20030409000102003040900010SW 2003 4 9 2003FA0000325 120020305G74006891969 CONTROL UNIT BELL 206 206L 1181522SW ALLSN 25OC 250C20R GL AUTO RELIGHT INTERMITTENT D O OTHER O OTHER NRNOT REPORTED 1 NM099984K 45054 CAE832197R AUTO-RELIGHT SYSTEM ACTIVATES INTERMEDIATELY DURING NORMAL ENGINE OPERATION. 1G71 3U3 U H2SW E4CE 20030409000232003040900023EU 2003 4 9 CA030312010 120020813G2750 CONTROL QUADRANT PILATSPC12 PC1245 7090551EU PWA PT6 PT6A67B 52043NE HARTZLHCE4A HCE4A3D GL FLAP SYSTEM FAILED W J DUMP FUEL A FLAME/FIRE CLCLIMB 1 CA (CAN) AFTER TAKEOFF THE PILOT SELECTED FLAPS UP. A FLAP WARNING LIGHT ILLUMINATED AND THE FLAPS DID NOT MOVE. (FLAPS REMAINED AT 15 DEGREES). THE PILOT RETURNED TO LAND AT THE AIRPORT WITHOUT INCIDENT. A FLAP RESET WAS CARRIED OUT ON THE GROUND SERVICEABLE. 1L71 3T4 TRTA78EU E26NE 5 CP210NE 20020128000442002012800044EU 2002 1 28 2002FA0000135 120020116G2913GHE1004 PUMP UROCOPEC120 EC120B 8680987EU TMECA ARRIUSARRIU2F NE HYDRAULIC SYS SLUGGISH C O OTHER O OTHER NRNOT REPORTED 1 WP25266SD346 1133 FLIGHT CONTROLS HAD A SLIGHT RATCHET FEELING AND SLUGGISH. HYDRAULIC OFF CHECKS RESPONDED SLOWLY (10 SECONDS). PROBABLE CAUSE: LOWER THAN NORMAL PRESSURE AND/OR LOWER THAN NORMAL FLOW. 1G72 3U3 UNCR0001RD E34NE 20020130000042002013000004EU 2002 1 30 2002FA0000139 120020117G3340350A73029001 CONTROL PANEL UROCOPEC120 EC120B 8680987EU TMECA ARRIUSARRIU2F NE SEARCH LIGHT FAILED C K NONE L NO TEST ININSP/MAINT 1 WP25277SD58 1134 SX 16 NIGHTSUN QUIT OPERATING. FOUND RELAY PANEL INOPERATIVE. REPLACE RELAY ASSEMBLY. PROBABLE CAUSE: RELAY INTERNAL FAILURE. 1G72 3U3 UNCR0001RD E34NE 20020130000052002013000005EU 2002 1 30 2002FA0000140 120020117G3340350A73029001 CONTROL PANEL UROCOPEC120 EC120B 8680987EU TMECA ARRIUSARRIU2F NE SEARCH LIGHT INOPERATIVE C O OTHER L NO TEST NRNOT REPORTED 1 WP25277SD58 1134 SX16 NIGHTSUN QUIT OPERATING. FOUND RELAY PANEL INOPERATIVE, REPLACE RELAY ASSEMBLY. PROBABLE CAUSE: RELAY INTERNAL FAILURE. 1G72 3U3 UNCR0001RD E34NE 20020130000062002013000006EU 2002 1 30 2002FA0000141 120020117G33406485000 LIGHT UROCOPEC120 EC120B 8680987EU TMECA ARRIUSARRIU2F NE ANTICOLLISION SHORTED C O OTHER L NO TEST NRNOT REPORTED 1 WP25266SD9 1133 ANTI COLLISION LIGHT POPPED CIRCUIT BREAKER. REPLACED WITH NEW ASSEMBLY. PROBABLY CAUSE: INTERNAL SHORT CIRCUIT. 1G72 3U3 UNCR0001RD E34NE 20020130000072002013000007NE 2002 1 30 2002FA0000142 220020117G7313319307840 NOZZLE UROCOPEC120 EC120B 8680987EU TMECA ARRIUSARRIU2F NE TURBINE SECTION BURNED C O OTHER O OTHER NRNOT REPORTED 1 WP25266SD200 1133 34144 ENGINE WOULD NOT START. REPLACED START NOZZLES (START-INJECTORS). POSSIBLE CAUSE: FUEL BURNED IN NOZZLE AT END OF START CYCLE. 1G72 3U3 UNCR0001RD E34NE 20020130000152002013000015SO 2002 1 30 2002FA0000146 120020116G2720317729 CONTROL CABLE MAULE M5 M5235C 5460135SO LYC O540 O540* 41532EA RUDDER LOOSE D O OTHER O OTHER NRNOT REPORTED 1 NM03382X 1660 7021C UPON LANDING, WINDS WERE DOWN RUNWAY AT 15 MPH, THE LEFT RUDDER CABLE CAME LOOSE AT AIRCRAFT NICOPRESS SLEEVE CAUSING AIRCRAFT TO GROUND LOOP. THERE WAS NO EVIDENCE OF CORROSION ON CABLE OR SLEEVE AND SLEEVE WAS PREVIOUSLY INSPECTED FOR CORRECT SWEDGE PER AD. THE AIRCRAFT IS REPAIRABLE AND WILL BE REPLACING ALL CABLES AND DOUBLING THE NUMBER OF NICOPRESS SLEEVES TO ENSURE SECURITY. 1H71 3O3 O 3A23 E295 20020130000732002013000073SO 2002 1 30 U23R624Y 120020108G5320 BRACKET PIPER PA34 PA34200T 7103406SO CONT O360 TSIO360RB 17025CE MCAULY3AF32C3AF32C505 GL LT ENGINE BROKEN B K NONE G MULTIPLE FAILURE ININSP/MAINT 1 EA0735GK 178 36 3449174 322317 992855 UPON ANNUAL INSPECTION OF THE AIRCONDITIONING COMPRESSOR, IT WAS NOTED TO MOVE AROUND BY PRESSING ON THE AIRCONDITIONING BELT FURTHER INSPECTION REVEALED THE FORWARD AIRCONDITIONING BRACKET TO BE BROKEN. DURING REMOVAL OF THE BRAKET IT WAS ALSO FOUND TO BE BROKEN AT THE LOWER FORWARD INBOARD ATTACH POINT ALSO. THERE WAS A TOTAL OF TWO BRAKES FOUND OF THIS ITEM ONE HIDDEN AND ONE NEEDING A MIRROR TO LOCATE. 1L72 3O3 O A7SO E9CE 5 CP22EA 20020130000922002013000092EU 2002 1 30 2002FA0000151 120020127G291342046 PUMP FOKKERF28 F28MK0070 4990811EU RROYCETAY TAY62015 04564NE HYD SYS LEAKING C A UNSCHED LANDING KJ FLUID LOSS WARNING INDICATION CLCLIMB 1 GL23324K 1490 11545 17107 APPROX. 2 HOURS INTO FLIGHT FROM DTW TO SNA SYSTEM 1 PUMP 1 FAULT LIGHT ILLUMINATED. CREW FOLLOWED THE ABNORMAL PROCEDURES FOR HYDRAULIC SYSTEM 1 LOW PRESSURE. CREW NOTICE SYSTEM NR 1 QUANTITY BEGINING TO DROP. CREW DIVERTED HOPING TO GET ON THE GROUND BEFORE LOSS OF TOTAL SYSTEM 1 QUANTITY AND PRESSURE. 15 - 20 MINUTES LATER SYSTEM 1 LO QUANTITY ALERT ILLIMINATED. GEAR AND FLAPS WERE LOWERED USING THE ALTERNATE PROCEDURES. AIRCRAFT LANDED AT THE SLN AIRPORT. A MAINTENANCE CREW WAS DISPATCED FROM DTW TO REPAIR THE PROBLEM. THE MAINTENANCE CREW INSPECTED THE LEFT ENGINE FOUND THE NR 1 HYD. PUMP LEAKING AT THE PUMP SPLIT LINE. THE PRESSURE FILTER WAS INSPECTED FOR CONTAIMINATION, NONE WAS FOUND. THE PUMP WAS RE2L72 4F4 FRTA20EU E25NE 20020201000012002020100001CE 2002 2 1 2002FA0000152 120020131G2731 PIN CESSNA172 172R 2072401CE LYC IO360 IO360L2A EA ELEVTOR TRIM SHEARED B K NONE O OTHER ININSP/MAINT 1 SO0324442474 17280862 L2869351A WHILE REMOVING THE TRIM TAB ACTUATOR FOR SERVICE, BOTH GROOVE-PINS (P/N 3/32X.38TYPE3) WHICH ATTACH THE ROLL CHAIN SPROCKET, (P/N 0310332-0) TO THE SCREW-INTERNAL THREADS (P/N 1260049-1) OF THE TRIM TAB ACTUATOR WERE FOUND TO HAVE SHEARED. THIS ALLOWED THE SPROCKET TO BE SLIPPED OFF BY HAND. ONLY FRICTION BETWEEN THE SPROCKET AND THE SCREW-INTERNAL THREADS WAS ENABLING THE TRIM TAB TO BE MOVED. 1H71 3O3 ONT3A12 1E10 20020201000022002020100002SO 2002 2 1 2002FA0000153 120020131G5600494739 WINDOW PIPER PA46 PA46350P 7104602SO PWA PT6 PT6A34 52043EA HARTZLHCE4N HCE4N3 NE FUSELAGE CRACKED B O OTHER O OTHER CRCRUISE 1 GL099167Q760 15 4622031 PCKRB008 HH1000 WINDOW CRACKED LOWER FORWARD CORNER FROM STORM WINDOW OPENING TO MOUNTING BOLTS. AIRCRAFT WAS AT CRUISE AND 5PSI WHEN INCIDENT OCCURED. 1L71 3O4 TRTA25SO E4EA 5 CP10NE 20020205000442002020500044SO 2002 2 5 2002FA0000156 220020105G8530 CONNECTING ROD CESSNA172 172H 2072424CE CONT O300 O300* 17022SO NR 3 CYLINDER FAILED D O OTHER RY PARTIAL RPM/PWR LOSS ENGINE STOPPAGE NRNOT REPORTED 1 EA233910R 17255410 NR 3 CYLINDER CONNECTING ROD AND CAP FAILED AT THE CRANKSHAFT. CONNECTING ROD FELL TO BOTTOM OF CYLINDER BORE AND WAS REPEATEDLY STRUCK BY THE CRANKSHAFT UNTIL ENGINE WAS SHUT DOWN. THE FAILURE OCCURRED AFTER FINAL POWER REDUCTION DURING A ROUTINE LANDING. PILOT REPORTED HEARING A LOUD BANG FOLLOWED BY POWER LOSS. CAUSE OF FAILURE INDETERMINABLE. PROBABLE CAUSE OF FAILURE DEFECT IN ROD CASTING. NOTED THAT THIS ENGINE HAS A MANUFACTURER RECOMMENDED TBO TIME OF 1800 HOURS. ENGINE HAD 2115 HOURS ON IT SINCE MAJOR OVERHAUL. ENGINE DISASSEMBLY WAS FOUND THAT ONE OF THE TWO ROD CAP BOLTS HAD BACKED OFF, AND THE NUT WAS FOUND IN THE BOTTOM OF THE CASE. 1H71 3O3 ONT3A12 E253 20020205000452002020500045 2002 2 5 2002FA0000157 420020121G3452118280001 TRANSFORMER PIPER PA38 PA38112 7103812SO LYC O235 O235* 41505EA TRANSPONDER SHORTED D K NONE O OTHER ININSP/MAINT 1 GL092509A 3878A0724 TRANSFORMER SHORTED. 1L71 3O3 O A18SO E223 20020205000472002020500047CE 2002 2 5 B3OR20020002 120020201G7170555501125 DRAIN VALVE CESSNA500 550 2076604CE PWA JT15 JT15D4 52112NE ENGINE CRACKED B B3ORK NONE O OTHER ININSP/MAINT 1 SW0326494 5500605 DURING A PHASE 1 & 2 INSPECTION, THE ENGINES WERE DE-COWLED FOR THE OIL FILTER CLEANING ITEM. A MECHANIC NOTICED SOME FUEL RESIDUE AROUND THE FUEL DRAIN "EPA" CAN. UPON INSPECTION THE CAN WAS FOUND TO HAVE A MOUNTING BRACKET BROKEN OFF OF IT. THE BREAK WAS WHERE THE BRACKET WAS WELDED TO THE CAN AND IT ACTUALLY WAS THE CAN ITSELF THAT HAD BROKEN, NOT THE BRACKET. THE OPPOSITE ENGINE WAS INSPECTED AND IT HAD A SIMILAR CRACK. IN RESEARCHING THIS PART, IT WAS FOUND THAT IN THE PAST YEAR, THIS PART HAD BEEN REPLACED ON 6 OTHER ENGINES FOR THE SAME REASON AT THIS LOCATION. THIS DEFINITELY SEEMS TO BE AN ITEM THAT DESERVES MORE ATTENTION WHEN INSPECTING THE ENGINES. 1L72 4F4 F A22CE E1NE 20020205000492002020500049SO 2002 2 5 HO1R15248 120020119G57116205401 SPAR PIPER PA32 PA32260 7103206SO LYC O540 O540E4B5 41532EA RT WING CORRODED B HO1RK NONE O OTHER ININSP/MAINT 1 EA217728J3679 321130 R1351240 DURING ANNUAL INSPECTION THE RIGHT WING AFT ATTACH FITTING OUTBOARD OF THE FUSELAGE AND AFT WING SPAR WERE FOUND TO EXHIBIT DISSIMILAR METAL CORROSION BETWEEN THE STEEL ATTACH FITTING AND THE REAR SPAR. THE AFT SPAR WAS CORRODED TO THE POINT WHERE A CRACK HAD DEVELOPED IN THE REAR SPAR. CRACK WAS NOT FOUND UNTIL STEEL ATTACH FITTING WAS REMOVED FOR HIDDEN DAMAGE INSPECTION. 1L71 3O3 O A3SO E295 20020205000582002020500058NE 2002 2 5 WRLA200201 220020201G7230 BLADE DOUG DC10 DC1030 3023501WP GE CF6 CF650C2 30018NE COMPRESSOR VIBRATION A WRLAA UNSCHED LANDING E VIBRATION/BUFFET CLCLIMB 1 SO11526MD 46998 517515 NR 1 ENGINE VIBRATION 80-95, ALL OTHER INDICATIONS NORMAL. EVENT OCCURRED AT THE TOP OF THE CLIMB SEGMENT WHEN THE FLIGHT AS THE CREW WAS LEVELING THE AIRCRAFT. THE CAPTAIN ELECTED TO RETURN TO MIA. LUBED FAN BLADES, PERFORMED MAX POWER RUN AT 80-95 PERCENT TRANSITION, NO VIBRATION NOTED. THE ENGINE WAS RUN AT ALL POWER SETTING FROM IDLE TO TAKEOFF POWER WITH NO VIBRATION NOTED ON THE NUMBER ONE ENGINE. 2L73 4F4 F A22WE E23EA 20020205001482002020500148SW 2002 2 5 CA020130005 120020122G6220206011118001 BEARING BELL 206011132113BELL 206 206L1 1182107SW ALLSN 250C 250C28B 03013GL CAGE FAILED W O OTHER I FLT. ATTITUDE INST. CRCRUISE 1 CA A5828 (CAN) PILOT REPORTED A "SPRINGY" FEELING IN CYCLIC ALONG WITH THE NECESSITY OF APPLYING CONSTANT FORWARD CYCLIC INPUT FOR CRUISE FLIGHT. NO PROBLEMS WERE FOUND IN THE FLIGHT CONTROLS. THE ROTOR HEAD WAS REMOVED AND DISASSEMBLED AND AT THIS TIME THE DAMAGED BEARING WAS NOTED. NO OTHER PARTS WERE FOUND DAMAGED. THE ROTOR HEAD, HAVING ONLY 80 HOURS REMAINING UNTIL OVERHAUL, HAS BEEN SENT FOR FURTHER EVALUATION AND OVERHAUL. THE FAILED BEARING IS BEING KEPT IN QUARANTINE FOR INSPECTION, IF REQUIRED. 1G71 3U3 U H2SW E1GL 20020205001492002020500149SW 2002 2 5 CA020131004 120020129G6340204001736005 CHAIN BELL 204040806011BELL 212 212 1181420SW PWA PT6T PT6T3 52045EA HYD DRIVE OIL BROKEN W AO UNSCHED LANDING OTHER JO WARNING INDICATION OTHER CRCRUISE 1 CA A1214562 (CAN) THE HELICOPTER WAS IN CRUISE WHEN ALL OF A SUDDEN THE ROTOR TACH GENERATOR INDICATOR WENT TO ZERO.BACK AT THE BASE AN ENGINEER TROUBLE SHOOTED THE PROBLEM AND FOUND THE TACH. GEN DRIVE WAS DISCONNECTED. THE ROTOR TACH GENERATOR DRIVE IS LOCATED IN THE #1 HYDRAULIC QUILL ASSEMBLY OF THE MAIN ROTOR TRANSMISSION. SUSPECT THE CHAIN HAS FAILED INSIDE THE HYDRAULIC/TACH GEN DRIVE QUILL. 1G71 4U4 U H4SW E22EA 20020205001922002020500192CE 2002 2 5 AUS20020002 120020102G571105230142 SPAR CESSNA172 172M 2072418CE LYC O320 O320E2D 41508EA MCAULY1C160 1C160DTM GL WING SPAR CORRODED W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) FORWARD SPAR ASSEMBLY CONTAINED SEVERE EXFOLIATION CORROSIONBETWEEN THE SPAR PNO 0523014-2 AND THE ATTACHMENT PLATE PNO 0523016-1. THE THICKNESS OF THE ASSEMBLY WAS REDUCED BY APPROXIMATELY 50% DUE TO THE CORROSION. THE RIVETS HOLDING THEASSEMBLY TOGETHER WERE ALSO CORRODED (18OF22). CORROSION WAS ALSO FOUND AT RIB TO SKIN INTERFACES. INVESTIGATION OF OTHER SIMILAR WINGS HELD IN STORAGE FOUND THEM TO BE IN A SIMILAR CONDITION. 1H71 3O3 ONT3A12 E274 5 NP910 20020205001962002020500196EA 2002 2 5 AUS20020008 220020103G8520AS13884M03 BEARING LYC IO540E1B5 GULSTM500 500U 0141108SW LYC O540 IO540E1B5 41532EA HARTZLHCA3X HCA3XK2 GL RECIPROCATING ENDELAMINATED W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) ENGINE NO1 MAIN BEARING DELAMINATED. METAL CONTAMINATION OF OIL FILTERS. 1H72 3O3 O 6A1 1E4 5 CP913 20020205001982002020500198GL 2002 2 5 AUS20020017 320020107G61101949 PROPELLER HARTZL HCE2YK2RB PIPER PA23 PA23250 7102308SO LYC O540 IO540C4B5 41532EA HARTZLHCE2Y HCE2YK2 GL PROPELLER ASSEMBFAULTY W K NONE O OTHER ININSP/MAINT 1 AUS 267 1949 (AUS) PROPELLER BLADE CLAMP BOLTS NOT IN SAFETY. NO SPACERS BETWEEN SPINNER BACKPLATE AND PROPELLER HUB. PROPELLER BLADES CONTACTINGBACKPLATE WHEN BLADE IS IN THE FEATHER POSITION.PERSONNEL/MAINTENANCE ERROR. 1L72 3O3 O 1A10 1E4 5 CP9EA 20020205001992002020500199NE 2002 2 5 AUS20020020 120020107G2560 FLOAT SKRSKYS76 S76C 8143008NE TMECA ARRIELARRIEL1S 60030NE EMERGENCY EQUIPMFAULTY W K NONE O OTHER DEDESCENT 1 AUS (AUS) AIRCRAFT SUFFERED AN UNCOMMANDED INFLATION OF THE REAR CELLS OF THE NOSE FLOATATION BAGS. THE FLOAT SYSTEM WAS NOT ARMED AT THE TIME. 1G72 3U3 UNCH1NE E19EU 20020205002002002020500200NE 2002 2 5 AUS20020022 220020111G73203031829 PIPE PWA PT6A65AG AIRTRCAT802 AT802A 0390308SW PWA PT6 PT6A65AG 52043NE HARTZLHCB5M HCB5MP3 GL FUEL CONTROLLINGCRACKED W K NONE ER VIBRATION/BUFFET PARTIAL RPM/PWR LOSS TOTAKEOFF 1 AUS PCE32620 (AUS) P3 PIPE TO FUEL CONTROL UNIT CRACKED. 1L71 3T4 TNCA19SW E4EA 6 CP44GL 20020205002012002020500201EU 2002 2 5 AUS20020023 120020107G5743 FITTING MUDRY 10 CAP10B 0950102EU LYC O360 AEIO360B2F 41514EA HOFMANHO29 HO29HM180 EU WING, LANDING GECRACKED W K NONE O OTHER ININSP/MAINT 1 AUS 990 (AUS) LH AND RH FORWARD LANDING GEAR ATTACHMENT BLOCKS CRACKED. FOUND DURING INSPECTION IAW AD/CAP10/3. 1L71 3O3 O A36EU 1E10 5 NP3EU 20020205002022002020500202SO 2002 2 5 AUS20020025 220020103G74141051675 CONDENSER BENDIX S6RN25 CESSNA206 U206G 2073356CE CONT O520 IO520F 17032SO MCAULYD3A34 D3A34C404 GL MAGNETO/DISTRIBUFAULTY W K NONE E VIBRATION/BUFFET CRCRUISE 1 AUS (AUS) MAGNETO CONDENSER FAULTY. A TOTAL OF FIVE CONDENSERS FAILED INAPPROXIMATELY 500 HOURS OF OPERATION. INVESTIGATION FOUND THATTHE FAILURE OCCURRED IN THE SMALL ATTACHMENT BRACKET HOLDING THECONDENSER IN THE POINTS CAVITY. 1H71 3O3 O A4CE E5CE 5 CP47GL 20020206000602002020600060CE 2002 2 6 AUS20020003 120020102G5220 DOOR CESSNA310 310L 2074230CE CONT O470 IO470U 17026SO MCAULY2AF34CD2AF34C81 GL EMERGENCY EXIT MISINSTALLED W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) EMERGENCY EXIT INCORRECTLY INSTALLED. ONLY TWO OF THREE LATCHING PINS ENGAGED. EMERGENCY RELEASE CABLE LOOPED AND THE TWO LATCHING PINS WERE FITTED BACKWARDS. IT WOULD HAVE BEEN IMPOSSIBLE FOR THE EMERGENCY EXIT TO BE RELEASED. 1L72 3O3 O 3A10 3E1 5 CP5EA 20020206000842002020600084SO 2002 2 6 AUS20020012 120020102G55109735500 BOLT PIPER LIFTSTRUT PIPER PA36 PA36285 7103610SO PWA PT6 PT6A20 52043EA HARTZLHCB3T HCB3TN3 GL HORIZONTAL STAB CRACKED W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) TAILPLANE LIFT STRUT CLEVIS BOLT CRACKED IN AREA OF FIRST THREAD ON THE HEAD END OF THE BOLT. 1L71 3O3 T A10SO E4EA 6 CP15EA 20020206000862002020600086SO 2002 2 6 AUS20020015 220020109G741410349367 IMPULSE COUPLINGBENDIX 10349505 CESSNA182 182Q 2072732CE CONT O470 O470* 17026SO MAGNETO WORN W K NONE O OTHER ININSP/MAINT 1 AUS L039021F (AUS) MAGNETO IMPULSE COUPLING FLYWEIGHTS WORN BEYOND LIMITS. 1H71 3O3 ONT3A13 E273 20020206000962002020600096EA 2002 2 6 AUS20020018 220020107G8530LW12425 CYLINDER PIPER PA23 PA23250 7102308SO LYC O540 IO540C4B5 41532EA HARTZLHCE2Y HCE2YK2 GL ENGINE FAULTY W K NONE W INADEQUATE Q C ININSP/MAINT 1 AUS (AUS) LT ENGINE NR 2 CYLINDER OUT OF ROUND. NR 5 CYLINDER BORE STEPPED AND BLUE MARKING ON FINS. NR 1 CYLINDER IS MARKED AS NITRIDED BUT IS ACTUALLY A CHROMED CYLINDER. RT ENGINE NR 4 CYLINDER NOT ENTERED ON RELEASE NOTE. NR 2 CYLINDER IS NOT MARKED ORANGE FOR CHROMED. CYLINDER SN A3104 DOES NOT EXIST IN THE PAPERWORK. 1L72 3O3 O 1A10 1E4 5 CP9EA 20020206000992002020600099SO 2002 2 6 AUS20020024 220020107G7310630626 BALANCE TUBE CESSNA182 182K 2072724CE CONT O470 O470R 17026SO FUEL DIST FRACTURED W O OTHER O OTHER NRNOT REPORTED 1 AUS 940 (AUS) ENGINE BALANCE TUBE FRACTURED AT WELD JOINT. NR 3 CYLINDER INOPERATIVE AND PROPELLER BLADE LOOSE. 1H71 3O3 ONT3A13 E273 20020206001012002020600101CE 2002 2 6 AUS20020027 120020110G7920124F0018CR0194 HOSE CESSNA441 441 2076020CE GARRTTTPE331TPE3318 01514WP HARTZLHCB3T HCB3TN5 GL RT ENGINE OIL RESTRICTED W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) RT ENGINE OIL COOLER SCAVENGE HOSE INTERNALLY RESTRICTED. SUSPECT HOSE COULD HAVE BEEN KINKED DURING ENGINE INSTALLATION. 1L72 3T4 TRTA28CE E4WE 6 CP15EA 20020206001022002020600102CE 2002 2 6 AUS20020028 120020114G52809981003034 DOOR BEECH 200 B200C 1152924CE PWA PT6 PT6A42 52043NE MLG SEPARATED W O OTHER D INFLIGHT SEPARATION NRNOT REPORTED 1 AUS (AUS) RT MAIN LANDING GEAR DOOR SEPARATED FROM AIRCRAFT DUE TO FAILURE OF THE HINGE PIN. 1L72 4T4 T A24CE E4EA 20020206001222002020600122SO 2002 2 6 AUS20020033 120020116G534197101301 FITTING PIPER PA36 PA36375 7103620SO LYC O720 IO720D1C 41546EA FUSELAGE CRACKED W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) RT FRONT SPAR ATTACHMENT FITTING ON FUSELAGE LOCATED AT RT STN 124.250 CRACKED IN REAR LAMINATE. CRACK LENGTH 10MM (0.39IN). 1L71 3O3 O A10SO 1E15 20020214000042002021400004NE 2002 2 14 AUS20020019 220020111G731030J228501 LINE CESSNA500 550 2076604CE PWA 530 PW530A NE FUEL SYS RUPTURED W K NONE K FLUID LOSS ININSP/MAINT 1 AUS (AUS) ENGINE HEAT EXCHANGER FUEL TUBE LEAKING. FUEL SPRAYING INSIDE COWLS AND ENTERING ENGINE THROUGH INTAKE. 1L72 4F4 F A22CE E00053EN 20020214000152002021400015CE 2002 2 14 CA020102002 120020102G3240 STATOR BFGOODRICH 215286 CESSNA500 550 2076604CE PWA JT15 JT15D4 52112NE BRAKE ASSY BROKEN W K NONE O OTHER ININSP/MAINT 1 CA 1411 (CAN) DISASSEMBLED BRAKE UNIT AND FOUND STATOR DISC P/N 133-89302 CHG "B" BROKEN. (SEE ATTACHED PHOTO'S). 1L72 4F4 F A22CE E1NE 20020214000512002021400051NM 2002 2 14 CA020104006 120020102G3213 COLLAR PIPER PA60 PA60600 7106001NM LYC O540 IO540K1F5 41532EA MLG CRACKED W O OTHER R PARTIAL RPM/PWR LOSS LDLANDING 1 CA (CAN) PILOT LANDED NORMAL: WHILE ROLLING ON RUNWAY AIRCRAF WENT RIGHT AND PILOT HAS A HARD TIME CONTROLLING AIRCRAFT BUT MANAGED TO GET AIRCRAFT STOPPED. SHUT DOWN ENGINES AND GOT OUT TO INVESTIGATE; NOTICED RIGHT MAIN GEAR TIRE 90 DEGREES FROM NORMAL WITH HELP GOT AIRCRAFT TO TARMAC.UNABLE TO GIVE PART NUMBER AS THERE IS NO FURTHER BREAKDOWN IN PARTS MANUAL. 1M72 3O3 ORTA17WE 1E4 20020215000172002021500017SW 2002 2 15 CA020104019 120020104G53100354130 TUBE MOONEYM20 M20J 5870219SW LYC O360 IO360A3B6 41514EA MCAULY2D34C B2D34C212 GL FUSELAGE MISINSTALLED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) WHEN INTERIOR OF THE A/C WAS REMOVED IT WAS NOTICED THAT THE TUBULAR STRUCTURE WELDED JOINT ON THE LT SIDE JUST FWD OF SPAR ON DIAGONAL BRACE BELOW THE FRONT OF REAR WINDOW IS MISSING A WELD. IN THE SAME AREA NOTICED A CLUSTER GUSSETS WITH INCOMPLETE WELDS. 1L71 3O3 O 2A3 1E10 5 CP7EA 20020215000732002021500073CE 2002 2 15 CA020111001 120020110G32601003810061 SWITCH BEECH 99 99 1154002CE PWA PT6 PT6A28 EA NLG INTERMITTENT W O OTHER J WARNING INDICATION DEDESCENT 1 CA (CAN) PILOT SELECTED GEAR DOWN AND GOT NO NOSE GREEN LIGHT. PILOT WAS READY TO DO A EMERGENCY EXTENTION WHEN THE GREEN LIGHT CAME ON. MAINTENANCE REPLACED THE SWITCH AND RETURNED AIRCRAFT TO SERVICE. 1L72 3T4 T A14CE E4EA 20020215000952002021500095SW 2002 2 15 CA020114002 120020108G6720206010793101 PITCH LINK BELL 206 206B 1181511SW ALLSN 250C 250C20B 03013GL TAIL ROTOR CRACKED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) FOUR CRACKS FOUND TWO ON EACH END OF PITCH LINK SIMILAR TO THOSE DESCRIBED IN ASB 206-87-39 AND OSN 206-99-36. 1G71 3U3 U H2SW E4CE 20020215001032002021500103CE 2002 2 15 CA020116002 120020104G271005341251 BUSHING CESSNA172 172M 2072418CE LYC O320 O320E2D 41508EA BELLCRANK WORN W K NONE O OTHER ININSP/MAINT 1 CA 13746 (CAN) BUSHING WAS FOUND TO BE ROTATING IN BELLCRANK ASSEMBLY. 1H71 3O3 ONT3A12 E274 20020215001042002021500104CE 2002 2 15 CA020116004 120020104G5511053200198 SPAR CESSNA172 172P 2072436CE LYC O320 O320D2J 41508EA HORIZONTAL STAB CRACKED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) CRACK WAS FOUND DURING A SCHEDULED INSPECTION OF THE AIRCRAFT, IN THE AREA OF THE FRONT SPAR OF THE STABILIZER. AT THE LIGHTENING HOLE BETWEEN THE TWO NOSE RIBS. 1H71 3O3 ONT3A12 E274 20020215001052002021500105SW 2002 2 15 CA020116005 120020108G3220AN5C32A BOLT AIRTRCAT802 AT802 0390305SW PWA PT6 PT6A67A 52043NE TAIL WHEEL WORN W K NONE O OTHER ININSP/MAINT 1 CA (CAN) DURING THE ANNUAL INSPECTION MAINTENANCE REMOVED BOLT AN5C-32A, AS PER INSPECTION SCHEDULE. THEY FOUND THAT THE BOLT WAS BADLY WORN AND THAT THREADS WERE DAMAGED. 1L71 3T4 TNCA19SW E26NE 20020215001072002021500107SO 2002 2 15 CA020116008 120020105G324409231500 TIRE PIPER PA31 PA31350 7103110SO LYC O540 TIO540J2BD 41532EA HARTZLHCE3Y HCE3YR2A GL NLG PUNCTURED W O OTHER O OTHER LDLANDING 1 CA (CAN) NOSE WHEEL TIRE BECAME FLAT DURING LANDING, CAUSING A SHIMMY NOTICEABLE TO PILOTS. AIRCRAFT WAS BROUGHT TO A STOP ON RUNWAY, WHERE IT WAS TOWED TO MAINTENANCE FACILITY. 1L72 3O3 O A20SO E14EA 5 CP33EA 20020215001082002021500108SO 2002 2 15 CA020117001 120020114G32440923150 TIRE PIPER PA31T PA31T2 7103127SO PWA PT6 PT6A135 52043NE NLG PUNCTURED W O OTHER O OTHER LDLANDING 1 CA (CAN) NOSE WHEEL TIRE BECAME FLAT DURING LANDING, CAUSING A SHIMMY NOTICEABLE TO PILOTS. 1L72 3T4 TRTA8EA E4EA 20020219000702002021900070NE 2002 2 19 CA020117012 220020111G7412 EXCITER PILATSPC12 PC1245 7090551EU PWA PT6 PT6A67B 52043NE HARTZLHCE4A HCE4A3D GL IGNITION SYSTEM FAILED W O OTHER J WARNING INDICATION TXTAXI/GRND HDL 1 CA (CAN) PILOT WENT TO START ENGINE AND HAD NO LIGHT OFF.TRIED TWICE TO START ENGINE AND HAD NO LIGHT OFF. IGNITION EXCITOR BOX WAS REPLACED AND AIRCRAFT RETURNED TO SERVICE.NOTE: THIS IS TYPICAL FOR PILATUS IGNITOR BOX. THE SAME BOX WILL LAST 2-3 TIMES LONGER ON A BEECH 99 OR A100. 1L71 3T4 TRTA78EU E26NE 5 CP210NE 20020219001242002021900124EU 2002 2 19 CA020117016 120020102G2700 CONTROL UNIT AIRBUS330 A330243 3930330EU RROYCERB211 RB211TRENT77 NE COCKPIT MALFUNCTIONED W D RETURN TO BLOCK O OTHER TXTAXI/GRND HDL 1 CA (CAN) AIRCRAFT RETURNED BACK TO GATE AFTER PUSH BACK. NO ECAM INDICATION OF RUDDER TRIM AND NO PEDESTAL INDICATION. TROUBLESHOOTING WAS CARRIED OUT PER CATTS , 2L72 4F4 FRTA46NM E39NE 20020219001312002021900131EU 2002 2 19 CA020118006 120020117G5230 HANDLE AIRBUS320 A320231 3930325EU IAE V2500 V2500A1 NE CARGO DOOR MALFUNCTIONED W A UNSCHED LANDING J WARNING INDICATION CLCLIMB 1 CA 2487324873 (CAN) AT APPRXIMATELY 10,000 FT ALTITUDE THE FWD CARGO DOOR INDICATED UNSAFE ON ECAM. THE AIRCRAFT DIVERTED AND WAS INSPECTED BY A COMPANY ACA. THE DOOR HANDLE WAS FOUND TO BE OUT OF THE DETENT BY ABOUT 1/4 OF AN INCH. THE HANDLE ASSY AND DOOR LOCKING MECHANISM WAS INSPECTED AND FOUND SERVICEABLE. THE INDICATING SYSTEM WAS CHECKED AND FOUND SERVICEABLE. AIRBUS HAS BEEN ADVISED AND IS UNDER INVESTAGATION. 2L72 4F4 FRTA28NM E311NE 20020219001332002021900133SW 2002 2 19 CA020118009 120020110G79102765030101 OIL TANK FRCHLDSA227 SA227DC 3377521SW GARRTTTPE331TPE33112UHR WP MCAULY4HFR344HFR34C652 NE ENGINE CRACKED W K NONE K FLUID LOSS ININSP/MAINT 1 CA (CAN) AN OIL LEAK WAS NOTED DURING A BASE INSPECTION. ON INVESTIGATION A .75 INCH LONG CRACK WAS FOUND IN THE SIDE WALL OF THE OIL TANK BETWEEN THE FILLER NECK BOSS AND THE SIGHT GAUGE BOSS. THE TWO BOSSES ARE CLOSE TO EACH OTHER ON THE SIDE OF THE TANK. THE CRACK FOLLOWED THE CURVE OF THE SIGHT GAUGE BOSS WELD BAND JUST OUTSIDE OF THE EDGE OF THE WELD. THE TANK WAS REMOVED REPAIRED AND REINSTALLED. 2L72 4T4 TRTA18SW E4WE 6 C3PNE 20020219001342002021900134SO 2002 2 19 CA020118010 120020102G79305581802 TRANSDUCER PIPER PA31T PA31T 7103124SO PWA PT6 PT6A28 EA OIL PRESSURE FAILED W EA ENGINE SHUTDOWN UNSCHED LANDING N FALSE WARNING CRCRUISE 1 CA (CAN) OIL PRESSURE GAUGE UNRELIABLE ON RIGHT ENGINE. AIRCRAFT ON FLIGHT FROM YXU TO YTZ, WHEN RIGHT ENGINE OIL PRESSURE GAUGE STARTED TO INDICATE OIL PRESSURE LOSS. ALL OTHER ENGINE PARAMETERS NORMAL. PRECAUTIONARY ENGINE SHUTDOWN WAS CARRIED OUT AND AIRCRAFT CONTINUED TO YTZ. TROUBLESHOOTING CARRIED OUT IAW PT6 MM AND OIL PRESSURE TRANSDUCER WASFOUND UNSERVICEABLE.OIL PRESSURE TRANSMITTER REPLACED AND ENGINE RUN C/W. ALL INDICATION NORMAL. 1L72 3T4 T A8EA E4EA 20020219001352002021900135CE 2002 2 19 CA020118011 120020108G273126612151 ACTUATOR CESSNA208 208B 2073701CE PWA PT6 PT6A114A 52043NE MCAULY3AF34C3GFR34C703 GL ELEVATOR TRIM FAILED W A UNSCHED LANDING F FLT CONT AFFECTED CLCLIMB 1 CA (CAN) AFTER TAKEOFF FROM YHM, THE AIRCRAFT LOST ELEVATOR TRIM ELECTRICAL AND MANUAL CONTROL AND THE AUTOPILOT FAILED. THE AIRCRAFT RETURNED TO THE AIRPORT. MAINTENANCE INVESTIGAITON FOUND ONE OF THE TWO RODS ON THE LT ELEVATOR TRIM ACTUATOR WAS BINDING A LITTLE WHEN THE ELEVATOR WAS IN THE NEUTRAL POSITION, BUT FREE WHEN THE ELEVATOR WAS DEFLECTED UP OR DOWN. THE ONE ROD WAS ADJUSTED 1/14 OF A TURN - SYSTEM TESTED AND FOUND TO BE FREE THROUGH THE RANGE OF TRAVEL OF THE ELEVATOR.THE ACTUATOR HAD RECENTLY BEEN REMOVED FOR OVERHAULED AND REINSTALLED. 