JASC 8530
Service difficulty reports · 4,342
Reports filed under 8530 · Reciprocating Engine Cylinder 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 = '8530' 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 = '8530' 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 CA951206005Cylinder · cracked(CAN) PILOT REPORTED SUDDEN ROUGHNESS IN ENGINE DURING CRUISE FLIGHT. POST-FLI GHT INSPECTION FOUND NR 2 CYLINDER TO BE CRACKED CIRCUMFERENCIALLY IN THE ALLOY HEAD MATERIAL WHERE IT JOINS WITH THE STEEL BARREL. WITH THE NR 2 CYLINDER REM OVED THE CRACK WAS FSDR 96ZZZX2859Cylinder · crackedCYLINDER CRACKED COMPLETELY AT EXHAUST ROCKER ARM. THE ROCKER ARM CEASED TO FUNCTION THROWING THE FLOATING CAM RING OUT OF TIME. ENGINE QUIT, LANDED IN ROAD, CHANGED CYLINDER, FLEW HOME. SUSPECT POSSIBLE OVER-TORQUING OF ROCKER ARM SHAFT OR STUCK EXHAUST VASDR 95ZZZX7008Push Rod · crackedFOUND BALL END IN PUSH ROD LOOSE AND PUSH ROD TUBE CRACKED ABOUT .75 INCH ON SAME END.SDR 96ZZZX585Cylinder · crackedDURING 100-HOUR INSPECTION OF ENGINE, A FACTORY REMANUFACTURE WITH 100 HOURS ON IT, A CRACK OR CASTING FLAW WAS DISCOVERED NEAR THE INTAKE FLANGE AREA, APPROXIMATELY .75 INCH DOWN FROM THE INTAKE FLANGE TOWARDS THE FIN AREA WHERE THE FINS MEET THE INTAKE PORT SDR 96ZZZX478Push Rod · damagedTHE PUSH ROD METAL INSERT ON THE VALVE END BECAME LOOSE. THIS ALLOWED THE INSERT TO POUND AGAINST THE METAL TUBE, CURLING THE METAL OVER, UNDER THE INSERT TO THE OUTSIDE.SDR 96ZZZX32Injector Tube · brokenPILOT REPORTED LT ENGINE RAN ROUGH & RPM WAS LOW ON TAKEOFF. TAKEOFF ABORTED. FOUND LT ENG, NR 4 CYL FUEL INJECTOR TUBE FROM FUEL MANIFOLD TO FUEL INJECTOR NOZZLE BROKEN AT SOLDERED FITTING ON MANIFOLD END OF TUBE. TUBE APPEARED TO HAVE BEEN PREVIOUSLY BENTSDR CA960103532Valve Seat · wrong depth(CAN)AFTER THE ENGINE WAS OVERHAULED, WITH SIX (6) NEW CYLINDERS FROM CONTINENTAL, THE ENGINE FAILED TO ACHIEVE FULL POWER ON THE POST INSPECTION/OVERHAUL RUN-UP. THE MAXIMUM RPM WAS 2700, INSTEAD OF THE REQUIRED 2850 RPM. TROUBLESHOOTING REVEALED THAT ONE OF SDR 96ZZZX3083Sleeve · air leakPILOT REPORTED HAVING A LOW FUEL FLOW INDICATION. INSPECTION REVEALED AN AIR LEAK IN THE UPPER DECK, NR 3 CYLINDER SLEEVE, WHERE THE SHAFT AND BLOCK CONNECT. SUBMITTER RECOMMENDS VISUAL INSPECTION AND IF NECESSARY, PART REPLACEMENT.SDR 95ZZZX7016Valve · separatedNR 3 CYLINDER EXHAUST VALVE SEPARATED THE STEM FROM THE HEAD. AIRCRAFT WAS FORCED TO LAND. ENGINE HAD GOOD HISTORY OF MAINTENANCE. THE ENGINE WAS NEW IN 1977. SUBMITTER SUGGESTS THE INDUSTRY SHOULD BE REQUIRED TO REMOVE THE EXHAUST SYSTEM