Allison 250-C20
Service difficulty reports · 945
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 = '250C20' 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 = '250C20' 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 AU000841Pipe · cracked(AUS) ENGINE OIL PIPE LEAKING IN AREA BENEATH P'' CLIPS. (X)SDR CA001013023Seal · spinning(CAN) THE UPPER SEAL FOUND SPINNING IN THE CAP.SDR CA000925028Spring · cracked(CAN) 600/YEARLY INSPECTION BEING CARRIED OUT ON MAIN DRIVESHAFT. UPON REMOVAL OF COUPLING CAP, FOUND SPRING BROKEN IN A DOZEN PIECES. THE PIECES DAMAGED THE INNER COUPLING RENDERING IT UNSERVICEABLE. THE CAP, SPRING AND INNER COUPLING WERE SCRAPED. (X)SDR CA000905015Governor · malfunctioned(CAN) WHILE RUNNING ON THE GROUND AT 100% N2 THE PILOT PULLED COLLECTIVE. AS HE PULLED IN POWER THE ROTOR RPM DROPPED TO 80%, ALL AIR LINES WERE LEAK CHECKED, GOVERNOR REPLACED & THE PROBLEM WENT AWAY.SDR CA001205010Transmission · failed(CAN) DURING THE SERVICEABILITY CHECK (AFTER THE METAL WAS FOUND ON THE CHIP PLUG) MORE METAL WAS FOUND ON THE CHIP PLUGS AND THE OIL MONITOR. MAST AND THE TRANSMISSION WERE REPLACED.SDR CA000828002Servo · jammed(CAN) WHILE PILOT WAS FLARING TO LAND, HE NOTICED IN A HOVER THAN MORE FORCE WAS REQUIRED TO MOVE THE CYCLIC TO THE RIGHT. UPON LANDING AND SHUTDOWN OF AIRCRAFT HE TRIED TO PERFORM A CONTROL CHECK OF THE CYCLIC AND FOUND THAT IT REQUIRED TWO HANDS AND CONSIDERSDR CA000824007Governor · failed(CAN) THE PILOT WAS ON THE GROUND AT FLIGHT IDLE AND ACCELERATED THE RPM TO NR RPM 100 PERCENT. THE RPM REACHED 108 PERCENT FOR 1 TO 3 SECONDS. THE PILOT TRIED TO BEEP THE RPM DOWN BUT NO RESPONSE. THE PILOT BROUGHT THE THROTTLE DOWN TO FLIGHT IDLE. THE PILSDR CA001205006Indicator · failed(CAN) THIS INDICATOR WAS ERRATIC EVER SINCE IT WAS INSTALLED. IT BOUNCES, GIVING BOUNCY READINGS OF 100 DEGREES C.SDR CA000801006Case · cracked(CAN) DURING A 100 HOUR INSPECTION AND TURBINE CHANGE THE AME NOTICED A CRACK IN THE ARMPIT AREA OF THE OUTER COMBUSTION CASE. INSPECTION C/W PER ALLISON 250-C20 SERIES O&M 10W2, 72-40-00 PARA 2B.SDR CA001205005Washer · missing(CAN) WHEN INVESTIGATING EXCESSIVE PLAY OF THE PILOTS PEDAL ADJUSTMENT, IT WAS NOTED THAT MISSING AND INCORRECT PARTS EXISTED. B0500-26 WASHERS WERE MISSING FROM THE ASSEMBLY AND THE TIE BOLT HAD ALMOST 1/4 OF END PLAY. (NOTE: PARTS ON ORDER.)SDR CA000720012Combustion Chamb · cracked(CAN) A HIGHER THAN NORMAL T.O.T. WAS EXPERIENCED UNDER NORMAL OPERATING TO-QUE SETTINGS. AIRCRAFT ENGINE WAS INSPECTED UPON LANDING TO DETECT A POSSIBLE MALFUNCTION. A CRACK WAS DISCOVERED IN THE COMBUSTION CASE ASSEMBLY IN THE REINFORCED PATCH AREA OF THE SDR CA000719013Case · cracked(CAN) OIL WAS NOTED LEAKING