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 = 'E90' 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 = 'E90' 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 2005FA0001349Spar Cap · crackedDURING COMPLIANCE WITH AD 89-25-10, 1,000 HOUR INTERVAL EDDY CURRENT INSPECTION, THE SPAR CAP WAS FOUND TO BE CRACKED 3 INCHES OB OF BATHTUB AT RT WING LOWER FORWARD SPAR ATTACH POINT.SDR 2005FA0000196Clevis Pin · brokenPILOT REPORTED SOUND (LIKE A TIRE BLOWING OUT) UPON LANDING. THERE WAS SEVERE VIBRATION ON ROLLOUT. THERE WAS NO VIBRATION ON TAXI BACK TO HANGAR. UPON EXITING AIRCRAFT, PILOT NOTICED RT MAIN GEAR MISALIGNED. FURTHER INSP BY MAINTENANCE, FOUND RETAINING CLSDR FCPR200400020Retaining Ring · dislodgedFUEL CELL RETAINING RING AND CLIP HAD DISLODGED AND MIGRATED TO THE FORWARD SIDE OF THE FUEL CELL, THEN PUNCTURED CELL RESULTING IN A FUEL LEAK.SDR 418611Blower · failedSMOKE IN COCKPIT CAUSED BY FAILED ELECTRICAL MOTOR ON VENT BLOWER ASSEMBLY. LOG BOOK WAS NOT AVAILABLE AT TIME OF INSTALLATION, SO TOTAL TIME OF PART IS UNKNOWN.SDR 2004FA0000843Hose · deterioratedDURING CLIMB OUT, OIL PRESSURE ON BOTH ENGINES DROPPED TO APPROXIMATELY 50 PSI WITH SLIGHT SURGING. AUTOFEATHER WAS ENGAGED AT THE TIME. MAINTENANCE FACILITY DISCOVERED THAT BOTH OIL COOLER LONG LINES WERE DETERIORATING INTERNALLY. THE HOSES ARE AEROQUIP HOSSDR 0042Trim Tab · wrong partDURING A DETAILED INSPECTION OF THE AIRCRAFT THE RUDDER TRIM TAB HORN BUSHING WAS FOUND TO BE WORN BEYOND ALLOWED LIMITS. REPLACEMENT OF THE HORN IN THE TRIM TAB IS NOT A GOOD OPTION, DUE TO THE AMOUNT OF DISASSEMBLY OF THE TAB IN ORDER TO ACCOMPLISH THE TASKSDR 0027Stator · brokenAFTER LANDING THE PILOT WROTE UP, RIGHT BRAKE HAS INTERMITTENT RAPID CYCLES OF, ON AND OFF BRAKE PRESSURE. ALSO INDICATED, APPEARS TO BE LEAKING HYDRAULIC FLUID. MAINTENANCE INSPECTED THE BRAKE AND FOUND THE INNER BRAKE CARRIER LINING BROKEN. THE PIECE OF TSDR GNL2004F00002Wheel · crackedON PREFLIGHT INSPECTION A DARK HAIR LINE CRACK EXTENDED FROM A BOLT HOLE ON THE IB SIDE OF THE WHEEL HALF. REMOVED WHEEL, APPLIED DYE PENT AND CONFIRMED THE CRACK. THE WHEEL HALF IS CONDEMNED AND REMOVED FROM SERVICE.SDR GNL2004F00001Actuator · failedNLG ACTUATOR FAILED ON RETRACTION, STRIPPED INTERNAL GEARS, IN THE SHAFT 5770 CYC/OH.SDR GNL2004F00000Windscreen · crackedTHE AIRCRAFT WAS AT 22,000 FT ENROUTE, WHEN THE CO-PILOTS WINDSCREENS INNER PLY CRACKED LIKE A SPIDER WEB ACROSS THE ENTIRE WINDSCREEN. THE PRESSURIZATION STARTED TO FAIL, THE CABIN CLIMBED TO 10,000 FT. THE PILOT DECLARED AN EMERGENCY, ASKED CENTER FOR BELOSDR 200FA0000645Rib · crackedEND RIB CRACKED SEVERAL PLACES. FWD SPAR, INBOARD END CRACKED.SDR 2003FA0000315Wheel · brokenTHE INBOARD WHEEL HALF FAILED FROM ONE BOLT HOLE AND THE CRACK WALKED ALL THE WAY AROUND THE WHEEL HALF. THE WHEEL AXLE NUT WAS THE ONLY THING THAT KEPT THE WHEEL ON THE AXLE. THIS HAPPENED DURING TAXI TO TAKEOFF.SDR 0020Torque Knee · crackedDURING COMPLIANCE OF SB 32-3134 AND AD 2002-01-10, RIGHT LANDING GEAR UPPER TORQUE KNEE WAS FOUND TO BE CRACKED AT PROTRUSION OF CENTER LUG. THIS UNIT HAD BEEN INSPECTED MULTI TIMES PRIOR TO THIS INSPECTION AND PASSED THOSE INSPECTIONS. UNITS EXACT TOTAL TIMSDR Q2A2003F00000Fitting · crackedWHILE PERFORMING NDT INSPECTION OF WING ATTACH FITTINGS, LEFT LOWER FORWARD FITTING FOUND CRACK IN RADIUS OF BOLT HOLE. SPAR WAS THEN REPLACED.SDR A152Wire · corrodedDURING INSPECTION OF FUEL PANEL DIODES: FOUND FUEL PANEL DIODES AND WIRING CONNECTION CORRODED: CLEANED , TREATED AND REINSTALLED PANEL.SDR CA020913005Washer · mismanufactured(CAN) SPECIAL 7/8 INCH DIAMETER PRELOAD INDICATING WASHER ASSY USED ON LOWER FORWARD WING ATTACH BOLTS INDICATED PROPER TORQUE PREMATURELY. ESTIMATE NORMAL TORQUE TO BE AT LEAST 300 FT LBS AND SUSPECT WASHER ASSEMBLY INIDCATED TORQUE AT APPROX 100 FT LBS.SDR 2002FA0001079Bolt · crackedRIGHT ENGINE HAD NO REVERSE, FOUND FORWARD REVERSING CABLE/GOVERNOR BLEED LINK BOLT CRACKED AND SPLIT OPEN AT HOLE IN BOLT FOR REVERSING CABLE TO THREAD THROUGH. REVERSING CABLE COULD MOVE FORWARD AND AFT WITHOUT CONTROLLING GOVERNOR. POSSIBLE BOLT HAD BEEN SDR CUX2002F00002Stiffener · crackedRIGHT WING UPPER FORWARD STIFFENER (PN 50-120068-7) WAS DISCOVERED CRACKED DURING A ROUTINE PHASE 1 INSPECTION. THE CRACK BEGAN AT THE INBOARD EDGE, EMANATING OUTWARD THROUGH THE FIRST 2 RIVET HOLES FOR A TOTAL LENGTH OF 1.55 INCHES. THE DAMAGED PART WAS REMSDR CUX2002F00001Skin · crackedRIGHT ELEVATOR TRIM TAB OUTER SKIN WAS DISCOVERED CRACKED AT THE UPPER INBOARD AFT CORNER DURING A ROUTINE PHASE 1 INSPECTION. THE CRACK BEGAN AT A SKIN ATTACH COUNTER SUNK RIVET AND EXTENDED FORWARD AND FAT APPROXIMATELY .350 INCH IN EACH DIRECTION. THE TABSDR CUX2002F00000Fitting · scratchedLEFT WING LOWER FORWARD INBOARD WING BOLT ATTACH FITTING (PN 50-120073-7) WAS DISCOVERED TO HAVE 3 SMALL SCRATCHES DURING A REPETITIVE INSPECTION OF AD. THE SCRATCHES WERE LOCATED ON THE ATTACH BOLT WASHER SEARING FACE RADIUS IN AN AXIAL DIRECTION AND WERE APSDR T4O2002F00004Rib · crackedFOUND DURING PHASE INSPECTION: LEFT ELEVATOR HAD A CRACKED INBOARD RIB (PN 50-610000-355), RIB DOUBLER BRACKET, AND INBOARD MAIN SPAR FLANGE AT INBOARD 90 DEGREES BEND, ALL WHERE