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 = 'AW139' 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 = 'AW139' 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 KY1R20150422001Line · crackedAFTER THE CREW REPORTED THAT THE COCKPIT, FWD AIR CONDITIONING WAS INOPERATIVE, BLOWING HOT AIR, TECH ATTEMPTED TO SERVICE SYS WITH AC SERVICING CART. CART WOULD NOT ALLOW TECH TO PROGRESS BEYOND RECOVERY TO VACUUM MODE, DIE TO "HIGH PRESSURE" IN THE SYS. ITSDR CA140701001Engine · overheated(CAN) WHILE PERFORMING EXTENDED HOVER DURING SEARCH AND RESCUE HOIST TRAINING, THE ENGINE OIL TEMPERATURE REACHED 140 C. THE MISSION WAS ABORTED AND THE ACFT RETURNED TO BASE. TOUBLESHOOTING IS ON-GOING AND OPERATOR WILL LIKELY ELECT TO REPLACE THE ENGINE.SDR CA140630010Bleed Valve · failed(CAN) THE NR 1 ENGINE EXPERIENCED A TORQUE UP TRIM UP TO 104 PERCENT DURING HOVER. THE MISSION WAS ABORTED. DURING THE TROUBLESHOOTING, THE NR 2 ENGINE COMPRESSOR BLEED VALVE, BOV WAS REPLACED. THE HELICOPTER HAS RETURNED TO SERVICE.SDR CA140606003Switch · malfunctioned(CAN) PRELIMINARY INVESTIGATION REVEALS THAT PRIOR DEPARTURE, THE RT BAGGAGE DOOR WAS PARTIALLY CLOSED. THE DOOR HAS 2 LOCKING PINS MECHANISM. ONLY THE LT PIN WAS FULLY ENGAGED IN THE LOCKING HOLE WHILE THE RT PIN WAS ENGAGED IN THE BETWEEN THE DOOR SEAL ANDSDR DT1R20140206003Gear Shaft · damagedDURING TROUBLESHOOTING AN OIL LEAK FROM THE ECS DRIVE SHAFT . FOUND A 0.006" DEEP CIRCUMFERENTIAL GROOVE ON THE ECS DRIVE SHAFT UNDERNEATH THE LIP SEAL. FOUND MULTIPLE SCORES APPROXIMATELY 0.010" DEEP IN THE AXIAL DIRECTION. THE SHAFT HAS BEEN DEEMED UNSERSDR AC2R2018042005Bearing · corrodedMAIN GEARBOX OIL COOLING FAN HAD A CORRODED BEARING ASSY.SDR AC2R2018042001Bearing · corrodedMAIN GEARBOX OIL COOLING FAN CORRODED. REMOVED THE BEARING ASSY.SDR AC2A201402200001Bearing · dislodgedON DAILY POST FLIGHT INSPECTION, IT WAS DISCOVERED THAT ONE OF THE ROTATING SCISSORS WAS NOT CONNECTED TO THE SWASHPLATE. BEARING HAD COME OUT OF THE RACE.SDR CA140103006Window · separated(CAN) RT WINDOW ASSY BECAME SEPARATED FROM COCKPIT DOOR IN FLIGHT. FLIGHT CREW DISCONTINUED FLIGHT AND SAFELY LANDED AT AIRPORT.SDR CA131231007Warning Light · illuminated(CAN) DURING MAINTENANCE HOVER, MAIN TRANSMISSION CHIP SUMP CAS CAUTION ILLUMINATED. NOT BURNABLE.SDR CA131216008Valve · failed(CAN) THE ENGINE WAS ITT MARGINAL. THE BOV WAS ADJUSTED WHICH CAUSED A SURGE ON DECEL. THE BOV WAS REPLACED WITH KNOWN SERVICEABLE UNIT AND IT WAS ADJUSTED. DURING TEST AND REPOSITIONING FLIGHT TO ANOTHER BASE, THE ENGINE EXPERIENCED UNRECOVERABLE SURGE ON DESDR CA131118028Slip Ring · failed(CAN) DURING A 50HR BY-WEEKLY INSPECTION, ENGINEER DISCOVERED THAT THE DUPLEX BEARING IN THE TAIL ROTOR SLIP RING HAD DETERIORATED BEYOND ACCEPTABLE LIMITS.SDR BB1R201401290001Blade · damagedMAIN ROTOR BLADE