Continental IO-550-F
Service difficulty reports · 81
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 = 'IO550F' 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 = 'IO550F' 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 AU510001780Cylinder · deterioratedENGINE CYLINDER NICKEL CARBIDE CYLINDER WALL COATING SEPARATED FROM BARREL. AREA OF MISSING COATING WAS APPROXIMATELY 10MM BY 35MM (0.39IN BY 1.37IN) LOCATED AT THE TOP OF THE BORE NEAR THE TOP SPARK PLUG HOLE.SDR CA051111003Cylinder · cracked(CAN) CYLINDER NR 4 HAD LARGE CRACK ACROSS CYLINDER, BELOW TOP SPARK PLUG HOLE. A CYLINDER DIFFERENTIAL CHECK CONFIRMED CYLINDERS 2, 6, AND 3 TO HAVE CRACKS IN THE SAME GENERAL LOCATION. ALL 6 CYLINDER ASSEMBLIES WHERE REMOVED. 6 NEW CYLINDER ASSEMBLIES P/N SDR CA050907004Radio · odor(CAN) UPON DEPARTURE FROM THE AIRPORT, THE PILOT SMELLED SMOKE IN THE COCKPIT. RETURNED TO THE AIRFIELD AND HAD MAINTENANCE INSPECT THE AIRCRAFT. RADIO NR 2 HAD A BURNT SMELL TO IT. RADIO WAS REMOVED AND DEFECT DEFERRED. PILOT CONTINUED ON WITHOUT FURTHER SDR AU510001865Cylinder · unserviceableENGINE CYLINDER DAMAGED. A PIECE OF THE NICKEL CARBIDE BORE COATING MISSING FROM THE TOP AREA OF THE CYLINDER BORE. SIZE OF MISSING PIECE APPROXIMATELY 20MM BY 5MM BY 0.254MM DEEP (0.78IN BY 0.19IN BY 0.010IN DEEP). THE SECOND COMPRESSION RING WAS ALSO FOUNSDR 2005FA0000970Cylinder Head · separatedHEAD SEPARATED FROM CYLINDER IN FLIGHT. NO INJURIES. NO INCIDENT. (K)SDR CA050503016Torque Link · cracked(CAN) FOUND CRACKED ON INSPECTION, ABOUT 1 INCH FROM THE FRONT OF THE SCISSOR ON THE BOTTOM CURVE ON BOTH SIDES. CRACK WAS ABOUT .1250 OF AN INCH LONG.SDR 2005FA0000951Connecting Rod · failedIN SLOW DESCENT FOR LANDING AT 3,000 FT AGL, SEVERE VIBRATION OCCURRED AND THEN WITHIN 30 SECONDS A LOUD BANG AND OIL COVERING WINDSHIELD AND SIDE WINDOWS. DIVERTED FLT ABOUT 5-6 MILES AWAY AND MADE SAFE LANDING AT AIRPORT. UPON INSPECTION, NR 2 ROD PENETRATEDSDR 2005FA0000569Bearing · damagedUPON DISASSEMBLY IT WAS NOTED THAT THIS BEARING SHELL IS BROKEN. IT IS LOCATED IN NR 2 FROM REAR SADDLE. IT APPEARS THAT THE BEARING HAS WORKED AND IS POLISHED AS RESULT: THE CRANKSHAFT, SN C159618N HAS OVERSIZED BLADE BUSHING BOSSES. UPON DISASSEMBLY, (LOSDR 2005FA0000813Main Bearing · disintegratedMETAL WAS FOUND IN OIL FILTER. CLEANED WENT FOR TEST FLIGHT, LOST OIL PRESSURE. ENGINE REMOVED, WITNESSED TEARDOWN. FOUND NR 2 MAIN BEARING SPUN AND DISINTEGRATED. CRANKSHAFT CHECKED OUT OK. ENGINE CASE WAS BADLY DAMAGED AT THE NR 2 BEARING BOSS ENGINE HASDR CA041019007Rod · wrong part(CAN) IMPROPER INSTALLATION OF THE OIL GAUGE ROD TUBE ADAPTER SPIGOT INTO THE CRANKCASE SUCH THAT IT