Boeing 747-243B
Service difficulty reports · 506
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 = '747243B' 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 = '747243B' 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 UIEA201000030Skin · damagedEXTERIOR FUSELAGE SKIN EXT. B/O BY 09" X 0.6" X 0.039" ON EXT FUSELAGE SKIN BETWEEN STA 540-560 AT STR 37/R. A SKIN REPAIR WAS ACCOMPLISHED AT DAMAGED IAW REA: MF00656R0010 REV A. REPEAT INSP PRIOR TO 20,000 CYCLES.SDR UIEA201000029Stringer · damagedLIGHTING STRIKE ON FASTENER HEAD BS 340-440 STR-32AL. DRILLED OUT AND INSTALLED HI-LOCK HL63PB6-4 B/N 36457-01 IAW SRM 51-30-02, PERFORMED HFEC IAW D67170 PART 651-00-00 T-16 AND 23 NO CRACKS FOUND.SDR UIEA201000028Stringer · crackedCRACK ON FWD CARGO STR 38 BS 480-500 RT. CRACKED AREA TRIMMED OUT, REINFORCED AREA WITH STRINGER SEGMENT PN N517MC-NRC624-1, IAW SRM 53-10-03 FIG 3 USING FASTENERS IAW SRM 51-30-02.SDR UIEA201000027Frame · crackedPERFORMED BOROSCOPE INSP AND FOUND CRACK ON FRAME BY LENGTH 3" AT BS 360, S-2R END OF CRACK STOPPED BY STOPPING HOLE. REINFORCED AREA WITH DOUBLER & ANGLE PN N517MC-NRC677-1/2 IAW SRM 53-10-04, FIG 18. PERMANENT REPAIR PRIOR TO 20,000 CYCLES IAW EO 4753B240 PASDR UIEA201000026Floorbeam · crackedCRACK ON AFT CARGO FLOORBEAM UPPER CHORD BS 1860, LBL 47-48. TRIM THE UPPER FLANGE DAMAGED IAW SRM 51-40-04, FIG 3, REF EO 4753B236.SDR UIEA201000021Angle · corrodedCORROSION ON ANGLE AFT TO BULK CARGO BEAM BS 2200 S38-40R. DAMAGED AREA TRIMMED OUT AREA REINFORCED WITH DOUBLER IAW SRM 51-40-03, FIG 1.SDR UIEA201000020Skin · crackedDURING MAJOR INSPECTION FOUND, LT BODY INBD DOOR SKIN CRACKED. DAMAGED AREA TRIMMED OUT AREA REINFORCED WITH DOUBLER PER SRM 52-80-02. REFERENCE NON-ROUTINE 984. NO OTHER ACTION REQUIRED.SDR UIEA20100019Carriage · damagedFOUND DURING MAJOR INSPECTION RIGHT INBD MID FLAP CARRIAGE SIDE (INBOARD POSITION) AFTER REMOVAL OF FAIL SAFE BOLT FOUND DAMAGE IN THE BORE. REPLACED RT INBD MID FLAP ASSY PER ATLAS EO REFERENCE NRC 795 AND 897.SDR UIEA201000016Floor Panel · gougedDEEP ABRASION AT UPPER DECK FLOOR STRUCTURE BS 780 RBL 79. THE WORK ACCOMPLISHED PER REA: MF00656R0005 RFTA: REF: 00656-0005. FASTENER INSTALLED PER SRM 51-30-02.SDR UIEA201000015Stringer · corrodedLEVEL 1 CORROSION ON AFT CARGO BILGE STRINGER BS 1840-1860 S-49R. DAMAGED AREA TRIMMED OUT REINFORCED AREA