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 = 'B60' 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 = 'B60' 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 2022FA0000024None · collapsedRIGHT ENGINE BECAME ROUGH IN CRUISE. AIRCRAFT LANDED UNEVENTFULLY. FOUND #2 CYLINDER HYDRAULIC LIFTER P/N: 15B28037 COLLAPSED. INTAKE VALVE STEM BROKEN. PISTON DAMAGED.SDR 2022FA0000023None · collapsedRIGHT ENGINE BECAME ROUGH IN CRUISE. AIRCRAFT LANDED UNEVENTFULLY. FOUND #2 CYLINDER HYDRAULIC LIFTER P/N: 15B28037 COLLAPSED. INTAKE VALVE STEM BROKEN. PISTON DAMAGED.SDR 2019FA0000415Brush Block · wrong partALTERNATOR RECEIVED FOR REPAIR OF DRIVE END THREADED BOSS. INSPECTION OF UNIT WRONG (NON FAA/PMA) BRUSH BLOCK ASSEMBLY, RECTIFIER ASSEMBLY AND STATER ASSEMBLY INSTALLED. 10 HOURS ESTIMATED FROM FIELD REPAIR AT ENGINE MAJOR OVERHAUL.SDR MI22018F00000Intake Valve · brokenPILOT SAYS HE WAS CLIMBING THROUGH 17000` WHEN THE RT ENG LOST POWER AND WAS RUNNING ROUGH. THE PILOT DESCENDED AND LANDED WITH THE LT ENG. REMOVED COWLING AND CHECKED COMPRESSION AND FOUND NR 2 CYLINDER NO COMPRESSION. REMOVED NR 2 CYLINDER RBC AND FOUND ISDR PCPR201804260001Skin · corrodedFOUND SEVERE CORROSION ON THE HORIZONTAL STABILIZER SKINS (MAGNESIUM).SDR 2017FA0000029Hub · crackedA HUB CRACK DISCOVERED DURING ROUTINE MAINTENANCE. THE HUB WAS REPLACED WITH A SERVICEABLE UNIT.SDR SPOA20141013001Interface Unit · faultyAPPROXIMATELY ONE HOUR INTO THE FLIGHT & WITHOUT WARNING CREW EXPERIENCED A VERY LOUD, FULL VOL STATIC SQUELCH COMING THROUGH THE OVERHEAD SPEAKERS. AFTER SWITCHING FROM COMM 2 TO COMM 1 THE SQUELCH NOISE WENT AWAY BRIEFLY. HOWEVER, IT CAME BACK A FEW SECONDSDR PCPR20131218001Crankcase · crackedOPERATOR REPORTED OIL IN ENGINE COMPARTMENT. TECHNICIAN PERFORMED VISUAL INSPECTION AND FOUND CRACK IN ENGINE CRANKCASE FORWARD OF NR 2 CYLINDER FLANGE.SDR CA120326008Bolt · loose(CAN) DURING TROUBLESHOOTING FOR AN UNRELATED PROBLEM, A BOLT PN#AN174-15A/M WAS FOUND LOOSE ON THE INBD PIVOT LOCATION OF THE L/H ELEVATOR. AN ANNUAL INSPECTION HAD BEEN COMPLETED PREVIOUSLY AND A VISUAL INSPECTION OF THIS AREA SHOWED NO ISSUES. TWO FLIGHTSSDR 2009FA0000817Window · fracturedRT SIDE REAR WINDOW FRACTURED (BLEW OUT) IN FLIGHT CAUSING CABIN SUDDEN DECOMPRESSION. (K)SDR CA090424005G Switch · failed(CAN) WHILE PERFORMING 12 MONTH INSP OF ELT IAW CAR 571 APPENDIX G THE G SWITCH FAILED TO OPERATE. G SWITCH REPLACED AND UNIT RETURN TO