Continental IO-470-L
Service difficulty reports · 144
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 = 'IO470L' 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 = 'IO470L' 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 2022FA0000244Filter Adapter · failedOIL FILTER ADAPTER IS AN F&M ENTERPRISES ADAPTER INSTALLED UNDER AN STC. IT IS AFFECTED BY A STRATUS MANDATORY SERVICE BULLETIN NO. SB-001, REV B AND AN AIRWORTHINESS DIRECTIVE AD22-04-04. A FIBER GASKET WAS INSTALLED BETWEEN THE ADAPTER NUT AND OIL PUMP BODY.SDR CA190731022Door · malfunctioned(CAN) DURING TAKEOFF CABIN ENTRANCE DOOR OPENED AND PILOT RETURNED TO AIRPORT. THE PILOT PROPERLY CLOSED THE DOOR AND ENSURED IT WAS LATCHED. HE THEN RETURNED TO THE RUNWAY TO CONTINUE THE INTENDED FLIGHT. (TC# 20190731022)SDR CA190731020Fuel Control · malfunctioned(CAN) RH ENGINE WAS SURGING ON TAKE OFF. PILOT ABORTED TAKE OFF AND MAINTENANCE TROUBLESHOT THE PROBLEM AND FOUND THAT THE MIXTURE SETTING ON THE RH ENGINE WAS EXCESSIVELY RICH. MAINTENANCE SET THE MIXTURE AS PER MAINTENANCE MANUAL AND AIRCRAFT WAS GROUND RUN SDR 2019FA0000043Connecting Rod · brokenPILOT FELT A SHUDDER OF THE LEFT ENGINE AND IT SHUT DOWN ON ITS OWN. THE AIRCRAFT LANDED WITHOUT INCIDENT. UPON INSPECTION WE FOUND THAT THE PROP DID NOT FEATHER, THE ENGINE SEIZED, THERE ARE THREE HOLES IN THE TOP ON THE LEFT ENGINE CASE HALF, OBSERVED THROUGSDR 2016FA0000234Axle · failedAXLE FAILURE ON LANDING RESULTING IN GROUND LOOP, PROP STRIKE, AND SUBSTANTIAL DAMAGE TO EMPENNAGE AND LT WING. THE ACFT JUST MODIFIED TO 29 X 11 X 10 AIR HAWKS FROM BUSHWHEELS AND 10" WHEELS. THE AXLE WAS THE STOCK ALUMINUM.SDR CA150831011Drive Coupling · worn(CAN) LEFT ENGINE LOST POWER IN FLIGHT, APPROXIMATELY 25 MINUTES AFTER DEPARTING, WHILE IN CRUISE AT 8000`, THE LT ENGINE QUIT. FUEL PUMP REMOVED AND FOUND THE COUPLING SHAFT PN: 631683 ROUNDED INTERNALLY AND DRIVE GEAR, PN: 631684 WORN. DRIVE GEAR AND COUPLINSDR CA150831012Gear · worn(CAN) LEFT ENGINE LOST POWER IN FLIGHT. APPROXIMATELY 25 MINUTES AFTER DEPARTING, WHILE IN CRUISE AT 8000 FT, THE LT ENGINE QUIT. FUEL PUMP REMOVED AND FOUND THE COUPLING SHAFT, PN: 631683 ROUNDED INTERNALLY AND DRIVE GEAR, PN: 631684 WORN. DRIVE GEAR AND CSDR CA141231002Relay · failed(CAN) WHILE GEAR OPERATION SWITCH WAS IN THE UP POSITION, GEAR LOWERED VIA THE MOTOR ON ITS OWN. PIC NOTED THAT SWITCH WAS UP AND LOCKED AND NO BREAKERS HAS "POPPED", HOWEVER BOTH PIC AND PASSENGER ALSO NOTICED THAT THE 3 GREEN WERE INDICATING. UPON TROUBLESHSDR CA150113033Diaphragm · failed(CAN) FOUND ACCUMULATOR DIAPHRAGM FAILED, OIL ON PRESSURE SIDE.SDR CA141209004Elt · inoperative(CAN) WHILE TESTING THE ELT ON ITS ANNUAL CERTIFICATION AS PER CAR 571 APPENDIX G FOUND NO OUTPUT POWER OR MODULATION FOR THE 121.5 MHZ FREQUENCY. THE UNIT RETURNED FOR REPAIR.SDR CA141203006Indicator · leaking(CAN) DURING FLIGHT, PILOT NOTICED THE FACE OF THE FUEL PRESSURE INDICATOR HAD FLUID POOLING IN THE BOTTOM OF IT. IT WAS REPORTED TO MAINTENANCE AND THE INDICATOR WAS REPLACED.SDR 2013FA0000503Cylinder · failedENGINE RAN INTERMITTENTLY ROUGH . NR 1 CYLINDER SHOWED VERY LOW EGT AND CHT. PERFORMED COMPRESSION TEST ON NR 1 CYLINDER. COMPRESSION WAS LOW AND AIR WAS ESCAPING PAST EXHAUST VALVE INTO EXHAUST STACK. R & R CYLINDER WITH REPAIRED AND INSPECTED UNIT. REPOSDR CA130807012Line · cracked(CAN) DURING A DAILY INSPECTION ON THE RT ENGINE, THE FUEL INJECTOR LINE AT THE NR 3 CYLINDER FUEL INJECTOR WAS FOUND FUEL/SOOT STAINED. A QUICK LEAK CHECK WITH THE FUEL BOOST PUMP RUNNING REVEALED A LEAK NEAR THE FITTING ATTACHING THE LINE TO THE FUEL INJECTSDR CA120809014Control Cable · crossed(CAN) IN CRUISE, PILOT ATTEMPTED TO CENTER THE BALL IN THE TURN AND BANK INDICATOR BY APPLYING RUDDER TRIM. WHEN APPLIED, AFFECT WAS OPPOSITE TO NORMAL, TURNED TRIM WHEEL LT AND RT RUDDER TRIM WAS NOTED. PILOT LANDED AND ADVISED MAINTENANCE. MAINTENANCE DISCSDR CA120430011Piston · failed(CAN) WHILE ON FINAL, THE ACFT STARTED TO VIBRATE, UPON SELECTION OF "GEAR DOWN" AT LOW POWER SETTINGS, 15" MANIFOLD, 2300 RPM. THE GEAR WAS CYCLED ONCE AND THE VIBRATION WORSENED. THE RPM ON THE RT ENGINE DROPED FROM 2300 TO 1500 RPM. ADJUSTING THE RT PROPSDR CA110503006Aileron · misinstalled(CAN) RT AILERON OUTBOARD ATTACH DISCONNECTED IN FLIGHT DUE TO IMPROPER INSTALLATION. ON INSPECTION PICK UP POINTS FOR AILERON ATTACH HAD BEEN MISSED INTERNALLY DUE TO DIFFICULTY IN VISUAL ALIGNMENT IN BETWEEN SKINS WHERE ATTACH HARDWARE PURCHASE AILERON ATTACSDR 2010FA0001103Control Cable · detachedDURING FLIGHT, THE RT ENGINE MIXTURE CONTROL FAILED AND THE ENGINE QUIT. AFTER LANDING, FOUND THE SWAGGED END OF THE MIXTURE CONTROL CABLE (PN 50-389010-21) HAD SEPARATED AT THE FUEL CONTROL UNIT.SDR 2010FA0000249Lifter · spalledENGINE CYLINDERS HAD LOW COMPRESSION. REMOVED CYLINDERS AND FUND LIFTERS HAD SPALLING AND CAM SHAFT WAS WORN. LIFTER PN 653888 AND PN 653877 INSTALLED. THESE PN ARE DESIGNATED AS NOT AFFECTED BY MSB 09-8 OR AD 2009-24-52.SDR 2010FA0000060Hub · mismanufacturedPROPELLER FACTORY NEW IN 12/10/99. PROPELLER HUB FOUND AT O/H TO BE UNAIRWORTHY DUE TO CYLINDER HOLES DEPTH DRILLED BY FACTORY TOO DEEP. 3 SMALL DIMPLES NOTED ON UNDERSIDE OF HUB ON INSPECTION. MFG HAS REJECTED HUB. FACTORY HAD TO HAVE IMPROPERLY DRILLED HUSDR CA091019001Wire · broken(CAN) TAIL BRACE WIRE FOUND BROKEN AS A RESULT OF A CRACK ORIGINATING IN CORROSION PITTING.SDR 2008FA0000847Spring · brokenSTARTER ADAPTER P/N 635050-A4, STARTER SPRING FAILED. STARTER ADAPTER OVERHAULED, RETURNED TO SERVICE AFTER OVERHAUL. PART SOLD, STARTER ADAPTER