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 = 'CT581401' 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 = 'CT581401' 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 CA020917006Gearbox · contaminated(CAN) THE AIRCRAFT WAS CONDUCTING NORMAL LOGGING OPERATIONS WHEN THE OIL PUMP CHIP LIGHT ILLUMINATED. A/C RETURNED TO BASE & SCREEN WAS REMOVED & CONTENTS INSPECTED. 5 PIECES OF ALUMINUM WERE FOUND, APPROX. 10MM LONG, ONE WAS 5MM WIDE, THE OTHER FOUR WERE 2 TSDR CA020913003Housing · worn(CAN) INPUTS HAVE SIGNS OF METAL TRANSFER IN FROM THE ROLLERS TO THE GEAR HOUSING BORE, ON THE RT HOUSING THE ROLLER PATH IS BREAKING UP. OIL-LITE WASHERS ARE WORN, DEBRIS WAS IN OIL FOUND IN AND AROUND THE ROLLER AREA. LT INPUT THE UPPER OIL-LIGHT WAS REMOVSDR CA020913002Bearing · worn(CAN) BEARINGS IN ACC DRIVE & AGB WERE NEW AT OVERHAUL. ENG RUN IN TEST CELL FOR 4 HOURS. IN A/C FOR 0.2 HRS. AFTER TEST CELL RUN, CHIP DETECTORS INSPECTED, NORMAL. ACC DRIVE UNIT REMOVED & BEVEL GEAR BEARINGS WORN. AGB REMOVED. REMOVED PINION GEAR HOUSING,SDR CA020913001Ring Gear · cracked(CAN) DURING NORMAL OPERATION, RING GEAR CRACKED, CHIP LIGHT ILLUMINATED, AIRCRAFT RETURNED FOR LANDING. GEARBOX REMOVED FOR FURTHER INVESTIGATION. REVEALED BROKEN TOOTH ON RING GEAR, BROKEN TOOTH ON PLANETARY PINION AND DAMAGED SUN GEAR. GEARBOX REPAIRESDR CA020430009Fuel Control · failed(CAN) AT 3.9 HOURS AFTER ENGINE INSTALLATION THE ENGINE PARTIALLY DECELERATED IN FLIGHT. THE ENGINE RESPONDED TO EMERGENCY THROTTLE AND WAS LANDED SAFELY. FUEL CONTROL WAS REPLACED.SDR CA020411004Lock · loose(CAN) AT FREEWHEEL CHANGE LOCKS WERE LOOSE. GEARS WERE REPLACED FOR FURTHER INSPECTION IN SHOP. PARTS WERE REMOVED FROM MAIN GEARBOX.SDR CA060413004Wire Harness · mismanufacturedSIX NEW HARNESSES WERE SENT TO COLUMBIA HELICOPTERS FOR JET CAL TEST. ALL SIX FAILED. THIS WAS THE RESULT OF AN ENGINE NOT PASSING TEST ON THE TEST STAND AND THE FAULT WAS FOUND TO BE A NEW T5 HARNESS. AFTER THAT WE HAVE BEEN SENDING ALL NEW T5 HARNESS OUT SDR CA020205003Cap · failed(CAN) DURING PHASE IVA OPS 6, WE FOUND OIL CONTAMINATION ON ENGINE NR 2 TANK. THE PACKING P/N MS29513-232 ON THE CAP ASSEMBLY P/N 416-50 TO BE THE CAUSE. REPLACED THE PACKING, FLUSHED OIL AND CHANGE OIL FILTER. RAN THE AIRCRAFT FOR 15 MINUTES AND AFTER OIL ANDSDR CA011221003Shaft · sheared(CAN) WHILE ON PAD, WITH ROTORS ENGAGED, IT WAS NOTICED ZERO AMPS ON DC AMMETER. THE GEN IREC SWITCH WAS SELECTED TO REC (RECTIFIED) AND 150 AMPS WAS READ. SUSPECTED DC GEN FAILURE. CARRIED OUT CHECK