Allison 250-C28B

Service difficulty reports · 286

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 = '250C28B'
  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 CA970311033Longeron · cracked(CAN) LEFT HAND SUPPORT P/N 206-031-332-031S AND LEFT LONGERON CRACKED AND WORKING.Apr 26, 1996 · Bell 206L1 · Fuselage Main, Longeron/StringerSDR AU960405Connector · high resistance(AUS) GOVERNOR LINEAR ACTUATOR (PNO 206062721103) EARTH TERMINAL CRIMP HAD HIGH RESISTANCE PREVENTING ACTUATOR FROM WORKING DURINGLANDINGMar 27, 1996 · Bell 206L1 · Fuel Controlling SystemSDR CA960325011Bearing · spun(CAN) ENGINE CHIP LIGHT CAME ON IN CRUISE FLIGHT AND AIRCRAFT LANDED. 2 CHIP PLUGS AND OIL FILTER INSPECTED AS PER ALLISON MM REQUIREMENTS FOR CHIP LIGHT INDICATION. VERY FINE BRONZE COLOURED MATERIAL AND TWO MAGNETIC SLIVERS NOTED. PLUGS AND FILTER CLEANED ANMar 13, 1996 · Bell 206L1 · Turbine Engine Accessory DriveSDR CA960327015Relief Valve · leaking(CAN)VALVE WAS FOUND TO BE LEAKING. UPON REMOVAL AND DISASSEMBLY, DIRT AND CORROSION WAS FOUND TO BE THE CAUSE. SUGGEST A SMALL HOLE BE DRILLED TO ALLOW WATER TO ESCAPE, OR REPOSITION VALVE BY TURNING BODY 90 DEGREES.Jan 30, 1996 · Bell 206L1 · Emergency Flotation SectionSDR HEEA966329Coupling · step wearENGINE REMOVED DUE TO TURBINE 3RD STAGE WHEEL REPLACEMENT. UPON INSPECTION OF TURBINE PARTS NOTED THE FOLLOWING: STEP WEAR BEYOND LIMITS ON N1 COUPLING I.D. SPLINES. INSTALLED NEW N1 COUPLING.Jan 2, 1996 · N5007Y · Bell 206L1 · Turbine SectionSDR 96ZZZX738Gearbox Housing · unbondingUPON DISASSEMBLY AND INSPECTION OF THE GEARBOX PARTS, HOUSING INSPECTION FOUND BRONZE LIFTING FROM TACK GEN. PAD. POSSIBLE CAUSE FOR BRONZE PLATING UNBONDING IS DUE TO SURFACE CORROSION ON HOUSING AND OIL ACCUMULATION UNDER BRONZE DEBONDS PLATING.Dec 29, 1995 · N1084Y · Bell 206L1 · Turbine Engine Reduction GearSDR HEEA956229Wheel · blade crackedENGINE REMOVED DUE TO 3RD STAGE TURBINE WHEEL INSPECTION. 3RD STAGE WHEEL RETURNED TO ALLISON FOR INSPECTION PER LETTER C1245F-RMG-1195. ZYGLO INSPECTION REVEALED ONE EACH INDICATION 1/8" FROM SHROUD OF L/E BACK SIDE OF BLADE. INDICATIONDOES NOT GO THROUGH Dec 12, 1995 · N50182 · Bell 206L1 · Turbine SectionSDR HEEA956230Wheel · blade crackedENGINE REMOVED DUE TO 3RD STAGE TURBINE WHEEL INSPECTION. 3RD STAGE WHEEL RETURNED TO ALLISON FOR INSPECTION PER LETTER C1245F-RMG-1195. ZYGLO INSPECTION REVEALED SIX EACH CRACKS ON L/E OF BLADES 1/8" FROM SHROUD 3/16" LONG. INSTALLED SERVICEABLE 3RD STAGE WDec 12, 1995 · N5017G · Bell 206L1 · Turbine SectionSDR HEEA956231Wheel · crackedENGINE REMOVED DUE TO 3RD STAGE TURBINE WHEEL INSPECTION. 