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 = 'AW109SP' 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 = 'AW109SP' 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 2026FA0000821Regulator Valve · faultedHELICOPTER N57HR EXPERIENCED NR 1 OIL HOT LIGHT IN FLIGHT. PER RFM IT SAYS TO ACHIEVE SAFE OEI FLIGHT AND SHUT DOWN ENGINE USING EMERGENCY SHUTDOWN IN AN EMERGENCY. 3-73 AND 3-20 IN RFM. WHICH IS WHAT THE CREW DID.SDR 2026FA0000528Pressure Switch · intermittentTHE MLG LEVER WAS IN UP POSITION, BUT THREE GREEN LIGHTS FOR THE GEAR (THE GEAR WAS DOWN) WITH ONE RED LIGHT SHOWING GEAR TRANSITION. MY AIRSPEED HAD EXCEEDED THE 140KT LIMIT FOR THE GEAR TO BE DOWN WHICH CAUSED THE AIRSPEED AUDIO. I ALSO NOTICED AN AMBER MASTSDR 2026FA0000348Pressure Sensor · malfunctionedPILOT REPORTED HIGH OIL PRESSURE, SECURED THE ENGINE IN FLIGHT AND PREFORMED A PRECAUTIONARY LANDING.SDR 2025FA0000770Life Vest · misconfiguredDURING A 6-MONTH GVI OF LIFE VESTS INSTALLED IN OUR AIRCRAFT, AN AMT DECIDED TO LOOK A LITTLE FURTHER THAN THE REQUIRED INSPECTION. FOUND A CO2 CARTRIDGE NOT SECURED AT ALL. THIS LED TO AN EXTENSIVE OF ALL SWITLIK IFE VESTS IN OUR FLEET AND STOCK INVENTORY. THSDR 2024FA0000833Elec Connector · burnedBURNING PLASTIC SMELL IN COCKPIT METHOD: NOTES: AFTER STARTUP, THE SMELL OF BURNING PLASTIC FILLED THE COCKPIT. REMOVED AND REPLACED THE MAIN BATTERY CONNECTOR AND LEADS IAW LEO MM 24-31-01. GROUND LUG ON CONNECTOR BURNED. SUSPECT INCORRECT ASSEMBLY FROM OEM.SDR 2023FA0000763Bypass Valve · faultedIN FLIGHT ENGINE #2 TEMP CAUTION ILLUMINATED ALONG WITH RISING TEMPERATURE INDICATION TO 131 CELSIUS. THEN, #2 PRESSURE WARNING ILLUMINATED WITH ERRATICALLY CHANGING PRESSURE INDICATION. SHUTDOWN #2 ENGINE AND LANDED. MAX CONTINUOUS OIL TEMPERATURE IS 128.5 C.SDR 2023FA0000426Bolt · groovedIT WAS REPORTED AS THE AIRCRAFT WAS COMING IN FOR A 200-HOUR INSPECTION. A SLIGHT BUMP COULD BE FELT IN FLIGHT; DURING THE INSPECTION, ALL PC LINK ROD ENDS, AND BOLTS WERE INSPECTED, AND THE BLUE UPPER BOLT WAS FOUND TO HAVE A STEP WORN INTO IT, THE BOLT WAS RSDR 2023F00015Coupler · debonded#2 DRIVE SHAFT COUPLER APPEARS TO HAVE BECOME DEBONDED, AND THE ANTI-SLIPPAGE PIN CANNOT ROTATE, INDICATING A POTENTIAL SLIPPAGE.SDR 2022FA0000435Antenna Lead · brokenNUMBER 1 GPS FAILED. INSPECTION REVEALED THE INTERNAL CONDUCTOR OF THE COAX ANTENNA CABLE FAILED AT ANTENNA CONNECTION. THIS IS A RECURRING CONDITION THAT HAPPENS EVERY 75-150 FH. ANTENNAS (GPS 1 & 2) ARE LOCATED ON THE TOP OF THE VERTICAL STABILIZER. THIS ARESDR 2022F00248Damper · crackedDURING PREFLIGHT AMT FOUND A CRACK AT THE INBOARD UPPER LUG OF ONE OF THE MAIN ROTOR DAMPERS. THIS WAS DETECTED VISUALLY WITH NO ENHANCEMENTS. DEFECTIVE DAMPER WAS REMOVED AND A SERVICEABLE DAMPER WAS INSTALLED.SDR 8LFA2021081900237Flow Divider · looseWE HAD JUST COMPLETING OEI TRAINING WITH THE TRAINING MODE ON THE NUMBER ONE ENGINE. AFTER COMPLETING OUR OEI TRAINING, ROGER PLACED THE TRAINING MODE BACK TO CENTER POSITION AND ALL INDICATIONS ON THE NUMBER ONE ENGINE WERE NORMAL. I PLACE THE RPM SWITCH BACSDR 2021F00117Gps · disengagedON 05/01/21 ON A EARLY MORNING NIGHT IFR RNAV 08 APPROACH TO ASTORIA AIRPORT (KAST). HELICOPTER HAD FAILURE INDICATIONS OF BOTH GPS SYSTEMS, AT SIMULTANEOUS MOMENT, CAUSING GPS 1 AND 2 FAILURE WARNINGS, COMBINED WITH TAWS FAILURE MESSAGE, DISCONNECT OF AFCS, SDR 2019FA0000414Trunnion · scoredPILOT REPORTED A MAIN ROTOR VIBRATION. UPON TRACK AND BALANCE OF THE MAIN ROTOR IT