1H71 3T3 T A37CE E4EA 5 CP60GL 20020219001362002021900136SW 2002 2 19 CA020121001 120020117G531171470101L FRAME BBAVIA8 8GCBC 1220803SW LYC O360 O360C2E 41514EA FUSELAGE BROKEN W K NONE O OTHER ININSP/MAINT 1 CA (CAN) -TUBE FOUND BROKEN THROUGH NEAR WELD, AT FWD ENDOF LT LANDING GEAR FITTING. 1H71 3O3 O A21CE E286 20020219001372002021900137NM 2002 2 19 CA020121003 120020105G2781Y35A TRANSDUCER BOEING767 767233 1385113NM PWA JT9 JT9D7R4D 52054NE FLAP / SLATS FAILED W O OTHER FJ FLT CONT AFFECTED WARNING INDICATION CLCLIMB 1 CA (CAN) EICAS MESSAGE FOR FLAP / SLAT ELEC. DISPLAYED.REPLACED THE ROTARY DIFFERENTIAL TRANSDUCER M603 AND ADJUSTED AS PER AMM 27-51-26-424-020. FOUND SERVICEABLE. 2L72 4F4 FRTA1NM E3NE 20020219001382002021900138EU 2002 2 19 CA020121006 120020102G3260 SENSOR AIRBUS320 A320211 3930320EU CFMINTCFM56 CFM565A1 NE MLG CONTAMINATED W A UNSCHED LANDING J WARNING INDICATION NRNOT REPORTED 1 CA (CAN) AIR TURN BACK TO MONTREAL DUE TO MAIN LANDING DOOR NOT SHOWING PROPERLY LATCHED. AFTER VERIFICATION, FOUND TO BE THE SENSORS CONTAMINATED WITH GREASE AFTER AN OVERNIGHT CHECK (OVERGREASED).SENSORS CLEANED, GEAR SWING COMPLETED, SYSTEMM FOUND SERVICEABLE. 2L72 4F4 FRTA28NM E29NE 20020220000012002022000001EA 2002 2 20 CA020121011 220020107G7230 COMPRESSOR PWA PT6 PT6A20 52043EA ENGINE FAILED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) ENGINE SENT FOR INVESTIGATION & REPAIR AFTER IT FOUND THAT ENGINE MAKING RUBBING NOISE COMING FROM COMPRESSOR SECTION WHILE SCHEDULE HSI BEING PERFORMED. THE COMPRESSOR HAD SUFFERED EXTENSIVE DAMAGE. DAMAGE STARTED WITH RUBBING AT 1ST STAGE COMPRESSOR STATOR & DISK SPACER&CONTINUED DOWNSTREAM TO IMPELLER. 1ST & 2ND STAGE COMPRESSOR SPACERS HAD RUBBING MARKS ON 180 DEG. OF SURFACE AREA. 3RD STAGE COMPRESSOR SPACER HAD SEVERE DAMAGE TO FRONT RIM. IT HAD HEAVY RUBBING MARKS & MISSING SUBSTANTIAL AMOUNT OF MATERIAL. COMPRESSOR 3RD STAGE BLADES & STATOR HAD EXTENSIVE DAMAGE. IMPELLER & IMPELLER HOUSING HAD RECD SECONDARY IMPACT DAMAGE FROM DEBRIS FROM THE MATERIAL LOST FROM 3D STAGE COMPRESSOR SPAC 3 T E4EA 20020220000032002022000003EA 2002 2 20 CA020122001 220020114G7414 GEAR BENDIX ROBSINR22 R22BETA 7640110NM LYC O320 O320B2C 41508EA MAGNETO STRIPPED W E ENGINE SHUTDOWN ER VIBRATION/BUFFET PARTIAL RPM/PWR LOSS TXTAXI/GRND HDL 1 CA K049802ER (CAN) THE AIRCRAFT RAN ROUGH ON L/H MAGNETO (APPROXIMATELY 200 RPM MAGNETO DROP). LT MAG WAS REMOVED AND FOUND TO HAVE 8-10 TEETH MISSING FROM GEAR (NYLON) WHEN VIEWED THROUGH TIMING WINDOW. MAG WAS REPLACED AND THE AIRCRAFT RETURNED TO SERVICE. 1G71 3O3 O H10WE E274 20020220000062002022000006WP 2002 2 20 CA020122005 120020121G6310C1683 RETAINER ROBSINR44 R44 7640120WP LYC O540 O540F1B5 41532EA M/R CLUTCH CRACKED W K NONE K FLUID LOSS ININSP/MAINT 1 CA (CAN) CLUTCH WAS REMOVED FROM SERVICE DUE TO OIL LEAK.INVESTIGATION REVEALED THAT SEAL RETAINER PLATE EAR APPEARRED TO BE CRACKED. RETAINER WAS REMOVED AND EAR WAS FOUND TO BE NO LONGER ATTACHED TO RETAINER PLATE.NO OTHER CRACKS COULD BE FOUND IN RETAINER PLATE OR ON OPPOSITE RETAINER. RETAINER PLATE WILL BE REPLACED WITH NEW. 1G71 3O3 O H11NM E295 20020220000072002022000007WP 2002 2 20 CA020122006 120020121G6310C1883 SPRAG CLUTCH ROBSINR44 R44 7640120WP LYC O540 O540F1B5 41532EA MAIN ROTOR CRACKED W K NONE K FLUID LOSS ININSP/MAINT 1 CA (CAN) CLUTCH WAS REMOVED FROM SERVICE DUE TO AN OIL LEAK. UPON DISSASSEMBLY THE SPRAG WAS INSPECTED AND THE CAGE FOUND CRACKED.THE CRACK WAS BETWEEN TWO WINDOWS RUNNING FROM THE CORNERS. SPRAG WILL BE REPLACED WITH NEW. 1G71 3O3 O H11NM E295 20020220000082002022000008EA 2002 2 20 CA020123001 120020123G2897601R571351 WIRE HARNESS CNDAIRCL600 CL6002B19 1900309EA GE CF34 CF343A1 30015NE WING FUEL CELL CHAFED W O OTHER N FALSE WARNING CRCRUISE 1 CA (CAN) WHILE IN FLIGHT, CREW REPORTED THAT THE LEFT FUEL QTY INDICATION AND TOTAL FUEL QTY INDICATION WENT TO DASHES. FUEL QTY INDICATION WAS DEFERRED PER MEL AND MLIS WRE USED TO CHECK FUEL QUANTITY BEFORE EACH FLIGHT. UPON FURTHER INVESTIGATION, MAINTENANCE DISCOVERED THAT THE WIRE HARNESS FOR THE NR 3 FUEL QTY PROBE WAS CHAFING ON THE FUEL DAM LOCATED INSIDE THE LEFT TANK. INSPECTION OF THE RT TANK ALSO DISCOVERED THAT THIS SAME CHAFING WAS PRESENT. BOTH LEFT AND RIGHT HARNESSES WERE REPLACED. THE HARNESS WAS REPOSITIONED SO AS NOT TO COME IN CONTACT WITH THE FUEL TANK. 2L72 4F4 FRTA21EA E15NE 20020220000092002022000009SO 2002 2 20 CA020123002 120020122G3245 TIRE PIPER PA31 PA31350 7103110SO LYC O540 TIO540J2BD 41532EA NLG PUNCTURED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) PILOTS VISUALLY NOTICED THAT THE NOSE WHEEL TIRE WAS FLAT AFTER THE AIRCRAFT WAS LANDED AND THE ENGINES WERE SHUT-DOWN. 1L72 3O3 O A20SO E14EA 20020220000102002022000010EA 2002 2 20 CA020123003 220020116G7210 GEARBOX BELL 212 212 1181420SW PWA PT6T PT6T3 52045EA REDUCTION GEAR CONTAMINATED W A UNSCHED LANDING J WARNING INDICATION CRCRUISE 1 CA 14924 (CAN) IN CRUISE FLIGHT THE PILOT THE PILOT NOTED THE C-BOX CHIP LIGHT FLICKER FAINTLY FOLLOWED SHORTLY BY THE C-BOX OIL PRESSURE CAUTION LIGHT ILLUMINATING.C-BOX OIL PRESSURE WAS OBSERVED DROPPING AND AN UNSCHEDULED BUT NORMAL LANDING PROCEDURE WAS CARRIED OUT. AFTER LANDING THE C-BOX OIL PRESSURE WAS OBSERVED TO DROP TO ZERO AND THE ENGINES WERE SHUT DOWN. NO EXTERNAL LEAKS WERE FOUND. AN ACCUMULATION OF METAL WAS FOUND ON THE REDUCTION (C-BOX) CHIP DETECTOR AND IN THE REDUCTION GEARBOX OIL FILTER. 1G71 4U4 U H4SW E22EA 20020220000112002022000011NE 2002 2 20 CA020123004 120020122G2913 SHAFT ABEX SKRSKYS76 S76A 8143006NE ALLSN 250C 250C30 03013GL HYD PUMP SHEARED W A UNSCHED LANDING J WARNING INDICATION CRCRUISE 1 CA 195853 (CAN) INFLIGHT INDICATION OF PRESSURE LOSS NR 1 SYSTEM. INSPECTION REVEALED PUMP SHAFT SHEARED AND BRASS PARTICLES IN FILTER. 1G72 3U3 U H1NE E1GL 20020220000122002022000012EA 2002 2 20 CA020124002 120020123G3040M7A16 WIRE DHAV DHC6 DHC6100 2802610EA PWA PT6 PT6A20 52043EA WINDSHIELD WIPERSHORTED W A UNSCHED LANDING B SMOKE/FUMES/ODORS/SPARKS CRCRUISE 1 CA (CAN) WIRE INSULATION WAS FOUND BURNED AND APPEARED TO HAVE SHORTED OUT ON OVERHEAD SWITCH PANEL IN FLIGHT COMPARTMENT, WHICH CAUSED ELECTRICAL BURNING ODOR IN THE FLIGHT DECK. 1H72 3T3 TRTA9EA E4EA 20020220000142002022000014EA 2002 2 20 CA020124004 120020115G21618161014 CONTROLLER CNDAIRCL600 CL6002B19 1900309EA GE CF34 CF343B1 NE CABIN TEMP FAULTY W O OTHER B SMOKE/FUMES/ODORS/SPARKS NRNOT REPORTED 1 CA (CAN) SMOKE IN CABIN DUE TO RT PACK OVER TEMP IN AUTO, REVERTED TO MANUAL TEMPERATURE CONTROL. FOUND TO BE THE TEMP CONTROLLER AT FAULT. REPLACED THE TEMPERATURE CONTROLLER. 2L72 4F4 FRTA21EA E15NE 20020220000152002022000015EA 2002 2 20 CA020124005 120020114G32347179015 CONTROL HANDLE CNDAIRCL600 CL6002B19 1900309EA GE CF34 CF343A1 30015NE MLG FAILED W O OTHER N FALSE WARNING APAPPROACH 1 CA (CAN) GEAR DISAGREE LIGHT ON APPROACH INTO WASHINGTON. CREW CONDUCTED A GO AROUND THEN CARRIED OUT A MANUAL EXTENSION. AFTER LANDING THE NOSE STEERING WAS INOPERATIVE. FOUND TO BE THE LANDING CONTROL LEVER AT FAULT. REPLACED LANDNG CONTROL LEVER, OPERATIONAL CHECK CARRIED OUT, SYSTEM FOUND SERVICEABLE. 2L72 4F4 FRTA21EA E15NE 20020220000162002022000016NM 2002 2 20 CA020124006 120020106G2821AC92272080D2A FILTER BOEING767 767333 1385301NM GE CF6 CF680C2B6F 30025NE FUEL SYSTEM FAILED W O OTHER J WARNING INDICATION NRNOT REPORTED 1 CA (CAN) FLIGHT CREW REPORT THAT THEY HAD A FUEL FILTER LIGHT ON EICAS FOR BOTH ENGINES. FOUND TO BE FINE MANUFACTURING DEBRIS (NEW AIRCRAFT). REPLACED TWO FILTERS AND DRAIN ALL RESERVOIRS, GROUND RUN AND LEAK CHECK CARRIED OUT. FLEET MANAGEMENT REQUEST TO HAVE BOTH FILTERS REPLACED AFTER 5 FLIGHT CYCLES. 2L72 4F4 FRTA1NM E13NE 20020220000172002022000017NM 2002 2 20 CA020124007 120020111G2910AE83580K COUPLING BOEING767 767233 1385113NM PWA JT9 JT9D7R4D 52054NE HYD LINE BROKEN W A UNSCHED LANDING KJ FLUID LOSS WARNING INDICATION CLCLIMB 1 CA (CAN) AFTER TAKEOFF FROM TORONTO AS FLAPS WERE RETRACTING FROM 1 TO UP, CENTRE HYDRAULIC QUANTITY AND C HYDRAULIC SYSTEM PRESSURE DISPLAYED EICAS MESSAGES / CAUTIONS AND HYDRAULIC PRESS LIGHTS ANNUNCIATED, THE AIRCRAFT RETURNED TO TORONTO USING ALTERNATE FLAPS/GEAR EXTENSION.FOUND AIR DRIVEN PUMP PRESSURE LINE COUPLING BROKEN.REPLACED ADP PRESSURE LINE COUPLING, CASE DRAIN FILTER CHECKED FOR CONTAMINATION AND FOUND CLEAN. SYSTEM LEAK CHECKED AND OPERATIONAL CHECK ALSO CARRIED OUT, AIRCRAFT FOUND SERVICEABLE. 2L72 4F4 FRTA1NM E3NE 20020220000182002022000018 2002 2 20 CA020124008 420020118G23309700029005 CONTROL UNIT AIRBUS330 A330342 EU RROYCERB211 RB211TRENT77 NE SMU FAILED W H DEACTIVATE SYST/CIRCUITS BA SMOKE/FUMES/ODORS/SPARKS FLAME/FIRE NRNOT REPORTED 1 CA (CAN) ON THE PRE-DEPARTURE CHECK THE SMU (SYSTEM MANAGEMENT UNIT) CAUGHT ON FIRE NO EXTERNAL FLAME BUT FLAME AND WITHIN THE UNIT AND SMOKE COMING OUT OF THE UNIT.THE UNIT WILL HAVE A STRIP REPORT DONE AT THE MANUFACTURER FOR ANALYSIS. UNIT REPLACED. 1L72 4F4 FRTA46NM E39NE 20020220000232002022000023SO 2002 2 20 CA020125001 120020123G291041 HYDRAULIC SYSTEMCLEVELANDXXX30142 PIPER PA31T PA31T2 7103127SO PWA PT6 PT6A135 52043NE FLUID CONTAMINATED W D RETURN TO BLOCK O OTHER TXTAXI/GRND HDL 1 CA (CAN) LEFT BRAKE WAS DRAGGING DURING AIRCRAFT TAXIING. THE AIRCRAFT WAS TOWED TO HANGAR WHERE THE BRAKE SYSTEM WAS FOUND WORKING NORMALLY. THE BRAKE SYSTEM (CALIPER & MASTER CYLINDER) WAS DISASSEMBLED AND WATER CONTAMINATION WAS FOUND PRESENT IN THE HYDRAULIC FLUID. SYTEM WAS DRAINED, CLEANED AND REPLENISHED WITH NEW HYDRAULIC FLUID. NEW O-RINGS WERE INSTALLED. THE BRAKE SYSTEM WAS BLED AND TESTED OK. 1L72 3T4 TRTA8EA E4EA 20020220000242002022000024GL 2002 2 20 CA020125002 220020104G72106890493 BEARING ALLSN 6894171 BELL 206 206B 1181511SW ALLSN 250C 250C20B 03013GL GEARBOX CRACKED W E ENGINE SHUTDOWN J WARNING INDICATION TXTAXI/GRND HDL 1 CA CAG35537 (CAN) THIS AIRCRAFT RUNNING NORMAL. PILOT ON START HEARD A LOUD SQUEELING NOISE, THEN GOT A CHIP LITE. MAINTENANCE FOUND HUGE AMOUNTS OF METAL ON BOTH PLUGS. PROBLEM FOUND TO BE 2 1/2 BEARING FAILURE. 2 1/2 BEARNING ON SPUR ADAPTER, REPLACED. PROBLEM SEEMS TO BE FROM A HIGH N1 GEAR TRAIN VIBRATION. POSSIBLE OUT OF BALANCE COMPRESSOR. 1G71 3U3 U H2SW E4CE 20020220000252002022000025GL 2002 2 20 CA020125003 320020114G6114A2202 BEARING PIPER PA32 PA32300 7103212SO LYC O540 IO540K1A5 41532EA HARTZLHCC2Y HCC2YK1 GL PROPELLER WORN W K NONE O OTHER ININSP/MAINT 1 CA (CAN) BALLS HAD SEVERELY DENTED BEARING RACE (INBOARD). REPLACED. FORK HAD SEVERE WEAR FROM PITCH CHANGE BLOCKS.BEARING P/N A2202 FORK P/N B2457-7 1L71 3O3 O A3SO 1E4 5 CP920 20020220000272002022000027CE 2002 2 20 CA020125004 120020114G531005132831 DOOR FRAME CESSNA172 172N 2072434CE LYC O320 O320H2AD 41508EA MCAULY1C160 1C160DTM GL FUSELAGE CRACKED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) ON A 200 HOUR INSPECTION WHILE INSTALLING LT HEATING DUCT LOOKING THROUGH LIGHTNING HOLE AT BOTTOM LT DOOR POST. FOUND AN 1 1/2 INCH CRACK AT DOOR HINGE SCREWS. 1H71 3O3 ONT3A12 E274 5 NP910 20020220000282002022000028SO 2002 2 20 CA020125005 120020114G531076467003 DOOR FRAME PIPER PA44 PA44180 7104402SO LYC O360 O360E1A6 41514EA FUSELAGE CRACKED W K NONE O OTHER ININSP/MAINT 1 CA 11790 (CAN) THE INNER DOOR FRAME WAS FOUND CRACKED ALSO THE OUTER FRAME OF FUSELAGE SKIN WAS CRACKED. THE INNER FRAME WAS REPLACED. THE OUTER FRAME WAS CLEANED OF CORROSION TREATED AND ZING CHROMATED. THE OUTER CRACK WAS STOP DRILLED USING 7/64 INCH DIA STOP DRILL HOLE.NOTE: THE OUTER SKIN CRACK WILL BE MONITORED IF IT EXTENDS BEYOND STOP DRILL HOLES IT WILL HAVE TO BE REPLACED. NOTE: P/N & DESCRIPTION FOUND IN PARTS MANUAL FIGURE 10-31. 1L72 3O3 O A19S0 E286 20020220000292002022000029EA 2002 2 20 CA020125006 120020110G2720C3CF1985 CONTROL CABLE DHAV DHC3 DHC3 2800202EA PWA R1340 S3H1G 52016NE RUDDER WORN W K NONE O OTHER ININSP/MAINT 1 CA (CAN) CABLE FOUND WORN DURING 800 HOUR INSPECTION. CABLE INSTALLATION WAS NORMAL. CABLE WAS WORN INSIDE C3CF383-7 FAIRLEAD. THE FAIRLEAD CONDITION AND INSTALLATION WAS NORMAL. 1H71 3R3 R A815 E142 20020220000452002022000045EU 2002 2 20 CA020125007 120020125G6720 ADJUSTER SNIAS AS332 AS332L 8680809EU TMECA MAKILAMAKILA1A 60040EU ANTITORQUE PEDALCRACKED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) PEDAL ADJUSTER LOCATION PIN SUPPORT CRACKED CAUSING THE PEDAL ADJUSTER LEVER TO BE UNMOVEABLE AND THE PEDALS UNADJUSTABLE. 2G72 4U4 U H4EU E12NE 20020220000462002022000046NE 2002 2 20 CA020125008 220020121G7314 SEAL BOEING727 727227 1384078NM PWA JT8 JT8D9A 52048NE FUEL PUMP FAILED W EA ENGINE SHUTDOWN UNSCHED LANDING YJ ENGINE STOPPAGE WARNING INDICATION CRCRUISE 1 CA (CAN) NR 2 ENGINE LOW OIL PRESS AND QUANTITY IN CRUISE YHM-YWG.ENGINE SHUT DOWN AND AIRCRAFT RETURNED TO YHM.ENGINE INSPECTED I.A.W. PW M.M. 72-00 PAGE 664 AND FUEL PUMP MAIN CARBON SEAL REPLACED. 2L73 4F4 F A3WE E2EA 20020220000482002022000048EU 2002 2 20 CA020128002 120020118G5230D21761 DOOR AEROSPAS355 AS355F1 8680810EU ALLSN 250C 250C20F 03013GL CARGO SEPARATED W O OTHER D INFLIGHT SEPARATION CRCRUISE 1 CA (CAN) IN CRUISE FLIGHT LT BAGGAGE DOOR DEPARTED THE AIRCRAFT, HITTING THE LT ENGINE COWL. THE AIRCRAFT WAS INSPECTED BY A QUALIFIED AME, BAGGAGE DOOR REPLACED, ENGINE COWL REPAIRED AND THE AIRCRAFT WAS RETURNED TO SERVICE. 1G72 3U3 U H11EU E4CE 20020220000522002022000052CE 2002 2 20 CA020128004 120020115G541226530351 DOUBLER CESSNA208 208B 2073701CE PWA PT6 PT6A114A 52043NE MCAULY3AF34C3GFR34C703 GL FIREWALL CRACKED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) THE LOWER FWD DOUBLER IS SITUATED ON BOTTOM OF FIREWALL & SUPPORTS NOSEGEAR SPRING ATTACH. DOUBLER FOUND CRACKED ON ITS LT WEB NEAR BOTTOM. 1H71 3T3 T A37CE E4EA 5 CP60GL 20020220000582002022000058EA 2002 2 20 CA020129001 120020129G2840TJ13 TRANSMITTER DHAV DHC2 DHC2MK1 2800102EA PWA R985 R985AN14B 52008NE FUEL CELL LEAKING W K NONE K FLUID LOSS ININSP/MAINT 1 CA (CAN) TWO FUEL TRANSMITTERS WERE FOUND TO BE LEAKING DURING ROUTINE MAINTENANCE.REFER TO FIQURE 42 OF THE DHC 2 PARTS MANUAL FOR CLARIFICATION.THE GASKET ITEM 42 WAS FOUND TO BE LEAKING BETWEEN ITEM 43(FLANGE) AND ITEM 3(CASE). THE GASKET THAT SEPERATED THE ITEMS APPEARED TO BE SWOLLEN AND DISTORTED, 1H71 3R3 R A806 5E1 20020220000592002022000059EA 2002 2 20 CA020129002 120020128G2701C2CF1977 STRUCTURE DHAV C2CF833A DHAV DHC2 DHC2MK1 2800102EA PWA R985 R985AN14B 52008NE CONTROL COLUMN CRACKED W K NONE O OTHER ININSP/MAINT 1 CA 26981 391 (CAN) DURING INSPECTION OF CONTROL COLUMN BASE AS PER CF-84-01-R1 A CRACK WAS NOTED ON THE REAR FACING WELD FILLET. WHERE THE VERTICAL TUBE IS WELDED TO THE HORIZONTAL TUBE.THE ASSEMBLY WAS REMOVED FOR REPAIR AND A SERVICABLE UNIT WAS REINSTALLED. 1H71 3R3 R A806 5E1 20020220000602002022000060EA 2002 2 20 CA020129003 220020108G72303039901 BLADE DHAV DHC6 DHC6300 2802606EA PWA PT6 PT6A28 EA COMPRESSOR CRACKED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) WHILE CARRYING OUT A POST LEASE INSPECTION ON THE AIRCRAFT BOTH ENGINES ARE SPLIT AT THE "C" FLANGE FOR HOT SECTION INSPECTION. DURING THE RIGHT H.S.I. THE ENGINEER NOTICED "LINES" ON SOME OF THE C.T. BLADES. NINE BLADES SEEM TO BE CRACKED. SEVEN BLADES CRACKED FROM TIP HEADING TOWARDS ROOT. TWO SEEM CRACKED ACROSS THE BLADE FROM LEADING EDGE TO TRAILING EDGE. 1H72 3T4 TRTA9EA E4EA 20020220000622002022000062EA 2002 2 20 CA020129005 220020118G73203031448 TUBE PIPER PA31T PA31T 7103124SO PWA PT6 PT6A28 EA FUEL CONTROL CRACKED W C ABORTED TAKEOFF RJ PARTIAL RPM/PWR LOSS WARNING INDICATION TOTAKEOFF 1 CA 14606 (CAN) LEFT ENGINE WOULD NOT ACCELERATE ON INITIAL TAKEOFF. NG AT 44 PERCENT. NO RESPONSE FROM POWER LEVER, REJECTED TAKEOFF AND RETURNED TO RAMP. 1L72 3T4 T A8EA E4EA 20020220000632002022000063GL 2002 2 20 CA020129006 220020123G726023039794 PUMP RROYCE 250C30P BELL 206 206L1 1182107SW ALLSN 250C 250C30P 03013GL GEAR OIL GALLED W K NONE O OTHER ININSP/MAINT 1 CA CAG95735 (CAN) DURING REINSTALLATION OF ENGINE BY OPERATOR. ENGINE HAD NO OIL PRESSURE: OPERATOR NOTED UNUSUAL NOISE HEARD COMING FROM GEARBOX WHEN N1 GEAR TRAIN SPUN. GEARBOX RETURNED FOR REPAIR. UPON INSPECTION FUEL CONTROL / OIL PUMP FLEXIBLE COUPLING SHAFT FOUND FRACTURED. WHEN TURNED BY HAND N1 GEAR TRAIN ROTATED NORMALLY. OIL PUMP COULD NOT BE TURNED BY HAND. OIL PUMP REMOVED & DISASSEMBLED. ONEOF IDLER GEARS HAD METAL BUILD-UP ON END FACE. ADJACENT FACES ON GEAR POCKET & SEPARATOR WERE ALSO HEAVILY SCORED. GEAR END CLEARANCES WERE MEASURED&FOUND TO BE .0005 TO .0075, WHICH IS WITHIN ROLLS ROYCE OVERHAUL LIMITS. IT W AS CONCLUDED OIL PUMP HAD SEIZED DUE T 1G71 3U3 U H2SW E1GL 20020220000662002022000066SO 2002 2 20 CA020130004 120020124G78109904404 EXHAUST STACK PIPER PA28 PA28140 7102802SO LYC O320 O320E3D 41508EA ENGINE CRACKED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) CRACKED EXHAUST STACK FROM CYLINDER NR 3 MELTED THE CARB HEAT CABLE INTERIOR LINING CAUSING THE CABLE TO BE VERY STIFF. CABLE. CRACK LOCATED INSIDE THE CARB HEAT SHROUD AT THE MOST FORWARD POINT WHICH IS VERY DIFFICULT TO INSPECT. RECOMMEND REMOVE SHROUD PERIODICALLY FOR BETTER INSPECTION. EXHAUST STACK WALL EROSION IS DIFFICULT TO DETECT. 1L71 3O3 O 2A13 E274 20020220000712002022000071SW 2002 2 20 CA020131002 120020118G5302222035231105 FITTING BELL 222 222U 1182140SW LYC LTS101LTS101750C1 41560NE VERTICAL FIN BROKEN W K NONE O OTHER ININSP/MAINT 1 CA (CAN) VERTICAL LOWER FIN FITTING FOUND ATTACHMENT LUG BROKEN OFF ON A PRE FLIGHT. 1G72 3U3 U H9SW E5NE 20020220000732002022000073SW 2002 2 20 CA020131003 120020129G2910212076301001 LINE BELL 212 212 1181420SW PWA PT6T PT6T3 52045EA NR 1 HYD SYSTEM BROKEN W A UNSCHED LANDING KJ FLUID LOSS WARNING INDICATION DEDESCENT 1 CA (CAN) HE AIRCRAFT NR 1 HYDRAULIC SYSTEM LOST SYSTEM PRESSURE(FLUID LOSS). THE ENGINEER FOUND A HYDRAULIC TUBE BROKEN IN THE MID POINT. 1G71 4U4 U H4SW E22EA 20020220000802002022000080NM 2002 2 20 CA020201003 120020118G612078249047 PCU DHAV DHC8 DHC8301 NM PWA PW120 PW123 NE HAMSTD14SF 14SF23 NE PROPELLER FAILED W C ABORTED TAKEOFF REJPARTIAL RPM/PWR LOSS VIBRATION/BUFFET WARNING INDICATION TOTAKEOFF 1 CA (CAN) JOURNEY LOG: TAKEOFF ABORTED DUE TO ENGINE NR 2 TORQUE NOT PASSING 60 PERCENT. ON SHUTDOWN PROP NR 2 WOULD NOT FEATHER. AIRCRAFT RETURNED TO GATE DUE TO NR 2 ENGINE SLUGGISH TO ACCELERATE, PROP FOUND NOT TO BE FEATHERING AUTOMATICALLY OR MANUALLY. INSPECTION ON PROP HUB ASSEMBLY, PCU REPLACED AS PER MM, ENGINE RUNS CARRIED OUT, OK. REPLACEMENT OF THE PCU WAS THE FINAL FIX. 2H72 4T4 TRTA13NM E20NE 6 CP7NE 20020220000812002022000081NM 2002 2 20 CA020201004 120020122G3297471515 WIRE HARNESS DHAV DHC8 DHC8* NM PWC 150 PW150A EA NLG SQUAT SWITCHSHORTED W A UNSCHED LANDING RJ PARTIAL RPM/PWR LOSS WARNING INDICATION CRCRUISE 1 CA (CAN) WEIGHT ON WHEELS CAUTION LIGHT ILLUMINATED IN FLIGHT. RELANDING DUE TO CAUTION LIGHT "WT ON WHEEL" INTERMITTENTLY ON. UNEVENTFUL RE-LANDING.FOUND SENSORS WIRING, TWISTED SHIELDED PAIR, SHORTED TO SHIELD. SENSOR REPLACED. 2H72 4T4 TRTA13NM E00062EN 20020220000822002022000082EU 2002 2 20 CA020201010 120020121G2435 WIRE BRAERODH125 HS125700A 4230170EU GARRTTTFE731TFE7313R 01518WP STARTER GEN WORN W K NONE O OTHER ININSP/MAINT 1 CA (CAN) LT ENGINE STARTER GENERATOR WIRING WORN AT SUPPORT BRACKET. 2L72 4F4 F A3EU E6WE 20020220000842002022000084EU 2002 2 20 CA020201012 120020121G2435257ES2873 FAIRLEAD BRAERODH125 HS125700A 4230170EU GARRTTTFE731TFE7313R 01518WP STARTER GEN BROKEN W K NONE O OTHER ININSP/MAINT 1 CA (CAN) LT ENGINE STARTER GENERATOR WIRING WORN AT SUPPORT BRACKET AND PHENOLIC FAIRLEAD BROKEN. 2L72 4F4 F A3EU E6WE 20020220000892002022000089EU 2002 2 20 CA020201015 120020119G2611 SMOKE DETECTOR AIRBUS320 A320211 3930320EU CFMINTCFM56 CFM565A1 NE E/E BAY FAILED W A UNSCHED LANDING N FALSE WARNING CLCLIMB 1 CA (CAN) AFTER TAKEOFF, AVIONIC VENT SMOKE MESSAGE, NO APPARENT OF SMOKE OR SMELL. RAT DEPLOYED. SMOKE INDICATION DISAPPEARED BEFORE LANDING. FLIGHT RETURNED TO FORT LADERDALE. AVIOINIC COMPARTMENT INSPECTED FOR EVIDENCE OF SMOKE, BLOWN DUCTS OR OVERHEATED EQUIPMENT. NO FAULT FOUND. SUSPECT BAD SMOKE DETECTOR INSTALLED. RAT RETRACTED AND TESTED. SMOKE DETECTION SYSTEM TESTED SERVICEABLE. 2L72 4F4 FRTA28NM E29NE 20020220000902002022000090EA 2002 2 20 CA020201017 120020119G5270 SENSOR CNDAIRCL600 CL6002B19 1900309EA GE CF34 CF343A1 30015NE PAX DOOR CONTAMINATED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) ON DEPARTURE THROUGH 4000 FT PAX OR LATCH. CAUTION MSG ILLUMINATED. CHECKLIST CARRIED OUT WITH PRESSURIZATION NORMAL. DECIDED ATO CONTINUE THROUGH 10000 FT, PASSENGER DOOR WARNING MSG WITH NORMAL PRESSURIZATION.AIRCRAFT RETURNED TO TORONTO. ON ARRIVAL FOUND DOOR HANDLE LATCH LOCK ALMOST UNLATCHED. FOUND EXCESS GREASE ON SENSORS, SENSORS CLEANED. PSEU MEMORY RESET AND DOOR OPERATION AND INDICATION CHECKED OK. 2L72 4F4 FRTA21EA E15NE 20020220000912002022000091EA 2002 2 20 CA020201018 120020120G5210 DOOR LATCH CNDAIRCL600 CL6002B19 1900309EA GE CF34 CF343A1 30015NE PAX DOOR LACK OF LUBE W K NONE O OTHER ININSP/MAINT 1 CA (CAN) DURING FLIGHT, AIRCRAFT WAS DIVERTED DUE TO PASSENGER DOOR FAULT. FOUND PASSENGER DOOR LATCH RED HANDLE STICKING. CLEANED AND LUBED, OPERATED DOOR SEVERAL TIMES, DOOR OPERATION AND INDICATION OK. 2L72 4F4 FRTA21EA E15NE 20020220000932002022000093EA 2002 2 20 CA020201019 120020106G4940897889 APU CNDAIRCL600 CL6002B19 1900309EA GE CF34 CF343A1 30015NE APU BAY FAILED W FO ACTIVATE FIRE EXT. OTHER J WARNING INDICATION NRNOT REPORTED 1 CA (CAN) AT 10,000 FT TRIED TO START THE APU, NO LIGHT OFF. APU SELECTED OFF. 2 MINUTES LATER, ATTEMPTED ANOTHER START, START COMPLETED, FUEL TRANSFERRED WITH STRONG SMELL OF FUEL, EGT HIGHER THAN NORMAL WITH ONE FIRE DETECTOR LOOP INOP. APU SHUTDOWN AND FIRE BOTTLE DISCHARGED. APU FIRE EXTINGUISHER BOTTLE AND SQUIB REPLACED. FIRE DETECTION LOOP REPLACED. SYSTEM TESTED SERVICEABLE. APU AND ENGINES RUN FOR 3 MINUTES, NO SMELL OF FUEL, ALL SYSTEMS OPERATE NORMAL. AIRCRAFT SERVICEABLE. 2L72 4F4 FRTA21EA E15NE 20020220000942002022000094EA 2002 2 20 CA020201020 120020110G322216050105 LANDING GEAR CNDAIRCL600 CL6002B19 1900309EA GE CF34 CF343A1 30015NE NLG FAILED W O OTHER J WARNING INDICATION CLCLIMB 1 CA (CAN) GEAR DISAGREE WARNING AFTER LANDING GEAR SELECTED UP ON TAKEOFF (NOSE GEAR UNSAFE). AIRCRAFT RETURNED TO BASE.AFTER EXTENSIVE TROUBLE SHOOTING, NEW NOSE LANDING GEAR ASSEMBLY INSTALLED. 2L72 4F4 FRTA21EA E15NE 20020220000952002022000095EU 2002 2 20 CA020201023 120020123G3230114079015 SELECTOR VALVE AIRBUS320 A320211 3930320EU CFMINTCFM56 CFM565A1 NE MLG FAILED W O OTHER J WARNING INDICATION DEDESCENT 1 CA (CAN) ON FINAL APPROACH TO VANCOUVER AT 1600 AGL "L/G NOT DOWNLOCKED" WARNING CAME ON. GEARS CYCLED. ALL EXTENDED NORMALLY THE SECOND TIME. THE GEAR AT FAULT WAS THE RT MAIN. MAIN LANDING GEAR SELECTOR VALVE REPLACED AS PER AMM TASK 32-31-12-400-001, LEAK CHECKED AND GEAR RETRACTED SEVERAL TIMES, NO FAULT FOUND. 2L72 4F4 FRTA28NM E29NE 20020220000962002022000096EU 2002 2 20 CA020201024 120020124G3231201122006 UPLOCK AIRBUS320 A320211 3930320EU CFMINTCFM56 CFM565A1 NE LT MLG DOOR FAILED W A UNSCHED LANDING J WARNING INDICATION CLCLIMB 1 CA (CAN) CLIMBING THROUGH 16,000 FT AT 265 KTS ECAM L/G DOOR OPEN. SLOWED TO 215 KTS. GEARS RECYCLED AS PER MAINTENANCE REQUEST, NO CHANGE. AMBER DOOR LIGHT INDICATION REMAINS ON UNTIL GEAR SELECTED DOWN. AIRCRAFT RETURNED TO TORONTO. LT MAIN LANDING GEAR DOOR UPLOCK REPLACED AS PER AMM 32-31-33. DOOR OPERATION CHECK CARRIED OUT. NO FAULT FOUND. AIRCRAFT SERVICEABLE. 2L72 4F4 FRTA28NM E29NE 20020220000992002022000099NE 2002 2 20 CA020201026 220020124G7200 ENGINE AIRBUS330 A330243 3930330EU RROYCERB211 RB211TRENT77 NE NR 2 VIBRATION W A UNSCHED LANDING EJ VIBRATION/BUFFET WARNING INDICATION CLCLIMB 1 CA (CAN) VIBRATION ON NR 2 ENGINE, (DURING CLIMB) INCREASING WITH ALTITUDE , ADVISORY 3.5 UNIT AT 22 000 FT AT 5.0 UNIT , FELT AIRFRAME VIBRATION. THE AIRCRAFT MADE AN AIR TURN BACK. A BLADES OFF INSPECTION WAS CARRIED OUT I.A.W. ENGINEERING ORDER 5-7231-001 ( BLADE ROOT INSP. C/OUT , NO FAULTS FOUND, BLADE ROOTS WERE CLEANED , LUBRICATED AND RE-INSTALLED) ENGINE RUN C/OUT SERVICEABLE.NOTE THE AIRCRAFT MADE AN OVERWEIGHT LANDING IN YMX AT 206 000 KGS , AUTOLAND PERFORMED , TOUCH DOWN AT 200 FEET/MINUTE.NO INSP. FOR HARD/OVERWEIGHT LANDING REQUIRED I.A.W. AMM 05-51-11-200-801. 