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 = 'S64E' 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 = 'S64E' 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 MDR03020Strap · crackedSTRAP IS CRACKED ON THE OB SIDE OF THE BLADE APPROXIMATELY 9.125 INCHES FROM THE TRAILING EDGE OF THE FAIRING. THE CRACK STARTS AT THE CUFF END OF THE BLADE AND EXTENDS TOWARD THE TIP END OF THE BLADE APPROXIMATELY 1 INCH. THE CRACKS START WHERE THE LEADING SDR MDR03019Strap · crackedTHE STRAP IS CRACKED ON THE OUTBOARD SIDE OF THE BLADE APPROXIMATELY 9.187 INCHES FROM THE TRAILING EDGE OF THE BLADE. THE CRACK STARTS AT THE CUFF END OF THE BLADE AND EXTENDS TOWARDS THE TIP END OF THE BLADE APPROXIMATELY 1 INCH. THE CRACKS START WHERE THESDR MDR03016Housing · crackedMGB, UPPER HOUSING, CRACKED UNDER NR 1 INPUT, LT SIDE. THE FIELD CREW NOTICED OIL LEAKING FROM MGB UPPER HOUSING UNDER NR 1 INPUT. INITIAL INSPECTION BY SHOP INDICATED OIL RESIDUE IN AREA, BUT NO CRACK WAS NOTICED. FPI INDICATED NO CRACK. HEAT GUNS WERE USSDR CA030702002Fcu · malfunctioned(CAN) A/C HAD JUST DROPPED A 15,000 LB LOAD OF LOGS AT LOG LANDING IN AN UP HILL YARD. PILOT MADE A LT PEDAL TURN TO DEPART LOG LANDING. COLLECTIVE LOWERED TO DESCEND BACK DOWN TO CUT BLOCK, NR 2 ENG N1 UNDER-SPEED WARNING SOUNDED & WITH WARNING LIGHTS, INDICSDR MDR03017Support · crackedFIFTH MOUNT FOUND CRACKED BY FIELD CREW. DURING INSPECTION, FIELD CREW VISUALLY NOTICED CRACK IN FIFTH MOUNT SUPPORT FOR THE RT ENGINE. FURTHER INSPECTION OF FIFTH MOUNT SUPPORT SHOWED CRACK BEGINNING IN .500 INCH RADII OF RT RIB, PN 6435-20278-110 EXTENDINGSDR MDR03015Bearing · disintegratedROLLER BRG FAILED. MGB, SN A6-032, REMOVED FOR MAKING METAL, INDICATED BY MGB CHIP LIGHT. INSP IN SHOP INDICATEDRATCHETING NOISE COMING FROM RT INPUT ASSY WHEN ROTATED. LG AMOUNT OF METALS WERE FOUND IN MGB SUMP. WHILE REMOVING RT 1ST STG PRIMARY INPUT ASSSDR CA030609005Valve · failed(CAN) A/C PICKED UP A 15,000 LB LOAD OF LOGS. PILOT MADE A LT PEDAL TURN TO DEPART FROM LOGGING CUT BLOCK & LOWERED COLLECTIVE TO DESCEND TO LOG LANDING. CREW HEAR A SWOOSH SOUND AT WHICH TIME NR 2 ENG N1 UNDER-SPEED WARNING SOUNDED & WARNING LIGHTS ILLUMINATESDR CA030331006Line · frozen(CAN) A/C WAS COVERED IN SNOW AND ICE & REQUIRED EXTENSIVE PREHEATING. ENGS WERE STARTED & NR 1 ENG TOOK LONGER TO LIGHT OFF. ONCE ALL WAS IN GREEN, A/C LIFTED OFF. APPROX. 