19950130001331995013000133EA 1995 1 30 95ZZZX411 219950107G8530ECI12967CP RINGS PIPER PA31 PA31350 7103110SO LYC O540 LTIO540J2BD 41533EA NR 1 CYLINDER DEFECTIVE D K NONE O OTHER ININSP/MAINT 1 AL0159764 151 317652037 L148468A OIL BLOWING OUT BREATHER. FOUND NR 1 CYLINDER AT 10/80. PULLED CYLINDER AND FOUND COMP. RINGS BROKEN IN MANY PIECES ABOUT .25 INCH TO 2.5 INCH. THESE RINGS ARE OF WRONG COMPOSITION. (BRITTLE). 1L72 3O3 O A20SO E14EA 19950130001361995013000136EA 1995 1 30 95ZZZX414 219950102G853071828 CYLINDER GULSTMAA1 AA1B 0631206SO LYC O235 O235C2C 41505EA ENGINE SEPARATION D O OTHER ER VIBRATION/BUFFET PARTIAL RPM/PWR LOSS CRCRUISE 1 NE019654L3800 2550 AA1B0154 L1185815 AIRCRAFT ENGINE, WHILE IN-FLIGHT, SUFFERED BARREL-TO-HEAD SEPARATION. SUSPECT CAUSE SEVERE METAL FATIGUE FROM WELDING MULTIPLE TIMES AND POSSIBLE IMPROPER WELDING PRACTICES AND MULTIPLE HEAT CYCLES. LYCOMING DOES NOT MANUFACTURE NEW CYLINDERS FOR THIS ENGINE. IF THEY DID, THIS WOULD NOT CONTINUE TO HAPPEN. SUBMITTER RECOMMENDS LYCOMING BE FORCED TO SUPPORT THE O-235C SERIES ENGINE. ALSO, MORE CAREFUL INSPECTION OF BARREL-TO-HEAD AREAS BY MAINTENANCE PERSONNEL AND OPERATORS. 1L71 3O3 O A11EA E223 19950303004291995030300429EA 1995 3 3 95ZZZX962 219950127G7322HA6IC5 CARBURETOR CESSNA182 R182 2072734CE LYC O540 O540J3C5 41532EA ACCELERATOR PUMP BINDING H K NONE W INADEQUATE Q C ININSP/MAINT 1 NM015482T23 75036815 R18201877 L2162940A CARBURETOR ACCELERATOR PUMP STICKING OR BINDING CAUSING EXTREMELY DIFFICULT THROTTLE OPERATION. THIS WAS A FACTORY REMANUFACTURED ENGINE WITH A NEW CARBURETOR. TIME IN SERVICE IS 23.0 HOURS. THIS HAS OCCURRED ONCE BEFORE ON THE SAME MODEL CARBURETOR, ON A DIFFERENT ENGINE AND AIRCRAFT. SUBMITTER RECOMMENDS INSPECTING ACCELERATOR PUMP AND THROTTLE SHAFT FOR FREEDOM OF MOVEMENT AND PROPER TRAVEL BEFORE INSTALLATION. 1H71 3O3 ORT3A13 E295 19950303004301995030300430EA 1995 3 3 95ZZZX963 219950201G7414S6LN MAGNETO PIPER PA31 PA31310 7103103SO LYC O540 TIO540J2BD 41532EA LT MAG SEPARATED D A UNSCHED LANDING KB FLUID LOSS SMOKE/FUMES/ODORS/SPARKS NRNOT REPORTED 1 SW9927337 14 8220066 3186 L160061 PILOT RETURNED TO BASE AFTER NOTICING SMOKE FROM LEFT ENGINE SOON AFTER TAKEOFF. MAINTENANCE DISCOVERED LT MAGNETO HAD SEPARATED FROM ENGINE CAUSING OIL LEAK AND SMOKE. REASON FOR MAGNETO SEPARATION IS UNKNOWN. NEW NUTS AND LOCKWASHERS HAD BEEN USED DURING INSTALLATION, AND STUDS ARE IN A GOOD CONDITION. 1L71 3O3 ORTA20SO E14EA 19950303004321995030300432SO 1995 3 3 95ZZZX965 219950207G741410357281 CAPACITOR 101630601 CESSNA310 T310R 2074246CE CONT O520 TSIO520B 17040SO RT ENG, RT MAG FAILED B AHTRK NONE O OTHER ININSP/MAINT 1 GL115094C466 9324 310R1417 RT176631R DURING ENGINE RUN-UP FOR A ROUTINE 50-HOUR INSPECTION, THE MECHANIC NOTED THE RIGHT ENGINE, RIGHT MAGNETO DID NOT RESPOND TO THE IGNITION SWITCH. FURTHER INVESTIGATION REVEALED THE MAGNETO CAPACITOR TO BE FAULTY. AFTER REPLACING THE CAPACITOR, THE MAGNETO OPERATION CHECKED NORMAL. NOTE: THIS IS THE SAME CONDITION THAT AD 94-06-09 PERTAINED TO, EXCEPT THE AD DOES NOT APPLY TO THIS CAPACITOR PART NUMBER OR DATE CODE. SUBMITTER STATED THIS CONDITION COULD CAUSE INJURY OR DEATH. 1L72 3O3 O 3A10 E8CE 19950303004411995030300441NE 1995 3 3 95ZZZX974 219950123G7230778487 MODULE DOUG DC9 DC981 3022081WP PWA JT8 JT8D217A 52053NE 6TH-7TH STAGES BLADE DAMAGE B AASTYA UNSCHED LANDING O OTHER CRCRUISE 1 SO23100225383 48024 P696930D FLT 410 - DURING FLIGHT, PILOT REPORTED A BANG ON NR 2 ENGINE. PILOT REDUCED POWER AND MADE A QRF. LANDING PERFORMED WITHOUT INCIDENTS. AT THE BASE, ENGINE WAS BORESCOPED BEFORE ANY ATTEMPT TO RESTART. DAMAGE FOUND ON 6TH, 7TH, AND 13TH STAGES COMPRESSOR GROUPS BLADES. DEBRIS IMPACTED ON TURBINE STAGES AND MIXER WITHOUT MAJOR DAMAGE. ENGINE WAS REPLACED, GROUND TEST PERFORMED SUCCESSFULLY. ACFT RETURNED TO SERVICE. 2L72 4F4 F A6WE E9NE 19950303005921995030300592NE 1995 3 3 95ZZZX981 219950206G72107757571 BEARING HAMSTD 77580010 SAAB SF340 340B 7860101EU GE CT7TP CT79B 30030NE GC 49 GEARCASE CRACKED BS SI3RK NONE O OTHER ININSP/MAINT 1 NE03174AE7018 9138 340B174 THE GEARCASE WAS RETURNED FOR 'MAKING METAL'. THE UNIT WAS DISASSEMBLED. EXAMINATION OF INTERNAL HARDWARE REVEALED A CRACKED INNER BEARING RACE ON THE PROPELLER SHAFT FORWARD ROLLER BEARING. REF. CMM 72-11-02. 2L72 4T4 TRTA52EU E8NE 19950303005931995030300593NE 1995 3 3 95ZZZX982 219950119G75306927221 COTTER PIN HAMSTD EVC32 BOEING747 747* NM PWA JT9 JT9* 52054NE ENG VANE CONTROLMISSING BSASI3RK NONE O OTHER ININSP/MAINT 1 NE03 75363 677 UPON DISASSEMBLY FOR OVERHAUL IT WAS OBSERVED THAT COTTER PIN, REF. CMM 75-31-01, FIGURE 2, ITEM 49, AND SHIM, FIGURE 2, ITEM 50, WERE NOT INSTALLED. NOTE: HEADED STRAIGHT PIN, FIGURE 2, ITEM 51, REMAINED IN INSTALLED POSITION. NOTE 2: LAST REPAIR PERFORMED BY ANOTHER AGENCY. 2L74 4F4 FRTA20WE E20EA 19950303005941995030300594NE 1995 3 3 95ZZZX983 219950206G72107757535 IDLER GEAR HAMSTD 77580010 SAAB SF340 340B 7860101EU GE CT7TP CT79B 30030NE GC 49 GEARCASE FAILURE BS SI3RK NONE O OTHER ININSP/MAINT 1 NE03201AE8129 1C6412310 340B201 THE UNIT WAS REMOVED FROM THE AIRCRAFT DUE TO A LT IDLER GEAR FAILURE. THE FAILED GEAR BROKE THROUGH THE GEAR CASE HOUSING. DISASSEMBLY OF THE UNIT REVEALED THE IDLER GEAR WEB HAD FAILED. ALSO, OBSERVED WAS BROKEN DAMPER RINGS, BROKEN RETAINING RINGS AND A BROKEN SLIDER BLOCK HOUSING. REF. CMM 72-11-02. 2L72 4T4 TRTA52EU E8NE 19950310000471995031000047EA 1995 3 10 95ZZZX1007 219950208G8530LW16343 INTAKE PIPE AMTR GHAWK GOSHAWK GL LYC O540 IO540P1A5 41532EA NR 3 CYL FLANGE BROKEN D K NONE O OTHER ININSP/MAINT 1 WP09345RM 304 001 L800048 DURING ROUTINE MAINTENANCE, MAINTENANCE PERSONNEL NOTED THAT NR 3 CYLINDER INTAKE PIPE WAS LOOSE AT CYLINDER. FOUND INTAKE PIPE BROKEN ABOUT 45 DEGREES AT THE FLANGE. REPLACED PART WITH A NEW INTAKE PIPE. OLD INTAKE PIPE HAD BEEN CHROMEPLATED BY UNKNOWN SHOP. SUSPECT HYDROGEN EMBRITTLEMENT. RECOMMEND THAT INTAKE PIPES NOT BE CHROMEPLATED. 1H71 3O3 O EXPA1H711E4 19950310000491995031000049SO 1995 3 10 95ZZZX1009 219950127G73226462124 PUMP FITTING GULSTM500 500A 0141104SW CONT O470 IO470M 17026SO ENGINE FUEL FAILED B UPNRO OTHER O OTHER NRNOT REPORTED 1 WP2557EB 1C109407BR 500A124571 FOUND FUEL PUMP HAS 90 DEGREE MALE TO FEMALE BRASS FITTING DEFECTIVE. FITTINGS ARE OVERTORQUED AND ONE FITTING FAILED IN-FLIGHT. OTHER PUMP, UPON REMOVAL, HAD FITTING FAIL WITH ABOUT 25 INCH/POUNDS OF TORQUE. 1H72 3O3 O 6A1 3E1 19950310000551995031000055NE 1995 3 10 95ZZZX1015 219950209G72503054289010 MANIFOLD DOUG DC8 DC871F 302199DWP GE CFM56 CFM562C1 13802NE INLET PORT RT CRACKED B EE4YK NONE O OTHER ININSP/MAINT 1 SO23825BX 28348 45978 693209 ENGINE NR 1, LOW PRESSURE TURBINE COOLING MANIFOLD DISTRIBUTOR INLET PORT CRACKED AT RIGHT SIDE. 2L74 4F4 FRT4A25 E2GL 19950310000561995031000056NE 1995 3 10 95ZZZX1016 219950209G72503054289010 MANIFOLD DOUG DC8 DC871F 302199DWP GE CFM56 CFM562C1 13802NE NR 3 ENGINE CRACKED B EE4YK NONE O OTHER ININSP/MAINT 1 SO23825BX 27785 45978 693303 ENGINE NR 3 LOW PRESSURE TURBINE COOLING MANIFOLD DISTRIBUTOR, CRACKED AT 10 O'CLOCK POSITION. 2L74 4F4 FRT4A25 E2GL 19950310002331995031000233SW 1995 3 10 HEEA954468 119950301G6320206040190005 PUMP BELL 206 206L1 1182107SW ALLSN 250C 250C30P 03013GL XMSN OIL LEAKING E HEEAK NONE K FLUID LOSS ININSP/MAINT 1 SW032125M 45649 LEAKING. REPLACED WITH SERVICEABLE OIL PUMP. 1G71 3U3 U H2SW E1GL 19950310002561995031000256GL 1995 3 10 HEEA954491 219950303G723023008090 GEAR SHAFT 23005200 BELL 206 206L1 1182107SW ALLSN 250C 250C28B 03013GL SPUR ADAPTER STEP WEAR E HEEAK NONE O OTHER ININSP/MAINT 1 SW033178K915 CAC70148 45765 CAE860046 ENGINE REMOVED DUE TO OIL OVERTEMP INSPECTION. UPON INSPECTION OF COMPRESSOR PARTS NOTED THE FOLLOWING: STEP WEAR BEYOND LIMITS ON SPUR ADAPTER GEARSHAFT FORWARD AND AFT SPLINES. INSTALLED NEW SPUR ADAPTER GEARSHAFT. 1G71 3U3 U H2SW E1GL 19950310004331995031000433NE 1995 3 10 95ZZZX1049 219950209G7261 ENGINE SNIAS 350 AS350D 8680803EU LYC LTS101LTS101600A3 41560NE OIL SYSTEM CHIP WARNING D A UNSCHED LANDING J WARNING INDICATION CRCRUISE 1 WP135771N 1344 DURING FLIGHT, ENGINE CHIP LIGHT WARNING MADE PRECAUTIONARY LANDING. MECHANIC INSPECTED ENGINE LUBE SYSTEM, CHIP PLUGS AND WIRING, FOUND NO DEFECTS. ACFT RETURNED TO SERVICE. 1G71 3U3 U H9EU E5NE 19950310005861995031000586SO 1995 3 10 95ZZZX1095 219950201G8540 GEAR TCRAFT19 F19 9230703GL CONT O200 O200A 17020SO CRANKSHAFT FAILED D A UNSCHED LANDING Y ENGINE STOPPAGE CRCRUISE 1 SO0420001 F126 255880 ACFT ON LOCAL FLIGHT WHEN ENGINE QUIT AT 1,000 FEET AGL. EMERGENCY LANDING MADE WITH ACFT DAMAGE. INVESTIGATION FOUND RT MAG BROKEN AT BASE. BOLTS HOLDING GEAR TO CRANKSHAFT FAILED. STARTER AND CLUTCH FROZEN. 1H71 3O3 O 1A9 E252 19950310005921995031000592EA 1995 3 10 95ZZZX1101 219950201G741410682016 DISTRIBUTOR GEARBENDIX D6LN3000 CESSNA182 R182 2072734CE LYC O540 O540J3C5 41532EA MAG TEETH STRIPPED D K NONE O OTHER ININSP/MAINT 1 SW074949S157 3070356 R18201488 L2110340A ACFT WAS FLOWN ON THE PREVIOUS EVENING. NO PROBLEMS NOTED. NEXT MORNING, ACFT WOULD NOT START. AFTER TROUBLESHOOTING ACFT, FOUND MAGNETO PROBLEMS UPON DISASSEMBLY OF MAG. BOTH DISTRIBUTOR GEARS WERE SEVERELY DAMAGED (TEETH WERE STRIPPED FROM BOTH GEARS). A NEW MAG WAS INSTALLED AND NO OTHER PROBLEMS WERE ENCOUNTERED. ACFT WAS RELEASED FOR SERVICE. 1H71 3O3 ORT3A13 E295 19950310005951995031000595SO 1995 3 10 95ZZZX1104 219950131G8540646209 DAMPENER CESSNA421 421C 2076016CE CONT O520 GTSIO520N 17032SO ACCESSORY CASE SEPARATED B ETERK NONE O OTHER ININSP/MAINT 1 SO116794D730 421C1030 FOUND METAL IN OIL. FOUND REAR ACCESSORY CASE JOURNAL HOLDING STARTER ADAPTER SHAFT SEVERELY WORN AND WALLOWED OUT. VISCOUS DAMPENER SEPARATED FROM HUB. 1L72 3O3 O A7CE E7CE 19950310006051995031000605SO 1995 3 10 95ZZZX1114 219950218G8530 ROCKER BOSS CESSNA150 150L 2071826CE CONT O200 O200A 17020SO ENGINE CYLINDER FAILED D A UNSCHED LANDING R PARTIAL RPM/PWR LOSS NRNOT REPORTED 1 SW173XZ 336 15074013 72IABKA48 CYLINDER EXHAUST AND INTAKE VALVE ROCKER BOSSES SEPARATED DURING FLIGHT RESULTING IN PRECAUTIONARY LANDING DUE TO LOSS OF ENGINE POWER. CYLINDER REPLACED AND AIRCRAFT RETURNED TO SERVICE. REF. AD 94-05-05. 1H71 3O3 O 3A19 E252 19950310006081995031000608SO 1995 3 10 95ZZZX1117 219950118G732463432610A9 FLOW DIVIDER CESSNA402 402B 207590PCE CONT O520 TSIO520E 17040SO ENGINE FUEL DEFECTIVE C K NONE O OTHER ININSP/MAINT 1 SW07535A 175 402B0591 20650271E PILOT REPORTED LT ENGINE WOULD NOT MAKE A CLEAN SHUT DOWN. INVESTIGATION REVEALED FLOW DIVIDER CHECK VALVE WAS PASSING FUEL BELOW PRESET PRESSURE. FOUND RUBER DIAPHRAGM DRIED OUT DUE TO LACK OF USE. 1L72 3O3 O A7CE E8CE 19950310006091995031000609SO 1995 3 10 95ZZZX1118 219950119G73226462122 FUEL PUMP BEECH 33 F33A 1151425CE CONT O520 IO520BA 17032SO ENGINE FAILED C A UNSCHED LANDING Y ENGINE STOPPAGE CRCRUISE 1 SW071096W 65 CE436 569112 ENGINE LOST POWER WHEN REDUCED FOR DESCENT. EFFORTS TO RESTART ENGINE FAILED. AIRCRAFT MADE AN UNEVENTFUL OFF AIRPORT LANDING. AFTER AIRCRAFT SAT, ENGINE WAS ABLE TO BE RESTARTED. PUMP WAS REMOVED AND SENT OUT FOR CHECK. MULTIPLE DISCREPANCIES WERE FOUND IN VALVE SEAT ALIGNMENT CAUSING ENGINE TO RUN RICH ON POWER REDUCTION. UNIT OVERHAULED LESS THAN 100 HOURS PRIOR BY CRS RV3R829L. 1L71 3O3 O 3A15 E5CE 19950310006201995031000620SO 1995 3 10 95ZZZX1129 219950206G7322 ENGINE CESSNA150 150M 2071830CE CONT O200 O200A 17020SO CARB RAN ROUGH D O OTHER ER VIBRATION/BUFFET PARTIAL RPM/PWR LOSS NRNOT REPORTED 1 GL13501PA 1772 15077482 275920R AD 93-18-03 AND PRECISION AIRMOTIVE SB NR MSA-2 R1, WAS DONE ON THIS CARB. AT 1521 HRS SMOH WHICH IS THE SINGLE PIECE VENTURI. IT WAS DONE BY A REPAIR STATION. AT 1771 HRS SMOH, ENGINE BEGAN TO RUN EXTREMELY ROUGH. OAT WAS ABOUT 27 DEGREES FAHRENHEIT. INVESTIGATION FOUND OUT THAT IF SINGLE PIECE VENTURI WAS INSTALLED AND ENGINE RAN ROUGH, IT NEEDED A DIFFERENT METERING NOZZLE, KIT PN 666-942. THIS WAS DONE AND IT RAN FINE. SUBMITTER SUGGESTS IF SINGLE PIECE VENTURI IS INSTALLED, THAT CHANGING THE FUEL NOZZLE IS A MUST. IT IS COVERED IN SB MSA-2. 1H71 3O3 O 3A19 E252 19950320000561995032000056GL 1995 3 20 95ZZZX1138 219950221G723023007217 MOUNT ASSY ALLSN 250C 250C30P 03013GL COMPRESSOR MISMANUFACTURED B UP9RK NONE W INADEQUATE Q C ININSP/MAINT 1 NM07 1177 821 CAE895130 MOUNT FACE TO MOUNT BOSS HEIGHT LIMITS ARE 1.715 INCHES TO 1.707 INCHES IN THE O/H MANUAL. THIS MOUNT MEASURED 1.770 INCHES TO 1.730 INCHES. THE MISALIGNMENT DAMAGED THE SPUR ADAPTER, GEAR SHAFT, COUPLING ADAPTER, AND IMPELLER BORE. 3 U E1GL 19950320000571995032000057WP 1995 3 20 95ZZZX1139 219950222G72503101512 BLADE 31016031 MTSBSIMU2 MU2B60 5780460CE GARRTTTPE331TPE33110 01514WP 1ST STAGE FAILED B DQIRCD ABORTED TAKEOFF RETURN TO BLOCK J WARNING INDICATION TOTAKEOFF 1 NM07132BK6530 90350120012 1529A P36236 DURING TAKEOFF POWER APPLICATION, LT ENGINE DEVELOPED HIGHER THAN NORMAL ITT. THE ENGINE WAS VISUALLY INSPECTED AND WAS FOUND TO HAVE EJECTED INTERNAL PARTS FROM THE TAILPIPE. TEAR DOWN INSPECTION REVEALED CAUSE TO HAVE BEEN GENERATED FROM ONE FIRST STAGE TURBINE BLADE FAILURE. BLADE TSN, 6529.8 - CSN 6988. 1H72 3T4 TRTA10SW E4WE 19950320000661995032000066SO 1995 3 20 95ZZZX1148 219950112G8530 CYLINDERS BEECH 36 A36TC 1151603CE CONT O520 TSIO520UB 17040SO ROCKER SHAFT EXCESS WORN B CCARK NONE O OTHER ININSP/MAINT 1 EA1748PD 581 EA75 515609 FACTORY NEW CYLINDERS TT 581.4 HOURS. INSTALLED 2-1-91, LOW COMPRESSION ALL CYLINDERS. CYLINDERS ARE WORN BEYOND SERVICEABLE LIMITS AND HAVE SEVERE RING WEAR. ROCKER SHAFTS ARE SEVERELLY WORN AND UNAIRWORTHY. 1L71 3O3 O 3A15 E8CE 19950320000671995032000067SO 1995 3 20 95ZZZX1149 219950203G8520 CAMSHAFT CESSNA402 402A 207590MCE CONT O520 TSIO520E 17040SO GEAR END BROKEN G O OTHER Y ENGINE STOPPAGE CRCRUISE 1 GL194584Q71 402A0084 183466R IN-FLIGHT ENGINE SHUT DOWN. CHECKED PROBLEM AND FOUND NO MOVEMENT IN VALVE TRAIN, ETC., WHEN PROP MOVED. PULLED ENGINE AND SENT BACK TO OVERHAUL AGENCY. VERIFIED UPON DISASSEMBLY THAT CAMSHAFT WAS BROKEN NEAR GEAR END. 1L72 3O3 O A7CE E8CE 19950320000771995032000077EA 1995 3 20 95ZZZX1159 219950220G7414ES103910881 COIL ELECTROSYS 103493653 PIPER PA34 PA34200 7103405SO LYC O360 LIO360C1E6 41515EA MAGNETO CRACKED B QKKRK NONE O OTHER ININSP/MAINT 1 CE01 0110063 DURING INSPECTION PER CUSTOMER INSTRUCTIONS, COIL CRACK WAS NOTED. REMOVED AND TESTED COIL. FOUND HIGH VOLTAGE LEAK OUT FROM CRACK. SUSPECT CAUSE MAY BE FROM MANUFACTURE DATE STAMP IN INSULATION. CRACK LOCATION ABOUT 1 INCH FROM OUTPUT TAB. 1L72 3O3 O A7SO 1E10 19950320000811995032000081EA 1995 3 20 95ZZZX1163 219950206G854071667 LOCK PLATE PIPER PA23 PA23250 7102308SO LYC O540 IO540C1B5 41532EA IDLE GEAR FAILED D EA ENGINE SHUTDOWN UNSCHED LANDING Y ENGINE STOPPAGE CRCRUISE 1 SO036792Y 274130 L526048 DURING PART 91 OPERATION, LEFT ENGINE QUIT RUNNING AND PILOT FEATHERED PROP AND LANDED AT AIRPORT. INSPECTION FOUND LOCK TAB FOR BOLT ON IDLE GEAR HAD BROKEN OFF AND BOLT BACKED OUT AND ENGINE JUMPED TIME AND QUIT. 1L72 3O3 O 1A10 1E4 19950320000831995032000083SO 1995 3 20 95ZZZX1165 219950216G8540643257 SHAFT GEAR 643259A5 CESSNA421 421C 2076016CE CONT O520 GTSIO520L 17032SO STARTER CLUTCH FAILED B QX2RK NONE O OTHER ININSP/MAINT 1 EA1188604429 421C0604 608427 DURING DISASSEMBLY OF THIS ENGINE, THE 'NEW STYLE' STARTER CLUTCH (REF: SB M92-10) GEAR TEETH WERE STARTING TO FAIL. ALSO, REF: CRITICAL SB 94-4. 1L72 3O3 O A7CE E7CE 19950320000841995032000084SO 1995 3 20 95ZZZX1166 219950216G8540643257 SHAFT GEAR 643259A5 CESSNA421 421C 2076016CE CONT O520 GTSIO520L 17032SO STARTER CLUTCH FAILED B QX2RK NONE O OTHER ININSP/MAINT 1 EA1188604429 421C0604 604981 DURING DISASSEMBLY OF THIS ENGINE, THE 'NEW STYLE' STARTER CLUTCH (REF: SB M92-10) GEAR GEETH WERE STARTING TO FAIL. ALSO, REF: CRITICAL SB 94-4. 1L72 3O3 O A7CE E7CE 19950320004361995032000436EA 1995 3 20 95ZZZX1208 219950215G73222525033 REGULATOR BODY BENDIX RSA10 LYC O540 IO540* 41532EA FUEL INJECT CRACKED D K NONE O OTHER ININSP/MAINT 1 SO09 FOUND CRACK AT THE CENTERBODY BELLOWS OPENING WITH O.E.M.'S BRASS BELLOWS ALREADY INSTALLED. RECOMMENDATIONS - HAVE A BETTER BELLOWS INSTALLING TOOL AND BIGGER BODY SUPPORT. 3 O 1E4 19950320004371995032000437EA 1995 3 20 95ZZZX1209 219950217G8520 CONNECT ROD PIPER PA31 PA31350 7103110SO LYC O540 LTIO540J2BD 41533EA NR 1,2,3 CYLS FAILED D EA ENGINE SHUTDOWN UNSCHED LANDING ERKVIBRATION/BUFFET PARTIAL RPM/PWR LOSS FLUID LOSS CLCLIMB 1 EA213581C4998 606 318052091 L110068A AFTER TAKEOFF, RIGHT ENGINE BECAME VERY ROUGH. ENGINE WAS FEATHERED, AIRCRAFT RETURNED TO AIRPORT AND LANDED. INSPECTION FOUND CONNECTING ROD CAPS HAD SEPARATED FROM NR 1, NR 2, AND NR 3 RODS. CONNECTING ROD PENETRATED BOTH BOTTOM AND TOP OF ENGINE CASE. 1L72 3O3 O A20SO E14EA 19950320004451995032000445 1995 3 20 95ZZZX1217 119950221G7312101050A1 VALVE ASSY CHNDLREVANS PWA JT9 JT9* 52054NE FUEL DEICE MISOVERHAULED D K NONE W INADEQUATE Q C ININSP/MAINT 1 NE03 CLEAR SILICONE COMPOUND USED FOR POTTING IN SWITCH CAVITY INSTEAD OF SILASTIC 'E' RTV. REMOVED TO CONVERT TO 101050A1. WIRE ENDS LEFT SUSPENDED IN CLEAR SILICONE. ORIGINAL PART NUMBER AND PARTS LIST NUMBER CROSSED OUT ON NAMEPLATE AND NEW P/N VIBROPEENED IN INCORRECT LOCATION. UNIT WAS RECEIVED FROM FEDERAL EXPRESS FOR OVERHAUL. 4 F E20EA 19950320004491995032000449EA 1995 3 20 95ZZZX1221 219950123G853076038 VALVE COVER PIPER PA31 PA31P 7103120SO LYC O541 TIGO541E1A 41539EA NR 4 CYL CRACKED DL K NONE K FLUID LOSS ININSP/MAINT 1 SO0911AB 31P7300169 L77962 OPERATOR/OWNER COMPLAINED OF OIL LEAK ON LEFT ENG. REMOVED COWLING AND FOUND OIL AROUND 2-4-6 CYLINDER AREAS. WASHED DOWN ENGINE. RAN AND SHUT DOWN ENGINE, FOUND OIL SEEPING FROM AROUND NR 4 CYLINDER VALVE COVER/GASKET. WASHED AREA AND RAN ENGINE AGAIN. FOUND OIL LEAKING AT SURFACE OF VALVE COVER. REMOVED VALVE COVER, FOUND COVER, PN 76038, CRACKED WHERE INTAKE ROCKER ARM HAD BEEN HITTING. 1L72 3O3 O A8EA E19EA 19950320007381995032000738SO 1995 3 20 95ZZZX1253 219950301G8520 CRANKSHAFT BEECH 35 V35B 1151548CE CONT O550 IO550B SO NR 3 CRANK CHEEKBROKEN G K NONE O OTHER ININSP/MAINT 1 GL131693W 1006 D9389 249112R ENGINE DISASSEMBLY REVEALED THE CRANKSHAFT HAD FAILED THROUGH THE NR 3 CRANK CHEEK. THE FRACTURE FACE WAS EXAMINED BY THE TCM METALLURGIST WHO CONFORMED THE FAILURE WAS IN BENDING OVERLAOD. THE NR 1 AND NR 2 MAIN BEARINGS WERE HAMMERED OUT TO EXTRUDE THE BEARINGS. THE CRANKCASE PARTING SURFACE WAS SEVERELY FRETTED AT THE NR 2 MAIN BEARING SUPPORT. FRETTING WAS ALSO PRESENT, BUT TO A LESSER DEGREE, ON THE NR 1 AND NR 3 MAIN BEARING SUPPORTS. BEARING AND ALUMINUM DEBRIS WAS PRESENT IN THE OIL SUMP. 1L71 3O3 O 3A15 E3SO 19950320007641995032000764EA 1995 3 20 95ZZZX1280 219950209G7414M3525 COIL SLICK 4281 CESSNA150 152 2071835CE LYC O235 O235L2C 41505EA LT MAG DEFECTIVE B OF1RA UNSCHED LANDING R PARTIAL RPM/PWR LOSS CRCRUISE 1 EA25894142596 042090 15282737 L2230215 ENGINE LOST 125 RPM IN-FLIGHT, LANDED WITHOUT INCIDENT, MAG CHECK REVEALED LT MAGNETO DEAD. TROUBLESHOT AND FOUND NO DEFECTS IN MAG AFTER DISASSEMBLY. REPLACED COIL AND RAN UP AND OPS CHECKED OKAY. 1H71 3O3 ONT3A19 E223 19950324000651995032400065EA 1995 3 24 95ZZZX1309 219950216G7414ES10357424 DIST BLOCK BENDIX S4LN200 MOONEYM20 M20F 5870214SW LYC O360 IO360A1A 41514EA MAGNETO LOOSE BUSHING DP K NONE O OTHER ININSP/MAINT 1 NM053205F971 409402 680002 RL274451A ON DISASSEMBLING THE MAG FOR INSPECTION, THE CENTER BRONZE BUSHING IN THE DISTRIBUTOR BLOCK WAS FOUND LOOSE IN THE PLASTIC MATERIAL OF THE BLOCK. THIS IS THE SECOND ELECTRO SYSTEMS DISTRIBUTOR BLOCK FOUND IN THIS CONDITION IN LAST MONTH, THE OTHER BLOCK WAS P/N ES10-357426. 1L71 3O3 O 2A3 1E10 19950324000701995032400070EA 1995 3 24 95ZZZX1314 219950130G741410507464 DISTRIBUTOR GEARBENDIX S4LN204 ENSTRMF28 F28A 3300406GL LYC O360 IO360C1A 41514EA RT MAG TEETH FAILED D A UNSCHED LANDING ER VIBRATION/BUFFET PARTIAL RPM/PWR LOSS CRCRUISE 1 WP139087 603 8017066 211 L1627651AC TEN MINUTES INTO A TOUR FLIGHT, ENGINE BECAME MOMENTARILY ROUGH. UPON RETURNING TO THE HELIPAD, A MAG CHECK REVEALED THE RIGHT MAG WAS DEAD. UPON REMOVAL AND INSPECTION, FOUND MORE THAN HALF OF THE PLASTIC TEETH WERE MISSING (BROKEN OFF) OF THE LARGE DISTRIBUTOR GEAR. 1G71 3O3 O H1CE 1E10 19950324001291995032400129GL 1995 3 24 HEEA954545 219950316G72506886407 WHEEL 6898735 BOLKMS105 BO105S 5626006EU ALLSN 250C 250C20B 03013GL 1ST STAGE SULFIDATION E HEEAK NONE O OTHER ININSP/MAINT 1 SW03541971740 CAT40390 S805 CAE830763 ENGINE REMOVED DUE TO 1750 HOUR INSPECTION AND TURBINE OVERHAUL. UPON INSPECTION OF TURBINE PARTS NOTED THE FOLLOWING: SULFIDATION ON ALL 1ST STAGE WHEEL BLADES. SCRAPPED 1ST STAGE WHEEL. 1G72 3U3 U H3EU E4CE 19950324001301995032400130GL 1995 3 24 HEEA954546 219950317G732040030043800 LINEAR ACTUATOR BELL 206 206L3 1182108SW ALLSN 250C 250C30 03013GL ENGINE INOPERATIVE E HEEAK NONE O OTHER ININSP/MAINT 1 SW033116P359 51530 BEEP MOTOR INOPERATIVE. 1G71 3U3 U H2SW E1GL 19950324004061995032400406EA 1995 3 24 95ZZZX1363 219950228G853073806P PUSH ROD CESSNA150 152 2071835CE LYC O235 O235L2C 41505EA ENGINE CYLNDER BROKEN DS K NONE O OTHER ININSP/MAINT 1 GL156145K 15285553 L232U415 FOUND 1 BROKEN AND 3 OTHERS CRACKED. ALL DAMAGE ON END OF THE TUBE NEAR INSERT OPPOSITE END OF TUBE WHERE PART NUMBER IS LOCATED. AD95-03-10 PERTAINS TO ASSEMBLY NR 73806 AND 'V' OR 'W' REVISION. PART TT UNKNOWN. 1H71 3O3 ONT3A19 E223 19950324004091995032400409EA 1995 3 24 95ZZZX1366 219950222G8550LW13306 GASKET MOONEYM20 M20M 5870222SW LYC O540 TIO540AF1A 41532EA OIL SUMP PAN BROKEN B GN1RK NONE K FLUID LOSS ININSP/MAINT 1 NE011085W232 270043 L912161A NEW MOONEY M20M AT 124.6, ENGINE OIL PAN GASKET LEAKING. REMOVED AND REPLACED WITH 06B2132C, REVISED PART NUMBER AND GASKET. THE TURBO MOUNT IS LOCATED ON THE SIDE OF THE OIL PAN. BOTH GASKETS LEAKED AT THE LT REAR SIDE. BOTH LW-13306 GASKETS WERE FOUND BROKEN AT THE SAME LOCATION. LYCOMING IS NOW USING THE OLD STYLE TIO-540 OIL PAN GASKET USED ON OTHER ENGINES. SEE FAA AC43-16 DATED 2-95. SUBMITTER RECOMMENDS SB FOR GASKET REPLACEMENTS. 1L71 303 ORT2A3 E14EA 19950324004101995032400410NE 1995 3 24 95ZZZX1367 219950216G851096657 COUPLING DOUG DC3 DC3G102A 3021404WP PWA R1830 R183094M1 52020NE ENG FRONT SEC BROKEN DLA K NONE O OTHER ININSP/MAINT 1 SW9913JA 945 4082 145873 REMOVED SN 145873 ENGINE DUE TO INCREASING AMOUNTS OF STEEL IN OIL SCREEN OVER A PERIOD OF 108 HRS. TSMOH WAS 2-1/2 YRS AND 945 HRS. TWO OIL ANALYSES DURING THAT TIME REPORTED ALL WEAR CHECKS NORMAL. UPON EXAMINING REMOVED ENGINE, FND PN 96657 COUPLING ASSY CRACKED COMPLETELY THROUGH. ALSO, AN APPROX 1 SQUARE INCH PIECE WAS BROKEN AWAY, BUT RETAINED IN PLACE BY CHANNEL DESIGN OF MATING PN 92991 COUPLING ASSY. ONLY REASON GEARS ARE TIMED IS SO MAGNETO TIMING CAN BE CHECKED VIA A TIMING PIN THROUGH A SIGHTING HOLE IN NOSE CASE. NOTED GEAR NOT TIMED, BROKEN PIECE WAS THROUGH THE GROOVE OF THE TOOTH WITH RIVET HOLE AND TIMING PIN (PN 93407) WAS NOT INSTALLED. 2L72 4R4 R A618 5E4 19950324004231995032400423WP 1995 3 24 95ZZZX1380 219950312G73218977807 FUEL CONTROL WOODWARD BAG JETSTMJETSTM3101 1500215EU GARRTTTPE331TPE33110UA 01514WP RT ENGINE FAILED B UN7RA UNSCHED LANDING R PARTIAL RPM/PWR LOSS CLCLIMB 1 SW19608JX 34 1945014 608 P42026 DURING REPOSITION FLIGHT FROM CIT TO BWI 20 MINUTES INTO FLIGHT, RT ENGINE STARTED BYPASSING FUEL, REDUCED POWER AND CONTINUED CLIMB. AT 19,000 FEET, NOTICED EGT AT 655. REDUCTION OF POWER DID NOT CHANGE EGT. POWER LEVER REDUCED TO FLIGHT IDLE, EGT WENT TO 650 DEGREES CENTIGRADE AT 80 PERCENT TORQUE. ON DESCENT BACK TO LIT, EGT AND POWER REDUCED ON ITS OWN (10,000 FEET EGT 600 DEGREES CENTIGRADE TORQUE 60 PERCENT) (2,000 FEET 400 DEGREES CENTIGRADE AND 6 PERCENT TORQUE). LANDED AT LIT WITHOUT INCIDENT. PILOTS SHUT RT ENGINE DOWN FOR TAXI. INSPECTED ENGINE FOR ANY EXTERNAL DEFECTS, NONE NOTED. REMOVED FUEL CONTROL FROM ENGINE FOR INSPECTION AT WOODWARD AND TO PERFORM SB TPE 331-73-0228 PER AD 94-26-07. 