Allison 250-C30S
Service difficulty reports · 449
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 = '250C30S' 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 = '250C30S' 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 HEEA0014091Spline Adapter · mis mfgRECEIVING INSPECTION REVEALED: MEASURED (.9853) .0002 BELOW SPECS .9855 - .9860 ON SPLINED ADAPTER O.D.SDR HEEA0014092Spline Adapter · mis mfgRECEIVING INSPECTION REVEALED: O.D. MEASURED (.9853) .0002 UNDER SPECS ON SPLINE ADAPTER O.D. INSTALLED A NEW SPLINE ADAPTER.SDR 98ZZZX2089Support · crackedTURBINE REMOVED FOR 2,000-HOUR OVERHAUL AND DID NOT STATE THAT ENGINE OR TURBINE WAS SMOKING OR USING OIL. WHEN COMBUSTION REMOVED, DISCOVERED THE FIRST STAGE NOZZLE HAD OIL STAINS ON THE VANES AND THE GP SUPPORT HAD OIL STAINS AROUND THE STRUT THAT WAS CRACKSDR HEEA0014025Nozzle Shield · crackedENGINE REMOVED DUE TO TURBINE CYCLES. UPON INSPECTION OF TURBINE PARTS NOTED: CRACKED BEYOND SERVICEABLE LIMITS ON NR1 NOZZLE SHIELD DOME AS MARKED.SDR HEEA0013995Nozzle Shield · crackedENGINE REMOVED DUE TO NR1 AND NR2 WHEEL CYCLES. UPON INSPECTION OF TURBINE PARTS NOTED: CRACKED BEYOND SERVICEABLE LIMITS ON NR1 NOZZLE SHIELD OUTER BAND.SDR HEEA0013942Fuel Pump · wornFUEL PUMP WORN DRIVE SHAFT SPLINES AND GEAR SPLINES.SDR 98ZZZX1741Engine · failedMARCH 29, 1998 IN CRUISE FLIGHT, THE NR 1 ENGINE OIL PRESSURE BEGAN TO FLUCTUATE. SHUT DOWN ENGINE AND DIVERTED TO BRAZORIA COUNTY FOR SINGLE ENGINE LANDING. MAINTENANCE FOUND NR 1 ENGINE OIL SCAVENGE INADEQUATE, OIL TANK EMPTY, AND ENGINE GEARBOX FULL OF OISDR HEEA0013501Fuel Pump · wornFUEL PUMP WORN SPLINES.SDR CA980317051Pitch Horn · cracked(CAN) CRACK FOUND ON THE TAIL ROTOR BLADE PTCH HORNS. CRACK STARTED FROM THE OUTBOARD BASE OF THE PITCH HORN AND ENDED AT THE INBOARD BASE OF PITCH HORN ALONG RADII OF THE CUFF OF THE PITCH HORN.SDR HEEA0013035Seal · defectiveENGINE REMOVED DUE TO FOD AND TURBINE OVERHAUL. UPON INSPECTION OF TURBINE PARTS NOTED: MEASURED .001 BELOW SPECS (1.2520 - 1.2515) ON SEAL O.D. INSTALLED A NEW SEAL.SDR HEEA0012987Scroll · misalignedCOMPRESSOR REPAIR DUE TO LOW POWER ON TEST CELL. INSPECTION OF COMPRESSOR PARTS REVEALED: MISALIGNMENT OF SCROLL ASSEMBLY TURNING VANES. INSTALLED A PHI OVERHAULED SCROLL.SDR HEEA0012989Nozzle · crackedENGINE REMOVED DUE TO TURBINE NR1 AND NR2 WHEEL CYCLES. UPON INSPECTION OF TURBINE PARTS NOTED: CRACKED BEYOND SERVICEABLE LIMITS ON NR1 NOZZLE TRAILING EDGE VANES. INSTALLED A DALLAS AIRMOTIVE OVERHAULED NR1 NOZZLE.SDR HEEA0012991Nozzle · defectiveENGINE REMOVED DUE TO TURBINE NR1 AND NR2 WHEEL CYCLES. UPON INSPECTION OF TURBINE PARTS NOTED: EXCESSIVE RUNOUT ON NR2 NOZZLE 1ST STAGE TIP PATH .007 AND NR2 TIP PATH .005. INSTALLED A NEW NR2 NOZZLE.SDR HEEA0012868Transmitter · leakingPRESSURE TRANSMITTER LEAKING OIL INTO ELECTRICAL CONNECTOR.SDR HEEA0012579Nozzle · crackedENGINE REMOVED DUE TO TURBINE CYCLES. UPON INSPECTION OF TURBINE PARTS NOTED: CRACKED BEYOND SERVICEABLE LIMITS ON NR 2 NOZZLE VANES AND KEY WELDS.SDR HEEA0012500Transmitter · failedFUEL PRESSURE TRANSMITTER READS HIGH OUT OF TOLERANCE.SDR HEEA0012381Combustion Liner · crackedRECEIVING INSPECTION REVEALED: CRACKED BEYOND SERVICEABLE LIMITS ON COMB. LINER INNER SKIRT. INSTALLED A DALLAS AIRMOTIVE OVERHAULED COMB. LINER.SDR HEEA0012375Gearshaft · wornENGINE REMOVED DUE TO TURBINE OVERHAUL AND COMPRESSOR N1 SHAFTING INSPECTION. UPON INSPECTION OF COMPRESSOR PARTS NOTED: STEP WEAR BEYOND SERVICEABLE LIMITS ON SPUR GEAR SHAFT SPLINES. INSTALLED A NEW SPUR GEARSHAFT.SDR CA971219003Engine · making metal(CAN) MAGNETIC CHIP DETECTOR WARNING LIGHT ON DURING FLIGHT. CHIP DETECTORS AND OIL FILTERS REMOVED. METAL DEBRIS FOUND ON BOTH.SDR 98ZZZX249Gear · wornRECEIVING INSPECTION - RECEIVED GEAR FROM ALLISON, TAG INDICATED THE PART WAS NEW. THE VISUAL INSPECTION OF GEAR INDICATED THE GEAR WAS USED AND UNSERVICEABLE BY AIR LOG ENGINE SHOP STANDARDS.SDR CA970916019Splines · worn(CAN) FUEL PUMP SPLINE SHAFT END WORN. REPLACED.SDR CA970822001Seal Runner · cracked(CAN) SEAL LEAKING AT OUTPUT DRIVE FLANGE ON ENGINE GEARBOX. DURING SEAL REPLACEMENT, IT WAS NOTICED THAT THE PTO GEAR AT THE SEAL LIP CONTACT WAS CRACKED.SDR CA970812004Torque Arm · chafed(CAN) ON APPROACH, NOSE LANDING GEAR DID NOT EXTEND. SCISSORS/TORQUE ARM HAD JAMMED AGAINST THE ACTUATOR RESTRICTING THE GEAR.SDR HEEA0010539Nozzle · crackedENGINE REMOVED DUE TO HIGH OIL TEMP. INSPECTION OF TURBINE PARTS REVEALED: CRACK BEYOND SERVICEABLE LIMITS ON #1 NOZZLE VANES. INSTALLED A STANDARD AERO OVERHAULED #1 NOZZLE.SDR HEEA0010537Coupling · step wearENGINE REMOVED DUE TO TURBINE OVERHAUL. INSPECTION OF TURBINE PARTS REVEALED: STEP WEAR BEYOND SERVICEABLE LIMITS ON N2 COUPLING SPLINES. INSTALLED A NEW N2 COUPLING.SDR CA970812003Hose · worn(CAN) DURING FINAL, NR 2 HYDRAULIC PRESSURE WAS AT 2700 PSI, 10 SECONDS LATER PRESSURE AT ZERO. NR 2 HYDRAULIC SWITCH SELECTED TO OFF. CONTROLS CHECKED FOR BINDING. AFTER SHUTDOWN, LEAK FOUND IN NOSE WHEEL AREA.SDR 97ZZZX4413Wheel Blades · erodedTURBINE ASSEMBLY RECEIVED DUE TO 2,000 HOUR