JASC 8520
Service difficulty reports · 2,214
Reports filed under 8520 · Reciprocating Engine Power Section, newest first.
Query with SQL
duckdb -csv -c "SELECT sdr_id, difficulty_date, n_number, aircraft_make, aircraft_model, part_name, part_condition, jasc_code, discrepancy FROM 'https://openairdocs.org/data/latest/faa_service_difficulty_report.parquet' WHERE jasc_code = '8520' ORDER BY difficulty_date DESC"
Prints the whole list as CSV. It reads the release’s Parquet files over HTTPS, so there’s nothing to download first. Install DuckDB to run it.
SELECT sdr_id, difficulty_date, n_number, aircraft_make, aircraft_model, part_name, part_condition, jasc_code, discrepancy FROM 'https://openairdocs.org/data/latest/faa_service_difficulty_report.parquet' WHERE jasc_code = '8520' ORDER BY difficulty_date DESC
Run it at the DuckDB prompt, or in any tool that reads Parquet over HTTPS. More ways to query the release are on Use the data.
SDR AU961004Crankcase · cracked(AUS) CRANKCASE CRACKED FROM NO2 CYLINDER MOUNT PADSDR AU960854Camshaft · pitted(AUS) ENGINE CAMSHAFT LOBE FOR NO5 CYLINDER EXHAUST VALVE AND CORRESPONDING LIFTER BADLY PITTED AND GALLEDSDR CA960529012Conrod Bolt · failed(CAN)ON POWER APPLICATION FOR TAKEOFF, SEVERE VIBRATION FROM ENGINE. POWER REDUCED AND ENGINE STOPPED. #2 CONNECTING ROD FAILED AND EXITED THE TOP OF CASE. CONROD CAP BOLTS FAILED.SDR CA960524019Dowel · sheared(CAN)METAL CONTAMINATION IN THE OIL FILTER AT 50 HOUR INSPECTION. SOURCE OF METAL IS #3 CONROD BEARING AND #2 MAIN BEARING. MAIN BEARING DOWEL PIN SEHARED AND CAUSED F.O.D. TO MAIN AND CONROD BEARINGS. ALL MAIN BEARING DOWELS RENEWED.SDR AU960769Crankcase · cracked(AUS) ENGINE CRANKCASE CRACKED IN AREA OF NO2 CYLINDER FORWARD UPPER HOLD DOWN STUD HOLE - CRACK LENGTH 31.75MM (1.25IN)SDR 96ZZZX2952Nut · mismanufacturedASSEMBLING THIS ENGINE DURING NORMAL OVERHAUL, THE ROD BOLT NUT WAS TORQUED AND THE BOLT MEASURED FOR STRETCH LENGTH. THE MICROMETER DID NOT SMOOTHLY SNUG UP. THE BOLT'S OUTBOARD EDGE MEASURED 2.255 INCHES AND INBOARD EDGE MEASURED, 2.259 INCHES. BELIEVING SDR CA960507015Crankcase · cracked(CAN)METAL FOUND IN OIL FILTER. A CYLINDER WAS REMOVED FOR INTERNAL CHECK. RADIUS CRACK FOUND AROUND REAR MAIN BEARING BOSS.SDR 96ZZZX2512Lifter · galledWHILE DOING TOP OVERHAUL, FOUND 3 HYDRAULIC LIFTERS PITTED AND GALLED. SUBMITTER RECOMMENDS CLOSER INSPECTION OF LIFTERS AT OVERHAUL.SDR 96ZZZX3369Crankshaft · crackedREMOVED CRANKSHAFT FROM ENGINE AT 1,425 HOURS FOR OVERHAUL. VISIBLE CRACKS AROUND OIL TRANSFER HOLE AT MAIN BEARING BEHIND ALTERNATOR GEAR. VISIBLE WITH NAKED EYE. CONFIRMED WITH MAGNAFLUX. THIS WAS A FACTORY REBUILT ENGINE.SDR 96ZZZX2519Crankshaft · failedPROPELLER SEPARATED FROM ENGINE DUE TO CRANKSHAFT FAILURE. INDICATION OF PREVIOUS CRACK AT AREA OF FRACTURE.SDR 96ZZZX2510Crankcase · crackedSMALL CRACK FOUND IN RIGHT SIDE OF CRANKCASE NEXT TO