2L72 4T4 TRTA21EU E4WE 19950331001431995033100143NE 1995 3 31 HEEA954346 219950214G72610292005220 OIL RETURN SNIAS 350 AS350B 8680801EU TMECA ARRIELARRIEL1 60030NE TURBINE BLOCKED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03350BZ846 2653 FREE TURBINE OIL RETURN RESTRICTED. 1G71 3U3 U H9EU E19EU 19950331001821995033100182GL 1995 3 31 HEEA954594 219950323G72616854424 SHAFT SEAL BELL 230 230 1182149SW ALLSN 250C 250C30 03013GL START/GENERATOR LEAKING E HEEAK NONE K FLUID LOSS ININSP/MAINT 1 SW03230UN 23009 LEAK AT STARTER GENERATOR SEAL. REPLACED WITH SERVICEABLE SEAL. 1G72 3U3 UNCH9SW E1GL 19950331001971995033100197GL 1995 3 31 HEEA954611 219950323G732325246928 GOVERNOR BELL 206 206L3 1182108SW ALLSN 250C 250C30P 03013GL ENGINE DEFECTIVE E HEEAK NONE O OTHER TOTAKEOFF 1 SW036160Z7083 51610 ON TAKEOFF, N1, N2 AND ROTOR FLUCTUATIONS -- OVERTORQUE EXCEEDING 120%. REPLACED WITH SERVICEABLE GOVERNOR AND PERFORMED OVERTORQUE INSPECTION. 1G71 3U3 U H2SW E1GL 19950331002211995033100221GL 1995 3 31 HEEA954635 219950324G7261MS9372019 SEAL 23033185 BELL 206 206L1 1182107SW ALLSN 250C 250C28B 03013GL OIL NOZZLE "T" LEAKING E AHEEAO OTHER AK FLAME/FIRE FLUID LOSS NRNOT REPORTED 1 SW0327702 CAT70676 45300 PILOT REPORTED A FIRE IN ENGINE COMPARTMENT. THE FIRE FLASHED, THEN EXTINGUISHED. INVESTIGATION REVEALED OIL LEAK AT 6 & 7 OIL NOZZLE "T" FITTING. REPLACED SEAL ASSEMBLY AND RETURNED ENGINE TO SERVICE. 1G71 3U3 U H2SW E1GL 19950331002231995033100223GL 1995 3 31 HEEA954637 219950324G72106893660 ENGINE ASSY BOLKMS105 BO105S 5626006EU ALLSN 250C 250C20B 03013GL NR 1 CHIP LIGHT E HEEAK NONE J WARNING INDICATION ININSP/MAINT 1 SW037136J4876 S830 #1 ENGINE CHIP LIGHT CAME ON IN FLIGHT. (FOUND METAL ON THE LOWER PLUG) INSTALLED SERVICEABLE ENGINE AND RETURNED AIRCRAFT TO SERVICE. 1G72 3U3 U H3EU E4CE 19950331003831995033100383EA 1995 3 31 95ZZZX1416 219950227G7314LW15473 PUMP PIPER PA28 PA28R201 7102816SO LYC O360 IO360C1C6 41514EA ENGINE FUEL WASHER FAILED B AOG5RK NONE O OTHER ININSP/MAINT 1 GL21802ND 2837002 L2528051A OIL QUICK DRAIN WOULD NOT SHUT OFF. FOUND 2 PARTS OF STEEL WASHER IN QUICK DRAIN. FOUND OTHER 2 PARTS OF WASHER IN PAN. WASHER IS FROM JUST BELOW LEVER SLOT OF PUMP WHERE IT SLIDES OVER PUMP VERTICAL PLUNGER SHAFT. THIS IS THE SECOND OCCURRENCE OF THIS FAILURE BY THIS OPERATOR (OTHER FAILED PUMP HAD 641 TSN). 1L71 3O3 O 2A13 1E10 19950331003901995033100390EA 1995 3 31 95ZZZX1423 219950303G853065427 VALVE SPRING PIPER PA28 PA28140 7102802SO LYC O320 O320E3D 41508EA OUTER WRONG PART D K NONE W INADEQUATE Q C ININSP/MAINT 1 SO013975K 2823861 L2497427AC CUSTOMER REPORTED ENGINE 'BACKFIRING' INTERMITTENTLY AT HIGH IDLE. VALVE TRAIN PROBLEMS SUSPECTED & COLD CYLINDER TESTER DISCLOSED NR 3 CYL SLIGHTLY COOL (COMPRESSION WAS EXCELLENT). CLOSER INSP DISCLOSED INCORRECT SPRINGS PN 65427 INSTALLED INSTEAD OF LW-11800. NO RECORD OF MX ON THIS CYL SINCE O/H. PN 65427 SPRING HAS ABOUT 35 POUNDS LESS LOAD THAN CORRECT SPRING & IS USED IN O-235/O-290 SERIES ENGINES. VALVE & GUIDE WEAR WERE CHECKED & WITHIN LIMITS, BUT ENOUGH MUST HAVE CHANGED SINCE ENG HAS RUN 1620 HRS SMOH W/O COMPLAINT OF BACKFIRING. IN THIS CASE, 'WEAK' SPRINGS ALLOWED VALVES TO RESONATE OR BOUNCE IN A NARROW RPM RANGE (1200-1500 RPM) & RESULTED IN 'AFTERFIRING'. REPLACING SPRINGS CURED PROBLEM.1L71 3O3 O 2A13 E274 19950331003941995033100394SO 1995 3 31 95ZZZX1427 219950201G8530 CYLINDERS CESSNA210 T210L 2073449CE CONT O520 TSIO520R 17040SO ENGINE WORN B BJ3RK NONE O OTHER ININSP/MAINT 1 WP15210MG 21060838 506427 ENGINE RUN SMOH WITH MOBIL AV-1 ENGINE OIL. ENG STARTED SHOWING HIGH READINGS OF IRON, CHROMIUM, ALUMINUN ON OIL ANALYSIS. CYLS REMOVED FOR INSP. ALL OIL CONTROL RINGS FND STUCK W/LEAD BUILD-UP & ALL CYL WALLS FND WORN UP TO .014 INCH. ENG REMOVED FROM ACFT & DISASSEMBLED. FND VERY HIGH SLUDGE BUILD-UP IN ENG CAUSING PARTIAL BLOCKAGE OF MAIN OIL GALLEY. THIS CAUSED PREMATURE MAIN & CONNECTING ROD BRNG WEAR TO NEAR FAILURE. CRANKSHAFT ALSO FND SCORED AT PROP TRANSFER COLLAR AREA. CAM FOLLOWERS FND PITTED. ENG O/H 2-1/2 YEARS EARLIER W/ALL NEW CYLS, BRNGS, & CAMSHAFT FOLLOWERS INSTALLED. SUBMITTER STATED SEEING SIMILAR DAMAGE IN OTHER ENG RUN ON THIS OIL. RECOMMEND INSP OF ENG WITH THIS OIL. 1H71 3O3 O 3A21 E8CE 19950331003961995033100396EA 1995 3 31 95ZZZX1429 219950224G74141068256013 HOUSING D6LN3000 PIPER PA32 PA32RT300 7103215SO LYC O540 IO540K1G5 41532EA CLAMP FLANGE CRACKED D K NONE K FLUID LOSS ININSP/MAINT 1 SO166240C 250 A139406GB 32R7885022 ENGINE WAS LEAKING OIL. INVESTIGATION REVEALED CRACKED MAG HOUSING AT LOWER HOLD DOWN FLANGE. GASKET SURFACE WAS CLEAN, CLAMP BLOCKS WERE PROPERLY POSITIONED AND TORQUED. CRACKED OUT SECTION REVEALED LARGE AREAS OF AIR POCKETS IN CASTING. SUSPECT CRACK STARTED FROM PRESSED IN IMPULSE PINS AGGREVATED BY INTERNAL WEAKNESS DUE TO FLAWED CASTING. 1L71 3O3 O A3SO 1E4 19950331003971995033100397EA 1995 3 31 95ZZZX1430 219950303G8520SL78290 PLUNGER ASSY SUPAIRPART PIPER PA28 PA28140 7102802SO LYC O320 O320E3D 41508EA TAPPET LOOSE D K NONE ER VIBRATION/BUFFET PARTIAL RPM/PWR LOSS ININSP/MAINT 1 SO013975K1620 2823861 L2497427AC DURING COURSE OF TROUBLESHOOTING A ROUGH RUNNING ENGINE, THE HYDRAULIC PLUNGER ASSEMBLIES WERE REMOVED FROM THE TAPPETS. THE 'STEMS' OF 7 OF THE 8 UNITS WERE LOOSE AND WOULD SPIN IN THE BODY OF THE PLUNGER ASSEMBLY. NO CLUE WAS FOUND TO INDICATE WHAT MADE THE STEMS LOOSE. THAT PART OF THE UNIT RIDES ONLY IN OIL, ONLY NORMAL WEAR NOTED, AND ONLY IN THE NORMAL PLACES. THIS DEFECT ALLOWED LIFTERS TO BLEED DOWN UNUSUALLY QUICKLY. PARTS WERE REPLACED AND DEFECTIVE LIFTERS RETURNED TO MANUFACTURER FOR FURTHER EVALUATION. 1L71 3O3 O 2A13 E274 19950331005921995033100592SO 1995 3 31 95ZZZX1460 219950222G8530538288 CYLINDER BEECH 33 F33A 1151425CE CONT O520 IO520BA 17032SO NR 1 GUIDE LOOSE D K NONE O OTHER ININSP/MAINT 1 SW071096W 70 CE436 569112 DURING A ROUTE INPSECTION, NR 1 CYLINDER DISPLAYED LOW COMPRESSION. FURTHER INVESTIGATION, AFTER REMOVAL OF CYLINDER, REVEALED A LOOSE VALVE GUIDE IN THE CYLINDER HEAD. THIS ENGINE HAD BEEN OVERHAULED 70.0 HOURS PREVIOUS TO THE INSPECTION. CAUSE: INCORRECT TOLERANCES ON INSTALLATION. PREVENTION: INSPECTION OF GUIDES AFTER 100 HOURS OF OPERATION. 1L71 3O3 O 3A15 E5CE 19950331005941995033100594EA 1995 3 31 95ZZZX1463 219950221G732230766 FLOAT FACET MA3A CESSNA150 152 2071835CE LYC O235 O235L2C 41505EA CARBURETOR FILLED B EBVRK NONE K FLUID LOSS ININSP/MAINT 1 GL096449M2888 CR27388 15284733 NOTED FUEL DRIPPING FROM COWL. UNCOWLED AND FOUND FUEL LEAKING FROM CARBURETOR ENGINE RAN ROUGH AT LOW SPEEDS. PULLED CARBURETOR AND FOUND FLOAT FULL OF FUEL. REPLACED WITH NEW. HAD METAL FLOAT REPLACED 10-12-89 UNDER PRECISION SERVICE BULLETIN MSA-1. 1H71 3O3 ONT3A19 E223 19950331005961995033100596SO 1995 3 31 95ZZZX1465 219950321G8530646255 PISTON CESSNA172 172F 2072414CE CONT O300 O300D 17022SO NR 3 CYLINDER CRACKED CP K NONE O OTHER ININSP/MAINT 1 SW998677U 17252580 29549D4D PISTON CRACKED ON NR 3 CYL. TOTAL TIME SINCE O/H MAJOR, 48 HOURS. CRACK WAS FROM LOWER OIL RING GROOVE UPWARD APPROX 1.5 INCHES. CYLINDER AND ALL COMPONENTS CHECK OUT GOOD. ALL SPECS CHECK GOOD. TELEDYNE CONTINENTAL INSPECTED AND STATED THE FAILED PISTON WAS DUE TO BEING ASSEMBLED INCORRECTLY NOT MANUFACTURING. THIS DIAGNOSIS IS IN DISAGREEMENT BY THE A & P TECH., THE SAFETY OFFICER AND OWNER. 1H71 3O3 ONT3A12 E253 19950331005971995033100597SO 1995 3 31 95ZZZX1466 119950210G8120 TURBOCHARGER PIPER PA46 PA46310P 7104605SO CONT O520 TSIO520BE 17040SO LT TURBO MOUNT BOLTS MISSING B EBVRK NONE O OTHER ININSP/MAINT 1 GL094378S1561 468508009 273622R DURING REPAIR OF PILOT COMPLAINT ON CHT SYSTEM, NOTED AND REPAIRED: LT TURBO MOUNT BOLTS MISSING. 1L71 3O3 O A25SO E8CE 19950331005981995033100598SO 1995 3 31 95ZZZX1467 119950210G8120 TURBOCHARGER PIPER PA46 PA46310P 7104605SO CONT O520 TSIO520BE 17040SO RT TURBO MOUNT INCORRECT BOLTS B EBVRK NONE O OTHER ININSP/MAINT 1 GL094378S1561 468508009 273622R DURING REPAIR OF PILOT COMPLAINT ON CHT SYSTEM, NOTED AND REPAIRED: INCORRECT MOUNT BOLTS IN RT TURBO. 1L71 3O3 O A25SO E8CE 19950407002081995040700208SO 1995 4 7 95ZZZX1601 219950321G8520 CONNECT ROD PIPER PA28 PA28R201T 7102813SO CONT O360 TSIO360FB 17025SO NR 3-4 FAILED G K NONE ERKVIBRATION/BUFFET PARTIAL RPM/PWR LOSS FLUID LOSS NRNOT REPORTED 1 WP232443M1328 28R7803128 THIS ENGINE, CONVERTED FROM A TSIO-360-GB, HAD NR 3 AND NR 4 CONNECTING RODS FAIL AT THE SAME TIME KNOCKING A HOLE IN THE UPPER CASE AREA OF ABOUT 8 INCHES DIAMETER. TELEDYNE-CONTINENTAL SB M86-11 R1 PERTAINS TO THIS SUB JECT. 1L71 3O3 O 2A13 E9CE 19950407002091995040700209EA 1995 4 7 95ZZZX1603 219950321G8520 CRANKCASE PIPER PA23 PA23250 7102308SO LYC O540 O540B1B5 41532EA LT ENGINE CRACKED G K NONE O OTHER ININSP/MAINT 1 WP234529P 2500 2733 L110440 CRANKCASES FOUND CRACKED AND FRETTING AROUND MAIN BEARING SUPPORT STRUCTURE IN THE AREA OF THE CRACKED CRANKSHAFTS. 1L72 3O3 O 1A10 E295 19950407002101995040700210EA 1995 4 7 95ZZZX1604 219950321G8520 CRANKCASE PIPER PA23 PA23250 7102308SO LYC O540 O540B1B5 41532EA RT ENGINE CRACKED G K NONE O OTHER ININSP/MAINT 1 WP234529P 2500 2733 L128540 CRANKCASES FOUND CRACKED AND FRETTING AROUND MAIN BEARING SUPPORT STRUCTURE IN THE AREA OF THE CRACKED CRANKSHAFTS. 1L72 3O3 O 1A10 E295 19950407003311995040700331NE 1995 4 7 HEEA954647 219950328G732325249994 GOVERNOR SHAFT BELL 412 412 1182202SW PWA PT6T PT6T3B 52045NE FREE TURBINE BINDING E HEEAK NONE O OTHER ININSP/MAINT 1 SW033911L 33023 FREE TURBINE GOV THROTTLE SHAFT BINDING. 1G72 4U4 U H4SW E22EA 19950407006131995040700613NE 1995 4 7 95ZZZX1682 219950303G72107895922 BOWED TAB WASHER 7758001 SAAB SF340 SF340A 7850100EU GE CT7TP CT75A2 30030NE GC 49 GEARCASE BROKEN B SI3RK NONE O OTHER ININSP/MAINT 1 NE03 16437 UDAC0185 GEE367286 GEARBOX WAS RETURNED FOR 'METAL CONTAMINATION'. AFTER TEAR DOWN OF GEARBOX, NOTICED TABS WERE BROKEN OFF TAB WASHER (ITEM 20A OF SEI 663) AND RETAINING NUT (ITEM 25 OF SEI 663) WAS BACKED OFF THREAD ON PROP SHAFT (ITEM 80 OF SEI 663). NOTE: NO OTHER DAMAGE SEEN. REF: CMM 72-11-02. 2L72 4T4 TRTA52EU E8NE6 19950407006141995040700614EA 1995 4 7 95ZZZX1683 219950323G7230 COMPRESSOR BEECH 90 B90 1152912CE PWA PT6 PT6A20 52043EA FIRST STAGE FOD DAMAGE G A UNSCHED LANDING AJ FLAME/FIRE WARNING INDICATION CRCRUISE 1 GL05939K 5092 1603 LJ349 PCE21635 MGY - EN ROUTE, RT ENGINE FUEL FLOW FLUCTUATED AND FLAMES WERE OBSERVED OUT OF EXHAUST. FLIGHT DIVERTED TO DAY WHERE INSPECTION SHOWED FOD TO FIRST STAGE COMPRESSOR. ENGINE REMOVED FOR INSPECTION AND REPAIR FOLLOW-UP. 1L72 3T3 T 3A20 E4EA 19950407007381995040700738EA 1995 4 7 95ZZZX1702 219950310G8530SL74230 GUIDE LW12419 SOCATATB9 TB9 8680694EU LYC O320 O320D2A 41508EA LOWER PORTION CRACKED B NX42K NONE O OTHER ININSP/MAINT 1 SO15140ER 1529 DURING CYLINDER OVERHAUL, THE EXHAUST VALVE GUIDE WAS FOUND CRACKED IN THE LOWER PORTION. 1L71 3O3 ONTAS1EU E274 19950407007391995040700739EA 1995 4 7 95ZZZX1703 219950310G853074230 GUIDE LW12416 SOCATATB9 TB9 8680694EU LYC O320 O320D2A 41508EA LOWER PORTION CRACKED B NX42K NONE O OTHER ININSP/MAINT 1 SO15140ER1757 1529 DURING CYLINDER OVERHAUL, THE EXHAUST VALVE GUIDE WAS FOUND CRACKED IN THE LOWER PORTION. 1L71 3O3 ONTAS1EU E274 19950407007401995040700740EA 1995 4 7 95ZZZX1704 219950310G853074230 GUIDE LW12419 SOCATATB9 TB9 8680694EU LYC O320 O320D2A 41508EA LOWER PORTION CRACKED B NX42K NONE O OTHER ININSP/MAINT 1 SO15117ER1763 1509 DURING CYLINDER OVERHAUL, THE EXHAUST VALVE GUIDE WAS FOUND CRACKED IN THE LOWER PORTION. 1L71 3O3 ONTAS1EU E274 19950407007411995040700741EA 1995 4 7 95ZZZX1705 219950308G853074230 GUIDE LW12416 SOCATATB9 TB9 8680694EU LYC O320 O320D2A 41508EA LOWER PORTION CRACKED B NX42K NONE O OTHER ININSP/MAINT 1 SO15137ER1665 1527 DURING CYLINDER OVERHAUL, THE EXHAUST VALVE GUIDE WAS FOUND CRACKED IN THE LOWER PORTION. 1L71 3O3 ONTAS1EU E274 19950407007421995040700742EA 1995 4 7 95ZZZX1706 219950310G853074230 GUIDE LW12416 SOCATATB9 TB9 8680694EU LYC O320 O320D2A 41508EA LOWER PART CRACKED B NX42K NONE O OTHER ININSP/MAINT 1 SO15130ER1568 1511 DURING CYLINDER OVERHAUL, EXHAUST VALVE GUIDE WAS FOUND CRACKED IN THE LOWER PORTION. 1L71 3O3 ONTAS1EU E274 19950407007471995040700747GL 1995 4 7 95ZZZX1711 219950313G726123006661 BODY ALLSN 501D 501D13 03004GL PUMP GEAR POCKETDEBONDED B WS2RK NONE O OTHER ININSP/MAINT 1 WP01 OIL PUMP REPAIR MATERIAL DEBONDING. APPROXIMATELY .50 SQUARE INCH OF MATERIAL HAS LIFTED AWAY FROM GEAR POCKET WALL. SURROUNDING MATERIAL SHOWS EVIDENCE OF GENERAL DEBONDING. BODY IDENTIFIED WITH 'IAR 7148'. 4 T E282 19950407007481995040700748NE 1995 4 7 95ZZZX1712 219950310G73142113045 HOUSING PWA JT9 JT9* 52054NE PUMP GEAR POCKETDEBONDED B WS2RK NONE O OTHER ININSP/MAINT 1 WP01 FUEL PUMP DEBONDING OF GEAR POCKET REPAIR MATERIAL APPROXIMATELY 50 PERCENT OF REPAIR MATERIAL IS MISSING FROM GEAR POCKET WALLS. REMAINDER IS FLAKING OFF. HOUSING IDENTIFIED WITH 'IAR 9931D'. 4 F E20EA 19950414000801995041400080GL 1995 4 14 HEEA954669 219950404G723023008090 GEARSHAFT 23005290 SKRSKYS76 S76A 8143006NE ALLSN 250C 250C30S 03013GL SPUR ADAPTER STEPWEAR E HEEAK NONE O OTHER ININSP/MAINT 1 SW033122H678 CAC90180 760233 CAE890176S ENGINE REMOVED DUE TO CYCLED 1ST AND 2ND STAGE WHEELS. UPON INSPECTION OF COMPRESSOR PARTS NOTED THE FOLLOWING: STEP WEAR BEYOND SPECS ON SPUR ADAPTER GEARSHAFT FWD AND AFT SPLINES AND STEP WEAR ON INTERNAL SPLINES OF SPLINE ADAPTER BEYOND SPECS. INSTALLED NEW SPUR ADAPTER GEARSHAFT AND SPLINE ADAPTER. SEE MMIR #4670 FOR SPLINE ADAPTER INFORMAITON. 1G72 3U3 U H1NE E1GL 19950414000821995041400082GL 1995 4 14 HEEA954671 219950404G725023032345 N1 COUPLING 23035128 SKRSKYS76 S76A 8143006NE ALLSN 250C 250C30S 03013GL TURBINE STEPWEAR E HEEAK NONE O OTHER ININSP/MAINT 1 SW033122H678 CAT90574 760233 CAE890176S ENGINE REMOVED DUE TO CYCLED 1ST AND 2ND STAGE WHEELS. UPON INSPECTION OF TURBINE PARTS NOTED THE FOLLOWING: FWD AND AFT SPLINE STEP WEAR BEYOND LIMITS ON N1 COUPLING. INSTALLED NEW COUPLING. 1G72 3U3 U H1NE E1GL 19950414000841995041400084NE 1995 4 14 HEEA954673 219950404G74219560147770 IGNITOR SNIAS 350 AS350B2 8680813EU TMECA ARRIELARRIEL1C 60030NE ENG LT DEFECTIVE E HEEAK NONE O OTHER ININSP/MAINT 1 SW036095S615 2777 DURING ROUTINE INSPECTION NOTED LH IGNITER DID NOT FIRE. 1G71 3U3 U H9EU E19EU 19950414001011995041400101GL 1995 4 14 HEEA954692 219950406G72106876925 TUBE ASSY. 23001938 AEROSPAS355 AS355F1 8680810EU ALLSN 250C 250C20B 03013GL GR BOX DEFECTIVE E HEEAK NONE K FLUID LOSS ININSP/MAINT 1 SW03579068674 CAG40092 5107 CAE840091 ENGINE WAS REMOVED DUE TO OIL LEAK AT AFT T/M BUSHING. UPON INSPECTION OF GEARBOX PARTS NOTED THE FOLLOWING: OIL TRANSFER TUBE FAILED DIMENSIONAL CHECK IN ACCORDANCE WITH CEB 1307. INSTALLED NEW TUBE ASSEMBLY. 1G72 3U3 U H11EU E4CE 19950414001071995041400107GL 1995 4 14 HEEA954703 219950407G721023056128 GEARSHAFT 23001938 AEROSPAS355 AS355F1 8680810EU ALLSN 250C 250C20F 03013GL ENG GR BOX SPALLED E HEEAK NONE O OTHER ININSP/MAINT 1 SW035796T361 CAG40449 5166 CAE840100 ENGINE REMOVED DUE TO MAIN ENGINE DRIVESHAFT FAILURE. UPON INSPECTION OF GEARBOX PARTS NOTED THE FOLLOWING: SPALLING ON GEAR TEETH OF BOTH GEARSHAFTS. INSTALLED NEW GEARSHAFT. SEE MMIR #4704 FOR OTHER GEARSHAFT INFORMATION. 1G72 3U3 U H11EU E4CE 19950414001081995041400108GL 1995 4 14 HEEA954704 219950407G72106896437 GEARSHAFT 23001938 AEROSPAS355 AS355F1 8680810EU ALLSN 250C 250C20F 03013GL ENG GR BOX SPALLED E HEEAK NONE O OTHER ININSP/MAINT 1 SW035796T361 CAG40449 5166 CAE840100 ENGINE REMOVED DUE TO MAIN ENGINE DRIVESHAFT FAILURE. UPON INSPECTION OF GEARBOX PARTS NOTED THE FOLLOWING: SPALLING ON GEARTEETH OF BOTH GEARSHAFTS. INSTALLED NEW GEARSHAFT. SEE MMIR #4703 FOR OTHER GEARSHAFT INFORMATION. 1G72 3U3 U H11EU E4CE 19950414003871995041400387EA 1995 4 14 95ZZZX1733 219950303G7414104001678 IMPULSE COUPLINGBENDIX S6LN1227 PIPER PA25 PA25260 7102508SO LYC O540 O540G1A5 41532EA LT MAG WORN D K NONE O OTHER ININSP/MAINT 1 CE079785P401 0127691 257556096 MAG INSPECTION FOUND FLYWEIGHT TO AXLE CLEARANCE BEYOND LIMITS. 1L71 3O3 O 2A10 E295 19950414003901995041400390SO 1995 4 14 95ZZZX1736 219950213G8530SA632932 PISTON CESSNA182 182C 2072708CE CONT O470 O470L 17026SO NR 3 CYLINDER FAILED D K NONE O OTHER NRNOT REPORTED 1 CE07856ST868 52465 80505964 PISTON WAS COMPLETELY DISINTEGRATING. ALL VALVES AND OTHER ENGINE PARTS COMPLETE AND ACCOUNTED FOR. SUSPECT CAUSE WAS METAL WAS TOO BRITTLE. PISTON PIN WAS IN ROD AND MOVING AROUND IN CYLINDER. 1H71 3O3 ONT3A13 E273 19950414004051995041400405EA 1995 4 14 95ZZZX1751 219950301G7200 ENGINE PWA PT6 PT6* 52043EA MAINT PART HARD O-RING D K NONE W INADEQUATE Q C ININSP/MAINT 1 CE07 DURING MAINTENANCE ON A PT6 ENGINE, FOUND A NEW O-RING PN MS9388115 CAME OUT OF PACKAGING UNUSEABLE DUE TO VERY HARD CONDITION. O-RING PURCHASED FROM AVIALL ABOUT JUNE, 1994. 3 T E2NE 19950414005201995041400520EA 1995 4 14 95ZZZX1781 219950329G8530LW13870 CYLINDER LYC O540 O540F1B5 41532EA NR 6 CYLINDER MISMANUFACTURED B YV3RK NONE W INADEQUATE Q C ININSP/MAINT 1 WP05 L2485640A CYLINDER NR 6 ON A NEW PRODUCTION ENGINE HAS THE CYLINDER HEAD ORIENTED 2 DEGREES CCW RELATIVE TO THE BASE AND THE OTHER CYLINDERS. THIS PUTS THE EXHAUST FLANGE SURFACE OUT OF ALIGNMENT WITH THE OTHER CYLINDERS AND THE PUSH ROD HOUSINGS ARE ASKEWED ACCORDINGLY. 3 O E295 19950414005291995041400529SO 1995 4 14 95ZZZX1790 219950224G732263255531 LEVER 632840A1 CESSNA210 T210N 2073456CE CONT O520 TSIO520R 17040SO THROTTLE BODY BROKEN DPA O OTHER R PARTIAL RPM/PWR LOSS DEDESCENT 1 CE075313U 913 21064862 522546 THROTTLE CONTROL FAILED AFTER POWER REDUCTION FOR DESCENT INTO MEM. ENGINE POWER REMAINED AT APPROXIMATELY 24 INCHES M. P. AIRCRAFT SUCCESSFULLY LANDED WITH MIXTURE CONTROL. FOUND THROTTLE LEVER BROKEN AT BASE OF ARM AND REAR ALTERNATOR BELT BROKEN. CAUSE OF BREAKAGE UNDETERMINED, THROTTLE CONTROL ATTACHMENT AND ALTERNATOR BELT CONDITION WERE KNOWN TO BE CHECKED AT 50-HOUR INSPECTION JUST PRIOR TO INCIDENT AND FOUND SATISFACTORY. FORWARDED INFORMATION ON INCIDENT TO CESSNA AN TCM PRODUCT SAFETY. 1H71 3O3 O 3A21 E8CE 19950414005381995041400538EA 1995 4 14 95ZZZX1799 219950325G8520 CYLINDER PIPER PA60 PA60602P 7106015NM LYC O540 IO540S1A5 41532EA RT ENG NR 4 BASE NUT FAILED D EA ENGINE SHUTDOWN UNSCHED LANDING JR WARNING INDICATION PARTIAL RPM/PWR LOSS CLCLIMB 1 WP236902T1893 350 608265046 ON TAKEOFF, RT ENGINE FIRE LIGHT, LOSS OF POWER. PILOT SHUT DOWN, RETURNED TO AIRPORT. FOUND NR 4 CYLINDER HELD ON BY ONE BASE NUT. EXAMINED CYLINDER/PISTON, FOUND NO DISCREPANCIES. SUSPECT NUTS OVER/UNDERTORQUED. 1M72 3O3 ORTA17WE 1E4 19950414005411995041400541EA 1995 4 14 95ZZZX1802 219950330G853074230 GUIDE PIPER PA28 PA28161 7102803SO LYC O320 O320D2A 41508EA EXH VALVE CRACKED B NX42K NONE O OTHER ININSP/MAINT 1 SO15167ER 398 LW12419 2841183 DURING CYLINDER OVERHAUL, EXHAUST VALVE GUIDE FOUND CRACKED AT THE LOWER END OF THE GUIDE. THE CRACK WAS ORIENTED IN THE SAME PLACE AS THE ROCKER ARM. 1L71 3O3 O 2A13 E274 19950414005421995041400542 1995 4 14 95ZZZX1803 119950216G7600310047503 CONTROL ASSY PWA PT6 PT6A65B 52043EA ENGINE DEFECTIVE B MASRK NONE O OTHER ININSP/MAINT 1 SW01 CONTROL ASSY DEFECTIVE. 4 T E4EA 19950414005431995041400543EA 1995 4 14 95ZZZX1804 219950216G72503029885 NUT PWA PT6 PT6A65B 52043EA POWER SECT DAMAGED B MASRK NONE W INADEQUATE Q C ININSP/MAINT 1 SW01 NEWLY OVERHAULED PART RECEIVED FROM TURBINE PARTS THAT HAS THREAD DAMAGE AND HEAVY CORROSION. RECEIVED UNDER P.O. NR 950207023. 4 T E4EA 19950421000971995042100097EA 1995 4 21 95ZZZX1811 219950119G7210310164701 BEARING BEECH 1900 1900D 1154162CE PWA PT6 PT6A65B 52043EA NR 6 SPALLED B MASRK NONE O OTHER ININSP/MAINT 1 SW0135YV 5412 64D513 UE35 114073 THE NR 6 BEARING WAS FOUND WITH SPALLING ON ONE INNER RACE HALF AND SEVERAL OF THE BEARING BALLS. SUBMITTER BELIEVES THE SPALLING TO BE INTRODUCED BY THE STATIC PROBLEMS THAT ARE KNOWN TO BE ASSOCIATED WITH THE PROPELLER SYSTEM. 2L72 4T4 TRTA24CE E4EA 19950421001001995042100100EA 1995 4 21 95ZZZX1814 219950102G7532311271401 VALVE ASSY BEECH 1900 1900C 1154161CE PWA PT6 PT6A65B 52043EA GAS GEN FRETTED B MASRK NONE O OTHER ININSP/MAINT 1 SW0176YV 5R106 UC76 32488 SUSPECT CAUSE OF FAILURE IS A FAULTY BLEED VALVE. THE DEFINITE CAUSE IS STILL UNDER INVESTIGATION. 2L72 4T4 TRTA24CE E4EA 19950421001011995042100101EA 1995 4 21 95ZZZX1815 219950112G7230310920901 BEARING BEECH 1900 1900C 1154161CE PWA PT6 PT6A65B 52043EA GAS GEN COMP FRACTURED B MASRK NONE O OTHER ININSP/MAINT 1 SW01118YV2353 FC12409 UC118 32027 THE PRELIMINARY INVESTIGATION IS INDICATING THE NR 1 BEARING FAILED. 2L72 4T4 TRTA24CE E4EA 19950421001191995042100119 1995 4 21 95ZZZX1833 119950315G61203031844 CASING ASSY PWA PT6 PT6A65B 52043EA PROP CONTROL DENTED B MASRK NONE W INADEQUATE Q C ININSP/MAINT 1 SW01 PART WAS RECEIVED FROM VENDOR (TURBINE PARTS) AND FOUND DENTED BEYOND SERVICEABLE LIMITS. 4 T E4EA 19950421001201995042100120EA 1995 4 21 95ZZZX1834 219950308G72603012124 HOUSING PWA PT6 PT6A65B 52043EA ASSORY GEARBOX MISMANUFACTURED B MASRK NONE W INADEQUATE Q C ININSP/MAINT 1 SW01 2390 PART RECEIVED FROM STOCK. WHEN HOUSING ASSEMBLED IN THE AGB, GEARS WOULD NOT ROTATE. FURTHER INVESTIGATION REVEALED THE GEARS' PARTS WORKED PROPERLY WHEN INSTALLED IN ANOTHER HOUSING ASSY. 4 T E4EA 19950421001211995042100121EA 1995 4 21 95ZZZX1835 219950308G72603008360 DRIVE GEAR PWA PT6 PT6A65B 52043EA ASSORY GEARBOX CORRODED B MASRK NONE W INADEQUATE Q C ININSP/MAINT 1 SW01 RECEIVED PART FROM STOCK. PLASTIC BEAD FOUND PACKED INTO GEAR END OF SHAFT. INNER LUG FOUND CORRODED AND PITTED. 4 T E4EA 19950421001221995042100122EA 1995 4 21 95ZZZX1836 219950327G7532310687301 PISTON PWA PT6 PT6A65B 52043EA BLEED VALVE DAMAGED B MASRK NONE W INADEQUATE Q C ININSP/MAINT 1 SW01 THE PISTON RECEIVED FROM PARTS ROOM AND FOUND DAMAGED. UNABLE TO INSTALL PISTON RINGS BECAUSE OF THE BENT RING GROOVE. 4 T E4EA 19950421001231995042100123EA 1995 4 21 95ZZZX1837 219950308G7210310236001 RING GEAR PWA PT6 PT6A65B 52043EA POWER SECTION TEETH NICKED B MASRK NONE W INADEQUATE Q C ININSP/MAINT 1 SW01 44A697 PART RECEIVED FROM VENDOR WITH GEAR TEETH NICKED. RETURNED TO VENDOR AS UNACCEPTABLE. 4 T E4EA 19950421001241995042100124EA 1995 4 21 95ZZZX1838 219950308G72603008785 GEAR PWA PT6 PT6A65B 52043EA ASSORY GEARBOX PITTED B MASRK NONE W INADEQUATE Q C ININSP/MAINT 1 SW01 PART RECEIVED FROM VENDOR FOUND CORRODED AND PITTED. RETURN TO VENDOR AS UNACCEPTABLE FOR USE. 4 T E4EA 19950421001261995042100126EA 1995 4 21 95ZZZX1840 219950301G7210310236001 RING GEAR PWA PT6 PT6A65B 52043EA POWER SECTION DAMAGED B MASRK NONE W INADEQUATE Q C ININSP/MAINT 1 SW01 36B504 RECEIVED PART FROM VENDOR THAT HAS DAMAGE ON GEAR TEETH. 4 T E4EA 19950421001271995042100127EA 1995 4 21 95ZZZX1841 219950222G72603017609 GEARSHAFT PWA PT6 PT6A65B 52043EA STARTER DRIVE DAMAGED B MASRK NONE W INADEQUATE Q C ININSP/MAINT 1 SW01 RECEIVING INSPECTION OF PART REVEALED DAMAGE TO SNAP-RING GROOVE, DRIVE AND SEAL END OF SHAFT AND GEAR FACE-PLATE. 