Allison 250-C30P
Service difficulty reports · 646
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 = '250C30P' 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 = '250C30P' 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 CA190528020Blade · damaged(CAN) DURING A ROUTINE DAILY INSPECTION OF A BELL 206L-4 THE PILOT/ENGINEER NOTED THAT A COVER PLATE ON THE BOTTOM OUTBOARD END OF ONE OF THE MAIN ROTOR BLADES HAD BECOME DEFORMED AND BULGED AWAY FROM THE BLADE. UPON CLOSER INSPECTION IT WAS NOTED THAT IT LOOKSDR CA190526001Combustion Liner · damaged(CAN) DURING CRUISE FLIGHT A LOUD HUMMING NOISE BECAME AUDIBLE. NO POWER LOSS OR ABNORMAL INDICATIONS OCCURRED AT THIS TIME ALTHOUGH IT WAS NOTED THAT TOT WAS A LITTLE HIGHER THAN NORMAL. THE PILOT LANDED THE AIRCRAFT AND DROPPED OFF PASSENGERS AND CONTINUED SDR EVCA201810181Flex Hose · rupturedUPON START UP PILOT NOTED GRINDING NOISE COMING FROM ENGINE COMPARTMENT. PILOT NOTED OIL LEAK. THE BASE AMT INSPECTED AND FOUND ENGINE OIL LINE RUPTURED AND METAL CHIPS ON ENGINE CHIP DETECTOR. DUE TO THE OIL LINE RUPTURE. IT IS BELIEVED THE ENGINE WAS OIL STASDR W7O2018F00000Blade · damagedTAIL ROTOR BLADE HAS A TOTAL TIME OF 1821.3 HOURS, UPON AN INSPECTION IT WAS DISCOVERED THAT TAIL ROTOR BLADE PN 2062200-301 SN 778 SHOWED SIGNS OF DEBONDING AND CRACK DURING VISUAL INSPECTION. BLADE WAS REMOVED FROM HUB ASSEMBLY AND SENT TO MANUFACTURE FOR SDR W7O2018F00001Blade · damagedTAIL ROTOR BLADE HAS A TOTAL TIME 1821.3 HOURS, UPON AN INSPECTION IT WAS DISCOVERED THAT TAIL ROTOR BLADE PN 2062200-301, SN 777 SHOWED SIGNS OF DEBONDING AND CRACKS DURING VISUAL INSPECTION. BLADE WAS REMOVED FROM HUB ASSEMBLY AND SENT MANUFACTURE FOR EVALUSDR EVCA201702261Combustion Case · crackedOUTER COMBUSTION CASE FOUND TO BE CRACKED WHILE PERFORMING CEB 72-3303SDR EVCA2017030100051Fuel Control · bindingPILOT REPORTED THROTTLE WAS UNABLE TO BE MOVED. MECHANIC FOUND FUEL CONTROL THROTTLE LEVER TO BE BINDING PREVENTING THROTTLE FROM MOVING.SDR CA151023005Converter · failed(CAN) IN FLIGHT, POWER TO THE CAMERA BECAME INTERMITTENT. AFTER RECYCLING ENG MASTER, POWER WAS NOT RESTORED. ON RETURNING TO THE AIRPORT SMOKE FUMES WERE NOTICED IN THE COCKPIT. REQUEST FOR IMMEDIATE LANDING FROM THE TOWER WAS ACCOMMODATED. MACHINE LANDEDSDR CA160119009Rotor · separated(CAN) ACFT WAS ON AN AERIAL APPLICATION MISSION WHEN IT WAS REQUIRED TO MAKE A FORCED LANDING. INITIAL REPORTS STATE THE TAIL ROTOR SEPARATED FROM THE ACFT.SDR HEER20150923715Bearing · spalledENGINE REMOVED 9-10-15 DUE TO METAL IN OIL. REASON FOUND TO BE PTO BEARING SPALLING OUTER RACE. INSTALLED NEW PTO BALL BEARING.
