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 = '501' 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 = '501' 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 5JHA20250930231Compressor · stalledWHILE IN CRUISE FLIGHT AT FL370 (37,000 FT) THE LEFT ENGINE SUFFERED A SUSPECTED COMPRESSOR STALL WHICH SUBSEQUENTLY LEAD TO THE COMPLETE FAILURE/FLAMEOUT OF THE LEFT ENGINE. ALL REQUIRED QRH PROCEDURES WERE ACCOMPLISH ALONG WITH AN ATTEMPTED RELIGHT/RESTART SDR 2025FA0000544Skin · crackedCRACK IN THE SKIN ON LEFT SIDE OF RUDDER EXTENDING APPROXIMATELY 2.5" FROM THE RIVET LINE JUST BELOW THE TRIM TAB. CRACK EXTENDS DOWNWARD AND AFT.SDR 2023FA0000026Gyro · erraticSHORTLY AFTER TAKE OFF FROM PWA .DURING CLIMB OUT THE CREW NOTICED THAT THE PILOTS HSI WOULD NOT ERECT AND DEICIDED TO TO RETURN TO PWA TO HAVE MAINTENANCE . AFTER MAINTENANCE ARRIVED IT WAS DETERMINED THAT THE HSI HAD FAUILEDSDR SI6R20160705002Door · failedREMOVED CONDITIONED AIR DUCT FROM AFT PRESSURE BULKHEAD TO EXPOSE PLASTIC DOORS THAT ARE HINGED TO CHECK VALVE. PRESSURIZED AIRCRAFT IN HANGAR IN ACCORDANCE WITH MAINTENANCE MANUAL TO 8.0 PSI. PUSHED ON CHECK VALVE HINGED DOORS WITH HANDLE OF PLIERS, WHEN RESDR SI6R20160705001Check Valve · failedAIRCRAFT AT CRUISE AT 43,000'. CONDITIONED AIR DUCT CAME LOOSE FROM WATER SEPARATOR, CABIN BEGAN DEPRESSURIZING. CHECK VALVE LOCATED ON AFT PRESSURE BULKHEAD FAILED WHEN IT CLOSED BREAKING APART INTO CONDITIONED AIR DUCT LINE. AIRCRAFT BUILT IN 1980. HINGESDR 2014FA0000112Seat Frame · brokenSTRESS ON CHAIR BACK AND METAL FATIGUE PROBABLE CAUSE. CHAIR WAS REPAIRED IAW PROCEDURE STC STO1043WI AND DWG D-10392.SDR VIBR20131202006Acm · inoperativeAIR CYCLE MACHINE INOPERATIVE. REPLACED AIR CYCLE MACHINE.SDR CA130212006Pump · leaking(CAN) A FUEL LEAK AT THE ECOLOGY TANK WAS NOTICED. A LEAK WAS ALSO OBSERVED COMING FROM THE INTERFACE BETWEEN THE FUEL PUMP AND FUEL CONTROL UNIT. THE LEAK RATE WAS INCREASED BY INCREASING THE POWER DURING GROUND RUN TESTS. THE CUSTOMER WILL REPLACE THE FUESDR VIBR20130528003Rib · crackedCRACKED RIBS ON LT HORIZONTAL STABILIZER L/E.SDR 2012FA0000819Display · failedPILOT REPORTED, DURING FLIGHT, THE MULTIFUNCTION DISPLAY FAILED CAUSING SMOKE IN CABIN. ACFT LANDED, MULTIFUNCTION DISPLAY UNIT WAS REMOVED, WIRES SECURED AND ACFT RESUMED FLIGHT.SDR COZR20121130002Guard · out of positionDURING AN UNDERFLOOR INSPECTION, FOUND THE CABLES FOR THE AILERON AUTOPILOT SERVO RUBBING ON THE CABLE DRUM GUARDS. FURTHER INVESTIGATION FOUND THE CABLE GUARDS CAN BE LOCATED IN DIFFERENT POSITIONS ON THE SERVO. THIS IS TO ALLOW FOR DIFFERENT CABLE ANGLES DSDR 2012FA0000626Frame · brokenFOUND SEAT BASE BROKEN.SDR L7OA2012F00165Indicator · inoperativeLEFT ENGINE INSTRUMENT DISPLAY INOPERATIVE.SDR CA120320005Duct · ruptured(CAN) DURING PHASE 4 INSPECTION, LT ENGINE COWL ANTI-ICING DUCTING WAS FOUND TO BE RUPTURED IN INTAKE COWL. PILOTS DID NOT REPORT ANY ABNORMAL OCCURANCES.SDR