4 T E4EA 19950421001281995042100128EA 1995 4 21 95ZZZX1842 219950327G72503043061 VANE RING PWA PT6 PT6A65B 52043EA HOT SECTION DENTED B MASRK NONE W INADEQUATE Q C ININSP/MAINT 1 SW01 7L779 THE VANE RING RECEIVED FROM THE PARTS ROOM AND FOUND DENTED AT THE OUTBOARD EXIT FLANGE. 4 T E4EA 19950421001311995042100131EA 1995 4 21 95ZZZX1845 219950118G7210310076701 SUN GEAR 3029694 BEECH 1900 1900C 1154161CE PWA PT6 PT6A65B 52043EA POWER SECTION FAILED B MASRK NONE O OTHER ININSP/MAINT 1 SW01156YV8851 8851 57B849 UC156 32589 INDICATIONS ARE THAT THE FAILURE OCCURRED IN THE 1ST STAGE GEAR REDUCTION AREA. THE INVESTIGATION CENTERS AROUND THE 1ST STAGE GEAR AND THE 1ST STAGE SUN GEAR AREA. 2L72 4T4 TRTA24CE E4EA 19950421001331995042100133NE 1995 4 21 95ZZZX1847 219950317G7250 BLADE GE CJ610 CJ6106 30006NE TURB 1ST STAGE BOWED B IY2RK NONE O OTHER ININSP/MAINT 1 SW15 251562A STAGE 1 TURBINE BLADES ARE BOWED OUT OF LIMITS. TIME ON THE BLADES IS UNKNOWN. THE BLADES ARE MARKED WITH 'BK' WHICH SHOULD IDENTIFY THE PART NUMBER. HOWEVER, 'BK' IS NOT RECOGNIZED BY GENERAL ELECTRIC. 4 J 1E16 19950421001341995042100134NE 1995 4 21 95ZZZX1848 219950317G72306002T57P05 BLUCKET 6028T47P01 GE CF700 CF7002D2 30010NE FAN ROTOR CRACKED B IY2RK NONE O OTHER ININSP/MAINT 1 SW15 2945 7689FT 304572B DURING EDDY CURRENT INSPECTION OF THE FAN BLUCKETS REQUIRED AS PART OF THE HOT SECTION INSPECTION, FOUND ONE FAN BLUCKET WITH A MINUTE CRACK ON THE LEADING EDGE IN THE HOT SECTION PORTION OF THE BLUCKET. 4 F E7EA 19950421004861995042100486SO 1995 4 21 95ZZZX1878 219950328G8520 CRANKCASE CONT O520 TSIO520WB 17040SO BEARING BORE DEFECTIVE B CYKRK NONE W INADEQUATE Q C ININSP/MAINT 1 GL07 518882 IN COMPLYING WITH SB M92-09 DURING ASSEMBLY USING NEW 12-POINT NUT PN 652541 AND TORQUE OF 790-810 INCHES/POUNDS, ENGINE FAILED TO TURN WHEN FULL TORQUE WAS REACHED. UPON DISASSEMBLY, MAIN BEARING BORES WERE FOUND OUT OF ROUND. SUSPECT 'SOFT' CRANKCASE. 3 O E8CE 19950421004981995042100498EA 1995 4 21 95ZZZX1890 219950404G8530AL16740 VALVE LYC O360 IO360C1C6 41514EA ENGINE EXHAUST WORN B YYBRK NONE O OTHER ININSP/MAINT 1 GL03 160 RL1811351A ONE CYLINDER WAS REMOVED FOR LOW COMPRESSION. INSPECTION REVEALED THE EXHAUST VALVE BADLY WORN IN THE VALVE KEEPER AREA. STEM DIAMETER WAS WORN FROM .336 INCH TO ,280 INCH. THE OTHER 3 CYLINDERS WERE INSPECTED AND FOUND TO HAVE WORN VALVES AS WELL. NO SIGNS OF IMPROPER ASSEMBLY WERE FOUND. THE VALVE HAS BEEN RETURNED TO AIRCRAFT TECHNOLOGY CORP. FOR ANALYSIS. SUSPECT THE VALVES MAY NOT HAVE BEEN PROPERLY HARDENED. 3 O 1E10 19950421005101995042100510EA 1995 4 21 95ZZZX1899 219950405G7414 COIL SLICK 4271 CESSNA177 177 2073704CE LYC O320 O320E2D 41508EA MAGNETO CRACKED D K NONE O OTHER ININSP/MAINT 1 SW1129406180 89080358 17700866 L2123927A THE MAGNETO COIL CRACKED CAUSING MAG TO FAIL. THIS REPORT IS IN CONJUNCTION WITH AN ADDITIONAL REPORT ON THE SAME AIRPLANE AT THE SAME TIME A DUAL MAG FAILURE OCCURRED ON LANDING ROLL OUT. INSPECTIONS ON THE NAGNETOS DO NOT REQUIRE REMOVAL OF COIL TO SATISFY INPSECTION, BUT IT WOULD BE HIGHLY RECOMMENDABLE TO DO SO. SHOP HAS NOW FOUND 4 CRACKED SLICK COILS. 1H71 3O3 ONTA13CE E274 19950421005141995042100514SO 1995 4 21 95ZZZX1903 219950301G7322 NOZZLE FACET MA3SPA CESSNA150 150J 2071820CE CONT O200 O200A 17020SO CARB DISCHARGE NOT COMPATIBLE D K NONE W INADEQUATE Q C ININSP/MAINT 1 NM0161184 BE2420609 15020869 251274A48 ONE-PIECE VENTURI, NOT COMPATIBLE WITH ORIGINAL DISCHARGE NOZZLE. SHOULD BE MANDATORY TO CHANGE DISCHARGE NOZZLE AT THE TIME OF ONE-PIECE VENTURI IS INSTALLED. OLD NOZZLE NOT COMPATIBLE WITH NEW VENTURI. 1H71 3O3 O 3A19 E252 19950421005221995042100522GL 1995 4 21 95ZZZX1912 219950130G7230 BLADE GOVT N22 N22S 3880103WP ALLSN 250B 250B17 03012GL COMPRESSOR SEPARATED D K NONE O OTHER ININSP/MAINT 1 EA276305U N22S160 CAE880492 AFTER REGULAR DAILY RUN AND COMPRESSOR RINSE, AIRCRAFT SHUT DOWN WITH NO PROBLEMS. FOUND AFTER SHUT DOWN, COMPRESSOR BLADES (STATIONARY) HAD SEPARATED FROM CASE AND FROZE COMPRESSOR. 1H72 3T3 TRTA7PC E10CE 19950428001971995042800197EA 1995 4 28 95ZZZX1974 219950328G8550LW15550 GEROTOR PIPER PA23 PA23250 7102308SO LYC O540 TIO540C1A 41532EA TURBO SCAVANGE SEIZED H K NONE O OTHER ININSP/MAINT 1 EA0554748 6 277554062 L364561A TURBO SCAVANGE PUMP FAILED. APPEARS THAT THE ROTOR CRACKED WHICH, IN TURN, SHEARED AN ANTI-ROTATION PIN IN THE PUMP HOUSING IN WHICH THE GEROTOR TURNS. THE HOUSINGS WERE DAMAGED BY THIS PUMP HOUSING SPINNING, THE TURBO WAS NOT SCAVANGED WITH OIL LEADING TO THE LOSS OVERBOARD OF THE ENGINE OIL. 1L72 3O3 O 1A10 E14EA 19950428002091995042800209NE 1995 4 28 95ZZZX1986 219950328G7320800816 CASE PWA JT8 JT8D219 52053NE 8TH STAGE STATORCRACKED BP SQ5RK NONE O OTHER ININSP/MAINT 1 NE03 TF6682 718144 EIGHTH STAGE STATOR SUPPORT SHELF CRACKED. CRACK APPEARS TO HAVE STARTED AT A SLOT. CRACK CAUSED SOME LIBERATION OF MATERIAL. FOR SUSPECT CAUSE SEE SB 6117. CASE WAS REMOVED AND IS IN THE PROCESS OF HAVING SB 6117 INCORPORATED. 4 F E9NE 19950428002141995042800214NE 1995 4 28 95ZZZX1991 219950309G732178360014068 EEC HAMSTD BOEING757 757222 1384956NM PWA 2037 PW2037 NE SOLDER JOINTS DEFECTIVE B OHERK NONE O OTHER ININSP/MAINT 1 NE03560UA16340 20370410 26660 EEC EXHIBITS FRACTURED SOLDER JOINTS: CHAN 'A' PROCESSOR BD. LOCATION U427, PIN NR 15 (UVPROM) BD ASSY 781336-9-068, SN 89011490. CHAN 'B' PROCESSOR BD. LOCATION U427, PIN NR 14 (UVPROM) BD ASSY 781338-9-068, SN 89012339. CAUSE OF FRACTURING IS UNKNOWN AT THIS TIME. SUSPECT OXIDIZED CHIP LEADS. 2L72 4F4 FRTA2NM E17NE 19950428002151995042800215WP 1995 4 28 95ZZZX1992 219950405G725031038391 SEAL 31070852 GARRTTTPE331TPE33112UAR 01514WP 1ST STAGE CRACKED B DSCRK NONE O OTHER ININSP/MAINT 1 GL25 6751 0233151120 P70059 DURING CAM INSPECTION, FOUND SEAL CRACKED 3 PLACES. SB 72-0840 AUTHORIZES INSTALLATION OF THIS PART TO PROVIDE INCREASED PRESSURE AGAINST 1ST STAGE ROTOR. THIS INCREASED PRESSURE RESULTS IN CRACKING OF THE SEAL EDGE DIAMETER. SUGGEST ALLIED SIGNAL ENGINEERING REVIEW PART/INSTALLATION PROBLEM. CSN, 9,014. 4 T E4WE 19950428002161995042800216NE 1995 4 28 95ZZZX1993 219950317G7250634E583P3 WHEEL GE CJ610 CJ6106 30006NE TURB 1ST STAGE BOGUS PART BL IY2RK NONE W INADEQUATE Q C ININSP/MAINT 1 SW15 251562A THIS WHEEL WAS FOUND IN A COMMERICAL ENGINE. THE PART NUMBER IS NOT RECOGNIZED BY GENERAL ELECTRIC. 4 J 1E16 19950428002171995042800217EA 1995 4 28 95ZZZX1994 219950406G73103032090 LINE BEECH 1900 1900C 1154161CE PWA PT6 PT6A65B 52043EA PRIMARY FUEL CRACKED D CD ABORTED TAKEOFF RETURN TO BLOCK R PARTIAL RPM/PWR LOSS TOTAKEOFF 1 SO11119CJ UC19 32250 PRIMARY ENGINE FUEL LINE CRACKED AT FERRULE REINFORCEMENT RESULTNG IN LOSS OF SUFFICIENT FUEL PRESSURE TO MAKE REQUIRED POWER. TAKEOFF WAS ABORTED. SUSPECT CAUSED BY FATIGUE FROM ENVIRONMENT. 2L72 4T4 TRTA24CE E4EA 19950428006181995042800618SO 1995 4 28 95ZZZX2054 219950303G741410357586 DISTRIBUTOR GEAR S6RSC25P PIPER PA46 PA46310P 7104605SO CONT O520 TSIO520BE 17040SO RT MAG WQORN B LF1RO OTHER ER VIBRATION/BUFFET PARTIAL RPM/PWR LOSS CRCRUISE 1 EA07121RF500 4608034 273695R OWNER COMPLAINED OF ROUGHNESS IN FLIGHT. MIXTURE CHANGE OR FUEL PUMP OPERATION WOULD NOT AFFECT ENGINE. PERFORMED MAGNETO CHECK ON GROUND. FOUND RT MAGNETO WOULD NOT KEEP ENGINE RUNNING. REMOVED RT MAGNETO AND FOUND 10 TEETH MISSING FROM DISTRIBUTOR GEAR. POSSIBLY CAUSED AN ENGINE BACKFIRE. GEAR SEEMED TO BE IN GOOD SHAPE. ROTOR GEAR IS METAL IN THESE MAGNETOS WHICH COULD CONTRIBUTE TO THIS PROBLEM. RECOMMEND 100 HOUR INSPECTIONS FOR THESE MAGNETOS. 1L71 3O3 O A25SO E8CE 19950428006991995042800699EA 1995 4 28 95ZZZX2067 219950408G7310LW102980134 LINE PIPER PA32 PA32300 7103212SO LYC O540 IO540K1A5 41532EA NR 3 CYL NOZ BROKEN D A UNSCHED LANDING ER VIBRATION/BUFFET PARTIAL RPM/PWR LOSS CRCRUISE 1 AL01316061394 327840137 L1586248A DURING FLIGHT, ENGINE BEGAN RUNNING VERY ROUGH. THE PILOT LANDED AT NEAREST AIRPORT. UPON INSPECTION, FOUND LINE GOING FROM THE SPIDER TO THE NR 3 CYLINDER FUEL NOZZLE HAD BROKEN. THIS BREAK OCCURRED UNDER THE B-NUT NEXT TO THE BALL AT THE END OF THE LINE WHERE IT CONNECTS TO THE FUEL NOZZLE. THE NUT WAS TIGHT AND CONNECTED PROPERLY. FUEL LINE REPLACED WITH NEW. 1L71 3O3 O A3SO 1E4 19950428007071995042800707NE 1995 4 28 95ZZZX2075 219950403G7310216365003 MANIFOLD 216362035 BAG BAE146BAE146200A 1500266EU LYC ALF502ALF502R 41580NE NR 5-6 NOZ PORT LEAKS D K NONE K FLUID LOSS ININSP/MAINT 1 SO13 8997 1110 227P MANIFOLD HAS LEAK IN SCALLOP AREA BETWEEN 5TH AND 6TH NOZZLES. A SB WAS ISSUED, ALF502R73-8, REQUIRING A ONE FPI OF ALL MANIFOLDS WITH P/N ENDING IN DASH 09 THROUGH DASH 34. WHEN COMPLETED, MANIFOLDS ARE REIDENTIFIED AS DASH 35 OR DASH 36. FPI FOR ALL MANIFOLDS HAS SINCE BEEN INCORPORATED INTO THE REPAIR MANUAL AND IS REQUIRED AT EACH OVERHAUL. SUBMITTER SUGGESTS SHORTER TIME BETWEEN OVERHAUL/REPAIR OR THAT THESE PARTS BE LIFE-LIMITED. 2H74 4F4 FRTA49EU E6NE 19950428007211995042800721GL 1995 4 28 95ZZZX2089 219950329G7321953505120 SCREW BENDIX 23059790 BELL 206 206L3 1182108SW ALLSN 250C 250C30 03013GL RETAINER PLATE FAILED B ALGRK NONE O OTHER ININSP/MAINT 1 SW03358AL1291 BR53561 51460 CAE895436 ON DAILY SERVICE CHECK, FOUND INBOARD SCREW WHICH SECURES BYPASS VALVE RETAINING PLATE TO THE FUEL CONTROL BODY WAS FOUND WITH HEAD BROKEN OFF. CAUSE UNKNOWN. COMPLETE FUEL CONTROL WITH BROKEN SCREW WAS SENT TO ALLIED SIGNAL - BENDIX FOR EVALUATION. CEB'S 73-3061 REPLACEMENT OF THESE SCREWS AND LAPPING THE RETAINER PLATE HAS BEEN PREVIOUSLY COMPLIED WITH AS HAS CEB 78-A-3065 REPLACMENT OF RELIEF VALVE. 1G71 3U3 U H2SW E1GL 19950505001261995050500126NE 1995 5 5 95ZZZX2098 219950407G723050H067 NUT PLATE PWA 4056 PW4056 NE STG 9-10 STATOR MISMANUFACTURED B TUVRK NONE W INADEQUATE Q C ININSP/MAINT 1 SO11 PURCHASED NUT PLATE ASSY HAS OVERALL LENGTH WHICH IS APROXIMATELY ONE INCH LONGER THAN A PN 50H067. IN ADDITION, NUT PATTERN IS INCORRECT FOR PN 4000 9/10 STAGE COMPRESSOR STATOR. 4 F E24NE 19950505001391995050500139EA 1995 5 5 95ZZZX2111 219950410G8550 DRIVE COUPLING PIPER PA44 PA44180 7104402SO LYC O360 O360E1A6 41514EA ENG OIL SUMP BLOCK OIL GALLEYD K NONE O OTHER ININSP/MAINT 1 NM09357DA 447995271 DURING COMPLETION OF AD 78-09-07 ON LT ENGINE AND WHILE INSTALLING LT MAG, RUBBER DRIVE COUPLING WAS DROPPED INTO ENGINE. WHEN SUMP DRAIN WAS REMOVED TO RETRIEVE COUPLING, TWO WERE FOUND NEAR THE QUICK DRAIN. ENGINE HAD A HISTORY OF LOW OIL PRESSURE ON OCCASIONS, BUT REASON HAD NOT BEEN FOUND. IT IS BELIEVED THE PREVIOUSLY LOST COUPLING WAS REASON FOR LOW OIL PRESSURES. 1L72 3O3 O A19S0 E286 19950505001421995050500142CE 1995 5 5 95ZZZX2114 119950404G81204078109006 TURBOCHARGER GARRTT CESSNA414 414 2075908CE CONT O520 TSIO520BB 17040SO RT ENGINE FAILED B EB1REA ENGINE SHUTDOWN UNSCHED LANDING R PARTIAL RPM/PWR LOSS CRCRUISE 1 EA1399EF XI000097 414A0666 236935R AIRCRAFT EXPERIENCED LOSS OF POWER ON RIGHT ENGINE DURING FLIGHT. THE ENGINE WAS SHUT DOWN AND MADE AN EMERGENCY LANDING. INVESTIGATION REVEALED THE TURBOCHARGER UNIT HAD FAILED INTERNALLY. THE TURBOCHARGER WAS REPLACED AND ENGINE WAS GROUND AND FLIGHT CHECKED SATISFACTORILY. 1L72 3O3 ORTA7CE E8CE 19950505001461995050500146EA 1995 5 5 95ZZZX2118 219950412G8550LW14888 SUMP ASSY PIPER PA44 PA44180 7104402SO LYC O360 LO360E1A6 41514EA INDUCTION DRAIN BOSS CRACKED D K NONE O OTHER ININSP/MAINT 1 CE053040A 447995093 L17672 DURING INSPECTION AT ENGINE OVERHAUL, BOTH INDUCTION DRAIN BOSSES ON OIL SUMPS WERE FOUND CRACKED. SUSPECT BOSSES CRACKED FROM OVER TIGHTENING DRAIN VALVE ASSY, PN 24995-00. 1L72 3O3 O A19S0 E286 19950505002311995050500231NE 1995 5 5 HEEA954876 219950425G72103024780 GEARBOX BELL 412 412 1182202SW PWA PT6T PT6T3B 52045NE COMBINING BOX MAKING METAL E HEEAK NONE O OTHER ININSP/MAINT 1 SW033911L13832 33023 METAL IN OIL. 1G72 4U4 U H4SW E22EA 19950505002441995050500244NE 1995 5 5 HEEA954889 219950425G731402527730007 FUEL PUMP BELL 212 212 1181420SW PWA PT6T PT6T3B 52045NE NR 1 ENG FAILED E HEEAO OTHER X ENGINE FLAMEOUT NRNOT REPORTED 1 SW031079U10278 31122 #1 ENGINE FLAMED OUT IN FLIGHT. FOUND FUEL PUMP DRIVE COUPLING FAILURE. MALE SPLINES ON DRIVE GEAR INSIDE PUMP WERE ROUNDED OFF. REPLACED FUEL PUMP AND RETURNED TO SERVICE. 1G71 4U4 U H4SW E22EA 19950505002471995050500247GL 1995 5 5 HEEA954892 219950425G72506898911 WHEEL 23031925 SKRSKYS76 S76A 8143006NE ALLSN 250C 250C30S 03013GL 1ST STAGE SULFIDATION E HEEAK NONE O OTHER ININSP/MAINT 1 SW03 1750 CAT90593 CAE890585 ENGINE REMOVED DUE TO TURBINE OVERHAUL. UPON INSPECTION OF TURBINE PARTS NOTED THE FOLLOWING: EXCESSIVE SULFIDATION AND DELAMINATION ON ALL 1ST STAGE WHEEL BLADES CAUSING 10 EACH BLADE TIP FAILURES .062" CHORDALLY PROGRESSING .062"ACROSS TRAILING EDGE MAXIMUM. SCRAPPED 1ST STAGE WHEEL. 1G72 3U3 U H1NE E1GL 19950505003141995050500314GL 1995 5 5 HEED9558 219950421G7320222360703101 SOLENOID BELL 230 230 1182149SW ALLSN 250C 250C30G2 03013GL NR 1 ENG INOPERATIVE E HEEDK NONE O OTHER ININSP/MAINT 1 SW03236X 678 23015 NR 1 ENGINE FLIGHT IDLE SOLENOID INOPERATIVE. 1G72 3U3 UNCH9SW E1GL 19950505003831995050500383SW 1995 5 5 95ZZZX2127 219950124G8530 RINGS CESSNA195 195B 2073112CE JACOBPR755 R755A2 35006SW ENGINE EXCESS WORN D O OTHER A FLAME/FIRE ININSP/MAINT 1 NM082164C 16149 31151 DURING HOT ENGINE START, A CARBURETOR FIRE RESULTED. FIRE EXTINGUISHED USING DRY CHEM. ENGINE WASHED DOWN AND FLOWN. EXCESS OIL CONSUMPTION NOTED (1 GALLON PER HOUR). TEAR DOWN OF ENGINE REVEALED WORN PISTON RINGS AND GUMMED-UP INTAKE VALVES PLUS GRIT IN OIL. SUBMITTER RECOMMENDS TO NOT USE DRY CHEMICAL ON ENGINE FIRES. 1H71 3R3 R A790 TC237 19950505004031995050500403NE 1995 5 5 95ZZZX2147 119950324G75000301027300 P2 PIPE SKRSKYS76 S76A 8143006NE TMECA ARRIELARRIEL1S 60030NE FREE TURBINE CORRODED D K NONE O OTHER ININSP/MAINT 1 EA2565MS 1503 760259 3516TEC DURING APPLICATION OF SB 292 75 0193, (TU 247 A), PN 9562810760 CLAMP WAS REMOVED. SERIOUS CORROSION WAS FOUND ON THE P2 AIR PIPE WHERE THE CLAMP ATTACHES TO THE PIPE. THE PIPE SUPPLIES COMPRESSOR DISCHARGE AIR WHICH IS EXTERNALLY ROUTED TO THE FREE TURBINE BEARING LABYRINTH SEAL. FAILURE OF THIS TUBE WILL CAUSE AN ENGINE FAILURE, POSSIBLY CATASTROPHIC IN NATURE. THE SB INCORPORATES AN IMPROVED STAINLESS STEEL CLAMP WHICH SHOULD ELIMINATE THE CORROSION PROBLEM. THE PURPOSE FOR THE BULLETIN IS TO REDUCE MECHANICAL STRESSES AND INCREASE MECHANICAL RESISTANCE ON END OF THE PIPE, AS STATED BY THE MANUFACTURER. 1G72 3U3 U H1NE E19EU 19950505004101995050500410NE 1995 5 5 95ZZZX2154 219950124G7230496706 DISK SKRSKYS64 S64A 8142504NE PWA JFTD12JFTD12A5A 52047NE ENGINE PITTED D K NONE O OTHER ININSP/MAINT 1 NM09 1536 604 8V1080 496706 P AND W SB 1508, REQUIRES ALL ENGINES TO BE COMPLETELY DISASSEMBLED TO CONDUCT A CORROSION INSPECTION EVERY 7 YEARS. SERIOUS CORROSION PITTING FOUND WHEN CONVERTING MILITARY T73-P-1 OR T73-P-700 ENGINES TO COML. USE. DISK FAILURE CAN OCCUR IF CORROSION INSPECTION NOT C/W. EXAMPLE SUBMITTED. 2G72 4U4 U H1EA E15EA 19950505004121995050500412GL 1995 5 5 95ZZZX2156 219950315G7250A6871505 BEARING C20B HILLERUH12 UH12E 4360122WP ALLSN 250C 250C20B 03013GL NR 5 FAILED B HDNRO OTHER J WARNING INDICATION NRNOT REPORTED 1 SW03114HA265 CAT35461 HA3014 NR 5 BEARING FAILED AT THE BALLS RETAINER. CHIP LIGHT CAME ON IN-FLIGHT. NO CAUSE AT THE TIME. THIS PART IS A P.M.A. F.A.A. APPROVED. 1G71 3O3 U 4H11 E4CE 19950505004221995050500422GL 1995 5 5 95ZZZX2166 219950417G72306890550 COMPRESSOR HUGHES369 369D 4470706WP ALLSN 250C 250C20B 03013GL ENGINE STALLS B EOORK NONE K FLUID LOSS ININSP/MAINT 1 AL033115Y8437 2785 CAC31132 500116D CAE832750 COMPRESSOR STALLS WITH SMALL, BUT RAPID POWER CHANGES. UNIT SENT IN FOR REPAIR. 1G71 3U3 U H3WE E4CE 19950505004251995050500425GL 1995 5 5 95ZZZX2169 219950407G732323007506 GOVERNOR HUGHES369 369D 4470706WP ALLSN 250C 250C20B 03013GL ENGINE DEFECTIVE B EOORK NONE O OTHER ININSP/MAINT 1 AL033115Y 711 500716D CAE830750 THE GOVERNOR WOULD NOT HOLD RPM WITH SLIGHT POWER CHANGES. THIS UNIT HAS BEEN SENT IN FOR REPAIR 2 TIMES BEFORE IN THE LAST 239.8 HOURS FOR THE SAME PROBLEM. SEE ALLISON 250 REPORT A160113. 1G71 3U3 U H3WE E4CE 19950505005181995050500518EA 1995 5 5 95ZZZX2175 219950406G8530 CYLINDER DOUG DC3 DC3C 3021457WP WRIGHTR1820 R182022 67020EA ENG NR 1 CYL 6 FAILED H AE UNSCHED LANDING ENGINE SHUTDOWN ERKVIBRATION/BUFFET PARTIAL RPM/PWR LOSS FLUID LOSS CRCRUISE 1 WP13991316128 1128 18949 73469 LEFT ENGINE RAN SLIGHTLY ROUGH AT CRUISE ALTITUDE (5,000 FEET). NOTED OIL LEAK AT NR 6 CYLINDER POSITION. FEATHERED LT ENGINE AND RETURNED TO HONOLULU. AFTER LANDING, FOUND NR 6 CYLINDER FAILURE. (METAL PARTICLES (ALUMINUM) FOUND IN OIL SCREEN. REMOVED ENGINE. NO RECOMMENDATIONS FOR THIS PROBLEM. 2L72 4R4 R A669 TC154 19950505005191995050500519SO 1995 5 5 95ZZZX2176 219950414G8520 CYLINDER BEECH 58 58 1152740CE CONT O520 IO520C 17032SO CYLINDER BASE STUD SHEARED D K NONE K FLUID LOSS ININSP/MAINT 1 EA05111AW1637 TH841 561631 PILOT REPORTED OIL LEAK. UPON INSPECTION, 3 UPPER CYLINDER BASE STUDS FOUND SHEARED. REMOVED CYLINDER AND NOTICED CASE CRACKED AT LOWER RIGHT STUD. 1L72 3O3 O 3A16 E5CE 19950505005251995050500525EA 1995 5 5 95ZZZX2182 219950224G8530LW17540RW VALVE CESSNA172 172M 2072418CE LYC O320 O320E2D 41508EA NR 3 CYL EXH FAILED D O OTHER ER VIBRATION/BUFFET PARTIAL RPM/PWR LOSS CRCRUISE 1 GL17643731350 17265201 3794427A DURING FLIGHT, ENGINE STARTED RUNNING ROUGH, ENGINE FAILED ON LANDING. NR 3 CYLINDER VALVE EXHAUST FAILED. REPLACED/OVERHAULED CYLINDER. AIRCRAFT RETURNED TO SERVICE. 1H71 3O3 ONT3A12 E274 19950505005291995050500529EA 1995 5 5 95ZZZX2186 219950411G8530LW18289 CYLINDER CESSNA150 152 2071835CE LYC O235 O235L2C 41505EA CYLINDER BARREL CRACKED D K NONE K FLUID LOSS ININSP/MAINT 1 AL039608252 15286004 L2498015 CRACK FOUND DURING AN INSPECTION TO FIND AN OIL LEAK. LOCATION OF CRACK IS AT THE BOTTOM PORTION OF CYLINDER BARREL, 3.75 INCHES FROM BOTTOM OF FLANGE. THE CRACK IS APPROXIMATELY 2 INCHES LONG AND EXTENDS PARALLEL TO COOLING FINS. 1H71 3O3 ONT3A19 E223 19950505005311995050500531SO 1995 5 5 95ZZZX2188 219950413G8530 CYLINDER CESSNA402 402B 207590PCE CONT O520 TSIO520E 17040SO CYL NR 5 CRACKED C EA ENGINE SHUTDOWN UNSCHED LANDING ER VIBRATION/BUFFET PARTIAL RPM/PWR LOSS CLCLIMB 1 GL173748C 1030 402B606 183845R AFTER TAKEOFF, LEFT ENGINE STARTED VIBRATING. ENGINE WAS SHUT DOWN AND AIRCRAFT RETURNED TO THE AIRPORT. INSPECTION REVEALED A CRACK IN THE NR 5 CYLINDER. SINCE OVERHAULED CYLINDERS HAVE HIGH TOTAL TIME, THEY ARE MORE LIKELY TO CRACK DUE TO AGE AND STRESS. RECOMMEND USING NEW CYLINDERS AT OVERHAUL TO REDUCE RECURRENCE OF THIS PROBLEM. 1L72 3O3 O A7CE E8CE 19950505005321995050500532SO 1995 5 5 95ZZZX2189 219950310G732230764 FLOAT FACET MA45 CESSNA182 182Q 2072732CE CONT O470 O470U 17026SO CARBURETOR FAILED D K NONE K FLUID LOSS ININSP/MAINT 1 GL17182HM1077 C002042 18266720 467536 AFTER FINDING A 4 FOOT DIAMETER FUEL STAIN ON THE FLOOR AND FUEL DRIPPING FROM COWLING, INVESTIGATION DISCOVERED THE FLOAT RIGHT PONTOON SOLDER JOINT HAD BROKE ALLOWING THE PONTOON TO COME FREE FROM THE FLOAT LEVER AND HOLD THE NEEDLE OFF ITS SEAT. RECORDS INDICATE THAT AT ENGINE OVEHAUL, CARUBURETOR WAS OVERHAULED, BUT NO MENTION OF FLOAT REPLACEMENT. MANUFACTURE DATE OF FLOAT: 4-84. 1H71 3O3 ONT3A13 E273 19950505005341995050500534EA 1995 5 5 95ZZZX2191 219950419G8530SL10301AZP CYLINDER CESSNA150 152 2071835CE LYC O235 O235L2C 41505EA HEAD MISMANUFACTURED G K NONE W INADEQUATE Q C ININSP/MAINT 1 WP1748670 15283359 NEW SUPERIOR CYLINDERS WERE INSTALLED AT ROUTINE OVERHAUL. AT FIRST OIL CHANGE, SIGNIFICANT AMOUNTS OF ALUMINUM WERE FOUND IN THE OIL FILTER. AFTER 5 MORE FLIGHT HOURS, THE FILTER WAS AGAIN INSPECTED, MORE ALUMINUM WAS FOUND. THE ENGINE WAS DISASSEMBLED AND INSPECTED. IT WAS FOUND THE OUTER SPRINGS (VALVE) WERE RUBBING AGAINST THE SPRING POCKETS, REMOVING ALUMINUM FROM THE INSIDE OF THE HEAD CASTING. THIS CONDITION WAS FOUND IN SEVERAL OTHER ENGINES WITH SUPERIOR MILLENIUM O-235-L2C CYLINDERS. 1H71 3O3 ONT3A19 E223 19950505007151995050500715NE 1995 5 5 95ZZZX2254 219950407G725050H067 NUTPLATE PWA 4056 PW4056 NE FLANGE STG 9-10 MISMFG B TUVRK NONE W INADEQUATE Q C ININSP/MAINT 1 SO11 PURCHASED NUTPLATE ASSY IDENTIFIED AS PN 50H069, WAS ONE OFFSET NUT WITH RELATION TO THE OTHERS. THIS CONFIGURATION IS CONSISTANT WITH PN 50H067. APPEARS NUTPLATE ASSY HAS BEEN MISIDENTIFIED. 4 F E24NE 19950505007211995050500721SO 1995 5 5 95ZZZX2260 219950323G8530648044 PISTON CONT O520 TSIO520BE 17040SO NR 1 THU NR 6 PIN BOSS CRACKEDB DC2RK NONE O OTHER ININSP/MAINT 1 SW15 791 273705R UPON DISASSEMBLY OF ENGINE FOR PROP STRIKE INSPECTION AND TOP O/H, PISTONS FOUND CRACKED IN THE PIN BOSS AREA EXTENDING UP TO THE TOP INSIDE SURFACE (ONE SIDE ONLY). SUBMITTER UNSURE OF CAUSE. COULD BE MANUFACTURE DEFECT, DETONATION, MISUSE, ETC. 3 O E8CE 19950505007221995050500722SO 1995 5 5 95ZZZX2261 219950410G8550538517 OIL PAN BEECH 55 D55 1152730CE CONT O520 IO520C 17032SO UNDER 2-4 CYLS CRACKED D O OTHER K FLUID LOSS CRCRUISE 1 SW0769RP 479 TE766 287258R DURING FLIGHT, PILOT NOTICED OIL STREAMING FROM RT COWLING. INSPECTION BY MAINTENANCE PERSONNEL REVEALED A 2 INCH CRACK IN THE OIL PAN AT LOWER RADIUS. SUSPECT FATIGUE, POOR STAMPING, DURING MANUFACTURING. 1L72 3O3 O 3A16 E5CE 19950505007291995050500729 1995 5 5 95ZZZX2269 119950419G792253E19600 VALVE LYC O540 AEIO540D4A5 41532EA THERMO BYPASS NUT LOOSE G A K NONE O OTHER ININSP/MAINT 1 WP17 L2334348A BYPASS VALVE REMOVED TO COMPLY WITH LYCOMING SB 518A. THE NUT WAS FOUND LOOSE AND HALF-WAY UNSCREWED FROM THE THREADED SHAFT OF THE VALVE. IT WAS NOTED THE S/N OF VALVE WAS HIGHER THAN THE AFFECTED S/N'S LISTED IN SB. SUBMITTER RECOMMENDS INSPECTION PER SB OF ALL VALVES REGARDLESS OF S/N'S SB SHOULD BE AMENDED OR AN AD ISSUED. 3 O 1E4 19950512000011995051200001SO 1995 5 12 95ZZZX2270 219950429G8520 CRANKSHAFT CONT O520 IO520A 17032SO ROD WEIGHTS OUT OF BALANCE BL YCTRK NONE W INADEQUATE Q C ININSP/MAINT 1 SW11 1 112746 THE CONNECTING ROD WEIGHTS ON THE LARGE END FROM THE LIGHTEST TO THE HEAVIEST WAS 57 GRAMS. THIS ENGINE HAS NEVER BEEN INSTALLED IN AN AIRCRAFT. 3 O E5CE 19950512001621995051200162GL 1995 5 12 HEEA954914 219950504G723023008090 GEARSHAFT 23051643 SKRSKYS76 S76A 8143006NE ALLSN 250C 250C30S 03013GL SPUR ADAPTER STEP WEAR E HEEAK NONE O OTHER ININSP/MAINT 1 SW035435V821 CAC90511 760158 CAE890507S ENGINE REMOVED DUE TO COMPRESSOR 1750 HOUR INSPECTION AND TURBINE OVERHAUL. UPON INSPECTION OF COMPRESSOR PARTS NOTED THE FOLLOWING: STEP WEAR BEYOND LIMITS ON SPUR ADAPTER GEARSHAFT FORWARD AND AFT SPLINES. INSTALLED NEW SPUR ADAPTER GEARSHAFT. 1G72 3U3 U H1NE E1GL 19950512001631995051200163GL 1995 5 12 HEEA954915 219950504G725023031494 LAB SEAL 23031925 SKRSKYS76 S76A 8143006NE ALLSN 250C 250C30S 03013GL NR 8 BEARING DEFECTIVE E HEEAK NONE W INADEQUATE Q C ININSP/MAINT 1 SW03 CAT90593 CAE890585S RECEIVING INSPECTION OF NEW, NEVER INSTALLED #8 BEARING. LAB SEAL INDICATED EXCESSIVELY FLATTENED LAB SEAL. INSTALLED NEW LAB SEAL. 1G72 3U3 U H1NE E1GL 19950512001641995051200164GL 1995 5 12 HEEA954916 219950504G725023031478 BEARING 23035128 SKRSKYS76 S76A 8143006NE ALLSN 250C 250C30P 03013GL NR 8 BEARING DEFECTIVE E HEEAK NONE W INADEQUATE Q C ININSP/MAINT 1 SW03 CAT95521 CAE900058 ENGINE REMOVED FOR MODIFICATION. UPON INSPECTION OF TURBINE PARTS NOTED THE FOLLOWING: PULLER GROOVE MISSING ON #8 BEARING. INSTALLED NEW #8 BEARING. 