Allison 250-C20
Service difficulty reports · 945
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 = '250C20' 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 = '250C20' 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 CA060803002Filter · wrong part(CAN) WHILE CARRYING OUT A SCAVENGE OIL FILTER REPLACEMENT IAW INSPECTION PROGRAM IT WAS NOTED THAT THE FILTER WAS DIFFERENT THAN THE REPLACEMENT FILTER. THE CORRECT FILTER FOR THE SCAVENGE OIL FILTER IS P/N 038088-08, WHAT WAS FOUND IN THE SCAVENGE OIL FILTERSDR CA050808002Pump · failed(CAN) AIRCRAFT WAS HAVING PROBLEM WITH INITIAL START. FUEL CHECK VALVE AND FCU HAD BEEN CHANGED FOR TROUBLESHOOTING. REPLACED ENGINE DRIVEN FUEL PUMP, AIRCRAFT RETURNED TO SERVICE.SDR 2005FA0001339Hub · damagedFOUND THE UPPER M/R P/C LINK BEARING HAD WORN INTO THE ATTACH HUB OF THE PITCH HOUSING ABOUT .130 INCH UNTIL THE SPHERICAL PART OF THE BEARING CONTACTED, PREVENTING FURTHER PROGRESSION. (K)SDR CA050810003Combustion Liner · cracked(CAN) THE PILOT WAS EXPERIENCING HIGH TOT (WITHIN FLIGHT MANUAL LIMITATION) AND REPORTED THAT THE AIRCRAFT WAS FAILING THE POWER CHECK. THE ENGINEER VISUALLY INSPECTED THE ENGINE FOR DISCREPENCIES AND FOUND A 2 INCH CRACK IN THE ARM PIT OF THE OUTER COMBUSTIONSDR CA050826007Fuel Control · malfunctioned(CAN) DURING A GROUND RUN UP, AIRCRAFT STARTED HOT AND FUEL WAS LEAKING FROM A HOLE WITH IN THE FCU BODY. THE FCU WAS REMOVED AND AIRCRAFT STARTED NORMALLY AND NO FURTHER ISSUES APPEARED.SDR CA050713003Yoke · cracked(CAN) CRACK FOUND DURING OVERHAUL 1 INCH LONG CRACK INDICATION LOCATED ON THE BOTTOM SECTION OF THE FILLET RADIUS.SDR CA050718009Intercostal · crackedDURING INSPECTION, INTERCOSTAL FOUND CRACKED ON BOTH LEGS. TAILBOOM REMOVED. AFT BULKHEAD FRAME FOUND CRACKED ABOVE BOLT HOLE. DAMAGE AT UPPER LEFT FITTING OF TAILBOOM ATTACH BOLTS.SDR CA050630006Relay · failedRELAY NOT ACTIVATING. REPLACED RELAY.SDR CA050623001Skin · cracked(CAN) APPROXIMATELY 2, PLATE CRACKEDSDR CA050610006Drive Shaft · sheared(CAN) ON LANDING GENERATOR FAIL LIGHT ILLUMINATED. AC SHUTDOWN, STARTER CHECKED AND SHAFT WAS FOUND TO BE SHEARED. STARTER REMOVED AND REPLACED WITH SERVICABLE.SDR CA050627004Bleed Valve · failedTOT INDICATOR CHECKED FOR CALIBRATION WITH BARFIELD TESTER, NO DEFECT NOTED. ON GROUND RUN OF AIRCRAFT, FOUND THE BLEED VALVE WAS NOT MOVING AS THE ENGINE WAS ACCELERATED. BLEED VALVE REPLACED WITH SERVICEABLE UNIT, ENGINE POWER CHECK C/O AND PASSED. AIRCRASDR CA050616009Starter Gen · failed(CAN) NOISE IN HEADSET REPORTED BY PILOT, THAT WAS GETTING WORSE. PILOT TURNED OFF GENERATOR AND NOISE WAS ELIMINATED. STARTER THEN FAILED TO ROTATE WHEN STARTER ATTEMPTED. START/GEN REPLACED AND A/C RETURNED TO SERVICE.SDR YTRR100737Governor · intermittentWHEN A LOAD IS APPLIED TO THE ENGINE THE GOVERNOR DROOPS AND WILL NOT RECOVER.SDR CA050609019Hanger Assy · damaged(CAN) UNUSUAL NOISE