Continental IO-550-N
Service difficulty reports · 335
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 = 'IO550N' 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 = 'IO550N' 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 CA050803009Exhaust Header · separated(CAN) PILOT HEARD UNUSUAL EXHAUST NOISE FROM ENGINE.ON INSPECTION, FOUND NR 5 CYLINDER EXHAUST HEADER HAD SEPARATED .1875 INCH FROM THE FLANGE JUST BELOW THE WELD.SDR 2005FA0001099Mount · brokenALTERNATOR MOUNT BROKEN AND OIL LEAK. (THE ALTERNATOR CASE MOUNT FLANGE BROKEN) DRIVESHAFT IN ALTERNATOR SHEARED. THE ENGINE DRIVE SHAFT HUB HAS NO DAMAGE. (K)SDR 2005FA0000723Exhaust Header · crackedDURING AN ANNUAL INSPECTION OF THIS AC. THE NR5 EXHAUST HEADER WAS FOUND TO BE CRACKED .7500 WAY AROUND THE CIRCUMFERENCE OF THE PIPE. NR 5 EXHAUST HEADER WAS REPLACED. (K)SDR AU510001759Solenoid · failed(AUS) STARTER SOLENOID FAILED. SUSPECT CAUSED BY FAILURE AND CRACKING OF END CAP WHICH ALLOWED COPPER DUST TO LEAK OUT. (CASA NR 510001759)SDR CA050202006Control Unit · restricted(CAN) PILOT NOTICED ELEVATOR CONTROL WAS STIFFER THAN USUAL ON APPROACH. UPON LANDING, FOUND THE LT ELEVATOR BALANCE WEIGHT HORN IS RUBBING AGAINST THE HORZIONTAL STABILIZER. FOUND THE ELEVATOR WILL NOT RUB ONCE THE AIRCRAFT IS WARMED UP. THE ELEVATOR TIP FSDR 2005FA0000332Exhaust Pipe · crackedAIRCRAFT OWNER SQUAWKED MANIFOLD PRESSURE AT 11 PERCENT. FOUND EXHAUST CRACKED AT NR 5 CYLINDER EXHAUST PORT. CRACK EMINATES FROM REAR OF MOUNTING FLANGE AND SPIRALS DOWN COUNTER CLOCKWISE SEVERAL INCHES FROM THERE.SDR 2005FA0000018Oil Cooler · crackedTHIS AIRCRAFT HAS HAD AN OIL COOLER REPLACED FOR THE SAME DEFECT AT <300 HOURS. THE NEW OIL COOLER IS CRACKED AGAIN AT THE LOWER LT FLANGE AREA. NOTE: MFG HAS A SIX POINT ENGINE MOUNT OPTION AVAILABLE TO REDUCE VIBRATION IN THE AIRCRAFT. THIS AIRCRAFT HAD SDR LC12005F00000Oil Cooler · crackedOIL COOLER IS CRACKED AT THE LOWER LT FLANGE AREA.SDR 2005FA0000164Lifter · corrodedDURING A RECENT MFG SYMPOSIUM, THE PROBLEM OF UNAIRWORTHY LIFTERS IN MFG ENGINES DISCUSSED. MFG ENGINE HAVE BEEN NOT HOLDING UP WELL IN THESE AREAS AND MANY SC`S ARE RECOMMENDING AN INSPECTION OF THE LIFERS DURING SCHEDULED MAINTENANCE. THIS AC WAS UNDERGOINSDR 220192004Bolt · chafedDURING REMOVAL AND REPLACEMENT OF PN 15708-001 INDUCTION DUCT ASSY IT WAS NOTED THAT INDUCTION DUCT WAS CRACKED IN AREA OF AN3-34 BOLT WHICH SERVES AS HINGE POINT FOR ALTERNATE AIR DOOR. AFTER REMOVING BOLT IT WAS FOUND TO HAVE A GROOVE WORN INTO BOLT SHANK ASDR 22010904Bolt · chafedDURING REMOVAL AND REPLACEMENT OF THE P/N 15708-001 INDUCTION DUCT ASSY. IT WAS NOTED THAT THE INDUCTION DUCT WAS CRACKED IN AREA OF AN3-34 BOLT WHICH SERVES AS HINGE POINT FOR ALTERNATE AIR DOOR. AFTER REMOVING BOLT IT WAS FOUND TO HAVE A GROOVE WORN INTO BSDR 2201092004Bolt · chafedDURING REMOVAL