Allison 250-C20B

Service difficulty reports · 1,981

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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.

SDR CA081009003Governor · inoperative(CAN) BENDIX KING GOVERNOR NOT RESPONDING WHEN BEEPED,Oct 2, 2008 · Bell 206B · Turbine GovernorSDR 2008FA0000835Diaphragm · crackedFLOURESCENT PENTRANT INSPECTION PRODUCED INDICATIONS AT 2 LOCATIONS ALONG BRAZING WHERE DIAPHRAGM AND OUTER RING ARE JOINED. INDICATIONS ARE APPROXIMATELY 1.60 AND 2.50 INCHES LONG, APPROX 180 DEGREES APART. VOIDS IN BRAZING ARE ALSO PRESENT AT 2 LOCATIONS. Sep 30, 2008 · Fuel Injector NozzleSDR CA080929005Pitch Link · separated(CAN) THE PITCH CHANGE ROD END BEARING BALL WAS FOUND SEPARATED FROM THE PITCH LINK. THE PILOT REPORTED THAT THE TAIL ROTOR FELT DIFFERENT UPON LANDING. IT WAS FOUND BY THE PILOT WHEN DOING A POST FLIGHT INSPECTION. AN AME WAS DISPATCHED TO ATTEND THE PROBLSep 24, 2008 · Doug MD500N · Tail Rotor Control SystemSDR CA080918005Spring · broken(CAN) DURING TAKEOFF THE LOW ROTOR HORN SOUNDED. THE PILOT ABORTED THE TAKEOFF, SHUT DOWN THE ENGINE AND CALLED MX. WHEN THE ENGINE COWL WAS OPENED THE FCU THROTTLE RETURN SPRING WAS FOUND IN THE BOTTOM OF THE ENGINE PAN.Sep 14, 2008 · Bell 206B · Power LeverSDR CA081209002Clutch · cracked(CAN) APPROX 100 HRS PRIOR TO SCHEDULED REMOVAL OF THE FREEWHEEL ASSY, METAL WAS DISCOVERED ON FREEWHEEL CHIP DETECTOR. CREW ORDERED REPLACEMENT ASSY AND MONITORED FURTHER INDICATIONS. UPON DISASSEMBLY AT THE OPERATOR`S OVERHAUL FACILITY, IT WAS NOTED THAT THESep 14, 2008 · Bell 206B · Engine/Transmission CouplingSDR CA080923003Wire · broken(CAN) ACFT OVERHAULED, CAME BACK TO BASE LAST WEEK OF AUGUST, NO SLING LOAD OPERATION HAS BEEN LOGGED. ELECTRICAL WIRE FOUND BROKEN AT HOOK CONNECTOR LOCATION. ELECTRICAL WIRE ATTACHED WITH CLAMPS (4X) ALONG THE SWING CABLE SUPPORT. THE ROUTING SEEMED TO BESep 12, 2008 · Bolkms BO105S · Fuselage Main, Bulkhead Fuselage wiringSDR WVX2008F00000Turbine · destroyedAIRCRAFT WAS IN A 70 FOOT HOVER AND HAD JUST PLACED A SLING LOAD ON THE GROUND WHEN A LOUD BANG OCCURRED THE LOUD BANG WAS THE TURBINE EXPLODING. AT THIS TIME, THE PILOT LOWERED THE COLLECTIVE AND ENTERED AN AUTO ROTATION. AIRCRAFT TOUCHED DOWN IN A LEVEL ATTISep 11, 2008 · N58251 · Hughes 369D · Turbine SectionSDR CA081014009Wire · chafed(CAN) PILOT TURNS ON ALL REQUIRED BREAKERS FOR FLIGHT INCLUDING NAV LIGHTS. PRE LIFT-OFF THE PILOT NOTES THE BREAKER FOR THE NAV LIGHTS AT MIDPOINT. PILOT RESETS SWITCH AND LIFTS OFF. AS THE ACFT FLIES THROUGH 300 