Boeing 747-230B
Service difficulty reports · 618
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 = '747230B' 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 = '747230B' 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 P5CA0501357Skin · chafedLEFT INBOARD ELEVATOR TOP LEADING EDGE SKIN FOUND CHAFED. ACCOMPLISHED REPAIR PER BOEING INSTRUCTIONS 1-1HR8MP AND FAA FORM 8100-9.SDR P5CA0501356Bulkhead · crackedBS 1241 LEFT SIDE CANTED BULKHEAD HAS CRACK IN WEB AREA ABOVE BULKHEAD FITTING. ACCOMPLISHED REPAIR PER BOEING INSTRUCTIONS 1-1I9Y5F AND FAA FORM 8100-9.SDR P5CA0501355Skin · crackedNR 4 PYLON INBOARD ACCESS PANEL CUTOUT AT NAC STATION 275-295 CRACKED AT EDGE. ACCOMPLISHED REPAIR PER BOEING INSTRUCTIONS 1-1HGUJB AND FAA FORM 8100-3.SDR P5CA0501354Skin · wornNR 2 PYLON INBOARD ACCESS PANEL CUTOUT AT NAC STATION 280-300 WORN AT EDGE. ACCOMPLISHED REPAIR PER BOEING INSTRUCTIONS 1-1IO8DO AND FAA FORM 8100-3.SDR P5CA0501353Skin · deformedDORSAL FIN FOUND WITH DEFECTS DEFORMED AT TOP EDGE. ACCOMPLISHED REPAIR PER BOEING INSTRUCTIONS 1-1I9VRK AND FAA FORM 8100-3.SDR P5CA0501352Stiffener · crackedNR 4R DOOR INTERNAL STIFFENER JUST FORWARD OF WINDOW CUT-OUT FOUND CRACKED. ACCOMPLISHED REPAIR PER BOEING 1-1I26OS AND FAA FORM 8100-3.SDR P5CA0501351Skin · crackedNR 2, 3 AND 4 PYLON PRECOOLER CUTOUT CRACKED AT AFT LOWER CORNER. ACCOMPLISHED REPAIR PER BOEING INSTRUCTIONS 1-1I08HV AND FAA FORM 8100-3.SDR P5CA0501385Structure · crackedLT FOUND 1 OFF STANDOFF HOLE WITH 2 OFF CRACKS APPROXIMATELY 3MM EACH AT BS 280 WEB. REPAIR CARRIED OUT IAW MFG MSG 1-1ME16G. REFER TO FAA FORM 8100-9 DATED JUNE 2, 2005. THIS REPAIR IS SUBJECT TO CONTINUE INSPECTION IAW SB 747-53A2293.SDR P5CA0501347Nozzle · damagedON WALK AROUND, FOUND A HOLE APPROXIMATELY 1.5 INCH IN DIAMETER ON NR 3 ENGINE LONG FIXED CORE EXHAUST NOZZLE AT 8:00 O’CLOCK POSITION. REPAIRED NR 3 ENGINE LONG FIXED CORE COWL EXHAUST NOZZLE AS PER GE ENGINE MANUAL 78-11-01, REPAIR 010.SDR P5CA0501340Wire · miswiredA-AUTOPILOT TOC F/L 320 SELECTED ALT HOLD A/C WENT 100 FT HIGH THEN DESCENDED TO 31500. DISENGAGED AUTOPILOT HAND FLEW A/C BACK TO F/L 320. SELECTED AUTOPILOT-B ALT HOLD. FOUND ALT HOLD JUMPER WIRES FROM AUTOPILOT-A PITCH COMPUTER AND NR 1 CADC PIN 64,65 SWSDR P5CA0501337Clamp · looseON TAKEOFF GROUND ROLL & SETTING TAKEOFF THRUST AT 105.4 DEGREES. SET ROLLING APPROXIMATELY 90 KNOTS. NR 2 ENGINE FIRE LIGHT CAME ON, ABORTED TAKEOFF WITH THROTTLES BACK AT IDLE & SHUT DOWN NR 2 ENGINE. BOTH A & B LOOPS READING 8 UNITS. BRAKE TEMPS