Lycoming IO-360-L2A
Service difficulty reports · 992
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 = 'IO360L2A' 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 = 'IO360L2A' 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 2026FA0000749Propeller · misinstalledPROPELLER INSTALLED INCORRECTLY AT THE FACTORY, INCORRECT CLOCKING CAUSING PROPELLER BUSHINGS TO BACK OUT: THE PROPELLER CLOCKED INCORRECTLY WITH #1 CYLINDER AT TOP DEAD CENTER. THE FACTORY SAFETY CABLES SHOWING THIS PROP HASN'T BEEN REMOVED SINCE TAKING DELISDR 2026FA0000684Seal · failedAFTER COMPLETION OF THE ANNUAL INSPECTION, WE PERFORMED A POST INSPECTION RUN. DURING IDLE WE CHECKED EACH MAGNETO AND FOUND THAT THE ENGINE RAN SIGNIFICANTLY ROUGHER ON THE LEFT MAGNETO THAN THE RIGHT MAGNETO. AT HIGHER RPM OPERATION WAS NORMAL. REMOVED LEFSDR 2026FA0000618Pump · failedENGINE DRIVEN FUEL PUMP FAILURE ALLOWED FUEL TO FLOOD ENGINE CRANKCASE. FOUND ON GROUND BEFORE FLIGHT.SDR 2026FA0000519Cylinder · crackedPILOT REPORTED LOUD NOISE FROM ENGINE, SIGNIFICANT POWER LOSS, AND LOUD VIBRATIONS. PILOT LANDED AT A NEARBY AIRPORT WHERE MANTIENCE DISCOVERED A LARGE CRACK IN CYLINDER #2(HEAD SEPERATING FROM THE BARREL).SDR 2026FA0000470Shutoff Valve · leakingFUEL SHUT OFF VALVE NOT STOPPING FUEL COMPLETELY. FUEL DRIPPING FROM FUEL STRAINER DURING INSPECTION.SDR 2026FA0000290Button · meltedUPON INSPECTION AFTER MAJOR ENGINE OVERHAUL, IT WAS DISCOVERED THAT THE ROCKER SHAFT THRUST BUTTONS HAD EITHER PARTIALLY OR COMPLETELY MELTED. A COMPLETE ENGINE TEARDOWN INSPECTION WAS THEN PERFORMED, ONLY ONE CYLINDER HAD BOTH THRUST BUTTONS COMPLETELY INTACTSDR 2026FA0000285Throttle Cable · severedLOSS OF THROTTLE CONTROL IN FLIGHT, DUE TO SEVERED THROTTLE CABLE.SDR NX422026031600011Crankcase · gougedUPON DISASSEMBLY FOR ITS FIRST OVERHAUL, DAMAGE WAS FOUND ON THE LEFT HAND CRANKCASE HALF TO THREE THRU STUD BORE LOCATIONS. THE DAMAGE APPEARS TO BE A GOUGE WITH DISPLACED METAL JUST UNDER THE CYLINDER PADS JUST INSIDE THE THRU STUD BORES. SIMILAR DAMAGE ON OSDR NX422026031600012Stud · damagedUPON DISASSEMBLY FOR IT'S FIRST OVERHAUL, DAMAGE WAS FOUND ON ONE OF THE THRU STUDS. THE DAMAGE APPEARS TO BE DIPLSACED STEEL UNDER THE THREADED PORTION ON THE SHOULDER OF THE THRU STUD. A RELEVANT INDICATION IS SEEN UNDER MAGNETIC PARTICLE INSPECTION. THE LEFSDR NX422026031600013Crankcase · gougedUPON DISASSEMBLY FOR ITS FIRST OVERHAUL, DAMAGE WAS FOUND ON THE LEFT HAND CRANKCASE HALF ON ALL FOUR THRU STUD BORE LOCATIONS. THE DAMAGE APPEARS TO BE A GOUGE WITH DISPLACED METAL JUST UNDER THE CYLINDER