Lycoming IO-360-A1B
Service difficulty reports · 33
Newest first. General aviation reporting is voluntary.
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 engine_model_key = 'IO360A1B' 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 engine_model_key = 'IO360A1B' 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 CA151124009Oil Filter · damaged(CAN) DURING THE ANNUAL INSPECTION THE OIL FILTER WAS REMOVED AND CUT OPEN FOR INSPECTION AND THE FILTER INTERIOR WAS FOUND TO BE BENT. THERE WAS NO DAMAGE TO THE EXTERNAL CAN OF THE FILTER, AND IT DID NOT APPEAR TO AFFECT THE FILTRATION OF THE OIL.SDR CA150604015Contact · loose(CAN) ENGINE WAS A RECENTLY REBUILT, FACTORY ENG WITH ABOUT 100 HOURS IN SERVICE. WHILE RUNNING UP THE ENG AFTER REFUELING, PERFORMED A MAGNETO DROP CHECK & THE ENG RAN ROUGH ON THE RT MAG. IT HAD BEEN OPERATING FINE UP UNTIL THIS TIME. THEN CHECKED THE TIMSDR 2013FA0000589Tube · crackedDURING ANNUAL INSPECTION, DISCOVERED A CIRCUMFERENTIAL CRACK WHERE AIRBOX OUTLET TUBE IS WELDED TO AIRBOX. CRACK EXTENDED AROUND .33 OF THE CIRCUMFERENCE OF THIS WELD.SDR 2012FA0000357Servo · defectiveWITH AFFECTED FUEL INJECTION SERVO INSTALLED ON ENGINES, ENGINE DOES NOT ACCELERATE THOUGH THE 1950-2000 RPM RANGE.SDR CA111028007Pushrod · corroded(CAN) ALUM ROD WAS BEING REMOVED TO REPLACE SOME CORRODED BLIND FASTENERS AT THE LOWER END FITTING (FIXED-END, STEEL FITTING). WHEN IT WAS DISCOVERED THE ALUMINUM TUBE WAS CORRODED APPROX 45 PERCENT AROUND THE CIRCUMFRENCE OF THE ROD, AT THE END OF THE STEEL SDR CA100121001Control Cable · worn(CAN) THE AILERON CABLES ON LAKE ACFT, MODELS, LA-4, -200, -250 HAVE BEEN FOUND WEARING AT FUS STA 117 0N LA-4, 200`S AND FUS STA 176 ON LA-250 WRE THE CABLE CONTACTS THE PHENOLIC FAIRLEAD. THE WEAR OF THESE CABLES IS DEPICTED IN AC43.13-1B, CHAP. 7, PG7-36, FSDR 2005FA0001514Bulkhead · crackedBULKHEAD CRACKED AROUND BOTH VERTICAL FIN FORWARD ATTACH BOLTS.SDR CA050908002Line · obstructed(CAN) NOSE GEAR FAILED TO LOCK DOWN DUE TO A PLUGGED RETURN LINE ORIFACE, ACTUATOR REMOVED/DISASSEMBLED/CLEANED/REASSEMBLED, REINSTALLED, HYDRAULIC SYSTEM FLUSHED, GEAR SWINGS COMPLETED. NO FAULTS FOUND.SDR 2004FA0000855Line · crackedDURING FLT, HYD PUMP STARTED TO CYCLE ABNORMALLY. IDENTIFIED HYDRAULIC PRESSURE LOSS TO LANDING GEAR RETRACT CIRCUIT AND ISOLATED WITH LDG GEAR SELECTOR. GEAR EXTENDED FOR LANDING NORMALLY. DURING POST INSPECTION FOR LEAK, LOCATED HYD TUBE AT AFT BULKHEAD STASDR 2004FA0000591Selector Valve · separatedDURING FLIGHT, THE FLT CREW MADE A FUEL TANK SELECTION CHANGE AND NOTICED THE FUEL WAS BURNING FROM THE PREVIOUS