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 CA080925006Engine · malfunctioned(CAN) WHILE DEPARTING AREA WITH AN AIRSPEED OF 30 TO 40 KNOTS AND A 500 FT PER MINUTE RATE OF DESCENT, NR 2 ENGINE N1 LOW RPM AUDIO HORN SOUNDED ALONG WITH ILLUMINATION OF NR 2 ENGINE LOW OIL PRESSURE LIGHT. A SCAN OF THE ENGINE GAUGES REVEALED THE NR 2 ENGINSDR CA080530001Servo · loose(CAN) DURING A POST-FLIGHT INSP, MECHANIC FOUND MOVEMENT BETWEEN THE FORK AND PISTON. THE PRIMARY SERVO WAS REPLACED. AFTER DISASSEMBLY AT REPAIR STATION, IT WAS DISCOVERED THAT THE MOVEMENT WAS CAUSED BY THE BREAKDOWN OF A LAMINATED REPAIR SHIM INSTALLED BETSDR CA061218007Oil System · malfunctioned(CAN) THE AIRCRAFT WAS INVOLVED IN HELICOPTER LOGGING OPERATIONS. AS THE AIRCRAFT WAS APPROACHING THE LOG LANDING WITH A LOAD, THE FLIGHT CREW WERE ALERTED BY A LOW OIL PRESSURE WARNING LIGHT FOR THE NR (2) ENGINE. A SCAN OF THE CORRESPONDING OIL PRESSURE INDSDR 2006FA0001195Damper · broken(REF: MDR06-093) DAMPER WAS REMOVED FROM THE AIRCRAFT DUE TO, THE PISTON PN 6410-26005-104, SN 550 FOUND BROKEN AFTER SHUTDOWN OF HELICOPTER. THE PISTON ROD BROKE NEAR THE FORK ASSEMBLY, PN 6410-26211-041 AND APPEARS TO BE BROKEN AT THREADS. DAMPER WAS INSTASDR CA061218010Bolt · damaged(CAN) THE AIRCRAFT WAS INVOLVED IN HELICOPTER LOGGING OPERATIONS. THE YARDING PROFILE WAS A DOWN HILL FLIGHT FROM THE HARVEST CUT BLOCK TO A ROAD SIDE LOG LANDING. AFTER ENCOUNTERING DOWN FLOWING WIND CONDITIONS THROUGH OUT THE FIRST LOGGING CYCLE OF THE DAY SDR 2006FA0001137Turbine Blades · fractured(REF NR: MDR06-092) VIBRATION FELT BY CREW, UPON LANDING, MAINTENANCE PERSONNEL FOUND METAL PARTICLES IN NR 2 ENGINE EXHAUST. UPON CLOSER EXAMINATION, A 2ND STAGE TURBINE BLADE WAS FOUND TO BE FRACTURED APPROXIMATELY 1 INCH FROM THE ROOT. THE FRACTURED PIECSDR CA061018003Rod · broken(CAN) THE AIRCRAFT WAS INVOLVED IN AERIAL LOGGING OPERATIONS AND HAD JUST SHUT DOWN FOR IT’S MIDDAY MAINTENANCE. THIS MAINTENANCE INVOLVES A FLUID LEVELS CHECK, SERVICING AND INSPECTION OF CRITICAL AREAS ON THE AIRCRAFT. ON THIS PARTICULAR DAY THE MAIN ROTOR DSDR CA061011013Turbine Blades · broken(CAN) THE AIRCRAFT WAS INVOLVED IN AERIAL LOGGING OPERATIONS, ON A SHORT FINAL APPROACH TO THE LOG LANDING THE AIRCRAFT DEVELOPED A VERY NOTICEABLE HIGH FREQUENCY VIBRATION THAT WAS FELT BY THE FLIGHT CREW THROUGHOUT THE AIRCRAFT INCLUDING THE FLIGHT CONTROLS.SDR 