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 2016FA0000153Governor · inoperativeEPOXY CAME LOOSE FROM END OF DRIVE SHAFT. CLIP CAME LOOSE ALLOWING DRIVE SHAFT SPLINES TO WEAR AND CAUSE EXCESSIVE DROOPING DURING ENGINE POWER CHANGES.SDR 2016FA0000154Governor · inoperativeEPOXY CAME LOOSE FROM END OF DRIVE SHAFT. CLIP CAME LOOSE ALLOWING DRIVE SHAFT SPLINES TO WEAR AND CAUSE UNSTABLE GOVERNOR CONTROL.SDR CA160302016Pressure Switch · failed(CAN) FUEL PRESSURE SWITCH, FOUND TO LEAK DURING A 300HR CAUTION LIGHT FUEL PRESSURE SWITCH TEST. UNIT WAS THEN DISASSEMBLED AND FOUND THE BLUE SILICONE COATING ON THE DIAPHRAGM WAS TORN.SDR CA160215022Coupling · broken(CAN) DURING A SCHEDULED 100/300 HR INSPECTION, THE OUTER DISC OF A 10 DISC PACK WAS DISCOVERED BROKEN THE EDGE RUB INDICATES THAT THE DISC HAS PROBABLY BEEN BROKEN FOR SOME TIME THE ACFT TT IS 9444.3. THE BROKEN PART IS UNKNOWN TIME IN SERVICE THE APPEARANCESDR CA160215013Support · broken(CAN) DURING INSPECTION OF FRONT PEDAL SUPPORT IT WAS NOTED THAT BOTH UPPER TANGS OF THE LEFT PEDAL SUPPORT WERE BROKEN OFF. THERE MAY BE SOME INDICATIONS THAT A TANG CRACKED AND THEN SNAPPED ALSO BREAKING THE OTHER UPPER TANG. THE LOWER TANGS OF THE PEDAL SUPSDR CA160203023Burner Can · cracked(CAN) PILOT NOTED HIGHER THEN NORMAL TOT TEMPERATURES IN FLIGHT, PILOT LANDED AT THE HANGER AND UPON FURTHER INVESTIGATION FOUND RT BURNER CAN ARMPIT CRACKED.SDR CA160120019Abrasion Strip · missing(CAN) MAIN ROTOR BLADE ABRASION STRIP SEPARATED FROM BLADE WHILE IN FLIGHT. VIBRATION CAUSED BY IMBALANCED ROTOR DISK REQUIRED RETURN TO BASE. ACFT WAS SHUTDOWN. NO FURTHER DAMAGE TO ACFT NOTED. REMAINING 4 ROTOR BLADES HAVE SAME HRS FLOWN AND HAVE BEEN RESDR CA160118014Snap Ring · damaged(CAN) ENGINE CHIP LIGHT ILLUMINATED DURING FLIGHT. UPON ENGINE DISASSEMBLY DISCOVERED THE SNAP RING THAT HOLDS THE SPUR ADAPTER GEARSHAFT TO THE BACK OF THE COMPRESSOR TO BE MANGLED. SNAP RING GROOVE HAD SINCE WORN FLAT.SDR R81R2016FA0000014Abrasion Strip · departedPILOT REPORTED NOISE THEN IMMEDIATE SEVERE VIBRATION WHILE TRANSITIONING FROM HOVER TO FWD FLIGHT APPORXIMATELY 12" ABOVE GROUND TO ROTOR. ACFT WAS LANDED WITHOUT INCIDENT. UPON ARRIVAL, ACFT WAS INSPECTED FOR ABNORMALITIES. FOUND MAIN ROTOR BLADE L/E ABRASDR DCGA2015FA0000520Engine · making metalENGINE CHIP LIGHT ILLUMINATED DURING TOUR FLIGHT. THE PILOT LANDED ACFT AND CALLED MAINTENANCE. MAINTENACE FOUND METAL FLAKE MEASURING LESS THAN .03125 ON UPPER AND LOWER ENGINE CHIP PLUGS. AFTER CLEANING THE PLUGS A 30 MINUTE GROUND RUN WAS PERFORMED AND THSDR IAVA2016F00016Compressor · defectiveINITIATED A NORMAL TAKEOFF TO THE SOUTH FROM TB-45. APPROXIMATELY 3-5 SECONDS AFTER INITIATION, A LOUD BANG WAS HEARD WITH ACCOMPANING AIRFRAME SHUTTER. ABORTED TAKE OFF. SECOND BANG AND SHUTTER FOLLOWED AS ACFT SETTLED TO THE GROUND.SDR 2015FA0000494Engine · making metalDURING GROUND RUN AFTER THE FIRST START OF THE DAY THE ENGINE CHIP LIGHT ILLUMINATED. MAINTENANCE INSPECTED THE UPPER AND LOWER ENGINE PLUGS AND FOUND 1 SLIVER ON THE UPPER PLUG. A 30 MINUTE GOUND RUN WAS PERFORMED AND THE PLUGS WERE RECHECKED AND FOUND CLEANSDR CA151014004Guide · chafed(CAN) DURING A 100 HR INSPECTION IT WAS FOUND THAT THE STRUT FAIRING GUIDE HAD WORN A GROOVE INTO THE STRUT. JUST BELOW THE ELBOW. THE GROOVE IS DETERMINED TO BE BEYOND REPAIR.SDR CA150917008Blade · debonded(CAN) DURING SCHEDULED INSPECTION THE L/E EROSION STRIP WAS FOUND DEBONDED DURING CLEANING PRIOR TO INSPECTION, AS IT CRINKLED WITH FINGER PRESSURE.SDR CA150918003Governor · malfunctioned(CAN) DURING ACFT RUN UP AND PRE TAKEOFF CHECKS THE PILOT WAS UNABLE TO OBTAIN FULL MAIN ROTOR RPM. THE ACFT WAS SHUTDOWN AND MAINTENANCE CONTACTED. THE AME FOUND THE ENGINE GOVERNOR ARM TO BE SEIZED. THE ENGINE GOVERNOR ASSEMBLY WAS REPLACED AND THE ACFT RETSDR 2015FA0000446Fork · crackedTHE ACFT WAS PERFORMING AERIAL APPLICATION UNDER RESTRICTED CATEGORY. PRIOR TO 9/8/2015, THE PILOT REPORTED THE ACFT FLEW SMOOTH. PILOT REPORTED THAT THE LAST FLIGHT ON 9/7/2015 THE ACFT DEVELOPED A SLIGHT LATERAL VIBRATION. THE NEXT MORNING ON 9/8/2015, HESDR CA150910011Vane · missing(CAN) A ENGINEER WAS CALLED TO THE HELICOPTER DUE TO A DEFECT OF LACK OF POWER IN THE POWER ASSURANCE CHECK. THE ENGINEER CARRIED OUT A COMPRESSOR WASH STILL LACK OF POWER. THE ENGINEER REMOVED THE COMBUSTION CASE AND FOUND PART OF THE COMPRESSOR CASE HALF STSDR CA150812006Chip Detector · failed(CAN) DURING SCHEDULED INSPECTION CHIP DETECTOR PLUG, P/N 23088398, WAS FOUND TO HAVE NO MAGNETIC PROPERTIES. THERE ARE NO INSTRUCTIONS FOR CONTINUED AIRWORTHINESS REQUIRING CHECK OF THE MAGNETIC PROPERTIES OF THE PLUG.SDR CA150812005Bracket · cracked(CAN) STROBE BRACKET CRACKING AT JUST AFT OF MOUNTING POINT. IF IT DEPARTED THE AIRCRAFT THE STOBE ASSY WOULD GO INTO THE TAIL ROTOR.SDR CA150812004Horn · failed(CAN) LOW ROTOR HORN FAILED, REMAINED QUIET AT SHUTDOWN.SDR CA151117023Discharge Tube · cracked(CAN) PILOT NOTICED ON LANDING A HIGHER THEN NORMAL TOT. INVESTIGATION FOUND THAT THERE WAS A CRACK FOUND IN THE DISCHARGE TUBE.SDR CA150804004Spring · broken(CAN) FOLLOWING THE SECOND GROUND RUN AND TEST FLIGHT FOLLOWING A TURBINE CHANGE THE PILOT