OTBD TRIM TAB PARTIALY DEBONDED AND CURLED IN DIRECTION OF AIRSTREAM. BLADE REMOVED AND RETURNED TO MFG FOR REPAIR.SDR CA131105001Module · malfunctioned(CAN) DURING GROUND CHECKS, IT WAS FOUND THAT THE ENGINE CONTROLS DID NOT RESPOND TO POWER LEVER MOVEMENTS WHEN THE GOVERNOR SWITCH WAS SELECTED TO MANUAL MODE. FUEL MANAGEMENT MODULE REPLACEMENT RECTIFIED THE PROBLEM.SDR CA131002009Slip Ring · failed(CAN) DURING A POST FLIGHT WALK AROUND, FROM A 1 HR FLT, IT WAS NOTED THE FIPS WIRING ON THE TAIL ROTOR WAS DAMAGED. INSPECTION REVEALED THAT THE SLIP RING ASSY HAD SEIZED CAUSING THE DRIVE PIN TO SHEAR THE DRIVE LINKS AND ALSO CAUSED THE 4 WIRING BUNDLES TO SDR AC2A9NA09252013Grommet · failedNEW STYLE EXHAUST SYS FAILURE AT ATTACHMENT POINTS WHERE RUBBER GROMMETS INSULATOR CONNECT TAIL PIPE. AFTER GROMMETS FAIL, THE MOVEMENT AND EXHAUST VIBRATION LEAD TO EXCESSIVE FIREWALL CRACKING.SDR AC2A201309170001Torque Sensor · damagedENGINE TORQUE MISCOMPARE CAS MESSAGE ILLUMINATED DURING GROUND RUN. FOUND TORQUE SENSORS DAMAGED FROM CONTACT WITH ROTATING COMPONENT.SDR ALGA2013081430702Warning Message · inoperativeAFTER TAKEOFF, INDICATIONS THAT LANDING GEARS DID NOT GO UP AND INTO THE LOCKED POSITION. RETURNED TO BASE. LANDING GEAR INDICATED DOWN AND LOCKED AND ACFT LANDED SAFELY.SDR ULXR201308140002Control Switch · inadequateGOVERNER MANUAL / AUTOMATIC CONTROL SWITCH IS LOCATED ON THE COLLECTIVE CONTROL HEAD. THIS SWITCH IS NEITHER A GUARDED OR LOCKOUT TYPE SWITCH. IT IS EASILY BUMPED INTO THE MANUAL CONTROL MODE. THIS HAS CAUSED SEVERAL MAIN ROTOR OVERSPEED INCIDENTS.THIS SWITCH SDR CA130521015Windshield · cracked(CAN) THE BOTH THE PIC & CO-PLIOT HEARD THE WINDSCREEN TO "POP" IN FLIGHT AND A CRACK WAS NOTICED IN BOTH THE RT & LT GLASS. THE CREW LANDED THE ACFT WITHOUT INCIDENT.SDR ALGA201304300001Landing Gear · inoperativeNLG FAILED TO RETRACT AFTER TAKEOFF.SDR DT1R20130423002Door · unsecureDURING FLIGHT AT APPROX 140 KTS THE RT CABIN DOOR OPENED. DOOR REMAINED ATTACHED TO THE ACFT. THE ACFT LANDED SAFELY. THE RT CABIN DOOR AND LOOSE EQUIPMENT WAS REMOVED FROM THE ACFT.SDR CA130412001Hook · detached(CAN) HELICOPTER DEPARTED AIRPORT FROM THE THRESHOLD OF RW19 DURING A VFR TRAINING FLIGHT. UPON RETURN TO AIRPORT, A VFR APPROACH TO THE THRESHOLD OF RW19 WAS CONDUCTED TO A LANDING. AFTER LANDING, THE LT SEAT PILOT NOTICED A SMALL OBJECT APPROXIMATELY 10 MESDR ULXR201308140001Control Switch · inadequateGOVERNER MANUAL/AUTOMATIC CONTROL SWITCH IS LOCATED ON THE COLLECTIVE CONTROL HEAD. THIS SWITCH IS NEITHER A GUARDED OR LOCKOUT TYPE SWITCH. IT IS EASILY BUMPED INTO THE MANUAL CONTROL MODE. THIS HAS CAUSED SEVERAL MAIN ROTOR OVERSPEED INCIDENTS. THIS SWITSDR CA130327007Hose · damaged(CAN) FLYING PILOT REMARKED ON A CURIOUS "STIFFNESS" DURING RT PEDAL APPLICATION ON PREVIOUS FLIGHTS. AFTER LANDING, PIC