SDR HEER20150918705Bearing · spalledENGINE REMOVED 7-13-15 DUE TO METAL IN OIL. PTO BALL BEARING FOUND SEVERELY SPALLED ON INNER RACE AND SCRATCHES ON BALLS. REPLACED WITH NEW PTO BALL BEARING.SDR CA150813008Fuel Control · malfunctioned(CAN) DURING LANDING THE PILOT REPORTED AN UNCOMMENTED SURGE OF 10 PERCENT TORQUE, AND A SLIGHT YAW. THE SURGE DID NOT IMPEAD LANDING OF THE ACFT, OR EXCEED ANY PARAMETERS. ONCE THE ACFT LANDED THE ENGINE WOULD NOT STABLIZE, AND CONTINUED TO SLIGHTLY SURGE UNSDR 2015FA0000374Bearing · failedDURING HOVER ON A LONG-LINE OPERATION, THE ENGINE CHIP LIGHT ILLUMINATED. PRECAUTIONARY LANDING PERFORMED AND GRAINS OF METAL WERE FOUND ON THE RT UPPER ENGINE CHIP DETECTOR. FOUND TO BE THE NR 1 BEARING IN THE COMPRESSOR. THIS IS THE OLD, ORIGINAL PART THASDR EVCA20150717001Mast · corrodedINTERIOR DIAMETER SURFACE OF MAST POLE SHOWING SIGNS OF CORROSION UNDERNEATH THE PAINT COATING.SDR YH7R2015FA0000450Shunt · failedENGINE FLAMED OUT DURING FLIGHT. INSPECTION OF ACFT FOUND THAT THE FUEL SHUTOFF VALVE WAS CYCLING FROM THE OPEN POSITION TO THE CLOSED POSITION WHEN BATTERY POWER, POWER WAS APPLIED AND THE FUEL SHUT OFF VALVE SWITCH WAS PLACED IN THE OPEN POSITION. IT WAS DSDR CA151019006Support · cracked(CAN) THE PILOT COMPLAINED OF HAVING FELT A SEVERE VIBRATION ON PEDALS AND SHAKING OF INSTRUMENTS CONSOLE. MAINTENANCE PROCEED TO INSPECT THE ACFT AND FOUND THAT THE TAIL ROTOR GEAR BOX SUPPORT HAD BROKEN OFF ON ONE STUD. NORMAL LANDING WAS PERFORMED WITHOUSDR 2015F00070Shaft · failedTAILROTOR DRIVE SHAFT FAILED AT NR 5 SECTION. ACFT LOST ALTITUDE FROM 40 FOOT HOVER AND SPUN TO GROUND AND WAS DAMAGED. NO INJURY'S.SDR CA150521001Release Cable · broken(CAN) INADVERTENT RELEASE OF EXTERNAL LOAD DURING FLIGHT. POST FLIGHT INSPECTION REVEALED BROKEN RELEASE CABLE.SDR CA150520010Pin · sheared(CAN) TRAINING ACFT WITH DUAL CONTROLS AND AAI LOCKOUT PEDAL STC SH 96-92 INSTALLED. ON A TRAINING FLIGHT DURING AUTO ROTATION, ATTEMPTING POWER RECOVERY, TRAINEE HELD CONTROLS TIGHT WHILE TRAINING CAPTAIN ATTEMPTED TO INPUT FULL LEFT PEDAL. DURING PEDAL INPSDR PG9R2015FA0000193Fcu · malfunctionedFERRY FLIGHT UNDER CFR PART 91. APPROXIMATELY 15 MINUTES INTO FLIGHT. STRAIGHT AND LEVEL CRUISE AT 80 PERCENT TORQUE, PILOT HEARD THE TORQUE WARNING HORN AND IMMEDIATELY AFTER THE ENGINE SPOOLING UP, PILOT LOWERED THE COLLECTIVE AND NOTED THE TORQUE DECREASINGSDR CA150218007Turbine · exploded(CAN) THE ACFT WAS ENROUTE TO THE REPAIR STATION AND 10 MINUTES OUT THE PILOT ENCOUNTERED A HUGE EXPLOSION LIKE SOUND WITH A MASSIVE LT YAW OF THE ACFT. STABILIZED THE ACFT AND SUCCESSFULLY CONDUCTED AN AUTOROTATION AND EMERGENCY LANDING. THE TURBINE SECTIONSDR CA141020002Fuel Control · failed(CAN) PILOT WAS UNABLE TO START HELICOPTER FOR 3RD SCHEDULED FLIGHT OF THE DAY. AME FOUND THAT THERE WAS NO FUEL FLOW TO THE ENGINE FUEL NOZZLE. TROUBLESHOOTING FOUND FUEL CONTROL UNIT TO BE AT FAULT HAVING NO FLOW FROM FUEL OUTLET PORT. FUEL CONTROL WAS REMSDR PBVA2014092500000Warning Light · illuminatedAFTER 30 