Lycoming IO-360-L2A
Service difficulty reports · 994
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 2015FA0000265Muffler · crackedSPOT WELDS FAILED CAUSING CARBON MONOXIDE TO ENTER HEAT SHROUD THEREFORE ENTERING CABIN.SDR OG5S2015FA0000237Muffler · crackedSPOT WELDS IN MUFFLER CAN LET LOOSE, LETTING CARBON MONOXIDE INTO CABIN HEAT DUCT.SDR OG5S2015FA0000238Muffler · crackedMUFFLER IS CRACKED INTERNALY AND SPOT WELDS HAVE BROKEN, ALLOWING CARBON MONOXIDE TO BE RELEASED INTO HEAT SHROUD AND INTO CABIN AREA.SDR OG5R2015FA0000200Muffler · failedDURING FLIGHT CARBON MONOXIDE WARNING ILLUMINATED. PILOT RETURNED TO LAND. MAINTENANCE DISCOVERED 2 SPOTWELDS ON THE SHROUD SUPPORT FLANGE OF THE MUFFLER HAD FAILED RESULTING IN OPEN HOLES IN THE MUFFLER CAN. REPLACED MUFFLER WITH NEW UNIT.SDR CA150526008Hose · restricted(CAN) AIRCRAFT DEVELOPED ROUGH RUNNING IN CRUISE SO ELECTED TO LAND. ON APPROACH THE ENG STOPPED BUT THE ACFT MADE A NORMAL LANDING WITH NO DAMAGE. INVESTIGATION FOUND THE FUEL LINE BETWEEN THE FUEL FLOW TRANSDUCER & FUEL FLOW DIVIDER WAS LOOSE AT THE FLOW DSDR OG5S2015FA0000187Muffler · crackedSITTING ON THE RAMP IDLING, RECEIVED A HIGH CO2 WARNING AFTER A COUPLE ON MINUTES. SHUTDOWN ENGINE AND CO2 WARNING CEASED. INSPECTED MUFFLER AND FOUND SPOT WELDS PULLING OUT FROM MUFFLER LINER THEREFORE RELEASING EXHAUST INTO HEAT SHROUD.SDR OG5S2015FA0000180Muffler · failedDURING ROUTINE INSPECTION NOTED THAT 2 SPOTWELDS ON THE SHROUD SUPPORT FLANGE OF THE MUFFLER CAN HAD FAILED RESULTING IN OPEN HOLES IN THE MUFFLER CAN. REPLACED MUFFLER WITH NEW UNIT.SDR BG8S2015FA0000192Magneto · out of alignmentREPLACED RT MAGNETO WITH O/H UNIT FROM O/H SHOP, MODEL 4371, SN 15011241. TIMED MAGNETO TO ENGINE PERFORMED GROUND RUN OPS CHECK GOOD ON GROUND, RELEASED AIRPLANE FOR SERVICE. DURING THE FIRST FLIGHT THE ENGINE RAN ROUGH ON CLIMB, PILOT RETURNED TO AIRPORT. RSDR 2015FA0000161Muffler · failedON TAKEOFF PILOT GOT A CARBON MONOXIDE WARNING ON PRIMARY FLIGHT DISPLAY. RETURNED AND LANDED WITHOUT INCIDENT. MAINTENANCE VERIFIED PRESENCE OF CARBON MONOXIDE DURING RUN-UP. VISUAL INSPECTION REVEALED SPOT WELD FAILED ON MUFFLER BODY WHERE THE SHROUD SUPPSDR CA150501007Screen · contaminated(CAN) FUEL SERVO INLET SCREEN FOUND TO HAVE LINT TYPE DEBRIS INSIDE.SDR CA150501006Screen · contaminated(CAN) FUEL SERVO INLET SCREEN FOUND TO HAVE LINT TYPE DEBRIS INSIDE.SDR OG5R2015040600123Muffler · crackedSPOT WELDS ON MUFFLER SEPARATED RELEASING EXHAUST INTO HEAT EXCHANGER.SDR 2015FA0000109Servo · looseFOUND FUEL SERVO COULD BE MOVED BY HAND SLIGHTLY. ATTACHING NUTS TORQUE STRIPE INDICATED NO BACKOFF OF THE 4 NUTS. SERVO IS MOUNTED ONTO AN ISOLATION BLOCK WITH 2 EA, PN 66224, GASKETS. FOUND NO DAMAGE AND INSTALLED 2 NEW GASKETS, TORQUE AND RECHECKED 14 HRS SDR CA150128003Wire · failed(CAN) TAIL NAV LIGHT WIRE SHORTED AGAINST ELEVATOR CABLE CAUSING BURN DAMAGE TO CABLE. THE NAV LIGHT WIRING