Lycoming O-360-C2A
Service difficulty reports · 18
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 = 'O360C2A' 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 = 'O360C2A' 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 2026FA0000405Mount · brokenENGINE MOUNT COMPLETE BROKEN IN TWO PARTS.SDR CA150817023Switch · failed(CAN) DURING THE 100 HR INSPECTION THE MAINTENANCE PERSONAL WENT TO TEST THE ELT FOR PROPER FUNCTION. THE REMOTE ELT SWITCH WAS ATTEMPTED TO BE ACTIVATED AND FOUND TO BE EXTREMELY STIFF. AN ABNORMAL AMOUNT OF PRESSURE WAS APPLIED AND THE SWITCH FINALLY MOVEDSDR CA130117013Camshaft · making metal(CAN) DURING A 100 HR INSPECTION, METAL FILINGS WERE DISCOVERED IN THE OIL FILTER. CYLINDER 2 AND CYL NR 4 WERE REMOVED AND THE CAMSHAFT INSPECTED. MISSING METAL WAS DISCOVERED ON THE NR 2 CYL EXHAUST LOBE. IN ADDITION WERE AND PITTING HAVE BEEN OBSERVED ON TSDR CA110222005Crankshaft · corroded(CAN) A COMPANY DIRECTED 2 YEAR INSPECTION OF THE ID OF THE CRANKSHAFT IAW SB 505B WAS COMPLETED AND PITTING WAS DISCOVERED. THE ID IS NOW AT MAX LIMITS AND PITTING REMAINS AND AN NDT INSPECTION WAS COMPLETED AND WILL BE COMPLETED EVERY 100 HRS AS REQUIRED IASDR 2010FA0001123Dipstick · brokenOIL DIP STICK BROKE AND DROPPED INTO CRANKCASE. DIP STICK TUBE EXTENSION IS INSTALLED AND DIP STICK ANCHORED END FITS INTO CAP CASTING AND IS SECURED BY A ROLL PIN. ANCHORED END OF DIP STICK FRACTURED AND SEPARATED AT LOWER HALF OF HOLE THAT ROLL PIN PENETRASDR CA090121005Crankshaft · corroded(CAN) UPON DESLUGING THE INNER BORE OF THE CRANKSHAFT, IT WAS DISCOVERED THAT THE PID COATING HAD BEGUN TO BUBBLE AND CHIP OFF. THE PID WAS REMOVED AND SURFACE CORROSION WAS DISCOVED UNDER THE PID SIMMILAR TO THAT REFERENCED IN AD 980208 AND SB 505B. IT SHOULDSDR CA081204008Hinge Pin · rusted(CAN) AN ATTEMPT TO REMOVE THE ENTRANCE DOOR USING THE EMERGENCY EXIT HANDLE FOUND THAT THE SYS HAD BECOME SEIZED. UPON CLOSER INSP, IT WAS FOUND THAT THE HINGE PIN (DISPITE PERIODIC LUBING) HAD BECOME RUSTED TO THE AIRFRAME PIN TABS. THE DOOR CONTINUED TO OSDR CA080806015Tire · damaged(CAN) TAIL WHEEL TIRE FOUND FLAT DURING TAXI, UPON DISASSEMBLY IT WAS FOUND THAT THE INNER CORDS WERE FOUND LET GO AND CUT THE TUBE.SDR 2006FA0000758Cylinder Head · separatedTHIS WAS A NEW CYLINDER INSTALLED APRIL 05, AT ENGINE OVERHAUL. THE CYLINDER COMPLETELY SEPARATED BETWEEN THE HEAD AND BARREL, IN FLIGHT. THE AIRCRAFT WAS SAFELY LANDED AT HOME AIRPORT. PN STAMPED ON CLY BASE: AEL65102, SN12.0F. (K)SDR CA050706005Control Cable · frayedRT FLAP CABLE FRAYED AT WING ROOT PULLEY. THIS CABLE WAS A GALVANIZED CABLE.SDR CA040525001Control Cable · frayedSTAINLESS STEEL CABLES, LT AND RT, FRAYED AT WING ROOT PULLEY. FLAP DOWN POSITION.SDR CA031201003Wire · chafed(CAN) NAV WIRE IN LT WING FOUND ATTACHED WITH MASKING TAPE TO COMPRESSION TUBE. WIRE WAS CHAFING ON TUBE AND EXPOSED WIRE CAUSING SHORT AGAINST COMPRESSION TUBE, BLOWING FUSE.SDR CA030616003Frame · broken(CAN) FRAME TUBE WAS BROKEN OFF ON BOTH SIDES OF TAIL SPRING FWD ATTACH BUSHING.SDR CA021031004Fuel Tank · cracked(CAN) ALUMINUM SPAR WINGS.- CRACK LOCATION ON WELD OF PREVIOUS REPAIR.SDR CA020523012Control Cable · frayed(CAN) LT AND RT FLAP UPPER CABLES FRAYED AT WING ROOT PULLEYS.SDR CA020112001Fuel Tank · leaking(CAN) FUEL LEAK DISCOVERED BY VISIAL INSPECTION AT FABRIC DRAIN HOLES IN TE OF WING. INBOARD FUEL TANK OF LEFT WING REMOVED AND PIN HOLE FOUND IN THE WELD WHERE DRAIN BOSS WHERE FUEL HOSE ATTACHES. BOSS REWELDED AND PRESSURE TESTED TANK. NO FURTHER LEAKS SDR CA970505007Clamp · wrong type(CAN) SHORTLY AFTER REFUELING THE AIRCRAFT, A MAJOR FUEL LEAK OCCURRED. INVESTIGATION REVEALED THAT THE INCORRECT SIZE OF CLAMPS WERE INSTALLED ON AN INTERCONNECT FUEL TANK HOSE. THE CLAMP FOUND IN USE WAS AN AN737TW-74. THE PARTS MANUAL SHOWS AN AN737TW-56 CLSDR CA960722008Control Cable · frayed(CAN) ON INSPECTION THE ELEVATOR CABLE WAS FOUND FRAYED WHERE IT PASSES OVER THE UPPER REAR PULLEY.
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