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 UIEA200700152Frame · crackedUPPER DECK STATION 740 STRINGER 6R FRAME CUTOUT CRACKED. REPAIRED STRINGER CUTOUT PER SRM 53-10-04 FIG 54.SDR UIEA200700191Frame · crackedBS 360 LT S24A STRINGER CUT-OUT CRACKED. CRACKED FRAME WEB REPAIRED AS PER BOEING MSG 1-307193755-1-2.SDR UIEA200700194Spar · damagedNR 4 ENG LT LOWER SPAR CHORDS (SIDE COWL HINGE AREA) AFT AREA FOUND DAMAGED. DAMAGED WEB REPAIRED AS PER BOEING MSG 1-308420578-2.SDR UIEA200700196Frame · crackedRT BS 900 TENSION TIE AREA NR 5 HOLE FOUND CRACK AT FRAME WEB THRU THICKNESS RUNNING I/B AND NR 10 HOLE FOUND CRACK AT FRAME WEB APPROX 0.060" IN LENGTH RUNNING DOWNWARD. CRACKED FRAME WEB REPAIRED AS PER BOEING MSG 1-306586780-2.SDR UIEA200700193Stringer · corrodedCABIN FLR SUPPORT BS 1283 RBL 117 CORROSION. OUT OF LIMIT, SUPPORT REPAIRED AS PER BOEING 1-310385513-2.SDR UIEA200700189Frame · crackedM/D STA 360 S-23R FRAME STRINGER CUT-OUT CRACK. CRACKED FRAME REPAIRED AS PER BOEING MSG 1-307825515-2-1.SDR UIEA200700154Frame · deformedMAIN DECK STATION 2000 STRINGER 13R FRAME INNER FLANGE FOUND DEFORMED. REPAIRED FLANGE PER SRM 51-40-03 FIG 1.SDR UIEA200700156Bracket · crackedAFTER REMOVAL OF PAX DECK SPLICE FITTING AT STATION 1416 LBL 2 IN THE BLG WHEEL WELL IS FOUND CRACKED. REPLACED FITTING PER SRM 51-10-01 PAGE 9.SDR UIEA200700153Frame · deformedMAIN DECK STATION 1960 STRINGER 13R FRAME INNER FLANGE FOUND DEFORMED. REPAIRED PER SRM 51-40-03 FIG 1.SDR UIEA200700190Shear Tie · crackedRT BS 940 TENSION TIE AREA HOLE NR 16 FOUND CRACKED AT AFT CHANNEL APPROX 0.060" RUNNING INBOARD LWR. CRACKED AFT CHANNEL REPAIRED AS PER BOEING MSG 1-303983211-2-2-4.SDR UIEA200700197Rib · crackedEMP LT STAB T/E RIB AT STAB BL421.5 WEB FOUND CRACKED. CRACKED WEB REPAIRED AS PER SRM 55-10-06 FIG 4.SDR UIEA200700187Rib · crackedRHW NR 23 VC FLAP I/B ARM ROTARY ATT RIB AT OLES 1278 I/B FACE FOUND CRACKED AT "D" HOLE FWD STIFFENER AREA. CRACKED RIB "D" HOLE REPAIRED AS PER BOEING MSG 1-308409234-2.SDR UIEA200700192Frame · crackedM/D STA270 S-R13A AREA FRAME CRACK. CRACKED FRAME WEB REPAIRED AS PER BOEING MSG 1-307196918-1-2.SDR UIEA200700177Shear Tie · crackedRT BS 860 TENSION TIE AREA HOLE NR 6 FOUND CRACKED AT AFT CHANNEL APPROX 0.060" IN LENGTH RUNNING UPWARD. RT BS 860 TENSION TIE CRACKED AFT CHANNEL, REPAIRED AS PER BOEING MSG 1-306486452-2.SDR UIEA200700179Frame · crackedLT BS 200 FRAME IS FOUND CRACKED AT 11EA FASTENER HOLES BETWEEN S13L AND S14L. CRACKED FRAME WEB REPAIRED AS PER SRM 51-40-03 FIG 1.SDR UIEA200700163Vertical Beam · crackedNWW RT VERTICAL BEAM WEB AT BS 280 WL 170-180 LOWER STAND OFF HOLE FOUND CRACK APPROX 1/8" LONG. CRACK WEB