Allison 250-C20B
Service difficulty reports · 1,981
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 = '250C20B' 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 = '250C20B' 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 CA090928010Fcu · malfunctioned(CAN) FCU WAS CAUSE OF DELAYED LIGHT OFF. ANYWHERE FROM 1-5 SECONDS AND WORSE WHEN COLD.SDR CA090915001Seal · failed(CAN) THE SEAL ASSY FAILED AND THE DRIVESHAFT GREASE LEAKED FROM THE COUPLING CAUSING THE DRIVESHAFT TO OVER-TEMP DUE TO LOSS OF LUBRICANT (TC# 20090915001)SDR KS12009F00000Exhaust Stack · crackedINSTALLED EXHAUST STACK ON 9/18/2008. ACFT TT 9927.8. DURING ANNUAL INSPECTION FOUND A CRACK AND HAD A WELD REPAIR DONE. 9/2/2009 ACFT TT 10302.9. DURING A 100 HR INSPECTION, FOUND ANOTHER CRACK. REPLACED EXHAUST STACK FROM SERVICE. (K)SDR CA090827006Seal · leakingDURING A DAILY INSP, DONE BY THE PILOT IN COMMAND, TELA TEMPS ON FWD DRIVESHAFT COUPLING WERE FOUND TO BE BLACK IN COLOR. UPON FURTHER INVESTIGATION GREASE WAS FOUND TO BE LEAKING AS WELL. DRIVESHAFT WAS REMOVED AND DISASSEMBLED. INNER PART OF THE SEAL WAS SDR CA090831004Pump · leakingPUMP LEAKING, SERVICABLE PUMP INSTALLED.SDR 2009FA0000740Impeller · crackedCOMPRESSOR WAS RECEIVED TO REPAIR FOR DAMAGE TO ROTOR. UPON DISASSEMBLY AND INSP, DISCOVERED THAT A SECTION OF SHROUD BETWEEN THE NR 2 VANES AT THE FWD END OF THE IMPELLER (IDENTIFIED AS DIAMETER I) HAD BROKEN OFF. CAUSE COULD NOT BE DETERMINED. HOURS AND CSDR 2009FA0000827Beam · crackedA SMALL CRACK WAS DISCOVERED IN THE ROOF BEAM WEB, TOP RIGHT OF VERTICAL TUNNEL, NEAR STA 87.20 AND WL 67.40. IT WAS FOUND DURING AN ANNUAL INSPECTION.SDR 2009FA0000662Gear · failedMETAL IN OIL. MAKING PASTE FROM GRINDING UP SMALL PIECES OF GEAR SHAFT.SDR 2009FA0000663Drive Gear · wornMETAL IN OIL. MATERIAL LOSS ON GEAR TEETH, WORN THROUGH NITRIDE COATING.SDR 2009FA0000664Gearshaft · wornMETAL IN OIL. MATERIAL LOSS ON GEAR TEETH, WORN THROUGH NITRIDE COATING.SDR 2009FA0000665Gearshaft · wornMATERIAL LOSS ON GEAR TEETH, WORN THROUGH NITRIDE COATING.SDR 2009FA0000666Gearshaft · wornMATERIAL LOSS ON GEAR TEETH, WORN THROUGH NITRIDE COATING.SDR 2009FA0000667Drive Gear · wornMATERIAL LOSS ON GEAR TEETH, WORN THROUGH NITRIDE COATING.SDR CA090730004Bearing · wornTHE LINEAR ACTUATOR ADJUSTMENT SCREW STICKS AND DOES NOT POP BACK OUT, THE SHAFT BEARING HAS PLAY IN IT.SDR CA090730005Arm · stiffTHE GOVERNOR CONTROL ARM IS STIFF, THIS CAUSES DROOP.SDR CA090721003Mount · cracked(CAN) NOTICED WORKING ENGINE MOUNT. INSPECTED ATTACHMENT BOLT FOR TORQUE AND FOUND IT PROPERLY TORQUED. LIFTED AFT END OF ENGINE AND FOUND MOVEMENT ON FIREWALL ATTACHMENT SIDE OF ENGINE MOUNT LEG AND UNDER CLOSER INSP FOUND IT CRACKED TWICE TO BOLT HOLE. REPLSDR CA090722008Fitting · broken(CAN) 10TH-100 HR