19980129000921998012900092GL 1998 1 29 98ZZZX323 219980106G7323252466712 GOVERNOR BELL 206 206B 1181511SW ALLSN 250C 250C20 03013GL ENGINE PT FAILED B LS1RK NONE O OTHER NRNOT REPORTED 1 EA139907K 1576 22981 2040 GOVERNOR SLOW TO RESPOND TO POWER CHANGES (HIGH AND LOW SIDE). 1G71 3U3 U H2SW E4CE 19980129001161998012900116EA 1998 1 29 98ZZZX348 219980106G8530LW12427 CYLINDER PIPER PA28 PA28181 7102807SO LYC O360 O360A4M 41514EA NR 4 CRACKED H A UNSCHED LANDING ER VIBRATION/BUFFET PARTIAL RPM/PWR LOSS NRNOT REPORTED 1 EA11317541546 287890478 L2483336A PILOT EXPERIENCED ROUGH ENGINE OPERATION AND RETURNED TO AIRPORT WITH UNEVENTFUL LANDING. INSPECTION BY MAINTENANCE PERSONNEL DISCOVERED NR 4 CYLINDER HAD ZERO COMPRESSION. CYLINDER WAS REMOVED AND FORWARDED TO ENGINE OVERHAUL SHOP WHERE FURTHER INSPECTION REVEALED CYLINDER WAS CRACKED APPROXIMATELY HALF WAY AROUND CIRCUMFERENCE BETWEEN CYLINDER BORE TO HEAD THREAD. NO HISTORY OF OPERATIONAL PROBLEMS WITH EITHER THIS CYLINDER OR OTHERS MOUNTED TO THIS ENGINE. 1L71 3O3 O 2A13 E286 19980226004651998022600465SO 1998 2 26 98ZZZX837 219980115G8550640766A4 SCAVENGE PUMP 642087A28 PIPER PA46 PA46310P 7104605SO CONT O520 TSIO520BE 17040SO TURBO OIL FAILED B FTKRK NONE K FLUID LOSS ININSP/MAINT 1 GL19357MM821 X89HEN 468508092 528514 ACFT UNDERWENT SCHEDULED 50-HR INSP. UPON POST-INSP AND RUN AND LEAK TEST, OIL NOTED COMING FROM TURBOCHARGER OUTLETS AND WASTEGATE SEAL DRAIN. FURTHER INVESTIGATION REVEALED SCAVENGE PUMP FAILURE. UPON DISASSY, END BEARING FOUND LOOSE CAUSING A BREAK IN SECTION AND SUBSEQUENT PUMP FAILURE. TURBOCHARGERS AND WASTGATE SENT FOR REPAIR. ENGINE REMOVED FOR STARTER ADAPTER REMOVAL. INSP REVEALED SCAVENGE PUMP'S RETAINING CLIP FOR END BEARING WAS NOT INSTALLED AND NO GROOVE IN SCAVENGE HOUSING FOR RETAINER CLIP. A SERVICEABLE HOUSING, NEW BEARING, AND GEARS INSTALLED. ACFT REASSEMBLED AND TESTED WITH NO FURTHER DEFECTS. 1-15-98 HOBBS: 1387.4 TSN: 821.2 HRS 1L71 3O3 O A25SO E8CE 19980226008681998022600868NE 1998 2 26 SI3R98002 219980203G72107757571 BEARING HAMSTD 6044T35P10 SAAB SF340 SF340A 7850100EU GE CT7TP CT79B 30030NE GC 49 GEARBOX CRACKED BS SI3RK NONE O OTHER ININSP/MAINT 1 NE03 14350 9191 GEE785342 DURING DISASSEMBLY OF GEARBOX, THE FORWARD ROLLER BEARING INNER RACE WAS FOUND CRACKED, PN 775757-1, FIG 7, ITEM 60. (X) 2L72 4T4 TRTA52EU E8NE 19980303000131998030300013GL 1998 3 3 98ZZZX819 219980115G72306896888 SCROLL BELL 206 206L4 1182110SW ALLSN 250C 250C30P 03013GL ENGINE COMP CRACKED D K NONE O OTHER ININSP/MAINT 1 NM01404W 1360 AP27963 52055 CAE895742 DURING SCHEDULED 100-HOUR INSPECTION, DISCOVERED COMPRESSOR SCROLL CRACKED IN ABOUT 2 O'CLOCK AREA OF RIGHT SHOULDER IN THE CURVATURE NEAR THE MATING SURFACE TO THE COMPRESSOR. THIS WAS A REPAIRED SCROLL THAT HAD BEEN INSTALLED DUE TO A PREVIOUSLY CRACKED SCROLL WHEN THE ENGINE ONLY HAD 712.3 HOURS TIME SINCE NEW. THE REPAIRED SCROLL ACCRUED 1,359.6 HOURS TIME SINCE REPAIR BEFORE IT FAILED IN THE SAME AREA AS THE PREVIOUS SCROLL THAT CRACKED. 1G71 3U3 UNCH2SW E1GL 19980305000291998030500029SO 1998 3 5 98ZZZX883 219980206G8520 CRANKCASE CESSNA340 340A 2076405CE CONT O520 TSIO520N 17040SO RT SIDE BROKEN B NT2RK NONE O OTHER ININSP/MAINT 1 CE073959G2646 1291 340A0243 509502 CRANKCASE BROKE AT UPPER REAR BETWEEN MAGNETOS DOMINATING ON THE RT SIDE OF THE CRANKCASE PARTING SURFACE. NO CRANKCASE PARTS WERE MISSING, BUT IT APPEARS TO BE INTERNAL FAILURE. THE ENGINE WAS REMOVED AND SENT TO RAM AIRCRAFT OFR OVERHAUL. 1L72 3O3 O 3A25 E8CE 19980305006241998030500624EA 1998 3 5 98ZZZX916 219980210G852077037 CRANKSHAFT PIPER PA28 PA28180 7102808SO LYC O360 O360A3A 41514EA NR 5 JOURNAL CRACKED G K NONE O OTHER ININSP/MAINT 1 NE0356WB 9 88894 284470 CRANKSHAFT WAS FOUND CRACKED AFTER PRECAUTIONARY REMOVAL FOLLOWING RECENT ENGINE OVERHAUL (8.8 HRS). CRANKSHAFT WAS PROCESSED BY REPAIR AGENCY PRIOR TO INSTALLATION. SUBMITTER SUGGGESTED PART MAY HAVE BEEN IMPROPERLY MACHINED. CRACK WAS AT NR 5 JOURNAL RADIUS APPROXIMATELY 2.50 INCHES IN LENGTH. 1L71 3O3 O 2A13 E286 19980305006291998030500629GL 1998 3 5 98ZZZX921 219980219G732123057344 FUEL CONTROL BENDIX HUGHES369 369E 4470707WP ALLSN 250C 250C20B 03013GL ENGINE MALFUNCTIONED D K NONE O OTHER ININSP/MAINT 1 WP23992SD1075 326671 510E HOT START ON FIRST START OF DAY ONLY. FOUND DURING A RECEIVED TEST. FIRST 2 TEST POINTS FOUND RICH CAUSED BY LEAKING START-DERICH BELLOWS. REPLACED BELLOWS AND RETESTED. 1G71 3U3 U H3WE E4CE 19980305006321998030500632EA 1998 3 5 98ZZZX924 219980210G8520LW17031 CRANKSHAFT LYC O320 O320D2J 41508EA JOURNAL CRACKED G K NONE W INADEQUATE Q C ININSP/MAINT 1 NE03 U9077 PART REMOVED FROM INVENTORY AND PRECAUTIONARY MPI PERFORMED. CRACKS IN JOURNAL RADII WERE APPARENT. THIS UNIT WAS PREVIOUSLY GROUND AND POLISHED BY AIR AGENCY. PART IS SCRAP. 3 O E274 19980305006331998030500633EA 1998 3 5 98ZZZX925 219980210G8520 CRANKSHAFT LYC O235 O235L2C 41505EA JOURNAL CRACKED G K NONE O OTHER ININSP/MAINT 1 NE03 143715 PART REMOVED FROM STOCK FOR PRECAUTIONARY MPI. UNIT WAS GROUND AND POLISHED BY AIR AGENCY AND FOUND TO HAVE CRACKS IN THE JOURNAL RADII. 3 O E223 19980305006341998030500634EA 1998 3 5 98ZZZX926 219980210G8520 CRANKSHAFT LYC O235 O235C1 41505EA JOURNAL CRACKED G K NONE O OTHER ININSP/MAINT 1 NE03 PART REMOVED FROM INVENTORY FOR PRECAUTIONARY MPI. CRANKSHAFT WAS GROUND AND POLISHED BY AIR AGENCY AND FOUND TO HAVE CRACKS IN THE JOURNAL RADII. 3 O E223 19980305006351998030500635EA 1998 3 5 98ZZZX927 219980210G852075006 CRANKSHAFT LYC O320 O320* 41508EA JOURNAL CRACKED G K NONE O OTHER ININSP/MAINT 1 NE03 121682 PART WAS REMOVED FROM INVENTORY FOR MPI FOLLOWING ADVISORY THAT AIR AGENCY MAY HAVE IMPROPERLY MACHINED CRANKSHAFT. PART WAS FOUND TO HAVE CRACKS IN THE JOURNAL RADII. PART IS NOT SERVICEABLE. 3 O E274 19980312000991998031200099SO 1998 3 12 98ZZZX998 119980223G2410635796 COUPLING PIPER PA28 PA28RT201T 7102817SO CONT O360 TSIO360FB 17025SO ALTERNATOR DRIVEFAILED B TRKRA UNSCHED LANDING JH WARNING INDICATION ELECT. POWER LOSS-50 PC CLCLIMB 1 SO152175K1000 28R7931028 ALTERNATOR FAILED WHEN GEAR WAS RETRACTED. GEAR LOWERED AND RETURNED TO FIELD. PILOT REPORTED ALTERNATOR CHANGED ABOUT 10 HOURS AGO AND REGULATOR CHANGED ABOUT 20 HOURS AGO FOR SAME PROBLEM. FOUND ALTERATOR DRIVE SHEARED. REF: SPECIAL AIRWORTHINESS BULLETIN NR ANE 97-04 DATED JULY 24, 1997. INSTALLED NEW DRIVE, OPERATION CHECKS GOOD. 1L71 3O3 O 2A13 E9CE 19980312001001998031200100CE 1998 3 12 98ZZZX999 119980203G3240070009993 LINE CESSNA182 182R 2072731CE CONT O470 O470U 17026SO LT BRAKE FAILED D CD ABORTED TAKEOFF RETURN TO BLOCK OK OTHER FLUID LOSS TOTAKEOFF 1 SW012939E4082 18268222 470551 LEFT BRAKE FAILED ON TAKEOFF ROLL AND TAKEOFF ABORTED. FOUND SMALL HOLE WORN THROUGH ALUMINUM BRAKE LINE WHERE LINE CHAFED ON AFT SIDE OF ENTRY STEP CASTING. INSTALLED NEW 0700099-93 BRAKE LINE. SUGGEST REMOVING LANDING GEAR STRUT FAIRINGS FOR INSPECTION AT ANNUAL INSPECTION. 1L71 3O3 ONT3A13 E273 19980312001011998031200101NE 1998 3 12 98ZZZX1000 219980218G8530399359 CYLINDER AIRTRCAT300 AT301 0390103SW PWA R1340 R1340AN1 52016NE NR 2 CRACKED H K NONE O OTHER ININSP/MAINT 1 WP173656C559 49 3010304 419312 THE NR 2 CYLINDER WAS FOUND CRACKED FROM THE REAR SPARK PLUG PORT TO THE FRONT SPARK PLUG PORT ON THE UPPER INTAKE SIDE OF THE CYLINDER HEAD. 1L71 3R3 R A9SW 5E2 19980312007101998031200710EA 1998 3 12 98ZZZX1020 219980227G7414M3975 COIL SLICK M4381 CESSNA150 152 2071835CE LYC O235 O235N2C 41505EA ENGINE MAG FAILED D O OTHER R PARTIAL RPM/PWR LOSS NRNOT REPORTED 1 SW0997428500 15285774 MAG COIL AT 500 HOURS BURNED THROUGH ON THE OPPOSITE SIDE OF HIGH TENSION LEAD. HAVE TO PULL COIL OUT TO SEE DAMAGED SPOT. ENGINE LOST POWER, TOOK MORE MANIFOLD PRESSURE TO MAINTAIN SAME RPM. 1H71 3O3 ONT3A19 E223 19980312007191998031200719GL 1998 3 12 98ZZZX1030 219980224G731347086 FILTER 6890917 AGUSTAA109 A109A 0260109EU ALLSN 250C 250C20B 03013GL FUEL NOZZLE COLLAPSED D K NONE O OTHER ININSP/MAINT 1 WP23 1284 CAE831751 FUEL NOZZLE FILTER IS PARTIALLY COLLAPSED DUE TO FOREIGN OBJECT INSERTED INTO INLET. 1G72 3U3 U H7EU E4CE 19980312007201998031200720NE 1998 3 12 98ZZZX1031 219980216G8530 CYLINDER BEECH 18 E18S 1151006CE PWA R985 R985AN14B 52008NE NR 4 SEPARATED D E ENGINE SHUTDOWN O OTHER NRNOT REPORTED 1 WP135611D 70 BA316 437424 THE CYLINDER HEAD SEPARATED FROM THE BARREL COMPLETELY THREE COOLING FINS DOWN FROM THE SPARK PLUG HOLE. THE CYLINDER REMAINS IN PLACE. DUE TO ENGINE ROUGHNESS, A PRECAUTIONARY SHUT DOWN WAS PERFORMED. AD 78-08-07 APPLIES TO THIS CONDITION. SUBMITTER RECOMMENDED INSPECTION FOR BLOW-BY BEFORE EACH FLIGHT INSTEAD OF THE 100-HOUR INTERVAL PER AD. 1L72 3R3 R A765 5E1 19980312007211998031200721EA 1998 3 12 98ZZZX1032 219980206G8550CH48103 FILTER CHAMPION PIPER PA44 PA44180 7104402SO LYC O360 O360E1A6 41514EA ENGINE OIL MALFUNCTIONED D K NONE O OTHER ININSP/MAINT 1 GL019VZ 50 F0214281 448195002 FILTER WAS REMOVED FOR A 100-HOUR INSPECTION. PRIOR TO CUTTING THE FILTER OPEN, A FOREIGN MATERIAL WAS VISIBLE ON THE OPENING OF THE FILTER. FURTHER INSPECTION REVEALED THE FOREIGN MATERIAL WAS A SEAL USED BETWEEN THE TOP OF THE FILTER CAN AND THE ELEMENT. AS A RESULT, UNFILTERED OIL COULD BE RETURNING TO THE ENGINE ALONG WITH THIS LOOSE MATERIAL. 1L72 3O3 O A19S0 E286 19980312007261998031200726GL 1998 3 12 98ZZZX1037 219980121G732050575 ADAPTER CESSNA525 525 2076601CE WILINTFJ44 FJ44 66000GL START NOZZLE WORN B CSLRK NONE O OTHER ININSP/MAINT 1 CE01195ME1408 5250110 1240 DURING ROUTINE INSPECTION CHECK 2, START NOZZLE ADAPTER WAS INSPECTED PER WILLIAMS ROLLS ROYCE FJ44-1A MM FOR DEFECTS. FRETTING WEAR OF .025 INCH WAS NOTED IN ZONE B(TIP) OF START NOZZLE, .020 INCH IS MAX SERVICE LIMIT FOR WEAR IN THIS AREA. INITIAL DISCOVERY OF WEAR WAS AT LAST ENGINE CHECK 1 INSPECTION. NO PREVIOUS WEAR NOTED PRIOR. CYCLES, 1,566. 1L72 4F4 FRTA1WI E3GL 19980312007271998031200727NE 1998 3 12 98ZZZX1038 219980217G731110718FAE FUEL HEATER PWA 118 PW118 NE FILTER BOWL STUDDEFECTIVE B VKURK NONE O OTHER ININSP/MAINT 1 CE07 11731 308 DURING INSPECTION AT OVERHAUL, THREE STUDS WERE FOUND LOOSE AROUND THE FILTER BOWL AREA (APPARENTLY 'WALLOWED OUT' DURING HOURS IN SERVICE). SITUATION COULD LEAD TO POSSIBLE FUEL LEAKAGE IF STUDS PULLED OUT. PART WAS INSPECTED IAW STEWART WARNER CMM 73-10-06. 4 T E20NE 19980312007331998031200733NE 1998 3 12 98ZZZX1044 219980203G8530 CYLINDER DOUG DC3 DC3C 3021457WP PWA R1830 R183092 52020NE NR 5 FAILED G E ENGINE SHUTDOWN O OTHER CRCRUISE 1 SW115831B 5 42100882 350920 WHILE IN CRUISE FLIGHT, THE FLIGHT CREW NOTICED OIL COMING FROM THE ENGINE VENT. THE ENGINE WAS SECURED AND THE PROPELLER FEATHERED. AN UNEVENTFUL LANDING WAS MADE. INSPECTION FOUND CYLINDER NR 5 WITH NO COMPRESSION. CYLINDER TO BE REMOVED AND FURTHER TROUBLESHOOTING DONE IF THE CYLINDER IS NOT THE PROBLEM. 2L72 4R4 R A669 5E4 19980312007361998031200736NE 1998 3 12 98ZZZX1046 219980215G7230 BLADES BOEING747 747273C 1384896NM PWA JT9 JT9* 52054NE ENGINE N1 DAMAGED B GK4YK NONE C F.O.D. LDLANDING 1 WP03470EV 20653 ON ARRIVAL NADI, FOUND FOUR N1 BLADES ON NR 1 ENGINE SEVERELY DAMAGED. SUSPECT CAUSE: INGESTION OF FOREIGN OBJECTS ON RUNWAY 02 CAUSED BY GEMINI AIR CARGO DC10-30F BLOWN WHEELS THAT LANDED EARLIER. 2L74 4F4 F A20WE E20EA 19980312007391998031200739NE 1998 3 12 SI3R98004 219980218G72107757602 IDLER BEARING HAMSTD 6044T35P10 SAAB SF340 SF340A 7850100EU GE CT7TP CT79B 30030NE GC 49 GEARBOX CRACKED BS SI3RK NONE O OTHER ININSP/MAINT 1 NE03 17027 7316 GEE785371 DURING DISASSSEMBLY OF GEARBOX, THE FORWARD IDLER GEAR BEARING INNER RACE WAS FOUND CRACKED. P/N 775760-2, FIG 8 ITEM 85. 2L72 4T4 TRTA52EU E8NE 19980319002641998031900264SO 1998 3 19 98ZZZX1060 219980205G8550 BREATHER PIPER PA34 PA34220T 7103420SO CONT O360 LTSIO360E 17025SO LT ENG OIL FROZEN B ARMMRA UNSCHED LANDING J WARNING INDICATION CLCLIMB 1 CE019284R232 3449005 PILOT REPORTED LOW OIL PRESSURE WARNING SOUNDED LEFT ENGINE, AND GAUGE INDICATED ZERO OIL PRESSURE AT APPROXIMATELY 'GEAR-UP' TIME OF TAKEOFF. LANDING WITHOUT INCIDENT. TROUBLESHOOTING DETERMINED TO BE FROZEN BREATHER. THIS SYSTEM HAS AIR/OIL SEPARATOR. PIPER IS IN PROCESS OF MODIFYING SYSTEM. ALL OPERATORS OF SENECA V AIRCRAFT SHOULD C/W THIS MODIFICATION WHEN AVAILABLE. ROUTING OF LT ENGINE BREATHER IS SLIGHTLY DIFFERENT THAN RT DUE TO AIR CONDITIONING COMPRESSOR BEING MOUNTED ON LT ENGINE. A LARGE PUDDLE OF OIL WAS FOUND AT LOCATION OF GROUND RUN. OIL WAS BLOWN THROUGH RETURN HOSE FROM SEPARATOR TO ENGINE. 1L72 3O3 O A7SO E9CE 19980319002691998031900269NE 1998 3 19 SI3R98006 219980224G72107757704 RETAIN NUT 7758001 SAAB SF340 SF340A 7850100EU GE CT7TP CT79B 30030NE GC49 GEARBOX LOOSE BS SI3RK NONE O OTHER ININSP/MAINT 1 NE03 UDAG0214 DURING DISASSEMBLY OF GEARBOX, THE DRIVE GEAR RETENTION NUT WAS REMOVED WITH NO TORQUE REQUIRED. INSTALLATION TORQUE IS 1550-1600 FEET/POUNDS. (NUT P/N 775770-4, FIG 7 ITEM 25). (X) 2L72 4T4 TRTA52EU E8NE 19980319002701998031900270NE 1998 3 19 SI3R98005 219980223G72107895781 TAB WASHER 5074T16G10 SAAB SF340 SF340A 7850100EU GE CT7TP CT79B 30030NE GC 49 GRBOX IDLRFAILED BS SI3RK NONE O OTHER ININSP/MAINT 1 NE03 11623 1H100033 GEE785623 DISASSEMBLY OF GEARCASE REVEALED THE MAIN PUMP SEIZED, THE TAB WASHER ON THE FORWARD RIGHT IDLER GEAR BROKEN. METAL CONTAMINATION THROUGHOUT THE CASE AND IN PUMP. THIS GEARCASE IS NOT REPAIRABLE AND IS CONSIDERED FOR SCRAP DISPOSITION. 2L72 4T4 TRTA52EU E8NE 19980319005881998031900588EA 1998 3 19 98ZZZX1079 219980305G8530 VALVE GUIDE PIPER PA24 PA24250 7102404SO LYC O540 O540A1A5 41532EA CYL 1-4 EXH DEFECTIVE D K NONE O OTHER ININSP/MAINT 1 SW996039P 241135 L102840 CHECKED VALVE GUIDE CLEARANCE IAW SB 388B AND FOUND EXHAUST VALVES GUIDES IN CYLINDERS 1 AND 4 TO BE OUT OF SPECIFICATIONS. THE INTAKE AND EXHAUST VALVES IN BOTH CYLINDERS ALSO WERE BELOW MANUFACTURER'S SPECIFICATIONS. 1L71 3O3 O 1A15 E295 19980319005891998031900589SO 1998 3 19 98ZZZX1080 119980305G5347 RAIL SUPPORT PIPER PA24 PA24250 7102404SO LYC O540 O540A1A5 41532EA PILOT SEAT CRACKED D A K NONE O OTHER ININSP/MAINT 1 SW996039P 241135 L102840 PILOT SEAT RAIL SUPPORT BRACKET CRACKED AT STA 77 AND STA 87. THE CRACKS WERE FOUND UNDER THE LEFT HAND SEAT RAIL IN THE FLANGE AREA AROUND THE NUT PLATES. 1L71 3O3 O 1A15 E295 19980319005901998031900590EA 1998 3 19 98ZZZX1081 219980201G7414M3333 IMPULSE COUPLINGSLICK 6351 PIPER PA32 PA32301 7103207SO LYC O540 IO540K1G5 41532EA ENGINE MAG FAILED D K NONE O OTHER ININSP/MAINT 1 AL058216T 95070029 328206037 L1795348A MAG IMPULSE COUPLING FAILED. REMOVED FROM ENGINE AT 469.8 HOURS SINCE NEW. 1L71 3O3 O A3SO 1E4 19980319005981998031900598NE 1998 3 19 98ZZZX1089 219980305G8530116733CP CYLINDER DOUG DC3 DC3C 3021457WP PWA R1830 R183092 52020NE LT ENG NR 3 CYL CRACKED G A UNSCHED LANDING K FLUID LOSS CRCRUISE 1 SW115831B 42100882 350920 APPROXIMATELY 30 MINUTES AFTER DEPARATURE, FLIGHT CREW NOTICED OIL LEAK IN LEFT ENGINE. CREW DIVERTED BACK TO AWM. MAINTENANCE FOUND CYLINDER NR 13 HEAD SEPARATING FROM BARREL. 2L72 4R4 R A669 5E4 19980325000011998032500001GL 1998 3 25 98ZZZX1026 219980210G73232539034 FLYWEIGHT BUSH BENDIX 23057870 HUGHES369 369D 4470706WP ALLSN 250C 250C20B 03013GL N2 GOVERNOR WORN H JP0MO OTHER J WARNING INDICATION NRNOT REPORTED 1 SO0150AP 1052 24224 1090585D 832359 PILOT EXPERIENCED DROOP OF N2 RPM (ROTOR) TO 100 PERCENT. BEEFED UP TO 102 PERCENT, THEN N2 RPM WENT UP TO 104 PERCENT. ERRATIC OPERATION NOTICED. RETURNED GOVERNOR TO REPAIR STATION FOR REPAIR AND REINSTALLED. PROBLEM CORRECTED. 1G71 3U3 U H3WE E4CE 19980326002881998032600288EA 1998 3 26 98ZZZX1109 219980305G85205015 STUD PARTENP68 P68C 6780105EU LYC O360 IO360A1B6 41514EA NR 2 CYL BASE FAILED B Q2ARK NONE O OTHER ININSP/MAINT 1 SW1773N 230 L2345951A DURING 100-HOUR INSPECTION, NR 2 CYLINDER BASE STUD FOUND BROKEN. SUBMITTER SUGGESTED POSSIBLY CAUSED BY ENGINE TOTAL TIME. 1H72 3O3 O A31EU 1E10 19980326003041998032600304SO 1998 3 26 98ZZZX1125 219980201G73245200106101 LINE CESSNA402 402C 207590RCE CONT O520 TSIO520UB 17040SO FLOW DIVIDER FAILED G K NONE ERKVIBRATION/BUFFET PARTIAL RPM/PWR LOSS FLUID LOSS NRNOT REPORTED 1 GL273246M 402C0294 FUEL REF LINE FROM FLOW DIVIDER TO BAFFLE BROKE CAUSING A ROUGH RUNNING ENGINE. AIRCRAFT LANDED WITHOUT INCIDENT. 1L72 3O3 O A7CE E8CE 19980326003211998032600321EA 1998 3 26 98ZZZX1142 219980212G8550MILH6000 LINE GULSTMAA1 AA1C 0631214SO LYC O235 O235L2C 41505EA OIL BREATHER BLOCKED H K NONE K FLUID LOSS ININSP/MAINT 1 SW9939058 AA1C0206 ENGINE BEGAN LEAKING OIL AT CYLINDER THRU STUD LOCATIONS. AT SAME TIME, FUEL PRESSURE ROSE APPROX 2 POUNDS. FOUND BREATHER LINE MIL-H-6000, .75 INCH TUBE, BLOCKED APPROX 95 PERCENT. BLOCKAGE APPEARS TO BE DETERIORATED INNER HOSE MATERIAL. HOSE MFG'D IN 1973. ACFT MFG'D IN 1978. HOSE WAS OLD AT TIME OF INSTALLATION. SUBMITTER RECOMMENDED CHANGING ALL RUBBER HOSES EVERY 5 YEARS AND INSPECTING ID OF BREATHER HOSE AT ANNUAL. PRESS BUILD-UP IN THE CRANKCASE CAN CAUSE LOSS OF ENGINE PROPELLLER NOSE SEAL AND SUBSEQUENT LOSS OF ALL ENGINE OIL. HIGHER THAN NORMAL FUEL PRESSURE CAN CAUSE FLOODING OF CARBURATED ENGINE. POOR CRANKCASE BREATHING CAN ALSO CONTRIBUTE TO ACCELERATED CORROSION. 1L71 3O3 O A11EA E223 19980326003271998032600327GL 1998 3 26 98ZZZX1147 219980223G7322252464429 FUEL CONTROL BENDIX 23057344 HUGHES369 369E 4470707WP ALLSN 250C 250C20B 03013GL ENGINE MALFUNCTIONED DL K NONE X ENGINE FLAMEOUT ININSP/MAINT 1 WP23550JM 310785 0013E CAE834981 ENGINE STILL HAVING DELAYED STARTS. ENGINE FLAMED OUT AT IDLE. RESTARTED WITH THE START PUMP ON, AND FLAMED OUT DURING THE START SEQUENCE. RESTARTED AGAIN, MADE IT TO IDLE, BUT FLAMED OUT AGAIN. REMOVED THE FUEL CONTROL AND INSTALLED A DASH 28 UNIT. NO FURTHER PROBLEMS. TIME ON FUEL CONTROL SN 310785 WAS 1237.5 HOURS TSO, AND 31.6 HOURS SINCE REPAIR. 1G71 3U3 U H3WE E4CE 19980326006181998032600618SO 1998 3 26 98ZZZX1176 219980301G73146467592 FUEL PUMP CESSNA172 R172K 2072431CE CONT O360 IO360K 17025SO STOP PIN DEFECTIVE D K NONE O OTHER ININSP/MAINT 1 WP23736XB2000 R1722860 355353 IN-FLIGHT MIXTURE CONTROL WOULD STICK AND WOULD NOT GO BACK TO FULL RICH MIXTURE. PREVIOUSLY, MOISTURE STIFF BUT WOULD MOVE, AND INSPECTION FOUND NO PROBLEMS. AFTER LAST 'STICK', INSPECTION FOUND THAT IDLE CUT-OFF STOP PIN WAS LOOSE IN ITS HOLE AND FREE TO MOVE IN AND OUT OF ITS HOLE FAR ENOUGH TO BLOCK MIXTURE LEVER. REPLACED PUMP WITH NEW PART. 1H71 3O3 O 3A17 E1CE 19980326006821998032600682CE 1998 3 26 AU980061 119980119G573058530158 COVER BEECH 585301565 BEECH 58 58 1152740CE CONT O520 IO520C 17032SO MCAULY3AF34C3AF34C502 GL WING SPAR SEPARATED W K NONE OE OTHER VIBRATION/BUFFET TOTAKEOFF 1 AUS (AUS) LH SPAR COVER SEPARATED AND JAMMED BETWEEN LANDING GEAR MICROSWITCHES. 1L72 3O3 O 3A16 E5CE 5 CP22EA 19980326006841998032600684NM 1998 3 26 AU980063 119980112G5330 SKIN BOEING767 767204 NM GE CF6 CF680A 30025NE BS 485 DAMAGED W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) FUSELAGE SKIN AND STRINGER 31R LOCATED AT STN 485 DAMAGED BY FORK LIFT DURING LOADING OF FORWARD CARGO HOLD. 2L72 4F4 FRTA1NM E13NE 19980326006851998032600685 1998 3 26 AU980064 419980122G2562 BATTERY E01 BEECH 200 200BEECH 1152920CE PWA PT6 PT6A41 52043EA HARTZLHCB3T HCB3TN3 GL EMERGENCY LOCATOLEAKING W K NONE O OTHER ININSP/MAINT 1 AUS 100124 (AUS) ELT BATTERIES LEAKING. FOUND DURING BATTERY CHANGE. 1L72 4T4 T A24CE E4EA 6 CP15EA 19980326006891998032600689CE 1998 3 26 AU980069 119980122G2910AE1003757G0310 HOSE CESSNA402 402C 207590RCE CONT O520 TSIO520VB 17040SO MCAULY3AF32C3AF32C505 GL HYDRAULIC MAIN DETERIORATED W K NONE OK OTHER FLUID LOSS LDLANDING 1 AUS (AUS) HYDRAULIC PRESSURE HOSE LOCATED BETWEEN RH HYDRAULIC PUMP AND FIREWALL DAMAGED AND LEAKING. LANDING GEAR WOULD NOT EXTEND AND AIRCRAFT LANDED WITH GEAR UP. INVESTIGATION FOUND THAT THE HOSE FAILED DUE TO EXPOSURE TO HEAT WITH THE FIRE SLEEVING AND THE OUTER HOSE CASE BURNED THROUGH DUE TO POSITIONING ON THE RH ENGINE EXHAUST PIPE STAINLESS STEEL SHROUD WHICH WAS TOUCHING THE EXHAUST PIPE. 1L72 3O3 O A7CE E8CE 5 CP22EA 19980326006911998032600691EU 1998 3 26 AU980071 119980128G5711 WEB BNORM BN2 BN2A26 1520226EU LYC O540 O540E4C5 41532EA HARTZLHCC2Y HCC2YK2 GL LT WING SPAR CRACKED W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) LH WING SPAR WEB CRACKED BEYOND LIMITS. 1H72 3O3 O A17EU E295 5 CP920 19980326006921998032600692EU 1998 3 26 AU980072 119980129G5711 WEB BNORM BN2 BN2A26 1520226EU LYC O540 O540E4C5 41532EA HARTZLHCC2Y HCC2YK2 GL RT WING SPAR CRACKED W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) LH AND RH SPAR WEBS CRACKED BEYOND LIMITS. 1H72 3O3 O A17EU E295 5 CP920 19980326006971998032600697EA 1998 3 26 AU980077 219980122G7532310334701 DIAPHRAGM PWA BLEEDVALVE PWA PT6 PT6A27 52043EA HARTZLHCB3T HCB3TN3 GL COMPRESSOR BLEEDFAILED W CD ABORTED TAKEOFF RETURN TO BLOCK ER VIBRATION/BUFFET PARTIAL RPM/PWR LOSS TOTAKEOFF 1 AUS 295 4P791 PCE41727 (AUS) ENGINE WOULD ONLY PRODUCE 40PSI TORQUE DURING TAKEOFF. GROUND INVESTIGATION FOUND THAT THE COMPRESSOR BLEED VALVE DIAPHRAGM WAS HOLED. 