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 = '369HS' 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 = '369HS' 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 2025FA0000782Filler · corrodedAIRCRAFT REG: N396HA, AIRCRAFT MSN 1488. BULK CARGO DOOR ENTRANCE CUTOUT LOWER EDGE FILLER FOUND WITH 4 OFF LOCATION CORRODED. MEASURING 30X15MM, 25X10MM,20X20MM AND 10X10MM.SDR 2011FA0000051Spar · crackedON 10/1/10 ACFT EXPERIENCED AN INFLIGHT FAILURE AND SUBSEQUENT SEPARATION OF THE OTBD SECTION OF THE HORIZ STABILIZER DUE TO A CRACK IN THE SPAR AT STA 42.5. THE CRACKING OF THE SPAR APPEARS TO HAVE ALLOWED THE FLEXING OF THE STABILIZER AND SUBESEQUENT FAILURSDR 2010FA0001107Seal · missingON 5/7/2010, INSTALLED A NEW ANTI-ICE VALVE PN 23053192 AT ACTT 14805.1. DURING A ROUTINE 100 HR INSP OF THE ACFT ON 9/24/2010 AT ACTT 14904.8. REMOVED AND INSPECTED THE VALVE AND DISCOVERED THAT THE POPPET SEAT SEAL WAS MISSING FROM THE POPPET. POPPET SEAT SDR 2010FA0000822Anti-Ice Valve · unsecureTHE INSTALLED ANTI-ICE VALVE (PN 23053192AL) POPPET SEAT RETAINING SCREW WAS NOT PROPERLY STAKED DURING THE MFG PROCESS AND AS A RESULT THE SCREW WAS INGESTED INTO THE TURBINE SECTION OF THE ENGINE AND DAMAGED THE NR 1, 2, 3 WHEELS, THE 1ST, 2ND AND 4TH STAGE SDR CA070201008Fcu · failed(CAN) AFTER THE AIRCRAFT WAS STARTED, THE PILOT DECIDED TO DO A WALK AROUND THE AIRCRAFT. FUEL WAS NOTICED FLOWING FROM THE ENGINE BAY TO THE GROUND. FURTHER INVESTIGATION REVEALED A MASSIVE FUEL LEAK AT THE FUEL CONTROL THROTTLE LEVER SHAFT SEAL. FUEL WAS FLOSDR CA020719003Bearing · failed(CAN) CHIP LIGHT CAME ON AT START UP. ENGINE CHIP PLUGS WERE CLEANED ONLY TO COME ON AGAIN ON THE NEXT START UP. THE ENGINE WAS IMMEDIATELY PULLED AND SENT TO AN OVERHAUL SHOP. THEY DISCOVERED THAT THE PROBLEM WAS THE NR 2 BEARING RACE WAS BEING WARN AWAY.SDR AUS20020115Bearing · cracked(AUS) MAIN TRANSMISSION BEARING INNER RACE SPLIT WITH HEAVY BRINNELLING EVIDENT. METAL CONTAMINATION OF TRANSMISSION OIL SYSTEM.SDR AUS20011238Blade · failed(AUS) SECOND STAGE COMPRESSOR BLADES (2OFF) FAILED). MAJOR DOWNSTREAM DAMAGE. SEVERAL OTHER SECOND STAGE ROTOR BLADES WERE FOUND TO BECRACKED FROM THE TRAILING EDGE.SDR AUS20010925Shaft · distorted(AUS) TAIL ROTOR GEARBOX OUTPUT SHAFT BEARINGS BREAKING UP AND SHAFTRUNOUT EXCESSIVE. SHAFT RUNOUT APPROXIMATELY 0.457MM (0.018IN). MAXIMUM RUNOUT 0.0254MM (0.001IN).SDR CA010621026Pulley · failed(CAN) OIL COOLER PULLEY IS MADE UP OF A SPLINE BELT PULLEY WITH A METAL RING THAT IS "STAKED" ONTO THE PULLEY. THE RING WAS FOUND AROUND THE ENGINE OUTPUT DRIVE SHAFT AFTER