OVERHAUL. FOUND FIRST STAGE WHEEL HAD BURNED AND ERODED BLADES CAUSED BY SULFIDATION.SDR HEEA0010482Turbine Wheel · sulfidationENGINE REMOVED DUE TO LOW POWER. UPON INSPECTION OF TURBINE PARTS NOTED; MINOR SULPHIDATION ON ALL BLADES ON #1 WHEEL. SCRAPPED 1ST STAGE WHEEL.SDR HEEA0010465Gear Shaft · step wearENGINE REMOVED DUE TO TURBINE CYCLES. UPON INSPECTION OF COMPRESSOR NOTED: STEP WEAR BEYOND SERVICEABLE LIMITS ON GEARSHAFT FORWARD AND AFT SPLINES. INSTALLED A NEW GEARSHAFT.SDR HEEA0010378Nozzle · over specRECEIVING INSPECTION REVEALED: MEASURED .015 OVER SPECS (4.445 - 4.450) ON #1 NOZZLE DIMENSION -AM-.SDR HEEA0010369Nozzle · excess runoutRECEIVING INSPECTION REVEALED: EXCESSIVE RUNOUT (.010) OF #2 NOZZLE 29-34 SEAL BORE. INSTALLED A NEW #2 NOZZLE.SDR HEEA0010211Collector · not bondedRECEIVING INSPECTION REVEALED: COATING NOT BONDED IN EXHAUST COLLECTOR SEAL BORE.SDR HEEA0010114Gearshaft · step wearENGINE REMOVED DUE TO LOW POWER. UPON INSPECTION OF COMPRESSOR PARTS NOTED: STEP WEAR BEYOND SERVICEABLE LIMITS ON SPUR GEARSHAFT AFT SPLINES. INSTALLED A NEW SPUR GEARSHAFT.SDR 97ZZZX4431Wheel Blades · brokenTURBINE ASSEMBLY WAS RECEIVED WITH ENGINE ASSEMBLY DUE TO MAKING METAL. UPON INSPECTION OF G.P. SECTION, FOUND SULFIDATION ON 1ST STAGE WHEEL. 1ST STAGE WHEEL: PN 23053299, SN X-138702, TT 1,348.1 HOURS, TC 1,697. SCRAPPED DUE TO MISSING BROKEN AND CRACKEDSDR HEEA0010020Combustion Liner · mis mfgRECEIVING INSPECTION REVEALED LOWER SECTION NINETY DEGREES OFF FROM COMBUSTION LINER TOP SECTION. INSTALLED A STANDARD AERO OVERHAULED COMBUSTION LINER.SDR HAIHEEA9912Rear Diffuser · defectiveASSEMBLY REQUIREMENT REVEALED: EXCESSIVE RUN OUT (.0045) OF REAR DIFFUSER #2 BEARING BORE (MAX RUN OUT .002) RE-INDEXED SHROUD NO CHANGE. #2 BEARING BORE .003 BELOW SPECS. INSTALLED A DALLAS AIRMOTIVE OVERHAULED REAR DIFFUSER.SDR 97ZZZX3547Combustion Liner · failedENGINE SHUT DOWN IN-FLIGHT. FOUND BROKEN PC LINE FROM GOVERNOR TO FUEL CONTROL AND A HIGH VIBRATION LEVEL. ENGINE WAS REMOVED. ON TEAR DOWN, FOUND COMBUSTION LINER UPPER AIR SKIRT LOOSE AND PIECES MISSING. ENGINE WAS FOD OUT. THIS WAS THE SECOND RE-WORKED SDR 97ZZZX2837Air Line · brokenIN CRUISE FLIGHT, NR 2 ENGINE SPOOLED DOWN TO 30 PERCENT AND THEN DOWN TO 10 PERCENT. ENGINE WAS SECURED AND AIRCRAFT WAS FLOWN TO AIRPORT FOR LANDING. FOUND PC AIR LINE, PN 6893073, BROKEN AT FERRULE ON FUEL CONTROL. THIS LINE COMES FROM GOVERNOR TO FUEL CSDR CA970501001Thermostat · failed(CAN) ENGINE OIL TEMP HIGH IN CRUISE ON NR 1 ENGINE. ALL OTHER PARIMETERS