PACKING, GASKET, AND HARDWARE AND NEW DECA L IAW 412 CR&O CHAPTER 79 & BHT-ALL-SPM. 1 G 7 2 4U 4 U H4SW E22EA 2002012300075 20020123 00075 GL 2002 1 23 ERAA077294 2 20011116 G 7200 250C20B ENGINE BOLKMS 105 BO105S 5626006 EU ALLSN 250C 250C20B 03013 GL ENG BAY MAKING METAL H ERAA K NONE O OTHER IN INSP/MAINT 1 FS 01 294EH 6308 S675 ENGINE IS MAKING METAL, BOTH PLUGS. FC-OP GEARSHAFT DAMAGED PN 6896437 ACTION TAKEN: INSTALLED NEW GEARSHAFT & COMPLIE D WITH CEB-A-1386 TQ METER GEAR INSPECTION . 1 G 7 2 3U 3 U H3EU E4CE 2002012300076 20020123 00076 EU 2002 1 23 ERAA077295 1 20011116 G 2435 GEARSHAFT BOLKMS 105 BO105S 5626006 EU STARTER GEN WORN H ERAA K NONE O OTHER IN INSP/MAINT 1 FS 01 124EH 4928 S559 ENGINE IS MAKING METAL. . STARTER GENERATOR GEARSHAFT IS WORN. ACTION TAKEN: INSTALLED NEW GEARSHAFT AND BEARINGS. COMPLIED WITH CEB A-1374 PRESSURE PROBE INSPECTION. 1 G 7 2 3U H3EU 2002012300079 20020123 00079 SW 2002 1 23 ERAA077296 1 20011116 G 6320 412040002103 BEARING BELL 412 412 1182202 SW TAIL ROTOR MAKING METAL H ERAA K NONE O OTHER IN INSP/MAINT 1 FS 01 418EH 7849 TRANSMISSION IS MAKING METAL. TAILROTOR QUILL BEARINGS CAUSE OF METAL CONTAMINATION. SEAL LEAKS. MAIN INPUT R/B QUILL , SYS II HYD QUILL AND AUX JETS ON RING GEAR CASE. ACTION TAKEN: REPAIRED, PARTIALLY DISASSEMBLED, VISUALLY INSPECTED E XPOSED COMP. INSTALLED NEW BEARINGS T/R QUILL AND PACKED WITH GEAR, INSTALLED NEW SEALS, AND GASKET, O RINGS TO REPAIR L EAKS. ALL WORK IAW BHT 412 CR&O. 1 G 7 2 4U H4SW 2002012300084 20020123 00084 SW 2002 1 23 ERAA077297 1 20011116 G 6210 SKIN BELL 412 412 1182202 SW M/R BLADE DAMAGED H ERAA K NONE O OTHER IN INSP/MAINT 1 FS 01 168EH 8848 33067 REMOVED FOR FLIGHT CHARACTERISTICS BLADE HAS CREASES UPPER AND LOWER, PAINT WORK NEEDED. L/S HAS SKIN DAMAGE WITH VOID AT STA 192-194, T/B AND CTR TRIM TABS HAVE SKIN DAMAGE WITH VOIDS, WATER FOUND IN CORE DURING BOND PREP FOR PATCHES, UPP ER SURFACE SKIN DAMAGE AT STA 226- 258 ESTENE DETERIORATED, REFLEX DOUBLER DEBONDED. 1 G 7 2 4U H4SW 2002012300086 20020123 00086 EU 2002 1 23 ERAA077298 1 20011116 G 6410 BLADE BOLKMS 105 BO105S 5626006 EU TAIL ROTOR DAMAGED H ERAA K NONE O OTHER IN INSP/MAINT 1 FS 01 293EH 11985 559 END CAP OF ONE BLADE HAS A SPLIT IN THE PAINT. PITCH MOVEMENT FEELS ROUGH. BLADES DAMAGED, BUSHINGS (TEFLON) DIRTY, SE ALS WARPED. ACTION TAKEN: REM'D BLADES AND SENT OUT FOR REPAIR. DISASSEMBLED TO FACILLITATE TEFLON BEARING CLEANING . CLEANED BEARING SURFACES AND REASSEMBLED HUB WITH NEW SEALS & NUTS. INSTALLED SERVICEABLE BLADES AND STATIC BALANCED TA ILROTOR ASSY. REPAIRED IAW BO105 REM M/M CHAPTER 34 & 33 AND MARVEL BOOK. 1 G 7 2 3U H3EU 2002012300090 20020123 00090 GL 2002 1 23 ERAA077515 2 20011204 G 7230 PLUG BOLKMS 105 BO105A EU ALLSN 250C 250C20B 03013 GL COMPRESSOR DISLODGED H ERAA K NONE O OTHER IN INSP/MAINT 1 FS 01 423EH 6244 543 ENGINE IS MAKING METAL. RESI-WELD FE 186 SEALANT PLUG DISLODGED FROM COMPRESSOR MOUNT. SEALANT PLUG LODGED IN OIL PUM P SCAVENGE PORT. THIS DID NOT LET THE OIL SCAVENGE, THUS LETTING THE BEARINGS STARVE FOR OIL CAUSING IT TO MAKE METAL. A CTION TAKEN: DISASSEMBLED ENGINE. GEARBOX AND TURBINE WILL NEED OVERHAUL AND COMPLETE INSPECTION OF COMPRESSOR. GEARB OX SN CAG-37622 TT 12330.8 TSO 4694.6 (LAST O/H 3-5-91) 1 G 7 2 3U 3 U H3EU E4CE 2001050200063 20010502 00063 NM 2001 5 2 ERKR200100067 1 20010326 G 5330 SKIN DOUG MD88 MD88 3023688 NM FUSELAGE DAMAGED B ERKR K NONE O OTHER IN INSP/MAINT 1 WP 07 12FQ 49766 REPAIRED SKIN PANEL, STATION 560, STRINGER 24R-25R RIGHT. 2 L 7 2 4F RT A6WE 2001050200064 20010502 00064 NM 2001 5 2 ERKR20010068 1 20010326 G 5512 5922577506 SKIN DOUG MD88 MD88 3023688 NM HORIZONTAL STAB CORRODED B ERKR K NONE O OTHER IN INSP/MAINT 1 WP 07 12FQ 49766 RIGHT HORIZONTAL STABILIZER, BARREL NUT HOLES XHS 27.234. THIS DOCUMENT PROVIDES REPAIR INSTRUCTIONS FOR CORROSION FOUND IN THE THREE BARREL NUT HOLE BORES OF THE RIGHT HORIZONTAL STABILIZER LOWER FORWARD AND LOWER CENTER SKIN PANELS. PART NUMBERS 5922576504 AND 5922577506.PER ECRA N12FQ55MD88002EAC. 2 L 7 2 4F RT A6WE 2001121100030 20011211 00030 SO 2001 12 11 ERY2001F00000 2 20011115 G 8520 CRANKCASE BEECH 58 58 1152740 CE CONT O550 IO550C SO ENGINE CRACKED F K NONE K FLUID LOSS IN INSP/MAINT 1 CE 07 384P 399 TH1888 684243 ENGINE OIL LEAK, FOUND 3 INCH LONG CRACK IN CRANKCASE ABOVE NR 3 CYLINDER, CRACK SEEMS TO ORIGINATE FROM UPPER CASE LEFT AND EXTEND DOWNWARD. 1 L 7 2 3O 3 O 3A16 E3SO 2001080300081 20010803 00081 CE 2001 8 3 ERYR682D2001 1 20010511 G 3242 50300010121 LINER BEECH 90 E90 1152914 CE LT MLG BRAKE BROKEN B E D ENGINE SHUTDOWN RETURN TO BLOCK L NO TEST TX TAXI/GRND HDL 1 SO 11 22TL LW334 OVERHAULED BRAKE ASSEMBLY WAS INSTALLED AND FUNCTIONALLY TESTED BY MAINTENANCE PERSONNEL WITH NO NOTED DEFECTS. DURING T AKEOFF ROLL PILOT NOTICED AIRCRAFT SEEM TO PULL TO ONE SIDE, PILOT ABORTED TAKEOFF AND RETURNED TO CHOCKS. MAINTENANCE P ERSONNEL VISUALLY EXAMINED BRAKES AND FOUND NO OBVIOUS DEFECTS. MAINTENANCE AND OPERATOR DECIDED TO PERFORM HIGH SPEED T AXI TO FURTHER TROUBLESHOOT BRAKING SYSTEM. DURING TAXI CHECK LT BRAKE FAILED AND BECAME COMPLETELY INEFFECTIVE. OPERATO R SHUT DOWN ENGINES AND AIRCRAFT WAS TOWED BACK TO MAINTENANCE FOR EVALUATION. MAINTENANCE EVALUATION DISCOVERED APPROXI MATE THREE INCH SECTION OF BRAKE LINING ASSEMBLY HAD BROKEN LOOSE AND ALLOWED LINING TO ROTATE OUT OF KEYWAY SLOTS. 1 L 7 2 3T 3A20 2001082900261 20010829 00261 SO 2001 8 29 GAC081601 1 20010816 G 2432 1159SCAV5201 CHARGER GULSTM G1159 GIV 3980115 SO TAIL FAILED B H DEACTIVATE SYST/CIRCUITS B SMOKE/FUMES/ODORS/SPARKS IN INSP/MAINT 1 SO 11 426QS 359 1426 DURING NORMAL MAINTENANCE WHILE ON THE GROUND THE BATTERY CHARGER BEGAN TO SMOKE AND THE CIRCUIT BREAKER POPPED. REMOVE D AND REPLACED BATTERY CHARGER WITH REPAIRED UNIT. 2 L 7 2 4F RT A12EA 2001080300083 20010803 00083 SW 2001 8 3 GDMA073295 1 20010612 G 7910 H33C32 BEARING 204062540001 BELL 205 205A1 1181414 SW ENGINE ROUGH H GDMA K NONE O OTHER IN INSP/MAINT 1 FS 01 97HJ 398 1771292 30173 MEDIUM FREQ VIBRATION IN THE AIRFRAME. REPLACED BEARINGS IN THE FAN 1 G 7 1 4U H1SW 2001042400307 20010424 00307 CE 2001 4 24 GLBA2001085 1 20010419 G 2720 CONTROL UNIT BEECH 1900 1900D 1154162 CE RUDDER MALFUNCTIONED A GLBA A UNSCHED LANDING F FLT CONT AFFECTED CL CLIMB 1 CE 01 257GL UE257 UNCOMMANDED RUDDERR BOOST IN FLIGHT, PENDING CORRECTIVE ACTION 2 L 7 2 4T RT A24CE 2001051500132 20010515 00132 CE 2001 5 15 GLBA2001094 1 20010506 G 5270 HANDLE BEECH 1900 1900D 1154162 CE PAX DOOR MALFUNCTIONED A GLBA D RETURN TO BLOCK N FALSE WARNING CL CLIMB 1 CE 01 257GL UE257 CABIN DOOR ANNUNCIATOR ILLUMINATED ON CLIMB-OUT, INSPECTED RESET CABIN DOOR HANDLE OPS CHECKED GOOD 2 L 7 2 4T RT A24CE 2001071700050 20010717 00050 CE 2001 7 17 GLBA2001104 1 20010521 G 2130 13037432 CONTROLLER BEECH 1900 1900D 1154162 CE ONLY INOPERATIVE A GLBA A UNSCHED LANDING O OTHER CR CRUISE 1 CE 01 257GL 138 UE257 CABIN PRESSURIZATION NOT HOLDING, REPLACED CONTROLLER 2 L 7 2 4T RT A24CE 2001080300084 20010803 00084 CE 2001 8 3 GLBA2001105 1 20010522 G 2840 12281301 METER BEECH 1900 1900D 1154162 CE FUEL FLOW FAILED A GLBA C ABORTED TAKEOFF J WARNING INDICATION TO TAKEOFF 1 CE 01 257GL 423 UE257 LEFT AND RIGHT FUEL FLOW GAUGES FLUCTUATED WHEN POWER ADVANCED, REPLACED FLOW METER 2 L 7 2 4T RT A24CE 2001080300085 20010803 00085 2001 8 3 GLBA2001111 4 20010527 G 3443 6227337001 RADAR EMB 120 EMB120 3260201 SO WX RADAR INOPERATIVE A GLBA A UNSCHED LANDING O OTHER CR CRUISE 1 CE 01 92GL 6786 15 120092 WEATHER RADAR FAILED, INSPECTED FOUND RT UNIT BAD REPLACED OPS CHECKED SYSTEM SATISFACTORY 2 L 7 2 4T RT A31SO 2001041700100 20010417 00100 NE 2001 4 17 H1IR069Y01 2 20010305 G 7230 3029051 VANE CESSNA 208 208B 2073701 CE PWA PT6 PT6A114A 52043 NE COMPRESSOR CRACKED B H1IR K NONE O OTHER IN INSP/MAINT 1 NE 01 28AN 2221 208B0751 PCEPC0677 COMPRESSOR TURBINE VANE RING OUTER RING ANTI ROTATION LUGS ARE CRACKED OR SEPARATED BEYOND THE MAXIMUM REPAIRABLE LIMIT OF SEVEN. 11 LUGS SEPARATED AND 1 EA CRACKED FROM A TOTAL OF 14. EXPERIENCE INDICATES NORMAL AS REMOVED VANE RINGS WIT H THIS TOTAL TIME SHOULD HAVE NO DEFECTS IN THIS AREA. 1 H 7 1 3T 3 T A37CE E4EA 2001041700101 20010417 00101 EA 2001 4 17 H1IR069Y02 2 20010305 G 7230 3032151 VANE PWA PT6 PT6A34 52043 EA COMPRESSOR CRACKED B H1IR K NONE O OTHER IN INSP/MAINT 1 NE 01 9D149 COMPRESSOR TURBINE VANE RING OUTER RING ANTI ROTATION LUGS ARE CRACKED OR SEPARATED BEYOND THE MAXIMUM REPAIRABLE LIMIT OF SEVEN. 9 OF 14 LUGS FOUND SEPARATED. 4 T E4EA 2001091000313 20010910 00313 EU 2001 9 10 HCMA075341 1 20010117 G 6420 350A33215300 BEARING SNIAS 350 AS350B2 8680813 EU TAIL ROTOR WORN E HCMA K NONE O OTHER IN INSP/MAINT 1 WP 13 997BH 837 2666 PART IS WORN BEYOND LIMITS. 1 G 7 1 3U H9EU 2001091000318 20010910 00318 EU 2001 9 10 HCMA075358 1 20010124 G 6410 355A12004008 BLADE SNIAS 350 AS350B2 8680813 EU TAIL ROTOR PEELING E HCMA K NONE O OTHER IN INSP/MAINT 1 WP 13 992BH 35 2889 WHITE PAINT IS PEELING OFF BLADE AND IS EXTREMELY HARD TO BALANCE. PLEASE REPAIR UNDER FULL WARRANTY. 1 G 7 1 3U H9EU 2001091000321 20010910 00321 EU 2001 9 10 HCMA075365 1 20010522 G 6420 350A33215300 BEARING SNIAS 350 AS350B2 8680813 EU TAIL ROTOR WORN E HCMA K NONE O OTHER IN INSP/MAINT 1 WP 13 992BH 805 2889 PART IS WORN BEYOND LIMITS. 1 G 7 1 3U H9EU 2001091000323 20010910 00323 EU 2001 9 10 HCMA075367 1 20010706 G 6420 350A33214501 ROD SNIAS 350 AS350BA 8680817 EU PITCH CONTROL WORN E HCMA K NONE O OTHER IN INSP/MAINT 1 WP 13 642BH 606 2495 PART IS WORN BEYOND LIMITS. 1 G 7 1 3U NC H9EU 2001091000324 20010910 00324 EU 2001 9 10 HCMA075368 1 20010706 G 6420 350A33214501 ROD SNIAS 350 AS350BA 8680817 EU PITCH CONTROL WORN E HCMA K NONE O OTHER IN INSP/MAINT 1 WP 13 862BH 159 2713 PART IS WORN BEYOND LIMITS. 1 G 7 1 3U NC H9EU 2001091000325 20010910 00325 EU 2001 9 10 HCMA075369 1 20010706 G 6420 350A33214501 ROD SNIAS 350 AS350B2 8680813 EU TAIL ROTOR WORN E HCMA K NONE O OTHER IN INSP/MAINT 1 WP 13 982BH 934 2876 PART IS WORN BEYOND LIMITS. 1 G 7 1 3U H9EU 2001091000327 20010910 00327 EU 2001 9 10 HCMA075370 1 20010706 G 6420 350A33214501 ROD SNIAS 350 AS350B2 8680813 EU PITCH CONTROL WORN E HCMA K NONE O OTHER IN INSP/MAINT 1 WP 13 992BH 474 2889 PART IS WORN BEYOND LIMITS. 1 G 7 1 3U H9EU 2001091000328 20010910 00328 EU 2001 9 10 HCMA075371 1 20010706 G 6420 350A33214501 ROD SNIAS 350 AS350B2 8680813 EU PITCH CONTROL WORN E HCMA K NONE O OTHER IN INSP/MAINT 1 WP 13 992BH 184 2889 PART IS WORN BEYOND LIMITS. 1 G 7 1 3U H9EU 2001091000329 20010910 00329 EU 2001 9 10 HCMA075372 1 20010706 G 6420 350A33214501 ROD SNIAS 350 AS350B2 8680813 EU PITCH CONTROL WORN E HCMA K NONE O OTHER IN INSP/MAINT 1 WP 13 992BH 599 2889 PART IS WORN BEYOND LIMITS. 1 G 7 1 3U H9EU 2001091000331 20010910 00331 EU 2001 9 10 HCMA075373 1 20010706 G 6420 350A33214501 ROD SNIAS 350 AS350B2 8680813 EU PITCH CONTROL WORN E HCMA K NONE O OTHER IN INSP/MAINT 1 WP 13 193BH 643 2894 PART IS WORN BEYOND LIMITS. 1 G 7 1 3U H9EU 2001091100001 20010911 00001 EU 2001 9 11 HCMA075374 1 20010706 G 6420 350A33214501 ROD SNIAS 350 AS350B2 8680813 EU PITCH CONTROL WORN E HCMA K NONE O OTHER IN INSP/MAINT 1 WP 13 194BH 499 2903 PART IS WORN BEYOND LIMITS. 1 G 7 1 3U H9EU 2001091100002 20010911 00002 EU 2001 9 11 HCMA075375 1 20010706 G 6420 350A33214501 ROD SNIAS 350 AS350B2 8680813 EU PITCH CONTROL WORN E HCMA K NONE O OTHER IN INSP/MAINT 1 WP 13 194BH 258 2903 PART IS WORN BEYOND LIMITS. 1 G 7 1 3U H9EU 2001091100003 20010911 00003 EU 2001 9 11 HCMA075376 1 20010706 G 6420 350A33214501 ROD SNIAS 350 AS350B2 8680813 EU PITCH CONTROL WORN E HCMA K NONE O OTHER IN INSP/MAINT 1 WP 13 194BH 170 2903 PART IS WORN BEYOND LIMITS. 1 G 7 1 3U H9EU 2001091100004 20010911 00004 EU 2001 9 11 HCMA075377 1 20010706 G 6420 350A33214501 ROD SNIAS 350 AS350B2 8680813 EU PITCH CONTROL WORN E HCMA K NONE O OTHER IN INSP/MAINT 1 WP 13 995BH 245 2987 PART IS WORN BEYOND LIMITS. 1 G 7 1 3U H9EU 2001091100005 20010911 00005 EU 2001 9 11 HCMA075378 1 20010706 G 6420 350A33214501 ROD SNIAS 350 AS350B2 8680813 EU PITCH CONTROL WORN E HCMA K NONE O OTHER IN INSP/MAINT 1 WP 13 196BH 932 3036 PART IS WORN BEYOND LIMITS. 1 G 7 1 3U H9EU 2001091100006 20010911 00006 EU 2001 9 11 HCMA075379 1 20010706 G 6420 350A33214501 ROD SNIAS 350 AS350B2 8680813 EU PITCH CONTROL WORN E HCMA K NONE O OTHER IN INSP/MAINT 1 WP 13 197BH 751 2666 PART IS WORN BEYOND LIMITS. 1 G 7 1 3U H9EU 2001091100007 20010911 00007 EU 2001 9 11 HCMA075380 1 20010706 G 6420 350A33214501 ROD SNIAS 350 AS350B2 8680813 EU PITCH CONTROL WORN E HCMA K NONE O OTHER IN INSP/MAINT 1 WP 13 198BH 900 3126 PART IS WORN BEYOND LIMITS. 1 G 7 1 3U H9EU 2001091100008 20010911 00008 EU 2001 9 11 HCMA075381 1 20010706 G 6420 350A33214501 ROD SNIAS 350 AS350B2 8680813 EU PITCH CONTROL WORN E HCMA K NONE O OTHER IN INSP/MAINT 1 WP 13 198BH 89 3126 PART IS WORN BEYOND LIMITS. 1 G 7 1 3U H9EU 2001091100009 20010911 00009 EU 2001 9 11 HCMA075382 1 20010706 G 6420 350A33214501 ROD SNIAS 350 AS350B2 8680813 EU PITCH CONTROL WORN E HCMA K NONE O OTHER IN INSP/MAINT 1 WP 13 198BH 546 3126 PART IS WORN BEYOND LIMITS. 1 G 7 1 3U H9EU 2001091100010 20010911 00010 EU 2001 9 11 HCMA075388 1 20010814 G 6410 355A12004008 BLADE SNIAS 350 AS350B2 8680813 EU TAIL ROTOR CRACKED E HCMA K NONE O OTHER IN INSP/MAINT 1 WP 13 992BH 874 2889 TAIL ROTOR BLADE CRACKED. 1 G 7 1 3U H9EU 2001091100011 20010911 00011 EU 2001 9 11 HCMA075391 1 20010821 G 5302 350A2300000201 TAIL BOOM SNIAS 350 AS350BA 8680817 EU TAIL MISMANUFACTURED E HCMA K NONE W INADEQUATE Q C IN INSP/MAINT 1 WP 13 642BH 15023 2495 TAILBOOM SKIN NOT PROPER THICKNESS. 1 G 7 1 3U NC H9EU 2001041900237 20010419 00237 NE 2001 4 19 HEEA071922 1 20010403 G 6410 7610105101041 BLADE SKRSKY S76 S76A 8143006 NE TAIL ROTOR DAMAGED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 1545X 12811 760050 TRAILING EDGE OF PADDLE A IS SPLIT OPEN. THE CENTER PLUG IS ALSO DEBONDED. SENT TO INTERNATIONAL AVIATION COMPOSITES FO R INSPECTION AND REPAIR. 1 G 7 2 3U H1NE 2001041900238 20010419 00238 NE 2001 4 19 HEEA071923 1 20010405 G 6210 7615009043050 TIP CAP SKRSKY S76 S76A 8143006 NE MAIN ROTOR BLADE CRACKED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 15460 760223 TOP SKIN HAS A CRACK SPANWISE APPROXIMATELY 2 INCHES FROM TRAILING EDGE. THE ABRASION STRIP HAS A CRACK WITH SEPARATION . SENT TO COMPOSITE TECHNICS FOR INSPECTION AND REPAIR. 1 G 7 2 3U H1NE 2001041900239 20010419 00239 NE 2001 4 19 HEEA071924 1 20010405 G 6210 7615009043050 TIP CAP SKRSKY S76 S76A 8143006 NE MAIN ROTOR BLADE CRACKED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 911UK 760275 TOP INNER AND OUTER DOUBLER SEPARATED BEYOND LIMITS. ABRASION STRIP HAS CRACKS ON BOTH SIDES. SENT TO COMPOSITE TECHNIC S FOR INSPECTION AND REPAIR. 1 G 7 2 3U H1NE 2001041900240 20010419 00240 2001 4 19 HEEA071925 4 20010405 G 2340 A3016W CONTROL PANEL SKRSKY S76 S76A 8143006 NE INTERPHONE MALFUNCTIONED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 761PH 760224 NEEDS EVALUATION. PERFORMED PRELIMINARY INSPECTION AND TESTED. FOUND SWITCHES S1, S4, S5, S8, LIGHT PANEL, VOLUME KNOB AND TRANSMIT KNOB BAD. ALSO LIGHT PANEL LIGHTS BAD FROM STOCK. REPLACED ALL AND RESOLDERED BAD SOLDER CONNECTION ON LI GHT PANEL. REPAIRED. BENCH CHECK GOOD. 1 G 7 2 3U H1NE 2001041900241 20010419 00241 SW 2001 4 19 HEEA071926 1 20010402 G 5302 214021211110S PANEL BELL 214 214ST 1182106 SW TAILBOOM MISMANUFACTURED E HEEA K NONE W INADEQUATE Q C IN INSP/MAINT 1 SW 03 PANEL RECEIVED PREVIOUSLY TRIMMED ALONG FORWARD END. CANNOT POSITION ON TAILBOOM TO ACHIEVE PROPER EDGE DISTANCE ON ALL FASTENERS. PANEL NEEDS TO BE MOVED FORWARD AND CORE TRANSITION IS ALREADY CONTACTING STRAP AT BOOM STATION 293.50. PA NEL IS SHORTER THAN THE PANEL REMOVED FROM THE TAILBOOM SENT TO BELL HELICOPTER TEXTRON FOR CREDIT. 2 G 7 2 4U H10SW 2001041900242 20010419 00242 SW 2001 4 19 HEEA071927 1 20010402 G 6330 206033505101 NODAL ARM BELL 206 206L3 1182108 SW TRANSMISSION MISMANUFACTURED E HEEA K NONE W INADEQUATE Q C IN INSP/MAINT 1 SW 03 ARM IS NOT MACHINED OUT AT INBOARD RADIUS. 1 G 7 1 3U H2SW 2001041900243 20010419 00243 SW 2001 4 19 HEEA071928 1 20010402 G 5302 206033412001A BRACKET BELL 206 206L3 1182108 SW TAILBOOM MISMANUFACTURED E HEEA K NONE W INADEQUATE Q C IN INSP/MAINT 1 SW 03 BRACKET HAS PILOT HOLES FROM FACTORY DRILLED OPPOSITE OF REQUIRED LAYOUT. 1 G 7 1 3U H2SW 2001041900244 20010419 00244 SW 2001 4 19 HEEA071929 1 20010403 G 2840 473203003 SIGNAL COND UNIT BELL 412 412 1182202 SW FUEL INDICATOR INTERMITTENT E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 FUEL LOW LEVEL LIGHT COMES ON INTERMITTENTLY. 1 G 7 2 4U H4SW 2001041900245 20010419 00245 SW 2001 4 19 HEEA071930 1 20010403 G 2612 30236ET1 AMPLIFIER BELL 412 412 1182202 SW FIRE DETECTOR MALFUNCTIONED E HEEA O OTHER N FALSE WARNING CR CRUISE 1 SW 03 5759N 33002 WHILE IN CRUISE FLIGHT THE BAGGAGE COMPARTMENT FIRE LIGHT ILLUMINATED. NO FIRE OBSERVED. MAINTENANCE REPAIRED CHAFED WI RE AT AMPLIFIER CONTROL CONNECTOR. 1 G 7 2 4U H4SW 2001041900246 20010419 00246 SW 2001 4 19 HEEA071931 1 20010403 G 7600 CONTROL UNIT BELL 214 214ST 1182106 SW NR 2 ENGINE MALFUNCTIONED E HEEA A UNSCHED LANDING J WARNING INDICATION CR CRUISE 1 SW 03 3897N 28106 IN CRUISE FLIGHT, NR 2 ENGINE DROPPED OFF LINE THEN RECOVERED BACK TO 100 PERCENT. PLACED NR 2 ENGINE IN ECU LOCKOUT AND RETURNED TO BASE. 2 G 7 2 4U H10SW 2001041900247 20010419 00247 SW 2001 4 19 HEEA071932 1 20010403 G 2435 BRUSHES BELL 407 407 SW STARTER GEN WORN E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 498PH 2544 53399 BRUSHES WORN. 1 G 7 1 3U O H2SW 2001041900248 20010419 00248 SW 2001 4 19 HEEA071933 1 20010403 G 2435 BRUSHES BELL 407 407 SW STARTER GEN WORN E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 490PH 1337 53378 BRUSHES WORN. 1 G 7 1 3U O H2SW 2001041900249 20010419 00249 SW 2001 4 19 HEEA071934 1 20010403 G 2822 1C641 PUMP BELL 412 412 1182202 SW FUEL BOOST FAILED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 1202T 33112 TRANSFER LIGHT COMING ON ABOVE 1700 LBS. REPLACED WITH SERVICEABLE PART. 1 G 7 2 4U H4SW 2001041900250 20010419 00250 SW 2001 4 19 HEEA071935 1 20010403 G 6720 412010406115 LINK BELL 412 412 1182202 SW ROD END WORN E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 2148K 36001 BEARINGS WORN. REPLACED WITH SERVICEABLE PART. 1 G 7 2 4U H4SW 2001041900251 20010419 00251 SW 2001 4 19 HEEA071936 1 20010403 G 6720 412010406115 LINK BELL 412 412 1182202 SW ROD END WORN E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 3893L 33006 BEARINGS WORN. REPLACED WITH SERVICEABLE PART. 1 G 7 2 4U H4SW 2001041900252 20010419 00252 SW 2001 4 19 HEEA071937 1 20010403 G 6720 412010406115 LINK BELL 412 412 1182202 SW ROD END WORN E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 2148K 36001 BEARINGS WORN. REPLACED WITH SERVICEABLE PART. 1 G 7 2 4U H4SW 2001041900253 20010419 00253 SW 2001 4 19 HEEA071938 1 20010403 G 6720 412010406115 LINK BELL 412 412 1182202 SW ROD END WORN E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 3911L 33023 BEARINGS WORN. REPLACED WITH SERVICEABLE PART. 1 G 7 2 4U H4SW 2001041900254 20010419 00254 SW 2001 4 19 HEEA071939 1 20010403 G 3340 7028521 STROBE BELL 412 412 1182202 SW EXTERIOR FAILED E HEEA K NONE L NO TEST IN INSP/MAINT 1 SW 03 3893L 33006 NO OUTPUT. REPLACED WITH SERVICEABLE PART. 1 G 7 2 4U H4SW 2001041900255 20010419 00255 SW 2001 4 19 HEEA071940 1 20010403 G 3340 G62504 LIGHT BELL 412 412 1182202 SW EXETERIOR SEARCH FAILED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 3893L 33006 SEARCH LIGHT WILL NOT POINT FORWARD. REPLACED WITH SERVICEABLE PART. 1 G 7 2 4U H4SW 2001041900256 20010419 00256 2001 4 19 HEEA071941 4 20010403 G 3416 5934D3 ALTIMETER BELL 407 407 SW COCKPIT INACCURATE E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 57416 53070 ALTIMETER IS 120 FEET OFF. 1 G 7 1 3U O H2SW 2001041900257 20010419 00257 SW 2001 4 19 HEEA071942 1 20010403 G 6210 206015001107 BLADE BELL 206 206L3 1182108 SW MAIN ROTOR CORRODED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 6251Y 1340 51556 TRAILING SKIN AND SPAR HAS EXCESSIVE CORROSION NEAR THE TIP ON THE LOWER SIDE. 1 G 7 1 3U H2SW 2001041900258 20010419 00258 SW 2001 4 19 HEEA071943 1 20010403 G 2435 23081018 STARTER GEN BELL 206 206L3 1182108 SW ENGINE FAILED E HEEA K NONE B SMOKE/FUMES/ODORS/SPARKS IN INSP/MAINT 1 SW 03 4835 51131 SMOKE AND SPARKS FROM AREA OF TERMINAL BLOCK WHEN MOTORING. REPLACED WITH SERVICEABLE PART. 1 G 7 1 3U H2SW 2001041900259 20010419 00259 SW 2001 4 19 HEEA071944 1 20010403 G 8011 SM20ACD200A21 RELAY BELL 206 206L3 1182108 SW STARTER FAILED E HEEA K NONE L NO TEST IN INSP/MAINT 1 SW 03 8592X 51508 STUCK IN ENERGIZED POSITION. REPLACED WITH SERVICEABLE PART. 1 G 7 1 3U H2SW 2001041900260 20010419 00260 GL 2001 4 19 HEEA071945 2 20010403 G 7532 23005366 BLEED VALVE BELL 206 206L3 1182108 SW ALLSN 250C 250C30 03013 GL ENGINE FAILED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 6610C 2612 51425 HIGH TOT. OVERHAULED AND REPLACED DIAPHRAGMS P/N 6899114. 1 G 7 1 3U 3 U H2SW E1GL 2001041900261 20010419 00261 GL 2001 4 19 HEEA071946 2 20010403 G 7532 23005366 BLEED VALVE BELL 206 206L3 1182108 SW ALLSN 250C 250C30 03013 GL ENGINE FAILED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 49EA 2131 51507 ENGINE RUNS HOT. OVERHAULED AND REPLACED DIAPHRAGMS P/N 6899114. 1 G 7 1 3U 3 U H2SW E1GL 2001041900262 20010419 00262 2001 4 19 HEEA071947 4 20010403 G 3416 1003511326 ALTIMETER BELL 212 212 1181420 SW COCKPIT MALFUNCTIONED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 5009N 30936 ALTIMETER WILL NOT ZERO OUT. 1 G 7 1 4U H4SW 2001041900263 20010419 00263 2001 4 19 HEEA071948 4 20010403 G 3416 212070238003 INDICATOR BELL 412 412 1182202 SW COCKPIT DAMAGED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 2149S 36002 ALTIMETER ADJUSTMENT KNOB DOES NOT TURN. 1 G 7 2 4U H4SW 2001041900264 20010419 00264 2001 4 19 HEEA071949 4 20010403 G 3416 212070238007 INDICATOR BELL 412 412 1182202 SW COCKPIT MALFUNCTIONED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 142PH 33150 WHEN BARO KNOB ON ALTIMETER IS TURNED, NEEDLE MOVES INTERMITTENTLY. 1 G 7 2 4U H4SW 2001041900265 20010419 00265 SW 2001 4 19 HEEA071950 1 20010403 G 2432 30126001 BATTERY BELL 412 412 1182202 SW DC SYSTEM DISCHARGED E HEEA K NONE L NO TEST IN INSP/MAINT 1 SW 03 3893L 33006 BATTERY WEAK. REPLACED WITH SERVICEABLE BATTERY. 1 G 7 2 4U H4SW 2001042000086 20010420 00086 SW 2001 4 20 HEEA071951 1 20010403 G 2432 30703001 BATTERY BELL 412 412 1182202 SW DC SYSTEM DISCHARGED E HEEA K NONE H ELECT. POWER LOSS-50 PC IN INSP/MAINT 1 SW 03 107X 33113 LOST ALL POWER AND WOULD NOT CHARGE. REPLACED WITH SERVICEABLE BATTERY. 1 G 7 2 4U H4SW 2001041900266 20010419 00266 SW 2001 4 19 HEEA071952 1 20010403 G 2822 2C271 CARTRIDGE BELL 206 206L1 1182107 SW BOOST PUMP INOPERATIVE E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 3178K 45765 BOOST PUMP CARTRIDGE INOPERATIVE. 1 G 7 1 3U H2SW 2001041900267 20010419 00267 SW 2001 4 19 HEEA071953 1 20010403 G 2822 2C271 CARTRIDGE BELL 206 206L1 1182107 SW BOOST PUMP FAILED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 3905B 45598 LEFT HAND FUEL BOOST PUMP CARTRIDGE FAILED. 1 G 7 1 3U H2SW 2001041900268 20010419 00268 SW 2001 4 19 HEEA071954 1 20010403 G 2822 2C271 CARTRIDGE BELL 206 206L3 1182108 SW BOOST PUMP INOPERATIVE E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 3116P 51530 BOOST PUMP CARTRIDGE INOPERATIVE. 1 G 7 1 3U H2SW 2001041900269 20010419 00269 SW 2001 4 19 HEEA071955 1 20010403 G 2432 32007001 BATTERY BELL 206 206L1 1182107 SW DC SYSTEM DISCHARGED E HEEA K NONE L NO TEST IN INSP/MAINT 1 SW 03 5019F 45244 BATTERY IS TOO WEAK TO REACH PROPER N1 FOR START. REPLACED WITH SERVICEABLE BATTERY. 1 G 7 1 3U H2SW 2001041900270 20010419 00270 SW 2001 4 19 HEEA071956 1 20010403 G 2432 32007001 BATTERY BELL 206 206L3 1182108 SW DC SYSTEM DISCHARGED E HEEA K NONE L NO TEST IN INSP/MAINT 1 SW 03 4835 51131 BATTERY WEAK DURING STARTS. REPLACED WITH SERVICEABLE BATTERY. 1 G 7 1 3U H2SW 2001041900271 20010419 00271 SW 2001 4 19 HEEA071957 1 20010403 G 2432 32007001 BATTERY BELL 206 206L1 1182107 SW DC SYSTEM DISCHARGED E HEEA K NONE L NO TEST IN INSP/MAINT 1 SW 03 3178K 45765 BATTERY DEAD AND WILL NOT HOLD CHARGE. REPLACED WITH SERVICEABLE BATTERY. 1 G 7 1 3U H2SW 2001041900272 20010419 00272 SW 2001 4 19 HEEA071958 1 20010403 G 2432 32007001 BATTERY BELL 206 206L1 1182107 SW DC SYSTEM DISCHARGED E HEEA K NONE L NO TEST IN INSP/MAINT 1 SW 03 5745S 45491 WEAK STARTING CAPACITY. REPLACED WITH SERVICEABLE BATTERY. 1 G 7 1 3U H2SW 2001041900273 20010419 00273 SW 2001 4 19 HEEA071959 1 20010403 G 3300 A413AHDACF1428 POWER SUPPLY BELL 206 206L1 1182107 SW LIGHTING INOPERATIVE E HEEA K NONE L NO TEST IN INSP/MAINT 1 SW 03 45RP 45521 POWER SUPPLY HAS NO POWER OUTPUT. 1 G 7 1 3U H2SW 2001041900274 20010419 00274 SW 2001 4 19 HEEA071960 1 20010403 G 3340 A490A POWER SUPPLY BELL 206 206L3 1182108 SW STROBE INOPERATIVE E HEEA K NONE L NO TEST IN INSP/MAINT 1 SW 03 6160Y 51609 INOPERATIVE - NO FLASH ON STROBE. REPLACED WITH SERVICEABLE PART. 1 G 7 1 3U H2SW 2001041900275 20010419 00275 SW 2001 4 19 HEEA071961 1 20010403 G 3340 A490A POWER SUPPLY BELL 206 206L3 1182108 SW STROBE INOPERATIVE E HEEA K NONE L NO TEST IN INSP/MAINT 1 SW 03 6251X 51552 NO POWER TO LIGHT BULB. REPLACED WITH SERVICEABLE PART. 1 G 7 1 3U H2SW 2001041900276 20010419 00276 SW 2001 4 19 HEEA071962 1 20010403 G 2432 RG222 BATTERY BELL 206 206L1 1182107 SW DC SYSTEM DISCHARGED E HEEA K NONE L NO TEST IN INSP/MAINT 1 SW 03 5014Y 45219 BATTERY TOO WEAK TO START AIRCRAFT. REPLACED WITH SERVICEABLE PART. 1 G 7 1 3U H2SW 2001041900277 20010419 00277 SW 2001 4 19 HEEA071963 1 20010403 G 2432 A1077 RELAY BELL 206 206L3 1182108 SW BATTERY OVERHEATED E HEEA K NONE L NO TEST IN INSP/MAINT 1 SW 03 4180F BATTERY RELAY STARTED SMOKING AFTER GENERATOR WAS PLACED ON LINE. REPLACED WITH SERVICEABLE PART. 1 G 7 1 3U H2SW 2001041900278 20010419 00278 SW 2001 4 19 HEEA071964 1 20010403 G 2430 A1077V CONTACTOR BELL 206 206L4 1182110 SW DC GENERATOR FAILED E HEEA K NONE L NO TEST IN INSP/MAINT 1 SW 03 7074W 52033 CONTACTOR STUCK CLOSED. 1 G 7 1 3U NC H2SW 2001041900279 20010419 00279 SW 2001 4 19 HEEA071965 1 20010403 G 2435 SM20ACD200A21 RELAY BELL 206 206L4 1182110 SW STARTER GEN FAILED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 7074W 52033 WHEN PILOT ENGAGED STARTER DURING ENGINE RINSE THE STARTER WOULD NOT COME OFF LINE UNTIL BATTERY SWITCH WAS TURNED OFF. FOUND STARTER RELAY WAS STUCK CLOSED. SENT TO PRECISION AVIONICS & INSTR. INC. FOR INSPECTION AND REPAIR. 1 G 7 1 3U NC H2SW 2001041900280 20010419 00280 SW 2001 4 19 HEEA071966 1 20010403 G 3260 XA7503DC SQUAT SWITCH BELL 206 206L3 1182108 SW MLG STUCK E HEEA K NONE L NO TEST IN INSP/MAINT 1 SW 03 42EA 51542 STUCK OPEN. SCRAPPED AND REPLACED WITH SERVICEABLE UNIT. 1 G 7 1 3U H2SW 2001041900281 20010419 00281 NE 2001 4 19 HEEA071967 2 20010403 G 7210 3024780 GEARBOX BELL 412 412 1182202 SW PWA PT6T PT6T3B 52045 NE NR 1 ENGINE MAKING METAL E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 2258F 33073 COMBINING GEARBOXMAKING METAL NR 1 SIDE. 1 G 7 2 4U 4 U H4SW E22EA 2001041900282 20010419 00282 SW 2001 4 19 HEEA071968 1 20010405 G 2432 30703001 BATTERY BELL 412 412 1182202 SW DC SYSTEM DISCHARGED E HEEA K NONE L NO TEST IN INSP/MAINT 1 SW 03 2149S 36002 VOLTAGE WAS AT 24 VOLTS AND THEN DROPPED TO 20 WITH ONLY THE BATTERY SWITCHES ON. REPLACED WITH SERVICEABLE BATTERY. 1 G 7 2 4U H4SW 2001041900283 20010419 00283 SW 2001 4 19 HEEA071969 1 20010405 G 6730 C42641100 SERVO VALVE 206076031109 BELL 206 206L3 1182108 SW ACTUATOR LEAKING E HEEA K NONE K FLUID LOSS IN INSP/MAINT 1 SW 03 RH0366 SERVO VALVE IS CAUSING EXCESSIVE INTERNAL LEAKAGE IN NEUTRAL POSITION. SENT TO FORTNER ACCESSORY SERVICE CORP. FOR WARRA NTY REPAIR. 1 G 7 1 3U H2SW 2001041900284 20010419 00284 SW 2001 4 19 HEEA071970 1 20010405 G 2432 RG222 BATTERY BELL 206 206L1 1182107 SW DC SYSTEM DISCHARGED E HEEA K NONE L NO TEST IN INSP/MAINT 1 SW 03 5007Q 45187 UNABLE TO START AIRCRAFT ON FIRST START ATTEMPT AND WAS WEAK ON THE SECOND START ATTEMPT. REPLACED WITH SERVICEABLE BATT ERY. 1 G 7 1 3U H2SW 2001041900285 20010419 00285 SW 2001 4 19 HEEA071971 1 20010405 G 2432 RG214 BATTERY BELL 214 214ST 1182106 SW DC SYSTEM DAMAGED E HEEA K NONE K FLUID LOSS IN INSP/MAINT 1 SW 03 3897N 28106 WEAK. FOUND DEEP GASH ON LOWER BATTERY CASE. 2 G 7 2 4U H10SW 2001041900286 20010419 00286 SW 2001 4 19 HEEA071972 1 20010405 G 2432 RG214 BATTERY BELL 214 214ST 1182106 SW DC SYSTEM DISCHARGED E HEEA K NONE L NO TEST IN INSP/MAINT 1 SW 03 3897N 28106 WILL NOT START AIRCRAFT. REPLACED WITH SERVICEABLE BATTERY. 2 G 7 2 4U H10SW 2001041900287 20010419 00287 SW 2001 4 19 HEEA071973 1 20010405 G 2432 RG214 BATTERY BELL 214 214ST 1182106 SW DC SYSTEM DISCHARGED E HEEA K NONE L NO TEST IN INSP/MAINT 1 SW 03 3897N 28106 WILL NOT GO IN A SERIES, WEAK. REPLACED WITH SERVICEABLE BATTERY. 2 G 7 2 4U H10SW 2001041900288 20010419 00288 2001 4 19 HEEA071974 4 20010405 G 2312 064101902 TRANSCEIVER BELL 206 206L3 1182108 SW COCKPIT FAILED E HEEA K NONE L NO TEST IN INSP/MAINT 1 SW 03 21497 51518 WILL NOT RECEIVE. PERFORMED PRELIMINARY INSPECTION AND TESTED. COULD NOT DUPLICATE PROBLEM. FOUND FREQUENCY SELECTOR I NTERMITTENTLY SWITCHING TO MEMORY PRESETS WHEN ADJUSTING FREQUENCY. CLEANED SW102 SWITCH AND SELECTOR CONTACTS. REPAIR ED. ADJUSTED SQUELCH AND MIC GAIN. BENCH CHECK GOOD. 1 G 7 1 3U H2SW 2001041900289 20010419 00289 2001 4 19 HEEA071975 4 20010405 G 2312 064102300 TRANSCEIVER BELL 412 412 1182202 SW COCKPIT STUCK E HEEA K NONE L NO TEST IN INSP/MAINT 1 SW 03 107X 33113 SQUELCH IS STICKING. PERFORMED PRELIMINARY INSPECTION AND TESTED. COULD NOT DUPLICATE PROBLEM. REMOVED CORROSION FROM UNIT. REPLACED BROKEN L505 COIL. ADJUSTED C/N SQUELCH, FREQUENCY, MIC GAIN AND SIDETONE. BENCH CHECK GOOD. 1 G 7 2 4U H4SW 2001041900290 20010419 00290 2001 4 19 HEEA071976 4 20010405 G 2312 064102300 TRANSCEIVER BELL 412 412 1182202 SW COCKPIT WEAK E HEEA K NONE L NO TEST IN INSP/MAINT 1 SW 03 142PH 33150 TRANSMITS UNREADABLE. PERFORMED PRELIMINARY INSPECTION AND TESTED. FOUND MODULATION VERY WEAK. ADJUSTED MIC GAIN, TRAN SMIT POWER, AND SIDETONE. FOUND MODULATION WOULD BECOME DISTORTED AFTER KEYED UP A FEW TIMES. REPLACED Q109 AND Q110 M ODULATORS. REPAIRED. REMOVED CORROSION FROM CHASSIS. BENCH CHECK GOOD. 1 G 7 2 4U H4SW 2001041900291 20010419 00291 2001 4 19 HEEA071977 4 20010405 G 2312 064102300 TRANSCEIVER BELL 412 412 1182202 SW COCKPIT UNRELIABLE E HEEA K NONE L NO TEST IN INSP/MAINT 1 SW 03 6559Z 36019 TRANSMITS UNREADABLE. PERFORMED PRELIMINARY INSPECTION AND TESTED. ALIGNED TRANSMITTER. REPAIRED PROBLEM. BENCH CHECK GOOD. 1 G 7 2 4U H4SW 2001041900293 20010419 00293 2001 4 19 HEEA071979 4 20010405 G 3451 066106902 DISPLAY BELL 412 412 1182202 SW DME/TACAN UNIT OUT OF TOLERANCE E HEEA K NONE L NO TEST IN INSP/MAINT 1 SW 03 142PH 33150 DME DISPLAY TOO DIM. PERFORMED PRELIMINARY INSPECTION. FOUND PHOTOCELL V901 HAD BROKEN LEG. REPAIRED LEG. REPAIRED UN IT. BENCH CHECK GOOD. 1 G 7 2 4U H4SW 2001041900294 20010419 00294 2001 4 19 HEEA071980 4 20010405 G 3452 066104100 TRANSPONDER BELL 412 412 1182202 SW ATC INOPERATIVE E HEEA K NONE L NO TEST IN INSP/MAINT 1 SW 03 2261D 33076 NO TRANSMIT OR RECEIVE. PERFORMED PRELIMINARY INSPECTION, TESTED UNIT, FOUND WOULD NOT POWER UP. FUSE BAD. ALSO TROUBL ESHOT UNIT DUE TO FUSE SHORTED AND FOUND TRANSISTOR Q101 BAD. INSTALLED FUSE AND TRANSISTOR Q101. TESTED UNIT AND FOUN D SHIELD IN POWER SUPPLY SHORTED. ALIGNED UNIT. BENCH CHECK GOOD. 1 G 7 2 4U H4SW 2001041900295 20010419 00295 2001 4 19 HEEA071981 4 20010405 G 3457 13824120234 GPS BELL 206 206L3 1182108 SW COCKPIT MALFUNCTIONED E HEEA K NONE L NO TEST IN INSP/MAINT 1 SW 03 6251Y 51556 CONSTANTLY CYCLES. PERFORMED PRELIMINARY INSPECTION. FOUND WPT BUTTON CYCLES THROUGH SEVERAL PAGES WHEN PRESSED. ALSO FOUND MSG, APT/VOR AND NAV BUTTONS INTERMITTENT. SELECTOR SWITCH ALSO INTERMITTENT. REPLACED 4 EACH SWITCHES FOR BUTTO NS AND SELECTOR SWITCH. REPAIRED PROBLEM. REPLACED WORN KEY CAPS. BENCH CHECK GOOD. 1 G 7 1 3U H2SW 2001041900296 20010419 00296 2001 4 19 HEEA071982 4 20010405 G 3421 1113034 INDICATOR BELL 412 412 1182202 SW COCKPIT INOPERATIVE E HEEA K NONE L NO TEST IN INSP/MAINT 1 SW 03 3893L 33006 TURN NEEDLE ON ATTITUDE INDICATOR INOPERATIVE. 1 G 7 2 4U H4SW 2001041900297 20010419 00297 SW 2001 4 19 HEEA071983 1 20010405 G 2844 124044 INDICATOR BELL 412 412 1182202 SW COCKPIT INOPERATIVE E HEEA K NONE L NO TEST IN INSP/MAINT 1 SW 03 FUEL PRESSURE INDICATOR NEEDLE STAYS ON ZERO. 1 G 7 2 4U H4SW 2001041900298 20010419 00298 SW 2001 4 19 HEEA071984 1 20010405 G 2844 124044 INDICATOR BELL 412 412 1182202 SW COCKPIT FLUCTUATES E HEEA K NONE L NO TEST IN INSP/MAINT 1 SW 03 3893L 33006 FUEL PRESSURE INDICATOR FLUCTUATES 8 TO 10 PSI. 1 G 7 2 4U H4SW 2001041900299 20010419 00299 SW 2001 4 19 HEEA071985 1 20010405 G 2800 20038000001 TRANSMITTER BELL 412 412 1182202 SW FUEL QUANTITY MALFUNCTIONED E HEEA K NONE L NO TEST IN INSP/MAINT 1 SW 03 142PH 33150 FUEL LOW LIGHT COMES ON AFTER REFUELING. REPLACED WITH SERVICEABLE UNIT. 1 G 7 2 4U H4SW 2001041900300 20010419 00300 SW 2001 4 19 HEEA071986 1 20010405 G 3040 204070907102 MOTOR BELL 412 412 1182202 SW WINDSHIELD WIPER LOOSE E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 142PH 33150 MOTOR IS LOOSE ON COVERTER. 1 G 7 2 4U H4SW 2001041900301 20010419 00301 SW 2001 4 19 HEEA071987 1 20010405 G 7810 212061202010 EXHAUST STACK BELL 412 412 1182202 SW ENGINE CRACKED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 108X 33115 EXHAUST STACK IS CRACKED AT SEAMS OF DUCT HALVES. THE CRACKED AREA EXCEEDS THE LIMITS. 1 G 7 2 4U H4SW 2001041900302 20010419 00302 SW 2001 4 19 HEEA071988 1 20010405 G 2910 212076006007 VALVE BELL 412 412 1182202 SW NR 2 HYD SYSTEM FAILED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 142PH 33150 NR 2 HYDRAULIC SYSTEM VALVE WILL NOT SHUT OFF. 1 G 7 2 4U H4SW 2001041900303 20010419 00303 SW 2001 4 19 HEEA071989 1 20010405 G 2820 212076015001 VALVE BELL 412 412 1182202 SW FUEL SYSTEM LEAKING E HEEA K NONE K FLUID LOSS IN INSP/MAINT 1 SW 03 2149S 36002 FUEL VALVE LEAKING THROUGH WEEP HOLE. SENT TO BELL HELICOPTER TEXTRON FOR INSPECTION AND REPAIR. 1 G 7 2 4U H4SW 2001041900304 20010419 00304 2001 4 19 HEEA071990 4 20010405 G 3424 214075244001 GYRO BELL 412 412 1182202 SW TURN RATE MALFUNCTIONED E HEEA K NONE L NO TEST IN INSP/MAINT 1 SW 03 1202T 33112 RATE OF TURN NEEDLE TRAVELS FULL LEFT AND RIGHT IN HOVER. 1 G 7 2 4U H4SW 2001041900305 20010419 00305 SW 2001 4 19 HEEA071991 1 20010405 G 2611 302319 SMOKE DETECTOR BELL 412 412 1182202 SW ENGINE MALFUNCTIONED E HEEA K NONE L NO TEST IN INSP/MAINT 1 SW 03 6559Z 36019 SMOKE DETECTION UNIT WOULD TEST INCONSISTENTLY. 1 G 7 2 4U H4SW 2001041900306 20010419 00306 SW 2001 4 19 HEEA071992 1 20010405 G 7714 39433339002 INDICATOR BELL 412 412 1182202 SW TRIPLE TACH INOPERATIVE E HEEA K NONE L NO TEST IN INSP/MAINT 1 SW 03 3893L 33006 NR 1 NEEDLE ON TRIPLE TACH INOPERATIVE. 1 G 7 2 4U H4SW 2001041900307 20010419 00307 SW 2001 4 19 HEEA071993 1 20010405 G 3213 412030437103 CAP BELL 412 412 1182202 SW CROSSTUBE WORN E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 2149S 36002 RUBBER WORN AND DETERIORATED ON CROSSTUBE. 1 G 7 2 4U H4SW 2001041900308 20010419 00308 SW 2001 4 19 HEEA071994 1 20010405 G 3246 412050015110 SKID BELL 412 412 1182202 SW MLG WORN E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 6559Z 36019 SADDLE FASTENERS MAKING MUD - SHOWING WEAR. 1 G 7 2 4U H4SW 2001041900309 20010419 00309 SW 2001 4 19 HEEA071995 1 20010405 G 2840 473203003 SIGNAL COND UNIT BELL 412 412 1182202 SW FUEL INDICATOR MALFUNCTIONED E HEEA K NONE L NO TEST IN INSP/MAINT 1 SW 03 142PH 33150 LOW FUEL LIGHT COMING ON AFTER REFUELING AIRCRAFT. 1 G 7 2 4U H4SW 2001041900310 20010419 00310 SW 2001 4 19 HEEA071996 1 20010405 G 2840 473203003 SIGNAL COND UNIT BELL 412 412 1182202 SW FUEL INDICATOR MALFUNCTIONED E HEEA K NONE L NO TEST IN INSP/MAINT 1 SW 03 1202T 33112 TRANSFER LIGHT CAME ON AT 1850 LBS. 1 G 7 2 4U H4SW 2001041900311 20010419 00311 SW 2001 4 19 HEEA071997 1 20010405 G 2840 473203003 SIGNAL COND UNIT BELL 412 412 1182202 SW FUEL INDICATOR MALFUNCTIONED E HEEA K NONE L NO TEST IN INSP/MAINT 1 SW 03 1202T 33112 TRANSFER LIGHT CAME ON AT 1850 LBS. 1 G 7 2 4U H4SW 2001041900312 20010419 00312 2001 4 19 HEEA071998 4 20010405 G 2340 AA34300 INTERPHONE BELL 412 412 1182202 SW COCKPIT MALFUNCTIONED E HEEA K NONE L NO TEST IN INSP/MAINT 1 SW 03 107X 33113 TRANSMITS AND RECEIVES POORLY. SENT TO EDMO DIST. FOR WARRANTY REPAIR. 1 G 7 2 4U H4SW 2001041900313 20010419 00313 2001 4 19 HEEA071999 4 20010405 G 2561 PHI10090 LIFE VEST BELL 412 412 1182202 SW CABIN FAILED E HEEA K NONE L NO TEST IN INSP/MAINT 1 SW 03 2148K 36001 LIFE VEST FAILED 3 MONTH INSPECTION. 1 G 7 2 4U H4SW 2001041900314 20010419 00314 2001 4 19 HEEA072000 4 20010405 G 3451 066106901 INDICATOR BELL 412 412 1182202 SW COCKPIT MALFUNCTIONED E HEEA K NONE L NO TEST IN INSP/MAINT 1 SW 03 6559Z 36019 DIGITS FLICKERING. REPLACED DISPLAY AND LENS. COOKED UNIT, INSPECTED AND BENCH CHECK GOOD. 1 G 7 2 4U H4SW 2001041900315 20010419 00315 2001 4 19 HEEA072001 4 20010405 G 3451 066106902 INDICATOR BELL 412 412 1182202 SW COCKPIT MALFUNCTIONED E HEEA K NONE L NO TEST IN INSP/MAINT 1 SW 03 6559Z 36019 SEGMENT VERY DIM IN DAYLIGHT. FOUND PHOTOCELL BAD. INSTALLED NEW PHOTOCELL. ALSO MISSING 2 EACH COVER SCREWS. INSTALL ED 2 SCREWS. BENCH CHECK GOOD. 1 G 7 2 4U H4SW 2001041900316 20010419 00316 2001 4 19 HEEA072002 4 20010405 G 3452 066107100 TRANSPONDER BELL 412 412 1182202 SW ATC FAILED E HEEA K NONE L NO TEST IN INSP/MAINT 1 SW 03 7128R 36007 NO OUTPUT. PERFORMED PRELIMINARY INSPECTION. FOUND MODULATOR WAS LOADING DOWN THE POWER SUPPLY VOLTAGES. REPLACED TWO EACH INSULATORS AND ONE EACH BUSHING FOR TRANSISTORS Q501 AND Q502. CLEANED CORROSION FROM BACKSIDE OF THE TRANSISTORS. REPAIRED. 1 G 7 2 4U H4SW 2001041900317 20010419 00317 2001 4 19 HEEA072003 4 20010405 G 3452 066107100 TRANSPONDER BELL 412 412 1182202 SW ATC INOPERATIVE E HEEA K NONE L NO TEST IN INSP/MAINT 1 SW 03 33008 36004 REPORTED INOPERATIVE. PERFORMED PRELIMINARY INSPECTION. CLEANED EXCESSIVE CORROSION FROM UNIT. FOUND WEAK RECEIVER SEN SE AND WEAK TRANSMIT POWER. REPLACED TRANSMITTER BOARD AND ALIGNED TO SPECS. ALIGNED THE RECEIVER. BENCH CHECK GOOD. 1 G 7 2 4U H4SW 2001041900318 20010419 00318 2001 4 19 HEEA072004 4 20010405 G 3455 066107700 RECEIVER BELL 412 412 1182202 SW ADF SYSTEM MALFUNCTIONED E HEEA K NONE L NO TEST IN INSP/MAINT 1 SW 03 2149S 36002 WILL NOT HOME TO STATIONS. PERFORMED PRELIMINARY INSPECTION. FOUND EXCESSIVE CORROSION IN UNIT AND UNDER F.C. I323 AND CAPACITOR C380. REPLACED I323 AND C380 AND CLEANED CORROSION. ALODYNED CHASIS. BENCH CHECK GOOD. 1 G 7 2 4U H4SW 2001041900319 20010419 00319 2001 4 19 HEEA072005 4 20010405 G 3454 071121627 CONTROL UNIT BELL 412 412 1182202 SW NAVIGATION SYS MALFUNCTIONED E HEEA K NONE L NO TEST IN INSP/MAINT 1 SW 03 142PH 33150 WILL NOT CHANNEL PROPERLY CAUSING VOR NOT TO WORK PROPERLY. PERFORMED PRELIMINARY INSPECTION. FOUND UNIT WILL NOT DISPL AY NAV FREQUENCY ON KTS-143. REPLACED IC I201 AND PHOTOCELL LENS. REPAIRED. BENCH CHECK GOOD. 1 G 7 2 4U H4SW 2001041900320 20010419 00320 SW 2001 4 19 HEEA072006 1 20010405 G 5210 204031762002 SPRING BELL 412 412 1182202 SW BLOCKS BROKEN E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 142PH 33150 DOOR SPRING BROKEN. REPLACED WITH SERVICEABLE SPRING. 1 G 7 2 4U H4SW 2001041900321 20010419 00321 SW 2001 4 19 HEEA072007 1 20010405 G 6320 212040233001 LINE BELL 412 412 1182202 SW OIL SYSTEM CHAFED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 2261D 33076 TUBE ASSY WAS FOUND CHAFED. REPLACED WITH SERVICEABLE TUBE. 1 G 7 2 4U H4SW 2001041900322 20010419 00322 SW 2001 4 19 HEEA072008 1 20010405 G 6320 212040233001 LINE BELL 412 412 1182202 SW OIL SYSTEM CHAFED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 3893L 33006 TUBE ASSY WAS FOUND CHAFED. REPLACED WITH SERVICEABLE TUBE. 1 G 7 2 4U H4SW 2001041900323 20010419 00323 SW 2001 4 19 HEEA072009 1 20010405 G 6320 212040234001 LINE BELL 412 412 1182202 SW OIL SYSTEM CHAFED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 2149S 36002 TUBE ASSY WAS FOUND CHAFED. REPLACED WITH SERVICEABLE TUBE. 1 G 7 2 4U H4SW 2001041900324 20010419 00324 SW 2001 4 19 HEEA072010 1 20010405 G 6320 212040234001 LINE BELL 412 412 1182202 SW OIL SYSTEM CHAFED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 2261D 33076 TUBE ASSY WAS FOUND CHAFED. REPLACED WITH SERVICEABLE TUBE. 1 G 7 2 4U H4SW 2001041900325 20010419 00325 SW 2001 4 19 HEEA072011 1 20010405 G 6320 212040234001 LINE BELL 412 412 1182202 SW OIL SYSTEM CHAFED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 3893L 33006 TUBE ASSY WAS FOUND CHAFED. REPLACED WITH SERVICEABLE TUBE. 1 G 7 2 4U H4SW 2001041900326 20010419 00326 SW 2001 4 19 HEEA072012 1 20010405 G 2911 212076007003 ACCUMULATOR BELL 412 412 1182202 SW HYD SYSTEM LEAKING E HEEA K NONE K FLUID LOSS IN INSP/MAINT 1 SW 03 2149S 36002 ACCUMULATOR LEAKS FROM WEEP HOLE. REPLACED WITH SERVICEABLE ACCUMULATOR. 1 G 7 2 4U H4SW 2001041900327 20010419 00327 SW 2001 4 19 HEEA072013 1 20010405 G 2910 212076302001 LINE BELL 412 412 1182202 SW HYD SYSTEM CHAFED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 2261D 33076 CHAFED BEYOND LIMITS. REPLACED WITH SERVICEABLE TUBE. 1 G 7 2 4U H4SW 2001041900328 20010419 00328 SW 2001 4 19 HEEA072014 1 20010405 G 2910 212076311001 LINE BELL 412 412 1182202 SW HYD SYSTEM CHAFED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 2261D 33076 CHAFED BEYOND LIMITS. REPLACED WITH SERVICEABLE TUBE. 1 G 7 2 4U H4SW 2001041900329 20010419 00329 SW 2001 4 19 HEEA072015 1 20010405 G 2560 214070966107 SEAT BELT BELL 412 412 1182202 SW COCKPIT TORN E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 1202T 33112 SEAT BELT TORN. REPLACED WITH SERVICEABLE BELT. 1 G 7 2 4U H4SW 2001041900330 20010419 00330 SW 2001 4 19 HEEA072016 1 20010405 G 6710 BEARING BELL 412 412 1182202 SW BELLCRANK WORN E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 142PH 33150 BEARINGS FOUND WORN DURING DAILY CHECK. REPLACED WITH SERVICEABLE ASSY. 1 G 7 2 4U H4SW 2001041900331 20010419 00331 SW 2001 4 19 HEEA072017 1 20010405 G 6710 412010182101 BEARING BELL 412 412 1182202 SW M/R PITCH LINK WORN E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 142PH 33150 BEARING FOUND WORN. SCRAPPED AND REPLACED WITH SERVICEABLE ASSY. 1 G 7 2 4U H4SW 2001041900332 20010419 00332 SW 2001 4 19 HEEA072018 1 20010405 G 6710 412010182101 BEARING BELL 412 412 1182202 SW M/R PITCH LINK WORN E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 1202T 33112 BEARING FOUND WORN. SCRAPPED AND REPLACED WITH SERVICEABLE ASSY. 1 G 7 2 4U H4SW 2001041900333 20010419 00333 SW 2001 4 19 HEEA072019 1 20010405 G 6230 412010405109 DRIVE LINK BELL 412 412 1182202 SW SWASHPLATE WORN E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 2261D 33076 WORN BEARING. REPLACED WITH SERVICEABLE ASSY. 1 G 7 2 4U H4SW 2001041900334 20010419 00334 SW 2001 4 19 HEEA072020 1 20010405 G 6720 412010406115 LINK BELL 412 412 1182202 SW ROD END WORN E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 142PH 33150 WORN BEARING. REPLACED WITH SERVICEABLE ASSY. 1 G 7 2 4U H4SW 2001041900335 20010419 00335 SW 2001 4 19 HEEA072021 1 20010405 G 6720 412010406115 LINK BELL 412 412 1182202 SW ROD END WORN E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 142PH 33150 WORN BEARING. REPLACED WITH SERVICEABLE ASSY. 1 G 7 2 4U H4SW 2001041900336 20010419 00336 2001 4 19 HEEA072022 4 20010405 G 2350 A3016W AUDIO PANEL BELL 412 412 1182202 SW COCKPIT MALFUNCTIONED E HEEA K NONE L NO TEST IN INSP/MAINT 1 SW 03 2149S 36002 TRANSMITS WITH MIC SELECTOR IN FM1 POSITION AND RECEIVES FM1 ON THE FM2 POSITION. PERFORMED PRELIMINARY INSPECTION AND F OUND UNIT TRANSMIT OUTPUT DISTORTED. REPLACED CAPACITOR C30 AND ALSO LIGHT PANEL WORN. REPLACED LIGHT PANEL. BENCH CH ECK GOOD. 1 G 7 2 4U H4SW 2001041900337 20010419 00337 SW 2001 4 19 HEEA072023 1 20010405 G 2840 APTE1391500SG TRANSDUCER BELL 412 412 1182202 SW FUEL SYSTEM MALFUNCTIONED E HEEA K NONE L NO TEST IN INSP/MAINT 1 SW 03 142PH 33150 CAUSING INDICATOR TO READ 5 PSI WHEN AIRCRAFT IS SHUTDOWN. REPLACED WITH SERVICEABLE TRANSMITTER. 1 G 7 2 4U H4SW 2001041900338 20010419 00338 SW 2001 4 19 HEEA072024 1 20010405 G 3340 G62504 SEARCH LIGHT BELL 412 412 1182202 SW EXTERIOR MALFUNCTIONED E HEEA K NONE L NO TEST IN INSP/MAINT 1 SW 03 142PH 33150 RETRACTION MOTOR WILL NOT SHUT OFF WHEN FULLY RETRACTED. REPLACED WITH SERVICEABLE LIGHT. 1 G 7 2 4U H4SW 2001041900339 20010419 00339 SW 2001 4 19 HEEA072025 1 20010405 G 6220 412010100193FM HUB BELL 412 412 1182202 SW MAIN ROTOR VIBRATION E HEEA K NONE E VIBRATION/BUFFET IN INSP/MAINT 1 SW 03 6559Z 36019 BLUE SPINDLE CAUSING VIBRATION. REPLACED WITH SERVICEABLE ASSY. 1 G 7 2 4U H4SW 2001041900340 20010419 00340 SW 2001 4 19 HEEA072026 1 20010405 G 6710 412010182101 BEARING BELL 412 412 1182202 SW M/R PITCH LINK WORN E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 2261D 33076 WORN BEARING. SCRAPPED AND REPLACED WITH SERVICEABLE ASSY. 1 G 7 2 4U H4SW 2001041900341 20010419 00341 SW 2001 4 19 HEEA072027 1 20010405 G 6710 412010182101 BEARING BELL 412 412 1182202 SW M/R PITCH LINK WORN E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 2261D 33076 WORN BEARING. SCRAPPED AND REPLACED WITH SERVICEABLE ASSY. 1 G 7 2 4U H4SW 2001041900342 20010419 00342 SW 2001 4 19 HEEA072028 1 20010405 G 6710 412010182101 BEARING BELL 412 412 1182202 SW M/R PITCH LINK WORN E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 3893N 33010 WORN BEARING. SCRAPPED AND REPLACED WITH SERVICEABLE ASSY. 1 G 7 2 4U H4SW 2001041900343 20010419 00343 SW 2001 4 19 HEEA072029 1 20010405 G 6710 412010182101 BEARING BELL 412 412 1182202 SW M/R PITCH LINK WORN E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 3893N 33010 WORN BEARING. SCRAPPED AND REPLACED WITH SERVICEABLE ASSY. 1 G 7 2 4U H4SW 2001041900344 20010419 00344 SW 2001 4 19 HEEA072030 1 20010405 G 6710 412010182101 BEARING BELL 412 412 1182202 SW M/R PITCH LINK WORN E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 3893N 33010 WORN BEARING. SCRAPPED AND REPLACED WITH SERVICEABLE ASSY. 1 G 7 2 4U H4SW 2001041900345 20010419 00345 SW 2001 4 19 HEEA072031 1 20010405 G 6710 412010182101 BEARING BELL 412 412 1182202 SW M/R PITCH LINK WORN E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 3893N 33010 WORN BEARING. SCRAPPED AND REPLACED WITH SERVICEABLE ASSY. 1 G 7 2 4U H4SW 2001041900346 20010419 00346 SW 2001 4 19 HEEA072032 1 20010405 G 6710 412010182101 BEARING BELL 412 412 1182202 SW M/R PITCH LINK WORN E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 3893L 33006 WORN BEARING. SCRAPPED AND REPLACED WITH SERVICEABLE ASSY. 1 G 7 2 4U H4SW 2001041900347 20010419 00347 SW 2001 4 19 HEEA072033 1 20010405 G 6710 412010182101 BEARING BELL 412 412 1182202 SW M/R PITCH LINK WORN E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 3893L 33006 WORN BEARING. SCRAPPED AND REPLACED WITH SERVICEABLE ASSY. 1 G 7 2 4U H4SW 2001041900348 20010419 00348 SW 2001 4 19 HEEA072034 1 20010405 G 6710 412010182101 BEARING BELL 412 412 1182202 SW M/R PITCH LINK WORN E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 3893L 33006 WORN BEARING. SCRAPPED AND REPLACED WITH SERVICEABLE ASSY. 1 G 7 2 4U H4SW 2001041900349 20010419 00349 SW 2001 4 19 HEEA072035 1 20010405 G 6710 412010182101 BEARING BELL 412 412 1182202 SW M/R PITCH LINK WORN E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 3893L 33006 WORN BEARING. SCRAPPED AND REPLACED WITH SERVICEABLE ASSY. 1 G 7 2 4U H4SW 2001041900350 20010419 00350 SW 2001 4 19 HEEA072036 1 20010405 G 6230 412010405109 DRIVE LINK BELL 412 412 1182202 SW SWASHPLATE WORN E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 6559Z 36019 WORN BEARING. REPLACED WITH SERVICEABLE ASSY. 1 G 7 2 4U H4SW 2001041900351 20010419 00351 SW 2001 4 19 HEEA072037 1 20010405 G 6230 412010405109 DRIVE LINK BELL 412 412 1182202 SW SWASHPLATE WORN E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 6559Z 36019 WORN BEARING. REPLACED WITH SERVICEABLE ASSY. 1 G 7 2 4U H4SW 2001041900352 20010419 00352 SW 2001 4 19 HEEA072038 1 20010405 G 6720 412010406115 LINK BELL 412 412 1182202 SW SWASHPLATE WORN E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 2149S 36002 MAIN ROTOR VIBRATION. REPLACED WITH SERVICEABLE ASSY. 1 G 7 2 4U H4SW 2001041900353 20010419 00353 SW 2001 4 19 HEEA072039 1 20010405 G 3212 412050013117 FLOAT BELL 412 412 1182202 SW MLG LEAKING E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 2261D 33076 LEAKING FROM AROUND FORWARD AIR VALVE. SENT TO OFFSHORE HELICOPTER SUPPORT FOR INSPECTION AND REPAIR. 1 G 7 2 4U H4SW 2001041900354 20010419 00354 SW 2001 4 19 HEEA072040 1 20010405 G 6710 412310400101 ROD END BELL 412 412 1182202 SW MAIN ROTOR WORN E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 3893L 33006 WORN. REPLACED WITH SERVICEABLE PART. 1 G 7 2 4U H4SW 2001041900355 20010419 00355 SW 2001 4 19 HEEA072041 1 20010405 G 6710 412310400101 ROD END BELL 412 412 1182202 SW MAIN ROTOR WORN E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 6559Z 36019 WORN. REPLACED WITH SERVICEABLE PART. 1 G 7 2 4U H4SW 2001041900356 20010419 00356 SW 2001 4 19 HEEA072042 1 20010405 G 6710 412310400101 ROD END BELL 412 412 1182202 SW MAIN ROTOR WORN E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 6559Z 36019 WORN. REPLACED WITH SERVICEABLE PART. 1 G 7 2 4U H4SW 2001041900357 20010419 00357 SW 2001 4 19 HEEA072043 1 20010405 G 6710 412310400101 ROD END BELL 412 412 1182202 SW MAIN ROTOR WORN E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 3893L 33006 WORN. REPLACED WITH SERVICEABLE PART. 1 G 7 2 4U H4SW 2001041900358 20010419 00358 SW 2001 4 19 HEEA072044 1 20010405 G 6710 412310400101 ROD END BELL 412 412 1182202 SW MAIN ROTOR WORN E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 2261D 33076 WORN. REPLACED WITH SERVICEABLE PART. 1 G 7 2 4U H4SW 2001041900359 20010419 00359 SW 2001 4 19 HEEA072045 1 20010405 G 6710 412310400101 ROD END BELL 412 412 1182202 SW MAIN ROTOR WORN E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 2261D 33076 WORN. REPLACED WITH SERVICEABLE PART. 1 G 7 2 4U H4SW 2001041900360 20010419 00360 SW 2001 4 19 HEEA072046 1 20010405 G 6710 412310400101 ROD END BELL 412 412 1182202 SW MAIN ROTOR WORN E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 6559Z 36019 WORN. REPLACED WITH SERVICEABLE PART. 1 G 7 2 4U H4SW 2001041900361 20010419 00361 SW 2001 4 19 HEEA072047 1 20010405 G 6710 412310400101 ROD END BELL 412 412 1182202 SW MAIN ROTOR WORN E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 6559Z 36019 WORN. REPLACED WITH SERVICEABLE PART. 1 G 7 2 4U H4SW 2001041900362 20010419 00362 SW 2001 4 19 HEEA072048 1 20010405 G 6710 412310400101 ROD END BELL 412 412 1182202 SW MAIN ROTOR WORN E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 6559Z 36019 WORN. REPLACED WITH SERVICEABLE PART. 1 G 7 2 4U H4SW 2001041900363 20010419 00363 SW 2001 4 19 HEEA072049 1 20010405 G 6710 412310400101 ROD END BELL 412 412 1182202 SW MAIN ROTOR WORN E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 3893L 33006 WORN. REPLACED WITH SERVICEABLE PART. 1 G 7 2 4U H4SW 2001041900364 20010419 00364 SW 2001 4 19 HEEA072050 1 20010405 G 6710 412310400101 ROD END BELL 412 412 1182202 SW MAIN ROTOR WORN E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 6559Z 36019 WORN. REPLACED WITH SERVICEABLE PART. 1 G 7 2 4U H4SW 2001041900365 20010419 00365 SW 2001 4 19 HEEA072051 1 20010405 G 6710 412310400101 ROD END BELL 412 412 1182202 SW MAIN ROTOR WORN E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 6559Z 36019 WORN. REPLACED WITH SERVICEABLE PART. 1 G 7 2 4U H4SW 2001041900366 20010419 00366 SW 2001 4 19 HEEA072052 1 20010405 G 6710 412310400101 ROD END BELL 412 412 1182202 SW MAIN ROTOR WORN E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 3893N 33010 WORN. REPLACED WITH SERVICEABLE PART. 1 G 7 2 4U H4SW 2001041900367 20010419 00367 SW 2001 4 19 HEEA072053 1 20010405 G 6710 412310400101 ROD END BELL 412 412 1182202 SW MAIN ROTOR WORN E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 1202T 33112 WORN. REPLACED WITH SERVICEABLE PART. 1 G 7 2 4U H4SW 2001041900368 20010419 00368 SW 2001 4 19 HEEA072054 1 20010405 G 6710 412310400101 ROD END BELL 412 412 1182202 SW MAIN ROTOR WORN E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 1202T 33112 WORN. REPLACED WITH SERVICEABLE PART. 1 G 7 2 4U H4SW 2001041900369 20010419 00369 SW 2001 4 19 HEEA072055 1 20010405 G 6710 412310400101 ROD END BELL 412 412 1182202 SW MAIN ROTOR WORN E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 1202T 33112 WORN. REPLACED WITH SERVICEABLE PART. 1 G 7 2 4U H4SW 2001041900370 20010419 00370 SW 2001 4 19 HEEA072056 1 20010405 G 6710 412310400101 ROD END BELL 412 412 1182202 SW MAIN ROTOR WORN E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 1202T 33112 WORN. REPLACED WITH SERVICEABLE PART. 1 G 7 2 4U H4SW 2001041900371 20010419 00371 SW 2001 4 19 HEEA072057 1 20010405 G 2560 501819409 SEAT BELT BELL 412 412 1182202 SW COCKPIT WORN E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 3893L 33006 WORN. 1 G 7 2 4U H4SW 2001041900372 20010419 00372 SW 2001 4 19 HEEA072058 1 20010405 G 2560 501836307 SEAT BELT BELL 412 412 1182202 SW COCKPIT FRAYED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 2298Z 33077 FRAYED. REPLACED WITH SERVICEABLE RESTRAINT. 1 G 7 2 4U H4SW 2001041900373 20010419 00373 2001 4 19 HEEA072059 4 20010405 G 2370 9806020023 CVR BELL 412 412 1182202 SW COCKPIT WILL NOT TEST E HEEA K NONE L NO TEST IN INSP/MAINT 1 SW 03 30YM 36032 FAILS TO ILLUMINATE TEST LIGHT. 1 G 7 2 4U H4SW 2001041900374 20010419 00374 2001 4 19 HEEA072060 4 20010405 G 2370 9806020023 CVR BELL 412 412 1182202 SW COCKPIT WILL NOT TEST E HEEA K NONE L NO TEST IN INSP/MAINT 1 SW 03 5759N 33002 WILL NOT LIGHT UP TEST LIGHT ON PUSH BUTTON TEST. FOUND UNIT FAILED FSK TEST AND ROTOR SPEED TEST. 1 G 7 2 4U H4SW 2001042000186 20010420 00186 SW 2001 4 20 HEEA072061 1 20010405 G 3212 D24911117 FLOAT BELL 412 412 1182202 SW MLG LEAKING E HEEA K NONE L NO TEST IN INSP/MAINT 1 SW 03 7128R 36007 LEAKING, FAILED 6 MONTH INSPECTION. 1 G 7 2 4U H4SW 2001042000187 20010420 00187 SW 2001 4 20 HEEA072062 1 20010405 G 3212 D24921119 FLOAT BELL 412 412 1182202 SW MLG FAILED E HEEA K NONE L NO TEST IN INSP/MAINT 1 SW 03 2014K 33020 AFTER ELECTRICAL INFLATION OF FLOAT SYSTEM, A LEAK AT THE REAR POP OFF VALVE WAS NOTED. VALVE THREADS WERE STRIPPED. V ALVE WOULD ONLY ROTATE. 1 G 7 2 4U H4SW 2001042000188 20010420 00188 SW 2001 4 20 HEEA072063 1 20010405 G 3212 D24921119 FLOAT BELL 412 412 1182202 SW MLG FAILED E HEEA K NONE L NO TEST IN INSP/MAINT 1 SW 03 7128R 36007 LEAKING, FAILED 6 MONTH INSPECTION. SENT TO OFFSHORE HELICOPTER SUPPORT FOR INSPECTION AND REPAIR. 1 G 7 2 4U H4SW 2001042000189 20010420 00189 2001 4 20 HEEA072064 4 20010405 G 2350 M880555002 SWITCH BELL 412 412 1182202 SW COMM SYSTEM STUCK E HEEA K NONE L NO TEST IN INSP/MAINT 1 SW 03 7128R 36007 INTERMITTENT HOT MIKE SWITCH STICKING. REPLACED WITH SERVICEABLE SWITCH. 1 G 7 2 4U H4SW 2001042000190 20010420 00190 SW 2001 4 20 HEEA072065 1 20010405 G 5260 PHI101741 STEP BELL 412 412 1182202 SW LEFT STUCK E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 2148K 36001 LEFT HAND STEP STAYING UP. REPLACED WITH SERVICEABLE UNIT. 1 G 7 2 4U H4SW 2001042000191 20010420 00191 SW 2001 4 20 HEEA072066 1 20010405 G 5260 PHI101741 STEP BELL 412 412 1182202 SW RIGHT STUCK E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 1202T 33112 RIGHT HAND STEP WILL NOT GO DOWN. REPLACED WITH SERVICEABLE UNIT. 1 G 7 2 4U H4SW 2001042000192 20010420 00192 SW 2001 4 20 HEEA072067 1 20010405 G 5260 PHI101741 STEP BELL 412 412 1182202 SW RIGHT STUCK E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 7128R 36007 RIGHT HAND STEP WILL NOT EXTEND. REPLACED WITH SERVICEABLE UNIT. 1 G 7 2 4U H4SW 2001042000193 20010420 00193 SW 2001 4 20 HEEA072068 1 20010405 G 5260 PHI101741 STEP BELL 412 412 1182202 SW LEFT STUCK E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 6559Z 36019 WOULD NOT LET LT STEP GO DOWN. REPLACED WITH SERVICEABLE UNIT. 1 G 7 2 4U H4SW 2001042000194 20010420 00194 2001 4 20 HEEA072069 4 20010405 G 2312 VFS10902 ANTENNA BELL 412 412 1182202 SW VHF DAMAGED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 3893N 33010 ANTENNA SPLIT. SCRAPPED AND REPLACED WITH SERVICEABLE PART. 1 G 7 2 4U H4SW 2001042000195 20010420 00195 SW 2001 4 20 HEEA072070 1 20010405 G 3212 412050017133 COVER BELL 412 412 1182202 SW FLOAT BAG TORN E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 3893L 33006 COVER TORN. SENT TO OFFSHORE HELICOPTER SUPPORT FOR INSPECTION AND REPAIR. 1 G 7 2 4U H4SW 2001042000196 20010420 00196 SW 2001 4 20 HEEA072071 1 20010405 G 2560 412070843105 SHOULDER BELT BELL 412 412 1182202 SW COCKPIT FRAYED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 7128R 36007 SHOULDER HARNESS WEB FRAYED. REPLACED WITH SERVICEABLE RESTRAINT. 1 G 7 2 4U H4SW 2001042000197 20010420 00197 SW 2001 4 20 HEEA072072 1 20010405 G 6710 412310400101 ROD END BELL 412 412 1182202 SW MAIN ROTOR WORN E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 2148K 36001 BEARING WORN. SCRAPPED AND REPLACED WITH SERVICEABLE UNIT. 1 G 7 2 4U H4SW 2001042000198 20010420 00198 SW 2001 4 20 HEEA072073 1 20010405 G 6710 412310400101 ROD END BELL 412 412 1182202 SW MAIN ROTOR WORN E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 2148K 36001 BEARING WORN. SCRAPPED AND REPLACED WITH SERVICEABLE UNIT. 1 G 7 2 4U H4SW 2001042000199 20010420 00199 SW 2001 4 20 HEEA072074 1 20010405 G 6710 412310400101 ROD END BELL 412 412 1182202 SW MAIN ROTOR WORN E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 142PH 33150 BEARING WORN. SCRAPPED AND REPLACED WITH SERVICEABLE UNIT. 1 G 7 2 4U H4SW 2001042000200 20010420 00200 SW 2001 4 20 HEEA072075 1 20010405 G 6710 412310400101 ROD END BELL 412 412 1182202 SW MAIN ROTOR WORN E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 2148K 36001 BEARING WORN. SCRAPPED AND REPLACED WITH SERVICEABLE UNIT. 1 G 7 2 4U H4SW 2001042000201 20010420 00201 SW 2001 4 20 HEEA072076 1 20010405 G 6710 412310400101 ROD END BELL 412 412 1182202 SW MAIN ROTOR WORN E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 2148K 36001 BEARING WORN. SCRAPPED AND REPLACED WITH SERVICEABLE UNIT. 1 G 7 2 4U H4SW 2001042000203 20010420 00203 SW 2001 4 20 HEEA072077 1 20010405 G 6710 412310400101 ROD END BELL 412 412 1182202 SW MAIN ROTOR WORN E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 1202T 33112 BEARING WORN. SCRAPPED AND REPLACED WITH SERVICEABLE UNIT. 1 G 7 2 4U H4SW 2001042000204 20010420 00204 SW 2001 4 20 HEEA072078 1 20010405 G 6710 412310400101 ROD END BELL 412 412 1182202 SW MAIN ROTOR WORN E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 1202T 33112 BEARING WORN. SCRAPPED AND REPLACED WITH SERVICEABLE UNIT. 1 G 7 2 4U H4SW 2001042000205 20010420 00205 2001 4 20 HEEA072079 4 20010405 G 3452 066106200 TRANSPONDER BELL 407 407 SW ATC MALFUNCTIONED E HEEA K NONE L NO TEST IN INSP/MAINT 1 SW 03 409PH 53059 LOW POWER AND WIDE PULSE WIDTH. PERFORMED PRELIMINARY INSPECTION AND FOUND F401 FUSE BLOWN AND Q415 BAD. REPLACED F401 FUSE AND Q415 TRANSISTOR. FOUND UNIT WILL NOT RECEIVE. REPLACED V101 CAVITY TUBE AND V301 PHOTOCELL. REPAIRED. BENCH CHECK GOOD. 1 G 7 1 3U O H2SW 2001042000206 20010420 00206 SW 2001 4 20 HEEA072080 1 20010405 G 3212 206050248121 FLOAT BELL 206 206L4 1182110 SW MLG FAILED E HEEA K NONE L NO TEST IN INSP/MAINT 1 SW 03 7074W 52033 L/H AFT FLOAT BAG FAILED 6 MONTH INSPECTION. SENT TO OFFSHORE HELICOPTER SUPPORT FOR WARRANTY REPAIR. 1 G 7 1 3U NC H2SW 2001042000207 20010420 00207 SW 2001 4 20 HEEA072081 1 20010405 G 6730 206076062107 ACTUATOR BELL 206 206L3 1182108 SW ROTOR SERVO SYS LEAKING E HEEA K NONE K FLUID LOSS IN INSP/MAINT 1 SW 03 8594X 51531 LEAKING. REPLACED WITH SERVICEABLE FLOAT. 1 G 7 1 3U H2SW 2001042000209 20010420 00209 2001 4 20 HEEA072082 4 20010405 G 2561 3500145NL72 LIFE VEST BELL 206 206L3 1182108 SW COCKPIT FAILED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 21497 51518 VEST WILL NOT HOLD AIR. SENT TO J.D. MANUFACTURING FOR INSPECTION AND REPAIR. 1 G 7 1 3U H2SW 2001042000210 20010420 00210 SW 2001 4 20 HEEA072083 1 20010405 G 6710 C4264215 SERVO VALVE 206076062003 BELL 206 206L3 1182108 SW MAIN ROTOR STUCK E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 4282Z RH4128A 51499 SLIDE AND SLEEVE ASSY (SERVO VALVE) HAS STICKY MOVEMENT. REPLACED WITH SERVICEABLE ASSY. 1 G 7 1 3U H2SW 2001042000211 20010420 00211 SW 2001 4 20 HEEA072084 1 20010405 G 7120 23069751 MOUNT BELL 407 407 SW ENGINE LOOSE E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 612PH 53199 ENGINE REAR MOUNT BEARING HAS PLAY. REPLACED WITH SERVICEABLE ASSY. 1 G 7 1 3U O H2SW 2001042000212 20010420 00212 SW 2001 4 20 HEEA072085 1 20010405 G 7120 206062102013 MOUNT BELL 206 206B3 1181506 SW ENGINE DAMAGED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 107PH 2789 DAMAGED BEYOND LIMITS. REPLACED WITH SERVICEABLE ASSY. 1 G 7 1 3U H2SW 2001042000213 20010420 00213 SW 2001 4 20 HEEA072086 1 20010405 G 7120 206062103017 MOUNT BELL 206 206B3 1181506 SW ENGINE DAMAGED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 107PH 2789 DAMAGED BEYOND LIMITS. REPLACED WITH SERVICEABLE ASSY. 1 G 7 1 3U H2SW 2001042000214 20010420 00214 SW 2001 4 20 HEEA072087 1 20010405 G 7120 206062101101 MOUNT BELL 206 206B3 1181506 SW ENGINE DAMAGED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 107PH 2789 DAMAGED BEYOND LIMITS. REPLACED WITH SERVICEABLE ASSY. 1 G 7 1 3U H2SW 2001042000215 20010420 00215 SW 2001 4 20 HEEA072088 1 20010405 G 7120 206062101102 MOUNT BELL 206 206B3 1181506 SW ENGINE DAMAGED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 107PH 2789 DAMAGED BEYOND LIMITS. REPLACED WITH SERVICEABLE ASSY. 1 G 7 1 3U H2SW 2001042000216 20010420 00216 SW 2001 4 20 HEEA072089 1 20010405 G 7120 206062103018 MOUNT BELL 206 206B3 1181506 SW ENGINE DAMAGED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 107PH 2789 DAMAGED BEYOND LIMITS. REPLACED WITH SERVICEABLE ASSY. 1 G 7 1 3U H2SW 2001042000217 20010420 00217 SW 2001 4 20 HEEA072090 1 20010405 G 7120 206064107101 MOUNT BELL 206 206L1 1182107 SW ENGINE WORN E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 2124Z 45646 WORN BEARING. REPLACED WITH SERVICEABLE ASSY. 1 G 7 1 3U H2SW 2001042000218 20010420 00218 2001 4 20 HEEA072091 4 20010405 G 2312 064101902 TRANSCEIVER BELL 206 206L3 1182108 SW VHF SYSTEM MALFUNCTIONED E HEEA K NONE L NO TEST IN INSP/MAINT 1 SW 03 4835 51131 UNABLE TO TUNE AND TRANSMIT. PERFORMED PRELIMINARY INSPECTION AND TESTED. COULD NOT DUPLICATE PROBLEM. ADJUSTED C/N SQ UELCH, CARRIER SQUELCH, MIC GAIN AND SIDETONE. BENCH CHECK GOOD. 1 G 7 1 3U H2SW 2001042000219 20010420 00219 2001 4 20 HEEA072092 4 20010405 G 2312 064101902 TRANSCEIVER BELL 206 206L3 1182108 SW VHF SYSTEM MALFUNCTIONED E HEEA K NONE L NO TEST IN INSP/MAINT 1 SW 03 31077 51520 THE LARGE OUTER CHANNEL CHANGE KNOB INTERMITTENT. PERFORMED PRELIMINARY INSPECTION AND TESTED. REPLACED DISPLAY BOARD A SSY. REPAIRED PROBLEM. ADJUSTED C/N SQUELCH AND BENCH CHECK GOOD. 1 G 7 1 3U H2SW 2001042000220 20010420 00220 2001 4 20 HEEA072093 4 20010405 G 2312 064101905 TRANSCEIVER BELL 206 206L1 1182107 SW VHF SYSTEM MALFUNCTIONED E HEEA K NONE L NO TEST IN INSP/MAINT 1 SW 03 5007Y 45192 WILL NOT CHANGE FROM STANDBY TO IN USE AND VERY HARD TO CHANGE FREQUENCY FOR FIRST 20 TO 30 MINUTES OF FLIGHT. PERFORMED PRELIMINARY INSPECTION AND TESTED. ADJUSTED MIC GAIN AND SIDETONE. BENCH CHECK GOOD. COULD NOT DUPLICATE PROBLEM. 1 G 7 1 3U H2SW 2001042000221 20010420 00221 2001 4 20 HEEA072094 4 20010405 G 2312 064105430 TRANSCEIVER BELL 206 206L4 1182110 SW VHF SYSTEM MALFUNCTIONED E HEEA K NONE L NO TEST IN INSP/MAINT 1 SW 03 7077F 52038 UNABLE TO CONTROL VOLUME. PERFORMED PRELIMINARY INSPECTION AND TESTED. REPLACED BAD S901. POTENTIOMETER SWITCH VOLUME REPAIRED. BENCH CHECK GOOD. 1 G 7 1 3U NC H2SW 2001042000222 20010420 00222 SW 2001 4 20 HEEA072095 1 20010405 G 7810 SUPPORT BRACKET BELL 412 412 1182202 SW EXHAUST STACK CRACKED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 108X 33115 SUPPORT BRACKET AND SHROUD CRACKED. REPLACED WITH SERVICEABLE PART. 1 G 7 2 4U H4SW 2001042000223 20010420 00223 SW 2001 4 20 HEEA072096 1 20010405 G 7810 212061202007 EXHAUST STACK BELL 412 412 1182202 SW ENGINE CRACKED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 22608 33075 EXHAUST STACK IS CRACKED AT SEAMS OF DUCT HALVES. REPLACED WITH SERVICEABLE PART. 1 G 7 2 4U H4SW 2001042000224 20010420 00224 SW 2001 4 20 HEEA072097 1 20010405 G 7810 212061210001 DUCT BELL 412 412 1182202 SW EXHAUST STACK CRACKED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 3893L 33006 CRACKED. REPLACED WITH SERVICEABLE PART. 1 G 7 2 4U H4SW 2001042000225 20010420 00225 2001 4 20 HEEA072098 4 20010405 G 2312 064101902 TRANSCEIVER BELL 206 206L1 1182107 SW VHF SYSTEM MALFUNCTIONED E HEEA K NONE L NO TEST IN INSP/MAINT 1 SW 03 45RP 45521 DISPLAY INOPERATIVE. PERFORMED PRELIMINARY INSPECTION AND TESTED. FOUND DISPLAY A LITTLE WEAK. REPLACED DS501 DISPLAY. REPAIRED. ADJUSTED MIC GAIN AND SIDETONE. BENCH CHECK GOOD. 1 G 7 1 3U H2SW 2001042000226 20010420 00226 2001 4 20 HEEA072099 4 20010405 G 2312 064101902 TRANSCEIVER BELL 206 206L1 1182107 SW VHF SYSTEM MALFUNCTIONED E HEEA K NONE L NO TEST IN INSP/MAINT 1 SW 03 45RP 45521 DISPLAY FLICKERS AND MEMORY RESETS. PERFORMED PRELIMINARY INSPECTION AND COULD NOT DUPLICATE PROBLEM. FOUND AUDIO LEVEL TO BE VERY LOW. REPLACED R505 VOLUME CONTROL AND CAPACITOR. ADJUSTED C/N SQUELCH, MODULATION AND SIDETONE. BENCH CH ECK GOOD. 1 G 7 1 3U H2SW 2001042000227 20010420 00227 2001 4 20 HEEA072100 4 20010405 G 2312 064101902 TRANSCEIVER BELL 206 206L3 1182108 SW VHF SYSTEM MALFUNCTIONED E HEEA K NONE L NO TEST IN INSP/MAINT 1 SW 03 3116L 51529 DISPLAY TOO DIM AND SEVERAL LED DIGITS INOPERATIVE. PERFORMED PRELIMINARY INSPECTION AND FOUND DISPLAY BAD. REPLACED AN D ADJUSTED C/N SQUELCH, MIC GAIN AND SIDETONE. BENCH CHECK GOOD. 1 G 7 1 3U H2SW 2001042000228 20010420 00228 2001 4 20 HEEA072101 4 20010405 G 2312 064101902 TRANSCEIVER BELL 206 206L3 1182108 SW VHF SYSTEM MALFUNCTIONED E HEEA K NONE L NO TEST IN INSP/MAINT 1 SW 03 21497 51518 DISPLAY IS UNREADABLE ON HIGH HUMIDITY MORNINGS. REMOVED AND REPLACED DISPLAY. ADJUSTED AND ALIGNED CARRIER NOISE SQUEL CH, CARRIER SQUELCH, MODULATION AND SIDETONE. BENCH CHECK GOOD. 1 G 7 1 3U H2SW 2001042000230 20010420 00230 2001 4 20 HEEA072102 4 20010405 G 2312 064101922 TRANSCEIVER BELL 206 206L3 1182108 SW VHF SYSTEM MALFUNCTIONED E HEEA K NONE L NO TEST IN INSP/MAINT 1 SW 03 21497 51518 WILL NOT TRANSMIT OR RECEIVE. PERFORMED PRELIMINARY INSPECTION AND ADJUSTED CARRIER NOISE SQUELCH, CARRIER SQUELCH, AND SIDETONE. BENCH CHECK GOOD. 1 G 7 1 3U H2SW 2001042000231 20010420 00231 2001 4 20 HEEA072103 4 20010405 G 2312 064105430 TRANSCEIVER BELL 206 206B3 1181506 SW VHF SYSTEM MALFUNCTIONED E HEEA K NONE L NO TEST IN INSP/MAINT 1 SW 03 2277A 3630 RADIO TOTALLY INOPERATIVE. WON''''T TURN ON. PERFORMED PRELIMINARY INSPECTION AND TESTED. COULD NOT DUPLICATE PROBLEM. ADJUSTED SIDETONE. REPLACED FADED DISPLAY LENS. BENCH CHECK GOOD. 1 G 7 1 3U H2SW 2001042000232 20010420 00232 2001 4 20 HEEA072104 4 20010405 G 2312 064105430 TRANSCEIVER BELL 206 206L3 1182108 SW VHF SYSTEM MALFUNCTIONED E HEEA K NONE L NO TEST IN INSP/MAINT 1 SW 03 21497 51518 FLIPPING FROM USE TO STANDBY. PERFORMED PRELIMINARY INSPECTION AND TESTED. COULD NOT DUPLICATE PROBLEM. ADJUSTED FREQU ENCY AND SIDETONE. BENCH CHECK GOOD. 1 G 7 1 3U H2SW 2001042000234 20010420 00234 SW 2001 4 20 HEEA072108 1 20010406 G 6220 407310100103 DAMPER BELL 407 407 SW MAIN ROTOR CORRODED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 724PH 53327 CORROSION IN SHEAR BEARING BORE. SENT TO BELL HELICOPTER TEXTRON FOR CREDIT AGAINST REPLACEMENT PART PURCHASED. REFEREN CE: DMR 715116. LABOR CREDIT ACCOMPLISHED ON J0151671-WA (INVOICE AND DMR NO. 687009. 1 G 7 1 3U O H2SW 2001042000235 20010420 00235 SW 2001 4 20 HEEA072109 1 20010406 G 6220 407310101101 BEARING BELL 407 407 SW MAIN ROTOR WORN E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 724PH 53327 BEARING WORN. SERIAL NUMBERS REMOVED ARE LP6967, LP6611, LP6567 AND LP6625. 1 G 7 1 3U O H2SW 2001042000240 20010420 00240 SW 2001 4 20 HEEA072112 1 20010406 G 6230 SEAL BELL 407 407 SW MAIN ROTOR FAILED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 722PH 1687 A874 53288 SWASHPLATE HAS A BLOWN GREASE SEAL. 1 G 7 1 3U O H2SW 2001042000241 20010420 00241 SW 2001 4 20 HEEA072113 1 20010406 G 6720 407375024101 CONTROL UNIT BELL 407 407 SW TAIL ROTOR DAMAGED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 740PH 291 53435 CAUSES PEDAL STOP TO ENGAGE INTERMITTENTLY WITHOUT ELECTRICAL OR MECHANICAL INPUT. 1 G 7 1 3U O H2SW 2001042000242 20010420 00242 SW 2001 4 20 HEEA072114 1 20010406 G 6320 407040006107FM TRANSMISSION BELL 407 407 SW MAIN ROTOR MAKING METAL E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 467PH 3132 53142 CHIP LIGHT HISTORY, POSSIBLY MAKING METAL. 1 G 7 1 3U O H2SW 2001042000243 20010420 00243 SW 2001 4 20 HEEA072115 1 20010406 G 6300 407340339103 BEARING PHIPBH40701 BELL 407 407 SW OIL COOLER ROUGH E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 612PH PHI0002 53199 OIL COOLER BLOWER BEARINGS ARE ROUGH. SERIAL NUMBERS REMOVED ARE E99-0635 AND E99-0696. 1 G 7 1 3U O H2SW 2001042000250 20010420 00250 SW 2001 4 20 HEEA072116 1 20010406 G 6510 407340339103 BEARING 407040302107 BELL 407 407 SW T/R DRIVESHAFT WORN E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 495PH 440 A1942 53397 WORN. SENT TO BELL HELICOPTER TEXTRON FOR CREDIT AGAINST REPLACEMENT PART PURCHASED. REFERENCE: DMR# 71506402. LABOR CREDIT ACCOMPLISHED ON J0147760-WA (INVOICE AND DMR NO. 686974). 1 G 7 1 3U O H2SW 2001042000251 20010420 00251 SW 2001 4 20 HEEA072117 1 20010406 G 6300 407340339101 BEARING PHIPBH40701 BELL 407 407 SW MAIN ROTOR WORN E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 495PH PHI0014 53397 OIL COOLER BLOWER BEARINGS ARE WORN. SERIAL NUMBERS REMOVED ARE ZV10128 AND ZV10209. 1 G 7 1 3U O H2SW 2001042000252 20010420 00252 SW 2001 4 20 HEEA072118 1 20010406 G 6510 407340339101 BEARING 407040302107 BELL 407 407 SW T/R DRIVESHAFT OVERHEATED E HEEA K NONE M OVER TEMP IN INSP/MAINT 1 SW 03 495PH A1937 53397 TAIL ROTOR DRIVESHAFT BEARINGS OVERHEATED. 1 G 7 1 3U O H2SW 2001042000253 20010420 00253 SW 2001 4 20 HEEA072119 1 20010406 G 7810 407063001101 EXHAUST STACK BELL 407 407 SW ENGINE CRACKED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 499PH 53400 EXHAUST STACK CRACKED. 1 G 7 1 3U O H2SW 2001042000254 20010420 00254 SW 2001 4 20 HEEA072120 1 20010406 G 6510 407340340101 DISC PACK BELL 407 407 SW T/R DRIVE CRACKED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 495PH 53397 TAIL ROTOR DISC PACK CRACKED. 1 G 7 1 3U O H2SW 2001042000255 20010420 00255 SW 2001 4 20 HEEA072121 1 20010406 G 6300 407340339103 BEARING 407040302101 BELL 407 407 SW T/R DRIVESHAFT OVERHEATED E HEEA K NONE M OVER TEMP IN INSP/MAINT 1 SW 03 491PH A15 53386 BEARING ON TAIL ROTOR DRIVESHAFT OVERHEATED. 1 G 7 1 3U O H2SW 2001042000262 20010420 00262 SW 2001 4 20 HEEA072122 1 20010406 G 6710 406010407101 IDLER LINK BELL 407 407 SW COLLECTIVE WORN E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 405PH 1913 53207 COLLECTIVE IDLER LINK IS EXCESSIVELY WORN. 1 G 7 1 3U O H2SW 2001042000263 20010420 00263 SW 2001 4 20 HEEA072123 1 20010406 G 6230 206010408001 PIN BELL 407 407 SW MAIN ROTOR WORN E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 405PH 53207 MAIN ROTOR PIVOT PIN IS EXCESSIVELY WORN. 1 G 7 1 3U O H2SW 2001042000264 20010420 00264 SW 2001 4 20 HEEA072124 1 20010406 G 6300 406310405101 UNIVERSAL JOINT BELL 407 407 SW MAIN ROTOR DRIVE WORN E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 417PH 2066 53038 UNIVERSAL JOINT ON MAIN ROTOR DRIVE IS EXCESSIVELY WORN. 1 G 7 1 3U O H2SW 2001042000265 20010420 00265 SW 2001 4 20 HEEA072125 1 20010406 G 7400 407375038101 GUARD BELL 407 407 SW START SWITCH BROKEN E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 495PH 53397 START SWITCH GUARD BROKEN. 1 G 7 1 3U O H2SW 2001042000266 20010420 00266 SW 2001 4 20 HEEA072126 1 20010406 G 6320 B4749 CHIP DETECTOR BELL 407 407 SW ENGINE GEARBOX LEAKING E HEEA K NONE K FLUID LOSS IN INSP/MAINT 1 SW 03 402PH 53159 ENGINE GEARBOX CHIP DETECTOR IS LEAKING. 1 G 7 1 3U O H2SW 2001042000269 20010420 00269 SW 2001 4 20 HEEA072127 1 20010406 G 6322 206061432121 HOUSING BELL 407 407 SW COOLLER BLOWER CRACKED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 402PH 53159 COOLER BLOWER HOUSING IS CRACKED. 1 G 7 1 3U O H2SW 2001042000270 20010420 00270 2001 4 20 HEEA072128 4 20010406 G 3120 M803B205VBATT CLOCK BELL 407 407 SW COCKPIT DAMAGED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 741PH 28 53457 SELECT BUTTON MISSING. 1 G 7 1 3U O H2SW 2001042000271 20010420 00271 SW 2001 4 20 HEEA072130 1 20010406 G 6510 407340339101 BEARING PHIPBH40701 BELL 407 407 SW OILCOOLER BLOWER OVERHEATED E HEEA K NONE M OVER TEMP IN INSP/MAINT 1 SW 03 402PH PHI0032 53159 OIL COOLER BLOWER BEARINGS OVERHEATED. 1 G 7 1 3U O H2SW 2001042000272 20010420 00272 2001 4 20 HEEA072131 4 20010406 G 2312 064105430 TRANSCEIVER BELL 206 206L3 1182108 SW VHF SYSTEM MALFUNCTIONED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 8591X 51495 RADIO FEEDS BACK INTO HEADSET WHEN TRANSMITTING ON OTHER VHF RADIO SYSTEM IN AIRCRAFT. PERFORMED PRELIMINARY INSPECTION. ADJUSTED CARRIER AND CARRIER/NOISE SQUELCH. BENCH CHECK GOOD. 1 G 7 1 3U H2SW 2001042000273 20010420 00273 2001 4 20 HEEA072132 4 20010406 G 2312 064105430 TRANSCEIVER BELL 206 206L3 1182108 SW VHF SYSTEM MALFUNCTIONED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 3108E 51498 VHF TRANSCEIVER DISPLAY FAILED. 1 G 7 1 3U H2SW 2001042000001 20010420 00001 2001 4 20 HEEA072133 4 20010406 G 2312 064105430 TRANSCEIVER BELL 206 206L1 1182107 SW VHF SYSTEM MALFUNCTIONED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 3904L 45597 VHF TRANSCEIVER BREAKS SQUELCH. 1 G 7 1 3U H2SW 2001042000002 20010420 00002 2001 4 20 HEEA072134 4 20010406 G 3452 066106200 TRANSCEIVER BELL 206 206L1 1182107 SW ATC MALFUNCTIONED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 5745S 45491 NR F2. PULSE. LOW OUTPUT POWER. LOW RESPONSE. REPLACED WITH SERVICEABLE PART. 1 G 7 1 3U H2SW 2001042000003 20010420 00003 2001 4 20 HEEA072135 4 20010406 G 3457 13824120234 GPS BELL 206 206L1 1182107 SW COCKPIT MALFUNCTIONED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 45RP 45521 TIME ENROUTE PAGE INOPERATIVE. PERFORMED PRELIMINARY INSPECTION AND TESTED. COULD NOT DUPLICATE PROBLEM BUT FOUND UNIT WOULD FAIL GPS TEST. RESET MEMORY AND REPROGRAMMED. FOUND CRYSTAL OFFSET OUT OF SPECS. ADJUSTED CRYSTAL FREQUENCY TO SPECS. REPAIRED PROBLEM. BENCH CHECK GOOD. 1 G 7 1 3U H2SW 2001042000004 20010420 00004 2001 4 20 HEEA072136 4 20010406 G 3457 13824120234 GPS BELL 206 206L3 1182108 SW COCKPIT MALFUNCTIONED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 42EA 51542 DROPS ALL WAYPOINTS. PERFORMED PRELIMINARY INSPECTION AND TESTED. COULD NOT DUPLICATE PROBLEM. REPLACED BAD ENT BUTTO N SWITCH AND BAD KEY CAPS. BENCH CHECK GOOD. 1 G 7 1 3U H2SW 2001042000005 20010420 00005 2001 4 20 HEEA072137 4 20010406 G 3457 13824120234 GPS BELL 206 206L1 1182107 SW COCKPIT MALFUNCTIONED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 2135V 45657 WILL NOT COME ON LINE. PERFORMED PRELIMINARY INSPECTION AND FOUND BATTERY DEAD AGAIN. SENT TO TRIMBLE NAVIGATION FOR IN SPECTION AND REPAIR. 1 G 7 1 3U H2SW 2001042000006 20010420 00006 2001 4 20 HEEA072138 4 20010406 G 3457 13824020109 GPS BELL 206 206L1 1182107 SW COCKPIT MALFUNCTIONED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 2124Z 45646 INOPERATIVE WILL NOT PASS CMM5 6-11. SENT TO TRIMBLE NAVIGATION FOR INSPECTION AND REPAIR. 1 G 7 1 3U H2SW 2001042000007 20010420 00007 2001 4 20 HEEA072139 4 20010406 G 3457 13824120234 GPS BELL 206 206B3 1181506 SW COCKPIT DISCHARGED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 22751 3627 BATTERY WEAK. SENT TO TRIMBLE NAVIGATION FOR INSPECTION AND REPAIR. 1 G 7 1 3U H2SW 2001042000008 20010420 00008 2001 4 20 HEEA072140 4 20010406 G 3457 13824120234 GPS BELL 206 206B3 1181506 SW COCKPIT MALFUNCTIONED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 2270G 3610 ENTER BUTTON STICKS IN. SENT TO TRIMBLE NAVIGATION FOR INSPECTION AND REPAIR. 1 G 7 1 3U H2SW 2001042000009 20010420 00009 2001 4 20 HEEA072141 4 20010406 G 3457 13824120234 GPS BELL 206 206B3 1181506 SW COCKPIT MALFUNCTIONED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 2270G 3610 MUST INPUT CODE EVERYTIME UNIT IS TURNED ON. UNIT ONLY PICKS UP ONE OR TWO SATELLITES WHEN ANOTHER UNIT WILL PICK UP SE VEN OR EIGHT IN THE SAME AIRCRAFT. UNIT ALSO INTERMITTENTLY RESTARTS, CHANGES MODES WHILE WAITING FOR IT TO PICK UP MOR E SATELLITES INTERMITTENTLY. SENT TO TRIMBLE NAVIGATION FOR WARRANTY REPAIR. 1 G 7 1 3U H2SW 2001042000010 20010420 00010 2001 4 20 HEEA072142 4 20010406 G 3457 13824120234 GPS BELL 206 206B3 1181506 SW COCKPIT MALFUNCTIONED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 2753F 2729 BUTTONS HARD TO PRESS. SENT TO TRIMBLE NAVIGATION FOR INSPECTION AND REPAIR. 1 G 7 1 3U H2SW 2001042000011 20010420 00011 2001 4 20 HEEA072143 4 20010406 G 3457 13824120234 GPS BELL 206 206L3 1182108 SW COCKPIT MALFUNCTIONED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 129MR 51129 FLASHES WARNING. SENT TO TRIMBLE NAVIGATION FOR INSPECTION AND REPAIR. 1 G 7 1 3U H2SW 2001042000012 20010420 00012 2001 4 20 HEEA072144 4 20010406 G 3457 13824120234 GPS BELL 206 206L1 1182107 SW COCKPIT MALFUNCTIONED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 5014Y 45219 CANNOT SET TIME. SENT TO TRIMBLE NAVIGATION FOR INSPECTION AND REPAIR. 1 G 7 1 3U H2SW 2001042000013 20010420 00013 2001 4 20 HEEA072145 4 20010406 G 3457 13824120234 GPS BELL 206 206L3 1182108 SW COCKPIT MALFUNCTIONED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 32041 51539 WILL NOT HOLD HEADING. SENT TO TRIMBLE NAVIGATION FOR INSPECTION AND REPAIR. 1 G 7 1 3U H2SW 2001042000014 20010420 00014 2001 4 20 HEEA072146 4 20010406 G 3457 13824120234 GPS BELL 206 206L1 1182107 SW COCKPIT MALFUNCTIONED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 2759U 45272 NO MEMORY. SENT TO TRIMBLE NAVIGATION FOR INSPECTION AND REPAIR. 1 G 7 1 3U H2SW 2001042000015 20010420 00015 2001 4 20 HEEA072147 4 20010406 G 3457 13824120234 GPS BELL 206 206L3 1182108 SW COCKPIT MALFUNCTIONED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 49EA 1382 51507 WILL NOT LOCATE ITSELF. SENT TO TRIMBLE NAVIGATION FOR WARRANTY REPAIR. 1 G 7 1 3U H2SW 2001042000016 20010420 00016 SW 2001 4 20 HEEA072148 1 20010406 G 6710 206001564001 WEB BELL 206 206L3 1182108 SW SERVO SUPPORT WORN E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 41791 51465 OUTBOARD AND INBOARD FORWARD SERVO WEB MOUNT LUGS ARE BEING WORN BY THE SERVO FORWARD ROD END BEARING DUE TO ROCKING MOT ION OF THE SERVO. REPLACED WITH SERVICEABLE PART. 1 G 7 1 3U H2SW 2001042000017 20010420 00017 SW 2001 4 20 HEEA072149 1 20010406 G 6710 206001564001 WEB BELL 206 206L3 1182108 SW SERVO MOUNT WORN E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 206FS 51506 OUTBOARD FORWARD SERVO MOUNT LUGS ARE BEING WORN BY THE SERVO FORWARD ROD END BEARING DUE TO ROCKING MOTION OF THE SERVO . REPLACED WITH SERVICEABLE PART. 1 G 7 1 3U H2SW 2001042000018 20010420 00018 SW 2001 4 20 HEEA072150 1 20010406 G 7810 206064300005 EXHAUST STACK BELL 206 206L3 1182108 SW ENGINE CRACKED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 53119 51575 EXHAUST ASSY CRACKED. REPLACED WITH SERVICEABLE PART. 1 G 7 1 3U H2SW 2001042000019 20010420 00019 SW 2001 4 20 HEEA072151 1 20010406 G 7120 206033201163A MOUNT BELL 206 206L3 1182108 SW ENGINE CRACKED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 4835 51131 CRACKED AT ENGINE MOUNT BOLT HOLE AREA. REPLACED WITH SERVICEABLE PART. 1 G 7 1 3U H2SW 2001042000020 20010420 00020 SW 2001 4 20 HEEA072152 1 20010406 G 7120 206064103001 BEARING BELL 206 206L3 1182108 SW ENGINE MOUNT WORN E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 53119 51575 ENGINE MOUNT BEARING WORN. REPLACED WITH SERVICEABLE PART. 1 G 7 1 3U H2SW 2001042000021 20010420 00021 SW 2001 4 20 HEEA072153 1 20010406 G 7120 206064105001 MOUNT BELL 206 206L3 1182108 SW ENGINE DAMAGED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 41791 51465 MECHANICAL DAMAGE BEYOND LIMITS. REPLACED WITH SERVICEABLE PART. 1 G 7 1 3U H2SW 2001042000022 20010420 00022 SW 2001 4 20 HEEA072154 1 20010406 G 7120 206064105002 MOUNT BELL 206 206L3 1182108 SW ENGINE CORRODED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 206LS 51070 ENGINE MOUNT CORRODED BEYOND LIMITS. REPLACED WITH SERVICEABLE PART. 1 G 7 1 3U H2SW 2001042000023 20010420 00023 SW 2001 4 20 HEEA072155 1 20010406 G 7120 206064105101 MOUNT BELL 407 407 SW ENGINE CORRODED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 436PH 51436 ENGINE MOUNT TUBE PITTED ON INSIDE. REPLACED WITH SERVICEABLE PART. 1 G 7 1 3U O H2SW 2001042000024 20010420 00024 SW 2001 4 20 HEEA072156 1 20010406 G 7120 206064105101 MOUNT BELL 206 206L3 1182108 SW ENGINE DAMAGED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 4835 51131 ENGINE MOUNT HAS MECHANICAL DAMAGE BEYOND LIMITS. REPLACED WITH SERVICEABLE PART. 1 G 7 1 3U H2SW 2001042000025 20010420 00025 SW 2001 4 20 HEEA072157 1 20010406 G 7120 206064105102 MOUNT BELL 407 407 SW ENGINE CORRODED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 436PH 51436 ENGINE MOUNT TUBE PITTED ON INSIDE. REPLACED WITH SERVICEABLE PART. 1 G 7 1 3U O H2SW 2001042000026 20010420 00026 SW 2001 4 20 HEEA072158 1 20010406 G 7120 206064105102 MOUNT BELL 206 206L3 1182108 SW ENGINE CORRODED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 4835 51131 ENGINE MOUNT HAS MECHANICAL AND CORROSION DAMAGE BEYOND LIMITS. REPLACED WITH SERVICEABLE PART. 1 G 7 1 3U H2SW 2001042000027 20010420 00027 SW 2001 4 20 HEEA072159 1 20010406 G 7120 206064106001 MOUNT BELL 206 206L3 1182108 SW ENGINE CORRODED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 206LS 51070 ENGINE MOUNT IS CORRODED BEYOND LIMITS. REPLACED WITH SERVICEABLE PART. 1 G 7 1 3U H2SW 2001042000028 20010420 00028 SW 2001 4 20 HEEA072160 1 20010406 G 7120 206064106001 MOUNT BELL 407 407 SW ENGINE CORRODED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 436PH 51436 ENGINE MOUNT TUBE PITTED ON INSIDE. REPLACED WITH SERVICEABLE PART. 1 G 7 1 3U O H2SW 2001042000029 20010420 00029 SW 2001 4 20 HEEA072161 1 20010406 G 7120 206064106101 MOUNT BELL 206 206L3 1182108 SW ENGINE CORRODED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 4835 51131 ENGINE MOUNT HAS PITTED CORROSION. REPLACED WITH SERVICEABLE PART. 1 G 7 1 3U H2SW 2001042000030 20010420 00030 SW 2001 4 20 HEEA072162 1 20010406 G 7120 206064107001 MOUNT BELL 206 206L3 1182108 SW ENGINE CORRODED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 206LS 51070 ENGINE MOUNT IS CORRODED BEYOND LIMITS. REPLACED WITH SERVICEABLE PART. 1 G 7 1 3U H2SW 2001042000036 20010420 00036 SW 2001 4 20 HEEA072163 1 20010406 G 7120 206064107003 MOUNT BELL 206 206L3 1182108 SW ENGINE CORRODED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 206LS 51070 ENGINE MOUNT IS CORRODED BEYOND LIMITS. REPLACED WITH SERVICEABLE PART. 1 G 7 1 3U H2SW 2001042000037 20010420 00037 SW 2001 4 20 HEEA072164 1 20010406 G 7120 206064107101 MOUNT BELL 407 407 SW ENGINE CORRODED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 436PH 51436 ENGINE MOUNT TUBE PITTED ON INSIDE. REPLACED WITH SERVICEABLE PART. 1 G 7 1 3U O H2SW 2001042000038 20010420 00038 SW 2001 4 20 HEEA072165 1 20010406 G 7120 206064107101 MOUNT BELL 206 206L3 1182108 SW ENGINE CORRODED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 41791 51465 ENGINE MOUNT HAS CORROSION DAMAGE BEYOND LIMITS. REPLACED WITH SERVICEABLE PART. 1 G 7 1 3U H2SW 2001042000039 20010420 00039 SW 2001 4 20 HEEA072166 1 20010406 G 7120 206064107101 MOUNT BELL 206 206L3 1182108 SW ENGINE DAMAGED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 4835 51131 ENGINE MOUNT HAS MECHANICAL DAMAGE BEYOND LIMITS. REPLACED WITH SERVICEABLE PART. 1 G 7 1 3U H2SW 2001042000040 20010420 00040 SW 2001 4 20 HEEA072167 1 20010406 G 7120 BEARING BELL 206 206L3 1182108 SW ENGINE MOUNT WORN E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 2619 51375 LEG HAS WORN BEARING. REPLACED WITH SERVICEABLE PART. 1 G 7 1 3U H2SW 2001042000041 20010420 00041 SW 2001 4 20 HEEA072168 1 20010406 G 7120 206064107103 MOUNT BELL 407 407 SW ENGINE CORRODED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 436PH 51436 ENGINE MOUNT TUBE PITTED ON INSIDE. REPLACED WITH SERVICEABLE PART. 1 G 7 1 3U O H2SW 2001042000042 20010420 00042 SW 2001 4 20 HEEA072169 1 20010406 G 7120 206064107103 MOUNT BELL 206 206L3 1182108 SW ENGINE CORRODED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 4835 51131 ENGINE MOUNT HAS CORROSION DAMAGE BEYOND LIMITS. REPLACED WITH SERVICEABLE PART. 1 G 7 1 3U H2SW 2001042000043 20010420 00043 SW 2001 4 20 HEEA072170 1 20010406 G 7120 BEARING BELL 206 206L3 1182108 SW ENGINE MOUNT WORN E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 2619 51375 LEG HAS WORN BEARING. REPLACED WITH SERVICEABLE PART. 1 G 7 1 3U H2SW 2001042000044 20010420 00044 SW 2001 4 20 HEEA072171 1 20010406 G 7810 206064300005 EXHAUST STACK BELL 206 206L3 1182108 SW ENGINE CRACKED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 21497 51518 EXHAUST STACK IS CRACKED. SCRAPPED AND REPLACED WITH SERVICEABLE PART. 1 G 7 1 3U H2SW 2001042000045 20010420 00045 SW 2001 4 20 HEEA072172 1 20010406 G 2560 206072841111 SEAT BELT BELL 206 206L3 1182108 SW COCKPIT MALFUNCTIONED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 4835 51131 SEAT BELT REEL WILL NOT RETRACT. REPLACED WITH SERVICEABLE PART. 1 G 7 1 3U H2SW 2001042000046 20010420 00046 SW 2001 4 20 HEEA072173 1 20010406 G 2560 206072841111 SEAT BELT BELL 206 206L3 1182108 SW COCKPIT STUCK E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 81671 51301 SEAT BELT STICKS. REPLACED WITH SERVICEABLE PART. 1 G 7 1 3U H2SW 2001042000047 20010420 00047 SW 2001 4 20 HEEA072174 1 20010406 G 2560 206072841115 SEAT BELT BELL 206 206L3 1182108 SW COCKPIT MALFUNCTIONED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 4835 51131 SEAT BELT REEL WILL NOT RETRACT. REPLACED WITH SERVICEABLE PART. 1 G 7 1 3U H2SW 2001042000048 20010420 00048 SW 2001 4 20 HEEA072175 1 20010406 G 2560 206072841115 SEAT BELT BELL 206 206L3 1182108 SW COCKPIT STUCK E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 81671 51301 SEAT BELT STICKS. REPLACED WITH SERVICEABLE PART. 1 G 7 1 3U H2SW 2001042000049 20010420 00049 EU 2001 4 20 HEEA072176 1 20010403 G 2432 RG355 BATTERY SNIAS 350 AS350B 8680801 EU DC SYSTEM DISCHARGED E HEEA K NONE L NO TEST IN INSP/MAINT 1 SW 03 972AE 225 3234 ENGINE SLOW TO START. REPLACED WITH SERVICEABLE BATTERY. 1 G 7 1 3U H9EU 2001042000050 20010420 00050 EU 2001 4 20 HEEA072177 1 20010403 G 6210 10581013 BLADE BOLKMS 105 BO105S 5626006 EU MAIN ROTOR DAMAGED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 724MB 3401 S756 NR 1 INBOARD STRIP HAS SEPARATION ON THE OUTBOARD END OF THE ABRASION STRIP. 1 G 7 2 3U H3EU 2001042000051 20010420 00051 EU 2001 4 20 HEEA072178 1 20010405 G 7810 10560186 EXHAUST PIPE BOLKMS 105 BO105S 5626006 EU ENGINE CORRODED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 724MB S756 RUST PITS THROUGH STACK AT MOUNT FLANGE. REPLACED WITH SERVICEABLE PART. 1 G 7 2 3U H3EU 2001050700548 20010507 00548 NE 2001 5 7 HEEA072350 1 20010409 G 2460 A1077B RELAY SKRSKY S76 S76A 8143006 NE ELECTRICAL SYS MALFUNCTIONED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 4253S 760035 ESSENTIAL BUSS READS LOW VOLTAGE. 1 G 7 2 3U H1NE 2001050700549 20010507 00549 NE 2001 5 7 HEEA072351 1 20010410 G 7160 7630207028059 SCREEN SKRSKY S76 S76C 8143008 NE ENGINE INTAKE BROKEN E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 505PH 760505 WIRE MESH HAS WIRE BROKEN. SCRAPPED AND REPLACED WITH SERVICEABLE SCREEN. 1 G 7 2 3U NC H1NE 2001050700550 20010507 00550 2001 5 7 HEEA072352 4 20010411 G 3457 8143902240B GPS SKRSKY S76 S76A 8143006 NE COCKPIT INOPERATIVE E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 4253S 760035 GPS INOPERATIVE. FOUND UNIT WOULD INTERMITTENLY TURN OFF BY ITSELF THEN TURN BACK ON AND SELF TEST AGAIN. 1 G 7 2 3U H1NE 2001050700551 20010507 00551 NE 2001 5 7 HEEA072353 1 20010411 G 7921 7630807901105 OIL COOLER SKRSKY S76 S76A 8143006 NE ENGINE DAMAGED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 1546G 760076 OIL COOLER CAUSING HIGH OIL TEMP. 1 G 7 2 3U H1NE 2001051500108 20010515 00108 2001 5 15 HEEA072354 4 20010411 G 3444 6223201001 INDICATOR BEECH 200 200BEECH 1152920 CE RADIO ALTIMETER INOPERATIVE E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 30PH BB635 NO INDICATIONS IN FLIGHT. 