THROUGH-BOLT JUST FORWARD OF CYLINDER NR 5. CONSIDERED NON-CRITICAL AREA PER SB M90-17.SDR AU961043Camshaft · spalled(AUS) LH AND RH ENGINES HAD SPALLED CAMSHAFT EXHAUST LOBES AND ASSOCIATED TAPPETS - BOTH THE ENGINES ARE OF LATE MODIFICATION STATUS WITH LARGE TAPPETS AND LUBRICATING SLOTS IN THE TAPPET GUIDE BORES - LW16702 ADDITIVE IS USED AT EACH OIL CHANGE - METAL CONTASDR AU960550Connecting Rod · distorted(AUS) RH ENGINE NO6 CYLINDER CONNECTING ROD BENT DUE TO HYDRAULIC LOCK DUE TO EXCESSIVE FUEL IN CYLINDERSDR 96ZZZX2646Cam · crackedENGINE RAN ROUGH AND BACK-FIRED CAUSING THE PILOT TO MAKE AN EMERGENCY LANDING. THE ENGINE (FRONT) WAS DISASSEMBLED FINDING THE CAM CRACKED.SDR 96ZZZX2992Lifter Body · collapsed45.9 HOURS AFTER OVERHAUL, PILOT FLYING AN X-C EXPERIENCED VERY ROUGH ENGINE. AFTER TROUBLESHOOTING ALL POSSIBLE ASPECTS, FOUND NR 2 CYLINDER EXHAUST HYDRAULIC LIFTER COLLAPSED AND DAMAGED PUSH ROD. A NEW LIFTER AND PUSH ROD WAS INSTALLED. OPS CHECK WAS PERSDR AU960719Tappet · failed(AUS) RH ENGINE NO4 CYLINDER EXHAUST TAPPET BODY FAILED ALLOWING EXHAUST VALVE TO REMAIN CLOSEDSDR AU960580Camshaft · wrong part(AUS) CAMSHAFT SUSPECT FAULTY - COMPARISON WITH A NEW ITEM FOUND THAT THE CAM PROFILE WAS DIFFERENT - INVESTIGATION FOUND THAT THE CAMSHAFT WAS MARKED IN SMALL LETTERS WITH THE PNO LW18837-85 BUT WAS ALSO MARKED WITH THE PNO 76097 WHICH IS THE PART NUMBER FORSDR 96ZZZX3377Rod Bolt · failedTAKEOFF FROM BUF TO UTICA, NY, PILOT REPORTED FLUX IN OIL PRESSURE LT ENGINE, FOLLOWED BY ZERO OIL PRESSURE. UNEVENTFUL DIVERT TO ROC. INVESTIGATION FOUND .75 INCH HOLE IN CRANKCASE JUST UNDER THE DATA PLATE. CYLINDER REMOVAL FOUND THE NR 3 ROD AND CAP SEPASDR 96ZZZM1011Engine · crackedRIGHT ENGINE OIL LEAK.SDR CA960530001Crankcase · cracked(CAN)CRANKCASE CRACKED AT #3 CYLINDER POSITION.SDR CA960423104Cylinder · detached(CAN)ON FINAL APPROACH, #2 ENGINE BEGAN TO RUN ROUGH, IDLE POWER SELECTED AND LANDED OK. #9 CYLINDER BROKE AWAY FROM CRANKCASE. SEVERAL MOUNTING STUDS PULLED.SDR CA960222201Main Bearing · fretted(CAN) DURING CRUISE ENGINE STARTED TO VIBRATE AND THEN STOPPED. AIRCRAFT RETURNED TO ORIGIN AND LANDED SAFELY. IT WAS DISCOVERED THAT ENGINE HAD STOPPED DUE TO #2 MAIN BEARING FAILURE. TEARDOWN REVEALED THAT THE #2 BEARING HAD TURNED IN THE CRANKCASE STOPPING SDR AU960552Tappet · spalled(AUS) NO1 AND NO2 CYLINDER TAPPET BODIES PNO LW72877 SPALLED - CAMSHAFT PNO LW18840 FORWARD LOBE WORNSDR 96ZZZX3657Case · crackedLEFT ENGINE OIL LEAK.SDR CA960409026Crankcase · cracked(CAN)AN OIL LEAK ON THE RIGHT HAND ENGINE WAS REPORTED. A SUBSEQUENT INSPECTION REVEALED A CRACK IN THE CRANKCASE APPROXIMATELY 3 1/2" LONG, FORWARD OF THE #5 CYLINDER. THE CAUSE OF THE CRACK IS NOT KNOWN.ENGINE REPLACED AND AIRCRAFT RETURNED TO SERVICE.SDR AU960479Crankshaft · broken(AUS) ENGINE CRANKSHAFT BROKEN AT NO9 CHEEKSDR 96ZZZX2875Crankshaft · brokenSIXTY-FIVE