THE ELEVATOR TORQUE TUBE ATTACHES. CRACKS VARY IN LENGTH FROM 1.3 INCHES ON SPASDR T4O2002F00001Skin · crackedRIGHT CENTER SECTION SKIN CRACKED 2.0 INCHES BETWEEN RIVETS AT DOUBLE ROW RIVET SKIN JOINT BETWEEN RIVETS. LOCATION ON SKIN IS JUST AFT OF MAIN WING SPAR CAP AT BL 16.25. THIS AREA IS PART OF THE PRESSURE VESSEL, BEFORE TRANSITION TO THE UNPRESSUREIZED WING.SDR 2002FA0000645Spar · crackedEND RIB CRACKED SEVERAL PLACES. FORWARD SPAR, INBOARD END CRACKED.SDR 2002FA0000513Compressor · brokenAFTER LANDING AND ENGINE SHUTDOWN, AIRCRAFT OBSERVED TO HAVE SMOKE COMING OUT OF NOSE SECTION. ON INSPECTION, FOUND AIR CONDITIONER COMPRESSOR SEIZED. SMOKE WAS CAUSED BY COMPRESSOR DRIVE MOTOR BELTS DRIVING THE SEIZED PULLEY ON COMPRESSOR, MELTING THE BELTSSDR 2002FA0000776Duct · collapsedAT STATION 277 IS THE HEATER REGISTER LOCATED FORWARD OF THE LAVATORY. TWO INCHES FROM THE HEAT DUCTING IN THIS AREA IS THE (1010 EV A .6250 IMPERIAL) TUBING THAT SUPPLIES PNEUMATIC PRESSURE TO THE EMPENNAGE DEICE BOOTS. THIS EMPENNAGE DEICE BOOT TUBING WAS SDR 2002FA0000365Landing Gear · failedMAIN LANDING GEAR A LOWER TORQUE KNEE, FAILED.SDR T402001F00000Skin · crackedRIGHT CENTER SECTION SKIN CRACKED 2.25 INCHES BETWEEN RIVETS AND BEYOND AT DOUBLE ROW RIVET SKIN JOINT BETWEEN RIVETS. LOCATION ON SKIN IS JUST AFT OF MAIN WING SPAR CAP AT BL 16.25. THIS AREA IS PART OF THE PRESSURE VESSEL BEFORE TRANSITION TO THE UNPRESSURSDR GON2001F00000Actuator · intermittentAC TOOK OFF, PILOT RETRACTED GEAR, GEAR WENT UP 1/3 WAY AND STOPPED, POPPED LANDING GEAR C/B AND RED HANDLE LIGHT ON PILOT ATTEMPTED TO EXTEND GEAR MANUALLY. GOT 3 PUMPS OF HANDLE AND IT STOPPED. COULD NOT MOVE, PILOT THEN FLEW FOR APPROX 1.5 HOURS TO BURN OSDR 0016Torque Link · crackedDURING INSPECTION OF UPPER TORQUE KNEE PER THE REQUIREMENTS OF RAYTHEON REOCCURRING SERVICE BULLETIN 32-3134, THE LEFT UPPER TORQUE KNEE ON ONE OF THE MAIN GEARS WAS NOTED TO BE CRACKED IN THE RADIUS OF THE SINGLE LUG. THIS CRACK WAS IN LOCATION NOTED TO BE RSDR 0015Torque Link · crackedDURING THE COMPLIANCE OF RAYTHEON RECURRING SERVICE BULLETIN 32-3134, INSPECTION OF THE MAIN LANDING GEAR TORQUE KNEE'S, CRACKS WERE FOUND IN THE RADIUS AREA OF THE UPPER TORQUE KNEE, ON EACH SIDE OF THE SINGLE LUG. THE CRACK IN THIS WAS IN THE AREA NOTED TO SDR 0013Support Bracket · crackedTHE RIGHT INBOARD LANDING GEAR ACTUATOR SUPPORT BRACKET IS CRACKED AT THE BOTTOM AREA OF THE BRACKET WHERE IT ATTACHES TO THE WING SPAR STRUCTURE. THE WING SPAR STRUCTURE IS NOT EFFECTED BY THIS CRACK. THE CRACK IS APPROXIMATELY .5 INCH LONG AND IS THE RADIUSSDR 0012Channel · crackedDURING THE PROCESS OF REPAIRING CRACKS IN THE BULKHEAD AT STATION 176.5 ON BOTH THE LEFT AND RIGHT SIDE CRACKS IN THE LEFT CHANNEL P/N 50-420014-229 AND RIGHT CHANNEL P/N 50-420018-230, IN THE RADIUS AREA OF THE BEND ON THE SKIN SIDE OF THE CHANNEL. THE CRACKSDR 0011Frame · crackedDURING COMPLIANCE OF THE 13,000 LANDING INSPECTION ON THE FUSELAGE BULKHEADS CRACKS WERE FOUND ON THE 176.5 BULKHEAD ON BOTH THE LEFT AND RIGHT SIDE OF THE AIRCRAFT. THE CRACKS ARE ON THE BULKHEAD FRAME P/N 50-420028-57 AND 50-420028-58, NEAR THE BOTTOM OF THSDR R2J2001F00002Pin · brokenWHILE TROUBLE SHOOTING LOW CABIN DIFFERENTIAL PRESSURE FOUND THAT THE OUTFLOW VALVE CONE WOULD HANG OPEN AT TIMES. VALVE REMOVED AND INSPECTED. FOUND THAT GUIDE PIN THAT GUIDES CONE TO KEEP IT FROM COCKING WAS BROKEN. OVERHAULED EXCHANGE VALVE WAS INSTALLEDSDR 0010Bulkhead · crackedDURING COMPLIANCE OF A 13,000 CYCLE INSPECTION CRACKS WERE FOUND ON BOTH THE LEFT AND RIGHT SIDE OF THE AIRCRAFT AT FUSELAGE BULKHEAD 176.5. SMALL CRACKS WERE FOUND AT THE POINT WHERE THE BULKHEAD AND FLOOR MEET. A CRACK WAS FOUND AT THE LEFT 176.5 BULKHEAD SDR CIEA0004Windshield · crackedDURING WASHING OF THE AIRCRAFT THE MECHANIC NOTICED AN UNUSUAL MARK ON THE CO-PILOTS WINDSHIELD. FURTHER INSPECTION REVEALED A CRACK IN THE OUTER WINDOW GLASS PANE APPROXIMATELY .5 INCH INBOARD OF THE CENTER POST AREA, RUNNING VERTICALLY APPROXIMATELY 12 INCHSDR ERYR682D2001Liner · brokenOVERHAULED BRAKE ASSEMBLY WAS INSTALLED AND FUNCTIONALLY TESTED BY MAINTENANCE PERSONNEL WITH NO NOTED DEFECTS. DURING TAKEOFF ROLL PILOT NOTICED AIRCRAFT SEEM TO PULL TO ONE SIDE, PILOT ABORTED TAKEOFF AND RETURNED TO CHOCKS. MAINTENANCE PERSONNEL VISUALLY EXSDR SDRS2001001Skin · crackedDURING SCHEDULED INSPECTION, TOP OF THE AILERON JUST OUTBOARD OF THE INNERMOST HINGE POINT ALONG THE LAP JOINT WAS FOUND TO BE CRACKED. CRACK WAS APPROX 4.5 INCHES LONG AND HAD BEEN CONCEALED UNDER THE PAINT. REPLACED THE AILERON WITH A SERVICEABLE PART.SDR CA010406006Windshield · failed(CAN) TWENTY MINUTES OUT, LEVEL AT 21,000 FEET, RT WINDSHIELD SHATTERED. AIRCRAFT DESCENDED TO SAFE ALTITUDE, INNER PLY CONFIRMED FAILED. AIRCRAFT RETURNED TO BASE AT REDUCED SPEED AND PRESS DIFF.SDR T402001F00001Skin · crackedRIGHT CENTER SECTION SKIN CRACKED BETWEEN RIVETS AND BEYOND AT DOUBLE ROW RIVET SKIN JOINT, BETWEEN RIVETS. LOCATION ON SKIN IS JUST AFT OF MAIN WING SPAR CAP AT BL 16.25. THIS AREA IS PART OF THE PRESSURE VESSEL BEFORE TRANSITION TO THE UNPRESSURIZED WING. SDR CIEA0002Dipstick · looseAPPROXIMATELY 15 MINUTES AFTER TAKEOFF THE PILOT NOTICED A RIGHT ENGINE