PADS JUST INSIDE THE THRU STUD BORES. SIMILAR DAMAGE OSDR 2026FA0000173Coil · bentUNDER NORMAL FLIGHT OPERATIONS, AT FIRST ROUTINE 500-HOUR INSPECTION FOUND COIL TAB WORN OUT OF LIMITS BECAUSE THE TAB WAS INCORRECTLY BEND AT FACTORY.SDR 2026FA0000167Cylinder Head · crackedENGINE WAS REPORTED RUNNING ROUGH, WAS FOUND TO HAVE A CRACK ON THE CYLINDER HEAD ON #4 CYLINDER. THE SAME PROBLEM WAS FOUND ON ANOTHER ENGINE, SAME TYPE AIRCRAFT, ENGINE AND CYLINDER.SDR NX422026022700009Crankcase · gougedUPON DISASSEMBLY FOR ITS FIRST OVERHAUL, DAMAGE WAS FOUND ON THE LEFT HAND CRANCASE TO ONE THRU STUD LOCATION. THE DAMAGE APPEARS TO BE A GOUGE WITH DISPLACED METAL JUST UNDER THE CYLINDER PAD INSIDE THE THRU STUD BORE. SIMILAR DAMAGE ON OTHER ENGINES WAS PREVSDR NX422026022700010Stud · displacedUPON DISASSEMBLY FOR IT'S FIRST OVERHAUL, DAMAGE WAS FOUND ON ONE OF THE THRU STUDS. THE DAMAGE APPEARS TO BE DISPLACED STEEL UNDER THE THREADED PORTION ON THE SHOULDER OF THE THRU STUD. THE DAMAGE IS MINOR BUT DUE TO THE SIMILAR LOCATION AND SEVERITY OF THE DSDR NX422026021800007Crankcase · gougedUPON DISASSEMBLY FOR ITS FIRST OVERHAUL, DAMAGE WAS FOUND ON THE LEFT HAND CRANCASE TO ALL 4 THRU STUD LOCATIONS. THE DAMAGE APPEARS TO BE A GOUGE WITH DISPLACED METAL JUST UNDER THE CYLINDER PAD INSIDE THE THRU STUD BORE. ON THREE OF THE THRU STUD BORES THE DSDR NX422026021800008Stud · displacedUPON DISASSEMBLY FOR IT'S FIRST OVERHAUL, DAMAGE WAS FOUND ON 2 OF THE THRU STUDS. THE DAMAGE APPEARS TO BE DISPLACED STEEL UNDER THE THREADED PORTION ON THE SHOULDER OF THE THRU STUD. THE DAMAGE IS MINOR BUT DUE TO THE SIMILAR LOCATION AND SEVERITY OF THE DAMSDR NX422026021800005Crankcase · gougedUPON DISASSEMBLY FOR ITS FIRST OVERHAUL, DAMAGE WAS FOUND ON THE LEFT HAND CRANCASE TO ALL 4 THRU STUD LOCATIONS. THE DAMAGE APPEARS TO BE A GOUGE WITH DISPLACED METAL JUST UNDER THE CYLINDER PAD INSIDE THE THRU STUD BORE. IN ADDITION, 1 OF THE THRU STUDS HAVESDR NX422026021800006Stud · displacedUPON DISASSEMBLY FOR IT'S FIRST OVERHAUL, DAMAGE WAS FOUND ON 1 OF THE THRU STUDS. THE DAMAGE APPEARS TO BE DISPLACED STEEL UNDER THE THREADED PORTION ON THE SHOULDER OF THE THRU STUD. THE DAMAGE IS MINOR BUT DUE TO THE SIMILAR LOCATION AND SEVERITY OF THE DAMSDR NX422026020600002Stud · displacedON DISASSEMBLY FOR ITS 1ST OVERHAUL, DAMAGE FOUND ON 2 OF THRU STUDS. DAMAGE APPEARS TO BE DISPLACED STEEL UNDER THREADED PORTION ON SHOULDER OF THRU STUDS. ON 1 THRU STUD. DAMAGE IS SEVERE WITH DISPLACED METAL FROM SMALLER NECKED DOWN PORTION OF STUD UP TO SDR NX422026020600001Crankcase · gougedUPON