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 = '206L3' 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 = '206L3' 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 EVCA20110511001Support Bracket · elongatedFOUND HANGER BRACKET HOLE ELONGATED ON TAILBOOM.SDR RMXA2186Connector · failedTOT OVERTEMP LIGHT ILLUMINATED WHEN BATTERY TURNED ON. REPAIRED WIRE IN CONNECTOR PLUG.SDR EOPA033011346ALStiffener · crackedCRACK IN STIFFENER NEAR TOP OF "BROOM CLOSET".SDR HEEA130833Bearing · spalledENGINE RMEOVED DUE TO HIGH CYCLED WHEELS. UPON INSP OF NR 5 BEARING FOUND SPALLING AT OUTER RACE SPLIT. SCRAPPED PART AND REPLACED WITH NEW.SDR EVCAJH031811Structure · corrodedCORROSION FOUND IN THE LOWER TUB UNDER THE FUEL TRANSFER TUBE.SDR EVCA00015Frame · crackedMECHANIC FOUND CRACK ON THE STA 155, BULKHEAD FRAME DURING A ROUTINE INSP.SDR RMXA20110217001Transmission · making metalWHILE DRAINING OIL FROM MAIN TRANSMISSION TO REPLACE THE FREEWHEELING UNIT FOR OVERHAUL,A METALLIC PIECE WAS FOUND AT THE DRAIN PORT. PREVIOUSLY THIS TRANSMISSION HAD CHIP LIGHTS AND THE SERVICEABILITY CHECKS REQUIRED BY THE MANUFACTURES MAINTENANCE MANUAL WESDR YTRA20101219001Shaft · crackedDURING ROUTINE MAINTENANCE & INSPECTION THE DRIVE SHAFT WAS FOUND TO BE CRACKED LENGTH WISE STARTING FROM A RIVET HOLE. THE TAIL ROTOR DRIVE SHAFT ADAPTER IS ATTACHED TO THE SHAFT USING SIZ BLIND RIVETS. THE CRACK IS EXTENDING FROM THE MANUFACTURE INSTALLED SDR EOPA111410358ALFrame · crackedFRAME FOUND TO HAVE 1.5 INCH CRACK.SDR CA101109012Bearing · noisy(CAN) DURING 100 HR INSPECTION OF T/R DRIVE SHAFT/BLOWER SHAFT BEARINGS, AFT BLOWER SHAFT BEARING FOUND TO BE NOISY. BEARING REMOVED AND INSPECTED AND FOUND TO BE ROUGH. FURTHER INSPECTION REVEALED BEARING HAD BEEN REPLACED NEW AT PREVIOUS 100 HR. BEARING RSDR EVCA00008Clevis Bolt · damagedPILOT REPORTED VIBRATION TO MECHANIC. MECHANIC INVESTIGATED AND FOUND PLAY IN RED LOWER PITCH CHANGE LINK CLEVIS. UPON DISASSY, MECHANIC FOUND BOLT AND CLEVIS SEVERLY DAMAGED. MECHANIC R & R BOLT AND CLEVIS.SDR 2010FA0000514Tach Generator · malfunctionedHYD PRESSURE FAILURE IN FLIGHT, ACCOMPANIED BY LOSS OF ROTOR TACH NEEDLE (WENT TO ZERO) AND LOW ROTOR RPM CAUTION LIGHT ILLUMINATION.SDR EVCA00005Fitting · crackedUPPER LT ATTACHMENT FITTING FOUND CRACKED DURING INSPECTION OF TAILBOOM. UPPER LT ATTACHMENT FITTING IAW ASB 206L-09-158. UPPER LT ATTACHMENT FITTING R & R.SDR CA091211005Attach Fitting · cracked(CAN) TAILBOOM-SIDE LOWER LT ATTACHMENT FITTING FOUND CRACKED DURING ANNUAL INSP. FITTING CRACKED THROUGH 2 RIVET HOLES TO EDGE. PHOTO ATTACHED. RECENT AD CF-2009-41 AND RELATED ASB IDENTIFY FUSELAGE-SIDE UPPER LT TAILBOOM ATTACHMENT FITTING AS PROBLEM AREA.SDR 2009F00106Thrust