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 CA030221007Arm · cracked(CAN) DURING ROUTINE MAINTENANCE INSPECTION OF THE CONTROL COLUMN, A CRACK WAS FOUND IN THE BOB WEIGHT ARMNEAR THE HOLE WHERE THE ARM IS ATTACHED TO THE ELEVATOR TORQUE TUBE. BOB WEIGHT ARM REPLACED.SDR CA030212004Hose · leaking(CAN) WHEEL WELL FOUND SOAKED WITH HYDRAULIC FLUID , AFTER LAST FLIGHT OF THE DAY. FOUND BRAKE FLUID RESEVOIR DEPLETED. TOPPED OFF BRAKE FLUID RESEVOIR BUT WAS UNABLE TO DETECT LEAK UNTIL THE A/C WAS ON JACKS. WE HAVE HAD 2 PRIOR OCCURRENCES AND DETERMINED THSDR 011703N792MAFuel Control · malfunctionedTHE AIRCRAFT ENCOUNTERED SEVER TURBULENCE, AT WHICH TIME THE ENGINE WENT TO 38 PERCENT N1/MIN FLOW. UPON REMOVAL OF FUEL CONTROL, IT WAS NOTED THAT IT RATTLED. FUEL CONTROL TO BE INSPECTED BY MFG.SDR 2003FA0000035Skin · crackedWHILE DOING A DAILY INSPECTION A 1 3/4 INCH CRACK WAS FOUND IN THE LT WING JUST ABOVE THE INBOARD FLAP BELLCRANK. WE OPERATE A FLEET OF 26 550 SERIES AIRCRAFT WITH A LARGE PORTION HAVING A REPAIR TO THE LT OR RT WING AT ONE POINT OR ANOTHER. I HAVE FOUND SEVERSDR CA030103012Fitting · cracked(CAN) APPROXIMATELY 8 INCH CRACK WHERE FLANGE IS WELDED TO PICCOLO TUBE AND 2 INCH CRACK IN PICCOLO TUBE ON OTHER SIDE OF INLET FITTING RESULTING IN BLEED AIR LEAK.SDR CA030103011Skin · cracked(CAN) TWO OF THE BALANCE WEIGHT ATTACHMENT SCREW HOLE HAD 1/2 INCH CRACKS STARTING FROM UNDER THE SCREW HEADS.SDR CA021220011Fitting · nicked(CAN) NICKS FOUND DURING INSPECTION. LOCATED ON UPPER LUGS OF WING SPAR CARRY THROUGH FITTINGS ON LT & RT SIDES OF MAIN & REAR STUB WING SPAR ASSY'S.SDR CA021220010Fitting · nicked(CAN) NICKS ON UPPER LUGS OF WING CARRY THROUGH FITTINGS ON FWD & REAR SPARS.SDR CA021220009Pin · corroded(CAN) CORROSION RESISTANT PINS WERE HARD TO REMOVE FROM THE BUSHINGS DUE TOO HEAVY CORROSION.SDR CA021220007Rib · worn(CAN) RIB EXTENSIONS WORN. WHEN FLAP IS FULLY RETRACTED THE RIB EXTENSIONS FRETTING ON THE FLAP TRACK AND FLAP TRACK RIVETS.SDR CA021218004Line · ruptured(CAN) AT A FLEX POINT NEAR THE UPPER FITTING OF THE LOWER BRAKE LINE RUPTERED ALLOWING THE BRAKE FLUID TO ESCAPE. UPON ARRIVAL AT CYXD ON FINAL FOR RUNWAY 16, THE GEAR WAS SELECTED DOWN. IMMEDIATELY TWO LIGHTS ILLUMINATED (POWER BRAKE LOW PRESS AND ANTISKID SDR CA021203003Motor · intermittent(CAN) FLAPS WILL NOT RETRACT COMPLETELY. INVESTIGATION REVEALED A SNAPPED COUPLING ON THE RT FLAPACTUATOR SHAFT AT THE GEARBOX. FURTHER INVESTIGATION REVEALED THE RT FLAP MOTOR WAS INTERMITENT. SUSPECT THE FLAP MOTOR BRAKE WAS NOT RELEASING DURING FLAP OPERASDR CA021204006Stator · broken(CAN) AFTER LANDING, WHILE TAXING THE A/C MADE A SUDDEN UNCOMMANDED RT TURN DUE TO A SEIZED RT WHEEL. MAINTENANCE PERSONAL DETERMINED THE BRAKE ASSY WAS JAMMED ON DUE TO A CRACKED STATOR PLATE. THE BRAKE ASSY WAS RETURNED FOR INVESTIGATION.SDR