CA120109001Fuel Filter · contaminated(CAN) AN INTERMITTENT FUEL BYPASS INDICATION IN CRUISE ON THE ENGINE. UPON REFERENCING THE FLIGHT MANUAL, IT STATED TO EXPECT PARTIAL OR FULL POWER LOSS SO PRECAUTIONARY MEASURES WERE TAKEN. THE ENGINE SHOWED NO SIGNS OF PARAMETER SHIFTING AND ALL TEMPERATURESSDR E81RJT2307930Skin · damagedDURING SCHEDULED PHASE INSP OF ACFT PREVIOUSLY MODIFIED, STC ST09559AC, ENGINE INSTALLATION NOTED (2) MISSING RIVET HEADS IN LT ENGINE INLET DUCT SKIN. SUBSEQUENT INVESTIGATION REVEALED MINOR CRACK FROM RIVET HOLE. NO FOD DAMAGE NOTED TO ENGINE. INLET DUCT SKSDR K452011F00001Angle · crackedDURING ROUTINE MX, THE LT LOWER SPEED BRAKE LOWER STIFFENER WAS FOUND CRACKED AT MID SPAN. THE COMPONENT WAS REPLACED IAW THE SRM. CAUSE UNKNOWN.SDR K452011F00000Angle · crackedDURING ROUTINE MX, THE RT LOWER SPEED BRAKE LOWER STIFFENER WAS FOUND CRACKED AT MID SPAN. THE COMPONENT WAS REPLACED IAW THE SRM. CAUSE UNKNOWN.SDR 2010FA0001175Blower Motor · burned outUPON TURNING THE COCKPIT DEFOG FAN TO LOW, SMOKE WAS OBSERVED COMING FROM THE DEFOG VENTS. SWITCH WAS RETURNED TO THE OFF POSITION AND THE CIRCUIT BREAKER FOR THE CABIN AIR SYS WAS PULLED. AN UNEVENTFUL LANDING WAS MADE. DURING REPAIR IT WAS NOTED THAT THE FSDR 2010FA0000734Line · leaking(EBVR) TROUBLESHOOT AND REPAIR FUEL LEAKING FROM BOTTOM OF NR 1 ENGINE BY THE FUEL CONTROL UNIT/ FUEL PUMP. TROUBLESHOT FUEL LEAK TO A CRACKED FUEL LINE. REMOVED EXISTING LINE AND INSTALLED O/H LINE. TORQUED AND SAFETIED.SDR 2009F00053Brake Assy · destroyedNORMAL BRAKE PRESSURE APPLIED TO BRAKE AFTER LANDING, ACFT VEERED TO THE RT DUE TO RT BRAKE LOCKING UP. ACFT WOULD NOT MOVE/TAXI UNDER ITS OWN POWER, TUG REQUIRED. ACFT LANDING WEIGHT WAS APPROX 9600 LBS. ACFT WAS AT SLOW TAXI SPEED 3-5 MPH WHEN EVENT OCCURSDR 2009FA0000501Adc · failedAT APPROX 7:30 PM WE BEGAN A DESCENT OUT OF FL420 FOR OUR ARRIVAL. OUTSIDE AIR TEMP WAS AS LOW AS -46 C AT ALTITUDE FOR 2 HOURS. AT FL340 WE GOT THE YELOW AMBER ENUCIATOR LIGHT JUST ABOVE THE PFD ILLUMINATING "AIU FAIL". OUTSIDE AIR TEMP WAS -31 C. IMMEDIASDR 2009FA0000338Seat Back · brokenUPPER SEAT BASE ASSY CRACKED AT CHAIR BACK ATTACH POINTS. STRESS ON CHAIR BACK AND METAL FATIGUE PROBABLE CAUSE. CHAIR WAS REPAIRED IAW PROCEDURE STC ST01043WI. (K)SDR 2008FA0000180Stud · brokenLT MLG ACTUATOR TO GEAR STUD BROKEN OFF AT BASE OF THE NUT ON THE TAPER SIDE, NUT AND WASHER SET MISSING AND STUD WAS NOT TIGHT IN THE GEAR.SDR 2006FA0000721Seat · crackedUPPER CHAIR BASE ASSEMBLY CRACKED AT CHAIR BACK ATTACH POINTS. ALSO, PREVIOUS INAPPROPRIATE REPAIR. CHAIR WAS REPAIRED IAW STC, STRUCTURAL SEAT REPAIR. (K)SDR 2006FA0000073Seat · crackedUPPER CHAIR BASE ASSEMBLY CRACKED AT CHAIR BACK ATTACH POINTS. STRESS ON CHAIR BACK AND METAL FATIGUE PROBABLE CAUSE. CHAIR WAS REPAIRED IAW STC. STRUCTURAL SEAT REPAIR. (K)SDR KBM2005F00083Indicator · failedDUAL TACH, NEEDLE WILL NOT PROVIDE READING. REMOVED AND