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 = '206L4' 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 = '206L4' 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 EVCA2019021100001Blade · debondedDURING INSPECTION FOUND EVIDENCE OF DEBONDING ON T/R BLADE P/N 206-016-201-135 S/N CS20648. REMOVED T/R HUB AND BLADE ASSEMBLY P/N 206-011-810-157G S/N HB2825 AND INSTALLED SERVICEABLE T/R HUB AND BLADE ASSEMBLY P/N 206-011-810-157G S/N HB2767 IAW BOTH BHT-206SDR EVCA201901142Attach Fitting · crackedTAILBOOM ATTACHMENT FITTING UPPER LEFT TAILBOOM SIDE CRACKED. AMT'S REMOVED AND REPLACED TAILBOOM FITTING.SDR EVCA2018120703Drive Ring · wornUPON INSPECTING AIR CONDITIONING DRIVE PULLEY AND SPLINE IN ACCORDANCE WITH AIR COMM SB206EC-18-07 AND AIR EVAC MIL 356. IT WAS DISCOVERED A/C DRIVE PULLEY TO BE WORN BEYOND LIMITS. DRIVE PULLEY WAS REPLACED AND INSTALLED IN ACCORDANCE WITH MIL 356 AND SB206ECSDR EVCA20181207002Pulley · wornUPON INSPECTING AIR CONDITIONING DRIVE PULLEY AND SPLINE IN ACCORDANCE WITH AIR COMM SB206EC-18-07 AND AIR EVAC MIL 356. IT WAS DISCOVERED A/C DRIVE PULLEY TO BE WORN BEYOND LIMITS. DRIVE PULLEY WAS REPLACED AND INSTALLED IN ACCORDANCE WITH MIL 356 AND SB206ECSDR EVCA20181207001Drive Ring · wornUPON INSPECTING AIR CONDITIONING DRIVE PULLEY AND SPLINE IN ACCORDANCE WITH AIR COMM SB206EC-18-07 AND AIR EVAC MIL 356. IT WAS DISCOVERED A/C DRIVE PULLEY TO BE WORN BEYOND LIMITS. DRIVE PULLEY WAS REPLACED AND INSTALLED IN ACCORDANCE WITH MIL 356 AND SB206ECSDR EVCA201811272Stiffener · crackedRT AFT STIFFENER IN CENTER POST HAS A 2 INCH CRACK ACROSS THE STIFFENER APPROXIMATELY AT WATERLINE 67, RIGHT BL 5 AND STATION 82. RT WEB HAS 1 INCH CRACK IN SAME LOCATION. REMOVED AND REPLACED RT AFT BROOM CLOSET ANGLE P/N 206-033-110-239S AND REPAIRED CRACK RSDR EVCA201810181Flex Hose · rupturedUPON START UP PILOT NOTED GRINDING NOISE COMING FROM ENGINE COMPARTMENT. PILOT NOTED OIL LEAK. THE BASE AMT INSPECTED AND FOUND ENGINE OIL LINE RUPTURED AND METAL CHIPS ON ENGINE CHIP DETECTOR. DUE TO THE OIL LINE RUPTURE. IT IS BELIEVED THE ENGINE WAS OIL STASDR EVCA2018081601Motor · failedDURING CRUISE FLIGHT, SMOKE WAS COMING OUT OF AIR CONDITIONING VENT. THE PILOT SHUT THE AIR CONDITIONING OFF. LANDED IN FIELD. NOTED SMOKE CLEARED ONCE A/C WAS SHUT OFF. AMT INSPECTED THE A/C SYSTEM. REMOVED AND REPLACED THE AFT AIR CONDITIONER BLOWER MOTORSDR EVCA201807051Attach Fitting · crackedTAILBOOM ATTACHMENT FITTING UPPER LEFT TAILBOOM SIDE CRACKED. AMT'S REMOVED AND REPLACED TAILBOOM FITTING.SDR EVCA201806141Inverter · odorCREW REPORTED DURING FLIGHT A QUICK FLASH OF LIGHT. QUOTING WRITTEN DISCREPANCY: SOFTBALL SIZE YELLOW FLAME EMITTED FROM UNDER MONITOR SHELF JUST BEHIND PILOT SEAT WITH MELTED PLASTIC SMELL. AMT DISCOVERED NO SIGN OF FLAME OR ELECTRICAL ISSUES. INSPECTED INVERSDR CA180709003Wire · burned(CAN) THE FOLLOWING WAS REPORTED TO BELL: AFTER START-UP, WHEN THE PILOT PUT