CONSISTS OF A 5 AMP CIRCUIT-BREAKER-SWITCH WITH THREE BRANCHES OF 22 GAUGE WIRE FOR THE WING TIP AND TAIL NAV LIGHTS. THE TAIL LIGHT WIRE RUNS AFT UNDESDR CA141215003Impulse Coupling · out of tolerance(CAN) ENGINE WAS HARD TO START WHEN HOT. FOUND IMPULSE COUPLING FIRING OFF 9-10 DEGREES AFTER TDC WHEN IT SHOULD BE CLOSER TO TDC. DIDN`T MAKE IT TO THE INITIAL 500 HOUR INSPECTION BEFORE INTERNAL MAGNETO TIMING REQUIRES ADJUSTMENT.SDR CA141215004Impulse Coupling · out of tolerance(CAN) ENGINE WAS HARD TO START WHEN HOT. FOUND IMPULSE COUPLING FIRING OFF 9-10 DEGREES AFTER TDC WHEN IT SHOULD BE CLOSER TO TDC. DIDN`T MAKE IT TO THE INITIAL 500 HOUR INSPECTION BEFORE INTERNAL MAGNETO TIMING REQUIRES ADJUSTMENT.SDR OG5R2014FA0000694Bushing · wornPILOT REPORTED CONTROL YOKES WERE GRINDING, DURING VISUAL INSPECTION FOUND SUPPORT GUIDE, FOR CONTROL YOKE BUSHING, BOTH TO BE WORN WITH SUPPORT GUIDE TO BE PENETRATING MATERIAL MORE THAN 75 PERCENT.SDR 1B2S2014FA0000690Bulkhead · crackedREAR AFT BULKHEAD WAS FOUND TO BE CRACKED DURING AN ANNUAL INSPECTION. THE CRACK IS LOCATED AT THE UPPER RT PORTION OF THE BULKHEAD. IT IS VISIBLE ON THE FORWARD SIDE OF THE BULKHEAD AND ALSO VISIBLE INSIDE THE BOLT HOLE WHERE THE VERTICAL STAB ATTACHES. THSDR 2014FA0000666Shaft · wornTHROTTLE WOULD HAVE TO MOVE BACK AROUND TWO INCHES FROM MAX RPM TO NOTICE A DECREASE IN RPM. THROTTLE WAS VERY LOOSE IN THOSE TWO INCHES OF TRAVEL. FOUND THROTTLE SHAFT TO BE WORN AND SLOPPY IN THE HIGH RPM POSITION.SDR CA141202038Vhf Comm · interference(CAN) VHF COM RADIO HAS LOTS OF STATIC ON FREQUENCY 120.0. TROUBLESHOOTING HAS DETERMINED THAT THE PROBLEM IS MOST LIKELY ASSOCIATED WITH THE FUEL SENDING UNITS. TYPE CERTIFICATE HOLDER IS AWARE OF THE PROBLEM. (TC# 20141202038)SDR YQYR20141205002Fuel Control · contaminatedFUEL SERVO VENTURI CONTAMINATED FROM OVER PRIMING, CAUSING IMPROPER ENGINE IDLE AND ENGINE STOPPAGE.SDR OG5R2014110400650Injector · malfunctionedON RUN UP, FOUND THAT THE THROTTLE CONTROL WOULD STICK AT LOW RPM. WHEN ENOUGH FORCE WAS APPLIED TO MOVE PAST THE STICKING POINT THE RPM WOULD JUMP 200-400 RPM. AFTER DISCONNECTING THE THROTTLE CONTROL WE FOUND THE CONTROL WAS SMOOTH. THIS MADE IT DIFFICULTSDR OG5S2014110400651Actuator · failedDURING INSPECTION, DISCOVERED TRIM ACTUATOR WOULD JAM IN BOTH UP AND DOWN TRAVEL. TOTAL ACTUATOR TRAVEL WAS ABOUT .5 OF SPECIFIED TRAVEL. REPLACED TRIM ACTUATOR.SDR YQYR20141205001Fuel Control · contaminatedFUEL SERVO VENTURI CONTAMINATED FROM OVER PRIMING, CAUSING IMPROPER ENGINE IDLE AND ENGINE STOPPAGE.SDR CA141113002Bellcrank · worn(CAN) BEARING HOUSING LOOSE IN BELLCRANK.SDR CA141113003Control Cable · frayed(CAN) CABLE STARTING TO FRAY AT REAR PULLEY.SDR CA141113004Control Cable · frayed(CAN) CABLE STARTING TO FRAY AT PULLEY.SDR 2014FA0000613Roller · brokenPILOT NOTED ENGINE VIBRATION AND PARTIAL POWER LOSS. UPON LANDING, FOUND EXCESSIVE OIL LEAKING FROM