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 16082Outflow Valve · failedTHE AIRCRAFT, AFTER DEPARTURE FROM SUS, WAS UNABLE TO PRESSURIZE THE CABIN. THE AIRCRAFT RETURNED TO SUS. OBTAINED A FERRY PERMIT TO RETURN TO AFJ. THE PROBLEM COULD NOT BE DUPLICATED. THE OUTFLOW VALVE AND SQUAT SWITCH WAS CHECKED.SDR 2003FA0001020Control Cable · misinstalledTHE PILOTS CONTROL WHEEL EMITS A GRINDING NOISE WHEN OPERATING THE AILERONS. FOUND THE AFT AILERON CONTROL CABLE WAS FOUND TO BE INCORRECTLY ROUTED INSIDE THE PILOTS CONTROL COLUMN. THE CABLE TENSION WAS LOW AND THE TURNBUCKLE WAS ADJUSTED TO THE END OF ITS TSDR 97CW1Wire Harness · chafedTHE FUEL PUMP WIRING HARNESS IS NOT SUPPORTED WITHIN THE FUEL CELL AND CHAFED ON THE ALUMINUM FUEL LINE FROM THE PRIMARY PUMP TO THE CHECK VALVE INSIDE THE FUEL CELL. THERE WAS .006 INCHES DAMAGE TO THE WALL OF THE FUEL LINE AND THE SHIELDING ON THE PUMP WIRISDR B30R20033017Wire Harness · chafedIN TROUBLESHOOTING A SUBMERGED FUEL BOOST PUMP CIRCUIT BREAKER POPPING, MAINTENANCE TECHNICIANS DISCOVERED THE FUEL BOOST PUMP ELECTRICAL HARNESS HAD CHAFFED THROUGH THE BUNDLE INSULATION AND WAS ARCING ON ALUMINUM FUEL LINE P/N 6526355-37 INSIDE THE WET WING.SDR B30R20033018Wire · arcedIN TROUBLESHOOTING A SUBMERGED FUEL BOOST PUMP CIRCUIT BREAKER POPPING, MAINTENANCE TECHNICIANS DISCOVERED THE FUEL BOOST PUMP ELECTRICAL HARNESSES HAD CHAFED THROUGH THE BUNDLE INSULATION AND WAS ARCING ON ALUMINUM FUEL LINES P/N 6526355-37 INSIDE BOTH THE LESDR 030926DWire Harness · chafedDURING INTERNAL INSPECTION OF THE FUEL BAYS FOUND FUEL PUMP WIRING HARNESSES IN RIGHT WING WAS DAMAGED BY CHAFFING THROUGH THE WIRING INSULATION. WIRING WAS CHAFFING AGAINST ALUMINUM FUEL LINE INSIDE TANK. CHAFFING CAUSED WEAR BEYOND LIMITS TO ALUMINUM FUEL SDR 030926CWire Harness · chafedDURING INTERNAL INSPECTION OF THE FUEL BAYS FOUND FUEL PUMP WIRING HARNESSES IN RIGHT WING WAS DAMAGED BY CHAFFING THROUGH THE WIRING INSULATION TO BEAR WIRE. WIRING WAS CHAFFING AGAINST ALUMINUM FUEL LINE INSIDE TANK. CHAFFING CAUSED WEAR BEYOND LIMITS TO ASDR 030926BWire Harness · chafedDURING INTERNAL INSPECTION OF THE FUEL BAYS FOUND FUEL PUMP WIRING HARNESSES IN RIGHT WING WAS DAMAGED BY CHAFFING THROUGH THE WIRING INSULATION. WIRING WAS CHAFFING AGAINST ALUMINUM FUEL LINE INSIDE TANK. CHAFFING CAUSED WEAR BEYOND LIMITS TO ALUMINUM FUEL SDR 030926AWire Harness · chafedDURING INTERNAL INSPECTION OF THE FUEL BAYS FOUND FUEL PUMP WIRING HARNESSES IN BOTH WINGS WERE DAMAGED BY CHAFFING THROUGH THE WIRING INSULATION. WIRING WAS CHAFFING AGAINST ALUMINUM FUEL LINES AND PUMP BODY INSIDE TANK. CHAFFING CAUSED WEAR BEYOND LIMITS TSDR VERTEX3Pump · scoredAFTER FINDING CHAFED FUEL BOOST PUMP WIRING ARCING AGAINST MOTIVE FLOW