Boeing 747-2D7B
Service difficulty reports · 726
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 = '7472D7B' 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 = '7472D7B' 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 UIEA200600131Hydraulic Line · crackedDURING CLIMB NR 4 HYD SYSTEM STARTED DECREASING AND LOW QUANTITY LIGHT CAME ON. FHB PROCEDURES C/W AND QUANTITY WAS STILL DECREASING. ENG PUMP SWITCH WAS POSITIONED TO "SUPPLY OFF" WITH ENGINE RUNNING. QUANTITY INDICATOR ZERO AT COMPLETION OF CHECKLIST. FOSDR UIEA200600136Start Valve · damagedNR4 ENGINE SHUT DOWN AT 1945Z DUE TO NR 4 START VALVE ENGINE LIGHT FLICKERING AND THEN COMING ON. REMOVED AND REPLACED NR 4 START VALVE AS PER AMM 80-11-04. PERFORMED GROUND OPS BY MONITORING SATISFACTORY.SDR UIEA200600121Seal · damagedACCOMPLISHED AIR TURNBACK DUE TO LOSS OF ALL OIL IN ENGINE NR 1, DURING CLIMBOUT. FOLLOWED SHORTLY BY A DROP IN OIL PRESSURE INTO THE MID TO LOWER AMBER BAND. FOUND NR 1 ENGINE HYD PUMP SHAFT SEAL CAVITY LEAKING OIL DURING IDLE RUN. HYD (EDP) PUMP SHAFT SEASDR UIEA200600127Relief Valve · leakingAT 3000 FT DURING CLIMBOUT FIRE DETECTION LIGHT ON PILOT'S CENTER ANNUNCIATOR PANEL ILLUMINATED, FOLLOWED SHORTLY BY A FIRE INDICATION ON NR 1 ENGINE. FIRE CAUSED SEVERE DAMAGE OR SEPARATION, CHECKLIST COMPLETE AS PER FHB 3.701. OVERWEIGHT LANDING AT 287.0 KSDR UIEA200600102Floorbeam · crackedBS 340 FLOORBEAM UPPER CHORD AFT FLANGE 1 HOLE AT RBL 41 FOUND CRACK RUNNING AFT. FLOORBEAM UPPER CHORD AFT FLANGE AT RBL 41" AREA HOLE OVERSIZED BY INCREMENT TO FINAL HOLE SIZE .309" GAGE DISTANCE IS 0.500". E/D= 1.618" WITHIN SB 53A2431 PART 3, TABLE 1 REQSDR UIEA200600101Floorbeam · crackedBS 380 FLOORBEAM UPPER CHORD FWD FLANGE 1 HOLE AT RBL 66 FOUND CRACK RUNNING FWD AND AFT. U/DECK BS 380 FLOORBEAM UPPER CHORD FWD FLANGE AT RBL 66" AREA REPAIRED AS PER SB 53A2431 FIG 9. CONTINUE INSPECTION IS REQUIRED AS PER SB 53A2431 PART 3.SDR UIEA200600100Floorbeam · crackedU/D BS 380 FLOORBEAM UPPER CHORD AFT FLANGE, 1 HOLE AT LBL 60 FOUND CRACK RUNNING AFT. U/DECK BS 380 FLOORBEAM UPPER CHORD AFT FLANGE AT LBL 60" AREA REPAIRED AS PER BS 53A2431 FIG 8. CONTINUE INSPECTION IS REQUIRED AS PER SB 53A2431 PART 3.SDR UIEA200600099Floorbeam · crackedU/D BS 360 FLOORBEAM UPPER CHORD FWD FLANGE, 2 HOLE AT RBL 48 AND 53 FOUND CRACK RUNNING AFT. BS 360 FLOORBEAM UPPER CHORD