FT, THE PILOT TURNS ON THE HEATER AND IN A FESep 4, 2008 · Bell 206B · Light System WiringSDR CA080925009Starter Gen · damaged(CAN) STARTER WAS SNAGGED BY PILOT WHICH MOTORED UNDER ITS OWN POWER. EXCESSIVE ROTATION CAUSED INTERNAL DAMAGE. STARTER WAS REPLACED AND NO ISSUES WERE NOTED.Aug 4, 2008 · Bell 206B · Starter-GeneratorSDR 7KF2008F00000Compressor · fodDURING FLIGHT WITH 2 MEDICAL PERSONNEL AND PILOT ABOARD HEADING BACK TO AIRPORT NR 1. ENGINE MADE A LOUD NOISE AND FLAMED OUT, PILOT NOTED ENGINE INDICATIONS AND SECURED THAT ENGINE, DECLARED AN EMERGENCY WITH TOWER AND LANDED AC WITHOUT INCIDENT. AFTER INVEJul 22, 2008 · N911LF · Bolkms BO105S · Turbine Engine Compressor SectionSDR HDN2008F00000Fire Detector · corrodedNR 1 ENG FIRE DETECTOR WARNING LIGHT ILLUMINATED DURING CRUISE FLIGHT. AC DIVERTED FROM FLIGHT PATH AND LANDED ON THE SHOULDER OF THE ROAD. IT WAS DETERMINED THAT THERE WAS NOT A FIRE. MAINT WAS DISPATCHED TO THE LZ. IT WAS DETERMINED THAT CORROSION WAS EVJul 17, 2008 · N911EB · Bolkms BO105S · Fire DetectionSDR CA080822014Labyrinth Seal · leaking(CAN) DURING INSPECTION, OIL WAS FOUND POOLING IN EXHAUST COLLECTOR, SUSPECT NR 5 LAB SEAL.Jul 7, 2008 · Bell 206B · Turbine Engine Oil SystemSDR CA080707003Bearing · failed(CAN) PILOT NOTED N1 INCREASE DURING CRUISE. REDUCED THROTTLE AND N1 DECREASED ACCORDINGLY. SOME THROTTLE CONTROL WAS POSSIBLE BUT THE ENGINE CONTINUED TO ACCELERATE. THROTTLE WAS REDUCED UNTIL IDLE STOP WAS REACHED AT WHICH TIME IT CONTINUED TO CLIMB. AT Jul 6, 2008 · Bell 206B3 · Fuel Control/Turbine EnginesSDR CA080717001Governor · malfunctioned(CAN) DURING GROUND RUN THE GOVERNOR WOULD NOT MAINTAIN ENGINE RPM. REMOVED AND SERVICEABLE GOVERNOR INSTALLED.Jul 5, 2008 · Bell 206B · Turbine GovernorSDR CA080702012Tube · chafed(CAN) INSP OF THE TAIL ROTOR CONTROL TUBE IAW CAMPAIGN NOTICE 351-67-10-017, A 7X7MM AREA WAS FOUND TO HAVE BEEN CHAFED TO A DEPTH OF .003 INCHES 15MM FWD OF THE PROTECTIVE SLEEVE INSTALLED ON THE CONTROL ROD IN THE 10 O`CLOCK POSITION LOOKING FWD FROM THE AFTJul 2, 2008 · Bolkms BO105S · Tail Rotor Control SystemSDR CA080621001Combust Chamber · cracked(CAN) ENGINE REPORTED HIGH OPERATING TEMP. ATTEMPTED POWER CHECK BUT NOTED 790 DEGREE TOT IN HOVER. ABORTED POWER CHECK UPON FURTHER VISUAL INSP FOUND RT ARM PIT CRACKED APPROX 5 INCH CRACK.Jun 11, 2008 · Turbine Engine Combustion SectionSDR 2008FA0000447Turbine Wheel · failedTURBINE ASSY RECEIVED FOR REPAIR DUE TO METAL IN OIL. UPON DISASSEMBLY, IT WAS NOTED THAT THE 1ST STAGE TURBINE WHEEL BLADES WERE MISSING