AND INSPECT VALVESDR 95ZZZX6769Cylinder · glazedENGINE INSTALLED WITH NEW MILLENNIUM CYLINDERS DURING MAJOR OVERHAUL. COMPRESSION CHECKS AFTER 100.5 HOURS REVEALED NR 1 - 52 PSI, NR 2 - 64 PSI, NR 3 - 52 PSI, NR 4 - 72 PSI. ALL CYLINDERS REMOVED FOR REHONING AND PISTONS RE-RINGED. SUBMITTER RECOMMENDS RSDR 96ZZZX4311Intake Tube · crackedFUEL STAINS WERE NOTED AROUND SEVERAL INTAKE TUBES. IN REMOVING THE COLLARS FROM THE CYLINDERS TO GAIN ACCESS TO THE INJECTORS, TWO OF THE INTAKE TUBES WERE FOUND CRACKED AROUND THE RADIUS OF THE FLANGE.SDR 95ZZZX6611Valve · burnedPILOT REPORTED LOSS OF RPM, ENGINE ROUGHNESS IN CRUISE FLIGHT, CONFIRMED BY EXTREMELY HOT INDICATION ON AIRCRAFT EGT SCANNER. NR 6 CYLINDER POSITION, FOUND NR 6 CYLINDER EXHAUST VALVE BURNED THROUGH, SEAT DETERIORATED BEYOND LIMITS. REMOVED NR 4 CYLINDER TO SDR 95ZZZX6610Cylinder · guide wornPILOT REPORTED LOSS OF RPM, ENGINE ROUGHNESS IN CRUISE FLIGHT, CONFIRMED BY EXTREMELY HOT INDICATION ON AIRCRAFT EGT SCANNER. NR 6 CYLINDER POSITION, FOUND NR 6 CYLINDER EXHAUST VALVE BURNED THROUGH, SEAT DETERIORATED BEYOND LIMITS. REMOVED NR 4 CYLINDER TO SDR 95ZZZX6776Cylinder Assy · corrodedINSPECTION FOUND CYLINDER ASSY WITH EXCESS RUST AND CORROSION AFTER 70 HOURS TT IN SERVICE. SUBMITTER STATES RUST IS DUE TO A NEW PROCESS CALLED 'MILLENNIUM CYLINDER' IN ADDITION TO IMPROPER PAINTED OR UNPAINTED CYLINDER ASSY.SDR 95ZZZX6548Piston · failedLOST OIL PRESSURE AND MADE FORCE LANDING, NO DAMAGE TO AIRCRAFT, PILOT OR PASSENGERS. FOUND PISTON FAILED.SDR DJSA950003Cylinder · crackedAIRCRAFT EN ROUTE FRM RWI TO PTK. RT ENGINE BACKFIRED AND RAN ROUGH. PRECAUTIONARY LANDING AT HLG WITHOUT INCIDENT. UPON INSPECTION, NR 11 CYLINDER ON NR 2 ENGINE WAS FOUND TO BE CRACKED. CHANGED CYLINDER. (X)SDR 96ZZZX49Valve · leakingAIRCRAFT WAS TAKING OFF, NOT GENERATING FULL POWER. NOTICED SLIGHT VIBRATION. RETURNED TO AIRPORT. VIBRATION INCREASED AS AIRCRAFT EXECUTED EMERGENCY LANDING AT AIRPORT. PERFORMED COMPRESSION CHECK, FOUND TO BE 20/80. REMOVED CYLINDER.SDR 95ZZZX6805Cylinder · rocker brokeTHIS CYLINDER WAS NOT WITHIN THE DIMENSIONAL SPECS REQUIRED IN AD 94-05-05, BUT WAS NOT REQUIRED TO BE INSPECTED UNTIL OVERHAUL. THE ROCKER BOSSES BROKE IN-FLIGHT, BUT A SAFE-ON-AIRPORT LANDING WAS MADE. SUBMITTER RECOMMENDS THAT AD 94-05-05 BE CHANGED TO RESDR 95ZZZX6573Valve · stuckSOME POWER LOSS WAS NOTED AFTER TAKEOFF WHEN EXHAUST VALVE STUCK. SUBMITTER SUGGESTS LYCOMING SERVICE BULLETINS BE COMPLIED WITH.SDR 95ZZZX6551Rocker Shaft · bolt shearedNR 2 CYLINDER VALVE COVER REMOVED FROM PUSHROD TUBE SEAL REPLACEMENT. FOUND