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 aircraft_model_key = '212' 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 aircraft_model_key = '212' 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 CA120505001Blade · failed(CAN) ON FINAL APPROACH NR 2 ENGINE COMPRESSOR STALL OCCURED FOLLOWED BY HIGH PITCH WHINING. PILOT SHUTDOWN ACFT AND AUTOROTATED, LANDED. UPON INVESTIGATION COMPRESSOR BLADE WAS FOUND LYING IN INLET SCREEN. UPON FURTHER INVESTIGATION 1ST STAGE COMPRESSOR WHESDR CA120507008Engine · overtemp(CAN) DURING FLIGHT, THE ENGINE STARTED TO SURGE FOLLOWED BY TEMPERATURE RISE AND POWER TURBINE SPEED FLUCTUATION. THE ENGINE THEN SHUT ITSELF DOWN. AN ENGINE RESTART RESULTED IN ENGINE TEMPERATURE OF 880F AT START. THE ENGINE WAS THEN OPERATED AT 70 PERCENSDR CA120409006Drain Valve · leaking(CAN) DURING DI NR 2 POWER SECTION WAS FOUND TO BE LOW ON OIL. AFTER INVESTIGATION LEAKAGE WAS FOUND FROM OIL DRAIN VALVE. UPON REMOVAL SCREWS HOLDING INPUT SPIGOT WERE FOUND PULLED OUT OF VALVE BODY, ALLOWING LEAKAGE PAST THE INTERNAL O-RING. THE SCREWS LOSDR ALGA201202291215Fitting · corrodedM/R HUB FITTING GOUGED BEYOND LIMITS.SDR ALGA201202291214Nut · corrodedM/R HUB NUT CORRODED BEYOND LIMITS.SDR ALGA201202291213Nut · corrodedM/R HUB NUT CORRODED BEYOND LIMITS.SDR ALGA201202291212Barrel · corrodedM/R HUB BARREL CORRODED BEYOND LIMITS.SDR ALGA201202291211Bolt · corrodedM/R HUB BOLT CORRODED BEYOND LIMITS.SDR ALGA201202291210Clevis · corrodedM/R HUB CLEVIS CORRODED BEYOND LIMITS.SDR ALGA201202291209Clevis · corrodedM/R HUB CLEVIS CORRODED BEYOND LIMITS.SDR ALGA201202291208Fitting · corrodedM/R HUB FITTING CORRODED BEYOND LIMITS.SDR ALGA201202291207Fitting · corrodedMAIN ROTOR FITTING CORRODED BEYOND LIMITS.SDR ALGA201202291206Bushing · corrodedM/R HUB HEAD BUSHING CORRODED BEYOND LIMITS.SDR ALGA201202291205Bushing · corrodedMAIN ROTOR HEAD BUSHING CORRODED BEYOND LIMITS.SDR ALGA201202291204Block · corrodedMAIN ROTOR PILLOW BLOCK CORRODED BEYOND LIMITS.SDR ALGA201202291203Block · corrodedMAIN ROTOR PILLOW BLOCK CORRODED BEYOND LIMITS.SDR ALGA201202291202Pitch Horn · corrodedMAIN ROTOR HEAT PITCH HORN CORRODED BEYOND LIMITS.SDR ALGA201202291201Pitch Horn · corrodedMAIN ROTOR HEAD PITCH HORN HAS CORROSION BEYOND LIMITS.SDR CA120227018Window · missing(CAN) THE ACFT WAS DESCENDING WHEN THE RT FORWARD POP OUT WINDOW WAS LOST IN FLIGHT FROM THE SLIDING, CREW, DOOR.SDR CA120217001Link · unserviceable(CAN) DURING CRUISE AT 100 KIAS AT 6500` ASL, ACFT VIOLENTLY PITCHED DOWN 20 DEGREES FROM LEVEL WITH SIGNIFICANT VIBRATIONS. COLLECTIVE WAS LOWERED AS CONTROL OF THE ACFT WAS REGAINED. WHILE TURNING TO RETURN TO BASE THERE WAS AN APPARENT 1:1 VERTICAL AS WESDR CA120227012Window · missing(CAN) CREW DOOR RT FORWARD POP OUT WINDOW WAS LOST IN FLIGHT. THE ACFT WAS IN A LEFT DESCENDING TURN. NO DAMAGE TO ACFT. POP OUT WINDOW WAS REPLACED.SDR CA120123004Blade · cracked(CAN) ACFT WAS MINUTE INTO FLIGHT AT 200FT AGL