Allison 250-C20B
Service difficulty reports · 1,981
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 = '250C20B' 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 = '250C20B' 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 CA000614012Bolt · loose(CAN) DURING A ROUTINE CLEANING BEHIND HAT RACK AREA, 2 BOLTS ATTACHING A SUPPORT ASSY (ITEM 34, 206 IPC FIG.67-2) WERE FOUND SIGNIFICANTLY LOOSE. AREA WAS INSPECTED FOR FURTHER DEFECTS, NONE FOUND. BOLTS WERE TIGHTENED PER BELL 206 MAINTENANCE MANUAL. A QUSDR CA000606031Fire Detector · loose(CAN) #1 FIRE WARNING LIGHT CAME ON IN CRUISE FLIGHT. PILOT RETARDED THROTTLE TO IDLE & RETURNED TO BASE. AIRCRAFT INSPECTED LOOSE WIRE ON DETECTOR FOUND, WIRE (MEET) TORQUED SYSTEM CHECKED & FOUND SERVICEABLE, AIRCRAFT RETURNED TO SERVICE.SDR 20000818SH001Line · failedCOMPRESSION FITTING PROVIDED WITH PLASTIC LINE FAILED IN ENGINE PLENUM CHAMBER AT FULL POWER DURING FLIGHT CAUSING OIL INGESTION INTO ENGINE CAUSING TURBINE OUTLET TEMPERATURE AND TORQUE SURGE WHEN OIL IGNITED WITH FUEL AIR MIXTURE IN BURNER CAN. FOUR QUART OSDR CA001013016Fuel Control · malfunctioned(CAN) EXTREMELY HIGH LIGHT OFF TEMPERATURE. FUEL CONTROL REPLACED AND TURBINE REMOVED FOR INSPECTION.SDR CA001013013Fuel Control · failed(CAN) FUEL CONTROL UNIT COULD NOT BE ADJUSTED TO STABILIZE THE IDLE SPEED. AFTER THE START THE IDLE WOULD BE 61-62 PERCENT. BRING THE THROTTLE TO 100% AND BACK TO IDLE, THEN THE SPEED WOULD BE 68-72 PERCENT. FURTHER ADJUSTMENT WOULD NOT CORECT THE PROBLEM. ALSSDR AU000384Strap · deteriorated(AUS) TENSION-TORSION (TT) STRAPS DETERIORATED. THE STRAPS WERE DISTORTED AND THE URETHANE COATING ADJACENT TO THE LATCH BOLT BUSHINGS WAS SPLIT REVEALING THE INTERNAL WINDINGS. (X)SDR CA000516001Battery · leaking(CAN) ELT WAS REMOVED FOR ANNUAL INSPECTION AND IT WAS NOTED THAT WHITE POWDER WAS ON OUTSIDE OF BATTERY AND ELT CASE. UPON INSPECTION AFTER BATTERY REMOVAL, A LEAK WAS DETECTED. BATTERY STILL HAD 5 MONTHS LEFT ON ITS LIFE. EXPIRATION, SEPT 2000. BATTERY SDR CA000530019Rod · stripped(CAN) THE THREADS BENEATH THE INNER POSITIONING NUT ON THE INTERCONNECT ROD WHICH LINKS THE CUT OF LEVER (QUADRANT POINTER) TO THE MAIN CONTROL SHAFT HAD FAILED. THIS ALLOWED THE FCU CUTOFF LEVER TO MOVE INTO CUTOFF INITIATING AN UNCOMMANDED ENGINE SHUTDOWN.SDR CA000516015Governor · defective(CAN) PILOT COMPLAINED OF LAGGING GOVERNOR WHICH ALSO TENDED TO UNDERSPEED AND OIVERSPEED AS COLLECTIVE WAS CHANGED AND NOT RECOVER TO THE SET RPM. UPON REMOVAL, THE AME NOTICED SOMETHING WAS NOT QUITE RIGHT AT THE DRIVESHAFT. UPON INPSPECTION, THE EPOXY, CISDR AU000359Turbine · failed(AUS) RH ENGINE TURBINE FAILED. SUSPECT CAUSED BY NO8 BEARING SUMP NUTCOMING LOOSE