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 CA090619003Quill Assy · shearedACFT WOULD NOT START, UPON FURTHER INVESTIGATION THE QUILL DRIVE FROM STARTER/GENERATOR TO ENGINE FOUND SHEARED.SDR CA090626008Drive Shaft · damagedNR 1 TAIL ROTOR DRIVESHAFT CONTACTED COVER CAUSING DAMAGE TO SHAFT.SDR CA090424002Support · cracked(CAN) FOUND BEARING SUPPORT ATTACHEMENT BOLT HOLE CRACKED.SDR CA090126003O-Ring · leaking(CAN) REPORTS OF A LOW FUEL CAUTION LIGHT COMING ON EARLY AND SMALL FUEL DRIP PROMPTED MX TO REMOVE THE LT FUEL CELL SUMP PLATE TO INSPECT THE LOW LEVEL FUEL SWITCH/BOOST PUMP AREA AND FACILITATE AN O-RING REPLACEMENT. UPON REMOVAL OF THE SUMP PLATE A T-SHIRT/SDR CA090119010Bearing · dirtyINTERMEDIATE GEARBOX RECEIVED TO INVESTIGATE HIGH ROTATIONAL FORCE TO TURN INPUT PINION. MEASURED TO BE 50 INCH POUNDS. THIS GEARBOX WAS INSTALLED ON AIRCRAFT IN 1995 AND UNTIL NOVEMBER OF 2008 HAD NEVER BEEN REMOVED. DISASSEMBLED GEARBOX AND FOUND AND ACCUSDR CA090116001Ring · out of positionWHILE WORKING ON THE AIRCRAFT IN THE HANGAR, IT WAS DISCOVERED THAT THE RT SLIDING DOOR WOULD ONLY OPEN APPROX SIX INCHES. IT WAS FOUND THAT ONE OF THE UPPER "D" RINGS ON THE RIGHT REAR BULKHEAD HAD ROTATED (PROBABLY WHEN THE CARGO NET WAS REMOVED FOR MAINTENSDR CA080811004Tuning Unit · cracked(CAN) TUBE ASSY WAS REPLACED EARLIER IN APRIL 2008 DURING WINTER MAINT. SINCE SINGLE HYDR SYS PARTS ARE HARD TO FIND ITEMS, SERVICEABLE PART WAS INSTALLED WITH APPROPRIATE CERTIFICATION. VISUAL INSP DIDN`T REVEALED ANY DAMAGE AND NO LEAK WAS NOTICED AT THIS TISDR CA080731002Bearing · rough(CAN) UPON A SCHEDULED INSPECTION OF THE TRANSMISSION WAFFER FILTER AN EXCESSIVE AMOUNT OF FERROUS METAL WAS FOUND. THERE HAD BEEN NO METAL FOUND ON THE CHIP DETECTOR OR IN THE COURSE INLET SCREEN. A SWEEP OF THE SUMP WITH A MAGNET FOUND NO METAL. AFTER DISSASSDR CA081023005Fitting · cracked(CAN) WHILE CONDUCTING 100 HR INSP NOTED AREA IN LT LOWER TAIL BOOM LONGERON AT FWD FITTING TO BE CRACKED. NDT CONFIRMED A CRACK INDCATION OF 1.5 INCHES LONG IN THE FITTING.SDR CA080722001Bearing · damaged(CAN) UPON DESCENT WITH AN EXTERNAL LOAD, MASTER CAUTION WARNING INDICATION ILLUMINATED. THE PIC CHECKED THE CAUTION PANEL TO FIND A TRANSMISSION OIL PRESSURE CAUTION LIGHT ILLUMINATED, TRANSMISSION OIL PRESSURE GAUGE INDICATING ZERO PRESSURE. A POST-SHUTDOWN SDR CA080718001Bearing · damaged(CAN) DURING HELI-PORTABLE SEISMIC DRILLING OPS, UPON DESCENT WITH AN EXTERNAL LOAD, THE MASTER CAUTION WARNING INDICATION ILLUMINATED. THE PIC CHECKED THE CAUTION PANEL TO FIND A TRANSMISSION OIL