INSP REVEALED SLIGHT `GIVE` OR PLAY BETWEEN TAILBOOM AND RT HORIZONTAL MOUNT FITTING. VISUAL INSP SHOWED NOTHING. HORIZONTAL STABILIZER WAS TIGHT IAW PROPER INSTALLATION. FURTHER DISASSEMBLY OF RT STABILIZER FROM TAILBOOM REVEALED MOUNTINGSDR CA090706001Check Valve · malfunctioned(CAN) PILOT ON HELI-PAD, BOTH ENG ONLINE WITH TORQUE`S MATCHED. WHEN PILOT PULLED ACFT INTO HOVER NOTICED A LARGE TORQUE SPLIT BETWEEN NR 1 AND NR 2 ENG. NR 1 Q READ 60 PERCENT AND N1 ONLY READ 90.5 PERCENT. COLLECTIVE LOWERED, ACFT LANDED WITH NO PROBLEMS, SDR 2009FA0000509Turbine · seizedDURING EXTERNAL LOAD OPERATIONS AT A HOVER, THE ENGINE STOPPED SUDDENLY CAUSING THE PILOT TO AUTO ROTATE FROM APPROX 80 FEET AGL. THE PROBABLE CAUSE OF THE ENGINE STOPPAGE IS A MALFUNCTION IN THE TURBINE MODULE. RECENT OCCURRENCE, NO PRELIMINARY REPORT PUBLISDR CA090529002Governor · fluctuates(CAN) GOVERNOR FLUCTUATES.SDR CA090525003Drive Shaft · mismanufactured(CAN) AIRFRAME AND T/R VIBRATION. THE RUNOUT OF THE TAILROTOR DRIVESHAFT WAS CHECKED AND THE FINDING WAS THE FWD SPLINES ARE BONDED INTO THE T/R INCORRECTLY, THE FWD SPLINES WERE 0.040 INCHES OVER. THE T/R LONG DRIVE SHAFT WAS REPLACED AND THE ACFT WAS RETURNESDR CA090528003Gearbox · leaking(CAN) GEARBOX LEAKING EXCESSIVELY.SDR CA090528004Bearing · worn(CAN) BEARINGS FOUND WORN.SDR 2009FA0000451Impeller · crackedIMPELLER CRACKED AT ATTACH POINT TO SHAFT. PILOT REPORTED LOUD NOISE AND LANDED THE HELICOPTER.SDR CA090508003Tail Boom · damaged(CAN) TAILBOOM WAS INSTALLED WHEN DEFORMATION WAS FIRST DISCOVERED. BOOM IS TWISTING AT THE MARKED AREAS. FWD INDENT IS .5 DEEP AT 100 PERCENT RPM FLAT PITCH AND THE 3 AFT INDENTS ARE AT LEAST .2500 INCH INDENTED AND RESEMBLE A RUBBER WAVE. AS SOON AS THE POWSDR 2009FA0000332Hub · crackedMAIN ROTOR HUB PN 51437-11 SN 20074 SHOWED SIGNS OF POSSIBLE CRACK DURING PREFLIGHT, PERFORMED DYE PENETRANT INSP, AS PRECAUTIONARY MEASURE, CRACK INDICATION PRESENT. REMOVED PART FROM FURTHER SERVICE, AND INSTALLED SERVICEABLE PART IN ITS PLACE. CRACK INDICSDR 2009F00029Transponder · malfunctionedACFT EQUIPPED WITH NEW GPS TRANSPONDER AND GNS430W GPS WITH TRAFFIC INFORMATION SERVICE (TIS) DISPLAYED ON GNS430W AND AUDIO WARNINGS IN PILOT/COPILOT AUDIO. FLIGHTS IN SEATTLE AREA MULTIPLE TIS FALSE WARNINGS (APPROX. ONE PER 0.5 FLIGHT HOURS) THAT WARN OF CSDR CA090407012Bearing · damaged(CAN) DURING A SERVICEABILITY CHECK AT T/R ASSY SECTION (BLADE S/N CS-10215) BEARING MOVING INSIDE THE BLADE, FOUND.SDR CA090407014Tube · chafed(CAN) DURING ANNUAL INSP OF HYDR BOOSTER 2 METAL TAGS OF PRESSURE AND RETURN FLEXIBLE LINE OF THE HYDR PUMP WERE CONTACTING 2 HYDR TUBES CAUSING CHAFING. HYDR TUBES ARE EAR OUT OF LIMIT CAUSING THE PARTS TO BE UNSERVICEABLE.SDR CA090421006Lens · spalled(CAN) SPALLS IN UPPER