ENGINE. DURING TROUBLESHOOTING INSPECTION, FOUND NR 1 CYLINDER INTAKE VALVE PUSH ROD AND HOUSING BENT. AFTER REMOVING CYLINDER, THE NR 1 INTAKE ROLLER TAPPETSDR DF2S2014FA0000645Line · separatedDURING TRAINING FLIGHT, ENGINE STARTED EXPERIENCING PROBLEM. ACFT MADE A SAFE LANDING AND TAXIED TO RAMP. UPON INITIAL INSPECTION, IT WAS NOTICED THAT THE NR 2 CYLINDER FUEL INJECTION LINE HAD BECOME SEPARATED FROM WELD AT B-NUT ON FUEL NOZZLE. LINE WAS RESDR CA141023004Bulkhead · cracked(CAN) PROPELLER FORWARD BULKHEAD FOUND CRACKED UPON INSPECTION OF THE PROPELLER. THE CRACKS ARE LOCATED AT 5 OF THE 6 BOLT HOLES, IN A SEMI-CIRCLE PATTERN WHERE THE PROPELLER BOLTS WASHERS SITS. CRACKS ARE CAUSED BY WASHERS EDGE & THE PRESENCES OF THE INHERISDR OG5R2014100900593Pump · failedDURING PHASE INSPECTION, DISCOVERED FOUR PIECES OF STEEL IN OIL SUCTION SCREEN. PIECES DETERMINED TO BE SWAGED WASHER FROM TOP OF ENGINE DRIVEN FUEL PUMP PISTON ROD. NO ABNORMAL OPERATION NOTED BY PILOTS. REPLACED FUEL PUMP.SDR CA141010014Landing Light · dim(CAN) ON WALK AROUND IT WAS NOTED THAT THE RT WING LANDING LIGHTS WERE VERY DIM. PART SENT FOR INVESTIGATION.SDR N3XR2014091600008Impulse Coupling · brokenDURING THE PRE-TAKE OFF RUN UP, THE RIGHT MAGNETO HAD NO SPARK AND THE ENGINE WOULD QUIT WHEN THAT MAGNETO WAS SELECTED. THE AIRCRAFT RETURNED TO THE RAMP. INVESTIGATION REVEALED THAT THE IMPULSE COUPLING, SLICK HAD FAILED AND PIECES OF ONE FLYWEIGHT AND SHAFTSDR CA140908020Cable · worn(CAN) FOUND RT AILERON CARRY THROUGH CABLE WEARING ON PHENOLIC WEAR STRIP NEAR FLAP CONTROL ROD. CABLE HAD WEAR THAT CAUSED BROKEN STRANDS.SDR 2014FA0000537Magneto · malfunctionedTHE MAGNETO TIMING TO THE ENGINE, BOTH MAGNETOS, CHANGED FROM 25 DEGREES TO APPROXIMATELY 34-35 DEGREES OVER THE COURSE OF 93 FLIGHT HOURS SINCE NEW. BECAUSE OF WARRENTY TERMS, WE ARE NOT ALLOWED TO OPEN THE MAGNETOS TO SEE THE ACTUAL CAUSE OF THIS.SDR 2014FA0000538Magneto · malfunctionedTHE MAGNETO TIMING TO THE ENGINE, BOTH MAGNETOS, CHANGED FROM 25 DEGREES TO APPROXIMATELY 34-35 DEGREES OVER THE COURSE OF 93 FLIGHT HOURS SINCE NEW. BECAUSE OF WARRENTY TERMS, WE ARE NOT ALLOWED TO OPEN THE MAGNETOS TO SEE THE ACTUAL CAUSE OF THIS.SDR EBNS2014101000597Switch · brokenSWITCH BROKE UNDER NORMAL USAGE.SDR CA140815004Control Cable · worn(CAN) FOUND LEFT HAND AILERON CARRY THROUGH CABLES WEARING ON PHENOLIC WEAR STRIP NEAR FLAP CONTROL ROD.SDR CA140729002Points · malfunctioned(CAN) PILOT REPORTED THAT ENGINE WAS RUNNING ROUGH ON THE LT MAGNETO. MAINTENANCE RUNUP CONFIRMED THE CONDITION. AFTER CHECKING SPARK PLUGS AND IGNITION WIRES THE MAGNETO WAS REMOVED AND DISASSEMBLED AS REQUIRED TO CHECK THE POINTS AND COIL. THE POINTS WERESDR CA140724001Hose · cracked(CAN) DURING SCHEDULED 100HR INSPECTION, THE LT AFT FUEL VENT HOSE WAS FOUND WITH SURFACE CRACKS, AND MINOR LEAK WHEN PRESSURIZED. HOSE REPLACED AND SYSTEM LEAK CHECKED, NO FAULT FOUND.SDR CA140716014Grounding