PRESSURE CAUTION LIGHT ILLUMINATED AND THE TRANSMISSION OIL PRESDR CA080710006Beam · cracked(CAN) DURING INSPECTION, NOTICED A CRACK ON THE LT MAIN BEAM CAP UPPER WEB NEAR THE FORWARD ENGINE FIRE WALL. THE ACFT WAS GROUNDED. THE AIRFRAME TIME 15185 HOURS. THE TIME ON THE MAIN BEAM CAP IS UNKNOWN.SDR CA080614001Line · leaking(CAN) THE PILOT WAS FLYING THE HELICOPTER WHEN THE COLLECTIVE BECAME STIFF TO MOVE. THE PILOT RELEASED THE LOAD AND NR 2 HYDR SYS HAD FAILED. THE PILOT LANDED THE ACFT. IT WAS FOUND THAT NR 2 HYD SYS HAD LOST ALL IT`S FLUID DUE TO A HYDRAULIC LINE HAD CHAFED TSDR CA080604011Attach Fitting · cracked(CAN) WHILE CONDUCTING A 25 HR INSP, A CRACK WAS NOTED ON THE LIFT LINK BEAM LUG. THE PART WAS REMOVED AND TT OF THE BEAM IS UNKNOWN AT THIS TIME. CRACK WAS FOUND ON THE AFT EAR OF LUG RT SIDE.SDR CA080523002Bolt · broken(CAN) WHILE PERFORMING ADI, AME DISCOVERED THAT A STAB BAR DAMPER TUBE ASSY P/N: 204-010-925-009 AND A DAMPER LEVER P/N: 212-010-301-001 WERE MISSING. IT APPEARS THAT THE TUBE ASSY UPPER BOLT P/N: AN174-20 BROKE OFF FIRST AND WAS THE CONTRIBUTING FACTOR OF THESDR CA080409005Circuit Breaker · inoperative(CAN) WHILE DOING A PREFLIGHT CHECK DURING FLIGHT TRAINING IT WAS NOTED THAT THE LT BOOST PUMP CIRCUIT BREAKER WAS NOT ABLE TO BE CYCLED. THE CIRCUIT BREAKER WAS REMOVED AND REPLACED. AFTER GOING THROUGH THE REST OF THE CIRCUIT BREAKER PANEL IS WAS NOTED THAT SDR CA080326001Wire · chafed(CAN) DURING START UP THE STARTER RELAY CIRCUIT BREAKER WAS POPPING NOT ALLOWING THE STARTER TO START. IT WAS FOUND THAT THERE WERE 2 WIRES LABELED K2D20 AND K3C20 CHAFFED INSIDE THE CO-PILOTS COLLECTIVE. K3C20 HAD BEEN SOLDER SPLICED AND CHAFED AT THE SPLICESDR CA080124003Crosstube · cracked(CAN) WHILE THE ENGINEER WAS CONDUCTING THE DI, A CRACK IN THE AFT DART CROSSTUBE WAS DISCOVERED. THE DART CROSSTUBE FOLLOWS 300/600 HR INSP CYCLE. CROSSTUBE WAS 60.7 FROM 300 HR INSP, AND 360.7 FROM THE 600 HR. CROSSTUBE WAS CHECKED FOR EXCESSIVE DEFLECTION, SDR CA080117002Bearing · unserviceable(CAN) FOUND TAIL ROTOR HUB ASSY OB BEARING CAGE INSERT OUT OF IS SOCKET. ASSY SEND FOR O/H. (TC NR 20080117002)SDR CA080111004Blade · delaminated(CAN) PILOT HEARD A MUFFED LOW POP SOUND, WITH NO UNUSUAL GAUGE, WARNING LIGHTS, OR VIBRATIONS. UPON DEPARTING FOR ANOTHER SKI RUN THE PILOT AGAIN NOTED AN UNUSUAL NOISE. AC WAS LANDED, AN EXTERIOR INSP WAS CONDUCTED. IT WAS THEN THAT THE DELAMINATING OF T/R SDR CA080128006Bearing · making metal(CAN) TSO OF THE TRANSMISSION ASSY 1186.6 HOURS. THE AC HAD TAKEN OFF AND WAS IN CRUISE WHEN A TRANSMISSION METAL