REPAIRED AS PER SRM 51-40-02 FIG 1.SDR UIEA200700165Hinge Fitting · crackedEMP LT HORIZ STAB C/S STAB HINGE NR 28 HOLE FOUND CRACK AT HINGE FTG 11 O/C POSITION APPROX 1/8" LONG. REPAIRED AS PER BOEING MSG 1-305519321-7.SDR UIEA200700164Door Frame · crackedRT NR 1 MED NR 9 DOOR STOP FTG AREA FOUND CRACK AT BS 488 FRAME WEB TOOLING HOLE APPROX 1/16" AND 1/8" LONG. RT NR 1 MED NR 9 DOORS STOP FTG AREA CRACK WEB REPAIRED AS PER SRM 53-10-04 FIG 121.SDR UIEA200700198Frame · crackedM/D LT BS 200 FRAME INNER CHORD IS FOUND CRACKED AT 1 FASTENER HOLE BETWEEN S13L AND S14L. CRACKED INNER CHORD REPAIRED AS PER SRM 51-40-03 FIG 1.SDR UIEA200700161Seat Track · corrodedCABIN TIE DOWN TRACK FLANGE CORRODED AT BS 1440-1480 RBL33. CORROSION SEAT TRACK REPAIRED AS PER SRM 53-10-05 FIG 25.SDR UIEA200700195Shear Tie · crackedRT BS 860 TENSION TIE AREA HOLE NR 5 FOUND CRACKED AT FWD CHANNEL APPROX 0.030" ON LENGTH RUNNING UPWARD. CRACKED TENSION TIE FWD CHANNEL REPAIRED AS PER BOEING MSG 1-306484452-2.SDR UIEA200700162Web · crackedM/D STA 360-380 S26R FLOOR WEB CRACK AT SKIN ATT AREA. CRACKED FLOOR WEB REPAIRED AS PER SRM 51-40-03 FIG 3.SDR UIEA200700158Attach Angle · crackedNR 2 PYLON CAP SKIN OUTBOARD LOWER ATTACH ANGLE FOUND CRACKED AS MARKED. REPAIRED AS PER SRM 54-11-02 FIG 7.SDR UIEA200700157Support · crackedLEFT FUSE TO WING LOWER PANEL 191KL FAIRING SUPPORT FRAME AT STA 1241 FOUND CRACKED. FAIRING SUPPORT FRAME REPAIRED IAW SRM 51-40-03.SDR UIEA200700159Support · corrodedAIR-CONDITIONING BAY FAIRING SUPPORT FOUND CORRODED AS MARKED AT STA 1110 LBL 12 (191EL FAIRING ATTACH AREA). REMOVED CORROSION AND REPAIRED PER SRM 53-50-04 FIG 2.SDR UIEA200700188Web · crackedM/D STA 340-360 S-26R FLR WEB CRACK AT SKIN ATT AREA. CRACKED FLOOR WEB REPAIRED AS PER SRM 51-40-03 FIG 3.SDR UIEA200700182Fitting · crackedM/D RT BS 840 FRAME TO TENSION TIE CONNECTION FOUND NR 8 HOLE CRACK AT TENSION TIE AFT CHANNEL. CRACKED AFT CHANNEL REPAIRED AS PER BOEING MSG 1-303978264-2.SDR UIEA200700185Attach Fitting · crackedM/D RT BS 880 FRAME TO TENSION TIE CONNECTION FOUND NR 6 HOLE CRACK AT TENSION TIE FWD CHANNEL. CRACKED AFT CHANNEL REPAIRED AS PER BOEING MSG 1-303986330-2.SDR UIEA200700184Attach Fitting · crackedM/D LT BS 840 FRAME TO TENSION TIE CONNECTION FOUND NR 5 HOLE CRACK AT TENSION TIE AFT CHANNEL. M/D LT BS 840 FRAME TO TENSION TIE CONNECTION TENSION TIE AFT CRACKED CHANNEL REPAIRED AS PER BOEING MSG 1-303978264-2.SDR UIEA200700183Attach Fitting · crackedM/D LT BS 840 FRAME TO TENSION TIE CONNECTION FOUND NR 4 HOLE CRACK AT TENSION TIE FWD CHANNEL. CRACK FWD CHANNEL REPAIRED AS PER BOEING MSG 1-303978264-2.SDR UIEA200700137Skin Panel · crackedRT WING UPPER TRAILING