HEARD ON SHUTDOWN. NR 1 T/R DRIVESHAFT HANGER SUPPORT 206-030-433-007 FOUND TO HAVE ELONGATED HOLES FOR HANGER ASSY ATTACH SCREWS 206-040-323-003. THESE SCREWS WERE WORN .333 THROUGH. NEW HANGER MOUNT, HANGER ASSY, BEARING COLLAR, DRIVESHSDR RT62005F00000Support Fitting · crackedREAR CROSSTUBE BOX-BEAM ASSEMBLY: LEFT FORWARD SUPPORT FITTING- 1 INCH VERTICAL CRACK, RT FORWARD SUPPORT FITTING - 1 INCH CRACK IN RADIUS. CRACKS FOUND DURING SCHEDULED INSPECTION. (K) (1 OF 4)SDR RT62005F00001Support Fitting · crackedREAR CROSSTUBE BOX-BEAM ASSEMBLY: LT FORWARD SUPPORT FITTING - 1 INCH VERTICAL CRACK. RT FORWARD SUPPORT FITTING - 1 INCH CRACK IN RADIUS. CRACKS FOUND DURING SCHEDULED INSPECTIONS. (NR2 OF 4) (K)SDR RT62005F00002Support Fitting · crackedREAR CROSSTUBE BOX-BEAM ASSEMBLY: LT FORWARD SUPPORT FITTING - 1 INCH VERTICAL CRACK. RT FORWARD SUPPORT FITTING - 1 INCH CRACK IN RADIUS. CRACKS FOUND DURING SCHEDULED INSPECTION. (NR3 OF 4) (K)SDR RT62005F00003Support Fitting · crackedREAR CROSSTUBE BOX-BEAM ASSEMBLY: LT FORWARD SUPPORT FITTING - 1 INCH VERTICAL CRACK. RT FORWARD SUPPORT FITTING - 1 INCH CRACK IN RADIUS. CRACKS FOUND DURING SCHEDULED INSPECTION. (NR4 OF 4) (K)SDR CA050411004Compressor · failed(CAN) CREW WAS PREPARING TO LIFT OFF AND HEARD A LOUD BANG AND FELT A TWITCH. MAINTENANCE REMOVED THE COMPRESSOR AND REPLACED IT WITH A SERVICABLE UNIT. AIRCRAFT TEST FLOWN AND RETURN TO SERVICE. AT MAINTENANCE FACILITY THE CASE WAS SPLIT AND THE SIXTH STAGSDR CA050525001Seal · leaking(CAN) OIL LEAK REAR SEAL. OIL LEAK REPAIRED, RETURN TO SERVICE..SDR CA050314004Turbine · stiff(CAN) AFTER A SCHEDULED INSP, WERE GOING TO DO A COMPRESSOR WASH, SINCE THE BLEED VALVE AREA WAS DIRTY. WHEN THE COMPRESSOR WAS NOTED AS BEING STIFF TO TURN, FURTHER INVESTIGATION WAS NEEDED. AFTER REMOVAL OF THE TURBINE ASSY, THE COMPRESSOR AND GEARBOX MOVESDR SD72005F00000Fuel Control · failedPILOT REPORTED DECAY OF N2 RPM WHEN ATTEMPTING TO REAPPLY COLLECTIVE FOLLOWING GRADUAL DECENT IN LOW ALTITUDE CRUISE FLIGHT. PRECAUTIONARY LANDING ACCOMPLISHED. SUBSEQUENT GROUND RUNS SHOWED MAXIMUM ACHIEVABLE N2 RPM OF 80 PERCENT. TEMPORARY REPLACEMENT WITSDR YTRR099528Fuel Control · malfunctionedUNABLE TO ADJUST START PROPERTIES OF FUEL CONTROL AFTER 443.8 TSOSDR CA050503007Battery · failed(CAN) BATTERY SPECIFIC GRAVITY CHECK AFTER CHARGING AND AFTER REMOVAL FROM AIRCRAFT NOT SERVICEABLE. BATTERY ONLY HAS 9.6 HOURS WILL NOT START AIRCRAFT.SDR 2005FA0000122Engine · making metalPILOT REPORTED HEARING A GRINDING NOISE FROM THE ENGINE WHICH WAS FOLLOWED BY AN ENGINE CHIP LIGHT INDICATION. A POWER ON PRECAUTIONARY LANDING WAS MADE. THE ENGINE WAS REMOVED AND REPLACD WITH A LOANER ENGINE. THE DISCREPANT ENGINE AS AN ASSEMBLY WAS SENT SDR CA050130002Bearing · seized(CAN) UPON INSPECTION OF THE LONG TAIL ROTOR PITCH CHANGE TUBE THE WALKING BEAM WAS OBSERVED TO BE A LITTLE RATCHETY TO ROTATE EVEN THOUGH IT ONLY ROTATES ABOUT 30 DEGREES OF TRAVEL. UPON THIS INSPECTION THE PART WAS REMOVED AND FURTHER INSPECTED. THE BEARINSDR YTRR099159Fuel Control · inoperativeFUEL CONTROL UNIT WOULD NOT MAINTAIN IDLE OF THE AIRCRAFT. THE UNIT HAD BEEN PREVIOUSLY REPAIRED 91.3 HRS AGO FOR THE SAME EXACT PROBLEM.SDR 2005FA0000277Tube · wornTHE PILOT WAS FLYING AT APPROX. 