TANK EVEN THOUGH THE SELECTOR HAD BEEN MOVED TO THE NEW TANK. AFTER LANDING, MAINTENANCE PERSONNEL FOUND THE FUEL SELECTOR SHAFT HAD BECOME SEPARATSDR AUS20040298Rod End · failed(AUS) RUDDER CONTROL ROD BALL JOINT SEIZED AND ROD END FAILED. THE SEIZED BALL JOINT ALLOWED THE CONTROL ROD END TO BEND UP AND DOWN DURING RUDDER APPLICATIONS UNTIL FINAL FAILURE.SDR AUS20030788Rivet · corroded(AUS) ELEVATOR PUSHROD AFT END FITTING RIVETS CORRODED. END FITTING SEPARATED FROM PUSHROD CAUSING LOSS OF CONTROL CAUSING DAMAGE TO AIRCRAFT DURING HEAVY LANDING.SDR AUS20030896Mount · wrong part(AUS) INCORRECT ENGINE MOUNTS FITTED. MANUFACTURER'S ILLUSTRATED PARTS CATALOGUE (IPC) INDICATES INCORRECT NUMBER. CORRECT PART NUMBER AND INSTALLATION PROCEDURES ARE FOUND IN THE MM. IPC INCORRECT.SDR CA020826008Doubler · cracked(CAN) LT WING LOWER SPAR CAP DOUBLER CRACKED AT OUTER BOLT HOLE.SDR CA020827009Hub · corroded(CAN) CORROSION ON HUB IN O-RING SEAL AREA. BALL WEAR ON BLADE BEARING. CHROME WORN THRU TO BASE METAL ON PITCH CHANGE ROD.SDR CA020606005Motor · worn(CAN) NOISE IN FLAP MOTOR CAUSED FURTHER INSPECTION. UPON ACCESSING MOTOR UNDER REAR SEAT, SPARKS WERE NOTED COMING OUT OF DRIVE AND OF MOTOR DURING ACTUATION. ARMATURE MOTOR BUSHINGS WERE WORN TO THE EXTENT THAT THERE WAS CONTACT WITH THE END PLATE DURING OPESDR AUS20020259Mount · corroded(AUS) STABILATOR MOUNTING BLOCK RIVETS SHEARED. INVESTIGATION FOUND THE UNDERSIDE OF THE ATTACHMENT BLOCK BADLY CORRODED AND THE RIVETS CORRODED.SDR CA011031021Attach Fitting · mismanufactured(CAN) AD 98-10-12, HORIZONTAL STAB ATTACHMENT FITTING NO OF NEW CUSTOMERS A/C HAVE BEEN INSPECTED AT COMPANY & ARE NOT IN COMPLIANCE WITH AD, ALTHOUGH ITS BEEN PREVIOUSLY SIGNED OFF. MOST INSPECTIONS REVEAL THAT CLEARANCE I S LESS THAN THE REQUIRED 5/32 INCH. SDR 20010326CW006Valve · wornEMERGENCY GEAR EXTENSION VALVE WAS OPENED DURING EMERGENCY GEAR EXTENSION TRAINING. THE NOSE GEAR FAILED TO FULLY EXTEND. THE VALVE WAS CLOSED AND NORMAL GEAR EXTENSION WAS ATTEMPTED. THE NOSE GEAR FAILED TO EXTEND. AFTER LANDING WITH THE NOSE GEAR TRAILINSDR CA990804034Spar · hole oversized(CAN) REQUIRED WASHERS NOT INSTALLED BETWEEN BUSHING AND FUSELAGE FITTING. THIS ALLOWED BUSHING TO MOVE FORWARD. BECAUSE THERE WAS NOT ENOUGH BEARING SURFACE, THIS ALLOWED BUSHING TO ENLARGE HOLE IN SPAR AND FILLER CAUSING CRACKS TO RADIATE FROM HOLE AND ALLSDR CA990804033Spar · hole oversized(CAN) WASHERS ARE REQUIRED BETWEEN BUSHING AND FUSELAGE ATTACH FITTING TO HOLD BUSHING IN PLACE. THESE WASHERS WERE MISSING AND ALLOWED THE BUSHING TO MOVE FORWARD. THERE WAS NOT ENOUGH BEARING