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 2001F00202Panel · crackedDURING PREFLIGHT, FOUND LEFT WING UPPER PANEL ASSEMBLY ABOVE NR 2 ENGINE PYLON AND ABOVE NR 1 SLAT CRACKED APPROXIMATELY 48 INCHES LONG FROM FORWARD TO AFT OF PANEL. REMOVED, REPAIRED AND REINSTALLED PANEL ASSEMBLY. REPAIRED IAW SRM 51-40-09 AND 51-40-12. (SDR UIEA01051Flap Track · corrodedDURING INSPECTION FOUND, NR 1 FLAP TRACK AFT INBOARD REAR SPAR ATTACH MOUNT HOLE CORRODED. REAMED HOLE OVERSIZE TO 1.139 FEET, FABRICATED BUSHING. INSTALLED BUSHING PER STANDARD PRACTICES. REINSTALLED WITH STANDARD SIZE HARDWARE. NR 3 FLAP TRACK BOTH REAR SDR UIEA01050Skin · crackedDURING INSPECTION FOUND PYLON SKIN NR 4 POSITION CRACKED AT ACCESS DOOR R/S BETWEEN NAC 211.42 AND 222.50. TRIMMED OUT CRACKED AREA. HFEC AREA FOR ADDITIONAL CRACKING, NO CRACKS FOUND. FABRICATED FILLER AND REPAIR DOUBLER, INSTALLED SAME PER STANDARD PRACTISDR UIEA01049Skin · chafedDURING INSPECTION OF LOWER FORWARD CARGO COMPARTMENT DOOR CUT OUT, FOUND FUSELAGE SKIN CHAFFED IN TWO AREAS AT THE AFT LOWER CORNER BETWEEN STRINGER 38/39R. POLISHED SKIN, HFEC INSPECTED, NO CRACKS. FABRICATED REPAIR DOUBLERS. INSTALLED PER STANDARD PRACTICSDR UIEA01048Beam · crackedDURING INSPECTION OF LOWER AFT CARGO COMPARTMENT DOOR, FOUND CRACK 1.5 INCHES LONG ON LOWER FORWARD END OF LOWER EDGE BEAM. STOP DRILLED CRACK. FABRICATED REPAIR DOUBLER. INSTALLED PER STANDARD PRACTICES IAW SRM 51-30. (M)SDR UIEA01047Door Frame · crackedDURING HFEC INSPECTION PER SB 747-53A2488 FOUND UPPER AFT CARGO COMPARTMENT DOOR CUT OUT WITH CRACK INDICATION OF .5MM AT FASTENER HOLE UNDER AFT HINGE, AFT HOLE, LOWER ROW (SECOND LAYER). FASTENER IS OUT OF THE SB INSPECT AREA AND NOT SUBJECT TO REWORK PER ASDR UIEA01043Stringer · corrodedDURING INSPECTION,FOUND STRINGER 51L AT BS 1480 CORRODED. TRIMMED OUT CORRODED AREA. FABRICATED NESTED CHANNEL REPAIR AND FILLER. INSTALLED NEW STRINGER END FITTING ALONG WITH FILLER AND NESTED CHANEL PER STANDARD PRACTICES. (M)SDR UIEA01042Doubler · corrodedDURING INSPECTION, FOUND BONDED DOUBLER CORRODED ON CANTED BULKHEAD BS 1241 AT LBL 11.33. USED GUN BARREL REAMER, REMOVED LAYER OF CORRODED SKIN OF BONDED DOUBLER. FABRICATED FILLER AND REPAIR DOUBLERS. INSTALLED PER STANDARD PRACTICES PER BOEING TELEX. (MSDR UIEA01041Frame · gougedDURING INSPECTION FOUND BS 360 FRAME DEEPLY GOUGED BETWEEN STRINGER 2L AND 2AL. CUT AWAY DAMAGED AREA. FABRICATED REPAIR FILLER, DOUBLERS AND SPLICE PLATES. INSTALLED PER STANDARD PRACTICES IAW BOEING TELEX. MODIFICATION SB 747-53-2272 PREVIOUSLY ACCOMPLISSDR UIEA01046Skin · crackedDURING HFEC INSPECTIN PER SB 747-53A2488 FOUND LOWER LOBE CARGO