4 T E4EA 6 CP15EA 19980326006981998032600698SO 1998 3 26 AU980078 119980120G27523203001007 ACTUATOR EMB 120 EMB120RT SO PWA 118 PW118A NE TE FLAP ACTUATORFAILED W K NONE F FLT CONT AFFECTED CLCLIMB 1 AUS 0046 (AUS) RH OUTBOARD FLAP ACTUATOR FAULTY. INVESTIGATION FOUND THAT THE ACTUATOR WAS NOT KEEPING THE FLAP WITHIN THE TOLERANCE OF DISAGREEMENT WITH THE OTHER FLAPS. 2L72 4T4 TRTA31SO E20NE 19980326006991998032600699EU 1998 3 26 AU980079 119980103G2421728471B IDG BAC 146 146200A 1500266EU LYC ALF502ALF502R5 41580NE AC GENERATOR-ALTLEAKING W K NONE K FLUID LOSS ININSP/MAINT 1 AUS 0594 LFO5961 (AUS) NO1 ENGINE INTEGRATED DRIVE GENERATOR (IDG) LEAKING OIL FROM SIGHT GLASS. 2H74 4F4 F A49EU E6NE 19980326007001998032600700NM 1998 3 26 AU980080 119980131G3150 WARNING LIGHT DHAV DHC8 DHC8102 2809003NM PWA 120 PW120A NE CENTRAL WARNING FAULTY W K NONE N FALSE WARNING TOTAKEOFF 1 AUS (AUS) MASTER CAUTION LIGHT ILLUMINATED DURING TAKEOFF. INDIVIDUAL CAUTION LIGHT COULD NOT BE IDENTIFIED AND ALL SYSTEMS CHECKED OUT SERVICEABLE. 2H72 4T4 TRTA13NM E20NE 19980326007011998032600701SW 1998 3 26 AU980081 119980103G5711 STRAP GULSTM500 500B 0141106SW LYC O540 IO540E1B5 41532EA HARTZLHCA3V HCA3VK4 GL WING SPAR STRUCTCRACKED W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) LH WING UPPER SPAR STRAP CRACKED. RH WING LOWER SPAR STRAP ALSO CRACKED. FOUND DURING INSPECTION IAW SB 223. 1H72 3O3 O 6A1 1E4 5 CP6EA 19980326007061998032600706EU 1998 3 26 AU980086 119980124G324650092371 WHEEL SAAB SF340 SF340A 7850100EU GE CT7TP CT75A2 30030NE ROTOL R320 R3204123F1 NE BEARING HOUSING FAILED W K NONE O OTHER ININSP/MAINT 1 AUS 1285 941820 (AUS) WHEEL INBOARD BEARING HOUSING BROKEN UP. SECONDARY DAMAGE TO THE BRAKE UNIT. WHEEL HAD BEEN REPAIRED 2586 LANDINGS PREVIOUSLY BY THE INSTALLATION OF A BUSHING BETWEEN THE WHEEL BEARING OUTER CUP AND THE BEARING HOUSING (REPAIR SCHEME R2 CMM32-41-16). 2L72 4T4 TRTA52EU E8NE6 6 CP5NE 19980326007091998032600709SO 1998 3 26 AU980089 119980123G3260MS272402 SWITCH EMB 110 EMB110P1 3260122SO PWA PT6 PT6A34 52043EA HARTZLHCB3T HCB3TN3 GL LANDING GEAR POSFAILED W K NONE ON OTHER FALSE WARNING LDLANDING 1 AUS (AUS) LH MAIN LANDING GEAR DOWN MICROSWITCH FAULTY. 1L72 4T4 T A21SO E4EA 6 CP15EA 19980326007101998032600710EU 1998 3 26 AU980090 119980104G61234049AA PUMP JETAIRJETSTMJETSTM4101 1500501EU GARRTTTPE331TPE33114GR 01514NE MCAULY5JFR B5JFR36C1101GL PROP FEATHER FAILED W K NONE O OTHER NRNOT REPORTED 1 AUS 64708 (AUS) PROPELLER UNFEATHERING PUMP FAILED. 2L72 4T4 TRTA41NM E18NE 5 CP15WE 19980326007111998032600711CE 1998 3 26 AU980091 119980130G2910520010789 PIPE CESSNA 402C CESSNA402 402C 207590RCE CONT O520 TSIO520VB 17040SO MCAULY3AF32C3AF32C505 GL HYD MAIN CORRODED W K NONE O OTHER ININSP/MAINT 1 AUS 4020508 (AUS) RH MAIN LANDING GEAR RETRACTION SYSTEM HYDRAULIC PIPE LOCATED IN AREA BELOW THE RH FLOOR CONTAINED PITTING CORROSION. SUSPECT DUETO CONTACT WITH DUCTING INSULATION. 1L72 3O3 O A7CE E8CE 5 CP22EA 19980326007171998032600717WP 1998 3 26 AU980097 119980117G6220369D2100411 FAIRING HUGHES369 369E 4470707WP ALLSN 250C 250C20B 03013GL MAIN ROTOR HEAD SEPARATED W K NONE FD FLT CONT AFFECTED INFLIGHT SEPARATION CRCRUISE 1 AUS (AUS) MAIN ROTOR HEAD FAIRING (CHINAMANS HAT) SEPARATED FROM AIRCRAFT.SUSPECT FAIRING DEVELOPED A CRACK ALLOWING THE FAIRING TO FLEX AND LOOSEN THE ATTACHMENT SCREWS. 1G71 3U3 U H3WE E4CE 19980326007181998032600718GL 1998 3 26 AU980098 119980120G3210 LANDING GEAR AMTR MAXAIRXP503 9570746GL AMTR 582 582 GL MAIN LANDING GEADAMAGED W K NONE O OTHER LDLANDING 1 AUS (AUS) AIRCRAFT HIT FENCE WHEN CONTROL LOST DURING LANDING. DAMAGE CAUSED TO LANDING GEAR, NOSE POD AND LOWER FUEL TANK. THIS DEFECT WAS RECEIVED FROM THE AUF AND IS FOR INFORMATION ONLY. 1H71 3I3 INTEXPA1H71EXP31 19980402000141998040200014WP 1998 4 2 98ZZZX1246 219980310G72408939735 COMBUSTION CASE BEECH 100 B100 1152919CE GARRTTTPE331TPE3316252B 01514WP LT ENG PLENUM FAILED B AYRRDAE UNSCHED LANDING ENGINE SHUTDOWN MO OVER TEMP OTHER TOTAKEOFF 1 SW0566804 BE82 P27165 DURING T/O, PILOT HEARD A 'POOF' SOUND. NOTICED THE COWLING PAINT DISCOLORED AND THE OIL FILLER DOOR OPEN. TAKEOFF ABORTED, AND ENG EMERG SHUTDOWN. INVEST DETERMINED THE LT ENG COMBUSTION CASE (PLENUM) HAD FAILED. ENG REMOVED FOR REPAIR, ENG COMPARTMENT DAMAGE REPAIRED. ENG DISASSEMBLED FOR INSPECT AND IT APPEARED THE PLENUM HAD FAILED AT/AROUND THE P-3 FITTING BOSS. ENG MFG CONTACTED TO ESTABLISH IF THE PLENUM WAS AN ORIGINAL COMPONENT FOR THE ENG. MFG REPLIED PLENUM P/N AND S/N WERE NOT IN THE FACILITIES DATA BASE, AND A NON-MFG REPAIR CODE WAS EVIDENT. SUBMITTER RECOMMENDED TO PREVENT RECURRENCE, INSPECT P-3 FITTING BOSS/CUSTOMER AIR PAD AREA OF THE COMBUSTION CASE (PLENUM) CLOSELY AT INSPECTIONS. 1L72 4T4 T A14CE E2WE 19980402000151998040200015EA 1998 4 2 CA960223013 219980312G855076354 OIL PUMP CESSNA172 172L 2072432CE LYC O320 O320E2D 41508EA ENG OIL CRACKED W A UNSCHED LANDING J WARNING INDICATION TXTAXI/GRND HDL 1 CA 3192 652 L4004427A (CAN) AFTER 2.5 HOUR FLIGHT, PILOT REPORTED OIL PRESSURE CREEPING DOWN DURING DESCENT. GROUND RUN CARRIED OUT AND PRESSURE MAINTAINED AT 70 TO 75 PSI. WHILE COMPASS SWING CARRIED OUT, PRESSURE DROPPED OFF AGAIN. ENGINE REMOVED FOR OVERHAUL. REPORT FROM O/H SHOP STATED THAT OIL PUMP WAS CRACKED INTERNALLY. 1H71 3O3 ONT3A12 E274 19980402000991998040200099CE 1998 4 2 CA970807045 119980312G243651530007B REGULATOR 51530007B BEECH 90 F90 1152909CE PWA PT6 PT6A135 52043NE HARTZLHCB4T HCB4TN3 GL DC SYSTEM MALFUNCTIONED W A UNSCHED LANDING J WARNING INDICATION CRCRUISE 1 CA 3414 PCE92260 EA621 (CAN) CREW REPORTED ELECTRICAL BUS SEPARATION FOLLOWED BY AVIONICS CIRCUIT BREAKERS TRIPPING. LEFT GENERATOR DEEMED TO BE THE CAUSE AND WAS ISOLATED. MAINTENANCE FOUND THAT THE LEFT HAND GENERATOR CONTROL UNIT FAILED. 1L72 4T4 T A31CE E4EA 6 CP40EA 19980402004271998040200427NE 1998 4 2 98ZZZX1261 219980128G7200 ENGINE BELL 412 412 1182202SW PWA PT6T PT6T3B 52045NE NR 1 FAILED B VE3RK NONE O OTHER APAPPROACH 1 WP2318LA 2220 36043 63393 ON FINAL APPROACH TO HOSPITAL ROOF TOP HELIPORT, RPM WARNING HORN ACTIVATED FOLLOWED BY 15 TO 20 SECONDS OF POPPING AND GRINDING NOISES FROM NR 1 ENGINE. AFTER GAINING AIRSPEED, ENGINE WAS SECURED AND AN OEI LANDING WAS MADE AT BURBANK AIRPORT. SUBSTANTIAL DAMAGE TO NR 1 ENGINE INTERIOR WAS FOUND, CAUSE UNKNOWN AT THIS TIME. COMPLETE TWIN-PAC BEING SENT TO PRATT & WHITNEY FOR EVALUATION. 1G72 4U4 U H4SW E22EA 19980402004401998040200440GL 1998 4 2 98ZZZX1273 219980309G72306876655 WHEEL BLADE BOLKMS105 BO105S 5626006EU ALLSN 250C 250C20B 03013GL COMPRESSOR NR 5 MISSING B CK2RK NONE O OTHER ININSP/MAINT 1 SW03105HH 1722 S339 CAE830493 UPON COMPRESSOR DISASSEMBLY FOR OVERHAUL, FOUND ONE BLADE MISSING FROM 5TH STAGE COMPRESSOR WHEEL. BLADE APPEARS TO HAVE EXITED THROUGH BLEED VALVE AS NO DOWNSTREAM DAMAGE OCCURRED. NO IN-SERVICE DIFFICULTY WAS REPORTED. THE COMPRESSOR WHEEL EXHIBITS EVIDENCE OF A CORROSION PIT HALF WAY THROUGH CHORD OF BLADE AT BREAK POINT. 1G72 3U3 U H3EU E4CE 19980402005771998040200577EA 1998 4 2 AU980115 219980205G7314LW13918 PUMP PIPER PA31 PA31350 7103110SO LYC O540 TIO540J2BD 41532EA HARTZLHCE3Y HCE3YR2 GL ENGINE FUEL MALFUNCTION W K NONE O OTHER ININSP/MAINT 1 AUS L160568A (AUS) RH ENGINE DRIVEN FUEL PUMP LOW PRESSURE OUTPUT. 1L72 3O3 O A20SO E14EA 5 CP33EA 19980402005781998040200578EA 1998 4 2 AU980116 219980205G8530LW13918 CYLINDER PIPER PA31 PA31350 7103110SO LYC O540 TIO540J2BD 41532EA HARTZLHCE3Y HCE3YR2 GL LT ENG NR 2-3 DEFECTIVE W K NONE O OTHER ININSP/MAINT 1 AUS L160568A (AUS) LH ENGINE NO2 AND NO3 CYLINDER HAD LOW COMPRESSION. NO2 CYLINDER PISTON DAMAGED. AFT THROUGH BOLTS EXCESSIVELY LOOSE. ENGINE HAD COMPLETED 14 HOURS OPERATION SINCE A BULK STRIP. 1L72 3O3 O A20SO E14EA 5 CP33EA 19980402005791998040200579SO 1998 4 2 AU980117 119980205G71605491602 DOOR PIPER PA31 PA31350 7103110SO LYC O540 TIO540J2BD 41532EA HARTZLHCE3Y HCE3YR2 GL ENG AIR INTAKE BROKEN W K NONE O OTHER ININSP/MAINT 1 AUS L160568A (AUS) ENGINE AIR INTAKE ALTERNATE AIR DOOR RETURN SPRING BROKEN. DOOR HINGE SHAFT AND BUSHES EXCESSIVELY WORN. 1L72 3O3 O A20SO E14EA 5 CP33EA 19980402005801998040200580SO 1998 4 2 AU980118 119980205G71204000707 MOUNT PIPER PA31 PA31350 7103110SO LYC O540 TIO540J2BD 41532EA HARTZLHCE3Y HCE3YR2 GL ENGINE CORRODED W K NONE O OTHER ININSP/MAINT 1 AUS L160568A (AUS) RH ENGINE MOUNTS BADLY CORRODED. 1L72 3O3 O A20SO E14EA 5 CP33EA 19980402005851998040200585EA 1998 4 2 AU980123 219980205G8500 ENGINE PIPER PA31 PA31350 7103110SO LYC O540 TIO540J2BD 41532EA HARTZLHCE3Y HCE3YR2 GL LT ENG DETERIORATED W K NONE O OTHER ININSP/MAINT 1 AUS L160568A (AUS) LH ENGINE CONDITION POOR. ALL ELECTRICAL WIRES, IGNITIONHARNESSES, HYDRAULIC AND OIL HOSES NOT SECURED. NO GROMMETS FOR PROTECTION OF WIRES AND HOSES WHERE THEY PASS THROUGH BAFFLES.DRAIN LINES FOR FUEL PUMP, HYDRAULIC PUMP AND WASTE GATE MISSING. CHT PROBE FITTED TO THE INCORRECT CYLINDER. 1L72 3O3 O A20SO E14EA 5 CP33EA 19980402005881998040200588NE 1998 4 2 AU980127 219980125G7230 ENGINE LYC LTS101750 BOLKMS117 BK117B2 5626013EU LYC LTS101LTS101750B1 41560NE ENG COMPRESSOR STALLED W K NONE R PARTIAL RPM/PWR LOSS CRCRUISE 1 AUS (AUS) NO1 ENGINE SUFFERED A COMPRESSOR STALL. 1G72 3U3 UNCH13EU E5NE10 19980402006021998040200602CE 1998 4 2 AU980141 119980130G551018256315 STABILIZER CESSNA 182H CESSNA182 182H 2072718CE CONT O470 O470R 17026SO MCAULY2A34C 2A34C66 GL HORIZONTAL STABICORRODED W K NONE O OTHER ININSP/MAINT 1 AUS 18256315 (AUS) HORIZONTAL STABILISER SEVERELY CORRODED. 1H71 3O3 ONT3A13 E273 5 CP3EA 19980402006031998040200603CE 1998 4 2 AU980142 119980130G553118256315 STABILIZER CESSNA 182H CESSNA182 182H 2072718CE CONT O470 O470R 17026SO MCAULY2A34C 2A34C66 GL VERT STAB SPAR CORRODED W K NONE O OTHER ININSP/MAINT 1 AUS 18256315 (AUS) VERTICAL STABILIZER SEVERELY CORRODED. FORWARD SPAR CORRODEDTHROUGH. 1H71 3O3 ONT3A13 E273 5 CP3EA 19980402006041998040200604CE 1998 4 2 AU980143 119980130G552018256315 RIVET CESSNA 182H CESSNA182 182H 2072718CE CONT O470 O470R 17026SO MCAULY2A34C 2A34C66 GL ELEVATOR STRUCTULOOSE W K NONE O OTHER ININSP/MAINT 1 AUS 18256315 (AUS) ELEVATOR BALANCE TAB RIVETS LOOSE. 1H71 3O3 ONT3A13 E273 5 CP3EA 19980402006051998040200605CE 1998 4 2 AU980144 119980130G552118256315 SPAR CESSNA 182H CESSNA182 182H 2072718CE CONT O470 O470R 17026SO MCAULY2A34C 2A34C66 GL ELEVATOR CRACKED W K NONE O OTHER ININSP/MAINT 1 AUS 18256315 (AUS) ELEVATOR SPAR AND RIB CRACKED. 1H71 3O3 ONT3A13 E273 5 CP3EA 19980402006061998040200606CE 1998 4 2 AU980145 119980130G273018256315 RIVET CESSNA 182H CESSNA182 182H 2072718CE CONT O470 O470R 17026SO MCAULY2A34C 2A34C66 GL ELEV TORQ TUBE LOOSE W K NONE O OTHER ININSP/MAINT 1 AUS 18256315 (AUS) ELEVATOR TORQUE TUBE RIVETS LOOSE AND WORKING. 1H71 3O3 ONT3A13 E273 5 CP3EA 19980402006081998040200608CE 1998 4 2 AU980147 119980130G533018256315 RIVET CESSNA 182H CESSNA182 182H 2072718CE CONT O470 O470R 17026SO MCAULY2A34C 2A34C66 GL AFT FUSELAGE DAMAGED W K NONE O OTHER ININSP/MAINT 1 AUS 18256315 (AUS) RIVETS LOCATED IN REAR FUSELAGE HAD THE RIVET HEADS DAMAGED BY BEING SANDEDFLAT. 1H71 3O3 ONT3A13 E273 5 CP3EA 19980402006111998040200611CE 1998 4 2 AU980150 119980130G281018256315 FUEL CELL CESSNA 182H CESSNA182 182H 2072718CE CONT O470 O470R 17026SO MCAULY2A34C 2A34C66 GL LT FUEL CRACKED W K NONE OK OTHER FLUID LOSS ININSP/MAINT 1 AUS 18256315 (AUS) LH FUEL TANK BLADDER CRACKED AND LEAKING. 1H71 3O3 ONT3A13 E273 5 CP3EA 19980402006121998040200612CE 1998 4 2 AU980151 119980130G532018256315 ANGLE CESSNA 182H CESSNA182 182H 2072718CE CONT O470 O470R 17026SO MCAULY2A34C 2A34C66 GL FUSELAGE CORRODED W K NONE O OTHER ININSP/MAINT 1 AUS 18256315 (AUS) FUSELAGE ANGLE BADLY CORRODED IN AREA OF WING STRUT ATTACHMENT. 1H71 3O3 ONT3A13 E273 5 CP3EA 19980402006131998040200613CE 1998 4 2 AU980152 119980130G561018256315 WINDSHIELD CESSNA 182H CESSNA182 182H 2072718CE CONT O470 O470R 17026SO MCAULY2A34C 2A34C66 GL COCKPIT DETERIORATED W K NONE O OTHER ININSP/MAINT 1 AUS 18256315 (AUS) WINDSCREEN BADLY CRAZED AND OPAQUE. 1H71 3O3 ONT3A13 E273 5 CP3EA 19980402006141998040200614CE 1998 4 2 AU980153 119980130G273018256315 CONTROL CABLE CESSNA 182H CESSNA182 182H 2072718CE CONT O470 O470R 17026SO MCAULY2A34C 2A34C66 GL ELEVATOR CONTROLMISROUTED W K NONE O OTHER ININSP/MAINT 1 AUS 18256315 (AUS) ELEVATOR CONTROL CABLE INCORRECTLY ROUTED. 1H71 3O3 ONT3A13 E273 5 CP3EA 19980402006151998040200615EA 1998 4 2 AU980154 219980201G74148442094 MAGNETO BENDIX D6RN3200 PIPER PA31 PA31350 7103110SO LYC O540 LTIO540J2BD 41533EA HARTZLHCE3Y HCE3YR2 GL RT ENG LT MAG SHORTED W K NONE EY VIBRATION/BUFFET ENGINE STOPPAGE TOTAKEOFF 1 AUS 8442094 RL238068A (AUS) RH ENGINE LH MAGNETO PRIMARY LEAD SHORT CIRCUITED TO MAGNETO CASE. 1L72 3O3 O A20SO E14EA 5 CP33EA 19980402006201998040200620CE 1998 4 2 AU980159 119980213G282474D81 VALVE CESSNA421 421C 2076016CE CONT O520 GTSIO520N 17032SO MCAULY3FF32 3FF32C501 GL FUEL XSFER VALVEWORN W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) INLET FUEL VALVE ASSEMBLY WORN. VALVE FAILED TEST IAW AD/CESSNA400/100A4 DUE TO WORN VALVE STEM. 1L72 3O3 O A7CE E7CE 5 CP45GL 19980402006231998040200623 1998 4 2 AU980162 119980210G7712310823801 SENSOR PWA PWA120PW125B NE LT ENGINE TORQ FAULTY W K NONE N FALSE WARNING CRCRUISE 1 AUS 124031 (AUS) LH ENGINE TORQUE SENSOR INTERNAL FAULT. 4 T E20NE 19980402006261998040200626EU 1998 4 2 AU980165 119980212G57204FS7023 BRACKET HWKSLYDH114 DH1142DA 2800504EU LYC O540 IO540K1C5 41532EA HARTZLHCA3V HCA3VK2 GL WING MAIN SPAR CRACKED W K NONE O OTHER ININSP/MAINT 1 AUS NSN (AUS) WING MAIN SPAR SUPPORT BRACKET CRACKED. 2L74 3I3 O A816 1E4 5 CP6EA 19980402006291998040200629 1998 4 2 AU980168 419980118G3416AK350 ENCODER BEECH 95 95B55 1152729CE CONT O470 IO470L 17026SO MCAULY2AF34C2AF34C55 GL ALTIMETER FAILED W O OTHER W INADEQUATE Q C CRCRUISE 1 AUS 3521189 (AUS) ALTITUDE ENCODER FAULTY. PERSONNEL/MAINTENANCE ERROR. 1L72 3O3 ORT3A16 3E1 5 CP5EA 19980402006301998040200630CE 1998 4 2 AU980169 119980218G3230 TUBE BEECH 58 58 1152740CE CONT O520 IO520C 17032SO LT LANDING GEAR DAMAGED W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) LH LANDING GEAR DRIVE TUBE CREASED AT INBOARD FITTING. 1L72 3O3 O 3A16 E5CE 19980402006351998040200635CE 1998 4 2 AU980174 119980218G2710 AILERON BEECH 58 58 1152740CE CONT O520 IO520C 17032SO AILERON CONTROL MISRIGGED W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) AILERON CONTROL SYSTEM INCORRECTLY RIGGED. 1L72 3O3 O 3A16 E5CE 19980402006411998040200641EA 1998 4 2 AU980182 219980212G7314LW15473 PUMP PARTENP68 P68B EU LYC O360 IO360A1B6 41514EA HARTZLHCC2Y HCC2YK2 GL ENGINE FUEL FAILED W K NONE O OTHER ININSP/MAINT 1 AUS L1164451A (AUS) ENGINE FUEL PUMP DRIVE LEVER FAILED ACROSS PIVOT PIN HOLES. LEVER SECTION WITHIN THE PUMP HAS SECONDARY CRACKING AND IS SLIGHTLY BOWED OUTWARDS. BROKEN PORTION OF LEVER FOUND IN THE ENGINE SUMP. 1H72 3O3 O A31EU 1E10 5 CP920 19980402006461998040200646CE 1998 4 2 AU980187 119980206G2750511523716 GEARBOX CESSNA 402C CESSNA402 402C 207590RCE CONT O520 TSIO520VB 17040SO MCAULY3AF32C3AF32C505 GL TE FLAP CONTROL FAILED W K NONE OF OTHER FLT CONT AFFECTED DEDESCENT 1 AUS 12546 NSN (AUS) FLAP GEARBOX IDLER GEAR TEETH SHEARED OFF. 1L72 3O3 O A7CE E8CE 5 CP22EA 19980402006471998040200647EA 1998 4 2 AU980188 219980220G8530SL75089STD PISTON BEECH 76 76 1153005CE LYC O360 LO360A1G6 41514EA RECIP ENG CRACKED W K NONE O OTHER ININSP/MAINT 1 AUS L24571A (AUS) PISTON CRACKED. 1L72 3O3 O A29CE 1E10 19980402006481998040200648NE 1998 4 2 AU980189 219980109G7314216041101 SEAL BAC 146 146200A 1500266EU LYC ALF502ALF502R5 41580NE ENGINE FUEL PUMPSCORED W KE NONE ENGINE SHUTDOWN OK OTHER FLUID LOSS NRNOT REPORTED 1 AUS 1069ANSETTSN LF05877A (AUS) NO2 ENGINE LOW PRESSURE FUEL PUMP SHAFT CARBON SEAL CONTACT FACE WORN AND SCORED. INTERNAL `O' RING SEAL DAMAGED. FUEL PUMP DRIVESHAFT SPLINES EXCESSIVELY WORN. SUSPECT CAUSED BY LUBRICATING GREASE BEING WASHED OUT OF SPLINES BY FUEL LEAKING PAST THE SHAFT SEAL. 2H74 4F4 F A49EU E6NE 19980402006501998040200650EU 1998 4 2 AU980191 119980213G332031851A CONNECTOR BAG JETSTMJETSTM3201 1500217EU GARRTTTPE331TPE33112UA 01514WP MCAULY4HFR344HFR34C653 NE PASSENGER COMPARBURNT W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) CABIN LIGHT CONNECTOR ON LEFT REAR LAMP OVERHEATED. CONNECTING WIRE MELTED AND BURN MARKS ON TRIM. 2L72 4T4 TRTA56EU E4WE 6 C3PNE 19980402006541998040200654EA 1998 4 2 AU980195 219980118G72503012264 COVER EMB 110 EMB110P1 3260122SO PWA PT6 PT6A34 52043EA HARTZLHCB3T HCB3TN3 GL TURBINE SECTION MISINSTALLED W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) NO2 BEARING COVER INCORRECTLY SEATED. PERSONNEL/MAINTENANCE ERROR. 1L72 4T4 T A21SO E4EA 6 CP15EA 19980402006561998040200656SW 1998 4 2 AU980198 119980225G27702770066001 PLUNGER FRCHLDSA227 SA227DC 3377521SW GARRTTTPE331TPE33112UA 01514WP MCAULY4HFR344HFR34C652 NE GUST LOCK/DAMPERFAILED W A K NONE F FLT CONT AFFECTED NRNOT REPORTED 1 AUS (AUS) RUDDER GUST LOCK SYSTEM PLUNGER ASSEMBLY INTERNAL SLEEVE SEPARATED AND MIGRATED ALONG THE PLUNGER SPIGOT FOULING THE RUDDER BELLCRANK. 2L72 4T4 TRTA18SW E4WE 6 C3PNE 19980402006631998040200663CE 1998 4 2 AU980205 119980216G24607277220 CIRCUIT BREAKER BEECH 200 200BEECH 1152920CE PWA PT6 PT6A41 52043EA HARTZLHCB3T HCB3TN3 GL FLAP MOTOR OPEN W K NONE O OTHER NRNOT REPORTED 1 AUS (AUS) FLAP MOTOR CIRCUIT BREAKER INTERMITTENT OPEN CIRCUIT. 1L72 4T4 T A24CE E4EA 6 CP15EA 19980402006641998040200664NE 1998 4 2 AU980206 219980217G732425890 FLOW DIVIDER EMB 120 EMB120 3260201SO PWA 118 PW118A NE RT ENG FUEL FAULTY W K NONE EX VIBRATION/BUFFET ENGINE FLAMEOUT DEDESCENT 1 AUS 1106 115476 (AUS) RH ENGINE FUEL FLOW DIVIDER FAULTY. 2L72 4T4 TRTA31SO E20NE 19980410000151998041000015SO 1998 4 10 98ZZZX1335 219980304G85206419311075 THRU BOLT CESSNA421 421C 2076016CE CONT O520 GTSIO520L 17032SO NR 6 CYL FLANGE FAILED B BXSRK NONE O OTHER ININSP/MAINT 1 EA0960RR 679 421C0885 292133R DURING 100-HOUR INSPECTION, FOUND THE NR 6 CYLINDER TOP FORWARD STUD/THRU-BOLT BROKEN AT THE CYLINDER BASE. TCM TECH REP SAYS THAT THERE HAS BEEN A PROBLEM WITH THRU-BOLTS BREAKING EVEN BEFORE THEY LEAVE THE FACTORY. HYDROGEN EMBRITTLEMENT IS THE CAUSE. SUBMITTER DOESN'T KNOW WHY THIS ONE BROKE. 1L72 3O3 O A7CE E7CE 19980410000171998041000017SO 1998 4 10 98ZZZX1337 219980325G7421RHB32S SPARK PLUG CHAMPION CESSNA210 P210N 2073454CE CONT O520 TSIO520P 17040SO ELECTRODE DELAMINATED B CS3RK NONE O OTHER ININSP/MAINT 1 WP17677PC63 P21000677 THE SIDE MOUNTED GROUND ELECTRODE SHOWS SIGNS OF DELAMINATION OR END SPLITS. PREVIOUS MDR SUBMITTED AND WRITTEN IN ALERT 230 SEPT 1997. 1H71 3O3 O 3A21 E8CE 19980410000291998041000029WP 1998 4 10 98ZZZX1276 219980217G7200 ENGINE BEECH 100 B100 1152919CE GARRTTTPE331TPE3316 01514WP RT ENGINE SEIZED B N81RAH UNSCHED LANDING DEACTIVATE SYST/CIRCUITS H ELECT. POWER LOSS-50 PC ININSP/MAINT 1 GL09108EB5418 1848 BE108 P27075 RIGHT ENGINE INSTALLATION AFTER REPAIRS FOR BIRD INGESTION AND COMPLETION OF HSI. AIRCRAFT WAS ON A FLIGHT CHECK FOR THE REQUIRED IN-FLIGHT NTS CHECK. ENG WAS SHUT DOWN AND ON RESTART, SPOOLED TO ABOUT 20 PERCENT WHEN ENG SEIZED. (SEIZURE APPEARS TO BE FROM INTERNAL SHAFT WARPAGE). DURING ATTEMPTED RESTART WHEN ENG SEIZED, THE LOAD ON STARTER WENT EXCESSIVE AND CAUSED STARTER TO OVERHEAT (LIGHT SMOKE FROM RT SIDE, NO FIRE) AND THE 325 RT BUSS CURRENT LIMITER BLEW. THE BLOWN CURRENT LIMITER SHUT DOWN ALL ELECTRICAL POWER TO THE RT SIDE. A SAFE LANDING WAS MADE AND UPON LT ENGINE SHUT DOWN, LT 325 CURRENT LIMITER BLEW. AIRCRAFT TOWED BACK TO MAINTENANCE HANGAR. REPORT IN C/W FAR 135.415 REQUIREMENT. 1L72 4T4 T A14CE E4WE 19980415000031998041500003WP 1998 4 15 AU980126 219980204G7210M274263144C CIRCLIP GARRTT COUPLING FRCHLDSA227 SA227DC 3377521SW GARRTTTPE331TPE33112UA 01514WP MCAULY4HFR344HFR34C652 NE LT ENG RED BOX FAILED W K NONE ER VIBRATION/BUFFET PARTIAL RPM/PWR LOSS DEDESCENT 1 AUS LOT3308 P70182 (AUS) LH ENGINE REDUCTION GEARBOX MAINSHAFT COUPLING ASSEMBLY PNO 3103726-2 CIRCLIP FAILED ALLOWING THE COUPLING TO MOVE FORWARD ONTO THE HIGH SPEED PINION GIVING MINIMAL SPLINE CONTACT AND EVENTUAL DECOUPLING OF THE DRIVE. 2L72 4T4 TRTA18SW E4WE 6 C3PNE 19980417000961998041700096EA 1998 4 17 98ZZZX1448 219980318G8530 VALVE SEAT CESSNA172 172P 2072436CE LYC O320 O320D2J 41508EA NR 3 CYL EXH VLVDAMAGED H K NONE ER VIBRATION/BUFFET PARTIAL RPM/PWR LOSS ININSP/MAINT 1 WP07540484627 505 17274857 L1223939A DURING AIRCRAFT RUN-UP, THE PILOT NOTICED THE ENGINE WAS RUNNING ROUGH. THE MECHANIC PULLED A COMPRESSION CHECK AND FOUND THAT NR 3 CYLINDER HAD NO COMPRESSION. FURTHER INVESTIGATING AND CYLINDER REMOVAL SHOWED THE EXHAUST VALVE SEAT INSIDE THE CYLINDER HAD SLIPPED OUT FROM ITS GROOVE; THUS, NOT ALLOWING FOR PROPER VALVE SEATING. 