N521UP

Part: BATTERY PACK — DISCHARGED (CABIN)

INSPECTION TYPE:N/A UPPER DECK EMERGENCY LIGHT INOP. REMOVED AND REPLACED BATTERY PACK IN REF TO 747 MM 33-51-04. OPS CHECKS GOOD. THIS CLEARS M389277. PLACARD REMOVED.

Part: LIGHT — INOPERATIVE (CABIN)

AFT L1 DOOR EMERGENCY LIGHT INOP. RELAMPED, OPS CHECK GOOD PER B747 MM 33-51-05.

Part: INTERCOSTAL — CRACKED (L1 DOOR) · airframe 62,889 hrs · 8,989 cycles

INSPECTION TYPE:C CABIN LT NR 1 DOOR BEAM INSTL FOUND CRACKED AS MARKED. NEW BEAM INTERCOSTAL FABRICATED USING MATL 7075-0.050" PER DWGABA7096. INTERCOSTAL HEAT TREATED TO T62 PER DPS7.00-1 HARDNESS HRB 78.4 IS ACCEPTABLE PER DPS1.05-3. HOLES PICKED UP ON NEW BEAM PER SRM 51-31-01 V.2R .40 AND REPROTECTED PER SRM 51-21-01 V.2R.40. NEW BEAM INTERCOSTAL INSTALLED PER SRM 51-33-01 AND 51-35-01V.2R.40.

Part: SIGN — INOPERATIVE (CABIN)

INSPECTION TYPE:N/A EXIT SIGN, LT & FWD OF UPPER DECK RT DOOR INOP. PREVIOUSLY DEACTIVITED, APPLIED DEACTIVATED PLACARD PER EO B747-3350-15296-B.

Part: STIFFENER — CRACKED (NR 2 PYLON) · airframe 79,715 hrs · 18,925 cycles

INSPECTION TYPE:C NR 2 PYLON RIGHT UPPER STIFFENER FOUND CRACKED JUST AFT OF FWD ENGINE MOUNT NR 13 HOLE AT INTERNAL ANGLE (1.125 INCH APPROX). NR 2 PYLON AFT OF RIGHT FWD ENGINE MOUNT NR 13 HOLE UPPER STIFFENER REPAIRED AS PER HX RS R54-50-35861 DETAIL VISUAL REPEAT INSPECTION IS REQUIRED TO THE SUBJECT REPAIR AREA EVERY C-CHECK OR 18 MONTHS WHICHEVER OCCURS FIRST REF UPS EO B747-5410-27520.

Part: FITTING — CRACKED (NR 1 PYLON) · airframe 79,715 hrs · 18,925 cycles

INSPECTION TYPE:C NR 1 PYLON REAR ENGINE MOUNT BULKHEAD UPPER LINK BEAM ATTACHMENT BATH FITTING FOUND CRACKED (CRACK LENGTH .375 INCH). NR 1 PYLON REAR ENGINE MOUNT BULKHEAD UPPER LINK BEAM ATTACHMENT BATH FITTING REPLACED AND INSTALLED AS PER SRM 51-10-01 PG 9 AND 51-30-02.

Part: FITTING — CRACKED (NR 3 PYLON) · airframe 79,715 hrs · 18,925 cycles

INSPECTION TYPE:C NR 3 PYLON REAR ENG MOUNT BULKHEAD UPPER LINK BEAM ATTACHMENT BATH FITTING FOUND SUSPECTED CRACK. CRACK LENGTH .3125 INCH. NR 3 PYLON REAR ENG MOUNT BULKHEAD UPPER LINK BEAM ATTACHMENT BATH FITTING REPLACED AND INSTALLED AS PER SRM 51-10-01 PG 9 AND 51-30-02.

Part: FITTING — CRACKED (NR 4 PYLON) · airframe 79,715 hrs · 18,925 cycles

INSPECTION TYPE:C NR 4 PYLON REAR ENG MOUNT BULKHEAD UPPER LINK BEAM ATTACHMENT BATH FITTING FOUND CRACKED. CRACK LENGTH .3125 INCH APPROX. NR 4 PYLON REAR ENGINE MOUNT BULKHEAD UPPER LINK BEAM ATTACHMENT BATH FITTING REPLACED AND INSTALLED AS PER SRM 51-10-01 PG 9 AND 51-30-02.

Part: ANGLE — CRACKED (NR 2 PYLON) · airframe 79,715 hrs · 18,925 cycles

INSPECTION TYPE:C NR 2 PYLON REAR ENG MOUNT BULKHEAD ATTACHMENT UPPER LINK BEAM AFT SIDE O/B ANGLE CRACKED AS MARKED (CRACK LENGTH .75 INCH). NR 2 PYLON REAR ENG MOUNT BULKHEAD ATTACHMENT UPPER LINK BEAM AFT SIDE O/B ANGLE REPAIRED AS PER SRM 54-14-03 FIG B & REFER NRC ALW51195 FOR WORKING DETAIL.

Part: RIB — CRACKED (NR 2 PYLON) · airframe 79,715 hrs · 18,925 cycles

INSPECTION TYPE:C NR 2 PYLON REAR ENG MOUNT BULKHEAD ATTACHMENT UPPER LINK BEAM O/B AND I/B SIDE RIB ANGLE FOUND CRACKED (NAC STA 277-4) FWD SIDE (CRACK LENGTH 1 INCH APPROX). NR 2 PYLON REAR ENG MOUNT BULKHEAD ATTACHMENT UPPER LINK BEAM O/B AND I/B SIDE RIB ANGLE REPAIRED AS PER SRM 54-14-03 FIG 13.

Part: RIB — CRACKED (NR 1 PYLON) · airframe 79,715 hrs · 18,925 cycles

INSPECTION TYPE:C NR 1 PYLON REAR ENG MOUNT BULKHEAD ATTACHMENT UPPER LINK BEAM O/B SIDE RIB ANGLE FOUND CRACKED FWD SIDE, CRACK LENGTH 1" BY 1/2". NR 1 PYLON REAR ENG MOUNT BULKHEAD ATTACHMENT UPPER LINK BEAM O/B SIDE RIB ANGLE REPAIRED AS PER HX RS NR R54-51-35856 AND UPS EO NR B747-5410-27512, DETAIL REPEAT INSP OF THE SUBJECT REPAIRED AREA IS REQUIRED AT EVERY 'C' CHK OR 18 MONTHS PER HX RS NR R54-51-35856 AND UPS EO NR B747-5410-27512.

Part: RIB — CRACKED (NR 3 PYLON) · airframe 79,715 hrs · 18,925 cycles

INSPECTION TYPE:C NR 3 PYLON REAR ENG MOUNT BULKHEAD ATTACHMENT ENG MOUNT BULKHEAD ATTACHMENT UPPER LINK BEAM O/B & I/B SIDE RIB ANGLE FOUND CRACKED (NAC STA 227.4) FWD SIDE (CRACK LENGTH .375 INCH & 1 INCH). NR 3 PYLON REAR ENG MOUNT BULKHEAD ATTACHMENT ENG MOUNT BULKHEAD UPPER LINK BEAM O/B SIDE RIB ANGLE REPAIRED AS PER SRM 54-14-03 FIG 13 AND O/B SIDE RIB ANGLE REPAIRED AS PER HX RS R54-51-35857 REPEAT INSP IS REQUIRED PER HX RS R54-51-35857 AND UPS EO B747-5410-27513.

Part: RIB — CRACKED (NR 1 PYLON) · airframe 79,715 hrs · 18,925 cycles

INSPECTION TYPE:C NR 1 PYLON DRY BAY UPPER LINK STRUT BEAM O/B SIDE ATTACHMENT RIB ANGLE FOUND CRACKED AS MARKED NAC STA 223 (AFT SIDE) , CRACK LENGTH 5/8" APPROX NR 1 PYLON DRY BAY UPPER LINK STRUT BEAM O/B SIDE ATTACHMENT RIB ANGLE REPAIRED AS PER HX RS NR R54-51-35856 AND UPS EO NR B747-5410-27512, DETAIL REPEAT INSPECTION OF THE SUBJECT REPAIRED AREA IS REQ. AT EVERY 'C' CHK OR 18 MONTHS PER HX RS NR R54-51-35856 AND UPS EO NR B747-5410-27512.

Part: FITTING — CORRODED (RT BLG DOOR) · airframe 79,715 hrs · 18,925 cycles

INSPECTION TYPE:C RIGHT BLG WHEEL WELL DOOR FWD SIDE INTERNAL FITTING FOUND CORROSION. CORROSION BLEND OUT 0.045" X 1" X 3" RIGHT B/G WHEEL WELL DOOR FWD SIDE INTERNAL FITTING REPLACED AND INSTALLED AS PER SRM 51-10-01 PG 9 AND 51-30-02.

Part: SPAR — CRACKED (LT WING TE FLAP) · airframe 79,715 hrs · 18,925 cycles

INSPECTION TYPE:C LHW O/B MID FLAP REAR SPAR O/B UPPER CHORD FOUND CRACKED, CRACK LENGTH 18" APPROX. LHW O/B MID FLAP REAR SPAR O/B UPPER CHORD BETWEEN WBL 801 TO MOST O/B AREA REPAIRED AS PER HX RS NR R57-58-35853 AND UPS ENGINEERING FILE NR 747-57-20148.

Part: FRAME — CRACKED (BS 400) · airframe 79,715 hrs · 18,925 cycles

INSPECTION TYPE:C E/E COMPT STA400 FRAME INNER CHORD FOUND CRACKED AT S44L, CRACK LENGTH 5/8". E/E COMPT BS 400 FRAME INNER CHORD AT ABOVE STR 44L AREA REPAIRED AS PER SRM 51-40-04 FIG 3.

Part: FITTING — CRACKED (FUSELAGE) · airframe 79,715 hrs · 18,925 cycles

INSPECTION TYPE:C M/D R3 DOOR CUTOUT FWD LWR CORNER FITTING CRACKED. CRACK LENGTH .5 INCH. M/D R3 DOOR CUTOUT FWD LWR CORNER FITTING REPLACED AS PER SRM 51-10-01 PG 9 AND INSTALLED AS PER SRM 51-30-02.

Part: SKIN — CRACKED (FUSELAGE) · airframe 79,715 hrs · 18,925 cycles

INSPECTION TYPE:C M/D LT NR 3 MED CUTOUT FWD LOWER CORNER FOUND SKIN AND BEAR STRAP CRACK, CRACK LENGTH 0.040" TO 3/4". M/D LT NR 3 MED CUTOUT FWD LOWER CORNER SKIN AND BEARSTRAP REPAIRED AS PER UPS EO NR B747-5330-24674 APPX 'M'.

Part: BEAR STRAP — CRACKED (FUSELAGE) · airframe 79,715 hrs · 18,925 cycles

INSPECTION TYPE:C M/D RT NR 3 MED CUTOUT FWD LOWER CORNER FOUND SKIN CRACK AND BEARSTRAP CORROSION, CRACK LENGTH 1/16 INCH APPROX. M/D RT NR 3 MED CUTOUT FWD LOWER CORNER SKIN AND BEAR STRAP REPAIRED AS PER UPS EO B747-5330-24674 APPENDIX 'N', BEAR STRAP CORROSION REMOVED AND REPROTECTED AS PER SRM 51-10-01 AND 51-10-02 ORI, 0.120" BLEND OUT DEPTH 0.010" BY 1/2" BY 6" WITHIN SRM 53-30-01 FIG 1 LIMIT (REF HX RS NR R53-41-35852, AND UPS EO B747-5330-27528)

Part: DOUBLER — CRACKED (FUSELAGE) · airframe 79,715 hrs · 18,925 cycles

INSPECTION TYPE:C M/D RIGHT BS 820 TENSION TIE TO FRAME CONNECTION FOUND 1 EA HOLE CRACK AT WEB DOUBLER AT STR 11R LOCATION. M/D RIGHT BS 820 TENSION TIE TO FRAME ATTACH DOUBLER REPLACED BETWEEN STR 9R TO 12R AREA AS PER SRM 51-10-01 PG 9 AND INSTALLED AS PER SRM 51-30-02.

Part: FRAME — CRACKED (FUSELAGE) · airframe 79,715 hrs · 18,925 cycles

INSPECTION TYPE:C AFT CARGO COMPT STA 1600 FRAME FOUND CRACKED ADJACENT TO SIDE GUIDE SUPPORT BRACKET AREA STR 39R. CRACK LENGTH .375 INCH. AFT CARGO COMPT BS 1600 FRAME AT STR 39R AREA REPAIRED AS PER SRM 51-40-03 FIG 1.

Part: FRAME — CRACKED (FUSELAGE) · airframe 79,715 hrs · 18,925 cycles

INSPECTION TYPE:C AFT CARGO COMPT STA 1580 FRAME FOUND CRACK ADJACENT TO SIDE GUIDE SUPPORT BRACKET AT S39R. CRACK LEGNTH .25 INCH. AFT CARGO COMPT BS 1580 STR 39R AREA FRAME REPAIRED AS PER SRM 51-40-03 FIG 1.

Part: ANGLE — CORRODED (FUSELAGE) · airframe 79,715 hrs · 18,925 cycles

INSPECTION TYPE:C RIGHT W/G WHEEL WELL STA 1319 VERTICAL ANGLE ATTACHED TO LONGERON FOUND CORROSION AS MARKED. CORROSION BLEND OUT 0.065" X .5" X 4" , HAS EXCEEDED SRM 53-10-01 FIG 1 LIMITS, RIGHT W/G WHEEL WHEEL BS 1319 VERTICAL ANGLE REPAIRED AS PER SRM 51-40-04 FIG 1.

Part: SUPPORT FITTING — WORN (RT BLG) · airframe 79,715 hrs · 18,925 cycles

INSPECTION TYPE:C RIGHT BLG I/B WHEEL WELL DOOR FWD INTERIOR DOOR SUPPORT FITTING FOUND WORN. RIGHT BLG I/B WHEEL WELL DOOR FWD INTERIOR DOOR SUPPORT FITTING REPLACED AS PER SRM 51-10-01 PG 9 AND INSTALLED AS PER SRM 51-30-02.

Part: LONGERON — CRACKED (FUSELAGE) · airframe 79,715 hrs · 18,925 cycles

INSPECTION TYPE:C RIGHT W/G WHEEL WELL STA 1248 LONGERON CRACK APPROX 0.850 INCH AS MARKED. RIGHT W/G WHEEL WELL BETWEEN BS 1244 TO BS 1270 O/B LONGERON REPAIRED AS PER SRM 51-40-04 FIG 3.

Part: FRAME — CRACKED (FUSELAGE) · airframe 79,715 hrs · 18,925 cycles

INSPECTION TYPE:C AFT CARGO COMPT STA 1560 FRAME FOUND CRACKED ADJACENT TO SIDE GUIDE SUPPORT BRACKET AREA AT STR 39R. CRACK LENGTH .3125 INCH. AFT CARGO COMPT BS 1560 STR 39R AREA FRAME REPAIRED AS PER SRM 51-40-03 FIG 1.

Part: REVEAL — CRACKED (L1 DOORWAY) · airframe 79,715 hrs · 18,925 cycles

INSPECTION TYPE:C M/D L1 DOOR FWD CUTOUT REVEAL CRACKED AT LATCH CAM FTG, CRACK LENGTH 3/8" APPROX. M/D L1 DOOR FWD CUTOUT REVEAL PANEL REPLACED AND INSTALLED AS PER SRM 51-10-01 PG 9 AND 51-30-02.