COMPT UPPER FORWARD DOOR CUT-OUT CRACKED 2MM. TRIMMED OUT CRACK. FABRICATED FILLER AND REPAIR DOUBLER. INSTALLED IAW SRM 53-30-03 TYPE 1 (SKIN CRACK ONLY). (M)SDR UIEA01045Pressure Panel · crackedDURING INSPECTION OF PRESSURE DECK NUMEROUS AREAS WERE FOUND WITH SPOT CORROSION BETWEEN BS 1460/1480 AT RBL 6, RBL 26.5; LBL 6, LBL 20, LBL 39, LBL 47.5. MOST AREAS BLENDED TO SRM LIMITS, TREATED AND FINISHED PER STANDARD PRACTICES. THE FOLLOWING AREAS WERESDR UIEA01044Bulkhead · crackedDURING INSPECTION OF AFT PRESSURE BULKHEAD BS 2360 PER SB 747-53A2275 FOUND CRACK .75 INCH LONG ORIGINATING FROM FASTENER HOLE FROM WEB TO Y-RING LAP JOINT BETWEEN STRINGER 24 AND 25R. CUT OUT CRACKED AREA. FABRICATED FILLER AND DOUBLER. OVERSIZED FASTENER SDR UIEA01007Frame · crackedDURING ACCOMPLISHMENT OF SB 747-53-2272 FOUND ONE CRACKED HOLE BS 360 LEFT ABOVE STRINGER 15L. STOP DRILLED CRACK, INSTALLED REPAIR DOUBLERS PER STANDARD PRACTICES IN A NON-MANDATORY ZONE. AMOC APPROVED PER PAR (9) OF AD 91-11-01. (M)SDR UIEA01008Frame · crackedDURING ACCOMPLISHEMENT OF SB 747-53-2272 FOUND TWO CRACKED HOLE BS 360 R/S AT STRINGER 14R AND STRINGER 15R. STOP DRILLED CRACK, INSTALLED REPAIR DOUBLERS PER STANDARD PRACTICES IN A NON-MANDATORY ZONE. AMOC APPROVED PER PAR 9 OF AD 91-11-01. (M)SDR UIEA01009Frame · crackedDURING ACCOMPLISHMENT OF SB 747-53-2272 FOUND ONE CRACKED HOLE BS 380 R/S AT STRINGER 14R. STOP DRILLED CRACK, INSTALLED REPAIR DOUBLER PER STANDARD PRACTICES IN A NON-MANDATORY ZONE. AMOC APPROVED PER PAR 9 OF AD 91-11-01. (M)SDR UIEA01011Frame · misdrilledDURING INSPECTION OF THE NOSE WHEEL FRAME STATIONS, FOUND NINE HOLES ON FRAME WEB BS 300 L/S SHORT EDGE DISTANCE. TRIMMED AWAY AFFECTED AREA. MANUFACTURED FILLERS, REPAIR STRAPS AND DOUBLERS. INSTALLED PER SRM 53-10-04. (M)SDR UIEA01010Skin · crackedDURING INSPECTION OF AFT LOWER LOBE CARGO DOOR CUTOUT, A CRACK WAS DISCOVERED AT THE UPPER FORWARD CORNER, STATION 1814 APPROX 1.3 INCH. TRIMMED OUT CRACK, MANUFACTURED FILLER AND EXTERNAL DOUBLER FROM .063 2024T3 ALUMINUM. INSTALLED PER SRM 53-30-03. (M)SDR UIEA01006Frame · damagedUPON REMOVAL OF FRAME SPLICE DOUBLER IAW SB747-53A-2272, FOUND ELONGATED HOLES IN FRAME WEB AT BS 300 RIGHT, JUST ABOVE STRINGER 14R BETWEEN RBL 60 AND RBL 70. TRIMMED OUT EXISTING WEB IN AREA OF ELONGATED HOLES. MANUFACTURED FILLER, REPAIR DOUBLERS AND SPLISDR UIEA01003Structure · corrodedDURING THE RECENT C-CHECK, THE UPPER CHORD AT BS 1840 WAS FOUND CORRODED BETWEEN LBL 75 AND 98 ON THE HORIZONTAL SURFACE AND EXTENDED DOWN ONTO THE VERTICAL SIDE. CORRODED SECTION WAS REMOVED, REPLACED AND REPAIR ANGLES WERE INSTALLED. REWORKED AREA EXTENDS SDR