FUEL SUPPLY LINE ON RT SIDE LT FUEL BOOST PUMP WAS ALSO INSPECTED. WIRING ON LT (NO ARCING AT THIS TIME) HAD RUBBED INTO MOTIVE FLOW FUEL SUPPLY LINE TO A POINT THAT SUPPLY LINE P/N 6526355SDR VERTEX2Wire · sparksRIGHT BOOST PUMP WIRING CHAFED ON MOTIVE FLOW FEED LINE IN FUEL BAY. CHAFED WIRE CAUSED ELECTRICAL ARC DAMAGE TO FUEL LINE. THIS APPEARS TO BE AN ORIGINAL BOOST PUMP. PROBLEM WAS NOTED DURING DEFUELING USING THE BOOST PUMP TO REMOVE FUEL FOR MAINTENANCE. THE 1SDR CA030910001Fire Loop · chafed(CAN) THE FIRE DETECTION SENSOR LOOP ON THE LT ENGINE WAS FOUND CHAFING ON THE REAR TOP BRACKET (SUPPORT AFT OF ENGINE COVER) DURING PHASE 1,2,3, & 4 INSPECTION. THE LOOP RESISTANCE MEASURED BEYOND LIMITS AND WAS REPLACED. WEAR DAMAGE ON THE BRACKET WAS REPAIRSDR CA030828005Blade · fractured(CAN) PILOTS NOTICED SLIGHTLY HIGHER ITT TEMP ON RT ENG A SLIGHT RISE IN N2 SPEEDS. TEMP AND N2 INDICATIONS, AS WELL AS ALL OTHER INDICATIONS WHERE NOTED TO BE WELL WITHIN NORMAL OPERATING PARAMETERS.ON FINAL INTO CALGARY AIRPORT WHILE POWERING BACK A SLIGHT VSDR CA030825007Wire · chafed(CAN) DURING REASSEMBLY CONTROL WHEEL, A TECHNICIAN DISCOVERED TWO BARE WIRES HIDDEN INSIDE THE CONTROL WHEEL ASSY. THE BARE WIRES COULD BE PARTIALLY SEEN FROM A SMALL OPENING IN THE FRONT SIDE OF THE CONTROL WHEEL PAD. AFTER DISMOUNTING THE CONTROL WHEEL ASSESDR CA030818003Bleed Valve · malfunctioned(CAN) RT ENGINE SURGES UPON DECELERATING THRU 70 PERCENT, SECONDARY ORIFICE ON BLEED OFF VALVE TORQUE MOTOR INSPECTED AND CLEANED. P3 AIR SEPERATOR INSPECTED AND CLEANED ASPER PRATT AND WHITNEY. BLEED OFF VALVES SWAPPED (RT TO LT). ENGINE GROUND RAN , NO FAULTSDR CA030909003Stator · failed(CAN) STATOR BROKEN ON RT BRAKE ASSY. IN REFERENCE TO A PREVIOUS SDR CA20030812005 SUBMITTED FOR ALT BRAKE FAILURE ON SAME A/C, THE RT BRAKE WAS REMOVED FOR CLOSER INSPECTION DURING AN UNRELATED PHASE INSPECTION.THE R/H BRAKE WAS ALSO FOUNDTO HAVE A BROKEN / SDR CA030812005Stator · failed(CAN) STATOR BROKEN ON LT BRAKE ASSY. ACCORDING TO THE WEAR INDICATORS, THERE WAS APPROX. 150-200 CYCLES OF BRAKE LIFE REMAINING.PROBLEM DESCRIPTION WOULD PROBABLY BE PREMATURE BRAKE FAILURE. THE LT WHEEL ASSY WAS ALSO REPLACED. INSPECTION OF THE RT BRAKE ASSYSDR 2003F00519Flange · crackedTHE PROBLEM STARTED WITH THE FREON AIR CONDITIONER CYCLING IN FLIGHT. AT THE SAME TIME THE LEFT PRE-COOL LITE ILLUMINATED MOMENTARLY UPON TAKE OFF. INVESTAGATION REVEALED A CRACK IN THE LEFT FLOW PACK OUTBOARD SIDE FLANGE. HEAT FROM THE CRACK VENTED IN THE TASDR CA030729014Spring · mismanufactured(CAN) MAINTENANCE TECHNICIANS WERE REPLACING A BROKEN HEADREST EXTENSION SPRING WITH A NEW PART WHEN THE NEW PART FAILED. THE NEW SPRING SUPPLIED BY CESSNA WAS FOUND TO BE EXTREMELY BRITTLE