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 UIEA200500017Cap · chafedDURING SCHEDULED MAINTENANCE, CHAFING MARK WAS FOUND ON THE LEFT SIDE OF THE SKIN ASSEMBLY AT NACELLE STATION 270. AFFECTED FASTENERS WERE REMOVED AND FASTENER HOLES WERE HFEC INSPECTED TO ENSURE CRACK AND DAMAGE FREE CONDITION. THE CHAFING DAMAGE WAS REMOVESDR UIEA200500014Skin · crackedDURING INSPECTION, NR 2 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 NS 235 TO STA 254. THE RIB INSTALLATION AT NACELLE STATION SDR UIEA200500008Fire Loop · chafedFLT EI 9867 - ON TAKEOFF ROLL, NR 4 ENGINE FIRE WARNING LIGHT AND BELL CAME ON. MAX BRAKES APPLIED AT 95 KTS. TAKEOFF ABORTED. INSPECTED NR 4 ENGINE, NO PRIMER DISCOLORATION OR ANY SIGN OF HEAT DAMAGE. PERFOMED NR 4 ENGINE PNEUMATIC LEAK CHECK, NORMAL PER SDR UIEA200500011Actuator · failedDURING CRUISE, NR 2 CROSSFEED VALVE DOES NOT OPEN. TRANSITION BLUE LIGHT STAYS ON. REMOVED AND REPLACED NR 2 CROSSFEED VALVE ACTUATOR IAW MM 28-22-02. OPS CHECK SATISFACTORILY S/N OFF 90060. (M)SDR UIEA200500006Control Panel · failedAIRCRAFT DIVERTED DUE TO (ILS LOC AND GS NOT RECEIVABLE) ON BOTH CAPTAIN AND FO HSI, ALL FLAGS VISIBLE ON BOTH SIDES INDICATING COMPLETE FAILURE OF THE ILS NAV CONTROL PANEL. REPLACED ILS CONTROL PANEL IAW MM 34-31-01 PERFORMED OPS CHECK ON ILS SYSTEM OK IAW SDR UIEA200400206Mechanism · brokenAFTER TAKEOFF AT APPROX 2,500 FT, THE LT ENTRY DOOR (L1) DOOR LIGHT CAME ON. ACCOMPLISHED CHECK LIST. THEN HEARD A LOAD NOISE WITH AIRCRAFT PRESS CLIMBING. RETURNED TO SFO. AFTER LANDING, FOUND DOOR LOCKING LUG BROKEN OFF. ACCOMPLISHED DETAILED INSPECTIONSDR UIEA200400201Structure · missingPOST FLIGHT INSPECTION, FLT EK4979, 07/DEC/2004. DURING INSPECTION, FOUND NR 4 ENGINE AFT CENTER BODY CRACKED OFF. MISSING, LAST 20 INCHES FROM T/E. REMOVED AND REPLACED NR 4 ENGINE AFT CTR BODY IAW MM 78-11-02. INSPECTED AREA AFT OF NR 4 ENGINE FLAPS, WINSDR UIEA200400198Actuator · leakingDURING CLIMB-OUT, NR 4 HYDRAULIC SYSTEM LOW QUANTITY LIGHT CAME ON WITH A DROP OF SYSTEM QUANTITY OIL FROM 8.5 TO 2.5, SYSTEM WAS SHUTDOWN. QUANTITY REMAINED AT 2.5. TURNED ADP TO CONTINUOUS, QUANTITY STARTED DROPPING, SYSTEM SHUTDOWN. REF: LOG PAGE 537018,SDR UIEA200400190Pdu · failedDURING CLIMB-OUT, NR 3 LEADING EDGE FLAP WOULD NOT RETRACT. REMOVED AND REPLACED NR 3 LE PDU. OPS CHECK OK IAW MM 