2L72 4F4 FRTA46NM E39NE 20020220001002002022000100NE 2002 2 20 CA020204002 220020201G7200658536916 BULLET BOEING737 737281 138448PNM PWA JT8 JT8D17 52049NE NR 2 ENGINE SEPARATED W A UNSCHED LANDING D INFLIGHT SEPARATION CLCLIMB 1 CA (CAN) FLT CREW RPTED DURING CLIMB AFTER TAKEOFF THEY EXPERIENCED SERIES OF LOUD BANGS FROM NR 2 ENGINE ACCOMPANIED BY ABNORMAL HIGH EGT & LOW N 2 RPM. ALL IND.S WERE NORMAL PRIOR TO NOICE. PROBLEM OCCURRED AFTER CLIMB THRUST SET. THE CREW REDUCED NR 2 THRUST TO ALMOST IDLE, AS PER ENGINE LIMITS / SURGE / STALL QUICK REF CHART (QRC) AND ENGINE OPERATED NORMALLY. A/C RETURNED&LANDED W/O INCID. - CFR WERE NOTIFIED&ON STANDBY.INIT MAINT INSPECTION FOUND NR 2 ENGINE NOSE CONE BULLET HAD SEPARATED FROM ITS ATTACHMENTS & JAMMED INTO ENGINE INLET GUIDEVANES. MAINT REPL ENGINE, 2L72 4F4 F A16WE E2EA 20020220001022002022000102EU 2002 2 20 CA020205001 220020127G8530N854115 EXHAUST VALVE DIAMONDA20 DA20A1 2990000GL ROTAX 912 ROTAX912 55555EU ENGINE CHIPPED W A UNSCHED LANDING RE PARTIAL RPM/PWR LOSS VIBRATION/BUFFET CLCLIMB 1 CA (CAN) SHORTLY AFTER T/O, A PARTIAL ENGINE POWER LOSS WAS EXPERIENCED WITH ASSOCIATED ENGINE VIBRATION AND REDUCED CLIMB PERFORMANCE.THE AIRCRAFT RETURNED TO THE AIRPORT TO LAND. THE COMPRESSION WAS FOUND TO BE LOW IN THE NR 3 CYLINDER. AIR WAS FOUND TO BE LEAKING OUT THE EXHAUST. THE EXHAUST VALVE WAS FOUND TO HAVE A 1/16 IN DIA HOLE.THE VALVE HAD ALSO MADE CONTACT WITH THE PISTON.TWO FLIGHTS PRIOR TO THE INCIDENT FLIGHT THE ENGINE EXPERIENCED A SUBSTANTIAL BACKFIRE ON SHUTDOWN DUE TO SHUTTING DOWN AT HIGH POWER.IT IS UNCLEAR IF THIS CONTRIBUTED TO THE DAMAGED VALVE. 1L71 3O3 INTTA4CH EXPE3I 20020220001052002022000105NE 2002 2 20 CA020205002 120020128G321314102B CYLINDER CONAERC2 C2 5110202NE LYC O360 O360A1A 41514EA MLG FAILED W O OTHER R PARTIAL RPM/PWR LOSS LDLANDING 1 CA (CAN) A/C C-2 SKIMMERS, BOTH UTILIZE COLONIAL STYLE MAIN UNDER CARRIAGE OLEOS. ONE OLEO PER A/C CAME APART.THE MAIN GEAR OLEOS ARE CRACKING AT LOWER END CAP TO CYLINDER (CASING) ATTACH BOLTS. WHEN THIS OCCURS, BEFORE LONG END CAP DISLODGES FROM OLEO CAUSING GEAR LEG & TRAILING DRAG ARM TO COLLAPSE.THE CRACKS IN THIS AREA HAVE ALSO BEEN FOUND ON NEWER STYLE GERDES & AEROFAB MANUFACTURED OLEOS, P/N 2-4111-11 INST ON LA-4 SERIES A/C. IF CRACKS ARE FOUND, LAKE A/C REPAIR IS TO ROTATE END CAP WITHIN CYLINDER, RE-DRILL & INST NEW HARDWARE. 1H71 3O3 O 1A13 E286 20020220001062002022000106NE 2002 2 20 CA020205003 120020124G791041650 CAP SKRSKYS61 S61N 8142104NE GE CT58 CT581401 30011NE OIL TANK FAILED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) DURING PHASE IVA OPS 6, WE FOUND OIL CONTAMINATION ON ENGINE NR 2 TANK. THE PACKING P/N MS29513-232 ON THE CAP ASSEMBLY P/N 416-50 TO BE THE CAUSE. REPLACED THE PACKING, FLUSHED OIL AND CHANGE OIL FILTER. RAN THE AIRCRAFT FOR 15 MINUTES AND AFTER OIL AND FILTER WILL BE REPLACED. IF NO FURTHER CONTAMINATION AIRCRAFT WILL BE RETURNED TO SERVICE. 2G72 4U4 U 1H15 1E3 20020228000032002022800003 2002 2 28 CA020115001 420020109G3425 SYMBOL GENERATORBENDIX 0660402111 PILATSPC12 PC1245 7090551EU PWA PT6 PT6A67B 52043NE HARTZLHCE4A HCE4A3D GL INTERNAL INOPERATIVE W D RETURN TO BLOCK H ELECT. POWER LOSS-50 PC ININSP/MAINT 1 CA 4481 (CAN) WHEN A/C POWERED UP, LOWER PILOT'S EFIS DISPLAY REMAINED BLANK. LOWER CO-PILOTS EFIS DISPLAY SWITCHED FOR TROUBLE SHOOTING. DISPLAY ALSO REMAINED BLANK. WHEN DISPLAY RETURNED TO IT'S ORIG POSSITION, IT REMAINEDBLANK AS WELL. IT DETERMINED THROUGH FURTHER TROUBLE SHOOTING THAT PILOT'S SG-465 SYMBOL GEN P/N 066-04021-11-11, S/N 4481, DEFECTIVE. IT CAUSED INTERNAL DAMAGE TO LOWER PILOT'S EFIS DISPLAY, P/N 066-03125-2500, S/N 3486. WHEN CO-PILOT'S EFIS DISPLAY INST IN POSSITION, IT TOO DAMAGED BY DEFECTIVE SYMBOL GEN. WHEN EFIS DISPLAY RETURNED TO IT'S ORIG POSSITION, IT IN TURN DAMAGED CO-PILOTS SYMBOL GEN,S/N 3354. PI LOT'S SYMBOL GEN&LOWER EFIS DISPLAY, AND 1L71 3T4 TRTA78EU E26NE 5 CP210NE 20020228000042002022800004NE 2002 2 28 CA020211003 220020130G72605018T49P01 CARBON SEAL GE CF343A1 CNDAIRCL600 CL6002B19 1900309EA GE CF34 CF343A1 30015NE ON R/H ENGINE DAMAGED W E ENGINE SHUTDOWN J WARNING INDICATION CRCRUISE 1 CA (CAN) AIRCRAFT TAT:4900.3 FLIGHT 5589 FROM CVG TO MKE.R. ENGINE LOW OIL PRESSURE WARNING IN FLIGHT. PERFORMED QRH. R. ENGINE TO IDLE, MSG WOULD NOT CLEAR. SHUT ENGINE DOWN. ENGINE OIL PSI FLUCTUATES BETWEEN 21 TO 30 PSI.DIVERTED TO GRR, DECLARED AN EMERGENCY AND LANDED.FOUND ENGINE 5 QTS LOW ON ARRIVAL AT GRR. REPLENISHED SYSTEM. SUBSEQUENTLY FAILED OIL CONSUMPTION RUN CHECK. (2 QUARTS USED). FOUND STARTER AND IDG CARBON SWALS CARBON SEALS P/N 5018T49P01 AND 5016T32P01 LEAKING.REPLACED SEALS. AIRCRAFT RETURNED TO SERVICE. 2L72 4F4 FRTA21EA E15NE 20020228000052002022800005WP 2002 2 28 CA020215008 120020214G5302C0231 TAIL CONE ROBSIN C0231 ROBSINR44 R44 7640120WP LYC O540 O540F1A5 41532EA TOP SKIN CRACKED W K NONE O OTHER ININSP/MAINT 1 CA 0253 (CAN) 2 INCH CRACK FOUND ON TOP SKIN OF TAIL CONE AT LOCATION OF AFT FACTORY INSTALLED VHF ANTENNA MOUNT 51.5 TO 53.5 INCHES AFT OF FORWARD TAIL CONE SKIN. CRACK APPEARS TO HAVE ORIGINATED FROM TAPERED FACTORY SHIM PN B322-1. 1G71 3O3 O H11NM E295 20020228000062002022800006EU 2002 2 28 CA020215011 120020207G28209170M59P03 FUEL LINE GE CF650C2 AIRBUS300 A300B4203 3930306EU GE CF6 CF650C2 30018NE AT 'B' NUT RANGEBROKEN W A UNSCHED LANDING Y ENGINE STOPPAGE CRCRUISE 1 CA 455262 (CAN) WHILE IN CRUISE THE #1 ENGINE SHUTDOWN BY ITSELF. COULD NOT RE-START THE ENGINE. CAPTAIN DECIDED TO LAND IN HOUSTON, TEXAS. MAINTENANCE FOUND A BROKEN FUEL LINE ON THE MEC GOING TO VARIABLE STATOR ACTUATOR. 2L72 4F4 FRTA35EU E23EA 20020228000072002022800007EA 2002 2 28 CA020221005 120020213G7620 ENGINE GE CF343B1 CNDAIRCL600 CL6002B19 1900309EA GE CF34 CF343B1 NE ENGINE FAILED W A UNSCHED LANDING E VIBRATION/BUFFET CLCLIMB 1 CA 872329 (CAN) AIRCRAFT WAS CLIMBING THROUGH 21K, ENGINE VIBE WENT TO 2.6, THEN ENGINE SHUT DOWN UNCOMMANDED. FLIGHT ATTENDANT REPORTED HEARING A "BANG" IN THE CABIN. ON THE GROUND, OIL WAS NOTED ON THE COWLINGS AND IN THE TAIL PIPE.PREPARATIONS BEING MADE FOR A CREW TO GO TO FWA TO PERFORM ENGINE CHANGE. REMOVED AND AREPLACED ENGINE. AIRCRAFT RETURNED TO SERVICE. 2L72 4F4 FRTA21EA E15NE 20020301000442002030100044NE 2002 3 1 HEEA077705 220020219G73200292958050 VALVE SNIAS 350 AS350B 8680801EU TMECA ARRIELARRIEL1D NE ENGINE FAILED E HEEAO OTHER O OTHER NRNOT REPORTED 1 SW03971AE1104 3230 22072 ENGINE WOULD START INTERMITTENTLY. 1G71 3U3 U H9EU E19EU 20020304001212002030400121EA 2002 3 4 CA020207004 120020206G52106003189021 BELLCRANK CNDAIR CL6012A12 CNDAIRCL601 CL6012A12 1900303EA GE CF34 CF341A NE NIL W K NONE O OTHER ININSP/MAINT 1 CA 3037 (CAN) DOOR HARD TO OPEN: INSPECTION FOUND CRANK ASSY CRACKED (P/N 600-31890-21) - PART CRACKED DUE TO IMPROPER INSTALLATION OF SB 601-0192 - DOGS OF LOST MOTION CRANK NOT CONTACTING DRIVE CRANK AND COLLAR SIMULTANIOUSLY. THIS CAUSED STRESS ON OPPOSITE EARS CAUSING EACH TO CRACK. 2L72 4F4 FRTA21AE E15NE 20020304001222002030400122EA 2002 3 4 CA020215003 120020212G5610NP1393215 WINDSHIELD PPG NP1393215 CNDAIRCL600 CL6002B19 1900309EA GE CF34 CF343B1 NE WINDSHIELD CRACKED W K NONE O OTHER ININSP/MAINT 1 CA 00229H5665 (CAN) RIGHT WINDSHIELD FOUND CRACKED ON THE GROUND. WINDSHIELD REMOVED AND REPLACED.THE WINDSHIELD INSTALLED WAS A PRE SERVICE BULLETIN WINDSHIELD. 2L72 4F4 FRTA21EA E15NE 20020304001232002030400123EA 2002 3 4 CA020215006 120020116G2613356072310 ELEMENT FENWAL CNDAIRCL600 CL6002B19 1900309EA GE CF34 CF343A1 30015NE ELEMENT FAILED W O OTHER O OTHER ININSP/MAINT 1 CA (CAN) LEFT 14TH DUCT WARNING ON AT TAKEOFF ROLL ABOVE V, ON EICAS, RED BY ENGINE. AIRCRAFT RETURNED TO TORONTO. RIGHT BLEED LEAK DETECTION CONTROL UNIT AND LOOP SENSING ELEMENT (A58WK) REPLACED.OPERATIONAL TEST OF 14TH STAGE BLEED PERFORMED AND OPERATION TEST OF BLEED LEAK DETECTION PERFORMED.ALL TESTS OK UNABLE TO FAULT SYSTEM, CHECKED SERVICEABLE. 2L72 4F4 FRTA21EA E15NE 20020426001122002042600112EA 2002 4 26 CA020221008 120020215G7603NAS464P416 BOLT CNDAIRCL600 CL6002B19 1900309EA GE CF34 CF343B1 NE THROTTLE WORN W E ENGINE SHUTDOWN E VIBRATION/BUFFET DEDESCENT 1 CA (CAN) DURING DESCENT, THE FLIGHT CREW WERE UNABLE TO RETARD THE NR 1 THROTTLE LEVER. THE ENGINE WAS SHUTDOWN THROUGH THE GLARE SHIELD'S FIRE PUSH BUTTON. EMERGENCY LANDING WAS DECLARED. MAINTENANCE STAFF VERIFIED THE BOLT SECURING THE "THROTTLE CONTROL LEVER ASSEMBLY" TO THE DOUBLE SPLINE EXHIBITED WEAR. "ROD ASSEMBLY" FOUND DISPLACED, AWAY FROM THE GEARBOX ASSEMBLY UNTIL THE ROD END'S RIVET CONTACTED WITH THE HEAT SHIELD BRACKET (BINDING CONDITION).BOLT REPLACED, THROTTLE CONTROL LEVER ASSEMBLY AND ROD ASSEMBLY REINSTALLED AND SECURED AS PER AMM. AIRCRAFT RETURNED TO SERVICE. 2L72 4F4 FRTA21EA E15NE 20020304001242002030400124NE 2002 3 4 CA020227003 220020131G8520SL74309 BEARING LYC TIO540J2B PIPER PA31 PA31 7103102SO LYC O540 TIO540J2B NE HARTZLHCC4Y HCC4YR2 GL BEARING DESTROYED W K NONE Y ENGINE STOPPAGE ININSP/MAINT 1 CA L429361A (CAN) #6 CON ROD BEARING FAILURE. PARTS RETURNED TO SUPERIOR AIR PARTS FOR EXAMINATION.THESE BEARINGS ARE A BIMETAL AS OPPOSED TO A TRIMETAL THAT WAS USED FOR MANY YEARS. I HAVE RECIEVED REPORTS FROM AUSTRALIA OF SEVERAL FAILURES OF THIS TYPE OF BEARING 1L72 3O3 O A20SO E14EA 5 CP52GL 20020304001252002030400125EA 2002 3 4 CA020228012 220020216G7323 GOVERNOR BENDIX 25249994 BELL 212 212 1181420SW PWA PT6T PT6T3 52045EA GOVERNOR W D RETURN TO BLOCK E VIBRATION/BUFFET HOHOVERING 1 CA C8103 (CAN) COCKPIT INDICATION OF ENGINE TORQUE SPLIT DURING HOVER TAXI, AIRCRAFT RETURNED TO RAMP. TORQUE SPLIT CAUSED BY N2 GOVERNOR FAILURE CONFIRMED BY UNIT REPLACEMENT. 1G71 4U4 U H4SW E22EA 20020304001262002030400126EU 2002 3 4 AUS20020041 120020118G21502676C010 DUCT BAC 146 146200A 1500266EU LYC ALF502ALF502R5 41580NE CABIN COOLING SYCRACKED W K NONE J WARNING INDICATION TOTAKEOFF 1 AUS (AUS) NO2 AIR CYCLE MACHINE INLET PIPE CRACKED. 2H74 4F4 F A49EU E6NE 20020304001272002030400127EU 2002 3 4 AUS20020044 120020121G8000S1991A1 RELAY LYC AEIO360B2F MUDRY 10 CAP10B 0950102EU LYC O360 AEIO360B2F 41514EA HOFMANHO29 HO29HM180 EU ENGINE STARTING FAULTY W K NONE E VIBRATION/BUFFET NRNOT REPORTED 1 AUS (AUS) STARTER RELAY FAULTY. 1L71 3O3 O A36EU 1E10 5 NP3EU 20020304001282002030400128SO 2002 3 4 AUS20020046 120020118G27316270142 CABLE PIPER PA32 PA32RT300 7103215SO LYC O540 IO540K1G5 41532EA HARTZLHCC2Y HCC2YK1 GL ELEVATOR TAB CONFAILED W K NONE F FLT CONT AFFECTED CLCLIMB 1 AUS (AUS) STABILATOR TRIM CABLE SEPARATED AT ELECTRIC TRIM SERVO ACTUATOR. 1L71 3O3 O A3SO 1E4 5 CP920 20020304001292002030400129SO 2002 3 4 AUS20020048 220020116G8520 CONNECTING ROD CONT TSIO520E CESSNA402 402B 207590PCE CONT O520 TSIO520E 17040SO MCAULY3AF32C3AF32C87 GL RECIPROCATING ENFAILED W K NONE EK VIBRATION/BUFFET FLUID LOSS DEDESCENT 1 AUS (AUS) RH ENGINE INTERNAL FAILURE. INSPECTION FOUND HOLES IN THE FORWARD END OF THE CRANKCASE IN THE AREA OF NO5 AND NO6 CYLINDERS. ON DISASSEMBLY MASSIVE INTERNAL DAMAGE FOUND. CONNECTING ROD FOUND IN SUMP. CAMSHAFT BROKEN. SUSPECT CONNECTING ROD OR CONNECTINGROD BOLT FAILURE. 1L72 3O3 O A7CE E8CE 5 CP22EA 20020304001302002030400130CE 2002 3 4 AUS20020049 120020118G3233JRA4582 ACTUATOR CESSNA210 210N 2073453CE CONT O520 IO520L 17032SO MCAULY3A32C D3A32C88 GL LANDING GEAR ACTFAULTY W K NONE O OTHER ININSP/MAINT 1 AUS BATCH2 (AUS) MAIN LANDING GEAR ACTUATOR HAS NO PROVISION FOR SEPARATION WASHER AND FELT. 1H71 3O3 O 3A21 E5CE 5 CP21EA 20020304001312002030400131NM 2002 3 4 AUS20020050 120020123G2824BACC63CE14S5S PLUG BOEING737 737376 NM CFMINTCFM56 CFM563C 13802EU FUEL TRANSFER VAFAULTY W K NONE J WARNING INDICATION NRNOT REPORTED 1 AUS (AUS) FUEL CROSSFEED VALVE CONNECTOR PLUG AND WIRING FAULTY. 2L72 4F4 FRTA16WE E21EU 20020304001322002030400132CE 2002 3 4 AUS20020051 120020122G2430S19432 CABLE CESSNA210 210N 2073453CE CONT O520 IO520L 17032SO MCAULYD3A34 D3A34C404 GL DC GENERATING SYWORN W K NONE HJ ELECT. POWER LOSS-50 PC WARNING INDICATION CRCRUISE 1 AUS (AUS) ALTERNATOR OUTPUT CABLE ARCING ON ALTERNATOR GROUND CABLE. CABLEHAD BEEN REMANUFACTURED FROM MIL-W-22759/16-4 MATERIAL. 1H71 3O3 O 3A21 E5CE 5 CP47GL 20020304001332002030400133EU 2002 3 4 AUS20020060 120020125G6320350A32106321 GASKET AEROSPAS355 AS355F1 8680810EU ALLSN 250C 250C20F 03013GL MAIN ROTOR GEARBFAULTY W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) MAIN ROTOR TRANSMISSION EPICYCLIC RING GEAR GASKET FAULTY. GASKET WAS EXTRUDING FROM BETWEEN THE UPPER AND LOWER CASES AND BREAKING INTO PIECES AND CAUSING AN OIL LEAK WHICH WAS PROGRESSIVELY WORSENING. ON DISASSEMBLY THE MATING CASE FLANGES SHOWEDSIGNS OF FRETTING. 1G72 3U3 U H11EU E4CE 20020304001342002030400134CE 2002 3 4 AUS20020061 120020121G323399101363 ACTUATOR CESSNA404 404CESSNA 2075901CE CONT O520 GTSIO520M 17032SO MCAULY3FF32 3FF32C501 GL LANDING GEAR ACTFAULTY W K NONE O OTHER LDLANDING 1 AUS (AUS) RH MAIN LANDING GEAR RETRACTION RAM INTERNAL FAULT CAUSING RAM TO BE UNLOCKED. RH MLG COLLAPSED ON LANDING. 1L72 3O3 O A25CE E7CE 5 CP45GL 20020304001352002030400135NM 2002 3 4 AUS20020065 120020117G5270A42006992302 SOLENOID BOEING737 7374Q8 138447QNM CFMINTCFM56 CFM563C 13802EU DOOR WARNING SYSFAULTY W K NONE N FALSE WARNING TOTAKEOFF 1 AUS (AUS) RH OVERWING EXIT FLIGHT LOCK RELAY AND SOLENOID FAULTY. 2L72 4F4 FRTA16WE E21EU 20020304001362002030400136 2002 3 4 AUS20020075 420020115G2564733M2537011 LIFE RAFT BOEING737 737476 NM CFMINTCFM56 CFM563C 13802EU LIFERAFT FAULTY W K NONE O OTHER ININSP/MAINT 1 AUS 11208487 (AUS) LIFERAFT FAULTY. LH BOTTLE PRESSURE READING ZERO. 2L72 4F4 FRTA16WE E21EU 20020304001372002030400137NM 2002 3 4 AUS20020079 120020204G215065771 COOLING FAN BOEING737 737476 NM CFMINTCFM56 CFM563C 13802EU CABIN COOLING SYFAILED W K NONE B SMOKE/FUMES/ODORS/SPARKS LDLANDING 1 AUS 10430 (AUS) NORMAL EXHAUST FAN FAILED. 2L72 4F4 FRTA16WE E21EU 20020304001382002030400138CE 2002 3 4 AUS20020084 120020125G2460S123230 CIRCUIT BREAKER CESSNA210 210N 2073453CE CONT O520 IO520L 17032SO MCAULYD3A34 D3A34C404 GL DC POWER DISTRIBFAILED W K NONE H ELECT. POWER LOSS-50 PC DEDESCENT 1 AUS (AUS) CIRCUIT BREAKER FAILED. 1H71 3O3 O 3A21 E5CE 5 CP47GL 20020304001392002030400139SO 2002 3 4 AUS20020086 220020130G741436066AA GEAR BENDIX 105005147 EAGLE XTS EAGLEXTS150 05607BZGL CONT O240 IO240A SO MCAULY1A135 1A135BRM GL MAGNETO/DISTRIBUWORN W K NONE O OTHER ININSP/MAINT 1 AUS 498 LHE3194060RH (AUS) LH AND RH MAGNETO GEARS WORN. 1H71 3I3 ONCA00005LAE7SO 5 NP842 20020304001402002030400140CE 2002 3 4 AUS20020090 120020206G28200800400261 PIPE CESSNA310 310R 2074245CE CONT O520 IO520M 17032SO MCAULY3AF32C3AF32C87 GL AIRCRAFT FUEL DICORRODED W K NONE OK OTHER FLUID LOSS ININSP/MAINT 1 AUS (AUS) RH INBOARD FUEL TRANSFER PIPE CORRODED AND LEAKING. 1L72 3O3 O 3A10 E5CE 5 CP22EA 20020304001412002030400141EU 2002 3 4 AUS20020096 120020209G3230HP848430621 VALVE SAAB SF340 SF340A 7850100EU GE CT7TP CT75A 30030NE ROTOL R354 R3544123F13 NE LANDING GEAR RETFAULTY W K NONE O OTHER LDLANDING 1 AUS 18217 (AUS) LANDING GEAR CONTROL VALVE FAULTY. INVESTIGATION FOUND THAT THE DOWN SOLENOID HAD A RESISTANCE PROBLEM. 2L72 4T4 TRTA52EU E8NE 6 CP61GL 20020304001422002030400142EU 2002 3 4 AUS20020100 220020131G73218063215 MEC GE CFM563C1 BOEING737 7374Q8 138447QNM CFMINTCFM56 CFM563C 13802EU FUEL CONTROL/TURFAULTY W K NONE E VIBRATION/BUFFET NRNOT REPORTED 1 AUS 857543 (AUS) NO2 ENGINE MAIN ENGINE CONTROL (MEC) FAULTY. 2L72 4F4 FRTA16WE E21EU 20020304001432002030400143NM 2002 3 4 AUS20020104 120020212G3230A42000028305 SOLENOID BOEING737 7374Q8 138447QNM CFMINTCFM56 CFM563C 13802EU LANDING GEAR RETFAULTY W K NONE O OTHER TOTAKEOFF 1 AUS (AUS) LANDING GEAR LOCK SOLENOID FAULTY. AIR/GROUND SWITCH S106 OUT OFADJUSTMENT. 2L72 4F4 FRTA16WE E21EU 20020304001442002030400144NM 2002 3 4 AUS20020110 120020105G5101 STRUCTURE BOEING727 727277 138408SNM PWA JT8 JT8D15 52051NE AIRCRAFT STRUCTUCORRODED W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) EXFOLIATION CORROSION FOUND AT NO3 CARGO DOOR UPPER FORWARD SIDEAT STN 1090, STRINGER 20R. FOUND DURING CPCP INSPECTION. 2L73 4F4 FRTA3WE E2EA 20020304001452002030400145NM 2002 3 4 AUS20020117 120020218G792128E997 OIL COOLER PWA PW120A DHAV DHC8 DHC8102 2809003NM PWA 120 PW120A NE HAMSTD14SF 14SF7 NE ENGINE OIL COOLELEAKING W K NONE EK VIBRATION/BUFFET FLUID LOSS CRCRUISE 1 AUS 428 REF75980 (AUS) NO2 ENGINE OIL COOLER LEAKING. LOSS OF ENGINE OIL. 2H72 4T4 TRTA13NM E20NE 6 CP7NE 20020304001462002030400146NM 2002 3 4 AUS20020122 120020218G7712311694201 SENSOR PWA PW120A DHAV DHC8 DHC8102 2809003NM PWA 120 PW120A NE HAMSTD14SF 14SF7 NE ENGINE BMEP/TORQFAULTY W KE NONE ENGINE SHUTDOWN E VIBRATION/BUFFET TOTAKEOFF 1 AUS 6362 120683 (AUS) ENGINE TORQUE SENSOR FAULTY. 2H72 4T4 TRTA13NM E20NE 6 CP7NE 20020304001472002030400147CE 2002 3 4 AUS20020125 120020126G7810 EXHAUST PIPE CONT GTSIO520H CESSNA421 421B 2076014CE CONT O520 GTSIO520H 17032SO MCAULY3AF34C3AF34C92 GL ENGINE COLLECTORLEAKING W K NONE EB VIBRATION/BUFFET SMOKE/FUMES/ODORS/SPARKS LDLANDING 1 AUS (AUS) RH ENGINE FIRE. ENGINE COMPARTMENT DAMAGED. FIRE WAS EXTINGUISHED USING CABIN FIRE EXTINGUISHER. INVESTIGATION FOUND THE FIRE WAS CAUSED BY MISALIGNMENT OF THE EXHAUST SWIVEL JOINT WHICH ALLOWEDEXHAUST GAS TO LEAK INTO THE ENGINE BAY. A LIST OF DAMAGE IS AS FOLLOWS:- 1.OUTBOARD ENGINE MOUNT BEAM HEAT DAMAGED 2.STARTER HEAT DAMAGED3.OUTBOARD REAR ENGINE MOUNT HEAT AFFECTED4.INTERCOOLER INDUCTION TUBE HEAT DAMAGED 5.VARIOUS FUEL, OIL AND DRAIN HOSES HEAT DAMAGED6.TURBOCHARGER SEIZED 7.TACHO GENERATOR HEAT AFFECTED 8.INTERCOOLER HEAT AFFECTED 9.VACUUM PUMP HEAT AFFECTED 10. OIL PUMP HEAT AFFECTED 1L72 3O3 O A7CE E7CE 5 CP22EA 20020304001482002030400148SO 2002 3 4 AUS20020127 120020215G3232455946 ACTUATOR PIPER PA31 PA31 7103102SO LYC O540 TIO540A2C 41532EA HARTZLHCE3Y HCE3YR2 GL LANDING GEAR DOOFAULTY W K NONE OJ OTHER WARNING INDICATION CLCLIMB 1 AUS 3552 (AUS) RH MAIN LANDING GEAR INBOARD DOOR ACTUATOR FAULTY. SUSPECTINTERNAL LOCK FAILURE. 1L72 3O3 O A20SO E14EA 5 CP33EA 20020304001492002030400149SO 2002 3 4 AUS20020128 120020215G3710215CC PUMP AIRBORNE 215CC PIPER PA31 PA31 7103102SO LYC O540 TIO540A2C 41532EA HARTZLHCE3Y HCE3YR2 GL VACUUM DISTRIBUTINOPERATIVE W K NONE OJ OTHER WARNING INDICATION CRCRUISE 1 AUS 3AU1603 (AUS) LH VACUUM PUMP DRIVE SHEARED. 1L72 3O3 O A20SO E14EA 5 CP33EA 20020304001502002030400150NM 2002 3 4 AUS20020130 120020206G291366087 PUMP BOEING737 7374Q8 138447QNM CFMINTCFM56 CFM563C 13802EU HYDRAULIC PUMP, SEIZED W K NONE KJ FLUID LOSS WARNING INDICATION CLCLIMB 1 AUS K0169 (AUS) NO1 ENGINE DRIVEN HYDRAULIC PUMP SEIZED AND LEAKING. RH MAINLANDING GEAR RETRACTION ACTUATOR HOSES ALSO LEAKING. 2L72 4F4 FRTA16WE E21EU 20020304001512002030400151NE 2002 3 4 AUS20020133 320020219G611454547AB SPIDER HAMSTD 22D40505 AIRTRCAT300 AT301 0390103SW PWA R1340 R1340AN1 52016NE HAMSTD22D 22D40 NE PROPELLER HUB SECRACKED W K NONE O OTHER ININSP/MAINT 1 AUS 570 82087 (AUS) PROPELLER SPIDER CRACKED. CRACK LENGTH 50.8MM (2IN). 1L71 3R3 R A9SW 5E2 5 CP736 20020304001522002030400152CE 2002 3 4 AUS20020136 120020221G3710215CC PUMP CONT GTSIO520M CESSNA404 404CESSNA 2075901CE CONT O520 GTSIO520M 17032SO MCAULY3FF32 3FF32C501 GL VACUUM DISTRIBUTUNSERVICEABLE W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) VACUUM PUMP FAILED. 1L72 3O3 O A25CE E7CE 5 CP45GL 20020304001532002030400153CE 2002 3 4 AUS20020137 120020221G3710215CC PUMP CONT GTSIO520M CESSNA404 404CESSNA 2075901CE CONT O520 GTSIO520M 17032SO MCAULY3FF32 3FF32C501 GL VACUUM DISTRIBUTFAILED W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) VACUUM PUMP FAILED. 1L72 3O3 O A25CE E7CE 5 CP45GL 20020304001542002030400154SO 2002 3 4 AUS20020141 120020225G54118617903 WEB PIPER PA44 PA44180 7104402SO LYC O360 O360E1A6 41514EA HARTZLHCC3Y HCC3YR2 NE NACELLE/PYLON, FCRACKED W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) RH ENGINE NACELLE TOP OUTBOARD WEB CRACKED IN AREA OF TOP REARENGINE MOUNT ATTACHMENT POINT. 1L72 3O3 O A19S0 E286 5 CP25EA 20020304001552002030400155CE 2002 3 4 AUS20020144 120020212G561010138402515 WINDSHIELD BEECH 200 200BEECH 1152920CE PWA PT6 PT6A41 52043EA HARTZLHCB3T HCB3TN3 GL FLIGHT COMPARTMECRACKED W K NONE O OTHER CRCRUISE 1 AUS 94055H2855 (AUS) WINDSHIELD CRACKED WHEN HEAT TURNED ON. 1L72 4T4 T A24CE E4EA 6 CP15EA 20020304001562002030400156EA 2002 3 4 AUS20020145 220020225G8520LW18840 CAMSHAFT LYC O360A4M PIPER PA28 PA28181 7102807SO LYC O360 O360A4M 41514EA AMTR C8289 C8289 GL RECIPROCATING ENFAILED W K NONE E VIBRATION/BUFFET CRCRUISE 1 AUS (AUS) CAMSHAFT LOBE FAILED. METAL CONTAMINATION OF OIL SYSTEM. OILPRESSURE RELIEF VALVE OFF SEAT. LOW OIL PRESSURE LED TO BEARING FAILURE AND SUBSEQUENT ENGINE SEIZURE. 1L71 3O3 O 2A13 E286 5 NEXPP5N 20020304001572002030400157NM 2002 3 4 AUS20020146 120020223G2913165W01020 PUMP BOEING737 737376 NM CFMINTCFM56 CFM563C 13802EU HYDRAULIC PUMP, FAILED W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) STANDBY HYDRAULIC PUMP FAILED. 2L72 4F4 FRTA16WE E21EU 20020306000072002030600007SO 2002 3 6 AUS20020037 220020117G8500810533R BEARING CESSNA404 404CESSNA 2075901CE CONT O520 GTSIO520M 17032SO MCAULY3FF32 3FF32C501 GL ENGINE MAKING METAL W K NONE O OTHER ININSP/MAINT 1 AUS 449 (AUS) ENGINE MAKING METAL. SUSPECT DEFECTIVE BEARINGS. 1L72 3O3 O A25CE E7CE 5 CP45GL 20020306000312002030600031SO 2002 3 6 AUS20020047 120020122G3260 BRACKET PIPER PA31 PA31350 7103110SO LYC O540 TIO540J2BD 41532EA HARTZLHCE3Y HCE3YR2 GL MLG OUT OF ADJUST W O OTHER N FALSE WARNING DEDESCENT 1 AUS (AUS) RT MAIN LANDING GEAR MICROSWITCH MOUNT BRACKET MOVED. MICROSWITCH OUT OF ADJUSTMENT. BRACKET HAD BEEN REMOVED DURING DRAG BRACE REPLACEMENT. 1L72 3O3 O A20SO E14EA 5 CP33EA 20020306000332002030600033WP 2002 3 6 AUS20020052 220020116G73218977801A FUEL CONTROL SWRNGNSA227 SA227* SW GARRTTTPE331TPE33112UHR WP MCAULY4HFR344HFR34C652 NE ENGINE FAULTY W A UNSCHED LANDING E VIBRATION/BUFFET CLCLIMB 1 AUS 3673 (AUS) FUEL CONTROL UNIT FAULTY. 2L72 4T4 TRTA5SW E4WE 6 C3PNE 20020306000362002030600036NE 2002 3 6 AUS20020054 220020126G720012680 ENGINE BOEING747 747338 NM RROYCERB211 RB211524G19 NE NR 2 VIBRATES W EA ENGINE SHUTDOWN UNSCHED LANDING EF VIBRATION/BUFFET FLT CONT AFFECTED CRCRUISE 1 AUS 7039 (AUS) NR 2 ENGINE VIBRATION EXCESSIVE. 2L72 4F4 FRTA20WE E30NE 20020306000452002030600045NM 2002 3 6 AUS20020059 120020119G24349110813 BEARING ROBSINR22 R22BETA 7640110NM LYC O320 O320B2C 41508EA DC ALTERNATOR LACK OF LUBE W A UNSCHED LANDING HJ ELECT. POWER LOSS-50 PC WARNING INDICATION CRCRUISE 1 AUS 340 (AUS) ALTERNATOR BEARING SEIZED. SUSPECT CAUSED BY LACK OF LUBRICATION. 1G71 3O3 O H10WE E274 20020306000472002030600047CE 2002 3 6 AUS20020062 120020109G5511123262224 SPAR CESSNA210 210N 2073453CE CONT O520 IO520L 17032SO MCAULYD3A34 D3A34C404 GL HORIZONTAL STAB CRACKED W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) HORIZONTAL STABILISER MAIN SPAR CRACKED. CRACKS WENT THROUGH SPAR, SPLICE AND CHANNEL. CRACKS RADIATED FROM THE TOP AND BOTTOM OF THE CENTRAL LIGHTENING HOLE. REAR ATTACHMENT FITTING ALSO CRACKED AT THE TAILPLANE TO FUSELAGE ATTACHMENT POINT. 1H71 3O3 O 3A21 E5CE 5 CP47GL 20020306000692002030600069NM 2002 3 6 AUS20020064 120020129G2781189929 SENSOR BOEING737 737400 138449ANM CFMINTCFM56 CFM563C 13802EU SLATS FAULTY W D RETURN TO BLOCK N FALSE WARNING TXTAXI/GRND HDL 1 AUS (AUS) NR 2 LEADING EDGE FLAP EXTEND SENSOR FAULTY. 2L72 4F4 FRTA16WE E21EU 20020306000712002030600071NM 2002 3 6 AUS20020066 120020128G4920737M49503011 APU BOEING737 737376 NM CFMINTCFM56 CFM563C 13802EU APU BAY LEAKING W K NONE K FLUID LOSS ININSP/MAINT 1 AUS (AUS) APU LEAKING FUEL FROM DRAIN MAST. 2L72 4F4 FRTA16WE E21EU 20020307000022002030700002CE 2002 3 7 AUS20020076 120020116G2842 SENSOR BEECH 76 76 1153005CE LYC O360 IO360A1G6 41514EA FUEL QUANTITY STUCK W O OTHER ERNVIBRATION/BUFFET PARTIAL RPM/PWR LOSS FALSE WARNING CLCLIMB 1 AUS (AUS) RT FUEL SENSOR JAMMED IN HALF FULL POSITION. ERRONEOUS FUEL INDICATIONS ALLOWED RT FUEL TANK TO BE LOW ON FUEL RESULTING IN RT ENGINE POWER LOSS. 1L72 3O3 O A29CE 1E10 20020307000062002030700006NE 2002 3 7 AUS20020081 220020125G8500R183092 ENGINE DOUG DC3 DC3CS1C3G 3021458WP PWA R1830 R183092 52020NE HAMSTD23E 23E50 NE LEFT MAKING METAL W O OTHER EK VIBRATION/BUFFET FLUID LOSS DEDESCENT 1 AUS 974 (AUS) LT ENGINE OIL FILTER CONTAMINATED WITH METAL. 