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 = '205A1' 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 = '205A1' 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 H4QA20260619001Relay · failedENROUTE TO A DIP SITE FOR ANOTHER BUCKET OF WATER THE PILOT SMELLED ELECTRICAL SMOKE IN THE CABIN OF THE AIRCRAFT. ODOR WAS IMMEDIATELY FOLLOWED BY SMOKE COMING FROM UNDER THE CENTER CONSOLE WHICH FILLED THE HELICOPTER CABIN. THE PILOT CALLED IN A MAYDAY OVER SDR 2022F00378Hose · rupturedAT APPROXIMATELY 10501.9 ACTT ON 9-29-22 AT 1530 PM I WAS TOLD THAT THERE HAD BEEN A HYDRAULIC SYSTEM 2 FAILURE ON N456TA. THE PILOT LANDED WITHOUT INCIDENT. AFTER SHUTDOWN I INVESTIGATED THE PROBLEM AND FOUND THAT THE #2 SYSTEM WAS ALMOST COMPLETELY EMPTY OSDR NKVA2025011500013Swashplate · crackedA TECHNICIAN REPORTED THAT DURING HIS DAILY INSPECTION HE FELT SOME "LOOSENESS" IN THE SWASHPLATE THAT HE HAD NOT NOTICE ON PRIOR DAILY INSPECTIONS. HE INVESTIGATED FURTHER AND FOUND THAT THE SWASHPLATE INNER RING WAS CRACKED AT THE GIMBAL ATTACHMENT LUG. THE SDR 2021FA0000284Swashplate · crackedA TECHNICIAN REPORTED THAT DURING HIS DAILY INSPECTION HE FELT SOME "LOOSENESS" IN THE SWASHPLATE THAT HE HAD NOT NOTICED ON PRIOR DAILY INSPECTIONS. HE INVESTIGATED FURTHER AND FOUND THAT THE SWASHPLATE INNER RING WAS CRACKED AT THE GIMBAL ATTACHMENT LUG. TSDR H4QA202007230001Crosstube · brokenREAR AFT CROSSTUBE FAILED WHILE AIRCRAFT WAS NOT RUNNING. CREW WANTED TO FILL BELLY TANK WITH WATER AND MARK NUMBER OF GALLONS, DURING FILLING OPERATIONS FROM WATER TENDER, REAR CROSSTUBE FAILED, BREAKING IN HALF, CAUSING HELICOPTER TO SETTLE ON ISOLAIR BELLYSDR LJEA2020061600001Gearbox · crackedMAIN GEARBOX CASE CRACKED IN WEBBING ABOVE INPUT QUILL. FERRY PERMIT REQUESTED TO RELOCATE AIRCRAFT TO A LOCATION FOR MAINTENANCE.SDR 2020F00078Gearbox · crackedCRACK SUSPECTED IN MAIN GEARBOX CASE ABOVE INPUT QUILL PURSUANT TO GUIDANCE FROM BELL HELICOPTERS IN BELL 205 CR&O FIG 66-37. CRACK APPEARS TO EXTEND THROUGH WEB IN AREA IDENTIFIED. CONTACTED BELL & RECEIVED LETTER OF NO TECHNICAL OBJECTION FOR A ONE TIME FERRSDR 2016FA0000387Fire Detector · failedENROUTE TO A FIRE, FIRE LIGHT CAME ON. NO SMOKE WAS DETECTED. LANDED AIRCRAFT BACK AT BASE. MECHANIC TROUBLESHOT THE SYSTEM AND FOUND BAD FIRE SENSOR PROBE IN ENGINE COMPARTMENT. CHANGED PROBE.SDR HEAA2016012501Crosstube · crackedDURING ROUTINE WINTER MAINTENANCE, AN INSPECTION OF THE LANDING GEAR CROSSTUBES WERE ACCOMPLISHED IAW THE MFG 300 HOUR INSPECTION. ONE OF THE SADDLES FOR THE ATTACHMENT