27-81-03. PDU OFF PN 126344-17-1, SN 22337, TOTAL MAINT DELAY, 3 HRS, 17 MIN. NOTE: NO FUEL WAS DUMPED.SDR UIEA200400181Cadc · failedHKG/BEL - AFTER DEPARTURE NR 2 ALTIMETER BECAME ERRATIC WITH ALT ALERT SOUNDING ENTER FOLLOWED BY AIRSPEED MACH INDICATOR FLAG AND SAT IND OF .05, SUSPECT RN 2 CADC FAILED. CHANGED NR 2 CADC IAW MM 34-12-01/401. CADC NR 2 OPERATIONAL TEST IAW MM 34-12-00 SATSDR UIEA200400171Wire · damagedDURING CLIMB AT FL15.0, NR 4 ENG NACELLE 'B' IND WENT OT 6.0. 'A' IND 3.1. THRUST LEVEL 110.0, N1 & EGT NORMAL ON ALL ENGS. 'B' IND RETURNED TO 3.5 AT FL25.0 WITH CLIMB POWER SET. NR 4 ENG 'A' & 'B' INDS WENT TO 8,0 & EGT ON NR 4 ENG WENT TO 940 & NR 4 THRSDR UIEA200400155Indicator · malfunctionedABORTED TAKEOFF, CAPTAINS AIRSPEED INDICATED 80 KNOTS. FIRST OFFICERS INDICATED 0. AIRCRAFT RETURNED TO BLOCKS CAPTAIN IND 100 KNOTS, F/O'S IND 0. CHECKED BRAKE TEMPERATURE FOR POSSIBLE HIGH ENERGY STOP. INDICATED NORMAL RANGE, NO FURTHER INSPECTION REQUIRSDR UIEA200400157Bulkhead · corrodedDURING SCHEDULED MAINTENANCE, FS 1350 BULKHEAD WED FOUND CORRODED NEAR STRINGER 1L LEVEL OF CORROSION, LEVEL 1, MINOR. TRIMED OUT CORRODED AREA. REMOVED NICKS, SCRATCHES, GOUGES, BURRS AND SHARP EDGES FROM THE REPAIR PART. PERFORMED HFEC INSPECTION TO ENSURESDR UIEA200400154Seat Track · damagedMAIN DECK SEAT TRACK CROWN DAMAGE 3 INCHES AT STATION 1802. DAMAGED SECTION OF SEAT TRACK WAS REPLACED IAW SRM 51-10-05. (M)SDR UIEA200400148Computer · failedMIA/LAX - EN ROUTE AFTER LEAVING MIAMI THE F/O PRESSURE ALTIMETER FLUCTUATING UNCONTROLLABLE AND MACH INDICATOR FLAP ALTERNATELY COMING IN VIEW. WITH A DIFFERENCE IN MACH SPEED OF 6.5, CAPTAIN 79 MACH. F/O .19 MACH INDICATED. SUSPECT F/O CADS. REMOVED AND SDR UIEA200400137Fitting · crackedFOUND DURING D-CHECK AT SIN, DAMAGE WAS FOUND AT FASTENER HOLE IN THE FITTING AFT VERTICAL FLANGE. THE DAMAGE WAS COMPLETELY REMOVED BY OVERSIZING THE HOLE TO .4521-4541 INCHES DIAMETER. AN OVERSIZE FASTENER AS THE SAME DESIGN TYPE REQUIRED, WAS INSTALLED ATSDR UIEA200400138Fuel Tank · corrodedFOUND DURING D-CHECK, AT SIN, CORROSION AT WING CENTER SECTION UPPE SKIN AT REAR SPAR BETWEEN BL 0 AND RBL 11.33. CORROSION WAS BLENDED USING A 20:1 RATIO, 125 RHR OR BETTER AND REMAINING THICKINESS TO BE .381 INCH OR GREATER. BLENDED AREA WAS SHOP/FLAP PEENSDR UIEA200400134Skin · crackedDUIRNG