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 = '550' 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 = '550' 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 2011F00105Line · splitLANDING GEAR RETRACT HYD LINE IN RT WING, INBD AFT BAY, RUPTURED. TUBING SPLIT IN STRAIGHT SECTION ALONG SEAM LINE. SLIT IS .5" IN LENGTH.SDR CA110527003Drive Shaft · shearedDURING TAKEOFF THE ENGINE FLAMED OUT AND THE PILOT RETURNED TO HOME BASE AND MADE A SAFE SINGLE ENGINE LANDING. TROUBLESHOOTING DISCOVERED A SHEARED FUEL CONTROL DRIVE SHAFT. MFG RECOMMENDS THE SDR BE CLOSED ON THE BASIS OF THE FOLLOWING INFORMATION.SDR SFOA20110427001Hydraulic Line · chafedON ROLLOUT AFTER LANDING THE CREW HAD NO BRAKING. EMERGENCY BRAKES AND THRUST REVERSER WERE OPERATIONAL. THE AIRCRAFT SAFELY SLOWED AND TAXIED TO THE RAMP UTILIZING THRUST REVERSERS TO CONTROL AIRCRAFT SPEED, THEN CHOCKS WERE APPLIED. THE CREW DISCOVERED A SDR CA110510004Buss Bar · burnedDURING RETURN FLIGHT, CREW EXPERIENCED A FAILED LT ENGINE ANTI-ICE INDICATION. UPON INVESTIGATION BY MX, ARCING AND EVIDENCE OF BURNING WAS FOUND IN AFT MOUNTED ELECTRICAL JUNCTION BOX. LT ANTI-ICE BUS BAR PN 6538342-7, FUSE LIMITER PN ANL175, FUSE LIMITER BASDR K45A042011Window · crackedDURING PHASE 49 INSPECTION, CRACKS AT HOLES NR 5 AND 6 WERE FOUND IN COPILOT'S OUTER SIDE WINDOW. THESE EXCEED ALLOWABLE LIMITS IAW THE MFG. WINDOW WILL BE REPLACED IAW MM.SDR 2011F00092Structure · crackedDURING PHASE 49 INSP EDDY CURRENT INP INDICATED A POSSIBLE CRACK. PAINT AND FILLER WERE REMOVED AND AREA INSPECTED BY VISUAL INSP USING MAGNIFICATION WHICH CONFIRMED 3 CRACKS IN BAND AT FS 287.78. IT APPEARS BAND WAS DAMAGED DURING LAST REPAINT OF ACFT, CAUSISDR CA110328002Bearing · failed(CAN) FLIGHT CREW HAD RT GENERATOR FAILURE IN CRUISE. RESET ONCE GENERATOR CAME BACK ON LINE. LATER GENERATOR FAILURE OCCURRED AGAIN FOLLOWED BY ENGINE ROLL BACK TO IDLE. CREW HAD NOTICED SLIGHT VIBRATION PRIOR TO INITIAL GENERATOR FAILURE. MAINTENANCE ARESDR 2011FA0000181Fcu · faultyDURING DECENT AT 12,000 FT, WHILE SOUTH OF WAYPOINT ON THE DUMPY ARRIVAL. THE RT ENGINE QUIT DUE TO A FAULTY FUEL CONTROL UNIT. THE CREW RAN THE CHECKLIST AND PROCEEDED VISUALLY FOR AN UNEVENTFUL FLAPS 15 LANDING.SDR VQMA20110314001Actuator · malfunctionedON CLIMB OUT, PILOT REPORTED ELEVATOR TRIM JAMMED AND WOULD NOT MOVE. PILOT RETURNED ACFT BACK TO DEPARTURE AND DIFFERENT ACFT DEPARTED. MX INSPECTED ACFT AND FOUND ELEVATOR TRIM ACTUATOR WORN AND CHAIN ON ACTUATOR VERY LOOSE AND BINDING WHENEVER TRIM UP WASSDR O2GA20110405Tube · crackedTUBES