Part: FRAME — CRACKED (FUSELAGE) · airframe 79,715 hrs · 18,925 cycles

INSPECTION TYPE:C AFT CARGO COMPT STA 1540 FRAME FOUND CRACKED ADJACENT TO SIDE GUIDE SUPPORT BRACKET AREA AT S39R. CRACK LENGTH .25 INCH. AFT CARGO COMPT BS 1540 STR 39R AREA FRAME REPAIRED AS PER SRM 51-40-03 FIG 1.

Part: RIB — CORRODED (RT BLG) · airframe 79,715 hrs · 18,925 cycles

INSPECTION TYPE:C RIGHT BLG I/B WHEEL WELL DOOR FWD AREA FOUND BULGE AS MARKED. RIGHT BLG I/B WHEEL WELL DOOR FWD SUPPORT RIB REPLACED AS PER SRM 51-10-01 PG 9 AND INSTALLED AS PER SRM 51-30-02.

Part: SUPPORT — CORRODED (A/C BAY) · airframe 79,715 hrs · 18,925 cycles

INSPECTION TYPE:C FX AIR CONDITIONING BAY PANEL SUPPORT FRAME FOUND CORROSION AT STA 1018 TO STA 1045 LBL 58, CORROSION BLEND OUT 0.045" BY 1" BY 1" EXCEED SRM 53-10-01 FIG 1 LIMITS, FX BS 987 TO BS 1060 LBL 58" FAIRING SUPPORT REPAIRED AS PER SRM 51-40-04 FIG 1.

Part: REVEAL — CORRODED (L1 DOOR) · airframe 79,715 hrs · 18,925 cycles

INSPECTION TYPE:C M/D L1 DOOR FWD CUTOUT REVEAL NR 9 STOP FTG DOUBLER BULGED UP. M/D L1 DOOR FWD CUTOUT REVEAL NR 9 STOP FTG AREA SPLICE DOUBLER REPLACED AND INSTALLED AS PER SRM 51-10-01 PG 9 AND 51-30-02.

Part: SHEAR WEB — CRACKED (FUSELAGE) · airframe 79,715 hrs · 18,925 cycles

INSPECTION TYPE:C M/D BETWEEN TENSION TIE RIGHT SLOPING SHEAR WEB CRACKED AT BS 820. CRACK LENGTH 1.5 INCH. M/D BETWEEN BS 820 TO BS 840 TENSION TIE RIGHT SLOPING SHEAR WEB REPLACED AND INSTALLED AS PER SRM 51-10-01 PG 9 AND 51-30-02.

Part: SKIN — CRACKED (FUSELAGE) · airframe 79,715 hrs · 18,925 cycles

INSPECTION TYPE:C U/D RIGHT BS 340 - 360 S6R LAP JOINT TOP ROW FASTENER ROW 1EA HOLE FOUND CRACK AT FX SKIN RUNNING AFT APPROX .125 INCH BEYOND RIVET HEAD. FX STR 6R BETWEEN BS 340-392 LAP JOINT SKIN REPAIRED AS PER SRM 53-30-03 FIG 26 AND UPS EO B747-5330-0209 APP B AND TAR S/N 127776 WITHOUT ZERO TIMING AT CRITICAL ROW FASTENERS. REPEAT INSPECTION IS REQUIRED AS PER SRM 53-30-03 FIG 26 AND UPS ASSIGNED MPI P19377.

Part: SHEAR TIE — DAMAGED (BS 940) · airframe 79,715 hrs · 18,925 cycles

INSPECTION TYPE:C M/D BS 940 LT TENSION TIE STEEL PLATE FOUND SEM. M/D BS 940 LT TENSION TIE ATTACH STEEL PLATE REPLACED AND INSTALLED AS PER HX RS NR R53-25-35850 CONTINUE INSPECTION ARE REQUIRED AS PER UPS EO B747-5310-27442.

Part: SKIN — CRACKED (BS 340-360 S5R) · airframe 79,715 hrs · 18,925 cycles

INSPECTION TYPE:C U/D RT BS 340-360 S5R LOCATION FOUND 1 HOLE CRACK AT FX SKIN RUNNING FWD AND AFT APPROX 1/8" BEYOND RIVET HEAD. FX BS340-360 STR5R AREA SKIN REPAIRED WITHOUT ZERO TIMING AT CRITICAL ROW FASTENER AS PER SRM 53-30-03 FIG 1 AND UPS EO B747-5330-26295 APP B AND TAR 127777. REPEAT INSPECTION IS REQUIRED AS PER SRM 53-30-03 FIG 1 AND UPS ASSIGNED MPI NR P19375.

Part: CHANNEL — CRACKED (FUSELAGE) · airframe 79,715 hrs · 18,925 cycles

INSPECTION TYPE:C M/D LEFT BS 900 TENSION TIE TO FRAME CONNECTION FOUND NR 5 AND 13 HOLE CRACK AT FWD CHANNEL. CRACK LENGTH 0.030" AND 0.040". M/D LEFT BS 900 TENSION TIE FWD CHANNEL REPAIRED AS PER SRM 53-10-11 FIG 2. REPEAT INSPECTION IS REQUIRED AS PER SRM 53-10-11 FIG 2 TABLE 4 AND UPS ASSIGNED MPI P19385.

Part: CHANNEL — DAMAGED (FUSELAGE) · airframe 79,715 hrs · 18,925 cycles

INSPECTION TYPE:C M/D RIGHT BS 940 TENSION TIE TO FRAME CONNECTION FOUND NR 4 HOLE CRACK AT FWD CHANNEL RUNNING DOWN. CRACK LENGTH 0.060 INCH. M/D RIGHT BS 940 TENSION TIE TO FRAME FWD CHANNEL NR 4 HOLE OVERSIZED IN STACK UP TO 0.309 INCH DIA BY INCREMENT AS PER EO B747-5310-23715 APP D. FASTENER INSTALLED AS PER EO B747-5310-23715 APP C AFTER HFEC INSPECTED PER NTM PART 6 51-00-00 FIG 16.

Part: CHANNEL — DAMAGED (FUSELAGE) · airframe 79,715 hrs · 18,925 cycles

INSPECTION TYPE:C M/D LEFT BS 820 TENSION TIE TO FRAME CONNECTION FOUND NR 20, 23, 24 HOLE WITH PILOT HOLE AT AFT CHANNEL. M/D LEFT BS 820 TENSION TIE TO FRAME ATTACH TENSION TIE AFT CHANNEL NR 20, 23, 24 HOLES OVERSIZED IN STACK UP TO 0.278 INCH DIA BY INCREMENT AS PER EO B747-5310-23715 APP D. FASTENERS INSTALLED AS PER EO B747-5310-23715 APP C, AFTER HFEC INSPECTED PER NTM PART 6 51-00-00 FIG 16.

Part: SHEAR TIE — DAMAGED (BS 900) · airframe 79,715 hrs · 18,925 cycles

INSPECTION TYPE:C M/D BS 900 LT TENSION TIE STEEL PLATE FOUND SEM. M/D LT BS 900 TENSION TIE STEEL PLATE REPAIRED AS PER HX RS NR R53-25-35847 AND REPEAT INSPECTION IS REQUIRED AS PER UPS EO NR B747-5310-27440.

Part: CHANNEL — DAMAGED (FUSELAGE) · airframe 79,715 hrs · 18,925 cycles

INSPECTION TYPE:C M/D RIGHT BS 820 TENSION TIE TO FRAME CONNECTION FOUND NR 23 AND 24 HOLE WITH PILOT HOLE. M/D RIGHT BS 820 TENSION TIE TO FRAME AFT CHANNEL NR 23 AND 24 HOLES OVERSIZED IN STACK UP TO 0.278 INCH DIA BY INCREMENT AS PER EO B747-5310-23715 APP D. FASTENER INSTALLED AS PER EO B747-5310-23715 APP C AFTER HFEC INSPECTED PER NTM PART 6 51-00-00 FIG 16.

Part: DOUBLER — CRACKED (FUSELAGE) · airframe 79,715 hrs · 18,925 cycles

INSPECTION TYPE:C M/D LEFT BS 820 TENSION TIE TO FRAME CONNECTION FOUND NR 12 HOLE CRACK AT FRAME WEB DOUBLER. M/D LEFT BS 820 TENSION TIE TO FRAME ATTACH DOUBLER AT HOLE NR 12 OVERSIZED IN STACK UP TO 0.247 INCH DIA BY INCREMENT AS PER EO B747-5310-23715 APP D. FASTENER INSTALLED AS PER EO B747-5310-23715 APP C, AFTER HFEC INSPECTED PER NTM PART 6 51-00-00 FIG 16.

Part: SHEAR TIE — DAMAGED (BS 900) · airframe 79,715 hrs · 18,925 cycles

INSPECTION TYPE:C M/D BS 900 RT TENSION TIE STEEL PLATE FOUND SEM. M/DECK BS 900 RT TENSION TIE ATTACH STEEL PLATE REPAIRED. AS PER HX RS NR R53-25-35847 REPEAT INSPECTION IS REQUIRED AS PER UPS EO NR B747-5310-27440.

Part: FRAME — CRACKED (FUSELAGE) · airframe 79,715 hrs · 18,925 cycles

INSPECTION TYPE:C M/D RIGHT BS 820 TENSION TIE TO FRAME CONNECTION FOUND NR 10 HOLE CRACK AT FRAME WEB. CRACK LENGTH .0625 INCH APPROX. M/D RIGHT BS 820 TENSION TIE ATTACH FRAME BETWEEN STR 8R TO STR 12R AREA REPAIRED AS PER SRM 53-10-04 FIG 132.

Part: CHANNEL — CRACKED (FUSELAGE) · airframe 79,715 hrs · 18,925 cycles

INSPECTION TYPE:C M/D RIGHT BS 900 TENSION TIE TO FRAME CONNECTION FOUND NR 5, 13, 14 HOLE CRACK AT FWD CHANNEL. CRACK LENGTH 0.030", 0.040", 0.060". M/D RIGHT BS 900 TENSION TIE FWD CHANNEL REPAIRED AS PER SRM 53-10-11 FIG 2. REPEAT INSPECTION IS REQUIRED AS PER SRM 53-10-11 FIG 2 TABLE 4 AND UPS ASSIGNED MPI P19384.

Part: SKIN — CRACKED (BS 340-360 S5L) · airframe 79,715 hrs · 18,925 cycles

INSPECTION TYPE:C U/D LT BS 340-360 S5L LOCATION FOUND 1 HOLE CRACK AT FX SKIN RUNNING FWD AND AFT APPROX 1/8" BEYOND RIVET HEAD FX BS 340-360 STR 5L AREA SKIN REPAIRED WITH OUT ZERO TIMING AT CRITICAL ROW FASTENER AS PER SRM 53-30-03 FIG 1 AND UPS EO B747-5330-26295 APPENDIX A AND HX TAR NR 127778 REPEAT INSPECTION IS REQUIRED AS PER SRM 53-30-03 FIG 1.

Part: PLATE — DAMAGED (BS 920) · airframe 79,715 hrs · 18,925 cycles

INSPECTION TYPE:C M/D BS 920 RHS TENSION TIE TO FRAME STEEL PLATE 2EA HOLE FOUND SEM AT MOST O/B AS MARKED. M/D BS 920 RT TENSION TIE ATTACH STEEL PLATE REPLACED AND INSTALLED AS PER HX RS NR R53-25-35848 AND REPEAT INSPECTION IS REQUIRED AS PER UPS EO NR B747-5310-27452.

Part: CHANNEL — CRACKED (FUSELAGE) · airframe 79,715 hrs · 18,925 cycles

INSPECTION TYPE:C M/D LEFT BS 880 TENSION TIE TO FRAME CONNECTION FOUND NR 6, 7, 16 HOLE CRACK AT AFT CHANNEL. CRACK LENGTH 0.030 INCH. M/D LEFT BS 880 TENSION TIE AFT CHANNEL REPAIRED AS PER SRM 53-10-11 FIG 2. REPEAT INSPECTION IS REQUIRED AS PER SRM 53-10-11 FIG 2 TABLE 4 AND UPS ASSIGNED MPI P19386.

Part: CHANNEL — CRACKED (FUSELAGE) · airframe 79,715 hrs · 18,925 cycles

INSPECTION TYPE:C M/D LEFT BS 840 TENSION TIE TO FRAME CONNECTION FOUND NR 4 HOLE CRACK AT FWD CHANNEL RUNNING UP AND DOWN. CRACK LENGTH 0.040 INCH. M/D LEFT BS 840 TENSION TIE FWD CHANNEL REPAIRED AS PER SRM 53-10-11 FIG 2. REPEAT INSPECTION IS REQUIRED AS PER SRM 53-10-11 FIG 2 TABLE 4 AND UPS ASSIGNED MPI P19389.

Part: DOUBLER — CRACKED (FUSELAGE) · airframe 79,715 hrs · 18,925 cycles

INSPECTION TYPE:C M/D RIGHT BS 840 TENSION TIE TO FRAME CONNECTION FOUND NR 3 HOLE CRACK AT FRAME WEB DOUBLER RUNNING UP. CRACK LENGTH 0.030 INCH. M/D RIGHT BS 840 TENSION TIE TO FRAME ATTACH DOUBLER REPLACED AND INSTALLED BETWEEN STR 9R TO STR 12R AREA AS PER SRM 51-10-01 PG 9 AND 51-30-02.

Part: CHANNEL — DAMAGED (FUSELAGE) · airframe 79,715 hrs · 18,925 cycles

INSPECTION TYPE:C M/D RIGHT BS 880 TENSION TIE TO FRAME CONNECTION FOUND NR 20 HOLE OVAL AT AFT CHANNEL. M/D RIGHT BS 840 TENSION TIE TO FRAME AFT CHANNEL NR 20 HOLE OVERSIZED IN STACK UP TO 0.309 INCH DIA BY INCREMENT AS PER EO B747-5310-23715 APP D. FASTENER INSTALLED AS PER EO B747-5310-23715 APP C, AFTER HFEC INSPECTED PER NTM PART 6 51-00-00 FIG 16.

Part: FAILSAFE — CRACKED (FUSELAGE) · airframe 79,715 hrs · 18,925 cycles

INSPECTION TYPE:C M/D LEFT BS 880 TENSION TIE TO FRAME CONNECTION FOUND NR 10 HOLE CRACK AT FAILSAFE CHORD RUNNING UP. CRACK LENGTH 0.040 INCH. M/D LEFT BS 880 BETWEEN STR 8L TO STR 12L AREA FAILSAFE CHORD REPAIRED AS PER SRM 51-40-03 FIG 2.

Part: FITTING — CRACKED (FUSELAGE) · airframe 79,715 hrs · 18,925 cycles

INSPECTION TYPE:C M/D LEFT BS 880 TENSION TIE TO FRAME CONNECTION FOUND NR 10 HOLE CRACK AT TIE CLIP RUNNING DOWN. CRACK LENGTH 0.040 INCH. M/D LEFT BS 880 STR 9L AREA FRAME ATTACH TIE CLIP REPLACED AND INSTALLED AS PER SRM 51-10-01 PG 9 AND 51-30-02.

Part: CHANNEL — CRACKED (BS 840) · airframe 79,715 hrs · 18,925 cycles

INSPECTION TYPE:C M/D RT BS 840 TENSION TIE TO FRAME CONNECTION FOUND NR 8 HOLE CRACK AND NR 20 HOLE OVAL AT FWD CHANNEL.(CRACK LENGTH 0.040"). M/D RT BS 840 TENSION TIE FWD CHANNEL REPAIRED AS PER SRM 53-10-11 FIG 2 REPEAT INSPECTION IS REQUIRED AS PER SRM 53-10-11 FIG 2 TABLE IV AND UPS ASSIGNED MPI NR P19388.