PIECES OF BLADE MATERIAL. THE APPARENT IMBALANCE OF THE GP ROTOR ASSY PRODUCED BY THE MISSING BLADE PIECES CAUSED THE GPMay 29, 2008 · Turbine SectionSDR CA080723004Stop · damaged(CAN) ACFT WAS CLIMBING AT APPROX 6000` ASL. (OAT 1°C). COLLECTIVE HIT ITS UPPER STOP DURING A POWER INCREASE. AT THIS POINT TORQUE READING WAS APPROX 65 PERCENT. T4 AND NG WERE WELL WITHIN MAX CONTINUOUS LIMITATIONS. ON 14 MAY 2006, SB 67.00.12 REV. 2 WAS CAMay 27, 2008 · Aerosp AS355F2 · Main Rotor ControlSDR CA080610002Starflex · wornM/R SWASHPLATE RECEIVED FOR O/H. AFTER DISASSEMBLY AND PAINT STRIPPING ROTATING STAR PN 369D27611-503 WAS FOUND WITH FORK INNER EAR SURFACE WEAR BEYOND LIMITS. THIS WEAR WAS FOUND FILLED WITH SOME SORT OF ADHESIVE ONCE THE ADHESIVE WAS REMOVED THE WEAR WAS BMay 23, 2008 · Hughes 369D · Main Rotor Mast/SwashplateSDR CA080527002Stator · missing(CAN) COMPRESSOR ASSY WAS REMOVED FOR O/H, AT WHICH TIME IT WAS NOTED THE 6TH STAGE STATOR BAND WAS MISSING ONE BLADE, WITH IMPACT DAMAGE NOTED ON OTHER BLADES ALSO IN THE 6TH BAND. NO DAMAGE NOTED FWD OF 6 TH STAGE. BURNER CAN REMOVED AND TURBINE INSPECTED FOMay 21, 2008 · Bell 206B · Turbine Engine Compressor SectionSDR CA080521007Clutch · malfunctioned(CAN) NOISE FROM FREEWHEEL ON SPOOLDOWN, NO INDICATIONS ON CHIP PLUG. REMOVED FREEWHEEL ASSY AND FOUND CLUTCH NOT FULLY RELEASING. REPLACED FREEWHEEL ASSY.May 16, 2008 · Bell 206B · Engine/Transmission CouplingSDR CA080416001Spring · broken(CAN) COMING OUT OF A MAJOR INSP, WHERE THE EJECTION SPRINGS ON ALL THE COWLS ( P/N 105-62648, 105-62664, 105-62643, 105-62663 AND 105-30851) WERE REPLACED. SEVERAL EJECTION SPRINGS P/N V40GT39-1-1AA WERE BREAKING INTO (2) PIECES. THIS PROBLEM HAPPENED STATICAApr 14, 2008 · Bolkms BO105S · Rotorcraft Tail BoomSDR CA080305017Bracket · unserviceable(CAN) ON REMOVAL OF DUAL CONTROLS, A GENERAL INSPECTION OF THE UNDERSEAT AREA REVEALED A CRACK ON THE BEARING CAP OF THE BRACKET ASSEMBLY WHICH IS USED TRANSFERING CONTROL INPUTS FROM CABIN BACK TO THE ROTORS. THE PART WAS REPLACED WITH NO INCIDENT.Feb 20, 2008 · Hughes 369A · Main Rotor ControlSDR CA080411001Actuator · failed(CAN) ACTUATOR FAILED, (WOULD NOT RETRACT) ON PRESTART TEST. FAILED IN THE EXTEN POSITION (CYCLIC FULL FWD) (TC NR 20080411001)Feb 20, 2008 · Bolkms BO105S · Rotorcraft Flight ControlSDR CA080411003Rod End · damaged(CAN) ROD END HAS TEFLON MISSING WITH METAL TO METAL CONTACT (TC NR 20080411003)Feb 20, 2008 · Bolkms BO105S · Rotorcraft Flight ControlSDR CA080130002Head · leaking(CAN) DURING AN INSPECTION THE EMERGENCY