DETECTOR LIGHT ILLUMINATED. THE PILOT LANDED AC BACK AT CAMP FOR THE ENGINEER TO INVESTIGATE THE DEFECT. THE BEARING IS AN ON CONDITION BEARING.SDR CA071214009Mount · cracked(CAN) RT ENGINE BIPOD INSPECTED FOR SUSPICIOUS CRACK IN FRONT TUBING DURING 100 HRS INSPECTION. NDT REVEALED CRACK MOUNT AT WELDED JOINT. NOTE: THIS MOUNT WAS MODIFIED IAW STC SH99-11, DART ADJUSTABLE MOUNT. (TC NR 20071214009)SDR CA071203006Mount · cracked(CAN) LT ENGINE TRIPOD AFT TUBING MOUNT FOUND CRACKED DURING 100 HRS INSPECTION JUST BELOW ENGINE MOUNTING PLATE AFT TUBE JUNCTION. NOTE: THIS MOUNT WAS MODIFIED IAW STC SH99-11, DART ADJUSTABLE MOUNT. (TC NR 20071203006)SDR CA071126011Fitting · broken(CAN) DURING THE INSPECTION OF THE LIFT LINK AREA, A CRACK WAS NOTED ON THE LIFT LINK FITTING. UPON FURTHER INVESTIGATION THE AFT EAR WAS COMPLETLY BROKEN FROM THE FITTING. THE BOLT SECURING THE LIFT LINK TO THE FITTING WAS INCORRECT FOR THAT PN OF FITTING. THSDR CA071127011Fitting · cracked(CAN) ON ROUTINE INSPECTION, A CRACK WAS NOTED IN THE LIFT LINK FITTING. TRANSMISSION WAS REMOVED AND SENT FOR REPAIR. THE TSO FOR THE COMPLETE TRANSMISSION WAS AT 785.1 AND TT 19803.1. NO AVAILABLE INFORMATION FOR TT ON THE SUMP ASSY CASE. (TC NR 20071127011)SDR CA070727003O-Ring · failed(CAN) LOST OF HYDRAULIC IN FLIGHT, EMERGENCY LANDING, FAULT FOUND IN THE ACCUMULATOR, O-RING P/N MS28775-212 REPLACED A/C GROUND RUN AND LEAK CHECK COMPLETED AND RELEASED TO SERVICE. (TC NR 20070727003)SDR CA070724005Control Lever · broken(CAN) THIS IS THE INITIAL REPORT. INFORMATION NOT HERE YET. THE PILOT COULD ONLY GET 92 PERCENT NR RP, LANDED THE AIRCRAFT NO INCIDENT, AFTER SHUTDOWN THE ENGINEER OPENED THE GOVERNOR SIDE ENGINE COWLING AND FOUND THE THE GOVERNOR LEVER BROKEN BOTH ENDS OF THESDR CA070807005Connector · burned(CAN) TRAINING FLIGHT, NOTICED SMOKE COMING UP FROM CENTER CONSOLE BEHIND VHF NR 2 RADIO. PUT DOWN, A/C ON GROUND. CO-PILOT JUMPED OUT TO CHECK IN BATT COMPARTMENT. NO ANOMALIES FOUND. FORCE TRIM CB POPPED. CARGO RELEASE LIGHT CAME ON AND STAYED ON. VHF RADISDR CA070720007Bearing · spalled(CAN) THIS PN BEARING IS A (ON CONDITION) PART. THE MAST WAS LAST OVERHAULED 2210.4 HOURS AGO. THE ENGINEER FOUND FERROUS METAL IN THE TRANSMISSION INTERNAL AND EXTERNAL FILTERS. A POWDER OR PASTE WAS FOUND ON THE TRANSMISSION CHIP DETECTOR, NOT ENOUGH TO ACTISDR CA080204006Wire · shorted(CAN) PILOT REPORTED SPARKS AND A SMALL AMOUNT OF SMOKE FROM THE OVERHEAD CONSOL. UPON INVESTIGATION IT WAS FOUND THAT THE LT OVERHEAD CONSOL PANEL HAD CHAFED THROUGH SEVERAL WIRES COMING UP THE CENTER