MINUTES IN CRUISE FLIGHT, TOT SUDDENLY WENT TO 840 CA, PRECAUTIONARY LANDING WAS MADE AND MAINTENANCE WAS CALLED. TOT SYSTEM WAS TESTED AND FOUND TO BE WORKING NORMAL. NO EXTERNAL DAMAGE WAS NOTED TO ENGINE. ENGINE WAS R & R AND SENT TO ENGINE SHSDR CA140805003Shaft · failed(CAN) AIRCRAFT OPERATED NORMALLY THROUGHOUT THE DAY UNTIL START OF LAST SCHEDULED FLIGHT. ENGINE SPOOLED UP NORMALLY, IGNITOR AUDIBLE BUT NO DROP IN FUEL PRESSURE OBSERVED WHEN THROTTLE ROLLED UP. ENGINE FAILED TO LIGHT OFF AND START ABORTED. INVESTIGATION FSDR CA140502002Bearing · cracked(CAN) BOTH INBD FEATHERING BEARINGS WERE FOUND TO BE CRACKED. BLADES REMOVED FROM SERVICE.SDR CA140325006Bearing · misinstalled(CAN) THE FEATHERING BEARING WAS STAKED FAR TOO TIGHT. CAUSING RESTRICTION ON TAIL ROTOR CONTROL. THIS WAS NOTED ON A PRE FLIGHT POST MAINTENANCE INSPECTION. THE BLADE ARE THE VAN HORN BLADES INSTALLED UNDER STC SH10-22. ASSY REMOVED AND NEW ASSEMBLY INSTALLSDR CA140314017Fuel Nozzle · malfunctioned(CAN) ENGINE VERY SLOW TO ACCELERATE THROUGH 40-50 PERCENT N1 DURING START PROCEDURE. ENGINE START SYS TROUBLESHOT AND FOUND FUEL NOZZLE TO BE CAUSE OF ISSUE. NOZZLE REMOVED AND RETURNED TO REPAIR FACILITY FOR REPAIR.SDR CA140127001Bolt · sheared(CAN) IN FLIGHT PILOT COULD FEEL VIBRATION IN THE AIRFRAME, DECIDED TO LAND. ENGINEER INSPECTED AIRFRAME INCLUDING REMOVAL OF DRIVESHAFT COVERS AND COWLS AS REQUIRED AND A DETAILED INSPECTION OF THE TAIL ROTOR AND DRIVE SYS ACCOMPLISHED. A TEST FLIGHT WAS ACSDR CA140109003Plug · leaking(CAN) ACFT HAD JUST DEPARTED FROM AN OFFSHORE PLATFORM WHEN THE T/R PEDALS LOCKED UP AT APPROXIMATELY MID-TRAVEL. PILOT CONTINUED ON AND MADE AN UNEVENTFUL EMERGENCY LANDING. AT THIS TIME, T/R FLAPPING BEARINGS ARE SUSPECT, BUT INITIAL INSPECTION HAS REVEALEDSDR 7ALA2013F00000Starter Gen · failedSTARTER GENERATOR FAILED IN FLIGHT. ACFT LOST POWER FOR BOOST PUMPS, LIGHTING AND RADIOS. ACFT LANDED AT NEAREST AVAILABLE AIRPORT. NO DAMAGE TO ACFT. BRUSH DETERIORATION SEEMS TO BE THE CAUSE.SDR CA130830013Blade · cracked(CAN) CRACK FOUND ON MAIN ROTOR BLADE LOWER SKIN THAT EXTENDS FROM THE T/E CHORD-WISE TOWARDS THE SPAR. CRACK IS APPROXIMATELY 9" IN LENGTH AND LOCATED 99.0" INBD FROM BLADE TIP. DAYLIGHT WAS VISIBLE THROUGH HALF OF THE CRACK LENGTH. THIS BLADE SN IS NOT AFSDR CA130805019Blade · delaminated(CAN) THE PILOT WAS CARRYING OUT HIS DAILY CHECK ON THE TAIL ROTOR BLADES. HE NOTICED A SOFT AREA BY FEEL. AN ENGINEER CARRIED OUT A TAP TEST AND FOUND THE DELAMINATION 1.5" FROM TIP AND .5" FROM ABRASION STRIP. APPROXIMATE AREA DELAMINATED, 8" SQ, 4 X 2". SDR CA130805020Blade · delaminated(CAN) THE PILOT WAS CARRYING OUT HIS DAILY CHECK ON THE TAIL ROTOR BLADES. HE NOTICED A SOFT AREA BY FEEL . AN ENGINEER CARRIED OUT A TAP TEST AND FOUND THE BLADE HAD AN DELAMINATION 2" FROM TIP AND .5" FROM ABRASION STRIP. APPROXIMATE AREA DELAMINATED 10.5SDR YTRA2013073000002Duplex Bearing · spalledMAIN ROTOR TRANSMISSION DUPLEX BEARING, BEARING SET SPALLING.SDR CA130722009Blade · delaminated(CAN) AN