2006FA0001135Bearing · cracked(REF NR:MDR06-090) MAIN GEARBOX PN 6435-20400065, SN A6-011 WAS REMOVED DUE TO FINDINGS OF FERROUS METAL IN THE OIL SCREEN AND FILTER. UPON DISASSEMBLY AND TEAR DOWN, THE SOURCE OF THE FERROUS METAL WAS DISCOVERED TO BE COMING FROM GHE SECOND STAGE INPUT ALSDR CA060704011Fuel Control · failed(CAN) AFTER SETTING A TURN OF LOGS DOWN ON LOG LANDING WITH A LT CROSS WIND, ACFT TURNED FULLY INTO WIND & BEGAN A CLIMB BACK UP HILL TO LOGGING UNIT WITH APPROXIMATELY 60% TORQUE INDICATED. AFTER ABOUT 7-10 SECONDS INTO CLIMB, N1 UNDERSPEED WARNING HORN SOUNSDR CA060621001Engine · failedA/C INVOLVED IN HELI-LOGGING OPS WITH A/C IN HOVER MADE A MODERATE PWR REDUCTION TO REPOSITION GRAPPLE ON A LOG. AS PWR WAS REDUCED A "WHOOSH" SOUND WAS HEARD AND N1 WARNING HORN ACTIVATED FOR NR 2 ENG. FLT CREW IDENTIFIED AND CONFIRMED THAT NR 2 ENG ENCOUNTESDR 2006FA0000795Spar · cracked(REF NR: MDR06-088) IB SIDE OF SPAR ON TRAILING EDGE HAS A CRACK. THE CRACK IS APPROX .482 INCH LONG AND RUNS FROM TIP END OF BLADE, DOWN INTO THE SCREW HOLE COUNTERSINK. BLADE HAS ACCUMULATED 660.4 HOURS SINCE LAST REPAIR. (K)SDR CA051102003Engine · failed(CAN) AFTER SLIGHT REDUCTION IN PWR SETTING PILOT HEARD A WHOOSH SOUND FOLLOWED BY N1 LOW RPM AUDIO WARNING HORN. CO-PILOT IDENTIFIED NR1 ENG IN A ROLLBACK CONDITION WITH A DECREASING N1 SPEED AND AN INCREASING T5 TEMP. AFTER VERIFICATION, EXECUTED A SHUTDOWNSDR CA051102002Fuel Control · failed(CAN) PILOT ELECTED TO BACK AC OUT AWAY FROM LOG LANDING. AS AC STARTED ITS REARWARD DESCENT DOWN TO LOGGING BLOCK, PILOT HEARD WHOOSH SOUND FOLLOWED BY AN ENG LOW RPM AUDIO WARN HORN. NR 2 ENG WAS IN ROLLBACK CONDITION W/DECREASING N1 SPEED, INCREASING T5 TEMSDR CA051013004Clamp · misinstalled(CAN) DURING GROUND RUN PHASE OF MAIN GB REPLACEMENT, NR 2 GEN VESPAL DRIVE SPLINE ADAPT STRIPPED OUT CAUSING GEN TO FALL OFF LINE. GEN WAS REMOVED FROM ACCY GB, DRIVE SPLINE ADAPTOR WAS REPLACED, GEN WAS REINSTALLED, FUNCTION TESTED. AC WAS RETURNED TO SERVISDR CA050824011Line · cracked(CAN) AC WAS INVOLVED IN LOGGING OPS. AS AC WAS APPROACHING LOG LANDING, PILOTS WERE NOTIFIED THAT WHITE SMOKE WAS COMING FROM NR 2 ENG. AC PROCEEDED TO SERVICE LANDING TO HAVE MAINT CREW LOOK AT PROBLEM. ENROUTE, COPILOT NOTICED WHITE SMOKE COMING FROM ENSDR CA050711003Engine · failedA/C INVOLVED IN AERIAL GRAPPLE LOGGING OPS ON DOWN WIND APPROACH TO LOG LANDING WITH