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 engine_model_key = 'CF343A1' 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 engine_model_key = 'CF343A1' 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 CA120126003Indication Sys · malfunctioned(CAN) THE OPERATOR IS REPORTING ABOUT FLAME FROM THE ENGINE ON THE GROUND DURING START. IAW INITIAL INFORMATION CREW WAS PERFORMING THE ENGINE START PROCEDURE WITH PAX ON BOARD. THE ITT WAS EXCEEDING 900 C AND THE ENGINE WAS STOPPED. IAW FDR THE TEMP WAS 1080 SDR CA120118010Drain · broken(CAN) AIRSPEED INDICATOR SHOWS +450 KTS WHILE MAIN SHOWING 250 , INCREASES EXPTENTIALLY AS AIRSPEED INCREASES 2. FOUND STBY PITIOT DRAIN CRACKED AND BROKEN. 3 .REPLACED STBY PITOT DRAIN (P/N 50034-001) THE NR 3 STATIC - PRESSURE SYSTEM HAS BEEN INSPECTED SDR CA120118007Engine · vibration(CAN) IFSD AND AIR TURNBACK. ACFT WAS AT 11,000 FT WHEN RT ENGINE VIBRATION LEVEL INCREASED THEN ITT WENT TO 1100.SDR CA120109010Servo · frozen(CAN) THE FLIGHT CREW REPORTED THAT THE ELEVATOR CONTROL WAS VERY STIFF DURING THE LANDING FLARE, ALMOST LIKE HE WAS FIGHTING THE AUTOPILOT. THE CREW CONFIRMED THE AP WAS DISENGAGED. AFTER LANDING, AT THE GATE THE ELEVATOR CONTROL STILL SEEMED VERY STIFF. THSDR CA120103008Fairing · dislodged(CAN) UPON REACHING CRUISE ALTITUDE OF FL 240 EXPERIENCED PRONOUNCED BUFFETING OF AIRFRAME AT APPROXIMATELY 300 KTS. BUFFETING SUBSIDED BY 250 KTS. TRIED DIFFERENT ALTITUDES, BUT EXPERIENCED SAME EFFECT TIME AFTER TIME. NO WARNING OR CAUTION MESSAGES. ENGINE SDR CA111222002Wire · burned(CAN) NR 1 IRS FAILED AFTER TAKEOFF, RESULTING IN A BLANK SCREEN AND HEADING FLAGS. ACFT DIVERTED. TROUBLESHOOTING CARRIED OUT AND FOUND WIRE 1FP9F22BLU SHORTED TO GROUND BETWEEN JB-10 AND MFD 1. DAMAGED WIRE LOCATED BEHIND MFD 1, REPAIRED IAW ESPM 20-11-00.SDR CA111220002Bulkhead Web · cracked(CAN) WHILE PERFORMING TASK RJ2-53-280-607, MRM TASK 53-61-153, IAW REQUIREMENTS OF ADCF-2011-30, PART B, 2 CRACKS WHERE FOUND ON THE FORWARD FACE OF REAR BULKHEAD WEB AT BS 621. CRACK A WAS FOUND TO BE .400" LONG ABOUT 0.400" FROM RIVET LINE ON REL 27.5 AND SDR CA111214008Skin · cracked(CAN) DURING A ROUTINE INSPECTION, A CRACK WAS FOUND AT APPROX WS 61.0 ON THE UNDERSIDE OF THE WING. THE CRACK IS 0.75 INCHES LONG. THE CRACK STARTS AT THE EDGE OF A SMALL RIVETED PANEL & PROCEEDS INTO THE THICKER SKIN. WING PLANK 601R10046.SDR CA111209006Tube · cracked(CAN) CENTER FUEL TANK WAS FUELED TO MAX CAPACITY, 5005 POUNDS. ACFT WAS PARKED IN HANGAR & FUEL WAS NOTED TO BE DRIPPING FROM LT AFT FACE OF MLG WW FWD BULKHEAD JUST TO LT OF ACFT CTR LINE. FURTHER INVESTIGATION REVEALED THE LEAK WAS COMING THROUGH THE BACKSDR CA111205010Bpsu · failed(CAN) ON APPROACH WHEN THE FLAPS WERE SELECTED