Allison 250-C20R
Service difficulty reports · 111
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 = '250C20R' 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 = '250C20R' 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 CA060831004Engine · power loss(CAN) AIRCRAFT LOST POWER RESULTING IN A HARD LANDING. DATE OF OCCURRENCE, JUNE 26, 2006. ROTORCRAFT LOST ENGINE POWER AT APPROX 400 FEET AND AUTOROTATED. AIRCRAFT IS CONSIDERED A TOTAL WRITE-OFF. TSB CURRENTLY INVESTIGATION ROOT CAUSE OF THIS EVENT. (TC NRSDR CA060227002Stiffener · crackedAFTER REMOVAL OF AFT FUSELAGE FAIRING FOR REPAIR. VISUAL INSPECTION AND CLEANING OF AFT FUSELAGE A STIFFENER FOUND CRACKED. STIFFENER REPLACED NEW.SDR CA060131005Turbine Wheel · crackedTURBINE RECEIVED AT ETI FOR REPAIR. NR 3 TURBINE WHEEL INSPECTED ON TEARDOWN. NR 3 TURBINE WHEEL SENT TO NDT FOR FPI. CRACKS WERE FOUND ON RIM. LOG CARDS SHOW THAT NR 3 TURBINE WHEEL (S/N HX-84-131) HAS TTSN: 819.1 AND TCSN: 770. NR 3 TURBINE WHEEL LIFE ISDR CA051202002Tail Boom · crackedDURING THE CLEANING OF THE TAIL BOOM, A CRACK WAS FOUND AT BOOM STATION 45". THE CRACK ORIGINATED FROM A RIVET THE TOP LEFT SLIP (FOR THE CAMLOC FITTING). THE CRACK MEASURED 3.5" AND RUNS ON AN 80 DEGREES ANGLE.SDR CA050901002Bearing · corroded(CAN) DURING A 1500 HR FREEWHEEL INSP, THE AFT BEARING IN THE OUTER SHAFT WAS FOUND CORRODED ON THE INSIDE OF THE OUTER RACE. BEARING WAS REMOVED AND RUST WAS PRESENT ON THE OUTER RACE. BEARING HAD PREVIOUSLY OVERHAULED BY BII IN 1999BEARING WAS REMOVED FROMSDR CA060303018Volt Regulator · failedAT START UP NO CHARGE. REPLACED VOLTAGE REGULATOR.SDR CA050718012Throttle Cable · brokenON START UP AT THE BASE, THE N1 WENT DIRECTLY TO MAXIMUM RPM. THE PILOT ATTEMPTED TO SHUT THE ENGINE WITH THE THROTTLE CONTROL AND DID NOT GET ANY EFFECT ON THE ENGINE. THE PILOT CALLED AN AME THAT COULD SHUT THE ENGINE BY ACTIVATING THE GAS PRODUCER LINKAGESDR AU510002099Blade · delaminated(AUS) TAIL ROTOR BLADE DELAMINATED. AREA OF DELAMINATION APPROXIMATELY 38.1MM LONG BY 9.525MM WIDE (1.5IN BY 0.375IN). SEE ATTACHMENT FOR PHOTOGRAPHS. (OTHER CAUSE: VOID DEVELOPED FROM POOR PREP WHEN REPAIRED BY HTC ) (CASA 510002099)SDR CA060303017Igniter · failedNO IGNITION. REPLACED IGNITER.SDR CA050405009Bearing · failed(CAN) AFT BEARING FAILURE, REMOVED STARTER GENERATOR. INSTALLED SERVICEABLE STARTER GENERATOR.SDR CA050214001Valve · obstructed(CAN) FLOAT BAGS WOULD NOT INFLATE DURING 3 YEAR OPERATIONAL CHECK, THE VALVE ASSY WAS ASSEMBLED WITH THE SHEARED PORTION OF THE SHEAR HEAD STILL IN THE VALVE OBSTRUCTING THE AIR FLOW TO THE BAGS.SDR