1G72 3U3 U H1NE E1GL 19950512003581995051200358WP 1995 5 12 95ZZZX2309 219950423G7200 ENGINE AMD FALC50FALCON50MYST2730106EU GARRTTTFE731TFE7313 01518WP NR 1 FAILED B NV1RE ENGINE SHUTDOWN EB VIBRATION/BUFFET SMOKE/FUMES/ODORS/SPARKS CRCRUISE 1 GL054350M6352 142 P76568 DAY/EWR - IN-FLIGHT SHUT DOWN 4-23-95, ENGINE EXPERIENCED INTERMITTENT VIBRATION AND ODOR EMISSION INTO CABIN. ABNORMAL N1 AND ITT READINGS INCREASED VIBRATION, PROMPTED SHUT DOWN WHILE DESCENDING INTO EWR AT 6,000 FEET. THE NR 1 ENGINE ON THIS AIRCRAFT HAD FAILED PREVIOUSLY UNDER SIMILAR CIRCUMSTANCES AND TIMES. SAME BLOCK OF SERIAL NUMBERS. 2L73 4F4 F A46EU E6WE 19950512004701995051200470SO 1995 5 12 95ZZZX2314 219950429G8530629401 RING CONT O520 IO520A 17032SO PISTON SCRAPER BROKEN D K NONE O OTHER ININSP/MAINT 1 SW11 112746 PISTON SCRAPER RING WAS BROKEN AT ASSEMBLY. PART OF THE BROKEN RING WAS IN THE OIL SUMP. 3 O E5CE 19950512004711995051200471SO 1995 5 12 95ZZZX2315 219950419G8520SA530213 ROD BOLT CONT O200 O200A 17020SO CON ROD MISMANUFACTURED B CT3RK NONE W INADEQUATE Q C ININSP/MAINT 1 WP17 INSPECTION OF CONNECTING ROD BOLTS REVEALED ONE SIDE OF THE BOLT HEAD WAS FLAT ON THE EDGE INSTEAD OF ROUND. SUBMITTER SUGGESTS IN VIEW OF ALL THE PROBLEMS INVOLVING SUPERIOR PARTS. THIS IS SUSPECT. 3 O E252 19950512004751995051200475 1995 5 12 95ZZZX2319 119950419G792253E19600 VALVE LYC O540 AEIO540D4A5 41532EA THERMO BYPASS CRIMP NUT LOOSE B CT3RK NONE O OTHER ININSP/MAINT 1 WP17 L2334348A BYPASS VALVE REMOVED TO COMPLY WITH LYCOMING SB 518A. THE NUT WAS FOUND LOOSE AND HALF-WAY UNSCREWED FROM THE THREADED SHAFT OF THE VALVE. IT WAS NOTED THE SERIAL NUMBER OF VALVE WAS HIGHER THAN THE AFFECTED SERIAL NUMBERS LISTED IN SB. RECOMMEND INSPECTION PER SB OF ALL VALVES REGARDLESS OF SERIAL NUMBERS. SB SHOULD BE AMENDED OR AN AD ISSUED. 3 O 1E4 19950512004791995051200479SO 1995 5 12 95ZZZX2323 219950401G8520646297 BRACKET BEECH 36 A36 1151604CE CONT O550 IO550B SO CYLINDERS 2-4 BROKEN D K NONE O OTHER ININSP/MAINT 1 NM034759M E1300 249125R SEVENTH STUD, CYLINDERS 2 AND 4: BRACKET BROKEN IN HALVES. ONE ONE-HALF FOUND LYING NEXT TO KEEL, OTHER ONE-HALF MISSING. (ANNUAL 100-HOUR INSPECTION.) REPLACED BRACKET AND NUT, PN 646312. SUSPECT CAUSE: PROGRESSIVE CRACK LEADING TO ULTIMATE FAILURE. 1L71 3O3 O 3A15 E3SO 19950519000941995051900094NE 1995 5 19 HEEA954941 219950510G75105044T08P05 VALVE BELL 214 214ST 1182106SW GE CT7TS CT72A 30030NE ENGINE AI CORROSION E HEEAK NONE O OTHER ININSP/MAINT 1 SW038045T 28101 GEE343061 ANTI ICE VALVE CORROSION. 2G72 4U4 U H10SW E8NE 19950519000951995051900095NE 1995 5 19 HEEA954942 219950510G73135051T35G05 NOZZLE BELL 214 214ST 1182106SW GE CT7TS CT72A 30030NE ENG FUEL DEFECTIVE E HEEAK NONE O OTHER NRNOT REPORTED 1 SW038045T 28101 GEE343006 FUEL NOZZLE DEFECTIVE. EXCESSIVE DROOLING AND SPITTING. SERIAL NUMBERS REMOVED PKHC4238 & PANO0613 & PKHA8102. 2G72 4U4 U H10SW E8NE 19950519004631995051900463GL 1995 5 19 95ZZZX2367 219950421G72306890550 COMPRESSOR HUGHES369 369D 4470706WP ALLSN 250C 250C20B 03013GL ENGINE STALLS B EOORK NONE R PARTIAL RPM/PWR LOSS NRNOT REPORTED 1 AL035074R5623 2432 1151D CAE832750 COMPRESSOR STALLS WITH SLIGHT BUT RAPID POWER CHANGES. NOTE: THIS ENGINE WAS REMOVED FROM ANOTHER A/C WITH THESE SYMPTOMS AND ANOTHER ENGINE INSTALLED SO IT COULD START A JOB. THIS COMPRESSOR WAS INSTALLED FOR TROUBLESHOOTING WHEN THIS ENGINE WAS INSTALLED IN 5074R. *(PREVIOUS MDR FOR THE SAME PROBLEM WAS FILLED OUT ON THIS ENGINE WHEN IT WAS INSTALLED ON N3115Y). BOTH COMPRESSORS HAVE BEEN SENT IN FOR REPAIR. 1G71 3U3 U H3WE E4CE 19950519004641995051900464GL 1995 5 19 95ZZZX2368 219950425G732323007506 GOVERNOR HUGHES369 369D 4470706WP ALLSN 250C 250C20B 03013GL ENGINE DEFECTIVE B EOORK NONE O OTHER ININSP/MAINT 1 AL034571V 478 4447 490487D CAE830976 'BEEP' RANGE IS ERRATIC. RPM JUMPS FROM POINT-TO-POINT DURING SMOOTH GOVERNOR TRIM MOTOR ACTUATION. UNIT SENT IN FOR REPAIR ON ALLISON 250 REPORT NR A160118. 1G71 3U3 U H3WE E4CE 19950519004651995051900465GL 1995 5 19 95ZZZX2369 219950430G732323007506 GOVERNOR 6887190 HUGHES369 369D 4470706WP ALLSN 250C 250C20B 03013GL ENGINE DEFECTIVE B EOORK NONE O OTHER ININSP/MAINT 1 AL033115Y 917 17979 500716D CAE838348 PILOT COULD NOT MAKE SMOOTH 'BEEP' ADJUSTMENTS. REMOVED AND REPLACED UNIT. FELT A NOTCH IN THE ROTATION OF THE LEVER ARM. UNIT SENT TO BE REPAIRED ON ALLISON 250 REPORT A160119. 1G71 3U3 U H3WE E4CE 19950519004731995051900473EA 1995 5 19 95ZZZX2377 219950427G741410357281H CAPACITOR BENDIX S4LN200 LYC O360 IO360A1A 41514EA MAG SHORTING DS K NONE O OTHER ININSP/MAINT 1 GL15 INVESTIGATION FOR AN INTERMITTENT DEAD MAG FOUND SPRING STRAP TOUCHING HOUSING AS P-LEAD IS PUSHED INTO COVER. 3 O 1E10 19950519004741995051900474SO 1995 5 19 95ZZZX2378 219950424G8530 CYLINDER CESSNA206 U206F 2073333CE CONT O520 IO520A 17032SO BASE MISINSTALLED D K NONE W INADEQUATE Q C ININSP/MAINT 1 EA077144Q U20603075 553939 TOTAL TIME 1067.8 SMOH. TIME SINCE TOP OVERHAUL 125.0. DURING MAINTENANCE TO REPAIR BURNED VALVES UPON CYLINDER REMOVAL, FOUND CYLINDERS GLUED ON AT BASE. (IT TOOK OVER AN HOUR USING AIR PRESSURE AND PULLING AND PRYING TO REMOVE ONE CYLINDER). IT SEEMS THAT A FOREIGN SUBSTANCE WAS APPLIED AROUND O-RING AT THE CYLINDER BASE. SUBMITTER BELIEVES THIS IS A CASE OF IMPROPER MATERIALS BEING USED. 1H71 3O3 O A4CE E5CE 19950519004751995051900475SO 1995 5 19 95ZZZX2379 219950427G8520633258 CRANKSHAFT BEECH 35 J35 1151522CE CONT O470 IO470C 17026SO FLANGE CORRODED D K NONE O OTHER ININSP/MAINT 1 CE038330D1870 D5483 8777380R REMOVED PROPELLER TO REPLACE CRANKSHAFT SEAL. FOUND CRANKSHAFT FLANGE SEVERELY CORRODED. REMOVED ENGINE FROM SERVICE FOR CRANKSHAFT REPLACEMENT. ENGINE HAD BEEN OVERHAULED BY AN 'IA' JUST 75 HOURS AND 3 YEARS PREVIOUS TO THIS DISCOVERY. SUBMITTER BELIEVES CORROSION EXISTED AT THAT TIME. 1L71 3O3 O 3A15 E273 19950519004841995051900484GL 1995 5 19 95ZZZX2389 219950427G8530SA10203 CYLINDER CESSNA150 150 2071802CE AMTR CUSHMNO200 05645GL NR 2 CYLINDER CRACKED H K NONE K FLUID LOSS ININSP/MAINT 1 EA076400T500 17800 ENGINE HAD MINOR OIL LEAK FOR APPROXIMATELY 100 HOURS. IN ONE WEEK, OIL LEAK BECAME SEVERE. FOUND NR 2 CYLINDER BARREL CRACKED ABOUT 4 INCHES FORM BASE OF CYLINDER. CYLNDER HELD 74 POUNDS OF COMPRESSION. SUBMITTER IS OF THE OPINION THE CRACK WAS CAUSED FROM A MANUFACTURING DEFECT. 1H71 3O3 ONT3A19 EXPA3O 19950519004901995051900490SO 1995 5 19 95ZZZX2395 219950321G8530632485 PUSH TUBE CONT O520 GTSIO520* 17032SO SEAM CORRODED B C6YRK NONE O OTHER ININSP/MAINT 1 SW05 PUSH TUBE WAS SENT IN FOR REPLATING. AFTER CLEANING PUSH TUBE, CORROSION WAS FOUND IN SEAM PENTRATING THROUGH THE TUBE. PUSH TUBES SHOULD BE MADE FROM SEAMLESS TUBING. 3 O E7CE 19950519006821995051900682NE 1995 5 19 95ZZZX2404 219950417G7323430128701 GOVERNOR 2860 SNIAS 350 AS350D 8680803EU LYC LTS101LTS101600A3 41560NE POWER TURBINE FAILED D A A UNSCHED LANDING O OTHER CLCLIMB 1 WP13138EH 513 1403 LE434500E DURING FLIGHT, EXPERIENCED LOW SIDE GOVERNOR FAILURE (LOW POWER). THE PILOT JUST LIFTED OFF PAD NR 1, ACFT WAS ABOUT 4 FEET OFF DECK, PILOT MANAGED TO SET IT BACK DOWN WITHOUT ANY INCIDENT OR DAMAGE TO THE AIRCRAFT. PILOT TOOK ANOTHER SHIP AND THE SAME PASSENGERS AND COMPLETED THE TOUR. THE MECHANIC REMOVED P.T. GOV. TSO 513.6, AND INSTALLED SERVICEABLE ONE AND C/W OPERATIONAL AND A MAX TOPPING CHECK FLIGHT AND PASSED CHECK FLIGHT. 1G71 3U3 U H9EU E5NE 19950519006841995051900684SO 1995 5 19 95ZZZX2406 219950403G8530 CYLINDER PIPER PA60 PA60601P 7106012NM CONT O520 IO520* 17032SO LT ENG NR 2 HEAD SEPARATION B VTMRA UNSCHED LANDING R PARTIAL RPM/PWR LOSS CRCRUISE 1 WP058244J982 61P0648796 L1918148A CYLINDER HEAD SEPARATED FROM CYLINDER BARREL IN-FLIGHT. THE ENGINE KEPT RUNNING, PILOT REDUCED POWER AND LANDED ACFT WITH NO OTHER DAMAGE TO ENGINE OR AIRCRAFT. THE CYLINDER, HEAD, AND PISTON ARE AT SHOP FOR INSPECTION. 1M72 3O3 ORTA17WE E5CE 19950519006981995051900698EA 1995 5 19 95ZZZX2420 219950324G85504013383 BAFFLE PIPER PA32 PA32R301 7103218SO LYC O540 IO540K1G5 41532EA OIL SUMP FAILED B AMYRK NONE O OTHER ININSP/MAINT 1 CE05923CN466 3213076 L2523848A DURING REMOVAL OF OIL PAN TO CHANGE PAN GASKET, FOUND OIL SUMP BAFFLE COMING APART WHERE VERTICAL FINS ARE ATTACHED TO HORIZONTAL PART, FOUND ALL RIVETS LOOSE, ONE RIVET HEAD COMPLETELY MISSING. 1L71 3O3 O A3SO 1E4 19950519007011995051900701EA 1995 5 19 95ZZZX2423 219950425G853076220 THROUGH-BOLT MOONEYM20 M20F 5870214SW LYC O360 IO360A1A 41514EA NR 1 CYLINDER FAILED DL K NONE O OTHER ININSP/MAINT 1 NM097112V2763 1788 220047 L12C2451A SUBJECT NR 1 CYLINDER UPPER THROUGH-BOLT FOUND BROKEN DURING PRE-FLIGHT. DETECTED AS THE MAJOR REMAINING PORTION AND HOLD-DOWN NUT FOUND BACKED OUT OF POSITION AND LODGED AGAINST CYL FINS. INST NEW BOLT, SPACER, AND NUT. TORQUED PER LYCOMING S.I. 10293. BOLT, THREADED END, BROKE OFF FLUSH WITH NUT'S SEATING SURFACE. INDICATIONS WERE A CRACK ABOUT 50 PERCENT ACROSS THE DIAMETER HAD EXISTED FOR SOME TIME AND BOLT ULTIMATELY FAILED IN A TYPICAL TENSILE FACTURE. 1L71 3O3 O 2A3 1E10 19950526000651995052600065EA 1995 5 26 95ZZZX2429 219950426G8530LW12966 CYLINDER PIPER PA31 PA31350 7103110SO LYC O540 TIO540J2BD 41532EA NR 1 HOLED E AE UNSCHED LANDING ENGINE SHUTDOWN EK VIBRATION/BUFFET FLUID LOSS APAPPROACH 1 SO17684JJ 698 317952194 L486361A DURING AN APPROACH TO LANDING, PILOT REPORTED A VIBRATON IN THE LEFT ENGINE AND OIL LEAKING FROM COWLING. A PRECAUTIONARY SHUT DOWN MADE AND PILOT MADE AN UNEVENTFUL LANDING. INSPECTION REVEALED A HOLE IN NR 1 CYLINDER UNDER THE INTAKE PUSH ROD HOUSING. THE HOLE ALLOWED EXHAUST GASES TO BURN A HOLE IN THE PUSH ROD HOUSING ALLOWING OIL LEAKAGE, AND THE PUSH ROD TO BREAK. SUBMITTER SUGGESTED PROBLEM MAY HAVE BEEN DUE TO A POOR WELD. 1L72 3O3 O A20SO E14EA 19950526000681995052600068EA 1995 5 26 95ZZZX2432 219950322G8530LW75089 PIN PLUG BEECH 23 C23 1151242CE LYC O360 O360A4K 41514EA PISTON WORN D K NONE O OTHER ININSP/MAINT 1 SO139226S 2904 M1723 L2042136A PISTON PIN CAP DEVELOPED WEAR AND WORKED OUT LARGE HOLE INSIDE OF PISTON CAUSING FAILURE OF OIL RING AND LOSS OF COMPRESSION. CAP HAD WORN DOWN TO .25 INCH THICKNESS AND WORKED OUT HOLE REACHING PISTON OIL RING GROOVE. 1L71 3O3 O A1CE E286 19950526000711995052600071SO 1995 5 26 95ZZZX2435 219950130G8530SA631475 PISTON BEECH 35 V35 1151538CE CONT O520 IO520BA 17032SO NR 2 CYLINDER FAILED D K NONE O OTHER NRNOT REPORTED 1 SW079516Q382 D8064 569329 PISTON SKIRT FAILED AT LOWER RING LAND ON THRUST SIDE. DEBRIS EXTENSIVELY DAMAGED CRANKCASE, CRANKSHAFT, CAMSHAFT, RODS, ADJACENT PISTONS AND CYLINDERS. ALSO, THE ENTIRE OIL SYSTEM WAS CONTAMINATED. 1L71 3O3 O 3A15 E5CE 19950526000811995052600081WP 1995 5 26 95ZZZX2445 219950404G725031038393 SEAL 31033155 GARRTTTPE331TPE33112UAR 01514WP TURBINE CRACKED H K NONE R PARTIAL RPM/PWR LOSS ININSP/MAINT 1 GL25 5283 1233152013 P70094C DURING INSPECTION FOR LOW POWER, FOUND PART CRACKED 12 PLACES UP TO APPROXIMATELY .5 INCH. SB 72-0840 AUTHORIZES INSTALLATION OF THIS PART TO PROVIDE INCREASED SEAL PLATE TENSION AGAINST FIRST STAGE ROTOR. THIS INCREASED TENSION RESULTS IN CRACKING AT THE SEAL PLATE EDGE DIAMETER. CRACKING RESULTS IN AIR LEAK AND SUBSEQUENT POWER LOSS. SUGGEST ALLIED SIGNAL ENGINEERING REVIEW PART/INSTALLATION PROBLEM. 4 T E4WE 19950526000821995052600082WP 1995 5 26 95ZZZX2446 219950509G725031038391 SEAL 31070852 GARRTTTPE331TPE33112UAR 01514WP TURBINE CRACKED B DSCRK NONE O OTHER ININSP/MAINT 1 GL25 8568 9233151435 P70017 DURING INSPECTION FOR COMPRESSOR DAMAGE, FOUND PART CRACKED 11 PLACES. SB 72-0840 AUTHORIZES INSTALLATION OF PN 3107085-2 TO PROVIDE INCREASED SEAL PLATE TENSION AGAINST FIRST ROTOR ASSY. THIS PART WAS MODIFIED TO PN 3107085-2 BY INCORPORATING A SHIM BETWEEN THE AIR SEAL AND CURVIC COUPLING (NOTE: LIFE LIMITED PART LOG IDENTIFICATION WAS NOT UPDATED UPON MODIFICATION). INCREASED TENSION ON SEAL FLANGE RESULTS IN CRACKING AT FLANGE EDGE. SUGGEST ALLIED SIGNAL ENGINEERING REVIEW CAUSE/RESULT OF THIS DISCREPANCY. TIME SINCE MOD: 2130 HOURS, 2132 CYCLES. NOTE: THIS IS THE FIFTH ASSEMBLY FOUND CRACKED. CYCLES: 8915. 4 T E4WE 19950526000831995052600083WP 1995 5 26 95ZZZX2447 219950508G72508683793 STATOR 8940423 GARRTTTPE331TPE3313U 01514WP 3RD STAGE FAILURE B DSCRO OTHER T ENGINE CASE PENETRATION CRCRUISE 1 GL25 1250 1013459365 P03209 ENGINE EXPERIENCED UNCONTAINED TURBINE SECTION FAILURE IN-FLIGHT. LOCATION OF PENETRATION THROUGH PENUM AND CONDITION OF REMAINING COMPONENTS INDICATE FAILURE OF THE 3RD STAGE ROTOR RESULTING FROM CONTACT OF ROTOR HUB WITH 3 INCH STATOR INNER SHEET METAL SEAL SUPPORT. THIRD STATOR WAS DUE REPLACEMENT IN 8 CYCLES AS REQUIRED BY AD NOTE 92-26-08. CSO: 592 4 T E4WE 19950526001271995052600127GL 1995 5 26 HEEA955024 219950518G7421CH34269 IGNITER PLUG BOLKMS105 BO105S 5626006EU ALLSN 250C 250C20B 03013GL ENGINE FAILED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03105WK281 S812 TIP WORN AND CORRODED, NO IGNITION. 1G72 3U3 U H3EU E4CE 19950526002241995052600224GL 1995 5 26 95ZZZX2472 219950307G732125400012V FUEL CONTROL BELL 206 206L3 1182108SW ALLSN 250C 250C30P 03013GL ENGINE DEFECTIVE B CZ4RK NONE W INADEQUATE Q C ININSP/MAINT 1 AL01133AL 323311 51133 PART WAS ZERO TSO, COULD NOT ADJUST START ADJUSTMENT FOR A COOL ENOUGH START EVEN AT LOWEST SETTINGS. 1G71 3U3 U H2SW E1GL 19950602000991995060200099NE 1995 6 2 95ZZZX2524 219950421G7321 FUEL CONTROL SNIAS 350 AS350D 8680803EU LYC LTS101LTS101600A3 41560NE BELLOWS AIR LEAKS D O OTHER J WARNING INDICATION APAPPROACH 1 WP133608R 1312 1265 LE435560E DURING FINAL APPROACH, M/R RPM DROOPS. PILOT MADE SOFT LANDING ON THE RUNWAY. INSPECTED AND PNEUMATIC LEAK CHECK AND FOUND AIR LEAKS FROM GOVERNOR BELLOWS OF THE FUEL CONTROL UNIT. REMOVED AND REPLACED WITH SERVICEABLE FCU. PERFORMED RUN-UP LEAK CHECK AND NG TOPPING CHECK. ACFT RETURNED TO SERVICE. 1G71 3U3 U H9EU E5NE 19950602001751995060200175EA 1995 6 2 95ZZZX2541 219950419G8530SL74230P5 VALVE GUIDE LW12416 PIPER PA28 PA28161 7102803SO LYC O320 O320D3G 41508EA EXHAUST CRACKED B NX42K NONE O OTHER ININSP/MAINT 1 SO15164ER 995 2841180 DURING CYLINDER REPAIR, THE EXHAUST GUIDE WAS FOUND CRACKED IN THE LOWER PORTION OF THE GUIDE. 1L71 3O3 O 2A13 E274 19950602001761995060200176EA 1995 6 2 95ZZZX2542 219950419G8530SL74230 VALVE GUIDE LW12416 PIPER PA28 PA28161 7102803SO LYC O320 O320D3G 41508EA EXHAUST CRACKED B NX42K NONE O OTHER ININSP/MAINT 1 SO15167ER 1189 2841183 DURING CYLINDER REPAIR, THE EXHAUST GUIDE WAS FOUND CRACKED IN THE LOWER PORTION. 1L71 3O3 O 2A13 E274 19950602001811995060200181SO 1995 6 2 95ZZZX2547 219950509G8530643766 VALVE GUIDE CONT O520 IO520* 17032SO INTAKE WORN D K NONE O OTHER ININSP/MAINT 1 SW11 807949R SIX EACH INTAKE VALVE GUIDES OUT OF NEW LIMITS, .0005 INCH (ONE-HALF THOUSANDTHS) AND TAPERED FROM TOP TO BOTTOM. 3 O E5CE 19950602001821995060200182SO 1995 6 2 95ZZZX2548 219950509G8530643767 VALVE GUIDE CONT O520 IO520* 17032SO EXHAUST WORN D K NONE O OTHER ININSP/MAINT 1 SW11 807949R SIX EACH EXHAUST VALVE GUIDES OUT OF NEW LIMITS, .0006 (SIX-TENTHS OF ONE THOUSANDTH). 3 O E5CE 19950602001831995060200183SO 1995 6 2 95ZZZX2549 219950509G8520 CRANKSHAFT CONT O520 IO520BA 17032SO ROD JOURNAL WORN H K NONE O OTHER ININSP/MAINT 1 SW11 807040R THREE OF THE CONNECTING ROD JOURNALS AND TWO OF THE MAIN BEARING JOURNALS ARE OUT OF NEW LIMITS, .0002 (TWO-TENTHS OF ONE THOUSANDTH). 3 O E5CE 19950602005171995060200517WP 1995 6 2 95ZZZX2613 219950511G72618656645 GASKET CESSNA441 441 2076020CE GARRTTTPE331TPE33110 01514WP PROP PITCH LEAKS H K NONE K FLUID LOSS ININSP/MAINT 1 WP17441JD26 4410336 P77715 ENGINE OIL LEAK DETERMINED TO BE PROP PITCH CONTROL GASKET. INSTALLED THREE MORE NEW GASKETS WITH SAME OIL LEAK. GASKETS HAVE THE WORD 'CANADA' MARKED ON THE EDGE OF THE TACH GENERATOR MOUNT FACE. GASKETS WERE INSTALLED PER GARRETT MM. 1L72 3T4 TRTA28CE E4WE 19950602005301995060200530EA 1995 6 2 95ZZZX2627 219950504G853077160 VALVE GUIDE LW12427 AVIANWSKYHWKSKYHAWK 0900104NM LYC O360 O360A4M 41514EA EXHAUST WORN B NQ2RK NONE O OTHER ININSP/MAINT 1 WP053823R207 17255323 L3387436A CYLINDER REMOVED DUE TO LOW COMPRESSION. FOUND .010 INCH WEAR IN EXHAUST GUIDE ALLOWING EXHAUST VALVE TO WEAR SEAT AND VALVE FACE. THIS WAS A FACTORY NEW ENGINE. VALVE GUIDE, PN 77160. VALVE, PN LW19001. 1B00 3 O A3NW E286 19950602005371995060200537 1995 6 2 95ZZZX2634 119950508G792253E19600 VALVE LYC O360 AEIO360B4A 41514EA THERMO BYPASS NUT LOOSE B CT3RK NONE W INADEQUATE Q C ININSP/MAINT 1 WP17 55733 L1654251A INSPECTION OF THERMOSTIC BYPASS VALVE. NUT WAS FOUND LOOSE. SERIAL NUMBER IS HIGHER THAN VALVES AFFECTED IN TEXTRON LYCOMING SB 518B. 3 O 1E10 19950609000801995060900080EA 1995 6 9 95ZZZX2646 219950418G8500 ENGINE CESSNA172 172P 2072436CE LYC O320 O320D2J 41508EA OIL SYSTEM MAKING METAL H K NONE O OTHER ININSP/MAINT 1 EA07620852283 17275209 L1162539A FILTER WAS OPENED DURING AN ANNUAL INSPECTION. A HIGH AMOUNT OF METAL WAS FOUND, MOSTLY ALUMINUM WITH SOME STEEL. AIRCRAFT WAS GROUNDED AND ENGINE SENT OUT TO OVERHAUL FACILITY FOR DISASSEMBLY. 1H71 3O3 ONT3A12 E274 19950609000811995060900081SO 1995 6 9 95ZZZX2647 219950426G74141056513 STOP PIN MOONEYM20 M20K 5870220SW CONT O360 TSIO360GB 17025SO LT MAG DISLOCATED D O OTHER J WARNING INDICATION CLCLIMB 1 EA074086H 250462 309496 PILOT REPORTED LOW OIL PRESSURE AFTER TAKEOFF. AFTER TROUBLESHOOTING ACTUAL PRESSURE, FOUND WHAT WAS LATER TO BE DETERMINED TO BE THE STOP PIN FROM THE LEFT MAGNETO IN THE SUCTION SCREEN CAUSING LOW FLOW TO OIL PUMP. 1L71 3O3 O 2A3 E9CE 19950609000911995060900091EA 1995 6 9 95ZZZX2657 219950421G8530 CYLINDER CESSNA172 172N 2072434CE LYC O320 O320H2AD 41508EA CYLS 2-4 RINGS BROKEN D K NONE O OTHER ININSP/MAINT 1 SW993065E4095 725 17271425 L405276 DURING 100-HOUR INSPECTION, COMPRESSION ON CYLINDERS 2 AND 4 LOW. REMOVED CYLINDERS. BROKEN AND MISSING PIECES OF RING. OIL SAMPLE SENT OUT. OVERHAUL FACILITY SAYS TAPPET DAMAGE. INSPECTED SAME AND FOUND NR 1 CYLINDER EXHAUST TAPPET WITH HEAVY DAMAGE. ENGINE SENT OUT FOR REPAIR. 1H71 3O3 ONT3A12 E274 19950609000931995060900093SO 1995 6 9 95ZZZX2660 219950130G8520629680M010 COLLAR CONT O520 IO520* 17032SO CRANKSHAFT OIL OUT OF SPEC B YCTRK NONE O OTHER ININSP/MAINT 1 SW11 OIL TRANSFER COLLAR IS OUT OF SPECIFICATIONS. THIS PART WOULD HAVE CAUSED AN ENGINE FAILURE. 3 O E5CE 19950609000941995060900094SO 1995 6 9 95ZZZX2661 219950407G8520649141 CRANKSHAFT CONT O470 O470R 17026SO MAIN BEARING WORN B YCTRK NONE O OTHER ININSP/MAINT 1 SW11 189509 CRANKSHAFT MAIN BEARING JOURNALS OUT OF LIMITS .0005 INCH (ONE-HALF THOUSANDS.) CRANKSHAFT CONNECTING ROD JOURNALS OUT OF LIMITS .0002 INCH. (TWO-TENTHS OF A THOUSANDS.) 3 O E273 19950609000951995060900095SO 1995 6 9 95ZZZX2662 219950130G8530629325 INTAKE PIPE CONT O520 IO520* 17032SO CYLINDER CRACKED B YCTRK NONE O OTHER ININSP/MAINT 1 SW11 INDUCTION PIPE CRACKED, APPROXIMATELY 1.50 INCHES LONG. 3 O E5CE 19950609000961995060900096SO 1995 6 9 95ZZZX2663 219950201G8530 CYLINDER BEECH 35 V35A 1151544CE CONT O520 IO520BA 17032SO NR 2 CRACKED B YCTRK NONE O OTHER ININSP/MAINT 1 SW117624N2147 521 D8854 1218568B CRACKED CYLINDER FROM EXHAUST PORT AROUND CYLINDER HEAD TO SPARK PLUG HOLE, THREE-FOURTHS SEPARATED FROM BARREL. 1L71 3O3 O 3A15 E5CE 19950609000971995060900097SO 1995 6 9 95ZZZX2664 219950216G8520 CRANKSHAFT CONT O520 IO520BA 17032SO ENGINE WORN B YCTRK NONE O OTHER ININSP/MAINT 1 SW11 807023R ENGINE WAS CONTAMINATED WITH METAL. THE CRANKSHAFT HAD TO BE TURNED UNDERSIZE TO REPAIR. FACTORY TEST RUN TIME ONLY. 3 O E5CE 19950609000981995060900098SO 1995 6 9 95ZZZX2665 219950306G8530646286 VALVE STEM CONT O520 IO520BB 17032SO CYLINDER WORN B YCTRK NONE O OTHER ININSP/MAINT 1 SW11 333 274831R FOUND 5 EXHAUST VALVE STEMS WORN ONE-FOURTH THE DIAMETER OF THE VALVE STEM. THESE WERE FOUND ON AN ENGINE TEAR DOWN FOR PROPELLER STRIKE. THESE VALVES WOULD EVENTUALLY HAVE CAUSED ENGINE FAILURE. 3 O E5CE 19950609001021995060900102SO 1995 6 9 95ZZZX2671 219950126G7414M3525 COIL SLICK 88090670 BEECH 58 58 1152740CE CONT O520 IO520C 17032SO MAG FAILED D K NONE O OTHER ININSP/MAINT 1 GL13358Y 825 TH1557 6763A7 NO HIGH TENSION RESISTANCE. SECOND COIL REPLACED ON AIRCRAFT. THIS COIL DATE CODE 91688. 1L72 3O3 O 3A16 E5CE 19950609001051995060900105EA 1995 6 9 95ZZZX2674 219950223G741410103209 COIL BENDIX PIPER PA28 PA28180 7102808SO LYC O360 O360A3A 41514EA MAG CRACKED D K NONE O OTHER ININSP/MAINT 1 GL1344156 A105928 7405224 THIS COIL WAS INSTALLED IN MAGNETO NOT COVERED BY AD 94-01-03 OR AD 94-01-03-R1. SUBMITTER SUGGESTS REMOVING PLASTIC FLAG ON DATA PLATE SIDE OF ALL SUSPECT MAGS AND LOOK WITH A PEN LIGHT FOR IMPROPER COILS. 1L71 3O3 O 2A13 E286 19950609001131995060900113GL 1995 6 9 GCHA957 219950413G723023005250 COMPRESSOR BELL 206 206L1 1182107SW ALLSN 250C 250C30P 03013GL SCROLL CRACKED I GCHAK NONE R PARTIAL RPM/PWR LOSS ININSP/MAINT 1 WP194227E7600 45702 CAE890233 REMOVED COMPRESSOR DUE TO CRACKED COMPRESSOR SCROLL AND LOW POWER. REMOVED COMPRESSOR S/N CAC-90608, AND REPLACED IT WITH COMPRESSOR S/N CAC-90095. 1G71 3U3 U H2SW E1GL 19950609001341995060900134GL 1995 6 9 HEEA955117 219950602G725023032345 COUPLING 23035128 SKRSKYS76 S76A 8143006NE ALLSN 250C 250C30S 03013GL ENG N1 STEPWEAR E HEEAK NONE O OTHER ININSP/MAINT 1 SW031546K826 CAT90437 760082 CAE890431S ENGINE REMOVED DUE TO TURBINE OVERHAUL. UPON INSPECTION OF TURBINE PARTS NOTED THE FOLLOWING: STEP WEAR BEYOND LIMITS ON N1 COUPLING FORWARD I.D. SPLINES. INSTALLED NEW N1 COUPLING. 1G72 3U3 U H1NE E1GL 19950609001351995060900135GL 1995 6 9 HEEA955118 219950602G725023055438 NOZZLE 23035128 SKRSKYS76 S76A 8143006NE ALLSN 250C 250C30S 03013GL 2ND STAGE DEFECTIVE E HEEAK NONE W INADEQUATE Q C ININSP/MAINT 1 SW032743E CAT90644 760155 CAE890476S RECEIVING INSPECTION OF NEW, NEVER INSTALLED 2ND STAGE NOZZLE INDICATES .009" RUNOUT IN BOTH TIP PATHS, DIAPHRAGM OFF CENTER. NOTE: DAMAGE TO KEYS AND TANGS BY ADJUSTMENT PRIOR TO RECEIPT BY PHI. INSTALLED NEW 2ND STAGE NOZZLE. 1G72 3U3 U H1NE E1GL 19950609001361995060900136GL 1995 6 9 HEEA955119 219950602G72506886407 WHEEL 6898735 BOLKMS105 BO105S 5626006EU ALLSN 250C 250C20B 03013GL 1ST STAGE SULFIDATION E HEEAK NONE O OTHER ININSP/MAINT 1 SW03818321000 CAT25276 S828 CAE836418 ENGINE REMOVED DUE TO CYCLED OUT 1ST AND 2ND STAGE WHEELS. UPON INSPECTION OF TURBINE PARTS NOTED THE FOLLOWING: MINOR SULFIDATION ON ALL 1ST STAGE WHEEL BLADES. SCRAPPED 1ST STAGE WHEEL. 1G72 3U3 U H3EU E4CE 19950609001381995060900138GL 1995 6 9 HEEA955121 219950602G72506898782 WHEEL 6898735 BOLKMS105 BO105S 5626006EU ALLSN 250C 250C20B 03013GL 2ND STAGE BLADES FAILED E HEEAK NONE O OTHER ININSP/MAINT 1 SW035419130 CAT32744F S804 CAE836073 ENGINE REMOVED DUE TO ENGINE FAILURE ON RUN-UP. UPON INSPECTION OF TURBINE PARTS NOTED THE FOLLOWING: 100% OF 1ST STAGE WHEEL BLADE TIPS FAILED .450" OUTBOARD FROM HUB TO BLADE TIP LEADING EDGE DUE TO THERMAL FATIGUE CAUSED BY ENGINE OPERATING IN AN OVERTEMPERATURE CONDITION AND 94% OF 2ND STAGE WHEEL BLADE TIPS FAILED .781" OUTBOARD FROM HUB TO BLADE TIP LEADING EDGE. SCRAPPED 1ST AND 2ND STAGE WHEELS. SEE MMIR #5120 FOR 2ND STAGE WHEEL INFORMATION. 1G72 3U3 U H3EU E4CE 19950609001491995060900149GL 1995 6 9 HEEA955057 219950523G725023032345 COUPLING 23035128 BELL 206 206L1 1182107SW ALLSN 250C 250C30P 03013GL ENG N1 STEPWEAR E HEEAK NONE O OTHER ININSP/MAINT 1 SW032135V683 CAT97841 45657 CAE895561 ENGINE REMOVED DUE TO TURBINE OVERHAUL AND COMPRESSOR 1750 HOUR INSPECTION. UPON INSPECTION OF TURBINE PARTS NOTED THE FOLLOWING: STEP WEAR BEYOND LIMITS ON N1 COUPLING I.D. SPLINES. INSTALLED NEW N1 COUPLING. 