WITH STRAP AND FILLER P/N N517MC-NRC196-1/2 PER SRM 53-10-03 FIG 9 USING FASTENERS PER SRM 51-30-02.SDR UIEA201000014Stringer · corrodedLEVEL 1 CORROSION ON AFT CARGO BILGE STRINGER BS 1860-1920 S-51L. DAMAGED AREA TRIMMED OUT REINFORCED AREA WITH DOUBLER AND STRAP P/N N517MC-NRC195-1/2 PER SRM 53-10-03 FIG 9. PROTECTED AREA PER SRM 51-10-02, INSTALLED RIVETS PER SRM 51-30-02.SDR UIEA201000013Stringer · corrodedLEVEL 1 CORROSION ON AFT CARGO BILGE STRINGER BS 1840-1920 S-50L. DAMAGED AREA TRIMMED OUT REINFORCED AREA WITH STRAP AND FILLER P/N N517MC-NRC187-1/2 PER SRM 53-10-03 FIG 9 USING FASTENERS PER SRM 51-30-02.SDR UIEA201000012Stringer · corrodedEXFOLIATION CORROSION ON INTERNAL SURFACE OF STRINGER BS 1715-1725 S-44L. DAMAGED AREA TRIMMED OUT REINFORCED AREA WITH STRAP AND FILLER P/N N517MC-NRC181-1/2 PER SRM 53-10-03 FIG 9 USING FASTENERS PER SRM 51-30-02.SDR UIEA201000011Floorbeam · crackedCRACK ON UPPER DECK FLOORBEAM WEB BS 460 RBL 33-55. ACCOMPLISHED PER REA: MF00656R0008 AND RFTA: 00656-0008. CRACKED AREA TRIMMED OUT REINFORCE WITH EXTRUDED TEE AND SPLICE AND FILLERS (2EA) P/N N517MC-NRC178-1/2/3/4 PER SRM 53-10-07 FIG 11 USING FASTENER PESDR UIEA201000010Lap Joint · dentedDENT ON EXT FUSELAGE SKIN LAP JOINT AND STRINGER AREA BETWEEN STA 500-520 RT SIDE S44R. DENT AREA TRIMMED OUT REINFORCE AREA WITH DOUBLER AND FILLER P/N N517MC-NCR135-1/2 PER SRM 53-30-03 FIG. 26. USING FASTENER PER SRM 51-30-02.SDR UIEA201000009Stop Fitting · corrodedNR 1L ENTRY DOOR FITTING ON DOOR HAS CORROSION (AFT EDGE). WORK ACCOMPLISHED PER MF00656R0007 RFTA REF: 00656-007. REINFORCED AREA WITH SPLICE AND FILLER P/N N517MC-NRC0109-1/-2 PER SRM 51-40-03 FIG 2 USING FASTENER PER SRM 51-30-02.SDR UIEA2010011400030Forging · corrodedCORROSION ON M/D WINDOW FORGING BS1000-1040 LT BETWEEN STR 20-22 (CORROSION REMOVED IAW SRM 51-70-01 AND SRM 56-20-01, FIG 1 REWORK AREAS FOUND OUT OF LIMITS IAW SRM 56-20-01, FIG 1, WINDOW REPLACED WITH A NEW WINDOW IAW DWG 65B04122).SDR VGQY2010070200043Doubler · crackedRT HORZ STAB TIP AREA, MOST O/B RIB WEB LWR CHORD FOUND CRACK. REMOVED AND REPLACED EXISTING REPAIR DOUBLER PER SRM 52-30-06 REV 166, FIGURE 1. REPAIR DIMENSION: 12.50 INCH BY 6.00 INCH; INSPECTION THRESHOLD: 20,000 FLIGHT CYCLES FROM DELIVERY OF AIRPLANE; SDR VGQY2010070100042Support Fitting · corrodedRIGHT WING LANDING GEAR INBOARD TRUNNION