FOUND CRACKED.SDR CA110228005Fcu · failed(CAN) POWER ROLL BACK DURING FLIGHT BTWEEN FL380 & FL400, THE CREW REPORTED A POWER ROLL BACK. THE FLIGHT WAS DIVERTED, WHERE IT LANDED SAFELY. SUSPECTED FCU TO BE THE ROOT CAUSE.SDR CA110214001Engine · power lossPOWER ROLLBACK DURING REVENUE FLIGHT, CLIMBING FROM FL330 TO FL340, THE ENGINE ROLLED BACK UNCOMMANDED FROM 91 PERCENT TO 73 PERCENT N1. UPON DESCENT TO FL320, THE ENGINE RECOVERED WITH NORMAL THROTTLE RESPONSE AND THE ACFT CONTINUED TO ITS DESTINATION WITHOUSDR E81RJT229431Element · shortedINVESTIGATED REPORTED ENGINE ANTI-ICE SYS FAIL INDICATION. FOUND (1) HEATING ELEMENT OPEN IN RT INBD WING L/E ANTI-ICE PANEL. ALSO NOTED FAULT IN RT WING L/E ANTI-ICE JUNCTION BOX CURRENT SENSOR CS10. FURTHER TROUBLESHOOTING REVEALED THE WIRING TERMINALS, ATTSDR CA110203003Bearing · worn(CAN) WHEN MAINTENANCE REPORTED FOR WORK A POOL OF OIL WAS FOUND UNDER THE ENGINE. TROUBLESHOOTING RESULTED IN FINDING A STUCK CHECK VALVE AND METAL PARTICLES IN THE OIL FILTER. THE ENGINE WAS REMOVED AND RETURNED TO A REPAIR FACILITY WHO REPORTED THAT THE AGBSDR CA110117008Window · crackedTHIS WINDOW IS NOT LAMINATED BUT THE CRACK RUNS ABOUT 75 PERCENT OF THE WAY AROUND THE CIRCUMFERENCE, LIKE IT IS LAMINATED AND SEPARATING. THE CRACK VARIES IN WIDTH GOING SOMETIMES INBD OF THE MOUNTING HOLES BUT NEVER IS DEEP ENOUGH TO BE IN THE VISIBLE AREA WSDR CA110118004Actuator · malfunctionedDURING A BASE INSP, IT WAS DISCOVERED THAT THE RUDDER TRIM WHEEL WAS EXTREMELY DIFFICULT TO OPERATE. ON EXAMINATION, IT WAS FOUND THAT 1 OF THE ACTUATOR SCREWS SEEMS TO HAVE JUMPED A THREAD. THE TRIM ACTUATOR WAS REPLACED WITH A NEW PN 55654-102.SDR SFOA20110106001Door · out of adjustTHE AIRCRAFT TOOK OFF AND MADE A NORMAL CLIMB TO CRUISE ALTITUDE. AFTER A FEW MINUTES IT WAS NOTED THAT THE LANDING GEAR UNLOCK AND HYD PRESS ON ANNUNCIATORS ILLUMINATED, A THUMP/BUMP WAS HEARD AND FELT, AFTER WHICH THE ANNUNCIATORS EXTINGUISHED. THIS HAPPENSDR R6F2011F00000Actuator · failedAFTER DEPARTURE, CREW WAS UNABLE TO RETRACT THE LANDING GEAR. LT MLG INITIALLY RETRACTED THEN RETURNED TO A DOWN AND LOCK POSITION. RT AND NLG OPERATED NORMALLY. AFTER COMPLETING THE GEAR MALFUNCTION CHECKLIST, CREW RETURNED TO DEPARTURE FOR A NORMAL APPROASDR R6F2011F00001Uplock Switch · failedAFTER DEPARTURE, CREW WAS UNABLE TO RETRACT THE LANDING GEAR. LT MAIN GEAR INITIALLY RETRACTED THEN RETURNED TO A DOWN AND LOCKED POSITION. RT AND NLG OPERATED NORMALLY. AFTER COMPLETING THE GEAR MALFUNCTION CHECKLIST CREW RETURNED TO DEPARTURE FOR A NORMALSDR DYCR02050520Control