Lycoming O-320-D2A
Service difficulty reports · 67
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 = 'O320D2A' 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 = 'O320D2A' 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 PO4R2016FA0000012Cylinder Head · separated2 SECONDS AFTER FULL POWER APPLICATION FOR TAKEOFF, A LOUD BANG WAS HEARD AND THE PILOT DETECTED SIGNIFICANT VIBRATION IMMEDIATELY. PILOT ABORTED TAKEOFF, LIMPED TO PARKING AND SHUTDOWN. VISUAL INSPECTION REVEALED NR 3 CYLINDER HEAD SEPARATION CONSISTENT WITSDR CA121205007Elt · no test(CAN) WHILE TESTING THE ELT ON ITS ANNUAL CERTIFICATION IAW CAR 571, APPENDIX-G THE TRANSMITTING POWER OF THE UNIT STARTED. OK, BUT WITHIN THE 3 MINUTES THE TRANSMITTING POWER DROPPED WELL BELOW SPECIFICATIONS. ELT REMOVED FROM SERVICE.SDR 2011FA0000367Attach Fitting · brokenDURING REMOVAL OF INTERIOR UPHOLSTERY FOR OTHER MX, FOUND THAT THE LT FORWARD OTBD MLG ATTACHMENT BOLT FITTING THAT IS PART OF THE TUBE FUSELAGE WAS BROKEN COMPLETELY THROUGH ON BOTH SIDES. THIS FITTING IS A BUSHING THAT IS WELDED TO THE FUSELAGE TUBE THAT ATTSDR 2010FA0000460Pressure Switch · bindingLANDING GEAR DID NOT EXTEND AND GEAR-UP LANDING WAS MADE. POST INCIDENT INSPECTION AND OPERATION CHECK DEMONSTRATED REPEATABLE FAILURE CONDITION. HYDRAULIC PRESURE SWITCH WAS SHOWN A SOURCE OF FAILURE.SDR CA100625004Crankshaft · broken(CAN) ON FEB 28/10, DURING CRUISE FLIGHT ENGINE DEVELOPED A VIBRATION FOLLOWED WITHIN SECONDS BY A TOTAL SEIZURE. AIRCRAFT WAS LANDED WITHOUT INJURY TO PILOT OR PASSENGER BUT TOTAL LOSS OF AIRFRAME. DISASSEMBLY OF ENGINE REVEALED THE CRANKSHAFT HAD FRACTUREDSDR 2008FA0000544Alternator · failedALTERNATOR WILL FAIL ABOVE 2500 RPM, LOW VOLTAGE LIGHT COMES ON AND THE VOLTMETER INDICATES BATTERY VOLTAGE. OPS CHECK DURING GROUND RUNS ARE NORMAL MAX RPM DURING GROUND RUN 2400 RPM. ALTERNATOR APPEARS TO BE RPM SENSITIVE. POSSIBLE CAUSE: BRUSHES NOT RIDINGSDR 2007FA0000784Float · failedTHE ENGINE DIED ON FINAL TO AIRPORT, PUMPED THE THROTTLE, AND THE ENGINE STARTED RUNNING AGAIN, RETARDED THROTTLE, AND THE ENGINE DIED AGAIN. LANDED WITHOUT INCIDENT. COULD NOT GET THE ENGINE TO RESTART ON THE GROUND. ENGINE WAS STARTED THE NEXT DAY, THE FUSDR CA060426001Mount · damaged(CAN) INSPECTION FOR ISSUANCE OF A C OF A AIRCRAFT TOTAL TIME: 2.8 HRS DURING THE INSPECITON OF THIS AIRCRAFT BY CIVIL AVIATION INSPECTOR, IT WAS NOTED THAT AN ENGINE CONTROL SUPPORT