600 FEET INDICATED, WHEN HE EXPERIENCED A VIOLENT YAW TO THE RIGHT AND A HIGH PITCH ENG. SOUND. AN EMERGENCY LANDING WAS MADE WITH PARTIAL POWER UNTIL THE LAST 50 FT. AND THEN THE PILOT HAD TO ENTER AUTOROTATION WITH NO POWER DUSDR S6G2005F00000Pin · crackedAFTER DISASSEMBLY OF T/R HUB ASSY, REQUIRED DUE TO SCHEDULED 600 HOUR INSPECTION AND RETENTION STRAP REPLACEMENT (CLOSE TO RETIREMENT LIFE), FOUND STRAP PIN (PN 109-8131-08-1, TSN 4070) AND RETENTION STRAP (PN 109-8131-07-1 TSN 1735). ALSO, REPLACED STRAP PISDR CA050107004Housing · leaking(CAN) DURING A TEST FLIGHT FOLLOWING AN OPS NR4 INSPECTION, THE TRANSMISSION OIL PRESSURE LIGHT ILLUMINATED AND THE OIL PRESSURE DROPPED SLIGHTLY BELOW THE RED LINE. AN IMMEDIATE DECENT WAS CONDUCTED AND UPON LANDING A MAJOR OIL LEAK WAS DISCOVERED. THE SOURCSDR CA050104010Bleed Valve · failed(CAN) BLEED VALVE WAS INSTALLED AFTER OVERHAUL TO REPLACE A TIME EXPIRED UNIT. SUBSEQUENT POWER CHECK REVEALED HIGH TOT. BLEED VALVE WAS WAS RETURNED TO VENDOR TO CORRECT FAULT. PART WAS INSTALLED AND FAILED A SECOND TIME. PART WAS REPLACED WITH ANOTHER UNSDR CA041129017Combustion Liner · cracked(CAN) THE PILOTS WERE DOING TRAINING, THEY NOTICED AN INCREASE IN TOT. DID A POWER CHECK AND FOUND THAT THE ENGINE WAS BELOW SPEC. AIRCRAFT RETURNED TO BASE AND IT WAS DISCOVERED THAT THE THERE WAS A 1 INCH CRACK THAT FOLLOWED A WELD IN THE E ARM PIT AREA. NSDR CA041209008Line · cracked(CAN) WHILE ON A SLING OPERATION, PILOT NOTICED A FLUID LEAKING FROM THE BELLY IN THE CARGO MIRROR. THE AIRCRAFT WAS LANDED IMMEDIATELY AND IT WAS DISCOVERED THAT FUEL WAS LEAKING FROM A FUEL LINE FITTING. THE ENGINE WAS SHUT DOWN AND THE LINE WAS CHECKED FOR SDR KBM2004F00244Skid · corrodedREMOVED LANDING GEAR ASSY DUE TO RT SKID FAILURE, JUST AFT OF AFT CROSS TUBE MOUTH, FOUND HEAVY CORROSION IN AREA OF FAILURE. APPEARED TO BE RELATED FILL LENGTH SKID SHOES. REPLACED SKID GEAR WITH AAI STC NR SH139250, THIS GEAR WAS REMOVED SERVICEABLE FROM ASDR YTRR099306Fuel Control · failedFUEL CONTROL PURCHASED NEW. ENGINE DEACCELERATED TO 88 PERCENT AND WAS NOT ABLE TO RECOVER.SDR CA041029006Tach Generator · unserviceableOUT OF THE FOUR MOUNTING PAD EARS, ONE EAR WAS FOUND COMPLETELY BROKEN OFF.SDR CA041027001Drag Pin · wornAFT CAST SURFACE OF DRAG PIN ASSY THAT IS PART OF M/R GEARBOX CONTACTED YOKE OF ISOLATION MOUNT. CONTACT DUE TO EXCESSIVE CASTING MATERIAL AFT OF BEARING BORE. COMPONENT SHOP RECEIVED AN ISOLATION MOUNT FOR REPAIR THAT HAD FRETTING/CONTACT MARKS ON YOKE. MARKSDR