EXTENDS TOO FAR INTO THE CASE ALLOWING THE OIL GAUGE ROD TO PROTRUDE TOO FAR INTO THE OIL SUMP AND CAUSING IT TO MAKE CONTACT WITH THE OIL SUMP. THE CONTACT CASDR CA041018005Cylinder · leaking(CAN) DURING THE FOLLOW-UP INSPECTION, COMPRESSION WAS FOUND WITHIN LIMITS BUT A SOAP LEAK TEST FOUND NR 5 CYLINDER LEAKING.THE CYLINDER ASSY WAS REMOVED WITH NO DEFECTS VISIBLE. THE LEAK SEAMS TO BE FROMBETWEEN THE CYLINDER BARREL AND HEAD WHERE THEY SCREW TOSDR CA041018004Cylinder · cracked(CAN) DURING A 50 HOUR INSPECTION, NR 4 CYLINDER WAS FOUND TO HAVE ZERO COMPRESSION.CLOSER EXAMINATION FOUND CRACKS EXTENDING FROM BOTH SPARK PLUG HOSE INTO THE EXHAUST PORT AND CYLINDER HEAD.A FOLLOW-UP ISPECTION INCLUDING COMPRESSON TEST AND SOAP LEAK TEST WSDR CA041006008Throttle Cable · broken(CAN) PILOT MAKING AN APPROACH TO SCHEDULED LANDING WHEN ENGINE POWER WENT TO IDLE WITH NO RESPONSE TO ACTIONS OF THROTTLE CONTROL. PILOT ELECTED TO LAND IN FIELD SHORT OF RUNWAY AND EXPERIENCED NO DIFFICULTY. AIRCRAFT EQUIPPED WITH TUNDRA TIRES. MAINTENANCESDR CA040709003Screw · worn(CAN) DURING ENGINE START, FIRST FLIGHT OF THE DAY, OIL PRESSURE WAS OBSERVED AS BEING TOO HIGH (75 PSI AT IDLE). SYSTEM BLOCKAGE WAS SUSPECTED, OIL FILTER INSPECTED (CLEAR), OIL DRAINED AND INSPECTED (CLEAR), PRESSURE CHECKED AT OTHER PRESSURE POINTS IAW MFGSDR CA040526008Fan · failedSHORTLY AFTER TAKEOFF SMOKE WAS OBSERVED IN THE COCKPIT AND EMERGENCY WAS DECLARED AND THE AIRCRAFT RETURNED FOR LANDING. AT THIS TIME THE AIRSPEED WAS READING EXTREMELY LOW. INVESTIGATION REVEALED THE STROBE/AVIONICS COOLING FAN CIRCUIT BREAKER OPEN. THE FSDR CA031103004Exhaust Valve · broken(CAN) THE FLIGHT CREW REPORTED A MINOR ENGINE VIBRATION AND HIGH NR 2 CYLINDER EGT AS WELL AS ERRATIC CHT INDICATIONS. EXAMINATION FOUND THAT DUE TO FAULTY INFORMATION FROM THE MULTI PROBE SYSTEM THE OBSERVED INFORMATION ACTUALLY REFLECTED NR 6 CYLINDER OPERASDR CA030514016Door Frame · cracked(CAN) DURING A CESSNA CONTINUED AIRWORTHINESS PROGRAM INSPECTION 53-10-02 A 2 INCH CRACK WAS NOTED IN THE DOOR POST AT THE BOTTOM LEFT OF THE WINDOW. A REPAIR HAD TO BE COMPLETED IN ACCORDANCE WITH CESSNA SEB 93-4 BY INSTALLING THE DOORPOST MODIFICATION KIT SKSDR CA030325007Cylinder · worn(CAN) ON INSPECTION OF 2 CYLINDERS, 1ST CYLINDER MEASUREMENT OF THE BARREL OF THE CYLINDER VARIES FROM 5.252' AT THE ENTRANCE OF THE CYLINDER AND 5.255' AT THE BOTTOM. MAXIMUM LIMITS ARE 5.256 INCHES. WE DISCOVERED A 'STEP' (SEE PHOTO) AT THE BOTTOM 0.008 DEESDR CA030726006Rivet · loose(CAN) LOOSE RIVETS ON BOTH WINGS AT AILERON HINGE BRACKET REPLACED.SDR CA030726005Alternator · failed(CAN) LOSS OF ALTERNATOR POWER. ALTERNATOR OVERHAULED.SDR