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 CA110215010Fcu · malfunctionedOCCASIONAL DELAYED LIGHT OFF AFTER THROTTLE IS CRACKED OPEN TO DETENT ON GROUND RUN. REPLACED FCU.SDR CA110203006Filter · cloggedON TAKEOFF FROM RAMP WHEN ACFT WAS PULLING IN 75 PERCENT TORQUE THE NR 1 FILTER LIGHT ILLUMINATED AS POWER WAS REDUCED THE LIGHT WOULD EXTINGUISH ON A SECOND ATTEMPT THE SAME OCCURRED. FLIGHT WAS TERMINATED AND ACFT RETURNED TO HANGAR. AIRFRAME FUEL FILTER WASDR CA110221005Filter · clogged(CAN) DURING TAKEOFF, FROM RAMP WHEN ACFT WAS PULLING IN 75 PERCENT TORQUE THE NR 1 FILTER LIGHT ILLUMINATED AS POWER WAS REDUCED THE LIGHT WOULD EXTINGUISH ON A SECOND ATTEMPT THE SAME OCCURRED. FLIGHT WAS TERMINATED AND ACFT RETURNED TO HANGER. AIRFRAME FUSDR CA110125038Turbine · leaking(CAN) DURING DEPARTURE FROM AIRFIELD, FLIGHT CREW PASSING THROUGH 800 FT AGL NOTED THE TURBINE N2 SPEED INCREASING FOLLOWED BY A LOUD HUMMING NOISE. THEY THEN HAD AN ENGINE CHIP LIGHT. THEY LANDED THE ACFT IMMEDIATELY. UPON MAINTENANCE ARRIVAL IT WAS NOTED SDR CA110106008Clamp · wornFOR STC SR01062LA, IT WAS DISCOVERED DURING INSPECTION THAT THERE THE HEAD OF THE TEE BOLT RESTS IN THE BAND CLAMP HAD WORN THROUGH TO THE POINT THAT THE TEE BOLT COULD BECOME DISENGAGED RESULTING POTENTIALLY IN EXHAUST CLAMP PARTS DEPARTING THE AIRCRAFT INTO SDR 2011F00003Transmission · making metalPILOT EXPERIENCED A MAIN ROTOR TRANSMISSION CHIP LIGHT DURING TAKEOFF. THE PILOT RETURNED TO LANDING WITH NO INCIDENT. MECHANICS VERIFIED CHIP LIGHT AND FOUND ONE .1250 INCH SLIVER ON THE LOWER PLUG AND A .0625 INCH SLIVER ON THE UPPER PLUG. WHEN DRAINING THESDR 2011F00004Transmission · making metalPILOT EXPERIENCED A MAIN ROTOR TRANSMISSION CHIP LIGHT DURING TAKEOFF. THE PILOT RETURNED TO LANDING WITH NO INCIDENT. MECHANICS VERIFIED CHIP LIGHT AND FOUND ONE .1250 INCH SLIVER ON THE LOWER PLUG AND A .0625 INCH SLIVER ON THE UPPER PLUG. WHEN DRAINING THE SDR CA101122023Encoder · failedBLIND ENCODER FAILED TO REPORT ALTITUDE. ENCODER REPLACED. CORROSION FOUND AROUND CONTACTS OF ENCODER D-SUB CONNECTOR. ENCODER LAST 24 MONTH RECERTIFICATION PERFORMED JUNE 22, 2009. TSN U/K.SDR CA101122029Fuel Nozzle · malfunctioned(CAN) AIRCRAFT EXPERIENCING START DELAY FROM OPENING THROTTLE TO ENGINE LIGHT OFF. FUEL NOZZLE REPLACED. AIRCRAFT NOW HAS NORMAL STARTS.SDR 2010FA0001143Turbine · damagedAT ENGINE SHUTDOWN AFTER LAST FLIGHT OF THE DAY THE MECHANIC HEARD A TURBINE RUB NOISE IN THE ENGINE ASSY. ACFT WAS REMOVED FROM SERVICE FOR MX.SDR 2010FA0001083Warning Light · false activationON APPROACH