1H71 3O3 ONT3A12 E274 19980417001021998041700102SO 1998 4 17 98ZZZX1454 219980330G8530653191 GASKET CESSNA206 TU206G 2073357CE CONT O520 TSIO520M 17040SO CYL NR 3 ROCKER LEAKS D K NONE K FLUID LOSS ININSP/MAINT 1 NM079438M9 U20604546 A SMALL OIL LEAK ON NR 3 CYLINDER WAS REPAIRED BY INSTALLING A NEW P/N 653191 ROCKER COVER GASKET. NINE HOURS LATER, A LARGE OIL LEAK WAS EVIDENT, CYLINDER NR 3. UPON PULLING COVER, FOUND GASKET HAD SHRUNK CAUSING OIL LEAK WHERE THE GASKET WENT STRAIGHT BETWEEN TWO SCREWS. 1H71 3O3 O A4CE E8CE 19980417002751998041700275SO 1998 4 17 AU980210 219980222G8530 CYLINDER CESSNA172 R172K 2072431CE CONT O360 IO360K 17025SO RT AFT HEAD SEPARATED W K NONE ER VIBRATION/BUFFET PARTIAL RPM/PWR LOSS CRCRUISE 1 AUS 478 355891 (AUS) RT REAR CYLINDER HEAD SEPARATED. 1H71 3O3 O 3A17 E1CE 19980417002781998041700278NE 1998 4 17 AU980214 219980225G85308408 VALVE GUIDE DHAV DHC2 DHC2EVANS 2801832EA PWA R985 R985AN14B 52008NE NR 1 CYL EXH LOOSE W K NONE O OTHER ININSP/MAINT 1 AUS 269 8408 8408 (AUS) NR 1 CYLINDER EXHAUST VALVE GUIDE LOOSE. 1H71 3O3 R A806 5E1 19980417002811998041700281EA 1998 4 17 AU980217 219980228G8520 TAPPET PIPER PA31 PA31350 7103110SO LYC O540 TIO540J2BD 41532EA NR 4 CYL CAM FAILED W K NONE ERKVIBRATION/BUFFET PARTIAL RPM/PWR LOSS FLUID LOSS NRNOT REPORTED 1 AUS L655261A (AUS) LT ENGINE CRANKCASE HOLED IN AREA ADJACENT TO NR 4 CYLINDER INLET CAM FOLLOWER. CAM FOLLOWER HEAD MISSING. NR 3 CYLINDER CAM FOLLOWER ALSO DAMAGED. 1L72 3O3 O A20SO E14EA 19980417002871998041700287EU 1998 4 17 AU980223 219980226G8500 ENGINE RROYCEGIPSY GIPSY30* 20005EU LT ENG MALFUNCTION W K NONE ER VIBRATION/BUFFET PARTIAL RPM/PWR LOSS CLCLIMB 1 AUS 66793 (AUS) LT ENGINE FLUCTUATING. ENGINE BOOST AND OIL PRESSURE DROPPED OFF AND ENGINE RAN ROUGH. 3 I E294 19980417002951998041700295NE 1998 4 17 AU980231 219980221G7230 COMPRESSOR BELL 412 412 1182202SW PWA PT6T PT6T3B 52045NE LT ENGINE DAMAGED W K NONE O OTHER NRNOT REPORTED 1 AUS 63417 (AUS) LT ENGINE COMPRESSOR DAMAGED. 1G72 4U4 U H4SW E22EA 19980417002961998041700296SO 1998 4 17 AU980232 219980306G8520643202 CRANKCASE STUD CESSNA402 402A 207590MCE CONT O520 TSIO520E 17040SO NR 5 CYL PAD CRACKED W K NONE O OTHER ININSP/MAINT 1 AUS 502423 (AUS) CRANKCASE CRACKED AT NR 5 CYLINDER MOUNTING PAD. BOTTOM TWO MOUNT STUDS BROKEN. 1L72 3O3 O A7CE E8CE 19980417003171998041700317NE 1998 4 17 AU980253 219980218G723031042764 IMPELLER GARRTT JETAIRJETSTMJETSTM4101 1500501EU GARRTTTPE331TPE33114GR 01514NE TURB ENG COMP DAMAGED W K NONE O OTHER ININSP/MAINT 1 AUS P75052 (AUS) COMPRESSOR BLADE FAILED AND SEPARATED. IMPELLER HAD SUFFERED A BIRDSTRIKE THIRTEEN DAYS EARLIER BUT INSPECTION FOUND IMPACT DAMAGE TO BE WITHIN LIMITS. 2L72 4T4 TRTA41NM E18NE 19980417003191998041700319SO 1998 4 17 AU980255 219980223G85206419441048 STUD CESSNA337 337F 2075725CE CONT O360 IO360C 17025SO NR 4&5 CYL SHEARED W K NONE O OTHER ININSP/MAINT 1 AUS 350027 772890800218 (AUS) CRANKCASE LOWER THOUGH BOLT LOCATED BETWEEN NR 4 AND NR 5 CYLINDERS SHEARED OFF AT THE THREAD. 1H72 3O3 O A6CE E1CE 19980417003231998041700323EA 1998 4 17 AU980259 219980303G8520 STUD BELL 47 47G3B1 1181028SW LYC O435 VO435A1F 41516EA ENG NR 5 CYL FAILED W K NONE O OTHER ININSP/MAINT 1 AUS L201552 (AUS) NR 5 CYLINDER HOLD DOWN STUDS FAILED. 1G71 3O3 O 2H3 E279 19980417003241998041700324 1998 4 17 AU980260 119980221G7400 IGNITION SYSTEM 912A ROTAX 912 ROTAX912 55555EU ENG IGNITION FAULTY W K NONE O OTHER DEDESCENT 1 AUS 4410151 (AUS) ENGINE WOULD NOT START. SUSPECT CAUSED BY WEAK IGNITION SYSTEM. 3 I EXPE3I 19980417003251998041700325SW 1998 4 17 AU980262 119980213G6200 MAIN ROTOR SYS BELL 206 206B 1181511SW ALLSN 250C 250C20B 03013GL DRIVE SYS STOPPAGE W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) MAIN ROTOR, TAIL ROTOR AND DRIVE SHAFT COMPONENTS - SUSPECT FOLLOWING DYNAMIC ROLLOVER ON 2/13/98. 1G71 3U3 U H2SW E4CE 19980417003261998041700326NM 1998 4 17 AU980263 119980123G5310 STRUCTURE BOEING727 7272J4 1384006NM PWA JT8 JT8D17 52049NE FUSELAGE CORRODED W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) AIRCRAFT STRUCTURE CORRODED. 2L73 4F4 FRTA3WE E2EA 19980417003271998041700327NM 1998 4 17 AU980264 119980115G5310 STRUCTURE BOEING727 72777C 1380420NM PWA JT8 JT8D15 52051NE FUSELAGE CORRODED W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) AIRCRAFT STRUCTURE CORRODED. 2L73 4F4 F A3WE E2EA 19980417003421998041700342SO 1998 4 17 AU980280 219980204G8520 CRANKCASE CONT O360 TSIO360E 17025SO ENGINE CRACKED W K NONE O OTHER ININSP/MAINT 1 AUS 237339R (AUS) ENGINE CRANKCASE RT HALF CRACKED IN NR 4 MAIN BEARING TUNNEL AND LT HALF CRACKED IN NR 2 AND NR 3 MAIN BEARING TUNNELS. CRANKSHAFT CRACKED ON NR 4 MAIN BEARING. CRACK LENGTH APPROXIMATELY 50.8MM (2 INCHES). 3 O E9CE 19980417003511998041700351EA 1998 4 17 AU980289 219980312G7314B2680 SCREW RG34720A BEECH 200 200BEECH 1152920CE PWA PT6 PT6A41 52043EA FUEL PUMP DEFECTIVE W K NONE O OTHER ININSP/MAINT 1 AUS B2680 PCE81596 (AUS) FUEL PUMP SCREWS FAILED TORQUE CHECK IAW ROMEC SB 101SB018. 1L72 4T4 T A24CE E4EA 19980417003531998041700353NE 1998 4 17 AU980291 219980303G8530366249 CYLINDER DHAV DHC3 DHC3 2800202EA PWA R1340 R134059 52016NE NR 2 - 3 CYL EXHDEFECTIVE W K NONE O OTHER ININSP/MAINT 1 AUS 10 (AUS) NR 2 AND NR 3 CYLINDERS LEAKING PAST EXHAUST VALVES. 1H71 3R3 R A815 5E2 19980417003601998041700360EA 1998 4 17 AU980298 219980302G8540LW10297 GEAR PIPER PA31 PA31350 7103110SO LYC O540 LTIO540J2BD 41533EA CRANK IDLER FAILED W K NONE E VIBRATION/BUFFET CRCRUISE 1 AUS 1628 L87968A (AUS) CRANKSHAFT IDLER GEAR TEETH FAILED. DAMAGE TO CAMSHAFT GEAR AND CRANKSHAFT GEAR. LOSS OF DRIVE TO OIL PUMP AND MAGNETO. 1L72 3O3 O A20SO E14EA 19980417003681998041700368 1998 4 17 AU980306 119980323G7602115C6030 SUPPORT LYC O360 O360A1F6 41514EA MIXTURE CONTROL CRACKED W K NONE O OTHER ININSP/MAINT 1 AUS L3482036A (AUS) ENGINE MIXTURE CONTROL CABLE CLAMP SUPPORT CRACKED. 3 O E286 19980417003701998041700370SO 1998 4 17 AU980309 219980304G8540537721 BEARING CESSNA404 404CESSNA 2075901CE CONT O520 GTSIO520M 17032SO ENG STARTER FAILED W K NONE O OTHER ININSP/MAINT 1 AUS 1069 276251R (AUS) STARTER SHAFT BEARING FAILED. METAL CONTAMINATION OF OIL SYSTEM. 1L72 3O3 O A25CE E7CE 19980417003711998041700371CE 1998 4 17 AU980310 119980313G3310A350CNIWBKSH CONNECTOR GRIMES A350CNIWBKSHCESSNA414 414A 2075907CE CONT O520 TSIO520N 17040SO INST PANEL LITE BURNT W K NONE B SMOKE/FUMES/ODORS/SPARKS NRNOT REPORTED 1 AUS (AUS) SPARE POST LIGHT CONNECTOR LOCATED BEHIND THE INSTRUMENT PANEL SHORT CIRCUITED AND BURNT. 1L72 3O3 O A7CE E8CE 19980417003741998041700374WP 1998 4 17 AU980313 219980327G726131035781 TUBE 31080801 SWRNGNSA227 SA227AC 8780603SW GARRTTTPE331TPE33111U 01514WP ENGINE OIL CHAFED W K NONE O OTHER ININSP/MAINT 1 AUS 2647 P44386 (AUS) REAR TURBINE OIL SUPPLY TUBE CHAFING ON UTS SYSTEM OIL SUPPLY TUBE. 2L72 4T4 TRTA8SW E4WE 19980417003841998041700384SO 1998 4 17 AU980324 219980218G74146210 MAGNETO CESSNA210 210N 2073453CE CONT O520 IO520L 17032SO LT MAG FAULTY W K NONE E VIBRATION/BUFFET CRCRUISE 1 AUS 88040262 567450 (AUS) LT MAGNETO FAULTY. 1H71 3O3 O 3A21 E5CE 19980417003851998041700385SO 1998 4 17 AU980325 219980324G8530653426A13 CYLINDER CESSNA150 150G 2071816CE CONT O200 O200A 17020SO EXH VALVES WORN W K NONE O OTHER ININSP/MAINT 1 AUS 20R005 (AUS) ENGINE CYLINDERS HAD LOW COMPRESSION. INVESTIGATION FOUND WORN EXHAUST VALVE GUIDES AND GLAZED AND OUT OF ROUND CYLINDER BORES. 1H71 3O3 O 3A19 E252 19980417003911998041700391EA 1998 4 17 AU980331 219980326G7322229164 TUBE FACET MA3PA LYC O235 O235H2C 41505EA CARBURETOR SEPARATED W K NONE E VIBRATION/BUFFET LDLANDING 1 AUS 413 DT31958 L24482815 (AUS) CARBURETOR ACCELERATOR PUMP DISCHARGE TUBE SEPARATED AND FELL INTO THE AIRBOX. 3 O E223 19980417003931998041700393GL 1998 4 17 AU980333 319980324G6114C90 HUB CESSNA206 U206G 2073356CE CONT O520 IO520F 17032SO MCAULY3A32C D3A32C90 GL PROPELLER CRACKED W K NONE O OTHER ININSP/MAINT 1 AUS 1182 7710030 (AUS) PROPELLER HUB CRACKED ON FLANGE AREA. INVESTIGATION ALSO FOUND THAT ALL THREE BLADE SOCKETS WERE FILLED WITH `SILASTIC' SEALANT. PERSONNEL/MAINTENANCE ERROR. 1H71 3O3 O A4CE E5CE 5 CP21EA 19980417005631998041700563WP 1998 4 17 CA970521009 219980319G72613615309101 OIL CAP LEAR 35 31A 5170531CE GARRTTTFE731TFE73122B 01518WP LT ENG OIL LOOSE W E ENGINE SHUTDOWN K FLUID LOSS CLCLIMB 1 CA 2946 P99188 (CAN) LOSS OF OIL PRESSURE INDICATION ON LT ENGINE DURING CLIMB. ENGINE PRECAUTIONARY SHUT DOWN CARRIED OUT. FOUND LT ENGINE OIL DIPSTICK CAP NOT SECURE. CLEANED ENGINE, REPLACED OIL CAP PACKING, AND RE-SERVICED ENGINE OIL SYSTEM. 2L72 4F4 FRTA10CE E6WE 19980417005921998041700592CE 1998 4 17 CA970605003 119980319G324640169 WHEEL CLEVELAND 40169 CESSNA441 441 2076020CE GARRTTTPE331TPE33110 01514WP MLG CRACKED W K NONE O OTHER ININSP/MAINT 1 CA 330 P77306 (CAN) OUTBOARD WHEEL HAS A .500 INCH CRACK RUNNING FROM BASE OF BOLT HOLE COUNTER BORE TO INSIDE OF WHEEL .500 INCH ABOVE O-RING AIR SEAL. CRACK ALLOWED TUBELESS TIRE TO SLOWLY DEFLATE. REPLACED. 1L72 3T4 TRTA28CE E4WE 19980417005981998041700598SO 1998 4 17 98ZZZX1456 219980227G8520641931981 BOLT CONT O470 IO470K 17026SO CASE THRU BOLT BROKE D K NONE O OTHER ININSP/MAINT 1 GL17 861591K THRU-BOLT BROKE AFTER 14 HOURS. ENGINE NEVER RAN BEFORE BOLT BROKE. 3 O 3E1 19980417006131998041700613EA 1998 4 17 98ZZZX1471 219980408G8530 ROCKER SHAFT CESSNA172 172R 2072401CE LYC O360 O360F1A6 41514EA NR 3 EXH-INT LOOSE G A UNSCHED LANDING R PARTIAL RPM/PWR LOSS CRCRUISE 1 SW15 2 A DEAD CYLINDER CAUSED AIRCRAFT TO LAND. TROUBLESHOOTING FOUND NR 3 CYLINDER DEAD. WHEN REMOVING THE VALVE COVER, FOUND THE INTAKE AND EXHAUST ROCKER SHAFTS LOOSE AND ONE RETAINING NUT WAS INSIDE THE VALVE COVER. THE ACFT HAD JUST BEEN RETURNED TO SERVICE 2 TACK HOURS EARLIER, THE LOG BOOK SHOWED THAT ALL PUSH ROD SEALS WERE REPLACED DUE TO OIL LEAKS. THE OIL SEALS WERE REPLACED BUT UPON RE-INSTALLATION OF THE ROCKER SHAFT, THE MECHANIC USED STAR WASHERS TO SECURE THE PLAIN NUTS INTO PLACE. THE CONTINENTAL ENGINE MANUALS CALLS FOR A LOCK P/N 50186. NEW LOCKS INSTALLED (24 EACH) ON ALL ROCKER SHAFT RETAINING NUTS AND CRIMP LOCKED AS REQUIRED. NO HARM WAS DONE AND GROUND RUN-UP WAS SATISFACTORY. 1H71 3O3 ONT3A12 E286 19980417006191998041700619SO 1998 4 17 98ZZZX1476 219980303G73229944 PLUG FACET MA45 CESSNA182 182N 2072730CE CONT O470 O470P 17026SO CARBURETOR BOWL MISSING DLA A UNSCHED LANDING A FLAME/FIRE CLCLIMB 1 WP239109G1752 BD175233 18260649 21119771R FOLLOWING TAKEOFF, ENGINE RUNNING ROUGH AND FIRE ERUPTED. AFTER LANDING, INSPECTION FOUND FIRE IN ENGINE COMPARTMENT DUE TO MISSING DRAIN PLUG FROM CARBURETOR BOWL. NO SAFETY WIRE EVIDENT. 1H71 3O3 ONT3A13 E273 19980417006641998041700664CE 1998 4 17 CA971104007 119980331G3233ADI79990035 PISTON ROD ADI79990033 BEECH 200 200BEECH 1152920CE PWA PT6 PT6A41 52043EA MLG ACTUATOR LEAKING W K NONE O OTHER ININSP/MAINT 1 CA 3967 ADI203M PCE81498 (CAN) MAIN LANDING GEAR ACTUATOR LEAKING FLUID BETWEEN PISTON ROD AND ACTUATOR HOUSING. DISASSEMBLY OF THE ACTUATOR REVEALED CORROSION ON ROD AFFECTED THE"O" RING CAUSING THE HYDRAULIC LEAK. NEW ACTUATOR INSTALLED. 1L72 4T4 T A24CE E4EA 19980417007491998041700749NE 1998 4 17 98ZZZX1490 219980406G7321105970 NOZZLE JFC3123 BAG BAE146BAE146200A 1500266EU LYC ALF502ALF502R 41580NE FCU PUMP FRACTURED D O OTHER Y ENGINE STOPPAGE CRCRUISE 1 WP05 12803920 F10956 FUEL CONTROL FAILURE. ENGINE SHUT DOWN IN-FLIGHT. SUSPECT CAUSE: PUMP NOZZLE IS FRACTURED CAUSING SEVERE CONTAMINATION. 2H74 4F4 FRTA49EU E6NE 19980424000871998042400087EA 1998 4 24 98ZZZX1518 219980301G8550 OIL PUMP GULSTMAA1 AA1A 0630710SO LYC O235 O235C2C 41505EA ENGINE OIL WRONG GEARS D K NONE W INADEQUATE Q C ININSP/MAINT 1 NE017255L AA1A0455 L1139615 ANNUAL INSPECTION RECORD CHECK FOUND AD 75-08-09 C/W NOV 1976. REPLACED GEARS 6-7-78. ENGINE OVERHAULED, NO DETAILS GIVEN. 6-30-79 - ENGINE REMOVED AND STORED. TT 697.4 HOURS. 6-30-84. ENGINE INSTALLED IN N 7255L. AD 81-18-04R2. SIGNED OFF ON AD LIST AS DUE AT 2,000 HRS OR OVERHAUL. IN C/W AD 96-09-10, ENGINE REMOVED AND GEARS INSPECTED AND FOUND TO BE SINTERED IRON. BOTH GEARS REPLACED WITH HARDENED STEEL. 1L71 3O3 O A11EA E223 19980424000911998042400091EA 1998 4 24 98ZZZX1522 219980227G7230230064802 PLATE 210193006 LYC ALF502ALF502* 41580EA NR 2 BEARING MISMARKED B C7GRK NONE W INADEQUATE Q C ININSP/MAINT 1 SO13 FACE PLATE WAS IDENTIFIED AS 2-300-649-02, PART WAS ACTUALLY 2-300-648-02. ASSEMBLY WAS RETURNED BY CUSTOMER FOR HAVING WRONG P/N INSTALLED. NOTIFIED MANUFACTURER OF MIS-IDENTIFICATION TO INITIATE CORRECTIVE ACTION. PERFORMED STOCK SWEEP, NO OTHERS FOUND MISIDENTIFIED. NOTIFIED CENTRAL DISTRIBUTION CENTER IN PHOENIX TO PERFORM STOCK SWEEP FOR SAME. 4 F E6NE 19980424000931998042400093NE 1998 4 24 98ZZZX1524 219980326G7230410100641 AXIAL ROTOR 410102050 LYC LTS101LTS101650B1 41560NE BLADE ROOT SEPARATION B C7GRK NONE O OTHER ININSP/MAINT 1 SO13 787 105244 LE41116AE AXIAL BLADE SEPARATION AT BLADE ROOT AREA - ENGINE FAILURE. INVESTIGATION ONGOING. CORRECTIVE ACTION IN PROGRESS. 3 U E5NE 19980424000941998042400094GL 1998 4 24 98ZZZX1525 219980330G72306896024 EJECTOR NOZZLE ALLSN 250C 250C28B 03013GL NR 1 BROKEN B XZNRK NONE O OTHER ININSP/MAINT 1 WP07 CAE860172 EJECTOR TUBE ASSY HAD TOP TUBE BROKEN OFF CAUSING DAMAGE TO IMPELLER REQUIRING IMPELLER TO BE SCRAPED, PIECES OF TUBE WERE FOUND IN COMBUSTOR AND TURBINE NR 1 NOZZLE. TUBE ROUTED TO ALLISON ENGINE CO. FOR ANALYSIS. OPERATOR ROUTED ENGINE TO REPAIR STATION FOR FOREIGN OBJECT DAMAGE REPAIR. 3 U E1GL 19980424000951998042400095NE 1998 4 24 98ZZZX1526 219980326G7240213139003 COMBUSTION LINER 91C242 LYC LF507 LF5071F NE ENGINE DISTORTED B C7GRK NONE O OTHER ININSP/MAINT 1 SO13 458 LF7367 UPON TEARDOWN OF THE ENGINE FOR AN UNRELATED ISSUE, IT WAS DISCOVERED THE COMBUSTION LINER WAS DISTORTED DUE TO BLOCKED COOLING HOLES. SUSPECT PLASMA COATING OVERSPRAY DURING OVERHAUL. INVESTIGATION IS ONGOING. SERVICE BULLETIN IS PENDING. 4 F E6NE 19980424002901998042400290EA 1998 4 24 HAIGJQR0184 219980410G7210M274263215B RING BELL 212 212 1181420SW PWA PT6T PT6T3 52045EA GR BOX CORRODED H GJQRK NONE O OTHER ININSP/MAINT 1 FS0198W 782 35100 RETAINING RING CORRODED REPLACED WITH NEW PARTS FROM BHT 1G71 4U4 U H4SW E22EA 19980424003421998042400342EA 1998 4 24 98ZZZX1548 219980410G852011B200511DL CRANKCASE CESSNA177 177RG 2073709CE LYC O360 IO360A1B6 41514EA NR 2 CYLINDER CRACKED D K NONE K FLUID LOSS ININSP/MAINT 1 EA252773V3900 1300 177RG0694 L1537951A DISCOVERED 5.50 INCH LONG CRACK ON CRANKCASE BELOW NR 2 CYLINDER FLANGE. CRACK WAS APPROXIMATELY 1 INCH BELOW BOTTOM FLANGE OF CYLINDER AND FOLLOWED ENTIRE BOTTOM CIRCUMFERENCE OF CYLINDER. CRACK WAS DISCOVERED AFTER PILOT REPORT OF A LARGE OIL LEAK FROM FORWARD LEFT SIDE OF COWLING AND STREAKING UNDER AIRCRAFT BELLY. 1H71 3O3 O A20CE 1E10 19980424003451998042400345SO 1998 4 24 98ZZZX1551 119980326G71208401002 MOUNT PIPER PA46 PA46310P 7104605SO CONT O520 TSIO520BE 17040SO FIREWALL RT CRACKED B ABONRK NONE O OTHER ININSP/MAINT 1 GL1940PM 1664 4608005 273699R DURING ANNUAL INSPECTION, FOUND ENGINE MOUNT CRACKED ON RT SIDE. CRACK IS LOCATED WHERE NLG HYDRAULIC ACTUATOR ATTACHES TO MOUNT. DESIGN REQUIRES ACTUATOR TO BE POSITIONED SUCH THAT IT STRESSES THE MOUNT. 1L71 3O3 O A25SO E8CE 19980424007691998042400769SO 1998 4 24 98ZZZX1582 219980408G8530 CYLINDER CONT O520 TSIO520H 17040SO NR 2 SEPARATION D K NONE O OTHER ININSP/MAINT 1 NM03 1100 506111 INSPECTION FOUND NR 2 CYLINDER SEPARATED BETWEEN BORE AND HEAD. 3 O E8CE 19980424007771998042400777EA 1998 4 24 98ZZZX1590 219980401G7310LW120980140 TUBE ASSY MOONEYM20 M20J 5870219SW LYC O360 IO360A3B6 41514EA NR 1 CYLINDER BROKEN D O OTHER ERKVIBRATION/BUFFET PARTIAL RPM/PWR LOSS FLUID LOSS NRNOT REPORTED 1 SO16191ER 243252 L2550151A THE PILOT REPORTED A ROUGH ENGINE AND MADE A PRECAUTIONARY LANDING. THE NR 1 CYLINDER FUEL INJECTOR LINE WAS BROKEN AT THE CYLINDER END. RAW FUEL WAS BEING SPRAYED ON THE ENGINE AS IT WAS RUNNING. THERE WAS NO FIRE. THIS IS A COMMON PROBLEM ON THIS INSTALLATION (NR 1 CYL). AD 93-02-05 IS C/W AT EACH 100-HOUR INSPECTION. 1L71 3O3 O 2A3 1E10 19980424007801998042400780EA 1998 4 24 98ZZZX1593 219980301G74144771 MAGNETO SLICK CESSNA172 172L 2072432CE LYC O320 O320E2D 41508EA ENG LT MAG FAILED D K NONE O OTHER ININSP/MAINT 1 SO09269CJ45 9603001 17259512 2841827A MAGNETO WAS INSTALLED AS A NEW UNIT WITH STC SE419CH ON THIS AIRCRAFT ON 4-28-97. THE STC IS THE UNISON ELECTRONIC IGNITION SYSTEM. DURING THE MAG CHECK WITH THE ENGINE RUNNING AND THE MAG SWITCH IN THE LEFT POSITION, THE ENGINE QUIT. OPERATION WAS NORMAL IN RIGHT MAG OR BOTH POSITIONS. AFTER CONTACTING UNISON, THEY SENT A NEW MAG AND SUGGESTED CHANGING THE UNIT OUT. AFTER THIS WAS DONE WITH A NEW MAG, THE OPERATIONAL CHECK OF THE SYSTEM WAS NORMAL. THE UNSERVICEABLE MAG WAS RETURNED TO UNISON. 1H71 3O3 ONT3A12 E274 19980424007991998042400799NM 1998 4 24 98ZZZX1612 219980126G7210 TRANSFER TUBE GULSTM690TP 690A 0141722SW GARRTTTPE331TPE3315251K NM NOSE CASE OIL BROKEN B HAXRE ENGINE SHUTDOWN EJ VIBRATION/BUFFET WARNING INDICATION CRCRUISE 1 SW1176WA 11342 P06944 CHIP LIGHT CAME ON IN-FLIGHT (VIBRATION). ENGINE SHUT DOWN IN-FLIGHT. FOUND METAL IN OIL SAMPLE. REMOVED NOSE CASE, FOUND OIL TRANSFER TUBE BROKEN OFF, BROKEN RING GEAR, AND ALL PLANETARY GEARS DAMAGED. SENT ENGINE TO AIRSEARCH FOR REPAIR. 188.5 HOURS AFTER GEARBOX INSPECTION. 1H72 3T4 T 2A4 E2WE 19980430002481998043000248SO 1998 4 30 98ZZZX765 219980210G8530 CRANKSHAFT CONT C145 C145* 17012SO CTWT JOURNAL BROKEN G A A UNSCHED LANDING O OTHER CRCRUISE 1 NE03 11 CRANKSHAFT BROKE AT THE COUNTERWEIGHT JOURNAL AREA IN-FLIGHT. PART WAS SERVICED BY AIR AGENCY PRIOR TO INSTALLATION DURING OVERHAUL. PART WILL BE SENT TO CONTINENTAL FOR EVALUATION. 3 O E253 19980430002491998043000249EA 1998 4 30 98ZZZX766 219980210G8520 CRANKSHAFT LYC O235 O235* 41505EA JOURNAL RADII CRACKED G K NONE O OTHER ININSP/MAINT 1 NE03 CRANKSHAFT WAS REMOVED FROM INVENTORY FOR PRECAUTIONARY MPI. RANK WAS PROCESSED BY AIR AGENCY AND WAS FOUND CRACKED AT THE JOURNAL RADII. 3 O E223 19980430002501998043000250EA 1998 4 30 98ZZZX767 219980210G852075006 CRANKSHAFT LYC O320 O320* 41508EA JOURNAL RADII CRACKED G K NONE O OTHER ININSP/MAINT 1 NE03 121682 PART WAS REMOVED FROM INVENTORY FOR MPI FOLLOWING ADVISORY THAT AIR AGENCY MAY HAVE IMPROPERLY MACHINED CRANKSHAFT. PART WAS FOUND TO HAVE CRACKS IN THE HOURNAL RADII. PART IS NOT SERVICEABLE. 3 O E274 19980430002561998043000256EA 1998 4 30 98ZZZX773 219980124G8520LW10842 CRANKSHAFT PIPER PA60 PA60601P 7106012NM LYC O540 IO540S1A5 41532EA NR 2 JOURNAL FAILED D AE UNSCHED LANDING ENGINE SHUTDOWN E VIBRATION/BUFFET CLCLIMB 1 NE03TGWOW882 8 61P068379633L1959748A PILOT (OWNER) DEPARTING FROM AIRPORT AND CLIMBING THROUGH 4,000 FEET NOTED LOUD BANG AND SEVERE VIBRATION FROM LT ENGINE. ENGINE SHUT DOWN AND SECURED AND SAFE LANDING MADE. DISASSEMBLY OF ENGINE REVEALED CRANKSHAFT BROKEN. BREAK OCCURRED AT THE REAR CHEEK OF THE NR 2 ROD JOURNAL IN THE RADII. CRANKCASE, RODS, CAMSHAFT AND CLYINDERS ALL NOW N.G. 1M72 3O3 ORTA17WE 1E4 19980430002571998043000257EA 1998 4 30 98ZZZX774 219980210G8520LW17577 CRANKSHAFT LYC O360 LIO360C1E6 41515EA JOURNAL RADII CRACKED G K NONE O OTHER ININSP/MAINT 1 NE03 CRANKSHAFT WAS REMOVED FROM INVENTORY FOR MPI FOLLOWING ADVISORY THAT IMPROPER MACHINE WORK WAS PERFORMED BY AIR AGENCY. SHAFT WAS FOUND TO HAVE CRACKS AT THE JOURNAL RADIUS. THIS CRANKSHAFT WAS RE-WORKED BY FAA - AIR AGENCY AND IS SCRAP. 3 O 1E10 19980430002581998043000258EA 1998 4 30 98ZZZX775 219980210G8520LW17577 CRANKSHAFT PIPER PA34 PA34200 7103405SO LYC O360 LIO360C1E6 41515EA JOURNAL RADII CRACKED G K NONE O OTHER ININSP/MAINT 1 NE0315008 220 347250346 PART WAS REMOVED FOR MPI AS A PRECAUTION. THIS CRANKSHAFT WAS RE-WORKED BY AIR AGENCY AND WAS FOUND TO HAVE CRACKS IN THE JOURNAL RADII. 1L72 3O3 O A7SO 1E10 19980430002601998043000260SO 1998 4 30 98ZZZX777 219980128G855007560201 PISTON CESSNA172 172F 2072414CE CONT O300 O300D 17022SO OIL FILTER ADAPTMISMANUFACTURED BS GJ1RK NONE W INADEQUATE Q C ININSP/MAINT 1 NE035772R 17253387 OIL FILTER ADAPTER LONGITUDINAL HOLE IN PISTON DOES NOT INTERSECT HOLES DRILLED THROUGH THE CIRCUMFERENCE. NO OIL IS ALLOWED TO THE FILTER ELEMENT. REPLACED PISTON, OPERATION RETURNED TO NORMAL. SUBMITTER STATED PART WAS NOT MADE ACCORDING TO PRINT. 1H71 3O3 ONT3A12 E253 19980430004351998043000435EA 1998 4 30 98ZZZX972 219980216G7322MA4SPA CARBURETOR CESSNA172 172N 2072434CE LYC O360 O360A4M 41514EA THROTTLE ARM DEFECTIVE D A K NONE W INADEQUATE Q C ININSP/MAINT 1 EA1391QS 17268167 INSPECTION OF THE CARBURETOR DETERMINED THE THROTTLE ARM BECAME LOOSE ON THE SHAFT. THIS CONDITION RESULTED IN LOSS OF CONTROL OF ENGINE RPM. THE NUT AND COTTER PIN WERE INTACT. SUSPECT THE ORIGINAL INSTALLATION WAS NOT PROPERLY INSTALLED AND TORQUED ALLOWING THE ARM TO BECOME LOOSE. IT IS SUGGESTED THAT CORRECT INSTALLATION AND TORQUE WOULD PREVENT THIS CONDITION. 1H71 3O3 ONT3A12 E286 19980430004491998043000449GL 1998 4 30 98ZZZX986 219980224G732123057344 FUEL CONTROL BENDIX 252464429 ALLSN 250C 250C20B 03013GL ENGINE MALFUNCTIONED D K NONE O OTHER ININSP/MAINT 1 WP23 639 BR55894 AE406008 FUEL CONROL UNIT WENT FROM 63 PERCENT TO 80 PERCENT AT FLIGHT IDLE SETTING, UNCOMMANDED. 