Strap · out of position(CAN) THE GROUND BONDING STRAP THAT GOES BETWEEN THE RUDDER LOWER HINDGE AND THE REAR FUSELAGE BULKHEAD GOT IN THE TRAVEL ARC OF THE REAR ELEVATOR BELLCRANK UPPER EVELVATOR CABLE ATTACH BOLT NUT PREVENTING MOVEMENT OF THE ELEVATOR CONTROL SYSTEM. THE STRAP IS SDR CA140618007Inertia Reel · failed(CAN) WHEN REPLACING THE REAR SHOULDER HARNESS INERTIA REEL ON THE C172, THE COVER BECAME DETACHED FROM THE ASSEMBLY AND THE RECOIL SPRING UNWOUND. IT CAME VERY CLOSE TO CAUSING INJURY TO THE AME. THE COVER APPEARED TO BE ATTACHED WITH GLUE ONLY IN 3 PLACES. WSDR KC2R2014FA0000391Impulse Coupling · crackedDURING PERFORMANCE OF A ROUTINE 500 HR INSPECTION OF MAGNETO, A CRACK WAS DISCOVERED IN IMPULSE COUPLING BASE PLATE, IN LINE WITH FLYWEIGHT AXLE. CRACK DISCOVERED DURING NDT "MAG PARTICLE INSPECTION" OF PART. IMPULSE WES REPLACED WITH NEW PART.SDR KC2R2014FA0000392Impulse Coupling · crackedDURING PERFORMANCE OF A ROUTINE 500 HR INSPECTION OF MAGNETO, A CRACK WAS DISCOVERED IN IMPULSE COUPLING BASE PLATE, IN LINE WITH FLYWEIGHT AXLE. CRACK DISCOVERED DURING NDT "MAG PARTICLE INSPECTION" OF PART. IMPULSE WES REPLACED WITH NEW PART.SDR OVDS2014FA0000292Spring · looseRUDDER RETURN SPRING BECAME DISCONNECTED FROM THE FORWARD BRACKET IN THE FRONT SECTION TUNNEL COMPARTMENT GIVING THE THE ACFT VERY LITTLE LT RUDDER CONTROL. UNABLE TO DETERMINE THE CAUSE AT THIS TIME, BOTH THE RUDDER RETURN SPRING AND THE BRACKET APPEAR TO BESDR CA140422003Bulkhead · cracked(CAN) FORWARD SPINNER BULKHEAD WAS FOUND CRACKED NEAR THE OUTSIDE OF AT LEAST 4 OF THE 6 PROPELLER BOLT HOLES. NO DAMAGE OR OTHER TRAUMA WAS NOTED ON THE SPINNER, PROPELLER OR AFT SPINNER BULKHEAD AND THE BULKHEAD WAS NOT FOUND TO HAVE BEEN STRESSED WHILE INSSDR CA140430006Control Wheel · cracked(CAN) THE CONTROL WHEEL WAS FOUND CRACKED THOUGH A NARROW SECTION OF THE BOTTOM OF THE WHEEL FROM THE MAP LIGHT HOLE TO THE FRONT EDGE OF THE CASTING. THE CRACK WEAKENS THE CONTROL WHEEL STRUCTURE AND IS LIKELY CAUSED BY NORMAL ELEVATOR-UP COMMAND INPUTS.SDR CA140603008Engine · making metal(CAN) ENGINE WAS NOTED TO BE MAKING BRONZE METAL FLAKES DISCOVERED DURING OIL FILTER INSPECTION. CYLINDERS WERE REMOVED FOR PISTON PIN PLUG REPLACEMENT AND CAMSHAFT WAS NOTED TO BE DETERIORATED. ENGINE WAS SENT OUT FOR O/H AT 2038.8 TSOH. LAST O/H DATE JUNE SDR CA140320003Control Cable · frayed(CAN) THIS IS A 2005 172S AIRPLANE WITH 1300 HOURS TOTAL TIME & THE ACFT HAS BEEN HUNGERED MOSTLY THAT WE ARE IMPORTING. DUE TO PAST EXPERIENCE OF FINDING FRAYED AILERON CABLES IN THESE MODELS, THE AILERON CABLES IN THE WINGS WERE REMOVED FOR DETAILED INSPECTSDR CA140317010Magneto · failed(CAN) WHILE TESTING THE LT MAGNETO DURING PRE-FLIGHT GROUND RUN, IT WAS NOTED THAT THE ENGINE RAN EXTREMELY ROUGH. THE LT MAGNETO WAS REMOVED AND LOOSE PARTS WERE FOUND INSIDE. MAGNETO REPLACED.
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