Boeing 747-228F
Service difficulty reports · 199
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 = '747228F' 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 = '747228F' 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 VGQY2010081000067Floorbeam · crackedHFEC OPEN HOLE INSP CARRIED OUT AND FOUND ONE HOLE WITH CRACK INDICATION AT BS 520 UPPER DECK FLOORBEAM UPPER CHORD FWD FLANGE LBL 17 AT 12 O'CLOCK BY PLAIN VIEW. COMPLIED WITH EN 1191-10.SDR VGQY2010080600062Structure · crackedMAIN DECK CARGO, MAIN ENTRANCE DOOR 1L, UPPER HINGE CUTOUT FOUND CRACK. STOP DRILL CARRIED OUT AS PER SRM 52-10-02 AND SRM 51-10-01 REVISION 117. FABRICATED REPAIR DOUBLER USING MATERIAL AMS 5518-0.050 INCH AS PER SRM 52-10-02 FIGURE 12 REVISION 117. CADMIUMSDR VGQY2010080600061Stringer · corrodedMAIN DECK CARGO, MAIN ENTRANCE DOOR 1L, UPPER HINGE CUTOUT FOUND CRACK. CORRODED STRINGER 29L TRIMMED-OFF PER SRM 53-10-03 REV 117, FIGURE 1. NEW REPAIR STRINGER AND SPLICE FABRICATED AS PER SRM 53-10-03 REV 117, FIGURE 1. NEW REPAIR STRINGER AND SPLICE INSDR VGQY10080600061AStringer · crackedAFT CARGO COMPT STRINGER 29L FOUND CRACKED AT SPLICE STA 1730-1740 LT.SDR VGQY2010080500059Frame · crackedCRACK FOUND ON NR 3 PYLON REAR ENGINE MOUNT BULKHEAD, INBOARD FORWARD FRAME, FROM BOTTOM 3RD FASTENER HOLE TO EDGE WITH LENGTH OF APPROX 0.25 INCH. BULKHEAD WEB CRACKED AREA TRIMED-OFF, REPAIR DOUBLER AND FILLER FABRICATED AND INSTALLED PER B747 SRM 54-11-03 SDR VGQY2010080500060Skin · corrodedFUSELAGE AT STA 1000 BETWEEN STRINGERS 41L - 43L FOUND SKIN CORROSION. SKIN TRIMMED-OUT, REPAIR DOUBLER AND FILLER FABRICATED AND INSTALLED PER SRM 53-30-03 REV 117 FIGURE 48. REPAIR REPETITIVE INSPECTION THRESHOLD AT 15, 000FC WITH INTERVALS OF 6000FC (INT SDR VGQY2010080400050Panel · crackedNR 1 SPOILER ACTUATOR FITTING PANEL SURFACE FOUND CRACKED. NR 1 SPOILER REMOVED AND REPLACED PER AMM 27-61-02 REV 79.SDR WGFY2010FA0751011Former · crackedPYLON NR 1 INTERNAL NS 270.00 UPPER RT SIDE FORMER CRACKED.SDR WGFY2010FA0751010Former · crackedPYLON NR 1INTERNAL NS 270.00 UPPER LT SIDE FORMER CRACKED.SDR WGFY2010FA0751009Former · crackedSTRUT NR 4 NAC 270.00 RT SIDE UPPER FORMER WAS CRACK.SDR WGFY2010FA0751008Former · crackedSTRUT NR 4 NS270.00 LT SIDE UPPER FORMER WAS CRACK.SDR WGFY2010FA0751007Stiffener · corrodedAFT WHEEL WELL BULKHEAD STIFFENERS CORROSION AT BS 