WHEN THE PILOT HEARD A LOUD BANG AND FELT A SLIGHT VIBRATION IN THE CYCLIC CONTROL STICK. ACFT LANDED 1 MINUTE LATER WITHOUT FURTHER INCIDENT OR VIBRATION. CRACK IN LOWER BLADE SKIN FOUND 4.5" FROM L/E AND 1.25"SDR CA120119012Ring Gear · cracked(CAN) CRACKS FOUND ON RING GEAR TEETH AFTER TRANSMISSION WAS DISASSEMBLED FOR CRACKED SUPPORT CASE LUG. RING GEAR SENT FOR NDI. INSPECTOR STATES THAT CRACKS WOULD NOT SHOW UP WITH MAGNAFLUX UNDER ANY CIRCUMSTANCE. CRACKS SHOWED UP READILY WITH LIQUID PENETRSDR CA120105011Lug · cracked(CAN) FOUND LT AFT LUG CRACKED ON TRANSMISSION SUPPORT CASE. CRACK FOUND WHEN TRANSMISSION WAS REMOVED FOR NON-RELATED AIRFRAME MAINTENANCE. THIS IS THE THIRD SIMILAR CRACKED CASE WE HAVE OBSERVED.SDR CA111214009Servo · defective(CAN) PART RECEIVED FROM CUSTOMER AS ZERO TIME FROM OVERHAUL. CUSTOMER REPORTED THAT LOWER CYLINDER LOCKS, WILL NOT EXTEND. SUSPECT IMPROPER BYPASS & SERVO LOWER CYLINDER SP & SI TIMING. SERVO FUNCTIONALLY CHECKED PRIOR TO DISASSEMBLY. THE SERVO LOWER PISTOSDR CA111214006Servo · defective(CAN) SERVO RECEIVED ZERO TIME SINCE OVERHAUL. CUSTOMER REPORTED LOWER CYLINDER ASSEMBLY LOCKS HYD WILL NOT EXTEND. SUSPECT IMPROPER BYPASS SERVO TIMING. SERVO FUNCTIONALLY TESTED PRIOR TO DISASSEMBLY. THE SERVO LOWER PISTON MOVED TO THE EXTEND POSITION BUSDR CA111123011Tube · cracked(CAN) P3 FILTER AIR TUBE CRACKED AT THE P3 FILTER.SDR CA111104008Fitting · cracked(CAN) CRACK FOUND IN BASE OF FITTING. APPEARS TO HAVE BEEN CRACKED AT MFG AS THE BELL HELICOPTER INSPECTORS MARK ENGRAVED IN THE PART HAS DISPLACED METAL INTO THE CRACK.SDR CA111030005Engine · power loss(CAN) THE ACFT WAS TRANSPORTING BACK TO BASE FIREFIGHTERS THAT HAD BEEN WORKING A FOREST FIRE WHEN THE PILOT NOTED ENGINE FLUCTUATIONS FOLLOWED BY A LOSS OF MAIN ROTOR SPEED. HE RETARDED BOTH ENGINES TO IDLE AND HE MADE AN AUTOROTATION IN A FIELD. THE HELO TSDR CA111018004Crosstube · failed(CAN) WHILE RELOADING ACFT AT A FOB, AFT CROSSTUBE FAILED JUST INBD OF THE OUTER EDGE OF LT SADDLE BRACKET AND CLAMP ASSY. ON INVESTIGATION, SOME PITTING CORROSION WAS NOTED UNDER THE SADDLE AREA AT A POINT WHERE THE FRACTURE SEEMS TO HAVE ORIGINATED. ADDITISDR CA110921007Line · broken(CAN) LINE SEPARATED FROM P3 FILTER HSG. UNDER HEAVY POWER CHANGE ENGINE TORQUE WOULD SPLIT FROM OTHER POWER SECTION. DEFECT FOUND DURING LEAK CHECK OF P3 AIR SYS.SDR CA090929004Bearing · loose(CAN) BEARING SLEEVE FOUND LOOSE DUE TO IMPROPER ADHESIVE USE AND IMPROPER STAKING OF BEARING ASSY.SDR CA110815017Control Tube · damaged(CAN) THIS CONTROL TUBE WAS REMOVED FROM THE AIRCRAFT AND AN INSPECTION WAS BEING CONDUCTED IN ACCORDANCE WITH B 212 MM CHAPTER 67 AND B 212 CR&O CHPATER 67. THE NYLATRON WEAR SLEEVES WERE REMOVED AND A RADIAL CRACK WAS REVEALED UNDER THE END SLEEVE. THE TUBE SDR ALGAR8311A1210305Nut · backed outLOWER RACE RETENTION NUT BACKED OFF TO END OF THREADS CAUSING CUTTING ACTION IN LOWER PORTION OF TRANSMISSION CASE.SDR CA110803029Fitting · crackedLIFT LINK FITTING AFT LUG FOUND CRACKED BY MECHANIC DURING DAILY INSP. CAUSE WAS FOUND TO BE WRONG P/N BOLT INSTALLED. TB 212-91-132 HAD BEEN COMPLETED WHICH INCORPORATES IMPROVED LIFT LINK FITTING P/N 212-030-154-101 THAT REQUIRES LARGER DIAMETER BOLT P/N 41SDR EOPA07201130569Mast · making metalTRANSMISSION LIGHT ILLUMINATED IN FLIGHT. ON FURTHER INVESTIGATION TRANSMISSION AND MAST ASSY REPLACEMENT REQUIRED.SDR 2011FA0000471Windshield · crackedHEATED WINDSHIELD WAS FOUND CRACKED WHEN ACFT LANDED.SDR CA110707015Actuator · seizedDROOP COMPENSATOR ACTUATOR SEIZED, WILL NOT EXTEND OR RETRACT.SDR CA110707014Seal · leakingHYDRAULIC PUMP LEAKING FROM INPUT SEAL.SDR CA110707016Selector Valve · intermittentFUEL VALVE, INTERMITTENT OPERATION.SDR CA070625003Door · detached(CAN) WHILE IN NORMAL CRUISE FLIGHT, THE PILOT`S DOOR DEPARTED THE ACFT. THE PROBABLE CAUSE WOULD BE IMPROPER INSTALLATION OF THE DOOR. THE PILOT LANDED AS SOON AS PRACTICAL AND INSPECTED THE ACFT FOR ANY OTHER DAMAGE. NONE FOUND. THE PILOT REMOVED THE CO-SDR CA110623010Relay · failed(CAN) PILOT APPLIED POWER TO NR 2 DC BUSS AND THE NR 2 STARTER-GENERATOR ENGAGED. THIS RESULTED IN THE NR 2 ENGINE STARTING TO SPOOL UP WITH THE STARTER SWITCH STILL IN THE OFF POSITION. TROUBLESHOOTING FOUND THE NR 2 GENERATOR RELAY MAIN CONTACTS WELDED IN THSDR CA110707012Oil Cooler · leakingHEATER LEAKING OIL FROM A WELD SEAM.SDR CA110611004Lock Plate · bentFUEL TRANSFER TUBE DISENGAGED FROM FUEL NOZZLE ALLOWING UN-RESTRICTED HIGH PRESSURE FUEL LEAKAGE. THE FUEL TRANSFER TUBE LOCK PLATE AT THE NR 6 FUEL NOZZLE LOCATION ON THE NR 1 ENGINE HAD NOT BEEN CORRECTLY INSTALLED 353.2 HOURS PREVIOUS DURING A SCHEDULED NOSDR CA110603008Fitting · crackedTHIS PART WAS INSPECTED IAW MFG ASB 212-10-142 B. DURING THE NDT INSP A CRACK WAS FOUND IN THE AREA HIGHLIGHTED BY THE ASB. THE PART HAS BEEN REMOVED FROM SERVICE AND IS WAITING FOR EVALUATION.SDR 2011F00115Line · leakingON CONDUCTING A MX OP CHECK FOR TAIL ROTOR SYS, ON ENGINE START THERE WAS A LEAK NOTICED. ACFT WAS SHUTDOWN AND ON FURTHER INVESTIGATION THERE WAS A HYD LINE FOUND RUPTURED.SDR CA110523002Engine · noisyNOISE/RUMBLE HEARD COMING FROM ENGINE AREA DURING START.SDR CA110518003Bearing Race · failedBEARING RACE FAILURE DISCOVERED AT 1200 HR INSPECTION. GRIP CONTAINING RACE WAS CONTAMINATED WITH METAL FLAKES.SDR CA110518002Grip · unserviceableREQUIRED UT INSPECTION SHOWED CRACK INDICATIONS. GRIP WAS SENT TO MFG FOR EVALUATION. EVALUATION AS FOLLOWS, "GRIP WAS SENT IN FOR UT INSP FOR CRACK INDICATION, INSPECTED WITH BUSHINGS INSTALLED & REMOVED. INSPECTED BORES FOR DIAMETER AND FOUND LOWER TANG BORSDR CA110516019Fuel Control · malfunctionedPOWER ROLLBACK DURING FLIGHT, THE ENGINE ROLLED BACK TO 80 PERCENT NG IN AUTO MODE. THE PILOT SWITCHED TO MANUAL MODE AND THE ENGINE RECOVERED. AFTER LANDING AT BASE AND TROUBLESHOOTING, SUBSEQUENT START ATTEMPTS IN AUTO MODE RESULTED IN A HUNG START AT 40 PER
Back to Bell 212