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 UIEA200400020Strut · crackedDURING ZONAL INSPECTION IT WAS DISCOVERED THE NR 4 ENGINE PYLON STRUT PRECOOLER EXHAUST VENT WITH CRACKS ON THE RIGHT SIDE OF THE STRUT. THE REPAIRS WERE MADE ON THE RIGHT SIDE OF THE STRUCT STRUCTURE ASSEMBLY. THE NR 3 STIFFENER WAS REINFORCED WITH A NEW LOSDR UIEA200400019Strut · crackedDURING D-CHECK AT SIN, DURING ZONAL INSPECTION IT WAS DISCOVERED THAT NR 3 ENGINE PYLON STRUT PRECOOLER EXHAUST VETN WITH CRACKS ON THE RIGHT SIDE OF THE STRUT. THE REPAIRS WERE MADE ON THE RIGHT SIDE OF THE STRUT STRUCTURE ASSEMBLY. THE NR 3 STIFFENER WAS RSDR UIEA200400017Strut · crackedDURING D-CHECK AT SIN, DURING ZONAL INSPECTION IT WAS DISCOVERED THAT NR 1 ENGINE PYLON STRUT PRECOOLER EXHAUST VENT HAD CRACKS ON THE RIGHT SIDE OF THE STRUT. THE REPAIRS WERE MADE ON THE RIGHT SIDE OF THE STRUT STRUCTURE ASSEMBLY. THE NR 3 STIFFENER WAS RESDR UIEA200400018Strut · crackedDURING D-CHECK AT SIN, DURING ZONAL INSPECTION IT WAS DISCOVERED THAT NR 2 ENGINE PYLON STRUT PRECOOLER EXHAUST VENT WITH CRACKS ON THE RIGHT SIDE OF THE STRUT. THE REPAIRS WERE MADE ON THE RIGHT SIDE OF THE STRUT STRUCTURE ASSEMBLY. THE NR 3 STIFFENER WAS RSDR UIEA200400016Attach Fitting · crackedDURNG D-CHECK AT SIN ON NR 1 PYLON DIAGONAL BRACE ATTACH FITTING, HFEC INSPECTOIN FOUND CRACK IN HOLE LOCATION REF 'A'. HOLE OVERSIZED TO .0405, BUT CRACK REMAINS. THE DEFECT WAS COMPLETELY REMOVED BY OVERSIZING THE HOLE TO .434 INCHES PRIOR TO FURTHER OVERSSDR UIEA200400015Skin · wrinkledDURING D-CHECK AT SIN, FOUND NR 3 PYLON HAS A WRINKLE CONDITION ON RIGHT SIDE. SKIN ASSEMBLY WAS TRIMMED TO REMOVE THE WRINKLED AREA. NDT INSPECTION OF THE REPAIR AREA, INCLUDING HFEC INSPECITON OF SKIN TRIMMED EDGES AND REPAIR FASTENER HOLES WAS PERFORMED TSDR UIEA200400014Skin · wrinkledDURING D-CHECK AT SIN, FOUND NR 2 PYLON HAS A WRINKLE CONDITION ON RIGHT SIDE. SKIN ASSY WAS TRIMMED TO REMOVED THE WRINKLED AREA. NDT INSPECTION OF THE REPAIR AREA, INCLUDING HFEC INSPECTION OF SKIN TRIMMED EDGES AND REPAIR FASTENERS HOLES WAS PERFORMED TO SDR UIEA200400013Panel · delaminatedDURING D-CHECK AT SIN, FOUND TOP PANEL P/N 65B08540-202 DELAMINATED. AREA AFFECTED EXCEED SRM REPAIR LIMITS. THE DAMAGED SKIN WAS REMOVED AND DISCARDED. A METAL TO METAL HOT BOND REPAIR WAS ACCOMPLISHED PER 747 SRM 51-40-06 SECTION 3 REQUIREMENTS. DETAIL VSDR UIEA200400012Spar · corrodedDURING DC-CHECK