POST OF THE WINDSHIELD CAUSING THE WIRES TO SHORT TO GROUNSDR CA070524001Pump · failed(CAN) DURING HELI-PORTABLE SEISMIC DRILLING OPERATIONS, UPON DESCENT WITH AN EXTERNAL LOAD: THE MASTER CAUTION WARNING INDICATION WAS ILLUMINATED. THE LOAD WAS SET AND RELEASED. THE CAUTION PANEL OBSERVED TO REVEAL THAT THE ENGINE DRIVEN FUEL PUMP WARNING LIGSDR CA070412004Governor · damaged(CAN) DURING THE DAILY INSPECTION PERFORMED BY THE ENGINEER, THE SCREW HOLDING THE GOV SERVO LEVER PLATE IN PLACE WAS ENTIRELY BACKED OUT OF THE HOLE. THIS PART HAD BEEN REPLACED, TESTED AND ADJUSTED AT TSN 2346.3 FOR LOOSE SCREWS. THE SCREWS ARE STAKED IN PSDR CA070418003Mount · cracked(CAN) ENGINE MOUNT WAS INSTALLED NEW IAW STC SH99-11. POWER PLANT WAS ALIGNED IAW MM SUPPLEMENT. THE MM SUPPLEMENT INCLUDES AN INSP EVERY 100 HRS OR ANNUALLY. NOTE TO INSPECT ENGINE MOUNTS FOR CRACKS, DAMAGE, CORROSION AND SECURITY. THE CRACK STARTED BELOW THSDR CA070321008Beam · cracked(CAN) WEB P/N 205-030-163-395 FOUND CRACKED AT INDUCTION BAFFLE SUPPORT WL 80.13. THE CRACK WAS APPROX 1 INCH IN LENGTH AND .5 INCH DOWN . REPAIR SCHEME IN PROGRESS THROUGH MFG. (TC NR 20070321008)SDR CA070126007Fitting · cracked(CAN) DURING AIRFRAME INSPECTION, A CRACK WAS FOUND ON LONGERON P/N 205-030-207-005 UNDER FITTING P/N 205-030-767-005. FITTING REMOVED, INSPECTED FOUND TO BE CRACKED AT AFT SIDE OF BOLT LOCATION. CRACKS IN FITTING P/N 205-030-767-005 NOT FOUND UNTIL REMOVAL OFSDR CA071210002Mount · sheared(CAN) DURING ROUTINE POST FLIGHT DAILY INSP, (3) OF THE (4) AN4H6A BOLTS THAT ATTACH THE TRANSMISSION AFT (5TH) MOUNT TO THE AIRFRAME FITTING ASSY WERE FOUND SHEARED OFF. FLIGHT OPERATION WERE NOT AFFECTED AND CONSIDERED TO BE NORMAL AT THE TIME. THE MOUNT ANDSDR CA061124010Case · cracked(CAN) CRACKING AT INPUT QUILL BOSS OF MAIN ROTOR TRANSMISSION. (TC NR 20061124010)SDR 2006FA0001088Adapter · damagedDURING INSPECTION AND REGREASE OF THE M/R TRANS DRIVE SHAFT, A CHECK OF THE TORQUE OF THE DRIVE SHAFT ADAPTOR BOLT WAS ACCOMPLISHED AND IT WAS DISCOVERED THAT THERE WAS NO TORQUE, THAT THE BREAKER BAR`S WEIGHT BROKE THE BOLT LOOSE, REMOVED THE ADAPTOR AND FOUNSDR CA070228005Blade · missing(CAN) VIBRATION ON OIL COOLER BLOWER, FURTHER INVESTIGATION REVEALED ONE BLADE MISSING. SERVICEABLE OIL COOLER BLOWER INSTALLED, A/C RETURNED TO SERVICE. (TC NR 20070228005)SDR CA060907005Actuator · failed(CAN) DURING LONG LINE SLINGING OPERATIONS, UPON APPROACHING A DROP ZONE WITH A LOAD. THE COLLECTIVE WAS RAISED TO CUSHION LANDING OF THE LOAD, THEN LOWERED TO TAKE TENSION OFF OF THE LINE. THE HELICOPTER TURNED