2L72 4R4 R A669 5E4 6 CP603 20020307000072002030700007GL 2002 3 7 AUS20020083 320020201G6111BU9606 BLADE BEECH 200 B200C 1152924CE PWA PT6 PT6A41 52043EA HARTZLHCB3T HCB3TN3 GL PROPELLER CRACKED W K NONE O OTHER ININSP/MAINT 1 AUS 2932 (AUS) LT PROPELLER NR 2 BLADE CRACKED. CRACK LENGTH APPROXIMATELY 40MM (1.57IN) RUNNING CHORDWISE ACROSS THE BLADE FROM THE TRAILING EDGE. CRACK IS LOCATED APPROXIMATELY 150MM (5.9IN) FROM THE BLADE TIP. 1L72 4T4 T A24CE E4EA 6 CP15EA 20020307000082002030700008CE 2002 3 7 AUS20020085 120020204G5751512400021 BALANCE WEIGHT CESSNA402 402C 207590RCE CONT O520 TSIO520E 17040SO MCAULY3AF32C3AF32C93 GL AILERONS BROKEN W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) RH AILERON INTERNAL BALANCE WEIGHT LOOSE. INVESTIGATION FOUND THE MIDDLE SECTION OF THE BALANCE WEIGHT WAS BROKEN OFF. 1L72 3O3 O A7CE E8CE 5 CP22EA 20020307000092002030700009GL 2002 3 7 AUS20020087 320020121G611190A8 BLADE CESSNA182 182B 2072706CE CONT O470 O470* 17026SO MCAULY2A34C 2A34C50 GL PROPELLER MISREPAIRED W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) INSPECTION OF PROPELLER WHEN RECEIVED FOR REPAIR FOUND THAT THE BLADE THREADS HAD BEEN TRUNCATED TO COMPLY WITH AD/PMC/24/3 BUT HAD NOT BEEN SHOT PEENED. THE RETENTION NUTS DID NOT HAVE THE O-RING GROOVE WIDENED AS LISTED IN SL 1990-2. AD/PMC/41HAD NOT BEEN INCORPORATED AT THE LAST OVERHAUL. THE SERIAL NUMBER OF ONEBLADE WAS INCORRECT IN THE LOGBOOK. PERSONNEL/MAINTENANCE ERROR. 1H71 3O3 ONT3A13 E273 5 CP3EA 20020307000102002030700010EA 2002 3 7 AUS20020088 220020125G7414AO9815 SCREW GIPPLDGA200 GA200 EU LYC O540 IO540K1A5 41532EA HARTZLHCC2Y HCC2YR1 GL MAGNETO LOOSE W O OTHER ER VIBRATION/BUFFET PARTIAL RPM/PWR LOSS CLCLIMB 1 AUS (AUS) LT MAGNETO SEPARATED FROM ENGINE. INVESTIGATION FOUND THAT THE MAGNETO BASE FLANGE RETAINING SCREWS (3OFF) FELL OUT AND WERE FOUND INSIDE THE ENGINE. SUSPECT CAUSED BY LACK OF TORQUE ON THESCREWS. PERSONNEL/MAINTENANCE ERROR. 1L71 3O3 ONCA00001LA1E4 5 CP920 20020307000592002030700059CE 2002 3 7 AUS20020091 120020203G5313 STRINGER BEECH 200 B200C 1152924CE PWA PT6 PT6A42 52043NE FUSELAGE CRACKED W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) STRINGER NR 9 LT LOCATED BEHIND FRONT PRESSURE BULKHEAD CRACKED AT THE END OF THE ATTACHMENT GUSSETT. 1L72 4T4 T A24CE E4EA 20020307000642002030700064CE 2002 3 7 AUS20020095 120020208G6120 CABLE BEECH 58 58 1152740CE CONT O520 IO520C 17032SO MCAULY3AF34C3AF34C502 GL PROP CONTROL WRONG PART W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) LT PROPELLER CONTROL CABLE DIAMETER WAS FOUND TO BE LESS THAN THE DIAMETER OF THE RH SIDE CABLE. LT CABLE WAS4.762MM (0.1875IN) INDIAMETER AND THE RT CABLE WAS 6.350MM (0.25IN). UNAPPROVED PART. 1L72 3O3 O 3A16 E5CE 5 CP22EA 20020307000682002030700068NE 2002 3 7 AUS20020098 220020122G7420311983301 IGNITION LEAD BEECH 200 B200C 1152924CE PWA PT6 PT6A42 52043NE IGNITION SYSTEM MISMANUFACTURED W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) ENGINE IGNITER LEADS CAUSING IGNITER PIN EROSION. LEADS ARE A NEW ITEM WITH SHORTER INSULATORS. 1L72 4T4 T A24CE E4EA 20020307000922002030700092EU 2002 3 7 AUS20020106 120020214G2520MS220441P00501 HOOK AEROSPAS355 AS355F1 8680810EU ALLSN 250C 250C20F 03013GL CABIN FAULTY W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) SAFETY HARNESS USED BY CAMERAMAN FAULTY. SNAP HOOK ON HARNESS MAY UNDER SOME CIRCUMSTANCES HAVE THE SPRING LOADED SAFETY CATCH FORCED OPEN ALLOWING THE SNAP HOOK TO SEPARATE FROM THE AIRCRAFT ATTACHMENT POINT. 1G72 3U3 U H11EU E4CE 20020307000962002030700096CE 2002 3 7 AUS20020111 120020207G716012507043 FILTER CESSNA206 U206F 2073333CE CONT O520 IO520F 17032SO MCAULYD3A34 D3A34C404 GL AIR INTAKE BURNED W O OTHER EB VIBRATION/BUFFET SMOKE/FUMES/ODORS/SPARKS NRNOT REPORTED 1 AUS (AUS) ENGINE AIR FILTER BURNT. 1H71 3O3 O A4CE E5CE 5 CP47GL 20020307001022002030700102CE 2002 3 7 AUS20020120 120020211G2823HE7805 SELECTOR SWITCH BEECH 58 58 1152740CE CONT O520 IO520C 17032SO AMTR C8289 C8289 GL FUEL SYSTEM CORRODED W K NONE O OTHER ININSP/MAINT 1 AUS 197 (AUS) LT FUEL SELECTOR VALVE EXCESSIVELY CORRODED DUE TO CONTAMINATION. 1L72 3O3 O 3A16 E5CE 5 NEXPP5N 20020307001032002030700103CE 2002 3 7 AUS20020121 120020211G2823HE7803 SELECTOR SWITCH BEECH 58 58 1152740CE CONT O520 IO520C 17032SO AMTR C8289 C8289 GL FUEL SYSTEM CORRODED W K NONE O OTHER ININSP/MAINT 1 AUS 197 (AUS) RT FUEL SELECTOR VALVE EXCESSIVELY CORRODED DUE TO CONTAMINATION. 1L72 3O3 O 3A16 E5CE 5 NEXPP5N 20020307001042002030700104EU 2002 3 7 AUS20020123 120020211G2434ALV2045BS BRUSH BLOCK BNORM BN2 BN2A26 1520226EU LYC O540 O540E4C5 41532EA HARTZLHCC2Y HCC2YK2 GL DC ALTERNATOR SHORTED W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) ALTERNATOR BRUSHES SHORTING BETWEEN THE SLIP RINGS AND ALTERNATOR SLIP RING END BEARING. 1H72 3O3 O A17EU E295 5 CP920 20020307001052002030700105SO 2002 3 7 AUS20020124 120020220G2140461731 REGULATOR VALVE PIPER PA31 PA31350 7103110SO LYC O540 TIO540J2BD 41532EA HARTZLHCE3Y HCE3YR2 GL HEATING SYSTEM FAULTY W K NONE K FLUID LOSS ININSP/MAINT 1 AUS (AUS) RT HEATER FUEL PRESSURE REGULATOR FAULTY. REGULATOR LEAKING FUELFROM DRAIN. 1L72 3O3 O A20SO E14EA 5 CP33EA 20020307001102002030700110CE 2002 3 7 AUS20020132 120020122G3230504501025 TORQUE TUBE CESSNA310 310R 2074245CE CONT O520 IO520M 17032SO MLG DAMAGED W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) LANDING GEAR TORQUE TUBE DAMAGED. SUSPECT DAMAGE ORIGINATED FROM CRACKING AROUND THE FORK BOLT AREA. 1L72 3O3 O 3A10 E5CE 20020307001152002030700115CE 2002 3 7 AUS20020139 120020225G3230MS935302 CLAMP CESSNA402 402C 207590RCE CONT O520 TSIO520VB 17040SO MCAULY3AF32C3AF32C505 GL MLG BLOWDOWN UNAPPROVED PART W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) LANDING GEAR EMERGENCY BLOWDOWN SYSTEM CONTROL CABLE CLAMP INCORRECT ITEM. THE INCORRECT ITEM WAS A RUBBER CUSHIONED CLAMP WHICH ALLOWED THE CONTROL CABLE TO SLIP AND JAM THE FIRINGSYSTEM. WHEN THE CORRECT CLAMP WAS FITTED THE SYSTEM OPERATED NORMALLY. UNAPPROVED PART. 1L72 3O3 O A7CE E8CE 5 CP22EA 20020307001242002030700124EA 2002 3 7 AUS20020142 220020223G8530SL19034 EXHAUST VALVE CESSNA150 152 2071835CE LYC O235 O235L2C 41505EA MCAULY1A103 1A103TCM GL ENGINE BURNED W A UNSCHED LANDING ER VIBRATION/BUFFET PARTIAL RPM/PWR LOSS CRCRUISE 1 AUS (AUS) EXHAUST VALVE BURNED. VALVE NOT SEATING CORRECTLY. 1H71 3O3 ONT3A19 E223 5 NP50GL 20020308000522002030800052EA 2002 3 8 CA020207002 220020203G72503027301 BLADE BEECH 200 B200 1152922CE PWA PT6 PT6A41 52043EA TURBINE SECTION CRACKED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) TWO (2) CT BLADES CRACKED. 1L72 4T4 T A24CE E4EA 20020308000532002030800053CE 2002 3 8 CA020208001 120020125G561010138402522 WINDSHIELD BEECH 200 200BEECH 1152920CE PWA PT6 PT6A41 52043EA COCKPIT FAILED W BGA EMER. DESCENT O2 MASK DEPLOYED UNSCHED LANDING O OTHER CRCRUISE 1 CA 97300H8611 (CAN) APPROX 15 MINS AFTER LEVELLING OFF AT CRUISE ALTITUDE OF 29,000 FEET, SMALL CRACK FORMED ON RIGHT WINDSHIELD. FEW SECONDS LATER, ENTIRE INNER PLY SHATTERED & CABIN PRESSURIZATION LOST AT RATE OF APPROX 2500 FT/MIN . EMERGENCY OXYGEN DEPLOYED & MASKS DONNED, & EMERGENCY DESCENT TO SAFE ALTITUDE OF 11,000 FEET CARRIED OUT BY CREW. A/C CARRIED ON TO MEDICINE HAT (CYXH), WHERE UNEVENTFUL APPROACH & LANDING WERE CARRIED OUT. INSPECTION OF WINDSHIELD UPON ARRIVAL CONFIRMED THAT ENTIRE INNER PLY HAD SHATTERED. HAD BEEN NO PREVIOUS REPORTS OF DAMAGE ON WINDOW,&WINDHSIELD HEAT OP NORMAL.INSPOF FUSELAGE WINDSHIELD ATTACH STRUCTURE REVEALED NO ABNORMALITIES. REPLACED WINDSHIELD. 1L72 4T4 T A24CE E4EA 20020308000552002030800055CE 2002 3 8 CA020208004 120020127G2731043200122 SKIN CESSNA150 152 2071835CE LYC O235 O235L2C 41505EA MCAULY1A103 1A103TCM GL ELEVATOR CRACKED W K NONE O OTHER ININSP/MAINT 1 CA 11841 (CAN) - CRACK FOUND ON PRE-FLIGHT. - CRACK LOCATED AT OUTBOARD AFT CORNER OF ELEVATOR UNDER TRIM TAB HINGE. 1H71 3O3 ONT3A19 E223 5 NP50GL 20020308000682002030800068EU 2002 3 8 CA020211015 120020206G6220350A31190703 STARFLEX 355A3100200 SNIAS 350 AS350B3 8680954EU TMECA ARRIELARRIEL2B NE MAIN ROTOR HUB DEBONDED W K NONE O OTHER ININSP/MAINT 1 CA M1801 (CAN) AIRCRAFT TOTAL TIME 463 HOURS CONDUCTED A 500/A CALENDAR INSPECTION. BUSHING FOUND LOOSE ON STARFLEX ARM DURING INSPECTION AS PER WORK CARD 62.20.605 PARA. 5.3. 1G71 3U3 U H9EU E00054EN 20020308000692002030800069EU 2002 3 8 CA020211017 220020209G7421897255 SPARK PLUG DIAMONDA20 DA20A1 2990000GL ROTAX 912 ROTAX912 55555EU CYLINDER HEAD BROKEN W K NONE O OTHER ININSP/MAINT 1 CA (CAN) ENGINE ROUGHNESS WAS NOTED ON STARTUP AT ALL POWER SETTINGS BELOW 1600 RPM. NR 3 CYLINDER SPARK PLUG WAS FOUND TO HAVE ELECTRODE BROKEN OFF AT 90 DEGREE BEND. 1L71 3O3 INTTA4CH EXPE3I 20020308000702002030800070GL 2002 3 8 CA020213008 220020208G7314P94C16602 PUMP AEROSPAS355 AS355F1 8680810EU ALLSN 250C 250C20F 03013GL FUEL BOOST MAKING METAL W K NONE O OTHER ININSP/MAINT 1 CA (CAN) NR 1 ENGINE FUEL BOOST PUMP WAS MAKING TOO MUCH NOISE AND VIBRATING AS COMPARED TO NR 2 FUEL BOOST PUMP. INSPECTED THE NR 1 ENGINE DRIVEN FUEL PUMP FILTER AND FOUND NON-FERROUS METAL IN THE FILTER. INSPECTED THE FUEL CONTROL FILTER FOR CONTAMINATION AND FOUND NON-FERROUS METAL. THE NR 1 FUEL BOOST PUMP PRESSURE WAS LOWER THAN THE NR 2 FUEL BOOST PUMP PRESSURE. REPLACED FUEL CONTROL, ENGINE DRIVEN FUEL PUMP AND NR 1 FUEL BOOST PUMP. 1G72 3U3 U H11EU E4CE 20020308000712002030800071NE 2002 3 8 CA020213010 220020204G731070077200G600 B-NUT BELL 427 427 1182207SW PWC PW207 PW207D NE FUEL LINE LEAKING W K NONE K FLUID LOSS ININSP/MAINT 1 CA (CAN) SMALL AMOUNT OF FUEL OBSERVED LEAKING FROM RT FLOOR CAVITY DRAIN. CAVITY WAS OPENED, FUEL TRANSFER LINE INSPECTED. LEAK ORIGINATED FROM AFT 'B' NUT FITTING. TORQUE WAS CHECKED ON 'B' NUT, WITHIN SPECS. AIRCRAFT DRAINED OF FUEL, LINE REMOVED AND INSPECTED. OUTCOME, STAINLESS BRAIDED FUEL LINE MANUFACTURED TOO SHORT. ORDERED NEW LINE FROM B.H.T. THIS LINE ALSO TOO SHORT. ORDERED NEW LINE, 2ND LINE LENGTH OK. NEW LINE INSTALLED. AIRCRAFT FUELED AND LEAK CHECK C/O. FUEL LEAK SOLVED. 1G71 3U3 U R00001RCE42NE 20020308000722002030800072CE 2002 3 8 CA020213011 120020201G322105411212 SUPPORT CESSNA182 182 2072702CE CONT O470 O470L 17026SO MCAULY2A36C 2A36C29 GL MLG CRACKED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) RT OUTBOARD LANDING GEAR SUPPORT CASTING FOUND TO BE CRACKED IN TWO PLACES. FAULT WAS DISCOVERED WHEN GEAR LEG WAS REMOVED FOR NDT OF LANDING GEAR COMPONENTS. NO OTHER FAULTS FOUND. LANDING GEAR NDT INSPECTION WAS CARRIED OUT AT OWNER'S REQUEST. 1H71 3O3 ONT3A13 E273 5 CP880 20020308000732002030800073SW 2002 3 8 CA020213012 120020125G7920427065244101 LINE BELL 427 427 1182207SW PWC PW207 PW207D NE ENGINE OIL CHAFED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) DURING MODIFICATION OF AIRCRAFT, NR 2 ENGINE OIL LINES WERE REMOVED. UPON REMOVAL OF LINES IT WAS OBSERVED THAT THE MAIN OIL FEED LINE (FROM OIL COOLER) WAS CHAFED TO A DEPTH OF 0.004 INCH. THE CHAFING OCCURRED IN THE AREA BELOW THE FORWARD ENGINE FIREWALL. THE FIREWALL HAS A STAINLESS STEEL 'TUNNEL' WHICH THE OIL LINES PASS THROUGH. THE FORWARD OUTBOARD EDGE OF THIS TUNNEL CHAFED INTO THE ALUMINUM OIL TUBE. THIS TUBE WAS REMOVED FROM SERVICE. 1G71 3U3 U R00001RCE42NE 20020308000742002030800074SW 2002 3 8 CA020213014 120020202G63202120400545 CASE BELL 205 205A1 1181414SW LYC T53 T5313B 41549NE TRANSMISSION CRACKED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) THE LIFT LINK BEARING BOSS WAS FOUND CRACKED DURING ROUTINE MAINTENANCE. 1G71 4U4 U H1SW E17EA 20020308000752002030800075EU 2002 3 8 CA020214002 120020205G24359740926112 RELAY PILATSPC12 PC1245 7090551EU PWA PT6 PT6A67B 52043NE HARTZLHCE4A HCE4A3D GL STARTER GEN FAILED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) WHILE IN CRUISE FLT "ESSENTIAL BUS" WARNING LIGHT ILLUMINATED ON CAWS PANEL. NR 2 BATTERY OBSERVED TO BE DISCHARGING AT APPROX 35 AMPS & SELECTED TO OFF POSITION. DISCHARGE RATE FROM BATTERY STOPPED & "ESSENTIAL BUS" LIGHT WENT OUT. WITHIN 3 MINS AOA CAUTION LIGHT CAME ON & LT WINDSCREEN FROSTING OVER. EMERGENCY LANDING REQUIRED & CARRIED OUT WITHOUT INCIDENT. MAINT PERFORMED GROUND RUN & FOUND FOLLOWING: NR 2 GENERATOR INDICATING 28.5 VOLTS BUT NO AMPRE OUTPUT. WHEN PROBE HEAT & LT WINDSCREEN HEATING WERE SELECTED ON. NR 2 BATTERY WOULD SHOW DISCHARGE OF 35 AMPS. THE NR 2 GEN RELAY REMOVED & BENCH TESTED. MAINT FOUND THAT TOP SET OF CONTACTS IN RELAY WERE NOT CLOSING. 1L71 3T4 TRTA78EU E26NE 5 CP210NE 20020308000772002030800077NM 2002 3 8 CA020215007 120020128G5754 ARM BOEING737 737217 1384464NM PWA JT8 JT8D17 52049NE LE SLAT DISLODGED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) MAINTENANCE FOUND NR 2 SLAT FOUND PROTRUDING 4 INCHES ON ONE SIDE ON WALKAROUND CHECK. SLAT MECHANISM FOUND OFF GUIDE TRACK. FLIGHT PERMIT (SPECIFIC PURPOSE, FERRY FLIGHT) ISSUED AND AIRCRAFT FLOWN TO BASE FOR REPAIRS. NR 2 LEADING EDGE SLAT DETENT ARM REPLACED AS PER MAINTENANCE MANUAL 51-81-00. SLAT OPERATED THROUGH ENTIRE RANGE SEVERAL TIMES AND OPERATION CHECKED SERVICEABLE. 2L72 4F4 F A16WE E2EA 20020308000852002030800085NE 2002 3 8 CA020215010 220020204G72703021436 DUCT CESSNA501 501 2076603CE PWA JD15 JT15D1A NE ENGINE CRACKED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) DURING DAILY INSPECTION, RT ENGINE FRONT & REAR INNER BYPASS DUCT FOUND CRACKED AND PIECE OF REAR UNDER BYPASS DUCT MISSING. AFTER REMOVAL OF THOSE ITEMS FROM THE ENGINE, THE INSPECTION REVEALED THAT THEY WERE PARTS WHICH WAS PREVIOUSLY WELDED/OVERHAUL ASSEMBLY INSTALLED AT THE LAST HOT SECTION INSPECTION.UNDER BYPASS DUCT P/N 3021436 & 3020330 1L72 4F4 F A27CE E25EA 20020311000082002031100008CE 2002 3 11 CA020220008 120020213G278099100554 MOTOR CESSNA500 550 2076604CE PWA JT15 JT15D4 52112NE LE FLAPS LOOSE W O OTHER F FLT CONT AFFECTED DEDESCENT 1 CA (CAN) THE SUBJECT LT MOTOR WILL MOVE TO ITS EXTREME END TRAVEL AND LOCK THE ARMATURE CAUSING THE C.B. TO POP AND THE FLAP SYSTEM TO STOP. WHEN THE CB WAS RESET THE FLAPS WOULD OPERATE NORMALLY, THIS HAPPENED TWICE DURING FLAP SELECTION AND WAS SNAGGED IN THE LOG BOOK. WHILE TROUBLESHOOTING THE SNAG, THE LT MOTOR LOCKED AND THE RT MOTOR CONTINUED TO RUN, SHEARING THE DRIVE SPROCKET ON THE RT GEARBOX OUTPUT SHAFT. THE FLAPS STOPPED MOVING AND THE MOTOR CONTINUED TO RUN UNTIL THE LIMIT SWITCH WAS REACHED AND THE MOTOR SHUT OFF. BOTH MOTORS AND GEARBOXES WERE REPLACED. 1L72 4F4 F A22CE E1NE 20020311000092002031100009EU 2002 3 11 CA020220010 120020208G243580601401 STARTER GEN AMD FALC50FALCON900 2700160EU GARRTTTFE731TFE7315BR WP ENGINE FAILED W H DEACTIVATE SYST/CIRCUITS H ELECT. POWER LOSS-50 PC TXTAXI/GRND HDL 1 CA (CAN) DURING START SEQUENCE, NR 2 ENGINE FAILED TO ROTATE, START SEQUENCE WAS CANCELLED, AND TRIED A SECOND TIME WITH NO ROTATION OF ENGINE. FAULT WAS TRACED TO THE STARTER GENERATOR, UNIT WAS REPLACED WITH A NEW AND START SEQUENCE WAS OK. NR 2 ENGINE STARTED AS PER MM. THIS IS THE SECOND STARTER GENERATOR FAILURE, THE OTHER HAPPENED 100 HOURS AGO ON NR 3 ENGINE. INSTALLED UPGRADED STARTER/GENERATOR [/N 8060-150. FALCON JET IS AWARE OF THIS PROBLEM. THE NR 1 ENGINE STARTER GEN AND APU STARTER GEN ARE GOING TO BE UPGRADED TO -150. 2L73 4F4 FRTA46EU E6WE 20020311000112002031100011GL 2002 3 11 CA020220015 120020216G7410N965177 WIRE DIAMONDA20 DA20A1 2990000GL ROTAX 912 ROTAX912 55555EU HOFMANHOV352HOV352F NE COIL BROKEN W K NONE O OTHER ININSP/MAINT 1 CA (CAN) FOLLOWING A FLIGHT THE ENGINE DID NOT SHUTDOWN WHEN IGNITION SELECTED TO OFF. NO RPM DROP WAS NOTED WHEN SWITCHING IGNITION FROM 'BOTH' TO 'R'.A BROKEN GROUND WIRE WAS FOUUND IN THE IGNITION CIRCUIT. 1L71 3O3 INTTA4CH EXPE3I 5 CTP5BO 20020426001072002042600107EA 2002 4 26 CA020221004 120020211G324650105711 WHEEL CNDAIRCL600 CL6002B19 1900309EA GE CF34 CF343B1 NE LT MLG MISSING W O OTHER D INFLIGHT SEPARATION NRNOT REPORTED 1 CA (CAN) AFTER FLT. CREW PERFORMED POST FLT INSPECTION AND FOUND LT OB WHEEL ASSY MISSING FROM A/C. THE MISSING WHEEL ASSY RECOVERED IN ATL FROM AIRPORT AUTH. IT OBVIOUSLY DEPARTED WHILE ON TAXI OR TAKEOFF. IT WAS RECOVERED WITH ANTI SKID DRIVE CAP INTACT. NEITHER INNER OR OUTER BEARINGS WERE FOUND IN WHEEL. INNER BORE OF WHEEL DAMAGED BY AXLE AS IT ROTATED AND CAME OFF AXLE. 2L72 4F4 FRTA21EA E15NE 20020311000132002031100013 2002 3 11 CA020221006 420020214G22106229815704 CIRCUIT BOARD CNDAIRCL600 CL6002B19 1900309EA GE CF34 CF343B1 NE FCC CARD FAILED W K NONE F FLT CONT AFFECTED APAPPROACH 1 CA 56512 (CAN) "ON FINAL TO TXK A/C WAS ALMOST UNCONTROLLABLE. YAW DAMPER THREW A/C IN A LT BANK & THEN A RT BANK WITH AUTOPILOT OFF. IT SETTLED DOWN ENOUGH TO GET A/C ON GROUND."MAINT SIGN OFF AS FOLLOWS: PERFORMED FCC DIAGNOSTICS T/S IAW CRJ MM. NO DEFECTS NOTED. PERFORMED CHECK ON RUDDER PRIMARY & SECONDARY FEEL MECHANISM CENTERING SPRINGS. FOUND PRIMARY SPRING TENSION TO BE AT 5 LBS. SET PRIMARY SPRING TENSION TO 10 LBS IAW CRJ MM. CHECKED RUDDER CONTROL CABLE TENSIONS & PERFORMED RIGGING CHECK IAW CRJ MM. OPS CHECK GOOD. R&R NR 1 & 2 FCC IAPS CARDS IAW CARJ MM. OPS CHECKS WERE GOOD & A/C WAS TEST FLOWN. 2L72 4F4 FRTA21EA E15NE 20020426001242002042600124EU 2002 4 26 CA020221019 220020218G8530N854115 EXHAUST VALVE DIAMONDA20 DA20A1 2990000GL ROTAX 912 ROTAX912F3 EU NR 3 CYLINDER CHIPPED W A UNSCHED LANDING RE PARTIAL RPM/PWR LOSS VIBRATION/BUFFET CLCLIMB 1 CA (CAN) AFTER TAKE-OFF IT WAS NOTED THAT THE ENGINE WAS NOT DEVELOPING FULL POWER. WHEN THE POWER SETTING WAS REDUCED TO ESTABLISH THE AIRCRAFT ON A DOWNWIND LEG A LOW FREQUENCY ENGINE VIBRATION WAS NOTED. A 1/4 INCH DIA CHIP WAS FOUND MISSING ON THE CIRCUMFERENCE OF THE EXHAUST VALVE OF NR 3 CYLINDER. 1L71 3O3 ONTTA4CH E00051EN 20020311000222002031100022EU 2002 3 11 CA020225005 220020225G8530N854105 INTAKE VALVE ROTAX 913435 DIAMONDA20 DA20A1 2990000GL ROTAX 912 ROTAX912 55555EU CYLINDER HEAD CRACKED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) DURING THE POST-INSPECTION ENGINE RUN SUBSTANTIAL ENGINE VIBRATION WAS NOTED. THE NR 4 CYLINDER WAS REMOVED AND THE INTAKE VALVE WAS FOUND TO HAVE A CRACK EXTENDING FROM A CENTRAL LOCATION TO THE EDGE OF THE VAVLE. SMALL CHIPS WERE ALSO NOTED TO BE MISSING FROM THE VALVE NEAR THE EDGES. 1L71 3O3 INTTA4CH EXPE3I 20020311000232002031100023EU 2002 3 11 CA020225006 220020225G8530N854105 INTAKE VALVE ROTAX 913435 DIAMONDA20 DA20A1 2990000GL ROTAX 912 ROTAX912 55555EU CYLINDER HEAD CORRODED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) THE BASE OF THE INTAKE VALVE STEM FROM THE NR 2 CYLINDER WAS FOUND TO BE PITTED. 1L71 3O3 INTTA4CH EXPE3I 20020311000242002031100024EU 2002 3 11 CA020225007 220020225G8530N854115 EXHAUST VALVE ROTAX 913435 DIAMONDA20 DA20A1 2990000GL ROTAX 912 ROTAX912 55555EU CYLINDER HEAD DAMAGED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) THE VALVE SEAT ON THE EXHAUST VALVE FROM CYLINDER NR 2 WAS FOUND TO BE DISHED. 1L71 3O3 INTTA4CH EXPE3I 20020311000252002031100025SW 2002 3 11 CA020226001 120020202G7810114018201 COVER BELL 205 205A1 1181414SW LYC T53 T5313B 41549NE EXHAUST DIFUSER CRACKED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) DURING THE DAILY INSPECTOIN, DAMAGE TO THE M/R BLADE WAS NOTICED. INSPECTION OF THE AIRCRAFT REVEALED THAT THE COVER, EXHAUST DIFFUSER, HELD BY A SPEC. BOLT AND TABWASHER ON THE COVER, TURB., REAR WAS MISSING. THE BOLT & TABWASHER WHERE STILL IN PLACE ON THE REAR TURB. COVER. IT SEEMS THAT THE EXHAUST DIFFUSER COVER HAD DISINTEGRATED AND ONE PIECE, APPROX 1 INCH LONG AND .250 INCH WIDE (APPROX 1.0 GR.) WAS SENT THROUGH THE ROTOR DISC FROM THE TAILROTOR, CAUSING THE MAIN ROTOR BALDE DAMAGE. BLADE CHANGE AND SPEC. INSPECTION AS PER MAINTENANCE MANUAL WILL BE CARRIED OUT. 1G71 4U4 U H1SW E17EA 20020311000262002031100026NE 2002 3 11 CA020226005 220020207G731402532330003 PUMP BEECH 200 B200 1152922CE PWA PT6 PT6A42 52043NE FUEL SYSTEM LEAKING W K NONE K FLUID LOSS ININSP/MAINT 1 CA (CAN) DURING SCHEDULED MAINTENANCE, NOTICED A DRIP OF FUEL COMING OFF OF THE ENGINE DRIVEN FUEL PUMP TO ENGINE FLANGE. WITH A CLOSER LOOK FOUND A BROWN STAIN AS WELL. REMOVED ENGINE DRIVEN FUEL PUMP ASSEMBLY AND INSPECTED. FOUND SPLINE DRIVE COUPLING WHICH ENTERS THE ENGINE ACCESSORY CASE CORRDED AND SEVERELY WORN. ENGINE DRIVEN PUMP ASSEMBLY REPLACED. 1L72 4T4 T A24CE E4EA 20020311000292002031100029EU 2002 3 11 CA020227009 220020216G7322961215 NEEDLE DIAMONDA20 DA20A1 2990000GL ROTAX 912 ROTAX912 55555EU CARBURETOR SHEARED W O OTHER ER VIBRATION/BUFFET PARTIAL RPM/PWR LOSS CRCRUISE 1 CA (CAN) DURING FLIGHT SUDDEN ROUGHNESS OCCURRED, PROP UNRESPONDSIVE WITH POWER FULL, AIRCRAFT RAN ROUGH THE WHOLE FLIGHT BACK, UNABLE TO MAINTAIN ALTITUDE, SLOW DESCENT APPROX 100 FEET/MIN FROM BIRDS HILL TO ST. ANDREWS. WINGS REMOVED AND AIRCRAFT TRANSOORTED TO WINNIPEG BASE, UPON INSPECTION FOUND L/H CARB NEEDLE SHEARED, NEEDLE AND CIRCLIP REPLACED, RT CARB INSP, WINGS REINSTALLED, SAFETIED AND TRAVEL CHECKED, PITOT STATIC TEST CARRIED OUT AS PER AWM 511 APPENDIX B. NO DEFECTS NOTED. AIRCRAFT GROUND RUN AND LEAK CHECKED SERVICEABLE. 1L71 3O3 INTTA4CH EXPE3I 20020311000362002031100036SW 2002 3 11 CA020228013 120020201G6220222010405115 SLEEVE BELL 222010400121BELL 222 222B 1182124SW LYC LTS101LTS101750C1 41560NE SWASHPLATE WORN W K NONE O OTHER ININSP/MAINT 1 CA EA73 (CAN) WHEN SWASH PLATE ASSY WAS REMOVED TO FACILITATE 7 YEAR MAST REMOVAL FOR INSPECTION AND RECALIBRATION, THE SLIDER BEARINGS (2OF) P/N 222-310-464-003 WERE FOUND DETACHED AND LOOSE, CREATING AN EXCESSIVE WEAR ON THE SLEEVE JOURNALS THAT HOUSE THESE BEARINGS TO A POINT WELL BEYOND CONTINUED AIRWORTHINESS. THE BALL SLEEVE ASSY AND SUPPORT WERE DEEMED UNSERVICEABLE AND WERE REPLACED AT GREAT EXPENSE. 1G72 3U3 U H9SW E5NE 20020311000372002031100037NM 2002 3 11 CA020228016 120020202G7920920024647 HOSE PIPER PA60 PA60601P 7106012NM LYC O540 IO540S1A5 41532EA ENGINE RUPTURED W EA ENGINE SHUTDOWN UNSCHED LANDING KJ FLUID LOSS WARNING INDICATION CLCLIMB 1 CA (CAN) TURBO OIL SUPPLY HOSE FROM OPTIONAL FILTER P/N 300180-501 TO WAISTGATE ACTUATOR ROUTED IN CLOSE PROXIMITY TO EXHAUST PIPES WITH SHARP BENDS DUE TO EXTREMITY TIGHT ROUTING. ADDITIONALLY THIS HOSE IS DISTURBED EVERY 50 HOURS DUE TO REMOVAL AND CLEANING OF FILTER ELEMENT CLEANING, SUBJECTING HOSE TO ADDITIONAL STRESSES. HOSE FAILED IN CLIMB OUT, RESULTING IN LOSS OF OIL PRESSURE. 1M72 3O3 ORTA17WE 1E4 20020311001052002031100105EU 2002 3 11 2002FA0000165 120020118G2910704A33690004 BELT SNIAS 350 AS350BA 8680817EU TMECA ARRIELARRIEL1B 6OO30NE HYDRAULIC SYS DEBONDED D A UNSCHED LANDING J WARNING INDICATION NRNOT REPORTED 1 WP19352NT395 2553 886 WHILE RETURNING FROM STRIP TOURS, THE AIRCRAFT EXPERIENCED A LOSS OF HYDRAULIC POWER. UPON SAFE LANDING ON THE TAXI WAY, THE AIRCRAFT WAS IMMEDIATELY TOWED TO THE MAINTENANCE HANGER AND INSPECTED FOR PROBABLE CAUSES OF THE HYDRAULIC FAILURE. IT WAS FOUND THAT THE BONDED SEAM OF THE HYDRAULIC DRIVE BELT HAD SEPARATED AT THE BOND. POSSIBLE RECOMMENDATIONS TO PREVENT REOCCURRANCE WOULD BE HIGHER QUALITY CONTROL AT THE MANUFACTURER OR A HIGHER QUALITY HYDRAULIC DRIVE BELT. 1G71 3U3 UNCH9EU E19EU 20020311001062002031100106 2002 3 11 2002FA0000172 420020201G34225050010902 GYRO SNIAS 350 AS350BA 8680817EU TMECA ARRIELARRIEL1B 6OO30NE COCKPIT PRECESSES D K NONE O OTHER ININSP/MAINT 1 WP13891SA 429 2201 4193 GYRO REMOVED DUE TO EXCESS PRECESSION. 1G71 3U3 UNCH9EU E19EU 20020311001102002031100110EU 2002 3 11 2002FA0000306 120020117G2435M20014 BRUSHES UROCOPEC120 EC120B 8680987EU TMECA ARRIUSARRIU2F NE STARTER GEN WORN C K NONE O OTHER ININSP/MAINT 1 WP25255SD300 1618XL 1102 34117 DEFECT FOUND DURING SCHEDULED MAINTENANCE, 100 HOUR INSPECTION. STARTER GENERATOR HAD PRIOR OVERHAUL AND MODIFICATION TO (XL) CONFIGURATION. FOUND 4 BRUSHES WORN LIMIT, 4 WITH UNDER 10 HOURS APPROXIMATE TIME LEFT. STARTER REPAIRED, NEW BRUSHES INSTALLED. POSSIBLE WRONG OR TOO SOFT CARBON COMPOUND. 1G72 3U3 UNCR0001RD E34NE 20020311001112002031100111WP 2002 3 11 2002FA0000308 120020209G3246369A795149 BEARING HUGHES369 369D 4470706WP ALLSN 250C 250C20 03013GL MLG INOPERATIVE B EOORK NONE O OTHER ININSP/MAINT 1 AL035074R 1151D FOUND LEFT FRONT MAIN LANDING GEAR KEEL BEARING AND RETAINER BACKED OUT OF KEEL FITTING. IT IS NORMALLY RETAINED WITH A CIRCLIP BUT IT WAS NOT ENGAGED BUT IT WAS CAPTURED BY THE BOLT. THE LIMIT OF REMOVAL WAS DEFINED BY THE FORK ON THE END OF THE LANDING GEAR LEG. THE ID OF THE BORE IN THE KEEL FITTING WAS WITHIN LIMITS AND A NEW RETAINER AND BEARING WERE INSTALLED WITH A NEW CIRCUP. 