SERVICE.SDR CA090409004Intake Valve · broken(CAN) PILOT REPORTED LT ENG RUNNING ROUGH, NO INDICATION ON GRAPHIC ENGINE MONITOR FOR CYL NR 5. OPENED COWLINGS, INSPECTED CYL NR 5, CHECKED SPARK PLUGS, CHECKED COMPRESSION NO FAULTS FOUND. DETERMINED THAT WIRING HARNESS FOR GRAPHIC ENG MONITOR INSTALLED ISDR CA080806005Turbocharger · malfunctioned(CAN) PILOT REPORTED LOW MANIFOLD PRESSURE ON LT ENG IN CLIMB OUT, ACFT RETURNED TO THE AIRPORT. MAINT BACK FLUSHED THE LT TURBO WASTEGATE AND CONTROLLER, GROUND RUN OK. NO OTHER DEFECTS NOTED, ACFT RETURNED TO SERVICE.SDR IWP2720085003Spring · misinstalledTHIS AIRCRAFT EXPERIENCED A BENT /DAMAGED RT MAIN GEAR RETRACT ROD ASSEMBLY P/N 60-810057-617. A CURRENT OVERLOAD OF THE LANDING GEAR MOTOR CIRCUIT. THE RT MAIN GEAR FAILED TO EXTEND. THE EMERGENCY GEAR FAILED TO ALSO EXTEND THE RETRACTED MAIN. AC WAS FORCED TSDR 2007FA0000506Skin · crackedBOTH FLAPS CRACKED AT ACTUATOR ATTACH POINT. LT FLAP SKIN AND RIB CRACKED. RT FLAP RIB CRACKED. RIGGING WAS OK, PROBABLY AN OPERATOR INDUCED PROBLEM. BELIEVE THE FLAPS HAVE BEEN LOWERED AT TOO HIGH AN AIRSPEED. (K)SDR DA62007F00000Escape Hatch · chafedDURING ANNUAL INSPECTION FOUND HINGED COVER FOR EMERGENCY EXIT RELEASE HANDLE WAS SAFETIED CLOSED WITH .020 INCH STAINLESS STEEL WIRE NOT COOPER BREAKAWAY WIRE OF (.040 INCH - .012 INCH). HAD TO CUT WIRE WITH WIRE CUTTING PLIERS IN ORDER TO BE ALLOWED ACCESS SDR DA62007F00006Bearing · corrodedDURING ANNUAL INSPECTION, FOUND WHEEL BEARINGS AND RACES TO BE WORN AND CORRODED. ALSO, FOUND THAT THERE WERE (2) DIFFERENT TYPES OF GREASE USED IN THE WHEEL BEARINGS AND THE MANUAL REF A MIL-G-3545 ONLY, WHICH IS A HIGH TEMP GREASE AND IS RED OR AMBER IN COLSDR DA62007F00005Window · misinstalledDURING ANNUAL INSPECTION, PILOT AND CO-PILOT SIDE WINDOWS SEALANT WAS FOUND TO BE CRACKED AND FULL OF AIR POCKETS. FOUND SEALANT TO BE IMPROPERLY APPLIED TO ATTEMPT TO RESEAL WINDOWS. AFTER REMOVAL OF THE SIDE WINDOWS, FOUND WASHERS IN SEALANT APPARENTLY USESDR CA070319006Tappet · spalled(CAN) ENGINE MODIFIED IAW FIREWALL FORWARD CENTRILUBE STC. PREVIOUS EXPERIENCE WITH THIS ENGINE SERIES PROMPTS REGULAR TAPPET INSPECTIONS. TAPPETS INSPECTED AND SPALLING WAS FOUND, EVEN ON THIS STC`D ENGINE. TAPPETS SENT TO FIREWALL FORWARD FOR EXAMINATION, ASDR DA62007F00007Door · corrodedDURING ANNUAL INSP FOUND CORROSION IN THE CABIN ENTRY DOOR IN 3 LOCATIONS. FIRST LOCATION WAS AT THE MIDDLE LOCKING PIN GUIDE