DISASSEMBLY FOR ITS FIRST OVERHAUL, DAMAGE WAS FOUND ON THE LEFT HAND CRANCASE ON ALL 4 OF THE FLOATING THRU STUD LOCATIONS. THE DAMAGE APPEARS TO BE A GOUGE WITH DISPLACED METAL JUST UNDER THE CYLINDER PAD INSIDE THE THRU STUD BORES. IN ADDITION, 2 OF THSDR NX422026020600003Crankcase · gougedUPON DISASSEMBLY FOR ITS FIRST OVERHAUL, DAMAGE WAS FOUND ON THE LEFT HAND CRANCASE TO THE UPPER MIDDLE FLOATING THRU STUD LOCATION. THE DAMAGE APPEARS TO BE A GOUGE WITH DISPLACED METAL JUST UNDER THE CYLINDER PAD INSIDE THE THRU STUD BORE. IN ADDITION, 2 OF SDR NX422026020600004Stud · displacedUPON DISASSEMBLY FOR IT'S FIRST OVERHAUL, DAMAGE WAS FOUND ON 2 OF THE THRU STUDS. THE DAMAGE APPEARS TO BE DISPLACED STEEL UNDER THE THREADED PORTION ON THE SHOULDER OF THE THRU STUDS. THE DAMAGE APPEARS TO BE VERY MINOR BUT DUE TO THE SIMILAR LOCATION AND SESDR 2026FA0000198Impulse Coupling · destroyedPILOT REPORT OF FLUCTUATING RPM'S WHILE IN CRUISE FLIGHT, PLUS OR MINUS 400RPM. DURING GROUND RUN FOR TROUBLESHOOTING, RH MAGNETO MAG DROP WAS EXCESSIVE. FURTHER ATTEMPTS AT CLEARING PLUGS, ETC, TO THEN RECHECK RH MAGNETO DROP RESULTED IN COMPLETE ENGINE SHUT SDR 2025FA0000775Crankcase · gougedDURING DISASSEMBLY OF THE ENGINE FOR OVERHAUL DAMAGE WAS FOUND ON THE LEFT CRANKCASE HALF AT EACH OF THE 4 THRU STUD CYLINDER PAD LOCATIONS. THE DAMAGE APPEARS TO BE A GOUGE DISPLACING SOME OF THE ALUMINUM CRANKCASE PAD DOWN INTO EACH OF THE THRU STUD BORE LOCSDR 2025FA0000574Elec Connector · intermittentENGINE OIL PRESSURE FLUCTUATES. REMOVED AND REPLACED THE OIL PRESSURE TRANSDUCER CONNECTOR JN004 PN: S2800-277 REFERENCING CESSNA/TEXTRON MODEL 172 (SERIES 1996 AND ON) WIRING DIAGRAM MANUAL REV A1, 77-40-01, FIGURE 03: SHEET 02 “ENGINE AND AIRFRAME MONITOR”.SDR 2025FA0000575Elec Connector · intermittentENGINE OIL PRESSURE ERRATIC. REMOVED AND REPLACED ENGINE OIL PRESSURE TRANSDUCER ELECTRICAL CONNECTOR (JN004) WITH NEW P/N S2800-277 REFERENCING CESSNA 172S WDG CH.79-30-01 (REV.A1). ENGINE RUN, OIL PRESSURE SYSTEM OPERATIONAL CHECK SATISFACTORY.SDR IKBR2025082600576Elec Connector · failedENGINE OIL PRESSURE ERRATIC. REMOVED AND REPLACED ENGINE OIL PRESSURE TRANSDUCER ELECTRICAL CONNECTOR (JN004) WITH NEW P/N S2800-277 REFERENCING CESSNA 172S WDG CH.79-30-01 (REV.A1). ENGINE RUN, OIL PRESSURE SYSTEM OPERATIONAL CHECK SATISFACTORY.SDR 2025FA0000577Elec Connector · intermittentENGINE OIL PRESSURE ERRATIC.REMOVED AND REPLACED ENGINE OIL PRESSURE TRANSDUCER ELECTRICAL CONNECTOR (JN004) WITH NEW P/N S2800-277 REFERENCING CESSNA 172S WDG CH.79-30-01 (REV.A1). ENGINE