EDGE OF ATTACHMENT FLANGE.SDR CA090401005Probe · damaged(CAN) ENGINE TECH RECEIVED NEW ITEM FROM STOCK. PART INSPECTED PRIOR TO INSTALLATION. PRESSURE PROBE WAS FOUND TO HAVE AN INSUFFICIENT AMOUNT OF BRAZE MATERIAL AT THE JOINT WHERE THE TUBE AND ELBOW ARE JOINED TOGETHER. IMPORTANT: MFG ISSUED AN ALERT CEB A-137SDR CA090402007Bearing · seized(CAN) NEW PMA ROD END FOR M/R PITCH LINK WAS INSTALLED AND BEARING WAS VERY TIGHT. AFTER 2.1 HRS OF OPERATION THE SWAGE LOST IT EFFECTIVENESS AND THE OUTER RACE OF THE BEARING STARTED TO ROTATE IN THE ROD END. THE ACFT WAS UNDERGOING TRACKING AND BALANCING WHESDR 2009FA0000260Pinion Gear · making metalENGINE CAME INTO SHOP FOR METAL IN OIL. UPON DISASSEMBLY TORQUE METER GEAR, P/N 23035299, S/N NN505263 PRIMARY FAILED PART. PINION GEAR P/N 6889700 S/N KU507731 SECONDARY FAILED PART FOR SOURCE OF MIO. BOTH GEARS SCRAPPED DUE TO WEAR WITH A TT IN SERVICE OF SDR CA090407013Stator Vane · unserviceable(CAN) DURING COMPRESSOR HALVES INSP, ONE STATOR BLADE OF THE LAST AXIAL COMPRESSOR STAGE WAS TORN AND WAS SIDEWAYS CONTACTING THE ONE NEXT TO IT. THE BLADE WAS ONLY HELD IN PLACE BY 5-10 PERCENT OF THE BLADE ROOT. THIS COULD HAVE CAUSED THE BLADE TO GO THRU THSDR CA090313009Blades · broken(CAN) ENGINE EXPERIENCED A COMPRESSOR STALL IN CRUISE. PILOT RETURNED TO BASE, AS THE ENGINE WAS LOADED UP FOR LANDING 2 MORE COMPRESSOR STALLS OCCURRED. ACFT WAS LANDED AND SHUTDOWN WITHOUT FURTHER INCIDENT. COMPRESSOR WAS SENT TO REPAIR SHOP WHERE IT WAS NOTSDR CA090223007Grip · cracked(CAN) WHILE DOING A FREEDOM OF CONTROLS CHECK PRIOR TO START UP THE PILOT WAS MOVING THE CYCLIC STICK THROUGH THE FULL RANGE OF MOVEMENT. WHILE DOING SO THE CYCLIC GRIP BROKE IN HALF IN HIS HANDS. THE PREFLIGHT CHECKS ENDED AFTER THE OCCURENCE.SDR CA090309004Feeder Cable · chafed(CAN) DURING A 600 HRS AIRFRAME INSP, THE GENERATOR OUTPUT CABLE OF ENGINE NR 2 WAS FOUND CHAFING ON THE MAIN RELAY BOX 1VE. THE SHEATH OF THE CABLE WAS WORN TO THE POINT WHERE THE CONDUCTOR WAS EXPOSED. A NEW WIRE WAS INSTALLED.SDR CA090306004Orifice · dirty(CAN) ENGINE PWR LOST WITH N2/NR SPEED DECELERATING TO ABOUT 90 PERCENT DURING LEVEL CRUISE FLIGHT AT 2000 FT. PILOT PROCEEDED TO EXECUTE SUCCESSFUL EMERGENCY LANDING. MX INSPECTED THE FUEL SYS FINDING NO APPARENT FAULT. A GROUND RUN WAS PERFORMED SATISFACTORSDR CA090115008Sprag Assy · unserviceableSPRAG ASSY FAILED 300 HR INSPECTION DUE TO 2 BROKEN CORNERS OF 2 DIFFERENT TEETH (SPRAGS). NO OTHER DAMAGE WAS FOUND TO THE ASSEMBLY AS A RESULT OF THIS INCIDENT. CLUTCH ASSY WAS WORKING FINE PRIOR TO INSPECTION. NEW SPRAG ASSY INSTALLED AND CLUTCH RETURNEDSDR CA090114005Skid · unserviceableTHE AIRCRAFT WAS BEING POSITIONED IN THE HANGER FOR MAINTENANCE. THE TAIL SKID WAS BEING USED TO STEADY THE HELICOPTER AS IT