ALL GRESDR P5CA0501341Regulator Valve · malfunctionedDURING CLIMBOUT NR 1 ENGINE NACELLE LOOPS A & B WENT INTO THE RED - SET BELL OFF - ENGINE SHUT DOWN OIL PRESSURE 45 PSI. REPLACED ENGINE PRESSURE REGULATING VALVE, LEAK CHECK OK. OPS CHECKED OK DURING ENGINE HIGH POWER ASSURANCE RUN, MM 36-11-19 & MM 36-11-0SDR P5CA0501336Shutoff Valve · failedDURING CLIMBOUT, NR 1 ENGINE NACELLE LOOPS A & B WENT INTO RED, SET WARNING BELLS OFF. ENGINE SHUTDOWN. OIL PRESSURE 45 PSI. REPLACED NR 1 ENGINE HIGH PRESSURE SHUTOFF VALVE PER MM 36-11-05. LEAK CHECK OIL, OPS CHECK NORMAL ON HIGH POWER RUN UP PER MM 71-0SDR P5CA0501334Computer · inoperativeALTITUDE ALERT SYSTEM INOP. REPLACED ALTITUDE ALERT COMPUTER AND TESTED OK PER MM 34-16-00.SDR P5CA0501339Yaw Damper · malfunctionedCREW REPORTED ON TAXI OUT UPPER RUDDER SHOWED 5 DEGREES LEFT AND LOWER RUDDER WAS CENTERED. AFTER TAXI IN, RUDDER POSITIONS WERE CONFIRMED BY MAINTENANCE. REPLACED YAW DAMPER COMPUTER AS PER MM 22-16-02. OPS CHECK PASSED ON GROUND.SDR P5CA0501338Powerpack · failedCREW REPORTED ON TAXI OUT UPPER RUDDER SHOWED 5 DEGREES LEFT AND LOWER RUDDER WAS CENTERED. AFTER TAXI IN, RUDDER POSITIONS WERE CONFIRMED BY MAINTENANCE. REPLACED RUDDER POWER PACK (UPPER) PER MM 27-21-16. NO HELP TRANSFERRED TO DMI 34039 MEL 22-3.SDR P5CAO501333Connector · looseTAWS SYSTEM GIVES ERRONEOUS INFORMATION CALL OUTS TERRAIN. FOUND P-3 CONNECTOR LOOSE AT TAWS INDICATOR. FOUND NO POWER AT PIN 63 ON NR 1 CADC RACK PLUG. RESTORED 26V PER WDM 34-12-12. ALL OPS & LEAK CHECK OK.SDR P5CA0501319Actuator · inoperativeDURING ENGINE START NR 3 ENGINE WOULD NOT LIGHT OFF. TROUBLESHOT, FOUND FUEL CONDITION ACTUATOR INOP. REMOVED & REPLACED CONDITION ACTUATOR PER MM 76-11-00. OPS NORMAL.SDR P5CA0501320Clamp · looseON PREFLIGHT, NR 4 THROTTLE WOULDN’T ADVANCE FORWARD. T/S FOUND SHIELD SUPPORT BRACKET CLAMPS LOOSE AT PUSH PULL CABLE. SECURED PUSH PULL SHIELD SUPPORT BRACKET CLAMPS PER MM 76-11-05. OPS CHECK OK.SDR P5CA0501316Valve · failedNR 2 PYLON VALVE FAILED TO OPEN ON ENGINE START. DEFERRED NR 2 ENGINE PYLON VALVE PER MEL 36-5-2. TRANSFERRED TO DMI 33793.SDR P5CAO501312Engine · stalledDURING CRUISE AT FL 310, NR 3 ENGINE COMPRESSOR STALLED, EGT WENT TO 500 DEGREES, N1 50 PERCENT, N2 40 PERCENT. PERFORMED RESTART THE ENGINE WOULD NOT START PAST 30 PERCENT N1, 40 PERCENT N2, WITH EGT AT 625 DEGREES & F/F AT 400 PPH. THROTTLE MOVEMENT HAD NOSDR UIEA200500005Pump · leakingNR 1 HYDRAULIC CONTENTS RAPIDLY DEPLETED DURING FLIGHT. APPROPRIATE DRILLS CARRIED OUT. REMOVED