REPLACED. (K)SDR 111004Line · brokenTHE AIRCRAFT DEPARTED MRY AND WHEN THE GEAR WAS SELECTED "RETRACT", THE HYDRAULIC LOW PRESS AND QUANTITY ANNUNCIATOR LIGHTS ILLUMINATED. THE FLIGHT CREW RETURNED TO MRY AND SELECTED THE GEAR "DOWN" AND HAD TO "BLOW" THE GEAR DOWN AND LANDED UNEVENTFULLY. IT SDR 2005FA0001268Structure · crackedUPPER CHAIR BASE ASSEMBLY CRACKED AT CHAIR BACK ATTACH POINTS. STRESS ON CHAIR BACK AND METAL FATIGUE PROBABLE CAUSE. CHAIR WAS REPAIRED IAW STRUCTURAL SEAT REPAIR. (K)SDR R2J2004F00001Control Cable · misinstalledDURING PHASE 5 INSPECTION, UPON REINSTALLING LT WING FLAP CABLES, NOTICED AIRCRAFT WAS DIFFERENT THAN MM DATA AS TO ROUTING OF FLAP CABLES ON LT OB BELLCRANK. EXPERIMENTED AND CONTACTED MFG TECH SUPPORT. FOUND DATA ON PG 27-50-01 PG 203 FIG 201 (SHEET 2) SHOSDR R2J2004F00000Brace · mismanufacturedWHILE REINSTALLING LT WING FLAP CABLES DURING PHASE 5 INSPECTION, NOTICED CABLE RUN TOO CLOSE TO STRUCTURE. INVESTIGATION AND NOTIFIED MFG TECH SUPPORT. IT WAS DETERMINED LT BRACE 5511037-3 AND RIB 5525130, CABLE PASS THRU WERE INCORRECTLY LOCATED DURING MANSDR CA040504002Reservoir · leaking(CAN) HYDRAULIC BRAKE RESERVOIR LEAKING. CRACK WELDED AND RETURNED TO SERVICE.SDR GVR2004F00000Seat Back · crackedUPPER CHAIR BASE ASSEMBLY CRACKED AT CHAIR BACK ATTACH POINTS. STRESS ON CHAIR BACK AND METAL FATIGUE PROBABLE CAUSE. ALSO, CHAIR BASE HAS HAD PREVIOUS INAPPROPRIATE REPAIR MADE. CHAIR WAS REPAIRED.SDR KBM2003F00080Window · crackedLT FORWARD WINDOW CRACKED AND CRAZED. REMOVED AND REPLACED.SDR 2003FA0000898Line · corrodedDURING GEAR RETRACTION AND GEAR EXTENSION, HYDRAULIC FLUID LEAKED UNDER PRESSURE. FOUND THIS LINE CORRODED SO BADLY THAT A HOLE HAD BEEN FORMED IN THE LINE. THE CORROSION WAS DUE TO PREVIOUS ROUTING OF AIR CONDITIONING DUCT TY-WRAPPED TO THE FOUR LANDING GEASDR 2003FA0000286Bellcrank · crackedRIGHT FLAP BELLCRANK FOLLOW-UP ROD ARM ATTACH POINT WAS CRACKED ON UPPER AND LOWER ARM. UPON INSPECTION OF OTHER BELLCRANKS; FOUND THAT SPACERS WERE MISSING BETWEEN FOLLOW-UP ROD-END AND BELLCRANK FOLLOW-UP ARM.SDR 1206SSkin Panel · crackedDURING A PHASE 1-5 DISCOVERED CRACKS IN LT AND RT WING SKIN AT AFT OUTBOARD EDGE OF WHEEL WELL CUT OUT. LT WING CRACK WAS .50 IN. LONG RT WING CRACK WAS 0.40 IN. LONG. REPAIRED IN ACCORDANCE WITH CESSNA REPAIR DEFINITION S-550-0264/02RD DATED NOVEMBER 14, 2000SDR CA020215010Duct · cracked(CAN) DURING DAILY INSPECTION, RT ENGINE FRONT & REAR INNER BYPASS DUCT FOUND CRACKED AND PIECE OF REAR UNDER BYPASS DUCT MISSING. AFTER REMOVAL OF THOSE ITEMS FROM THE ENGINE, THE INSPECTION REVEALED THAT THEY WERE PARTS WHICH WAS PREVIOUSLY WELDED/OVERHAUL ASDR 2002FA0000094Check Valve · failedCHECK VALVE FAILED AND ALLOWED THE RT ENGINE BLEED AIR TO FLOW UNABATED FROM RT ENGINE ACROSS AND INTO THE LT ENGINE VIA THE AIRCRAFT BLEED AIR LINES DURING IN FLIGHT RESTARTS OF THE LT ENGINE. HOT BLEED AIR GASES DISTURBED THE NORMAL AIRFLOW INTO THE