BRACKET WAS CONTACTING THE LOWER TUBE OF THE ENGINE MOUNT. NO DAMAGE TO THE SDR CA040823004Carburetor · failed(CAN) DURING A LOCAL FLIGHT, PILOT REPORTED THAT THE THROTTLE WAS BINDING. AIRCRAFT LANDED SAFELY. THE MAINTENANCE INVESTIGATION INDICATED THAT THE CARBURETOR BUTTERFLY VALVE WAS EXTREMELY STIFF. THIS CARBURETOR WAS INSTALLED PRIOR TO THIS FLIGHT AND UPON RUN SDR CA031028004Volt Regulator · failed(CAN) VOLTAGE REGULATOR FAILED AND ALSO CAUSED DAMAGE TO THE ALTERNATOR DIODES. THE ALTERNATOR DIODES WERE REPLACED, AND THE VOLTAGE REGULATOR REPLACED WITH A NEW VR200A UNIT. CHARGING SYSTEM TESTED OK.SDR CA030409014Bellcrank · cracked(CAN) FOUND BRACKET CRACKED FOR A LENGTH OF ABOUT 2 CENTIMETERS JUST BELOW FORWARD BOLT HOLE. DEFECT CAN ONLY BE SEEN WITH INSPECTION MIRROR FROM OUTBOARD INSPECTION HOLE.SDR AUS20021166Mount · cracked(AUS) ENGINE MOUNT CRACKED IN SEVERAL AREAS. FURTHER INSPECTION FOUND BOTH LOWER ENGINE MOUNT BRACKETS LOCATED BEHIND THE FIREWALL ALSO CRACKED. LH AND RH TOP FUSELAGE SKINS REMOVED FOR INSPECTION ANDLH TOP MOUNT STRUCTURE FOUND CRACKED. LH RUDDER BAR ATTACHMESDR CA020917005Rod End · broken(CAN) ON A SCHEDULED MAINTENANCE INSPECTION THE RT AILERON SWIVEL ROD END WAS FOUND STIFF. ON FURTHER INSPECTION THE BEARING RACE WAS FOUND BROKEN AND SOME OF THE BALL BEARINGS WERE MISSING.SDR AUS20020725Gear · stripped(AUS) RH MAGNETO DISTRIBUTOR GEAR HAD FIFTEEN TEETH STRIPPED.SDR AUS20020726Exhaust Valve · cracked(AUS) NO3 CYLINDER EXHAUST VALVE HEAD CRACKED AND BURNT.SDR AUS20020475Spark Plug · fouled(AUS) NR 4 CYLINDER SPARK PLUGS FOULED.SDR AU010182Crankshaft · corroded(AUS) CRANKSHAFT INTERNAL BORE CORRODED. FOUND DURING INSPECTION IAWAD/LYC/102 AMDT2 PART 1 AND PART 2.SDR AU010184Pushrod · misinstalled(AUS) ENGINE PUSHRODS AND TAPPETS INCORRECTLY FITTED DURING ASSEMBLY FOLLOWING A BULK STRIP FOLLOWING A PROPELLER STRIKE. METAL CONTAMINATION OF ENGINE.SDR AU001323Fitting · cracked(AUS) RT WING REAR SPAR INBOARD ATTACHMENT BRACKET CRACKED. CRACKSAPPEAR TO INITIATE FROM THE ACCESS PANEL ON THE LOWER WING SKIN PANELS ARE NONSTANDARD ACCESS PANELS.SDR AU001324Fitting · cracked(AUS) LT WING REAR SPAR INBOARD ATTACHMENT BRACKET CRACKED. CRACKSAPPEAR TO INITIATE FROM THE ACCESS PANEL ON THE LOWER WING SKIN PANELS ARE NON STANDARD ACCESS PANELS.SDR CA000427020Wire · corroded(CAN) THE AUDIO SYS INVESTIGATED DUE TO REPEATED PROBLEMS RPTED BY PILOTS EVEN FOLLOWING MAINT CARRIED