INSPECTED AND RETAGGED AND SOLD TO MFG. MAINT INSTALLED STARTER ADAPTER AND SPRING FAILED 14 HOURS LATER.SDR CA071002005Piston · damaged(CAN) DURING CRUISE FLT, RT ENGINE BEGAN TO LOOSE OIL PRESSURE. OIL TEMP & CHT INCREASED. PILOT ELECTED TO SHUTDOWN ENGINE AS A VIBRATION BECAME APPARENT & OIL PRESSURE DECREASED TO NEAR ZERO. AN EMERGENCY DECLARED & AIRCRAFT LANDED WITHOUT FURTHER INCIDENT. USDR CA071212002Spar · cracked(CAN) DURING ANNUAL INSPECTION, VISUAL INSPECTION OF AREA REVEALED A SUSPECTED CRACK. NOT OF DYE PENETRANT AND EDDY CURRENT CONFIRMED. MFG SERVICE KIT TO INSTALLED. PART LAST NDT INSPECTED 22.1 HRS PREVIOUS AND NO INDICATIONS. (TC NR 20071212002)SDR CA070801001Fuel Cell · deteriorated(CAN) THE RT WING LEADING EDGE FUEL CELL WAS REMOVED BECAUSE OF A FUEL LEAK. A REPLACEMENT FUEL CELL WAS ORDERED. PRIOR TO INSTALLATION OF THE NEW (OVERHAULED) CELL, IT WAS INSPECTED AND FOUND TO CONTAIN A LARGE QUANTITY OF SAWDUST-LIKE PARTICLES. ON FURTHER ISDR CA060624001Bolt · loose(CAN) AILERON TRIM BOLT FOUND MIGRATING OUT OF LINKAGE ARM ON LT AILERON TRIM TAB ASSEMBLY. BOLT WAS NOTED TO BE FINGER-TIGHT ONLY AND NOT SET INTO LOCKING DEVICE. NOTE: BOLT WAS FOUND IN THIS CONDITION AFTER FLIGHT CONTROLS WERE INSTALLED AFTER AIRCRAFT WAS PSDR 2006FA0000327Impulse Coupling · rustedDURING A ROUTINE INSP, ALL MAGNETOS WERE REMOVED FOR POINTS AND CONDENSER REPLACEMENT. RUST WAS FOUND ON THE FLYWEIGHT/AXLE AREA OF THE IMPULSE COUPLING. A WEAR CHECK WAS MADE AND IT WAS DETERMINED THAT ALL COUPLINGS FAILED IAW MSB. NOTE: THE FLYWEIGHT/ AXSDR 2005FA0001613Control Cable · corrodedAILERON CABLE RUNNING FROM LT WHEEL WELL AREA LOWER REAR SPAR THRU CABIN UNDER FLOOR TO PEDESTAL AND CONTROL SPROCKET WAS FOUND SEVERELY RUSTED AND ABOUT HALF THE WIRE STRANDS HAD FAILED IN THE AREA WHERE THE CABLE MET THE SWAGED TERMINAL END. AREA IS VERY HARSDR 2005FA0001598Control Cable · failedAILERON CABLE RUNNING FROM LT WHEEL WELL AREA LOWER REAR SPAR THRU CABIN UNDERFLOOR TO PEDESTAL AND CONTROL SPROCKET WAS FOUND SEVERELY RUSTED AND ABOUT HALF THE WIRE STRANDS HAD FAILED IN THE AREA WHERE THE CABLE MET THE SWAGED TERMINAL END. AREA IS VERY HARDSDR 2005FA0001595Control Cable · damagedAILERON CABLE RUNNING FROM LT WHEEL WELL AREA LOWER REAR SPAR THRU CABIN UNDER FLOOR TO PEDESTAL AND CONTROL SPROCKET WAS FOUND SEVERELY RUSTED AND ABOUT HALF THE WIRE STRANDS HAD FAILED IN THE AREA WHERE THE CABLE MET THE SWAGED TERMINAL END. AREA IS VERY HASDR 2005FA0001596Control Cable · failedAILERON CABLE RUNNING FROM LT WHEEL WELL AREA LOWER REAR SPAR THRU CABIN UNDER FLOOR TO PEDESTAL AND CONTROL SPROCKET WAS FOUND SEVERELY RUSTED AND ABOUT HALF THE WIRE STRANDS HAD FAILED IN THE AREA WHERE THE CABLE MET THE SWAGED TERMINAL END. AREA IS VERY HARSDR 2005FA0001614Control Cable · corrodedAILERON CABLE RUNNING FROM LT WHEEL WELL AREA LOWER REAR SPAR THRU CABIN UNDER FLOOR TO PEDESTAL AND CONTROL SPROCKET WAS FOUND SEVERELY RUSTED AND ABOUT HALF THE WIRE STRANDS HAD FAILED IN THE AREA WHERE THE CABLE MET THE SWAGED TERMINAL END. AREA IS VERY HARSDR 2005FA0001615Control Cable · corrodedAILERON CABLE RUNNING FROM LT WHEEL WELL AREA LOWER REAR SPAR THRU CABIN UNDER FLOOR TO PEDESTAL AND CONTROL SPROCKET WAS FOUND SEVERELY RUSTED AND ABOUT HALF THE WIRE STRANDS HAD FAILED IN THE AREA WHERE THE CABLE MET THE SWAGED TERMINAL END. AREA IS VERY HARSDR 2005FA0001364Spar Cap · corrodedDURING AN ANNUAL INSPECTION, SOME CORROSION WAS FOUND IN THE AREA OF THE RT WING TIE DOWN ASSY, UPON FURTHER INVESTIGATION AN AREA OF APPROXIMATELY 8 INCHES IN LENGTH WITH SEVERE INTERGRANULAR CORROSION WAS DISCOVERED ON THE LOWER SPAR CAP POSSIBLY CAUSED BY DSDR CA050617007Doubler · cracked(CAN) DURING ROUTINE LPI INSPECTION OF THE FRONT WING SPAR CARRY THRU STRUCTURE AND REPAIR DOUBLERS IN ACCORDANCE WITH AD90-08-14, THE LT FWD REPAIR DOUBLER WAS FOUNDCRACKED IN THE LOWER BEND RADIUS IN THE SAME SPOT AS THE ACTUAL WING SPAR WHICH THE DOUBLER WASDR CA050512009Coupling · wornAIRCRAFT IN CRUISE, ENGINE SPUTTERED AND DIED. BOOST PUMP ACTIVATED AND ENGINE RESTARTED. PART IS AN ON-CONDITION ITEM. THE SQUARE DRIVE ROUNDED OFF UNTIL IT WOULD NO LONGER ENGAGE THE DRIVE GEAR P/N 631684. THIS CAUSED THE FUEL PUMP TO STOP ROTATING RESULSDR CA041215003Relay · malfunctioned(CAN) DURING A MISSED APPROACH PILOT INITIATED A TURN TO RETURN FOR A 2ND APPROACH WHEN MLG EXTENDED UNCOMMANDED WITH NO DOWN OR UP INDICATION LIGHTS. PILOT SLOWED ACRFT & CONTINUED TO DESTINATION WITH MLG SELECTED DOWN & CONFIRMED MLG DOWN WITH EMERGENCY GEARSDR CA041026012Shaft · brokenPILOTS LT RUDDER PEDAL BROKE AT THE UPPER PEDAL SHAFT. THE PEDAL WAS FOUND BROKEN AFTER COMPLETION OF A FLIGHT. RUDDER PEDAL WAS REPLACED. INSPECTION OF THE PEDAL REVEALED WORN SHAFT ATTACHMENT HOLES.SDR D942004F00000Rocker · brokenON TAKEOFF ROLL PILOT LOST POWER TO THE LT ENGINE. INVESTIGATION REVEALED THAT THE NR 5 CYLINDER EXHAUST VALVE ROCKER ARM WAS BROKEN. ADDITIONAL INSPECTION REVEALED DAMAGE TO THE NR 5 PUSH ROD AND HOUSING, AND THE HYDRAULIC LIFTER ASSY. ENGINE WAS MANUFACTUSDR 2004FA0000753Vibrator · burnedJUST AFTER DEPARTURE A BURNING ODOR WAS NOTICED FROM THE FRONT OF THE AIRCRAFT. A STANDARD FLIGHT PATTERN BACK TO RUNWAY WAS EXPEDITED. LATER FINDING THE IGN VIBRATOR HAD STARTED A FIRE IN THE FRONT PILOTS LOWER FIREWALL PANEL. A GEAR UP LANDING BECAME THE SDR 2004FA0000768Vibrator · burnedPILOT DEPARTED ON MAINT TEST FLIGHT ON CROSS WIND. PILOT NOTICED BURNING ODOR AS PILOT TURNED BASE LEG TO LAND ON DEPARTURE RUNWAY, AC HAS SMOKE IN COCKPIT. AC WAS LANDED GEAR UP. AFTER AREA OF PILOT SIDE