Cable · frayedDURING A PHASE 1, THROUGH 5 INSP, FOUND BROKEN STRANDS IN A FLAP CABLE, PN 5565150-3 FOR THE RT FLAP. AFTER INSTALLING THE NEW FLAP CABLE IT WAS DISCOVERED THAT THE CHOICE OF LOCKING PINS FOR THE TURNBUCKLE WERE TOO SHORT OR TOO LONG. FURTHER INVESTIGATION DISDR CA101123005Actuator · overservicedDURING A FUNCTIONAL CHECK, MECHANIC NOTICED HE COULD NOT MOVE RUDDER TRIM TO FULL DEFLECTION. MOVEMENT RESTRICTED TO ABOUT A 1/2 DEGREES LT TO RT. FOLLOWING THE TROUBLE SHOOTING GUIDE IN THE MM AND OUR OWN INVESTIGATION OF THE RUDDER TRIM ACTUATOR SYSTEM, WSDR CA101109001Fcu · failed(CAN) FLAMEOUT DURING A FLIGHT TEST AT FL250, WHILE CHECKING AIRFRAME OUTFLOW AND SAFETY VALVE, THE ENGINE SPOOLED DOWN AND FLAMED OUT. AN UNEVENTFUL SINGLE ENGINE LANDING WAS MADE. POST FLIGHT TROUBLESHOOTING IDENTIFIED A FUEL CONTROL (FCU) ADJUSTMENT ISSUESDR CA101013004Bolt · wrong partDURING A SERVICEABILITY CHECK, A RUBBING NOISE WAS NOTICED WHEN THE RT AILERON WAS MOVED TO IT`S FULL EXTENSION. FURTHER INVESTIGATION REVEALED THAT THE UPPER RT BOLT HOLDING THE ACTUATOR PLATE (PN 5565386-3) TO THE AILERON QUADRANT WAS RUBBING ON THE UPPER AISDR VQMA2010100800004Frame · damagedDURING SCHEDULED MX, INSP NOTED DAMAGE TO A FRAME AT FUSELAGE STA 205.23 AND WATER LINE 112. MX PERFORMED A MAJOR REPAIR BY REMOVING DAMAGED AREA AND INSTALLING A NEW SPLICE IAW REPORT S-550-0047/07PRD.SDR VQMA2010100800003Frame · damagedDURING SCHEDULED MX, INSP NOTED DAMAGE TO A FRAME AT FUSELAGE STA 180.77 AND WATER LINE 112. MX PERFORMED A MAJOR REPAIR BY REMOVING DAMAGED AREA AND INSTALLING A NEW SPLICE IAW REPORT S-550-0047/07PRD.SDR VQMA2010100800002Frame · damagedDURING SCHEDULED MX, INSP NOTED DAMAGE TO A FRAME AT FUSELAGE STA 168 AND WATER LINE 121. MX PERFORMED A MAJOR REPAIR BY FABRICATING AND INSTALLING A DOUBLER IAW REPORT NR S-550-0047/07PRD AND SRM CHAP 51.SDR VQMA2010100800001Frame · damagedDURING SCHEDULED MX, INSP NOTED DAMAGE TO A FRAME AT FUSELAGE STA 179.5 AND WATER LINE 107. MX PERFORMED A MAJOR REPAIR BY FABRICATING AND INSTALLING A DOUBLER IAW REPORT NR S-550-0047/07PRD AND SRM, CHAPTER 51.SDR 2010FA0001066Seat Frame · 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 STO1042WI AND DWG D-10395.SDR G13A292JDisplay · failedSHORTLY AFTER TAKEOFF, THE CO-PILOT PFD FAILED. CREW WENT TO REVERSIONARY MODE AND CONTINUED IAW CHECKLIST. UPON APPROACH WHILE ON FINAL THE PILOT SIDE PFD DISPLAY ALSO FAILED. THE CREW THEN SWITCHED PILOT INFORMATION TO THE MFD AND LANDED THE ACFT IN VFR CSDR SFOA67Wire · chafedDURING POST ENGINE START/PREFLIGHT CHECKS, NOTED