NORMAL. POSSIBLE INDICATION PROBLEM BUT 10 MINUTES LATER, OIL PRESSURE WAS FLUCTUATING. AIRCRAFT RETURNED. OIL TEMP THERMOSTAT STUCK CLOSED. REPLACED.SDR HAIHEEA9457N1 Coupling · stepwearENGINE REMOVED DUE TO CYCLED #1 AND #2 TURBINE WHEELS. UPON INSPECTION OF TURBINE PARTS NOTED: STEP WEAR BEYOND SERVICABLE LIMITS ON N1 COUPLING FORWARD SPLINES. INSTALLED A NEW N1 COUPLING.SDR HEEA979154Nozzle · crackedENGINE REMOVED DUE TO BROKEN STUD ON TURBINE MOUNT PAD. TURBINE DISASSEMBLED DUE TO HIGH VIBRATION ON TEST CELL. DISASSEMBLY INSPECTION REVEALED: CRACKED BEYOND SERVICEABLE LIMITS ON #1 NOZZLE VANES. INSTALLED A DALLAS AIRMOTIVE OVERHAULED #1 NOZZLE.SDR HEEA979139Wheel · defectiveTURBINE WHEEL DEFECTIVESDR 97ZZZX927Filter Cap · failedSHORTLY AFTER TAKEOFF FROM AN OFFSHORE PLATFORM IN THE GULF OF MEXICO, THE NR 1 ENGINE FIRE WARNING LIGHT ILLUMINATED AND THE NR 1 ENGINE OIL PRESSURE BEGAN TO FLUCTUATE. THE FLIGHT CREW SECURED THE NR 1 ENGINE AT WHICH TIME THE FIRE WARNING LIGHT EXTINGUISHEDSDR HEEA968807Heat Exchanger · weld leaksHEAT EXCHANGER LEAKS AT WELD ALONG OUTER B-NUTLINE.SDR HEEA968763Gearshaft · step wearENGINE REMOVED DUE TO CYCLED OUT 1ST AND 2ND STAGE WHEELS. UPON VISUAL INSPECTION OF COMPRESSOR NOTED THE FOLLOWING: STEP WEAR BEYOND SERVICEABLE LIMITS ON SHAFT AFT SPLINES. INSTALLED A USED SERVICEABLE PART.SDR HEEA968764Gearshaft · step wearENGINE REMOVED DUE TO CRACKED SCROLL. UPON VISUAL INSPECTION OF COMPRESSOR NOTED THE FOLLOWING: STEP WEAR BEYOND SERVICEABLE LIMITS ON SHAFT AFT SPLINES. INSTALLED A USED SERVICEABLE PART.SDR HEEA968409Combustion Liner · defectiveUPON INSTALLATION OF COMBUSTOR LINER NOTED: UNABLE TO INSTALL FUEL NOZZLE AND IGNITER PLUGS DUE TO MISALIGNMENT. REPLACED DISCREPANT PART.SDR 96ZZZX5539Nozzle · crackedUPON MAJOR REPAIR OF TURBINE, FOUND WEB OF OUTER BAND SEEMS TO HAVE BEEN MACHINED BELOW SPECS AND REPLATED. THIS CAUSED A WEAK SPOT IN FLANGE OF NOZZLE THAT CRACKED AND WENT INTO BOTH BLADE TIP PATHS. NOZZLE IS TO BE SCRAPPED. ASSURE THAT PARENT METAL IS MASDR HEEA967656Idler Gear · making metalENGINE REMOVED DUE TO METAL GENERATION. UPON INSPECTION OF GEARBOX PARTS NOTED: IMPROPER FINISH MACHINING ON GENERATOR IDLER GEARSHAFT GEAR TEETH, SPALLING GEAR TEETH WITH LARGE CHIPS OF METAL MISSING IN 3 AREAS CAUSING METAL PICKOUT ON STARTERGENERATOR GEARSDR 96ZZZX4849Scavenge Tube · bracket brokenUPON DISASSEMBLY OF GEARBOX, REMOVED OIL PUMP ASSY AND SCAVENGE TUBE. FOUND ALIGNMENT BRACKET ON SCAVENGE BROKEN.
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