RUN, OIL PRESSURE SYSTEM OPERATIONAL CHECK SATISFACTORY.SDR 2025FA0000578Elec Connector · failedFUEL PRESSURE INDICATIONS ERRATIC. REPLACE FUEL PRESSURE TRANSDUCER CONNECTOR (JN001) PN: S2800-277 REFERENCING TEXTRON MODEL 172 (SERIES 1996 AND ON) WIRING DIAGRAM MANUAL REV A1 SECTION 77-20-01, FIGURE 02 (REV A0).SDR IKBR2025082600579Elec Connector · intermittentENGINE OIL PRESSURE INDICATION ERRATIC. REMOVED AND REPLACED ENGINE OIL PRESSURE TRANSDUCER WIRING CONNECTOR WITH NEW P/N S2800-277 REFERENCING CESSNA 172S WDG CH.77-40-01 (REV. A1). ENGINE RUN, OIL PRESSURE OPERATIONAL CHECK SATISFACTORY.SDR 2025FA0000643Servo · contaminatedAIRCRAFT DIED IN RUNUP AREA TWICE. ONCE ON RAMP, ONCE IN RUNUP. FAILED IDLE CHECK. FUEL SERVO WAS REMOVED AND FOUND TO BE CONTAMINATED. REPLACED WITH NEW.SDR 2025FA0000644Servo · contaminatedAIRCRAFT HAD MOMENTARY POWER LOSS/VIBRATION AFTER ADDING FULL POWER ON A TOUCH AND GO. ABORTED TAKEOFF. TOOK AIRCRAFT TO A RUNUP AREA AND CYCLED THE ENGINE FROM POWER IDLE TO FULL POWER MULTIPLE TIMES AND COULD NOT RECREATE THE ISSUE. FUEL SERVO REPLACED.SDR 2025FA0000602Servo · contaminatedMOMENTARY ENGINE ROUGHNESS/VIBRATION. CLIMBING OUT ON THE MISSED APPROACH AT CRQ, ENGINE LOST BETWEEN 200-400RPM AND BEGAN CHUGGING, I CHECKED MIXTURE WHICH WAS FULL RICH, LEANED SLIGHTLY, THE CHUGGING STOPPED. I THEN MOVED THE MIXTURE FULL RICH AND DID NOT ENSDR 2025FA0000603Servo · contaminatedMOMENTARY ENGINE ROUGHNESS/VIBRATION/LOSS OF POWER. PILOT SQUAWK: PARTIAL LOSS OF ENGINE POWER RIGHT AFTER TAKEOFF, 200-300 RPMS, CAME BACK AFTER A COUPLE SECONDS BUT DID NOT WANT TO CONTINUE FLIGHT. FUEL SERVO REPLACED.SDR ODAR2025080600002Cylinder Head · crackedSUBSTANTIAL ENGINE VIBRATION REPORTED BY PILOT DURING FLIGHT. #4 CHT CONSISTENTLY ~40% HIGHER THAN OTHER CYLINDERS. MAG CHECKS NORMAL. VIBRATION REMAINED THE SAME REGARDLESS OF MAGS SELECTED. OIL PRESSURE AND TEMP REMAINED IN GREEN. PERFORMED COMPRESSION CHECKSDR 2025FA0000526Elec Connector · faultedERRATIC ENGINE OIL PRESSURE READINGS. REMOVED AND REPLACED ENGINE OIL PRESSURE TRANSDUCER ELECTRICAL CONNECTOR (JN004) P/N S2800-277 (KIT) AT THE TRANSDUCER.SDR 2025FA0000527Elec Connector · abnormalERRATIC ENGINE OIL PRESSURE INDICATION. REMOVED AND REPLACED ENGINE OIL PRESSURE TRANSDUCER ELECTRICAL CONNECTOR (JN004) P/N S2800-277 (KIT) AT THE TRANSDUCER.SDR 2025FA0000516Engine · auto shutdownAIRCRAFT AND CREW EXPERIENCED ENGINE ROUGHNESS AND THE ENGINE QUITTING WHILE IN FLIGHT. THE CREW AND AIRCRAFT MADE AN UNPOWERED SAFE LANDING AT KARR (HOME AIRPORT). INITIAL INSPECTION FOUND THAT THE