AT SIN, FOUND CORROSION ON THE LOWER SECTION OF THE UPPER T-CHORD OF SPAR NR 1 AND NR 2 OF RIGHT INOARD MID FLAP. FOUND ON ROUTINE CARD 12FM40010. CORROSION LEVEL 1. LOCALLY BLEND OUT CORROSION DAMAGE FROM THE EFFECTED CHORD FLANGE LOWER SURSDR UIEA200400011Stiffener · crackedDURING D-CHECK AT SIN, FOUND NR 16 KRUEGER FLAP INBOARD STIFFENER CRACKED. TRIMMED OUT CRACKED SEGMENT OF STRINGER FLANGE TO REMOVE DAMAGE. NDT INSPECT STRINGER TO INSURE CRACK AND DEFECT FREE CONDITION. INSTALLED ALUMINUM REPAIR ANGLE AND ALUMINUM FILLER TSDR UIEA200400010Skin · corrodedDURING D-CHECK AT SIN, CENTER WING TANK, LOWER SKIN ABOVE NR 1 ACM FOUND CORRODED. LEVEL 1. CORROSION WAS BLENDED OUT WITH A MACHINED FINISH. THE BLENDED AREA WAS HFEC INSPECTED AND FLAP/SHOP PEENED. ALODINE PRIMER AND BMS 3-23 CORROSION INHIBITING COMPOUNSDR UIEA200400009Skin · corrodedDURING (D) CHECK, WING LOWER SKIN CORROSION FOUND AROUND SURGE TANK SUMP DRAIN VALVE AT WING STA 1487, BETWEEN STRINGERS S-5 AND S-6 LT SIDE. CORROSION DAMAGE IS REPAIRED BY BLEND OUT. REPAIR AREA IS SHOP PEENED AND HFEC INSPECTED. APPLIED ALODINE 1200 AND SDR UIEA200400008Beam · crackedDURING (D) CHECK AT SIN, RT WING LEADING EDGE NOSE BEAM WEB FOUND WITH 4.2500 CRACK AT ILES 1042. REPAIR, TRIM OUT SECTION OF CRACKED WEB TO REMOVE DAMAGE. NDT INSPECTED TO ENSURE CRACK AND DEFECT FREE CONDITION. SPLICE IN REPLACEMENT WEB REPAIR SECTION WITSDR UIEA200400002Odor · detectedAFTER LANDING, STRONG FUEL ODOR IN THE COCKPIT, BALLAST FUEL 5000 AND TWO PACKS RUNNING. PERFORMED THOROUGH VISUAL CHECK OF AIR CONDITIONING BAY AND WING BODY FAIRING AREA PER MM 28-11-00. NO FUEL LEAKS NOTED. RAN PACK, NO FUEL ODOR NOTED. (M)SDR UIEA200300069Fire Loop · shortedNR 2 ENGINE INDICATED FIRE ON APPROACH, SHOT BOTH BOTTLES, INDICATIONS CONTINUED. FOLLOWED FHB PROCEDURES FOR ENGINE FIRE CHECKLISTS. DISCHARGED FIRST BOTTLE, TIMED 30 SECOND LIGHT REMAINED ON. DISCHARGED SECOND BOTTLE, LIGHT REMAINED ON. B-LOOP REMAINED OSDR UIEA200300068Duct · leakingON CLIMB-OUT, NR 3 ENGINE NACELLE TEMPERATURE WENT TO 6.0, LOOPS A/B. WITH POWER PULLED BACK TO CRUISE TEMPERATURE DROPPED TO 3.5 - 4.0. REMOVED AND REPLACED FORWARD 8TH STAGE DUCT ASSEMBLY AS PER MM 36, ACCOMPLISHED LEAK CHECK ON ABOVE IDLE RUN UP, ALL NORMSDR UIEA200300064Csd · malfunctionedNR 1 GENERATOR FIELD TRIPPED CAUSING NR 2 GENERATOR TO TRIP ALSO. CHECKED EACH GENERATOR FREQUENCY AND VOLTS NR 2 OK. RETURNED TO NORMAL