AND REPLACED NR 1 ENGINE EDP IAW MM 29-11-05. NO EVIDENCE OF LEAKS AFTERWARDS. SERVICED NR 1 HYDRAULIC SYSTEM TO FULL. INSPECTED PRESS AND CASE DRAIN FILTERS. SDR UIEA2005005Pump · leakingNR 1 HYD CONTENTS RAPIDLY DEPLETED DURING FLIGHT. APPROPRIATE DRILLS CARRIED OUT. REMOVED AND REPLACED NR 1 ENGINE EDP IAW MM. NO EVIDENCE OF LEAKS AFTERWARDS. SERVICED NR 1 HYD SYSTEM TO FULL. INSPECT PRESS AND CASE DRAIN FILTERS. SECURED ENGINE COWL ANSDR P5CA0501311Valve · failedNR 3 PACK HAD NO CONTROL FROM FLIGHT ENGINEERS STATION. PACK STAYS ON AND WILL NOT SHUT DOWN. REMOVED AND REPLACED FLOW CONTROL VALVE PER MM 21-51-00.SDR P5CA0601429Relief Valve · failedCREW REPORTED NR 1 ENGINE NACELLE TEMP WENT TO TOP END OF SCALE. RETARDED THROTTLES, TEMP DECREASED. RETURNED TO RMS. FOUND NR 1 ENGINE PRESSURE RELIEF VALVE FAILED. REPLACED PER AMM 36-11-03. OPS OK.SDR P5CA0401288Link · missingNR 4 ENGINE T/R BLOCKER DOOR LINK MISSING AT 4 O'CLOCK POSITION. REMOVED BLOCKER DOOR AND BROKEN LINK PER CDL 78-31-1. T/R LOCKED OUT PER DDPG 78-1.SDR P5CA0401287Regulator Valve · failedON TAXI OUT DUCT LOW PRESS LIGHT CAME ON WITH DROP IN DUCT PRESSURE ON GAGE. ISOLATED LEFT WING PRESS LESS THAN 15 PSI. REPLACED PRESSURE REGULATOR VALVE ON ENGINE NR 2 PER MM 36-1114. PERFORMED ENGINE RUN PER MM 71-00-00. OPS CHECK OK.SDR UIEA200400196Spar · crackedD-CHECK, DURING SCHEDULED MAINTENANCE INSPECTION, CRACKS WERE FOUND AT ENDS OF THE NR 15 KRUEGER FLAP FRONT SPAR. TRIMMED OUT CRACKED REGION OF SPAR ATTACHED FLANGES. NDT INSPECTED TRIMMED EDGES TO ENSURE CRACK AND DEFECT FREE CONDITION. INSTALLED REPAIR FISDR UIEA200400197Spar · crackedD-CHECK, DURING SCHEDULED MAINTENANCE INSPECTION, CRACKS WERE FOUND AT ENDS OF THE NR 16 KRUEGER FLAP FRONT SPAR. TRIMMED OUT CRACKED REGION OF SPAR ATTACHED FLANGES. NDT INSPECTED TRIMMED EDGES TO ENSURE CRACK AND DEFECT FREE CONDITION. INSTALLED REPAIR FISDR UIEA200400195Fairing · delaminatedD-CHECK, DURING SCHEDULED MAINTENANCE INSPECTION, DELAMINATION WAS FOUND ON NR 4 PYLON FAIRING ASSY. AT THE AFFECTED AREA, SKIN AND CORE WERE TRIMMED FROM BOTH IB AND OB SIDES WITH REPLACEMENT CORE, SKIN AND DOUBLERS BONDED IAW SRM 51-40-06. PERFORM DETAILEDSDR UIEA200400194Fairing · delaminatedD-CHECK, DURING SCHEDULED MAINTENANCE INSPECTION, DELAMINATION WAS FOUND ON NR 2 PYLON FAIRING ASSY. AT THE AFFECTED AREA, SKIN AND CORE WERE TRIMMED FROM THE OB SKIN SIDE AND REPLACEMENT CORE AND SKIN WERE SPLICED BY BONDING IAW SRM 51-40-06. IT WAS FURTHERSDR UIEA200400193Frame · crackedD-CHECK, DURING