FROM 8 TO 20 DEGREES THE CREW RECEIVED A FLAP FAIL CAUTION MESSAGE. THE FLAPS STOPPED AT 10 DEGREES. THE FLAP SKEW DETECTION SYSTEM WAS RESET AND THE ACFT DISPATCHED UNDER MEL 27-02 IAW ADCF-2007-10R1. UPON RETSDR CA111202001Selector Valve · failed(CAN) DURING THE APPROACH, THE NLG FAILED TO EXTEND UPON GEAR DOWN SELECTION AND THE CREW RECEIVED A GEAR DISAGREE WARNING MESSAGE. THE GEAR SELECTOR WAS CYCLED SEVERAL TIMES WITHOUT SUCCESS. THE LANDING GEAR MANUAL RELEASE HANDLE WAS PULLED AND ALL 3 GEARS SDR CA111124004Windshield · failed(CAN) THE RT SIDE WINDSHIELD OUTER PLY CRACKED IN CRUISE FLIGHT AT FL360. FLIGHT CREW ACTIONED THE QRH AND RETURNED TO BASE. MAINTENANCE R & R THE RT SIDE WINDSHIELD IAW AMM CHAP 56-11-01.SDR CA111125002Mount · cracked(CAN) DURING ROUTINE INSPECTION, THE ENGINEER FOUND CRACKS ON BOTH LOWER LUGS OF THE NLG DOOR ACTUATOR MECHANISM BASE. THE BASE IS MOUNTED ON THE RT WALL IN THE FWD SECTION OF THE NOSE WW. THE BASE WAS REPLACED. DURING REMOVAL OF THE ACTUATOR, ONE OF THE LUSDR CA111116010Angle · cracked(CAN) CRACKS FOUND ON THE OTBD SIDE OF LT SUPPORT ANGLE IN THE LT SIDE COLLECTOR TANK BY AN AME WHEN HE WAS IN THE FUEL TANKS CARRYING OUT TASK: RJ2-28-900-750 FOR FUNCTIONAL CHECK OF COLLECTOR TANK CHECK VALVES. THE CRACKS ARE APPROXIMATELY 2.300" EMINATING SDR CA111117009Angle · cracked(CAN) WHILE CARRYING OUT TASK: RJ2-28-900-750 FOR FUNCTIONAL CHECK OF COLLECTOR TANK CHECK VALVES, CRACKS WERE FOUND ON THE OTBD SIDE OF ANGLE, PN 601R10011-14A IN THE RT SIDE COLLECTOR TANK. THE CRACKS ARE 1.495" AND 1.200" IN LENGTH AND WERE OBSERVED TO BE SDR CA111114005Selector Valve · failed(CAN) DURING THE APPROACH, THE NLG DIDN`T COME DOWN ON SELECTION. THE CREW MANAGED TO LOWERED THE GEAR AND THE ACFT LANDED WITHOUT FURTHER INCIDENT. THE LANDING GEAR RETRACTION SYS WAS DEFERRED IAW MEL 32-30-01 AND THE ACFT FLEW TO A MX BASE. THE NLG EXTENSISDR CA111111001Valve · failed(CAN) ACFT HAD A LT PACK DEFERRED. PILOT REPORTED THE RT PACK OVER PRESSURIZED ON TAKEOFF. 10TH STAGE VLV CLOSED & CREW WAS NOT ABLE TO RE-OPEN THE VLV. THE RT PACK SHUTOFF & THE AIRPLANE DEPRESSURIZED, PAX O2 MASKS WERE DROPPED & USED. THE ACFT DIVERTED, SDR CA111109001Windshield · failed(CAN) ON DESCENT INTO DESTINATION, CAPTAIN`S WINDSHIELD SHATTERED. FLIGHT CONTINUED ON INTO DESTINATION AND LANDED SAFELY. ACFT REMOVED FROM SERVICE. MX REPLACED LT WINDSHIELD IAW AMM 56-11-01 AND OPS TEST CARRIED OUT SERVICEABLE. THERE APPEARS TO BE EROSIONSDR CA111026001Switch · intermittent(CAN) SHORTLY AFTER TAKEOFF THE NOSE GEAR DIDN`T RETRACT UPON GEAR UP SELECTION. THE FLIGHT CREW FOLLOWED THE QUICK REF HANDBOOK PROCEDURE, CONDUCTED AN ALTERNATE GEAR EXTENSION AND LANDED BACK WITHOUT FURTHER INCIDENT. HISTORICAL REVIEW INDICATED