PROP WAS FREEWHEELING WITH NO RESISTANCE. NR 3 CYLINDER HAD ASDR 2025FA0000400Valve Guide · cokedCREW REPORTED ROUGH RUNNING ENGINE/VIBRATION IN CRUISE FLIGHT LASTING 2-3 MINUTES ALONG WITH A # 2 CYLINDER EGT FLUCTUATION. TROUBLESHOT PROBLEM TO FIND # 2 CYLINDER EXHAUST VALVE STICKING.SDR 2025FA0000384Indication Sys · erraticENGINE OIL PRESSURE INDICATION ERRATIC. ONLY FLUCTUATES IN FLIGHT. STEADY DURING GROUND OPERATIONS.SDR 2025FA0000357Piston · cloggedRIGHT BRAKE LOCKED UP WHEN TAXIING TO RUNWAY, AIRCRAFT WENT INTO THE GRASS. NO DAMAGE TO AIRCRAFT.SDR 2025FA0000296Exhaust Valve · stuckEXTREME VIBRATION OF AIRCRAFT ENGINE AFTER START UP. TROUBLESHOT AND FOUND #4 CYLINDER EXHAUST VALVE STUCK OPENSDR 2025FA0000286Impulse Coupling · brokenWHILE PERFORMING HARTZELL AVIATION ALERT S.B. NO. 225 IT WAS FOUND ON MAGNETO S/N H-Y103862 HAD A BROKEN IMPULSE CAM ASSEMBLY PIN. MAGNETO WAS INSTALLED 4/14/2025 AND REMOVED FOR INSPECTION ON 4/21/2025. HARTZELL AVIATION HAS BEEN NOTIFIED.SDR IKBR2025041400264Elec Connector · failedCREW REPORTS TEMPORARY OIL PRESSURE LOSS ON APPROACH. ALL OTHER ENGINE INDICATIONS WERE NORMAL. UPON LANDING OIL PRESSURE RETURNED TO NORMAL. MECHANICS INSPECTED ENGINE. NO DEFECTS WERE NOTED. AVIONICS TECHNICIAN REPLACED THE OIL PRESSURE TRANSDUCER ELECTRICALSDR 2025FA0000217Engine · power lossON TAKE-OFF THE ENGINE LOST POWER MOMENTARILY AND PILOT WAS ABLE TO ABORT TAKE-OFF AND LAND WITHOUT INJURIES. POWER RESTORED ITS SELF AND TROUBLESHOOTING COULD NOT DUPLICATE THE LOSS OF POWER.SDR 2025FA0000218Engine · power lossWHILE IN STRAIGHT AND LEVEL FLIGHT PILOT REPORTED THE ENGINE RPM REDUCED SIGNIFYINGLY RESULTING IN POWER LOSS. AFTER A BRIEF TIME THE ENGINE RPM BEGAN TO OPERATE NORMALLY AND POWER WAS RESTORED. PILOT LANDED WITHOUT INCIDENT. TROUBLESHOOTING COULD NOT DUPLISDR 2025FA0000206Propeller · brokenN500GP LINED UP CENTERLINE ON RWY 05 @ KDYL, APPLIED TAKEOFF POWER, APPROXIMATELY 30-50FT ON ROLLOUT EXPERIENCED SUDDEN VIBRATION, PULLED POWER AND EXITED RWY AT NEAREST TAXIWAY. SHUT DOWN AND VISUALLY INSPECTED AIRCRAFT. NOTIFIED MAINTENANCE.SDR N3XR202502280001Seal · failedFUEL WAS DISCOVERED IN ENGINE OIL. INSPECTION REVEALED THAT THE FUEL PUMP LW-15473 SEAL HAD FAILED AND LEAKED INTO THE OIL. THE ENGINE WAS CHANGED.SDR 2025FA0000133Cylinder Head · crackedENGINE CYLINDER #2 CRACKED ACROSS COOLING FINS. CREW NOTICED LOSS OF POWER/SHUDDER. BURNING SMELL COMING THROUGH CABIN AIR VENTS.SDR 2025FA0000134Muffler · crackedCREW REPORTS EXHAUST SMELL IN CABIN. VISUAL INSPECTION FOUND MUFFLER CRACKED.
Back to Lycoming IO-360-L2A