TO THE LT AND THE RT TAIL ROTOR PEDAL WAS FOUND SDR CA060727001Nut · cracked(CAN) THIS IS AN ON CONDITION ITEM. SO HISTORY MAY NOT BE ACCURATE. M/R HUB ASSY HAS 18437.6 TIME SINCE NEW. M/R HEAD ASSY WAS IN FOR O/H AND REQUIRES ACORN NUTS TO BE NDT. THIS ONE WAS FOUND CRACKED. (TC NR 20060727001)SDR CA060728003Bearing · failed(CAN) THE TAIL ROTOR DRIVESHAFT HANGER HAD BEEN INSTALLED THE NIGHT BEFORE THE FAILURE. WE SUSPECT AN INNER COUPLING FAILURE. THE SUSPECT COUPLING HAD BEEN RECOATED JUST BEFORE INSTALLATION BY USING AN AMS2451/4 PROCESS. (TC NR 20060728003)SDR CA060706002Blade · cracked(CAN) CRACK ON BOTH SIDES OF BLADE BOLT BORE. TRAVELLING IN CHORDWISE DIRECTION. THE LEADING EDGE CRACK TRAVELS RIGHT TO THE LEADING EDGE AND THE TRAILING EDGE CRACK IS APPROXIMATLEY 6 INCHES LONG. IT APPEARS ALL DOUBLERS ON THE LOWER PART OF THE BLADE ARE SDR CA060622005Cable · melted(CAN) DURING TURN AROUND CHECK BY THE AME, THE WIRES TO THE STARTER GENERATOR WERE FOUND TO BE SUBJECTED TO HEAT DAMAGE. THERE WAS NO INDICATION TO THE PILOT OF ANY DEFECT. FURTHER INVESTIGATION FOUND THE STARTER GENERATOR WIRE BUNDLE BELOW THE ENGINE DECK SDR CA060602004Drag Brace · cracked(CAN) THE DRAG BRACE WAS IN THE COMPONENT SHOP GETTING ITS 1200 HR INSPECTION/24 MONTH INSPECTION. THE DRAG BRACE ASSEMBLY WAS PREPARED FOR NDT MAGNETIC PARTICLE INSPECTION. THE NDT SHOP FOUND THIS FITTING WAS CRACKED ON THE IB CURVE. (TC NR 20060602004)SDR CA060524001Fitting · crackedAIRCRAFT WAS ON SEISMIC DRILL MOVE JOB. THE ENGINEER WAS DOING HIS DAILY INSPECTION WHEN NOTICED THAT ONE EAR OF THE LIFT LINK FITTING WAS APPEARED CRACKED. A CLOSER VISUAL LOOK CONFIRMED IT WAS CRACKED. INVESTIGATING IF THE BUSHING WAS WRONG FOR THIS INSTSDR CA060331005Saddle · crackedCRACK WAS FOUND ON SKID TUBE AT FORWARD CROSSTUBE MOUNTING SADDLE. THERE WAS NO REPORT OF A HARD LANDING WITH THIS AIRCRAFT AT THIS TIME. TIMES FOR THESE SKID TUBES WERE NOT AVAILABLE.SDR CA060315007Yoke · crackedCRACKS ORIGINATING IN ATTACHMENT BOLT HOLES.SDR CA051001001Crosstube · cracked(CAN) HIGH SKID GEAR. UPON LANDING THE FRONT CROSS TUBE CRACKED IN THE MIDDLE OF THE TUBE, BETWEEN THE MOUNTING SADDLES. FROM THE INFORMATION WE HAVE AT THIS TIME, THE AIRCRAFT WAS NOT HARD LANDED.SDR CA050924001Blade · failed(CAN) AS THE A/C WAS APPROACHING STAGING WITH A SLING LOAD, THE PILOT HEARD A LOUD BANG FOLLOWED BY A LOUD SCREECHING NOISE FROM THE ENGINE. THE A/C LANDED IMMEDIATELY WITH POWER AND THE ENGINE SHUT DOWN. UPON FURTHER INVESTIGATION, ONE OF THE COMPRESSOR FIR
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