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 CA110414009Sealant · damagedWHILE COMPLETING 100 HR INSP 5-22A A VOID WAS FOUND IN THE SEALANT OF THE DOUBLER AT THE ROOT END OF THE BLADE. DUE TO THE HOURS ON THE BLADE IT WAS DETERMINED THAT IT IS A MFG FLAW. VOID DEPTH .162" MAX ALLOWABLE DEPTH IS .060"SDR CA110408003Fitting · cracked(CAN) TAIL BOOM LOWER LT ATTACHMENT FITTING FOUND CRACKED ON DAILY INSPECTION. ACFT GROUNDED. R & R WITH NEW PART. CRACK EXTENDS FROM TAIL BOOM ATTACHMENT BOLT HOLE TO EDGE OF FITTING. ALSO, A SECOND CRACK FOUND PROGRESSING FROM THE BOLT HOLE IN THE OPPOSITSDR CA110330004Fitting · cracked(CAN) ONE INCH CRACK IN LOAD FLANGE OF FITTING.SDR CA110322004Blade · delaminated(CAN) DURING DAILY INSPECTION, THE TAIL ROTOR BLADE WAS FOUND TO HAVE DELAMINATED SKIN ON THE OTBD SIDE OF THE BLADE, 4 INCHES FROM END TIP OF BLADE & AFT OF LE STAINLESS STEEL STRIP. THE ALUMINUM SKIN HAD DEBONDED FROM THE SPARE APPROX 5 INCHES SPAN WISE & 3SDR CA080813010Line · bent(CAN) TRANSMISSION OIL COOLER SOLID LINES WERE BENT TO FIT AT DRAIN VALVE ENDS AND WERE INSTALLED OPPOSITE TO THEIR RESPECTIVE DRAIN VALVE TEES. BOTH LINES WERE REPLACED AND RE-ROUTED CORRECTLY.SDR CA110317004Blade · cracked(CAN) MAIN ROTOR BLADE, PN 212-015-501-115 WITH TTSN 2986 .4 HR WAS REMOVED FROM HELICOPTER ON OCTOBER 20 2010 & SENT INTO FACILITY IN FEBRUARY 2011. BLADE WAS SENT IN FOR INSPECTION & FULL CHORD SKIN & HONEYCOMB CORE REPAIR AT STATION 244.0 - 253.0 UPON INSPSDR CA110322009Fuel Sys · blocked(CAN) PARTIAL INTERNAL BLOCKAGE CAUSED FUEL PRESS DIFFERENTIAL SWITCH TO ACTIVATE LIGHT ON CAUTION PANEL FOR NR 1 POWER SECTION.SDR CA110216005Relay · shortedINDICATION ON CAUTION PANEL DIM INTERNAL SHORT.SDR CA110214014Attach Fitting · cracked(CAN) CAP SECTION UNDER UPPER LEFT HAND TAIL BOOM ATTACHMENT FITTING FOUND CRACKED VERTICALLY TO EDGE ON DAILY INSPECTION. AIRCRAFT REMOVED FROM SERVICE. TAIL BOOM REMOVED FOR CAP REPLACEMENT.SDR CA110214012Support Case · crackedMAIN TRANSMISSION SUPPORT CASE FOUND CRACKED ON DAILY INSPECTINO. AME NOTICED OIL WEEPING FROM AREA AROUND LIFT LINK FITTING. TRANSMISSION REMOVED FOR INSPECTION AND REPAIR.SDR CA110210001Fuel Control · inoperativeUPON 1ST START OF THE DAY, NR 1 ENG WOULD NOT ACCELERATE PAST 40 PERCENT NI. PROBLEM WAS TROUBLESHOT & ALL INDICATION POINTED TO THE AFCU. A NEW UNIT WAS THEN INSTALLED & THE ACFT WAS SUCCESSFULLY STARTED. THAT PROVED THE ORIGINAL AFCU WAS THE FAULTY COMPONESDR CA110206002Stiffener · crackedSTIFFENER, IN BASE OF FIN FOUND CRACKED ALONG FLANGE AGAINST SKIN.SDR CA110322010Transfer Valve · failed(CAN) VALVE SLOW TO ACTIVATE, CAUTION LIGHT WILL NOT ALWAYS GO OUT.SDR CA110124002Filter · clogged(CAN) PILOT COMPLAINED OF SLOW