1G71 3U3 U H2SW E1GL 19950609001521995060900152NE 1995 6 9 HEEA955060 219950523G72610292005220 ENGINE SNIAS 350 AS350B2 8680813EU TMECA ARRIELARRIEL1 60030NE OIL SYS FAILED E HEEAK NONE O OTHER ININSP/MAINT 1 SW03609511294 2771 OIL BLOWING OUT EXHAUST AND OIL PSI FELL TO ZERO. 1G71 3U3 U H9EU E19EU 19950609001621995060900162GL 1995 6 9 HEEA955071 219950524G72506886407 WHEEL 6898735 BOLKMS105 BO105S 5626006EU ALLSN 250C 250C20B 03013GL 1ST STAGE BLADESSULFIDATION E HEEAK NONE O OTHER ININSP/MAINT 1 SW03541971691 CAT37782 S805 CAE802035F ENGINE REMOVED DUE TO TURBINE 1750 HOUR INSPECTION AND BURNT 1ST STAGE NOZZLE. UPON INSPECTION OF TURBINE PARTS NOTED THE FOLLOWING: MINOR SULFIDATION ON ALL 1ST STAGE WHEEL BLADES. SCRAPPED 1ST STAGE WHEEL. 1G72 3U3 U H3EU E4CE 19950609001631995060900163GL 1995 6 9 HEEA955072 219950524G72506895801 WHEEL 23033185 BELL 206 206L1 1182107SW ALLSN 250C 250C28B 03013GL 1ST STAGE BLADESSULFIDATION E HEEAK NONE O OTHER ININSP/MAINT 1 SW032758N1373 CAT70546 45267 CAE860213 ENGINE REMOVED DUE TO TURBINE OVERHAUL. UPON INSPECTION OF TURBINE PARTS NOTED THE FOLLOWING: SULFIDATION ON ALL 1ST STAGE WHEEL BLADES. SCRAPPED 1ST STAGE WHEEL. 1G71 3U3 U H2SW E1GL 19950609001811995060900181GL 1995 6 9 HEEA955091 219950525G723023007208 DIFFUSER VANE 23033192 ALLSN 250C 250C28C 03013GL ENGINE SEPARATION E HEEAK NONE O OTHER ININSP/MAINT 1 SW03 CAC28048 CAE280047 ENGINE REMOVED DUE TO TURBINE OVERHAUL, COMPRESSOR N1 SHAFTING INSPECTION AND UPGRADE CEB'S. UPON INSPECTION OF COMPRESSOR PARTS NOTED THE FOLLOWING: TURNING VANE APPEARS TO BE SEPARATING FROM FORWARD AND AFT PLATES ON DIFFUSER VANE ASSY AND MATING SURFACES ARE DEFLECTED CAUSING LOW POWER DURING TEST CELL RUN. 3 U E1GL 19950609002551995060900255SO 1995 6 9 95ZZZX2683 119950503G8120646434 CLAMP PIPER PA46 PA46310P 7104605SO CONT O520 TSIO520BE 17040SO LT TURBO EXH BROKEN D K NONE O OTHER ININSP/MAINT 1 WP23424J 468408019 273511R ON 5-3-95 WHILE ENGINE WAS BEING CHECKED FOR UNRELATED MATTER, MECHANIC NOTED BROKEN CLAMP WHICH HOLDS EXHAUST TO LEFT TURBOCHARGER. IT APPEARED TO HAVE BEEN OVERTORQUED AS ENDS OF CLAMP WERE TOUCHING AND SAFETY WIRED IN THAT POSITION. MECHANIC THEN REMOVED AND INSPECTED SIMILAR CLAMP ON RIGHT TURBO TO EXHAUST AND FOUND IT CRACKED ALSO. SUGGEST EARLY REPLACEMENT. THESE APPEARED TO BE ORIGINAL EQUIPMENT. 1L71 3O3 O A25SO E8CE 19950609002681995060900268EA 1995 6 9 95ZZZX2696 219950503G7414ES10382585 CONTACT ASSY 1068255511 MOONEYM20 M20J 5870219SW LYC O360 IO360A3B6 41514EA CAM FOLLOWER WORN B NX42K NONE O OTHER ININSP/MAINT 1 SO15189ER 396 B6208910C 24169814 MAGNETO WAS REMOVED FROM THE AIRCRAFT AFTER MAGNETO TIMING CHECK INDICATED MAGNETO INTERNAL TIMING WAS OFF BY 10 DEGREES. MAGNETO DISASSEMBLY INSPECTION REVEALED EXCESSIVE CAM FOLLOWER WEAR. CAM FOLLOWER ALSO APPEARED MELTED. CONTINUED OPERATION WOULD HAVE CAUSED MAGNETO TO BECOME INOPERATIVE. 1L71 3O3 O 2A3 1E10 19950609002721995060900272 1995 6 9 95ZZZX2700 119950502G792275944 VALVE LYC O360 IO360A1B6 41514EA THERMO BYPASS CRIMP NUT LOOSE D K NONE O OTHER ININSP/MAINT 1 EA09 122198 REF LYC SB 518B. TWO OUT OF THREE NUTS HAVE BEEN LOOSE. ONE NUT WAS CRACKED. 3 O 1E10 19950609002841995060900284EA 1995 6 9 95ZZZX2712 219950303G853069603 HOSE CESSNA172 172M 2072418CE LYC O320 O320E2D 41508EA INTAKE COUPLING DEFECTIVE D K NONE R PARTIAL RPM/PWR LOSS ININSP/MAINT 1 GL139526H 17266201 L4349627A UPON INVESTIGATION OF LOWER THAN NORMAL POWER OUTPUT, FOUND INTAKE COUPLING HOSE INTERIOR (ALL 4) INTERNALLY REDUCING IN SIZE FROM 1.75 INCHES TO 1.25 INCHES. THIS IS A SUBSTANTIAL REDUCTION IN FLOW (NEARLY ONE-HALF VOLUME) FROM 3.06 SQUARE INCH TO 1.56 SQUARE INCH. THE COUPLINGS APPEAR TO HAVE SUFFERED FROM HEAT DUE TO PROXIMITY OF HOT EXHAUST. POWER RESUMED NORMAL UPON REPLACEMENT OF NEW COUPLINGS. 1H71 3O3 ONT3A12 E274 19950609002851995060900285CE 1995 6 9 95ZZZX2713 119950303G8011EBB75A BENDIX DRIVE PRESTOLITE MZ4222 CESSNA172 172L 2072432CE LYC O320 O320E2D 41508EA STARTER FAILED D K NONE O OTHER ININSP/MAINT 1 GL137809G 17259559 THE STARTER MOTOR TURNS, BUT THE BENDIX WILL NOT ENGAGE. POSSIBLE FAULTS: 1. WORN. 2. WRONG LUBRICANT - NOT SILICONE AS RECOMMENDED. 3. DIRT/OIL PREVENTING 'SLIDING' AS REQUIRED. 1H71 3O3 ONT3A12 E274 19950609002861995060900286SO 1995 6 9 95ZZZX2714 219950303G853024047 VALVE GUIDE CESSNA150 150M 2071830CE CONT O200 O200A 17020SO EXHAUST FAILED D K NONE W INADEQUATE Q C ININSP/MAINT 1 GL13714AJ 1005 15079024 255534A48 ENGINE MAJOR OVERHAULED WITH CYLINDERS SUPPLIED BY AERO AVIATION. CYLINDERS WENT 100 HOURS AND VALVE GUIDES FAILED DUE TO IMPROPER INSTALLATION. THEY WERE INSTALLED SO LOOSE THAT FIRE WAS EATING AWAY AT THE OUTSIDE OF THE GUIDE WHERE IT IS SUPPOSED TO BE A PRESS FIT IN THE CYLINDER HEAD. SN 41593, SN 41591, SN 41595 HAD GUIDES INSTALLED BY A BETTER CYLINDER HOUSE, THE ENGINE NOW HAS 450 HOURS SMOH, AND RUNS JUST FINE. 1H71 3O3 O 3A19 E252 19950609002871995060900287SO 1995 6 9 95ZZZX2715 219950303G85501250922202 ADAPTER CESSNA182 182E 2072712CE CONT O470 O470* 17026SO OIL FILTER DEFECTIVE D K NONE O OTHER ININSP/MAINT 1 GL139390X 18253790 WHEN INSPECTING FILTER ADAPTER IAW SEB 93-1R1A, FOUND FRETTING OF THE MOUNTING THREADS. THIS RENDERED THE ADAPTER UNAIRWORTHY. ADAPTER REPLACED WITH NEW UNIT. 1H71 3O3 ONT3A13 E273 19950609002921995060900292SO 1995 6 9 95ZZZX2720 219950407G8530 CYLINDER CESSNA340 340A 2076405CE CONT O520 TSIO520N 17040SO ENGINE DEFECTIVE D K NONE O OTHER ININSP/MAINT 1 SW05300JM3527 432 340A0233 509401 AT OVERHAUL, 5 CYLINDERS WERE CERAMICHROME AND 1 WAS CHANNELCHROME. AT THE 100-HOUR INSPECTION. COMPRESSION WAS HIGH 60'S ON THE CERAMICHROME, 77 ON THE CHANNELCHROME. A PRE-BUY INSPECTION WAS DONE 2 HOURS LATER AND THE COMPRESSION DROPPED 20 POUNDS ON THE CERAMICHROME. THIS PROBLEM IS CONSISTENT ON CERAMICHROME CYLINDERS. 1L72 3O3 O 3A25 E8CE 19950609004081995060900408EA 1995 6 9 95ZZZX2725 219950518G8530 RETAIN STUD CESSNA172 172N 2072434CE LYC O320 O320H2AD 41508EA NR 4 CYL ROCKER BACKED OUT D A UNSCHED LANDING ERKVIBRATION/BUFFET PARTIAL RPM/PWR LOSS FLUID LOSS CRCRUISE 1 NE03734XC1100 17269188 RL00595576T AFTER APPROXIMATELY 5 MINUTES IN CRUISE FLIGHT, THE PILOT REPORT A LOSS OF ENGINE POWER AND A SEVERE ROUGHNESS AND AN AIRPORT LANDING WAS MADE WITHOUT INCIDENT. INVESTIGATION REVEALED NR 4 CYLINDER INTAKE VALVE PUSH ROD AND SHROUD WERE BURNED AND LEAKING OIL. THE EXHAUST VALVE RETAIN STUD FOR THE FULCRUM AND ROCKER ARM HAD BACKED OUT APPROXIMATELY 5 THREADS; THUS, CREATING EXCESSIVE VALVE CLEARANCE. THE OTHER 3 CYLINDERS WERE INSPECTED AND THIS CONDITION OF THE ROCKER ASSY RETAIN STUD ALSO EXSISTED ON NR 2 CYLINDER. 1H71 3O3 ONT3A12 E274 19950609004101995060900410EA 1995 6 9 95ZZZX2727 219950517G8530AL19001 VALVE LYC O320 O320D3G 41508EA EXHAUST WORN B CYKRK NONE ER VIBRATION/BUFFET PARTIAL RPM/PWR LOSS ININSP/MAINT 1 GL07 336 L851039A ENGINE RAN ROUGH AT IDLE AND LOUD MECHANICAL NOISES WERE REPORTED. VISUAL INSPECTION OF ENGINE BEFORE DISASSEMBLY SHOWED ZERO VALVE STEM TO ROCKER CLEARANCE. DISASSEMBLY OF CYLINDER SHOWED EXHAUST VALVE PN AL19001 WORN EXCESSIVELY IN THE RETAINER GROOVE. RECOMMEND REPLACEMENT OF EXHAUST VALVE. 3 O E274 19950609004111995060900411EA 1995 6 9 95ZZZX2728 219950517G8530AL19001 VALVE LYC O320 O320E2D 41508EA EXHAUST WORN B CYKRK NONE ER VIBRATION/BUFFET PARTIAL RPM/PWR LOSS ININSP/MAINT 1 GL07 296 L3354027A ENGINE RAN ROUGH AT IDLE AND LOUD MECHANICAL NOISES WERE REPORTED. VISUAL INSPECTION OF ENGINE BEFORE DISASSEMBLY SHOWED ZERO VALVE STEM TO ROCKER CLEARANCE. DISASSEMBLY OF CYLINDER SHOWED EXHAUST VALVE PN AL19001 WORN EXCESSIVELY IN THE RETAINER GROOVE. RECOMMEND REPLACEMENT OF EXHAUST VALVE. 3 O E274 19950609004121995060900412SO 1995 6 9 95ZZZX2729 219950530G85500024100143 PAN BEECH 36 A36 1151604CE CONT O520 TSIO520UB 17040SO ENGINE CRACKED B HBKRK NONE K FLUID LOSS ININSP/MAINT 1 SW118285C268 E2810 HOLE HAD BROKEN OUT IN CENTER OF PAN. PAN IS FORMED FROM .032. NOTIFIED BEECH OF PROBLEM. INSTALLED A NEW PART. BEECH INDICATED THEY MAY USE .061 MATERIAL SOMETIME IN THE FUTURE. 1L71 3O3 O 3A15 E8CE 19950609004171995060900417EA 1995 6 9 95ZZZX2734 219950418G8530 CYLINDER PIPER PA28 PA28161 7102803SO LYC O320 O320D3G 41508EA NR 4 FAILED D A UNSCHED LANDING ER VIBRATION/BUFFET PARTIAL RPM/PWR LOSS CLCLIMB 1 NE038115H 800 288016117 L941139A PILOT DECLARED AN EMERGENCY SHORTLY AFTER TAKEOFF DUE TO ROUGH RUNNING ENGINE. FOUND NR 4 CYLINDER HAD .50 INCH DIAMETER PIECE OF ALUMINUM BURNED OUT NEAR EXHAUST VALVE SEAT. POSSIBLY CAUSED BY PRE-IGNITION OR DETONATION. APPROXIMATELY 300 HOURS PRIOR, ENGINE WAS CRACKING THE PORECELAIN IN THE SPARK PLUGS. MOST LIKELY HAPPENED DUE TO IMPROPER LEANING. 1L71 3O3 O 2A13 E274 19950609004191995060900419EA 1995 6 9 95ZZZX2736 219950511G855061837 VALVE SLEEVE PIPER PA28 PA28180 7102808SO LYC O360 O360A3A 41514EA PRESS RELIEF VLVBROKEN D K NONE O OTHER ININSP/MAINT 1 WP117851W4402 281870 L726636A FOUND LARGE ALUMINUM PARTS IN SUCTION SCREEN. THEY APPEARED BROKEN AND UNMARRED, I,E,; HAD NOT BEEN GROUND UP IN A GEAR TRAIN. FURTHER INVESTIGATION USING LYCOMING OVERHAUL MANUAL NR 60294-7, PAGE 7-2, IDENTIFIED POSS END ITEM, DISASSEMBLED OIL PSI RELIEF VALVE PLUG AND FOUND SLEEVE (IT-16) MISSING 2 SIDES. UPON REMOVAL OF SLEEVE, WAS ABLE TO REASSEMBLY ENTIRE ITEM WITH PARTS FOUND IN SUCTION SCREEN. INSTALLED NEW ASSY AND RETURNED ENGINE TO SERVICE. 1L71 3O3 O 2A13 E286 19950609006191995060900619GL 1995 6 9 95ZZZX2784 219950522G723023005250 COMPRESSOR BELL 206 206L3 1182108SW ALLSN 250C 250C30P 03013GL ENGINE CONTAMINATED B ALGRK NONE O OTHER ININSP/MAINT 1 SW03343AL10813 51372 DURING A COMPRESSOR CHANGE FOUND WHILE POSITIONING THE COMPRESSOR ON A WORK BENCH, A SMALL WHITE HARD BEAD ROLLED OUT OF THE SCROLL DISCHARGE TUBE. THE COMPRESSOR SCROLL WAS BORESCOPED TO CHECK FOR ANY MORE BEADS WHICH MAY HAVE BEEN LODGED IN THE SCROLL. NO FURTHER BEADS WERE NOTED. 1G71 3U3 U H2SW E1GL 19950609006201995060900620GL 1995 6 9 95ZZZX2785 219950502G72606898642 GEARSHAFT BELL 206 206L3 1182108SW ALLSN 250C 250C30P 03013GL GEARBOX PITTED B ALGRK NONE O OTHER ININSP/MAINT 1 SW03343AL3053 51372 UPON DISASSEMBLY AND INSPECTION, FOUND AIR OIL GEARSHAFT PITTED. 1G71 3U3 U H2SW E1GL 19950609006391995060900639GL 1995 6 9 95ZZZX2804 219950502G724023030911 COMBUSTION CASE 230335128 SKRSKYS76 S76 8143010NE ALLSN 250C 250C30S 03013GL ARMPIT CRACKED B ALGRK NONE O OTHER ININSP/MAINT 1 SW03701AL 1750 28263 760238 THIS DEFECT WAS DISCOVERED AT 1750-HOUR OVERHAUL. OUTER COMBUSTION CASE WAS CRACKED IN ARMPIT UNDER THE SCREEN PATCH REINFORCEMENT AND EXTENDED ON SEAM AND INTO THE SEAM PERPENDICULAR TO THE FLANGE AND PARALLEL TO THE FLANGE. A CRACK SUCH AS THIS MAY CAUSE POSSIBLE POWER LOSS IN ENGINE. NO REPAIR IS PERMITTED IN THIS AREA. OUTER COMBUSTION CASE IS SCRAPPED. CAUSE UNKNOWN. 1G72 3U3 U H1NE E1GL 19950609008291995060900829EA 1995 6 9 95ZZZX2839 219950505G72613004091 SCREEN BEECH 200 200BEECH 1152920CE PWA PT6 PT6A41 52043EA OIL SCAV PUMP BLOCKED BL ERY2E ENGINE SHUTDOWN JK WARNING INDICATION FLUID LOSS CRCRUISE 1 SO11780RC4949 1808 BB780 PCE81769 PILOT REPORTED LOSS OF OIL PRESSURE DURING FLIGHT. THE ENGINE WAS SHUT DOWN AND AN UNEVENTFUL LANDING MADE. OIL WAS LEAKING FROM THE COMPRESSOR INLET AND BLEED AIR VALVES. AFTER TROUBLESHOOTING, THE ACCESSORY GEARBOX WAS DISASSEMBLED AND THE INLET SCREEN FOR THE OIL SCAVAGE PUMP WAS BLOCKED WITH VARNISH COATING FROM INSIDE THE GEARBOX. ENGINE REMOVED AND SENT TO P AND W FOR REPAIR. 1L72 4T4 T A24CE E4EA 19950616000631995061600063WP 1995 6 16 95ZZZX2851 219950510G725031038391 SEAL 31969752 GARRTTTPE331TPE33112UA 01514WP TURB ROTATE AIR CRACKED B DSCRK NONE O OTHER ININSP/MAINT 1 GL25 6977 9233151471 P70032 DURING INSPECTION FOR CAM, FOUND PART CRACKED 15 PLACES. SB 72-0840 AUTHORIZES INSTALLATION OF PN 3107085-2 TO PROVIDE INCREASED SEAL PLATE TENSION AGAINST THE FIRST STAGE ROTOR ASSEMBLY BY INCORPORATING A SHIM BETWEEN THE AIR SEAL AND CURVIC COUPLING. INCREASED TENSION ON THE SEAL FLANGE RESULTS IN CRACKING AT THE SEAL PLATE FLANGE; 3714 CYCLES, 3735:28 HOURS IN SERVICE SINCE COMPLIANCE WITH SB 72-0840. 4 T E4WE 19950616000641995061600064NE 1995 6 16 95ZZZX2852 219950530G7314025323150 PUMP PESCO CESSNA425 425 2076018CE PWA PT6 PT6A112 52043NE LT ENG FUEL FAILED D K NONE K FLUID LOSS NRNOT REPORTED 1 SW091BM 2092 4250042 PCE12091 FUEL PUMP ON LEFT ENGINE, SEAL LEAKED FUEL INTO FUEL CONTROL DRIVE, WASHING THE GREASE OUT OF THE DRIVE BEARING CAUSING BEARING FAILURE AND DRIVE COUPLING TO SHEAR. 1L72 3T3 TRTA7CE E4EA 19950616001301995061600130EA 1995 6 16 95ZZZX2883 219950501G732246A227 VENTURI FACET MA45 PIPER PA32 PA32260 7103206SO LYC O540 O540E4B5 41532EA CARBURETOR CORRODED D K NONE O OTHER ININSP/MAINT 1 GL234315T R418863 327200016 L1061440 FOUND CORROSION IS OCCURRING BELOW THE SURFACE OF THE CASTING CAUSING THE SURFACE TO BUBBLE UP, CHANGING THE SHAPE OF THE VENTURI. IF THIS PART IS PLATED, CAN THE PLATING BE ELIMINATED? 1L71 3O3 O A3SO E295 19950616001331995061600133SO 1995 6 16 95ZZZX2886 219950519G8520 CRANKSHAFT BEECH 55 95B55 1152706CE CONT O520 IO520E 17032SO FLANGE CRACKED D A UNSCHED LANDING JK WARNING INDICATION FLUID LOSS NRNOT REPORTED 1 SO093653A 600 TC1309 515599R EMERGENCY LANDING MADE DUE TO OIL LOSS AND PRESSURE LOSS. FOUND OIL LOSS AT APPROXIMATELY 1 QUART PER MINUTE AT 1,000 RPM. REMOVED PROPELLER AND FOUND FLANGE CRACKED 50 PERCENT AROUND CIRCUMFERENCE OF FLANGE. FAILURE OF CRANKSHAFT (LOSS OF PROPELLER) WAS VERY LIKELY TO HAPPEN AT ANY TIME. NOTE: THIS INSTALLATION IS A COLEMILL CONVERSION. VAR CRANKSHAFT NOT INSTALLED. 1L72 3O3 O 3A16 E5CE 19950616001391995061600139SO 1995 6 16 95ZZZX2892 219950530G8520633620 CRANKSHAFT CESSNA340 340CESSNA 2076404CE CONT O520 TSIO520J 17040SO MAIN JOURNAL BROKE D EA ENGINE SHUTDOWN UNSCHED LANDING Y ENGINE STOPPAGE CRCRUISE 1 EA037632Q6532 440 3400236 218750 ENGINE FAILURE - LEVEL AT 12,000 FEET MSL CRUISE POWER. RAPID REDUCTION IN RPM, M.A.P., AND O.P., THEN PUT IN FEATHER. UPON LANDING, MECHANIC DETERMINED THAT NR 1 AND NR 2 CYLINDERS PISTONS DO NOT MOVE WHEN CRANKSHAFT/PROPELLER IS ROTATED. ALTHOUGH THE ENGINE HAS YET TO BE DISASSEMBLED, IT CAN BE ASSUMED THE CRANKSHAFT IS PROBABLY BROKEN AT A REAR MAIN JOURNAL. 1L72 3O3 O 3A25 E8CE 19950616001521995061600152SO 1995 6 16 95ZZZX2906 219950504G7310635158S4S32 HOSE ASSY BEECH 33 F33A 1151425CE CONT O520 IO520BB 17032SO FUEL INJ LEAKING B ACGHRK NONE K FLUID LOSS ININSP/MAINT 1 GL038132N404 CE1585 578743 PILOT REPORTS THE ENGINE COULD NOT BE LEANED AT ALTITUDE AND THAT IT WOULD NOT IDLE OR CONTINUE RUNNING AT SPEEDS BELOW 800 RPM. FOUND THE FLEXIBLE FUEL LINE LEAKING THROUGH THE BRAIDED EXTERIOR ALONG ITS ENTIRE LENGTH. THIS LINE SUPPLIES FUEL FROM THE FUEL INJECTOR TO THE FUEL FLOW TRANSMITTER HARD LINE. IT IS ROUTED BETWEEN NR 3 AND NR 5 CYLINDERS. 1L71 3O3 O 3A15 E5CE 19950616003261995061600326NE 1995 6 16 95ZZZX2938 219950605G7321 FUEL CONTROL CESSNA425 425 2076018CE PWA PT6 PT6A112 52043NE ROD ENDS REQ LUBE B EIPRO OTHER O OTHER DEDESCENT 1 WP076773L 4250037 PCE12119 HOBBS 115.1. TT A/F 4861.2. ON DESCENT, LEFT ENGINE DID NOT RESPOND TO POWER REDUCTION. TROUBLESHOT, CLEANED, AND LUBRICATED F.C.U., ROD ENDS, AND LINKGAGE. OPS CHECK OKAY. FLIGHT CHECK OKAY. ENGINE T.S.O. 1369.7. 1L72 3T3 TRTA7CE E4EA 19950616003281995061600328WP 1995 6 16 95ZZZX2940 219950605G723030720122 BLADE AMD FALC50FALCON50MYST2730106EU GARRTTTFE731TFE7313 01518WP 2ND STAGE LP SEPARATED D O OTHER O OTHER CRCRUISE 1 GL054350M6299 142 76556 SECOND STAGE L.P. BLADE SEPARATED IN STRESS RUPTURE, 4712 CYCLES. OCCURRED ON 1-31-95 IN-FLIGHT. REF: SB TFE 731-72-3556. 2L73 4F4 F A46EU E6WE 19950616003291995061600329WP 1995 6 16 95ZZZX2941 219950605G723030720122 BLADE AMD FALC50FALCON50MYST2730106EU GARRTTTFE731TFE7313 01518WP 2ND STAGE LP FAILED D K NONE O OTHER NRNOT REPORTED 1 GL054350M6352 142 76568 OCCURRENCE 4-26-95. SECOND STAGE L.P. BLADE FAILURE IN-FLIGHT TO EWR. REF: SB TFE731-72-3556 STRESS RUPTURE. 2L73 4F4 F A46EU E6WE 19950616003381995061600338EA 1995 6 16 95ZZZX2950 219950503G741410382585 CONTACT ASSY D6LN3000 PIPER PA32 PA32RT300 7103215SO LYC O540 IO540K1G5 41532EA RT MAG TIP BROKEN B CQVRK NONE O OTHER ININSP/MAINT 1 CE013659028 8325063 32R7885197 L1831648A PILOT NOTED A DEAD MAG IN THE RIGHT POSITION. INVESTIGATION REVEALED THE POINTS NOT OPENING. CONTACT ASSEMBLY HAS TIP BROKEN OFF. PART TOTAL TIME 30 HRS. TCM IGNITION SB 651 COVERS THIS, BUT IS NOT WELL KNOWN. RECOMMEND ALERT BE ISSUED. 1L71 3O3 O A3SO 1E4 19950616003451995061600345SO 1995 6 16 95ZZZX2957 219950521G8500 ENGINE GULSTM680 685 0141612SW CONT O520 GTSIO520K 17032SO NR 2 CYL FAILED D K NONE O OTHER ININSP/MAINT 1 EA05333HQ 12018 605129 ENG. LOST M.P. AND OIL PRESS. FOUND COMP. TURBO DAMAGE, NR 2 CYLINDER. PISTON NOT MOVING AND LIFTERS MISSING FROM HOUSINGS. THREE CYLINDERS FOUND VISIBLY CRACKED. OIL FOUND IN VAC. AND PRESS. PUMP LINES. 'LINES FOUND CON BACKWARDS ON VAC-PRESS. PUMP.' 71 HRS S.M.O.H. RECENT ANNUAL S.M.O.H. SUBMITTER SUGGESTS STRICTER CONTROL ON ENG. OVERHAULERS AND MAINT. SHOP. 1H72 3O3 O 2A4 E7CE 19950616003471995061600347EA 1995 6 16 95ZZZX2959 219950514G7322MA4SPA CARBURETOR FACET PIPER PA28 PA28140 7102802SO LYC O320 O320E3D 41508EA VENTURI DEFECTIVE D K NONE O OTHER ININSP/MAINT 1 SO051453T 200 287225521 L3182327A SINCE INSTALLING ONE-PIECE VENTURI, ENG. HAS PROGRESSIVELY RUN RICH - HAVE HAD CARB. APART ON 2 OCCASIONS TO CHECK FLOAT LEVEL, VENTURI, ACCELL. PUMP, AND NEEDLE AND SEAT FOR PERFORMANCE, MIXTURE HAS TO BE LEANED (1) KNOB. VIOLENT SHUDDER ON POWER REDUCTION UNLESS MIXTURE IS LEANED FIRST. SUSPECT CARB. NEEDS DIFFERENT DISCHARGE NOZZLE WITH THIS VENTURI. 1L71 3O3 O 2A13 E274 19950616003541995061600354EA 1995 6 16 95ZZZX2966 219950606G8550 ENGINE CESSNA210 P210N 2073454CE LYC O540 TIO540V2AD 41532EA OIL PAN OIL SLUDGE D K NONE O OTHER ININSP/MAINT 1 SO034994K800 P21000392 L861661A DURING TEAR DOWN INSPECTION OF ENGINE AFTER PROP STRIKE, THICK OIL SLUDGE DEPOSITS WERE FOUND IN THE CRANKSHAFT AND THE OIL PAN. TWO ACCESSORY HOUSING GEARS HAD TO BE REPLACED DUE TO PITTING AND WEAR. RECORDS SHOW THE ENGINE HAD BEEN RUN USING MOBILE AV-1 OIL FROM 05-02-88 THROUGH 03-25-93 FOR A TOTAL OF 592.6 HOURS. THE SOLID FILM IN THE CRANKSHAFT AND OIL PAN MEASURED .1250 INCH THICK. 1H71 3O3 O 3A21 E14EA 19950616004781995061600478SO 1995 6 16 95ZZZX3002 219950515G8520 ROD CESSNA414 414A 2075907CE CONT O520 TSIO520NB 17040SO ENGINE FAILED E EAVVA UNSCHED LANDING O OTHER NRNOT REPORTED 1 GL0936934820 414A0486 276819R ENGINE CAME APART IN-FLIGHT. SUSPECT CONNECTING ROD OR COUNTERWEIGHT FAILURE. DATE 5-15-95. 1L72 3O3 O A7CE E8CE 19950616004821995061600482EA 1995 6 16 95ZZZX3006 219950529G8520149518 BEARING WRIGHTR1820 R182080 67020EA MASTER ROD FAILED B EJ4RK NONE O OTHER ININSP/MAINT 1 SW11 473912 MASTER ROD BEARING FAILED AND SEIZED TO CRANKSHAFT ROD JOURNAL ON GROUND AFTER START-UP. LACK OF PROPER LUBRICATION. SUSPECT CAUSED FROM NOT PROPERLY PRE-OILING DURING START-UP. SUBMITTER SUGGESTS THIS ENGINE IS EXTREMELY SENSITIVE TO OIL STARVATION AT START-UP, ESPECIALLY AFTER SITTING. 4 R E259 19950616004911995061600491NE 1995 6 16 95ZZZX3015 219950529G8530116731 CYLINDER PWA R1830 R183092 52020NE NR 12 FAILED B EJ4RO OTHER O OTHER NRNOT REPORTED 1 SW11 480 56873 NR 12 CYLINDER SKIRT CRACKED AND BROKE OFF IN-FLIGHT AFTER CHAFING MOST OF ONE SIDE OF PISTON AWAY. 4 R 5E4 19950623000271995062300027GL 1995 6 23 95ZZZX3026 219950207G732023007827 VALVE BELL 206 206L3 1182108SW ALLSN 250C 250C30 03013GL ENG INOPERATIVE C K NONE O OTHER ININSP/MAINT 1 EU01732H 20 3457 51607 VALVE INOPERATIVE. 1G71 3U3 U H2SW E1GL 19950623000281995062300028GL 1995 6 23 95ZZZX3027 219950128G732023007827 VALVE BELL 206 206L3 1182108SW ALLSN 250C 250C30 03013GL ENG FAILED C K NONE O OTHER ININSP/MAINT 1 EU01732H 1526 2395 51607 THE SOLENOID VALVE IS NOT WORKING. 1G71 3U3 U H2SW E1GL 19950623000361995062300036SO 1995 6 23 95ZZZX3034 219950607G855012509222 ADAPTER ASSY BEECH 35 J35 1151522CE CONT O470 IO470C 17026SO OIL FILTER WORN GS A UNSCHED LANDING JK WARNING INDICATION FLUID LOSS CRCRUISE 1 EA018378D405 D5497 786273CR DURING CRUISE FLIGHT, THE ENGINE BEGAN TO LOSE OIL PRESSURE. THE PILOT DECLARED AN EMERGENCY AND LANDED IN A FIELD WITH MINIMAL DAMAGE. THE ENGINE HAD BEEN EQUIPPED WITH FULL FLOW OIL FILTER KIT INSTALLED UNDER STC 3262 WE. THE THREADS ON THE ADAPTER ASSEMBLY BECAME WORN AND THE ADAPTER WAS LOOSE WHERE IT FITS INTO THE ENGINE ACCESSORY CASE. THE OIL LEAKED OUT AROUND THE ADAPTER AND THE ENGINE SEIZED. THE ADAPTER NUT ITEM NR 5 GETS TORQUED DOWN COMPRESSING A PACKING ITEM NR 6. IF THE NUT WERE UNDERTORQUED, THE WEIGHT OF THE FILTER PLUS THE LENGTH OF THE ADAPTER WOULD CREATE LEVERAGE TO VIBRATE AND WEAR OUT THE THREADS OF THE ADAPTER. THE THREADS OF THE ENGINE CASE WERE IN GOOD CONDITION. 1L71 3O3 O 3A15 E273 19950623000401995062300040EA 1995 6 23 95ZZZX3038 219950606G7250310250201 BLADE 3029312 BEECH 1900 1900C 1154161CE PWA PT6 PT6A65B 52043EA 1ST PT TIP MISSING B MASRK NONE W INADEQUATE Q C ININSP/MAINT 1 SW01259AF 3729 UB55 32028 THE POWER SECTION WAS RECEIVED FROM ARIZONA AIRWAYS WITH 35 PERCENT OF A FIRST STAGE PT BLADE TIP PLATFORM MISSING. AFTER THE PT BLADE AND DISK WERE DISASSEMBLED AND INSPECTED, A TOTAL OF (2) 1ST STAGE AND (11) 2ND STAGE BLADES WERE REPLACED. 2L72 4T4 TRTA24CE E4EA 19950623000421995062300042NE 1995 6 23 95ZZZX3040 219950301G7210310983901 SHAFT BEECH 1900 1900D 1154162CE PWA PT6 PT6A67 52043NE PROP SHAFT GALLED B MASRK NONE O OTHER ININSP/MAINT 1 SW013YV 3970 4X271 UE3 114086 THE POWER SECTION WAS REPORTED AS HARD TO ROTATE. UPON DISASSEMBLY, FOUND PROP SHAFT AND SLEEVE WAS GALLED IN SUCH A WAY THAT IT COULD NOT ROTATE FREELY. IT HAS BEEN DETERMINED THE GALLING OCCURRED DUE TO FUEL OIL HEATER CONTAMINATING THE OIL SYSTEM WITH FUEL. 2L72 4T4 TRTA24CE E26NE 19950623000431995062300043NE 1995 6 23 95ZZZX3041 219950411G7250311269601 BEARING BEECH 1900 1900D 1154162CE PWA PT6 PT6A67 52043NE PWR TURB SPALLED B MASRK NONE O OTHER ININSP/MAINT 1 SW01154ZV21613557 FC22643 UE154 32041 THE METAL OBSERVED IN THE POWER SECTION WAS BEING GENERATED BY THE NR 4 BEARING. THE CAUSE OF THE NR 4 BEARING SPALLING IS UNDER INVESTIGATION BY PRATT AND WHITNEY CANADA. 2L72 4T4 TRTA24CE E26NE 19950623000441995062300044NE 1995 6 23 95ZZZX3042 219950221G7210310835601 SUN GEAR PWA PT6 PT6A67 52043NE POWER SECT TEETH MISSING B MASRK NONE O OTHER ININSP/MAINT 1 SW01 4756 UE004 114018 THE FIRST STAGE SUN GEAR WAS SPALLED AND SEVERAL GEAR WERE FOUND LIBERATED. INVESTIGATION IS LOOKING TOWARD ELECTROSTATIC DISCHARGE DUE TO THE SPALLING AND PAST HISTORY OF THE ENGINE AND PROPELLER COMBINATION. 4 T E26NE 19950623000481995062300048EA 1995 6 23 95ZZZX3046 219950410G7250310023601 SEAL RING PWA PT6 PT6A65B 52043EA HOT SECT EXCESS GAP B MASRK NONE W INADEQUATE Q C ININSP/MAINT 1 SW01 PARTS RECEIVED FROM PRATT AND WHITNEY AND WERE FOUND TO HAVE AN EXCESSIVE GAP 1,000. 4 T E4EA 19950623000491995062300049EA 1995 6 23 95ZZZX3047 219950515G73133005305 WASHER KEY PWA PT6 PT6A65B 52043EA GAS GENERATOR MISINSTALLED B MASRK NONE W INADEQUATE Q C ININSP/MAINT 1 SW01 RECEIVED FUEL NOZZLE SET FROM STOCK AND ONE KEY WASHER WAS FOUND TO BE IMPROPERLY INSTALLED. SET RETURNED TO OVERHAUL FACILITY REGIONAL AIRCRAFT SERVICES. 4 T E4EA 19950623000501995062300050NE 1995 6 23 95ZZZX3048 219950413G72103037767CL1 GEAR ASSY PWA PT6 PT6A67 52043NE POWER SECT GALLED B MASRK NONE W INADEQUATE Q C ININSP/MAINT 1 SW01 65C908 PART RECEIVED FROM STOCK AS NEW PART FROM PWC. PART SHOWS GAULING MARKS ON GEAR SIDEWALLS. PART RETURNED TO VENDOR. 