1 L 7 2 4T A24CE 2001050700590 20010507 00590 2001 5 7 HEEA072355 4 20010409 G 3445 MI585200 RADAR BELL 412 412 1182202 SW COCKPIT FAILED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 2298Z 33077 BURNED OUT 3 INDICATORS. PERFORMED PRELIMINARY INSPECTION. FOUND UNIT DOES NOT POWER UP. FOUND Q604, Q605 BAD ON POWER SUPPLY. REPLACED Q604, Q605. REPAIRED. ADJUSTED TO SPECS. BENCH CHECK GOOD. 1 G 7 2 4U H4SW 2001050700591 20010507 00591 2001 5 7 HEEA072356 4 20010409 G 3445 MI585200 RADAR BELL 412 412 1182202 SW COCKPIT FAILED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 3911L 33023 SCREEN ROLLS THEN GOES BLANK. PERFORMED PRELIMINARY INSPECTION. FOUND UNIT DOES NOT POWER UP. REPLACED Q604, Q605. RE PAIRED. ADJUSTED TO SPECS. BENCH CHECK GOOD. 1 G 7 2 4U H4SW 2001050700592 20010507 00592 2001 5 7 HEEA072357 4 20010409 G 3445 MI585200 RADAR BELL 412 412 1182202 SW COCKPIT FAILED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 3893N 33010 INOPERATIVE. NO NOISE BAND DURING TEST. PERFORMED PRELIMINARY INSPECTION. COULD NOT DUPLICATE. ADJUSTED STC AND GAIN VOLTAGE. BENCH CHECK GOOD. 1 G 7 2 4U H4SW 2001050700593 20010507 00593 2001 5 7 HEEA072358 4 20010409 G 3445 MI585200 RADAR BELL 412 412 1182202 SW COCKPIT SHORTED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 3911L 33023 SHORTED INTERNALLY. PERFORMED PRELIMINARY INSPECTION. FOUND UNIT DOES NOT TURN ON. REPLACED Q601, Q602, Q604, Q605 ON P OWER SUPPLY. REPAIRED. BENCH CHECK GOOD. 1 G 7 2 4U H4SW 2001050700594 20010507 00594 2001 5 7 HEEA072359 4 20010409 G 3445 MI585200 RADAR BELL 412 412 1182202 SW COCKPIT FAILED E HEEA O OTHER L NO TEST NR NOT REPORTED 1 SW 03 3893P 33012 GAPS IN TEST PATTERN. PERFORMED PRELIMINARY INSPECTION. FOUND R/T TRANSMITTING POWER OUT INTERMITTENT. REPLACED MAGNETR ON. REPAIRED. BENCH CHECK GOOD. 1 G 7 2 4U H4SW 2001050700595 20010507 00595 2001 5 7 HEEA072360 4 20010409 G 3445 MI585200 RADAR BELL 412 412 1182202 SW COCKPIT FAILED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 5759N 33002 PICTURE SCREEN SIZE FLUCTUATES AND ERRATIC. PERFORMED PRELIMINARY INSPECTION. TROUBLESHOT AND FOUND BAD HIGH VOLTAGES. REPLACED Q604 AND Q605. REPAIRED HIGH VOLTAGE PROBLEM. DISPLAY SLIGHTLY DISTORTED, REPLACED STABILIZATION BOARD, REPAI RED. BENCH CHECK GOOD. 1 G 7 2 4U H4SW 2001050800202 20010508 00202 2001 5 8 HEEA072361 4 20010409 G 3445 MI585200 RADAR BELL 412 412 1182202 SW COCKPIT FAILED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 1202T 33112 UNIT WILL NOT POWER UP. PERFORMED PRELIMINARY INSPECTION. TROUBLESHOT AND REPLACED F202 FUSE. ADJUSTED STC AND GAIN VOL TAGE. BENCH CHECK GOOD. 1 G 7 2 4U H4SW 2001050800203 20010508 00203 2001 5 8 HEEA072362 4 20010409 G 3445 MI5852013 RADAR BELL 412 412 1182202 SW COCKPIT FAILED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 2298Z 33077 FAILS TARGETS AT HIGH RANGE SETTINGS. PERFORMED PRELIMINARY INSPECTION. FOUND MANUAL GAIN SET TOO HIGH, SHOWING FALSE TA RGETS. ADJUSTED ANC, MANUAL GAIN AND COLORS. BENCH CHECK GOOD. 1 G 7 2 4U H4SW 2001050800204 20010508 00204 2001 5 8 HEEA072363 4 20010409 G 3442 MI5852013 RADAR BELL 412 412 1182202 SW COCKPIT FAILED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 2261D 33076 RADAR SYSTEM WOULD NOT POWER UP. PERFORMED PRELIMINARY INSPECTION. FOUND UNIT NOT POWERING UP. FOUND BURNT FOIL ON SWIT CH PANEL. REPAIRED FOIL AND BENCH CHECK GOOD. 1 G 7 2 4U H4SW 2001050800205 20010508 00205 2001 5 8 HEEA072364 4 20010409 G 3442 MI5852013 RADAR BELL 412 412 1182202 SW COCKPIT FAILED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 2298Z 33077 NO INDICATION, BLANK SCREEN. PERFORMED PRELIMINARY INSPECTION. FOUND UNIT NOT DRAW AMPS. REPLACED Q4204, Q4205 TRANSISTO RS ON POWER SUPPLY. REPAIRED. ADJUSTED UNIT TO SPECS. BENCH CHECK GOOD. 1 G 7 2 4U H4SW 2001050800206 20010508 00206 2001 5 8 HEEA072365 4 20010409 G 3442 MI5852013 RADAR BELL 412 412 1182202 SW COCKPIT FAILED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 2298Z 33077 DOES NOT INDICATE. PERFORMED PRELIMINARY INSPECTION. COULD NOT DUPLICATE. ADJUSTED COLORS, ANC AND MANUAL GAIN. BENCH CHECK GOOD. 1 G 7 2 4U H4SW 2001050800207 20010508 00207 2001 5 8 HEEA072366 4 20010409 G 3442 MI5852013 RADAR BELL 412 412 1182202 SW COCKPIT FAILED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 3911L 33023 BLANK SCREEN. PERFORMED PRELIMINARY INSPECTION. FOUND UNIT DRAWS EXCESSIVE CURRENT. REPLACED Q4204, Q4205 TRANSISTORS O N POWER SUPPLY. REPAIRED. FOUND RED AND YELLOW COLORS IN NOISE BAND. REPLACED IC U1402, U1403, U1406. REPAIRED. BEN CH CHECK GOOD. 1 G 7 2 4U H4SW 2001050800208 20010508 00208 2001 5 8 HEEA072367 4 20010409 G 3442 MI5852013 RADAR BELL 412 412 1182202 SW COCKPIT FAILED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 3911L 33023 WILL NOT COME ON BUT WILL POWER UP. PERFORMED PRELIMINARY INSPECTION. FOUND DISPLAY FADES IN AND OUT. CLEANED ALL BOARD S AND PINS. FOUND CORROSION ON MEMORY BOARD CONNECTOR. CLEANED CORROSION. BENCH CHECK GOOD. 1 G 7 2 4U H4SW 2001050800209 20010508 00209 2001 5 8 HEEA072368 4 20010409 G 3442 MI5852013 RADAR BELL 412 412 1182202 SW COCKPIT FAILED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 2298Z 33077 CYCLES ON AND OFF. FLICKERS MOST OF THE TIME AND DOES NOT BRING UP PICTURE. PERFORMED PRELIMINARY INSPECTION. COULD NOT VERIFY COMPLAINT. ADJUSTED ANC AND INTENSITY. BENCH CHECK GOOD. 1 G 7 2 4U H4SW 2001050800210 20010508 00210 2001 5 8 HEEA072369 4 20010409 G 3442 MI5852013 RADAR BELL 412 412 1182202 SW COCKPIT FAILED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 3893N 33010 LEFT SIDE OF DISPLAY WILL NOT DIM. PERFORMED PRELIMINARY INSPECTION. COULD NOT VERIFY COMPLAINT. BENCH CHECK GOOD. 1 G 7 2 4U H4SW 2001050800211 20010508 00211 2001 5 8 HEEA072370 4 20010409 G 3442 MI5852013 RADAR BELL 412 412 1182202 SW COCKPIT FAILED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 3893N 33010 TOP HALF OF DISPLAY DISTORTED. PERFORMED PRELIMINARY INSPECTION. REPLACED SOCKET PINS ON VARIOUS CONNECTORS. REPLACED C RT ASSEMBLY. ALIGNED TO SPECS. BENCH CHECK GOOD. 1 G 7 2 4U H4SW 2001050800212 20010508 00212 2001 5 8 HEEA072371 4 20010409 G 3442 MI5852013 RADAR BELL 412 412 1182202 SW COCKPIT FAILED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 3893P 33012 SCREEN WENT BLANK. PERFORMED PRELIMINARY INSPECTION. FOUND DISPLAY SHRUNK ON SCREEN. REPLACED R133 AND Q1318 ON VIDEO B OARD. REPAIRED. BENCH CHECK GOOD. 1 G 7 2 4U H4SW 2001050800213 20010508 00213 2001 5 8 HEEA072372 4 20010409 G 3442 MI5852013 RADAR BELL 412 412 1182202 SW COCKPIT FAILED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 3911L 33023 COLORS INCORRECT ON TEST MODE. TEST UNSTABLE INTERMITTENTLY. PERFORMED PRELIMINARY INSPECTION. COULD NOT VERIFY COMPLAI NT. BENCH CHECK GOOD. 1 G 7 2 4U H4SW 2001050800214 20010508 00214 2001 5 8 HEEA072373 4 20010409 G 3442 MI5852013 RADAR BELL 412 412 1182202 SW COCKPIT FAILED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 3893N 33010 SCREEN TURNS BLUE. PERFORMED PRELIMINARY INSPECTION. FOUND HIGH VOLTAGE POWER SUPPLY CAUSING LOUD POPPING NOISE. REPLAC ED HIGH VOLTAGE POWER SUPPLY. BENCH CHECK GOOD. 1 G 7 2 4U H4SW 2001050800215 20010508 00215 2001 5 8 HEEA072374 4 20010409 G 3442 MI5852013 RADAR BELL 412 412 1182202 SW COCKPIT FAILED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 107X 33113 VIDEO IS WAVY. SCREEN IS BLANK ON THE TOP AND BOTTOM. PERFORMED PRELIMINARY INSPECTION. FOUND DISPLAY BLANKS OUT AND CO LORS FADE IN AND OUT. FOUND IC U1241 BAD ON TIMING BOARD. REPLACED IC U1241. REPAIRED. ALSO REPLACED 30 EACH SOCKET PINS ON CONNECTORS. BENCH CHECK GOOD. 1 G 7 2 4U H4SW 2001050800216 20010508 00216 2001 5 8 HEEA072375 4 20010409 G 3442 MI5852013 RADAR BELL 412 412 1182202 SW COCKPIT FAILED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 1202T 33112 INOPERATIVE. NO DISPLAY ON SCREEN. PERFORMED PRELIMINARY INSPECTION. COULD NOT VERIFY COMPLAINT. CLEANED SLIGHT CORROS ION ON BOARDS AND CONNECTORS. ADJUSTED TO SPECS. BENCH CHECK GOOD. 1 G 7 2 4U H4SW 2001050800217 20010508 00217 2001 5 8 HEEA072376 4 20010409 G 3442 MI5852013 RADAR BELL 412 412 1182202 SW COCKPIT FAILED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 107X 33113 DISPLAY ERRATIC. PERFORMED PRELIMINARY INSPECTION. REPLACED P1201 CONNECTOR AND CLEANED CORROSION FROM PINS ON SEVERAL C ONNECTORS. BENCH CHECK GOOD. 1 G 7 2 4U H4SW 2001050800218 20010508 00218 2001 5 8 HEEA072377 4 20010409 G 3442 MI585202 ANTENNA BELL 412 412 1182202 SW RADAR DAMAGED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 1202T 33112 WILL NOT HOLD PROPER TILT. PERFORMED PRELIMINARY INSPECTION. COULD NOT DUPLICATE. BENCH CHECK GOOD. 1 G 7 2 4U H4SW 2001050800219 20010508 00219 2001 5 8 HEEA072378 4 20010409 G 2561 PHI10090 LIFE VEST BELL 412 412 1182202 SW CABIN LEAKING E HEEA K NONE L NO TEST IN INSP/MAINT 1 SW 03 7128R 36007 LEAKS. SENT TO J.D. MANUFACTURING FOR INSPECTION AND REPAIR. 1 G 7 2 4U H4SW 2001050800220 20010508 00220 2001 5 8 HEEA072379 4 20010409 G 3442 MI585202 ANTENNA BELL 412 412 1182202 SW RADAR DAMAGED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 2148K 36001 WILL NOT SHOW SWEEP AND NO TARGETS DISPLAYED. REPLACED WITH SERVICEABLE UNIT. 1 G 7 2 4U H4SW 2001050800221 20010508 00221 SW 2001 5 8 HEEA072380 1 20010409 G 5260 PHI101741 STEP BELL 412 412 1182202 SW RIGHT STUCK E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 3893L 33006 RIGHT STEP STUCK IN STOW POSITION. REPLACED WITH SERVICEABLE UNIT. 1 G 7 2 4U H4SW 2001050800222 20010508 00222 SW 2001 5 8 HEEA072381 1 20010409 G 2510 222320823119 SEAT BELT BELL 206 206L3 1182108 SW COCKPIT DAMAGED E HEEA K NONE W INADEQUATE Q C IN INSP/MAINT 1 SW 03 31077 51520 BAD SHOULDER HARNESS TENSION ADJUSTERS BACKWARDS AND RUB AGAINST BODY AND CANNOT BE ADJUSTED. 1 G 7 1 3U H2SW 2001050800223 20010508 00223 2001 5 8 HEEA072382 4 20010409 G 3422 5040017901 INDICATOR BELL 206 206L3 1182108 SW ATTITUDE FAILED E HEEA K NONE L NO TEST IN INSP/MAINT 1 SW 03 30KH 51527 WOULD NOT ERECT. REPLACED WITH SERVICEABLE PART. 1 G 7 1 3U H2SW 2003081500011 20030815 00011 SW 2003 8 15 HEEA072383 1 20010409 G 2820 206063650001 VALVE BELL 206 206L1 1182107 SW FUEL SYSTEM LEAKING E HEEA K NONE K FLUID LOSS IN INSP/MAINT 1 SW 03 5019F 45244 LEAKING FUEL VALVE. REPLACED WITH SERVICEABLE PART. 1 G 7 1 3U H2SW 2001050800224 20010508 00224 SW 2001 5 8 HEEA072384 1 20010409 G 7120 206064107109 LEG ASSY BELL 206 206L3 1182108 SW ENGINE MOUNT WORN E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 42EA 51542 BEARING WORN. REPLACED WITH SERVICEABLE PART. 1 G 7 1 3U H2SW 2001050800225 20010508 00225 SW 2001 5 8 HEEA072385 1 20010409 G 7810 206064203101 DUCT BELL 206 206L3 1182108 SW EXHAUST CRACKED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 42EA 51542 CRACKED. REPLACED WITH SERVICEABLE PART. 1 G 7 1 3U H2SW 2001050800226 20010508 00226 SW 2001 5 8 HEEA072386 1 20010409 G 2510 206072841113 SEAT BELT BELL 206 206L3 1182108 SW COCKPIT STUCK E HEEA K NONE L NO TEST IN INSP/MAINT 1 SW 03 4835 51131 INERTIA REEL RATCHETY AND INTERMITTENTLY STICKS WHEN EXTENDING. REPLACED WITH SERVICEABLE PART. 1 G 7 1 3U H2SW 2001050800227 20010508 00227 SW 2001 5 8 HEEA072387 1 20010409 G 2913 206076030101 PUMP BELL 206 206L3 1182108 SW HYD SYSTEM NOISY E HEEA K NONE E VIBRATION/BUFFET IN INSP/MAINT 1 SW 03 30KH 51527 NOISE COMING FROM HYDRAULIC SYSTEM DURING CRUISE AND ON APPROACHES INTERMITTENT. REPLACED WITH SERVICEABLE PART. 1 G 7 1 3U H2SW 2001050800228 20010508 00228 SW 2001 5 8 HEEA072388 1 20010409 G 3212 206050247109 COVER BELL 206 206L1 1182107 SW FLOAT LOOSE E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 5007Q 45187 LEFT AFT FLOAT COVER FLAP VELCRO HAS COME LOOSE FROM COVER. STITCHING CAME OUT. REPLACED WITH SERVICEABLE PART. 1 G 7 1 3U H2SW 2001050800229 20010508 00229 SW 2001 5 8 HEEA072389 1 20010409 G 3210 206323018 CROSSTUBE BELL 206 206L3 1182108 SW MLG CORRODED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 21497 51518 CORROSION PITS UNDER SADDLE MOUNTS. SCRAPPED AND REPLACED WITH SERVICEABLE CROSSTUBE. 1 G 7 1 3U H2SW 2001050800230 20010508 00230 SW 2001 5 8 HEEA072390 1 20010409 G 2824 205060612003 VALVE BELL 412 412 1182202 SW FUEL SYSTEM BYPASSING E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 7128R 36007 ALLOWS FUEL TO BYPASS IN THE CLOSED POSITION. SENT TO ITT AEROSPACE FOR INSPECTION AND REPAIR. 1 G 7 2 4U H4SW 2001050800231 20010508 00231 SW 2001 5 8 HEEA072391 1 20010409 G 2844 209062003001 SWITCH BELL 412 412 1182202 SW FUEL SYSTEM MALFUNCTIONED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 3893L 33006 LOW PRESSURE LIGHT WILL NOT COME ON. SCRAPPED AND REPLACED WITH SERVICEABLE PART. 1 G 7 2 4U H4SW 2001050800232 20010508 00232 SW 2001 5 8 HEEA072392 1 20010409 G 2844 209062003001 SWITCH BELL 412 412 1182202 SW FUEL SYSTEM LEAKING E HEEA K NONE K FLUID LOSS IN INSP/MAINT 1 SW 03 3893L 33006 LEAKING THROUGH SWITCH BODY. SCRAPPED AND REPLACED WITH SERVICEABLE PART. 1 G 7 2 4U H4SW 2001050800233 20010508 00233 SW 2001 5 8 HEEA072393 1 20010409 G 2844 209062003001 SWITCH BELL 412 412 1182202 SW FUEL SYSTEM MALFUNCTIONED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 7128R 36007 C-BOX PRESSURE LIGHT ILLUMINATES INTERMITTENTLY AND REMAINS ON 1 TO 2 MINUTES, THEN GOES OUT. C-BOX OIL PRESSURE REMAIN S STEADY. SCRAPPED AND REPLACED WITH SERVICEABLE PART. 1 G 7 2 4U H4SW 2001050800234 20010508 00234 SW 2001 5 8 HEEA072394 1 20010409 G 7810 212061201011 EJECTOR BELL 412 412 1182202 SW ENGINE CRACKED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 2261D 33076 CRACKED. SCRAPPED AND REPLACED WITH SERVICEABLE PART. 1 G 7 2 4U H4SW 2001050800235 20010508 00235 SW 2001 5 8 HEEA072395 1 20010409 G 7810 212061201012 EJECTOR BELL 412 412 1182202 SW EXHAUST CRACKED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 2261D 33076 CRACKED AT MOUNTING PADS. SCRAPPED AND REPLACED WITH SERVICEABLE PART. 1 G 7 2 4U H4SW 2001050800236 20010508 00236 SW 2001 5 8 HEEA072396 1 20010409 G 7810 212061210001 DUCT BELL 412 412 1182202 SW EXHAUST CRACKED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 3893L 33006 CRACKED. SCRAPPED AND REPLACED WITH SERVICEABLE PART. 1 G 7 2 4U H4SW 2001050800237 20010508 00237 2001 5 8 HEEA072397 4 20010409 G 3413 212070239001 INDICATOR BELL 412 412 1182202 SW COCKPIT VSI ERRATIC E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 7128R 36007 ERRATIC READINGS FAILED STATIC CHECK. 1 G 7 2 4U H4SW 2001050800238 20010508 00238 2001 5 8 HEEA072398 4 20010409 G 3413 212070239001 INDICATOR BELL 412 412 1182202 SW COCKPIT VSI ERRATIC E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 7128R 36007 ERRATIC ABOVE 2000 FEET MSL. 1 G 7 2 4U H4SW 2001050800239 20010508 00239 SW 2001 5 8 HEEA072399 1 20010409 G 5260 212070418105 ACTUATOR BELL 412 412 1182202 SW STEP INOPERATIVE E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 5759N 33002 STEP ACTUATOR DOES NOT FUNCTION. 1 G 7 2 4U H4SW 2001050800240 20010508 00240 SW 2001 5 8 HEEA072400 1 20010409 G 7714 212075037101 INDICATOR BELL 412 412 1182202 SW N1 ERRATIC E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 3911L 33023 BOUNCES ERRATICALLY. 1 G 7 2 4U H4SW 2001050800241 20010508 00241 SW 2001 5 8 HEEA072401 1 20010409 G 5260 212075418103 ACTUATOR BELL 412 412 1182202 SW STEP INOPERATIVE E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 7128R 36007 ROD BROKEN ON ACTUATOR AND IS INOPERATIVE. 1 G 7 2 4U H4SW 2001050800242 20010508 00242 SW 2001 5 8 HEEA072402 1 20010409 G 5260 212075418105 ACTUATOR BELL 412 412 1182202 SW STEP INOPERATIVE E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 3893N 33010 STEP WILL NOT RETRACT. 1 G 7 2 4U H4SW 2001050800243 20010508 00243 SW 2001 5 8 HEEA072403 1 20010409 G 5260 212075418105 ACTUATOR BELL 412 412 1182202 SW STEP FROZEN E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 6559Z 36019 STEP ACTUATOR FROZEN. 1 G 7 2 4U H4SW 2001050800244 20010508 00244 SW 2001 5 8 HEEA072404 1 20010409 G 2510 214070966101 SEAT BELT BELL 412 412 1182202 SW COCKPIT DAMAGED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 2261D 33076 END UNSTITCHED. 1 G 7 2 4U H4SW 2001050800245 20010508 00245 SW 2001 5 8 HEEA072405 1 20010409 G 2510 214070966101 SEAT BELT BELL 412 412 1182202 SW COCKPIT DAMAGED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 2261D 33076 END UNSTITCHED. 1 G 7 2 4U H4SW 2001050800246 20010508 00246 SW 2001 5 8 HEEA072406 1 20010409 G 6420 412010418105 BEARING BELL 412 412 1182202 SW MAIN ROTOR CORRODED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 PITTING ON RACE. SENT TO BELL HELICOPTER TEXTRON FOR CREDIT. 1 G 7 2 4U H4SW 2001050800247 20010508 00247 SW 2001 5 8 HEEA072407 1 20010409 G 5320 206033201167S STIFFENER BELL 206 206L1 1182107 SW FUSELAGE BENT E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 STIFFENER CHANNELS ARE NOT BENT CORRECTLY. U-CHANNEL VERTICAL FLANGES ARE SUPPOSED TO BE BENT UP 90 DEGREES. THE FLANG ES ON THESE TWO CHANNELS ARE 85 DEGREES AND 95 DEGREES. THIS CAUSES THE FITTING, P/N 206-031-629-103 TO BE INSTALLED AT AN ANGLE, AND WILL CAUSE THE ENGINE MOUNT BOLT TO BE INSTALLED AT AN ANGLE THROUGH THE BULKHEAD. SENT TO BELL HELICOPTE R TEXTRON FOR CREDIT. 1 G 7 1 3U H2SW 2001050800248 20010508 00248 SW 2001 5 8 HEEA072408 1 20010409 G 7714 214074280107 DETECTOR BELL 412 412 1182202 SW RPM LIMIT MALFUNCTIONED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 3893L 33006 RPM WARNING LIGHT FLICKERS ON AND OFF AROUND 75 PERCENT N2. 1 G 7 2 4U H4SW 2001050800249 20010508 00249 2001 5 8 HEEA072409 4 20010409 G 3424 214075244001 GYRO BELL 412 412 1182202 SW TURN RATE MALFUNCTIONED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 6559Z 36019 TURN NEEDLE OSCILLATES. 1 G 7 2 4U H4SW 2001050800250 20010508 00250 SW 2001 5 8 HEEA072410 1 20010409 G 5260 212075418105 ACTUATOR BELL 412 412 1182202 SW STEP INOPERATIVE E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 3911L 33023 DOES NOT WORK. 1 G 7 2 4U H4SW 2001050800251 20010508 00251 SW 2001 5 8 HEEA072411 1 20010409 G 5260 212075418105 ACTUATOR BELL 412 412 1182202 SW STEP INOPERATIVE E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 7128R 36007 STEP WILL NOT EXTEND. 1 G 7 2 4U H4SW 2001050800252 20010508 00252 2001 5 8 HEEA072412 4 20010409 G 3424 214075244001 GYRO BELL 412 412 1182202 SW RATE OF TURN INOPERATIVE E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 1202T 33112 NO RATE OF TURN INDICATION. 1 G 7 2 4U H4SW 2001050800253 20010508 00253 2001 5 8 HEEA072413 4 20010409 G 3424 214075244001 GYRO BELL 412 412 1182202 SW RATE OF TURN INOPERATIVE E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 3893L 33006 TURN NEEDLE IS INOPERATIVE. 1 G 7 2 4U H4SW 2001050800254 20010508 00254 SW 2001 5 8 HEEA072414 1 20010409 G 5230 2353 HANDLE BELL 412 412 1182202 SW CARGO DOOR DAMAGED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 3911L 33023 HEAT COATING WORN OFF BAGGAGE DOOR HANDLE. HANDLE LOOSE ON IT''S SHAFT. REPLACED WITH SERVICEABLE PART. 1 G 7 2 4U H4SW 2001050800255 20010508 00255 NE 2001 5 8 HEEA072415 2 20010409 G 7323 25249994 GOVERNOR BELL 412 412 1182202 SW PWA PT6T PT6T3B 52045 NE FREE TURBINE INOPERATIVE E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 3893N 33010 N2 WILL NOT REACH 100 PERCENT. FOUND INTERIOR OF UNIT VERY DIRTY. TEFLON TUBE WAS WORN. REPLACED TEFLON TUBE WITH NEW PART AND CLEANED INTERIOR PARTS. 1 G 7 2 4U 4 U H4SW E22EA 2001050800256 20010508 00256 NE 2001 5 8 HEEA072416 2 20010409 G 7323 25249994 GOVERNOR BELL 412 412 1182202 SW PWA PT6T PT6T3B 52045 NE FREE TURBINE MALFUNCTIONED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 3893N 33010 N2 WENT HIGH WITH THROTTLE AT IDLE. FOUND UNIT TO BE SLIGHTLY HANGING. SPLIT UNIT AND FOUND INTERIOR OF UNIT TO BE DIRT Y, WITH FLYWEIGHTS STICKING. THIS WAS THE CAUSE OF THE HANGING ON BENCH. CLEANED INTERIOR OF UNIT AND GOVERNOR TESTED OK. 1 G 7 2 4U 4 U H4SW E22EA 2001050800257 20010508 00257 NE 2001 5 8 HEEA072417 2 20010409 G 7320 2526385 BELLOWS 324473514 BELL 412 412 1182202 SW PWA PT6T PT6T3B 52045 NE FUEL CONTROL DEFECTIVE E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 3893N 212 A34690 33010 IDLES AT 45 PERCENT N1 AND WILL NOT ACCELERATE. FOUND ALL FLOWS TO BE VERY LOW AND UNADJUSTABLE. SPLIT UNIT AND FOUND B ELLOWS TO BE DEFECTIVE. 1 G 7 2 4U 4 U H4SW E22EA 2001050800258 20010508 00258 NE 2001 5 8 HEEA072418 2 20010409 G 7320 324473514 FUEL CONTROL BELL 412 412 1182202 SW PWA PT6T PT6T3B 52045 NE ENGINE MALFUNCTIONED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 3893N 33010 ENGINE SLOW TO START. SMOKES ON START CYCLE. RAN UNIT AS RECEIVED ON TEST BENCH. COULD NOT DUPLICATE PROBLEM. 1 G 7 2 4U 4 U H4SW E22EA 2001050800259 20010508 00259 NE 2001 5 8 HEEA072419 2 20010409 G 7320 324473514 FUEL CONTROL BELL 412 412 1182202 SW PWA PT6T PT6T3B 52045 NE ENGINE MALFUNCTIONED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 3893N 33010 ENGINE SLOW TO START. SMOKES ON START CYCLE. RAN UNIT AS RECEIVED ON TEST BENCH. COULD NOT DUPLICATE PROBLEM. 1 G 7 2 4U 4 U H4SW E22EA 2001050800260 20010508 00260 NE 2001 5 8 HEEA072420 2 20010409 G 7320 324473514 FUEL CONTROL BELL 412 412 1182202 SW PWA PT6T PT6T3B 52045 NE ENGINE MALFUNCTIONED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 3911L 33023 7 PERCENT TORQUE SURGE AT FLAT PITCH. RAN UNIT AS RECEIVED ON TEST BENCH. COULD NOT DUPLICATE PROBLEM. 1 G 7 2 4U 4 U H4SW E22EA 2001050800261 20010508 00261 NE 2001 5 8 HEEA072421 2 20010409 G 7320 32447368 FUEL CONTROL BELL 412 412 1182202 SW PWA PT6T PT6T3B 52045 NE ENGINE MALFUNCTIONED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 3911L 33023 7 PERCENT N1 OSCILLATION, TOO MUCH CUSHION ON THE HIGH SIDE, UNABLE TO ADJUST. RAN UNIT AS RECEIVED ON TEST BENCH. COUL D NOT DUPLICATE PROBLEM. 1 G 7 2 4U 4 U H4SW E22EA 2003081500012 20030815 00012 SW 2003 8 15 HEEA072422 1 20010409 G 6730 41005496101 SERVO BELL 412 412 1182202 SW FLT CONTROLS LEAKING E HEEA O OTHER K FLUID LOSS NR NOT REPORTED 1 SW 03 SERVO CAUSING EXCESSIVE INTERNAL LEAKAGE DURING TESTING. 1 G 7 2 4U H4SW 2001050800262 20010508 00262 SW 2001 5 8 HEEA072423 1 20010409 G 6710 212076005105 CYLINDER BELL 412 412 1182202 SW MAIN ROTOR BYPASSING E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 CAUSING EXCESSIVE BYPASS DURING TESTING. 1 G 7 2 4U H4SW 2001050800263 20010508 00263 SW 2001 5 8 HEEA072424 1 20010409 G 3213 412050010111A CROSSTUBE BELL 412 412 1182202 SW MLG DAMAGED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 3911L 33023 AFT CROSSTUBE SPREAD BEYOND LIMITS. REPLACED WITH SERVICEABLE PART. 1 G 7 2 4U H4SW 2001050800264 20010508 00264 SW 2001 5 8 HEEA072425 1 20010409 G 3213 412015060102 SKID SHOE BELL 412 412 1182202 SW MAIN SKID TORN E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 1202T 33112 SHOE TORN AT MOUNT POINTS. REPLACED WITH SERVICEABLE PART. 1 G 7 2 4U H4SW 2001050800265 20010508 00265 SW 2001 5 8 HEEA072426 1 20010409 G 3213 412030437103 CAP BELL 412 412 1182202 SW MLG DETERIORATED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 6559Z 36019 RUBBER ON CAP DETERIORATED. 1 G 7 2 4U H4SW 2001050800266 20010508 00266 SW 2001 5 8 HEEA072427 1 20010409 G 3213 412050016102 SHOE BELL 412 412 1182202 SW MLG WORN E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 1202T 33112 WORN. REPLACED WITH SERVICEABLE PART. 1 G 7 2 4U H4SW 2001050800267 20010508 00267 SW 2001 5 8 HEEA072428 1 20010409 G 3213 412050016102 SHOE BELL 412 412 1182202 SW MLG WORN E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 3893N 33010 WORN. REPLACED WITH SERVICEABLE PART. 1 G 7 2 4U H4SW 2001050800268 20010508 00268 SW 2001 5 8 HEEA072429 1 20010409 G 3212 412050017133 COVER BELL 412 412 1182202 SW FLOAT TORN E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 3893L 33006 FLOAT COVER TORN. 1 G 7 2 4U H4SW 2001050800269 20010508 00269 SW 2001 5 8 HEEA072430 1 20010409 G 3212 412050017133 COVER BELL 412 412 1182202 SW FLOAT TORN E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 2149S 36002 FLOAT COVER TORN. REPLACED WITH SERVICEABLE COVER. 1 G 7 2 4U H4SW 2001050800270 20010508 00270 SW 2001 5 8 HEEA072431 1 20010409 G 3212 412050017135 COVER BELL 412 412 1182202 SW FLOAT WORN E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 2261D 33076 WORN VELCRO. 1 G 7 2 4U H4SW 2001050800271 20010508 00271 SW 2001 5 8 HEEA072432 1 20010409 G 3213 412050045107 CROSSTUBE BELL 412 412 1182202 SW MLG DAMAGED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 UPON REMOVING CENTER PIVOT SADDLE; IT WAS FOUND THAT THERE WAS NO HOT BOND AGENT UNDER PIVOT. REPAIRED. 1 G 7 2 4U H4SW 2001050800272 20010508 00272 SW 2001 5 8 HEEA072433 1 20010409 G 2510 412070843105 STRAP BELL 412 412 1182202 SW COCKPIT FRAYED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 6559Z 36019 STRAPS FRAYED. REPLACED RESTRAINTS. 1 G 7 2 4U H4SW 2001050800273 20010508 00273 SW 2001 5 8 HEEA072434 1 20010409 G 7712 412075008111 INDICATOR BELL 412 412 1182202 SW COCKPIT READS LOW E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 2261D 33076 NUMBER TWO NEEDLE READS LOW. REPLACED WITH SERVICEABLE PART. 1 G 7 2 4U H4SW 2001050800274 20010508 00274 2001 5 8 HEEA072435 4 20010409 G 3414 412075009105 INDICATOR BELL 412 412 1182202 SW COCKPIT INACCURATE E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 2298Z 33077 13 KNOT DIFFERENCE BETWEEN PILOTS AND COPILOTS INSTRUMENTS. 1 G 7 2 4U H4SW 2001050800275 20010508 00275 SW 2001 5 8 HEEA072436 1 20010409 G 7714 412075010109 INDICATOR BELL 412 412 1182202 SW TRIPLE TACH READS LOW E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 7128R 36007 INDICATES 2 PERCENT LOW. SENT TO MASCO FOR WARRANTY REPAIR. 1 G 7 2 4U H4SW 2001050800276 20010508 00276 SW 2001 5 8 HEEA072437 1 20010409 G 7714 412075010109 INDICATOR BELL 412 412 1182202 SW TRIPLE TACH STUCK E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 7128R 36007 N2 NEEDLES STICK WHEN POWER IS CHANGED. 1 G 7 2 4U H4SW 2001050800277 20010508 00277 SW 2001 5 8 HEEA072438 1 20010409 G 7714 412075010109 INDICATOR BELL 412 412 1182202 SW TRIPLE TACH INOPERATIVE E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 3893N 33010 NR 1 TACH NEEDLE STOPPED ALL INDICATING. 1 G 7 2 4U H4SW 2001050800278 20010508 00278 SW 2001 5 8 HEEA072439 1 20010409 G 2436 51539002N GCU BELL 412 412 1182202 SW NR 1 GENERATOR FAILED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 6559Z 36019 NR 2 GENERATOR FAILED IN FLIGHT, WOULD NOT RESET. 1 G 7 2 4U H4SW 2001050800279 20010508 00279 SW 2001 5 8 HEEA072440 1 20010409 G 3213 AB412050016101 SKID SHOE BELL 412 412 1182202 SW MLG WORN E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 2261D 33076 SKID SHOE WORN THROUGH. REPLACED WITH SERVICEABLE PART. 1 G 7 2 4U H4SW 2001050800280 20010508 00280 SW 2001 5 8 HEEA072441 1 20010410 G 6720 PHI41294 BUSHING BELL 412 412 1182202 SW TAIL ROTOR WORN E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 6559Z 36019 BUSHINGS AND ROD ENDS WORN. REPLACED WITH SERVICEABLE PART. 1 G 7 2 4U H4SW 2003081500013 20030815 00013 SW 2003 8 15 HEEA072442 1 20010410 G 6420 PHI41294 ROTOR HEAD BELL 412 412 1182202 SW TAIL ROTOR VIBRATION E HEEA O OTHER E VIBRATION/BUFFET NR NOT REPORTED 1 SW 03 108X 33115 TAIL ROTOR PRODUCING A HIGH FREQ VIBRATION. REPLACED WITH SERVICEABLE PART. 1 G 7 2 4U H4SW 2001050800281 20010508 00281 2001 5 8 HEEA072443 4 20010410 G 2312 064105430 TRANSCEIVER BELL 206 206L3 1182108 SW COCKPIT NOISY E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 21497 51518 A LOT OF BACKGROUND NOISE IN RECEPTION MODE. PERFORMED PRELIMINARY INSPECTION AND FOUND CARRIER SQUELCH INTERMITTENT, AD JUSTED R184. 1 G 7 1 3U H2SW 2001050800282 20010508 00282 2001 5 8 HEEA072444 4 20010410 G 2312 064105430 TRANSCEIVER BELL 206 206L1 1182107 SW COCKPIT MALFUNCTIONED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 45RP 45521 DISPLAY BLINKS ON AND OFF. PERFORMED PRELIMINARY INSPECTION. SWAPPED OUT DISPLAY. NO HELP. REPLACED BAD VOLUME POTENT IOMETER, CRACKED TRANSFER SWITCH AND PUSH BUTTON AND IC I901. FOUND BRIGHT DASHES TO APPEAR ACROSS MIDDLE OF USE FREQUE NCY. REPLACED IC I505 AND I506. NO HELP. 1 G 7 1 3U H2SW 2001050800283 20010508 00283 SW 2001 5 8 HEEA072445 1 20010410 G 6330 206033506101 RESTRAINT BELL 206 206L1 1182107 SW TRANSMISSION WORN E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 5019F 45244 BEARINGS WORN. REPLACED WITH SERVICEABLE RESTRAINT. 1 G 7 1 3U H2SW 2001050800284 20010508 00284 SW 2001 5 8 HEEA072446 1 20010410 G 6330 206033506101 RESTRAINT BELL 206 206L3 1182108 SW TRANSMISSION WORN E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 6610C 51425 BEARINGS WORN. REPLACED WITH SERVICEABLE RESTRAINT. 1 G 7 1 3U H2SW 2001050800285 20010508 00285 2001 5 8 HEEA072447 4 20010410 G 2312 064105430 TRANSCEIVER BELL 206 206L1 1182107 SW COCKPIT MALFUNCTIONED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 2135V 45657 WILL NOT TRANSMIT ON ALL FREQUENCIES AND WILL NOT SWITCH. PERFORMED PRELIMINARY INSPECTION. COULD NOT DUPLICATE PROBLEM . ADJUSTED FREQUENCY. FOUND DISPLAY STAYING DIM ALL THE TIME. REPLACED BAD V901 PHOTOCELL. REPAIRED PROBLEM. BENCH CHECK GOOD. 1 G 7 1 3U H2SW 2001050800286 20010508 00286 SW 2001 5 8 HEEA072448 1 20010410 G 7933 209070262101 INDICATOR BELL 412 412 1182202 SW ENGINE OIL READS HIGH E HEEA K NONE L NO TEST IN INSP/MAINT 1 SW 03 6559Z 36019 INDICATES ABOVE RED LINE. 1 G 7 2 4U H4SW 2001050800287 20010508 00287 SW 2001 5 8 HEEA072449 1 20010410 G 7933 209070262101 INDICATOR BELL 412 412 1182202 SW ENGINE OIL READS HIGH E HEEA K NONE L NO TEST IN INSP/MAINT 1 SW 03 3911L 33023 INDICATES ABOVE RED LINE. 1 G 7 2 4U H4SW 2001050800288 20010508 00288 SW 2001 5 8 HEEA072450 1 20010410 G 7933 209070262101 INDICATOR BELL 412 412 1182202 SW ENGINE OIL STUCK E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 3911L 33023 STICKS WHEN ENGINE IS FIRST RUN UP. 1 G 7 2 4U H4SW 2001050800289 20010508 00289 SW 2001 5 8 HEEA072451 1 20010410 G 6720 PHI41294 BUSHING BELL 412 412 1182202 SW TAIL ROTOR WORN E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 3893L 33006 WORN BEARINGS/BUSHINGS. REPLACED WITH SERVICEABLE PART. 1 G 7 2 4U H4SW 2001050800290 20010508 00290 2001 5 8 HEEA072452 4 20010410 G 3421 PHI4121017601 CONNECTOR BELL 412 412 1182202 SW ATTITIUDE GYRO LOOSE E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 CONNECTOR PLUG RECEPTACLE LOOSE IN HOUSING. REPLACED WITH SERVICEABLE PART. 1 G 7 2 4U H4SW 2001050800291 20010508 00291 SW 2001 5 8 HEEA072453 1 20010410 G 2821 AC985F10 FUEL FILTER BELL 214 214ST 1182106 SW FUEL SYSTEM MALFUNCTIONED E HEEA K NONE J WARNING INDICATION IN INSP/MAINT 1 SW 03 3897N 28106 FUEL FILTER LIGHT. REPLACED WITH SERVICEABLE PART. 2 G 7 2 4U H10SW 2001050800292 20010508 00292 SW 2001 5 8 HEEA072454 1 20010410 G 7712 412075008111 INDICATOR BELL 412 412 1182202 SW TORQUE INOPERATIVE E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 2261D 33076 NR 1 NEEDLE IS INOPERATIVE. 1 G 7 2 4U H4SW 2001050800293 20010508 00293 SW 2001 5 8 HEEA072455 1 20010410 G 7712 412075008111 INDICATOR BELL 412 412 1182202 SW TORQUE SPLIT E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 2261D 33076 HAS A 10 PERCENT SPLIT. ALSO NOTICED WITH JUST THE NR 1 ENGINE RUNNING THE TRANSMISSION NEEDLE FLUCTUATING AND BRINGING THE NR 2 NEEDLE WITH IT. 1 G 7 2 4U H4SW 2001050800294 20010508 00294 SW 2001 5 8 HEEA072456 1 20010410 G 7714 412075010109 INDICATOR BELL 412 412 1182202 SW TRIPLE TACH READS LOW E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 3893L 33006 NR 1 ENGINE READING LOW. 1 G 7 2 4U H4SW 2001050800295 20010508 00295 SW 2001 5 8 HEEA072457 1 20010410 G 7714 412075010111 INDICATOR BELL 412 412 1182202 SW TRIPLE TACH INOPERATIVE E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 3893L 33006 NR 1 NEEDLE INOPERATIVE. 1 G 7 2 4U H4SW 2001050800296 20010508 00296 SW 2001 5 8 HEEA072458 1 20010410 G 3213 AB205050403031 CROSSTUBE BELL 412 412 1182202 SW MLG CORRODED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 22347 36005 CORRODED BEYOND LIMITS UNDER BOTH SADDLE MOUNTS. SCRAPPED AND REPLACED WITH SERVICEABLE TUBE. 1 G 7 2 4U H4SW 2001050800297 20010508 00297 SW 2001 5 8 HEEA072459 1 20010410 G 5260 PHI101741 ACTUATOR BELL 412 412 1182202 SW STEP INOPERATIVE E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 2149S 36002 WILL NOT OPERATE LEFT STEP ACTUATOR. REPLACED WITH SERVICEABLE PART. 1 G 7 2 4U H4SW 2001050800298 20010508 00298 SW 2001 5 8 HEEA072460 1 20010410 G 5260 PHI101741 ACTUATOR BELL 412 412 1182202 SW STEP INOPERATIVE E HEEA K NONE L NO TEST IN INSP/MAINT 1 SW 03 2261D 33076 LEFT STEP WILL NOT RAISE. REPLACED WITH SERVICEABLE PART. 1 G 7 2 4U H4SW 2001050800299 20010508 00299 SW 2001 5 8 HEEA072461 1 20010410 G 5260 PHI101741 ACTUATOR BELL 412 412 1182202 SW STEP INOPERATIVE E HEEA K NONE L NO TEST IN INSP/MAINT 1 SW 03 3893L 33006 LT STEP WILL NOT EXTEND. REPLACED WITH SERVICEABLE PART. 1 G 7 2 4U H4SW 2001050800300 20010508 00300 SW 2001 5 8 HEEA072462 1 20010410 G 5260 PHI101741 ACTUATOR BELL 412 412 1182202 SW STEP INOPERATIVE E HEEA K NONE L NO TEST IN INSP/MAINT 1 SW 03 6559Z 36019 LT STEP WILL NOT RETRACT. REPLACED WITH SERVICEABLE PART. 1 G 7 2 4U H4SW 2001050800301 20010508 00301 GL 2001 5 8 HEEA072463 2 20010410 G 7320 25490924 FUEL CONTROL BELL 206 206L1 1182107 SW ALLSN 250C 250C30P 03013 GL ENGINE LEAKING E HEEA K NONE K FLUID LOSS IN INSP/MAINT 1 SW 03 2133X 45634 CAE890024 FUEL LEAKING FROM AROUND BYPASS COVER. DURING OVERHAUL FOUND EXCESSIVE CORROSION AND PITTING AROUND BYPASS COVER AND BOR E. THIS CONDITION WILL CAUSE LEAKING FROM THE BYPASS COVER. REPLACED COMPLETE MAIN FLOW BODY ASSY. UNIT TESTED SATISF ACTORY. 1 G 7 1 3U 3 U H2SW E1GL 2001050800302 20010508 00302 GL 2001 5 8 HEEA072464 2 20010410 G 7320 252464430 FUEL CONTROL BELL 206 206B3 1181506 SW ALLSN 250C 250C20B 03013 GL ENGINE MALFUNCTIONED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 2753F 2729 GOING HOT AND WOULD NOT RESPOND TO ADJUSTMENTS. REPLACED WITH SERVICEABLE FUEL CONTROL. 1 G 7 1 3U 3 U H2SW E4CE 2001050800303 20010508 00303 GL 2001 5 8 HEEA072465 2 20010410 G 7320 25490925 FUEL CONTROL BELL 206 206L3 1182108 SW ALLSN 250C 250C20B 03013 GL ENGINE ERRATIC E HEEA K NONE L NO TEST IN INSP/MAINT 1 SW 03 8589X 51487 INCONSISTENT STARTS. SOME STARTS NORMAL. OTHERS DELAYED AND TENDED TO HAVE HIGH TOT. REPLACED WITH SERVICEABLE FUEL CO NTROL. 1 G 7 1 3U 3 U H2SW E4CE 2001050800304 20010508 00304 2001 5 8 HEEA072466 4 20010410 G 3421 5040017901 INDICATOR BELL 206 206L1 1182107 SW COCKPIT PRECESSES E HEEA K NONE L NO TEST IN INSP/MAINT 1 SW 03 45RP 45521 EXCESSIVE PRECESSING. REPLACED WITH SERVICEABLE ATTITUDE INDICATOR. 1 G 7 1 3U H2SW 2001050800305 20010508 00305 2001 5 8 HEEA072467 4 20010410 G 3421 5040017901 INDICATOR BELL 206 206L3 1182108 SW COCKPIT INACCURATE E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 4835 51131 INDICATES 7-8 DEGREE LEFT TURN IN LEVEL FLIGHT. REPLACED WITH SERVICEABLE ATTITUDE INDICATOR. 1 G 7 1 3U H2SW 2001050800306 20010508 00306 2001 5 8 HEEA072468 4 20010410 G 3421 5040017901 INDICATOR BELL 206 206L3 1182108 SW COCKPIT MALFUNCTIONED E HEEA K NONE L NO TEST IN INSP/MAINT 1 SW 03 8591X 51495 ROLLING AND WILL NOT HOLD A LEVEL ATTITUDE. REPLACED WITH SERVICEABLE ATTITUDE INDICATOR. 1 G 7 1 3U H2SW 2001050800307 20010508 00307 2001 5 8 HEEA072469 4 20010410 G 3422 5050010902 GYRO BELL 206 206L3 1182108 SW COCKPIT MALFUNCTIONED E HEEA K NONE L NO TEST IN INSP/MAINT 1 SW 03 6251X 51552 LAGS 40 DEGREE IN 180 DEGREE TURN. REPLACED WITH SERVICEABLE PART. 1 G 7 1 3U H2SW 2001050800308 20010508 00308 SW 2001 5 8 HEEA072470 1 20010410 G 6520 PHI2062003 HOUSING BELL 206 206L3 1182108 SW TAIL ROTOR LEAKING E HEEA K NONE K FLUID LOSS IN INSP/MAINT 1 SW 03 21497 51518 TAIL ROTOR GEARBOX INPUT SEAL LEAKING. REPLACED WITH SERVICEABLE PART. 1 G 7 1 3U H2SW 2001050800309 20010508 00309 GL 2001 5 8 HEEA072471 2 20010410 G 7320 25490925 FUEL CONTROL BELL 206 206L3 1182108 SW ALLSN 250C 250C20B 03013 GL ENGINE MALFUNCTIONED E HEEA K NONE R PARTIAL RPM/PWR LOSS IN INSP/MAINT 1 SW 03 4835 51131 STARTS STAGNATES AT 33 PERCENT N1. RAN UNIT ON TEST BENCH AND COULD NOT DUPLICATE PROBLEM. 1 G 7 1 3U 3 U H2SW E4CE 2001050800310 20010508 00310 SW 2001 5 8 HEEA072472 1 20010410 G 6210 200578S69D BOLT BELL 206 206L1 1182107 SW M/R BLADE DAMAGED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 5019F 45244 AREA OF SHANK BEHIND THREADS, IS OVERSIZED AND WILL NOT ALLOW BOLT TO GO THROUGH BUSHING. REPLACED WITH SERVICEABLE PART . 1 G 7 1 3U H2SW 2001050800311 20010508 00311 SW 2001 5 8 HEEA072473 1 20010410 G 5260 212075418105 ACTUATOR BELL 412 412 1182202 SW STEP INOPERATIVE E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 6559Z 36019 LT STEP WILL NOT RETRACT. 1 G 7 2 4U H4SW 2001050800312 20010508 00312 SW 2001 5 8 HEEA072474 1 20010410 G 7332 206061535007 TRANSDUCER BELL 206 206L1 1182107 SW FUEL PRESSURE MALFUNCTIONED E HEEA O OTHER O OTHER CR CRUISE 1 SW 03 513EH 45421 WHILE IN CRUISE FLIGHT THE FUEL PRESSURE INDICATOR SHOWED A DECREASE IN FUEL PRESSURE. REPLACED PRESSURE TRANSMITTER. 1 G 7 1 3U H2SW 2001050800313 20010508 00313 SW 2001 5 8 HEEA072475 1 20010410 G 5610 222180109 WINDOW BELL 430 430 1182150 SW COCKPIT SEPARATED E HEEA O OTHER D INFLIGHT SEPARATION NR NOT REPORTED 1 SW 03 430X 49058 ENROUTE TO MP283 AT 3000 FEET AT 135 KNOTS, THE CO-PILOT''S DOOR WINDOW DEPARTED THE AIRCRAFT. INSPECTED AND FOUND NO DA MAGE TO AIRCRAFT. 1 G 7 2 3U RT H9SW 2001050800314 20010508 00314 2001 5 8 HEEA072476 4 20010411 G 3457 8143902240B GPS BELL 412 412 1182202 SW COCKPIT FAILED E HEEA K NONE L NO TEST IN INSP/MAINT 1 SW 03 2149S 36002 WILL NOT RECEIVE SATELLITES. COULD NOT DUPLICATE PROBLEM. BENCH CHECK GOOD. 1 G 7 2 4U H4SW 2001050800315 20010508 00315 2001 5 8 HEEA072477 4 20010411 G 3457 8143902240B GPS BELL 412 412 1182202 SW COCKPIT FAILED E HEEA K NONE L NO TEST IN INSP/MAINT 1 SW 03 2149S 36002 GPS WENT OFF LINE/ON LINE. COULD NOT DUPLICATE PROBLEM. BENCH CHECK GOOD. 1 G 7 2 4U H4SW 2001050800316 20010508 00316 2001 5 8 HEEA072478 4 20010411 G 3457 8143902240B GPS BELL 206 206L3 1182108 SW COCKPIT FAILED E HEEA K NONE L NO TEST IN INSP/MAINT 1 SW 03 4835 51131 CDI (EXTERNAL) DOES NOT INDICATE PROPERLY. DOES NOT AGREE WITH GPS CDI REMAINS 2 DIVISIONS DIFFERENT. SENT TO TRIMBLE N AVIGATION FOR INSPECTION AND REPAIR. 1 G 7 1 3U H2SW 2001050800317 20010508 00317 2001 5 8 HEEA072480 4 20010411 G 3457 8143802240D GPS BELL 407 407 SW COCKPIT FAILED E HEEA K NONE L NO TEST IN INSP/MAINT 1 SW 03 492PH 53390 FALLS OFF LINE. 1 G 7 1 3U O H2SW 2001050800318 20010508 00318 2001 5 8 HEEA072481 4 20010411 G 3457 8143802240D GPS BELL 206 206B3 1181506 SW COCKPIT FAILED E HEEA K NONE L NO TEST IN INSP/MAINT 1 SW 03 22743 3624 LOCKS ON ONE LOCATION, WILL NOT UPDATE IN FLIGHT. SENT TO TRIMBLE NAVIGATION FOR WARRANTY REPAIR. 1 G 7 1 3U H2SW 2001050800319 20010508 00319 2001 5 8 HEEA072482 4 20010411 G 3442 80510800001 CONTROL BOX BELL 206 206L3 1182108 SW RADAR FAILED E HEEA K NONE L NO TEST IN INSP/MAINT 1 SW 03 6610Y 51419 NO TARGETS DISPLAYED. 1 G 7 1 3U H2SW 2001050800320 20010508 00320 2001 5 8 HEEA072483 4 20010411 G 3443 80510890001 CONTROL BOX BELL 206 206L3 1182108 SW RADAR FAILED E HEEA K NONE L NO TEST IN INSP/MAINT 1 SW 03 6610Y 51419 WOULD NOT TRACK AIRCRAFT PROPERLY. 1 G 7 1 3U H2SW 2001050800321 20010508 00321 SW 2001 5 8 HEEA072484 1 20010411 G 7921 8538100 OIL COOLER BELL 412 412 1182202 SW ENGINE LEAKING E HEEA K NONE K FLUID LOSS IN INSP/MAINT 1 SW 03 1202T 33112 LEAKING FROM CENTER CORE AREA. 1 G 7 2 4U H4SW 2001050800322 20010508 00322 SW 2001 5 8 HEEA072485 1 20010411 G 2820 869A6TT CHECK VALVE BELL 206 206L1 1182107 SW ENGINE MALFUNCTIONED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 3178K 45765 CHECK VALVES POSSIBLY CAUSING ENGINE FLAME OUT. REPLACED WITH SERVICEABLE PART. 1 G 7 1 3U H2SW 2001050800323 20010508 00323 SW 2001 5 8 HEEA072486 1 20010411 G 2820 869A6TT VALVE BELL 206 206L1 1182107 SW ENGINE STUCK E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 45RP 45521 STICKING OPEN. REPLACED WITH SERVICEABLE PART. 1 G 7 1 3U H2SW 2001050800324 20010508 00324 2001 5 8 HEEA072487 4 20010411 G 2214 7000298901 COMPUTER BELL 412 412 1182202 SW AFCS MALFUNCTIONED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 2148K 36001 NR 2 HELIPILOT WOULD NOT COME ON. 1 G 7 2 4U H4SW 2001050800325 20010508 00325 2001 5 8 HEEA072488 4 20010411 G 2212 7000299901 CONTROL UNIT BELL 412 412 1182202 SW AFCS FAILED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 3893L 33006 NR 2 HELIPILOT WILL NOT CYCLE AFCS CAUTION LIGHT WITH HELIPILOT ON AND TURNING HELIPILOT NR 2 ON AND OFF. 1 G 7 2 4U H4SW 2001050800326 20010508 00326 2001 5 8 HEEA072489 4 20010411 G 3444 7000839901 INDICATOR BELL 412 412 1182202 SW RADAR ALTIMETER MALFUNCTIONED E HEEA K NONE L NO TEST IN INSP/MAINT 1 SW 03 108X 33115 FLAG WILL NOT PULL. 1 G 7 2 4U H4SW 2001050800327 20010508 00327 2001 5 8 HEEA072490 4 20010411 G 3444 7000839904 INDICATOR BELL 412 412 1182202 SW RADAR ALTIMETER FAILED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 33008 36004 READS LOW AND DH LIGHT DOES NOT COME ON AT SET ALTITUDE. 1 G 7 2 4U H4SW 2001050800328 20010508 00328 SW 2001 5 8 HEEA072491 1 20010411 G 2910 70066L000R230 HOSE BELL 412 412 1182202 SW HYD SYSTEM LEAKING E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 108X 33115 LEAKING THROUGH STEEL BRAIDED SLEEVE. REPLACED WITH SERVICEABLE HOSE. 1 G 7 2 4U H4SW 2001050800329 20010508 00329 SW 2001 5 8 HEEA072492 1 20010411 G 3110 78805059008 INDICATOR BELL 206 206L3 1182108 SW COCKPIT INTERMITTENT E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 4282Z 51499 INTERMITTENT DISPLAY. 1 G 7 1 3U H2SW 2001050800330 20010508 00330 2001 5 8 HEEA072493 4 20010411 G 3416 6221205004 ALTIMETER BELL 412 412 1182202 SW COCKPIT MALFUNCTIONED E HEEA K NONE L NO TEST IN INSP/MAINT 1 SW 03 1202T 33112 TESTS AT 42 INSTEAD OF 50 +/-5. 1 G 7 2 4U H4SW 2001050800331 20010508 00331 SW 2001 5 8 HEEA072494 1 20010411 G 6730 6225194001 SERVO BELL 206 206L1 1182107 SW AUTOPILOT MALFUNCTIONED E HEEA K NONE L NO TEST IN INSP/MAINT 1 SW 03 5744Y 45465 INTERMITTENT FEEDBACK (KICKING) IN AUTOPILOT SYSTEM. REPLACED WITH SERVICEABLE PART. 1 G 7 1 3U H2SW 2001050800332 20010508 00332 SW 2001 5 8 HEEA072495 1 20010411 G 6730 6225194001 SERVO BELL 206 206L1 1182107 SW AUTOPILOT MALFUNCTIONED E HEEA K NONE L NO TEST IN INSP/MAINT 1 SW 03 5744Y 45465 CAUSES AUTOPILOT SYSTEM TO DISENGAGE AND FEEDBACK IN CONTROLS (KICKING). REPLACED WITH SERVICEABLE PART. 1 G 7 1 3U H2SW 2001050800333 20010508 00333 SW 2001 5 8 HEEA072496 1 20010411 G 6730 6225194001 SERVO BELL 206 206L1 1182107 SW AUTOPILOT MALFUNCTIONED E HEEA K NONE L NO TEST IN INSP/MAINT 1 SW 03 5744Y 45465 SERVO CAUTION LIGHT ILLUMINATES AND AUTOPILOT SYSTEM DISENGAGES. REPLACED WITH SERVICEABLE PART. 1 G 7 1 3U H2SW 2001050800334 20010508 00334 SW 2001 5 8 HEEA072497 1 20010411 G 6730 6225194001 SERVO BELL 206 206L1 1182107 SW AUTOPILOT MALFUNCTIONED E HEEA K NONE L NO TEST IN INSP/MAINT 1 SW 03 5744Y 45465 AUTOPILOT SYSTEM INTERMITTENTLY DISENGAGES AND SERVO CAUSES KICKING IN PILOT''''S CYCLIC STICK. REPLACED WITH SERVICEABL E PART. 1 G 7 1 3U H2SW 2001050800335 20010508 00335 SW 2001 5 8 HEEA072498 1 20010411 G 3110 65013008 INDICATOR BELL 206 206L3 1182108 SW COCKPIT DAMAGED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 4835 51131 STICKS. FACEPLATE CAME OFF DURING REMOVAL OF INDICATOR. SENT TO MASCO FOR INSPECTION AND REPAIR. 1 G 7 1 3U H2SW 2001050800336 20010508 00336 GL 2001 5 8 HEEA072499 2 20010411 G 7240 6854255 VALVE BELL 206 206L3 1182108 SW ALLSN 250B 250B* GL ENGINE DAMAGED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 206FS 51506 THREADS DAMAGED THAT GO INTO COMBUSTION CASE. REPLACED WITH SERVICEABLE PART. 1 G 7 1 3U 3 T H2SW E10CE 2001050800337 20010508 00337 SW 2001 5 8 HEEA072500 1 20010411 G 7120 BEARING BELL 407 407 SW ENGINE MOUNT DAMAGED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 719PH 53266 REAR ENGINE MOUNT BEARING UNSTAKED. SENT TO DALLAS AIRMOTIVE FOR OVERHAUL. 1 G 7 1 3U O H2SW 2001050800338 20010508 00338 SW 2001 5 8 HEEA072501 1 20010411 G 7100 6892836 TUBE BELL 206 206L3 1182108 SW ENGINE LEAKING E HEEA K NONE K FLUID LOSS IN INSP/MAINT 1 SW 03 6610C 51425 TUBE ASSY LEAKING. REPLACED WITH SERVICEABLE PART. 1 G 7 1 3U H2SW 2001050800339 20010508 00339 GL 2001 5 8 HEEA072502 2 20010411 G 7420 6893283 IGNITION LEAD BELL 206 206L4 1182110 SW ALLSN 250B 250B* GL ENGINE INOPERATIVE E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 7077F 52038 IGNITION LEAD INOPERATIVE. 1 G 7 1 3U 3 T NC H2SW E10CE 2001050900093 20010509 00093 GL 2001 5 9 HEEA072505 2 20010411 G 7532 6894063 BLEED VALVE BELL 206 206L3 1182108 SW ALLSN 250B 250B* GL ENGINE MALFUNCTIONED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 8588X 51486 WOULD NOT ACTUATE. REPLACED WITH SERVICEABLE PART. 1 G 7 1 3U 3 T H2SW E10CE 2001050800340 20010508 00340 2001 5 8 HEEA072506 4 20010411 G 3421 5040017901 INDICATOR BELL 206 206L3 1182108 SW ATTITUDE FAILED E HEEA K NONE L NO TEST IN INSP/MAINT 1 SW 03 8591X 51495 ROLLING, WILL NOT HOLD A LEVEL ALTITUDE. REPLACED WITH SERVICEABLE PART. 1 G 7 1 3U H2SW 2001050800341 20010508 00341 2001 5 8 HEEA072507 4 20010411 G 3421 5040017901 INDICATOR BELL 206 206L1 1182107 SW ATTITUDE PRECESSES E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 45RP 45521 PRECESSES. REPLACED WITH SERVICEABLE PART. 1 G 7 1 3U H2SW 2001050800342 20010508 00342 2001 5 8 HEEA072508 4 20010411 G 3421 5040017901 INDICATOR BELL 206 206L3 1182108 SW ATTITUDE PRECESSES E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 6160Y 51609 PILOT REPORTS THAT AFTER INSTRUMENT SLOWLY STARTED TO PRECESS THE CARD WAS CORRECTED AND INSTRUMENT FROZE UP IN WINGS LE VEL AND NOSE ON HORIZON POSITION. REPLACED WITH SERVICEABLE PART. 1 G 7 1 3U H2SW 2001050800343 20010508 00343 2001 5 8 HEEA072509 4 20010411 G 3421 5040017901 INDICATOR BELL 206 206L1 1182107 SW ATTITUDE INOPERATIVE E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 5019F 45244 PILOT REPORTED INDICATOR INOPERATIVE. REPLACED WITH SERVICEABLE PART. 1 G 7 1 3U H2SW 2001050800344 20010508 00344 2001 5 8 HEEA072510 4 20010411 G 3422 5050010902 GYRO BELL 206 206L3 1182108 SW COCKPIT SMOKE E HEEA O OTHER B SMOKE/FUMES/ODORS/SPARKS NR NOT REPORTED 1 SW 03 41791 51465 SMOKING AND POPS CIRCUIT BREAKER. REPLACED TRANSFORMER, RESISTORS AND BEARINGS. BENCH CHECK GOOD. 1 G 7 1 3U H2SW 2001050800345 20010508 00345 2001 5 8 HEEA072511 4 20010411 G 3422 5050010902 GYRO BELL 206 206L1 1182107 SW COCKPIT PRECESSES E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 5007Q 45187 PRECESSES 2 DEGREES EVERY 5 MINUTES. REPLACED WITH SERVICEABLE PART. 1 G 7 1 3U H2SW 2001050800346 20010508 00346 SW 2001 5 8 HEEA072512 1 20010411 G 6320 50501008380401 SEAL BELL 206 206L3 1182108 SW OIL PUMP LEAKING E HEEA K NONE K FLUID LOSS IN INSP/MAINT 1 SW 03 6160Y 51609 OIL LEAKING FROM TRANSMISSION OIL PUMP DRIVE SHAFT SEAL. REPLACED TRANSMISSION OIL PUMP. 1 G 7 1 3U H2SW 2001050800347 20010508 00347 2001 5 8 HEEA072514 4 20010411 G 2562 569880101 SWITCH BELL 206 206L4 1182110 SW ELT FAILED E HEEA K NONE L NO TEST IN INSP/MAINT 1 SW 03 7077F 52038 RED LIGHT STAYS ON DIM. REPLACED WITH SERVICEABLE SWITCH. 1 G 7 1 3U NC H2SW 2001050800348 20010508 00348 NE 2001 5 8 HEEA072515 2 20010411 G 7420 3029107 LEAD BELL 412 412 1182202 SW PWA PT6T PT6T3B 52045 NE IGNITER FRAYED E K NONE O OTHER IN INSP/MAINT 1 SW 03 1202T 33112 FRAYED. REPLACED WITH SERVICEABLE CABLE. 1 G 7 2 4U 4 U H4SW E22EA 2001050800349 20010508 00349 SW 2001 5 8 HEEA072516 1 20010411 G 7722 3030083 COMPENSATOR BELL 412 412 1182202 SW TRIM FLUCTUATES E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 6559Z 36019 ITT FLUCTUATES IN FLIGHT AT OR ABOVE 2500 FEET ALTITUDE. 1 G 7 2 4U H4SW 2001050800350 20010508 00350 NE 2001 5 8 HEEA072517 2 20010411 G 7321 32447066 CONTROL UNIT BELL 412 412 1182202 SW PWA PT6T PT6T3B 52045 NE ENGINE MALFUNCTIONED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 142PH 33150 TORQUE OSCILLATIONS DURING POWER CHANGES. TESTED UNIT AND COULD NOT DUPLICATE PROBLEM. 1 G 7 2 4U 4 U H4SW E22EA 2001050800351 20010508 00351 NE 2001 5 8 HEEA072518 2 20010411 G 7321 32447066 CONTROL UNIT BELL 412 412 1182202 SW PWA PT6T PT6T3B 52045 NE ENGINE CONTAMINATED E HEEA O OTHER J WARNING INDICATION NR NOT REPORTED 1 SW 03 3893N 33010 DROOPING IN FLIGHT, FOUND TURCO IN FITTINGS. CLEANED AND POLISHED SERVO VALVE, LEVERS AND FITTINGS. UNIT TESTED OK. 1 G 7 2 4U 4 U H4SW E22EA 2001050800352 20010508 00352 SW 2001 5 8 HEEA072519 1 20010411 G 6510 327211 DISC PACK BELL 206 206L3 1182108 SW T/R SHAFT CORRODED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 206LS 51070 CORRODED BEYOND LIMITS. REPLACED WITH NEW PARTS. 1 G 7 1 3U H2SW 2001050800353 20010508 00353 SW 2001 5 8 HEEA072520 1 20010411 G 6510 327211 DISC PACK BELL 206 206L3 1182108 SW T/R DRIVE SHAFT CORRODED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 41128 51134 PITTED BEYOND LIMITS. REPLACED WITH NEW PARTS. 1 G 7 1 3U H2SW 2001050800354 20010508 00354 SW 2001 5 8 HEEA072521 1 20010411 G 6510 327211 DISC PACK BELL 206 206L3 1182108 SW T/R DRIVE SHAFT FRETTED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 41791 51465 FRETTING BEYOND LIMITS. REPLACED WITH NEW PARTS. 1 G 7 1 3U H2SW 2001050800355 20010508 00355 SW 2001 5 8 HEEA072522 1 20010411 G 6510 327211 DISC PACK BELL 206 206L1 1182107 SW T/R DRIVE SHAFT CRACKED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 45RP 45521 CRACKED. REPLACED WITH NEW PARTS. 1 G 7 1 3U H2SW 2001050800356 20010508 00356 SW 2001 5 8 HEEA072523 1 20010411 G 6510 327211 DISC PACK BELL 206 206L1 1182107 SW T/R DRIVE SHAFT CRACKED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 45RP 45521 CRACKED. REPLACED WITH NEW PARTS. 1 G 7 1 3U H2SW 2001050800357 20010508 00357 SW 2001 5 8 HEEA072524 1 20010411 G 6510 327211 DISC PACK BELL 407 407 SW T/R DRIVE SHAFT CORRODED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 436PH 51436 CORRODED BEYOND LIMITS. REPLACED WITH NEW PARTS. 1 G 7 1 3U O H2SW 2001050800358 20010508 00358 SW 2001 5 8 HEEA072525 1 20010411 G 6510 327211 DISC PACK BELL 206 206L1 1182107 SW T/R DRIVE SHAFT CORRODED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 5014V 45217 CORRODED BEYOND LIMITS. REPLACED WITH NEW PARTS. 1 G 7 1 3U H2SW 2001050800359 20010508 00359 SW 2001 5 8 HEEA072526 1 20010411 G 6510 327211 DISC PACK BELL 206 206L3 1182108 SW T/R DRIVE SHAFT CORRODED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 6251X 51552 CORRODED BEYOND LIMITS. REPLACED WITH NEW PARTS. 1 G 7 1 3U H2SW 2001050800360 20010508 00360 SW 2001 5 8 HEEA072527 1 20010411 G 6510 327211 DISC PACK BELL 206 206L4 1182110 SW T/R DRIVE SHAFT CORRODED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 7077F 52038 CORRODED BEYOND LIMITS. REPLACED WITH NEW PARTS. 1 G 7 1 3U NC H2SW 2001050800361 20010508 00361 2001 5 8 HEEA072528 4 20010411 G 2330 002000002 AMPLIFIER BELL 206 206L3 1182108 SW PA SYSTEM INOPERATIVE E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 31077 51520 INOPERATIVE. WILL NOT TURN ON. PERFORMED PRELIMINARY INSPECTION. FOUND Q3204 BAD. REPLACED. CLEANED RUST ON HOUSING AND PAINTED. FUNCTION CHECK GOOD. 1 G 7 1 3U H2SW 2001050800362 20010508 00362 2001 5 8 HEEA072529 4 20010411 G 3457 0110005400 GPS BELL 206 206L1 1182107 SW COCKPIT FAILED E HEEA K NONE L NO TEST IN INSP/MAINT 1 SW 03 5007Q 45187 LOOSES SATELLITES DURING FLIGHT. 1 G 7 1 3U H2SW 2001050800363 20010508 00363 2001 5 8 HEEA072530 4 20010411 G 3457 0110005400 GPS BELL 206 206L3 1182108 SW COCKPIT FAILED E HEEA K NONE L NO TEST IN INSP/MAINT 1 SW 03 21497 51518 WILL NOT ACQUIRE SATELLITE SIGNAL. 1 G 7 1 3U H2SW 2001050800364 20010508 00364 2001 5 8 HEEA072531 4 20010411 G 3457 0110005400 GPS BELL 206 206L1 1182107 SW COCKPIT FAILED E HEEA K NONE L NO TEST IN INSP/MAINT 1 SW 03 21240 45647 DROPPING OFF. 1 G 7 1 3U H2SW 2001050800365 20010508 00365 2001 5 8 HEEA072532 4 20010411 G 3457 0110005400 GPS BELL 206 206L1 1182107 SW COCKPIT FAILED E HEEA K NONE L NO TEST IN INSP/MAINT 1 SW 03 5007Y 45192 WILL NOT COME ON LINE FOR 20-40 MINUTES. 1 G 7 1 3U H2SW 2001050800366 20010508 00366 2001 5 8 HEEA072533 4 20010411 G 3457 BATTERY BELL 206 206L3 1182108 SW GPS DISCHARGED E HEEA K NONE L NO TEST IN INSP/MAINT 1 SW 03 6748D 81509251 51106 INTERNAL BATTERY WEAK. SENT TO GARMIN INTERNATIONAL FOR INSPECTION AND REPAIR. 1 G 7 1 3U H2SW 2001050800367 20010508 00367 2001 5 8 HEEA072534 4 20010411 G 3457 0110005400 GPS BELL 206 206L3 1182108 SW COCKPIT UNRELIABLE E HEEA K NONE L NO TEST IN INSP/MAINT 1 SW 03 979BH 51403 GPS UNRELIABLE. SENT TO GARMIN INTERNATIONAL FOR INSPECTION AND REPAIR. 1 G 7 1 3U H2SW 2001050800368 20010508 00368 GL 2001 5 8 HEEA072535 2 20010411 G 7261 03808808 ELEMENT BELL 206 206L3 1182108 SW ALLSN 250C 250C30 03013 GL ENG OIL SYSTEM BYPASSING E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 31077 51520 BYPASSED EARLY. SCRAPPED LOCALLY AND REPLACED WITH NEW FILTER. 1 G 7 1 3U 3 U H2SW E1GL 2001050800369 20010508 00369 2001 5 8 HEEA072536 4 20010411 G 3457 0845000000 GPS BELL 206 206L1 1182107 SW COCKPIT INOPERATIVE E HEEA K NONE L NO TEST IN INSP/MAINT 1 SW 03 2775A 45297 1ST DIGIT OF DISPLAY INOPERATIVE. SENT TO MAGELLAN SYSTEMS FOR INSPECTION AND REPAIR. 1 G 7 1 3U H2SW 2001050800370 20010508 00370 2001 5 8 HEEA072537 4 20010411 G 3457 0845000000 GPS BELL 206 206L3 1182108 SW COCKPIT MALFUNCTIONED E HEEA K NONE L NO TEST IN INSP/MAINT 1 SW 03 81671 51301 WILL NOT KEEP USER WAYPOINTS WHEN POWER IS CYCLED. SENT TO MAGELLAN SYSTEMS FOR INSPECTION AND REPAIR. 1 G 7 1 3U H2SW 2001050800371 20010508 00371 2001 5 8 HEEA072538 4 20010411 G 3457 0845000000 GPS BELL 206 206L3 1182108 SW COCKPIT INOPERATIVE E HEEA K NONE L NO TEST IN INSP/MAINT 1 SW 03 81671 51301 POWER BUTTON IS INOPERATIVE. SENT TO MAGELLAN SYSTEMS FOR INSPECTION AND REPAIR. 1 G 7 1 3U H2SW 2001050800372 20010508 00372 SW 2001 5 8 HEEA072539 1 20010411 G 6510 406040340101 DISC PACK BELL 206 206L3 1182108 SW T/R DRIVE SHAFT CORRODED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 41128 51134 PITTED BEYOND LIMITS. REPLACED WITH SERVICEABLE PART. 1 G 7 1 3U H2SW 2001050800373 20010508 00373 SW 2001 5 8 HEEA072540 1 20010411 G 6720 206001058101 CONTROL ROD BELL 206 206L3 1182108 SW TAIL ROTOR CORRODED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 41791 51465 CORROSION UNDER NYLATRON SLEEVE FOUND TO BE .020 INCH DEEP. SCRAPPED AND REPLACED WITH SERVICEABLE PART. 1 G 7 1 3U H2SW 2001050800374 20010508 00374 SW 2001 5 8 HEEA072541 1 20010411 G 6720 206001058101 CONTROL ROD BELL 206 206L4 1182110 SW TAIL ROTOR CORRODED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 7074W 52033 CORROSION BEYOND LIMITS. SCRAPPED AND REPLACED WITH SERVICEABLE PART. 1 G 7 1 3U NC H2SW 2001050800375 20010508 00375 SW 2001 5 8 HEEA072542 1 20010411 G 6330 206033506101 RESTRAINT BELL 206 206L3 1182108 SW TRANSMISSION WORN E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 42EA 51542 WORN SPHERICAL BEARINGS. 1 G 7 1 3U H2SW 2001050800376 20010508 00376 SW 2001 5 8 HEEA072543 1 20010411 G 6330 206033506101 RESTRAINT BELL 206 206L3 1182108 SW TRANSMISSION WORN E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 2619 51375 BEARING IN TRANSMISSION RESTRAINT CAME UNSTAKED. REPLACED WITH SERVICEABLE PART. 1 G 7 1 3U H2SW 2001050800377 20010508 00377 SW 2001 5 8 HEEA072544 1 20010411 G 6330 206033506103 RESTRAINT BELL 206 206L3 1182108 SW TRANSMISSION WORN E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 6251X 51552 BEARING WORN. REPLACED WITH SERVICEABLE PART. 1 G 7 1 3U H2SW 2001050800378 20010508 00378 SW 2001 5 8 HEEA072545 1 20010411 G 6330 206033506103 RESTRAINT BELL 206 206L3 1182108 SW TRANSMISSION WORN E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 81671 51301 BOTH RESTRAINT ARM BEARINGS HAS EXCESSIVE WEAR IN BEARINGS. REPLACED WITH SERVICEABLE PART. 1 G 7 1 3U H2SW 2001050800379 20010508 00379 SW 2001 5 8 HEEA072546 1 20010411 G 6330 206033506101 RESTRAINT BELL 206 206L3 1182108 SW TRANSMISSION WORN E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 53119 51575 BEARING WORN AND ONE BEARING UNSTAKED. REPLACED WITH SERVICEABLE PART. 1 G 7 1 3U H2SW 2001050800380 20010508 00380 SW 2001 5 8 HEEA072547 1 20010411 G 6330 206033506101 RESTRAINT BELL 206 206L3 1182108 SW TRANSMISSION WORN E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 21497 51518 BEARINGS WORN. REPLACED WITH SERVICEABLE PART. 1 G 7 1 3U H2SW 2001050800381 20010508 00381 SW 2001 5 8 HEEA072548 1 20010411 G 2810 206064611001 FUEL CELL BELL 206 206L1 1182107 SW FUSELAGE TORN E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 45RP 45521 LEAKING, FOUND SMALL TEAR AT FRONT OF CELL. 1 G 7 1 3U H2SW 2001050800382 20010508 00382 SW 2001 5 8 HEEA072549 1 20010411 G 2810 206064611001 FUEL CELL BELL 206 206L1 1182107 SW FUSELAGE LEAKING E HEEA K NONE K FLUID LOSS IN INSP/MAINT 1 SW 03 3178K 45765 MAIN FUEL CELL LEAKS. 1 G 7 1 3U H2SW 2001050800383 20010508 00383 SW 2001 5 8 HEEA072550 1 20010411 G 7714 206075681101 INDICATOR BELL 206 206L1 1182107 SW DUAL TACH MALFUNCTIONED E HEEA K NONE P NO WARNING INDICATION IN INSP/MAINT 1 SW 03 3178K 45765 DUAL TACH HAS NO LIGHT. 1 G 7 1 3U H2SW 2001050800384 20010508 00384 SW 2001 5 8 HEEA072551 1 20010411 G 7714 206075681101 INDICATOR BELL 206 206L1 1182107 SW DUAL TACH SPLIT E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 5007Q 45187 2 PERCENT SPLIT IN NEEDLE INDICATION. 1 G 7 1 3U H2SW 2001050800385 20010508 00385 SW 2001 5 8 HEEA072552 1 20010411 G 7714 206075681117 INDICATOR BELL 206 206L3 1182108 SW DUAL TACH STUCK E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 21497 51518 TURBINE NEEDLE STAYING AT ZERO AT TIMES AND VERY UNRELIABLE. 1 G 7 1 3U H2SW 2001050800386 20010508 00386 SW 2001 5 8 HEEA072553 1 20010411 G 7712 206075739103 INDICATOR BELL 206 206L3 1182108 SW TORQUEMETER FLUCTUATES E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 42EA 51542 INDICATOR FLUCTUATES 4 TO 5 PERCENT AT ALL TIMES. 1 G 7 1 3U H2SW 2001050800387 20010508 00387 SW 2001 5 8 HEEA072554 1 20010411 G 7712 206075739103 INDICATOR BELL 206 206L3 1182108 SW TORQUEMETER FLUCTUATES E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 81671 51301 FLUCTUATES 3 TO 5 PERCENT ABOVE 80 PERCENT TORQUE. 1 G 7 1 3U H2SW 2001050800388 20010508 00388 SW 2001 5 8 HEEA072555 1 20010411 G 7712 206075739103 INDICATOR BELL 206 206L1 1182107 SW TORQUEMETER FLUCTUATES E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 45RP 45521 TORQUE NEEDLE BOUNCES 2 TO 4 PERCENT. 1 G 7 1 3U H2SW 2001050800389 20010508 00389 SW 2001 5 8 HEEA072556 1 20010411 G 7712 206075739103 INDICATOR BELL 206 206L3 1182108 SW TORQUEMETER FLUCTUATES E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 53119 51575 FLUCTUATES 10 PERCENT AND INTERMITTENTLY STICKS AT 6 PERCENT AFTER SHUTDOWN. 1 G 7 1 3U H2SW 2001050800390 20010508 00390 SW 2001 5 8 HEEA072557 1 20010411 G 6730 206076062003 CYLINDER BELL 206 206L3 1182108 SW SERVO DAMAGED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 31077 51520 THE PILOT VALVE THROUGH BOLTS (2 EA) ARE VERY STIFF AND CANNOT BE MOVED BY HAND. STIFF FLIGHT CONTROLS. REPLACED WITH S ERVICEABLE SERVO. 1 G 7 1 3U H2SW 2001050800391 20010508 00391 SW 2001 5 8 HEEA072558 1 20010411 G 6730 206076062003 CYLINDER BELL 206 206L3 1182108 SW SERVO LEAKING E HEEA K NONE K FLUID LOSS IN INSP/MAINT 1 SW 03 6610Y 51419 LEAKING AT REAR SEAL. REPLACED WITH SERVICEABLE SERVO. 1 G 7 1 3U H2SW 2001050800392 20010508 00392 SW 2001 5 8 HEEA072559 1 20010411 G 3212 206369002 FLOAT BELL 206 206L1 1182107 SW MLG DAMAGED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 45RP 45521 HAS HOLE ON FRONT END. 1 G 7 1 3U H2SW 2001050800393 20010508 00393 SW 2001 5 8 HEEA072560 1 20010411 G 2821 222366621101 FUEL FILTER BELL 206 206L3 1182108 SW FUEL SYSTEM MALFUNCTIONED E HEEA K NONE P NO WARNING INDICATION IN INSP/MAINT 1 SW 03 30KH 51527 LIGHT WILL NOT COME ON. 1 G 7 1 3U H2SW 2001050800394 20010508 00394 SW 2001 5 8 HEEA072561 1 20010411 G 2821 222366621101 FUEL FILTER BELL 206 206L4 1182110 SW FUEL SYSTEM MALFUNCTIONED E HEEA K NONE P NO WARNING INDICATION IN INSP/MAINT 1 SW 03 7074W 52033 LIGHT STAYS ON. 1 G 7 1 3U NC H2SW 2001050800395 20010508 00395 SW 2001 5 8 HEEA072562 1 20010411 G 2821 222366621101 FUEL FILTER BELL 206 206L1 1182107 SW FUEL SYSTEM STUCK E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 3178K 45765 BYPASS BUTTON STICKS. SENT TO PUROFLOW CORP. FOR INSPECTION AND REPAIR. 1 G 7 1 3U H2SW 2001050800396 20010508 00396 SW 2001 5 8 HEEA072563 1 20010411 G 2821 222366621101 FUEL FILTER BELL 206 206L1 1182107 SW FUEL SYSTEM MALFUNCTIONED E HEEA K NONE P NO WARNING INDICATION IN INSP/MAINT 1 SW 03 45RP 45521 ELECTRICAL PIN IN FILTER HEAD BROKEN. REPLACED WITH SERVICEABLE FUEL FILTER ASSY. 1 G 7 1 3U H2SW 2001050800397 20010508 00397 GL 2001 5 8 HEEA072564 2 20010411 G 7420 23060816 LEAD BELL 206 206L3 1182108 SW ALLSN 250C 250C30 03013 GL IGNITER SHORTED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 6160Y 51609 ONE OF THE FOUR TANGS ON B RECEPTACLE END BROKEN. 1 G 7 1 3U 3 U H2SW E1GL 2001050800398 20010508 00398 GL 2001 5 8 HEEA072565 2 20010411 G 7323 252467711 GOVERNOR BELL 206 206L1 1182107 SW ALLSN 250C 250C28B 03013 GL ENGINE DIRTY E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 5019F 45244 WILL NOT RECOVER RPM AFTER COLLECTIVE POWER CHANGES. FOUND INTERIOR OF UNIT TO BE DIRTY WHICH COULD HAVE CAUSED GOVERNOR TO HANG AND HAVE HYSTERSIS PROBLEMS. 1 G 7 1 3U 3 U H2SW E1GL 2001050900094 20010509 00094 GL 2001 5 9 HEEA072566 2 20010411 G 7323 252469211 GOVERNOR BELL 206 206L1 1182107 SW ALLSN 250C 250C28B 03013 GL ENGINE MALFUNCTIONED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 45RP 45521 AIRCRAFT EXPERIENCES OVERSPEEDS ON LANDINGS AND DROOPS DURING TAKE OFF. REPLACED GOVERNOR ASSY. 1 G 7 1 3U 3 U H2SW E1GL 2001050900095 20010509 00095 GL 2001 5 9 HEEA072567 2 20010411 G 7323 252469211 GOVERNOR BELL 206 206L3 1182108 SW ALLSN 250C 250C30P 03013 GL ENGINE MALFUNCTIONED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 6610C 8138 51425 N2 SLOW TO RECOVER AFTER POWER CHANGES. GOVERNOR RESPONDED POORLY ON TEST BENCH. SLOPE RESPONDED SLOWLY. CLEANED INTER IOR AND UNIT TESTED OK. 1 G 7 1 3U 3 U H2SW E1GL 2001050900096 20010509 00096 GL 2001 5 9 HEEA072568 2 20010411 G 7320 25490925 FUEL CONTROL BELL 206 206L3 1182108 SW ALLSN 250C 250C30 03013 GL ENGINE FLUCTUATES E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 81671 51301 TORQUE FLUCTUATING 10 PERCENT ON TAKE OFF. PERFORMED PRELIMINARY INSPECTION AND FOUND EXCESSIVE SIDE PLAY AT THE CUTOFF LINKAGE. REPLACED AND UNIT TESTED OK. 1 G 7 1 3U 3 U H2SW E1GL 2001050900097 20010509 00097 GL 2001 5 9 HEEA072569 2 20010411 G 7320 25490925 FUEL CONTROL BELL 206 206L3 1182108 SW ALLSN 250C 250C30 03013 GL ENGINE MALFUNCTIONED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 81671 51301 STARTING PROBLEMS AND OSCILLATIONS ABOVE 80 PERCENT TORQUE. PERFORMED PRELIMINARY INSPECTION AND COULD NOT DUPLICATE PRO BLEM. 1 G 7 1 3U 3 U H2SW E1GL 2001050900098 20010509 00098 GL 2001 5 9 HEEA072570 2 20010411 G 7320 25490925 FUEL CONTROL BELL 206 206L1 1182107 SW ALLSN 250C 250C30 03013 GL ENGINE MALFUNCTIONED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 45RP 45521 HUNG STARTS IN THE 40 TO 50 PERCENT N1 RANGE. PERFORMED PRELIMINARY INSPECTION AND FOUND NO DISCREPANCIES. UNIT TESTED OK. 1 G 7 1 3U 3 U H2SW E1GL 2001050900099 20010509 00099 GL 2001 5 9 HEEA072571 2 20010411 G 7320 25490925 FUEL CONTROL BELL 206 206L3 1182108 SW ALLSN 250C 250C30 03013 GL ENGINE MALFUNCTIONED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 81671 51301 ENGINE LIGHTS OFF VERY HOT ON ALL STARTS AND THERE IS NO MORE ADJUSTMENT LEFT FOR LIGHTOFF DERICHMENT. IF ACCELERATION IS MOVED BACK, START IS STILL HOT AND ACCELERATION SLOW. PERFORMED PRELIMINARY INSPECTION AND FOUND NO DISCREPANCIES. U NIT TESTED OK. 1 G 7 1 3U 3 U H2SW E1GL 2001050800399 20010508 00399 SW 2001 5 8 HEEA072572 1 20010412 G 6322 206061432121 HOUSING BELL 407 407 SW BLOWER CRACKED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 510PH 53209 PART IS CRACKED. 1 G 7 1 3U O H2SW 2001050800400 20010508 00400 SW 2001 5 8 HEEA072573 1 20010412 G 7810 407062021101 DUCT BELL 407 407 SW EXHAUST CRACKED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 510PH 53209 PART IS CRACKED. 1 G 7 1 3U O H2SW 2001050800401 20010508 00401 SW 2001 5 8 HEEA072574 1 20010412 G 2840 407362005103 SWITCH BELL 407 407 SW LIGHT MALFUNCTIONED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 417PH 53038 LOW LEVEL LIGHT WILL NOT GO OUT. 1 G 7 1 3U O H2SW 2001050900100 20010509 00100 SW 2001 5 9 HEEA072576 1 20010412 G 3212 206373902103 RELIEF VALVE BELL 407 407 SW FLOAT LEAKING E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 493PH 53393 RELIEF VALVE ON FLOAT LEAKING. 1 G 7 1 3U O H2SW 2001050900101 20010509 00101 SW 2001 5 9 HEEA072577 1 20010412 G 6420 406312100101 BEARING 407012101111 BELL 407 407 SW T/R HUB WORN E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 467PH 53198 53142 TAIL ROTOR HUB BEARING WORN. 1 G 7 1 3U O H2SW 2001050900102 20010509 00102 SW 2001 5 9 HEEA072578 1 20010412 G 6420 406312100101 BEARING 407012101111 BELL 407 407 SW T/R HUB WORN E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 467PH 53198 53142 TAIL ROTOR HUB BEARING WORN. 1 G 7 1 3U O H2SW 2001050900103 20010509 00103 SW 2001 5 9 HEEA072579 1 20010412 G 6420 406312100101 BEARING 407012101111 BELL 407 407 SW T/R HUB WORN E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 467PH 53198 53142 TAIL ROTOR HUB BEARINGWORN. 1 G 7 1 3U O H2SW 2001050900104 20010509 00104 SW 2001 5 9 HEEA072580 1 20010412 G 2510 222320823130 SEAT BELT BELL 407 407 SW COCKPIT TORN E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 417PH 53038 SEAT BELT TAG TORN. 1 G 7 1 3U O H2SW 2001050900105 20010509 00105 SW 2001 5 9 HEEA072581 1 20010412 G 2820 AV23B11754 VALVE BELL 412 412 1182202 SW FUEL SYSTEM LEAKING E HEEA K NONE K FLUID LOSS IN INSP/MAINT 1 SW 03 7128R 36007 LEAKING SHAFT SEAL. REPLACED WITH SERVICEABLE PART. 1 G 7 2 4U H4SW 2001051000167 20010510 00167 EU 2001 5 10 HEEA072582 1 20010409 G 5531 350A1400200802 SPAR SNIAS 350 AS350B2 8680813 EU STABILIZER CHAFED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 350BZ 2653 SPAR INSIDE CHAFED FROM CONDUIT. REPLACED WITH SERVICEABLE PART. 1 G 7 1 3U H9EU 2001051000168 20010510 00168 EU 2001 5 10 HEEA072583 1 20010409 G 3213 350A41108602 CROSSTUBE SNIAS 350 AS350B2 8680813 EU MLG CHAFED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 350BZ 2653 CHAFED BY FLOAT ASSEMBLY. REPLACED WITH SERVICEABLE PART. 1 G 7 1 3U H9EU 2001051000169 20010510 00169 EU 2001 5 10 HEEA072584 1 20010409 G 3213 350A41108702 CROSSTUBE SNIAS 350 AS350B2 8680813 EU MLG CORRODED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 350BZ 2653 SURFACE CORROSION EXCEEDS COVERAGE AREA AND DEPTH LIMITS. REPLACED WITH SERVICEABLE PART. 1 G 7 1 3U H9EU 2001051000170 20010510 00170 2001 5 10 HEEA072585 4 20010411 G 3457 8143802240D GPS SNIAS 350 AS350B 8680801 EU COCKPIT FAILED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 973AE 3229 LOST POSITION. CANT FIND ITSELF. 1 G 7 1 3U H9EU 2001051000171 20010510 00171 2001 5 10 HEEA072586 4 20010411 G 3457 8143802240D GPS SNIAS 350 AS350B 8680801 EU COCKPIT DAMAGED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 970AE 3235 FACE PLATE DELAMINATED. 1 G 7 1 3U H9EU 2001051000172 20010510 00172 2001 5 10 HEEA072587 4 20010411 G 3421 504001790116 GYRO SNIAS 350 AS350B2 8680813 EU COCKPIT FAILED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 40466 3004 WOULD NOT FAST ERECT. REPLACED WITH SERVICEABLE PART. 1 G 7 1 3U H9EU 2001051000173 20010510 00173 EU 2001 5 10 HEEA072588 1 20010411 G 6510 552200 BEARING BOLKMS 105 BO105S 5626006 EU T/R DRIVESHAFT DAMAGED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 724MB S756 WHILE ROTATING M/R HEAD, NOTICED CLICKING SOUND COMING FROM BEARING ON TAILBOOM. REMOVED T/R DRIVESHAFT AND REPLACED ROU GH BEARING. 1 G 7 2 3U H3EU 2001050700556 20010507 00556 2001 5 7 HEEA072594 4 20010417 G 3450 071106603 RECEIVER SKRSKY S76 S76A 8143006 NE COCKPIT MALFUNCTIONED E HEEA K NONE L NO TEST IN INSP/MAINT 1 SW 03 1546G 760076 WILL NOT GIVE BEARING INFO OR AUDIO. PERFORMED PRELIMINARY INSPECTION AND FOUND HUNDREDS SECTION S101 TERMINAL #26 HAS B ROKEN WIRE AND VOLUME CONTROL NOISY. RESOLDERED WIRE ON S101 TERMINAL 26 AND CLEANED VOLUME CONTROL. REPAIRED. BENCH CHECK GOOD. 1 G 7 2 3U H1NE 2001050700557 20010507 00557 2001 5 7 HEEA072595 4 20010417 G 3451 066106602 TRANSCEIVER SKRSKY S76 S76A 8143006 NE DME WEAK E HEEA K NONE L NO TEST IN INSP/MAINT 1 SW 03 761PH 760224 WEAK RECEIVE AND TRANSMIT. 1 G 7 2 3U H1NE 2001050700558 20010507 00558 2001 5 7 HEEA072596 4 20010417 G 3454 066400700 RECEIVER SKRSKY S76 S76A 8143006 NE VOR MALFUNCTIONED E HEEA K NONE L NO TEST IN INSP/MAINT 1 SW 03 5435V 760158 CAUSES VOR GREEN NEEDLE TO INDICATE 15-20 DEGREES OFF. REPLACED I404, I406, I403, I407, C413, C430 AND C438. NO HELP. REPLACED I408 AND C438, I406. TROUBLESHOT AND REPAIRED A BROKEN FOIL UNDER I404. REPAIRED PROBLEM. RMI AND VOR BEARIN GS OUT OF TOLERANCE. ALIGNED THE VOR AND RMI BOARDS. BENCH CHECK GOOD. 1 G 7 2 3U H1NE 2001050700559 20010507 00559 2001 5 7 HEEA072597 4 20010419 G 2312 VFS10902 ANTENNA SKRSKY S76 S76A 8143006 NE VHF DAMAGED E HEEA K NONE L NO TEST IN INSP/MAINT 1 SW 03 911MJ 760231 REPORTED TO TRANSMIT GARBLED. SCRAPPED AND REPLACED WITH SERVICEABLE UNIT. 1 G 7 2 3U H1NE 2001050700560 20010507 00560 2001 5 7 HEEA072598 4 20010419 G 2340 A3016W INTERPHONE SKRSKY S76 S76A 8143006 NE COCKPIT MALFUNCTIONED E HEEA K NONE L NO TEST IN INSP/MAINT 1 SW 03 5128 760181 AFTER UNIT WARMS UP, TRANSMITS AND RECEIVES BROKEN. PERFORMED PRELIMINARY INSPECTION. FOUND AMP BOARD AR1 AND TRANSISTO R Q8 BAD, REPLACED SAME. REPAIRED. BENCH CHECK GOOD. 1 G 7 2 3U H1NE 2001050700561 20010507 00561 NE 2001 5 7 HEEA072599 1 20010419 G 2510 A1077B RELAY SKRSKY S76 S76A 8143006 NE COCKPIT FAILED E HEEA K NONE L NO TEST IN INSP/MAINT 1 SW 03 4253S 760035 WOULD NOT PULL WITH GENERATORS ON THE LINE, FOUND LOW RESISTANCE BETWEEN X1 AND X2. SENT TO PRECISION AVIONICS & INSTR. INC. FOR INSPECTION AND REPAIR. 1 G 7 2 3U H1NE 2001050700562 20010507 00562 SW 2001 5 7 HEEA072600 1 20010419 G 3340 ACR4F LIGHT BELL 412 412 1182202 SW EXTERNAL INOPERATIVE E HEEA K NONE L NO TEST IN INSP/MAINT 1 SW 03 3893N 33010 NOT WORKING. SENT TO OFFSHORE HELICOPTER SUPPORT FOR INSPECTION AND REPAIR. 1 G 7 2 4U H4SW 2001050900106 20010509 00106 SW 2001 5 9 HEEA072601 1 20010416 G 2822 205061635005 SWITCH BELL 412 412 1182202 SW BOOST PUMP MALFUNCTIONED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 BOOST PUMP LIGHT WILL NOT GO OUT. 1 G 7 2 4U H4SW 2001050900107 20010509 00107 NE 2001 5 9 HEEA072602 2 20010416 G 7532 3043023 BLEED VALVE BELL 412 412 1182202 SW PWA PT6T PT6T3B 52045 NE ENGINE MALFUNCTIONED E HEEA O OTHER J WARNING INDICATION CR CRUISE 1 SW 03 3893P 33012 CPPS62415 IN CRUISE FLIGHT OBSERVED A 6 PERCENT TORQUE SPLIT. REPLACED WITH SERVICEABLE PART. 1 G 7 2 4U 4 U H4SW E22EA 2001050900108 20010509 00108 SW 2001 5 9 HEEA072603 1 20010416 G 2435 200SGL132Q STARTER GEN BELL 206 206L1 1182107 SW ENGINE VIBRATION E HEEA O OTHER E VIBRATION/BUFFET CR CRUISE 1 SW 03 2761N 2032 45277 HIGH FREQUENCY VIBRATION. ALSO THERE IS A CONSIDERABLE AMOUNT OF RUST COLORED RESIDUE OR DUST COMING FROM THE FRONT BEA RING. REPLACED WITH SERVICEABLE PART. 1 G 7 1 3U H2SW 2001050900109 20010509 00109 NE 2001 5 9 HEEA072604 2 20010416 G 7323 25249994 GOVERNOR BELL 412 412 1182202 SW PWA PT6T PT6T3B 52045 NE NR 1 ENGINE FAILED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 3893L 33006 NR 1 ENGINE OSCILLATES DURING POWER TRANSITION AT APPROX. 80 PERCENT TORQUE. FOUND GOVERNOR WAS HANGING. FOUND INTERIOR OF UNIT VERY DIRTY WHICH CAUSED THE FLYWEIGHTS TO STICK. CLEANED FLYWEIGHTS AND REPLACED FLYWEIGHT PINS DUE TO WEAR. UNIT TESTED OK. 1 G 7 2 4U 4 U H4SW E22EA 2001050900110 20010509 00110 SW 2001 5 9 HEEA072605 1 20010416 G 6710 C4264215 SLEEVE BELL 206 206L3 1182108 SW M/R CONTROL LEAKING E HEEA K NONE K FLUID LOSS IN INSP/MAINT 1 SW 03 8587X 51464 CAUSING EXCESSIVE INTERNAL LEAKAGE DURING TESTING. SENT TO FORTNER ACCESSORY SERVICE CORP. FOR WARRANTY REPAIR. 1 G 7 1 3U H2SW 2001050900111 20010509 00111 GL 2001 5 9 HEEA072606 2 20010416 G 7421 CH34187A IGNITER BELL 206 206L3 1182108 SW ALLSN 250C 250C30 03013 GL ENGINE MALFUNCTIONED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 6610C 51425 AIRCRAFT HAS DELAYED LIGHT OFF AFTER ENGINE WASH. REPLACED WITH SERVICEABLE IGNITER. 1 G 7 1 3U 3 U H2SW E1GL 2001050900112 20010509 00112 SW 2001 5 9 HEEA072607 1 20010416 G 6730 206076031023 SERVO BELL 206 206L1 1182107 SW MAIN ROTOR STUCK E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 SPOOL STICKS IN SLEEVE OF LAP ASSY. SUSPECT DEFECTIVE LAPPING. 1 G 7 1 3U H2SW 2001050900113 20010509 00113 SW 2001 5 9 HEEA072608 1 20010416 G 6730 C4264113 PLUG 206076062003 BELL 206 206L3 1182108 SW CYLINDER STUCK E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 937S RH3037A 51258 FOUND PLUG STICKS IN SLEEVE AND SPRING STICKS ON SPOOL. SENT TO FORTNER ACCESSORY SERVICE CORP. FOR WARRANTY REPAIR. 1 G 7 1 3U H2SW 2001050900114 20010509 00114 SW 2001 5 9 HEEA072609 1 20010416 G 6730 SERVO 206076062003 BELL 206 206L3 1182108 SW MAIN ROTOR LEAKING E HEEA K NONE K FLUID LOSS IN INSP/MAINT 1 SW 03 RH0958 CAUSING EXTERNAL LEAKAGE OF SERVO DURING TESTING. FOUND DEFECTIVE LAPPING. SENT TO FORTNER ACCESSORY SERVICE CORP. FOR WARRANTY REPAIR. 1 G 7 1 3U H2SW 2001050900115 20010509 00115 SW 2001 5 9 HEEA072610 1 20010416 G 6730 SERVO 206076062003 BELL 206 206L3 1182108 SW MAIN ROTOR LEAKING E HEEA K NONE K FLUID LOSS IN INSP/MAINT 1 SW 03 49EA RH3886A 51507 CAUSING EXCESSIVE INTERNAL LEAKAGE. FOUND DEFECTIVE LAPPING. SENT TO FORTNER ACCESSORY SERVICE CORP. FOR WARRANTY REP AIR. 1 G 7 1 3U H2SW 2001050900116 20010509 00116 SW 2001 5 9 HEEA072611 1 20010416 G 6730 SERVO 206076062003 BELL 206 206L3 1182108 SW MAIN ROTOR LEAKING E HEEA K NONE K FLUID LOSS IN INSP/MAINT 1 SW 03 206FS RH1092 51506 CAUSING EXCESSIVE INTERNAL LEAKAGE. FOUND DEFECTIVE LAPPING. SENT TO FORTNER ACCESSORY SERVICE CORP. FOR WARRANTY REP AIR. 1 G 7 1 3U H2SW 2001050900117 20010509 00117 2001 5 9 HEEA072612 4 20010417 G 3444 071111400 CONNECTOR BELL 206 206L1 1182107 SW ALTIMETER LOOSE E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 5744Y 45465 ANTENNA CABLE CONNECTOR LOOSE FROM CABLE. INSPECTED ANTENNA AND FOUND BROKEN BEYOND REPAIR. SCRAPPED ANTENNA. 1 G 7 1 3U H2SW 2001050900118 20010509 00118 2001 5 9 HEEA072613 4 20010417 G 3444 071111401 ANTENNA BELL 206 206L3 1182108 SW RADAR ALTIMETER UNRELIABLE E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 141BH 51303 INTERMITTENT AND UNRELIABLE. 1 G 7 1 3U H2SW 2001050900119 20010509 00119 2001 5 9 HEEA072614 4 20010417 G 3444 071111401 ANTENNA BELL 206 206L3 1182108 SW RADAR ALTIMETER INACCURATE E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 30KH 51527 ANTENNA HAS A 50 FOOT ERROR. 1 G 7 1 3U H2SW 2001050900120 20010509 00120 2001 5 9 HEEA072615 4 20010417 G 3442 WIRE BELL 206 206L3 1182108 SW ANTENNA SEPARATED E K NONE O OTHER IN INSP/MAINT 1 SW 03 8591X 13278 51495 ANTENNA CABLE PULLED OUT. 1 G 7 1 3U H2SW 2001050900121 20010509 00121 2001 5 9 HEEA072616 4 20010417 G 3452 071119208 CONTROL UNIT BELL 412 412 1182202 SW COCKPIT MALFUNCTIONED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 108X 33115 DISPLAY BLANKS OUT WHEN CHANGING DIGITS. PERFORMED PRELIMINARY INSPECTION AND REPLACED DISPLAY LENS AND I203, I204, I205 AND I206 IC CHIPS. NO HELP. FOUND J303 FLEX CABLE BAD. REPLACED J303 CABLE, I303 IC CHIP, I306 IC CHIP AND I202 IC C HIP. NO HELP. 1 G 7 2 4U H4SW 2001050900122 20010509 00122 2001 5 9 HEEA072617 4 20010417 G 3454 069102505 TRANSCEIVER BELL 206 206L4 1182110 SW VOR SYSTEM WEAK E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 7077B 52037 WEAK RECEIVE. PERFORMED PRELIMINARY INSPECTION. FOUND MODULATION LOW AND WILL NOT ADJUST. REPLACED Q313, Q312 AND R505 . ALSO FOUND NAV RECEIVER WEAK. TROUBLESHOT AND FOUND SEVERAL COIL AND INDUCTORS FROZEN. REPLACED L202, L206, L300, L 301, L303 AND L304. ALSO REPLACED T205. COMM RECEIVER SENSITIVITY VERY WEAK AND WILL NOT ADJUST. 1 G 7 1 3U NC H2SW 2001050900123 20010509 00123 2001 5 9 HEEA072618 4 20010417 G 2312 064100900 TRANSCEIVER BELL 212 212 1181420 SW COCKPIT FAILED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 5736J 31140 ON INITIAL INSTALLATION UNIT WOULD NOT TRANSMIT DURING FUNCTIONAL TEST. FOUND MODULATION WEAK WHEN UNIT WAS COOL AND WOU LD GO UP AS UNIT WARMED UP. REPLACED CR325 DIODE AND REALIGNED TRANSMITTER. REPAIRED. BENCH CHECK GOOD. 1 G 7 1 4U H4SW 2001050900124 20010509 00124 2001 5 9 HEEA072619 4 20010417 G 2312 064102300 TRANSCEIVER BELL 412 412 1182202 SW COCKPIT FAILED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 2149S 36002 WILL NOT RECEIVE. REMOVED BROKEN PIN FROM RF CONNECTOR. REMOVED CORROSION FROM CHASIS. ADJUSTED C/N SQUELCH, CARRIER S QUELCH, MIC GAIN AND SIDETONE. BENCH CHECK GOOD. 1 G 7 2 4U H4SW 2001050900125 20010509 00125 2001 5 9 HEEA072620 4 20010417 G 2312 064102300 TRANSCEIVER BELL 412 412 1182202 SW COCKPIT OUT OF ADJ E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 142PH 33150 TRANSMIT SCRATCHY. FOUND RF CONNECTOR LOOSE ON UNIT. TIGHTENED RF CONNECTOR. ALIGNED TRANSMITTER. REPAIRED. ADJUSTED CARRIER SQUELCH. REMOVED CORROSION FROM CHASIS. BENCH CHECK GOOD. 1 G 7 2 4U H4SW 2001050900126 20010509 00126 2001 5 9 HEEA072621 4 20010417 G 2312 064102300 TRANSCEIVER BELL 412 412 1182202 SW COCKPIT INOPERATIVE E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 2148K 36001 INOPERATIVE, WILL NOT COME ON. FOUND FUSE OPEN. REPLACED HEADER AND APPLIED HUMISEAL TO HEADER FOR CORROSION CONTROL. ADJUSTED C/N SQUELCH, MIC GAIN, AND SIDETONE. BENCH CHECK GOOD. 1 G 7 2 4U H4SW 2001050900127 20010509 00127 2001 5 9 HEEA072622 4 20010417 G 2312 064102302 RECEIVER BELL 214 214ST 1182106 SW COCKPIT FAILED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 59805 28141 SQUELCH STAYS ON. ALIGNED RECEIVER SEVERAL TIMES. SWAPPED Q317 AND Q319 TRANSISTORS. REALIGNED RECEIVER BOARD. REPLAC ED Q304, Q305, Q306, Q307, Q308, Q317, Q318, Q319, Q320 AND Q321 TRANSISTORS AND I301 IC CHIP. ALSO REPLACED BROKEN NAM EPLATE. ADJUSTED VCO VOLTAGE AND REALIGNED RECEIVER. REPLACED RECEIVER BOARD. BENCH CHECK GOOD. 2 G 7 2 4U H10SW 2001050900128 20010509 00128 2001 5 9 HEEA072623 4 20010417 G 2312 064105430 TRANSCEIVER BELL 407 407 SW COCKPIT MALFUNCTIONED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 724PH 53327 INTERMITTENT RADIO WOULD NOT BREAK SQUELCH. FOUND LENS BAD AND MHZ SWITCH HOUSING BAD. REPLACED SWITCH HOUSING, LENS AN D FOUND POWER OUT LOW. ADJUSTED. REPLACED COIL T604. REPAIRED. ALSO FOUND MODULATION DISTORTED. REPLACED TRANSISTOR KIT Q124, Q130. REPAIRED. BENCH CHECK GOOD. 1 G 7 1 3U O H2SW 2001050900129 20010509 00129 2001 5 9 HEEA072624 4 20010417 G 3422 060001500 GYRO BELL 206 206L3 1182108 SW COCKPIT FAILED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 31077 51520 D.G. DOES NOT TRACK IN TURNS. 1 G 7 1 3U H2SW 2001050900130 20010509 00130 2001 5 9 HEEA072625 4 20010417 G 3422 060001500 GYRO BELL 206 206L3 1182108 SW COCKPIT MALFUNCTIONED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 31077 51520 CAUSES HIS TO STICK AND BE ERRATIC. 1 G 7 1 3U H2SW 2001050900131 20010509 00131 2001 5 9 HEEA072626 4 20010417 G 3444 066106103 INDICATOR BELL 206 206L3 1182108 SW RADAR ALTIMETER ERRATIC E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 8591X 51495 ERRATIC AND INACCURATE READINGS. 1 G 7 1 3U H2SW 2001050900132 20010509 00132 2001 5 9 HEEA072627 4 20010417 G 3444 066106103 INDICATOR BELL 206 206L1 1182107 SW RADAR ALTIMETER ERRATIC E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 45RP 45521 RADAR ALTIMETER ERRATIC. 1 G 7 1 3U H2SW 2001050900133 20010509 00133 2001 5 9 HEEA072628 4 20010417 G 3444 066106103 INDICATOR BELL 206 206L3 1182108 SW RADAR ALTIMETER FAILED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 141BH 51303 WILL NOT INDICATE CORRECT ALTITUDE. 1 G 7 1 3U H2SW 2001050900134 20010509 00134 2001 5 9 HEEA072629 4 20010417 G 3444 066106103 INDICATOR BELL 206 206L3 1182108 SW RADAR ALTIMETER ERRATIC E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 8587X 51464 ABOVE 300 FEET READINGS ARE ERRATIC OVER ROUGH TERRAIN. 1 G 7 1 3U H2SW 2001050900135 20010509 00135 2001 5 9 HEEA072631 4 20010417 G 3444 066106103 INDICATOR BELL 206 206L3 1182108 SW RADAR ALTIMETER INACCURATE E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 30KH 51527 50 FOOT INDICATING ERROR. 1 G 7 1 3U H2SW 2001050900136 20010509 00136 2001 5 9 HEEA072632 4 20010417 G 3452 066106200 TRANSCEIVER BELL 206 206L3 1182108 SW COCKPIT DEFECTIVE E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 3116P 51530 KNOB DEFECTIVE. PERFORMED PRELIMINARY INSPECTION. REPLACED KNOB SHAFT. TRANSMIT POWER WEAK. INSTALLED V101 REPAIRED. FOUND UNIT MISSING IDENT BUTTON. INSTALLED BUTTON. ADJUSTED PULSE WIDTH. BENCH CHECK GOOD. 1 G 7 1 3U H2SW 2001050900137 20010509 00137 2001 5 9 HEEA072633 4 20010417 G 3452 066106200 TRANSPONDER BELL 206 206L3 1182108 SW COCKPIT FAILED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 4835 51131 TRANSPONDER WILL NOT TRANSMIT. PERFORMED PRELIMINARY INSPECTION. FOUND UNIT NOT RECEIVING OR TRANSMITTING. FOUND V101 TUBE BAD. REPLACED V101 TUBE. REPAIRED. ALSO FOUND SWITCH PANEL BAD. REPLACED. BENCH CHECK GOOD. 1 G 7 1 3U H2SW 2001050900138 20010509 00138 2001 5 9 HEEA072634 4 20010417 G 3452 066106200 TRANSPONDER BELL 206 206L4 1182110 SW COCKPIT MALFUNCTIONED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 7077F 52038 REPLY LIGHT INOPERATIVE. 1 G 7 1 3U NC H2SW 2001050900139 20010509 00139 2001 5 9 HEEA072635 4 20010417 G 3452 066106200 TRANSPONDER BELL 206 206L3 1182108 SW COCKPIT FAILED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 6160Y 51609 WILL NOT COME ON. 1 G 7 1 3U H2SW 2001050900140 20010509 00140 2001 5 9 HEEA072636 4 20010417 G 3452 066106200 TRANSPONDER BELL 206 206L3 1182108 SW COCKPIT INTERMITTENT E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 31821 51076 TRANSMITS INTERMITTENTLY. MTL LOW. CANNOT MEASURE FREQUENCY. 1 G 7 1 3U H2SW 2001050900141 20010509 00141 2001 5 9 HEEA072637 4 20010417 G 3451 066106600 TRANSCEIVER BELL 212 212 1181420 SW DME MALFUNCTIONED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 5009N 30936 NO OUTPUT TO THE INDICATOR. 1 G 7 1 4U H4SW 2001050900142 20010509 00142 2001 5 9 HEEA072638 4 20010417 G 3431 066107800 RECEIVER BELL 412 412 1182202 SW VOR MALFUNCTIONED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 7128R 36007 MARKER BEACON WOULD NOT TEST. PERFORMED PRELIMINARY INSPECTION AND REPLACED FRONT CONNECTOR J6341 BECAUSE OF A BAD PIN. REPAIRED. BENCH CHECK GOOD. 1 G 7 2 4U H4SW 2001050900143 20010509 00143 2001 5 9 HEEA072639 4 20010417 G 3431 066107800 RECEIVER BELL 412 412 1182202 SW GLIDE SLOPE INOPERATIVE E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 2148K 36001 GLIDE SLOPE INOPERATIVE. PERFORMED PRELIMINARY INSPECTION AND REPLACED TRANSISTOR Q311. REPAIRED. BENCH CHECK GOOD. 1 G 7 2 4U H4SW 2001050900144 20010509 00144 2001 5 9 HEEA072640 4 20010417 G 3431 066107800 RECEIVER BELL 412 412 1182202 SW GLIDE SLOPE INOPERATIVE E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 142PH 33150 GLIDE SLOPE INOPERATIVE. PERFORMED PRELIMINARY INSPECTION AND FOUND GS NEEDLE PEGS OUT WHEN VIBRATED. REPLACED RECEPTAC LES I-5 ON GLIDESLOPE BOARD. REPAIRED. ADJUSTED VOR HEADING. ADJUSTED HI/LOW SENSE ON MARKER BEACON. BENCH CHECK GOO D. 1 G 7 2 4U H4SW 2001050900145 20010509 00145 2001 5 9 HEEA072641 4 20010417 G 3444 066304400 INDICATOR BELL 412 412 1182202 SW RADAR ALTIMETER ERRATIC E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 2149S 36002 ERRATIC IN FLIGHT. 1 G 7 2 4U H4SW 2001050900146 20010509 00146 2001 5 9 HEEA072642 4 20010417 G 3444 066305401 INDICATOR BELL 206 206L3 1182108 SW RADAR ALTIMETER INACCURATE E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 8591X 51495 ERRATIC AND INACCURATE. 1 G 7 1 3U H2SW 2001050900147 20010509 00147 2001 5 9 HEEA072643 4 20010417 G 3444 066305401 INDICATOR BELL 206 206L3 1182108 SW RADAR ALTIMETER MALFUNCTIONED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 8593X 51509 WILL NOT INDICATE OR POWER UP. 1 G 7 1 3U H2SW 2001050900148 20010509 00148 2001 5 9 HEEA072644 4 20010417 G 3444 066305401 INDICATOR BELL 407 407 SW RADAR ALTIMETER INTERMITTENT E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 4999 53323 INTERMITTENT.. 1 G 7 1 3U O H2SW 2001050900149 20010509 00149 2001 5 9 HEEA072645 4 20010417 G 3444 066305401 INDICATOR BELL 206 206L3 1182108 SW RADAR ALTIMETER READS LOW E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 6603X 51412 NEEDLE READS LOW. SENT TO HONEYWELL, KANSAS FOR WARRANTY REPAIR. 1 G 7 1 3U H2SW 2001050900150 20010509 00150 2001 5 9 HEEA072646 4 20010417 G 3444 066305401 INDICATOR BELL 206 206L3 1182108 SW RADAR ALTIMETER INTERMITTENT E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 141BH 51303 INTERMITTENT, UNRELIABLE WHEN WORKING. SENT TO HONEYWELL, KANSAS FOR WARRANTY REPAIR. 1 G 7 1 3U H2SW 2001050900151 20010509 00151 2001 5 9 HEEA072647 4 20010417 G 3432 066400700 RECEIVER BELL 412 412 1182202 SW VOR FAILED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 3911L 33023 WILL NOT RECEIVE. PERFORMED PRELIMINARY INSPECTION. REPLACED OPEN FUSE F501. REPAIRED PROBLEM. ADJUSTED LOCALIZER DEV IATION. BENCH CHECK GOOD. 1 G 7 2 4U H4SW 2001050900152 20010509 00152 2001 5 9 HEEA072648 4 20010417 G 3453 066402600 RECEIVER BELL 206 206L3 1182108 SW LORAN MALFUNCTIONED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 8590X 51494 UNABLE TO PUT IN A DIFFERENT WAYPOINT DUE TO KNOB OUT. PERFORMED PRELIMINARY INSPECTION. FOUND S202 SWITCH BROKEN AND R ETAINER RING MISSING FROM END OF PULL SCAN KNOB SHAFT. REPLACED S202 SWITCH AND RETAINER RING. REPAIRED. BENCH CHECK GOOD. 1 G 7 1 3U H2SW 2001050900153 20010509 00153 2001 5 9 HEEA072649 4 20010417 G 3453 066402600 RECEIVER BELL 206 206L3 1182108 SW LORAN INOPERATIVE E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 8588X 51486 INOPERATIVE. NO DISPLAY. 1 G 7 1 3U H2SW 2001050900154 20010509 00154 2001 5 9 HEEA072651 4 20010418 G 3453 066402600 RECEIVER BELL 206 206L3 1182108 SW LORAN FAILED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 8592X 51508 SCREEN GOES BLANK AFTER EXTENDED USE. SUSPECT OVERHEATING DUE TO FAULTY COOLING FAN. 1 G 7 1 3U H2SW 2001050900155 20010509 00155 SW 2001 5 9 HEEA072652 1 20010418 G 2436 163404751 VOLT REGULATOR BELL 206 206L3 1182108 SW ELECTRICAL FAILED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 30KH 51527 GENERATOR KICKS OFF LINE. 1 G 7 1 3U H2SW 2001050900156 20010509 00156 GL 2001 5 9 HEEA072653 2 20010418 G 7261 174000101 FILTER BELL 206 206L1 1182107 SW ALLSN 250C 250C30P 03013 GL ENGINE OIL LEAKING E HEEA K NONE K FLUID LOSS IN INSP/MAINT 1 SW 03 5007Q 45187 COULD NOT GET FACET FILTER TO STOP LEAKING. 1 G 7 1 3U 3 U H2SW E1GL 2001050900157 20010509 00157 GL 2001 5 9 HEEA072654 2 20010418 G 7261 174000103 FILTER BELL 206 206L3 1182108 SW ALLSN 250C 250C30P 03013 GL ENGINE OIL LEAKING E HEEA K NONE K FLUID LOSS IN INSP/MAINT 1 SW 03 6610C 51425 UNABLE TO STOP FILTER HOUSING FROM LEAKING. SENT TO PUROLATOR FACETS FOR INSPECTION AND REPAIR. 1 G 7 1 3U 3 U H2SW E1GL 2003081500050 20030815 00050 SW 2003 8 15 HEEA072655 1 20010418 G 7910 1740352 INDICATOR BELL 206 206L1 1182107 SW ENGINE OIL DAMAGED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 45RP 45521 BUTTON WOULD NOT EXTEND DURING BYPASS CHECK. REPLACED WITH SERVICEABLE PART. 1 G 7 1 3U H2SW 2001050900158 20010509 00158 NE 2001 5 9 HEEA072657 2 20010418 G 7412 103815504 EXCITER BELL 412 412 1182202 SW PWA PT6T PT6T3B 52045 NE ENGINE WEAK E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 2149S 36002 WEAK. 1 G 7 2 4U 4 U H4SW E22EA 2001050900159 20010509 00159 2001 5 9 HEEA072658 4 20010418 G 3425 1113025 INDICATOR BELL 412 412 1182202 SW HSI INTERMITTENT E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 2149S 36002 CDI OFF FLAG DISPLAYS INTERMITTENTLY. SENT TO MASCO FOR WARRANTY REPAIR. 1 G 7 2 4U H4SW 2001050900160 20010509 00160 2001 5 9 HEEA072659 4 20010418 G 3425 1113025 INDICATOR BELL 412 412 1182202 SW HSI PRECESSES E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 2149S 36002 PRECESSES. 1 G 7 2 4U H4SW 2001050900161 20010509 00161 2001 5 9 HEEA072660 4 20010418 G 3421 1113034 INDICATOR BELL 412 412 1182202 SW COCKPIT MALFUNCTIONED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 2261D 33076 RT FLAG STICKS TO THE RIGHT. 1 G 7 2 4U H4SW 2001050900162 20010509 00162 2001 5 9 HEEA072661 4 20010418 G 3421 1113034 INDICATOR BELL 412 412 1182202 SW COCKPIT MALFUNCTIONED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 2261D 33076 ADI TUMBLES WHEN POWER IS APPLIED. 1 G 7 2 4U H4SW 2001050900163 20010509 00163 GL 2001 5 9 HEEA072662 2 20010418 G 7261 174000101 FILTER BELL 206 206L3 1182108 SW ALLSN 250C 250C30 03013 GL ENGINE OIL LEAKING E HEEA K NONE K FLUID LOSS IN INSP/MAINT 1 SW 03 3116P 51530 LEAKING. 1 G 7 1 3U 3 U H2SW E1GL 2001050900164 20010509 00164 2001 5 9 HEEA072663 4 20010418 G 2300 122024102 CONTROL UNIT BELL 407 407 SW COCKPIT INOPERATIVE E HEEA K NONE L NO TEST IN INSP/MAINT 1 SW 03 495PH 53397 INOPERATIVE. LIGHTS WONT PULSE AND WONT ILLUMINATE. 1 G 7 1 3U O H2SW 2001050900165 20010509 00165 SW 2001 5 9 HEEA072664 1 20010418 G 3340 122024102 CONTROL UNIT BELL 407 407 SW COCKPIT FAILED E HEEA K NONE L NO TEST IN INSP/MAINT 1 SW 03 719PH 53266 WHEN BATTERY SWITCH IS TURNED ON, FWD LANDING WOULD NOT TURN OFF. ALSO FWD LIGHT WOULD NOT PULSATE. 1 G 7 1 3U O H2SW 2001050900166 20010509 00166 2001 5 9 HEEA072666 4 20010418 G 2311 4000038 TRANSMITTER BELL 206 206L4 1182110 SW COCKPIT FAILED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 7074W 52033 CANNOT GET SQUELCH TEST OR ANY TRANSMISSION FROM ANY CHANNEL ON FM RADIO. REPLACED VOLUME CONTROL, VOLUME KNOB AND FRONT PANEL. REPAIRED. BENCH CHECK GOOD. 1 G 7 1 3U NC H2SW 2001050900167 20010509 00167 2001 5 9 HEEA072667 4 20010418 G 2311 4000038 TRANSMITTER BELL 412 412 1182202 SW COCKPIT MALFUNCTIONED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 6559Z 36019 RATCHETING VOLUME KNOB. REPLACED VOLUME POTENTIOMETER. REPAIRED PROBLEM. BENCH CHECK GOOD. 1 G 7 2 4U H4SW 2001050900168 20010509 00168 2001 5 9 HEEA072668 4 20010418 G 2311 4000038 TRANSMITTER BELL 206 206L3 1182108 SW COCKPIT INTERMITTENT E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 6251X 51552 INTERMITTENT. REPLACED VOLUME POTENTIOMETER, VOLUME KNOB AND CHANNEL KNOB. REPAIRED PROBLEM. BENCH CHECK GOOD. 1 G 7 1 3U H2SW 2001050900169 20010509 00169 2001 5 9 HEEA072669 4 20010418 G 2312 4000103000 TRANSCEIVER BELL 206 206L1 1182107 SW COCKPIT MALFUNCTIONED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 5744Y 45465 HIGH LEVEL OF SQUELCH BLEEDING OVER INTO ALL AUDIO SYSTEMS. FOUND CORROSION ON UNIT. CLEANED CORROSION FROM UNIT. FOUN D INTERMITTENT TRANSMIT ON HIGHER FREQUENCIES 469.9875 MHZ. ALIGNED TRANSMITTER TO SPECS. BENCH CHECK GOOD. 1 G 7 1 3U H2SW 2001050900170 20010509 00170 2001 5 9 HEEA072670 4 20010418 G 2312 4000103000 TRANSCEIVER BELL 206 206L1 1182107 SW COCKPIT INTERMITTENT E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 5744Y 45465 FM UHF BAND INTERMITTENTLY DOES NOT TRANSMIT OR RECEIVE. 1 G 7 1 3U H2SW 2001050900171 20010509 00171 2001 5 9 HEEA072671 4 20010418 G 2211 4033089901 COMPUTER BELL 412 412 1182202 SW COCKPIT MALFUNCTIONED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 108X 33115 WONT HOLD ALTITUDE. 1 G 7 2 4U H4SW 2001050900172 20010509 00172 SW 2001 5 9 HEEA072672 1 20010418 G 6710 412001300105 BELLCRANK BELL 412 412 1182202 SW MAIN ROTOR WORN E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 3893N 33010 BEARINGS WORN. REPLACED WITH SERVICEABLE PART. 1 G 7 2 4U H4SW 2001050900173 20010509 00173 SW 2001 5 9 HEEA072673 1 20010418 G 6220 412010216105 BEARING BELL 412 412 1182202 SW MAIN ROTOR DAMAGED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 2148K 36001 BEARING RETAINING RING POPPED OUT OF GROOVE. ALSO BEARING SPINS IN HOUSING. REPLACED WITH SERVICEABLE PART. 1 G 7 2 4U H4SW 2001050900174 20010509 00174 SW 2001 5 9 HEEA072674 1 20010418 G 6220 412010216107 BEARING BELL 412 412 1182202 SW MAIN ROTOR FROZEN E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 1202T 33112 BEARING FROZEN. REPLACED WITH SERVICEABLE PART. 1 G 7 2 4U H4SW 2001051000118 20010510 00118 SW 2001 5 10 HEEA072675 1 20010418 G 5610 412018060111 CAM BELL 412 412 1182202 SW WINDOW WORN E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 6559Z 36019 WORN WINDOW. SCRAPPED AND REPLACED WITH SERVICEABLE PART. 1 G 7 2 4U H4SW 2001050900175 20010509 00175 SW 2001 5 9 HEEA072676 1 20010418 G 5310 STRUCTURE BELL 412 412 1182202 SW ENGINE BAY DELAMINATED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 108X 33115 ENGINE BAY STRUCTURE DELAMINATED. 