OF SKID GEAR TO THE FUSELAGE WAS FOUND DEBONDED ON THE CROSSTUBE. ICA INSTRUCTIONS CALL FOSDR H4QA20151028559Support · bentDURING SCHEDULED MX IT WAS DISCOVERED THAT A BEARING WOULD NOT FIT BETWEEN THE MOUNTING LUGS OF THE SWASHPLATE SUPPORT, PN 204-011-404-125, SN RE18039. THE SWASHPLATE SUPPORT LUGS WERE DIMENSIONALLY CHECKED & ENGINEERING CONTACTED. THE DIMENSIONAL CHECK REVESDR CA150929013Shaft · sheared(CAN) STARTER GENERATOR SHAFT SHEARED IN FLIGHT UNDER NORMAL LOADS CAUSING LOSS OF DC POWER GENERATION. ACFT RETURNED TO BASE UNEVENTFULLY.SDR 2015FA0000355Connector · burnedPILOT REPORTED BURNED PLASTIC ODOR FROM ENGINE COMPARTMENT. MECHANIC INSPECTED ENGINE COMPARTMENT AND FOUND A BURNED AREA ON THE STARTER/GENERATOR CONNECTOR PLUG BACKSHELL. REPLACED THE STARTER AND THE HARNESS FROM THE STARTER/GENERATOR TO THE ENGINE DECK. SDR CA150713024Hydraulic Line · ruptured(CAN) DURING FLIGHT THE PILOT EXPERIENCED A LOSS OF NR 2 HYD PRESS. PILOT RETURN TO THE BASE AFTER ISOLATING THE SYS. ONCE THE ACFT LANDED SAFELY, THE INVESTIGATION REVEALED THE LINE TO THE PRESS SIDE OF HYD PUMP NR 2 HAD RUPTURED AT THE 90 DEGREE FITTING. SDR CA150421003Blade · damaged(CAN) DURING A MAINTENANCE FLIGHT CHECKING MAIN ROTOR SYS TRACK AND BALANCE, THE ACFT WAS INCREASING AIRSPEED FROM 60 KNOTS TO 100 KNOTS. A LOUD BANG WAS HEARD IN THE CABIN, THE ACFT POWER WAS ROLLED OFF & THE ACFT WAS PUT INTO AN AUTOROTATION DESCENT. DURINSDR CA150316004Blade · cracked(CAN) DURING INSPECTION OF ACFT BLOWER FAN, IT WAS NOTED THAT 4 OF THE FAN BLADES WERE CRACKED AT THE BASE.SDR CA150225006Shield · leaking(CAN) DURING DAILY INSPECTION, NOTICED THAT THE HANGER BEARING ASSEMBLY GREASE SHIELD WAS LEAKING. UNIT WAS REPLACED WITH SERVICEABLE, GND RUN CARRIED OUT & NO FURTHER FAULTS. ACFT RELEASED.SDR CA150121002Spider Gear · cracked(CAN) LOWER PLANETARY SPIDER ASSEMBLY PART NUMBER 205-040-785-003 FOUND CRACKED DURING ROUTINE OVERHAUL. NO KNOWN CAUSE AND NO OTHER DISCREPANCIES FOUND. PART REPLACED WITH NEW PART OF SAME PART NUMBER AND OVERHAUL OF TRANSMISSION COMPLETED.SDR CA140819004Servo · malfunctioned(CAN) WHEN PILOT CARRIED OUT START UP CHECK LIST AT IDLE, A HYDRAULIC SYSTEMS CHECK WAS CARRIED OUT. SYSTEM 2 WAS CLOSED AND CONTROLS FUCTIONED PROPERLY. SYSTEM 2 WAS TURNED ON AND SYSTEM 1 WAS CLOSED. THE COLLECTIVE BEGAN TO RISE SLOWLY. THE TEST WAS CARRISDR CA140428004Beam · cracked(CAN) PERFORMING A SCHEDULE INSPECTION, A VISUAL INSPECTION WAS DONE ON THE LT MAIN BEAM CAP. THE CAP WAS FOUND TO BE CRACKED COMPLETELY THREW. A NEW CAP, PN 