4 T E26NE 19950623000511995062300051EA 1995 6 23 95ZZZX3049 219950417G72403035567 SEAL ASSY PWA PT6 PT6A65B 52043EA HOT SECT MISIDENTIFIED B MASRK NONE W INADEQUATE Q C ININSP/MAINT 1 SW01 50013 PART RECEIVED FROM STOCK AND WAS FOUND TO BE IMPROPERLY IDENTIFIED. PART IS A CL 5, BUT IS IDENTIFIED AS A CL 7. 4 T E4EA 19950623003271995062300327EA 1995 6 23 95ZZZX3085 219950511G74142G6394 MAGNETO BOSCH DOUG DC3 R4D8 3021474WP WRIGHTR1820 R182080 67020EA NR 2 ENGINE NR 1DEFECTIVE D K NONE O OTHER ININSP/MAINT 1 SW173906J 1200 43344 EXCESSIVE MAGNETO DROP ON RUN-UP. SUSPECT CAUSE INTERNAL MAG PROBLEM. DOUGLAS MANUAL RECOMMENDS NO FIELD WORK, JUST REPLACE AND SEND FOR OVERHAUL. 2L72 4R4 R 6A2 E259 19950623003331995062300333WP 1995 6 23 95ZZZX3091 219950314G72603070394 BRACKET ISRAEL1124 1124 4500102EU GARRTTTFE731TFE7313 01518WP ASSORY GEARBOX BROKEN B AXEFRK NONE O OTHER ININSP/MAINT 1 GL31420JM5217 193 P77130 WHILE COWL OPENED FOR NON-RELATED MAINTENANCE, NOTED INBOARD ACCESSORY GEARBOX TO FAN SUPPORT STRUT HANGING LOOSE DUE TO BROKEN MOUNTING EARS ON GEARBOX STRUT ROD ATTACH BRACKET. WHILE REPLACING BRACKET AND ADJUSTING PER TFE 731-3 L.M.M. 72-60-01, NOTED SLIGHT PRELOAD ON BRACKET AND ROD-END BEARING OF SHAFT REQUIRED TO INSTALL LOWER BOLT. LOOSENING FIT BY EXPANDING LOWER ROD-END ONE-HALF TURN PRODUCED A MUCH BETTER FIT WITH NO PRELOAD. SUBMITTER SUSPECTS SLIGHT PRELOAD STRESS OVER TIME CREATED FATIGUE. BELIEVE NEW PN 3070394-1 BRACKET MAY BE IMPROVED PART. 2M72 4F4 F A2SW E6WE 19950623006411995062300641NE 1995 6 23 HEEA955179 219950613G732125491281 FUEL CONTROL BOLKMS117 BK117B1 5626012EU LYC LTS101LTS101650B1 41560NE ENGINE DEFECTIVE E HEEAK NONE O OTHER NRNOT REPORTED 1 SW03217UC2405 7152 ENGINE HOT STARTS. REPLACED WITH SERVICEABLE FUEL CONTROL AND RETURNED AIRCRAFT TO SERVICE. 1G72 3U3 U H13EU E5NE 19950623006531995062300653GL 1995 6 23 HEEA955191 219950615G72506895801 WHEEL 23033185 BELL 206 206L1 1182107SW ALLSN 250C 250C28B 03013GL 1ST STAGE SULFIDATION E HEEAK NONE O OTHER ININSP/MAINT 1 SW0350182951 CAT70556 45242 CAE860771 ENGINE REMOVED DUE TO LOW POWER. UPON INSPECTION OF TURBINE PARTS NOTED THE FOLLOWING: SEVERLY SULFIDATED BLADE TIP ON #1 WHEEL CAUSING WHEEL AND NOZZLE CONTACT WITH TRAILING EDGE TIPS OF 8 EACH BLADES MISSING. SCRAPPED #1 WHEEL. 1G71 3U3 U H2SW E1GL 19950630000051995063000005SO 1995 6 30 95ZZZX3130 219950516G73146493683AIR PUMP PIPER PA34 PA34200T 7103406SO CONT O360 LTSIO360EB 17025SO RT ENG FUEL SEAL LEAK D O OTHER K FLUID LOSS CRCRUISE 1 GL0376PB 332 B119404BR 347970067 266445R ON 2-21-95, THE RIGHT ENGINE DEVELOPED A SURGE ON F.F. AND M.A.P. DURING CRUISE. AFTER TROUBLESHOOTING, DISCOVERED ANEROID SEAL HAD FAILED. THE PUMP WAS REPAIRED AND REINSTALLED (PART TT 257.5.) ON 5-16-95, THE SAME THING HAPPENED TO THE RIGHT ENGINE 62.6 HRS AFTER IT WAS REPAIRED. GENUINE T.C.M. PARTS WERE USED AND IT WAS REPAIRED BY A T.C.M. DEALER UNDER WARRANTY. NOTE: THE PUMPS T.B.O. IS 1800 HOURS. 1L72 3O3 O A7SO E9CE 19950630000091995063000009SO 1995 6 30 95ZZZX3134 219950419G8520 CRANKCASE BEECH 55 95B55 1152706CE CONT O470 IO470L 17026SO NR 4 CYLINDER CRACKED D K NONE O OTHER ININSP/MAINT 1 SO06213CH733 TC2298 272888R DURING INSPECTION, A .75 INCH CRACK WAS FOUND RADIATING UPWARD FROM THE AFT UPPER MOUNTING STUD FOR NR 4 CYLINDER. THE ENGINE HAD 732.9 HOURS SINCE BEING REBUILT BY THE FACTORY AND HAD BEEN IN SERVICE FOR 24 MONTHS. 1L72 3O3 O 3A16 3E1 19950630000121995063000012EA 1995 6 30 95ZZZX3137 219950605G7414M3637 CONTACT SLICK 4250R CESSNA172 172N 2072434CE LYC O360 O360A4A 41514EA MAGNETO POINTS CLOSED D K NONE O OTHER ININSP/MAINT 1 WP25734RA68 1010138 17269044 L1032136F A MISS ON ONE MAG CAUSED REMOVAL AND EXAMINATION OF THE MAG. THE POINT GAP WAS CLOSED DOWN AND THE POINTS WERE OF A TYPE NOT SEEN IN THIS SERIES MAG BEFORE. SINCE THEY HAD BEEN INSTALLED A SHORT TIME BEFORE, A CALL TO THE INSTALLING AGENCY WAS MADE. ACCORDING TO THEIR SLICK MANUAL, M3637 WAS CORRECT (1993). ACCORDING TO THE '94 (AND '89) MANUAL, M3081 WOULD BE CORRECT. A CALL TO SLICK VERIFIED THE MISTAKE IN THE 1993 MANUAL. 1H71 3O3 ONT3A12 E286 19950630000151995063000015EA 1995 6 30 95ZZZX3140 219950512G7414ES10382585 BREAKER POINT BENDIX 3FLN3000 MOONEYM20 M20C 5870208SW LYC O360 IO360A3B6 41514EA CAM FOLLOWER EXCESS WEAR BLADYTRK NONE O OTHER ININSP/MAINT 1 SO156079Q3 C090010G 3255 l2568151A DURING 100-HOUR PHASE INSPECTION, MAG WAS REPLACED WITH OVERHAULED UNIT. TWO AND ONE-HALF FLIGHT HOURS LATER, MAG FAILED. FOUND CAM FOLLOWER ON BOTH BREAKER POINTS EXCESSIVELY WORN. MAG TIMING OUT OF LIMITS. SUBMITTER SUGGESTS MFG CHANGE FROM PHENOLIC TO PLASTIC CAM FOLLOWER MATERIAL TO BE THE CONTRIBUTING FACTOR. 1L71 3O3 O 2A3 1E10 19950630000391995063000039NE 1995 6 30 95ZZZX3164 219950518G7200 ENGINE LEAR 23 23LEAR 5170102CE GE CJ610 CJ6104 30006NE LT ENGINE FLAME OUT C B EMER. DESCENT X ENGINE FLAMEOUT CLCLIMB 1 SO17154AG6814 3490 23034 LEFT ENGINE FLAMED OUT AT 40,900 FEET CLIMBING THROUGH BAD WEATHER. PILOT REQUEST DESCENT TO 10,000 FEET AND NEAREST AIRPORT. AIRCRAFT ENGINE RE-LIGHT PROCEDURES FOLLOWED, ENGINE RE-STARTED AT 20,000 FEET, AND NORMAL LANDING AT NEAREST AIRPORT. ENGINE INSPECTED FOR DAMAGE, NONE NOTED. GROUND RUNS PERFORMED ALL NORMAL. AIRCRAFT RETURNED TO SERVICE. ATTRIBUTE CAUSE TO POOR WEATHER, HEAVY TURBULENCE AND RAINS. 1L72 4J4 J A5CE 1E16 19950630003161995063000316EA 1995 6 30 95ZZZX3191 219950510G741410357584 DISTRIBUTOR GEAR S4LN20 PIPER PA28 PA28180 7102808SO LYC O360 O360A3A 41514EA MAGNETO LOOSE FINGER D K NONE ER VIBRATION/BUFFET PARTIAL RPM/PWR LOSS ININSP/MAINT 1 EA079521J 942448T 283739 ENGINE RAN ROUGH ON RIGHT MAG. DISASSEMBLED MAG AND FOUND TEETH ON DISTRIBUTOR GEAR MISSING AND LOOSE DISTRIBUTOR FINGER ELECTRODE. LOOSE ELECTRODE PROBABLY HIT STATIONARY ELECTRODE CAUSING TEETH TO BREAK. 1L71 3O3 O 2A13 E286 19950630003171995063000317SO 1995 6 30 95ZZZX3192 219950526G73146467661 PUMP BEECH 36 A36 1151604CE CONT O550 IO550* SO ENG FUEL DEFECTIVE D O OTHER ER VIBRATION/BUFFET PARTIAL RPM/PWR LOSS CRCRUISE 1 WP258180N198 E2606 281968R ENGINE RAN ROUGH AT ALTITUDE, AUTOMIX NOT WORKING. WOULD NOT AUTOLEAN. 1L71 3O3 O 3A15 E3SO 19950630003181995063000318CE 1995 6 30 95ZZZX3194 119950531G7603AN311 BOLT BEECH 33 F33A 1151425CE CONT O520 IO520BA 17032SO THROTTLE CONTROLBROKEN D A UNSCHED LANDING O OTHER CRCRUISE 1 GL0324184 CE765 569214 PILOT REPORTED NO THROTTLE CONTROL WHILE AT CRUISE POWER. AFTER LANDING, FOUND THROTTLE CONTROL DISCONNECTED FROM FUEL CONTROL ARM. BOLT WAS FOUND IN ENGINE COMPARTMENT BROKEN OFF AT THE COTTER PIN HOLE. 1L71 3O3 O 3A15 E5CE 19950630003271995063000327 1995 6 30 95ZZZX3203 119950519G792275944 VALVE LYC O360 O360* 41514EA THERMO BYPASS CRIMP NUT LOOSE D K NONE O OTHER ININSP/MAINT 1 GL21 ON C/W LYC SB 518C BY CHECKING FOR LOOSE CRIMP NUTS, HAVE INSPECTED 6 AND FOUND 4 LOOSE NUTS. 3 O E286 19950630003371995063000337SO 1995 6 30 95ZZZX3213 219950615G8530530658 BUSHING 632043 CESSNA421 421C 2076016CE CONT O520 GTSIO520L 17032SO PISTON PIN SPLIT B NT2RK NONE O OTHER ININSP/MAINT 1 CE07525RG903 421C0616 241062R FOUND NR 1 PISTON PIN ROD BUSHINGS CRACKED CIRCUMFERENCE WISE .3750 INCH AND SPLIT ABOUT .0312 INCH. FOUR OUT OF 6 BUSHINGS CRACKED. NR 2 CYLINDERS WERE REMOVED FOR LOW COMPRESSION AT ANNUAL. 1L72 3O3 O A7CE E7CE 19950630003401995063000340EA 1995 6 30 95ZZZX3216 219950501G8530 RING PIPER PA31 PA31350 7103110SO LYC O540 LTIO540J2BD 41533EA CYLINDER BROKEN D E ENGINE SHUTDOWN J WARNING INDICATION CRCRUISE 1 NM0727354 153 317752180 L222568A ENGINE SHUT DOWN IN-FLIGHT DUE TO LOSS OF OIL PRESSURE. INVESTIGATION REVEALED BROKEN COMPRESSION RINGS ON 1 CYLINDER AND SEVERELY WORN RINGS ON ANOTHER. THESE WERE NUCHROME CYLINDERS WITH 153.2 HOURS SINCE NEW. ENGINE OVERHAUL AGENCY INDICATED THEY HAVE SEEN THIS PROBLEM BEFORE AND ATTRIBUTE ITS CAUSE TO AN EXCESSIVELY LEAN MIXTURE CREATING HIGH HEAD TEMPERATURES. ENGINE HAS BEEN REPAIRED. 1L72 3O3 O A20SO E14EA 19950630003581995063000358NE 1995 6 30 95ZZZX3234 219950605G75322856201 BLEED VALVE SNIAS 350 AS350BA 8680817EU TMECA ARRIELARRIEL1 60030NE ENGINE INOP D A A UNSCHED LANDING K FLUID LOSS CRCRUISE 1 WP13269JM 1398 401 AIRCRAFT DEPARTED. ON ITS FIRST FLIGHT ABOUT 8:45, PILOT HEARD A BIG BANG COMING FROM THE ENGINE FOLLOWED BY POPPING SOUND AND LOSS OF POWER. THE PILOT WENT INTO EMERGENCY PROCEDURE. AS DECREASE OF POWER, ENGINE CAME BACK ON-LINE. THE PILOT MANAGED TO SET THE ACFT DOWN ON A PRIVATE PROPERTY. MECHANICS WERE SENT OUT AND FOUND BLEED VALVE INOP. REPLACED THE VALVE AND C/W RUN-UP AND OPS CHECK AND FOUND ACFT AND ENGINE SERVICEABLE. 1G71 3U3 UNCH9EU E19EU 19950630003771995063000377EA 1995 6 30 95ZZZX3239 219950518G853073806 PUSHROD CESSNA150 152 2071835CE LYC O235 O235L2C 41505EA CYLINDER TIP FAILED D K NONE O OTHER NRNOT REPORTED 1 SW115241Q 15285088 L2241915 PUSHROD TIP SEPARATION. SECOND FAILURE ON THIS ENGINE. TOTAL TIME 6696. ENGINE TSMOH 366. REMOVED PN 73806. REPLACED WITH NEW PUSHROD PN 73806, REV A. 1H71 3O3 ONT3A19 E223 19950630003851995063000385SO 1995 6 30 95ZZZX3247 219950612G8530643767 GUIDE CONT O520 IO520* 17032SO EXHAUST OUT OF LIMITS B YCTRK NONE W INADEQUATE Q C ININSP/MAINT 1 SW11 SIX EACH EXHAUST VALVE GUIDES DEFECTIVE OUT OF 6 EACH NEW TCM CYLINDERS. ALL GUIDES ARE OUT OF NEW LIMITS AND TAPERED FROM TOP TO BOTTOM. TOTAL OF 18 EXHAUST GUIDES, PN 643767, REPORTED OUT OF LIMITS BY SUBMITTER. 3 O E5CE 19950630003861995063000386NE 1995 6 30 95ZZZX3248 219950503G73233535196 DRIVE PIN WOODWARD 8061526 GE CFM56 CFM565A 13802NE HMU MISMANUFACTURED H K NONE W INADEQUATE Q C ININSP/MAINT 1 SW99 79445 INVESTIGATI0N OF 2 FIELD REJECTS (DUE TO OVERSPEED GOV FAULT INDICATIONS). MFG FND CARBIDE WEAR PAD OF GOV DRIVE PIN ASSY IMPROPERLY POSITIONED WHEN BRAZED IN PLACE. INVESTIGATION FOCUSED UPON 1 MFG LOT. THESE CONDITIONS RESULT IN WEAR WHICH CAUSES A SHIFT IN OVERSPEED GOV SET POINT (IN REDUCED SPEED DIRECTION). THIS IS NOT BELIEVED TO BE A SAFETY CONCERN BECAUSE OF FAULT INDICATING LOGIC WHICH WILL PRECEDE ANY OPERATING PROBLEMS. WOODWARD & GEAE ARE COORDINATING ADVISABILITY OF SB TO INFORM FIELD OF CONDITION & RECOMMEND CHECK/REPLACE INTERVAL IN ORDER TO PREVENT POSSIBLE UNSCHEDULED REMOVAL. AFFECTED S/NS: WYG 79269-79270, WYG 79272-79290, WYG 79374-79382, WYG 79436-79443, WYG 79445, WYG 84161-84162. 4 F E29NE 19950630003961995063000396EA 1995 6 30 95ZZZX3258 219950602G732225244919 SERVO PIPER PA60 PA60600 7106001NM LYC O540 IO540K1J5 41532EA FUEL INJ LT DEFECTIVE B BSYRK NONE R PARTIAL RPM/PWR LOSS ININSP/MAINT 1 GL078090J 600576796118L646648A LEFT ENGINE WILL NOT PRODUCE POWER. REMOVED AND REPLACED FUEL SERVO. OPS CHECKED GOOD. 1M72 3O3 ORTA17WE 1E4 19950630004021995063000402SO 1995 6 30 95ZZZX3264 219950612G73146462121A5 FUEL PUMP CESSNA185 A185F 2072821CE CONT O520 IO520D 17032SO ENGINE DEFECTIVE D K NONE ER VIBRATION/BUFFET PARTIAL RPM/PWR LOSS ININSP/MAINT 1 NE054446C536 C319410BR 18504338 293028R AIRCRAFT EXPERIENCED INTERMITTENT ROUGHNESS. FUEL PRESSURE CHECK SHOWED FLUCTUATING FUEL PRESSURE. REPLACED PUMP, ENGINE RAN SMOOTH WITH NO FLUCTUATION OF FUEL PRESSURE. 1H71 3O3 O 3A24 E5CE 19950630004031995063000403SO 1995 6 30 95ZZZX3265 219950607G8530 CYLINDER CESSNA150 150 2071802CE CONT O200 O200A 17020SO NR 4 CYL ROCKER BOSS BROKEN D K NONE ER VIBRATION/BUFFET PARTIAL RPM/PWR LOSS ININSP/MAINT 1 NE0566386 1283 150760101 31612A PILOT COMPLAINED OF ROUGH RUNNING ENGINE. UPON INVESTIGATION, FOUND NR 4 CYLINDER ROCKER SHAFT BOSSES (3 EACH) BROKEN OFF. CYLINDER HAD ONLY 1283 HOURS SINCE OVERHAUL. SEE AD 94-05-05. 1H71 3O3 ONT3A19 E252 19950630005961995063000596EA 1995 6 30 95ZZZX3270 219950612G8530 VALVE GUIDE PIPER PA32 PA32301T 7103209SO LYC O540 TIO540S1AD 41532EA EXHAUST EXCESS WEAR D K NONE O OTHER ININSP/MAINT 1 EA038317Y873 328124005 L751761A C/W INSPECTION ITEM NR 9. REMOVAL OF ROCKER BOX COVERS EA400 HOURS AND FOUND EXCESSIVE EXHAUST DEPOSITS ON AND AROUND VALVE SPRINGS. C/W LYC SB 388B. EXHAUST VALVE GUIDE WEAR TO BE VERY EXCESSIVE .050 INCH PLUS ON FIVE OF THE SIX CYLINDERS, 837.00 HOURS SINCE NEW. SUBMITTER SUGGESTS VALVE FAILURE WAS IMMINENT WHICH COULD CAUSE TOTAL LOSS OF POWER. 1L71 3O3 O A3SO E14EA 19950630006091995063000609SO 1995 6 30 95ZZZX3283 219950619G8530534398 ROCKER ARM CESSNA414 414 2075908CE CONT O520 TSIO520J 17040SO LT ENG CYLS WORN B MJ7RK NONE O OTHER ININSP/MAINT 1 GL0513MN 1400 4140422 218655R ROCKER ARM BEARING WORN BEYOND LIMITS. SUSPECT DUE TO AGE AND OIL STARVATION TO THIS PART. 1L72 3O3 ORTA7CE E8CE 19950707000251995070700025NE 1995 7 7 95ZZZX3312 219950614G8500 ENGINE DOUG DC3 DC3A 3021433WP PWA R1830 R183090D 52020NE NR 2 MAKING METAL C RPFBK NONE O OTHER NRNOT REPORTED 1 SW1732MS 1183 473 4978 CP350411 OIL TEMP HIGHER THAN NORMAL ON TRAINING FLIGHT. FOUND SMALL AMOUNT OF METAL IN OIL SCREEN. ENGINE REMOVED FOR REPAIR 6-13-95. 2L72 4R4 R A669 5E4 19950707002681995070700268EA 1995 7 7 95ZZZY0717 219950405G7200 ENGINE BELL 212 212 1181420SW PWA PT6T PT6T3 52045EA CONTROL SYS MALFUNCTION H CZ4RK NONE O OTHER ININSP/MAINT 1 FS0124HL 30815 ENGINE HAD UNCONTROLLED ACCELERATION FROM IDLE. RPM OF NF REACHED 110% BEFORE MANUAL GOVERNOR WAS ENGAGED AND ENGINE SECURED. INVESTIGATION REVEALED NO LOOSE LINES, NO LINES WITH ICE, AND AFCU DRIVESHAFT WAS SERVICABLE. ENGINE WAS REMOVED AND RETURNED TO PRATT & WHITNEY FOR EVALUATION AND REPAIR. 1G71 4U4 U H4SW E22EA 19950707002731995070700273EU 1995 7 7 95ZZZY0722 119950405G7931IPT70RT11000250GTRANSDUCER BOLKMS117 BK117A3 5626015EU LYC LTS101LTS101650B1 41560NE ENG OIL DEFECTIVE H R7MAK NONE O OTHER ININSP/MAINT 1 FS01202HN183 7115 LE45071 PRESSURE TRANSDUCER UNIT CAUSES PRESSURE FLUCTUATION. REPLACED WITH NEW UNIT(S) CORRECTED PROBLEM. 1G72 3U3 U H13EU E5NE 19950707002751995070700275EU 1995 7 7 95ZZZY0725 119950405G7931IPT70RT11000250GTRANSDUCER BOLKMS117 BK117B1 5626012EU LYC LTS101LTS101750B1 41560NE ENG OIL DEFECTIVE H R7MAK NONE O OTHER ININSP/MAINT 1 FS01911VU101 7141 LE45582 #2 OIL PRESSURE GAUGE FLUCTUATES. REPLACED WITH NEW UNIT CORRECTED PROBLEM. 1G72 3U3 U H13EU E5NE10 19950707002821995070700282NE 1995 7 7 95ZZZY0759 219950426G7250430136201 BEARING BOLKMS117 BK117B1 5626012EU LYC LTS101LTS101750B1 41560NE ENGINE FAULTY H R7MAK NONE W INADEQUATE Q C ININSP/MAINT 1 FS017059N66 7154 LE45518E THIS BEARING IS AFFECTED BY SB LT101-72-10-0151. ALLIED SIGNAL PARTS FACILITY FAILED TO ISOLATE AND DISCARD THIS BEARING. SUBSQUENTLY, ALLIED SIGNAL SHIPPED THE BEARING TO RMH. ALLIEDSIGNAL ADVISED RMH OF ERROR. THE AIRCRAFT WAS GROUNDED AND THE ENGINE REMOVED. 1G72 3U3 U H13EU E5NE10 19950707003401995070700340NE 1995 7 7 95ZZZY1001 219950510G7250414129001 PT ROTOR BOLKMS117 BK117A4 5626017EU LYC LTS101LTS101650B1 41560NE ENGINE BLADE SHIFT H R7MAK NONE O OTHER ININSP/MAINT 1 FS01127HH1231 7060 LE45244E FAILED SERVICE BULLETIN LT 101-72-10-0153. EXCESSIVE IBPT BLADE SHIFT. #12 +0.012". REPLACED WITH NEW UNIT(S), CORRECTED PROBLEM. 1G72 3U3 U H13EU E5NE 19950707003411995070700341NE 1995 7 7 95ZZZY1002 219950510G7250414129001 PT ROTOR BOLKMS117 BK117A3 5626015EU LYC LTS101LTS101650B1 41560NE ENGINE BLADE SHIFT H R7MAK NONE O OTHER ININSP/MAINT 1 FS01117MA1076 7107 LE45155E FAILED SERVICE BULLETIN LT 101-72-10-0153. EXCESSIVE IBPT BLADE SHIFT. #4-0.0145". REPLACED WITH NEW UNIT(S), CORRECTED PROBLEM. 1G72 3U3 U H13EU E5NE 19950707003421995070700342NE 1995 7 7 95ZZZY1003 219950510G7250411105056 ROTOR ASSY BOLKMS117 BK117B1 5626012EU LYC LTS101LTS101750B1 41560NE GAS PRODUCER DEFECTIVE H R7MAK NONE O OTHER ININSP/MAINT 1 FS017059N1817 7154 LE45752 DUE SERVICE BULLETIN LT 101-72-10-0150. REQUIRES DISASSEMBLY AND INSPECTION OF ROTOR BROACH SLOTS FOR POSSIBLE CRACKS IN THE DISC/TENON AREA. LAB SEAL ENCLOSED WITH ROTOR. REPLACED WITH NEW UNIT(S), CORRECTED PROBLEM. 1G72 3U3 U H13EU E5NE10 19950707003451995070700345GL 1995 7 7 95ZZZY1458 219950612G732323007505 GOVENOR ALLSN 250C 250C20B 03013GL ENGINE DEFECTIVE H XH3RK NONE O OTHER ININSP/MAINT 1 FS01 NG SPLIT. FOUND GOV FAULTY 3 U E4CE 19950707003511995070700351NE 1995 7 7 EKGA9520836 219950505G73210164448080 FUEL CONTROL SNIAS 350 AS350B 8680801EU TMECA ARRIELARRIEL1B 6OO30NE ENGINE DEFECTIVE E EKGAK NONE O OTHER ININSP/MAINT 1 WP07123TV2057 1682 4045 FCU WILL NOT PRODUCE MINIMUM ROTOR RPM. 1G71 3U3 U H9EU E19EU 19950707003611995070700361NE 1995 7 7 RMXA9520533 219950326G7313411101007 NOZZLE ASSY BOLKMS117 BK117B1 5626012EU LYC LTS101LTS101750B1 41560NE GAS PRODUCER CRACKED E RMXAK NONE R PARTIAL RPM/PWR LOSS ININSP/MAINT 1 SW05117VU578 7211 LE45528E UPON INSPECTION OF ENGINE ASSEMBLY FOR CAUSE OF LOW POWER (-86%) THE G.P. NOZZLE WAS FOUND TO HAVE A LARGE CIRCUMFERENTIAL CRACK ON THE INNER SHROUD TO VANE ASSY. WELD (81/2" CRACK) CIRCUMFERENCE OF INNER SHROUD IS APPROXIMATELY 19". REPLACED NOZZLE. 1G72 3U3 U H13EU E5NE10 19950707003721995070700372GL 1995 7 7 RMXA9520553 219950326G72506895021 1ST NOZZLE ALLSN 250C 250C20B 03013GL ENGINE DEFECTIVE E RMXAK NONE W INADEQUATE Q C ININSP/MAINT 1 SW05 DIAPHRAM IMPROPERLY INSTALLED, BOLT HOLES WOULD NOT LINE UP. 3 U E4CE 19950707006051995070700605EA 1995 7 7 95ZZZX3315 219950428G7414 MAGNETO BENDIX 6050880 BEECH B80 B80 1153010CE LYC O540 IGSO540A1D 41532EA LT ENG LT MAG POINTS GROUNDED D K NONE O OTHER ININSP/MAINT 1 CE0565RW 2224 924 LD404 L256450 ON THE THIRD FLIGHT OF THE DAY, THE LEFT ENGINE FAILED TO START. THE CAP WAS REMOVED FROM THE MAG AND MOISTURE WAS FOUND WHICH WAS GROUNDING THE VIBRATOR POINTS. MAG WAS DRYED OUT. OPS CHECK OK. 1L72 3O3 ORT3A20 1E7 19950707006181995070700618EA 1995 7 7 95ZZZX3328 219950406G73222539449 ADJUSTING NUT BENDIX 252427311 CESSNA188 A188B 2073005CE LYC O540 IO540K1G5 41532EA SERVO BALL STEM MISSING B JK2RK NONE O OTHER ININSP/MAINT 1 GL074854R 31705 18802373T L1880848A INJECTOR ARRIVED WITH NO FUEL FLOW. UPON PUTTING IT ON FLOW BENCH USING NORMAL FLOW PROCEDURES, WAS UNABLE TO GET FUEL FLOW. REMOVED HEX BRASS NUT FROM REGULATOR. THE RETAINING AND FLOW ADJUSTING NUT WAS MISSING. RECOMMEND ALL FLOW BENCH OPERATORS SHOULD BE CAUTIONED ABOUT C/W SB RS-71, LOCTITE THE ADJUSTING NUT. 1L71 3O3 O A9CE 1E4 19950707006191995070700619NE 1995 7 7 95ZZZX3329 219950502G7250411105064 ROTOR LYC LTS101LTS101650C3 41560NE GP ROTOR BLADES CRACKED B E5RRK NONE O OTHER ININSP/MAINT 1 SO13 202 LE41115 DURING INSPECTION PER SB LT101-72-50-0150, SEVERAL BLADES FOUND TO HAVE INDICATION OF CRACKS DURING FPI. CRACKS WERE IN THE BLADE ROOT AREA. INVESTIGATION IS ON-GOING. 3 U E5NE 19950714001321995071400132GL 1995 7 14 95ZZZX3334 219950608G732123057344 FUEL CONTROL HUGHES369 369D 4470706WP ALLSN 250C 250C20B 03013GL ENGINE MALFUNCTION B EOORK NONE O OTHER ININSP/MAINT 1 AL035313Y 66 490496D CAE831718 AIRCRAFT HUNG-START AT 30 PERCENT - ALL SUBSEQUENT ADJUSTMENT HAD LITTLE OR NEGATIVE EFFECT ON THE FUEL SCHEDULING. REMOVED AND REPLACED UNIT AND AIRCRAFT STARTS NOW. UNIT SENT IN FOR OVERHAUL. 1G71 3U3 U H3WE E4CE 19950714001341995071400134GL 1995 7 14 95ZZZX3336 219950512G72506876667 AIR TUBE BOLKMS105 BO105CBS 5626008EU ALLSN 250C 250C20 03013GL NR 1 ENGINE HOLE CHAFED E A UNSCHED LANDING Y ENGINE STOPPAGE CRCRUISE 1 SW0354197 1663 CAT37782 S805 CAE802035F IN CRUISE FLIGHT, PILOT EXPERIENCED AN ENGINE TORQUE SPLIT, NR 1 ENGINE DROPPING OFF-LINE. LANDED ON OFFSHORE PLATFORM WITHOUT INCIDENT. FOUND HOLE CHAFED IN AIR TRANSFER TUBE, WITH ASSOCIATED CRACKS. ALLISON IPC, CHAPTERS 2-60, FIGURE 13, ITEM 24. 1G72 3U3 UNCH3EU E4CE 19950714001351995071400135GL 1995 7 14 95ZZZX3337 219950531G72616895096 FILTER CAP 23035179 SKRSKYS76 S76A 8143006NE ALLSN 250C 250C30S 03013GL GEAR BOX OIL BROKEN E EA ENGINE SHUTDOWN UNSCHED LANDING BJ SMOKE/FUMES/ODORS/SPARKS WARNING INDICATION CRCRUISE 1 SW031546K CAG90620 760082 CAE890616S ON 5-31-95 AT 1700, PILOT REPORTED NR 2 ENGINE LOW PRESSURE LIGHT ON. OIL PRESSURE LOW. SMELL OF OIL IN CABIN. SHUT DOWN ENGINE. SINGLE ENGINE LANDING MADE IN HOUMA. FOUND EAR ON ENGINE OIL FILTER CAP BROKEN, O-RING CUT. MINIMUM OIL PRESSURE BEFORE ENGINE SHUT DOWN, 50 PSI. S-76 IPC, FIGURE 9, SECTION 72-60-00, ITEM 4. 1G72 3U3 U H1NE E1GL 19950714001701995071400170GL 1995 7 14 95ZZZX3373 219950525G725023035262 ROLLER BEARING 23051643 SKRSKYS76 S76A 8143006NE ALLSN 250C 250C30S 03013GL COMPRESSOR NR 1 FAILED B ALGRK NONE O OTHER ININSP/MAINT 1 SW03708AL1965 244 MP00558 760277 CAE890775S REPORTED LOUD GRINDING NOISE ON SHUT DOWN. COMPRESSOR WAS DISASSEMBLED DUE TO IMPELLER DRAGGING ON SHROUD AND FOUND NR 1 ROLLER BEARING HAD FAILED. UPON DISASSEMBLY, FOUND SEPARATE CAGE FOR ROLLERS BROKEN. APPROXIMATELY 80 DEGREES OF SEPARATOR CAGE BROKEN OFF. FOUND 2 EACH ROLLERS AND PARTS FROM SEPARATOR CAGE LAYING ON TOP OF BEARING INSIDE OF NR 1 BEARING HOUSING. 1G72 3U3 U H1NE E1GL 19950728002171995072800217CE 1995 7 28 95ZZZX3470 119950601G81204066105 TURBOCHARGER AIRESRCH CESSNA210 T210N 2073456CE CONT O520 TSIO520R 17040SO BEARINGS FAILED B BTSRA UNSCHED LANDING R PARTIAL RPM/PWR LOSS CLCLIMB 1 GL235244A357 TJR6449 21063324 517272 FOLLOWING DEPARTURE FROM AIRPORT WHILE IN A CRUISE CLIMB AT 8,500 FEET MSL, THE AIRCRAFT'S ENGINE LOST POWER, THEN SURGED. AN IMMEDIATE RETURN TO AIRPORT WAS MADE AND ON THE DESCENT, THE ENGINE WAS INTERMITTENTLY SURGING. MANIFOLD PRESSURE VARIATIONS FROM 18 INCHES UP TO 27 INCHES DURING POWER SURGES. PART OF THE TIME ENGINE WOULD RUN SMOOTHLY. LANDED WITHOUT INCIDENT WITH SURGING POWER OUTPUT. 1H71 3O3 O 3A21 E8CE 19950728002211995072800221SO 1995 7 28 95ZZZX3474 219950620G8550 ADAPTER CESSNA207 T207A 2073614CE CONT O520 TSIO520M 17040SO OIL PUMP THREAD DAMAGE D K NONE O OTHER ININSP/MAINT 1 WP079629M1394 20700712 520424 DURING COMPLIANCE WITH SEB 92-1R1 (CESSNA). ADAPTER WAS REMOVED FROM PUMP HOUSING AND THREAD DAMAGE WAS EVIDENT. 3OX MAGNIFICATION OF DAMAGE APPEARED TO BE A MANUFACTURING DEFECT. NO DAMAGE DUE TO MISUSE IS SUSPECTED. SEB 93-1R1 IS TO CHECK THREAD DAMAGE DUE TO IMPROPER TORQUE AND SUBSEQUENT LOOSENESS. THIS CONDITION DID NOT EXIST AND SEB 93-1R1 DOES NOT APPLY TO THIS AIRCRAFT BY SERIAL NUMBER, HOWEVER, ENGINE AND PART IN QUESTION ARE SAME AS SERIAL NUMBER AIRCRAFT IN EFFECTIVITY CLAUSE. 1H71 3O3 O A16CE E8CE 19950728002271995072800227EA 1995 7 28 95ZZZX3480 219950606G7322CF2541803 DIAPHRAGM STEM BENDIX RSA10ED1 LYC O540 IO540K1A5 41532EA FUEL SERVO FAILED B PB4RA UNSCHED LANDING Y ENGINE STOPPAGE NRNOT REPORTED 1 SO13 59361 ENGINE FAILURE CAUSING FORCED LANDING. FUEL DIAPHRAGM STEM FAILED (PN CF2541803). BROKE AT BALL SWAGE AREA INTERRUPTING FUEL FROM SERVO TO ENGINE. 3 O 1E4 19950728002351995072800235GL 1995 7 28 HEEA955222 219950626G72506895801 WHEEL 23031899 BELL 206 206L1 1182107SW ALLSN 250C 250C28B 03013GL 1ST STAGE SULFIDATION E HEEAK NONE O OTHER ININSP/MAINT 1 SW035745S1494 CAT70036 45491 CAE860022 ENGINE REMOVED DUE TO TURBINE OVERHAUL. UPON INSPECTION OF TURBINE PARTS NOTED THE FOLLOWING: MINOR SULFIDATION ON ALL BLADES. SCRAPPED 1ST STAGE WHEEL. 1G71 3U3 U H2SW E1GL 19950728002361995072800236GL 1995 7 28 HEEA955223 219950626G725023032280 WHEEL 23035128 SKRSKYS76 S76A 8143006NE ALLSN 250C 250C30S 03013GL 2ND STAGE SULFIDATION E HEEAK NONE O OTHER ININSP/MAINT 1 SW031545K1685 CAT95464 760047 CAE890643 ENGINE DISASSEMBLED DUE TO TURBINE OVERHAUL. UPON INSPECTION OF TURBINE PARTS NOTED THE FOLLOWING: MINOR SULFIDATION ON OUTER TIP PATH AREAS OF ALL BLADES. SCRAPPED 2ND STAGE WHEEL. 