AND WOULD BREAK IF DEFLECTED. A CALL TO CESSNA CUSTOMER SUPPORT CONFIRSDR CA030724006Pad · corroded(CAN) DUE TO LEAKING GASKET AT BLEED AIR SUPPLY TUBE FOR INLET VANE ANTI-ICING THE FORWARD FACE OF THE UPPER LT ENGINE MOUNT PAD HAS CORRODED.SDR CA030724005Axle · corroded(CAN) DURING A PHASE 1-5 INSPECTION OF THE MAIN LANDING GEAR THE AXLE EXPANSION PLUG PN 5514350 WAS FOUND CORRODED. UPON REMOVAL OF THE PLUG CORROSION WAS FOUND ON THE AXLE BORE APPROXIMATELY 1.5 INCHES FROM THE END.SDR CA030724004Wire · broken(CAN) DUCT OVERHEAT SENSOR WIRE PN W84C20 WAS FOUND BARE & BROKEN UNDER DUCT COUPLING CLAMP. THE ELECTRICAL CIRCUIT WAS COMPLETED THROUGH THE CLAMP AND DID NOT SHORT TO GROUND BECAUSE IT WAS ISOLATED BY THE SILICONE RUBBER COUPLING.SDR CA030724003Seal · damaged(CAN) BOTH MAIN LANDING GEAR WHEEL ASSEMBLIES WERE INSTALLED WITH THE INBOARD WHEEL BEARING SEAL INSTALLED ON THE INCORRECT SIDE OF THE SNAP RING. THE MAIN WHEEL INSTALLATION BUILD-UP OUT OF SEQUENCE WITH THE BUILD-UP SHOWN IN THE COMPONENT MAINTENANCE MANUAL.SDR CA030716001Deflector · cracked(CAN) TECHNICIANS FOUND CRACKED AND MISSING PIECES OF DIFFUSER DEFLECTOR SEGMENTS DURING AN ENGINE INTERNAL BORESCOPE INSPECTION. AFTER INVESTIGATION IT WAS FOUND THAT THE STARTER GENERATOR HAD BEEN REMOVED IN MARCH 2003 FOR CAUSING HIGH FREQUENCY VIBRATIONS. SDR CA030710004Seal · dirty(CAN) CAMPAIGN NOTICE 851-52-20-020 TO INSPECT THE EMERGENCY EXIT FOR STICKING CARRIED OUT. THE EMERGENCY EXIT OF AIRCRAFT WAS INITIALLY DIFFICULT TO OPEN. THE SEAL WAS CLEANED AND INSPECTED AND FOUND SERVICEABLE. THE EMERGENCY EXIT WAS REINSTALLED AND FUNCTIOSDR CA030702001Bolt · wrong part(CAN) BOLTS ORDERED FROM CESSNA AIRCRAFT COMPANY UNDER PROPRIETARY PN S346151 WERE RECEIVED AND DETERMINED TO BE INCORRECT. THE ORIGINAL BOLTS REMOVED FROM THE ENGINE MOUNT INSTALLATION WERE STAMPED WITH PN NAS464P864. REPLACEMENT BOLTS ORDERED FROM CESSNA UNDSDR CA030625004Strut · punctured(CAN) PILOT REPORTED THAT THE NOSE OLEO WAS BOTTOMING OUT WHILE TAXING THE AIRCRAFT. WHEN ATTEMPTING TO SERVICE THE AIRSIDE OF THE OLEO IT WAS DISCOVERED THAT OIL WAS PRESENT AT THE AIR VALVE. THE STRUT WAS DISASSEMBLED TO VERIFY IF ANY DAMAGE HAD OCCURRED TO SDR CA030626001Seal · damaged(CAN) IN PREPARATION FOR A PHASE 5 INSPECTION MAINTENANCE TECHNICIANS HAD DIFFICULTY REMOVING THE EMERGENCY EXIT DOOR. UPON REMOVAL IT WAS NOTED THAT THE DOOR SEAL HAD SOME FORM OF LUBRICANT ON IT THAT CAUSED THE SEAL TO STICK TO THE FRAME. THE AIRCRAFT MAINTESDR 2003FA0000654Line · crackedAIRCRAFT CAME BACK FROM A TRIP LEAKING HYDRAULIC FLUID FROM THE NOSE GEAR AREA. FOUND LINE PN 6517105-39 CRACKED AND LEAKING HYDRAULIC FLUID.SDR GVR2003F00004Seat · crackedUPPER CHAIR BASE ASSEMBLY CRACKED AT CHAIR BACK ATTACH