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 = 'B200' 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 = 'B200' 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 CA040505002Hose · ruptured(CAN) BRAKE DEICE HOSE RUPTURED AND CAUSED BLEED AIR FAILURE SYSTEM TO ACTIVATE LIGHT. HOSE WAS REMOVED AND LINE CAPPED, WARNING SYSTEM REPAIRED IAW MFG MM. CH 21 BRAKE HOSE ORDERED AND SYSTEM PLACARDED AND MADE INOPERATIVE.SDR CA040423006Switch · shorted(CAN) PILOT REPORTED THAT THE STALL HEAT APPEARED TO BE ON (HIGH) MODE ON THE GROUND WHEN A WALK-AROUND WAS CONDUCTED. MAINTENANCE CONFIRMED BY RESEARCHING WIRING DIAGRAM AND SYSTEM OPERATION. TROUBLESHOT AND FOUND LT MAIN GEAR SAFETY SWITCH P/N 101-364628-3SDR CA040428003Exhaust Stack · cracked(CAN) DURING ROUTINE INSPECTION A CRACK WAS NOTED AT THE LIP HEAT WELD TO THE FORWARD SECTION OF THE EXHAUST STACK. EXHAUST UNIT WAS ORDERED AND INSTALLED WITHOUT ANY INCIDENT.SDR CA040426003Window · warped(CAN) DURING A ROUTINE DAILY INSPECTION IT WAS NOTED THE RT AFT CABIN WINDOW HAD A INWARD CONCAVE APPEARANCE ACROSS THE CENTER FROM TOP TO BOTTOM. UPON REMOVAL WITH THE USE OF A STRAIGHT EDGE IT WAS WARPED ACROSS THIS AREA. NO FURTHER DEFECTS IN THE FORM OF CRSDR CA040324002Battery · discharged(CAN) PILOT REPORTED COMPLETE ELECTRICAL FAILURE AND LANDED WITH GEAR MANUALLY EXTENDED. INSPECTION FOUND STARTER SWITCHES IN THE 'ON' POSITION AND BATTERY DOWN TO 12VOLTS, NO OTHER INDICATION OF FAULT WAS FOUND. I FEEL THAT WITH THE SWITCHES IN THE 'ON' POSITSDR 0026Windshield · crackedDURING CRUISE THE COPILOTS WINDSHIELD INNER PANE SHATTERED. NO DEBRIS FELL INTO THE CABIN OTHER THAN DUST. THE OUTER PANE STAYED IN TACT. THE PILOT DESENDED TO A LOWER ALTITUDE AS RECOMMANDED BY THE AIRCRAFT FLIGHT MANUAL. THE AIRCRAFT LANDED WITHOUT INCIDSDR AC02004F00000Windshield · crackedDURING FLIGHT, AT FLIGHT LEVEL, 21,000 FT, COPILOTS WINDSHIELD INNER PANEL CRACKED. PILOT IMMEDIATELY DESCENDED TO A SAFE ALTITUDE AND LANDED AS SOON AS POSSIBLE. UPON INSPECTION, FOUND NO DAMAGE TO OUTER PANEL. WINDSHIELD HEAT WAS OPERATING NORMALLY. NO RSDR UG12004F00000Motor · shortedREMOVED MOTOR DUE TO ARCING/ SHORTING TO CASE AND FAILURE. SHIPPED SAME AS CORE TO MFG. PART FAILURE OCCURRED IN FLIGHT AND EMERGENCY LANDING GEAR EXTENSION PERFORMED FOR LANDING WITHOUT INCIDENT.SDR AKG2004F00003Bulkhead · damagedIN COMPLETING AD, NOT ONLY WAS SCORING FOUND ACROSS THE MID SPAN, BUT ALSO ALL THE WAY AROUND WHERE THE (U) FRAME LAYS ON TOP OF THE BULKHEAD WEB. THERE IS NOT A PATCH REPAIR FOR THIS. THE BULKHEAD WEB WILL HAVE TO BE REPLACED.SDR CA040126002Hinge · worn(CAN) MAINTENANCE INSPECTION DISCOVERED LT ENGINE INLET VANE HINGE PIN WAS WORKING OUT OF THE HINGE AND CONTACTING THE INNER COWL STRUCTURE. MFG