10 MINS INTO 1ST CYCLE, CREW NOTICED ENGS WERE UNMATCHED. ATTEMPTED TO MATCH THEM USDR JYD2003F00000Fitting · crackedCRACK FROM RIVET HOLE BOTTOM LEFT CORNER TO OUTER EDGE OF FITTING. CRACK LENGTH APPROXIMATELY .5000 INCH. THIS IS ONE OF FOUR EARS THAT ATTACH TO THE PYLON LONGERONS. THIS PART OF THE ASSEMBLY THAT THE TAIL ROTOR GEARBOX ATTACHES TO. CAUSE UNKNOWN AT THIS SDR 2003FA0000138Blade · damagedONE OF THE TWO TRAILING EDGE STUDS THAT WAS HOLDING THE TIP END WEIGHT PACKAGE FRACTURED (TRAIL EDGE). THE FRACTURE OCCURED APPROX. 1/4 INCH BELOW THE LOCK RING IN THE BALANCE PLATE ASSY. THIS CAUSED THE LEADING EDGE STUD TO DEFORM, ALLOWING THE WEIGHT PACKASDR CA030102002Connector · loose(CAN) WITH FUEL QTY GAUGES INDICATING 550 LBS IN THE FWD TANK & 500 LBS IN THE AFT TANK & LOW LEVEL WARNING LIGHTS ILLUMINTED, FLT CREW FELT THEY HAD ENOUGH FUEL REMAINING TO RETURN TO THE LOGGING AREA FOR ONE MORE TURN. WHILE PICKING UP THE LAST TURN, BOTH OFSDR CA021122007Fuel Control · failed(CAN) A/C DEPARTED WITH A 13,000 LB LOAD OF LOGS, COLLECTIVE WAS LOWERED TO DECREASE ENGINE POWER. CREW HEARD A SWOOSH SOUND & NR 2 ENG N1 UNDER-SPEED WARNING SOUNDED & WARNING LIGHTS ILLUMINATED INDICATING A SOFT STALL. JETTISONED LOAD AND EXECUTED INFLIGHT SDR MDR02011Tip Cap · brokenTRAILING EDGE TIP WEIGHTS (UP TO 5 EA) AND ATTACHMENT BOLT (1 EA) DEPARTED FROM TIP RIB ASSEMBLY AND WENT THROUGH TIP CAP. DURING THE POCKET REPLACEMENT PROCESS AT SUPPLIER, A TIP RIB WAS INSTALLED IN THE NEW POCKET ASSEMBLY THAT WAS MISSING AN INBOARD DOUBLESDR JYD2002F00004Wheel · crackedTWO CRACKS FOUND IN FORWARD INDEX WHEEL, HIGH-SPEED SHAFT (SN 46) REMOVED FROM SERVICE FOR O/H HAVING A TSO/ 2992.8 WITH AN UNK TT. DURING INSPECTION PROCESS, MAG PARTICLE INSP DETECTED TWO CRACKS. CRACK 1 LOCATION: BEGINNING AT 11 OCLOCK POSITION IN 1.625 SDR JYD2002F00000Spar · crackedCRACK WAS FOUND ON THE TIP END OF MAIN ROTOR BLADE SPAR (PN 641520504102/ SN 64-65325910). DURING POST FLIGHT INSPECTION, FIELD CREW VISUALLY DETECTED A CRACK INDICATION ON TOP SIDE OF SPAR. TOTAL CRACK LENGTH IS APPROX. 2 INCHES LONG WITH 1.5 INCHES EXTENDSDR JYD2003F00002Hub · crackedFRONT HUB (PN 712701, SN 3V4176) FOUND CRACKED DURING OVERHAUL INSP. COMPRESSOR (SN 672571) WAS REMOVED FROM SERVICE DUE TO REACHING ITS OVERHAUL INTERVAL, HAVING A (TSO 2987.9 HOURS), (TT OF 5978.0 HOURS). DURING OVERHAUL INSPECTION, TWO CRACKS WERE DETECTESDR JYD2002F00006Compressor Wheel · crackedSECOND STAGE COMPRESSOR DISK WAS FOUND CRACKED DURING OVERHAUL INSPECTION. COMPRESSOR WAS REMOVED FROM SERVICE DUE TO REACHING ITS OVERHAUL INTERVAL, HAVING A TSO OF 2987.9 HOURS AND TT OF 5978.0 HOURS. DURING OVERHAUL INSPECTION, FIVE CRACKS WERE DETECTED BSDR JYD2001F00005Hub · crackedFRONT HUB, PN 712701, SN 3V4170 FOUND CRACKED DURING OVERHAUL. COMPRESSOR WAS REMOVED FROM SERVICE DUE TO REACHING ITS OVERHAUL INTERVAL. DURING THE OVERHAUL INSPECTION, TWO CRACKS WERE DETECTED BY FLUORESCENT PENETRANT INSPECTION(FPI). 