AND ALLOWING THE NO8 BEARING OIL NOZZLE TO DISLODGE. SUSPECT FAILURE THEN OCCURRED DUE TO FAILURE OF NO8 BEARING.SDR CA000714034Cargo Hook · twisted(CAN) THE PILOT CAME BACK FROM WORK AND REPORTED HE COULD NOT LATCH LOAD ON CARGO HOOK. A VISUAL INSP ON CARGO HOOK EMERG RELEASE CABLE SHOWED THERE WAS TOO MUCH STRAIN ON CABLE THAT CAUSED MECHANICAL RELEASE TO MOVE THE INTERNAL HOOK MECHANISM FROM LATCHED SDR CA000516014Adapter · damaged(CAN) EXCESSIVE DAMAGE TO SPLINES OF ADAPTER AND INNER SPLINES OF THE COMPRESSOR TO TURBINE COUPLING SHAFT. IN SOME CASEA SPLINE TOOTH IS COMPLETELY SHEARED OFF.SDR CA000511004Bushing · loose(CAN) PILOT STARTED AIRCRAFT AND FOUND PEDAL FORCES EXCESSIVE. AIRCRAFT WAS SHUT DOWN. T/R WAS DISASSEMBLED AND IT WAS FOUND THAT ONE OF THE OUTBOARD BUSHING HAD SLID APPROXIMATELY .25 INCH OFF THE INNER SLEEVE AND WAS RUBBING THE OUTBOARD SPACER, LOCATED INSISDR CA000614011Pitch Link · unsafetied(CAN) DURING MAINTENANCE, PERFORMED BELOW THE ENGINE PAN, A TAIL ROTOR FLIGHT CONTROL BOLT WAS FOUND UNFASTENED. T/R ANTI-TORQUE CONTROL TUBE (ITEM NR 21, 206 IPC FIG.67-2) REAR ATTACHMENT BOLT FOUND WITH NUT BACKED OFF, NO COTTER PIN INSTALLED. AIRCRAFT GROSDR CA000505011Shield · cracked(CAN) WHEN COMPLETING CEB A-1370, 1ST STAGE NOZZLE SHIELD INSPECTION, FOUND AREA OF INSPECTION CRACKED.SDR AU000393Heat Shield · cracked(AUS) FIRST STAGE TURBINE NOZZLE HEAT SHIELD CRACKED. FOUND DURING INSPECTION IAW ROLLS ROYCE CEBA-1370.SDR AU000331Blade · cracked(AUS) MAIN ROTOR BLADE CRACKED. BUSHING LOOSE.SDR CA000414009Brush Block · broken(CAN) POST-FLIGHT INSPECTION REVEALED THAT ONE OF THE BRUSHES WAS WORN DOWN TWICE AS MUCH AS THE OTHER VISIBLE BRUSH. UPON REMOVAL, IT WAS THEN NOTED THAT ONE OTHER BRUSH WAS BROKEN AND/OR BURNT OFF. HOWEVER, THE STARTER/GENERATOR WAS STILL FUNCTIONING AS ITSDR CA000518013Pitch Link · unserviceable(CAN) DURING A TAILROTOR (T/R) GEARBOX CHANGE,THE T/R PITCH CHANGE BELLCRANK WAS FOUND DAMAGED. THE DAMAGE WAS CAUSED FROM THE SAFETY WIRE CHAFING NEAR THE PIVOT BEARING. SAFETY WIRE IS FASTENED TO PIVOT BEARING STUD FROM THE T/R GEARBOX.SDR CA000414016Flyweight · damaged(CAN) N1 SPEED DROPPED TO 60 PERCENT GOVERNOR REMOVED AND FOUND THAT SHAFT WAS RESISTANT TO BEING ROTATED, SPECIFIED INTERNAL FLYWEIGHTS AS THE PROBLEM AREA.SDR CA001013007Fuel Control · failed(CAN) FUEL CONTROL UNIT START DE-RICH AND START ACCELERATION SETTINGS AT THE EXTREME CCW POSITIONS. UNIT CAUSING THE ENGINE TO COMPRESSOR STALL DURING START UP.SDR CA000404016Shaft · sheared(CAN) NR TACHOMETER INDICATOR NOT FUNCTIONING. TACHOMETER REMOVED TO FIND THAT THE SHAFT WAS SHEARED. SERVICEABLE TACHOMETER INSTALLED.SDR CA000404009Bevel Gear · broken(CAN) PILOT REPORTED A