AND REPLACEMENT OF THE P/N 15708-001 INDUCTION DUCT ASSY IT WAS NOTED THAT DUCT WAS CRACKED IN THE AREA OF THE AN3-34 BOLT THAT SERVES AS THE HINGE POINT FOR THE ALTERNATE AIR DOOR. AFTER REMOVING THE BOLT IT WAS FOUND TO BE CHAFFED ALL THE WAYSDR 16970704Exhaust Header · crackedTHIS AIRCRAFT HAD THE NR 1,NR 3,NR 5 HEADERS REPLACED WITH NEW PARTS AT 154.0 HRS. THE AIRCRAFT THEN EXPERIENCED A CRACK IN THE NR 5 HEADER AT 180.0 HRS. THERE DOES NOT SEEM TO BE ANY ABNORMAL STRESS ON THE PART/INSTALLATION. AIRCRAFT EXHAUST SYSTEM WILL BE MSDR B3OR20040719Hinge · looseANNUAL INSP, ALTERNATE AIR SOURCE DOOR WAS LOOSE. MECHANIC FOUND DOOR SPRING P/N 1250728-1, HINGE PIN P/N MS20253P2-364 IN INDUCTION AIR BOX DUCTING. PIN AND SPRING WERE RE-ASSEMBLED WITH DOOR. WHEN PARTS WERE RE-ASSEMBLED, BOTH UPPER AND LOWER ENDS OF HINGESDR CA040615012Hinge · corroded(CAN) FLAP HINGE ASSEMBLY HAS INTERGRANULAR CORROSION ON THE FORWARD EDGE OF THE HINGEJUST BELOW THE BOTTOM WING SKIN ABOVE THE HINGE FAIRING.SDR CA040615013Hinge · corroded(CAN) FLAP HINGE ASSEMBLY HAS INTERGRANULAR CORROSION ON THE FORWARD EDGE OF THE HINGEJUST BELOW THE BOTTOM WING SKIN ABOVE THE HINGE FAIRING.SDR CA040615014Hinge · corroded(CAN) FLAP HINGE ASSEMBLY HAS INTERGRANULAR CORROSION ON THE FORWARD EDGE OF THE HINGEJUST BELOW THE BOTTOM WING SKIN ABOVE THE HINGE FAIRING.SDR CA040615015Hinge · corroded(CAN) WING FLAP HINGE HAS INTERGRANULAR CORROSION ON THE LEADING EDGE OF HINGE JUST BELOW THE WING SKIN AND FLAP HINGE FAIRING.SDR 2004FA0000573Clamp · crackedAD WAS COMPLIED WITH AT 250 HOURS BY INSP AND INSTALLATION OF MFG SERVICE KIT (PN CK-002) (WORM TYPE CLAMP) INSTALLED ON THE FUEL PRESSURE TRANSDUCER. THE CLAMP WAS TORQUED TO THE EXACT TORQUE AS CALLED. 6/2/04-DURING AN OIL CHANGE THE CLAMP SUPPLIED IN KIT SDR 21200003AAlternator · looseTHIS ACFT HAD A ALTERNATOR NR 1 FAIL LIGHT. UPON TROUBLE SHOOTING IT WAS FOUND THAT THE AFT HOUSING OF THE ALTERNATOR WAS LOOSE. FOUR SCREWS ATTACHING THE HOUSING WERE STILL SAFETY WIRED. IT DOES NOT APPEAR THAT SCREWS HAD LOOSENED OR THAT THE FORWARD HOUSINSDR CA040107008Oil Cooler · cracked(CAN) OIL COOLER FOUND CRACKED ON OB FORWARD LOWER CORNER FLANGE WHERE THE BAFFLE IS ATTACHED. CRACK IS ABOUT 1 INCH LONG. THIS IS THE THIRD COOLER FOUND CRACKED ON THE TYPE OF INSTALLATION.SDR 7011203Connector · looseAIRCRAFT WAS IN FOR AN ANNUAL INSPECTION. A FUEL LEAK WAS NOTED AS A DISCREPANCY. FURTHER INVESTIGATION REVEALED THAT THE ORIGIN OF THE LEAK WAS COMING FROM A HOSE/BULKHEAD FITTING CONNECTION ON THE FIREWALL. THE HOSE B-NUT WAS FOUND TO BE FINGER TIGHT. THE FISDR 2003FA0001246Link · mismanufacturedWHILE RIGGING AC, USING TORQUE SPEC FROM MFG MM. AILERON FINAL CONTROL LINK THREADS WERE DESTROYED WHILE ATTEMPTING TO REACH LOW END OF SPECIFIED TORQUE (REF MFG MM CHAP 27, SECT 27-10, B., STEP 9). THE MFG WAS