1ST CRACK LOCATION DSDR JYD2001F00004Bevel Gear · crackedMAIN GEARBOX PN 643520400063, SN A6032 WAS REMOVED FROM SERVICE WITH A TOTAL TIME OF 3683.8 AND A TIME SINCE OVERHAUL OF 1172.0 FOR AN OVER TEMP CONDITION. DURING OVERHAUL INSPECTION, THIRTEEN CRACKS WERE DETECTED BY FLUORESCENT PENETRANT INSPECTION, EXTENDINSDR JYD2001F00003Compressor Wheel · crackedCOMPRESSOR, PN JFTD12A4A, SN 672491 HAVING A TOTAL TIME OF7090.9 AND A TIME SINCE OVERHAUL OF 3147.9 WAS REMOVED FOR OVERHAUL. DURING INSPECTION, 14 CRACKS WERE DETECTED IN THE 3RD STAGE COMPRESSOR DISK PN670403, SN M103AA0069 BY LIQUID PENETRANT INSPECTION. SDR JYD2001F00002Plate · crackedCRACKS FOUND IN ROOT AREA OF THREE INTERNAL SPLINES OF LOWER PLATE OF 2ND STAGE PLANETARY PLATE ASSY. MAIN GEARBOX WAS REMOVED FOR OVERHAUL. DURING THE INSPECTION PROCESS, THREE CRACKS WERE DETECTED BY FLUORESCENT PENETRANT INSPECTION INTHE INTERNAL SPLINES SDR CA011012008Servo Valve · failed(CAN) A/C IN LOGGING OPS NEAR SAYWARD, BC. AS PILOT MADE HIS APPROACH TO LOG LDG& INITIATED FLARE TO SLOW DOWN HIS APPROACH, A/C'S NOSE ABRUPTLY PITCHED UP & CONTINUED TO DO SO EVEN WITH FULL FWD CYCLIC APPLIED. A/C FINALLY LEVELED OFF THEN BEGAN VIOLENTLY PITSDR 20010613CW017Blade · crackedBLADE REMOVED FOR BIM INDICATION. THE SPAR IS CRACKED ON BOTTOM SIDE UNDER NR 9 POCKET, APPROXIMATELY 1 INCH STARTING AT BACK WALL RADIUS, RUNNING CHORDWISE TOWARDS LEADING EDGE. PROBABLE CAUSE: CORROSION.SDR 20010524CW002Housing · crackedDURING TEARDOWN FOR OVERHAUL, A CRACK WAS VISUALLY NOTICED AT APPROX THE 2 OCLOCK POSITION(AS INSTALLED ON AIRCRAFT) IN THE STRADDLE MOUNT OF THE IDLER GEAR ALIGNMENT BEARING PN SB2154-1 OF CENTER HOUSING PN 6435-66409-043. FURTHER INSPECTION AFTER REMOVAL OFSDR 20010427CW008Seal · crackedENGINE DISASSEMBLED FOR REPAIR OF COMPRESSOR. AT DISASSEMBLY, 9TH STAGE DISK DOUBLE LIPPED REAR ROTATING AIRSEAL, WAS FOUND TO BE CRACKED IN 3 PLACES, APPROXIMATELY 0 , 30, AND 120 DEGREES. ENGINE WAS OPERATED UNDER NORMAL CONDITIONS AND NO ABNORMALITIES SDR 20001219SH020Blade · crackedTHE TOP SIDE OF THE TRAILING EDGE RETENTION BLOCK SCREW HOLE HAD A CRACK WHICH EXTENDED APPROXIMATELY 360 DEGREES AT A 7 O CLOCK POSITION (AS VIEWED FROM THE TOPSIDE LOOKING DOWN). THIS CRACK WAS DISCOVERED DURING A VISUAL INSPECTION PERFORMED IN THE FIELD. SDR 20001218SH001Blade · crackedTHE TOP SIDE OF THE TRAILING EDGE RETENTION BLOCK SCREW HOLE HAD A CRACK WHICH EXTENDED APPROXIMATELY .360 