ADVISES THE HINGE ENDS ARE CRIMPED TO PREVENT PIN MOVEMENT, HOWEVER ON THIS ASSY THE PIN APPEARS TO HAVE WORN THRSDR XVQ2004F00000Chain · misroutedLANDING GEAR WOULD NOT EXTEND WHEN LANDING HANDLE SELECTED FOR DOWN. PILOT SUCCESSFULLY EXTENDED GEAR RECEIVING THREE DOWN AND LOCKED INDICATION. UNEVENTFUL LANDING PERFORMED. INSPECTION OF SYSTEM REVEALED THAT THE NLG RETRACT CHAIN WAS IMPROPERLY ROUTED OVSDR SVB2004F00000Engine · making metalON JAN 6, 2004 AIRCRAFT DEPARTED, ABOUT 10 MILES OUT THE PILOT NOTICED A RT ENGINE CHIP LIGHT. PILOT RETURNED TO DEPARTURE AND MADE AN UNEVENTFUL LANDING. AFTER INSPECTION OF THE CHIP DETECTOR BY MAINT IT WAS FOUND TO HAVE A PIECE OF GEAR TOOTH ON IT. FURTHSDR DWH2004F00000Wire Harness · brokenPILOT REPORTED LT MLG DOWN AND LOCKED INDICATOR WAS NOT ILLUMINATED AFTER LANDING GEAR EXTENSION AND DECLARED AN EMERGENCY. THE AIRCRAFT WAS LANDED ANT VNY WITHOUT INCIDENT. UPON INVESTIGATION, A TY-WRAP WAS MISSING FROM THE LT MLG DRAG ACTUATING ROLLER HAD SDR AKG2004F00001Windshield · brokenCOPILOTS WINDSHIELD INSIDE GLASS SHATTERED IN FLIGHT AIRCRAFT AND WINDSHIELD.SDR 2003FA0001247Angle · damagedTWO ANGLES THAT ARE THE FORWARD MOUNTING STRUCTURE OF THE VERTICAL STABILIZER TO THE HORIZONTAL STABILIZER HAVE 2 HOLES EACH WITH BOLTS THAT ATTACH THE HORIZONTAL STAB., AND 5 HOLES EACH WITH 4 LOCKBOLTS INSTALLED THAT ATTACH TO THE VERTICAL STAB. THE TOP HOLESDR CA040129007Bracket · cracked(CAN) ELEVATOR FORWARD BALLAST WEIGHT STOP BRACKET AND BOLT FOUND BENT APPROXIMATELY 80 DEGREES FROM ITS ORIGINALLY INSTALLED POSITION. DENTS ON WEIGHT FACE INDICATE STOP BOLT AND BRACKET ASSEMBLY WAS SUBJECTED TO SEVERAL SEVERE CONTROL MOVEMENTS OF THE AIRCRASDR 2003FA0001273Circuit Breaker · trippedDURING CLIMB, AC RT NR 1 BUSS FEEDER 50 AMP BREAKER OPEN. LT NR 1 BUSS FEEDER BREAKER OPENED SHORTLY AFTERWARD RESULTING IN LOSS OF PILOT SIDE EFIS, MFD, AND VARIOUS OTHER SYS. CREW RETURNED TO FLIGHT ORIG POINT, LANDED WITHOUT INCIDENT. VISUAL INSP OF CB PANSDR CA031205001Windshield · cracked(CAN) WHILE IN CRUISE FLIGHT THE PILOT HEARD A 'CLAP' AND THEN NOTICED A CRACK IN THE RT WINDSHIELD. THE AIRCRAFT RETURNED TO BASE. INSPECTION DETERMINED CRACK TO BE IN THE EXTERIOR PANE, LIKELY ORIGINATING FROM A SMALL STONE BRUISE. WINDSHIELD TO BE REPLACED.SDR CA031031010Duct · cracked(CAN) DISCOVERED COWL DUCT CRACKING DURING ROUTINE MAINTENANCE INSPECTION. MFG HAS PREVIOUSLY IDENTIFIED THIS PROBLEM AND DESIGNED A FIELD REPAIR TO RECTIFY IT. INCORPORATED FIELD REPAIR FR-KA-00038 TO BOTH ENGINE COWLS. DUCT PN 101-910049-12 ALSO AFFECTEDSDR CA040902008Antenna · vibrationA/C ORIGINALLY EQUIPPED WITH ANTENNA MOD CI4510-700 IAW LSTC NR C-LSA02-377/D. ANTENNA LATER RECALLED BY MANUFACTURER. REPLACEMENT ANTENNA MOD CI2480-100. DURING