STRANGE NOISE COMING FROM MAIN ROTOR TRANSMISSION WITH CHIP LIGHT ILLUMINATED. SUBSEQUENT INSPECTION FOUND EXCESSIVE METAL ON CHIP DETECTOR. THE TRANSMISSION WAS DISASSEMBLED ENOUGH TO FIND THE SOURCE OF THE METAL (OUTPUT BEVEL GEAR TOOSDR CA000404007Fuel Control · seized(CAN) IT TOOK SEVERAL ATTEMPTS TO SHUT ENGINE DOWN. THROTTLE SHAFT ON FCU SEIZED. IT WAS FOUND THAT AN OVERSIZE BUSHING HANGING ON THE THROTTLE CAM TO BE THE PROBLEM.SDR LS1R066572Fcu · damagedPART IS RUPTURED. HOLE IN SKID.SDR CA000329021Pinion Gear · worn(CAN) M/R TRANSMISSION RECEIVED FOR INSPECTION. DURING VISUAL INSPECTION, IT WAS NOTED THAT THE INPUT PINION HAD UNCOMMON DAMAGE TO THE DRIVE SPLINES. SUBMITTER SUGGESTED CAUSE COULD BE INCORRECT SHIMMING OF ATTACHING PARTS OR LOSS OF TORQUE TO THE NUT (PN 3SDR CA000317001Support Bracket · cracked(CAN) T/R DRIVESHAFT DAMPER SUPPORT BRACKET AT STA 197.78 HAS TWO HOLES WITH NUTPLATES RIVETED BEHIND TO SUPPORT THE GRAPHITE DAMPER. SPACERS WERE NOT PROPERLY ATTACHED THAT HOLD THE DAMPER TO THE DAMPER SUPPORT BRACKETS AND CAUSED A HOLE TO BE PUNCHED OUT BYSDR CA000317005Gasket · cracked(CAN) LEFT FUEL CELL DOOR ASSY REMOVED FOR ANNUAL/100 HOUR INSPECTION AND A SMALL AMOUNT OF FUEL WAS NOTICED. FUEL QUANTITY SENDER P/N 369D269303-3 WAS REMOVED AND GASKET P/N 15-423 WAS REPLACED.SDR CA000307001Structure · cracked(CAN) SECURING LUGS (P/N D2731) THAT SECURE THE HIGH SKID GEAR STEP ASSY FOUND CRACKED. SUBMITTER SUSPECTED CAUSE OF CRACKS IS IMPROPER TORQUE OF THE NUT AND BOLT WHICH SHOULD BE UP TO 60 INCH/POUNDS. MANUFACTURER HAS BEEN NOTIFIED.SDR CA000317002Bearing · damaged(CAN) WHILE PERFORMING DAILY INSPECTION, THE ENGINEER NOTICED THAT THE TEFLON LINING WAS PROTRUDING ON THE ROD END BEARING OF THE BOOSTED LATERAL CONTROL TUBE BETWEEN SWASHPLATE AND HYDRAULIC UNIT.SDR CA000306028Gearbox · making metal(CAN) GEARBOX MAKING METAL. 3.5 MM SLIVER .040 INCH THICK FOUND ON LOWER CHIP PLUG. SUBSEQUENT GROUND RUNS PRODUCED 1 MM SLIVER .035INCH AND 2 MM SLIVER .040 INCH.SDR CA000412001Drive Shaft · damaged(CAN) UPON REMOVAL OF TAIL ROTOR GEARBOX AND DRIVESHAFT, EXTENSIVE DAMAGE WAS FOUND ON TAIL ROTOR DRIVESHAFT. INVESTIGATION REVEALED THAT THE DAMPER BRACKET WAS BROKEN OFF WHICH ALLOWED THE TAIL ROTOR DRIVESHAFT TO WHIP AND RESULT IN THIS DAMAGE.SDR CA000218010Bearing · spalled(CAN) PREMATURE SPALLING ON INNER RACE OF NR 2 BEARING LEAD TO THE REMOVAL OF THE COMPRESSOR ASSY.SDR AGQA065693Exciter · inoperativeEXCITER INOPERATIVE.SDR CA000215009Brush Block · destroyed(CAN) BRUSHES ARE FAILING PREMATURELY, SUBMITTER SPECIFIED THAT THIS IS A NATIONAL PROBLEM THAT IS NOT ISOLATED TO THIS PN BRUSH OR PN STARTER.SDR 20000405SH028Combustion Liner · crackedDURING HOVERING ON