3 U E4CE 19980430004531998043000453SO 1998 4 30 98ZZZX990 219980210G8530537750 BOLT 654654A1 CESSNA421 421C 2076016CE CONT O520 GTSIO520L 17032SO NR 5 CYL ROCKER FAILED D K NONE K FLUID LOSS ININSP/MAINT 1 NE01886041500 421C0604 292083R PILOT REPORTED OIL LEAKING FROM RIGHT ENGINE. FOUND HOLE IN NR 5 CYLINDER ROCKER COVER. HEAD OF BOLT BROKE OFF THAT ATTACHES ROCKER ARM AND SHAFT TO CYLINDER ASSEMBLY. NEW BOLTS INSTALLED AND NEW ROCKER COVER. 1L72 3O3 O A7CE E7CE 19980430011691998043001169NE 1998 4 30 98ZZZX1096 219980307G7261 SEAL LEAR 25 25 5170506CE GE CJ610 CJ6106 30006NE OIL FILLER NECK FAILED E E ENGINE SHUTDOWN JK WARNING INDICATION FLUID LOSS CRCRUISE 1 GL2328CK 6642 045 211205 RIGHT ENGINE SHUT DOWN IN-FLIGHT DUE TO LOW OIL PRESSURE. REPLACED FILLER NECK SEAL, INSPECTED OIL FILTER AND CHIP DETECTOR. SERVICED WITH MOBILE JET II. GROUND RUN, LEAKED CHECKED, AND RETURNED TO SERVICE. 2L72 4J4 J A10CE 1E16 19980501000061998050100006GL 1998 5 1 98ZZZX1619 219980409G732323057870 GOVERNOR HUGHES369 369D 4470706WP ALLSN 250C 250C20B 03013GL POWER TURBINE MALFUNCTIONED B LS1RK NONE O OTHER ININSP/MAINT 1 EA131097J 301 90081D CAE833805 PT GOVERNOR WAS SURGING BELOW LIMITS. PT GOVERNOR REPLACED, OPS CHECK OK. AIRCRAFT RETURNED TO SERVICE. CNTRL NR 98-4-5. 1G71 3U3 U H3WE E4CE 19980501000071998050100007GL 1998 5 1 98ZZZX1620 219980409G732223056936 FUEL CONTROL BELL 206 206B 1181511SW ALLSN 250C 250C20B 03013GL ENGINE DEFECTIVE B LS1RK NONE O OTHER ININSP/MAINT 1 EA13206BX 1730 2872 CAE833239 FUEL CONTROL BEARING - BLUE GREASE WASHED OUT. SENT FOR REPAIR. CNTRL NR 98-4-7. 1G71 3U3 U H2SW E4CE 19980501000131998050100013EA 1998 5 1 98ZZZX1626 219980414G8510LW10551 RING GEAR PIPER PA28 PA28181 7102807SO LYC O360 O360A4M 41514EA STARTER WRONG PART D A K NONE W INADEQUATE Q C ININSP/MAINT 1 WP074149Y43 2843128 L3592736A DURING ROUTINE INSPECTION, MECHANIC NOTICED THERE WAS ABNORMAL AMOUNT OF WEAR ON THE STARTER RING GEAR FOR ONLY HAVING 43 HOURS TT ON THE PART. UPON FURTHER INSPECTION, FOUND THE WRONG P/N RING GEAR INSTALLED. THE CORRECT RING GEAR IS P/N 72566 WHICH IS FOR A RT ROTATING ENGINE. THE P/N LW-10551 RING GEAR IS FOR A LT ROTATING ENGINE. THIS IS EVIDENCED WHILE SITTING IN THE PILOT SEAT, THE RING GEAR BEVEL (CHAMFER SIDE) SHOULD BE ON THE RIGHT SIDE FOR RT ROTATION, AND LEFT SIDE FOR LT ROTATION. ALTHOUGH THERE WERE WEAR MARKS, SYSTEM OPERATIONS WERE NORMAL. 1L71 3O3 O 2A13 E286 19980508000161998050800016WP 1998 5 8 98ZZZX1639 219980402G723031013731 PLATE LOCK GARRTTTPE331TPE3312 01514WP IMPELLER SHROUD FAILED BS FTURK NONE O OTHER ININSP/MAINT 1 NE05CGHQG P06697C BOLTS ATTACHING THE FIRST STAGE IMPELLER SHROUD TO THE IMPELLER HOUSING WERE FOUND LOOSE AND MISSING DURING A ROUTINE ENGINE INSPECTION. THESE BOLTS USE A LOCK TAB P/N 3101373-1 TO LOCK A MS9489-19 BOLT AND SPACER IN PLACE. REPLACEMENT PARTS WERE ORDERED AND IT WAS FOUND THE LOCK TABS HAVE A LARGER HOLE THAN THE BOLT IT IS SUPPOSED TO LOCK. THE LOCK TAB HOLE MEASURES .224 INCH AND THE BOLT IS .187 INCH. WHEN THE LOCK TAB IS BENT TO LOCK THE BOLT HEAD, THERE IS ENOUGH ROOM FOR THE BOLT TO TURN IF VIBRATION OCCURS. SUGGEST LOCK TAB HOLE DIAMETER IS REDUCED TO PROPERLY LOCK THE BOLT IN PLACE. 3 T E3WE 19980508006421998050800642GL 1998 5 8 HEEA0014004 219980421G72306887619 SEAL 23033191 ALLSN 250C 250C28B 03013GL ENG COMP FAILED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03 CAC70662 CAE860213 COMPRESSOR DISASSEMBLED DUE TO LOW POWER ON TEST CELL. UPON INSPECTION OF COMPRESSOR PARTS NOTED: CRACKED AND FLAKING ON SEAL CARBON OUTER EDGE. INSTALLED A NEW SEAL. 3 U E1GL 19980508008681998050800868NE 1998 5 8 98ZZZX1645 219980415G7230360705 COUPLING LOCK PWA JT8 JT8* 52044NE ENGINE COMP WORN B B97RK NONE O OTHER ININSP/MAINT 1 NE03 82330013 ENGINE COUPLING LOCK HAS MAX WEAR ON OD .010. ACTUAL .012. WEAR EXCEEDS MANUAL LIMITS. RETURNED TO CUSTOMER. 4 F E2EA 19980508008761998050800876EA 1998 5 8 98ZZZX1655 219980406G7322105217 CARBURETOR FACET MA4SPA CESSNA172 172L 2072432CE LYC O320 O320E2D 41508EA FUEL INLET WORN D K NONE K FLUID LOSS ININSP/MAINT 1 SO337201Q3149 548 75008623 17260501 L3287027A FUEL INLET FITTING HAD STRIPED THREADS OUT OF CARBURETOR HOUSING AND LEAKING FUEL. INSTALLED REBUILT PART. 1H71 3O3 ONT3A12 E274 19980508008911998050800891SO 1998 5 8 98ZZZX1670 219980414G8520 CRANKCASE CESSNA206 U206G 2073356CE CONT O520 IO520F 17032SO NR 6 CYL STUD CRACKED D K NONE O OTHER ININSP/MAINT 1 AL03756QP580 U20604274 564851 THE CRANKCASE SPLIT FROM NR 6 CYLINDER HOLE TO OIL FILLER HOLE ON TOWARD TO THE FRONT OF THE CASE. THIS OCCURRED IN CONJUNCTION WITH THE CYLINDER MOUNTING STUD IN THIS IMMEIDATE AREA FAILING. THE CIRCUMSTANCES UNDER WHICH IT OCCURED WERE 'NORMAL OPERATION'. SUSPECT CAUSE - OVERTORQUEING OF SAID CYLINDER STUD BOLT. 1H71 3O3 O A4CE E5CE 19980508008961998050800896EA 1998 5 8 98ZZZX1675 219980409G8530 VALVE GUIDE CESSNA172 172P 2072436CE LYC O320 O320D2J 41508EA NR 3 CYL EXH VLVDEFECTIVE D CD ABORTED TAKEOFF RETURN TO BLOCK O OTHER TOTAKEOFF 1 SW999477L 1400 17276562 L1045839A ON TAKEOFF, A MOMENTARY ENGINE ROUGHNESS PROMPTED THE PILOT TO ABORT TAKEOFF. THE AIRCRAFT EXCEEDED RUNWAY LENGTH AND STRUCK AN ANTENNA. INSPECTION OF THE ENGINE REVEALED A BUILD-UP OF CARBON IN THE NR 3 EXHAUST VALVE GUIDE. NOTE: ALL EXHAUST VALVE GUIDES WERE REAMED APPROXIMATELY 650 HRS PRIOR TO INCIDENT. AFTER INCIDENT, ENGINE RUN-UP WAS NORMAL. 1H71 3O3 ONT3A12 E274 19980508009191998050800919GL 1998 5 8 98ZZZX1697 219980417G7414 DRIVE COUPLING AMTR SONERISONERAI2 GL AMTRVWVOLKS VW2200VOLKS GL ENGINE MAGNETO FAILED G A A UNSCHED LANDING Y ENGINE STOPPAGE CRCRUISE 1 GL11247RJ 999 THE CAST ALUMINUM MAGNETO DRIVE COUPLING WHICH IS KEYED TO THE FLYWHEEL BROKE INTO FOUR PIECES. THE RESULTANT FRICTION MELTED AND FUSED A PORTION OF THE BROKEN PIECES OF THE COUPLING TO THE STATIONARY CROSS MEMBER ENGINE MOUNT. THIS FAILURE OF THE MAGNETO COUPLING RESULTED IN THE FAILURE OF THE ENGINE DURING CRUISE AND ULTIMATELY THE ACCIDENT WHICH DESTROYED THE AIRCRAFT AND INJURED THE PILOT. THE COUPLING BROKE AT THE KEYWAYS AND SHOWED EVIDENCE OF PRE-EXISTING CRACKS POSSIBLY CASTING FLAWS. SUBMITTER RECOMMENDED THE MAGNETO DRIVE COUPLING BE MILLED FROM A SOLID PIECE OF HIGH GRADE ALUMINUM AND ALL EDGES BE RADIUSED TO PREVENT CRACKING. 1M71 3O3 O EXPA1M71EXP3O 19980508011291998050801129GL 1998 5 8 HEEA0014091 219980430G7230230052711 SPLINE ADAPTER ALLSN 250C 250C30S 03013GL ENGINE MIS MFG E HEEAK NONE W INADEQUATE Q C ININSP/MAINT 1 SW03 RECEIVING INSPECTION REVEALED: MEASURED (.9853) .0002 BELOW SPECS .9855 - .9860 ON SPLINED ADAPTER O.D. 3 U E1GL 19980508014141998050801414NE 1998 5 8 CA980407014 219980331G7200 ENGINE BOEING727 727212 138407GNM PWA JT8 JT8D17 52049NE NR 2 FAILED W CEFDABORTED TAKEOFF ENGINE SHUTDOWN ACTIVATE FIRE EXT. RETURN TO BLOCK AT FLAME/FIRE ENGINE CASE PENETRATION TOTAKEOFF 1 CA 4289513899 689976 (CAN) DURING TAKEOFF, NR 2 ENGINE FAILED WITH SUBSEQUENT FIRE WARNING. TAKEOFF WAS REJECTED. FIRE DRILL AND EVACUATION CARRIED OUT. FURTHER REPORT TO FOLLOW. PART TC: 19,706. 2L73 4F4 F A3WE E2EA 19980515000681998051500068EA 1998 5 15 CA980407007 219980212G8500 ENGINE BBAVIA8 8GCBC 1220803SW LYC O360 O360C2E 41514EA POWER SECT MAKING METAL W K NONE O OTHER ININSP/MAINT 1 CA 1112 L2691136A (CAN) ENGINE REMOVED DUE TO NON-FERROUS METAL IN THE OIL SCREEN. ENGINE SHIPPED FOR REPAIR. REPORT TO FOLLOW. 1H71 3O3 O A21CE E286 19980515002681998051500268EA 1998 5 15 98ZZZX1716 219980401G7314LW15473 PUMP PIPER PA32 PA32300 7103212SO LYC O540 IO540S1A5 41532EA ENGINE FUEL LOOSE D K NONE W INADEQUATE Q C ININSP/MAINT 1 AL0530004 327840120 RL2044548A UPON VISUAL INSPECTION OF NEWLY OVERHAULED ENGINE, FOUND ALL OF THE BOLTS SECURING THE BOTTOM DIAPHRAGM PLATE TO THE FUEL PUMP BODY WERE LOOSE, AT LEAST .0312 INCH OF SPACE COULD BE SEEN UNDER BOLT HEAD. THIS WAS A NEW PUMP INSTALLED BY ENGINE SHOP. SUBMITTER ADVISED INSPECTING EVEN NEW PARTS FOR DEFECT. 1L71 3O3 O A3SO 1E4 19980515002741998051500274SO 1998 5 15 98ZZZX1722 119980409G7430103572001E SWITCH PIPER PA28 PA28181 7102807SO LYC O360 O360* 41514EA IGNITION MALFUNCTIONED H K NONE O OTHER ININSP/MAINT 1 EA05814971926 288090227 SUBMITTER STATES AS A STANDARD PRACTICE AT RUN-UP, TEST IGNITION SWITCHES IN THE 'OFF' AND PAST 'OFF' POSITIONS AS STATED BY TCM AD 76-07-12 REGARDLESS OF WHETHER IT APPLIES OR NOT. THIS SWITCH DID NOT APPLY, YET FAILED THE PAST 'OFF' TEST. IT HAD A 4 NUMBER DATE CODE OF 8148 AND CAME OUT OF A 1980 AIRCRAFT. 1L71 3O3 O 2A13 E286 19980515002791998051500279GL 1998 5 15 98ZZZX1725 219980429G731047086 FILTER ALLSN 250C 250C20B 03013GL FUEL NOZZLE CONTAMINATED D K NONE O OTHER ININSP/MAINT 1 SW99 1270 AT17547 FOUND SOME CONTAMINATION ON FILTER WHERE SCREEN ATTACHES TO BASE. ALSO, BLACK PARTICULATES ON BASE FACING INLET OF FUEL. CONTAMINATION CLEANED BY ULTRASONIC METHOD GOOD. 3 U E4CE 19980515002931998051500293EA 1998 5 15 98ZZZX1739 219980418G7414ES103571651 COIL BENDIX ENSTRMF28 F28A 3300406GL LYC O360 HIO360C1A 41514EA ENG LT MAG FAILED D K NONE R PARTIAL RPM/PWR LOSS ININSP/MAINT 1 NE0157SJ 550 278 L1238751A COMPLAINT WAS 'MISFIRE' AT CRUISE POWER. SYMPTOM WAS NOSE YAW AT ERRATIC INTERVALS. NORMAL PREFLIGHT RUN-UP CHECK SHOWED NO PROBLEM. MAGNETO CHECK AT HOVER POWER CAUSED ENGINE FAILURE WHEN 'LEFT' MAGNETO POSITION WAS SELECTED. RECORDS INDICATE THIS COIL HAS BEEN IN SERVICE AT LEAST SINCE ENGINE MAJOR OVERHAUL IN 1987. 1G71 3O3 O H1CE 1E10 19980515004351998051500435GL 1998 5 15 98ZZZX1740 219980424G72306890550 COMPRESSOR HUGHES369 369D 4470706WP ALLSN 250C 250C20B 03013GL ENGINE FOD B LS1RK NONE K FLUID LOSS ININSP/MAINT 1 EA13369AW8878 470117D CAC33463 COMPRESSOR STALLING. FOUND 1ST STAGE BEARING LEAKING. APPEARS THAT COMPRESSOR HAD FOD. REMOVED FROM AIRCRAFT AND OVERHAULED COMPRESSOR INSTALLED. CONTROL NR 98-4-11. 1G71 3U3 U H3WE E4CE 19980515004961998051500496GL 1998 5 15 HAI00000002 219980508G753223005366 BLEED VALVE BELL 206 206L3 1182108SW ALLSN 250C 250C30P 03013GL ENGINE FAILED H K NONE O OTHER ININSP/MAINT 1 FS01899BH 51089 ENGINE FAILED POWER ASSURANCE CHECK DURING TEST FLIGHT FOLLOWING INSTALLATION OF ENGINE FOLLOWING EXTENDED MAINTENANCE INCLUDING BLEED VALVE OVERHAUL. INSTALLED REPLACEMENT OVERHAULED BLEED VALVE AND ENGINE TESTED AT +10% 1G71 3U3 U H2SW E1GL 19980515009431998051500943GL 1998 5 15 98ZZZX1788 219980401G72506851531 NOZZLE BOLKMS105 BO105S 5626006EU ALLSN 250C 250C20 03013GL NR 4 CRACKED B TI1RK NONE O OTHER ININSP/MAINT 1 SW05911LF182 ER20738 S663 CRACKED DIAPHRAGM. REMOVED AND REPLACED. 1G72 3U3 U H3EU E4CE 19980515009441998051500944GL 1998 5 15 98ZZZX1789 219980401G72506878498 NOZZLE BOLKMS105 BO105S 5626006EU ALLSN 250C 250C20 03013GL NR 2 FAILED B TI1RK NONE O OTHER ININSP/MAINT 1 SW05911LF182 X46696 S663 NR 1 BLADE PATH BREAKING OUT NOZZLE NR 2. REMOVED AND REPLACED. 1G72 3U3 U H3EU E4CE 19980515009751998051500975EU 1998 5 15 98ZZZX1820 119980327G733210593910 SWITCH BOLKMS105 BO105S 5626006EU ALLSN 250C 250C20B 03013GL DIFF PRESS FAILED B TI1RK NONE W INADEQUATE Q C ININSP/MAINT 1 SW05 2201 DIFFERENTIAL PRESSURE SWITCH DEFECTIVE. INSTALLED ON AIRCRAFT AND DID NOT FUNCTION. REMOVED AND REPLACED. 1G72 3U3 U H3EU E4CE 19980515009771998051500977GL 1998 5 15 98ZZZX1822 219980330G732125490923 FUEL CONTROL SKRSKYS76 S76 8143010NE ALLSN 250C 250C30 03013GL ENGINE DEFECTIVE B TI1RK NONE W INADEQUATE Q C ININSP/MAINT 1 SW05 85140002 FUEL CONTROL OUT OF STOCK OVERHAUL. ENGINE WOULD NOT GO ABOVE 30 PERCENT OR 500 DEGREES CELSIUS. HANGS. REMOVED AND REPLACED. 1G72 3U3 U H1NE E1GL 19980522000301998052200030SO 1998 5 22 98ZZZX1852 219980430G732230764 FLOAT FACET 10396512 CESSNA180 180C 2072608CE CONT O470 O470L 17026SO CARBURETOR DETACHED B KZ3RK NONE K FLUID LOSS ININSP/MAINT 1 WP079208T925 H236694 50708 804379L4 WEAR WHERE CARBURETOR FLOAT NEEDLE RIDES. PIVOT POINT VERY LOOSE. FLOAT DETACHED. PRECISION HAS NEW FLOAT THAT IS COMPOSITE. THE ONLY INDICATION WAS THAT THE CARBURETOR WAS DRIPPING AFTER A FLIGHT. 1H71 3O3 O 5A6 E273 19980522000331998052200033EA 1998 5 22 98ZZZX1855 219980430G8520L18639 GEAR LOCKPLATE LW17281 PIPER PA44 PA44180 7104402SO LYC O360 O360A1H 41514EA CRANKSHAFT BROKEN B OG5RK NONE O OTHER ININSP/MAINT 1 GL21191ND2206 296 4495003 LW2269136A DURING SCHEDULED ENGINE INSPECTION, CRANKSHAFT LOCK TAB WAS FOUND IN THE OIL SUMP SCREEN. REMOVED SUMP AND ACCESSORY HOUSING TO VERIFY. TAB ON BOLT WAS CONFIRMED BROKEN. CRANKSHAFT GEAR BOLT WAS FOUND TO HAVE MINIMAL TORQUE REMAINING. (LESS THAN 100 INCH/POUND). NEW BOLT AND LOCKPLATE INSTALLED PER LYCOMING INSTRUCTIONS AND RE-ASSEMBLED ENGINE. ENGINE HAS 295.6 HOURS SINCE FACTORY OVERHAUL ON 10-21-97. 1L72 3O3 O A19S0 E286 19980522000361998052200036EA 1998 5 22 98ZZZX1858 219980506G8520 CAMSHAFT CESSNA182 TR182 2072735CE LYC O540 O540L3C5 41532EA LOBES WORN D K NONE O OTHER ININSP/MAINT 1 SW996341S 1482 R18201662 L2152240A ENGINE HAS LOW POWER. REMOVED CYLINDERS FOR TOP OVERHAUL AND FOUND CAM HAD BAD LOBES. TBO ON THIS ENGINE IS 2,000 HOURS. 1H71 3O3 O 3A13 E295 19980522000391998052200039SO 1998 5 22 98ZZZX1861 219980411G8520626168 CONNECTING ROD CESSNA175 175 2072502CE CONT O300 GO300A 17022SO CYL NR 2 FAILED D O OTHER ERKVIBRATION/BUFFET PARTIAL RPM/PWR LOSS FLUID LOSS NRNOT REPORTED 1 SO067111M1233 55411 101631AR CONNECTING ROD BROKE AT PISTON PIN AREA. REMAINING POSTION OF ROD PUNCHED HOLE IN CRANKCASE, DAMAGED PISTON, AND RESULTED IN ENGINE SHUT DOWN. 1H71 3O3 ONT3A17 E298 19980522000541998052200054NE 1998 5 22 98ZZZX1875 219980505G7250804131 CASE 804127 PWA JT8 JT8D217A 52053NE ENGINE CRACKED B RA1RK NONE O OTHER ININSP/MAINT 1 SW05 NX7298 717369 ENGINE REMOVED FROM SERVICE DUE TO TURBINE FAILURE. DISASSEMBLY REVEALED HPC AND TURBINE FAILURE DUE TO C-8 SHELF CRACK FAILURE. 4 F E9NE 19980522002311998052200231SO 1998 5 22 AU980334 219980123G8530643873 VALVE 653443A13 CESSNA182 182P 2075816CE CONT O470 O470R 17026SO ENGINE EXHAUST WORN W K NONE O OTHER ININSP/MAINT 1 AUS 222760 (AUS) ENGINE EXHAUST VALVES P/N 643873 (3 OFF) AND VALVE GUIDE P/N 643767 (1 OFF) WORN BEYOND LIMITS. CAM FOLLOWERS (5 OFF) P/N 646277 (EXHAUST) AND P/N 628488 (INLET) CORRODED ON FACE. PART TC: 171. 1H71 3O3 ONTTA13 E273 19980522002331998052200233NM 1998 5 22 AU980336 119980217G5755BN138 BRACKET 651734748 BOEING727 72777C 1380420NM PWA JT8 JT8D15 52051NE NR 2 SPOILER FAILED W K NONE F FLT CONT AFFECTED CRCRUISE 1 AUS 417 BN138 (AUS) LEFT NR 2 SPOILER ACTUATOR ATTACHMENT BRACKET FAILED. SUSPECT CAUSED BY INCORRECT RIGGING. 2L73 4F4 F A3WE E2EA 19980522002361998052200236NE 1998 5 22 AU980339 219980320G7250 LOCK BAG BAE146BAE146100A 1500260EU LYC ALF502ALF502R5 41580NE NR 2 ENGINE MISINSTALLED W A K NONE O OTHER ININSP/MAINT 1 AUS LF05156 (AUS) NR 2 ENGINE 4TH TURBINE RETAINING NUT SEPARATED DUE TO INCORRECT CRIMPING OF THE LOCKING CUP. PERSONNEL/MAINTENANCE ERROR. 2H74 4F4 FRTA49EU E6NE 19980522002381998052200238EU 1998 5 22 AU980341 119980320G3213 AXLE GROB G115 G115C 1660303EU LYC O235 O235H2C 41505EA LT MLG CRACKED W K NONE O OTHER ININSP/MAINT 1 AUS L24482815 (AUS) LT AND RT MAIN LANDING GEAR AXLES CRACKED. 1L71 3O3 ONTA57EU E223 19980522002391998052200239EU 1998 5 22 AU980342 119980320G3213 AXLE GROB G115 G115C 1660303EU LYC O235 O235H2C 41505EA RT MLG CRACKED W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) LT AND RT MAIN LANDING GEAR AXLES CRACKED. 1L71 3O3 ONTA57EU E223 19980522002401998052200240EU 1998 5 22 AU980343 119980320G3213 AXLE GROB G115 G115C 1660303EU LYC O235 O235H2C 41505EA LT MLG CRACKED W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) LT AND RT MAIN LANDING GEAR AXLES CRACKED. 1L71 3O3 ONTA57EU E223 19980522002411998052200241EU 1998 5 22 AU980344 119980320G3213 AXLE GROB G115 G115C 1660303EU LYC O235 O235H2C 41505EA RT MLG CRACKED W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) LT AND RT MAIN LANDING GEAR AXLES CRACKED. 1L71 3O3 ONTA57EU E223 19980522002431998052200243EU 1998 5 22 AU980346 119980320G3213 AXLE GROB G115 G115C 1660303EU LYC O235 O235H2C 41505EA RT MLG CRACKED W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) LT AND RT MAIN LANDING GEAR AXLES CRACKED. 1L71 3O3 ONTA57EU E223 19980522002461998052200246 1998 5 22 AU980349 119980318G7603115C7100 CABLE LYC O360 O360A1F6 41514EA POWER LEVER FAILED W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) ENGINE THROTTLE CABLE OUTER GUIDE TUBE SEPARATED FROM INNER CABLE AT ENGINE END. PART TC: 954. 3 O E286 19980522002471998052200247 1998 5 22 AU980350 119980326G716011159 CABLE LYC O360 O360A1F6 41514EA ENGINE AIR INTAKDISTORTED W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) CARBURETOR HEAT CABLE THREADED SHAFT BENT. PART TC: 1,055. 3 O E286 19980522002481998052200248CE 1998 5 22 AU980351 119980324G32131241110200 BEARING CESSNA210 210K 2073446CE CONT O520 IO520L 17032SO LT MLG TRUNNION FAILED W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) LT MAIN LANDING GEAR AFT TRUNNION SPHERICAL BEARING OUTER RACE SHATTERED. INCORRECT BEARING FITTED. A BUSH SHOULD BE FITTED IN THIS AREA AND NOT A SPHERICAL BEARING. PERSONNEL/MAINTENANCE ERROR. UNAPPROVED PART. 1H71 3O3 O 3A21 E5CE 19980522002491998052200249 1998 5 22 AU980352 119980326G7603115C7100 CABLE LYC O360 O360A1F6 41514EA POWER LEVER FAULTY W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) ENGINE THROTTLE CABLE OUTER GUIDE TUBE SEPARATED FROM INNER CABLE AT ENGINE END. PART TC: 1,055. 3 O E286 19980522002501998052200250CE 1998 5 22 AU980353 119980324G571121100015 SPAR CESSNA210 210K 2073446CE CONT O520 IO520L 17032SO WING ATTACH LUG CORRODED W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) WING SPAR ASSEMBLY CONTAINED DEEP PITTING CORROSION ON THE LOWER WING ATTACHMENT LUG. CAUSED BY A BROKEN AND RUSTY SCAT HOSE WIRE RESTING ON THE SPAR. 1H71 3O3 O 3A21 E5CE 19980522002521998052200252EU 1998 5 22 AU980355 119980331G324648290 BEARING AIRBUS300 A300B4203 3930306EU GE CF6 CF650C2 30018NE NR 6 WHEEL FAILED W K NONE B SMOKE/FUMES/ODORS/SPARKS TXTAXI/GRND HDL 1 AUS (AUS) NR 6 WHEEL INNER BEARING COLLAPSED. DAMAGE CAUSED TO AXLE. PART TC: 227. 2L72 4F4 F A35EU E23EA 19980522002551998052200255CE 1998 5 22 AU980358 119980323G5312 BULKHEAD CESSNA210 210K 2073446CE CONT O520 IO520L 17032SO BS 209 CRACKED W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) FUSELAGE BULKHEAD LOCATED AT STN 209 CRACKED. BULKHEAD HAD BEEN INCORRECTLY REPAIRED PREVIOUSLY ALLOWING CRACKING AT HORIZONTAL STABILIZER ATTACHMENT POINTS. PERSONNEL/MAINTENANCE ERROR. 1H71 3O3 O 3A21 E5CE 19980522002561998052200256CE 1998 5 22 AU980359 119980324G273103103625 SCREW CESSNA210 210K 2073446CE CONT O520 IO520L 17032SO ELEVATOR TAB DISTORTED W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) ELEVATOR TRIM ACTUATOR SCREW BENT. 1H71 3O3 O 3A21 E5CE 19980522002571998052200257CE 1998 5 22 AU980360 119980324G27311260759 CONTROL CABLE 12607510 CESSNA210 210K 2073446CE CONT O520 IO520L 17032SO ELEVATOR TAB CORRODED W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) ELEVATOR TRIM CABLES P/N 126075-9 AND P/N 126075-10 CORRODED. 1H71 3O3 O 3A21 E5CE 19980522002581998052200258NM 1998 5 22 AU980361 119980402G3250 CAM PIPER PA60 PA60600A 7106002NM LYC O540 IO540K1J5 41532EA NLG STEERING INCORRECT FIT W K NONE O OTHER CLCLIMB 1 AUS (AUS) NOSE WHEEL CENTERING CAM INCORRECTLY INSTALLED PREVENTING CORRECT RETRACTION OF NOSE LANDING GEAR. PERSONNEL/MAINTENANCE ERROR. 1M72 3O3 ORTA17WE 1E4 19980522002601998052200260EU 1998 5 22 AU980363 119980326G5610CAP101018 WINDSHIELD MUDRY 10 CAP10B EU LYC O360 AEIO360B2F 41514EA COCKPIT CRACKED W K NONE O OTHER DEDESCENT 1 AUS (AUS) FORWARD WINDSCREEN CRACKED. CRACK ORIGINATED FROM A CRACK REPAIR CARRIED OUT IN JULY 1997. 1L71 3O3 O A36EU 1E10 19980522002611998052200261CE 1998 5 22 AU980364 119980225G261299120363 DETECTOR CESSNA500 500CESSNA 2076602CE PWA JT15 JT15D1 52060NE FIRE DETECTION BROKEN W K NONE N FALSE WARNING CRCRUISE 1 AUS (AUS) FIRE WIRE BROKEN GIVING FALSE FIRE INDICATION. 1L72 4F4 F A22CE E1NE 19980522002731998052200273SW 1998 5 22 AU980376 119980406G291027810322755 PIPE FRCHLDSA227 SA227DC 3377521SW GARRTTTPE331TPE33112UA 01514WP HYDRAULIC CRACKED W K NONE K FLUID LOSS CRCRUISE 1 AUS (AUS) HYDRAULIC PIPE CRACKED AND LEAKING AT FLARED END. 2L72 4T4 TRTA18SW E4WE 19980522002751998052200275EA 1998 5 22 AU980378 219980406G7320LW120980100 PIPE PIPER PA31 PA31 7103102SO LYC O540 TIO540A1A 41532EA RT ENG NR 4 INJ FRACTURED W K NONE ER VIBRATION/BUFFET PARTIAL RPM/PWR LOSS CLCLIMB 1 AUS 2132 L114761 (AUS) RT ENGINE NR 4 INJECTOR LINE FRACTURED ADJACENT TO THE INJECTOR NOZZLE. 1L72 3O3 O A20SO E14EA 19980522002761998052200276CE 1998 5 22 AU980379 119980317G243503600907 BEARING LEARSIEGLER BEECH 1900 1900C 1154161CE PWA PT6 PT6A65B 52043EA STARTER/GEN COLLAPSED W K NONE H ELECT. POWER LOSS-50 PC CLCLIMB 1 AUS 1356 (AUS) RT ENGINE STARTER/GENERATOR FORWARD BEARING COLLAPSED. PART TC: 1,010. 