3RD STAGE WHEEL RETURNED TO ALLISON FOR INSPECTION PER LETTER C1245F-RMG-1195. ZYGLO INSPECTION REVEALED ONE EACH INDICATION ON L/E 15/16" FROM HUB. INSTALLED SERVICEABLE 3RD STAGE WHEEL.Dec 12, 1995 · N5007Y · Bell 206L1 · Turbine SectionSDR HEEA956232Wheel · blade crackedENGINE REMOVED DUE TO 3RD STAGE TURBINE WHEEL INSPECTION. 3RD STAGE WHEEL RETURNED TO ALLISON FOR INSPECTION PER LETTER C1245F-RMG-1195. ZYGLO INSPECTION REVEALED ONE EACH BLADE CRACKED 3/32" FROM HUB L/E 3/16" LONG, AND ONE EACH BLADECRACKED 1/8" FROM SHROUDec 12, 1995 · N3905B · Bell 206L1 · Turbine SectionSDR HEEA956233Wheel · blade crackedENGINE REMOVED DUE TO 3RD STAGE TURBINE WHEEL INSPECTION. 3RD STAGE WHEEL RETURNED TO ALLISON FOR INSPECTION PER LETTER C1245F-RMG-1195. ZYGLO INSPECTION REVEALED FOUR EACH BLADES CRACKED 3/16" LONG, 1/16" FROM SHROUD ON L/E. INSTALLED SERVICEABLE 3RD STADec 12, 1995 · N5745S · Bell 206L1 · Turbine SectionSDR HEEA956234Wheel · crackedENGINE REMOVED DUE TO 3RD STAGE TURBINE WHEEL INSPECTION. 3RD STAGE WHEEL RETURNED TO ALLISON FOR INSPECTION PER LETTER C1245F-RMG-1195. ZYGLO INSPECTION REVEALED THREE EACH CRACKS 3/16" LONG, 1/16" FROM SHROUD ON L/E. CRACKSLOCATED 180 DEGREES AROUND WHDec 12, 1995 · N22425 · Bell 206L1 · Turbine SectionSDR HEEA956160Wheel · blade damageENGINE REMOVED DUE TO LOUD GRINDING NOISE, HIGH PITCH SQUEAL ACCOMPANIED BY TORQUE FLUCTUATIONS. UPON INSPECTION OF TURBINE PARTS NOTED THE FOLLOWING: RIM BREAKOUT OF 1 1/2" AND 1/4" OF TWO EACH BLADES ON 3RD STAGE WHEEL. SUSPECT CAUSE OF FAILURE TO BE A STNov 29, 1995 · N21240 · Bell 206L1 · Turbine SectionSDR HEEA956161Wheel · damagedENGINE REMOVED DUE TO LOUD ROAR AND WHINE FOLLOWED BY ENGINE CHIP LIGHT. UPON INSPECTION OF TURBINE PARTS NOTED THE FOLLOWING: RIM BREAKOUT OF 1 3/4" AND 1/4" OF THREE EACH BLADES ON 3RD STAGE WHEEL. SUSPECT CAUSE OF FAILURE TO BE A STRESS CRACK ORIGINATINGNov 29, 1995 · N27702 · Bell 206L1 · Turbine SectionSDR 95ZZZX6874Wheel · rim break outLOUD GRINDING, HIGH PITCH SQUEAL ACCOMPANIED BY TORQUE FLUCTUATIONS. TEAR DOWN INSPECTION REVEALED 3RD STAGE WHEEL EXHIBITED RIM BREAK OUT OF 1.50 INCHES AND .25 INCH OF 2 EACH BLADES. SUSPECT CAUSE OF FAILURE TO BE A STRESS CRACK ORIGINATING ON THE LEADING Nov 26, 1995 · N21240 · Bell 206L1 · Turbine SectionSDR 95ZZZX6873Wheel · rim break outLOUD ROAR AND WHINE FOLLOWED BY ENGINE CHIP LIGHT. TEAR DOWN INSPECTION REVEALED 3RD STAGE WHEEL EXHIBITED RIM BREAK OUT OF 1.75 INCH AND .25 INCH OF 3 