FLT, REPLACEMENT ANTENNA VIBRATED LOUD ENOUGH TO BE HEARD IN COCKPIT. ANTENNA REMOVED. INSTALSDR FTU2003F000AATach Generator · malfunctionedDURING ATTEMPT TO START RT ENGINE, THERE WAS NO NG RPM FROM THE RIGHT ENGINE INDICATION. FURTHER INVESTIGATION LEAD TO THE REMOVAL OF THE NG TACH GENERATOR AT WHICH TIME IT WAS DETERMINED THE GENERATOR DRIVE SHAFT WAS BROKEN. OTHER PIECE OF THE DRIVE SHAFT WSDR E812003F00001Wire · chafedINVESTIAGATED COMPLAINT OF LT LANDING LIGHT NOT ILLUMINATING. FOUND LT LANDING LIGHT POWER SUPPLY WIRE L173C18 CHAFED THROUGH AND CORRODED AT APPROXIMATE HALFWAY POINT BETWEEN LANDING LIGHT AND NOSE WHEEL WELL CONNECTOR P509. CHECKS SHOWED VOLTAGE PRESENT ATSDR 2003FA0000958Clutch · brokenAIR CONDITIONING COMPRESSOR CLUTCH ASSY HAD FAILED AFTER 58.0 HOURS OF AIRCRAFT OPERATION. APPEARS THAT THE ELECTRIC CLUTCH ASSY HAD BEEN ACTIVATED CONTINOUSLY AND OPERATED WHENEVER THE ENGINE WAS OPERATING.SDR CA040325001Windshield · failed(CAN) INNER PLY ON CAPTAINS WINDSHIELD INSTANTLY SHATTERED AT APPROXIMATELY 28,000 FT, CAUSING THE CREW TO COMMENCE AN EMERGENCY DESCENT AND LANDING. WEATHER WAS FAIR AT THE TIME AND THERE WAS NO WINDSHIELD HEAT ON.SDR 0021Sprocket · defectiveDURING COMPLIANCE, THE AILERON SPROCKET WAS FOUND TO HAVE A POSSIBLE DEFECT. DOING A VISUAL INSPECTION BETWEEN THE TWO GEARS OF THE AILERON SPROCKET, ON THE LARGE GEAR NEAR THE SHAFT AREA, IT APPEARS THE WELDING MAY NOT HAVE BEEN COMPLETED IN A SMALL AREA, APSDR CA030827013Hose · deteriorated(CAN) BRAKE DE-ICE HOSE WAS FOUND TO BE BLOCKED DUE TO DETERIORATION OF THE INSIDE OF HOSE. THE UPPER FLEXIBLE HOSE WAS FOUND TO PASS SHOP AIR THROUGH AN AIR NOZZLE BUT WAS NOT FOUND TO PASS THE VOLUME SUPPLIED BY THE ENGINE BLEED AIR. THE LARGE VOLUME OF AIRSDR 2003FA0000916Heater · crackedTROUBLESHOT NR 2 ENGINE OIL LEAK. FOUND A HAIRLINE CRACK NEAR UPPER INBOARD WELD OF PARTS MAIN BODY. LOCATED JUST UNDER WELD AND APPROX .7500 INCH IN LENGTH.SDR 2003FA0001057Floor Panel · misinstalledCABIN FLOOR SKIN AT THE CABIN ENTRANCE IS TOO THIN AND FLEXIBLE. THE SKIN FLEXES OVER A BULKHEAD THAT IS CENTERED IN THE ENTRANCEWAY. A BOARDING PERSON WILL PLACE THERE FEET ON EITHER SIDE OF THIS BULKHEAD. THIS CONSTANT FLEXING WOULD EVENTUALLY CRACK THE FSDR 2003FA0001056Duct · crackedCRACKS ARE DEVELOPING IN LOWER DUCT SKINS (PN 101-9100495) OF THE AFT LOWER ENGINE COWLINGS. (ENGINE INLETS, BOTH NR 1 AND NR 2). CRACKS IN RIVET ROW AFT OF INSPECTION PANEL (PN 101-910049-47) AND IN AFT ROW OF NUT PLATES FOR INSPECTION PANEL AT RETAINER/ SPSDR 2003FA0001058Plenum · leakingWATER WAS NOTED DRIPPING FROM BELLY BEACON. AFT FREON EVAP PLENUM FOUND TO BE LEAKING. REMOVED PLENUM, FOUND PLASTIC SECTION (BOX END) OF PLENUM CRACKED AND BROKEN AT ALL LOWER MOUNTING