CA041124009Disc Pack · cracked(CAN) DISC PACK, 1 DISC CRACKED.SDR CA041123010Bypass Switch · corroded(CAN) FILTER LIGHT CAME ON UPON LANDING. REMOVED FILTER AND INSPECTED. NO CONTAMINATION FOUND AND TEST LIGHT CIRCUIT. A LIGHT CAME ON AGAIN AND UPON INVESTIGATION, IT WAS FOUND THAT THE SWITCH WAS CORRODED. A NEW FILTER ASSY. WAS INSTALLED AND TESTED. IT SDR CA040921007Bleed Valve · failed(CAN) ENGINE FLAMED OUT TWICE DURING TEST FLIGHT FOR BLEED VALVE CHANGE AND RELIGHT ON BOTH OCCATIONS BY AUTO RELIGHT.SDR CA040723004Bushing · loose(CAN) ALL 3 BUSHINGS FOUND LOOSE ON D.I. STARFLEX WAS REPLACED.SDR CA040806005Bushing · loose(CAN) ALL 3 BUSHINGS FOUND LOOSE ON D.I. STARFLEX WAS REPLACED.SDR CA040428007Turbine · failed(CAN) THIS MORNING THE PILOT WAS IN CRUISE WHEN A LOUD BANG OCCURRED AND THE TOT INCREASED. WITH NO ENGINE, THE PILOT AUTOROTATED TO A CLEAR SPOT TO THE GROUND. NO DAMAGE TO AIRCRAFT. THE ENGINE HAD FAILED. A VISUAL OF THE TURBINE SECTION SHOWS SUBSTANTIASDR CA040427015Mount · cracked(CAN) CLIP AND FITTING AT RT ENGINE MOUNT LOCATION HAS CRACK DAMAGE. REMOVED CLIP P/N 206-032-303-014 AND FITTING P/N 206-031-337-004 AND REPLACED WITH NEW CLIP P/N 206-032-303-230S AND NEW FITTING P/N 206-033-670-104S. RT ENGINE PAN UPPER LONGERON FOUND TO HASDR CA040419001Compressor · damaged(CAN) ENGINE FAIL AT APPROX 150 FT. AGL ON CLIMB OUT, PILOT HEARD LOUD BANG ENGINE QUIT. PRELIMINARY INSPECTION SHOWS COMPLETE COMPRESSOR FAILURE.SDR AUS20040050Shield · cracked(AUS) FIRST STAGE TURBINE NOZZLE SHIELD CRACKED AROUND 90 PERCENT OF RADIUS. ONE PIECE OF SHIELD ABOUT THE SIZE OF A 50 CENT PIECE DISLODGED AND WAS FOUND SITTING IN THE BOTTOM OF THE COMBUSTION LINER.SDR CA040206002Sight Glass · cracked(CAN) SIGHT GLASS ON FORWARD SIDE OF RANGE EXTENDER WAS FOUND TO BE THE CAUSE OF A SLOW FUEL LEAK. WHEN THE AIRCRAFT WAS FULL OF FUEL AND KEPT IN THE HANGAR OVER NIGHT A SMALL POOL OF FUEL WAS NOTICED ON THE FLOOR. A CRACK RUNNING ACROSS FROM TWO SCREWS WAS SDR CA031120010Fuel Control · failed(CAN) PILOT RETURNING TO BASE NOTICED RAPID TORQUE GAUGE FLUCTUATION BETWEEN 5 PERCENT TO 10 PERCENT, OCCURRING MOSTLY AT AROUND 85 PERCENT TORQUE. LATER PILOT AND AME CONDUCTING TEST FLIGHT TO CONFIRM PROBLEM NOTICED SLIGHT ENGINE SURGING NOTICEABLE ONLY BY SDR CA031015019Turbine · failed(CAN) AFTER ENGINE WAS SHUTDOWN A RUBBING NOISE WAS HARD COMING FROM THE N1 TURBINE WHEELS. IT WAS CONFIRMED BY MOTORING THE ENGINE AFTER SHUTDOWN. TURBINE WAS REPLACED AND SENT TO AN APPROVED REPAIR FACILITY.SDR CA031001008Bearing · failed(CAN) DURING FLIGHT PILOT REPORTED AN ENGINE CHIP WARNING