SCHEDULE MAINTENANCE, FOUND CRACK DAMAGE AT PRE-COOLER EXHAUST CUTOUT LOWER AFT CORNER AT NACELLE STATION 248, NR 4 PYLON. TRIMMED THE NR 3 STIFFENER BASE BOTTOM TO REMOVE THE CRACK. TRIMMED THE SKIN ASSEMBLY AND WINDOW STRAP. NDT INSPECTED EACH REPASDR UIEA200400133Skin · crackedDURING SCHEDULED MAINTENANCE, FOUND CRACK DAMAGE AT PRE-COOLER EXHAUST CUTOUT LOWER AFT CORNER AT NACELLE STATION 248, NR 3 PYLON. TRIMMED THE NR 3 STIFFENER BASE BOTTOM TO REMOVED THE CRACK. TRIMMED THE SKIN ASSEMBLY AND WINDOW STRAP. NDT INSPECTED EACH RESDR UIEA200400131Skin · crackedDURING SCHEDULE MAINTENANCE, FOUND CRACK DAMAGE AT PRE-COOLER EXHAUST CUTOUT LOWER AFT CORNER AT NAC STATION 248, NR 1 PYLON. TRIMMED THE NR 3 STIFFENER BASE BOTTOM TO REMOVE THE CRACK. TRIMMED THE SKIN ASSEMBLY AND WINDOW STRAP. NDT INSPECTED EACH REPAIR ASDR UIEA200400132Skin · crackedDURING SCHEDULE MAINTENANCE, FOUND CRACK DAMAGE AT PRE-COOLER EXHAUST CUTOUT LOWER AFT CORNER AT NACELLE STATION 248, NR 2 PYLON. TRIMMED THE NR 3 STIFFENER BASE BOTTOM TO REMOVE THE CRACK. TRIMMED THE SKIN ASSEMBLY AND WINDOW STRAP. NDT INSPECTED EACH REPASDR UIEA200400130Housing · corrodedDUIRNG SCHEDULED MAINTENANCE, FOUND CORROSION DAMAGE AT THE MAIN BEARING HOUSING BORE OF THE LEFT WING INBOARD TRAILING EDGE MID-FLAP CARRIAGE BEARING HOUSINGS ASSEMBY. REAMED BORE TO 6.100 INCHES DIAMETER AND REMOVED LOCAL SURFACE DAMAGE FROM AFFECTED AREA OFSDR 2004F00359Panel · delaminatedDURING FA12 A-CHECK ACCOMPLISHING ROUTINE WORK CARD 11M15002 INSPECTION OF LEFT WING UPPER SURFACE, FOUND LEFT LEADING EDGE INBOARD OF NR 1 PYLON PANEL VOIDED UPPER SURFACE WING STATION 1116 PANEL. T64R (M)SDR 2004F00354Seat Track · crackedDURING FA12 A-CHECK ACCOMPLISHING ROUTINE WORK CARD 02EM15002 INSPECTION OF MAIN CABIN FOUND MAIN CARGO DECK LEFT OUTBOARD FLOOR TRACK BROKEN OUT AT FUSELAGE STATION 1820. (M) T64RSDR UIEA200400124Thermal Switch · failedSHORTLY AFTER LEVEL OFF AT FL30.0 RIGHT WING OVERHEAT LIGHT ILLUMINATED. CHECK LIST PERFORMED, LIGHT EXTINGUISHED BEFORE 5 MINUTES CONTINUED AGAIN, COMPLETED CHECKLIST LIGHT STAYED ON NR 3 AND NR 4 BLEED VALVES CLOSED, RIGHT ISOLATION VALVE CLOSED ZERO AIR PRSDR UIEA200400119Indicator · malfunctionedDURING CLIMB, WHEN CLEARED INS WAYPOINT AND SELECTING INS MDU, CDI ON C/A AND F/O HSI WOULD NOT CENTER X WHEN CLEARED VOR AND SELECTING ON INS MDU, HSI SHOWED ABOUT 30 DEGREE DIFFERENCE IN UPDATE. EXCESSIVE DIFFERENCE IN DRIFT ON ARRIVAL . 