INCH AT A 7 O''CLOCK POSITION (AS VIEWED FROM THE TOPSIDE LOOKING DOWN). THIS CRACK WAS DISCOVERED DURING A VISUAL INSPECTION PERFORMED IN THE FIELD. (SDR 20001012SH019Structure · crackedDURING TEARDOWN, MGB, PN 6435-20400-063, SN 16-084, FOR O/H, 5 CRACKS VISUALLY NOTICED IN 5 OF 9 LIGHTENING HOLES IN LOWER PLATE OF 2ND STAGE PLANETARY PLATE ASSY, P/N 6435-20231-014, SN EAC 3691. FLUORESCENT MAGNETIC PARTICLE INSPECT(FMPI) REVEALED 8 CRACKS.SDR 20001219SH021Housing · crackedMAIN LANDING GEAR, PN 6425-50100-013, -014, WAS REMOVED FOR OVERHAUL. DURING THE FLUORESCENT MAGNETIC PARTICLE INSPECTION PROCESS, 15 LINEAR INDICATIONS, NOT VISIBLE TO THE NAKED EYE, WERE REVEALED ON THE UPPER COLLAR HOUSING WITH MEASUREMENTS OF .093 INCH TOSDR 20001218SH003Housing · crackedMAIN LANDING GEAR PN 6425-50100-013, -014 WAS REMOVED FOR OVERHAUL. DURING THE FLUORESCENT MAGNETIC PARTICLE INSPECTION PROCESS, 15 LINEAR INDICATIONS, NOT VISIBLE TO THE NAKED EYE, WERE REVEALED ON THE UPPER COLLAR HOUSING WITH MEASUREMENTS OF .093 INCH TO SDR 20001218SH002Housing · crackedMAIN LANDING GEAR PN 6425-50100-013, -014 WAS REMOVED FOR OVERHAUL. DURING THE FLUORESCENT MAGNETIC PARTICLE INSPECTION PROCESS, 15 LINEAR INDICATIONS, NOT VISIBLE TO THE NAKED EYE, WERE REVEALED ON THE UPPER COLLAR HOUSING WITH MEASUREMENTS OF .093 INCH TO SDR 20001219SH019Arm · crackedARM ASSEMBLY HAD CRACK INDICATION ON OUTBOARD MOUNTING LUG EXTENDING FROM .256 INCH/.252 INCH DIAMETER THROUGH-HOLE TO .34 INCH RADIUS. CIRCUMSTANCES UNDER WHICH CRACKING OCCURRED ARE UNKNOWN. POSSIBLE CAUSE IS FROM FRETTING MOVEMENT BETWEEN SLEEVE MOUNTING SDR 20001218SH006Arm · crackedARM ASSEMBLY HAD CRACK INDICATION ON OUTBOARD MOUNTING LUG EXTENDING FROM .256 INCH/.252 INCH DIAMETER THROUGH HOLE TO .34 INCH RADIUS. CIRCUMSTANCES UNDER WHICH CRACKING OCCURRED ARE UNKNOWN. POSSIBLE CAUSE IS FROM FRETTING MOVEMENT BETWEEN SLEEVE MOUNTING SDR CA000614013Gearbox · stripped(CAN) COPILOT NOTICED NR 2 ENGINE OIL PRESSURE IND FLUCTUATING THEN FOLLOWED BY ILLUMINATION OF ENGINE OIL PRESSURE WARNING LIGHT. PILOT BROUGHT ENGINE BACK TO FLT IDLE WHERE ENG OIL PRESSURE STABILIZED AT 38 PSI. ON FINAL APPROACH, ENG OIL PRESSURE DROPPED SDR 20000405SH022Bearing · making metalAFTER A HALF-HOUR GROUND RUN AND 0.5 FLIGHT, FOUND A LARGE VOLUME OF DISCOLORED (PURPLE IN APPEARANCE) AND METAL CONTAMINATED GREASE HAD EXTRUDED PAST THE BEARING SEAL AND WAS FOUND ON THE A/C DECK UNDER THE BEARING. THE BEARING WAS NOT HOT TO THE TOUCH AT THSDR CA991208075Valve · worn(CAN) ENGINE EXPERIENCED A SOFT STALL; POWER LOSS AND AN INCREASE IN ITT. THIS IS DUE TO AN