ACCELERATION ON NR 2 PS. MEETING WITH MAINTENANCE CREW DECIDED TO TROUBLESHOOT WITH A 4 ACTION RESPONSE. FIRST ACTION WAS TO CHECK ENGINE DRIVEN FUEL PUMP OUTPUT. BOTH ENGINES MEASURE SAME FUEL OUTPUT INDICATING NO PROBLEMS ISDR CA101222006Monitor · misinstalled(CAN) IN-FLIGHT THE MASTER CAUTION THE TRANSMISSION OIL PRESSURE LIGHT ILLUMINATED AND THE TRANSMISSION OIL PRESSURE WAS RAPIDLY FALLING. THE ACFT WAS LANDED IMMEDIATELY IN A SAFE ZONE. UPON LANDING, OIL WAS CONFIRMED LEAKING FROM THE TRANSMISSION. TRANSMISSDR CA110613013Indicator · misoverhauledITT INDICATOR REMOVED FOR REMARKING. UNIT DISSASEMBLED IN O/H FACILITY AND FOUND UN-APPROVED PARTS INSTALLED. UNIT REMOVED FROM SERVICE.SDR CA110214010Engine · power lossPOWER LOSS/IFSD ENGINE SHUT ITSELF DOWN WITHOUT ANY NOTICE. AN UNEVENTFUL SINGLE LANDING WAS MADE. POST EVENT INSP FOUND A LARGE TEAR IN THE GAS GENERATOR CASE. THE ENGINE WAS SENT TO MFG FOR INVESTIGATION WHERE THE CAUSE WAS IDENTIFIED A CRACKING FROM FATISDR CA100930008Case · rupturedHELICOPTER WAS LIFTING OFF STAGING AREA WITH 150FT LONGLINE AND APPROX 2600 LBS EXTERNAL LOAD. WHEN LOAD WAS APPROX 30FT OFF THE GROUND THE PILOT HEARD A LOUD "POP. NR1 ENG HAD FAILED. EXTERNAL LOAD WAS JETTISONED, A SINGLE ENGINE FAILURE EMERGENCY LANDING SDR CA100928006Tee Fitting · loose(CAN) LOSS OF RGB OIL PRESSURE DURING TRAINING FLIGHT, AIRCRAFT EXPERIENCED LOSS OF RGB OIL. PILOT WAS FORCED TO MAKE AN UNSCHEDULED LANDING. INVESTIGATION REVEALED LOSS OF OIL PRESSURE WAS CAUSED BY A LOOSE TEE FITTING ON THE OIL PRESSURE SWITCH DUE TO THE SDR CA100824005Retainer · failed(CAN) DURING THE FIRST REVENUE FLT AFTER THE NR 2 ENGINE WAS CHANGED (APPROX 20 HRS PREVIOUS) THE PILOTS REPORTED THAT CHIP LIGHT FOR THE NR 2 ENG WAS FLICKERING VERY FAINTLY, ALTHOUGH NO LIGHTS WERE SEEN DURING THE POST ENG CHANGE, GROUND RUNS OR TEST FLIGHT.SDR CA100811007Mount · crackedLOCATION OF SMALL CRACK - TOP OF BEAM DIRECTLY UNDER THE ISOLATION MOUNT, FWD. LT OF MOUNT HOLE. CRACK DETECTED DURING ROUTINE INSPECTION, PART REPLACED, SHIMMING AND INSTALLATION OF AFFECTED PART APPEARED OK. ALL OTHER RELATED MOUNTS AND COMPONENTS FOUND SESDR CA100812016Control Tube · noisyINTERNAL NOISE (RATTLING) INSIDE OF CONTROL TUBE ASSY ON MAIN ROTOR SHUTDOWN.SDR CA100726012Packing · pinchedHYDRAULIC LEAK DISCOVERED BY FORESTRY GROUND CREW MEMBER WHILE HOOKING UP WATER BUCKET LONG LINE TO HELICOPTER BELLY CARGO HOOK. PILOT OBSERVED NR2 SYS HYD RESERVOIR FLUID LEVEL BELOW NORMAL LIMITS. AME TRACED LEAK TO NR 2 HYD ACCUMULATOR. PART WAS DISASSEMBSDR CA100726011Actuator · failedACTUATOR ASSY SEIZED/FAILED TO MOVE OR FUNCTION.SDR CA100617006Impeller · mismanufacturedIMPELLER ON OIL COOLER BLOWER ASSY MANUFACTURED INCORRECTLY