Allison 250-C20
Service difficulty reports · 945
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 = '250C20' 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 = '250C20' 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 KBMA88793Bearing · wornTAIL ROTOR OIL COOLER HANGER BEARING, WORN, ROUGH, AND EXCESSIVE PLAY. INSTALLED NEW BEARINGS.SDR CA011002002Piston · clogged(CAN) TORQUE INDICATOR ON THE GROUND READ 70 PERCENT TORQUE THEN CLIMBED TO 90 PERCENT TORQUE WITHOUT ADVANCING THE THROTTLE OR INCREASING THE POWER. TORQUE INDICATOR REPLACED, DEFECT DID NOT GO AWAY. REPLACED THE ENGINE GEARBOX. IT WAS NOTED THAT THE BLEED ORSDR CA011011009Pump · failed(CAN) PUMP NOT WORKING MOTOR UNSERVICEABLE. REPLACED PUMP ASSEMBLY.SDR CA011002003Bearing · failed(CAN) PILOT REPORTED A CHIP LIGHT & A LOUD GRINDING NOISE COMING FROM THE ENGINE REGION. THE PILOT MADE A PRECAUTIONARY LANDING TO A LANDING SIGHT. THE CHIP PLUGS WERE REMOVED & FOUND LARGE AMOUNT OF FLAKES. ON THE INVESTIGATION FOUND THE TWO AND A HALF BEARINSDR CA011119001Shaft · grooved(CAN) ONLY APPLIES TO A/C EQUIPPED WITH CASEY HEATER & ATTACHED DUCTING. DURING GROUND RUN CHECKS AFTER OPS CHECK (600 HR) INBOARD HEATING DUCT CONTACTED SHAFT ASSY P/N 206-040-325-5 & ADAPTER P/N 206-040-328-003 HEATING DUCT (HOSE) WASTORN & WIRE IN HEATER (HSDR KBMA88794Volt Regulator · malfunctionedVOLTAGE REGULATOR MAX ADJUSTMENT IS 27.5 VOLTS. REMOVED AND REPLACED SERVICEABLE VOLTAGE REGULATOR.SDR CA011011007Structure · vibration(CAN) PART CAUSING HIGH VIBRATION IN T/R SYSTEM. REPLACED VERTICAL FIN.SDR CA011011008Fitting · cracked(CAN) PART CRACK AT REAR RIVET. REPLACED FITTING.SDR RYMA33656Transmission · failedMAKING METAL. TWO PRIOR PROBLEMS WITH MM WERE REPAIRED UNDER WARRANTY BY MFG. REPLACED WITH NEW UNIT CORRECTED PROBLEM.SDR AUS20010925Shaft · distorted(AUS) TAIL ROTOR GEARBOX OUTPUT SHAFT BEARINGS BREAKING UP AND SHAFTRUNOUT EXCESSIVE. SHAFT RUNOUT APPROXIMATELY 0.457MM (0.018IN). MAXIMUM RUNOUT 0.0254MM (0.001IN).SDR VGY2001F00000Fuel Control · faultyAFTER INSTILLATION OF O/H ENG, HELICOPTER WAS GROUND RUN AND ALL ENG INSTRUMENTS AND OPERATION WAS NORMAL. A HOVER TEST FLIGHT WAS PERFORMED AND EVERYTHING STILL NORMAL. A SERIES OF 2 OR 3 HOVERING AUTOS WERE PERFORMED. DURING SPOOL UP ON LAST AUTO, NR 2 WOSDR CA020405019Starter Gen · inoperative(CAN) STARTER GENERATOR INOPERATIVE.SDR 2001F00604Turbine Wheel · brokenTURBINE RECEIVED FROM FIELD, REMOVED COMB CASE FOUND