THAT 2 SIMISDR CA111021003Bearing · seized(CAN) IN CRUISE, WITH THE AUTOPILOT (AP) ENGAGED, THE ACFT STARTED TO ROLL. THE AP WAS DISENGAGED AND THE CREW FELT SEVERE STIFFNESS ON THE AILERON SYS. FOLLOWING THE QUICK REF HANDBOOK PROCEDURE, THE CREW DISCONNECT THE AILERON SYS. THE CAPTAIN SIDE REMAINEDSDR CA111005009Skin · cracked(CAN) DURING A SCHEDULED IN-HOUSE TASK FOR SCRATCH AND DENT SURVEY OF THE EXTERNAL FUSELAGE, THE AME NOTICED A CRACK EMITING FROM BOTH THE FWD AND AFT LATCH CUT-OUT FOR THE LT SIDE ELECTRONICS BAY DOOR IN THE NOSE OF THE ACFT. THE DAMAGE LOCATED AT STA FS 177SDR CA110930001Windshield · failed(CAN) DURING THE APPROACH, THE LT WINDSHIELD SHATTERED, THE CREW CONTINUED THE APPROACH AND LANDED WITHOUT FURTHER INCIDENT. THE WINDSHIELD WAS REPLACED AND THE ACFT RELEASED FOR SERVICE.SDR COMA2011092750072Engine · vibrationON CLIMBOUT FROM DTW CONSTANT LEFT ENGINE N1 VIB INDICATION, AT NORMAL CRUISE POWER IN EXCESS OF 3.2. NORMAL INDICATION AT REDUCED LESS THAN 60 PERCENT POWER SETTINGS. EMERGENCY DECLARED, A/C RETURNED TO DTW LANDED SAFELY. PERFORMED INSPECTION OF LEFT ENGINSDR CA110927006Engine · overtemp(CAN) DURING CLIMB THE CREW HEARD BANG SOUND FOLLOWED BY ACFT VIBRATION. LT ENGINE ITT INDICATING OVERTEMP WITH DECREASING N1 & N2, THE CREW SHUTDOWN THE LT ENGINE, DECLARED EMERGENCY THEN BACK TO THE ORIGIN. MX CONFIRMED ITT 1149 DEGREE CELSIUS MAXIMUM. SDR CA110920002Sensor · failed(CAN) "FLAPS FAIL" ON ED1 AFTER FLAPS RETRACTION. FLAPS STOPPED AT 6 DEGREES. ACFT RETURNED TO AIRPORT. MX FOUND AN INOPERATIVE SKEW SENSOR ON LT WING.SDR CA110921002Stud · broken(CAN) ON TAXI OUT ACFT LOST APU CAME BACK TO GATE, FOUND APU STUD MISSING THAT HOLDS OIL LINE IN PLACE CAUSED AUTO SHUTDOWN. APU BAY WAS COMPLETLY COVERED IN OIL. CLEANED UP ALL VISIBLE OIL , CHECKED DUCTS NO OIL FOUND. APU PUT ON MEL AND NEXT TAKEOFF ABORTESDR CA110921006Turbine · failed(CAN) IN THE CLIMB, CREW HEARD A LOUD BANG FROM THE NR1 ENGINE, FOLLOWED BY VERY HIGH ITT INTO RED ABOVE 900 AND VIBRATION INDICATION WENT TO DASH LINES. ENGINE THROTTLED BACK AND ITT WAS IN RED, VIBRATION REMAINED LOUD AND CONTINUOUS STRONG VIBRATION. CREW SSDR CA110916003Actuator · seized(CAN) FLAP FAIL ON APPROACH. FLAPS AT ZERO, SELECTED TO 8 AND RECEIVED FLAP FAIL MESSAGE. THERE WAS NO MOVEMENT OF THE FLAPS AT 3000 FT WITH AN OAT OF 8 DEGREES SPEED 195 KNOTS. CRUISE ALT FOR FLIGHT WAS FL 350 AND THEY WERE THERE FOR APPROX 1.5 HRS AND OAT ASDR CA110916006Bushing · unserviceable(CAN) BRAKE FOUND LEAKING ON LANDING AND SPRAYED BRAKE FLUID ONTO HOT BRAKES WHICH CAUSED SMOKE TO BE NOTICED FROM AIRPORT TOWER. EMERGENCY RESPONSE SUMMONED TO INVESTIGATE, ACFT TOWED TO GATE, BRAKE CHANGED AND RETURNED TO SERVICE. INVESTIGATION OF CONTINUASDR