1480, WL 156.SDR WGFY2010FA0751006Stiffener · corrodedAFT WHEEL WELL BULKHEAD STIFFENERS CORROSION AT BS 1480, WL 166.SDR WGFY2010FA0751005Stiffener · corrodedAFT WHEEL WELL BULKHEAD STIFFNERS CORROSION AT BS 1480, WL 176.SDR WGFY2010FA0751004Stiffener · crackedPYLON NR2 STRAP STA 250 BETWEEN STIFFENER NR 2 & STIFFENER NR 3 WAS CRACKED.SDR WGFY2010FA0751003Stiffener · crackedPYLON NR 2 STIFFENER NR 3 AND STRAP, STA 248 WAS CRACKED.SDR WGFY2010FA0751002Strap · crackedPYLON NR1, STA 248.00 STRAP WAS CRACKED.SDR WGFY2010FA0751001Stiffener · crackedPYLON NR 1 STIFFENER NR3, STA 243 & 248 WAS CRACKED.SDR Q2SA752010A/C Pack · damagedUPON CLIMB, A NOISE WAS HEARD BY THE CREW ACCOMPANIED WITH A SMELL AND THEN SMOKE IN THE COCKPIT. THE FLIGHT ENGINEER IMMEDIATELY TURNED OFF THE LEFT PACK AND THE SMOKE STOPPED. AFTER REQUEST AND SUBSEQUENT APPROVAL TO HOLD TO CONSULT MANUALS, THE CREW AND OSDR Q2SA752009Actuator · brokenAIR TURN BACK: NR1 HYD SYSTEM FAILURE. MASTER WARNING INDICATION AFTER GEAR RETRACTION, UPON DEPARTING, SYSTEM INDICATED TOTAL FLUID LOSS AND FAILURE OF THE NR 1 HYD SYS. GEAR RETRACTED NORMALLY AND FLAPS WERE STILL IN POSITION 10. WHILE WORKING THROUGH THE ASDR Q2SA752008Comparator · failedAT FLIGHT LEVEL 31.0 A/C HAD INDICATOR SPLIT RUDDER. UPPER RUDDER 5 DEG RT TO LWR RUDDER 2 UNITS TO THE LEFT. A SHORT TIME LATER, UNCOMMANDED INPUT TO RUDDER, NECESSITATED EXCESSIVE AILERON USE TO CONTROL. AT APPROXIMATELY 14,000 FT AND SPEED LESS THAN 250 SDR Q2SA753006Mec · failedNORMAL THRUST TAKEOFF WAS ESTABLISHED ON RUNWAY AT EBLG. UPON INITIAL CLIMB AT APPROXIMATELY 2100 FT NR 2 ENGINE, FLAMED OUT. ADDITIONAL SHUTDOWN PROCEDURES WERE ACCOMPLISHED PER COMPANY GUIDELINES IN ADDITION TO THE DUMPING OF FUEL TO REDUCE LANDING WEIGHT.SDR Q2SA754008Connector · looseNR 1 LEFT L1 LOWER LOCK WIRE SMOKES IN FLIGHT EACH TIME HEAT CYCLES TO WINDOW. RE-SECURED L1 WINDOW HEAT CONNECTIONS AND OPS CHECKED IAW B747 AMM 30-40-00. OPS CHECK GOOD, NO DEFECTS NOTED. ADDITIONALLY, PERFORMED SMOKE IN CABIN INSPECTION IAW AMM 5-51-00 PSDR Q2SA754007Unknown · odorON DESCENT, EVIDENCE OF STRONG ELECTRICAL ODOR EMITTING FROM FORWARD INSTRUMENT PANEL. ODOR APPEARS TO GO AWAY WHEN STORM LIGHTS ARE TURNED OFF. PERFORMED CONDITIONAL INSPECTION FOR SMOKE IN CABIN IAW MM 05-51-50. NO SMOKE OR FUMES NOTED.SDR Q2SA754006Clamp · looseIN CRUISE, ENGINE FIRE WARNING