LIST PROCEDURE & THAT WAS WHEN THE DC GEN LIST ILLUMINASDR CA011106001Support · cracked(CAN) ON BOARD VIBRATION MONITORING SYSTEM INDICATED INCREASING VIBRATION LEVELS AT NR 2 TAIL ROTOR DRIVESHAFT HANGER. VISUAL INSPECTION REVEALED CRACK IN AFT SUPPORT FRAME.SDR CA011012007Freewheel Unit · worn(CAN) DURING LIFTING OP AT 86 PERCENT Q. PILOT NOTICED TORQUE SPLIT ACCOMPANIED BY THUD NOISE & YAW KICK. A/C RT-SRV AREA WHERE INPUT FREEWHEEL UNITS WERE REMOVED FOR INSP. HIGHER THAN NORMAL WEAR FOUND ON BOTH UNITS FOR THE TIME IN SERVICE.AFTER GATHERING INFSDR CA010724004Bearing · making metal(CAN) INVESTIGATION OF A CHIP LIGHT ON FORWARD CHIP PLUG SHOULD A BUILD UP OF BLACK FUZZY PASTE WITH SOME INDICATION OF FERROUS MATERIAL. ENGINE WAS REMOVED AND DISASSEMBLED. SUBSTANCIAL WEAR WAS FOUND ON ACCESSORY DRIVE GEAR BOX IMPUT PISTON BEARINGS. PARTS WSDR CA010711001Access Panel · distorted(CAN) AS THE A/C DEPARTED THE HELI PAD, THE LT ENGINE DOOR OPENED. THE FLIGHT CREW LANDED AT THE END OF THE RUNWAY & ATTEMPTED TO CLOSE THE DOOR. THEY WERE UNSUCCESSFUL DUE TO THE BENT HINGE. THE A/C WAS TAXIED BACK TO THE HANGAR & THE LT ENGINE DOOR WAS REPLASDR CA010522016Plate · cracked(CAN) ON POST FLIGHT INSPECTION A CRACK WAS FOUND EXTENDING UPWARD FROM BIFILAR ATTACH BOLT HOLE ON MAIN ROTOR HUB UPPER PLATE. MAIN ROTOR HEAD REMOVED FROM SERVICE. ON DISASSEMBLY, SHIM CHECK WAS CARRIED AS PER SB 61B10-46, AND FOUND TO BE WITHIN ACCEPTABLE TSDR CA010503017Bearing · failed(CAN) INPUT BEARING FAILED DURING THE INITIAL RUN IN PROCEDURE. INVESTIGATION SHOWED THAT BEARING PUSHER TOOL WAS IMPROPERLY USED CAUSING DEFORMATION OF BEARING CAGE AT OVERHAUL. TOOL WAS REMOVED FROM SHOP TO PREVENT POSSIBLE REOCCURRENCE.SDR CA010301029Blade · debonded(CAN) AIRCRAFT LANDED TO REFUEL. IT WAS NOTED THAT DURING A WALKAROUND THAT, A ROTOR BLADE POCKET HAD BECOME DEBONDED. A TEMPORARY REPAIR WAS MADE AND THE AIRCRAFT WAS FLOWN BACK TO BASE.SDR CA010108019Hub · torn(CAN) DURING SHUTDOWN PILOTS NOTICED A WHISTLING SOUND COMING FROM MAIN ROTOR BLADES. DURING A VISUAL INSPECTION AFTER ROTORS HAD STOPPED A POCKET LOWER SKIN WAS SEEN TO BE MISSING. ROTOR BLADE WAS REPLACED AND THE AIRCRAFT RETURNED TO SERVICE.SDR CA001201024Valve · cracked(CAN) A/C INVOLVED IN HELI-LOGGING OPS 15 MILES SOUTH OF SQUAMISH&60 MINS INTO ITS 1ST CYCLE OF DAY. A/C HAD JUST DELIVERED ITS LOAD TO LOG LDG&ABOUT TO TRANSITION INTO A CLIMB BACK UP HILL WHEN YAW & SUBSEQUENT TORQUE SPLIT NOTICED. FURTHER INVEST. REVEALED SDR CA001122007Fitting · cracked(CAN) ON POST-FLIGHT