OUT. COMPLETE WIRING CHECKED FROM DASHBOARD TO HEADSET/PHONES & JACK. SHIELDING OF WIRE STRIPPED TO CHECK ITS CONDITION. IT OBSERVED THAT BARE WIRE STRANDSDR CA991210019Engine · failed(CAN) ENGINE STOPPED AT ALT, ENG WOULD NOT RESTART. NO FAULTS WERE FOUND WITH ENG AT BENCH TEST AFTER INCIDENT.SDR AU990815Magneto · faulty(AUS) RIGHT MAGNETO FAULTY.SDR AU990737Magneto · faulty(AUS) MAGNETO FAULTY. ENGINE WAS JUST RECEIVED FROM OVERHAUL.SDR CA990223010Tube · misinstalled(CAN) DURING FLIGHT, THE PILOT NOTICED THROTTLE MOVEMENT WAS OBSTRUCTED. THE AIRCRAFT LANDED SAFELY. ON THE GROUND, THE THROTTLE OPERATION WAS NORMAL. ON REMOVAL OF THE AIR INTAKE, MAINTENANCE PERSONNEL FOUND THE PUMP DISCHARGE TUBE ASSEMBLY SITTING ON THE SDR AU990057Bolt · cracked(AUS) WING SPAR BOLTS CRACKED UNDER THE BOLT HEAD. PART TC: 3,547.SDR AU990012Splice · cracked(AUS) LEFT WING AFT LOWER SPLICE PLATE CRACKED APPROXIMATELY 2 MM (0.079 INCH) IN LENGTH. ALSO, THE FORWARD RIGHT ANGLE DOUBLER WAS CRACKED IN THE LOWER BEND RADIUS FOR APPROXIMATELY 25 MM (0.984 INCH). FOUND IAW AD/ROBIN/8A2. PART TC: 5,707.SDR AU990017Bolt · cracked(AUS) WHEN WING SPAR BOLTS WERE MAGNAFLUXED, (NOT A REQUIREMENT OF THIS AD), ALL 12 BOLTS WERE FOUND CRACKED UNDER HEAD. FOUND DURING COMPLIANCE WITH AD/ROBIN/8A2. PART TC: 5,707.SDR AU981274Skin · cracked(AUS) LEFT WING UPPER LEADING EDGE SKIN CRACKED IN AREA OF RIVET LINE ON THE MAIN SPAR. CRACK APPROXIMATELY 52.8 MM (2 INCHES) IN LENGTH LOCATED 209.55 MM (8.25 INCHES) OUTBOARD OF THE WING ROOT. CRACK APPROXIMATELY 19.05 MM (0.75 INCHES) LOCATED 514.35 MM (SDR CA980810007Tappet · failed(CAN) PILOT REPORTED A ROUGH RUNNING ENGINE. INITIAL INVESTIGATION FOUND THE HYDRAULIC TAPPET BODY AND SYSTEM HAD FAILED ON THE NR 4 CYLINDER INTAKE SIDE. THE ENGINE IS BEING SENT FOR TEARDOWN AND INVESTIGATION. FURTHER REPORT TO FOLLOW.SDR CA980602014Crankshaft · pitted(CAN) WHILE COMPLYING WITH AD 98-02-08 INSPECTION, PITS WERE FOUND IN THE CRANKSHAFT BORE.SDR 97ZZZX4497Spark Plug · brokenENGINE RPM DROPPED TO APPROXIMATELY 2,000 RPM ON CLIMB-OUT. GROUND RUN-UP WAS NORMAL BEFORE AND AFTER FLIGHT AND DURING FIRST 200 FEET OF CLIMB OUT. INSPECTION OF INDUCTION, FUEL AND IGNITION SYSTEMS, REVEALED TWO AUBURN SR-87 AC PLUGS WITH BROKEN INSULATORSSDR 97ZZZX1224Crankshaft · crackedTHIS AIRCRAFT IS USED EXCLUSIVELY FOR FLIGHT TRAINING. ON PRE-FLIGHT, STUDENT AND INSTRUCTOR FOUND OIL ON THE COWLING. UPON INSPECTION, TWO