LIGHT. DURING SERVICEABILITY CHECK 2ND CHIP LIGHT REPORTED. THE ENGINE WAS DISASSEMBLED. THE TURBINE SECTION OF THE ENGINE, IN THE NR 5 BEARING AREA THE SNAP RING AND SPACER WERE UNSEATED AND RESTING OSDR CA031001007Tachometer · worn(CAN) DURING GROUND RUN PILOT EXPERIENCED LOSS OF HYDRAULIC POWER TO THE FLIGHT CONTROLS. THE MAIN ROTOR TACHOMETER WAS REMOVED. THE INTERNAL SPLINES OF THE TACH WERE WORN ALLOWING THE HYD PUMP SPLINES NOT TO ENGAGE.SDR CA030826004Plate · loose(CAN) LOOSE CONNECTOR MOUNTING PLATE. INSTALLED SERVICEABLE UNIT TSO 0:0.SDR CA030729016Control Cable · failed(CAN) AT PREFLT, PILOT REPORTED A 'BINDING' AT EXTREME RT PEDAL. MAINT DISCONNECTED SECTIONS OF SYS & COULDN`T REPEAT. DAYS LATER PILOT REPORTED SIMILAR BINDING PLUS A 'BANG' BEFORE MOVING SMOOTHLY AGAIN. DURING INVEST, ENGINEERING FOUND BINDING WHERE 2 CABLESDR XMSR778KBlade · crackedCRACK FROM TRAILING EDGE TO SPAR BOTH BOTTOM AND TOP OF BLADE. CRACK IS APPROX 19 INCHES OUTBOARD OF REAR BLADE PIN HOLE. CRACK 4.6250 INCHES LONG AND T (ED) OF 1.5000 EACH WAY ON THE BOTTOM AND ON TOP SIDE T 2 INCHES TOWARD OUTBOARD AND .5000 INCH TOWARD INSDR CA030407010Frame · cracked(CAN) DURING A 6000 HR. 2T AIRFRAME INSPECTION, TAILBOOM TAILCONE AREA WAS INSPECTED AS AN REQUIREMENT OF EUROCOPTER S/B 55.00.09 'CHECK OF FIN ATTACHMENT FRAME. A CRACK WAS FOUND EMANATING FROM AN ANCHOR NUT ATTACHMENT RIVET IN TWO DIRECTIONS. THIS CRACK HAD SDR CA030218004Spring · broken(CAN) SPRING BROKE, TURNED SIDEWAYS AND CHAFED SPHERICAL COUPLING AND PLATE.SDR CA021104008Disc Pack · cracked(CAN) DURING ROUTINE INSPECTION, BOLTS ON THE MOST FORWARD DISC PACK WAS FOUND TO BE LOOSE. THE BOLTS WERE TORQUE SEALED AS PER MANUFACTURERS INSTRUCTIONS. THE LOOSE BOLTS WERE WORN, THE HOLES IN THE DISC PACK WERE ELONGATED AND ONE PLATE OF THE DISC PACK WASSDR AUS20021120Fitting · faulty(AUS) FUEL SYSTEM UNIONS FAULTY AND LEAKING. AIRCRAFT IS REGISTERED IN USA.SDR CA020815001Drive Shaft · sheared(CAN) IN CRUISE FLT, NR 2 ENGINE TORQUE DROPPED BELOW ENGINE TRIM ADJUSTMENT WITH POWER FLUXS. NR 2 ENGINE THROTTLED BACK FROM FLT TO IDLE. RETURNED TO GATE AS A PRECAUTION. ENGINE DECELED FROM POINT TO ACTIVATE REIGNITION SYS, & CONTINUED TO SPOOL DOWN TO ASDR AUS20020748Strut · cracked(AUS) LT MAIN LANDING GEAR STRUT CRACKED FROM RIVET HOLE. CRACK LENGTH 9.525MM (0.375IN).SDR CA020612006Spur Adapter · spalled(CAN) ENGINE CHIP LIGHT FOUND METAL PARTICLES ON BOTH CHIP PLUGS. 