Part: FITTING — CRACKED (FUSELAGE) · airframe 79,715 hrs · 18,925 cycles

INSPECTION TYPE:C M/D RIGHT BS 880 TENSION TIE TO FRAME CONNECTION FOUND NR 10 HOLE CRACK AT TIE CLIP RUNNING UP AND DOWN. CRACK LENGTH 0.040 INCH. M/D RIGHT BS 880 STR 9R FRAME ATTACH TIE CLIP REPLACED AND INSTALLED AS PER SRM 51-10-01 PG 9 AND 51-30-02.

Part: O-RING — CUT (STEERING SYS)

INSPECTION TYPE:N/A HYDRAULIC SYSTEM NR 1 FLUID LOSS IN FLIGHT. FOUND CUT O-RING ON LEFT NOSE WHEEL STEERING ACT TRANSFER TUBE. REPLACED SEALS IAW 32-51-05. OPS AND LEAK CHECKS GOOD DUE TO HYD FLUID LOSS. NR 1 EDP REMOVED AND REPLACED IAW MM 29-11-05. OPS AND LEAK CHECKS GOOD. CASE DRAIN AND PRESS FILTERS REPLACED. OPS AND LEAKS CHECK GOOD.

Part: BATTERY — INOPERATIVE (EMERGENCY LIGHT)

FOUND EMERG LT AT MAIN CARGO DECK ENTRANCE INOP, LT ASSY ON REQ A863705. REMOVED AND REPLACED BATTERY ASSY IAW MM 33-51-00. OPS CK OK.

Part: STRINGER — DAMAGED (FUSELAGE)

FOUND FUSELAGE DAMAGE ON THE LEFT SIDE FROM A CONTAINER STRIKE. DAMAGE TO FRAME, 2 STRINGERS, AND A 9" BY 9" HOLE. INSTALLED 33"X23" DOUBLER PER SRM 53-30-03 FIG 17.

Part: OXYGEN BOTTLE — LEAKING

AIR TURN BACK. IN CRUISE O2 DROPPED TO 150 PSI. REPLACED CREW O2 BOTTLES, USED SONICAIR AND SOAP LEAK CHECK FOR ALL FLEX LINES, ON DEMAND REGULATORS, O2 BOTTLES, ALL ACCESSIBLE (B) NUT CONNECTIONS AND LINES, REG AND SHUT OFF VALVES. BLOW OUT DISC STILL INTACT. LEAK CHECKED FOR 24 HRS. TAXIED WITH CABIN PRESSURIZED.ALL CHECKS DONE WITH NO DECAY NOTED.SYSTEM MAINTAINED PRESS OF 1725 PSI.

Part: LIGHT — INOPERATIVE (COCKPIT)

INSPECTION TYPE:N/A EMERGENCY LIGHTS OVER STEPS INOP. RELAMPED BATTERY PACK PER MM 33-51-04

Part: FRAME — DAMAGED (FUSELAGE) · airframe 77,205 hrs · 18,330 cycles

INSPECTION TYPE:C M/D LT BS 488 FRAME EXISTING REPAIR BETWEEN S16 AND S22 REPLACE FRAME WEB REPAIR PER SRM 53-10-04 FIG 121. FRAME WEB REPAIRED AS PER SRM 53-10-04 FIG 121 AT BS 488 BETWEEN STR 15L - 19L AREA NEW SEGMENT WEB REPLACED AND INSTALLED AT BETWEEN S19L-29L AREA AS PER SRM 51-10-01 PG 9 AND 51-30-02.

Part: SPAR — CRACKED (LT WING) · airframe 77,205 hrs · 18,330 cycles

INSPECTION TYPE:C LT WING FRONT SPAR WEB AT WS 642 AREA 1EA HOLE (9TH HOLE COUNT FROM TOP) COMMON TO RIB POST FOUND CRACK AT WEB. CRACK LENGTH .0625 INCH. LT WING FRONT SPAR WEB AT WS 642 (9TH HOLE COUNT FROM TOP) COMMON TO RIB POST IN ZONE A AS PER SB 747-57A2311 R2 TABLE 3 WITH REPEAT INSP INTERVALS OF 1600 FLIGHT CYCLES OR 6200 FLIGHT HOURS WHICHEVER IS EARLIER.

Part: ATTACH ANGLE — CRACKED (NR 4 PYLON) · airframe 77,205 hrs · 18,330 cycles

INSPECTION TYPE:C NR 4 PYLON NAC STA 221.9 REAR ENG MOUNT B/H UPPER OF MID SPAR WEB ATT T-ANGLE FOUND CRACKED JUST AT O/B SIDE. CRACK LENGTH 1.75 INCH. NR 4 PYLON NAC STA 221.9 REAR ENG MOUNT B/H UPPER OF MID SPAR WEB ATT T-ANGLE REPAIRED AS PER SRM 51-40-04 FIG 1.

Part: CHANNEL — CRACKED (FUSELAGE) · airframe 77,205 hrs · 18,330 cycles

INSPECTION TYPE:C M/D BS 2350 LBL 10 TO 40 HAT SECTION FLANGE FOUND CORRODED. CORRORION BLEND OUT 0.032" X 1" X 10" EXCEED SRM LIMIT. HAT SECTION REPLACED AS PER SRM 51-10-01 PG 9 AND 51-30-02.

Part: CARGO TRACK — CORRODED (CARGO BAY) · airframe 77,205 hrs · 18,330 cycles

INSPECTION TYPE:C U/D BS560 RBL28 TIE DOWN TRACK FOUND CORROSION. CORROSION BLEND OUT 0.036" BY 1/2" BY 4" EXCEED SRM LIMIT. TIE DOWN TRACK REPLACED AS PER SRM 51-10-01 PG9 AND INSTALLED AS PER SRM 51-30-02 JUST AT RBL28 BTN BS540 ANI BS570. P/N BAC1520-1567-7178T6511RK

Part: CHANNEL — CRACKED (FUSELAGE) · airframe 77,205 hrs · 18,330 cycles

INSPECTION TYPE:C M/D BS 2350 LBL 30 HAT SECTION FOUND CRACK. CRACK LENGTH .5 INCH. HAT SECTION REPLACED AS PER SRM 51-10-01 AND 51-30-02.

Part: FLOOR SUPPORT — CORRODED (BS 2250-2280) · airframe 77,205 hrs · 18,330 cycles

BS 2250 TO 2280 RBL80 FLOOR SUPPORT FOUND CORRODED. CORROSION BLEND OUT 0.025" BY 1.5" BY 3" EXCEED SRM LIMIT. BS 2220-2290 RT O/B AREA FLOOR SUPPORT REPLACED AND INSTALLED AS PER SRM 51-10-01 PG9 AND 51-30-02.

Part: ANGLE — CORRODED (FUSELAGE) · airframe 77,205 hrs · 18,330 cycles

INSPECTION TYPE:C M/D BS800-810 LBL117 FLOOR SUPPORT "L" ANGLE LWR FACE FOUND CORROSION. CORROSION BLEND OUT 0.028" BY 1/2" BY 2" EXCEED SRM LIMIT. FLOOR SUPPORT REPAIRED AS PER SRM 51-40-03 FIG 2.

Part: SEAT TRACK — CORRODED (BS 750-840) · airframe 77,205 hrs · 18,330 cycles

BS 750 TO 840 RBL 11 SEAT TRACK FLANGE FOUND CORRODED. CORROSION BLEND OUT 0.034" BY 1/2" BY 2" EXCEED SRM LIMIT. BS 750 TO BS 850 RBL11 TRACK REPAIRED AS PER SRM 53-10-05 FIG 14.

Part: CARGO TRACK — CRACKED (FUSELAGE) · airframe 77,205 hrs · 18,330 cycles

INSPECTION TYPE:C M/D BS 520-530 RBL 91 TIE DOWN TRACK I/B FLANGE FOUND CRACK. CRACK LENGTH .4375 INCH. M/D BS 480 TO BS 530 RBL 91 AREA SEAT TRACK REPAIRED AS PER SRM 53-10-05 FIG 4.

Part: CARGO TRACK — CORRODED (MAIN DECK) · airframe 77,205 hrs · 18,330 cycles

INSPECTION TYPE:C M/D TIE DOWN TRACK BS 480-510 LBL 33 CORRODED. CORROSION BLEND OUT 0.042 X .75 X 3 INCH EXCEED SRM LIMIT. CABIN BS 460 TO BS 510 LBL 33 TRACK REPLACED AND INSTALLED AS PER SRM 51-10-01 PG 9 AND 51-30-02.

Part: CARGO TRACK — CORRODED (BS 480-520) · airframe 77,205 hrs · 18,330 cycles

TIE DOWN TRACK BS480-520 LBL63-68 CORRODED. CORROSION BLEND OUT 0.030" BY 1/2" BY 3" EXCEED SRM LIMIT. TIE DOWN TRACK REPAIED AT BS480-530 LBL63-68 AS PER SRM 53-10-05 FIG4.

Part: FLOORBEAM — CORRODED (BS 480) · airframe 77,205 hrs · 18,330 cycles

FLOORBEAM UPPER CHORD BS 480 LBL 33-63 CORRODED. CORROSION BLEND OUT 0.034" BY 1" BY 20" EXCEED SRM LIMIT. BS 480 BL0 TO LBL78 FLOORBEAM UPPER CHORD. REPAIRED AS PER SRM 53-10-07 FIG 10.

Part: REVEAL — CRACKED (R1 DOOR) · airframe 77,205 hrs · 18,330 cycles

INSPECTION TYPE:C M/D R1 DOOR CUTOUT FWD UPPER CORNER REVEAL FOUND CRACK. CRACK LENGTH .75 INCH. CORNER REVEAL REPLACED AS PER SRM 51-10-01 PG 9 AND INSTALLED AS PER SRM 51-30-02.

Part: STIFFENER — CRACKED (NR 3 PYLON) · airframe 77,205 hrs · 18,330 cycles

INSPECTION TYPE:C NR 3 PYLON REAR MOUNT B/H UPPER T-CHORD RT END 2EA HOLE FOUND CRACKED. CRACK LENGTH .5 INCH. NR 3 PYLON REAR MOUNT B/H UPPER T-CHORD REPLACED AND INSTALLED AS PER SRM 51-10-01 PG 9 AND 51-30-02.

Part: SUPPORT FITTING — CRACKED (BULKHEAD HINGE) · airframe 77,205 hrs · 18,330 cycles

BS2598 B/H STABILIZER HINGE SUPPORT FITTING AREA FOUND 1 HOLE CRACK AT FRAME SUPPORT (4TH LAYER FROM AFT) CRACK LENGTH 0.030". BOLT HOLE REWORKED TO 0.500" AS PER EO B747-5310-14056 AND HOLE CONFIRMED CRACK FREE.

Part: HINGE BRACKET — CRACKED (HORIZONTAL STAB) · airframe 77,205 hrs · 18,330 cycles

BS 2598 B/H STABILIZER HINGE SUPPORT FITTING AREA 1EA HOLE CORROSION CRACK AT FRAME SUPPORT (4TH LAYER FROM AFT) CRACK LENGTH 0.030". BOTH HOLE REWORKED TO 0.500" AS PER EO B747-5310-14056 HOLE CONFIRMED CRACK FREE.

Part: STIFFENER — CRACKED (FUSELAGE) · airframe 77,205 hrs · 18,330 cycles

INSPECTION TYPE:C NWW RT SIDE PANEL BS 300-320 WL160 STIFFENER RADIUS AREA FOUND INTERMITTENT CRACKS, CRACK LENGTH 1/4" - 1/2". NWW RT SIDE PANEL BS 300-320 WL160 STIFFENER REPLACED AND INSTALLED AS PER SRM 51-10-01 PG 9 AND 51-30-02.

Part: STIFFENER — CRACKED (NLG WW) · airframe 77,205 hrs · 18,330 cycles

NWW RT SIDE PANEL BS 300-320 WL 150 STIFFENER RADIUS AREA FOUND INTERMITTENT CRACKS, CRACK LENGTH : 1/4" - 1/2". STIFFENER REPLACED AND INSTALLED AS PER SRM 51-10-01 PG 9 AND 51-30-02.

Part: FLOORBEAM — CRACKED (FUSELAGE) · airframe 77,205 hrs · 18,330 cycles

INSPECTION TYPE:C U/D BS 340 FLOORBEAM UPPER CHORD FWD AND AFT FLANGE FOUND 8EA FLOOR PANEL ATT HOLE CRACKED. CRACK LENGTH 0.063 INCH. U/D BS 340 RBL 36 TO LHS MOST O/B FLOORBEAM UPPER CHORD REPAIRED AS PER RS R53-15-35489 AND UPS EO B747-5310-24401-A.

Part: STIFFENER — CRACKED (NLG WW) · airframe 77,205 hrs · 18,330 cycles

NWW RT SIDE PANEL BS300-320 WL170 STIFFENER RADIUS AREA FOUND INTERMITTENT CRACKS, CRACK LENGTH 1/4-3/8. STIFFENER REPLACED AND INSTALLED AS PER SRM 51-10-01 PG 9 AND 51-30-02.

Part: FLOORBEAM — CRACKED (BS 360) · airframe 77,205 hrs · 18,330 cycles

INSPECTION TYPE:C U/D BS 360 FLOORBEAM AFT FLANGE AT LBL 26 FOUND 1EA FLOOR PANEL ATT HOLE CRACK RUNNING AFT 0.040 INCH. U/D BS 360 LBL 26 FLOORBEAM AFT FLANGE REPAIRED AS PER EO B747-5320-12407 APP D PLAN C FIG 3.

Part: STRINGER — CORRODED (CARGO BAY) · airframe 77,205 hrs · 18,330 cycles

INSPECTION TYPE:C BULK CARGO STR CORROSION FROM BS 1945-1960 S50R. CORROSION BLEND OUT 0.055" BY 1" BY 6" EXCEED SRM LIMIT. BULK CARGO COMPT BS 1930-1960 STR 50R AREA STRINGER REPAIRED AS PER SRM 53-10-03 FIG 8.

Part: STRUCTURE — MISREPAIRED (FUSELAGE) · airframe 77,205 hrs · 18,330 cycles

INSPECTION TYPE:C SHORT EDGE MARGIN FOUND AT U/D BS 380 AFT FLANGE RBL 40, 45, 50, 55.5, 61 AND 66.5 (LESS THAN 1.3). U/D BS 380 AFT FLANGE UPPER CHORD RBL 40, 45, 50, 55.5, 61 AND 66.5 AREA REPAIRED AS PER EO B747-5320-12407 APP D PLAN C FIG 3.

Part: STIFFENER — CRACKED (TUNNEL) · airframe 77,205 hrs · 18,330 cycles

INSPECTION TYPE:C NWW LT SIDE PANEL BS260-280 WL 180 STIFFENER RADIUS AREA. FOUND CRACK APP 1 3/8" LONG, STIFFENER. REPLACED AS PER SRM 51-10-01 PG9 AND INSTALLED AS PER SRM 51-30-02.

Part: FLOORBEAM — CRACKED (FUSELAGE) · airframe 77,205 hrs · 18,330 cycles

INSPECTION TYPE:C U/D BS 360 FLOORBEAM UPPER CHORD AFT FLANGE AT RBL 43 FOUND 1EA FLOOR PANEL ATT HOLE CRACK RUNNING FWD .0626 INCH LONG. CRACK LENGTH .0625 INCH. U/D BS 360 FLOORBEAM UPPER CHORD AFT FLANGE AT RBL43 REPAIRED AS PER EO B747-5320-12407 APP D PLAN C FIG 3.