1 G 7 2 4U H4SW 2001050900176 20010509 00176 SW 2001 5 9 HEEA072677 1 20010418 G 6220 412030437103 CAP BELL 412 412 1182202 SW MAIN ROTOR DAMAGED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 2298Z 33077 RUBBER IS DAMAGED. 1 G 7 2 4U H4SW 2001050900177 20010509 00177 SW 2001 5 9 HEEA072678 1 20010418 G 6220 412030437103 CAP BELL 412 412 1182202 SW MAIN ROTOR DAMAGED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 3893N 33010 RUBBER LORD MOUNT WEAR FROM OIL. REPLACED WITH SERVICEABLE PART. 1 G 7 2 4U H4SW 2001050900178 20010509 00178 SW 2001 5 9 HEEA072679 1 20010418 G 6220 412030437103 CAP BELL 412 412 1182202 SW MAIN ROTOR DAMAGED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 3911L 33023 RUBBER WORN. REPLACED WITH SERVICEABLE PART. 1 G 7 2 4U H4SW 2001050900179 20010509 00179 SW 2001 5 9 HEEA072680 1 20010418 G 6220 412030437103 CAP BELL 412 412 1182202 SW MAIN ROTOR DAMAGED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 7128R 36007 RUBBER EXTRUDED. 1 G 7 2 4U H4SW 2001050900180 20010509 00180 SW 2001 5 9 HEEA072681 1 20010419 G 6710 214001347005 ACTUATOR BELL 412 412 1182202 SW MAIN ROTOR STUCK E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 1202T 33112 FORCE TRIM STICKING. 1 G 7 2 4U H4SW 2001050900181 20010509 00181 SW 2001 5 9 HEEA072682 1 20010419 G 7330 206364601101 TRANSMITTER BELL 206 206L3 1182108 SW FUEL SYSTEM MALFUNCTIONED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 UNABLE TO CALIBRATE FUEL SYSTEM. 1 G 7 1 3U H2SW 2001050900182 20010509 00182 SW 2001 5 9 HEEA072683 1 20010419 G 8011 214060056103 STARTER BELL 214 214ST 1182106 SW ENGINE FAILED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 WILL NOT ENGAGE OR SPIN. 2 G 7 2 4U H10SW 2001050900183 20010509 00183 SW 2001 5 9 HEEA072684 1 20010419 G 5260 212075418105 ACTUATOR BELL 412 412 1182202 SW STEP STUCK E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 STICKS EXENDED. 1 G 7 2 4U H4SW 2001050900184 20010509 00184 2001 5 9 HEEA072685 4 20010419 G 3413 44600045800 INDICATOR BELL 407 407 SW VERTICAL SPEED STUCK E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 493PH 53393 VERTICAL SPEED INDICATOR STICKING. SENT TO MASCO FOR INSPECTION AND REPAIR. 1 G 7 1 3U O H2SW 2001050900185 20010509 00185 SW 2001 5 9 HEEA072686 1 20010419 G 7333 473203003 SIGNAL COND UNIT BELL 412 412 1182202 SW TRANS PUMPS FAILED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 1202T 33112 NR 1 AND 2 TRANSFER PUMPS WOULD NOT SHUT OFF AFTER FORWARD FUEL TANKS EMPTIED. 1 G 7 2 4U H4SW 2001050900186 20010509 00186 SW 2001 5 9 HEEA072687 1 20010419 G 7333 473203003 SIGNAL COND UNIT BELL 412 412 1182202 SW FUEL SYSTEM INOPERATIVE E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 142PH 33150 CAUSES FUEL QUANTITY INDICATOR RO READ ZERO. 1 G 7 2 4U H4SW 2001050900187 20010509 00187 SW 2001 5 9 HEEA072688 1 20010419 G 7333 473203003 SIGNAL COND UNIT BELL 412 412 1182202 SW FUEL SYSTEM INOPERATIVE E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 107X 33113 LOW FUEL LIGHT COMES ON AT 1320 LBS. 1 G 7 2 4U H4SW 2001050900188 20010509 00188 SW 2001 5 9 HEEA072689 1 20010419 G 7333 473203003 SIGNAL COND UNIT BELL 412 412 1182202 SW FUEL SYSTEM FAILED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 107X 33113 LOW FUEL LIGHT COMES ON AT 1320 LBS. 1 G 7 2 4U H4SW 2001050900189 20010509 00189 SW 2001 5 9 HEEA072690 1 20010419 G 2140 S5008EC3 HOSE BELL 206 206L3 1182108 SW HEATER LEAKING E HEEA K NONE K FLUID LOSS IN INSP/MAINT 1 SW 03 31077 51520 HOSE ASSY WIRE BRAIDING IS CHAFED AND HOSE IS LEAKING. SCRAPPED AND REPLACED WITH SERVICEABLE UNIT. 1 G 7 1 3U H2SW 2001051000119 20010510 00119 SW 2001 5 10 HEEA072691 1 20010419 G 2140 S5008EC3 HOSE BELL 206 206L3 1182108 SW HEATER CRACKED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 41128 51134 FERRULE CRACKED ON HOSE. SCRAPPED AND REPLACED WITH SERVICEABLE UNIT. 1 G 7 1 3U H2SW 2001050900190 20010509 00190 SW 2001 5 9 HEEA072692 1 20010419 G 2140 S5008EC3 HOSE BELL 206 206L3 1182108 SW HEATER LEAKING E HEEA K NONE K FLUID LOSS IN INSP/MAINT 1 SW 03 206LS 51070 HEATER HOSE LEAKING FROM FITTINGS. SCRAPPED AND REPLACED WITH SERVICEABLE UNIT. 1 G 7 1 3U H2SW 2001050900191 20010509 00191 SW 2001 5 9 HEEA072693 1 20010419 G 2140 S50301 VALVE BELL 206 206L3 1182108 SW CABIN HEAT CORRODED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 206LS 51070 BALL BEARING AND SPRING CORRODED INSIDE OF VALVE. SCRAPPED AND REPLACED WITH SERVICEABLE UNIT. 1 G 7 1 3U H2SW 2001050900192 20010509 00192 SW 2001 5 9 HEEA072694 1 20010419 G 2140 S50301 VALVE BELL 206 206L3 1182108 SW CABIN HEAT CORRODED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 41128 51134 CORRODED BALL BEARING AND SPRING. SCRAPPED AND REPLACED WITH SERVICEABLE UNIT. 1 G 7 1 3U H2SW 2001050900193 20010509 00193 2001 5 9 HEEA072695 4 20010419 G 3418 SC628P HORN BELL 206 206L3 1182108 SW COCKPIT MALFUNCTIONED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 21497 51518 HORN HAS STEADY SOUND ONLY, MUST PULSATE. SCRAPPED AND REPLACED WITH SERVICEABLE UNIT. 1 G 7 1 3U H2SW 2001050900194 20010509 00194 SW 2001 5 9 HEEA072696 1 20010419 G 7714 SC628P HORN BELL 206 206L1 1182107 SW COCKPIT INTERMITTENT E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 45RP 45521 WORKS INTERMITTENTLY. REPLACED WITH SERVICEABLE UNIT. 1 G 7 1 3U H2SW 2001050900195 20010509 00195 SW 2001 5 9 HEEA072697 1 20010419 G 2140 R02221 VENT BELL 412 412 1182202 SW HEATER INOPERATIVE E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 2261D 33076 HEATER INOPERATIVE. REPLACED WITH SERVICEABLE PART. 1 G 7 2 4U H4SW 2001050900196 20010509 00196 2001 5 9 HEEA072698 4 20010419 G 3444 DMC632 ANTENNA BELL 206 206L3 1182108 SW RADAR ALTIMETER WEAK E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 8594X 51531 CORRODED CAUSING WEAK RECEPTION. REPLACED WITH SERVICEABLE PART. 1 G 7 1 3U H2SW 2001050900197 20010509 00197 2001 5 9 HEEA072699 4 20010419 G 3444 DMC634A ANTENNA BELL 412 412 1182202 SW RADAR ALTIMETER DAMAGED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 3893N 33010 BASE IS DAMAGED. BASE IS CRACKED. SCRAPPED AND REPLACED WITH SERVICEABLE PART. 1 G 7 2 4U H4SW 2001050900198 20010509 00198 2001 5 9 HEEA072700 4 20010419 G 2562 ELT910 ELT BELL 206 206L4 1182110 SW CABIN MALFUNCTIONED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 7077F 52038 WOULD NOT SHUT OFF. REPLACED WITH SERVICEABLE PART. 1 G 7 1 3U NC H2SW 2001050900199 20010509 00199 SW 2001 5 9 HEEA072701 1 20010419 G 2844 BSE20630G TRANSDUCER BELL 206 206L3 1182108 SW FUEL PRESSURE INTERMITTENT E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 4835 51131 FUEL PRESSURE GAUGE INTERMITTENTLY PEGS OUT. 1 G 7 1 3U H2SW 2001050900200 20010509 00200 NE 2001 5 9 HEEA072702 2 20010419 G 7420 CH5339901 LEAD BELL 412 412 1182202 SW PWA PT6T PT6T3B 52045 NE IGNITER BURNED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 2149S 36002 BURN HOLE IN LEAD. 1 G 7 2 4U 4 U H4SW E22EA 2001050900201 20010509 00201 2001 5 9 HEEA072703 4 20010419 G 3423 CB2100T6C COMPASS BELL 412 412 1182202 SW COCKPIT LOW E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 3893N 33010 LOW ON FLUID. 1 G 7 2 4U H4SW 2001050900202 20010509 00202 2001 5 9 HEEA072704 4 20010419 G 3423 C2300DL4B COMPASS BELL 206 206L1 1182107 SW COCKPIT INACCURATE E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 3178K 45765 INDICATES 25 DEGREES OFF FROM ACTUAL COURSE. REPLACED WITH SERVICEABLE PART. 1 G 7 1 3U H2SW 2001050900203 20010509 00203 2001 5 9 HEEA072705 4 20010419 G 3423 CB2100T6D COMPASS BELL 214 214ST 1182106 SW COCKPIT INTERMITTENT E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 5748M 28102 HAS FRICTION LIGHT INTERMITTENT, WILL NOT CALIBRATE. 2 G 7 2 4U H10SW 2001050900204 20010509 00204 2001 5 9 HEEA072706 4 20010419 G 3442 MI5851345 INDICATOR BELL 212 212 1181420 SW RADAR FAILED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 5010F 30936 DOES NOT PAINT TARGETS. FOUND UNIT HAS NO NOISE, ADJUSTED AUTOMATIC NOISE CONTROL. TROUBLESHOT VIDEO BOARD AND REPLACED R1450 RESISTOR. REPAIRED. BENCH CHECK GOOD. 1 G 7 1 4U H4SW 2001050900205 20010509 00205 2001 5 9 HEEA072707 4 20010419 G 3442 MI5851345 INDICATOR BELL 412 412 1182202 SW RADAR FAILED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 6559Z 36019 PAINTS FALSE TARGETS AND BAD TEST PATTERN. PERFORMED PRELIMINARY INSPECTION AND ADJUSTED ANC AND INTENSITY. BENCH CHECK GOOD. 1 G 7 2 4U H4SW 2001050900206 20010509 00206 2001 5 9 HEEA072708 4 20010419 G 3442 MI5851345 INDICATOR BELL 412 412 1182202 SW RADAR FAILED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 2149S 36002 WOULD NOT GO INTO TEST MODE. ALSO HAD FALSE TARGETS ON HIGH RANGE SETTINGS. FOUND DISPLAY TEST PATTERN INTERMITTENTLY D ROPPING OFF. FOUND LOGIC NR 1 BOARD CAUSING PROBLEM. REPLACED LOGIC #1 BOARD FROM P40 INDICATOR. REPAIRED. BENCH CHE CK GOOD. 1 G 7 2 4U H4SW 2001050900207 20010509 00207 2001 5 9 HEEA072709 4 20010419 G 3442 MI5851345 INDICATOR BELL 412 412 1182202 SW RADAR INACCURATE E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 2149S 36002 NOT PAINTING PROPER PICTURE. PERFORMED PRELIMINARY INSPECTION. FOUND SPIKES ON TEST PATTERN. TROUBLESHOT AND FOUND C12 20 ON LOGIC NR 1 BOARD BAD. REPLACED C1220. REPAIRED. BENCH CHECK GOOD. 1 G 7 2 4U H4SW 2001050900208 20010509 00208 2001 5 9 HEEA072710 4 20010419 G 3442 MI5851345 INDICATOR BELL 412 412 1182202 SW RADAR INACCURATE E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 2149S 36002 WHEN RADAR IS IN STANDBY MODE AZIMUTH LINES ARE VISIBLE. PERFORMED PRELIMINARY INSPECTION. FOUND LOGIC NR 2 BOARD IC U1 346 HAS COLD SOLDER JOINT ON PIN 9. RESOLDERED IC. REPAIRED. BENCH CHECK GOOD. 1 G 7 2 4U H4SW 2001050900209 20010509 00209 2001 5 9 HEEA072711 4 20010419 G 2561 PHI10090 LIFE VEST BELL 206 206L4 1182110 SW CABIN WILL NOT TEST E HEEA K NONE L NO TEST IN INSP/MAINT 1 SW 03 7074W 52033 FAILED TO PASS 3 MONTH INFLATION TEST. 1 G 7 1 3U NC H2SW 2001050900211 20010509 00211 2001 5 9 HEEA072713 4 20010419 G 2340 AA34300 INTERPHONE BELL 412 412 1182202 SW CABIN INOPERATIVE E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 107X 33113 INOPERATIVE - LOW RECEIVE AUDIO. 1 G 7 2 4U H4SW 2001050900212 20010509 00212 2001 5 9 HEEA072714 4 20010419 G 2340 AA34300 INTERPHONE BELL 206 206L1 1182107 SW CABIN MALFUNCTIONED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 27766 45312 SENSITIVITY TOO LOW. 1 G 7 1 3U H2SW 2001050900213 20010509 00213 2001 5 9 HEEA072715 4 20010419 G 2340 AA95759 CONTROLLER SNIAS 350 AS350B 8680801 EU AUDIO MALFUNCTIONED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 971AE 3230 MIC STAYS HOT IN VOX POSITION. SENT TO NORTHERN AIRBORNE TECHNOLOGY FOR INSPECTION AND REPAIR. 1 G 7 1 3U H9EU 2001050900214 20010509 00214 2001 5 9 HEEA072716 4 20010419 G 2340 A3016W INTERPHONE BELL 412 412 1182202 SW CABIN WEAK E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 2298Z 33077 BOTH VHF RADIOS WEAK AND GARBLED. PERFORMED PRELIMINARY INSPECTION. FOUND TRANSMIT LEVELS R36-R41 SET TOO LOW. SET LEV ELS TO 9V. REPAIRED. ALSO FOUND LIGHT PANEL AND VOLUME AND TRANSMIT KNOBS BAD. REPLACED. BENCH CHECK GOOD. 1 G 7 2 4U H4SW 2001050900215 20010509 00215 2001 5 9 HEEA072717 4 20010419 G 2340 A3016W INTERPHONE BELL 212 212 1181420 SW CABIN MALFUNCTIONED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 1074C 30989 NO AUDIO OUT AT ANY POSITION ON ROTARY SELECTOR. FOUND R36-R41 TRANSMIT LEVELS ADJUSTED ALL THE WAY DOWN. ALSO FOUND SW ITCHES S1, S2, S3, S11, LIGHT PANEL, TRANSMIT AND VOLUME KNOBS ALL BAD. ADJUSTED TRANSMIT LEVELS ON R36-R41 AND REPLACE D ALL BAD PARTS. REPAIRED. BENCH CHECK GOOD. 1 G 7 1 4U H4SW 2001050900216 20010509 00216 2001 5 9 HEEA072718 4 20010419 G 2564 ACR108BP LIFE RAFT BELL 206 206L3 1182108 SW EMERGENCY EQUIP DISLODGED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 30KH 51527 DURING POSTFLIGHT INSPECTION, NOTICED THAT LIFE RAFT WAS COMING OUT OF COVER. FURTHER INVESTIGATION FOUND THAT INFLATIO N BOTTLE VALVE WAS SLOWLY LEAKING GAS INTO THE RAFT. SENT TO OFFSHORE HELICOPTER SUPPORT FOR WARRANTY REPAIR. 1 G 7 1 3U H2SW 2001050900217 20010509 00217 SW 2001 5 9 HEEA072719 1 20010419 G 3030 HEATER BELL 412 412 1182202 SW PITOT TUBE INOPERATIVE E HEEA K NONE L NO TEST IN INSP/MAINT 1 SW 03 2261D 33076 HEATER INOPERATIVE. REPLACED WITH SERVICEABLE PART. 1 G 7 2 4U H4SW 2001050900218 20010509 00218 SW 2001 5 9 HEEA072720 1 20010419 G 2422 ASH5845 INVERTER BELL 212 212 1181420 SW ELECTRICAL FAILED E HEEA K NONE L NO TEST IN INSP/MAINT 1 SW 03 102PH 30899 NO VOLTAGE OUTPUT. 1 G 7 1 4U H4SW 2001050900219 20010509 00219 SW 2001 5 9 HEEA072721 1 20010419 G 6320 412040123101 QUILL ASSY BELL 412 412 1182202 SW ROTOR BRAKE LEAKING E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 142PH 33150 ROTORBRAKE QUILL LEAKING. REPLACED WITH SERVICEABLE PART. 1 G 7 2 4U H4SW 2001050900220 20010509 00220 SW 2001 5 9 HEEA072722 1 20010419 G 5320 412060802117 BRACKET BELL 412 412 1182202 SW FUSELAGE WORN E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 3893L 33006 WORN. REPLACED WITH SERVICEABLE PART. 1 G 7 2 4U H4SW 2001050900221 20010509 00221 SW 2001 5 9 HEEA072723 1 20010419 G 5210 BEARING BELL 412 412 1182202 SW HINGE WORN E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 2261D 33076 BEARINGS WORN AND MAKING MUD. REPLACED WITH SERVICEABLE PART. 1 G 7 2 4U H4SW 2001050900222 20010509 00222 SW 2001 5 9 HEEA072724 1 20010419 G 5210 412060804101 HINGE BELL 412 412 1182202 SW PAX DOOR BROKEN E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 107X 33113 BROKEN. REPLACED WITH SERVICEABLE PART. 1 G 7 2 4U H4SW 2001050900223 20010509 00223 SW 2001 5 9 HEEA072725 1 20010419 G 5330 412070528107 PANEL BELL 412 412 1182202 SW FUSELAGE CRACKED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 1202T 33112 CRACKED. REPLACED WITH SERVICEABLE PART. 1 G 7 2 4U H4SW 2001050900224 20010509 00224 SW 2001 5 9 HEEA072727 1 20010419 G 2422 412075101103 INVERTER BELL 412 412 1182202 SW ELECTRICAL FAILED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 2261D 33076 WOULD NOT TURN ON. 1 G 7 2 4U H4SW 2001050900225 20010509 00225 2001 5 9 HEEA072728 4 20010419 G 3442 PLATE BELL 412 412 1182202 SW ANTENNA MISSING E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 6559Z 36019 FACE PLATE MISSING. 1 G 7 2 4U H4SW 2001050900226 20010509 00226 2001 5 9 HEEA072729 4 20010419 G 2211 4025008918 COMPUTER BELL 412 412 1182202 SW AFCS FAILED E HEEA K NONE L NO TEST IN INSP/MAINT 1 SW 03 3911L 33023 KICK OFF IN FLIGHT AND WANDERS AFTER SET IN CRUISE FLIGHT. REPLACED WITH SERVICEABLE PART. 1 G 7 2 4U H4SW 2001050900227 20010509 00227 SW 2001 5 9 HEEA072730 1 20010419 G 6220 407010101101 YOKE BELL 407 407 SW MAIN ROTOR HEAD DAMAGED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 724PH 2481 53327 AT 2500 HOUR INSPECTION FOUND YOKE DAMAGED IN WEB AREA. ITEM WAS SENT ON FOR ULTRASONIC INSPECTION. 1 G 7 1 3U O H2SW 2001051000174 20010510 00174 2001 5 10 HEEA072731 4 20010416 G 3457 8143902240B GPS SNIAS 350 AS350B 8680801 EU COCKPIT FAILED E HEEA O OTHER B SMOKE/FUMES/ODORS/SPARKS CL CLIMB 1 SW 03 855PH 3351 ON CLIMB, GPS SCREEN WENT BLANK AND COCKPIT FILLED WITH A BURNT ELECTRICAL ODOR. REPLACED WITH SERVICEABLE PART. 1 G 7 1 3U H9EU 2001051000175 20010510 00175 2001 5 10 HEEA072732 4 20010417 G 2312 069102525 TRANSCEIVER SNIAS 350 AS350B2 8680813 EU COCKPIT FAILED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 6095S 2777 DOES NOT TRANSMIT OR RECEIVE. FOUND VCO TO BE BAD. 1 G 7 1 3U H9EU 2001051000176 20010510 00176 2001 5 10 HEEA072733 4 20010417 G 3444 066106103 INDICATOR SNIAS 350 AS350B2 8680813 EU RADAR ALTIMETER MALFUNCTIONED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 6095S 2777 WILL NOT SELF TEST PROPERLY. 1 G 7 1 3U H9EU 2001051000177 20010510 00177 EU 2001 5 10 HEEA072734 1 20010419 G 2422 SS50 INVERTER SNIAS 350 AS350B 8680801 EU ELELCTRICAL FAILED E HEEA K NONE L NO TEST IN INSP/MAINT 1 SW 03 970AE 689 3235 NOT CHARGING MEDICAL EQUIPMENT. 1 G 7 1 3U H9EU 2001050900228 20010509 00228 SW 2001 5 9 HEEA072746 1 20010423 G 2435 206062200113 STARTER GEN BELL 407 407 SW ENGINE FAILED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 740PH 276 53435 FAILED 300 HOUR INSPECTION. 1 G 7 1 3U O H2SW 2001050900229 20010509 00229 SW 2001 5 9 HEEA072747 1 20010423 G 6720 C807382 CONTROL ROD BELL 407 407 SW TAIL ROTOR INTERFERENCE E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 998SP 127 53403 INSPECTION OF INTERFERENCE BETWEEN T/R CONTROL TUBE AND N1 TELEFLEX CABLE IN ROOF BEAM. INSPECTION DUE TO FINDING A N1 TELEFLEX CABLE ROUTED THROUGH THE WRONG LIGHTENING HOLE AND INTERFERING WITH THE T/R CONTROL TUBE. 1 G 7 1 3U O H2SW 2001050900230 20010509 00230 SW 2001 5 9 HEEA072748 1 20010423 G 2913 214076334101 PUMP BELL 214 214ST 1182106 SW HYD SYSTEM LEAKING E HEEA A UNSCHED LANDING K J FLUID LOSS WARNING INDICATION CR CRUISE 1 SW 03 59806 28140 WHILE IN CRUISE FLIGHT, LOST UTILITY HYDRAULIC POWER. RETURNED TO BASE FOR MAINTENANCE. 2 G 7 2 4U H10SW 2001050900231 20010509 00231 SW 2001 5 9 HEEA072749 1 20010424 G 8011 214060056103 STARTER BELL 214 214ST 1182106 SW ENGINE FAILED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 KICKING OFF AT START. 2 G 7 2 4U H10SW 2001050900232 20010509 00232 SW 2001 5 9 HEEA072751 1 20010424 G 6300 214030603111 SUPPORT BRACKET BELL 214 214ST 1182106 SW MAIN ROTOR MISMANUFACTURED E HEEA K NONE W INADEQUATE Q C IN INSP/MAINT 1 SW 03 BEARING DOES NOT FIT IN BEARING BORE. 2 G 7 2 4U H10SW 2001051000120 20010510 00120 SW 2001 5 10 HEEA072752 1 20010424 G 6300 214030603111 SUPPORT BELL 214 214ST 1182106 SW MAIN ROTOR MISMANUFACTURED E HEEA K NONE W INADEQUATE Q C IN INSP/MAINT 1 SW 03 BEARING DOES NOT FIT IN BEARING BORE. 2 G 7 2 4U H10SW 2001051000121 20010510 00121 SW 2001 5 10 HEEA072753 1 20010424 G 2730 214001970111 ACTUATOR BELL 214 214ST 1182106 SW NR 1 ELEVATOR MALFUNCTIONED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 NR 1 ELEVATOR WONT STAY ON LINE. 2 G 7 2 4U H10SW 2001051000122 20010510 00122 SW 2001 5 10 HEEA072754 1 20010424 G 6300 206001364001 TRUNNION BELL 206 206L3 1182108 SW MAIN ROTOR DR RATCHETING E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 BEARING RATCHETING. 1 G 7 1 3U H2SW 2001051000123 20010510 00123 SW 2001 5 10 HEEA072762 1 20010427 G 6710 214001347005 ACTUATOR BELL 214 214ST 1182106 SW ROTARY STUCK E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 STICKS INTERMITTENTLY. 2 G 7 2 4U H10SW 2001051000124 20010510 00124 SW 2001 5 10 HEEA072763 1 20010427 G 8011 214060056103 STARTER BELL 214 214ST 1182106 SW ENGINE FAILED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 WILL NOT START ON AIRCRAFT BATTERIES. 2 G 7 2 4U H10SW 2001051000125 20010510 00125 SW 2001 5 10 HEEA072764 1 20010427 G 8011 214060056103 STARTER BELL 214 214ST 1182106 SW ENGINE FAILED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 WILL NOT START ON AIRCRAFT BATTERIES. 2 G 7 2 4U H10SW 2001051000126 20010510 00126 SW 2001 5 10 HEEA072765 1 20010427 G 2730 214001970111 ACTUATOR BELL 214 214ST 1182106 SW ELEVATOR MALFUNCTIONED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 NR 1 ELEVATOR KICKS OFF LINE. 2 G 7 2 4U H10SW 2001051000127 20010510 00127 SW 2001 5 10 HEEA072766 1 20010427 G 8011 214060056103 STARTER BELL 214 214ST 1182106 SW ENGINE FAILED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 WILL NOT ENGAGE. 2 G 7 2 4U H10SW 2001051000178 20010510 00178 EU 2001 5 10 HEEA072767 1 20010423 G 5510 STRUCTURE SNIAS 350 AS350B 8680801 EU STABILIZER CRACKED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 854PH 887 3248 CRACKED. 1 G 7 1 3U H9EU 2001051500433 20010515 00433 NE 2001 5 15 HEEA072890 2 20010501 G 7200 70BM041720 TURBINE SNIAS 350 AS350B 8680801 EU TMECA ARRIEL ARRIEL1D NE ENGINE FAILED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 973AE 831 3229 22126 HIGH OIL CONSUMPTION. SENT TO TURBOMECA FOR CREDIT AGAINST REPLACEMENT PART PURCHASED. 1 G 7 1 3U 3 U H9EU E19EU 2001051500434 20010515 00434 NE 2001 5 15 HEEA072891 2 20010501 G 7200 70BM041720 TURBINE SNIAS 350 AS350B 8680801 EU TMECA ARRIEL ARRIEL1D NE ENGINE FAILED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 971AE 685 3230 22072 HIGH OIL CONSUMPTION. SENT TO TURBOMECA FOR CREDIT AGAINST REPLACEMENT PART PURCHASED. 1 G 7 1 3U 3 U H9EU E19EU 2001051500442 20010515 00442 SW 2001 5 15 HEEA072893 1 20010430 G 6210 206015001115 BLADE BELL 206 206L3 1182108 SW MAIN ROTOR DAMAGED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 8592X 120 51508 NUMBER ONE FINGER ON UPPER SURFACE TRAILING EDGE HAS 7 INCHES OF THE FINGER MISSING. SENT TO BELL HELICOPTER TEXTRON FOR CREDIT. 1 G 7 1 3U H2SW 2001051500443 20010515 00443 SW 2001 5 15 HEEA072894 1 20010430 G 6300 214040844109 RETAINER BELL 214 214ST 1182106 SW M/R DRIVE CORRODED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 PITTING ON SPRAGS. SENT TO BELL HELICOPTER TEXTRON FOR CREDIT. 2 G 7 2 4U H10SW 2001051500444 20010515 00444 SW 2001 5 15 HEEA072895 1 20010501 G 2910 212076176001 TUBE BELL 412 412 1182202 SW HYD SYSTEM CRACKED E HEEA O OTHER J WARNING INDICATION CR CRUISE 1 SW 03 3911L 33023 DURING CRUISE FLIGHT THE NR 1 HYDRAULIC SYSTEM LIGHT CAME ON. MAINTENANCE FOUND A CRACKED TUBE. 1 G 7 2 4U H4SW 2001051500445 20010515 00445 SW 2001 5 15 HEEA072896 1 20010501 G 2910 M832481906 O-RING BELL 214 214ST 1182106 SW HYD MOTOR LEAKING E HEEA O OTHER K J FLUID LOSS WARNING INDICATION NR NOT REPORTED 1 SW 03 59806 28140 THE UTILITY HYDRAULIC SYSTEM FAILED IN FLIGHT. MAINTENANCE REPLACED LEAKING O-RINGS ON HYDRAULIC MOTOR. 2 G 7 2 4U H10SW 2001051500446 20010515 00446 SW 2001 5 15 HEEA072897 1 20010501 G 2910 M832481904 O-RING BELL 214 214ST 1182106 SW HYD MOTOR LEAKING E HEEA O OTHER K J FLUID LOSS WARNING INDICATION NR NOT REPORTED 1 SW 03 59806 28140 THE UTILITY HYDRAULIC SYSTEM FAILED IN FLIGHT. MAINTENANCE REPLACED LEAKING O-RINGS ON HYDRAULIC MOTOR. 2 G 7 2 4U H10SW 2001051500447 20010515 00447 SW 2001 5 15 HEEA072898 1 20010501 G 2910 214076333103 MOTOR BELL 214 214ST 1182106 SW HYD SYSTEM SEIZED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 59806 28140 THE UTILITY HYDRAULIC SYSTEM FAILED IN FLIGHT. MAINTENANCE REPLACED SEIZED HYDRAULIC MOTOR. 2 G 7 2 4U H10SW 2001051500448 20010515 00448 SW 2001 5 15 HEEA072899 1 20010501 G 6230 2005712103D BOLT BELL 206 206L1 1182107 SW SWASHPLATE CORRODED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 5014V 45217 CORROSION PITTING ON SURFACE OF BOLTS. REPLACED WITH SERVICEABLE BOLTS. 1 G 7 1 3U H2SW 2001051500449 20010515 00449 SW 2001 5 15 HEEA072900 1 20010501 G 3040 204070907001 CONVERTER BELL 412 412 1182202 SW WINDSHIELD WIPER INOPERATIVE E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 6559Z 36019 CONVERTER INOPERATIVE. 1 G 7 2 4U H4SW 2001051500450 20010515 00450 SW 2001 5 15 HEEA072901 1 20010501 G 2140 205072277009 VALVE BELL 412 412 1182202 SW HEATER FAILED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 1202T 33112 WILL NOT REGULATE TEMPERATURE, STAYS FULL HOT. 1 G 7 2 4U H4SW 2001051500451 20010515 00451 SW 2001 5 15 HEEA072902 1 20010501 G 5230 STRUCTURE BELL 206 206L3 1182108 SW CARGO DOOR CRACKED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 6160Y 51609 CRACKED IN SEVERAL PLACES. REPLACED WITH SERVICEABLE PART. 1 G 7 1 3U H2SW 2001051500452 20010515 00452 SW 2001 5 15 HEEA072903 1 20010501 G 6710 206001343001 ELBOW BELL 206 206L1 1182107 SW CYCLIC CORRODED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 5014V 45217 CORRODED BEYOND LIMITS. REPLACED WITH SERVICEABLE PART. 1 G 7 1 3U H2SW 2001051500453 20010515 00453 SW 2001 5 15 HEEA072904 1 20010501 G 6710 206001344001 CYCLIC STICK BELL 206 206L1 1182107 SW COCKPIT CORRODED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 5014V 45217 CORRODED BEYOND LIMITS. REPLACED WITH SERVICEABLE PART. 1 G 7 1 3U H2SW 2001051500454 20010515 00454 SW 2001 5 15 HEEA072905 1 20010501 G 6710 206001396001 SHAFT BELL 206 206L3 1182108 SW CYCLIC STICK STRIPPED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 31077 51520 THREADS STRIPPED ON SHAFT; PILOT WAS UNABLE TO FRICTION DOWN CYCLIC STICK. SCRAPPED AND REPLACED WITH SERVICEABLE PART. 1 G 7 1 3U H2SW 2001051500455 20010515 00455 SW 2001 5 15 HEEA072906 1 20010501 G 6710 206001397101 PIVOT SUPPORT BELL 206 206L3 1182108 SW CYCLIC DAMAGED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 206LS 51070 BORE FOR BARREL NUTS DAMAGED BEYOND LIMITS. SCRAPPED AND REPLACED WITH SERVICEABLE PART. 1 G 7 1 3U H2SW 2001051500456 20010515 00456 SW 2001 5 15 HEEA072907 1 20010501 G 6710 BEARING BELL 206 206L1 1182107 SW BELLCRANK DAMAGED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 5019F RE1927 45244 BEARING UNSTAKED. REPLACED WITH SERVICEABLE PART. 1 G 7 1 3U H2SW 2001051500457 20010515 00457 SW 2001 5 15 HEEA072908 1 20010501 G 6710 BEARING BELL 206 206L1 1182107 SW BELLCRANK WORN E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 45RP RE1303 45521 WORN BEARINGS. REPLACED WITH SERVICEABLE PART. 1 G 7 1 3U H2SW 2001051500458 20010515 00458 SW 2001 5 15 HEEA072909 1 20010501 G 6710 BEARING BELL 206 206L1 1182107 SW BELLCRANK DAMAGED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 45RP RE3050 45521 CENTER BEARING UNSTAKED. REPLACED WITH SERVICEABLE PART. 1 G 7 1 3U H2SW 2001051500459 20010515 00459 SW 2001 5 15 HEEA072910 1 20010501 G 6710 BEARING BELL 206 206L1 1182107 SW BELLCRANK WORN E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 5019F 45244 WORN BEARING. REPLACED WITH SERVICEABLE PART. 1 G 7 1 3U H2SW 2001051500460 20010515 00460 SW 2001 5 15 HEEA072911 1 20010501 G 6710 BEARING BELL 206 206L3 1182108 SW BELLCRANK DAMAGED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 21497 51518 BEARING UNSTAKED. REPLACED WITH SERVICEABLE PART. 1 G 7 1 3U H2SW 2001051500461 20010515 00461 SW 2001 5 15 HEEA072912 1 20010501 G 6710 WASHER BELL 206 206L4 1182110 SW BELLCRANK UNBONDED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 7077F 52038 WASHER UNBONDED AND BEARINGS WORN. REPLACED WITH SERVICEABLE PART. 1 G 7 1 3U NC H2SW 2001051500462 20010515 00462 SW 2001 5 15 HEEA072913 1 20010501 G 6710 BEARING BELL 206 206L1 1182107 SW BELLCRANK WORN E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 45RP 45521 WORN BEARINGS. REPLACED WITH SERVICEABLE PART. 1 G 7 1 3U H2SW 2001051500463 20010515 00463 SW 2001 5 15 HEEA072914 1 20010501 G 6710 PAD BELL 206 206L3 1182108 SW BELLCRANK UNBONDED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 41128 51134 BUFFER PADS NEAR BEARINGS UNBONDED. REPLACED WITH SERVICEABLE PART. 1 G 7 1 3U H2SW 2001072600082 20010726 00082 GL 2001 7 26 HEEA073007 2 20010511 G 7261 6892846 LINE BELL 407 407 SW ALLSN 250C 250C47B GL COMPRESSOR CHAFED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 417PH 53038 CAE847194 LINE IS CHAFED. REPLACED LINE. 1 G 7 1 3U 3 U O H2SW E1GL 2001072600084 20010726 00084 NE 2001 7 26 HEEA073008 1 20010511 G 2435 6854424 SEAL SKRSKY S76 S76A 8143006 NE ALLSN 250C 250C30S 03013 GL STARTER GEN DISLODGED E HEEA A UNSCHED LANDING J WARNING INDICATION CR CRUISE 1 SW 03 1546K 760082 CAE890071S IN CRUISE FLIGHT, NR 1 ENGINE OIL PRESSURE BEGAN TO FLUCTUATE BETWEEN GREEN ARC AND LOWER RED ARC. MAINTENANCE FOUND STA RTER GENERATOR SEAL UNSEATED. REPLACED, SERVICED ENGINE OIL SYSTEM AND RETURNED AIRCRAFT TO SERVICE. 1 G 7 2 3U 3 U H1NE E1GL 2001072600086 20010726 00086 NE 2001 7 26 HEEA073009 1 20010511 G 3212 VALVE SKRSKY S76 S76A 8143006 NE FLOAT BOTTLE LEAKING E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 1545K 760047 WHILE IN FLIGHT THE LT NOSE FLOAT ASSEMBLY STARTED TO DEPLOY. MAINTENANCE FOUND FLOAT VALVE LEAKING INTERNALY AND STARTE D TO INFLATE BAG. 1 G 7 2 3U H1NE 2001080300087 20010803 00087 2001 8 3 HEEA073010 4 20010514 G 3140 LIGHT COCKPIT ILLUMINATED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 INSTRUMENT PANEL LIGHT WILL NOT EXTINGUISH. 2001072600090 20010726 00090 NE 2001 7 26 HEEA073011 2 20010518 G 7230 BLADE SNIAS 350 AS350B 8680801 EU TMECA ARRIEL ARRIEL1D NE COMPRESSOR CRACKED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 971AE 720 3230 22072 CRACKED COMPRESSOR BLADE. 1 G 7 1 3U 3 U H9EU E19EU 2001072600096 20010726 00096 NE 2001 7 26 HEEA073012 2 20010518 G 7230 BLADE SNIAS 350 AS350B 8680801 EU TMECA ARRIEL ARRIEL1D NE COMPRESSOR CRACKED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 971AE 720 3230 22072 CRACKED COMPRESSOR BLADE. 1 G 7 1 3U 3 U H9EU E19EU 2001072600102 20010726 00102 SW 2001 7 26 HEEA073013 1 20010507 G 2450 HARNESS BELL 412 412 1182202 SW COCKPIT CHAFED E HEEA A UNSCHED LANDING B SMOKE/FUMES/ODORS/SPARKS CR CRUISE 1 SW 03 142PH 33150 WHILE IN CRUISE FLIGHT THE 115 VOLT AFCS CIRCUIT BREAKER POPPED. MAINTENANCE TURNED BATTERY POWER ON AND THE MASTER CAUT ION PANEL CIRCUIT BREAKER POPPED ALSO, WITH VISIBLE SMOKE. FOUND CHAFED WIRE BUNDLE WHERE IT EXITS WINDSHIELD POST AREA AT FORWARD EDGE OF R/H PANEL. 1 G 7 2 4U H4SW 2001072600113 20010726 00113 SW 2001 7 26 HEEA073014 1 20010507 G 7933 407375004101 INDICATOR BELL 407 407 SW COCKPIT READS HIGH E HEEA K NONE N FALSE WARNING IN INSP/MAINT 1 SW 03 740PH 53435 READS HIGH 150+ AT TIMES THEN GOES TO 130 WHICH IS STILL 5 TO 10 PSI HIGH PER DIRECT READING GAUGE. SENT TO BELL HELICOP TER TEXTRON FOR CREDIT AGAINST REPLACEMENT PART PURCHASED. REFERENCE: DMR#715195. 1 G 7 1 3U O H2SW 2001072600120 20010726 00120 SW 2001 7 26 HEEA073015 1 20010507 G 6300 407310203101 MOUNT BELL 407 407 SW MAIN ROTOR SEPARATED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 491PH 991 53386 MOUNT SEPARATED. 1 G 7 1 3U O H2SW 2001072600131 20010726 00131 SW 2001 7 26 HEEA073016 1 20010507 G 2424 206075447101 VOLT REGULATOR BELL 407 407 SW ELECTRICAL FAILED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 612PH 53199 WILL NOT PICK UP LOAD. 1 G 7 1 3U O H2SW 2001072600137 20010726 00137 SW 2001 7 26 HEEA073017 1 20010507 G 6321 206340301101 DISK BELL 407 407 SW ROTOR BRAKE WORN E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 467PH 3135 53142 WORN. SENT TO BELL HELICOPTER TEXTRON FOR CREDIT AGAINST REPLACEMENT PART PURCHASED. REFERENCE: DMR#715175. 1 G 7 1 3U O H2SW 2001072600145 20010726 00145 SW 2001 7 26 HEEA073022 1 20010507 G 6730 212076005105 CYLINDER BELL 412 412EP 1182205 SW M/R CONTROL LEAKING E HEEA K NONE K FLUID LOSS IN INSP/MAINT 1 SW 03 6106C 196 36257 LEAKING FROM BOTTOM WEEP HOLE. 1 G 7 2 4U H4SW 2001072600146 20010726 00146 SW 2001 7 26 HEEA073023 1 20010507 G 2822 407362013101 PRESSURE SWITCH BELL 407 407 SW BOOST PUMP FAILED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 495PH 53397 LEFT HAND BOOST PUMP LIGHT WOULD NOT COME ON. 1 G 7 1 3U O H2SW 2001072600148 20010726 00148 SW 2001 7 26 HEEA073024 1 20010507 G 7921 406360500101 COOLER BELL 407 407 SW ENGINE OIL LEAKING E HEEA K NONE K FLUID LOSS IN INSP/MAINT 1 SW 03 510PH 53209 COOLER LEAKING. 1 G 7 1 3U O H2SW 2001072600150 20010726 00150 SW 2001 7 26 HEEA073025 1 20010507 G 6410 406016100119 BLADE BELL 407 407 SW TAIL ROTOR DAMAGED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 720PH 53277 VOID BETWEEN SKIN AND BLOCK. 1 G 7 1 3U O H2SW 2001072600151 20010726 00151 SW 2001 7 26 HEEA073026 1 20010507 G 3246 407050201101 CROSSTUBE BELL 407 407 SW MLG CORRODED E HEEA K NONE W INADEQUATE Q C IN INSP/MAINT 1 SW 03 409PH 4056 53059 CORROSION, SENDING IN FOR EVALUATION DUE TO POSSIBLE MFG. DEFECT. 1 G 7 1 3U O H2SW 2001072600153 20010726 00153 SW 2001 7 26 HEEA073027 1 20010507 G 6520 406040400117FM GEARBOX BELL 407 407 SW TAIL ROTOR MAKING METAL E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 720PH 2282 53277 TAIL ROTOR GEARBOX MAKING METAL. 1 G 7 1 3U O H2SW 2001072600154 20010726 00154 SW 2001 7 26 HEEA073028 1 20010507 G 6230 406010401117 SWASHPLATE BELL 407 407 SW MAIN ROTOR ROUGH E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 490PH 1231 53378 SWASHPLATE BEARING HAS A ROUGH SOUND WHEN ROTATED. 1 G 7 1 3U O H2SW 2001072600155 20010726 00155 SW 2001 7 26 HEEA073029 1 20010507 G 7714 407375008101 INDICATOR BELL 407 407 SW DUAL TACH INOPERATIVE E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 722PH 53288 ROTOR NEEDLE INOPERATIVE. 1 G 7 1 3U O H2SW 2001072600156 20010726 00156 SW 2001 7 26 HEEA073030 1 20010507 G 7921 406360500101 COOLER BELL 407 407 SW ENGINE OIL OVERHEATED E HEEA K NONE M OVER TEMP IN INSP/MAINT 1 SW 03 409PH 53059 OIL COOLER OVERHEATING. 1 G 7 1 3U O H2SW 2001072600157 20010726 00157 SW 2001 7 26 HEEA073031 1 20010507 G 6220 407010103101 PITCH HORN BELL 407 407 SW MAIN ROTOR CORRODED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 724PH 2481 53327 CORROSION BEYOND LIMITS. 1 G 7 1 3U O H2SW 2001072600158 20010726 00158 SW 2001 7 26 HEEA073032 1 20010507 G 6220 406010107105 ADAPTER BELL 407 407 SW MAIN ROTOR CORRODED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 724PH 53327 MAIN ROTOR HUB ADAPTER CORRODED. 1 G 7 1 3U O H2SW 2001072600161 20010726 00161 SW 2001 7 26 HEEA073036 1 20010507 G 2822 1C2710 CARTRIDGE BELL 407 407 SW BOOST PUMP INOPERATIVE E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 8595X 53267 BOOST PUMP CARTRIDGE INOPERATIVE. 1 G 7 1 3U O H2SW 2001072600162 20010726 00162 SW 2001 7 26 HEEA073037 1 20010507 G 6510 206061432121 HOUSING BELL 407 407 SW BLOWER CRACKED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 457PH 53147 BLOWER HOUSING CRACKED AND POPPED RIVETS. 1 G 7 1 3U O H2SW 2001072600164 20010726 00164 SW 2001 7 26 HEEA073038 1 20010507 G 6500 407040316101 FLYWHEEL BELL 407 407 SW TAIL ROTOR WORN E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 612PH 53199 FLYWHEEL HAS WORN SPLINES. 1 G 7 1 3U O H2SW 2001072600165 20010726 00165 SW 2001 7 26 HEEA073039 1 20010507 G 6720 BOLT BELL 407 407 SW TAIL ROTOR SEIZED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 467PH 53142 LINK BOLT FROZEN IN BEARING. 1 G 7 1 3U O H2SW 2001072600166 20010726 00166 SW 2001 7 26 HEEA073040 1 20010507 G 3212 206050247137 COVER BELL 407 407 SW FLOAT TORN E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 719PH 53266 FLOAT COVER HAS TORN END CAPS. 1 G 7 1 3U O H2SW 2001072600167 20010726 00167 SW 2001 7 26 HEEA073041 1 20010507 G 3212 212073905001 INDICATOR BELL 407 407 SW FLOAT BOTTLE DAMAGED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 495PH 53397 FLOAT BOTTLE INDICATOR FULL OF WATER, NOT READABLE. 1 G 7 1 3U O H2SW 2001072600168 20010726 00168 SW 2001 7 26 HEEA073042 1 20010507 G 6220 407010105101 STUD 407010100115 BELL 407 407 SW DROOP STOP CRACKED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 724PH A351 53327 STUD CRACKED. 1 G 7 1 3U O H2SW 2001072600169 20010726 00169 SW 2001 7 26 HEEA073043 1 20010507 G 6710 BEARING BELL 407 407 SW UNIVERSAL LOOSE E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 495PH 610 53397 UNIVERSAL UPPER BEARING LOOSE. 1 G 7 1 3U O H2SW 2001072600170 20010726 00170 SW 2001 7 26 HEEA073044 1 20010507 G 7120 407060111101 MOUNT BELL 407 407 SW ENGINE WORN E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 491PH 53386 WORN BEARING IN ENGINE MOUNT. 1 G 7 1 3U O H2SW 2001072600176 20010726 00176 SW 2001 7 26 HEEA073045 1 20010507 G 2560 PLACARD BELL 407 407 SW SEAT BELT DAMAGED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 720PH 53277 TAG UNREADABLE ON SEAT BELT. 1 G 7 1 3U O H2SW 2001072600177 20010726 00177 SW 2001 7 26 HEEA073046 1 20010507 G 2560 PLACARD BELL 407 407 SW SEAT BELT TORN E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 417PH 53038 TAG TORN. 1 G 7 1 3U O H2SW 2001072600184 20010726 00184 SW 2001 7 26 HEEA073047 1 20010507 G 2840 407362005103 SWITCH BELL 407 407 SW COCKPIT STUCK E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 724PH 53327 SWITCH STICKS IN CLOSED POSITION. 1 G 7 1 3U O H2SW 2001072600186 20010726 00186 SW 2001 7 26 HEEA073048 1 20010507 G 3212 206050247135 COVER BELL 407 407 SW FLOAT WORN E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 467PH 53142 FLOAT COVER IS WORN. 1 G 7 1 3U O H2SW 2001072600188 20010726 00188 SW 2001 7 26 HEEA073049 1 20010507 G 3212 206050247135 COVER BELL 407 407 SW FLOAT WORN E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 499PH 53400 FLOAT COVER WORN. 1 G 7 1 3U O H2SW 2001072600189 20010726 00189 SW 2001 7 26 HEEA073050 1 20010507 G 6420 407340339101 BEARING BELL 407 407 SW COOLER BLOWER NOISY E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 494PH 181 53396 BEARING MAKING NOISE. 1 G 7 1 3U O H2SW 2001072600190 20010726 00190 SW 2001 7 26 HEEA073051 1 20010507 G 3212 70079H100F210 HOSE BELL 407 407 SW MLG DAMAGED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 407PH 53003 SLIGHT DAMAGE NEAR FITTING. 1 G 7 1 3U O H2SW 2001072600191 20010726 00191 SW 2001 7 26 HEEA073052 1 20010507 G 6510 206061432121 HOUSING BELL 407 407 SW BLOWER DAMAGED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 467PH 53142 NUT PLATES BAD. 1 G 7 1 3U O H2SW 2001072600194 20010726 00194 SW 2001 7 26 HEEA073053 1 20010507 G 6300 407310203101 MOUNT BELL 407 407 SW MAIN ROTOR WORN E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 8595X 2481 53267 WORN RUBBER ON MAIN ROTOR DRIVE MOUNT. 1 G 7 1 3U O H2SW 2001072600196 20010726 00196 SW 2001 7 26 HEEA073054 1 20010507 G 6710 406010425107 LEVER BELL 407 407 SW MAIN ROTOR WORN E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 402PH 2366 53159 LEVER WORN AND SLOPPY. 1 G 7 1 3U O H2SW 2001072600197 20010726 00197 SW 2001 7 26 HEEA073055 1 20010507 G 6710 406310405101 UNIVERSAL JOINT BELL 407 407 SW MAIN ROTOR WORN E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 457PH 2332 53147 UNIVERSAL ON MAIN ROTOR DRIVE, WORN. 1 G 7 1 3U O H2SW 2001072600202 20010726 00202 SW 2001 7 26 HEEA073056 1 20010507 G 2560 PLACARD BELL 407 407 SW SEAT BELT DAMAGED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 721PH 53278 BAD LABELS. 1 G 7 1 3U O H2SW 2001072600203 20010726 00203 SW 2001 7 26 HEEA073057 1 20010507 G 2560 PLACARD BELL 407 407 SW SEAT BELT DAMAGED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 721PH 53278 BAD LABELS. 1 G 7 1 3U O H2SW 2001072600204 20010726 00204 SW 2001 7 26 HEEA073058 1 20010507 G 2560 PLACARD BELL 407 407 SW SEAT BELT DAMAGED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 721PH 53278 BAD LABELS. 1 G 7 1 3U O H2SW 2001072600205 20010726 00205 SW 2001 7 26 HEEA073059 1 20010507 G 2560 PLACARD BELL 407 407 SW SEAT BELT DAMAGED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 721PH 53278 BAD LABELS. 1 G 7 1 3U O H2SW 2001072600206 20010726 00206 SW 2001 7 26 HEEA073060 1 20010509 G 6510 206061432121 HOUSING BELL 407 407 SW BLOWER CRACKED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 510PH 53209 TAIL ROTOR OIL COOLER BLOWER HOUSING IS CRACKED. 1 G 7 1 3U O H2SW 2001072600207 20010726 00207 SW 2001 7 26 HEEA073061 1 20010509 G 2560 PLACARD BELL 407 407 SW SEAT BELT LOOSE E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 720PH 53277 LABEL COMING OFF BELT. 1 G 7 1 3U O H2SW 2001072600208 20010726 00208 SW 2001 7 26 HEEA073062 1 20010509 G 6420 406312100101 BEARING 407012101111 BELL 407 407 SW TAIL ROTOR WORN E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 720PH 53398 53277 TAIL ROTOR BEARING WORN. 1 G 7 1 3U O H2SW 2001072600209 20010726 00209 SW 2001 7 26 HEEA073063 1 20010509 G 6310 214040841101 SEAL 406040500123 BELL 407 407 SW FREEWHEEL UNIT LEAKING E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 467PH A3174 53142 FREEWHEEL UNIT SEAL LEAKING. 1 G 7 1 3U O H2SW 2001072600210 20010726 00210 SW 2001 7 26 HEEA073064 1 20010509 G 6310 406340102101 CARBON SEAL 406040500123 BELL 407 407 SW FREEWHEEL UNIT LEAKING E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 467PH A3174 53142 CARBON SEAL LEAKING. 1 G 7 1 3U O H2SW 2001072600211 20010726 00211 SW 2001 7 26 HEEA073065 1 20010509 G 3210 407040624101 TUBE BELL 407 407 SW MLG CORRODED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 406PH 53198 TUBE WORN. 1 G 7 1 3U O H2SW 2001072600212 20010726 00212 SW 2001 7 26 HEEA073066 1 20010509 G 3210 407040623101 LINE BELL 407 407 SW MLG CORRODED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 406PH 53198 LINE WORN. 1 G 7 1 3U O H2SW 2001072600213 20010726 00213 SW 2001 7 26 HEEA073067 1 20010509 G 7921 407062021101 DUCT BELL 407 407 SW OIL COOLER CRACKED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 406PH 53198 OIL COOLER DUCT CRACKED. 1 G 7 1 3U O H2SW 2001072600214 20010726 00214 SW 2001 7 26 HEEA073068 1 20010509 G 6510 206061432121 HOUSING BELL 407 407 SW BLOWER CRACKED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 406PH 53198 BLOWER HOUSING CRACKED. 1 G 7 1 3U O H2SW 2001072600215 20010726 00215 SW 2001 7 26 HEEA073069 1 20010509 G 5210 206064819005S SKIN BELL 407 407 SW CREW DOOR CORRODED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 510PH 53209 CORRODED, SENDING IN FOR EVALUATION. IT HAS BEEN DETERMINED, POSSIBLE MFG DEFECT. NO PREVENTIVE MAINT BETWEEN 2 METALS . 1 G 7 1 3U O H2SW 2001072600216 20010726 00216 SW 2001 7 26 HEEA073070 1 20010509 G 5210 206064819006S SKIN BELL 407 407 SW CREW DOOR CORRODED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 510PH 53209 CORRODED, SENDING IN FOR EVALUATION. IT HAS BEEN DETERMINED, POSSIBLE MFG DEFECT. NO PREVENTIVE MAINT BETWEEN 2 METALS . 1 G 7 1 3U O H2SW 2001072600217 20010726 00217 SW 2001 7 26 HEEA073071 1 20010509 G 6710 406310404101 ROD END BELL 407 407 SW MAIN ROTOR WORN E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 402PH 2977 53159 ROD END ON MAIN ROTOR IS WORN. 1 G 7 1 3U O H2SW 2001072600219 20010726 00219 SW 2001 7 26 HEEA073072 1 20010509 G 6710 406010417101 LINER BELL 407 407 SW BEARING WORN E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 402PH 53159 BEARING LINER WORN. 1 G 7 1 3U O H2SW 2001072600220 20010726 00220 SW 2001 7 26 HEEA073073 1 20010509 G 6710 406310405101 UNIVERSAL JOINT BELL 407 407 SW MAIN ROTOR WORN E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 499PH 463 53400 WORN BEARING. 1 G 7 1 3U O H2SW 2001072600222 20010726 00222 SW 2001 7 26 HEEA073074 1 20010509 G 6720 407001026101 TUBE BELL 407 407 1182206 SW TAIL ROTOR WORN E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 409PH 53059 TAIL ROTOR CONTROL TUBE HAS A WORN BEARING. 1 G 7 1 3U O H2SW 2001072600223 20010726 00223 SW 2001 7 26 HEEA073075 1 20010509 G 6510 206061432121 HOUSING BELL 407 407 SW BLOWER CRACKED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 722PH 53288 BLOWER HOUSING CRACKED. 1 G 7 1 3U O H2SW 2001072600224 20010726 00224 SW 2001 7 26 HEEA073076 1 20010509 G 6710 406310405101 UNIVERSAL JOINT BELL 407 407 SW MAIN ROTOR WORN E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 495PH 730 53397 WORN BEARING. 1 G 7 1 3U O H2SW 2001072600225 20010726 00225 SW 2001 7 26 HEEA073077 1 20010509 G 3201 206052105035 CUSHION BELL 407 407 SW MLG DEBONDED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 409PH 53059 CUSHION UNBONDED. 1 G 7 1 3U O H2SW 2001072600226 20010726 00226 SW 2001 7 26 HEEA073078 1 20010509 G 6510 206061432121 HOUSING BELL 407 407 SW BLOWER CRACKED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 409PH 53059 BLOWER HOUSING CRACKED. 1 G 7 1 3U O H2SW 2001072600227 20010726 00227 SW 2001 7 26 HEEA073079 1 20010509 G 6510 206061432121 HOUSING BELL 407 407 SW BLOWER CRACKED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 498PH 53399 CRACKED AND WORKING RIVETS. 1 G 7 1 3U O H2SW 2001072600228 20010726 00228 SW 2001 7 26 HEEA073080 1 20010509 G 6510 406040320101 SHAFT PHIPBH40701 BELL 407 407 SW COOLER BLOWER WORN E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 405PH PHI0012 53207 COOLER BLOWER SHAFT HAS WORN SPLINES. 1 G 7 1 3U O H2SW 2001072600229 20010726 00229 SW 2001 7 26 HEEA073081 1 20010509 G 6310 406340102101 CARBON SEAL BELL 407 407 SW TRANSMISSION LEAKING E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 8595X 53267 CARBON SEAL LEAKING. 1 G 7 1 3U O H2SW 2001072600230 20010726 00230 SW 2001 7 26 HEEA073082 1 20010509 G 6720 PHI407112 TRUNNION BELL 407 407 SW TAIL ROTOR WORN E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 724PH 53327 TRUNNION EAR WORN. LEAKING. 1 G 7 1 3U O H2SW 2001072600231 20010726 00231 SW 2001 7 26 HEEA073083 1 20010509 G 6310 406040550101 ADAPTER BELL 407 407 SW TRANSMISSION LEAKING E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 722PH 53288 ADAPTER SEAL LEAKING. 1 G 7 1 3U O H2SW 2001072600232 20010726 00232 SW 2001 7 26 HEEA073085 1 20010509 G 6510 407340339103 BEARING PHIPBH40701 BELL 407 407 SW COOLER BLOWER WORN E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 495PH 190 PHI0010 53397 WORN BEARINGS. 1 G 7 1 3U O H2SW 2001072600234 20010726 00234 SW 2001 7 26 HEEA073086 1 20010509 G 6710 214001347005 ACTUATOR BELL 214 214ST 1182106 SW MAIN ROTOR SLOW E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 RELEASES SLOW. 2 G 7 2 4U H10SW 2001072600236 20010726 00236 SW 2001 7 26 HEEA073087 1 20010509 G 6710 214001347005 ACTUATOR BELL 214 214ST 1182106 SW MAIN ROTOR STUCK E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 FORE/AFT TRIM RELEASE STICKING. 2 G 7 2 4U H10SW 2001072600237 20010726 00237 SW 2001 7 26 HEEA073088 1 20010509 G 8011 214060056103 STARTER BELL 214 214ST 1182106 SW ENGINE SLIPPED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 CLUTCH SLIPPAGE OUT OF LIMITS. 2 G 7 2 4U H10SW 2001072600239 20010726 00239 SW 2001 7 26 HEEA073089 1 20010509 G 7120 209062105001 BEARING BELL 412 412 1182202 SW MOUNT ROD END DAMAGED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 BEARINGS EXTREMELY TIGHT. BURNISHED BEARING USING BOLT AND TURNING SLOWLY. A SLIVER OF BEARING RACE FELL OUT. APPAREN TLY WHAT WAS CAUSING THE TIGHTNESS IN THE FIRST PLACE. ONCE THIS SLIVER WAS OUT THE BEARINGS ARE TOO LOOSE AND WOULD ON LY HAVE HALF ITS LIFE. 1 G 7 2 4U H4SW 2001072600242 20010726 00242 SW 2001 7 26 HEEA073090 1 20010511 G 2933 222375019105 TRANSMITTER BELL 214 214ST 1182106 SW HYD INDICATOR MALFUNCTIONED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 59806 28140 NR 1 HYDRAULIC PRESSURE GAUGE MALFUNCTIONED. REPLACED PRESSURE GAUGE. 2 G 7 2 4U H10SW 2001072600243 20010726 00243 SW 2001 7 26 HEEA073091 1 20010511 G 6300 407340339101 BEARING BELL 407 407 SW BLOWER SHAFT FAILED E HEEA O OTHER E VIBRATION/BUFFET NR NOT REPORTED 1 SW 03 740PH 223 53435 AIRCRAFT DEVELOPED A VIBRATION IN FLIGHT. FOUND FWD. BEARING ON BLOWER SHAFT FAILED. 1 G 7 1 3U O H2SW 2001072600244 20010726 00244 SW 2001 7 26 HEEA073092 1 20010514 G 7740 DPUA0101 COMPUTER BELL 206 206L3 1182108 SW COCKPIT FAILED E O OTHER J WARNING INDICATION NR NOT REPORTED 1 SW 03 30KH 51527 INTELLASTART CAUTION LIGHTS COMES ON INTERMITTENTLY AND WILL NOT LINK TO LAPTOP COMPUTER. SYSTEM FAILED DOWNLOAD PORT T EST. 1 G 7 1 3U H2SW 2001072600246 20010726 00246 SW 2001 7 26 HEEA073093 1 20010514 G 2910 ELBOW BELL 214 214ST 1182106 SW HYD SYSTEM CHAFED E HEEA O OTHER K J FLUID LOSS WARNING INDICATION AP APPROACH 1 SW 03 59806 28140 ON FINAL APPROACH, THE OIL COOLER LIGHT ILLUMINATED. FOUND THE UTILITY HYDRAULIC SYSTEM LOST FLUID. MAINTENANCE FOUND L EAK AT ELBOW WHERE THE SUPPORT HAD CHAFED THROUGH DUE TO JAM NUT BEING LOOSE. 2 G 7 2 4U H10SW 2001072600247 20010726 00247 EU 2001 7 26 HEEA073094 1 20010510 G 8010 845UN01Q4AA5F SWITCH SNIAS 350 AS350B 8680801 EU STARTER FAILED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 973AE 105 3229 VEMD RECORDING START SWITCH. 1 G 7 1 3U H9EU 2001072600249 20010726 00249 EU 2001 7 26 HEEA073095 1 20010510 G 6321 350A32050002 BRAKE ASSY SNIAS 350 AS350B 8680801 EU MAIN ROTOR DAMAGED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 970AE 282 3235 OIL SOAKED FROM LEAKING SEAL OF INPUT. 1 G 7 1 3U H9EU 2001072600251 20010726 00251 2001 7 26 HEEA073096 4 20010510 G 3120 B1894522282A CLOCK SNIAS 350 AS350B 8680801 EU COCKPIT MALFUNCTIONED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 974AE 2653 CANNOT RESET SWEEP SECOND HAND FOR ELAPSED TIMER. 1 G 7 1 3U H9EU 2001072600252 20010726 00252 2001 7 26 HEEA073097 4 20010510 G 3120 B1894522282A CLOCK SNIAS 350 AS350B 8680801 EU COCKPIT MALFUNCTIONED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 970AE 754 3235 PILOT REPORTS SECOND HAND DOESN'T FUNCTION. 1 G 7 1 3U H9EU 2001072600253 20010726 00253 EU 2001 7 26 HEEA073098 1 20010510 G 6730 SC5084 SERVO SNIAS 350 AS350B 8680801 EU MAIN ROTOR LEAKING E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 974AE 1976 2653 LEAKED AT TOP SIDE OF PISTON. 1 G 7 1 3U H9EU 2001072600255 20010726 00255 EU 2001 7 26 HEEA073099 1 20010510 G 6410 355A12004008 BLADE SNIAS 350 AS350B 8680801 EU TAIL ROTOR CRACKED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 974AE 3045 2653 CRACK AT TRIM TAB AREA ON TRAILING EDGE. 1 G 7 1 3U H9EU 2001072600258 20010726 00258 EU 2001 7 26 HEEA073100 1 20010510 G 6730 SC5083 SERVO SNIAS 350 AS350B 8680801 EU MAIN ROTOR LEAKING E HEEA K NONE K FLUID LOSS IN INSP/MAINT 1 SW 03 974AE 374 2653 LEAKING AT UPPER PISTON SEAL AREA. 1 G 7 1 3U H9EU 2001072600260 20010726 00260 EU 2001 7 26 HEEA073101 1 20010510 G 6410 355A09103601 BEARING SNIAS 350 AS350B 8680801 EU TAIL ROTOR SEPARATED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 973AE 473 3229 SEPARATED AT EDGES. 1 G 7 1 3U H9EU 2001072600263 20010726 00263 2001 7 26 HEEA073102 4 20010510 G 3100 614764031 INDICATOR SNIAS 350 AS350B 8680801 EU COCKPIT STUCK E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 854PH 3248 NEEDLE STICKS. 1 G 7 1 3U H9EU 2001072600265 20010726 00265 EU 2001 7 26 HEEA073103 1 20010510 G 2910 MA12401 PRESSURE SWITCH SNIAS 350 AS350B2 8680813 EU HYD SYSTEM INACCURATE E HEEA O OTHER N FALSE WARNING IN INSP/MAINT 1 SW 03 4000L 2873 INACCURATE READINGS. 1 G 7 1 3U H9EU 2001072600267 20010726 00267 2001 7 26 HEEA073104 4 20010510 G 3100 614764031 INDICATOR SNIAS 350 AS350B 8680801 EU COCKPIT FAILED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 854PH 3248 NOT INDICATING. 1 G 7 1 3U H9EU 2001072600270 20010726 00270 2001 7 26 HEEA073105 4 20010510 G 3160 845UN01Q4AA5F SWITCH SNIAS 350 AS350B 8680801 EU VEMD FAILED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 971AE 3230 FAILURE ON VEMD. 1 G 7 1 3U H9EU 2001072600272 20010726 00272 EU 2001 7 26 HEEA073107 1 20010510 G 3252 350A75208000 DAMPER SNIAS 350 AS350B 8680801 EU MLG LEAKING E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 972AE 295 3234 LEAKING AROUND SHAFT SEAL. 1 G 7 1 3U H9EU 2001072600285 20010726 00285 EU 2001 7 26 HEEA073109 1 20010510 G 7714 G300103 WARNING SYSTEM SNIAS 350 AS350B 8680801 EU ENGINE MALFUNCTIONED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 854PH 3248 ROTOR LIGHT DOES NOT FLASH AT LOWER RPMS. 1 G 7 1 3U H9EU 2001072600288 20010726 00288 EU 2001 7 26 HEEA073110 1 20010510 G 6240 614764031 INDICATOR SNIAS 350 AS350B 8680801 EU COCKPIT MALFUNCTIONED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 854PH 3248 ROTOR NEEDLE WILL NOT GO ABOVE 340 RPM. 1 G 7 1 3U H9EU 2001072600290 20010726 00290 EU 2001 7 26 HEEA073111 1 20010510 G 6240 G300102 WARNING SYSTEM SNIAS 350 AS350B2 8680813 EU ROTOR MALFUNCTIONED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 4034Q 2918 ROTOR ALARM SYSTEM WILL NOT WORK PROPERLY. 1 G 7 1 3U H9EU 2001072600321 20010726 00321 2001 7 26 HEEA073112 4 20010510 G 3416 150201182 ALTIMETER SNIAS 350 AS350B 8680801 EU COCKPIT INACCURATE E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 973AE 3229 150 TO 200 FEET OFF ACTUAL ALTITUDE. 1 G 7 1 3U H9EU 2001072700004 20010727 00004 EU 2001 7 27 HEEA073113 1 20010510 G 6240 614764031 INDICATOR SNIAS 350 AS350B 8680801 EU COCKPIT INOPERATIVE E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 856PH 3352 INDICATOR INOPERATIVE. 1 G 7 1 3U H9EU 2001072700005 20010727 00005 EU 2001 7 27 HEEA073114 1 20010510 G 6340 50071550020 SENSOR SNIAS 350 AS350B 8680801 EU ROTOR TACH FLUCTUATES E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 856PH 3352 ROTOR TACH FLUCTUATES. PIN B IN CONNECTOR WILL NOT SEAT. 1 G 7 1 3U H9EU 2001072700006 20010727 00006 EU 2001 7 27 HEEA073115 1 20010510 G 6520 BEARING SNIAS 350 AS350B2 8680813 EU PITCH CONTROL CRACKED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 40466 3811 3004 PITCH CONTROL BEARINGS CRACKED. 1 G 7 1 3U H9EU 2001072700007 20010727 00007 EU 2001 7 27 HEEA073116 1 20010510 G 6410 355A09103600 BEARING SNIAS 350 AS350B2 8680813 EU TAIL ROTOR CRACKED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 40466 3004 TAIL ROTOR BEARINGS CRACKED. 1 G 7 1 3U H9EU 2001072700012 20010727 00012 SW 2001 7 27 HEEA073164 1 20010523 G 8011 214060056103 STARTER BELL 214 214ST 1182106 SW CLUTCH HOUSING CONTAMINATED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 3897N 28106 OIL IN CLUTCH HOUSING ON 250 HOUR INSPECTION. 2 G 7 2 4U H10SW 2001072700013 20010727 00013 SW 2001 7 27 HEEA073165 1 20010524 G 3340 6500306N RECEPTACLE BELL 407 407 SW TAIL FAILED E HEEA K NONE L NO TEST IN INSP/MAINT 1 SW 03 719PH 53266 TAIL LIGHT WON'T LIGHT. SCRAPPED LOCALLY. 1 G 7 1 3U O H2SW 2001072700016 20010727 00016 SW 2001 7 27 HEEA073170 1 20010524 G 7920 204040760109 FILTER ELEMENT BELL 407 407 SW ENGINE OIL MAKING METAL E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 467PH 53142 MAKING METAL. SCRAPPED LOCALLY. 1 G 7 1 3U O H2SW 2001072700017 20010727 00017 SW 2001 7 27 HEEA073172 1 20010524 G 7932 S207A GAUGE BELL 407 407 SW OIL LEVEL CONTAMINATED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 467PH 53142 OIL LEVEL INDICATOR HAZED. SCRAPPED LOCALLY. 1 G 7 1 3U O H2SW 2001072700049 20010727 00049 SW 2001 7 27 HEEA073191 1 20010524 G 6510 206061432118 INLET BELL 407 407 SW TAIL ROTOR CRACKED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 467PH 53142 INLET CRACKED; WORN. 1 G 7 1 3U O H2SW 2001072700051 20010727 00051 SW 2001 7 27 HEEA073192 1 20010525 G 2841 206063633103 INDICATOR BELL 206 206L1 1182107 SW FUEL QTY STUCK E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 NEEDLE STICKS THROUGHOUT SCALE INTERMITTENTLY. 1 G 7 1 3U H2SW 2001072700053 20010727 00053 SW 2001 7 27 HEEA073193 1 20010531 G 6300 212340100103 SEAL BELL 212 212 1181420 SW MAIN ROTOR DEFECTIVE E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 DEFECTS FOUND ON SEAL LIP. 1 G 7 1 4U H4SW 2001072700055 20010727 00055 SW 2001 7 27 HEEA073194 1 20010531 G 6300 212340105101 SEAL BELL 212 212 1181420 SW MAIN ROTOR DEFECTIVE E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 DEFECTS FOUND ON SEAL LIP. 1 G 7 1 4U H4SW 2001072700056 20010727 00056 SW 2001 7 27 HEEA073195 1 20010531 G 6300 MS2764642 BEARING BELL 212 212 1181420 SW MAIN ROTOR MISMARKED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 MISIDENTIFIED. PICK TICKET SHOWS P/N MS27646-42 BUT TICKET HAS A BOLT P/N UNKNOWN. 1 G 7 1 4U H4SW 2001072700068 20010727 00068 SW 2001 7 27 HEEA073197 1 20010601 G 6300 BEARING BELL 407 407 SW MAIN ROTOR WORN E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 8595X 2481 53267 WORN BEARINGS AND BOLT HOLES. SERIAL NUMBERS REMOVED ARE LK0963 AND LK1030. 1 G 7 1 3U O H2SW 2001072700071 20010727 00071 SW 2001 7 27 HEEA073198 1 20010601 G 2844 407362013101 PRESSURE SWITCH BELL 407 407 SW BOOST PUMP MALFUNCTIONED E HEEA K NONE L NO TEST IN INSP/MAINT 1 SW 03 510PH 53209 BOOST PUMP LIGHT FAILED TO ILLUMINATE. 1 G 7 1 3U O H2SW 2001072700072 20010727 00072 SW 2001 7 27 HEEA073199 1 20010601 G 2820 222366621103 FUEL FILTER BELL 407 407 SW ENGINE CHAFED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 493PH 53393 FUEL FILTER CHAFED ON BOWL. 1 G 7 1 3U O H2SW 2001072700073 20010727 00073 SW 2001 7 27 HEEA073200 1 20010601 G 3110 407375001105 INDICATOR BELL 407 407 SW MGT INOPERATIVE E HEEA K NONE L NO TEST IN INSP/MAINT 1 SW 03 493PH 53393 NO INDICATION. 1 G 7 1 3U O H2SW 2001072700076 20010727 00076 SW 2001 7 27 HEEA073201 1 20010601 G 3212 206373901103 SOLENOID VALVE BELL 407 407 SW MLG FLOAT DAMAGED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 721PH 53278 WOULD NOT SEAT WHEN SERVICED. 1 G 7 1 3U O H2SW 2001072700085 20010727 00085 SW 2001 7 27 HEEA073202 1 20010601 G 6710 BEARING BELL 407 407 SW MAIN ROTOR WORN E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 498PH 1291 53399 WORN BEARING. 1 G 7 1 3U O H2SW 2001072700086 20010727 00086 SW 2001 7 27 HEEA073203 1 20010601 G 2420 SM20ACD300A21 RELAY BELL 407 407 SW FADEC MALFUNCTIONED E HEEA O OTHER O OTHER IN INSP/MAINT 1 SW 03 720PH 53277 FADEC DEGRADE LIGHT 3 LIGHTS. 1 G 7 1 3U O H2SW 2001072700087 20010727 00087 SW 2001 7 27 HEEA073204 1 20010601 G 6320 407040006107 GEARBOX BELL 407 407 SW MAIN ROTOR MAKING METAL E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 612PH 2074 53199 MAIN ROTOR GEARBOX MAKING METAL. 1 G 7 1 3U O H2SW 2001072700089 20010727 00089 SW 2001 7 27 HEEA073205 1 20010601 G 2420 SM20ACD300A21 RELAY BELL 407 407 SW GENERATOR MALFUNCTIONED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 4999 53323 INTERMITTENT START LIGHT. 1 G 7 1 3U O H2SW 2001072700091 20010727 00091 SW 2001 7 27 HEEA073206 1 20010601 G 7712 407375003107 INDICATOR BELL 407 407 SW TORQUE MALFUNCTIONED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 501PH 53401 INDICATES APPROX. 8% LOW. INDICATES 0% AT FLIGHT IDLE. 1 G 7 1 3U O H2SW 2001072700093 20010727 00093 SW 2001 7 27 HEEA073207 1 20010601 G 7931 407375004101 INDICATOR BELL 407 407 SW ENGINE OIL MALFUNCTIONED E HEEA K NONE L NO TEST IN INSP/MAINT 1 SW 03 742PH 26 53461 OIL PRESSURE DROPPED TO 90 PSI. 1 G 7 1 3U O H2SW 2001072700094 20010727 00094 SW 2001 7 27 HEEA073210 1 20010601 G 7933 407375004101 INDICATOR BELL 407 407 SW ENGINE OIL FAILED E HEEA K NONE L NO TEST IN INSP/MAINT 1 SW 03 740PH 53435 TEMP SIDE QUIT INDICATING. 1 G 7 1 3U O H2SW 2001072700095 20010727 00095 SW 2001 7 27 HEEA073214 1 20010601 G 7933 407375004101 INDICATOR BELL 407 407 SW ENGINE OIL MALFUNCTIONED E HEEA K NONE L NO TEST IN INSP/MAINT 1 SW 03 723PH 53283 WHEN GAUGE GETS HOT (4 TO 6 MIN) ENG OIL PRESSURE GOES TO ZERO. 1 G 7 1 3U O H2SW 2001072700096 20010727 00096 2001 7 27 HEEA073215 4 20010601 G 3120 M803B205VBATT CLOCK BELL 407 407 SW COCKPIT MALFUNCTIONED E HEEA K NONE L NO TEST IN INSP/MAINT 1 SW 03 407PH 53003 LIGHT WILL NOT WORK. 1 G 7 1 3U O H2SW 2001072700097 20010727 00097 SW 2001 7 27 HEEA073216 1 20010601 G 2420 SM20ACD300A21 RELAY BELL 407 407 SW FADEC FAILED E HEEA K NONE L NO TEST IN INSP/MAINT 1 SW 03 499PH 53400 FADEC FAULT WORD IGN I FLT. 1 G 7 1 3U O H2SW 2001072700098 20010727 00098 SW 2001 7 27 HEEA073217 1 20010601 G 3212 206373901103 SOLENOID VALVE BELL 407 407 SW MLG FLOAT FAILED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 8595X 53267 CANNOT SERVICE FLOAT BOTTLES. 1 G 7 1 3U O H2SW 2001072700099 20010727 00099 SW 2001 7 27 HEEA073218 1 20010601 G 2420 SM20ACD300A21 RELAY BELL 407 407 SW GENERATOR STUCK E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 494PH 53396 STICKING INTERMITTENTLY. 1 G 7 1 3U O H2SW 2001080300090 20010803 00090 SW 2001 8 3 HEEA073351 1 20010605 G 3150 214175122111 PANEL BELL 214 214ST 1182106 SW COCKPIT DAMAGED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 EXCHANGE UNIT RECEIVED INOPERATIVE. 2 G 7 2 4U H10SW 2001080300092 20010803 00092 SW 2001 8 3 HEEA073352 1 20010606 G 6710 214001347005 ACTUATOR BELL 214 214ST 1182106 SW CYCLIC STUCK E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 LATERAL FORCE TRIM STICKING. 2 G 7 2 4U H10SW 2001080300100 20010803 00100 SW 2001 8 3 HEEA073354 1 20010608 G 6321 D01631 PAD BELL 407 407 SW ROTOR BRAKE WORN E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 8595X 53267 WORN AND GLAZED. 1 G 7 1 3U O H2SW 2001080300108 20010803 00108 SW 2001 8 3 HEEA073355 1 20010608 G 6720 406312103101 LINK BELL 407 407 SW TAIL ROTOR WORN E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 490PH 53378 WORN BEARINGS. SERIAL NUMBERS REMOVED ARE NHFS4534 AND NHFS4483. 1 G 7 1 3U O H2SW 2001080300109 20010803 00109 SW 2001 8 3 HEEA073356 1 20010608 G 3212 206050247131 COVER BELL 407 407 SW FLOAT TORN E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 457PH 53147 TORN AND DETERIORATED. 1 G 7 1 3U O H2SW 2001080300114 20010803 00114 SW 2001 8 3 HEEA073357 1 20010608 G 7921 407062021101 DUCT BELL 407 407 SW OIL COOLER CRACKED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 510PH 53209 OIL COOLER DUCT CRACKED. 1 G 7 1 3U O H2SW 2001080300115 20010803 00115 SW 2001 8 3 HEEA073358 1 20010608 G 6510 206061432121 HOUSING BELL 407 407 SW BLOWER CRACKED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 720PH 53277 CRACKED. 1 G 7 1 3U O H2SW 2001080300116 20010803 00116 SW 2001 8 3 HEEA073359 1 20010608 G 3212 212073905001 GAUGE BELL 407 407 SW MLG CONTAMINATED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 740PH 53435 WATER IN GAUGE. 1 G 7 1 3U O H2SW 2001080300117 20010803 00117 SW 2001 8 3 HEEA073360 1 20010608 G 3260 8869K59 SWITCH BELL 407 407 SW MLG INTERMITTENT E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 724PH 53327 INTERMITTENT OPERATION. NO POSITIVE MOVEMENT. 1 G 7 1 3U O H2SW 2001080300128 20010803 00128 SW 2001 8 3 HEEA073361 1 20010608 G 3310 FCB205AT4 RELAY BELL 407 407 SW COCKPIT INTERMITTENT E HEEA K NONE L NO TEST IN INSP/MAINT 1 SW 03 4999 53323 INTERMITTENT IGNITION WHENEVER STARTER IS LATCHED. 1 G 7 1 3U O H2SW 2001080300133 20010803 00133 SW 2001 8 3 HEEA073362 1 20010608 G 7810 407063001101 EXHAUST STACK BELL 407 407 SW ENGINE CRACKED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 405PH 53207 CRACKED AT WELDED AREA. 1 G 7 1 3U O H2SW 2001080300137 20010803 00137 SW 2001 8 3 HEEA073363 1 20010608 G 6720 406012129101 LINK BELL 407 407 SW TAIL ROTOR DAMAGED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 409PH 53059 RATCHETY. 1 G 7 1 3U O H2SW 2001080300138 20010803 00138 SW 2001 8 3 HEEA073365 1 20010608 G 6320 407340339103 BEARING PHIPBH40701 BELL 407 407 SW COOLER BLOWER ROUGH E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 402PH PHI0012 53159 ROUGH. SERIAL NUMBERS REMOVED ARE B01-0584 AND B01-0569. 1 G 7 1 3U O H2SW 2001080300139 20010803 00139 SW 2001 8 3 HEEA073366 1 20010608 G 3212 212073905001 GAUGE BELL 407 407 SW MLG CONTAMINATED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 719PH 53266 MOISTURE IN GAUGE. 1 G 7 1 3U O H2SW 2001080300140 20010803 00140 SW 2001 8 3 HEEA073367 1 20010608 G 3212 212073905001 GAUGE BELL 407 407 SW MLG READS LOW E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 719PH 53266 READS LOW. 1 G 7 1 3U O H2SW 2001080300141 20010803 00141 SW 2001 8 3 HEEA073368 1 20010608 G 6720 406312103101 LINK BELL 407 407 SW TAIL ROTOR WORN E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 4999 53323 WORN BEARINGS. 1 G 7 1 3U O H2SW 2001080300142 20010803 00142 SW 2001 8 3 HEEA073369 1 20010608 G 6720 406312103101 LINK BELL 407 407 SW TAIL ROTOR WORN E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 4999 53323 WORN BEARINGS. 1 G 7 1 3U O H2SW 2001080300143 20010803 00143 SW 2001 8 3 HEEA073370 1 20010608 G 3212 206050247135 COVER BELL 407 407 SW FLOAT TORN E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 494PH 53396 END CAP TORN AND FRAYED. 1 G 7 1 3U O H2SW 2001080300144 20010803 00144 SW 2001 8 3 HEEA073371 1 20010608 G 6220 406310200101 ROD END BELL 407 407 SW MAIN ROTOR WORN E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 496PH 53398 BEARING WORN. 1 G 7 1 3U O H2SW 2001080300145 20010803 00145 SW 2001 8 3 HEEA073372 1 20010608 G 7100 407001026101 TUBE BELL 407 407 1182206 SW TAIL ROTOR WORN E K NONE O OTHER IN INSP/MAINT 1 SW 03 720PH 53277 TAIL ROTOR CONTROL TUBE HAS A BEARING WORN. 1 G 7 1 3U O H2SW 2001080300146 20010803 00146 SW 2001 8 3 HEEA073373 1 20010608 G 2400 M835362028M RELAY BELL 407 407 SW COCKPIT MALFUNCTIONED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 417PH 53038 FADEC AUTO/MANUAL LIGHT COMES ON THEN GOES OUT. 1 G 7 1 3U O H2SW 2001080300147 20010803 00147 SW 2001 8 3 HEEA073374 1 20010608 G 6322 407340339103 BEARING PHIPBH40701 BELL 407 407 SW COOLER BLOWER ROUGH E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 498PH PHI0034 53399 ROUGH. SERIAL NUMBERS REMOVED ARE H99-2406 AND H99-2403. 1 G 7 1 3U O H2SW 2001080300148 20010803 00148 SW 2001 8 3 HEEA073375 1 20010608 G 6322 406040320101 SHAFT PHIPBH40701 BELL 407 407 SW COOLER BLOWER WORN E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 498PH PHI0034 53399 ROUGH. 1 G 7 1 3U O H2SW 2001080300149 20010803 00149 SW 2001 8 3 HEEA073376 1 20010608 G 6300 407040316101 FLYWHEEL BELL 407 407 SW MAIN ROTOR WORN E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 467PH 53142 WORN SPLINES. 1 G 7 1 3U O H2SW 2001080300159 20010803 00159 SW 2001 8 3 HEEA073377 1 20010608 G 6510 206061432121 HOUSING BELL 407 407 SW BLOWER CRACKED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 447PH 53114 CRACKED. 1 G 7 1 3U O H2SW 2001080300160 20010803 00160 SW 2001 8 3 HEEA073378 1 20010608 G 6300 407340339103 BEARING PHIPBH40701 BELL 407 407 SW COOLER BLOWER ROUGH E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 409PH PHI0007 53059 ROUGH. SERIAL NUMBERS REMOVED ARE K98-0736 AND H99-1758. SENT TO BELL HELICOPTER TEXTRON FOR CREDIT AGAINST REPLACEMENT PARTS PURCHASED. REPLACED WITH SERIAL NUMBERS SNB01-0793 AND SNB01-0755. REFERENCE: DMR#71726100 AND 71726101. LAB OR CREDIT ACCOMPLISHED ON J0161088-WA (INVOICE AND DMR NO. 687026). 1 G 7 1 3U O H2SW 2001080300162 20010803 00162 SW 2001 8 3 HEEA073379 1 20010608 G 3212 206050247132 COVER BELL 407 407 SW FLOAT TORN E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 494PH 53396 TORN. 1 G 7 1 3U O H2SW 2001080300163 20010803 00163 SW 2001 8 3 HEEA073380 1 20010608 G 2560 407370720101 RESTRAINT BELL 407 407 SW COCKPIT DAMAGED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 404PH 53188 LABELS DETERIORATING. 1 G 7 1 3U O H2SW 2001080300165 20010803 00165 SW 2001 8 3 HEEA073381 1 20010608 G 2560 407370721101 RESTRAINT BELL 407 407 SW COCKPIT DAMAGED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 404PH 53188 LABELS DETERIORATING. 1 G 7 1 3U O H2SW 2001080300166 20010803 00166 SW 2001 8 3 HEEA073382 1 20010608 G 6310 222060084101 PRESSURE SWITCH BELL 407 407 SW M/R GEARBOX FAILED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 720PH 53277 ANTI ICE LIGHT WILL NOT GO OUT. 1 G 7 1 3U O H2SW 2001080300167 20010803 00167 SW 2001 8 3 HEEA073383 1 20010608 G 6510 206061432121 HOUSING BELL 407 407 SW BLOWER CRACKED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 402PH 53159 CRACKED. 1 G 7 1 3U O H2SW 2001080300168 20010803 00168 SW 2001 8 3 HEEA073384 1 20010608 G 3310 FCB205AT4 RELAY BELL 407 407 SW COCKPIT FAILED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 499PH 53400 CAUSED FADEC FAULT WORD IGN 1 FLT. 1 G 7 1 3U O H2SW 2001080300170 20010803 00170 SW 2001 8 3 HEEA073385 1 20010608 G 6510 406040339105 BEARING 407040302101 BELL 407 407 SW T/R DRIVESHAFT ROUGH E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 467PH A926 53142 VIBRATION ON TAILBOOM. BEARING ROUGH. SENT TO BELL HELICOPTER TEXTRON FOR CREDIT AGAINST REPLACEMENT PART PURCHASED. REFERENCE: DMR#71513300. LABOR CREDIT ACCOMPLISHED ON J0162309-WA (INVOICE AND DMR NO. 687029). 1 G 7 1 3U O H2SW 2001080300171 20010803 00171 SW 2001 8 3 HEEA073386 1 20010608 G 6300 407040320101 SHAFT PHIPBH40701 BELL 407 407 SW COOLER BLOWER WORN E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 467PH PHI0020 53142 WORN SPLINES. 1 G 7 1 3U O H2SW 2001080300173 20010803 00173 SW 2001 8 3 HEEA073388 1 20010608 G 7720 MS280343 BULB BELL 407 407 SW TEMP INDICATOR FAILED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 740PH 53435 PRESSURE INDICATION READS ZERO. 1 G 7 1 3U O H2SW 2001080300174 20010803 00174 2001 8 3 HEEA073389 4 20010608 G 3120 602EN6026 SWITCH BELL 407 407 SW CLOCK FAILED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 467PH 53142 CAUSES FLIGHT TIME MODE OF CLOCK TO NOT WORK. 1 G 7 1 3U O H2SW 2001080300175 20010803 00175 SW 2001 8 3 HEEA073390 1 20010608 G 6710 406310405101 UNIVERSAL JOINT BELL 407 407 SW TAIL ROTOR DAMAGED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 447PH 1110 53114 EXCESSIVE PLAY. 1 G 7 1 3U O H2SW 2001080300176 20010803 00176 SW 2001 8 3 HEEA073391 1 20010608 G 6500 406040072105 SPLINE ADAPTER BELL 407 407 SW TAIL ROTOR DRIVE WORN E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 720PH 53277 WORN. 1 G 7 1 3U O H2SW 2001080300177 20010803 00177 SW 2001 8 3 HEEA073392 1 20010608 G 7810 407063001101 EXHAUST STACK BELL 407 407 SW ENGINE CRACKED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 494PH 53396 CRACKED. 1 G 7 1 3U O H2SW 2001080300178 20010803 00178 SW 2001 8 3 HEEA073393 1 20010608 G 2910 70079H000Y150 HOSE BELL 407 407 SW MLG KINKED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 498PH 53399 KINKED ON 90 DEGREE END. 1 G 7 1 3U O H2SW 2001080300180 20010803 00180 SW 2001 8 3 HEEA073394 1 20010608 G 6230 406310411101 BOOT BELL 407 407 SW MAIN ROTOR WORN E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 490PH 53378 SMALL HOLE WORN IN BOOT. 1 G 7 1 3U O H2SW 2001080300182 20010803 00182 SW 2001 8 3 HEEA073395 1 20010611 G 3300 407076501109 HARNESS BELL 407 407 SW ELECTRICAL CHAFED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 499PH 53400 CHAFED NEAR PROBE NR 3 CONNECTOR. HARNESS NOT SECURED PROPERLY. 1 G 7 1 3U O H2SW 2001080300183 20010803 00183 SW 2001 8 3 HEEA073396 1 20010611 G 6510 206061432119 BLOWER BELL 407 407 SW TAIL ROTOR CRACKED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 402PH 53159 CRACKED. 1 G 7 1 3U O H2SW 2001080300184 20010803 00184 SW 2001 8 3 HEEA073397 1 20010611 G 3212 206050247135 COVER BELL 407 407 SW FLOAT TORN E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 402PH 53159 FORWARD CAP-THREAD BARE AND TORN. 1 G 7 1 3U O H2SW 2001080300185 20010803 00185 SW 2001 8 3 HEEA073398 1 20010611 G 6300 BEARING PHIPBH40701 BELL 407 407 SW COOLER BLOWER FAILED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 740PH PHI0002 53435 NR 1 BEARING FAILED IN FLIGHT. 1 G 7 1 3U O H2SW 2001080300186 20010803 00186 SW 2001 8 3 HEEA073399 1 20010611 G 6300 BEARING PHIPBH40701 BELL 407 407 SW COOLER BLOWER FAILED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 740PH PHI0002 53435 NR 1 BEARING FAILED IN FLIGHT. 1 G 7 1 3U O H2SW 2001080300187 20010803 00187 SW 2001 8 3 HEEA073400 1 20010611 G 6300 406040322101 BEARING PHIPBH40701 BELL 407 407 SW COOLER BLOWER FAILED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 740PH PHI0002 53435 NR 1 BEARING FAILED IN FLIGHT. 1 G 7 1 3U O H2SW 2001080300188 20010803 00188 SW 2001 8 3 HEEA073401 1 20010611 G 6300 407340339103 BEARING PHIPBH40701 BELL 407 407 SW COOLER BLOWER FAILED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 740PH PHI0002 53435 NR 1 BEARING FAILED IN FLIGHT. SERIAL NUMBERS REMOVED ARE M00-0854 AND M00-0882. 1 G 7 1 3U O H2SW 2001080300189 20010803 00189 SW 2001 8 3 HEEA073402 1 20010611 G 6300 407340339103 BEARING PHIPBH40701 BELL 407 407 SW COOLER BLOWER OVERHEATED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 467PH PHI0007 53142 DISCOLORATION OF BEARING GREASE. SERIAL NUMBERS REMOVED ARE B01-0810 AND B01-0817. 1 G 7 1 3U O H2SW 2001080300190 20010803 00190 SW 2001 8 3 HEEA073403 1 20010611 G 6510 206061432121 HOUSING BELL 407 407 SW COOLER BLOWER DAMAGED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 494PH 53396 WORKING RIVETS. 1 G 7 1 3U O H2SW 2001080300191 20010803 00191 SW 2001 8 3 HEEA073405 1 20010611 G 6510 206061432121 HOUSING BELL 407 407 SW COOLER BLOWER CRACKED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 467PH 53142 CRACKED. 1 G 7 1 3U O H2SW 2001080300192 20010803 00192 SW 2001 8 3 HEEA073406 1 20010611 G 6710 406310404101 ROD END BELL 407 407 1182206 SW MAIN ROTOR WORN E K NONE O OTHER IN INSP/MAINT 1 SW 03 57416 4857 53070 MAIN ROTOR ROD END HAS WORN BEARINGS. 1 G 7 1 3U O H2SW 2001080300193 20010803 00193 SW 2001 8 3 HEEA073407 1 20010611 G 3212 206050247131 COVER BELL 407 407 SW FLOAT WORN E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 499PH 53400 VELCRO ON END CAPS WORN. 1 G 7 1 3U O H2SW 2001080300194 20010803 00194 SW 2001 8 3 HEEA073408 1 20010611 G 3212 206050247132 COVER BELL 407 407 SW FLOAT WORN E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 499PH 53400 VELCRO ON END CAPS WORN. 1 G 7 1 3U O H2SW 2001080300195 20010803 00195 SW 2001 8 3 HEEA073409 1 20010611 G 6320 407040623101 LINE BELL 407 407 SW OIL SYSTEM LEAKING E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 724PH 53327 LEAKING AT FLARE. 1 G 7 1 3U O H2SW 2001080300196 20010803 00196 SW 2001 8 3 HEEA073410 1 20010611 G 6510 206061432121 HOUSING BELL 407 407 SW BLOWER CRACKED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 724PH 53327 CRACKED IN TWO PLACES. 1 G 7 1 3U O H2SW 2001080300197 20010803 00197 SW 2001 8 3 HEEA073411 1 20010611 G 7810 407063001101 EXHAUST STACK BELL 407 407 SW ENGINE CRACKED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 724PH 53327 CRACKED AROUND BASE. 1 G 7 1 3U O H2SW 2001080300198 20010803 00198 SW 2001 8 3 HEEA073412 1 20010611 G 6710 406310405101 UNIVERSAL JOINT BELL 407 407 SW TAIL ROTOR WORN E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 491PH 654 53386 WORN BEARING. 1 G 7 1 3U O H2SW 2001080300199 20010803 00199 SW 2001 8 3 HEEA073413 1 20010611 G 6320 407040623101 LINE BELL 407 407 SW OIL SYSTEM LEAKING E HEEA K NONE K FLUID LOSS IN INSP/MAINT 1 SW 03 408PH 53228 FLARE LEAKING. 1 G 7 1 3U O H2SW 2001080300216 20010803 00216 SW 2001 8 3 HEEA073414 1 20010611 G 6220 407310101101 BEARING BELL 407 407 SW MAIN ROTOR CRACKED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 720PH 2331 53277 SHIM CRACKED. 1 G 7 1 3U O H2SW 2001080300219 20010803 00219 SW 2001 8 3 HEEA073416 1 20010611 G 6230 406310411101 BOOT BELL 407 407 SW MAIN ROTOR CRACKED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 407PH 53003 CRACKED. SCRAPPED ON SITE. 1 G 7 1 3U O H2SW 2001080300220 20010803 00220 SW 2001 8 3 HEEA073417 1 20010611 G 6321 PAD BELL 407 407 SW ROTOR BRAKE WORN E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 492PH 53390 WORN PADS. 1 G 7 1 3U O H2SW 2001080300222 20010803 00222 SW 2001 8 3 HEEA073418 1 20010611 G 6710 407030211101 COVER BELL 407 407 SW COLLECTIVE BROKEN E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 724PH 53327 BROKEN. SCRAPPED ON SITE. PHI REQUESTS FOR CREDIT AGAINST REPLACEMENT PART PURCHASED. REFERENCE: DMR#711790. 1 G 7 1 3U O H2SW 2001080300229 20010803 00229 SW 2001 8 3 HEEA073419 1 20010611 G 6710 407030211101 COVER BELL 407 407 SW COLLECTIVE BROKEN E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 724PH 53327 BROKEN. SCRAPPED ON SITE. 1 G 7 1 3U O H2SW 2001080300231 20010803 00231 SW 2001 8 3 HEEA073422 1 20010611 G 6310 214040841101 SEAL BELL 407 407 SW FREEWHEEL UNIT LEAKING E HEEA K NONE K FLUID LOSS IN INSP/MAINT 1 SW 03 407PH 53003 LEAKING. SCRAPPED IN HOUSE. 1 G 7 1 3U O H2SW 2001080300232 20010803 00232 SW 2001 8 3 HEEA073423 1 20010611 G 2910 70079H000Y150 HOSE BELL 407 407 SW MLG FRAYED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 409PH 53059 FRAYED. SCRAPPED IN HOUSE. 1 G 7 1 3U O H2SW 2001080300255 20010803 00255 EU 2001 8 3 HEEA073433 1 20010611 G 2560 AFG0348056 HARNESS SNIAS 350 AS350B2 8680813 EU SEAT BELT INOPERATIVE E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 4034Q 2918 REEL INOPERATIVE. 1 G 7 1 3U H9EU 2001080300259 20010803 00259 EU 2001 8 3 HEEA073434 1 20010611 G 2822 P94B12209 PUMP SNIAS 350 AS350B 8680801 EU FUEL SYSTEM INTERMITTENT E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 973AE 691 3229 PUMP INTERMITTENTLY NOT COMING ON. 1 G 7 1 3U H9EU 2001080300260 20010803 00260 2001 8 3 HEEA073437 4 20010611 G 3421 5040111916 GYRO SNIAS 350 AS350B 8680801 EU COCKPIT MALFUNCTIONED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 972AE 3234 TUMBLES WHEN POWER APPLIED. 1 G 7 1 3U H9EU 2001080300261 20010803 00261 EU 2001 8 3 HEEA073515 1 20010619 G 2612 9560132140 FIRE DETECTOR SNIAS 350 AS350B2 8680813 EU TMECA ARRIEL ARRIEL1D NE ENGINE INTERMITTENT E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 4034Q 2918 9432 INTERMITTENT. 1 G 7 1 3U 3 U H9EU E19EU 2001080300292 20010803 00292 NE 2001 8 3 HEEA073516 2 20010619 G 7412 9550173220 EXCITER SKRSKY S76 S76C 8143008 NE TMECA ARRIEL ARRIEL1D NE ENGINE INOPERATIVE E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 505PH 760505 INOPERATIVE. 1 G 7 2 3U 3 U NC H1NE E19EU 2001080600006 20010806 00006 NE 2001 8 6 HEEA073517 2 20010619 G 7310 0292958050 VALVE SKRSKY S76 S76C 8143008 NE TMECA ARRIEL ARRIEL1S1 60030 NE ENGINE LEAKING E HEEA O OTHER K B FLUID LOSS SMOKE/FUMES/ODORS/SPARKS NR NOT REPORTED 1 SW 03 505PH 1441 760505 20017 FUEL SMELL IN COCKPIT DURING START. 1 G 7 2 3U 3 U NC H1NE E19EU 2001080600008 20010806 00008 NE 2001 8 6 HEEA073518 2 20010619 G 7200 9560115450 MAGNETIC SEAL SNIAS 350 AS350B 8680801 EU TMECA ARRIEL ARRIEL1D NE ENGINE LEAKING E HEEA O OTHER K FLUID LOSS NR NOT REPORTED 1 SW 03 856PH 3352 9728 LEAKING. 1 G 7 1 3U 3 U H9EU E19EU 2001080600009 20010806 00009 NE 2001 8 6 HEEA073519 2 20010619 G 7200 9560137520 MAGNETIC SEAL SNIAS 350 AS350B 8680801 EU TMECA ARRIEL ARRIEL1D NE ENGINE LEAKING E HEEA O OTHER K FLUID LOSS NR NOT REPORTED 1 SW 03 856PH 3352 9728 LEAKING. 1 G 7 1 3U 3 U H9EU E19EU 2001080600011 20010806 00011 NE 2001 8 6 HEEA073520 2 20010619 G 7200 0292005310 ENGINE SKRSKY S76 S76C 8143008 NE TMECA ARRIEL ARRIEL1S 60030 NE NACELLE MALFUNCTIONED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 505PH 1622 760505 HIGH OIL CONSUMPTION. 1 G 7 2 3U 3 U NC H1NE E19EU 2001080600016 20010806 00016 NE 2001 8 6 HEEA073521 1 20010619 G 6730 30006762102 MANIFOLD 766500980511 SKRSKY S76 S76A 8143006 NE MAIN ROTOR LEAKING E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 1002 CAUSING LEAKAGE BETWEEN MAIN AND BYPASS SERVO VALVES ON SYSTEM ONE ON FINAL TEST. FOUND MISSING LEE PLUG IN DRILLED PAS SAGE ON SYSTEM ONE BETWEEN MAIN AND BYPASS SERVO VALVES. SENDING TO VENDOR FOR REPAIR. 1 G 7 2 3U H1NE 2001080600022 20010806 00022 2001 8 6 HEEA073522 4 20010619 G 3442 7021450601 COMPUTER SKRSKY S76 S76A 8143006 NE COCKPIT INOPERATIVE E O OTHER O OTHER NR NOT REPORTED 1 SW 03 760PH 760078 WX RADAR SYSTEM INOPERATIVE. 1 G 7 2 3U H1NE 2001080600023 20010806 00023 NE 2001 8 6 HEEA073523 1 20010619 G 6230 7610408020047 SCISSORS SKRSKY S76 S76A 8143006 NE MAIN ROTOR WORN E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 4253S 760035 WORN BUSHINGS. REPLACED WITH SERVICEABLE PART. 1 G 7 2 3U H1NE 2001080600025 20010806 00025 NE 2001 8 6 HEEA073524 1 20010619 G 2435 7630007661043 DUCT SKRSKY S76 S76C 8143008 NE STARTER GEN CRACKED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 505PH 760505 CRACKED. SENDING TO VENDOR FOR REPAIR. 1 G 7 2 3U NC H1NE 2001080600027 20010806 00027 NE 2001 8 6 HEEA073525 1 20010619 G 6300 7635109045102 GEAR SKRSKY S76 S76A 8143006 NE M/R DRIVE DAMAGED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 NO RIVET IN CENTER OF GEAR. SENDING TO VENDOR FOR REPAIR. 1 G 7 2 3U H1NE 2001080600029 20010806 00029 2001 8 6 HEEA073526 4 20010619 G 3160 7645001098105 DISPLAY SKRSKY S76 S76C 8143008 NE COCKPIT INTERMITTENT E HEEA O OTHER N FALSE WARNING NR NOT REPORTED 1 SW 03 505PH 760505 CENTER DISPLAY UNIT SHOWING AN INTERMITTENT FAIL FAULT ALONG WITH GIVING INTERMITTENT INCORRECT INFORMATION AND CAUSING INTERMITTENT NR 1 AND 2 ENGINE OUT WARNING LIGHTS TO COME ON IN FLIGHT. SENT TO VENDOR FOR REPAIR. 1 G 7 2 3U NC H1NE 2001080600031 20010806 00031 NE 2001 8 6 HEEA073527 1 20010619 G 2120 7650007901103 BLOWER SKRSKY S76 S76C 8143008 NE CABIN INOPERATIVE E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 505PH 760505 OPEN BETWEEN PINS A AND C. SENT TO VENDOR FOR REPAIR. 1 G 7 2 3U NC H1NE 2001080600034 20010806 00034 2001 8 6 HEEA073529 4 20010619 G 2215 7690001802106 ACTUATOR SKRSKY S76 S76C 8143008 NE AFCS MALFUNCTIONED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 505PH 760505 FULL RIGHT HARD OVER. SENT TO VENDOR FOR REPAIR. 1 G 7 2 3U NC H1NE 2001080600036 20010806 00036 2001 8 6 HEEA073530 4 20010619 G 2215 7690001802106 ACTUATOR SKRSKY S76 S76C 8143008 NE AFCS INOPERATIVE E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 505PH 760505 SHOWS NO MOVEMENT ON INDICATOR. SENT TO VENDOR FOR REPAIR. 1 G 7 2 3U NC H1NE 2001080600038 20010806 00038 2001 8 6 HEEA073531 4 20010619 G 2215 7690001802106 ACTUATOR SKRSKY S76 S76C 8143008 NE AFCS INOPERATIVE E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 505PH 760505 AFCS SYSTEM SHOWS NO MOVEMENT ON INDICATOR. SENT TO VENDOR FOR REPAIR. 1 G 7 2 3U NC H1NE 2001080600040 20010806 00040 NE 2001 8 6 HEEA073532 1 20010619 G 6730 7826002 SERVO SKRSKY S76 S76C 8143008 NE TAIL ROTOR LEAKING E HEEA O OTHER K J FLUID LOSS WARNING INDICATION NR NOT REPORTED 1 SW 03 505PH 760505 LEAKING PAST SERVO ACTUATOR PISTON. SENT TO VENDOR FOR REPAIR. 1 G 7 2 3U NC H1NE 2001080600041 20010806 00041 2001 8 6 HEEA073533 4 20010619 G 3457 81439000232 RECEIVER SKRSKY S76 S76A 8143006 NE GPS MALFUNCTIONED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 3122G 760232 WILL NOT RECOGNIZE DATA CARD. SENDING TO VENDOR FOR REPAIR. 1 G 7 2 3U H1NE 2001080600044 20010806 00044 GL 2001 8 6 HEEA073534 2 20010620 G 7261 23066681 FILTER HOUSING BELL 407 407 SW ALLSN 250C 250C47B GL OIL FILTER BOWL MALFUNCTIONED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 407PH 53003 OIL FILTER BOWL BYPASS BUTTON POPS CONTINUOUSLY. REPLACED WITH SERVICEABLE PART. 1 G 7 1 3U 3 U O H2SW E1GL 2001080600049 20010806 00049 SW 2001 8 6 HEEA073535 1 20010620 G 2821 23066697 FILTER BELL 407 407 SW FUEL SYSTEM CLOGGED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 493PH 53393 POPPED BYPASS BUTTON. REPLACED WITH SERVICEABLE PART. 1 G 7 1 3U O H2SW 2001080600051 20010806 00051 GL 2001 8 6 HEEA073537 2 20010620 G 7320 23072725 HMU BELL 407 407 SW ALLSN 250C 250C47B GL ENGINE NOISY E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 723PH 53283 LOUD HUMMING NOISE IN ENGINE COMPARTMENT WITH BOOST PUMPS ON. REPLACED WITH SERVICEABLE PART. 1 G 7 1 3U 3 U O H2SW E1GL 2001080600052 20010806 00052 NE 2001 8 6 HEEA073538 2 20010620 G 7200 0292005310 ENGINE SKRSKY S76 S76C 8143008 NE TMECA ARRIEL ARRIEL1S1 60030 NE ENGINE BAY MAKING METAL E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 505PH 1734 760505 FOUND OIL SAMPLE HAS HIGH IRON. 1 G 7 2 3U 3 U NC H1NE E19EU 2001080600053 20010806 00053 NE 2001 8 6 HEEA073539 2 20010620 G 7200 70BMA01030 ECU SKRSKY S76 S76C 8143008 NE TMECA ARRIEL ARRIEL1S1 60030 NE NR 1 ENGINE MALFUNCTIONED E HEEA O OTHER O OTHER IN INSP/MAINT 1 SW 03 505PH 2021 760505 REVERSION LIGHT ON NR 1 THROTTLE STAYS ON. 1 G 7 2 3U 3 U NC H1NE E19EU 2001080600054 20010806 00054 NE 2001 8 6 HEEA073540 1 20010620 G 2820 PT06CE84SSR CONNECTOR SKRSKY S76 S76A 8143006 NE NR 2 ENGINE DIRTY E HEEA O OTHER N FALSE WARNING CR CRUISE 1 SW 03 1546K 760082 WHILE IN CRUISE FLIGHT, THE NR 2 ENGINE FUEL FLOW INDICATOR BEGAN TO FLUCTUATE. CLEANED CANNON PLUG AT TRANSMITTER. 1 G 7 2 3U H1NE 2001080600055 20010806 00055 SW 2001 8 6 HEEA073558 1 20010615 G 8011 214060056103 STARTER BELL 214 214ST 1182106 SW ENGINE MALFUNCTIONED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 SLOW TO START. 2 G 7 2 4U H10SW 2001080600056 20010806 00056 SW 2001 8 6 HEEA073559 1 20010615 G 8011 214060056103 STARTER BELL 214 214ST 1182106 SW ENGINE FAILED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 DISENGAGES DURING BATTERY START. 2 G 7 2 4U H10SW 2001080600057 20010806 00057 SW 2001 8 6 HEEA073563 1 20010618 G 6700 206001552001 BELLCRANK BELL 206 206L3 1182108 SW FLIGHT CONTROLS WORN E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 6160Y 51609 PIVOT BUSHING WORN AND BEARINGS WORN. REPLACED WITH SERVICEABLE BELLCRANK ASSEMBLY. 1 G 7 1 3U H2SW 2001080600058 20010806 00058 SW 2001 8 6 HEEA073564 1 20010618 G 6700 206001554001 SUPPORT FITTING BELL 206 206L3 1182108 SW CYCLIC BELLCRANK WARPED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 206LS 51070 CYCLIC BELLCRANK SUPPORT ASSY. WARPED. SCRAPPED AND REPLACED WITH SERVICEABLE SUPPORT ASSY. 1 G 7 1 3U H2SW 2001080600059 20010806 00059 SW 2001 8 6 HEEA073565 1 20010618 G 6710 206001713101 SUPPORT BRACKET BELL 206 206L1 1182107 SW MAIN ROTOR CORRODED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 5014V 45217 EXCESSIVE CORROSION. SCRAPPED AND REPLACED WITH SERVICEABLE SUPPORT ASSY. 1 G 7 1 3U H2SW 2001080600060 20010806 00060 SW 2001 8 6 HEEA073566 1 20010618 G 6220 206010003007 CONE SET BELL 206 206L1 1182107 SW M/R HEAD CORRODED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 5014V 45217 CORROSION PITTING ON SURFACE OF CONES. REPLACED WITH SERVICEABLE ASSY. 1 G 7 1 3U H2SW 2001080600064 20010806 00064 SW 2001 8 6 HEEA073567 1 20010618 G 6420 206010795103 PITCH LINK BELL 206 206L3 1182108 SW TAIL ROTOR WORN E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 6251X 51552 WORN. REPLACED WITH SERVICEABLE ASSY. 1 G 7 1 3U H2SW 2001080600065 20010806 00065 SW 2001 8 6 HEEA073568 1 20010618 G 6420 206010795105 PITCH LINK BELL 206 206L3 1182108 SW TAIL ROTOR WORN E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 21497 51518 WORN. REPLACED WITH SERVICEABLE ASSY. 1 G 7 1 3U H2SW 2001080600066 20010806 00066 SW 2001 8 6 HEEA073569 1 20010618 G 6420 206010802101 BUSHING BELL 206 206L1 1182107 SW TAIL ROTOR WORN E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 5007Q 45187 WORN. REPLACED WITH SERVICEABLE ASSY. 1 G 7 1 3U H2SW 2001080600067 20010806 00067 SW 2001 8 6 HEEA073570 1 20010618 G 6220 206011117003 RESTRAINT BELL 206 206L3 1182108 SW FLAP WEAK E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 206FS 51506 SPRINGS WEAK AND STICKING ARMS. REPLACED WITH SERVICEABLE ASSY. 1 G 7 1 3U H2SW 2001080600068 20010806 00068 SW 2001 8 6 HEEA073571 1 20010618 G 6220 206011117003 RESTRAINT BELL 206 206L1 1182107 SW FLAP STUCK E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 5019F 45244 YELLOW BLADE RESTRAINT STICKING IN STOWED POSITION. REPLACED WITH SERVICEABLE ASSY. 1 G 7 1 3U H2SW 2001080600069 20010806 00069 SW 2001 8 6 HEEA073572 1 20010618 G 6220 206011117003 RESTRAINT BELL 206 206L4 1182110 SW FLAP STUCK E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 7077F 52038 STICKING. REPLACED WITH SERVICEABLE ASSY. 1 G 7 1 3U NC H2SW 2001080600070 20010806 00070 SW 2001 8 6 HEEA073573 1 20010618 G 6200 206011135007 BOLT BELL 206 206L3 1182108 SW MAIN ROTOR CRACKED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 2619 51375 END CAP CRACKED. REPLACED WITH SERVICEABLE ASSY. 1 G 7 1 3U H2SW 2001080600071 20010806 00071 SW 2001 8 6 HEEA073574 1 20010618 G 6400 206011725001 ROD BELL 206 206L3 1182108 SW TAIL ROTOR BINDING E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 21497 51518 BINDING. REPLACED WITH SERVICEABLE ASSY. 1 G 7 1 3U H2SW 2001080600073 20010806 00073 SW 2001 8 6 HEEA073575 1 20010618 G 6400 206011725001 ROD BELL 206 206L1 1182107 SW TAIL ROTOR ROUGH E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 45RP 45521 ROUGH BEARING. REPLACED WITH SERVICEABLE ASSY. 1 G 7 1 3U H2SW 2001080600074 20010806 00074 SW 2001 8 6 HEEA073576 1 20010618 G 6400 206011725001 ROD BELL 206 206L3 1182108 SW TAIL ROTOR WORN E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 6160Y 51609 WORN BEARING. REPLACED WITH SERVICEABLE ASSY. 1 G 7 1 3U H2SW 2001080600075 20010806 00075 SW 2001 8 6 HEEA073577 1 20010618 G 5302 206032308003 FRAME BELL 206 206L3 1182108 SW TAIL BOOM CRACKED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 41791 51465 CRACKED TAILBOOM MOUNTING RING. REPLACED WITH SERVICEABLE ASSY. 1 G 7 1 3U H2SW 2001080600077 20010806 00077 SW 2001 8 6 HEEA073578 1 20010618 G 5302 206032308103 FRAME BELL 206 206L3 1182108 SW TAIL BOOM CRACKED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 4835 51131 TAILBOOM RING CRACKED AT ATTACHMENT HOLE. REPLACED WITH SERVICEABLE ASSY. 1 G 7 1 3U H2SW 2001080600079 20010806 00079 SW 2001 8 6 HEEA073579 1 20010618 G 5312 206033107107B BULKHEAD BELL 206 206L3 1182108 SW FUSELAGE CORRODED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 41128 51134 SEVERE CORROSION AT LATCH AREA WHERE SHIM WAS BONDED WITH ADHESIVE. REPLACED WITH SERVICEABLE ASSY. 1 G 7 1 3U H2SW 2001080600081 20010806 00081 SW 2001 8 6 HEEA073580 1 20010618 G 5320 206033302101 CHANNEL BELL 206 206L3 1182108 SW FUSELAGE CRACKED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 4835 51131 BULKHEAD CRACKED AT LT FWD ENGINE MOUNT HOLE IN UPPER FLANGE RADIUS. REPLACED WITH SERVICEABLE ASSY. 1 G 7 1 3U H2SW 2001080600082 20010806 00082 SW 2001 8 6 HEEA073581 1 20010618 G 5330 206033310139 ACCESS PANEL BELL 206 206L3 1182108 SW FUSELAGE CORRODED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 4835 51131 CORRODED AT ACCESS PANEL AREA BEYOND LIMITS. REPLACED WITH SERVICEABLE ASSY. 1 G 7 1 3U H2SW 2001080600084 20010806 00084 SW 2001 8 6 HEEA073582 1 20010618 G 5302 206033407101 COWLING BELL 206 206L4 1182110 SW TAIL ROTOR CRACKED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 7074W 52033 CRACKED AND CHAFED. REPLACED WITH SERVICEABLE ASSY. 1 G 7 1 3U NC H2SW 2001080600086 20010806 00086 SW 2001 8 6 HEEA073583 1 20010618 G 3212 206030104023 FITTING BELL 206 206L3 1182108 SW FLOAT DAMAGED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 42EA 51542 RUBBER MISSING. REPLACED WITH SERVICEABLE ASSY. 1 G 7 1 3U H2SW 2001080600088 20010806 00088 SW 2001 8 6 HEEA073584 1 20010618 G 2730 BELLCRANK BELL 206 206L3 1182108 SW ELEVATOR ASSY BINDING E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 31077 51520 BELLCRANK BEARING BINDING AT TIMES. REPLACED WITH SERVICEABLE ASSY. 1 G 7 1 3U H2SW 2001080600092 20010806 00092 SW 2001 8 6 HEEA073585 1 20010618 G 3212 206030104023 FITTING BELL 206 206L3 1182108 SW FLOAT DAMAGED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 21497 51518 RUBBER MISSING. REPLACED WITH SERVICEABLE ASSY. 1 G 7 1 3U H2SW 2001080600094 20010806 00094 SW 2001 8 6 HEEA073586 1 20010618 G 6330 206033506101 RESTRAINT BELL 206 206L1 1182107 SW TRANSMISSION WORN E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 45RP 45521 WORN BEARINGS. 1 G 7 1 3U H2SW 2001080600097 20010806 00097 SW 2001 8 6 HEEA073587 1 20010618 G 6330 206033516101 FLEXURE BELL 206 206L3 1182108 SW TRANSMISSION DETERIORATED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 21497 51518 RUBBER DETERIORATED. 1 G 7 1 3U H2SW 2001080600139 20010806 00139 SW 2001 8 6 HEEA073588 1 20010618 G 6300 206033518007 STOP BELL 206 206L3 1182108 SW M/R DRIVE WORN E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 6251X 51552 WORN BEARING. 