FWD FLANGE AT RBL 48" AND RBL 53". REPAIRED AS PER SB 53A2431 FIG 9. CONTINUE INSPECTION IS REQUIRED AS PER SB 53A2431 PART 3.SDR UIEA200600098Floorbeam · crackedU/D BS 360 FLOORBEAM UPPER CHORD AFT FLANGE 1 HOLE AT RBL 43 FOUND CRACK RUNNING FWD. U/DECK BS 360 FLOORBEAM UPPER CHORD AFT FLANGE AT RBL 43" AREA. REPAIRED AS PER SB 53A2431 FIG 9. CONTINUE INSPECTION IS REQUIRED AS PER SB 53A2431 PART 3.SDR UIEA200600097Floorbeam · damagedBS 340 FLOORBEAM UPPER CHORD AFT FLANGE 3 HOLE AT LBL 29, 31 AND 32 FOUND CRACKS. BS 340 FLOOR BEAM UPPER CHORD AFT FLANGE LBL 29" OVERSIZE TO .309" AND GAGE DISTANCE .440" E/D = 1.423, WITHIN BS53A2431 PART 3 TABLE 1. REQUIREMENT, REPAIR IS NOT REQUIRED. USDR UIEA200600096Bulkhead · crackedRT SIDE BS 1000 BULKHEAD CHORD AREA, CRACK REVEAL AT BULKHEAD CHORD HEEL AREA APPROX, 2" IN LENGTH JUST BELOW STR 38R. BS 1000 BULKHEAD CHORD BETWEEN STR 36/37R TO STR 40/41R CHORD SEGMENT REPAIRED AS PER SB 747-53A2471 R1. REPEAT INSPECTION IS REQUIRED AS PSDR UIEA200600095Bulkhead · crackedLT SIDE BS 1000, BULKHEAD CHORD AREA, CRACK REVEALED AT BULKHEAD CHORD HEEL AREA APPROX, 1-1/4" IN LENGTH, JUST BELOW STR 38L. BS 1000 BULKHEAD CHORD BETWEEN STR 36/37L TO STR 40/41L CHORD SEGMENT REPAIRED AS PER SB 747-53A2474 R1. REPEAT INSPECTION IS REQUISDR UIEA200600091Brace · chafedPYLON NR 3 DIAGONAL BRACE OUTBOARD SIDE ON ZONE 4 HAS TWO CHAFED AREAS. BLENDED OUT 2 AREAS, ACCOMPLISHED HFEC PER NDT MANUAL D6-7170, PART6 RT4 NO DEFECTS NOTED. ROTO PEEN AREAS, TREATED AND PRIMED AS PER BOEING SB 747-54-2198. REQUIRES REPETATIVE INSPECTISDR UIEA200600090Skin · crackedL-1 DOOR EXTERIOR SKIN, UPPER HINGE CUT OUT AREA OF THE DOOR, PREVIOUS DOUBLER ON THE LOWER EDGE APPEARS TO HAVE A HAIR LINE CRACK INDICATION VISUAL INSPECTION. REMOVED CRACKED DOUBLER, FOUND DOOR SKIN WITH 1/2" CRACK AT UPPER HINGE CUT OUT LOWER AFT CORNER, SDR UIEA200600089Seat Track · damagedMAIN CARGO COMPARTMENT SEAT TRACK HAT SECTION AT BS 1975- RBL 76" WITH A HOLE. REMOVED FLOOR PANEL TO GET ACCESS IAW SRM 51-30-02. CUT OUT DAMAGE SECTION IAW 51-40-04. FABRICATE PARTS PER SAMPLE IAW SRM 51-40-04. ALODINE + PRIMER NEW PARTS IAW SRM 51-10-02SDR UIEA200600088Engine · failedNORMAL TAKEOFF THRUST SET N1 100.1/OAT AND 03.