1G72 3U3 U H1NE E1GL 19950728002371995072800237GL 1995 7 28 HEEA955224 219950626G72506898911 WHEEL 23035128 SKRSKYS76 S76A 8143006NE ALLSN 250C 250C30S 03013GL 1ST STAGE SULFIDATION E HEEAK NONE O OTHER ININSP/MAINT 1 SW031545K1685 CAT95464 760047 CAE890643 ENGINE DISASSEMBLED DUE TO TURBINE OVERHAUL. UPON INSPECTION OF TURBINE PARTS NOTED THE FOLLOWING: MINOR SULFIDATION ON ALL 1ST STAGE WHEEL BLADES. SCRAPPED 1ST STAGE WHEEL. 1G72 3U3 U H1NE E1GL 19950728002911995072800291GL 1995 7 28 HEEA955283 219950629G725023038212 INTERNAL SUMP 23033185 BELL 206 206L1 1182107SW ALLSN 250C 250C28B 03013GL ENG N2 SEAL DEFECTIVE E HEEAK NONE O OTHER ININSP/MAINT 1 SW035737T CAT70180 45454 CAE860136 ENGINE REMOVED DUE TO N2 SEIZURE. UPON INSPECTION OF TURBINE PARTS NOTED THE FOLLOWING: 50% OF GRAPHITE LIFTING IN INTERNAL SUMP 9/12 SEAL, CAUSING N2 SEIZURE. 1G71 3U3 U H2SW E1GL 19950728003481995072800348CE 1995 7 28 TEIL952 119950505G2910124D0036SL0226 HOSE ASSY CESSNA500 560CESSNA 2076750CE PWA JT15 JT15D5 52112NE RT HYD FAILED H TEILK NONE KJ FLUID LOSS WARNING INDICATION LDLANDING 1 SW09502T 2583 5600153 108316 DURING APPROACH AND LANDING AT SAT, AS LANDING GEAR WAS EXTENDED, HYDRAULIC LOW FLOW (RH) AND HYDRAULIC LOW LEVEL LIGHTS ILLUMINATED. INSPECTION ON THE GROUND AT SAT BY LOCAL MAINTENANCE PERSONNEL DETERMINED THE RH HYDRAULIC PUMP PRESSURE LINE HAD FAILED AND WAS LEAKING FLUID. REPLACEMENT LINE WAS ORDERED AND SHIPPED TO SAT MAINTENANCE PERSONNEL FROM CESSNA AIRCRAFT AT ICT. LINE WAS REPLACED, SYSTEMS SERVICED, AND GROUND RUNS ACCOMPLISHED. HYDRAULIC PRESSURE FILTERS WERE INSPECTED FOR METAL CONTAMINATION AND NONE FOUND. SYSTEM BLED AND AIRCRAFT RETURNED TO SERVICE. 2L72 4F4 FRTA22CE E25EA 19950728003491995072800349GL 1995 7 28 TEIL953 219950508G732310560590 LEVER ASSY BOLKMS105 BO105CBS 5626008EU ALLSN 250C 250C20B 03013GL GOV DEFECTIVE H TEILK NONE W INADEQUATE Q C ININSP/MAINT 1 SW09 GOVENOR ATTACH BEARING WILL NOT GO ON SLEEVE. MIC DIMENSION OF BEARING SHAFT 6.016 MM. NEW PART SECURED AND INSTALLED. NEW PART SHAFT DIMENSION 5.9 MM. 1G72 3U3 UNCH3EU E4CE 19950728003521995072800352NE 1995 7 28 95ZZZX3488 219950626G7414SF14LN3 MAGNETO BENDIX DOUG DC3 DC3 3021401WP PWA R1830 R183092 52020NE RT ENG RT MAG LOOSE D E ENGINE SHUTDOWN ER VIBRATION/BUFFET PARTIAL RPM/PWR LOSS CRCRUISE 1 SW1124320 028394 20197 CP313794 RIGHT ENGINE STARTED RUNNING ROUGH IN-FLIGHT. ENGINE SHUT DOWN AND FEATHERED. FOUND RIGHT MAG HAS COME LOOSE. RE-TIMED AND TORQUED RIGHT MAG. OPS CHECKED SATISFACTORY. 2L72 4R4 R A669 5E4 19950728003561995072800356SO 1995 7 28 95ZZZX3492 119950618G812007A19870 BRACKET PIPER PA46 PA46350P SO LYC O540 TIO540AE2A 41532EA LT TURBOMOUNT BROKEN D K NONE O OTHER ININSP/MAINT 1 GL1961FL 1110 4622037 L897161A LEFT TURBOMOUNT BRACKET BROKE AT SUMP ATTACH POINT. THIS BRACKET SUPPORTS THE TURBOCHARGER. 1L71 3O3 ORTA25SO E14EA 19950728003581995072800358EA 1995 7 28 95ZZZX3494 219950628G853015F1995736 PUSH ROD LYC O360 IO360A3B6 41514EA ENGINE CORRODED B IBIRK NONE W INADEQUATE Q C ININSP/MAINT 1 EA27 RECEIVED 3 EACH PUSH ROD ASSEMBLIES FROM DISTRIBUTOR. PUSH ROD ASSEMBLY HAS EXCESSIVE WEATHERING CORROSION AND PITTING ON THE OUTER SURFACE ON THE RODS. REFERENCED TO THE VENDOR FOR INSPECTION AND DISPATCH. ROD ASSEMBLIES WERE NOT PRESERVED IN ANY TYPE OF ANTI-CORROSION PACKING. 3 O 1E10 19950728003681995072800368SO 1995 7 28 95ZZZX3504 219950524G8530630046 PISTON PIN BEECH 58 58 1152740CE CONT O550 IO550C SO NR 5 CYLINDER FRACTURED DS K NONE O OTHER ININSP/MAINT 1 EA0191WM 1314 TH1396 676056H WHEN REMOVING NR 2 AND NR 5 CYLINDERS TO CORRECT LOW COMPRESSION (LEAKING PAST RINGS), BOTH PISTON PINS WERE FOUND BROKEN IN TWO. 1L72 3O3 O 3A16 E3SO 19950728003721995072800372SO 1995 7 28 95ZZZX3508 219950711G8530SA6291171 ROTOR COIL CONT O470 O470* 17026SO NR 6 CYL EXH FAILED B YCTRK NONE O OTHER ININSP/MAINT 1 SW11 34 462596 SUPERIOR AIR PARTS VALVE ROTOR FAILED. NR 6 CYLINDER EXHAUST VALVE POSITION CAUSING ENGINE METAL CONTAMINATION. 3 O E273 19950728003731995072800373SO 1995 7 28 95ZZZX3509 219950711G8530SA6291171 ROTOR COIL CONT O470 O470* 17026SO NR 2 CYL EXH FAILED B YCTRK NONE O OTHER ININSP/MAINT 1 SW11 34 462596 SUPERIOR AIR PARTS VALVE ROTOR FAILED. NR 2 CYLINDER EXHAUST VALVE POSITION CAUSING ENGINE METAL CONTAMINATION. 3 O E273 19950728003741995072800374EA 1995 7 28 95ZZZX3510 219950612G73106390107 HOSE ASSY PIPER PA28 PA28140 7102802SO LYC O320 O320E2A 41508EA ENGINE CARB BROKE D K NONE O OTHER ININSP/MAINT 1 GL09432243207 287425346 AT ANNUAL, NOTED ENGINE HOSES DATED 1974. UPON REMOVAL OF FUEL PRESSURE LINE FOR REPLACEMENT, FLEX HOSE BROKE NEAR SOCKET. HOSE WAS VERY BRITTLE AND INNER LINER WAS CRACKED. SUBMITTER RECOMMENDED AD TO ESTABLISH LIFE LIMIT ON FLEXIBLE HOSES AT 5 YEARS OR ENGINE OVERHAUL, WHICHEVER COMES FIRST. 1L71 3O3 O 2A13 E274 19950728003801995072800380SO 1995 7 28 95ZZZX3516 219950711G8530SA6291171 ROTOR COIL CONT O520 IO520BA 17032SO NR 3 CYL EXH BROKEN B YCTRK NONE O OTHER ININSP/MAINT 1 SW11 560 232563R SUPERIOR AIR PARTS VALVE ROTOR FAILED. NR 3 CYLINDER EXHAUST VALVE POSITION CAUSING ENGINE METAL CONTAMINATION. 3 O E5CE 19950728003811995072800381SO 1995 7 28 95ZZZX3517 219950711G8530SA6291171 ROTOR COIL CONT O470 O470* 17026SO NR 3 CYL EXH FAILED B YCTRK NONE O OTHER ININSP/MAINT 1 SW11 34 462596 SUPERIOR AIR PARTS VALVE ROTOR FAILED. NR 3 CYLINDER EXHAUST VALVE POSITION CAUSING ENGINE METAL CONTAMINATION. 3 O E273 19950728003821995072800382SO 1995 7 28 95ZZZX3518 219950711G8530SA6291171 ROTOR COIL CONT O520 IO520BA 17032SO NR 5 CYL EXH BROKEN B YCTRK NONE O OTHER ININSP/MAINT 1 SW11 560 232563R SUPERIOR AIR PARTS VALVE ROTOR FAILED. NR 5 CYLINDER EXHAUST VALVE POSITION CAUSING ENGINE METAL CONTAMINATION. 3 O E5CE 19950728003901995072800390SO 1995 7 28 95ZZZX3526 219950524G8550CH48108 OIL FILTER BEECH 58 58 1152740CE CONT O550 IO550C SO SEAL DEFECTIVE DS K NONE W INADEQUATE Q C ININSP/MAINT 1 EA0191WM 65 F11D301 TH1396 676056H RUBBER SEAL FOUND PROTRUDING FROM CENTER HOLE WHEN FILTER WAS REMOVED: 1L72 3O3 O 3A16 E3SO 19950728003921995072800392EA 1995 7 28 95ZZZX3528 219950705G7322 PUMP BENDIX PIPER PA24 PA24260 7102406SO LYC O540 IO540D4A5 41532EA INJ PUMP DAUBER FOD D K NONE O OTHER ININSP/MAINT 1 SO119155P 244641 ON 100-HOUR INSPECTION, DISCOVERED LARGE MUDDAUBERS' NESTS IN THE INLET TO THE FUEL INJECTION PUMP. THIS WEBCO KIT WAS INSTALLED IN RESPONSE TO AN AD NOTE FOR AN ALTERNATE ENGINE INLET AIR SOURCE. (CARBURETOR HEAT BOX TYPE DEVICE). THIS AREA IS AFTER THE AIR INTAKE FILTER AND CANNOT BE DISCOVERED ON PRE-FLIGHT. 1L71 3O3 O 1A15 1E4 19950804000011995080400001GL 1995 8 4 HEEA955336 219950710G73201564T1005 SERVOMOTOR BOLKMS105 BO105S 5626006EU ALLSN 250C 250C20B 03013GL ENG CONTROL TRIPS BREAKER E HEEAK NONE O OTHER ININSP/MAINT 1 SW033071K1395 S859 POPS CIRCUIT BREAKER. INSPECTED BY ACCESSORY OVERHAUL SHOP AND FOUND MOTOR HAS INTERMITTENT OPERATION. 1G72 3U3 U H3EU E4CE 19950804001251995080400125NE 1995 8 4 EGRA95101 219950612G74129580113800 GENERATOR ARRIEL1C2 AEROSPSA365 AS365N2 8680815EU TMECA ARRIELARRIEL1C 60030NE ENGINE INOP E EGRAK NONE O OTHER ININSP/MAINT 1 EA17272NE281 12105 6435 HE GENERATOR INOPERATIVE . REPLACED 1G72 3U3 URTH10EU E19EU 19950804001501995080400150GL 1995 8 4 EGRA9524 219950410G732125490922 FUEL CONTROL 250C30P BELL 206 206L 1181522SW ALLSN 250C 250C20B 03013GL ENGINE MALFUNCTION E EGRAO OTHER O OTHER TOTAKEOFF 1 EA17209PD277 895752 52075 FUEL CONTROL REQUIRES INTERNAL ADJUSTMENT TO START DERICH AND ACCEL. FUEL CONTROL SENT TO AIRWORK FOR REPAIR. UNIT REPAIRED BY AIRWORK UNDER WORK ORDER # V04689. UNIT RETURNED TO KEYSTONE AND PERFORMED OPERATIONAL CHECKS. OP CHECKED GOOD. 1G71 3U3 U H2SW E4CE 19950804001791995080400179NE 1995 8 4 EGRA9557 219950427G7421CH34016 IGNITER PLUG BOLKMS117 BK117A3 5626015EU LYC LTS101LTS101650B1 41560NE ENGINE DEFECTIVE E EGRAK NONE O OTHER ININSP/MAINT 1 EA17116MB2163 7095 ENGINE IGNITER PLUG INOPERATIVE. 1G72 3U3 U H13EU E5NE 19950804002461995080400246GL 1995 8 4 HEEA955378 219950720G753223053176 BLEED VALVE AEROSPAS355 AS355F1 8680810EU ALLSN 250C 250C20F 03013GL ENGINE DEFECTIVE E HEEAK NONE O OTHER NRNOT REPORTED 1 SW035793Y6481 5141 #1 ENGINE COMPRESSOR SURGES WITH THROTTLE APPLICATION. REPLACED BLEED VALVE AND RETURNED TO SERVICE. 1G72 3U3 U H11EU E4CE 19950804005151995080400515GL 1995 8 4 HEEA955480 219950728G72106876925A TUBE ASSY 23001938 AEROSPAS355 AS355F1 8680810EU ALLSN 250C 250C20F 03013GL GEAR BOX MAKING METAL E HEEAK NONE O OTHER ININSP/MAINT 1 SW035793Y7930 CAG40058 5141 CAE840058 ENGINE REMOVED DUE TO METAL IN OIL. UPON INSPECTION OF GEARBOX PARTS NOTED THE FOLLOWING: BELOW CEB1307 REQUIREMENTS ON TUBE ASSEMBLY. INSTALLED NEW TUBE ASSY. PART RETURNED TO ALLISON FOR CEB1307. REFERENCE: AFA#24405A (PART IS OUT OF CALENDAR DATE AND TIME LIMITS) 1G72 3U3 U H11EU E4CE 19950804005181995080400518GL 1995 8 4 HEEA955483 219950728G725023004223 WHEEL 23031899 BELL 206 206L1 1182107SW ALLSN 250C 250C28B 03013GL 2ND STAGE MIS MFG E HEEAK NONE W INADEQUATE Q C ININSP/MAINT 1 SW035745S CAT70036 45491 CAE860022 UPON INSPECTION OF NEW NEVER INSTALLED #2 WHEEL NOTED THE FOLLOWING: RECEIVED OVERMACHINED PER O/H SPECS ON #2 WHEEL SPLINES. INSTALLED NEW #2 WHEEL. 1G71 3U3 U H2SW E1GL 19950804005321995080400532NE 1995 8 4 95ZZZX3579 219950530G7200 ENGINE LEAR 24 24D 5170311CE GE CJ610 CJ6106 30006NE NR 1 FLAME-OUT D O OTHER X ENGINE FLAMEOUT CRCRUISE 1 GL25888FA9078 4483 257 251357A AT CRUISE ALTITUDE OF 45,000 FEET, ABOUT 1.5 HOURS INTO FLIGHT, BOTH ENGINES FLAMED OUT AT EXACTLY THE SAME TIME. THE FIRST INDICATION WAS A SLIGHT BUMP, THEN THE RPM GAUGES STARTED ERODING FROM 95 PERCENT. THE CREW WAS ABLE TO EXECUTE A RE-LIGHT ON BOTH ENGINES AT 25,000 FEET. BOTH ENGINES WERE CHECKED FOR FOD DAMAGE. FUEL FILTERS WERE CHECKED. P AND D VALVES WERE LOOKED AT. NO REASON FOR FLAME-OUT WAS FOUND AT THIS TIME. 2L72 4J4 J A10CE 1E16 19950804005331995080400533NE 1995 8 4 95ZZZX3580 219950530G7200 ENGINE LEAR 24 24D 5170311CE GE CJ610 CJ6106 30006NE NR 2 FLAME-OUT D O OTHER X ENGINE FLAMEOUT CRCRUISE 1 GL25888FA9122 4483 257 251358A AT CRUISE ALTITUDE OF 45,000 FEET, ABOUT 1.5 HOURS INTO FLIGHT, BOTH ENGINES FLAMED OUT AT EXACTLY THE SAME TIME. THE FIRST INDICATION WAS A SLIGHT BUMP, THEN THE RPM GAUGES STARTED ERODING FROM 95 PERCENT. THE CREW WAS ABLE TO EXECUTE A RE-LIGHT ON BOTH ENGINES AT 25,000 FEET. BOTH ENGINES WERE CHECKED FOR FOD DAMAGE. FUEL FILTERS WERE CHECKED. P AND D VALVES WERE LOOKED AT. NO REASON FOR FLAME-OUT WAS FOUND AT THIS TIME. 2L72 4J4 J A10CE 1E16 19950804005431995080400543WP 1995 8 4 95ZZZX3592 219950621G7310YA001295 LINE BRAERODH125 HS125700A 4230170EU GARRTTTFE731TFE7313 01518WP RT ENGINE DAMAGED B WLCRK NONE O OTHER ININSP/MAINT 1 WP0134RE 257022 LINE ASSEMBLY FOUND KINKED AT LOWER END. THIS PART IS AN ENGINE MAIN FUEL SUPPLY LINE (FLEXIBLE). THIS LINE MUST BE DISCONNECTED IN ORDER TO ALLOW CERTAIN DEFUELING OPERATIONS. CARE MUST BE EXERCISED WHEN DISCONNECTING THE LOWER FITTING; OTHERWISE, KINKING WILL OCCUR RESULTING IN DIMINISHED FUEL SUPPLY TO THE ENGINE. SUBMITTER SUGGESTS MECHANICS SHOULD BE ADVISED TO USE MORE CARE WHEN DISTURBING THIS LINE ASSEMBLY. ACFT TT 3,223 HOURS. 2L72 4F4 F A3EU E6WE 19950804006111995080400611GL 1995 8 4 95ZZZX3609 219950629G7310219216 FILTER CESSNA525 525 2076601CE WILINTFJ44 FJ44 66000GL LT ENGINE WARN LIGHT B IW1RL ABORTED APPROACH J WARNING INDICATION APAPPROACH 1 EA2594MZ 33 5250094 1206 LEFT FUEL FILTER BYPASS INDICATOR LIGHT ILLUMINATED (ANNUNCIATING PENDING FILTER BYPASS) DURING 'GO-AROUND'. AIRCRAFT LANDED WITHOUT PROBLEMS. LEFT ENGINE FUEL FILTER ELEMENT WAS REPLACED. NO OBVIOUS FAULTS NOTED. RIGHT ENGINE FILTER ELEMENT WAS ALSO REPLACED. IT, TOO, HAD NO OBVIOUS FAULTS. 1L72 4F4 FRTA1WI E3GL 19950804006121995080400612SO 1995 8 4 95ZZZX3610 219950710G7310641032148 VALVE CESSNA404 404CESSNA 2075901CE CONT O520 GTSIO520M 17032SO ENGINE FUEL GASKET FAILED D O OTHER K FLUID LOSS NRNOT REPORTED 1 SO172FOR 4040628 276446R NEWLY INSTALLED OVERHAULED ENGINE AFTER 20 HOURS OF FLYING TIME. FUEL DISTRIBUTION VALVE ON TOP OF ENGINE HAD A BLOWN GASKET WHICH SPRAYED RAW FUEL ALL OVER THE ENGINE WHILE IN FLIGHT. ENGINE OVERHAULED BY TELEDYNE CONTINENTAL MOTORS. 1L72 3O3 O A25CE E7CE 19950804006241995080400624EA 1995 8 4 95ZZZX3622 219950703G731060100040544 HOSE CESSNA172 R172K 2072431CE LYC O320 O320E2D 41508EA ENGINE FUEL LEAKING D K NONE K FLUID LOSS ININSP/MAINT 1 EA093315V R1722248 FUEL HOSE RUNS ACROSS THE TOP OF THE ENGINE. WHEN PRESSURE CHECKED, IT LEAKED ALONG THE ENTIRE LENGTH. TAG ON HOSE HAS THE FOLLOWING DATA: PAW 601000-4-0544. PT10-89. A4Q89. 1000 PSI. RUBBER. 00624. TSO - 053A. SEE AEROQUIP SBAA135 - THESE HOSES ARE STILL OUT THERE. 1H71 3O3 O 3A17 E274 19950804006321995080400632NE 1995 8 4 95ZZZX3630 219950607G7260208312604 LOCK PIN 208325023 SEMCO CLNGERCHALLENGER 8070802NM LYC ALF502ALF502L2 41580NE ASSORY DR GR BOXFAILED BL SH5RK NONE O OTHER ININSP/MAINT 1 NE03733CF1486 82G004 1041 LF03089S OIL ANALYSIS, FINDING AN INCREASE IN METAL CONTAMINATION, INVESTIGATION REVEALED THE ACCESSORY DRIVE GEARBOX DRIVESHAFT LOCK ASSY POST SB ALF502L 72-0175, HAD DROPPED DOWN ONTO THE STARTER DRIVESHAFT MACHINING AWAY AT THE DRIVESHAFT WHICH CAUSED THE REPLACEMENT OF THE FOLLOWING COMPONENTS: ACCESSORY DRIVE GEARBOX MODULE, FUEL/OIL HEAT EXCHANGER, THE ENGINE DRIVEN OIL PUMP ASSY AND THE NR 12 BEARING. SUSPECT CAUSED BY FAILURE OF THE DRIVESHAFT LOCK PIN (PN 2-083-126-04). RECOMMEND ASAP (ESPECIALLY IF NOT ON ACTIVE OIL ANALYSIS PROGRAM) TO REMOVE ACCESSORY DRIVE GEARBOX DRIVESHAFT LOCK ASSY AND INSPECT DRIVESHAFT LOCK PIN (PN 2-083-126-04) FOR BEING ANYTHING LESS THAN STRAIGHT WITH EVENLY CUT ENDS. 1B00 4 F A13SO E6NE 19950804006341995080400634GL 1995 8 4 95ZZZX3632 219950701G7250 WHEEL ALLSN 250C 250C20 03013GL TURBINE SHAFT MISMFG B UP9RK NONE W INADEQUATE Q C ININSP/MAINT 1 NM07 FACTORY NEW WHEEL SPLINED ADAPTER SHAFT PILOT MEASURES 0.566 INCH WHICH IS APPROXIMATELY 0.010 INCH LARGER THAN MAXIMUM. WHEEL RETURNED TO ALLISON. 3 U E4CE 19950804006411995080400641NE 1995 8 4 95ZZZX3639 219950525G7414SB9RU3 MAGNETO BOSCH AIRTRCAT300 AT301 0390103SW PWA R1340 R1340* 52016NE RT ENGINE SHORTED D K NONE Y ENGINE STOPPAGE NRNOT REPORTED 1 SW1136552 900 3010299 MAGNETO COVER ON RIGHT MAGNETO VIBRATED SCREWS LOOSE CAUSING COVER TO GROUND COIL KILLING MAGNETO WHICH CAUSED ENGINE FAILURE. 1L71 3R3 R A9SW 5E2 19950804006521995080400652EA 1995 8 4 95ZZZX3650 219950613G7414K3823 DISTRIBUTOR SLICK 6250 PIPER PA32 PA32* SO LYC O540 IO540K1G5 41532EA MAG BLOCK DESTROYED B BF1RK NONE O OTHER ININSP/MAINT 1 EA05 30 DISMANTLED MAG FOUND DISTRIBUTOR OR BEARING BLOCK DESTROYED BY ARCING FROM DEFECTIVE COIL. 1L71 3O3 O A3SO 1E4 19950804006551995080400655SO 1995 8 4 95ZZZX3653 219950703G8530 CYLINDER CESSNA404 404CESSNA 2075901CE CONT O520 GTSIO520M 17032SO LT ENG NR 3 CRACKED B APCRK NONE O OTHER ININSP/MAINT 1 NM0141SA 1298 4040023 276274R LEFT ENGINE NR 3 CYLINDER CRACKED AT BOTH SPARKPLUG HOLES. SUBMITTER KNOWS OF MANY EXAMPLES OF IDENTICAL FAILURES THROUGHOUT FLEET AIRCRAFT. 1L72 3O3 O A25CE E7CE 19950804006561995080400656EA 1995 8 4 95ZZZX3654 219950712G7322HA6 CARBURETOR VALVE CESSNA172 172RG 2072438CE LYC O360 O360F1A6 41514EA CONTROL ARM SEIZED D K NONE O OTHER ININSP/MAINT 1 NM015210V 20 172RG0471 L2854136A PILOT REPORTED THROTTLE WOULD NOT MOVE FROM IDLE AFTER START. REMOVED CARBURETOR, FOUND CONTROL ARM SEIZED. REPLACED CARBURETOR UNDER WARRANTY. SENT CARBURETOR TO PRECISION AIRMOTIVE FOR WARRANTY/PROBLEM INSPECTION. 1H71 3O3 O 3A17 E286 19950804007441995080400744SO 1995 8 4 95ZZZX3657 219950627G8530 CYLINDER CESSNA310 310P 2074238CE CONT O470 IO470VO 17026SO RT ENG NR 4 EXITED D AE UNSCHED LANDING ENGINE SHUTDOWN ERKVIBRATION/BUFFET PARTIAL RPM/PWR LOSS FLUID LOSS NRNOT REPORTED 1 WP255819M 8 310P00119 1487209V THE AIRCRAFT MADE AN EMERGENCY LANDING WITH THE RIGHT ENGINE FEATHERED. THE COPILOT HAD NOTED NR 4 CYLINDER EXIT THROUGH THE SIDE COWLING IN A DOWNWARD DIRECTION. THE CONNECTING ROD WAS STILL ON THE CRANK, BENT SLIGHTLY AFT AND THE PISTON PIN BOSS WAS ELONGATED. ALL HOLD-DOWNS WERE BROKEN OFF. 1L72 3O3 O 3A10 3E1 19950804007451995080400745EA 1995 8 4 95ZZZX3658 219950705G853073806 PUSHROD BEECH 77 77 1153007CE LYC O235 O235L2C 41505EA ENGINE FAILED D K NONE W INADEQUATE Q C ININSP/MAINT 1 WP17380251491 TH1208 L2167815 PUSHROD FAILED AND WAS NOT MARKED WITH THE PROPER P/N PER THE A.O. 80-25-02 LYCOMING ADVISED THAT THE PROPER PUSHRODS WERE INSTALLED DURING ORIGINAL ASSEMBLY. ALL PUSHRODS REMOVED AND INSPECTED. ALL FOUND TO HAVE THE WRONG P/N. NO RECORDS OF THE PUSHRODS BEING REPLACED. 1L71 3O3 O A30CE E223 19950804007491995080400749EA 1995 8 4 95ZZZX3662 219950706G8530 CYLINDER PIPER PA28 PA28140 7102802SO LYC O320 O320E2A 41508EA NR 4 WORN G K NONE O OTHER ININSP/MAINT 1 EA0167WA 5724 1247 287125267 L2935627A NR 4 CYLINDER FOUND TO HAVE CHOKE BORE OUT OF TOLERANCE. SUSPECT CAUSE FOUND TO BE 2 INCH SCAT HOSE COLLAPSED BLOCKING OFF COOLING AIR. 1L71 3O3 O 2A13 E274 19950804007521995080400752EA 1995 8 4 95ZZZX3665 219950626G7322 CONTROL BOLT CESSNA177 177 2073704CE LYC O320 O320D2A 41508EA THROTTLE DETACHED D A UNSCHED LANDING R PARTIAL RPM/PWR LOSS CLCLIMB 1 WP233420T3934 17700720 L2095127AC AT ABOUT 700 FEET ALTITUDE AFTER DEPARTURE, ENGINE WENT TO IDLE. AFTER A SUCCESSFUL OFF AIRPORT LANDING WAS MADE, BOLT AND HARDWARE CONNECTING THROTTLE CONTROL TO CARBURETOR WERE FOUND MISSING. INSTALLED NEW BOLT, NUT, SPACER, AND WASHERS. AIRCRAFT TOWED TO A ROAD AND WITH CHP PERMISSION, RETURNED TO AIRPORT. SUBMITTER STATED BOLT AND CASTELLATED NUT HAD PROBABLY BEEN OVERTORQUED. MAYBE MANY TIMES IN PAST. SUBMITTER SUGGESTS REPLACING AT OVERHAUL AND DO NOT OVERTORQUE. 1H71 3O3 ONTA13CE E274 19950804007611995080400761SO 1995 8 4 95ZZZX3674 219950716G8520 CRANKCASE BEECH 55 E55 1152732CE CONT O520 IO520C 17032SO ENGINE CRACKED D K NONE K FLUID LOSS ININSP/MAINT 1 SW9991WC 3016 300 TE909 231829R AIRCRAFT HAS SEVERAL OIL LEAKS ON RT ENGINE FINALLY RESULTING IN CRACKED CASE. SUSPECT THAT WHEN TEAR DOWN IS DONE, CRANK HAS COUNTERWEIGHT PROBLEM. THIS IS THE THIRD ENGINE THIS YEAR TO REJECT DUE TO CRANK PROBLEMS. SUBMITTER STATED MAYBE ENGINE OVERHAUL SHOULD REQUIRE CLOSER CRANK OVERHAUL INSPECTION FOR BUSHING REPLACMENT, 300 TSO. 1L72 3O3 O 3A16 E5CE 19950804007621995080400762SO 1995 8 4 95ZZZX3675 219950705G8520 CRANKCASE BEECH 55 95B55 1152706CE CONT O470 IO470L 17026SO NR 6 CYL THRU BOLT SEPARATED D K NONE W INADEQUATE Q C ININSP/MAINT 1 SW0596NL TC721 297553R DURING A SCHEDULED INSPECTION, THE LOWER FORWARD CRANKCASE THROUGH-BOLT ON NR 6 CYLINDER WAS FOUND COMPLETELY SEPARATED. FURTHER INSPECTION FOUND THE BOLT IMPROPERLY INSTALLED. THE BOLT FAILED IN THE O-RING GROOVE LOCATED IN THE MIDDLE PORTION OF THE BOLT. THIS ENGINE WAS A FACTORY REMANUFACTURE WITH 77.2 HRS SINCE INSTALLED ON THIS AIRCRAFT, P/N 641931981. 1L72 3O3 O 3A16 3E1 19950804007671995080400767EA 1995 8 4 95ZZZX3680 219950619G7322105135 CARBURETOR JET FACET MA4SPA CESSNA172 172N 2072434CE LYC O320 O320H2AD 41508EA ENGINE BLOCKED DL K NONE O OTHER ININSP/MAINT 1 SO065415J 1248 CT610931 17273785 TEAR DOWN OF CARBURETOR TO IDENTIFY REASON FOR FAILURE. MAIN JET ASSEMBLY WAS FOUND PARTIALLY BLOCKED. BLOCKAGE REMOVED USING A .040 INCH PIECE OF SAFETY WIRE PASSED THROUGH THE OUTLET END OF THE MAIN JET ASSEMBLY. 1H71 3O3 ONT3A12 E274 19950811001171995081100117WP 1995 8 11 95ZZZX3727 219950630G726030753562 ADAPTER SPLINE CESSNA650 650 2076802CE GARRTTTFE731TFE731* 01518WP RT ENGINE STRIPPED B GMCRK NONE O OTHER ININSP/MAINT 1 GL235111 440 6507011 102124 RIGHT ENGINE WOULD NOT ROTATE WHEN STARTER BUTTON ENGAGED. FOUND OUTER SPLINES ON ADAPTER STRIPPED. LEFT ENGINE SPLINE ADAPTER ALSO WORN EXCESSIVELY. MFG RECOMMENDS INSPECTION AT 2,100 HOUR INTERVALS. OPERATOR CONTROL NR 95-003. 2L72 4F4 F A9NM E6WE 19950811001191995081100119WP 1995 8 11 95ZZZX3729 219950201G721030730371 WASHER GARRTTTFE731TFE7312 01518WP PLANETARY GEAR CRACKED B AN3DK NONE O OTHER ININSP/MAINT 1 WP05 DURING DETAILED INSPECTION OF PLANETARY ASSEMBLY, PN 3073037-1/2, WASHERS HAVE BEEN FOUND CRACKED ON SEVERAL TFE 731-2/3 ENGINES. CURRENT MAINTENANCE MANUALS DO NOT REQUIRE REMOVING THIS BEARING CAGE TO ACCOMPLISH INSPECTION OF GEAR ASSEMBLY. SEE LIGHT MM 72-02-41, PAGE 224C, AND MM 72-72-02, SECTION 2 INSPECTION. APPROXIMATELY 30 OF THESE WASHERS HAVE BEEN FOUND CRACKED IN THE LAST 6 MONTHS. ALL HAVE BEEN SENT TO THE MANUFACTURER. PART TOTAL TIMES 3747.0 TO 6938.0. 4 F E6WE 19950811001201995081100120EA 1995 8 11 95ZZZX3730 219950714G7532310334601 DIAPHRAM 310092205 BEECH 200 200BEECH 1152920CE PWA PT6 PT6A41 52043EA BLEED VALVE RUPTURED B LX5RK NONE O OTHER NRNOT REPORTED 1 GL19971LL 9B540 BB572 PCE81368 DIAPHRAM RUPTURED RENDERING BLEED VALVE INOPERATIVE. 1L72 4T4 T A24CE E4EA 19950811001331995081100133GL 1995 8 11 95ZZZX3743 219950710G725068993737 WHEEL HX66921 BELL 206 206B3 1181506SW ALLSN 250C 250C20B 03013GL 3RD STAGE CRACKED B SZTRK NONE O OTHER ININSP/MAINT 1 WP07206WP2773 CAT34702 2752 CAE830842 ENGINE WOULD NOT MAKE POWER. FOUND 3RD STAGE WHEEL CRACKED. 1G71 3U3 U H2SW E4CE 19950811001341995081100134GL 1995 8 11 95ZZZX3744 219950414G7250A6871505 BEARING BOLKMS105 BO105C 5626005EU ALLSN 250C 250C20B 03013GL TURBINE NR 5 FAILED B HDNRK NONE O OTHER ININSP/MAINT 1 SW03105SJ153 077 S104 CAT23301 NR 5 BEARING BALL RETAINER FLAKING OFF. THE BEARING MANUFACTURED BY SUPERIOR TURBINE. 1G72 3U3 U H3EU E4CE 19950811001391995081100139EA 1995 8 11 95ZZZX3749 219950707G854072230 IDLER SHAFT HUGHES269 269C 4470504WP LYC O360 HIO360D1A 41514EA ENG REAR CASE STUDS BROKE D A K NONE O OTHER ININSP/MAINT 1 GL098377F1120 480680 L836851A STUDS, .3125 INCH, IN REAR OF CRANKCASE THAT HOLDS IDLER GEAR SHAFT BROKE WHICH LET THE IDLER GEAR GET BETWEEN CRANK AND CAMSHAFT WHICH CAME LOOSE AND WAS VERY NEAR FAILURE. ENGINE HAD 1,120 HOURS TOTAL SINCE NEW. THE STUDS IN THE REAR OF THE CASE SHOULD BE .3750 INCH STUDS. HAVE HAD THIS SAME THING HAPPEN ON ANOTHER ENGINE OF SAME MAKE AND MODEL WITH 1,102 HOURS SINCE MOH AND TOTAL TIME OF 3,200 HOURS. 1G71 3O3 O 4H12 1E10 19950811001401995081100140GL 1995 8 11 95ZZZX3750 219950703G7200 ENGINE BELL 206 206B3 1181506SW ALLSN 250C 250C20B 03013GL FUEL FILTER FLAME OUT H A O OTHER X ENGINE FLAMEOUT HOHOVERING 1 GL23321JW10309 3446 820486 ENGINE FLAMED OUT IN HOVER. EXPERIENCED SUCCESSFUL RESTART ON FIRST ATTEMPT. TWO MINUTES RUN AT 100 PERCENT N2 WITH BOOST PUMPS OFF - CHECKED OKAY. SHUT DOWN ENGINE. BLED SYSTEM, FOUND AIR IN ENGINE MOUNTED FUEL FILTER HOUSING. RAN ENGINE, SHUT DOWN, BLED FILTER AGAIN - NO AIR FOUND. AIRCRAFT RETURNED TO SERVICE. NOTE: AIRCRAFT WAS JUST RETURNED TO SERVICE AFTER APPROXIMATELY 5 WEEKS IN PAINT SHOP ABOUT TEN HOURS BEFORE FLAMEOUT. 