GROUND RUNNING THE A/C. A NEW PART WAS USED TO COMPARE THE STAKING MARKS ON THE OLD PULSDR 20000412SH028Probe · damagedTHE NYLON INSERT IN THE TEMPERATURE PROBE LET GO RESULTING IN FLUCTUATION AND DROPPING OIL PRESSURE AND A LOSS OF OIL. THE ENGINE HAD TO BE TORN DOWN FOR INSPECTION. MAIN DAMAGE SEEMS TO BE THE ENGINE''S NR 8 BEARING WHICH WAS DESTROYED. (X)SDR 99ZZZX1473Valve · brokenDURING TAKEOFF, ENGINE OIL PRESSURE DROPPED BELOW MINIMUMS. THROTTLE WAS CLOSED AND AIRCRAFT WAS AUTOROTATED. CHECK VALVE NIPPLE HAD SEVERED AT OIL COOLER INLET.SDR 98ZZZX3339Blade · crackedHELICOPTER INBOUND FOR LANDING WHEN PILOT NOTICED VIBRATION, MADE NORMAL LANDING. MAINT EXAM OF ROTOR SYS FOUND YELLOW BLADE CRACKED FROM TRAILING EDGE OF BLADE, BOTH TOP AND BOTTOM TO MAIN SPAR. CRACK LOCATED AT BLADE STA 71 OR 19.3750 INCHES FROM END OF ADSDR CA980804009Fan · wrong part(CAN) IN SHOP FOR REPAIR, LEAR SIEGLER STARTER/GENERATOR HAD AN APC FAN P/N 1503G1107 INSTEAD OF THE LEAR SIEGLER FAN P/N 23032-1481.SDR 98ZZZX1272Case Half · erodedA SLIGHT RUB WAS HEARD IN THE COMPRESSOR WHEN THE N1 WAS ROTATED. UPON CASE HALF REMOVAL FOR INSPECTION, SEVERE VANE EROSION WAS FOUND. THE CHORD OF ONE VANE WAS SO THIN AS TO CAUSE THE VANE TO BEND AND RUB ON THE COMPRESSOR ROTOR. SUBMITTER SUSPECTS CASE HSDR 97ZZZX4860Door · departedDURING FLIGHT, THE RIGHT MAIN DOOR OPENED, THEN DEPARTED THE AIRCRAFT. THE DOOR HINGES WERE MODIFIED BY THE INSTALLATION OF QUICK REMOVAL DOOR HINGES STC SH2530 NM. DISCOVERED DURING INSPECTION THAT THE LATCHING FEATURE USED WAS NOT PROPERLY ENGAGED ALLOWINGSDR 97ZZZX3993Blade · crackedDURING POST-FLIGHT INSPECTION AFTER APPROXIMATELY A 2-HOUR FLIGHT, PILOT NOTICED PINHOLE IN T/R BLADE LEADING EDGE WITH APPROXIMATELY 1 INCH CRACKS DOWN BOTH SIDES OF BLADES. THESE BLADES HAD NEW DESIGN ABRASION STRIPS INSTALLED IAW AD 95-03-11 ON 1-2-96 AT PSDR 97ZZZX2835Bearing · crackedOVERRUNNING CLUTCH BEARING OUTER RACE IS CRACKED.SDR 97ZZZX1669Bearing · failedTAIL ROTOR PITCH CHANGE LINKS WERE INSTALLED AT 13,300.8 AIRCRAFT HOURS. AT 13,432 AIRCRAFT HOURS, ONE PITCH CHANGE LINK FAILED AT ONE END. THE BEARING APPEARS TO HAVE BEEN EXCESSIVELY OVER ROLL STAKED UPON INSTALLATION INTO THE LINK BEARING HOUSING. FAILURSDR AU970163Blade · cracked(AUS) TAIL ROTOR BLADE SKIN CRACKED IN AREA JUST INBOARD OF THE LEADING EDGE PROTECTIVE STRIP RUNNING CHORDWISE TOWARDS THE TRAILING EDGE - CRACK LENGTH APPROXIMATELY 25.4MM (1IN)SDR AU970120Blade · cracked(AUS) TAIL ROTOR BLADE SKIN CRACKED IN AREA INBOARD OF THE LEADING EDGE PROTECTION STRIP RUNNING CHORDWISE FROM THE LEADING EDGE TOWARDS