Lycoming O-360-C2E
Service difficulty reports · 129
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 = 'O360C2E' 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 = 'O360C2E' 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 CA011130004Control Cable · frayed(CAN) - LT & RT UPPER FLAP CABLES FRAYED AT WING ROOT PULLEYS. BOTH LT & RT PULLEYS FOUND SEIZED AND WORN.SDR CA011130005Fuel Tank · cracked(CAN) RT OUTBOARD TANK CRACKED, LOWER SIDE, AT THE END OF REINFORCING INDENT, ON PREVIOUSLY REPAIRED WELD.SDR CA011130001Pulley · seized(CAN) - LT & RT PULLEYS AT WING ROOT FOUND SEIZED AND WORN. - BOTH FLAP CABLES FRAYED AT THAT POSITION. - SMALL ALUMINUM PULLEYS, HARD TO LUBRICATED AND PROVIDE A TIGHT DEFLECTING RADIUS FOR CABLES.SDR CA011130002Control Cable · frayed(CAN) - LT & RT UPPER FLAP CABLES FRAYED AT WING ROOT PULLEYS. BOTH LT & RT PULLEYS FOUND SEIZED AND WORN.SDR CA021114009Control Cable · frayed(CAN) LT AND RT RUDDER CABLES FRAYED AT CABIN PULLEYS. BOTH CABLES MADE OF STAINLESS STEELSDR CA011031012Pulley · worn(CAN) - LT & RT PULLEYS INBOARD & OUTBOARD ALL FOUND WORN.- LT & RT CABLES FRAYED UNSERVICEABLE AND REPLACED. - CABLES FRAYED AT PULLEYS ON OUTBOARD POSITION.- SOLID ALUMINUM PULLEYS WITH SMALL RADIUS AND SEIZE EASILY CAUSING EXCESSIVE CABLE WEAR.SDR CA021114007Control Cable · frayed(CAN) LT AND RT RUDDER CABLES FRAYED AT CABIN PULLEY. BOTH CABLES MADE OF STAINLESS STEEL.SDR CA011120003Cable · frayed(CAN) BOTH LT AND RT CABLES FRAYED JUST INCHES FWD OF BAGGAGE COMPARTMENT PULLEYS.SDR CA021114005Control Cable · frayed(CAN) LT AND RT RUDDER CABLES FRAYED AT CABIN. PULLEY CABLES MADE FROM STAINLESS STEEL.SDR CA010813022Shutoff Valve · failed(CAN) - THREADED COLLAR THAT SECURES VALVE SHAFT IN BODY CAME LOOSE AND DETACHED ITSELF FROM SHUTOFF BALL INSIDE VALVE. FOR SOME REASON THE VALVE WAS OR WENT INTO THE CLOSED POSITION & STARVED THE ENGINE FOR FUEL DURING TAXI OUT FOR DEPARTURE. - THERE IS NOTHISDR CA010813021Structure · cracked(CAN) - FUEL TANK CRACKING. - POSSIBLY DUE TO TOO LIGHT GUAGE OF MATERIAL & NO INTERNAL BAFFLES INTANK. CRACKS USUALLY OCCUR AT END OF STIFFENER INDENTS. - WE AVERAGE 2-3 FUEL TANK FAILURE DUE TO CRACKING PER FLYING SEASON.SDR CA010628028Pulley · seized(CAN) ON 100 HR, INSPECTION TECHICIAN DISCOVERED 2 FLAP SYSTEM PULLEYS INSIDE FUSELAGE SEIZED AND FLATS WORN INTO THEM FROM CABLE RUBBING. THIS IS AN ONGOING PROBLEM FOR US AS ALMOST EVERY 100 HR INSP. WE ARE FINDING THIS AND OFTEN HAVE TO CHANGE CABLES ALSO. SDR CA010628016Pulley · seized(CAN) LT AND RT PULLEYS FOUND SEIZED AT WING ROOT(100 HOUR INSP.) BOTH CABLES FREYED AND UNSERVICEABLE. (LT/RT) AT POSITION OF PULLEY.SOLID ALUMINUM PULLEYS, NO BEARING , DIFFICULT TO KEEP LUBRICATED. HIGH POTENTIAL FOR INFLIGHT FLAP CABLE FAILURE.SDR CA001207027Mount · cracked(CAN) ENGINE MOUNT WAS REMOVED FOR NDT INSPECTION DURING ENGINE CHANGE DUE TBO. (X)SDR CA001106002Bracket · failed(CAN) IN-FLIGHT FAILURE OF REAR HALF OF BRACKET CAUSING ALTERNATOR FORWARD MOUNT TO BREAK. PILOT NOTICED BURNING SMELL IN COCKPIT FROM ALTERNATOR BELT AND UPON LANDING, INVESTIGATED AND FOUND ALTERNATOR HANGING ONLY BY THE WIRES AND SUPPORT