OPERATION WITH NR 3. NR 1 FREQUENCY WAS OVER 8000 THEN TRIPPED AGAIN. NR 1 CSD DISCONNECTED BY CHECKLIST PROCEDURES. RSDR UIEA200300042Seal · wornDFW/ANC AIR TURNBACK, AT FL 31 CABIN ALT WENT TO 10 WITH DIFFERENTIAL AT 6.8 AND UNABLE TO PREVENT CABIN FROM CLIMBING 50-100 FPM. AIRCRAFT DESCENDED TO FL 29.0 THEN FL 25.0. MAX DIFFERENTIAL THAT COULD BE HELD WAS 6.5 AND CABIN CONTINUED TO CLIMB 50-100 FPMSDR UIEA200300040Connector · looseDURING CRUISE, NR 4 ENGINE NACELLE TEMP INDICATOR SHOWED 5.9. STARTED FLUCTUATING TO 6.5, EVENTUALLY READING 7.0. ACCOMPLISHED ABNORMAL PROCEDURES IAW 3.26.10. AIRCRAFT DIVERTED. NO FUEL DUMPED. TROUBLESHOOTING FOUND 1 CONNECTOR LOOSE ON LT LOWER DETECTORSDR UIEA200300018Warning Light · false indicationINFLIGHT ENGINE SHUTDOWN, NR 2 ENGINE WAS SHUTDOWN DUE TO FIRE DETECTION LIGHT AND FAULT LIGHT. NR 2 FIRE DETECTION 'A' LOOP WOULD NOT TEST. COMPLETED ENGINE SHUTDOWN CHECKLIST. HYDRAULIC SYSTEM SHUTDOWN FOR 20 MINUTES. INCIDENT TIME FRAME, AIRCRAFT DEPARTSDR UIEA200300010Stiffener · crackedDURING CURRENT C-CHECK, AT SIAEC FOUND NR 2 PYLON (NR 3) LONGITUDINAL STIFFENER VERTICAL FLANGE, BELOW PRECOOLER EXHAUST VENT, CRACKED THREE PLACES AT NAC 245, 247 AND 257. PYLON PREVIOUSLY MODIFIED PER SB 747-54-2163 AND 747-54-2091 WHICH CONSISTS OF AN UPPESDR UIEA200300011Stiffener · crackedDURING CURRENT C-CHECK AT SIAEC, FOUND NR 3 PYLON NR 3 LONGITUDINAL STIFFENER VERTICAL FLANGE, BELOW PRECOOLER EXHAUST VENT, CRACKED THREE PLACES AT NAC 245, 247 AND 257. PYLON PREVIOUSLY MODIFIED PER SB 747-54-2163 AND 747-54-2091 WHICH CONSISTS OF AN UPPER SDR UIEA200300012Stiffener · crackedDURING CURRENT C-CHECK AT SIAEC, FOUND NR 4 PYLON NR 3 LONGITUDINAL STIFFENER VERTICAL FLANGE, BELOW PRECOOLER EXHAUST VENT, CRACKED THREE PLACES AT NAC 245, 247 AND 257. PYLON PREVIOUSLY MODIFIED PER SB 747-54-2163 AND 747-54-2091 WHICH CONSISTS OF AN UPPER SDR UIEA200300009Skin · delaminatedDURING CURRENT C-CHECK AT SIAEC, FOUND NR 3 ENGINE LEFT FAN COWL DELAMINTED APPROXIMATELY 8 INCHES BY 8 INCHES IN GENERAL REWORK AREA NOTED BY SB 78-2150 DURING TRAS LOCK MODIFICATION. THE OUTER DELAMINTED SKIN AND FILLER WERE STAGGER CUT TO REMOVE DELAMINATESDR UIEA200300007Engine · inoperativeDURING CLIMB OUT AT APPROXIMATELY 18,800 FT, NR 3 ENGINE HAD THREE LOUD BANGS. WHEN THROTTLE WAS RETARDED BANGS STOPPED. THRUST LEVER REMAINED AT IDLE FOR REMAINDER OF THE FLIGHT. THE ONLY INDICATION NOTICED WAS