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 CA010423009Gear · broken(CAN) MAIN ROTOR TRANSMISSION REMOVED FOR MAKING METAL. UPON DISASSEMBLY IT WAS DISCOVERED THAT ON INPUT GEAR TOOTH HAD BROKEN OFF. THE TOOTH WAS FOUND IN THE SCAVENGE PUMP INTAKE.REMNANTS OF THE TOOTH WERE FOUND IN THE SCAVANGE SPRAY TUBE.SDR SW15200110390Mast · flakingCOATING FLAKING OFF INNER DIAMETER OF MAIN ROTOR STATIC MAST. COATING CHIPS FALLING INTO MAIN ROTOR TRANSMISSION. CAUSE OF FLAKING UNKNOWN. NO FACTORY REPAIR AUTHORIZED IN THE HMI. FACTORY REPS HAVE NOT YET AUTHORIZED A REPAIR. EFFECT ON MAST AND TRANSMISSDR SW15200110389Mast · flakingCOATING FLAKING OFF INNER DIAMETER OF MAIN ROTOR STATIC MAST. COATING CHIPS FALLING INTO MAIN ROTOR TRANSMISSION. CAUSE OF FLAKING, UNKNOWN. NO FACTORY REPAIR AUTHORIZED IN THE MHI. FACTORY REPS HAVE NOT YET AUTHORIZED A REPAIR. EFFECT ON MAST AND TRANSMISDR AU010183Mast · damaged(AUS) MAIN ROTOR MAST SUBJECTED TO TORSIONAL DAMAGE DURING N2 LOCKUP ON START.SDR AC2A072834Governor · debondedPILOT REPORTED N2 OVERSPEED UNCONTROLLABLE WITH RPM TRIM MOTOR. NR 1 ENGINE RETURNED TO FLIGHT IDLE. FUEL JETTISONED, AND PILOT PERFORMED RUN-ON LANDING. REMOVED GOVERNOR AND FOUND DRIVE SPLINE DISENGAGED FROM GOVERNOR SHAFT. GOVERNOR REPLACEMENT FIXED PROBLSDR EHA2001F00002Gearbox · failedNR 1 ENGINE TORQUE REMAINED AT 60 PER CENT WHEN ENGINE TRANSITIONED FROM HIGH TORQUE TO GROUND IDLE. OPERATION ABOVE 60 PER CENT APPEARED NORMAL. CAUSE DETERMINED TO BE FAILURE OF THE TORQUE METER TO BLEED PRESSURE DURING ENGINE TORQUE TRANSITION. ENGINE GESDR 20010328CW008Engine · making metalENGINE CHIP ILLUMINATED ON CAUTION PANEL.SDR 20010314CW001Fire Detector · shortedDURING PRESTART CHECK. AFT PROBE SHORTED TO ELBOW ON ENGINE AIR SYSTEM.SDR AC2A072782Spline Adapter · corrodedCOMPRESSOR WAS REMOVED DUE TO F.O.D. SPLINE ADAPTER WAS REMOVED IN ORDER TO DISASSEMBLE COMPRESSOR ROTOR FOR REPAIR. SPLINE ADAPTER WAS FOUND TO HAVE A RING OF CORROSION AROUND OUTSIDE CIRCUMFRENCE OF ADAPTER .650 INCH FROM REAR END OF ADAPTER. CORROSION IS ATSDR AU010139Gearbox · making metal(AUS) ENGINE GEARBOX OUT OF LIMITS. CHIP DETECTORS CONTAMINATED WITHMETAL PARTICLES.SDR CA010209004Bell Assy · unappoved part(CAN) STARTER GEN RECEIVED FOR OVERHAUL. FOUND THE ADE (COMM END) END BELL ASSEMBLY TO BE 3, WHICH ACCORDING TO THE OEM IS AN OLD, OBSOLETED PART THAT WAS APPLICABLE ONLY TO THE 23032-005 STARTER-GENERATOR, WHICH IS ITSELF OBSOLETE, UNSUPPORTED AND NOT LISTED SDR CA010307013Cover · grooved(CAN)WHEN REINSTALLING A MAIN DRIVESHAFT AFTER A INPUT TRANSMISSION SEAL REPLACEMENT, FOUND THAT THE TRANSMISSION END OF THE SHAFT COULD NOT MOVE. OPENED THE COUPLING END FOUND THAT SPRINGS