FROM TRANSMISSION DURING GROUND RUN. REMOVAL OF THE PAINT REVEALED A CRACK ON THE UPPER CASE STARTING FROM THE SPLIT LINE BETWEEN TWO MOUNTING STUDS AT THE 4:30 POSITION, VIEWED FROM THE TOP. AIRCRAFT WAS GROUNDED, TRANSMISSION RSDR CA000731018Pump · contaminated(CAN) AFTER A DAYS FLYING, IT WAS DISCOVERED THAT THE HYDRAULIC FILTER BYPASS BUTTON HAD POPPED. THE BUTTON WAS DEPRESSED, AIRCRAFT RUN UP, BUTTON POPPED AGAIN. CONTAMINATES WERE FOUND IN THE FILTER. ALL HYDRAULIC LINES, SERVOS WERE FLUSHED, A NEW FILTER INSSDR CA001205007Nozzle · failed(CAN) DURING A SCHEDULED REMOVAL OF THE COMPRESSOR ASSEMBLY, THE FIRST STAGE NOZZLE WAS VISUALLY INSPECTED AND OBSERVED THAT 4 VANES WERE CRACKED BEYOND MANUFACTURER'S LIMITS. UNIT REPLACED. (X)SDR AU000500Cuff · cracked(AUS) MAIN ROTOR CUFF CRACKED FROM BOLT HOLE. CRACK LENGTH 10MM (0.393IN). FOUND DURING DYE PENETRANT INSPECTION IAW AD/HIL12/17(SB 36-1).SDR CA001013021Governor · misinstalled(CAN) WHEN CHECKING THE GOVERNOR ON RECEIPT, IT WAS NOTED THAT THE T FITTING WAS INSTALLED IN THE WRONG PORT. FITTING WAS REMOVED AND INSTALLED IN THE CORRECT PORT.SDR CA000614018Elt · failed(CAN) DURING ANNUAL RECERTIFICATION, THE ELT WAS FOUND TO HAVE NO TRANSMIT POWER OUTPUT. THE UNIT WAS SENT BACK TO FOR REPAIR STATION.SDR CA001205009Pitch Link · misinstalled(CAN) INCORRECT P/N FORK INSTALLED ON THE UPPER END OF THE ASSEMBLY. THIS FORK HAS THE SAME DIMENSION AS THE BOTTOM FORK (.8621). WHEN INSTALLED OVER THE TRUNNION THERE IS A SPREAD STRESS OF .013 INCHES.SDR CA001122011Screw · sheared(CAN) THE SCREW HEAD RETAINING THE FUEL CONTROL UNIT RATIO LEVER COVER (FUEL SIDE) SEPARATED IN-FLIGHT ALLOWING FUEL TO LEAK INTO THE ENGINE COMPARTMENT UNDER HIGH PRESSURE AND REDUCE THE FUEL FLOW TO THE ENGINE TO THE POINT WHERE CONTINUED FLIGHT WAS NOT POSSSDR CA001013019Turbine · failed(CAN) DURING A COMPRESSOR WASH, BRULIN AND WATER MIX WAS COMING OUT OF THE NR 6 AND NR 7 AIR DELIVERY TUBE. UPON FURTHER INVESTIGATON IT WAS DISCOVERED THAT THE TUBE WAS NOT WELDED TO THE ASSY. (X)SDR CA000606009Bearing · worn(CAN) WHILE IN-FLIGHT, THE PILOT COULD HEAR A LOUD METALLIC SCREAMING GRINDING NOISE FROM THE ENGINE. HE LANDED AT A CLEARING AND SHUT DOWN ENGINE. THE ENGINE GEARBOX HAD QUICK DISCONNECT CHIP PLUGS, PULLED THE CHIP DETECTORS AND FOUND FERROUS METAL ON THE OSDR CA001013015Gearbox · loose(CAN) NOTED ENGINE MOUNT WAS LOOSE. TURBINE TO GEARBOX ATTACHMENT FOUND LOOSE. NOTED ENGINE NOISE AND VIBRATION. GEARBOX REPLACED.SDR CA000713004Nut · cracked(CAN) DURING A SCHEDULED OVERHAUL OF THE ABOVE DESCRIBED MAIN ROTOR HUB ASSEMBLY, A COMPONENT WITHIN THIS ASSEMBLY KNOWN AS THE MAST NUT WAS FOUND TO HAVE A CRACK INDICATION. THIS WAS DETECTED DURING THE MAGNETIC