PERCENT POWER IN LEVEL FLIGHT, IFR CONDITIONS. CRANKSHAFT BROKE AT FIRST MAIN BEARING AFT NOSE BEARING THROUGH CHEEK. CRANKSHAFT TOTAL TIME, 2,301 HOURS. INSPECTED, MAGNAFLUXED, AND PERFORMED ULTRASONIC INSPECTION AT 1,485 HOURS. SUSPECT FATIGUESDR 96ZZZX2189Connect Rod · bolt not markedENGINE DISASSEMBLED AND FOUND 3 BOLTS WITH NO HEAD MARKING. ONE EACH LOCATED ON NR 6 ROD. TWO EACH LOCATED ON NR 1 ROD.SDR 96ZZZX1714Stud Nut · crackedTWELVE-POINT NUT ON THROUGH-BOLT, PN 641931-10.75, CRACKED. NUT IS LOWER FORWARD NUT ON NR 6 CYLINDER. SUBMITTER RECOMMENDS USING 6-POINT NUT ONLY.SDR AU960447Crankcase · defective(AUS) DURING RECIFICATION FOR A LEAKING PUSHROD TUBE AND REPLACEMENT OF NO1 CYLINDER, A LOWER CRANKCASE THROUGH STUD PULLED OUT - THE CRANK CASE WAS SPLIT AND IT WAS THEN FOUND THE FRONT BEARING HOUSING WAS 0.0010IN OUT OF ROUND AND THE MIDDLE HOUSING WAS +0.0SDR AU960391Cam Follower · worn(AUS) LH AND RH ENGINE CAM FOLLOWERS WORN BEYOND LIMITS - LH ENGINE CAMSHAFT REQUIRES REPLACEMENT - BOTH ENGINES HAVE HAD LW16702ADDITIVE IAW SB 446B AND OIL CHANGE EACH 50 HOURS SINCE OVERHAULSDR AU960390Camshaft · worn(AUS) ENGINE CAMSHAFT LOBES WORN - FOUND DURING PERIODIC INSPECTIONSDR AU960336Crankcase · cracked(AUS) CRANKCASE CRACKED FROM NO6 CYLINDER TOP REAR STUD - FURTHER INVESTIGATION FOUND CRANKCASE WAS CRACKED IN FOUR AREAS -CRACKING CAUSED BY THERMAL STRESS DUE TO POWER AND TEMPERATURE LOADS IMPOSED DURING FLIGHT TRAININGSDR AU960268Crankshaft · worn(AUS) ENGINE CONTAINED NUMEROUS DEFICIENCIES MAKING IT UNSERVICEABLE FOR USE: 1. CRANKSHAFT 0.0254MM TO 0.0508MM (0.001IN TO 0.002IN) UNDER MINIMUM LIMITS2. CRANKCASE MAIN TUNNELS 0.0254MM TO 0.0508MM (0.001IN TO0.002IN) OUT OF LIMITS3. CYLINDERS (3OFF) REQUIRSDR 96ZZZX1535Crankshaft · crackedWHILE CONDUCTING AN ANNUAL INSPECTION, DISCOVERED SEVERAL SUSPICIOUS BROWN STAINS. AREA WAS CLEANED AND A DYE PENTRANT INSPECTION PERFORMED. CRACKS WERE FOUND RADIATING CIRCUMFERENTIALLY AROUND CRANKSHAFT AND FLANGE IN THE AREA OF THE FLANGE RADIUS. PROP HASDR 98ZZZX4451Valve Guide · wornDURING A ROUTINE COMPRESSION CHECK, THE EXHAUST VALVE WAS FOUND LEAKING ON THE NR 5 CYLINDER. THE REMOVED CYLINDER, EXHAUST VALVE AND GUIDE WERE FOUND WORN OUT. SUBMITTER SUGGESTED CAUSE AS DEFECTIVE PARTS AND/OR ASSEMBLY PROCESS FROM THE FACTORY.SDR CA960327005Crankcase · cracked(CAN) ON INSPECTION, A CRACK WAS NOTICED ON THE LEFT SIDE UNDER THE OIL FILLER. IT WAS 2 INCHES LONG AND WENT TOWARDS THE SECOND CYLINDER BASE.SDR AU960443Crankshaft · worn(AUS) ENGINE SUFFERED TWO CRANKSHAFT MAIN BEARING EXCESSIVE WEAR INCIDENTS IN APPROXIMATELY 50 HOURS OPERATION: 1. FIRST OCCURRENCE WAS AT 8.5 HOURS AFTER INSTALLATION FOLLOWING OVERHAUL - ENGINE WAS INSPECTED/CHECKED, NEW BEARINGS AND A USED SERVICEABLE CRANSDR 96ZZZX2066Crankshaft · failedAFTER TAKEOFF WHILE IN LEVEL FLIGHT, THE PILOT EXPERIENCED A SUDDEN ENGINE SEIZURE ON