ACTUATED FOR ENGINE NR 2, CREW BROUGHT ENGINE NR 2 TO IDLE POWER AND OPTED TO SHUTDOWN THE ENGINE IN ACCORDANCE WITH QUICK REFERENCE HANDBOOK. NO ENGINE FIRE EXTINGUISHING DEVICE WAS USED, CREW CONTINUED FLIGHT TO DGAA AND LANDESDR Q2SA754005Sequence Valve · faultyON CLIMBOUT OF WIII, AFTER GEAR RETRACTION, WITH THE GEAR HANDLE IN THE UP POSITION THE NOSE LANDING GEAR HAD AN UNWANTED EXTENSION AND RETRACTION CYCLING. CREW CYCLED THE GEAR DOWN AND BACK UP, AND WITNESSED THE SAME PHENOMENON WITH THE NOSE LANDING GEAR ANDSDR UIEA200900002Blades · missingDURING DESCENT CREW REPORTED SIGNIFICANT VIBRATION FROM NR 1 ENGINE. INSPECTION FOUND MISSING BLADES IN THE LPT AREA. ENGINE CHANGE IS IN PROGRESS.SDR Q2SA753005Sensor · failedON TAKE-OFF FROM LEIGE, BELGIUM (EBLG), NR 2 ENGINE FLAMED OUT. LOUD NOISE HEARD AND AIRCRAFT YAWED LEFT. IGNITION AND ENGINE ANTI-ICE IN USE. ENGINE RELIGHT AT 3000' AGL, ALL PARAMETERS NORMAL. AIRCRAFT CONTINUED TO DESTINATION AT DOHA, QATAR (OTBD). NO SDR UIEA200900003Inu · failedAIR TURN BACK DUE TO NR 1 INS RED WARNING LIGHT ON WITH HDG AND FLIGHT DIRECTOR FLAGS IN VIEW. FOUND NR 1 INU FAILED. REPLACED INU, OPS CHECKED OK.SDR Q2SA751007Rod End · shearedAFTER DEPARTURE FROM LAGOS, NIGERIA (DNMM), RIGHT BODY GEAR DOOR WOULD NOT INDICATE CLOSED WITH GEAR RETRACTED. FLIGHT CREW FOLLOWED QRH. UNABLE TO CONTINUE TO DESTINATION DUE TO INCREASE FUEL BURN. AIR TURN BACK. NO FUEL DUMP PERFORMED. INSPECTION CONFIRSDR Q2SA753004Pump · defectiveON CLIMB-OUT FROM EBLG (LIEGE, BELGIUM), NR 2 ENGINE FILTER BYPASS LIGHT ILLUMINATED, THEN WENT OUT. APPROXIMATELY 3 MINUTES LATER, NR 2 ENGINE FLAME OUT OCCURRED. IN FLIGHT ENGINE START COMPLETED. 3 HOURS, 20 MINUTES LATER AT FL350, FILTER BYPASS LIGHT ILLSDR UIEA200800328Panel · crackedNOSE WHEEL WELL LT SIDE AT STA 273.0, WATER LINE 160 HAS A 0.250 INCH CRACK DETECTED WITH HFEC INSPECTION. INTERM REPAIR WAS ACCOMPLISHED IAW SRM 53-10-04, FIG 116, SHEETS 1 THRU 6. INITIAL AND REPEAT INSPECTION TO BE ACCOMPLISHED AT 15,000 FC AND THERE AFTESDR UIEA200800329Skin Panel · debondedRT WING UPPER SURFACE L/E PANEL AT ILES 328.5 HAS A PREVIOUS REPAIR AREA 7.0 BY 6.0 INCHES DISBONDING AND CRACKING. PERMANENT REPAIR ACCOMPLISHED IAW SRM 51-40-09, FIG 18, SHEETS 2 AND 5, PREPREG 250 DEGREE F CURE IAW SRM 51-40-12. ALSO, REF EO NR 4757A465.SDR Q2SA751006Transceiver · failedDURING FLIGHT (EBBR), NR 1 AND NR 2 VHF WOULD NOT RECEIVE TRANSMISSIONS OVER NORMAL DISTANCE, LOST COMMUNICATION WITH ATC. AIR TURN BACK TO EBBR DUE TO VHF TRANSCEIVER FAILURES, NO FUEL DUMP REQUIRED. R&R NR 1 VHF TRANSCEIVER IN ACCORDANCE WITH AMM 23-21-01. SDR UIEA200800295Inu · failedNR 1 INS DIFFERS FROM NR 2 INS BY 35 NM OR 50 KTS. FAILED ACCURACY TEST. DUMPED FUEL AND DIVERTED TO JFK. REPLACED NR 1 INU AND ALIGNED OPS CHECKED OK PER 34-41-03. (S)SDR Q2SA751005Bleed Valve · malfunctionedVERBAL REPORT, AT 5,000FT CLIMB OUT FROM PHIK, NR 4 ENGINE HIGH NACELLE TEMP AND FIRE WARNING INDICATIONS WENT OFF. REDUCED THRUST FOR 15 SECONDS, WARNING LIGHT WENT OUT. CLOSED BLEED VALVE AND TEMPERATURE DECREASED. AIRCRAFT OPERATED WITH REDUCED THRUST ASDR UIEA200800192Door · damagedWHILE TROUBLESHOOTING INBOUND LOG ITEM FOR NR 1 HYD SYSTEM OVERHEAT BODY GEAR DOORS BOTH SIDES CAME IN CONTACT WITH THE TIRES WHEN HYD POWER WAS APPLIED. CAUSING DAMAGE TO BOTH DOORS. REMOVED AND REPLACED RT AND LT INBOARD BODY GEAR DOORS PER AMM 32-14-01.SDR UIEA200800185Pump · failedCREW REPORTED HYD SYSTEM NR 1 OVERHEAT. ADP AND EDP TURNED OFF. ALL PUMPS ON NR 1 OFF OCCASIONAL OVERHEAT INDICATION CONTINUED. AFTER 1 HOUR NO OVERHEAT INDICATION. THEN THE PROBLEM RETURNED. REMOVED AND REPLACED NR 1 ENGINE EDP PER AMM 29-11-05, OPS AND SDR UIEA200800181Skin Panel · delaminatedRT WING UPPER FIXED T/E PANEL HAS LOOSE AND WORKING FASTENERS, PANEL IS DELAMINATED. PANEL LOCATED INBOARD OF INBOARD AILERON, AT WBL STA 445.0, DELAMINATION AFT EDGE OF PANEL. AREA OF DELAMINATION IS 9.0 INCH LONG BY 1.5 INCH WIDE. PERMANENT REPAIR ACCOMPLSDR UIEA200800180Skin Panel · delaminatedRT WING UPPER FIXED L/E PANEL DELAMINATED, 6.0 FEET OUTBOARD OF NR 3 ENGINE, 12 INCHES FROM AFT EDGE OF PANEL AT ILES STA 772.5. AREA OF DELAMINATION IS 14.0 INCH LONG BY 3.0 INCH WIDE. PERMANENT REPAIR ACCOMPLISHED AS PER B747-200 SRM 51-40-09, FIG 18, SHEESDR UIEA200800179Skin Panel · crackedRT WING UPPER FIXED TRAILING EDGE PANEL HAS COMPOSITE CRACK, 3.5 INCHES FROM FORWARD EDGE OF PANEL AT WBL STA 515. PERMANENT REPAIR ACCOMPLISHED AS PER B747-200 SRM 51-40-09, FIG 2, SHEET 1, 2 AND 5 PREPREG 250 DEGREES CURE PER SRM 51-40-12. REF: ATLAS AIR ESDR UIEA200800178Skin Panel · delaminatedLT WING UPPER FIXED L/E PANEL DELAMINATED, INBOARD OF NR 2 ENGINE, 8.0 INCHES FROM AFT EDGE OF PANEL AT ILES STA 545.56. AREA