THE "SPEED BRAKE EXTENDED" ANNUNCIATOR FAILED TO ILLUMINATE. VISUAL INSPECTION CONFIRMED THE BRAKES EXTENDED, & "HYD PRESS" LIGHT EXTINGUISHED CONFIRMING SYS HAD COMPLETED IT’S CYCLE. ANNUNCIATOR LIGHT TEST PERSDR 2010FA0000897Seat · brokenUPPER SEAT BASE ASSY CRACKED AT CHAIR BACK ATTACH POINTS. STRESS ON CHAIR BACK AND METAL FATIGUE PROBABLE CAUSE. CHAIR WAS REPAIRED IAW REPAIR STA PROCEDURES STC STO1042WI.SDR CA100831005Engine · flamed outIFSD DURING NON-REVENUE DELIVERY FLIGHT FUEL FLOW WAS FLUCTUATING ON ONE ENGINE, OTHER ENGINE PARAMETERS WERE STABLE. PILOT MOVED THROTTLES AND, THE ENGINE FLAMED OUT. IT WAS RESTARTED. FUEL FLOW WAS STILL FLUCTUATING, HOWEVER THE FLIGHT WAS COMPLETED UNEVESDR 2010FA0000782Seat · broken(GVRR) UPPER SEAT BASE ASSY CRACKED AT CHAIR BACK ATTACH POINTS. STRESS ON CHAIR BACK AND METAL FATIGUE PROBABLE CAUSE. ALSO, PREVIOUS INAPPROPRIATE REPAIR. CHAIR WAS REPAIRED IAW STC ST01042WI.SDR CA100716001Bearing · failedENGINEERING TECHNICAL REPORT ETR JT15D-015 NR 3 LP TURBINE BEARING HEAVILY WORN AND CAGE WAS BROKEN IN TWO PLACES (EXCESSIVE RADIAL MOVEMENT IN THE LP TURBINE PACK). ROLLERS FELL OUT OF THE BEARING CAGE WHEN THE BEARING WAS REMOVED.SDR CA100614002Squat Switch · inoperativeFLIGHT CREW HAD UNCOMMANDED DEPRESSURIZATION FOLLOWING REDUCTION OF POWER AT CRUISE. PROBLEM FOUND TO BE LT SQUAT SWITCH POSITON NR 5 DID NOT CHANGE TO FLIGHT MODE. SWITCH REPLACED.SDR GNL2010F00001Regulator · stickingACFT DOOR SEAL OST PRESSURE AT ALTITUDE, THE PILOTS NOTICED A DOOR SEAL WARNING ANNUNCIATOR AND STARTED A DESCENT FROM 41,000 FT. THE CABIN EVENTUALLY STARTED TO EQUALIZE PRESSURE AND THE OXYGEN MASKS DEPLOYED. NO PERSONS HARMED. FURTHER INVESTIGATION FOUNDSDR CA100525016Actuator · failed(CAN) NOSE LANDING GEAR FAILED TO RETRACT.SDR CA100809021Fuel Nozzle · unserviceableON 05 MAY 2010, THIS ACFT WAS IN THE SERVICE CTR. A 450 HR, 5 POINT CALIBRATION RUN, WAS CONDUCTED ON THIS ENGINE. THE ENGINE FAILED THE CALIBRATION RUNS DUE TO AN OVERTEMP CONDITION. THE ACFT WAS FERRIED TO THE MAIN ACFT MFG SERVICE CTR FOR A FULL BORESCOPE ISDR 2010FA0000404Seat Frame · broken(GVRR) UPPER SEAT BASE ASSY CRACKED AT CHAIR BACK ATTACH POINTS. STRESS ON CHAIR BACK AND METAL FATIGUE PROBABLE CAUSE. CHAIR WAS REPAIRED IAW STC 01042WI.SDR 2010FA0000287Seat Frame · broken(GVRR) UPPER SEAT BASE ASSY CRACKED AT CHAIR BACK ATTACH POINTS. STRESS ON CHAIR BACK AND METAL FATIGUE PROBABLE CAUSE. ALSO PREVIOUS INAPPROPRIATE REPAIR. CHAIR WAS REPAIRED IAW STC 01042WI.SDR CA100211006Link · corroded(CAN) DURING SCHEDUALED RT & LT MLG