2L72 4T4 TRTA24CE E4EA 19980522002771998052200277SO 1998 5 22 AU980380 219980217G853021935 ROCKER ARM CESSNA172 172E 2072412CE CONT O300 O300C 17022SO NR 4 CYL INT VLVBROKEN W K NONE EF VIBRATION/BUFFET FLT CONT AFFECTED CRCRUISE 1 AUS 21935 (AUS) NR 4 CYLINDER INLET VALVE ROCKER ARM BROKEN AND PUSHROD BENT. PART TC: 3,090. 1H71 3O3 ONT3A12 E253 19980522002781998052200278NE 1998 5 22 AU980381 219980403G7250 TURBINE BELL 412 412 1182202SW PWA PT6T PT6T3B 52045NE NR 2 ENG FAILED W K NONE E VIBRATION/BUFFET NRNOT REPORTED 1 AUS 61412 (AUS) NR 2 ENGINE POWER SECTION FAILED. 1G72 4U4 U H4SW E22EA 19980522002821998052200282EA 1998 5 22 AU980385 219980318G8530LW12425 VALVE GUIDE LW12425 PIPER PA23 PA23250 7102308SO LYC O540 IO540C4B5 41532EA ENG INLET LOOSE W K NONE O OTHER ININSP/MAINT 1 AUS ECNZ102921 L1405448A (AUS) ENGINE INLET VALVE GUIDE FOUND LOOSE IN HEAD. 1L72 3O3 O 1A10 1E4 19980522002831998052200283EA 1998 5 22 AU980386 219980403G853025288 POST 72242 PIPER PA31 PA31350 7103110SO LYC O540 TIO540J2BD 41532EA NR 3 CYL EXH VLVBROKEN W K NONE ER VIBRATION/BUFFET PARTIAL RPM/PWR LOSS TOTAKEOFF 1 AUS 1776 25288 L538261A (AUS) NR 3 CYLINDER EXHAUST VALVE ROCKER POST FAILED. 1L72 3O3 O A20SO E14EA 19980522002841998052200284CE 1998 5 22 AU980387 119980407G2460CM358950 CIRCUIT BREAKER CESSNA402 402C 207590RCE CONT O520 TSIO520VB 17040SO DC POWER DISTRIBFAILED W K NONE B SMOKE/FUMES/ODORS/SPARKS NRNOT REPORTED 1 AUS (AUS) AVIONICS CIRCUIT BREAKER SWITCH SMOKING. 1L72 3O3 O A7CE E8CE 19980522002901998052200290EA 1998 5 22 AU980393 219980226G8530ECNZ9230F SPARK PLUG 76190 GULSTM500 500S 0141107SW LYC O540 IO540E1B5 41532EA LT ENG SEPARATED W K NONE ER VIBRATION/BUFFET PARTIAL RPM/PWR LOSS TXTAXI/GRND HDL 1 AUS ECNZ9230F L1373648 (AUS) LT ENGINE POWER DOWN DURING PRE TAKE-OFF CHECKS. INVESTIGATION FOUND NR 4 CYLINDER UPPER SPARK PLUG HAD SEPARATED FROM THECYLINDER. CAUSE APPEARS TO BE FROM EROSION OF THE SPARK PLUG HOLE UNDER THE HELICOIL. SUSPECT FROM A VOID FORMED WHEN WELD REPAIRS WERE CARRIED OUT. 1H72 3O3 O 6A1 1E4 19980522002911998052200291EA 1998 5 22 AU980394 219980326G8520L3256836A CRANKCASE LYC O360 O360A4M 41514EA ENGINE DEFECTIVE W K NONE O OTHER ININSP/MAINT 1 AUS L3256836A L3256836A (AUS) ENGINE CRANKCASE TUNNEL MEASUREMENTS OUT OF LIMITS. 3 O E286 19980522002961998052200296WP 1998 5 22 AU980399 219980404G732289778021 FCU WOODWARD 89778021 GARRTTTPE331TPE33110U 01514WP RT ENGINE MALFUNCTIONED W K NONE EX VIBRATION/BUFFET ENGINE FLAMEOUT LDLANDING 1 AUS 2123540 (AUS) RIGHT ENGINE FUEL CONTROL UNIT (FCU) FAULTY. 4 T E4WE 19980522002981998052200298SO 1998 5 22 AU980401 119980319G81204091709001 COMPRESSOR BLADEGARRTT 4091709001 PIPER PA31 PA31350 7103110SO LYC O540 LTIO540J2BD 41533EA EXHAUST TURBO ERODED W K NONE O OTHER ININSP/MAINT 1 AUS 595 IK0159 L42868A (AUS) TURBOCHARGER COMPRESSOR BLADE LEADING EDGES SEVERELY ERODED. DURING INVESTIGATION, AN AN363C-362 NUT WITH THE REMAINS OF A SCREW STILL ATTACHED WAS FOUND ON THE TOP OF THE INDUCTION AIR FILTER BETWEEN THE FILTER AND THE TURBOCHARGER. 1L72 3O3 O A20SO E14EA 19980522002991998052200299SO 1998 5 22 AU980402 219980324G8530646286 VALVE 639272PO10 CESSNA210 T210L 2073449CE CONT O520 TSIO520H 17040SO ENG EXH WORN W K NONE O OTHER ININSP/MAINT 1 AUS 304 BT8458846084 506872 (AUS) THREE ENGINE CYLINDERS REMOVED DUE TO LOW COMPRESSION. ALL EXHAUST VALVES PN 646286 AND VALVE GUIDES PN 636242 WERE FOUND TO BE WORN BEYOND LIMITS WITH 0.508MM (.020 INCH), 1.016MM (.041 INCH) AND 1.168MM (.046 INCH) CLEARANCES. 1H71 3O3 O 3A21 E8CE 19980522003051998052200305CE 1998 5 22 AU980408 119980220G531205121871 BULKHEAD 05121872 CESSNA172 172P 2072436CE LYC O320 O320D2G 41508EA LT RT DOOR POST CRACKED W K NONE O OTHER ININSP/MAINT 1 AUS (AUS) LT AND RT LOWER AFT DOOR POST BULKHEADS (PN 0512187-1 LT AND PN 0512187-2 RT) CRACKED. FOUND DURING INSPECTION IAW SB SEB 97-1. PART TC: 5,920. 1H71 3O3 ONT3A12 E274 19980522003081998052200308SO 1998 5 22 AU980411 119980326G2436 DIODE GULSTMAA5 AA5B 3960105SO LYC O360 O360A4K 41514EA DC REGULATOR FAILED W K NONE H ELECT. POWER LOSS-50 PC CRCRUISE 1 AUS (AUS) DURING CRUISE, THE 'OVER-VOLTAGE' PROTECTION ZENER DIODE FAILED, CAUSING EXTENSIVE FAILURE OF ELECTRICAL AND AVIONICS EQUIPMENT. 1L71 3O3 O A16EA E286 19980522003131998052200313CE 1998 5 22 AU980417 119980218G2710 CONTROL ARM BEECH 58 58 1152740CE CONT O520 IO520C 17032SO AILERON CONTROL MISRIGGED W K NONE W INADEQUATE Q C ININSP/MAINT 1 AUS (AUS) AILERON CONTROL SYSTEM RIGGED INCORRECTLY. THE AILERON BELLCRANKS WERE NOT HITTING THE STOPS AND THE AILERONS WERE SHORT OF TRAVEL BY FIVE DEGREES. PERSONNEL/MAINTENANCE ERROR. 1L72 3O3 O 3A16 E5CE 19980522003141998052200314NM 1998 5 22 AU980418 119980331G2910D10010D06 PIPE DHAV DHC8 DHC8102 2809003NM PWA 120 PW120A NE HYDRAULIC SYS CRACKED W K NONE OK OTHER FLUID LOSS ININSP/MAINT 1 AUS (AUS) HYDRAULIC LINE PERMASWAGE FITTING BROKEN. THE COLLAR HAD CRACKED AND BROKEN APPROXIMATELY 4.76MM (0.1875 INCH) BELOW NUT. 2H72 4T4 TRTA13NM E20NE 19980522003151998052200315NE 1998 5 22 AU980419 219980404G7261 CHIP DETECTOR CFMINTCFM56 CFM565A1 NE ENG SCAV CONTAMINATED W K NONE O OTHER ININSP/MAINT 1 AUS 731139 (AUS) REAR SCAVENGE CHIP DETECTOR FOUND WITH SIGNIFICANT `M50' METAL DEBRIS. 4 F E29NE 19980522003191998052200319CE 1998 5 22 AU980424 119980417G3260 SWITCH BEECH 200 200BEECH 1152920CE PWA PT6 PT6A41 52043EA HARTZLHCB3T HCB3TN3 GL RT MLG UP OUT OF ADJUST W K NONE ON OTHER FALSE WARNING CLCLIMB 1 AUS (AUS) RIGHT MAIN LANDING GEAR `UP' POSITION MICROSWITCH OUT OF ADJUSTMENT. 1L72 4T4 T A24CE E4EA 6 CP15EA 19980522003211998052200321CE 1998 5 22 AU980427 119980324G3300 LIGHT CESSNA210 210K 2073446CE CONT O520 IO520L 17032SO LIGHTING SYSTEM INOPERATIVE W K NONE L NO TEST ININSP/MAINT 1 AUS (AUS) ROTATING BEACON, LANDING LIGHT, TAXI LIGHT AND PANEL LIGHTING INOPERATIVE. PERSONNEL/MAINTENANCE ERROR. 1H71 3O3 O 3A21 E5CE 19980522003221998052200322SO 1998 5 22 AU980428 219980324G7310 FITTING CESSNA210 210K 2073446CE CONT O520 IO520L 17032SO ENGINE FUEL DISTWORN W K NONE K FLUID LOSS ININSP/MAINT 1 AUS (AUS) FUEL PRESSURE FITTING ON ENGINE FUEL PUMP CHAFED THROUGH. 1H71 3O3 O 3A21 E5CE 19980522003281998052200328SW 1998 5 22 AU980437 119980423G63202060400203 GEAR JR3TYPE BELL 206 206B3 1181506SW ALLSN 250C 250C20B 03013GL M/R GEARBOX PITTED W K NONE O OTHER ININSP/MAINT 1 AUS 380 BKW11302 CAE831527 (AUS) DURING A SCHEDULED INSPECTION, METAL WAS FOUND ON THE M/R TRANSMISSION'S CHIP DETECTORS. ON TEAR DOWN INSPECTION, THE TRANSMISSION'S INPUT GEAR SHAFT WHICH FORMS THE INNER BEARING SURFACE FOR BEARING PN 206-040-031-107 RACE WAS FOUND TO HAVE SEVERE BRINELLING AND DESTRUCTIVE PITTING. PART TC: 7,037. 1G71 3U3 U H2SW E4CE 19980522003291998052200329NE 1998 5 22 AU980438 219980408G7230 FAN BLADE CFMINTCFM56 CFM565A1 NE TURBINE ENGINE BIRD STRIKE W K NONE EC VIBRATION/BUFFET F.O.D. TOTAKEOFF 1 AUS 731158 (AUS) RIGHT ENGINE BIRD STRIKE. BORESCOPE INSPECTION FOUND DAMAGE TO EIGHT FAN BLADES, OUTLET GUIDE VANES, AND ACOUSTIC LINERS. 4 F E29NE 19980522003361998052200336SO 1998 5 22 AU980445 119980326G3213025992 TRUNNION PIPER PA44 PA44180 7104402SO LYC O360 O360E1A6 41514EA HARTZLHCC2Y HCC2YR2 GL RT MLG FAILED W K NONE O OTHER LDLANDING 1 AUS (AUS) RIGHT MAIN LANDING GEAR TRUNNION HOUSING SHEARED IN AREA JUST BELOW THE PIVOT BEARING. LANDING GEAR COLLAPSED DURING LANDING. THE PROPELLER CONTACTED THE GROUND CAUSING THE ENGINE TO STOP. 1L72 3O3 O A19S0 E286 5 CP920 19980522003371998052200337SO 1998 5 22 AU980446 119980422G5210 DOOR EMB 120 EMB120 3260201SO PWA 118 PW118A NE FWD ENTRY NOT CLOSED W K NONE OJ OTHER WARNING INDICATION CLCLIMB 1 AUS (AUS) FORWARD ENTRY DOOR INCORRECTLY CLOSED DUE TO DOOR ALIGNMENT MARKS BEING WORN OFF. 2L72 4T4 TRTA31SO E20NE 19980522003521998052200352CE 1998 5 22 AU980462 119980227G7931 LINE CESSNA310 310L 2074230CE CONT O470 IO470* 17026SO ENGINE OIL PRESSSLUDGED W K NONE O OTHER CRCRUISE 1 AUS (AUS) DURING FLIGHT, THE RT ENGINE GAUGE DISPLAYED LOW OIL PRESSURE. ENGINE GROUND RUN WITH A CALIBRATED OIL PRESSURE GAUGE PLUMBED INTO SYSTEM WAS CARRIED OUT WITH NO FAULT FOUND. SUSPECTING IT COULD HAVE BEEN A SLUDGE PROBLEM IN THE PRESSURE LINE BETWEEN THE GAUGE AND ENGINE, THE LINE WAS PURGED AND REFILLED WITH CLEAN OIL. 1L72 3O3 O 3A10 E1CE 19980522006221998052200622GL 1998 5 22 98ZZZX1916 219980417G7414 DRIVE COUPLER AMTR SONERISONERAI2 GL AMTRVWVOLKS VW2200VOLKS GL MAGNETO FAILED H A UNSCHED LANDING Y ENGINE STOPPAGE NRNOT REPORTED 1 GL03247RJ180 999 ALUMINUM MAGNETO DRIVE COUPLER FRACTURED CAUSING ENGINE STOPPAGE IN-FLIGHT. PART USED IN EXPERIMENTAL AIRCRAFT FOUND TO HAVE AN APPROX 200 HOUR USE. RECOMMEND REMOVING ALL IN SERVICE AND REPLACE WITH THOSE MADE FROM PHENOLIC OR MICARTA (NOT SURE WHICH MATERIAL NOW BEING USED BY GREAT PLAINS AIRCRAFT, NEBRASKA). DID FIND OUT THE PART MUST NOT BE MADE FROM ROUND STOCK (DUE TO GRAIN), BUT CUT AND SHAPED FROM FLAT STOCK. 1M71 3O3 O EXPA1M71EXP3O 19980522006261998052200626SO 1998 5 22 98ZZZX1920 219980402G8530 VALVE CESSNA150 150J 2071820CE CONT O200 O200A 17020SO NR 4 CYL INTAKE FAILED D A UNSCHED LANDING R PARTIAL RPM/PWR LOSS NRNOT REPORTED 1 GL11390DM 15070334 20590370A AIRCRAFT WAS ON A TRAINING FLIGHT WHEN POWER WAS LOST, WITH 1500 RPM BEING MAXIMUM AVAILABLE. A SAFE LANDING WAS MADE ON A COUNTY STONE ROAD. INVESTIGATION REVEALED THE INTAKE VALVE STEM HAD BROKEN AT THE BOTTOM OF VALVE KEEPER RECESS. KEEPER AND TOP OF STEM WERE STILL IN PLACE ON TOP OF SPRING UNDER ROCKER ARM. VALVE DAMAGED NR 4 CYLINDER AND PISTON. VALVE HEAD BROKE OFF, WENT THROUGH INTAKE AND DAMAGED NR 1 CYLINDER. CYLINDER HAD 400 HOURS SINCE LIMITED MAINTENANCE RELEASE WITH EXHAUST GUIDE BEING REPLACED. 1H71 3O3 O 3A19 E252 19980529000591998052900059GL 1998 5 29 98ZZZX1935 219980501G732223051985 FUEL CONTROL BOLKMS105 BO105S 5626006EU ALLSN 250C 250C20B 03013GL ENGINE DEFECTIVE B AC2RK NONE O OTHER ININSP/MAINT 1 SW038776 2052 85470185 S776 DURING VISUAL INSPECTION OF FUEL CONTROL DURING ENGINE BUILD-UP, FOUND FUEL CONTROL DRIVE SHAFT BEARING MAKING NOISE WHEN ROTATED BY HAND, AND HAD SLIGHT RADIAL PLAY AND ROUGH FEEL WHEN SIDE LOAD WAS APPLIED AND ROTATED. SENT IN FOR REPAIR. 1G72 3U3 U H3EU E4CE 19980529000601998052900060GL 1998 5 29 98ZZZX1936 219980501G732323057269 GOVERNOR BELL 206 206B 1181511SW ALLSN 250C 250C20 03013GL ENGINE FAILED B AC2RK NONE O OTHER ININSP/MAINT 1 SW0321460 1369 85520222 4075 ROTOR SPEED NR DROOPING TO 95 PERCENT AND WOULD NOT RECOVER. GOVERNOR WAS REPLACED WITH SERVICEABLE UNIT AND DROOP DID NOT RECUR. 1G71 3U3 U H2SW E4CE 19980529002381998052900238EA 1998 5 29 98ZZZX1979 219980505G7414M3975 COIL SLICK 4371 CESSNA172 172M 2072418CE LYC O320 O320E2D 41508EA MAGNETO OPEN D K NONE O OTHER ININSP/MAINT 1 EA096814H1100 052394 17265594 4254527A DURING A ROUTINE 500-HOUR INSPECTION ON THE MAGNETOS, FOUND THE COIL SECONDARY RESISTANCE OUT OF LIMITS: THE CIRCUIT WAS OPEN. 1H71 3O3 ONT3A12 E274 19980529003831998052900383GL 1998 5 29 98ZZZX1981 219980512G731047086 FILTER 6890917 BELL 206 206B 1181511SW ALLSN 250C 250C20 03013GL FUEL NOZZLE CONTAMINATED B HEFRK NONE O OTHER ININSP/MAINT 1 WP2190215 1698 DISCOVERED AT CLEAN AND FLOW CHECK. ITEM 1700-2000 TBO. CONTAMINATION OF FUEL NOZZLE FILTER. 1G71 3U3 U H2SW E4CE 19980529003911998052900391SO 1998 5 29 98ZZZX1986 219980304G8530631521 VALVE SPRING 653452D CESSNA421 421C 2076016CE CONT O520 GTSIO520N 17032SO NR 1 CYLINDER FAILED D A UNSCHED LANDING E VIBRATION/BUFFET CLCLIMB 1 WP09748CA859 421C0905 604132 PILOT REPORTED VIBRATION ON RT SIDE OF AIRCRAFT DURING TAKEOFF ROLL AND CLIMB OUT. COULD NOT CORRECT WITH ENGINE CONTROLS (RPM, M.A.P., FUEL OR MAGS). RETURNED TO AIRPORT MAINT FACILITY AND REPORTED OUT OF BALANCE PROP. UPON MAINT GROUND RUN, ENG RAN ROUGH, VIBRATION AT IDLE RPM AND BACKFIRING OUT THE EXHAUST. DIFFERENTIAL COMPRESSION CHECK REVEALED NR 1 CYL AT ZERO COMPRESSION. UPON FURTHER INSP, NOTED 3 PIECES WITH SUBSEQUENT DAMAGE TO THE GUIDE AND VALVE. DAMAGE TO THE GUIDE WAS SO SEVERE, THE EXHAUST VALVE WAS STUCK IN THE OPEN POSITION CAUSING THE DEAD CYLINDER. 1L72 3O3 O A7CE E7CE 19980529004071998052900407WP 1998 5 29 98ZZZX2002 219980515G732121011445 EEC AMD FALC50FALCON50MYST2730106EU GARRTTTFE731TFE7313 01518WP ENGINE FAILED D K NONE O OTHER ININSP/MAINT 1 WP23XAAVE 843640 022 P76193 AFTER BENCH ADJUSTMENT OF EEC, EEC WAS INSTALLED IN ACFT. DURING START OF ENGINE, EEC TRIPPED TO MANUAL MODE AND UNABLE TO RESET. AFTER EXTENSIVE T/S, DETERMINED EEC WAS UNSERVICEABLE. A REVIEW OF TEAR DOWN/REPAIR REPORT REVEALED EEC REMOVED FROM SERVICE FOR THE SAME FAILURE. FAA FORM 8130-3 STATED INSP ONLY. EEC RETURNED TO ALLIED SIGNAL FOR WARRANTY CONSIDERATION. THIS WAS SECOND EEC THAT FAILED WHILE CORRECTING A SQUAWK DURING THE SAME MAINT VISIT BY CUSTOMER. THE FIRST FAILED EEC WAS REPORTED ON A SEPARATE M OR D REPORT. 2L73 4F4 F A46EU E6WE 19980529004131998052900413EA 1998 5 29 98ZZZX2008 219980519G72503001538 LOCK 3011438 BEECH 100 A100 1152915CE PWA PT6 PT6A28 EA CT VANE RING MISINSTALLED DSA K NONE W INADEQUATE Q C ININSP/MAINT 1 SW0996AU B162 PCE50443 REMOVED RIGHT ENGINE POWER SECTION FOR ACCESS TO PERFORM SCHEDULED HOT SECTION INSPECTION. UPON DISASSEMBLY, DISCOVERED TAB WASHERS (16 EACH) WERE NOT BENT TO THE SAFETY POSITION. THESE WASHERS SAFETY THE BOLTS THAT RETAIN THE CT VANE RING AND NR 2 BEARING COVER. ENGINE LOG BOOK DID NOT REVEAL ANY MAINTENANCE IN THIS PART OF THE ENGINE SINCE OVERHAUL BY THE MANUFACTURER. SUSPECT CAUSE: MISSED AT QUALITY CONTROL INSPECTION AT OVERHAUL FACILITY. 1L72 3T4 T A14CE E4EA 19980605000061998060500006GL 1998 6 5 98ZZZX2014 219980324G724023030911 COMBUSTION CASE BELL 407 407 SW ALLSN 250C 250C47B GL FUEL NOZZLE CRACKED D A K NONE O OTHER ININSP/MAINT 1 WP0158236821 53069 CAE847085 HIGHER THAN NORMAL MGT INDICATION BY PILOT WAS REPORTED. INSPECTED AND PERFORMED TEST OF MEASURED GAS TEMPERATURE SYSTEM. NO ANOMALLY OBSERVED. UPON FURTHER INSPECTION FOUND SEAM WELDS AROUND FUEL NOZZLE BOSS CRACKED ALLOWING COOLING AIR TO ESCAPE. 1G71 3U3 UO H2SW E1GL 19980605000141998060500014NE 1998 6 5 98ZZZX2022 219980513G723050B927 BEARING BOEING777 777222 1385219NM PWA PW4077PW4077 NE NR 1 MAIN FAILED B WA2DE ENGINE SHUTDOWN J WARNING INDICATION NRNOT REPORTED 1 NE03767UA8537 0006 26918 P777021 ENGINE REMOVED ON 5-6-98 DUE IN-FLIGHT SHUT DOWN FOLLOWING OIL FILTER BYPASS LIGHT AND LOW OIL PRESSURE LIGHT. DISASSEMBLY INSPECTION REVEALED FAILED NR 1 MAIN BEARING WITH HEAVY SPALLING AND 360 DEGREE CAGE SEPARATION. THE BEARING HAS BEEN TURNED OVER TO PRATT AND WHITNEY ENGINEERING FOR INVESTIGATION. 2L72 4F4 FRTT0001SE E46NE 19980605000211998060500021NE 1998 6 5 98ZZZX2029 219980430G7230717623 HUB PWA JT8 JT8* 52044NE ENGINE HPC MISDRILLED B RA1RK NONE W INADEQUATE Q C ININSP/MAINT 1 SW05 9S4137 HIGH COMPRESSOR REAR HUB WAS RECEIVED WITH SB 4070 HOLES NOT PROPERLY LOCATED. THE HUB BORE SHOULD HAVE BEEN SCALLOPED, BUT THE HOLES WERE LOCATED ON THE BALANCE FLANGE AND THE DISK WAS DRILLED COMPLETELY THROUGH. THE OVERHAUL AGENCY WAS FENIX AVIATION CORP., MIAMI, FLORIDA 33142. 4 F E2EA 19980605000251998060500025SO 1998 6 5 98ZZZX2033 219980220G8550629218 DRIVEN GEAR CESSNA421 421C 2076016CE CONT O520 GTSIO520N 17032SO OIL PUMP SEIZED D O OTHER JR WARNING INDICATION PARTIAL RPM/PWR LOSS CRCRUISE 1 WP09745CA 156 421C1043 610040 PILOT REPORTED YAW IN AIRCRAFT AND APPARENT LOSS OF POWER ON LT ENGINE (LOW RPM AND MAP). PILOT EXERCISED EMERGENCY PROCEDURES TO RESTORE POWER, BUT WAS UNSUCCESSFUL AND THE ENG WAS SHUT DOWN IN-FLIGHT. PROP WAS ALREADY IN FEATHER POSITION WHICH WOULD INDICATE LOSS OF OIL PRESSURE. INSPECTION REVEALED THE OIL PUMP DRIVE GEAR ASSY SHAFT HAD SHEARED AT POINT OF ENGAGEMENT TO THE CAMSHAFT GEAR RESULTING IN LOSS OF TACH INDICATION AND OIL PRESS. FURTHER INSP OF OIL PUMP ASSY REVEALED SEVERE DRIVEN GEAR SHAFT AND BUSHING WEAR WITH HOUSING SIDE WALL WEAR. BUSHINGS AND SHAFT WEAR BECAME SO SEVERE THE OIL PUMP DRIVEN GEAR WOULD NOT PROFILE WITH THE DRIVE GEAR CAUSING BOTH GEARS TO LOCK UP AND SUBSEQUENT SHAFT FAIL1L72 3O3 O A7CE E7CE 19980605000401998060500040EA 1998 6 5 98ZZZX2048 219980424G855073772 OIL JET PIPER PA46 PA46350P SO LYC O540 TIO540AE2A 41532EA PISTON COOLING FAULTY B SO5RK NONE O OTHER ININSP/MAINT 1 NE03621CA509 4636008 L9621861A REPETITIVE OIL ANALYSIS REVEALED HIGH WEAR METAL LEVELS FROM CYLINDER AREA WEAR (PISTON, RINGS, LINER). REMOVED AND REPLACED CYLINDERS WITH FACTORY NEW CYLINDER KITS. WHILE CYLINDERS WERE REMOVED, PISTON COOLING OIL JETS WERE REMOVED AND TESTED. FIVE OUT OF 6 FAILED INITIAL TEST. AFTER CLEANING ALL SIX, 4 WERE RETURNED TO SERVICE AND 2 WERE REPLACED WITH NEW. THIS IS THE SECOND AIRCRAFT/ENGINE COMBINATION OCCURRENCE. SUBMITTER SUSPECTED CLOGGED OIL JETS NOT PROPERLY COOLING/LUBRICATING PISTONS CAUSING DISTORTION RESULTING IN WEAR. 1L71 3O3 ORTA25SO E14EA 19980605000981998060500098CE 1998 6 5 CA980318039 119980224G812040727619 TURBINE GARRTT 4652929002 CESSNA182 TR182 2072735CE LYC O540 O540L3C5 41532EA ENGINE TURBO MISREPAIRED W K NONE W INADEQUATE Q C ININSP/MAINT 1 CA 2203 MHR0106 L2185440A (CAN) TURBO WAS SENT FOR REPAIR DUE TO RUBBING OF COMPRESSOR ON CASING. SHOP FOUND AUTOMOTIVE PARTS INSTALLED. 1H71 3O3 O 3A13 E295 19980612003321998061200332GL 1998 6 12 98ZZZX2087 219980430G73222537739 VALVE SLEEVE BENDIX 25490923 SKRSKYS76 S76A 8143006NE ALLSN 250C 250C30S 03013GL FLOW BODY SEPARATED B ALGRK NONE O OTHER ININSP/MAINT 1 SW035427S 331596 760168 DURING SHOP INSPECTION FOR DECELERATION OF ENGINE, FOUND FUEL CONTROL BONDING ON SLEEVE SEPARATED. 1G72 3U3 U H1NE E1GL 19980612003371998061200337 1998 6 12 98ZZZX2092 219980305G8530 ENGINE AMTR KISTR1 LYC O235* NR 4 CYLINDER FAILED G A A UNSCHED LANDING Y ENGINE STOPPAGE CRCRUISE 1 GL0366SK 021 L858515 THIRTY MINUTES INTO LOCAL FLIGHT, ENGINE FAILED. PILOT MADE A FORCED LANDING IN A PLOWED FARM FIELD. NO VISIBLE DAMAGE INCURRED TO AIRPLANE. ON TEARDOWN, DEEP SCORING WAS FOUND IN THE OIL PUMP GEAR HOUSING. ALUMINUM AND PISTON RING PIECES WERE FOUND IN THE SUMP. A 2 INCH CRACK WAS FOUND IN CASE HALF. NR 4 PISTON DISINTEGRATED FROM CYLINDER. THREE LIFTERS HAD MISSING PIECES. THE CAMSHAFT HAD IMPACT DAMAGE ON ALL LOBES. ALL RODS HAVE IMPACT DAMAGE. NR 4 CYLINDER IS UNSERVICEABLE. 0 19980612003381998061200338GL 1998 6 12 98ZZZX2093 219980513G72106894171 GEARBOX HUGHES369 369D 4470706WP ALLSN 250C 250C20B 03013GL ENGINE FAILED B LS1RK NONE J WARNING INDICATION ININSP/MAINT 1 EA131097J5072 1508 CAG31160F 900801D TORQUE PRESSURE INCREASED WHEN THROTTLE WAS REDUCED. SUSPECT TORQUE PISTON BLEED HOLE IS PLUGGED IN GEARBOX. GEARBOX SHIPPED TO OVERHAUL FACILITY FOR INSPECTION/REPAIR. REF: CONTROL NR 98-5-5. 1G71 3U3 U H3WE E4CE 19980612003391998061200339GL 1998 6 12 98ZZZX2094 219980512G72306890550 COMPRESSOR HUGHES369 369D 4470706WP ALLSN 250C 250C20B 03013GL ENGINE SEIZED B LS1RK NONE O OTHER ININSP/MAINT 1 EA131097J6421 1 CAC34712 900801D COMPRESSOR INSTALLED ON AIRCRAFT AT ZERO TSO. AFTER GROUND RUNS, AIRCRAFT WAS TEST FLOWN. UPON NEXT START ATTEMPT AFTER APROXIMATELY 10 MINUTES SHUTDOWN TIME, ANOTHER START WAS ATTEMPTED. COMPRESSOR HAD SEIZED. UPON REMOVAL AND INSPECTION, IT WAS FOUND TO BE WHEEL RUB ON CASE HALF PLASTIC. 1G71 3U3 U H3WE E4CE 19980612003401998061200340GL 1998 6 12 98ZZZX2095 219980512G72306890550 COMPRESSOR HUGHES369 369D 4470706WP ALLSN 250C 250C20B 03013GL ENGINE VIBRATION B LS1RK NONE O OTHER ININSP/MAINT 1 EA131097J5675 2288 CAC35331 900801D EXHAUST STACKS CRACKED. VIBRATION ANALYSIS CHECK INDICATED COMPRESSOR WAS VIBRATING EXCESSIVELY. COMPRESSOR WAS REMOVED AND SENT FOR REPAIR EVALUATION. REF: CONTROL NR 98-5-9. 1G71 3U3 U H3WE E4CE 19980612003621998061200362SO 1998 6 12 98ZZZX2117 219980422G8530SA640518 PISTON CESSNA180 180H 2072618CE CONT O470 O470R 17026SO NR 5 FAILED D A UNSCHED LANDING ER VIBRATION/BUFFET PARTIAL RPM/PWR LOSS CLCLIMB 1 NM05180BH198 18052132 1313345R4 ABOUT 15 SECONDS AFTER TAKEOFF, ENGINE BEGAN TO RUN ROUGH AND LOSE POWER. PILOT COULD NOT MAINTAIN ALTITUDE, AND MADE AN UNEVENTFUL LANDING. INSPECTED ENGINE, FOUND NR 5 PISTON BROKEN AND NO LONGER IN THE CYLINDER; ALSO, A 2 INCH CRACK FROM BASE OF NR 5 PISTON LEADING UP TO BACK BONE OF CASE. 1H71 3O3 O 5A6 E273 19980612003711998061200371EA 1998 6 12 98ZZZX2126 219980507G741410382807 CAPACITOR CESSNA172 172N 2072434CE LYC O320 O320H2AD 41508EA MAGNETO DEFECTIVE H A UNSCHED LANDING R PARTIAL RPM/PWR LOSS NRNOT REPORTED 1 SO17733LW1099 17268384 L104776 MAGNETO POINTS AND COILS REPLACED ON 500-HOUR INSPECTION. AIRCRAFT MADE FORCED LANDING APPROXIMATELY 3 HOURS LATER. FOUND CAM FOLLOWERS MELTED ON ONE SET AND RESET OTHER SET AND FLEW ACFT BACK TO BASE (APPROX ONE-HALF HOUR). NEW POINTS SHOWED SIGNS OF HEAT AFTER THIS SHORT FLIGHT. BENDIX SB 587 REFERS TO THIS PROBLEM BEING CAUSED BY BAD CAPACITORS. REPLACED BOTH SETS OF POINTS AND BOTH CAPACITORS. 