Boeing 757-23A
Service difficulty reports · 1,397
Newest first. General aviation reporting is voluntary.
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 = '75723A' 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 = '75723A' 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 08FDEA01959Skin · dentedEXTERNAL SMALL HOLE FLUSH REPAIR AT FUSELAGE BS740, S-18L, TO BE EVALUATED. EXISTING REPAIR EVALUATED AS PER EO F-5100-7-5001 PT1 ATTACHMENT B AND FOUND TO BE PREVIOUSLY ACCOMPLISHED IAW B757-200 SRM 53-00-01 FIG 208. REPAIR IS CLASSIFIED AS MAJOR PER GMM 6-SDR 2004F00073Switch · failedON TAKEOFF ROLL, EPR BUTTON WOULD NOT ILLUMINATE AND EPR READING ON LEFT SIDE WAS LOW. TAKEOFF ABORTED. CLEANED AND REPOSITIONED EPR PUSHBUTTON SWITCH. TESTED THRUST MANAGEMENT COMPUTER. OPERATIONAL CHECKED NORMAL. (M)SDR 02061802Stringer · dentedSTRINGER 16L DENTED AT BS 612 AND BS 617. REPAIRED AS PER SRM 53-00-03 FIGURE 201 AND ER 02-0687.SDR 02061801Skin · dentedTWO DENTS IN SKIN, BS 611 AND 615 AT STR 16L LBL 65. INSTALLED DOUBLER OVER DAMAGE; CUTOUT PER SRM 53-00-01 AND ER 02-0687.SDR 02042901LightSeat 16C Emergency Light INOP. Deferred I.A.W. MEL 33-51-03 Situation 1 Category C Authorization Number 57-0233. Removed and Replaced Light Assembly; Light Assembly had been ripped from seat.SDR CA020426006Smoke · detected(CAN) CROSSING TOP THURDERSTORM, APPLIED MAX CONTINUOUS FOR 30 SEC. SPEED DROP TO M.72 AT FL 360. SMELL OF OIL BURNED FOR 3 MINS ALL PARAMETERS NORMAL ACTION TAKEN LMWS 51130 ITEM 1,2 BVCU BITE CHECK, MCD'S INSPECTED ON BOTH ENGINE. BOTH ENGINE TEST C/O AS PSDR AUS20020362Segment · separated(AUS) DURING INSPECTION, THE LT ENGINE INBOARD THRUST REVERSER NR 1 CASCADE (PN LJ76662) AND THE SUPPORT RING SECTION (PN LJ7599) WERE FOUND MISSING.SDR 02040201Power Supply · inoperativeEmergency Path Lighting INOP; Replaced R2 door power supply for E-path lighting. Ops checked good as per M/M 33-51-1SDR 2002F00104Wire Harness · damagedEMERGENCY ESCAPE PATH LIGHTING SEAT 27ABC INOPERATIVE. INVESTIGATION REVEALED WIRES BROKEN AND BURNED AT PLUG. REPLACED WIRING HARNESS. (M)SDR AUS20011173Nut · loose(AUS) NR 1 ENGINE DRIVEN HYDRAULIC PUMP PRESSURE LINE UNION JAM NUT LOOSE AND LEAKING. INVESTIGATION FOUND THAT IT WAS CHAFED THROUGH FOR 50 PERCENT OF THE CIRCUMFERENCE ON THE JAM NUT SIDE WITH A CORRESPONDING RIDGE (FRACTURE) ON THE INSIDE. UNION IS LOCATED SDR 2001F00450Sensor · failedON PUSH BACK, STARTING RIGHT ENGINE, APU FAULT CAUSING POWER LOSS. ECU BITE CHECK WAS ACCOMPLISHED WITH NO FAULTS FOUND. AIRCRAFT RELEASED. ABOUT 30 MINUTES AFTER DEPARTURE APU FAULTED, SINGLE ELECTRICAL SOURCE, AIRCRAFT RETURNED TO DEPARTURE STATION. ON INSDR 2001F00264Module · malfunctionedMASTER CAUTION/WARNING LIGHT SWITCH ILLUMINATED AFTER TAKEOFF WITHOUT ANY ASSOCIATED EICAS MESSAGE OR ANNUNCIATOR LIGHT. MASTER CAUTION COULD NOT BE RESET. REMOVED AND REPLACED MASTER WARNING MODULE, OPS CHECK GOOD. (M)SDR 