FLOAT SYS WERE DEPLOYED ACCIDENTALLY. (2) REFURBISHED KITS (PN:28022969) WERE ORDERED. BOTH VALVE ASSY (PN: 105-E-0031) WERE REBUILDED INCLUDING SHEARHEAD ASSY. (PN:29022979) NITROGEN PRESSURE WAS BROUGHT UP TO 3200PSI Jan 15, 2008 · Bolkms BO105S · Emergency Flotation SectionSDR CA080121008Sprag Clutch · corroded(CAN) DURING 300 HOUR INSPECTION PART WAS FOUND TO HAVE PITTING ON SEVERAL ELEMENTS. SPRAG CLUTCH REPLACED. (TC NR 20080121008)Jan 9, 2008 · Hughes 369D · Engine/Transmission CouplingSDR CA071227007Cap · cracked(CAN) DURING ROUTINE INSPECTION AND FILTER CHANGE, A CRACK AROUND THE EAR OF THE CAP WAS NOTED. THE STUD WAS ALSO STRIPPED. MFG COVERED THIS TOPIC IN THEIR CSL-1251. TORQUEING IS THE POSSIBLE CAUSE FOR THIS DEFECT, THE LETTER RECOMMENDS 30-40 LBS-IN. IT IS IMPDec 18, 2007 · Hughes 369D · Turbine Engine Oil SystemSDR CA080221006Bolt · cracked(CAN) MAIN ROTOR TRANSMISSION RECEIVED FOR OVERHAUL AFTER NDT INSPECTION 31 OF THE 32 RING GEAR BOLTS P/N 369H5105 WERE FOUND CRACKED UNDER THE BOLT HEADS. (TC NR 20080221006)Dec 14, 2007 · Hughes 369A · Main Rotor Transmission MountSDR CA071210005Housing · cracked(CAN) CLUTCH HOUSING RECEIVED FOR OVERHAUL AFTER PAINT STRIPPING HOUSING SENT OUT FOR NDT INSPECTION AND CAME BACK FOUND CRACKED ON ENGINE SIDE OF HOUSING. (TC NR 20071210005)Dec 4, 2007 · Hughes 369D · Engine/Transmission CouplingSDR CA071127006Bulkhead · cracked(CAN) AFT BULKHEAD P/N 206-030-446-001F CRACKED AT RT GEARBOX MOUNTING HOLE. (TC NR 20071127006)Nov 22, 2007 · Bell 206B · Rotorcraft Tail BoomSDR CA071030010Housing · mismanufactured(CAN) DUE TO A INTERNAL CASTING DEFECT INSIDE THE OIL FILTER HOUSING, THE PRESSURE REGULATING POPPET CANNOT FULLY BOTTOM OUT WHEN INSTALLED. THIS THEN GIVES A FALSE INDICATION OF PROPER POSITION OF THE POPPET WHEN (BACKED OUT) 5.5 TURNS FOR INITIAL ADJUSTMENT Oct 30, 2007 · Bell 206B · Engine Oil Distribution (Airframe Furnished)SDR CA071030004Carbon Seal · damaged(CAN) DURING AN OIL LEAK WAS DISCOVERED BY THE BLEED VALVE. NR 1 BEARING CARBON SEAL FOUND DAMAGED, THE BEARING WAS REMOVED AND UPON INSPECTION FOUND UNSERVICEABLE. THE BEARING WHEN TURNED HAD A ROUGH, COURSE FEELING TO IT. (TC NR 20071030004)Oct 29, 2007 · Bell 206B · Turbine Engine Oil SystemSDR CA071112002Bracket · broken(CAN) RUDDER PEDALS WERE FOUND TO BE LOOSE IN MOUNTS ON FURTHER INVESTIGATION IT WAS FOUND THE BRACKET THAT THE RUDDER PEDALS MOUNT IN WAS BROKEN ON (3) OF THE (4) MOUNTING BOLT EARS. (TC NR 20071112002)Oct 26, 2007 · Hughes 369D · Rudder Control SystemSDR CA071025001Spring · mismanufactured(CAN) POOR METAL COMPOSITION IN PART CAUSES CRACKING. THESE PARTS WILL CRACK WITHOUT BEING SUBJECT TO FLIGHT. ONE BATCH HAS BEEN DISPOSED OF AND THE NEXT BATCH HAS THE SAME ISSUE. THE MFG HAS BEEN NOTIFIED. REF MBB-BO-105 IPC 60-00-00 FIG 8 ITEM NR 440. (TC NROct 23, 2007 · Bolkms BO105S · Main Rotor SystemSDR CA071023001Oil System · low pressure(CAN) LOSS OF ENGINE OIL PRESSURE IN FLIGHT. ENGINE WILL BE REMOVED AND SENT FOR INVESTIGATION. (TC NR 20071023001)Oct 22, 2007 · Bell 206B · Engine Oil PressureSDR CA071023005Oil System · low pressure(CAN) LOSS OF ENGINE OIL PRESSURE IN FLIGHT. ENGINE WILL BE REMOVED AND SENT FOR INVESTIGATION. (TC NR 20071023005)Oct 22, 2007 · Bell 206B · Engine Oil PressureSDR CA071024002Clutch · cracked(CAN) THE A/C HAD A FREEWHEEL CHIP LIGHT AND LANDED AT MAIN BASE, AFTER DOING THE 2 MINUTE COOLDOWN THE ENGINE WAS SHUTDOWN. WHILE SPOOLING DOWN A NOISE WAS NOTICED THAT WAS NOT NORMAL. THE FREEWHEEL WAS REMOVED AND DISASSEMBLED. THE CLUTCH CAGE WAS FOUND CRACOct 19, 2007 · Bell 206B · Engine/Transmission CouplingSDR N9V2007F00000Drive Shaft · brokenPILOT MADE EASY RT TURN. FELT AN INCREASE IN VIBRATION. HE MADE A PRECAUTIONARY LANDING AT THE NEAREST AIRPORT. FOUND THAT A FLEX FRAME HAD BROKEN ON THE MOST FORWARD END OF THE DRIVESHAFT THROUGH THE BOLT HOLE. THE DRIVESHAFT HAD A JUMP ROPE EFFECT WHEN TOct 5, 2007 · N2HV · Bell 206B · Tail Rotor Drive ShaftSDR CA071022006Gearbox · making metal(CAN) APPROXIMATELY 5 MILES FROM AIRPORT, MAGI NR1 LIGHT ILLUMINATED. PULSED OFF AND 2 MINUTES LATER LIGHT ILLUMINATED AGAIN. AN EMERGENCY LANDING WAS CARRIED OUT. BOTH NR1 AND NR2 MAGNETIC PLUGS CHECKED AND FOUND CONTAMINATED WITH METAL. THE GEARBOX WAS REPLAOct 3, 2007 · Bolkms BO105S · Main Rotor GearboxSDR CA071023006Gearbox · making metal(CAN) APPROXIMATELY 5 MILES FROM DESTINATION, MAG NR1 LIGHT ILLUMINATED. PULSED OFF AND 2 MINUTES LATER LIGHT BACK ON. NR1 THROTTLE ROTATED TO IDLE, CONTINUED APPROACH TO DESTINATION, CRASH TRUCK ADVISED. ON FINAL, NR1 THROTTLE ADVANCED AND NORMAL LANDING CAROct 3, 2007 · Bolkms BO105S · Main Rotor GearboxSDR 74509272007Relay · failedODOR OF BURNING INSULATION DETECTED IN CABIN. NO SMOKE PRESENT. CHECKED FOR TRIPPED CIRCUIT BREAKERS. NONE FOUND. RECYCLED/RESET BOTH GENERATORS TO CHECK LOAD ON EACH. NO PROBLEMS DETECTED AND RESTORED BOTH GENERATORS. CONTINUED TO FINAL LANDING AT BASE Sep 27, 2007 · N485EC · Bolkms BO105S · Passenger Compartment LightingSDR CA070928004Belt · worn(CAN) ON LANDING, THE PILOT FELT A STRANGE VIBRATION. AFTER LANDING, THE