205-030-163-095S INSTALLED.SDR CA131129010Blade · delaminated(CAN) BLADE WAS REPAIRED IN JULY 2013 TO CORRECT SOME DELAMINATION FROM AN OLDER DENT AT 18" FROM THE BLADE TIP. UPON LANDING AT A REMOTE SITE AND SHUTTING DOWN THE ACFT THE PILOT OBSERVED A BLISTER AT 6" IN DIAMETER AND AT 20 CHORDWISE CREASES OTBD OF DAMAGESDR CA130920009Diffuser · cracked(CAN) DURING A ROUTINE MAINTENANCE ACTION, A CRACK WAS DISCOVERED AROUND THE BLEED VALVE PORT. ACFT HAS BEEN REMOVED FROM SERVICE. UP-DATE: CRACK FOUND ON COMPRESSOR DIFFUSER MANIFOLD DURING DI .7500" LENGTH SPLITTING FROM BLEED AIR FITTING WELDED AREA.SDR CA131009002Blade · separated(CAN) A SUDDEN MEDIUM FREQUENCY VIBRATION WAS FELT IN FLIGHT. A PRECAUTIONARY LANDING WAS CARRIED OUT. AFTER VISUAL INSPECTION, IT WAS DISCOVERED THAT THE TIP CAP FILLER HAD SEPARATED CAUSING THE VIBRATION. BOTH BLADES WERE REPLACED, THE TAIL ROTOR WAS BALASDR CA140603003Beam · cracked(CAN) WHILE PERFORMING A DA!LY INSPECTION, IT WAS FOUND THAT THE UPPER LT MAIN BEAM CAP PORTION, EXTRUDING FROM THE ENGINE DECK, SOMETIMES REFEREED TO AS THE "INDICATOR." PORTION, WAS CRACKED. A FLIGHT PERMIT WAS ACTIVATED THROUGH TC AND THE FAA TO FLY TO A MSDR CA130813006Support · mismanufactured(CAN) UPON REMOVAL OF THE NEW SUPPORT, PN 204-011-404-125 FROM THE PACKAGING THE PART DISPLAYED THE FOLLOWING: SEVERAL AREAS WHERE MACHINING WAS NOT COMPLETE. TOOLING MARKS WERE EVIDENT IN SEVERAL AREAS. THE CASTING DISPLAYED VOIDS, POROSITY AND MATERIAL FSDR CA130705006Fitting · cracked(CAN) AME WAS PERFORMING POST FLIGHT/DAILY INSPECTION FOLLOWING LAST FLIGHT OF DAY. DURING INSPECTION, A SMALL VERTICAL LINE WAS NOTED ON THE LT LUG OF THE FITTING THROUGH WHICH THE BOLT SECURING THE TAIL ROTOR DRIVE SHAFT FLEXIBLE COUPLING ASSY TO THE F1TTINGSDR CA130627001Quill · broken(CAN) INPUT QUILL IN-FLIGHT FAILURE, FREEWHEEL UNIT FAILURE, INPUT DRIVESHAFT FAILURE, ENGINE OVERSPEED, AUTOROTATIVE LANDING.SDR CA130528009Tube · cracked(CAN) CRACKED TUBE UNDERNEATH FITTING SLEEVE, TUBE POPPED OUT OF FITTING AND BLEW OUT MOST OF FLUID.SDR CA130323001Shaft · sheared(CAN) STARTER GENERATOR FAILED TO TURN OVER ENGINE FOR START. INSPECTION REVEALED THE SHAFT HAD SHEARED.SDR CA120912012Blade · damaged(CAN) MAIN ROTOR BLADE CRACKED FROM L/E TO T/E UPPER AND LOWER SURFACE AT APPROXIMATELY 77" FROM BLADE TIP. ACFT LANDED SAFELY, MAIN ROTOR BLADE INTACT AS 1 PIECE. BLADE WAS REPAIRED IN 2004 APPROXIMATELY 319 HOURS AGO.SDR CA120817001Longeron · cracked(CAN) TOP LT LONGERON ON ACFT LOCATED IN AFT COMPARTMENT WAS CRACKED BEHIND DOUBLER ON TOP LT TAILBOOM ATTACHMENT. CRACK WAS FOUND DURING DAILY INSPECTION, MACHINE WAS FLOWN TO ACFT SERVICE CENTER WERE LONGERON WAS REPLACED.SDR CA120629008Bearing · damaged(CAN) DEBRIS, METAL, FOUND ON ENGINE CHIP DETECTOR. 