TO LANDING THE PILOT HAD AN ENGINE CHIP LIGHT EVENT. THE LIGHT REMAINED ON DURING SHUTDOWN BUT WHEN MX ARRIVED THE LIGHT WAS OUT. BOTH ENGINE CHIP PLUGS WERE PULLED AND WERE FOUND TO BE CLEAN OF DEBRIS. THE LIGHT EVENT COULD NOT BE DUPLICATED.SDR 2010FA0001084Connector · dirtyON APPROACH TO LANDING THE PILOT HAD A CHIP LIGHT EVENT. MX REMOVED BOTH ENGINE CHIP PLUGS AND FOUND NO DEBRIS. IT WAS DETERMINED THAT THE LOWER CHIP PLUG CONNECTOR PLUG WAS SHORTED INTERNALLY AND CAUSING THE LIGHT. THE CONNECTOR WAS REPLACED.SDR CA101115010Servo · leaking(CAN) HYDRAULIC SERVO PN: 206-076-031-015 FOUND LEAKING FROM VALVE ASSEMBLY DURING 100 HOUR INSPECTION. HYDRAULIC SERVO REPLACED.SDR CA100930004Drain Valve · failedDURING A PREFLIGHT INSP, ENG FUEL FILTER DRAIN VALVE PN 206-061-634-003 WAS TURNED TO DRAIN FUEL. AT THAT TIME IT WAS NOTICED THAT THE SPRING ACTION WAS ROUGH AND UPON FURTHER INVESTIGATION IT WAS DETERMINED THAT 2 SMALL SPRINGS IN THE HANDLE HAD FALLEN DOWN SDR 2010FA0001107Seal · missingON 5/7/2010, INSTALLED A NEW ANTI-ICE VALVE PN 23053192 AT ACTT 14805.1. DURING A ROUTINE 100 HR INSP OF THE ACFT ON 9/24/2010 AT ACTT 14904.8. REMOVED AND INSPECTED THE VALVE AND DISCOVERED THAT THE POPPET SEAT SEAL WAS MISSING FROM THE POPPET. POPPET SEAT SDR CA100927002Blade · brokenENGINE FAILURE IN FLIGHT, PILOT SUCCESSFULLY AUTO ROTATED ACFT ONTO CREEK BED. NO DAMAGE TO AIRFRAME. COMPRESSOR CASE HALF HAD A HOLE IN THE SIDE. COMPRESSOR AND TURBINE ASSYS REMOVED FOR FURTHER INSP. INSP BEING CARRIED OUT LTD. WE HAVE BEEN INFORMED THAT SDR CA100916006Strut · crackedAFTER CHANGING A LANDING GEAR DAMPER FOR LOW PRESSURE, THE ACFT WAS PLACED BACK ON THE GROUND. AFTER IT WAS SITTING ON THE GROUND THE SAME ACFT ORIENTATION PRIOR TO CHANGING THE DAMPER WAS NOTED, TAIL LOW AND LEANING TOWARD THE LT. UPON INSP OF THE LANDING GSDR CA100915004Ground Stud · looseAFTER ENGINE START, PILOT REPORTED GEN WAS INTERMITTENT. AFTER TROUBLESHOOTING WAS PERFORMED AND NOTHING WAS FOUND A GROUND RUN WAS PERFORMED WITH HAT RACK AREA REMOVED. IT WAS DISCOVERED THAT WHEN THE PILOT TRIED TO ACTIVATE THE STARTER GENERATOR, THERE WERSDR 2010FA0000952Engine · making metalON APPROACH TO LANDING PILOT HAD AN ENGINE CHIP WARNING LIGHT. THE PILOT LANDED THE ACFT AND THE LIGHT REMANED ILLUMINATED. MX FOUND METAL PARTICLES AND PASTE ON THE LOWER AND UPPER ENGINE CHIP PLUGS. THE ENGINE WAS REMOVED FROM THE ACFT.SDR 2010FA0001002Stator Vane · brokenUPON REMOVAL OF THE COMPRESSOR CASE FOUND 2 6TH STG STATOR VANES MISSING. THE VANES HAD BROKEN OFF NEAR THE BLADE ROOT, AT APPROX THE