CA041029005Bearing · spalledTHE AIRCRAFT WAS ON A FLIGHT WHEN A TRANSMISSION CHIP LIGHT OCCURRED, APPROPRIATE ACTION WAS TAKEN. THERE WAS FERROUS METAL FOUND ON THE TRANSMISSION OIL MONITOR AND TRANSMISSION CHIP DETECTORS. THE TRANSMISSION AND MAST WERE REMOVED FOR INVESTIGATION. THE MSDR CA041007002Tail Rotor · misrigged(CAN) TAIL ROTOR FLAPPING ANGLE FOUND SET TO 18 DEGREES INSTEAD OF THE CORRECT ANGLE OF 12 DEGREES ALLOWING POSSIBLE COTACT WITH TAILBOOMSDR CA041109006Drag Pin · unserviceable(CAN) DURING INSPECTION THE DRAG LINK BEARING WAS FOUND SMOKING. THIS A NEW STYLE IN WHICH BEARING AND NOT WHOLE ASSEMBLY IS REPLACED. NEW BEARING INSTALLEDNOTE: THIS STYLE OF BEARING WAS INTRODUCED THROUGHT B206-00-173 TO ELIMINATE THE PROBLEM WITH THE STAKINSDR CA050216010Hanger Assy · rotated(CAN) PILOT REPORTED A HIGH FREQUENCY VIBRATION. UPON INVESTIGATION, THE BEARING IN THE FORWARD HANGER ASSEMBLY OF THE OIL COOLER BLOWER WAS FOUND TO BE ROTATING. BLOWER ASSEMBLY REPLACED.SDR CA040917005Mount · misaligned(CAN) LOWER MOUNTING BASE WAS FOUND TO BE INSTALLED 90 DEGREES FROM CORRECT ALIGNMENT TO ALLOW ENGAGEMENT OF LOCK PIN.SDR CA040901002Drive Assy · damaged(CAN) TWICE WITHIN A 20 HOUR PERIOD,THE YELLOW TEMP INDICATERS CHANGED COLOUR, AND GREASE WAS LEAKING FROM THE FWD. END OF THE DRIVE SHAFT. THE SHAFT WAS REPLACED AND NO FURTHER PROBLEMS HAVE BEEN REPORTED.THE SPHERICAL COUPLING WAS REPLACED ON THE PROBLEM SHASDR EAHR200400001Scroll · crackedCOMPRESSOR DISCHARGE SCROLL CRACKED AT LOWER RT CUSTOMER BLEED AIR FITTING.SDR YTRR096993Governor · malfunctionedTHE GOVERNOR WAS INSTALLED AND AFTER 65.8 HOURS N2 WAS NOT ADJUSTABLE ABOVE 97 PERCENT. THE GOVERNOR WAS REPLACED AND THE PROBLEM DISAPPEARED.SDR YTRR096994Fuel Control · malfunctionedFUEL CONTROL WAS OVERHAULED. INSTALLED AND AFTER 164.1 TSO THE START ACCELERATE COULD NOT BE ADJUSTED AND THE ENGINE WOULD HANG AT 60 PERCENT N1 AND COULD NOT BE INCREASED FURTHER.SDR 2004FA0000733Mount · out of positionAIRCRAFT FOUND TO HAVE CONTACT WITH FAN CONTROL ROD AND FAN DRIVESHAFT. WHICH MAY HAVE BEEN THE CAUSE OF HIGH VIBRATION IN AIRFRAME. MFG CALLED TO CHECK THE ALIGNMENT OF THE FAN MOUNT. SECOND TIME WE HAD RUB WITH DRIVESHAFT SINCE AIRCRAFT WAS NEW. UPON REMSDR CA040817007Pump · malfunctioned(CAN) ON STARTUP OF THE ENGINE THERE WAS A HOWLING NOISE COMING FROM THE ENGINE. THE NOISE WOULD ONLY BE ON STARTUP AND WOULD GO AWAY ONCE THE ENGINE WAS RUNNING. IT WAS DETERMINED THAT THE NOISE WAS COMING FROM THE FUEL PUMP AND WAS REPLACED.SDR YTRR096997Governor · failedGOVERNOR WAS OVERHAULED, AFTER 482.3 TSO, THE GOVERNOR EXPERIENCED A LOW SIDE FAILURE WHERE N2 COULD NOT BE SET ABOVE 92 PERCENT.SDR YTRR096996Governor · failedGOVERNOR WAS OVERHAULED AND AFTER 98.3 HRS TSO, THE ENGINE EXPERIENCE AN OVERSPEED THAT WAS CAUSED BY A HIGH SIDE FAILURE.
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