OF 1 SCAT HOSE. (SDR CA001018004Bracket · cracked(CAN) ON 100 HOUR INSPECTION, LOWER STABILIZER ATTACHMENT BRACKET, WHICH SPANS BETWEEN TAIL POST AND STAB AFT SPAR FITTING, WAS FOUND CRACKED APPROXIMATELY 1 INCH UP FROM LOWER WELD AREA. CRACKS FOUND ON BOTH SIDE ANGLES.SDR CA001207026Mount · cracked(CAN) ON PER FLIGHT PILOT NOTICED LT FLAP WAS NOT FAIRED WITH UPPER WING GAP COVER.FURTHER INSPECTION FOUND L/H INBOARD FLAP MOUNT LOWER BOLT HOLE CRACKED OUT.DUE TO PREVIOUS FAILURES, A FLEET VIAUAL SPECIAL INSPECTION WAS CARRIED OUT, ON INBOARD FLAP MOUNTS, SDR CA000829012Mount · cracked(CAN) PILOT REPORTED A TENDENCY FOR A/C TO ROLL TO RIGHT, ON FULL FLAP SELECTION. VISUAL INSPECTION INDICATED L/H INBOARD FLAP MOUNT HAD CONSIDERABLE VERTICAL MOVEMENT. FURTHER INSPECTION REVEALED THAT INBOARD FLAP MOUNT LOWER ATTACHMENT POINT HAD BROKEN FREE.SDR CA990715017Cylinder Head · cracked(CAN) ENGINE VIBRATION AND POWER LOSS WHILE GLIDER IN TOW. CRACK AROUND NR 2 CYLINDER. CYLINDER HAD BEEN OVERHAULED SUBJECT TO FREEDOM FREE PROCESS AND CERMICROME PLATING.SDR CA990715021Mount · cracked(CAN) IN DESCENT AFTER GLIDER RELEASE AND AFTER EXTENDING FLAPS TO 27 DEGREES, PILOT NOTICED UNCOMMANDED ROLL TO THE RIGHT. VISUAL INSPECTION INDICATED THAT THE LEFT FLAP APPEARED TO BE IN APPROPRIATE POSITION, WHILE RIGHT FLAP WAS AT APPROXIMATELY 7-12 DEGRESDR CA990303012Frame · cracked(CAN) THE FRAME FOUND CRACKED ALL THE WAY AROUND APPROXIMATELY 2 INCHES UP FROM THE BOTTOM.SDR CA990303013Frame · cracked(CAN) CRACK FOUND AT WELD AROUND FRAME. THIS IS THE TAILWHEEL SPRING FORWARD ATTACH POINT. ALSO P/N 7-1470-36.SDR CA980608004U-Bolt · broken(CAN) DURING POST-FLIGHT INSPECTION, PILOT NOTICED RIGHT LANDING GEAR U-BOLT BROKEN. REPLACED.SDR CA980407007Engine · making metal(CAN) ENGINE REMOVED DUE TO NON-FERROUS METAL IN THE OIL SCREEN. ENGINE SHIPPED FOR REPAIR. REPORT TO FOLLOW.SDR CA970731013Gear Leg · broken(CAN) LEFT MAIN GEAR FAILED DURING TAXI ONTO RUNWAY FROM GRASS LANDING AREA. FAILURE OCCURRED IN THE MAIN GEAR LEG JUST PAST THE ATTACHMENT SADDLE. GEAR LEG COMPLETELY SEPARATED FROM THE AIRCRAFT STRUCTURE. WING AND PROP CONTACTED THE GROUND.SDR CA960909030Valve · missing rivets(CAN) TWO RIVETS FOUND MISSING AND ALL OTHERS WERE FOUND TO BE LOOSE, ATTACHING BOTH REINFORCING STRIPS.SDR CA960711012Engine · vibrations(CAN) PILOT REPORTED AN ENGINE VIBRATION THAT WAS MOST NOTABLE AT 1000-1200 RPM. PROP HAS BEEN OVERHAULED AND BALANCED, SWAPPED FROM A SISTER AIRCRAFT AND TRACKED CHECKED. CARBURETOR HAS BEEN CHECKED, VIBRATION WAS SEVERE ENOUGH TO LOOSEN THE THROUGH BOLTS ON SDR CA960711011Bracket · cracked(CAN) CRACKS FROUND IN LEFT AND RIGHT ARM OF THE LOWER AFT STAB BRACKET. THIS PART HAS BEEN FOUND CRACKED BEFORE AND REPAIRED BY WELDING. THESE LATEST CRACKS WERE FOUND THROUGH OR NEXT TO THE PREVIOUS REPAIRS. WELD REPAIRS WERE ONCE AGAIN CARRIED OUT.SDR CA960610004Rubber Bushing · deteriorated(CAN)ON ANNUAL INSPECTION, THE LOWER RIGHT ENGINE MOUNT RUBBER BUSHING FOUND SEVERELY DETERIORATED. THIS MOUNT IS DIRECTLY BELOW THE OIL FILLER TUBE AND IS SUSCEPTIBLE TO OIL SPILLAGE.
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