Washer · flakingAFTER MAIN ROTOR BLADE CHANGE, DURING TRACK AND BALANCE, ROTOR SYS WOULD NOT RESPOND TO NORMAL CORRECTIONS. REMOVED ROTOR HEAD AND DISASSEMBLED TRUNION ASSY, FOUND "THRUST WASHER" FACE FLAKING OFF AND EFFECTING CENTERING. REPLACED THRUST WASHER AND RE-CENTERSDR HEEA126213Fitting · crackedFOUND CRACK DURING ASB 206L-09-158 INSPECTION. REPLACED FITTING. NOTE: PREVIOUSLY SUBMITTED ON 10/15/09.SDR HEEA126111Control Tube · crackedCORROSION AND CRACKS ON CONTROL TUBE, NEXT TO END AT FIXED CLEVIS. SCRAPPED CONTROL TUBE. NOTE: PREVIOUSLY SUBMITTED ON 10/6/09.SDR HEEA126112Structure · corrodedEXCESSIVE CORROSION ON TOP CENTER SURFACE OF HORIZONTAL STABILIZER ASSY. SENT TO VENDOR FOR REPAIR. NOTE: PREVIOUSLY SUBMITTED ON 10/6/09.SDR HEEA126113Structure · corrodedCORROSION AND CRACKS ON LT STABILIZER SPAR TUBE. SENT TO VENDOR FOR REPAIR. NOTE: PREVIOUSLY SUBMITTED ON 10/6/09.SDR CA090706005Blade · debondedM/R BLADE UPPER SKIN DEBONDED AT BLADE TIP AT STA 218.07 AREA OF DAMAGE 1 INCH BY INCH.SDR B4S2009F00000Attach Fitting · crackedDURING THE 100 HOUR INSPECTION, WHILE COMPLETING STEP 13A OF THE AFT FUSELAGE/TAILBOOM AREA SECTION OF 05-11, THE UPPER LT ATTACH FITTING WAS SUSPECTED OF BEING CRACKED. THE PAINT WAS REMOVED FROM THE FITTING AND THE AREA SUBJECTED TO DYE-PENETRANT INSPECTIOSDR CA090505002Support · cracked(CAN) WHILE CARRYING OUT A POST LEASE INSP, THE ENGINEER NOTICED A CRACK IN THE PAINT ON THE SUPPORT, UPPER LT FOR THE HORIZONTAL FIN ASSY. HE REMOVED THE SUPPORT TO VERIFY THAT IS WAS A CRACK, ON THE BACK SIDE OF THE SUPPORT THE CRACK SHOWED THROUGH. THE CRACSDR 2009FA0000339Blade · debondedTHE AERODYNAMIC FILLER THAT IS USED TO MAINTAIN CONTOUR OF MAIN ROTOR BLADE BETWEEN L/E AND BLADE SKIN WAS FOUND TO LIFTING OR DEBONDING DURING A ROUTINE 100 HR INSP IAW MFG INSP PROGRAM. AREA THAT WAS LIFTING WAS AT APPROX 55 INCHES X 57 INCHES FROM ROOT OF SDR 2009FA0000313Pump · failedLOSS OF HYDR POWER WHILE IN FLIGHT. ALSO ROTOR TACH WENT TO ZERO. LOW ROTOR CAUTION LIGHT CAME ON AND HORN SOUNDED.SDR EVCA 2009/03/30Blade · crackedDURING POST FLIGHT INSPECTION, PILOT DISCOVERED A CRACK IN A MAIN ROTOR BLADE STARTING AT THE TRAILING EDGE AND CONTINUING FORWARD TO THE SPAR.SDR 2009FA0000093Valve · failedCUTOFF VALVE ASSY FAILED. THE EPOXY BOND THAT RETAINS THE END CAP IN THE VALVE FAILED. THEN FUEL PRESSURE WAS PRESENT IN THE VALVE ASSY THE PRESSURE WOULD PUSH THE END CAP PARTIALLY OUT OF THE VALVE ASSY. THIS EFFECTIVELY INCREASED THE LENGTH OF THE VALVE. SDR CA081229003Governor · failed(CAN) PILOT ENCOUNTERED HIGH SIDE GOVERNOR FAILURE. TORQUE INCREASED FROM 85 TO 100 PERCENT DURING CLIMB WITH NO COLLECTIVE INPUT. NR/N2 INCREASED TO 110 PERCENT AND THROTTLE WAS