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 = 'A109S' 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 = 'A109S' 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 S6GA202405140133Landing Gear · false indicationWHEN SELECTING LANDING GEAR DOWN, THE L/H MAIN LANDING DID NOT SHOW DOWN AND LOCKED.SDR S6GA202404080113Skin · crackedA CRACK WAS DISCOVERED IN THE TAIL BOOM SKIN JUST AFT OF THE RH ELEVATOR TORQUE TUBE MOUNTING HOLE. APPROXIMATELY 2.5" LONG AT APPROXIMATE STATION 8540. REPAIR IS LISTED IN LEONARDO ASRP AND COMPLIED WITH ASRP CH. 3C-A-53-51-02-05A-664A-D.SDR 2024F00045Dampener · shearedAFTER COMPLETION OF A HOIST AT ~0159 AND IN CRUISE FLIGHT BACK TO THE AIRPORT I NOTICED A SLIGHT CHANGE IN THE AIRCRAFT'S NORMAL VIBRATIONS. I SLOWED THE AIRCRAFT TO SEE IF THERE WAS ANY CHANGE IN THE VIBRATION, AND THERE DIDN'T SEEM TO BE. AT THE TIME WE ALSOSDR 2023FA0000504Torque Tube · crackedDURING A SCHEDULED INSPECTION THE ELEVATOR TORQUE TUBE WAS FOUND CRACKED APPROXIMATELY 90% THROUGH. HAD IT CRACKED COMPLETELY THE ELEVATOR COULD HAVE DEPARTED THE LEFT SIDE OF THE TAIL AND POSSIBLY HIT THE TAIL ROTOR.SDR 2021F00029Hydraulic System · low pressureON APPROACH, THE NORMAL UTILITY PRESSURE WAS TOO LOW TO FULLY EXTEND AND LOCK THE LANDING GEAR. THE PILOT THEN USED THE EMERGENCY HYDRAULIC SYSTEM TO EXTEND AND LOCK THE LANDING GEAR WITHOUT AN ISSUE.SDR S6G2021F00000Skin · crackedA CRACK WAS DISCOVERED IN THE SKIN, LEFT SIDE OF AIRCRAFT AT THE TOP SIDE OF THE BAGGAGE DOOR FRAME EXTENDING UP APPROXIMATELY 5 INCHES AS STATION 5741.00. THE REPAIR IS LISTED IN THE SRM AND WILL COMPLY WITH SRM 3C-A-53-42-01-02A-664A-D, LT SKIN FUSELAGE STASDR S6GA2019FA0000141Regulator Valve · failedREPORTED BY PILOT: ON FINAL FOR THE RNAV 23 INTO KRZN, I GOT A NR 2 ENG OIL HOT LIGHT. INITIAL COMPARISON OF THE ACTUAL OIL TEMP SHOWED 123, AND STILL IN THE GREEN. THAT LASTED FOR ABOUT 5 SECONDS WHEN THE TEMP STARTED TO CLIMB RAPIDLY TO 127 BEFORE I COULD PLSDR CA160128008Blade · cracked(CAN) DURING INSPECTION OF THE TAIL ROTOR BLADE A CRACK WAS FOUND ON THE TRAILING SIDE BELOW THE BLADE BOLT. THE PAINT WAS REMOVED TO CONFIRM THE BLADE WAS CRACKED. THE BLADE HAS BEEN REMOVED AND SENT TO THE MFG FOR ANALYSIS.SDR CA150910006Turbine Blades · fractured(CAN) ON SHUTDOWN CREW NOTICED VIBRATION AND I HIGH PITCH SOUND COMING FROM THE RT NR 2 ENGINE. MAINTENANCE INSPECTED THE AREA AND FOUND THAT 1 OF THE TURBINE BLADES FROM THE POWER SECTION HAD FRACTURED ROUGHLY .7500 PERCENT OF THE WAY UP THE BLADE, AND WAS ESDR 2014FA0000664Crossbeam · chafedDURING 50 HR, 30 