OBSERVED LT BRAKE FLUID LINE ON LT SIDE OF ACFT TO BE RUNNING BETWEEN PARTS OF THE FLAPPER VALVE ASSY. IT WAS OBVIOUSLY RESTRICTING RT PESDR CA130212018Wire Harness · damaged(CAN) IFSD WAS PILOT INDUCED DUE TO HIGH AND FLUCTUATING ITT. AFTER THE DCU AND THE FDR DATA WAS REVIEWED, IT APPEARS TO BE A CONNECTIONS ISSUE. IT WAS RECOMMENDED TO THE TO CHECK ALL THE CONNECTIONS AND ITT HARNESS TO CORRECT THIS ISSUE. THE PREVIOUSLY PROSDR CA130130007Attach Fitting · cracked(CAN) DURING A POST FLIGHT ENGINEERS FOUND RT EXHAUST NOZZLE ATTACHMENT CRACKED.SDR CA130130006Support · broken(CAN) DURING POST FLIGHT INSPECTION, THE ENGINEERS NOTICED THAT THE LT ATTACHMENT SUPPORT ON THE RT EXHAUST NOZZLE HAS BROKEN OFF. DURING FURTHER INSP WE NOTICED THAT THE STRINGER ON THE EXHAUST SUPPORT ASSY HAS CRACKED. LT FORWARD EXHAUST ATTACHMENT BRACKETSDR CA121105007Engine · making metal(CAN) DURING FLIGHT, A CHIP LIGHT INDICATION RESULTED IN A PILOT INDUCED IFSD. AN UNEVENTFUL SINGLE ENGINE LANDING WAS MADE. POST FLIGHT INSPECTION FOUND DEBRIS ON THE CHIP DETECTORS WHICH ARE CURRENTLY BEING ANALYZED.SDR CA120822004Damper · failed(CAN) DURING ROUTINE 50 HRS INSPECTION, A CRACK WAS FOUND ON MAIN ROTOR LAG DAMPER PISTON. LAG DAMPER REPLACED IAW AMP.SDR CA120803005Bleed Valve · malfunctioned(CAN) DURING A 50 HR INSPECTION, A PIECE OF THE P2.8 FLAPPER VALVE WAS FOUND IN THE ENGINE FIRE BOTTLE COMPARTMENT OF THE NR 2 ENGINE. THE FLAPPER VALVE IS POST SB41042. SB41042 WAS INTRODUCED AS A RESULT OF A SIMILAR PROBLEM WITH THE PRE SB VALVES.SDR CA120723016Exhaust Duct · collapsed(CAN) EXHAUST DUCT COLLAPSED. EXHAUST NOZZLE FOR NR 1 ENGINE.SDR CA120822006Blades · failed(CAN) DURING AN INSPECTION OF 300 HRS, FOUND SUSPECT CRACKS ON 2 TIP CAP OF MAIN ROTOR BLADES. CLEANED THE AREA, CHECKED WITH MAGNIFYING GLASS. REPLACED BOTH MAIN ROTOR BLADES.SDR ALGA2012060101Warning Light · illuminatedIN CRUISE FLIGHT, NR 1 FUEL PUMP CAUTION LIGHT ILLUMINATED.SDR 2012FA0000361Blade · crackedDURING PREFLIGHT INSPECTION, FOUND POSSIBLE CRACK AT TAIL ROTOR BLADE. LOCATION WHERE THE FWD STRAP MEETS THE POCKET ON THE L/E, APPROX LENGTH .750. REMOVED TAIL ROTOR BLADE FROM SERVICE FOR FURTHER INSPECTION.SDR 2012FA0000342Blade · crackedDURING DAILY CHECK AFTER FLIGHT, MECHANIC NOTICED CRACK ON 1 TAIL ROTOR BLADE, JUST AFT OF EROSION SHIELD, EXTENDING FROM THE INBD END OF EROSION SHIELD TO WITHIN APPROX 8" OF OTBD TIP OF THE BLADE. MAX OPENING OF CRACK, APPROX .1875" AT INBD END. CRACK IS ESDR CA120530003Line · chafed(CAN) ACFT HAD BEEN SHUTDOWN, PASSENGERS DISEMBARKED AND ACFT WAS BEEN PREPARED FOR TOW BACK TO HANGAR WHEN HYDRAULIC FLUID WAS SEEN ON THE GROUND UNDER THE ACFT. FORWARD COWLING ON THE UPPER DECK WAS OPENED AND HYDRAULIC FLUID WAS NOTED ON THE RT SIDE OF THESDR DT1R20120606005Slip Ring · chafedDURING POST-FLIGHT INSPECTION, THE