OF DELAMINATION IS 2.0 BY 2.0 INCHES. PERMANENT REPAIR ACCOMPLISHED AS PER B747-200 SRM 51-40-09, FIG 18, SHEETS 3 AND 5 PREPREG 250SDR UIEA200800177Skin Panel · crackedLT WING UPPER FIXED LEADING EDGE PANEL CRACKED AND DELAMINATED, ILES 833.00, 20 INCHES FROM AFT EDGE OF PANEL. PERMANENT REPAIR ACCOMPLISHED AS PER B747-200 SRM 51-40-09, FIG 18, SHEETS 3 AND 5 PREPREG 250 DEGREES CURE PER SRM 51-40-12. REF: ATLAS AIR EO NR SDR Q2SA751004Cowling · inflt separationINFLIGHT ON CLIMB-OUT AT ABOUT 10,000 FT, LOUD NOISE HEARD WITH SLIGHT YAW TO THE LEFT. INFLIGHT INSPECTION REVEALED PANELS MISSING ABOVE THE NR 2 ENGINE PYLON AND DAMAGE TO THE LEADING EDGE OF THE WING JUST ABOVE THE NR 2 ENGINE PYLON. NO ABNORMAL FLIGHT INSDR Q2SA752007Wire · brokenNR 4 LEADING EDGE FLAP DID NOT RETRACT AFTER TAKEOFF. AMBER LEADING EDGE FLAP LIGHT ON FORWARD PANEL AND FLIGHT ENGINEER PANEL ILLUMINATED. REPAIRED WIRE NR W840-C345-20R PER WDM 20-30-12.SDR UIEA200800006O-Ring · leakingAPPROX 1 HOUR 15 MIN AFTER T/O NR 1 ENGINE OIL QTY IND ZERO, TEMP AND PRESS NORMAL ABOUT 2 HOURS 30 MIN AFTER T/O PRESSURE BEGAN VERY SLOW DROP WITH SLOW FLUX 5 PSI DURING DESCENT WITH ENGINE AT IDLE OIL PRESSURE LIGHT ILLUMINATED OCCASIONALLY BUT PRESS NEVER SDR UIEA200700481Skin · delaminatedRIGHT WING SPOILER NR 7 HAS DELAMINATION. DISBONDED UPPER AND LOWER SURFACE 35" BY 25". REMOVED AND REPLACED THE NR 7 SPOILER IAW AMM 27-62-01 OPS CHECKED TRANS TO RUN UP AND LEAK CHECK SHEET 01-AA-74A ITEM NR 3.SDR 754004Computer · no testAUTOPILOT A WILL NOT ENGAGE AND AUTOPILOT B IS ALREADY DEFERRED. DUMPED FUEL AND DIVERTED INTO RKSI. AUTOPILOT A ROLL COMPUTER DOES NOT PASS SELF TEST. REPLACED AUTOPILOT A ROLL COMPUTER AND AUTOPILOT B MONITOR LOGIC UNIT.SDR 754003Cadc · malfunctionedAUTOPILOT B ALTITUDE HOLD WOULD NOT CAPTURE OR HOLD ALTITUDE. VERTICAL SPEED COMMAND UNUSABLE AND MANUAL PITCH WHEEL CONTROL UNUSABLE. AUTOPILOT A PREVIOUSLY DEFERRED. REMOVED AND REPLACED CADC TO CORRECT AUTOPILOT B. REMOVED AND REPLACED P10 PANEL TO RESOLSDR 754002Control System · unstableDURING CLIMB-OUT, THE VERTICAL SPEED WHEEL MOVED TO FULL NOSE UP POSITION WITH "B" AUTOPILOT SELECTED. IN CRUISE AUTO STAB "B" LIGHT ILLUMINATED SEVERAL TIMES. AT FL 340 WITH ALTITUDE HOLD SELECTED, VERTICAL SPEED VARIED +/- 2000 FPM. WITH AUTOPILOT OFF, THE
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