WAS NOT INSTALLED PROPERLY. THE COVER WAS GROOVED. INSPECTED THE INNSDR RX8R2000001Blade · delaminatedHELICOPTER TECHNOLOGY COMPANY MAIN ROTOR BLADES PN 500P2100-101 WERE INSTALLED NEW 8/14/00 TTAC 5096.0. BLADES WERE INSPECTED IAW A.D.2000-24-51 (MSB 2100-02) ON 11/11/00, TTAC 5149.7 AND NO DEFECTS WERE NOTED. BLADES WERE INSPECTED IAW A.D. 2000-25-52 (MSB SDR CA010110006Bolt · misinstalled(CAN) DURING COUPLING REPLACEMENT (BENDIX TO KAMATIC), IT WAS NOTED THAT THE TAIL ROTOR DRIVESHAFT TO COUPLING BOLTS WERE TOO LONG AND IF ALLOWED TO REMAIN IN SERVICE WOULD CONTACT THE COUPLING WEB AND SET UP STRESS RISES.THE BOLTS CALLED OUT IN THE IPC ARE THSDR CA010110007Shim · split(CAN) DURING TAIL ROTOR GEARBOX REPLACEMENT, IT WAS NOTED THAT THE TORQUE WAS LOST ON THE KAMATIC COUPLING BOLT. FURTHER INVESTIGATION REVEALED THE SHIMS BETWEEN COUPLING AND TAIL ROTOR GEARBOX WERE FOUND SPLIT DUE TO COUPLING BOLT TORQUE. MAINTENANCE MANUAL ISDR CA010103010B-Nut · loose(CAN) ENGINE HUNG START AT 38 PERCENT N1 GOVERNOR PC AIR TUBE FITTING "B" NUT FOUND LOOSE.SDR CA001201020Pin · broken(CAN) DURING AN APPROACH FOR LANDING TO REFUEL, THE PILOT AND ENGINEER ON BOARD EXPERIENCED A NOTICEABLE VIBRATION. UPON LANDING THE ENGINEER FOUND THAT A M/R BLADE PIN WAS SITTING A BIT HIGHER THAN THE OTHERS. WHEN HE UNLATCHED TO PIN, THE THREADED PORTION OSDR AU001078Case · cracked(AUS) MAIN ROTOR TRANSMISSION LOWER CASE CONTAINED NUMEROUS CRACKS AND WAS LEAKING IN AREA BELOW MOUNT FOR PIN ASSEMBLY PN 206-031-633-101. (X)SDR CA010108021Blade · failed(CAN) M/R BLADE P/N 500P2100-101 S/N A204 WS INSPECTED I.A.W. THE MANUFACTURERS RECOMMENDATIONS AND HELICOPTER TECHNOLOGY CORP SB 2100-2 INSPECTION OF M/R BLADE FOR DEBONDING. THE M/R BLADE WAS INSTALLED ON THE A/C AND A SERIES OF FLIGHTS WERE CONDUCTED FOR TRSDR CA001106006Blade · missing(CAN) N1 AND N2 SYSTEMS ABLE TO ROTATE PRIOR TO DISMANTLING, TURBINE FULLY DISMANTLED. NO EVIDENCE OF FOD UPSTREAM OF 2ND STAGE TURBINE WHEEL. HEAVY D.O.D. DOWNSTREAM OF 2ND WHEEL. 2ND TURBINE WHEEL MISSING ONE TURBINE BLADE. QTY SIX BLADES APPROX. 180 INCSDR CA001106007Mount · failed(CAN) CRACK RADIATING ACROSS REAR PORT SIDE ATTACHMENT HOLE FOR THE TAIL ROTOR GEARBOX STUDS. (X)SDR CA001110045Bolt · failed(CAN) DURING CRUISE FLIGHT, PILOT WAS ONLY ABLE TO ACHIEVE 98 PERCENT N2 ON NR 1 ENGINE. UPON LANDING AT THE MAINTENANCE FACILITY, AN INSPECTION FOUND THE NR 1 ENGINE GOVERNOR CABLE WHERE IT ATTACHES TO THE COLLECTIVE FORK HAD BECOME DISENGAGED. REF: MBB PSDR AU000976Floatation · faulty(AUS) EMERGENCY FLOATS INFLATED OVERNIGHT WITH NO REASON OR CAUSE BEING FOUND. INVESTIGATION OF THE FLOAT SYSTEM FOUND THAT THE SQUIB HAD BEEN FIRED ELECTRICALLY AND