LEVEL OF THE COMPRESSOR CASE PLASTIC COATING. THE COMPRESSOR CASE HAD BEEN O/H 366.6 HRS PRIOR.SDR 2010FA0001010Seal · leakingFOUND SEAL LEAKING. THIS IS THE LATEST SEAL, HAVING PROBLEMS WITH. THESE SEALS ARE VERY DIFFICULT TO INSTALL DUE TO NEW MATERIALS AND NO CHANGES IN PROCEDURE OR TOOLING HAS COME FROM THE MFG. THE PROCESS OF INSTALLING THE SEAL USUALLY DESTROYS THE SEALING LSDR CA100824006Pin · brokenTENSION TORSION PIN BROKE OFF AT MAIN ROTOR HEAD WHERE DRAG BRACE ATTACHES TO PIN. ACFT WAS IN CRUISE FLIGHT PERFORMING AERIAL SPRAY APPLICATION. ACFT STARTED TO SHAKE AND VIBRATE. PILOT PERFORMED EMERGENCY LANDING IN SPRAY BLOCK ON A PREVIOUSLY CLEARED LANSDR HXF2010F00000Skid · crackedDURING A 100 HR INSP, A CRACK WAS FOUND ON THE RT FWD LANDING GEAR FOOT. THE CRACK LOOKS TO HAVE ORIGINATED AT THE LOWER END, OTBD SIDE AT THE TOP OF THE BOSS AREA JUST ABOVE THE SKID TUBE MOUNT HOLES. THE CRACK EXTENDS UP ABUT 1" AND SPIDERS FWD AND AFT. TSDR 2010FA0000798Pinion Gear · damagedMETAL IS SPREAD AT THE CONTACT POINT OF THE GEAR TEETH. IT APPEARS LIKE THE METAL IS SOFT. THE CONDITION OF THIS GEAR CAUSED A HIGH VIBRATION IN THE ENGINE ASSY.SDR KS12010F00000Turbine · seizedHELICOPTER PILOT LANDED TO HOOK UP LONG LINE (UNDER FAA PART 133), HOOKED UP LONG LINE. PILOT HOVERED INTO POSITION FOR AN EXTERNAL LOAD LIFT AND HEARD A LOUD GRINDING NOISE AND HAD AN ENGINE CHIP LIGHT. HE LANDED THE ACFT, SHUT IT DOWN AND CHECKED THE CHIP SDR HDNR20100723CCDCoupling · fracturedCOMPRESSOR ADAPTER COUPLING FRACTURED IN THE SAME FAILURE MODE AS ADDRESSED BY AD 2004-26-09. THIS COMPRESSOR WAS IN THE POST-AD, CEB A-1392 (PRE-REV. 2), CONFIGURATION WHICH WAS INTENDED TO FIX THE ORIGINAL PROBLEM WITH THIS PART FRACTURING. THE PARTS ASSEMBSDR HDNA201006212010Clamp · looseAT TAKEOFF, THE NR1 ENGINE FIRE LIGHT ILLUMINATED. THE ACFT RETURNED TO LANDING ZONE WITHOUT INCIDENT. UPON INSP, IT WAS FOUND THAT THE NR 1 ENGINE INBD EXHAUST STACK HAD COME LOOSE FROM THE TURBINE EXHAUST COLLECTOR AND HAD WEDGED ITSELF INTO THE ENGINE COWLISDR CA100707006Rotor Head · corroded(CAN) DURING A 300 HOUR INSPECTION, DIS-ASSEMBLY OF THE TAIL ROTOR , THE ENGINEER EXPERIENCED DIFFICULTY REMOVING THE TAIL ROTOR TO SHAFT ATTACHMENT BOLT. UPON REMOVAL OF THE BOLT AND INSPECTION OF THE T/R ASSY. THE ENGINEER DISCOVERED THAT THERE WAS CONSIDESDR 2010FA0000578Engine · making metalPILOT DEPARTED THE AIRPORT FOR A TOUR FLIGHT AND AN ENGINE CHIP WARNING LIGHT CAME ON. THE PILOT RETURNED TO THE AIRPORT. MX PULLED THE UPPER AND LOWER CHIP PLUGS AND FOUND A SMALL AMOUNT OF MATERIAL ON THE