Continental IO-240-B
Service difficulty reports · 346
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 = 'IO240B' 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 = 'IO240B' 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 CA081110003Spar · delaminated(CAN) DURING THE 6000 HOUR INSP DELAMINATIONS AND CRACKS WERE DISCOVERED ON THE SPAR BRIDGE. THE DELAMINATIONS AND CRACKS WERE FOUND ON THE RT SIDE ON THE AFT UPPER CORNER AT THE FILLET FROM BRIDGE TO SKIN INSIDE OF THE FUESLAGE AS VIEWED FROM THE GAS TANK ARESDR CA081106006Arm · cracked(CAN) BOTH ARMS OF THE NLG WHEEL FORK ASSY WERE FOUND CRACKED APPROXIMATELY 1.75 INCH FWD OF THE WHEEL AXLE BOLT. BOTH ARMS ARE CRACKED THRU THE LOWER PORTION AND A .25 INCH CRACK HAS STARTED ON THE UPPER SIDE OF THE ARMS.SDR CA081028004Tube · worn(CAN) DURING ROUTINE INSP/OPS CHAEK IT WAS FOUND THAT THE S-TUBE WHICH ALLOWS FOR THE POSITIONING OF THE RUDDER PEDAL ON THE PILOTS RT SIDE, HAD WORN THE CABLE TO THE POINT OF FINDING A FEW BROKEN CABLE STRANDS. THE RUDDER CABLES WERE ONLY DUE FOR REPLACEMENT SDR CA081009011Rudder Pedal · worn(CAN) ACFT WAS INSPECTED BY MAINT TO REPLACE A DEFECTIVE RUDDER PEDAL ADJUSTING CABLE. UPON COMPLETION OF THE JOB IT WAS NOTICED THAT THE SLIDE ASSY WAS NOT ABLE TO MAKE FULL TRAVEL. CLOSER INSP FOR OTHER SYMPTOMS REVEALED THAT THE RUDDER CABLE HAD WORN THROUGSDR CA081008002Bracket · cracked(CAN) ON SEPTEMBER 2, 2008, DURING A ROUTINE 100 HOUR INSPECTION THE ALTERNATOR MOUNTING BRACKET WAS FOUND TO BE CRACKED ON THE INSIDE RADIUS OF THE BRACKET RIGHT NEXT TO 1 OF THE 2 MOUNTING BOLT HOLES. THIS WAS THE SECOND CRACKED BRACKET FOUND ON THIS ACFT ANSDR CA081008003Bracket · cracked(CAN) ON MARCH 14, 2008, DURING A ROUTINE 100 HOUR INSPECTION THE ALTERNATOR MOUNTING BRACKET WAS FOUND TO BE CRACKED ON THE INSIDE RADIUS OF THE BRACKET RIGHT NEXT TO 1 OF THE 2 MOUNTING BOLT HOLES.SDR CA080214001Rudder Pedal · corroded(CAN) IT HAS BEEN NOTICED THAT ALTHOUGH THIS AREA IS LUBRICATED IAW THE MFG MAINT SCHEDULE WITH LPS2, THIS AREA CONTINUOUSLY CORRODES TO THE POINT THAT IT AFFECTS THE POSITIONING OF THE RUDDER PEDALS. (TC NR 20080214001)SDR CA081211002Propeller · cracked(CAN) PRIOR TO A TRAINING FLIGHT WITH A STUDENT A WALK AROUND WAS PERFORMED ON THE ACFT WHERE IT WAS NOTED THAT ONE OF THE PROPELLER BLADE LEADING EDGE TIPS HAD AN INDICATION OF POSSIBLE ROCK CHIP DAMAGE OF APPROXIMATELY .2500 INCH IN LENGTH AND LESS THAN A .0SDR 2008FA0000067Gear · making metalPRIOR TO PERFORMING SB 03-7 INSPECTION, 2 NEW GEARS WERE ORDERED FROM MFG IN EVENT WOULD NEED THEM DURING INSPECTION. AT 372.9 TACH TIME, THE RT MAGNETO GEAR BROKE A TOOTH DURING START AND WAS IDENTIFIED DURING