THE TRAILING EDGE - CRACK LENGTH APPROXIMATELY 25.4MM (1IN)SDR 97ZZZX200Swashplate · bushing detachedVIBRATION FELT THROUGH T/R PEDALS, SPECIFICALLY LEFT PEDALS. UPON INSPECTION, BUSHING AT INBOARD END OF T/R SWASHPLATE T-HEAD HAD COME OUT, SLID INBOARD ON T/R OUTPUT SHAFT AND DAMAGED T/R OUTPUT SHAFT SEAL.SDR 96ZZZX4103Pulley Assy · bottom outON SOME MAIN ROTOR TRANSMISSION ASSEMBLIES, THE SPLINES ON THE PULLEY ASSEMBLY DRIVER BOTTOM OUT ON THE SPLINES OF THE GEARSHAFT INPUT BEVEL PINION (369A5107-21). THIS RESULTS IN A GAP BETWEEN THE GUARD (369H5657) AND THE SPACER (369A5165). OPERATING WITH THSDR 96ZZZX3839Link Assy · bushing looseWHILE C/W WITH VISUAL INSPECTION PER AD 93-03-13 (R/D 3-21-95) TWO BLADE ATTACHMENT BUSHINGS WERE FOUND LOOSE IN ONE LEAD/LAG LINK ASSY. M/R HUB TO BE RETURNED TO A MDHS SERVICE CENTER FOR REPLACEMENT OF THIS LINK ASSY WITH A SERVICEABLE PART.SDR 96ZZZX3836Pinion Shaft · wornMAIN ROTOR TRANSMISSION LOCKNUT LOST TORQUE AND ALLOWED BEARINGS TO FRET ON SHAFT WEARING THE SHAFT UNDER THE BEARINGS AND ACCESSORY DRIVE GEAR. THIS ALLOWED THE DRIVE PIN TO SHEAR AND WHENEVER TORQUE WAS BELOW 6 PERCENT ENGINE TORQUE, THE OIL PUMP AND ROTOR SDR AU960192Housing · corroded(AUS) STABILIZER STRUT DAMPER SHAFT PULLED FROM FITTING DURING HEAVY VIBRATION FOLLOWING TAIL ROTOR DRIVE SHAFT FAILURE (MDR 96/0191) - FITTING EXHIBITED SIGNS OF SEVERE INTERGRANNULAR CORROSION - AIRCRAFT OPERATES IN A SALT LADEN ENVIRONMENTSDR AU960191Drive Shaft · sheared(AUS) TAIL ROTOR DRIVE SHAFT SHEARED APPROXIMATELY 457.2MM (18IN) FROM THE FORWARD END - SEVERAL LONGITUDINAL CRACKS WERE EVIDENT IN THEAREA OF THE FAILURE WHEN VIEWED UNDER X10 MAGNIFICATIONSDR CA960116010Fcu · failure(CAN)START LAG AT AROUND 28 PERCENT N1 UP TO 38 PERCENT. THEN START RESUMED FOR SECOND PEAK. WOULD NEED HIGH CHARGE BATTERY FOR START-UP. FIRST PEAK 720 DEGREES, THEN WENT BACK DOWN TO 550 DEGREES THROUGH 28 PERCENT N1 TO 38 PERCENT N1. SECOND PEAK AT 38 PERCSDR 95ZZZX6348Bolt · wrong partACFT WAS IN FOR A 100-HOUR INSP. MECHANIC PERFORMING TAIL ROTOR GEARBOX MOUNT RE-TORQUE, CUT THE SAFETY WIRE AND THE BOLT PULLED OUT. IT WAS ALSO FOUND THAT 2 OTHER BOLTS WERE ONLY IN PLACE BY 2 THREADS. MECHANIC STATED BOLTS WERE INCORRECT, PN NAS1304-24H,SDR 95ZZZX1316Strut Assy · crackedAFTER FLIGHT, THE PILOT NOTED THAT THE HELICOPTER WAS SITTING VERY LOW ON THE AFT LEFT SIDE. AN INSPECTION WAS CONDUCTED AND FOUND AFT LEFT LANDING GEAR STRUT ASSY CRACKED AT THE INSIDE RIVET HOLE. THE RIVET ATTACHES THE SUPPORT FOR THE LOWER GUIDE AND FILLE
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