EDGE COMPOSITE PANEL HAS A 2.0 INCH CRACK, INBOARD OF INBOARD AILERON AT WBL 445.00, 10.0 INCHES FROM AFT EDGE. PERMANENT REPAIR WAS ACCOMPLISHED AS PER 747-200 SRM 51-40-09, FIG 2, TABLE 1 AND 747-200 SRM 51-40-12. ALSO, REFERENCE ATLSDR UIEA200700136Skin Panel · delaminatedLT WING UPPER TRAILING EDGE SKIN PANEL HAS A 6.0 INCH BY 6.0 INCH AREA OF DELAMINATION AND FASTENERS ARE PULLING THRU THE SKIN, AT WBL 239.00 INBOARD OF NR 6 SPOILER AND 62.0 INCHES FROM AFT EDGE. PERMANENT REPAIR WAS ACCOMPLISHED AS PER 747-200 SRM 51-40-09,SDR UIEA200700135Structure · crackedDURING WALK AROUND, FOUND LEFT WING GEAR INBOARD SHOCK STRUT DOOR DAMAGED ALONG THE LOWER 27" OF THE T/E WITH APPROX 7" DAMAGE ON DOOR FAIRING. LEFT WING GEAR INBOARD CHOCK STRUT DOOR ASSY REMOVED IAW CDL 32-12-1. REPLACED LOWER STRUT DOOR AND FAIRING AS PERSDR UIEA200700133Valve · unserviceableWHEN "A" AUTOPILOT IS CONNECTED THE ACF GOES INTO A STEEP DIVE WITH STAB TRIM "A" LIGHT ON ALL ATTITUDE. WHEN AUTOPILOT "B" IS CONNECTED A/C PORPOISES + - 1,200 FRM WITH STAB TRIM "B" LIGHT ON. THIS HAPPENED ABOVE FL 27.0. IF FLYING AT 27.0 IT MAINTAINED A GSDR UIEA200700121Frame · crackedNR 1 PYLON AFT UPPER BULKHEAD "T" FRAME HAS A CRACK AT AFT FLANGE AND A SECOND CRACK AT FORWARD FLANGE, OUTBOARD OF NR 1 PYLON FRONT SPAR CHORD ASSEMBLY. AFT FLANGE CRACK IS 0.750 INCH LONG. FORWARD FLANGE CRACK IS 0.375 INCH LONG AT NACELLE STATION 270.00. ASDR UIEA200700123Angle · crackedVERTICAL "L" EXTRUSION ANGLE CRACKED AT RIGHT WING UPPER SURFACE, BELOW GAP PANEL 611CT FOR NR 3 PYLON AT INBOARD SIDE, FORWARD CORNER, WING STATION 670.25. REMOVED AND REPLACED "L" ANGLE EXTRUSION P/N 221738-3-1 AS PER 747-200 SRM 51-30-02 AND SRM 51-10-02. SDR UIEA200700122Skin · crackedNR 4 PYLON CUT-OUT FOR PRE-COOLER EXHAUST AIR, RT SIDE OF PYLON AT NACELLE STATION 248.0 HAS A 2.625 INCH CRACK AT AFT, LOWER CORNER. ACCOMPLISHED INTERIM REPAIR, LOCATED CRACK AS PER NDT 747 MANUAL 51-00-00 PAR 6 AND STOP DRILLED BY REAMING EXISTING HI-LOCK SDR UIEA200700119Panel · crackedRIGHT WING, UPPER TRAILING EDGE PANEL, OUTBOARD OF NR 8 SPOILER HAS A 7.0 INCH LONG BY 1.5 INCH WIDE CRACK. PERMANENT REPAIR WAS ACCOMPLISHED AS PER 747-200 SRM 51-40-09, FIG 2, TABLE 1 AND SRM 51-40-12. ALSO, REFERENCE ATLAS AIR XEO NR 57-030107.SDR UIEA200700118Skin · crackedNR 3 PYLON TOP SKIN, AFT EDGE, ABOVE LINK FITTING HAS A 0.375 INCH CRACK. TRIMMED OUT SKIN TO REMOVE CRACK AS PER 747 SRM 51-10-01. ACCOMPLISHED HFEC INSPECTION TO VERIFY REMOVAL OF CRACK AS PER 747 NDT MANUAL PAR 6 SECTION 51-00-00 FIG 4. ALSO, REFERENCE ASDR UIEA200700120Seat Track · crackedFOUND MAIN CARGO COMPARTMENT SEAT TRACK AT STATION 1816, LBL 99 HAS CRACK CROWN