7.7 HRS LATER DEBRIS WAS FOUND AGAIN ON ENGINE CHIP DETECTOR. 1 HR AFTER ENGINE WAS REMOVED FROM ACFT DUE TO MORE METAL FOUND ON ENGINE CHIP DETECTOR. ENGINE INSPECTED AND FOUND NR 1 BEARING AND RACES TO BESDR CA120629007Nut · damaged(CAN) DEBRIS, METAL, FOUND ON ENGINE CHIP DETECTOR. 7.7 HRS LATER DEBRIS WAS FOUND AGAIN ON ENGINE CHIP DETECTOR. 1 HR AFTER ENGINE WAS REMOVED FROM ACFT DUE TO MORE METAL FOUND ON ENGINE CHIP DETECTOR. DURING INSPECTION INTO METAL GENERATION BY ENGINES THESDR CA120817004Tachometer · failed(CAN) CO-PILOT DUAL TACH N2 ENGINE RPM NEEDLE, FLUCUATES FROM 0 TO 50 PERCENT THEN STICKS.SDR CA120223006Cap · fractured(CAN) FAILURE OF CAP, IN ORDER TO EXAMINE THE FRACTURE SURFACE OF A STRUCTURAL LONGERON, HERE-IN REFERRED TO AS A CAP. THE CAP, PN 205-030-207-005 AND THE ASSOCIATED TAILBOOM ATTACHMENT FITTING, PN 205-030-767-005, WERE SUBSEQUENTLY SENT TO FOR EXAMINATION ANDSDR CA120116003Gimbal Ring · damaged(CAN) DURING 100 HRS INSPECTION, 2 SMALL DAMAGED SCREWS WHERE FOUND IN THE BOTTOM OF THE MAIN TRANSMISSION BAY STILL ATTACHED WITH LOCKING WIRE. FURTHER INSPECTION REVEALED THAT THE SCREW BELONGED TO 1 OF THE 4 SWASHPLATE GIMBAL RING ATTACHEMENT POINTS. SWASSDR CA111220005Blade · cracked(CAN) 3 CRACKS DEVELOPED ON BOTTOM SIDE OF BLADE SKIN, PN 212-015-501-115, SN A6009 (TSN) 3521.9, 1 CRACK 5.5", THE OTHER 2 CRACKS ARE 2.5" - 3.5" RESPECTIVELY. MEASURING FROM TRIM TAB EDGE INBD 41.5" IS THE LONG, 5.5. THE OTHER 2 CRACKS ARE OTBD A FEW INCHESDR CA110909011Governor · failed(CAN) ACFT LEVELED OFF AFTER CLIMB, A BANG WAS HEARD THEN ACFT YAWED, ROTOR LOW HORN AND LIGHT SOUNDED. ENGINE FAILURE WAS CONFIRMED- N1 WAS AT 25 PERCENT AND TORQUE WAS READING 0. ACFT AUTOROTATED TO GROUND. FUEL CELLS AND AIRFRAME FILTER ON BOARD INSPECTESDR CA110726007Channel · mismanufacturedNEW PART DOES NOT FIT ACFT OR FIXTURE PLATE. MANUFACTURED .040 TOO WIDE.SDR CA110711020Coupling · failedTHE PILOT NOTICED A SLIGHT YAW AS HE WAS TOUCHING DOWN. HE ALSO NOTICED THAT WHEN WHEN APPLYING COLLECTIVE TO TAKEOFF, THERE WAS NO RESPONSE FROM THE PEDALS. THE AIRCRAFT WAS SHUTDOWN AND AS IT WAS WINDING DOWN, A LOUD GRINDING NOISE WAS HEARD COMING FROM THSDR CA111222011Diffuser · used(CAN) UPON LANDING AND PERFORMING A POST FLIGHT VISUAL INSPECTION THE AME FOUND THE BOTTOM STRUT ON THE