FORWARD ROCKER SHAFT THROUGH-BOLT IN 3 PIECES. BOLT SHEARED FLUSH IN CYL HEAD, ALSO, INSIDE ROCKER SHAFT. APPROX .3125 INCH HOLE IN FWD SHAFT HOLDER WAS FND ENLARGED TO .50 INCH. ESDR 95ZZZX6552Guide · excess wearPILOT EXPERIENCED ROUGH ENGINE ON RUN-UP. PERFORMED COMPRESSION TEST AND FOUND CYLINDER NR 3 HAD ZERO COMPRESSION. UPON REMOVAL OF CYLINDER, FOUND EXHAUST VALVE MISSING APPROX ONE-THIRD OF FACE AREA. FURTHER INSP REVEALED EXCESSIVE WEAR OF GUIDE. OTHER FIVSDR 95ZZZX6767Cylinder · boss brokenEXHAUST VALVE INBOARD ROCKER ARM SHAFT BOSS BROKEN OFF CYLINDER ASSY. ROCKER ARM AND SHAFT LIFTED UP CRACKING CYLINDER ON OUTBOARD SIDE WHERE SHAFT PASSES THROUGH CYLINDER. SUBMITTER SUSPECTED DEFECTIVE CASTING AS THERE IS NO EVIDENCE OF PREVIOUS CRACK.SDR 95ZZZX6450Cylinder · departedNR 6 CYLINDER DEPARTED THE CASE. ALL THE CYLINDER BASE STUDS WERE BROKEN.SDR CA951120013Valve Guide · cracked(CAN) DURING DIFFERENTIAL COMPRESSION CHECK IT WAS FOUND THAT NR 3 CYLINDER HAD A SEVERE EXHAUST LEAK (20/80). AFTER REMOVAL AND INSPECTION OF THE NR 3 CYLINDER IT WAS REVEALED THAT THE EXHAUST VALVE GUIDE WAS CRACKED AND BADLY WORN AS A RESULT OF THE LONGITUSDR 97ZZZX12Valve Guide · excess wearNR 3 CYLINDER HAD POOR COMPRESSION. IN THE PROCESS OF REMOVING CYLINDER IT WAS NOTED THE ROCKER ARMS WERE INCORRECTLY INSTALLED. THE INTAKES WERE ON THE EXHAUST AND THE EXHAUST WAS ON THE INTAKE. IN CHECKING THE OTHER CYLINDERS, ALL THE REMAINING ROCKER ARMSSDR ERA00018Nr 3 Cylinder · lost valveLT ENGINE VIBRATION AND LEAKING OIL, SHUTDOWN ENGINE AND MADE UNEVENTFUL LANDING. REPLACED NR 3 CYLINDER.SDR 95ZZZX6402Cylinder · boss brokenNR 5 CYLINDER ON LT ENGINE INBOARD EXHAUST ROCKER SHAFT ARM BOSS BROKE OFF CYLINDER. NO EVIDENCE OF PREVIOUS CRACK. NO INDICATION OF VALVE CONTACTING PISTON. SUSPECT CASTING DEFECT AT MANUFACTURER.SDR 95ZZZX6386Cylinder · separatedDURING NORMAL TAKEOFF, OPERATOR EXPERIENCED SEVERE ROUGHNESS OF ENGINE. RETURNED TO AIRPORT. DURING TEAR DOWN OF ENGINE, FOUND NR 3 CYLINDER SEPARATED AT BARREL. CYLINDERS TORN DOWN 400 HOURS PRIOR FOR CHROME. SUBMITTER BELIEVES CYLINDER NOT REASSEMBLED COSDR 95ZZZX6546Valve · brokenENGINE - NR 3 EXHAUST VALVE BROKE (STEM INTACT) CAUSING ENGINE FAILURE AND RESULTNG IN EMERGENCY LANDING/ACCIDENT. ANNUAL INSPECTION ACCOMPLISHED OCTOBER 6, 1995. HAD NOT FLOWN FROM 6-26-91 THROUGH 6-26-95. FOUR YEARS OF INACTIVE FLIGHT TIME.SDR 96ZZZX481Rocker · boss failedPILOT OWNER DEPARTED HOME AIRPORT FOR ROUTINE SCENIC FLIGHT. AFTER ABOUT 20 MINUTES INTO CROSS-COUNTRY FLIGHT, ENGINE STARTED RUNNING ROUGH, CARBURETOR HEAT HAD NO