1H71 3O3 ONT3A12 E274 19980612003751998061200375EA 1998 6 12 98ZZZX2130 219980415G8520SL78027 BOLT PIPER PA22 PA22160 7102214SO LYC O320 O320B2A 41508EA CONNECT ROD FAILED D A K NONE W INADEQUATE Q C ININSP/MAINT 1 WP118701D 225882 L1268339A THIS ONE OUT OF EIGHT NEW CONNECTING ROD BOLTS STRETCHED AND DECREASED IN DIAMETER WHEN BEING TORQUED TO OEM SPECIFICATION DURING ENGINE OVERHAUL. ALL EIGHT BOLTS ARE 'NOT' BEING PUT INTO SERVICE. BOLT WOULD NOT TORQUE TO OEM SPECIFICATIONS. 1H71 3O3 O 1A6 E274 19980619000041998061900004EA 1998 6 19 98ZZZX2160 219980416G853060009 VALVE KEEPER LW11633 CESSNA150 152 2071835CE LYC O235 O235L2C 41505EA NR 4 CYLINDER WORN B LJQRK NONE O OTHER ININSP/MAINT 1 EA09757RM 407 A5383 15279944 L1917815 VALVE KEEPERS WORN, BUT STILL INSTALLED. LET VALVE ASSY MOVE DOWN IN KEEPER ASSY. VALVE WOULD NOT COMPLETELY CLOSE. NO DAMAGE TO CYLINDER OR PISTON. 1H71 3O3 ONT3A19 E223 19980619000081998061900008NE 1998 6 19 98ZZZX2164 219980518G8530MYHN52 CYLINDER SCWZERG164 G164A 3952704EA PWA R1340 R1340AN1 52016NE NR 4 CRACKED B IL1RK NONE O OTHER ININSP/MAINT 1 EA234869524 1628 21888 INSPECTION FOUND NR 4 CYLINDER CRACKED IN ROCKER BOSS AREA. 1Q71 3R3 R 1A16 5E2 19980619000101998061900010SO 1998 6 19 98ZZZX2166 219980328G852035972 ROD BOLT BEECH 55 95A55 1152704CE CONT O470 IO470L 17026SO NR 1 FAILED DL K NONE O OTHER NRNOT REPORTED 1 CE051040T TC318 1923459LR ROD BOLT WAS MAGNAFLUXED AND CLEANED 75.8 HOURS PRIOR TO FAILURE. TT UNKNOWN, SUSPECT UNDETECTED METAL FATIGUE. BOLT BROKE UNDER FULL POWER AND HIGH RPM. SUGGEST CHANGING OUT ROD BOLTS WITH NEW BOLTS AT EACH MAJOR OVERHAUL. 1L72 3O3 O 3A16 3E1 19980619009171998061900917NE 1998 6 19 98ZZZX2190 219980428G731402532330002 FUEL PUMP SUNDSTRANDEM BEECH 200 200BEECH 1152920CE PWA PT6 PT6A42 52043NE DRIVE SHAFT FAILED H O OTHER X ENGINE FLAMEOUT CRCRUISE 1 WP05430MC 995 BB904 PCE93097 DURING CRUISE FLIGHT, THE RT ENGINE FLAMED OUT AND WOULD NOT RESTART IN-FLIGHT. AFTER A SAFE LANDING, THE ENGINE STARTED NORMALLY. HOWEVER, WHEN POWERED UP TO 100 PERCENT, THE ENGINE WOULD IMMEDIATELY FLAME OUT. INSPECTION REVEALED THE HIGH PRESSURE, ENGINE-DRIVEN FUEL PUMP WAS AT FAULT. THE SPLINED DRIVE SHAFT FROM THE ACCESSORY SECTION TO THE FUEL PUMP WAS FOUND STRIPPED. THERE WAS, HOWEVER, ENOUGH SHEARED METAL LEFT IN THE DRIVE COUPLING TO ALLOW THE DRIVE SHAFT TO ENGAGE INTERMITTENTLY. CLOSE INSPECTION OF THE STRIPPED SHAFT DID NOT REVEAL ANY REASON FOR FAILURE, EXCEPT FOR METAL FATIGUE. THE PUMP AND DRIVE SHAFT WERE REPLACED AND THE ENGINE FUNCTIONED NORMALLY. 1L72 4T4 T A24CE E4EA 19980619009251998061900925EA 1998 6 19 98ZZZX2198 219980501G8530 VALVE LYC O360 IO360A1A 41514EA NR 3 CYL EXHAUSTFAILED D O OTHER ER VIBRATION/BUFFET PARTIAL RPM/PWR LOSS NRNOT REPORTED 1 SO16 HEAD OF VALVE SEPARATED IN-FLIGHT. ENGINE HAD APPROXIMATELY 2,000 HOURS. 3 O 1E10 19980619009261998061900926NE 1998 6 19 SI3R98008 219980520G72106044T35P10 GEARBOX HAMSTD GC49 SAAB SF340 SF340A 7850100EU GE CT7TP CT79B 30030NE DAMAGED B SI3RK NONE O OTHER ININSP/MAINT 1 NE03 14611788 UDAG0843 DISASSEMBLY OF GEARBOX REVEALED SEVERE DAMAGE TO THE DAMPER RING ON THE RIGHT FORWARD IDLER GEAR. ALSO, RIGHT FORWARD IDLER GEAR WEB CRACKED (P/N 792207-3) BULKHEAD (P/N 775754-13) HAS 0.060 INCH - 0.080 INCH GROOVE WORN IN. RECOMMEND SCRAP DISPOSITION. (P/N 775760-2, FIG 8 ITEM 85). HSS SO NR 85198SE. CUST: SIMMONS A/L. 2L72 4T4 TRTA52EU E8NE 19980626000871998062600087EA 1998 6 26 98ZZZX2208 219980604G8530 BOSS ECLW12967CN PIPER PA31 PA31350 7103110SO LYC O540 TIO540J2BD 41532EA EXHAUST CRACKED B K NONE W INADEQUATE Q C ININSP/MAINT 1 SO1141162 318452002 PURCHASED 12 (COMPLETE) OVERHAULED CYLINDERS FOR TIO-540J2BD. FOURTH OF TWELVE REPAIRED UNDER WORK ORDER NR 64856, S/N 03, FOUND CRACKS ON EXHAUST STUD BOSS. 1L72 3O3 O A20SO E14EA 19980626000911998062600091GL 1998 6 26 98ZZZX2211 219980520G72306890502 WHEEL BLADE BELL 206 206B 1181511SW ALLSN 250C 250C20B 03013GL COMP STG 3 FAILED B KUVRO OTHER R PARTIAL RPM/PWR LOSS CLCLIMB 1 SO19262BH9193 2463 C38375 3563 CAE833583 THE PILOT REPORTED COMPRESSOR STALLS DURING LIFT OFF OF THE HELICOPTER. AFTER INSPECTION OF THE COMPRESSOR, THE NR 3 WHEEL WAS FOUND MISSING A BLADE. THE BLADE BROKE OFF DAMAGING SEVERAL WHEELS BEFORE EXITING OUT. 1G71 3U3 U H2SW E4CE 19980626001121998062600112SO 1998 6 26 98ZZZX2231 219980605G8540632617 GEAR CESSNA337 337G 2075730CE CONT O360 IO360A 17025SO DRIVE PAD FAILED DS K NONE O OTHER ININSP/MAINT 1 SO1137BJ 850 33701503 VACUUM PUMP FAILED. NEW PUMP WOULD NOT WORK. FOUND GEAR TEETH (ALL) MISSING FROM DRIVE GEAR. 1H72 3O3 O A6CE E1CE 19980626001171998062600117EA 1998 6 26 98ZZZX2236 219980513G8520 CRANKSHAFT CESSNA185 A185F 2072821CE LYC O540 TIO540J2BD 41532EA CYL 2-3 AREA FAILED G A UNSCHED LANDING R PARTIAL RPM/PWR LOSS NRNOT REPORTED 1 GL157140H 1059 18503351 L833061A ENGINE RPM SURGED AND FLUCTUATED. ENGINE LOST POWER. AIRCRAFT FLIPPED OVER DURING EMERGENCY LANDING. MAJOR DAMAGE, NO INJURIES. NO PROPELLER STRIKE. PRE TEAR-DOWN EXAM INDICATES THE ENGINE CRANKCHAFT IS BROKEN BETWEEN NR 2 AND NR 3 CYLINDERS. 1H71 3O3 O 3A24 E14EA 19980626002891998062600289GL 1998 6 26 98ZZZX2241 219980527G7250369H7301503 ROD HUGHES500N 500N 3027374SW ALLSN 250C 250C20R2 GL GAS PRODUCER CRACKED G K NONE O OTHER ININSP/MAINT 1 WP07524FB6037 LN004 INSPECTION FOUND GAS PRODUCER INTERCONNECT TUBE WITH CRACKS, 2 EACH, 180 DEGREES APART AT SHORT END. 1G71 3U3 UNCH3WE E4CE 19980626002911998062600291NE 1998 6 26 98ZZZX2242 219980521G7250798808 AIRSEAL PWA JT8 JT8* 52044NE LP TURBINE CRACKED B M9QRK NONE W INADEQUATE Q C ININSP/MAINT 1 SW17 WHILE RE-EVALUATING THE DATA FOR TI-JT8D-117 ON WELDING OF THE KNIFE EDGE AIRSEALS ON 2ND, 3RD, AND 4TH STAGE ROTATING AIRSEALS, CRACKING WAS DETECTED IN THE PEDESTAL RADIUS. THE PART WAS DAMAGED AS THE RESULT OF THE LASER WELDING PROCESS. REF: THE INVESTIGATION IS CONTINUING. OPERATOR CONTROL NR M9QR564N AND 98ZZZX2243. (X) 4 F E2EA 19980626002921998062600292NE 1998 6 26 98ZZZX2243 219980521G7250759059 AIRSEAL PWA JT8 JT8* 52044NE LP TURBINE CRACKED B M9QRK NONE W INADEQUATE Q C ININSP/MAINT 1 SW17 WHILE RE-EVALUATING THE DATA FOR TI-JT8D-117 ON WELDING OF THE KNIFE EDGE AIRSEALS ON 2ND, 3RD, AND 4TH STAGE ROTATING AIRSEALS, CRACKING WAS DETECTED IN THE PEDESTAL RADIUS. THE PART WAS DAMAGED AS THE RESULT OF THE LASER WELDING PROCESS. THE INVESTIGATION IS CONTINUING. REF: OPERATOR CONTROL NR M9QR564N AND 98ZZZX2242. 4 F E2EA 19980626003861998062600386GL 1998 6 26 HEEA0014442 219980601G723023007208 DIFFUSER 23033191 BELL 206 206L1 1182107SW ALLSN 250C 250C28B 03013GL ENGINE MISMANUFACTURED E HEEAK NONE W INADEQUATE Q C ININSP/MAINT 1 SW033892R CAC70726 45594 CAE860059 RECEIVING INSPECTION REVEALED: DISTORTED BEYOND SERVICEABLE LIMITS ON VANE ASSY. (VANE L/E). 1G71 3U3 U H2SW E1GL 19980626003871998062600387GL 1998 6 26 HEEA0014443 219980601G7260230595681 BEARING 23035179 SKRSKYS76 S76A 8143006NE ALLSN 250C 250C30S 03013GL GEARBOX MISMANUFACTURED E HEEAK NONE W INADEQUATE Q C ININSP/MAINT 1 SW0322342 CAG90183 760096 CAE890431S RECEIVING INSPECTION REVEALED: RUST BEYOND SERVICEABLE LIMITS ON 3 AND 4 CAGE. INSTALLED A NEW 3 AND 4 CAGE. 1G72 3U3 U H1NE E1GL 19980626004001998062600400EA 1998 6 26 HEEA0014570 219980604G7532310092205 BLEED VALVE BEECH 200 200BEECH 1152920CE PWA PT6 PT6A41 52043EA ENGINE COMP FAULTY E HEEAK NONE O OTHER ININSP/MAINT 1 SW03789DS BB478 BLEED VALVE POPPING AT HIGH TORQUE. 1L72 4T4 T A24CE E4EA 19980626004431998062600443SW 1998 6 26 HEEA0014468 119980602G6710206062721109 ACTUATOR BELL 206 206L1 1182107SW ALLSN 250C 250C28B 03013GL DROOP COMP INOPERATIVE E HEEAK NONE O OTHER ININSP/MAINT 1 SW03 ACTUATOR INOPERATIVE. 1G71 3U3 U H2SW E1GL 19980626004441998062600444SW 1998 6 26 HEEA0014469 119980602G6710206062721109 ACTUATOR BELL 206 206L1 1182107SW ALLSN 250C 250C28B 03013GL DROOP COMP INOPERATIVE E HEEAK NONE O OTHER ININSP/MAINT 1 SW03 ACTUATOR HAS NO MOVEMENT. 1G71 3U3 U H2SW E1GL 19980626004451998062600445SW 1998 6 26 HEEA0014470 119980602G6710206062721109 ACTUATOR BELL 206 206L1 1182107SW ALLSN 250C 250C28B 03013GL DROOP COMP. DAMAGED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03 END OF OUTPUT SHAFT SPLIT. 1G71 3U3 U H2SW E1GL 19980626004481998062600448SW 1998 6 26 HEEA0014473 119980602G6710206062721109 ACTUATOR BELL 206 206L3 1182108SW ALLSN 250C 250C30P 03013GL DROOP COMP INOPERATIVE E HEEAK NONE O OTHER ININSP/MAINT 1 SW0331821 51076 ACTUATOR INOPERATIVE. 1G71 3U3 U H2SW E1GL 19980626004581998062600458GL 1998 6 26 HEEA0014487 219980602G73143881005 SPLINE BELL 206 206L1 1182107SW ALLSN 250C 250C30P 03013GL FUEL PUMP WORN E HEEAK NONE O OTHER ININSP/MAINT 1 SW035006F1480 45181 PUMP HAS EXCESSIVE DRIVE SHAFT SPLINE WEAR AND GEAR SPLINE WEAR. 1G71 3U3 U H2SW E1GL 19980626004771998062600477SW 1998 6 26 HEEA0014516 119980604G6710206062721109 ACTUATOR BELL 206 206L1 1182107SW ALLSN 250C 250C30P 03013GL DROOP COMP ERRATIC E HEEAK NONE O OTHER ININSP/MAINT 1 SW035737T 45454 DROOP COMP ACTUATOR INTERMITTENTLY ERRATIC. 1G71 3U3 U H2SW E1GL 19980626004991998062600499SW 1998 6 26 HEEA0014550 119980604G6710206062721109 ACTUATOR BELL 206 206L3 1182108SW ALLSN 250C 250C30P 03013GL DROOP COMP INOPRATIVE E HEEAK NONE O OTHER ININSP/MAINT 1 SW038591X 51495 ACTUATOR INOPERATIVE. 1G71 3U3 U H2SW E1GL 19980626005561998062600556GL 1998 6 26 HEEA0014463 219980602G73201564T1005 ACTUATOR BOLKMS105 BO105S 5626006EU ALLSN 250C 250C20B 03013GL FUEL CONTROL INOPERATIVE E HEEAK NONE O OTHER ININSP/MAINT 1 SW03 ACTUATOR INOPERATIVE. 1G72 3U3 U H3EU E4CE 19980626005581998062600558GL 1998 6 26 HEEA0014465 219980602G73201564T1005 SERVO MOTOR BOLKMS105 BO105S 5626006EU ALLSN 250C 250C20B 03013GL FUEL CONTROL FAULTY E HEEAK NONE O OTHER ININSP/MAINT 1 SW03911DD S830 UNABLE TO ADJUST AND SLIP. 1G72 3U3 U H3EU E4CE 19980626005631998062600563GL 1998 6 26 HEEA0014488 219980602G73222537739 METERING VALVE BOLKMS105 BO105S 5626006EU ALLSN 250C 250C30P 03013GL FLOW BODY FAULTY E HEEAK NONE O OTHER ININSP/MAINT 1 SW03911BR S719 ENGINE DECELERATED. BENCH TESTED UNIT AS RECEIVED. FOUND FLOWS TO HANG. INSPECTED UNIT AND FOUND METERING VALVE SLEEVE, P/N 2537739. UNIT TESTED. REPLACED METERING VALVE SLEEVE, P/N 2537739, WITH SERVICEABLE METERING VALVE SLEEVE, P/N 2537739. BENCH TEST UNIT. 1G72 3U3 U H3EU E1GL 19980626008661998062600866NE 1998 6 26 98ZZZX2255 219980424G7230407402C BLADE 670402 SKRSKYS64 S64F NE PWA JFTD12JFTD12A5A 52047NE 2ND STAGE FRACTURED B JYDRA UNSCHED LANDING R PARTIAL RPM/PWR LOSS EXEXTERNAL LOAD 1 NM09159AC349 H64871 64084 677817 ON 4-24-98, AIRCRAFT WAS ON A FIRE FIGHTING MISSION. DURING CLIMB-OUT, A LOUD 'BANG' SOUND OCCURRED, FOLLOWED BY A LEFT YAW. THE LOAD OF WATER WAS JETTISONED AND PILOTS PUSHED MAXIMUM BEEP ON BOTH ENGINES. THE NR 1 ENG WAS CARRYING THE LOAD. THE NR 2 ENG READ 70 PERCENT N1, 485 DEGREES CELSIUS T5, 6-700 POUND FUEL FLOW, AND ZERO TORQUE. ENG WAS NOT PRODUCING ANY POWER SO IT WAS AN IN-FLIGHT FAILURE. ACFT LANDED IN FIRST AVAILABLE CLEAR AREA AND SHUT DOWN. WHEN MOTORING NR 2 ENG, A VIBRATION WAS FELT IN THE AIRFRAME. THE ENG WAS RETURNED TO ERICKSON AIR-CRANE WHERE ONE 2ND STAGE BLADE WAS FOUND FRACTURED JUST ABOVE THE ROOT PLATFORM. IT WAS SENT TO PWA, FOR FAILURE INVESTIGATION AND REPORT ON CAUSE. 2G72 4U4 U H6EA E15EA 19980703001661998070300166GL 1998 7 3 HEEA0014653 219980608G74129580113800 GENERATOR SKRSKYS76 S76A 8143006NE ALLSN 250C 250C30S 03013GL ENGINE INTERMITTENT E HEEAK NONE O OTHER ININSP/MAINT 1 SW0315460 760223 IGNITION GENERATOR INTERMITTENT. 1G72 3U3 U H1NE E1GL 19980703001861998070300186GL 1998 7 3 HEEA0014762 219980611G73207630103901102 ACTUATOR SKRSKYS76 S76A 8143006NE ALLSN 250C 250C30S 03013GL ENGINE CONTROL MALFUNCTIONED E HEEAK NONE O OTHER ININSP/MAINT 1 SW031545X 185 760050 MOTOR ROTATES TOO LONG BEFORE SHAFT MOVES. 1G72 3U3 U H1NE E1GL 19980703001881998070300188NE 1998 7 3 HEEA0014781 219980611G72103024780 GEARBOX BELL 412 412 1182202SW PWA PT6T PT6T3B 52045NE COMBINING G/BOX FAILED E HEEAK NONE O OTHER NRNOT REPORTED 1 SW03107X 12873 33113 COMBINING GEARBOX MAKING METAL. 1G72 4U4 U H4SW E22EA 19980703001891998070300189NE 1998 7 3 HEEA0014782 219980611G72103024780 GEARBOX BELL 412 412 1182202SW PWA PT6T PT6T3B 52045NE COMBINING G/BOX MAKING METAL E HEEAK NONE O OTHER NRNOT REPORTED 1 SW033893N7597 33010 COMBINING GEARBOX MAKING METAL. 1G72 4U4 U H4SW E22EA 19980703004951998070300495NE 1998 7 3 98ZZZX2262 219980513G7250798157001 RING PWA JT8 JT8D217A 52053NE N1 TURBINE FAILED B RA1RK NONE O OTHER ININSP/MAINT 1 SW05 708416 ENGINE REMOVED FROM SERVICE FOR 'LPT DAMAGE'. THE SECOND STAGE VANE INNER SUPPORT LOCATING PIN BROKE LOOSE AND CAUSED IMPACT DAMAGE TO THE T2 AND T3 BLADES, AND COMPLETE FAILURE OF ALL T4 BLADES. 4 F E9NE 19980703005061998070300506EA 1998 7 3 98ZZZX2273 219980602G8520 CAMSHAFT LOBE LYC O720 IO720B1A 41546EA NR 2 CYL EXH SPALLED D K NONE O OTHER ININSP/MAINT 1 SW99 1111 L81854 DURING 100-HOUR INSPECTION AND INSPECTION FOR REPORTED SLIGHT APPARENT POWER LOSS, FOUND NR 2 CYLINDER EXHAUST VALVE LIFTER BODY AND CAMSHAFT LOBE FAILED PREMATURELY. CAMSHAFT AND LIFTERS HAD BEEN RECONDITIONED AND REGROUND AT MAJOR OVERHAUL INSTEAD OF NEW. NO REPORTED OPERATING DIFFICULTIES. BALANCE OF ENGINE CLEAN INTERNALLY. ENGINE ALWAYS ON SHELL 20W50 AD OIL. 3 O 1E15 19980703005081998070300508EA 1998 7 3 98ZZZX2275 219980420G8520LW10646 CONNECT ROD BEECH 60 B60 1153605CE LYC O541 TIO541E1C4 41536EA NR 3 CYLINDER FAILED E A UNSCHED LANDING ER VIBRATION/BUFFET PARTIAL RPM/PWR LOSS CRCRUISE 1 SO1366HW 2951 734 P559 L111959 NR 3 CYLINDER ROD BROKE IN CRUISE FLIGHT. 1L72 3O3 O A12CE E10EA 19980703005211998070300521EA 1998 7 3 98ZZZX2288 219980605G7414M333 IMPULSE COUPLINGSLICK PIPER PA32 PA32300 7103212SO LYC O540 IO540K1G5 41532EA MAG PAWL PIN WORN H K NONE O OTHER ININSP/MAINT 1 AL0540698 327440056 APPROXIMATE TIME ON COMPONENT 450 HOURS. NOTED ONE PAWL WORN MORE THAN THE OTHER, .130 INCH AS COMPARED TO .100 INCH. NOTE, .150 INCH MAXIMUM ALLOWED BY SLICK. ALSO, NOTED THAT ONE PAWL PIN SEEMED SOFTER THAN THE OTHER BY USING FILE AS DESCRIBED IN SLICK SB SB 1-80A. SUBMITTER THOUGHT THIS MAY BE OF FURTHER INTEREST. 1L71 3O3 O A3SO 1E4 19980703007311998070300731EA 1998 7 3 HEEA0014851 219980622G7532312320201 VALVE BELL 212 212 1181420SW PWA PT6T PT6T3 52045EA BLEED AIR SYSTEMFAULTY E HEEAK NONE O OTHER ININSP/MAINT 1 SW03 BLEED VALVE NOT READING CORRECTLY. TIME SINCE REPAIR 0:00. 1G71 4U4 U H4SW E22EA 19980703007421998070300742EA 1998 7 3 HEEA0014912 219980622G72103024780 GEARBOX BELL 212 212 1181420SW PWA PT6T PT6T3 52045EA COMBINING MAKING METAL E HEEAK NONE O OTHER ININSP/MAINT 1 SW031082G6610 31109 COMBINING GEARBOX HAS METAL CONTAMINATION ON NR 2 SIDE. 1G71 4U4 U H4SW E22EA 19980703007501998070300750NE 1998 7 3 HEEA0014938 219980622G72303017600 ENGINE BELL 412 412 1182202SW PWA PT6T PT6T3B 52045NE COMPR SECTION STALLS E HEEAK NONE R PARTIAL RPM/PWR LOSS ININSP/MAINT 1 SW033893P13424 33012 COMPRESSOR STALLS. 1G72 4U4 U H4SW E22EA 19980703007531998070300753GL 1998 7 3 HEEA0015043 219980626G726023063413 GEAR 6894171 BOLKMS105 BO105S 5626006EU ALLSN 250C 250C20B 03013GL ENGINE PITTED E HEEAK NONE O OTHER ININSP/MAINT 1 SW038197X CAG38881 S808 CAE835215 RECEIVING INSPECTION REVEALED: PITS BEYOND SERVICEABLE LIMITS ON A/O SEP. GEAR TEETH. INSTALLED A NEW A/O SEP. GEAR. 1G72 3U3 U H3EU E4CE 19980703007601998070300760EA 1998 7 3 HEEA0014838 119980622G6710204060762103 ACTUATOR BELL 212 212 1181420SW PWA PT6T PT6T3 52045EA MAIN ROTOR FAILED E HEEAK NONE O OTHER ININSP/MAINT 1 SW033208H 31304 MOTOR WILL NOT ACTUATE. 1G71 4U4 U H4SW E22EA 19980703008131998070300813GL 1998 7 3 HEEA0014914 219980622G731423068651 SEAL BELL 407 407 SW ALLSN 250C 250C47B GL FUEL PUMP LEAKING E HEEAK NONE K FLUID LOSS ININSP/MAINT 1 SW03447PH111 53114 FUEL PUMP SEAL DRAIN LEAKING. 1G71 3U3 UO H2SW E1GL 19980703008141998070300814GL 1998 7 3 HEEA0014915 219980622G731423069251 SEAL BELL 407 407 SW ALLSN 250C 250C47B GL FUEL PUMP LEAKING E HEEAK NONE K FLUID LOSS ININSP/MAINT 1 SW03447PH310 53114 FUEL PUMP SEAL DRAIN LEAKING. 1G71 3U3 UO H2SW E1GL 19980703008251998070300825GL 1998 7 3 HEEA0014934 219980622G732023068651 HMU BELL 407 407 SW ALLSN 250C 250C47B GL ENGINE FAILED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03403PH797 53177 FADEC FAILURE. 1G71 3U3 UO H2SW E1GL 19980703008911998070300891GL 1998 7 3 HEEA0015035 219980626G7320VSB628CP FADEC HORN BELL 407 407 SW ALLSN 250C 250C47B GL COCKPIT DEFECTIVE E HEEAK NONE O OTHER ININSP/MAINT 1 SW03408PH 53228 FADEC HORN WEAK AND INAUDIBLE WITH ENGINE RUNNING. 1G71 3U3 UO H2SW E1GL 19980714000611998071400061NE 1998 7 14 CA980331024 219980320G7261310137101 BEARING PWA 118 PW118 NE OIL PUMP SPALLED W K NONE O OTHER ININSP/MAINT 1 CA 189989089 115376 (CAN) OPER REPORTED METAL CONTAMINATION OF RGB. RGB FOUND COMPLETELY CLEAN WITH NO SIGN OF METAL CONTAMINATION. TURBOMACHINE CHIP DETECTOR CHECKED, FOUND A SINGLE FLAKE OF SHINY METAL . FILTERS CHECKED FOR CONTENT ANALYSIS. TURBOMACHINERY FILTER FND HEAVILY CONTAMINATED WITH M50 MAT'L. SOURCE OF METAL CONTAM IDENTIFIED FROM A SPALLED OIL PUMP DRIVE BRG. SECONDARY DAMAGE NOT EXTENSIVE, RESTRICTED TO COMPONENTS IN ACCY G/B OF REAR INLET CASE. BRG NEVER REPLACED. ORIG BRG FITTED TO ENG AT NEW PRODUCTION. ENG HAS HISTORY OF VIBRATION , POSSIBLE OIL PUMP DR BRG SUSTAINED DAMAGE OR REACHED ITS LIFE-LIMIT. PART TC: 19,018. 4 T E20NE 19980714000621998071400062EA 1998 7 14 CA980331026 219980306G852072877 TAPPET BODY LYC O360 AEIO360A1B6 41514EA ENGINE CAMSHAFT SPALLED W K NONE O OTHER ININSP/MAINT 1 CA 1746 L2663251A (CAN) DURING A SCHEDULED 50 HR INSP THAT CONTAINED TASKS REQUIRED TO C\W THE ON CONDITION PROGRAM ESTABILSHED FOR THE ENGINE. A MODERATE AMT OF SMALL METAL PARTICLES FOUND IN OIL FILTER ELEMENT. SUBSEQUENT INSP OF THE OIL SYSTEM SUCTION STRAINER REVEALED A SMALL AMOUNT OF MUCH LARGER METAL PARTICLES. NR 1 AND NR 3 CYLINDERS REMOVED . WITH THE CYLINDERS REMOVED, INSPECTION REVEALED ABNORMAL WEAR ON FRONT AND REAR LOBES OF THE CAMSHAFT AND THE TAPPETS WERE VERY BADLY SPALLED. THE ENGINE WAS REMOVED FOR REPAIR. 3 O 1E10 19980714000631998071400063CE 1998 7 14 CA980407023 119980323G32421338932 STATOR CESSNA500 550 2076604CE PWA JT15 JT15D4 52112NE LT BRAKE CRACKED W O OTHER O OTHER TXTAXI/GRND HDL 1 CA 331 (CAN) AIRCRAFT LANDED NORMALLY BUT WHILE TURNING AROUND AFTER TAXIING, THE LT WHEEL LOCKED UP. BRAKING WAS NORMAL DURING LANDING. WHEN MAINTEANCE REMOVED BRAKE, THE DISK-STATOR (P/N 133-893-2) WAS FOUND CRACKED IN THE AREA OF A KEY SLOT IN THE STATOR. BOTH MAIN WHEELS WERE REPLACED AND LT BRAKE WAS REPLACED AND BLED. PART TC: 498. 1L72 4F4 F A22CE E1NE 19980714001431998071400143GL 1998 7 14 98ZZZX2338 219980330G72506898735 TURBINE SUPORT BOLKMS105 BO105CBS 5626008EU ALLSN 250C 250C20 03013GL ENGINE CRACKED B EOPRK NONE O OTHER ININSP/MAINT 1 AL01492HL6074 CAT35860 S803 CAE836307 FOUND CIRCUMFERENTIAL CRACKS IN THE POWER TURBINE SUPPORT RADIUS AREA. REPLACED TURBINE. 1G72 3U3 UNCH3EU E4CE 19980714004261998071400426GL 1998 7 14 HEEA0015075 219980701G731323031866 NOZZLE 23033185 BELL 206 206L1 1182107SW ALLSN 250C 250C28B 03013GL ENGINE BLISTERED E HEEAK NONE O OTHER ININSP/MAINT 1 SW035012V CAT70486 45200 CAE860248 DURING MACHINING NOTED: BLISTERED COATING BEYOND SERVICEABLE LIMITS ON NR 2 NOZZLE, NR 2 TIP PATH. 1G71 3U3 U H2SW E1GL 19980714004271998071400427GL 1998 7 14 HEEA0015076 219980701G731323055430 NOZZLE 23033185 BELL 206 206L1 1182107SW ALLSN 250C 250C28B 03013GL ENGINE MISMANUFACTURED E HEEAK NONE W INADEQUATE Q C ININSP/MAINT 1 SW035012V CAT70486 45200 CAE860248 RECEIVING INSPECTION REVEALED: COATING LIFTING ON NR 2 NOZZLE 2ND STAGE TIP PATH. 1G71 3U3 U H2SW E1GL 19980714004281998071400428GL 1998 7 14 HEEA0015077 219980701G731323055430 NOZZLE 23033185 BELL 206 206L1 1182107SW ALLSN 250C 250C28B 03013GL ENGINE FLAKING E HEEAK NONE J WARNING INDICATION ININSP/MAINT 1 SW035745S CAT70404 45491 CAE860697 ENGINE REMOVED DUE TO OIL OVERTEMP. UPON INSPECTION OF TURBINE PARTS NOTED: COATING FLAKING ON NR 2 NOZZLE, NR 1 AND NR 2 TIP PATHS. 1G71 3U3 U H2SW E1GL 19980715000061998071500006NE 1998 7 15 98ZZZX2259 219980605G7323D210507 GOVERNOR WOODWARD CESSNA208 208B 2073701CE PWA PT6 PT6A114 52043NE ENGINE FAILED H K NONE O OTHER ININSP/MAINT 1 SW999762B5992 2173315U 208B0109 DURING ENGINE CHANGE, OVERSPEED GOVERNOR WAS TRANSFERRED FROM ENGINE DUE OVERHAUL TO LOANER ENGINE. AFTER INSTALL ON LOANER ENGINE, PR0P SHAFT WOULD NOT ROTATE. UPON REMOVAL OF OVERSPEED GOVERNOR, SMALL BALL BEARING CAME OUT OF GOVERNOR OIL PORT. FLUSHED RGB AND FOUND FIVE BALL BEARINGS, FOUND TWO MORE INSIDE GOVERNOR AFTER DISASSEMBLY OF GOVERNOR. FOUND BEARING CAGE AND OUTER RACE DAMAGED. ALL SEVEN BEARINGS WERE FOUND. REPLACED OVERSPEED GOVERNOR WITH OVERHAULED UNIT. 1H71 3T3 T A37CE E4EA 19980717000741998071700074EA 1998 7 17 AU980470 319980425G6111 BLADE WACO YMF YMF 9600412EA JACOBPR755 R755B2 35007SW SNSNCHW96JB W96JB EA PROPELLER CRACKED H K NONE F FLT CONT AFFECTED LDLANDING 1 AUS AD4765 (AUS) PROPELLER HAD SPLITS DEVELOPING AFT OF THE METAL LEADING EDGE AND BETWEEN LAMINATION MIDWAY ALONG THE CENTER OF BLADE. FINE CRACKS WERE ALSO FOUND IN THE LEADING METAL SHEATH AT RADIUS OF STRESS RELIEVING POINTS. 