T/R FIPS SLIP RINGWIRES WERE FOUND TO BE CHAFED AND BROKEN, CAUSING ARCING DAMAGE ON THE TAIL ROTOR HUB DAMPER BRACKETS.SDR CA120426004Hose · leaking(CAN) FOUND HYDRAULIC HOSES LEAKING WITH VERY LOW TIME IN SERVICE. NONE OF THE INSTANCES WERE A RESULT OF CHAFING OR IMPROPER INSTALLATION.SDR AC2A201204170001Stop · crackedDURING AN INSPECTION, A CRACK WAS DISCOVERED ON A MAIN ROTOR DROOP STOP.SDR ALGA201203230002Casting · crackedDURING A 300 HR INSPECTION, FOUND VIBRATION CASTING CRACKED RT SIDE UNDER FLOOR.SDR ALGA2012032300001Bulkhead · crackedWHILE COMPLYING WITH 300 HR INSPECTION, A CRACK WAS DISCOVERED IN THE NOSE ELECTRICAL/AVIONICS AREA, THE LATERAL BULKHEAD IS CRACKED ON BOTH SIDES.SDR ALGA2012021700001Casting · crackedDURING A 300 HOUR INSPECTION, MX FOUND CRACK IN DOUBLER ON RT SIDE OF ACFT OF PILOT'S DOOR IN HAMMERS AREA. ON FURTHER INVESTIGATION, AFTER REMOVAL OF FLOOR PANELS, MX FOUND HAMMERS CASTING CRACKED. THIS REPORT IS INCOMPLETE DUE TO NO DATA RECEIVED FROM MFGSDR ALGA2012013000777Step · crackedLEFT CABIN STEP CRACKED ON ACFT LEG. FOUND LEG CRACKED HALF WAY THROUGH. REPLACED WITH NEW PART.SDR ALGA2012012550005Structure · failedDURING POST FLIGHT INSPECTION MECHANICS OBSERVED THAT A PORTION OF THE COWLING ON THE TAIL BOOM DIRECTLY UNDER THE VERTICAL FIN WAS BROKEN OFF.SDR CA120123012Longeron · cracked(CAN) DURING THE 48 MONTHS INSPECTION, THE AMO CARRYING THE INSPECTION FOUND A CRACK ON THE LT UPPER LONGERON ASSY ON THE AIRFRAME SIDE WHERE THE TAIL ASSY ATTACHED TO THE AIRFRAME ON THE LT TOP CORNER, MFG WAS CONTACTED AND ENGINEERING IS WORKING ON THE APPROSDR CA120123011Bearing · sheared(CAN) DURING THE 48 MONTHS INSPECTION, THE AMO CARRYING OUT THE INSPECTION NOTICE ON DISSASSEMBLY OF THE MAIN ROTOR HEAD, 1 OF THE ELASTOMERIC BEARINGS HAD BECOME SEPARATED AT MORE THAN 270 DEGREES AROUND WITH ONLY A SMALL AMOUNT OF ELASTOMER STAYING CONNECTEDSDR CA120227004Cyclic Control · malfunctioned(CAN) WHILE PERFORMING A FLIGHT CONTROL CHECK IT WAS FOUND THAT WITH FULL FORWARD CYCLIC INPUT THE COLLECTIVE COULD ONLY BE LIFTED 70 PERCENT OF THE WAY UP. WHEN THE COLLECTIVE WAS FORCED HIGHER UP IN TRAVEL IT WOULD IN TURN FORCE THE CYCLIC AFT. SO WITH FULLSDR CA111208022Window · departed(CAN) WHILE IN CRUISE ENROUTE VERY ABRUPTLY AND WITHOUT WARNING THE ENTIRE CO-PILOT`S COCKPIT DOOR WINDOW DEPARTED THE AIRCRAFT. IMMEDIATELY THE AIRCRAFT WAS SLOWED FROM CRUISE(APPROX 150KTS) TO 80KTS INDICATED AND DIVERTED TO AIRPORT . OUR THOUGHT WAS TO INSPSDR 2011FA0000759Tube · missingDURING FIRST SCHEDULED INSPECTION SINCE MFG OF LIFERAFT, FOUND THAT SURVIVAL KIT CONTAINED AN INCORRECT MANUAL INFLATION PUMP. CORRECT PUMP HAS AN INTEGRAL HOSE. INSTALLED PUMP HAD NO HOSE, A FITTING INCOMPATIBLE WITH THE TOP BUOYANCY TUBE MANUAL INFLATION R
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