2001F00211Wire Rope · out of adjR1 DOOR FAILED THE EMERGENCY POWER ACTUATION CABLE SYSTEM TEST. ADJUSTED DOOR EMERGENCY ACTUATION CABLE, FUNCTIONAL CHECK GOOD. (M)SDR 2001F00210Wire Rope · out of adjR2 DOOR FAILED THE EMERGENCY POWER ACTUATION CABLE SYSTEM TEST. ADJUSTED DOOR EMERGENCY ACTUATION CABLE, FUNCTIONAL CHECK GOOD. (M)SDR 2001F00209Wire Rope · out of adjL2 DOOR FAILED THE EMERGENCY POWER ACTUATION CABLE SYSTEM TEST. ADJUSTED DOOR EMERGENCY ACTUATION CABLE, FUNCTIONAL CHECK GOOD. (M)SDR CA010727020Hydraulic Line · leaking(CAN) AIRCRAAFT RETURNED TO THE GATE, AFTER PUSH BACK, DUE TO A HYDRAULIC LEAK AT THE L/H MAIN LANDING GEAR DOWNLOCK ACTUATOR SUPPLY FLEX LINE. LINE WAS FOUND RUPTURED AT MID POINT. LINE WAS REPLACED AND AIRCRAFT WAS RETURNED TO SERVICE.SDR 2001F00050Wire · cutFOUND FLOOR PROXIMITY EMERGENCY ESCAPE PATH LIGHT AT ROW 18 INOPERATIVE, WIRES CUT AT LIGHT. SPLICED WIRES AND RESTOWED CORRECTLY. (M)SDR AUS20010517Seal · failed(AUS) RH ENGINE HP6 DUCT SEALS FAILED AND LEAKING.SDR CA010402013Valve · cracked(CAN) R/H HYDRAULIC QUANTITY DECREASING DURING LAST MINUTE OF FLIGHT. FOUND DURING WALKAROUND, RT ANTI-SKID MODULE VALVE V35 IN WHEEL WELL CRACKED, VALVE REPLACED, LEAK CHECK CUT OUT AND ACFT BACK TO SERVICE.SDR 2001F00208Wire Rope · out of adjR4 DOOR FAILED THE EMERGENCY POWER ACTUATION CABLE SYSTEM TEST. ADJUSTED DOOR EMERGENCY ACTUATION CABLE, FUNCTIONAL CHECK GOOD. (M)SDR 20010320SG002Fseu · failedON APPROACH, WHEN FLAPS 30 WAS SELECTED FLAPS WOULD NOT EXTEND BEYOND 25, LEADING EDGE LIGHT CAME ON. NORMAL FLAPS 25 LANDING ACCOMPLISHED. ADJUSTED SLAT 5 LOSS SENSING SENSOR AND REPLACED FSEU. (M)SDR 20010316SG002Fseu · failedON APPROACH WHEN FLAPS 30 WAS SELECTED FLAPS WOULD NOT EXTEND BEYOND 25, LEADING EDGE LIGHT CAME ON. NORMAL FLAPS 25 LANDING ACCOMPLISHED. ADJUSTED SLAT 5 LOSS SENSING SENSOR AND REPLACED FSEU. (M)SDR CA001219009Tube · failed(CAN) THIS UNIT WAS SENT FOR OVERHAUL AND FAILED HYDROSTATIC TEST, AND THE INFLATABLE FAILED THE PROOF TEST, ALSO NOTICE THAT THE LOWER TUBE FAILED THE TEST AT 4 PSI AND SEPARATED ALONG THE MAIN SEAM ADJACENT TO THE PRESSURE RELEASE VALVE.SDR CA001004009Fan · seized(CAN) AIRCRAFT WAS DIVERTED DUE TO BURNING ODOR IN COCKPIT AND FWD CABIN, CREW STATED THAT ODOR STOPPED AS SOON AS ALTERNATE FAN SELECTION WAS CARRIED OUT. UPON ARRIVALMAINTENANCE FOUND NR 1 EQUIPMENT COOLING FAN BREAKER POPPED, FAN FOUND SEIZED. AIRCRAFT WAS SDR CA000714009Duct · cracked(CAN) IN FLIGHT, LOUD WISHING NOISE FROM CEILING AT ROW 12 AND PASSENGER WERE COMPLAINING ABOUT VERY COLD TEMPERATURE. AFTER INVESTIGATION, MAINTENANCE FOUND A LEAK AT AIR PLENUM AROUND R2/L2 DOOR AREA. LEAK WAS COMING FROM A PREVIOUS REPAIR. PLENUM REPAIRED ASDR CA000530051Acm · seized(CAN) CREW UNABLE TO CONTROL FLIGHT DECK, LT AIR CYCLE MACHINE SEIZED, SENT TO SHOP FOR REPAIR AND REPORT.SDR N8TA00051701Hose · leakingTHREE MINUTES AFTER TAKEOFF, CREW OBSERVED EICAS