1Q71 3R3 R ATC542 E237 5 NP170 19980717000791998071700079 1998 7 17 AU980477 119980429G7120595104815 MOUNT 60510021 PWA PT6 PT6A112 52043NE ENGINE CRACKED H K NONE O OTHER ININSP/MAINT 1 AUS L12610R12611 (AUS) ENGINE MOUNT FOOT CRACKED. 3 T E4EA 19980717000901998071700090SO 1998 7 17 AU980488 219980301G8520629071629072 CRANKCASE BEECH 35 V35 1151538CE CONT O520 IO520BA 17032SO NR 2 CYL PAD CRACKED H K NONE O OTHER ININSP/MAINT 1 AUS 358 629071629072 1214397B (AUS) AT ENGINE BULK STRIP, FOLLOWING THE SEPARATION OF NR 2 CYLINDER HEAD (REFER MDR 98/0488), A 127 MM (5 INCH) LONG CRACK WAS FOUND IN THE CRANKCASE RUNNING FROM THE MATING FACE BACKBONE FLANGE DOWN TO THE NR 2 CYLINDER PAD. THE CRACK WAS OBSCURED BY THE LT MAGNETO AND HAD SILICON SEALANT SPREAD OVER ITS ENTIRE LENGTH. 1L71 3O3 O 3A15 E5CE 19980717000911998071700091SO 1998 7 17 AU980489 219980421G8530643767 GUIDE CESSNA182 182D 2072710CE CONT O470 O470L 17026SO NR 4 EXH VALVE WORN H K NONE O OTHER ININSP/MAINT 1 AUS (AUS) DURING PERIODIC INSPECTION, NR 4 CYLINDER COMPRESSION WAS 20/80. THE EXHAUST VALVE P/N 646286 WAS REMOVED AND FOUND TO BE WORN 0.203 MM (0.008 INCH) JUST ABOVE STEM NECK. THE VALVE GUIDE P/N 643767 WAS WORN 0.457 MM (0.018 INCH) AT THE LOWER HALF AREA. 1H71 3O3 ONT3A13 E273 19980717000931998071700093EA 1998 7 17 AU980491 219980418G8520STD1065 DOWEL PIPER PA28 PA28181 7102807SO LYC O360 O360A4M 41514EA CRANKSHAFT SHEARED H K NONE ERYVIBRATION/BUFFET PARTIAL RPM/PWR LOSS ENGINE STOPPAGE CRCRUISE 1 AUS 585 L1636736A L1636736A (AUS) CRANKSHAFT ACCESSORY DRIVE GEAR POSITIONING DOWEL SHEARED. AIRCRAFT SUFFERED A LOSS OF POWER AND WAS DAMAGED DURING A FORCED LANDING. ENGINE HAD SUFFERED A PROPELLER STRIKE PRIOR TO THE LAST OVERHAUL AT WHICH THE DOWEL PIN WAS INSPECTED BUT NOT REPLACED. 1L71 3O3 O 2A13 E286 19980717001001998071700100WP 1998 7 17 AU980498 119980404G6320STD2209 BOLT ROBSINR44 R44 7640120WP LYC O540 O540F1B5 41532EA ENGINE SEPARATED H K NONE E VIBRATION/BUFFET CRCRUISE 1 AUS L2518140A L2518140A (AUS) BOLT HEAD SEPARATED FROM THE SHANK. DOWEL PIN SHEARED. 1G71 3O3 O H11NM E295 19980717001011998071700101WP 1998 7 17 AU980499 119980426G6320A6881 SWITCH ROBSINR44 R44 7640120WP LYC O540 O540F1B5 41532EA M/R GRB TEMP FAULTY H K NONE N FALSE WARNING CRCRUISE 1 AUS (AUS) MAIN ROTOR GEARBOX TEMPERATURE SWITCH FAULTY. 1G71 3O3 O H11NM E295 19980717001181998071700118WP 1998 7 17 AU980516 219980501G726131080261 PUMP SWRNGNSA227 SA227AC 8780603SW GARRTTTPE331TPE33111U 01514WP ENG OIL SCAV FAILED H K NONE EB VIBRATION/BUFFET SMOKE/FUMES/ODORS/SPARKS DEDESCENT 1 AUS P44005 (AUS) ENGINE TURBINE OIL SCAVENGE PUMP DRIVE GEAR TEETH MISSING. TURBINE SEAL AND TURBINE ALSO DAMAGED. 2L72 4T4 TRTA8SW E4WE 19980717001221998071700122NM 1998 7 17 AU980520 119980422G7931APT761000 TRANSDUCER DHAV DHC8 DHC8201 2809001NM PWA PW120 PW123 NE OIL SYS FAULTY H K NONE EK VIBRATION/BUFFET FLUID LOSS CLCLIMB 1 AUS 54782520 (AUS) LT ENGINE OIL PRESSURE TRANSDUCER FAULTY. 2H72 4T4 TRTA13NM E20NE 19980717001381998071700138EA 1998 7 17 AU980536 219980513G8520LW12186 NUT LYC O540 LTIO540J2BD 41533EA ENGINE MISMANUFACTURED H K NONE W INADEQUATE Q C ININSP/MAINT 1 AUS (AUS) CONNECTING ROD NUT INCORRECTLY MACHINED AT FACTORY. 3 O E14EA 19980717001481998071700148EA 1998 7 17 AU980547 219980429G7414M3485SLICK BEARING SLICK 4370 LYC O360 O360C1F 41514EA MAGNETO LOOSE H K NONE O OTHER ININSP/MAINT 1 AUS 92090338 (AUS) MAGNETO BEARING SPINNING IN CAP. 3 O E286 19980717001541998071700154WP 1998 7 17 AU980553 219980519G73202762026223 PIPE SWRNGNSA227 SA227AC 8780603SW GARRTTTPE331TPE33111U 01514WP FUEL SYS CRACKED H K NONE ER VIBRATION/BUFFET PARTIAL RPM/PWR LOSS CRCRUISE 1 AUS P44495C (AUS) DP/P TRANSDUCER RIGID SUPPLY PIPE CRACKED AROUND BEND RADIUS. 2L72 4T4 TRTA8SW E4WE 19980717001631998071700163EA 1998 7 17 AU980562 219980521G8520L721061A BOLT PIPER PA31 PA31 7103102SO LYC O540 TIO540A2C 41532EA LT ENG NR 6 CYL FAILED H K NONE ER VIBRATION/BUFFET PARTIAL RPM/PWR LOSS CLCLIMB 1 AUS 1572 L721061A L721061A (AUS) LT ENGINE NR 6 CYLINDER HOLD-DOWN BOLTS/STUDS (6OFF) BROKEN. 1L72 3O3 O A20SO E14EA 19980717001651998071700165CE 1998 7 17 AU980564 119980511G7603 ARM BEECH 200 200BEECH 1152920CE PWA PT6 PT6A41 52043EA LT POWER LEVER LOOSE H K NONE E VIBRATION/BUFFET NRNOT REPORTED 1 AUS (AUS) LT ENGINE POWER LEVER INPUT ARM MOVING ON THE INPUT SHAFT. 1L72 4T4 T A24CE E4EA 19980717001691998071700169EA 1998 7 17 AU980568 219980527G8530LW14995 SPRING BEECH 76 76 1153005CE LYC O360 O360A1G 41514EA NR 2 CYL INT BROKEN H K NONE O OTHER ININSP/MAINT 1 AUS L2850836A (AUS) LT ENGINE, NR 2 CYLINDER INLET VALVE PUSHROD SHROUD TUBE RETAINING SPRING BROKEN IN HALF AND LYING IN THE BOTTOM OF THE ROCKER BOX. 1L72 3O3 O A29CE E286 19980717003151998071700315EA 1998 7 17 AU980578 219980415G7421REM40E SPARK PLUG PIPER PA28 PA28161 7102803SO LYC O320 O320D3G 41508EA SNSNCH ENGINE FAILED H K NONE EY VIBRATION/BUFFET ENGINE STOPPAGE LDLANDING 1 AUS L731339A (AUS) NR 3 CYLINDER TOP SPARK PLUG CENTER ELECTRODE CERAMIC BROKEN. NR 3 CYLINDER LOWER SPARK PLUG FOULED. 1L71 3O3 O 2A13 E274 19980717003351998071700335SO 1998 7 17 AU980601 219980505G8520537290 CRANKSHAFT CESSNA182 182K 2072724CE CONT O470 O470R 17026SO MCAULY ENGINE PITTED H K NONE O OTHER ININSP/MAINT 1 AUS 1788 712355 132305 712355 (AUS) CRANKSHAFT PITTED IN AREA OF CRANKSHAFT FELT SEAL. THE DEPTH OF THE PITTING WAS 0.127MM TO 0.254MM (0.005 INCH TO 0.010 INCH). SUSPECT CAUSED BY MOISTURE RETENTION OF THE FELT SEAL. 1H71 3O3 ONT3A13 E273 19980717003461998071700346NE 1998 7 17 AU980614 219980125G7321GEJN0236ANSETTS FCU CFMINTCFM56 CFM565A1 NE FUEL SYSTEM FAILED H E ENGINE SHUTDOWN EJ VIBRATION/BUFFET WARNING INDICATION NRNOT REPORTED 1 AUS 894 GEJN0236ANSE 731159 (AUS) NR 2 ENGINE ELECTRONIC FUEL CONTROL UNIT (EFU) FAULTY. WORKSHOP INVESTIGATION FOUND THE UNIT FAILED PRESSURE SUB-SYSTEM CHANNEL `A' TEST. PART TC: 21,089. 4 F E29NE 19980717003541998071700354SO 1998 7 17 AU980622 219980522G8530653446 CYLINDER CESSNA206 U206F 2073333CE CONT O520 IO520F 17032SO MCAULY ENGINE CRACKED H K NONE O OTHER ININSP/MAINT 1 AUS 175939R 175939R 931708 (AUS) ENGINE CYLINDER CRACKED BETWEEN THE EXHAUST VALVE AND THE LOWER SPARK PLUG HOLE. PART TC: 1,680. 1H71 3O3 O A4CE E5CE 19980717003571998071700357NE 1998 7 17 AU980625 219980606G73203016724 LINE PWA PT6 PT6A112 52043NE RT ENGINE BROKEN H K NONE W INADEQUATE Q C LDLANDING 1 AUS PCE12575 (AUS) RT ENGINE P3 LINE FOUND BROKEN AT COMPRESSOR CASE FLANGE END. SUSPECT CAUSED BY CONTINUALLY DISCONNECTING AND RECONNECTING THE LINE FOR ENGINE COMPRESSOR WASHES. 3 T E4EA 19980717003641998071700364WP 1998 7 17 AU980633 219980611G732289737524 FCU GARRTTTPE331TPE33111U 01514WP FUEL SYSTEM FAULTY H K NONE ER VIBRATION/BUFFET PARTIAL RPM/PWR LOSS TOTAKEOFF 1 AUS 5988 2173576 44709 (AUS) ENGINE FUEL CONTROL UNIT FAULTY. 4 T E4WE 19980717003731998071700373SO 1998 7 17 AU980642 219980611G7320630626 BRACKET CESSNA182 182A 2072704CE CONT O470 O470L 17026SO BALANCE TUBE BROKEN H K NONE O OTHER NRNOT REPORTED 1 AUS 069769R (AUS) ENGINE INDUCTION SYSTEM BALANCE TUBE SUPPORT BRACKET BROKEN. ENGINE BACKFIRE CAUSED BALANCE TUBE TO COME OUT OF RUBBERS. 1H71 3O3 ONT3A13 E273 19980717003771998071700377EA 1998 7 17 AU980646 219980611G742050383 IGNITOR LEAD 103815501E BEECH 200 200BEECH 1152920CE PWA PT6 PT6A41 52043EA HARTZL RT ENGINE BROKEN H K NONE O OTHER NRNOT REPORTED 1 AUS 10276 (AUS) RT ENGINE IGNITOR LEAD BROKEN. THE FOLLOWING DEFECTS IN THE IGNITION SYSTEM WERE ALSO FOUND: 1. RELAY P/N 50-380048-1. 2. FUEL INDICATION CB PANEL CONNECTOR J108 CONTAMINATED WITH MOISTURE AND CORROSION. 3. IGNITOR BOX P/N 10-381550. 1L72 4T4 T A24CE E4EA 19980717003821998071700382SO 1998 7 17 AU980651 219980204G8530 CYLINDER CESSNA150 150G 2071816CE CONT O200 O200A 17020SO ENGINE WORN H K NONE O OTHER ININSP/MAINT 1 AUS 65861 B1002 (AUS) NR 2 CYLINDER WORN BEYOND LIMITS. 1H71 3O3 O 3A19 E252 19980717003861998071700386NE 1998 7 17 AU980655 219980212G72303968007 MOTOR CFMINTCFM56 CFM565A1 NE COMPRESSOR FAILED H K NONE EJ VIBRATION/BUFFET WARNING INDICATION CLCLIMB 1 AUS 23691 2794ANSSNO03 (AUS) COMPRESSOR GUIDE VANE MOTOR FAULTY. PART TC: 23,691. 4 F E29NE 19980717003911998071700391SO 1998 7 17 AU980660 219980515G8550 HOSE CESSNA210 210M 2073450CE CONT O520 TSIO520R 17040SO TURBOCHARGER BURNT H K NONE K FLUID LOSS ININSP/MAINT 1 AUS 293517R (AUS) FLEXIBLE OIL SUPPLY LINES TO TURBOCHARGER AND OIL PRESSURE HOSE BURNT DUE TO BEING ROUTED UNDER THE REAR EXHAUST PIPE. ONE HOSE HAD BEEN BURNT SUFFICIENTLY FOR OIL LEAKAGE TO OCCUR. 1H71 3O3 O 3A21 E8CE 19980717004101998071700410SO 1998 7 17 AU980685 119980602G81204708183 VALVE PIPER PA31 PA31350 7103110SO LYC O540 LTIO540J2BD 41533EA HARTZL RT TURBOCHARGER WARPED H K NONE ER VIBRATION/BUFFET PARTIAL RPM/PWR LOSS TOTAKEOFF 1 AUS 2279 GLO106 L279268A (AUS) RT ENGINE TURBOCHARGER WASTEGATE BUTTERFLY VALVE WARPED CAUSING THE VALVE TO STAY OPEN. 1L72 3O3 O A20SO E14EA 19980717004151998071700415EA 1998 7 17 AU980690 219980506G8530 CYLINDER O4351 STNSONL5 L5B 8630204NE LYC O435 O4351 41516EA ENGINE LEAKING H K NONE K FLUID LOSS ININSP/MAINT 1 AUS L0033868 (AUS) NR 5 CYLINDER LEAKING FROM BARREL/HEAD JOINT. ENGINE WAS ON THE FIRST TEST FLIGHT FOLLOWING AN ENGINE REBUILD. 1H71 3O3 O A764 E228 19980722000031998072200003NE 1998 7 22 AU980473 219980421G73228063040 FCU WOODWARD 8063040 PILATSPC12 PC12 7090550EU PWA PT6 PT6A67 52043NE FUEL SYS MALFUNCTIONED H K NONE E VIBRATION/BUFFET NRNOT REPORTED 1 AUS 11416011 110012 (AUS) FUEL CONTROL UNIT FAULTY. NO FUEL FLOW INDICATION. SUSPECT FUEL VALVE STUCK IN CLOSED POSITION. 1L71 3T4 TRTA78EU E26NE 19980722000041998072200004NE 1998 7 22 AU980546 219980517G73203352528060 PIPE GE CFM56 CFM56* 13802NE NR 1 ENG FUEL LOOSE H K NONE K FLUID LOSS ININSP/MAINT 1 AUS 725496 (AUS) NR 1 ENGINE 9TH STAGE FUEL LINE (TC2 SENSE LINE) TO TURBINE, CLEARANCE CONTROL VALVE `B' NUT LOOSE. 4 F E2GL 19980722000051998072200005NE 1998 7 22 AU980626 219980529G7200 INDICATORS PILATSPC12 PC12 7090550EU PWA PT6 PT6A67 52043NE ENGINE FLUCTUATE H K NONE O OTHER CRCRUISE 1 AUS 110042 (AUS) ENGINE INSTRUMENTS FLUCTUATING. INSPECTION OF THE ENGINE AND THE OIL FILTER FOLLOWED BY GROUND RUNS AND TEST FLIGHT COULD NOT CONFIRM THE DEFECT. 1L71 3T4 TRTA78EU E26NE 19980724006491998072400649NE 1998 7 24 98ZZZX2428 219980603G8530615324 CYLINDER CVAC 440 C131D 2422750WP PWA R2800 R2800103W 52026NE NR 2 ENG NR 5 WORN C W2LMK NONE O OTHER ININSP/MAINT 1 SO15131CW 307 A181P0DV 542809 P33738 CYLINDER ASSY HAD EXTREME CLEARANCES BETWEEN VALVES AND VALVE GUIDES WHICH IS NOT INDICATIVE OF 307.0 HOURS OF OPERATION ON A CYLINDER. UTILIZING USAF SPECS, I.E., SODIUM FILLED DOME TYPE EXHAUST VALVES AND CLOSE TOLERANCE STEEL VALVE GUIDES. ALSO, EXCESSIVE PISTON TO CYLINDER BARREL SCUFFING. THIS CYLINDER ASSY SHOWS EVIDENCE OF 1,000 HOURS OF OPERATION USAGE. 2L72 4R4 R 6A6 5E8 19980724006501998072400650NE 1998 7 24 98ZZZX2429 219980603G8530615326 CYLINDER CVAC 440 C131D 2422750WP PWA R2800 R2800103W 52026NE NR 2 ENG NR 9 WORN C W2LMK NONE O OTHER ININSP/MAINT 1 SO15131CW 307 37615 542809 P33738 CYLINDER ASSY HAD EXTREME CLEARANCES BETWEEN VALVES AND VALVE GUIDES WHICH IS NOT INDICATIVE OF 307.0 HOURS OF OPERATION ON A CYLINDER ASSY. UTILIZING USAF SPECS, I.E., SODIUM FILLED DOME TYPE EXHAUST VALVES AND CLOSE TOLERANCE STEEL VALVE GUIDES. IN ADDITION, PISTON ASSY IS A FAA PMA P/N WHICH WHENTHIS ENGINE WAS OVERHAULED IN 1972, HAS BEEN CHANGED ALREADY, BUT THE ENG RECORDS DO NOT REFLECT THIS. THE R2800-52/99/101/103W O/H AND PARTS MANUALS SHOW SPECIFIC AND NON-SUBSTITUTABLE P&W P/N'S FOR THE PISTON INSTALLED IN THIS POSITION. THIS CYL ASSY SHOWS IN EXCESS OF 1,000 HRS OPER USAGE. 2L72 4R4 R 6A6 5E8 19980724006511998072400651NE 1998 7 24 98ZZZX2430 219980603G8530615324 CYLINDER CVAC 440 C131D 2422750WP PWA R2800 R2800103W 52026NE NR 2 ENG NR 15 WORN C W2LMK NONE O OTHER ININSP/MAINT 1 SO15131CW 307 5066 542809 P33738 CYLINDER ASSY HAD EXTREME CLEARANCES BETWEEN VALVES AND VALVE GUIDES WHICH IS NOT INDICATIVE OF 307.0 HOURS OF OPERATION ON A CYLINDER ASSY. UTILIZING USAF SPECS, I.E., SODIUM FILLED DOME TYPE EXHAUST VALVES AND CLOSE TOLERANCE STEEL VALVE GUIDES. ALSO, EXCESSIVE PISTON TO CYLINDER BARREL SCUFFING. THIS CYLINDER ASSY SHOWS EVIDENCE OF 1,000 HOURS OF OPERATION USAGE. 2L72 4R4 R 6A6 5E8 19980724006521998072400652NE 1998 7 24 98ZZZX2431 219980603G8530615325 CYLINDER CVAC 440 C131D 2422750WP PWA R2800 R2800103W 52026NE NR 2 ENG NR 11 WORN C W2LMK NONE O OTHER ININSP/MAINT 1 SO15131CW 307 RR1151 542809 P33738 CYLINDER ASSY HAD EXTREME CLEARANCES BETWEEN VALVES AND VALVE GUIDES WHICH IS NOT INDICATIVE OF 307.0 HOURS OF OPERATION ON A CYLINDER ASSY. UTILIZING USAF SPECS, I.E., SODIUM FILLED DOME TYPE EXHAUST VALVES AND CLOSE TOLERANCE STEEL VALVE GUIDES. ALSO, EXCESSIVE PISTON TO CYLINDER BARREL SCUFFING. PISTON ASSY IS AN FAA PMA P/N, WHICH, WHEN THIS ENG WAS OVERHAULED IN 1972, REVEALED CYL ASSY HAD BEEN CHANGED ALREADY, BUT ENG RECORDS DID NOT REFLECT THIS. R2800-99/52/101/103W O/H AND PARTS MANUALS SHOW SPECIFIC AND NON-SUBSTITUTABLE P&W P/N'S FOR THE PISTON IN THIS POSITION. THIS CYLINDER ASSY SHOWS EVIDENCE OF 1,000 HOURS OF OPERATION USAGE. 2L72 4R4 R 6A6 5E8 19980724006531998072400653NE 1998 7 24 98ZZZX2432 219980603G8530615323 CYLINDER CVAC 440 C131D 2422750WP PWA R2800 R2800103W 52026NE NR 1 ENG NR 8 WORN C W2LMK NONE O OTHER ININSP/MAINT 1 SO15131CW 167 1141 542809 NK510656 CYLINDER ASSY HAD EXTREME CLEARANCES BETWEEN VALVES AND VALVE GUIDES WHICH IS NOT INDICATIVE OF 167.1 HOURS OF OPERATION ON A CYLINDER ASSY. UTILIZING USAF SPECS, I.E., SODIUM FILLED DOME TYPE EXHAUST VALVES AND CLOSE TOLERANCE STEEL VALVE GUIDES. ALSO, EXCESSIVE PISTON TO CYLINDER BARREL SCUFFING. THIS CYLINDER ASSY SHOWS EVIDENCE OF 1,000 HOURS OF OPERATION USAGE. 2L72 4R4 R 6A6 5E8 19980724006561998072400656NE 1998 7 24 98ZZZX2435 219980603G8530615324 CYLINDER CVAC 440 C131D 2422750WP PWA R2800 R2800103W 52026NE NR 1 ENG NR 3 WORN C W2LMK NONE O OTHER ININSP/MAINT 1 SO15131CW 167 309880 542809 NK510656 CYLINDER ASSY HAD EXTREME CLEARANCES BETWEEN VALVES AND VALVE GUIDES WHICH IS NOT INDICATIVE OF 167.1 HOURS OF OPERATION ON A CYLINDER ASSY. UTILIZING USAF SPECS, I.E., SODIUM FILLED DOME TYPE EXHAUST VALVES AND CLOSE TOLERANCE STEEL VALVE GUIDES. ALSO, EXCESSIVE PISTON TO CYLINDER BARREL SCUFFING. THIS CYLINDER ASSY SHOWS EVIDENCE OF 1,000 HOURS OF OPERATION USAGE. 2L72 4R4 R 6A6 5E8 19980724006571998072400657NE 1998 7 24 98ZZZX2436 219980603G8530615326 CYLINDER CVAC 440 C131D 2422750WP PWA R2800 R2800103W 52026NE NR 1 ENG NR 9 WORN C W2LMK NONE O OTHER ININSP/MAINT 1 SO15131CW 167 A258 542809 NK510656 CYLINDER ASSY HAD EXTREME CLEARANCES BETWEEN VALVES AND VALVE GUIDES WHICH IS NOT INDICATIVE OF 167.1 HOURS OF OPERATION ON A CYLINDER ASSY. UTILIZING USAF SPECS, I.E., SODIUM FILLED DOME TYPE EXHAUST VALVES AND CLOSE TOLERANCE STEEL VALVE GUIDES. ALSO, EXCESSIVE PISTON TO CYLINDER BARREL SCUFFING. THIS CYLINDER ASSY SHOWS EVIDENCE OF 1,000 HOURS OF OPERATION USAGE. 2L72 4R4 R 6A6 5E8 19980724006601998072400660EA 1998 7 24 98ZZZX2439 219980505G8520LW12697 CRANKSHAFT PIPER PA38 PA38112 7103812SO LYC O235 O235L2C 41505EA ENGINE FAILED HS HE8SA UNSCHED LANDING Y ENGINE STOPPAGE NRNOT REPORTED 1 CE09244356462 2149 3879A1121 L2120215 AIRCRAFT DESTROYED AS A RESULT OF FORCED LANDING INDUCED BY A SEPARATION OF THE ENGINE CRANKSHAFT. SUBSEQUENT INVESTIGATION DISCLOSED A FATIGUE FAILURE ADJACENT TO THE CENTER MAIN BEARING JOURNAL. THIS ENGINE HAD EXPERIENCED 2 PREVIOUS PROPELLER STRIKES WHICH DID NOT REQUIRE CRANKSHAFT INSPECTION UNDER LYC AD 91-14-22. SUBMITTER SUGGESTED REVISING LYCOMING AD 91-14-22 TO REQUIRE CRANKSHAFT INSPECTION IAW LYC SL L163C, FOLLOWING ANY PROPELLER STRIKE RESULTING IN PROP REWORK OR REPLACEMENT. 1L71 3O3 O A18SO E223 19980724006611998072400661CE 1998 7 24 98ZZZX2440 119980421G2701MS276454 BEARING CESSNA172 172N 2072434CE LYC O360 O360A4M 41514EA YOKE LOOSE H K NONE O OTHER ININSP/MAINT 1 WP07264ER9520 17270716 L3184636A FOUND BEARING HOUSING AT BASE OF YOKE LOOSE. HOUSING IS PRESSED IN. A WELD MAY PREVENT THIS. 1H71 3O3 ONT3A12 E286 19980724006651998072400665EA 1998 7 24 98ZZZX2444 219980605G8520 CRANKCASE PIPER PA28 PA28161 7102803SO LYC O320 O320D3G 41508EA ALT MT AREA CRACKED D K NONE K FLUID LOSS ININSP/MAINT 1 EA058085A 288016065 L1752739A WHILE INVESTIGATING OIL LEAK, FOUND ENGINE CASE CRACKED RT FORWARD AFT BOSS WHERE ALTERNATOR BRACKET ATTACHES. ENGINE IS LYCOMING FACTORY OVERHAUL, INSTALLED 8-30-97, 340 HRS SMOH. 1L71 3O3 O 2A13 E274 19980724006731998072400673SO 1998 7 24 98ZZZX2452 219980615G8520653058A1 CAMSHAFT CESSNA414 414A 2075907CE CONT O520 TSIO520NB 17040SO PROP GOV DRIVE FAILED B PIYRE ENGINE SHUTDOWN J WARNING INDICATION CRCRUISE 1 EA212622A157 414A0310 OPERATOR EXPERIENCED AN IN-FLIGHT FEATHERING OF THE LEFT ENGINE AND IMMEDIA TELY SHUT DOWN. UPON INVESTIGATION, IT WAS REVEALED THE CAMSHAFT HAD BROKEN AT THE PROPELLER GOVERNOR DRIVE END. CAUSE UNKNOWN, UNIT SENT TO FACTORY FOR INSPECTION. 1L72 3O3 O A7CE E8CE 19980724006801998072400680SW 1998 7 24 98ZZZX2459 119980526G7160649643 INDUCTION TUBE MOONEYM20 M20K 5870220SW CONT O360 TSIO360MB 17025CE CYL NR 3 FLANGE CRACKED B EA6RK NONE K FLUID LOSS ININSP/MAINT 1 NE01747MR254 251212 317222 NOTICED FUEL STAINS AROUND CYLINDER NR 3. REMOVED AND INSPECTED, INDUCTION TUBE WAS CRACKED AROUND FLANGE. 1L71 3O3 O 2A3 E9CE 19980724006851998072400685SO 1998 7 24 98ZZZX2465 219980625G8540653236 DRIVE GEAR CESSNA172 R172E 2072413CE CONT O360 IO360D 17025SO OIL PUMP FAILED CLA O OTHER J WARNING INDICATION CRCRUISE 1 SO0924FC R1720199 062942R WHILE IN-FLIGHT, OIL PRESSURE AND TACHOMETER DROP TO ZERO, WAS ABLE TO LAND ON PRIVATE GRASS STRIP WITHOUT INCIDENT. DETERMINED THE OIL PUMP DRIVE GEAR HAS FAILED CAUSING FAILURE OF OIL PUMP, TACH DRIVE AND ALTERNATOR GEAR. 1H71 3O3 O 3A17 E1CE 19980724006871998072400687EA 1998 7 24 98ZZZX2467 219980608G7314 GASKET ROMEC R69080J4A PIPER PA31 PA31350 7103110SO LYC O540 LTIO540J2BD 41533EA RELIEF VALVE LEAK DLA O OTHER BK SMOKE/FUMES/ODORS/SPARKS FLUID LOSS LDLANDING 1 EA05101MA D8586 317752186 RL184768A UPON LANDING, PILOT REPORTED SMELLING FUEL IN THE CABIN. UPON INVESTIGATING THE SMELL, FOUND WHEN FUEL PUMPS AND EMERGENCY FUEL PUMP WERE TURNED ON, FUEL WAS LEAKING BADLY FROM THE GASKET AT THE RELIEF VALVE. LYC SB 529 AND CRANE/LEAR ROMEC SB 101SB020 COVERS THIS PROBLEM. THIS AIRCRAFT HAD JUST COME OUT OF INSPECTION THREE HOURS BEFORE THIS HAPPENED AND THERE WAS NO FUEL LEAKAGE AND SCREWS WERE NOT LOOSE. 1L72 3O3 O A20SO E14EA 19980724006941998072400694NE 1998 7 24 98ZZZX2474 219980603G7310416198001 TUBE BOLKMS117 BK117A3 5626015EU LYC LTS101LTS101650B1 41560NE ENG FUEL AFT FAILED H K NONE KY FLUID LOSS ENGINE STOPPAGE ININSP/MAINT 1 SW99967LS 7067 LE45224 DURING ENGINE COOL DOWN PERIOD, THE ENGINE SHUT DOWN ON ITS OWN. THE MAIN FUEL LINE (AFT REAR) TO THE MANIFOLD HAD CRACKED JUST BEHIND THE FLARE AT THE MANIFOLD CONNECTION, HALF OF THE CIRCUMFERENCE. 1G72 3U3 U H13EU E5NE 19980724007031998072400703GL 1998 7 24 98ZZZX2483 219980605G75102060626253 ACTUATOR HUGHES369 369D 4470706WP ALLSN 250C 250C20B 03013GL ENGINE ANTI-ICE FAILED B EOORK NONE O OTHER ININSP/MAINT 1 AL035074R 468 1151D CAE832750 DURING AN ANNUAL INSPECTION OF THE ENGINE ANTI-ICE VALVE SYSTEM, FOUND THE ACTUATOR ERRATIC (THIS AIRCRAFT HAS BEEN MODIFIED, BY FIELD APPROVAL, FOR INSTALLATION OF THE BELL HELICOPTER 206B ENGINE ANTI-ICE ACTUATOR SYSTEM). REPLACED ACTUATOR. 1G71 3U3 U H3WE E4CE 19980724007171998072400717WP 1998 7 24 98ZZZX2497 219980515G732121011445 EEC AMD FALC50FALCON50MYST2730106EU GARRTTTFE731TFE7313 01518WP ENGINE FAILED B K NONE O OTHER ININSP/MAINT 1 WP23XAAVE 117755 022 P76193 EEC WAS CONNECTED TO BENCH TEST EQUIPMENT TO ADJUST EFR SETTING. AFTER EEC WARM-UP PERIOD PRIOR TO ADJUSTING EFR, THE TECHNICIAN FOUND THE EEL WAS NOT FUNCTIONING. A REVIEW OF THE TEAR DOWN/REPAIR REPORT REVEALED THE EEC HAD BEEN REMOVED FROM SERVICE FOR THE SAME REASON THE TECHNICIAN FOUND WHILE ATTEMPTING TO BENCH SET THE EPR SETTING. IT WAS FURTHER NOTED THAT THERE WAS NO REPAIRS ACCOMPLISHED TO THIS EEC. THE FAA FORM 8130-3 STATED INSPECTION ONLY. 2L73 4F4 F A46EU E6WE 19980724007191998072400719NE 1998 7 24 SADF9803 219980607G7200 ENGINE BAC 146 AVRO146RJ1001500096EU LYC LF507 LF5071F NE NR 1 VIBRATION A SADFCD ABORTED TAKEOFF RETURN TO BLOCK E VIBRATION/BUFFET TOTAKEOFF 1 SO23505MM E3242 LF07262 BOG/VUP - FLT 594 - REJECTED TAKEOFF DUE TO HIGH VIBRATION (MAX TRUST 1.0 INCHREASING DURING RUNNING TO 1.2) ENGINE NR 1 REJECTED WAS DONE AT 65 KNOTS. IT WAS CLEANED AND ADJUSTED. VIBRATION PICKUP P246 CONNECTOR WAS CHECKED, AND FOUND OK. ENGINE NR 1 RUN-UP. N1 SET 95.1 AND VIBRATION WAS 0.5 IAW AMM 72-00-00. (X) 2H74 4F4 FRTA49EU E6NE 19980731003821998073100382NE 1998 7 31 CA980406023 219980219G73220164448390 FCU TURBOMECA 0164448390 SNIAS 350 AS350B 8680801EU TMECA ARRIELARRIEL1B 6OO30NE ENGINE MALFUNCTIONED W K NONE O OTHER LDLANDING 1 CA 399 327B 840 (CAN) ROTOR RPM WOULD DROP AS LOW AS 377 RPM EACH TIME A POWER DEMAND WAS MADE. NR WOULD ALWAYS RECOVER WITHIN 3-4 SECONDS. FCU REPLACED. 