1G71 3U3 U H3WE E4CE 20020311001122002031100112WP 2002 3 11 2002FA0000309 120020212G3210369HG20073 GUIDE HUGHES369 369D 4470706WP ALLSN 250C 250C20 03013GL MLG BROKEN B EOORK NONE O OTHER ININSP/MAINT 1 AL035074R 1151D DURING 100/300 ROUTINE INSPECTION THE GUIDE TUBE FOR THE SPRING LOADED FILLETS WERE FOUND BROKEN ON (3) THREE LANDING GEAR. 1G71 3U3 U H3WE E4CE 20020311001682002031100168EA 2002 3 11 2002FA0000317 220020225G8520 BEARING MOONEYM20 M20M 5870222SW LYC 0540 TIO540AF1B 41532EA MCAULY3D32C B3D32C417 GL ENGINE FAILED D K NONE O OTHER ININSP/MAINT 1 NM01355RZ399 DURING A REGULER OIL CHANGE INTERVAL. METAL CONTAMINATS WER NOTED IN THE FOLDS OF THE OIL FILTER. THEY APPEARED TO BE OF ALUMINUM. FURTHER INVESTIGATION INTO THE PICK UP SCREEN FOUND A LARGER AMOUNT OF DEBRIS. SIZE OF THE DEBRIS APPEARED TO BE AROUND 1/16 OF AN INCH IN SIZE. IN ACCORDANCE WITH TEXTRON LYCOMING SERVICE INSTRUCTION THE AIRCRAFT WAS GROUNDED. SAMPLEL FROM BOTH THE FILTER AND PICK UP SCREEN WERE PACKAGED SEPERATLY AND SENT TO TEXTRON LYCOMING IN THE SAME PACKAGE BUT SEPERATED. TEXTRON CALLED BACK AND SAID THE CONTENS OF THE SAMPLE WERE BEARING MATERIAL. AT THE SAME TIME AS THE OIL WAS DRAINED FROM THE ENGINE, A SAMPLE WAS TAKEN FOR ANALYSIS. THE OIL SAMPLE WAS SHIPPED TO AOA. THE OIL ANALYSIS CAME 1L71 3O3 ORT2A3 E14EA 5 CP58GL 20020312000092002031200009CE 2002 3 12 2002FA0000167 120020116G2421648843 ALTERNATOR BEECH 33 F33A 1151425CE CONT O520 IO520BB 17032SO ENGINE FAILED B VJ3RO OTHER H ELECT. POWER LOSS-50 PC NRNOT REPORTED 1 WP035544A72 CE1343 825767R ALTERNATOR FAILED IN FLIGHT, WILL NOT CARRY THE LOAD. REPLACED ALTERNATOR, GROUND CHECKED OK. RETURNED TO SERVICE. 1L71 3O3 O 3A15 E5CE 20020312000122002031200012GL 2002 3 12 2002FA0000170 120020128G2822 PUMP DIAMONDA20 DA20C1 2990001GL CONT O240 IO240B 17063SO FUEL BOOST INOPERATIVE G A UNSCHED LANDING YJ ENGINE STOPPAGE WARNING INDICATION NRNOT REPORTED 1 EA07645DC C0145 806272 ENGINE QUIT DURING STALL PRACTICE. ENGINE WOULD START BUT NOT RUN. LANDED IN FIELD. FUEL PRESSURE TOO LOW. FACTORY REP INSTALLED SETUP GAGES AND ADJUSTED TO PROPER SPECS. ENGINE RAN GOOD AFTER PROPER ADJUSTMENT. 1L71 3O3 ONTTA4CH E7SO 20020312000152002031200015CE 2002 3 12 2002FA0000174 120020123G781099102992 EXHAUST PIPE CESSNA340 340A 2076405CE CONT O520 TSIO520* 17040SO RT ENGINE CRACKED B EWGRO OTHER O OTHER NRNOT REPORTED 1 SO05340WT 340A0332 PILOT OBSERVED RT FUEL QUANTITY INDICATOR FAILED, THEN RT FUEL TRANSFER LIGHT ON AND RT LANDING LIGHT CIRCUIT BREAKER POPPED. AFTER FLIGHT, VISUAL INSPECTION OF THE RT ENGINE NACELLE IDENTIFIED A BURN THROUGH NACELLE SKIN ADJACENT TO THE RT ENGINE OVERBOARD TAILPIPE. INVESTIGATION REVEALED THE TAILPIPE HAD FAILED AT THE OUTBOARD BEND, IN THE ENGINE COMPARTMENT, DAMAGING THE EXTERNAL NACELLE SKIN, FIREWALL, CANTED BULKHEAD, ENGINE BEAM, AND WIRING BEHIND THE FIREWALL. 1L72 3O3 O 3A25 E8CE 20020312000162002031200016SO 2002 3 12 2002FA0000175 220020130G8500IO470D ENGINE CESSNA310 310G 2074218CE CONT O470 IO470D 17026SO 5&6 CYLINDERS FAILED D E ENGINE SHUTDOWN E VIBRATION/BUFFET ININSP/MAINT 1 SO198939Z2642 1170 310G0039 WHILE PERFORMING A STATIC GROUND RUN, AT APPROX. 2200 RPMS THE ENGINE SHOOK VIOLENTLY. THE ENGINE WAS QUICKLY SHUT DOWN AND FUEL SHUT-OFF VALVE SELECTED TO THE OFF POSITION. CLOSE INSPECTION OF THE ENGINE REVEALED THAT THE NR 6 CYLINDER HAD SEPARATED FROM THE ENGINE. THE NR 5 CYLINDER WAS JAMMED WITH THE PISTON CONNECTING ROD SEVERED IN HALF. THE FORWARD ENGINE CASE WAS CRACKED IN SEVERAL PLACES EXPOSING BOTH NR 5 AND NR 6 CYLINDER ASSEMBLIES INNER MECHANISM AND CRANKSHAFT. RECOMMENDATIONS ARE TO REMOVE ENGINE AND SUBMIT IT TO A TEARDOWN INSPECTION ALONG WITH A METALLURGIC EVALUATION ON THE INTERNAL PARTS FOR FAILURE. IN PARTICULAR, THE NR 5 CYLINDER CONNECTING ROD AND FORWARD ENGINE CASE. 1L72 3O3 O 3A10 3E1 20020312000172002031200017NE 2002 3 12 2002FA0000176 220020125G7314025323150 PUMP CESSNA208 208B 2073701CE PWA PT6 PT6A114A 52043NE FUEL SYSTEM FAILED C NSPAA UNSCHED LANDING YJ ENGINE STOPPAGE WARNING INDICATION NRNOT REPORTED 1 SO059454B845 208B0072 HAD AN ENGINE FAILURE WHICH RESULTED IN THE AIRCRAFT LANDING SHORT OF THE AIRPORT. NO ONE WAS INJURED AND THE AIRCRAFT WAS NOT DAMAGED. ENGINE QUIT DUE TO ENGINE DRIVEN FUEL PUMP FAILURE. FUEL PUMP WAS REMOVED, A NEW PUMP INSTALLED, AND THE AIRCRAFT RETURNED TO SERVICE. 1H71 3T3 T A37CE E4EA 20020312000182002031200018SO 2002 3 12 2002FA0000180 220020124G74146320 MAGNETO PIPER PA46 PA46310P 7104605SO CONT O520 TSIO520* 17040SO RIGHT FAILED D O OTHER O OTHER NRNOT REPORTED 1 CE0547BC 4608129 PILOT REPORTED FAILED RT MAGNETO. REMOVED MAGNETO FROM ENGINE AND DISASSEMBLED. FOUND ONE OF THE COIL ANCHOR WEDGES WAS DISPLACED AND HAD MIGRATED ONTO THE SECONDARY TOWER. THE TOWER WAS BURNED AND MELTED AND THERE WAS OBVIOUS SIGNS OF A DIRECT SHORT AT THE SECONDARY TERMINAL CONTACT TAB. 1L71 3O3 ORTA25SO E8CE 20020312000192002031200019CE 2002 3 12 2002FA0000186 120020129G5412 FIREWALL CESSNA172 172R 2072401CE LYC O360 IO360A1A 41514EA ENGINE BAY CRACKED D MNZSK NONE O OTHER ININSP/MAINT 1 CE03361SA 17280755 DISCOVERED DURING ROUTINE MAINTENANCE THAT THE LEFT LOWER FIREWALL HAD CRACK LOCATED BENEATH THE DOUBLER FOR THE LEFT LOWER COWL MOUNT. IN ONE INSTANCE, CRACK WAS ACTUALLY LOCATED BENEATH THE LEFT FLANGE OF THE BATTERY MOUNT. 1H71 3O3 ONT3A12 1E10 20020312000202002031200020CE 2002 3 12 2002FA0000187 120020210G5412 FIREWALL CESSNA172 172S 2072439CE LYC O360 IO360A1A 41514EA ENGINE BAY CRACKED D K NONE O OTHER ININSP/MAINT 1 GL03364MA 172S8007 IT WAS DISCOVERED DURING AN ANNUAL INSPECTION THAT THE FIREWALL HAD A 2.75 INCH CRACK AT THE CENTER, LOWER COWL MOUNT DOUBLER. ALMOST IMPOSSIBLE TO VISUALLY DISCOVER W/O KNOWLEDGE OF THE PROBLEM. 1H71 3O3 ONT3A12 1E10 20020312000262002031200026CE 2002 3 12 2002FA0000197 120020130G2421 BEARING BEECH 35 S35 1151532CE CONT O520 IO520* 17032SO ALTERNATOR INOPERATIVE B X0FRK NONE L NO TEST ININSP/MAINT 1 WP0710WR 340 A86333 D7689 1203824B AIRCRAFT CAME IN FOR ALTERNATOR FAILURE. TESTED ALTERNERATOR SYSTEM AND DETERMINED ALTERNATOR, FAILED. REMOVED ALTERNATOR, NOTICED THAT THE COTTER KEY, NUT AND WASHER THAT HOLDS THE CLUTCH ON, WAS MISSING. FOUND CLUTCH ASSEMBLY BROKEN AND SHAFT OF ALTERNATOR VERY WORN OUT. REMOVED ENGINE AND OIL PAN. FOUND MISSING HARDWARE IN OIL PAN. APPEARS SHAFT BEARINGS WORN OUT AND SHAFT WAS LOOSE ENOUGH TO BAKE COTTER KEY AND TO DISLODGE NUT AND WASHER. ALTERNATOR INTERIOR OIL SOAKED. FRONT BEARING/SEAL WORN OUT. 1L71 3O3 O 3A15 E5CE 20020312000272002031200027CE 2002 3 12 2002FA0000198 120020115G7120 WASHER CESSNA208 208 2073702CE PWA PT6 PT6A11 52043NE ENGINE BOLTS WRONG PART B K NONE W INADEQUATE Q C ININSP/MAINT 1 AL05208LB801 20800283 DURING A ROUTINE INSPECTION, FOUND THE ENGINE MOUNT BOLTS HAD AN960616L WASHERS INSTALLED UNDER BOLT HEADS (12 BOLTS ) TOTAL. THIS TYPE BOLT MUST HAVE MS20002C6 WASHERS. 1H71 3T3 TNTA37CE E4EA 20020312000282002031200028 2002 3 12 2002FA0000199 420020109G611305503671 SPINNER CESSNA172 172S 2072439CE LYC O360 IO360A1A 41514EA PROPELLER CRACKED B FE4RK NONE O OTHER ININSP/MAINT 1 AL05792SP156 172S8717 FOUND CRACKED PROP SPINNER. 1H71 3O3 ONT3A12 1E10 20020312000292002031200029WP 2002 3 12 2002FA0000201 120020129G2820168863Q01 HOSE NAMER F51 P51D 6402304WP PCKARDV1650 V16507 49001SO FUEL SYSTEM SPLIT D K NONE O OTHER ININSP/MAINT 1 EA1751JB 4473029A UPON INSTALLATION OF A FUEL SELECTOR NOTICED THE OUTER COVER OF THE HOSE SPLIT AS IT WAS INSTALLED ON AN NIPPLE FITTING. AFTER CLOSE EXAMINATION, THE NEW HOSE SHOWS A MARK / CUT GOING THE LENGTH OF THE HOSE. IN SOME AREAS IT IS A MARK AND OTHER AREAS IT IS A CUT THROUGH THE OUTER LAYER OF THE HOSE. THE DEFECT IS STRAIGHT WITH NO WAVERING AND APPEARS LIKE IT CAME FROM THE MANUFACTURES EQUIPMENT THIS WAY. THIS MATERIAL REQUIRED REPLACEMENT OF ALL NEWLY INSTALLED HOSE ON THIS AIRCRAFT. 1L71 4V4 V L113 EXP4V 20020312000302002031200030EA 2002 3 12 2002FA0000204 220020116G8520LW13827 CRANKCASE PIPER PA60 PA60601P 7106012NM LYC O540 IO540S1A5 41532EA RT ENGINE CRACKED G K NONE O OTHER ININSP/MAINT 1 CE07502SB2585 61P0502207 L1784148A CRANKCASE FAILED NEAR NR 2 CYLINDER, CRACKED FROM IN FRONT OF CYLINDER RADIALLY BELOW AND AROUND TO THE REAR OF THE CYLINDER. CRACK EXTENDS MORE THAN 180 DEGREES, ALL 3 UPPER CYLINDER BASE STUDS AND UPPER CRANKCASE THRU BOLT WERE ALL BROKEN. THE ONLY THING STILL HOLDING THE CYLINDER TO THE ENGINE WAS THE LOWER .5000 THRU BOLT. 1M72 3O3 ORTA17WE 1E4 20020312000312002031200031 2002 3 12 2002FA0000205 420020131G2300S28701 SWITCH CESSNA172 172R 2072401CE LYC O360 IO360A1A 41514EA MICROPHONE INTERMITTENT B LC1RO OTHER O OTHER NRNOT REPORTED 1 EA0735331 17281037 REOCCURING INTERMITTENT PUSH TO TALK SWITCH OPERATION. 1H71 3O3 ONT3A12 1E10 20020312000332002031200033SO 2002 3 12 2002FA0000209 220020123G8520 SLEEVE CONT O520 GTSIO520M 17032SO LIFTER BORE SEPARATED B CQ2RK NONE W INADEQUATE Q C ININSP/MAINT 1 SW15 276346R LIFTER BORES WERE SLEEVED (12 EA) NOTE: SLEEVES CAME LOOSE IN ALL HOLES (EXCEPT 2), ROTATING AND BLOCKING OIL PASSAGE. NO SAFETY PINS IN PLACE TO MAINTAIN SECURITY OF SLEEVES, NO OTHER MEANS OF HOLDING SLEEVES IN PLACE. ONLY THING THAT APPEARED TO HOLD SLEEVES WAS BURR, CREATED WHEN OIL HOLE WAS DRILLED, AND MAYBE DRAIN HOLE AT BOTTOM WAS BURRED. (INTENDED TO HAVE AN INTERFERENCE FIT ONLY, BETWEEN HOLE PREPAIRED FOR SLEEVE AND SLEEVE WAS OF VERY THIN WALL, ALUMINUM SLEEVE MATERIAL HOLE FINISH SIZE IS 1.000 INCH, FOR LIFTER, SLEEVE APPEARS TO HAVE APPROX 1.125 DIAMETER CREATING ONLY A .062 WALL THICKNESS. NOT ENOUGH TO MAINTAIN SECURITY WITHOUT AID OF STABILIZING PIN OR (WELD IN PLACE) OR MEANS OF SAFETY. 3 O E7CE 20020312000352002031200035CE 2002 3 12 2002FA0000211 120020128G3230NAS561P628 PIN CESSNA441 441 2076020CE GARRTTTPE331TPE331* 01514WP LT MLG CRACKED G K NONE O OTHER ININSP/MAINT 1 SW03689AE5026 4410281 DUE TO PIN FAILURE ON AIRCRAFT, PINS WERE REMOVED FOR INSPECTION AND THE LEFT TO THE POINT OF FAILURE . THE FORWARD PIN ON THE RIGHT SIDE WAS INTACT BUT SHOWING SIGNS OF SHEARING. ALL FOUR MAIN LANDING GEAR PIVOT SLOTTED PINS WERE REPLACED WITH NEW NAS561P628. 1L72 3T3 TRTA28CE E2WE 20020312000392002031200039CE 2002 3 12 2002FA0000214 120020213G28201200406131 LINE CESSNA210 T210L 2073449CE CONT O520 TSIO520* 17040SO FUEL VENT CORRODED D K NONE K FLUID LOSS ININSP/MAINT 1 WP09711PJ2500 21061128 LINE DEVELOPED PINHOLE LEAK DUE TO CORROSION WHERE CABIN VENT SCEET HOSE RESTED ON TOP OF IT. 1H71 3O3 O 3A21 E8CE 20020312000402002031200040CE 2002 3 12 2002FA0000216 120020212G3233JE1 ACTUATOR CESSNA340 340CESSNA 2076404CE CONT O520 TSIO520N 17040SO HARTZLHCJ3Y PHCJ3YF2 GL RT MLG BROKEN D O OTHER N FALSE WARNING NRNOT REPORTED 1 CE03340TC9000 3400082 218720R EB1908 RT MLG DOWN LIGHT DID NOT SHOW DOWN AND LOCK. REMOVED RIGHT SWITCH (DOWNLOCK) 1SE1 SWITCH AND ACTUATOR SWITCH LEAF (JE1) FELL OUT. THE JE1 ACTUATOR WAS BROKEN AND PART OF THE ACTUATOR WAS MISSING. ORDERED NEW PARTS,REPLACED 1SE1(SWITCH)AND ACTUATOR JE1 WITH MFG PART, PART NUMBER S2112-1 (ACTUATOR) AND S2088-4(SWITCH). 1L72 3O3 O 3A25 E8CE 5 CP36EA 20020312000412002031200041SO 2002 3 12 2002FA0000217 220020215G8550642841 LINE PIPER PA28 PA28R201T 7102813SO CONT O360 TSIO360FB 17025SO ENGINE OIL WORN G A UNSCHED LANDING J WARNING INDICATION CRCRUISE 1 NM05113VK2620 450 28R7803352 ENGINE LOST OIL PRESSURE IN CRUISE FLIGHT. THE PILOT MADE AN UNSCHEDULED LANDING. INVESTIGATION REVEALED THAT THE OIL FILLER CAP HAD COME OFF AND THE ENGINE LOST OIL. THE INTERNAL AREA OF THE OIL FILLER TUBE HAD WORN AND WOULD NO LONGER PUT SUFFICIENT PRESSURE ON THE OIL CAP RETAINING SPRING CLIPS. DUE TO THE IMPACT ON SAFETY, THE OIL FILLER TUBE SHOULD BE REPLACED AT ENGINE TBO. 1L71 3O3 O 2A13 E9CE 20020312000462002031200046CE 2002 3 12 2002FA0000223 120020206G57530523921 ROLLER CESSNA172 172R 2072401CE LYC O360 IO360A1A 41514EA TE FLAP GOUGED B IB1RK NONE O OTHER ININSP/MAINT 1 EA234206K933 17280751 DURING ACCOMPLISHMENT OF SB, THE LT FLAP INBOARD TRACK INBOARD AFT BEARING SUPPORT ARM WAS FOUND TO BE GOUGED .025 INCH DEEP MATCHING THE OUTER RADIUS OF THE ROLLER ASSEMBLY. THE ROLLER ASSEMBLY WAS FOUND TO HAVE THE INNER ROLLER CAGE OFFSET ENOUGH TO ALLOW THE OUTSIDE DIAMETER OF THE ASSEMBLY TO ROTATE AGAINST THE FLAP SUPPORT ARM CAUSING THE GOUGE. THE OFFSET OF THE INNER CAGE WAS FOUND TO BE .025 INCH MATCHING THE DEPTH OF THE GOUGE. PROBABLE CAUSE APPEARS TO BE IMPROPER CENTERING OF THE INNER BEARING CAGE AT INITIAL ASSEMBLY. MFG HAS BEEN NOTIFIED. RECOMMEND BEARING INSPECTION AT FLAP INSTALLATION AND ASSURING CLEARANCE BETWEEN THE BEARING ENDS AND THE FLAP SUPPORT ARMS. 1H71 3O3 ONT3A12 1E10 20020312000472002031200047SO 2002 3 12 2002FA0000224 120020205G270062701113 CONTROL CABLE PIPER PA28 PA28181 7102807SO LYC O360 O360* 41514EA STABILATORS FRAYED B UC2RK NONE O OTHER ININSP/MAINT 1 GL194146D2546 2843153 FOUND THE RT AND LT FORWARD STABILATOR CONTROL CABLES FRAYED AND WORN DURING A 100 HOUR INSPECTION. 1L71 3O3 O 2A13 E286 20020312000492002031200049CE 2002 3 12 2002FA0000226 120020206G7120085112120 BEAM CESSNA340 340A 2076405CE CONT O520 TSIO520* 17040SO RT ENGINE CORRODED B FCPRK NONE O OTHER ININSP/MAINT 1 NM092696U 340A0780 FOUND RT OUTBOARD ENGINE BEAM CORRODED BEYOND LIMIT, CANTED BULKHEAD WAS ALSO CORRODED BEYOND LIMITS. SUGGEST SHORTER INTERVAL BETWEEN INSPECTIONS. 1L72 3O3 O 3A25 E8CE 20020312000542002031200054SO 2002 3 12 2002FA0000230 220020110G8520630393 PUSHROD PIPER PA34 PA34200T 7103406SO CONT O360 LTSIO360EB 17025SO LT ENGINE CRACKED C K NONE O OTHER ININSP/MAINT 1 EA17912843197 1371 347970111 306764 ON ANNUAL INSPECTION OF THE LT ENGINE (TOTAL TIME 3197.9) THREE PUSH RODS WERE NOTED TO BE CRACKED ALONG ALMOST THE ENTIRE LENGTH OF THE PUSHRODS EXTENDING FROM THE VERY TOP. PUSHRODS REPLACED WITH NEW AND 9 OVERHAULED. BECAUSE OF THIS FINDING ALL 12 PUSHRODS ON RIGHT ENGINE WERE OVERHAULED. CAUSE UNKNOWN. RECOMMEND MORE FREQUENT INSPECTION OF PUSHRODS. CRACK IN PUSHROD EXTENDING FULL LENGTH OF ROD. 1L72 3O3 O A7SO E9CE 20020312000722002031200072SW 2002 3 12 2002FA0000249 120020201G5711 SPAR BBAVIA7 7AC 2110102SW CONT A65 A65* 17003SO LT WING CRACKED D K NONE O OTHER ININSP/MAINT 1 GL0383280 1947 DURING INSPECTION OF AD INSPECTION. FOUND LEFT WING FORWARD SPAR CRACKED AT UNDER SIDE OF SPAR OUT BOUND OF LIFT STRUT ATTACH POINT. OWNER WAS CALLED TO INFORM HIM THIS WING WILL BE REPAIRED WITH NEW SPAR INSTALLED. 1H71 3O3 O A759 E205 20020312000772002031200077SW 2002 3 12 2002FA0000254 120020222G5711 SPAR BBAVIA7 7EC 2110120SW CONT C90 C90* 17009SO RT WING CRACKED D K NONE O OTHER ININSP/MAINT 1 GL1570824 337 DURING THIS ANNUAL INSPECTION FOUND COMPRESSION CRACKS ON THE RIGHT WING REAR SPAR AT TOP LOCATION ON TOP SIDE OF SPAR. THIS COMPRESSION CRACK WAS HIDDEN UNDER OLD SPAR VARNISH AND WOULD HAVE BEEN MISSED IF TOP INSPECTION HOLES WERE NOT INSTALLED ALSO MANY OTHER CRACKS WERE SPOTTED IN SAME AREAS. BUT WERE NR 2 PENCIL LINES THE MFG USED TO LOCATE THE GLUE LINES. 1H71 3O3 O A759 E252 20020312000812002031200081CE 2002 3 12 2002FA0000257 120020205G561010138402521 WINDSHIELD BEECH 200 B200 1152922CE PWA PT6 PT6A60A 52043NE COCKPIT CRACKED D O OTHER O OTHER NRNOT REPORTED 1 NM0963791 BB1100 WINDOW SHATTERED DURING FLIGHT AT ALTITUDE. REPLACED WITH NEW UNIT USING MFG SUPPLIED INSTALLATION KIT. 1L72 4T4 T A24CE E4EA 20020312000832002031200083SO 2002 3 12 2002FA0000259 120020115G322274381 FITTING GULSTMGV GULFSTREAMGV3980116SO RROYCEBR700 BR700710A110 NE NLG CRACKED G O OTHER O OTHER NRNOT REPORTED 1 EA03588GA940 588 AFTER GEAR EXTENSTION, CREW HAD A LOUD BANG, AND NOTICED LOSS OF LEFT HAND HYDRAULIC FLUID. AFTER LANDING INSPECTION SHOWED NOSE GEAR SWIVEL FITTING CRACKED AT FORGED SEAM. 2L72 4F4 FRTA12EA E00057EN 20020312000842002031200084SW 2002 3 12 2002FA0000260 120020201G5710 STRUT BBAVIA7 7CCM 21101MWSW CONT C90 C90* 17009SO WING DAMAGED D K NONE O OTHER ININSP/MAINT 1 GL152762E 7AC6345 WING STRUTS HAD FILLED WITH WATER FROM SITTING OUTSIDE. RUST STAINS VISIBLE FROM OUTSIDE OF STRUT. WHEN POKED WITH AN 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. 1H71 3O3 O A759 E252 20020312000852002031200085SW 2002 3 12 2002FA0000261 120020201G5711 SPAR BBAVIA7 7CCM 21101MWSW CONT C90 C90* 17009SO WING CRACKED D K NONE O OTHER ININSP/MAINT 1 GL152762E 7AC6345 CRACK ON BOTTOM SURFACE OF SPAR LEFT SIDE REAR. FOUND PRIOR TO CRACK INSPECTION AS PER AD, OWNER DISCONTINUED ANNUAL INSPECTION PRIOR TO FULL INSPECTION. 1H71 3O3 O A759 E252 20020312000882002031200088SO 2002 3 12 2002FA0000266 120020205G5280 BOLT PIPER PA31 PA31350 7103110SO LYC O540 TIO540* 41532EA NLG DOOR WORN D K NONE O OTHER ININSP/MAINT 1 WP1957PA 317305081 PILOT REPORTED NOSE WHEEL WOULD NOT LOCK (UP) AND RETURNED TO BASE WITHOUT ABNORMAL INDICATION. MAINTENANCE INSPECTION REVEALED THAT THE BOLTS IN THE NOSE WHEEL RIGHT DOOR WERE WORN AND WERE REPLACED. DOOR WAS STRAIGHTENED AND RERIGGED. RETRACTION AND OPS CHECKED OK. FLOWN AND RELEASED FOR SERVICE. 1L72 3O3 O A20SO E14EA 20020312000902002031200090CE 2002 3 12 2002FA0000268 120020213G324066109 LINER CESSNA172 172N 2072434CE LYC O320 O320* 41508EA BRAKE CYLINDER CRACKED D K NONE O OTHER ININSP/MAINT 1 SW03737ES 17269366 ON INSPECTION OF BRAKE LININGS AT A 100 HOUR INSPECTION, THE RIGHT BRAKE LININGS WERE FOUND CRACKED. UPON REMOVAL, THE THEY WERE FOUND LOOSE ON THE BRAKING PLATE. LINING RIVETS WERE FOUND TO BE IMPROPERLY SWAGED AND APPEARED TO BE COMPRESSED WITH IMPROPER TOOLING. 1H71 3O3 ONT3A12 E274 20020312000912002031200091SO 2002 3 12 2002FA0000269 220020216G8530654441 VALVE SPRING CESSNA188 A188B 2073005CE CONT O240 IO240A SO CYLINDER FAILED D TPMGK NONE L NO TEST ININSP/MAINT 1 SW13731LJ910 18802975T 812753R DURING ANNUAL INSPECTION, PERFORMED A COMPRESSION CHECK ON ALL ENGINE CYLINDERS. TWO CYLINDERS FAILED THE CHECK LEAKING BY THE VALVES. REMOVED CYLINDERS, DISASSEMBLED. CHECKED VALVE SPRINGS INNER AND OUTER TENSION PER CONT OVERHAUL MANUAL USING A VALVE SPRING TESTER AND FOUND THAT THE INNER AND OUTER VALVE SPRINGS FAILED. TOTAL TIME ON THESE SPRINGS 910 SINCE NEW. REPLACED INNER AND OUTER VALVE SPRINGS WITH NEW SPRINGS AFTER CHECKING SPRING TENSIONS. 1L71 3O3 O A9CE E7SO 20020312000922002031200092WP 2002 3 12 2002FA0000270 220020118G725030606901 BLADE GARRTTTFE731TFE7315R 01518WP TURBINE SECTION DAMAGED B UO2RO OTHER O OTHER NRNOT REPORTED 1 GL19 1842 1196 P91152 3RD LPT BLADE SEPARATED AT MID-SPAN CAUSING DAMAGE BEYOND LIMITS TO 7EA 3RD LPT BLADES. ALSO DAMAGED THE EXHAUST NOZZLE AND 3RD LPT NOZZLE BEYOND LIMITS. 4 F E6WE 20020312000932002031200093CE 2002 3 12 2002FA0000272 120020218G8120 CROSSOVER TUBE BEECH 33 F33A 1151425CE CONT O520 IO520BB 17032SO TURBOCHARGER BROKEN B YEBRK NONE O OTHER ININSP/MAINT 1 CE057254T315 CE1065 813757R DURING AN ANNUAL INSPECTION, THE TURBOCHARGER CROSSOVER TUBE WAS FOUND DAMAGED FROM THE AIRCRAFT DRIVE PULLEY. THIS AIRCRAFT HAS BEEN MODIFIED BY TURBO FLITE STC SA5223NM AND SE5222NM. UPON REMOVAL OF THE TUBE A HOLE WAS DISCOVERED BELOW THE DAMAGED AREA THAT WAS APPARENTLY CAUSED FROM THE INSTALLER DEFORMING THE TUBE TO GAIN CLEARANCE FOR THE DRIVE PULLEY. AFTER ORDERING A REPLACEMENT PART FROM THE MANUFACTURER, I WAS INSTRUCTED TO DEFORM THE TUBE TO GAIN CLEARANCE BETWEEN THE REPLACEMENT TUBE AND AIRCRAFT DRIVE PULLEY. THIS ACTION IS LIKELY TO CAUSE THE TUBE TO FAIL AS MENTIONED ABOVE. 1L71 3O3 O 3A15 E5CE 20020312000982002031200098CE 2002 3 12 2002FA0000278 120020202G280025765362 SERVO CESSNA172 172R 2072401CE LYC IO360 IO360L2A EA FUEL SYSTEM MALFUNCTIONED B AP1RO OTHER RJ PARTIAL RPM/PWR LOSS WARNING INDICATION NRNOT REPORTED 1 EA112317U 17280695 L2802451A REPORTED ENGINE LOST POWER TWICE (ENG RUNNING 1 HOUR). 1H71 3O3 ONT3A12 1E10 20020313000012002031300001CE 2002 3 13 2002FA0000279 120020214G8000S1577A1 CONTACTOR CESSNA150 152 2071835CE LYC O235 O235L2C 41505EA STARTER STUCK B LV0RK NONE O OTHER ININSP/MAINT 1 CE018908747 15282625 STARTER ENGAGED UPON CLOSING AIRCRAFT MASTER SWITCH. FOUND S1577A1 CONTACTOR IN THE STUCK CLOSED POSITION, WITH NO ELECTRICAL POWER APPLIED. REPLACED CONTACTOR. 1H71 3O3 ONT3A19 E223 20020313000022002031300002EA 2002 3 13 2002FA0000282 220020214G741410357584 GEAR PIPER PA28 PA28180 7102808SO LYC O360 O360* 41514EA RT MAGNETO DAMAGED D K NONE O OTHER ININSP/MAINT 1 EA039614J1684 283767 RT MAGNETO WAS INTERMITTENT, AND FINALLY FAILED. DISTRIBUTOR GEAR ALMOST HALF OF THE TEETH WERE MISSING. NO RELATED PROBLEMS WITH MAGNETO OR VISIBLE CAUSE. POSSIBLY DAMAGED AT SAME PREVIOUS INSTALLATION. 1L71 3O3 O 2A13 E286 20020313000042002031300004SO 2002 3 13 2002FA0000284 120020218G3710842CW PUMP PIPER PA31 PA31P 7103120SO LYC O541 TIO541E1A4 41536EA VACUUM SYSTEM SEIZED B EKIRK NONE O OTHER ININSP/MAINT 1 WP07648SC 31P7300143 L55562 BOTH PUMPS FAILED WITHIN 30 MINUTES OF EACH OTHER. BOTH LOW TEMPERATURE PUMPS OVERLOADED. 1L72 3O3 O A8EA E10EA 20020313000052002031300005SO 2002 3 13 2002FA0000285 120020219G270062701113 CONTROL CABLE PIPER PA28 PA28181 7102807SO LYC O360 O360* 41514EA STABILATOR WORN B UC2RK NONE O OTHER ININSP/MAINT 1 GL194145X2536 2843152 DURING A ROUTINE INSPECTION THE RT AND LT FORWARD STABILATOR CABLES WERE FOUND WORN AND FRAYED. THE AILERON RIGHT AND LEFT BALANCE CABLES WERE ALSO FOUND IN A SIMILAR CONDITION. THE WORN AND FRAYED PARTS OF THE CABLES WERE FOUND AT PULLEYS FAIRLEADS OR ANY PLACE THE CABLES CAME IN CONTACT WITH. 1L71 3O3 O 2A13 E286 20020313000062002031300006SO 2002 3 13 2002FA0000286 120020219G270062701114 CONTROL CABLE PIPER PA28 PA28181 7102807SO LYC O360 O360* 41514EA STABILATOR WORN B UC2RK NONE O OTHER ININSP/MAINT 1 GL194145X2536 2843152 DURING A ROUTINE INSPECTION THE RT AND LT FORWARD STABILATOR CABLE WERE FOUND WORN AND FRAYED. THE AILERON RIGHT AND LEFT BALANCE CABLES WERE ALSO FOUND IN A SIMILAR CONDITION. THE WORN AND FRAYED PARTS OF THE CABLES WERE FOUND AT PULLEYS FAIRLEADS OR ANY PLACE THE CABLES CAME IN CONTACT WITH. PROBABLE CAUSE: SUBSTANDARD CABLE AND IMPROPER ALIGNMENT BY MANUFACTURER. 1L71 3O3 O 2A13 E286 20020313000082002031300008CE 2002 3 13 2002FA0000293 120020226G812063272913 TURBOCHARGER BEECH 36 B36TC 1151609CE CONT O520 TSIO520* 17040SO ENGINE LEAKING B EKGRK NONE K FLUID LOSS ININSP/MAINT 1 WP07234PT56 EA662 527458 TURBOCHARGER WAS FOUND TO BE LEAKING OIL INTO INDUCTION SYSTEM. CHECKED SYSTEMS AS PER MFG AND MM. THIS IS NR 1 OF SEVERAL REPLACED ON THIS ENGINE. 1L71 3O3 O 3A15 E8CE 20020313000102002031300010CE 2002 3 13 2002FA0000295 120020122G57510322709 BRACKET CESSNA195 195A 2073110CE JACOBSR755 R7559 35003EA AILERON HINGE CORRODED D K NONE O OTHER ININSP/MAINT 1 CE03195DH 7588 INBOARD AILERON HINGE BRACKET, THESE MAGNESIUM BRACKETS WERE SEVERELY CORRODED AND CRACKED UNDER THE PAINT AND COULD ONLY BE SEEN AFTER BEAD BLASTING. THESE BRACKETS ARE THE ATTACH FOR THE AILERONS AND ARE CRACKING COMPLETELY ACROSS THE RETAINING BOSS FOR THE BEARING. SUGGEST PAINT REMOVAL AND INSPECTION OF BRACKET OR REPLACE WITH STC`S ALUMINUM BRACKETS. APPROXIMATELY 80 PERCENT OF THE ORIGINAL BRACKETS WE HAVE INSPECTED HAVE BEEN SEVERELY CORRODED/ CRACKED. 1H71 3R3 R A790 TC121 20020313000112002031300011CE 2002 3 13 2002FA0000296 120020122G575103227091 BRACKET CESSNA195 195A 2073110CE JACOBSR755 R7559 35003EA AILERON HINGE CORRODED D K NONE O OTHER ININSP/MAINT 1 CE03195DH 7588 INBOARD AILERON HINGE BRACKET, THESE MAGNESIUM BRACKETS WERE SEVERLY CORRODED AND CRACKED UNDER THE PAINT AND COULD ONLY BE SEEN AFTER BEAD BLASTING. THESES BRACKETS ARE THE ATTACH FOR THE AILERONS AND ARE CRACKING COMPLETELY ACROSS THE RETAINING BOSS FRO THE BEARING. SUGGEST PAINT REMOVAL AND INSPECTION OF BRACKET OR REPLACE WITH STC`S ALUMINUM BRACKETS. THE ORIGINAL BRACKETS, WE HAVE INSPECTED, HAVE BEEN SEVERELY CORRODED/ CRACKED. 1H71 3R3 R A790 TC121 20020313000122002031300012SO 2002 3 13 2002FA0000297 120020225G29101776604 HOSE PIPER PA31 PA31350 7103110SO LYC O540 TIO540* 41532EA HYD SYSTEM DAMAGED G A UNSCHED LANDING J WARNING INDICATION CLCLIMB 1 SW114106F6363 318252034 HOSE ASSEMBLY FAILED AFTER TAKE-OFF AND NOSE GEAR WOULD NOT RETRACT. PILOT TRIED TO HAND PUMP THE MANUAL HYDRAULIC PUMP WITH SO SUCCESS. INSPECTION NOTED LINE BLEW A HOLE BELOW THE TSO TAG AREA. IT IS RECOMMENDED THAT ON ANNUAL INSPECT BOTH ACTUATOR HOSE ASSEMBLY SHOULD BE INSPECTED BELOW THE TSO TAG AND SPIRAL WRAP FOR DAMAGE. 1L72 3O3 O A20SO E14EA 20020313000152002031300015 2002 3 13 2002FA0000300 420020204G6113C5046 PLATE CESSNA182 R182 2072734CE LYC O540 O540J3C5 41532EA MCAULY2D34C B2D34C218 GL PROP SPINNER CRACKED B OF1RK NONE W INADEQUATE Q C ININSP/MAINT 1 EA174770T750 R18201758 L2392340A 993189 DURING A 50 HOUR INSPECTION THE SPINNER ASSEMBLY WAS DETECTED TO BE VERY LOOSE ON THE PROP. UPON FURTHER EXAMINATION BOTH SPINNER ATTACH PLATES WERE FOUND CRACKED ALL THE WAY AROUND FOUR OF SIX PROP ATTACH BOLT HOLES. CRACKS EMANATED FROM THE CORNER OF EACH BOLT HEAD AND WENT IN EACH DIRECTION ALL THE WAY TO THE EDGE OF THE ATTACH PLATES (3 CRACKS ON ONE PLATE AND ONE ON THE OTHER). AFTER CHECKING THE PARTS CATALOG IT WAS DETERMINED THAT THE SIX WASHERS REQUIRED FOR THE ATTACH BOLTS HAD BEEN OMITTED DURING THE PROPELLER ASSEMBLY. DURING REPAIR OF AC, INSTALLED THE SIX WASHERS REQUIRED BY THE MFG CATALOG. BELIEVE IT WILL PREVENT FUTURE REOCCURRENCE. 