23400 FUEL DUMPED.SDR UIEA200400106Door · crackedR-4 DOOR LOWER AFT CORNER HAS 2 CRACKS, ONE CRACK IS 4 INCHES AND THE OTHER CRACK IS 3 INCHES, STA 1715, W/L 199.8. CAUSE OF DAMAGE UNKNOWN. CRACKS FOUND DURING VISUAL INSPECTION. INSTALLED DOUBLER REPAIR IAW SRM.SDR UIEA200400095Slide · deployedDURING TEST, THE UPPER DECK SLIDE FAILED TO FULLY DEPLOY. SLIDE (PN 7A14124, SN GU148 WAS REMOVED AND REPLACED WITH A NEW SLIDE PN 7A1248-36, SN G639.SDR UIEA200400098Brake · damagedGT9813/24 RME/JFK BRAKE TEMPERATURE OVERHEAT LIGHT: BRAKE TEMPERATURE OVERHEAT LIGHT ILLUMINATED DURING TAXI-IN. LEFT BODY, LEFT REAR BRAKE TEMPERATURE APPROXIMATELY INDICATING 7.40. FOUND NR 7 BRAKE DAMAGED, REMOVED AND REPLACED SAME IAW MM, LEAK CHECKS GOSDR UIEA200400088Warning Switch · out of adjustCARGO DOOR LIGHT ANNUNCIATOR LIGHT CAME ON IN FLIGHT AS WELL AS FORWARD CARGO LIGHT ON F/E PANEL. FHB PROCEDURE CARRIED OUT. ADJUSTED DOOR WARNING SWITCH. OPERATED DOOR SEVERAL TIMES, DOOR LIGHTS NORMAL, ALL OFF WHEN DOOR CLOSED MM 52-34-00/501. AIRCRAFT WSDR UIEA200400051Bushing · worn(D) CHECK, DURING SCHEDULE MAINTENANCE, NR 8 MOVEABLE CANOE AFT SECTION SECONDARY DOOR ASSEMBLY LOWER BEARING FOUND MIGRATED. THE LUG BORES ARE OVERSIZED TO 0.7827 INCH DIAMETER TO REMOVE DAMAGE. NDT INSPECTED TO ENSURE CRACK AND DEFECT FREE. AN ALUMINUM RESDR UIEA200400050Skin · crackedD CHECK, DURING SCHEDULE MAINTENANCE. CRACKS WERE FOUND ON NR 4 PYLON PRECOOLER EXHAUST CUTOUT AFT LOWER CORNER. ON THE RT SIDE OF STRUT STRUCTURE ASSEMBLY, THE OUTER SKIN WAS TRIMMED. NDT INSPECTION WAS ACCOMPLISHED TO ENSURE CRACK AND DEFECT FREE CONDITIOSDR UIEA200400049Skin · crackedD CHECK, DURING SCHEDULE MAINTENANCE. CRACKS WERE FOUND ON NR 3 PYLON PRECOOLER EXHAUST CUTOUT AFT LOWER CORNER. ON THE RT SIDE OF STRUT STRUCTURE ASSY, THE OUTER SKIN WAS TRIMMED. NDT INSPECTION WAS ACCOMPLISHED TO ENSURE CRACK AND DEFECT FREE CONDITION. SDR UIEA200400048Skin · crackedD CHECK, DURING SCHEDULE MAINTENANCE. CRACKS WERE FOUND ON NR 2 PYLON PRECOOLER EXHAUST CUTOUT AFT LOWER CORNER. ON THE RT SIDE OF STRUT STRUCTURE ASSY, THE OUTER SKIN WAS TRIMMED. NDT INSPECTION WAS ACCOMPLISHED TO ENSURE CRACK AND DEFECT FREE CONDITION. SDR UIEA200400047Skin · crackedD CHECK, DURING