1G71 3U3 U H9EU E19EU 19980731003831998073100383GL 1998 7 31 CA980406025 219980403G723023005200 SCROLL 23005200 BELL 206 206L1 1182107SW ALLSN 250C 250C28B 03013GL COMPRESSOR CRACKED W K NONE O OTHER ININSP/MAINT 1 CA 1059 CAC70614 CAE860407 (CAN) CRACK FOUND IN COMPRESSOR SCROLL AT 2 O'CLOCK POSITION APPROXIMATELY 1.5 INCHES LONG. ALSO FOUND BLEED VALVE MOUNT SCREW THREADS DAMAGED. SUBMITTER STATED THIS IS THE THIRD INSTANCE THAT A CRACK HAS BEEN FOUND IN THIS AREA OF THE 250-C28 ENGINE BY THE REPORTING ENGINEER. 1G71 3U3 U H2SW E1GL 19980731003891998073100389EA 1998 7 31 CA980406046 219980307G7200 ENGINE BEECH 200 200BEECH 1152920CE PWA PT6 PT6A41 52043EA NR 1 FAILED W EA ENGINE SHUTDOWN UNSCHED LANDING MJ OVER TEMP WARNING INDICATION CLCLIMB 1 CA 4428 PCE81271 (CAN) DURING CLIMB, THE AIRCRAFT YAWED TO THE LEFT. THE NR 1 ENGINE OVERTEMPED. THE ENGINE WAS SHUTDOWN AND THE AIRCRAFT RETURNED TO BASE. POST-FLIGHT INSPECTION FOUND THE ENGINE HAD AN INTERNAL FAILURE RESULTING IN ENGINE PARTS EXITING THE ENGINE THROUGH THE EXHAUST STACKS. 1L72 4T4 T A24CE E4EA 19980731006451998073100645GL 1998 7 31 HEEA0015155 219980713G72506886407 WHEEL 6898735 BOLKMS105 BO105S 5626006EU ALLSN 250C 250C20B 03013GL ENGINE MISMANUFACTURED E HEEAK NONE W INADEQUATE Q C ININSP/MAINT 1 SW0350293556 CAT40303 S677 CAE835254 ENGINE REMOVED DUE TO COMPRESSOR OVERHAUL. TURBINE DISASSEMBLED DUE TO LOW POWER ON TEST CELL. UPON INSPECTION OF TURBINE PARTS NOTED: MEASURED .006 INCH OVER BLUEPRINT SPECS (6.190-6.191) ON NR 1 WHEEL OUTSIDE DIAMETER. INSTALLED A NEW NR 1 WHEEL. 1G72 3U3 U H3EU E4CE 19980731006461998073100646GL 1998 7 31 HEEA0015214 219980722G7230230052711 SPLINE ADAPTER ALLSN 250C 250C30S 03013GL COMPRESSOR MISMANUFACTURED E HEEAK NONE W INADEQUATE Q C ININSP/MAINT 1 SW03 68260 RECEIVING INSPECTION REVEALED: MEASURED .0005 INCH BELOW SPECS (.9855 INCH - .9860 INCH) ON SPLINE ADAPTER OUTSIDE DIAMETER. 3 U E1GL 19980731006471998073100647GL 1998 7 31 HEEA0015215 219980722G7230230052711 SPLINE ADAPTER BELL 206 206L3 1182108SW ALLSN 250C 250C30P 03013GL COMPRESSOR MISMANUFACTURED E HEEAK NONE W INADEQUATE Q C ININSP/MAINT 1 SW033116P 68262 51530 RECEIVING INSPECTION REVEALED: MEASURED .0005 INCH BELOW SPECS (.9855 INCH - .9860 INCH) ON SPLINE ADAPTER OUTSIDE DIAMETER. 1G71 3U3 U H2SW E1GL 19980807000031998080700003GL 1998 8 7 98ZZZX2531 219980608G72106893672 PINION GEAR 23063393 BELL 407 407 SW ALLSN 250C 250C47B GL GEARBOX GALLED B ALGRK NONE O OTHER ININSP/MAINT 1 SW03477AL850 NN76206 53203 CAE847197 UPON DISASSEMBLY AND INSPECTION OF PARTS, FOUND EXCESSIVE GALLING ON PINION GEAR AND SPALLING ON T/M GEAR. PINION GEAR HAD EXCESSIVE GALLING ON GEAR TEETH. POSSIBLY DUE TO IMPROPER MESHING OF GEARS. SECONDARY DAMAGE. T/M GEAR PN 689367. SN NN144843, TT: 849.6 HOURS. SPALLING GEAR TEETH. 1G71 3U3 UO H2SW E1GL 19980807000041998080700004GL 1998 8 7 98ZZZX2532 219980608G725023032328 ROTATING SEAL 23063354 BELL 407 407 SW ALLSN 250C 250C47B GL NR 5 MAKING METAL B ALGRK NONE O OTHER ININSP/MAINT 1 SW03477AL850 53203 CAE847189 ENGINE WAS REMOVED FOR MAKING METAL. REMOVED NR 5 BEARING AND FOUND METAL IN BEARING CAVITY. REMOVED NR 5 BEARING FOR INSPECTION AND FOUND METAL SLIVERS UNDER NR 5 BEARING NUT AND CAP LOCK WASHER. 1G71 3U3 UO H2SW E1GL 19980807000081998080700008GL 1998 8 7 98ZZZX2536 219980608G72506871505 BEARING 23063354 BELL 407 407 SW ALLSN 250C 250C47B GL FWD NR 5 FAILED B ALGRK NONE O OTHER ININSP/MAINT 1 SW03567AL282 MP74957 53246 CAE847271 ENGINE REMOVED FOR MAKING METAL. UPON INSPECTION BEARINGS FOUND BAD NR 5 BEARING. SOURCE OF METAL WAS CAUSED BY GEARBOX TORQUE METER AND PINION GEAR DETERIORATING. 1G71 3U3 UO H2SW E1GL 19980807001041998080700104EA 1998 8 7 CA980407012 219980328G7314RG9080 FUEL PUMP PIPER PA31 PA31 7103102SO LYC O540 TIO540A2B 41532EA ENGINE LEAKING W K NONE K FLUID LOSS ININSP/MAINT 1 CA L161761 (CAN) AFTER OVERHAULED ENGINE WAS INSTALLED, A LEAK CHECK WAS CARRIED OUT. WHEN AIRCRAFT BOOSTER PUMPS WERE TURNED ON, FUEL POURED FROM THE ENGINE DRIVEN FUEL PUMP THROUGH THE BASE DRAIN LINE. THE FUEL PUMP WAS REPLACED AND THE FAILED PUMP WAS RETURNED TO THE ENGINE OVERHAULER. 1L72 3O3 O A20SO E14EA 19980807001061998080700106SO 1998 8 7 CA980407016 119980103G291012035015013 LINES EMB 120 EMB120RT SO PWA 118 PW118 NE HAMSTD14RF 14RF9 NE RT NACELLE CHAFED W K NONE O OTHER ININSP/MAINT 1 CA 10347 115667 880529 (CAN) ON 'C' CHECK FOUND HYDRAULIC TUBES TOUCHING EACH OTHER AND CHAFING. TUBES LOCATED AT OUTBOARD OF RIGHT ENGINE NACELLE, AT ACCESS PANEL 44ZCR AND 44ZAR. ALSO, TWO OTHER LINES, P/N'S 120-35193-001 AND 120-35193-003. 2L72 4T4 TRTA31SO E20NE 6 CP11NE 19980807001111998080700111NE 1998 8 7 CA980407022 219980317G7210311468201 GEAR PWA 120 PW120A NE RGB SPALLED W K NONE O OTHER ININSP/MAINT 1 CA 1741211966 120872 (CAN) REDUCTION GEARBOX (RGB) WAS SENT FOR INVESTIGATION AFTER REPORTS THE RGB WAS MAKING METAL. DISASSEMBLY OF THE RGB FOUND THE SOURCE OF THE METAL WAS THE SPALLING OF THE FIRST STAGE GEARS. THERE WAS NO CONTRIBUTING FACTORS TO THE SPALLING OF THE FIRST STAGE GEARS, HOWEVER, THE RGB INPUT SHAFT HAD 2501.5 HOURS AND THE 1ST STAGE HELICAL GEARS EACH HAD 17,411.8 HOURS. ONCE THE 1ST STAGE HELICAL GEARS FAILED, THE RGB INPUT SHAFT WOULD SUFFER SECONDARY TOOTH DAMAGE. SECONDARY DAMAGE WAS ALSO SUFFERED TO THE NR 11 BEARING. THE NR 8 AND NR 9 BEARINGS WERE ALSO REPLACED AS A PRECAUTIONARY MEASURE. 4 T E20NE 19980807001161998080700116NE 1998 8 7 CA980415006 219980408G732039680010 ACTUATOR AIRBUS320 A320211 3930320EU CFMINTCFM56 CFM565A1 NE NR 2 ENGINE LEAKING W K NONE K FLUID LOSS ININSP/MAINT 1 CA 1784017840 731584 (CAN) FOUND NR 2 ENGINE LEAKING FUEL WHEN DOING WALKAROUND. TRACED LEAK TO VBV ACTUATOR MOTOR. REPLACED MOTOR, ENGINE RUN CARRIED OUT AND FUNCTIONALLY AND LEAK CHECKED SERVICEABLE. AIRCRAFT RETURNED TO SERVICE. 2L72 4F4 FRTA28NM E29NE 19980807001191998080700119NE 1998 8 7 CA980415012 219980330G7320714810 VALVE BOEING727 72722 1384002NM PWA JT8 JT8D7B 52053NE NR 1 ENGINE MALFUNCTIONED W CD ABORTED TAKEOFF RETURN TO BLOCK E VIBRATION/BUFFET TOTAKEOFF 1 CA 4309 657265 (CAN) DURING ENGINE SPOOL-UP IN PREPARATION TO TAKEOFF, NR 1 ENGINE EXPERIENCED MULTIPLE COMPRESSOR STALLS. AIRCRAFT RETURNED TO THE RAMP. ENGINE INSPECTED FOR DAMAGE AND F.O.D. NO DISCREPANCIES FOUND. FUEL PRESSURIZATION AND DUMP VALVE ADJUSTED. ENGINE RUN-UP TO CONFIRM OPERATION AFTER ADJUSTMENTS. ACCELERATION CHECK, CONFIDENCE CHECK, AND POWER LEVER RESPONSE CHECKED SERVICEABLE. AIRCRAFT RELEASED FOR SERVICE. 2L73 4F4 F A3WE E2EA 19980807001221998080700122NE 1998 8 7 CA980415015 219980406G74213037946 IGNITER BEECH 1900 1900D 1154162CE PWA PT6 PT6A67D NE NR 2 ENGINE FAILED W K NONE O OTHER ININSP/MAINT 1 CA 33 (CAN) DURING START ATTEMPT, THE NR 2 ENGINE FAILED TO IGNITE. MAINTENANCE FOUND THE RIGHT HAND IGNITION EXCITER PLUG WAS FAULTY. THE EXCITER WAS REPLACED AND THE AIRCRAFT WAS RELEASED FOR SERVICE. 2L72 4T4 TRTA24CE E26NE 19980807001241998080700124NE 1998 8 7 CA980415017 219980406G74213037946 IGNITER BEECH 1900 1900D 1154162CE PWA PT6 PT6A67D NE NR 2 ENGINE FAILED W K NONE O OTHER ININSP/MAINT 1 CA 12 PCEPS0163 (CAN) DURING START, THE RIGHT HAND CIRCUIT BREAKER FOR THE IGNITION EXCITER TRIPPED REPEATEDLY. THE EXCITER WAS REPLACED AND THE AIRCRAFT WAS RELEASED FOR SERVICE. 2L72 4T4 TRTA24CE E26NE 19980807001271998080700127EA 1998 8 7 CA980415020 219980324G8530 CYLINDERS CESSNA172 172P 2072436CE LYC O320 O320D2J 41508EA MCAULY1C160 1C160DTM GL ENGINE FAILED W EB ENGINE SHUTDOWN EMER. DESCENT RYJPARTIAL RPM/PWR LOSS ENGINE STOPPAGE WARNING INDICATION APAPPROACH 1 CA 1566 L1378839A 735155 (CAN) ON APPROACH, THE ENGINE EXPERIENCED POWER LOSS, WITH ENGINE PERFORMANCE DETERIORATING THE ENGINE FAILED AND THE AIRCRAFT GLIDED TO A SAFE LANDING. POST-FLIGHT ENGINE COMPRESSION TEST REVEALED ALL FOUR CYLINDERS HAD LOW COMPRESSION. THE CYLINDERS AND PISTONS WERE REMOVED AND SENT FOR REPAIR. AFTER REPAIR, THE CYLINDERS WERE REPLACED. THE ENGINE WAS GROUND RUN SERVICEABLE AND THE AIRCRAFT RETURNED TO SERVICE. 1H71 3O3 ONT3A12 E274 5 NP910 19980807001291998080700129EA 1998 8 7 CA980415023 219980310G7322 PY LINE EMB 110 EMB110P2 3260124SO PWA PT6 PT6A34 52043EA NR 2 ENGINE CRACKED W K NONE RE PARTIAL RPM/PWR LOSS VIBRATION/BUFFET NRNOT REPORTED 1 CA PCE56398 (CAN) DUE TO EXCESSIVE VIBRATION ON NR 2 ENGINE CAUSED BY FAULTY STARTER/GENERATOR, THE PY LINE CRACKED RESULTING IN A DROP IN NG. 1L72 4T4 T A21SO E4EA 19980807001331998080700133EA 1998 8 7 CA980416007 219980406G7322 VALVE CESSNA172 172N 2072434CE LYC O320 O320H2AD 41508EA MCAULY1C160 1C160DTM GL CARBURETOR BLOCKED W AEB UNSCHED LANDING ENGINE SHUTDOWN EMER. DESCENT WE INADEQUATE Q C VIBRATION/BUFFET CLCLIMB 1 CA 595 RL5776T 79756 (CAN) ON TAKEOFF, AT 1,100 FEET, THE ENGINE QUIT. THE PILOT RESTARTED THE ENGINE, BUT IT RAN ROUGH AND WOULD NOT EXCEED 1,700 RPM. PILOT RETURNED TO BASE. THE CARBURETOR WAS REMOVED AND TWO STONES, OF A SMOOTH CYLINDRICAL SHAPE OF PORCELAIN OR CERAMIC LIKE MATERIAL, WERE FOUND SITTING ON TOP OF THE BUTTERFLY VALVE. REMOVAL OF THE STONES AND REINSTALLATION OF THE CARBURETOR RECTIFIED THE PROBLEM. THE MANUFACTURER WAS CONTACTED AND STATED THAT THESE TYPE OF STONES WERE USED DURING OVERHAUL TO DEBUR PARTS. 1H71 3O3 ONT3A12 E274 5 NP910 19980807001351998080700135SO 1998 8 7 CA980416009 119980406G7170LW120984124 DRAIN LINE PIPER PA31 PA31P 7103120SO LYC O541 TIGO541E1A 41539EA NR 2 CYLINDER CHAFING W K NONE O OTHER ININSP/MAINT 1 CA RL47562 (CAN) FUEL DRAIN LINE OF NR 2 CYLINDER RUBBED (CHAFED) AGAINST THE PROPELLER ACCUMULATOR AND RISKED RUPTURING THE DRAIN INJECTION LINE. THIS LINE IS LESS THAN 4 INCHES FROM THE EXHAUST SYSTEM AND CONSTITUTES A HIGH RISK OF ENGINE FIRE IF THE DRAIN INJECTOR LINE RUPTURED. 1L72 3O3 O A8EA E19EA 19980807001391998080700139NE 1998 8 7 CA980417001 219980403G8530 HEAD DHAV DHC2 DHC2MK1 2800102EA PWA R985 R985AN14B 52008NE NR 9 CYLINDER SEPARATED W CD ABORTED TAKEOFF RETURN TO BLOCK RJ PARTIAL RPM/PWR LOSS WARNING INDICATION TOTAKEOFF 1 CA 416 5127 (CAN) ON TAKEOFF, THE PILOT HEARD A POP AND THE ENGINE HAD A POWER LOSS. ON RETURN TO RAMP, INSPECTION FOUND THE NR 9 CYLINDER HEAD SEPARATED FROM THE BARREL. THE CYLINDER ASSEMBLY WAS REPLACED AND THE AIRCRAFT RETURNED TO SERVICE. 1H71 3R3 R A806 5E1 19980807001531998080700153WP 1998 8 7 CA980417017 119980408G24212CM353CIJ SHAFT CVAC 440 440 2422902WP ALLSN 501D 501D13 03004GL AC GENERATOR SHEARED W H DEACTIVATE SYST/CIRCUITS H ELECT. POWER LOSS-50 PC CRCRUISE 1 CA 752 501678 (CAN) DURING CRUISE, LT ALTERNATOR LIGHT CAME ON. GENERATOR WOULD NOT RESET. MAINTENANCE INVESTIGATION FOUND THAT THE SHAFT WAS SHEARED. THE GENERATOR WAS NOT FOUND TO BE SEIZED. 2L72 4R4 T 6A6 E282 19980807001541998080700154EU 1998 8 7 CA980421005 119980328G5522B332200B00C SKIN DORNERDO228 DO228202 2992030EU GARRTTTPE331TPE3315 01514WP ELEVATOR DAMAGED W BA EMER. DESCENT UNSCHED LANDING CEFF.O.D. VIBRATION/BUFFET FLT CONT AFFECTED CRCRUISE 1 CA 770 P39245 (CAN) DURING CRUISE IN STILL AIR, AIRCRAFT STRUCK BY LIGHTNING. IT APPEARS TO HAVE ENTERED VHF COMM ANTENNA ON FORWARD FUSELAGE BELLY. EXIT POINT WAS AT RIGHT ELEVATOR TRAILING EDGE. A SMALL AREA AT EXIT POINT WAS MELTED INTO A BLOB. THE AFT HALF OF THE ELEVATOR TIP TOP AND BOTTOM HAD TOTALLY BEEN BLOWN OFF. APPROX 80 PERCENT OF AREA OF THE RIGHT ELEVATOR WAS RENDERED USELESS DUE TO EITHER TORN FABRIC OR FABRIC DEBONDING FROM ELEVATOR. OTHER DAMAGE INCLUDED, 1 COMM ANTENNA, 2 ADF ANTENNAS, 3 STATIC WICKS, 1 LANDING LIGHT, 1 TRANSPONDER. CREW NOTED AIRCRAFT ONLY ABLE TO CONTROL IN SLOW FLIGHT WITH ONLY CREW ON BOARD. EMERGENCY LANDING NECESSARY. 2H72 4T4 TRTA16EU E4WE 19980807001591998080700159EA 1998 8 7 CA980421012 119980403G5530C2FS569A BRACKET DHAV DHC2 DHC2MK1 2800102EA PWA R985 R985AN14B 52008NE BS 186 CRACKED W K NONE O OTHER ININSP/MAINT 1 CA 9326 JP211065 (CAN) DURING 700 HOUR INSPECTION, VERTICAL STABILIZER FRONT FIN PICKUP AT STA 186.40 WAS FOUND CRACKED. CRACK EXTENDED ALONG BOTH WELDED JOINTS BETWEEN SIDE WEBS AND UPPER NUT FACE. 1H71 3R3 R A806 5E1 19980807001661998080700166SO 1998 8 7 98ZZZX2599 219980611G7322 THROTTLE FACET MA45 CESSNA182 182N 2072730CE CONT O470 O470R 17026SO CARBURETOR STICKS D A K NONE O OTHER ININSP/MAINT 1 SW01110US 288 N171777CMF 18260234 800439R4 THROTTLE WOULD STICK WIDE OPEN AT FULL POWER. UPON DISASSEMBLY OF CARBURETOR, DETERMINED THAT WEAR OF THE FULL OPEN STOPS ON THE CARBURETOR BODY AND THROTTLE STOP ARM, THE POWER ENRICHMENT LEVER OPERATES THE AIR METERING PIN WOULD TRAVEL PAST ITS DESIGN LIMITS. EVENTUALLY, THE ACTION BROKE THE AIR METERING PIN AND JAMMED IT BETWEEN THE LEVER AND AIR METERING JET WHEN AT FULL POWER. RECOMMEND TO CHECK FOR EXCESSIVE WEAR OF STOPS, ESPECIALLY FULL OPEN. INSTALLED OVERHAULED MARVEL-SCHREBLER CARB., MA4-5, P/N 10-4893-1, FROM CONSOLIDATED FUEL SYSTEMS, INC. 1H71 3O3 ONT3A13 E273 19980807001671998080700167SO 1998 8 7 98ZZZX2600 219980527G8530639661 VALVE B3762A2 LUSCOM8 8A 8190104SO CONT A65 A651 17003SO NR 2 CYL INT FAILED H A UNSCHED LANDING R PARTIAL RPM/PWR LOSS CRCRUISE 1 AL031322B 5959 AIRCRAFT IN-FLIGHT, LOST POWER, MADE FORCED LANDING ON ROAD. DAMAGE TO WINGS AND FUSELAGE, NO INJURIES, TEAR DOWN OF ENGINE REVEALED BROKEN NR 2 CYLINDER INTAKE VALVE. ENGINE TSOH: 120 HOURS. 1H71 3O3 O A694 E205 19980807001681998080700168SO 1998 8 7 98ZZZX2601 219980501G8530SA631475 PISTON CESSNA210 210L 2073448CE CONT O520 IO520L 17032SO PIN BORE WORN D K NONE O OTHER ININSP/MAINT 1 SW171609X20 21060645 PISTON PIN BORE IN PISTON WORN. PISTONS HAVE 20 HOURS IN SERVICE SINCE NEW. PARTS WERE BOUGHT FROM SUPERIOR PARTS. 1H71 3O3 O 3A21 E5CE 19980807001721998080700172NE 1998 8 7 98ZZZX2605 219980623G7230810251 VANE PWA JT8 JT8D217A 52053NE T2 INNER SEAL DAMAGED B RA1RK NONE O OTHER ININSP/MAINT 1 SW05 717368 ENGINE REMOVED FROM SERVICE FOR LPT FAILURE. THE SECOND STAGE VANE DAMAGE AT INNER AIR SEAL. SPECIFIC CAUSE OF FAILURE IS UNDER INVESTIGATION AT GE. 4 F E9NE 19980807001841998080700184SO 1998 8 7 98ZZZX2617 219980616G8530637781 VALVE CESSNA340 340A 2076405CE CONT O520 TSIO520NB 17040SO NR 5 CYL EXHAUSTFAILED B G1TRK NONE O OTHER ININSP/MAINT 1 SW17340MD923 340A0058 R266560R WHILE DOING COMRPESSION CHECK ON THE ENGINE, FOUND LOW COMPRESSION NR 5 CYLINDER. REMOVED ROCKER BOX COVER AND FOUND THE EXHAUST VALVE TOP STEM WORN DOWN TO BE EVEN WITH THE ROTATOR. THE ROCKER ARM WAS ALSO DAMAGED BY HITTING THE ROTATOR. VALVE MAY HAVE BEEN DEFECTIVE. 1L72 3O3 O 3A25 E8CE 19980807001901998080700190SO 1998 8 7 98ZZZX2622 219980701G8530SA10200AL CYLINDER CESSNA172 172H 2072424CE CONT O300 O300D 17022SO NR 2 WORN D K NONE O OTHER ININSP/MAINT 1 GL193794F222 12214 17255289 34859D6D NR 2 CYLINER REMOVED FOR ZERO COMPRESSION. EXHAUST VALVE SEAT BADLY WORN AND EXHAUST GUIDE VERY LOOSE. INTAKE VALVE ALSO LEAKING AND SEAT IS TOO WIDE. EXHAUST VALVE EXTREMELY LOOSE IN GUIDE. COULD CAUSE HEAD OF VALVE TO BREAK OFF CAUSING A CATASTROPHIC ENGINE FAILURE. SUBMITTER RECOMMENDED CLOSER QUALITY CONTROL OF CYLINDER ASSY, NEW COMPLETE CYLINDER ASSY INSTALLED. 1H71 3O3 ONT3A12 E253 19980807002021998080700202EA 1998 8 7 98ZZZX2634 219980401G7322105257 CARBURETOR FACET MA3PA CESSNA150 152 2071835CE LYC O235 O235L2C 41505EA COTTER PIN MISOVERHAULED B EBVRK NONE W INADEQUATE Q C ININSP/MAINT 1 GL099KA 641 DM0765 15284552 DURING DISASSEMBLY FOR REPAIR, NOTED THAT ALL INSTALLED COTTER PINS WERE STANDARD STEEL HARDWRE AND NOT THE STAINLESS STEEL COTTER PINS SPECIFIED IN THE ILLUSTRATED PARTS LIST OF THE APPROPRIATE COMPONENT MM. 1H71 3O3 ONT3A19 E223 19980807002131998080700213EA 1998 8 7 98ZZZX2645 219980626G7322105135 CARBURETOR BOWL CESSNA172 172N 2072434CE LYC O320 O320H2AD 41508EA ENGINE LOOSE D A K NONE O OTHER ININSP/MAINT 1 GL19738QP3423 1375 CK818348 17270157 L777276T DURING FLIGHT, PILOT REPORTED A RATTLING NOISE WHEN THE CARBURETOR HEAT WAS APPLIED. AFTER LANDING, THE ENGINE COULD NOT BE SHUT DOWN USING MIXTURE CONTROL. DURING TROUBLESHOOTING, FOUND THAT CARBURETOR BOWL ATTACHMENT BOLTS HAD COME LOOSE, BUT THE LOCKING TAB HAD NOT BEEN DISTURBED. THIS, IN TURN, CAUSED A GAP OF .030 INCH BETWEEN THE BOWL AND UPPER MOUNT ALLOWING FUEL INTO THE ENGINE. SUBMITTER RECOMMENDED A CLOSER LOOK BE TAKEN AT THE CARBURETOR DURING ROUTINE INSPECTION PAYING ATTENTION TO THE BOLTS. 1H71 3O3 ONT3A12 E274 19980807002151998080700215SO 1998 8 7 98ZZZX2647 219980707G8520646277 LIFTER CESSNA310 310R 2074245CE CONT O550 IO550A SO TAPPET FACE FAILED D K NONE O OTHER ININSP/MAINT 1 EA05989041110 310R1240 280352R ENGINE REMOVED FROM SERVICE DUE TO METAL CONTAMINATION DUE TO PREMATURE FAILURE OF TAPPET BODIES. 1L72 3O3 O 3A10 E3SO 19980807002241998080700224NE 1998 8 7 98ZZZX2561 219980601G7210 GEARBOX EMB 120 EMB120RT SO PWA 118 PW118 NE REDUCTION GRBOX CHAFED B WVERK NONE O OTHER ININSP/MAINT 1 EA09212AS RGB115001 120008 PCE115001 ON REDUCTION GEARBOX JUST IN FRONT OF RIGHT FORWARD ENGINE MOUNT FORWARD LOWER BOLT HOLE, THERE IS A CHAFE MARK .958 INCH BY .480 INCH. DEEPEST SPOT IS .098 INCH CAUSED BY MISLOCATED BONDING WIRE FROM NACELLE TO ENGINE. 2L72 4T4 TRTA31SO E20NE 19980807002251998080700225NE 1998 8 7 SI3R98009 219980605G72105074T51G10 GEARBOX GC49 SAAB SF340 SF340A 7850100EU GE CT7TP CT79B 30030NE ENGINE WORN B SI3RK NONE O OTHER ININSP/MAINT 1 NE03 10542 1H100219 GEE785434 DISASSEMBLY OF GEAR CASE REVEALED THE TAB WASHER AND RETAINING RING ON THE FORWARD RIGHT IDLER GEAR BROKEN. BROKEN BEARING (P/N 775765-2) IN SLIDER BLOCK ASSY. INPUT PINION GEAR WORN. METAL CONTAMINATION LOCAL TO THIS AREA. HSS SO NR 86314 SE. CUST: WINGS WEST A/L 2L72 4T4 TRTA52EU E8NE 19980807002361998080700236NE 1998 8 7 98ZZZX2572 219980106G7240729237 COMBUSTION CASE BOEING747 747* NM PWA JT9 JT9D7J 52054NE ENGINE CRACKED H K NONE O OTHER ININSP/MAINT 1 SW99 6690012030 BD5083 FGPJM 662446 FPI INSPECTION OF THIS CASE FOUND A 360 DEGREE CIRCUMFERENTIAL CRACK INDICATION ON THE FRONT FLANGE. EDDY CURRENT INSPECTION FOUND AN INDICATION AROUND 20 PERCENT OF THE CIRCUMFERENCE. P & W HAVE BEEN ASKED TO INVESTIGATE THIS CASE AS PROPAGATION OF THIS CRACK WOULD HAVE CAUSED A RUPTURE EVENT. 2L74 4F4 FRTA20WE E20EA 19980807002391998080700239NE 1998 8 7 98ZZZX2573 219980606G7210664643 GEARBOX BOEING727 727251 138408HNM PWA JT8 JT8D15 52051NE ENG OIL LINE LEAK B EB1RE ENGINE SHUTDOWN K FLUID LOSS NRNOT REPORTED 1 EA13279US 0162 21158 P700522B PRECAUTIONARY SHUTDOWN NR 3 ENG. ENG LOW OIL PRESS LIGHT ILLUMINATED WHILE LANDING, OIL QTY GAUGE READS ZERO. ENG OIL PRESS LOW. COWLING OPENED AND MAJOR OIL LEAK NOTED. VISUAL INSP DID NOT UNCOVER OIL LEAK. ENG CLEANED AND OIL SYS RESERVICED. ENG STARTED AND LEAK IDENTIFIED IMMEDIATELY. BANJO FITTING ON THE OIL PRESS SENSE LINE FOUND LOOSE WHERE IT ATTACHED TO GRBX AND OIL WAS SPRAYING OUT. ENG SHUT DOWN AND INVEST REVEALED THREADS HOLDING BANJO FITTING TO GRBX WERE BADLY WORN. A HELIOCOIL INSERT INSTALLED IN THREADED BOSS OF GRBX. AFTER REPAIR OF GRBX, ENG RESERVICED WITH OIL AND LEAK CHECK PERFORMED. NO LEAKAGE NOTED DURING HIGH POWER ENG RUN AND ALL INDICATIONS NORMAL. ACFT RETURNED TO SERVICE. 2L73 4F4 F A3WE E2EA 19980807002401998080700240EA 1998 8 7 98ZZZX2574 219980615G741410349237 GEAR BEECH 60 60 1153602CE LYC O541 TIO541E1A4 41536EA RT MAGNETO FAILED H K NONE ER VIBRATION/BUFFET PARTIAL RPM/PWR LOSS ININSP/MAINT 1 NM11 P38 PILOT REPORTED ROUGH RUNNING ENGINE. REMOVED FUEL CONTROL, FLOW CHECKED. FOUND BAD RIGHT MAGNETO. TEETH STRIPPED FROM DISTRIBUTOR GEAR. 1L72 3O3 O A12CE E10EA 19980807002491998080700249GL 1998 8 7 98ZZZX2583 219980529G725023001967 WHEEL BOLKMS105 BO105S 5626006EU ALLSN 250C 250C20B 03013GL NR 3 SHROUD CRACKED B CK2RK NONE O OTHER ININSP/MAINT 1 SW03911ET2252 CAT40415 S187 CAE830500 UPON REMOVAL OF 3RD STAGE TURBINE WHEEL FOR CYCLE LIMIT, FOUND A CRACK COMPLETELY THROUGH THE WHEEL SHROUD AND A PORTION OF ONE BLADE. 1G72 3U3 U H3EU E4CE 19980807002521998080700252EU 1998 8 7 98ZZZX2586 119980706G26129560129980 DETECTOR SNIAS 350 AS350B2 8680813EU TMECA ARRIELARRIEL1D NE ENGINE FIRE FAILED B ARC0RK NONE O OTHER ININSP/MAINT 1 SW174035W989 13275 2912 9442 DURING 500-HOUR T INSP' INSPECTION OF 3 OF THE 6 ENGINE FIRE DETECTORS WERE FOUND DEFECTED PER TURBOMECA MM CHAP 26-11-00 PARA 1 INSPECTION PROCEDURES. TWO WERE OVERHEATED AND ON ONE THE OHMS WERE TOO LOW. SUBMITTER STATED THE OPERATOR BELIEVES THEY SHOULD HAVE HAD LONGER COMPONENT LIFE SINCE THIS IS THE ONLY FORM OF FIRE PROTECTION FOR THE AIRCRAFT. 1G71 3U3 U H9EU E19EU 19980807002531998080700253EU 1998 8 7 98ZZZX2587 119980706G26129560129980 DETECTOR SNIAS 350 AS350B2 8680813EU TMECA ARRIELARRIEL1D NE ENGINE FIRE FAILED B RC0RK NONE O OTHER ININSP/MAINT 1 SW174035W989 13276 2912 9442 DURING 500-HOUR T INSP' INSPECTION OF 3 OF THE 6 ENGINE