AC WAS GROUNDED PENDING MAINTENANCE TROUBLESHOOTING. A CLOSE INSP WAS COMPLETED AND DETERMINED TO BE A LOOSE COOLER BELT CAUSING EXCESSIVE VIBRATION AT 100 PERCENT. THE BELT WAS REPLACESep 25, 2007 · Hughes 369D · Engine Fuel/Oil CoolerSDR CA071015006Fcu · out of adjust(CAN) FCU SN 304536 REMOVED FOR OVERHAUL(RUNNING NORMAL)FCU SN 308210 TSO 0 INSTALLED (FROM SAE)AND REQUIRED MAXIMUM ADJUSTMENTS,START DERICH AND START ACCEL.TO GET ENGINE TO START. AFTER 7.3HRS, OUR AME DEEMED IT NECESSARY TO CHANGE IT FOR A BETTER ONE. A LOSep 20, 2007 · Bell 206B · Fuel Control/Turbine EnginesSDR 2007FA0000868Blade · crackedEXCESSIVE 1 PER REVOLUTION VIBRATION NOTICED IN MAIN ROTOR SYSTEM. THE AIRCRAFT WAS LANDED WITHOUT INCIDENT. INVESTIGATION REVEALED CORD WISE CRACKS IN UPPER AND LOWER SKINS AT STATION 1979 EXTENDING FROM THE TRAILING EDGE TO THE AFT SIDE OF THE SPAR. THE HSep 11, 2007 · N2MF · Agusta A109 · Main Rotor BladesSDR CA070910007Fuel Control · unserviceable(CAN) OVERSPEED OCCURED DURING FLIGHT, FUEL CONTROL REPLACED WITH SERVICEABLE UNIT. WHEN REMOVED, IT WAS NOTED THAT THE FCU INPUT SHAFT BEARING WAS DAMAGED. FCU SENT OUT FOR INSP/REPAIR. (TC NR 20070910007)Sep 10, 2007 · Bell 206B · Fuel Control/Turbine EnginesSDR CA070927007Stator Vane · failed(CAN) NR 6 STATOR VANE FAILURE (1 VANE ONLY). NO EROSION TO NEIGHBORING VANES OR PLASTIC COATING. FOUND BY HELICOPTER OPERATOR. (TC NR 20070927007)Sep 5, 2007 · Hughes 369D · Turbine Engine Compressor SectionSDR CA070928001Stator Vane · failed(CAN) PILOT REPORTS UNUSUAL NOISE COMING FROM AIRCRAFT DURING GROUND RUN. AIRCRAFT IS GROUNDED UNTIL ENGINEER INVESTIGATES THE UNUSUAL NOISE. NOISE IS DESCRIBED AS A (KNOCKING NOISE COMING FROM THE ENGINE) AND TOT HOTTER THAN USUAL. DURING THE GROUND RUN THE Aug 31, 2007 · Hughes 369D · Turbine Engine Compressor SectionSDR CA070821005B-Nut · loose(CAN) THE ROTORCRAFT DEPARTED AT LANDING AREA AT APPROX 4500 FT WITH ALL NORMAL PARAMETERS. AT APPROX 4300 FT THE PILOT NOTICED A DIFFERENCE IN ENGINE NOISE LEVELS. THE DIFFERENCE IN NOISE LEVELS WERE ACCOMPANIED BY ACTIVATION OF THE ENGINE AUTO RE-LIGHT SYS AAug 20, 2007 · Bell 206B · Engine Bleed Air SystemSDR CA070823008Tank · failed(CAN) TANK UNIT WAS INSTALLED FOR AN INACCURATE FUEL INDICATION. AFTER INSTALLATION OF THE REPAIRED TANK UNIT WE APPLIED GROUND POWER FOR THE FUEL CALIBRATION AND FOUND THE GAUGE TO BE INOPERATIVE. AFTER TROUBLESHOOTING IT WAS DETERMINED THAT THE TANK UNIT WASAug 18, 2007 · Bell 206B · Fuel Storage
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