WAS BEING HOISTED TO HAVE THE LANDING GEAR REMOVED. A PORTION OF THE TAIL SKID BROKE OFF IN THE ENGINEER’S HAND. THE CAUSE OF THE BRSDR CA090112011Bellcrank · crackedA CRACK WAS FOUND ON THIS FLIGHT CONTROL BELLCRANK DURING ANNUAL INSPECTION.SDR CA090121012Pump · unknownDURING ENGINE TROUBLESHOOTING A STARTING ISSUE, THE FUEL PUMP WAS REPLACED DUE TO UNDETERMINED REASONS.SDR CA090122009Support Tube · crackedDURING A FUEL CELL CHANGE (DUE TO FUEL SEEPAGE), A SMALL CRACK WAS FOUND IN THE AFT CROSSTUBE SUPPORT STRUCTURE, ON THE RT SIDE OF THE AIRCRAFT. THE LOCATION OF THE CRACK WAS AT THE FWD BOTTOM RIVET OF THE CROSSTUBE SUPPORT. THE CRACK WAS APPROXIMATELY 1/4 INSDR 2008FA0000902Tube · unserviceableTHIS DEFECT WAS DETECTED DURING TROUBLESHOOTING FOR AN ENGINE PWR PROBLEM. THIS FLEX TYPE TUBE ASSY WAS INSTALLED IN CONJUCTION WITH AN STC FROM ENG PWR PROBLEM. THIS FLEX TYPE TUBE ASSY WAS INSTALLED IN CONJUNCTION WITH AN STC, PC SAFETY VALVE KIT SE5511NM.SDR CA081204004Handle · damaged(CAN) DURING CRUISE, THE ROTOR BRAKE HANDLE DOWN WARNING LIGHT TURN ON INTERMITTENTLY. THE WARNING LIGHT SWITCH IS ADJUSTED TO WARN PILOT IF THE HANDLE IS NOT IN ITS NEUTRAL OR DOWN POSITION AND TO VERIFY IF THE REASON IS NOT THE PILOT`S SEAT BELT BEING UNDER SDR CA081125005Washer · cracked(CAN) THE VERTICAL FIN WAS REMOVED TO FACILITATE SEAL REPLACEMENT OF THE PITCH CHANGE MECHANISM. THE RADIUS WASHERS THAT ARE USED ON THE VERTICAL FIN ATTACHMENT WERE INSPECTED, AND IT WAS NOTED THAT 3 OF THE 4 WASHERS HAD CRACKS ON THE OUTSIDE PERIMETER OF THESDR CA081105001Pump · misinstalled(CAN) TWICE NOW WE HAD FOUND THE FWD MAIN TANK BOOST PUMPS WHERE INSTALLED IN THE WRONG ORIENTATION, THE TRANSFER TUBES (FEED LINE) WAS PULL OUT OF THE FEED TANK. THE FORWARD TRANSFER PUMP HAS SYMMETRICAL MOUNTING HOLE. THE ORIENTATION OF THE PUMP DETERMINES TSDR CA081107007Drive Shaft · failed(CAN) DURING REMOVAL OF THE GOVERNOR FOR SCHEDULED OVERHAUL, AT REMOVAL FROM ENGINE GEARBOX, THE CLIP THAT RETAINS THE DRIVEGEAR ON THE PT SHAFT WAS NOT LOCATED IN THE GROOVE ON THE SHAFT, AND THE WASHERS THAT ARE RETAINED BY THE CLIP AND SET AGAINST THE DRIVESDR 2009FA0000508Turbine · seizedDURING EXTERNAL LOAD OPERATIONS AT A HOVER, THE ENGINE STOPPED SUDDENLY CAUSING THE PILOT TO AUTOROTATE FROM APPROXIMATELY 120-150 FEET AGL. THE PROBABLE CAUSE OF THE ENGINE STOPPAGE WAS A MALFUNCTION IN THE TURBINE MODULE. NO FINAL REPORT HAS BEEN PUBLISHEDSDR CA081021005Governor · malfunctioned(CAN) PILOT REPORTED ROTOR SPEED HUNTING IN CRUISE SO THE GOVERNOR WAS REMOVED TO CLEAN THE ORIFICES. ONCE REMOVED IT WAS NOTICED THAT THE EPOXY BOND ON THE END OF THE DRIVESHAFT WAS MISSING AND THE SPLINE DRIVE WAS LOOSE ON THE GOVERNOR DRIVESHAFT. IF LEFT TH
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