CA110914008Rvdt · inoperative(CAN) "STEERING INOP" CAUTION MSG ON ED1. RVDT REPLACED IAW 32-51-20.SDR CA110831001Window · cracked(CAN) DURING A FLIGHT THE ACFT EXPERIENCED ARCING FOLLOWED BY CRACKING IN THE PILOT`S LT SIDE WINDOW. NO PRESSURIZATION ISSUES FELT AND FLIGHT CONTINUED. ACFT GROUNDED AND ULTIMATELY FERRIED IAW SL RJ-SL-56-004 WHERE SIDE WINDOW WAS REPLACED.SDR CA110826002Wire · damaged(CAN) DURING TESTING OF THE FLAP ELECTRICAL SYS FOR AN UNRELATED REASON, MX FOUND AN OPEN CIRCUIT BETWEEN THE NR 1 FLAP POWER DRIVE UNIT (PDU) THERMISTOR AND THE FLAP ELECTRONIC CONTROL UNIT (FECU). FURTHER INVESTIGATION REVEALED THAT ELECTRICAL WIRE, 1CE46A2SDR CA110824001Angle · cracked(CAN) WHILE CARRYING OUT AN INSPECTION OF THE WING FUEL TANKS FOR TASK RJ2-57-510-502 AND RJ2-57-610-502, THE AME NOTICED CRACKS ON THE LOWER CAP ANGLES FWD OF RIB AT APPROX WS29.42 IN THE CENTER AND RT FUEL TANKS. CAP ANGLES PN 601R-10011-13A AND 601R10011-14SDR CA110824004Windshield · broken(CAN) WHILE CRUISING AT F320, F/O NOTICED HIS WINDSCREEN BEGIN TO ARC, IMMEDIATELY AFTERWARD THE OUTER WINDSCREEN PANE SHATTERED. CREW FOLLOWED THEIR QUICK REF HANDBOOK AND CONTINUED TO DESTINATION. NO EMERGENCY WAS DECLARED. MX REPLACED WINDSHIELD ASSY.SDR CA110818004Door · damaged(CAN) THE FLIGHT CREW REPORTED A POSSIBLE BIRD STRIKE ON ROTATION IN THE AREA OF THE NOSE GEAR. SUBSEQUENT INSPECTION REVEALED DAMAGE TO THE LT LOWER CORNER OF THE NLG AFT DOOR (GEAR DOWN CONFIGURATION). THE NLG AFT DOOR WAS REPLACED AND THE ACFT RETURNED TOSDR CA110825004Shutoff Valve · failed(CAN) DURING INITIAL CLIMB, THE LT PACK OFF(S) CAME ON EICAS. THE CREW DECIDE TO KEEP THE APU ON AFTER 5000 FT. THE CREW COULD NOT FIND A QRH FOR THE LOSS OF 1 PACK, BUT THEY TRIED TO RESET THE LT PACK WITHOUT SUCCESS. REACHING FL130 THEY DECIDED TO TRANSFESDR CA110811003Bearing · wornON DEPARTURE THE CREW REJECTED THE TAKEOFF AT V1 DUE TO A CONFIG SPOILER WARNING MESSAGE. THIS RESULTED IN A HIGH ENERGY STOP. THE CAUSE OF THE CONFIG SPOILER MESSAGE WAS DETERMINED TO BE A LARGE AMOUNT OF PLAY (ABOUT .040) IN THE LT FLIGHT SPOILER OTBD BEARSDR CA110808004Wire Harness · failedDURING CLIMB THE FLAPS WERE RETRACTED TO ZERO, SHORTLY AFTER THE CREW RECEIVED A FLAP FAIL CAUTION MESSAGE. THE FLIGHT CONTINUED AND THE CREW PERFORMED A FLAPLESS LANDING WITHOUT FURTHER INCIDENT. LOCAL MX FOUND THE FLAPS CONT CH1 AND FLAPS CONT CH2 CIRCUIT BRSDR CA110803019Windshield · crackedDURING CRUISE FLIGHT A 12" LONG CRACK DEVELOPED IN THE LT WINDSHIELD. THERE WERE NO REPORTED PRESSURIZATION PROBLEMS. THE ACFT DIVERTED AND THE WINDSHIELD WAS REPLACED. WINDSHIELD PN NP139321-13, SN 05111H6795, WINDOW TSN 13718, CSN 11263.SDR CA110812001Angle · crackedDURING HEAVY MX VISIT, AN AME NOTICED A CRACK