MENTIONED TO THE AME ONBOARD THAT THE THROTTLE FELT A LITTLE STIFF WHEN ROLLING DOWN FROM 100%. THE AME THEN GOT OUT TO CHECK AND NOTICED THE SPRING WAS IN A DIFFERENT PSDR K2D2015F00000Pump · failedDURING CRUISE FLIGHT, THE MAIN ROTOR TRANSMISSION LOW OIL PRESSURE LIGHT ILLUMINATED. AN UNSCHEDULED PRECAUTIONARY LANDING WAS MADE IN AN OPEN FIELD WITHOUT INCIDENT. FOLLOWED HELICOPTER MM TROUBLESHOOTING PROCEDURES AND FOUND THE MAIN ROTOR TRANSMISSION OILSDR CA150617020Blade · damaged(CAN) PILOT WAS ON APPROACH BACK TO FORESTRY BASE, 1.5 MILES WHEN HE AND HIS PASSENGER HEARD A LOUD POP. THEY LOOKED AROUND THE CABIN BUT FOUND AND FELT NOTHING. UPON LANDING AND SHUTDOWN, A WHISTLING SOUND WAS HEARD FROM THE BLADES. AN INVESTIGATION BY THE PISDR CA150511010Bearing · failed(CAN) ROTOR RPM WANDERING. REMOVED GOVERNOR, FOUND BEARING PIECES IN CAVITY.SDR MKHA20150507001Tail Rotor · brokenDURING A FLIGHT THE PILOT EXPERIENCED EXCESSIVE VIBRATION. THE PILOT MADE A PRECAUTIONARY LANDING & NOTIFIED MX. MX DISCOVERED THE PITCH HORN ON THE OTBD TAIL ROTOR BLADE WAS BROKEN OFF.SDR CA150504003Gear · cracked(CAN) AN EXCESSIVE OIL LEAK AT TURBINE/GEARBOX JOINT WAS DISCOVERED DURING A DAILY INSPECTION. FURTHER INVESTIGATION SHOWED THE GEARBOX FLANGE APPEARS TO BE CRACKED. THE ENGINE GEARBOX WAS REPLACED AND SENT FOR REPAIRS. THE GEARBOX TSO 4552.9 AND TSN 11,440.5SDR DXMR202002190164Sending Unit · inaccurateREPLACED FUEL QUANTITY SENDING UNIT, SN 2366 TT THIS UNIT 447.3 HOURS, INSTALLED 31 OCT 2014. SINCE NEW SENDER WAS SHOWING HIGHER FUEL LEVELS THAN AVAILABLE IN TANK. HAS BEEN A REOCCURRING PROBLEM WITH THESE SENDING UNITS WITH MULTIPLE ROTORCRAFT.SDR CA150428003Impeller · failed(CAN) 2 MILES FROM FINAL PILOT HEARD A LOUD BANG. ALL GAUGES MONITORED AND SITUATION ASSESSED. ENGINE OIL TEMPERATURE SLOWLY STARTED RISING. ACFT LANDED SAFELY. DURING ENGINE SHUTDOWN PROCEDURE ENGINE OIL TEMPERATURE ROSE TO APPROXIMATELY 140C. AME WAS SENTSDR CA150331007Blade · damaged(CAN) DURING REGULAR 100HR INSPECTION, TAP TEST OF THE MAIN ROTOR BLADE DISCOVERED A VOID. THE BLADE HAS BEEN SENT FOR REPAIR.SDR CA150220002Vent Line · leaking(CAN) DURING FORWARD FLIGHT WITH UNDERSLUNG LOAD AND SIGNIFICANT NOSE DOWN ATTITUDE FUEL ODOR WAS NOTICED IN CABIN. ACFT WAS RETURNED TO BASE AND GROUNDED FOR TROUBLESHOOTING. TROUBLESHOOTING WAS COMMENCED LATER IN THE WEEK AND FUEL VENT LINE LOCATED IN VERTISDR 9EKA02132015007Line · looseFLYING MAIL RUN, THE MAG PLUG NR 2 LIGHT ILLUMINATED. ATTEMPTED TO PULSE THE CHIP WITHOUT SUCCESS. NOTICED NR 2 ENG TOT RISING, MAX OBSERVED 748 DEGREES C. BROUGHT NR 