EFFECT. RETURN HOME WITH PARTIAL POWER. INSPECTION OF NR 2 CYLINDER ROCKER REVEALED ALL FOUR SDR 95ZZZX6745Seal · leaksSHORTLY AFTER REPLACING A REPAIRED NR 5 CYLINDER, OIL LEAKS DEVELOPED AROUND OUTBOARD ENDS OF SHROUD TUBES. COMPARISON TO ORIGINAL TCM PARTS SHOWED REPLACEMENT SEAL TO BE LARGER IN OUTSIDE DIAMETER CAUSING SEAL NOT TO PROPERLY FIT IN MACHINED RECESS CAUSING LSDR 95ZZZX6537Pushrod · failedPUSHROD MARKED AS 73806# FAILED AT END OF PUSHROD. LYCOMING MANDATORY SB OA-522 IN CONJUNCTION WITH AD 95-03-10, WAS ACCOMPLISHED 2-16-95. NO DEFECTS IN ENGINE VALVE TRAIN OR VALVES STICKING WERE NOTED. PARTS WERE REPLACED AND ENGINE RAN OK AND RETURNED TO SDR 95ZZZX6570Cylinder · crackedLOSS OF POWER AND ENGINE ROUGHNESS WAS REPORTED. UPON INSPECTION, CYLINDER NR 2 WAS FOUND TO HAVE LOW COMPRESSION. FURTHER INSPECTION LED TO FINDING A CRACK APPROXIMATELY ONE-HALF WAY AROUND THE CIRCUMFERENCE OF THE CYLINDER BETWEEN THE FINS AT THE JUNCTION SDR 95ZZZX6417Rocker Shaft · wornDURING ROUTINE OIL CHANGE, OIL FILTER WAS FOUND CONTAMINATED WITH FERROUS MATERIAL. OIL ANALYSIS DETERMINED MATERIAL TO BE CASE HARDENED STEEL. UPON INSPECTION, FOUND SEVERE CORROSION IN CYLINDER WALLS, STARTER HOUSING, AND GEARS. ALSO, WORN ROCKER SHAFTS. SDR 95ZZZX6383Cylinder · crackedFOUND THREE CYLINDERS CRACKED BETWEEN THE SPARK PLUG AND INJECTOR HOLES. SUBMITTER STATED CRACKS MAY BE CAUSED BY OVERTORQUING THE INJECTOR NOZZLES OR POSSIBLY EXCESSIVE VIBRATION.SDR 95ZZZX6381Piston · wrong partFOUND 11 OUT OF 12 CYLINDERS WITH THIS P/N PISTON WHICH IS NOT APPROVED FOR USE IN GTSIO520 ENGINES. PISTONS WERE SENT FROM ECI AS PART OF A GTSIO-520 CYLINDER ASSY. P/N 632585 CYLINDER IS DOMED WITH NO STEEL INSERT FOR THE TOP RING GROOVE. THE CORRECT PISTSDR 95ZZZX6302Pushrod · looseDURING ROUTINE INSPECTION, A VALVE GUIDE CLEARANCE CHECK WAS DONE. THE NR 1 CYLINDER INTAKE PUSHROD WAS FOUND TO HAVE THE STEM LOOSE. IT COULD EASILY BE REMOVED BY HAND. THIS PART IS NORMALLY A PRESS-FIT AND IS NOT REMOVABLE. REPLACED WITH NEW.SDR 95ZZZX6616Cylinder · crackedINSTALLED CERMICHROME OHL CYLINDERS AT OVERHAUL. AT 350 SMOH, DETECTED AN OIL LEAK FROM THE HEAD-BARREL-JUNCTION. UPON REMOVAL, DETECTED A CIRCUMFERENTIAL CRACK 1.50 INCHES LONG, ONE INCH FROM THE TOP OF THE BARREL AT THE 12:00 POSITION.SDR 95ZZZX6609Cylinder · crackedINSTALLED CERMICHROME OHL CYLINDERS AT OVERHAUL. AT 50 SMOH, DETECTED A LEAK IN THE NR 4 CYLINDER-HEAD-BARRREL JUNCTION. UPON REMOVAL, OBSERVED A 11 INCH CIRCUMFERENTIAL CRACK 1 INCH FROM THE TOP OF THE BARREL AT THE 6:00 POSITION.SDR 95ZZZX6407Guide · excess wornOWNER