1 G 7 1 3U H2SW 2001080600141 20010806 00141 SW 2001 8 6 HEEA073589 1 20010618 G 6300 206033554101 LINK BELL 206 206L3 1182108 SW M/ROTOR DRIVE DETERIORATED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 41128 51134 BEARINGS SEPARATED AND DETERIORATED BEYOND LIMITS. 1 G 7 1 3U H2SW 2001080600146 20010806 00146 SW 2001 8 6 HEEA073590 1 20010618 G 6300 206033554101 LINK BELL 206 206L3 1182108 SW M/R DRIVE DETERIORATED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 41128 51134 BEARINGS SEPARATED AND DETERIORATED BEYOND LIMITS. 1 G 7 1 3U H2SW 2001080600147 20010806 00147 SW 2001 8 6 HEEA073591 1 20010618 G 6300 206033554101 LINK BELL 206 206L3 1182108 SW M/R DRIVE DAMAGED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 41128 51134 MECHANICAL DAMAGE BEYOND LIMITS. 1 G 7 1 3U H2SW 2001080600149 20010806 00149 SW 2001 8 6 HEEA073592 1 20010618 G 6300 206033554101 LINK BELL 206 206L3 1182108 SW LT PYLON DAMAGED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 8591X 51495 LT AFT PYLON LINK UPPER BEARING EXTRUDING. 1 G 7 1 3U H2SW 2001080600150 20010806 00150 SW 2001 8 6 HEEA073593 1 20010618 G 6300 206033554101 LINK BELL 206 206L3 1182108 SW M/R DRIVE WORN E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 6251Y 51556 ELASTOMERIC BEARING SEPARATED. 1 G 7 1 3U H2SW 2001080600151 20010806 00151 SW 2001 8 6 HEEA073594 1 20010618 G 6300 206033554101 LINK BELL 206 206L3 1182108 SW M/R DRIVE DAMAGED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 8591X 51495 RT FWD PYLON LINK UPPER BEARING EXTRUDING. 1 G 7 1 3U H2SW 2001080600152 20010806 00152 SW 2001 8 6 HEEA073595 1 20010618 G 6300 206033554101 LINK BELL 206 206L3 1182108 SW M/R DRIVE DAMAGED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 42EA 51542 ELASTOMERIC BEARING AT UPPER END HAS RUBBER COMING UNBONDED. 1 G 7 1 3U H2SW 2001080600158 20010806 00158 SW 2001 8 6 HEEA073596 1 20010618 G 6300 206033554101 LINK BELL 206 206L3 1182108 SW M/R DRIVE DAMAGED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 92MT 51175 ELASTOMERIC DEBONDED. 1 G 7 1 3U H2SW 2001080600159 20010806 00159 SW 2001 8 6 HEEA073597 1 20010618 G 7600 206062721103 ACTUATOR BELL 206 206L1 1182107 SW ENGINE CONTROLS INOPERATIVE E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 SPREAD WILL NOT WORK. 1 G 7 1 3U H2SW 2001080600160 20010806 00160 SW 2001 8 6 HEEA073598 1 20010618 G 7600 206062721105 ACTUATOR BELL 206 206L3 1182108 SW ENGINE CONTROLS INTERMITTENT E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 6251X 51552 INTERMITTENT. 1 G 7 1 3U H2SW 2001080600161 20010806 00161 SW 2001 8 6 HEEA073599 1 20010618 G 7600 206062721109 ACTUATOR BELL 206 206L3 1182108 SW ENGINE CONTROLS STUCK E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 8588X 51486 STICKING, WILL NOT ACTUATE. 1 G 7 1 3U H2SW 2001080600162 20010806 00162 SW 2001 8 6 HEEA073600 1 20010618 G 7600 206062721109 ACTUATOR BELL 206 206L3 1182108 SW ENGINE CONTROLS STUCK E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 8594X 51531 STICKING, WILL NOT ACTUATE. 1 G 7 1 3U H2SW 2001080600163 20010806 00163 SW 2001 8 6 HEEA073601 1 20010618 G 7600 206062721109 ACTUATOR BELL 206 206L3 1182108 SW ENGINE CONTROLS STUCK E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 3116P 51530 STICKING. 1 G 7 1 3U H2SW 2001080600164 20010806 00164 SW 2001 8 6 HEEA073602 1 20010618 G 2121 206070475005 BLOWER BELL 412 412 1182202 SW CABIN FAILED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 142PH 33150 POPS CIRCUIT BREAKER. REPLACED WITH SERVICEABLE PART. 1 G 7 2 4U H4SW 2001080600165 20010806 00165 SW 2001 8 6 HEEA073603 1 20010618 G 2424 206075447007 VOLT REGULATOR BELL 206 206L3 1182108 SW GENERATOR FAILED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 6610C 51425 GENERATOR DROPS OFF LINE. 1 G 7 1 3U H2SW 2001080600166 20010806 00166 SW 2001 8 6 HEEA073604 1 20010618 G 3246 206323017 CROSSTUBE BELL 206 206L1 1182107 SW MLG CORRODED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 3178K 45765 CORROSION BEYOND LIMITS. REPLACED WITH SERVICEABLE CROSSTUBE. 1 G 7 1 3U H2SW 2001080600167 20010806 00167 SW 2001 8 6 HEEA073605 1 20010618 G 3246 206323018 CROSSTUBE BELL 206 206L1 1182107 SW MLG CORRODED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 3178K 45765 CORROSION BEYOND LIMITS. REPLACED WITH SERVICEABLE CROSSTUBE. 1 G 7 1 3U H2SW 2001080600168 20010806 00168 SW 2001 8 6 HEEA073606 1 20010618 G 3246 206323018 CROSSTUBE BELL 206 206L3 1182108 SW MLG CORRODED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 42EA 51542 CORROSION BEYOND LIMITS. REPLACED WITH SERVICEABLE CROSSTUBE. 1 G 7 1 3U H2SW 2001080600169 20010806 00169 SW 2001 8 6 HEEA073607 1 20010618 G 2842 206364601101 TRANSMITTER BELL 206 206L3 1182108 SW FUEL INDICATOR FAILED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 31077 51520 WILL NOT INDICATE FUEL QUANTITY IN FORWARD CELLS. 1 G 7 1 3U H2SW 2001080600212 20010806 00212 SW 2001 8 6 HEEA073609 1 20010618 G 2437 209070263003 INDICATOR BELL 412 412 1182202 SW DUAL VOLT STUCK E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 142PH 33150 NEEDLE STICKS, AMP METER SIDE. 1 G 7 2 4U H4SW 2001080600215 20010806 00215 SW 2001 8 6 HEEA073610 1 20010618 G 6720 212001705001 BELLCRANK BELL 412 412 1182202 SW TAIL ROTOR DAMAGED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 3893L 33006 BEARING UNSTAKED. REPLACED WITH SERVICEABLE BELLCRANK. 1 G 7 2 4U H4SW 2001080600218 20010806 00218 SW 2001 8 6 HEEA073611 1 20010618 G 6720 212001705001 BELLCRANK BELL 412 412 1182202 SW TAIL ROTOR WORN E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 2261D 33076 WORN BEARINGS. REPLACED WITH SERVICEABLE BELLCRANK. 1 G 7 2 4U H4SW 2001080600220 20010806 00220 SW 2001 8 6 HEEA073612 1 20010618 G 6720 212001710001 BELLCRANK BELL 412 412 1182202 SW TAIL ROTOR DAMAGED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 1202T 33112 SNAP RING MISSING FROM BEARING. REPLACED WITH SERVICEABLE PART. 1 G 7 2 4U H4SW 2001080600221 20010806 00221 SW 2001 8 6 HEEA073613 1 20010618 G 6720 212060740001 BELLCRANK BELL 412 412 1182202 SW TAIL ROTOR WORN E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 2261D 33076 BEARING WORN. REPLACED WITH SERVICEABLE PART. 1 G 7 2 4U H4SW 2001080600222 20010806 00222 SW 2001 8 6 HEEA073614 1 20010618 G 6720 212060740001 BELLCRANK BELL 412 412 1182202 SW TAIL ROTOR WORN E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 107X 33113 BEARING WORN. REPLACED WITH SERVICEABLE PART. 1 G 7 2 4U H4SW 2001080600224 20010806 00224 SW 2001 8 6 HEEA073615 1 20010618 G 7600 212061101001 BEARING BELL 412 412 1182202 SW ENGINE CONTROLS WORN E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 108X 33115 BEARING WORN. REPLACED WITH SERVICEABLE PART. 1 G 7 2 4U H4SW 2001080600225 20010806 00225 SW 2001 8 6 HEEA073616 1 20010618 G 7600 206062721109 ACTUATOR BELL 206 206L1 1182107 SW ENGINE CONTROLS INOPERATIVE E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 2124Z 45646 BEEP ACTUATOR INOPERATIVE. 1 G 7 1 3U H2SW 2001080600227 20010806 00227 SW 2001 8 6 HEEA073617 1 20010618 G 2810 206063632101 FUEL CELL BELL 206 206L3 1182108 SW FUSELAGE LEAKING E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 3116P 51530 FILLED CELL WITH FUEL AND LT FWD FUEL CELL STARTING LEAKING AT WEEP HOLE. 1 G 7 1 3U H2SW 2001080600228 20010806 00228 SW 2001 8 6 HEEA073618 1 20010618 G 2840 206064635101 TRANSMITTER BELL 206 206L3 1182108 SW FUEL INDICTOR FAILED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 4835 51131 CAUSES NEEDLE TO DROP TO ZERO IN FLIGHT. 1 G 7 1 3U H2SW 2001080600229 20010806 00229 SW 2001 8 6 HEEA073619 1 20010618 G 3110 206070266007 INDICATOR BELL 206 206L1 1182107 SW COCKPIT MALFUNCTIONED E HEEA O OTHER N FALSE WARNING NR NOT REPORTED 1 SW 03 5007Q 45187 INSTRUMENT INDICATES 3-4 PERCENT WHEN SYSTEMS ARE SHUT DOWN AND TAKES 5-6 SECONDS TO START INDICATING DURING STARTS. 1 G 7 1 3U H2SW 2001080600232 20010806 00232 SW 2001 8 6 HEEA073620 1 20010618 G 2436 206075447007 VOLT REGULATOR BELL 206 206L3 1182108 SW GENERATOR MALFUNCTIONED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 21497 51518 GENERATOR WENT OFF LINE AND WON'T RESET. 1 G 7 1 3U H2SW 2001080600233 20010806 00233 SW 2001 8 6 HEEA073621 1 20010618 G 2436 206075447007 VOLT REGULATOR BELL 206 206L3 1182108 SW GENERATOR MALFUNCTIONED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 21497 51518 ON FIRST START OF THE DAY, GENERATOR WILL NOT COME ON LINE. 1 G 7 1 3U H2SW 2001080600236 20010806 00236 SW 2001 8 6 HEEA073622 1 20010618 G 7714 206075545005 SENSOR BELL 206 206L3 1182108 SW MAIN ROTOR MALFUNCTIONED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 42EA 51542 LOW RPM AUDIO COMES ON INTERMITTENTLY AT IDLE AFTER MUTE BUTTON HAS BEEN DEPRESSED. AUDIO AND LIGHT FLICKER AT 100 PERC ENT N2. 1 G 7 1 3U H2SW 2001080600240 20010806 00240 SW 2001 8 6 HEEA073623 1 20010618 G 7933 206075678107 INDICATOR BELL 206 206L3 1182108 SW OIL TEMP FAILED E HEEA O OTHER N FALSE WARNING NR NOT REPORTED 1 SW 03 6603X 51412 OIL TEMPERATURE WOULD NOT COME UP OFF BOTTOM OF IND. 1 G 7 1 3U H2SW 2001080600242 20010806 00242 SW 2001 8 6 HEEA073624 1 20010618 G 7714 206075681105 INDICATOR BELL 206 206L3 1182108 SW DUAL TACH FAILED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 21497 51518 ROTOR NEEDLE DOESN'T ENGAGE UNTIL ALMOST 100 PERCENT ENGINE RPM. 1 G 7 1 3U H2SW 2001080600244 20010806 00244 SW 2001 8 6 HEEA073625 1 20010618 G 7714 206075682103 INDICATOR BELL 206 206L3 1182108 SW ENGINE TACH FAILED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 6160Y 51609 UNRELIABLE AT LOW RPM DURING STARTS. 1 G 7 1 3U H2SW 2001080600246 20010806 00246 SW 2001 8 6 HEEA073626 1 20010618 G 7714 206075682107 INDICATOR BELL 206 206L3 1182108 SW ENGINE TACH FAILED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 141BH 51303 INOPERATIVE. 1 G 7 1 3U H2SW 2001080600247 20010806 00247 SW 2001 8 6 HEEA073627 1 20010618 G 3246 206323002M CROSSTUBE BELL 206 206L3 1182108 SW MLG CORRODED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 206FS 51506 CORROSION PITS BEYOND LIMITS. REPLACED WITH SERVICEABLE CROSSTUBE. 1 G 7 1 3U H2SW 2001080600250 20010806 00250 SW 2001 8 6 HEEA073628 1 20010618 G 3246 206323017 CROSSTUBE BELL 206 206L3 1182108 SW MLG CORRODED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 41128 51134 FWD CROSSTUBE CORRODED BEYOND LIMITS. REPLACED WITH SERVICEABLE CROSSTUBE. 1 G 7 1 3U H2SW 2001080600251 20010806 00251 SW 2001 8 6 HEEA073629 1 20010618 G 3246 206323017 CROSSTUBE BELL 206 206L3 1182108 SW MLG CORRODED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 206FS 51506 CORROSION PITS BEYOND LIMITS. REPLACED WITH SERVICEABLE CROSSTUBE. 1 G 7 1 3U H2SW 2001080600252 20010806 00252 SW 2001 8 6 HEEA073630 1 20010618 G 3246 206323018 CROSSTUBE BELL 206 206L3 1182108 SW MLG CORRODED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 41128 51134 AFT CROSSTUBE CORRODED BEYOND LIMITS. REPLACED WITH SERVICEABLE CROSSTUBE. 1 G 7 1 3U H2SW 2001080600253 20010806 00253 SW 2001 8 6 HEEA073631 1 20010618 G 3246 206323018 CROSSTUBE BELL 206 206L1 1182107 SW MLG CORRODED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 5019F 45244 CORROSION NEAR OR AT CROSSTUBE SADDLE MOUNTING AREA. REPLACED WITH SERVICEABLE CROSSTUBE. 1 G 7 1 3U H2SW 2001080600254 20010806 00254 SW 2001 8 6 HEEA073632 1 20010618 G 3246 206324003 SKID BELL 206 206L3 1182108 SW MLG CORRODED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 41128 51134 LT SKID TUBE CORRODED BEYOND LIMITS. REPLACED WITH SERVICEABLE CROSSTUBE. 1 G 7 1 3U H2SW 2001080600255 20010806 00255 SW 2001 8 6 HEEA073633 1 20010618 G 3246 206324007 SKID BELL 206 206L3 1182108 SW MLG CORRODED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 206FS 51506 CORROSION PITS BEYOND LIMITS. REPLACED WITH SERVICEABLE CROSSTUBE. 1 G 7 1 3U H2SW 2001080600257 20010806 00257 SW 2001 8 6 HEEA073634 1 20010618 G 3246 206324008 SKID BELL 206 206L3 1182108 SW MLG CORRODED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 206FS 51506 CORROSION PITS BEYOND LIMITS. REPLACED WITH SERVICEABLE PART. 1 G 7 1 3U H2SW 2001080600258 20010806 00258 SW 2001 8 6 HEEA073635 1 20010618 G 7933 206375006101 INDICATOR BELL 206 206L1 1182107 SW TOT FLUCTUATES E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 3905B 45598 FLUCTUATES WHEN VHF IS KEYED. SENT TO MASCO FOR INSPECTION AND REPAIR. 1 G 7 1 3U H2SW 2001080600260 20010806 00260 SW 2001 8 6 HEEA073636 1 20010618 G 7933 206375007103 INDICATOR BELL 206 206L3 1182108 SW TOT FAILED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 8593X 51509 NEEDLE WENT TO ZERO. 1 G 7 1 3U H2SW 2001080600276 20010806 00276 SW 2001 8 6 HEEA073637 1 20010618 G 7160 209062214001 ACTUATOR BELL 412 412 1182202 SW AIR INTAKE INOPERATIVE E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 6559Z 36019 INOPERATIVE. 1 G 7 2 4U H4SW 2001080600277 20010806 00277 SW 2001 8 6 HEEA073638 1 20010618 G 7923 209072433101 VALVE BELL 412 412 1182202 SW ENGINE OIL STUCK E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 142PH 33150 WILL NOT OPEN - STICKS. 1 G 7 2 4U H4SW 2001080600279 20010806 00279 SW 2001 8 6 HEEA073639 1 20010618 G 7923 209072433101 VALVE BELL 412 412 1182202 SW ENGINE OIL CORRODED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 1202T 33112 CANNON PLUG WAS CORRODED TO CONNECTOR AND WHEN CANNON PLUG WAS REMOVED VALVE CONNECTOR CAME OFF WITH CANNON PLUG. 1 G 7 2 4U H4SW 2001080600286 20010806 00286 2001 8 6 HEEA073641 4 20010619 G 3454 066107810 RECEIVER BELL 230 230 1182149 SW COCKPIT MALFUNCTIONED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 14UH 23028 CAUSES DISPLAY TO FLICKER AND TURN OFF. SENDING TO VENDOR FOR REPAIR. 1 G 7 2 3U NC H9SW 2001080600290 20010806 00290 SW 2001 8 6 HEEA073642 1 20010619 G 8011 214060056103 STARTER BELL 214 214ST 1182106 SW ENGINE FAILED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 8045T 28101 FUNCTIONAL CHECKED GOOD AND FOUND STARTER WOULD NOT STAY ENGAGED. IT WOULD KICK OFF AFTER APPROX. 5 TO 6 SECONDS. SENDI NG TO VENDOR FOR REPAIR. 2 G 7 2 4U H10SW 2001080600296 20010806 00296 SW 2001 8 6 HEEA073643 1 20010619 G 6322 6038T59P02 BLOWER BELL 214 214ST 1182106 SW COOLING FAILED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 3897N 28106 SHAFT SHEARED. SENDING TO VENDOR FOR REPAIR. 2 G 7 2 4U H10SW 2001080600298 20010806 00298 2001 8 6 HEEA073644 4 20010619 G 3457 0110010600 GPS BELL 412 412 1182202 SW COCKPIT FAILED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 22347 36005 CANNOT FIND ITSELF. IN SHOP REPAIR. 1 G 7 2 4U H4SW 2001080600301 20010806 00301 2001 8 6 HEEA073645 4 20010619 G 3416 066104800 ALTIMETER BELL 412 412 1182202 SW COCKPIT ERRATIC E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 142PH 33150 DISPLAYS ERRATIC ALTITUDE. IN SHOP REPAIR. 1 G 7 2 4U H4SW 2001080600303 20010806 00303 2001 8 6 HEEA073646 4 20010619 G 3451 066106900 INDICATOR BELL 412 412 1182202 SW DME/ TACAN FAILED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 3893L 33006 DIGITS OUT. IN SHOP REPAIR. 1 G 7 2 4U H4SW 2001080600305 20010806 00305 2001 8 6 HEEA073647 4 20010619 G 3451 066106900 INDICATOR BELL 412 412 1182202 SW COCKPIT INTERMITTENT E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 2148K 36001 SEGMENT LIGHT INTERMITTENTLY GOES BLANK IN NR 2 POSITION. IN SHOP REPAIR. 1 G 7 2 4U H4SW 2001080600306 20010806 00306 2001 8 6 HEEA073648 4 20010619 G 3451 066106902 INDICATOR BELL 412 412 1182202 SW COCKPIT INTERMITTENT E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 5759N 33002 DISPLAY FLASHES ON/OFF INTERMITTENTLY. IN SHOP REPAIR. 1 G 7 2 4U H4SW 2001080600307 20010806 00307 2001 8 6 HEEA073649 4 20010619 G 3416 13012001 ALTIMETER BELL 412 412 1182202 SW COCKPIT READS HIGH E HEEA O OTHER N FALSE WARNING NR NOT REPORTED 1 SW 03 107X 33113 READS 90 FEET HIGH. IN SHOP REPAIR. 1 G 7 2 4U H4SW 2001080600308 20010806 00308 SW 2001 8 6 HEEA073650 1 20010619 G 2121 206070475005 BLOWER BELL 412 412 1182202 SW CABIN FAILED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 2298Z 33077 BURNT OUT. IN SHOP REPAIR. 1 G 7 2 4U H4SW 2001080600309 20010806 00309 SW 2001 8 6 HEEA073651 1 20010619 G 7921 209011710005 TUBE BELL 412 412 1182202 SW OIL COOLER WORN E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 6559Z 36019 WORN AT LOCATION WHERE EXCLUDER SEAL RIDES. IN SHOP REPAIR. 1 G 7 2 4U H4SW 2001080600310 20010806 00310 SW 2001 8 6 HEEA073652 1 20010619 G 7921 BEARING BELL 412 412 1182202 SW OIL COOLER DAMAGED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 2298Z 51009046 33077 BEARING RACE SPINNING. IN SHOP REPAIR. 1 G 7 2 4U H4SW 2001080600311 20010806 00311 SW 2001 8 6 HEEA073653 1 20010619 G 6320 212070116009 INDICATOR BELL 412 412 1182202 SW XMSN OIL READS LOW E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 142PH 33150 READS LOW. SENDING TO VENDOR FOR REPAIR. 1 G 7 2 4U H4SW 2001080600312 20010806 00312 2001 8 6 HEEA073654 4 20010619 G 3100 212075067119 INDICATOR BELL 412 412EP 1182205 SW COCKPIT FAILED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 6106C 36257 I.T.T WOULD NOT INDICATE ANY TEMP. AT ALL; NEEDLES DID NOT MOVE. SENDING TO VENDOR FOR REPAIR. 1 G 7 2 4U H4SW 2001080600314 20010806 00314 SW 2001 8 6 HEEA073655 1 20010619 G 2910 212076006007 VALVE BELL 412 412 1182202 SW HYD SYSTEM BYPASSING E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 5759N 33002 BYPASS BUTTON POPPED. SENDING TO VENDOR FOR REPAIR. 1 G 7 2 4U H4SW 2001080600315 20010806 00315 SW 2001 8 6 HEEA073656 1 20010619 G 3246 212321103 CROSSTUBE BELL 412 412 1182202 SW MLG CORRODED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 6559Z 36019 FOUND CORROSION UNDER SADDLE TO A DEPTH OF .022 BEFORE TOTAL CLEAN UP. SENDING TO VENDOR FOR CREDIT. 1 G 7 2 4U H4SW 2001080600322 20010806 00322 GL 2001 8 6 HEEA073657 2 20010619 G 7323 25249994 GOVERNOR BELL 412 412 1182202 SW ALLSN 250C 250C* GL FREE TURBINE MALFUNCTIONED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 2298Z 33077 ACCELERATES VERY FAST. IN SHOP REPAIR. 1 G 7 2 4U 3 U H4SW E4CE 2001080600325 20010806 00325 2001 8 6 HEEA073658 4 20010619 G 2210 2593996333 TARSYN BELL 412 412 1182202 SW AFCS INTERMITTENT E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 6559Z 36019 INTERMITTENT KICK IN THE AFCS SYSTEM WHEN SWITCHING BETWEEN SAS AND ATT MODES. IN SHOP REPAIR. 1 G 7 2 4U H4SW 2001080600327 20010806 00327 SW 2001 8 6 HEEA073659 1 20010619 G 7100 3024780 GEARBOX BELL 412 412 1182202 SW NR 1 ENGINE DAMAGED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 5759N 2510 33002 TRANSFERRING OIL FROM C-BOX TO NR 1 ENGINE. IN SHOP REPAIR. 1 G 7 2 4U H4SW 2001080600328 20010806 00328 GL 2001 8 6 HEEA073660 2 20010619 G 7532 312320301 BLEED VALVE BELL 412 412 1182202 SW ALLSN 250C 250C* GL COMPRESSOR FAILED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 2298Z 33077 CAUSED COMPRESSOR STALL AT 84 PERCENT N1. SENDING TO VENDOR FOR REPAIR. 1 G 7 2 4U 3 U H4SW E4CE 2001080600329 20010806 00329 SW 2001 8 6 HEEA073661 1 20010619 G 7714 32005007 TACH GENERATOR BELL 412 412 1182202 SW NR 2 ENGINE FAILED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 3893L 33006 NR 2 ENGINE N1 INDICATOR WENT TO ZERO IN FLIGHT. SENDING TO VENDOR FOR REPAIR. 1 G 7 2 4U H4SW 2001080600331 20010806 00331 SW 2001 8 6 HEEA073662 1 20010619 G 7712 32447066 CONTROL UNIT BELL 412 412 1182202 SW TORQUE ERRATIC E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 2149S 36002 ERRATIC TORQUE LIMITING, N2 DROOPING EARLY. IN SHOP REPAIR. 1 G 7 2 4U H4SW 2001080600333 20010806 00333 SW 2001 8 6 HEEA073663 1 20010619 G 7712 32447066 CONTROL UNIT BELL 412 412 1182202 SW TORQUE MALFUNCTIONED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 2149S 36002 AIRCRAFT HAS 6 PERCENT TORQUE SPLIT AT HIGH POWER SETTINGS. IN SHOP REPAIR. 1 G 7 2 4U H4SW 2001080600334 20010806 00334 SW 2001 8 6 HEEA073664 1 20010619 G 7712 32447066 CONTROL UNIT BELL 412 412 1182202 SW TORQUE MALFUNCTIONED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 5759N 33002 10 PERCENT TORQUE SPLIT. IN SHOP REPAIR. 1 G 7 2 4U H4SW 2001080600336 20010806 00336 2001 8 6 HEEA073665 4 20010619 G 3442 4000038 KNOB BELL 412 412 1182202 SW CONTROL HEAD BROKEN E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 2148K 36001 BROKEN KNOB. IN SHOP REPAIR. 1 G 7 2 4U H4SW 2001080600338 20010806 00338 2001 8 6 HEEA073666 4 20010619 G 3422 4020936903 INDICATOR BELL 412 412 1182202 SW COCKPIT MALFUNCTIONED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 3893L 33006 SHOWS 30 DEGREE CLIMB WITH ACFT LEVEL. SENDING TO VENDOR FOR REPAIR. 1 G 7 2 4U H4SW 2001080600342 20010806 00342 2001 8 6 HEEA073667 4 20010619 G 2210 4033089901 COMPUTER BELL 412 412 1182202 SW COCKPIT INTERMITTENT E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 1202T 33112 CAUSES DECOUPLE LIGHT TO COME ON INTERMITTENTLY. SENDING TO VENDOR FOR REPAIR. 1 G 7 2 4U H4SW 2001080600344 20010806 00344 SW 2001 8 6 HEEA073668 1 20010619 G 6210 412015300109 BLADE BELL 412 412 1182202 SW MAIN ROTOR DAMAGED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 2148K 14262 36001 OUTBOARD ABRASION STRIP HAS SEVERAL HOLES FROM EROSION. SENDING TO VENDOR FOR REPAIR. 1 G 7 2 4U H4SW 2001080600345 20010806 00345 SW 2001 8 6 HEEA073669 1 20010619 G 6210 412015300109 BLADE BELL 412 412 1182202 SW MAIN ROTOR DAMAGED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 1202T 33112 HAS SMALL SECTION OF SKIN MISSING NEAR OUTBOARD TAB. IN SHOP FOR REPAIR. 1 G 7 2 4U H4SW 2001080600346 20010806 00346 SW 2001 8 6 HEEA073670 1 20010619 G 6210 412015300109 BLADE BELL 412 412 1182202 SW MAIN ROTOR DAMAGED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 1202T 33112 SCARF JOINT SEPARATED AND LOOSE. IN SHOP FOR REPAIR. 1 G 7 2 4U H4SW 2001080600348 20010806 00348 SW 2001 8 6 HEEA073671 1 20010619 G 6210 412015300109 BLADE BELL 412 412 1182202 SW MAIN ROTOR DAMAGED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 3893P 33012 CRACKED LEADING EDGE ABRASION STRIP. IN SHOP FOR REPAIR. 1 G 7 2 4U H4SW 2001080600350 20010806 00350 SW 2001 8 6 HEEA073672 1 20010619 G 7712 412075008111 INDICATOR BELL 412 412 1182202 SW COCKPIT MALFUNCTIONED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 2261D 33076 COPILOT READS 3 PERCENT HIGHER THAN PILOTS AND ENG TORQUE SHOW 4 PERCENT SPLIT WHERE AS THE PILOTS SHOW ONLY A 1%. IN SH OP FOR REPAIR. 1 G 7 2 4U H4SW 2001080600352 20010806 00352 SW 2001 8 6 HEEA073673 1 20010619 G 7714 412075010109 INDICATOR BELL 412 412 1182202 SW TRIPLE TACH READS LOW E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 2148K 36001 NR 2 ENGINE AND N2 ROTOR NEEDLE READS 2 PERCENT LOW. IN SHOP FOR REPAIR. 1 G 7 2 4U H4SW 2001080600356 20010806 00356 2001 8 6 HEEA073674 4 20010619 G 3460 5205160006 INDICATOR BELL 412 412 1182202 SW COCKPIT MALFUNCTIONED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 142PH 33150 NAV FLAG WILL NOT PULL. IN SHOP FOR REPAIR. 1 G 7 2 4U H4SW 2001080600357 20010806 00357 2001 8 6 HEEA073675 4 20010619 G 2340 A3016W INTERPHONE BELL 412 412 1182202 SW COCKPIT MALFUNCTIONED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 2149S 36002 FM AUDIO BLEEDS OVER WHEN FM NR 1 SELECTOR SWITCH IS SET TO DOWN POSITION. IN SHOP FOR REPAIR. 1 G 7 2 4U H4SW 2001080600359 20010806 00359 2001 8 6 HEEA073676 4 20010619 G 2340 A3016W INTERPHONE BELL 412 412 1182202 SW COCKPIT WEAK E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 2261D 33076 VERY WEAK ON RADIO CHANNELS. IN SHOP FOR REPAIR. 1 G 7 2 4U H4SW 2001080600361 20010806 00361 2001 8 6 HEEA073677 4 20010619 G 3443 MI5851345 INDICATOR BELL 412 412 1182202 SW RADAR FAILED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 2148K 36001 RADAR WILL NOT INDICATE TARGETS, ALSO WILL NOT SHOW TEST BAND. IN SHOP FOR REPAIR. 1 G 7 2 4U H4SW 2001080600363 20010806 00363 2001 8 6 HEEA073678 4 20010619 G 3442 MI5851345 DISPLAY BELL 412 412 1182202 SW RADAR SYS INOPERATIVE E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 2149S 36002 RADAR INOPERATIVE WITH BLANK SCREEN. IN SHOP FOR REPAIR. 1 G 7 2 4U H4SW 2001080600366 20010806 00366 2001 8 6 HEEA073679 4 20010619 G 3442 MI5851352 RADAR BELL 412 412 1182202 SW COCKPIT INOPERATIVE E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 2149S 36002 RADAR INOPERATIVE WITH BLANK SCREEN. IN SHOP FOR REPAIR. 1 G 7 2 4U H4SW 2001080600367 20010806 00367 2001 8 6 HEEA073680 4 20010619 G 3442 MI585136 RADAR BELL 412 412 1182202 SW COCKPIT INOPERATIVE E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 2149S 36002 RADAR INOPERATIVE WITH BLANK SCREEN. IN SHOP FOR REPAIR. 1 G 7 2 4U H4SW 2001080600371 20010806 00371 2001 8 6 HEEA073682 4 20010619 G 3442 MI585200 RADAR BELL 412 412 1182202 SW COCKPIT FAILED E HEEA O OTHER L NO TEST NR NOT REPORTED 1 SW 03 2261D 33076 RF BAND BROKEN AND TEST PATTERN BREAKS UP. IN SHOP FOR REPAIR. 1 G 7 2 4U H4SW 2001080600373 20010806 00373 SW 2001 8 6 HEEA073683 1 20010619 G 6720 PHI41294 BUSHING BELL 412 412 1182202 SW TAIL ROTOR WORN E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 107X 33113 WORN. IN SHOP FOR REPAIR. 1 G 7 2 4U H4SW 2001080600375 20010806 00375 SW 2001 8 6 HEEA073684 1 20010619 G 6730 212076005105 CYLINDER BELL 412 412 1182202 SW ROTOR SERVO LEAKING E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 2261D 33076 LEAKING. IN SHOP FOR REPAIR. 1 G 7 2 4U H4SW 2001080600376 20010806 00376 2001 8 6 HEEA073685 4 20010619 G 2312 064105430 TRANSCEIVER BELL 206 206L3 1182108 SW VHF SYSTEM FAILED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 21497 51518 DISPLAY NUMBERS DON'T COME ON. IN SHOP FOR REPAIR. 1 G 7 1 3U H2SW 2001080600377 20010806 00377 2001 8 6 HEEA073686 4 20010619 G 2312 069102435 RADIO BELL 206 206L3 1182108 SW VHF SYSTEM FAILED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 6251X 51552 VHF RADIO WILL NOT POWER UP. IN SHOP FOR REPAIR. 1 G 7 1 3U H2SW 2001080600378 20010806 00378 SW 2001 8 6 HEEA073687 1 20010619 G 2821 1110900 FILTER BELL 206 206L1 1182107 SW FUEL SYSTEM BYPASSING E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 5019F 45244 BUTTON POPS FOR NO REASON, INTERMITTENTLY. IN SHOP FOR REPAIR. 1 G 7 1 3U H2SW 2001080600379 20010806 00379 SW 2001 8 6 HEEA073688 1 20010619 G 2510 206033105115 SEAT BELL 206 206L3 1182108 SW COCKPIT MISMARKED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 3108E 51498 PANEL IS MISIDENTIFIED. IN SHOP FOR REPAIR. 1 G 7 1 3U H2SW 2001080600380 20010806 00380 SW 2001 8 6 HEEA073689 1 20010619 G 6330 206033506101 RESTRAINT BELL 206 206L3 1182108 SW TRANSMISSION WORN E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 42EA 51542 WORN AND UNSTAKED BEARINGS. IN SHOP FOR REPAIR. 1 G 7 1 3U H2SW 2001080600381 20010806 00381 SW 2001 8 6 HEEA073690 1 20010619 G 6330 206033506101 RESTRAINT BELL 206 206L3 1182108 SW TRANSMISSION DAMAGED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 31077 51520 BOTH BEARINGS UNSTAKED. SENDING TO VENDOR FOR REPAIR. 1 G 7 1 3U H2SW 2001080600382 20010806 00382 SW 2001 8 6 HEEA073691 1 20010619 G 6330 206033506101 RESTRAINT BELL 206 206L3 1182108 SW TRANSMISSION DAMAGED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 4835 51131 BEARINGS WORN. IN SHOP FOR REPAIR. 1 G 7 1 3U H2SW 2001080600383 20010806 00383 SW 2001 8 6 HEEA073692 1 20010619 G 6330 206033506103 RESTRAINT BELL 206 206L4 1182110 SW TRANSMISSION WORN E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 7074W 52033 BEARINGS WORN. IN SHOP FOR REPAIR. 1 G 7 1 3U NC H2SW 2001080600384 20010806 00384 SW 2001 8 6 HEEA073693 1 20010619 G 7933 206375007103 INDICATOR BELL 206 206L3 1182108 SW TOT FAILED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 6160Z 51610 DURING START TOT INDICATOR DID NOT INDICATE TEMPERATURE. SENDING TO VENDOR FOR REPAIR. 1 G 7 1 3U H2SW 2001080600385 20010806 00385 SW 2001 8 6 HEEA073694 1 20010619 G 2435 23081018 STARTER GEN BELL 206 206L3 1182108 SW ENGINE MALFUNCTIONED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 6251X 51552 TROUBLESHOOTING GENERATOR PROBLEM. IN SHOP FOR REPAIR. 1 G 7 1 3U H2SW 2001080600386 20010806 00386 GL 2001 8 6 HEEA073695 2 20010619 G 7323 252469211 GOVERNOR BELL 206 206L3 1182108 SW ALLSN 250C 250C* GL ENGINE FAILED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 30KH 51527 WILL NOT HOLD 100 PERCENT N2 SETTING. IN SHOP FOR REPAIR. 1 G 7 1 3U 3 U H2SW E4CE 2001080600387 20010806 00387 GL 2001 8 6 HEEA073696 2 20010619 G 7321 25490925 FUEL CONTROL BELL 206 206L3 1182108 SW ALLSN 250C 250C* GL ENGINE MALFUNCTIONED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 31073 51519 ENGINE WOULD HIT 850 DEGREE ON START. ADJUSTING START/DERICH AND START/ACCELERATION TO MINIMUM WOULD NOT BRING THE ENGI NE TO AN ACCEPTABLE START TEMPERATURE. IN SHOP FOR REPAIR. 1 G 7 1 3U 3 U H2SW E4CE 2001080600388 20010806 00388 SW 2001 8 6 HEEA073697 1 20010619 G 2822 2C271 CARTRIDGE BELL 206 206L3 1182108 SW BOOST PUMP FAILED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 4835 51131 BOOST PUMP QUIT RUNNING IN FLIGHT. SENDING TO VENDOR FOR REPAIR. 1 G 7 1 3U H2SW 2001080600389 20010806 00389 2001 8 6 HEEA073698 4 20010619 G 3421 5040017901 INDICATOR BELL 206 206L3 1182108 SW ATTITUDE MALFUNCTIONED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 21497 51518 SLOW TO ERECT. IN SHOP FOR REPAIR. 1 G 7 1 3U H2SW 2001080600391 20010806 00391 2001 8 6 HEEA073700 4 20010619 G 3457 8143802240D GPS BELL 206 206B3 1181506 SW COCKPIT FAILED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 22743 3624 LOSES MEMORY. SENDING TO VENDOR FOR REPAIR. 1 G 7 1 3U H2SW 2001080600392 20010806 00392 2001 8 6 HEEA073701 4 20010619 G 2350 AA34200 RADIO BELL 206 206L4 1182110 SW COCKPIT LOW E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 7077B 52037 VOLUME TOO LOW AND WOULD NOT ADJUST. SENDING TO VENDOR FOR REPAIR. 1 G 7 1 3U NC H2SW 2001080600393 20010806 00393 2001 8 6 HEEA073703 4 20010619 G 2350 PHI001200001201 MIXER BOX BELL 206 206L3 1182108 SW COCKPIT FAILED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 3116P 51530 WILL NOT RECEIVE ON PILOT'S SIDE. IN SHOP FOR REPAIR. 1 G 7 1 3U H2SW 2001080600394 20010806 00394 2001 8 6 HEEA073704 4 20010619 G 2561 BOTTLE BELL 206 206L3 1182108 SW LIFE VEST BROKEN E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 42EA 51542 "JERK TO INFLATE" TAG ON C02 BOTTLE ASSEMBLY BROKEN. SENDING TO VENDOR FOR REPAIR. 1 G 7 1 3U H2SW 2001080600395 20010806 00395 SW 2001 8 6 HEEA073705 1 20010619 G 6320 206033518007 STOP BELL 206 206L3 1182108 SW M/R GEARBOC DETERIORATED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 21497 51518 RUBBER DETERIORATED. SENDING TO VENDOR FOR REPAIR. 1 G 7 1 3U H2SW 2001080600396 20010806 00396 SW 2001 8 6 HEEA073706 1 20010619 G 2432 RG214 BATTERY BELL 214 214ST 1182106 SW BATTERY BAY DISCHARGED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 8045T 485 28101 BATTERY WEAK. WON'T HOLD A CHARGE. 2 G 7 2 4U H10SW 2001080600397 20010806 00397 SW 2001 8 6 HEEA073707 1 20010619 G 2432 RG214 BATTERY BELL 214 214ST 1182106 SW BATTERY BAY DISCHARGED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 8045T 485 28101 BATTERY WEAK. WON'T HOLD A CHARGE. 2 G 7 2 4U H10SW 2001080600398 20010806 00398 2001 8 6 HEEA073708 4 20010619 G 3452 066106200 TRANSCEIVER BELL 407 407 SW COCKPIT FAILED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 4999 53323 COULD NOT BE PICKED UP BY TOWER. SENDING TO VENDOR FOR REPAIR. 1 G 7 1 3U O H2SW 2001080600399 20010806 00399 SW 2001 8 6 HEEA073709 1 20010620 G 6210 206015001115 BLADE BELL 206 206L3 1182108 SW MAIN ROTOR CORRODED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 979BH 903 51403 CORRODED AT BLADE TIP AND LATCH PLATE UNBONDED. 1 G 7 1 3U H2SW 2001080600400 20010806 00400 SW 2001 8 6 HEEA073710 1 20010620 G 6210 206015001115 BLADE BELL 206 206L3 1182108 SW MAIN ROTOR CORRODED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 979BH 903 51403 CORRODED AT BLADE TIP. 1 G 7 1 3U H2SW 2001080600401 20010806 00401 SW 2001 8 6 HEEA073712 1 20010620 G 5302 STRUCTURE BELL 407 407 SW VERTICAL FIN CORRODED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 405PH BP1875 53207 VERTICAL FIN CORRODED. 1 G 7 1 3U O H2SW 2001080600402 20010806 00402 SW 2001 8 6 HEEA073713 1 20010620 G 3212 206050247131 COVER BELL 407 407 SW MLG WORN E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 494PH 53396 AFT END CAP IS WORN AND TORN. TO BE RETURNED TO VENDOR. 1 G 7 1 3U O H2SW 2001080600403 20010806 00403 SW 2001 8 6 HEEA073714 1 20010620 G 3212 206050247138 COVER BELL 407 407 SW FLOAT WORN E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 719PH 53266 COVER WORN AND END CAP LOOSE. TO BE RETURNED TO VENDOR. 1 G 7 1 3U O H2SW 2001080700005 20010807 00005 SW 2001 8 7 HEEA073715 1 20010620 G 6510 206061432118 INLET BELL 407 407 SW T/R OIL COOLER CRACKED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 719PH 53266 OIL COOLER INLET COVER CRACKED. TO BE RETURNED TO VENDOR. 1 G 7 1 3U O H2SW 2001080700006 20010807 00006 SW 2001 8 7 HEEA073716 1 20010620 G 6510 206061432121 HOUSING BELL 407 407 SW T/R BLOWER CRACKED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 724PH 53327 BLOWER HOUSING HAS CRACKS. TO BE RETURNED TO VENDOR. 1 G 7 1 3U O H2SW 2001080700007 20010807 00007 SW 2001 8 7 HEEA073717 1 20010620 G 6510 206061432121 HOUSING BELL 407 407 SW T/R BLOWER CRACKED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 719PH 53266 BLOWER HOUSING HAS CRACKS. TO BE RETURNED TO VENDOR. 1 G 7 1 3U O H2SW 2001080700008 20010807 00008 SW 2001 8 7 HEEA073718 1 20010620 G 2435 206062200113 STARTER GEN BELL 407 407 SW ENGINE ARCED E HEEA O OTHER B SMOKE/FUMES/ODORS/SPARKS IN INSP/MAINT 1 SW 03 741PH 357 53457 ARCING 1 G 7 1 3U O H2SW 2001080700009 20010807 00009 SW 2001 8 7 HEEA073719 1 20010620 G 2435 206062200113 STARTER GEN BELL 407 407 SW ENGINE WORN E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 447PH 1558 53114 STARTER GENERATOR BRUSHES WORN BEYOND LIMITS. 1 G 7 1 3U O H2SW 2001080700010 20010807 00010 SW 2001 8 7 HEEA073721 1 20010620 G 2435 SHAFT BELL 407 407 SW STARTER GEN BENT E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 417PH 1190 99405 53038 SHAFT BENT. 1 G 7 1 3U O H2SW 2001080700011 20010807 00011 SW 2001 8 7 HEEA073722 1 20010620 G 2435 BRUSHES BELL 407 407 SW STARTER GEN WORN E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 740PH 3794 1828 53435 BRUSHES WORN BEYOND LIMITS. REPAIRED BY PHI. (BELL WILL BE INVOICED) 1 G 7 1 3U O H2SW 2001080700012 20010807 00012 SW 2001 8 7 HEEA073723 1 20010620 G 6321 PAD BELL 407 407 SW ROTOR BRAKE WORN E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 417PH 337 53038 WORN PAD. TO BE RETURNED TO VENDOR. 1 G 7 1 3U O H2SW 2001080700013 20010807 00013 SW 2001 8 7 HEEA073724 1 20010620 G 3212 206373901103 SOLENOID VALVE BELL 407 407 SW FLOAT BOTTLE LEAKING E HEEA K NONE K FLUID LOSS IN INSP/MAINT 1 SW 03 722PH 53288 AFTER FLOAT BOTTLE CHANGE VALVE ASSY LEAKED NITROGEN FROM SOLENOID OPENING ADJUSTMENT CAP. TO BE RETURNED TO VENDOR. 1 G 7 1 3U O H2SW 2001080700014 20010807 00014 SW 2001 8 7 HEEA073725 1 20010620 G 7931 222375077113 TRANSMITTER BELL 407 407 SW OIL PRESSURE READS LOW E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 719PH 53266 ENGINE OIL PRESSURE READING LOW. TO BE RETURNED TO VENDOR. 1 G 7 1 3U O H2SW 2001080700015 20010807 00015 SW 2001 8 7 HEEA073726 1 20010620 G 7931 222375077113 TRANSMITTER BELL 407 407 SW OIL PRESSURE READS LOW E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 742PH 53461 ENGINE OIL PRESSURE INDICATING 30 PSI LOW IN CRUISE FLIGHT. TO BE RETURNED TO VENDOR. 1 G 7 1 3U O H2SW 2001080700018 20010807 00018 GL 2001 8 7 HEEA073727 2 20010620 G 7412 23064130 IGNITER BOX BELL 407 407 SW ALLSN 250C 250C47B GL ENGINE INTERMITTENT E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 4999 53323 WORKS INTERMITTENTLY. AIRCRAFT WOULD NOT LIGHT OFF. TO BE RETURNED TO VENDOR. 1 G 7 1 3U 3 U O H2SW E1GL 2001080700019 20010807 00019 SW 2001 8 7 HEEA073728 1 20010620 G 6520 406040453101 SEAL BELL 407 407 SW T/R GEARBOX LEAKING E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 612PH 228 53199 SEAL LEAKING OIL. TO BE RETURNED TO VENDOR. 1 G 7 1 3U O H2SW 2001080700023 20010807 00023 SW 2001 8 7 HEEA073729 1 20010620 G 6310 406040500123B FREEWHEEL UNIT BELL 407 407 SW MAIN ROTOR LEAKING E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 405PH 2236 53207 FRONT SEAL LEAKING. TO BE RETURNED TO VENDOR. 1 G 7 1 3U O H2SW 2001080700025 20010807 00025 SW 2001 8 7 HEEA073730 1 20010620 G 6710 406310405101 UNIVERSAL JOINT BELL 407 407 SW M/R PITCH CHANGE WORN E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 612PH 53199 BLUE MAIN ROTOR PITCH CHANGE BEARING WORN. TO BE RETURNED TO VENDOR. 1 G 7 1 3U O H2SW 2001080700026 20010807 00026 SW 2001 8 7 HEEA073731 1 20010620 G 6710 406310405101 UNIVERSAL JOINT BELL 407 407 SW M/R PITCH CHANGE WORN E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 612PH 53199 BEARING WORN. TO BE RETURNED TO VENDOR. 1 G 7 1 3U O H2SW 2001080700028 20010807 00028 SW 2001 8 7 HEEA073732 1 20010620 G 6710 406310405101 UNIVERSAL JOINT BELL 407 407 SW M/R PITCH CHANGE WORN E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 491PH 1201 53386 BEARING WORN. TO BE RETURNED TO VENDOR. 1 G 7 1 3U O H2SW 2001080700029 20010807 00029 SW 2001 8 7 HEEA073733 1 20010620 G 6710 406310405101 UNIVERSAL JOINT BELL 407 407 SW M/R PITCH CHANGE WORN E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 720PH 53277 BEARING WORN. TO BE RETURNED TO VENDOR. 1 G 7 1 3U O H2SW 2001080700030 20010807 00030 SW 2001 8 7 HEEA073734 1 20010620 G 6710 406310405101 UNIVERSAL JOINT BELL 407 407 SW M/R PITCH CHANGE WORN E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 447PH 53114 BEARING WORN. TO BE RETURNED TO VENDOR. 1 G 7 1 3U O H2SW 2001080700031 20010807 00031 SW 2001 8 7 HEEA073735 1 20010620 G 6710 406310405101 UNIVERSAL JOINT BELL 407 407 SW M/R PITCH CHANGE WORN E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 4999 436 53323 BEARING WORN. TO BE RETURNED TO VENDOR. 1 G 7 1 3U O H2SW 2001080700032 20010807 00032 SW 2001 8 7 HEEA073736 1 20010620 G 6300 407010206103 BEARING BELL 407 407 SW MAIN ROTOR WORN E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 724PH 53327 BEARING WORN. TO BE RETURNED TO VENDOR. 1 G 7 1 3U O H2SW 2001080700035 20010807 00035 SW 2001 8 7 HEEA073737 1 20010620 G 6420 406312100101 BEARING 407012101111 BELL 407 407 SW TAIL ROTOR WORN E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 510PH 53311 53209 WORN. TO BE RETURNED TO VENDOR. (J0169320) 1 G 7 1 3U O H2SW 2001080700036 20010807 00036 SW 2001 8 7 HEEA073738 1 20010620 G 6420 406312100101 BEARING 407012101111 BELL 407 407 SW TAIL ROTOR WORN E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 499PH 53393 53400 WORN. TO BE RETURNED TO VENDOR. (J0159304) 1 G 7 1 3U O H2SW 2001080700037 20010807 00037 SW 2001 8 7 HEEA073739 1 20010620 G 6420 406312100101 BEARING 407012101111 BELL 407 407 SW TAIL ROTOR WORN E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 495PH 53397 53397 WORN. TO BE RETURNED TO VENDOR. (J0154475) 1 G 7 1 3U O H2SW 2001080700038 20010807 00038 SW 2001 8 7 HEEA073740 1 20010620 G 3210 407030112103 STRAP BELL 407 407 SW MLG DAMAGED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 405PH 53207 SURFACE DAMAGE. SCRAPPED LOCALLY. 1 G 7 1 3U O H2SW 2001080700039 20010807 00039 SW 2001 8 7 HEEA073741 1 20010620 G 5210 407070620138 PANEL BELL 407 407 SW PAX DOOR CRACKED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 407PH 53003 CRACKED AND WORN. SCRAPPED LOCALLY. 1 G 7 1 3U O H2SW 2001080700040 20010807 00040 SW 2001 8 7 HEEA073742 1 20010620 G 5210 407070620157 PANEL BELL 407 407 SW PAX/CREW DOOR DAMAGED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 404PH 53188 DOOR PANEL DAMAGED. SCRAPPED LOCALLY. 1 G 7 1 3U O H2SW 2001080700041 20010807 00041 SW 2001 8 7 HEEA073743 1 20010620 G 5210 407070620157 PANEL BELL 407 407 SW PAX/CREW DOOR CRACKED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 409PH 53059 CRACKED AND BROKEN. SCRAPPED LOCALLY. 1 G 7 1 3U O H2SW 2001080700042 20010807 00042 SW 2001 8 7 HEEA073744 1 20010620 G 5210 407070620158 PANEL BELL 407 407 SW PAX/CREW DOOR CRACKED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 409PH 53059 CRACKED AND BROKEN. SCRAPPED LOCALLY. 1 G 7 1 3U O H2SW 2001080700043 20010807 00043 SW 2001 8 7 HEEA073745 1 20010620 G 5210 407070620158 PANEL BELL 407 407 SW PAX/CREW DOOR DAMAGED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 404PH 53188 DAMAGED. SCRAPPED LOCALLY. 1 G 7 1 3U O H2SW 2001080700044 20010807 00044 SW 2001 8 7 HEEA073746 1 20010620 G 5210 407070620218 PANEL BELL 407 407 SW PAX/CREW DOOR CRACKED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 724PH 53327 CRACKED AND STAINED. SCRAPPED LOCALLY. 1 G 7 1 3U O H2SW 2001080700046 20010807 00046 SW 2001 8 7 HEEA073747 1 20010620 G 5260 407301109 STEP BELL 407 407 SW FUSELAGE CORRODED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 493PH 53393 HEAVY CORROSION AROUND MOUNTING HOLES. SCRAPPED LOCALLY. 1 G 7 1 3U O H2SW 2001080700049 20010807 00049 2001 8 7 HEEA073748 4 20010620 G 2350 PA1120NVPHI HEADSET BELL 407 407 SW COCKPIT FAILED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 407XM 53464 WILL NOT TRANSMIT. REPLACED WITH SERVICEABLE PART. 1 G 7 1 3U O H2SW 2001080700052 20010807 00052 SW 2001 8 7 HEEA073749 1 20010620 G 6520 PHI407111 HOUSING BELL 407 407 SW INPUT SEAL LEAKING E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 407PH 53003 LEAKING. REPLACED WITH SERVICEABLE PART. 1 G 7 1 3U O H2SW 2001080700053 20010807 00053 2001 8 7 HEEA073750 4 20010620 G 3400 CI196 ANTENNA BELL 407 407 SW NAVIGATION CORRODED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 457PH 53147 CORROSION AT BASE. SCRAPPED AND REPLACED WITH SERVICEABLE PART. 1 G 7 1 3U O H2SW 2001080700054 20010807 00054 GL 2001 8 7 HEEA073751 2 20010620 G 7421 CH34187A IGNITER BELL 407 407 SW ALLSN 250C 250C47B GL ENGINE ERODED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 496PH 53398 ELECTRODE ERODED CAUSING DELAYED LIGHT OFF. SCRAPPED AND REPLACED WITH SERVICEABLE PART. 1 G 7 1 3U 3 U O H2SW E1GL 2001080700056 20010807 00056 SW 2001 8 7 HEEA073752 1 20010620 G 3110 407375038101 PANEL BELL 407 407 SW COCKPIT BROKEN E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 407PH 53003 SWITCH GUARD BROKEN. SCRAPPED AND REPLACED WITH SERVICEABLE PART. 1 G 7 1 3U O H2SW 2001080700057 20010807 00057 GL 2001 8 7 HEEA073753 2 20010620 G 7313 6899001 NOZZLE BELL 407 407 SW ALLSN 250C 250C47B GL FUEL SYSTEM CORRODED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 740PH 291 53435 CAE847473 THREADS RUSTED AND DAMAGED. REPLACED WITH SERVICEABLE PART. 1 G 7 1 3U 3 U O H2SW E1GL 2001080700058 20010807 00058 SW 2001 8 7 HEEA073754 1 20010620 G 7921 407062021101 DUCT BELL 407 407 SW OIL COOLER CRACKED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 719PH 53266 OIL COOLER TRANSITION DUCT IS CRACKED. TO BE RETURNED TO VENDOR. 1 G 7 1 3U O H2SW 2001080700059 20010807 00059 SW 2001 8 7 HEEA073755 1 20010620 G 6330 407310203101 MOUNT BELL 407 407 SW TRANSMISSION DAMAGED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 493PH 53393 RUBBER IN MOUNT BAD. SERIAL NUMBERS REMOVED ARE LP1891 AND LP1902. TO BE RETURNED TO VENDOR. 1 G 7 1 3U O H2SW 2001080700060 20010807 00060 SW 2001 8 7 HEEA073756 1 20010620 G 6510 407340340101 DISC PACK BELL 407 407 SW T/R DRIVE BROKEN E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 407PH 53003 BROKEN. TO BE RETURNED TO VENDOR. 1 G 7 1 3U O H2SW 2001080700061 20010807 00061 SW 2001 8 7 HEEA073757 1 20010620 G 2840 407362005103 SWITCH BELL 407 407 SW COCKPIT MALFUNCTIONED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 495PH 53397 FALSE INDICATION, LIGHT ON WITH 400 LBS OF FUEL. TO BE RETURNED TO VENDOR. 1 G 7 1 3U O H2SW 2001080700062 20010807 00062 SW 2001 8 7 HEEA073758 1 20010620 G 2840 407362005103 SWITCH BELL 407 407 SW COCKPIT MALFUNCTIONED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 457PH 53147 LOW LEVEL LIGHT COMES ON INTERMITTENTLY. TO BE RETURNED TO VENDOR. 1 G 7 1 3U O H2SW 2001080700063 20010807 00063 SW 2001 8 7 HEEA073759 1 20010620 G 2822 407362013101 PRESSURE SWITCH BELL 407 407 SW ENGINE MALFUNCTIONED E O OTHER O OTHER NR NOT REPORTED 1 SW 03 723PH 53283 RT PUMP LIGHT DOES NOT ILLUMINATE WITH A/C POWER ON AND PUMP OFF. TO BE RETURNED TO VENDOR. 1 G 7 1 3U O H2SW 2001080700064 20010807 00064 SW 2001 8 7 HEEA073760 1 20010620 G 2822 407362013101 PRESSURE SWITCH BELL 407 407 SW ENGINE MALFUNCTIONED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 723PH 53283 LT TRANSFER PUMP LIGHT DOES NOT ILLUMINATE WITH A/C POWER ON AND PUMP OFF. TO BE RETURNED TO VENDOR. 1 G 7 1 3U O H2SW 2001080700066 20010807 00066 SW 2001 8 7 HEEA073761 1 20010620 G 2822 407362013101 PRESSURE SWITCH BELL 407 407 SW ENGINE MALFUNCTIONED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 467PH 53142 RT BOOST PUMP LIGHT DOES NOT ILLUMINATE WITH CIRCUIT BREAKER PULLED. TO BE RETURNED TO VENDOR. 1 G 7 1 3U O H2SW 2001080700067 20010807 00067 SW 2001 8 7 HEEA073762 1 20010620 G 7930 407375004101 INDICATOR BELL 407 407 SW ENGINE OIL INACCURATE E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 493PH 53393 ENGINE OIL PRESSURE READS 70 PSI WITH NO ENGINE POWER. TO BE RETURNED TO VENDOR. 1 G 7 1 3U O H2SW 2001080700068 20010807 00068 SW 2001 8 7 HEEA073763 1 20010620 G 2910 70061V000V444A TUBE BELL 407 407 SW HYD SYSTEM CHAFED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 407PH 53003 CHAFED. TO BE RETURNED TO VENDOR. 1 G 7 1 3U O H2SW 2001080700072 20010807 00072 SW 2001 8 7 HEEA073764 1 20010620 G 8000 SM20ACD300A21 RELAY BELL 407 407 SW STARTER STUCK E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 407XM 53464 STARTER RELAY STUCK IN CLOSED POSITION ON ENGINE WASH. TO BE RETURNED TO VENDOR. 1 G 7 1 3U O H2SW 2001080700073 20010807 00073 SW 2001 8 7 HEEA073765 1 20010620 G 2841 70077P140B370 HOSE BELL 412 412 1182202 SW FUEL SYSTEM DAMAGED E HEEA C ABORTED TAKEOFF J WARNING INDICATION TO TAKEOFF 1 SW 03 108X 33115 SHORTLY AFTER TAKEOFF, BOTH FUEL TRANSFER CAUTION LIGHTS ILLUMINATED. THE FUEL QUANTITY INDICATOR SHOWED BOTH FORWARD F UEL CELLS EMPTY AND MID TANKS SHOWING 50 LBS. WITH 1500 LBS ON BOARD. REPLACED 3 EACH HOSES. (P/N 70-077P140B370, P/N 70 -077P288W294, P/N 412-061-610-103) 1 G 7 2 4U H4SW 2001080700074 20010807 00074 SW 2001 8 7 HEEA073766 1 20010620 G 2931 222375019105 TRANSMITTER BELL 214 214ST 1182106 SW HYD SYSTEM MALFUNCTIONED E HEEA A UNSCHED LANDING J WARNING INDICATION CL CLIMB 1 SW 03 59806 28140 SHORTLY AFTER TAKEOFF, THE NR 1 HYDRAULIC PRESSURE GAUGE PEGGED OUT. REPLACED PRESSURE TRANSMITTER. 2 G 7 2 4U H10SW 2001080700075 20010807 00075 SW 2001 8 7 HEEA073767 1 20010620 G 6420 407312100101 BEARING 407012101111 BELL 407 407 SW TAIL ROTOR DEBONDED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 141MA 53038 53016 ELASTOMERIC BEARING DEBONDED. TO BE RETURNED TO VENDOR. (J0165342-WA) 1 G 7 1 3U O H2SW 2001080700076 20010807 00076 SW 2001 8 7 HEEA073768 1 20010620 G 6510 406040339105 BEARING 407040302101 BELL 407 407 SW TAIL ROTOR VIBRATES E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 467PH A164 53142 ROUGH VIBRATION ON TAILBOOM. TO BE RETURNED TO VENDOR. (J0162310-WA) 1 G 7 1 3U O H2SW 2001080700077 20010807 00077 SW 2001 8 7 HEEA073769 1 20010620 G 6510 407340339103 BEARING 407040302101 BELL 407 407 SW TAIL ROTOR OVERHEATED E HEEA O OTHER M OVER TEMP IN INSP/MAINT 1 SW 03 467PH A15 53142 OVERHEATED. TO BE RETURNED TO VENDOR. (J0164213-WA) 1 G 7 1 3U O H2SW 2001080700235 20010807 00235 SW 2001 8 7 HEEA073770 1 20010620 G 6510 407340339103 BEARING 407040302107 BELL 407 407 SW TAIL ROTOR MAKING METAL E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 499PH A1964 53400 METAL. TO BE RETURNED TO VENDOR. (J0167780-WA) 1 G 7 1 3U O H2SW 2001080700236 20010807 00236 SW 2001 8 7 HEEA073771 1 20010620 G 6510 407340339103 BEARING 407040302107 BELL 407 407 SW TAIL ROTOR WORN E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 719PH A1949 53266 WORN. TO BE RETURNED TO VENDOR. (J0168105-WA) 1 G 7 1 3U O H2SW 2001080700237 20010807 00237 SW 2001 8 7 HEEA073772 1 20010620 G 6420 406312100101 BEARING 407012101111 BELL 407 407 SW TAIL ROTOR WORN E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 724PH 53277 53327 WORN. TO BE RETURNED TO VENDOR. (J0166791-WA) 1 G 7 1 3U O H2SW 2001080700238 20010807 00238 SW 2001 8 7 HEEA073773 1 20010620 G 6310 406340102101 CARBON SEAL 406040500123 BELL 407 407 SW FREEWHEEL UNIT WORN E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 409PH A4361 53059 WORN. TO BE RETURNED TO VENDOR. (J0165492-WA) 1 G 7 1 3U O H2SW 2001080700239 20010807 00239 SW 2001 8 7 HEEA073774 1 20010620 G 6420 406312100101 BEARING 407012101111 BELL 407 407 SW TAIL ROTOR WORN E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 402PH 53396 53159 WORN. TO BE RETURNED TO VENDOR. (J0165250-WA) 1 G 7 1 3U O H2SW 2001080700240 20010807 00240 SW 2001 8 7 HEEA073775 1 20010620 G 6310 406340102101 CARBON SEAL PHI407109 BELL 407 407 SW FREEWHEEL UNIT LEAKING E HEEA K NONE K FLUID LOSS IN INSP/MAINT 1 SW 03 490PH 53378 FREEWHEELING UNIT FORWARD SEAL LEAKING OIL. TO BE RETURNED TO VENDOR. (J0160511-WA) 1 G 7 1 3U O H2SW 2001080700241 20010807 00241 SW 2001 8 7 HEEA073776 1 20010620 G 6300 406040320101 SHAFT PHIPBH40701 BELL 407 407 SW COOLER BLOWER WORN E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 490PH PHI0015 53378 WORN SPLINES. TO BE RETURNED TO VENDOR. (J0167662-WA) 1 G 7 1 3U O H2SW 2001080700242 20010807 00242 SW 2001 8 7 HEEA073777 1 20010620 G 6300 407340339103 BEARING PHIPBH40701 BELL 407 407 SW COOLER BLOWER ROUGH E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 490PH PHI0015 53378 ROUGH. SERIAL NUMBERS REMOVED ARE B00-2007 AND B00-2035. TO BE RETURNED TO VENDOR. (J0167662-WA) 1 G 7 1 3U O H2SW 2001080700243 20010807 00243 SW 2001 8 7 HEEA073779 1 20010620 G 6300 406040320101 SHAFT PHIPBH40701 BELL 407 407 SW COOLER BLOWER WORN E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 499PH PHI0004 53400 WORN SPLINES. TO BE RETURNED TO VENDOR (J0166773-WA) 1 G 7 1 3U O H2SW 2001080700244 20010807 00244 SW 2001 8 7 HEEA073780 1 20010620 G 6300 407340339103 BEARING PHIPBH40701 BELL 407 407 SW COOLER BLOWER WORN E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 499PH PHI0004 53400 WORN. SERIAL NUMBERS REMOVED ARE F99-2018 AND F99-1690. TO BE RETURNED TO VENDOR (J0166773-WA) 1 G 7 1 3U O H2SW 2001080700245 20010807 00245 SW 2001 8 7 HEEA073781 1 20010620 G 6420 407312100101 BEARING 407012101111 BELL 407 407 SW TAIL ROTOR CHAFED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 141MA 1733 53393 53016 ELASTOMER SHEETING AND CHAFING. TO BE RETURNED TO VENDOR (J0169927-WA) 1 G 7 1 3U O H2SW 2001080700246 20010807 00246 SW 2001 8 7 HEEA073782 1 20010620 G 6420 406312100101 BEARING 407012101111 BELL 407 407 SW TAIL ROTOR WORN E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 141MA 613 53393 53016 WORN. TO BE RETURNED TO VENDOR (J0169927-WA) 1 G 7 1 3U O H2SW 2001080700282 20010807 00282 EU 2001 8 7 HEEA073783 1 20010619 G 6210 10515141 BLADE BOLKMS 105 BO105S 5626006 EU MAIN ROTOR DAMAGED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 81982 6167 S818 THE OUTBOARD LEADING EDGE STRIP SEPARATED ON THE OUTBOARD TIP. SENDING TO VENDOR FOR REPAIR. 1 G 7 2 3U H3EU 2001080700283 20010807 00283 EU 2001 8 7 HEEA073784 1 20010619 G 6210 10515150 BLADE BOLKMS 105 BO105S 5626006 EU MAIN ROTOR DAMAGED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 81982 5832 S818 THE OUTBOARD LEADING EDGE STRIP SEPARATED IN SEVERAL AREAS. SENDING TO VENDOR FOR REPAIR. 1 G 7 2 3U H3EU 2001080700285 20010807 00285 EU 2001 8 7 HEEA073785 1 20010619 G 5320 350A21010108 DRAIN LINE SNIAS 350 AS350B2 8680813 EU FUSELAGE LEAKING E HEEA O OTHER K FLUID LOSS NR NOT REPORTED 1 SW 03 40466 3004 PIPE LEAKS AT CONNECTION. REPLACED WITH SERVICEABLE PIPE. 1 G 7 1 3U H9EU 2001080700287 20010807 00287 EU 2001 8 7 HEEA073786 1 20010619 G 7921 1184961 OIL COOLER SNIAS 350 AS350B2 8680813 EU ENGINE OIL CORRODED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 40466 3004 OIL COOLER CORRODED. REPLACED WITH SERVICEABLE ENG OIL COOLER. 1 G 7 1 3U H9EU 2001080700288 20010807 00288 EU 2001 8 7 HEEA073787 1 20010619 G 6322 1184964 OIL COOLER SNIAS 350 AS350B2 8680813 EU TRANSMISSION CORRODED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 40466 3004 OIL COOLER CORRODED. REPLACED WITH SERVICEABLE TRANS OIL COOLER. 1 G 7 1 3U H9EU 2001080700325 20010807 00325 EU 2001 8 7 HEEA073788 1 20010619 G 6520 BEARING SNIAS 350 AS350B 8680801 EU PITCH LINK WORN E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 856PH 3352 INBOARD BEARING WORN. REPLACED WITH SERVICEABLE T/R PITCH LINK. 1 G 7 1 3U H9EU 2001080700327 20010807 00327 EU 2001 8 7 HEEA073789 1 20010619 G 6300 350A57117720 STOP SNIAS 350 AS350B2 8680813 EU MAIN ROTOR WORN E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 40466 3004 WORN AT STOP. REPLACED WITH SERVICEABLE STOP PLATE. 1 G 7 1 3U H9EU 2001080700331 20010807 00331 EU 2001 8 7 HEEA073791 1 20010619 G 3040 350A89103701 ARM SNIAS 350 AS350B2 8680813 EU WINDSHIELD WIPER CRACKED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 40466 3004 CRACKED AT MOUNT. REPLACED WITH SERVICEABLE WIPER ARM. 1 G 7 1 3U H9EU 2001080700332 20010807 00332 EU 2001 8 7 HEEA073792 1 20010619 G 2560 504305401 INERTIA REEL SNIAS 350 AS350B2 8680813 EU SEAT BELT BROKEN E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 4000L 2873 RECEIVED NEW INERTIAL REEL AND FOUND RELEASE CABLE AT ATTACHMENT BROKEN AT REEL. SENDING TO VENDOR FOR REPAIR. 1 G 7 1 3U H9EU 2001080700333 20010807 00333 EU 2001 8 7 HEEA073793 1 20010619 G 6220 704A33633116 BEARING SNIAS 350 AS350B2 8680813 EU MAIN ROTOR DAMAGED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 40466 3004 ELASTOMERIC RUBBER SEPARATED BEYOND LIMITS. SENDING TO VENDOR FOR REPAIR. 1 G 7 1 3U H9EU 2001080700336 20010807 00336 EU 2001 8 7 HEEA073794 1 20010619 G 2931 MA12401 PRESSURE SWITCH SNIAS 350 AS350B 8680801 EU HYD SYSTEM DEFECTIVE E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 856PH 3352 HYD. CAUTION LIGHT ILLUMINATED INTERMITTENTLY. SENDING TO VENDOR FOR REPAIR. 1 G 7 1 3U H9EU 2001080700337 20010807 00337 2001 8 7 HEEA073795 4 20010619 G 3452 066106200 TRANSCEIVER BOLKMS 117 BK117A1 5626010 EU COCKPIT MALFUNCTIONED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 911LK 7068 ATC REPORTED NOT GETTING THE RIGHT NUMBER. PERFORMED PRELIMINARY INSPECTION AND FOUND INTERMITTENT DIAL, ALSO MTL OUT OF SPECIFICATIONS, SIGNAL CUTS OUT AT -64DB WHEN DYNAMIC RANGE IS SET TO -9DB, ADJUSTED IF SECTION AND PRESELECTOR, NO HEL P. PROBLEM ON MAIN BOARD. SENDING TO VENDOR FOR REPAIR. 1 G 7 2 3U H13EU 2001091100012 20010911 00012 GL 2001 9 11 HEEA075478 2 20010821 G 7250 23033861 COVER 6898735 BOLKMS 105 BO105S 5626006 EU ALLSN 250C 250C20B 03013 GL SUMP CRACKED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 5031U CAT34156F S678 TURBINE REMOVED DUE TO NR 1 & 2 WHEEL CYCLES. UPON INSPECTION OF TURBINE NOTED NR 8 SUMP NUT BRAZEMENT ERODED AND CRACK ED. SCRAPPED COVER AND REPLACED WITH SERVICEABLE PART. 1 G 7 2 3U 3 U H3EU E4CE 2001091100013 20010911 00013 GL 2001 9 11 HEEA075479 2 20010821 G 7250 23053299 TURBINE WHEEL BELL 206 206L3 1182108 SW ALLSN 250C 250C30P 03013 GL ENGINE DAMAGED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 6251X 1904 51552 CAE895491 ENGINE REMOVED DUE TO 2000 HOUR INSPECTION. UPON INSPECTION OF TURIBNE PARTS NOTED SULFIDATION ON LEADING EDGE OF NR 1 WHEEL BLADES. SCRAPPED AND REPLACED WITH SERVICEABLE PART. 1 G 7 1 3U 3 U H2SW E1GL 2001091100014 20010911 00014 GL 2001 9 11 HEEA075480 2 20010821 G 7230 23066675 LINER BELL 206 206L3 1182108 SW ALLSN 250C 250C30P 03013 GL COMPRESSOR DAMAGED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 21497 51518 TORQUE OSCILLATIONS ABOVE 80%. 1 G 7 1 3U 3 U H2SW E1GL 2001091100015 20010911 00015 SW 2001 9 11 HEEA075481 1 20010821 G 7120 23069751 MOUNT BELL 206 206L3 1182108 SW ALLSN 250C 250C30P 03013 GL ENGINE DAMAGED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 30KH 51527 BEARING UNSTAKED. REPLACED WITH SERVICEABLE PART. 1 G 7 1 3U 3 U H2SW E1GL 2001091100016 20010911 00016 2001 9 11 HEEA075482 4 20010827 G 3434 066301201 SENSOR SKRSKY S76 S76A 8143006 NE MARKER BEACON BROKEN E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 1546G 760076 LIGHT SENSOR BROKEN. PERFORMED PRELIMINARY INSPECTION. FOUND V101 PHOTOCELL BROKEN OFF. REPLACED. REPAIRED. ALSO INS TALLED 3 LIGHT HOODS. BENCH CHECK GOOD. 1 G 7 2 3U H1NE 2001091100017 20010911 00017 2001 9 11 HEEA075483 4 20010828 G 2350 100005430 HEADSET SKRSKY S76 S76A 8143006 NE RADIO BROKEN E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 760PH 760078 BROKEN WIRES. SCRAPPED AND REPLACED WITH SERVICEABLE PART. 1 G 7 2 3U H1NE 2001091100018 20010911 00018 GL 2001 9 11 HEEA075484 2 20010828 G 7412 106149501 IGNITER BOX SKRSKY S76 S76A 8143006 NE ALLSN 250C 250C30S 03013 GL ENGINE INOPERATIVE E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 4253S 760035 IGNITER BOX INOPERATIVE. 1 G 7 2 3U 3 U H1NE E1GL 2001091200001 20010912 00001 2001 9 12 HEEA075485 4 20010828 G 3425 1113025 INDICATOR SKRSKY S76 S76A 8143006 NE HSI DAMAGED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 1546G 760076 HSI COURSE KNOB COMES OFF. 1 G 7 2 3U H1NE 2001091200002 20010912 00002 SW 2001 9 12 HEEA075486 1 20010821 G 6320 204040379003 QUILL BELL 412 412 1182202 SW LEAKING E HEEA K NONE K FLUID LOSS IN INSP/MAINT 1 SW 03 2149S 36002 QUILL ASSY SEEPING. REPLACED WITH SERVICEABLE PART. 1 G 7 2 4U H4SW 2001091200003 20010912 00003 SW 2001 9 12 HEEA075487 1 20010821 G 3246 205050400101 SADDLE 412050015110 BELL 412 412 1182202 SW SKID TUBE MISDRILLED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 7128R DRK100692 36007 MISDRILLED HOLES. THE HOLES FOR THE BOLTS (99-13-1), THAT ATTACHES THE FWD. CROSSTUBE TO THE SKID TUBE SADDLE ARE DRILL ED FOR AN4 BOLTS. 1 G 7 2 4U H4SW 2001091200004 20010912 00004 SW 2001 9 12 HEEA075488 1 20010821 G 2822 205060606003 PUMP BELL 412 412 1182202 SW FUEL BOOST MALFUNCTIONED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 6559Z 36019 PUMP PRODUCES NO PRESSURE. 1 G 7 2 4U H4SW 2001091200018 20010912 00018 SW 2001 9 12 HEEA075489 1 20010821 G 6320 205076034007 FILTER ELEMENT BELL 412 412 1182202 SW M/R GEARBOX FAILED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 2261D 33076 FILTER BYPASS EXTENDED. REPLACED WITH SERVICEABLE PART. 1 G 7 2 4U H4SW 2001091200019 20010912 00019 SW 2001 9 12 HEEA075490 1 20010821 G 6420 206001725001 PAD BELL 206 206L3 1182108 SW TAIL ROTOR DAMAGED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 6748D 51106 GREASE SEALS MISSING. REPLACED WITH SERVICEABLE PART. 1 G 7 1 3U H2SW 2001091200020 20010912 00020 SW 2001 9 12 HEEA075491 1 20010821 G 6720 206001763001 BELLCRANK BELL 206 206L3 1182108 SW TAIL ROTOR CORRODED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 6748D 51106 TAIL ROTOR BELLCRANK ASSY HAS CORROSION. REPLACED WITH SERVICEABLE PART. 1 G 7 1 3U H2SW 2001091200021 20010912 00021 SW 2001 9 12 HEEA075492 1 20010821 G 6210 206010200133 BLADE BELL 206 206B3 1181506 SW MAIN ROTOR CORRODED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 2277A 2336 3630 EXTREME TRAILING EDGE SPAR CORRODED AT THE TIP OF THE BLADE. 1 G 7 1 3U H2SW 2001091200022 20010912 00022 SW 2001 9 12 HEEA075493 1 20010821 G 6230 206010360005 LINK BELL 206 206L3 1182108 SW MAIN ROTOR CORRODED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 81671 51301 MAIN ROTOR HEAD LINK ASSY IS CORRODED. SCRAPPED. 1 G 7 1 3U H2SW 2001091200023 20010912 00023 SW 2001 9 12 HEEA075494 1 20010821 G 6220 206011117003 RESTRAINT BELL 206 206L3 1182108 SW MAIN ROTOR STUCK E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 30KH 51527 STICKING. REPLACED WITH SERVICEABLE PART. 1 G 7 1 3U H2SW 2001091200024 20010912 00024 SW 2001 9 12 HEEA075495 1 20010821 G 6220 206011117003 RESTRAINT BELL 206 206L3 1182108 SW MAIN ROTOR STUCK E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 6160Z 51610 STICKING. REPLACED WITH SERVICEABLE PART. 1 G 7 1 3U H2SW 2001091200025 20010912 00025 SW 2001 9 12 HEEA075496 1 20010821 G 6420 206011725001 ROD BELL 206 206L3 1182108 SW TAIL ROTOR WORN E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 21497 51518 ROD BEARING WORN. SCRAPPED. 1 G 7 1 3U H2SW 2001091200026 20010912 00026 SW 2001 9 12 HEEA075497 1 20010821 G 6300 206033553001 STOP BELL 206 206L3 1182108 SW MAIN ROTOR DEBONDED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 8591X 51495 RUBBER DEBONDED. SCRAPPED. 1 G 7 1 3U H2SW 2001091200027 20010912 00027 SW 2001 9 12 HEEA075498 1 20010821 G 6300 206033554101 LINK BELL 206 206L3 1182108 SW MAIN ROTOR DAMAGED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 BEARING BAD. 1 G 7 1 3U H2SW 2001091200028 20010912 00028 SW 2001 9 12 HEEA075499 1 20010821 G 6310 206040015015 DISK BELL 206 206L3 1182108 SW MAIN ROTOR DAMAGED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 21497 8748 51518 DISC WORN CAUSING NOISE WHEN ROTOR BRAKES APPLIED. REPLACED WITH SERVICEABLE PART. 1 G 7 1 3U H2SW 2001091200029 20010912 00029 SW 2001 9 12 HEEA075500 1 20010821 G 6310 206040270101 SUPPORT BELL 206 206L3 1182108 SW MAIN ROTOR LEAKING E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 21497 51518 LEAKING. REPLACED WITH SERVICEABLE PART. 1 G 7 1 3U H2SW 2001091200030 20010912 00030 SW 2001 9 12 HEEA075501 1 20010821 G 6310 206040270101 SUPPORT BELL 206 206B3 1181506 SW MAIN ROTOR LEAKING E HEEA K NONE K FLUID LOSS IN INSP/MAINT 1 SW 03 22751 3627 LEAKING. REPLACED WITH SERVICEABLE PART. 1 G 7 1 3U H2SW 2001091200031 20010912 00031 SW 2001 9 12 HEEA075502 1 20010821 G 6520 206040402105 GEARBOX BELL 206 206L3 1182108 SW TAIL ROTOR DAMAGED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 21497 8684 51518 PLAY IN OUTPUT SHAFT, UNABLE TO BALANCE TAIL ROTOR. REPLACED WITH SERVICEABLE PART. 1 G 7 1 3U H2SW 2001091200032 20010912 00032 SW 2001 9 12 HEEA075503 1 20010821 G 6520 206040402105 GEARBOX BELL 206 206L3 1182108 SW TAIL ROTOR MAKING METAL E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 21497 51518 MAKING METAL. REPLACED WITH SERVICEABLE PART. 1 G 7 1 3U H2SW 2001091200033 20010912 00033 SW 2001 9 12 HEEA075504 1 20010821 G 3246 206050128001 SHOE BELL 206 206L3 1182108 SW MLG SKID WORN E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 42EA 51542 SKID SHOE WORN. SCRAPPED. 1 G 7 1 3U H2SW 2001091200034 20010912 00034 SW 2001 9 12 HEEA075505 1 20010821 G 3246 206050129001 SHOE BELL 206 206L3 1182108 SW MLG SKID WORN E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 42EA 51542 SKID SHOE WORN. SCRAPPED. 1 G 7 1 3U H2SW 2001091200035 20010912 00035 SW 2001 9 12 HEEA075506 1 20010821 G 3213 206053109007 CROSSTUBE BELL 206 206L3 1182108 SW MLG CORRODED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 979BH 51403 CORRODED BEYOND LIMITS. SCRAPPED. 1 G 7 1 3U H2SW 2001091200036 20010912 00036 SW 2001 9 12 HEEA075507 1 20010821 G 3213 206053109008 CROSSTUBE BELL 206 206L3 1182108 SW MLG CORRODED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 979BH 51403 CROSSTUBE CORRODED BEYOND LIMITS. SCRAPPED. 1 G 7 1 3U H2SW 2001091200037 20010912 00037 SW 2001 9 12 HEEA075508 1 20010821 G 3213 206053203101 CROSSTUBE BELL 206 206L3 1182108 SW MLG CORRODED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 108PH 51334 CROSSTUBE CORRODED BEYOND LIMITS. SCRAPPED. 1 G 7 1 3U H2SW 2001091200038 20010912 00038 SW 2001 9 12 HEEA075509 1 20010821 G 2820 206061613003 FITTING BELL 206 206L3 1182108 SW FUEL SUMP CORRODED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 3108E 51498 FWD. FUEL SUMP FITTINGS CORRODED. REPLACED WITH SERVICEABLE FITTINGS. 1 G 7 1 3U H2SW 2001091200039 20010912 00039 SW 2001 9 12 HEEA075510 1 20010821 G 2820 206061634003 VALVE BELL 206 206L3 1182108 SW FUEL SYSTEM LEAKING E HEEA K NONE K FLUID LOSS IN INSP/MAINT 1 SW 03 42EA 51542 LEAKING FROM FUEL COCK. REPLACED WITH SERVICEABLE PART. 1 G 7 1 3U H2SW 2001091200042 20010912 00042 SW 2001 9 12 HEEA075511 1 20010821 G 6710 206062721109 ACTUATOR BELL 206 206L1 1182107 SW ENGINE INOPERATIVE E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 5019F 45244 ACTUATOR INOPERATIVE. REPLACED WITH SERVICEABLE PART. 1 G 7 1 3U H2SW 2001091200044 20010912 00044 SW 2001 9 12 HEEA075512 1 20010821 G 6710 206062721109 ACTUATOR BELL 206 206L3 1182108 SW ENGINE INOPERATIVE E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 ACTUATOR WILL NOT EXTEND OR RETRACT. 1 G 7 1 3U H2SW 2001091200045 20010912 00045 SW 2001 9 12 HEEA075513 1 20010821 G 6710 206062721109 ACTUATOR BELL 206 206L3 1182108 SW ENGINE INTERMITTENT E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 81SP 51029 WOULD NOT BEEP. BEEP WAS INTERMITTENT THROUGHOUT ADJUSTMENT ATTEMPTS. 1 G 7 1 3U H2SW 2001091200047 20010912 00047 SW 2001 9 12 HEEA075514 1 20010821 G 6710 206062721109 ACTUATOR BELL 206 206L3 1182108 SW ENGINE MALFUNCTIONED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 30KH 51527 N2 CHANGES IN FLIGHT. 1 G 7 1 3U H2SW 2001091200048 20010912 00048 SW 2001 9 12 HEEA075515 1 20010821 G 6710 206062721109 ACTUATOR BELL 206 206L3 1182108 SW ENGINE INOPERATIVE E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 ACTUATOR INOPERATIVE. 1 G 7 1 3U H2SW 2001091200049 20010912 00049 SW 2001 9 12 HEEA075516 1 20010821 G 6710 206062721109 ACTUATOR BELL 206 206L4 1182110 SW ENGINE INTERMITTENT E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 7074W 52033 ACTUATOR INTERMITTENT OPERATION. 1 G 7 1 3U NC H2SW 2001091200062 20010912 00062 SW 2001 9 12 HEEA075517 1 20010821 G 6710 206062721109 ACTUATOR BELL 206 206L3 1182108 SW ENGINE FAILED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 41791 51465 ACTUATOR MOTOR WORKED SEVERAL TIMES ON AIRCRAFT AND QUIT. BENCH TEST WAS ABLE TO RETRACT BUT NOT EXTEND. 1 G 7 1 3U H2SW 2001091200064 20010912 00064 SW 2001 9 12 HEEA075518 1 20010821 G 6710 206062721113 ACTUATOR BELL 206 206L3 1182108 SW DROOP COMP FAILED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 ACTUATOR WILL NOT RETRACT. 1 G 7 1 3U H2SW 2001091200066 20010912 00066 SW 2001 9 12 HEEA075519 1 20010821 G 2841 206063633103 INDICATOR BELL 206 206L3 1182108 SW FUEL QTY FLUCTUATES E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 8592X 51508 FLUCTUATING; OCCASIONALLY PEGGING OUT ON THE HIGH SIDE. 1 G 7 1 3U H2SW 2001091200088 20010912 00088 SW 2001 9 12 HEEA075520 1 20010821 G 7120 206064105101 LEG ASSY BELL 206 206L4 1182110 SW ENGINE MOUNT CORRODED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 62127 52023 CORROSION ON INSIDE OF TUBE. REPLACED WITH SERVICEABLE PART. 1 G 7 1 3U NC H2SW 2001091200093 20010912 00093 SW 2001 9 12 HEEA075521 1 20010821 G 7120 206064105101 LEG ASSY BELL 206 206L3 1182108 SW ENGINE MOUNT CORRODED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 81671 51301 PITTING ON INSIDE OF TUBE. SCRAPPED AND REPLACED WITH SERVICEABLE PART. 1 G 7 1 3U H2SW 2001091200094 20010912 00094 SW 2001 9 12 HEEA075522 1 20010821 G 7120 206064105102 LEG ASSY BELL 206 206L4 1182110 SW ENGINE MOUNT DAMAGED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 62127 52023 ELONGATED HI-LOC HOLES. SCRAPPED AND REPLACED WITH SERVICEABLE PART. 1 G 7 1 3U NC H2SW 2001091200096 20010912 00096 SW 2001 9 12 HEEA075523 1 20010821 G 7120 206064106101 LEG ASSY BELL 206 206L4 1182110 SW ENGINE MOUNT CORRODED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 62127 52023 CORROSION ON INSIDE OF TUBE. SCRAPPED AND REPLACED WITH SERVICEABLE PART. 1 G 7 1 3U NC H2SW 2001091200099 20010912 00099 SW 2001 9 12 HEEA075524 1 20010821 G 6220 206011100159 HUB BELL 206 206L3 1182108 SW MAIN ROTOR LEAKING E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 4835 51131 YELLOW GRIP SLINGING GREASE. REPLACED WITH SERVICEABLE ASSY. 1 G 7 1 3U H2SW 2001091200100 20010912 00100 SW 2001 9 12 HEEA075525 1 20010821 G 6320 206040004107 TRANSMISSION BELL 206 206L3 1182108 SW MAIN ROTOR MAKING METAL E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 31077 51520 MAKING METAL. REPLACED WITH SERVICEABLE ASSY. 1 G 7 1 3U H2SW 2001091200101 20010912 00101 SW 2001 9 12 HEEA075526 1 20010821 G 7120 206064106101 LEG ASSY BELL 206 206L4 1182110 SW ENGINE MOUNT CHAFED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 62127 52023 CHAFED BEYOND LIMITS. SCAPPED AND REPLACED WITH SERVICEABLE PART. 1 G 7 1 3U NC H2SW 2001091200102 20010912 00102 SW 2001 9 12 HEEA075527 1 20010821 G 7120 206064106101 LEG ASSY BELL 206 206L3 1182108 SW ENGINE MOUNT CHAFED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 81671 51301 CHAFED BEYOND LIMITS. SCAPPED AND REPLACED WITH SERVICEABLE PART. 1 G 7 1 3U H2SW 2001091200103 20010912 00103 SW 2001 9 12 HEEA075528 1 20010821 G 7120 206064106101 LEG ASSY BELL 206 206L3 1182108 SW ENGINE MOUNT DAMAGED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 979BH 51403 END FITTING RIVET HOLES ARE ELONGATED AND WORN BEYOND LIMITS. SCAPPED AND REPLACED WITH SERVICEABLE PART. 1 G 7 1 3U H2SW 2001091200147 20010912 00147 SW 2001 9 12 HEEA075529 1 20010821 G 7120 206064107101 LEG ASSY BELL 206 206L3 1182108 SW ENGINE MOUNT DAMAGED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 81671 51301 RIVET HOLES ARE ELONGATED. SCAPPED AND REPLACED WITH SERVICEABLE PART. 1 G 7 1 3U H2SW 2001091200148 20010912 00148 SW 2001 9 12 HEEA075530 1 20010821 G 7120 206064107109 LEG ASSY BELL 206 206L4 1182110 SW ENGINE MOUNT DAMAGED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 62127 52023 ELONGATED HI-LOC HOLES. SCAPPED AND REPLACED WITH SERVICEABLE PART. 1 G 7 1 3U NC H2SW 2001091200149 20010912 00149 SW 2001 9 12 HEEA075531 1 20010821 G 7120 206064107111 LEG ASSY BELL 206 206L4 1182110 SW ENGINE MOUNT CHAFED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 62127 52023 CHAFED BEYOND LIMITS. SCAPPED AND REPLACED WITH SERVICEABLE PART. 1 G 7 1 3U NC H2SW 2001091200150 20010912 00150 SW 2001 9 12 HEEA075532 1 20010821 G 6730 206076062003 CYLINDER BELL 206 206L3 1182108 SW SERVO SYSTEM LEAKING E HEEA K NONE K FLUID LOSS IN INSP/MAINT 1 SW 03 8594X 51531 LEAKING. REPLACED WITH SERVICEABLE PART. 1 G 7 1 3U H2SW 2001091200151 20010912 00151 SW 2001 9 12 HEEA075533 1 20010821 G 6730 206076062003 CYLINDER BELL 206 206L3 1182108 SW SERVO SYSTEM LEAKING E HEEA K NONE K FLUID LOSS IN INSP/MAINT 1 SW 03 8591X 51495 LEAKING. REPLACED WITH SERVICEABLE PART. 1 G 7 1 3U H2SW 2001091200152 20010912 00152 SW 2001 9 12 HEEA075534 1 20010821 G 3246 206323002M CROSSTUBE BELL 206 206L3 1182108 SW MLG SKID CORRODED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 108PH 51334 CORRODED BEYOND LIMITS IN SADDLE AREA. SCRAPPED AND REPLACED WITH SERVICEABLE PART. 1 G 7 1 3U H2SW 2001091200153 20010912 00153 SW 2001 9 12 HEEA075535 1 20010821 G 3246 206323017 CROSSTUBE BELL 206 206L1 1182107 SW MLG SKID CORRODED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 5007Q 45187 CORROSION PITS. SCRAPPED AND REPLACED WITH SERVICEABLE PART. 1 G 7 1 3U H2SW 2001091200154 20010912 00154 SW 2001 9 12 HEEA075536 1 20010821 G 3246 206323017 CROSSTUBE BELL 206 206L3 1182108 SW MLG SKID CORRODED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 8592X 51508 CORRODED BEYOND LIMITS IN AREA AROUND SADDLES. SCRAPPED AND REPLACED WITH SERVICEABLE PART. 1 G 7 1 3U H2SW 2001091200156 20010912 00156 SW 2001 9 12 HEEA075537 1 20010821 G 3246 206323017 CROSSTUBE BELL 206 206L3 1182108 SW MLG SKID CORRODED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 6748D 51106 CORROSION BEYOND LIMITS. SCRAPPED AND REPLACED WITH SERVICEABLE PART. 1 G 7 1 3U H2SW 2001091200157 20010912 00157 SW 2001 9 12 HEEA075538 1 20010821 G 3246 206323017 CROSSTUBE BELL 206 206L3 1182108 SW MLG SKID CORRODED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 42EA 51542 CORROSION PITS UNDER BOTH SADDLE MOUNT AREAS. SCRAPPED AND REPLACED WITH SERVICEABLE PART. 1 G 7 1 3U H2SW 2001091200158 20010912 00158 SW 2001 9 12 HEEA075539 1 20010821 G 3246 206323018 CROSSTUBE BELL 206 206L3 1182108 SW MLG SKID CORRODED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 6748D 51106 CORROSION BEYOND LIMITS. SCRAPPED AND REPLACED WITH SERVICEABLE PART. 1 G 7 1 3U H2SW 2001091200159 20010912 00159 SW 2001 9 12 HEEA075540 1 20010821 G 3246 206324007 SKID BELL 206 206L3 1182108 SW MLG CORRODED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 979BH 51403 CORROSION BEYOND LIMITS. SCRAPPED AND REPLACED WITH SERVICEABLE PART. 1 G 7 1 3U H2SW 2001091200160 20010912 00160 SW 2001 9 12 HEEA075541 1 20010821 G 3246 206324008 SKID BELL 206 206L3 1182108 SW MLG CORRODED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 979BH 51403 CORROSION BEYOND LIMITS. SCRAPPED AND REPLACED WITH SERVICEABLE PART. 1 G 7 1 3U H2SW 2001091200161 20010912 00161 SW 2001 9 12 HEEA075542 1 20010821 G 3246 206324459 SKID BELL 206 206L3 1182108 SW MLG DAMAGED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 4835 51131 RIVET POPPED. SCRAPPED AND REPLACED WITH SERVICEABLE PART. 1 G 7 1 3U H2SW 2001091200162 20010912 00162 SW 2001 9 12 HEEA075543 1 20010821 G 3246 206324459 SKID BELL 206 206L3 1182108 SW MLG CORRODED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 6748D 51106 CORROSION BEYOND LIMITS. SCRAPPED AND REPLACED WITH SERVICEABLE PART. 1 G 7 1 3U H2SW 2001091200174 20010912 00174 SW 2001 9 12 HEEA075544 1 20010821 G 3246 206324460 SKID BELL 206 206L3 1182108 SW MLG CORRODED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 6748D 51106 CORROSION BEYOND LIMITS. SCRAPPED AND REPLACED WITH SERVICEABLE PART. 1 G 7 1 3U H2SW 2001091200175 20010912 00175 SW 2001 9 12 HEEA075545 1 20010821 G 6520 212040004009 GEARBOX BELL 412 412 1182202 SW TAIL ROTOR LEAKING E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 107X 33113 INPUT QUILL SEAL LEAKING. REPLACED WITH SERVICEABLE ASSY. 1 G 7 2 4U H4SW 2001091200177 20010912 00177 SW 2001 9 12 HEEA075546 1 20010821 G 6300 212040005103 DRIVE SHAFT BELL 412 412 1182202 SW MAIN ROTOR LEAKING E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 1202T 33112 GREASE SEALS LEAKING. REPLACED WITH SERVICEABLE ASSY. 1 G 7 2 4U H4SW 2001091200179 20010912 00179 SW 2001 9 12 HEEA075548 1 20010821 G 6510 212040600005 BEARING BELL 412 412 1182202 SW TAIL ROTOR OVERHEATED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 2149S 36002 OVERTEMP INDICATION. REPLACED WITH SERVICEABLE PART. 1 G 7 2 4U H4SW 2001091200180 20010912 00180 GL 2001 9 12 HEEA075549 2 20010821 G 7532 23005366 BLEED VALVE BELL 206 206L3 1182108 SW ALLSN 250C 250C30P 03013 GL ENGINE MALFUNCTIONED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 4835 51131 ENGINE T.O.T. RUNNING HIGHER THAN NORMAL. REPLACED WITH SERVICEABLE PART. 1 G 7 1 3U 3 U H2SW E1GL 2001091200182 20010912 00182 GL 2001 9 12 HEEA075550 2 20010821 G 7532 23005366 BLEED VALVE BELL 206 206L3 1182108 SW ALLSN 250C 250C30P 03013 GL ENGINE MALFUNCTIONED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 4835 51131 ENGINE T.O.T. RUNNING HIGHER THAN NORMAL. REPLACED WITH SERVICEABLE PART. 1 G 7 1 3U 3 U H2SW E1GL 2001091200185 20010912 00185 GL 2001 9 12 HEEA075551 2 20010821 G 7200 23008727 SOLENOID BELL 206 206L3 1182108 SW ALLSN 250C 250C30 03013 GL ENGINE STUCK E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 4835 51131 STUCK OPEN CAUSING HIGH T.O.T. REPLACED WITH SERVICEABLE PART. 1 G 7 1 3U 3 U H2SW E1GL 2001091200190 20010912 00190 SW 2001 9 12 HEEA075552 1 20010821 G 7160 23033400 FILTER BELL 206 206L3 1182108 SW ENGINE INTAKE DAMAGED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 4835 51131 N1 HANGS UP DURING STARTS. REPLACED WITH SERVICEABLE PART. 1 G 7 1 3U H2SW 2001091200192 20010912 00192 SW 2001 9 12 HEEA075553 1 20010821 G 2435 23081018 STARTER GEN BELL 206 206L3 1182108 SW ELECTRICAL FAILED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 21497 51518 GENERATOR WILL NOT RESET. REPLACED WITH SERVICEABLE PART. 1 G 7 1 3U H2SW 2001091200194 20010912 00194 GL 2001 9 12 HEEA075554 2 20010821 G 7321 252464430 FUEL CONTROL BELL 206 206B3 1181506 SW ALLSN 250C 250C30 03013 GL ENGINE MALFUNCTIONED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 22743 3624 UNABLE TO ADJUST START TEMP. LOW ENOUGH TO GET ENG. STARTED. START MODE FUEL FLOW APPROX. 3 TIMES ALLISON LIMITS. FOUND FLOWS 12PPH HIGH. (METERING VALVE SHIFTED), RECALIBRATED AND TESTED OK. 1 G 7 1 3U 3 U H2SW E1GL 2001091200197 20010912 00197 GL 2001 9 12 HEEA075555 2 20010821 G 7323 252469211 GOVERNOR BELL 206 206L3 1182108 SW ALLSN 250C 250C30 03013 GL ENGINE MALFUNCTIONED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 4835 51131 UNABLE TO CORRECT OVERSPEED. FOUND GOVERNOR BREAK RESPONDED 100 RPM EARLY. TESTED SATISFACTORY. 1 G 7 1 3U 3 U H2SW E1GL 2001091200203 20010912 00203 GL 2001 9 12 HEEA075556 2 20010821 G 7321 25490925 FUEL CONTROL BELL 206 206L3 1182108 SW ALLSN 250C 250C30 03013 GL ENGINE MALFUNCTIONED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 31073 2534 51519 ENGINE WOULD NOT ACCELERATE ON START, ADJUSTING START DERICHMENT AND START ACCELERATION TO MAXIMUM HAD NO EFFECT. FOUND PRESSURIZING VALVE TO BE STICKING. REMOVED VALVE AND POLISHED. VALVE WOULD STILL HANG UP. REPLACED VALVE AND UNIT TES TED SATISFACTORY. 1 G 7 1 3U 3 U H2SW E1GL 2001091200204 20010912 00204 GL 2001 9 12 HEEA075557 2 20010821 G 7321 25490925 FUEL CONTROL BELL 206 206L3 1182108 SW ALLSN 250C 250C30 03013 GL ENGINE MALFUNCTIONED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 4282Z 9935 51499 START ACCEL ADJUSTMENT FROZEN. REPLACED WITH SERVICEABLE FUEL CONTROL. 1 G 7 1 3U 3 U H2SW E1GL 2001091200208 20010912 00208 SW 2001 9 12 HEEA075558 1 20010821 G 2432 32007001 BATTERY BELL 206 206L3 1182108 SW MAIN BATTERY DISCHARGED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 8587X 51464 LOW STARTING CAPACITY AND WILL NOT TAKE A FULL CHARGE. REPLACED WITH SERVICEABLE BATTERY. 1 G 7 1 3U H2SW 2001091200209 20010912 00209 SW 2001 9 12 HEEA075559 1 20010821 G 2432 32007001 BATTERY BELL 206 206L3 1182108 SW MAIN BATTERY OVERHEATED E HEEA O OTHER J WARNING INDICATION NR NOT REPORTED 1 SW 03 4835 51131 BATTERY HOT LIGHT CAME ON. REPLACED WITH SERVICEABLE BATTERY. 1 G 7 1 3U H2SW 2001091200212 20010912 00212 SW 2001 9 12 HEEA075560 1 20010821 G 6210 412015300109 BLADE BELL 412 412 1182202 SW MAIN ROTOR DAMAGED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 7128R 11837 36007 BLADE DIVES UNABLE TO TRACK. 1 G 7 2 4U H4SW 2001091200213 20010912 00213 SW 2001 9 12 HEEA075561 1 20010821 G 6210 412015300109 BLADE BELL 412 412 1182202 SW MAIN ROTOR MISMANUFACTURED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 7128R 11544 36007 BLADE EXCESSIVELY HEAVY AND CANNOT GET TO 80 PERCENT ROTOR RPM. 1 G 7 2 4U H4SW 2001091200214 20010912 00214 SW 2001 9 12 HEEA075562 1 20010821 G 3213 412050010111A CROSSTUBE BELL 412 412 1182202 SW MLG CORRODED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 6559Z 3621 36019 CROSSTUBE CORRODED. SCRAPPED. 1 G 7 2 4U H4SW 2001091300001 20010913 00001 SW 2001 9 13 HEEA075563 1 20010821 G 3212 412050013113 FLOAT BELL 412 412 1182202 SW RT MLG LEAKING E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 6559Z 36019 RT MID FLOAT BAG LEAKING AROUND RELIEF VALVE. SENT TO OFFSHORE HELICOPTER SUPPORT FOR INSPECTION AND REPAIR. 1 G 7 2 4U H4SW 2001091300002 20010913 00002 SW 2001 9 13 HEEA075564 1 20010821 G 3212 412050013113 FLOAT BELL 412 412 1182202 SW MLG LEAKING E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 2148K 36001 FLOAT BAG LEAKING. 1 G 7 2 4U H4SW 2001091300003 20010913 00003 SW 2001 9 13 HEEA075565 1 20010821 G 3246 412050015110 SKID BELL 412 412 1182202 SW MLG DAMAGED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 107X 33113 FWD SADDLE RIVETS LOOSE. SCRAPPED AND REPLACED WITH SERVICEABLE TUBE. 1 G 7 2 4U H4SW 2001091300004 20010913 00004 SW 2001 9 13 HEEA075566 1 20010821 G 3212 412050017133 COVER BELL 412 412 1182202 SW FLOAT BAG TORN E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 2258F 33073 FLOAT BAG COVER VELCRO TORN. 1 G 7 2 4U H4SW 2001091300005 20010913 00005 SW 2001 9 13 HEEA075567 1 20010821 G 3212 412050017133 COVER BELL 412 412 1182202 SW FLOAT BAG WORN E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 2261D 33076 FLOAT BAG COVER VELCRO WORN. 1 G 7 2 4U H4SW 2001091300006 20010913 00006 SW 2001 9 13 HEEA075568 1 20010821 G 3212 412050017135 COVER BELL 412 412 1182202 SW FLOAT BAG TORN E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 2258F 33073 FLOAT BAG VELCRO TORN. 1 G 7 2 4U H4SW 2001091300007 20010913 00007 SW 2001 9 13 HEEA075569 1 20010821 G 3213 412050045107 CROSSTUBE BELL 412 412 1182202 SW MLG CORRODED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 7128R 1290 36007 FOUND CORROSION UNDER CENTER PIVOT MOUNT. SCRAPPED AND REPLACED WITH SERVICEABLE TUBE. 1 G 7 2 4U H4SW 2001091300008 20010913 00008 SW 2001 9 13 HEEA075570 1 20010821 G 5210 412060804101 HINGE BELL 412 412 1182202 SW PAX DOOR DAMAGED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 1202T 33112 RIVET LOOSE. REPLACED WITH SERVICEABLE HINGE. 1 G 7 2 4U H4SW 2001091300009 20010913 00009 SW 2001 9 13 HEEA075571 1 20010821 G 2810 412061668101 CAP BELL 412 412 1182202 SW FUEL CELL DAMAGED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 5759N 33002 CAP CAN TURN BEYOND OPEN POSITION OR OFTEN MISPOSITIONS CLOSURE CLAWS CAUSING CAP TO BE DIFFICULT TO REMOVE. REPLACED WI TH SERVICEABLE ASSY. 1 G 7 2 4U H4SW 2001091300010 20010913 00010 2001 9 13 HEEA075572 4 20010821 G 2330 002000002 AMPLIFIER BELL 412 412 1182202 SW PA SYSTEM INOPERATIVE E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 33008 36004 PA INOPERATIVE. PERFORMED PRELIMINARY INSPECTION. FOUND FUSE F1 AND TRANSISTOR Q8 BAD. REPLACED. BENCH CHECK GOOD. 1 G 7 2 4U H4SW 2001091300011 20010913 00011 2001 9 13 HEEA075573 4 20010821 G 2312 064101900 RADIO BELL 206 206L3 1182108 SW VHF COMMS WEAK E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 3107N 51512 GARBLED AND WEAK. PERFORMED PRELIMINARY INSPECTION. FOUND UNIT HAD TOO MUCH POWER OUT BUT GOOD MODULATION. THEN MODULA TORS BECAME VERY WEAK AND DISTORTED. FOUND Q121, Q122 TRANSISTORS BAD. REPLACED Q121 AND Q122 TRANSISTORS. ADJUSTED M IC GAIN AND SIDETONE. REPAIRED. FOUND MEMORY NOT WORKING DUE TO BROKEN FOIL ON SW102 SWITCH. REPAIRED BROKEN FOIL. RE PAIRED. BENCH CHECK GOOD. 1 G 7 1 3U H2SW 2001091300012 20010913 00012 2001 9 13 HEEA075574 4 20010821 G 2312 064101900 RADIO BELL 206 206L1 1182107 SW VHF COMMS MALFUNCTIONED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 1076Y 45380 WOULD NOT CHANGE FREQUENCY. REPLACED BAD KHZ KNOB/SHAFT AND RESOLDERED COLD SOLDER ON SW102 SWITCH. REPAIRED. ALIGNED RECEIVER AND ADJUSTED C/N SQUELCH, MIC GAIN AND SIDETONE. REPLACED BAD DISPLAY LENS. BENCH CHECK GOOD. 1 G 7 1 3U H2SW 2001091300013 20010913 00013 2001 9 13 HEEA075575 4 20010824 G 2312 064101902 RADIO BELL 206 206L3 1182108 SW VHF COMMS INTERMITTENT E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 8593X 51509 INTERMITTENTLY UNABLE TO CHANGE FREQUENCY. PERFORMED PRELIMINARY INSPECTION. FOUND SELECTOR KNOBS INTERMITTENTLY DO NOT CHANGE FREQUENCY. CLEANED WAFER SWITCHES. REPAIRED. FOUND POWER OUT LOW AT 135 MHZ. REPLACED C623 AND C624 CAPACITO RS. REPAIRED. ADJUSTED C/N SQUELCH, MIC GAIN AND SIDETONE. BENCH CHECK GOOD. 1 G 7 1 3U H2SW 2001091300014 20010913 00014 2001 9 13 HEEA075576 4 20010824 G 2312 064102300 TRANSCEIVER BELL 412 412 1182202 SW VHF COMMS MALFUNCTIONED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 142PH 33150 SQUELCH STAYS ON ALL THE TIME AND THE RF CONNECTOR IS DAMAGED. PERFORMED PRELIMINARY INSPECTION. REPLACED BAD RF CONNECT OR. REPAIRED. ADJUSTED CARRIER SQUELCH, FREQUENCY AND POWER OUT. BENCH CHECK GOOD. 1 G 7 2 4U H4SW 2001091300015 20010913 00015 2001 9 13 HEEA075577 4 20010824 G 2312 064102300 TRANSCEIVER BELL 412 412 1182202 SW VHF COMMS MALFUNCTIONED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 30YM 36032 NO SIDETONE. PERFORMED PRELIMINARY INSPECTION. FOUND UNIT NOT MODULATING AND TRANSMIT POWER OUT EXCESSIVE AND COULD NOT ADJUST EITHER. REPLACED BAD Q109 AND Q110 TRANSISTORS. REPAIRED. ADJUSTED POWER OUT AND SIDETONE. FOUND L505 COIL BR OKEN. REPLACED COIL. REMOVED LIGHT CORROSION FROM CHASSIS. BENCH CHECK GOOD. 1 G 7 2 4U H4SW 2001091300016 20010913 00016 2001 9 13 HEEA075578 4 20010824 G 2312 064105430 TRANSCEIVER BELL 206 206L3 1182108 SW VHF COMMS MALFUNCTIONED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 8588X 51486 TRANSMISSION GARBLED. PERFORMED PRELIMINARY INSPECTION. COULD NOT DUPLICATE COMPLAINT BUT FOUND DISPLAY LENS BAD. REPLA CED LENS AND REPAIRED. ADJUSTED FREQUENCY AND SIDETONE. BENCH CHECK GOOD. 1 G 7 1 3U H2SW 2001091300017 20010913 00017 2001 9 13 HEEA075579 4 20010824 G 2312 064105430 TRANSCEIVER BELL 206 206L3 1182108 SW VHF COMMS FAILED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 205FC 51130 FIRST AND LAST DIGITS DISAPPEAR INTERMITTENTLY. PERFORMED PRELIMINARY INSPECTION. FOUND DISPLAY NOT DIMMING PROPERLY. REPLACED V901 PHOTOCELL. REPAIRED. FOUND FREQUENCY SELECTORS INTERMITTENT AND MHZ CHANGED BY ITSELF A COUPLE OF TIMES. FOUND FREQUENCY SELECTOR CONTACTS VERY DIRTY. CLEANED. REPAIRED. REGLUED DISPLAY LENS WHICH WAS LOOSE. ADJUSTED FRE QUENCY. BENCH CHECK GOOD. 1 G 7 1 3U H2SW 2001091300018 20010913 00018 2001 9 13 HEEA075580 4 20010824 G 2312 064105430 TRANSCEIVER BELL 206 206L3 1182108 SW VHF COMMS FAILED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 8588X 51486 SQUELCH WILL NOT RESET AFTER RECEPTION OR TEST. SENT TO HONEYWELL, KANSAS FOR WARRANTY REPAIR. 1 G 7 1 3U H2SW 2001091300019 20010913 00019 2001 9 13 HEEA075581 4 20010824 G 2312 066106200 TRANSCEIVER BELL 206 206B3 1181506 SW VHF COMMS FAILED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 22743 3624 WILL NOT TRANSMIT AT THE RIGHT FREQUENCY. PERFORMED PRELIMINARY INSPECTION. ADJUSTED FREQUENCY, PULSE WIDTH AND POWER. ALIGNED PRESELECTOR AND IF. REPAIRED. ALSO REPLACED BAD V301 PHOTOCELL. UNIT BENCH CHECK GOOD. 1 G 7 1 3U H2SW 2001091300020 20010913 00020 2001 9 13 HEEA075582 4 20010824 G 2312 066106200 TRANSCEIVER BELL 206 206L1 1182107 SW VHF COMMS BROKEN E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 3905B 45598 SELECTOR KNOB BROKEN INTERNALLY. PERFORMED PRELIMINARY INSPECTION. FOUND FACEPLATE BAD. REPLACED FACEPLATE. REPAIRED. CLEANED CODE SELECTOR WAFER SWITCHES. ALIGNED IF SECTION. UNIT BENCH CHECK GOOD. 1 G 7 1 3U H2SW 2001091300021 20010913 00021 2001 9 13 HEEA075583 4 20010824 G 2312 066106200 TRANSCEIVER BELL 206 206L4 1182110 SW VHF COMMS MALFUNCTIONED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 62127 52023 NO REPLY. PERFORMED PRELIMINARY INSPECTION. FOUND REPLY LIGHT VERY DIM DUE TO BAD PHOTOCELL. REPLACED V301 PHOTOCELL. REPAIRED PROBLEM. ALSO REPLACED BAD R477 RESISTOR AND ADJUSTED FREQUENCY AND PULSE WIDTH. BENCH CHECK GOOD. 1 G 7 1 3U NC H2SW 2001091300022 20010913 00022 2001 9 13 HEEA075584 4 20010824 G 2312 066106200 TRANSCEIVER BELL 206 206L3 1182108 SW VHF COMMS FAILED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 30KH 51527 NO TRANSMIT. PERFORMED PRELIMINARY INSPECTION. FOUND FOUND V101 CAVITY OSCILLATOR BAD. REPLACED V101, REPAIRED. ADJUS TED TO SPECS. BENCH CHECK GOOD. 1 G 7 1 3U H2SW 2001091300023 20010913 00023 2001 9 13 HEEA075585 4 20010824 G 2312 066106200 TRANSCEIVER BELL 206 206L3 1182108 SW VHF COMMS FAILED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 41128 51134 UNIT FAILED ALTITUDE CERTIFICATION. UNIT TRANSMITS IMPROPER CODES BETWEEN 700 AND 900 PA. PERFORMED PRELIMINARY INSPECT ION. ADJUSTED TUBE FOR PROPER FREQUENCY BAND WIDTH. BENCH CHECK GOOD. 1 G 7 1 3U H2SW 2001091300024 20010913 00024 2001 9 13 HEEA075586 4 20010824 G 2312 066106200 TRANSCEIVER BELL 206 206L3 1182108 SW VHF COMMS FAILED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 6161A 51611 NOT TRANSMITTING. PERFORMED PRELIMINARY INSPECTION. FOUND DRAWING EXCESSIVE CURRENT. FOUND Q1 AND Q3 SHORTED. SENT TO AVCOM AVIONICS & INSTRUMENTS FOR INSPECTION AND REPAIR. 1 G 7 1 3U H2SW 2001091300025 20010913 00025 2001 9 13 HEEA075587 4 20010824 G 3452 066107100 TRANSPONDER BELL 412 412 1182202 SW ATC FAILED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 21498 36003 WENT DEAD. PERFORMED PRELIMINARY INSPECTION. FOUND CR106 DIODE BURNT AND C111 CAPACITOR SHORTED. ALSO FOUND C115 CAPAC ITOR BAD. REPLACED CR106 DIOD AND C111 AND C115 CAPACITORS. ADJUSTED MTL. UNIT BENCH CHECK GOOD. 1 G 7 2 4U H4SW 2001091300026 20010913 00026 2001 9 13 HEEA075589 4 20010827 G 2312 066107800 RECEIVER BELL 412 412 1182202 SW NAVIGATION FAILED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 22347 36005 BAD FROM STOCK. FOUND AT 60 DEGREES TO. NEEDLE DOES NOT FOLLOW WHEN TURNING COMPASS. SENT TO GREATLAKES AVIONICS FOR W ARRANTY REPAIR. 1 G 7 2 4U H4SW 2001091300027 20010913 00027 2001 9 13 HEEA075590 4 20010827 G 3416 066304400 ALTIMETER BELL 412 412 1182202 SW COCKPIT INOPERATIVE E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 2149S 36002 DH LIGHT IS INOPERATIVE. PERFORMED PRELIMINARY INSPECTION. FOUND DH SWITCH BROKEN AND LENS CLAMP BROKEN. INSTALLED DH SWITCH AND LENS CLAMP. ALSO REPLACED THE PHOTOCELL. THE DH LIGHT STAYS ON AT ALL TIMES AND NO SELF TEST. SENT TO GREA TLAKES AVIONICS FOR INSPECTION AND REPAIR. 1 G 7 2 4U H4SW 2001091300082 20010913 00082 2001 9 13 HEEA075591 4 20010827 G 2312 0691024155 TRANSCEIVER BELL 206 206L3 1182108 SW VHF COMMS INTERMITTENT E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 6251X 51552 DIGITAL SEGMENTS ARE INTERMITTENT. PERFORMED PRELIMINARY INSPECTION. REPLACED DISPLAY. REPAIRED. BENCH CHECK GOOD. 1 G 7 1 3U H2SW 2001091300083 20010913 00083 2001 9 13 HEEA075592 4 20010827 G 3452 071119218 CONTROL PANEL BELL 214 214ST 1182106 SW ATC INTERMITTENT E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 59806 28140 DIGITS INOPERATIVE. PERFORMED PRELIMINARY INSPECTION. FOUND HEADER BAD. DIGITS INTERMITTENTLY FLICKERS. DRIVER BOARD CAUSING SOME BRIGHT SEGMENTS ON DISPLAY. INSTALLED HEADER P305, J304, CAPACITOR NETWORK U301. DIGITS WILL NOT CHANGE W HEN DIAL IS TURNED. SENT TO HONEYWELL, KANSAS FOR INSPECTION AND REPAIR. 2 G 7 2 4U H10SW 2001091300084 20010913 00084 2001 9 13 HEEA075593 4 20010827 G 2312 071121525 CONTROL UNIT BELL 214 214ST 1182106 SW COCKPIT INOPERATIVE E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 59806 28140 DISPLAY HAS ONE DIGIT INOPERATIVE. PERFORMED PRELIMINARY INSPECTION. FOUND IC 201 BAD. REPLACED. BENCH CHECK GOOD. 2 G 7 2 4U H10SW 2001091300085 20010913 00085 2001 9 13 HEEA075594 4 20010827 G 2312 071121540 CONTROL UNIT BELL 412 412 1182202 SW VHF COMMS FAILED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 7128R 36007 UNIT DOES NOT KEEP LAST TWO DIGITS WHEN TURNED ON. PERFORMED PRELIMINARY INSPECTION. FOUND IC 1205 BAD. REPLACED. BEN CH CHECK GOOD. 1 G 7 2 4U H4SW 2001091300086 20010913 00086 2001 9 13 HEEA075595 4 20010827 G 3455 066107700 RECEIVER BELL 412 412 1182202 SW ADF INOPERATIVE E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 2149S 36002 ADF RECEIVER INOPERATIVE. 