THAT THE SYSTEM HAD OPERATED NORMALLY. (X)SDR CA001027014Blade · broken(CAN) PILOT REPORTED A STRANGE VIBRATION IN THE HELICOPTER. UPON INVESTIGATION ENGINEERING FOUND THE UPPER LEADING EDGE LUG OF THE BLADE CRACKED AND BROKE LOOSE FROM THE BLADE AND ONE BLADE RETENTION PIN BENT. MAIN ROTOR BLADE AND BLADE RETENTION PINS WERE REPSDR AU001039Mast · cracked(AUS) MAIN ROTOR MAST CRACKED AT TOP BEARING JOURNAL. FOUND DURING MAGNETIC PARTICLE INSPECTION. (X)SDR CA001013034Bearing · loose(CAN) STARTER-GENERATOR WAS REMOVED TO INVESTIGATE AN ENGINE VIBRATION. AME FOUND THE DRIVE END BEARING WAS VERY LOOSE, WITH RADIAL PLAY. SENT UNIT TO AMO. AMO DISASSEMBLED & FOUND D.E. BALL BEARING HAD CONSIDERABLE PLAY IN BOTH RADIAL (.010) X AXIAL (.025) DISDR CA001205014Governor · failed(CAN) GOVERNOR ARM ALMOST SEIZED (SHAFT TO BODY). UNIT REQUIRED EXTREME FORCE TO MOVE, WAS ALSO CAUSING HEAVY COLLECTIVE.SDR CA001016002Starter · failed(CAN) PILOT NOTICED SPRAY OUT OF ENGINE BAY AREA AND WHEN HE CHECKED INSTRUMENT PANEL, TORQUE GAUGE WAS FLUCTUATING AND OIL PRESSURE WAS DROPPING BELOW 30 PSI. AIRCRAFT WAS LANDED AND LARGE AMOUNT OF OIL NOTICED COMING OUT OF STARTER AREA. STARTER WAS REMOVESDR CA001205012Stud · failed(CAN) DURING INSTALLATION THERE WAS NO TORQUE OF THE FORWARD HOUSING NUTS, IT WAS NOTED THAT THE STUD WAS PULLING FROM THE HOUSING. THE UNIT WAS REMOVED AND SENT BACK TO ACRO FOR REPAIR.SDR CA000925030Pitch Link · cracked(CAN) CRACK DISCOVERED DURING DAILY INSPECTION. (X)SDR AU000840Hose · failed(AUS) TRANSMISSION OIL HOSE FAILED. (X)SDR CA001005019Support Bracket · broken(CAN) DURING A DAILY INSPECTION CHECK, TWO BREAKS WERE FOUND IN TH E UPPER MAIN ATTACHMENT POINT FOR THE VERTICAL FIN REAR SUPPORT. THE BROKEN PIECE IS APPROXIMATELY 1 INCH BY 1 INCH IN SIZE. (X)SDR 20001019SH004Engine · making metalENGINE PRODUCED CHIP LIGHTS. REMOVED CHIP DETECTOR, CLEANED, RE-INSTALLED. RAN ENGINE 30 MINUTES AND FOUND MORE CHIPS. REMOVED ENGINE AND SENT FOR REPAIR. (X)SDR CA000906004Valve · worn(CAN) THE HELICOPTER EXHIBITED OCCASIONAL OSCILLATIONSIN TORQUE, N1 & TOT. AFTER EXTENSIVE TROUBLESHOOTING AN OVERHAULED DOUBLE CHECK VALVE WAS INSTALLED AND PROBLEM WAS RECTIFIED.VALVE ASSEMBLY SENT TO STANDARD AERO LTD IN WINNIPEG AS CORE EXCHANGE FOR OVERHASDR CA020103016Coupling · cracked(CAN) CIRCUMFERENCE CRACKS ON PILOT O.D AREA. DISCREPANCY FOUND DURING COMPRESSOR REPAIR. DUE TO CUSTOMER REPORT METAL CONTAMINATION.SDR CA000905014Pump · failed(CAN) WHILE IN 4 FT HOVER, AN ENGINE FLAMEOUT OCCURRED. UPON INVESTIGATION IT WAS DISCOVER THE THE ENGINE DRIVEN FUEL PUMP TO BE IN BY PASS. FUEL CONTROL AND FUEL PUMP REPLACED.SDR CA000905013Fuel Control · failed(CAN) WHILE IN 4 FT