POINTS. CHAIR WAS REPAIRED IAW STC ST01042WI STRUCTURAL SEAT REPAIR.SDR 2003FA0000762Controller · miswiredPX CONTROLLER REPLACED DUE TO INTERNAL FAILURE AFTER REPLACEMENT PILOT COMPLAINED ABOUT A 6000+ FOOT PER MINUTE CABIN CLIMB RATE AND THAT THE CONTROLLER BACK LIGHTING CAME ON WHEN THROTTLES WERE REDUCED BELOW 90 PERCENT. INSPECTION OF THE SYSTEM REVEALED THATSDR CA030610001Rib · worn(CAN) DURING PHASE 5 INSPECTION SEVERAL FLAP RIB EXTENSIONS WERE FOUND WORN BY THE RIVETS SECURING THE FLAP TRACKS TO THE WING. THE CENTER HINGE INBOARD AND OUTBOARD EXTENSIONS ON THE LT FLAP AND THE INBOARD ON THE RT FLAP WERE WORN BEYOND LIMITS AND REPLACED.SDR CA030605014Switch · out of rig(CAN) THE FLAP SYSTEM SECONDARY SWITCHES LOCATED IN THE AFT CABIN WERE FOUND TO BE SEVERELY OUT OF RIG. THIS ALLOWED THE FLAP BELL CRANKS TO OVER TRAVEL CONTACTING THE WING STRUCTURE DURING FLAP OPERATION. NO STRUCTURAL DAMAGE WAS FOUND. SYSTEM RERIGGED & CHECSDR CA030627002Insulation · burned(CAN) DURING AN INSPECTION ON THE AIRCRAFT, THE COCKPIT HEADLINER WAS REMOVED TO ACCESS THE G-SWITCH FOR A FUNCTIONAL CHECK. ONCE THE HEADLINER PANEL WAS REMOVED A SECTION OF INSULATION THAT WAS NEXT TO THE MAP LIGHT FOR THE CO-PILOT WAS FOUND SCORCHED AND BRISDR CA030603006Stator · broken(CAN) A/C WAS TAXIING TO POSITION TO PARK ON APRON WHEN IT HAD AN UNCOMMANDED BRAKING ACTION ON LT SIDE OF A/C. FLIGHT CREW SHUT DOWN AS NORMAL AND INVESTIGATED PROBLEM. UPON VIEWING LT BRAKE, NOTICED PIECES OF BRAKE STICKING OUT AND REASON FOR BRAKE TO JAM. SDR GVR2003F00003Seat · crackedUPPER CHAIR BASE ASSEMBLY CRACKED AT CHAIR BACK ATTACH POINTS. STRESS ON CHAIR BACK AND METAL FATIGUE PROBABLE CAUSE. ALSO PREVIOUS INAPPROPRIATE REPAIR. SOMEONE PUT A GUSSET IN AREA MARKED 2. CHAIR WAS REPAIRED IAW ST01042WI STRUCTURAL SEAT REPAIR.SDR GVR2003F00002Seat · crackedUPPER CHAIR BASE ASSEMBLY CRACKED AT CHAIR BACK ATTACH POINTS. STRESS ON CHAIR BACK AND METAL FATIGUE PROBABLE CAUSE. CHAIR WAS REPAIRED IAW ST01042WI STRUCTURAL SEAT REPAIR.SDR 5868Sprocket · detachedAIRCRAFT PITCH TRIM CONTROL FROZE IN PLACE, DURING FLIGHT, DUE TO THE RIGHT PITCH TRIM ACTUATOR CHAIN SPROCKET PN 556450-6 BECOMING DISLODGED FROM ACTUATOR DUE TO ATTACHMENT PIN FOR THE SPROCKET PN S2637-6Z11 COMING OUT OF THIS SPROCKET TO SHAFT ATTACHMENT. ASDR AUS20030389Probe · separated(AUS) LT ENGINE T1 PROBE SHEARED. PROBE ENTERED ENGINE CAUSING DAMAGE TO SPINNER, FAN BLADES AND BYPASS STATORS. SUSPECT PROBE SHEARED DUE TO FOD. SMALL PIECES OF YELLOW PLASTIC MATERIAL WERE FOUND IN THE CORE STATOR VANES UPON ENGINE DISASSEMBLY.SDR 2003FA0000358Antenna · separatedTHE HF ANTENNA BROKE OFF DURING FLIGHT, FROM THE VERTICAL STABILIZER TENSION UNIT. THE ANTENNA CABLE SLAPPED AGAINST THE TAILCONE, CHIPPING PAINT. NO STRUCTURAL DAMAGE FOUND.SDR CA030409011Piccolo Tube · cracked(CAN) A RIGHT ENGINE INLET FOUND CRACKED WHERE INLET INTO PICOLO TUBE FOR LIP HEAT IS MOUNTED. CRACK RADIATES UPWARD ABOUT 4 INCHES. NEW INLET INSTALLED. TESTSDR CGO2003F00003Case · crackedWHILE INSPECTING ELT BATTERY IN CONJUNCTION WITH PHASE 18. 