1 G 7 2 4U H4SW 2001091300087 20010913 00087 SW 2001 9 13 HEEA075596 1 20010827 G 2824 205060606003 PUMP BELL 412 412 1182202 SW FUEL TRANSFER INOPERATIVE E HEEA O OTHER J WARNING INDICATION CR CRUISE 1 SW 03 2149S 36002 WHILE IN CRUISE FLIGHT, NR 2 FUEL TRANSFER LIGHT ILLUMINATED. REPLACED INOPERATIVE NR 2 TRANSFER PUMP. 1 G 7 2 4U H4SW 2001091300088 20010913 00088 SW 2001 9 13 HEEA075598 1 20010827 G 6320 406340100101 PUMP BELL 407 407 SW OIL SYSTEM LEAKING E HEEA K NONE K FLUID LOSS IN INSP/MAINT 1 SW 03 407PH 53003 INTERNAL SEAL LEAKING. 1 G 7 1 3U O H2SW 2001091300089 20010913 00089 SW 2001 9 13 HEEA075605 1 20010827 G 2844 407362013101 PRESSURE SWITCH BELL 407 407 SW FUEL SYSTEM FAILED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 510PH 53209 NO LIGHT WHEN PUMP IS OFF. 1 G 7 1 3U O H2SW 2001091300090 20010913 00090 SW 2001 9 13 HEEA075607 1 20010827 G 3340 407076502103S CONNECTOR BELL 407 407 SW CABIN CORRODED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 405PH 53207 CANNON PLUG CORRODED. REPEATED PROBLEM WITH CANNON PLUG, SENDING IN FOR EVALUATION FOR POSSIBLE MFG DEFECT. 1 G 7 1 3U O H2SW 2001091300091 20010913 00091 2001 9 13 HEEA075609 4 20010828 G 2350 100005430 HEADSET BELL 206 206L3 1182108 SW AUDIO SYSTEM INOPERATIVE E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 4835 51131 INOPERATIVE. SCRAPPED AND REPLACED WITH SERVICEABLE PART. 1 G 7 1 3U H2SW 2001091300093 20010913 00093 2001 9 13 HEEA075610 4 20010828 G 3410 1113025 INDICATOR BELL 412 412 1182202 SW HSI MALFUNCTIONED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 1202T 33112 CAUSED THE FLIGHT DIRECTOR TO OSCILLATE IN HEADING MODE. 1 G 7 2 4U H4SW 2001091300096 20010913 00096 2001 9 13 HEEA075611 4 20010828 G 3420 1113025 INDICATOR BELL 412 412 1182202 SW HSI MALFUNCTIONED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 1202T 33112 COURSE NEEDLE WILL NOT FOLLOW COPILOT'S COURSE NEEDLE. 1 G 7 2 4U H4SW 2001091300097 20010913 00097 2001 9 13 HEEA075612 4 20010828 G 3421 1113034 INDICATOR BELL 412 412 1182202 SW AFCS MALFUNCTIONED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 30YM 36032 RATCHETY IN FLIGHT AND CAUSES AFCS TO KICK. 1 G 7 2 4U H4SW 2001091300099 20010913 00099 2001 9 13 HEEA075613 4 20010828 G 3420 1258103 INDICATOR BELL 412 412 1182202 SW HSI INACCURATE E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 5759N 33002 COURSE SET 10 DEGREES OFF. 1 G 7 2 4U H4SW 2001091300100 20010913 00100 2001 9 13 HEEA075614 4 20010828 G 3457 13824120234 RECEIVER BELL 206 206B3 1181506 SW GPS MALFUNCTIONED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 2268V 3605 LOSES ITSELF. PERFORMED PRELIMINARY INSPECTION. COULD NOT DUPLICATE PROBLEM. FOUND NAV, AUX AND ENT BUTTONS VERY INTER MITTENT. REPLACED. FOUND D12 BACKLIGHTING BULB INOPERATIVE. REPLACED. REPAIRED. BENCH CHECK GOOD. 1 G 7 1 3U H2SW 2001091300102 20010913 00102 2001 9 13 HEEA075615 4 20010828 G 3457 13824120234 RECEIVER BELL 206 206L3 1182108 SW GPS MALFUNCTIONED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 129MR 51129 CLEARS ITSELF WHEN TURNED OFF, HAS TO HAVE MGUA CODE ENTERED AND UNABLE TO DISABLE SAFEGUARD. PERFORMED PRELIMINARY INSP ECTION. CLEANED MEMORY AND REPROGRAMMED. ALSO DISABLED SAFEGUARD CODE. REPAIRED. BENCH CHECK GOOD. 1 G 7 1 3U H2SW 2001091300103 20010913 00103 SW 2001 9 13 HEEA075616 1 20010828 G 5302 206031329103S ATTACH FITTING BELL 206 206L3 1182108 SW TAIL BOOM CRACKED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 4835 51131 UPPER LT TAIL BOOM FITTING CRACKED AT MOST FWD OUTBOARD RIVET HOLE. REPLACED WITH SERVICEABLE FITTING. 1 G 7 1 3U H2SW 2001091300104 20010913 00104 SW 2001 9 13 HEEA075617 1 20010828 G 5340 206033109001 FITTING BELL 206 206L3 1182108 SW FUSELAGE WORN E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 42EA 51542 WORN. SCRAPPED AND REPLACED WITH SERVICEABLE FITTING. 1 G 7 1 3U H2SW 2001091300105 20010913 00105 SW 2001 9 13 HEEA075618 1 20010828 G 3213 206053203115 CROSSTUBE BELL 206 206L3 1182108 SW MLG CORRODED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 4835 51131 CORROSION PITS. REPLACED WITH SERVICEABLE CROSSTUBE. 1 G 7 1 3U H2SW 2001091300107 20010913 00107 SW 2001 9 13 HEEA075619 1 20010828 G 6710 206062721109 ACTUATOR BELL 206 206L3 1182108 SW ENGINE INOPERATIVE E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 6160Z 51610 ACTUATOR INOPERATIVE. 1 G 7 1 3U H2SW 2001091300109 20010913 00109 SW 2001 9 13 HEEA075620 1 20010828 G 7810 206064300005 EXHAUST STACK BELL 206 206L3 1182108 SW ENGINE CRACKED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 42EA 51542 EXHAUST STACK CRACKED. REPLACED WITH SERVICEABLE PART. 1 G 7 1 3U H2SW 2001091300110 20010913 00110 SW 2001 9 13 HEEA075621 1 20010828 G 7810 206064300005 EXHAUST STACK BELL 206 206L3 1182108 SW ENGINE CRACKED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 4835 51131 EXHAUST STACK CRACKED. REPLACED WITH SERVICEABLE PART. 1 G 7 1 3U H2SW 2001091300113 20010913 00113 SW 2001 9 13 HEEA075622 1 20010828 G 7910 206064522101 TUBE BELL 206 206L3 1182108 SW OIL SYSTEM MISMANUFACTURED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 8588X 51486 APPROXIMATELY 3/8 INCH TOO SHORT SPANWISE. REPLACED WITH SERVICEABLE PART. 1 G 7 1 3U H2SW 2001091300114 20010913 00114 SW 2001 9 13 HEEA075623 1 20010828 G 2120 206070936001 FLAPPER VALVE BELL 206 206L3 1182108 SW AIR DISTRIBUTION BROKEN E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 6251Y 51556 LEVER ON FLAPPER BROKEN. SCRAPPED AND REPLACED WITH SERVICEABLE PART. 1 G 7 1 3U H2SW 2001091300125 20010913 00125 SW 2001 9 13 HEEA075624 1 20010828 G 2510 206072841111 SEAT BELT BELL 206 206L3 1182108 SW COCKPIT FRAYED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 30KH 51527 FRAYED BELT. SCRAPPED AND REPLACED WITH SERVICEABLE PART. 1 G 7 1 3U H2SW 2001091300127 20010913 00127 SW 2001 9 13 HEEA075625 1 20010828 G 7930 206075187003 INDICATOR BELL 206 206L3 1182108 SW OIL TEMP READS HIGH E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 INDICATOR READS 8 PSI HIGH. 1 G 7 1 3U H2SW 2001091300131 20010913 00131 SW 2001 9 13 HEEA075626 1 20010828 G 2420 206075447007 VOLT REGULATOR BELL 206 206L3 1182108 SW AC SYSTEM MALFUNCTIONED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 4835 51131 GENERATOR FAIL CAUTION LIGHT CAME ON. 1 G 7 1 3U H2SW 2001091300133 20010913 00133 SW 2001 9 13 HEEA075627 1 20010828 G 2420 206075447007 VOLT REGULATOR BELL 206 206L3 1182108 SW AC SYSTEM FAILED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 6161A 51611 GEN FAILED LIGHT ILLUMINATED, GEN WENT OFF LINE WHEN THROTTLE ROLLED DOWN TO IDLE. 1 G 7 1 3U H2SW 2001091300134 20010913 00134 SW 2001 9 13 HEEA075628 1 20010828 G 2420 206075447007 VOLT REGULATOR BELL 206 206L3 1182108 SW AC SYSTEM FAILED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 21497 51518 GENERATOR WILL NOT STAY ON LINE. 1 G 7 1 3U H2SW 2001091300136 20010913 00136 SW 2001 9 13 HEEA075629 1 20010828 G 6420 206075545005 SENSOR BELL 206 206L3 1182108 SW ROTOR RPM FAILED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 3116P 51530 NO SIGNAL SENT TO INDICATOR. REPLACED WITH SERVICEABLE PART. 1 G 7 1 3U H2SW 2001091300139 20010913 00139 2001 9 13 HEEA075630 4 20010828 G 3421 206075606103 GYRO BELL 206 206L3 1182108 SW COCKPIT PRECESSES E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 PRECESSING 10 DEGREES PER MINUTE. 1 G 7 1 3U H2SW 2001091300140 20010913 00140 SW 2001 9 13 HEEA075631 1 20010828 G 7714 206075681101 INDICATOR BELL 206 206L1 1182107 SW DUAL TACH STICKS E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 5019F 45244 TURBINE NEEDLE STICKS DURING START. 1 G 7 1 3U H2SW 2001091300142 20010913 00142 SW 2001 9 13 HEEA075632 1 20010828 G 7714 206075681105 INDICATOR BELL 206 206L3 1182108 SW DUAL TACH FLUCTUATES E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 3116P 51530 FLUCTUATE IN FLIGHT OR GOES TO ZERO. 1 G 7 1 3U H2SW 2001091300143 20010913 00143 SW 2001 9 13 HEEA075633 1 20010828 G 7714 206075681117 INDICATOR BELL 206 206L3 1182108 SW DUAL TACH FAILED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 21497 51518 TURBINE NEEDLE NOT WORKING. 1 G 7 1 3U H2SW 2001091300144 20010913 00144 SW 2001 9 13 HEEA075634 1 20010828 G 7714 206075681123 INDICATOR BELL 206 206L3 1182108 SW DUAL TACH INACCURATE E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 NEEDLES OFF ZERO. 1 G 7 1 3U H2SW 2001091300146 20010913 00146 SW 2001 9 13 HEEA075635 1 20010828 G 7714 206075682107 INDICATOR BELL 206 206L3 1182108 SW GAS PRODUCER ERRATIC E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 4835 51131 INDICATOR VERY ERRATIC AND UNRELIABLE IN THE LOW RANGE DURING STARTS. 1 G 7 1 3U H2SW 2001091300161 20010913 00161 SW 2001 9 13 HEEA075636 1 20010828 G 7712 206075739103 TORQUEMETER BELL 206 206L3 1182108 SW COCKPIT FLUCTUATES E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 42EA 51542 INDICATOR HAS A CONSTANT FLUCTUATION IN CRUISE FLIGHT. REPLACED WITH SERVICEABLE INDICATOR. 1 G 7 1 3U H2SW 2001091300178 20010913 00178 SW 2001 9 13 HEEA075637 1 20010828 G 6321 206076047003 CYLINDER BELL 206 206L1 1182107 SW ROTOR BRAKE FAILED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 5019F 45244 ROTOR BRAKE WILL NOT ENGAGE. REPLACED WITH SERVICEABLE PART. 1 G 7 1 3U H2SW 2001091300179 20010913 00179 SW 2001 9 13 HEEA075638 1 20010828 G 5260 206301109 STEP BELL 206 206L3 1182108 SW FUSELAGE CORRODED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 6748D 51106 CORROSION ON STEP BEYOND LIMITS. SCRAPPED AND REPLACED WITH SERVICEABLE PART. 1 G 7 1 3U H2SW 2001091300181 20010913 00181 SW 2001 9 13 HEEA075639 1 20010828 G 7933 206375007103 INDICATOR BELL 206 206L3 1182108 SW TOT WILL NOT TEST E HEEA K NONE L NO TEST IN INSP/MAINT 1 SW 03 30KH 51527 TOT LIGHT WILL NOT TEST. REPLACED WITH SERVICEABLE PART. 1 G 7 1 3U H2SW 2001091300182 20010913 00182 SW 2001 9 13 HEEA075640 1 20010828 G 5260 206301110 STEP BELL 206 206L3 1182108 SW FUSELAGE CORRODED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 6748D 51106 CORROSION ON STEP BEYOND LIMITS. SCRAPPED AND REPLACED WITH SERVICEABLE PART. 1 G 7 1 3U H2SW 2001091300183 20010913 00183 SW 2001 9 13 HEEA075641 1 20010828 G 7933 206375007103 INDICATOR BELL 206 206L3 1182108 SW TOT INTERMITTENT E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 92MT 51175 TOT INDICATOR NEEDLE INTERMITTENTLY STICKS AT ZERO DURING START. REPLACED WITH SERVICEABLE PART. 1 G 7 1 3U H2SW 2001091300187 20010913 00187 SW 2001 9 13 HEEA075642 1 20010828 G 2844 209062003001 SWITCH BELL 412 412 1182202 SW FUEL SYSTEM MALFUNCTIONED E HEEA O OTHER J WARNING INDICATION NR NOT REPORTED 1 SW 03 6559Z 36019 FLICKERING LIGHT. SCRAPPED AND REPLACED WITH SERVICEABLE PART. 1 G 7 2 4U H4SW 2001091300192 20010913 00192 SW 2001 9 13 HEEA075643 1 20010828 G 7160 209062214001 ACTUATOR BELL 412 412 1182202 SW AIR INTAKE INOPERATIVE E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 108X 33115 ACTUATOR INOPERATIVE. 1 G 7 2 4U H4SW 2001091300193 20010913 00193 SW 2001 9 13 HEEA075644 1 20010828 G 7922 209070262101 REGULATOR BELL 412 412 1182202 SW OIL TEMP MALFUNCTIONED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 NOT MARKING PROPERLY. 1 G 7 2 4U H4SW 2001091300194 20010913 00194 SW 2001 9 13 HEEA075645 1 20010828 G 7933 209070262101 INDICATOR BELL 412 412 1182202 SW ENGINE OIL READS HIGH E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 142PH 33150 READS 30 PSI HIGH. REPLACED WITH SERVICEABLE PART. 1 G 7 2 4U H4SW 2001091300195 20010913 00195 SW 2001 9 13 HEEA075646 1 20010828 G 7931 209070262101 INDICATOR BELL 412 412 1182202 SW ENGINE OIL READS LOW E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 142PH 33150 READS 5 PSI LOW. REPLACED WITH SERVICEABLE PART. 1 G 7 2 4U H4SW 2001091300196 20010913 00196 SW 2001 9 13 HEEA075647 1 20010828 G 2912 2111328 FILTER ELEMENT BELL 206 206L1 1182107 SW HYD SYSTEM BYPASSING E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 5019F 45244 BYPASS INDICATOR EXTENDED. REPLACED WITH SERVICEABLE PART. 1 G 7 1 3U H2SW 2001091300197 20010913 00197 SW 2001 9 13 HEEA075648 1 20010828 G 2912 2111328 FILTER ELEMENT BELL 206 206L4 1182110 SW HYD SYSTEM BYPASSING E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 7074W 52033 BYPASS BUTTON POPPED. REPLACED WITH SERVICEABLE PART. 1 G 7 1 3U NC H2SW 2001091300198 20010913 00198 SW 2001 9 13 HEEA075649 1 20010828 G 7120 212060718001 BEARING BELL 412 412 1182202 SW ENGINE MOUNT WORN E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 2148K 36001 WORN BEARING. SCRAPPED AND REPLACED WITH SERVICEABLE PART. 1 G 7 2 4U H4SW 2001091300199 20010913 00199 SW 2001 9 13 HEEA075650 1 20010828 G 8011 214060056705 STARTER BELL 214 214ST 1182106 SW ENGINE FAILED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 CLUTCH SLIPPAGE, OUT OF LIMITS AND STICKING 2 G 7 2 4U H10SW 2001091300200 20010913 00200 SW 2001 9 13 HEEA075651 1 20010829 G 3212 206050247135 COVER BELL 407 407 SW FLOAT BAG DETERIORATED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 57416 53070 DETERIORATED. SCRAPPED IN HOUSE. PHI REQUESTS FOR CREDIT AGAINST REPLACEMENT PART PURCHASED. REFERENCE: DMR#68645101. 1 G 7 1 3U O H2SW 2001091300218 20010913 00218 SW 2001 9 13 HEEA075653 1 20010831 G 6220 206011149105 YOKE BELL 206 206L3 1182108 SW MAIN ROTOR HEAD SPALLED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 SPAULDING ON OUTBOARD JOURNAL, SCUFFING ON INBOARD JOURNAL AND CORROSION ON RETAINER BORE. SENT TO BELL HELICOPTER TEXTR ON FOR WARRANTY REPAIR. REFERENCE: DMR#727503. 1 G 7 1 3U H2SW 2001091300220 20010913 00220 SW 2001 9 13 HEEA075654 1 20010831 G 8011 214060056103 STARTER BELL 214 214ST 1182106 SW ENGINE FAILED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 BURNED AND WON'T CROSS START. 2 G 7 2 4U H10SW 2001091300221 20010913 00221 EU 2001 9 13 HEEA075655 1 20010821 G 6320 4638302002 PINION GEAR 4638001004 BOLKMS 105 BO105S 5626006 EU M/R GEARBOX SPALLED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 911HM 226 S683 GEAR TEETH SPALLING AT TOOTH TIP. REPLACED WITH SERVICEABLE PART. 1 G 7 2 3U H3EU 2001091300223 20010913 00223 EU 2001 9 13 HEEA075656 1 20010821 G 6320 4638303001 BEVEL GEAR 4638001004 BOLKMS 105 BO105S 5626006 EU M/R GEARBOX SPALLED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 911HM 226 S683 GEAR TEETH SPALLING AT TOOTH ROOT. REPLACED WITH SERVICEABLE PART. 1 G 7 2 3U H3EU 2001091300224 20010913 00224 2001 9 13 HEEA075657 4 20010824 G 2350 066105571 AUDIO PANEL BOLKMS 105 BO105S 5626006 EU COCKPIT INOPERATIVE E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 81982 S818 ICS INOPERATIVE. PERFORMED PRELIMINARY INSPECTION. FOUND SWITCH S211 BAD AND SWITCHES S201 THROUGH 210 NOISY. REPLACED SWITCH S211 AND CLEANED SWITCHES S201 THROUGH 210 WITH MISTY CONTACT CLEANER. REPAIRED. BENCH CHECK GOOD. 1 G 7 2 3U H3EU 2001091300244 20010913 00244 EU 2001 9 13 HEEA075658 1 20010824 G 2435 150SG122Q STARTER GEN SNIAS 350 AS350B2 8680813 EU ELECTRICAL FAILED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 40466 345 3004 WOULD NOT START OR GENERATE POWER. 1 G 7 1 3U H9EU 2001091300245 20010913 00245 EU 2001 9 13 HEEA075659 1 20010824 G 6410 355A12004008 BLADE SNIAS 350 AS350B2 8680813 EU TAIL ROTOR CRACKED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 4000L 3850 2873 TAIL ROTOR BLADE HAS A CRACKED SPAR. 1 G 7 1 3U H9EU 2001091300248 20010913 00248 2001 9 13 HEEA075660 4 20010827 G 2312 071121540 CONTROL PANEL BOLKMS 105 BO105S 5626006 EU VHF COMMS FAILED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 4302G S853 DISPLAY UNREADABLE. PERFORMED PRELIMINARY INSPECTION. FOUND DISPLAY SEGMENTS UNREADABLE. FOUND CORROSION UNDER J203 HE ADER CAUSING PROBLEM. REMOVED HEADER AND REMOVED CORROSION. REPLACED J203 HEADER AND APPLIED HUMISEAL AROUND HEADER FO R CORROSION CONTROL. REPAIRED DISPLAY PROBLEM. FOUND TRANSFER SWITCH INTERMITTENT. CLEANED S102 TRANSFER SWITCH. REP AIRED AND BENCH CHECK GOOD. 1 G 7 2 3U H3EU 2001091300249 20010913 00249 EU 2001 9 13 HEEA075661 1 20010828 G 7933 10590947 INDICATOR BOLKMS 105 BO105S 5626006 EU TOT INCORRECT E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 COULD NOT REMOVE ERRORS. OFF AT EACH END OF SCALE. 1 G 7 2 3U H3EU 2001091300251 20010913 00251 EU 2001 9 13 HEEA075662 1 20010828 G 5510 11730550 STRUCTURE BOLKMS 117 BK117A1 5626010 EU HORIZONTAL STAB DEBONDED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 911TL 7198 PAINT PEELED AND TRAILING EDGE DEBONDED. 1 G 7 2 3U H13EU 2001091300252 20010913 00252 EU 2001 9 13 HEEA075663 1 20010828 G 5510 11730550 STRUCTURE BOLKMS 117 BK117A1 5626010 EU HORIZONTAL STAB DETERIORATED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 911RZ 7092 PAINT DETERIORATED, STRIP. METAL TRAILING EDGE ALODINED AND PRIMED. RIGHT DEVORE FLOODLIGHT INSERT LOOSE. 1 G 7 2 3U H13EU 2001100100093 20011001 00093 2001 10 1 HEEA075926 4 20010910 G 3416 066303102 ALTIMETER COCKPIT DAMAGED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 PARTS LOOSE INSIDE. SENT TO FIELDTECH AVIONICS, INC. FOR WARRANTY REPAIR. 2001100200063 20011002 00063 GL 2001 10 2 HEEA075927 2 20010910 G 7323 252469211 GOVERNOR SKRSKY S76 S76A 8143006 NE ALLSN 250C 250C30S 03013 GL ENGINE FAILED E HEEA O OTHER J WARNING INDICATION NR NOT REPORTED 1 SW 03 5435V 760158 CAE890469S ENGINE N2, T5, FUEL FLOW AND N1 ALL BLEED OFF PRIOR TO REACHING ENGINE LIMITING CHECK PARAMETERS. REPLACED WITH SERVICEA BLE PART. 1 G 7 2 3U 3 U H1NE E1GL 2001100200066 20011002 00066 GL 2001 10 2 HEEA075928 2 20010918 G 7250 23062753 NOZZLE BELL 206 206B3 1181506 SW ALLSN 250C 250C20B 03013 GL TURBINE VANE BURNED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 2270G 3610 CAE835824 BOLT BROKEN OFF IN NR 6 & 7 JET MOUNT. NR 1 NOZZLE VANES BURNED BEYOND REPAIRABLE LIMITS. OVERTEMP INSPECTION CW 2-23- 00 FOR A 930 DEGREE EXCEEDANCE AND FOUND ACCEPTABLE. PART SCRAPPED. REPLACED WITH SERVICEABLE PART. 1 G 7 1 3U 3 U H2SW E4CE 2001100200068 20011002 00068 GL 2001 10 2 HEEA075929 2 20010918 G 7250 6886407 TURBINE WHEEL BELL 206 206B3 1181506 SW ALLSN 250C 250C20B 03013 GL TURBINE SECTION DAMAGED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 2270G 808 3610 CAE835824 BOLT BROKEN OFF IN #6&7 JET MOUNT. WHEEL BLADES SULPHIDATED DUE TO OVERTEMP OF 930 DEGREES ON 2-23-00. PARTS WERE FOUN D TO BE ACCEPTABLE WHEN INSPECTED FOR OVERTEMP. PART SCRAPPED. REPLACED WITH SERVICEABLE PART. 1 G 7 1 3U 3 U H2SW E4CE 2001100200069 20011002 00069 GL 2001 10 2 HEEA075930 2 20010918 G 7250 6898782 TURBINE WHEEL BELL 206 206B3 1181506 SW ALLSN 250C 250C20B 03013 GL ENGINE DAMAGED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 2270G 808 3610 CAE835824 BOLT BROKEN OFF IN 6&7 JET MOUNT. WHEEL BLADES SULPHIDATED DUE TO OVERTEMP OF 930 DEGREES ON 2-23-00. PARTS WERE FOUND TO BE ACCEPTABLE WHEN INSPECTED FOR OVERTEMP. PART SCRAPPED. REPLACED WITH SERVICEABLE PART. 1 G 7 1 3U 3 U H2SW E4CE 2001100200071 20011002 00071 NE 2001 10 2 HEEA075931 1 20010924 G 7500 650852201 VALVE SKRSKY S76 S76A 8143006 NE NR 1 ENGINE MALFUNCTIONED E HEEA A UNSCHED LANDING R J PARTIAL RPM/PWR LOSS WARNING INDICATION HO HOVERING 1 SW 03 760PH 760078 WHEN ATTEMPTING TO DEPART, A LARGE TORQUE SPLIT OCCURRED WHEN ATTEMPTING TO PICK UP INTO A HOVER. INSPECTION OF NR 1 EN GINE BY PILOT REVEALED THE PC SAFETY VALVE PARTIALLY CLOSED. PILOT OPENED VALVE AND COMPLIED WITH POWER CHECK AND FOUND NORMAL. MAINTENANCE INSPECTED VALVE AND ENGINE. RELEASED AIRCRAFT FOR SERVICE. 1 G 7 2 3U H1NE 2001100200072 20011002 00072 SW 2001 10 2 HEEA075933 1 20010910 G 2824 205060606003 PUMP BELL 412 412 1182202 SW FUEL TRANFER INOPERATIVE E HEEA A UNSCHED LANDING J WARNING INDICATION CR CRUISE 1 SW 03 2149S 36002 WHILE IN CRUISE FLIGHT, NR 2 TRANSFER LIGHT ILLUMINATED. REPLACED INOPERATIVE NR 2 TRANSFER PUMP. 1 G 7 2 4U H4SW 2001100200075 20011002 00075 2001 10 2 HEEA075934 4 20010910 G 2312 064101902 TRANSCEIVER BELL 206 206L1 1182107 SW COCKPIT FAILED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 5007N 45184 FIRST START OF THE DAY UNIT WOULD NOT TRANSMIT. REPLACED WITH SERVICEABLE PART. 1 G 7 1 3U H2SW 2001100200076 20011002 00076 2001 10 2 HEEA075935 4 20010910 G 2312 066106200 TRANSCEIVER BELL 206 206L1 1182107 SW COCKPIT FAILED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 5019F 45244 NO INDICATED OUTPUT. SCRAPPED AND REPLACED WITH SERVICEABLE PART. 1 G 7 1 3U H2SW 2001100200077 20011002 00077 GL 2001 10 2 HEEA075936 2 20010910 G 7412 103815504 EXCITER BELL 412 412 1182202 SW ALLSN 250B 250B* GL ENGINE FAILED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 2258F 33073 CAUSING THE CIRCUIT BREAKER TO POP. 1 G 7 2 4U 3 T H4SW E10CE 2001100200089 20011002 00089 SW 2001 10 2 HEEA075938 1 20010910 G 6330 206033554101 LINK BELL 206 206L4 1182110 SW MAIN ROTOR DAMAGED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 7074W 52033 ELASTOMERIC PURGING OUT OF MOUNT. 1 G 7 1 3U NC H2SW 2001100200090 20011002 00090 SW 2001 10 2 HEEA075939 1 20010910 G 7714 206075682107 INDICATOR BELL 206 206L3 1182108 SW GAS PRODUCER ERRATIC E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 6251X 51552 ERRATIC BETWEEN 0-15 DEGREES. 1 G 7 1 3U H2SW 2001100200091 20011002 00091 SW 2001 10 2 HEEA075941 1 20010910 G 6510 212040600005 HANGER ASSY BELL 412 412 1182202 SW TAIL ROTOR LEAKING E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 107X 33113 COUPLING LEAKING GREASE. REPLACED WITH SERVICEABLE PART. 1 G 7 2 4U H4SW 2001100200093 20011002 00093 SW 2001 10 2 HEEA075942 1 20010910 G 7722 212075067105 INDICATOR BELL 412 412 1182202 SW ITT FLUCTUATES E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 5759N 33002 FLUCTUATING AT HIGH TEMPERATURES. REPLACED WITH SERVICEABLE PART. 1 G 7 2 4U H4SW 2001100200094 20011002 00094 SW 2001 10 2 HEEA075943 1 20010910 G 6730 212076005111 SERVO BELL 412 412 1182202 SW ROTOR LEAKING E HEEA K NONE K FLUID LOSS IN INSP/MAINT 1 SW 03 2149S 36002 TOP PILOT VALVES LEAK WHEN THE AIRCRAFT IS STATIC, NOT RUNNING. NO LEAKS WHEN AIRCRAFT RUNS IS A STATIC LEAK ONLY. REPL ACED WITH SERVICEABLE PART. 1 G 7 2 4U H4SW 2001100200095 20011002 00095 SW 2001 10 2 HEEA075944 1 20010910 G 2820 214066226103 CHECK VALVE BELL 412 412 1182202 SW INTERMITTENT E HEEA K NONE N FALSE WARNING IN INSP/MAINT 1 SW 03 2148K 36001 INTERMITTENT LIGHT. SCRAPPED AND REPLACED WITH SERVICEABLE PART. 1 G 7 2 4U H4SW 2001100200097 20011002 00097 2001 10 2 HEEA075945 4 20010910 G 2200 2593996333 TARSYN BELL 212 212 1181420 SW COCKPIT MALFUNCTIONED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 5736D 31135 PILOTS ADI BEGAN TUMBLING IN LEVEL FLIGHT. REPLACED WITH SERVICEABLE PART. 1 G 7 1 4U H4SW 2001100200098 20011002 00098 SW 2001 10 2 HEEA075946 1 20010910 G 2432 32007001 BATTERY BELL 206 206L3 1182108 SW MAIN DISCHARGED E HEEA K NONE L NO TEST IN INSP/MAINT 1 SW 03 31077 51520 WEAK BATTERY. REPLACED WITH SERVICEABLE PART. 1 G 7 1 3U H2SW 2001100200099 20011002 00099 GL 2001 10 2 HEEA075947 2 20010910 G 7320 324473513 FUEL CONTROL BELL 412 412 1182202 SW ALLSN 250B 250B* GL ENGINE OUT OF ADJ E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 3893L 33006 NO TOPPING ADJUSTMENT LEFT. REPLACED WITH SERVICEABLE PART. 1 G 7 2 4U 3 T H4SW E10CE 2001100200100 20011002 00100 SW 2001 10 2 HEEA075948 1 20010910 G 6220 412010182101 BEARING BELL 412 412 1182202 SW MAIN ROTOR WORN E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 107X 33113 WORN BEARING. SCRAPPED AND REPLACED WITH SERVICEABLE PART. 1 G 7 2 4U H4SW 2001100200102 20011002 00102 SW 2001 10 2 HEEA075949 1 20010910 G 6230 412010405109 LINK BELL 412 412 1182202 SW MAIN ROTOR WORN E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 5759N 33002 WORN BEARING. REPLACED WITH SERVICEABLE PART. 1 G 7 2 4U H4SW 2001100200103 20011002 00103 SW 2001 10 2 HEEA075950 1 20010910 G 6230 412010406115 LINK BELL 412 412 1182202 SW MAIN ROTOR WORN E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 2149S 36002 WORN BEARING. REPLACED WITH SERVICEABLE PART. 1 G 7 2 4U H4SW 2001100200104 20011002 00104 SW 2001 10 2 HEEA075951 1 20010910 G 6230 412010406115 LINK BELL 412 412 1182202 SW MAIN ROTOR WORN E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 2149S 36002 WORN BEARING. REPLACED WITH SERVICEABLE PART. 1 G 7 2 4U H4SW 2001100200105 20011002 00105 SW 2001 10 2 HEEA075952 1 20010910 G 6210 412015300109 BLADE BELL 412 412 1182202 SW MAIN ROTOR CRACKED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 142PH 33150 LARGE CRACK BY MID TRIM TAB. REPLACED WITH SERVICEABLE PART. 1 G 7 2 4U H4SW 2001100200106 20011002 00106 SW 2001 10 2 HEEA075953 1 20010910 G 3213 412050016102 SHOE BELL 412 412 1182202 SW MLG WORN E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 5759N 33002 WORN. REPLACED WITH SERVICEABLE PART. 1 G 7 2 4U H4SW 2001100200107 20011002 00107 SW 2001 10 2 HEEA075954 1 20010910 G 6710 412310400101 ROD END BELL 412 412 1182202 SW MAIN ROTOR WORN E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 2149S 36002 WORN. REPLACED WITH SERVICEABLE PART. 1 G 7 2 4U H4SW 2001100200110 20011002 00110 2001 10 2 HEEA075955 4 20010910 G 3421 50400179015 INDICATOR BELL 206 206L1 1182107 SW COCKPIT PRECESSES E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 5007Q 45187 WILL NOT CAGE AND PRECESSES. REPLACED WITH SERVICEABLE PART. 1 G 7 1 3U H2SW 2001100200111 20011002 00111 2001 10 2 HEEA075956 4 20010910 G 3457 8143902240B GPS BELL 412 412 1182202 SW COCKPIT FAILED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 33008 36004 RAIM UNAVAILABLE. 1 G 7 2 4U H4SW 2001100200112 20011002 00112 2001 10 2 HEEA075957 4 20010910 G 3416 8800T ENCODER BELL 412 412 1182202 SW COCKPIT FAILED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 2148K 36001 GPS DISPLAYS EXTERNAL ALTIMETER LOST COMMUNICATIONS MESSAGE. REPLACED WITH SERVICEABLE PART. 1 G 7 2 4U H4SW 2001100200114 20011002 00114 SW 2001 10 2 HEEA075958 1 20010910 G 7740 DPUA0101 COMPUTER BELL 206 206L3 1182108 SW COCKPIT MALFUNCTIONED E K NONE O OTHER IN INSP/MAINT 1 SW 03 41791 51465 INTELLISTART LIGHT STAYS ON, COULDN'T ACCESS WITH MLP. SENT TO ALTAIR AVIONICS CORP. FOR INSPECTION AND REPAIR. 1 G 7 1 3U H2SW 2001100200115 20011002 00115 SW 2001 10 2 HEEA075959 1 20010910 G 6520 PHI2062003 SEAL BELL 206 206L3 1182108 SW T/R GEARBOX LEAKING E HEEA K NONE K FLUID LOSS IN INSP/MAINT 1 SW 03 30KH 51527 SEAL LEAKING. REPLACED WITH SERVICEABLE PART. 1 G 7 1 3U H2SW 2001100200117 20011002 00117 2001 10 2 HEEA075960 4 20010910 G 3400 212075399101 INDICATOR BELL 212 212 1181420 SW COCKPIT FAILED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 WILL NOT REFLECT AN INDICATION. SENT TO BELL HELICOPTER TEXTRON FOR CREDIT. 1 G 7 1 4U H4SW 2001100200118 20011002 00118 SW 2001 10 2 HEEA075961 1 20010910 G 5302 206031329103S ATTACH FITTING BELL 206 206L3 1182108 SW TAILBOOM MISMANUFACTURED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 FITTING WILL NOT SIT FLAT AGAINST TAILBOOM RING. FITTING IS NOT MACHINED FLAT AND HAS A SLIGHTLY ROUNDED CONTOUR SO THE RE IS A GAP AROUND THE PERIMETER OF THE FACE OF THE FITTING. ALSO FOUND FITTING TO BE APPROXIMATELY .30 THICKER AT THE TAILBOOM ATTACH BOLT HOLE. SENT TO BELL HELICOPTER TEXTRON FOR CREDIT. 1 G 7 1 3U H2SW 2001100300009 20011003 00009 SW 2001 10 3 HEEA075971 1 20010913 G 5302 407030801105 SKIN BELL 407 407 SW TAILBOOM CRACKED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 4999 2516 53323 CRACK IN SKIN ON LEFT HAND SIDE. SENT TO BELL HELICOPTER TEXTRON FOR CREDIT AGAINST REPLACEMENT PART PURCHASED. REFEREN CE: DMR#720464. 1 G 7 1 3U O H2SW 2001100300010 20011003 00010 SW 2001 10 3 HEEA075972 1 20010913 G 6210 407015001117 BLADE BELL 407 407 SW MAIN ROTOR DELAMINATED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 405PH 3683 53207 DELAMINATION NEAR BLADE TIP. 1 G 7 1 3U O H2SW 2001100300011 20011003 00011 SW 2001 10 3 HEEA075974 1 20010913 G 6230 406010401117 SWASHPLATE BELL 407 407 SW MAIN ROTOR LEAKING E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 724PH 1368 53327 GREASE DISCOLORED AND LEAKING. 1 G 7 1 3U O H2SW 2001100300012 20011003 00012 SW 2001 10 3 HEEA075975 1 20010913 G 3246 407050202101 CROSSTUBE BELL 407 407 SW MLG CORRODED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 409PH 53059 CORROSION AT CHAFE PADS. SENT IN FOR EVALUATION DUE TO PREVIOUS MANUFACTURE DEFECTS. 1 G 7 1 3U O H2SW 2001100300016 20011003 00016 SW 2001 10 3 HEEA075977 1 20010913 G 2700 412301300101 ACTUATOR BELL 412 412EP 1182205 SW FLIGHT CONTROLS STUCK E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 6106C 36257 STICKING INTERMITTENTLY IN FLIGHT. 1 G 7 2 4U H4SW 2001100300017 20011003 00017 SW 2001 10 3 HEEA075978 1 20010914 G 6710 406310404101 ROD END BELL 407 407 SW MAIN ROTOR WORN E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 404PH 3352 53188 ROD END WORN. 1 G 7 1 3U O H2SW 2001100300018 20011003 00018 SW 2001 10 3 HEEA075980 1 20010914 G 6710 406310405101 UNIVERSAL JOINT BELL 407 407 SW MAIN ROTOR WORN E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 723PH 923 53283 UNIVERSAL WORN. 1 G 7 1 3U O H2SW 2001100300019 20011003 00019 SW 2001 10 3 HEEA075981 1 20010914 G 6310 214040814105 SLEEVE BELL 407 407 SW TRANSMISSION WORN E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 724PH 53327 WORN. SENT TO BELL HELICOPTER TEXTRON FOR CREDIT AGAINST REPLACEMENT PART PURCHASED. REFERENCE: DMR#720445. 1 G 7 1 3U O H2SW 2001100300022 20011003 00022 SW 2001 10 3 HEEA075987 1 20010914 G 6510 407340340103 DISC PACK BELL 407 407 SW MAIN ROTOR CRACKED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 499PH 53400 DISC PACK CRACKED. 1 G 7 1 3U O H2SW 2001100300023 20011003 00023 SW 2001 10 3 HEEA075988 1 20010914 G 6710 406310405101 UNIVERSAL JOINT BELL 407 407 SW MAIN ROTOR WORN E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 720PH 1442 53277 WORN BEYOND LIMITS. SENT TO BELL HELICOPTER TEXTRON FOR CREDIT AGAINST REPLACEMENT PART PURCHASED. REFERENCE: DMR#7190 8903. 1 G 7 1 3U O H2SW 2001100300025 20011003 00025 SW 2001 10 3 HEEA075989 1 20010914 G 2840 407362005103 SWITCH BELL 407 407 SW FUEL INDICATOR FAILED E HEEA O OTHER N FALSE WARNING NR NOT REPORTED 1 SW 03 498PH 53399 LOW LEVEL ANNUNCIATOR LIGHT WOULD NOT GO OUT. 1 G 7 1 3U O H2SW 2001100300042 20011003 00042 SW 2001 10 3 HEEA075990 1 20010914 G 6510 406001704101 BELLCRANK BELL 407 407 SW TAIL ROTOR CHAFED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 4999 53323 CHAFED FROM CONTROL TUBE. 1 G 7 1 3U O H2SW 2001100300053 20011003 00053 SW 2001 10 3 HEEA075993 1 20010914 G 2910 FITTING BELL 407 407 SW HYD HOSE BROKEN E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 719PH 53266 FITTING BROKE OFF IN HOSE END, CANNOT REMOVE. 1 G 7 1 3U O H2SW 2001100300054 20011003 00054 SW 2001 10 3 HEEA075994 1 20010914 G 6710 406310405101 UNIVERSAL JOINT BELL 407 407 SW MAIN ROTOR WORN E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 406PH 767 53198 WEAR BEYOND ALLOWABLE LIMITS. 1 G 7 1 3U O H2SW 2001100300055 20011003 00055 SW 2001 10 3 HEEA075995 1 20010914 G 2910 B-NUT BELL 407 407 SW HYD SYSTEM DAMAGED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 740PH 729 53435 B NUT THREADS ARE UNDERCUT AND WILL NOT TIGHTEN. 1 G 7 1 3U O H2SW 2001100300056 20011003 00056 SW 2001 10 3 HEEA075996 1 20010914 G 6710 406310405101 UNIVERSAL JOINT BELL 407 407 SW MAIN ROTOR WORN E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 457PH 2509 53147 WORN BEARING. 1 G 7 1 3U O H2SW 2001100300057 20011003 00057 SW 2001 10 3 HEEA075997 1 20010914 G 6710 406310405101 UNIVERSAL JOINT BELL 407 407 SW MAIN ROTOR WORN E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 8595X 53267 WORN BEARING. 1 G 7 1 3U O H2SW 2001100300059 20011003 00059 SW 2001 10 3 HEEA075998 1 20010914 G 6710 406010425107 LEVER BELL 407 407 SW MAIN ROTOR WORN E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 494PH 1848 53396 WORN BUSHINGS. 1 G 7 1 3U O H2SW 2001100300060 20011003 00060 SW 2001 10 3 HEEA075999 1 20010914 G 6710 406010425107 LEVER BELL 407 407 SW MAIN ROTOR WORN E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 494PH 1848 53396 WORN BUSHINGS. 1 G 7 1 3U O H2SW 2001100300061 20011003 00061 SW 2001 10 3 HEEA076000 1 20010914 G 5320 407070620125 PANEL BELL 407 407 SW COLLECTIVE CRACKED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 496PH 53398 PANEL CRACKED. 1 G 7 1 3U O H2SW 2001100300062 20011003 00062 SW 2001 10 3 HEEA076001 1 20010914 G 6710 406310405101 UNIVERSAL JOINT BELL 407 407 SW MAIN ROTOR DAMAGED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 495PH 1139 53397 BEARING UNSTAKED. 1 G 7 1 3U O H2SW 2001100300063 20011003 00063 SW 2001 10 3 HEEA076006 1 20010914 G 6510 407340340103 DISC PACK BELL 407 407 SW TAIL ROTOR CRACKED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 499PH 53400 CRACKED. SCRAPPED IN HOUSE. 1 G 7 1 3U O H2SW 2001100300070 20011003 00070 SW 2001 10 3 HEEA076007 1 20010914 G 6510 407340340101 DISC PACK BELL 407 407 SW TAIL ROTOR CRACKED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 402PH 53159 CRACKED. SCRAPPED IN HOUSE. 1 G 7 1 3U O H2SW 2001100300073 20011003 00073 SW 2001 10 3 HEEA076008 1 20010914 G 6510 407340340101 DISC PACK BELL 407 407 SW TAIL ROTOR CRACKED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 722PH 53288 CRACKED. SCRAPPED IN HOUSE. 1 G 7 1 3U O H2SW 2001100300074 20011003 00074 SW 2001 10 3 HEEA076009 1 20010914 G 6310 204040760109 FILTER ELEMENT BELL 407 407 SW TRANSMISSION FAILED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 495PH 53397 RUN IN AFTER TRANS CHANGE. SCRAPPED IN HOUSE. 1 G 7 1 3U O H2SW 2001100300076 20011003 00076 SW 2001 10 3 HEEA076012 1 20010914 G 7170 70031A202000 LINE BELL 407 407 SW EXH DRAIN CHAFED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 407PH 53003 DRAIN LINE WAS WORN THROUGH STEEL BRAIDING. SCRAPPED IN HOUSE. 1 G 7 1 3U O H2SW 2001100300078 20011003 00078 SW 2001 10 3 HEEA076016 1 20010917 G 6710 214001347005 ACTUATOR BELL 214 214ST 1182106 SW AUTOFLIGHT SYS STUCK E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 ROTARY ACTUATOR STICKING. 2 G 7 2 4U H10SW 2001100300079 20011003 00079 SW 2001 10 3 HEEA076017 1 20010917 G 5260 212075418105 ACTUATOR BELL 412 412 1182202 SW STEP FROZEN E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 ACTUATOR MOTOR FROZEN. 1 G 7 2 4U H4SW 2001100300081 20011003 00081 SW 2001 10 3 HEEA076018 1 20010917 G 2840 473203003 SIGNAL COND UNIT BELL 412 412 1182202 SW FUEL SYSTEM OUT OF ADJ E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 COULD NOT ADJUST E TO -.03PF WHEN CALIBRATING NR 1 FUEL SYSTEM. 1 G 7 2 4U H4SW 2001100300083 20011003 00083 SW 2001 10 3 HEEA076019 1 20010919 G 2432 RG214 BATTERY BELL 214 214ST 1182106 SW MAIN DISCHARGED E HEEA K NONE L NO TEST IN INSP/MAINT 1 SW 03 8045T 233 28101 WEAK. WOULD NOT TAKE A CHARGE. 2 G 7 2 4U H10SW 2001100300084 20011003 00084 SW 2001 10 3 HEEA076020 1 20010919 G 2432 RG214 BATTERY BELL 214 214ST 1182106 SW MAIN DISCHARGED E HEEA K NONE L NO TEST IN INSP/MAINT 1 SW 03 8045T 233 28101 WEAK. WOULD NOT TAKE A CHARGE. 2 G 7 2 4U H10SW 2001100300085 20011003 00085 SW 2001 10 3 HEEA076021 1 20010919 G 2432 RG214 BATTERY BELL 214 214ST 1182106 SW MAIN DISCHARGED E HEEA K NONE L NO TEST IN INSP/MAINT 1 SW 03 59806 487 28140 WEAK. 2 G 7 2 4U H10SW 2001100300086 20011003 00086 SW 2001 10 3 HEEA076022 1 20010919 G 2432 RG214 BATTERY BELL 214 214ST 1182106 SW MAIN DISCHARGED E HEEA K NONE L NO TEST IN INSP/MAINT 1 SW 03 59806 473 28140 WON'T START AIRCRAFT. 2 G 7 2 4U H10SW 2001100300087 20011003 00087 SW 2001 10 3 HEEA076023 1 20010919 G 2432 RG214 BATTERY BELL 214 214ST 1182106 SW MAIN DISCHARGED E HEEA K NONE L NO TEST IN INSP/MAINT 1 SW 03 5748M 465 28102 WEAK. 2 G 7 2 4U H10SW 2001100300089 20011003 00089 SW 2001 10 3 HEEA076024 1 20010919 G 2432 RG214 BATTERY BELL 214 214ST 1182106 SW MAIN DISCHARGED E HEEA K NONE L NO TEST IN INSP/MAINT 1 SW 03 5748M 465 28102 WEAK. 2 G 7 2 4U H10SW 2001100300090 20011003 00090 SW 2001 10 3 HEEA076025 1 20010919 G 2432 RG214 BATTERY BELL 214 214ST 1182106 SW MAIN DISCHARGED E HEEA K NONE L NO TEST IN INSP/MAINT 1 SW 03 3897N 902 28106 WEAK. 2 G 7 2 4U H10SW 2001100300092 20011003 00092 SW 2001 10 3 HEEA076026 1 20010919 G 2432 RG214 BATTERY BELL 214 214ST 1182106 SW MAIN DISCHARGED E HEEA K NONE L NO TEST IN INSP/MAINT 1 SW 03 59806 911 28140 WON'T START AIRCRAFT. 2 G 7 2 4U H10SW 2001100300094 20011003 00094 SW 2001 10 3 HEEA076027 1 20010919 G 2432 RG214 BATTERY BELL 214 214ST 1182106 SW MAIN DISCHARGED E HEEA K NONE L NO TEST IN INSP/MAINT 1 SW 03 3897N 380 28106 WEAK. 2 G 7 2 4U H10SW 2001100300095 20011003 00095 SW 2001 10 3 HEEA076028 1 20010919 G 2432 RG214 BATTERY BELL 214 214ST 1182106 SW MAIN SHORTED E HEEA K NONE L NO TEST IN INSP/MAINT 1 SW 03 3897N 380 28106 WEAK. FOUND UNIT INTERNALLY SHORTED. 2 G 7 2 4U H10SW 2001100300097 20011003 00097 SW 2001 10 3 HEEA076029 1 20010919 G 2432 RG214 BATTERY BELL 214 214ST 1182106 SW MAIN DISCHARGED E HEEA K NONE L NO TEST IN INSP/MAINT 1 SW 03 6957Y 89 28139 WEAK. 2 G 7 2 4U H10SW 2001100300098 20011003 00098 SW 2001 10 3 HEEA076030 1 20010919 G 2432 RG214 BATTERY BELL 214 214ST 1182106 SW MAIN DISCHARGED E HEEA K NONE L NO TEST IN INSP/MAINT 1 SW 03 6957Y 89 28139 WEAK. 2 G 7 2 4U H10SW 2001100300099 20011003 00099 SW 2001 10 3 HEEA076031 1 20010919 G 2432 RG214 BATTERY BELL 214 214ST 1182106 SW MAIN DISCHARGED E HEEA K NONE L NO TEST IN INSP/MAINT 1 SW 03 8045T 28101 WEAK. 2 G 7 2 4U H10SW 2001100300100 20011003 00100 SW 2001 10 3 HEEA076032 1 20010919 G 2432 RG214 BATTERY BELL 214 214ST 1182106 SW MAIN DISCHARGED E HEEA K NONE L NO TEST IN INSP/MAINT 1 SW 03 8045T 28101 WEAK. 2 G 7 2 4U H10SW 2001100300101 20011003 00101 SW 2001 10 3 HEEA076033 1 20010919 G 2432 RG214 BATTERY BELL 214 214ST 1182106 SW MAIN DISCHARGED E HEEA K NONE L NO TEST IN INSP/MAINT 1 SW 03 6957Y 253 28139 WON'T HOLD A CHARGE. 2 G 7 2 4U H10SW 2001100300102 20011003 00102 SW 2001 10 3 HEEA076034 1 20010919 G 2432 RG214 BATTERY BELL 214 214ST 1182106 SW MAIN DISCHARGED E HEEA K NONE L NO TEST IN INSP/MAINT 1 SW 03 59806 742 28140 WON'T START AIRCRAFT. SCRAPPED. 2 G 7 2 4U H10SW 2001100400005 20011004 00005 SW 2001 10 4 HEEA076035 1 20010919 G 2432 RG214 BATTERY BELL 214 214ST 1182106 SW MAIN DISCHARGED E HEEA K NONE L NO TEST IN INSP/MAINT 1 SW 03 3897N 226 28106 WEAK. 2 G 7 2 4U H10SW 2001100400006 20011004 00006 SW 2001 10 4 HEEA076036 1 20010919 G 2432 RG214 BATTERY BELL 214 214ST 1182106 SW MAIN DISCHARGED E HEEA K NONE L NO TEST IN INSP/MAINT 1 SW 03 59806 372 28140 WEAK. 2 G 7 2 4U H10SW 2001100400007 20011004 00007 SW 2001 10 4 HEEA076037 1 20010919 G 2432 RG214 BATTERY BELL 214 214ST 1182106 SW MAIN OVERHEATED E HEEA K NONE M L OVER TEMP NO TEST IN INSP/MAINT 1 SW 03 5748M 28102 OVERHEAT AND ACID SMELL. REPLACED WITH SERVICEABE BATTERY. 2 G 7 2 4U H10SW 2001100400008 20011004 00008 SW 2001 10 4 HEEA076038 1 20010919 G 2432 RG214 BATTERY BELL 214 214ST 1182106 SW MAIN OVERHEATED E HEEA K NONE M OVER TEMP IN INSP/MAINT 1 SW 03 5748M 28102 OVERHEAT AND ACID SMELL. REPLACED WITH SERVICEABE BATTERY. 2 G 7 2 4U H10SW 2001100400009 20011004 00009 SW 2001 10 4 HEEA076039 1 20010919 G 2432 RG214 BATTERY BELL 214 214ST 1182106 SW MAIN DISCHARGED E HEEA K NONE L NO TEST IN INSP/MAINT 1 SW 03 59805 28141 WON'T START AIRCRAFT. REPLACED WITH SERVICEABE BATTERY. 2 G 7 2 4U H10SW 2001100400010 20011004 00010 SW 2001 10 4 HEEA076040 1 20010919 G 2432 RG214 BATTERY BELL 214 214ST 1182106 SW MAIN DISCHARGED E HEEA K NONE L NO TEST IN INSP/MAINT 1 SW 03 59805 28141 WON'T START AIRCRAFT. REPLACED WITH SERVICEABE BATTERY. 2 G 7 2 4U H10SW 2001100400011 20011004 00011 SW 2001 10 4 HEEA076041 1 20010919 G 2432 RG214 BATTERY BELL 214 214ST 1182106 SW MAIN DISCHARGED E HEEA K NONE L NO TEST IN INSP/MAINT 1 SW 03 59806 28140 WEAK. REPLACED WITH SERVICEABE BATTERY. 2 G 7 2 4U H10SW 2001100400012 20011004 00012 SW 2001 10 4 HEEA076042 1 20010919 G 2432 RG214 BATTERY BELL 214 214ST 1182106 SW MAIN DISCHARGED E HEEA K NONE L NO TEST IN INSP/MAINT 1 SW 03 59806 28140 WEAK. REPLACED WITH SERVICEABE BATTERY. 2 G 7 2 4U H10SW 2001100400013 20011004 00013 SW 2001 10 4 HEEA076043 1 20010919 G 2432 RG214 BATTERY BELL 214 214ST 1182106 SW MAIN DISCHARGED E HEEA K NONE L NO TEST IN INSP/MAINT 1 SW 03 6957Y 28139 WON'T HOLD A CHARGE. REPLACED WITH SERVICEABE BATTERY. 2 G 7 2 4U H10SW 2001100400014 20011004 00014 SW 2001 10 4 HEEA076044 1 20010919 G 2432 RG214 BATTERY BELL 214 214ST 1182106 SW MAIN DISCHARGED E HEEA K NONE L NO TEST IN INSP/MAINT 1 SW 03 8045T 28101 WEAK. 2 G 7 2 4U H10SW 2001100400015 20011004 00015 SW 2001 10 4 HEEA076045 1 20010919 G 2432 RG214 BATTERY BELL 214 214ST 1182106 SW MAIN DISCHARGED E HEEA K NONE L NO TEST IN INSP/MAINT 1 SW 03 59806 28140 WEAK. 2 G 7 2 4U H10SW 2001100400016 20011004 00016 SW 2001 10 4 HEEA076046 1 20010919 G 2432 RG214 BATTERY BELL 214 214ST 1182106 SW MAIN DISCHARGED E HEEA K NONE L NO TEST IN INSP/MAINT 1 SW 03 59806 28140 WEAK. REPLACED WITH SERVICEABLE BATTERY. 2 G 7 2 4U H10SW 2001100400022 20011004 00022 SW 2001 10 4 HEEA076047 1 20010919 G 2432 RG214 BATTERY BELL 214 214ST 1182106 SW MAIN DISCHARGED E HEEA K NONE L NO TEST IN INSP/MAINT 1 SW 03 59805 461 28141 WON'T START AIRCRAFT. 2 G 7 2 4U H10SW 2001100400029 20011004 00029 SW 2001 10 4 HEEA076048 1 20010919 G 2432 RG214 BATTERY BELL 214 214ST 1182106 SW MAIN DISCHARGED E HEEA K NONE L NO TEST IN INSP/MAINT 1 SW 03 BATTERY DEAD. 2 G 7 2 4U H10SW 2001100400030 20011004 00030 SW 2001 10 4 HEEA076049 1 20010924 G 3212 214031792102 COVER BELL 214 214ST 1182106 SW MLG FLOAT MISSING E HEEA O OTHER D INFLIGHT SEPARATION NR NOT REPORTED 1 SW 03 8045T 28101 AFTER SHUTDOWN AT HELIPORT, FOUND AFT PORTION OF RIGHT HAND FLOAT COVER MISSING. REPLACED FLOAT COVER. 2 G 7 2 4U H10SW 2001100400031 20011004 00031 2001 10 4 HEEA076050 4 20010924 G 2397 M39012160004 CONNECTOR BELL 212 212 1181420 SW NR 1 VHF RADIO SHORTED E HEEA C ABORTED TAKEOFF B SMOKE/FUMES/ODORS/SPARKS TO TAKEOFF 1 SW 03 102PH 30899 PRIOR TO TAKEOFF, SMELLED ELECTRICAL "BURNING" ODOR. MAINTENANCE FOUND WIRING HARNESS FROM NR 1 VHF RADIO TO BULKHEAD FI TTING SHORTED AT CANNON PLUG. 1 G 7 1 4U H4SW 2001100400038 20011004 00038 SW 2001 10 4 HEEA076051 1 20010924 G 6322 6038T59P02 BLOWER BELL 214 214ST 1182106 SW SHAFT FAILED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 8045T 28101 THE #1 PARTICLE SEPARATOR CAUTION LIGHT CAME ON. MAINTENANCE FOUND PARTICLE SEPARATOR BLOWER SHAFT SHEARED. 2 G 7 2 4U H10SW 2001100400051 20011004 00051 SW 2001 10 4 HEEA076054 1 20010924 G 6220 407310101101 BEARING 407010100115 BELL 407 407 SW MAIN ROTOR SEPARATED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 407PH A222 53003 SEPARATION. 1 G 7 1 3U O H2SW 2001100400054 20011004 00054 SW 2001 10 4 HEEA076056 1 20010924 G 7931 222375077113 TRANSMITTER BELL 407 407 SW ENGINE OIL MALFUNCTIONED E HEEA O OTHER N FALSE WARNING IN INSP/MAINT 1 SW 03 723PH 53283 ENGINE PRESSURE DROPPED TO ZERO. 1 G 7 1 3U O H2SW 2001100400056 20011004 00056 SW 2001 10 4 HEEA076058 1 20010928 G 7120 206064107103 LEG ASSY BELL 206 206L3 1182108 SW ENGINE MOUNT WORN E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 ROD END BEARING ON NEW LEG ASSEMBLY IS NEAR WEAR LIMITS. 1 G 7 1 3U H2SW 2001100400083 20011004 00083 SW 2001 10 4 HEEA076060 1 20010928 G 7120 206064106101 LEG ASSY BELL 206 206L3 1182108 SW ENGINE MOUNT MISMANUFACTURED E HEEA K NONE W INADEQUATE Q C IN INSP/MAINT 1 SW 03 PART DOES NOT FIT PHI INSPECTION FIXTURE WHICH WAS MANUFACTURED TO MATCH SEVERAL OF THESE PART NUMBERED LEG ASSEMBLIES. 1 G 7 1 3U H2SW 2001100400084 20011004 00084 EU 2001 10 4 HEEA076062 1 20010910 G 6230 126891P BEARING SNIAS 350 AS350B 8680801 EU MAIN ROTOR WORN E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 974AE 2653 WORN ROD END BEARINGS ON MAIN ROTOR PC LINKS. PENDING VENDOR RETURN. 1 G 7 1 3U H9EU 2001100400085 20011004 00085 EU 2001 10 4 HEEA076063 1 20010910 G 2432 30248001 BATTERY BOLKMS 105 BO105S 5626006 EU MAIN MALFUNCTIONED E HEEA K NONE L NO TEST IN INSP/MAINT 1 SW 03 6607K S841 "BATT 60" LIGHT CAME ON WHEN ATTEMPTING ENGINE START. REPLACED WITH SERVICEABLE PART. 1 G 7 2 3U H3EU 2001100400086 20011004 00086 EU 2001 10 4 HEEA076064 1 20010910 G 6321 350A32050002 BRAKE ASSY SNIAS 350 AS350B 8680801 EU MAIN ROTOR WORN E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 972AE 502 3234 WORN BRAKE LINING. PENDING VENDOR RETURN. 1 G 7 1 3U H9EU 2001100400087 20011004 00087 EU 2001 10 4 HEEA076066 1 20010910 G 6410 355A09103601 BEARING 355A12005004 SNIAS 350 AS350B 8680801 EU TAIL ROTOR DELAMINATED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 971AE 7458 3230 LAMINANT SEPARATION AT THE END OF THE BEARINGS. PENDING VENDOR RETURN. 1 G 7 1 3U H9EU 2001100400088 20011004 00088 GL 2001 10 4 HEEA076067 2 20010910 G 7421 9550168770 IGNITER SNIAS 350 AS350B 8680801 EU ALLSN 250C 250C* GL ENGINE WORN E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 856PH 612 3352 LT IGNITER PLUG WORN. SCRAPPED AND REPLACED WITH SERVICEABLE PART. 1 G 7 1 3U 3 U H9EU E4CE 2001100400089 20011004 00089 EU 2001 10 4 HEEA076068 1 20010910 G 6230 BEARING SNIAS 350 AS350B 8680801 EU MAIN ROTOR WORN E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 974AE 2653 WORN ROD END BEARINGS ON MAIN ROTOR PC LINKS. PENDING VENDOR RETURN. 1 G 7 1 3U H9EU 2001102200110 20011022 00110 GL 2001 10 22 HEEA076247 2 20011002 G 7230 23064570 LINER BELL 407 407 1182206 SW ALLSN 250B 250B* GL COMPRESSOR CHAFED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 467PH 53142 RUMBLING NOISE AROUND 30 PERCENT N1 DURING START. SENT TO STANDARD AERO FOR EXCHANGE. 1 G 7 1 3U 3 T O H2SW E10CE 2001102200112 20011022 00112 GL 2001 10 22 HEEA076248 2 20011002 G 7412 23064130 IGNITER BELL 407 407 1182206 SW ALLSN 250B 250B* GL ENGINE INOPERATIVE E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 741PH 53457 IGNITOR BOX INOPERATIVE. 1 G 7 1 3U 3 T O H2SW E10CE 2001102200115 20011022 00115 NE 2001 10 22 HEEA076249 2 20011003 G 7320 0292928650 VALVE SNIAS 350 AS350B 8680801 EU TMECA ARRIEL ARRIEL1D NE FUEL METERING MALFUNCTIONED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 971AE 936 3230 22072 NG AND TORQUE FLUCTUATIONS. PENDING VENDOR RETURN. 1 G 7 1 3U 3 U H9EU E19EU 2001102300003 20011023 00003 EU 2001 10 23 HEEA076250 1 20011003 G 7197 0301037070 HARNESS SNIAS 350 AS350B 8680801 EU ENGINE ERRATIC E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 856PH 703 3352 T-4 ERRATIC. PENDING VENDOR RETURN. 1 G 7 1 3U H9EU 2001102300004 20011023 00004 2001 10 23 HEEA076251 4 20011004 G 8300 3024780 GEARBOX BELL 412 412 1182202 SW RGB MAKING METAL E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 1202T 33112 RGB SECTION MAKING METAL CHIPS IN FILTER AND CHIP PLUG. PENDING VENDOR REPAIR. 1 G 7 2 4U H4SW 2001102300005 20011023 00005 NE 2001 10 23 HEEA076252 1 20011004 G 7714 BUTTON SKRSKY S76 S76A 8143006 NE N1 INDICATOR MISSING E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 760PH 760078 TACHO CHECK BUTTON MISSING. PENDING VENDOR REPAIR. 1 G 7 2 3U H1NE 2001102300006 20011023 00006 NE 2001 10 23 HEEA076253 1 20011004 G 3212 7625101102101 FLOAT SKRSKY S76 S76A 8143006 NE MLG WILL NOT TEST E HEEA K NONE L NO TEST IN INSP/MAINT 1 SW 03 911MJ 760231 FAILED INFLATION TEST. PENDING VENDOR REPAIR. 1 G 7 2 3U H1NE 2001102300007 20011023 00007 2001 10 23 HEEA076254 4 20011004 G 2215 7690001802106 ACTUATOR SKRSKY S76 S76A 8143006 NE AFCS CHATTERING E HEEA O OTHER F J FLT CONT AFFECTED WARNING INDICATION NR NOT REPORTED 1 SW 03 760PH 760078 CHATTERING INDUCING PORPOISE IN AIRCRAFT. PENDING VENDOR REPAIR. 1 G 7 2 3U H1NE 2001102300008 20011023 00008 EA 2001 10 23 HEEA076255 2 20011009 G 7200 ENGINE BELL 212 212 1181420 SW PWA PT6T PT6T3 52045 EA NACELLE MALFUNCTIONED E HEEA O OTHER J WARNING INDICATION NR NOT REPORTED 1 SW 03 102PH 30899 HIGH OIL CONSUMPTION. SENT TO PRATT AND WHITNEY FOR WARRANTY REPAIR. 1 G 7 1 4U 4 U H4SW E22EA 2001102300009 20011023 00009 EA 2001 10 23 HEEA076256 2 20011009 G 7200 ENGINE BELL 212 212 1181420 SW PWA PT6T PT6T3 52045 EA NACELLE CORRODED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 1079U 16590 31122 CORROSION AT 12 OCLOCK. SENT TO PRATT AND WHITNEY FOR INSPECTION AND REPAIR. 1 G 7 1 4U 4 U H4SW E22EA 2001102300010 20011023 00010 EA 2001 10 23 HEEA076257 2 20011009 G 7200 ENGINE BELL 212 212 1181420 SW PWA PT6T PT6T3 52045 EA NACELLE STALLED E HEEA O OTHER M J OVER TEMP WARNING INDICATION NR NOT REPORTED 1 SW 03 5736D 9772 31135 COMPRESSOR STALLS AND HIGH ITT. SENT TO PRATT AND WHITNEY FOR INSPECTION AND REPAIR. 1 G 7 1 4U 4 U H4SW E22EA 2001102300011 20011023 00011 NE 2001 10 23 HEEA076258 2 20011009 G 7200 ENGINE BELL 412 412 1182202 SW PWA PT6T PT6T3B 52045 NE NACELLE STALLED E HEEA O OTHER J WARNING INDICATION NR NOT REPORTED 1 SW 03 3893N 20429 33010 COMPRESSOR STALLS ABOVE 85 PERCENT N1 AND OVERTEMP (PEGGED OUT GAUGE). SENT TO PRATT AND WHITNEY FOR INSPECTION AND REPA IR. 1 G 7 2 4U 4 U H4SW E22EA 2001102300012 20011023 00012 EA 2001 10 23 HEEA076259 2 20011009 G 7200 ENGINE BELL 212 212 1181420 SW PWA PT6T PT6T3 52045 EA NACELLE MALFUNCTIONED E HEEA O OTHER R J PARTIAL RPM/PWR LOSS WARNING INDICATION NR NOT REPORTED 1 SW 03 5009N 6539 30936 LOW POWER. SENT TO PRATT AND WHITNEY FOR INSPECTION AND REPAIR. 1 G 7 1 4U 4 U H4SW E22EA 2001102300013 20011023 00013 NE 2001 10 23 HEEA076260 2 20011009 G 7200 ENGINE BELL 412 412 1182202 SW PWA PT6T PT6T3B 52045 NE NACELLE OSCILLATES E HEEA O OTHER J WARNING INDICATION NR NOT REPORTED 1 SW 03 22347 1620 36005 TORQUE OSCILLATIONS. SENT TO PRATT AND WHITNEY FOR INSPECTION AND REPAIR. 1 G 7 2 4U 4 U H4SW E22EA 2001102300014 20011023 00014 EA 2001 10 23 HEEA076261 2 20011009 G 7200 ENGINE BELL 212 212 1181420 SW PWA PT6T PT6T3 52045 EA NACELLE HOT START E HEEA O OTHER M J OVER TEMP WARNING INDICATION NR NOT REPORTED 1 SW 03 5736D 7809 31135 HOT STARTS. SENT TO PRATT AND WHITNEY FOR INSPECTION AND REPAIR. 1 G 7 1 4U 4 U H4SW E22EA 2001102300015 20011023 00015 NE 2001 10 23 HEEA076262 2 20011009 G 7200 ENGINE BELL 412 412 1182202 SW PWA PT6T PT6T3B 52045 NE NACELLE STALLED E HEEA O OTHER M J OVER TEMP WARNING INDICATION NR NOT REPORTED 1 SW 03 22347 5034 36005 COMPRESSOR STALLS AND ITT OVER 1000 DEGREES. SENT TO PRATT AND WHITNEY FOR INSPECTION AND REPAIR. 1 G 7 2 4U 4 U H4SW E22EA 2001102300016 20011023 00016 NE 2001 10 23 HEEA076263 2 20011009 G 7200 ENGINE BELL 412 412 1182202 SW PWA PT6T PT6T3B 52045 NE NACELLE STALLED E HEEA O OTHER C J F.O.D. WARNING INDICATION NR NOT REPORTED 1 SW 03 7128R 11662 36007 COMPRESSOR STALLS - FOD TO COMPRESSOR BLADES. SENT TO PRATT AND WHITNEY FOR OVERHAUL. 1 G 7 2 4U 4 U H4SW E22EA 2001102300017 20011023 00017 SW 2001 10 23 HEEA076264 1 20011009 G 5412 FIREWALL BELL 412 412 1182202 SW ENGINE BAY LOOSE E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 5759N 15595 33002 AFT ENGINE FIRE WALL ATTACHMENT FLANGE RIVETS LOOSE. 1 G 7 2 4U H4SW 2001102300018 20011023 00018 NE 2001 10 23 HEEA076265 2 20011009 G 7200 ENGINE BELL 412 412 1182202 SW PWA PT6T PT6T3B 52045 NE ENGINE BAY OVERHEATED E HEEA O OTHER M J OVER TEMP WARNING INDICATION NR NOT REPORTED 1 SW 03 2149S 1691 36002 ITT WENT ABOVE 900 DEGREES DURING MANUAL GOVERNOR CHECK.. 1 G 7 2 4U 4 U H4SW E22EA 2001102300019 20011023 00019 NE 2001 10 23 HEEA076266 2 20011009 G 7200 ENGINE BELL 412 412 1182202 SW PWA PT6T PT6T3B 52045 NE ENGINE BAY OVERHEATED E HEEA O OTHER M J OVER TEMP WARNING INDICATION NR NOT REPORTED 1 SW 03 3893P 15285 33012 HIGH N1 ON POWER CHECK. 1 G 7 2 4U 4 U H4SW E22EA 2001102300020 20011023 00020 NE 2001 10 23 HEEA076267 2 20011009 G 7200 ENGINE BELL 412 412 1182202 SW PWA PT6T PT6T3B 52045 NE ENGINE BAY OVERHEATED E HEEA O OTHER M J OVER TEMP WARNING INDICATION NR NOT REPORTED 1 SW 03 2298Z 12293 33077 HIGH ITT AND WEAR ON GEARBOX CASE AND COVER. 1 G 7 2 4U 4 U H4SW E22EA 2001102300021 20011023 00021 NE 2001 10 23 HEEA076268 2 20011009 G 7200 ENGINE BELL 412 412 1182202 SW PWA PT6T PT6T3B 52045 NE ENGINE BAY OVERSPEED E HEEA O OTHER J WARNING INDICATION NR NOT REPORTED 1 SW 03 22347 8022 36005 N1 OVERSPEED AT 116 PERCENT. 1 G 7 2 4U 4 U H4SW E22EA 2001102300022 20011023 00022 EA 2001 10 23 HEEA076269 2 20011009 G 7200 BLADE BELL 212 212 1181420 SW PWA PT6T PT6T3 52045 EA ENG COMPRESSOR CORRODED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 1082G 16728 31109 COMPRESSOR BLADE CORRODED. 1 G 7 1 4U 4 U H4SW E22EA 2001102300023 20011023 00023 NE 2001 10 23 HEEA076270 2 20011009 G 7200 COMPRESSOR BELL 412 412 1182202 SW PWA PT6T PT6T3B 52045 NE ENGINE SEIZED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 3893L 6819 33006 COMPRESSOR SEIZED. 1 G 7 2 4U 4 U H4SW E22EA 2001102300024 20011023 00024 NE 2001 10 23 HEEA076271 2 20011009 G 7297 ENGINE BELL 412 412 1182202 SW PWA PT6T PT6T3B 52045 NE ENGINE BAY MALFUNCTIONED E HEEA O OTHER J WARNING INDICATION NR NOT REPORTED 1 SW 03 800Y 7681 33134 ENGINE HAS HIGH T-5 HARNESS OHMS OUT LESS THAN 100 OHMS. 1 G 7 2 4U 4 U H4SW E22EA 2001102300025 20011023 00025 NE 2001 10 23 HEEA076272 2 20011009 G 7200 ENGINE BELL 412 412 1182202 SW PWA PT6T PT6T3B 52045 NE ENGINE BAY OVERSPEED E HEEA O OTHER J WARNING INDICATION NR NOT REPORTED 1 SW 03 22347 17028 36005 N1 OVERSPEED AT 116 PERCENT. REPLACED WITH SERVICEABLE ENGINE. 1 G 7 2 4U 4 U H4SW E22EA 2001102300026 20011023 00026 GL 2001 10 23 HEEA076273 2 20011011 G 7323 252469211 GOVERNOR SKRSKY S76 S76A 8143006 NE ALLSN 250C 250C30S 03013 GL ENGINE OSCILLATES E HEEA K NONE L NO TEST IN INSP/MAINT 1 SW 03 5435V 10875 760158 CAE890432S ENGINE N1, T5, TORQUE AND FUEL FLOW OSCILLATES AT HIGH POWER SETTINGS. REPLACED WITH SERVICEABLE PART. 1 G 7 2 3U 3 U H1NE E1GL 2001102300027 20011023 00027 NE 2001 10 23 HEEA076274 1 20011011 G 6321 40004769R CALIPER SKRSKY S76 S76A 8143006 NE ROTOR BRAKE LEAKING E HEEA K NONE K FLUID LOSS IN INSP/MAINT 1 SW 03 911MJ 760231 CALIPER LEAKING. REPLACED WITH SERVICEABLE PART. 1 G 7 2 3U H1NE 2001102300028 20011023 00028 NE 2001 10 23 HEEA076275 1 20011011 G 6321 40004769R CALIPER SKRSKY S76 S76A 8143006 NE ROTOR BRAKE LEAKING E HEEA K NONE K FLUID LOSS IN INSP/MAINT 1 SW 03 911MJ 760231 CALIPER LEAKING. REPLACED WITH SERVICEABLE PART. 1 G 7 2 3U H1NE 2001102300029 20011023 00029 NE 2001 10 23 HEEA076276 1 20011011 G 2121 7650007901102 BLOWER SKRSKY S76 S76A 8143006 NE VENT MALFUNCTIONED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 3122H 760233 VENT BLOWER POPS CIRCUIT BREAKER. REPLACED WITH SERVICEABLE PART. 1 G 7 2 3U H1NE 2001102300030 20011023 00030 2001 10 23 HEEA076277 4 20011012 G 3450 258719342 COMPASS SKRSKY S76 S76A 8143006 NE COCKPIT MALFUNCTIONED E HEEA K NONE L NO TEST IN INSP/MAINT 1 SW 03 760PH 760078 HIS OFF FLAG WILL NOT PULL. REPLACED WITH SERVICEABLE PART. 1 G 7 2 3U H1NE 2001102300031 20011023 00031 NE 2001 10 23 HEEA076278 1 20011012 G 6321 7665009803105 MODULE 350A33200406 SKRSKY S76 S76A 8143006 NE ROTOR BRAKE ASSY INTERMITTENT E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 760PH MA1154 760078 ROTOR BRAKE WARNING LIGHT INTERMITTENTLY DOES NOT ILLUMINATE WITH ROTOR BRAKE ENGAGED. REPLACED WITH SERVICEABLE PART. 1 G 7 2 3U H1NE 2001102300032 20011023 00032 NE 2001 10 23 HEEA076279 2 20011012 G 7421 9550166670 IGNITER SKRSKY S76 S76A 8143006 NE TMECA ARRIEL ARRIEL1 60030 NE ENGINE INOPERATIVE E HEEA K NONE L NO TEST IN INSP/MAINT 1 SW 03 760PH 760078 INOPERATIVE NO SPARK. REPLACED WITH SERVICEABLE PART. 1 G 7 2 3U 3 U H1NE E19EU 2001102300033 20011023 00033 SW 2001 10 23 HEEA076280 1 20011001 G 3212 407073848101 BOTTLE BELL 407 407 1182206 SW FLOAT BAG DISCHARGED E HEEA K NONE K FLUID LOSS IN INSP/MAINT 1 SW 03 491PH 53386 VALVE VENTING. COULD NOT SERVICE WITH NITROGEN. 1 G 7 1 3U O H2SW 2001102300034 20011023 00034 SW 2001 10 23 HEEA076281 1 20011001 G 3212 407073848101 BOTTLE BELL 407 407 1182206 SW FLOAT BAG DISCHARGED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 491PH 53386 VALVE VENTING. COULD NOT SERVICE WITH NITROGEN. 1 G 7 1 3U O H2SW 2001102300035 20011023 00035 SW 2001 10 23 HEEA076283 1 20011001 G 2435 206062200113 STARTER GEN BELL 407 407 1182206 SW ENGINE MALFUNCTIONED E HEEA K NONE L NO TEST IN INSP/MAINT 1 SW 03 495PH 2628 53397 STARTING PROBLEMS. DEAD SPOT. 1 G 7 1 3U O H2SW 2001102300036 20011023 00036 SW 2001 10 23 HEEA076284 1 20011001 G 2435 BRUSHES BELL 407 407 1182206 SW STARTER GEN WORN E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 405PH 622 Y0099 53207 WORN BRUSHES. 1 G 7 1 3U O H2SW 2001102300037 20011023 00037 SW 2001 10 23 HEEA076285 1 20011001 G 6420 407012101111 HUB BELL 407 407 1182206 SW TAIL ROTOR PEELING E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 742PH 248 53461 PAINT PEELING FROM BLADE. 1 G 7 1 3U O H2SW 2001102300038 20011023 00038 SW 2001 10 23 HEEA076286 1 20011001 G 7921 8538100 OIL COOLER BELL 412 412 1182202 SW OIL SYSTEM MAKING METAL E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 1202T 33112 METAL IN OIL. 1 G 7 2 4U H4SW 2001102300039 20011023 00039 SW 2001 10 23 HEEA076287 1 20011001 G 7921 8538100 OIL COOLER BELL 412 412 1182202 SW OIL SYSTEM LEAKING E HEEA O OTHER K FLUID LOSS NR NOT REPORTED 1 SW 03 1202T 33112 LEAKING FROM CENTER SECTION. REPLACED WITH SERVICEABLE COOLER. 1 G 7 2 4U H4SW 2001102300040 20011023 00040 SW 2001 10 23 HEEA076288 1 20011001 G 7921 8538100 OIL COOLER BELL 412 412 1182202 SW OIL SYSTEM MALFUNCTIONED E HEEA O OTHER M J OVER TEMP WARNING INDICATION NR NOT REPORTED 1 SW 03 1202T 33112 HIGH TEMPERATURE READINGS ABOUT 100 DEGREES IN RED LINE. ALSO C-BOX CAUTION LIGHT CAME ON. REPLACED WITH SERVICEABLE CO OLER. 1 G 7 2 4U H4SW 2001102300041 20011023 00041 SW 2001 10 23 HEEA076289 1 20011001 G 7921 8538100 OIL COOLER BELL 212 212 1181420 SW OIL SYSTEM CONTAMINATED E HEEA O OTHER K FLUID LOSS NR NOT REPORTED 1 SW 03 3131S 30953 CONTAMINATED FROM MAST, ALSO LEAKS. 1 G 7 1 4U H4SW 2001102300042 20011023 00042 SW 2001 10 23 HEEA076290 1 20011001 G 7921 8538100 OIL COOLER BELL 412 412 1182202 SW OIL SYSTEM CONTAMINATED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 2148K 36001 METAL CONTAMINATED. 1 G 7 2 4U H4SW 2001102300043 20011023 00043 SW 2001 10 23 HEEA076291 1 20011001 G 6320 TRANSMISSION BELL 412 412 1182202 SW MAIN ROTOR MAKING METAL E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 800Y 33134 TRANSMISSION MAKING METAL. SENT TO DRAKE AIR FOR INSPECTION AND REPAIR. 1 G 7 2 4U H4SW 2001102300044 20011023 00044 SW 2001 10 23 HEEA076292 1 20011001 G 6310 COMBINING BOX BELL 412 412 1182202 SW TRANSMISSION MAKING METAL E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 800Y 33134 C-BOX MAKING METAL. 1 G 7 2 4U H4SW 2001102300045 20011023 00045 SW 2001 10 23 HEEA076293 1 20011001 G 7921 8538100 OIL COOLER BELL 412 412 1182202 SW OIL SYSTEM LEAKING E HEEA O OTHER K FLUID LOSS NR NOT REPORTED 1 SW 03 2258F 33073 OIL COOLER LEAKS. 1 G 7 2 4U H4SW 2001102300046 20011023 00046 SW 2001 10 23 HEEA076294 1 20011001 G 7921 8538100 OIL COOLER BELL 212 212 1181420 SW OIL SYSTEM CONTAMINATED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 5736J 31140 METAL CONTAMINATION. 1 G 7 1 4U H4SW 2001102300052 20011023 00052 SW 2001 10 23 HEEA076295 1 20011001 G 6310 COMBINING BOX BELL 412 412 1182202 SW TRANSMISSION MAKING METAL E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 1202T 33112 C-BOX MAKING METAL. 1 G 7 2 4U H4SW 2001102300064 20011023 00064 SW 2001 10 23 HEEA076296 1 20011001 G 6300 8538100 OIL COOLER BELL 412 412 1182202 SW MAIN ROTOR LEAKING E HEEA O OTHER K FLUID LOSS NR NOT REPORTED 1 SW 03 1202T 33112 OIL COOLER LEAKING FROM CENTER CORE. 1 G 7 2 4U H4SW 2001102300071 20011023 00071 SW 2001 10 23 HEEA076298 1 20011001 G 6300 8538100 OIL COOLER BELL 412 412 1182202 SW MAIN ROTOR CONTAMINATED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 33008 36004 METAL CONTAMINATION. 1 G 7 2 4U H4SW 2001102300131 20011023 00131 SW 2001 10 23 HEEA076299 1 20011001 G 6300 8538100 OIL COOLER BELL 212 212 1181420 SW MAIN ROTOR CONTAMINATED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 5736D 31135 OIL COOLER HAS METAL CONTAMINATION. 1 G 7 1 4U H4SW 2001102300132 20011023 00132 SW 2001 10 23 HEEA076300 1 20011001 G 6300 8538100 OIL COOLER BELL 412 412 1182202 SW MAIN ROTOR LEAKING E HEEA O OTHER K FLUID LOSS NR NOT REPORTED 1 SW 03 OIL COOER LEAKING OIL. 1 G 7 2 4U H4SW 2001102300133 20011023 00133 SW 2001 10 23 HEEA076301 1 20011001 G 6300 8538100 OIL COOLER BELL 412 412 1182202 SW MAIN ROTOR LEAKING E HEEA O OTHER K FLUID LOSS NR NOT REPORTED 1 SW 03 22347 36005 OIL COOLER SEEPING. 1 G 7 2 4U H4SW 2001102300134 20011023 00134 SW 2001 10 23 HEEA076302 1 20011001 G 6320 TRANSMISSION BELL 212 212 1181420 SW MAIN ROTOR MAKING METAL E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 5736D 31135 TRANSMISSION MAKING METAL. 1 G 7 1 4U H4SW 2001102300135 20011023 00135 SW 2001 10 23 HEEA076303 1 20011002 G 2435 BRUSHES BELL 407 407 1182206 SW STARTER GEN WORN E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 720PH 1566 2109 53277 BRUSHES WORN. 1 G 7 1 3U O H2SW 2001102300136 20011023 00136 SW 2001 10 23 HEEA076307 1 20011002 G 6500 206061432121 HOUSING BELL 407 407 1182206 SW COOLER BLOWER CRACKED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 447PH 53114 BLOWER HOUSING CRACKED. 1 G 7 1 3U O H2SW 2001102300139 20011023 00139 SW 2001 10 23 HEEA076308 1 20011002 G 6500 206061432121 HOUSING BELL 407 407 1182206 SW COOLER BLOWER CRACKED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 496PH 53398 TAIL ROTOR COOLER BLOWER HOUSING IS CRACKED. 1 G 7 1 3U O H2SW 2001102300140 20011023 00140 SW 2001 10 23 HEEA076309 1 20011002 G 6500 206061432121 HOUSING BELL 407 407 1182206 SW COOLER BLOWER DAMAGED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 8595X 53267 TAIL ROTOR COOLER BLOWER HOUSING HAS WORKING RIVETS. 1 G 7 1 3U O H2SW 2001102300142 20011023 00142 SW 2001 10 23 HEEA076310 1 20011002 G 2821 206061634003 VALVE BELL 407 407 1182206 SW FUEL FILTER LEAKING E HEEA K NONE K FLUID LOSS IN INSP/MAINT 1 SW 03 406PH 53198 EXTERNAL FUEL FILTER DRAIN VALVE LEAKING AROUND HANDLE WHEN DRAINING FUEL. 1 G 7 1 3U O H2SW 2001102300146 20011023 00146 SW 2001 10 23 HEEA076311 1 20011002 G 2435 BRUSHES BELL 407 407 1182206 SW STARTER GEN WORN E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 501PH 95189 53401 300 HOUR SCHEDULE CHANGE. WORN BRUSHES. 1 G 7 1 3U O H2SW 2001102300148 20011023 00148 SW 2001 10 23 HEEA076312 1 20011002 G 2435 206062200113 STARTER GEN BELL 407 407 1182206 SW ENGINE FAILED E HEEA K NONE L NO TEST IN INSP/MAINT 1 SW 03 8595X 1808 53267 STARTER GENERATOR WOULD NOT CRANK ENGINE ON LAST START OF THE DAY. 1 G 7 1 3U O H2SW 2001102300149 20011023 00149 SW 2001 10 23 HEEA076313 1 20011002 G 2435 BRUSHES BELL 407 407 1182206 SW STARTER GEN WORN E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 490PH 2203 98136 53378 STARTER GEN HAS WORN BRUSHES. 1 G 7 1 3U O H2SW 2001102300167 20011023 00167 SW 2001 10 23 HEEA076314 1 20011002 G 2435 BRUSHES BELL 407 407 1182206 SW STARTER GEN WORN E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 496PH 1607 99100 53398 STARTER GEN HAS WORN BRUSHES. 1 G 7 1 3U O H2SW 2001102300168 20011023 00168 SW 2001 10 23 HEEA076317 1 20011002 G 5347 206072215102 SUPPORT BELL 407 407 1182206 SW CABIN BROKEN E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 722PH 53288 FOUND SEAT SUPPORT BROKEN IN TWO. 1 G 7 1 3U O H2SW 2001102300169 20011023 00169 SW 2001 10 23 HEEA076318 1 20011002 G 6321 HOUSING BELL 407 407 1182206 SW ROTOR BRAKE WORN E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 496PH 1701 53398 REMOVED FOR MODIFICATION. FOUND EXCESSIVE WEAR ON HOUSING, BRAKE PAD BOLT RETAINER HOLES AND PAD RETAINER BOLTS. 1 G 7 1 3U O H2SW 2001102300170 20011023 00170 SW 2001 10 23 HEEA076319 1 20011002 G 3212 212073905001 GAUGE BELL 407 407 1182206 SW FLOAT PRESSURE CONTAMINATED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 409PH 53059 UNREADABLE DUE TO MOISTURE IN GLASS. 1 G 7 1 3U O H2SW 2001102300171 20011023 00171 SW 2001 10 23 HEEA076320 1 20011002 G 3212 212073905001 GAUGE BELL 407 407 1182206 SW FLOAT PRESSURE CONTAMINATED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 720PH 53277 WATER IN GAUGE. 1 G 7 1 3U O H2SW 2001102300175 20011023 00175 SW 2001 10 23 HEEA076321 1 20011002 G 2510 222320823130 SEAT BELT BELL 407 407 1182206 SW COCKPIT FRAYED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 405PH 53207 SEAT BELT FRAYED. 1 G 7 1 3U O H2SW 2001102300176 20011023 00176 SW 2001 10 23 HEEA076322 1 20011002 G 2844 222375077115 TRANSDUCER BELL 407 407 1182206 SW FUEL SYSTEM READS LOW E HEEA K NONE L NO TEST IN INSP/MAINT 1 SW 03 467PH 3307 53142 PRESSURE READS LOW. 1 G 7 1 3U O H2SW 2001102300177 20011023 00177 SW 2001 10 23 HEEA076323 1 20011002 G 7714 222375077119 TRANSMITTER BELL 407 407 1182206 SW ENGINE TORQUE MALFUNCTIONED E HEEA K NONE L NO TEST IN INSP/MAINT 1 SW 03 405PH 3728 53207 FADEC DEGRADE LIGHT. 1 G 7 1 3U O H2SW 2001102300178 20011023 00178 GL 2001 10 23 HEEA076324 2 20011002 G 7532 23005366 BLEED VALVE BELL 407 407 1182206 SW ALLSN 250C 250C47B GL ENGINE FAILED E HEEA K NONE L NO TEST IN INSP/MAINT 1 SW 03 496PH 53398 HIGH MGT. REPLACED WITH SERVICEABLE BLEED VALVE. 1 G 7 1 3U 3 U O H2SW E1GL 2001102300179 20011023 00179 GL 2001 10 23 HEEA076325 2 20011002 G 7297 23065805 HARNESS BELL 407 407 1182206 SW ALLSN 250C 250C47B GL ENGINE FAILED E HEEA K NONE L NO TEST IN INSP/MAINT 1 SW 03 405PH 53207 FADEC DEGRADE LIGHT ILLUMINATED ON SHUTDOWN. 1 G 7 1 3U 3 U O H2SW E1GL 2001102300180 20011023 00180 GL 2001 10 23 HEEA076326 2 20011002 G 7297 23065805 HARNESS BELL 407 407 1182206 SW ALLSN 250C 250C47B GL ENGINE FAILED E HEEA K NONE L NO TEST IN INSP/MAINT 1 SW 03 405PH 53207 CONSTANT FADEC DEGRADE LIGHT. TO BE SENT TO VENDOR FOR CREDIT. 1 G 7 1 3U 3 U O H2SW E1GL 2001102300181 20011023 00181 GL 2001 10 23 HEEA076327 2 20011002 G 7297 23065805 HARNESS BELL 407 407 1182206 SW ALLSN 250C 250C47B GL ENGINE FAILED E HEEA K NONE L NO TEST IN INSP/MAINT 1 SW 03 496PH 53398 FADEC DEGRADE LIGHT. TO BE SENT TO VENDOR FOR CREDIT. 1 G 7 1 3U 3 U O H2SW E1GL 2001102300182 20011023 00182 GL 2001 10 23 HEEA076328 2 20011002 G 7297 23065805 HARNESS BELL 407 407 1182206 SW ALLSN 250C 250C47B GL ENGINE FAILED E HEEA K NONE L NO TEST IN INSP/MAINT 1 SW 03 405PH 53207 SHORT BETWEEN PIN D & C OF TORQUE TRANSMITTER CONNECTOR. TO BE SENT TO VENDOR FOR CREDIT. 1 G 7 1 3U 3 U O H2SW E1GL 2001102300183 20011023 00183 SW 2001 10 23 HEEA076329 1 20011002 G 7700 23071644 ECU BELL 407 407 1182206 SW ALLSN 250C 250C47B GL ENGINE MALFUNCTIONED E HEEA K NONE L NO TEST IN INSP/MAINT 1 SW 03 490PH 53378 CONTINUES TO HAVE NPOS & OS FAULTS. TO BE SENT TO VENDOR FOR REPAIR. 1 G 7 1 3U 3 U O H2SW E1GL 2001102300184 20011023 00184 SW 2001 10 23 HEEA076330 1 20011002 G 2432 31908001 BATTERY BELL 407 407 1182206 SW MAIN WEAK E HEEA K NONE L NO TEST IN INSP/MAINT 1 SW 03 501PH 53401 BATTERY WEAK. 1 G 7 1 3U O H2SW 2001102300185 20011023 00185 SW 2001 10 23 HEEA076331 1 20011002 G 3201 400052007109 BEAM BELL 407 407 1182206 SW MLG CORRODED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 57416 53070 BEAM ASSY CORRODED AND BOLT HOLE WORN. 1 G 7 1 3U O H2SW 2001102300186 20011023 00186 SW 2001 10 23 HEEA076332 1 20011002 G 3201 400052007115 BEAM BELL 407 407 1182206 SW MLG CORRODED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 409PH 53059 BEAM CORRODED AROUND BUSHINGS. IN SHEETMETAL SHOP FOR REPAIR. 1 G 7 1 3U O H2SW 2001102300187 20011023 00187 SW 2001 10 23 HEEA076333 1 20011002 G 3201 400052009101 BOLT BELL 407 407 1182206 SW MLG CORRODED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 409PH 53059 PITTED THROUGH COATING. SCRAPPED AND REPLACED WITH SERVICEABLE BOLT. 1 G 7 1 3U O H2SW 2001102300188 20011023 00188 SW 2001 10 23 HEEA076334 1 20011002 G 6720 406012129101 LINK BELL 407 407 1182206 SW TAIL ROTOR WORN E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 493PH 53393 ROD END BEARINGS WORN. 1 G 7 1 3U O H2SW 2001102300189 20011023 00189 SW 2001 10 23 HEEA076335 1 20011002 G 6310 BEARING 406040500119 BELL 407 407 1182206 SW SUPPORT FAILED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 8595X A1505 53267 ROLLER FELL OUT OF BEARING. 1 G 7 1 3U O H2SW 2001102300190 20011023 00190 SW 2001 10 23 HEEA076336 1 20011002 G 6310 SEAL 406040500123 BELL 407 407 1182206 SW FREEWHEEL UNIT LEAKING E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 612PH A4015 53199 FRONT SEAL LEAKING. 1 G 7 1 3U O H2SW 2001102300191 20011023 00191 SW 2001 10 23 HEEA076337 1 20011002 G 6310 SEAL 406040500127 BELL 407 407 1182206 SW FREEWHEEL UNIT LEAKING E HEEA K NONE K FLUID LOSS IN INSP/MAINT 1 SW 03 407PH A3753 53003 FRONT SEAL LEAKING. 1 G 7 1 3U O H2SW 2001102300193 20011023 00193 SW 2001 10 23 HEEA076338 1 20011002 G 6710 406310404101 ROD END BELL 407 407 1182206 SW MAIN ROTOR WORN E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 404PH 3368 53188 ROD END ASSY WORN. 1 G 7 1 3U O H2SW 2001102300200 20011023 00200 SW 2001 10 23 HEEA076339 1 20011002 G 6710 406310405101 UNIVERSAL JOINT BELL 407 407 1182206 SW MAIN ROTOR WORN E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 612PH 1498 53199 MAIN ROTOR UNIVERSAL WORN. 1 G 7 1 3U O H2SW 2001102300202 20011023 00202 SW 2001 10 23 HEEA076340 1 20011002 G 6710 406310405101 UNIVERSAL JOINT BELL 407 407 1182206 SW MAIN ROTOR WORN E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 408PH 1817 53228 BEARINGS WORN. 1 G 7 1 3U O H2SW 2001102300203 20011023 00203 SW 2001 10 23 HEEA076341 1 20011002 G 6710 406310405101 UNIVERSAL JOINT BELL 407 407 1182206 SW MAIN ROTOR WORN E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 490PH 53378 WORN. 1 G 7 1 3U O H2SW 2001102300204 20011023 00204 SW 2001 10 23 HEEA076342 1 20011002 G 6710 406310405101 UNIVERSAL JOINT BELL 407 407 1182206 SW MAIN ROTOR WORN E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 408PH 53228 UNIVERSAL WORN. 1 G 7 1 3U O H2SW 2001102300206 20011023 00206 SW 2001 10 23 HEEA076343 1 20011002 G 6720 406312103101 LINK BELL 407 407 1182206 SW TAIL ROTOR WORN E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 405PH 53207 WORN BEARING. 1 G 7 1 3U O H2SW 2001102300209 20011023 00209 SW 2001 10 23 HEEA076344 1 20011002 G 6720 406312103101 LINK BELL 407 407 1182206 SW TAIL ROTOR WORN E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 405PH 53207 WORN BEARING. 1 G 7 1 3U O H2SW 2001102300211 20011023 00211 SW 2001 10 23 HEEA076345 1 20011002 G 6710 407001523101 IDLER ASSY BELL 407 407 1182206 SW MAIN ROTOR WORN E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 493PH 53393 MAIN ROTOR CONTROL IDLER ASSY HAS WORN BEARINGS. 1 G 7 1 3U O H2SW 2001102300214 20011023 00214 SW 2001 10 23 HEEA076348 1 20011002 G 6420 407012101111 HUB BELL 407 407 1182206 SW TAIL ROTOR NOISY E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 721PH 4756 53278 CLICKING NOISE. 1 G 7 1 3U O H2SW 2001102300216 20011023 00216 SW 2001 10 23 HEEA076349 1 20011002 G 6420 BEARING BELL 407 407 1182206 SW T/R TRUNNION NOISY E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 612PH 2540 53199 CLICKING NOISE COMING FROM TRUNNION BEARING. 1 G 7 1 3U O H2SW 2001102300217 20011023 00217 SW 2001 10 23 HEEA076350 1 20011002 G 6420 407012101111 HUB BELL 407 407 1182206 SW TAIL ROTOR NOISY E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 722PH 1468 53288 CLICKING NOISE WHEN PUSHED TO STOPS. 1 G 7 1 3U O H2SW 2001102300219 20011023 00219 SW 2001 10 23 HEEA076351 1 20011002 G 6300 407340339103 BEARING 407040302101 BELL 407 407 1182206 SW T/R DRIVESHAFT WORN E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 467PH A926 53142 WORN ON INNER DIAMETER. 1 G 7 1 3U O H2SW 2001102300221 20011023 00221 SW 2001 10 23 HEEA076352 1 20011002 G 7810 407062021101 DUCT BELL 407 407 1182206 SW EXHAUST CRACKED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 720PH 53277 EXHAUST DUCT CRACKED. 1 G 7 1 3U O H2SW 2001102400001 20011024 00001 SW 2001 10 24 HEEA076353 1 20011003 G 6420 BEARING BELL 407 407 1182206 SW T/R TRUNNION NOISY E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 612PH 2803 53199 T/R TRUNNION BEARING CLICKS WHEN FLAPPED. 1 G 7 1 3U O H2SW 2001102400002 20011024 00002 SW 2001 10 24 HEEA076354 1 20011003 G 6410 BLADE BELL 407 407 1182206 SW TAIL ROTOR FLAKING E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 722PH 251 53288 PAINT FLAKING OFF BLADES. 1 G 7 1 3U O H2SW 2001102400003 20011024 00003 SW 2001 10 24 HEEA076355 1 20011003 G 3212 212073905001 GAUGE 407073848101 BELL 407 407 1182206 SW FLOAT BOTTLE DAMAGED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 495PH 242 53397 NEEDLE STICKING AND FACE CRACKED. TO BE RETURNED TO BELL HELICOPTER TEXTRON FOR CREDIT AGAINST REPLACEMENT PART PURCHASE D. 1 G 7 1 3U O H2SW 2001102400004 20011024 00004 SW 2001 10 24 HEEA076356 1 20011003 G 6500 407340340101 DISC PACK BELL 407 407 1182206 SW TAIL ROTOR DRIVE CRACKED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 408PH 53228 NR 3 SHORT SHAFT FWD COUPLING DISK PACK FOUND CRACKED. 1 G 7 1 3U O H2SW 2001102400005 20011024 00005 SW 2001 10 24 HEEA076357 1 20011003 G 6500 407340340103 DISC PACK BELL 407 407 1182206 SW TAIL ROTOR DRIVE CRACKED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 405PH 53207 FWD COUPLING DISC ON NR 4 T/R SEGMENTED DRIVE SHAFT CRACKED. 1 G 7 1 3U O H2SW 2001102400006 20011024 00006 SW 2001 10 24 HEEA076358 1 20011003 G 6500 407340340103 DISC PACK BELL 407 407 1182206 SW TAIL ROTOR DRIVE CRACKED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 407PH 53003 CRACKED. TO BE RETURNED TO BELL HELICOPTER TEXTRON FOR CREDIT AGAINST REPLACEMENT PART PURCHASED. 1 G 7 1 3U O H2SW 2001102400007 20011024 00007 SW 2001 10 24 HEEA076359 1 20011003 G 3212 407350300101 FLOAT BELL 407 407 1182206 SW MLG TORN E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 493PH 53393 FLOAT BAG TORN. 1 G 7 1 3U O H2SW 2001102400008 20011024 00008 SW 2001 10 24 HEEA076360 1 20011003 G 3212 407350302101 FLOAT BELL 407 407 1182206 SW MLG LEAKING E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 405PH 53207 FLOAT BAG LEAKING. 1 G 7 1 3U O H2SW 2001102400009 20011024 00009 SW 2001 10 24 HEEA076361 1 20011003 G 2844 407362013101 PRESSURE SWITCH BELL 407 407 1182206 SW FUEL CELL MALFUNCTIONED E HEEA O OTHER N FALSE WARNING IN INSP/MAINT 1 SW 03 417PH 4129 53038 TRANSFER LIGHT WILL NOT GO OUT. 1 G 7 1 3U O H2SW 2001102400010 20011024 00010 SW 2001 10 24 HEEA076362 1 20011003 G 2844 407362013101 PRESSURE SWITCH BELL 407 407 1182206 SW FUEL CELL STUCK E HEEA K NONE L NO TEST IN INSP/MAINT 1 SW 03 495PH 53397 PRESSURE SWITCH STUCK IN OFF POSITION. 1 G 7 1 3U O H2SW 2001102400011 20011024 00011 SW 2001 10 24 HEEA076363 1 20011003 G 7712 407375003107 INDICATOR BELL 407 407 1182206 SW COCKPIT INOPERATIVE E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 4999 2556 53323 TORQUE INDICATOR LIGHT INOPERATIVE. 1 G 7 1 3U O H2SW 2001102400012 20011024 00012 SW 2001 10 24 HEEA076364 1 20011003 G 7714 407375008101 TACHOMETER BELL 407 407 1182206 SW COCKPIT WILL NOT TEST E HEEA K NONE L NO TEST IN INSP/MAINT 1 SW 03 405PH 3728 53207 ROTOR NEEDLE FAILS BIT TEST. 1 G 7 1 3U O H2SW 2001102400013 20011024 00013 SW 2001 10 24 HEEA076365 1 20011003 G 3210 70079H000Y150 HOSE BELL 407 407 1182206 SW MLG KINKED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 612PH 53199 HOSE ASSY KINKED. 1 G 7 1 3U O H2SW 2001102400014 20011024 00014 SW 2001 10 24 HEEA076366 1 20011003 G 3212 8226003 FUSEABLE PLUG BELL 407 407 1182206 SW FLOAT BOTTLE LEAKING E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 612PH 53199 LT FLOAT BOTTLE LEAKING AT CENTER OF FUSIBLE PLUG. 1 G 7 1 3U O H2SW 2001102400015 20011024 00015 SW 2001 10 24 HEEA076367 1 20011003 G 3212 8226003 FUSEABLE PLUG BELL 407 407 1182206 SW FLOAT BOTTLE FAILED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 722PH 53288 FUSIBLE PLUG FAILED RELEASING ALL PRESSURE FROM FLOAT BOTTLE. 1 G 7 1 3U O H2SW 2001102400016 20011024 00016 SW 2001 10 24 HEEA076371 1 20011003 G 6300 SPLINE ADAPTER PHIPBH40701 BELL 407 407 1182206 SW COOLER BLOWER WORN E K NONE O OTHER IN INSP/MAINT 1 SW 03 406PH PHI0010 53198 WORN SPLINES. 1 G 7 1 3U O H2SW 2001102400017 20011024 00017 SW 2001 10 24 HEEA076372 1 20011003 G 6300 407340339101 BEARING PHIPBH40701 BELL 407 407 1182206 SW COOLER BLOWER OVERHEATED E HEEA K NONE M OVER TEMP IN INSP/MAINT 1 SW 03 407PH PHI0013 53003 OIL COOLER BLOWER BEARING OVERHEATED. 1 G 7 1 3U O H2SW 2001102400018 20011024 00018 SW 2001 10 24 HEEA076375 1 20011003 G 6300 407340339103 BEARING PHIPBH40701 BELL 407 407 1182206 SW COOLER BLOWER ROUGH E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 409PH PHI0019 53059 BEARING ROUGH. 1 G 7 1 3U O H2SW 2001102400019 20011024 00019 SW 2001 10 24 HEEA076376 1 20011003 G 6300 BEARING PHIPBH40701 BELL 407 407 1182206 SW COOLER BLOWER ROUGH E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 57416 PHI0022 53070 WORN AND ROUGH BEARINGS. 1 G 7 1 3U O H2SW 2001102400020 20011024 00020 SW 2001 10 24 HEEA076378 1 20011003 G 6300 407340339103 BEARING PHIPBH40701 BELL 407 407 1182206 SW COOLER BLOWER WORN E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 447PH PHI0031 53114 COOLER BLOWER BEARING IS WORN. 1 G 7 1 3U O H2SW 2001102400021 20011024 00021 SW 2001 10 24 HEEA076383 1 20011003 G 6520 PHI407112 BOOT BELL 407 407 1182206 SW TAIL ROTOR LEAKING E HEEA K NONE K FLUID LOSS IN INSP/MAINT 1 SW 03 405PH 53207 BOOT SEAL LEAKING. 1 G 7 1 3U O H2SW 2001102400022 20011024 00022 SW 2001 10 24 HEEA076384 1 20011003 G 6520 PHI407112 BOOT BELL 407 407 1182206 SW TAIL ROTOR LEAKING E HEEA K NONE K FLUID LOSS IN INSP/MAINT 1 SW 03 409PH 53059 BOOT SEAL LEAKING. 1 G 7 1 3U O H2SW 2001102400023 20011024 00023 SW 2001 10 24 HEEA076385 1 20011003 G 6720 BUSHING PHI407112 BELL 407 407 1182206 SW IDLER WORN E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 493PH 53393 WEAR ON BUSHINGS. 1 G 7 1 3U O H2SW 2001102400024 20011024 00024 SW 2001 10 24 HEEA076386 1 20011003 G 2822 1C2710 CARTRIDGE BELL 407 407 1182206 SW BOOST PUMP INOPERATIVE E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 724PH 53327 INOPERATIVE. REPLACED WITH SERVICEABLE BOOST PUMP CARTRIDGE. 1 G 7 1 3U O H2SW 2001102400025 20011024 00025 SW 2001 10 24 HEEA076387 1 20011003 G 2435 BRUSHES BELL 407 407 1182206 SW STARTER GEN WORN E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 490PH 2239 53378 STARTER GEN BRUSHES FAILED INSPECTION. 1 G 7 1 3U O H2SW 2001102400026 20011024 00026 GL 2001 10 24 HEEA076388 2 20011003 G 7320 23007827 VALVE BELL 407 407 1182206 SW ALLSN 250C 250C47B GL ENGINE STUCK E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 724PH 53327 VALVE STICKING. REPLACED WITH SERVICEABLE VALVE. 1 G 7 1 3U 3 U O H2SW E1GL 2001102400027 20011024 00027 SW 2001 10 24 HEEA076389 1 20011003 G 6300 406310405101 BEARING BELL 407 407 1182206 SW UNIVERSAL WORN E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 724PH 53327 WORN BEARING. 1 G 7 1 3U O H2SW 2001102400028 20011024 00028 SW 2001 10 24 HEEA076390 1 20011003 G 6710 406310405101 UNIVERSAL BELL 407 407 1182206 SW MAIN ROTOR WORN E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 724PH 53327 WORN BEARING. 1 G 7 1 3U O H2SW 2001102400029 20011024 00029 SW 2001 10 24 HEEA076391 1 20011003 G 6230 406310411101 BOOT BELL 407 407 1182206 SW MAIN ROTOR TORN E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 447PH 53114 BOOT TORN. 1 G 7 1 3U O H2SW 2001102400030 20011024 00030 SW 2001 10 24 HEEA076392 1 20011003 G 6720 406312103101 LINK BELL 407 407 1182206 SW TAIL ROTOR WORN E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 612PH 53199 WORN BEARINGS. 1 G 7 1 3U O H2SW 2001102400031 20011024 00031 SW 2001 10 24 HEEA076394 1 20011003 G 6210 407015001117 BLADE BELL 407 407 1182206 SW MAIN ROTOR CRACKED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 406PH 3924 53198 MAIN ROTOR BLADE IS CRACKED. 1 G 7 1 3U O H2SW 2001102400032 20011024 00032 SW 2001 10 24 HEEA076395 1 20011003 G 6510 407340339101 BEARING 407040302107 BELL 407 407 1182206 SW T/R DRIVESHAFT ROUGH E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 491PH A1937 53386 TAIL ROTOR DRIVESHAFT BEARING ROUGH. 1 G 7 1 3U O H2SW 2001102400034 20011024 00034 SW 2001 10 24 HEEA076396 1 20011003 G 7120 BEARING BELL 407 407 1182206 SW BIPOD MOUNT WORN E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 724PH 53327 BIPOD MOUNT HAS A WORN BEARING. 1 G 7 1 3U O H2SW 2001102400035 20011024 00035 SW 2001 10 24 HEEA076397 1 20011003 G 7120 BEARING BELL 407 407 1182206 SW BIPOD MOUNT WORN E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 407PH 53003 WORN BEARING. 1 G 7 1 3U O H2SW 2001102400036 20011024 00036 SW 2001 10 24 HEEA076398 1 20011003 G 6510 407340340103 DISC PACK BELL 407 407 1182206 SW TAIL ROTOR CRACKED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 4999 53323 TAIL ROTOR DISC PACK IS CRACKED. 1 G 7 1 3U O H2SW 2001102400037 20011024 00037 SW 2001 10 24 HEEA076399 1 20011003 G 7933 407375005101 INDICATOR BELL 407 407 1182206 SW XMSN OIL TEMP MALFUNCTIONED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 492PH 53390 TRANSMISSION OIL TEMP INDICATOR SHOWED ONLY 2 BAR SEGMENTS. 1 G 7 1 3U O H2SW 2001102400038 20011024 00038 2001 10 24 HEEA076400 4 20011003 G 3421 50400179015 ADI BELL 407 407 1182206 SW COCKPIT FAILED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 406PH 53198 FLAG DOES NOT PULL AND GAUGE DOES NOT CORRESPOND TO ATTITUDE. REPLACED WITH SERVICEABLE ATTITUDE IND. 1 G 7 1 3U O H2SW 2001102400039 20011024 00039 2001 10 24 HEEA076401 4 20011003 G 3421 50400179015 ADI BELL 407 407 1182206 SW COCKPIT FAILED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 406PH 53198 ATTITUDE INDICATOR STAYS IN LEFT TURN. REPLACED WITH SERVICEABLE ATTITUDE IND. 1 G 7 1 3U O H2SW 2001102400040 20011024 00040 SW 2001 10 24 HEEA076403 1 20011003 G 6300 BEARING PHIPBH40701F BELL 407 407 1182206 SW COOLER BLOWER ROUGH E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 491PH PHI0015 53386 OIL COOLER BLOWER HAS ROUGH BEARINGS. 1 G 7 1 3U O H2SW 2001102400041 20011024 00041 SW 2001 10 24 HEEA076404 1 20011003 G 3213 407050201101 CROSSTUBE BELL 407 407 1182206 SW MLG CORRODED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 57416 53070 FORWARD CROSSTUBE HAS CORROSION. SCRAPPED AND REPLACED WITH SERVICEABLE CROSSTUBE. 1 G 7 1 3U O H2SW 2001102400042 20011024 00042 SW 2001 10 24 HEEA076405 1 20011003 G 3213 407050202101 CROSSTUBE BELL 407 407 1182206 SW MLG CORRODED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 57416 53070 AFT CROSSTUBE HAS CORROSION. SCRAPPED AND REPLACED WITH SERVICEABLE CROSSTUBE. 1 G 7 1 3U O H2SW 2001102400043 20011024 00043 SW 2001 10 24 HEEA076406 1 20011003 G 2510 407070720117 SEAT BACK BELL 407 407 1182206 SW COCKPIT TORN E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 722PH 53288 TORN. SCRAPPED AND REPLACED WITH SERVICEABLE SEAT BACK. 1 G 7 1 3U O H2SW 2001102400044 20011024 00044 SW 2001 10 24 HEEA076407 1 20011003 G 5210 407070620137 PANEL BELL 407 407 1182206 SW CREW DOOR CRACKED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 496PH 53398 CRACKS. SCRAPPED AND REPLACED WITH SERVICEABLE PANEL. 1 G 7 1 3U O H2SW 2001102400045 20011024 00045 SW 2001 10 24 HEEA076408 1 20011003 G 5210 407070620138 PANEL BELL 407 407 1182206 SW CREW DOOR CRACKED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 722PH 53288 CRACKED AND BROKEN IN SEVERAL PLACES. SCRAPPED AND REPLACED WITH SERVICEABLE PANEL. 1 G 7 1 3U O H2SW 2001102400046 20011024 00046 SW 2001 10 24 HEEA076409 1 20011003 G 5210 407070620138 PANEL BELL 407 407 1182206 SW CREW DOOR CRACKED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 493PH 53393 SEVERAL CRACKS. SCRAPPED AND REPLACED WITH SERVICEABLE PANEL. 1 G 7 1 3U O H2SW 2001102400047 20011024 00047 SW 2001 10 24 HEEA076410 1 20011003 G 5230 407070620143 PANEL BELL 407 407 1182206 SW CARGO DOOR CRACKED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 612PH 53199 LITTER DOOR PANEL CRACKED. SCRAPPED AND REPLACED WITH SERVICEABLE PANEL. 1 G 7 1 3U O H2SW 2001102400048 20011024 00048 SW 2001 10 24 HEEA076411 1 20011003 G 5230 407070620157 PANEL BELL 407 407 1182206 SW CARGO DOOR CRACKED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 405PH 53207 LT REAR DOOR PANEL HAS NUMEROUS CRACKS. SCRAPPED AND REPLACED WITH SERVICEABLE PANEL. 1 G 7 1 3U O H2SW 2001102400049 20011024 00049 SW 2001 10 24 HEEA076412 1 20011003 G 5210 407070620157 PANEL BELL 407 407 1182206 SW CREW DOOR CRACKED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 496PH 53398 DOOR TRIM PANEL CRACKED. SCRAPPED AND REPLACED WITH SERVICEABLE PANEL. 1 G 7 1 3U O H2SW 2001102400050 20011024 00050 SW 2001 10 24 HEEA076413 1 20011003 G 5210 407070620157 PANEL BELL 407 407 1182206 SW CREW DOOR CRACKED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 612PH 53199 LT PASSENGER DOOR PANEL CRACKED. SCRAPPED AND REPLACED WITH SERVICEABLE PANEL. 1 G 7 1 3U O H2SW 2001102400051 20011024 00051 SW 2001 10 24 HEEA076414 1 20011003 G 5210 407070620158 PANEL BELL 407 407 1182206 SW CREW DOOR CRACKED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 496PH 53398 CRACKED PANEL. SCRAPPED AND REPLACED WITH SERVICEABLE PANEL. 1 G 7 1 3U O H2SW 2001102400052 20011024 00052 SW 2001 10 24 HEEA076415 1 20011003 G 5230 407070620158 PANEL BELL 407 407 1182206 SW CARGO DOOR CRACKED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 612PH 53199 RT REAR DOOR PANEL CRACKED. SCRAPPED AND REPLACED WITH SERVICEABLE PANEL. 1 G 7 1 3U O H2SW 2001102400053 20011024 00053 SW 2001 10 24 HEEA076416 1 20011003 G 5210 407070620179 PANEL BELL 407 407 1182206 SW CREW DOOR CRACKED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 496PH 53398 DOOR PANEL CRACKED. SCRAPPED AND REPLACED WITH SERVICEABLE PANEL. 1 G 7 1 3U O H2SW 2001102400054 20011024 00054 SW 2001 10 24 HEEA076417 1 20011003 G 5310 407070620180 PANEL BELL 407 407 1182206 SW DOOR FRAME CRACKED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 493PH 53393 PILOT DOOR POST TRIM PANEL CRACKED. SCRAPPED AND REPLACED WITH SERVICEABLE PANEL. 1 G 7 1 3U O H2SW 2001102400055 20011024 00055 SW 2001 10 24 HEEA076418 1 20011003 G 5230 407070620205 COVER BELL 407 407 1182206 SW CARGO DOOR CRACKED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 496PH 53398 LITTER DOOR LATCH COVER CRACKED. SCRAPPED AND REPLACED WITH SERVICEABLE COVER. 1 G 7 1 3U O H2SW 2001102400056 20011024 00056 SW 2001 10 24 HEEA076419 1 20011003 G 5210 407070620217 PANEL BELL 407 407 1182206 SW CREW DOOR CRACKED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 405PH 53207 PANEL CRACKED. SCRAPPED AND REPLACED WITH SERVICEABLE PANEL. 1 G 7 1 3U O H2SW 2001102400057 20011024 00057 SW 2001 10 24 HEEA076420 1 20011003 G 5210 407070620218 PANEL BELL 407 407 1182206 SW CREW DOOR CRACKED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 405PH 53207 PANEL CRACKED. SCRAPPED AND REPLACED WITH SERVICEABLE PANEL. 1 G 7 1 3U O H2SW 2001102400058 20011024 00058 SW 2001 10 24 HEEA076421 1 20011003 G 5230 407070620205 COVER BELL 407 407 1182206 SW CARGO DOOR CRACKED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 612PH 53199 LITTER DOOR LATCH COVER CRACKED. SCRAPPED AND REPLACED WITH SERVICEABLE COVER. 1 G 7 1 3U O H2SW 2001102400059 20011024 00059 SW 2001 10 24 HEEA076422 1 20011003 G 5210 407070620218 PANEL BELL 407 407 1182206 SW CREW DOOR CRACKED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 612PH 53199 PANEL CRACKED. SCRAPPED AND REPLACED WITH SERVICEABLE PANEL. 1 G 7 1 3U O H2SW 2001102400060 20011024 00060 SW 2001 10 24 HEEA076423 1 20011003 G 2510 407070622115 SEAT BELL 407 407 1182206 SW ARM REST CRACKED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 612PH 53199 LT AFT FACING SEAT ARM REST FABRIC TORN. SCRAPPED AND REPLACED WITH SERVICEABLE ARM REST. 1 G 7 1 3U O H2SW 2001102400061 20011024 00061 2001 10 24 HEEA076424 4 20011003 G 2312 064100900 TRANSCEIVER BELL 412 412 1182202 SW RADIO SYSTEM MALFUNCTIONED E HEEA K NONE L NO TEST IN INSP/MAINT 1 SW 03 5759N 33002 WEAK AND GARBLED. IN SHOP REPAIR. 1 G 7 2 4U H4SW 2001102400062 20011024 00062 2001 10 24 HEEA076425 4 20011003 G 2312 064101900 TRANSCEIVER BELL 206 206L3 1182108 SW RADIO SYSTEM MALFUNCTIONED E HEEA K NONE L NO TEST IN INSP/MAINT 1 SW 03 3116P 51530 DOES NOT RECEIVE. IN SHOP REPAIR. 1 G 7 1 3U H2SW 2001102400063 20011024 00063 2001 10 24 HEEA076426 4 20011003 G 3452 066106200 TRANSCEIVER BELL 206 206L3 1182108 SW ATC SYSTEM MALFUNCTIONED E HEEA K NONE L NO TEST IN INSP/MAINT 1 SW 03 21497 51518 WOULD NOT TRANSMIT POWER MODE C SIGNALS. IN SHOP REPAIR. 1 G 7 1 3U H2SW 2001102400064 20011024 00064 2001 10 24 HEEA076427 4 20011003 G 3451 066106600 TRANSCEIVER BELL 412 412 1182202 SW DME SYSTEM MALFUNCTIONED E HEEA K NONE L NO TEST IN INSP/MAINT 1 SW 03 6559Z 36019 DME SYSTEM TRANSCEIVER INOPERATIVE; WILL NOT COME ON. REPLACED WITH SERVICEABLE PART. 1 G 7 2 4U H4SW 2001102400065 20011024 00065 2001 10 24 HEEA076428 4 20011003 G 3452 066107100 TRANSPONDER BELL 412 412 1182202 SW ATC SYSTEM MALFUNCTIONED E HEEA K NONE L NO TEST IN INSP/MAINT 1 SW 03 2149S 36002 TRANSMIT OFF FREQUENCY AND REPLY RATE IS LOW AND ERRATIC. REPLACED WITH SERVICEABLE PART. 1 G 7 2 4U H4SW 2001102400066 20011024 00066 2001 10 24 HEEA076429 4 20011003 G 3416 066304400 ALTIMETER BELL 412 412 1182202 SW RADAR MALFUNCTIONED E HEEA K NONE L NO TEST IN INSP/MAINT 1 SW 03 2149S 36002 KEEPS CYCLING AFTER PUSHING TEST BUTTON. PENDING VENDOR REPAIR. 1 G 7 2 4U H4SW 2001102400067 20011024 00067 2001 10 24 HEEA076430 4 20011003 G 3453 066402600 TRANSCEIVER LORAN SYSTEM MALFUNCTIONED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 DISPLAY REMAINED BLANK AFTER BEING ON FOR 10 MINUTES AND REMAINED BLANK AFTERWARDS. PENDING VENDOR REPAIR. 2001102400068 20011024 00068 2001 10 24 HEEA076431 4 20011003 G 3452 071119218 CONTROL UNIT BELL 412 412 1182202 SW TRANSPONDER WILL NOT TEST E HEEA K NONE L NO TEST IN INSP/MAINT 1 SW 03 142PH 33150 WON'T TEST PROPERLY. REPLACED WITH SERVICEABLE PART. 1 G 7 2 4U H4SW 2001102400069 20011024 00069 SW 2001 10 24 HEEA076432 1 20011003 G 5520 205030856131 STRUCTURE BELL 412 412 1182202 SW ELEVATOR CRACKED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 5759N 33002 SHEETMETAL CRACK WHERE SPAR IS MOUNTED TO ELEVATOR. REPLACED WITH SERVICEABLE PART. 1 G 7 2 4U H4SW 2001102400070 20011024 00070 SW 2001 10 24 HEEA076433 1 20011003 G 6700 BEARING BELL 206 206L3 1182108 SW BELLCRANK WORN E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 6251X 51552 BEARINGS WORN. REPLACED WITH SERVICEABLE PART. 1 G 7 1 3U H2SW 2001102400071 20011024 00071 SW 2001 10 24 HEEA076434 1 20011003 G 6220 206011117003 RESTRAINT BELL 206 206L3 1182108 SW MAIN ROTOR HEAD STUCK E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 4180F STICKS IN THE DOWN POSITION. REPLACED WITH SERVICEABLE PART. 1 G 7 1 3U H2SW 2001102400079 20011024 00079 SW 2001 10 24 HEEA076435 1 20011003 G 6220 206011117003 RESTRAINT BELL 206 206L3 1182108 SW MAIN ROTOR HEAD STUCK E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 4835 51131 STICKING IN RETRACT POSITION. REPLACED WITH SERVICEABLE PART. 1 G 7 1 3U H2SW 2001102400086 20011024 00086 SW 2001 10 24 HEEA076436 1 20011003 G 6320 206040088005 VALVE BELL 206 206L3 1182108 SW MAIN ROTOR MISMANUFACTURED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 IMPROPERLY MANUFACTURED THREADS, CANNOT BE INSTALLED INTO TRANSMISSION CASE WITHOUT CAUSING DAMAGE TO CASE THREADS. TRI ED TO INSTALL VALVE INTO TWO DIFFERENT CASES AND COULD NOT. 1 G 7 1 3U H2SW 2001102400087 20011024 00087 SW 2001 10 24 HEEA076437 1 20011003 G 6320 206040190005 PUMP BELL 206 206L3 1182108 SW MAIN ROTOR LEAKING E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 4835 51131 LEAKS PAST SEAL. REPLACED WITH SERVICEABLE PUMP. 1 G 7 1 3U H2SW 2001102400127 20011024 00127 SW 2001 10 24 HEEA076438 1 20011003 G 6710 206062721109 ACTUATOR BELL 206 206L1 1182107 SW M/R CONTROL INOPERATIVE E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 5014Y 45219 INOPERATIVE NO EXTENSION OR RETRACTION OF CONTROL SHAFT. REPLACED WITH SERVICEABLE ACTUATOR. 