LT ENGINSDR 2002FA0000056Pin · shearedTHE SHEAR PIN CONNECTING THE FLAP DRIVE MOTOR TO THE FLAP GEARBOX SHEARED OFF AS THE CREW ATTEMPTED TO POSITION FLAPS TO 2ND POSITION. AFTER INVESTIGATION, THE FLAP GEAR BOX WAS DETERMNED TO BE DEFECTIVE.SDR 20001030SH032Control Box · chafedELEVATOR TRIM CHAIN IN PEDESTAL CHAFED ON SPERRY RI-106 REMOTE CONTROL BOX. CASE OF CONTROL BOX WAS SEVERLY WORN. IT WAS EVIDENT THIS CONDITION EXISTED FOR SOME TIME. THIS COULD HAVE POSSIBLY LED TO JAMMING OF THE ELEVATOR TRIM SYSTEM. UNIT WAS REMOVED AND SDR 99ZZZX2050Torque Tube · looseDURING PHASE 2 INSPECTION, FOUND NOSE GEAR DOORS HANGING DOWN. OPEN GEAR DOORS FOUND TORQUE TUBE FOR DOORS, THE ATTACH NUTPLATE HOLDER IS CRACKED ON WELD. PART WAS REPLACED. THE PART WAS INSTALLED NEW WHEN THE AIRCRAFT WAS DELIVERED NEW.SDR 98ZZZX4549Adc · malfunctionedUPON INITIAL 'POWER-UP' OF AIR DATA COMPUTER, ALTIMETER FALLS OFF LINE (FLAGS), AND REMAINS OFF LINE UNTIL AIR DATA COMPUTER IS IN THE OFF POSITION.SDR 98ZZZX4548Adc · malfunctionedUPON INITIAL 'POWER-UP' OF AIR DATA COMPUTER, ALTIMETER CLIMBS TO 4,000 FEET, AND DROPS VERY SLOWLY. UPON FLIGHT DESCENT, ALTITUDE 'CAPTURE' IS SLOW, AND CAN INDICATE 200 TO 400 FEET IN ERROR.SDR 98ZZZX4229Bulb · failedWHEN SELECTED DOWN, THE GEAR EXTENDED, BUT NO LEFT MAIN GEAR DOWN LIGHT ILLUMINATED. THE GEAR WAS BLOWN DOWN. THE AIRCRAFT LANDED WITHOUT INCIDENT. INVESTIGATION REVEALED GEAR DOWN LIGHT WAS BURNED OUT. BULB WAS REPLACED AND GEAR WAS FOUND TO FUNCTION NORMSDR 98ZZZX454Control Cable · frayedWHILE PERFORMING PHASE INSPECTION 1 THROUGH 5, FOUND THE ELEVATOR CABLE FRAYED GOING THROUGH THE CONTROL LOCK CONDUIT. THE MM ALLOWS 3 STRANDS BROKEN IN ANY 10 INCH SECTION. THIS CABLE HAD 6 STRANDS BROKEN. SUSPECT CAUSE FOR THIS IS THE FRONT OF THE CONDUIT SDR 97ZZZX4536Control Cable · brokenRUDDER SERVO CABLE BROKEN. DISCOVERED CONDITION WHEN C/W SCHEDULED PHASE 5 CESSNA CITATION INSPECTION. NEW CABLE INSTALLED 8-16-94 AT 3,362 HOURS. FOUND BROKEN AT 3,640.2 HOURS. SUBMITTER STATED SAFETY OF FLIGHT ITEM!!SDR 97ZZZX4535Control Cable · brokenRUDDER SERVO CABLE BROKEN. DISCOVERED CONDITION WHEN C/W SCHEDULED PHASE 5 CESSNA CITATION INSPECTION. NEW CABLE INSTALLED 8-16-94 AT 3,362 HOURS. FOUND BROKEN AT 3,640.2 HOURS. SUBMITTER STATED SAFETY OF FLIGHT ITEM!!SDR 97ZZZX2028Hose · failedDURING CRUISE AT FL 370, PRESSURIZATION SET FOR FL 380 WITH CABIN AT APPROX 7,000 FEET. CREW HEARD A DULL NOISE, CABIN OXY MASK DEPLOYED, MASTER WARN RED LIGHTS AND CABIN ALTITUDE INCREASING. ACFT DIVERTED FOR REPAIR. FOUND FAILED BLEED SYS HOSE AND A NON-SDR 97ZZZX1646Gas Generator · corrosion holeWHILE TROUBLESHOOTING AN EXISTING PROBLEM WITH ONE ENGINE, THE DIFFUSER TUBES WERE FOUND TO HAVE HEAVY CORROSION WITH SEVERAL HOLES CORRODED THROUGH. SUBSEQUENT INSPECTION OF THE OTHER ENGINE RESULTED IN FINDING THE SAME PROBLEM. BOTH ENGINES WERE REMOVED AN
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