2 ENG THROTTLE TO IDLE & MONITORED ENG OIL PRESS WHICH WAS DECREASING. AS THE NR 2 ENG OISDR CA141224005Engine · malfunctioned(CAN) HELICOPTER WAS STARTED FOR A GROUND RUN. IT WAS NOTED THAT DURING THE GROUND RUN, MAIN ROTOR BLADES STARTED TO TURN. THEN THE MAIN ROTOR BLADES STARTED TO DEACCELERATE WITH NO THROTTLE ADJUSTMENT. WE ARE TROUBLESHOOTING THE OBSERVATION DEFECT.SDR CA141210006Tie · missing(CAN) LOWER TYWRAP HOLDING SWASHPLATE BELLOWS FOUND MISSING ON POST FLIGHT INSPECTION THAT WAS INSTALLED IAW ASB-BO-105-40A-107R1.SDR CA141127008Valve · failed(CAN) DUE TO THE DURATION OF THE FLIGHT, PILOT FELT HE WAS GETTING AN ERRONEOUS FUEL QTY READING AND DECIDED TO LAND AND REFUEL. UPON REMOVING THE FUEL CAP, HE IMMEDIATELY OBSERVED THAT THE INTERNAL FUEL CELL HAD COLLAPSED AS IT WAS MOSTLY BLOCKING THE FUEL FSDR CA141022010Blade · debonded(CAN) DURING INSPECTION CRACKS WERE NOTED IN THE SEALANT COVERING THE ROOT FITTING TO DOUBLE ADHESIVE. SEALANT WAS REMOVED TO EXPOSE THE ADHESIVE BOND LINE. ROOT FITTING ATTACH BOLTS WERE LOOSENED TO RELIEVE THE FITTING. A DISBOND IN THE ROOT FITTING TO DOUSDR 2014FA0000586Chip Detector · contaminatedDURING A RTB FLIGHT AT 700 AGL, ACFT MADE A PRECAUTIONARY LANDING ON A FOOTBALL FIELD DURING A NONSTOP FLIGHT DUE TO MASTER CAUTION LIGHT WITH A CORRESPONDING ENGINE CHIP INDICATION. NO ABNORMAL ENGINE PERFORMANCE WAS NOTED AND ENGINE OIL TEMPERATURES AND PRESDR 2014FA0000598Combustion Case · crackedPILOT STATED THE TOT HAS INCREASED 30+ DEGREES C FROM THE NORMAL CRUISE OPERATING TEMPERATURE. NO DEGRADATION IN POWER WAS MENTIONED OR NOTED. ON INSPECTION, FOUND A 2.75 INCH CRACK ON THE RT SIDE OF THE OUTER COMBUSTION CASE JUST BELOW THE SPLIT WELD LINE WSDR 9EKA20140806008Compressor · stalledWHILE FLYING A DISTANCE OF 100NM, FOR THE COMPLETION OF THE CONTRACT FLIGHT I HAD TWO COMPRESSOR STALLS. THE FIRST HAPPENED AT A CONSTANT POWER SETTING OF 80% TORQUE, 1000' PA, CAVU WITH WINDS 150/10 KTS, A HEADWIND. HEARD A LOUD BANG FOLLOWED BY YAWING OF THSDR CA140811005Turbine · making metal(CAN) DURING POST INSTALLATION GROUND RUNS AFTER A SCHEDULED TURBINE CHANGE THERE WERE THREE ENGINE CHIP INDICATIONS ON BOTH THE UPPER AND LOWER CHIP DETECTOR. FIRST CHIP INDICATION WAS BURNED, CHIP RETURNED IN 10 SECONDS, ENGINE SHUT DOWN, FOUND TWO SMALL HAISDR CA140729003Shaft · loose(CAN) NR 2 ENGINE TORQUE INCREASED TO 95 PERCENT + RPM INCREASED TO 103 PERCENT DURING FLIGHT, WITH NR 1 ENGINE TORQUE DROPPING TO 10 PERCENT FOR 2 SEC. ENGINES WERE TRIMMED BACK TO WITHIN ENGINE PARAMETERS FOR DURATION OF FLIGHT. NR 2 ENGINE FCU SHAFT