SCREW HOLES, CRACKS RADIATING FROM OF RIVET HOLES. PLASTIC BOX END, WHESDR CA030718002Wheel · cracked(CAN) DURING WHEEL OVERHAUL THE NDT FACILITY DISCOVERED 3 CRACKS IN THE OUTER-HALF OF THE WHEEL ASSEMBLY. CRACKING WAS IN THE WEB AREA BETWEEN THE BEARING BOSS AND THE BEAD SEAT FLANGE. THE INBOARD HALF WAS NOT DAMAGED. OUTBOARD WHEEL HALF SCRAPPED AND REPLACESDR CA030703009Bulkhead · cracked(CAN) NACELLE BULKHEAD CRACKED FROM LOWER RT BOLT HOLE TO EDGE OF BULKHEAD. NEW BULKHEAD INSTALLED ON BOTH NACELLES. PROBLEM ATTRIBUTED TO AIRCRAFT AGE AND NUMBER OFCYCLES.SDR CA030703008Stringer · cracked(CAN) 600 HR INSPECTION REVEALED 2 CRACKED STRINGERS (NR 9 RT HYD TSB 2472 REV.II.)SDR CA030627010Plate · leaking(CAN) DURING SCHEDULED INSPECTION, FOUND EXHAUST SEAL PLATE FROM LT ENGINE OUTBOARD EXHAUST STACK TO THE HEATED ENGINE INTAKE ANTI-ICE LIP WITH ONE BOLT MISSING AND THE REMAINING BOLTS LOOSE. THE RESULTING EXHAUST LEAK HAS CAUSED SOOT TO BUILDUP ON THE ENGINE SDR CA030702003Fire Detector · malfunctioned(CAN) AFTER TAKEOFF AIRCRAFT CLIMBED OUT, AND A RT ENGINE FIRE WARNING LIGHT CAME ON. COULD NOT SEE SMOKE, ENGINE FUNCTIONED NORMAL.. RETURNED TO MAINTENANCE FACILITY.SDR CA030610005Bolt · loose(CAN) UPON INSPECTION THE TRIM TAB ACTUATOR WAS FOUND TO HAVE 2 BOLTS, P/N 130909B38, LOOSE. THE ACTUATOR SHOWED NO INDICATIONS OF DAMAGE OR MALFUNCTION, TRIM TAB FREE PLAY INSPECTION WAS WELL WITHIN TOLERANCE. BOLTS WERE TORQUED AND ANTI SABATOGE LAQUER WASSDR CA030610007Actuator · misinstalled(CAN) FLAP ACTUATOR WAS FOUND TO HAVE BEEN INSTALLED INCORRECTLY WITH LUBRICANT VENT HOLE DOWN WHICH RESULTS IN LOSS OF LUBRICANT. ACTUATOR WAS REMOVED AND FOUND TO BE UNSERVICEABLE DUE TO HAVING TOO MUCH END PLAY. THE ACTUATOR WAS SENT FOR REPAIR, RE-INSTALLSDR CA030610006Regulator · failed(CAN) PNEUMATIC REGULATOR FAILURE IN CRUISE FLIGHT OCCURRED. PILOTS HAD TWO BLEED AIR FAIL LIGHTS, LEFT AND RIGHT, AND ALSO NOTED LOSS OF SUCTION AND PNEUMATIC PRESSURES CONFORMING LIGHT INDICATION. PILOTS RETURNED TO BASE. UPON INSPECTION THE REGULATOR FOUND SDR CA030424006Actuator · leaking(CAN) DURING A POST FLIGHT WALK AROUND, THE PILOT NOTICED HYDRAULIC FLUID LEAKING FROM THE NOSE GEAR ACTUATOR P/N 112-280022-21. THE FLUID WAS COMING FROM ABOVE THE RETAINER. THE ACTUATOR WAS REPLACED WITH A OVERHAULED UNIT. DURING THE RIGGING PROCESS THE POSISDR 2003FA0000364Fuel Control · malfunctionedDURING LANDING ROLLOUT, THE PILOT TRIED TO APPLY REVERSE AND THE AIRCRAFT VEERED OFF INTO THE LEFT GRASSY AREA, AND EVENTUALLY CAME TO REST IN THE WEST SOFT AREA. AN ENGINE RUNUP AFTERWARDS REVEALED A DISCREPANCY IN THE RT ENGINE FUEL CONTROL. IT WAS REPLACESDR 2003FA0000314Control Valve · inoperativeDURING APPROACH TO LANDING AT ABQ THE GEAR WOULD NOT EXTEND IN