1 G 7 1 3U H2SW 2001102400130 20011024 00130 SW 2001 10 24 HEEA076439 1 20011003 G 3212 206073926109 VALVE BELL 412 412 1182202 SW MLG LEAKING E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 107X 33113 LEAKS ABOVE 2900 PSI. REPLACED WITH SERVICEABLE VALVE. 1 G 7 2 4U H4SW 2001102400132 20011024 00132 SW 2001 10 24 HEEA076440 1 20011003 G 3213 206323017 CROSSTUBE BELL 206 206L3 1182108 SW MLG CORRODED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 53119 51575 CORRODED BEYOND LIMITS AT SUPPORT MOUNT AREA, MEASURED .010 INCHES IN ZONE 1. REPLACED WITH SERVICEABLE CROSSTUBE. 1 G 7 1 3U H2SW 2001102400133 20011024 00133 SW 2001 10 24 HEEA076441 1 20011003 G 3213 206323018 CROSSTUBE BELL 206 206L3 1182108 SW MLG CORRODED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 53119 51575 CORRODED BEYOND LIMITS AT SUPPORT MOUNT AREA, MEASURED .010 INCHES IN ZONE 1. REPLACED WITH SERVICEABLE CROSSTUBE. 1 G 7 1 3U H2SW 2001102400134 20011024 00134 SW 2001 10 24 HEEA076442 1 20011004 G 3246 206324008 SKID BELL 206 206L3 1182108 SW MLG CRACKED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 31821 51076 18 INCH CRACK AT LOWER SIDE SKID TUBE. REPLACED WITH SERVICEABLE SKID TUBE. 1 G 7 1 3U H2SW 2001102400135 20011024 00135 SW 2001 10 24 HEEA076443 1 20011004 G 5260 206331119 STEP BELL 206 206L3 1182108 SW FUSELAGE CORRODED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 53119 51575 INTERGRANULAR CORROSION BEYOND LIMITS AT MOUNT AREA. REPLACED WITH SERVICEABLE STEP. 1 G 7 1 3U H2SW 2001102400136 20011024 00136 SW 2001 10 24 HEEA076444 1 20011004 G 5260 206331120 STEP BELL 206 206L3 1182108 SW FUSELAGE CORRODED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 53119 51575 INTERGRANULAR CORROSION BEYOND LIMITS AT MOUNT AREA. REPLACED WITH SERVICEABLE STEP. 1 G 7 1 3U H2SW 2001102400137 20011024 00137 SW 2001 10 24 HEEA076445 1 20011004 G 7933 206375007103 INDICATOR BELL 206 206L3 1182108 SW OVERTEMP WILL NOT TEST E HEEA K NONE L NO TEST IN INSP/MAINT 1 SW 03 3116P 51530 OVERTEMP LIGHT WILL NOT TEST. PENDING VENDOR REPAIR. 1 G 7 1 3U H2SW 2001102400138 20011024 00138 SW 2001 10 24 HEEA076446 1 20011004 G 7921 209062501005 OIL COOLER BELL 412 412 1182202 SW ENGINE LEAKING E HEEA K NONE K FLUID LOSS IN INSP/MAINT 1 SW 03 2149S 36002 LEAKING. PENDING VENDOR REPAIR. 1 G 7 2 4U H4SW 2001102400145 20011024 00145 SW 2001 10 24 HEEA076447 1 20011004 G 7600 212061101001 BEARING BELL 412 412 1182202 SW ENGINE CONTROLS WORN E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 1202T 33112 WORN BEARING. REPLACED WITH SERVICEABLE BEARING. 1 G 7 2 4U H4SW 2001102400146 20011024 00146 2001 10 24 HEEA076448 4 20011004 G 3100 212070262101 INDICATOR BELL 412 412 1182202 SW COCKPIT MALFUNCTIONED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 5759N 33002 PRESSURE NEEDLE STICKS AFTER START UP ONLY SHOWS PRESSURE IF GAUGE IS TAPPED. REPLACED WITH SERVICEABLE INDICATOR. 1 G 7 2 4U H4SW 2001102400147 20011024 00147 SW 2001 10 24 HEEA076449 1 20011004 G 5260 212075418105 STEP BELL 412 412 1182202 SW FUSELAGE FAILED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 6559Z 36019 WILL NOT EXTEND. PENDING VENDOR REPAIR. 1 G 7 2 4U H4SW 2001102400148 20011024 00148 SW 2001 10 24 HEEA076450 1 20011004 G 6730 212076004101 SERVO BELL 412 412 1182202 SW TAIL ROTOR LEAKING E HEEA K NONE K FLUID LOSS IN INSP/MAINT 1 SW 03 107X 33113 LEAKING. REPLACED WITH SERVICEABLE SERVO. 1 G 7 2 4U H4SW 2001102400149 20011024 00149 SW 2001 10 24 HEEA076451 1 20011004 G 6730 212076005111 SERVO BELL 412 412 1182202 SW TAIL ROTOR STIFF E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 2261D 33076 MOVEMENTS ARE STIFFENED AND VERY HARD TO MOVE. REPLACED WITH SERVICEABLE SERVO. 1 G 7 2 4U H4SW 2001102400151 20011024 00151 SW 2001 10 24 HEEA076452 1 20011004 G 6710 214001347005 ACTUATOR BELL 412 412 1182202 SW ROTARY STUCK E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 1202T 33112 STICKING. PENDING VENDOR REPAIR. 1 G 7 2 4U H4SW 2001102400153 20011024 00153 GL 2001 10 24 HEEA076453 2 20011004 G 7532 23005366 BLEED VALVE BELL 206 206L3 1182108 SW ALLSN 250C 250C30 03013 GL ENGINE MALFUNCTIONED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 6251X 7023 51552 HIGH TOT, DIDN'T CLOSE SMOOTHLY WHEN PRESSURE WAS APPLIED. REPLACED WITH SERVICEABLE BLEED VALVE. 1 G 7 1 3U 3 U H2SW E1GL 2001102400154 20011024 00154 GL 2001 10 24 HEEA076454 2 20011004 G 7310 23005667 LINE BELL 206 206L3 1182108 SW ALLSN 250C 250C30 03013 GL FUEL SYSTEM CRACKED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 21497 51518 LINE IS CRACKED AT FLARE. REPLACED WITH SERVICEABLE LINE. 1 G 7 1 3U 3 U H2SW E1GL 2001102400157 20011024 00157 GL 2001 10 24 HEEA076455 2 20011004 G 7310 23007827 SOLENOID VALVE BELL 206 206L3 1182108 SW ALLSN 250C 250C30 03013 GL FUEL SYSTEM STUCK E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 3108E 51498 STICKS INTERMITTENTLY. REPLACED WITH SOLENOID VALVE. 1 G 7 1 3U 3 U H2SW E1GL 2001102400158 20011024 00158 SW 2001 10 24 HEEA076456 1 20011004 G 7120 23069751 MOUNT BELL 206 206L3 1182108 SW ENGINE DAMAGED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 31077 51520 BEARING CAME UNSTAKED. REPLACED WITH SERVICEABLE MOUNT. 1 G 7 1 3U H2SW 2001102400159 20011024 00159 GL 2001 10 24 HEEA076457 2 20011004 G 7323 252469211 GOVERNOR BELL 206 206L1 1182107 SW ALLSN 250C 250C30 03013 GL ENGINE MALFUNCTIONED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 5014V 13616 45217 N2 DROOP TO 97 PERCENT. COMPLETED DROOP COMPENSATION ADJUSTMENTS AND COMPLETED OPERATIONAL CHECK. FOUND ACCEPTABLE. A FTER 2:45 ADDITIONAL FLIGHT HOURS REPORTED N2 DROOP TO 97 PERCENT WITH N2 OVERSPEED TO 102 PERCENT. REPLACED WITH SERVIC EABLE GOVERNOR. 1 G 7 1 3U 3 U H2SW E1GL 2001102400164 20011024 00164 NE 2001 10 24 HEEA076458 2 20011004 G 7323 25249994 GOVERNOR BELL 412 412 1182202 SW PWA PT6T PT6T3B 52045 NE FREE TURBINE MALFUNCTIONED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 2149S 36002 NR 2 ENGINE SURGES. REPLACED WITH SERVICEABLE GOVERNOR. 1 G 7 2 4U 4 U H4SW E22EA 2001102400168 20011024 00168 NE 2001 10 24 HEEA076459 2 20011004 G 7323 25249994 GOVERNOR BELL 412 412 1182202 SW PWA PT6T PT6T3B 52045 NE FREE TURBINE MALFUNCTIONED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 2149S 36002 ENGINE OSCILLATES CONSTANTLY 1 TO 3 PERCENT N1 WITH ITT FLUCTUATIONS. REPLACED WITH SERVICEABLE GOVERNOR. 1 G 7 2 4U 4 U H4SW E22EA 2001102400170 20011024 00170 NE 2001 10 24 HEEA076460 2 20011004 G 7323 25249994 GOVERNOR BELL 412 412 1182202 SW PWA PT6T PT6T3B 52045 NE FREE TURBINE MALFUNCTIONED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 800Y 33134 SURGING. REPLACED WITH SERVICEABLE GOVERNOR. 1 G 7 2 4U 4 U H4SW E22EA 2001102400171 20011024 00171 SW 2001 10 24 HEEA076461 1 20011004 G 7603 THROTTLE BELL 206 206L3 1182108 SW ENGINE CONTROLS STIFF E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 31077 51520 THROTTLE STIFF. REPLACED WITH SERVICEABLE FUEL CONTROL. 1 G 7 1 3U H2SW 2001102400173 20011024 00173 SW 2001 10 24 HEEA076462 1 20011004 G 7603 THROTTLE BELL 206 206L3 1182108 SW FUEL CONTROL STIFF E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 31077 51520 THROTTLE STIFF. REPLACED WITH SERVICEABLE FUEL CONTROL. 1 G 7 1 3U H2SW 2001102400179 20011024 00179 2001 10 24 HEEA076463 4 20011004 G 2200 2593996333 TARSYN BELL 412 412 1182202 SW AUTOFLIGHT MALFUNCTIONED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 3893L 33006 COMPASS CONTROL PANEL NEEDLE FLIPPING CONSTANTLY. PENDING VENDOR REPAIR. 1 G 7 2 4U H4SW 2001102400183 20011024 00183 EA 2001 10 24 HEEA076464 2 20011004 G 7532 DIAPHRAGM 3033063 BELL 212 212 1181420 SW PWA PT6T PT6T3 52045 EA BLEED VALVE DAMAGED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 102PH 2A599 30899 INCREASE OF 40 DEGREES ITT AND 4 PERCENT N1 AT POWER CHECK SETTINGS. FOUND HOLE IN DIAPHRAGM. REPLACED WITH SERVICEABLE DIAPHRAGM. 1 G 7 1 4U 4 U H4SW E22EA 2001102400184 20011024 00184 SW 2001 10 24 HEEA076465 1 20011004 G 7100 32447066 CONTROL UNIT BELL 412 412 1182202 SW TORQUE FAILED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 2149S 36002 CAUSING TORQUE SPLITS. REPLACED WITH SERVICEABLE TORQUE CONTROL UNIT. 1 G 7 2 4U H4SW 2001102400195 20011024 00195 NE 2001 10 24 HEEA076466 2 20011004 G 7320 324473514 FUEL CONTROL BELL 412 412 1182202 SW PWA PT6T PT6T3B 52045 NE ENGINE MALFUNCTIONED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 2149S 36002 ENGINE SURGING DURING POWER CHANGES CAUSING AIRCRAFT TO YAW. REPLACED WITH SERVICEABLE FUEL CONTROL. 1 G 7 2 4U 4 U H4SW E22EA 2001102400198 20011024 00198 2001 10 24 HEEA076467 4 20011004 G 3442 4000023010 RADAR BELL 206 206L3 1182108 SW WX RADAR SYS MALFUNCTIONED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 42EA 51542 NO MODULATION OUT. REPLACED WITH SERVICEABLE RT-15. 1 G 7 1 3U H2SW 2001102400200 20011024 00200 2001 10 24 HEEA076468 4 20011004 G 3442 4000038 CONTROL HEAD BELL 206 206L3 1182108 SW WX RADAR MALFUNCTIONED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 42EA 51542 HAS DEAD SPOT ON VOLUME CONTROL. REPLACED WITH SERVICEABLE PART. 1 G 7 1 3U H2SW 2001102400202 20011024 00202 SW 2001 10 24 HEEA076469 1 20011004 G 6210 412015300109 BLADE BELL 412 412 1182202 SW MAIN ROTOR DAMAGED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 2149S 36002 UNABLE TO TRACK. REPLACED WITH SERVICEABLE BLADE. 1 G 7 2 4U H4SW 2001102400203 20011024 00203 SW 2001 10 24 HEEA076470 1 20011004 G 6210 412015300109 BLADE BELL 412 412 1182202 SW MAIN ROTOR DAMAGED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 2149S 36002 LEADING EDGE EROSION. REPLACED WITH SERVICEABLE BLADE. 1 G 7 2 4U H4SW 2001102400204 20011024 00204 SW 2001 10 24 HEEA076471 1 20011004 G 3212 412050013109 FLOAT BELL 412 412 1182202 SW MLG LEAKING E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 6559Z 36019 LEAKING. PENDING VENDOR REPAIR. 1 G 7 2 4U H4SW 2001102400205 20011024 00205 SW 2001 10 24 HEEA076472 1 20011004 G 3212 412050017135 COVER BELL 412 412 1182202 SW FLOAT BAG WORN E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 6559Z 36019 WORN AND TORN. PENDING VENDOR REPAIR. 1 G 7 2 4U H4SW 2001102500001 20011025 00001 SW 2001 10 25 HEEA076473 1 20011004 G 3213 412050045107 CROSSTUBE BELL 412 412 1182202 SW MLG CORRODED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 800Y 3378 33134 CORRODED IN SEVERAL AREAS BEYOND LIMITS. THE CORRODED AREAS ARE NEAR THE SKID MOUNTS TO 18" TOWARD THE CENTER. RETURNIN G FOR CREDIT. 1 G 7 2 4U H4SW 2001102500002 20011025 00002 SW 2001 10 25 HEEA076475 1 20011004 G 6220 412310400101 BEARING BELL 412 412 1182202 SW MAIN ROTOR WORN E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 2149S 36002 WORN LOWER BEARING. REPLACED WITH SERVICEABLE BEARING. 1 G 7 2 4U H4SW 2001102500003 20011025 00003 SW 2001 10 25 HEEA076476 1 20011004 G 6320 41800044 TRANSMITTER BELL 412 412 1182202 SW M/R GEARBOX MALFUNCTIONED E HEEA O OTHER N FALSE WARNING NR NOT REPORTED 1 SW 03 3893N 33010 PRESSURE INDICATOR NEEDLE PEGGED OUT ON HIGH SIDE. REPLACED WITH SERVICEABLE TRANSMITTER. 1 G 7 2 4U H4SW 2001102500004 20011025 00004 2001 10 25 HEEA076477 4 20011004 G 3421 5040017928 INDICATOR BELL 412 412 1182202 SW ATTITUDE PRECESSES E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 107X 33113 INDICATOR PRECESSES 5-8 DEGREES. REPLACED WITH SERVICEABLE INDICATOR. 1 G 7 2 4U H4SW 2001102500005 20011025 00005 2001 10 25 HEEA076478 4 20011004 G 3130 6895D4655 SWITCH BELL 412 412 1182202 SW CVR MALFUNCTIONED E HEEA O OTHER L NO TEST NR NOT REPORTED 1 SW 03 107X 33113 CVR INTERMITTENTLY WON'T TEST. PENDING VENDOR REPAIR. 1 G 7 2 4U H4SW 2001102500006 20011025 00006 SW 2001 10 25 HEEA076479 1 20011004 G 2844 7G547 SWITCH BELL 206 206B3 1181506 SW FUEL PRESSURE FAILED E HEEA O OTHER J WARNING INDICATION NR NOT REPORTED 1 SW 03 22751 3627 FUEL PRESSURE SWITCH OPERATED CORRECTLY ON INSTALLATION - NEXT MORNING FUEL PUMP LIGHT CAME ON AND WOULD NOT GO OUT. REP LACED WITH SERVICEABLE SWITCH. 1 G 7 1 3U H2SW 2001102500007 20011025 00007 2001 10 25 HEEA076480 4 20011004 G 3442 7021450601 COMPUTER BELL 214 214ST 1182106 SW COCKPIT FAILED E O OTHER O OTHER NR NOT REPORTED 1 SW 03 5748M 28102 WEATHER RADAR SYSTEM DROPS OFF IN FLIGHT. PENDING VENDOR REPAIR. 2 G 7 2 4U H10SW 2001102500008 20011025 00008 2001 10 25 HEEA076481 4 20011004 G 2350 AA38300 AMPLIFIER BELL 412 412 1182202 SW ICS NOISY E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 142PH 33150 LOUD STATIC NOISE WHEN AIRCRAFT IS RUNNING. PENDING VENDOR RETURN. 1 G 7 2 4U H4SW 2001102500009 20011025 00009 2001 10 25 HEEA076482 4 20011004 G 2350 AA38300 AMPLIFIER BELL 412 412 1182202 SW ICS NOISY E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 142PH 33150 LOUD STATIC NOISE WHEN AIRCRAFT IS RUNNING. PENDING VENDOR RETURN. 1 G 7 2 4U H4SW 2001102500010 20011025 00010 SW 2001 10 25 HEEA076483 1 20011004 G 3213 AB412050016101 SKID SHOE BELL 412 412 1182202 SW MLG WORN E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 1202T 33112 WORN. REPLACED WITH SERVICEABLE SKID SHOE. 1 G 7 2 4U H4SW 2001102500011 20011025 00011 SW 2001 10 25 HEEA076484 1 20011004 G 3213 AB412050016102 SKID SHOE BELL 412 412 1182202 SW MLG WORN E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 6559Z 36019 WORN. REPLACED WITH SERVICEABLE SKID SHOE. 1 G 7 2 4U H4SW 2001102500012 20011025 00012 2001 10 25 HEEA076485 4 20011004 G 3442 MI5851345 INDICATOR BELL 412 412 1182202 SW RADAR SYSTEM FAILED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 2149S 36002 WON'T PAINT TARGETS ON 10 MILE SCALE. REPLACED WITH SERVICEABLE INDICATOR. 1 G 7 2 4U H4SW 2001102500013 20011025 00013 2001 10 25 HEEA076486 4 20011004 G 3442 MI5852013 INDICATOR BELL 412 412 1182202 SW RADAR SYSTEM FAILED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 3893L 33006 SCREEN GOES BLANK AND SHOWS YELLOW VERTICAL LINES. REPLACED WITH SERVICEABLE INDICATOR. 1 G 7 2 4U H4SW 2001102500014 20011025 00014 2001 10 25 HEEA076487 4 20011004 G 3442 MI5852013 INDICATOR BELL 412 412 1182202 SW RADAR SYSTEM FAILED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 3893L 33006 SCREEN SHRINKS. REPLACED WITH SERVICEABLE INDICATOR. 1 G 7 2 4U H4SW 2001102500015 20011025 00015 SW 2001 10 25 HEEA076488 1 20011004 G 2497 MS915872 SHUNT BELL 206 206L3 1182108 SW GENERATOR FAILED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 31077 51520 GENERATOR LIGHT ILLUMINATED IN FLIGHT AND GEN. WOULD RESET. REPLACED WITH SERVICEABLE SHUNT. 1 G 7 1 3U H2SW 2001102500016 20011025 00016 2001 10 25 HEEA076489 4 20011004 G 3421 PHI4121017601 INDICATOR BELL 412 412 1182202 SW ATTITUDE PRECESSES E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 3893L 33006 PRECESSES EXCESSIVELY. REPLACED WITH SERVICEABLE PART. 1 G 7 2 4U H4SW 2001102500017 20011025 00017 SW 2001 10 25 HEEA076490 1 20011004 G 5260 407301107 STEP BELL 407 407 1182206 SW FUSELAGE CORRODED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 409PH 53059 CORROSION BEYOND LIMITS. SCRAPPED. 1 G 7 1 3U O H2SW 2001102500018 20011025 00018 SW 2001 10 25 HEEA076491 1 20011004 G 5260 407301108 STEP BELL 407 407 1182206 SW FUSELAGE CORRODED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 409PH 53059 CORROSION BEYOND LIMITS. SCRAPPED. 1 G 7 1 3U O H2SW 2001102500019 20011025 00019 SW 2001 10 25 HEEA076492 1 20011004 G 6320 407375005101 INDICATOR BELL 407 407 1182206 SW XMSN OIL TEMP FAILED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 740PH 53435 NO TRANSMISSION TEMPERATURE INDICATION. INDICATOR READ ZERO. 1 G 7 1 3U O H2SW 2001102500020 20011025 00020 SW 2001 10 25 HEEA076495 1 20011005 G 3212 206050247137 COVER BELL 407 407 1182206 SW FLOAT WORN E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 4999 53323 FLOAT COVER HAS WORN END CAPS. 1 G 7 1 3U O H2SW 2001102500021 20011025 00021 SW 2001 10 25 HEEA076496 1 20011005 G 6510 206061432121 HOUSING BELL 407 407 1182206 SW COOLER BLOWER CRACKED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 499PH 53400 BLOWER HOUSING HAS A CRACKED AT CORNER. 1 G 7 1 3U O H2SW 2001102500022 20011025 00022 SW 2001 10 25 HEEA076497 1 20011005 G 6710 406310404101 ROD END BELL 407 407 1182206 SW MAIN ROTOR WORN E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 498PH 1749 53399 MAIN ROTOR ROD END HAS WORN BEARINGS. 1 G 7 1 3U O H2SW 2001102500023 20011025 00023 SW 2001 10 25 HEEA076498 1 20011005 G 6220 412010219101 BEARING BELL 412 412EP 1182205 SW PENDULUM DAMPER TORN E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 6106C 388 36257 SEAL ON PENDULUM DAMPER TORN CAUSING LOSS OF GREASE AND WEAR ON INNER RACE. 1 G 7 2 4U H4SW 2001102500024 20011025 00024 SW 2001 10 25 HEEA076499 1 20011005 G 6710 406310405101 UNIVERSAL BELL 407 407 1182206 SW MAIN ROTOR WORN E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 721PH 451 53278 UNIVERSAL WORN. 1 G 7 1 3U O H2SW 2001102500025 20011025 00025 SW 2001 10 25 HEEA076500 1 20011005 G 6720 BEARING BELL 407 407 1182206 SW LINK ASSY STUCK E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 4999 53323 STICKING BEARING. SENT TO BELL HELICOPTER TEXTRON FOR CREDIT AGAINST REPLACEMENT PART PURCHASED. REFERENCE: DMR#720438 . 1 G 7 1 3U O H2SW 2001102500026 20011025 00026 SW 2001 10 25 HEEA076501 1 20011005 G 6300 206362002103 CAP BELL 407 407 1182206 SW M/R DRIVE WORN E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 499PH 53400 WORN AND HARD TO OPEN. 1 G 7 1 3U O H2SW 2001102500027 20011025 00027 SW 2001 10 25 HEEA076502 1 20011005 G 6710 406310405101 UNIVERSAL BELL 407 407 1182206 SW MAIN ROTOR WORN E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 406PH 1246 53198 BEARING WORN. 1 G 7 1 3U O H2SW 2001102500028 20011025 00028 SW 2001 10 25 HEEA076503 1 20011005 G 2432 28SP100 CELL BELL 407 407 1182206 SW BATTERY BURNED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 501PH 53401 CELL BURNT. 1 G 7 1 3U O H2SW 2001102500029 20011025 00029 SW 2001 10 25 HEEA076504 1 20011005 G 7120 407060111101 MOUNT BELL 407 407 1182206 SW ENGINE WORN E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 407PH 53003 ONE BEARING WORN. 1 G 7 1 3U O H2SW 2001102500030 20011025 00030 SW 2001 10 25 HEEA076505 1 20011005 G 3212 206050247131 COVER BELL 407 407 1182206 SW FLOAT TORN E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 493PH 53393 TATTERED AND TORN. 1 G 7 1 3U O H2SW 2001102500034 20011025 00034 SW 2001 10 25 HEEA076506 1 20011005 G 6310 406040316101 ADAPTER BELL 407 407 1182206 SW ENG XMSN COUP WORN E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 494PH 53396 WORN SPLINES. SENT TO BELL HELICOPTER TEXTRON FOR CREDIT AGAINST REPLACEMENT PART PURCHASED. REFERENCE: DMR#720545. 1 G 7 1 3U O H2SW 2001102500035 20011025 00035 SW 2001 10 25 HEEA076507 1 20011005 G 6510 206061432121 HOUSING BELL 407 407 1182206 SW COOLER BLOWER CRACKED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 409PH 53059 COOLER BLOWER HOUSING CRACKED. 1 G 7 1 3U O H2SW 2001102500036 20011025 00036 SW 2001 10 25 HEEA076508 1 20011005 G 6510 206061432121 HOUSING BELL 407 407 1182206 SW COOLER BLOWER CRACKED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 57416 53070 COOLER BLOWER HOUSING CRACKED AND RIVETS WORKING. 1 G 7 1 3U O H2SW 2001102500037 20011025 00037 SW 2001 10 25 HEEA076509 1 20011005 G 3212 206050247131 COVER BELL 407 407 1182206 SW FLOAT TORN E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 723PH 53283 TORN END COVER. 1 G 7 1 3U O H2SW 2001102500038 20011025 00038 SW 2001 10 25 HEEA076510 1 20011005 G 2510 407370720101 RESTRAINT BELL 407 407 1182206 SW COCKPIT MALFUNCTIONED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 8595X 53267 INERTIA REEL LOCKS UP AND STRAPS FRAYED. 1 G 7 1 3U O H2SW 2001102500039 20011025 00039 SW 2001 10 25 HEEA076511 1 20011005 G 2822 2C273 CARTRIDGE BELL 412 412EP 1182205 SW BOOST PUMP INOPERATIVE E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 6106C 36257 FUEL CARTRIDGE INOPERATIVE. 1 G 7 2 4U H4SW 2001102500040 20011025 00040 SW 2001 10 25 HEEA076513 1 20011005 G 2820 206061634003 VALVE BELL 407 407 1182206 SW FUEL SYSTEM STUCK E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 402PH 53159 FUEL VALVE STICKING. 1 G 7 1 3U O H2SW 2001102500041 20011025 00041 SW 2001 10 25 HEEA076520 1 20011008 G 6510 407340339103 BEARING 407040302101 BELL 407 407 1182206 SW T/R DRIVESHAFT WORN E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 499PH A15 53400 WORN BEARING. SCRAPPED IN HOUSE. 1 G 7 1 3U O H2SW 2001102500042 20011025 00042 SW 2001 10 25 HEEA076521 1 20011008 G 8011 214060056103 STARTER BELL 214 214ST 1182106 SW ENGINE BURNED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 5748M 161 28102 BURNT. WILL NOT OPERATE. 2 G 7 2 4U H10SW 2001102500043 20011025 00043 SW 2001 10 25 HEEA076522 1 20011008 G 8011 214060056103 STARTER BELL 214 214ST 1182106 SW ENGINE FAILED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 5748M 210 28102 WILL NOT DISENGAGE. 2 G 7 2 4U H10SW 2001102500044 20011025 00044 SW 2001 10 25 HEEA076523 1 20011008 G 8011 214060056103 STARTER BELL 214 214ST 1182106 SW ENGINE FAILED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 59806 42 28140 WILL NOT ENGAGE. CLUTCH IN PIECES. 2 G 7 2 4U H10SW 2001102500045 20011025 00045 SW 2001 10 25 HEEA076524 1 20011008 G 8011 214060056103 STARTER BELL 214 214ST 1182106 SW ENGINE FAILED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 5748M 51 28102 DOES NOT DISENGAGE. 2 G 7 2 4U H10SW 2001102500046 20011025 00046 SW 2001 10 25 HEEA076525 1 20011009 G 5320 206020113173S CAP BELL 206 206A 1181508 SW FUSELAGE CRACKED E HEEA O OTHER W INADEQUATE Q C NR NOT REPORTED 1 SW 03 RECEIVED DENTED AND CRACK AT LEADING EDGE. 1 G 7 1 3U H2SW 2001102500050 20011025 00050 SW 2001 10 25 HEEA076527 1 20011010 G 7712 222375077119 TRANSMITTER BELL 407 407 1182206 SW TORQUE MALFUNCTIONED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 494PH 1228 53396 LOW TORQUE INDICATION. 1 G 7 1 3U O H2SW 2001102500061 20011025 00061 SW 2001 10 25 HEEA076528 1 20011010 G 3212 206373901103 SOLENOID VALVE BELL 407 407 1182206 SW MLG FAILED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 405PH 53207 DISCHARGED ON ITS OWN. INSTALLED 11-9-99 AT A/C TOTAL TIME 2102:15 AND REMOVED AT A/C TOTAL TIME 3683:40. 1 G 7 1 3U O H2SW 2001102500062 20011025 00062 SW 2001 10 25 HEEA076529 1 20011010 G 2400 A490ATSCF1428 POWER SUPPLY BELL 407 407 1182206 SW WEAK E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 493PH 2297 53393 POWER SUPPLY HAS WEAK OUTPUT. 1 G 7 1 3U O H2SW 2001102500063 20011025 00063 SW 2001 10 25 HEEA076530 1 20011010 G 7700 222375077113 TRANSMITTER BELL 407 407 1182206 SW OIL PRESSURE FLUCTUATES E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 407PH 6597 53003 FLUCTUATING APPROX. 10 PSI. 1 G 7 1 3U O H2SW 2001102500068 20011025 00068 SW 2001 10 25 HEEA076531 1 20011010 G 7714 212075037109 INDICATOR BELL 412 412EP 1182205 SW ENGINE FLUCTUATES E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 6106C 36257 FLUCTUATES ON START CYCLE UNTIL 30 PERCENT N1 SPEED ATTAINED. 1 G 7 2 4U H4SW 2001102500069 20011025 00069 SW 2001 10 25 HEEA076532 1 20011010 G 8011 214060056103 STARTER BELL 214 214ST 1182106 SW ENGINE FAILED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 3897N 477 28106 FAILED CLUTCH INSPECTION AND BEARING EXTENDING FROM HOUSING. 2 G 7 2 4U H10SW 2001102500104 20011025 00104 SW 2001 10 25 HEEA076534 1 20011010 G 3110 SM20ACD300A21 RELAY BELL 407 407 1182206 SW COCKPIT FAILED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 467PH 53142 START LIGHT WILL NOT ILLUMINATE. 1 G 7 1 3U O H2SW 2001102500106 20011025 00106 SW 2001 10 25 HEEA076535 1 20011010 G 7933 407375004101 INDICATOR BELL 407 407 1182206 SW ENG OIL TEMP FAILED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 723PH 53283 WILL GO TO ZERO INTERMITTENTLY. 1 G 7 1 3U O H2SW 2001102500107 20011025 00107 SW 2001 10 25 HEEA076536 1 20011010 G 7712 407375003107 INDICATOR BELL 407 407 1182206 SW TORQUE INOPERATIVE E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 720PH 53277 NO INDICATION ON GAUGE. IT WILL NOT TEST. 1 G 7 1 3U O H2SW 2001102500108 20011025 00108 SW 2001 10 25 HEEA076537 1 20011010 G 7931 222375077113 TRANSMITTER BELL 407 407 1182206 SW ENGINE OIL FAILED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 723PH 53283 ENGINE PRESSURE DROPPED TO ZERO. SENT TO BELL HELICOPTER TEXTRON FOR CREDIT AGAINST REPLACEMENT PART PURCHASED. REFEREN CE: DMR#720488. 1 G 7 1 3U O H2SW 2001102500109 20011025 00109 SW 2001 10 25 HEEA076538 1 20011010 G 3212 206373901103 SOLENOID VALVE BELL 407 407 1182206 SW MLG FAILED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 491PH 53386 UNABLE TO SEAT FILLER VALVE. 1 G 7 1 3U O H2SW 2001102500110 20011025 00110 SW 2001 10 25 HEEA076539 1 20011010 G 2844 407362013101 PRESSURE SWITCH BELL 407 407 1182206 SW BOOST PUMP FAILED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 723PH 30 53283 LEFT BOOST PUMP LIGHT DOESN'T ILLUMINATE WHEN SWITCH IS IN OFF POSITION. 1 G 7 1 3U O H2SW 2001102500111 20011025 00111 SW 2001 10 25 HEEA076540 1 20011010 G 3212 206373901103 SOLENOID VALVE BELL 407 407 1182206 SW MLG FLOAT LEAKING E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 491PH 53386 FLOAT BAG SOLENOID VALVE LEAKING. 1 G 7 1 3U O H2SW 2001102500112 20011025 00112 SW 2001 10 25 HEEA076541 1 20011010 G 2913 206076030111 PUMP BELL 407 407 1182206 SW HYD SYSTEM DAMAGED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 491PH 1452 53386 DRIVE SPLINES WORN. 1 G 7 1 3U O H2SW 2001102500113 20011025 00113 SW 2001 10 25 HEEA076542 1 20011010 G 6320 BEARING BELL 407 407 1182206 SW MAIN ROTOR WORN E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 406PH 3893 53198 BEARINGS WORN. 1 G 7 1 3U O H2SW 2001102500117 20011025 00117 SW 2001 10 25 HEEA076543 1 20011010 G 3212 206373901103 SOLENOID VALVE BELL 407 407 1182206 SW FLOAT BAG LEAKING E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 491PH 53386 FLOAT BAG SOLENOID VALVE IS LEAKING. 1 G 7 1 3U O H2SW 2001102500119 20011025 00119 SW 2001 10 25 HEEA076545 1 20011010 G 6230 406010401117 SWASHPLATE BELL 407 407 1182206 SW MAIN ROTOR LEAKING E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 494PH 1163 53396 GREASE PURGES THROUGH THE TOP. 1 G 7 1 3U O H2SW 2001102500120 20011025 00120 SW 2001 10 25 HEEA076546 1 20011010 G 3212 206373901103 SOLENOID VALVE BELL 407 407 1182206 SW FLOAT BAG LEAKING E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 467PH 53142 SOLENOID VALVE FOR FLOAT BAG LEAKING. 1 G 7 1 3U O H2SW 2001102500121 20011025 00121 SW 2001 10 25 HEEA076547 1 20011010 G 6300 407310203101 MOUNT BELL 407 407 1182206 SW MAIN ROTOR DETERIORATED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 499PH 1974 53400 MAIN ROTOR MOUNT DETERIORATED. 1 G 7 1 3U O H2SW 2001102500122 20011025 00122 SW 2001 10 25 HEEA076550 1 20011010 G 6310 406040500123B FREEWHEEL UNIT BELL 407 407 1182206 SW MAIN ROTOR LEAKING E HEEA O OTHER K FLUID LOSS NR NOT REPORTED 1 SW 03 723PH 3100 53283 LEAKING AT FRONT SEAL. . 1 G 7 1 3U O H2SW 2001102500123 20011025 00123 SW 2001 10 25 HEEA076551 1 20011010 G 6300 407010206103 SPRING BELL 407 407 1182206 SW MAIN ROTOR SEPARATED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 723PH 2485 53283 SPRING HAS SEPARATION. 1 G 7 1 3U O H2SW 2001102500125 20011025 00125 SW 2001 10 25 HEEA076555 1 20011010 G 6730 206076062107 SERVO BELL 407 407 1182206 SW CYCLIC LEAKING E HEEA O OTHER K FLUID LOSS NR NOT REPORTED 1 SW 03 494PH 1866 53396 CYCLIC SERVO LEAKING. 1 G 7 1 3U O H2SW 2001102500126 20011025 00126 SW 2001 10 25 HEEA076556 1 20011010 G 6730 206076062107 SERVO BELL 407 407 1182206 SW CYCLIC LEAKING E HEEA O OTHER K FLUID LOSS NR NOT REPORTED 1 SW 03 494PH 1866 53396 CYCLIC SERVO LEAKING. 1 G 7 1 3U O H2SW 2001102500128 20011025 00128 SW 2001 10 25 HEEA076557 1 20011010 G 6210 407015001117 BLADE BELL 407 407 1182206 SW MAIN ROTOR CRACKED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 409PH 4173 53059 MAIN ROTOR BLADE CRACKED AT OUTBOUND TRIM TAB. 1 G 7 1 3U O H2SW 2001102500129 20011025 00129 SW 2001 10 25 HEEA076558 1 20011010 G 6320 407040006107 TRANSMISSION BELL 407 407 1182206 SW MAIN ROTOR MAKING METAL E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 721PH 1594 53278 MAIN ROTOR TRANSMISSION MAKING METAL. 1 G 7 1 3U O H2SW 2001102500130 20011025 00130 SW 2001 10 25 HEEA076559 1 20011010 G 6300 BEARING BELL 407 407 1182206 SW MAIN ROTOR WORN E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 405PH 3728 53207 WORN BEARINGS. 1 G 7 1 3U O H2SW 2001102500133 20011025 00133 2001 10 25 HEEA076560 4 20011010 G 3197 CONNECTOR BELL 407 407 1182206 SW INSTRUMENT PANEL DAMAGED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 405PH 3728 53207 BENT PIN IN PLUG. 1 G 7 1 3U O H2SW 2001102500134 20011025 00134 SW 2001 10 25 HEEA076564 1 20011010 G 7714 32005037 TACH GENERATOR BELL 412 412 1182202 SW NR 2 ENGINE FAILED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 107X 33113 ON INBOUND FLIGHT, THE NR 2 ENGINE OUT LIGHT ILLUMINATED. REPLACED NR 2 ENGINE N1 TACH GEN. 1 G 7 2 4U H4SW 2001102500136 20011025 00136 SW 2001 10 25 HEEA076565 1 20011010 G 2910 212076433001 LINE BELL 412 412 1182202 SW HYD SYSTEM CRACKED E HEEA A UNSCHED LANDING K J FLUID LOSS WARNING INDICATION CR CRUISE 1 SW 03 1202T 33112 WHILE IN CRUISE FLIGHT, NR 1 HYDRAULIC SYSTEM FAILED. MAINTENANCE REPLACED HYDRAULIC TUBE ASSY DUE TO CRACK IN ONE OF TH E CURVES. 1 G 7 2 4U H4SW 2001102500140 20011025 00140 NE 2001 10 25 HEEA076566 2 20011011 G 7200 23063412 HOSE BELL 407 407 1182206 SW ALLSN 250C 250C40B 03032 NE ENGINE LEAKING E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 8595X 53267 HOSE LEAKS UNDER PRESSURE. REPLACED WITH SERVICEABLE HOSE. 1 G 7 1 3U 3 U O H2SW E1GL 2001102500142 20011025 00142 SW 2001 10 25 HEEA076567 1 20011011 G 6230 406010401117 SWASHPLATE BELL 407 407 1182206 SW MAIN ROTOR DAMAGED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 720PH 1861 53277 SWASHPLATE SEAL SPINNING IN CAP. 1 G 7 1 3U O H2SW 2001102500143 20011025 00143 SW 2001 10 25 HEEA076568 1 20011011 G 6310 406040500119 SUPPORT BELL 407 407 1182206 SW MAIN ROTOR LEAKING E HEEA O OTHER K FLUID LOSS NR NOT REPORTED 1 SW 03 8595X 53267 SUPPORT LEAKING FROM SEAL. 1 G 7 1 3U O H2SW 2001102500144 20011025 00144 SW 2001 10 25 HEEA076572 1 20011011 G 6420 BEARING BELL 407 407 1182206 SW TAIL ROTOR HUB WORN E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 742PH 1146 53461 TAIL ROTOR HUB HAS A WORN BEARING. 1 G 7 1 3U O H2SW 2001102500145 20011025 00145 SW 2001 10 25 HEEA076573 1 20011011 G 6300 407310203101 MOUNT BELL 407 407 1182206 SW MAIN ROTOR DETERIORATED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 402PH 53159 DETERIORATED. 1 G 7 1 3U O H2SW 2001102500146 20011025 00146 SW 2001 10 25 HEEA076574 1 20011011 G 6510 407340340103 DISC PACK BELL 407 407 1182206 SW T/R DRIVE CRACKED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 723PH 53283 DISC PACK CRACKED. 1 G 7 1 3U O H2SW 2001102500148 20011025 00148 SW 2001 10 25 HEEA076575 1 20011011 G 6510 407340340103 DISC PACK BELL 407 407 1182206 SW T/R DRIVE CRACKED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 724PH 53327 DISC PACK CRACKED. 1 G 7 1 3U O H2SW 2001102500149 20011025 00149 2001 10 25 HEEA076580 4 20011011 G 2312 064100900 TRANSCEIVER BELL 412 412 1182202 SW VHF SYSTEM WEAK E HEEA K NONE L NO TEST IN INSP/MAINT 1 SW 03 2261D 33076 TRANSMITS WEAK. REPLACED WITH SERVICEABLE PART. 1 G 7 2 4U H4SW 2001102500150 20011025 00150 2001 10 25 HEEA076581 4 20011011 G 3420 071105200 INDICATOR BELL 230 230 1182149 SW ATTITUDE PRECESSES E HEEA K NONE L NO TEST IN INSP/MAINT 1 SW 03 911RC 23037 INTERMITTENT PROBLEM OF PRECESSING 30 DEGREES. REPLACED WITH SERVICEABLE PART. 1 G 7 2 3U NC H9SW 2001102500151 20011025 00151 2001 10 25 HEEA076582 4 20011011 G 3442 071111401 ANTENNA BELL 206 206L3 1182108 SW RADAR DAMAGED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 6748D 51106 COAX PULLED OUT FROM ANTENNA CONNECTOR. REPLACED WITH SERVICEABLE PART. TO BE SENT TO VENDOR FOR REPAIR. 1 G 7 1 3U H2SW 2001102500152 20011025 00152 2001 10 25 HEEA076583 4 20011011 G 3457 13824120234 GPS BELL 206 206L1 1182107 SW COCKPIT FAILED E HEEA K NONE L NO TEST IN INSP/MAINT 1 SW 03 3905B 45598 FAILED DUMPING ALL WAYPOINTS, RECEIVER AND BATTERY BACK UP FAIL KEPT FLASHING IN MESSAGE MODE. REPLACED WITH SERVICEABLE PART. 1 G 7 1 3U H2SW 2001102500153 20011025 00153 SW 2001 10 25 HEEA076584 1 20011011 G 6510 204040620011 SHAFT BELL 412 412 1182202 SW TAIL ROTOR DAMAGED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 1202T 33112 WEIGHT MISSING. REPLACED WITH SERVICEABLE PART. 1 G 7 2 4U H4SW 2001102500154 20011025 00154 SW 2001 10 25 HEEA076585 1 20011011 G 2140 205072277009 VALVE BELL 412 412 1182202 SW HEATER INTERMITTENT E K NONE L NO TEST IN INSP/MAINT 1 SW 03 107X 33113 HEATER MIXING VALVE WORKS INTERMITTENTLY. REPLACED WITH SERVICEABLE PART. 1 G 7 2 4U H4SW 2001102500163 20011025 00163 SW 2001 10 25 HEEA076586 1 20011011 G 6400 BEARING BELL 206 206L3 1182108 SW TAIL ROTOR WORN E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 3108E 51498 BEARINGS WORN AND RUSTED. REPLACED WITH SERVICEABLE PART. 1 G 7 1 3U H2SW 2001102500164 20011025 00164 SW 2001 10 25 HEEA076587 1 20011011 G 3212 206050248111 FLOAT BELL 206 206L3 1182108 SW MLG FAILED E HEEA K NONE L NO TEST IN INSP/MAINT 1 SW 03 4835 51131 FAILED ALTERNATE CHAMBER CHECK. REPLACED WITH SERVICEABLE PART. 1 G 7 1 3U H2SW 2001102500165 20011025 00165 GL 2001 10 25 HEEA076588 2 20011011 G 7230 206075682107 INDICATOR BELL 206 206L3 1182108 SW ALLSN 250C 250C30P 03013 GL GAS PRODUCER MALFUNCTIONED E HEEA K NONE L NO TEST IN INSP/MAINT 1 SW 03 6748D 51106 DID NOT FUNCTION PROPERLY. NEEDLE SLOW TO REACT AND HANGS UP AT APPROX. 10 PERCENT. REPLACED WITH SERVICEABLE PART. 1 G 7 1 3U 3 U H2SW E1GL 2001102500166 20011025 00166 NE 2001 10 25 HEEA076589 2 20011011 G 7510 209062214001 ACTUATOR BELL 412 412 1182202 SW PWA PT6T PT6T3B 52045 NE ENGINE STUCK E HEEA K NONE L NO TEST IN INSP/MAINT 1 SW 03 107X 33113 STICKING. REPLACED WITH SERVICEABLE PART. 1 G 7 2 4U 4 U H4SW E22EA 2001102500167 20011025 00167 SW 2001 10 25 HEEA076590 1 20011011 G 2910 212076433011 TUBE BELL 412 412 1182202 SW HYD SYSTEM CRACKED E HEEA K NONE K FLUID LOSS IN INSP/MAINT 1 SW 03 1202T 33112 TUBE ASSY CRACKED. REPLACED WITH SERVICEABLE PART. 1 G 7 2 4U H4SW 2001102500169 20011025 00169 SW 2001 10 25 HEEA076591 1 20011011 G 2510 222320823119 SEAT BELT BELL 206 206L4 1182110 SW COCKPIT FRAYED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 7074W 52033 SEAT BELT FRAYED. REPLACED WITH SERVICEABLE PART. 1 G 7 1 3U NC H2SW 2001102500170 20011025 00170 SW 2001 10 25 HEEA076592 1 20011011 G 2432 30126001 BATTERY BELL 412 412 1182202 SW MAIN DISCHARGED E HEEA K NONE L NO TEST IN INSP/MAINT 1 SW 03 1202T 33112 SLOW TO CHARGE. REPLACED WITH SERVICEABLE PART. 1 G 7 2 4U H4SW 2001102500171 20011025 00171 SW 2001 10 25 HEEA076593 1 20011011 G 7714 32005037 TACH GENERATOR BELL 412 412 1182202 SW ENGINE FAILED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 107X 33113 ENGINE OUT LIGHT WON'T GO OUT. REPLACED WITH SERVICEABLE PART. 1 G 7 2 4U H4SW 2001102500172 20011025 00172 SW 2001 10 25 HEEA076594 1 20011011 G 2432 32007001 BATTERY BELL 206 206L3 1182108 SW MAIN WEAK E HEEA K NONE L NO TEST IN INSP/MAINT 1 SW 03 4835 51131 WEAK AND AIRCRAFT SLOW TO START. REPLACED WITH SERVICEABLE PART. 1 G 7 1 3U H2SW 2001102500173 20011025 00173 NE 2001 10 25 HEEA076595 2 20011011 G 7320 324473511 FUEL CONTROL BELL 412 412 1182202 SW PWA PT6T PT6T3B 52045 NE ENGINE MALFUNCTIONED E HEEA K NONE J WARNING INDICATION IN INSP/MAINT 1 SW 03 2149S 36002 CAUSING TORQUE OSCILLATIONS OF 10-15 PERCENT AT A HOVER. REPLACED WITH SERVICEABLE PART. 1 G 7 2 4U 4 U H4SW E22EA 2001102500174 20011025 00174 2001 10 25 HEEA076596 4 20011011 G 2561 3500145NL72 LIFE VEST BELL 412 412 1182202 SW EMERGENCY EQUIP LEAKING E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 142PH 33150 LIFE VEST LEAKS. REPLACED WITH SERVICEABLE PART. 1 G 7 2 4U H4SW 2001102500175 20011025 00175 SW 2001 10 25 HEEA076597 1 20011011 G 2422 412075101101 INVERTER BELL 412 412 1182202 SW ELECTRICAL INTERMITTENT E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 107X 33113 WORKS INTERMITTENTLY DUE TO WATER DAMAGE. REPLACED WITH SERVICEABLE PART. 1 G 7 2 4U H4SW 2001102500185 20011025 00185 2001 10 25 HEEA076598 4 20011011 G 3421 5050010902 GYRO BELL 206 206L1 1182107 SW COCKPIT MALFUNCTIONED E HEEA K NONE L NO TEST IN INSP/MAINT 1 SW 03 5019F 45244 ADJUSTMENT KNOB WILL NOT FUNCTION. REPLACED WITH SERVICEABLE PART. 1 G 7 1 3U H2SW 2001102500186 20011025 00186 SW 2001 10 25 HEEA076599 1 20011011 G 3340 7028521 LIGHT BELL 412 412 1182202 SW STROBE FAILED E HEEA K NONE L NO TEST IN INSP/MAINT 1 SW 03 2261D 33076 WILL NOT COME ON. REPLACED WITH SERVICEABLE PART. 1 G 7 2 4U H4SW 2001102500188 20011025 00188 2001 10 25 HEEA076600 4 20011011 G 3457 8143902240B GPS BELL 412 412 1182202 SW COCKPIT FAILED E HEEA K NONE L NO TEST IN INSP/MAINT 1 SW 03 33008 36004 WHEN UNIT IS TURNED ON, POWERS UP FOR APPROX. 15 SECONDS TO ONE MINUTE THEN GOES BLANK. REPLACED WITH SERVICEABLE PART. 1 G 7 2 4U H4SW 2001102500189 20011025 00189 SW 2001 10 25 HEEA076601 1 20011011 G 2497 A1077V CONTACTOR BELL 206 206L3 1182108 SW ELECTRICAL LOOSE E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 4835 51131 A2 TERMINAL STUD LOOSE. REPLACED WITH SERVICEABLE PART. 1 G 7 1 3U H2SW 2001102500190 20011025 00190 2001 10 25 HEEA076602 4 20011011 G 2340 A3016R MIXER BOX BELL 412 412 1182202 SW INTERPHONE MALFUNCTIONED E HEEA K NONE L NO TEST IN INSP/MAINT 1 SW 03 1202T 33112 LIGHT BLINKS ON AND OFF. REPLACED WITH SERVICEABLE PART. 1 G 7 2 4U H4SW 2001102500192 20011025 00192 2001 10 25 HEEA076603 4 20011011 G 2562 ELP362D ELT BELL 412 412 1182202 SW CABIN DISCHARGED E HEEA K NONE L NO TEST IN INSP/MAINT 1 SW 03 142PH 33150 BATTERY WEAK, LOW VOLTAGE. REPLACED WITH SERVICEABLE PART. 1 G 7 2 4U H4SW 2001102500193 20011025 00193 2001 10 25 HEEA076604 4 20011011 G 2562 ELT910 ELT BELL 412 412 1182202 SW CABIN INTERMITTENT E HEEA K NONE L NO TEST IN INSP/MAINT 1 SW 03 107X 33113 INTERMITTENTLY COMES ON IN FLIGHT. REPLACED WITH SERVICEABLE PART. 1 G 7 2 4U H4SW 2001102500195 20011025 00195 2001 10 25 HEEA076605 4 20011011 G 2300 G4434A CONTROL HEAD BELL 412 412 1182202 SW COMM SYSTEM INOPERATIVE E HEEA K NONE L NO TEST IN INSP/MAINT 1 SW 03 2261D 33076 ON/OFF SWITCH INOPERATIVE. REPLACED WITH SERVICEABLE PART. 1 G 7 2 4U H4SW 2001102500196 20011025 00196 2001 10 25 HEEA076606 4 20011011 G 3140 MI5852013 INDICATOR BELL 412 412 1182202 SW INSTRUMENT PANEL FAILED E HEEA K NONE L NO TEST IN INSP/MAINT 1 SW 03 107X 33113 DISPLAYS ONLY GREEN IN MAP MODE. REPLACED WITH SERVICEABLE PART. 1 G 7 2 4U H4SW 2001102500200 20011025 00200 2001 10 25 HEEA076607 4 20011011 G 3442 MI5852013 INDICATOR BELL 412 412 1182202 SW RADAR MALFUNCTIONED E HEEA K NONE L NO TEST IN INSP/MAINT 1 SW 03 107X 33113 DISPLAYS RANDOM RANGES. REPLACED WITH SERVICEABLE PART. 1 G 7 2 4U H4SW 2001102500202 20011025 00202 2001 10 25 HEEA076608 4 20011011 G 3442 MI585200 INDICATOR BELL 412 412 1182202 SW RADAR MALFUNCTIONED E HEEA K NONE L NO TEST IN INSP/MAINT 1 SW 03 107X 33113 DISPLAYS RANDOM RANGES. REPLACED WITH SERVICEABLE PART. 1 G 7 2 4U H4SW 2001102500204 20011025 00204 SW 2001 10 25 HEEA076609 1 20011011 G 5260 PHI101741 ACTUATOR BELL 412 412 1182202 SW STEP FAILED E HEEA K NONE L NO TEST IN INSP/MAINT 1 SW 03 1202T 33112 STEP WON'T GO DOWN. REPLACED WITH SERVICEABLE PART. 1 G 7 2 4U H4SW 2001102500207 20011025 00207 SW 2001 10 25 HEEA076610 1 20011011 G 6720 PHI41294 CONTROL UNIT BELL 412 412 1182202 SW TAIL ROTOR WORN E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 5759N 33002 WORN BEARINGS. REPLACED WITH SERVICEABLE PART. 1 G 7 2 4U H4SW 2001102500209 20011025 00209 SW 2001 10 25 HEEA076611 1 20011012 G 6720 406312103101 LINK BELL 407 407 1182206 SW TAIL ROTOR WORN E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 407PH 53003 BEARING WORN. TO BE SENT TO BELL HELICOPTER TEXTRON FOR CREDIT AGAINST REPLACEMENT PART PURCHASED. 1 G 7 1 3U O H2SW 2001102500211 20011025 00211 SW 2001 10 25 HEEA076612 1 20011012 G 6720 406312103101 LINK BELL 407 407 1182206 SW TAIL ROTOR WORN E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 407PH 53003 BEARING WORN. 1 G 7 1 3U O H2SW 2001102500212 20011025 00212 SW 2001 10 25 HEEA076613 1 20011012 G 6420 407312100101 BEARING 407012101111 BELL 407 407 1182206 SW TAIL ROTOR HUB WORN E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 491PH 53025 53386 WORN ELASTOMER. TO BE SENT TO BELL HELICOPTER TEXTRON FOR CREDIT AGAINST REPLACEMENT PART PURCHASED. LABOR CREDIT ACCOM PLISHED ON J0188327-WA (INVOICE AND DMR NO. 687168). 1 G 7 1 3U O H2SW 2001102500214 20011025 00214 NE 2001 10 25 HEEA076614 2 20011012 G 7314 02527730008 PUMP BELL 412 412 1182202 SW PWA PT6T PT6T3B 52045 NE ENGINE FUEL FAILED E HEEA O OTHER R J PARTIAL RPM/PWR LOSS WARNING INDICATION NR NOT REPORTED 1 SW 03 2149S 36002 ENGINE OSCILLATIONS AND SEAL LEAKING. REPLACED WITH SERVICEABLE FUEL PUMP. 1 G 7 2 4U 4 U H4SW E22EA 2001102500216 20011025 00216 SW 2001 10 25 HEEA076615 1 20011012 G 3040 204070907101 MOTOR BELL 412 412 1182202 SW WINDSHIELD WIPER FAILED E HEEA K NONE L NO TEST IN INSP/MAINT 1 SW 03 3893L 33006 PILOT WIPER INOPERATIVE. REPLACED WITH SERVICEABLE PART. 1 G 7 2 4U H4SW 2001102500218 20011025 00218 SW 2001 10 25 HEEA076616 1 20011012 G 5310 BEARING BELL 412 412 1182202 SW STRUCTURE MISMANUFACTURED E HEEA K NONE W INADEQUATE Q C IN INSP/MAINT 1 SW 03 2298Z 33077 I/D BORE BEARING TOO SMALL. (BEARING P/N 209-031-351-001) REPLACED WITH SERVICEABLE PART. 1 G 7 2 4U H4SW 2001102500219 20011025 00219 SW 2001 10 25 HEEA076617 1 20011012 G 7700 B4429 CHIP DETECTOR 350A33200406 BELL 412 412 1182202 SW MAIN ROTOR MALFUNCTIONED E HEEA K NONE L NO TEST IN INSP/MAINT 1 SW 03 2148K MA1154 36001 CAUSES REMOTE CAT'S EYE TO TRIP. REPLACED WITH SERVICEABLE PART. 1 G 7 2 4U H4SW 2001102500221 20011025 00221 2001 10 25 HEEA076618 4 20011003 G 3457 0110010600 GPS BOLKMS 117 BK117A1 5626010 EU COCKPIT FAILED E HEEA K NONE L NO TEST IN INSP/MAINT 1 SW 03 217UC 7152 GPS WENT BLANK. PENDING VENDOR REPAIR. 1 G 7 2 3U H13EU 2001102500222 20011025 00222 EU 2001 10 25 HEEA076622 1 20011004 G 6300 350A33215300 BEARING SNIAS 350 AS350B1 8680811 EU MAIN ROTOR WORN E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 856PH 3352 BEARING WORN. 1 G 7 1 3U H9EU 2001102500223 20011025 00223 EU 2001 10 25 HEEA076623 1 20011004 G 7500 704A34415099 HOSE SNIAS 350 AS350B 8680801 EU BLEED AIR TORN E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 972AE 88 3234 TORN. PENDING VENDOR RETURN FOR CREDIT. 1 G 7 1 3U H9EU 2001102500224 20011025 00224 EU 2001 10 25 HEEA076625 1 20011004 G 6730 EMRL8RSP3C BEARING SNIAS 350 AS350B 8680801 EU MAIN ROTOR SERVO WORN E HEEA K NONE O OTHER NR NOT REPORTED 1 SW 03 974AE 2653 WORN ROD END BEARINGS ON MAIN ROTOR SERVOS. PENDING VENDOR RETURN FOR CREDIT. 1 G 7 1 3U H9EU 2001102500225 20011025 00225 EU 2001 10 25 HEEA076628 1 20011004 G 6520 350A33215001 BEARING SNIAS 350 AS350B 8680801 EU TAIL ROTOR WORN E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 856PH 3352 WORN BEARING. 1 G 7 1 3U H9EU 2001102500226 20011025 00226 EU 2001 10 25 HEEA076629 1 20011004 G 7721 56375600010 INDICATOR SNIAS 350 AS350B 8680801 EU COCKPIT WORN E HEEA K NONE O OTHER NR NOT REPORTED 1 SW 03 856PH 3352 ERRATIC INDICATIONS. SENT TO AMERICAN EUROCOPTER CORP. FOR CREDIT AGAINST REPLACEMENT PART PURCHASED. REFERENCE: RMA# R032847. 1 G 7 1 3U H9EU 2001102500228 20011025 00228 EU 2001 10 25 HEEA076630 1 20011004 G 6730 704A34240015 ACCUMULATOR SNIAS 350 AS350B 8680801 EU ROTO SERVO LEAKING E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 974AE 2653 WILL NOT HOLD CHARGE. LEAKING. 1 G 7 1 3U H9EU 2001102500229 20011025 00229 EU 2001 10 25 HEEA076631 1 20011011 G 2435 BRUSHES SNIAS 350 AS350B 8680801 EU STARTER GEN ARCED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 856PH 3352 BRUSHES ARCING WHEN STARTER IS TURNING. REPLACED WITH SERVICEABLE PART. 1 G 7 1 3U H9EU 2001102500231 20011025 00231 2001 10 25 HEEA076632 4 20011011 G 3120 B1894522282A CLOCK SNIAS 350 AS350B 8680801 EU COCKPIT INACCURATE E HEEA K NONE L NO TEST IN INSP/MAINT 1 SW 03 856PH 3352 DOES NOT KEEP CORRECT TIME. REPLACED WITH SERVICEABLE PART. 1 G 7 1 3U H9EU 2001111400001 20011114 00001 GL 2001 11 14 HEEA076800 2 20011016 G 7250 6898977 COUPLING ALLSN 250C 250C20J 03013 GL ENGINE CORRODED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 CAE272598 N1 COUPLING HAS EXCESSIVE RUST CAUSING PITTING. 3 U E4CE 2001111400002 20011114 00002 NE 2001 11 14 HEEA076801 2 20011019 G 7421 9550168760 IGNITER SNIAS 350 AS350B 8680801 EU TMECA ARRIEL ARRIEL1B 6OO30 NE WORN E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 856PH 3352 CONDUCTOR WORN. SENT TO TURBOMECA FOR CREDIT AGAINST REPLACEMENT PART PURCHASED. 1 G 7 1 3U 3 U H9EU E19EU 2001111400003 20011114 00003 NE 2001 11 14 HEEA076802 1 20011019 G 7700 9550176740 THERMOCOUPLE SKRSKY S76 S76C 8143008 NE TMECA ARRIEL ARRIEL1A 60030 NE ENGINE WORN E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 505PH 760505 WORN PROBES. 1 G 7 2 3U 3 U NC H1NE E19EU 2001111400004 20011114 00004 NE 2001 11 14 HEEA076803 1 20011025 G 7100 0292005310 ENGINE SKRSKY S76 S76C 8143008 NE TMECA ARRIEL ARRIEL1 60030 NE NACELLE LEAKING E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 505PH 1306 760505 LOW POWER, LEAKING. 1 G 7 2 3U 3 U NC H1NE E19EU 2001111400005 20011114 00005 SW 2001 11 14 HEEA076806 1 20011016 G 6300 407340339103 BEARING BELL 407 407 1182206 SW MAIN ROTOR FAILED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 492PH 53390 BEARING INNER RACE TURNING ON SHAFT JOURNAL. 1 G 7 1 3U O H2SW 2001111400006 20011114 00006 SW 2001 11 14 HEEA076807 1 20011016 G 6300 407340339103 BEARING BELL 407 407 1182206 SW MAIN ROTOR FAILED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 492PH 53390 BEARING INNER RACE TURNING ON SHAFT JOURNAL. 1 G 7 1 3U O H2SW 2001111400007 20011114 00007 SW 2001 11 14 HEEA076808 1 20011016 G 6300 407340339103 BEARING BELL 407 407 1182206 SW MAIN ROTOR FAILED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 496PH 53398 BEARING INNER RACE TURNING ON SHAFT JOURNAL. 1 G 7 1 3U O H2SW 2001111400008 20011114 00008 SW 2001 11 14 HEEA076809 1 20011016 G 6300 407340339103 BEARING BELL 407 407 1182206 SW MAIN ROTOR FAILED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 496PH 53398 BEARING INNER RACE TURNING ON SHAFT JOURNAL. 1 G 7 1 3U O H2SW 2001111400009 20011114 00009 SW 2001 11 14 HEEA076810 1 20011016 G 6510 407040302107 DRIVE SHAFT BELL 407 407 1182206 SW TAIL ROTOR DAMAGED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 496PH 1903 53398 BEARING INNER RACE TURNING ON SHAFT JOURNAL. 1 G 7 1 3U O H2SW 2001111400010 20011114 00010 SW 2001 11 14 HEEA076811 1 20011016 G 6510 407040302107 DRIVE SHAFT BELL 407 407 1182206 SW TAIL ROTOR DAMAGED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 496PH 1299 53398 BEARING INNER RACE TURNING ON SHAFT JOURNAL. 1 G 7 1 3U O H2SW 2001111400011 20011114 00011 SW 2001 11 14 HEEA076812 1 20011016 G 6510 407040302103 DRIVE SHAFT BELL 407 407 1182206 SW TAIL ROTOR DAMAGED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 492PH 53390 BEARING INNER RACE TURNING ON SHAFT JOURNAL. 1 G 7 1 3U O H2SW 2001111400013 20011114 00013 SW 2001 11 14 HEEA076813 1 20011016 G 6510 407040302107 DRIVE SHAFT BELL 407 407 1182206 SW TAIL ROTOR DAMAGED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 492PH 1597 53390 BEARING INNER RACE TURNING ON SHAFT JOURNAL. 1 G 7 1 3U O H2SW 2001111400015 20011114 00015 SW 2001 11 14 HEEA076814 1 20011016 G 6510 SHAFT BELL 407 407 1182206 SW COOLER BLOWER FAILED E HEEA A UNSCHED LANDING E J VIBRATION/BUFFET WARNING INDICATION CR CRUISE 1 SW 03 4999 53323 IN CRUISE, AIRCRAFT DEVELOPED SEVERE VERTICAL VIBRATION. FOUND FORWARD BEARING ON NR 2 TAIL ROTOR OIL COOLER BLOWER SHA FT FAILURE. 1 G 7 1 3U O H2SW 2001111400017 20011114 00017 SW 2001 11 14 HEEA076815 1 20011017 G 2432 32007001 BATTERY BELL 206 206L3 1182108 SW MAIN DISCHARGED E HEEA K NONE L NO TEST IN INSP/MAINT 1 SW 03 31821 51076 RECEIVED FROM PARTS. WEAK FROM INSTALLATION AND FAILED COMPLETELY. REPLACED WITH SERVICEABLE BATTERY. 1 G 7 1 3U H2SW 2001111400018 20011114 00018 SW 2001 11 14 HEEA076816 1 20011018 G 2432 32007001 BATTERY BELL 206 206L3 1182108 SW MAIN FAILED E HEEA O OTHER L NO TEST NR NOT REPORTED 1 SW 03 3116P 51530 WILL NOT HOLD CHARGE. REPLACED WITH SERVICEABLE BATTERY. 1 G 7 1 3U H2SW 2001111400020 20011114 00020 SW 2001 11 14 HEEA076817 1 20011018 G 2432 32007001 BATTERY BELL 206 206L3 1182108 SW MAIN DISCHARGED E HEEA K NONE L NO TEST IN INSP/MAINT 1 SW 03 4180F TOO WEAK TO START AIRCRAFT. REPLACED WITH SERVICEABLE BATTERY. 1 G 7 1 3U H2SW 2001111400027 20011114 00027 NE 2001 11 14 HEEA076820 2 20011018 G 7321 32448891 FUEL CONTROL BELL 412 412 1182202 SW PWA PT6T PT6T3B 52045 NE ENGINE FLUCTUATES E HEEA A UNSCHED LANDING J WARNING INDICATION CL CLIMB 1 SW 03 22608 10321 33075 AFTER DEPARTURE, NR 1 ENGINE STARTED TO HAVE N1 FLUCTUATIONS. REPLACED FUEL CONTROL. 1 G 7 2 4U 4 U H4SW E22EA 2001111400028 20011114 00028 SW 2001 11 14 HEEA076821 1 20011018 G 2432 32007001 BATTERY BELL 206 206L1 1182107 SW MAIN DISCHARGED E HEEA O OTHER L NO TEST NR NOT REPORTED 1 SW 03 406EH 45183 WEAK BATTERY. REPLACED WITH SERVICEABLE BATTERY. 1 G 7 1 3U H2SW 2001111400029 20011114 00029 SW 2001 11 14 HEEA076822 1 20011018 G 2432 32007001 BATTERY BELL 206 206L3 1182108 SW MAIN DISCHARGED E HEEA O OTHER L NO TEST NR NOT REPORTED 1 SW 03 206LS 51070 WEAK BATTERY. REPLACED WITH SERVICEABLE BATTERY. 1 G 7 1 3U H2SW 2001111400031 20011114 00031 SW 2001 11 14 HEEA076823 1 20011018 G 2432 32007001 BATTERY BELL 206 206L1 1182107 SW MAIN DISCHARGED E HEEA O OTHER L NO TEST NR NOT REPORTED 1 SW 03 5745S 45491 DEAD BATTERY. REPLACED WITH SERVICEABLE BATTERY. 1 G 7 1 3U H2SW 2001111400032 20011114 00032 SW 2001 11 14 HEEA076824 1 20011018 G 2432 32007001 BATTERY BELL 206 206L3 1182108 SW MAIN DISCHARGED E HEEA O OTHER L NO TEST NR NOT REPORTED 1 SW 03 8593X 51509 WEAK BATTERY. REPLACED WITH SERVICEABLE BATTERY. 1 G 7 1 3U H2SW 2001111400034 20011114 00034 SW 2001 11 14 HEEA076825 1 20011018 G 2432 32007001 BATTERY BELL 206 206L3 1182108 SW MAIN DISCHARGED E HEEA O OTHER L NO TEST NR NOT REPORTED 1 SW 03 54641 51184 WEAK BATTERY. REPLACED WITH SERVICEABLE BATTERY. 1 G 7 1 3U H2SW 2001111400035 20011114 00035 SW 2001 11 14 HEEA076826 1 20011018 G 2432 32007001 BATTERY BELL 206 206L1 1182107 SW MAIN DISCHARGED E HEEA O OTHER L NO TEST NR NOT REPORTED 1 SW 03 2777D 45299 DEAD BATTERY. REPLACED WITH SERVICEABLE BATTERY. 1 G 7 1 3U H2SW 2001111400046 20011114 00046 SW 2001 11 14 HEEA076827 1 20011018 G 2432 32007001 BATTERY BELL 206 206L3 1182108 SW MAIN DISCHARGED E HEEA O OTHER L NO TEST NR NOT REPORTED 1 SW 03 8587X 51464 WEAK BATTERY. REPLACED WITH SERVICEABLE BATTERY. 1 G 7 1 3U H2SW 2001111400047 20011114 00047 SW 2001 11 14 HEEA076828 1 20011018 G 2432 32007001 BATTERY BELL 206 206L3 1182108 SW MAIN DISCHARGED E HEEA O OTHER L NO TEST NR NOT REPORTED 1 SW 03 6610C 51425 WEAK BATTERY. REPLACED WITH SERVICEABLE BATTERY. 1 G 7 1 3U H2SW 2001111400048 20011114 00048 SW 2001 11 14 HEEA076829 1 20011018 G 2432 32007001 BATTERY BELL 206 206L3 1182108 SW MAIN DISCHARGED E HEEA O OTHER L NO TEST NR NOT REPORTED 1 SW 03 41791 51465 WEAK BATTERY. REPLACED WITH SERVICEABLE BATTERY. 1 G 7 1 3U H2SW 2001111400050 20011114 00050 SW 2001 11 14 HEEA076830 1 20011018 G 2432 32007001 BATTERY BELL 206 206L3 1182108 SW MAIN DISCHARGED E HEEA O OTHER L NO TEST NR NOT REPORTED 1 SW 03 6161A 51611 WEAK BATTERY. REPLACED WITH SERVICEABLE BATTERY. 1 G 7 1 3U H2SW 2001111400051 20011114 00051 SW 2001 11 14 HEEA076831 1 20011018 G 2432 32007001 BATTERY BELL 206 206L3 1182108 SW MAIN FAILED E HEEA O OTHER L NO TEST NR NOT REPORTED 1 SW 03 31077 51520 WON'T TAKE A CHARGE. REPLACED WITH SERVICEABLE BATTERY. 1 G 7 1 3U H2SW 2001111400052 20011114 00052 SW 2001 11 14 HEEA076832 1 20011018 G 2432 32007001 BATTERY BELL 206 206L3 1182108 SW MAIN DISCHARGED E HEEA O OTHER L NO TEST NR NOT REPORTED 1 SW 03 41791 51465 DEAD BATTERY. REPLACED WITH SERVICEABLE BATTERY. 1 G 7 1 3U H2SW 2001111400054 20011114 00054 SW 2001 11 14 HEEA076833 1 20011018 G 2432 32007001 BATTERY BELL 206 206L3 1182108 SW MAIN DISCHARGED E HEEA O OTHER L NO TEST NR NOT REPORTED 1 SW 03 WEAK BATTERY. REPLACED WITH SERVICEABLE BATTERY. 1 G 7 1 3U H2SW 2001111400055 20011114 00055 SW 2001 11 14 HEEA076834 1 20011018 G 2432 32007001 BATTERY BELL 206 206L3 1182108 SW MAIN FAILED E HEEA O OTHER L NO TEST NR NOT REPORTED 1 SW 03 141BH 51303 WON'T TAKE CHARGE. REPLACED WITH SERVICEABLE BATTERY. 1 G 7 1 3U H2SW 2001111400057 20011114 00057 SW 2001 11 14 HEEA076835 1 20011018 G 2432 32007001 BATTERY BELL 206 206L3 1182108 SW MAIN DISCHARGED E HEEA O OTHER L NO TEST NR NOT REPORTED 1 SW 03 6160Y 51609 DEAD. REPLACED WITH SERVICEABLE BATTERY. 1 G 7 1 3U H2SW 2001111400059 20011114 00059 SW 2001 11 14 HEEA076836 1 20011018 G 2432 32007001 BATTERY BELL 206 206L1 1182107 SW MAIN DISCHARGED E HEEA O OTHER L NO TEST NR NOT REPORTED 1 SW 03 1078D 45397 WEAK. REPLACED WITH SERVICEABLE BATTERY. 1 G 7 1 3U H2SW 2001111400061 20011114 00061 SW 2001 11 14 HEEA076837 1 20011018 G 2432 32007001 BATTERY BELL 206 206L3 1182108 SW MAIN DISCHARGED E HEEA O OTHER L NO TEST NR NOT REPORTED 1 SW 03 141BH 51303 WEAK. REPLACED WITH SERVICEABLE BATTERY. 1 G 7 1 3U H2SW 2001111400066 20011114 00066 SW 2001 11 14 HEEA076838 1 20011018 G 2432 32007001 BATTERY BELL 206 206L3 1182108 SW MAIN DISCHARGED E HEEA O OTHER L NO TEST NR NOT REPORTED 1 SW 03 6161A 51611 WEAK. REPLACED WITH SERVICEABLE BATTERY. 1 G 7 1 3U H2SW 2001111400067 20011114 00067 SW 2001 11 14 HEEA076839 1 20011018 G 2432 32007001 BATTERY BELL 206 206L3 1182108 SW MAIN DISCHARGED E HEEA O OTHER L NO TEST NR NOT REPORTED 1 SW 03 41791 51465 WEAK. REPLACED WITH SERVICEABLE BATTERY. 1 G 7 1 3U H2SW 2001111400068 20011114 00068 SW 2001 11 14 HEEA076840 1 20011018 G 2432 32007001 BATTERY BELL 206 206L3 1182108 SW MAIN DISCHARGED E HEEA O OTHER L NO TEST NR NOT REPORTED 1 SW 03 54641 51184 WEAK. REPLACED WITH SERVICEABLE BATTERY. 1 G 7 1 3U H2SW 2001111400069 20011114 00069 SW 2001 11 14 HEEA076841 1 20011018 G 2432 32007001 BATTERY BELL 206 206L3 1182108 SW MAIN DISCHARGED E HEEA O OTHER L NO TEST NR NOT REPORTED 1 SW 03 4835 51131 WEAK. REPLACED WITH SERVICEABLE BATTERY. 1 G 7 1 3U H2SW 2001111400071 20011114 00071 SW 2001 11 14 HEEA076842 1 20011018 G 2432 32007001 BATTERY BELL 206 206L3 1182108 SW MAIN DISCHARGED E HEEA O OTHER L NO TEST NR NOT REPORTED 1 SW 03 6251Y 51556 WEAK. REPLACED WITH SERVICEABLE BATTERY. 1 G 7 1 3U H2SW 2001111400072 20011114 00072 SW 2001 11 14 HEEA076843 1 20011018 G 2432 32007001 BATTERY BELL 206 206L3 1182108 SW MAIN DISCHARGED E HEEA O OTHER L NO TEST NR NOT REPORTED 1 SW 03 4835 51131 WEAK. REPLACED WITH SERVICEABLE BATTERY. 1 G 7 1 3U H2SW 2001111400073 20011114 00073 SW 2001 11 14 HEEA076844 1 20011018 G 2432 32007001 BATTERY BELL 206 206L3 1182108 SW MAIN DISCHARGED E HEEA O OTHER L NO TEST NR NOT REPORTED 1 SW 03 6160Z 51610 WEAK. REPLACED WITH SERVICEABLE BATTERY. 1 G 7 1 3U H2SW 2001111400075 20011114 00075 SW 2001 11 14 HEEA076845 1 20011018 G 2432 32007001 BATTERY BELL 206 206L3 1182108 SW MAIN DISCHARGED E HEEA O OTHER L NO TEST NR NOT REPORTED 1 SW 03 6160Z 51610 WEAK. REPLACED WITH SERVICEABLE BATTERY. 1 G 7 1 3U H2SW 2001111400076 20011114 00076 SW 2001 11 14 HEEA076846 1 20011018 G 2432 32007001 BATTERY BELL 206 206L3 1182108 SW MAIN DISCHARGED E HEEA O OTHER L NO TEST NR NOT REPORTED 1 SW 03 8591X 51495 WEAK. REPLACED WITH SERVICEABLE BATTERY. 1 G 7 1 3U H2SW 2001111400080 20011114 00080 SW 2001 11 14 HEEA076847 1 20011018 G 2432 32007001 BATTERY BELL 206 206L3 1182108 SW MAIN OVERHEATED E HEEA O OTHER M J OVER TEMP WARNING INDICATION NR NOT REPORTED 1 SW 03 81SP 51029 BATTERY HOT LIGHT. REPLACED WITH SERVICEABLE BATTERY. 1 G 7 1 3U H2SW 2001111400093 20011114 00093 SW 2001 11 14 HEEA076848 1 20011018 G 2432 32007001 BATTERY BELL 206 206L3 1182108 SW MAIN DISCHARGED E HEEA O OTHER L NO TEST NR NOT REPORTED 1 SW 03 32041 51539 WEAK. REPLACED WITH SERVICEABLE BATTERY. 1 G 7 1 3U H2SW 2001111400094 20011114 00094 SW 2001 11 14 HEEA076849 1 20011018 G 2432 32007001 BATTERY BELL 206 206L3 1182108 SW MAIN DISCHARGED E HEEA O OTHER L NO TEST NR NOT REPORTED 1 SW 03 41791 51465 WEAK. REPLACED WITH SERVICEABLE BATTERY. 1 G 7 1 3U H2SW 2001111400095 20011114 00095 SW 2001 11 14 HEEA076850 1 20011019 G 2840 407362005103 SWITCH BELL 407 407 1182206 SW FUEL INDICATION MALFUNCTIONED E HEEA O OTHER N FALSE WARNING NR NOT REPORTED 1 SW 03 417PH 53038 LOW LEVEL LIGHT STAYS ON. 1 G 7 1 3U O H2SW 2001111400096 20011114 00096 SW 2001 11 14 HEEA076851 1 20011019 G 6710 406310405101 UNIVERSAL BELL 407 407 1182206 SW MAIN ROTOR WORN E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 510PH 53209 UNIVERSAL WORN. 1 G 7 1 3U O H2SW 2001111400098 20011114 00098 SW 2001 11 14 HEEA076852 1 20011019 G 3212 206373902103 RELIEF VALVE BELL 407 407 1182206 SW MLG MALFUNCTIONED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 404PH 53188 RELIEF VALVE KEPT RELEASING PRESSURE DOWN TO 2750 PSI. 1 G 7 1 3U O H2SW 2001111400099 20011114 00099 SW 2001 11 14 HEEA076853 1 20011019 G 3212 206050247135 COVER BELL 407 407 1182206 SW MLG FLOAT DAMAGED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 495PH 53397 END COVERS COMING UNSEWN. 1 G 7 1 3U O H2SW 2001111400113 20011114 00113 SW 2001 11 14 HEEA076854 1 20011019 G 3212 206050247138 COVER BELL 407 407 1182206 SW MLG FLOAT DAMAGED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 491PH 53386 END COVERS COMING UNSEWN. 1 G 7 1 3U O H2SW 2001111400114 20011114 00114 SW 2001 11 14 HEEA076856 1 20011019 G 2510 407370720101 SEAT BELT BELL 407 407 1182206 SW COCKPIT DAMAGED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 8595X 53267 SHOULDER STRAP FRAYED FROM WEAR. 1 G 7 1 3U O H2SW 2001111400115 20011114 00115 SW 2001 11 14 HEEA076857 1 20011019 G 3212 206050247138 COVER BELL 407 407 1182206 SW MLG FLOAT DETERIORATED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 4999 53323 DETERIORATED. 1 G 7 1 3U O H2SW 2001111400117 20011114 00117 SW 2001 11 14 HEEA076858 1 20011019 G 3212 212073905001 GAUGE BELL 407 407 1182206 SW MLG FLOAT DAMAGED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 402PH 53159 PRESSURE GAUGE HAS MOISTURE AND RUST. 1 G 7 1 3U O H2SW 2001111400121 20011114 00121 SW 2001 11 14 HEEA076859 1 20011019 G 7810 407063001101 EXHAUST STACK BELL 407 407 1182206 SW ENGINE CRACKED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 510PH 53209 EXHAUST STACK CRACKED. 1 G 7 1 3U O H2SW 2001111400122 20011114 00122 SW 2001 11 14 HEEA076860 1 20011019 G 6720 406312103101 LINK BELL 407 407 1182206 SW TAI ROTOR WORN E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 612PH 53199 LINK HAS WORN BEARINGS. 1 G 7 1 3U O H2SW 2001111400125 20011114 00125 SW 2001 11 14 HEEA076862 1 20011019 G 2822 206076030111 PUMP BELL 407 407 1182206 SW FUEL BOOST WORN E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 501PH 864 53401 PUMP SHAFT SPLINE WEAR. 1 G 7 1 3U O H2SW 2001111400126 20011114 00126 SW 2001 11 14 HEEA076863 1 20011019 G 6300 407010206103 SPRING BELL 407 407 1182206 SW MAIN ROTOR WORN E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 721PH 2952 53278 WORN BEARINGS. 1 G 7 1 3U O H2SW 2001111400127 20011114 00127 SW 2001 11 14 HEEA076864 1 20011019 G 6710 406010426101 LINK BELL 407 407 1182206 SW MAIN ROTOR WORN E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 499PH 2025 53400 LINK HAS WORN BUSHINGS. 1 G 7 1 3U O H2SW 2001111400140 20011114 00140 SW 2001 11 14 HEEA076865 1 20011019 G 6710 406010426101 LINK BELL 407 407 1182206 SW MAIN ROTOR WORN E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 499PH 2025 53400 LINK HAS WORN BUSHINGS. 1 G 7 1 3U O H2SW 2001111400142 20011114 00142 SW 2001 11 14 HEEA076866 1 20011019 G 6710 406010426101 LINK BELL 407 407 1182206 SW MAIN ROTOR WORN E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 499PH 53400 LINK HAS WORN BUSHINGS. 1 G 7 1 3U O H2SW 2001111400143 20011114 00143 SW 2001 11 14 HEEA076867 1 20011019 G 6710 406010426101 LINK BELL 407 407 1182206 SW MAIN ROTOR WORN E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 499PH 2025 53400 LINK HAS WORN BUSHINGS. 1 G 7 1 3U O H2SW 2001111400145 20011114 00145 SW 2001 11 14 HEEA076869 1 20011019 G 2840 407375016103 SIGNAL COND UNIT BELL 407 407 1182206 SW FUEL INDICTION MALFUNCTIONED E HEEA O OTHER N FALSE WARNING NR NOT REPORTED 1 SW 03 495PH 53397 LOW LEVEL LIGHT WILL NOT GO OUT. 1 G 7 1 3U O H2SW 2001111400146 20011114 00146 SW 2001 11 14 HEEA076870 1 20011019 G 3110 407375005101 INDICATOR BELL 407 407 1182206 SW XMSN OIL TEMP INOPERATIVE E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 457PH 53147 TRANSMISSION OIL TEMP INDICATOR INOPERATIVE. 1 G 7 1 3U O H2SW 2001111400147 20011114 00147 SW 2001 11 14 HEEA076871 1 20011019 G 2840 407375016103 SIGNAL COND UNIT BELL 407 407 1182206 SW FUEL INDICATION MALFUNCTIONED E HEEA O OTHER N FALSE WARNING NR NOT REPORTED 1 SW 03 495PH 53397 LEVEL LIGHT STAYING ON WITH 550 POUNDS OF FUEL. 1 G 7 1 3U O H2SW 2001111400148 20011114 00148 SW 2001 11 14 HEEA076872 1 20011022 G 3210 206323006 CROSSTUBE BELL 206 206L3 1182108 SW MLG CORRODED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 MLG CROSSTUBE CORRODED. 1 G 7 1 3U H2SW 2001111400152 20011114 00152 SW 2001 11 14 HEEA076873 1 20011023 G 6710 406010429101 PIN BELL 407 407 1182206 SW MAIN ROTOR WORN E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 499PH 53400 PIN WORN. 1 G 7 1 3U O H2SW 2001111400158 20011114 00158 SW 2001 11 14 HEEA076874 1 20011023 G 6300 406040316101 ADAPTER BELL 407 407 1182206 SW MAIN ROTOR WORN E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 402PH 53159 ADAPTER HAS WORN SPLINES. 1 G 7 1 3U O H2SW 2001111400159 20011114 00159 SW 2001 11 14 HEEA076875 1 20011023 G 6710 406010429101 PIN BELL 407 407 1182206 SW MAIN ROTOR WORN E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 417PH 53038 PIN WORN. 1 G 7 1 3U O H2SW 2001111400160 20011114 00160 SW 2001 11 14 HEEA076878 1 20011023 G 6321 206340301103 BRAKE BELL 407 407 1182206 SW MAIN ROTOR LEAKING E HEEA O OTHER K FLUID LOSS NR NOT REPORTED 1 SW 03 467PH 3152 53142 ROTOR BRAKE IS DAMAGED AND LEAKS. 1 G 7 1 3U O H2SW 2001111400161 20011114 00161 SW 2001 11 14 HEEA076879 1 20011023 G 6321 HOUSING BELL 407 407 1182206 SW ROTOR BRAKE WORN E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 490PH 1638 53378 EXCESSIVE HOUSING WEAR. 1 G 7 1 3U O H2SW 2001111400162 20011114 00162 SW 2001 11 14 HEEA076880 1 20011023 G 6230 406010401115 SWASHPLATE BELL 407 407 1182206 SW MAIN ROTOR WORN E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 447PH 53114 DUPLEX BEARING WORN. 1 G 7 1 3U O H2SW 2001111500001 20011115 00001 SW 2001 11 15 HEEA076881 1 20011023 G 6710 406010428109 HUB BELL 407 407 1182206 SW MAIN ROTOR WORN E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 417PH 646 53038 HUB IS WORN. 1 G 7 1 3U O H2SW 2001111500008 20011115 00008 SW 2001 11 15 HEEA076884 1 20011024 G 3110 407375003107 INDICATOR BELL 407 407 1182206 SW TORQUE MALFUNCTIONED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 404PH 53188 GOES TO TEST IN FLIGHT. 1 G 7 1 3U O H2SW 2001111500009 20011115 00009 SW 2001 11 15 HEEA076885 1 20011024 G 6320 407340339101 BEARING PHIPBH40701 BELL 407 407 1182206 SW COOLER BLOWER ROUGH E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 742PH 44 PHI0039 53461 ROUGH AND NOISY. 1 G 7 1 3U O H2SW 2001111500010 20011115 00010 SW 2001 11 15 HEEA076886 1 20011024 G 6320 206040156001 SEAL BELL 407 407 1182206 SW M/R GEARBOX LEAKING E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 417PH 53038 SEAL HAS OIL LEAK. 1 G 7 1 3U O H2SW 2001111500016 20011115 00016 SW 2001 11 15 HEEA076887 1 20011024 G 3212 206050247132 COVER BELL 407 407 1182206 SW MLG FLOAT TORN E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 496PH 53398 TORN. 1 G 7 1 3U O H2SW 2001111500017 20011115 00017 SW 2001 11 15 HEEA076888 1 20011024 G 3212 206050247138 COVER BELL 407 407 1182206 SW MLG FLOAT WORN E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 492PH 53390 WORN. TO BE SENT TO BELL HELICOPTER TEXTRON FOR CREDIT AGAINST REPLACEMENT PART PURCHASED. 1 G 7 1 3U O H2SW 2001111500018 20011115 00018 SW 2001 11 15 HEEA076889 1 20011024 G 3212 206050247138 FLOAT BELL 407 407 1182206 SW MLG FLOAT WORN E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 8595X 53267 WORN. 1 G 7 1 3U O H2SW 2001111500019 20011115 00019 SW 2001 11 15 HEEA076890 1 20011024 G 6510 206061432121 HOUSING BELL 407 407 1182206 SW BLOWER CRACKED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 4999 53323 BLOWER HOUSING CRACKED. 1 G 7 1 3U O H2SW 2001111500020 20011115 00020 SW 2001 11 15 HEEA076891 1 20011024 G 6510 206061432121 HOUSING BELL 407 407 1182206 SW BLOWER CRACKED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 723PH 53283 BLOWER HOUSING CRACKED. 1 G 7 1 3U O H2SW 2001111500022 20011115 00022 SW 2001 11 15 HEEA076892 1 20011024 G 2435 BRUSHES BELL 407 407 1182206 SW STARTER GEN WORN E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 723PH 96240 53283 STARTER GENERATOR HAS WORN BRUSHES. 1 G 7 1 3U O H2SW 2001111500025 20011115 00025 SW 2001 11 15 HEEA076893 1 20011024 G 6730 206076062107 SERVO BELL 407 407 1182206 SW CYCLIC WORN E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 4999 53323 PISTON ROD END BEARING WORN. 1 G 7 1 3U O H2SW 2001111500026 20011115 00026 SW 2001 11 15 HEEA076894 1 20011024 G 6321 206340301103 BRAKE BELL 407 407 1182206 SW ROTOR WORN E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 3193E 2496 53276 FOUND EXCESSIVE WEAR ON HOUSING, BRAKE PAD BOLT RETAINER HOLES AND PAD RETAINER BOLTS. OVERHAULED, MODIFIED, TESTED AND RETURNED TO AIRCRAFT. 1 G 7 1 3U O H2SW 2001111500028 20011115 00028 SW 2001 11 15 HEEA076895 1 20011024 G 3212 212073905001 GAUGE BELL 407 407 1182206 SW FLOAT PRESSURE DAMAGED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 467PH 53142 FOGGED OVER. CANNOT READ AMOUNT OF PRESSURE IN FLOAT BOTTLE. 1 G 7 1 3U O H2SW 2001111500029 20011115 00029 SW 2001 11 15 HEEA076896 1 20011024 G 3212 212073905001 GAUGE BELL 407 407 1182206 SW FLOAT PRESSURE DAMAGED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 467PH 53142 NUMBERED DIAL MOVES. UNABLE TO VERIFY EXACT AMOUNT OF PRESSURE IN FLOAT BOTTLE. T 1 G 7 1 3U O H2SW 2001111500032 20011115 00032 GL 2001 11 15 HEEA076897 2 20011024 G 7532 23005366 BLEED VALVE BELL 407 407 1182206 SW ALLSN 250C 250C47B GL ENGINE FAILED E HEEA O OTHER R J PARTIAL RPM/PWR LOSS WARNING INDICATION NR NOT REPORTED 1 SW 03 4999 53323 LOW POWER ENGINE. IN SHOP REPAIR. 1 G 7 1 3U 3 U O H2SW E1GL 2001111500036 20011115 00036 SW 2001 11 15 HEEA076898 1 20011024 G 6230 406010401117 SWASHPLATE BELL 407 407 1182206 SW MAIN ROTOR LEAKING E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 724PH 53327 GREASE LEAKING FROM TOP SEAL. 1 G 7 1 3U O H2SW 2001111500037 20011115 00037 SW 2001 11 15 HEEA076899 1 20011024 G 6520 406040400117 GEARBOX BELL 407 407 1182206 SW TAIL ROTOR WORN E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 490PH 53378 OUTPUT SHAFT SPLINE WORN. REPLACED WITH SERVICEABLE T/R GEARBOX ASSEMBLY. 1 G 7 1 3U O H2SW 2001111500049 20011115 00049 SW 2001 11 15 HEEA076900 1 20011024 G 6310 406040500123B FREEWHEEL UNIT BELL 407 407 1182206 SW MAIN ROTOR LEAKING E HEEA K NONE K FLUID LOSS IN INSP/MAINT 1 SW 03 8595X 53267 LEAKING FROM SEAL. REPLACED WITH SERVICEABLE PART. 1 G 7 1 3U O H2SW 2001111500050 20011115 00050 SW 2001 11 15 HEEA076901 1 20011024 G 6710 406310405101 UNIVERSAL BELL 407 407 1182206 SW MAIN ROTOR WORN E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 493PH 53393 RED MAIN ROTOR P/C LINK BEARING WORN WITH PLAY. 1 G 7 1 3U O H2SW 2001111500051 20011115 00051 SW 2001 11 15 HEEA076902 1 20011024 G 6710 406310405101 UNIVERSAL BELL 407 407 1182206 SW MAIN ROTOR LOOSE E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 498PH 53399 BEARING HAD RADIAL PLAY. 1 G 7 1 3U O H2SW 2001111500055 20011115 00055 SW 2001 11 15 HEEA076903 1 20011024 G 6710 406310407101 SEAL 406010401115 BELL 407 407 1182206 SW SWASHPLATE LEAKING E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 406PH A707 53198 UPPER BEARING GREASE SEAL LEAKING ON UNIBALL. 1 G 7 1 3U O H2SW 2001111500056 20011115 00056 SW 2001 11 15 HEEA076904 1 20011024 G 6230 406310411101 BOOT BELL 407 407 1182206 SW M/R MAST TORN E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 495PH 53397 MAST BOOT TORN. 1 G 7 1 3U O H2SW 2001111500058 20011115 00058 SW 2001 11 15 HEEA076905 1 20011024 G 6710 407001523101 IDLER ASSY BELL 407 407 1182206 SW M/R CONTROL WORN E K NONE O OTHER IN INSP/MAINT 1 SW 03 724PH 53327 TAIL ROTOR CONTROL IDLER ASSY HAS BEARINGS WORN. 1 G 7 1 3U O H2SW 2001111500059 20011115 00059 SW 2001 11 15 HEEA076906 1 20011024 G 6420 407012101111 HUB BELL 407 407 1182206 SW TAIL ROTOR WORN E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 490PH 1765 53378 WORN ELASTOMERIC BEARING. TO BE SENT TO BELL HELICOPTER TEXTRON FOR CREDIT AGAINST REPLACEMENT PART PURCHASED. 1 G 7 1 3U O H2SW 2001111500061 20011115 00061 SW 2001 11 15 HEEA076907 1 20011024 G 6797 407076508103 HARNESS BELL 407 407 1182206 SW INSTRUMENT PANEL FAILED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 457PH 53147 PEDAL STOP SWITCH DAMAGED BY INTERFERENCE WITH INSTRUMENT PANEL FRAME. 1 G 7 1 3U O H2SW 2001111500063 20011115 00063 SW 2001 11 15 HEEA076908 1 20011024 G 5260 407301110 STEP BELL 407 407 1182206 SW FUSELAGE CORRODED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 492PH 53390 CORRODED AT BRACKET MOUNT BOLT HOLES. REPLACED WITH SERVICEABLE STEP. 1 G 7 1 3U O H2SW 2001111500064 20011115 00064 SW 2001 11 15 HEEA076909 1 20011024 G 6220 407310101101 BEARING 407010100115 BELL 407 407 1182206 SW MAIN ROTOR WORN E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 501PH A436 53401 SHEAR BEARINGS WORN AND SEPARATING. TO BE SENT TO BELL HELICOPTER TEXTRON FOR CREDIT AGAINST REPLACEMENT PART PURCHASED. 1 G 7 1 3U O H2SW 2001111500067 20011115 00067 SW 2001 11 15 HEEA076910 1 20011024 G 6220 407310104103 SPRING 407010150105 BELL 407 407 1182206 SW FRAHM ASSY BROKEN E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 501PH A560 53401 SPRINGS FOUND BROKEN. 1 G 7 1 3U O H2SW 2001111500068 20011115 00068 SW 2001 11 15 HEEA076911 1 20011024 G 6320 407340339101 BEARING BELL 407 407 1182206 SW MAIN ROTOR OVERHEATED E HEEA K NONE M OVER TEMP IN INSP/MAINT 1 SW 03 404PH 53188 BEARING OVERHEATED. 1 G 7 1 3U O H2SW 2001111500069 20011115 00069 SW 2001 11 15 HEEA076912 1 20011024 G 6510 407340340103 DISC PACK BELL 407 407 1182206 SW TAIL ROTOR FAILED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 4999 53323 FORWARD BLOWER SHAFT BEARING FAILED. 1 G 7 1 3U O H2SW 2001111500070 20011115 00070 2001 11 15 HEEA076913 4 20011024 G 3120 M803B205VBATT LIGHT BELL 407 407 1182206 SW CLOCK INOPERATIVE E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 498PH 53399 HALF OF INDICATOR BACKLIGHT INOPERATIVE. 1 G 7 1 3U O H2SW 2001111500071 20011115 00071 SW 2001 11 15 HEEA076914 1 20011024 G 2400 MS24509A10 SWITCH BELL 407 407 1182206 SW ELECTRICAL DIST BROKEN E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 8595X 53267 BROKEN INTERNALLY. REPLACED WITH SERVICEABLE SWITCH. 1 G 7 1 3U O H2SW 2001111500093 20011115 00093 SW 2001 11 15 HEEA076918 1 20011024 G 6200 206011135105 BOLT BELL 206 206L3 1182108 SW MAIN ROTOR DAMAGED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 NICKS IN THREADED AREA. 1 G 7 1 3U H2SW 2001111500094 20011115 00094 SW 2001 11 15 HEEA076919 1 20011026 G 6700 206011732103 SLEEVE BELL 407 407 1182206 SW CONTROL TUBE WORN E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 612PH 53199 PART IS WORN EXCESSIVELY. 1 G 7 1 3U O H2SW 2001111500095 20011115 00095 SW 2001 11 15 HEEA076920 1 20011026 G 6220 BEARING 407010100115 BELL 407 407 1182206 SW M/R HUB SHEARED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 501PH A436 53401 SHEARING BEARINGS SEPARATION. 1 G 7 1 3U O H2SW 2001111500096 20011115 00096 SW 2001 11 15 HEEA076921 1 20011026 G 6420 407012101111 HUB BELL 407 407 1182206 SW TAIL ROTOR WORN E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 741PH 1022 53457 WORN BEARING, CLICKING NOISE. PARTS AND LABOR CREDIT ACCOMPLISHED ON J0189948-WA. 1 G 7 1 3U O H2SW 2001111500097 20011115 00097 SW 2001 11 15 HEEA076922 1 20011026 G 6510 407340339103 BEARING 407040302107 BELL 407 407 1182206 SW TAIL ROTOR ROUGH E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 491PH A1871 53386 BEARING ROUGH. 1 G 7 1 3U O H2SW 2001111500098 20011115 00098 SW 2001 11 15 HEEA076923 1 20011026 G 6510 407340339103 BEARING 407040302107 BELL 407 407 1182206 SW TAIL ROTOR ROUGH E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 491PH A1875 53386 ROUGH. 1 G 7 1 3U O H2SW 2001111500099 20011115 00099 SW 2001 11 15 HEEA076924 1 20011026 G 6300 407340339101 BEARING BELL 407 407 1182206 SW MAIN ROTOR WORN E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 BEARING WORN. 1 G 7 1 3U O H2SW 2001111500108 20011115 00108 SW 2001 11 15 HEEA076926 1 20011026 G 7931 209070262101 INDICATOR BELL 412 412 1182202 SW OIL PRESSURE READS HIGH E HEEA O OTHER N FALSE WARNING CL CLIMB 1 SW 03 33008 36004 AFTER TAKEOFF, PILOT NOTED NR 2 ENGINE OIL PRESSURE WAS INDICATING HIGH. REPLACED OIL TEMP/PRESS INDICATOR. 1 G 7 2 4U H4SW 2001111500110 20011115 00110 EU 2001 11 15 HEEA076927 1 20011019 G 6220 350A31191600 STARFLEX SNIAS 350 AS350B 8680801 EU MAIN ROTOR CRACKED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 970AE 317 3235 CRACKED SPHERICAL STOP CUT OUT AREA, LOWER AFT AS MARKED. 1 G 7 1 3U H9EU 2001111500112 20011115 00112 2001 11 15 HEEA076928 4 20011019 G 3120 B1894522282A CLOCK SNIAS 350 AS350B 8680801 EU COCKPIT INACCURATE E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 856PH 3352 DOES NOT KEEP CORRECT TIME. 1 G 7 1 3U H9EU 2001111500113 20011115 00113 2001 11 15 HEEA076936 4 20011030 G 3416 066104800 ALTIMETER SKRSKY S76 S76A 8143006 NE COCKPIT ERRATIC E HEEA K NONE L NO TEST IN INSP/MAINT 1 SW 03 911MJ 760231 RT WAS CAUSING ERRATIC READING ON APPROACH. REPLACED WITH SERVICEABLE PART. 1 G 7 2 3U H1NE 2001111500114 20011115 00114 NE 2001 11 15 HEEA076937 1 20011031 G 6410 7610105101041 BLADE SKRSKY S76 S76A 8143006 NE TAIL ROTOR CORRODED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 1546G 8350 760076 CORROSION ON BOX BEAM AND TRAILING IS SPLIT OPEN ON PADDLE "B". PENDING VENDOR REPAIR. 1 G 7 2 3U H1NE 2001111500115 20011115 00115 NE 2001 11 15 HEEA076938 1 20011031 G 6220 7610208500046 SPINDLE SKRSKY S76 S76A 8143006 NE MAIN ROTOR BINDING E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 1545K 760047 DROOP STOP BINDS UP WHEN INSTALLED. FOUND WHEN TORQUEING UP SPINDLE. A BIND PREVENTS THE DROOP STOP FROM RETURNING TO STATIC POSITION AT SHUTDOWN. IT IS FREE TO MOVE WHEN NOT INSTALLED. PENDING VENDOR REPAIR. 1 G 7 2 3U H1NE 2001111500116 20011115 00116 NE 2001 11 15 HEEA076939 1 20011031 G 6210 7615009043050 TIP CAP SKRSKY S76 S76A 8143006 NE MAIN ROTOR CRACKED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 760PH 760078 OUTER DOUBLER ON LOWER SIDE CRACKED AND HAS "C" CHANNEL DEBONDED. PENDING VENDOR REPAIR. 1 G 7 2 3U H1NE 2001111500118 20011115 00118 NE 2001 11 15 HEEA076940 1 20011031 G 6210 7615009043054 TIP CAP SKRSKY S76 S76C 8143008 NE MAIN ROTOR CRACKED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 505PH 760505 FIBERGLASS SKIN NEAR THE TRAILING EDGE IS CRACKED AND HAS SOME SEPARATION NEXT TO THE ABRASION STRIP. PENDING VENDOR REP AIR. 1 G 7 2 3U NC H1NE 2001111500119 20011115 00119 NE 2001 11 15 HEEA076941 1 20011031 G 6210 7615009100041A BLADE SKRSKY S76 S76A 8143006 NE MAIN ROTOR CRACKED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 1545K 12595 760047 LEADING EDGE TITANIUM STRIP HAS A COMPLETE CHORDWISE CRACK WITH MULTIPLE BRANCH WHICH EXTENDS BEYOND LIMITS. PENDING VEN DOR REPAIR. 1 G 7 2 3U H1NE 2001111500120 20011115 00120 NE 2001 11 15 HEEA076942 1 20011031 G 6210 7615009100042A BLADE SKRSKY S76 S76A 8143006 NE MAIN ROTOR CRACKED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 911MJ 14090 760231 TRAILING EDGE CRACKED JUST INBOARD OF TRIM TAB. REPLACED WITH SERVICEABLE BLADE. 1 G 7 2 3U H1NE 2001111500121 20011115 00121 NE 2001 11 15 HEEA076943 1 20011031 G 6210 7615009100053 BLADE SKRSKY S76 S76A 8143006 NE MAIN ROTOR DAMAGED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 911MJ 5266 760231 TRAILING EDGE DAMAGE AT AREA OF P/N - S/N STENCIL. REPLACED WITH SERVICEABLE BLADE. 1 G 7 2 3U H1NE 2001111500122 20011115 00122 NE 2001 11 15 HEEA076944 1 20011031 G 6320 7635109045102 GEAR SKRSKY S76 S76A 8143006 NE M/R GEARBOX MISMANUFACTURED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 RIVET NOT INSTALLED IN GEAR. RIVET REQUIRED TO PREVENT OIL FROM LEAKING. PENDING VENDOR REPAIR. 1 G 7 2 3U H1NE 2001111500123 20011115 00123 NE 2001 11 15 HEEA076945 1 20011031 G 6320 7635109500043 TRANSMISSION SKRSKY S76 S76A 8143006 NE MAIN ROTOR MAKING METAL E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 911MJ 10333 760231 CHIP LIGHT ON LANDING. INSPECTED AND FOUND A 1/2" BY 3/16" PIECE OF A GEAR TOOTH ON THE LEFT CHIP PLUG. REPLACED WITH S ERVICEABLE ASSEMBLY. 1 G 7 2 3U H1NE 2001111500125 20011115 00125 NE 2001 11 15 HEEA076946 1 20011031 G 3340 7655002005101 LIGHT SKRSKY S76 S76A 8143006 NE SEARCH LIGHT MALFUNCTIONED E HEEA K NONE L NO TEST IN INSP/MAINT 1 SW 03 792CH 760193 WILL NOT MOVE UP OR DOWN. REPLACED WITH SERVICEABLE PART. 1 G 7 2 3U H1NE 2001111500127 20011115 00127 NE 2001 11 15 HEEA076947 1 20011031 G 6730 7665009803106 POWERPACK SKRSKY S76 S76A 8143006 NE SERVO SYSTEM CRACKED E HEEA K NONE L NO TEST IN INSP/MAINT 1 SW 03 911MJ 760231 POWER PACK HOUSING CRACKED AT DRAIN FITTING. PENDING VENDOR REPAIR. 1 G 7 2 3U H1NE 2001111500130 20011115 00130 GL 2001 11 15 HEEA076948 2 20011031 G 7421 9550166530 LEAD SKRSKY S76 S76A 8143006 NE ALLSN 250C 250C30S 03013 GL IGNITER FRAYED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 760PH 760078 FRAYED AND WORN. REPLACED WITH SERVICEABLE PART. 1 G 7 2 3U 3 U H1NE E1GL 2001111500132 20011115 00132 GL 2001 11 15 HEEA076949 2 20011031 G 7421 9550166670 IGNITER SKRSKY S76 S76A 8143006 NE ALLSN 250C 250C30S 03013 GL ENGINE FRAYED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 760PH 760078 FRAYED AND WORN. REPLACED WITH SERVICEABLE PART. 1 G 7 2 3U 3 U H1NE E1GL 2001111500133 20011115 00133 GL 2001 11 15 HEEA076950 2 20011031 G 7421 9550168770 IGNITER SKRSKY S76 S76A 8143006 NE ALLSN 250C 250C30S 03013 GL ENGINE DAMAGED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 760PH 760078 INOPERATIVE - WILL NOT FIRE. CENTER ELETRODE CAME OUT. REPLACED WITH SERVICEABLE PART. 1 G 7 2 3U 3 U H1NE E1GL 2001111500134 20011115 00134 NE 2001 11 15 HEEA076951 1 20011031 G 7410 9550176020 GENERATOR SKRSKY S76 S76A 8143006 NE ALLSN 250C 250C30S 03013 GL IGNITER CORRODED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 760PH 760078 CORROSION. REPLACED WITH SERVICEABLE PART. 1 G 7 2 3U 3 U H1NE E1GL 2001111500135 20011115 00135 2001 11 15 HEEA076952 4 20011031 G 2340 A3016W INTERPHONE SKRSKY S76 S76A 8143006 NE COCKPIT MALFUNCTIONED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 5435V 760158 COMM NR 1 TRANSMITS GARBLED. REPLACED WITH SERVICEABLE PART. 1 G 7 2 3U H1NE 2001111500136 20011115 00136 2001 11 15 HEEA076953 4 20011031 G 3442 7007700613 INDICATOR SKRSKY S76 S76C 8143008 NE RADAR SYSTEM INTERMITTENT E HEEA K NONE L NO TEST IN INSP/MAINT 1 SW 03 505PH 760505 INTERMITTENTLY DISPLAYS FAIL. PENDING VENDOR REPAIR. 1 G 7 2 3U NC H1NE 2001111500137 20011115 00137 2001 11 15 HEEA076954 4 20011031 G 2350 AA34300 CONNECTOR SKRSKY S76 S76A 8143006 NE RADIO FAILED E HEEA K NONE L NO TEST IN INSP/MAINT 1 SW 03 913UK 760276 CANNOT PROGRAM MOTOROLA MCS 2000 RADIO. PENDING VENDOR REPAIR. 1 G 7 2 3U H1NE 2001111500139 20011115 00139 2001 11 15 HEEA076955 4 20011031 G 3457 N0002000 GPS COCKPIT FAILED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 NEW UNIT DOES NOT GIVE GPS POSITION AND TRANSMITS INTERMITTENTLY WITH CDU. TO BE SENT TO VENDOR FOR WARRANTY REPAIR. 2001111600047 20011116 00047 EU 2001 11 16 HEEA076956 1 20011101 G 7100 0292005220 ENGINE SNIAS 350 AS350B2 8680813 EU TMECA ARRIEL ARRIEL1D NE NACELLE MAKING METAL E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 40466 5392 3004 ENGINE MAKING METAL. 1 G 7 1 3U 3 U H9EU E19EU 2001111600050 20011116 00050 2001 11 16 HEEA076957 4 20011030 G 3457 0110005400 GPS BELL 206 206L1 1182107 SW COCKPIT FAILED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 5007Q 45187 TAKES AN EXTENDED PERIOD OF TIME TO ACQUIRE SATTELITES. REPLACED WITH SERVICEABLE PART. 1 G 7 1 3U H2SW 2001111600051 20011116 00051 2001 11 16 HEEA076958 4 20011030 G 2312 064100900 TRANSCEIVER BELL 412 412 1182202 SW COCKPIT MALFUNCTIONED E HEEA K NONE L NO TEST IN INSP/MAINT 1 SW 03 2261D 33076 TRANSMITS WEAK AND GARBLED. REPLACED WITH SERVICEABLE PART. 1 G 7 2 4U H4SW 2001111600053 20011116 00053 2001 11 16 HEEA076959 4 20011030 G 2312 064102300 TRANSCEIVER BELL 412 412 1182202 SW COCKPIT INTERMITTENT E HEEA K NONE L NO TEST IN INSP/MAINT 1 SW 03 107X 33113 UNIT CUTS OUT IN FLIGHT INTERMTTENTLY. REPLACED WITH SERVICEABLE PART. 1 G 7 2 4U H4SW 2001111600054 20011116 00054 2001 11 16 HEEA076960 4 20011030 G 2312 064102300 TRANSCEIVER BELL 412 412 1182202 SW COCKPIT WEAK E HEEA K NONE L NO TEST IN INSP/MAINT 1 SW 03 6559Z 36019 RECEIVES VERY WEAK/ TRANSMITS GOOD. REPLACED WITH SERVICEABLE PART. 1 G 7 2 4U H4SW 2001111600055 20011116 00055 2001 11 16 HEEA076961 4 20011030 G 2312 064105430 TRANSCEIVER BELL 206 206L3 1182108 SW COCKPIT INOPERATIVE E HEEA K NONE L NO TEST IN INSP/MAINT 1 SW 03 30KH 51527 INOPERATIVE. REPLACED WITH SERVICEABLE PART. 1 G 7 1 3U H2SW 2001111600056 20011116 00056 2001 11 16 HEEA076962 4 20011030 G 3455 066104701 TRANSCEIVER BELL 412 412 1182202 SW ADF SYSTEM MALFUNCTIONED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 2261D 33076 WILL NOT PAINT AND NO AUDIO. REPLACED WITH SERVICEABLE PART. 1 G 7 2 4U H4SW 2001111600058 20011116 00058 2001 11 16 HEEA076963 4 20011030 G 3452 066106200 TRANSPONDER BELL 206 206L3 1182108 SW COCKPIT INTERFERENCE E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 31821 51076 TRANSPONDER SQUAWKING 24000 FEET. REPLACED WITH SERVICEABLE PART. 1 G 7 1 3U H2SW 2001111600060 20011116 00060 2001 11 16 HEEA076964 4 20011030 G 3452 066107100 TRANSPONDER BELL 412 412 1182202 SW COCKPIT INOPERATIVE E HEEA K NONE L NO TEST IN INSP/MAINT 1 SW 03 7128R 36007 INOPERATIVE, WILL NOT TRANSMIT. PENDING VENDOR REPAIR. 1 G 7 2 4U H4SW 2001111600061 20011116 00061 2001 11 16 HEEA076965 4 20011030 G 3452 066107100 TRANSPONDER BELL 214 214ST 1182106 SW COCKPIT INOPERATIVE E HEEA K NONE L NO TEST IN INSP/MAINT 1 SW 03 59806 28140 INOPERATIVE. PENDING VENDOR REPAIR. 2 G 7 2 4U H10SW 2001111600066 20011116 00066 2001 11 16 HEEA076966 4 20011030 G 3100 071119208 CONTROL SWITCH BELL 412 412 1182202 SW COCKPIT FAILED E HEEA O OTHER O OTHER IN INSP/MAINT 1 SW 03 2148K 36001 STATION KNOB WHEN TURN TO RIGHT IT SPRINGS BACK TO LEFT. REPLACED WITH SERVICEABLE PART. 1 G 7 2 4U H4SW 2001111600067 20011116 00067 2001 11 16 HEEA076967 4 20011030 G 3400 071121525 CONTROL UNIT BELL 412 412 1182202 SW COCKPIT INOPERATIVE E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 107X 33113 SEVERAL SEGMENTS INOPERATIVE. REPLACED WITH SERVICEABLE PART. COULD NOT VERIFY COMPLAINT. BENCH CHECK GOOD. 1 G 7 2 4U H4SW 2001111600073 20011116 00073 2001 11 16 HEEA076968 4 20011030 G 2312 071121525 CONTROL UNIT BELL 412 412 1182202 SW COCKPIT INTERMITTENT E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 2148K 36001 DIGITS INTERMITTENTLY LOSE PART OF NUMBERS. REPLACED WITH SERVICEABLE PART. 1 G 7 2 4U H4SW 2001111600082 20011116 00082 2001 11 16 HEEA076969 4 20011030 G 3454 071121627 CONTROL UNIT BELL 412 412 1182202 SW NAVIGATION FAILED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 2148K 36001 WHEN SUN HITS KFS, IT DOES NOT GET BRIGHT. REPLACED WITH SERVICEABLE PART. 1 G 7 2 4U H4SW 2001111600083 20011116 00083 SW 2001 11 16 HEEA076970 1 20011030 G 2422 INVERTER BELL 412 412 1182202 SW ELECTRIAL FAILED E HEEA O OTHER B SMOKE/FUMES/ODORS/SPARKS NR NOT REPORTED 1 SW 03 142PH 33150 NR 1 INVERTER DROPPED OFF LINE AND ELECTRICAL FUMES WERE NOTED BY PILOT. FOUND BURNED WIRE IN WINDSHIELD POST COVER AT T OP OF POST. 1 G 7 2 4U H4SW 2001111600084 20011116 00084 SW 2001 11 16 HEEA076971 1 20011030 G 2820 AE89411M VENT BELL 412 412 1182202 SW FUEL SYSTEM LEAKING E HEEA O OTHER K B FLUID LOSS SMOKE/FUMES/ODORS/SPARKS NR NOT REPORTED 1 SW 03 22608 33075 HAD STRONG FUEL ODOR IN COCKPIT. FOUND A SMALL AMOUNT OF FUEL HAD SEEPED THROUGH THE RT EXTERNAL TANK VENT DUE TO HIGH F UEL LEVEL AND THE ATTITUDE OF THE AIRCRAFT. 1 G 7 2 4U H4SW 2001111600085 20011116 00085 SW 2001 11 16 HEEA076972 1 20011031 G 3212 206030104023 FITTING BELL 206 206L3 1182108 SW MLG FLOAT CHAFED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 6251X 51552 PART IS CHAFED. REPLACED WITH SERVICEABLE FITTING. 1 G 7 1 3U H2SW 2001111600086 20011116 00086 SW 2001 11 16 HEEA076973 1 20011031 G 6300 206033501004 FITTING BELL 206 206L3 1182108 SW MAIN ROTOR CORRODED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 54641 51184 FITTING IS CORRODED BEYOND LIMITS. REPLACED WITH SERVICEABLE PART. 1 G 7 1 3U H2SW 2001111600088 20011116 00088 SW 2001 11 16 HEEA076974 1 20011031 G 6320 206033518007 STOP BELL 206 206L3 1182108 SW M/R GEARBOX DETERIORATED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 31077 51520 DETERIORATION. REPLACED WITH SERVICEABLE PART. 1 G 7 1 3U H2SW 2001111600089 20011116 00089 SW 2001 11 16 HEEA076975 1 20011031 G 3210 206052105013 STRAP BELL 206 206L3 1182108 SW MLG CORRODED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 6251X 51552 CORROSION. REPLACED WITH SERVICEABLE PART. 1 G 7 1 3U H2SW 2001111600090 20011116 00090 SW 2001 11 16 HEEA076976 1 20011031 G 6710 206076062003 CYLINDER BELL 206 206L3 1182108 SW CYCLIC LEAKING E HEEA O OTHER K FLUID LOSS NR NOT REPORTED 1 SW 03 3116L 51529 LEAKING BEYOND LIMITS ON END CAP SIDE OF SERVO. PENDING VENDOR REPAIR. 1 G 7 1 3U H2SW 2001111600091 20011116 00091 SW 2001 11 16 HEEA076977 1 20011031 G 7800 212061117001 TUBE BELL 412 412 1182202 SW EXHAUST WORN E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 1202T 33112 WORN BEARINGS. REPLACED WITH SERVICEABLE TUBE ASSY. 1 G 7 2 4U H4SW 2001111600093 20011116 00093 SW 2001 11 16 HEEA076978 1 20011031 G 6710 214001347005 ACTUATOR BELL 412 412 1182202 SW AUTO FLIGHT INTERMITTENT E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 1202T 33112 STICKS INTERMITTENTLY. PENDING VENDOR REPAIR. 1 G 7 2 4U H4SW 2001111600096 20011116 00096 2001 11 16 HEEA076979 4 20011031 G 3424 214075244001 GYRO BELL 412 412 1182202 SW COCKPIT INOPERATIVE E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 2148K 36001 CO-PILOT RATE OF TURN NEEDLE DOES NOT MOVE. PENDING VENDOR REPAIR. 1 G 7 2 4U H4SW 2001111600098 20011116 00098 SW 2001 11 16 HEEA076980 1 20011031 G 6220 222310504101 BEARING BELL 230 230 1182149 SW MAIN ROTOR DELAMINATED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 911RC 23037 DELAMINATION. PENDING VENDOR REPAIR. 1 G 7 2 3U NC H9SW 2001111600102 20011116 00102 SW 2001 11 16 HEEA076981 1 20011031 G 2435 23032048 STARTER GEN BELL 212 212 1181420 SW ENGINE FAILED E HEEA O OTHER M B OVER TEMP SMOKE/FUMES/ODORS/SPARKS NR NOT REPORTED 1 SW 03 102PH 30899 RED GLOW WAS OBSERVED IN THE STARTER GENERATOR FOLLOWED BY SMOKE, STARTER NEVER ENGAGED. REPLACED WITH SERVICEABLE PART. 1 G 7 1 4U H4SW 2001111600103 20011116 00103 NE 2001 11 16 HEEA076982 2 20011031 G 7323 25249994 GOVERNOR BELL 412 412 1182202 SW PWA PT6T PT6T3B 52045 NE ENGINE OSCILLATES E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 5759N 33002 ENGINE OSCILLATES AT 100 PERCENT ON GROUND. REPLACED WITH SERVICEABLE PART. 1 G 7 2 4U 4 U H4SW E22EA 2001111600104 20011116 00104 SW 2001 11 16 HEEA076983 1 20011031 G 2822 2C271 CARTRIDGE BELL 206 206L1 1182107 SW BOOST PUMP FAILED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 5007N 45184 LT BOOST PUMP FUEL PRESSURE DROPPED TO ZERO, LT BOOST PUMP LIGHT ILLUMINATED. REPLACED WITH SERVICEABLE PART. 1 G 7 1 3U H2SW 2001111600109 20011116 00109 NE 2001 11 16 HEEA076984 2 20011031 G 7320 324473514 FUEL CONTROL BELL 412 412 1182202 SW PWA PT6T PT6T3B 52045 NE ENGINE SURGES E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 2149S 36002 ENGINE SURGING AT 100 PERCENT NR. REPLACED WITH SERVICEABLE PART. 1 G 7 2 4U 4 U H4SW E22EA 2001111600111 20011116 00111 SW 2001 11 16 HEEA076985 1 20011031 G 2841 393008047 INDICATOR BELL 212 212 1181420 SW COCKPIT FAILED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 5736J 31140 UNIT READ ZERO. PENDING VENDOR REPAIR. 1 G 7 1 4U H4SW 2001111600112 20011116 00112 SW 2001 11 16 HEEA076986 1 20011031 G 6710 412001300105 BELLCRANK BELL 412 412 1182202 SW MAIN ROTOR INOPERATIVE E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 1202T 33112 BEARING WILL NOT ROTATE. REPLACED WITH SERVICEABLE PART. 1 G 7 2 4U H4SW 2001111600113 20011116 00113 SW 2001 11 16 HEEA076987 1 20011031 G 6220 412001900101 SUPPORT BELL 412 412 1182202 SW MAIN ROTOR WORN E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 1202T 33112 WORN BEARING. REPLACED WITH SERVICEABLE PART. 1 G 7 2 4U H4SW 2001111600115 20011116 00115 SW 2001 11 16 HEEA076988 1 20011031 G 6230 412010405109 LINK BELL 412 412 1182202 SW MAIN ROTOR DAMAGED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 1202T 33112 SPUN BEARING. REPLACED WITH SERVICEABLE PART. 1 G 7 2 4U H4SW 2001111600116 20011116 00116 SW 2001 11 16 HEEA076989 1 20011031 G 5260 412076620101 UNIVERSAL BELL 412 412 1182202 SW STEPS WORN E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 5759N 33002 WORN BEARING. REPLACED WITH SERVICEABLE PART. 1 G 7 2 4U H4SW 2001111600117 20011116 00117 SW 2001 11 16 HEEA076990 1 20011031 G 2400 51539002N CONTROL UNIT BELL 412 412 1182202 SW ELELCTRICAL FAILED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 142PH 33150 WON'T HOLD PARALLEL VOLTAGE. PENDING VENDOR REPAIR. 