*C WITH AUTOTHROTTLES ON AT 1500. AGL JUST AFTER CLIMB, THRUST SET TO 102.5, NR 4 ENGINE EXPERIENCED A MASSIVE COMPRESSOR STALL AT 2800, MSL. IMMEDIATELY REDUCED THRUST TO NR 4 ENGINE. STALL CEASED AT THAT TIMESDR UIEA200600080Skin · delaminatedLEFT WING UPPER LEADING EDGE PANEL AT NR 2 ENGINE PYLON DELAMINATED AT PREVIOUS REPAIR JUST I/B OF L/E GAP PANEL. REMOVED DAMAGE LEADING EDGE PANEL IAW B-747-200 SRM 51-30-02.SENT TO OUTSIDE SERVICE AIRCRAFT CONNECTION INC. REPAIRED PER SRM 51-40-08 PAGE 1, SDR UIEA200600065Seat Track · brokenMAIN DECK AT APPROX STA 1900 LEFT SIDE SEAT TRACK HAS TWO BROKEN LUGS AT SIDE CARGO DOOR. REPLACED SEAT TRACK PER SRM 53-10-05 AND EO 4753A753.SDR UIEA200600066Duct · blownRTO: DURING T/O ROLL, FIRE DET LIGHT CAME ON WITH HIGH NR 4 EGT AND BOTH NR 4 ENGINE NACELLE TEMPS WERE APPROX 7.0 T/O ABORTED AT 80KTS. BRAKE O/H LIGHT CAME ON LW/RF. REMOVED AND REPLACED DAMAGE 14TH STAGE DUCT LT SIDE, LEAK CK OK REF MM 75-25-00. ACCOMPLISDR UIEA200600061Union · wornATB:LOSS NR 4 HYD SYSTEM AFTER GEAR UP. SYSTEM LEAKING. FOUND UNION ON HYD RETURN LINE WORN, REPLACED OPS AND LEAK CHECKED NORMAL AS PER MM 29-00-00.SDR UIEA200600012Fan Blade · bird strikeON WALKAROUND FOUND NR 3 ENGINE SUSTAINED BIRD STRIKE, FOUND FAN BLADE BENT. PERFORMED CHAPTER FIVE BIRD STRIKE INSPECTION, NO FINDINGS. REMOVED AND REPLACED FAN BLADE. BORESCOPED CORE ENGINE, NO FINDINGS. PERFORMED OPS RUNUPS WITH NO FINDINGS. RELEASED ASDR UIEA200600006Panel · missingON WALKAROUND FOUND NR 1 ENGINE LOWER ACCESS PANEL MISSING.SDR UIEA200500130Skin · damagedDURING D-CHECK, NR 4 PYLON HAD CRACK DAMAGE IN THE SKIN ASSEMBLY AND THE ADJACENT NR 3 STIFFENER, AT PRECOOLER EXHAUST CUTOUT LOWER EDGE NEAR THE AFT CORNER AT STATION 248. THE NR 3 STIFFENER LOWER FLANGE WAS TRIMMED TO REMOVE CRACKS. THE CRACK IN THE SKIN ASDR UIEA200500129Skin · crackedDURING D-CHECK, FOUND NR 3 PYLON, CRACKED DAMAGE WAS FOUND IN THE SKIN ASSEMBLY AND THE ADJACENT NR 3 STIFFENER, AT PRECOOLER EXHAUST CUTOUT LOWER EDGE NEAR THE AFT CORNER AT STATION 248. THE NR 3 STIFFENER LOWER FLANGE WAS TRIMMED TO REMOVE CRACKS. THE CRACSDR UIEA200500128Skin · damagedDURING D-CHECK FOUND NR 2 PYLON HAS CRACK DAMAGE IN THE SKIN ASSEMBLY AND THE ADJACENT NR 3 STIFFENER, AT PRE-COOLER EXHAUST CUTOUT LOWER EDGE NEAR THE AFT CORNER AT STATION 248. THE NR 3 STIFFENER LOWER FLANGE WAS TRIMMED TO REMOVED CRACKS. THE CRACK IN THESDR UIEA200500127Skin · crackedDURING D-CHECK, NR 1 PYLON HAD CRACK DAMAGE IN THE SKIN ASSEMBLY AND