SCHEDULED MAINTENANCE INSPECTION THE NR 3 PYLON AFT ENGINE MOUNT BULKHEAD UPPER ASSY FRAMES CRACKED. STOPPED DRILLED THE CRACK ENDS IAW SRM 51-10-01. HFEC INSPECTED TO ENSURE CRACK CONTAINMENT. FABRICATED AND INSTALLED REPAIR ANGLES ON THE FSDR UIEA200400192Skin · crackedDURING SCHEDULED MAINTENANCE INSPECTION, THE BULKHEAD UPPER ASSY FORWARD ANGLE FRAME OF THE NR 2 PYLON LT AND RT SIDE WERE FOUND CRACKED. FABRICATED AND INSTALLED REPAIR ANGLES ON THE FORWARD AND AFT FRAMES IN THE REPAIR AREA. INSTALLED THE REPAIR ANGLES BY SDR UIEA200400191Strap · crackedDURING SCHEDULED MAINTENANCE, FOUND CRACK NR 4 PYLON AT AFT MOUNT BULKHEAD FRAME STRAP. SUBJECT CRACK WAS LOCATED ALONG THE STRUT UPPER SKIN ASSY LOWER EDGE. CRACK AFT END WAS CONTAINED WITH A STOP HOLE IN THE STRAP. THE REPAIR AREA WAS NDT INSPECTED, INCLUSDR UIEA200400189Rib · crackedDURING SCHEDULED MAINTENANCE. FOUND CRACK AT RT VARIABLE CAMBER FLAP HINGE RIB ASSEMBLY. TRIMMED THE FLANGE TO REMOVE THE DAMAGE. HFEC THE AFFECTED AREA TO ENSURE DEFECT FREE CONDITION. THE REPAIR AND RESTORATION WAS ACCOMPLISHED TO RESTORE TO THE ORIGINALSDR P5CA0401263Fuel Cell · overservicedFUEL SPILL RIGHT WING. FOUND NR 4 MAIN OVER FILLED. DRAINED RIGHT SURGE TANK IAW 28/21/00, RESET SYSTEM & CONTINUED FUELING. CHECK OF VOLUMETRIC SYSTEM IAW 28-21-00 SATISFACTORY.SDR P5CA0401251Wire · chafedNR 3 ENGINE BLEED VALVE CLOSED, LIGHT STAYS ON AT CRUISE PWR & POPPED C/B AT LANDING. REPAIRED CHAFED WIRE PYLON TO HIGH STAGE BLEED VALVE PER WPM CH 20-10-13, OPERATIONAL CHECK OK.SDR UIEA200400167Fitting · corrodedWHILE PERFORMING EO 4757A087, REAR SPAR UPPER CHORD AND SIDE BODY INSPECTION. CORROSION STILL EXIST ON THE UPPER REAR SPAR INTERNAL SPLICE FITTING AFTER INCORPORATING NR 5 HOLE DIA MAX OF 1.40 INCHES WITH SLEEVED BOLT REPAIR. LEVEL 1 MINOR. REAMED HOLE NR 5SDR UIEA200400169Spar · corrodedFOUND DURING SCHEDULED MAINTENANCE, CORROSION ON FRONT SPAR WEB, FSS 979.27, LOWER CHORD, LEFT SIDE. BLENDED OUT CORROSION WITH 125 RT FINISH. HFEC INSPECTED OPEN FASTENER HOLES, TO ENSURE DEFECT FREE CONDITION. FLAP PEEN BLENDED SURFACES. FABRICATED AND ISDR UIEA200400161Spar · corrodedDURING SCHEDULED MAINTENANCE, CORROSION WAS FOUND LEFT WING SKIN FORWARD OF FRONT SPAR OLES 1378-1387, 1410, 1438-1447. CORROSION WAS REMOVED BY BLENDING. NDT INSPECTED TO CONFIRM DAMAGE FREE CONDITION. BLENDED AREAS WERE FLAP PEENED, ALODINE 1200 AND BMS 1SDR UIEA200400160Fairing · wornDURING SCHEDULED MAINTENANCE, FOUND NR 1 MOVABLE CANOE PRIMARY DOOR FAIRING BEARINGS WORN. HOLE