HOVER THE ENGINE FLAMEOUT OCCURRED. UPON INVESTIGATION WE FOUND THE ENGINE DRIVEN FUEL FILTER TO BE IN BY-PASS. FUEL CONTROL & FUEL PUMP REPLACED.SDR 20000912SH007Wire · brokenIN CRUISE FLIGHT, NR 1 ENGINE FIRE LIGHT ILLUMINATED. FOUND AND REPAIRED BROKEN WIRE. (X)SDR CA001205008Governor · failed(CAN) SPIKES ON OR ABOVE 103 PERCENT N2 WHEN THE TORQUE IS ABOUT 73 PERCENT. QUADRANT READS 93 ON POINTER TO ATTAIN 103 PERCENT. SO ENGINE DOES NOT GENERAGE ENOUGH POWER AT THE STANDARD RIGGING LOCATION OF 81. UNIT REPLACED.SDR CA000801012Governor · malfunctioned(CAN) WHILE MAKING POWER CHANGES IN HOVER, THE ROTOR RPM DROPS AND OVERSPEEDS. 152.0 HOURS SINCE REPAIR.SDR CA000802017Tip Cap · cracked(CAN) DURING FLIGHT A VIBRATION WAS FELT IN THE FLOOR AND WENT AWAY AS THE AIRCRAFT WAS RETURNING TO THE LANDING SITE. THE ENGINEER INSPECTED THE AIRCRAFT AND FOUND THE TIP PLATE OF THE R/H SIDE OF THE HORIZONTAL STABILIZER WAS MISSING.SDR CA000811002Hose · corroded(CAN) DURING ROUTINE MAINTENANCE, THE SHEATHING WAS PULLED BACK FROM THE FUEL HOSE ASSEMBLY AND THE ALUMINUM ENDS WERE SEVERELY CORRODED. FURTHER INVESTIGATION REVEALED BOTH ENDS HAD SEVERE CORROSION. THE HOSE IS A FUEL HOSE WHICH RUNS FROM THE FORWARD ENGISDR CA000811003Mast · failed(CAN) EVENT: DURING PILOT TRAINING OFF-LEVEL LANDING BEING CONDUCTED; A/C LANDED ON SLOPE WITH RT SKID LOW. PILOTS WERE CHECKING THEIR RESPECTIVE SIDES OF A/C AND A/C MOVED ON SLOPE. PILOT APPLIED CYCLIC INPUT WHEN THE A/C SLIPPED. WHEN A/C LIFTED INTO HOSDR AU000572Pipe · loose(AUS) PR FUEL PIPE BETWEEN THE FUEL CONTROL UNIT AND THE POWER TURBINEGOVERNOR HAD A LOOSE B'''' NUT. (X)SDR CA001013022Actuator · seized(CAN) THE LINEAR ACTUATOR IS SEIZED IN THE MOST FORWARD POSITION. WHEN THE UNIT IS ACTUATED THE MOTOR RUNS AND THEN STOPS RIGHT AWAY.SDR AU000523Bolt · wrong part(AUS) MAIN ROTOR HUB LATCH BOLTS HAD UNKNOWN HISTORY AND WERE REPLACED. THE LATCH BOLTS WERE SERIAL NUMBERED FOR USE ON BELL 206L TYPE AIRCRAFT AND HAVE A 1200 HOUR LIFE. (X)SDR 20000711SH001Transmission · making metalMAIN ROTOR CHIP LIGHT CAME ON IN-FLIGHT AND WOULD NOT PULSE OFF. AFTER REMOVAL OF MAIN ROTOR CHIP DETECTOR AND MAIN ROTOR OIL FILTER, FOUND STEEL SLIVERS AND CHIPS, BRONZE IN THE FILTER, AND OIL DRAINED. TRANSMISSION REMOVED AND SHIPPED TO EUROCOPTER CANADA SDR CA000706036Washer · broken(CAN) DEFECT WAS FOUND DURING PREFLIGHT.SDR AU000425Main Rotor · damaged(AUS) MAIN ROTOR SPLIT CONE HALF INSTALLED UPSIDE DOWN. MAIN ROTOR TRUNNION CHAMFER DAMAGED BY SHARP EDGE OF CONE. MAST SPLIT CONE SEAT FRETTING.SDR AU000482Trunnion · damaged(AUS) MAIN ROTOR TRUNNION FAULTY. MAST AND SPLIT CONES ALSO REPLACED.
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