MESSAGE, LEFT HYDRAULIC SYSTEM QUANTITY AND QUANTITY DROPPED TO .20; SYSTEM WAS DEPRESSURIZED. ALL GEAR EXTENSIONS AND ALT FLAP EXTENSIONS ACCOMPLISHED FOLLOWED BY AN UNEVENTFUL LANDING. UPON INVESTIGATION, THSDR CA000110077Panel · separated(CAN) DURING SERVICE CHECK NR 2 ENGINE COLD STREAM PANEL RIPPED OFF. OPERATOR REPORTED TO ROLLS ROYCE FOR INVESTIGATION. PANELS AND BOLT TORQUE ARE TO BE INSPECTED AT D.I. ITEM CLOSED BY OPERATOR. AMO INFORMED AND WILL COMLPLY WITH THE DI CHECK ALSO.SDR CA000110076Connector · corroded(CAN) DURING INSPECTION ON THE ELECTRICAL HARNESS IN THE NOSE GEAR WHEELWELL, THE ELECTRICAL HARNESS BRACKET ALD393 AND THE CONNECTOR D40488P FOUND CONTAMINATED WITH WATER ON 25 PERCENT OF CONNECTOR AREA. CAUSES WIRES TO BECOME BRITTLE AT CRIMPED AREA. THE BSDR CA991210024Connector · corroded(CAN) DURING ROUTINE INSPECTION, HARNESS BRACKET ALD393 AND CONNECTOR D40488P FOUND CONTAMINATED WITH WATER ON 25 PERCENT OF THE CONNECTOR AREA. CAUSED WIRES TO BECOME BRITTLE AT CRIMPED AREA. ALSO, THE BACKSHELL OF THE CONNECTOR WAS SEIZED DUE TO CORROSIOSDR 99ZZZM805Control · failedDURING TRANSITION FROM HIGH CLIMB POWER TO CRUISE POWER LT ENGINE APPEARED TO SURGE. ALL ENGINE INDICATIONS WERE NORMAL PRIOR TO AND AFTER SURGE EVENT. REMOVED BLVL CONTROL C8E38-9 AND INSTALLED BLVL CONTROL C8E38-12, OPERATIONAL CHECK NORMAL. (M)SDR CA990916002Engine · malfunctioned(CAN) OIL CONS. AND VIBRATION,SDR N8TA990801Fuel Nozzle · displatedDURING TALKEOFF, FIRE WARING ACTIVATED FOR NR 2 ENGINE. CREW INITIATED FIRE EXTINGUISHER AND ENGINE SHUT DOWN PROCEDURES. PRELIMINARY INVESTIGATION REVEALED COMBUSTION CASE BURN-THROUGH AT NR 9 FUEL NOZZLE. (X)SDR CA990812015Vor Panel · overheated(CAN) AFTER ENGINE START, VARIOUS ANNUNCIATOR LIGHTS ILLUMINATED, BATTERY OFF, APU BATTERY DISCHARGE, STANDBY POWER OFF, LT AND RT WING AND ENGINE. A/C DISAGREE. LT VOR/DME PANEL OVERHEATING, SAME REMOVED AND REPLACED.SDR CA990804038Idg · damaged(CAN) 45 MINUTES AFTER DEPARTURE, THE LT GENERATOR CAME OFF LINE AND IDG LIGHT CAME ON, POWER GENERATION AND IDG DISCONNECT CHECKLIST ACCOMPLISHED. NR 1 ENGINE IDG INTEGERATED DRIVE GENERATOR FOUND DAMAGED WITH CASING CRACKED AND LEAKING OIL, BOTH REPLACED. SDR CA990715016Warning Light · illuminated(CAN) DURING CRUISE AT 31,000 FEET ONE HOUR INTO FLIGHT, AFT CARGO FIRE LIGHT CAME ON. NO EICAS WARNING. FIRE BOTTLES DISCHARGED IAW QRH. AFLOTS CARD REPLACED. LOGIC CARD.SDR CA990323020Eec · malfunctioned(CAN) FLIGHT CREW NOTED NR 1 ENGINE COULD NOT REACH SELECTED EPR WITH THROTTLE FULL FORWARD. AT 35 KNOTS, A REJECTED TAKEOFF WAS ACTIONED. MAINTENANCE CARRIED OUT A BITE TEST ON THE LEFT ELECTRONIC ENGINE CONTROL (EEC) AND FOUND AN INTERNAL FAULT. THE EEC WSDR NOCA0299Light · inoperativeJFK - FLIGHT ATTENDANT EMERGENCY FLASHLIGHT AT L1 DOOR FOUND INOPERATIVE DURING INSPECTION. REPLACED FLIGHT ATTENDANT EMERGENCY FLASHLIGHT AT L1 DOOR. OPS CHECKED OK. (M)SDR NOCA0199CTemp