ELONGATION WAS FOUND IN TWO LOCATIONS. OVERSIZED THE HOLES TO A MAXIMUM DIAMETER OF .7827 INCHES. DRY PNETRANT INSPECTED THE AFFECTED AREA TO ENSURE DEFECT FREE SDR UIEA200400173Skin · corrodedDURING SCHEDULED MAINTENANCE, FOUND CORROSION ON LEFT WING TOP SKIN UPPER SURFACE AT APPROXIMATELY WBL 143, JUST FORWARD OF STRINGER 30. THE CORROSION WAS REMOVED BY BLENDING. HFEC INSPECTED THE SKIN SURFACE TO ENSURE DAMAGE AND DEFECT FREE. FLAP PEEN THE BSDR UIEA200400166Bulkhead · crackedDURING SCHEDULED MAINTENANCE INSPECTION, THE BULKHEAD UPPER ASSEMBLY FORWARD ANGLE FRAMES OF THE NR 3 PYLON LHS AND RHS WERE FOUND CRACKED. STOP DRILLED THE CRACK ENDS PER 747 SRM 51-10-01. HFEC INSPECTED TO ENSURE CRACK CONTAINMENT. FABRICATED AND INSTALLESDR UIEA200400162Pylon · crackedDURING SCHEDULED MAINTENANCE, NR 1 PYLON CRACK DAMAGE WAS FOUND AT PRE-COOLER EXHAUST CUTOUT LOWER AFT CORNER AT STATION 248. THE NR 3 STIFFENER WAS REINFORCED WITH A NEW LOWER REPAIR ANGLE FROM FS 235-254. THE RIB INSTALLATION AT NACELLE STATION 248 WAS MODSDR UIEA200400165Pylon · crackedDURING SCHEDULED MAINTENANCE, NR 4 PYLON, CRACK DAMAGE WAS FOUND AT PRE-COOLER EXHAUST CUTOUT LOWER AFT CORNER AT FS 248. THE NR 3 STIFFENER WAS REINFORCED WITH A NEW LOWER REPAIR ANGLE FROM FS 235-FS 254. THE RIB INSTALLATION AT NACELLE STATION 248 WAS MODISDR UIEA200400163Pylon · crackedDURING SCHEDULED MAINTENANCE, NR 2 PYLON, CRACK DAMAGE WAS FOUND AT PRE-COOLER EXHAUST CUTOUT LOWER AFT CORNER AT FS 248. THE NR 3 STIFFENER WAS REINFORCED WITH A NEW LOWER REPAIR ANGLE FROM FS 235-FS 254. THE RIB INSTALLATION AT NACELLE STATION 248 WAS MODISDR UIEA200400164Pylon · crackedDURING SCHEDULED MAINTENANCE, NR 3 PYLON, CRACK DAMAGE WAS FOUND AT PRE-COOLER EXHAUST CUTOUT LOWER AFT CORNER AT FS 248. THE NR 3 STIFFENER WAS REINFORCED WITH A NEW LOWER REPAIR ANGLE FROM FS 235-254. THE RIB INSTALLATION AT NACELLE STATION 248 WAS MODIFIESDR 2004F00418Coupler · failedEN ROUTE FROM PANC TO RDSI AT FL320, IN CRUISE MODE, WHEN HF NR 1 MIC IS KEYED THE FOLLOWING DISCREPANCY WAS NOTED, 'WITH AUTOPILOT ENGAGED AND AUTOTHROTTLES ENGAGED, AIRCRAFT EXPERIENCED THREE SEVERE RIGHT YAWS. THE LAST TWO WERE WITH THE AUTOTHROTTLES DISENSDR P5CA0401174Transducer · failedAUTO BRAKES INOP. REPLACED ANTI-SKID TRANSDUCER NR 3 POSITION, SPIN CHECK NORMAL (NO LIGHT ILLUMINATE PER MM 32-43-00).SDR P5CA0401136Comparator · inoperativeRUDDER RATIO LIGHT CAME ON AFTER TAKEOFF. REMOVED AND REPLACED RUDDER RATIO COMPARATOR.
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