Part: FLOORBEAM — CRACKED (FUSELAGE) · airframe 77,205 hrs · 18,330 cycles

INSPECTION TYPE:C U/D BS 360 FLOORBEAM UPPER CHORD AFT FLANGE AT LBL 47 FOUND 1EA PANEL ATT HOLE CRACK RUNNING AFT .0625 INCH LONG. CRACK LENGTH .0625 INCH. U/D BS 360 FLOORBEAM UPPER CHORD AFT FLANGE AT LBL 47 AREA REPAIRED AS PER RO B747-5320-12407 APP D PLAN C FIG 3.

Part: PANEL — DAMAGED (RT WING) · airframe 77,205 hrs · 18,330 cycles

INSPECTION TYPE:C RIGHT WING I/B LANDING LIGHT I/B PANEL FOUND PUNCH HOLE. CRACK LENGTH .375 INCH DIA. PANEL REPAIRED AS PER RS R57-41-35483 AND ENGINEERING FILE NUMBER 747-57-20091.

Part: WEB — CRACKED (RT WING) · airframe 77,205 hrs · 18,330 cycles

INSPECTION TYPE:C RIGHT WING - L/E D-FAIRING SUPPORT WEB FOUND CRACK AT R2 PDU I/B AREA. CRACK LENGTH 3.5 INCHES. RIGHT WING L/E D-FAIRING SUPPORT WEB REPAIRED AT ILES943 TO ILES955.5 AREA APPROX AS PER SRM 57-20-03 FIG 7.

Part: STIFFENER — CRACKED (NLG WW) · airframe 77,205 hrs · 18,330 cycles

NWW RT SIDE PANEL BS 280-300 WL 170 STIFFENER RADIUS AREA FOUND INTERMITTENT CRACKS, CRACK LENGTH 1/4" - 3/8". STIFFENER REPLACED AND INSTALLED AS PER SRM 51-10-01 PG 9 AND 51-30-02.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · airframe 77,205 hrs · 18,330 cycles

INSPECTION TYPE:C COCKPIT BS 380-390 LBL 58-63 FLOOR SUPPORT -T- ANGLE LWR FACE FOUND CORROSION. CORROSION BLEND OUT 0.035" X 1" X 1" EXCEED SRM LIMIT. COCKPIT BS 340 TO BS 400 LBL 58-63 SUPPORT -T- REPLACED AND INSTALLED AS PER SRM 51-10-01 PG 9 AND 51-30-02.

Part: SEAT TRACK — CORRODED (BS 480-520) · airframe 77,205 hrs · 18,330 cycles

BS 480-520 LBL46 SEAT TRACK O/B FLANGE FOUND CORROSION. CORROSION BLEND OUT 0.55" BY 1/2" BY 1.5" EXCEED SRM LIMIT. BS480-530 LBL46 SEAT TRACK REPLACED AND INSTALLED AS PER SRM 51-10-01 PG 9 AND 51-30-02.

Part: STIFFENER — CRACKED (FUSELAGE) · airframe 77,205 hrs · 18,330 cycles

INSPECTION TYPE:C U/D BS 400 AND BS 410 RBL 78-80 RIGHT CREW DOOR CUTOUT LWR SILL AREA 2EA VERTICAL STIFFENER FOUND CRACK. CRACK LENGTH .25 INCH. STIFFENER REPLACED AS PER SRM 51-10-01 PG 9, 51-30-05 AND INSTALLED AS PER SRM 51-30-02.

Part: STIFFENER — CRACKED (FUSELAGE) · airframe 77,205 hrs · 18,330 cycles

INSPECTION TYPE:C NWW RT SIDE PANEL BS 280-300 WL160 STIFFENER RADIUS AREA FOUND INTERMITTENT CRACKS CRACK LENGTH 1/4" TO 3/8". RT STIFFENER REPLACED AT BS 280-300 WL160 AREA AS PSR SRM 51-10-01 PG 9 AND INSTALLED AS PER SRM 51-30-02.

Part: STRUCTURE — MISREPAIRED (FUSELAGE) · airframe 77,205 hrs · 18,330 cycles

INSPECTION TYPE:C SHORT EDGE MARGIN FOUND AT U/D BS 380 AFT FLANGE LBL 44, 50, 55.5, 61, 66.5 AND 72 AREA (LESS THAN 1.3). U/D BS 380 AFT FLANGE UPPER CHORD AT LBL 44, 50, 55.5, 61, 66.5 AND 72 AREA REPAIRED AS PER EO B747-5320-12407-F APP D PLAN C FIG 3.

Part: FITTING — CRACKED (L3 DOOR) · airframe 77,205 hrs · 18,330 cycles

INSPECTION TYPE:C M/D LT NR 3 DOOR FWD LOWER CORNER REVEAL FITTING FOUND CRACKED AS MARKED CRACK LENGTH 1/2". REVEAL FTG REPLACED AND INSTALLED AS PER SRM 51-10-01 PG 9 AND 51-30-02.

Part: FLOORBEAM — CORRODED (FUSELAGE) · airframe 77,205 hrs · 18,330 cycles

INSPECTION TYPE:C U/D BS 520 LBL 56-74 FLOORBEAM UPPER CHORD FOUND CORRODED. CORROSION BLEND OUT 0.070" X 1.5" X 2" EXCEED SRM LIMIT. U/D BS 520 LEFT O/B MOST TO RBL 56 FLOORBEAM UPPER CHORD REPAIRED AS PER SRM 53-10-07 FIG 13.

Part: SHEAR TIE — CRACKED (FUSELAGE) · airframe 77,205 hrs · 18,330 cycles

INSPECTION TYPE:C CTR TANK LT LBL 83 LWR SHEAR TIE SUSPECT CRACK. CRACK LENGTH .625 INCH. CTR TANK LT LBL 83 LWR SHEAR TIE REPLACED AS PER SRM 51-10-01 PG 9 AND INSTALLED AS PER SRM 51-30-02.

Part: STRINGER SPLICE — CRACKED (FUSELAGE) · airframe 77,205 hrs · 18,330 cycles

INSPECTION TYPE:C AFT CARGO STR SPLICE CRACKED ON BS 1740 S49L. CRACK LENGTH .25 INCH. AFT CARGO COMPT BS 1740 STR 49L SPLICE REPLACED AND INSTALLED AS PER SRM 51-10-01 PG 9 AND 51-30-02.

Part: SUPPORT FITTING — CRACKED (FWD CARGO BAY) · airframe 77,205 hrs · 18,330 cycles

INSPECTION TYPE:C FWD CARGO COMPT RT AFT STOP FITTING LOWER SUPPORT I/B SIDE FOUND CRACKED AT STA 970 TO STA 975 RBL 24 BELOW FLOOR AREA AS MARKED. CRACK LENGTH 6.5 INCH. FWD CARGO COMPT RT AFT STOP FITTING LWR SUPPORT REPLACED AS PER SRM 51-10-01 PG 9 & INSTALLED AS PER SRM 51-30-02.

Part: SHEAR TIE — CRACKED (FUSELAGE) · airframe 77,205 hrs · 18,330 cycles

INSPECTION TYPE:C CTR TANK RT RBL 83 LWR SHEAR TIE SUPPORT CRACK. CRACK LENGTH .875 INCH. CTR TANK RT RBL 83 LWR SHEAR TIE REPLACED AS PER SRM 51-10-01 PG 9 AND INSTALLED AS PER SRM 51-30-02.

Part: SPAR — CRACKED (LT WING) · airframe 77,205 hrs · 18,330 cycles

INSPECTION TYPE:C LT WING FRONT SPAR UPPER CHORD WS 642 AREA FOUND 1EA HOLE CRACK AT WEB RUNNING O/B APPROX .0625 INCH LONG. LT WING FRONT SPAR UPPER CHORD WS 642 WEB REPAIRED AS PER RS R57-21-35488. INSPECT THE FRONT SPAR IN ZONE-A AS PER SB 747-57A2311 R2 TABLE 3 WITH REPEAT INSPECTION INTERVALS OF 1600 FLIGHT CYCLES OR 6200 FLIGHT HOURS WHICHEVER IS EARLIER.

Part: PLATE — CRACKED (LT WING) · airframe 77,205 hrs · 18,330 cycles

INSPECTION TYPE:C LEFT WING SURGE TANK WS 1516 UPPER STR 10 VENT CHANNEL ATTACH PLATE CRACK. CRACK LENGTH .375 INCH. LEFT WING SURGE TANK WS 1516 UPPER STR 10 VENT CHANNEL ATTACH PLATE REPLACED AND INSTALLED AS PER SRM 51-10-01 PG 9 & 51-30-02.

Part: DOOR FRAME — CRACKED (R3 DOOR) · airframe 77,205 hrs · 18,330 cycles

R3 DOOR AFT FRAME UPPER CORNER CRACKED, CRACK LENGTH 1 INCH. R3 DOOR AFT FRAME UPPER CORNER REPAIRED AS PER SRM 52-10-02 FIG 10.

Part: CARGO TRACK — CORRODED (FUSELAGE) · airframe 77,205 hrs · 18,330 cycles

INSPECTION TYPE:C M/D BS 440-460 RBL 88 TIE DOWN TRACK O/B FLANGE FOUND CORROSION. CORROSION BLEND OUT 0.055" X 1" X 1" EXCEED SRM LIMIT. M/D BS 410-460 RBL 88 TRACK REPLACED AND INSTALLED AS PER SRM 51-10-01 PG 9 AND 51-30-02.

Part: CARGO TRACK — CORRODED (BS 420-440) · airframe 77,205 hrs · 18,330 cycles

BS 420-440 RBL88 TIE DOWN TRACK I/B FLANGE FOUND CORROSION. CORROSION BLEND OUT 0.030" BY 1/2" BY 2" EXCEED SRM LIMIT. BS410-460 RBL88 TRACK REPLACED AND INSTALLED AS PER SRM 51-10-01 PG 9 AND 51-30-02.

Part: CARGO TRACK — CORRODED (FUSELAGE) · airframe 77,205 hrs · 18,330 cycles

INSPECTION TYPE:C M/D - BS 440-460 LBL 11 TIE DOWN TRACK I/B FLANGE FOUND CORROSION. CORROSION BLEND OUT 0.057" X .5" X 1.5" EXCEED SRM LIMIT. M/D BS 440-460 LBL 11 TIE DOWN TRACK REPAIRED AS PER SRM 53-10-05 FIG 17.

Part: STRINGER CLIP — CRACKED (FUSELAGE) · airframe 77,205 hrs · 18,330 cycles

INSPECTION TYPE:C AFT CARGO STR CLIP BROKEN ON BS 1720 S40L. CRACK LENGTH .25 INCH AFT CARGO COMPT BS 1720 STR 40L ATT CLIP REPLACED AND INSTALLED AS PER SRM 51-10-01 PG 9 AND 51-30-02.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · airframe 77,205 hrs · 18,330 cycles

INSPECTION TYPE:C M/D BS 240-260 RBL 72 FLOOR SUPPORT CORROSION. CORROSION BLEND OUT 0.028" X .5" X 1" EXCEED SRM 53-10-01 FIG 1 LIMITS. M/D BS 220 TO BS 300 RT FLOOR SUPPORT REPLACED & INSTALLED AS PER SRM 51-10-01 PG 9 & 51-30-02.

Part: FRAME — CRACKED (NR 3 PYLON) · airframe 77,205 hrs · 18,330 cycles

INSPECTION TYPE:C NR 3 PYLON REAR MOUNT BULKHEAD FOUND CRACKS AT BOTH SIDES FWD AND AFT FRAME WEB. CRACK LENGTH 1 INCH TO 3.5 INCH. NR 3 PYLON REAR MOUNT BULKHEAD FWD AND AFT BOTH SIDES FRAME WEB REPLACED AND REPAIRED AS PER RS R54-53-35482 AND ENGINEERING FILE NUMBER 747-54-20054.

Part: STRINGER — CRACKED (FUSELAGE) · airframe 77,205 hrs · 18,330 cycles

INSPECTION TYPE:C FWD CARGO LT SIDEWALL BS 500 STR 38 FOUND CRACKED AT RIVET AREA. CRACK LENGTH .5 INCH. FWD CARGO LT BS 473 TO BS 500 STR 38 REPAIRED AS PER SRM 53-10-03 FIG 3.

Part: ATTACH ANGLE — CRACKED (NR 4 PYLON) · airframe 77,205 hrs · 18,330 cycles

INSPECTION TYPE:C NR 4 PYLON NAC STA 221.9 REAR ENG MOUNT B/H LOWER OF MID SPAR WEB LHS I/B AREA T-ANGLE CRACKED. CRACK LENGTH .5 INCH. NR 4 PYLON NAC STA 221.9 REAR ENG MOUNT B/H LOWER OF MID SPAR WEB ATTACH T-ANGLE REPLACED AND INSTALLED AS PER SRM 51-10-01 PG 9 AND 51-10-02.

Part: BEAM — CORRODED (FWD CARGO BAY) · airframe 77,205 hrs · 18,330 cycles

INSPECTION TYPE:C FWD CARGO DOOR INTERNAL LINER ATTACH BEAM A/NUT AREA FOUND SURFACE CORRODED FS 580 FWD AS MARKED. CORROSION BLEND OUT 0.070" X 1" X 1" EXCEES SRM LIMIT. FWD CARGO DOOR INTERNAL LINER ATTACH BEAM FWD OF BS 580 LOWER AREA REPAIRED AS PER SRM 51-40-02 FIG 1.

Part: FRAME — CRACKED (FUSELAGE) · airframe 77,205 hrs · 18,330 cycles

INSPECTION TYPE:C M/D RIGHT BS434 FRAME S26R AREA FOUND 2EA HOLE CRACKED AT AFT WEB DOUBLER. CRACK LENGTH .125 AND .0625 INCH. M/D RIGHT BS 434 FRAME WEB DOUBLER REPAIRED AT BETWEEN STR 23 TO S30 AREA AS PER SRM 53-10-04 FIG 9.

Part: FITTING — CRACKED (LT WING) · airframe 77,205 hrs · 18,330 cycles

INSPECTION TYPE:C LT WING NR 2 L/E PDU FWD SUPPORT ATT NOSE BEAM UPPER CHORD FOUND CRACK AS MARK, NR 7 VC FLAP I/B. CRACK LENGTH .625 AND 2.5 INCH. LT WING NR 2 L/E PDU FWD SUPPORT ATT NOSE BEAM UPPER CHORD AT BETWEEN AILES 949 - 962 AREA REPAIRED AS PER SRM 57-20-03 FIG 7.

Part: STRINGER — CORRODED (BS 2160-2170) · airframe 77,205 hrs · 18,330 cycles

RT LOWER FUSELAGE EXTERNAL SKIN SURFACE FOUND BILGE UP AT STA 2160 TO STA 2170 STR 45R. BULK CARGO BS 2150 TO BS 2180 S45R STRINGER REPAIRED AS PER SRM 53-10-03 FIG 1.

Part: ATTACH BRACKET — CRACKED (FUSELAGE) · airframe 77,205 hrs · 18,330 cycles

INSPECTION TYPE:C M/D BS 434 FRAME ATT BRACKET AT S26R FWD FOUND CRACKED. CRACK LENGTH .25 INCH. BRACKET REPLACED AS PER SRM 51-10-01 PG 9, 51-30-05 AND INSTALLED AS PER SRM 51-30-02.

Part: STIFFENER — CRACKED (BS 280-300) · airframe 77,205 hrs · 18,330 cycles

NWW TOP PANEL BS280-300 RBL 10 STIFFENER RADIUS AREA FOUND CRACK APP 3/4". NWW TOP PANEL BS280-300 RBL10 STIFFENER REPLACED AS PER SRM 51-10-01 PG9 AND INSTALLED AS PER SRM 51-30-02.