UPPER SUPPORT FITTING FORWARD OUTBOARD FASTENER HOLE AREA FOUND CORROSION AT BOLT HEAD SIDE. REMOVED CORROSION AND PFI PER SOPM 20-20-02. COMPLIED WITH EN 1122-10.SDR VGQY2010070100041Door · corrodedRIGHT WING LANDING GEAR SHOCK STRUT DOOR - UPPER 'U' CAP FOUND CORRODED AT UPPER SIDE. REMOVED AND REPLACED RT WLG SHOCK STRUT UPPER DOOR PER AMM 32-12-07 REV 90.SDR UIEA201000184Skin · damagedDURING JACKING OF DATUM AIRPLANE, MX DAMAGED THE FUSELAGE SKIN SECTION 48 - BS2594.5 AT S-26R (ABOVE THE TAIL JACK PAD). MEASURING 2.5 IN. D AND 0.437 IN DEPTH. THE DAMAGE IS LOCATED APPROX 3.5 IN FWD OF BS 2598 BUTT JOINT. "INTERIM REPAIR PERFORMED AS DESCRIBSDR UIEA200900060Relay · failedAFTER TAKEOFF FROUND SAFETY RELAY LIGHT ILLUMINATED. OTHER INDICATIONS WERE BOTH ATC TRANSPONDERS INOP, LOW SPEED BRAKE RELEASE LIGHT ILLUMINATED. PERFORMED ACTION PLAN SENT AND CHECKED OK PER AMM 32-09-02. REPLACED DEFECTIVE R226 RELAY REPLACED PRIMARY SQUATSDR UIEA200900059Connector · dirtyAIR TURN BACK AFTER TAKEOFF GROUND SAFETY RELAY LIGHT ON. OTHER INDICATIONS WERE BOTH ATC TRANSPONDERS INOP, LOW SPEED BRAKE RELEASE LIGHT ILLUMINATED. AUTO THROTTLES/FRATTS DISENGAGED AUTO PRESSURIZATION INOP. WIRING CHECKED PER WDM 32-09-00. FOUND R952 ONSDR UIEA200900058Relay · misinstalledAIR TURN BACK. ATC TRANSPONDER INOP. GROUND SAFETY RELAY LIGHT ON IN FLIGHT COULD NOT PRESSURIZE PAST 1.8 PSID. LOW SPEED BRAKE RELEASE LIGHT ILLUMINATED. RESET C/B BOTH TRANSPONDERS RERACKED, GROUND OPS CHECKED OK. SWAPPED RELAY BETWEEN R952 AND K3. FOUSDR UIEA200900051Latch · looseCAPTAIN'S INSTRUMENT PANEL CAME OUT DURING TAKEOFF ACCELERATION. (RTO) AT APPROX 60 KNOTS. SECURED CAPT'S INSTRUMENT PANEL. REPAIRED PANEL HOLD DOWN LATCH IAW 31-11-11 PERFORMED INSPECTION 5-51-10 FOR RTO.SDR UIEA200900037Skin Panel · corrodedRT WING INBOARD AFT FLAP UPPER EXTERNAL SURFACE PANEL HAS EVIDENCE OF CORROSION AT WBL 259.30 AND 12 INCHES FROM TRAILING EDGE. CUT OUT AREA OF CORROSION AND PERMANENT REPAIR ACCOMPLISHED AS PER B747-200 SRM 57-50-02 FIG 5, SHEET 4 AND 10 AND SRM 51-40-06. ASDR UIEA200900019Brace · chafedPYLON NR 1 DIAGONAL BRACE IS CHAFED ON OTBD SIDE 11 O'CLOCK POSITION, ZONE 5, 29.5 INCHES FROM FORWARD END. CHAFE IS 2.0 INCH LONG BY 0.125 INCH WIDE. INTERIM REPAIR WAS ACCOMPLISHED AS PER 747-200 SRM 54-41-01, FIG 3 SHEETS 1 THRU 4. REFERENCE ATLAS AIR EOSDR UIEA200900018Panel · delaminatedLT WING UPPER SURFACE L/E FIXED PANEL AT ILES 664.97 HAS AN AREA OF 6.0 BY 18.0 INCHES OF DELAMINATION. PERMANENT REPAIR ACCOMPLISHED AS PER 747-200 SRM 51-40-09, FIG 18 SHEET 2 AND 5. PREPREG 250* F CURE PER SRM 51-40-12. REFERENCE ATLAS AIR EO 4757A477.SDR UIEA200900005Panel · delaminatedLT WING, UPPER SURFACE FIXED L/E PANEL AT OLES 1210.5 AND 5.0 INCHES FROM FORWARD EDGE OF PANEL, SKIN HAS AN AREA OF 2.0 BY 3.0 INCHES OF DELAMINATION. PERMANENT REPAIR ACCOMPLISHED AS PER B747-200 SRM 51-40-09 FIG 18, SHEETS 4 AND 5, PREPREG 250 DEGREES F CUSDR UIEA200800349Amplifier · failedHIGH SPEED REJECTED TAKEOFF FOR CARGO FIRE INDICATION, NR 1 MAIN DECK WARNING ON TAKEOFF ROLL. REJECTED SPEED 146KTS. PERFORMED HIGH ENERGY STOP INSPECTION PER 5-31-10, ALL CHECKED OKAY. REMOVED AND REPLACED NR 1 SMOKE DETECTOR AMPLIFIER, ALL OPS CHECKED OKSDR UIEA200800338Controller · failedRUDDER RATIO LIGHT CAME ON IN CLIMB PASSING THROUGH 5000FT. PROCEEDED AS PER FHB 3-27-24. REMOVED AND REPLACED LOWER REPLACED LOWER RUDDER RATIO CHANGER AND PERFORMED REQUIRED CHECKS PER MM 27-21-00SDR UIEA200800334Bolt · looseAIR TURNBACK AFTER TAKEOFF LOUD NOISE FROM OVERHEAD HATCH. CARRIED OUT HATCH SEAL CHECK AND DOOR CUTOUT CHECK FOR ABNORMALITIES ALL OKAY. FOUND HINGE BOLTS LOOSE. TIGHTENED SAME PER STANDARD PRACTICES. PRESSURIZED AIRCRAFT AND LEAK CHECKED, NO LEAKS NOTED.SDR UIEA200800333Element · false activationDURING CLIMBOUT AT 17000 FEET NR 2 ENGINE FIRE WARNING BELL AND LIGHT CAME ON. ACCOMPLISHED CHECKLIST, BOTH FIRE BOTTLES WERE DISCHARGED, HYD PUMP SUPPLY OFF FOR 1 HOUR AND 30 MINUTES NR 2 FIRE WARNING LIGHT AND NACELLE TEMP STAYED AT 7.9 AND 8.9 AFTER BLOCK SDR UIEA200800310Skin · puncturedDURING GROUND OPERATION IN FUSELAGE SKIN, STA 430, STRINGER 37R NEAR THE GROUND POWER RECEPTACLE WAS STRUCK CAUSING DAMAGE CONSISTING OF A PUNCTURE MEASURING 3X6 INCHES. INTERIM REPAIR ACCOMPLISHED IAW EO 4753B209. (K)SDR UIEA200800299Inu · failedAIR TURN BACK, DURING CLIMBOUT BOTH INST WARNING LIGHTS WITH ATT LIGHT ILLUMINATED. CAPT`S ADI ATT AND COMPAS FLAG IN VIEW. CAPTS HSI HDG, FLAG IN VIEW. REMOVED AND REPLACED NR 1 INU IAW 34-41-03. COOLING SYSTEM TESTED OK AND INS NAV TEST OK. (K)SDR UIEA200800268Bleed Valve · leakingLT WING LEADING EDGE OVERHEAT LIGHT ILLUMINATED. LIGHT DID NOT GO OUT UNTIL THROTTLE WAS RETARDED. FOUND PYLON VALVE