SULPHADATION ON NR 1 WHEEL. WHEEL HAS BROKEN BLADES DUE TO SULPHADATION. (M)SDR KBMA88769Switch · inoperativeLIGHT STAYS OFF WITH BREAKER PULLED. REMOVED AND REPLACED WITH NEW SWITCH.SDR CA011002009Fitting · cracked(CAN) TAILBOOM FITTING LT FUSELAGE SIDE FOUND CRACKED VERTICALLY 1 INCH IN LENGTH. NEW PART ORDERED AND INSTALLED.SDR KBMA88767Display · inoperativeLED DISPLAY UNREADABLE. REMOVED AND REPLACED WITH SERVICEABLE UNIT.SDR CA020118003Bearing · spalled(CAN) UPON INSPECTION 3 BALL BEARINGS, FOUND EXCESSIVELY SPALLED AND INNER RACE SHOWED 3 SIGNS OF PITTING IN 3 AREAS. BEARING WAS SCRAPPED.SDR CA020118004Mast · corroded(CAN) UPON 1500 HOUR INSPECTION OF MAST BEARING RETAINING NUT REMOVAL. PRC SEALANT WAS REMOVED FROM THE LOWER MAST THREADS TO UNCOVER CORROSION PITTING WELL IN EXCESS OF CORROSION TOLERANCES. MAST WAS SCRAPPED.SDR CA010810005Blade · dented(CAN) DURING A DAILY INSPECTION THE PILOT NOTICED A DENT ON THE LEADING EDGE OF THE NOTED T/R BLADE. UPON INSPECTION THE DAMAGE WAS MEASURED AND FOUND TO BE IN LIMITS. FURTHER TO THE INVESTIGATION IT WAS FOUND THAT A SCREW HAD COME LOOSE FROM THE GEARBOX FAIRISDR KBMA88659Indicator · inoperativeVSI REPORTED INOPERATIVE. REMOVED AND REPLACED WITH SERVICEABLE UNIT.SDR CA010724012Strap · cracked(CAN) WHILE INSTALLING ELECTRICAL EQUIPMENT, A CRACK WAS FOUND ON THE AFT OUTBOARD RADIUS, STATION 100.8. THE CRACK STARTED FROM THE EDGE OF THE STRAP AT A TOOLING MARK MADE EITHER DURING MANUFACTURE OR PREVIOUS INSTALLATION. THE CRACK IS APPROXIMATELY 2 1/2 ISDR CA010724036Seal · damaged(CAN) ON PRE-FLIGHT INSPECTION, GREASE LEAKAGE ON FORWARD COUPLING ON INPUT DRIVESHAFT WAS NOTED. FURTHER INSPECTION REVEALED THATTHE FORWARD SEAL ASSY HAD FAILED AND ALL THE GREASE IN THE FORWARD COUPLING WAS THROWN OUT WHICH CAUSED AN OVERHEAT CONDITION. A MSDR KBMA88672Indicator · inoperativeSHOWING 20 PERCENT BANK ANGLE AFTER FIVE MINUTES IN FLIGHT. REPLACED WITH SERVICEABLE UNIT.SDR CA010808003Bearing · spalled(CAN) TRANSMISSON REMOVED FROM A/C DUE TO METAL CONTAMINATION AND EXCESSIVE NOISE. ON DISASSEMBLY, MAIN INPUT GEAR SHAFT P/N 206040040003 WAS FOUND TO HAVE VERTICAL PLAY. AFTER REMOVING THE SHAFT AND THE DUPLEX THRUST BEARING P/N 2060400321 THE TOP BEARING OF SDR CA020405018Pump · inoperative(CAN) FORWARD BOOST PUMP INOPERATIVE.SDR 2001FA0000234Blade · crackedFOUND CRACK ON PREFLIGHT. NO SURE CAUSE FOR CRACK. CRACK BEYOND LIMITS.SDR CA010627040Support Bracket · broken(CAN) THE FLANGE FOR THE VERTICAL FIN UPPER ATTACHMENT BOLT IS SEPARATED FROM SUPPORT DUE TO CRACK.SDR 2001FA0000300Engine · malfunctionedDEPARTING THE AIRPORT, THE ENGINE FLAMED OUT OR SURGED. THE ENGINE WAS RUN ON A TEST CELL. TEST CELL SHOWED: 1)A CYCLING ANTI-ICE VALVE SOLENOID. 