CA021122008Shaft · damaged(CAN) DAMAGE WAS FOUND ON THE AILERON TRIM CONTROL SHAFT MIDWAY BETWEEN THE TRIM WHEEL AND CHAIN GEAR. THIS DAMAGE WAS FOUND WHILE CARRYING OUT AN IN HOUSE CAMPAIGN (851-018) TO LOOK FOR THIS TYPE OF DAMAGE TO THE SHAFT. THE DAMAGE WAS CAUSED BY THE CLAMPING SSDR CA021121003Shaft · chafed(CAN) THE CLAMP SCREW ON THE FLIGHT DIRECTOR MODE SELECTOR CONNECTOR PLUG RUBBED AGAINST THE AILERON TRIM CONTROL SHAFT ABOUT 3 INCHES FROM THE AFT END OF THE SHAFT. THE 1/4 INCH SOLID STEEL SHAFT WAS WORN TO .238 INCH DIAMETER AT THIS CONTACT POINT. 3/8 INCHESDR 2002FA0001297Wire Harness · chafedOPERATOR NOTED NR 2 DIRECTIONAL GYRO CIRCUIT BREAKER POPPING. MAINTENANCE DETERMINED A WIRE BUNDLE ROUTED AROUND THE DATA TRANSFER UNIT (DTU) WAS CHAFING AGAINST THE OUTBOARD CONNECTOR PLUG ON THE DTU. ONE WIRE IN THE BUNDLE WAS FOUND SHORTED AGAINST THE CONNESDR CA021101011Wire · split(CAN) DURING A PHASE 5 INSPECTION, A 10 GAUGE WIRE WAS FOUND TO HAVE SPLIT OPEN EXPOSING 2 INCHES OF BARE WIRE BEHIND THE LT CIRCUIT BREAKER PANEL. THIS WIRE TIES THE LT AND RT CIRCUIT BREAKER PANELS AT CB58 AND CB120 RESPECTIVELY. THE MATERIAL SPEC ON THE WIRSDR B3OR20020020Bolt · brokenAFTER TAKEOFF, PILOT NOTICED NOISE IN NOSE AREA, WIND NOISE IN COCKPIT. CREW WAS ABLE TO SEE NOSE GEAR DOORS WERE OPEN AND STEADY. REDUCED SPEED AND LOWERED LANDING GEAR WITH NO PROBLEMS. DOORS REMAINED OPEN AND STEADY. A/C LANDED WITHOUT MISHAP. FOUND THATSDR CA021115004Door · separated(CAN) RT ENGINE ANTI-ICE VALVE REPLACED, INVESTIGATION SHOWS THAT INNER HALF OF LOWER COWLING FASTENERS NOT SECURED. AIRCRAFT DEPARTED YVR, CREW NOTICED A 'BANG' AND THEN A CONSTANT VIBRATION, GOING THROUGH 8,000 FT, CLIMBING OUT. CREW CONTINUED TO CLIMB THROSDR CA021001003Rib · worn(CAN) RIB EXTENSIONS ON FLAP ASSY'S ON BOTH LT & RT FLAPS WERE WORN BY THE RIVETS HOLDING THE FLAP TRACKS ON THE WING. THE WEAR WAS AS MUCH AS 50 PERCENT MATERIAL THICKNESS.THESE 4 RIB EXTENSIONS WERE REPLACED. SIMILAR WEAR ON THE INBOARD & OUTBOARD RIB EXTENSSDR CA021002001Bulkhead · worn(CAN) WHERE THE ELEVATOR TRIM CABLES PASS THROUGH THE CANTED BULKHEAD, THE RT CABLE WAS FOUND WEARING INTO THE LOWER CORNER OF THE HOLE & THE LT CABLE WAS JUST CLEAR BY ABOUT .020 INCH.SDR CA021001008Panel · corroded(CAN) FWD OUTBOARD CORNER OF BONDED DOUBLER. PANEL WAS BEING REPLACED DO TO OIL CANNING FROM DATE OF MANUFACTURE WHEN THE CORROSION WAS FOUND AT THE FWD OUTBOARD CORNER WHERE THE PANEL CONTACTS A MONEL DOUBLER SPLICE PLATE. THIS IS NOT AN AREA THAT CAN BE INSSDR CA021001007Bushing · corroded(CAN) DURING PHASE 5 INSPECTION CORROSION WAS NOTICED AROUND THE TRUNNION INNER PINS.AFTER MUCH DIFFICULTY THE PINS WERE REMOVED AND CORROSION WAS FOUND ON THE INSIDE OF THE BUSHINGS,SEIZING THE PINS. THE PINS ARE STACKED TO THE TRUNNION AND BUSHING WITH ROLL SDR CA020930005Rivet · broken(CAN) INLET