FROM MFG. CTR SPLINED HUB MACHINED TOO HIGH, CAUSING IMPELLER TO RUB ON OUTER STATOR HSG. PART RETURNED TO MFG FOR WARRANTY.SDR CA100913001Engine · failedABORTED TAKEOFF, DURING TAKEOFF, A CONTINUOUS NOISE WAS NOTED AND THE TORQUE INDICATION OF ENGINE NR 1 WAS 4 PERCENT LESS THAN ENGINE NR 2. ENGINE NR 1 TEMP THEN FELL TO 600 DEGREE C AND A LOSS OF TORQUE OCCURRED. AN EMERGENCY LANDING WAS MADE AND THE ENGINESDR CA100812018Blower · vibration(CAN) PILOT REPORTED HIGH VIBRATION IN TAIL ROTOR PEDALS. THIS IS DUE TO A INTERNAL VIBRATION INSIDE OF OIL COOLER BLOWER ASSEMBLY. (TC# 20100812018)SDR CA100430007Quill · cracked(CAN) TRANSMISSION TAIL ROTOR DRIVE QUILL CORK FOUND LEAKING OIL DURING 600 HOUR INSPECTION AND REPACK OF OUTPUT FLEX COUPLING. DRIVE QUILL REMOVED AND BEARING RETAINER FOUND CRACKED COMPLETELY ACROSS.SDR ALGA3810AL122398Impeller · crackedBLOWER ASSY. REMOVED FROM ACFT DUE TO A CRACKED IMPELLER. IMPELLER WAS CRACKED COMPLETELY THROUGH ON 3 SIDES OF THE MOUNTING BOSS.SDR 2010FA0000164Blade · detachedDURING GROUND RUN FOLLOWING COMPLETION OF ANNUAL INSP AND CHECK OF GENERATOR BEING INOPERATIVE. A VIB. WAS NOTED WITH THE ENGINE SHUTDOWN. INSP OF THE ACFT SHOWED A HOLE IN THE AFT COWLING TO THE RT SIDE OF THE OIL COOLER. THE DAMAGE CONTINUED THROUGH 2 BULSDR CA091211007Support · cracked(CAN) DURING 300 HRS SCHEDULE INSP, A CRACK WAS FOUND IN THE LOWER SECTION OF THE TAILBOOM. AFTER REMOVAL OF THE DEFECTIVE PART THE FORMER LOWER 212-030-124-017 AND THE SUPPORT 212-030-124-037 WERE CRACKED.SDR CA091211006Support · cracked(CAN) DURING A 300 HRS SCHEDULE INSP, 4 CRACKS WERE FOUND AROUND SCREW HOLES OF SUPPORT 205-032-817-019 IN THE TOOLBOOM LOWER AREA.SDR CA100114007Retainer · misinstalled(CAN) PART INSTALLED BACKWARDS, ALLOWING THE FUEL LINE BETWEEN THE AFCU AND MFCU TO BECOME DISCONNECTED. RESULTING IN ENGINE FLAME OUT. ALTHOUGH NOT A CONTRIBTING FACTOR AT THIS TIME, THE RETAINER IS ILLUSTRATED BACKWARDS IN THE IPC AND MM.SDR CA091109006Barrel · cracked(CAN) 2 CRACKS IN BARREL GRIP AREA, COURSE THREAD END, RUNNING LONGITUDLINALY, ONE 1/4 INCH, ONE 1/2 INCH LONG.SDR CA090914002Washer · cracked(CAN) DURING A 600HRS INSPECTION, ONE OF THE WASHER P/N 204-030-913-005 WAS FOUND CRACKED. THE CRACK IS COMING INWARD FROM THE OUTTER CIRCONFERENCE OF THE WASHER. THIS IS THE THIRD TIME THAT THIS WASHER IS BEING REPLACED OVER A PERIOD OF JUST OVER A YEAR, THE SDR CA100505007Transmission · failedDURING FLIGHT, PILOT HAD TRANSMISSION CHIP LIGHT AND RETURNED TO HANGAR TO LAND, ON SHUTDOWN UNUSUAL NOISE WAS HEARD COMING FROM THE TRANSMISSION, CHIP PLUGS AND INTERNAL OIL FILTER WERE REMOVED AND INSPECTED, LARGE CHIPS WERE NOTED ON THE CENTER AND LOWER CHISDR CA090914010Connector · misinstalled(CAN) ACTUATOR CONNECTOR FOR SPHERICAL BEARING SCREW LOCK CUP INCORRECTLY LOCKED FROM MANUFACTURER. (TC# 20090914010)SDR CA090730008Line · crackedFOREST FIRE FIGHTING CREW NOTICED HYD FLUID LEAKING AS HELICOPTER LANDED TO HOOK UP WATER BUCKET CABLE TO CARGO HOOK. HELICOPTER WAS SHUTDOWN AND PILOT FOUND CRACKED LINE IN NR 1 HYD SYS. SUSPECT OVERTIGHTENING OF NUT AND VIBRATION AS PROBABLE CAUSE OF CRACKSDR U0GA125467Engine · stoppedDURING A NEW HIRE INITIAL TRAINING FLIGHT, NR 1 ENGINE QUIT. DEPARTED A CONFINED AREA WITH A SIMULATED ENGINE FAILURE OF THE NR 2 ENGINE. THE SIMULATED NR 2 ENGINE FAILURE WAS INDUCED BY THE INSTRUCTOR WITH PLENTY OF OBSTACLE CLEARANCE PAS VTOCS, ACCELERATINSDR U0GA2009072582699Engine · failedDURING TRAINING FLIGHT, NR 1 ENGINE QUIT. DEPARTED A CONFINED AREA WITH A SIMULATED ENGINE FAILURE OF THE NR 2 ENGINE. THE SIMULATED NR 2 ENGINE FAILURE WAS INDUCED BY THE INSTRUCTOR WITH PLENTY OF OBSTACLE CLEARANCE PAST VTOCS, ACCELERATING TO VY . ALSO THE NSDR CA090727009Plate · improper part(CAN) RETAINER PLATE IS NOT AUTHORIZED FOR INSTALLATION IN A 212 HANGER ASSY, -005 IS REQUIRED. COUPLING INNER SPLINES WORN DUE TO LOSS OF CLAMP UP FORCE.SDR CA090909003Skin · crackedSKIN PN 212-030-099-066 CRACKED AT FWD FAIRING ATTACH ANCHOR NUT.SDR CA090706009Tube · cracked(CAN) ON NR 1 ENGINE START UP THE PILOT NOTED A SLOW AND HUNG START AND WAS UNABLE TO SPOOL ENG TO 100 PERCENT, MX PRESSURE CHECKED PNEUMATIC SYS AND FOUND AIR LEAKING FROM A CRACKED PNEUMATIC TUBE NEAR FLARE AT P3 FILTER.SDR CA090702010Bearing · spalledFOUND FLECKS OF METAL ON CTR CHIP PLUG.SDR CA090603006Drive Shaft · damaged(CAN) COUPLING YELLOW TEMP PLATES FOUND TURNED BLACK, AIRFRAME AND DRIVESHAFT INSPECTED FOR CAUSE, NONE FOUND, DRIVESHAFT REMOVED AND INSPECTED, GREASE FOUND BURNED, DRIVESHAFT REPLACED, DRIVESHAFT SENT TO OVERHAUL FACILITY.SDR U0GA2009052681797Transmission · overservicedDURING CRUISE FLIGHT, NOTICED A HIGH MAIN TRANSMISSION TEMPERTURE. AT THAT TIME MY PASSANGER IN THE BACK SEAT INFORMED ME THAT HE COULD DETECT A BURNED OIL ODOR. TURNED THE ACFT AROUND AND RETURNED TO DEPARTURE. MX DRAINED A LITTLE MORE THE A QUART FROM THESDR CA090511007Windshield · cracked(CAN) WINDSHIELD FOUND CRACKED DURING DAILY CHECK.SDR CA090511008Tee Fitting · cracked(CAN) CRACK FOUND IN THREADED AREA DURING FLUID LEAK INVESTIGATION.SDR CA090511009Seal · leaking(CAN) SEAL FOUND LEAKING DURING DAILY CHECK.SDR CA090408010Turbine · failed(CAN) SHORTLY AFTER T/O, THE NR 1 ENGINE CHIP LIGHT ILLUMINATED, ACCOMPANIED BY RISING TEMPERATURE IN EXCESS OF 810°C. THE PILOT SHUT THE POWER SECTION DOWN AND LANDED WITHOUT FURTHER INCIDENT. MX DETERMINED THAT THE DISTRESS ORIGINATED IN THE POWER SECTION OF
Back to Bell 212