1 G 7 2 4U H4SW 2001111600119 20011116 00119 SW 2001 11 16 HEEA076991 1 20011031 G 2430 51509002R CONTROL UNIT BELL 412 412 1182202 SW GENERATOR FAILED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 142PH 33150 CAUSES GENERATOR TO KICK OFF LINE. PENDING VENDOR REPAIR. 1 G 7 2 4U H4SW 2001111600120 20011116 00120 2001 11 16 HEEA076992 4 20011031 G 3416 8503S20LW ALTIMETER BELL 412 412 1182202 SW COCKPIT READS LOW E HEEA O OTHER O OTHER IN INSP/MAINT 1 SW 03 142PH 33150 READS 125 FEET LOW. REPLACED WITH SERVICEABLE PART. 1 G 7 2 4U H4SW 2001111600121 20011116 00121 SW 2001 11 16 HEEA076993 1 20011031 G 6321 94501031 BRAKE BELL 412 412 1182202 SW MAIN ROTOR WORN E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 107X 33113 PUCKS WORN AND BROKEN MICRO SWITCH. REPLACED WITH SERVICEABLE PART. 1 G 7 2 4U H4SW 2001111600123 20011116 00123 2001 11 16 HEEA076994 4 20011031 G 2340 A3016W INTERPHONE BELL 412 412 1182202 SW COCKPIT DAMAGED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 2149S 36002 VOLUME KNOB SHAFT LOOSE. REPLACED WITH SERVICEABLE PART. 1 G 7 2 4U H4SW 2001111600124 20011116 00124 2001 11 16 HEEA076995 4 20011031 G 3442 MI5851352 RADAR BELL 412 412 1182202 SW COCKPIT MALFUNCTIONED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 2149S 36002 ANTENNA WOULD NOT SWEEP. REPLACED WITH SERVICEABLE PART. 1 G 7 2 4U H4SW 2001111600125 20011116 00125 2001 11 16 HEEA076996 4 20011031 G 3140 MI5852013 INDICATOR BELL 412 412 1182202 SW COCKPIT MALFUNCTIONED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 107X 33113 PICTURE PULSES AND TEST PATTERN IS BROKEN AND OFF COLOR. REPLACED WITH SERVICEABLE PART. 1 G 7 2 4U H4SW 2001111600126 20011116 00126 2001 11 16 HEEA076997 4 20011031 G 3140 MI585200 RADAR BELL 212 212 1181420 SW COCKPIT MALFUNCTIONED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 102PH 30899 PILOT HSI CIRCUIT BREAKER POPS IN FLIGHT. REPLACED WITH SERVICEABLE PART. 1 G 7 1 4U H4SW 2001111600127 20011116 00127 2001 11 16 HEEA076998 4 20011031 G 3140 MI5852013 INDICATOR BELL 212 212 1181420 SW COCKPIT FAILED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 102PH 30899 SCREEN FLASHES ON THEN OFF WITH DISTORTED IMAGING. REPLACED WITH SERVICEABLE PART. 1 G 7 1 4U H4SW 2001111600130 20011116 00130 2001 11 16 HEEA076999 4 20011031 G 3442 MI585202 RADAR BELL 412 412 1182202 SW WX SYSTEM CONTAMINATED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 2149S 36002 WEATHER RADAR HAS GAPS IN DISPLAY, FLUTTER WHILE SWEEPING. FOUND WATER IN UNIT. REPLACED WITH SERVICEABLE PART. 1 G 7 2 4U H4SW 2001111600132 20011116 00132 SW 2001 11 16 HEEA077000 1 20011031 G 6720 BUSHING BELL 412 412 1182202 SW TAIL ROTOR WORN E HEEA O OTHER O OTHER IN INSP/MAINT 1 SW 03 1202T 33112 WORN BUSHINGS AND BEARINGS. REPLACED WITH SERVICEABLE PART. 1 G 7 2 4U H4SW 2001111600133 20011116 00133 SW 2001 11 16 HEEA077001 1 20011031 G 2840 MS3108R14S5S CONNECTOR BELL 412 412 1182202 SW NR 2 ENGINE SHORTED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 22347 36005 FUEL VALVE LIGHT CAME ON. MAINTENANCE FOUND SHORTED CANNON PLUG AT NR 2 ENGINE LORI VALVE CAUSING FUEL VALVE TO CYCLE. 1 G 7 2 4U H4SW 2001111600134 20011116 00134 2001 11 16 HEEA077002 4 20011031 G 2200 212001139001 PIN BELL 412 412 1182202 SW NR 2 ENGINE LOOSE E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 107X 33113 COPILOT THROTTLE WOULD NOT CONTROL THE NR 2 ENGINE. MAINTENANCE FOUND PIN CONNECTING COPILOT THROTTLE GRIP TO SHAFT IN C OLLECTIVE STICK TO HAD BACKED OUT. REINSTALLED PIN. 1 G 7 2 4U H4SW 2001111600137 20011116 00137 2001 11 16 HEEA077003 4 20011031 G 3453 066402600 COMPUTER BELL 206 206L3 1182108 SW COCKPIT FAILED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 8592X 51508 WILL NOT POWER UP. PENDING VENDOR REPAIR. 1 G 7 1 3U H2SW 2001111600139 20011116 00139 SW 2001 11 16 HEEA077004 1 20011031 G 3246 206324007 SKID BELL 206 206L3 1182108 SW MLG CRACKED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 31801 51074 BOTTOM OF SKID TUBE HAS A 20 INCH CRACK EXTENDING FROM BELOW WHEEL LUG AFT. THERE ARE TWO ADDITIONAL CRACKS IN THE SAME AREA. PENDING VENDOR REPAIR. 1 G 7 1 3U H2SW 2001111600140 20011116 00140 SW 2001 11 16 HEEA077005 1 20011031 G 2810 222366652003 FITTING BELL 206 206L3 1182108 SW FUEL CELL CORRODED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 81SP 51029 THREADS ON FITTING CORRODED. REPLACED WITH SERVICEABLE PART. 1 G 7 1 3U H2SW 2001111600162 20011116 00162 2001 11 16 HEEA077006 4 20011031 G 2561 5018362071028 HARNESS BELL 412 412 1182202 SW SAFETY EQUIP WORN E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 2149S 36002 WORN. REPLACED WITH SERVICEABLE PART. 1 G 7 2 4U H4SW 2001111600163 20011116 00163 SW 2001 11 16 HEEA077007 1 20011031 G 2823 206063640109 VALVE BELL 407 407 1182206 SW FUEL SHUT OFF FAILED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 405PH 53207 FUEL SHUT OFF VALVE MAKING GRINDING NOISE. REPLACED WITH SERVICEABLE VALVE. 1 G 7 1 3U O H2SW 2001111900001 20011119 00001 SW 2001 11 19 HEEA077008 1 20011031 G 2820 206063640109 VALVE BELL 407 407 1182206 SW FUEL SYSTEM STUCK E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 8595X 53267 INOPERATIVE - STUCK IN THE MID TRAVEL POSITION. TO BE SENT TO BELL HELICOPTER TEXTRON FOR CREDIT AGAINST REPLACEMENT PAR T PURCHASED. 1 G 7 1 3U O H2SW 2001111900002 20011119 00002 GL 2001 11 19 HEEA077009 2 20011031 G 7532 23005366 BLEED VALVE BELL 407 407 1182206 SW ALLSN 250C 250C30 03013 GL ENGINE FAILED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 496PH 53398 HIGH MGT. REPLACED WITH SERVICEABLE BLEED VALVE. 1 G 7 1 3U 3 U O H2SW E1GL 2001111900004 20011119 00004 SW 2001 11 19 HEEA077010 1 20011031 G 7100 23069706 TUBE BELL 407 407 1182206 SW ENGINE WRONG PART E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 493PH 53393 INCORRECT LINE. REPLACED WITH SERVICEABLE TUBE. 1 G 7 1 3U O H2SW 2001111900005 20011119 00005 SW 2001 11 19 HEEA077011 1 20011031 G 6710 406310405101 UNIVERSAL BELL 407 407 1182206 SW MAIN ROOR WORN E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 406PH 53198 RED BLADE PITCH ROD UNIVERSAL BEARING IS WORN. 1 G 7 1 3U O H2SW 2001111900006 20011119 00006 SW 2001 11 19 HEEA077012 1 20011031 G 6710 406310405101 UNIVERSAL BELL 407 407 1182206 SW MAIN ROTOR WORN E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 492PH 53390 WORN BEARING. 1 G 7 1 3U O H2SW 2001111900007 20011119 00007 SW 2001 11 19 HEEA077013 1 20011031 G 6710 406310411101 BOOT BELL 407 407 1182206 SW MAIN ROTOR TORN E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 493PH 53393 BOOT TORN. 1 G 7 1 3U O H2SW 2001111900008 20011119 00008 SW 2001 11 19 HEEA077014 1 20011031 G 6720 406312103101 LINK BELL 407 407 1182206 SW TAIL ROTOR WORN E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 495PH 53397 T/R P/C LINK WORN BEARING. 1 G 7 1 3U O H2SW 2001111900009 20011119 00009 SW 2001 11 19 HEEA077015 1 20011031 G 6720 406312103101 LINK BELL 407 407 1182206 SW TAIL ROTOR WORN E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 495PH 53397 T/R P/C LINK WORN BEARING. 1 G 7 1 3U O H2SW 2001111900010 20011119 00010 SW 2001 11 19 HEEA077016 1 20011031 G 6420 407012101111 HUB BELL 407 407 1182206 SW TAIL ROTOR WORN E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 407PH 53003 WORN FEATHERING BEARINGS. 1 G 7 1 3U O H2SW 2001111900012 20011119 00012 SW 2001 11 19 HEEA077019 1 20011031 G 2840 407375016103 SIGNAL COND UNIT BELL 407 407 1182206 SW FUEL INDICATION MALFUNCTIONED E HEEA O OTHER N FALSE WARNING NR NOT REPORTED 1 SW 03 495PH 53397 LOW LEVEL LIGHT ON WITH PLENTY OF FUEL ON BOARD. 1 G 7 1 3U O H2SW 2001111900013 20011119 00013 SW 2001 11 19 HEEA077020 1 20011031 G 6240 407375008101 INDICATOR BELL 407 407 1182206 SW DUAL TACH INOPERATIVE E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 406PH 53198 DUAL TACH INOPERATIVE. 1 G 7 1 3U O H2SW 2001111900038 20011119 00038 SW 2001 11 19 HEEA077022 1 20011031 G 3340 4596 LAMP BELL 407 407 1182206 SW EXTERIOR BURNED OUT E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 8595X 53267 BURNED OUT. SCRAPPED LOCALLY AND REPLACED WITH SERVICEABLE PART. 1 G 7 1 3U O H2SW 2001111900040 20011119 00040 GL 2001 11 19 HEEA077023 2 20011031 G 7510 6899080B VALVE BELL 407 407 1182206 SW ALLSN 250C 250C47B GL ANTI ICE SYSTEM STUCK E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 495PH 53397 ANTI ICE VALVE STICKS IN ON POSITION INTERMITTENTLY. REPLACED WITH SERVICEABLE PART. 1 G 7 1 3U 3 U O H2SW E1GL 2001111900041 20011119 00041 SW 2001 11 19 HEEA077024 1 20011031 G 3210 70079H000Y150 HOSE BELL 407 407 1182206 SW MLG KINKED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 493PH 53393 HOSE ASSY KINKED. 1 G 7 1 3U O H2SW 2001111900042 20011119 00042 SW 2001 11 19 HEEA077025 1 20011031 G 6321 D01631 PAD BELL 407 407 1182206 SW M/R BRAKE WORN E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 724PH 53327 WORN PAD. 1 G 7 1 3U O H2SW 2001111900043 20011119 00043 SW 2001 11 19 HEEA077026 1 20011031 G 5320 D01661 BOLT BELL 407 407 1182206 SW FUSELAGE DAMAGED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 724PH 53327 GROOVED. 1 G 7 1 3U O H2SW 2001111900045 20011119 00045 2001 11 19 HEEA077027 4 20011031 G 3120 LIGHT BELL 407 407 1182206 SW COCKPIT CLOCK INOPERATIVE E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 8595X 3053 53267 INTERNAL LIGHT QUIT WORKING. 1 G 7 1 3U O H2SW 2001111900047 20011119 00047 SW 2001 11 19 HEEA077028 1 20011031 G 2800 P49389 RELEASE SYSTEM BELL 407 407 1182206 SW VALVE FAILED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 405PH 53207 FAILED INSPECTION. 1 G 7 1 3U O H2SW 2001111900053 20011119 00053 SW 2001 11 19 HEEA077032 1 20011101 G 6320 407340339101 BEARING BELL 407 407 1182206 SW WORN E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 491PH 53386 BEARING WORN. 1 G 7 1 3U O H2SW 2001111900055 20011119 00055 NE 2001 11 19 HEEA077035 2 20011101 G 7200 ENGINE BELL 412 412 1182202 SW PWA PT6T PT6T3B 52045 NE NR 2 FAILED E HEEA O OTHER R X J PARTIAL RPM/PWR LOSS ENGINE FLAMEOUT WARNING INDICATION CR CRUISE 1 SW 03 22347 36005 SHORTLY AFTER DEPARTURE, IN CRUISE, PILOT HEARD SQUEAL, BANG AND LOW RPM AUDIO. NOTED NR 2 ENGINE FAILED. SECURED ENGIN E AND COMPLETED FLIGHT WITH RUN ON LANDING. 1 G 7 2 4U 4 U H4SW E22EA 2001111900056 20011119 00056 SW 2001 11 19 HEEA077036 1 20011102 G 5302 214040617105 HANGER ASSY BELL 214 214ST 1182106 SW MISMANUFACTURED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 825H 28137 WILL NOT FIT IN SUPPORT ON AIRCRAFT. HOLES MILLED IN WRONG AREA. 2 G 7 2 4U H10SW 2001111900058 20011119 00058 SW 2001 11 19 HEEA077037 1 20011102 G 8011 214060056103 STARTER BELL 214 214ST 1182106 SW ENGINE MALFUNCTIONED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 DISENGAGES DURING STARTING WITH GOOD BATTERIES. 2 G 7 2 4U H10SW 2001111900060 20011119 00060 SW 2001 11 19 HEEA077038 1 20011102 G 7120 206064107103 MOUNT BELL 206 206L3 1182108 SW ENGINE WORN E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 623Q 292 ENGINE MOUNT LEG WORN BEARING BEYOND LIMITS. SENT TO BELL HELICOPTER TEXTRON FOR WARRANTY CREDIT ON BEHALF OF CUSTOMER U .S. WEST. REFERENCE: INVOICE AND DMR NO. 687181. 1 G 7 1 3U H2SW 2001111900077 20011119 00077 2001 11 19 HEEA077039 4 20011030 G 2350 066105571 AUDIO PANEL BOLKMS 105 BO105S 5626006 EU COCKPIT MALFUNCTIONED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 81982 S818 COIL LOOSE MOUNT AND NOT CONNECTED TO BOARD. PENDING VENDOR REPAIR. 1 G 7 2 3U H3EU 2001111900078 20011119 00078 2001 11 19 HEEA077040 4 20011030 G 3454 071121612 CONTROL UNIT BOLKMS 105 BO105S 5626006 EU COCKPIT MALFUNCTIONED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 86CH S557 LED READ OUT ARE UNREADABLE ON DISPLAY. REPLACED WITH SERVICEABLE PART. 1 G 7 2 3U H3EU 2001111900079 20011119 00079 EU 2001 11 19 HEEA077041 1 20011031 G 6321 350A32501000 LINER 350A32050002 SNIAS 350 AS350B 8680801 EU M/R BRAKE WORN E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 971AE M918 3230 WORN LINING. 1 G 7 1 3U H9EU 2001111900080 20011119 00080 EU 2001 11 19 HEEA077042 1 20011031 G 6720 350A33215001 BALL 350A33200406 SNIAS 350 AS350B 8680801 EU TAIL ROTOR WORN E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 972AE MA1154 3234 WORN BALL. PENDING VENDOR RETURN FOR CREDIT. 1 G 7 1 3U H9EU 2001111900081 20011119 00081 2001 11 19 HEEA077043 4 20011031 G 3420 5050010902 GYRO SNIAS 350 AS350B 8680801 EU COCKPIT MALFUNCTIONED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 856PH 3352 COMPASS CARD SPINS. REPLACED WITH SERVICEABLE PART. 1 G 7 1 3U H9EU 2001111900082 20011119 00082 EU 2001 11 19 HEEA077044 1 20011031 G 6730 SC5083 SERVO SNIAS 350 AS350B 8680801 EU SERVO SYSTEM LEAKING E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 971AE 958 3230 LEAKING PAST SHAFT SEAL. PENDING VENDOR RETURN. 1 G 7 1 3U H9EU 2001111900083 20011119 00083 EU 2001 11 19 HEEA077045 1 20011031 G 2432 RG390E BATTERY BOLKMS 117 BK117A1 5626010 EU MAIN WEAK E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 911RS S670 WEAK. REPLACED BATTERY. 1 G 7 2 3U H13EU 2001111900084 20011119 00084 EU 2001 11 19 HEEA077046 1 20011031 G 6730 1564T1005 ACTUATOR BOLKMS 117 BK117A1 5626010 EU NR 2 RPM MALFUNCTIONED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 911RS S670 AFTER STARTING BOTH ENGINES, NR 2 RPM COULD NOT BE INCREASED OR DECREASED WITH BEEP SWITCH. REPLACED ACTUATOR. 1 G 7 2 3U H13EU 2001120400169 20011204 00169 NE 2001 12 4 HEEA077200 1 20011106 G 6210 TIP CAP SKRSKY S76 S76A 8143006 NE M/R BLADE MISMANUFACTURED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 22342 16268 760096 UNABLE TO INSTALL TIP CAP, SCREW HOLES DO NOT LINE UP. 1 G 7 2 3U H1NE 2001120400170 20011204 00170 NE 2001 12 4 HEEA077201 1 20011106 G 3297 PHIS761178002 HARNESS SKRSKY S76 S76A 8143006 NE MLG OUT OF ADJ E HEEA O OTHER O OTHER TO TAKEOFF 1 SW 03 911UK 760275 ON TAKE OFF UPON RETRACTING LANDING GEAR GOT AN UNSAFE FLIGHT. MAINTENANCE ADJUSTED THE NOSE CENTERING PROXIMITY SENSOR. 1 G 7 2 3U H1NE 2001120400172 20011204 00172 SW 2001 12 4 HEEA077204 1 20011106 G 6322 PHIPBH40701 BLOWER BELL 407 407 1182206 SW OIL COOLER FAILED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 496PH 53398 FORWARD BEARING LOUD AND ROUGH. 1 G 7 1 3U O H2SW 2001120400174 20011204 00174 SW 2001 12 4 HEEA077205 1 20011106 G 7120 214031252141 SUPPORT BELL 214 214ST 1182106 SW ENG MOUNT MISMARKED E HEEA K NONE W INADEQUATE Q C IN INSP/MAINT 1 SW 03 MISIDENTIFIED. SUPPORT RECEIVED WAS A RT SUPPORT; YET WAS MARKED FOR THE LT SUPPORT P/N. 2 G 7 2 4U H10SW 2001120400177 20011204 00177 SW 2001 12 4 HEEA077206 1 20011106 G 7120 206064107103 LEG ASSY BELL 206 206L3 1182108 SW ENG MOUNT MISMARKED E HEEA K NONE W INADEQUATE Q C IN INSP/MAINT 1 SW 03 MISIDENTIFIED AND MISMANUFACTURED. 1 G 7 1 3U H2SW 2001120400178 20011204 00178 SW 2001 12 4 HEEA077207 1 20011106 G 5302 206020113173S CAP BELL 206 206L3 1182108 SW TAIL BOOM CRACKED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 DENTED AND CRACKED AT LEADING EDGE. 1 G 7 1 3U H2SW 2001120400179 20011204 00179 SW 2001 12 4 HEEA077208 1 20011107 G 8011 214060056103 STARTER BELL 214 214ST 1182106 SW ENGINE MALFUNCTIONED E HEEA K NONE L NO TEST IN INSP/MAINT 1 SW 03 WON'T STAY ENGAGED AT CROSS START. 2 G 7 2 4U H10SW 2001120400180 20011204 00180 SW 2001 12 4 HEEA077209 1 20011107 G 6300 214040104001 ROLLER BELL 214 214ST 1182106 SW MAIN ROTOR CORRODED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 PITTING ON ROLLERS. 2 G 7 2 4U H10SW 2001120400183 20011204 00183 SW 2001 12 4 HEEA077210 1 20011109 G 3300 214175140103 POWER SUPPLY BELL 214 214ST 1182106 SW LIGHTS INOPERATIVE E HEEA K NONE L NO TEST IN INSP/MAINT 1 SW 03 POWER SUPPLY INOPERATIVE. 2 G 7 2 4U H10SW 2001120400184 20011204 00184 SW 2001 12 4 HEEA077211 1 20011109 G 2435 206062200113 STARTER GEN BELL 407 407 1182206 SW ENGINE FAILED E HEEA K NONE L NO TEST IN INSP/MAINT 1 SW 03 402PH 1157 53159 FAILED 300 HOUR INSPECTION. 1 G 7 1 3U O H2SW 2001120400186 20011204 00186 SW 2001 12 4 HEEA077212 1 20011113 G 7120 206064106101 LEG ASSY BELL 206 206L3 1182108 SW ENG MOUNT MISMARKED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 PARTS MISIDENTIFIED. 1 G 7 1 3U H2SW 2001120400188 20011204 00188 SW 2001 12 4 HEEA077213 1 20011113 G 2435 BRUSHES BELL 407 407 1182206 SW STARTER GEN WORN E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 499PH 1790 95171 53400 WORN BRUSHES. 1 G 7 1 3U O H2SW 2001120400192 20011204 00192 SW 2001 12 4 HEEA077214 1 20011115 G 3300 214175140103 POWER SUPPLY BELL 214 214ST 1182106 SW LIGHTS DISCHARGED E HEEA K NONE L NO TEST IN INSP/MAINT 1 SW 03 POWER SUPPLY DEAD. 2 G 7 2 4U H10SW 2001120400194 20011204 00194 SW 2001 12 4 HEEA077215 1 20011115 G 6520 214040404101 SHAFT 214540001101 BELL 214 214ST 1182106 SW T/R GEARBOX CORRODED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 59806 1711 A26 28140 EXCESSIVE CORROSION AT TAIL ROTOR OUTPUT SHAFT DRIVE SPLINES. 2 G 7 2 4U H10SW 2001120400200 20011204 00200 SW 2001 12 4 HEEA077216 1 20011115 G 7120 206064106101 LEG ASSY BELL 206 206L3 1182108 SW ENG MOUNT MISMARKED E HEEA K NONE W INADEQUATE Q C IN INSP/MAINT 1 SW 03 MISIDENTIFIED. IT SHOULD BE 206-064-106-001. 1 G 7 1 3U H2SW 2001120400220 20011204 00220 SW 2001 12 4 HEEA077217 1 20011115 G 6300 206010003007 CONE SET BELL 206 206L3 1182108 SW MAIN ROTOR MISMARKED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 CONE SET MISIDENTIFIED. 1 G 7 1 3U H2SW 2001120400221 20011204 00221 SW 2001 12 4 HEEA077218 1 20011116 G 6300 212010103007 FITTING BELL 212 212 1181420 SW MAIN ROTOR GOUGED E HEEA K NONE W INADEQUATE Q C IN INSP/MAINT 1 SW 03 PART IS GOUGED ON TOP AND WAS NOT ACCEPTABLE PER OUR INSPECTORS. 1 G 7 1 4U H4SW 2001120400223 20011204 00223 SW 2001 12 4 HEEA077222 1 20011120 G 7712 407375003107 INDICATOR BELL 407 407 1182206 SW TORQUE INOPERATIVE E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 408PH 53228 WON'T INDICATE TORQUE. 1 G 7 1 3U O H2SW 2001120500001 20011205 00001 SW 2001 12 5 HEEA077223 1 20011120 G 6730 206076062105 SERVO BELL 407 407 1182206 SW ROTOR SERVO LEAKING E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 402PH 4730 53159 SERVO IS LEAKING. 1 G 7 1 3U O H2SW 2001120500002 20011205 00002 SW 2001 12 5 HEEA077228 1 20011120 G 6220 407010150105A FRAHM BELL 407 407 1182206 SW MAIN ROTOR BROKEN E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 499PH 53400 FRAHM HAS A BROKEN SPRING. 1 G 7 1 3U O H2SW 2001120500003 20011205 00003 SW 2001 12 5 HEEA077232 1 20011120 G 7712 407375003107 INDICATOR BELL 407 407 1182206 SW TORQUE MALFUNCTIONED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 407PH 53003 BACK LIGHT INOPERATIVE. 1 G 7 1 3U O H2SW 2001120500004 20011205 00004 SW 2001 12 5 HEEA077233 1 20011120 G 6510 407040302103 DRIVE SHAFT BELL 407 407 1182206 SW TAIL ROTOR WORN E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 8595X 53267 SPLINES WORN BEYOND LIMITS. 1 G 7 1 3U O H2SW 2001120500005 20011205 00005 SW 2001 12 5 HEEA077235 1 20011120 G 7714 407375008101 INDICATOR BELL 407 407 1182206 SW DUAL TACH INOPERATIVE E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 447PH 53114 NR NEEDLE INOPERATIVE. 1 G 7 1 3U O H2SW 2001120500006 20011205 00006 SW 2001 12 5 HEEA077238 1 20011120 G 7714 407375008101 INDICATOR BELL 407 407 1182206 SW DUAL TACH INOPERATIVE E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 417PH 53038 TURBINE NEEDLE PEGGED TO THE HIGH. 1 G 7 1 3U O H2SW 2001120500011 20011205 00011 SW 2001 12 5 HEEA077241 1 20011121 G 6310 214040841101 SEAL BELL 407 407 1182206 SW TRANSMISSION WORN E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 492PH 53390 SEAL IS WORN. 1 G 7 1 3U O H2SW 2001120500012 20011205 00012 SW 2001 12 5 HEEA077242 1 20011121 G 6310 214040814105 SLEEVE BELL 407 407 1182206 SW TRANSMISSION WORN E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 492PH 53390 SLEEVE WORN. 1 G 7 1 3U O H2SW 2001120500014 20011205 00014 SW 2001 12 5 HEEA077243 1 20011121 G 6710 406310405101 UNIVERSAL BELL 407 407 1182206 SW MAIN ROTOR WORN E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 724PH 1588 53327 BEARING WORN. 1 G 7 1 3U O H2SW 2001120500015 20011205 00015 SW 2001 12 5 HEEA077244 1 20011121 G 6710 406310405101 UNIVERSAL BELL 407 407 1182206 SW MAIN ROTOR WORN E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 501PH 908 53401 WORN. 1 G 7 1 3U O H2SW 2001120500016 20011205 00016 SW 2001 12 5 HEEA077245 1 20011121 G 6710 406310405101 UNIVERSAL BELL 407 407 1182206 SW MAIN ROTOR WORN E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 501PH 908 53401 UNIVERSAL WORN. 1 G 7 1 3U O H2SW 2001120500018 20011205 00018 SW 2001 12 5 HEEA077246 1 20011121 G 6710 406310405101 UNIVERSAL BELL 407 407 1182206 SW MAIN ROTOR WORN E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 501PH 908 53401 WORN. 1 G 7 1 3U O H2SW 2001120500020 20011205 00020 SW 2001 12 5 HEEA077247 1 20011121 G 2910 70061J180W164A HOSE BELL 407 407 1182206 SW HYD SYSTEM CHAFED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 402PH 53159 CHAFED. 1 G 7 1 3U O H2SW 2001120500021 20011205 00021 SW 2001 12 5 HEEA077248 1 20011121 G 2910 70061J285W210A HOSE BELL 407 407 1182206 SW HYD SYSTEM CHAFED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 402PH 53159 CHAFED. 1 G 7 1 3U O H2SW 2001120500033 20011205 00033 SW 2001 12 5 HEEA077249 1 20011121 G 2840 206362002103 ADAPTER BELL 407 407 1182206 SW FUEL INDICATOR WORN E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 499PH 53400 FUEL INDICATOR ADAPTER IS WORN. 1 G 7 1 3U O H2SW 2001120500035 20011205 00035 SW 2001 12 5 HEEA077250 1 20011121 G 6510 206061432121 HOUSING BELL 407 407 1182206 SW COOLER BLOWER CRACKED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 499PH 53400 COOLER BLOWER HOUSING IS CRACKED. 1 G 7 1 3U O H2SW 2001120500040 20011205 00040 SW 2001 12 5 HEEA077251 1 20011121 G 3340 A490ATSDF1428 POWER SUPPLY BELL 407 407 1182206 SW EXTERIOR LIGHTS FAILED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 141MA 53016 FAULTY GROUND WIRE AT PLUG CAUSED UNIT TO FAIL. 1 G 7 1 3U O H2SW 2001120500041 20011205 00041 SW 2001 12 5 HEEA077252 1 20011121 G 2420 SM20ACD300A21 RELAY BELL 407 407 1182206 SW INTERMITTENT E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 402PH 53159 INTERMITTENT. 1 G 7 1 3U O H2SW 2001120500043 20011205 00043 SW 2001 12 5 HEEA077253 1 20011121 G 2497 407375012103 WIRE BELL 407 407 1182206 SW FADEC DAMAGED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 510PH 53209 CAUSING FADEC DEGRADE LIGHT. 1 G 7 1 3U O H2SW 2001120500044 20011205 00044 SW 2001 12 5 HEEA077254 1 20011121 G 2420 SM20ACD300A21 RELAY BELL 407 407 1182206 SW COCKPIT FAILED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 510PH 53209 CAUSES IGNITION FAULT TO APPEAR SEVERAL TIMES. 1 G 7 1 3U O H2SW 2001120500046 20011205 00046 SW 2001 12 5 HEEA077255 1 20011121 G 2820 70079H000Y150 HOSE BELL 407 407 1182206 SW FUEL SYSTEM KINKED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 490PH 53378 HOSE ASSY KINKED. 1 G 7 1 3U O H2SW 2001120500048 20011205 00048 SW 2001 12 5 HEEA077256 1 20011121 G 6340 214040806003 PRESSURE SWITCH BELL 407 407 1182206 SW TRANSMISSION OIL FAILED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 723PH 53283 TRANSMISSION OIL PRESSURE LIGHT DOESN'T COME ON DURING SHUT DOWN. 1 G 7 1 3U O H2SW 2001120500049 20011205 00049 SW 2001 12 5 HEEA077257 1 20011121 G 7120 407060111101 MOUNT BELL 407 407 1182206 SW ENGINE INOPERATIVE E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 417PH 4197 53038 INOPERATIVE. 1 G 7 1 3U O H2SW 2001120500050 20011205 00050 SW 2001 12 5 HEEA077258 1 20011121 G 6320 407340339101 BEARING BELL 407 407 1182206 SW MAIN ROTOR OVERHEATED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 612PH 53199 BEARING OVERHEATED 1 G 7 1 3U O H2SW 2001120500052 20011205 00052 SW 2001 12 5 HEEA077259 1 20011121 G 6710 BEARING BELL 407 407 1182206 SW IDLER ASSY WORN E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 491PH CT1279 53386 WORN BEARING. 1 G 7 1 3U O H2SW 2001120500053 20011205 00053 SW 2001 12 5 HEEA077260 1 20011121 G 2844 407362013101 PRESSURE SWITCH BELL 407 407 1182206 SW FUEL PRESSURE STUCK E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 447PH 53114 STICKS IN CLOSED POSITION. 1 G 7 1 3U O H2SW 2001120500054 20011205 00054 SW 2001 12 5 HEEA077261 1 20011121 G 5210 206064819006S DOOR BELL 407 407 1182206 SW PAX/CREW CORRODED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 723PH 53283 CORRODED AROUND BOTH LATCHES. 1 G 7 1 3U O H2SW 2001120500055 20011205 00055 SW 2001 12 5 HEEA077262 1 20011121 G 2820 70079H100F210 HOSE BELL 407 407 1182206 SW FUEL SYSTEM CHAFED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 406PH 53198 INSULATION CHAFED THROUGH. 1 G 7 1 3U O H2SW 2001120500056 20011205 00056 SW 2001 12 5 HEEA077263 1 20011121 G 3210 407040624101 TUBE BELL 407 407 1182206 SW MLG CHAFED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 499PH 53400 TUBE ON MLG CHAFED. 1 G 7 1 3U O H2SW 2001120500057 20011205 00057 2001 12 5 HEEA077264 4 20011121 G 2340 PM212302 SWITCH BELL 407 407 1182206 SW COCKPIT BROKEN E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 406PH 53198 MIC SPRING TABS WORN. REPORTED STICKING ICS. 1 G 7 1 3U O H2SW 2001120500058 20011205 00058 SW 2001 12 5 HEEA077267 1 20011121 G 6340 214040806003 PRESSURE SWITCH BELL 407 407 1182206 SW TRANSMISSION OIL INTERMITTENT E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 491PH 53386 INTERMITTENTLY STICKING. LIGHT WILL NOT COME ON AFTER SHUTDOWN. 1 G 7 1 3U O H2SW 2001120500069 20011205 00069 SW 2001 12 5 HEEA077269 1 20011121 G 6321 PAD BELL 407 407 1182206 SW ROTOR BRAKE WORN E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 612PH 53199 WORN PADS, 1 G 7 1 3U O H2SW 2001120500070 20011205 00070 SW 2001 12 5 HEEA077270 1 20011121 G 3212 206050247131 COVER BELL 407 407 1182206 SW MLG FLOAT WORN E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 724PH 53327 COVER WORN. 1 G 7 1 3U O H2SW 2001120500071 20011205 00071 SW 2001 12 5 HEEA077271 1 20011121 G 6310 214040841101 SEAL BELL 407 407 1182206 SW TRANSMISSION LEAKING E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 722PH 53288 LEAKING. 1 G 7 1 3U O H2SW 2001120500072 20011205 00072 SW 2001 12 5 HEEA077272 1 20011121 G 6400 BEARING BELL 407 407 1182206 SW OIL COOLER SHAFT FAILED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 499PH 53400 OIL COOLER SHAFT BEARING FAILED. 1 G 7 1 3U O H2SW 2002011800081 20020118 00081 NE 2002 1 18 HEEA077387 2 20011203 G 7200 ENGINE SKRSKY S76 S76C 8143008 NE TMECA ARRIEL ARRIEL1S 60030 NE ENGINE BAY MALFUNCTIONED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 505PH 2030 760505 20529TEC ENGINE WOULD NOT START. 1 G 7 2 3U 3 U NC H1NE E19EU 2002011800082 20020118 00082 NE 2002 1 18 HEEA077388 1 20011204 G 6210 7615009100048A BLADE SKRSKY S76 S76A 8143006 NE MAIN ROTOR MISMANUFACTURED E HEEA K NONE W INADEQUATE Q C IN INSP/MAINT 1 SW 03 911MJ 12101 760231 UNABLE TO INSTALL TIP CAPS - TWO DIFFERENT TIP CAPS. TIP CAP BLOCK HOLES APPEAR TO BE DRILLED 1/8 INCH TOO FAR FORWARD WHEN AFT SCREWS INSERTED. 1 G 7 2 3U H1NE 2002011800083 20020118 00083 NE 2002 1 18 HEEA077389 1 20011204 G 6210 7615009100051A RIB SKRSKY S76 S76A 8143006 NE MAIN ROTOR BLADE DEBONDED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 5426U 11828 760167 MAIN ROTOR BLADE TIP RIB UNBONDED. 1 G 7 2 3U H1NE 2002011800084 20020118 00084 NE 2002 1 18 HEEA077390 1 20011204 G 6210 TAB SKRSKY S76 S76A 8143006 NE MAIN ROTOR BLADE SPLIT E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 4253S 7247 760035 MAIN ROTOR BLADE TRIM TAB IS SPLIT OPEN NEAR THE TIP OF THE BLADE. 1 G 7 2 3U H1NE 2002011800088 20020118 00088 NE 2002 1 18 HEEA077391 1 20011204 G 6210 7615009100053 BLADE SKRSKY S76 S76A 8143006 NE MAIN ROTOR DELAMINATED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 4253S 7056 760035 LAMINATE AT STA 44 ON THE LOWER SIDE IS SEPARATED. . 1 G 7 2 3U H1NE 2002011800090 20020118 00090 2002 1 18 HEEA077392 4 20011204 G 3420 501145301 GYRO SKRSKY S76 S76A 8143006 NE AFCS PRECESSES E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 5435V 760158 VERTICAL GYRO PRECESSES. 1 G 7 2 3U H1NE 2002011800091 20020118 00091 2002 1 18 HEEA077393 4 20011204 G 3420 125780 INDICATOR SKRSKY S76 S76A 8143006 NE ADI PRECESSES E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 5426U 760167 ADI PRECESSES HORIZONTALLY IN FLIGHT. 1 G 7 2 3U H1NE 2002011800092 20020118 00092 NE 2002 1 18 HEEA077394 2 20011211 G 7261 9560134100 MAGNETIC SEAL SNIAS 350 AS350B 8680801 EU TMECA ARRIEL ARRIEL1 60030 NE ENGINE LEAKING E HEEA K NONE K FLUID LOSS IN INSP/MAINT 1 SW 03 974AE 2653 ENGINE MAGNETIC SEAL IS LEAKING. 1 G 7 1 3U 3 U H9EU E19EU 2002011800093 20020118 00093 NE 2002 1 18 HEEA077395 2 20011211 G 7421 9550168760 IGNITER SNIAS 350 AS350B 8680801 EU TMECA ARRIEL ARRIEL1 60030 NE ENGINE WORN E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 971AE 3230 ENGINE IGNITER WORN. 1 G 7 1 3U 3 U H9EU E19EU 2002011800094 20020118 00094 NE 2002 1 18 HEEA077396 2 20011211 G 7421 9550168760 IGNITER SNIAS 350 AS350B 8680801 EU TMECA ARRIEL ARRIEL1 60030 NE ENGINE WORN E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 971AE 3230 ENGINE IGNITER WORN. 1 G 7 1 3U 3 U H9EU E19EU 2002011800095 20020118 00095 EU 2002 1 18 HEEA077397 1 20011211 G 7170 0174078010 DRAIN VALVE SNIAS 350 AS350B2 8680813 EU TMECA ARRIEL ARRIEL1 60030 NE ENGINE LEAKING E HEEA K NONE K FLUID LOSS IN INSP/MAINT 1 SW 03 4031L 3078 2907 ENGINE DRAIN VALVE LEAKING FUEL AT PLUG. 1 G 7 1 3U 3 U H9EU E19EU 2002011800096 20020118 00096 SW 2002 1 18 HEEA077401 1 20011126 G 2435 BRUSHES BELL 407 407 1182206 SW STARTER GEN WORN E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 407PH 2533 98221 53003 STARTER GENERATOR HAS WORN BRUSHES. 1 G 7 1 3U O H2SW 2002011800099 20020118 00099 2002 1 18 HEEA077402 4 20011127 G 2210 214074305105 AMPLIFIER BELL 214 214ST 1182106 SW AFCS MALFUNCTIONED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 TRIPS OFF WHEN CONTROL IS MOVED. 2 G 7 2 4U H10SW 2002011800105 20020118 00105 2002 1 18 HEEA077403 4 20011127 G 2210 214074301105 AMPLIFIER BELL 214 214ST 1182106 SW AFCS MALFUNCTIONED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 PITCH TRIPS AFTER 30 TO 45 MINUTES OF FLIGHT. RESETS BUT ONLY FOR SHORT PERIOD OF TIME. 2 G 7 2 4U H10SW 2002011800109 20020118 00109 SW 2002 1 18 HEEA077404 1 20011127 G 2730 214001970111 ACTUATOR BELL 214 214ST 1182106 SW ELEVATORS MALFUNCTIONED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 ACTUATOR TRIPS OFF BOTH ELEVATOR SYSTEMS. 2 G 7 2 4U H10SW 2002011800115 20020118 00115 SW 2002 1 18 HEEA077428 1 20011203 G 7120 BEARING BELL 206 206L3 1182108 SW ENGINE MOUNT WORN E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 BEARING WORN PREMATURELY. 1 G 7 1 3U H2SW 2002012200001 20020122 00001 SW 2002 1 22 HEEA077429 1 20011203 G 6300 206040320103 SHAFT BELL 206 206L3 1182108 SW MAIN ROTOR DAMAGED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 UNABLE TO BALANCE SHAFT. 1 G 7 1 3U H2SW 2002012200002 20020122 00002 SW 2002 1 22 HEEA077430 1 20011203 G 6320 206040146103 GEAR BELL 206 206L3 1182108 SW M/R GEARBOX MISMARKED E HEEA K NONE W INADEQUATE Q C IN INSP/MAINT 1 SW 03 GEAR SERIAL NUMBER A-FS9423 AND A-FS9409 ARE IMPROPERLY MARKED WITH PART NUMBER 204-040-146-103. 1 G 7 1 3U H2SW 2002012200003 20020122 00003 SW 2002 1 22 HEEA077431 1 20011203 G 3213 206323017 CROSSTUBE BELL 206 206L3 1182108 SW MLG CORRODED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 CROSSTUBE HAS CORROSION. 1 G 7 1 3U H2SW 2002012200004 20020122 00004 SW 2002 1 22 HEEA077432 1 20011203 G 3213 206323018 CROSSTUBE BELL 206 206L3 1182108 SW MLG CORRODED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 CROSSTUBE HAS CORROSION. 1 G 7 1 3U H2SW 2002012200005 20020122 00005 SW 2002 1 22 HEEA077433 1 20011203 G 6320 214001373101 IDLER GEAR BELL 214 214ST 1182106 SW NEW MISSING E HEEA K NONE W INADEQUATE Q C IN INSP/MAINT 1 SW 03 BEARING MISSING WHEN PACKAGED PART WAS OPENED. 2 G 7 2 4U H10SW 2002012200006 20020122 00006 SW 2002 1 22 HEEA077434 1 20011203 G 2913 222380009105 PUMP BELL 430 430 1182150 SW NR 1 HYD SYSTEM FAILED E HEEA A UNSCHED LANDING J WARNING INDICATION CL CLIMB 1 SW 03 430X 1638 49058 DURING CLIMB OUT AFTER TAKEOFF, THE NR 1 HYDRAULIC SYSTEM FAILED. MAINTENANCE FOUND DRIVE SHAFT DISENGAGED FROM THE NR 1 HYDRAULIC PUMP. REPLACED PUMP. 1 G 7 2 3U RT H9SW 2002012200007 20020122 00007 SW 2002 1 22 HEEA077435 1 20011203 G 2497 WIRE BELL 412 412 1182202 SW NR 1 GENERATOR BROKEN E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 33008 36004 NR 1 GENERATOR FAILED. MAINTENANCE FOUND WIRE BROKEN AT TERMINAL "A" ON NR 1 GENERATOR. 1 G 7 2 4U H4SW 2002012200008 20020122 00008 SW 2002 1 22 HEEA077436 1 20011206 G 7120 206064106101 LEG ASSY BELL 206 206L3 1182108 SW ENGINE MOUNT MISMARKED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 PART NUMBER INCORRECT, PART MADE OF STEEL (MISIDENTIFIED) SHOULD BE 206064106001. 1 G 7 1 3U H2SW 2002012200009 20020122 00009 SW 2002 1 22 HEEA077437 1 20011206 G 5260 212075418105 ACTUATOR BELL 412 412 1182202 SW STEP INOPERATIVE E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 STEP ACTUATOR WOULD NOT MOVE AT ALL. 1 G 7 2 4U H4SW 2002012200010 20020122 00010 SW 2002 1 22 HEEA077438 1 20011206 G 8011 214060056103 STARTER BELL 214 214ST 1182106 SW ENGINE INOPERATIVE E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 5748M 378 28102 STARTER WILL NOT STAY ENGAGED. 2 G 7 2 4U H10SW 2002012200011 20020122 00011 SW 2002 1 22 HEEA077439 1 20011206 G 8011 214060056705 STARTER BELL 214 214ST 1182106 SW ENGINE MALFUNCTIONED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 59806 241 28140 STARTER STAYS STUCK IN THE ON POSITION. 2 G 7 2 4U H10SW 2002012200012 20020122 00012 SW 2002 1 22 HEEA077440 1 20011206 G 6220 222310503101 BEARING BELL 230 230 1182149 SW MAIN ROTOR HEAD DELAMINATED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 BEARING HAS DELAMINATED ELASTOMER. 1 G 7 2 3U NC H9SW 2002012200013 20020122 00013 SW 2002 1 22 HEEA077441 1 20011206 G 2435 206062200113 STARTER GEN BELL 407 407 1182206 SW ENGINE INOPERATIVE E HEEA K NONE L NO TEST IN INSP/MAINT 1 SW 03 457PH 2446 53147 STARTER GENERATOR WILL NOT MOTOR OVER. 1 G 7 1 3U O H2SW 2002012200014 20020122 00014 SW 2002 1 22 HEEA077442 1 20011206 G 2435 206062200113 STARTER GEN BELL 407 407 1182206 SW ENGINE ARCED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 741PH 2258 53457 STARTER GENERATOR IS ARCING. 1 G 7 1 3U O H2SW 2002012200015 20020122 00015 SW 2002 1 22 HEEA077445 1 20011210 G 2910 HYDRAULIC SYSTEM BELL 430 430 1182150 SW NR 1 MALFUNCTIONED E HEEA O OTHER J WARNING INDICATION NR NOT REPORTED 1 SW 03 430X 49058 ONE HOUR AND 10 MINUTES INTO THE FLIGHT THE SCAS KICKED OFF. THE NR 1 HYDRAULIC SYSTEM PRESSURE FLUCTUATED BETWEEN 0 AN D 130 PSI WITH RESITANCE IN THE TAIL ROTOR PEDALS. DURING ENGINE COOL DOWN, TURNED NR 1 HYDRAULIC SYSTEM ON AND PRESSUR E WAS STEADY AT 1430 PSI WITH NO RESISTANCE IN THE TAIL ROTOR PEDALS. CLEANED ALL CONNECTORS IN HYDRAULIC SYSTEM AT BYP ASS SOLENOID, PRESSURE SWITCHES, PRESSURE TRANSDUCERS AND SERVICED RESERVOIR. 1 G 7 2 3U RT H9SW 2002012200016 20020122 00016 SW 2002 1 22 HEEA077446 1 20011214 G 8011 214060056103 STARTER BELL 214 214ST 1182106 SW ENGINE SLOW E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 3897N 270 28106 STARTER IS SLOW TO START. 2 G 7 2 4U H10SW 2002012200017 20020122 00017 SW 2002 1 22 HEEA077447 1 20011214 G 8011 214060056103 STARTER BELL 214 214ST 1182106 SW ENGINE WEAK E HEEA K NONE L NO TEST IN INSP/MAINT 1 SW 03 3897N 36 28106 STARTER IS WEAK. 2 G 7 2 4U H10SW 2002012200018 20020122 00018 SW 2002 1 22 HEEA077448 1 20011214 G 8011 214060056103 STARTER BELL 214 214ST 1182106 SW ENGINE MALFUNCTIONED E HEEA K NONE L NO TEST IN INSP/MAINT 1 SW 03 8045T 431 28101 STARTER WON'T STAY ENGAGED. 2 G 7 2 4U H10SW 2002012200019 20020122 00019 EU 2002 1 22 HEEA077449 1 20011203 G 7931 ZRA25500 TRANSMITTER SNIAS 350 AS350B 8680801 EU ENG OIL PRESS MALFUNCTIONED E HEEA K NONE L NO TEST IN INSP/MAINT 1 SW 03 973AE 3229 ENGINE OIL PRESSURE HADN`T ANY INDICATION ON START FOR 3 SECONDS. 1 G 7 1 3U H9EU 2002012200020 20020122 00020 EU 2002 1 22 HEEA077450 1 20011203 G 6310 350A35110500 GIMBAL JOINT SNIAS 350 AS350B 8680801 EU MAIN ROTOR BROKEN E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 855PH 3351 GIMBAL JOINT IS BROKEN. 1 G 7 1 3U H9EU 2002012200021 20020122 00021 EU 2002 1 22 HEEA077451 1 20011203 G 7721 56375600010 INDICATOR SNIAS 350 AS350B 8680801 EU COCKPIT DAMAGED E HEEA K NONE L NO TEST IN INSP/MAINT 1 SW 03 856PH 3352 T4 INDICATOR WAS RECEIVED WITH RATTLE NOISE INSIDE. DID NOT INSTALL ON AIRCRAFT. WAS ISSUED AND RETIRED UNSERVICEABLE. SOUNDS LIKE LOOSE SCREW INSIDE. 1 G 7 1 3U H9EU 2002012200022 20020122 00022 2002 1 22 HEEA077452 4 20011203 G 3120 B1894522282A CLOCK SNIAS 350 AS350B 8680801 EU COCKPIT INOPERATIVE E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 974AE 2653 CLOCK WILL NOT WIND UP. 1 G 7 1 3U H9EU 2002012200023 20020122 00023 EU 2002 1 22 HEEA077453 1 20011203 G 6320 350A32310121 FRICTION RING SNIAS 350 AS350B 8680801 EU M/R GEARBOX LEAKING E HEEA K NONE K FLUID LOSS IN INSP/MAINT 1 SW 03 855PH 3351 FRICTION RING LEAKS. 1 G 7 1 3U H9EU 2002012200024 20020122 00024 EU 2002 1 22 HEEA077454 1 20011203 G 6710 SC5083 SERVO SNIAS 350 AS350B 8680801 EU MAIN ROTOR LEAKING E HEEA K NONE K FLUID LOSS IN INSP/MAINT 1 SW 03 855PH 3351 SERVO LEAKS. 1 G 7 1 3U H9EU 2002012200025 20020122 00025 EU 2002 1 22 HEEA077455 1 20011203 G 7721 56375600010 INDICATOR SNIAS 350 AS350B 8680801 EU COCKPIT STUCK E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 856PH 3352 T4 INDICATOR NEEDLE STICKS INTERMITTENTLY AT 700 DURING START. 1 G 7 1 3U H9EU 2002012200026 20020122 00026 EU 2002 1 22 HEEA077456 1 20011203 G 6710 SC5083 SERVO SNIAS 350 AS350B2 8680813 EU MAIN ROTOR LEAKING E HEEA K NONE K FLUID LOSS IN INSP/MAINT 1 SW 03 40466 3004 SERVO LEAKING. 1 G 7 1 3U H9EU 2002012200027 20020122 00027 2002 1 22 HEEA077458 4 20011203 G 3160 350A67622202 INDICATOR SNIAS 350 AS350B 8680801 EU PITOT HEAT MALFUNCTIONED E HEEA K NONE N FALSE WARNING IN INSP/MAINT 1 SW 03 856PH 3352 PITOT HEAT LIGHT WOULD NOT GO OUT. 1 G 7 1 3U H9EU 2002012200028 20020122 00028 EU 2002 1 22 HEEA077459 1 20011203 G 6230 PAINT SNIAS 350 AS350B 8680801 EU M/R SHAFT MISSING E HEEA K NONE W INADEQUATE Q C IN INSP/MAINT 1 SW 03 974AE 2653 THE MAIN ROTOR SHAFT`S SPECIAL PAINT COAT MISSING. 1 G 7 1 3U H9EU 2002012200029 20020122 00029 EU 2002 1 22 HEEA077460 1 20011203 G 6220 350A37112601 LINK SNIAS 350 AS350B 8680801 EU MAIN ROTOR HEAD CORRODED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 974AE 2653 SCISSOR LINKS HAS CORROSION. 1 G 7 1 3U H9EU 2002012200030 20020122 00030 EU 2002 1 22 HEEA077461 1 20011203 G 6230 350A37100206 STAR SNIAS 350 AS350B 8680801 EU SWASHPLATE CORRODED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 974AE 2653 NON ROTATING STAR HAS CORROSION. 1 G 7 1 3U H9EU 2002012200031 20020122 00031 2002 1 22 HEEA077462 4 20011206 G 3416 150201182 ALTIMETER SNIAS 350 AS350B2 8680813 EU NEW DAMAGED E HEEA O OTHER W INADEQUATE Q C NR NOT REPORTED 1 SW 03 PART WAS RECEIVED AT PHI CLAIMING TO BE SERVICEABLE, MECHANIC CLAIMS GUAGE OFF. 1 G 7 1 3U H9EU 2002012200032 20020122 00032 2002 1 22 HEEA077463 4 20011206 G 3416 150201182 ALTIMETER SNIAS 350 AS350B 8680801 EU COCKPIT STUCK E HEEA K NONE L NO TEST IN INSP/MAINT 1 SW 03 972AE 3234 ALTIMETER STICKS WHEN GOING UP AS MUCH AS 300 FEET. 1 G 7 1 3U H9EU 2002012200033 20020122 00033 EU 2002 1 22 HEEA077464 1 20011211 G 6520 350A33214501 ROD END BEARING SNIAS 350 AS350B 8680801 EU PITCH CONTROL WORN E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 855PH 3351 PITCH CONTROL ROD SPHERICAL BEARING WORN. 1 G 7 1 3U H9EU 2002012200034 20020122 00034 GL 2002 1 22 HEEA077550 2 20011217 G 7260 23007248 GEARSHAFT 23035179 SKRSKY S76 S76A 8143006 NE ALLSN 250C 250C30S 03013 GL GEARBOX SPALLED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 1545X 339 CAG95129 760050 CAE890508S GEARSHAFT IN GEARBOX HAS SPALLING ON GEARTEETH. 1 G 7 2 3U 3 U H1NE E1GL 2002012200035 20020122 00035 GL 2002 1 22 HEEA077551 2 20011217 G 7260 23007151 BEARING 23035179 SKRSKY S76 S76A 8143006 NE ALLSN 250C 250C30S 03013 GL GEARBOX SPALLED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 1545X 339 CAG95129 760050 CAE890508S GEAR HAS SPALLING ON BALL BEARING. 1 G 7 2 3U 3 U H1NE E1GL 2002012200036 20020122 00036 NE 2002 1 22 HEEA077552 2 20011220 G 7320 0164248690 FUEL CONTROL SNIAS 350 AS350B2 8680813 EU TMECA ARRIEL ARRIEL1D NE ENGINE MALFUNCTIONED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 4034Q 1806 2918 ENGINE SLOW START DURING COLD WEATHER. 1 G 7 1 3U 3 U H9EU E19EU 2002012200042 20020122 00042 SW 2002 1 22 HEEA077559 1 20011217 G 3110 407375015103 WARN PANEL BELL 407 407 1182206 SW COCKPIT MALFUNCTIONED E HEEA O OTHER N FALSE WARNING NR NOT REPORTED 1 SW 03 4999 53323 HYD. SYSTEM LIGHT FLASHING IN FLIGHT. 1 G 7 1 3U O H2SW 2002012200043 20020122 00043 SW 2002 1 22 HEEA077560 1 20011217 G 6240 412075010111 INDICATOR BELL 412 412EP 1182205 SW TRIPLE TACH FLUCTUATES E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 6106C 36257 TRIPLE TACH NEEDLES FLUCTUATE. 1 G 7 2 4U H4SW 2002012200044 20020122 00044 SW 2002 1 22 HEEA077561 1 20011217 G 6240 412075010111 INDICATOR BELL 412 412EP 1182205 SW TRIPLE TACH FLUCTUATES E HEEA K NONE L NO TEST IN INSP/MAINT 1 SW 03 6106C 36257 TRIPLE TACH NEEDLES FLUCTUATE. 1 G 7 2 4U H4SW 2002012200045 20020122 00045 SW 2002 1 22 HEEA077562 1 20011217 G 2821 222366621103 FUEL FILTER BELL 407 407 1182206 SW FUEL SYSTEM DEFECTIVE E HEEA O OTHER N FALSE WARNING NR NOT REPORTED 1 SW 03 493PH 53393 FUEL FILTER LIGHT ILLUMINATED. 1 G 7 1 3U O H2SW 2002012200056 20020122 00056 SW 2002 1 22 HEEA077563 1 20011217 G 7700 407375016103 SIGNAL COND UNIT BELL 407 407 1182206 SW ENGINE INACCURATE E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 405PH 53207 SIGNAL CONDITIONING UNIT LOW LEVEL ON FULL FUEL. 1 G 7 1 3U O H2SW 2002012200071 20020122 00071 SW 2002 1 22 HEEA077568 1 20011217 G 6220 SPRING BELL 407 407 1182206 SW FRAHM ASSY BROKEN E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 742PH 53461 FRAHM ASSEMBLY HAS A BROKEN SPRING. 1 G 7 1 3U O H2SW 2002012200072 20020122 00072 SW 2002 1 22 HEEA077569 1 20011217 G 6320 407040006107 GEARBOX BELL 407 407 1182206 SW MAIN ROTOR MAKING METAL E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 495PH 3052 53397 MAIN ROTOR GEARBOX MAKING METAL. 1 G 7 1 3U O H2SW 2002012200073 20020122 00073 SW 2002 1 22 HEEA077570 1 20011217 G 6310 406040500131 FREEWHEEL UNIT BELL 407 407 1182206 SW MAIN ROTOR LEAKING E HEEA K NONE K FLUID LOSS IN INSP/MAINT 1 SW 03 741PH 1173 53457 FREEWHEEL UNIT IS LEAKING. 1 G 7 1 3U O H2SW 2002012200075 20020122 00075 SW 2002 1 22 HEEA077572 1 20011217 G 6310 406040500127 FREEWHEEL UNIT BELL 407 407 1182206 SW MAIN ROTOR MAKING METAL E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 495PH 1405 53397 FREEWHEEL UNIT IS MAKING METAL. 1 G 7 1 3U O H2SW 2002012200077 20020122 00077 SW 2002 1 22 HEEA077575 1 20011217 G 6510 407040302107 DRIVE SHAFT BELL 407 407 1182206 SW TAIL ROTOR PEELING E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 501PH 967 53401 PAINT PEELING OFF TAIL ROTOR DRIVE SHAFT. 1 G 7 1 3U O H2SW 2002012200078 20020122 00078 SW 2002 1 22 HEEA077576 1 20011217 G 7714 407375002103 INDICATOR BELL 407 407 1182206 SW COCKPIT MALFUNCTIONED E HEEA K NONE N FALSE WARNING IN INSP/MAINT 1 SW 03 491PH 53386 NG INDICATOR SHOWS EXCEEDANCE, CANNOT CLEAR. 1 G 7 1 3U O H2SW 2002012200080 20020122 00080 SW 2002 1 22 HEEA077577 1 20011217 G 6220 SPRING BELL 407 407 1182206 SW FRAHM ASSY BROKEN E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 493PH A630 53393 FRAHM ASSY HAS BROKEN SPRING. 1 G 7 1 3U O H2SW 2002012200081 20020122 00081 SW 2002 1 22 HEEA077578 1 20011217 G 7712 407375003107 INDICATOR BELL 407 407 1182206 SW TORQUE MALFUNCTIONED E HEEA K NONE L NO TEST IN INSP/MAINT 1 SW 03 406PH 53198 TORQUE INDICATOR HAS DIM LIGHTING. 1 G 7 1 3U O H2SW 2002012200084 20020122 00084 2002 1 22 HEEA077580 4 20011217 G 2210 214074305105 AMPLIFIER BELL 214 214ST 1182106 SW AUTO FLIGHT MALFUNCTIONED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 CAUSES ELEVATOR TO TRIP OFF LINE. 2 G 7 2 4U H10SW 2002012200087 20020122 00087 SW 2002 1 22 HEEA077583 1 20011218 G 2822 407362013101 PRESSURE SWITCH BELL 407 407 1182206 SW BOOST PUMP FAILED E HEEA O OTHER N FALSE WARNING NR NOT REPORTED 1 SW 03 402PH 53159 BOOST PUMP LIGHT WILL NOT COME ON WHEN PUMP OFF. 1 G 7 1 3U O H2SW 2002012200091 20020122 00091 SW 2002 1 22 HEEA077584 1 20011218 G 6322 407062021101 DUCT BELL 407 407 1182206 SW OIL COOLER CRACKED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 496PH 53398 OIL COOLER DUCT CRACKED. 1 G 7 1 3U O H2SW 2002012200124 20020122 00124 SW 2002 1 22 HEEA077585 1 20011218 G 6300 407340339103 BEARING PHIPBH40701 BELL 407 407 1182206 SW COOLER BLOWER WORN E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 510PH PHI0025 53209 WORN BEARING. 1 G 7 1 3U O H2SW 2002012200127 20020122 00127 SW 2002 1 22 HEEA077586 1 20011218 G 3212 212073905001 GAUGE BELL 407 407 1182206 SW FLOAT PRESSURE CONTAMINATED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 4999 53323 PRESSURE GAUGE IS FULL OF MOISTURE. 1 G 7 1 3U O H2SW 2002012200128 20020122 00128 SW 2002 1 22 HEEA077587 1 20011218 G 3212 206050247137 COVER BELL 407 407 1182206 SW FLOAT WORN E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 447PH 53114 FLOAT COVER IS BADLY WORN. 1 G 7 1 3U O H2SW 2002012200130 20020122 00130 SW 2002 1 22 HEEA077589 1 20011218 G 3212 8226003 FUSEABLE PLUG BELL 407 407 1182206 SW FLOAT LEAKING E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 407PH 53003 FLOAT BOTTLE FUSABLE PLUG IS LEAKING. 1 G 7 1 3U O H2SW 2002012200131 20020122 00131 SW 2002 1 22 HEEA077590 1 20011218 G 6321 206076047101 CYLINDER BELL 407 407 1182206 SW ROTOR BRAKE LEAKING E HEEA O OTHER K FLUID LOSS NR NOT REPORTED 1 SW 03 490PH 53378 CYLINDER LEAKING FROM PISTON SEAL. 1 G 7 1 3U O H2SW 2002012200132 20020122 00132 SW 2002 1 22 HEEA077592 1 20011218 G 6320 206061432121 HOUSING BELL 407 407 1182206 SW COOLER BLOWER DAMAGED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 490PH 53378 RIVETS WORKING. 1 G 7 1 3U O H2SW 2002012200133 20020122 00133 SW 2002 1 22 HEEA077593 1 20011218 G 6340 214040806003 PRESSURE SWITCH BELL 407 407 1182206 SW XMSN OIL FAILED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 491PH 53386 TRANSMISSION OIL PRESSURE CAUTION LIGHT CAME ON. 1 G 7 1 3U O H2SW 2002012200134 20020122 00134 SW 2002 1 22 HEEA077594 1 20011218 G 6300 407340339101 BEARING BELL 407 407 1182206 SW MAIN ROTOR FAILED E HEEA K NONE L NO TEST IN INSP/MAINT 1 SW 03 447PH 53114 FAILED OPERATIONAL TEST (RAN HOT ABOVE 270 F.) 1 G 7 1 3U O H2SW 2002012200135 20020122 00135 SW 2002 1 22 HEEA077595 1 20011218 G 6420 406312103101 LINK BELL 407 407 1182206 SW TAIL ROTOR WORN E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 721PH 53278 TAIL ROTOR LINK WORN. 1 G 7 1 3U O H2SW 2002012200136 20020122 00136 SW 2002 1 22 HEEA077596 1 20011218 G 6330 407310203101 MOUNT BELL 407 407 1182206 SW TRANSMISSION DAMAGED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 496PH 53398 TRANSMISSION MOUNT RUBBER BAD. 1 G 7 1 3U O H2SW 2002012200137 20020122 00137 SW 2002 1 22 HEEA077598 1 20011218 G 6300 406310405101 UNIVERSAL BELL 407 407 1182206 SW M/R DRIVE WORN E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 499PH 1198 53400 MAIN ROTOR DRIVE UNIVERSAL WORN. 1 G 7 1 3U O H2SW 2002012200139 20020122 00139 SW 2002 1 22 HEEA077600 1 20011218 G 2822 407362013101 PRESSURE SWITCH BELL 407 407 1182206 SW ENGINE FAILED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 496PH 53398 PRESSURE SWITCH FAILED. 1 G 7 1 3U O H2SW 2002012200147 20020122 00147 SW 2002 1 22 HEEA077601 1 20011218 G 6720 406312103101 PITCH LINK BELL 407 407 1182206 SW TAIL ROTOR WORN E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 510PH 53209 PITCH LINK WORN. 1 G 7 1 3U O H2SW 2002012200148 20020122 00148 SW 2002 1 22 HEEA077602 1 20011218 G 6320 407310203101 MOUNT BELL 407 407 1182206 SW TRANSMISSION CRACKED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 494PH 53396 TRANSMISSION MOUNT CRACKED RUBBER. 1 G 7 1 3U O H2SW 2002012200149 20020122 00149 SW 2002 1 22 HEEA077603 1 20011218 G 7712 222375077119 TRANSMITTER BELL 407 407 1182206 SW TORQUE METER MALFUNCTIONED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 407PH 53003 TORQUE SPIKE TO 134.1 PERCENT FOR ONE SECOND. 1 G 7 1 3U O H2SW 2002012200150 20020122 00150 SW 2002 1 22 HEEA077604 1 20011218 G 6420 406312100101 BEARING 407012101111 BELL 407 407 1182206 SW T/R HUB WORN E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 496PH 53006 53398 WORN. SENT TO BELL HELICOPTER TEXTRON FOR CREDIT AGAINST REPLACEMENT PART PURCHASED. REFERENCE: DMR#73147302. LABOR C REDIT ACCOMPLISHED ON J0194971-WA (INVOICE AND DMR NO. 687199). 1 G 7 1 3U O H2SW 2002012200151 20020122 00151 SW 2002 1 22 HEEA077607 1 20011218 G 6710 406010425107 LEVER BELL 407 407 1182206 SW MAIN ROTOR WORN E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 498PH 2031 53399 LEVER ASSY HAS WORN BUSHINGS. 1 G 7 1 3U O H2SW 2002012300001 20020123 00001 SW 2002 1 23 HEEA077608 1 20011218 G 6420 406312100101 BEARING 407012101111 BELL 407 407 1182206 SW TAIL ROTOR HUB WORN E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 492PH 53246 53390 TAIL ROTOR HUB BEARING WORN. 1 G 7 1 3U O H2SW 2002012300092 20020123 00092 SW 2002 1 23 HEEA077609 1 20011218 G 6510 BEARING BELL 407 407 1182206 SW BELLCRANK WORN E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 407PH 53003 TAIL ROTOR BELLCRANK BEARING WORN. 1 G 7 1 3U O H2SW 2002012300002 20020123 00002 SW 2002 1 23 HEEA077610 1 20011218 G 6510 BEARING BELL 407 407 1182206 SW BELLCRANK WORN E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 402PH 53159 TAIL ROTOR BELLCRANK BEARING WORN. 1 G 7 1 3U O H2SW 2002012300003 20020123 00003 SW 2002 1 23 HEEA077611 1 20011218 G 6300 BEARING BELL 407 407 1182206 SW PITCH LINK WORN E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 402PH AF6463 53159 BEARING WORN. 1 G 7 1 3U O H2SW 2002012300004 20020123 00004 SW 2002 1 23 HEEA077612 1 20011218 G 6300 406310405101 UNIVERSAL BELL 407 407 1182206 SW M/R DRIVE WORN E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 490PH 53378 MAIN ROTOR DRIVE UNIVERSAL IS WORN. 1 G 7 1 3U O H2SW 2002012300005 20020123 00005 SW 2002 1 23 HEEA077613 1 20011218 G 6321 206076047101 CYLINDER BELL 407 407 1182206 SW MAIN ROTOR BRAKE DAMAGED E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 495PH 53397 MAIN ROTOR BRAKE CYLINDER HANDLE HARD TO OPERATE. 1 G 7 1 3U O H2SW 2002012300006 20020123 00006 SW 2002 1 23 HEEA077614 1 20011218 G 2822 1C2710 CARTRIDGE BELL 407 407 1182206 SW FUEL PUMP INOPERATIVE E HEEA O OTHER O OTHER NR NOT REPORTED 1 SW 03 719PH 53266 FUEL PUMP CARTRIDGE INOPERATIVE. 1 G 7 1 3U O H2SW 2002012300007 20020123 00007 SW 2002 1 23 HEEA077615 1 20011219 G 6320 214040806003 PRESSURE SWITCH BELL 407 407 1182206 SW M/R GEARBOX FAILED E HEEA K NONE L NO TEST IN INSP/MAINT 1 SW 03 499PH 53400 WOULD NOT TURN ON TRANSMISSION LIGHT AFTER SHUTDOWN. 1 G 7 1 3U O H2SW 2002012300008 20020123 00008 SW 2002 1 23 HEEA077616 1 20011219 G 6300 406310405101 UNIVERSAL BELL 407 407 1182206 SW M/R DRIVE WORN E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 494PH 2367 53396 MAIN ROTOR DRIVE UNIVERSAL IS WORN. 1 G 7 1 3U O H2SW 2002012300009 20020123 00009 SW 2002 1 23 HEEA077617 1 20011219 G 6300 406310405101 UNIVERSAL BELL 407 407 1182206 SW M/R DRIVE WORN E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 494PH 671 53396 MAIN ROTOR DRIVE UNIVERSAL IS WORN. 1 G 7 1 3U O H2SW 2002012300010 20020123 00010 SW 2002 1 23 HEEA077618 1 20011219 G 6300 406310405101 UNIVERSAL BELL 407 407 1182206 SW M/R DRIVE WORN E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 494PH 1150 53396 MAIN ROTOR DRIVE UNIVERAL IS WORN. 1 G 7 1 3U O H2SW 2002012300011 20020123 00011 SW 2002 1 23 HEEA077619 1 20011219 G 6300 406310405101 UNIVERSAL BELL 407 407 1182206 SW M/R DRIVE WORN E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 494PH 2201 53396 MAIN ROTOR DRIVE UNIVERSAL IS WORN. 1 G 7 1 3U O H2SW 2002012300012 20020123 00012 SW 2002 1 23 HEEA077620 1 20011219 G 6322 206061432121 HOUSING BELL 407 407 1182206 SW COOLER BLOWER DAMAGED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 493PH 53393 COOLER BLOWER HOUSING HAS WORKING RIVETS. 1 G 7 1 3U O H2SW 2002012300013 20020123 00013 SW 2002 1 23 HEEA077621 1 20011219 G 2840 407362005103 SWITCH BELL 407 407 1182206 SW FUEL SYSTEM STUCK E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 491PH 53386 SWITCH STICKING, INACCURATE READINGS TO GAUGE. 1 G 7 1 3U O H2SW 2002012300014 20020123 00014 SW 2002 1 23 HEEA077622 1 20011219 G 6420 406312100101 BEARING 407012101111 BELL 407 407 1182206 SW TAIL ROTOR HUB WORN E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 493PH 53400 53393 TAIL ROTOR HUB BEARING IS WORN. 1 G 7 1 3U O H2SW 2002012300015 20020123 00015 SW 2002 1 23 HEEA077623 1 20011219 G 7712 222375077119 TRANSMITTER BELL 407 407 1182206 SW TORQUE INDICATOR FAILED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 402PH 53159 CEASED SENDING PRESSURE SIGNAL TO TORQUE GAUGE. 1 G 7 1 3U O H2SW 2002012300016 20020123 00016 SW 2002 1 23 HEEA077624 1 20011219 G 6300 406310405101 UNIVERSAL BELL 407 407 1182206 SW M/R DRIVE WORN E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 740PH 916 53435 MAIN ROTOR DRIVE UNIVERSAL WORN. 1 G 7 1 3U O H2SW 2002012300017 20020123 00017 SW 2002 1 23 HEEA077625 1 20011219 G 6300 406310405101 UNIVERSAL BELL 407 407 1182206 SW M/R DRIVE WORN E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 740PH 916 53435 MAIN ROTOR DRIVE UNIVERSAL IS WORN. 1 G 7 1 3U O H2SW 2002012300018 20020123 00018 SW 2002 1 23 HEEA077626 1 20011219 G 2822 407362013101 PRESSURE SWITCH BELL 407 407 1182206 SW BOOST PUMP FAILED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 491PH 53386 RIGHT FUEL BOOST PUMP LIGHT DOES NOT COME ON WHEN CIRCUIT BREAKER SWITCH IS TURNED OFF. 1 G 7 1 3U O H2SW 2002012300019 20020123 00019 SW 2002 1 23 HEEA077627 1 20011219 G 2510 407370720101 SEAT BELT BELL 407 407 1182206 SW COCKPIT FRAYED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 491PH 53386 SEAT BELT HAS FRAYED ENDS. 1 G 7 1 3U O H2SW 2002012300095 20020123 00095 SW 2002 1 23 HEEA077628 1 20011219 G 6300 406012129101 PITCH LINK BELL 407 407 1182206 SW MAIN ROTOR WORN E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 501PH 53401 PITCH LINK BEARING WORN ON RIVET SIDE. 1 G 7 1 3U O H2SW 2002012300097 20020123 00097 SW 2002 1 23 HEEA077629 1 20011219 G 6300 407340339101 BEARING BELL 407 407 1182206 SW MAIN ROTOR ROUGH E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 492PH 53390 GREASE TURNING DARK GREY. BEARING ROUGH. 1 G 7 1 3U O H2SW 2002012300099 20020123 00099 SW 2002 1 23 HEEA077630 1 20011219 G 6300 407340339101 BEARING BELL 407 407 1182206 SW MAIN ROTOR OVERHEATED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 406PH 53198 MAIN ROTOR BEARING RUNNING HOT. LABEL TURNED BLACK. 1 G 7 1 3U O H2SW 2002012300100 20020123 00100 SW 2002 1 23 HEEA077631 1 20011219 G 6510 206061432121 HOUSING BELL 407 407 1182206 SW COOLER BLOWER CRACKED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 501PH 53401 BLOWER HOUSING CRACKED AT LEFT HAND CORNER. 1 G 7 1 3U O H2SW 2002012300101 20020123 00101 SW 2002 1 23 HEEA077632 1 20011219 G 2822 407362013101 PRESSURE SWITCH BELL 407 407 1182206 SW ENGINE MALFUNCTIONED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 495PH 53397 LIGHT WILL NOT COME ON. 1 G 7 1 3U O H2SW 2002012300102 20020123 00102 SW 2002 1 23 HEEA077634 1 20011219 G 6300 406310405101 UNIVERSAL BELL 407 407 1182206 SW MAIN ROTOR WORN E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 490PH 1910 53378 MAIN ROTOR UNIVERSAL WORN. 1 G 7 1 3U O H2SW 2002012300103 20020123 00103 SW 2002 1 23 HEEA077635 1 20011219 G 6510 206061432121 HOUSING BELL 407 407 1182206 SW COOLER BLOWER CRACKED E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 499PH 53400 COOLER BLOWER HOUSING CRACKED. 1 G 7 1 3U O H2SW 2002012300104 20020123 00104 SW 2002 1 23 HEEA077638 1 20011219 G 6420 BEARING BELL 407 407 1182206 SW PITCH LINK WORN E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 499PH 53400 BEARINGS WORN. 1 G 7 1 3U O H2SW 2002012300105 20020123 00105 SW 2002 1 23 HEEA077640 1 20011219 G 6420 BEARING BELL 407 407 1182206 SW PITCH LINK WORN E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 496PH 53398 PITCH LINK HAS WORN BEARINGS. 1 G 7 1 3U O H2SW 2002012300106 20020123 00106 SW 2002 1 23 HEEA077641 1 20011219 G 3212 206050247138 COVER BELL 407 407 1182206 SW FLOAT WORN E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 491PH 53386 FLOAT COVER ASSY WORN. 1 G 7 1 3U O H2SW 2002012300107 20020123 00107 SW 2002 1 23 HEEA077642 1 20011219 G 3212 206050247137 COVER BELL 407 407 1182206 SW FLOAT WORN E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 491PH 53386 FLOAT COVER END CAP WORN. 1 G 7 1 3U O H2SW 2002012300108 20020123 00108 SW 2002 1 23 HEEA077643 1 20011219 G 3212 206050247132 COVER BELL 407 407 1182206 SW FLOAT WORN E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 491PH 53386 FLOAT COVER ASSY WORN. 1 G 7 1 3U O H2SW 2002012300109 20020123 00109 SW 2002 1 23 HEEA077644 1 20011219 G 6420 406012129101 LINK BELL 407 407 1182206 SW PITCH LINK ASSY WORN E HEEA K NONE O OTHER IN INSP/MAINT 1 SW 03 407PH 53003 PITCH LINK ASSY WORN. 1 G 7 1 3U O H2SW 2002060600082 20020606 00082 SW 2002 6 6 HEEA079393 1 20010910 G 7740 DPUA0101 COMPUTER BELL 206 206L3 1182108 SW COCKPIT MALFUNCTIONED E K NONE O OTHER IN INSP/MAINT 1 SW 03 41791 51465 INTELLISTART LIGHT STAYS ON, COULDN'T ACCESS WITH MLP. SENT TO ALTAIR AVIONICS CORP. FOR INSPECTION AND REPAIR. 1 G 7 1 3U H2SW 2001041900195 20010419 00195 2001 4 19 HEED072193 4 20010314 G 2210 7690001802106 ACTUATOR SKRSKY S76 S76C 8143008 NE AFCS ERRATIC E HEED O OTHER O OTHER NR NOT REPORTED 1 SW 03 278X 760440 ERRATIC OPERATION WHEN CYCLIC ISMOVED TO THE RIGHT OF CENTER. REPLACED UNIT. 1 G 7 2 3U NC H1NE 2001041900218 20010419 00218 SW 2001 4 19 HEED072195 1 20010314 G 2435 206062200113 STARTER GEN BELL 407 407 SW ENGINE FAILED E HEED O OTHER O OTHER NR NOT REPORTED 1 SW 03 3193E 53276 PILOT INFLIGHT HEARD BANG IN HEADSET FOLLOWED BY SERVERE STATIC IN HEADSET. GENERATOR VOLTAGE METER STARTED DROPPING FRO M 28 VOLTS UP ON LANDING. REPLACED UNIT. 1 G 7 1 3U O H2SW 2001041900219 20010419 00219 2001 4 19 HEED072198 4 20010314 G 3416 06603640005 ENCODER BELL 407 407 SW ALTIMETER MALFUNCTIONED E HEED O OTHER O OTHER NR NOT REPORTED 1 SW 03 3193E 53276 UNRELIABLE SIGNAL RYAN TCAD DISPLAYS STARS CODE. PART WAS BAD FROM STOCK. MODE C SIGNAL WAS 22,000 FT (SHOULD HAVE BEEN 1,000 FT) REPLACED UNIT. 1 G 7 1 3U O H2SW 2001041900196 20010419 00196 2001 4 19 HEED072200 4 20010314 G 3454 066107810 RECEIVER SKRSKY S76 S76C 8143008 NE COCKPIT INOPERATIVE E HEED O OTHER O OTHER NR NOT REPORTED 1 SW 03 476X 760436 DOES NOT DRIVE NR 1 POINTER ON HSI PILOTS OR COPILOTS. REPLACED UNIT. 1 G 7 2 3U NC H1NE 2001041900197 20010419 00197 2001 4 19 HEED072201 4 20010314 G 2300 A30161ACR MIXER BOX SKRSKY S76 S76C 8143008 NE COCKPIT INTERMITTENT E HEED O OTHER O OTHER NR NOT REPORTED 1 SW 03 476X 760436 INTERMITTANT LOSS OF HEADSET SIDETONE. REPLACED UNIT. 1 G 7 2 3U NC H1NE 2001041900198 20010419 00198 NE 2001 4 19 HEED072202 1 20010314 G 7920 0292105230 PUMP SKRSKY S76 S76C 8143008 NE OIL SYSTEM FAILED E HEED O OTHER O OTHER NR NOT REPORTED 1 SW 03 476X 760436 OIL DRAINS BACK INTO ACCESSORY GEARBOX AFTER SHUTDOWN. REPLACED UNIT. 1 G 7 2 3U NC H1NE 2001041900199 20010419 00199 NE 2001 4 19 HEED072203 2 20010314 G 7421 9550166670 IGNITER SKRSKY S76 S76C 8143008 NE TMECA ARRIEL ARRIEL1S 60030 NE ENGINE WEAK E HEED O OTHER O OTHER NR NOT REPORTED 1 SW 03 476X 760436 WEAK- WILL NOT START AIRCRAFT. FOUND BAD ON 150 HOURS INSPECTION. REPLACED UNIT. 1 G 7 2 3U 3 U NC H1NE E19EU 2001041900200 20010419 00200 NE 2001 4 19 HEED072204 2 20010314 G 7210 9560134100 MAGNETIC SEAL SKRSKY S76 S76C 8143008 NE TMECA ARRIEL ARRIEL1S 60030 NE ENGINE LEAKING E HEED O OTHER K FLUID LOSS NR NOT REPORTED 1 SW 03 476X 760436 THIS SEAL LEAKED SINCE THE ENGINE 15529 WAS INSTALLED ON 9/7/2000 AT ATT: 4867.15 REPLACED UNIT. 1 G 7 2 3U 3 U NC H1NE E19EU 2001041900201 20010419 00201 2001 4 19 HEED072205 4 20010314 G 2300 A30161ACR MIXER BOX SKRSKY S76 S76C 8143008 NE COCKPIT INTERMITTENT E HEED O OTHER O OTHER NR NOT REPORTED 1 SW 03 478X 760493 BOX CUTS OUT IN ICS. REPLACED UNIT. 1 G 7 2 3U NC H1NE 2001041900202 20010419 00202 2001 4 19 HEED072206 4 20010314 G 2300 A30161ACR MIXER BOX SKRSKY S76 S76C 8143008 NE COCKPIT INTERMITTENT E HEED O OTHER O OTHER NR NOT REPORTED 1 SW 03 478X 760493 INTERMITTLY INOPERATIVE COMPLETELY IN ALL SWITCH POSITIONS. REPLACED UNIT. 1 G 7 2 3U NC H1NE 2001041900203 20010419 00203 2001 4 19 HEED072207 4 20010314 G 2300 A30161ACR MIXER BOX SKRSKY S76 S76C 8143008 NE COCKPIT MALFUNCTIONED E HEED O OTHER O OTHER NR NOT REPORTED 1 SW 03 278X 760440 THIDS ICS BOX WAS JUST RETURNED FROM REPAIR FOR THE SAME THING-BLEED OVER ON VHF''''S AND NAV''''S. REPLACED UNIT. 1 G 7 2 3U NC H1NE 2001041900204 20010419 00204 NE 2001 4 19 HEED072208 1 20010314 G 2910 7665009801104 MODULE SKRSKY S76 S76C 8143008 NE HYD SYSTEM MALFUNCTIONED E HEED O OTHER J WARNING INDICATION NR NOT REPORTED 1 SW 03 478X 760493 HYD MODULE CAUSES INTERMITT 32 SYSTEM SERVO LITE. REPLACED UNIT. 1 G 7 2 3U NC H1NE 2001041900205 20010419 00205 NE 2001 4 19 HEED072211 1 20010314 G 6210 7615009100053 BLADE SKRSKY S76 S76C 8143008 NE MAIN ROTOR CRACKED E HEED K NONE O OTHER IN INSP/MAINT 1 SW 03 476X 760436 SUSPECT CRACKING OF MAIN ROTOR SPAR. REPLACED UNIT. 1 G 7 2 3U NC H1NE 2001041900206 20010419 00206 NE 2001 4 19 HEED072212 2 20010314 G 7421 9550166670 IGNITER SKRSKY S76 S76C 8143008 NE TMECA ARRIEL ARRIEL1S 60030 NE ENGINE ERODED E HEED O OTHER O OTHER NR NOT REPORTED 1 SW 03 476X 760436 ERODED CENTER ELECTRODE. REPLACED UNIT. 1 G 7 2 3U 3 U NC H1NE E19EU 2001041900207 20010419 00207 NE 2001 4 19 HEED072213 2 20010314 G 7261 0292105230 PUMP SKRSKY S76 S76C 8143008 NE TMECA ARRIEL ARRIEL1S1 60030 NE OIL SYSTEM FLUCTUATES E HEED O OTHER O OTHER NR NOT REPORTED 1 SW 03 476X 760436 15529TEC FLUCTUATING OIL PRESSURE . REPLACED UNIT. 1 G 7 2 3U 3 U NC H1NE E19EU 2001041900208 20010419 00208 NE 2001 4 19 HEED072214 1 20010314 G 2437 50284003 PANEL SKRSKY S76 S76C 8143008 NE COCKPIT WILL NOT TEST E HEED O OTHER L NO TEST NR NOT REPORTED 1 SW 03 476X 760436 BATTERY FEED FAULT WILL NOT TEST PROPERLY. REPLACED UNIT. 1 G 7 2 3U NC H1NE 2001041900209 20010419 00209 2001 4 19 HEED072215 4 20010314 G 3457 8144002241D GPS SKRSKY S76 S76C 8143008 NE COCKPIT MALFUNCTIONED E HEED O OTHER O OTHER NR NOT REPORTED 1 SW 03 476X 760436 COPILOT HSI NEEDLE WILL NOT POINT TO LRN HEADING, SYSTEM WENT OFFLINE AND LOST. REPLACED UNIT. 1 G 7 2 3U NC H1NE 2001041900210 20010419 00210 NE 2001 4 19 HEED072216 2 20010314 G 7200 1S1 ENGINE SKRSKY S76 S76C 8143008 NE TMECA ARRIEL ARRIEL1S1 60030 NE ENGINE BAY MAKING METAL E HEED O OTHER O OTHER NR NOT REPORTED 1 SW 03 89H 760406 GENERATING METAL AT THE ACCESSORY MAG PLUG. REPLACED UNIT. 1 G 7 2 3U 3 U NC H1NE E19EU 2001041900211 20010419 00211 NE 2001 4 19 HEED072218 1 20010315 G 6220 SB5080102 ROD END BEARING SKRSKY S76 S76C 8143008 NE MAIN ROTOR WORN E HEED O OTHER O OTHER NR NOT REPORTED 1 SW 03 89H 760406 BEARING WORN. REPLACED UNIT. 1 G 7 2 3U NC H1NE 2001041900212 20010419 00212 2001 4 19 HEED072220 4 20010315 G 2300 A30161ACYR MIXER BOX SKRSKY S76 S76C 8143008 NE COCKPIT INTERMITTENT E HEED O OTHER O OTHER NR NOT REPORTED 1 SW 03 278X 760440 ICS BOX INTERMITTENT OPERATION IN ALL CHANNELS. REPLACED UNIT. 1 G 7 2 3U NC H1NE 2001041900213 20010419 00213 NE 2001 4 19 HEED072221 1 20010315 G 7922 8A308203 THERMOSTAT SKRSKY S76 S76C 8143008 NE OIL TEMP MALFUNCTIONED E HEED O OTHER O OTHER NR NOT REPORTED 1 SW 03 89H 760406 CAUSING HIGH OIL TEMPERATURE. LOCALLY SCRAPPED. REPLACED UNIT. 1 G 7 2 3U NC H1NE 2001042000079 20010420 00079 NE 2001 4 20 HEED072223 1 20010315 G 3246 50075551 WHEEL SKRSKY S76 S76C 8143008 NE NLG WORN E HEED O OTHER O OTHER NR NOT REPORTED 1 SW 03 89H 760406 LININGS P/N 50007665, WORN. REPLACED UNIT. 1 G 7 2 3U NC H1NE 2001041900214 20010419 00214 2001 4 19 HEED072224 4 20010315 G 2300 A30161ACR MIXER BOX SKRSKY S76 S76C 8143008 NE COCKPIT INTERMITTENT E HEED O OTHER O OTHER NR NOT REPORTED 1 SW 03 89H 760406 CUTS OUT ALL STATIONS DURING TRANSMITTION AND RECEPTION. REPLACED UNIT. 1 G 7 2 3U NC H1NE 2001041900215 20010419 00215 NE 2001 4 19 HEED072225 1 20010315 G 3246 50075551 WHEEL SKRSKY S76 S76C 8143008 NE NLG WORN E HEED O OTHER O OTHER NR NOT REPORTED 1 SW 03 89H 760406 LININGS ARE WORN. REPLACED UNIT. 1 G 7 2 3U NC H1NE 2001041900220 20010419 00220 SW 2001 4 19 HEED072226 1 20010315 G 2841 407375006101 INDICATOR BELL 407 407 SW FUEL QUANITY INOPERATIVE E HEED O OTHER O OTHER NR NOT REPORTED 1 SW 03 3193E 53276 DISPLAY, BLANK, NO NUMBER ON BARS SHOWING. REPLACED UNIT. 1 G 7 1 3U O H2SW 2001041900221 20010419 00221 SW 2001 4 19 HEED072233 1 20010315 G 3244 028630 TIRE BELL 430 430 1182150 SW MLG WORN E HEED O OTHER O OTHER NR NOT REPORTED 1 SW 03 430X 857 49058 EXCESSIVE WEAR. REPLACED UNIT. 1 G 7 2 3U RT H9SW 2001041900216 20010419 00216 NE 2001 4 19 HEED072251 1 20010316 G 3610 7650007903102 SHUTOFF VALVE SKRSKY S76 S76C 8143008 NE BLEED AIR LEAKING E HEED O OTHER O OTHER NR NOT REPORTED 1 SW 03 89H 760406 LEAKING WILL NOT SHUT OFF. REPLACED UNIT. 1 G 7 2 3U NC H1NE 2001041900217 20010419 00217 NE 2001 4 19 HEED072254 2 20010316 G 7210 9560115450 MAGNETIC SEAL SKRSKY S76 S76C 8143008 NE TMECA ARRIEL ARRIEL1S 60030 NE ENGINE LEAKING E HEED O OTHER K FLUID LOSS NR NOT REPORTED 1 SW 03 476X 760436 THIS SEAL LEAKED SINCE THE ENGINE S/N 15529 WAS INSTALLED ON 9/7/2000. REPLACED UNIT. 1 G 7 2 3U 3 U NC H1NE E19EU 2001080700338 20010807 00338 2001 8 7 HEED073491 4 20010614 G 2350 A30161ACVR ICS BOX SKRSKY S76 S76C 8143008 NE COCKPIT INTERMITTENT E HEED O OTHER O OTHER NR NOT REPORTED 1 SW 03 478X 61 760493 INTERMITTENTLY TRANSMISSION ON ALL CHANNELS. REPLACED UNIT. 1 G 7 2 3U NC H1NE 2001080700339 20010807 00339 NE 2001 8 7 HEED073492 1 20010614 G 3340 3012543 LIGHT SKRSKY S76 S76C 8143008 NE STROBE BURNED OUT E HEED K NONE O OTHER IN INSP/MAINT 1 SW 03 478X 760493 FLASH TUBE BURNED OUT. SCRAPPED REPLACED UNIT. 1 G 7 2 3U NC H1NE 2001080700340 20010807 00340 NE 2001 8 7 HEED073493 1 20010614 G 7714 H190110 INDICATOR SKRSKY S76 S76C 8143008 NE ENGINE N1 FAILED E HEED K NONE O OTHER IN INSP/MAINT 1 SW 03 478X 760493 PIECES OF LED SECTIONS MISSING IN NUMBER DISPLAY. BURNED OUT. REPLACED UNIT. 1 G 7 2 3U NC H1NE 2001080700341 20010807 00341 NE 2001 8 7 HEED073494 1 20010614 G 2432 RG380E44 BATTERY SKRSKY S76 S76C 8143008 NE MAIN DISCHARGED E HEED K NONE L NO TEST IN INSP/MAINT 1 SW 03 478X 760493 WOULD CRANK AIRCRAFT ENGINES TO START BATTERY DEAD. VERY WEAK ON FIRST START OFTHE DAY. REPLACED UNIT. 1 G 7 2 3U NC H1NE 2001080700344 20010807 00344 NE 2001 8 7 HEED073495 1 20010614 G 3110 SCREW SKRSKY S76 S76C 8143008 NE AHRS BROKEN E HEED K NONE O OTHER IN INSP/MAINT 1 SW 03 476X 3507 1005 760436 J2 PLUG ATTACHMENT SCREW IS BROKEN. REPLACED UNIT. 1 G 7 2 3U NC H1NE 2001080700346 20010807 00346 NE 2001 8 7 HEED073496 1 20010614 G 5320 9550147560 FITTING SKRSKY S76 S76C 8143008 NE THREADS CORRODED E HEED K NONE O OTHER IN INSP/MAINT 1 SW 03 476X 760436 INTERNAL THREADS FOR BANJO FITTING ARE CORRODED. REPLACED UNIT. 1 G 7 2 3U NC H1NE 2001080700347 20010807 00347 NE 2001 8 7 HEED073497 2 20010614 G 7321 0164348810 FUEL CONTROL SKRSKY S76 S76C 8143008 NE TMECA ARRIEL ARRIEL1S 60030 NE ENGINE MALFUNCTIONED E HEED K NONE O OTHER IN INSP/MAINT 1 SW 03 476X 760436 N2 LAGS CREATING A 20 PERCENT TORQUE SPLIT. REPLACED UNIT. 1 G 7 2 3U 3 U NC H1NE E19EU 2001080700351 20010807 00351 NE 2001 8 7 HEED073498 2 20010614 G 7261 CHECK VALVE SKRSKY S76 S76C 8143008 NE TMECA ARRIEL ARRIEL1S 60030 NE OIL PUMP STUCK E HEED K NONE O OTHER IN INSP/MAINT 1 SW 03 476X 722SO 760436 CHECK VALVE STICKING. REPLACED UNIT. 1 G 7 2 3U 3 U NC H1NE E19EU 2001080700353 20010807 00353 NE 2001 8 7 HEED073499 1 20010614 G 2560 110175601 SEAT BELT SKRSKY S76 S76C 8143008 NE COCKPIT WORN E HEED K NONE O OTHER IN INSP/MAINT 1 SW 03 476X 5687 760436 WORN SEAT BELT. REPLACED UNIT. 1 G 7 2 3U NC H1NE 2001080700355 20010807 00355 2001 8 7 HEED073500 4 20010614 G 2210 BEARING SKRSKY S76 S76C 8143008 NE AFCS ACTUATOR WORN E HEED O OTHER O OTHER NR NOT REPORTED 1 SW 03 89H 760406 PIVOT BEARINGS WORN. REPLACED UNIT. 1 G 7 2 3U NC H1NE 2001080700357 20010807 00357 2001 8 7 HEED073501 4 20010614 G 2312 071128265 CONTROL HEAD SKRSKY S76 S76C 8143008 NE VHF SYSTEM MALFUNCTIONED E HEED O OTHER O OTHER NR NOT REPORTED 1 SW 03 89H 760406 TURNS ITSELF OFF AFTER 2 OR 3 MINUTES. REPLACED UNIT. 1 G 7 2 3U NC H1NE 2001080700359 20010807 00359 2001 8 7 HEED073502 4 20010614 G 2350 A30161ACVR ICS BOX SKRSKY S76 S76C 8143008 NE COCKPIT NOISY E HEED O OTHER O OTHER NR NOT REPORTED 1 SW 03 89H 760406 LOUD NOISE IN MIC. REPLACED UNIT. 1 G 7 2 3U NC H1NE 2001080700361 20010807 00361 2001 8 7 HEED073503 4 20010614 G 2350 A30161ACVR ICS BOX SKRSKY S76 S76C 8143008 NE COCKPIT FAILED E HEED O OTHER O OTHER NR NOT REPORTED 1 SW 03 89H 760406 COPILOT HEADSET FREQUENTLY CUTS OUT. BAD FROM STOCK. REPLACED UNIT. 1 G 7 2 3U NC H1NE 2001080700363 20010807 00363 2001 8 7 HEED073504 4 20010614 G 2350 A30161ACVR ICS BOX SKRSKY S76 S76C 8143008 NE COCKPIT FAILED E HEED O OTHER O OTHER NR NOT REPORTED 1 SW 03 89H 760406 COPILOT HEADSET FREQUENTLY CUTS OUT. BAD FROM STOCK. REPLACED UNIT. 1 G 7 2 3U NC H1NE 2001080700365 20010807 00365 2001 8 7 HEED073505 4 20010614 G 2210 7690001802106 ACTUATOR SKRSKY S76 S76C 8143008 NE AFCS CHATTERING E HEED K NONE O OTHER IN INSP/MAINT 1 SW 03 478X 760493 CHATTERING. REPLACED UNIT. 1 G 7 2 3U NC H1NE 2001080700366 20010807 00366 NE 2001 8 7 HEED073506 2 20010614 G 7200 70BMA01040 CONTROL UNIT SKRSKY S76 S76C 8143008 NE TMECA ARRIEL ARRIEL1S1 60030 NE ENGINE FAILED E HEED O OTHER O OTHER NR NOT REPORTED 1 SW 03 478X 2968 760493 20063 NR 1 ENGINE RUN UP FAULT. REPLACED UNIT. 1 G 7 2 3U 3 U NC H1NE E19EU 2001080700367 20010807 00367 2001 8 7 HEED073507 4 20010614 G 2370 D5152010112 CVR SKRSKY S76 S76C 8143008 NE COCKPIT WILL NOT TEST E HEED K NONE L NO TEST IN INSP/MAINT 1 SW 03 478X 760493 FDR WILL NOT TEST. REPLACED UNIT. 1 G 7 2 3U NC H1NE 2001080700368 20010807 00368 2001 8 7 HEED073508 4 20010614 G 2210 7690001802106 ACTUATOR SKRSKY S76 S76C 8143008 NE AFCS INTERMITTENT E HEED O OTHER O OTHER NR NOT REPORTED 1 SW 03 478X 760493 KICKING INTERMITTLY. REPLACED UNIT. 1 G 7 2 3U NC H1NE 2001080700396 20010807 00396 2001 8 7 HEED073511 4 20010614 G 2210 7690001802106 ACTUATOR SKRSKY S76 S76C 8143008 NE AFCS CHATTERING E HEED O OTHER O OTHER NR NOT REPORTED 1 SW 03 278X 760440 CHATTERING, ROUGH IN TRAVEL, STICKING. REPLACED UNIT. 1 G 7 2 3U NC H1NE 2001080700398 20010807 00398 NE 2001 8 7 HEED073512 1 20010614 G 3240 BRAKE SKRSKY S76 S76C 8143008 NE NLG WORN E HEED K NONE O OTHER IN INSP/MAINT 1 SW 03 278X 760440 WORN BRAKES. S/NOS: DEC-82-217, AND NOV-3-467. REPLACED UNIT. S/NOS: JAN 80-286, AND MAR 84-677. 1 G 7 2 3U NC H1NE 2001080700399 20010807 00399 2001 8 7 HEED073513 4 20010614 G 2210 7690001802106 ACTUATOR SKRSKY S76 S76C 8143008 NE AFCS CHATTERING E HEED K NONE O OTHER IN INSP/MAINT 1 SW 03 278X 760440 JUMPING, CHATTERING. REPLACED UNIT. 1 G 7 2 3U NC H1NE 2001080700401 20010807 00401 NE 2001 8 7 HEED073514 1 20010614 G 3230 4608 PRIORITY VALVE SKRSKY S76 S76C 8143008 NE MLG FAULTY E HEED K NONE O OTHER IN INSP/MAINT 1 SW 03 278X 5007 760440 IRREGULAR PRESSURE CAUSES RANGING GEAR TO RETRACT UNEVENLY. REPLACED UNIT. 1 G 7 2 3U NC H1NE 2001080700403 20010807 00403 SW 2001 8 7 HEED073543 1 20010614 G 3260 222336001105 ACTUATOR BELL 430 430 1182150 SW DOWNLOCK LEAKING E HEED K NONE O OTHER IN INSP/MAINT 1 SW 03 430X 1081 49058 LEAKS. REPLACED UNIT. 1 G 7 2 3U RT H9SW 2001080700428 20010807 00428 SW 2001 8 7 HEED073545 1 20010614 G 7400 FCB205AT9 RELAY BELL 407 407 SW ALLSN 250B 250B* GL IGNITER FAILED E HEED O OTHER O OTHER NR NOT REPORTED 1 SW 03 3193E 1986 53276 AUTO RELIGHT ON CAUTION PANEL FAILED TO COME ON AT ENGINE START ATTEMPLT AND NO ENGINE IGNITION OR LIGHT OFF. SCRAPPED. REPLACED UNIT. 1 G 7 1 3U 3 T O H2SW E10CE 2001080700429 20010807 00429 GL 2001 8 7 HEED073546 2 20010614 G 7421 CH34187A IGNITER BELL 407 407 SW ALLSN 250B 250B* GL ENGINE CRACKED E HEED K NONE O OTHER IN INSP/MAINT 1 SW 03 3193E 1986 53276 CRACKED CERAMIC AND ERROIDED TIP. REPLACED UNIT. 1 G 7 1 3U 3 T O H2SW E10CE 2001080700430 20010807 00430 SW 2001 8 7 HEED073548 1 20010614 G 6500 ES731861 BLOWER BELL 407 407 SW TAIL ROTOR SHORTED E HEED K NONE O OTHER IN INSP/MAINT 1 SW 03 3193E 53276 POPS CIRCUIT BREAKER. REPLACED UNIT. 1 G 7 1 3U O H2SW 2001080700431 20010807 00431 SW 2001 8 7 HEED073549 1 20010614 G 2841 407375006101 INDICATOR BELL 407 407 SW FUEL QUANITY FAILED E HEED K NONE O OTHER IN INSP/MAINT 1 SW 03 3193E 53276 DISPLAY BLANK REPLACED UNIT. 1 G 7 1 3U O H2SW 2001080700432 20010807 00432 2001 8 7 HEED073550 4 20010614 G 3120 775330200 CLOCK BELL 407 407 SW COCKPIT STOPPED E HEED K NONE O OTHER IN INSP/MAINT 1 SW 03 3193E 53276 CLOCK STOPPED. REPLACED UNIT. 1 G 7 1 3U O H2SW 2001080700433 20010807 00433 SW 2001 8 7 HEED073552 1 20010614 G 6322 407040303101 SHAFT BELL 407 407 SW FAN VIBRATION E HEED O OTHER E VIBRATION/BUFFET NR NOT REPORTED 1 SW 03 3193E 1178 53276 HIGH RDA VIBRATION LEVEL. REPLACED UNIT. 1 G 7 1 3U O H2SW 2001080700434 20010807 00434 SW 2001 8 7 HEED073553 1 20010614 G 6510 ES731861 MOTOR BELL 407 407 SW BLOWER FAILED E HEED K NONE O OTHER IN INSP/MAINT 1 SW 03 3193E 53276 POP CIRCUIT BREAKER. REPLACED UNIT. 1 G 7 1 3U O H2SW 2001092400101 20010924 00101 SW 2001 9 24 HEED073554 1 20010614 G 6300 406310405101 BEARING BELL 407 407 SW P/C LINK WORN E HEED K NONE O OTHER IN INSP/MAINT 1 SW 03 3193E 2164 53276 WORN BEARINGS, SCRAPPED. REPLACED UNIT. 1 G 7 1 3U O H2SW 2001092400103 20010924 00103 SW 2001 9 24 HEED073555 1 20010614 G 6300 406010417101 BEARING BELL 407 407 SW P/C LINK WORN E HEED K NONE O OTHER IN INSP/MAINT 1 SW 03 3193E 2189 53276 WORN BEARINGS, SCRAPPED. REPLACED UNIT. 1 G 7 1 3U O H2SW 2001092400104 20010924 00104 SW 2001 9 24 HEED073556 1 20010614 G 6300 406010417101 BEARING BELL 407 407 SW P/C LINK WORN E HEED K NONE O OTHER IN INSP/MAINT 1 SW 03 3193E 2189 53276 WORN BEARINGS, SCRAPPED. REPLACED UNIT. 1 G 7 1 3U O H2SW 2001092400105 20010924 00105 SW 2001 9 24 HEED073557 1 20010614 G 7931 222375077113 TRANSMITTER BELL 407 407 SW OIL PRESSURE FLUCTUATES E HEED K NONE O OTHER IN INSP/MAINT 1 SW 03 3193E 2065 53276 FLUCTUATING OIL PRESSURE. REPLACED UNIT. 1 G 7 1 3U O H2SW 2001071300079 20010713 00079 NM 2001 7 13 HN6R0000218 1 20010618 G 5311 FRAME BOEING 737 737400 NM FUSELAGE CRACKED B HN6R K NONE O OTHER IN INSP/MAINT 1 NM 01 932NU 25248 BS 827 FRAME IS CRACKED AT PSU RAIL ATTACHMENT BRACKET INBOARD FASTENER (LEFT HAND SIDE). CAUSE UNKNOWN . REMOVED DAM AGE, FABRICATED REPAIR PARTS AND INSTALLED. 2 L 7 2 4F RT A16WE 2002012300133 20020123 00133 EU 2002 1 23 ISHA077178 1 20011119 G 6520 350A3310021 PINION GEAR 350A33020005 SNIAS 350 AS350D 8680803 EU T/R GEARBOX DEFECTIVE H ISHA K NONE O OTHER IN INSP/MAINT 1 FS 01 67GE 3243 M1280 1604 GEAR REJECTED AT INTERMOUNTAIN TURBINE FOR PITTING AND UNABLE TO ESTABLISH PROPER STATIC GEAR PATTERN REPLACED ASSY. WIT H EXCHANGE 1 G 7 1 3U H9EU 2002012300134 20020123 00134 EU 2002 1 23 ISHA077179 1 20011119 G 6520 350A33100121 BEVEL GEAR 350A33020005 SNIAS 350 AS350D 8680803 EU T/R GEARBOX DEFECTIVE H ISHA K NONE O OTHER IN INSP/MAINT 1 FS 01 67GE 3243 M1280 1604 REJECTED BY NAMPA VALLEY HELICOPTERS DUE TO PITTING AND UNABLE TO ESTABLISH STATIC GEAR PATTERN REPLACED WITH EXCHANGE A SSY. 1 G 7 1 3U H9EU 2001092400107 20010924 00107 EU 2001 9 24 IVSA074819 1 20010806 G 3340 122394R5123 MODULE UROCOP EC120 EC120B 8680987 EU LIGHT BURNED OUT H IVSA O OTHER O OTHER CR CRUISE 1 FS 01 166DL 227 1066 PILOT REPORTED ANTI COLLISION LIGHT INOP. FLASH TUBE FOUND BURNED AND CRACKED. REPLACEMENT TUBE ORDERED AND INSTALLED. OPS CHECKED OK. 1 G 7 2 3U NC R0001RD 2001092400108 20010924 00108 WP 2001 9 24 IVSA075461 1 20010831 G 6310 D2761 ACTUATOR ROBSIN R44 R44 7640120 WP CLUTCH DEFECTIVE H IVSA O OTHER O OTHER NR NOT REPORTED 1 FS 01 UNK 76 1031 MOTOR FAILED TO OPERATE WHEN CALLED ON TO ENGAGE M/R DRIVE BELTS. WOULD NOT OPERATE IN EITHER DIRECTION. MOTOR REPLACED , DEFECTIVE MOTOR RETURNED TOROBINSON FOR WARRANTY CREDIT. 1 G 7 1 3O H11NM 2001100400091 20011004 00091 WP 2001 10 4 IVSA075920 1 20010924 G 6320 D2761 ACTUATOR ROBSIN R44 R44 7640120 WP CLUTCH FAILED H IVSA O OTHER O OTHER NR NOT REPORTED 1 FS 01 7189C 176 1031 CLUTCH ACTUATOR MOTOR FAILED FOR THE 2ND TIME. REPLACEMENT MOTOR INSTALLED. FURTHER TOUBLESHOOTING REVEALED SHEAVE ALI GNMENT OUT OF LIMITS CAUSING INFLIGHT ILLUMINATION OF CLUTCH LIGHT. ALIGNMENT CORRECTED AND FLIGHTS CONTINUED NORMALLY. BAD MOTOR RETURNED FOR WARRANTY CREDIT. 1 G 7 1 3O H11NM 2002011000162 20020110 00162 EU 2002 1 10 IVSA076105 1 20011003 G 6210 355A11002009 BLADE AEROSP AS355 AS355* EU MAIN ROTOR CRACKED H IVSA K NONE O OTHER IN INSP/MAINT 1 FS 01 335FP 4892 5456 BLADE REMOVED FOR REPAIR OF LEADING EDGE ABRASION STRIP CRACKS. CUSTOMER REQUESTED EXCHANGE BLADE IN ORDER TO RESUME FL IGHTS. EXCHANGE BLADE INSTALLED, REPAIRABLE BLADE RETURNED TO AEC 1 G 7 2 3U H11EU 2002012300136 20020123 00136 WP 2002 1 23 IVSA077371 1 20011212 G 6300 D1742 WHEEL ROBSIN R44 R44 7640120 WP CENTER HUB CORRODED H IVSA K NONE O OTHER IN INSP/MAINT 1 FS 01 7186Z 190 737C PAINT ON FAN WHEEL LOOSE AND FLAKING OFF DUE TO POOR ADHESION, PROBABLY CAUSED BY IMPROPER PREPARATION, ALLOWING PREMATU RE CORROSION. 1 G 7 1 3O H11NM 2001092400111 20010924 00111 SW 2001 9 24 JJWA073276 1 20010612 G 6320 206040236017 HOUSING BELL 206 206B 1181511 SW GEARBOX STRIPPED H JJWA K NONE O OTHER IN INSP/MAINT 1 FS 01 5005N 8864 1931 STUD PULLED OUT WITH LESS THAN 50 INCH POUND ON TORQUE WRENCH WHEN INSTALLING FW UNIT IN ENGINE - HIDDEN DAMAGE NOT FOU ND BY BELL CSF OVERHAUL FACILITY. NEW HOUSING SENT BY CSF. 1 G 7 1 3U H2SW 2002012400001 20020124 00001 SW 2002 1 24 JJWA077061 1 20011105 G 6710 206062721113 ACTUATOR BELL 206 206B 1181511 SW MAIN ROTOR CORRODED H JJWA K NONE O OTHER IN INSP/MAINT 1 FS 01 281CB 3303 ACTUATOR FAILED AFTER FEBRUARY 2001 OVERHAUL. NO ALODINE OR OTHER CORROSION PROTECTION ON INSIDE OF CASE.INTERNAL CORROS ION CAUSED FAILURE. 1 G 7 1 3U H2SW 2001121100136 20011211 00136 NE 2001 12 11 JV652J 2 20010828 G 7250 UL36199 CASE RROYCE RB211 RB211535E4 54555 NE ENGINE CRACKED D K NONE O OTHER IN INSP/MAINT 1 SW 07 21825 ESN31340 CASE ASSEMBLY EXHIBITED 2 AXIAL CRACKS APPROXIMATELY 2.0 INCHES IN LENGTH AND 3.5 TO 4 INCHES APART. CRACKS PROPAGATED THROUGH THE CASE WALL. CASE HAD 7277 TOTAL CYCLE. 4 F E12EU 2001040500110 20010405 00110 EU 2001 4 5 KBMA88583 1 20010205 G 6520 350A33215300 LAMINATED HINGE SNIAS 350 AS350BA 8680817 EU TAIL ROTOR DELAMINATED E KBMA K NONE O OTHER IN INSP/MAINT 1 WP 19 1188P 9755 2347 HINGE DELAMINATED 1 G 7 1 3U NC H9EU 2001030700630 20010307 00630 EU 2001 3 7 KBMA88585 1 20010127 G 6720 350A33214501 BUSHING SNIAS 350 AS350B2 8680813 EU TMECA ARRIEL ARRIEL1 60030 NE T/R ROD BEARING CRACKED I KBMA K NONE O OTHER IN INSP/MAINT 1 WP 19 115SH 2136 3141 BUSHING CRACKED 1 G 7 1 3U 3 U H9EU E19EU 2001030700633 20010307 00633 EU 2001 3 7 KBMA88634 1 20010127 G 5320 350A54112420 BRACKET SNIAS 350 AS350B2 8680813 EU TMECA ARRIEL ARRIEL1 60030 NE STARTER GEN CRACKED E KBMA K NONE O OTHER IN INSP/MAINT 1 WP 19 115SH 2136 3141 STARTER GENTERATOR AIR VENT DUCT BRACKET IS CRACKED. 1 G 7 1 3U 3 U H9EU E19EU 2001030700631 20010307 00631 EU 2001 3 7 KBMA88637 1 20010201 G 7714 0177555170 CONTROL BOX SNIAS 350 AS350BA 8680817 EU TMECA ARRIEL ARRIEL1 60030 NE TACH GEN MALFUNCTIONED E KBMA K NONE O OTHER IN INSP/MAINT 1 WP 19 350SH 4435 2957 TACH BOX CLOSES BLEED VALVE AT 96% AND OPENS AT 95% 1 G 7 1 3U 3 U NC H9EU E19EU 2001030700629 20010307 00629 EU 2001 3 7 KBMA88638 1 20010127 G 5320 TL100AXE12L50DK LATCH SNIAS 350 AS350BA 8680817 EU TMECA ARRIEL ARRIEL1 60030 NE FUSELAGE STUCK I KBMA O OTHER O OTHER NR NOT REPORTED 1 WP 19 180EH 3439 2337 LATCH WAS STICKING. 1 G 7 1 3U 3 U NC H9EU E19EU 2001030700621 20010307 00621 EU 2001 3 7 KBMA88639 1 20010130 G 2915 12TW13 SWITCH SNIAS 350 AS350B 8680801 EU TMECA ARRIEL ARRIEL1 60030 NE HYDRAULIC SYSTEM INOPERATIVE E KBMA K NONE O OTHER IN INSP/MAINT 1 WP 19 37SH 9207 2300 HYDRAULIC SWITCH WAS FAULTY. 1 G 7 1 3U 3 U H9EU E19EU 2001040500100 20010405 00100 EU 2001 4 5 KBMA88643 1 20010215 G 7110 350A58154322 HINGE PIN SNIAS 350 AS350B2 8680813 EU TMECA ARRIEL ARRIEL1 60030 NE ENG COWLING BROKEN E KBMA K NONE O OTHER IN INSP/MAINT 1 WP 19 115SH 2169 3141 COWLING HINGE PIN BROKEN. 1 G 7 1 3U 3 U H9EU E19EU 2001040500124 20010405 00124 EU 2001 4 5 KBMA88645 1 20010217 G 7712 9580113720 TRANSMITTER SNIAS 350 AS350B 8680801 EU TORQUE INDICATOR INOPERATIVE E KBMA K NONE L NO TEST IN INSP/MAINT 1 WP 19 37SH 9250 2300 TORQUE GUAGE NOT WORKING PROPERLY. 1 G 7 1 3U H9EU 2001040500105 20010405 00105 2001 4 5 KBMA88646 4 20010218 G 2312 064105430 VHF COMM SNIAS 350 AS350BA 8680817 EU TMECA ARRIEL ARRIEL1 60030 NE COCKPIT INOPERATIVE E KBMA K NONE L NO TEST IN INSP/MAINT 1 WP 19 350SH 4474 2957 VHF INOPERATIVE, COMES ON ONLY WHEN VOLUME IS ALL THE WAY DOWN. 1 G 7 1 3U 3 U NC H9EU E19EU 2001040500106 20010405 00106 2001 4 5 KBMA88649 4 20010220 G 2312 064010540030 VHF COMM SNIAS 350 AS350BA 8680817 EU TMECA ARRIEL ARRIEL1 60030 NE COCKPIT MALFUNCTIONED E KBMA K NONE L NO TEST IN INSP/MAINT 1 WP 19 1188P 9792 2347 VHF HAS CONSTANT SQUELCH ON AFTER APPROX 30 MINUTES OF OPERATION. WILL NOT RESET. 1 G 7 1 3U 3 U NC H9EU E19EU 2001040500109 20010405 00109 GL 2001 4 5 KBMA88679 2 20010227 G 7310 7G547 PRESSURE SWITCH BELL 206 206B 1181511 SW ALLSN 250C 250C20 03013 GL FUEL SYSTEM MALFUNCTIONED E KBMA K NONE J WARNING INDICATION IN INSP/MAINT 1 WP 19 667JM 9830 3444 FUEL PRESSURE SWITCHES NOT OPERATING PROPERLY. CAUTION LITE REMAINS ON WITH CIRCUIT BREAKER IN. 1 G 7 1 3U 3 U H2SW E4CE 2001050300002 20010503 00002 NE 2001 5 3 KBMA88694 2 20010320 G 7210 9560134100 MAGNETIC SEAL SNIAS 350 AS350BA 8680817 EU TMECA ARRIEL ARRIEL1 60030 NE ENGINE LEAKING B KBMA K NONE K FLUID LOSS IN INSP/MAINT 1 WP 19 230SH 3523 2337 ENGINE FRONT MAG SEAL LEAKING. 1 G 7 1 3U 3 U NC H9EU E19EU 2001050300004 20010503 00004 EU 2001 5 3 KBMA88695 1 20010320 G 6420 350A33215300 BEARING SNIAS 350 AS350BA 8680817 EU TMECA ARRIEL ARRIEL1 60030 NE TAIL ROTOR WORN B KBMA K NONE O OTHER IN INSP/MAINT 1 WP 19 230SH 3523 2337 TAIL ROTOR TETTER BEARINGS WORN. 1 G 7 1 3U 3 U NC H9EU E19EU 2001050300020 20010503 00020 EU 2001 5 3 KBMA88698 1 20010320 G 6220 BUSHING SNIAS 350 AS350BA 8680817 EU TMECA ARRIEL ARRIEL1 60030 NE MAIN ROTOR DEBONDED B KBMA K NONE O OTHER IN INSP/MAINT 1 WP 19 230SH 3523 2337 REBONDED BUSHING. DUE TO STATIONARY SCISSORS BUSHING DEBONDED. 1 G 7 1 3U 3 U NC H9EU E19EU 2001041700018 20010417 00018 NE 2001 4 17 KBMA88699 2 20010320 G 7414 9560137520 MAGNETO SNIAS 350 AS350BA 8680817 EU TMECA ARRIEL ARRIEL1 60030 NE RIGHT LEAKING C KBMA K NONE O OTHER IN INSP/MAINT 1 WP 19 230SH 3523 2337 REAR ENGINE MAGNETO SEAL LEAKING. 1 G 7 1 3U 3 U NC H9EU E19EU 2001050300022 20010503 00022 EU 2001 5 3 KBMA88700 1 20010320 G 2435 9560134100 MAGNETIC SEAL SNIAS 350 AS350BA 8680817 EU TMECA ARRIEL ARRIEL1 60030 NE ENGINE LEAKING B KBMA K NONE K FLUID LOSS IN INSP/MAINT 1 WP 19 230SH 3523 2337 STARTER GENERATOR MAGNETIC SEAL LEAKING. REMOVED AND REPLACED SEAL. 1 G 7 1 3U 3 U NC H9EU E19EU 2001041700020 20010417 00020 2001 4 17 KBMA88706 4 20010317 G 3422 5050031904 GYRO SNIAS 350 AS350B2 8680813 EU TMECA ARRIEL ARRIEL1 60030 NE COCKPIT PRECESSES C KBMA K NONE O OTHER IN INSP/MAINT 1 WP 19 345SH 69 3345 DIRECTIONAL GYRO RAPIDLY PRESSESSING. GYRO HAD APPROX. 10 HOURS ON UNIT. 1 G 7 1 3U 3 U H9EU E19EU 2001041700017 20010417 00017 EU 2001 4 17 KBMA88707 1 20010318 G 6710 SC5083 SERVO SNIAS 350 AS350B2 8680813 EU TMECA ARRIEL ARRIEL1 60030 NE MAIN ROTOR LEAKING C KBMA K NONE K FLUID LOSS IN INSP/MAINT 1 WP 19 115SH 2268 3141 LEAKING FROM WEEPHOLE. 1 G 7 1 3U 3 U H9EU E19EU 2001041700023 20010417 00023 EU 2001 4 17 KBMA88709 1 20010318 G 7712 9580113720 TRANSMITTER SNIAS 350 AS350BA 8680817 EU TMECA ARRIEL ARRIEL1 60030 NE ENGINE TORQUE MALFUNCTIONED C KBMA K NONE O OTHER IN INSP/MAINT 1 WP 19 270SH 7577 1864 NEEDLE MOVES TO UPPER LIMIT OF SCALE AND STOPS THERE FOR A COUPLE OF MINUTES. 1 G 7 1 3U 3 U NC H9EU E19EU 2001041700021 20010417 00021 NE 2001 4 17 KBMA88711 2 20010323 G 7412 955016870 IGNITER SNIAS 350 AS350BA 8680817 EU TMECA ARRIEL ARRIEL1 60030 NE RIGHT INTERMITTENT C KBMA K NONE O OTHER IN INSP/MAINT 1 WP 19 270SH 7599 1864 RIGHT IGNITER INTERMITTENT. 1 G 7 1 3U 3 U NC H9EU E19EU 2001041700019 20010417 00019 EU 2001 4 17 KBMA88712 1 20010311 G 7410 HE402F IGNITER BOX SNIAS 350 AS350BA 8680817 EU TMECA ARRIEL ARRIEL1 60030 NE RIGHT INOPERATIVE C KBMA K NONE O OTHER IN INSP/MAINT 1 WP 19 1188P 9846 2347 RIGHT IGNITOR IS INOPERATIVE. 1 G 7 1 3U 3 U NC H9EU E19EU 2001041700022 20010417 00022 NE 2001 4 17 KBMA88713 2 20010312 G 7230 420800003 FAN SNIAS 350 AS350B2 8680813 EU TMECA ARRIEL ARRIEL1 60030 NE ENGINE CHAFED C KBMA K NONE O OTHER IN INSP/MAINT 1 WP 19 53SH 4998 2009 FAN BLADES HITTING HOUSING. ADJUSTED BLADES. OPS CHECKED GOOD. 1 G 7 1 3U 3 U H9EU E19EU 2001052900040 20010529 00040 EU 2001 5 29 KBMA88728 1 20010418 G 5553 22201BC060016L BOLT SNIAS 350 AS350BA 8680817 EU VERTICAL STAB SHEARED E KBMA K NONE O OTHER NR NOT REPORTED 1 WP 19 270SH 7704 1864 BOLTS SHEARED, INSTALLED NEW BOLTS AS REQUIRED. 1 G 7 1 3U NC H9EU 2001040500108 20010405 00108 2001 4 5 KBMA88818 4 20010208 G 3421 5040017901 GYRO SNIAS 350 AS350BA 8680817 EU TMECA ARRIEL ARRIEL1 60030 NE COCKPIT INOPERATIVE E KBMA K NONE O OTHER IN INSP/MAINT 1 WP 19 270SH 7475 1864 PRECESSING AND FLAG INDICATOR INOPERATIVE. 1 G 7 1 3U 3 U NC H9EU E19EU 2001040500107 20010405 00107 2001 4 5 KBMA88819 4 20010208 G 3422 200DCL GYRO SNIAS 350 AS350BA 8680817 EU TMECA ARRIEL ARRIEL1 60030 NE COCKPIT MALFUNCTIONED E KBMA K NONE O OTHER IN INSP/MAINT 1 WP 19 270SH 7475 1864 DIRECTIONAL GYRO MAKES EXCESSIVE NOISE. 1 G 7 1 3U 3 U NC H9EU E19EU 2001040500125 20010405 00125 EU 2001 4 5 KBMA99419 1 20010109 G 6520 350A33215001 BEARING SNIAS 350 AS350BA 8680817 EU TAIL ROTOR WORN E KBMA K NONE O OTHER IN INSP/MAINT 1 WP 19 350SH 4396 2957 BEARING WORN. 1 G 7 1 3U NC H9EU 2001100400138 20011004 00138 EU 2001 10 4 KUVA075921 1 20010928 G 6420 109013105111 PIVOT AGUSTA A109 A109A2 0260120 EU TAIL ROTOR WORN H KUVA K NONE O OTHER IN INSP/MAINT 1 FS 01 584RH 2361 7356 T/R TURNNION P/N 109-0131-05-111 TT: 2360.8. THE TRUNNION SHOWED SIGNIFIGANT WEAR AT DISSASSEMBLY AFTER THE PILOT NOTED A HIGH FREQUENCY VIBRATION. THE AGUSTA T/R ASSY IS SUBJECT TO BECOMING STIFF, WHEN THIS OCCURS THE T/R HUB SHOULD BE COM PLETELY DISSASSEMBLED AND INSPECTED FOR WEAR. I WOULD SUGGEST AGUSTA INSTITUTE A SCHEDULED INSPECTION PRIOR TO THE 2400 HR. INSPECTION THAT IS NOW IN PLACE. 1 G 7 2 3U H7EU 2001100400140 20011004 00140 EU 2001 10 4 KUVA075922 1 20010928 G 6420 109013105111 PIVOT AGUSTA A109 A109 0260109 EU TAIL ROTOR WORN H KUVA K NONE O OTHER IN INSP/MAINT 1 FS 01 584RH 2361 7356 T/R TURNNION P/N 109-0131-05-111 TT: 2360.8. THE TRUNNION SHOWED SIGNIFIGANT WEAR AT DISSASSEMBLY AFTER THE PILOT NOTED A HIGH FREQUENCY VIBRATION. THE AGUSTA T/R ASSY IS SUBJECT TO BECOMING STIFF, WHEN THIS OCCURS THE T/R HUB SHOULD BE COM PLETELY DISSASSEMBLED AND INSPECTED FOR WEAR. I WOULD SUGGEST AGUSTA INSTITUTE A SCHEDULED INSPECTION PRIOR TO THE 2400 HR. INSPECTION THAT IS NOW IN PLACE. 1 G 7 2 3U H7EU 2002012400002 20020124 00002 GL 2002 1 24 KUVA076138 2 20011010 G 7230 6890483 BEARING RACE 6890550 AGUSTA A109 A109A2 0260120 EU ALLSN 250C 250C20B 03013 GL COMPRESSOR CHAFED H KUVA K NONE O OTHER IN INSP/MAINT 1 FS 01 168BH CAC6026 7256 CAC6026 BEARING P/N 23034787 S/N MP78657 CHAFFED RACE P/N 6890483 S/N MP119218 CAUSING BOTH PARTS TO SCRAP. 1 G 7 2 3U 3 U H7EU E4CE 2001041900222 20010419 00222 SW 2001 4 19 LS1R071905 1 20010404 G 7921 8538312 COOLER BELL 206 206B3 1181506 SW TRANSMISSION CONTAMINATED E LS1R O OTHER O OTHER NR NOT REPORTED 1 EA 13 206BY 2871 PART HAS TRANSMISSION CHIPS. 1 G 7 1 3U H2SW 2001041900223 20010419 00223 WP 2001 4 19 LS1R071906 1 20010404 G 3340 6014313 POWER SUPPLY HUGHES 369 369D 4470706 WP STROBE FAILED E LS1R O OTHER O OTHER NR NOT REPORTED 1 EA 13 369AW 470117D PART WILL NOT FLASH. 1 G 7 1 3U H3WE 2001041900224 20010419 00224 WP 2001 4 19 LS1R071907 1 20010404 G 7810 369A8230504 EXHAUST STACK HUGHES 369 369D 4470706 WP ENGINE CRACKED E LS1R O OTHER O OTHER NR NOT REPORTED 1 EA 13 1097J 900801D PART IS CRACKED. 1 G 7 1 3U H3WE 2001041900225 20010419 00225 WP 2001 4 19 LS1R071908 1 20010404 G 3211 369H6006 BRACE HUGHES 369 369D 4470706 WP MLG WORN E LS1R O OTHER O OTHER NR NOT REPORTED 1 EA 13 369AW 470117D PART IS WORN EXCESSIVELY. 1 G 7 1 3U H3WE 2001041900226 20010419 00226 WP 2001 4 19 LS1R071909 1 20010404 G 3211 369H6006 BRACE HUGHES 369 369D 4470706 WP MLG WORN E LS1R O OTHER O OTHER NR NOT REPORTED 1 EA 13 369AW 470117D PART IS WORN EXCESSIVELY. 1 G 7 1 3U H3WE 2001041900227 20010419 00227 WP 2001 4 19 LS1R071910 1 20010404 G 3211 369H6006 BRACE HUGHES 369 369D 4470706 WP MLG CRACKED E LS1R O OTHER O OTHER NR NOT REPORTED 1 EA 13 369AW 470117D PART IS CRACKED. 1 G 7 1 3U H3WE 2001041900228 20010419 00228 WP 2001 4 19 LS1R071911 1 20010404 G 2821 369A8116 FUEL FILTER HUGHES 369 369D 4470706 WP ENGINE BROKEN E LS1R O OTHER O OTHER NR NOT REPORTED 1 EA 13 369AW 470117D PART IS BROKEN. 1 G 7 1 3U H3WE 2001041900229 20010419 00229 GL 2001 4 19 LS1R071914 2 20010404 G 7210 810151 MAGNETIC SEAL BELL 206 206B3 1181506 SW ALLSN 250C 250C20B 03013 GL ENGINE LEAKING E LS1R O OTHER K FLUID LOSS NR NOT REPORTED 1 EA 13 206BX 2872 PART IS LEAKING. 