1H71 3O3 ORT3A13 E295 5 CP7EA 20020313000162002031300016CE 2002 3 13 2002FA0000303 120020207G812063272913 TURBOCHARGER BEECH 36 B36TC 1151609CE CONT O520 TSIO520* 17040SO ENGINE LEAKING B EKGRK NONE K FLUID LOSS ININSP/MAINT 1 WP07234PT21 EA662 527458 TURBOCHARGER LEAKING OIL IN INDUCTION. THIS UNIT WAS REMOVED AND RETURNED DIRECTLY TO MFG FOR INVESTIGATION. THIS IS NR 3 FOR THIS ENGINE. NO WORD FROM MFG ON CAUSE OF PROBLEM. ENGINE IS TO BE REPLACED BY MFG. 1L71 3O3 O 3A15 E8CE 20020313000182002031300018CE 2002 3 13 2002FA0000307 120020304G5610511604202 WINDSHIELD CESSNA421 421B 2076014CE CONT O360 TSIO360* 17025SO COCKPIT DEPARTED D O OTHER D INFLIGHT SEPARATION NRNOT REPORTED 1 SW01421LP 421B0323 AT APPROXIMATELY 17,000 FEET CO-PILOTS WINDSHIELD DEPARTED AIRCRAFT, RECOMMEND LARASCOPE INSPECTION OF WINDSHIELD HOLES. TOTAL TIME ON PART 6,234.9. 1L72 3O3 O A7CE E9CE 20020313000192002031300019SO 2002 3 13 2002FA0000310 120020222G3110587837 MASTER SWITCH PIPER PA34 PA34200T 7103406SO CONT O360 TSIO360EB 17025SO COCKPIT BROKEN B CTURK NONE O OTHER ININSP/MAINT 1 GL213054K 347970102 307788 THE MASTER SWITCH IS DIVIDED INTO TWO SWITCHES A THAT ARE COUPLED TOGETHER WITH A PLASTIC TAB. THE HALF OF THE SWITCH THAT CONTROLS THE ALTERNATOR FIELDS IS HIDDEN UNDER THE SIDE PANEL. WHEN THE TAB THAT COUPLES THE TWO TOGETHER BROKE, THE ALTERNATORS DROPPED OFF LINE. 1L72 3O3 O A7SO E9CE 20020313000362002031300036GL 2002 3 13 2002FA0000325 320020225G61101A105SCM7153 PROPELLER AMRGENAA1 AA1 0630610SO LYC O235 O235C 41505EA MCAULY1A105 1A105SCM GL NOSE SEPARATED G A UNSCHED LANDING ED VIBRATION/BUFFET INFLIGHT SEPARATION CRCRUISE 1 EA215999L2642 142 AA10299 G7005 WHILE CRUISING AT 5000 FEET THE PILOT REPORTED SEVERE VIBRATION. AFTER PERFORMING AN UNEVENTFUL LANDING AND ENGINE SHUT DOWN, THE PILOT OBSERVED THAT APPROXIMATELY 4 INCH INCHES OF ONE BLADE TIP WAS MISSING. FURTHER INVESTIGATION REVEALED THAT A SMALL STONE HAD LEFT A SMALL NICK IN THE LEADING EDGE OF THE PROPELLER BLADE WHICH IS WHERE THE TIP SEPPARATED FROM THE REST OF THE BLADE. 1L71 3O3 O A11EA E223 5 NP918 20020313000372002031300037SO 2002 3 13 2002FA0000326 220020226G8530CN635448FC CYLINDER CESSNA340 340CESSNA 2076404CE CONT O520 TSIO520K 17040SO RT ENGINE BROKEN B A UNSCHED LANDING ER VIBRATION/BUFFET PARTIAL RPM/PWR LOSS CLCLIMB 1 SO11986CB 1401 3400328 R21752771K PILOT REPORTED PARTIAL LOSS OF POWER AND VIBRATION FROM RIGHT ENGINE ON CLIMB-OUT. UPON INSPECTION FOUND RIGHT ENGINE NR 2 CYINDER HEAD BROKEN IN THE AREA OF THE FOURTH AND FIFTH COOLING FINS. HEAD WAS COMPLETELY SEPARATED FROM THE BARREL AND WAS HELD IN PLACE ONLY BY THE ENGINE COOLING BAFFLES. 1L72 3O3 O 3A25 E8CE 20020313000382002031300038NE 2002 3 13 2002FA0000329 220020215G73103037088 LINE CESSNA500 560CESSNA 2076750CE PWA JT15 JT15D5 52112NE FUEL BYPASS LEAKING B PB8RK NONE K FLUID LOSS ININSP/MAINT 1 SO15999AD 5600136 LT ENGINE HAD A FUEL LEAK. FOUND FUEL BYPASS TUBE LEAKING. LEAK AT SOLDIER JOINT, CRACK OR OTHER DEFECT. INSTALLED NEW TUBE. 2L72 4F4 FRTA22CE E25EA 20020313000402002031300040CE 2002 3 13 2002FA0000331 120020207G1400 NUT CESSNA210 210D 2073414CE CONT O520 IO520* 17032SO ELT ANTENNA LOOSE B W1NRK NONE O OTHER ININSP/MAINT 1 SW11375HW157 21058251 THE ELT ANTENNA WAS FOUND TO BE LOOSE ON VISUAL INSPECTION. REMOVED ELT ANTENNA ASSEMBLY, FOR PROGRESSIVE INSPECTION. FOUND SHIELD LOCKING NUT SECURING METAL RADIATING ROD TO ANTENNA BASE ASSEMBLY WAS LOOSE. WHEN RADIATING ROD WAS REMOVED FROM ANTENNA BASE ASSEMBLY, THE FEMALE BNC BARREL CONNECTOR SOLDIER JOINT WAS BROKEN. THE SECURING OF THE 24 INCH RADIATING ROD IS ACCOMPLISHED ONLY BY MEANS OF AN INSULATING PLASTIC HOUSING AT THE ANTENNA BASE IN A COMPRESSION NUT. THE FEMALE BNC BARREL SHOULD HAVE BEEN CRIMPED. 1H71 3O3 O 3A21 E5CE 20020313000412002031300041CE 2002 3 13 2002FA0000332 120020207G3710442CW12 PUMP BEECH 58 58 1152740CE CONT O520 IO520* 17032SO VACUUM SYS INOPERATIVE B ODARO OTHER J WARNING INDICATION NRNOT REPORTED 1 EA2158WC TH766 PILOT EXPERIENCED DUAL VACUUM PUMP FAILURE IN FLIGHT IN VFR CONDITIONS. 1L72 3O3 O 3A16 E5CE 20020313000422002031300042CE 2002 3 13 2002FA0000333 120020207G3700442CW12 PUMP BEECH 58 58 1152740CE CONT O520 IO520* 17032SO VACUUM PUMP INOPERATIVE B ODARK NONE O OTHER ININSP/MAINT 1 EA2158WC TH766 PILOT EXPERIENCED DUAL VACUUM PUMP FAILURE IN FLIGHT IN VFR CONDITIONS. 1L72 3O3 O 3A16 E5CE 20020313000622002031300062SO 2002 3 13 2002FA0000334 120020110G2140A23D0475 SHUTOFF VALVE PIPER PA31 PA31350 7103110SO LYC O540 TIO540* 41532EA FUEL REGULATOR LEAKING B DQIRO OTHER J WARNING INDICATION NRNOT REPORTED 1 NM074089Y4 318152101 CREW REPORTED FUEL PRESSURE FOR RIGHT ENGINE WOULD DROP INTERMITTENTLY, THE HEATER FUEL SUPPLY COMES FROM FUEL FOR RIGHT ENGINE. TURNED HEATER ON, AND FUEL LEAKED FROM FUEL REGULATOR/SHUTOFF VALVE. THIS WAS A NEW VALVE THAT REPLACED A NEW VALVE PER THE REQUIREMENTS OF AD. 1L72 3O3 O A20SO E14EA 20020313000632002031300063NE 2002 3 13 B3OR20020005 220020202G7270310863201 DUCT CESSNA500 550 2076604CE PWA JT15 JT15D4 52112NE ENG BYPASS CRACKED B B3ORK NONE P NO WARNING INDICATION ININSP/MAINT 1 SW03264948237 1390 5500605 PCE71394 AIRCRAFT WAS INDUCTED INTO A PHASE1,2,5A & B INSPECTION.DURING THE INSPECTION OF THE NUMBER 2 ENGINE, THE FRONT BY-PASS DUCT WAS FOUND CRACKED AND A PIECE MISSING FROM IT. THE DUCT WAS REMOVED AND REPLACED WITH A SERVICEABLE DUCT. 1L72 4F4 F A22CE E1NE 20020313001182002031300118CE 2002 3 13 2002FA0000335 120020308G1420A60088 AMMETER CESSNA441 441 2076020CE GARRTTTPE331TPE33110 01514WP MCAULY4HFR344HFR34C660 NE INST PANEL BLEW OUT G H DEACTIVATE SYST/CIRCUITS P NO WARNING INDICATION CRCRUISE 1 WP17442HA960 4410243 N442HA A CESSNA 441 WAS DECENDING THROUGH APPROX. 12000 FT WHEN THE PROPELLER DE-ICE AMP METER EXPLODED SENDING BROKEN GLASS INTO THE PILOT FACE JUST MISSING HIS EYES. PRIOR TO THE FAILURE THE PILOT HAD SELECTED THE PROPELLER DE-ICE SYSTEM TO THE ON POSITION. TO CYCLE THE SYSTEM PRIOR TO LANDING. THE PILOT SHUT DOWN THE PROPELLER DE-ICE SYSTEM FOLLOWING THIS INCIDENT. THE CIRCUIT PROTECTOR DID NOT OPEN WITH THIS FAILURE. THE GAGE WAS REMOVED AND INSPECTED THE SHUNT LOCATED IN THE BACK OF THE GAGE HAD BURNED AND MELTED OPENING THE CIRCUIT. 1L72 3T4 TRTA28CE E4WE 5 C3PNE 20020313001192002031300119 2002 3 13 2002FA0000336 420020305G2330 CONNECTOR SOCATATBM TBM700 8682000EU PWA PT6 PT6* 52043EA WIRE HARNESS LOOSE B G1KRK NONE O OTHER ININSP/MAINT 1 SO11703QD 129 OPERATOR REPORTED INTERMITTENT DME AND HEADPHONE JACK PROBLEMS. UPON TROUBLESHOOTING, TECHNICIAN DISCOVERED 21 LOOSE CONNECTORS ON THE SYMBOL GENERATOR DUE TO BAD CRIMPING TECHNIQUES. WIRING WAS REPAIRED AND OPERATIONAL CHECKED OK. 1L71 3T3 TRTA60EU E2NE 20020313001202002031300120CE 2002 3 13 2002FA0000337 120020304G32409638003425 MASTER CYLINDER BEECH 33 F33A 1151425CE CONT O520 IO520BB 17032SO BRAKE SYS INOPERATIVE B VJ3RK NONE O OTHER ININSP/MAINT 1 WP078242T CE1610 820462R BRAKE MASTER CYLINDER WILL NOT HOLD PRESSURE, WHEN PRESSURE IS APPLIED TO THE BRAKE IT BLEEDS DOWN. REMOVED AND INSTALLED NEW MASTER CYLINDER, OPERATION CHECKED NORMAL. 1L71 3O3 O 3A15 E5CE 20020313001232002031300123NE 2002 3 13 ERAA077889 220020107G7230PT6T3B SEAL BELL 412 412 1182202SW PWA PT6T PT6T3B 52045NE COMPRESSOR LEAKING H ERAAO OTHER K FLUID LOSS NRNOT REPORTED 1 FS01412EH8992 33001 ENGINE HAS 2013.9 HRS SINCE OVERHAUL BY PRATT & WHITNEY. REMOVED FROM AIRCRAFT DUE TO HIGH OIL CONSUMPTION. USED 5QTS OF OIL IN 10.8 HRS; SUSPECTED COMP SEAL LEAK. RETURNING ON ERA REPAIR ORDER RW-887792 REQUESTING WARRANTY REPAIR DUE TO SUCH LOW TIME ON ENGINE. 1G72 4U4 U H4SW E22EA 20020314000022002031400002SO 2002 3 14 2002FA0000343 120020313G7910 SUMP PIPER PA46 PA46350P 7104602SO LYC O540 TIO540AE2A 41532EA ENGINE OIL CRACKED P K NONE O OTHER ININSP/MAINT 1 WP23137JT1300 4622151 L946761A OIL SUMP CRACKED AT TURBOCHARGER MOUNTING BRACKET ATTACHMENT POINT. 1L71 3O3 ORTA25SO E14EA 20020314000032002031400003NE 2002 3 14 2002FA0000341 220020226G7314025323150 PUMP CESSNA208 208B 2073701CE PWA PT6 PT6A114 52043NE FUEL SYSTEM SHEARED D A UNSCHED LANDING XJ ENGINE FLAMEOUT WARNING INDICATION NRNOT REPORTED 1 WP11121HA 208B0069 ENGINE FAILED IN FLIGHT DUE TO SHEARED FUEL PUMP DRIVE, AIRCRAFT LANDED SAFELY IN FARMERS FIELD. NO AIRCRAFT DAMAGE. SUGGEST MANDATORY DRIVE REPLACEMENT AT EACH OVERHAUL. 1H71 3T3 T A37CE E4EA 20020314000042002031400004SW 2002 3 14 2002FA0000342 120020219G32324196001C ACTUATOR MOONEYM20 M20E 5870212SW LYC O360 IO360A1A 41514EA MLG FAILED D O OTHER J WARNING INDICATION NRNOT REPORTED 1 WP1779830 494 AC MADE GEAR UP LANDING DUE TO FAILURE OF GEAR TO EXTEND EITHER ELEC OR MAN. FAILURE TO OPERATE ELEC WAS NOT DETERMINED BUT PROBABLY IN AC GEAR CONTROL SYS. FAILURE TO EXTEND WITH MAN SYS (EMERGENCY) WAS CAUSED BY A STRIPPED GEAR IN MAN DISENGAGE ASSY MOUNTED ON THE GEAR ACT. WHEN ENGAGEING MAN SYS A LEVER IS MOVED AT DISENGAGE UNIT TO SLIDE FEMALE SPLINED GEAR ONTO SPLINED MALE END OF EXTEN CABLE ALLOWING GEAR TO BE EXTENDED WITH HAND CRANK. ENGAGE LEVER IN CABIN OR LEVER ON DISENGAGE ASSY WAS LOOSE IT WOULD ALLOW FEMALE GEAR TO PARTIALLY ENGAGE CABLE AND DURING ELEC OP FEMALE GEAR WOULD GRIND AGAINST END OF EXTEN CABLE TO POINT THERE WOULDN`T BE ENOUGH TEETH LEFT FOR EMER SYS TO OP. 1L71 3O3 O 2A3 1E10 20020318001342002031800134NE 2002 3 18 HEEA078002 220020226G72000292005220 ENGINE SNIAS 350 AS350B 8680801EU TMECA ARRIELARRIEL1D NE DAMAGED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03855PH4813 3351 NO N1 INDICATION NOISE WHEN TURNING ENGINE. 1G71 3U3 U H9EU E19EU 20020319000632002031900063GL 2002 3 19 HEEA078019 220020311G723023056634 SPUR ADAPTER 23051643 SKRSKYS76 S76A 8143006NE ALLSN 250C 250C30S 03013GL COMPRESSOR FAILED E HEEAK NONE O OTHER ININSP/MAINT 1 SW033122G704 CAC90474 760232 CAE890279S COMPRESSOR WAS REMOVED WITH ENGINE DUE TO TURBINE NR 1 & 2 WHEEL CYCLES. DECISION MADE TO COMPLY WITH COMPRESSOR 2000 HOUR INSPECTION AND OVERHAUL FOR IHTI REQUIREMENTS. SPUR GEAR FAILED NO-GO GAUGE CHECK. SUBMITTAL FOR CREDIT ACCOMPLISHED ON AFA 63885A. 1G72 3U3 U H1NE E1GL 20020320000012002032000001GL 2002 3 20 HEEA078070 220020226G7320412074101101 TRANSDUCER BELL 407 407 1182206SW ALLSN 250C 250C47B GL ENGINE FAILED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03510PH 53209 TRANSDUCER CAUSES ENGINE DECELERATION ON TAKE OFF. 1G71 3U3 UO H2SW E1GL 20020426001202002042600120NE 2002 4 26 CA020221017 220020210G7200RB211524B4 ENGINE LKHEED1011 10113853 5265020WP RROYCERB211 RB211524B40254555NE NR 1 OVERHEATED W F ACTIVATE FIRE EXT. MJ OVER TEMP WARNING INDICATION TXTAXI/GRND HDL 1 CA 14838 (CAN) 2 MINUTES AFTER LANDING , AFTER THRUST REVERSER STOWING , THE FIRST OFFICER CALLED OUT HIGH TGT RAISING RAPIDALY AND ENGINE RUN DOWN , TEMPERATURE ROSE TO 850 DEGREES ON NR 1 ENGINE. THE TAIL PIPE FIRE DRILL WAS CARRIED OUT. MAINTENANCE CARRIED OUT AN HP TURBINE BOROSCOPE IAW MM, NO FAULTS FOUND. THE DFDR WAS REPLACED. THE ENGINE WAS REPLACED FOR COMPANY CONVENIENCE. 2L73 4F4 F A23WE E12EU 20020426001232002042600123NE 2002 4 26 CA020221018 220020202G7230RB21122B02 FAN BLADE LKHEED1011 10113851 5265010WP RROYCERB211 RB21122B02 54555NE NR 2 ENGINE DAMAGED W E ENGINE SHUTDOWN FEJFLT CONT AFFECTED VIBRATION/BUFFET WARNING INDICATION CLCLIMB 1 CA (CAN) SHORTLY AFTER TAKEOFF NR 2 ENGINE N1 INDICATION SHOWED 10 PERCENT HIGHER THAN NR 1 AND 3 ENGINES. ALL PARAMETERS WERE THE SAME. WHEN THRUST WAS REDUCED TO LOWER N1 SETTING, NR 2 ENGINE HIGH VIBRATION WAS CONFIRMED ON BOTH CHANNELS AT 2.5 UNITS (VIB. LIGHT ON). ENGINE NR 2 WAS SHUT DOWN PER QRH. AFTER INSPECTION , MAINTENANCE FOUND ICE ACCUMULATION STUCK IN THE DUCT AND MANY LP FAN BLADE TIPS WERE BENT. ALL LP FAN BLADES WERE REPLACED. 2L73 4F4 F A23WE E12EU 20020426001562002042600156NM 2002 4 26 CA020222001 120020214G7830LJ76673 ACCESS PANEL LJ75010 BOEING757 75728A 1384976NM RROYCERB211 RB211535E43754555NE THRUST REVERSER MISSING W O OTHER D INFLIGHT SEPARATION TXTAXI/GRND HDL 1 CA 0044 (CAN) WHEN AIRCRAFT LANDED CREW SELECTED REVERSERS, THE NR 2 ENGINE, RT THRUST REVERSER WOULD NOT STOW. DURING THE WALK AROUND, THE CREW FOUND THE NR 2 ENGINE THRUST REVERSER DUCT ACCESS PANEL (P/N LJ76673) RIPPED OFF AND DAMAGE TO THE THE RT TRANSLATING COWL (P/N 75010 ; S/N 0044). THE NR 2 ENGINE THRUST REVERSER FORWARD LATCH ACCESS PANEL HAD A TEMPORARY REPAIR CARRIED OUT I.A.W. ROLLS-ROYCE REPAIR PROJECT-PRODUCT. THE AIRCRAFT RELEASED. 2L72 4F4 FRTA2NM E12EU 20020321000232002032100023CE 2002 3 21 CA020226002 120020226G7800175400125 MUFFLER CESSNA 175400125 CESSNA172 172M 2072418CE LYC O320 O320E2D 41508EA MCAULY1C160 1C160DTM GL ON ENGINE CRACKED W O OTHER O OTHER ININSP/MAINT 1 CA NONE (CAN) FOUND DURING AD CF90-03R2 MUFFLER INSPECTION. CRACK FOUND AT BASE OF TAIL PIPE TO MUFFLER CAN CONNECTION. (ALONG WELD BEAD.)MUFFLER REPLACED IN ACCORDANCE ADCF90-03R2. PART 1 SUB PART 5. 1H71 3O3 ONT3A12 E274 5 NP910 20020321000242002032100024EA 2002 3 21 CA020228008 120020214G5610NP1393225 WINDOW CNDAIR CL6002B19 CNDAIRCL600 CL6002B19 1900309EA GE CF34 CF343A1 30015NE CAPTAIN SIDE CRACKED W O OTHER O OTHER ININSP/MAINT 1 CA 7082 (CAN) DURING FLIGHT L-2 WINDOW DEVELOPED A CRACK. CAPTAINS SIDE WINDOW REPLACED AS PER AIRCRAFT MAINTENANCE MANUAL 56-12-01. 2L72 4F4 FRTA21EA E15NE 20020321000252002032100025EA 2002 3 21 CA020228009 120020204G27603G5209C SPOILER CNDAIRCL600 CL6002B19 1900309EA GE CF34 CF343A1 30015NE L/H OUTBOARD FAILED W O OTHER O OTHER ININSP/MAINT 1 CA (CAN) SPOILER FAULT EICAS INDICATES LEFT OUTBOARD SPOILER PROBLEM (WHITE BOX).SEVERAL PREVIOUS SNAGS OCCURRED WITH SYSTEM CHECKED OUT AND NO FAULTS FOUND (INTERMITTENT FAULT). WIRING CHECKED OUT NO FAULT FOUND.FLIGHT SPOILER CONTROL LEVER HANDLE REPLACED. 2L72 4F4 FRTA21EA E15NE 20020416000072002041600007EA 2002 4 16 CA020228015 120020228G5610NP13932110 WINDSHIELD CNDAIRCL600 CL6002B19 1900309EA GE CF34 CF343B1 NE COCKPIT CRACKED W A UNSCHED LANDING O OTHER CRCRUISE 1 CA 13551 (CAN) THE WINDSHIELD INSTALLED WAS A POST SERVICE BULLETIN WINDSHIELD. RT WINDSHIELD CORE PLY CRACKED IN CRUISE AT FL 350. FLIGHT DIVERTEDREMOVED AND REPLACED WINSHIELD. AIRCRAFT RETURNED TO SERVICE. 2L72 4F4 FRTA21EA E15NE 20020321000262002032100026SW 2002 3 21 CA020306005 120020305G6220204011143005 BARREL BELL 204011140005BELL 205 205A1 1181414SW LYC T53 T5317A 41549NE INTERIOR CRACKED W K NONE O OTHER ININSP/MAINT 1 CA A13534 (CAN) NDT REVEALED A 1.5 INCH CRACK ON THE INTERIOR OF THE COARSE THREADED END. THE CRACK IS NOT VISIBLE ON THE EXTERIOR. 1G71 4U4 U H1SW E17EA 20020321000902002032100090CE 2002 3 21 CA020130008 120020119G534712139902 BRACKET BEECH 1900 1900D 1154162CE PWA PT6 PT6A67D NE HARTZLHCE4A HCE4A3I NE SEAT CRACKED W K NONE O OTHER ININSP/MAINT 1 CA 13347 (CAN) DURING THIRD INSPECTION WE FOUND NINE SEAT BRACKET CRACKED. THE CRACK WAS GENERATED FROM THE REAR THRU THE HOLE ADJACENT TO THE BEND.AFTER FLEET INVESTIGATION WE FOUND 33 BRACKET CRACKED. 2L72 4T4 TRTA24CE E26NE 5 CP10NE 20020321000912002032100091CE 2002 3 21 CA020130009 120020114G33409003312 LIGHT BEECH 1900 1900D 1154162CE PWA PT6 PT6A67D NE HARTZLHCE4A HCE4A3I NE STROBE FAILED W K NONE L NO TEST ININSP/MAINT 1 CA (CAN) AFTER SELECTING THE BEACON SWITCH TO ON, FOUND THAT THE TAIL BEACON LIGHT WAS NOT FLASHING. THE LIGHT WAS REPLACED. 2L72 4T4 TRTA24CE E26NE 5 CP10NE 20020321000932002032100093NM 2002 3 21 CA020131009 120020114G552385520271003 STOP DHAV DHC8 DHC8* NM PWA PW120 PW123 NE HAMSTD14SF 14SF23 NE ELEVATOR DETERIORATED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) DURING CREW WALKAROUND, THEY NOTICED DAMAGE TO LT TRAILING EDGE OF THE ELEVATOR SPRING TAB. THE DAMAGE TO THE TAB WAS INBOARD, ADJACENT TO THE RUDDER. THE TRAILING RUDDER WAS ALSO DAMAGED FROM CONTACT WITH ELEVATOR SPRING TAB. THE LT ELEVATOR SPRING TAB REPLACED. RD 8-55-1214 ISSUED FOR 200 HOURS ALLOWANCE FOR DAMAGE TO LT SIDE OF THE TRAILING RUDDER. THE ELEVATOR BUMPER STOP WAS REPLACED, AS IT WAS DETERIORATED. 2H72 4T4 TRTA13NM E20NE 6 CP7NE 20020321000972002032100097NM 2002 3 21 CA020201007 120020121G3260854144465101 BRACKET DHAV DHC8 DHC8* NM PWC 150 PW150A EA MLG FAILED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) IT WAS NOTICED DURING ROUTINE MAINTENANCE THAT THE LT UPLOCK ACTUATOR SUPPORT BRACKETS WERE MISSING THE ATTACH HI-LITES (QTY 6) THRU AFT FRAME (THIS HAS INITIATED A FLEET WIDE INSPECTION AS DIRECTED BY DASH-8-400 AOM 050) AC SN 4033 HAS SUFFERED A STRUCTURAL DAMAGE DUE TO MISSING FASTENERS IN AFT END OF THE BRACKETS FOR THE LT MAIN LANDING GEAR. UPLOCK. MAINTENANCE WILL CHANGE THE ENTIRE SHEAR DIAPHRAGM , THE SUPPORT BRACKET DOUBLER , SUPPORT BRACKET SHIM , ATTACHMENT CLEATS AND REMOVE AND REPLACE BOTH UPLOCK BRACKETS. 2H72 4T4 TRTA13NM E00062EN 20020321000982002032100098NM 2002 3 21 CA020201008 120020124G3320404820 SOCKET DHAV DHC8 DHC8* NM PWC 150 PW150A EA LIGHTS OVERHEATED W O OTHER B SMOKE/FUMES/ODORS/SPARKS DEDESCENT 1 CA (CAN) BURNING SMELL FROM TOILET OBSERVED BY CABIN CREW. RIGHTHAND GENERATOR SWITCHED OFF. EMERGENCY DECLARED. AIRCRAFT LANDED SAFELY AND PASSENGERS DISEMBARKED ON RUNWAY AND TAKEN BY BUS TO TERMINAL. TOILET AND PANELS CHECKED BY FIREFIGHTERS. NO TRACE OF FIRE FOUND. AIRCRAFT TOWED TO GATE AND PASSENGERS BRIEFED BY COMMANDER.INVESTIGATION OF THE AIRCRAFT SHOWED A BURNED AND MELTED HOLDER FOR THE FLUORESCENT TUBE IN THE LAVATORY THAT HAD CAUSED THE SMOKE/SMELL. 2H72 4T4 TRTA13NM E00062EN 20020321001022002032100102NE 2002 3 21 CA020201013 220020122G73149234A8 PUMP AMD FALCONFALCON20 2730103EU GE CF700 CF7002D2 30010NE FUEL SYSTEM LEAKING W K NONE K FLUID LOSS ININSP/MAINT 1 CA (CAN) AFTER COMPLETION OF UNLOADING FREIGHT, OUR AIRCRAFT WAS REPOSITIONING TO THE MAINTENANCE FACILITY AT FBO. DURING ENGINE SHUTDOWN, AN ENGINEER FROM OUR CONTRACTED AMO NOTICED FUEL LEAKING FROM THE RIGHT ENGINE LOWER COWLING. IN ORDER TO STOP THE FUEL FROM LEAKING, THE RIGHT ENGINE EMERGENCY SHUT DOWN LEVER WAS PULLED.AFTER VISUAL INSPECTION, A SMALL HOLE ON THE FCU BOOST PUMP CASTING WAS OBSERVED.THE SMALL HOLE SEEMS TO ORIGINATE FROM A DEFECT IN THE CASTING. 2L72 4F4 FRTA7EU E7EA 20020322000012002032200001EU 2002 3 22 CA020207001 120020120G3520C24091 SQUAT SWITCH AMD FALC10FALCON10 2730101EU GARRTTTFE731TFE73121C NE LT MLG CONTAMINATED W O OTHER O OTHER CLCLIMB 1 CA (CAN) LOSS OF PRESSURIZATION AFTER TAKEOFF. RECTIFICATION: MOISTURE WAS FOUND ON THE LT LANDING GEAR SQUAT SWITCH 9G1. SUSPECT SQUAT SWITCH 9G1 WAS COLD SOAKED, CLEANED AND LUBED. PASSENGER OXYGEN MASK HAD NO OXYGEN FLOW. SYSTEM IS OPERATING IAW F10 M.M. WHICH STATES THAT THERE IS NO OXYGEN FLOW BELOW 15,000 FT. AIRCRAFT SYSTEM GROUND CHECKED SERVICEABLE. 2L72 4F4 F A33EU E6WE 20020322000022002032200002EA 2002 3 22 CA020207003 120020118G3241 BRAKE CNDAIRCL601 CL6012A12 1900303EA GE CF34 CF341A NE ANIT SKID MALFUNCTIONED W D RETURN TO BLOCK L NO TEST TXTAXI/GRND HDL 1 CA (CAN) DURING TAXI- ANTI-SKID TEST FAILURE - WIRES BG15B20BLU & GB30B20WHT - SUSPECT CYCLIC FAILURE. 2L72 4F4 FRTA21AE E15NE 20020322000042002032200004 2002 3 22 CA020208002 420020208G3422 VANE SIGMATEK 235010616 CESSNA172 172M 2072418CE LYC O320 O320E2D 41508EA MCAULY1C160 1C160DTM GL GYRO STUCK W K NONE O OTHER ININSP/MAINT 1 CA T53207J (CAN) COPPER VANE RUBS AGAINST POT ALUMINUM GYRO CASE CREATING BLACK RESIDUE CAUSING VANE TO STICK. THIS CAUSES HORIZION TO DIPLAY A PITCH OR ROLL WHEN LEVEL. 1H71 3O3 ONT3A12 E274 5 NP910 20020322000052002032200005CE 2002 3 22 CA020208005 120020206G2497 WIRE BEECH 1900 1900D 1154162CE PWA PT6 PT6A67D NE HARTZLHCE4A HCE4A3I NE FUSELAGE SHORTED W K NONE N FALSE WARNING ININSP/MAINT 1 CA (CAN) DURING PREFLIGHT CHECKS, CREW NOTICED FALSE FIRE WARNING, FUEL SHUTOFF VALVE ACTUATION, ALTHOUGHT VALVE ACTUATION WAS AUDIBLE. AIRCRAFT WAS FERRIED TO MAINTENANCE FACILITY FOR REPAIRS. WIRING SUSPECTED AS CAUSE OF FALSE INDICATIONS HOWEVERE MEG OF WIRING REVEALED NO SHORTS. PRIMARY WIRES WERE TO BE REPLACED BUT DURING PROCESS, A CHAFFED WIRE WAS DISCOVERED UNDER THE FORWARD CLOSET AREA, BEHIND THE TCAS RX / TX. OCCASIONALLY, THE WIRE WAS MAKING CONTACT WITH A KNURLED FITTING RELATING TO THE TCAS. THE WIRE WAS REPAIRED AND THE AREA PROTECTED FROM ADDITIONAL CHAFFING. AIRCRAFT RETURNED TO SERVICE. 2L72 4T4 TRTA24CE E26NE 5 CP10NE 20020322000062002032200006NM 2002 3 22 CA020211001 120020210G542085310380 BEAM DHAV DHC8 DHC8301 NM PWA PW120 PW123 NE HAMSTD14SF 14SF15 NE NLG WW CRACKED W K NONE O OTHER ININSP/MAINT 1 CA 27861 (CAN) NLG WHEEL WELL BOX STRUCTURE WAS FOUND CRACKED WHILE DOING TASK 5310/27D (DETAILED VISUAL INSPECTION).DAMAGE WAS REPAIRED IN ACCORDANCE TO REPAIR DRAWING RD 8-53-2376 2H72 4T4 TRTA13NM E20NE 6 CP7NE 20020322000082002032200008EA 2002 3 22 CA020211016 120020211G3222C3UF1085 STRUT DHAV DHC3 DHC3 2800202EA PWA R1340 S3H1G 52016NE FLOAT CRACKED W K NONE O OTHER ININSP/MAINT 1 CA 18089 (CAN) FLOAT STRUTS REMOVED TO PERFORM ANNUAL INSPECTION AS PER DEHAVILLAND SERVICE BULLETIN 3/30. SIX INCH LONG CRACK FOUND VISUALLY THROUGHOUT CENTER OF THE BASE OF THE STRUT CASTING. 1H71 3R3 R A815 E142 20020322000092002032200009EU 2002 3 22 CA020212001 120020212G5210NOGIVEN ATTACH FITTING PILATSPC12 PC1245 7090551EU PWA PT6 PT6A67B 52043NE HARTZLHCE4A HCE4A3D GL CABIN DOOR LOOSE W K NONE O OTHER ININSP/MAINT 1 CA (CAN) ATTACHMENT BRACKET FOR CABIN DOOR COUNTER BALANCE SYSTEM FOUND WITH LOOSE RIVETS. RIVETS REMOVED AND REPLACED WITH CR3243-4 BLIND RIVETS. 1L71 3T4 TRTA78EU E26NE 5 CP210NE 20020322000102002032200010NE 2002 3 22 CA020213001 220020211G72107826511 BRACKET DHAV DHC8 DHC8301 NM PWA PW120 PW123 NE HAMSTD14SF 14SF15 NE REDUCTION G/B CRACKED W K NONE O OTHER ININSP/MAINT 1 CA 22926 (CAN) WHILE REMOVING THE ENGINE ACCESSORIES IN THE SHOP,AFTER AN ENGINE CHANGE, IT WAS DISCOVERED THAT THE PROPELLER DE-ICE BRUSH BLOCK MOUNTING BRACKET WAS CRACKED AROUND BOTH MOUNTING BOLT HOLES. THIS WOULD EVENTUALLY LEAD TO A COMPLETE FAILURE OF THE BRACKET AND THEREFORE PROPELLER DAMAGE AND LOSS OF DE-ICE CAPABILITY. THE BRACKET WAS REPLACED WITH A NEW UNIT. 2H72 4T4 TRTA13NM E20NE 6 CP7NE 20020322000112002032200011CE 2002 3 22 CA020213006 120020201G2435 BEARING LEAR 45 45LEAR 5170805CE GARRTTTFE731TFE7312 01518WP STARTER GEN FAILED W A UNSCHED LANDING EJ VIBRATION/BUFFET WARNING INDICATION CRCRUISE 1 CA (CAN) ON A TRIP FROM HOUSTON TO CALGARY, VIBRATION OCCURRED IN AIRCRAFT, RT GENERATOR FAILED, THE AIRCRAFT DIVERTED TO WICHITA WHERE THE RT STARTER/GENERATOR WAS REPLACED. AIRCRAFT AND COMPONENT TIME 871.0 HOURS, 454 CYCLES. 2L72 4F4 FRTT00008WIE6WE 20020322000122002032200012CE 2002 3 22 CA020213007 120020213G272003101965 SPRING CESSNA172 172M 2072418CE LYC O320 O320E2D 41508EA MCAULY1C160 1C160DTM GL RUDDER CONTROL BROKEN W K NONE O OTHER ININSP/MAINT 1 CA (CAN) RUDDER WAS ANGLED TO ONE SIDE UPON FURTHER INSPECTION FOUND THAT IT WOULD NOT RETURN TO NEUTRAL.RUDDER SPRING WAS FOUND HANGING IN POSITION DETACHED FROM ONE SIDE, THE END HAD BROKEN OFF. PART WAS REPALCED AND AIRCRAFT WAS RETURNED TO SERVICE. 1H71 3O3 ONT3A12 E274 5 NP910 20020322000132002032200013EA 2002 3 22 CA020215001 120020211G2612 WIRE HARNESS CNDAIRCL604 CL604 1900301EA GE CF34 CF343B1 NE FIRE DETECTION CHAFED W C ABORTED TAKEOFF EY VIBRATION/BUFFET ENGINE STOPPAGE TOTAKEOFF 1 CA (CAN) DURING TAKE-OFF ROLL, THE POWER SET TO TAKE OFF N1, THE SPEED WERE JUST CALLED ALIVE, WHEN THE LEFT ENGINE ROLLED BACK TO IDLE. THE AIRCRAFT WAS TAXIED CLEAR AND WHILE TAXIING BACK TO FBO LEFT ENGINE SHUT DOWN. THE CAS MESSAGE INDICATED HYD SOV 1 AND ENGINE FUEL SOV CLOSED WITH OUT SELECTION. TROUBLESHOOTING REVEALED WIRE BUNDLE LOCATED BEHIND NR 2 EFIS TUBE CHAFING ON THE EFIS CONNECTOR. THE LEFT ENGINE FIRE PUSH BUTTON WIRE MADE CONTACT WITH A LIVEWIRE AND ACTIVATED A FIRE PUSH SELECTION. FOUR WIRES REPAIRED AND WIRE BUNDLE SECURED AS REQUIRED. 2L72 4F4 FRTA21EA E15NE 20020322000142002032200014EU 2002 3 22 CA020215016 120020214G32309740926112 RELAY PILATSPC12 PC1245 7090551EU PWA PT6 PT6A67B 52043NE HARTZLHCE4A HCE4A3D GL LANDING GEAR INTERMITTENT W O OTHER J WARNING INDICATION NRNOT REPORTED 1 CA (CAN) LANDING GEAR WOULD NOT EXTEND. PILOT HAD TO USE EMERGENCY EXTENSION. MAINTENANCE FOUND THE POWER PACK RELAY WAS ACTUATING YET NO POWER WOULD GO THROUGH.RELAY WAS REPLACED AND AIRCRAFT RETURNED OT SERVICE. 