DAY VISUAL INSPECTION, TECH NOTICED RESIDUE ON CROSSMEMBER UNDER NR 2 ENGINE DECK. ON FURTHER INSPECTION, FOUND WEAR HOLE IN NR 2 ENGINE DECK FOUND TO BE CHAFED THROUGH BY ENGINE FIRE SUPPRESSANT DISTRIBUTION TUBE.SDR CA141202010Engine · malfunctioned(CAN) ON DESCENT, THE PILOT WAS UNABLE TO REDUCE THE RT ENGINE DOWN TO IDLE. THE SITUATION WAS CONTROLLED BY SLOWING THE HELICOPTER RATE OF DESCENT. THE PILOT LANDED THE HELICOPTER SAFELY. THE TROUBLESHOOTING REVEALED NO FAULT CODE, AND THE MECHANIC WAS UNABLSDR 2014102000162Engine · malfunctionedAFTER CONDUCTING 133D HOIST OFFSHORE AT NIGHT. WHILE ENROUTE NR 1 ECU, ENGINE CONTROL UNIT, FAIL WARNING LIGHT ILLUMINATED. NR 1 ENGINE REVERTED TO MANUAL MODE. PILOT SET GOVERNOR CONTROL SWITCH TO MANUAL, AND TRIMMED THE ENGINE BELOW THE NR 1 ENGINE. MANUSDR 2014FA0000461Bolt · wornPILOT REPORTED A VERTICAL VIBRATION. INSPECTION REVEALED THE BOLT WHICH ATTACHES THE MAIN ROTOR PITCH LINK UPPER ROD END TO THE MAIN ROTOR HEAD PITCH LEVER ASSEMBLY WAS SEVERELY WORN. FURTHER INSPECTION REVEALED THE LEVER ASSEMBLY BUSHINGS WERE ALSO WORN FROSDR CA140416001Latch · worn(CAN) DURING APPROACH THE CABIN LT DOOR OPENED IN FLIGHT. THE CREW SLOWED THE ACFT DOWN AND CONTINUED WITH THE APPROACH AND LANDED SAFELY. MAINTENANCE REMOVED AND INSPECTED THE DOOR, THE DOOR SAFETY LATCHING MECHANISM WAS REPLACED, THE DOOR WAS ALSO RE-ADJUSSDR CA121003017Fuel Tank · chafed(CAN) FUEL WAS NOTICED UNDERNEATH THE ACFT. THE ACFT WAS GROUNDED AND INSPECTED FOR LOCATION OF FUEL LEAK. AFTER REMOVING THE 2 FORWARD TANKS THE AFT TANK WAS FOUND WITH CHAFING MARKS ON LOWER PORTION CAUSED BY ANCHOR NUTS, USED TO SECURE THE FORWARD PANEL ISDR CA111129005Wire · chafed(CAN) POSITION LIGHT CB POPPED, DAY FLIGHT, RESET DID NOT WORK. FLIGHT ABORTED, INSPECTION REVEALED SEVERE CHAFFING OF WIRES INSIDE THE WINGLET & HORIZONTAL STABILIZER CAUSED BY INADEQUATE SHEATHING & TIE DOWN CAUSING WIRES TO RUB ON THE WINGLET STRUCTURE ON SDR CA110803016Hub · seizedDURING INSP, TAIL ROTOR BLADE BOLTS REQUIRED A ARBOR PRESS TO BE REMOVED. UPON INSPECTION OF BLADE BOLT IT WAS FOUND TO HAVE BEEN WET ASSEMBLED WITH DRY MOLY LUBRICATE, ADDITIONALLY WHEN THE BLADE WAS TO BE REMOVED FOR INSP, IT REQUIRED EXCESSIVE FORCE TO REMSDR DT1R200800001Lever · damagedOPENED THE ACCESS PANEL UNDER THE CO-PILOT'S SEAT, FOUND THE YAW TRIM LEVER (PN 109-0020-47-7 NSN) DETACHED FROM THE YAW TRIM MOTOR SHAFT. NO DAMAGE NOTED TO THE MOTOR SHAFT. THE LEVER WAS INTACT BUT DAMAGED AT THE POINT WHERE IT CONTACTS THE SHAFT, BUT HAD
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