THAT THE N1 WAS AROUND 76 PERCENT AT ONE POINSDR UIEA200300002Beam · crackedDURING CURRENT C-CHECK AT SIA, FOUND RT WING LE BEAM WEB CRACKED AT OLES 1200. CRACK REMOVED BY CUTTING THE WEB AT OLES 1190 AND DISCARDING THE INBOARD SECTION FROM OLES 1190 TO 1200. PERFORMED HFEC INSPECTION OF CUT EDGE TO ENSURE CRACK FREE CONDITION. NO SDR UIEA200300005Skin · crackedDURING CURRENT C-CHECK AT SIA, FOUND BS 1241 L/S KICK FITTING AT BOLT HOLE NR 11 CRACKED IN WING SKIN ONLY. REAMED HOLE TO 1.169 INCH. NO CRACK INDICATION. FINAL REAMED HOLE TO 1.284 INCH IN WING SKIN AND CHORD. REAMED STRINGER SPLICE FITTING TO 1.126 INCHSDR UIEA200300003Skin · wrinkledDURING CURRENT C-CHECK AT SIA, FOUND NR 2 PYLON R/S SKIN WRINKLED TWO PLACES FROM 1) NAC 286 TO 300 AT STR 5, 2) NAC 300 TO 316 AT STRINGER6. REPAIR AREA (1) CUTOUT EXISTING DAMAGE IN FLAT BAY AREAS ONLY. HFEC INSPECTED ALL OPEN HOLES, CUT EDGES AND ADJACENTSDR UIEA200300001Spar · corrodedDURING CURRENT C CHECK, FOUND LT STABILIZER REAR SPAR CORRODED AT STABILIZER B/L 372, STA 550. NO ESTABILISHED LEVEL OF CORROSION DECLARED SINCE ITEM DISCOVERED DURING ROUTINE INSPECTION. REMOVED EXISTING SPAR SPLICES LOCATED AT STAB STA. 525 AND 570. REMOVSDR UIEA200200053Metering Valve · leakingSTRONG SMELL OF FUEL AFTER SUPPLYING A/C PACK WITH AIR FROM THE APU. SUSPECT FUEL LEAK. FOUND FUEL DROP FROM THE FORWARD FUSELAGE DRAIN. APU RENDERED INOPERATIVE. REMOVED AND REPLACED FUEL METERING VALVE PER MM 49-31-07. OPS AND LEAK CHECK OK. (M)SDR UIEA200200051Transponder · failedDURING INITIAL CLIMB, TRANSPONDER FAIL LIGHT ILLUMINATED WITH NR 1 SET SELECTED. SELECTED NR 2 TO NO AVAIL. CIRCUIT BREAKER CHECKED OK. DIVERTED. C/A: REPLACED MODE S TRANSPONDER IAW MM. TEST CARRIED OUT. OPS CHECK SATISFACTORY. ALSO ATC TRANSPONDER NRSDR UIEA200200036Battery · overheatedDURING PREFLIGHT, THERE WAS STRONG BURNING SMELL IN COCKPIT. TROUBLESHOT, NR 3 ACM MAKING A NOISE, DEFERRED. DURING CRUISE AFTER 2.5 HOURS OF FLIGHT, BURNING ODOR RETURNED IN COCKPIT. AFTER SEARCHING FOR SOURCE IT WAS NOTICED NR 1 GEN KVAR/KW METER WAS READSDR 2002F00970Skin · crackedDURING CURRENT C-CHECK AT SIAEC, FOUND RT WING L/E STATIONS NR ILES 378, 400, 446, 467, AND 546 NOSE CAP POSITIONS CRACKED AND CORRODED AT TOP ROW OF RIVETS. SIX CRACKED/ CORRODED AREAS TRIMMED OUT. ALL AREAS HFEC INSPECTED FOR ADDITIONAL CRACKS. NONE FOUNDSDR UIEA200200032Panel · crackedDURING CURRENT (C) CHECK AT SIAEC FOUND