SCHEDULE MAINTENANCE. CRACKS WERE FOUND ON NR 1 PYLON PERCOOLER EXHAUST CUTOUT AFT LOWER CORNER. ON THE RT SIDE OF STRUT STRUCTURE ASSY, THE OUTER SKIN WAS TRIMMED. NDT INSPECTION WAS ACCOMPLISHED TO ENSURE CRACK AND DEFECT FREE CONDITION. SDR UIEA200400045Beam · crackedD CHECK, CRACKS WERE FOUND AT RT WING LE LOWER OUTBOARD BEAM LOCATIONS AT ILES 414.50 AND 543.93. TRIMMED OUT CRACKED PORTIONS OF BEAM NDT INSPECTED TO ENSURE CRACK AND DEFECT FREE CONDITION. SPLICED IN REPLACEMENT SECTIONS OF BEAM BETWEEN TRIM LINES AND PROSDR UIEA200400044Stiffener · crackedD CHECK, DURING SCHEDULE MAINTENANCE OF NR 1 PYLON, THE LHS NR 5 STIFFENER END WAS FOUND CRACKED AT NAC STA 288.0 WL 146.5. TRIMMED OFF THE CRACKED STIFFENER END. FABRICATED A REPAIR PLATE TO MATCH THE TRIMMED OFF PORTION OF THE STIFFENER ATTACHING FLANGE. SDR UIEA200400042Skin · dentedD CHECK, DURING A MAINTENANCE INSP, WRINKLED SKIN/ DENTS WERE FOUND ON THE EXTERIOR SKIN ASSEMBLY OF NR 3 PYLON JUST AFT OF THE TITANIUM DOUBLER, BETWEEN THE MID SPAR CORD AND NR 5 STIFFENER. AFFECTED SKIN ASSEMBLY WAS TRIMMED TO REMOVE DAMAGE. NDT INSP, INCSDR UIEA200400041Skin · dentedDURING A MAINTENANCE INSPECTION, WRINKLED SKIN/ DENTS WERE FOUND ON THE EXTERIOR SKIN ASSEMBLY OF NR 2 PYLON JUST AFT OF THE TITANIUM DOUBLER, BETWEEN THE MID SPAR CHORD AND NR 5 STIFFENER. AFFECTED SKIN ASSEMBLY WAS TRIMMED TO REMOVE DAMAGE. NDT INSPECTION,SDR UIEA200400043Frame · crackedD CHECK, DURING SCHEDULE MAINTENANCE INSPECTION OF NR 3 PYLON, THE BULKHEAD UPPER ASSEMBLY RHS FORWARD ANGLE FRAME FLANGE WAS FOUND CRACKED AT THE END FASTENER HOLE COMMON TO THE FRONT SPAR FITTING AND STRUT CAP SKIN ASSY. FABRICATED A REPAIR ANGLE TO RESTORESDR UIEA200400039Floorbeam · damagedDURING D CHECK, FOUND UPPER DECK FLOORBEAM, ONE ELONGATED HOLE WITH A SHORT EDGE MARGIN WAS FOUND COMMON TO STA 360 UPPER DECK FLOORBEAM UPPER CORD. THIS AIRCRAFT WAS MODIFIED TO A SPECIAL FREIGHTER CONFIGURATION. OVERSIZED SME HOLE TO 0.250 INCH DIAMETER (CSDR UIEA200400038Skin · dentedDURING D CHECK, SKIN DENT FOUND ON FWD CARGO DOOR CUTOUT. A SKIN GOUGE ON THE SKIN OF THE FORWARD CARGO DOOR CUTOUT AFT SKIN EDGE, BS670, BETWEEN S-37 AND S-38 WAS REPAIRED BY TRIMMING OUT THE GOUGE. A HFEC AND DETAILED VISUAL INSPECTION WITHIN 20 INCHES WASSDR UIEA200400037Housing · corrodedDURING D CHECK AT SIN, PITTED