RUDDER PEDALS WAS NOTICED AND PUT OUT. ON FURTHER ISDR AKV2004F00000Cylinder · crackedAIRCRAFT WAS AT A CRUISING ALTITUDE OF 6000 FT MSL WHEN PILOT HEARD A LOUD BANG AND FELT SEVERE VIBRATION. PILOT STATED THAT WHEN HE LOOKED OUT AT THE LEFT ENGINE HE SAW SMOKE AND OIL COMING FROM THE COWLING; AT WHICH TIME HE ELECTED TO SHUT THAT ENGINE DOWN.SDR CA040304007Control Cable · broken(CAN) DURING CRUISE FLIGHT THE PILOT NOTICED THAT THE RT MIXTURE WAS NOT RESPONDING TO CONTROL MOVEMENT. THE AIRCRAFT RETURNED TO BASE UNEVENTFULLY AND UPON MAINTENANCE INSPECTION FOUND THE ENGINE SIDE OF THE CABLE HAD BROKEN AT THE ROD END WHERE THE CABLE SHESDR CA031021008Cam Follower · spalled(CAN) WHILE INVESTIGATING PROBLEM OF LEAKING EXHAUST VALVE CYLINDER NR 6. A CHECK OF THE VISABLE CAMSHAFT INDICATED SEVERE SPALLING ON CAM FOLLOWER FOR NR 5 CYLINDER. CHECK OF OIL SCREEN SHOWED NO METAL. CHECK OF OIL SCREEN WELL REVEALED METAL. AIRCRAFT HASDR IPM2003F00000Relief Valve · failedENGINE WOULD LOOSE POWER INTERMITTENTLY AND DURING CLIMB AFTER TAKEOFF. DETERMINED TO BE DEFECTIVE RELIEF VALVE AND SEAT IN ENGINE FUEL PUMP. (WP11200400873)SDR CA030818004Pitch Stop · stripped(CAN) DURING INSPECTION OF THE PROP, MAINTENANCE ATTEMPTED TO REMOVE THE SPINNER BUT COULDN'T BECAUSE THE LOW PITCH STOP THREADS WERE STRIPPED, WHERE THE SPINNER ATTACHES TO THE LOW PITCH STOP. THE LOW PITCH STOP HAD TO BE REMOVED FROM THE P ROPELLER SO THE SPSDR CA030818001Piston · broken(CAN) UPON DOING A CYLINDER INSPECTION IT WAS NOTICED THAT THE COMPRESSION ON THE NR 4 CYLINDER WAS LOW. REMOVAL OF THE CYLINDER REVEALED A PISTON SKIRT LAYING IN OIL SUMP WHICH HAD COME FROM THE NR 5 CYLINDER. THESE PISTON SKIRTS BREAKING OFF HAVE CREATED 2 ISDR CA030530006Nut · cracked(CAN) CUSTOMER COMPLAINED OF SPINNER CRACKING. OVER HAULED BOTH PROPS AS A PRECAUTIONERY. CHECKED PROP BEFORE DISASSEMBLY. TRACK, ANGLES, BALANCE WITHIN SPEC. FOUND HUB CRACKED IN THREADS. MATE TO PROBLEM PROPELLER. 1 CRACKED BLADE NUT.SDR AUS20030532Solenoid · faulty(AUS) HEATER LEAKING FUEL FROM CASE DRAIN. INVESTIGATION FOUND THAT THE SOLENOID HAD NOT CLOSED AFTER THE HEATER WAS LAST USED.SDR CA030517001Fuel Cell · contaminated(CAN) DURING CREW WALK AROUND & ACTUATION WATER DRAINS, CREWS CONSISTENTLY FIND WATER EVEN IF COMPLETELY DRAINED ON PREVIOUS FLIGHT. AIRCRAFT INSPECTED AND ALL FUELCAPS COMPLETELY RESEALED AND SEAL SEATS CLEANED. ALL FUEL BLADDERS INTERNALLY I NSPECTED AND FOUSDR CA030604009Rudder Pedal · worn(CAN) AFTER FINDING A BROKEN RUDDER PEDAL, AN INSPECTION WAS CARRIED OUT ON THE OTHER A/C. ON ONE OF THE AIRCRAFT, THE ATTACHMENT POINT FOR THE RUDDER PEDAL WAS FOUND EXCESSIVELY WORN IN THE SAME LOCATION AS THE BROKEN PEDAL FOUND ON THE OTHER AIRCRAFT. INSP
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