CRACKS WERE FOUND ON THE CRANKSHAFT COVERGING AT THE RADIUS OF THE CRANKSHAFT AND CRANKSHAFT FLANGE. THIS ENGINE AND SDR AU970165Torque Link · broken(AUS) LH MAIN LANDING GEAR LOWER TORQUE LINK BROKEN AT INBOARD ATTACHMENT LUG - OUTBOARD LUG CONTAINS A HAIR LINE CRACK - RH MLG TORQUE LINK CONTAINS SOME PITTING IN THE ATTACHMENT LUG HOLESSDR AU970107Torque Link · broken(AUS) RH MAIN LANDING GEAR LOWER TORQUE LINK FAILED AT LOWER ATTACHMENT HOLESSDR CA961216013Crankshaft · corroded(CAN) DETAILED INSPECTION OF THE ENGINE CRANKSHAFT CARRIED OUT AS PER LYCOMING SB #505A REVEALED CORROSION AND DEEP PITTING IN THE INSIDE DIAMETER (I.D.). REMOVAL OF THE CORROSION AND PITTING TO THE MAXIMUM ALLOWABLE I.D. OF 1.910" STILL INDICATED PITTING IN TSDR CA961216014Crankshaft · corroded(CAN) DETAILED INSPECTION OF THE ENGINE CRANKSHAFT CARRIED OUT AS PER LYCOMING SB #505A REVEALED CORROSION AND DEEP PITTING IN THE INSIDE DIAMETER (I.D.). REMOVAL OF THE CORROSION AND PITTING TO THE MAXIMUM ALLOWABLE I.D. OF 1.910" STILL INDICATED PITTING IN TSDR CA961216015Crankshaft · corroded(CAN) DETAILED INSPECTION OF THE ENGINE CRANKSHAFT CARRIED OUT AS PER LYCOMING SB #505A REVEALED CORROSION AND DEEP PITTING IN THE INSIDE DIAMETER (I.D.). REMOVAL OF THE CORROSION AND PITTING TO THE MAXIMUM ALLOWABLE I.D. OF 1.910" STILL INDICATED PITTING IN TSDR CA961216016Crankshaft · corroded(CAN) DETAILED INSPECTION OF THE ENGINE CRANKSHAFT CARRIED OUT AS PER LYCOMING SB #505A REVEALED CORROSION AND DEEP PITTING IN THE INSIDE DIAMETER (I.D.). REMOVAL OF THE CORROSION AND PITTING TO THE MAXIMUM ALLOWABLE I.D. OF 1.910" STILL INDICATED PITTING IN TSDR CA961216017Crankshaft · corroded(CAN) DETAILED INSPECTION OF THE ENGINE CRANKSHAFT CARRIED OUT AS PER LYCOMING SB #505A REVEALED CORROSION AND DEEP PITTING IN THE INSIDE DIAMETER (I.D.). REMOVAL OF THE CORROSION AND PITTING TO THE MAXIMUM ALLOWABLE I.D. OF 1.910" STILL INDICATED PITTING IN TSDR CA961216018Crankshaft · corroded(CAN) DETAILED INSPECTION OF THE ENGINE CRANKSHAFT CARRIED OUT AS PER LYCOMING SB #505A REVEALED CORROSION AND DEEP PITTING IN THE INSIDE DIAMETER (I.D.). REMOVAL OF THE CORROSION AND PITTING TO THE MAXIMUM ALLOWABLE I.D. OF 1.910" STILL INDICATED PITTING IN TSDR CA961216019Crankshaft · corroded(CAN) DETAILED INSPECTION OF THE ENGINE CRANKSHAFT CARRIED OUT AS PER LYCOMING SB #505A REVEALED CORROSION AND DEEP PITTING IN THE INSIDE DIAMETER (I.D.). REMOVAL