NORMAL OPERATION. LANDING GEAR HYDRAULIC POWER PACK MOTOR WOULD RUN WHEN HANDLE IN DOWN POSITION BUT GEAR WOULD NOT MOVE. EXTENDED GEAR WITH EMERGENCY SYSTEM. INSTALLED NEW SOLENOID VALVE AND GESDR CA030425005Resistor · loose(CAN) CREW REPORTED TOTAL LOSS OF ENGINE TEMPERATURE INDICATION DURING TAXI OPERATIONS. ALL TROUBLESHOOTING PROCEDURES WERE FOLLOWED IN THE ENGINE AND AIRFRAME MANUFACTURER'S MAINTENANCE MANUALS. AIRFRAME WIRING HARNESS WAS CONNECTED TO MULTIMETER FOR TESTS. OSDR 2003FA0000321Windshield · crackedCO-PILOT WINDSHIELD CRACKED DURING CRUISE. THIS UNIT WAS INSTALLED ON 01/16/2002 AT 7294.2 TT A/F. CURRENT INSPECTION REQUIREMENT CALLS FOR A WINDSHIELD SCREW TORQUE CHECK EACH 200 HOURS. OUR EXPERIENCE HAS SHOWN THAT SOON AFTER RETORQUEING THE WINDSHIELD WSDR DBC2003F00000Actuator · inoperativeACTURATOR, ON APPROACH, PILOT SELECTED GEAR DOWN. PILOT FELT NOSE GEAR TOOK LONGER THAN NORMAL TO REACH DOWN AND LOCKED POSITION. LANDING GEAR RETRACT TEST COMPLIED WITH. NOSE GEAR EXTEND TIME WAS FOUND TO BE OUT OF LIMITS IAW MM. NOSE GEAR ACTUATOR REPLACSDR CA030129004Coax · unserviceable(CAN) DURING AIRCRAFT IMPORTATION INSPECTION INTO CANADA, AVIONICS CHECKS NOTED WEAK NAVIGATION, COMMS, G/S RECEPTION. TROUBLESHOOTING FOUND THAT THE COAXIAL CABLE INSTALLED FOR THE ENTIRE AIRCRAFT, NAVIGATION, AND COMMUNICATIONS SYSTEMS HAD A MANUFACTURING DSDR 2003FA0000023Windshield · crackedFOUND 3 INCH CRACK ACROSS LOWER,OUTSIDE CORNER OF OUTSIDE GLASS PANEL WITH SOME DELAMINATION EXTENDING 3 INCHES OUT OF SAME CORNER. TECHNICIAN BELIEVES CONTINUAL RETORQING OF WINDSHIELD SCREWS CALLED OUT BY RAYTHEON CAUSED THE CRACK AND INCREASES THE CHANCES OSDR DJFA2006370Generator · unknownLOST LT GENERATOR IN FLIGHT, COULD NOT RESET. AIRCRAFT DIVERTED AND LANDED WITHOUT INCIDENT. COULD NOT DUPLICATE PROBLEM ON THE GROUND, SWAPPED GCU GROUND RAN AND TEST FLEW AIRCRAFT WITH NO FURTHER PROBLEMS.SDR 0227Gcu · malfunctionedLOST LEFT GENERATOR IN FLIGHT. COULD NOT RESET. AIRCRAFT DIVERTED TO TYS AND LANDED WITHOUT INCIDENT. COULD NOT DUPLICATE PROBLEM ON THE GROUND, SWAPED GCU GROUND RAN AND TEST FLEW AIRCRAFT WITH NO FURTHER PROBLEMS.SDR CA030106002Fuse · blown(CAN) FUSE (GMW1) HAS POPPED ON THREE DIFFERENT COMPANY B200 AIRCRAFT. FUSE PROJECTS 28 VDC OUTPUT CIRCUIT FROM THE EFIS STANDBY POWER SUPPLY (WIRES W3203-2 AND W3204-4). HAVE SUBMITTED QUERY TO RAYTHEON TECH SUPPORT FOR RECTIFICATION.SDR CA021118005Carbon Seal · failed(CAN) PILOT NOTICED SLIGHT OIL PRESSURE FLUCTUATION OF THE RT ENGINE DURING A TRAINING FLIGHT AND RETURNED TO BASE. OIL LOSS CONFIRMED AND DETERMINED THAT THE OIL (4 LITERS) HAD EXITED THROUGH THE ENGINE BREATHER SYSTEM. REMOVED ACCESSORY GEARBOX AND REPLACED
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