ANGLE PIECE. THE SECOND LOCATION IS AT THE LOWER LOCKING PIN GUIDE ANGLE PIECE AND THE THIRD LOCATION IS ON A FRAME AT THE LOWER FWDSDR DA62007F00002Motor · damagedFLAPS FAILED IN DOWN POSITION ON LANDING. DURING TROUBLESHOOTING AND INSPECTION FOUND FLAP MOTOR AND WIRING TO BE SUBMERGED IN WATER APPROXIMATELY 1.5 INCHES TO 2 INCHES DEEP. AFTER WATER WAS CLEANED UP AND MOTOR WAS ALLOWED TO DRY FLAPS FUNCTIONED PROPERLY.SDR DA62007F00004Control Cable · corrodedDURING ANNUAL INSP, FOUND SEVERAL CONTROL CABLES THAT WERE CORRODED DUE TO BEING SUBMERGED IN WATER AND THAT WERE EXPOSED TO THE EVAPORATION OF THE WATER THAT HAD COLLECTED IN THE BELLY OF THE AC. CONTROL CABLES WILL BE REMOVED AND REPLACED, WATER DRIED UP ANSDR 2006FA0001153Stiffener · crackedDURING ANNUAL INSPECTION, STIFFENER PART NUMBER 60-410025-51 LOCATED UNDER THE NOSE BAGGAGE FLOOR ON THE RIGHT SIDE AT STATION 67 BETWEEN THE MAIN AND STANDBY INVERTER WAS FOUND CRACKED AROUND THE HI-LOK FASTENER HOLES. REMOVAL OF THE STIFFENER ALLOWED FURTHESDR 2006FA0001151Keel · crackedDURING ANNUAL INSPECTION, STIFFENER PART NUMBER 60-410025-51 LOCATED UNDER THE NOSE BAGGAGE FLOOR ON THE RIGHT SIDE AT STATION 67 BETWEEN THE MAIN AND STANDBY INVERTER WAS FOUND CRACKED AROUND THE HI-LOK FASTENER HOLES. REMOVAL OF THE STIFFENER ALLOWED FURTHESDR 2005FA0000766Cylinder · crackedDURING DIFFERENTIAL COMPRESSION TEST, AIR WAS HEARD LEAKING FROM LOWER CYLINDER AREA. COMPRESSION WAS 40/80. USING LIQUID LEAK DETECTOR, FOUND AIR BLOWING OUT FROM A CRACK IN CYLINDER FIN. REMOVED CYLINDER FROM ENGINE AND NOTED A CRACK IN THE COMBUSTION CHASDR CA050228008Control Cable · frayed(CAN) (.0625) ELEVATOR TRIM CABLE WAS FOUND WITH WIRES BROKEN IN A CRITICAL FATIGUE AREA, (.2500) LENGTH FROM AFT END, THROUGH THE IDLER PULLY AND CAPSTAN OF BENDIX FCS 810 AUTOPILOT TRIM SERVO. SEC 7 PART B: FOUND DURING AUTOPILOT REPLACEMENT. SEC 7 PART SDR 2005FA0000463Service difficultyWHILE INVESTIGATING OIL LEAK FROM TURBO, FOUND IMPELLER/TURBINE SHAFT HOLD DOWN NUT LOOSE ALLOWING SHAFT TO MOVE LATERALLY. THIS CAUSED SHAFT TO BECOME UNSEATED AT BEARING SEALS. DISCREPANCY WAS DISCOVERED EARLY ENOUGH TO KEEP IMPELLER AND TURBINE WHEELS FROSDR CYW2005F00000Transmitter · inoperativeFUEL QUANTITY INDICATORS WOULD ONLY SHOW APPROX 35 GALS MAX EVEN WITH FULL FUEL. FOUND IB AND OB LEADING EDGE CELL TRANSMITTERS GROUNDED TO AIRFRAME. REMOVAL REVEALED GROMMETS DETERIORATED ALLOWING TRANSMITTER CASE TO