NOTIFIED OF THIS SITUATION AND RESPONDED WITH: SDR 2003FA0001275Starter · wornSTARTER ADAPTER FAILURE. STARTER WOULD NOT TURN ENGINE. NO METAL CHIPS FOUND IN ENGINE OIL AT THIS TIME BUT POTENTIAL EXISTS WITH THIS TYPE OF FAILURE.SDR CA031030002Condenser · failed(CAN) FOUND MAGNETO IS ALIVE WITH MAGNETO SWITCHED OFF. CONDENSOR IS OPEN CIRCUIT INTERNALLY.SDR 8010304Lanyard · misroutedTHE AIRCRAFT CAME INTO OUR FACILITY FOR AN ANNUAL INSPECTION. WHILE PERFORMING THE INSPECTION IT WAS NOTED THAT THE PARACHUTE LANYARD CABLES THAT CONNECT THE ROCKET PICK-UP COLLAR TO THE PARACHUTE WERE MISROUTED. THIS WAS MOST LIKELY DONE WHEN ACCOMPLISHING CASDR 2003FA0001074Hinge · damagedINSP ON STOP-TO-STOP TRAVEL OF LT AILERON, NOTICED ODD DOUBLE BUMP SOUND, MVMT AT STOPS. LT WINGTIP, AILERON WERE REMOVED TO FACILITATE FURTHER INSP. IB AILERON HINGE MOVED UP AND DOWN WITH FORCE APPLIED TO IT. VERT MVMT (0.053”) WAS MEASURED APPROX AT BRG SDR 2003FA0000867Attach Bolt · improper partFOUND LOWER ENGINE MOUNT TO FIREWALL BOLTS LOOSE. BOTH LOWER BOLTS WERE TO LONG AND GRIP LENGTH TO LONG. REPLACED BOTH BOLTS WITH PROPER SIZE AND TORQUED TO SPECS.SDR 2003FA0000809Cylinder · out of toleranceDURING ENGINE ASSEMBLY AFTER LIGHTING STRIKE INSPECTION IN ACCORDANCE WITH TCM SB M88-9 FOUND ALL CYLINDERS TO HAVE EXCESSIVE DRY LIFTER CLEARANCE. MANUFACTURERS SPECIFICATION IS .060 TO .200 INCH., ALL CYLINDER ALL VALVES EXCEEDED .200 INCH CLEARANCE.SDR CA030731007Dipstick · broken(CAN) THE DIPSTICK SEPARATED & BROKE OFF FROM THE CAP.SDR 2003FA0000568Oil Cooler · crackedOIL COOLER CRACKED AT OUTBOARD FLANGE, AT BAFFLING MOUNT. THIS IS THE TENTH OIL COOLER ON A/C THAT OUR REPAIR STATION HAS SEEN WITH A CRACKED OIL COOLER IN THE EXACT SAME LOCATION. MFG HAS AN OPTIONAL SB22-71-03 BAFFLE MODIFICATION THAT SUGGESTS THAT THE BAFSDR 2003FA0001280Starter Gen · failedSTARTER ADAPTER FAILED. WOULD NOT TURN PROP. NO METAL WAS FOUND IN THE ENGINE OIL THIS TIME BUT POTENTIAL EXISTS WITH THIS TYPE FAILURE.SDR R895W25Plate · delaminatedDURING ANNUAL INSPECTION, FOUND LOWER FORWARD FUSELAGE EXHAUST HEAT PLATE DELAMINATED. FURTHER INSPECTION REVEALED HOT SPOT UNDERNEATH CO-PILOT'S RUDDER PEDAL INSPECTION PANEL ABOVE THE EXHAUST AREA OUTLET. ALSO FOUND VISIBLE LIGHT SHOWING THROUGH THE COMPOSSDR 2002FA0001042Grommet · deformedDURING ANNUAL INSPECTION FOUND MAIN GEAR LEG ATTACH BRACKET GROMMETS SEVERELY CRACKED AROUND FLANGES AND DISTORTED. HAVE FOUND SIMILAR CONDITION ON SEVERAL CIRRUS SR20 AND SR22 AIRCRAFT WITH TOTAL TIME IN SERVICE AS LOW AS 105 HOURS. TOTAL FAILURE OF THE GROMSDR 99ZZZX3473Crankshaft · failedENGINE SHOOK VIOLENTLY. MIXTURE CONTROL WAS PULLED BACK TO CUT-OFF IMMEDIATELY. THE ENGINE SEIZED UP. A SAFE LANDING WAS MADE. TEAR-DOWN INSPECTION REVEALED THE CRANKSHAFT HAD FAILED.
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