SURFACE AVAILABLE, SO THE BUSHING MOVED ENLARGING THE HOLE IN THSDR 99ZZZX1560Gasket · wrong partDURING 100-HOUR ANNUAL INSPECTION, MAGNETO TYPE BENDIX D2000 SERIES REMOVED FOR CONTACT BREAKER REPLACEMENT AND INTERNAL TIMING CHECK. MAGNETO REFITTING WITH LYCOMING GASKET P/N 62224 INSTEAD OF LW-12681. THE MAGNETO BECAME LOOSE AND BACKED OFF FROM THE ENGISDR CA981006015Hub · corroded(CAN) PROPELLER RECEIVED FOR CORROSION INSPECTION. INSPECTION FOUND THE HUB CORRODED. THE SUBMITTER STATES THAT THE LAST CORROSION INSPECTION, WHICH WAS IN 1988, REQUIRED REWORK TO THE MAXIMUM LIMITS DUE TO THE LACK OF INSPECTION AT THE SCHEDULED TIME.SDR AU980847Mount · cracked(AUS) RIGHT LOWER ENGINE MOUNT TUBE CRACKED.SDR CA980519011Hub · lack of lube(CAN) PROPELLER RECEIVED FOR CORROSION INSPECTION. INSPECTION FOUND THE PROPELLER HUB REAR BORE TO BE OVERSIZE. THE CONTROL FORK TO BE OVERSIZE. THE PISTON TO BE UNDERSIZE. THESE CONDITIONS ARE A RESULT OF LACK OF LUBRICATION. THE HUB HAD NOT BEEN GREASED.SDR CA980504011Blade · damaged(CAN) PROPELLER RECEIVED FOR CORROSION INSPECTION. BOTH PROPELLER BLADES WERE FOUND BADLY NICKED FROM FOD. FIELD REPAIRS WERE NOT MADE IN ACCORDANCE WITH THE HARTZELL MANUAL.SDR CA971031003Cylinder · worn(CAN) PROPELLER RECEIVED FOR CORROSION INSPECTION. CYLINDER FOUND WORN AND WAS REPLACED. THE PROPELLER BLADE (P/N S78FBM-1.5) WAS FOUND NICKED ON THE LEADING EDGE AND THE FACE AND WAS TRIMMED.SDR CA970506007Blade · damaged(CAN) PROPELLER RECEIVED FOR CORROSION INSPECTION. #1 PROPELLER BLADE HAD DAMAGE TO THE FACE SIDE DUE TO BOLT OR SCREW DAMAGE WHICH WAS NOT DRESSED OUT, WHEN PROPELLER WAS RECEIVED FOR INSPECTION.SDR CA970407006Blade · eroded(CAN) PROPELLER RECEIVED FOR CORROSION INSPECTION. BLADE LEADING EDGE ERODED/CORRODED. FILING AND DRESSING OUT REQUIRED.SDR CA970407007Fork · worn out(CAN) INSPECTION FOUND PROPELLER FORK WORN.SDR 96ZZZX4398Impulse Cam · wornINSPECTED MAGNETO RIVETED CAM ASSY AND FOUND WORN BEYOND 'X' PLUS .014 INCH. SUBMITTER STATES THESE EARLY RIVETED UNITS SHOULD BE CHANGED OUT TO THE SNAP RING STYLE AT 500 HOURS. NEW STYLE FOR THIS APPLICATION IS 10-400167-9.SDR CA960222007Elbow · cracked(CAN) SLIGHT OIL LEAK NOTED AT #1 CYLINDER. FOUND OIL RETURN FITTING ON CYLINDER HEAD CRACKED AROUND 90 PERCENT OF THE CIRCUMFERENCE AT PIPE THREADS FLUSH WITH BOSS.SDR 95ZZZX2316Ring · defectiveAFTER 2-HOUR TEST RUN, NR 1 CYLINDER WAS STILL BURNING OIL AND HAD NOT SEATED. INSPECTION OF THE CYLINDER FOUND CHROME HAD CHIPPED OFF THE EDGE OF THE RING AT THE GAP. IT APPEARS TO BE A MANUFACTURING DEFECT.
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