TOUCH AIRFRAME. RECOMMEND REPLACING GROSDR 2005FA0000211Oil Cooler · crackedCOOLER SPLIT AT WELD ON END OF COOLER. SPLIT WAS 2+ INCHES LONG RIGHT DOWN THE CENTER OF THE WELD. (GL19200501920) (GL19200502021) (K)SDR 2004FA0000797Valve · brokenWITHIN THE LAST 3 TO 3.5 HOURS OF FLIGHT, THE PILOT NOTED THE ENGINES WERE RUNNING ROUGH AND FLEW TO OUR FACILITY FOR DISCOVERED THAT THE INTAKE VALVE KEEPER KEYS WERE BROKEN, THE NR 6 CYLINDER HAD A STUCK EXHAUST VALVE. THE PILOT REPORTED HAVE THE NR 6 CYLINSDR 2003FA0001101Rod · destroyedON FINAL APPROACH, LEFT ENGINE, NR 5 ROD BROKE AND BROKE CRANKCASE.SDR 2003FA0000960Oil Cooler · crackedWE HAVE FOUND 3 OIL COOLERS IN THE PAST YEAR ON THESE AC WITH IDENTICAL CRACKS ON THE DIAGONAL SUPPORT BARS AT THE INBOARD WELD. THIS LEADS TO SEPARATION OF ONE END OF THE BAR. CAUSE OF THE CRACKS ARE NOT OBVIOUS. WE ARE ALSO AWARE OF 2 OTHER AC THAT HAVE ESDR 2003FA0000514Lifter · corrodedLIFTERS PITTED AND MUSHROOMED.SDR 2002FA0001091Lifter · spalledSEVEN SPALLING OF LIFTERS AND CAM SHAFT WITH ONLY 130 HOURS USE. ALSO FAILED WITH 60 HOURS USE.SDR 2002FA0001102Camshaft · erodedWITH NO PROBLEMS TO 1952 HRS SINCE NEW (TBO1600), THIS ENGINE WAS OVERHAULED IN FEB 99. NOTHING BUT PROBLEMS SINCE. AT FIRST OIL CHANGE, AFTER OVERHAUL (35 HOURS) ABNORMAL METAL SLIVERS FOUND IN OIL FILTER. CONTINUED FLYING. MORE FERROUS METAL AT 2ND OIL CSDR 2002FA0000992Pin · failedTHE LIFTER BORES WERE ALL SLEEVED (ALL 12) NOTE: THE SLEEVES CAME LOOSE IN ALL THE HOLES (EXCEPT TWO) ROTATING AND BLOCKING OFF OIL PASSAGES. THERE WERE NO STANDARD SAFETY PINS, OR DEVICES TO HOLE THE LIFTER SLEEVE IN PLACE. THERE ARE MANY OTHER ENGINES IN SSDR 2002FA0001103Lifter · erodedWITH NO PROBLEMS TO 1952 HOURS SINCE NEW (TBO1600), THIS ENGINE WAS OVERHAULED IN FEB 99. NOTHING BUT PROBLEMS SINCE. AT FIRST OIL CHANGE AFTER OVERHAUL (35 HOURS) ABNORMAL METAL SLIVERS FOUND IN OIL FILTER. CONTINUED FLYING. MOR FEROUS METAL AT 2ND OIL CHSDR CA000920015Bolt · sheared(CAN) THE NR 3 CYLINDER CONNECTING ROD BOLT FAILED DUE TO FATIGUE, OR DEFECTIVE MATERIAL.SDR 20000821SH011Bolt · rustedDURING ANNUAL INSPECTION, FOUND THE HORIZONTAL STABILIZERS TO CREAK WHEN FORCED UP OR DOWN. DURING INVESTIGATION, NOTICED MOVEMENT IN THE AFT ATTACH FITTING FOR BOTH SIDES. REMOVED THE BOLTS FROM THEIR CLOSE TOLERANCE HOLES TO DISCOVER THEY WERE TOO SHORT. SDR EY2R57053Hub · corrodedHUB CORRODED INSIDE EXTENSION AT THE PARTING SURFACE.SDR 