CRACKED CLOSURE PANEL ON LT WING LE NR12 KRUGER FLAP FOLDING NOSE SECTION OF THE CENTER ATTACH BRACKET AT ILES 480. TRIMMED OUT CRACKED SECTION OF CLOSURE WEB. FABRICATED NEW SECTION OF WEB AND ASSOCIATED SLICE DOUBLERSDR UIEA200200034Skin · corrodedDURING CURRENT (C) CHECK AT SIAEC FOUND RIGHT HORIZONTAL STABILIZER BOTTOM SKIN AT STA 343 OUTER SURFACE CORRODED (LEVEL 2). FASTENERS REMOVED IN THE AFFECTED AREA. ALL HOLES CHECKED FOR CORROSION, OVER-SIDED AND HFEC INSPECTED FOR CRACKS. NO ADDITIONAL CORRSDR UIEA200200033Beam · crackedDURING CURRENT (C) CHECK AT SIAEC FOUND LOWER KEEL BEAM CHORD INBOARD VERTICAL FLANGE CRACKED 10 INCH FROM BS 1344 TO 1354 AT LBL 9.0. LEVEL 1 CORROSION PRESENT IN CRACKED AREA OF VERTICAL WEB THROUGH ABOUT 50 PERCENT OF THE ORIGINAL THICKNESS. CRACKED/ CORSDR UIEA200200028Indicator · stoppedAIR TURN BACK: F/OS AIR SPEED INDICATOR STOPPED AT 138 KTS. MACH OK. ALL OTHER FLIGHT INDICATONS OK. SWITCHED TO ALTERNATE STATIC-NO HELP. RETURNED TO ORD. C/A: REPLACED F/OS AIR SPEED INDICATOR AND ACCOMPLISHED FULL PITOT STATIC CHECK WITH 500 TESTER. CSDR UIEA01073Fitting · crackedDURING INSPECTION, FOUND THE NR 4 PYLON STRUT TO DIAGONAL BRACE FITTING WITH ONE SHEARED FASTENER. OVERSIZED HOLE, HFEC OF OVERSIZED HOLE INDICATED A DEFECT IN THE ATTACH FITTING. REMOVED PYLON, REMOVED FITTING, FOUND RADIUS FILLER NOT INSTALLED. PERFORMED SDR UIEA01072Fitting · crackedDURING INSPECTION, FOUND THE NR 1 PYLON STRUT TO DIAGONAL BRACE FITTING CRACKED IN THE COMMON RADIUS OF THE HORIZONTAL TO VERTICAL SUPPORT FLANGE ALONG WITH ONE SHEARED FASTENER. REMOVED PYLON, REMOVED FITTING, FOUND RADIUS FILLER NOT INSTALLED. PERFORMED HFSDR UIEA01071Intercostal · crackedDURING INSPECTION, FOUND MAIN DECK FLOOR LINE INTERCOSTALS FROM STATION 340-380 LEFT CRACKED AT NUMEROUS FASTENER HOLES. TRIMMED OFF SHEAR TIES CONTAINING CRACKED FASTENER HOLES. PERFORMED HFEC INSPECTION AT CUT LINE TO ENSURE NO CRACKS. NO CRACKS FOUND. FSDR UIEA01070Frame · crackedDURING INSPECTION, FOUND FRAME WEB AND DOUBLER STATION 440 CRACKED AT STRINGER 13R, CRACK ENDS IN EXISTING FASTENER LOCATION. PERFORMED OPEN HOLE HFEC INSPECTION TO ENSURE CRACK CONTAINMENT. FABRICATED DOUBLERS AND FILLERS. INSTALLED PER STANDARD PRACTICES SDR UIEA01069Frame · crackedDURING INSPECTION, FOUND FRAME WEB STATION 220 CRACKED AT STRINGER 14R, 1.2 INCH COMMON TO THE TRIANGULAR CUTOUT. STOP DRILLED CRACK. PERFORMED OPEN HOLE HFEC INSPECTION