LEAKING. REPLACED VALVE, OPS CHECKED OK. (A)SDR AIEA200800259Frame · crackedDURING C-CHECK FOUND FRAME CRACKED AT STATION 320 STRINGER 25R. FRAME REPAIRED AS PER SRM 53-10-04 FIGURE 10. (A)SDR AIEA200800258Frame · crackedDURING C-CHECK FOUND FRAME CRACKED AT STATION 280 STRINGER 26L. FRAME REPAIRED AS PER SRM 53-10-04 FIGURE 10. (A)SDR AIEA200800257Frame · crackedDURING C-CHECK FOUND FRAME CRACKED AT STATION 280 STRINGER 26R. FRAME REPAIRED AS PER SRM 53-10-04 FIGURE 10. (A)SDR AIEA200800256Fire Detector · dirtyRETURN TO BLOCKS INTERMITTENT FIRE WARNING DURING TAXI. FOUND EVIDENCE OF DE-GERM IN CARGO SNIFFED TUBE. CLEANED SNUFFER TUBES WITH CONTACT CLEANER. SYSTEM OPS CHECK NORMAL AS PER MM 26-16-00. (A)SDR UIE2008F00023Skin · crackedCARRY OUT NR 4 PYLON EXHAUST SKIN CRACK CONDITIONAL CHECK REF EO NR 4754A250. REPAIRED CRACK IAW MFG MESSAGE 1-299984882-19. (K)SDR UIE2008F00022Stringer · crackedSTA 396, STRINGER 25 L, FATIGUE CRACKED. REPLACED STRINGER IAW DWG 65B11089. (K)SDR UIE2008F00024Stringer · crackedSTA 320, STRINGER 25L HAS FATIGUE CRACK. FRAME REPAIRED AT STA 320 LT SIDE IAW SRM 53-10-04, FIG 10. (K)SDR UIE2008F00026Fastener · looseNR 1 PYLON AFT BULKHEAD CHORD FOUND SEVERAL ATTACH FASTENERS, LOOSE. REPLACED FASTENERS IAW MFG MESSAGE NR 1-875740529-4. (K)SDR UIE2008F00025Fastener · looseNR 4 PYLON AFT BULKHEAD CHORD FOUND SEVERAL ATTACH FASTENERS LOOSE. REPLACED FASTENERS IAW MFG MESSAGE NR 1-875740529-4. (K)SDR UIE2008F00003Frame · crackedFRAME CRACKED AT STATION 400 STRINGER 22R. REPLACED DAMAGED FRAME IAW SRM 51-10-01 AND SRM 51-30-02. (K)SDR UIE2008F00001Frame · crackedFRAME CRACKED AT STATION 400, STRINGER 22R. REPLACED DAMAGED FRAME IAW SRM 51-10-01 AND SRM 51-30-02. (K)SDR UIE2008F00018Structure · dentedNR 1 ENGINE LT "C" DUCT (REVERSER) EXTERIOR FOUND WITH 1 EACH DENT AT 7 O`CLOCK POSITION. NR 1 REVERSER EXTERIOR SURFACE DENT REPAIRED IAW ENGINE MANUAL 78-32-01, REPAIR NR 4. (K)SDR UIE2008F00017Skin · dentedNR 3 ENGINE, RT SIDE ABOUT 4 O`CLOCK POSITION HAS 2 DENTS. NR 3 ENGINE REVERSER REPAIRED IAW ENGINE MANUAL 78-32-01, REPAIR NR 4. (K)SDR UIE2008F00016Skin · dentedNR 1 ENGINE LT "C" DUCT (REVERSER) EXTERIOR FOUND WITH 1 EACH DENT AT 7 O`CLOCK POSITION. NR 1 REVERSER EXTERIOR SURFACE DENT REPAIRED IAW CF650 ENGINE MANUAL 78-32-01, REPAIR NR 4. (K)
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