Part: FRAME — CRACKED (BS 2231) · airframe 77,205 hrs · 18,330 cycles

LT BS 2231 FRAME INNER FLANGE BETWEEN S24L AND S25L FOUND 1 HOLE CRACK AT FRAME STRAP CRACK LENGTH 1/16". BS 2231 LT FRAME ATTACH STRAP REPAIRED BETWEEN STR 24L TO 26L AS PER SRM 53-10-04 FIG 15. CONTINUED INSPECTION IS REQUIRED AS PER SRM 53-10-04 FIG 115 TABLE 2 AND SB 747-53A2450.

Part: FRAME — CRACKED (FUSELAGE) · airframe 77,205 hrs · 18,330 cycles

INSPECTION TYPE:C M/D LEFT BS 434 FRAME ABOVE S26L AREA FOUND 1EA HOLE CRACK AT FRAME INNER CHORD. CRACK LENGTH .0625 INCH. FRAME CHORD REPLACED AS PER SRM 51-10-01 PG 9 AND INSTALLED AS PER SRM 51-30-02.

Part: SUPPORT FITTING — CRACKED (AFT CARGO BAY) · airframe 77,205 hrs · 18,330 cycles

INSPECTION TYPE:C AFT CARGO COMPT BS 1910 LBL 46 FIXED END STOP O/B SUPPORT FITTING FOUND CRACKED. CRACK LENGTH .375 INCH. AFT CARGO COMPT BS 1910 LBL 46 FIXED END STOP O/B SUPPORT FITTING REPLACED AND INSTALLED AS PER SRM 51-10-01 PG 9 AND 51-30-02.

Part: WEB — CORRODED (FWD CARGO BAY) · airframe 77,205 hrs · 18,330 cycles

INSPECTION TYPE:C FWD CARGO COMPT TORQUE BOX UPPER ACCESS PANEL UPPER SURFACE FOUND SURFACE CORROSION AT STA 660-680 RBL 50 TO RBL 57. CORROSION BLEND OUT 0.055" X 1" X 4" EXCEED SRM 53-10-01 FIG 1 LIMITS, WEB REPLACED & INSTALLED AS PER SRM 51-10-01 PG 9 & 51-30-02.

Part: STRAP — CRACKED (FUSELAGE) · airframe 77,205 hrs · 18,330 cycles

INSPECTION TYPE:C M/D RIGHT BS 800 FRAME INNER FLANGE BETWEEN S26R-17R FOUND 1EA FASTENER LOCATION CRACKED AT FRAME STRAP. CRACK LENGTH 1.25 INCH. REPAIRED AS PER RS R53-10-35484 AND UPS EO B747-5310-24451-A.

Part: ATTACH BRACKET — CRACKED (FUSELAGE) · airframe 77,205 hrs · 18,330 cycles

INSPECTION TYPE:C M/D BS 434 FRAME ATT BRACKET AT 26L FWD FOUND CRACK. CRACK LENGTH 3/8". M/D BS 434 FRAME ATT BRACKET AT STR 26L AREA REPLACED AS PER SRM 51-10-01 PG 9 AND INSTALLED AS PER SRM 51-30-02.

Part: STIFFENER — CRACKED (NLG WW) · airframe 77,205 hrs · 18,330 cycles

INSPECTION TYPE:C NWW TOP PANEL BS 260-280 BL 0 STIFFENER FOUND CRACK AT PREVIOUS REPAIRED AREA. CRACK LENGTH .25 INCH. NWW TOP PANEL BS 260-280 BL 0 STIFFENER REPLACED AND INSTALLED AS PER SRM 51-10-01 PG 9 AND 51-30-02.

Part: FRAME — CRACKED (FUSELAGE) · airframe 77,205 hrs · 18,330 cycles

INSPECTION TYPE:C M/D LEFT BS 434 FRAME AT S26L FOUND 2EA HOLE CRACKED AT FRAME WEB AND AFT WEB DOUBLER. CRACK LENGTH 0.040 INCH. M/D LEFT BS 434 FRAME WEB & DOUBLER REPAIRED BETWEEN STR 23 TO STR 30 AREA AS PER SRM 53-10-04 FIG 99.

Part: STIFFENER — CRACKED (NLG WW) · airframe 77,205 hrs · 18,330 cycles

INSPECTION TYPE:C NWW TOP PANEL BS 280-300 LBL 10 STIFFENER RADIUS AREA FOUND CRACK APPROX .75 INCH. NWW TOP PANEL BS 280-300 LBL 10 STIFFENER REPLACED AS PER SRM 51-10-01 PG 9 AND INSTALLED AS PER SRM 51-30-02.

Part: CLIP — CRACKED (NLG WW) · airframe 77,205 hrs · 18,330 cycles

INSPECTION TYPE:C N/G WHEEL WELL LT SIDEWALL PANEL VERTICAL BEAM TYPICAL CLIP FOUND CRACK AS MARK AT STA340 WL180 LBL30, CRACK LENGTH 1/4". CLIP REPLACED AT BS340 WL180 LBL30 AREA AS PER SRM 51-10-01 PG 9 AND INSTALLED AS PSR SRM 51-30-02.

Part: CLIP — CRACKED (NLG WW) · airframe 77,205 hrs · 18,330 cycles

INSPECTION TYPE:C N/G WHEEL WELL RT SIDEWALL PANEL VERTICAL BEAM TYPICAL CLIP FOUND CRACK AS MARK AT RBL 30 STA 280 WL 182. CRACK LENGTH .25 INCH. N/G WHEEL WELL RT SIDEWALL PANEL VERT BEAM CLIP AT BS 280 WL 182 REPLACED AND INSTALLED AS PER SRM 51-10-01 PG 9 AND 51-30-02.

Part: BOLT — SHEARED (LT BLG W/W) · airframe 77,205 hrs · 18,330 cycles

INSPECTION TYPE:C LEFT BLG WHEEL WELL LBL 15 SUSPECT 1EA MOUNT BOLT FOUND SHEARED AS MARKED AT STA 1350 KEEL BEAM. BORE HOLE REAMED TO 0.776 INCH. BOLT REPLACED AS PER MM 20-51-01 AND BOLT HOLE INSPECTED AFTER NEW FITTING REPLACED AND INSTALLED AS PER SRM 51-10-01 PG 9 AND 51-30-02.

Part: CLIP — CRACKED (NLG WW) · airframe 77,205 hrs · 18,330 cycles

INSPECTION TYPE:C N/G WHEEL WELL LT SIDEWALL PANEL VERTICAL BEAM TYPICAL CLIP FOUND CRACK AS MARK AT STA 280 WL 163 LBL 30. CRACK LENGTH .25 INCH. N/G WHEEL WELL LT SIDEWALL PANEL VERTICAL BEAM CLIP REPLACED AND INSTALLED AT BS 280 WL 163 LBL 30 AREA AS PER SRM 51-10-01 PG 9 AND 51-30-02.

Part: RIB — CRACKED (RT WING) · airframe 77,205 hrs · 18,330 cycles

INSPECTION TYPE:C RIGHT WING SURGE TANK WS 1516 RIB LOWER CHORD STR 6 AND STR 8 FOUND CRACKED. CRACK LENGTH 0.75 INCH & 1 INCH. RIGHT WING SURGE TANK WS 1516 RIB LOWER CHORD STR 6 TO THE FWD END AREA REPAIRED AS PER SRM 57-10-05 FIG 4.

Part: RIB — CRACKED (LT WING) · airframe 77,205 hrs · 18,330 cycles

INSPECTION TYPE:C LEFT WING - SURGE TANK WS 1516 RIB LWR STR 6 & 9 SUSPECT CRACK. CRACK LENGTH 1.125 INCH. LEFT WING WS 1516 RIB LWR STR -9 AREA REINSPECTED BY NDT, NO CRACK REVEALED AND STR -6 AREA REPAIRED AS PER SRM 57-10-05 FIG 4.

Part: RIB — CRACKED (RT WING) · airframe 77,205 hrs · 18,330 cycles

INSPECTION TYPE:C RIGHT WING SURGE TANK WS 1516 RIB UPPER CHORD STR 8 FOUND CRACKED. CRACK LENGTH 0.625 INCH. RIGHT WING SURGE TANK WS 1516 RIB UPPER CHORD STR 8 AREA REPAIRED AS PER SRM 57-10-05 FIG 3.

Part: THRUST LINK — CRACKED (NR 4 PYLON) · airframe 76,199 hrs · 18,102 cycles

INSPECTION TYPE:AD NR 4 PYLON REAR ENGINE MOUNT THRUST LINK AFT LUG FOUND CRACK INDICATION AT UPPER AND LOWER SURFACE APPROX 100 PERCENT FSH. NR 4 ENG MOUNT THRUST LINK REPLACED AS PER AMM 71-21-03.

Part: THRUST LINK — CRACKED (NR 2 PYLON) · airframe 76,199 hrs · 18,102 cycles

INSPECTION TYPE:AD NR 2 ENG REF TAR FORM S/N: 115643 - UPS REQUEST REPLACEMENT OF THRUST LINK. NR 2 ENG THRUST LINK REPLACED AND BOTH ATTACH BOLTS REPLACED AS PER AMM 71-21-03.

Part: THRUST LINK — CRACKED (NR 1 PYLON) · airframe 76,199 hrs · 18,102 cycles

INSPECTION TYPE:AD CRACK INDICATION REVEALED ON NR 1 PYLON THRUST LINK FWD LUG LOWER SURFACE BY APPROX 80 PERCENT FSH. NR 1 PYLON THRUST LINK REPLACED AND FWD AND AFT MOUNT BOLTS REPLACED AS PER AMM 71-21-03.

Part: THRUST LINK — CRACKED (NR 3 PYLON) · airframe 76,199 hrs · 18,102 cycles

INSPECTION TYPE:AD CRACK INDICATION REVEALED ON NR 3 PYLON THRUST LINK AFT LUG LOWER SURFACE BY APPROX 90 PERCENT FSH. NR 3 ENG PYLON THRUST LINK REPLACED AND AFT MOUNTING BOLT REPLACED AS PER AMM 71-21-03.

Part: THRUST LINK — CRACKED (NR 1 PYLON) · airframe 76,199 hrs · 18,102 cycles

INSPECTION TYPE:AD CRACK INDICATION REVEALED NR 1 PYLON THRUST LINK AFT LUG LOWER SURFACE BY APPROX 90 PERCENT FSH. NR 1 PYLON THRUST LINK REPLACED AND FWD AND AFT MOUNT BOLTS REPLACED AS PER AMM 71-21-03.

Part: THRUST LINK — CRACKED (NR 3 PYLON) · airframe 76,199 hrs · 18,102 cycles

INSPECTION TYPE:AD CRACK INDICATION REVEALED ON NR 3 PYLON THRUST LINK FWD LUG LOWER SURFACE BY APPROX 60 PERCENT FSH. NR 3 ENG THRUST LINK REPLACED AND AFT MOUNT BOLT REPLACED AS PER AMM 71-21-03.

Part: ENGINE — FAILED (NR 3)

NR 3 ENGINE FAILED. REPLACED NR 3 ENGINE IAW TASK CARD 5000, 5016. OPS CHECK GOOD.

Part: SPLICE — CRACKED (NLG WW) · airframe 73,613 hrs · 17,591 cycles

INSPECTION TYPE: C, NWW BS 400 STR R44 RIGHT AFT CORNER INTERNAL CIRCUMFERENTIAL SKIN SPLICE FOUND CRACK APPROX .25 INCH LONG RUNNING AFT. THE CRACKED SPLICE REMOVED FOR STOP HOLE DRILLED. THE STOP CONFIRMED NIL CRACK BEYOND THE STOP HOLE. THE AREA REPAIRED PER SRM 53-30-03 FIG 35.

Part: FRAME — CRACKED (ZONE 222) · airframe 73,613 hrs · 17,591 cycles

INSPECTION TYPE: C, U/D - BS 360 RT FRAME WEB FOUND CRACKED AT STR-2A. THE CRACK WAS PREVIOUS REPAIRED PER SRM 54-40-02 FIG 1. THE CRACK CONFIRMED NIL ADDITIONAL CRACK BEYOND THE FASTENER HOLES.

Part: SEAT TRACK — CORRODED (FUSELAGE) · airframe 73,613 hrs · 17,591 cycles

INSPECTION TYPE: C, U/D - BS 480-520 RBL 62 SEAT TRACK CORRODED. CORROSION REMOVED IAW SRM 51-10-01. CORROSION BLEND OUT 0.050 X 1 X 8 INCH. CORROSION BLEND OUT EXCEED SRM 53-10-01 FIG 1 LIMITS. REPAIR PER SRM 53-10-05 FIG 1A. CIC APPLIED IAW UPS EO M-5100-2780-E.

Part: SEAT TRACK — CORRODED (FUSELAGE) · airframe 73,613 hrs · 17,591 cycles

INSPECTION TYPE:C U/D - BS 480-520 RBL 44 SEAT TRACK CORRODED. CORROSION REMOVED IAW SRM 51-10-01. CORROSION BLEND OUT 0.040 X 1 X 10 INCH EXCEED SRM 53-10-01 FIG 1 LIMITS. REPAIR PER SRM 53-10-05 FIG 1A. CIC APPLIED IAW EO M-5100-2780-E.

Part: FRAME — CRACKED (FUSELAGE) · airframe 73,613 hrs · 17,591 cycles

INSPECTION TYPE: C, U/D-BS 500 RIGHT FRAME WEB DOUBLER (AFT FACE) FOUND CRACKED. STR-R11 BS 500 RIGHT FRAME AT STR 11 CRACKED REPAIRED PER HX RS R53-10-35214, ALL CRACK STOPPED AT THE STOP HOLES, CONFIRMED BY NDT.

Part: SUPPORT FITTING — CRACKED (FUSELAGE) · airframe 73,613 hrs · 17,591 cycles

INSPECTION TYPE: C, U/D- BS 420 RIGHT FRAME STR 6 STOP SUPPORT FITTING FOUND CRACKED AS MARKED. STOP FITTING REPLACED AS PER SRM 51-10-01 PG 8.

Part: FRAME — CRACKED (FUSELAGE) · airframe 73,613 hrs · 17,591 cycles

INSPECTION TYPE: C, U/D - BS 460 LT FRAME O/B CHORD FOUND CRACKED BETWEEN STR-12A & STR-13. BS 460 LEFT O/B CHORD REPLACED PER SRM 51-10-01.

Part: SEAT TRACK — CRACKED (FUSELAGE) · airframe 73,613 hrs · 17,591 cycles

INSPECTION TYPE: C, U/D - BS 498 RBL 44 SEAT TRACK CRACKED. CRACKED SEAT TRACK REPAIRED PER SRM 53-10-05 FROM BS 480-520.

Part: FRAME — CRACKED (FUSELAGE) · airframe 73,613 hrs · 17,591 cycles

INSPECTION TYPE:C U/D- BS 360 LEFT FRAME WEB DOUBLER FOUND CRACKED AT STR L10A (AFT FACE). U/D BS 360 LEFT FRAME WEB DOUBLER REPLACE PER HX NRC 5613 FOR THE SUBJECT FRAME WEB REPLACEMENT DETAIL. REF HX RS R53-15-35211 AND UPS EO B747-5310-21306-A.