FOUNDSDR IGAL2014FA0000404Support Bracket · defectiveDURING SCHEDULED 100 HOUR INSPECTION AND COMPIANCE WITH ASB206-12-129, REV C DATED 09 JUNE 2014 FOR INSPECTION ONLY, WHICH IS DIRECTLY APPLICABLE TO THE PART THAT WAS FOUND DEFECTIVE, THE SUPPORT BRACKET WAS FOUND BOTH CRACKED AND BROKEN. MFG WAS NOTIFIED AT SDR CA140604010Tube · melted(CAN) DISCOVERED DURING ROUTINE PITOT STATIC TEST THAT SOME WELL INTENTIONED PERSON HAD PROTECTED THE STATIC LINE, ENGINE OIL PRESSURE LINES TOGETHER IN SPI-RAP WHICH MADE THE COLLECTION OF PIECES TOO LARGE FOR THE SPACE PROVIDED. THIS PREVENTED THE HEATER DUSDR CA140605008Hose · leaking(CAN) AFTER FLIGHT, THE OIL RESERVOIR WAS NOTICED TO BE LOW AND EXCESSIVE OIL WAS FOUND ON THE BOTTOM OF THE HELICOPTER. INVESTIGATION FOUND THE ENGINE RETURN LINE FROM THE EXTERNAL FILTER TO THE OIL COOLER HAD A LEAK COMING THROUGH THE STEEL BRAIDED LINE COVSDR HEFR201404290001Bearing · failedOPERATOR EXPERIENCED ERRATIC ENGINE OPERATION INCLUDING INABILITY TO LIGHT OFF AS WELL AS UNCOMMANDED, INCREASES IN N2 & NR SPEEDS. PILOT REPORTED THAT WHEN HE WAS LANDING FROM A HOVER TAXI, NOTICED THE N2 AND NR RISING, ROLLED THE THROTTLE TO IDLE AT WHICH TSDR CA140423011Bolt · unserviceable(CAN) T/R GEARBOX OIL WAS DARK AND EVIDENCE OF BLACK PASTE AND METAL ON CHIP PLUG. IT WAS DECIDED TO R & R T/R GEARBOX AND IN THE PROCESS OF DOING SO IT WAS DISCOVERED THAT THE COUPLING BOLT ATTACHING THE T/R DRIVESHAFT COUPLING TO THE T/R GEARBOX INPUT GEAR SSDR CA140217004O-Ring · missing(CAN) THE OVER RUNNING CLUTCH WAS PURCHASED AS AN EXCHANGE UNIT. THIS UNIT WAS INSTALLED AT TTAF 16552.9 HRS. THE INSPECTION CRITERIA IS A VISUAL OIL CHECK EACH 100 HRS, 300 HR HOOK TIME INSPECTION AND A 1800 HR OVERHAUL PERIOD. THIS UNIT AT INSTALL WAS TSO OFSDR CA140108003Arm · seized(CAN) DURING AN UNSCHEDULED BELL CRANK CHANGE, IT WAS DISCOVERED THAT THE GOVERNOR ARM WAS SEIZED. A RENTAL GOVERNOR WAS INSTALLED WHILE THIS UNIT GOES FOR REPAIR. INSPECTION OF THE CONTROL LINKAGE INDICATES THAT THE SPRING ROD PROTECTION SYSTEM HAD BEEN IN USSDR CA140106009Blade · debonded(CAN) LOWER SURFACE OF OTBD ERROSION SHELL FOUND DEBONDED IN 3 LOCATIONS. DEBOND AREA EXCEEDS TOTAL ALLOWABLE OF 5 CM SQUARE, REF MM CHAPTER 14, PAGE 11, PARA 12-4.SDR CA140108002Damper · collapsed(CAN) WHILE ATTEMPTING THE FIRST START OF THE DAY THE ACFT SUDDENLY SHIFTED TAIL LOW AND TO THE RIGHT. IT WAS DETERMINED THAT THE RT REAR LANDING GEAR DAMPER HAD COLLAPSED TO THE FULLY RETRACTED POSITION AND OIL WAS LEAKING FROM THE PISTON CAP AREA. THE DAMP
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