ON THE GENERATOR, SMOKE EMITTED FROM BATTERY COMPARTMENT AND OVER HEAD PANEL. ENGINE WAS IMMEDIATELY SHUT DOWN AND BATTERY SWITCHED OFF. WE OPENED THE BATTERY COMPARTMENT, DIDN`T SESDR EVCA2018060100001Stiffener · crackedDURING A MAINTENANCE INSPECTION, A CRACK WAS FOUND ON THE STIFFNER IN THE VERTICAL TUNNEL AT BS 88, WL 68.SDR YTRA20180221052Pump · failedWHILE IN CRUISE FLIGHT THE HYDRAULIC SYSTEM FAILED. REPLACED THE PUMP.SDR EVCA201802021Mount · crackedWHILE PERFORMING SCHEDULED 100 HOUR INSPECTION, NOTED A 1.5 INCH CRACK IN THE TAILBOOM MOUNTING RING EXTENDING FROM THE UPPER LT MOUNTING HOLE TO THE EDGE OF THE BULKHEAD.SDR EVCA201712011Bulkhead · corrodedFOUND BULKHEAD PN: 206-033-302-141 TO BE SIGNIFICANTLY CORRODED REQUIRING MAJOR REPAIR/REPLACEMENTSDR EVCA2017111400002Packing · leakingFLIGHT CREW REPORTED A STRONG FUEL SMELL IN THE COCKPIT/CABIN AREA. DURING MAINTENANCE INVESTIGATION IT WAS NOTED THAT THE DRAIN ON THE FUEL INTERCONNECT AFT FUEL CELL FITTING WAS LEAKING. REPLACED PACKING MS29512-04SDR EVCA201711061Stiffener · crackedDURING MAINTENANCE INSPECTION OF THE AIRCRAFT FOUND THE TOP END OF THE RT AFT VERTICAL CONTROL TUBE TUNNEL STIFFENER CRACKED.SDR EVCA20171109001Connector · unsecureDURING DEPARTURE FROM BASE PILOT REPORTED AN ELECTRICAL BURNING ODOR IN THE CABIN. ON MAINTENANCE INVESTIGATION, FOUND THAT THERE WAS A LOOSE CONNECTION AT THE BATTERY RELAY OF THE POSITIVE LEAD WIRE NR P1A4. THE LOOSE CONNECTION DAMAGED THE RING TERMINALS SDR EVCA201710130001Motor · failedFLIGHT CREW REPORTED SMELLING A BURNING ODOR IN THE AIRCRAFT WHEN THE AIR CONDITIONER WAS OPERATING. AFTER MAINTENANCE INVESTIGATION, FOUND THE AFT BLOWER MOTOR OF THE AIR CONDITIONER SYSTEM TO HAVE A BURNED ELECTRICAL CONNECTOR. AIR CONDITIONER INSTALLED ISDR 2018FA0000226Shaft · shearedPILOT REPORTED LOSS OF HYDRAULICS. RETURNED TO AIRPORT. MECHANIC REMOVED HYDRAULIC PUMP WHICH IS BOLTED TO THE TACHOMETER GENERATOR. THEN REMOVED TACHOMETER GENERATOR THAT IS BOLTED TO THE MAIN TRANSMISSION. DURING REMOVAL OF TACHOMETER GENERATOR THE MECHASDR EVCA201709261Blower Motor · burnedDURING CRUISE FLIGHT THE FLIGHT CREW REPORTED SMOKE AND BURNING SMELL IN THE CABIN. DURING MAINTENANCE INVESTIGATION BLACK SOOT WAS FOUND AROUND AFT AIR CONDITIONING VENTS AND THE AFT AIR CONDITIONER BLOWER MOTOR WAS MAKING A METALLIC SOUND AND SHOWED SIGNS OFSDR EVCA201708161Stiffener · crackedDURING MAINTENANCE FOUND THE LT UPPER STIFFENER CLIP AND THE BULKHEAD STRUCTURE AT THE FS 145 BULKHEAD TO BE CRACKED. ON BULKHEAD PN: 206-033-107-121 THERE WAS A .7" CRACK EXTENDING THROUGH THE 3RD UPPER RIVET HOLE FROM THE BOX BEAN AND A 1" CRACK EXTENDING THSDR EVCA201707180001Attach Fitting · crackedFOUND LT TAILBOOM ATTACHMENT FITTING PN: 206-031-403-005 TO HAVE A 1.6" LONG CRACK. FITTING LOCATED ON TAILBOOM SIDE OF BULKHEAD.SDR EVCA201707061Attach Fitting · crackedUPPER LT ATTACH FITTING ON THE TAILBOOM WAS FOUND TO BE CRACKED