WAS DISCOVERED THAT THE VIBRATION WAS FROM THE TAIL ROTOR. THIS WAS NOT A COMMON OCCURRENCE AS THE TAIL ROTOR UNDERGOES A DETAILED INSPECTION EVERY 200-HOURS. IT IS VERY UNCOMMOSDR CA190528004Reduction Gb · cracked(CAN) PRIOR TO AIRCRAFT DEPARTING THE CREW NOTICED AN EXCESSIVE AMOUNT OF OIL ON THE ENGINE DECK. MAINTENANCE ACCOMPLISHED MULTIPLE SEAL REPLACEMENTS AND THE SOURCE OF THE OIL LEAK COULD NOT BE IDENTIFIED. THE ENGINE WAS SUBSEQUENTLY REMOVED AND SENT TO P&W FOSDR 2018FA0000434Relay · failedCUSTOMER REPORTED THAT THE CREW ALERTING SYSTEM (CAS) MESSAGE ECU1FAIL ILLUMINATES ON THE RELATED DISPLAY AND THAT THE ENGINE CONTROL (ECU) REVERTS THE ENGINE FROM ECU CONTROL TO THE MANUAL MODE OF CONTROL. AFTER EXTENSIVE TROUBLE SHOOTING AND RECOMMENDATIONSSDR 2018FA0000371Wire · damagedENGINE POSITION NR 1, CUSTOMER REPORTED THAT THE CREW ALERTING SYSTEM (CAS) MESSAGE "ECU1 FAIL" ILLUMINATES ON THE RELATED DISPLAY AND THAT THE ENGINE CONTROL (ECU) REVERTS THE ENGINE FROM ECU CONTROL TO THE MANUAL MODE OF CONTROL. AFTER EXTENSIVE TROUBLE SHOOSDR 2018FA0000433Bushing · looseDURING A WALK AROUND INSPECTION THE TECHNICIAN NOTICED THAT THE ROCKER ARM ASSEMBLY ON THE TAIL ROTOR HUB ASSEMBLY WAS VERY LOOSE. FURTHER INVESTIGATION REVEALED THAT THE BEARING HAD BECOME LOOSE IN THE ROCKER ARM ASSEMBLY. IN THIS APPLICATION THE BEARING ISSDR 2018FA0000380Rocker · looseDURING A WALK AROUND INSPECTION THE TECHNICIAN NOTICED THAT THE ROCKER ARM ASSEMBLY ON THE TAIL ROTOR HUB ASSEMBLY WAS VERY LOOSE. FURTHER INVESTIGATION REVILED THAT THE BEARING HAD BECOME LOOSE IN THE ROCKER ARM ASSEMBLY. IN THIS APPLICATION THE BEARING IS ROSDR I7LA2018081800125Oil Cooler · wornPILOT NOTED A SLIGHT INCREASE, WITHING LIMITS IN THE NR 1 ENGINE OIL TEMP DURING FLIGHT. DURING FINAL APPROACH, THE OIL TEMP STARTING INCREASING, THE PILOT ABORTED THE APPROACH, SECURED THE NR 1 ENGINE IAW THE RFM AND SUCCESSFULLY COMPLETED A RUN ON LANDINGSDR BV0A2018031900036Crossbeam · crackedDURING AN INSPECTION PER SERVICE BULLETIN 109SP-118 A CRACK WAS OBSERVED IN P/N 109-0330-17.SDR I7LA201705110103Attach Fitting · crackedDURING A 1200 HOUR INSPECTION, A CRACK WAS FOUND IN THE LOWER LT TAIL BOOM ATTACH FITTING. AFTER REMOVING THE TAIL BOOM, FOUND A CRACK IN THE BULKHEAD & FRAME ASSEMBLY.SDR I7LA2015F00098Bracket · crackedDURING A 1,600-HOUR INSPECTION A TWO INCH CRACK WAS FOUND IN THE LT LONGERON BRACKET. THE CRACKED LONGERON BRACKET IS LOCATED AT THE AFT LOWER LT FUSELAGE TO TAIL BOOM ATTACH POINT. THE SUBJECT PART IS 1 OF 4 POINTS THAT ATTACH THE TAIL BOOM TO THE FUSELAGE. SDR CA141105001Engine · making metal(CAN) DURING FLIGHT, THE CREW EXPERIENCED AN ENGINE NR 2 CHIP DETECTOR MESSAGE BEING DISPLAYED IN THE COCKPIT. THE PILOT THEN DECIDED TO DIVERT WHERE AN UNEVENTFUL LANDING WAS MADE. A VISUAL INSPECTION ON THE ENGINE NR 2 SHOWED A LARGE AMOUNT OF DEBRIS.SDR 2014FA0000562Blade · crackedDURING A DAILY INSPECTION , A ONE INCH CRACK ON ONE OF THE TWO TAIL ROTOR BLADES WAS DETECTED. INITAL INSPECTION WAS VISUAL A 10X GLASS WAS USED TO VARIFY. AIRCRAFT WAS REMOVED FROM SERVICE AND WILL RETURN TO SERVICE AFTER A SERVICEABLE TAIL ROTOR BLADE IS ISDR CA140710007Control Rod · worn(CAN) DURING INSPECTION, THE ECS RETURN LINE HAD COME LOSE IN FLIGHT, AND STARTED TO WEAR A HOLE IN TO ONE OF THE MAIN ROTOR SERVO CONTROL RODS. THE ECS LINE IS A 2" ORANGE SCAT HOSE CONNECTED TO THE ECS SYS WITH A STANDARD CLAMP. THE CLAMP WAS INSPECTED AND
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