EXHAUST DIFFUSER CRACKED WITH A SECTION OF MATERIAL MISSING. THE EXHAUST DIFFUSER SERVES AS THE REAR BEARING SUPPORT. AS A RESULT OF THIS DEFECT THE POWERSDR CA101122028Baffle · detachedBAFFLE DIVIDING FORWARD AND AFT SECTIONS OF FUEL CELL, FOUND DETACHED. FUEL IS ABLE TO MOVE AROUND POTENTIALLY CAUSING C OF G ISSUES. IN LOW FUEL SITUATIONS, SLOSHING FUEL MAY CAUSE SUPPLY TO THE PUMPS TO DIMINISH, POTENTIALLY CAUSING ENGINE FUEL STARVATION. SDR CA100901007Beam · crackedTHE ACA HOLDER WAS DOING HIS DAILY PREFLIGHT WHEN HE NOTICED 2 BLACK LINES THAT APPEARED TO BE CRACKS. THE ACA HOLDER LOOKED CLOSER AND FOUND THE TRANSMISSION 5TH MOUNT FITTING BEAM WAS CRACKED ON THE BOTTOM OF THE BEAM, WHERE THE 5TH RUBBER MOUNT IS LOCATED.SDR H4QA2010F00111Housing · crackedCOMBUSTION CHAMBER HOUSING FOUND CRACKED 8 INCHES LONG FROM (LOOKING FORWARD) 12:30-2:30 POSITION. CRACK WAS FOUND AFTER SHUTDOWN DURING DAILY INSPECTION BY MECHANIC. NO IRREGULAR INDICATIONS OR PERFORMANCE DURING FLIGHT WAS NOTICED OR EMERGENCY ACTIONS WERESDR CA091120005Igniter · failed(CAN) FOUND IGNITER PLUG 1 OF 4 INSTALLED, FAILED CAUSED BY IGNITER INTERIOR CATHODE BECOMING LOOSE.SDR CA091120004Igniter · failed(CAN) FOUND IGNITER PLUG , 2 OF 4 INSTALLED FAILED CAUSED BY IGNITER INTERIOR CATHODE BECOMING LOOSE.SDR CA091109002Boot · separated(CAN) DURING THE 12 MONTH INSP AND RE-GREASE OF THE INPUT DRIVE SHAFT, IT WAS DISCOVERED THAT THE INNER DIAMETER OF THE BOOT HAD COMPLETELY SEPERATED FROM THE RING IT IS SUPPOSED TO BE GLUED TO. GREASE WAS FOUND BETWEEN THE BOOT AND THE RING WHICH SHOWS THE AISDR CA091006004Shaft · worn(CAN) WHILE FLYING THE PILOT HAD A CAUTION LIGHT. IT WAS THE FUEL PUMP CAUTION LIGHT THAT HAD ILLUMINATED. THE PILOT LANDED AS SOON AS PRACTICAL. THE ENG FUEL CONTROL WAS REMOVED TO CORRECT THE DEFECT. A LITTLE HISTORY OF THE FUEL CONTROL . THE FUEL CONTROL WSDR CA090818006Bolt · brokenWHILE THE ENGINEER WAS CARRYING OUT A DAILY INSP, FOUND HALF A BOLT WITH NUT ATTACHED ON ENG DECK. FURTHER INVESTIGATION REVEALED THAT BOLT (ONE OF TWO) WAS PART OF THE ATTACHMENT OF THE PILLOW BLOCK ASSY TO THE ENG BIPOD MOUNT ASSY. PART OF THE BOLT APPEARESDR CA090806005Governor · unknownEXCESSIVE ENGINE DROOP.SDR CA090702013Fitting · crackedDURING A POST FLIGHT INSP, THE TAIL ROTOR DRIVE FITTING WAS FOUND CRACKED. TIME ON THE FITTING IS UNKNOWN. CRACK WAS FOUND RADIATING FROM THE BORE OF THE BARREL NUT ATTACHMENT. UNSURE IT THIS MAYBE THE CAUSE OF OVER TORQUING OF THE BOLT. NUT WAS REPLACED W
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