UPPER PLUG .79MM OR LESS IN SIZE. AFTER A 30 MINUTE PSDR CA100622017Floor Panel · corrodedDURING A 100 HR/ANNUAL INSP, BAGGAGE FLOOR PROTECTIVE PANEL WAS REMOVED TO INSPECT THE BAGGAGE FLOOR PANEL. CORROSION WAS NOTED AROUND AN INSERT AREA AND FURTHER INVESTIGATION FOUND THAT CORROSION HAD PENETRATED THE UPPER SKIN, AND WAS MOVING INTO THE HONEYCOMSDR 2010FA0000519Warning Light · false activationPILOT EXPERIENCED AN ENGINE CHIP LIGHT DURING A TOUR FLIGHT AND PROCEEDED TO LAND AT AN OFFSITE AIRPORT. MX ARRIVED ON SCENE AND FOUND THAT THE LIGHT WAS NO LONGER ON. THE MECHANIC INSPECTED UPPER AND LOWER ENGINE CHIP DETECTORS AND FOUND NO EVIDENCE OF METALSDR DCGA2010F00115Engine · making metalPILOT EXPERIENCED AN ENGINE CHIP LIGHT DURING FLIGHT AND PERFORMED AN UNSCHEDULED LANDING AT AIRPORT. THE AIRCRAFT WAS TRANSPORTED BY TRUCK TO ITS HOME BASE. THE ENGINE ASSEMBLY WAS REMOVED FROM AIRCRAFT FOR INSPECTION BY ROLLS ROYCE TECHNICIAN.SDR CA100520002Longeron · crackedUPPER LONGERON, PN 369D23072-3, CRACKED 2.5 AFT OF STA 131.0 BULKHEAD, CRACK ORIGINATED FROM A FASTENER HOLE AND ENDED AT THE EDGE OF THE HORIZ LEG OF THE EXTRUSION.SDR CA100527004Pin · worn(CAN) BLADE PIN FOUND TO BE CRACKED BY PILOT ON A VISUAL INSPECTION. IT IS AN EXPANDABLE PIN WITH A NUT TO ADJUST TENSION. PIN FOUND TO BE CRACKED AT THE END OF THE THREADS, PIN HAD 779.4 HOURS REMAINING ON IT.SDR P3T2010F00000Spindle · corrodedTRANSMISSION SPINDLE MOUNT, WAS FOUND TO HAVE EXCESSIVE PITTING CORROSION DURING A 1200 HR TRANSMISSION TOP CASE INSPECTION. R & R WITH -0-TT, NEW SPINDLE. SENT OLD CORE TO VENDOR BUT UPON NDT INSP, VENDOR REJECTED CORE DUE TO POSSIBLE STRESS CRACKS AND WASSDR 2010FA0000447Firewall · crackedCRACK AT STA 124, ENGINE FIREWALL, M/R TRANSMISSION OIL COOLER LINES AREA.SDR 2010FA0000822Anti-Ice Valve · unsecureTHE INSTALLED ANTI-ICE VALVE (PN 23053192AL) POPPET SEAT RETAINING SCREW WAS NOT PROPERLY STAKED DURING THE MFG PROCESS AND AS A RESULT THE SCREW WAS INGESTED INTO THE TURBINE SECTION OF THE ENGINE AND DAMAGED THE NR 1, 2, 3 WHEELS, THE 1ST, 2ND AND 4TH STAGE SDR 2010FA0000446Firewall · crackedCRACK AT STA 124, ENGINE FIREWALL, M/R TRANSMISSION OIL COOLER LINES AREA.SDR 2010F00067Tube · loosePILOT NOTED LOW POWER AND HIGH TOT. DURING CRUISE FLIGHT.SDR 2010FA0000445Firewall · crackedCRACK AT STA 124, ENGINE FIREWALL, M/R TRANSMISSION OIL COOLER LINES AREA.SDR CA100211005Adapter · cracked(CAN) ACFT WAS IN CRUISE AT 800 FT WHEN THE PILOT HEARD A HUMMING NOISE FOR ABOUT 2 SECONDS. AFTER THE 2 SECONDS THE ENGINE SHUTDOWN. PILOT AUTO ROTATED AND LANDED