Part: FITTING — CORRODED (RT WING) · airframe 73,613 hrs · 17,591 cycles

INSPECTION TYPE:C, RT BS 1241 WING REAR SPAR UPPER SPLICE PLATE AREA HOLE NR 5 FOUND CORROSION APPROX 0.040 INCH AT UPPER SPLICE FITTING. HOLE CRACKS REMOVED AND BUSHING FABRICATED AND INSTALLED AS PER SOPM 20-50-03 AND WORK PROCESS CARD UW656931.

Part: STRINGER — CRACKED (ZONE 224) · airframe 73,613 hrs · 17,591 cycles

INSPECTION TYPE: C, U/D - BS 440-460 RIGHT STR-12 FWD END FOUND CRACKED & DEFORMED. CRACKED STRINGER REPLACED AT BS 440-460 RIGHT STR 12 PER SRM 51-10-01. P/N BAC1517-1551-2024T4.

Part: FLOORBEAM — CRACKED (FUSELAGE) · airframe 73,613 hrs · 17,591 cycles

INSPECTION TYPE:C, U/D BS 330 RBL 61 FLOORBEAM UPPER CHORD FOUND CRACKED AS MARKED. U/D - BS 330 RBL 58 TO MOST O/B FLOORBEAM UPPER CHORD REPAIRED AS PER SRM 51-40-04 FIG 2.

Part: SPLICE — CRACKED (ZONE 211) · airframe 73,613 hrs · 17,591 cycles

INSPECTION TYPE:C M/D - BS 400, STR 23-24L, FRAME I/B CHORD O/B FACE ATT SPLICE FOUND CRACK. BS 400 STR 23-24L FRAME SPLICE REPLACED PER SRM 51-10-01 PG 8.

Part: DOUBLER — CRACKED (FRAME) · airframe 73,613 hrs · 17,591 cycles

INSPECTION TYPE: C, M/D- BS 440 BELOW STR 13L FRAME ATT DOUBLER FOUND CRACKED. BS 440 FRAME DOUBLER REPLACED PER HX RS R53-12-35212 FOR DETAIL AND UPS EO B747-5310-21298-A.

Part: FRAME — CRACKED (ZONE 211) · airframe 73,613 hrs · 17,591 cycles

INSPECTION TYPE: C, M/D - BS 460 BTN STR 13L AND 14L FRAME WEB FOUND CRACKED. CRACKED FRAME WEB REPLACED PER SRM 51-10-01.

Part: FRAME — CRACKED (FUSELAGE) · airframe 73,613 hrs · 17,591 cycles

INSPECTION TYPE: C, M/D - BS 400, S23-24R FRAME I/B CHORD O/B FACE ATT SPLICE FOUND CRACK. FRAME SPLICE REPLACED PER SRM 51-10-01.

Part: WEB — CRACKED (FUSELAGE) · airframe 73,613 hrs · 17,591 cycles

INSPECTION TYPE: C, M/D- BS 440 BETWEEN STR 13AL AND 14L FRAME WEB FOUND CRACKED. CRACKED FRAME WEB REPLACED PER SRM 51-10-01.

Part: SKIN — CRACKED (RT WING) · airframe 73,613 hrs · 17,591 cycles

INSPECTION TYPE:C, RT WING - CRACK FOUND ON RT WING UPPER SKIN AT BS 1241 UPPER SPLICE PLATE AREA AT HOLE NR 11 BY APPROX 0.040 INCH LONG RUNNING FWD. HOLE CRACKS REMOVED AND BUSHING FABRICATED AND INSTALLED AS PER SOPM 20-50-03 AND WORK PROCESS CARD UW653051.

Part: LONGERON — CRACKED (FUSELAGE) · airframe 73,613 hrs · 17,591 cycles

INSPECTION TYPE: C, MAIN E/E COMPT LOWER FUSELAGE INTERIOR STRINGER FOUND CRACKED AT STA 440 TO STA 460 STR 37L. STA 440 TO STA 460 STR 37L REPAIRED AS PER SRM 53-10-03 FIG 3.

Part: SPAR — CRACKED (LT WING) · airframe 73,613 hrs · 17,591 cycles

INSPECTION TYPE: C, LT WING MID SPAR UPPER CHORD FASTENER (1EA) EDGE FOUND CRACK BETWEEN WS 382 TO WS 411. LEFT WING - MID SPAR UPPER CHORD REPAIRED AS PER SRM 57-10-06 FIG 5, JUST AT WS 382-411.

Part: SPAR — CRACKED (RT WING) · airframe 73,613 hrs · 17,591 cycles

INSPECTION TYPE: C, RIGHT WING - MID SPAR UPPER CHORD FASTENER (1EA) EDGE FOUND CRACK BETWEEN WS 382 TO WS 411. RIGHT WING - MID SPAR UPPER CHORD REPAIRED AS PER SRM 57-10-06 FIG 5, JUST AT WS 382-411.

Part: SHEAR ANGLE — CRACKED (FUSELAGE) · airframe 73,613 hrs · 17,591 cycles

INSPECTION TYPE: C, M/D - BS 440, APPROX STR 16L, FRAME ATT SHEAR ANGLE FOUND CRACK. CRACKED SHEAR ANGLE REPLACED PER SRM 51-10-01.

Part: FRAME — CRACKED (FUSELAGE) · airframe 73,613 hrs · 17,591 cycles

INSPECTION TYPE: C, M/D- BS 440, BELOW STR 31L, FRAME WEB FOUND CRACK. BS 440 STR 13L FRAME WEB SECTIONAL REPLACED PER HX RS R53-12-35212 FOR DETAIL AND UPS EO B747-5310-21298-A.

Part: FRAME — CRACKED (FUSELAGE) · airframe 73,613 hrs · 17,591 cycles

INSPECTION TYPE: C, M/D- LEFT BS 360 FRAME & DOUBLER S24AL STR CUTOUT CRACKED. M/D- LEFT BS 360 FRAME & DOUBLER REPAIRED AS PER HX RS R53-12-35213 AND UPS EO B747-5310-21311-A.

Part: SPAR — CRACKED (RT WING) · airframe 73,613 hrs · 17,591 cycles

INSPECTION TYPE:C, RIGHT WING - MID SPAR UPPER CHORD FASTENER 2EA EDGE FOUND CRACK BETWEEN WS 440 - WS 460. RIGHT WING - MID SPAR UPPER CHORD REPAIRED AS PER SRM 57-10-06 FIG 5, JUST AT WS 440 - 460.

Part: RIB — CRACKED (LT WING) · airframe 73,613 hrs · 17,591 cycles

L/E PNL SUPPORT RIB FOUND CRACKED AT WS 1420 JUST O/B OF NR 1 L/E FLAP PDU. L/E PNL SUPPORT RIB REPAIRED AS PER HX RS NR R57-41-35209 JUST AT WS 1420 O/B OF NR 1 L/E FLAP PDU. REFER UPS EO NR B747-5740-21328-A

Part: DOUBLER — CRACKED (FUSELAGE FRAME) · airframe 73,613 hrs · 17,591 cycles

INSPECTION TYPE: C, M/D- BS 460, BETWEEN STR 13-14L, FRAME DOUBLER FOUND CRACK. FRAME DOUBLER REPLACED PER SRM 51-10-01 PG 8.

Part: DOUBLER — CRACKED (FRAME) · airframe 73,613 hrs · 17,591 cycles

INSPECTION TYPE:C M/D- LEFT BS 400 FRAME S15L DOUBLER CRACKED AT STR CUTOUT. DOUBLER REPAIRED AS PER HX RS R53-10-35210 AND UPS EO B747-5310-21303-A.

Part: FLOORBEAM — CRACKED (ZONE 222) · airframe 73,613 hrs · 17,591 cycles

INSPECTION TYPE: C, U/D BS 330, BET STR 13-14R, APPROX RBL 70-75 FLOORBEAM WEB FOUND CRACK. U/D FLOORBEAM WEB REPAIRED AS PER SRM 53-10-07 FIG 11.

Part: SUPPORT — CORRODED (KEELBEAM) · airframe 73,613 hrs · 17,591 cycles

INSPECTION TYPE: C, FX - KEEL BEAM PANEL SUPPORT LOWER SURFACE FOUND SURFACE CORROSION AT STA 1480 LBL 16 TO RBL 16. CORROSION REMOVED IAW SRM 51-10-01. CORROSION BLEND OUT 0.040 X 1 X 3 INCH. CORROSION BLEND OUT EXCEED SRM 53-10-01 FIG 1 LIMITS. PANEL SUPPORT REPLACED AS PER SRM 51-10-01 FIG 8. CIC APPLIED IAW EO NR M-5100-2780-E.

Part: FLOORBEAM — CRACKED (FUSELAGE) · airframe 73,613 hrs · 17,591 cycles

INSPECTION TYPE:C, LT BS 340 WL 280-320 UPPER DECK FLOORBEAM ONE EA FASTENER HOLE CRACK REVEALED AT FLOORBEAM UPPER CHORD AND STRAP LAYER. FLOORBEAM REPAIRED AS PER SRM 53-10-07 FIG 23 PLUS SB 747-53A2459 REV 1 PART 3 MODIFICATION.

Part: FLOORBEAM — CRACKED (FUSELAGE) · airframe 73,613 hrs · 17,591 cycles

INSPECTION TYPE:C RIGHT BS 360 UPPER DECK FLOORBEAM ONE FASTENER HOLE CRACK FOUND AT FRAME WEB BS 360, WL 280 TO 320. BS 360 RT FRAME WEB CRACKED AREA REPAIRED PER HX RS R53-15-35211 BY CRACKED FRAME WEB DOUBLER REPLACED & FRAME WEB REINFORCEMENT PER THE HX RS R53-15-35211 AND UPS EO B747-5310-21306-A.

Part: FLOORBEAM — CRACKED (FUSELAGE) · airframe 73,613 hrs · 17,591 cycles

INSPECTION TYPE: C, LT BS 360 UPPER DECK FLOORBEAM ONE EA FASTENER HOLE CRACK REVEALED AT FLOORBEAM WEB AND FRAME WEB DOUBLER LAYER FOR DETAILS BS 360, WL 280 TO 320. LEFT BS 360 FLOORBEAM WEB & FRAME WEB CRACK REPAIRED AND FLOORBEAM WEB SECTIONAL REPLACED PER SRM 53-10-07 FIG 11 & HX RS R53-15-35211 & FRAME WEB REPLACED PER SRM 51-10-01 & HX RS R53-15-35211 AND UPS EO B747-5310-21306-A.

Part: FLOORBEAM — CRACKED (FUSELAGE) · airframe 73,613 hrs · 17,591 cycles

INSPECTION TYPE: C, RIGHT BS 340 UPPER DECK FLOORBEAM, ONE HOLE CRACK FOUND AT FRAME WEB. ONE HOLE CRACK FOUND AT FLOORBEAM WEB BS 340 WL 280 TO 320. RIGHT BS 340 UPPER DECK FLOORBEAM WEB & FRAME WEB REPAIRED AS PER HX RS R53-15-35211 AND UPS EO B747-5310-21306-A.

Part: PANEL — CRACKED (LT WING) · airframe 73,613 hrs · 17,591 cycles

INSPECTION TYPE:C, LT WLG W/W FWD CANTED BULKHEAD LOWER AREA CRACKED AT STA 1241, LBL 94 AS MARKED (CLOSEOUT PANEL). CANTED BULKHEAD LT CLOSEOUT PANEL REPLACED AS PER UPS EO B747-5310-2758-E APPENDIX E.

Part: SKIN — CRACKED (TE FLAP) · airframe 70,081 hrs · 16,930 cycles

INSPECTION TYPE: C, FX FLAP JOINT OUTER SKIN AT BS 1688 S46R 1EA TOP ROW FASTENER HOLE (JUST AFT OF EXISTING REPAIR PATCH) FOUND CRACKED APPROX 0.040 INCH RUNNING AFT. REF NRC 7496 & 7484 FOR SKIN REPAIRED AS PER SRM 53-30-03 FIG 17.

Part: SKIN — CRACKED (MLG DOOR) · airframe 70,081 hrs · 16,930 cycles

INSPECTION TYPE: C, LT BODY MLG WW - BODY MLG I/B STRUT DOOR EXTERNAL SURFACE SKIN FOUND CRACKED AT REAR UPPER CORNER. SKIN REPAIRED AS PER SRM 52-80-02 FIG 1.

Part: FITTING — CRACKED (RT WING) · airframe 70,081 hrs · 16,930 cycles

INSPECTION TYPE: C, RT WING REAR SPAR BS 1241 KICK FTG HOLE-D FOUND CRACK AT KICK FTG APPROX 0.030 INCH RUNNING I/B. HOLE-D REPAIRED AS PER RS R57-12-35029 AND EO B747-5710-18862-A.

Part: SKIN — CRACKED (FUSELAGE) · airframe 70,081 hrs · 16,930 cycles

INSPECTION TYPE: C, M/D - L3 DOOR CUTOUT AFT UPPER CORNER FOUND CRACK AT FX SKIN AND TRIPLER RUNNING FROM EDGE TO FASTENER HOLE. M/D - L3 DOOR CUTOUT AFT UPPER CORNER SKIN AND TRIPLER REPAIRED AS PER HX RS R-53-41-35034 AND UPS EO B747-5310-18865-A.

Part: SKIN — CRACKED (FUSELAGE) · airframe 70,081 hrs · 16,930 cycles

INSPECTION TYPE: C, DURING RAP ACCOMPLISH, ITEM N521UP-46-26 CLASSIFY AS CATEGORY -D- REPAIR. SKIN REPAIRED AT BS 2030-2045 STR 44R - 45R AREA AS PER SRM 53-30-03 FIG 1.

Part: STRINGER CLIP — CORRODED (FUSELAGE) · airframe 70,081 hrs · 16,930 cycles

INSPECTION TYPE: C, AFT CARGO COMPT - BELOW FLOOR STRINGER ATT TIE CLIP FOUND CORROSION AT STA 1696 TO STA 1700 STR 48R. DUE TO COR TIE CLIP OUT OF SRM 53-10-01 FIG 1 LIMIT NEED TO BE CHANGED BLENDED AERA .75 X .5 INCH AND MAT'L REMAIN 0.020 INCH. AFT CARGO COMPT STA 1696 TO STA 1700 STRINGER S48R ATT TIE CLIP REPLACED AS PER SRM 51-10-01 PG 8.

Part: STRINGER — CRACKED (FUSELAGE) · airframe 70,081 hrs · 16,930 cycles

INSPECTION TYPE: C, M/D - BS 2180-2200 STR 12L STRINGER CRACKED. M/D BS 2180-2200 STR 12L REPAIRED AS PER HX RS 53-61-35030 & UPS ENG 'R FILE 747-53-20140.

Part: STIFFENER — CORRODED (KEELBEAM) · airframe 70,081 hrs · 16,930 cycles

INSPECTION TYPE: C, FX KEELBEAM BOX RT STIFFENER FOUND CORROSION CRACKED AT STA 1460 RBL 6. FX KEEL BEAM BOX AT RBL 6 STA 1460 STIFFENER REPLACED AS PER SRM 51-10-01 PG 8. DUE TO CORROSION CRACK TO STIFFENER OUT OF SRM 53-10-01 FIG LIMITED NEED TO BE CHANGED. DAMAGED AREA .75 X 1.5 X 0.032 INCH MAT'L REMAINED.

Part: SHEAR TIE — CORRODED (FUSELAGE) · airframe 70,081 hrs · 16,930 cycles

INSPECTION TYPE: C, AFT CARGO STA 1840 STR 45R TO 46R SHEAR TIE CORROSION REVEALED. CORROSION BLEND OUT 0.040 X 1 X 2 INCH. SHEAR TIE BRACKET REPLACED AS PER SRM 51-10-01 PG 8.