1G71 3U3 U H2SW E4CE 19950811001431995081100143GL 1995 8 11 95ZZZX3753 219950622G724023056130 BURNER LINER BELL 206 206B 1181511SW ALLSN 250C 250C20B 03013GL COMB CAN MISINSTALLED B ASNCDK NONE W INADEQUATE Q C ININSP/MAINT 1 SO17455H 958 3453 CAE833825 WHEN BURNER CAN LINER WAS ASSEMBLED, THE LOWER SKIRT WAS TURNED 90 DEGREES WHICH MISPLACED TWO LARGE COOLING HOLES. THIS CAUSED THE ENGINE TO START SLOW (60 SECONDS), HANG AT 42 PERCENT, AND HAVE A DELAYED LIGHT OFF. THE PROBLEM ONLY SHOWED UP AFTER ABOUT 500 HOURS IN USE. 1G71 3U3 U H2SW E4CE 19950811002411995081100241NE 1995 8 11 F6LM9581 219950227G7421956013490 HE IGNITER SNIAS 350 AS350B2 8680813EU TMECA ARRIELARRIEL1 60030NE ENGINE DEFECTIVE H F6LMK NONE O OTHER ININSP/MAINT 1 SO196095T744 2671 9241 IGNITER WOULD NOT FIRE, TESTED ON OTHER BOX STILL INOP. REPLACED HE IGNITER, OPS CHECKED OKAY 1G71 3U3 U H9EU E19EU 19950811002891995081100289GL 1995 8 11 HEEA955519 219950802G7321252494410 FUEL CONTROL BELL 206 206L 1181522SW ALLSN 250C 250C28B 03013GL ENGINE DEFECTIVE E HEEAK NONE O OTHER NRNOT REPORTED 1 SW037074W8748 52033 FUEL CONTROL BY-PASS COVER RETENTION SCREW HEAD BROKEN (SHEARED) 1G71 3U3 U H2SW E1GL 19950811004081995081100408EA 1995 8 11 95ZZZX3799 219950621G7414 HOUSING BENDIX S4LN1209 BEECH 23 B19 1151215CE LYC O320 O320E2C 41508EA RT MAGNETO CRACKED D K NONE O OTHER ININSP/MAINT 1 EA21245827195 1550 243050 MB540 L1803127A DURING ANNUAL INSPECTION, THE RIGHT MAGNETO HOUSING WAS FOUND CRACKED IN SEVERAL PLACES. CRACKED ON BOTH SIDES OF THE MAGNETO DOWN NEAR THE DRIVE END. 1L71 3O3 O A1CE E274 19950811004991995081100499EA 1995 8 11 95ZZZX3860 219950717G853060401 ROCKER SHAFT CESSNA177 177 2073704CE LYC O320 O320E2D 41508EA NR 3 CYL EXH CRACKED D K NONE O OTHER ININSP/MAINT 1 SW112942X1417 17700542 L2027927A DURING THE CHANGING OF THE PUSHROD HOUSING TUBE SEALS WHICH INVOLVES REMOVING THE ROCKER BOXES, FOUND THE VALVE ROCKER SHAFT ON THE EXHAUST SIDE OF CYLINDER NR 3 CRACKED ABOUT ONE-HALF THE WAY AROUND AND .25 INCH FROM THE END. 1H71 3O3 ONTA13CE E274 19950811005981995081100598GL 1995 8 11 95ZZZX3922 219950727G72306887121 VENT TUBE HUGHES369 369D 4470706WP ALLSN 250C 250C20B 03013GL COMP ASSY DETACHED B EOORK NONE O OTHER ININSP/MAINT 1 AL033115Y 500716D CAE830348 ENGINE DIFFUSER VENT ORIFICE TUBE WOULD NOT STAY IN PLACE. INSPECTION FOUND END OF THE TUBE THAT SLIPS INTO THE VENT BOSS WAS DEFORMED. INSTALLED NEW TUBE. 1G71 3U3 U H3WE E4CE 19950818000561995081800056SO 1995 8 18 95ZZZX3998 219950701G8550CH48109 FILTER CHAMPION CESSNA207 T207A 2073614CE CONT O520 TSIO520M 17040SO ENG OIL SYSTEM GASKET DISPLACEDDPA K NONE W INADEQUATE Q C ININSP/MAINT 1 NM01803AN50 20700570 283222R OIL FILTER INTERNAL GASKET WAS OUT OF PLACE AND COVERING INLET PASSAGE OF FILLER BODY. APPEARS TO BE MANUFACTURE DEFECT. SUBMITTER ADVISES A CLOSER INSPECTION OF OIL FILTER PRIOR TO INSTALLATION TO INSURE GASKET IS NOT BLOCKING INLET HOLE. 1H71 3O3 O A16CE E8CE 19950818000701995081800070EA 1995 8 18 95ZZZX4012 219950801G8520LW18837 CAMSHAFT CESSNA172 172M 2072418CE LYC O320 O320E2D 41508EA ENGINE WEAR G K NONE W INADEQUATE Q C ININSP/MAINT 1 NE0113599 1200 17262390 CAMSHAFT WAS PURCHASED FROM AIR SUPPORT INTERNATIONAL, INC. CAMSHAFT WAS OVERHAULED AT AIRCRAFT SPECIALTIES SERVICES FAA REPAIR STATION DD2R764K. CAMSHAFT SHOWED SIGNS OF PREMATURE WEAR. SUBMITTED BY EXECUTIVE FLYERS 141 SCHOOL LP8S302Q. 1H71 3O3 ONT3A12 E274 19950818000711995081800071EA 1995 8 18 95ZZZX4013 219950801G8520LW18837 CAMSHAFT PIPER PA28 PA28161 7102803SO LYC O320 O320D3G 41508EA ENGINE WEAR G K NONE W INADEQUATE Q C ININSP/MAINT 1 NE012180E 532 287916165 CAMSHAFT PURCHASED FORM AIR SUPPORT INTERNATIONAL, INC. CAMSHAFT WAS OVERHAULED AT AIRCRAFT SPECIALTIES SERVICES, FAA REPAIR STATION DD2R764K. CAMSHAFT SHOWED SIGNS OF PREMATURE WEAR. SUBMITTED BY EXECUTIVE FLYERS 141 SCHOOL LP8S302Q. 1L71 3O3 O 2A13 E274 19950818000751995081800075EA 1995 8 18 95ZZZX4017 219950801G8520LW18837 CAMSHAFT CESSNA172 172M 2072418CE LYC O320 O320E2D 41508EA ENGINE WEAR G K NONE W INADEQUATE Q C ININSP/MAINT 1 NE0161992 666 17264943 CAMSHAFT WAS PURCHASED FROM AIR SUPPORT INTERNATIONAL, INC. CAMSHAFT WAS OVERHAULED AT AIRCRAFT SPECIALTIES SERVICES, FAA REPAIR STATION DD2R764K. CAMSHAFT SHOWED SIGNS OF PREMATURE WEAR. SUBMITTED BY EXECUTIVE FLYERS 141 SCHOOL LP8S302Q. 1H71 3O3 ONT3A12 E274 19950818000771995081800077SO 1995 8 18 95ZZZX4019 219950714G8530629404 VALVE CESSNA150 150L 2071826CE CONT O200 O200A 17020SO NR 3 CYL EXH BINDING D K NONE O OTHER ININSP/MAINT 1 EA136836G229 15072336 681947A INSPECTION REVEALED VALVE STEM TIGHT IN GUIDE DUE TO EXCESSIVE CARBON BUILD-UP. AFTER CLEAN-UP OF GUIDE, THE CLEARANCE WAS MEASURED AND DETERMINED TO BE IN LIMITS. CAUSE OF CARBON BUILD-UP, POSSIBLE RICH CARBURETOR. INSPECTION OF 3 REMAINING CYLINDERS ON ENGINE REVEALED NO PROBLEMS. ENGINE TT 4,082.0. TSM O/H, 979 HOURS. 1H71 3O3 O 3A19 E252 19950818000791995081800079EA 1995 8 18 95ZZZX4021 219950312G731402532330003 FUEL PUMP PESCO STBROSSD3 SD330 8100602EU PWA PT6 PT6A45R 52043EA LEFT ENGINE STRIPPED D A A UNSCHED LANDING Y ENGINE STOPPAGE CRCRUISE 1 GL13336MV 392 8519 SH3018 84070 DURING CRUISE AND LEVEL FLIGHT ON 3-12-94, ENGINE SHUT DOWN. CREW TRIED SEVERAL ATTEMPTS AT RESTART WITH NO SUCCESS. FEATHERED ENGINE AND LANDED AT NEAREST AIRPORT. MAINTENANCE FOUND FUEL PUMP DRIVE SPLINES STRIPPED. REPLACED FUEL PUMP WITH OVERHAULED UNIT IAW MM 73-11-02. UNIT SENT BACK TO OVERHAUL SHOP FOR TEAR-DOWN REPORT. 2H72 4T4 T A41EU E4EA 19950818000821995081800082EA 1995 8 18 95ZZZX4024 219950726G853069602 TUBE ENSTRMF28 F28C 3300407GL LYC O360 HIO360E1AD 41514EA ENG INDUCTION DETACHED H A UNSCHED LANDING R PARTIAL RPM/PWR LOSS CLCLIMB 1 WP275689T2085 85 4742 HELICOPTER DEPARTED SCK AIRPORT AND MADE A FORCED LANDING IN A FIELD. INVESTIGATION FOUND AN INDUCTION TUBE HAD COME LOOSE. RECOMMEND DURING OVERHAUL, ALL TUBES BE RE-SWAGED. 1G71 3O3 O H1CE 1E10 19950818000881995081800088EA 1995 8 18 95ZZZX4030 219950605G7250310209404 GAS GENERATOR PWA PT6 PT6A65B 52043EA GAS GEN CASE DAMAGED B MASRK NONE O OTHER ININSP/MAINT 1 SW01 PART RECEIVED FROM EDM IN OVERHAULED CONDITION. WHEN GAS GENERATOR CASE WAS ASSEMBLED AND RUN ON THE TEST CELL FOR EVALUATION, ENGINE RAN HOT AND TOO FAST. ALL CORRECTIVE ACTIONS FAILED TO CORRECT THE PROBLEM. THE GAS GENERATOR CASE WAS REPLACED AND THE ASSEMBLED ENGINE RAN WELL WITHIN LIMITS. SUSPECT HIDDEN CRACKS OR DAMAGE TO THE CASE AND SAID CASE HAS BEEN SENT TO PWC FOR EVALUATION. 4 T E4EA 19950818000891995081800089EA 1995 8 18 95ZZZX4031 219950621G72603040026 HOUSING PWA PT6 PT6A65B 52043EA GAS GEN AGB BORE OVERSIZE B MAXRK NONE W INADEQUATE Q C ININSP/MAINT 1 GL13 PWC95M376 THE HOUSING WAS RECEIVED FROM PWC AFTER THEY REPAIRED THE HOUSING AND REINSPECTED ALL BEARING BORES. THE BEARING BORES WERE MEASURED BY DTS INSPECTION DEPARTMENT AND FOUND OUT OF TOLERANCE. (OVERSIZED). PART RETURNED TO PWC FOR REWORK AND/OR REPAIR. 4 T E4EA 19950818000901995081800090EA 1995 8 18 95ZZZX4032 219950725G7320311454801 LEVER BEECH 200 200BEECH 1152920CE PWA PT6 PT6A41 52043EA FCU ACTUATOR JAMS D A K NONE W INADEQUATE Q C ININSP/MAINT 1 GL132883 BB144 PCE80042 LEFT POWER LEVER WOULD INTERMITTENTLY STOP BEFORE FULL TRAVEL IN QUADRANT, LIMITING ENGINE SPEED TO APPROXIMATELY 80 PERCENT N1. ENGINE WAS NEWLY OVERHAULED, AND FCU LEVER, PN 311458-01, WAS INSTALLED DURING C/W SB 3304. FCU LEVER FOUND JAMMING ON PROPELLER REVERSE CONTROL FOLLOWING LEVER. REINSTALLED ORIGINAL FCU LEVER, PN 3010454, NO FURTHER PROBLEMS NOTED. THIS PROBLEM IS ADDRESSED BY SB 3310, WHICH INSTALLS LEVER, PN 3119355-01. 1L72 4T4 T A24CE E4EA 19950818000971995081800097GL 1995 8 18 95ZZZX4039 219950622G7260 GEARBOX AEROSPAS355 AS355F1 8680810EU ALLSN 250C 250C20F 03013GL NR 1 ENGINE FAILED E A UNSCHED LANDING JX WARNING INDICATION ENGINE FLAMEOUT CRCRUISE 1 SW035774M11516 5009 CAE840464 INBOUND FOR OFFSHORE PLATFORM, PILOT REPORTED NR 1 ENGINE CHIP LIGHT ILLUMINATED, AIRCRAFT YAWED, ENGINE FLAMED OUT. LANDED AT ONSHORE WITHOUT INCIDENT. INVESTIGATION REVEALED BOTH ENGINE ACCESSORY GEARBOX CHIP PLUGS COVERED WITH METAL. N1 DOES NOT TURN FREELY. ENGINE TSO, 3,199:55. 1G72 3U3 U H11EU E4CE 19950818005831995081800583SO 1995 8 18 95ZZZX4060 219950615G7320RSA7AD1 SERVO BENDIX BEECH 58 58P 1152744CE CONT O520 TSIO520WB 17040SO FUEL SERVO DIAPHRAGM TORN DL O OTHER B SMOKE/FUMES/ODORS/SPARKS CRCRUISE 1 SO013807T2480 494 56467 TJ332 L518458 DURING CRUISE, RT MAG INTERMITTENT. AT 14,000 FEET ALTITUDE, FUEL VENTING OUT OF LT ENGINE INBOARD UPPER COWL VENT. FOUND FUEL SERVO DIAPHRAGM TORN ALLOWING FUEL INTO AIR SIDE. FUEL VENTED OUT MAG FILTER AND INTO MAG CAUSING MISFIRE. 1L72 3O3 O A23CE E8CE 19950818005851995081800585NE 1995 8 18 95ZZZX4062 219950719G73211037642 SCREW WOODWARD 8061858 GE CF6 CF680C2A5 NE FUEL CONTROL BROKEN BL UU2RK NONE O OTHER ININSP/MAINT 1 GL03 WOODWARD HAS RECENTLY FOUND SEVERAL INSTANCES OF BROKEN SCREWS WHILE DIS-ASSEMBLING FUEL CONTROLS. THERE WAS NO FUNCTIONAL PROBLEM AS A RESULT OF THIS FAILURE. FURTHER INVESTIGATION HAS SHOWN THE BROKEN SCREWS ARE HARDER THAN THAT WHICH IS ALLOWED PER THE ENGINEERING DRAWING. INSPECTION OF SEVERAL PARTS HAS LED TO THE CONCLUSION THE BROKEN PARTS ARE ALL FROM THE SAME MANUFACTURING LOT AND NOT PROPERLY HEAT TREATED. INSPECTION RECORDS INDICATE THE LOT WAS PROCESSED PROPERLY, AND CONFORMED TO DRAWING REQUIREMENTS SO SEARCH FOR ROOT CAUSE IS FOCUSING ON POSSIBLE MIX-UP DUE TO LOOK-ALIKE PARTS OR POSSIBILITY SOME PORTION OF LOT MAY HAVE MISSED THAT OPERATION. 4 F E13NE 19950818005881995081800588NE 1995 8 18 95ZZZX4065 219950719G73211037642 SCREW WOODWARD 8061886 GE CF6 CF680C2A5 NE FUEL CONTROL BROKEN BL UU2RK NONE O OTHER ININSP/MAINT 1 GL03 WOODWARD HAS RECENTLY FOUND SEVERAL INSTANCES OF BROKEN SCREWS WHILE DIS-ASSEMBLING FUEL CONTROLS. THERE WAS NO FUNCTIONAL PROBLEM AS A RESULT OF THIS FAILURE. FURTHER INVESTIGATION HAS SHOWN THE BROKEN SCREWS ARE HARDER THAN THAT WHICH IS ALLOWED PER THE ENGINEERING DRAWING. INSPECTION OF SEVERAL PARTS HAS LED TO THE CONCLUSION THE BROKEN PARTS ARE ALL FROM THE SAME MANUFACTURING LOT AND NOT PROPERLY HEAT TREATED. INSPECTION RECORDS INDICATE THE LOT WAS PROCESSED PROPERLY, AND CONFORMED TO DRAWING REQUIREMENTS SO SEARCH FOR ROOT CAUSE IS FOCUSING ON POSSIBLE MIX-UP DUE TO LOOK-ALIKE PARTS OR POSSIBILITY SOME PORTION OF LOT MAY HAVE MISSED THAT OPERATION. 4 F E13NE 19950818005891995081800589NE 1995 8 18 95ZZZX4066 219950719G73211037642 SCREW WOODWARD 8061888 GE CF6 CF680C2A5 NE FUEL CONTROL BROKEN BL UU2RK NONE O OTHER ININSP/MAINT 1 GL03 WOODWARD HAS RECENTLY FOUND SEVERAL INSTANCES OF BROKEN SCREWS WHILE DIS-ASSEMBLING FUEL CONTROLS. THERE WAS NO FUNCTIONAL PROBLEM AS A RESULT OF THIS FAILURE. FURTHER INVESTIGATION HAS SHOWN THE BROKEN SCREWS ARE HARDER THAN THAT WHICH IS ALLOWED PER THE ENGINEERING DRAWING. INSPECTION OF SEVERAL PARTS HAS LED TO THE CONCLUSION THE BROKEN PARTS ARE ALL FROM THE SAME MANUFACTURING LOT AND NOT PROPERLY HEAT TREATED. INSPECTION RECORDS INDICATE THE LOT WAS PROCESSED PROPERLY, AND CONFORMED TO DRAWING REQUIREMENTS SO SEARCH FOR ROOT CAUSE IS FOCUSING ON POSSIBLE MIX-UP DUE TO LOOK-ALIKE PARTS OR POSSIBILITY SOME PORTION OF LOT MAY HAVE MISSED THAT OPERATION. 4 F E13NE 19950818005901995081800590NE 1995 8 18 95ZZZX4067 219950719G73211037642 SCREW WOODWARD 8061889 GE CF6 CF680C2A5 NE FUEL CONTROL BROKEN BL UU2RK NONE O OTHER ININSP/MAINT 1 GL03 WOODWARD HAS RECENTLY FOUND SEVERAL INSTANCES OF BROKEN SCREWS WHILE DIS-ASSEMBLING FUEL CONTROLS. THERE WAS NO FUNCTIONAL PROBLEM AS A RESULT OF THIS FAILURE. FURTHER INVESTIGATION HAS SHOWN THE BROKEN SCREWS ARE HARDER THAN THAT WHICH IS ALLOWED PER THE ENGINEERING DRAWING. INSPECTION OF SEVERAL PARTS HAS LED TO THE CONCLUSION THE BROKEN PARTS ARE ALL FROM THE SAME MANUFACTURING LOT AND NOT PROPERLY HEAT TREATED. INSPECTION RECORDS INDICATE THE LOT WAS PROCESSED PROPERLY, AND CONFORMED TO DRAWING REQUIREMENTS SO SEARCH FOR ROOT CAUSE IS FOCUSING ON POSSIBLE MIX-UP DUE TO LOOK-ALIKE PARTS OR POSSIBILITY SOME PORTION OF LOT MAY HAVE MISSED THAT OPERATION. 4 F E13NE 19950818005911995081800591NE 1995 8 18 95ZZZX4068 219950719G73211037642 SCREW WOODWARD 8061893 GE CF6 CF680C2A5 NE FUEL CONTROL BROKEN BL UU2RK NONE O OTHER ININSP/MAINT 1 GL03 WOODWARD HAS RECENTLY FOUND SEVERAL INSTANCES OF BROKEN SCREWS WHILE DIS-ASSEMBLING FUEL CONTROLS. THERE WAS NO FUNCTIONAL PROBLEM AS A RESULT OF THIS FAILURE. FURTHER INVESTIGATION HAS SHOWN THE BROKEN SCREWS ARE HARDER THAN THAT WHICH IS ALLOWED PER THE ENGINEERING DRAWING. INSPECTION OF SEVERAL PARTS HAS LED TO THE CONCLUSION THE BROKEN PARTS ARE ALL FROM THE SAME MANUFACTURING LOT AND NOT PROPERLY HEAT TREATED. INSPECTION RECORDS INDICATE THE LOT WAS PROCESSED PROPERLY, AND CONFORMED TO DRAWING REQUIREMENTS SO SEARCH FOR ROOT CAUSE IS FOCUSING ON POSSIBLE MIX-UP DUE TO LOOK-ALIKE PARTS OR POSSIBILITY SOME PORTION OF LOT MAY HAVE MISSED THAT OPERATION. 4 F E13NE 19950818005921995081800592NE 1995 8 18 95ZZZX4069 219950719G73211037642 SCREW WOODWARD 8061896 GE CF6 CF680C2A5 NE FUEL CONTROL BROKEN BL UU2RK NONE O OTHER ININSP/MAINT 1 GL03 WOODWARD HAS RECENTLY FOUND SEVERAL INSTANCES OF BROKEN SCREWS WHILE DIS-ASSEMBLING FUEL CONTROLS. THERE WAS NO FUNCTIONAL PROBLEM AS A RESULT OF THIS FAILURE. FURTHER INVESTIGATION HAS SHOWN THE BROKEN SCREWS ARE HARDER THAN THAT WHICH IS ALLOWED PER THE ENGINEERING DRAWING. INSPECTION OF SEVERAL PARTS HAS LED TO THE CONCLUSION THE BROKEN PARTS ARE ALL FROM THE SAME MANUFACTURING LOT AND NOT PROPERLY HEAT TREATED. INSPECTION RECORDS INDICATE THE LOT WAS PROCESSED PROPERLY, AND CONFORMED TO DRAWING REQUIREMENTS SO SEARCH FOR ROOT CAUSE IS FOCUSING ON POSSIBLE MIX-UP DUE TO LOOK-ALIKE PARTS OR POSSIBILITY SOME PORTION OF LOT MAY HAVE MISSED THAT OPERATION. 4 F E13NE 19950818005931995081800593NE 1995 8 18 95ZZZX4070 219950719G73211037642 SCREW WOODWARD 8061526 GE CFM56 CFM565A 13802NE FUEL CONTROL BROKEN BL UU2RK NONE O OTHER ININSP/MAINT 1 GL03 WOODWARD HAS RECENTLY FOUND SEVERAL INSTANCES OF BROKEN SCREWS WHILE DIS-ASSEMBLING FUEL CONTROLS. THERE WAS NO FUNCTIONAL PROBLEM AS A RESULT OF THIS FAILURE. FURTHER INVESTIGATION HAS SHOWN THE BROKEN SCREWS ARE HARDER THAN THAT WHICH IS ALLOWED PER THE ENGINEERING DRAWING. INSPECTION OF SEVERAL PARTS HAS LED TO THE CONCLUSION THE BROKEN PARTS ARE ALL FROM THE SAME MANUFACTURING LOT AND NOT PROPERLY HEAT TREATED. INSPECTION RECORDS INDICATE THE LOT WAS PROCESSED PROPERLY, AND CONFORMED TO DRAWING REQUIREMENTS SO SEARCH FOR ROOT CAUSE IS FOCUSING ON POSSIBLE MIX-UP DUE TO LOOK-ALIKE PARTS OR POSSIBILITY SOME PORTION OF LOT MAY HAVE MISSED THAT OPERATION. 4 F E29NE 19950818006951995081800695GL 1995 8 18 95ZZZX4087 219950609G7210A6887772 BEARING 6894171 BELL 206 206B 1181511SW ALLSN 250C 250C20B 03013GL GEARBOX GALLED B ALGRK NONE J WARNING INDICATION ININSP/MAINT 1 SW03209AL132 032 1044 8800956BA DISASSEMBLED GEARBOX DUE TO 'ENGINE CHIP LIGHT'. DISCOVERED THE P.T.O. ROLLER BEARING TO BE 'GALLING ROLLERS'. CAUSE UNKNOWN. 1G71 3U3 U H2SW E4CE 19950825002251995082500225EA 1995 8 25 95ZZZX4181 219950803G85307380685 PUSHROD CESSNA150 152 2071835CE LYC O235 O235L2C 41505EA CYL NR 3 MUSHROOMED D K NONE O OTHER ININSP/MAINT 1 EA01757UR 15280018 L2016515 CYLINDER NR 3 REMOVED FOR LOW COMPRESSION, FOUND EXCESSIVE CLEARANCE BETWEEN EXHAUST VALVE AND ROCKER ARM CAUSED BY PUSHROD THAT HAD MUSHROOMED UNDER BALL END. 1H71 3O3 ONT3A19 E223 19950825002321995082500232SO 1995 8 25 95ZZZX4188 219950804G8520632857 BEARING PIPER PA34 PA34220T 7103420SO CONT O360 LTSIO360KB 17025SO REAR MAIN BROKEN D K NONE O OTHER ININSP/MAINT 1 SW11837471174 348133074 268263R INSPECTION OF OIL FILTER ELEMENT DURING ROUTINE OIL CHANGE AND LARGE AMOUNT OF ALUMINUM SHAVINGS AND MINOR AMOUNT OF STEEL (MAGNETIC) PARTICLES WERE FOUND. ENGINE WAS REMOVED FROM AIRCRAFT AND DISASSEMBLED. FOUND REAR INTERMEDIATE MAIN BEARING HAD BROKEN INTO ABOUT 6-8 PIECES, BUT WAS BEING HELD IN PLACE BY CASE WEB AND BEARING JOURNAL. THE BEARING PIECES HAD SHIFTED ENOUGH TO SPIN IN WEB AND PRODUCE THE SHAVINGS OF ALUMINUM FOUND IN THE FILTER. IT WAS NOTED DURING DISASSEMBLY THAT TORQUE ON THROUGH-BOLT NUTS AT THIS WEB SEEMED LOW. ENGINE WAS OVERHAULED WITH BOTH CASE AND CRANKSHAFT BEING RETURNED TO SERVICE AFTER REPAIR. 1L72 3O3 O A7SO E9CE 19950825005721995082500572SO 1995 8 25 95ZZZX4262 219950518G8520 CAMSHAFT CESSNA207 207 2073602CE CONT O520 IO520F 17032SO CYL 3-4 LOBE FAILED D K NONE O OTHER ININSP/MAINT 1 AL031704U486 472013 20700304 286372R FAILURE OF CAMSHAFT AT NR 3 AND NR 4 INTAKE LOBE. DESTROYED LIFTER BODIES, METAL IN ENGINE, ETC. TIME SINCE OVERHAUL 486.1 HOURS. 1H71 3O3 O A16CE E5CE 19950825005761995082500576EA 1995 8 25 95ZZZX4266 219950627G8530SL74230 GUIDE SOCATATB9 TB9 8680694EU LYC O320 O320D2A 41508EA EXHAUST VALVE CRACKED B NX42K NONE O OTHER ININSP/MAINT 1 SO15138ER 971 1528 DURING CYLINDER REPAIR, THE EXHAUST VALVE GUIDE WAS FOUND CRACKED AT BOTH THE TOP AND BOTTOM PORTIONS OF THE GUIDE. THE CRACKS WERE NOT CONNECTED. 1L71 3O3 ONTAS1EU E274 19950825005771995082500577EA 1995 8 25 95ZZZX4267 219950627G853074230 GUIDE SOCATATB9 TB9 8680694EU LYC O320 O320D2A 41508EA CYLINDER EXHAUSTBROKEN B NX42K NONE O OTHER ININSP/MAINT 1 SO15177ER 1376 1353 DURING CYLINDER REPAIR, A RECTANGULAR SECTION OF THE EXHAUST VALVE GUIDE THAT MEASURED APPROXIMATELY .3125 INCH X .25 INCH WAS FOUND MISSING FROM THE LOWER PORTION OF THE GUIDE. 1L71 3O3 ONTAS1EU E274 19950825005781995082500578EA 1995 8 25 95ZZZX4268 219950627G8530SL74230 GUIDE LW12416 SOCATATB9 TB9 8680694EU LYC O320 O320D2A 41508EA CYLINDER EXHAUSTBROKEN B NX42K NONE O OTHER ININSP/MAINT 1 SO15245ER 722 1350 DURING CYLINDER REPAIR, A HALF-MOON SHAPED SECTION OF THE EXHAUST VALVE GUIDE THAT MEASURED APPROXIMATELY .3125 INCH X .25 INCH WAS FOUND MISSING FROM THE LOWER PORTION OF THE GUIDE. 1L71 3O3 ONTAS1EU E274 19950825005791995082500579EA 1995 8 25 95ZZZX4269 219950606G7414ES10382585 CONTACT ASSY D4LN3000 MOONEYM20 M20J 5870219SW LYC O360 IO360A3B6 41514EA MAGNETO WORN B NX42K NONE O OTHER ININSP/MAINT 1 SO15193ER997 497 B208905G 243243 WHEN MAGNETO WAS UNDERGOING PRELIMINARY INSPECTION, THE CONTACT ASSEMBLY WAS FOUND PITTED AND THE CAM FOLLOWER WAS EXCESSIVELY WORN. SOME CAM FOLLOWER MATERIAL HAD TRANSFERRED TO THE OUTER FELT OF THE CONTACT ASSEMBLY. A THIN DARK COATING WAS FOUND ON THE MAGNETO CAM. CAUSE IS SUSPECTED TO BE CAM FOLLOWER WEAR. CAM FOLLOWER WEAR RESULTS IN DECREASING CONTACT CLEARANCE AND MAY LEAD TO MAGNETO FAILURE. 1L71 3O3 O 2A3 1E10 19950825005811995082500581SO 1995 8 25 95ZZZX4271 219950727G7322 GASKET FACET MA5SPA CESSNA175 175 2072502CE CONT O300 GO300A 17022SO CARBURETOR WRONG PART G K NONE W INADEQUATE Q C ININSP/MAINT 1 GL156618E 56118 61919A FOLLOWING ENGINE OVERHAUL, CARBURETOR WAS RE-INSTALLED TO OIL SUMP USING O-RING SUPPLIED IN KIT NR 627372-A1, PAGE 25 OF GO-300 PARTS MANUAL, FORM X30020. CARBURETOR INSTALLED PER G0-300 PARTS MANUAL, FIGURE 5, WHICH CALLS FOR AN O-RING. NO O-RING GROOVE EXISTED. G0-300 OVERHAUL MANUAL, SECTION 12-11 CALLS OUT GASKET OR O-RING DEPENDING ON PART NUMBER. OIL PUMP INSTALLED. INDUCTION SYSTEM SHOWN IN FIGURE 8. 1H71 3O3 ONT3A17 E298 19950825005891995082500589GL 1995 8 25 95ZZZX4279 219950805G732323007505 GOVERNOR HUGHES369 369D 4470706WP ALLSN 250C 250C20B 03013GL ENGINE ERRATIC B EOORK NONE O OTHER ININSP/MAINT 1 AL034282X 424 28419 180253D CAE833827 GOVERNOR IS ERRATIC WITH ANY POWER CHANGE. UNIT REMOVED AND SENT IN FOR REPAIR ON ALLISON 250 REPORT NR A151615. 1G71 3U3 U H3WE E4CE 19950825005981995082500598NE 1995 8 25 95ZZZX4288 219950801G7530451077 SENSE LINE BOEING727 72722 1384002NM PWA JT8 JT8D7B 52053NE NR 3 ENGINE BROKEN D O OTHER J WARNING INDICATION CRCRUISE 1 SW99400RG 19149 P648871 DURING CRUISE, NR 3 ENGINE'S FUEL FLOW AND EGT BEGAN TO CLIMB WITH LOWER RPM'S AT SAME THROTTLE SETTING AS NR 1 AND NR 2 ENGINES. OK, PRESSURE GOOD, NO VIBRATION NOTED. REDUCED POWER TO IDLE FOR ABOUT 1.50 HOURS, INBOUND TO EWR. FOUND 13TH STAGE AIR PRESSURE SENSE LINE BROKEN AT 13TH STAGE SADDLE DUCT. LINE BROKE AT FERRULE TO TUBE WELD JUNCTION, SUSPECT CAUSE - VIBRATION. 2L73 4F4 F A3WE E2EA 19950825006201995082500620EU 1995 8 25 95ZZZX4310 219950727G8530935730 GEAR AMTR CH701 CH701 0564900GL ROTAX 582 ROTAX582 55555EU ROTARY VALVE TEETH SHEARED G O OTHER ER VIBRATION/BUFFET PARTIAL RPM/PWR LOSS NRNOT REPORTED 1 CE03701ZA414 73001 4016584 ROTARY VALVE GEAR OIL SUMP FASTENER BROKE AND SUMP FELL TO A LOWER LEVEL THAN THE CRANKSHAFT. LACK OF LUBRICATION FROM SUMP CAUSED BRASS ROTARY VALVE GEAR TO SHEAR OFF ITS TEETH. RESULT WAS THE ROTARY VALVE SLIPPED AND BECAME OUT OF TIME WITH ENGINE; THUS, ROUGHNESS AND POWER LOSS OCCURRED. 1H71 3O3 INTEXPA1H71EXPE3I 19950901003421995090100342SO 1995 9 1 95ZZZX4349 219950815G7414M3525 COIL SLICK 4201REVE TCRAFT19 F19 9230703GL CONT O200 O200A 17020SO MAGNETO OPEN H K NONE O OTHER ININSP/MAINT 1 AL013682T145 89060087 F089 255713 INSPECTION FOUND M3121 DISTRIBUTOR BLOCK AND ROTOR CONTACTS BURNED. M3525 COIL FAILED - OPEN AND HAD A CRACK IN SIDE. 1H71 3O3 O 1A9 E252 19950901003431995090100343EA 1995 9 1 95ZZZX4350 219950731G852071105ASR218 LIFTER PIPER PA38 PA38112 7103812SO LYC O235 O235L2C 41505EA NR 2 CYL EXH BROKEN D K NONE O OTHER ININSP/MAINT 1 SO152412K1071 3879A0621 L1874815 DURING ANNUAL INSPECTION, NR 2 CYLINDER WAS REMOVED DUE TO LOW COMPRESSION. WHEN CYLINDER WAS REMOVED, THE CUP PORTION OF THE EXHAUST SOLID LIFTER FELL TO THE FLOOR. THE CUP SECTION OF THE LIFTER HAD BROKEN COMPLETELY OFF. ALL LIFTERS HAD BEEN REPLACED DURING PREVIOUS ENGINE OVERHAUL. 1L71 3O3 O A18SO E223 19950901003481995090100348EA 1995 9 1 95ZZZX4355 219950728G8530SL134441 PISTON PIN PIPER PA60 PA60601P 7106012NM LYC O540 LTIO540J2BD 41533EA NR 3 CYLINDER BROKEN D K NONE O OTHER ININSP/MAINT 1 SW1736BW 243 61P0232033 L227168A DISASSEMBLING ENGINE FOR SEALING OIL LEAKS. WHEN NR 3 PISTON PIN WAS PUSHED OUT IT WAS FOUND BROKEN IN HALF RIGHT IN THE MIDDLE OF THE CONNECTING ROD BUSHING. FOUND LIGHT (0.002 INCH - 0.003 INCH DEEP) SCORING IN CONNECTING ROD BUSHING. APPARENTLY, THE PIN HAD NOT BEEN BROKEN FOR LONG. REMAINDER OF CYLINDER ASSY APPEARED NORMAL. NO SIGNIFICANT DIFFERENCE FROM OTHER 5. PLAN TO SUBMIT PIN TO U. OF T. METALLURGY LAB FOR ANALYSIS. APPEARS TO BE METAL DEFECT. 1M72 3O3 ORTA17WE E14EA 19950901003541995090100354EA 1995 9 1 95ZZZX4361 219950712G7210310074701 SHAFT PWA PT6 PT6A65B 52043EA PROP MISMATCH SET B MASRK NONE W INADEQUATE Q C ININSP/MAINT 1 SW01 PART WAS RECEIVED FROM THE VENDOR. THE PROP SHAFT AND SLEEVE HAVE TO BE A MATCHED SET, SAME S/N. THE SLEEVE HAS A S/N OF A1351. THE SHAFT IS S/N 5F780. THEREFORE, THIS IS NOT A MATCHED SET. 4 T E4EA 19950901003711995090100371NE 1995 9 1 95ZZZX4378 219950730G8530 PISTON GRUMANSA16 HU16 3950405EA PWA R1830 R1830* 52020NE RT ENG NR 9 CYL DAMAGED D E ENGINE SHUTDOWN JE WARNING INDICATION VIBRATION/BUFFET CRCRUISE 1 WP287025J 110 131910 AT 6,500 MSL-10 MI E OF DSM, RT ENGINE CHIP DETECTOR LIGHT CAME ON WITH ENGINE VIBRATION. FEATHERED RT ENGINE, PRECAUTIONARY. LANDING NORMAL. FOUND VALVE AND PISTON DAMAGE NR 9 CYLINDER. REPLACED CYLINDER, RECHECKED BOTH ENGINES FOR VALVE CLEARANCE, CHANGED OIL. 2H72 4R4 R EXPA2H725E4 19950901003771995090100377SO 1995 9 1 95ZZZX4384 219950817G8500 ENGINE CESSNA414 414A 2075907CE CONT O520 TSIO520NB 17040SO CYLINDER DEFECTIVE D K NONE ER VIBRATION/BUFFET PARTIAL RPM/PWR LOSS NRNOT REPORTED 1 NE03300SQ817 414A0416 800543 ENGINE HAS HIGH OIL CONSUMPTION, HIGH COOLENT PRESSURE, ROUGH RUNNING, LOW MANIFOLD PRESSURES. SUSPECT POSSIBLE CRACKED CYLINDER(S). 1L72 3O3 O A7CE E8CE 19950901003831995090100383EA 1995 9 1 95ZZZX4390 219950726G8520LW12596 ROD BOLT BEECH 80 65B80 1152812CE LYC O540 IGSO540A1A 41532EA NR 6 ROD BROKEN D O OTHER ER VIBRATION/BUFFET PARTIAL RPM/PWR LOSS NRNOT REPORTED 1 CE05265RW122 LD381 LL317830 ROD BOLT BROKE SUDDENLY WITH NO WARNING. ENGINE WAS RUNNING SMOOTH UNTIL ROD BROKE. 1L72 3O3 O 3A20 1E7 19950901003851995090100385SO 1995 9 1 95ZZZX4392 219950801G8520649895 CRANKCASE CESSNA402 402B 207590PCE CONT O520 TSIO520E 17040SO NR 4 CYL PAD CRACKED D K NONE K FLUID LOSS ININSP/MAINT 1 SW0753SA 7712 469 402B0597 20650271E DURING A ROUTINE INSPECTION, THE LEFT ENGINE CRANKCASE WAS