COWLING HAD APPROXIMATELY 1/4 OF THE RIVET HEADS MISSING ON THREE CONSECUTIVE RIVETS, PLUS 1 RIVET HEAD LIFTING. LOCATION WAS THE 3RD ROW OF RIVETS FROM THE FRONT OF THE INLET, AT THE 2 O'CLOCK POSITION.SDR CA020918012Engine · leaking(CAN) DURING THE DISASSEMBLY OF THE ENGINE FOR HOT SECTION INSPECTION, AN OIL LEAK WAS DISCOVERED IN THE AREA OF THE 3.5 BEARING.SDR 2002FA0001063Brake Assy · lockedR/H BRAKE ASSY LOCKED UP UPON LANDING CAUSING DAMAGE TO INBOARD WHEEL HALF.SDR AUS20020927Rib · cracked(AUS) WING RIB WEB CRACKED DUE TO FLEXING CAUSED BY AILERON PULLEYBRACKET AND FLAP PULLEY BRACKET ATTACHED TO RIB.SDR AUS20020926Cable · frayed(AUS) TRAILING EDGE FLAP CABLES (14OFF) FRAYED. FLAP CABLE PART NUMBERS ARE:- PNO 6565007-102-1CR, PNO 6565007-100-1CR, PNO 6565007-114CR, PNO 6565007-112CR, PNO 6565007-401, PNO6565007-90CR, PNO 5565150-16CR (2OFF), PNO 5565150-3CR(2OFF), PNO 5565150-2CR, PNOSDR 2002FA0000962Motor · failedON DECENT, THE COPILOT DETECTED AN ODOR THAT APPEARED TO BE ELECTRICAL IN ORIGIN. THE CHECKLIST WAS EXECUTED AND THE ODOR WAS ELIMINATED. MAINTENANCE FOUND AND REPLACED THE INOP BLOWER FAN AND RETURNED THE AIRCRAFT BACK TO SERVICE. TBO FOR THIS PART IS 350SDR GVR2002F00000Seat Back · crackedUPPER CHAIR BASE ASSEMBLY CRACKED AT CHAIR BACK ATTACH POINTS. STRESS ON CHAIR BACK AND METAL FATIGUE PROBABLE CAUSE. CHAIR WAS REPAIRED IAW STC STRUCTURAL SEAT REPAIR.SDR CA020711002Door Frame · worn(CAN) OUTBOARD DOOR SKIN HAS WORN THE DOOR FRAME LINTEL AT THE RADIUS INTO THE DOOR OPENING AS MUCH AS 50 PERCENT MATERIAL THICKNESS.SDR AUS20020679Retainer · separated(AUS) LANDING GEAR SELECTOR CIRCLIP (RETAINER) DISLOCATED.SDR 2002FA0000855Line · chafedFRESH AIR DUCT IN TAILCONE FOUND CHAFING AGAINST SPEED BRAKE CONTROL LINES.SDR CNQ2002F00002Duct · chafedFRESH AIR DUCT IN TAILCONE FOUND CHAFFING AGAINST SPEED BROKE CONTROL LINES. CHAFED THROUGH CREATING SEVERE LEAK.SDR CNQ2002F00000Line · chafedTHE ORANGE FRESH AIR DUCT IN THE TAILCONE IS CHAFING AGAINST THE SPEED BRAKE LINES. THIS RESULTED IN A FAILURE IN THE SPEED BRAKE LINE. THE CREW AND PASSENGERS OF THE AIRCRAFT REPORTED A HYD FLUID MIST COMING OUT OF THE WEMACS IN THE CABIN. REPLACED DUCT ASDR FUK2002F00000Thermoswitch · wrong partLOW TEMPERATURE SWITCH (PN M1060045144) WAS INSTALLED IN PLACE OF CORRECT HI TEMPERATURE SWITCH(PN M1165155144) AT THE TIME OF MANUFACTURE, CAUSING HEAT SYSTEM TO NOT FUNCTION AT ALL. HIGH AND LOW TEMPERATURE SWITCHES ARE IDENTICAL IN APPEARANCE. MFG SHOULD SDR CA020606014Stator · cracked(CAN) TCN = 588 AFTER DISASSEMBLY IT WAS FOUND THAT ONE STATOR DISC WAS CRACKED AND THE SECOND WAS BROKENCOMPLETELY THROUGH AND SEPARATED APPROX 3/8 INCH. DURING NDT INSPECTION OF THE TORQUE PLATE IT WAS FOUND TO HAVE SEVERAL SMALL CRACKS EMANATING FROM THE RSDR CA020606013Stator · cracked(CAN) TCN = 584 AFTER DISASSEMBLY OF