TORQUE INDICATION FLUCTUATION, FOLLOWED BY A DROPPING OIL PRESSURE INDICATION. THE PILOT REDUCED THE POWER ON THE ENGINE. THE PILOT RETURNED TO THE AIRPORT AND LANDED WITHOUT INCIDENT, WSDR 20000405SH005Bolt · crackedDURING INSPECTION OF WING SPARS IAW AD 89-25-10 AND BEECH SIRM MANUAL, THE LEFT LOWER FORWARD WING BOLT WAS FOUND CRACKED USING DYE PENETRANT. (X)SDR CA000118024Wheel · broken(CAN) INNER WHEEL (BRAKE HALF) CRACKED DURING TAXI AND JAMMED THE BRAKE. FURTHER INVESTIGATION REVEALED CRACKS IN THE OTHER MAIN WHEEL HALVES.SDR 99ZZZX2798Power Supply · failedTUL - AIRCRAFT DEPARTED AND HAD JUST LEVELED OUT OF 14,500 FEET WHEN SMOKE WAS DISCOVERED IN THE CABIN. SMOKE WAS COMING FROM THE RIGHT WINDOW FRAME NEAR SEAT NR 6. THE PILOT RETURNED TO TVL. WELL BEFORE LANDING, THE SMOKE HAD QUIT AND CLEARED OUT OF THE CASDR 99ZZZX2375Wheel Half · crackedPERFORMED DRY PENETRANT INSPECTION ON WHEEL HALVES PER BF GOODRICH MM, PARA 2 PAGE 501 REV 1/86. FOUND CRACK STARTING INSIDE TIE BOLT-HOLE EXTENDING OUTWARD IN TWO DIRECTIONS PAST THE WHEEL HALF PACKING GROOVE. CRACK WAS FOUND IN ONE TIE-BOLT HOLE ONLY. ALLSDR 99ZZZX1653Actuator · misoverhauledDURING PHASE INSPECTIONS, BOTH LT AND RT ELEVATOR TRIM ACTUATORS WERE FOUND OUT OF FREE-PLAY LIMITS PER BEECH E90 MM. ACQUIRED 2 NEW ACTUATORS. BOTH INSTALLED WITH ALL NEW BUSHINGS AND BOLTS IN SYSTEM. AFTER FINAL RIGGING, ANOTHER FREE-PLAY CHECK WAS MADE. SDR 99ZZZX1652Actuator · misoverhauledDURING PHASE INSPECTIONS, BOTH LT AND RT ELEVATOR TRIM ACTUATORS WERE FOUND OUT OF FREE-PLAY LIMITS PER BEECH E90 MM. ACQUIRED 2 NEW ACTUATORS. BOTH INSTALLED WITH ALL NEW BUSHINGS AND BOLTS IN SYSTEM. AFTER FINAL RIGGING, ANOTHER FREE-PLAY CHECK WAS MADE. SDR 99ZZZX1965Strut · corrodedDURING REPLACEMENT OF WIPER RING AND SCRAPER RING ON NOSE LANDING GEAR, REMOVED PAD P/N 104036D3ZM0908 TO REPLACE. SEVERE CORROSION NOTED INSIDE OF UPPER CYLINDER BEHIND PAD. SUSPECT MOISTURE BEING TRAPPED IN PAD AS CAUSE OF CORROSION.SDR 99ZZZX1924Fitting · looseDURING ROUTINE INSPECTION, NOTICED ONE OF FOUR HUCK BOLTS, ON RT NLG DRAG LEG FITTING, BROKE AND ALL BUT ONE ON BOTH LT AND RT FITTINGS WERE LOOSE. REMOVED ALL EIGHT HUCKBOLTS FROM FITTINGS AND INSTALLED NAS464-PE-LA4 AND NAS464-P3-LA5 BOLTS WITH SELF-LOCKINGSDR 99ZZZX1923Fitting · looseDURING ROUTINE INSPECTION, NOTICED ONE OF FOUR HUCK BOLTS, ON RT NLG DRAG LEG FITTING, BROKE AND ALL BUT ONE ON BOTH LT AND RT FITTINGS WERE LOOSE. REMOVED ALL EIGHT HUCKBOLTS FROM FITTINGS AND INSTALLED NAS464-P3-LA4 AND NAS464-P3-LA5 BOLTS WITH SELF-LOCKING
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