ROLLED TO IDLE WITH NO INITIAL EFFECT. NR/N2 THEN DROPPED TO 90 PERCENT. A DESDR YTRR2008121880114Blade · damagedON POST FLIGHT INSP, PILOT FOUND BOTH MAIN ROTOR BLADES HAD EVIDENCE OF IMPACT DAMAGE. FURTHER INSP REVEALED THAT BOTH MAIN ROTOR BLADES HAD CONTACTED THE WINGLETS ON THE HORIZ STABILIZER. THE PILOT REPORTED THAT IN CRUISE FLIGHT HE ENCOUNTERED SOME TURBULENCESDR 2008FA0000897Bolt · debondedMAIN ROTOR BLADE BOLT LWR PLUG, PN 206-011-137-001, FELL OUT ON ENG SHUTDOWN WHEN ROTOR RPM DROPPED BELOW 40 PERCENT. THIS ALLOWED LEAD BALANCE WEIGHTS TO ALSO FALL OUT OF BOLT. THIS PLUG IS BONDED INTO THE BOLT AT MFG AND APPEARS TO NOT HAVE HAD ADEQUATE ADHESDR AC2A2008120579692Throttle Cable · brokenENGINE WOULD NOT RESPOND TO THROTTLE INPUTS. SUSPECT A BROKEN THROTTLE CABLE.SDR 2008FA0000858Exciter · intermittentENGINE HAD AN INTERMITTENT DELAYED LIGHTOFF CAUSING HOT STARTS. REPLACING THE IGNITION EXCITER CORRECTED THE PROBLEM. THE DEFECTIVE EXCITER WAS FOUND TO HAVE A LOOSE STUD WHERE THE INPUT VOLTAGE IS APPLIED. SUSPECT THIS WAS CAUSING A LOW OUTPUT VOLTAGE. IT SDR CA081216002Frame · cracked(CAN) UPON REMOVAL OF BELL INSTALLED HEATER ASSY. A VISUAL INSPECTION WAS COMPLETED OF THE AREA`S SURROUNDING STRUCTURE. THE LT AFT FRAME ASSY WAS FOUND CRACKED BEYOND LIMITS. THE CRACK WAS NOTED TO PROTRUDE FROM A RIVET HOLE ACROSS THE FACE OF THE FRAME. SDR CA081216001Frame · cracked(CAN) UPON REMOVAL OF AFT CABIN HAT RACK ASSY RT FRAME ASSY WAS FOUND CRACKED. FRAME ASSY WAS REMOVED AND REPLACED NEW.SDR CA081031001Coupling · cracked(CAN) DURING A SHEDULED 100/300 HR INSP OF THE FWD T/R DRIVESHAFT SEGMENT THOMAS COUPLINGS, THE FWD THOMAS COUPLING WAS FOUND CRACKED. UPON FURTHER DISSASSEMBLY ONLY ONE OF THE LAMIATES WAS FOUND CRACKED. THE COUPLING WAS REMOVED FROM SERVICE AND REPLACED NEW.SDR QMLA1027200808047Rheostat · burnedPILOTS REPORT, THE AIRCRAFT LANDED AT EMMETSBURG HOSPITAL AS PART OF THE ORIENTATION TRAINING FOR NEW PILOT. THE ENGINES WENT TO IDLE AND THE PILOT GOT OUT OF THE AIRCRAFT TO TALK TO THE POLICEMAN SECURING THE LZ. WHEN THE PILOT GOT BACK IN THE AIRCRAFT, SMOSDR CA081001004Fitting · cracked(CAN) UPPER LT TAILBOOM ATTACHMENT FITTING ON THE FUSELAGE SIDE FOUND CRACKED FROM THE RIVET HOLES.SDR AC2A2008090878102Unknown · unknownDEPARTED AIRPORT AT 0951 WITH VFR CONDITIONS, CLEAR SKIES 12 MILES VISIBILITY. 