THE RT ENGINE. AN UNEVENTFUL LANDING WAS MADE. THE CRANK WAS FOUND BROKEN AT THE NR 3 MAIN BEARING SADDLE BETWEEN THE NR 4 AND NR 5 ROD THROW. THERE WAS CATASTROPHIC DAMAGSDR 96ZZZX1782Connecting Rod · failedCONNECTING ROD NR 1 CYLINDER FAILED AND CAME THROUGH THE CASE. THE ROD BEARING HAD NOT SPUN, THE ONLY ROD BOLT FOUND APPEARED TO HAVE FAILED AFTER THE FACT.SDR CA960311002Crankshaft · off centre(CAN) THE CRANKSHAFT WAS REMOVED FOR REPAIR OF CORROSION IN ACCORDANCE WITH LYCOMING MSB 505A. THE CENTRE-BORE IN THE FRONT MAIN BEARING AREA WAS FOUND TO BE OFF CENTRE BY APPROXIMATELY 0.050 INCHES. THE AMO RECEIVED APPROVAL TO REPAIR THE CORROSION BY GRINDINSDR 96ZZZX1559Crankcase · crackedENGINE CRANKCASE 1157-21 DEFECTIVE DUE TO CRACKS AFT OF NR 2 CYLINDER. ALSO, NR 2 AND NR 3 BEARING SADDLES HAVE CRACKS. CRANKCASE PN 643202 MODIFIED TO 1157-21 PER STC SE 3630SW.SDR 96ZZZX1467Rod Bolt · failedNR 4 TOP ROD BOLT FAILED IN-FLIGHT. SEE AD NOTE 95-7-1 TW SMITH SENT LETTER TO SATISFY AD, THAT BOLT WAS NOT INSTALLED AT ENGINE OVERHAUL. TIME SINCE O/H WAS ABOUT 120 HRS.SDR AU960316Crankcase · cracked(AUS) LH ENGINE CRANKCASE CRACKED - CRACK STARTED ABOVE AND FORWARD OF NO5 CYLINDER AND EXTENDED DOWNWARDS TO THE ALTERNATOR ATTACHMENT PAD - VISIBLE CRACK LENGTH 110MM (4.33IN)SDR CA960328010Camshaft · spalled(CAN) DURING INSPECTION AND UPON DISMANTLING, #5 AND #1 EXHAUST LOBE, AND #3 AND #4 INTAKE LOBES ON CAMSHAFT WERE SPALLED. THE LIFTERS CONTACTING THE SPALLED LOBES WERE ALSO SPALLED. #2 EXHAUST LIFTER, #4 EXHAUST LIFTER AND #6 INTAKE LIFTER WERE CORROSIVELY PISDR CA960328009Camshaft · spalled(CAN) DURING INSPECTION AND UPON DISMANTLING, #3 & #4 INTAKE LOBES, #5 EXHAUST LOBE, AND #5 & #6 INTAKE LOBES ON CAMSHAFT WERE SPALLED. TWO LOBES WERE SPALLED OVER ENTIRE FACE AND TWO WERE SPALLED ONLY IN THE CENTRE. TWO LIFTERS WERE CORRODED BADLY. ALL MAIN BSDR CA960311015Gear · chipped(CAN) DURING INSPECTION, METAL CHIPS FOUND IN ENGINE PORTION OF OIL SUMP. DETERMINED TO BE PART OF UNKNOWN GEAR TOOTH. METAL IDENTIFIED TO BE BLOWER INTERMEDIATE GEAR. BLOWER SECTION REMOVED TO CONFIRM FINDING.SDR AU960273Cam Follower · failed(AUS) ENGINE CAM FOLLOWERS FAILED - SEVERE INTERNAL DAMAGE TO ENGINE - METAL CONTAMINATION OF OIL SYSTEMSDR 96ZZZX4933Crankshaft · corrosion pitsENGINE DISASSEMBLED AT O/H, CRANKSHAFT INSPECTED. FRONT MAIN ID FND WITH NUMEROUS CORROSION PITS, APPROX 2.0 INCHES AFT OF FRONT EDGE OF FLANGE PILOT. CRANK ASSY LW 17676, SN V721 (CRANK AND BUSHING SUBASSY LW17622) HAS ALWAYS OPERATED WITH CONSTANT-SPEED PSDR CA960321006Studs · broken(CAN) DURING CRUISE FLIGHT, RIGHT ENGINE BEGAN TO RUN ROUGH. INVESTIGATION REVEALED 4 BROKEN STUDS 1-P/N 5015, 2-P/N 38-13, 1-P/N 69679 ON THE BOTTOM FLANGE OF #5 CYLINDER. MOVEMENT OF THE CYLINDER CAUSED THE INDUCTION PIPE SEAL P/N 72711 TO DISLOCATE, CAUSING
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