2) A RICH FUEL FLOW. 3) A WARPED OUTER COMBUSTION CHAMBER. THIS TOGETHER, COULD CAUSE A SURGE.SDR AQH2001F00000Seal · torn1) INSTALLED NEW SEAL PN23063371, MGR-80201, REV B, OTHER MARKINGSON SEAL ARE 63005SOCN. 2) SEAL STARTED LEAKING LESS THAN 4 HOURS AND 15 STARTS LATER, SEAL LIP IS TORN, APPEARS LIKE A RIP, SUSPECT SEAL IS NOT COMPATIBLE WITH EXXON 8380 TURBINE OIL AND MAYBE SDR CA010625031Bearing · failed(CAN) PILOT FELT ENGINE VIBRATION, 30 MINUTES INTO THE FLIGHT, WITH CLIMB OF T.O.O. TURN BACK FOR LANDING. ENGINE OIL PRESS FLACTUATE. 6FT ABOVE GROUND THE ENGINE QUIT. THE PILOT DID LOWER AUTOROTATION, NO DAMAGE TO AIRCRAFT AND NO ONE GOT INJURED. INITIAL INSSDR CA031117009Support · cracked(CAN) WHILE PERFORMING AN AW CHECK, CRACKS WERE SUSPECTED IN AFT CROSS TUBE SUPPORT AREA. AFTER PAINT STRIPPING CRACKS CONFIRMED AS FOLLOWS. A SMALL HAIRLINE CRACK WAS FOUND ON THE FWD LEG OF THE LT CROSS TUBE SUPPORT. CRACK IS JUST OUTBOARD OF 90 DEGREE ANSDR CA010621026Pulley · failed(CAN) OIL COOLER PULLEY IS MADE UP OF A SPLINE BELT PULLEY WITH A METAL RING THAT IS "STAKED" ONTO THE PULLEY. THE RING WAS FOUND AROUND THE ENGINE OUTPUT DRIVE SHAFT AFTER GROUND RUNNING THE A/C. A NEW PART WAS USED TO COMPARE THE STAKING MARKS ON THE OLD PULSDR 20010613CW021Bearing · failedAIRCRAFT IN CRUISE FLIGHT. PILOT NOTICED THAT THE MAIN ROTOR NR 2 STARTED TO OVER-SPEED. PILOT LANDED AIRCRAFT SAFELY UNDER ITS OWN POWER. AFTER INVESTIGATING CAUSE, IT WAS FOUND THAT THE ENGINE FUEL CONTROL SHAFT BEARING HAD FAILED CAUSING FUEL CONTROL TO SDR CA020405022Bolt · worn(CAN) EXCESSIVE WEAR ON THE MAIN ROTOR BLADE BOLT SHANK.SDR CA010425004Brushes · broken(CAN) STARTER-GENERATOR WAS INSPECTED BECAUSE OF PREVIOUS HISTORY OF PROBLEMS IN THIS AR4A. UPON INSPECTION FOUND 3 BRUSH LEADS BROKEN OFF BRUSHES AND 3 SPRINGS BROKEN. THE STARTER GENERATOR HAS BEEN REMOVED FOR OVERHAUL. STARTER-GENERATOR LAST OVERHAULED AT CSDR 20010416CW016Governor · failedGOVERNOR FAILURE RANGES FROM 72 HOURS TO 1750 HOURS.SDR 20010301CW004Elt · crackedINSPECTING ELT, FOUND CASE TO BE IN MANY PIECES WITH CRACKS THROUGHOUT ENTIRE UNIT. PLASTIC SEEMS TO BE VERY SOFT AND BRITTLE. THIS IS SECOND ELT OF THIS MAKE AND