THROUGH THE RIVETS AT THE FORWARD END. CRACK MEASURES 1.34 INCHES.SDR EVCA201705261Control Tube · rotatedFIXED LENGTH COLLECTIVE CONTROL TUBE, FOUND TO HAVE ROTATATED BETWEEN THE CLEVIS AND THE CONTROL TUBE BODY AT THE SERVO END OF THE CONTROL TUBE.SDR EVCA201705221Control Tube · abnormalWHILE PERFORMING INSPECTION OF THE AIRCRAFT FOUND THE COLLECTIVE CONTROL TUBE FOUND TO HAVE ROTATIONAL MOVEMENT BETWEEN THE CLEVIS AND THE CONTROL TUBE AT THE JUNCTION WITH THE TRANSMISSION BELLCRANK.SDR EVCA201705173Control Tube · abnormalWHILE PERFORMING A PREFLIGHT INSPECTION OF THE AIRCRAFT FOUND COLLECTIVE CONTROL TUBE TO HAVE ONE OF ITS FIXED AND NONADJUSTABLE CLEVISES TO BE ROTATING WITHIN THE TUBE.SDR EVCA201705172Tube · damagedWHILE PERFORMING PREFLIGHT OF THE AIRCRAFT FOUND BOTH CYCLIC TUBES PN: 206-001-193-001 SN: US1214 AND US1215 TO HAVE THEIR FIXED AND NON ADJUSTABLE CLEVISES TO BE ROTATING WITHIN THE TUBES.SDR EVCA201705171Tube · damagedWHILE PERFORMING PREFLIGHT OF THE AIRCRAFT FOUND BOTH CYCLIC TUBES TO HAVE THEIR FIXED AND NON ADJUSTABLE CLEVISES TO BE ROTATING WITHIN THE TUBES.SDR EVCA201703241Wire · shortedTHE PILOT WAS ON FINAL APPROACH, WHEN AIRCRAFT EXPERIENCED COMPLETE AVIONICS FAILURE. ALL SCREENS WENT BLACK, SMOKE IN COCKPIT COMING FROM THE OVERHEAD CIRCUIT BREAKER PANEL. PILOT WAS ABLE TO MAINTAIN A NORMAL LANDING PROCEDURE DURING THIS EVENT. ON LANDISDR EVCA2017030100051Fuel Control · bindingPILOT REPORTED THROTTLE WAS UNABLE TO BE MOVED. MECHANIC FOUND FUEL CONTROL THROTTLE LEVER TO BE BINDING PREVENTING THROTTLE FROM MOVING.SDR EVCA201612071Bulkhead · crackedTAIL BOOM RING/BULKHEAD ASSY PN: 206-032-400-027 HAS APPROXIMATELY ONE 1/2 - 3/4 INCH CRACK AROUND THE UPPER LEFT SIDE OF THE UPPER LEFT INTERCOSTAL/MOUNT POINT.SDR EVCA201611181Fitting · crackedUPPER LEFT TAILBOOM FITTING ON THE TAILBOOM SIDE OF THE BULKHEAD IS CRACKED FROM EDGE TO EDGE OF THE FITTING.SDR EVCA201610061Elec Connector · burnedWHILE FLYING PILOT AND PASSENGERS REPORTED A BURNING SMELL WHEN AIRCRAFT WAS APPROACHING BASE FOR LANDING. DURING INSPECTION, MECHANIC FOUND THE MOLEX CONNECTOR WAS MELTED ON THE BRACKET TO THE AFT BLOWER MOTOR HOUSING.SDR EVCA20160917161Stiffener · crackedDURING INSPECTION, FOUND RT SIDE WEB OF THE VERTICAL CONTROLS TUNNEL TO HAVE A CRACK AT THE TOP AFT EDGE OF THE STRUCTURE. UPON DETAILED INSPECTION FOUND THE AFT RT VERTICAL TUNNEL STIFFENER TO BE CRACKED THROUGH.SDR EVCA201608071Connector · burnedWHILE IN FLIGHT, THE PILOT AND CREW REPORTED AN UNUSUAL ODOR SIMILAR TO HOT RUBBER IN THE ACFT CABIN AND PERFORMED A PRECAUTIONARY UNSCHEDULED LANDING. MAINTENANCE FOUND THE AIR CONDITIONING SYSTEM TO BE THE CAUSE AND DEACTIVATED AND MEL THE SYSTEM. UPON DETSDR EVCA201607060001Hose · leakingWHILE APPROACHING A REMOTE UNIMPROVED LANDING SITE THE PILOT REPORTED HEARING A METAL GRINDING SOUND FROM THE ENGINE AREA FOLLOWED BY A LOSS OF HYDRAULIC POWER FOR THE FLIGHT CONTROLS. UPON