OVERFUEL OR INADEQUATE AIR CONDITION IN THE COMBUSTOR. CORRECTIVE ACTIONS WERE DEVELOPED BY AIR CRANE AND P&W. HPX FUEL PUMP GEAR DESIGN CHANGE ELIMINATING THE MATESDR 99ZZZX4664Bearing · failedDUPLEX BEARING, PN SB1060-102, SN EAC 1727, TT OF 792.0 HRS, FAILED IN MGB, PN 6435-20400-065, SN A6-037, LEAVING LARGE FRAGMENTS OF FERROUS METAL IN SUMP AND SUMP SCREEN. FURTHER INSP INDICATED BOTH INNER-BEARING RACES OF SB1060-102 DUPLEX BEARING INSTALLED SDR CA991208074Blade · broken(CAN) OPERATOR HAS IMPOSED A LIMIT OF 36 GRAMS MINIMUM WEIGHT ON ALL THE BLADES AT INSTALLATION. A PERIODIC STRUM CHECK IS ALSO IMPOSED.SDR 99ZZZX1657Blade · crackedBLADE REMOVED FROM AIRCRAFT DUE TO BIM INDICATION. ALL CRACKS WERE LOCATED ON BOTTOM SIDE OF THE BLADE. SB-64E-62-10-01, WHICH ULTRASONICALLY INSPECTS THE TWO MOST OUTBOARD BOLT HOLES ON THE TOP AND BOTTOM SIDE, WAS C/W 39.8 HOURS PRIOR TO REMOVAL OF THE BLASDR 99ZZZX1679Blade · damagedDURING DAILY INSPECTION, THE POSSIBILITY OF A TABLOCK FAILURE WAS INVESTIGATED USING A 'BRIGHT LIGHT'. THE ENGINE WAS REMOVED AND SENT TO EAC WHERE A BORESCOPE INSPECTION WAS PERFORMED. DURING THE INSPECTION, ONE 3RD STAGE BLADE TABLOCK WAS FOUND MISSING. TSDR 97ZZZX3841Blade · crackedSPAR IS CRACKED ON THE BOTTOM SIDE BACKWALL RADIUS APPROXIMATELY 112.1 INCHES FROM TIP END. SPAR AT CRACK LOCATION SHOWS NO OBVIOUS SIGNS OF DAMAGE ON THE EXTERIOR SURFACE.SDR JYDR970327Shoulder Bolt · crackedFOUND CRACK IN FIRST TWO THREADS WITH MPI. FOUND CRACK-LIKE INDICATION ON INNER RACE ABOUT .750 INCH LONG WITH MPI. COMPONENT P/N 6511007000019. PART MARKINGS: VENDOR CODE - 81996 - U. S. ARMY AVIATION AND TROOP COMMAND. THIS IS A BREAKOUT PART. (X)SDR 96ZZZX5194Tablock · missingTABLOCK FOUND MISSING AT POST-FLIGHT INSPECTION ON 7-4-96 DUE TO NOISE FROM STATOR RUBBING. LAST OVERHAUL PERFORMED BY SABRELINER. WHEN INSPECTING COMPRESSOR THROUGH INLET, CONTACT OF 3RD STAGE BLADE NOTED ON FACE OF 4TH STAGE STATOR NEAR CENTERLINE OF ENGINSDR 96ZZZX5181Tablock · missingTABLOCK MISSING AT POST-FLT INSP ON 3-29-96. LAST O/H PERFORMED BY EAC ON 3-23-95. WHEN INSP COMP THRU INLET, CONTACT OF 3RD STG BLD NOTED ON FACE OF 4TH STG STATOR NEAR CENTERLINE OF ENG (ROOT END OF BLD). BLD MOVED AFT CONTACTING FRONT OF STATOR DUE TO TASDR CA960304005Pump · making metal(CAN) DURING HOVER AFTER 18 MINUTES OF FLIGHT, THIS LOGGING HELICOPTER DEVELOPED A STIFFNESS OF CYCLIC AND THEN COLLECTIVE PITCH. SLINGING WAS ABORTED AND PRECAUTIONARY LANDING WAS CARRIED OUT. AFTER FURTHER INVESTIGATION, IT WAS DISCOVERED THAT THERE WAS META
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