A 15,000 LB SINGLE LOG LOAD. PILOT REDUCED POWER TO 30% TQ. UPON ACTION CREW HEARD SOUND OF ENG SPOOLING DOWN FOLLOWED BY LOW RPM AUDIO WARNING HORN & ILLUM OF WARNING LIGHTSDR 2005FA0000818Duct · crackedNR 1 ENGINE REMOVED FROM ACFT, DUE TO 5 INCH AXIAL BULGE AT OUTER TURBINE CASE, 2-3 OCLOCK POSITION WITH APPROX .5625 INCH HORIZONTAL CRACK RUNNING THROUGH CENTER MOST PORTION OF THE BULGED AREA. UPON REMOVAL OF ENGINE HOT SECTION, TURBINE OUTLET DUCT FOUNSDR 2005FA0000817Thrust Washer · wornMAIN GEAR BOX, SN A6051 REMOVED FOR BRASS CONTAMINATION. UPON DISASSEMBLY DISCOVERED BRASS MATERIAL WAS FROM SECOND STAGE PLANETARY THRUST WASHERS. 34 OUT OF 36 THRUST WASHERS WORN ON ID BEYOND MAX SERVICEABLE LIMITS. 18 EA BEARINGS HAD SHARP EDGES INNER RACSDR 2005FA0000341Spar · cracked(MDR05-074) THE SPAR IS CRACKED ON THE BOTTOM SIDE OF THE BLADE BETWEEN POCKET LOCATIONS NR 5 AND NR 6. CRACK IS APPROXIMATELY .300 INCH IN LENGTH .650 INCH FROM THE BACKWALL RUNNING CHORDWISE TO .950 INCH FROM THE BACKWALL. BLADE HAD A BIM INDICATION AND WASDR 2005FA0000339Axle · cracked(MDR05-073) FOUND CRACKED DURING NDT INSPECTION. CRACK IS APPROXIMATELY 1 INCH IN LENGTH AND IS IN THE KEY GROOVE. THIS IS FIRST KNOW DEFECT OF THIS TYPE FOR THIS PART. CAUSE IS UNKNOWN AND NO RECOMMENDATIONS TO PREVENT RECURRENCE AT THIS TIME. (K)SDR 2005FA0000002Spar · crackedBLADE WAS RECEIVED WITH AN UNSERVICEABLE BIM INDICATION. DURING LEAK CHECK, A CHORDWISE CRACK, APPROX .5 INCH LONG WITH A CORROSION PIT IN THE CENTER, WAS FOUND. THE CRACK IS LOCATED APPROX 70.75 INCH FROM TIP END AND 3.25 INCH FROM L/E. CORROSION PIT A CENSDR JYDRMDR04066Bearing · crackedTHE AIRCRAFT CREW REPORTED, AFTER PULLING MAX POWER, THAT THE AC JUMPED. AFTER RETURNING TO THE LANDING, THE MECHANICS CHECKED THE CHIP DETECTOR IN THE MAIN GEAR BOX AND FOUND FERROUS METAL. UPON TEARDOWN OF THE GEARBOX IN THE SHOP, DISCOVERED THAT THE INNERSDR MDR04060Spacer · crackedCOMPRESSOR, SN 672543, CAME INTO THE SHOP AND DURING THE PRELIMINARY TEST RUN, THE VIBES WERE AT 1.7 MILS. WITH THE VIBES EXCEEDING THE LIMITS, THE COMPRESSOR HAD TO BE DISASSEMBLED FOR BALANCE. DURING THE VISUAL INSPECTION OF THE 3-4 SPACER, THERE APPEARED SDR 2004F00385Cam · failedMAIN GEARBOX S/N A6-168 WAS REMOVED FOR OVERHAUL FROM THE AIRCRAFT. THE 2ND STAGE ASSY WAS DISASSEMBLED AND CAM ASSY WAS REMOVED AND CLEANED FOR NDT INSPECTION. UPON INSPECTION FROM NDT, 2 