1 G 7 1 3U 3 U H2SW E4CE 2001041900230 20010419 00230 GL 2001 4 19 LS1R071915 2 20010404 G 7210 6894171 GEARBOX HUGHES 369 369D 4470706 WP ALLSN 250C 250C20B 03013 GL ENGINE LEAKING E LS1R O OTHER K FLUID LOSS NR NOT REPORTED 1 EA 13 5211R 1161D PART IS LEAKING. 1 G 7 1 3U 3 U H3WE E4CE 2001041900231 20010419 00231 SW 2001 4 19 LS1R071916 1 20010406 G 6510 204040602005 SHAFT BELL 204 UH1H 1181407 SW TAIL ROTOR WORN E LS1R O OTHER O OTHER NR NOT REPORTED 1 EA 13 53AG 7221588 PART IS WORN EXCESSIVELY. 1 G 7 1 4U EXPA1G71 2001041900232 20010419 00232 SW 2001 4 19 LS1R071917 1 20010406 G 6510 204040602005 SHAFT BELL 204 UH1H 1181407 SW TAIL ROTOR WORN E LS1R O OTHER O OTHER NR NOT REPORTED 1 EA 13 53AG 7221588 PART IS WORN EXCESSIVELY. 1 G 7 1 4U EXPA1G71 2001041900233 20010419 00233 SW 2001 4 19 LS1R071918 1 20010406 G 7930 206011721009 BEARING BELL 206 206B3 1181506 SW INDICATOR LOOSE E LS1R O OTHER O OTHER NR NOT REPORTED 1 EA 13 90322 1736 PART IS LOOSE BEARINGS. 1 G 7 1 3U H2SW 2001041900234 20010419 00234 GL 2001 4 19 LS1R071919 2 20010406 G 7314 369A81433 PUMP HUGHES 369 369E 4470707 WP ALLSN 250C 250C20B 03013 GL FUEL SYSTEM NOISY E LS1R O OTHER E VIBRATION/BUFFET NR NOT REPORTED 1 EA 13 765KV 0082E PART IS NOISY. 1 G 7 1 3U 3 U H3WE E4CE 2001041900235 20010419 00235 SW 2001 4 19 LS1R071920 1 20010406 G 6320 206031509001 DRAG PIN BELL 206 206B3 1181506 SW M/R GEARBOX WORN E LS1R O OTHER O OTHER NR NOT REPORTED 1 EA 13 90322 1736 PART IS WORN EXCESSIVELY. 1 G 7 1 3U H2SW 2001041900236 20010419 00236 SW 2001 4 19 LS1R071921 1 20010406 G 5522 206070178012 SKIN BELL 206 206B3 1181506 SW ELEVATOR DAMAGED E LS1R O OTHER O OTHER NR NOT REPORTED 1 EA 13 9907K 2040 PART HAS A HOLE. 1 G 7 1 3U H2SW 2001041900194 20010419 00194 WP 2001 4 19 LS1R072189 1 20010410 G 7714 369A45167 TACHOMETER HUGHES 369 369E 4470707 WP COCKPIT INACCURATE E LS1R O OTHER O OTHER NR NOT REPORTED 1 EA 13 8330P 105 0330E TACHOMETER IS INACCURATE. 1 G 7 1 3U H3WE 2003080700113 20030807 00113 SW 2003 8 7 LS1R072190 1 20010410 G 2700 205001706009 CABLE DRUM BELL 204 UH1H 1181407 SW FLT CONTROLS STRETCHED E LS1R O OTHER O OTHER NR NOT REPORTED 1 EA 13 51AG 7120178 CABLE DRUM STRETCHED. 1 G 7 1 4U EXPA1G71 2001050700552 20010507 00552 SW 2001 5 7 LS1R072589 1 20010416 G 6300 206030539101 MOUNT BELL 206 206B3 1181506 SW INPUT DRIVE WORN E LS1R K NONE O OTHER IN INSP/MAINT 1 EA 13 90322 8439 1736 PART IS WORN EXCESSIVELY. 1 G 7 1 3U H2SW 2001050700553 20010507 00553 SW 2001 5 7 LS1R072590 1 20010416 G 3310 20407570545 CONTROL PANEL BELL 204 UH1H 1181407 SW COCKPIT LIGHTS INOPERATIVE E LS1R K NONE L NO TEST IN INSP/MAINT 1 EA 13 53AG 4790 7221588 LIGHTS WILL NOT COME ON. CONTROL PANEL INOPERATIVE. 1 G 7 1 4U EXPA1G71 2001050700554 20010507 00554 2001 5 7 LS1R072591 4 20010416 G 3457 66000201 GPS BELL 206 OH58A 1181579 SW COCKPIT INOPERATIVE E LS1R K NONE O OTHER IN INSP/MAINT 1 EA 13 54AG 221 7120721 GPS WILL NOT RECIEVE. 1 G 7 1 3U H2SW 2001050700555 20010507 00555 SW 2001 5 7 LS1R072592 1 20010416 G 2424 07639CSV1152 REGULATOR BELL 204 UH1H 1181407 SW ELECTRICAL OUT OF ADJ E LS1R K NONE L NO TEST IN INSP/MAINT 1 EA 13 53AG 7221588 REGULATOR UNABLE TO HOLD ADJUSTMENT. 1 G 7 1 4U EXPA1G71 2001050700563 20010507 00563 SW 2001 5 7 LS1R072735 1 20010419 G 7714 32005023 TACH GENERATOR BELL 206 206B3 1181506 SW ENGINE INOPERATIVE E LS1R O OTHER O OTHER NR NOT REPORTED 1 EA 13 206BX 2872 PART IS BROKEN. 1 G 7 1 3U H2SW 2001050800201 20010508 00201 SW 2001 5 8 LS1R072736 1 20010419 G 2740 205001505001 BEARING BELL 212 212 1181420 SW BELLCRANK LOOSE E LS1R K NONE O OTHER IN INSP/MAINT 1 EA 13 8530F 30920 BELLCRANK HAS LOOSE BEARINGS. 1 G 7 1 4U H4SW 2001050700564 20010507 00564 SW 2001 5 7 LS1R072737 1 20010419 G 7714 212070108007 INDICATOR BELL 212 212 1181420 SW TRIPLE TACH INTERMITTENT E LS1R K NONE O OTHER IN INSP/MAINT 1 EA 13 8530F 1241 30920 PART IS INTERMITTENT. 1 G 7 1 4U H4SW 2001050700565 20010507 00565 WP 2001 5 7 LS1R072738 1 20010419 G 2740 369A717011 MOTOR HUGHES 369 369D 4470706 WP LATERAL TRIM MALFUNCTIONED E LS1R K NONE O OTHER IN INSP/MAINT 1 EA 13 500DC 4014 290456D PART IS SLOW. 1 G 7 1 3U H3WE 2001050700566 20010507 00566 SW 2001 5 7 LS1R072739 1 20010425 G 7603 206062721113 BEARING BELL 206 206B3 1181506 SW ACTUATOR LOOSE E LS1R O OTHER O OTHER NR NOT REPORTED 1 EA 13 206BY 318 2871 PART HAS LOOSE BEARINGS. 1 G 7 1 3U H2SW 2001050700567 20010507 00567 SW 2001 5 7 LS1R072740 1 20010426 G 2822 1C381 PUMP BELL 206 206B3 1181506 SW FUEL BOOST INOPERATIVE E LS1R O OTHER O OTHER NR NOT REPORTED 1 EA 13 9907K 563 2040 PART IS INOPERATIVE. 1 G 7 1 3U H2SW 2001050700568 20010507 00568 WP 2001 5 7 LS1R072741 1 20010427 G 7810 369A8230503 EXHAUST PIPE HUGHES 369 369D 4470706 WP ENGINE CRACKED E LS1R K NONE O OTHER IN INSP/MAINT 1 EA 13 5211R 529 1161D PART IS CRACKED. 1 G 7 1 3U H3WE 2001050700569 20010507 00569 WP 2001 5 7 LS1R072742 1 20010427 G 2740 369A7010 LOCK HUGHES 369 369E 4470707 WP STAB DAMAGED E LS1R O OTHER O OTHER NR NOT REPORTED 1 EA 13 765KV 0082E PART HAS FEED BACK. 1 G 7 1 3U H3WE 2001051500435 20010515 00435 2001 5 15 LS1R072915 4 20010509 G 2300 069102100 RADIO HUGHES 369 369D 4470706 WP COCKPIT WEAK E LS1R O OTHER O OTHER NR NOT REPORTED 1 EA 13 1097J 900801D RADIO IS WEAK. 1 G 7 1 3U H3WE 2001051500436 20010515 00436 WP 2001 5 15 LS1R072916 1 20010509 G 7714 369H4551 TACH GENERATOR HUGHES 369 369D 4470706 WP ENGINE SHEARED E LS1R O OTHER O OTHER NR NOT REPORTED 1 EA 13 1097J 900801D TACH GEN IS SHEARED. 1 G 7 1 3U H3WE 2001051500437 20010515 00437 2001 5 15 LS1R072917 4 20010509 G 2300 TFM1380 CONTROL UNIT HUGHES 369 369D 4470706 WP RADIO INOPERATIVE E LS1R O OTHER O OTHER NR NOT REPORTED 1 EA 13 5211R 1161D RADIO CONTROL INOP. 1 G 7 1 3U H3WE 2001051500438 20010515 00438 WP 2001 5 15 LS1R072918 1 20010509 G 3300 369H64255 CONTROL UNIT HUGHES 369 369D 4470706 WP DIMMER SWITCH INOPERATIVE E LS1R K NONE O OTHER IN INSP/MAINT 1 EA 13 1097J 1461 900801D DIMMER SWITCH CIRCUIT-SHORTED. 1 G 7 1 3U H3WE 2001051500439 20010515 00439 GL 2001 5 15 LS1R072919 2 20010509 G 7412 10614950 EXCITER HUGHES 369 369E 4470707 WP ALLSN 250C 250C20B 03013 GL ENGINE UNSERVICEABLE E LS1R O OTHER O OTHER NR NOT REPORTED 1 EA 13 765KV 952 0082E EXCITER IS UNSERVICEABLE. 1 G 7 1 3U 3 U H3WE E4CE 2001051500440 20010515 00440 WP 2001 5 15 LS1R072920 1 20010509 G 7400 369A45143 EPO ASSY HUGHES 369 369E 4470707 WP COCKPIT MALFUNCTIONED E LS1R O OTHER O OTHER NR NOT REPORTED 1 EA 13 129GA 0052E HAS SOLID TONE. 1 G 7 1 3U H3WE 2001051500441 20010515 00441 2001 5 15 LS1R072921 4 20010509 G 2350 066105570 AUDIO PANEL HUGHES 369 369E 4470707 WP COCKPIT INTERMITTENT E LS1R O OTHER O OTHER NR NOT REPORTED 1 EA 13 129GA 0052E AUDIO PANEL IS INTERMITTENT. 1 G 7 1 3U H3WE 2001072700136 20010727 00136 WP 2001 7 27 LS1R073005 1 20010522 G 2110 6890550 COMPRESSOR HUGHES 369 369E 4470707 WP AIR CONDITIONER DAMAGED E LS1R K NONE O OTHER IN INSP/MAINT 1 EA 13 129GA 1647 0052E COMPRESSOR IS DAMAGED. 1 G 7 1 3U H3WE 2001072700137 20010727 00137 WP 2001 7 27 LS1R073117 1 20010524 G 6420 369D27609501 SWASHPLATE HUGHES 369 369D 4470706 WP TAIL ROTOR LOOSE E LS1R K NONE O OTHER IN INSP/MAINT 1 EA 13 500DC 1006 290456D SWASHPLATE HAS EXCESIVE AXIAL PLAY. 1 G 7 1 3U H3WE 2001072700147 20010727 00147 WP 2001 7 27 LS1R073118 1 20010524 G 6520 369D25400 GEARBOX HUGHES 369 369D 4470706 WP TAIL ROTOR MAKING METAL E LS1R K NONE O OTHER IN INSP/MAINT 1 EA 13 369AW 3154 470117D TAIL ROTOR GEARBOX IS MAKING METAL. 1 G 7 1 3U H3WE 2001072700148 20010727 00148 WP 2001 7 27 LS1R073263 1 20010604 G 7714 369A45167 INDICATOR HUGHES 369 369D 4470706 WP TACHOMETER SHORTED E LS1R O OTHER O OTHER NR NOT REPORTED 1 EA 13 5211R 1479 1161D TACHOMETER IS SHORTED OUT. 1 G 7 1 3U H3WE 2001072700149 20010727 00149 WP 2001 7 27 LS1R073264 1 20010604 G 6700 369A717011 MOTOR HUGHES 369 369D 4470706 WP LATERAL TRIM INTERMITTENT E LS1R K NONE O OTHER IN INSP/MAINT 1 EA 13 1097J 1683 900801D LATERAL TRIM MOTER IS INTERMITTENT. 1 G 7 1 3U H3WE 2001072700150 20010727 00150 2001 7 27 LS1R073265 4 20010604 G 2312 KY195B RADIO HUGHES 369 369D 4470706 WP VHF DISTORTED E LS1R O OTHER O OTHER NR NOT REPORTED 1 EA 13 5027P 2220 611002D VHF RADIO IS DISTORTED. 1 G 7 1 3U H3WE 2001072700154 20010727 00154 WP 2001 7 27 LS1R073266 1 20010604 G 3300 369H6425 SWITCH HUGHES 369 369E 4470707 WP DIMMER CONTROL INOPERATIVE E LS1R K NONE O OTHER IN INSP/MAINT 1 EA 13 8330P 1215 0330E DIMMER CONTROL INOPERATIVE. 1 G 7 1 3U H3WE 2001072700156 20010727 00156 WP 2001 7 27 LS1R073267 1 20010604 G 2436 369A4652 VOLT REGULATOR HUGHES 369 369E 4470707 WP ELECTRICAL INOPERATIVE E LS1R K NONE L NO TEST IN INSP/MAINT 1 EA 13 8330P 1791 0330E VOLTAGE REGULATOR WILL NOT COME ON LINE. 1 G 7 1 3U H3WE 2001072700159 20010727 00159 SW 2001 7 27 LS1R073268 1 20010604 G 7714 SHAFT BELL 206 OH58A 1181579 SW TACH GENERATOR SHEARED E LS1R K NONE L NO TEST IN INSP/MAINT 1 EA 13 58AG 809 13702 7221131 TACH GENERATOR SHAFT IS SHEARED. 1 G 7 1 3U H2SW 2001092400115 20010924 00115 WP 2001 9 24 LS1R073476 1 20010618 G 2822 164A81343 PUMP HUGHES 369 369E 4470707 WP FUEL SYSTEM INOPERATIVE E LS1R K NONE L NO TEST IN INSP/MAINT 1 EA 13 765KV 18 0082E PART IS WILL NOT RUN WHEN POWER A. 1 G 7 1 3U H3WE 2001092400116 20010924 00116 WP 2001 9 24 LS1R073477 1 20010618 G 6720 369D21800501 SEAL HUGHES 369 369D 4470706 WP T/R PITCH CONTRO ROTATED E LS1R K NONE O OTHER IN INSP/MAINT 1 EA 13 5211R 1151 1161D PART IS SEAL ROTATES. 1 G 7 1 3U H3WE 2001092400117 20010924 00117 WP 2001 9 24 LS1R073478 1 20010618 G 6300 204031920003 DAMPER HUGHES 369 369E 4470707 WP MAIN ROTOR WORN E LS1R K NONE O OTHER IN INSP/MAINT 1 EA 13 8330P 0330E PART IS WORN EXCESSIVELY. 1 G 7 1 3U H3WE 2001092400118 20010924 00118 SW 2001 9 24 LS1R073479 1 20010619 G 6700 0710105200 VALVE BELL 212 212 1181420 SW FLIGHT CONTROL BROKEN E LS1R K NONE O OTHER IN INSP/MAINT 1 EA 13 8530F 30920 PART IS BROKEN. 1 G 7 1 4U H4SW 2001092400119 20010924 00119 WP 2001 9 24 LS1R073480 1 20010619 G 2510 369H6525503 SEAT HUGHES 369 369D 4470706 WP COCKPIT CRACKED E LS1R K NONE O OTHER IN INSP/MAINT 1 EA 13 5211R 1161D PART IS CRACKED. 1 G 7 1 3U H3WE 2001092400120 20010924 00120 WP 2001 9 24 LS1R073481 1 20010619 G 2810 369H81013 FUEL CELL HUGHES 369 369D 4470706 WP FUSELAGE LEAKING E LS1R K NONE K FLUID LOSS IN INSP/MAINT 1 EA 13 369AW 470117D PART IS LEAKING. 1 G 7 1 3U H3WE 2001092400121 20010924 00121 WP 2001 9 24 LS1R073482 1 20010619 G 7810 369A8230503 EXHAUST PIPE HUGHES 369 369D 4470706 WP ENGINE CRACKED E LS1R K NONE O OTHER IN INSP/MAINT 1 EA 13 5211R 1161D PART IS CRACKED. 1 G 7 1 3U H3WE 2001092400122 20010924 00122 SW 2001 9 24 LS1R073483 1 20010619 G 6320 206032309536 BEARING BELL 206 OH58A 1181579 SW MAIN ROTOR DAMAGED E LS1R K NONE O OTHER IN INSP/MAINT 1 EA 13 58AG 7221131 PART IS OUT OF RACE. 1 G 7 1 3U H2SW 2001092400123 20010924 00123 SW 2001 9 24 LS1R073484 1 20010619 G 2432 201A GAUGE BELL 206 OH58A 1181579 SW BATTERY MALFUNCTIONED E LS1R K NONE O OTHER IN INSP/MAINT 1 EA 13 58AG 7221131 GAGE PEGS OUT. 1 G 7 1 3U H2SW 2001092400124 20010924 00124 WP 2001 9 24 LS1R073485 1 20010619 G 6300 369D21400503 DAMPER HUGHES 369 369D 4470706 WP MAIN ROTOR STRETCHED E LS1R K NONE O OTHER IN INSP/MAINT 1 EA 13 500DC 290456D PART IS STRETCHED. 1 G 7 1 3U H3WE 2001092400126 20010924 00126 WP 2001 9 24 LS1R073486 1 20010619 G 6230 369D27609501 SWASHPLATE HUGHES 369 369D 4470706 WP MAIN ROTOR LOOSE E LS1R K NONE O OTHER IN INSP/MAINT 1 EA 13 500DC 290456D PART HAS EXCESIVE AXIAL PLAY. 1 G 7 1 3U H3WE 2001092400127 20010924 00127 WP 2001 9 24 LS1R073487 1 20010619 G 6720 369D21800501 BEARING HUGHES 369 369E 4470707 WP T/R ROTOR LOOSE E LS1R K NONE O OTHER IN INSP/MAINT 1 EA 13 129GA 0052E BEARINGS FALL OUT. 1 G 7 1 3U H3WE 2001092400128 20010924 00128 2001 9 24 LS1R073488 4 20010619 G 2300 TFM138B RADIO HUGHES 369 369D 4470706 WP COCKPIT STUCK E LS1R K NONE O OTHER IN INSP/MAINT 1 EA 13 5027P 611002D PART IS STICKING. 1 G 7 1 3U H3WE 2001092400130 20010924 00130 SW 2001 9 24 LS1R074916 1 20010720 G 2432 AG380E4440 BATTERY BELL 204 UH1H 1181407 SW MAIN BATTERY WEAK E LS1R K NONE L NO TEST IN INSP/MAINT 1 EA 13 51AG 7120178 PART IS WEAK. 1 G 7 1 4U EXPA1G71 2001092400131 20010924 00131 SW 2001 9 24 LS1R074917 1 20010720 G 2432 G641E BATTERY BELL 206 206B3 1181506 SW MAIN BATTERY DISCHARGED E LS1R K NONE O OTHER IN INSP/MAINT 1 EA 13 9907K 2040 PART IS BAD CELLS. 1 G 7 1 3U H2SW 2001092400132 20010924 00132 WP 2001 9 24 LS1R074918 1 20010720 G 6510 369D2172121 BEARING HUGHES 369 369E 4470707 WP T/R LINK LOOSE E LS1R K NONE O OTHER IN INSP/MAINT 1 EA 13 765KV 0082E BEARINGS FALL OUT. 1 G 7 1 3U H3WE 2001092400134 20010924 00134 WP 2001 9 24 LS1R074919 1 20010720 G 6400 369D2172313 LINK HUGHES 369 369D 4470706 WP TAIL ROTOR WORN E LS1R K NONE O OTHER IN INSP/MAINT 1 EA 13 5027P 611002D PART IS WORN EXCESSIVELY. 1 G 7 1 3U H3WE 2001092400136 20010924 00136 WP 2001 9 24 LS1R074920 1 20010720 G 6400 369D2172313 LINK HUGHES 369 369D 4470706 WP TAIL ROTOR WORN E LS1R K NONE O OTHER IN INSP/MAINT 1 EA 13 5027P 611002D PART IS WORN EXCESSIVELY. 1 G 7 1 3U H3WE 2001092400138 20010924 00138 WP 2001 9 24 LS1R074921 1 20010720 G 7332 369H81443 PRESSURE SWITCH HUGHES 369 369E 4470707 WP FUEL SYSTEM MALFUNCTIONED E LS1R K NONE O OTHER IN INSP/MAINT 1 EA 13 8330P 0330E COMES IN TO LOW. 1 G 7 1 3U H3WE 2001092400140 20010924 00140 WP 2001 9 24 LS1R074922 1 20010720 G 7714 8DJ150FEA INDICATOR HUGHES 369 369D 4470706 WP COCKPIT UNSERVICEABLE E LS1R K NONE O OTHER IN INSP/MAINT 1 EA 13 5211R 1161D PART IS UNREADABLE AND UNSERVICEABLE. 1 G 7 1 3U H3WE 2001092400141 20010924 00141 WP 2001 9 24 LS1R074923 1 20010720 G 7810 369A8230503 EXHAUST PIPE HUGHES 369 369E 4470707 WP ENGINE CRACKED E LS1R K NONE O OTHER IN INSP/MAINT 1 EA 13 765KV 457 0082E PART IS CRACKED. 1 G 7 1 3U H3WE 2001092400142 20010924 00142 WP 2001 9 24 LS1R074924 1 20010720 G 7810 369A8230503 EXHAUST PIPE HUGHES 369 369D 4470706 WP ENGINE CRACKED E LS1R K NONE O OTHER IN INSP/MAINT 1 EA 13 5211R 1161D PART IS CRACKED. 1 G 7 1 3U H3WE 2001092400143 20010924 00143 WP 2001 9 24 LS1R074925 1 20010720 G 2432 G641E BATTERY HUGHES 369 369E 4470707 WP MAIN BATTERY OVERHEATED E LS1R K NONE O OTHER IN INSP/MAINT 1 EA 13 8330P 0330E PART OVERHEATED. 1 G 7 1 3U H3WE 2001092400144 20010924 00144 SW 2001 9 24 LS1R074926 1 20010720 G 5320 206031302269 SUPPORT BELL 206 206B3 1181506 SW FUSELAGE CRACKED E LS1R K NONE O OTHER IN INSP/MAINT 1 EA 13 49718 1917 PART IS CRACKED. 1 G 7 1 3U H2SW 2001092400145 20010924 00145 SW 2001 9 24 LS1R074927 1 20010720 G 5320 206031301129 SUPPORT BELL 206 206B3 1181506 SW FUSELAGE CRACKED E LS1R K NONE O OTHER IN INSP/MAINT 1 EA 13 49718 1917 PART IS CRACKED. 1 G 7 1 3U H2SW 2001092400147 20010924 00147 SW 2001 9 24 LS1R074928 1 20010720 G 2730 205001905001 BELLCRANK BELL 212 212 1181420 SW ELEVATOR WORN E LS1R K NONE O OTHER IN INSP/MAINT 1 EA 13 8530B 30702 PART IS WORN EXCESSIVELY. 1 G 7 1 4U H4SW 2001092400148 20010924 00148 WP 2001 9 24 LS1R074929 1 20010720 G 7810 369A8230504 EXHAUST STACK HUGHES 369 369D 4470706 WP ENGINE CRACKED E LS1R K NONE O OTHER IN INSP/MAINT 1 EA 13 500DC 290456D PART IS CRACKED. 1 G 7 1 3U H3WE 2001092400150 20010924 00150 GL 2001 9 24 LS1R074930 2 20010720 G 7320 369A717011 MOTOR HUGHES 369 369D 4470706 WP ALLSN 250C 250C20B 03013 GL LATERAL TRIM NOISY E LS1R K NONE O OTHER IN INSP/MAINT 1 EA 13 5211R 1161D PART IS NOISY. 1 G 7 1 3U 3 U H3WE E4CE 2001092400151 20010924 00151 SW 2001 9 24 LS1R074931 1 20010720 G 2810 20601675001 FUEL CELL BELL 206 206B3 1181506 SW FUSELAGE LEAKING E LS1R K NONE O OTHER IN INSP/MAINT 1 EA 13 49718 1917 PART IS LEAKING. 1 G 7 1 3U H2SW 2001092400153 20010924 00153 SW 2001 9 24 LS1R074932 1 20010720 G 2910 205076099007 CYLINDER BELL 204 UH1H 1181407 SW HYD SYSTEM WORN E LS1R K NONE O OTHER IN INSP/MAINT 1 EA 13 53AG 7221588 PART IS WORN EXCESSIVELY. 1 G 7 1 4U EXPA1G71 2001092400155 20010924 00155 SW 2001 9 24 LS1R074934 1 20010803 G 5320 2060313291 FITTING BELL 206 206B3 1181506 SW FUSELAGE CRACKED E LS1R K NONE O OTHER IN INSP/MAINT 1 EA 13 206BX 2872 PART IS CRACKED. 1 G 7 1 3U H2SW 2001092400157 20010924 00157 SW 2001 9 24 LS1R074935 1 20010813 G 6321 204001376003 BRAKE BELL 206 OH58A 1181579 SW MAIN ROTOR STUCK E LS1R K NONE O OTHER IN INSP/MAINT 1 EA 13 58AG 1360 7221131 PART MOVEMENT RESTRICTED. 1 G 7 1 3U H2SW 2001092400159 20010924 00159 WP 2001 9 24 LS1R074936 1 20010813 G 8000 IC34 BRUSHES HUGHES 369 369E 4470707 WP STARTER FAILED E LS1R K NONE O OTHER IN INSP/MAINT 1 EA 13 8330P 0330E PART IS BAD BRUSHES. 1 G 7 1 3U H3WE 2001092400160 20010924 00160 WP 2001 9 24 LS1R074937 1 20010813 G 2810 164A134 FUEL CELL HUGHES 369 369D 4470706 WP FUSELAGE INOPERATIVE E LS1R K NONE O OTHER IN INSP/MAINT 1 EA 13 1097J 900801D NO POWER. 1 G 7 1 3U H3WE 2001092400162 20010924 00162 WP 2001 9 24 LS1R074938 1 20010813 G 2821 369H8102 HOSE HUGHES 369 369E 4470707 WP FUEL SYSTEM DIRTY E LS1R K NONE O OTHER IN INSP/MAINT 1 EA 13 8330P 0330E DIRT IN FUEL FILTER. 1 G 7 1 3U H3WE 2001092400163 20010924 00163 WP 2001 9 24 LS1R074939 1 20010813 G 2822 IC34 PUMP HUGHES 369 369E 4470707 WP FUEL SYSTEM INOPERATIVE E LS1R K NONE O OTHER IN INSP/MAINT 1 EA 13 8330P 0330E PART WILL NOT OPERATE. 1 G 7 1 3U H3WE 2001092400168 20010924 00168 WP 2001 9 24 LS1R074940 1 20010813 G 7400 369A45143 EPO ASSY HUGHES 369 369E 4470707 WP ENGINE MALFUNCTIONED E LS1R O OTHER O OTHER NR NOT REPORTED 1 EA 13 8330P 0330E PART WON'T TURN OFF. 1 G 7 1 3U H3WE 2001092400169 20010924 00169 SW 2001 9 24 LS1R074941 1 20010813 G 2432 G641 BATTERY BELL 206 206B3 1181506 SW MAIN BATTERY BURNED E LS1R K NONE O OTHER IN INSP/MAINT 1 EA 13 9907K 2040 PART IS BURNED. 1 G 7 1 3U H2SW 2001092400171 20010924 00171 SW 2001 9 24 LS1R074942 1 20010817 G 7921 8537651 OIL COOLER BELL 212 212 1181420 SW ENGINE MAKING METAL E LS1R K NONE O OTHER IN INSP/MAINT 1 EA 13 8530F 30920 PART MAKING METAL. 1 G 7 1 4U H4SW 2001092400172 20010924 00172 2001 9 24 LS1R074943 4 20010817 G 2300 FM138 RADIO HUGHES 369 369E 4470707 WP COCKPIT FAILED E LS1R K NONE O OTHER IN INSP/MAINT 1 EA 13 8330P 0330E PART WILL NOT TRANSMITT. 1 G 7 1 3U H3WE 2001092400173 20010924 00173 WP 2001 9 24 LS1R075709 1 20010905 G 7400 369A45133 EPO ASSY HUGHES 369 369E 4470707 WP ENGINE MALFUNCTIONED E LS1R K NONE O OTHER IN INSP/MAINT 1 EA 13 8330P 0330E PART WARNING SIGNAL ACTIVATES. 1 G 7 1 3U H3WE 2001092400174 20010924 00174 WP 2001 9 24 LS1R075710 1 20010905 G 7400 369A45143 EPO ASSY HUGHES 369 369D 4470706 WP MALFUNCTIONED E LS1R K NONE O OTHER IN INSP/MAINT 1 EA 13 5027P 14 611002D PART WARNING SIGNAL ACTIVATES. 1 G 7 1 3U H3WE 2001092400175 20010924 00175 WP 2001 9 24 LS1R075711 1 20010905 G 7400 369A45143 EPO ASSY HUGHES 369 369E 4470707 WP ENGINE MALFUNCTIONED E LS1R K NONE O OTHER IN INSP/MAINT 1 EA 13 8330P 51 0330E PART WARNING SIGNAL ACTIVATES. 1 G 7 1 3U H3WE 2001100400143 20011004 00143 WP 2001 10 4 LS1R075923 1 20010928 G 7400 369A45143 EPO ASSY 369D HUGHES 369 369D 4470706 WP COCKPIT OUT OF ADJ E LS1R K NONE O OTHER IN INSP/MAINT 1 EA 13 369AW 673 470117D 470117D PART IS OUT OF CALIBRATION. 1 G 7 1 3U H3WE 2001100400144 20011004 00144 SW 2001 10 4 LS1R075924 1 20010928 G 7720 SEL019BC INDICATOR BELL 206 206B3 1181506 SW COCKPIT INACCURATE E LS1R K NONE O OTHER IN INSP/MAINT 1 EA 13 9907K 1000 2040 PART IS INACCURATE. 1 G 7 1 3U H2SW 2001100400145 20011004 00145 WP 2001 10 4 LS1R075925 1 20010928 G 7400 369A45143 EPO ASSY HUGHES 369 369D 4470706 WP COCKPIT MALFUNCTIONED E LS1R O OTHER N FALSE WARNING NR NOT REPORTED 1 EA 13 369AW 470117D PART IS ACTUATES WARNING HORN. 1 G 7 1 3U H3WE 2002012400003 20020124 00003 GL 2002 1 24 LS1R076721 2 20011022 G 7321 23065104 FUEL CONTROL HUGHES 369 369D 4470706 WP ALLSN 250C 250C20 03013 GL ENGINE MALFUNCTIONED E LS1R K NONE O OTHER IN INSP/MAINT 1 EA 13 5027P 611002D MAKES ENGINE RUMBLE AT IDLE; ENGINE N1 DECREASES 1/2 TO 1 PERCENT WITH START PUMP ON AND RETURNS TO NORMAL WHEN OFF. 1 G 7 1 3U 3 U H3WE E4CE 2002012400004 20020124 00004 WP 2002 1 24 LS1R076722 1 20011022 G 3150 369H64255 CONTROL UNIT 369D HUGHES 369 369D 4470706 WP INSTRUMENT PANEL FAILED E LS1R K NONE L NO TEST IN INSP/MAINT 1 EA 13 369AW 470117D 470117D INSTRUMENT PANEL LIGHT DIMMER CONTROL FAILED. 1 G 7 1 3U H3WE 2002012400005 20020124 00005 2002 1 24 LS1R076723 4 20011022 G 3420 206070274005 INDICATOR BELL 206 206B3 1181506 SW COCKPIT INOPERATIVE E LS1R O OTHER O OTHER NR NOT REPORTED 1 EA 13 206BY 2871 ATTITUDE INDICATOR NEEDLE WILL NOT MOVE. 1 G 7 1 3U H2SW 2002012400006 20020124 00006 WP 2002 1 24 LS1R076724 1 20011022 G 2822 1C34 PUMP HUGHES 369 369D 4470706 WP FUEL BOOST FAILED E LS1R K NONE O OTHER IN INSP/MAINT 1 EA 13 369AW 470117D BOOST PUMP WILL NOT TURN ON. 1 G 7 1 3U H3WE 2002012400007 20020124 00007 2002 1 24 LS1R076725 4 20011022 G 3424 206070274005 INDICATOR BELL 206 206B3 1181506 SW COCKPIT INOPERATIVE E LS1R O OTHER O OTHER NR NOT REPORTED 1 EA 13 9907K 2040 TURN AND BANK INDICATOR NEEDLE WILL NOT MOVE. 1 G 7 1 3U H2SW 2002012400008 20020124 00008 SW 2002 1 24 LS1R076726 1 20011022 G 2822 206062681101 PUMP BELL 206 206B3 1181506 SW FUEL BOOST MALFUNCTIONED E LS1R O OTHER O OTHER NR NOT REPORTED 1 EA 13 206BY 2871 BOOST PUMP PRODUCING LOW PRESSURE AND LOUD NOISE. 1 G 7 1 3U H2SW 2002012400009 20020124 00009 WP 2002 1 24 LS1R076727 1 20011022 G 7400 369A45143 EPO ASSY HUGHES 369 369D 4470706 WP COCKPIT MALFUNCTIONED E LS1R O OTHER O OTHER NR NOT REPORTED 1 EA 13 5027P 611002D LOW ROTOR RPM ACTUATES WHEN EPO IS ACTIVATED. 1 G 7 1 3U H3WE 2002012400010 20020124 00010 WP 2002 1 24 LS1R076728 1 20011022 G 6400 369D27514 BELLCRANK HUGHES 369 369D 4470706 WP TAIL ROTOR WORN E LS1R K NONE O OTHER IN INSP/MAINT 1 EA 13 5027P 611002D TAIL ROTOR BELLCRANK EARS WORN AND SPRUNG. 1 G 7 1 3U H3WE 2002012400011 20020124 00011 WP 2002 1 24 LS1R076729 1 20011022 G 6720 369D21800501 PITCH CONTROL HUGHES 369 369D 4470706 WP TAIL ROTOR WORN E LS1R K NONE O OTHER IN INSP/MAINT 1 EA 13 5027P 611002D TAIL ROTOR PITCH CONTROL IS WORN EXCESSIVELY. 1 G 7 1 3U H3WE 2002012400012 20020124 00012 SW 2002 1 24 LS1R076730 1 20011022 G 7603 1606470001 THROTTLE CABLE BELL 206 206B3 1181506 SW ENGINE BROKEN E LS1R K NONE O OTHER IN INSP/MAINT 1 EA 13 90322 1736 THROTTLE CABLE IS BROKEN. 1 G 7 1 3U H2SW 2002012400013 20020124 00013 GL 2002 1 24 LS1R076731 2 20011022 G 7261 1740996 FILTER BELL 206 206B3 1181506 SW ALLSN 250C 250C20B 03013 GL ENGINE OIL LEAKING E LS1R K NONE K FLUID LOSS IN INSP/MAINT 1 EA 13 206BX 2872 ENGINE OIL FILTER IS LEAKING. 1 G 7 1 3U 3 U H2SW E4CE 2002012400014 20020124 00014 WP 2002 1 24 LS1R076732 1 20011022 G 2820 369D281081 VENT LINE HUGHES 369 369D 4470706 WP ENGINE FUEL BENT E LS1R K NONE O OTHER IN INSP/MAINT 1 EA 13 5027P 611002D FUEL VENT LINE IS BENT. 1 G 7 1 3U H3WE 2002012400015 20020124 00015 2002 1 24 LS1R076733 4 20011022 G 3422 103002201 GYRO BELL 206 206B3 1181506 SW COCKPIT INOPERATIVE E LS1R K NONE O OTHER IN INSP/MAINT 1 EA 13 9907K 2040 DIRECTIONAL GYRO IS INOPERATIVE. 1 G 7 1 3U H2SW 2002012400016 20020124 00016 2002 1 24 LS1R076734 4 20011022 G 3421 500DC GYRO BELL 206 206B3 1181506 SW COCKPIT INOPERATIVE E LS1R K NONE O OTHER IN INSP/MAINT 1 EA 13 9907K 2040 ATTITUDE GYRO CONTROL INOPERATIVE. 1 G 7 1 3U H2SW 2002012400017 20020124 00017 WP 2002 1 24 LS1R076929 1 20011031 G 7400 369A45143 EPO ASSY HUGHES 369 369D 4470706 WP COCKPIT MALFUNCTIONED E LS1R K NONE O OTHER IN INSP/MAINT 1 EA 13 369AW 470117D EPO UNIT FEEDS BACK. 1 G 7 1 3U H3WE 2002012400018 20020124 00018 WP 2002 1 24 LS1R076930 1 20011031 G 7400 369A45143 EPO ASSY HUGHES 369 369D 4470706 WP COCKPIT MALFUNCTIONED E LS1R K NONE O OTHER IN INSP/MAINT 1 EA 13 369AW 470117D EPO ASSY FEEDS BACK. 1 G 7 1 3U H3WE 2002012400019 20020124 00019 SW 2002 1 24 LS1R076931 1 20011031 G 7931 209070262009 INDICATOR BELL 212 212 1181420 SW ENGINE OIL INTERMITTENT E LS1R K NONE O OTHER IN INSP/MAINT 1 EA 13 8530B 30702 INTERMITTENT. 1 G 7 1 4U H4SW 2002012400020 20020124 00020 WP 2002 1 24 LS1R076932 1 20011031 G 2430 A700ZG RCCB HUGHES 369 369D 4470706 WP ELECTRICAL FAILED E LS1R O OTHER O OTHER NR NOT REPORTED 1 EA 13 369AW 470117D RCCB HAS NO OUTPUT. 1 G 7 1 3U H3WE 2002012400021 20020124 00021 WP 2002 1 24 LS1R076933 1 20011031 G 2424 369A4652 VOLT REGULATOR HUGHES 369 369D 4470706 WP ELELCTRICAL OUT OF ADJ E LS1R K NONE O OTHER IN INSP/MAINT 1 EA 13 369AW 470117D PART IS OUT OF CALIBRATION. 1 G 7 1 3U H3WE 2002012400022 20020124 00022 2002 1 24 LS1R076934 4 20011031 G 3420 5040017901 INDICATOR BELL 212 212 1181420 SW COCKPIT INOPERATIVE E LS1R K NONE L NO TEST IN INSP/MAINT 1 EA 13 8530B 30702 ARTIFICIAL HORIZON WILL NOT COME ON LINE. 1 G 7 1 4U H4SW 2002012400023 20020124 00023 2002 1 24 LS1R076935 4 20011031 G 3420 5040017901 INDICATOR BELL 212 212 1181420 SW COCKPIT INOPERATIVE E LS1R K NONE L NO TEST IN INSP/MAINT 1 EA 13 8530F 30920 ARTIFICIAL HORIZON WILL NOT COME ON LINE. 1 G 7 1 4U H4SW 2001032600396 20010326 00396 EU 2001 3 26 MALA010220 1 20010220 G 5320 FLOOR SUPPORT SAAB SF340 340B 7860101 EU FUSELAGE CORRODED A MALA K NONE O OTHER IN INSP/MAINT 1 GL 15 424XJ 424 FOUND DURING C-CHECK, CORROSION ON LT FLOOR SUPPORT FLANGE ON SEAT TRACK AT BL-0 STA 294 THRU STA 413. REFER TO CELSIUS W/O 19347, TASK 1526. MAINTENANCE REMOVED CORROSION AND CHECK LIMIT. REMOVED CORROSION IAW 51-70-40 MATERIAL REMOVED IS OUT OF LIMITS IAW SRM 53-70-60. REMOVED FWD CLIP IAW SRM 51-40-21, FABRICATED NEW ANGLE IAW SRM 51-20-20/30, ALODINE D, PRIMED AND PAINTED IAW SRM 51-20-42/43. INSTALLED IAW SRM 51-40-21/23. REMAINING AREA WITHIN ALLOWABLE LIMIT REF SR M 53-70-60. 2 L 7 2 4T RT A52EU 2001041700083 20010417 00083 SO 2001 4 17 MQGR20013601 1 20010412 G 5740 1159W307012 ATTACH FITTING GULSTM G1159 G1159B 3953535 SO WINGLET CORRODED B K NONE O OTHER IN INSP/MAINT 1 SW 99 74A 5720 036 DURING RECOMMENDED INSPECTION OF WINGLET ATTACH HARDWARE FOR CORROSION, FOUND CORROSION IN THE WINGLET TO WING ATTACHMEN T FITTING. IT APPEARS THIS CORROSION IS THE RESULT OF IMPROPER SEALING OF THE ATTACHMENT HARDWARE SINCE WATER WAS FOUND TRAPPED IN THE ONLY AREA OF CORRSION. THIS CORROSION WAS VERY DEEP AND WAS IN THE VOID BETWEEN THE UPPER AND LOWER BUS HINGS. 2 L 7 2 4F RT A12EA 2003091800071 20030918 00071 WP 2003 9 18 N32B2001004 1 20010910 G 5713 STRINGER DOUG DC6 DC6A 3021706 WP PWA R2800 R2800* 52026 NE STA17, LT WING CRACKED G O OTHER O OTHER NR NOT REPORTED 1 AL 01 7780B 21494 45372 STRINGER 17 CRACKED AT WING, STA 140. REPAIRED 17 AT WING STA L40 IAW NAC 2001-05. 2 L 7 4 4R 4 R 6A3 5E8 2001092400178 20010924 00178 CE 2001 9 24 N988ME 1 20010918 G 2752 505211516 PISTON BEECH BEECH B300 B300 1159232 CE RT FLAP ACTUATOR CRACKED C K NONE K FLUID LOSS IN INSP/MAINT 1 SW 99 988ME 4611 935A91 RIGHT OUTBOARD FLAP ACTUATOR CRACKED AT BASE OF PISTON WHERE THE END PLUG IS ATTACHED. THE CRACK WAS 1.5 INCHES LONG AN D RESULTED IN THE LOSS OF THE LUBRICATING OIL FROM OUT OF THE PISTON AND SCREW ASSEMBLY. THE LOSS OF OIL WAS THE FIRST INDICATION OF A PROBLEM, AND IT WAS WHILE INVESTIGATING THE OIL LEAK THAT THE CRACK WAS DISCOVERED.THIS CRACK COULD RESU LT IN A SIGNIFICANT LOSS OF STRUCTURAL STRENGTH OF THE ACTUATOR WHICH COULD RESULT IN THE STRUCTURAL FAILURE OF THE ACTU ATOR ASSEMBLY. 2 L 7 2 4T RT A24CE 2001052400007 20010524 00007 NE 2001 5 24 NE032001B2128 2 20010330 G 7260 BEARING HAMSTD SAAB SF340 340B 7860101 EU GE CT7TP CT79B 30030 NE GEARCASE CRACKED D MHMF K NONE O OTHER IN INSP/MAINT 1 NE 03 20743 UDAG0844 GEE785555 UPON DISASSEMBLY OF GEARCASE FOUND THE RIGHT AFT BEARING AND FORWARD ROLLER BEARING CRACKED. ALSO THE LEFT IDLER BEARIN G WAS FOUND WITH BRINNELLING/SPALLING ON RACEWAYS. 2 L 7 2 4T 4 T RT A52EU E8NE 2001092400179 20010924 00179 CE 2001 9 24 NMO192 1 20010912 G 3230 S217830144 HOSE CESSNA 210 T210L 2073449 CE NOSE GEAR FAILED G K NONE K FLUID LOSS LD LANDING 1 NM 01 6721M 3000 34 21061137 DURING LANDING, NOSE GEAR EXTENDED AND LOCKED, BUT MAIN GEAR DID NOT LOCK INTO PLACE. PILOT TRIED TO LOCK MAIN GEAR USIN G HAND HYDRAULIC PUMP WITH NO SUCCESS. AIRCRAFT LANDED WITH LOCKED NOSE GEAR AND COLLAPSED MAIN GEAR. SUFFERED DAMAGE TO REAR OF FUSELAGE, LEFT ELEVATOR, AND LEFT HORIZONTAL STABILIZER. INVESTIGATION FOUND FAILED NOSE GEAR HYDRAULIC FLEX L INE. THE FAILURE OF THIS LINE ALLOWED EXHAUSTION OF LANDING GEAR HYDRAULIC FLUID AFTER THE NOSE GEAR EXTENDED AND LOCKED , PREVENTING THE MAIN GEAR FROM LOCKING INTO PLACE.CONDITIONAL PART FAILURE. NO HISTORY NOTED IN AIRCRAFT MAINTENANCE RE CORDS ASSOCIATED WITH NOSE GEAR HYDRAULIC HOSE REPLACEMENT SINCE 1976. 1 H 7 1 3O 3A21 2001040900520 20010409 00520 GL 2001 4 9 NWOR140K 3 20010301 G 6111 V8433NS4 BLADE HARTZL HCA3V HCA3VK2 GL PROPELLER CRACKED B K NONE O OTHER IN INSP/MAINT 1 SW 05 490 BJ567 INSPECTION FOUND CRACKS AT TRAILING EDGE SIDE OF RETENTION AREA. 5 C P6EA 2001040900521 20010409 00521 GL 2001 4 9 NWOR140K1 3 20010301 G 6111 V8433NS4 BLADE HARTZL HCA3V HCA3VK2 GL PROPELLER CRACKED B K NONE O OTHER IN INSP/MAINT 1 SW 05 490 BJ567 INSPECTION FOUND CRACK ALONG LEADING EDGE SIDE OF RETENTION AREA. 5 C P6EA 2001040900493 20010409 00493 GL 2001 4 9 NWOR140K2 3 20010301 G 6111 V8433NS4 BLADE HARTZL HCA3V HCA3VK2 GL PROPELLER CRACKED B NWOR K NONE O OTHER IN INSP/MAINT 1 SW 05 490 560 DURING INSPECTION, CRACK FOUND ALONG TRAILING EDGE OF RETENTION AREA OF BLADE. 5 C P6EA 2001040900540 20010409 00540 GL 2001 4 9 NWOR140K3 3 20010301 G 6111 V8433NS4 BLADE HARTZL HCA3V HCA3VK2 GL PROPELLER CRACKED B K NONE O OTHER IN INSP/MAINT 1 SW 05 490 560 DURING INSPECTION CRACK WAS FOUND ALONG TRAILING EDGE OF RETENTION AREA. 5 C P6EA 2001040900551 20010409 00551 GL 2001 4 9 NWOR140K4 3 20010301 G 6111 V8433NS4 BLADE HARTZL HCA3V HCA3VK2 GL PROPELLER CRACKED B K NONE O OTHER IN INSP/MAINT 1 SW 05 490 560 ON INSPECTION 4.5 INCH CRACK WAS FOUND ON TRAILING EDGE SIDE OF BLADE RETENTION AREA. 5 C P6EA 2001040900552 20010409 00552 GL 2001 4 9 NWOR140K5 3 20010301 G 6111 V8433NS4 BLADE HARTZL HCA3V HCA3VK2 GL PROPELLER CRACKED B K NONE O OTHER IN INSP/MAINT 1 SW 05 490 FOUND 3.5 INCH CRACK ALONG TRAILING EDGE SIDE OF RETENTION AREA OF BLADE. 5 C P6EA 2001040900163 20010409 00163 EA 2001 4 9 NX4200315 2 20010207 G 8550 78531 PUMP LYC IO360 IO360L2A EA ENGINE OIL DEFECTIVE B NX42 K NONE O OTHER IN INSP/MAINT 1 SO 15 2177 L2780951A WHEN REASSEMBLING THE OIL PUMP, IT WAS NOTED THAT DESPITE ATTEMPTS TO CENTER THE OIL PUMP BODY, THE IMPELLERS WOUL BIND WITH TORQUE APPLIED TO THE HOUSING. ALL DIMENTIONAL INSPECTIONS WERE WITHIN LIMITS. THE PROBLEM DISAPPEARED AFTER REPL ACING THE COMBINATION OF THE OIL PUMP HOUSING AND DRIVEN IMPELLER. IT IS ASSUMED THAT THERE WAS A MACHING ALIGNMENT ERR OR IN THE HOUSING, DRIVEN IMPELLER SHAFT, OR POSSIBLY A COMBINATION OF BOTH. 3 O 1E10 2001040900159 20010409 00159 EA 2001 4 9 NX4200420 2 20010207 G 8520 LW16711 BEARING LYC IO360 IO360L2A EA ENGINE DEFECTIVE B NX42 K NONE O OTHER IN INSP/MAINT 1 SO 15 2179 L2780651A DURING ENGINE DISASSEMBLY FOR ROUTINE OVERHAUL IT WAS NOTED THAT SOME NR 3 MAIN BEARING SURFACE MATERIAL HAD RELEASED FR OM THE BEARING SHELL. 3 O 1E10 2001040900160 20010409 00160 EA 2001 4 9 NX4200440 2 20010207 G 8520 LW13884 MAIN BEARING LYC IO360 IO360L2A EA ENGINE DEFECTIVE B K NONE O OTHER IN INSP/MAINT 1 SO 15 2169 L2784651A DURING ENGINE DISASSEMBLY FOR ROUTINE OVERHAUL IT WAS NOTED THAT SOME NR 2 MAIN BEARING SURFACE MATERIAL HAD RELEASED FR OM THE BEARING SHELL. 3 O 1E10 2001121300020 20011213 00020 2001 12 13 O3HR111501 4 20011115 G 2564 INLET LIFE RAFT OBSTRUCTED B O3HR K NONE O OTHER IN INSP/MAINT 1 SW 03 DURING SCHEDULED MAINTENANCE INSPECTION ON RAFT (PN 64449101, SN 0150), IT WAS NOTED THAT ONE COMPARTMENT INFLATED AT A FASTER RATE THAN THE OTHER, SUBSEQUENT INSPECTION REVEALED A FOREIGN OBJECT BLOCKING THE INLET PORT. THE DEBRIS APPEARS TO BE INTERNAL HOSE MATERIAL, WHICH ACCUMULATED DURING THE MANUFACTURING PROCESS. RECOMMENDATION: INSPECT HOSE ASSEMB LIES INTERNALLY PRIOR TO BUILD UP OF MANIFOLD. MANIFOLD ASSY PN BREAKDOWN: HOSE 64457-101 (1 EA) , HOSE 64457-103 (2 EA)) 2002011800055 20020118 00055 WP 2002 1 18 OMNIDMR01 1 20011220 G 5302 369D23601501 STRUCTURE HUGHES 369 369D 4470706 WP HORIZONTAL STAB CRACKED C K NONE O OTHER IN INSP/MAINT 1 SW 99 86ST 711012D HORIZONTAL STABILIZER CRACKED ON TRAILING EDGE AND TRIM TAB CRACKED ON LEADING EDGE DUE TO EXCESS FLUTTER. CRACKING CON CENTRATED AROUND AREA OF DAMPER WEIGHTS. TABS WERE TOO LONG AND ARE SUPPORTED ONLY BY RIVETS LOCATED ON LEADING EDGE,THE DAMPER WEIGHTS ADDED TO COMPENSATE. THE WEIGHTS NOT FLUSH TO TAB CREATES EXCESSIVE DRAG AND FURTHER CONTRIBUTES TO EXCE SSIVE VIBRATION. THE EXCESSIVE FLUTTER COMMON IN 369 SERIES. 1 G 7 1 3U H3WE 2002011800056 20020118 00056 WP 2002 1 18 OMNIDMR02 1 20010917 G 5302 421087505 STRUCTURE HUGHES 369 369E 4470707 WP HORIZONTAL STAB CRACKED C K NONE O OTHER IN INSP/MAINT 1 SW 99 7065C HORIZONTAL STABILIZER CRACKED ON TRAILING AND TRIM TAB CRACKED ON LEADING EDGE DUE TO EXCESSIVE FLUTTER. CRACKING IS CON CENTRATED AROUND AREA FO DAMPER WEIGHTS. TABS WERE TOO LONG AND ONLY SUPPORTED BY RIVETS LOCATED ON LEADING EDGE, THE D AMPER WEIGHTS ADDED TO COMPENSATE. THE WEIGHTS ARE NOT FLUSH TO TAB AND CREATES EXCESSIVE DRAG AND FURTHER CONTRIBUTES T O EXCESSIVE VIBRATION. THE EXCESSIVE FLUTTER IS COMMIN 369 SERIES. PROBLEM HAS BEEN IDENTIFIEDIN SERVICE NOTICE EN-44 ( REWORK OF HORIZONTAL STABILIZER ASSEMBLY) 1 G 7 1 3U H3WE 2002011800057 20020118 00057 WP 2002 1 18 OMNIDMR03 1 20010807 G 5302 421087905 STRUCTURE HUGHES 369 369E 4470707 WP HORIZONTAL STAB CRACKED C K NONE O OTHER IN INSP/MAINT 1 SW 99 440TJ 0099990812 HORIZONTAL STABILIZER IS CRACKED ON TRAILING EDGE AND TRIM TAB IS CRACKED ON LEADING EDGE DUE TO EXCESSIVE FLUTTER.CRACK ING IS CONCENTRATED AROUND AREA OF DAMPER WEIGHTS. TABS WERE TOO LONG AND ONLY SUPPORTED BY RIVETS LOCATED ON LEADING E DGE, CAUSING EXCESSIVE FLUTTER DURING FLIGHT; THE DAMPER WEIGHTS WERE ADDED TO CONPENSATE. THESE WEIGHTS ARE NOT FLUSH TO TAB, CREATING EXCESSIVE DRAG ON TABS AND FURTHER CONTRIBUTES TO EXCESSIVE VIBRATION. THIS EXCESSIVE FLUTTER IS COMMO N IS THE 369 SERIES. PROBLEM HAS BEEN IDENTIFIED IN SERVICE NOTICE EN-44 1 G 7 1 3U H3WE 2002011800058 20020118 00058 EU 2002 1 18 OMNIDMR04 1 20011214 G 5302 421087503 STRUCTURE HUGHES 369 369FF 4470709 EU HORIZONTAL STAB CRACKED C K NONE O OTHER IN INSP/MAINT 1 SW 99 30042 0099990855 HORIZONTAL STABILIZER CRACKED ON TRAILING EDGE ABD TRAIM TAB CRACKED ON LEADING EDGE DUE TO EXCESSIVE FLUTTER. CRACKING IS CONCENTRATED AROUND AREA OF DAMPER WEIGHTS. TABS WERE TOO LONG AND ONLY SUPORTED BY RIVET ON THE LEADING EDGE, CAUS ING EXCESSIVE FLUTTER DURING FLIGHT; THE DAMPER WEIGHTS ARE NOT FLUSH TO THE TAB CREATING EXCESSIVE DRAG ON THE TABS AND FURTHER CONTRIBUTES TO THE EXCESSIVE VIBRATION. THIS EXCESSIVE FLUTTER IS COMMON IN THE 369 SERIES, AND HAS BEEN IDEN TIFIED IN SERVICE NOTICE FN-29.1 1 G 7 1 3U H3WE 2001050200051 20010502 00051 SO 2001 5 2 PNSA010201 1 20010227 G 3297 WIRE PIPER PA31 PA31350 7103110 SO MLG INDICATOR DAMAGED E PNSA A UNSCHED LANDING N FALSE WARNING DE DESCENT 1 AL 03 28KE 318152049 AFTER SELECTING GEAR DOWN, LT DOWN LIGHT DID NOT ILLUMINATE. RETURNED TO BASE. REPAIRED WIRE ON LH DOWN LIGHT SWITCH. OP S CHECKED OK. 1 L 7 2 3O A20SO 2001050200052 20010502 00052 SO 2001 5 2 PNSA010203 1 20010228 G 6120 CONTROL CABLE PIPER PA31 PA31350 7103110 SO PROP CONTROL FAILED E PNSA C ABORTED TAKEOFF R J PARTIAL RPM/PWR LOSS WARNING INDICATION TO TAKEOFF 1 AL 03 3588Z 318052130 DURING TAKE-OFF ROLL RT ENGINE DID NOT DEVELOPE FULL RPM. ABORTED TAKE-OFF RETURNED FOR MAINTENANCE. REPLACED PROP CONTR OL CABLE DUE TO INTERNAL FAILURE. 1 L 7 2 3O A20SO 2001041000013 20010410 00013 SO 2001 4 10 PNSA010205 1 20010201 G 3297 WIRE PIPER PA31 PA31350 7103110 SO MLG BROKEN E PNSA A UNSCHED LANDING O OTHER CL CLIMB 1 AL 03 3588Z 318052130 DURING CLIMB PILOT COULD NOT PLACE THE GEAR LEVER IN THE UP POSITION. RETURNED TO BASE FOR MAINTENANCE. REPAIRED BROKEN WIRE ON GEAR ANTI RETRACT SOLENOID. 1 L 7 2 3O A20SO 2001091800135 20010918 00135 EA 2001 9 18 PNSA010506 2 20010501 G 7322 25245009 SERVO PIPER PA31 PA31350 7103110 SO LYC O540 TIO540J2BD 41532 EA LT ENGINE FAILED A PNSA C ABORTED TAKEOFF R PARTIAL RPM/PWR LOSS TO TAKEOFF 1 AL 03 3588Z 318052130 L840061A LT ENGINE WOULD NOT DEVELOP TAKEOFF POWER. ABORTED TAKEOFF. RETURNED FOR MAINTENANCE. REPLACED FUEL SERVO. 1 L 7 2 3O 3 O A20SO E14EA 2001050200053 20010502 00053 NE 2001 5 2 R004765 3 20010313 G 6114 D51105 FORK DORNER DO32 DO328100 2996000 NM PWA 119 PW119B NE HARTZL HDE6C HDE6C3B NE HUB BROKEN B SJ3R O OTHER E VIBRATION/BUFFET NR NOT REPORTED 1 GL 05 SJ3R 2503 2503 HL327 THE PROPELLER WAS RECEIVED FOR COMPLAINT OF VIOLENT VIBRATION. AFTER DISASSEMBLY, INSPECTION REVEALED C7075 BLADE BEARIN GS BROKEN, BEARINGS FRAGMENTS EMBEDDED IN BLADE SOCKETS 3, 4 & 6, COMPLOSITE WINDING DAMAGE TO BLADE NR 6, BLADE NR 6 FO RK SLOT THIN WALL SIDE BROKEN ON FORK CAM FOLLOWER AND RETENTION WASHER DAMAGED BEYOND LIMITS ON BLADE NR 6 PITCH CHANG E BRACKET, BLADE NR 6 PITCH CHANGE BRACKET BOLTS FAILED INCOMMING TORQUE TEST. 2 H 7 2 4T 4 T RT A45NM E20NE 6 C P34NE 2001050200054 20010502 00054 NE 2001 5 2 R004808 3 20010315 G 6114 C7075 BEARING DORNER DO32 DO328100 2996000 NM PWA 119 PW119B NE HARTZL HDE6C HDE6C3B NE HUB BROKEN B SJ3R O OTHER E VIBRATION/BUFFET NR NOT REPORTED 1 GL 05 SJ3R 1724 HL87 THE PROPELLER WAS RECEIVED FOR COMPLAINT OF EXCESSIVE VIBRATION. AFTER DISASSEMBLY, INSPECTION REVEALED C7075 BLADE BEAR INGS BROKEN, BEARING FRAGMENTS FOUND IN HUB BLADE SOCKETS 2 THROUGH 6, COMPOSITE WINDING DAMAGE TO BLADES 2 THROUGH 4, B LADE NR 4 FORK SLOT THIN WALL SIDE BRIKEN ON FORK CAM FOLLOWER AND B-475 RETENTION WASHER DAMAGED BEYOND REPAIR ON BLADE NR 4 PITCH CHANGE BRACKET, PITCH CHANGE BRACKET BOLTS FAILED TORQUE TEST ON BLADES 3 & 4. 2 H 7 2 4T 4 T RT A45NM E20NE 6 C P34NE 2002012900020 20020129 00020 SW 2002 1 29 R20888 1 20011108 G 3710 SCREW MOONEY M20 M20J 5870219 SW FILTER ATTACH CORRODED B K NONE O OTHER IN INSP/MAINT 1 CE 03 300YB 243010 INSTRUMENT AIR FILTER ATTACHING SCREW CORRODED AND CAUSES METAL DEBRIS TO ENTER VACUUM SYSTEM UNFILTERED. 1 L 7 1 3O 2A3 2001092500017 20010925 00017 NE 2001 9 25 R3R220010621 2 20010618 G 7200 3015537 SEAL PWA CESSNA 500 550 2076604 CE PWA JT15 JT15D4 52112 NE NR 2 ENGINE LEAKING B R3R2 K NONE K FLUID LOSS IN INSP/MAINT 1 SW 01 586RE PT285 5500199 PCE70585 FOUND HYDRAULIC PUMP DRIVE PAD ON ENGINE NR 2 LEAKING. NEWLY INSTALLED SEAL I.D. FOUND APPROX. .015 INCH TOO LARGE FOR SHAFT IT IS SUPPOSED TO SEAL. SHAFT DIAMETER: 0.865 INCH, SEAL ID: 0.880 INCH. THIS PROBLEM OCCURRED WITH AT LEAST SIX SEALS BEFORE ONE WAS FOUND WITH THE CORRECT "TIGHT" FIT ON THE DRIVE SHAFT. 1 L 7 2 4F 4 F A22CE E1NE 2001030700604 20010307 00604 2001 3 7 R7MR291732569 4 20010108 G 2311 TFM403G TRANSCEIVER SNIAS 350 AS350B2 8680813 EU UHF/FM TRANS FAILED B R7MR O OTHER O OTHER NR NOT REPORTED 1 NM 07 97LG 2917 UNIT FAILED UPON INSTALLATION. UNACCEPTABLE SIDETONE. REPLACED WITH NEW UNIT, CORRECTED PROBLEM. 1 G 7 1 3U H9EU 2001030700606 20010307 00606 EU 2001 3 7 R7MR325232577 1 20010119 G 2460 SS120 INVERTER SNIAS 350 AS350B3 8680954 EU ELELCTRICAL INOPERATIVE B R7MR K NONE O OTHER IN INSP/MAINT 1 NM 07 392LG 374 3252 UNIT INOPERATIVE. NO AC OUT. REPLACED WITH NEW UNIT, CORRECTED PROBLEM. 1 G 7 1 3U H9EU 2001030700605 20010307 00605 NM 2001 3 7 R7MR32573 1 20010110 G 3150 900A3720002111 DISPLAY DOUG MD900 MD900 3027375 NM COCKPIT INOPERATIVE B R7MR K NONE O OTHER IN INSP/MAINT 1 NM 07 901CF 75 90000012 UNIT INOPERATIVE. ROW OF LIGHTS ON ALPHA DISPLAY MISSING. 1 G 7 2 3U NC H19NM 2001030700608 20010307 00608 NE 2001 3 7 R7MR32581 2 20010115 G 7230 70BM035420 COMPRESSOR SNIAS 350 AS350B2 8680813 EU TMECA ARRIEL ARRIEL1 60030 NE ENGINE SEIZED B R7MR O OTHER O OTHER NR NOT REPORTED 1 NM 07 97LG 413 2917 COMPRESSOR SEIZED. REPLACED WITH NEW UNIT, CORRECTED PROBLEM. 1 G 7 1 3U 3 U H9EU E19EU 2001030700609 20010307 00609 NE 2001 3 7 R7MR32582 2 20010115 G 7230 70BM025020 BLADE SNIAS 350 AS350B2 8680813 EU TMECA ARRIEL ARRIEL1 60030 NE COMPRESSOR FAILED B R7MR O OTHER O OTHER NR NOT REPORTED 1 NM 07 97LG 413 2917 COMPRESSOR BLADE WILL NOT ROTATE. REPLACED WITH NEW UNIT, CORRECTED PROBLEM. 1 G 7 1 3U 3 U H9EU E19EU 2001030700636 20010307 00636 2001 3 7 R7MR32592 4 20010117 G 2312 064010540030 TRANSCEIVER SNIAS 350 AS350B3 8680954 EU VHF RADIO INOPERATIVE B R7MR K NONE O OTHER IN INSP/MAINT 1 NM 07 103LN 848 3128 UNIT INOPERATIVE. BREKS SQUELCH ON ITS OWN. REPLACED WITH NEW UNIT, CORRECTED PROBLEM. 1 G 7 1 3U H9EU 2001030700635 20010307 00635 EU 2001 3 7 R7MR32595 1 20010117 G 7714 1179405603 INDICATOR BOLKMS 117 BK117A4 5626017 EU COCKPIT INOPERATIVE B R7MA K NONE O OTHER IN INSP/MAINT 1 NM 07 527RM 53 7111 UNIT INOPERATIVE. NO INDICATION WHILE ENGINE IS RUNNING. REPLACED WITH NEW UNIT, CORRECTED PROBLEM. 1 G 7 2 3U H13EU 2001040500116 20010405 00116 NM 2001 4 5 R7MR32618 1 20010126 G 6710 900C3820021105 ACTUATOR DOUG MD900 MD900 3027375 NM M/ROTOR CONTROL LEAKING B R7MR K NONE O OTHER IN INSP/MAINT 1 NM 07 901CF 1926 90000012 HYDRAULIC UNIT, DUAL SERVO ACTUATOR, MR CONTROL LEAKING BEYOND SERVICEABLE LIMITS. REPLACED WITH NEW UNIT, CORRECTED PR OBLEMS. 1 G 7 2 3U NC H19NM 2001040500123 20010405 00123 NM 2001 4 5 R7MR32619 1 20010127 G 2916 900H3821502107 GAUGE DOUG MD900 MD900 3027375 NM HYD RESERVOIR LOOSE B R7MR K NONE O OTHER IN INSP/MAINT 1 NM 07 901CF 2625 90000012 SIGHT GAUGE RIBBON WILL NOT STAY ATTACHED AT BOTTOM OF INDICATOR TUBE, WHICH RENDERS THE QUANTITY OF HYDRAULIC FLUID IN THE RESERVOIR UNRELIABLE. REPLACED WITH NEW UNIT, CORRECTED PROBLEM. 1 G 7 2 3U NC H19NM 2001040500117 20010405 00117 EU 2001 4 5 R7MR32629 1 20010102 G 6410 355A12004008 BLADE SNIAS 350 AS350B2 8680813 EU TAIL ROTOR PEELING B R7MR K NONE O OTHER IN INSP/MAINT 1 NM 07 97LG 73 2917 PAINT PEELING. REPLACED WITH NEW UNIT CORRECTED PROBLEM. 1 G 7 1 3U H9EU 2001040900190 20010409 00190 EU 2001 4 9 R7MR32643 1 20010104 G 6720 350A33214501 ROD SNIAS 350 AS350B3 8680954 EU TMECA ARRIEL ARRIEL1 60030 NE PITCH CONTROL WORN B R7MR K NONE O OTHER IN INSP/MAINT 1 NM 07 103LN 310 3128 PITCH CONTROL ROD WORN BEYOND SERVICEABLE LIMITS. REPLACED WITH NEW UNIT, CORRECTED PROBLEM. 1 G 7 1 3U 3 U H9EU E19EU 2001040900006 20010409 00006 EU 2001 4 9 R7MR32651 1 20010128 G 2460 SP461310 SWITCH BOLKMS BK117 BK117C1 5626025 EU TMECA ARRIEL ARRIEL1 60030 NE DC SYSTEM WORN B R7MR K NONE O OTHER IN INSP/MAINT 1 NM 07 117SU 1080 7527 TOGGLE SWITCH WORN BEYOND SERVICEABLE LIMITS. REPLACED WITH NEW UNIT, CORRECTED PROBLEM. 1 G 7 2 3U 3 U NC H13EU E19EU 2001050300230 20010503 00230 EU 2001 5 3 R7MR32654 1 20010111 G 8000 845UN1Q4AA5F SWITCH SNIAS 350 AS350B3 8680954 EU STARTER INOPERATIVE B R7MR K NONE O OTHER IN INSP/MAINT 1 NM 07 52281 541 3249 UNIT INOPERATIVE. REMOVED AND REPLACED WITH NEW UNIT, CORRECTED PROBLEM. 1 G 7 1 3U H9EU 2001040900007 20010409 00007 EU 2001 4 9 R7MR32656 1 20010226 G 6320 ZARISEC135 TRANSMISSION UROCOP EC135 EC135P1 8680990 EU PWA PW206 PW206A NE MAIN ROTOR COLLAPSED B R7MA K NONE L NO TEST NR NOT REPORTED 1 NM 07 135SJ 594 EC1350054 MAIN ROTOR TRANSMISSION COLLAPSED. REPLACED WITH NEW UNIT, CORRECTED PROBLEM. 1 G 7 2 3U 3 U O H88EU E42NE 2001040900009 20010409 00009 EU 2001 4 9 R7MR32657 1 20010228 G 6220 L621M1003101 DAMPER UROCOP EC135 EC135P1 8680990 EU PWA PW206 PW206A NE MAIN ROTOR WORN B R7MA K NONE O OTHER IN INSP/MAINT 1 NM 07 135SJ 946 EC1350054 ELASTOMERICS WORN BEYOND SERVICEABLE LIMITS. REPLACED WITH NEW UNIT, CORRECTED PROBLEM. THE REPLACEMENT DAMPER HAS LES S THAN 1 YEAR TO SERVICE LIFE. 1 G 7 2 3U 3 U O H88EU E42NE 2001040900010 20010409 00010 EU 2001 4 9 R7MR32658 1 20010228 G 6220 L621M1003101 DAMPER UROCOP EC135 EC135P1 8680990 EU PWA PW206 PW206A NE MAIN ROTOR WORN B R7MA K NONE O OTHER IN INSP/MAINT 1 NM 07 135SJ 946 EC1350054 ELASTOMERICS WORN BEYOND SERVICEABLE LIMITS. SPLITLINE CRACK LONGER THAN 40MM. REPLACED WITH NEW UNIT, CORRECTED PROBL EM NOTE: THE REPLACEMENT DAMPER HAS LESS THAN 1 YEAR TO SERVICE LIFE. 1 G 7 2 3U 3 U O H88EU E42NE 2001040900020 20010409 00020 EU 2001 4 9 R7MR32659 1 20010228 G 6220 L621M1003101 DAMPER UROCOP EC135 EC135P1 8680990 EU PWA PW206 PW206A NE MAIN ROTOR WORN B R7MA K NONE O OTHER IN INSP/MAINT 1 NM 07 135SJ 390 EC1350054 ELASTOMERICS WORN BEYOND SERVICEABLE LIMITS. SPLITLINE CRACK LONGER THAN 40MM. REPLACED WITH NEW UNIT, CORRECTED PROBL EM. NOTE: THE REPLACEMENT DAMPER HAS LESS THAN 1 YEAR TO SERVICE LIFE. 1 G 7 2 3U 3 U O H88EU E42NE 2001040900021 20010409 00021 EU 2001 4 9 R7MR32660 1 20010228 G 6220 L621M1003101 DAMPER UROCOP EC135 EC135P1 8680990 EU PWA PW206 PW206A NE MAIN ROTOR WORN B R7MA K NONE O OTHER IN INSP/MAINT 1 NM 07 135SJ 390 EC1350054 ELASTOMERICS WORN BEYOND SERVICEABLE LIMITS. SPLITLINE CRACK LONGER THAN 40MM. REPLACED WITH NEW UNIT, CORRECTED PROBL EM. NOTE: THE REPLACEMENT DAMPER HAS LESS THAN 1 YEAR TO SERVICE LIFE. 1 G 7 2 3U 3 U O H88EU E42NE 2001040900023 20010409 00023 EU 2001 4 9 R7MR32661 1 20010228 G 6220 L621M1003101 DAMPER UROCOP EC135 EC135P1 8680990 EU PWA PW206 PW206A NE MAIN ROTOR WORN B R7MA K NONE O OTHER IN INSP/MAINT 1 NM 07 135SJ 390 EC1350054 REPLACED WITH LOWER DAMPER. REPLACED WITH NEW UNIT, CORRECTED PROBLEM. NOTE: THE REPLACEMENT DAMPER HAS LESS THAN 1 Y EAR TO SERVICE LIFE. 1 G 7 2 3U 3 U O H88EU E42NE 2001040900024 20010409 00024 EU 2001 4 9 R7MR32662 1 20010228 G 6220 L621M1003101 DAMPER UROCOP EC135 EC135P1 8680990 EU PWA PW206 PW206A NE MAIN ROTOR WORN B R7MA K NONE O OTHER IN INSP/MAINT 1 NM 07 135SJ 390 EC1350054 REPLACED WITH LOWER DAMPER. REPLACED WITH NEW UNIT, CORRECTED PROBLEM. NOTE: THE REPLACEMENT DAMPER HAS LESS THAN 1 Y EAR TO SERVICE LIFE. 1 G 7 2 3U 3 U O H88EU E42NE 2001040900025 20010409 00025 EU 2001 4 9 R7MR32663 1 20010228 G 6220 L621M1003101 DAMPER UROCOP EC135 EC135P1 8680990 EU PWA PW206 PW206A NE MAIN ROTOR WORN B R7MA K NONE O OTHER IN INSP/MAINT 1 NM 07 135SJ 390 EC1350054 REPLACED WITH LOWER DAMPER. REPLACED WITH NEW UNIT, CORRECTED PROBLEM. NOTE: THE REPLACEMENT DAMPER HAS LESS THAN 1 Y EAR TO SERVICE LIFE. 1 G 7 2 3U 3 U O H88EU E42NE 2001040900029 20010409 00029 EU 2001 4 9 R7MR32664 1 20010228 G 6220 L621M1003101 DAMPER UROCOP EC135 EC135P1 8680990 EU PWA PW206 PW206A NE MAIN ROTOR WORN B R7MA K NONE O OTHER IN INSP/MAINT 1 NM 07 135SJ 390 EC1350054 SPLITLINE CRACK LONGER THAN 40MM. REPLACED WITH NEW UNIT, CORRECTED PROBLEM. NOTE: THE REPLACEMENT DAMPER HAS LESS THA N 1 YEAR TO SERVICE LIFE. 1 G 7 2 3U 3 U O H88EU E42NE 2001040900326 20010409 00326 SO 2001 4 9 R7MR32667 1 20010125 G 6410 704A33633171 HINGE EMB 120 EMB120 3260201 SO TAIL ROTOR WORN C R7MR K NONE O OTHER IN INSP/MAINT 1 NM 07 92GL 460 120092 ELASTOMERICS WORN BEYOND SERVICEABLE LIMITS. REPLACED WITH NEW UNITS FROM 1 EACH KIT PART NUMBER 355A33-2153-00, CORREC TED PROBLEM. 2 TEETERING BEARINGS EQUALS 1 KIT. 2 L 7 2 4T RT A31SO 2001040900031 20010409 00031 EU 2001 4 9 R7MR32670 1 20010125 G 6410 704A33633116 BEARING SNIAS 350 AS350B2 8680813 EU TAIL ROTOR WORN C R7MR K NONE O OTHER IN INSP/MAINT 1 NM 07 92LG 460 2575 ELASTOMERICS WORN BEYOND SERVICEABLE LIMITS. REPLACED WITH NEW UNITS FROM 1 EACH KIT PART NUMBER 355A09-1036-01 CORRECT ED PROBLEM. 4 HALF SHELLS EQUALS 1 KIT. 1 G 7 1 3U H9EU 2001040900032 20010409 00032 EU 2001 4 9 R7MR32671 1 20010105 G 6410 704A33633116 BEARING SNIAS 350 AS350B2 8680813 EU TMECA ARRIEL ARRIEL1 60030 NE TAIL ROTOR WORN C R7MR K NONE O OTHER IN INSP/MAINT 1 NM 07 94LG 649 2728 ELASTOMERICS WORN BEYOND SERVICEABLE LIMITS. REPLACED WITH NEW UNITS FROM 1 EACH KIT PART NUMBER 355A09-1036-01, CORREC TED PROBLEM. 4 HALF SHELLS EQUALS 1 KIT. 1 G 7 1 3U 3 U H9EU E19EU 2001040900038 20010409 00038 EU 2001 4 9 R7MR32675 1 20010130 G 6220 704A3363320851 STOP SNIAS 350 AS350B2 8680813 EU M/R STARFLEX WORN C R7MR K NONE O OTHER IN INSP/MAINT 1 NM 07 92LG 1203 2575 ELASTOMERICS WORN BEYOND SERVICEABLE LIMITS. REPLACED WITH NEW UNIT, CORRECTED PROBLEM. 1 G 7 1 3U H9EU 2001040900039 20010409 00039 EU 2001 4 9 R7MR32676 1 20010130 G 6220 704A3363320851 STOP SNIAS 350 AS350B2 8680813 EU M/R STARFLEX WORN C R7MR K NONE O OTHER IN INSP/MAINT 1 NM 07 92LG 1203 2575 ELASTOMERICS WORN BEYOND SERVICEABLE LIMITS. REPLACED WITH NEW UNIT, CORRECTED PROBLEM. 1 G 7 1 3U H9EU 2001040900377 20010409 00377 EU 2001 4 9 R7MR32677 1 20010130 G 6220 704A3363320851 STOP SNIAS 350 AS350B2 8680813 EU M/R STARFLEX WORN C R7MR K NONE O OTHER IN INSP/MAINT 1 NM 07 92LG 1203 2575 ELASTOMERICS WORN BEYOND SERVICEABLE LIMITS. REPLACED WITH NEW UNIT, CORRECTED PROBLEM. 1 G 7 1 3U H9EU 2001040900046 20010409 00046 EU 2001 4 9 R7MR32683 1 20010204 G 2932 MA12401 PRESSURE SWITCH SNIAS 350 AS350B2 8680813 EU HYD SYSTEM INOPERATIVE C R7MR K NONE O OTHER IN INSP/MAINT 1 NM 07 92LG 12 2575 PRESSURE SWITCH INOPERATIVE. HYDRAULIC LIGHT GOES OUT WHEN SWITCH IS TAPPED. REPLACED WITH NEW UNIT, CORRECTED PROBLEM . 1 G 7 1 3U H9EU 2001040900157 20010409 00157 EU 2001 4 9 R7MR32697 1 20010127 G 6230 350A37112602 SCISSORS SNIAS 350 AS350B2 8680813 EU SWASHPLATE WORN C R7MR K NONE O OTHER IN INSP/MAINT 1 NM 07 92LG 460 2575 WORN BEYOND SERVICEABLE LIMITS. SCARRED BUSHING. REPLACED WITH NEW UNIT, CORRECTED PROBLEM. 1 G 7 1 3U H9EU 2001040900158 20010409 00158 EU 2001 4 9 R7MR32698 1 20010127 G 6230 704A33640021 SPACER SNIAS 350 AS350B2 8680813 EU SWASHPLATE WORN C R7MR K NONE O OTHER IN INSP/MAINT 1 NM 07 92LG 460 2575 WORN BEYOND SERVICEABLE LIMITS. REPLACED WITH NEW UNITS, CORRECTED PROBLEM. 1 G 7 1 3U H9EU 2001040900211 20010409 00211 2001 4 9 R7MR32704 4 20010221 G 3120 B1894522282A CLOCK SNIAS 350 AS350B3 8680954 EU TMECA ARRIEL ARRIEL1 60030 NE COCKPIT INOPERATIVE B R7MR K NONE O OTHER IN INSP/MAINT 1 NM 07 397LG 193 3268 UNIT INOPERATIVE. REPLACED WITH NEW UNIT, CORRECTED PROBLEM. 1 G 7 1 3U 3 U H9EU E19EU 2001040900215 20010409 00215 2001 4 9 R7MR32706 4 20010202 G 3416 150201182 ALTIMETER SNIAS 350 AS350B3 8680954 EU TMECA ARRIEL ARRIEL1 60030 NE COCKPIT INOPERATIVE B R7MR K NONE O OTHER IN INSP/MAINT 1 NM 07 397LG 175 3268 UNIT INOPERATIVE. REPLACED WITH NEW UNIT, CORRECTED PROBLEM. 1 G 7 1 3U 3 U H9EU E19EU 2001040900238 20010409 00238 NE 2001 4 9 R7MR32713 2 20010222 G 7261 350A54113800 TUBE SNIAS 350 AS350B3 8680954 EU TMECA ARRIEL ARRIEL1 60030 NE AIR OIL VENT CRACKED B R7MR K NONE O OTHER IN INSP/MAINT 1 NM 07 397LG 91 3268 CRACKED BEYOND SERVICABLE LIMITS. REPLACED WITH NEW UNIT, CORRECTED PROBLEM. 1 G 7 1 3U 3 U H9EU E19EU 2001040900240 20010409 00240 2001 4 9 R7MR32716 4 20010103 G 3160 B19030MC02 DISPLAY SNIAS 350 AS350B3 8680954 EU TMECA ARRIEL ARRIEL1 60030 NE COCKPIT INOPERATIVE B R7MR K NONE O OTHER IN INSP/MAINT 1 NM 07 397LG 163 3268 UNIT INOPERATIVE. WILL NOT TRANSFER INFORMATION BETWEEN SCREENS. REPLACED WITH NEW UNIT, CORRECTED PROBLEM. 1 G 7 1 3U 3 U H9EU E19EU 2001112700026 20011127 00026 CE 2001 11 27 RASFTYRK178 1 20011113 G 7120 45A34361005 MOUNT BRACKET BEECH MU300 400A 1155402 CE LT ENGINE CRACKED B ERY2 K NONE O OTHER IN INSP/MAINT 1 SO 11 708TA 3367 RK178 WHILE PERFORMING A ROUTINE SCHEDULED INSPECTION, INSPECTORS NOTED THE LT FORWARD ENGINE MOUNT BRACKET TO BE CRACKED APPR OX 50 PERCENT THROUGH THE LOWER HALF. 2 H 7 2 4F RT A16SW 2001112700028 20011127 00028 CE 2001 11 27 RASFTYRK180 1 20011113 G 7120 45A34361005 MOUNT BRACKET BEECH MU300 400A 1155402 CE LT ENGINE CRACKED B ERY2 K NONE O OTHER IN INSP/MAINT 1 SO 11 709TA 3201 RK180 WHILE PERFORMING A ROUTINE SCHEDULED INSPECTION, INSPECTORS NOTED THE LT FORWARD ENGINE MOUNT BRACKET TO BE CRACKED APPR OX 75 PERCENT THROUGH THE LOWER HALF. 2 H 7 2 4F RT A16SW 2001112700029 20011127 00029 CE 2001 11 27 RASFTYRK183 1 20011113 G 7120 45A34361005 MOUNT BRACKET BEECH MU300 400A 1155402 CE LT ENGINE CRACKED B ERY2 K NONE O OTHER IN INSP/MAINT 1 SO 11 710TA 3195 RK183 WHILE PERFORMING A ROUTINE SCHEDULED INSPECTION, INSPECTORS NOTED THE LT FORWARD ENGINE MOUNT BRACKET TO BE CRACKED APPR OX 75 PERCENT THROUGH THE LOWER HALF. 2 H 7 2 4F RT A16SW 2001112700030 20011127 00030 CE 2001 11 27 RASFTYRK189 1 20011113 G 7120 45A34361005 MOUNT BRACKET BEECH MU300 400A 1155402 CE LT ENGINE CRACKED B ERY2 K NONE O OTHER IN INSP/MAINT 1 SO 11 715TA 3107 RK189 WHILE PERFORMING A ROUTINE SCHEDULED INSPECTION, INSPECTORS NOTED THE LT FORWARD ENGINE MOUNT BRACKET TO BE CRACKED APPR OX 80 PERCENT THROUGH THE LOWER HALF. 2 H 7 2 4F RT A16SW 2002011000092 20020110 00092 CE 2002 1 10 RASFTYRK195 1 20011231 G 7120 45A34361005 MOUNT BRACKET BEECH MU300 400A 1155402 CE LT ENGINE CRACKED B ERY2 K NONE O OTHER IN INSP/MAINT 1 SO 11 718TA 2992 RK195 CRACK FOUND IN LT FORWARD ENGINE MOUNT BRACKET WHILE PERFORMING FLUORESCENT PENETRANT INSPECTION AS PER RAYTHEON AIRCRAF T SAFETY COMMUNIQUE NR 189. 2 H 7 2 4F RT A16SW 2002011000093 20020110 00093 CE 2002 1 10 RASFTYRK198 1 20011127 G 7120 45A34361005 MOUNT BRACKET BEECH MU300 400A 1155402 CE LT ENGINE CRACKED B ERY2 K NONE O OTHER IN INSP/MAINT 1 SO 11 798TA 2805 RK198 WHILE PERFORMING A ROUTINE SCHEDULED INSPECTION, INSPECTORS NOTED THE LT FORWARD ENGINE MOUNT BRACKET TO BE CRACKED APPR OX 75 PERCENT THROUGH THE LOWER HALF. 2 H 7 2 4F RT A16SW 2001092500023 20010925 00023 CE 2001 9 25 RFS20011 1 20010808 G 3233 NAS464P4A29 BOLT CESSNA CESSNA 210 210K 2073446 CE MLG ACTUATOR CRACKED B K NONE O OTHER IN INSP/MAINT 1 SW 99 8142G 5891 1781 21059442 WHILE REPLACING THE RT MLG ACTUATOR AS PART OF COMPIANCE WITH CESSNA SEB01-2, IT WAS DISCOVERED THAT ONE OF THE THREE NA S ATTACH BOLTS WAS BROKEN.IT WAS ONLY BEING HELD IN PLACE BY THE SAFETY WIRE LINKING THE THREE BOLTS. THE BOLT HAD FAIL ED BETWEEN THE FIRST AND SECOND THREADS COUNTING FROM THE SHANK OF THE BOLT. PROCURED AND INSTALLED 3EA NEW NAS BOLTS T O CORRECT. 1 H 7 1 3O 3A21 2001092500032 20010925 00032 NE 2001 9 25 RO 2 20010820 G 7230 30756441 CARBON SEAL ALIDSG AMD FALC90 FALCON900EX 2730009 EU GARRTT TFE731 TFE73160 NE HP CASE BROKEN B E ENGINE SHUTDOWN K FLUID LOSS NR NOT REPORTED 1 SW 99 1101 NA N990WM 112239 THE NR 4 CARBON SEAL CERAMIC RING WAS FOUND TO BE BROKEN DURING THE ENGINE TEARDOWN. THE CARBON RING SEAL WAS ALSO FOUND BROKEN. THERE WAS MUCH COLLATERIAL DAMAGE. THE OPERATOR REPORTED OIL LOSS DURING FLIGHT WITH SUBSEQUENT OIL CONTAMINATI ON UPON POST FLIGHT ENGINE EXAMINATION. THERE WILL BE AN ENGINE CONDITION REPORT GENERATED TO DETAIL THE FINDINGS POST A NALYTICAL INSPECTION. 2 L 7 3 4F 4 F RT A46EU E1NM 2001092500034 20010925 00034 WP 2001 9 25 RO462097 2 20010905 G 7230 30745557 STATOR AMD FALC50 FALCON900 2700160 EU GARRTT TFE731 TFE7315BR WP COMPRESSOR SEPARATED B C ABORTED TAKEOFF M Y OVER TEMP ENGINE STOPPAGE TO TAKEOFF 1 SW 99 2462 95146 ENGINE RETURNED FOR MAINTENANCE WHEN AIRCRAFT WAS EXPERIENCING ENGINE TEMPERATURE LIMIT AT TAKE OFF AND SUBSEQUENT HUNG STARTS. THE INNER HUB OF THE 4TH LOW COMPRESSOR STATOR WAS FOUND SEPARATED DURING ENGINE MAINTENANCE DISASSEMBLY. MAJO R ENGINE COMPONENT DOWNSTREAM DAMAGE OCCURED AS SECONDARY DAMAGE. ENGINE MANUFACTURER NOTIFIED OF THIS UNIQUE FINDINGS. 2 L 7 3 4F 4 F RT A46EU E6WE 2001042400282 20010424 00282 SO 2001 4 24 RX8R2001001 1 20010413 G 5280 4252931 SKIN PIPER PA42 PA42720 7104212 SO PWA PT6 PT6A61 52043 EA HARTZL HCB3T HCB3TN3 GL MLG DOOR DEBONDED B RX8R K NONE O OTHER IN INSP/MAINT 1 SO 15 RX8R 5203 11 425501038 PCE99080 BU10583 AFTER LANDING IT WAS NOTICED THAT THE RIGHT INBOARD LANDING GEAR DOOR SKIN HAD PEELED OFF FROM THE REST OF THE DOOR AT T HE LEADING EDGE. UPON FURTHER EXAMINATION THE DOOR SKIN AND SUPPORTING STRUCTURE WHICH ARE BONDED TOGETHER WITH STRUCTUR AL ADHESIVE SHOWED CORROSION AT THE BONDING SURFACE ON BOTH THE DOOR SKIN AND THE DOOR STRUCTURE. OPERATORS OF PA42-720 AIRCRAFT MAY WANT TO INSPECT THE LEADING EDGE OF THE INB. LNDG. DOORS FOR CORROSION AND SEPARATION OF THE SKIN. 1 L 7 2 4T 4 T A23SO E4EA 6 C P15EA 2001050300041 20010503 00041 EU 2001 5 3 RYMR32642 1 20010106 G 6420 350A33214501 CONTROL ROD SNIAS 350 AS350B3 8680954 EU PITCH CONTRL WORN B R7MA K NONE O OTHER IN INSP/MAINT 1 NM 07 52285 505 3251 WORN BEYOND SERVICEABLE LIMITS. REMOVED AND REPLACED WITH NEW UNIT, CORRECTED PROBLEM. 1 G 7 1 3U H9EU 2001072400523 20010724 00523 NM 2001 7 24 S012730131 1 20010403 G 7100 FCU BOEING 747 747209B NM PWA JT9 JT9D7R4G2 52054 NE W SAJF E ENGINE SHUTDOWN X ENGINE FLAMEOUT CR CRUISE 1 WP 03 24628 725343 B-18771 #2 ENG FLAME OUT AT FL330,TAT -4C,EGT 352 DEG.C,EPR 1.02 & DROPPING,ENG SHUTDOWN,WINDMILLED APPROX. 1 MIN AT OIL PRESS 22 PSI,ENG WAS RESTARTED & OPERATED NORMALLAY.C/A:1.I.A.W AMM 71-00-43,MAIN FUEL FILTER AND EVBC FUEL FILTER INSP ED NML AND REPLACED. 2.CHECKED EVBC PT3 AND PS3 WATER TRAP,NO WATER EVIDENCE FOUND. 3.PFMED FUEL TANKS WATER DRAINING. 4 .REPLACED FUEL CONTROL UNIT AND FUEL PUMP ASSY. 5.REPLACED FUEL HEATER DUE MOUNT BOLTS INSERT DAMAGED. 6.PFMED WINDMILLI NG INSP,MAIN OIL FILTER AND ALL MAGNETIC CHIP DETECTORS INSPED NML. 7.ENG RUN-UP TEST WITH TAKEOFF POWER SATISFACTORY. 8 .AFTER TEST OF REMOVED PARTS FOR FINAL INVESTIGATION,THE MAIN CAUSE OF THE IFSD APPEARS TO BE A LEAN FCU ALONG WITH PO 2 L 7 4 4F 4 F RT A20WE E3NE 2001061400019 20010614 00019 NE 2001 6 14 S01472016 2 20010426 G 7200 ENGINE BOEING 747 747400 NM PWA 4056 PW4056 NE NR 4 FAILED W SAJF C ABORTED TAKEOFF R J PARTIAL RPM/PWR LOSS WARNING INDICATION TO TAKEOFF 1 WP 03 40413 24311 717621 COMPLETE REGISTRATION NUMBER (B18273) AFTER T/O THRUST HAS SET ON T/O ROLLING, LOUD BANG SOUND WAS HEARD, T/O IS ABORTED AT 110 KNOTS. (1) IAW FIM 71-00-00, ENGINE SURGE DURING FORWARD THRUST FIG 107 PERFORM ENGINE 4 INLET FAN BLADE, FAN CA SE DUCT SEGMENTS, TURBINE EXHAUST AREA AND 6TH TURBINE BLADE INSP NORMAL. (2) BORESCOPE INSP (HPC 5,6,10TH STAGE AND HPT 1,2ND STAGE: LPT 3RD STAGE BLADE), CONDITION NORMAL. (3)2.5 AND 2.9 BLEED VALVE AND VSV SYS CHECK NORMAL. (4 )REPLACE D NR 4 ENGINE AND RUN UP CHECK NORMAL. 2 L 7 4 4F 4 F RT A20WE E24NE 2001011102735 20010111 02735 CE 2001 1 11 SAILJ1052 1 20010102 G 3230 508200646 TORQUE TUBE RAYTHN NA BEECH 90 C90 1152913 CE PWA PT6 PT6A21 52043 EA HARTZL HCB3T HCB3TN3 GL MLG CRACKED B K NONE O OTHER IN INSP/MAINT 1 SO 13 6356C 5726 NA LJ1052 AIRCRAFT CAME INTO MAINTENANCE FOR SCHEDULED TBO OF THE LANDING GEAR MOTOR. THE MOTOR IS ATTACHED TO THE LANDING GEAR GE ARBOX WHICH IS ALSO ATTACHED TO THE FAILED TORQUE TUBE. INSPECTION SHOWED NO EVIDENCE OF CORROSION. FAILURE AREA IS LOCA TED AT AND AROUND THE ATTACH HARDWARE HOLES HOWEVER,INSPECTION REVEALED NO EVIDENCE OF IMPOPER INSTALLATION, ALIGNMENT, BINDING OR CONDITION THAT MIGHT BE ATTRIBUTE TO THE FAILURE. A COPY OF THIS REPORT WAS PROVIDED TO LOCAL FSDO 13 WEST CO LUMBIA, SC. ASI/BOB SWITTER/ASI BILL ROBERTS FOR THEIR REVIEW. NO INCIDENT OR INJURY WAS INVOLVED. 1 L 7 2 3T 4 T 3A20 E4EA 6 C P15EA 2001011100563 20010111 00563 NM 2001 1 11 SROM200100001 1 20010102 G 3230 65446916 HYDROMECH UNIT BOEING 737 737205 NM NLG MALFUNCTIONED C SROM A UNSCHED LANDING J WARNING INDICATION CL CLIMB 1 AL 03 733AR 6 23466 DEPARTING ANC NOSE GEAR WOULD NOT RETRACT - STAYED DOWN & LOCKED - TRIED TWICE WITH SAME RESULTS. RETURNED TO ANC LANDI NG WT 111.7 SMOOTH LANDING.ACCOMPLISHED OVERWEIGHT LANDING INSPECTION PER M/M 5-51-291. REPLACED NOSE GEAR HYD. MODULAR PACKAGE REF. MM 32-33-31. REPLACED NOSE GEAR ACT. FLOW RESTRICTOR REF. MM 32-00. REPLACED NG GRAVEL DEFLECTOR ACTU. R EF. MM SUP. 32-23-22NOTE: MODULAR PACKAGE REPLACED TO CORRECT PROBLEM - RESTRICTOR AND ACTUATOR REPLACEMENT WERE PRECAU TIONARY. 2 L 7 2 4F A16WE 2001011100589 20010111 00589 NM 2001 1 11 SROM200100002 1 20010104 G 3233 ACTUATOR BOEING 737 737205 NM NLG FAILED C SROM A UNSCHED LANDING J WARNING INDICATION CL CLIMB 1 AL 03 733AR 23466 AIR TURNBACK DUE TO NOSE GEAR WOULD NOT RETRACT THIS IS A REPEAT EVENT THAT LAST HAPPENED 7 LANDINGS AGO. REPLACED NOS E GEAR LOCK MECHANISM AND SPRINGS, CONSISTING OF INDIVIDUAL ITEMS P/N 65-46245-4, 65-46242-11, 65-46240-13 & 69-6745-1, ALL WITH 1327 HOURS AND 1009 LANDINGS SINCE OVERHAUL. REPLACED HYDRAULIC TRANSFER CYCLINDER P/N 69-14106-7 WITH 10 HOUR S AND 7 LANDINGS SINCE OVERHAUL. REPLACED LOCK ACTUATOR P/N 65-17819-14 WITH 1327 HOURS AND 1009 LANDINGS SINCE OVERHAU L. RE-RIGGED NOSE GEAR DOORS. PERFORMED NORMAL RETRACTION AND EXTENSION TESTS. PERFORMED EMERGENCY EXTENSION TEST. A LL TESTS NORMAL. 2 L 7 2 4F A16WE 2001040900181 20010409 00181 NM 2001 4 9 SROM200100003 1 20010201 G 3350 58782 LEAD BOEING 737 737205 NM CABIN FAILED C SROM K NONE L NO TEST IN INSP/MAINT 1 AL 03 733AR 6 23466 FLOOR TRACK LIGHTING - FORWARD CABIN INOP REPLACED FORWARD TRACE STRIP. OPS CHECKED OK FOUND OPEN IN ELECTRICAL CIRCUI T OF STRIP. 2 L 7 2 4F A16WE 2001040900061 20010409 00061 NM 2001 4 9 SROM200100004 1 20010202 G 3350 1010425 LENS BOEING 737 737205 NM CABIN BROKEN C SROM K NONE O OTHER IN INSP/MAINT 1 AL 03 736BP 3 23465 OVERHEAD ENERGENCY LIGHT ROW 2 IS BROKEN NOTE: LENS ONLY BROKEN. REPLACED UNIT P/N 10-1042-5. EMER LT OPS CK GOOD. 2 L 7 2 4F A16WE 2001050200050 20010502 00050 NM 2001 5 2 SROM200100005 1 20010308 G 3222 65737625 STRUT BOEING 737 737290C 138448V NM NLR DISCHARGED C SROM A UNSCHED LANDING J WARNING INDICATION CL CLIMB 1 AL 03 740AS 58172 3 22578 AFTER TAKEOFF NOSE GEAR DID NOT LOCK UP, RED NOSE GEAR LIGHT ON, SYS A PRESURE NORMAL BUT FLUCTUATING SLIGHTLY AND ABNOR MAL NOISES COMING FROM NOSE WHEEL, CYCLED GEAR DOWN 3 GREEN, RETRACTED SAME PROBLEM, LANDED NORMALLY. FOUND NOSE STRUT FLAT, ACCOMPLISHED NOSE GEAR STRUT SERVICE PER TASK CARD 18232017. ACCOMPLISHED GEAR RETRACT & FREE FALL TEST, OPS CHE CKS GOOD, REMOVED NOSE GEAR JACK AND PAR. CHANGES SCHRADER VALVE. 2 L 7 2 4F A16WE 2001050200062 20010502 00062 2001 5 2 SROM200100006 4 20010319 G 3422 8221088001 INDICATOR BOEING 737 737205 NM COCKPIT FAILED C SROM A UNSCHED LANDING O OTHER CR CRUISE 1 AL 03 736BP 1 1 23465 DURING NORMAL CRUISE FLIGHT, 45 MINUTES INTO THE FLIGHT, THE FIRST OFFICIERS 5ATI EHSI WENT BLACK, FLICKERED BACK ON MOM ENTARILY A FEW TIMES AND THEN STAYED BLACK. THIS WAS A NEW DISPLAY ON ITS FIRST FLIGHT. 2 L 7 2 4F A16WE 2001041800298 20010418 00298 NM 2001 4 18 SROM200100007 1 20010223 G 5311 65582805 FRAME BOEING 737 737205 NM PWA JT8 JT8D17 52049 NE FUSELAGE CORRODED C SROM K NONE O OTHER IN INSP/MAINT 1 AL 03 736BP 23465 DURING C CHECK INSPECTION, FOUND CORROSION ON FRAME. 2 L 7 2 4F 4 F A16WE E2EA 2001041800299 20010418 00299 NM 2001 4 18 SROM200100008 1 20010223 G 5310 694820416 SHEAR TIE BOEING 737 737205 NM PWA JT8 JT8D17 52049 NE FUSELAGE CORRODED C SROM K NONE O OTHER IN INSP/MAINT 1 AL 03 736BP 23465 DURING C CHECK, FOUND CORROSION ON SHEAR TIE. 2 L 7 2 4F 4 F A16WE E2EA 2001041800300 20010418 00300 NM 2001 4 18 SROM200100009 1 20010223 G 5320 65582806 ANGLE BOEING 737 737205 NM PWA JT8 JT8D17 52049 NE FUSELAGE CORRODED C SROM K NONE O OTHER IN INSP/MAINT 1 AL 03 736BP 23465 DURING C CHECK INSPECTION, FOUND LEVEL 1 CORROSION ON ANGLE. 2 L 7 2 4F 4 F A16WE E2EA 2001041800302 20010418 00302 NM 2001 4 18 SROM200100010 1 20010223 G 5313 6948948501 STRINGER BOEING 737 737205 NM PWA JT8 JT8D17 52049 NE FUSELAGE CORRODED C SROM K NONE O OTHER IN INSP/MAINT 1 AL 03 736BP 23465 DURING C CHECK INSPECTION, FOUND CORROSION ON STRINGER. 2 L 7 2 4F 4 F A16WE E2EA 2001041800303 20010418 00303 NM 2001 4 18 SROM200100011 1 20010307 G 5743 658276415 BEAM BOEING 737 737205 NM PWA JT8 JT8D17 52049 NE LT MLG CORRODED C SROM K NONE O OTHER IN INSP/MAINT 1 AL 03 736BP 29717 23465 DURING C CHECK INSPECTION, FOUND THE LEFT MLG BEAM HAS SEVERAL AREA OF LEVEL 1 CORROSION ON LOWER SURFACE AT PANEL MOU NTING HOLES. 2 L 7 2 4F 4 F A16WE E2EA 2001041800309 20010418 00309 NM 2001 4 18 SROM200100012 1 20010310 G 5330 SKIN BOEING 737 737205 NM PWA JT8 JT8D17 52049 NE FUSELAGE CRACKED C SROM K NONE O OTHER IN INSP/MAINT 1 AL 03 736BP 29717 23465 DURING C CHECK INSPECTION, FOUND A CRACK IN THE FORWARD GALLEY DOOR (R1) EXTERIOR SKIN AT LOWER HINGE CUTOUT CRACKED AT UPPER CORNER. 2 L 7 2 4F 4 F A16WE E2EA 2001041800304 20010418 00304 NM 2001 4 18 SROM200100013 1 20010310 G 5330 SKIN BOEING 737 737205 NM PWA JT8 JT8D17 52049 NE FUSELAGE CRACKED C SROM K NONE O OTHER IN INSP/MAINT 1 AL 03 736BP 29717 23465 DURING C CHECK INSPECTION, FOUND A CRACK IN SKIN AT UPPER HINGE CUTOUT ON THE FORWARD GALLEY DOOR. 2 L 7 2 4F 4 F A16WE E2EA 2001041800305 20010418 00305 NM 2001 4 18 SROM200100014 1 20010312 G 5330 6546881143 SKIN BOEING 737 737205 NM PWA JT8 JT8D17 52049 NE FUSELAGE CRACKED C SROM K NONE O OTHER IN INSP/MAINT 1 AL 03 736BP 29717 23465 DURING C CHECK INSPECTION, FOUND SKIN DAMAGE/CRACK AT THE FORWARD APU DOOR HINGE CUTOUT. 2 L 7 2 4F 4 F A16WE E2EA 2001041000272 20010410 00272 NM 2001 4 10 SROM200100015 1 20010312 G 5330 6546881143 SKIN BOEING 737 737205 NM FUSELAGE CRACKED C SROM K NONE O OTHER IN INSP/MAINT 1 AL 03 736BP 29717 23465 DURING C CHECK INSPECTION FOUND SKIN DAMAGE/CRACK AT APU DOOR AFT HINGE CUTOUT. 2 L 7 2 4F A16WE 2001041800306 20010418 00306 NM 2001 4 18 SROM200100016 1 20010313 G 5330 655298873 SKIN BOEING 737 737205 NM PWA JT8 JT8D17 52049 NE FUSELAGE CRACKED C SROM K NONE O OTHER IN INSP/MAINT 1 AL 03 736BP 23465 DURING C CHECK INSPECTION, FOUND A SKIN CRACK AT AFT ENTRY DOOR (L2) CUTOUT (LOWER). 2 L 7 2 4F 4 F A16WE E2EA 2001042400266 20010424 00266 NM 2001 4 24 SROM200100017 1 20010323 G 5343 65465431 ATTACH FITTING BOEING 737 737205 NM FUSELAGE CORRODED C SROM K NONE O OTHER IN INSP/MAINT 1 AL 03 733AR 29449 3332 23466 DURING C CHECK INSPECTION FOUND CORROSION ON BORE AND FACES OF BS 685 LUG, LT. REPAIRED PER EA 5310-01930. 2 L 7 2 4F A16WE 2001042400267 20010424 00267 NM 2001 4 24 SROM200100018 1 20010323 G 5330 654576960 SKIN BOEING 737 737205 NM FUSELAGE CORRODED C SROM K NONE O OTHER IN INSP/MAINT 1 AL 03 733AR 29449 3332 23466 DURING C CHECK INSPECTION, FOUND LEVEL 1 CORROSION ON SKIN. REPAIRED PER EA 5330-01517. 2 L 7 2 4F A16WE 2001042400268 20010424 00268 NM 2001 4 24 SROM200100019 1 20010403 G 5720 656717217 FITTING BOEING 737 737205 NM LT WING CORRODED C SROM K NONE O OTHER IN INSP/MAINT 1 AL 03 733AR 29449 3332 23466 DURING C CHECK INSPECTION, FOUND CORROSION ON ATTACH FITTING. REPLACED FITTING PER MM 57-15-50. 2 L 7 2 4F A16WE 2001042400269 20010424 00269 NM 2001 4 24 SROM200100020 1 20010321 G 5330 654577453 SKIN BOEING 737 737205 NM FUSELAGE GOUGED C SROM K NONE O OTHER IN INSP/MAINT 1 AL 03 733AR 29449 1704 23466 DURING C CHECK INSPECTION, FOUND FUSELAGE EXTERNAL SKIN GOUGE BS 830 STRINGER 22 LT. REPAIRED PER SRM 53-30-03 FIGURE 6 . 2 L 7 2 4F A16WE 2001042400270 20010424 00270 NM 2001 4 24 SROM200100021 1 20010321 G 5330 654577453 SKIN BOEING 737 737205 NM FUSELAGE GOUGED C SROM K NONE O OTHER IN INSP/MAINT 1 AL 03 733AR 29449 1704 23466 DURING C CHECK INSPECTION, FOUND FUSELAGE EXTERNAL SKIN GOUGED AT BS 890 STRINGER 21 LT. REPAIRED PER SRM 53-30-03 FIGU RE 6. 2 L 7 2 4F A16WE 2001042400271 20010424 00271 NM 2001 4 24 SROM200100022 1 20010323 G 5743 656717218 FITTING BOEING 737 737205 NM LT WING CORRODED C SROM K NONE O OTHER IN INSP/MAINT 1 AL 03 733AR 29449 3332 23466 DURING C CHECK INSPECTION AND MAIN LANDING GEAR TIME CHANGE, FOUND FACES OF RT MLG I/B STABILIZER AFT MOUNT FITTING COR RODED. REPLACED FITTING PER MM 57-15-0/SOPM 20-50-01 DWG 65-82770. 2 L 7 2 4F A16WE 2001092500035 20010925 00035 2001 9 25 SROM200100023 4 20010522 G 3420 8221088001 DISPLAY BOEING 737 737205 NM COCKPIT FAILED C SROM A UNSCHED LANDING O OTHER CR CRUISE 1 AL 03 736BP 299 299 23465 CAPTAINS 5 ATI EHSI FAILED IN CRUISE FLIGHT. INSTUMENT DISPLAY WAS STILL PRESENTED, BUT WAS NON-FUNCTIONAL WITH A "DU F AILURE" ANNUNCIATOR LIT. REPLACEMENT UNIT CORRECTED THE PROBLEM. 2 L 7 2 4F A16WE 2001092500036 20010925 00036 NM 2001 9 25 SROM200100025 1 20010712 G 3350 58209 LIGHT BOEING 737 737205 NM CABIN DEFECTIVE C SROM K NONE L NO TEST IN INSP/MAINT 1 AL 03 733PA 6 23466 L1 EXIT LIGHT AT BOTTOM RIGHT CORNER IS VERY DIM. REPLACED BATTERY PACK AND LIGHT/LENS, ALSO REPAIRED BROKEN WIRE AT CO NNECTOR. PERFORMED OPS CHECK WITH NO AMBIENT LIGHT, BRIGHTNESS EQUAL TO OTHER EXIT SIGNS. 2 L 7 2 4F A16WE 2001092500037 20010925 00037 NM 2001 9 25 SROM200100026 1 20010821 G 2910 106056342 LINE BOEING 737 737205 NM HYD SYSTEM CHAFED C SROM H A DEACTIVATE SYST/CIRCUITS UNSCHED LANDING K J FLUID LOSS WARNING INDICATION CR CRUISE 1 AL 03 736BP 1 23465 DURING NORMAL CRUISE FLIGHT LEFT "A" SYSTEM HYDRAULIC LOW PRESSURE LIGHT ILLUMINATED, LEFT "A" SYSTEM PUMP TURNED OFF AN D NOTICED QUNTITY WAS LOW, THEN "A" SYSTEM RIGHT SIDE STARTED TO FLUCUATE AND SHUT DOWN WITH RETURN TO ANC. INSPECTION FOUND PRESSURE LINE CHAFFED THRU AT GENERATOR BLAST TUBE SUPPORT JUST AFT OF PUMP. REPLACE LINE. AND ADDED CLAMP STAND OFF. REPLACED CASE DRAIN FILTER WHICH WAS FOUND CLEAN. OPS AND LEAK CHECKED GOOD. REFILLED HYD SYSTEM. REF. 29-11-41 . 2 L 7 2 4F A16WE 2001100900035 20011009 00035 NM 2001 10 9 SROM200100027 1 20011008 G 5210 694070310 COVER BOEING 737 737205 NM PAX DOOR BROKEN C SROM A UNSCHED LANDING O OTHER CL CLIMB 1 AL 03 736BP 47 23465 "EXTREMELY LOUD AIR LEAK FROM L1 DOOR. RETURNED TO PANC." INSP FOUND L-1 DOOR LOWER HINGE TOP TRIM PIECE HAD BROKEN LOOSE AND JAMMED IN DOOR HINGE. REPLACED HINGE FLAP ASSY. PRESS A/C NO LEAKS. 2 L 7 2 4F A16WE 2002012900152 20020129 00152 NM 2002 1 29 SROM200100028 1 20011101 G 3233 6544604 ACTUATOR BOEING 737 737205 1384456 NM MLG DEFECTIVE C SROM A UNSCHED LANDING J WARNING INDICATION CL CLIMB 1 AL 03 733PA 1084 23466 ON GRAVEL DEFLECTOR EQUIPED AIRCRAFT NOSE GEAR WOULD NOT LOCK UP AFTER T/O. CYCLED GEAR WITH SAME RESULTS. NOSE GREEN LIGHT GOES OUT, BUT RED LIGHT STAYS ON WITH AIR NOISE HEARD. GEAR LOCKED DOWN OK. REMOVED AND REPLACED NOSE GEAR GRA VEL DEFLECTOR ACTUATOR PER MM 32-23-22. LUBED NOSE GEAR PER TASK CARD 18212000. OPS CK PER TASK 18132003. EMERGENCY EXTENSION CK GOOD. FOUND STRUT FLAT SERVICED PER A/C PLACARD. 2 L 7 2 4F RT A16WE 2002012900153 20020129 00153 NM 2002 1 29 SROM200100029 1 20011123 G 3222 657376210 MODULE BOEING 737 737205 1384456 NM NLG INTERMITTENT A SROM A UNSCHED LANDING J WARNING INDICATION CL CLIMB 1 AL 03 733PA 2795 23466 ON GRAVEL DEFLECTOR EQUIPED AIRCRAFT "ON DEPARTURE FROM ANCHORAGE NOSE WHEEL WOULD NOT RETRACT CYCLED GEAR ONCE, NOSE WH EEL WOULD NOT RETRACT, RETURNED TO AIRPORT FOR OVERWEIGHT LANDING WAS SMOOTH AND NORMAL". AIRCRAFT PLACED ON JACKS AND GEAR TESTED NORMAL. AS PRECAUTION REPLACED NLG MODULAR PACKAGE, AND LUBED GEAR. GEAR AGAIN TESTED NORMAL. 2 L 7 2 4F RT A16WE 2002013000022 20020130 00022 NM 2002 1 30 SROM200100030 1 20011125 G 3220 657376210 LANDING GEAR BOEING 737 737205 1384456 NM NOSE INOPERATIVE C SROM A UNSCHED LANDING J WARNING INDICATION CL CLIMB 1 AL 03 733PA 2796 23466 ON GRAVEL DEFLECTOR EQUIPED AIRCRAFT "NOSE LANDING GEAR WOULD NOT RETRACT AFTER TAKEOFF - RETURNED TO AIRPORT". 2 L 7 2 4F RT A16WE 2002013000023 20020130 00023 NM 2002 1 30 SROM200100031 1 20011213 G 3220 657376210 LANDING GEAR BOEING 737 737205 1384456 NM NOSE CONTAMINATED C SROM A UNSCHED LANDING J WARNING INDICATION CL CLIMB 1 AL 03 733PA 2869 23466 ON GRAVEL DEFLECTOR EQUIPED AIRCRAFT "NOSE GEAR RED LIGHT STAYED ON AFTER GEAR RETRACTION (GEAR SOUNDED LIKE IT DID NOT RETRACT COMPLETELY) RECYCLED GEAR SAME PROBLEM. RETURNED TO ANC LANDING WT. WAS 109.7. INSP. FOUND SLUSH IN GEAR ARE A (NOSE) AND STRUT WAS A LITTLE LOW. CLEANED GEAR OF SLUSH AND RESET NOSE STRUT PRESS. LUBED NOSE GEAR CYCLED NOSE SEV ERAL TIMES OPS CK GOOD. 2 L 7 2 4F RT A16WE 2001041900134 20010419 00134 SW 2001 4 19 SW152001 1 20010321 G 6510 476441809 SHAFT BELL 47 47 1180602 SW TAIL ROTOR FAILED G HFZS B R EMER. DESCENT AUTOROTATION D F INFLIGHT SEPARATION FLT CONT AFFECTED UK UNKNOWN 1 SW 15 1575 73 TAIL ROTOR DRIVE FAILURE. TAIL ROTOR FORWARD SHAFT, AFT COUPLING FAILURE. LOSS OF LUBRICATION DUE TO STRIPPED TREADS ON SCREW ILLUSTRATED PARTS BREAKDOWN. 1 G 7 1 3O H1 2001051000249 20010510 00249 WP 2001 5 10 SW15200110389 1 20010315 G 6230 369D22014 MAST HUGHES 369 369E 4470707 WP ALLSN 250C 250C20B 03013 GL MAIN ROTOR FLAKING H K NONE O OTHER IN INSP/MAINT 1 SW 15 500TP 5200 5200 0494E CAE836593 COATING FLAKING OFF INNER DIAMETER OF MAIN ROTOR STATIC MAST. COATING CHIPS FALLING INTO MAIN ROTOR TRANSMISSION. CAUS E OF FLAKING, UNKNOWN. NO FACTORY REPAIR AUTHORIZED IN THE MHI. FACTORY REPS HAVE NOT YET AUTHORIZED A REPAIR. EFFECT ON MAST AND TRANSMISSION. 1 G 7 1 3U 3 U H3WE E4CE 2001051000248 20010510 00248 WP 2001 5 10 SW15200110390 1 20010315 G 6230 369D22014 MAST HUGHES 369 369E 4470707 WP ALLSN 250C 250C20B 03013 GL MAIN ROTOR FLAKING H K NONE O OTHER IN INSP/MAINT 1 SW 15 600TP 5200 5200 525 CAE836593 COATING FLAKING OFF INNER DIAMETER OF MAIN ROTOR STATIC MAST. COATING CHIPS FALLING INTO MAIN ROTOR TRANSMISSION. CAUS E OF FLAKING UNKNOWN. NO FACTORY REPAIR AUTHORIZED IN THE HMI. FACTORY REPS HAVE NOT YET AUTHORIZED A REPAIR. EFFECT ON MAST AND TRANSMISSION? 1 G 7 1 3U 3 U H3WE E4CE 2001050300135 20010503 00135 CE 2001 5 3 SW15200110531 1 20010326 G 5330 002440000143 DOUBLER BEECH 33 35C33 1151408 CE CONT O470 IO470* 17026 SO FUSELAGE CRACKED H K NONE O OTHER IN INSP/MAINT 1 SW 15 94SS 9446 CD1089 DURING 100 HOUR INSPECTION FOUND CRACKS IN THE DOUBLER TALL PN 002440000143. THE DOUBLER IS CRACKED JUST FORWARD OF THE AFT BULKHEAD APPROX 1 INCH JUST BEFORE THE RADIUSED AREA EXTENDING OUTBOARD .2500. 1 L 7 1 3O 3 O 3A15 E1CE 2001050300149 20010503 00149 CE 2001 5 3 SW15200110535 1 20010326 G 5520 639204 BUSHING BEECH 33 35C33 1151408 CE CONT O470 IO470* 17026 SO COUNTERWEIGHT IMPROPER PART H K NONE O OTHER IN INSP/MAINT 1 SW 15 94SS CD1089 THE INCORRECT BUSHING WAS IDENTIFIED DURING DEMINSIONAL INSPECTION OF THE COUNTER- WEIGHT PRIOR TO INSTALLATION. 1 L 7 1 3O 3 O 3A15 E1CE 2001050300003 20010503 00003 CE 2001 5 3 SW15200110536 1 20010328 G 5312 00244002465 BULKHEAD BEECH 33 35C33 1151408 CE CONT O470 IO470* 17026 SO FUSELAGE CRACKED H K NONE O OTHER IN INSP/MAINT 1 SW 15 1444M 7583 CD827 DURING 100 HOUR INSPECTION FOUND CRACKS IN THE DOUBLER TAIL, A CRACK ON THE RIGHT HAND SKIN SECTION AND A CRACK ON THE A FT BULKHEAD APPROX 1 INCH AT THE BEGINNING OF THE RADIUSED AREA RADIATING OUTBOARD .7500 ON THE RIGHT SIDE AND .5000 ON THE LEFT SIDE. THE SKIN SECTION IS CRACKED 1.75 INCH FROM THE AFT EDGE OF THE SKIN, JUST ABOVE THE CRACK IN THE DOUB LER EXTENDING OUTBOARD .7500 INCH. THE BULKHEAD CRACKS EXTENDS .3750 INCH DOWN THE RADIUSED AREA AT THE TOP LEFT HAND C ORNER. 1 L 7 1 3O 3 O 3A15 E1CE 2001050300315 20010503 00315 EA 2001 5 3 SW15200110851 2 20010405 G 7314 LW15473 PUMP PIPER PA28 PA28* SO LYC O360 IO360A1A 41514 EA FUEL SYSTEM DEFECTIVE D K NONE O OTHER IN INSP/MAINT 1 SW 15 0 L977336A PART INSTALLED NEW AT OVERHAUL. TEST CESS OPERATION WITHIN REQUIRED PRESSURE AND FLOW. AT INSTALLATION IN AIRCRAFT, PU MP WOULD NOT FUNCTION AND WOULD NOT ALLOW FUEL TO BE PUMPED THRU USING BOOST PUMP. 1 L 7 1 3O 3 O 2A13 1E10 2001080200086 20010802 00086 SO 2001 8 2 SW15200111824 1 20010425 G 3110 KNOB PIPER PA46 PA46310P 7104605 SO MOR CONTROL INOPERATIVE C K NONE O OTHER IN INSP/MAINT 1 SW 15 184AL 4697026 MANUAL OVER RIDE (MOR) CONTROL LEVER KNOB CAME APART CAUSING THIS SYSTEM TO BE RENDERED INOPERATIVE AND A CERTAIN SAFETY ISSUE. PROBLEM CAN BE SOLVED WITH PROPER INSTALLATION. THIS AIRCRAFT JUST COMPLETED A PHASE I AND II INSPECTION. 1 L 7 1 3O RT A25SO 2001080200087 20010802 00087 CE 2001 8 2 SW15200112233 1 20010423 G 6123 B15941 SPRING HARTZL BEECH 95 95B55 1152729 CE FEATHERING SPRNG CORRODED C K NONE O OTHER IN INSP/MAINT 1 SW 15 2023Z EB488 TC2171 UPON DISASSEMBLY OF THIS PROPELLER FOR OVERHAUL IT WAS NOTED THAT THIS FEATHERING SPRING WAS BROKEN AND SHOWS SIGNS THAT IT HAS BEEN BROKEN FOR SOME TIME. THE BREAK WAS BETWEEN THE 1ST AND 2ND COIL AND WAS ALSO CORRODED. 1 L 7 2 3O RT 3A16 2001080200089 20010802 00089 SO 2001 8 2 SW15200112234 1 20010427 G 6120 FORK HARTZL PIPER PA23 PA23160 7102304 SO PITCH CHANGE CRACKED C K NONE O OTHER IN INSP/MAINT 1 SW 15 76HK 3341 AY34B 231423 AT OVERHAUL THE PITCH CHANGE FORK NR B2457-3 WAS FOUND TO HAVE A CRACK APPROX. .1875 INCHES IN LENGTH LOCATED AT THE LOW ER INSIDE RADIUS OF THE NR 2 BLADE PITCH CHANGE SLOT. 1 L 7 2 3O 1A10 2001080200091 20010802 00091 GL 2001 8 2 SW15200112284 3 20010517 G 6110 BULKHEAD CESSNA 172 172D 2072410 CE LYC O320 O320* 41508 EA MCAULY 1C172 1C172EM GL PROPELLER CRACKED G K NONE O OTHER IN INSP/MAINT 1 SW 15 54855 497 497 17275068 FORWARD PROPELLER BULKHEAD HAS BEEN CRACKING WITH MINIMAL HOURS. BOLTS HAVE BEEN PROPERLY TORQUED AND SAFETY WIND. 1 H 7 1 3O 3 O NT 3A12 E274 5 N P910 2001080200093 20010802 00093 CE 2001 8 2 SW15200112285 1 20010516 G 5541 04330106 SPAR CESSNA 150 152 2071835 CE RUDDER CRACKED D K NONE O OTHER IN INSP/MAINT 1 SW 15 49780 4684 15281314 CRACK IN UPPER LIGHTING HOLE, UNDER THE TOP HINGE, IN THE LEADING EDGE RUDDER SKIN/SPAR. TO PREVENT RECURRANCE, REMOVE OR ELEMINATE LIGHTING HOLE IN NEW OR REPLACEMENT PARTS. 1 H 7 1 3O NT 3A19 2001092500058 20010925 00058 EU 2001 9 25 TI1R001403 1 20010122 G 6240 1179405303 TACHOMETER BOLKMS 117 BK117A1 5626010 EU COCKPIT FAILED B TI1R O OTHER O OTHER NR NOT REPORTED 1 SW 05 TRIPLE TACHOMETER - ROTOR TACHOMETER FAILED. REMOVED AND REPLACED. 1 G 7 2 3U H13EU 2001082100055 20010821 00055 2001 8 21 TI1R001405 4 20010221 G 3416 1042011968E ALTIMETER COCKPIT INOPERATIVE B TI1R O OTHER J WARNING INDICATION NR NOT REPORTED 1 SW 05 ALTIMETER, ENCO - CODE OFF FLAG WILL NOT STOW. REMOVED AND REPLACED. 2001082100063 20010821 00063 2001 8 21 TI1R001428 4 20010409 G 3421 5040017926 LIGHT BOLKMS 117 BK117B2 5626013 EU ATTITUDE GYRO INOPERATIVE B TI1R O OTHER O OTHER NR NOT REPORTED 1 SW 05 117MK 7196 ATTITUDE GYRO, INTERNAL LIGHTING, INOPERATIVE. REMOVED AND REPLACED. 1 G 7 2 3U NC H13EU 2001091300273 20010913 00273 EU 2001 9 13 TI1R001441 1 20010407 G 7810 3039621 CLAMP UROCOP EC135 EC135P1 8680990 EU PWA PW206 PW206A NE EXHAUST CRACKED B TI1R K NONE O OTHER IN INSP/MAINT 1 SW 05 911SV 0070 EXHAUST CLAMP, CRACK ON BAND END. REMOVED AND REPLACED. 1 G 7 2 3U 3 U O H88EU E42NE 2001092500101 20010925 00101 EU 2001 9 25 TI1R001442 1 20010424 G 2810 L281M20C1002 TANK UROCOP EC135 EC135P1 8680990 EU PWA PW206 PW206A NE MAIN FUEL CELL LEAKING B TI1R K NONE K FLUID LOSS IN INSP/MAINT 1 SW 05 911SV 0070 MAIN TANK LEAKING. REMOVED AND REPLACED. 1 G 7 2 3U 3 U O H88EU E42NE 2001091300275 20010913 00275 EU 2001 9 13 TI1R001444 1 20010409 G 6230 L623M2005101 SWASHPLATE UROCOP EC135 EC135P1 8680990 EU PWA PW206 PW206A NE MAIN ROTOR EXCESS PLAY B TI1R O OTHER O OTHER NR NOT REPORTED 1 SW 05 911SV 1034 0070 SWASHPLATE, REMOVED AT AEC REQUEST, EXCESSIVE PLAY. REMOVED AND REPLACED. 1 G 7 2 3U 3 U O H88EU E42NE 2001092500102 20010925 00102 EU 2001 9 25 TI1R001445 1 20010409 G 5320 4649305034 SUPPORT UROCOP EC135 EC135P1 8680990 EU PWA PW206 PW206A NE SUPPORT TUBE LOOSE B TI1R K NONE O OTHER IN INSP/MAINT 1 SW 05 911SV 0070 SUPPORT TUBE, REMOVED AT AEC REQUEST, EXCESSIVE PLAY BETWEEN SUPPORT TUBE AND SLIDING TUBE. REMOVED AND REPLACED. 1 G 7 2 3U 3 U O H88EU E42NE 2001092500103 20010925 00103 EU 2001 9 25 TI1R001446 1 20010409 G 6220 L623M1002105 CLAMP UROCOP EC135 EC135P1 8680990 EU PWA PW206 PW206A NE MAIN ROTOR INOPERATIVE B TI1R K NONE O OTHER IN INSP/MAINT 1 SW 05 911SV 0070 ROTOR SCISSOR CLAMP, REMOVED AT AEC REQUEST, REMOVED AND REPLACED. 1 G 7 2 3U 3 U O H88EU E42NE 2001092500104 20010925 00104 EU 2001 9 25 TI1R001447 1 20010422 G 3240 10477665 CYLINDER UROCOP EC135 EC135P1 8680990 EU PWA PW206 PW206A NE BRAKE ASSY LEAKING B TI1R K NONE K FLUID LOSS IN INSP/MAINT 1 SW 05 911SV 1231 0070 BRAKE CYLINDER, LEAKING FLUID, REMOVED AND REPLACED. 1 G 7 2 3U 3 U O H88EU E42NE 2001092500106 20010925 00106 EU 2001 9 25 TI1R001449 1 20010503 G 5320 11780184111 SPACER BOLKMS 117 BK117A1 5626010 EU FUSELAGE MISMANUFACTURED B TI1R K NONE W INADEQUATE Q C IN INSP/MAINT 1 SW 05 SPACER - SPACERS HAVE NO GROOVE CUT INTO THEM FOR THE ORING. REMOVED AND REPLACED. 1 G 7 2 3U H13EU 2001092500113 20010925 00113 EU 2001 9 25 TI1R001464 1 20010428 G 2822 9A2045 CARTRIDGE UROCOP EC135 EC135P1 8680990 EU PWA PW206 PW206A NE FUEL PUMP INOPERATIVE B TI1R K NONE O OTHER IN INSP/MAINT 1 SW 05 911SV 0070 FUEL PUMP CARTRIDGE, PUMP INOPERATIVE, TRIPS CIRCUIT BREAKER. 1 G 7 2 3U 3 U O H88EU E42NE 2001091300283 20010913 00283 2001 9 13 TI1R001467 4 20010512 G 3421 5040017926 GYRO BOLKMS 117 BK117B2 5626013 EU ATTITUDE TUMBLES B TI1R O OTHER O OTHER NR NOT REPORTED 1 SW 05 117MK 7196 ATTITUDE GYRO, TUMBLING, REMOVED AND REPLACED. 1 G 7 2 3U NC H13EU 2001091300285 20010913 00285 EU 2001 9 13 TI1R001471 1 20010522 G 7714 L771M40C1005 INDICATOR UROCOP EC135 EC135P1 8680990 EU PWA PW206 PW206A NE TRIPLE TACH ERRATIC B TI1R O OTHER O OTHER NR NOT REPORTED 1 SW 05 911SV 0070 TRIPLE TACHOMETER INDICATOR, NR NEEDLE ERRATIC, REMOVED AND REPLACED. 1 G 7 2 3U 3 U O H88EU E42NE 2001091300286 20010913 00286 EU 2001 9 13 TI1R001472 1 20010526 G 2822 9A2045 CARTRIDGE UROCOP EC135 EC135P1 8680990 EU PWA PW206 PW206A NE FUEL PUMP FAULTY B TI1R O OTHER O OTHER NR NOT REPORTED 1 SW 05 911SV 0070 FUEL PUMP CARTRIDGE, POSITIVE TERMINAL GROUNDED, TRIPS BREAKER. REMOVED AND REPLACED. 1 G 7 2 3U 3 U O H88EU E42NE 2001091300287 20010913 00287 EU 2001 9 13 TI1R001473 1 20010526 G 2822 9A2045 CARTRIDGE UROCOP EC135 EC135P1 8680990 EU PWA PW206 PW206A NE FUEL PUMP INTERMITTENT B TI1R O OTHER O OTHER NR NOT REPORTED 1 SW 05 911SV 0070 FUEL PUMP CARTRIDGE, MOTOR INTERMITTENT, REMOVED AND REPLACED. 1 G 7 2 3U 3 U O H88EU E42NE 2001091300295 20010913 00295 2001 9 13 TI1R001481 4 20010618 G 3160 066040211411 SYMBOL GENERATOR BOLKMS 117 BK117B2 5626013 EU COCKPIT MALFUNCTIONED B TI1R O OTHER O OTHER NR NOT REPORTED 1 SW 05 117MK SIGNAL GENERATOR, INTERMITTENTLY CAUSES EFIS TO GO TO (TEST IN PROGRESS)-THEN ERROR OF SIGNAL ON EFIS T, REMOVED AND REP LACED. 1 G 7 2 3U NC H13EU 2001091300296 20010913 00296 2001 9 13 TI1R001482 4 20010616 G 3425 4021541671 INDICATOR COCKPIT DEFECTIVE B TI1R O OTHER O OTHER NR NOT REPORTED 1 SW 05 ARTIFICIAL HORIZON, HSI - WILL NOT STABILIZE, ROLLING RIGHT/ DIVING. REMOVED AND REPLACED. 2001091300297 20010913 00297 2001 9 13 TI1R001483 4 20010606 G 3422 060001500 GYRO DIRECTIONAL GYRO DAMAGED B TI1R K NONE W INADEQUATE Q C IN INSP/MAINT 1 SW 05 KG102A DIRECTIONAL GYRO - RECEIVED WITH CONNECTOR GUIDE PIN BROKEN AND LOOSE HARDWARE INSIDE AND SEAL ON BOTTOM. REMOVE D AND REPLACED. 2001091300301 20010913 00301 EU 2001 9 13 TI1R001488 1 20010410 G 2435 23081057 STARTER GEN UROCOP EC135 EC135P1 8680990 EU PWA PW206 PW206A NE ENGINE INOPERATIVE B TI1R O OTHER O OTHER NR NOT REPORTED 1 SW 05 911SV 1231 0070 STARTER GENERATOR, NEEDS BRUSH REPLACEMENT AND RUN-IN. 2000 TBO REMOVED AND REPLACED. 1 G 7 2 3U 3 U O H88EU E42NE 2001091300302 20010913 00302 2001 9 13 TI1R001489 4 20010628 G 3442 066308432 INDICATOR BOLKMS BK117 BK117C1 5626025 EU TMECA ARRIEL ARRIEL1 60030 NE RADAR INOPERATIVE B TI1R O OTHER O OTHER NR NOT REPORTED 1 SW 05 313LS 2773 7509 IN FLIGHT 6, INDICATION UNIT STOPS FUNCTIONING. SCREW FELL OUT FROM INSIDE. REMOVED AND REPLACED COLOR RADAR IND. 1 G 7 2 3U 3 U NC H13EU E19EU 2001080900257 20010809 00257 EU 2001 8 9 TXEA81788 1 20010423 G 6420 350A33200406 BEARING SNIAS 350 AS350BA 8680817 EU T/R SPIDER LOOSE H K NONE O OTHER IN INSP/MAINT 1 SW 09 22TV 10 1591 BEARING HAS PLAY. 1 G 7 1 3U NC H9EU 2002020500052 20020205 00052 GL 2002 2 5 V5MR198Y 1 20010924 G 3220 11799001 BRACKET CIRRUS SR SR22 2130001 GL NLG DAMAGED B V5MR K NONE O OTHER IN INSP/MAINT 1 GL 15 705CD 54 0005 NOSE WHEEL PANT BRACKETS, QTY 2, FOUND WITH ELONGATED MOUNTING HOLES UNDER NORMAL USE. AIRCRAFT HAS BEEN OPERATED BY A SINGLE INDIVIDUAL WITH MINIMAL TAKEOFFS AND LANDING IN APPROXIMATELY FOUR MONTHS TIME. FURTHERMORE, THE MOUNTING HOLES IN THE NEW REPLACEMENT PART ARE LARGER THAN THE AN3 BOLT THAT IS SPECIFIED TO SECURE IT TO THE FORK ASSEMBLY. THE HOLE IS LARGER THAN .1875 OF INCH (AN3) BUT SMALLER THAN .2500 OF AN INCH. NO BUSHINGS ARE SPECIFIED IN THE MFG IPC. 1 L 7 1 3O NT A00009CH 2002020500053 20020205 00053 GL 2002 2 5 V5MR198Y1 1 20010924 G 3220 11799001 BRACKET CIRRUS SR SR20 05628AJ GL CONT IO360 IO360* 17025 CE NLG ELONGATED B V5MR K NONE O OTHER IN INSP/MAINT 1 GL 15 6000C 244 1037 NOSE WHEEL PANT BRACKETS, QTY2, FOUND WITH ELONGATED MOUNTING HOLES UNDER NORMAL USE. AIRCRAFT HAS BEEN OPERATED BY A S INGLE INDIVIDUAL WITH MINIMAL TAKEOFFS AND LANDING IN APPROXIMATELY ONE YEARS TIME. FURTHERMORE, THE MOUNTING HOLES IN THE NEW REPLACEMENT PART ARE APPRECIABLY LARGER THAN THE AN3 BOLT THAT IS SPECIFIED TO SECURE IT TO THE FORK ASSEMBLY. THE HOLE IS LARGER THANT .1875 OF INCH BUT SMALLER THAN .2500 OF AN INCH. 1 L 7 1 3O 3 O NT A00009CH E1CE 2002020500054 20020205 00054 GL 2002 2 5 V5MR198Y2 1 20010924 G 3220 12936001 BUMPER BLOCK CIRRUS SR SR20 05628AJ GL CONT IO360 IO360* 17025 CE NLG DETERIORATED B V5MR K NONE O OTHER IN INSP/MAINT 1 GL 15 2014Y 344 1078 REBOUND BUMPERS, QTY 2, FOUND VERY DETERIORATED UNDER NORMAL USE. THEY WERE IN SERVICE FOR 344.4 HOURS IN LESS THAN ONE YEAR. THE AIRCRAFT IS OPERATED AS PART OF A CLUB AND SEES MANY TAKEOFF AND LANDING CYCLES. THE DETERIORATION COULD BE DUE TO INTERACTION WITH ENGINE SOLVENTS AND/OR HEAT. 1 L 7 1 3O 3 O NT A00009CH E1CE 2002020500055 20020205 00055 GL 2002 2 5 V5MR198Y3 1 20010924 G 3220 11799001 BRACKET CIRRUS SR SR20 05628AJ GL CONT IO360 IO360* 17025 CE NLG ELONGATED B V5MR K NONE O OTHER IN INSP/MAINT 1 GL 15 2014Y 402 1078 NOSE WHEEL PANT BRACKETS, QTY 2, FOUND WITH ELONGATED MOUNTING HOLES UNDER NORMAL USE. AIRCRAFT HAS BEEN OPERATED AS A CLUB AIRCRAFT WITH MANY TAKEOFFS AND LANDING IN LESS THAN ONE YEARS TIME. FURTHERMORE, THE MOUNING HOLES IN THE NEW REP LACEMENT PART ARE APPRECIABLY LARGER THAN THE AN3 BOLT THAT IS SPECIFIED TO SECURE IT TO THE FORK ASSEMBLY. 1 L 7 1 3O 3 O NT A00009CH E1CE 2002020500057 20020205 00057 GL 2002 2 5 V5MR198Y5 1 20010924 G 3220 12936001 BUMPER BLOCK CIRRUS SR SR20 05628AJ GL CONT IO360 IO360* 17025 CE NLG DETERIORATED B V5MR K NONE O OTHER IN INSP/MAINT 1 GL 15 197CD 344 1098 REBOUND BUMPERS, QTY 2, FOUND MISSING SINCE LAST INSPECTION. THEY WERE IN NORMAL SERVICE FOR 223.7 HOURS IN LESS THAN O NE YEAR. AIRCRAFT SEES MINIMAL TAKEOFF AND LANDING CYCLES. THE DETERIORATION AND SUBSEQUENT LOSS OF THE PARTS IN QUEST ION COULD BE DUE TO INTERACTION WITH ENGINE SOLVENTS AND/OR HEAT. DUE TO VIBRATION CAUSED BY SHIMMY OF THE NOSE LANDING GEAR STRUT ASSEMBLY PN 11907-003 OR BY SHIMMY OF A NOES WHEEL PANT THAT IS LOOSE ON ITS PANT BRACKETS PN 1179-001. 1 L 7 1 3O 3 O NT A00009CH E1CE 2001050900290 20010509 00290 SO 2001 5 9 WI2 2 20010422 G 7260 632617 GEAR CESSNA 337 337 2075702 CE CONT O360 IO360C 17025 SO ACCESSORY DRIVE WORN D K NONE O OTHER IN INSP/MAINT 1 GL 13 2364S 104 0664 060696R ACCESSORY DRIVE GEAR TEETH WORN AWAY 104 HOURS SINCE INSTALLATION. GEAR HAD BEEN INSTALLED DUE TO FAILURE OF PREVIOUS G EAR FOR THE SAME REASON. DRIVEN GEAR WAS NOT WORN. 1 H 7 2 3O 3 O A6CE E1CE 2001050900291 20010509 00291 SO 2001 5 9 WI3 2 20010427 G 7260 632617 GEAR CESSNA 337 337 2075702 CE CONT O360 IO360C 17025 SO ACCESSORY DRIVE WORN D K NONE O OTHER IN INSP/MAINT 1 GL 13 2397S 317 0697 060694R ACCESSORY DRIVE GEAR TEETH WORN AWAY 317 HOURS SINCE FACTORY REBUILD OF ENGINE. DRIVEN GEAR WAS NOT WORN. 1 H 7 2 3O 3 O A6CE E1CE 2001051500084 20010515 00084 SO 2001 5 15 WP012001B1728 1 20010102 G 3244 850X6 TIRE PIPER PA12 PA12 7101202 SO MLG MISMANUFACTURED G K NONE O OTHER IN INSP/MAINT 1 WP 01 3021M 121576 MOUNTED TWO GOODYEAR 8.50 X 6 6PR TIRES, PN856C61-3, ON CLEVELAND WHEELS. ONE TIRE APPEARED LARGER IN DIAMETER THAN TH E OTHER. MEASURED BOTH TIRES, AT 25PSI ONE TIRE IS 20.1250 AND THE OTHER IS 20.9375 IN DIAMETER. 1 H 7 1 3O A780 2001100900036 20011009 00036 SW 2001 10 9 WTXR200100277 1 20010926 G 2820 31024691 LINE SWRNGN SA226 SA226TC 8780404 SW GARRTT TPE331 TPE33110UA 01514 WP FUEL MANIFOLD CRACKED B WTXR K NONE K FLUID LOSS TX TAXI/GRND HDL 1 SW 99 332BA TC222E P54132 AFTER LANDING AND TAXING TO RAMP, PILOT NOTICED FLUID RUNNING OUT OF BOTTOM OF ENGINE COWLING. ENGINE WAS SHUT DOWN AND MAINTENANCE WAS CALLED.MAINTENANCE FOUND A CRACK IN THE FUEL MANIFOLD AT THE 6 O'CLOCK POSITION,IN THE "B" NUT FITTING N ECK. INSTALLED SERVICABLE MANIFOLD, LEAK CHECKED OK. 2 L 7 2 4T 4 T RT A8SW E4WE 2001080200117 20010802 00117 2001 8 2 WVBA2001034 4 20010521 G 2210 KA132 SWITCH ALIDSG PIPER PA31 PA31350 7103110 SO ACCEL SWITCH FAILED C WVBA O OTHER O OTHER NR NOT REPORTED 1 AL 01 42WP 2305 2305 3512 318252038 PILOT REPORTED SWITCH WOULD NOT TEST IN EITHER POSITION. SWITCH WAS REMOVED FROM SERVICE. PARTS TAKE FROM 3 TO 12 WEEK S TO BE DELIVERED RENDERING THE AUTOPILOT INOPEATIVE FOR THAT TIME FRAME. WITH SWITCHES FAILING RIGHT OUT OF THE BOX OR VERY FEW HOURS IN SERVICE, WE RECOMMEND ELIMINATING THIS SWITCH FRO THE SYSTEM AS THE AUTOPILOT CAN STILL BE PHYSICALLY OVERCOME OR MANUALLY CUT OFF BY A SWITCH ON THE YOKE. 1 L 7 2 3O A20SO 2001080200118 20010802 00118 SO 2001 8 2 WVBA2001035 1 20010521 G 2913 1213HBG310 PUMP PIPER PA31 PA31350 7103110 SO HYDRAULIC SYS FAILED C WVBA O OTHER J WARNING INDICATION NR NOT REPORTED 1 AL 01 300ED 192 317852008 PILOT REPORTED RIGHT HYDRAULIC PUMP FAILED CHECK DURING RUN UP. PUMP WAS REMOVED AND IT WAS DISCOVERED THAT THE SHAFT H AD SHEARED. DURING REMOVAL OF THE FITTINGS IT WAS DISCOVERED THAT THE SMALL PRESSED IN NOZZLE, SPRING AND BALL HAD COME LOOSE WITH THE BALL JAMMING THE PUMP VANES AND CAUSING THE SHAFT TO SHEAR. NOTE: THIS WAS ON THE PRESSURE OUTLET SIDE . THE PUMP WAS REMOVED AND REPLACED. 1 L 7 2 3O A20SO 2001080200119 20010802 00119 SO 2001 8 2 WVBA2001036 1 20010529 G 2140 A23D04 REGULATOR PIPER PA31 PA31350 7103110 SO HEATER LEAKING C WVBA K NONE K FLUID LOSS IN INSP/MAINT 1 AL 01 42WP 160 318252038 DURING INSPECTION IT WAS NOTICED THAT FUEL STAIN WAS IN THE DRAIN TUBE OF THE FUEL PRESSURE REGULATOR OF THE FRONT COMBU STION HEATER. THE REGULATOR WAS INSPECTED AND FOUND TO BE LEAKING FROM THE GASKET OF THE UPPER PARTING SURFACE. UNIT W AS REMOVED AND REPLACED. IT SHOULD BE NOTED THAT THIS UNIT WAS INSPECTED PER SB WHICH INCLUDES A PRESSURE CHECK TO COMP LY WITH AD AND WAS DETERMINED SERVICABLE. TIME SINCE INSPECTION WAS 59 HOURS. 1 L 7 2 3O A20SO 2002012400025 20020124 00025 SW 2002 1 24 YTRR077311 1 20011129 G 6330 BEARING BELL 206 206L1 1182107 SW RESTRAINT WORN H YTRA K NONE O OTHER IN INSP/MAINT 1 FS 01 142DP 331 LK0765 45585 SPHERICAL BEARING CAME UNSTAKED WHICH ALLOWED THE BEARING TO FLOAT IN THE LATERAL SPRING ARM. 1 G 7 1 3U H2SW 2002012400028 20020124 00028 SW 2002 1 24 YTRR077356 1 20011206 G 6710 206062721103 ACTUATOR BELL 206 206L1 1182107 SW MAIN ROTOR SEIZED H YTRA O OTHER O OTHER NR NOT REPORTED 1 FS 01 142DP 386 45585 THE LINEAR ACTUATOR OPERATED FOR APPROXIMATELY 3 MONTHS BEFORE FAILING. CAUSE OF THE FAILURE IS UNKNOWN. PART RETURNED T O PRECISION HELIPARTS FOR EVALUATION. 1 G 7 1 3U H2SW 2001050200041 20010502 00041 SO 2001 5 2 ZVSR409Y 1 20010220 G 5522 SKIN GULSTM G1159 G1159 3953505 SO ELEVATOR CORRODED B K NONE O OTHER IN INSP/MAINT 1 SO 11 117JJ 163 EXTENSIVE SURFACE CORROSION ON HORIZONTAL STABILIZER AND ELEVATORS. CORROSION ON ELEVATORS EXTENDED THROUGH THE SKIN SUR FACE. CORROSION WAS FOUND WHILE AIRCRAFT WAS IN MAINTENANCE FOR AN EXTERIOR PAINT JOB. CORROSION WAS FOUND AFTER PAINT W AS STRIPPED AND A VISUAL INSPECTION WAS PREFORMED. 2 L 7 2 4F RT A12EA