OF THE CORROSION AND PITTING TO THE MAXIMUM ALLOWABLE I.D. OF 1.910" STILL INDICATED PITTING IN TSDR CA961216020Crankshaft · corroded(CAN) DETAILED INSPECTION OF THE ENGINE CRANKSHAFT CARRIED OUT AS PER LYCOMING SB #505A REVEALED CORROSION AND DEEP PITTING IN THE INSIDE DIAMETER (I.D.). REMOVAL OF THE CORROSION AND PITTING TO THE MAXIMUM ALLOWABLE I.D. OF 1.910" STILL INDICATED PITTING IN TSDR CA961216021Crankshaft · corroded(CAN) DETAILED INSPECTION OF THE ENGINE CRANKSHAFT CARRIED OUT AS PER LYCOMING SB #505A REVEALED CORROSION AND DEEP PITTING IN THE INSIDE DIAMETER (I.D.). REMOVAL OF THE CORROSION AND PITTING TO THE MAXIMUM ALLOWABLE I.D. OF 1.910" STILL INDICATED PITTING IN TSDR CA961216022Crankshaft · corroded(CAN) DETAILED INSPECTION OF THE ENGINE CRANKSHAFT CARRIED OUT AS PER LYCOMING SB #505A REVEALED CORROSION AND DEEP PITTING IN THE INSIDE DIAMETER (I.D.). REMOVAL OF THE CORROSION AND PITTING TO THE MAXIMUM ALLOWABLE I.D. OF 1.910" STILL INDICATED PITTING IN TSDR CA961216023Crankshaft · corroded(CAN) DETAILED INSPECTION OF THE ENGINE CRANKSHAFT CARRIED OUT AS PER LYCOMING SB #505A REVEALED CORROSION AND DEEP PITTING IN THE INSIDE DIAMETER (I.D.). REMOVAL OF THE CORROSION AND PITTING TO THE MAXIMUM ALLOWABLE I.D. OF 1.910" STILL INDICATED PITTING IN TSDR CA961216024Crankshaft · corroded(CAN) DETAILED INSPECTION OF THE ENGINE CRANKSHAFT CARRIED OUT AS PER LYCOMING SB #505A REVEALED CORROSION AND DEEP PITTING IN THE INSIDE DIAMETER (I.D.). REMOVAL OF THE CORROSION AND PITTING TO THE MAXIMUM ALLOWABLE I.D. OF 1.910" STILL INDICATED PITTING IN TSDR CA961115002Crankshaft · cracked(CAN) ENGINE RECEIVED FOR REPAIR FOR A CRANKSHAFT CRACKED AT THE MAIN BEARING JOURNAL EXTENDING FROM THE FRONT EXPANSION PLUG SEAT IN A SPIRAL (ANTI CLOCKWISE FROM THE FRONT) TO APPROXIMATELY HALF WAY BETWEEN THE FORWARD THRUST FACE AND THE CROSS FEED OIL HOLESDR CA960916010Crankshaft · cracked(CAN) PILOT REPORTED AN OIL LEAK IN THE PROP AREA AND AN OIL SMELL IN THE CABIN. INVESTIGATION REVEALED THAT THE CRANKSHAFT ASSEMBLY HAD A CRACK FROM THE PROP FLANGE GOING IN A SPIRAL AFT OF THE FLANGE ON THE CRANKSHAFT. THE CRACK WAS APPROXIMATELY 4.5" LONG ASDR CA960826065Pushrod · broken(CAN) UPON PULLING THE THROTTLE BACK THE PUSHROD BROKE AT THE FORWARD THREADED END, WHERE IT ATTACHES TO THE CLEVIS ASSEMBLY. THE PILOT HAD ENOUGH TRAVEL TO PERFORM A SAFE LANDING.
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