A TRAINING FLIGHT, THE PILOT NOTICED THAT TOT TEMPERATURE WAS HIGHER THAN NORMAL. AFTER TROUBLESHOOTING WHICH INCLUDED CHANGING BLEED VALVE AND CHECKING ANTI-ICE FOR PROPER CLOSING, THERE WAS NO CHANGE. POWER CHECK ON ENGINE INDICATED SUBSSDR AGQA065674Exciter · failedEXCITER IS POWERLESS, WILL NOT EXCITE IGNITER.SDR AGQA065675Exciter · failedEXCITER IS INOPERABLE, WILL NOT EXCITE.SDR 20000412SH019Ignition Lead · chafedDURING POST-FLIGHT, IGNITION LEAD WAS FOUND CHAFING ON THE LOWER B-NUT OF THE PC AIR REFERENCE LINE ON THE GOVERNOR. FURTHER INSPECTION REVEALED THE ADEL CLAMPS FOR THE LEAD AND LINE, AT THAT POINT, WERE MISSING. REPLACED MISSING CLAMPS. (X)SDR AU000201007Blade · damaged(AU) M/R BLADES WERE FOUND TO HAVE DENTS THAT EXCEEDED THE .010 INCH LIMIT AND WERE LOCATED APPROXIMATELY 23-33INCHES FROM THE TIP. M/R BLADES SENT TO AN APPROVED REPAIR FACILITY FOR FURTHER INSPECTION. THE DENTS EXCEEDED THE ALLOWABLE LIMTS. HOWEVER, THE SDR CA000201007Blade · damaged(CAN) M/R BLADES WERE FOUND TO HAVE DENTS THAT EXCEEDED THE .010 INCH LIMIT AND WERE LOCATED APPROX 23 INCH - 33 INCHES FROM THE TIP. M/R BLADES SENT TO AN APPROVED REPAIR FACILITY FOR FURTHER INSPECTION THE DENTS EXCEEDEDTHE ALLOWABLE LIMTS. HOWEVER THE LEADISDR AGQA065669Bleed Valve · failedBLEED VALVE STALLED IN-FLIGHT.SDR AGQA065670Governor · fluctuatedGOVERNOR IS FLUCTUATING IN POWER.SDR CA000128030Brush Block · broken(CAN) WHILE PERFORMING 100 HR INSPECTION ON STARTER/GEN, A BRUSH LEAD WAS FOUND BROKEN AND ANOTHER BADLY DAMAGED. SUBMITTER STATED THIS IS THE 3RD OCCURRENCE IN THE LAST 3 MONTHS.SDR 2000ZZZX727Governor · malfunctionedIN CRUISE FLIGHT, THE POWER TURBINE ROTOR DROOPED TO 90 PERCENT AND WOULD NOT RECOVER. THE PILOT LOWERED COLLECTIVE, RECOVERED ROTOR SPEED AND DID A POWER ON RECOVERY.SDR ERAA065953Heat Shield · mismanufacturedNEW HEAT SHIELD WITH OUTER BAND TOO THICK.SDR HEEA065981Tie Bolt · mismanufacturedRECEIVING INSPECTION REVEALED FREE LENGTH .0005 INCH OVER SERVICEABLE LIMITS.SDR AU000128065Float Bag · ruptured(AU) WHILE INFLATING FLOAT BAG TO INSPECT FOR FUNCTIONING, THE FLOAT RUPTURED AT THE FIRST OR SECOND COMPARTMENT FROM THE FRONT. IT APPEARS THAT THE RELIEF VALVES WERE NOT RELIEVING AT THE PROPER PRESET PRESSURES.SDR CA000128065Float · ruptured(CAN) WHILE INFLATING FLOAT BAG TO INSPECT FOR FUNCTIONALLY, THE FLOAT RUPTURED AT THE FIRST OR SECOND COMPARTMENT FROM THE FRONT. IT APPEARS THAT THE RELIEF VALVES WERE NOT RELIEVING AT THE PROPER PRESET PRESSURES.SDR ERAA065950Combustion Case · misoverhauledCOMBUSTION CASE REPAIRED AND RETURNED WITH AIR TUBE BOSS RETAINING RING NOT BEING MACHINED. COULD NOT BE INSTALLED ON AIRCRAFT.
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