INSPECTION, UPPER LEFT HAND LUG OF TAIL PYLON HINGE FITTING WAS FOUND CRACKED. HINGE REPLACED WITH STEEL PART NR S6120-66117-041 IN ACCORDANCE WITH S61320-23. (X)SDR CA001012010Hose · leaking(CAN) WHILE IN-FLIGHT, PRIMARY HYDRAULIC PRESSURE DROPPED. AFTER LANDING, FOUND A HYDRAULIC PRESSURE HOSE FROM THE PUMP TO THE MANIFOLD HAD STARTED TO LEAK. HOSE WAS REPLACED AND LEAK CHECKED. AIRCRAFT RETURNED TO SERVICE. (X)SDR CA001012009Check Valve · cracked(CAN) DURING REFUELING OF HELICOPTER, A HYDRAULIC LEAK WAS DETECTED. THE FAULT WAS FOUND TO BE A CHECK VALVE/FITTING FOR THE PRIMARY HYDRAULIC MANIFOLD. FITTING WAS REPLACED WITH A LATER P/N STEEL PART. (X)SDR CA001012012O-Ring · leaking(CAN) WE HAVE HAD 5 CASES OF UNACCEPTABLE GREASE LEAKAGE RATES FROM THE INPUT COUPLINGS.WHEN THE COUPLINGS WERE DISASSEMBLED THE O-RING P/N M83248-1-132 WAS FOUND TO BE EITHER FLAT OR DETERIORATED. ACRO (LANGLEY) TOLD ME THAT THEY DID A HARDNESS TEST ON THEIR SDR CA001012003Gearbox · failed(CAN) TAKEOFF WAS ABORTED WHEN A LOUD BANG WAS HEARD BY FLIGHT CREW. NR 2 ENGINE SHUT DOWN & A/C LANDED BACK ON THE HELI PAD. ON TOUCH DOWN THE TAIL WHEEL MISSED THE PAD & THE AIRCRAFT CAME TO REST ON THE KEEL JUST FORWARD OF THE TAIL WHEEL. ALL PAX WERE UNLOASDR CA000925012Gearbox · cracked(CAN) OIL LEAK WAS DETECTED ON RIGHT HAND FORWARD SIDE OF MAIN GEARBOX. AFTER FURTHER INVESTIGATION, FOUND THERE WAS A CRACK IN THE LOWER HOUSING ASSY. THE CRACK WAS 2.75 INCHES LONG AND LOCATED APPROXIMATELY 4 INCHES ABOVE AND FORWARD OF THE FORE AND AFT SESDR CA000925011Blade · cracked(CAN) THE T/R SPINDLE INSPECTION WAS BEING C/O AT WHICH TIME A CRACK IN THE SKIN OF THE TAIL ROTOR BLADE WAS DISCOVERED. THE BLADE WAS REMOVED FROM SERVICE AND IMMEDIATELY SENT BACK TO THE MANUFACTURER FOR REPAIR EVALUATION. (X)SDR CA000706024Blade · leaking(CAN) WHILE IN-FLIGHT, THE B.I.M. CAUTION LIGHT ILLUMINATED. AIRCRAFT LANDED AND SHUTDOWN. BLADE PRESSURE WAS COMFIRMED TO BE LOWER THAN MINIMUM. ALLOWABLE. BLADE WAS REMOVED AND SENT TO REPAIR FACILITY WHERE IT WAS DETERMINED TO BE LEAKING FROM THE AREA OF SDR CA000621006Transmission · deformed(CAN) INSIDE DIAMETER OF GARLOCK SEAL WAS DEFORMED CAUSING FORWARD TRANSMISSION OIL LEAK. (X)SDR CA000606004Accessory Unit · failed(CAN) AIRCRAFT WAS IN CLIMB AT 90 KNOTS WHEN PILOTS FELT A SUDDEN YAW. IT WAS CONFIRMED THAT NR 1 ENGINE HAD FLAMED OUT. AIRCRAFT WAS LANDED SINGLE ENGINE. INSPECTION OF CHIP PLUGS INDICATED A FAILURE IN THE ACCESSORY DRIVE SECTION. ENGINE WAS REMOVED AND SSDR CA000606008Sprag Clutch · failed(CAN) DURING LOGGING OPERATIONS, NR 2 SPRAGUE CLUTCH FAILED TO ENGAGE ON APPROACH TO DROP ZONE. HELICOPTER WAS STABILIZED IN HOVER AND NR 2 ENGINE WAS SHUT DOWN. HELICOPTER LANDED ON BARGE WITHOUT FURTHER INCIDENT.SDR CA000606005Gascolator · failed(CAN) AIRCRAFT REFUELED AND TAXIED ONTO RUNWAY FOR DEPARTURE. AIRCRAFT BOOST PUMPS WERE NOT TURNED ON AT THIS POINT AS THE PILOTS WERE INSURING ENGINES WOULD RUN WITHOUT BOOST PUMPS AS STATED IN THE OPS MANUAL. WHILE TAXIING ON THE RUNWAY, NR 1 ENGINE FLAMEDSDR CA000511005Blade · torn(CAN) POST FLIGHT INSPECTION REVEALED TWO TEARS IN TAIL ROTOR BLADE POCKET (19 & 16 INCH FROM TIP). IT APPEARS THAT LEADING EDGE TAPE CAME LOOSE AND FLAPPED AGAINST BLADE CAUSING THE TWO TEARS.SDR CA000505006Fuel Control · misriggedENGINE FAILED TO RESPOND TO COLLECTIVE INPUT. A/C COMPLETED TEST FLIGHT TO ISOLATE PROBLEM WITH NO POSITIVE RESULTS. ENGINE CHANGED OUT. REPORT REQUESTED .05, 15, 2000. ENGINE RIGGING SPECIFIED TO BE THE MOST LIKELY CAUSE.SDR CA000511007Bearing · failed(CAN) ENGINE CHIP PLUG INDICATED CHIPS & THEN PLUG CLEANED & INSPECTED, SHOWING NO SLIVERS, ONLY PASTE. NEXT DAY AFTER 50 MINS OF FLT, FLUXS OCCURRED ON FUEL & OIL PRESSURES&NG&THEN ENGINE FLAMED-OUT. SUBSEQUENTLY, SINGLE ENGINE LANDING CARRIED OUT AT LOGGING SDR CA000320001Bearing · worn(CAN) A T/R SPINDLE WAS REMOVED TO REPLACE A LIFE LIMITED PART. WHILE THE SPINDLE WAS OFF, A VISUAL INSPECTION OF THE FLAPPING BEARING INNER RACE REVEALED A CRACK. BEARING REPLACED.SDR CA000118003Blade · torn(CAN) ROTORCRAFT WAS RETURNING TO BASE WHEN SOUND WAS HEARD OF BLADE TAPE COMING OFF A BLADE. NO FURTHER SOUNDS OR PROBLEMS OCCURRED. UPON ARRIVAL AT BASE, IT WAS DISCOVERED THAT THE BOTTOM SIDE OF A MAIN ROTOR BLADE POCKET HAD DEPARTED THE ROTORCRAFT.SDR CA000203004Pump · seized(CAN) NO CONTAMINATION WAS FOUND WITHIN THE FCU AND THE FUEL CENTRIFUGAL PURIFI ER. THE EDP MATCHED BEARINGS WERE FOUND SEIZED IN PUMP BODY. FAA AC 43 -16A ISSUED MAY 1999 WAS REFRENCED TO THE OPERATOR AND THEY HAVE REVIEWED THEIR SYSTEMS AND VERIFIED THE USESDR CA991229022Fuel Control · failed(CAN) NR2 ENGINE WOULD NOT RESPOND PROPERLY TO INCREASED POWER SETTING. FCU REPLACED BUT SUBSEQUENT FAILURE 50 HRS LATER. FCU''S AND FUEL SAMPLES WERE SENT FOR INVESTIGATION. AWAITING FOLLOW UP REPORT. CALL RECEIVED FROM OPERATOR SPECIFYING MATERIAL BREAKDOWN SDR CA000110024Gear · failed(CAN) HELICAL GEARS SENT OUT FOR NICKEL-SULFAMATE REPAIR OF PILOT BORES I.A.W. SIKORSKY S61 OVERHAUL MANUAL. HOWEVER, IT WAS LATER DETERMINED THAT THE REQUIRED