12 MONTH EMERGENCY EQUIPMENT INSPECTIONS AND FAR 91.207(D); NOTED: ELT BATTERY CASE CRACKED, CORROSION FROM LEAKING BATTERY MATERIAL ON INTERIOR OF SAME AREA. BATTERY MFG, EXPIRATION DATE OF 7/2003,SDR CA030321001Actuator · failed(CAN) DURING THE DAILY INSPECTION THE NUT SECURING THE RUDDER TRIM TABACTUATOR UPPER BOLT WAS NOTICED MISSING. THE NUT SECURING THE LOWER BOLT WAS LOOSE WITH NO COTTER PIN INSTALLED. 5.7 HOURS HAD ELAPSEDSINCE THE PHASE 1 THRU 4 INSPECTION. THE UPPER AND LOWSDR CA030320002Stator · broken(CAN) AIRCRAFT RETURNED FROM TRIP MARCH 17 / 03 WITH A SNAG IN THE LOGBOOK ( 2016B)- BRAKES ARE GRABBING WHEN APPLIED, NOTICEABLE AT LOW SPEEDS AND DURING GROUND TURNS. A/C WHEEL AND BRAKE ASSY'S REMOVED AND DISMANTLED FOR INSPECTION.BRAKE ASSY S/N 1649 HAD ASDR CA030311001Rib · worn(CAN) DURING A PHASE 5 INSPECTION THE FLAP RIB EXTENSIONS WERE FOUND WORN BY THE RIVETS SECURING THE FLAP TRACKS TO THE WING TRAILING EDGE. DAMAGE WAS DOCUMENTED AND REPAIRED AS PER IN HOUSE SB.THE RT INBOARD CENTER HINGE WAS REPLACED.SDR CA030312023Warning Light · illuminated(CAN) DURING APPROACH, ANTI-SKID INOP ANNUNC ILLUM. EMERG SYS WAS UTILIZED FOR FINAL BRAKING. ILLUM OF ANTI-SKID ANNUNC, NORMAL BRAKING, ANTI-SKID OR POWER BRAKES ARE BLOCKED, ARE NOT AVAILABLE BY DESIGN. EMER BRAKING MUST BE UTILIZED. A/C WAS RETURNING FROSDR CA030312022Seal · contaminated(CAN) DURING CRUISE AT FL 410, CREW NOTED INCREASED NOISE LEVEL AND CABIN ALT RISING. LOUD BANG FOLLOWED WITH DECOMPRESSION OF CABIN. SECONDARY DOOR SEAL HELD AGAINST TOTAL DECOMPRESSION. EMER DESCENT AND UNSCHEDULED LANDING FOLLOWED. ON GROUND IT WAS FOUND TSDR ESE2003F00000Blower · failedDECENDING, AFTER A 3 HOUR FLIGHT, THE CREW SMELLED FUMES WHILE PASSING THROUGH 8,000 FEET. FUMES WERE ALSO EXHAUST TYPE FUMES. THE CREW TURNED TEMPERATURE CONTROL TO FULL COLD. THE SMELL DISAPPEARED. LEVEL AT 4,000 FEET ON DOWNWIND LEG , THE CREW SELECTED SDR GVR2003F00001Seat · crackedUPPER CHAIR BASE ASSEMBLY CRACKED AT CHAIR BACK ATTACH POINTS. CHAIR WAS REPAIRED IAW STC ST01042WI STRUCTURAL SEAT REPAIR.SDR CA030221009Bearing · failed(CAN) AT FLIGHT LEVEL 33,000 FT A POPPING SOUND FOLLOWED BY ENGINE VIBRATIONS WAS EXPERIENCED. RT POWER LEVER RETARDED SLOWLY AND VIBRATION LEVEL SOFTENED,BUT, STILL NOTICEABLE, ALL ENGINE PARAMETERS WERE NORMAL AND STEADY. AT 73 PERCENT ON DECENT THRU 29000 F
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