THE BRAKE UNIT IT WAS FOUND THAT THE STATOR DISC'S WERE CRACKED. DURING NDT INSPECTION OF THE TORQUE PLATE IT WAS FOUND THAT THERE WERE SEVERAL SMALL CRACKS EMANATING FROM THE RIVET HOLES.SDR CA020606010Stator · cracked(CAN) AFTER DISASSEMBLING THE BRAKE UNIT, IT WAS FOUND THAT THE STATORS WERE VISUALLY CRACKED.AFTER NDT INSPECTION IT WAS FOUND THAT THE TORQUE PLATE HAD SEVERAL CRACKS GENERATING FROM THE RIVET HOLES.SDR CA020524001Duct · disconnected(CAN) AIRCRAFT AT 28,000 FT HAD LOSS OF CABIN PRESSURE CONTROL. AIRCRAFT EXECUTED EMERGENCY DESCENT TO 10,000 FT PROCEEDING TO DESTINATION WITHOUT FURTHER INCIDENT. MAINTENANCE INVESTIGATION REVEALED ACM FLEX DUCT HAD UNCOUPLED FROM MATING TUBE, SUSPECTED CAUSDR AUS20020456Starter Gen · seized(AUS) LT ENGINE STARTER-GENERATOR SEIZED. SUSPECT CAUSED BY FAILURE OF THE FAN END BEARING. EVIDENCE OF POLING.SDR 2002FA0000635Stud · brokenDURING SCHEDULED REPLACEMENT OF THE MLG STRUT CYLINDERS, THE HYD ACTUATOR ATTACH STUD WAS BEING REMOVED FOR RE-USE. UPON APPLYING A TENSION LOAD ON THE STUD TO REMOVE IT, PER MM, THE STUD SEPARATED ALONG THE THREADS WELL BELOW THE MAX TORQUE LIMIT, THE CRACK BSDR 2002FA0000626Bolt · wrong partA LOOSE GENERATOR GROUND CABLE BOLT WAS DISCOVERED WHILE TROUBLESHOOTING AN AMMETER SPLIT BETWEEN THE LEFT AND RIGHT ENGINE GENERATORS. AN AN610A BOLT WAS FOUND INSTALLED INSTEAD OF THE CORRECT AN6-6A BOLT. THE BOLT WAS TOO LONG AND TORQUE COULD BE REACHED.SDR 2002FA0000647Seat Back · crackedUPPER SEAT BASE ASSEMBLY CRACKED AT SEAT BACK ATTACH POINTS. STRESS ON SEAT BACK AND METAL FATIGUE PROBABLE CAUSE. SEAT WAS REPAIRED.SDR CA020419001Stator · cracked(CAN) DISASSEMBLED BRAKE UNIT AFTER 488 LANDINGS FOUND 1 STATOR DISC CRACKED ALMOST ALL THE WAY THROUGH, AND 2ND STATOR WITH SMALLER CRACKS.SDR CA020416005Connector · damaged(CAN) PILOTS REPORTED THAT THEY COULD NOT START EITHER ENGINE USING EXTERNAL POWER BUT ENGINES STARTED FINE USING BATTERY POWER. MAIN POWER CABLES AND GROUND CABLE FOUND LOOSE AT GPU CONNECTOR. BOTH THE CONNECTOR STUDS AND THE POWER CABLE ENDS BURNED AND MELTESDR CA020416003Lens · missing(CAN) ON WALKAROUND AFTER A FLIGHT A CREW MEMBER NOTICED THE RT NAV LIGHT LENS COVER MISSING. REPLACED WITH NEW AND CONTINUED FLIGHT TO HOME BASE.SDR 2002FA0000636Battery Pack · misrepairedBATTERY HAS BEEN REPAIRED WITH NON-PMAD CELLS.SDR WC72002F00000Valve · stuckDURING A PREFLIGHT INSPECTION, WHILE DRAINING THE FUEL SUMP ON THE RIGHT WITN, THE DARIN VALVE BECAME STUCK IN THE OPEN POSITION. THE TOPPED OF WING WAS PROFUSELY DRAINING ON THE HANGER FLOOR. AFTER THE AIRCRAFT WAS DEFUELED AND THE DRAIN VALVE REMOVED. IT SDR CA020327008Stator · cracked(CAN) WHILE CARRYING OUT A COMPANY DIRECTED INSPECTION, NR 1 STATOR DISC WAS FOUND CRACKED THROUGH, THE OTHER WAS CRACKED IN SEVERAL PLACES.
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