1.5 MILES SOUTHWEST AT AN ALTITUDE OF 500 FT AND CLIMBING, HEARD A LOUD REPORT ASSOCIATED WITH A HARD RT YAW AND NR DECREASING THROUGH 92 PERCENT. HAD JUST PASSED OVER A CLEAR AREASDR 2008FA0000337Rod · chafedDURING AN INSPECTION THE THE TAIL ROTOR PITCH CONTROL TUBE SLEEVES, WE DISCOVERED THAT BELLCRANK PN 206-001-763-001 HAD BEEN CHAFED INTO BY THE RIVET SECURING THE ROD END OF ROD ASSEMBLY PN 206-011-725-001. THIS WEAR OCCURS WHEN LEVER ASSEMBLY PN 206-011-722-1SDR EHA2008F00001Chip Detector · activatedCHIP LIGHT ILLUMINATED, PILOT LANDED AIRCRAFT IMMEDIATELY. INSPECTION FOUND TINY SLIVER ON CHIP PLUG, NO FURTHER FINDINGS. FOLLOWED MANY PROCEDURES. NO FURTHER PORBLEMS NOTED. (K)SDR EGI2008F00002Blade · damagedDURING SCHEDULED 100 HOUR INSP OF AC, INSP OF TAIL ROTOR BLADES REVEALED THAT ONE T/R BLADE HAD MECHANICAL DAMAGE. THE DAMAGE WAS CONFINED TO THE T/E WHICH CONSISTED OF A DENT AT T/R BLADE STA 16.5 APPROXIMATELY .010 INCH DEEP AND THE T/E BENT IN A SPAN OF APSDR 2008FA0000440Rod · chafedDURING AN INSPECTION OF THE TAIL ROTOR PITCH CONTROL TUBE SLEEVES, WE DISCOVERED THAT BELLCRANK PN 206001763001 HAD BEEN CHAFED INTO BY THE RIVET SECURING THE ROD END OF ROD ASSEMBLY PN 206011725001. THIS WEAR OCCURS WHEN LEVER ASSEMBLY PN 206011722105 PIVOT DSDR MD0519081Drive Shaft · scoredCOAX CABLE FROM ANTENNA MOUNTED ON OIL RESERVOIR COWLING SCORED THE (NR 3) TAIL ROTOR DRIVESHAFT SEGMENT.SDR EGI2008F00001Blade · damagedVISUAL INSPECTION OF M/R BLADE PRIOR TO INSTALLATION FOUND A .017 IN. DEEP DENT IN THE LOWER GRIP PLATE AT STATION 17.5. THIS M/R BLADE WAS PREVIOUSLY REMOVED IN SERVICEABLE CONDITION AND PLACED IN STOCK. COMMUNICATION WITH MFG PSE RECOMMENDS SENDING TO RBI FOSDR MD05012008Bulkhead · crackedFORWARD TAILBOOM BULKHEAD CRACKED.SDR CA080303004Disc Pack · cracked(CAN) DISC PAC WAS REMOVED FOR INSPECTION DURING A SCHEDULED 1200 HOUR INSPECTION. CRACKED DISC WAS DISCOVERED DURING DISASSEMBLY. ONE DISC OF TEN IN PAC WAS COMPLETELY CRACKED ON BOTH SIDES ON ATTACHEMENT BOLT HOLE SO THAT A PIECE OF THE DISC WAS BROKEN AWAY.SDR EVCA022308002Frame · crackedTAILBOOM ATTACH FRAME FOUND CRACKED DURING SCHEDULED INSPECTION.SDR EVCA022308001Frame · crackedTAILBOOM ATTACH FRAME FOUND CRACKED DURING SCHEDULED INSPECTION.SDR CA080211017Pump · damaged(CAN) DURING FLIGHT, AC LOST HYDRAULICS. AC LANDED SAFELY. MAINT FOUND HYDRAULICS PUMP SPLINE ROUNDED OFF. TACH GENERATOR SPLINES WORN AS WELL. (TC NR 20080211017)SDR 02082008203CGShaft · strippedWHILE ENROUTE, PILOT EXPERIENCED A HYDRAULIC FAILURE. PULLING THE CIRCUIT BREAKER HAD NO EFFECT (SYSTEM IS AUTOMATICALLY ON WHEN POWER IS REMOVED). PILOT THEN TURNED SWITCH OFF AND PROCEEDED WITH AN UNEVENTFUL LANDING. UPON INSPECTION IT WAS DETERMINED THATSDR EGI2008F00000Control Tube · shearedPILOT REPORTED TO MAINTENANCE THAT THE ELEVATOR HAD AN EXCESSIVE AMOUNT OF TRAVEL AND THE CYCLIC SEEMED TO BE SLIGHTLY STIFF FORE AND AFT. TROUBLESHOOTING PERFORMED BY MAINTENANCE AND FOUND THE ELEVATOR CONTROL TUBE SHEARED AT THE SHEAR PIN WHICH IS LOCATED I
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