1L71 3T4 TRTA78EU E26NE 5 CP210NE 20020426000742002042600074EU 2002 4 26 CA020218002 120020214G27809450202201 SHAFT PILATSPC12 PC1245 7090551EU PWA PT6 PT6A67B 52043NE HARTZLHCE4A HCE4A3D GL LT LE FLAP BROKEN W O OTHER J WARNING INDICATION LDLANDING 1 CA (CAN) WHILE ON APPROACH, PILOT REPORTED THAT WHEN HE SELECTED 30 DEGS OF FLAP HE GOT FLAP WARNING ON CAWS PANEL. NO EFFECT ON FLT CONTROLS AND HE LANDED WITH OUT INCIDENT. PILOT RESET FLAPS ON GROUND AND TRIED TO RETRACT FLAPS. FLAPS WOULD NOT RETRACT AND FLAP WARNING ON CAWS PANEL CAME ON. PILOT COULD NOT GET FLAPS TO RESET. MAINTENANCE DISPATCHED FROM PRINCE ALBERT BASE. FLAPS WERE CHECKED FOR ASSEMETARY. IT FOUND THAT LT FLAP 1/2 INCH LOWER THAN RIGHT FLAP. WHEN LEFT INBOARD FLEX SHAFT DISCONNECTED FROM POWER DRIVE UNIT, FLEX SHAFT HAD SHEARED AT SWAGED END THAT GOES INTO POWER DRIVE UNIT. 1L71 3T4 TRTA78EU E26NE 5 CP210NE 20020322000152002032200015NM 2002 3 22 CA020219002 120020215G32321U1085 SEQUENCE VALVE BOEING727 727227 1384078NM PWA JT8 JT8D* NE LT MLG CRACKED W D RETURN TO BLOCK KJ FLUID LOSS WARNING INDICATION TXTAXI/GRND HDL 1 CA (CAN) ON ENGINE START UP FOR DEPARTURE, CREW NOTICED QUANTITY OF "A" SYSTEM HYDRAULICS DROPPING .ENGINE SHUT DOWN MAINTENANCE FOUND LT MLG DOOR LOCK SEQUENCE VALVE HOUSING WAS CRACKED AND LEAKING FLUID.MAINTENANCE REPLACED THE VALVE, A/C WAS POSITIONED GEAR DOWN TO A MAINTENANCE FACILITY FOR A GEAR SWING,WHICH WAS CARRIED OUT AND THE A/C WAS RETURNED TO SERVICE. 2L73 4F4 F A3WE E2EA 20020325000022002032500002NM 2002 3 25 CA020220014 120020219G331018271 POWER SUPPLY DHAV DHC8 DHC8102 2809003NM PWA 120 PW120A NE HAMSTD14SF 14SF7 NE INSTRUMENT PANELFAILED W A UNSCHED LANDING B SMOKE/FUMES/ODORS/SPARKS CLCLIMB 1 CA 30945 (CAN) THE FLIGHT CREW DETECTED A STRONG BURNING ODOUR SHORTLY AFTER TAKE OFF FROM YTZ - MUCH LIKE "A BURNING CIRCUIT BOARD". THE AIRCRAFT DIVERTED INTO YYZ FOR LANDING. MAINTENANCE INSPECTED THE AIRCRAFT AND FOUND THE 5 VOLT POWER SUPPLY FOR THE CAPTAIN'S INSTRUMENT PANEL LIGHTING WAS BURNING. THE POWER SUPPLY WAS REMOVED AND REPLACED. 2H72 4T4 TRTA13NM E20NE 6 CP7NE 20020325000032002032500003EA 2002 3 25 CA020221002 120020221G5711S66422024T8511 SPAR CAP CNDAIRCL215 CL2151A10 1900320EA PWA R2800 CA3 52026NE HAMSTD43E 43E60 NE WING CRACKED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) CRACK WAS DICOVERED WHILE PERFORMING NDT IN ACCORDANCE WITH AIRWORTHINESS DIRECTIVE CF93-07. WHILE CARRYING OUT REPAIR, ADDITIONAL CRACKING WAS FOUND IN AREA OUTSIDE OF THE INSPECTION PARAMETERS OF AD CF93-07 AT RBL 53 AND RBL 58. 2H72 4R4 RRTA14EA E231 6 CP871 20020325000042002032500004NM 2002 3 25 CA020221009 120020201G2170 CLAMP BOEING757 75728A 1384976NM RROYCERB211 RB211535E43754555NE PRECOOLER LOOSE W O OTHER O OTHER CLCLIMB 1 CA (CAN) WHEN REACHING FL330 , THE CABIN ALTITUDE LIGHT CAME NI AND THE RT PACK INOP LIGHT CAME N. WE STARTED DESCENT, THE CABIN STABILIZED AT FL 250. THE RT PACK WAS RESETTED AND FOUND OK. THE CREW STAYED AT THAT LEVEL FOR THE REMAINDER OF THE FLIGHT . MAINTENANCE FOUND A COUPLING /CLAMP ON THE PRECOOLER LINE LOOSE THE COUPLING / CLAMP WAS RESECURED & LEAK CHECKED SERVICEABLE. 2L72 4F4 FRTA2NM E12EU 20020325000052002032500005EA 2002 3 25 CA020225003 220020211G7200PT6A34 ENGINE DHAV DHC6 DHC6300 2802606EA PWA PT6 PT6A34 52043EA NACELLE DETERIORATED W K NONE W INADEQUATE Q C ININSP/MAINT 1 CA 12395 (CAN) - DETERIORATION INTERNALLY- COATING DETERIORATED ON SMALL EXIT DUCT WHICH CAUSED DAMAGE TO TURBINE BLADES.- CORROSION THROUGHOUT ENGINE (UNEXPLAINABLE) INSIDE AND OUT - WHITE POWDER. 1H72 3T4 TRTA9EA E4EA 20020325000062002032500006 2002 3 25 CA020226003 420020213G31609788132012 DISPLAY PILATSPC12 PC1245 7090551EU PWA PT6 PT6A67B 52043NE HARTZLHCE4A HCE4A3D GL CAWS FAILED W E ENGINE SHUTDOWN H ELECT. POWER LOSS-50 PC TXTAXI/GRND HDL 1 CA (CAN) - POWER FAILURE IN CAWS DISPLAY UPON START UP.- DISPLAY & CONTROL UNIT REMOVED DIRECTED FOR BENCH CHECK.- REPLACED DISPLAY & CONTROL UNIT, NORMAL OPERATION RESULTS. 1L71 3T4 TRTA78EU E26NE 5 CP210NE 20020325000072002032500007CE 2002 3 25 CA020226008 120020220G2823NAS561P36 ROLL PIN CESSNA 12161061 CESSNA206 U206F 2073333CE CONT O520 IO520F 17032SO YOKE SHEARED W A UNSCHED LANDING O OTHER CRCRUISE 1 CA (CAN) FUEL SELECTOR WOULD NOT ROTATE VALVE. DISASSEMBLED AND FOUND PIN SECTION MISSING ALLOWING HOUSING YOKE TO ROTATE ON SHAFT. PIN REPLACED. 1H71 3O3 O A4CE E5CE 20020325000082002032500008EA 2002 3 25 CA020226009 120020213G56106003303026 WINDSHIELD CNDAIRCL604 CL604 1900301EA GE CF34 CF343B1 NE COCKPIT FAILED W O OTHER D INFLIGHT SEPARATION CRCRUISE 1 CA (CAN) ENROUTE TO KINGSTON, JAMAICA, FROM TORONTO, A CRACK OCCURRED IN THE FACEPLY OF THE CO-PILOT'S WINDSCREEN. ON DESCENT INTO KINGSTON, THE PLY BEGAN TO DELAMINATE. APPROXIMATELY 2/3'S OF THE FACE PLY DEPARTED THE AIRCRAFT PRIOR TO TOUCHDOWN IN JAMAICA. 2L72 4F4 FRTA21EA E15NE 20020325000092002032500009NM 2002 3 25 CA020226011 120020223G291082970009129 LINE DHAV DHC8 DHC8102 2809003NM PWA 120 PW120A NE HAMSTD14SF 14SF7 NE HYD SYSTEM LEAKING W K NONE K FLUID LOSS ININSP/MAINT 1 CA 31242 (CAN) UPON A WALK AROUND INSPECTION, MAINTENANCE NOTICED A LARGE AMOUNT OF FLUID DRIPPING FROM THE LEFT NACELLE. THE LEFT MAIN LANDING GEAR DOORS MECHANICAL SEQUENCE VALVE "DOWN" PRESSURE LINE WAS FOUND LEAKING. THE LINE WAS REPLACED AND THE SYSTEM LEAK CHECKED AND SERVICED PRIOR TO RETURNING THE AIRCRAFT TO SERVICE 2H72 4T4 TRTA13NM E20NE 6 CP7NE 20020325000102002032500010NM 2002 3 25 CA020226012 120020222G291082950010269 LINE DHAV DHC8 DHC8102 2809003NM PWA 120 PW120A NE HAMSTD14SF 14SF7 NE HYD SYSTEM LEAKING W K NONE K FLUID LOSS ININSP/MAINT 1 CA 28282 (CAN) THE FLIGHT CREW REPORTED A HYDRAULIC FLUID LEAK FROM THE RT NACELLE AND NR 4 FLAP TRACK AREA.MAINTENANCE FOUND THE NR 1 HYDRAULIC SYSTEM "DUMP" LINE FOR THE RT INBOARD SPOILER LEAKING. THE LINE WAS REPLACED AND THE SYSTEM LEAK CHECKED AND FUNCTION CHECKED PRIOR TO RETURNING THE AIRCRAFT TO SERVICE. 2H72 4T4 TRTA13NM E20NE 6 CP7NE 20020325000112002032500011NM 2002 3 25 CA020226013 120020225G2497242110037C12A1 WIRE DHAV DHC8 DHC8102 2809003NM PWA 120 PW120A NE HAMSTD14SF 14SF7 NE FUSELAGE BURNED W O OTHER B SMOKE/FUMES/ODORS/SPARKS CRCRUISE 1 CA 35067 (CAN) FLIGHT CREW REPORTED THAT THE LEFT INTAKE HEATER ADAPTER WAS INTERMITTANT AND LEFT AC "A" PHASE VOLTAGE SHOWED 64-80 VOLTS. AFTER MANY COMPONENTS WERE REPLACED FOR TROUBLESHOOTING, BURNED WIRING WAS FOUND BENEATH THE ENTRANCE FLOOR (WIRING TROUGH) FOR THE AC SYSTEM. THE WIRING WAS REPAIRED IN ACCORDANCE TO SYD 8-24-005. NOTE: AD CF 98-08R2 ADDRESSES SIMILAR PROBLEMS BUT DOES NOTAFFECT THIS AREA OF THE TROUGH!THIS WIRING WAS CHAFED AGAINST THE TROUGH WHICH OVERHEATED AND BURNT THROUGH "A" PHASE. "B" AND "C" PHASE WIRING WAS ALSO DAMAGED BUT NOT A BAD AS "A" PHASE. 2H72 4T4 TRTA13NM E20NE 6 CP7NE 20020325000122002032500012EU 2002 3 25 CA020226016 120020222G52445711012367 ATTACH FITTING PILATSPC12 PC1245 7090551EU PWA PT6 PT6A67B 52043NE HARTZLHCE4A HCE4A3D GL OIL COOLER DOOR CRACKED W O OTHER J WARNING INDICATION CRCRUISE 1 CA (CAN) AIRCRAFT WAS IN ROUTE TO HOME BASE AND 20 MINUTES INTO ITS FLIGHT WNEN THE OIL TEMPERATURE DROPPED FROM 60 C TO 40 C AND THE OIL PRESSURE WENT UP THE BOTTOM OF THE RED LINE WHICH IS 130 PSI.THE PROBLEM WAS THE OIL COOLER DOOR HINGE HOLDER CRACKED AND ALLOWED THE DOOR TO BE INEFFECTIVE IN CONTROLLING THE TEMPERATURE OF THE OIL. 1L71 3T4 TRTA78EU E26NE 5 CP210NE 20020325000132002032500013WP 2002 3 25 CA020227001 220020219G7322307080022 FUEL CONTROL LEAR 35 35A 5170602CE GARRTTTFE731TFE73122B 01518WP LT ENGINE DEFECTIVE W E ENGINE SHUTDOWN M OVER TEMP TXTAXI/GRND HDL 1 CA (CAN) LT ENGINE HOT START ON MANUAL AND COMPUTER MODE. LT FCU REPLACED, GROUND RUNS C/O, GROUD CHECK SERVICEABLE. 2L72 4F4 F A10CE E6WE 20020325000142002032500014EU 2002 3 25 CA020227004 120020226G32429462061335 SWIVEL PILATSPC12 PC1245 7090551EU PWA PT6 PT6A67B 52043NE HARTZLHCE4A HCE4A3D GL MLG BRAKE SYS LEAKING W K NONE K FLUID LOSS ININSP/MAINT 1 CA (CAN) HYD BRAKE FLUID WAS NOTED LEAKING FROM THE SWIVEL FITTING ON THE BRAKE LINE ,LT MLG TRAILING LINK AREA. PART REPLACED WITH NEW, BRAKES BLED, RETURNED TO SERVICE. 1L71 3T4 TRTA78EU E26NE 5 CP210NE 20020325000162002032500016NM 2002 3 25 CA020227010 120020226G3230 LATCH BOEING727 727221 1384071NM PWA JT8 JT8D17 52049NE MLG FAILED W O OTHER O OTHER CLCLIMB 1 CA (CAN) DURING GEAR RETRACTION LEVER LATCH FAILED TO RELEASE ALL OTHER INDICATIONS NORMAL.REPAIRED WIRING AT LEVER LOCK SOLENOID BY REPLACING TERMINAL CONNECTOR LEVER LOCK SYSTEMM OPS TESTED AS PER MM 32-31-11. NO FURTHER DISCREPANCY. 2L73 4F4 F A3WE E2EA 20020325000172002032500017SO 2002 3 25 CA020227011 120020222G2510ASABOVE FRAME PIPER PA28 PA28R200 7102811SO LYC O360 IO360C1C 41514EA SEAT CRACKED W K NONE W INADEQUATE Q C ININSP/MAINT 1 CA (CAN) BOTH LT AND RT UPPER FORWARD WELD JOINTS FAILED ON SEAT FRAME ASSEMBLY. THE SEAT ASSEMBLY IS VERY DIFFICULT TO INSPECT IN THIS AREA AS IT IS COVERED WITH UPHOLSTERY. 1L71 3O3 O 2A13 1E10 20020325000182002032500018SO 2002 3 25 CA020227013 120020222G2520 FRAME PIPER PA28 PA28R200 7102811SO LYC O360 IO360C1C 41514EA SEAT CRACKED W K NONE W INADEQUATE Q C ININSP/MAINT 1 CA (CAN) BOTH LT AND RT UPPER FORWARD WELD JOINTS FAILED ON SEAT FRAME ASSEMBLY.THE SEAT ASSEMBLY IS VERY DIFFICULT TO INSPECT IN THIS AREA AS IT IS COVERED WITH UPHOLSTERY. 1L71 3O3 O 2A13 1E10 20020325000192002032500019 2002 3 25 CA020228001 420020217G341734100408 ADC BOEING737 737217 1384464NM PWA JT8 JT8D17 52049NE COCKPIT FAILED W A UNSCHED LANDING HJ ELECT. POWER LOSS-50 PC WARNING INDICATION CLCLIMB 1 CA (CAN) JUST AFTER TAKEOFF CAPTAINS AIRSPEED, STANDBY AIRSPEED, GROUND PROX WARNING, AND MACH TRIM INDICATORS FAILED. AIRCRAFT RETURNED TO AIRPORT. NR 1 CENTRAL AIR DATA COMPUTER REPLACED AND OPERATION CHECKED SERVICEABLE. 2L72 4F4 F A16WE E2EA 20020325000202002032500020NM 2002 3 25 CA020228002 120020123G3211NHA65B0150211 BEARING BOEING747 747475 NM GE CF6 CF680C2* GL RT MLG CRACKED W K NONE O OTHER ININSP/MAINT 1 CA MHB950 (CAN) RT BODY GEAR RETRACT ACTUATOR,, LOWER BEARING FAILED.FOUND SPHERICAL BEARING INNER RACE CRACKED THROUGH. LARGE PIECE OF INNER RACE BROKEN OUT. ROLLERS CORRODED AND MISSING. WATER INGRESSION TO BEARING EVIDENT UPON DISASSEMBLY. HIGH LEVEL OF CORROSION TO ROLLERS AND INNER RACE. RETAINING RING AND ATTACHING HARDWARE WORN THROUGH. END ASSEMBLY REPLACED.END ASSEMBLY - 65B01531-4 P/N NHA 65B01502-11 S/N MHB950 2L74 4F4 FRTA20WE E23EA 20020325000212002032500021EU 2002 3 25 CA020228003 120020212G5530D5537002500800 PANEL AIRBUS320 A320211 3930320EU CFMINTCFM56 CFM565A1 NE VERTICAL STAB CRACKED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) VERTICAL STAB LEADING EDGE PANELS 322AL, 322CL AND 322BL CRACKED. PANEL 322AL CRACKED APPROXIMATELY 4 INCHES FROM LOWER EDGE LT SIDE. PANEL 322CL CRACKED APPROXIMATELY 4 INCHES FROM LOWER EDGE LT SIDE. ALSO 322BL. PRODUCTION PERMIT RAISED FOR REPAIR IF BEYOND LIMITS. 2L72 4F4 FRTA28NM E29NE 20020325000222002032500022EU 2002 3 25 CA020228004 120020212G2740D55981002 FITTING AIRBUS320 A320211 3930320EU CFMINTCFM56 CFM565A1 NE RT & LT STAB FAILED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) LT AND RT THS REAR ATTACH BEARING FOUND LOOSE IN REAR YOKE FITTINGS.BORES IN THE THS LT AND RT REAR SUPPORT FITTING FOUND BEYOND PRODUCTION TOLERANCES. BUSHINGS WILL BE NICKEL PLATED TO RETURN OD DIAMETER. THIS CONSIDERED A PERMANENT FIX FOR THE RT FITTING AND TEMPORARY REPAIR & THE LT IS ACCEPTABLE FOR 4000 FLIGHT CYCLES, AWAITING AIRBUS FINAL DISPOSTION. 2L72 4F4 FRTA28NM E29NE 20020325000232002032500023NM 2002 3 25 CA020228005 120020212G5532D5537002500800 PANEL AIRBUSA319 A319114 3930350NM CFMINTCFM56 CFM565A1 NE VERTICAL STAB CRACKED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) VERTICAL STAB LEADING EDGE PANELS 322AL AND 322CL CRACKED. PANEL 322AL CRACKED APPROXIMATELY 4 INCHES FROM LOWER EDGE LT SIDE. PANEL 322CL CRACKED APPROXIMATELY 4 INCHES FROM LOWER EDGE LT SIDE. 2L72 4F4 FRTA28NM E29NE 20020325000242002032500024EA 2002 3 25 CA020228010 120020205G2760270003 PCU CNDAIRCL600 CL6002B19 1900309EA GE CF34 CF343A1 30015NE SPOILERS FAILED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) FLIGHT SPOILER CAUTION MESSAGE CAME ON DURING APPROACH. WENT OUT AFTER LANDING. INTERMITTENT PROBLEM THAT OCCURRED SEVERAL TIME IN RECENT PAST. SECU (SPOILER ELECTRONIC CONTROL UNIT) NR 1 FAULT CODES 02,51,E8 DISPLAYED. SECU NR 2 FAULT CODES EC,52,EA DISPLAYED. RIGHT OUTBOARD SPOILER PCU (POWER COANTROL UNIT) REPLACED AND RIGGED. SECU NR 1 AND 2 REPLACED. SYSTEM RESET AND OPERATION CHECKED SERVICEABLE. PCU P/N 27000-3SECU P/N 49-164-05 2L72 4F4 FRTA21EA E15NE 20020325000262002032500026EA 2002 3 25 CA020228014 120020222G27208220287401 CIRCUIT CARD CNDAIRCL600 CL6002B19 1900309EA GE CF34 CF343B1 NE RUDDER CONTROL FAILED W O OTHER F FLT CONT AFFECTED CLCLIMB 1 CA (CAN) AFTER EXCEEDING 250 KTS IAS, RUDDER FLUTTERED UNTIL AIRCRAFT WAS IN LANDING CONFIGURATION. REMOVED AND REPLACED LEFT (UPPER) LHP-4000 CARD IAW AIRCRAFT MM 22-12-01. OPS CHECKED GOOD ON GROUND. 2L72 4F4 FRTA21EA E15NE 20020325000272002032500027NM 2002 3 25 CA020228017 120020205G3320 LIGHT DHAV DHC8 DHC8* NM PWC 150 PW150A EA ROW 20A BURNED OUT W H DEACTIVATE SYST/CIRCUITS A FLAME/FIRE ININSP/MAINT 1 CA (CAN) DURING AN INSPECTION MAINTENANCE NOTICED THE LT SIDEWALL LAMP (FORWARD SHORT OR SECOND FROM THE BACK) AT ROW 20A WAS FOUND BURNED. THE LAMP WAS REPLACED AND APPROXIMATELY 1 HOUR LATER WE HAD A FIRE. THE CREW IMMEDIATELY TURNED THE LIGHTS OFF AND PULLED THE CB. THE 20 AMP CB DID NOT POP. THE ASSEMBLY WAS REMOVED AND REPLACED.IT WAS NOTED THAT THE LOCKING RELEASE DID NOT PROTRUDE AS MUCH AS THE NEW ASSEMBLY INSTALLED. 2H72 4T4 TRTA13NM E00062EN 20020325000282002032500028NM 2002 3 25 CA020228019 120020223G29136617302 PUMP DHAV DHC8 DHC8* NM PWC 150 PW150A EA HYD SYSTEM FAILED W O OTHER O OTHER CRCRUISE 1 CA (CAN) DURING A FLIGHT THE AIRCRAFT LOST THE RT HYDRAULIC SYSTEM DUE TO PUMP FAILURE DURING CRUISE, AFTER USING THE POWER TRANSFER UNIT (LEFT TO RIGHT HYDRAULIC PUMP) FOR GEAR EXTENSION, NO FLAP MOVEMENT OBSERVED (LEFT HYDRAULIC SYSTEM), A FLAPLESS LANDING WAS PERFORMED. NR 2 EDP REPLACED. CASE DRAIN FILTER BADLY CONTAMINATED WITH METAL. CASE DRAIN, RETURN AND PRESSURE FILTERS REPLACED. ENGINE UNS CARRIED OUT, ALL THREE FILTERS REPLACED, SYSTEM BLEED AND SERVICED. AIRCRAFT RELEASED FOR 25 HOURS PRIOR TO REPLACING FILTERS AGAIN. 2H72 4T4 TRTA13NM E00062EN 20020325000292002032500029NE 2002 3 25 CA020301001 220020228G7250 ENGINE CNDAIRCL600 CL6002B19 1900309EA GE CF34 CF343A1 30015NE RIGHT FAILED W EA ENGINE SHUTDOWN UNSCHED LANDING DJ INFLIGHT SEPARATION WARNING INDICATION CLCLIMB 1 CA (CAN) A/C 7216, FLT 5266 FROM ATW TO CVG. PRELIM INFO.AT 3000 FEET IN CLIMB RIGHT ENGINE SHUTDOWN DUE TO VIBRATION. RETURNED TO ATW. AFT END (LPTM) OF NR 2 ENGINE MISSING. RIGHT HORIZ STAB L/E DAMAGED. VERTICAL STAB APPARENTLY HAS A SMALL HOLE. NO CONFIRMATION OF ANY FUSELAGE PENETRATION OR DENTS. PIE FAIRING DAMAGED. MAINT CREW ALREADY ON GROUND AT ATW SENDING REPL ENGINE, 2 CORE COWLS, PIE FAIRING&JETPIPE CONE. MORE DETAILS WILL BE FURNISHED WHEN KNOWN. ENGINE IS ORIG EQUIP, DELIVERED ON FEB 26, 1998. NO PREVIOUS HISTORY ON ENGINE OTHER THAN ON FEB 10/11 IN ORLANDO FAN BLADES 7 THRU 28 BLENDED OUT FOR ROUGHNESS & R. INLET CROSION ON LOWER HALF REPD.ADD: 2-28-2002 NEGEL KEYS - ARRIVE D ON-SITE AT 22:00 APPROX 2L72 4F4 FRTA21EA E15NE 20020325000302002032500030EA 2002 3 25 CA020301002 120020301G5610601R330331 WINDSHIELD CNDAIRCL600 CL6002B19 1900309EA GE CF34 CF343A1 30015NE COCKPIT CRACKED W O OTHER O OTHER DEDESCENT 1 CA 15704 (CAN) LEFT WINDSHIELD CRACKED DURING DESCENT. REMOVED AND REPLACED WINDSHIELD. 2L72 4F4 FRTA21EA E15NE 20020325000312002032500031EA 2002 3 25 CA020301003 120020301G5610NP1393222 WINDOW CNDAIRCL600 CL6002B19 1900309EA GE CF34 CF343B1 NE COCKPIT CRACKED W O OTHER O OTHER CRCRUISE 1 CA (CAN) DURING CRUISE, COPILOT WINDOW INNER PLY SHATTERED. AIRCRAFT LANDED SAFELY. NEW WINDOW INSTALLED P/N NP-139322-6 AND S/N 01138H8148. 2L72 4F4 FRTA21EA E15NE 20020325000322002032500032 2002 3 25 CA020301004 420020301G6113055032111 BULKHEAD CESSNA 055032111 CESSNA172 172S 2072439CE LYC IO360 IO360L2A EA MCAULY1A170 1A170E GL SPINNER CRACKED W K NONE O OTHER ININSP/MAINT 1 CA NONE (CAN) SPINNER WAS NOTICED DEFORMED DURING GROUND HANDLING.SPINNER BULKHEAD FOUND CRACKED AND FLANGE SEPERATED CAUSING SPINNER DEFORMATION. 1H71 3O3 ONT3A12 1E10 5 NP857 20020325000332002032500033SO 2002 3 25 CA020304001 120020227G57404029400 FITTING PIPER PA31 PA31350 7103110SO LYC O540 TIO540J2BD 41532EA HARTZLHCE3Y HCE3YR2A GL WING CRACKED W K NONE O OTHER ININSP/MAINT 1 CA 1637016370 (CAN) INSPECTION REVEALED A SMALL CRACK IN THE WEB WHERE IT JOINS THE LOWER RIGHT BOLT HOLE.THE CRACK RUNS PERPENDICULAR TO THE WEB.PART TIME IS UNKNOWN, TIME GIVEN IS AIRFRAME TIME. 1L72 3O3 O A20SO E14EA 5 CP33EA 20020325000342002032500034NE 2002 3 25 CA020304002 220020301G7200 ENGINE CNDAIRCL600 CL6002B19 1900309EA GE CF34 CF343B1 NE RIGHT LEAKING W EA ENGINE SHUTDOWN UNSCHED LANDING KJ FLUID LOSS WARNING INDICATION CRCRUISE 1 CA 13218 (CAN) DEPARTURE FROM SAN ANTONIO, TEXAS DURING CRUISE PHASE OF FLT NR 2 ENGINE EXHIBITED OIL TEMP OF 185C & PRESSURE OF 27 PSI. CREW C/W WITH AFM PROCEEDURES & SHUTDOWN ENGINE. CREW DECLARED EMERGENCY & LANDED IN EL PASO, TEXAS. MESA SENT 2 MECHANICS TO INVESTIGATE. DURING INVEST. OIL FOUND IN TAIL PIPE & OIL FILTER FOUND TO HAVE CARBON RESIDUE / PIECES IN IT ALSO CARBON RESIDUE FOUND IN B-SUMP SCREENS. GE REP CONSULTED. IT DETERMINED WITH GE THAT ENGINE EXPERIENCED "B-SUMP COKE SHEDDING". GAE SUGGESTED THAT MX CLEAN ALL SCREENS REASSEMBLE & RUN ENGINE AT CRUISE POWER FOR 1 HR THEN REMOVE & CHECK FILTER&SCREENS. FINDING WERE GOOD. A/C THEN FAIRIED TO FRES NO & CHECKED AGAIN PER GE SB 79-0014&AD 2001 2L72 4F4 FRTA21EA E15NE 20020325000352002032500035EA 2002 3 25 CA020304005 220020301G8520 CONNECTING ROD PIPER PA31 PA31350 7103110SO LYC O540 TIO540J2BD 41532EA LT ENGINE FAILED W EA ENGINE SHUTDOWN UNSCHED LANDING E VIBRATION/BUFFET CRCRUISE 1 CA (CAN) DURING A SHORT FLIGHT APPROXIMATLY 5 MINUTES. AFTER T/O, PILOTS NOTICED A FAINT CLICKING NOISE FOLLOWED IMMEDIATLY BY A SLIGHT VIBRATION THEN SMOKE FROM THE LT ENGINE. THE ENGINE WAS SHUT DOWN AND FEATHERED IMMEDIATLY. AFTER LANDING VISUAL INSPECTION CONFIRMED THE NR 6 CONNECTING ROD HAD PENETRATED THE CRANKCASE ABOUT 2-3 INCHES OUTBOARD OF THE CASE SPINE. 1L72 3O3 O A20SO E14EA 20020325000362002032500036EU 2002 3 25 CA020304006 220020222G732077208602 SLEEVE TRW CASC509 FOKKERF27 F27MK100 4990617EU RROYCETAY TAYMK65015 EU GOVERNOR ASSY MISREPAIRED W K NONE W INADEQUATE Q C ININSP/MAINT 1 CA 1751 (CAN) TWO FUEL FLOW REGULATORS RECEIVED HAD SLIPPER SLEEVE ASSEMBLIES INSTALLED IN REVERSE MODE. THESE UNITS HAD BEEN PREVIOUSLY REPAIRED BY ROLLS ROYCE BRAZIL AND IT IS ESTIMATED THAT THERE MAY BE 11 (ELEVEN) SIMILAR UNITS. THIS CONDITIION HAS BEEN ASSOCIATED WITH POSSIBLE LOW FLOW AND LOW EPR. 2H72 4T4 F A817 20020325000372002032500037 2002 3 25 CA020305002 420020220G2210 AUTOPILOT SYS BOEING737 73776N 13844CHNM CFMINTCFM567CFM567B22 13802NE COCKPIT MALFUNCTIONED W H DEACTIVATE SYST/CIRCUITS F FLT CONT AFFECTED APAPPROACH 1 CA (CAN) ON APPROACH WITH THE AUTOPILOT ENGAGED WHEN AT APPROX. 6300 FT, THE AIRCRAFT PITCHED UP 5-10 DEGREES AND THE AUTO THROTTLES MOVED FORWARD. THE AUTOPILOT WAS DISENGAGFED BY THE COPILOT AND THE AIRCRAFT CONTINUED ITS APPROACH WITH THE AUTOPILOT OFF AND THE AIRCRAFT LANDED WITHOUT FURTHER INCIDENT. MAINTENANCE COMPLETED A SERIES OF AUTOPILOT TESTS AND WERE UNABLE TO IDENTIFY ANY DISCREPANCIES. OPERATOR HAS SENT THE FLIGHT DATA ACQUISITION DATA TO BOEING AND THE AUTOPILOT MANUFACTURER, HONEYWELL ASKING THEM TO PROVIDE AN EXPLANATION AS TO WHAT MAY HAVE CAUSED THE DATA AIRPLANE TO DEPART THE FLIGHT PLAN. 2L72 4F4 FRTA16WE E00055EN 20020325000382002032500038NM 2002 3 25 CA020305003 120020222G2697 WIRE BOEING737 737297 1384480NM PWA JT8 JT8D9A 52048NE APU BAY CHAFED W A UNSCHED LANDING J WARNING INDICATION CRCRUISE 1 CA (CAN) DURING FLT A/C EXPERIENCED FLICKERING LT WING BODY OVERHEAT INDICATION WITH INCREASING FREQ. OVERHEAT LIGHT ILLUMINATED OFF & FLICKERED ON & OFF CONTINUOUSLY WHEN LT ENGINE BLEED VALVE & ISOLATION VALVE WERE CLOSED (WITH APU OFF). FLT CREW CONTACTED MCC & CYCLED VALVES WITH NO RESOLVE.DUE TO ICING CONDITIONS ENROUTE & INABILITY TO CONFIRM BLEED AIR WAS ISOLATED - A/C WAS DIVERTED TO FOR PRECAUTIONARY LDG. FLT CREW PERFORMED ENGINE RUNS & COULD NOT FAULT. MAINT CALLED OUT TO INSPECT - INDICATION PROBLEM WAS ISOLATED TO A SEVERELY CHAFED WIRE IN APU AREA OF OVERHEAT LOOP. TEMP REPAIR CARRIED OUT.A/C RT-SRV WITH NO FURTHER INCIDENTS TO REPORT. 2L72 4F4 F A16WE E2EA 20020325000392002032500039EA 2002 3 25 CA020306001 220020223G7200 COMPRESSOR BEECH 200 200BEECH 1152920CE PWA PT6 PT6A41 52043EA RT ENGINE FAILED W E ENGINE SHUTDOWN EA VIBRATION/BUFFET FLAME/FIRE CRCRUISE 1 CA 17593 (CAN) THE AIRCRAFT WAS IN CRUISE FLIGHT AT FL20000. THERE WAS A LOUD BANG THAT SHUCK THE AIRCRAFT AND FLAMES APPEARED COMING OUT OF THE EXHAUST STACKS. THE ENGINE WAS SHUT DOWN AND FEATHERED. FLAMES EXTINGUISHED RIGHT AWAY IN THE STAKES. THERE WAS A SMALL AMOUNT OF FLAME NOTICED IN THE LOUVERS OF THE BLEED AIR VALVE OUTLETS, THAT EXTINGUISHED AFTER A BRIEF PERIOD. THE AIRCRAFT CONTINUED AND LANDED WITHOUT ANY FURTHER DIFFICULTIES. 1L72 4T4 T A24CE E4EA 20020325000402002032500040EA 2002 3 25 CA020306002 120020304G32347179015 HANDLE CNDAIRCL600 CL6002B19 1900309EA GE CF34 CF343B1 NE MLG SELECTOR FAILED W A UNSCHED LANDING J WARNING INDICATION CRCRUISE 1 CA (CAN) IN CRUISE, LOUD NOISE COMING FROM NOSE AREA AND MESSAGES (GEAR DISAGREE(W) AND NOSE DOOR (W) POSTED. MESSAGE CLEARED BY THEMSELVES AFTER SEVERAL SECONDS. AIRCRAFT DID AN AIR TURN BACK WHERE IT LANDED SAFELY. AIRCRAFT WAS FERRIED FOR TROUBLESHOOTING. GEAR SWINGS WERE CARRIED OUT BUT UNABLE TO REPRODUCE SNAG. BASED ON THE SYMPTOMS, IT WAS ELECTED TO REPLACE THE PSEU AND THE LANDING GEAR HANDLE.PSEU REMOVED: P/N 8-648-08 S/N 221AIRCRAFT BACK IN SERVICE. 2L72 4F4 FRTA21EA E15NE 20020325000412002032500041NM 2002 3 25 CA020306003 120020301G2150 ACM BOEING737 737268 138448QNM PWA JT8 JT8D17 52049NE ACM BAY FAILED W A UNSCHED LANDING B SMOKE/FUMES/ODORS/SPARKS CRCRUISE 1 CA (CAN) FLIGHT 183 AIRCRAFT ON FLIGHT TO YWG FROM YHM AND AT CRUISING ALTITUDE, THE FORWARD LAV SMOKE DETECTOR ACTIVATED. THE FLIGHT ATTENDENTS ADVISED THE CAPTAIN OF SMOKE IN THE CABIN AND THE REAR SMOKE DETECTOR GOING OFF. FLIGHT CREW REQUESTED PRIORITY LANDING ING YAM AND LANDED WITHOUT INCIDENT. CFR WAS CALLED OUT AND FOLLOWED AIRCRAFT TO THE GATE - NO REPORT OF SMOKE.MAINTENANCE IN YAM INSPECTED THE AIR CONDITIONING SYSTEM AND SUSPECTED THE LT ACM OIL EAS OVERSERVICED - ACM WAS DRAINED AND AIR CONDITIONING SYSTEM WAS TESTED IAW MM 21-51-00 AND CHECKED SERVICEABLE - NO SMOKE (SMELL) PRESENT.AIRCRAFT RETURNED TO SERVICE WITH NO FURTHER INCIDENTS TO REPORT. AIRCRAFT GROUND CHECKED SERVICEABLE. 2L72 4F4 F A16WE E2EA 20020325000422002032500042EU 2002 3 25 CA020306004 120020228G56109598110111 WINDOW PILATSPC12 PC1245 7090551EU PWA PT6 PT6A67B 52043NE HARTZLHCE4A HCE4A3D GL COCKPIT CRACKED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) A CRACK WAS FOUND IN THE LT SIDE WINDOW IN THE TOP CORNER EXTENDING FORWARD AND AFT FROM A SCREW HOLE. THE CRACK WAS NOT VISIBLE INSTALLED IN THE AIRCRAFT. IT WAS DISCOVERED WHILE REMOVING FOR A DIFFERENT REASON. SIDE WINDOW WAS REPLACED AND AIRCRAFT RETURNED TO SERVICE. THE SIDE WINDOW CRACK WAS COVERED BY THE WINDOW/WINDSHIELD ONE PIECE RETAINER. 1L71 3T4 TRTA78EU E26NE 5 CP210NE 20020325000432002032500043CE 2002 3 25 CA020307002 120020222G531207126161 BULKHEAD CESSNA182 182K 2072724CE CONT O470 O470C 17026SO FUSELAGE CRACKED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) REAR BULKHEAD FOUND CRACKED DURING IMPORT INSPECTION. 1H71 3O3 ONT3A13 E273 20020325000442002032500044CE 2002 3 25 CA020307004 120020222G321107416032 SUPPORT CESSNA 07416032 CESSNA182 182K 2072724CE CONT O470 O470C 17026SO MLG CRACKED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) RT LANDING GEAR OUTBOARD SUPPORT BRACKET CRACKED IN REAR CORNER FROM LANDING GEAR LEG ATTACH BOLT. FOUND ON IMPORT INSPECTION. PERIODIC REMOVAL OF LANDING GEAR LEGS FOR INSPECTION WOULD FACILITATE INSPECTION. 1H71 3O3 ONT3A13 E273 20020325000452002032500045CE 2002 3 25 CA020307005 120020222G5330LM07133343 SKIN CESSNA182 182K 2072724CE CONT O470 O470C 17026SO FUSELAGE CORRODED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) FORWARD FUSELAGE SKIN CORRODED AT FORWARD SKIN BASE OF DOOR POST. STRINGER ENGINE MOUNT CORRODED AT ENGINE MOUNT STRINGER. 