Sensor · inoperativeDURING FLIGHT, CABIN TEMP INCREASE, CREW ATTEMPTED TO REGULATE BY USING TRIM AIR SWITCH. TRIM AIR SWITCH HAD NO EFFECT . CABIN ALTITUDE STARTED TO CLIMB. CREW COMMENCED DESCENT. EVALUATION CONDUCTED TO PREVENT RECURRENCE WITH CHKS OF TRIM AIR VALVE SYS TESSDR NOCA0199BValve · inoperableDURING FLIGHT, CABIN TEMP INCREASE, CREW ATTEMPTED TO REGULATE BY USING TRIM AIR SWITCH. TRIM AIR SWITCH HAD NO EFFECT. CABIN ALTITUDE STARTED TO CLIMB. CREW COMMENCED DESCENT. EVALUATION CONDUCTED TO PREVENT RECURRENCE WITH CHECKS OF TRIM AIR VALVE SYS TESDR NOCA0199AWater Nozzle · inoperativeDURING FLIGHT, CABIN TEMPERATURE INCREASE, CREW ATTEMPTED TO REGULATE BY USING THE TRIM AIR SWITCH. TRIM AIR SWITCH HAD NO EFFECT. CABIN ALTITUDE STARTED TO CLIMB. CREW COMMENCED DESCENT. EVALUATION CONDUCTED TO PREVENT RECURRENCE WITH CHKS OF TRIM AIR VALSDR CA990125012Sensor Line · loose(CAN) RIGHT ENGINE BLEED OFF - EICAS MESSAGE WHEN TAKEOFF POWER APPLIED. MESSAGE WENT OUT WHEN POWER REDUCED. SECOND ATTEMPT NORMAL. RT ENGINE PRESSURE RELIEF SHUT OFF VALVE SENSOR LINE INSPECTED AND TIGHTENED.SDR CA990614046Wire · burned(CAN) AFT GALLEY CREW REPORTED SMOKE FROM OUTBOARD COFFEE MAKER. COFFEE MAKER REPLACED DUE TO BURNED WIRES.SDR CA990223014Coffee Maker · burnt(CAN) CREW REPORTED SMOKE IN GALLEY. FOUND BURNED WIRING ON OUTBOARD COFFEEMAKER, REPLACED.SDR 98ZZZX4714Receiver · failedBUE/BOG - FLT 088 - AIR TURN BACK WXR FAIL DISPLAYED ON HSI. TEST OK ON GROUND AND IN-FLIGHT. REPLACED RADAR TRANSCEIVER. ACCOMPLISHED OPERATIONAL TEST. RADAR WORKED OK.SDR NOCA2598Screen · contaminatedIN FLIGHT APU START SCHEDULED BY MAINTENANCE. APU IN FLIGHT START UNSUCCESSFUL. ON GROUND INSPECTION OF APU INLET PLENUM FOUND DEBRIS ON INLET SCREEN. DEBRIS REMOVED. INSPECTION OF CHIP DETECTORS OK. LEAK CHECK OK. APU OPS CHECK OK. (M)SDR NOCA2298Slide · malfunctionedON CREW TRAINING OF EMERGENCY EVACUATION, THE R-3 DOOR EVACUATION SIDE DID NOT DEPLOY AUTOMATICALLY ON DOOR OPENING, IT HAD TO BE MANUALLY DEPLOYED. ESCAPE SLIDE PART NR D31041, S/N 0474 WAS SENT TO AIR CRUISERS FOR INSPECTION AND EVALUATION. INSPECTION REVESDR NOCA2198Valve · inoperativeSNN - ACCOMPLISHED HIGH ENERGY STOP INSPECTION. NO DISCREPANCIES NOTED. PERFORMED RIGHT ENGINE RUN UP. BLEED LIGHT CAME ON AT 90 PERCENT. BLEED SWITCH POSITIONED TO OFF AND PLACARDED. ASSIGNED MEL IAW NAA DISPATCH DEVIATION GUIDE. REPLACED RIGHT ENGINE PRSDR NOCA2098Elt · inoperativeEMERGENCY LOCATOR TRANSMITTER SIGNAL INTERMITTENTLY TRANSMITTING DURING FLIGHT. SIGNAL CAN BE HEARD ON 121.5. REPLACED ELT TRANSMITTER. (M)SDR CA990119026Oil Pump · malfunctioned(CAN) DURING FLIGHT, EICAS MESSAGE INDICATED LOSS OF OIL PRESSURE AND HIGH VIBRATIONS ON NR 2 ENGINE. AIRCRAFT DIVERTED. ENG DISASSEMBLY AND REMOVAL OF OIL PUMP FOUND LOSS OF DRIVE AT THE OIL PUMP QUILL SHAFT. SUBSEQUENT STRIP OF 06 MODULE REVEALED LOSS OF
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