THE ADJACENT NR 3 STIFFENER, AT PRECOOLER EXHAUST CUTOUT LOWER EDGE NEAR THE AFT CORNER AT STATION 248. THE NR 3 STIFFENER LOWER FLANGE WAS TRIMMED TO REMOVE CRACKS. THE CRACK IN THE SKIN SDR UIEA200500124Support · crackedD-CHECK, NR 2 PYLON, RT LWR AFT SKIRT FAIRING LOWER STIFFENER CRACKED. STOPPED DRILLED THE CRACK. NDT AND HFEC INSPECTED ALL AFFECTED FASTENER HOLES AND REPAIR AREA TO ENSURE CRACKS AND DAMAGE FREE CONDITION. FABRICATED AND INSTALLED 0.050 INCH THICK REPAIRSDR UIEA200500123Skin · chafedD-CHECK, DURING MAINTENANCE INSPECTION, THE NR 2 STRUT RT SIDE SKIN ASSEMBLY INTERNAL BONDED DOUBLER WAS FOUND CHAFED AT THE 463AR ACCESS PANEL CUTOUT. THE INTERNAL DOUBLER AND SKIN WERE TRIMMED BACK PAST THE EXISTING CUTOUT IN THE OUTER SKIN. THE REPAIR ARESDR UIEA200500122Pressure Panel · crackedD-CHECK, FUSELAGE STA 1241 SLOPING PRESSURE DECK WEB WAS FOUND WITH CRACK AT DUCT CUTOUT. THE CRACKED AREA REPAIRED BY CUTTING EXISTING WEB SECTIONS BETWEEN UPPER EDGE OF THE SLOPING DECK AND REAR SPAR AND FROM BL 0 TO TRIM LINE. HFEC INSPECTED THE EDGE OF TSDR UIEA200500121Angle · out of limitsD-CHECK, NR 4 PYLON SIDE COWL HINGE SUPPORT ANGLE BRACE, ONE HOLE EXCEEDING LIMITS. THE HOLE WAS OVERSIZED TO 0.484 INCHES DIAMETER INCLUDING A .0312 DIAMETER INSURANCE CUT. THE HOLE WAS NDT INSPECTED TO ENSURE A CRACK AND DAMAGE FREE CONDITION. A REPAIR STSDR UIEA200500120Trunnion · chafedD-CHECK, RECESSED MARK ON RT BODY GEAR IB TRUNNION SUPPORT FITTING. THE RECESSED MARK WAS BLENDED OUT WITH A MINIMUM 63 RHR SURFACE FINISH. 10X VISUALLY AND HFEC INSPECTED TO ENSURE CRACK AND CORROSION FREE CONDITION. ALODINED AND REINSTATED THE FINISH. FISDR UIEA200500056Control System · intermittentAFTER ROLLING OUT 360 DEGREES, VOR COURSE INBOUND, ALL NAV INDICATIONS, OK. AFTER DESCENDING TO FL 10.0 JUST PRIOR TO CROSSING THE VOR SELECTED ILS FREQ ON CAPT AND FO MCP, BOTH HIS SELECTOR SWITCHES WERE SET TO ILS AND NAV MODE ON ILS. CPT HAD COURSE AND G/SDR UIEA200500045Structure · crackedLOUD AIR LEAK FROM AROUND DOOR ON MAIN CARGO DECK. AREA BY PALLET POSITION LR-MR. AFT OBSERVATION WINDOW DOOR. REMOVED AND INSTALLED NR 4 MAIN ENTRY DOOR IAW AMM. LEAK CHECK IAW AMM. NO LEAK NOTED. CABIN PRESSURIZATION LEAKAGE TEST ACCOMPLISHED IAW MM. SDR UIEA200500038Spar · corrodedDURING SCHEDULE INSPECTION, CORROSION WAS FOUND ON THE REAR SPAR ATTACHMENT HOLES OF NR 5 