PRE-TAKEOFF RUNUP. THE ENGINE WAS INSPECTED ANSDR CA071212006Blade · cracked(CAN) LONGITUDINAL CRACK AT BLADE TIP NR 1 BLADE. CRACK APPROX 1.5 INCH LONG AT APPROX .75 CHORD. FOUND DURING INSPECTION (ROUTINE). APPEARS TO BE CAUSED BY IMPACT DAMAGE FROM FOD. (TC NR 20071212006)SDR CA071212007Blade · cracked(CAN) LONGITUDINAL CRACK AT BLADE TIP, NR 1 BLADE. CRACK APPROX 0.75 INCH LONG AT .25 CHORD. FOUND DURING INSPECTION (ROUTINE). NO APPARENT CAUSE, NO IMPACT DAMAGE FROM FOD. (TC NR 20071212007)SDR CA071102004Tube · damaged(CAN) DURING A SPECIAL INSPECT TO THE MAIN AND NOSE WHEEL ASSEMBLIES, DEFECTS WERE NOTED IN THE TIRE-TUBES INSTALLED INTO BOTH MAIN AND THE NOSE WHEELS. REPORTS HAVE BEEN MADE OF TIRE-TUBES FAILING WITH VERY LOW TIME. AFTER RECEIVING THESE REPORTS AN INSPECTIOSDR CA071115008Bearing · seized(CAN) PILOT REPORTED MIXTURE STICKING DIFFICULT TO MOVE. INSPECTION REVEALED MIXTURE CONTROL ROD END AT MECHANICAL FUEL PUMP SEIZED. ROD END WAS REPLACED WITH NEW UNIT. THIS ROD END IS OF THE SAME PN WHICH SEIZED ON ANOTHER AIRCRAFT`S THROTTLE CONTROL WHICH RESDR FA20071025001Gear · brokenIN CRUISE, NOTICED DROP IN OIL PRESSURE BELOW YELLOW ARC NOT INDICATED DURING RUN UP & TAKEOFF. MADE PRECAUTIONARY RETURN TO HOME BASE & LANDED APPROX 7-8 MINUTES AFTER NOTICING DROP IN OIL PRESSURE. OIL PRESSURE INDICATED ZERO PSI DURING TAXI BACK TO HANGESDR CA071018001Engine · stalled(CAN) DURING POWER ON STALL THE PROPELLER CAME TO A FULL STOP, THROTTLE WAS AT 1700 RPM AND THE NOSE POINTED UP FOR A STALL CONFIGURATION AND ON POWER APPLICATION THE ENGINE CAME TO A FULL STOP. THE AIRCRAFT WAS THEN POINTED NOSE DOWN, THE PROPELLER STARTED WISDR CA070927005Gear · loose(CAN) FOLLOWING A 50HR OIL CHANGE, IT WAS NOTED THE AC WAS VERY DIFFICULT TO START TO CARRY OUT THE REQUIRED LEAK CHECK. TROUBLESHOOTING REVEALED A DEFECTIVE MAGNETO. WHEN THE MAG WAS REMOVED IT WAS NOTED THAT THE DRIVE GEAR P/N 36066 WAS LOOSE ON THE DRIVE GESDR CA070927006Gear · loose(CAN) THE AIRCRAFT WAS HARD TO START WITH NO APPARENT REASON. AFTER TROUBLESHOOTING, A HARD STARTING PROBLEM ON ONE OTHER A/C IN THE FLEET AND FINDING A LOOSE DRIVE GEAR ON THE LT MAG IT WAS DECIDED TO CHECK THIS A/C FOR A SIMILAR PROBLEM. THE LT MAG WAS REMOVSDR 2007FA0000825Pump · failedTHE MIXTURE CONTROL SHAFT ON THE ENGINE DRIVEN FUEL PUMP FROZE UP AT HALF TRAVEL BETWEEN FULL RICH AND IDLE CUT OFF. THIS CREATED A LEAN MIXTURE CONTROL WAS DISCONNECTED FROM THE FUEL PUMP, THEN THE FUEL PUMP CONTROL SHAFT HAD TO BE FREED UP. THE MIXTURE CABSDR CA070803015Transmitter · defective(CAN) PILOT REPORTED LOW OIL PRESSURE DURING DESCENT WITH ENGINE RPM REDUCED TO IDLE. COMPLEATED OIL PRESSURE GUAUGE