2 1/2 BEARING AND INNER RACE ON THE SPUR ADAPTER FOUND SPALLED.SDR AUS20020681Liner · faulty(AUS) ENGINE EXHIBITED LOW POWER FOLLOWING REPLACEMENT OF COMBUSTIONLINER. SUSPECT BOTTOM LOUVRES INCORRECTLY SET. THE LINER FITTED WAS ZERO HOURS TIME SINCE OVERHAUL.SDR AUS20020331Bleed Valve · faulty(AUS) COMPRESSOR BLEED VALVE SUSPECT STICKING.SDR CA020403008Stiffener · cracked(CAN) CRACKED VERTICAL STIFFENER. CUTOUT IN HORIZONTAL STIFFENER WAS TOO SMALL WHICH PUT PRESSURE ON VERTICAL STIFFENER CAUSING IT TO CRACK.SDR 2003FA0000325Control Unit · intermittentAUTO-RELIGHT SYSTEM ACTIVATES INTERMEDIATELY DURING NORMAL ENGINE OPERATION.SDR CA011211014Strut · cracked(CAN) CRACK FOUND ON UPPER PART OF STRUT AROUND THE BRACE ATTACHMENT HOLE.SDR CA011211015Strut · cracked(CAN) CRACK FOUND ON UPPER PART OF STRUT AROUND THE BRACE ATTACHMENT HOLE.SDR CA011211017Strut · cracked(CAN) CRACK FOUND ON UPPER PART OF STRUT AROUND THE BRACE ATTACHMENT HOLE.SDR CA011211016Strut · cracked(CAN) CRACK FOUND ON UPPER PART OF STRUT AROUND THE BRACE ATTACHMENT HOLE.SDR CA011105002Tube · corroded(CAN) DURING TRANSMISSION 1500 HOUR INSPECTION CORROSION AND PITTING FOUND ON THE FLARE OF THE TUBE ASSEMBLY.SDR CA011003009Leg Assy · corroded(CAN) WHILE CARRYING OUT A 100 HOUR INSPECTION THE ENGINEER NOTICED A HILOCK COLLAR IN THE ENGINE BAY. UPON INVESTIGATION IT WAS NOTED THAT THE HI-LOCK PIN HAD CORRODED THROUGH & THE COLLAR FELL OFF. LEG ASSEMBLY REPLACED WITH NEW.SDR CA010912003Fitting · cracked(CAN) ROUTINE INSPECTION UPPER LEFT TAIL ATTACH FITTING FOUND CRACKED.REPLACED AS PER BELL STRUCTURAL REPAIR MANUAL 6-214, BUT NUMEROUS REPORTS OF CRACKS IN THIS LH UPPER FITTING AREA OF TAILBOOM/FUSELAGE INTERFACE.SDR AUS20010762Oil System · blocked(AUS) NR 6 AND NR 7 BEARING OIL SCAVENGE PORT PARTIALLY BLOCKED BY CARBON DEPOSITS. OIL TYPE HAD BEEN CHANGED FROM MOBIL 254 TO MOBIL 291.SDR CA010724031Bulkhead · cracked(CAN) THE TAIL BOOM WAS REMOVED FOR 1200 HOUR INSPECTION. CRACKS WERE FOUND AROUND THE TOP LEFT ATTACH BOLT HOLE SHIM PART 206-032-400-117, WHEN THE BULK HEAD WAS REMOVED CRACKS WERE FOUND ALONG THE TOP EDGE OF THE MATING SURFACE OF THE BULK HEAD AND BOLT ATTSDR CA010724032Fitting · corroded(CAN) THE FITTING WAS FOUND CORRODED ON 1200 HOUR INSPECTION AND NEW PART 206-033-173-001 WAS INSTALLED. THE ORIGINAL PART IS MANUFACTURED FROM MAGNESIUM WHERE THE NEW PART IS ALUMINUM SO AFTER 13109 OF FLYING ON A AIRCRAFT MANUFACTURED IN 1978 THIS WOULD NOTSDR CA010727015Bulkhead · cracked(CAN) THE TAIL BOOM WAS REMOVED FOR 1200 HOUR INSPECTION. CRACKS WERE FOUND AROUND THE TOP LEFT ATTACH BOLT HOLE SHIM PART # 206-032-400-117. WHEN THE BULKHEAD WAS REMOVED, CRACKS WERE FOUND ALONG THE TOP EDGE OF THE MATING SURFACE OF THE BULKHEAD AND BOLT ATT
Back to Allison 250-C20R