TRAILING EDGE FLAP TRACK. OVERSIZED THE AFFECTED ATTACHMENT HOLES. MAGNETIC PARTICLE INSPECTED THE REWORKED AREA TO ENSURE CRACK AND DEFECT FREE CONDITION. THE REPAIRESDR UIEA200500039Skin · delaminatedDURING SCHEDULE INSPECTION, DELAMINATION WAS FOUND ON THE OUTBOARD TRAILING EDGE FLAP AFT FLAP LOWER SKIN PANEL. PANELS EXCEEDED 25 PERCENT DAMAGE OF THE TOTAL AREA. TRIMMED OUT THE DELAMINATED SKIN REGIONS. NDT INSPECTED TO ENSURE CRACK AND DEFECT FREE CONSDR UIEA200500037Mount · crackedDURING SCHEDULED INSPECTION, NR 4 PYLON, BULKHEAD UPPER CHORD CRACKED AT STATION 270. STOP DRILLED THE CRACK PER 747 SRM 51-10-01. NDT INSPECTED THE REPAIR AREA, INCLUDING HFEC INSPECTION OF ALL TRIMMED FLANGE EDGES AND STOP DRILLED HOLES TO ENSURE CRACK REMSDR UIEA200500034Skin · dentedDURING INSPECTION, FOUND DENT (SKIN WRINKLE) NR 2 NACELLE STRUT INBOARD SKIN BETWEEN NACELLE STATION 286 TO 300.1. CONFIRMED THAT THE AFFECTED WAS FREE FROM DISCOLORATION. NDT CONDUCTIVITY MEASURED READING ACCOMPLISHED. HFEC INSPECTED AND WAS FOUND TO BE DASDR UIEA200500035Bulkhead · crackedDURING SCHEDULED INSPECTION, NR 1 PYLON, THE BULKHEAD UPPER LEFT SIDE FORWARD AND AFT CHORD ANGLES WERE FOUND CRACKED. TRIMMED AND STOP DRILLED THE CRACK PER 747 SRM 51-10-01 NDT INSPECTED THE REPAIRED AREA, INCLUDING HFEC INSPECTION OF ALL TRIMMED FLANGE EDGSDR UIEA200500036Bulkhead · crackedDURING SCHEDULED INSPECTION, NR 3 PYLON, THE BULKHEAD UPPER LEFT AND RIGHT SIDE FORWARD CHORD ANGLES WERE FOUND CRACKED. STOP DRILLED THE CRACK PER 747 SRM 51-10-01. NDT INSPECTED THE REPAIR AREA, INCLUDING HFEC INSPECTION OF ALL TRIMMED FLANGE EDGES AND STOSDR UIEA200500029Bulkhead · crackedDURING SCHEDULE MAINTENANCE, THE BULKHEAD UPPER LEFT AND RIGHT SIDE FORWARD CHORD ANGLES WERE FOUND CRACKED, NR 2 PYLON. STOPPED DRILLED THE CRACK END AND NDT INSPECTED TO ENSURE CRACK CONTAINMENT. INSTALLED ALUMINUM REPAIR ANGLES COMMON TO THE UPPER FORWARDSDR UIEA200500028Frame · crackedDURING DESCENT, CABIN STILL CLIMBS APPROX 800 PER MINUTE WITH THROTTLES AT IDLE. REPEAT ITEM, SEE LOG PAGE 548463 ITEM 1. REMOVED AND REPLACED R2 DOOR ASSEMBY DUE TO CRACK IN DOOR FRAME PER MM 52-11-01. PER BOEING TELECOM 1-195VDL CONVERTED DOOR TO CARGO FRSDR UIEA200500030Link · migratedDURING SCHEDULE MAINTENANCE, NR 4 T/E FLAP TRACK FAIL/SAFE LINK TOP END BEARING ON THE 'T' CHORD FOUND MIGRATED. THE LEFT FIXED