Allison 250-C20B

Service difficulty reports · 1,981

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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.

SDR CA110215010Fcu · malfunctionedOCCASIONAL DELAYED LIGHT OFF AFTER THROTTLE IS CRACKED OPEN TO DETENT ON GROUND RUN. REPLACED FCU.Feb 12, 2011 · Bell 206B · Fuel Control/Turbine EnginesSDR 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 WAJan 25, 2011 · Bolkms BO105S · Aircraft Fuel Filter/StrainerSDR 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 FUJan 25, 2011 · Bolkms BO105S · Aircraft Fuel Filter/StrainerSDR 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 Jan 21, 2011 · Bell 206B · Turbine SectionSDR 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 Jan 5, 2011 · Hughes 369D · Engine Exhaust SystemSDR 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 THEDec 28, 2010 · N842LA · Hughes 369E · Main Rotor GearboxSDR 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 Dec 28, 2010 · N842LA · Hughes 369E · Main Rotor GearboxSDR 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.Nov 15, 2010 · Bell 206B · Altimeter, Barometric/EncoderSDR CA101122029Fuel Nozzle · malfunctioned(CAN) AIRCRAFT EXPERIENCING START DELAY FROM OPENING THROTTLE TO ENGINE LIGHT OFF. FUEL NOZZLE REPLACED. AIRCRAFT NOW HAS NORMAL STARTS.Nov 5, 2010 · Bell 206B · Fuel Injector NozzleSDR 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.Oct 27, 2010 · N842LA · Hughes 369E · Turbine SectionSDR 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.Oct 5, 2010 · N454JH · Hughes 369E · Engine Indicating SystemSDR 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.Oct 5, 2010 · N454JH · Hughes 369E · Turbine Engine System WiringSDR CA101115010Servo · leaking(CAN) HYDRAULIC SERVO PN: 206-076-031-015 FOUND LEAKING FROM VALVE ASSEMBLY DURING 100 HOUR INSPECTION. HYDRAULIC SERVO REPLACED.Oct 3, 2010 · Bell 206B · Rotorcraft Servo SystemSDR 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 Sep 29, 2010 · Bell 206B3 · Engine Fuel and ControlSDR 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 Sep 24, 2010 · N9233F · Hughes 369HS · Ice/Rain Protection SystemSDR 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 Sep 24, 2010 · Bell 206B · Turbine Engine Compressor SectionSDR 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 GSep 16, 2010 · Hughes 369D · Main Landing Gear Strut/Axle/TruckSDR 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 WERSep 9, 2010 · Bell 206B3 · Electrical Power System WiringSDR 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.Sep 5, 2010 · N842LA · Hughes 369E · Engine (Turbine/Turboprop)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.Sep 2, 2010 · Turbine Engine Compressor SectionSDR 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 LSep 1, 2010 · N765KV · Hughes 369E · Main Rotor GearboxSDR 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 LANAug 24, 2010 · Hiller UH12E · Main Rotor HeadSDR 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. TAug 8, 2010 · N50AP · Hughes 369D · Wheel/Ski/FloatSDR 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.Jul 26, 2010 · Turbine Engine Accessory DriveSDR 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 Jul 26, 2010 · N9460T · Hughes 369E · Turbine SectionSDR 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 ASSEMBJul 15, 2010 · N911RJ · Bolkms BO105S · Turbine Engine Compressor SectionSDR 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 COWLIJun 21, 2010 · N911EB · Bolkms BO105S · Engine Collector/Tailpipe/NozzleSDR 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 CONSIDEJun 18, 2010 · Bolkms BO105S · Tail Rotor HeadSDR 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 PJun 17, 2010 · N454JH · Hughes 369E · Engine (Turbine/Turboprop)SDR 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 HONEYCOMJun 3, 2010 · Bell 206B · Fuselage Floor PanelSDR 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 METALMay 29, 2010 · N842LA · Hughes 369E · Engine Indicating SystemSDR 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.May 24, 2010 · N842LA · Doug MD500E · Engine (Turbine/Turboprop)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.May 17, 2010 · Hughes 369D · Fuselage Main, Longeron/StringerSDR 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.May 17, 2010 · Hughes 369D · Main Rotor BladesSDR 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 WASMay 14, 2010 · N206PA · Bell 206B · Main Rotor GearboxSDR 2010FA0000447Firewall · crackedCRACK AT STA 124, ENGINE FIREWALL, M/R TRANSMISSION OIL COOLER LINES AREA.May 5, 2010 · N5279F · Hughes 369E · Fuselage Main, BulkheadSDR 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 May 5, 2010 · N9233F · Hughes 369HS · Ice/Rain Protection SystemSDR 2010FA0000446Firewall · crackedCRACK AT STA 124, ENGINE FIREWALL, M/R TRANSMISSION OIL COOLER LINES AREA.Apr 8, 2010 · N5278F · Hughes 369E · Fuselage Main, BulkheadSDR 2010F00067Tube · loosePILOT NOTED LOW POWER AND HIGH TOT. DURING CRUISE FLIGHT.Mar 4, 2010 · N500PH · Hughes 369E · Compressor Bleed ValveSDR 2010FA0000445Firewall · crackedCRACK AT STA 124, ENGINE FIREWALL, M/R TRANSMISSION OIL COOLER LINES AREA.Feb 16, 2010 · N1576F · Hughes 369E · Fuselage Main, BulkheadSDR 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 DISSIPATEDFeb 10, 2010 · Turbine Engine Compressor SectionSDR 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 OFeb 6, 2010 · N742LA · Doug MD500E · Turbine Engine Compressor SectionSDR 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.Jan 14, 2010 · Turbine SectionSDR 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 Dec 31, 2009 · N97TV · Bell 206B3 · Fuel Control/Turbine EnginesSDR 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 ATTACDec 21, 2009 · Bell 206B · Engine Oil System (Airframe Furnished)SDR 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 COVEDec 11, 2009 · Turbine SectionSDR CA091016003Guide · broken(CAN) ANTI- ICE GUIDE ASSY FOUND BROKE UNDERNEATH "B" NUT. FOUND DURING COMPRESSOR CHANGE.Oct 15, 2009 · Bell 206B · Engine Anti-Icing SystemSDR 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 Oct 5, 2009 · Bell 206B · Turbine Engine Combustion SectionSDR 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 WAOct 5, 2009 · Bell 206B · Turbine Engine Combustion SectionSDR 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 THSep 29, 2009 · Turbine Engine Reduction Gear
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