CALIBRATION CHART USING CABIBRATED GAUGE. INDICATED 30PSI -> ACTUAL 38PSI, INDICATED 20 -> ACTUAL 27PSI, INDICATED 15PSI -> ACTUAL 20PSI, INDISDR CA070729001Fork · cracked(CAN) DURING ROUTING INSPECTION, A CRACK SIMILAR TO THE ONE IN THE ATTACHMENT WAS FOUND. FORK WAS REPLACED. FLEET INSPECTION REVEALED (3) OTHER AIRCRAFT WITH VARYING CRACK PROGRESSION ALL FORKS WERE REPLACED. (TC NR 20070729001)SDR CA070823006Bracket · broken(CAN) ALTERNATOR BRACKET IS BREAKING ON THESE AIRCRAFT AROUND 100 HOURS T/S. THE FACTORY HAS RUN OUT OF STOCK AND IS ROBBING THE PART FROM NEW PRODUCTION AIRCRAFT. SUGGEST RE ENGINEERING AND POSSIBLE AD. (TC NR 20070823006)SDR 2007FA0000490Crankshaft · crackedCRANKSHAFT HAD A VERY LARGE, DEEP FORGING LAP ON THE NR 3 CRANK CHEEK. AN EFFORT WAS MADE TO REMOVE THE LAP BY LOCALIZED GRINDING BUT THE IT WAS TOO DEEP TO REMOVE. CRANKSHAFT WAS DETERMINED UNAIRWORTHY BY ENGINEERING.SDR 2007FA0000276Bolt · brokenAC, RETURN FROM FLIGHT WITH BOTH BOLTS BROKEN; ATTACHING THE FORWARD HORIZONTAL STABILIZER MOUNT BRACKETS. ATT 1) GIVES FLIGHT INFO. ATT 2 AND 3) SHOW THE IPB BRAKE DOWN OF THE BOLTS AND LOCATION FROM MFG PARTS BOOK. ATT 4) PICTURES OF BOLTS AND AIRCRAFT. SDR CA070803010Transmitter · defective(CAN) OIL PRESSURE REPORTED LOW WHEN ENGINE BROUGHT BACK TO IDLE FOR LANDING. INSTALLED NEW OIL PRESSURE SENDER AND AIRFRAME GAUGE CALIBRATION CHECK COMPLETED. LOGBOOK NOT AT CURRENTLY CLOSE AT HAND, FOR TOTAL TIME ON OIL SENDER, OPERATOR HAS REPLACED THEM INSDR CA070322006Pump · out of adjust(CAN) PILOT REPORTED ENGINE STOPPED DURING POWER OFF STALL. RECORDS INDICATED (2) SID97-3C FUEL SET UP ADJUSTMENTS CARRIED OUT IN THE PREVIOUS FIVE DAYS OR 13.1 HRS PRIOR TO THE INCIDENT. SID CHECK REVEALED UNMETERED PRESSURE OUT OF LIMITS BY -1.1 PSI, LIMIT SDR CA061214002Seal · leaking(CAN) AIRCRAFT BROUGHT IN FOR 50 HR.MAINTENANCE CHECK FOUND FUEL ON BOTTOM OF COWL AND IT WAS TRACED BACK TO THE ENGINE DRIVEN FUEL PUMP. THE SEALS IN THE FUEL PUMP HAD STARTED TO FAIL OR HAD FAILED AROUND THE MIXTURE CONTROL LEVER ASSY. THE TOP COVER ALSO WASSDR CA070322003Bushing · missing(CAN) DURING INSPECTION IT WAS NOTED THAT THE TOP RUDDER ATTACHMENT PIN BUSHING WAS MISSING. FURTHER INSPECTION REVEALED THE BUSHING HAD FALLEN OUT AND WAS SITTING IN A VOID AREA BELOW THE ASSEMBLY. THE BUSHING WAS RE-INSTALLED IAW MFG INSTRUCTION. THE RUDDER SDR CA061115001Unknown · unknown(CAN) REPORTED DEFECT, ON APPLICATION OF FULL POWER, ENGINE WOULD ALMOST CUT-OUT, THEN CATCH AND ACHIEVE FULL POWER. THE AIRCRAFT HAD PREVIOUSLY BEEN SNAGGED FOR QUITING SHORTLY AFTER LANDING, ON OCT. 17TH, AT WHICH TIME THE FUEL SYSTEM HAD BEEN INSPECTED, ANDSDR CA070322002Gear · worn(CAN) THE FACT THAT IT IS POSSIBLE TO ACCIDENTALLY ENGAGE THE STARTER DRIVE WHILE THE ENGINE IS RUNNING AND THAT THE STARTER GEAR ENGAGES INTO THE ACCESSORY CASE OF THE ENGINE WHICH WOULD RESULT IN SIMILAR DAMAGE, IT WAS SUSPECTED AT THE TIME THAT THE DAMAGE FSDR CA061004001Pump · out of adjust(CAN) AIRCRAFT ENGINE FAILED IMMEDIATELY AFTER SPIN RECOVERY. INSTRUCTOR CONFIRMED FUEL PUMP ON AND MIXTURE FULL RICH. INSTRUCTOR ESTABLISHED BEST GLIDE ATTITUDE AND RESTARTED ENGINE IAW AFM (ENGAGING STARTER). UPON LANDING AND TAXI, INSTRUCTOR KEPT POWER ASDR CA060918006Gear · worn(CAN) DURING TROUBLESHOOTING OF THE FUEL SYSTEM DUE TO ENGINE QUITTING ON ROLL OUT FROM LANDING, THE ENGINE FUEL SYSTEM WAS BEING CHECKED IAW SID97-3C, AT WHICH TIME DURING A GROUND RUN IT WAS NOTICED THAT OIL PRESSURE HAD DROPPED TO ALMOST (0). THE ENGINE WASSDR CA060918007Pump · out of adjust(CAN) PILOT REPORTED ENGINE QUIT ON TOUCH DOWN, ABLE TO RESTART. FUEL INJECTION SYSTEM CHECKED IAW SID97-3C AND ADJUSTED. BOTH INLINE FUEL FILTERS INSPECTED FOR CONTAMINANTS, CLEANED AND RE-INSTALLED. SMALL AMOUNT OF CONTAMINANTS FOUND IN INLINE FILTER AFTER TSDR CA060918005Gear · worn(CAN) DURING THE FIRST 25/100 HR INSPECTION ON THIS AIRCRAFT, INSPECTION OF THE OIL SYSTEM REVEALED CONTAMINATION ON THE DRAIN PLUG MAGNET AND OIL FILTER. SUBSEQUENTLY, THE STARTER WAS REMOVED FOR CLUSTER AND DRIVE GEAR INSPECTION. THE STARTER AND CLUSTER GEARSDR CA060918003Hook · cracked(CAN) PILOT NOTICED CANOPY LIGHT ON IN FLIGHT AND RETURNED FOR LANDING. INSPECTION REVEALED THAT THE CANOPY LATCH PLATE ( P/N 22-5613-61-00) ON THE LT SIDE WAS BROKEN ALLOWING THE CANOPY LIGHT TO BE ILLUMINATED. 2 MICRO SWITCHES ARE USED TO TURN THE WANING LIGSDR 2006FA0000533Exhaust Riser · crackedON A 100HR INSP NR 2 EX RISER CRACKED AT FLANGE. THIS HAS BEEN FOUND ON A NUMBER OF AIRCRAFT OF THIS TYPE.SDR 2006FA0000534Exhaust Riser · crackedON A 100HR INSP #2 EX RISER CRACKED AT FLANGE. THIS HAS BEEN FOUND ON A NUMBER OF AIRCRAFT OF THIS TYPE.SDR 2006FA0000535Exhaust Riser · crackedON A 100HR INSP NR 2 EX RISER CRACKED AT FLANGE. THIS HAS BEEN FOUND ON A NUMBER OF AIRCRAFT OF THIS TYPE.SDR 2006FA0000536Exhaust Riser · crackedON A 100HR INSP NR 2 EXHAUST RISER CRACKED AT FLANGE. THIS HAS BEEN FOUND ON A NUMBER OF AIRCRAFT OF THIS TYPE.SDR CA060504004Engine · failedENGINE QUIT ON APPROACH, ONCE LANDED THE PILOT RESTARTED THE ENGINE AND TAXIED TO THE PARKING AREA. THE AIRCRAFT WAS INSPECTED AND IT SEEMS TO BE FUEL PRESSURE THAT WAS THE CAUSE OF THE ENGINE FAILURE. RIGGING AND MULTIPLE TESTS WERE CONDUCTED AND THE PROBLESDR CA060414001Hub · cracked4 INCHES LONGITUDINAL CRACK FROM TIP TO HUB ON NR 2 