Part: LONGERON — CRACKED (FUSELAGE) · airframe 70,081 hrs · 16,930 cycles

INSPECTION TYPE: C, M/D- BS 1940-1960 STRINGER 1R STRINGER END CRACKED. STRINGER REPAIRED AS PER SRM 53-10-03 FIG 6.

Part: STRINGER — CRACKED (FUSELAGE) · airframe 70,081 hrs · 16,930 cycles

INSPECTION TYPE: C, AREA AFT OF BULK CARGO STA 2180-2200 S50L STRINGER END CORROSION CRACK FOUND. AFT OF BULK CARGO BS 2180-2200 S50L STRINGER REPAIRED AS PER SRM 53-10-03 FIG 1.

Part: REVEAL — CRACKED (DOOR FRAME) · airframe 70,081 hrs · 16,930 cycles

INSPECTION TYPE: C, M/D - R5 DOOR FWD CUTOUT REVEAL CRACK AT S-16 AS MARKED. REPAIRED AS PER SRM 53-10-04 FIG 91 AT M/D R5 DOOR FWD CUT REVEAL AT S-16.

Part: FLOORBEAM — CORRODED (CARGO BAY) · airframe 70,081 hrs · 16,930 cycles

INSPECTION TYPE: C, BULK CARGO STA 2040 LBL 60 - RBL 60 FLOORBEAM STRAP FOUND CORRODED AT UPPER AND LOWER SURFACE. DEFECT TRANSVERSE FLOORBEAM REMOVED AND SERVICABLE FLOORBEAM REPLACED PER SRM 51-10-01 PG 8, CORROSION BLEND OUT (0.020 INCH X 1 X 4 INCH).

Part: STRINGER — CORRODED (CARGO BAY) · airframe 70,081 hrs · 16,930 cycles

INSPECTION TYPE: C, FWD CARGO COMPT BELOW FLOOR BIGLE SURFACE STRINGER END TO SKIN SURFACE FOUND CORROSION CRACK AT STA 820 TO STA 823 STG 47L. CORROSION BLEND OUT 0.060 X 0.5 X 0.5 INCH BS 820-830 STRINGER S47L REPAIRED AS PER SRM 53-10-03 FIG 1.

Part: STRINGER — CRACKED (FUSELAGE) · airframe 70,081 hrs · 16,930 cycles

INSPECTION TYPE: C, M/D CROWN - S4R STR END CORROSION CRACKED AT BS 1238. M/D STRINGER BN BS 1210 AND BS 1240 S4R REPAIRED AS PER SRM 53-10-03 FIG 5 DUE TO COR CRACK LENGTH .5 INCH FROM EDGE TO 2ND FASTENER HOLE AREA EXCEEDED SRM 53-10-01 FIG 1 LIMITATION.

Part: STRINGER — CRACKED (FUSELAGE) · airframe 70,081 hrs · 16,930 cycles

INSPECTION TYPE: C, M/D - BS 1720- 1740 STR 9R STRINGER END CRACKED. M/D - BS 1720-1740 STR 9R STRINGER END REPAIRED AS PER HX RS R-53-61-35035 AND ENG'R FILE NUMBER 747-53-20146.

Part: LONGERON — CORRODED (AFT CARGO) · airframe 70,081 hrs · 16,930 cycles

AFT CARGO STA 1696-1700 STR 48R CORROSION REVEALED. TIE CLIP AND HI-LOCKS REINSTALLED IAW SRM 51-30-02. CORROSION BLEND OUT (0.080 INCH X 1 INCH X 2 INCHES) AFT CARGO - BS 1690 - 1710 STR 48R REPAIRED IAW SRM 53-10-03 FIG 7.

Part: SHEAR TIE — CRACKED (FUSELAGE) · airframe 70,081 hrs · 16,930 cycles

INSPECTION TYPE: C, M/D - BS 1020 FRAME SHEAR TIE FOUND CRACKED BETWEEN S-8R AND S-9R. M/D BS 1020 FRAME SHEAR TIE 1 EA REPLACE AS PER SRM 51-10-01 BETWEEN S-8R AND S-9R.

Part: WEB — CRACKED (FUSELAGE) · airframe 70,081 hrs · 16,930 cycles

INSPECTION TYPE: C, M/D - STA 560 TO 580 STR 23R ATT WEB FOUND CORROSION CRACK. SUPPORT WEB REPLACED AS PER SRM 51-10-01.

Part: BUSHING — CORRODED (KEELBEAM) · airframe 70,081 hrs · 16,930 cycles

INSPECTION TYPE: C, A REPAIR BUSHING IS INSTALLED ON THE KEEL BEAM INTERIOR BATH TUB FITTING AT LT FWD BOLT HOLE & THE WALL THICKNESS OF THE BUSHING IS ONLY 0.020 INCH. REPAIR BUSHING REPLACED AS PER RS R53-49-35025 AND ENG'R/FILE NR 747 -53-20139.

Part: FITTING — CORRODED (CRACKED) · airframe 70,081 hrs · 16,930 cycles

INSPECTION TYPE: C, LT BS 1241 WING REAR SPAR LOWER SPLICE PLATE ONE EACH BOLT HOLE -K- LOCATION FOUND CRACK AND CORROSION AT 3 O'CLOCK POSITION 0.040 INCH DEPTH APPROX AND 5 O'CLOCK POSITION 0.040 INCH APPROX RESPECTIVELY. REPAIRED AS PER R57-12-35029 AND EO B747-5710-18862-A.

Part: LONGERON — CORRODED (FUSELAGE) · airframe 70,081 hrs · 16,930 cycles

INSPECTION TYPE:C AFT CARGO BS 1745 S49R STRINGER SPLICE FITTING CORROSION CRACK. CORROSION BLEND OUT 0.063 X 1.5 X 4 INCH. STRINGER SPLICE REPLACED AS PER SRM 51-10-01 PG 8.

Part: STRINGER — CRACKED (FUSELAGE) · airframe 70,081 hrs · 16,930 cycles

INSPECTION TYPE: C, M/D - BS 2340 - 2360 STR 12R STRINGER END CRACKED. CRACKED STRINGER TRIMMED OUT AS PER SRM 51-10-01 AND PERFORM STRINGER REPAIRED AS PER SRM 53-10-03 FIG 4.

Part: STRINGER — CRACKED (FUSELAGE) · airframe 70,081 hrs · 16,930 cycles

INSPECTION TYPE: C, M/D - BS 1958 S13R, STRINGER END FOUND CRACK. M/D BS 1958 S13R STRINGER END CRACKED REPAIRED AS PER SRM 53-10-03 FIG 12.

Part: STRINGER — CRACKED (FUSELAGE) · airframe 70,081 hrs · 16,930 cycles

BS 1940 - 1960 STR 2R STRINGER END CRACKED. M/D BS 1940 - 1960 STR 2R STRINGER END REPAIRED AS PER HX RS R-53-61-35035 AND ENG'R 747-53-20146.

Part: STRINGER — CORRODED (FUSELAGE) · airframe 70,081 hrs · 16,930 cycles

INSPECTION TYPE: C, M/D CROWN - S-4R STR CORRODED AT BS 1338. CORROSION BLEND OUT (0.033 X .5 X 2 INCH) STRINGER REPAIRED AS PER SRM 53-10-03 FIG 2.

Part: STRINGER — CRACKED (FUSELAGE) · airframe 70,081 hrs · 16,930 cycles

INSPECTION TYPE: C, M/D- BS 1488 S10R STRINGER END FOUND CRACKED AS MARKED. M/D - BS 1488 S10R STRINGER END REPAIRED AS PER HX RS R53-61-35035 AND ENG'R FILE NUMBER 747-53-20146.

Part: STRINGER — CRACKED (FUSELAGE) · airframe 70,081 hrs · 16,930 cycles

INSPECTION TYPE: C, BULK CARGO STA 1960 S47R STRINGER END CORROSION CRACKED. STRINGER REPAIRED AT BS 1960 - 1990 STR 47R AREA AS PER SRM 53-10-03 FIG 1 DUE TO CORROSION CRACK .3125 INCH LENGTH OUT OF SRM FIG 1 LIMITATION.

Part: SHEAR TIE — CRACKED (FUSELAGE) · airframe 70,081 hrs · 16,930 cycles

INSPECTION TYPE: C, M/D - BS 1020 FRAME SHEAR TIE FOUND CRACKED BETWEEN S-9R AND S-11R. M/D BS 1020 S9R-S11R FRAME SHEAR TIE (2EA) REPLACED AS PER SRM 51-10-01 PG 8.

Part: STRINGER — CRACKED (FUSELAGE) · airframe 70,081 hrs · 16,930 cycles

INSPECTION TYPE: C, M/D - BS 1940 - 1960 STR 8R STRINGER END CRACKED. M/D BS 1940-1960 STR 8R STRINGER REPLACED AS PER SRM 53-10-03 FIG 12.

Part: STRINGER — CORRODED (FUSELAGE) · airframe 70,081 hrs · 16,930 cycles

INSPECTION TYPE: C, M/D CROWN - S4R STRINGER CORRODED FROM BS 1311 TO 1319. CORROSION BLEND OUT 0.030 X .5 X 2 INCH EXCEED SRM LIMIT. STRINGER REPAIRED AS PER SRM 53-10-03 FIG 2.

Part: FLOOR SUPPORT — CORRODED (CARGO BAY) · airframe 70,081 hrs · 16,930 cycles

INSPECTION TYPE: C, BULK CARGO STA 1920-1980 LBL 45 FLOOR SUPPORT UPPER AND LWR SURFACE CORRODED. BULK CARGO STA 1920-1950 LBL 45 FLOOR SUPPORT REPAIRED AS PER SRM 53-10-07 FIG 20 DUE TO BLEND OUT (1.25 INCH X 3 INCH X 0.019 INCH) EXCEEDED SRM 53-10-01 FIG 1 LIMITATION. BS 1950 TO BS 1980 LBL 45 FLOOR SUPPORT CORROSION REMOVED WITHIN SRM 53-10-01 FIG 1 LIMITATION.

Part: FLOOR SUPPORT — CORRODED (CARGO BAY) · airframe 70,081 hrs · 16,930 cycles

BULK CARGO STA 1920-1940 LBL 30 FLOOR SUPPORT STRUCTURE UPPER AND LOWER SURFACE FOUND CORRODED. BULK CARGO STA 1920-1970 LBL 30 INCH FLOOR SUPPORT REPAIRED AS PER SRM 53-10-07 FIG 20. CORROSION BLEND OUT (0.025 INCH X .875 INCH X 6 INCH).

Part: FLOOR SUPPORT — CORRODED (CARGO BAY) · airframe 70,081 hrs · 16,930 cycles

INSPECTION TYPE: C, BULK CARGO STA 1920-2040 RBL 22 FLOOR SUPPORT UPPER AND LWR SURFACE FOUND CORRODED. BULK CARGO STA 1920 TO 1990 RBL 22 FLOOR SUPPORT REPAIRED AS PER SRM 53-10-07 FIG 20 DUE TO COROSION BLEND AREA (1 INCH X 6 INCH X 0.026 INCH) OUT OF SRM 53-10-01 FIG 1 LIMITATION & AREA BS 1990 TO 2040 R22 FLOOR SUPPORT AREA CORROSION REMOVED & REPROTECTED AS PER SRM 51-10-01 & 51-10-02 WITHIN SRM 53-10-01 FIG 1 LIMITATION.

Part: FLOOR SUPPORT — CORRODED (CARGO BAY) · airframe 70,081 hrs · 16,930 cycles

INSPECTION TYPE: C, BULK CARGO STA 1920-1980 LBL 8 FLOOR SUPPORT STRUCTURE UPPER AND LOWER SURFACE FOUND CORRODED. CORROSION REMOVED AND REPROTECTED AS PER SRM 51-10-01& 51-10-02 & FLOOR SUPPORT REPAIRED AT BS 1920 TO 1950 LBL 8 AS PER SRM 53-10-07 FIG 20. CORROSION BLEND OUT (0.020 INCH X 1 INCH X 8 FT).

Part: FLOOR SUPPORT — CORRODED (CARGO BAY) · airframe 70,081 hrs · 16,930 cycles

INSPECTION TYPE: C, BULK CARGO STA 1920-1980 RBL 15 FLOOR SUPPORT UPPER AND LOWER SURFACE CORROSION FOUND. BULK CARGO STA 1920-1950 RBL 15 FLOOR SUPPORT REPAIRED AS PER SRM 53-10-07 FIG 20 & CORROSION REMOVED & REPROTECTED AT BS 1950-1980 AREA AS PER SRM 51-10-01 & 51-10-02 CORROSION BLEND OUT (0.020 INCH X 1.5 INCH X 7 INCH).

Part: FLOOR SUPPORT — CORRODED (CARGO BAY) · airframe 70,081 hrs · 16,930 cycles

BULK CARGO STA 1920-1940 LBL 15 FLOOR SUPPORT STRUCTURE UPPER AND LOWER SURFACE CORRODED. BULK CARGO STA 1920-1940 LBL L5 FLOOR SUPPORT REPAIRED AS PER SRM 53-10-07 FIG 20. CORROSION BLEND OUT (0.020 INCH X 1.25 INCH X 6 INCH).

Part: REVEAL — CRACKED (L5 DOOR) · airframe 70,081 hrs · 16,930 cycles

INSPECTION TYPE:C M/D - L5 DOOR FUSELAGE FWD CUTOUT REVEAL FOUND CRACKED AT BS 2232 BETWEEN 16L - 17L. M/D L5 DOOR FWD CUTOUT REVEAL S-16 REPAIRED AS PER SRM 53-10-04 FIG 91.

Part: HINGE — CORRODED (EMERGENCY EXIT) · airframe 70,081 hrs · 16,930 cycles

INSPECTION TYPE: C, M/D - L5 DOOR T/T LWR HINGE LWR BEARING ASSY MOUNTING SUPPORT AREA CORROSION. CORROSION BLEND OUT (0.040 X 1 X 1 INCH). M/D L5 DOOR LWR HINGE LWR SUPPORT WEB REPLACED AS PER SRM 51-10-01 PG 8.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · airframe 70,081 hrs · 16,930 cycles

INSPECTION TYPE: C, M/D - FLOOR SUPPORT FOUND CORROSION AT BS 2316 LBL 25-26. FLOOR SUPPORT REPLACED AS PER SRM 51-10-01 PG 8. CORROSION BLEND OUT 0.037 X 1 X 1 INCH.

Part: FRAME — CRACKED (FUSELAGE) · airframe 70,081 hrs · 16,930 cycles

INSPECTION TYPE: C, M/D - FRAME FOUND CRACKED AT BS 360 BETWEEEN STR 14R AND 15R. FRAME REPAIRED AS PER RS 53-12-35026 AND UPS EO B747-5310-18852-A.

Part: DOOR FRAME — CRACKED (FUSELAGE) · airframe 70,081 hrs · 16,930 cycles

INSPECTION TYPE: C, M/D - R2 PAX DOOR FOUND AFT FRAME LOWER CORNER CRACKED AS MARKED. LOWER CORNER REPAIRED AS PER SRM 52-10-02 FIG 8.

Part: INTERCOSTAL — CRACKED (FUSELAGE) · airframe 70,081 hrs · 16,930 cycles

INSPECTION TYPE: C, COCKPIT - BS 360 - 380 S1 - 2R INTERCOSTAL AFT WEB CRACKED. SUPPORT WEB REPAIRED AS PER SRM 51-40-03 FIG 3.