UIEA01002Skin · corrodedDURING THE RECENT C-CHECK, THE R/W EXTERNAL SKIN WAS CORRODED AT WS 320 COMMON TO STRINGER 15 AND WBL 179. CORROSION REMOVED, AREA BLENDED, TREATED AND REFINISHED IAW 57-30-01 FIG 2. (M)SDR UIEA01004Spar · corrodedDURING THE RECENT C-CHECK, THE REAR SPAR (OUTSIDE SURFACE) WAS FOUND CORRODED IN THE VICINITY OF THE NR 2 INBOARD FUELING VALVE MOUNT BOLT HOLES AT WS 562.50. FUELING EQUIPMENT AND MOUNT BOLT REMOVED. AREA REWORKED BY SPOT FACING CORRODED AREA, BLENDED, TREASDR UIEA01001Cylinder · corrodedDURING THE RECENT C-CHECK, THE LEFT OUTER CYLINDER SPUD BOSS WAS FOUND CORRODED IN THE AREA OF CHROME LOSS. AREA CLEANED OF CORROSION, TREATED, CHECKED FOR HEAT RELATED DAMAGE. REWORK AREA IS 5MM IN DIAMETER WITH MISSING CHROME AND MATERIAL LOSS OF .4 MM AFTSDR 2001F00162Panel · crackedDURING PREFLIGHT, FOUND LEFT WING UPPER PANEL ASSEMBLY ABOVE NR 2 ENGINE PYLON AND ABOVE NR 1 SLAT CRACKED APPROXIMATELY 48 INCHES LONG FROM FORWARD TO AFT OF PANEL. REMOVED, REPAIRED AND REINSTALLED PANEL ASSEMBLY. REPAIRED IAW SRM 51-40-09 AND 51-40-12. (SDR 20010206SG002Actuator · brokenDURING CRUISE, THE RED GEAR WARNING LIGHT ILLUMINATED INTERMITTENTLY. PLACED GEAR HANDLE IN THE UP POSITION AND HEARD THUMPING NOISE APPARENTLY FROM THE NOSE LANDING GEAR (NLG) WHEEL WELL AREA WITH SUBSEQUENT LOSS OF NR 1 SYSTEM HYDRAULIC QUANTITY. PLACED GESDR 20010108AP010Structure · damagedON POSTFLIGHT, FOUND NR 15 LEADING EDGE KRUEGER FLAP DAMAGED AND APPROX HALF OF FLAP PARTIALLY SEPARATED ROM MOUNTS CAUSING IMPACT DAMAGE TO THE RIGHT HORIZONTAL STABILIZER LEADING EDGE AND UPPER SURFACE. REPLACED NR 15 LEADING EDGE KRUEGER FLAP. REPAIRED DASDR 20010108AP009Structure · damagedON POSTFLIGHT, FOUND NR 15 LEADING EDGE KRUEGER FLAP DAMAGED AND APPROXIMATELY HALF OF FLAP PARTIALLY SEPARATED FROM MOUNTS CAUSING IMPACT DAMAGE TO THE RIGHT HORIZONTAL STABILIZER LEADING EDGE AND UPPER SURFACE. REPLACED NR 15 LEADING EDGE KRUEGER FLAP. REPSDR 20001212AP008Support Bracket · crackedNR 4 ENGINE FIRE LOOP MOUNT TUBE AT 12:00 POSITION ABOVE HIGH PRESSURE TURBINE CRACKED. REMOVED AND REPLACED FIRE LOOP SUPPORT BRACKETS IAW AMM 26-11-01. (M)SDR 20001212AP007Support Bracket · crackedNR 3 FIRE LOOP SUPPORT BRACKET AT 1:00 POSITION ABOVE THE DIFFUSER AT THE ELECTRICAL CONNECTION TO THE LOOP IS CRACKED. REMOVED AND REPLACED FIRE LOOP SUPPORT BRACKETS IAW AMM 26-11-01. (M)SDR 20001212AP006Support Bracket · crackedNR 2 FIRE LOOP SUPPORT BRACKET AT 1:00 POSITION ABOVE THE DIFFUSER AT THE ELECTRICAL CONNECTION TO THE LOOP IS CRACKED. REMOVED AND REPLACED FIRE LOOP SUPPORT BRACKETS IAW AMM 26-11-01. (M)SDR 20001212AP005Support Bracket · brokenNR 