MODEL THAT HAS BEEN FOUND IN THIS CONDITION DURING TESTING FOR NON OPERATION.SDR KBMA88680Pressure Switch · inoperativeFORWARD BOOST PUMP PRESSURE SWITCH INOPERATIVE.SDR KBMA88679Pressure Switch · malfunctionedFUEL PRESSURE SWITCHES NOT OPERATING PROPERLY. CAUTION LITE REMAINS ON WITH CIRCUIT BREAKER IN.SDR 20010420CW015Skin Panel · debondedAFTER LANDING AND WALK AROUND, RIGHT SKID PANEL METAL STRIP WAS FOUND DEBONDED FROM SKID PANEL.SDR CA010307007Bearing · corroded(CAN) SEVERE PITTING OF LOWER BEARING JOURNAL INNER RACE AT LOWER PORTION OF MAST ASSEMBLY.SDR CA010110023Gear · failed(CAN) BURR ON GEAR FACE CAUSED DAMAGE TO THE BEARING.SDR CA010110014Bolt · misinstalled(CAN) INBOARD LATERAL BALANCE WEIGHTS LOOSE. INBOARD BOLT P/N AN4-12A WAS TOO LONG FOR THE AMOUNT BALANCE WEIGHTS INSTALLED. WE CONTACTED PRODUCT SUPPORT AND THEY SAID TO INSTALL A SHORTER AN4 BOLT. WE INSTALLED AN AN4-11A BOLT.SDR CA001218013Fitting · broken(CAN) UPON SCHEDULED INSPECTION THE RT HORIZONTAL STABILIZER WAS FOUND TO HAVE SOME PLAY. FURTHER INVESTIGATION REVEALED THE FITTING WHICH ATTACHES THE STABILIZER TO THE TAIL BOOM WAS CRACKED. WHEN THE STAB WAS REMOVED, THE FITTING CAME OFF IN 2 PIECES. IT WASSDR CA001205011Mast · failed(CAN) DURING THE SERVICEABILITY CHECK (AFTER THE METAL WAS FOUND ON THE CHIP PLUG) MORE METAL WAS FOUND ON THE CHIP PLUGS AND THE OIL MONITOR. MAST AND THE TRANSMISSION WERE REPLACED. (X)SDR R7MR32686Sensor · inoperativeUNIT INOPERATIVE. NO PRESSURE DROOP INDICATION. REPLACED WITH NEW UNIT, CORRECTED PROBLEM.SDR CA001201018Line · loose(CAN) ENGINE DECELERATED ON TAKEOFF FOR TEST FLIGHT AFTER ENGINE CHANGE. CAUSE WAS DETERMINED TO BE LOOSE B-NUT ON GOVERNOR TO FUEL CONTROL UNIT AIR LINE.SDR CA001030005Line · failed(CAN) OIL LINE FAILED AT AREA WHERE IT IS CLAMPED TO THE UPPER DECK. (X)SDR CA001017007Compressor · cracked(CAN) DURING 100-HOUR INSPECTION OF THE HELICOPTER, A BLACK LINE WAS OBSERVED ON ONE OF THE COMPRESSOR ASSEMBLY MOUNTING PAD ARMS WHICH FORMS THE REAR DIFFUSER OF THE COMPRESSOR. CLOSER VISUAL INSPECTION WITH MAGNIFYING GLASS CONFIRMED CRACK. THE CRACKED MOUSDR CA000926017Disc Pack · misinstalled(CAN) WHILE INSPECTING A NEW PART PRIOR TO INSTALLATION, IT WAS NOTED THAT INDIVIDUAL DISCS WERE NOT CORRECTLY STACKED PER BELL 206 MAINTENANCE MANUAL (FIGURE 65-6, PARAGRAPH 65-19 CAUTION COPY ATTACHED.) THE NOTE ATTACHED TO THE DISC SET STATES THAT THEY MUST
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