CA020906001Link · severed(CAN) AMPHIB FLOATS SELECTED TO DOWN POSITION AND AIRCRAFT LANDED ON RUNWAY. THE PILOT FELT THE RT AFT FLOAT CONTACT PAVEMENT AND IMMEDIATELY INITIATED A GO-AROUND. SELECTED GEAR UP AND LANDED WITH NO INCIDENT ON THE WATER. INSPECTION FOUND THE RT MLG ACTUATSDR CA030726003Throttle · malfunctioned(CAN) NEW THROTTLE INSTALLED DUE TO MALFUNCTION.SDR 2002FA0000109Distributor · burnedMAGNETO HAD FAILED 9.3 HOURS AFTER BEING SUPPLIED AS A PART OF A FACTORY REBUILT ENGINE. IT WAS DISASSEMBLED AND THE DISTRIBUTOR, COIL, CAPACITOR AND BREAKER WERE REPLACED. MAGNETO WAS CHECKED OK. 2.5 HOURS AFTER THIS REPAIR THE MAGNETO FAILED AGAIN. THE DSDR 2002FA0000101Distributor · burnedMAGNETO FAILED - WOULD NOT RUN AT ALL. THE DISTRIBUTOR GEAR SUPPORT WAS FOUND TO BE BADLY BURNED SHOWING DEEP TRACKING FROM SPARKS GOING FROM THE SHAFT TO GROUND ON THE M3485 BEARING CAP BY ARCING ACROSS THE SUPPORT. SUPPORT HAS A DEEP TRACK BURNED ACROSS ITSDR 2002FA0000100Distributor · burnedMAGNETO FAILED - WOULD NOT RUN AT ALL. THE DISTRIBUTOR GEAR SUPPORT WAS FOUND TO BE BADLY BURNED FROM SPARKS GOING FROM THE THE SHAFT TO GROUND ON THE M3485 BEARING CAP BY ARCING ACROSS THE SUPPORT. SUPPORT IS BADLY MELTED. M3215 CARBON BRUSH IS BURNED ALSOSDR CA010831006Tube · leaking(CAN) NR 5 CYLINDER FUEL DISTRIBUTION TUBE RUPTURED DURING CRUISE FLIGHT. TUBE BREAK IS AT THE CONNECTION TO FUEL DISTRIBUTOR VALVE. CONNECTION POINT A CYLINDER REMAINED INTACT. FAILURE OCCURRED AT FLANGE END WHERE TUBE FLARE END IS BRAZED TO TUBE ASSY. NO POSSDR CA010821011Arm · cracked(CAN) DURING A 200 HOUR ANNUAL INSPECTION, THE PILOT R/H RUDDER PEDAL ARM FOUND LOOSE. THE ARM WAS CRACKED IN TWO PLACES: FROM EACH OF THE ATTACH BOLT HOLES TO THE BOTTOM OF THE TUBE.SDR CA010320018Line · chafed(CAN) LINE ASSEMBLY - FUEL, STRAINER TO ELBOW FOUND CHAFING AGAINST RT NOSE GEAR STEERING BOOT.1.50 INCH X 0/032 INCH TUBING FOUND WORN BY 0/018 INCH ON ONE SIDE. PART HAS BEEN REPLACED WITH A NEW LINE ASSEMBLY - FUEL AND PROTECTED WITH NYLON SPIRAL WRAP.SDR CA000714031Exhaust Pipe · burned(CAN) EXHAUST COLLECTOR FOUND BURNED AND CRACKED.SDR CA000614010Throttle Control · defective(CAN) AT SCHEDULED MAINTENANCE FUNCTION, THE THROTTLE CONTROL WAS FOUND TO BE DEFECTIVE. THE OUTER CASING (SHROUD) HAD SEPARATED AT A SWAGED FITTING NEAR THE ENGINE END.SDR 99ZZZX2471Counterweight · looseDURING START-UP OF THE ENGINE, THE NR 1 CYLINDER TRAILING COUNTER WEIGHT ON THE CRANKSHAFT CAME LOOSE FROM CRANKSHAFT AND MADE A HOLE IN THE TOP OF THE CASE. CSB99-3A HAD BEEN COMPLETED 1.7 HOURS PRIOR. REASON FOR FAILURE UNKNOWN AT THIS TIME.
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