EACH BLADES. SUSPECT CAUSE OF FAILURE TO BE A STRESS CRACK ORIGINATING ON THE LEADING EDGE SIDE OF BREAK OUNov 20, 1995 · N27702 · Bell 206L1 · Turbine SectionSDR 95ZZZX6886Nr 2 Nozzle · eroded vaneUPON DISASSEMBLY OF TURBINE, INSPECTION OF PARTS FOR LOW POWER FOUND BURNED AND ERODED VANE L.E. AND T.E.Nov 10, 1995 · N27554 · Bell 206L1 · Turbine SectionSDR 95ZZZX68851st Nozzle · eroded valveUPON DISASSEMBLY OF TURBINE, INSPECTION OF PARTS FOR LOWER POWER FOUND BURNED AND ERODED VANE L.E. AND T.E.Nov 9, 1995 · N27554 · Bell 206L1 · Turbine SectionSDR HEEA955801Fuel Control · leaksFUEL LEAKS FROM BY-PASS VALVE RETENTION PLATE. REPLACED WITH SERVICEABLE FUEL CONTROL.Sep 21, 1995 · N2249Z · Bell 206L1 · Fuel Control/Turbine EnginesSDR HEEA955802Governor · defectiveGOVERNOR LEVER STIFF. REPLACED WITH SERVICEABLE GOVERNOR.Sep 21, 1995 · N10778 · Bell 206L1 · Turbine GovernorSDR 97ZZZX3213Ejector Nozzle · crackedDURING FLIGHT, PILOT HEARD A LOUD BANG FOLLOWED BY A WHINE. PILOT LANDED THE AIRCRAFT WITH NO FURTHER PROBLEMS. INSPECTED AND FOUND EJECTOR NOZZLE ASSY MISSING ONE NOZZLE, FOUND THE BROKEN NOZZLE HAD BEEN SUCKED IN BY THE COMPRESSOR, AND FOUND THE REMAINS OFSep 5, 1995 · N5753D · Bell 206L1 · Turbine Engine Compressor SectionSDR HEEA955493Gearshaft · step wearENGINE REMOVED DUE TO HIGH COMPRESSOR VIBRATIONS. UPON INSPECTION OF COMPRESSOR PARTS NOTED THE FOLLOWING: STEPWEAR BEYOND MAINTENANCE MANUAL SPECS ON SPURGEAR FWD AND AFT SPLINES. INSTALLED NEW SPURGEAR. PART HELD AT EAI FOR WARRANTY APPLICATION. REFERENCAug 2, 1995 · N5737T · Bell 206L1 · Turbine Engine Compressor SectionSDR HEEA955519Fuel Control · defectiveFUEL CONTROL BY-PASS COVER RETENTION SCREW HEAD BROKEN (SHEARED)Aug 2, 1995 · N7074W · Bell 206L · Fuel Control/Turbine EnginesSDR HEEA955482N1 Coupling · stepwearENGINE REMOVED DUE TO TURBINE OVERHAUL AND 1750 HOUR INSPECTION. UPON INSPECTION OF TURBINE PARTS NOTED THE FOLLOWING: STEPWEAR IN EXCESS OF MAINTENANCE MANUAL LIMITS ON N1 COUPLING FWD. INTERNAL SPLINES. INSTALLED NEW N1 COUPLING.Jul 28, 1995 · N5745S · Bell 206L1 · Turbine Engine Compressor SectionSDR HEEA955483Wheel · mis mfgUPON INSPECTION OF NEW NEVER INSTALLED #2 WHEEL NOTED THE FOLLOWING: RECEIVED OVERMACHINED PER O/H SPECS ON #2 WHEEL SPLINES. INSTALLED NEW #2 WHEEL.Jul 28, 1995 · N5745S · Bell 206L1 · Turbine SectionSDR HEEA955405Wheel · sulfidationENGINE REMOVED DUE TO LOW POWER. UPON INSPECTION OF TURBINE PARTS NOTED THE FOLLOWING: MINOR SULFIDATION ON ALL BLADES. SCRAPPED 1ST STAGE WHEEL.Jul 24, 1995 · N406EH · Bell 206L1 · Turbine