HELICOPTER. ENG HAD FLAMES COMING OUT OF THE EXHAUST STACKS UPON LANDING BUT QUICKLY DISSIPATEDSDR 2010FA0000174Blades · damagedPILOT EXPERIENCED COMPRESSOR STALL DURING FLIGHT WITH LOUD NOISE AND YAW OF ACFT. PILOT EXPERIENCED LOSS OF ENGINE POWER AND PROCEEDED TO LAND ACFT. UPON INSP MX FOUND 1 EA 1ST STAGE COMPRESSOR BLADE BROKEN OFF AT ROOT AND LAYING IN PLENUM CHAMBER IN FRONT OSDR 2010FA0000059Turbine Wheel · separatedDURING A TURBINE TEST (SLAVE ENGINE) THERE WAS AN UNCONTAINED FAILURE OF THE PT ROTOR ASSY (4TH STAGE WHEEL). THE WHEEL EXITED THE ENGINE AND CAUSED SUBSTANTIAL DAMAGE TO THE TEST FACILITY. 2 TEST MECHANICS RECEIVED MINOR INJURIES.SDR USX2010F00000Fcu · fluctuatesENG TORQUE BEGAN FLUCTUATING +- 15 PERCENT. CHANGED DOUBLE CHECK VALVE, GROUND RUN, STILL FLUCTUATING; CHANGED GOVERNOR, GROUND RUN, STILL FLUCTUATING; CHANGED BLEED VALVE, GROUND RUN, NO FLUCTUATIONS; PICKED UP ACFT TO HOVER AND FUEL CONTROL FAILED CAUSING SDR CA100111003Tube · chafed(CAN) DURING A PREFLIGHT CHECK, IT WAS NOTED BY THE PILOT THAT AN ABNORMAL SOUND WAS OCCURRING IN THE VERTICAL TUNNEL AREA DURING T/R PEDAL MOVEMENT. UPON INSPECTION OF THE AREA, IT WAS NOTED THAT THE T/R PEDAL PUSH-PULL TUBE (P/N 206-001-020-029) UPPER ATTACSDR CA091211003Turbine Wheel · broken(CAN) TURBINE CUSTOMER WORKSCOPE WAS "REPAIR FOR VIBRATION - .9 IPS AT 32,000RPM. AND CRACKED EXHAUST CLAMP & STACKS". AFTER DISMANTLE, IT WAS DISCOVERED THAT NR 3 WHEEL HAS A PIECE OF METAL BROKEN OFF ON T/E SIDE OF OUTER SHROUD BETWEEN WHEEL BLADES THAT COVESDR CA091016003Guide · broken(CAN) ANTI- ICE GUIDE ASSY FOUND BROKE UNDERNEATH "B" NUT. FOUND DURING COMPRESSOR CHANGE.SDR CA091028010Case · cracked(CAN) THE MAINTENANCE CREW WERE DOING A 600 HOUR INSPECTION AND THE AME LOOKED IN THE LH ARMPIT OF THE BURNER CAN AND FOUND IT TO BE CRACKED ON A HORIZONTAL PLANE BESIDE WELD. THE COMBUSTION CASE WAS WAS REPLACED WITH A SERVICEABLE PART. IT WAS NOTED THAT THE SDR CA091110001Combustion Liner · bent(CAN) - AFTER AN INSP OF THE ENG FOR EXCESSIVE TOT DURING STARTUP, AT WHICH TIME COMBUSTION CASE, COMBUSTION LINER, FUEL NOZZLE, & IGNITER WERE REMOVED AND REINSTALLED. ENGINE WOULD NOT START. THERE WAS NO SPARK AT IGNITER. AFTER TROUBLESHOOTING, IGNITER WASDR CA100128003Gear · broken(CAN) TORQUEMETER GEAR PURCHASED NEW IN THE US FOR USE IN A RENTAL GEARBOX MODULE. UPON RETURN TO SHOP AFTER LEASE WITH 35.4 HOURS, VISUAL INSP REVIELED THAT A LARGE SECTION OF GEAR HAD BROKEN OFF. SUBSEQUENT INSP AND FORENSIC ANALYSIS REVEALED A MFG DEFECT TH
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