1 ENGINE FIRE LOOP SUPPORT TUBE AT 12:00 JUST ABOVE THE HIGH PRESSURE TURBINE IS BROKEN. REMOVED AND REPLACED FIRE LOOP SUPPORT BRACKETS IAW AMM 26-11-01. (M)SDR 20001024AP001Battery · corrodedF/O''S EMERGENCY LIGHT (FLASHLIGHT) BATTERIES CORRODED. CHANGED BATTERIES, OPERATES NORMAL. ALL EMERGENCY EQUIPMENT BATTERIES ARE CHECKED AND REPLACED AS NECESARY AT A-CHECK. NEXT CHECK DUE JULY 17, 2000. (M)SDR 20000728SH009Compressor · crackedAFTER ENG AND MODULE DISASSEMBLY, ENG SHOP INSP GROUP FOUND DEBLADED HPC11-14TH SPOOL-SHAFT A VISIBLE CRACK. A SEPARATED PIECE OF 12TH STAGE DOVETAIL PRESSURE SURFACE EDGE (REAR SIDE) APPROX 1.5 INCHES LONG CIRCUMFERENTIALLY STARTING FROM A CRACK. PART PARAMSDR UIEA00025Skin · crackedDURING C-CHECK, FOUND 25 INCH CRACK ON FUSELAGE SKIN STA 980L. CRACK STARTS AT STR 37L AND CONTINUES TO STR 38L. ADDITIONALLY, FOUND DRAG SPLICE FITTING CRACKED, FRONT SPAR PRESSURE BULKHEAD CHORD CRACKED, FRONT SPAR PRESSURE BULKHEAD WEB CRACKED, AND STR 38SDR UIEA99073Frame · crackedFUSELAGE FRAME AT BS 1265 LEFT SIDE FOUND WEB CRACK AND SEVERAL FASTENER HOLES ELONGATED. INTERIM REPAIR IAW BOEING TELEXS TO BE INSPECTED EVERY 2000 FLIGHTS. (M)SDR UIEA99072Angle · crackedMAIN DECK, CREASEBEAM ATTACHED ANGLE AT BS 980 STRINGER 5L AND 5R FOUND CRACK. THE CRACKED FLANGE WAS TRIMMED OUT AND REPAIR DOUBLER AND ANGLE WERE INSTALLED IAW BOEING TELEXS. (M)SDR UIEA99071Strap · crackedNR 1, 2, 3, 4, PYLONS EXTERIOR RIGHT PRE-COOLER EXHAUST CUTOUT FOUND WITH CRACK,AND NR 3 STIFFENER CRACK. REPAIRS CARRIED OUT IAW BOEING TELEXS AND SB 747-54-2163 R1 AND SB 747-54A2158 R2. THE SB REVS HAVE BEEN APPROVED ALTERNATE METHOD OF COMPLIANCE. (M)SDR UIEA99070Strap · cracksNR 4 PYLON INTERIOR, LEFT BULKHEAD STRAP AT NAC STATION 286 FOUND CRACKED. REPAIRED IAW BOEING TELEXS, TO BE RE-INSPECTED EVERY C-CHECK NOT TO EXCEED 18 MONTHS OR 1000 FLTS. (M)SDR UIEA99069Fitting · oversizeNR 1 AND NR 4 PYLONS FOUND FASTENER HOLE SIZE TO EXCEED TOLERANCE PER SB 747-54A2152 IN SPRINGBEAM SUPPORT FITTINGS IN 3 HOLE LOCATIONS. HOLES WERE OVERSIZED, NDT PERFORMED TO VERIFY NO CRACKS. NO INSURANCE CUT WAS PERFORMED AND FASTENERS INSTALLED. THIS ISSDR UIEA99068Spar Web · crackedRIGHT WING FUEL TANK INTERIOR WS 382 TO WS 411 MID SPAR AFT UPPER WEB SURFACE FOUND CRACK PROPAGATING FROM EXISTING REPAIR. MID SPAR WEB CRACK AT MSS 400 WAS TRIMMED OUT AND A PERMANENT REPAIR INSTALLED. AT MSS 394 A FREEZE PLUG WAS INSTALLED COMMON TO THE WSDR UIEA99067Spar Web · crackedLEFT WING MID SPAR AND UPPER CHORD, FASTENER HOLES ELONGATED AND CRACKED. ALSO, EXISTING REPAIR DOUBLER FASTENER HOLE CHIPPED FROM WS 400 TO WS 385. AT 12 HOLE LOCATIONS BETWEEN