BLADE. PROPELLER REMOVED FROM SERVICE. CRACK SIMILAR TO CRACK ON A/C C-GGMV,SDR CA060414002Blade · cracked4 INCHES CRACK FROM TIP TO HUB ON NR 2 BLADE, SIMILAR TO THAT REPORTED WITH SDR #20060221008. PROPELLER REMOVED FROM SERVICE.SDR CA060221010Bracket · crackedDURING ROUTINE INSPECTION, A SMALL CRACK WAS DISCOVERED ON THE ALTERNATOR BRACKET. FURTHER INSPECTION REVEALED THAT THE TOP NUT TCM P/N 2443 WHICH IS USED TO MOUNT THE BRACKET TO THE ENGINE WAS STRIPPED. THE NUT ATTACHES TO ONE OF THE ENGINE THRU STUDS AT THSDR CA060221008Blade · crackedDURING PRE-FLIGHT INSPECTION, THE PILOT INSTRUCTOR DISCOVERED A POSSIBLE CRACK ON THE PROPELLER. CLOSER INSPECTION REVEALED AN APPROXIMATELY 4" CRACK ON NR 2 BLADE OF PROPELLER. THE CRACK IS DEVELOPED LONGITUDINAL ON BLADE FROM TIP TO HUB. NO IMPACT MARK ORSDR CA060314002Circuit Board · burnedTHREE GARMIN AUDIO PANELS GMA 340 HAD TO BE SENT BACK TO GARMIN FOR REPAIRS DUE TO A SHORT CIRCUIT OCCURRING WHEN PLUGGING IN HEADSETS WITH THE MASTER SWITCH ON. FIRST WAS ON JANUARY 17, 2006, LAST TWO OCCURRED ON SAME DAY FEB 2, 2006. OPERATING AIRCRAFT FORSDR CA060123005Inertia Reel · broken(CAN) PILOT REPORTED THAT THE REEL MECHANISM IN THE LT SHOULDER HARNESS ASSEMBLY ON THE RT SEAT WAS DEFECTIVE AND WAS NOT ALLOWING THE BELT TO RETRACT. AFTER REMOVAL, THE BELT WAS FINALLY RETRACTED AFTER SHAKING THE LOOSE NYLON PIECES THAT HAD BROKEN, INSIDE SDR CA051215002Seal · loosePILOT REPORTED FLAPS WOULD NOT RETRACT. INSPECTION FOUND SEAL MIGRATED INTO FLAP SWITCHES. RE-GLUED PER DIAMOND INSTRUCTIONS. THIS UNIT HAD BEEN RE-GLUED TWICE BEFORE. DIAMOND IS LOOKING INTO A MECHANICAL SEAL RETENTION SOLUTION, AND HAS OFFERED TO CONTINUSDR 2005FA0001542Roll Pin · backed outROLL PIN LOCKING THE NOSE STRUT ELECTROMETRIC SPRING PLATE (PN 20-3220-05-02) TO THE SHOCK ABSORBER ROD (PN 20-3220-05-01) HAD WORKED OUT UNLOCKING THE ASSY.SDR CA051024004Grommet · worn(CAN) AC WAS SNAGGED WITH GEN LIGHT NOT ILLUMINATING WITH BATTERY AND GENERATOR SWITCHES ON. DURING TROUBLESHOOTING IT WAS FOUND THAT WHERE ALTERNATOR CONTROL AND BATTERY WIRES PASS THROUGH GROMMET OF ENGINE BAFFLE, WIRES HAD CHAFFED THROUGH PLASTIC INSULATORSDR 2005FA0001299Rotor Shaft · shearedUNSCHEDULED FAILURE OF THE LT ENGINE MAGNETO DURING ENGINE START. FOUND MAGNETO ROTOR SHAFT SHEARED AT POINTS CAM DRIVE END.SDR CA050915001Injection System · out of adjustAIRCRAFT ENGINE QUIT DURING LANDING AND HAD RESTART DIFFICULT. A/C WAS FINALLY STARTED AND TAXIED BACK TO A MX HANGAR. IT WAS NOTED THAT ENGINE RAN EXTREMELY ROUGH AT IDLE. A SET OF CALIBRATED FUEL SET UP GAUGES WERE ATTACHED AND A FUEL SYSTEM CHECK CARRIED
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