CRACKS WERE FOUND TO BE LOCATED ON GEAR TOOTH AREA. EACH CRACK APPROSDR 2004F00336Housing · crackedMAIN GEAR BOX S/N A6-168 WAS REMOVED FOR OVERHAUL AND CRACK IN MAIN AFT SIDE OF INPUT FROM THE AIRCRAFT. DURING FPI, THERE WAS A CRACK FOUND IN THE LEFT INPUT BOTTOM SIDE APPROXIMATELY .5 INCH LONG, AND THE RIGHT SIDE WAS FOUND TO ALSO HAVE A CRACK INDICATIONSDR 2004F00286Duct · crackedDURING DISASSEMBLY OF N1 SECTION, IT WAS NOTICED THAT THERE WAS A LARGE PIECE OF MATERIAL WEDGED IN BETWEEN TWO 1ST STAGE BLADES. UPON FURTHER DISASSEMBLY/INVESTIGATION THE OUTLET DUCT ASSEMBLY WAS FOUND TO BE MISSING A LARGE SECTION OF THE OUTER DUCT APPROXISDR 2004F00364Splice · crackedIN THE COURSE OF PERFORMING POST FLIGHT INSPECTION THE FIELD MAINTENANCE CREW DISCOVERED A CRACKED IN THE LEFT SPLICE FITTING. THE CRACK ORIGINATED AT THE FORWARD HI-LOCK FASTENER ON THE PYLON SIDE FUSELAGE 770 INCH WL 178 LBL 14. THIS CRACK MEASURES .400 INSDR CA040623002Dump Valve · malfunctioned(CAN) AS COLLECTIVE WAS LOWERED FLIGHT CREW HEARD A (WHOOSH) SOUND FOLLOWED BY AN ENG N1 UNDER-SPEED WARNING AUDIO. FLIGHT CREW VERIFIED ENG, IMMEDIATELY EXECUTED AN IN-FLIGHT SHUTDOWN OF NR 1 ENG TO PREVENT OVER-TEMP CONDITION. WITH NR 1 ENG SHUTDOWN, AC RETUSDR CA040603003Dump Valve · malfunctioned(CAN) PILOT BEGAN DESCENT, HEARD (WHOOSH) SOUND TYPICAL OF SOFT STALLING ENG. FOLLOWED BY N1 UNDERSPEED AUDIO, INDICATOR LIGHT WARNING. FLT CREW VERIFIED NR 1 ENG AS BEING AT FAULT. COPILOT SHUTDOWN ENG, BEGAN TO MOTOR TO DECREASE T5 TEMP WHILE PILOT RELEASEDSDR CA040527004Duct · failedA/C WAS INVOLVED IN HELICOPTER LOGGING OPERATIONS IN THE AREA OF POWER RIVER BRITISH COLUMBIA. DURING THE FIRST LOGGING CYCLE OF THE DAY THE FLIGHT CREW NOTICED WHAT APPEARED TO BE SMOKE IN THE COCKPIT. AN IMMEDIATE A CHECK OF ALL SYSTEMS AND CIRCUIT BREAKERSDR CA040519005Pump · failed(CAN) THE FLIGHT CREW WAS ALERTED BY THE ILLUMINATION OF THE ENGINE OIL PRESSURE WARNING LIGHT FOR NR 1 ENGINE. A CHECK OF THE CORRESPONDING OIL PRESSURE INDICATOR RELIEVED ZERO PSI. THE CREW IMMEDIATELY SHUT DOWN THE SUBJECT ENGINE, RETURNED TO THE SERVICE SDR MDR04048Blade · crackedDURING ROUTINE INSPECTION, THE POCKET (PN 6516100010041) WAS FOUND CRACKED ON THE OB SIDE APPROX 6 INCHES FROM THE LE AND 56.5 INCHES FROM THE TIP END. THE CRACK RUNS UNDER THE STIFFENER ON THE POCKET. THE CRACK IS APPROXIMATELY 1.25 INCHES IN LENGTH. PROBASDR MDR04049Strap · crackedDURING ROUTINE INSP, THE STRAP WAS FOUND CRACKED ON THE OB SIDE OF THE BLADE APPROX 9.375 INCHES FROM THE TE OF THE FAIRING THE CRACK STARTS AT THE CUFF END OF THE BLADE AND EXTENDS TOWARD THE TIP END OF THE BLADE APPROX 1.0 INCH. THE STRAP IS CRACKED ON THE SDR MDR04042Blade · crackedDURING NORMAL AIRCRAFT INSPECTION, THE FOLLOWING WAS FOUND; THE OB SIDE OF THE POCKET IS CRACKED 1.8125 INCHES FROM THE TRAILING EDGE AND .25 INCH FROM THE TIP END. THE CRACK IS RUNNING SPAN WISE AND IS .6875 INCH LONG. PROBABLE CAUSE IS UNKNOWN.SDR MDR04041Blade · crackedDURING NORMAL AIRCRAFT INSPECTIN, THE FOLLOWING WAS FOUND. THE OB SIDE OF THE POCKET HAS THREE CRACKS RUNNING SPANWISE APPROXIMATEL .398 INCH FROM THE TRAILING EDGE. THE FIRST CRACK IS 75 INCH FROM THE TIP END AND .835 INCH LONG. THE SECOND CRACK IS 9 INCH SDR MDR04040Blade · crackedDURING NORMAL AIRCRAFT INSPECTION, THE FOLLOWING WAS FOUND: TWO SPANWISE CRACKS EXIST AT THE TRAILING EDGE ON THE OB SIDE. THE FIRST CRACK IS 7.25 INCH FROM OB END OF THE POCKET AND IS 1.25 INCH IN LENGTH. THE SECOND CRACK IS 14.5 INCHES FROM THE OB END OF SDR JYD2004F00002Rotor Head · crackedDURING NORMAL AC INSPECTION, THE FOLLOWING WAS FOUND; THE OB SIDE OF THE POCKET IS CRACKED 1.8125 INCH FROM THE TRAILING EDGE AND .25 INCH FROM THE TIP END. THE CRACK IS RUNNING SPAN WISE AND IS 6875 INCH LONG. PROBABLE CAUSE UNKNOWN. (MDR04-042)SDR JYD2004F00001Rotor Head · crackedDURING NORMAL AC INSPECTION, THE FOLLOWING WAS FOUND; THE OB SIDE OF THE POCKET HAS 3 CRACKS RUNNING SPANWISE APPROXIMATELY .398 INCH FROM THE TRAILING EDGE. THE FIRST CRACK IS 7.5 INCH FROM THE TIP END AND .835 INCH LONG. THE SECOND CRACK IS 9 INCHES FROM SDR JYD2004F00000Rotor Head · crackedDURING NORMAL AIRCRAFT INSPECTION, THE FOLLOWING WAS FOUND: TWO SPANWISE CRACKS EXIST AT THE T/E ON THE OB SIDE. THE FIRST CRACK IS 7.25 INCHES FROM OB END OF THE POCKET AND IS 1.25 INCHES IN LENGTH. THE SECOND CRACK IS 14.5 INCHES FROM THE OB END OF THE POCSDR MDR03038Spar · crackedTHE BLADE WAS INSPECTED DUE TO A BIM INDICATION IN THE FIELD. DURING THE INSPECTION, A LEAK INDICATION WAS NOTED ON THE BOTTOM SIDE OF THE SPAR BETWEEN POCKETS 5 AND 6. AFTER REMOVAL OF POCKETS 5 AND 6, AND FPI INSPECTION REVEALED A CRACK IN THE SPAR RUNNINGSDR MDR03037Housing · crackedTHE TGB CENTER HOUSING WAS FOUND CRACKED WHILE INSTALLED ON THE AIRCRAFT. IT WAS REMOVED PREMATURELY ON