TO AN ANGLE AT FS409+128, STR 21R. THERE WERE NO SPECIFIC INSPECTIONS CALLED UP FOR THAT AREA AT THIS TIME. MFG WAS NOTIFIED OF FINDING. THE DAMAGED PORTION OF THE ANGLE WAS CUT OUT AND A TEMPORARY REPAIR HAS BEENSDR CA110708011Fitting · corrodedWHILE COMPLETING A DETAILED INSP OF THE HORIZ STABILIZER PIVOT FITTINGS IAW TASK RJ2-55-320-502, IRON OXIDE COLORED CORROSION WAS OBSERVED COMING THROUGH THE FITTING HALVES ON BOTH THE LT AND RT FITTINGS. UPON FURTHER INSP, THE BUSHING IN THE LT HORIZONTAL SSDR CA110704004Compressor Blade · damagedSHORTLY AFTER TAKEOFF, THE CREW HEARD A LOUD BANG AND FELT A SEVERE VIBRATION, THE ENGINE INDICATION AND CREW ALERTING SYS (EICAS) DISPLAYED THE NR 2 ENGINE INTER TURBINE TEMP (ITT) AT 960C AND THE N2 CORE VIBRATION AMBER MESSAGE. THE CREW SHUTDOWN THE NR 2 ESDR LEJM2011FA0000422O-Ring · failedON APPROACH, THE CREW RECIEVED A "IDG 2" CAS MESSAGE. THE CREW LANDED WITHOUT INCIDENT. I NSP OF THE GENERATOR FOUND THAT THE FILTER DELTA P INDICATOR O-RING HAD FAILED RESULTING IN TOTAL FLUID LOSS. OPS WERE CONTINUED IAW MEL.SDR CA110526004Line · chafedDURING CRUISE FLIGHT INBD TO A MX BASE, THE NR 1 HYD QUANTITY WENT TO ZERO FOLLOWED BY THE PRESSURE GOING TO ZERO WITH ASSOCIATED SYS LOW PRESSURE CAUTION MESSAGES. THE NR 1 HYD SYS PRESSURE LINE IN THE AFT EQUIPMENT BAY WAS FOUND CHAFED THROUGH. IT APPEARS TSDR CA110507001Fitting · corroded(CAN) WHILE CARRYING OUT A DETAILED INSPECTION OF THE HORIZONTAL STABILIZER PIVOT FITTINGS IAW TASK NR RJ2-55-320-502, THE AME OBSERVED IRON OXIDE COLORED SUBSTANCE ON AND AROUND THE STABILIZER PIVOT PINS. UPON FURTHER CLEAN UP OF THE AREA AND CLOSER INSPECTISDR CA110502001Oil Tank · cracked(CAN) DURING ROUTINE MAINTENANCE, HIGH OIL CONSUMPTION WAS NOTED ON THE RH ENGINE (CF34-3A1, S/N 807264, TSR 7858, CSR 6203). INITIAL INVESTIGATION INDICATED AN OIL LEAK ON THE ENGINE. THE ENGINE WAS CLEANED AND GROUND RUNS CARRIED OUT. A CRACK AT THE TOP WELDSDR CA110511008Controller · failedAFTER TAKEOFF, SEVERAL CAUTIONS APPEARED: PITOT BASE HEAT, LT AOA HEAT, STATIC HEAT, LT PITOT HEAT AND SUBSEQUENTENT "MACH TRIM". AFTER COMPLETION OF THE QRH, AND NORMAL CHECKLIST, RETURNED TO DEPARTURE. AIR DATA SENSOR HEATER CONTROLLER NR 1 REPLACED IAW AMSDR CA110623004Cabin Pressure · unknownDURING CLIMB THROUGH FL250, CREW FOUND THE CABIN ALTITUDE WAS CLIMBING. EMERGENCY DESCENT TO 10000 FTSDR CA110407003Filter · clogged(CAN) A REJECTED TAKEOFF WAS PERFORMED AFTER THE FLIGHT CREW HAD RECEIVED A WING ANTI-ICE & RT WING ANTI-ICE CAUTION MSG. THE FLIGHT CREW TAXIED BACK TO GATE & THE ACFT WAS REMOVED FROM SERVICE. DURING TROUBLESHOOTING, BOTH WING ANTI-ICE MODULATING SHUTOFF SDR MASA2011040502328Engine · fireNUMBER 2 ENG FIRE. MX R2 ENGINE.
Back to GE CF34-3A1