CORROSION FOUND OUTBOARD TRAILING EDGE MID-FLAP IB CARRIAGE BRG HOUSING. REMOVED LOCAL SURFACE DAMAGE FROM THE AFFECTED AREA OF HOUSING. NDT INSPECTED TO INSURE CRACK AND DEFECT FREE CONDITION. SMOOTH, BLENDED AND REFINISHED HOSDR UIEA200400034Fire Loop · chafedAT APPROXIMATELY 10,000 FT, NR 2 ENIGNE 'A' LOOP WAS INDICATING 7 UNITS, 'B' LOOP INDICATING 2.5. COMPLETED FHB 3.26.10 PROCEDURES NACELLE TEMPERATURE INDICATION ABNORMAL. RETARDED THROTTLE NO CHANGE, 30 SECON LATER 'A' LOOP INDICATES 9 PLUS, 'B' LOOP FLUCTUSDR UIEA200300065Throttle · stuckNR 3 ENGINE THROTTLE STUCK AT POSITION IT WAS IN AT CRUISE POWER. IT FINALLY CAME LOOSE AT 10,000 FT. SHUT DOWN ENGINE AT 10,000 FT AND RESTARTED BETWEEN 10,000 FT AND 4,000 FT. OPERATED OK AFTER START. INSPECTED NR 3 ENGINE FOR WINDMILLING PER MM 72-00-00SDR UIEA200300066Engine · leakingDOV-RMS - NR 3 ENGINE SHUTDOWN DUE TO ZERO OIL QUANTITY AND PERSSUER BELOW 10 PSI WITH LOW OIL PRESSURE LIGHT ON AT 1509Z. AFTER SHUTDOWN OIL PRESSURE WENT TO ZERO WHILE WINDMILLING. AIRCRAFT DIVERTED TO AMS. REMOVED AND REPLACED ENGINE NR 3 ACCORDING TO MMSDR UIE2003F00001Warning System · malfunctionedDURING TAKEOFF AT APPROXIMATELY 75 KNOTS, PILOTS LEADING EDGE FLAP INDICATED UNSAFE WITH F/E LT WING PANEL LEADING EDGE FLAP INDICATORS ALSO INDICATING UNSAFE. NO WARNING HORN WAS HEARD AT ANY TIME DURING TAKEOFF. VISUALLY AND MANUALLY CHECKED ALL LEFT WING SDR UIEA200300056Controller · malfunctionedDURING CRUISE FL370, PACKS NR 1 & 2 OPERATING, NR 1 PACK AIRFLOW APPROX 20 PSI & NR 2 PACK AIRFLOW 33 PSI, CABIN BEGAN TO CLIMB RAPIDLY. RATE LIMIT LIGHT ON. CABIN SHOWED A MOMENTARY DESCENT THEN BEGAN TO CLIMB RAPIDLY. SELECTED MANUAL PRESSURE. CABIN CONSDR UIEA200300043Transmitter · looseTLV - ACCEPTANCE FLIGHT FROM C-CHECK AIR TURNBACK, AFTER TAKEOFF DURING FLAP RETRACTION INBOARD FLAPS STOPPED AT 19 DEGREES INDICATES FLAP ASYMMETRY. AIRCRAFT RETURNED TO TLV. NO FUEL DUMPED. FOUND RIGHT OUTBOARD FLAP TRANSMITTER LOOSE. TIGHTENED TRANSMITTSDR UIEA200300020Trunnion · lack of lubeNOSE LANDING GEAR WOULD NOT EXTEND NORMALLY. EXTENDED OK WITH ALTERNATE SWITCH. LUBRICATED NOSE LANDING GEAR TRUNNIONS PER MM 12-21-01. JACKED AIRCRAFT PER MM 7-11-02. RESET ALTERNATE GEAR SYSTEM PER 32-36-00 AND ACCOMPLISHED NOSE LANDING GEAR SWING PER 32
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