REPORTED EXCESSIVE BLOW-BY. COMPRESSION CHECK NR 2 - 52/80 AND NR 4 - 50/80. EXHAUST VALVES LEAKING. PISTONS HEAVY WITH CARBON BUILD-UP. EXHAUST GUIDES WORN BEYOND TCM LIMITS. SUBMITTER STATES THIS IS 4 OUT 10 CYLINDERS INSTALLED, ALL WITH LESS THANSDR CA961112048Valve · worn(CAN) EXHAUST VALVE STEM FOUND WORN. SUSPECT BUILD UP OF CARBON POSSIBLY DUE TO A COMBINATION 100 LOW LEAD FUEL AND SYNTHETIC OIL USAGE. TECHNICAL BULLETIN 912-13 ADDRESSES THIS PROBLEM.SDR 96ZZZX386Guide · wornINSTALLED 4 NEW TCM POWER PACKS. AFTER 24 HOURS, LOST COMPRESSION ON TWO CYLINDERS. VALVE GUIDES OUT OF LIMITS.SDR 96ZZZX385Guide · wornINSTALLED 6 RECONDITIONED CHROME UNITS BY DIVCO. AFTER 110 HOURS, LOST COMPRESSION IN TWO CYLINDER GUIDES WORN BEYOND LIMITS.SDR 96ZZZX384Guide · wornONE YEAR AGO INSTALLED 4 NEW TCM POWER PACKS. DROPPED COMPRESSION ON ONE EXHAUST VALVE AFTER 300 HOURS. WORN GUIDE WAS AT FAULT.SDR 96ZZZX383Guide · wornINSTALLED 6 CERMICHROME CYLINDER REBUILT UNITS WITH 643767 GUIDES. 120 SMOA. COMPRESSION LEAK ON TWO CYLINDERS. PULLED ALL 6 AND RETURNED UNITS TO ECI. THEY DIAGNOSED AS JUST WORN OUT. THEY REPAIRED SAME AND SUGGESTED FULL FLOW LIFTERS AND DRILLED ROCKERSSDR 96ZZZX382Guide · wornINSTALLED 6 NEW SUPERIOR MILLENIUM CYLINDERS. THREE CYLINDERS LOST COMPRESSION WITHIN 24 HOURS. PULLED ALL 6 CYLINDERS. ALL 6 EXHAUST GUIDES WORN BEYOND SERVICE LIMITS. THESE WERE THEIR 'POWER PACKS'. PRE-ASSEMBLED WITH NEW VALVES, SPRINGS, PISTONS, ETC.SDR 95ZZZX6803Cylinder Assy · crackedENGINE OPERATION NORMAL ON TAKEOFF, CLIMB, AND CRUISE SETTING. ROUGHLY 15 MINUTES INTO FLIGHT, THE ENGINE LOST MANIFOLD PRESSURE. FULL THROTTLE MANIFOLD PRESSURE WAS 25 INCHES. PILOT LANDED WITHOUT INCIDENT. INSPECTION FOUND THE NR 4 CYLINDER HAD CRACKED OSDR 95ZZZX6175Cylinder · crackedROUGHLY 15 MINUTES INTO FLIGHT, THE ENGINE LOST MANIFOLD PRESSURE. MAXIMUM M/P WAS 25 INCHES. INSPECTION FOUND THE NR 4 CYLINDER CRACKED AND STARTING TO MELT THE NR 6 CYLINDER.SDR CA951122017Valve · broken(CAN)PILOT REPORTED A ROUGH RUNNING ENGINE ON APPRAOCH. POST FLIGHT INVESTIGATION REVEALED ONE OF THE EXHAUST VALVES HAD FRACTURED AND SEPARATED FROM ITS STEM AND DESTROYED THE PISTON CROWN AND CYLINDER CA P. THE EXHAUST VALVES ON ALL CYLINDERS INDICATED A "TUSDR 95ZZZX6163Cylinder · crackedENGINE BECAME ROUGH DURING FLIGHT. UPON LANDING AND INSPECTION, IT WAS DETERMINED THAT CYLINDER NR 4 WOULD NOT PASS CYLINDER LEAKAGE TEST. AFTER FURTHER INSPECTION, CYLINDER WAS FOUND TO BE CRACKED ONE-HALF WAY AROUND CIRCUMFERENCE BETWEEN FINS AT JUNCTION O
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