LUGS. ACCOMPLISHED PERMANENT REPAIR AS PER 747-200 SRM 53-10-05 FIG 1A, ALSO, REFERENCE ATLAS AIR EO 4753A921.SDR UIEA20070039Duct · crackedNR 3 PYLON AIR VALVE INDICATES 10-PSI IN CRUISE WITH 95 PERCENT N1 SET IS NOT REGULATING CORRECTLY WITH ISOLATION VALVE OPEN. THE LEFT AND RIGHT MANIFOLD PRESSURE ONLY INDICATE 26-PSI. LEAK CHECK FOUND NO FAULT ON ENGINE AREA. SUSPECT CRACKED DUCT ON THE WISDR UIEA2006310Skin Panel · delaminatedLT WING UPPER L/E PANEL HAS A PREVIOUS REPAIR DELAMINATED AND CRACKED, 8.0 IN. BY 5.0 IN. ACCOMPLISHED PERMANENT REPAIR AS PER B747 SRM 51-40-09 FIG 1 AND B747 SRM 51-40-12. ALSO, REFERENCE ATLAS AIR EO 4757A335.SDR UIEA2006309Skin Panel · delaminatedRT WING UPPER SURFACE T/E PANEL HAS 4.0 IN. BY 2.0 IN. AREA OF DELAMINATION LOCATED 30 INCHES I/B OF I/B AILERON. ACCOMPLISHED PERMANENT REPAIR AS PER B747 SRM 51-40-09 FIG 2 AND B747 SRM 51-40-12. ALSO, REFERENCE ATLAS AIR EO 4757A334.SDR UIEA2006307Panel · tornRT WING LOWER PANEL 671AB INBOARD CORNER IS TORN, 2.0 INCH BY 2.0 INCH AREA. ACCOMPLISHED PERMANENT REPAIR AS PER B747 SRM 51-40-09 FIG 1 AND B747 SRM 51-40-12. ALSO REFERENCE ATLAS AIR EO 4757A334.SDR UIEA2006308Firewall · crackedAPU COMPARTMENT TITANIUM FIREWALL, LOWER LT WEB IS CRACKED. ACCOMPLISHED PERMANENT REPAIR AS PER B747 SRM 53-10-04 FIG 30. ALSO, REFERENCE ATLAS EO 4753A866.SDR UIEA2006306Skin Panel · damagedLT WING OUTBOARD MID-FLAP L/E DAMAGE AT OUTBOARD TRACK CUT-OUT. PERMANENT COMPOSITE REPAIR TO L/E WAS ACCOMPLISHED AS PER B747 SRM 51-40-14 AND PERMANENT REPAIR TO RIB SECTION LOCATED AT WBL 794, AS PER B747 SRM 51-40-03 FIG 1. ALSO, REFERENCE ATLAS AIR EO 4SDR UIEA200600302Connector · dirtyON DESCENT, NR 2 ENGINE EGT WENT TO ZERO WITH A VISIBLE BARBER POLE. CLEANED CONNECTOR ON FORWARD LEAD GROUND, OPS CHECKED PER 77-21-00, CHECKED OKAY.SDR UIEA200600300Pdu · failedAIR TURN BACK, ON CLIMB NR 4 LEFT LEADING EDGE FLAP GROUP WOULD NOT RETRACT PNEUMATICALLY. THE GROUP WAS ALREADY ON DEFERRAL FOR BEING INOP ELECTRICALLY. CREW DUMPED 69000 KILOS OF FUEL. UPON RETURN MAINTENANCE REMOVED AND REPLACED NR 4 PDU, ALL OPS AND LEASDR UIEA200600299Gcu · failedAIRCRAFT DIVERTED TO JFK DUE TO NR 3 ENGINE GEN BUS TIE OPEN, FIELD OFF LIGHT ON. ZERO VOLTAGE ZERO FREQS. THEN NR 4 BUS TIE GEN OPEN FIELD OFF LIGHT ON, VOLTS AND FREQS NORMAL. REPLACED NR 3 GCU AND REPLACED THE RT BPCU BOTH ENGINES, OPS CHECKED OKAY AND ASDR UIEA200600296Sensor · unserviceableUNABLE TO MAKE COMPUTED T/O N1 FOR NR 2 ENGINE. REMOVED AND REPLACED NR 2 ENGINE CIT SENSOR IAW MM 73-21-02. CHECKED CDP LINE FOR BLOCKAGE. ACCOMPLISHED VSV/VBV RIG CHECK IAW MM 75-30-00. LEAK CHECK GOOD.
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