TO ENSURE CRACK CONTAINMENT IN STOP HOLE. FABRICATED DOUBLER AND INSTALLED PER STANDARDSDR UIEA01068Frame · crackedDURING INSPECTION, FOUND FRAME AND DOUBLER STATION 520 CRACKED AT STRINGER 10A (L) AND 11L COMMON TO THE STRINGER CUT-OUT AT 10A(L) AND 11L. FABRICATED DOUBLERS AND INSTALLED PER STANDARD PRACTICES IAW SRM 53-10-04. CLIP REPLACED. REINSPECT AREA PER SB 747-SDR UIEA01067Frame · crackedDURING INSPECTION, FOUND FRAME DOUBLER AND CLIP COMMON TO STATION 500 CRACKED AT STRINGER 10A (L) AND 11L. FABRICATED DOUBLERS AND INSTALLED PER STANDARD PRACTICES IAW SRM 53-10-04. CLIP REPLACED. REINSPECT AREA PER SB 747-53A2265 AT 3000 CYCLE INTERVALS. SDR UIEA01066Frame · crackedDURING INSPECTION, FOUND FRAME WEB DOUBLER STATION 420 CRACKED AT STRINGER 16L COMMON TO THE STRINGER CUT-OUT. CRACK NOT STOP DRILLED DUE TO CRACK PROXIMITY TO EDGE OF THE PART. FABRICATED DOUBLER AND INSTALLED PER STANDARD PRACTICES IAW SRM 53-10-04. REINSSDR UIEA01065Doubler · crackedDURING INSPECTION, FOUND FRAME STATION 420 CRACKED AT STRINGER 14 (E)L AND STRINGER 15L AT THE SHEAR DOUBLER COMMON TO THE STRINGER CUTOUT. TRIMMED AWAY TWO FASTENER ROWS OF THE OUTBOARD REINFORCING ANGLE. STOP DRILLED CRACKS. FABRICATED FILLER, DOUBLERS ANSDR UIEA01064Frame · crackedDURING HFEC INSPECTION, FOUND FRAME STATION 800 CRACKED AT STRINGER 17R COMMON TO THE AFT INNER CHORD AT A FASTENER HOLE. TRIMMED OUT CRACK. FABRICATED FILLER AND REPAIR STRAPS AND INSTALLED PER STANDARD PRACTICES IAW SRM 53-10-04 FIG 114. HFEC (FLAT SURFACSDR UIEA01063Frame · crackedDURING INSPECTION FOUND FRAME STATION 480 CRACKED AT STRINGER 14R COMMON TO THE CUTOUT. STOP DRILLED CRACK. FABRICATED REPAIR DOUBLER AND INSTALLED PER STANDARD PRACTICES IAW SRM 53-10-04. REINSPECTION TO BE ACCOMPLISHED AT 3000 CYCLES AND REPETITIVE AT 300SDR UIEA01062Skin · crackedDURING HFEC INSPECTION, FOUND THE LOWER AFT CARGO COMPARTMENT DOOR CUT-OUT, UPPER FORWARD CORNER SKIN CRACKED. CRACK TRIMMED AWAY. FILLER AND REPAIR DOUBLERS FABRICATED AND INSTALLED PER STANDARD PRACTICES IAW SRM 53-30-03 FIG 60, TYPE II. REINSPECTION IS RSDR UIEA00053Turbine · failedATB - FLT 3120 - CREW HEARD A LOUD BANG FROM RIGHT SIDE OF AIRCRAFT, THEN NR 4 ENGINE SHUTOFF. UPON RETURN TO LAX, IT WAS DISCOVERED THAT NR 4 ENGINE TURBINE SECTION HAS FAILED AND THE ENGINE HAS INTERNAL DAMAGE. SEVERAL BLADES FOUND DAMAGED DURING BORESCOPE
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