TRAILING EDGE UPPER CHORD HOLE HAS ELONGATED DAMAGED. OVERSIZED HOUSING BORE TO A MAXIMUM OF .8930 INCH DIAMTER. NDT INSPECTED THSDR UIEA200500025Skin · crackedDURING INSPECTION, NR 16 KRUEGER FLAP, FOUND CRACK AT PANEL ATTACH FASTENER HOLE. TRIMMED OUT AFFECTED SPAR SEGMENT. NDT INSPECTED TO ENSURE CRACK AND DEFECT FREE CONDIION. INSTALLED REPAIR FILLER AND ALUMINUM REPAIR ANGLE WITH ADDITIONAL FASTENERS. REFINISDR UIEA200500027Spar · crackedDURING SCHEDULED MAINTENANCE, NR 3 PYLON INBOARD MIDSPAR CHORD WAS FOUND CRACKED ON THE VERTICAL FLANGE. THE AFFECTED SECTION OF CHORD WAS TRIMMED OUT. NDT INSPECTION WAS PERFORMED AT TRIMMED EDGES AND AT AL AFFECTED FASTENERS LOCATION TO ENDURE A CRACK AND SDR UIEA200500026Bulkhead · crackedDURING INSPECTION, .5 INCH CRACK FOUND ON RT WHEEL WELL SLOPING PRESSURE DECK AT STATION 1240, RBL 35. THE CRACK ORIGINATED FROM THE WATER LINE CONNECTOR HOLE AND EXTENDS UPWARDS. THE CRACKED SLOPING PRESSURE DECK WEB WAS TRIMMED OUT AND REPAIRED WITH DOUBLESDR UIEA200500023Frame · chafedD-CHECK AT SINGAPORE, DURING INSPECTION GOUGES WERE FOUND ON THE STATION 2460 BULKHEAD INNER T-CHORD TOP SURFACE AT LBL 30, AND WL 235. BLENDED OUT THE DAMAGED AREA AND INSTALLED A REPAIR STRAP OF .0710 INCH THICK CLAD 2040-T3 MATERIAL. (M)SDR UIEA200500024Fitting · elongatedDURING INSPECTION, REPORTED ELONGATED HOLES IN THE TEN LATCH FITTING OF THE MAIN DECK SIDE CARGO DOOR. THE TEN LATCH FITTING WERE REWORKED WITHIN ALLOWABLE REWORK LIMITS. (M)SDR UIEA200500019Link · gougedDURING D-CHECK, DEEP GOUGE FOUND ON THE EDGE OF THE INBOARD LINK ON THE NR 18 VARIABLE CAMBER FLAP. BLENDED OUT DAMAGE FROM SURFACE OF LINK. NDT INSPECTED TO ENSURE CRACK AND DEFECT CONDITION. SHOP PREENED PER SOPM 20-10-03, INTENSITY .006A2. REFINISHED LISDR UIEA200500016Skin · crackedDURING INSPECTION, NR 4 PYLON, CRACK DAMAGE WAS FOUND AT PRE-COOLER EXHAUST CUTOUT LOWER AFT CORNER AT NACELLE STATION 248. THE NR 3 STIFFENER WAS REINFORCED WITH A NEW STEEL LOWER REPAIR ANGLE FROM NACELLE STATION 235 TO STATION 254. THE RIB INSTALLATION ATSDR UIEA200500015Skin · crackedDURING INSPECTION, NR 3 PYLON, CRACK DAMAGE WAS FOUND AT PRE-COOLER EXHAUST CUTOUT LOWER AFT CORNER AT NACELLE STATION 248. THE NR 3 STIFFENER WAS REINFORCED WITH A NEW STEEL LOWER REPAIR ANGLE FROM NACELLE STATION 235 TO 254. THE RIB INSTALLATION AT NACELLE
Back to Boeing 747-2D7B