PARTICLE INSPECTION. THIS NUT HAS SINCE BEEN SESDR CA000706035Casting · cracked(CAN) CRACK FOUND AT AFT CASTING WHERE TAIL ROTOR GEARBOX MOUNTS IN TAILBOOM ON R/H HOLE. CASTING REMOVED BY OVERHAUL SHOP FOR REPLACEMENT AND CRACK ALSO LOCATED IN LT MOUNTING AREA. CRACK WAS FOUND ON SCHEDULED 100 HOUR INSPECTION OF AIRCRAFT.SDR CA001013010Bearing · loose(CAN) BEARING FOUND LOOSE IN THE DRAG PIN, POOR STAKING SEEMS TO BE THE CAUSE.SDR CA000516012Nozzle · cracked(CAN) A GROUP OF 2ND STAGE NOZZLES ARE IN THE PROCESS OF RECALL. IT WAS FOUND THAT REPAIRS MADE TO SOME NOZZLES; WHICH WAS AN APPROVED REPAIR , HAVE FAILED TO REACH O/H AND ARE CRACKING WHERE THE FIRST STAGE BLADE PATH WAS JOINED TO THE 2ND STAGE NOZZLE. TRASDR CA000427015Exhaust Stack · cracked(CAN) CRACK AT RIVET JOINT (TOP) WHICH THEN CAUSED THE CLAMP TO BREAK.SDR CA000404017Wire · broken(CAN) BROKEN WIRE FOUND ON GOVERNOR BEEP SWITCH. WIRE RE-SOLDERED AND AIRCRAFT RETURNED TO SERVICE.SDR 20000424SH019Bearing · making metalMETAL FLAKES DETECTED ON MAGNETIC PICK-UP IN LOWER GEARBOX AND OIL PUMP MAGNETIC PICK-UP. DISASSEMBLED GEARBOX FOR INSPECTION. BEARING INNER AND OUTER RACES BOTH HAD AREAS THAT HAD FLAKED OFF METAL. (X)SDR 20000412SH028Probe · damagedTHE NYLON INSERT IN THE TEMPERATURE PROBE LET GO RESULTING IN FLUCTUATION AND DROPPING OIL PRESSURE AND A LOSS OF OIL. THE ENGINE HAD TO BE TORN DOWN FOR INSPECTION. MAIN DAMAGE SEEMS TO BE THE ENGINE''S NR 8 BEARING WHICH WAS DESTROYED. (X)SDR CA000308003Bolt · broken(CAN) REAR/TOP ATTACHMENT BOLT OF VERTICAL FIN ASSY WAS FOUND BROKEN (STILL IN PLACE) ON 600 HOUR CHECK. THE OTHER 3 BOLTS WERE FOUND BELOW MINIMUM TORQUE VALUE.SDR CA000310010Relay · failed(CAN) GENERATOR WENT OFFLINE DURING FLIGHT. INVESTIGATION REVEALED GENERATOR RELAY WAS CLOSING, BUT THERE WAS NO POWER TRANSFER THRU RELAY. RELAY REPLACED.SDR CA000224022Fan · separated(CAN) DURING CRUISE FLIGHT, THE AIR DISTRIBUTION FAN DEPARTED THE MOTOR/FAN ASSEMBLY. THE FAN THEN CHEWED THROUGH THE LOWER CHIN BUBBLE AND DEPARTED THE AIRCRAFT.SDR CA000301019Skin · cracked(CAN) FOLLOWING RECEIPT OF SERVICE DIFFICULTY ADVISORY AV-1999-03R1, AN INSPECTION REVEALED A CRACK IN THE BULKHEAD BELOW THE NUTPLATES. CRACK HAD PREVIOUSLY BEEN REPAIRED WITH A PATCH BUT CRACK HAD SPREAD INTO AN ADJOINING STRUCTURAL PANEL. ANOTHER CRACK WAS SDR CA000218009Bearing Cage · failed(CAN) STARTER/GENERATOR REMOVED BECAUSE OF EXCESSIVE VIBRATIONS . IT WAS LATER FOUND THAT BEARING LINER WAS VERY LOOSE IN THE DRIVE END END BELL WHICH ALLOWED THE ARMATURE TO FLOP AROUND. NEW END BELL WAS INSTALLED. FAULTY STARTER/GEN WAS QUARANTINED.SDR CA000215012Nozzle · cracked(CAN) THE 2ND STAGE NGV,FIRST STAGE BLADE PATH WAS FOUND CRACKED 50% AROUND