20000328SH003Control Cable · failedCABLE WITH A TWIST TEST OF THE CABLE END SIMILAR TO THE DUKES CABLES ON THE PIPER PA31 FLAP SYSTEMS. (X)SDR 99ZZZX2463Oil Cooler · leakingPART FAILED DURING NORMAL SERVICE. PART HAD PREVIOUSLY BEEN REPAIRED USING EPOXY. THE EPOXY FAILED ALLOWING THE COOLER TO BEGIN LEAKING AT POINT OF ORIGINAL REPAIR. RECOMMEND ELIMINATING USE OF EPOXY ON OIL COOLERS AS EPOXY FAILURE IS COMMON.SDR 99ZZZX1138Pump · malfunctionedLEFT ENGINE VACUUM PUMP EXHIBITED LOW PRESSURE INDICATION. REMOVED PUMP. FOUND SHAFT HARD TO ROTATE. IT DID NOT SHEAR AS EXPECTED. REPLACED PUMP.SDR 98ZZZX3940Gear · shearedGROUND PERSONNEL NOTICED PIECE MISSING FROM DRAG BRACE TO NOSE GEAR ATTACH BOLT. BOLT WITH INTEGRAL PIN SERVES AS UPLOCK FOR NOSE GEAR. INSPECTION REVEALED P/N 60-820091 PIN SHEARED AT LEFT DRAG BRACE AND CORRODED IN NOSE GEAR. FAILURE MAY HAVE BEEN CAUSED SDR 98ZZZX2686Uplock Pin · failedON LANDING, NOSE GEAR COLLAPSED. SECTION OF LOWER DRAG BRACE FOUND ON RUNWAY. SECTION HAD BROKEN OFF AT OVERCENTER PIN. UPLOCK P/N FAILED, BOTH ENDS DEPARTED AIRCRAFT AND WERE NOT FOUND. SECTION OF UPLOCK PIN REMAINED IN NOSE GEAR UPPER STRUT HOUSING. BEESDR 98ZZZX2457Structure · corrodedWHILE DOING PAINT AND INTERIOR, SEVERE CORROSION WAS NOTICED UNDER THE EXISTING INSULATION. SUBMITTER STATED THE CORROSION WAS CAUSED BY THE INSULATION HOLDING WATER FROM SEAL CONDENSATION. ALSO, FOUND WINDOWS WITH BAD SEAL POSSIBLY FROM SITTING ON THE RAMP SDR 98ZZZX2275Connect Rod · failedNR 3 CYLINDER ROD BROKE IN CRUISE FLIGHT.SDR 98ZZZX88Fitting · damagedWHILE C/W WING BOLT REPLACEMENT AND WING INSPECTION, FOUND LOWER AFT WING FITTINGS ON BOTH WINGS WITH COMPRESSION MARKS. BEECHCRAFT FIELD SERVICE CONTACTED PER MM INSTRUCTIONS. SPECIAL TOOLING AVAILABLE TO RESURFACE FITTING FACE. SUBMITTER SUGGESTED OWNERS SDR 97ZZZX5085Pump · leakingPUMP WAS SPEWING FUEL AT CASE PARTING LINE AT REGULATOR. GASKET HAD PUSHED ITS WAY OUT FROM BETWEEN HALVES. RESEALED BY REPAIR STATION. WAS TOLD THIS WAS OFTEN SEEN DUE TO THINNESS OF GASKET IF ONLY OIL OR GREASE WERE PRESENT ON MATING SURFACES WHEN ASSEMBLSDR 97ZZZX4956Oil Cooler · leakingTHE FIRST OIL COOLER WAS INSTALLED WHEN THE ORIGINAL OIL COOLER DEVELOPED A LEAK AT 2426.8 HOURS. THIS OIL COOLER DEVELOPED A LEAK AFTER ABOUT 6 HOURS. OIL COOLER NR 2 WAS INSTALLED AND DEVELOPED A LEAK AFTER 2 HRS. THE NR 2 OIL COOLER WAS CUT IN TWO TO SEE
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