SectionSDR HEEA955331Fuel Nozzle · defectiveENGINE HARD TO START. REQUIRED BATTERY CART ON 2 OR 3 STARTS. REPLACED WITH SERVICEABLE FUEL NOZZLE.Jul 6, 1995 · N5742N · Bell 206L1 · Fuel Injector NozzleSDR HEEA955283Internal Sump · seal defectiveENGINE REMOVED DUE TO N2 SEIZURE. UPON INSPECTION OF TURBINE PARTS NOTED THE FOLLOWING: 50% OF GRAPHITE LIFTING IN INTERNAL SUMP 9/12 SEAL, CAUSING N2 SEIZURE.Jun 29, 1995 · N5737T · Bell 206L1 · Turbine SectionSDR HEEA955222Wheel · sulfidationENGINE REMOVED DUE TO TURBINE OVERHAUL. UPON INSPECTION OF TURBINE PARTS NOTED THE FOLLOWING: MINOR SULFIDATION ON ALL BLADES. SCRAPPED 1ST STAGE WHEEL.Jun 26, 1995 · N5745S · Bell 206L1 · Turbine SectionSDR HEEA955191Wheel · sulfidationENGINE REMOVED DUE TO LOW POWER. UPON INSPECTION OF TURBINE PARTS NOTED THE FOLLOWING: SEVERLY SULFIDATED BLADE TIP ON #1 WHEEL CAUSING WHEEL AND NOZZLE CONTACT WITH TRAILING EDGE TIPS OF 8 EACH BLADES MISSING. SCRAPPED #1 WHEEL.Jun 15, 1995 · N50182 · Bell 206L1 · Turbine SectionSDR HEEA955072Wheel · sulfidationENGINE REMOVED DUE TO TURBINE OVERHAUL. UPON INSPECTION OF TURBINE PARTS NOTED THE FOLLOWING: SULFIDATION ON ALL 1ST STAGE WHEEL BLADES. SCRAPPED 1ST STAGE WHEEL.May 24, 1995 · N2758N · Bell 206L1 · Turbine SectionSDR HEEA954917Wheel · sulfidationENGINE REMOVED DUE TO TURBINE OVERHAUL. UPON INSPECTION OF TURBINE PARTS NOTED THE FOLLOWING: MINOR SULFIDATION ON 1ST STAGE WHEEL BLADES. SCRAPPED 1ST STAGE WHEEL.May 4, 1995 · N3905B · Bell 206L1 · Turbine SectionSDR HEEA954764Fuel Nozzle · defectiveAIRCRAFT WILL NOT START ABOVE 12% N1. REPLACED FUEL NOZZLE DUE TO IMPROPER SPRAY PATTERN.Apr 11, 1995 · N50034 · Bell 206L1 · Fuel Injector NozzleSDR HEEA954635Seal · leakingPILOT REPORTED A FIRE IN ENGINE COMPARTMENT. THE FIRE FLASHED, THEN EXTINGUISHED. INVESTIGATION REVEALED OIL LEAK AT 6 & 7 OIL NOZZLE "T" FITTING. REPLACED SEAL ASSEMBLY AND RETURNED ENGINE TO SERVICE.Mar 24, 1995 · N27702 · Bell 206L1 · Turbine Engine Oil SystemSDR HEEA954491Gear Shaft · step wearENGINE REMOVED DUE TO OIL OVERTEMP INSPECTION. UPON INSPECTION OF COMPRESSOR PARTS NOTED THE FOLLOWING: STEP WEAR BEYOND LIMITS ON SPUR ADAPTER GEARSHAFT FORWARD AND AFT SPLINES. INSTALLED NEW SPUR ADAPTER GEARSHAFT.Mar 3, 1995 · N3178K · Bell 206L1 · Turbine Engine Compressor SectionSDR 95ZZZX1345Tube Assy · brokenON TAKEOFF, NOTED THAT N2 RPM DROPPED TO 98 PERCENT AND DID NOT RECOVER. UPON LANDING, RPM RECOVERED TO 100 PERCENT.Feb 10, 1995 · N27483 · Bell 206L1 · Turbine Governor
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