LANDING FOUND HYDRAULIC FLUID LEAKING DOWN SIDE OF AIRCRAFT. MAINTENANSDR EVCA20160624162Stiffener · crackedDURING 300 HR PERIODIC INSPECTION OF ACFT, FOUND STIFFENER, PN: 206-033-110-239S TO BE CRACKED AT THE INTERFACE WHERE THE BOX BEAM MEETS THE VERTICAL TUNNEL ON THE RT SIDE OF THE VERTICAL TUNNEL.SDR EVCA201606241Trunnion · crackedFOUND A PILLOW BLOCK TRUNNION ON THE MAIN ROTOR HEAD THAT HAD A CRACKED MOUNTING LUG.SDR YTRA2016062417601Control Tube · debondedCONTROL TUBE IS DEBONDED FROM CLEVIS.SDR XHCR2016FA0000362Fuel Cell · leakingFUEL CELL: PN 206-064-633-101, SN 85633 MANUFACTURED IN 06/20/04 WAS FOUND TO BE IN AN UNAIRWORTHY CONDITION DURING A ROUTINE 24 MONTH INSPECTION. IT IS THE METHOD OF FAILURE AND THE TRENDING OF FAILURES OF CELLS MADE BY THIS COMPANY THAT HAS SPURRED THIS REPSDR EVCA201605261Frame · crackedWHILE PERFORMING INSPECTIONS OF THE ACFT IT WAS FOUND THAT THE FS 145 BULKHEAD HAD A CRACKED CLIP, PN 206-033-107-055 WITH 5 CRACKS, ALL MEASURING BETWEEN 3/32" & 5/16" IN LENGTH. UPON REMOVAL OF THE CLIP, FRAME, PN 206-033-107-121 WAS FOUND TO HAVE MULTIPLE SDR EVCA201603151Fuel Cell · leakingUPON PRE-FLIGHT PILOT FOUND FUEL POOLING UNDER ACFT. UPON INSPECTION FOUND THAT FUEL WAS SEEPING THROUGH THE RT FWD FUEL CELL, PN 206-063-632-102. FUEL PERMEATING THROUGH RUBBER CELL MEMBRANE.SDR EVCA201603152Shaft · jammedWHILE REPLACING A LEAKING HYD PUMP & LEAKING TRANSMISSION OIL PUMP, IT WAS DISCOVERED THAT THE ROTOR TACH GEN TO HYD PUMP DRIVE SPLINES, SHAFT PN 20546AA, WERE SEIZED IN THE ROTOR TACH GEN. APPARENT CAUSE WAS OIL & HYD FLUID WASHING OUT LUBRICATING GREASE.SDR YTRA20151106001Shaft · shearedPILOT EXPERIENCED PROBLEMS WITH THE FLIGHT CONTROL HYD SYS DURING THE LANDING CYCLE.SDR CA151023005Converter · failed(CAN) IN FLIGHT, POWER TO THE CAMERA BECAME INTERMITTENT. AFTER RECYCLING ENG MASTER, POWER WAS NOT RESTORED. ON RETURNING TO THE AIRPORT SMOKE FUMES WERE NOTICED IN THE COCKPIT. REQUEST FOR IMMEDIATE LANDING FROM THE TOWER WAS ACCOMMODATED. MACHINE LANDEDSDR CA151007019Gearbox · making metal(CAN) DURING SHUTDOWN, PILOT REPORTED AN UNFAMILIAR METALLIC NOISE FOLLOWED SHORTLY BY ILLUMINATION OF THE COMBINING GEARBOX CHIP LIGHT. INSPECTION OF THE CHIP PLUG REVEALED METAL PARTICLES IN EXCESS OF ALLOWABLE, ACFT GROUNDED. COMBINING GEARBOX IS APPROXIMSDR CA150813008Fuel Control · malfunctioned(CAN) DURING LANDING THE PILOT REPORTED AN UNCOMMENTED SURGE OF 10 PERCENT TORQUE, AND A SLIGHT YAW. THE SURGE DID NOT IMPEAD LANDING OF THE ACFT, OR EXCEED ANY PARAMETERS. ONCE THE ACFT LANDED THE ENGINE WOULD NOT STABLIZE, AND CONTINUED TO SLIGHTLY SURGE UNSDR CA150811005Attach Fitting · cracked(CAN) DURING ROUTINE 100 HOUR INSPECTION, THE UPPER LT TAIL BOOM ATTACH FITTING WAS FOUND CRACKED.SDR EVCA20150717001Mast · corrodedINTERIOR DIAMETER SURFACE OF MAST POLE SHOWING SIGNS OF CORROSION UNDERNEATH THE PAINT COATING.
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