PHASE 22 TRAILING LINK FWD BORE INSP, IT WAS NOTED THAT THERE WAS CORROSION FOUND INSIDE THE FWD BORE. TRAILING LINKS WERE REMOVED FROM ACFT AND SENT TO MFG FOR FURTHER INSP AND REPAIR. UPON FURTHER INVESTIGATION FROM MFG ITSDR ZZTA01232010Fuel Control · malfunctionedAIRCRAFT DEPARTED KNOXVILLE, TN EN ROUTE TO HAMMOND, LA ON A PART 91 FLIGHT. NEARING FL 330 WHILE CLIMBING TO FL 360, THE CREW REDUCED THE POWER ON BOTH ENGINES TO REMAIN WITHIN OPERATING LIMITS. THE RIGHT ENGINE WOULD NOT RESPOND TO THROTTLE MOVEMENTS AND WSDR 2010FA0000194Wire · chafedPILOT REPORTS AUTOPILOT CB TRIPPED. TROUBLESHOT PROBLEM AND FOUND WIRING INSIDE COPILOTS YOKE TO BE CHAFED AND SHORTING TO GROUND WHERE THE WIRING GOES FROM THE BACK OF THE YOKE INTO THE YOKE CONTROL WHEEL.SDR 2009FA0001082Reservoir · out of toleranceRECEIVED AN INSPECTED PNEUMATIC RESERVOIR (EMERGENCY BRAKE/GEAR BLOWDOWN BOTTLE) WITH 8130-3 NR AE-67615 DATED 10/29/2009. UPON INSTALLATION AND OPS CHECKS, THE INSPECTOR DETERMINED THAT THE BOTTLE MFG DATE OF JUNE 1980 MEANT THAT THE BOTTLE LIFE LIMIT OF 24 YSDR CA091231001Torque Tube · cracked(CAN) SMALL CRACKS STARTING FROM WELDS WHERE TUBE ENDS ARE WELDED TO MOUNTING PLATE ENDS. CAMPAIGN NOTICE 851-32-30-051 CESSNA 550 (TC NR 20091231001)SDR CA091211002Bracket · cracked(CAN) DURING AN INSP OF THE NOSE WHEEL WELL, A CRACK WAS VISUALLY OBSERVED ON ONE OF THE WELDS SECURING THE 2 NUT PLATE BRACKETS TO THE TORQUE TUBE ASSY. TORQUE TUBE WAS REMOVED AND FPI WAS CARRIED OUT TO VERIFY THE CRACK.SDR CA091211001Bracket · cracked(CAN) DURING A ROUTINE INSP OF NOSE WHEEL, A SUSPECTED CRACK WAS VISUALLY OBSERVED ON 1 OF THE 4 WELDS SECURING 2ND NUT PLATE BRACKETS TO THE TORQUE TUBE ASSY. TORQUE TUBE WAS REMOVED AND NDT VERIFIED THE CRACK AND FOUND 2 MORE CRACKS.SDR Z3O2009F00000Scavenge Pump · inoperativeWHILE TAXIING FOR TAKEOFF, THE LT ENGINE LOST OIL PRESSURE AND SMOKE WAS COMING OUT EXHAUST, SHUT ENGINE DOWN BEFORE THE PSI DROPPED BELOW 40 PSI. INSPECTED ENGINE AND FOUND OIL PUMP/SCAVANGE PUMP (PN 310426801, SN OP0764) INOPERATIVE, INSTALLED O/H PUMP (PN SDR CA091015002Link · cracked(CAN) THE LINK IS FOR THE SEAT TILT ADJUSTMENT AND WHERE THE ROUND TUBE IS SQUEEZED TO FORM A FLATTENED END, IT IS CRACKED.SDR CA091015001Spacer · debonded(CAN) THE DEFOG OUTLET IS HELD OPEN BY 3 SPACERS BONDED BETWEEN FWD AND AFT SKIN OF THE OUTLET DUCT. THE LT SPACER DEBONDED FROM FWD SKIN AND THE DUCT FRETTED ON INSIDE LWR PORTION OF WINDSHIELD - NOT SURE WHETHER ONE HAD AN EFFECT ON THE OTHER. THE NEW DUCT C
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