WS 388 AND 407 OVERSIZE HI-LOCKS WERE INSTALLED AND AT ONE LOCATION SEPARATE FRESDR UIEA99066Spar Web · corrosionLEFT WING FRONT SPAR WEB CORRODED BETWEEN FSSO 1314 TO FSSO 1322. TRIMMED OUT CORRODED AREAS, NDT WEB NO CRACK INDICATION. REPAIRED IAW BOEING TELEXS. (M)SDR UIEA99065Doubler · crackedNR 1 PYLON CAP SKIN MOD MO 54-0074 AREA FOUND WITH EXISTING DOUBLER, BULKHEAD FRAME CRACK AT STATION 270. THE CRACKED FRAME FLANGE WAS TRIMMED TO REMOVED DAMAGE, NDT PERFORMED TO VERIFY NO OTHER CRACKS. NEW REPAIR ANGLES AND NEW DOUBLER INSTALLED IAW BOEING SDR UIEA99064Frame · crackedNR 3 PYLON INTERIOR AFT MOUNT BULKHEAD WEB AFT SIDE AT NAC STATION 286 FOUND WITH CRACK. DAMAGED AREA WAS TRIMMED OUT, NDT INSPECTED, REPAIRED IAW BOEING TELEXS. (M)SDR UIEA99063Drive Link · chafedNR 3 FLAP TRACK MOVEABLE CANOE FAIRING FIXED DRIVE LINK CHAFED, BLENDED OUT DAMAGE AND NDT INSPECTED. SHOT PEENED AND REPAIRED IAW BOEING TELEX. (M)SDR UIEA99059Tee Chord · crackedDURING ROUTINE INSPECTION OF NR 1 AND NR 4 PYLONS, CRACKS WERE DISCOVERED IN THE RT UPPER TEE CHORD, FORWARD HORIZONTAL FLANGE, NACELLE STA 270. CRACK LENGTH IN NR 1 PYLON WAS 2.25 INCHES, NR 4 PYLON WAS 1.25 INCHES. REPAIRS ACCOMPLISHED IAW KLM DATA FAX 99-SDR UIEA99058Fitting · interferenceDURING ROUTINE IMPLEMENTATION OF SB 747-53A2390, FASTENER INTERFERENCE OCCURRED AT THE NR 7 AND NR 8 HOLES IN BOTH THE LEFT AND RIGHT SPLICE AREAS. THE NUTS IN THE SUBJECT AREA INTERFERE WITH THE FLANGE OF THE SPLICE FITTINGS ABOVE THE FASTENER HOLES. RESOLVSDR UIEA99057Beam · crackedDURING ROUTINE INSPECTION OF THE WING TRAILING EDGE AREA, FOUND THE UPPER CHORD SUPPORT BEAM CRACKED IN THE VICINITY OF THE LINK ASSEMBLY. MADE PERMANENT REPAIR BY SPLICING IN A REPLACEMENT SECTION IAW KLM ENGINEERING AND MAINTENANCE REPORT NR 1H105453 AND BOSDR 99ZZZX3052Tee Chord · crackedDURING ROUTINE INSPECTION OF NR 1 AND NR 4 PYLONS, CRACKS WERE DISCOVERED IN THE RT UPPER TEE CHORD, FORWARD HORIZONTAL FLANGE, NACELLE STA 270. CRACK LENGTH IN NR 1 PYLON WAS 2.25 INCHES, NR 4 PYLON WAS 1.25 INCHES. REPAIRS ACCOMPLISHED IAW KLM DATA FAX 99-SDR UIEA99056Frame · dentedFRAME DENTED AT STA 1840 RT TWO PLACES, FIRST BETWEEN STR 12 AND STR 13, SECOND BETWEEN STR 10 AND STR 11. FRAME REPAIRED BETWEEN STR 12/13 PER SRM 53-10-04 FIG 87. FRAME REPAIRED BETWEEN STR 10/11 PER ACC KLM DFX 99-127 REV 2. (X)SDR UIEA99055Structure · crackedBULK CARGO DOOR SKIN, DOUBLER AND TRIPLER CRACKED ON BOTTOM OF CUT-OUT AT BS 1980 RT BETWEEN STR 37 AND STR 38. CRACK IS HORIZONTAL AND MEASURES 0.500 INCHES. CRACK REPAIRED PER ACC KLM DFX 99-120. FORM 8110-3 ISSUED. (X)
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