1H71 3O3 ONT3A13 E273 20020325000652002032500065CE 2002 3 25 CA020307008 120020228G3060C40536 BRACKET BEECH 200 200BEECH 1152920CE PWA PT6 PT6A41 52043EA MCAULY4HFR344HFR34C754 NE BRUSH BLOCK BENT W K NONE H ELECT. POWER LOSS-50 PC ININSP/MAINT 1 CA (CAN) PROP SYNCROPHASER TARGET CONTACTED THE SYNCROPHASER MONOPOLE DAMAGING THE MONOPOLE, MONOPOLE BRACKET AND PROP DE-ICE BRUSH BLOCK BRACKET. THE PROP DE-ICE BRUSH BLOCK BRACKET WAS BENT ENOUGH TO DISPLACE THE PROP DE-ICE BRUSHES ENOUGH TO SHORT ACROSS DE-ICE SLIP RING CAUSING PARALLEL PROTECTION BREAKERS TO POP.AS YOU CAN SEE WITH THE ILLUSTRATION PROVIDED THE WHOLE ASSEMBLY (PROP DEICE BRUSH BLOCK & PROP SYNCROPHASER PICKUP) IS SECURED TO (2) 'A' FLANGE BOLTS. THERE IS A SIGNIFICANT DISTANCE (ARM) THAT IS NOT SUPPORTED WHILE TRYING TO MAINTAIN TARGET TO MONOPOLE GAP (0.032 +/- 0.005). 1L72 4T4 T A24CE E4EA 6 C3PNE 20020325000682002032500068SW 2002 3 25 CA020307009 120020226G632068750121 INSERT BELL 206 206B 1181511SW ALLSN 250C 250C20 03013GL COMPESSOR MOUNT LEAKING W K NONE K FLUID LOSS ININSP/MAINT 1 CA (CAN) OIL LEAKING FROM LOWER STARBOARD COMPRESSOR MOUNT INSERT. ENGINE REMOVED, DISASSEMBLED AND GEARBOX SENT TO ENGINE OVERHAUL FACILITY. 1G71 3U3 U H2SW E4CE 20020325000692002032500069SO 2002 3 25 CA020307010 220020304G8540627307A CASTING CESSNA150 150L 2071826CE CONT O200 O200A 17020SO RT MAG OPENING CORRODED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) WHILE REMOVING COMPONENTS OFF OF THE ACCESORIE CASE, (UN RELATED REPAIR) DISCOVERED VER DEEP PITTING AND CORROSSION AROUND THE RIGHT MAGNETO OPENING.CASTING WAS REPLACED. 1H71 3O3 O 3A19 E252 20020325000702002032500070SW 2002 3 25 CA020307011 120020227G2520206031103043 ANGLE BELL 206 206B 1181511SW ALLSN 250C 250C20B 03013GL SEAT CRACKED W K NONE O OTHER ININSP/MAINT 1 CA 10942 (CAN) WHILE COMPLETING INTERIOR REPAINTING PROCESS, TWO CRACKS WERE DISCOVERED ALMOST IDENTICAL, ORIGINATING FROM THE JOINTS BETWEEN EACH OF THE 3 SEAT PANELS. THE CRACKS WERE EACH APPROX. 2 INCHES IN LENGTH ON THE FORWARD SIDE OF THE ANGLE. 1G71 3U3 U H2SW E4CE 20020325000722002032500072EA 2002 3 25 CA020307013 120020307G2130GG670800051 SENSOR CNDAIRCL600 CL6002B19 1900309EA GE CF34 CF34* NE BLEED TEMP INOPERATIVE W B EMER. DESCENT W INADEQUATE Q C CLCLIMB 1 CA (CAN) IN CLIMB, AT FL310 (GOING TO FL390), FLT CREW NOTICED CABIN PRESSURE OF 7700 FT. BY LOOKING AT ECSP, THEY OBSERVED THAT 2 BLEED PRESSURE WERE AT ZERO & THAT BOTH PACKS OUTLINES WERE WHITE. NO MORE PRESSURIZATION & NO MESSAGES WERE POSTED. FLT CREW CARRIED OUT EMERGENCY DESCENT TO FL100 DURING WHICH CABIN ALTITUDE REACHED 11200 FT (THEY GOT CAS MESSAGES CABIN ALT (C) & CABIN ALT (W) DURING DESCENT). AFTER 2 TENTATIVES OF RESETTNG PACKS, CREW ELECTED TO APPLY QRH ABN 2-12 "UNPRESSURIZED FLT PROC" & TO CONTINUE FLT TO DESTINATION AT FL100. ON GROUND MECHANICS REPLACED BOTH BLEED TEMPERATURE SENSORS. 2L72 4F4 FRTA21EA E15NE 20020325000732002032500073SO 2002 3 25 CA020307015 220020304G855022355 GEAR CESSNA150 150L 2071826CE CONT O200 O200A 17020SO OIL PUMP BROKEN W ED ENGINE SHUTDOWN RETURN TO BLOCK J WARNING INDICATION TXTAXI/GRND HDL 1 CA (CAN) PILOT RETURNED TO BLOCKS AND SHUT ENGINE DOWN AFTER NOTICING THAT THE RPM GAUGE WAS UNSERVICABLE. UPON FURTHER INSPECTION FOUND THAT THE UPPER OIL PUMP GEAR, WHICH IS ALSO THE TACHOMETER DRIVE SHAFT. HAD SPLIT. THE PIECE WAS RECOVERED. AND THE GEAR / SHAFT WAS REPLACED WITH NEW. THE RESULTING DEFECT MAY HAVE ALSO CAUSED SOME WEAR TO THE BUSHING AND OIL PUMP HOUSING. 1H71 3O3 O 3A19 E252 20020325000742002032500074EU 2002 3 25 CA020307016 120020305G2913AE71112112CTD PUMP AIRBUS330 A330342 EU RROYCERB211 RB211TRENT77 NE HYD SYSTEM LOOSE W O OTHER K FLUID LOSS APAPPROACH 1 CA (CAN) DURING FINAL APPROACH INTO YVR, ECAM INDICATION OF GREEN SYSTEM RESERVOIR "UNDERFULL" WAS TRIGGERED, CREW CARRIED OUT PROCEDURES AS DETAILED ON ECAM WHICH INCLUDED DEPRESSURISING BOTH GREEN SYSTEM ENGINE DRIVEN PUMPS. AS A RESULT ON LANDING, AFTER ROLL-OUT A/C HAD TO BE TOWED FROM RUNWAY DUE TO NO NOSE WHEEL STEERING. INSPECTION WAS CARRIED OUT AND FOUND NR 1 HYDRAULIC PUMP(GREEN SYSTEM) ON NR 2 ENGINE PRESSURE LINE WAS LEAKING AT THE E.D.H.P DUE TO "B" NUT HAD BACKED OFF CAUSING A LEAK. "B" NUT WAS TIGHTENED, SYSTEM WAS SERVICED AND LEAK CHECK SERVICEABLE. AIRCRAFT WAS RETURNED TO SERVICE. 1L72 4F4 FRTA46NM E39NE 20020325000762002032500076NE 2002 3 25 CA020308002 220020305G73145008735G PUMP AIRBUS320 A320231 3930325EU IAE V2500 V2500A1 NE FUEL SYSTEM FAILED W CD ABORTED TAKEOFF RETURN TO BLOCK RWJPARTIAL RPM/PWR LOSS INADEQUATE Q C WARNING INDICATION TOTAKEOFF 1 CA 2419124191 (CAN) DURING INITIAL ROLL AT 1.2 EPR THE ECAM MESSAGE "COMP VANE NR 2" APPEARED ON THE UPPER ECAM SCREEN. THE ENGINE EXPERIENCED A LIGHT COMPRESSOR STALL. THE TAKE-OFF WAS REJECTED AT 50 KTS AND THE AIRCRAFT RETURNED TO THE GATE WITH BOTH ENGINES RUNNING. MAINTENANCE OPERATIONS CONTROL DISPATCHED ENGINEERS FROM YYZ. THE HP FUEL PUMP AND FUEL MANAGEMENT UNIT WERE REPLACED. A POWER ASSURANCE TEST WAS CARRIED OUT AND NO FAULTS WERE FOUND. THE AIRCRAFT WAS RETURNED TO SERVICE. 2L72 4F4 FRTA28NM E311NE 20020325000782002032500078EU 2002 3 25 CA020308003 120020308G276130829100 VALVE AIRBUS310 A310 EU GE CF6 CF680C2A5 NE SPOILERS UNSERVICEABLE W H DEACTIVATE SYST/CIRCUITS K FLUID LOSS CRCRUISE 1 CA (CAN) FLT 757, LOST OF BLUE HYDRAULIC SYSTEM FLUID IN FLIGHT. HYDRAULIC LEAK WAS FOUND COMING FROM NR 3 RT SPOILER VALVE GROUP AT THE FILTER HOUSING CAP PACKING. AFFECTED SPOILER VALVE GROUP WAS REPLACED AND A/C WAS RETURNED TO SERVICE. 2L72 4F4 FRTA35EU E13NE 20020325000802002032500080WP 2002 3 25 CA020308004 120020308G3220152460101 SLEEVE LKHEED1011 1011385114 WP RROYCERB211 RB21122B02 54555NE NLG TORQUE BROKEN W K NONE O OTHER ININSP/MAINT 1 CA (CAN) DURING WALKAROUND FOUND NLG UPPER TORQUE LINK RT DETENT SLEEVE BROKEN IN TWO. REPLACED UPPER TORQUE LINK'S RT SPRING, INDEX AND DETENT SLEEVES AND A/C WAS RETURNED TO SERVICE. 2L73 4F4 F A23WE E12EU 20020429000472002042900047EA 2002 4 29 CA020308006 220020224G741410382588 COIL BENDIX 1068255514 CESSNA172 172N 2072434CE LYC O320 O320H2AD 41508EA MAGNETO WRONG PART W O OTHER R PARTIAL RPM/PWR LOSS CRCRUISE 1 CA GO1FA068 (CAN) NEW OVERHAUL ENGINE FROM LYCOMING. ENGINE 25 HOURS. ENGINE VERY ROUGH BACKFIRE, NO POWER. POINTS DEEPLY PITTED, BRUSH ASSEMBLY WORN AT 25 HOURS. CANADIAN AIRCRAFT COMPONENT CORD STRIP REPORT W/O 2244. WRONG PART NUMBER COIL FOR THIS MAGNETO 10-382588 18 FOR 8 CYLINDERS ENGINE. PARTS REQUIRED:COIL10-382790 QTY 2 BRUSH 10-160844 QTY 2 CONTACT ASSY10-382585 QTY 2 1H71 3O3 ONT3A12 E274 20020325000852002032500085NM 2002 3 25 CA020308013 120020228G7931 ENGINE DHAV DHC8 DHC8102 2809003NM PWA 120 PW120A NE HAMSTD14SF 14SF7 NE LEFT FAILED W C ABORTED TAKEOFF J WARNING INDICATION TOTAKEOFF 1 CA (CAN) START OF THE DAY. NR 1 OIL PRESSURE WOULD GO TO 70PSI. THEN SPIKED TO 90PSI. ALL GROUND TEST SYSTEM NORMAL. ON TAKEOFF ROLL AT V1 NR 1 ENGINE OIL PRESSURE LIGHT CAME ON INTERMITTENTLY AS OIL DROPPED TO 40PSI AT LEAST 3 TIMES OIL PRESSURE THEN RESUMED NORMAL OPERATION. AIRCRAFT FLOWN BACK TO OTTAWA, THE OIL FILTERS, AND SCAVENGE FILTER CHECKED NO METAL FOUND. TALKING WITH ENGINE MANUFACTURER THEY ADVISE TO REPLACE THE PRESSURE REGULATING VALVE. 2H72 4T4 TRTA13NM E20NE 6 CP7NE 20020325000862002032500086EA 2002 3 25 CA020312002 220020301G8520AEL18840 CAMSHAFT CESSNA172 172M 2072418CE LYC O320 O320E2D 41508EA MCAULY1C160 1C160DTM GL ENGINE WORN W K NONE O OTHER ININSP/MAINT 1 CA (CAN) METAL FOUND IN OIL FILTER DURING SCHEDULED MAINTENANCE. ENGINE DISMANTLED AT OVERHAUL FACILITY. NR 4 EXHAUST LOBE FOUND TO BE WEARING AFTER 85.2 HOURS SINCE NEW. 1H71 3O3 ONT3A12 E274 5 NP910 20020325000872002032500087EU 2002 3 25 CA020312003 120020222G5412 SKIN BOLKMS117 BK117A4 5626017EU LYC LTS101LTS101650B1 41560NE FIREWALL CRACKED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) - FIREWALL ASSEMBLY AFT LT.- STA 5896, WL 2830, BL 430 AND WL 2740, BL570.- FIREWALL IS MADE OF 0.016" TITANIUM THROUGH WHICH BOTH THE FIRE EXTINGUISHER AND AIR CONDITIONER TUBING ASSEMBLY FITTINGS PASS. - CRACKS FORM AROUND FITTING HOLES IN TITANIUM. - SUSPECT CRACKS FORM DUE TO EXTREME VIBRATION AS HELICOPTER PASSES THRU TRANSLATIONAL LIFT. FITTINGS ARE RIGID - FIREWALL VIBRATES. 1G72 3U3 U H13EU E5NE 20020325000882002032500088EU 2002 3 25 CA020312006 120020222G7920 ENGINE AMD FALC20FALCON200 2730150EU GARRTTATF3 ATF36A4 29002WP LEFT LEAKING W EA ENGINE SHUTDOWN UNSCHED LANDING BKJSMOKE/FUMES/ODORS/SPARKS FLUID LOSS WARNING INDICATION CRCRUISE 1 CA (CAN) THE CREW HAD SMOKE IN THE COCKPIT. THEY NOTICED THAT THE LT ENGINE OIL PRESSURE HAD DROPPED. THEY TURNED OFF THE LT BLEED VALVE WHICH CLEARED THE SMOKE THEN THEY SHUT DOWN THE ENGINE AFTER THEY LANDED. I FOUND A LARGE AMOUNT OF OIL ON THE ENGINE'S TAIL CONE. THE OIL WAS COMING FROM THE NR 4 AND 5 SUMP VENT TUBE. THIS ENGINE HAS HAD THE NR 4 AND 5 CARBON SEALS REPLACED TWICE IN THE LAST YEAR DUE TO OIL LEAKING ON THE VENT TUBE AND HAVING HIGH SUMP PRESSURES. 2L72 4F4 FRTA7EU E7WE 20020325000902002032500090EA 2002 3 25 CA020312008 220020305G8520LW13282 CRANKCASE CESSNA150 152 2071835CE LYC O235 O235L2C 41505EA ENGINE DAMAGED W K NONE K FLUID LOSS ININSP/MAINT 1 CA (CAN) DEFECT OBSERVED DURING ROUTINE MAINTENANCE. OIL LEAKING FROM CRANKCASE LT HALF NEAR CENTRE BOLTS THAT SECURE CASES TOGETHER. FURTHER INSPECTION REVEALED A PIN HOLE THAT APPEARS TO ORIGINATE FROM WITHIN/INTERNAL TO THE CRANKCASE. ENGINE REMOVED SENT TO APPROVED OVERHAUL STATION FOR INSPECTION AND POSSIBLE REPAIR. 1H71 3O3 ONT3A19 E223 20020325000912002032500091NE 2002 3 25 CA020312009 220020219G7230310061601 BEARING PWA JT15 JT15D5 52112NE ENGINE FAILED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) THE OPERATOR REMOVED THE ENGINE FROM THE AIRCRAFT WHEN HE FOUND EXTENSIVE METAL CONTAMINATION OF THE OIL PRESSURE FILTER. AFTER PERFORMING AN OIL FLUSH, RUN & RECHECK AS SUGGESTED BY THE MAINTENANCE MANUAL. THE ENGINE WAS REMOVED AND SHIPPED TO ATI FOR INVESTIGATION AND CORRECTION.THE CAUSE OF THE METAL CONTAMINATION WAS FOUND TO BE A DAMAGED NR 1 BEARING. THE CAUSE OF THE BEARING FAILURE WAS NOT ABLE TO BE DETERMINED. 4 F E25EA 20020325000922002032500092EU 2002 3 25 CA020313002 120020222G6410355A12004008 BLADE SNIAS 350 AS350B2 8680813EU TMECA ARRIELARRIEL1D1 NE TAIL ROTOR WILL NOT BALANCEW O OTHER F FLT CONT AFFECTED NRNOT REPORTED 1 CA (CAN) THE TAIL ROTOR HAS HAD A PROBLEM OF GOING OUT OF BALANCE. THE FIRST TIME IT WENT OUT OF BALANCE HAD TO REMOVE WEIGHT FROM ONE OF THE TIPS OF THE BLADE. THE SECOND TIME HAD TO ADD WEIGHT TO THE BLADE OUT OF BALANCE. THE THIRD TIME THE T/R WENT OUT OF BALANCE HAD TO ADD MAXIMUM WEIGHT TO THE BLADE TIP. REPLACED TAIL ROTOR BLADE ASSEMBLY. 1G71 3U3 U H9EU E19EU 20020325000932002032500093EA 2002 3 25 CA020313005 220020305G8520LW12201 CAMSHAFT PIPER PA31 PA31350 7103110SO LYC O540 LTIO540J2BD 41533EA ENGINE WORN W K NONE O OTHER ININSP/MAINT 1 CA (CAN) DURING ENGINE ROCKER VALVES INSPECTION, NR 4 CYLINDER INTAKE VALVE LIFT WAS FOUND VERY LOW. THE CYLINDER WAS REMOVED AND CAMSHAFT INTAKE VALVE LOBE WAS FOUND WORN. THE ENGINE WAS REMOVED FROM THE AIRCRAFT AND SENT FOR REPAIR. 1L72 3O3 O A20SO E14EA 20020325000942002032500094NE 2002 3 25 CA020313006 220020311G7314 SHAFT PIPER PA31T PA31T2 7103127SO PWA PT6 PT6A135 52043NE FUEL PUMP STRIPPED W E ENGINE SHUTDOWN XY ENGINE FLAMEOUT ENGINE STOPPAGE DEDESCENT 1 CA (CAN) FCU AND FUEL PUMP WAS REMOVED FROM ENGINE. FUEL PUMP TO ENGINE SHAFT WAS FOUND STRIPPED, RESULTING IN FUEL STARVATION. 1L72 3T4 TRTA8EA E4EA 20020325000962002032500096EU 2002 3 25 CA020314002 120020312G3222AN427 BOLT PILATSPC12 PC1245 7090551EU PWA PT6 PT6A67B 52043NE HARTZLHCE4A HCE4A3D GL MLG LINK CORRODED W K NONE O OTHER ININSP/MAINT 1 CA (CAN) AIRCRAFT WAS DELIVERED WITH S/B 32-006 COMPLIED WITH THEREBY NOT REQUIRING INSPECTION EVERY 100HRS OF THE MLG TRAILING LINK BOLTS THE SUBJECT AIRCRAFT HAD THE TRAILING LINK SAFETY BOLTS REMOVED FOR OTHER ACESS AND THEY WERE FOUND TO BE BADLY CORRODED AND GOUGED AND WORN. 1L71 3T4 TRTA78EU E26NE 5 CP210NE 20020325001032002032500103GL 2002 3 25 HEEA078252 220020322G720023063392 ENGINE BELL 407 407 1182206SW ALLSN 250C 250C47B GL ENGINE BAY FAILED E HEEAK NONE O OTHER ININSP/MAINT 1 SW034999 1969 53323 FADEC FAILURE ON ENG START. TOT MAXED AT 1063 DEGREES. RETURNED ENGINE TO ROLLS ROYCE FOR REPAIR 1G71 3U3 UO H2SW E1GL 20020325001052002032500105GL 2002 3 25 HEEA078253 220020322G725023007189 NOZZLE BELL 206 TH57A 1180821SW ALLSN 250C 250C18A 03011GL TURBINE SECTION FAILED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03116 162678 TURBINE REMOVED FOR OVERHAUL. LOW AREA FLOW 10.17 CAUSE LOW POWER ON TEST CELL. POWER WENT FROM -5.3 TO -7.0. OVERHAULED NOZZLE, INSTALLED AND POWER WENT TO -3. 1G71 3U3 U EXPA1G71E4CE 20020325001062002032500106GL 2002 3 25 HEEA078254 220020322G720023071644 ECU BELL 407 407 1182206SW ALLSN 250C 250C47B GL ENGINE FAILED E HEEAK NONE O OTHER ININSP/MAINT 1 SW034999 2548 53323 FADEC FAILURE ON ENG. START. T.O.T. MAXED AT 1063 DEGREES. RETURNED TO ROLLS ROYCE 1G71 3U3 UO H2SW E1GL 20020327000112002032700011GL 2002 3 27 HEEA078383 220020322G753223005366 BLEED VALVE BELL 407 407 1182206SW ALLSN 250C 250C47B GL ENGINE FAILED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03723PH9089 53283 HIGH TOT. REPLACED WITH SERVICEABLE BLEED VALVE. 1G71 3U3 UO H2SW E1GL 20020327000122002032700012GL 2002 3 27 HEEA078384 220020322G753223005366 BLEED VALVE BELL 407 407 1182206SW ALLSN 250C 250C47B GL ENGINE FAILED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03723PH2995 53283 FAILED POWER ASSURANCE CHECK. REPLACED WITH SERVICEABLE BLEED VALVE. 1G71 3U3 UO H2SW E1GL 20020327000132002032700013GL 2002 3 27 HEEA078385 220020322G724023030911 COMBUSTION LINER BELL 407 407 1182206SW ALLSN 250C 250C47B GL ENGINE CRACKED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03491PH 53386 COMBUSTION LINER CRACKED AT FUEL NOZZLE MOUNT BOSS. 1G71 3U3 UO H2SW E1GL 20020327000162002032700016GL 2002 3 27 HEEA078386 220020322G732123054164 SENSOR BELL 407 407 1182206SW ALLSN 250C 250C47B GL FADEC MALFUNCTIONED E HEEAK NONE O OTHER ININSP/MAINT 1 SW038595X 53267 CAE847060 CAUSING NP1, NP1 RATE, OS, NPOS AND NPD FAULTS TO FADEC SYSTEM. REPLACED WITH SERVICEABLE PICKUP ASSY. 1G71 3U3 UO H2SW E1GL 20020327000172002032700017GL 2002 3 27 HEEA078388 220020322G742123064130 IGNITER BOX BELL 407 407 1182206SW ALLSN 250C 250C47B GL ENGINE INTERMITTENT E HEEAK NONE O OTHER ININSP/MAINT 1 SW03496PH 53398 IGNITER WORKS INTERMITTENTLY. REPLACED WITH SERVICEABLE PART. 1G71 3U3 UO H2SW E1GL 20020327000182002032700018GL 2002 3 27 HEEA078389 220020322G723023064570 LINER BELL 407 407 1182206SW ALLSN 250C 250C47B GL COMPRESSOR CHAFED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03491PH 53386 CHAFING ON FUEL NOZZLE. REPLACED WITH SERVICEABLE PART. 1G71 3U3 UO H2SW E1GL 20020327000202002032700020GL 2002 3 27 HEEA078391 220020322G732023072725 HMU BELL 407 407 1182206SW ALLSN 250C 250C47B GL FAILED E HEEAK NONE L NO TEST ININSP/MAINT 1 SW03496PH 53398 ELONGATED DRIVE PIN HOLE, FAILED 300 HOUR BACKLASH INSPECTION. REPLACED WITH SERVICEABLE PART. 1G71 3U3 UO H2SW E1GL 20020327000212002032700021GL 2002 3 27 HEEA078392 220020322G732023072725 HMU BELL 407 407 1182206SW ALLSN 250C 250C47B GL ENGINE FAILED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03496PH2526 53398 WHEN SWITCH TO MANUAL MODE, ENGINE HAS HIGH ACCELERATION. REPLACED WITH SERVICEABLE PART. 1G71 3U3 UO H2SW E1GL 20020327000702002032700070CE 2002 3 27 2002FA0000399 120020326G37101H525 MANIFOLD CESSNA172 172R 2072401CE LYC IO360 IO360L2A EA VACUUM SYSTEM DETACHED B K NONE O OTHER ININSP/MAINT 1 SO15482ER2921 17280631 L2780151A THIS AIRCRAFT USES DUAL VACUUM PUMPS. THESE PUMPS ARE CONNECTED TO THE VACUUM SYSTEM VIA A MANIFOLD ASSEMBLY. THIS MANIFOLD PERFORMS TWO IMPORTANT FUNCTIONS, ONE TO ALLOW FOR A COMBINED SOURCE OF VACUUM FROM THESE TWO PUMPS, AS WELL AS PROVIDE AN ISOLATION FUNCTION SHOULD ONE PUMP FAIL. THIS MANIFOLD VALVE, IS ASSEMBLED USING SMALL ALUMINUM RIVETS. THEY HAVE BEEN FAILING ALLOWING THE MANIFOLD VALVE TO SEPARATE WHILE MOUNTED ON THE FIREWALL. THIS RENDERS THE ENTIRE VACUUM SYSTEM INNOPERATIVE, AND COMPLETELY DISCONNECTS THE TWO PUMPS FROM THE SYSTEM. 1H71 3O3 ONT3A12 1E10 20020327000932002032700093CE 2002 3 27 2002FA0000346 120020226G5712082217569 RIB CESSNA310 310P 2074238CE CONT O470 IO470* 17026SO LT WING CRACKED G K NONE O OTHER ININSP/MAINT 1 SW11310GR8825 310P0064 NR 8 RIB, LT WING SIDE BRACE LOCATION HAD CRACK THAT PROPAGATED THE FULL UPPER AREA OF THE SIDE BRACE. THE FORWARD ATTACH BOLT WAS MISSING AND EVIDENCE OF SPINNING ON THE SURFACE OF THE RIB. AFT BOLT WAS HELD BY 2 THREADS. INSPECTED AREA AT ANNUAL. 1L72 3O3 O 3A10 E1CE 20020327000952002032700095SO 2002 3 27 2002FA0000348 120020305G76031159P200597 THROTTLE CABLE GULSTMG1159 G1159 3953505SO RROYCESPEY SPEY5118 54523EU NR 2 ENGINE BROKEN C K NONE O OTHER ININSP/MAINT 1 SO07949NA 221 8974 DURING NORMAL MAINTENANCE INSPECTION THE NR 2 ENGINE THROTTLE CABLE (FS-512 R) WAS FOUND TO BE SEVERELY FRAYED WITH APPROXIMATELY 50 PER CENT OF THE STRANDS BROKEN. THE OTHER CABLES DID NOT HAVE ANY BROKEN STRANDS BUT DID HAVE SOME WIRES BROKEN. 2L72 4F4 FRTA12EA E2EU 20020327000982002032700098SO 2002 3 27 2002FA0000351 120020301G571128018 SPAR LUSCOM8 8A 8190104SO CONT A65 A65* 17003SO WING CORRODED D K NONE O OTHER ININSP/MAINT 1 SO05134K 1821 4072 DURING ANNUAL INSPECTION OF THE CARRY THROUGH SPARS, INTER GRANULAR CORROSION WAS FOUND IN THE BOTTOM WEB OF THE AFT SPAR, NONE FOUND IN THE FORWARD SPAR. PROBABLE CAUSE WAS IN MANUFACTURING. RECOMMEND CONTINUED INSPECTION OF OLD SPARS. 1H71 3O3 O A694 E205 20020327000992002032700099SO 2002 3 27 2002FA0000352 120020301G531228007 BULKHEAD LUSCOM8 8A 8190104SO CONT A65 A65* 17003SO FUSELAGE CRACKED D K NONE O OTHER ININSP/MAINT 1 SO051345K1821 4072 BULKHEAD WAS FOUND CRACKED DURING THE REPLACEMENT OF THE VERTICAL ATTACH FITTING PER AD. PROBABLE CAUSE WAS AN EARLIER GROUND LOOP THIS AIRCRAFT SUFFERED IN 1959. THE CRACK WAS IN BETWEEN TWO BOLT HOLES AND WAS UNNOTICEABLE UNLESS THE VERTICAL FIN WAS REMOVED. 1H71 3O3 O A694 E205 20020327001102002032700110EA 2002 3 27 2002FA0000355 220020201G8500B1741 WHEEL ROBSINR22 R22BETA 7640110NM LYC O320 O320B2C 41508EA ENGINE FAN CRACKED D K NONE O OTHER ININSP/MAINT 1 SO062359T3646 2359 1438039A DURING REMOVAL OF FAN ASSEMBLY WHICH IS MOUNTED ON A TAPERED SHAFT, THE FAN MOUNTING WAS FOUND TO BE CRACKED THROUGH. ALSO THE REINFORCEMENT PLATE WHICH IS USED TO STRENGTHEN THE FAN ASSEMBLY WAS FOUND TO BE SEVERELY CRACKED. THIS SIDE OF THE FAN ASSEMBLY MOUNTS TO THE FAN NUT WAS OVER TORQUED CAUSING UNDUE STRESS ON THE TAPERED SHAFT CAUSING THE FAILURE. THIS AREA IS HARD TO INSPECT WITHOUT FAN REMOVAL, THEREFORE IT WENT UNDETECTED WHICH EVENTUALLY LEAD TO THE REINFORCEMENT PLATE CRACKING. SUGGEST USING APPROPRIATE TORQUE ON RETENTION NUT. 1G71 3O3 O H10WE E274 20020327001122002032700112SW 2002 3 27 2002FA0000356 120020318G5711 SPAR BBAVIA7 7ECA 21101NNSW CONT O200 O200* 17020SO RT WING DAMAGED D K NONE O OTHER ININSP/MAINT 1 CE079571S 7ECA379 WHILE RECOVERING WINGS FOUND NUMEROUS LOOSE RIBS THAT HAD RUBBED GROVES IN THE SPARS. SOME SMALL CRACKS ORIGINATING FROM THE NAIL HOLES. AIRPLANE HAD BEEN USED IN AEROBATICS. REPLACED ALL FOUR WING SPARS. 1H71 3O3 O A759 E252 20020327001162002032700116CE 2002 3 27 2002FA0000364 120020228G56105116052 WINDOW CESSNA425 425 2076018CE PWA PT6 PT6A60 52043NE FUSELAGE CRACKED B CTYRK NONE O OTHER ININSP/MAINT 1 GL2183GF 4250132 WINDOW, LOCATED IN UPPER CABIN DOOR, WAS FOUND TO HAVE 4 CONSECUTIVE MOUNTING HOLES BROKEN ALONG LOWER EDGE. A RETAINING RING, CALLED OUT IN PARTS BOOK, WAS NOT INSTALLED ON THIS WINDOW. THE INSTALLATION APPEARS TO HAVE BEEN DONE AT THE FACTORY, DUE TO DATE ON WINDOW. NOTE: OTHER WINDOWS ON THIS AIRCRAFT USE RETAINING RINGS. 1L72 3T4 TRTA7CE E4EA 20020327001182002032700118CE 2002 3 27 2002FA0000365 120020214G323050810323 LANDING GEAR BEECH 90 E90 1152914CE PWA PT6 PT6A60A 52043NE MLG FAILED B QH5RK NONE O OTHER ININSP/MAINT 1 NM07727MT LW271 MAIN LANDING GEAR A LOWER TORQUE KNEE, FAILED. 1L72 3T4 T 3A20 E4EA 20020327001202002032700120SO 2002 3 27 2002FA0000368 120020307G273062701113 CONTROL CABLE PIPER PA28 PA28181 7102807SO LYC O540 TIO540* 41532EA FWD STABILATOR WORN B UC2RK NONE O OTHER ININSP/MAINT 1 GL194149A2234 2843189 DURING A ROUTINE INSPECTION THE RIGHT AND LEFT FORWARD STABILATOR CABLE WERE FOUND WORN AND FRAYED. THE AILERON RIGHT AND LEFT BALANCE CABLES WERE ALSO FOUND IN A SIMILAR CONDITION. THE WORN AND FRAYED PARTS OF THE CABLES WERE FOUND AT PULLEYS FAIRLEADS OR ANY PLACE THE CABLES CAME IN CONTACT WITH. PROBABLE CAUSE: SUBSTANDARD CABLE AND IMPROPER ALIGNMENT BY MANUFACTURER. 1L71 3O3 O 2A13 E14EA 20020327001212002032700121SO 2002 3 27 2002FA0000369 120020307G2730627701114 CONTROL CABLE PIPER PA28 PA28181 7102807SO LYC O540 TIO540* 41532EA STABILATOR WORN B UC2RK NONE O OTHER ININSP/MAINT 1 GL194149A2234 2843189 DURING A ROUTINE INSPECTION THE RIGHT AND LEFT FORWARD STABILATOR CABLE WERE FOUND WORN AND FRAYED. THE AILERON RIGHT AND LEFT BALANCE CABLES WERE ALSO FOUND IN A SIMILAR CONDITION. THE WORN AND FRAYED PARTS OF THE CABLES WERE FOUND AT PULLEYS FAIRLEADS OR ANY PLACE THE CABLES CAME IN CONTACT WITH. PROBABLE CAUSE- SUBSTANDARD CABLE AND IMPROPER ALIGNMENT BY MANUFACTURER. 1L71 3O3 O 2A13 E14EA 20020327001222002032700122SO 2002 3 27 2002FA0000370 120020307G271062701123 CONTROL CABLE PIPER PA28 PA28181 7102807SO LYC O540 TIO540* 41532EA AILERON WORN B UC2RK NONE O OTHER ININSP/MAINT 1 GL194149A2234 2843189 DURING A ROUTINE INSPECTION THE RIGHT AND LEFT FORWARD STABILATOR CABLE WERE FOUND WORN AND FRAYED. THE AILERON RIGHT AND LEFT BALANCE CABLES WERE ALSO FOUND A SIMILAR CONDITION. THE WORN AND FRAYED PARTS OF THE CABLES WERE FOUND AT PULLEYS FAIRLEADS OR ANY PLACE THE CABLES CAME IN CONTACT WITH. PROBABLE CAUSE: SUBSTANDARD CABLE AND IMPROPER ALIGNMENT BY MANUFACTURER. 1L71 3O3 O 2A13 E14EA 20020327001232002032700123SO 2002 3 27 2002FA0000371 120020307G271062701124 CABLE PIPER PA28 PA28181 7102807SO LYC O540 TIO540* 41532EA AILERON WORN B UC2RK NONE O OTHER ININSP/MAINT 1 GL194149A2234 2843189 DURING A ROUTINE INSPECTION THE RIGHT AND LEFT FORWARD STABILATOR CABLE WERE FOUND WORN AND FRAYED. THE AILERON RIGHT AND LEFT BALANCE CABLES WERE ALSO FOUND IN A SIMILAR CONDITION. THE WORN AND FRAYED PARTS OF THE CABLES WERE FOUND AT PULLEYS FAIRLEADS OR ANY PLACE THE CABLES CAME IN CONTACT WITH. PROBABLE CAUSE: SUBSTANDARD CABLE AND IMPROPER ALIGNMENT BY MANUFACTURER. 1L71 3O3 O 2A13 E14EA 20020327001242002032700124SO 2002 3 27 2002FA0000372 120020227G273062701113 CABLE PIPER PA28 PA28181 7102807SO LYC O360 O360* 41514EA FWD STABILATOR WORN B UC2RK NONE O OTHER ININSP/MAINT 1 GL194146R2592 2843160 DURING A ROUTINE INSPECTION THE RIGHT AND LEFT FORWARD STABILATOR CABLES WERE FOUND WORN. THE LEFT AILERON BALANCE CABLE WAS ALSO FOUND IN A SIMILAR CONDITION. THE WORN PARTS OF THE CABLE WERE FOUND AT PULLEYS, FAIRLEADS. PROBABLE CAUSE: SUBSTANDARD CABLE AND IMPROPER ALIGNMENT BY MANUFACTURE. 1L71 3O3 O 2A13 E286 20020327001252002032700125SO 2002 3 27 2002FA0000373 120020227G273062701114 CABLE PIPER PA28 PA28181 7102807SO LYC O360 O360* 41514EA FWD STABILATOR WORN B UC2RK NONE O OTHER ININSP/MAINT 1 GL194146R2592 2843160 DURING A ROUTINE INSPECTION THE RIGHT AND LEFT FORWARD STABILATOR CABLES WERE FOUND WORN. THE LEFT AILERON BALANCE CABLE WAS ALSO FOUND IN A SIMILAR CONDITION. THE WORN PARTS OF THE CABLE WERE FOUND AT PULLEYS, FAIRLEADS. PROBABLE CAUSE: SUBSTANDARD CABLE AND IMPROPER ALIGNMENT BY MANUFACTURE. 1L71 3O3 O 2A13 E286 20020327001262002032700126SO 2002 3 27 2002FA0000374 120020227G271062701123 CABLE PIPER PA28 PA28181 7102807SO LYC O360 O360* 41514EA LT AILERON WORN B UC2RK NONE O OTHER ININSP/MAINT 1 GL194146R2592 2843160 DURING A ROUTINE INSPECTION THE RIGHT AND LEFT FORWARD STABILATOR CABLES WERE FOUND WORN. THE LEFT AILERON BALANCE CABLE WAS ALSO FOUND IN A SIMILAR CONDITION. THE WORN PARTS OF THE CABLE WERE FOUND AT PULLEYS, FAIRLEADS. 1L71 3O3 O 2A13 E286 20020327001282002032700128EA 2002 3 27 2002FA0000376 220020301G7322MA4SPA TUBE PIPER PA23 PA23160 7102304SO LYC O320 O320* 41508EA CARB DISCHARGE DAMAGED D K NONE O OTHER ININSP/MAINT 1 SW013326P 231277 ENGINE WILL NOT START, FOUND ACCELERATING PUMP DISCHARGE TUBE IN AIR BOX. REMOVE CARBURETOR FOR OVERHAUL. 1L72 3O3 O 1A10 E274 20020327001312002032700131CE 2002 3 27 2002FA0000377 120020302G5550354051303 FITTING BEECH 35 B35 1151506CE CONT E185 E185* 17014SO STAB ATTACH MALFUNCTIONED D K NONE O OTHER ININSP/MAINT 1 SW015208C D2553 LOOKED AT RUDDERVATORS MOVEMENT, THIS FITTING WAS MOVING