MPI CRACK CHECKS AFTER GRINDING WERE NOT CARRIED OUT BY THE COMPANY THAT DID THE REPAIR PROCESS.SDR CA991112004Bevel Gear · broken(CAN) DURING SERVICING REMOVAL OF COARSE SCREEN, ENGINEER NOTICED SEVERAL SMALL PIECES OF NON-FERROUS METAL WHICH WAS FOUND IN PART OF THE BEVEL GEAR TOOTH .SDR CA000301008Bevel Gear · broken(CAN) MAIN GEAR BOX BEVEL GEAR HAS A BROKEN TOOTH. BEVEL GEAR SENT TO ENGINEERING FIRM FOR ANALYSIS AS TO DETERMINE THE CAUSE OF FAILURE. FRACTURE OCCURRED AT HEEL OF THE TOOTH AND FAILURE OCCURRED AS A RESULT OF A FATIGUE MODE OF PROGRESSIVE FAILURE.SDR CA000110023Fuel Control · failed(CAN) FUEL CONTAMINATION WAS FOUND WITHIN THE FCU AND THE FUEL CENTRIFUGAL PURIFIER. THE PURIFIER HAS BEEN SENT FOR TEAR DOWN.SDR CA991027043Drive Shaft · separated(CAN) DURING CLIMB AT 80 PERCENT TORQUE, NR 1 ENGINE LOST POWER AND ROTORCRAFT LANDED ON SINGLE ENGINE. POST-FLIGHT INVESTIGATION REVEALED THAT NR 1 DRIVESHAFT HAD SEPARATED FROM THE TRANSMISSION INPUT DUE TO TRANSMISSION INPUT GEAR SEIZING.SDR ERAA064509Oil Cooler · failedOIL COOLER REPAIRED AND RETURNED TO ERA 7-14-99. HIGH TEMP 1 REACHES 121 DEGREES WITHIN 15 MINUTES OF HOVER. COOLING FIN PLUGGED UP.SDR CA991027037Harness · misrouted(CAN) WIRE CHAFING BETWEEN THE 26 VAC BUNDLE FOR INSTRUMENT LIGHTS AND COMPASS SYSTEM WIRE BUNDLES RESULTED IN A ELECTRICAL SHORT AND SUBSEQUENT LOSS OF PILOT INSTRUMENT LIGHTS AND THE C-14 GYRO SYCRONIZER FOR THE COMPASS SYSTEMS. INVESTIGATION REVEALED THAT SDR CA991208059Gps · failed(CAN) AFTER LANDING ON DECK, THE GARMIN GPS DROPPED OFF-LINE AND PERFORMED AN AUTOMATIC RE-BOOT.SDR CA990927021Bearing · failed(CAN) PINION BEARING WAS IN INITIAL STAGES OF FAILURE.SDR CA991208058Gps · failed(CAN) DURING CRUISE, THE GPS DROPPED OFF-LINE AND PERFORMED AN AUTOMATIC RE-BOOT.SDR CA990915041Blade · cracked(CAN) OVER A 6 WEEK PERIOD, 4 TAIL ROTOR BLADES HAVE BEEN REMOVED FOR SMALL POCKET CRACKS. EACH TIME A BLADE WAS REPLACED, THE T/R WAS REBALANCED TO 0.1 IPS. THE CRACKS OCCURRED ON TWO DIFFERNT ENT T/R ASSEMBLIES. A SPECTRUM RUN FOR VIBRATION IN THE TAIL SESDR CA991208057Gps · failed(CAN) DURING TAXI, THE GARMIN GPS DROPPED OFF- LINE AND THEN PERFORMED AN AUTOMATIC RE-BOOT.SDR 99ZZZX3082Rotor Disc · crackedDURING LIGHT OVERHAUL, THE STAGE 1 COMPRESSOR ROTOR DISC WAS VISUALLY INSPECTED. TWO CRACKS WERE FOUND ON THE AFT FACE, IN THE CORNER, OF THE LT BLADE COVETHAIL SLOTS. ONE EACH IN TWO SLATS. POSSIBLE CAUSE, PITTING AND/OR INCLUSION. RECURRENCE PREVENTION:
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