AME NOTICED T/R BLADE HAD SOME PAINT MISSING. FURTHER INVESTIGATION THE AME FOUND NEAR THE TIP OF THE T/R BLADE A DELAMINATION HAD OCCURRED ON THE ONE SIDE OF THE T/R BLADE THROUGH A TAP TEST. HE INSPECTED THE SECOND T/R BLADE AND FOUND A DELAMINATISDR EVCA20130722045Engine · power lossPILOT STATED AFTER TURNING FINAL TO BASE, THE ACFT EXPERIENCED A PARTIAL ENGINE LOSS OF POWER (SIMILAR TO ROLLING THE ENGINE TO FLIGHT IDLE). THE ACFT WAS APPROX 80 TO 100 FT ABOVE THE GROUND AT ABOUT 40 KTS. THE PILOT MADE AN EMERGENCY LANDING WHICH RESULTESDR YTRA52117/175/178Mast · mismanufacturedMAST POLE MFG INCORRECTLY. SCALLOP FOR DRIVE LINK THROUGH BOLT MACHINED IN WRONG LOCATION.SDR 2013F00141Support · fracturedENGINE WAS REMOVED FROM THE ACFT DUE TO A CHIP LIGHT. ON REMOVAL OF THE COMPRESSOR FOUND THAT THE REAR SUPPORT WAS THE SOURCE OF THE METAL. THE AREA OF THE REAR SUPPORT ADJACENT TO THE NR 2 BEARING RETAINING RING GROOVE WAS FOUND TO BE FRACTURED WITH PIECES SDR 2013FA0000424Bearing · failedA/C WAS ON A BRAVO TOUR, PILOT HEARD A BANG FOLLOWED BY A POWER LOSS AND ENTERED A AUTOROTATION TO THE RIVER EMERGANCY FLOATATION ACTIVATED AND A LANDING WAS MADE. FOUND NR 2 ENGINE COMPRESSOR BEARING FAILED.SDR ULXR201306040001Mast · mismanufacturedMAIN ROTOR MAST INCORRECTLY MANUFACTURED. SWASHPLATE AND MAIN ROTOR HUB PITCH HORNS DO NOT LINE UP CORRECTLY.SDR CA130514006Battery · failed(CAN) ACFT WOULD NOT START. BATTERY REPLACED. BATTERY WAS IN SERVICE FOR 66 HRS OVER 5 MONTHS.SDR YTRA2013073000001Mast · mismanufacturedMAST POLE MANUFACTURED INCORRECTLY. SCALLOP FOR DRIVE LINK THROUGH BOLT MACHINED IN WRONG LOCATION. MAST POLE HAS 44 RIN.SDR CA130411004Drive Shaft · cracked(CAN) OPERATOR FOUND 2 SMALL CRACKS ON THE DRIVESHAFT FROM RIVET HOLE IN FLANGE ADAPTER DRIVESHAFT WAS REPLACED.SDR 2013FA0000087Circuit Breaker · unserviceableDURING FLIGHT THE PILOT NOTED SMOKE EMANATING FROM THE AFT CABIN AREA AND MADE AN EMERGENCY LANDING IN A FIELD LOCATION. AFTER TROUBLESHOOTING OF THE SYS, NOTED THE CIRCUIT BREAKER WAS IN THE OPEN POSITION AND THEREFORE DID NOT TRIP AS REQUIRED AFTER AFT EVAPSDR CA121205005Strap · failed(CAN) UPON REMOVAL OF THE ELT FOR ANNUAL RECERTIFICATION, THE VELCRO STRAP THAT HOLDS THE ELT INTO ITS MOUNTING TRAY WAS FOUND TO BE UNSERVICEABLE. THE MATERIAL HAD DEGRADED SUCH THAT PULLING ON THE VELCRO TO UNFASTEN IT CAUSED IT TO TEAR LONGITUDINALLY. WHESDR ALGA2012101801Transceiver · smokeRADIO LOST DISPLAY, THEN STARTED SMOKING ON START UP. R & R VHF TRANSCEIVER.SDR ALGA201210126702Drive Shaft · crackedSHAFT AFT RIVETED FLANGE IS CRACKED.SDR CA121107005Case · failed(CAN) FAILED OUTER COMBUSTION CASE.SDR ALGA2012091901Bearing · wornFOUND TAILROTOR HUB & BLADE ASSY ONE BEARING WORN.SDR ALGA2012092105Rotor · wornHARD TO TURN N2 ROTOR. DISASSEMBLY IAW MANUAL, COMPLIED WITH PRELIMINARY FOUND GRAPHITE ON 9-12/13-18 SUMP COVER BORE LIFTTING CAUSE HEAVY RUBBING TO SEAL KNIVES CAUSE N2 ROTOR HARD TO TURN. REPLACED SUMP COVER ASSY.
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