SEPTEMBER 3, 2000. THE SHOP DETECTED THE CRACK VISUALLY. THE CRACK BEGAN AT THE SECOND ROSAN STUD CLOCKWISE FROM THE ROSAN SEAT PAD LOCATED 34 DEGREES FRSDR MDR03035Housing · crackedTGB CENTER HOUSING WAS FOUND CRACKED WHILE INSTALLED ON THE AIRCRAFT. IT WAS REMOVED PREMATURELY ON OCTOBER 20, 2000. THE SHOP DETECTED THE CRACK VISUALLY. THE CRACK BEGAN AT THE SECOND ROSAN STUD CLOCKWISE FROM THE ROSAN SEAT PAD LOCATED 34 DEGREES FROM CSDR MDR03021Housing · crackedTHE TGB CENTER HOUSING WAS FOUND CRACKED WHILE INSTALLED ON AIRCRAFT. IT WAS REMOVED PREMATURELY, HAVING TSO 89.0 HOURS. THE SHOP DETECTED THE CRACK VISUALLY. THE CRACK BEGAN AT THE SECOND ROSAN STUD, CLOCKWISE FROM THE ROSAN SEAT PAD LOCATED 34 DEGREES FROSDR MDR03033Housing · crackedTAIL GB AND SERVO ASSY WAS REMOVED FROM AC FOR 2ND STAGE HYD FLUID LEADING INTO THE T/R GB. T/R SERVO ASSY WAS REMOVED FROM THE T/R GB ASSY. THE HYD SHOP, REVEALED HEAVY SCORING ON EXPOSED AREA OF PISTON. ONCE PRESSURIZED TO SIMULATE OPERATION CONDITION, ATSDR JYD2004F00004Compressor Wheel · cracked2ND STAGE COMPRESSOR DISK (PN 670802, SN H63817) WAS FOUND CRACKED DURING OVERHAUL INSPECTION. COMPRESSOR (SN 672571) WAS REMOVED FROM SERVICE DUE TO REACHING ITS O/H INTERVAL, HAVING A TSO OF 2987.9 HOURS AND A TT OF 5978.0 HOURS. DURING O/H INSPECTION, FIVSDR MDR03026Strap · crackedTHE STRAP IS CRACKED ON THE OUTBOARD SIDE OF THE BLADE, APPROXIMATELY 9.5 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 2 INCHES. THE CRACK STARTS WHERE TSDR MDR03025Compressor Wheel · crackedONE EACH CRACK INDICATION FOUND BY EDDY CURRENT INSPECTION. INDICATION IS IN THE LOCATION OF THE BLADE RETENTION PIN HOLE, ON THE CENTER FLANGE. INDICATION COULD NOT BE DETECTED BY FPI WHICH IS THE METHOD OF INSPECTION CALLED FOR IN THE OVERHAUL MANUAL. CAUSDR MDR03023Blade · crackedTHE BLADE WAS REMOVED FROM THE AIRCRAFT FOR BIM INDICATION. A 10-DAY LEAK CHECK WAS PERFORMED AND A CRACK WAS FOUND IN THE SPAR 117.75 INCHES FROM THE TIP END AND 4.50 INCHES FROM THE LEADING EDGE ON THE BOTTOM SIDE OF THE BLADE. CAUSE: UNKNOWNSDR MDR03022Blade · crackedTHE BLADE WAS REMOVED FROM THE AIRCRAFT FOR BIM INDICATION. A 10-DAY LEAK CHECK WAS PERFORMED AND A LEAK WAS FOUND IN A CRACK IN NR 18 POCKET. AFTER THE POCKET WAS REMOVED AND ADHESIVE WAS CHEMICALLY REMOVED, THE CRACK WAS FOUND 168.75 INCHES FROM THE ROOT E
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