THE CIRCUMFERENCE. THE BLADE PATH HAD BEEN REPLACED AND WAS JOINED AT THE SECOND NOZZLE BY A BRAZED BUT JOINT. THIS IS /WAS A DAR APPROVED REPAIR. SUSPECT NGV ARE REQUESTED TO BE REMOVSDR CA000301042Bulkhead · cracked(CAN) DURING 300-HOUR INSPECTION, CRACK FOUND ON REAR BULKHEAD OF TAILBOOM AT TH E STROBE POWER AREA.SDR CA000301043Probe · shorted(CAN) DURING DAILY INSPECTION, WHEN BATTERY WAS TURNED ON, THE TRANSMISSION TEMPERATURE LIGHT ILLUMINATED.SDR 2000ZZZX816Nozzle · misdrilledHOLES IN UPPER PART OF NOZZLE DRILLED IMPROPERLY, DISCOVERED ON SHELF. PARTS WAS NEW AND SUBMITTER STATED THIS WAS DONE DURING MANUFACTURING. NOTE: SHOULD HAVE 4 HOLES.SDR AU000203010Line · decayed(AU) FUEL LINES HAD DECAYED TO THE POINT THAT RUBBER WAS COMING THROUGHTHE BRAID. THESE SMALL PIECES OF RUBBER CAUSED FUEL CHECK VALVES TO STICK OPEN AND CAUSED LOW PRESSURE FUEL PRESSURE READINGS. NEW FUEL HOSES INSTALLED.SDR CA000203010Line · damaged(CAN) FUEL LINES HAD DECAYED TO THE POINT THAT RUBBER WAS COMING THRU BRAID. THESE SMALL PIECES OF RUBBER CAUSED FUEL CHECK VALVES TO STICK OPEN AND CAUSED LOW PRESS FUEL PRESSURE READINGS. NEW FUEL HOSES INSTALLED.SDR AU000110033Stator · misoverhauled(AU) STARTER/GENERATOR SENT TO OVERHAUL AFTER ONLY 96 HOURS. STATOR COWLING OUTLET SCREEN FOUND TO BE CLOGGED WITH SOME FOREIGN INSULATION WHICH HAD OCCURRED DURING THE PREVIOUS REWIND. STATOR IS NOW QUARANTINED UNTIL FURTHER INVESTIGATION IS COMPLETED AS TOSDR CA000110033Stator · failed(CAN) STARTER GENERATOR SENT TO OVERHAUL AFTER ONLY 96 HOURS. STATOR COWLING OUTLET SCREEN FOUND TO BE CLOGGED WITH SOME FOREIGN INSULATION WHICH HAD OCCURRED DURING THE PREVIOUS REWIND. STATOR IS NOW QUARANTINED UNTIL FURTHER INVESTIGATION IS COMPLETED AS TO SDR CA000110006Shaft · stripped(CAN) HYDRAULIC SYSTEM FAILURE WHICH WAS LATER ATTRIBUTED TO COUPLING FAILURE INSIDE HYD PUMP.SDR CA000404014Servo · failed(CAN) EXCESSIVE VERTICAL PLAY AT PILOT INPUT TRUNNION AND PILOT VALVE AREA OF THE SERVO. FEEDBACK IS EXCESSIVE, ALSO CHATTERING AN VIBRATING AND NOISY DURING GROUND RUN AND TEST FLIGHTS.SDR CA991210090Actuator · failed(CAN) ON TAKEOFF, THE NR, N2 DECREASED AND WOULD NOT RESPOND TO BEEP INPUT.SDR HEED064609Lining Carrier · wornLINING CARRIER WORN. REPLACED PART.SDR CA991007060Governor · leaking(CAN) FUEL LEAK BEYOND LIMITS FROM GOVERNOR. UNIT CHANGED.SDR CA991209005Fcu · failed(CAN) ENGINE WAS FAILING DECEL CHECKS.SDR CA000518008Spline Adapter · chafed(CAN) SPLINED ADAPTER AT THE AFT END OF SHORT T/R DRIVE SHAFT RUBBING ON ENGINE OIL TANK COOLER COWLING. CHAFING THROUGH THE COWLING HONEYCOMB. COWLING WAS REPAIRED TO ALLOW CLEARANCE FOR THE COUPLING ADAPTER.
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