Part: STRINGER CLIP — CORRODED (FUSELAGE) · airframe 70,081 hrs · 16,930 cycles

INSPECTION TYPE: C, M/D - STA 580, STR 23R ATTACH TIE CLIP FOUND CORROSION REVEALED. M/D BS 580 S23R ATT TIE CLIP REPLACED AS PER SRM 51-10-01 PG 8 DUE TO CORROSION 1 X 0.5 X 0.020 INCH MAT'L REMAIN OUT OF SRM 53-10-01 FIG 1 LIMITATION.

Part: STRINGER CLIP — CORRODED (FUSELAGE) · airframe 70,081 hrs · 16,930 cycles

INSPECTION TYPE: C, M/D - STA 560 STR 23R ATTACH TIE CLIP FOUND CORROSION REVEALED. M/D BS 560 S-23R ATT TIE CLIP REPLACED AS PER SRM 51-10-01 DUE TO CORROSION BLENDED AREA .5 X 1 X 0.030 INCH MATL REMAINS, EXCEED SRM 53-10-01 FIG 1 LIMITATION.

Part: REVEAL — CRACKED (PAX DOORWAY) · airframe 70,081 hrs · 16,930 cycles

INSPECTION TYPE: C, M/D - R4 PAX DOOR CUTOUT FWD REVEAL FOUND CRACKED AT LOWER PORTION BETWEEN S-23 AND S-24 AS MARKED. M/D - R4 DOOR CUTOUT FWD REVEAL PANEL BETWEEN S-23R AND S-24R CRACKED REPAIRED AS PER SRM 53-10-04 FIG 84.

Part: SHEAR TIE — CRACKED (FUSELAGE) · airframe 70,081 hrs · 16,930 cycles

INSPECTION TYPE:C M/D - BS 1500, BET STR 20 - 22R FRAME ATT SHEAR TIE FOUND CRACK. SHEAR TIE REPLACED AS PER SRM 51-10-01 PAGE 8.

Part: TEE FITTING — CORRODED (FUSELAGE) · airframe 70,081 hrs · 16,930 cycles

INSPECTION TYPE: C, LT MLG WW STA 1241 BL 0 VERTICAL TEE FITTING CORROSION CRACK REVEALED. CORROSION BLEND OUT 0.063 X 2 X 10. BL 0 STIFFENER AT BS 1241 CTR SECTION REPLACED AS PER SRM 51-10-01 PG 8.

Part: STRUCTURE — CORRODED (FUSELAGE) · airframe 70,081 hrs · 16,930 cycles

INSPECTION TYPE: C, FX - KEELBEAM BOX EXTERNAL LOWER STRUCTURE LOWER SURFACE FOUND CORROSION AT STA 1255 TO STA 1260 RBL 7 TO RBL 9. CORROSION BLEND OUT 0.070 X 2 X 4 INCH. KEELBEAM LOWER STRUCTURE CORROSION REPAIR BETWEEN BS 1256 AND BS 1265, RBL 7 TO RBL 9 AS PER SRM 53-10-01 FIG 1, RS R53-49-35033 AND UPS ENG'R FILE 747-53-20143.

Part: STRINGER — CRACKED (FUSELAGE) · airframe 70,081 hrs · 16,930 cycles

INSPECTION TYPE: C, AFT CARGO STA 1745 S41L STRINGER FOUND CRACKED AT FASTENER HOLE. AFT CARGO BS 1740-1760 S41L STRINGER REPAIRED AS PER SRM 53-10-03 FIG 2.

Part: STRAP — CORRODED (PAX DOORFRAME) · airframe 70,081 hrs · 16,930 cycles

INSPECTION TYPE: C, M/D - R1 DOOR FRAME LWR HINGE CUTOUT STRAP FOUND CRACKED AS MARKED. LOWER HINGE CUTOUT REPAIRED IAW SRM 52-10-02 FIG.12.

Part: SKIN — CORRODED (FUSELAGE) · airframe 70,081 hrs · 16,930 cycles

INSPECTION TYPE: C, FX - AIR CONDITIONING BAY REAR FAIRING SKIN SURFACE FOUND CORROSION AT STA 1235 TO STA 1255 RBL 9 TO LBL 9. SKIN REPLACED AS PER SRM 51-10-01 PAGE 8. CORROSION BLEND OUT 0.012 X 4 X 4 INCH.

Part: BULKHEAD — CRACKED (NR 2 PYLON) · airframe 70,081 hrs · 16,930 cycles

INSPECTION TYPE: C, NR 2 PYLON REAR ENGINE MOUNT BULKHEAD 5EA FASTENER HOLE CRACKED AT FRAME WEB. NR 2 PYLON REAR ENGINE MOUNT BULKHEAD FRAME WEB REPAIRED AS PER HX RS R54-53-35022 AND UPS EO B747-5410-17055-B.

Part: BULKHEAD — CRACKED (RUDDER) · airframe 70,081 hrs · 16,930 cycles

INSPECTION TYPE: C, UPPER RUDDER ASSY LWR BHD INTERIOR WEB SKIN CRACKED TWO LOCATIONS AT RED MARKED. UPPER RUDDER ASSY LOWER BULKHEAD WEB INT SKIN WEB REPAIRED AS PER SRM 51-40-02 FIG 1.

Part: FRAME — CRACKED (FUSELAGE) · airframe 70,081 hrs · 16,930 cycles

INSPECTION TYPE: C, U/D - LT FRAME SHEAR TIE CRACKED (BS 520) AT S9L. U/D BS 520 LT FRAME AT S9L REPAIRED AS PER HX RS R53-12-35024 AND UPS EO B747-5310-18844-A.

Part: WEB — CRACKED (HORIZONTAL STAB) · airframe 70,081 hrs · 16,930 cycles

INSPECTION TYPE: C, EMP - LT HORIZONTAL STAB TIP FAIRING SUPPORT STRUCTURE VERTICAL WEB IS FOUND CRACKED AT APPROX 10 INCHES AFT OF HS REAR SPAR AT HSBL 421.5. EMP - LT HORIZONATAL STAB TIP FAIRING SUPPORT STRUCTURE VERTICAL WEB REPAIRED AS PER HX RS R55-13-35021 (UPS EO 747-55-20001).

Part: SKIN — CRACKED (FUSELAGE) · airframe 70,081 hrs · 16,930 cycles

INSPECTION TYPE: C, AFT CARGO DOOR CUTOUT AFT UPPER CORNER AREA FOUND FOUND 1EA HOLE CRACK AT SKIN AND BEARSTRAP APPROX .0625 INCH RUNNING UPWARD AND DOWNWARD. AFT CARGO DOOR CUTOUT AFT UPPER CORNER HINGE CAP 1EA BOLT HOLE REPAIRED AS PER BOEING MSG UPS-HKG-03-00105H RS R53-61-35020 AND UPS EO B747-5330-18849-A. REF TAR S/N 103610.

Part: CLIP — CRACKED (NLG WW) · airframe 70,081 hrs · 16,930 cycles

INSPECTION TYPE: C, NWW TUNNEL - RT BS 300 VERTICAL BEAM 3RD STIFFENER CLIP FOUND CRACKED (COUNT FROM TOP). CLIP REPLACED AS PER SRM 51-10-01 PAGE 8 AND AN AREA PAINT TOUCHED UP PER MM 51-24-11.

Part: BEAM — CRACKED (NLG WW) · airframe 70,081 hrs · 16,930 cycles

INSPECTION TYPE: C, NLG WW TUNNEL - LT BS 280 VERTICAL BEAM WEB FOUND CRACK AT LOWER STANDOFF HOLE BETWEEN 1ST AND 2ND STIFFENER CLIP (COUNT FROM TOP). VERTICAL BEAM WEB REPLACED WITH SERVICEABLE NEW PART AS PER SRM 51-10-01 PG 8 AN AREA PAINT TOUCH UP PER MM 51-24-11.

Part: BEAM — CRACKED (NLG WW) · airframe 70,081 hrs · 16,930 cycles

INSPECTION TYPE: C, NLG WW TUNNEL - RT BS 280 VERTICAL BEAM WEB FOUND CRACK AT LOWER STANDOFF HOLE BETWEEN 1ST & 2ND STIFFENER CLIP (COUNT FROM TOP). DEFECT WEB REMOVED AND SERVICEABLE WEB REPLACED AS PER SRM 51-10-01 PG 8.

Part: FITTING — CORRODED (LT MLG WW) · airframe 70,081 hrs · 16,930 cycles

INSPECTION TYPE: C, LT MLG W/W STA 1480 CUTOUT PNL O/B OF O/B TRUNNION FITTING AREA FOUND CORRODED AT ACCESS PANEL AREA. CORROSION BLEND OUT (0.030 X 1 X 3 INCH) BULKHEAD WEB REPAIRED AS PER SRM 51-40-02 FIG 1.

Part: BULKHEAD — CRACKED (FUSELAGE) · airframe 70,081 hrs · 16,930 cycles

INSPECTION TYPE:C, FX - STA 1480 PRESSURE BULKHEAD LEFT O/B LOWER WEB FOUND CRACKED AT LBL 90 TO LBL 92 HI-LOK AREA. FX STA 1480 PRESSURE BULKHEAD LEFT O/B LOWER WEB REPAIRED AS PER SRM 51-40-02 FIG 1 JUST AT LBL 90 TO LBL 92.

Part: STRUCTURE — CORRODED (KEELBEAM) · airframe 70,081 hrs · 16,930 cycles

INSPECTION TYPE: C, FX - KEEL BEAM BOX INTERIOR LOWER STRUCTURE FOUND HEAVY CORROSION AT STA 1450 TO STA 1465 LBL 6 TO LBL 8. CORROSION BLEND OUT 0.149 X .75 X 1.5 INCH. REPAIRED CARRIED OUT AS PER HX RS R53-49-35025 UPS ENG'R FILE 747- 53-20139.

Part: LONGERON — CORRODED (FUSELAGE) · airframe 70,081 hrs · 16,930 cycles

INSPECTION TYPE: C, FX - KEEL BEAM BOX INTERIOR LOWER STRUCTURE FOUND HEAVY CORROSION AT STA 1450 TO STA 1465 RBL 6 TO RBL 8. LONGERON REPAIRED AT BS 1456 TO 1480 RT AS PER HX RS R53-49-35025 ITEM 1 TO ITEM 19 AND ENG'R FILE NUMBER 747-53-20139. CORROSION BLEND OUT 158 X .75 X 1 INCH EXCEED SRM LIMIT.

Part: ANGLE — CRACKED (FUSELAGE) · airframe 70,081 hrs · 16,930 cycles

INSPECTION TYPE: C, NLG WW STA 320 LBL 30 PRESSURE DECK LT UPPER ANGLE AREA CRACKED AS MARK. NLG WW LT PRESSURE DECK UPPER ANGLE AT LBL 30 FROM BS 260-340 REPLACED AS PER SRM 51-10-01 PG 8.

Part: ANGLE — CRACKED (FUSELAGE) · airframe 70,081 hrs · 16,930 cycles

INSPECTION TYPE: C, NLG W/W STA 320 RBL 30 PRESSURE DECK RT UPPER ANGLE AREA CRACKED AS MARK. NLG W/W PRESSURE DECK RT UPPER CORNER ANGLE AT RBL 30 REPLACED AS PER SRM 51-10-01 PG 8.

Part: SKIN — WORN (NR 4 PYLON)

INSPECTION TYPE: P/S, NR 4 PYLON I/B SIDE HAS HOLE WORN IN PREVIOUS REPAIR. ***OPEN***

Part: WEB — CRACKED (CREW ENTRY DOOR)

INSPECTION TYPE: PFLT, 3 INCH CRACK IN WEB AFT FRAME UPPER SIDE, MARKED. REMOVED FRAME WEB AT STA 488 FROM APPROX 5-16 TO 5-22. STARTED FABRICATION OF REPLACEMENT WEB AND TWO SPLICE PLACE IAW SRM 53-10-04. COMPLETED FABRICATING OF WEB & (2) SPLICE PLATES. TREATED, PRIME, PAINTED & STARTED TO INSTALL REF SRM 53-10-4 ON LWR SPLICE PLATE. COMPLETED THE EO FOR SHORT FASTENER EDGE DISTANCE. COMPLETED REPAIR.

Part: WIRE — BROKEN (COCKPIT)

INSPECTION TYPE:PFLT FOUND F/O EMERGENCY LIGHT INOP ON GLARESHIELD. R/R BULB NO HELP. FOUND WIRE W2032-WHT/BLU BROKEN. REPAIRED IAW WDM 33-13-11. OPS CHECK OKAY.

Part: LIGHT — INOPERATIVE (COCKPIT)

ESCAPE SLIDE EMERGENCY LIGHT INOP. TRANSFER TO MEL 25-11-1 CAT C PLACARD INSTALLED.

Part: LIGHT — INOPERATIVE (CREW STAIRS)

INSPECTION TYPE:AS EMERGENCY ENTRY LIGHT IN CEILING AT BOTTOM OF CREW STAIRS INOP. INSTALLED LIGHT BULBS OPS CHECK NORMAL.

Part: ODOR — DETECTED (COCKPIT)

INSPECTION TYPE:N/A OIL SMELL AND HAZE IN COCKPIT AT TOP OF DESCENT WHEN THROTTLES RETARDED. VERIFIED SOURCE OF OIL SMELL FROM NR 3 ENGINE PNEUMATICS. LOCKED OUT NR 3 ENGINE PYLON VALVE TO ISOLATE PNEUMATICS FROM AIRFRAME.

Part: COALESCER BAG — CONTAMINATED (A/C BAY)

INSPECTION TYPE:N/A BLEED AIR SMOKE REPORTED IN UPPER DECK BY MAINTENANCE JUMPSEATERS AND NOTICEABLE BY FLIGHT CREW AT TOP OF DESCENT. ISOLATED NR 3 PACK AND SMOKE DISSIPATED. RAN 1 & 2 PACKS ONLY. VERIFIED ACM OIL SERVICED TO PROPER LEVEL. FOUND OIL RESIDUE IN COALESCER BAG. NO PART AVAIL. DEFERRED NR 3 PACK.

Part: STRINGER — CORRODED (STA 1148 25L)

INSPECTION TYPE:N/A CORROSION STA 1148 STRINGER 25L TO 26L ***MRR FILED AS OPEN****

Part: ENGINE — LEAKING (NR 1)

INSPECTION TYPE:N/A FSA ITEM H22303 SMOKE IN COCKPIT. REMOVED AND REPLACED NR 1 ENGINE AS PER UPS TC5000 AND WAN 678705.

Part: RESISTOR — BLOWN (COCKPIT)

INSPECTION TYPE:N/A SMOKE IN THE C/P ON TOP OF DESCENT. COULD NOT LOCATE SOURCE. DID NOT SMELL ELECTRICAL. COMPLETED C/P SMOKE/FUME EVACUATION CHECKLIST. SMOKE WAS MODERATE TO HEAVY FROM GLARESHIELD-AREA THROUGH WHOLE UPPER DECK. ADJUSTED NR 1 & 4 ENG N2 GROUND IDLE PER MM 71-00-00. NR 2 ENG NR 2 IP BLEED VALVE ACOUSTICAL ATTENUATOR BLOWN THROUGH, REMOVED AND REPLACED SAME NR 1 ENG RUN REQ FOR LEAK CHECK AND IGN VERIFICATION RUN NR 1 ENGINE, NO LEAK NOTED. NR 2 ENG RUN REQUIRED FOR LEAK CHECK. RAN NR 2 ENGINE, NO LEAK NOTED.

Part: ENGINE (ENGINE #3)

INSPECTION TYPE:N/A SHORTLY AFTER DECENT, SMOKE CAME INTO COCPIT FROM UNDETERMINED SOURC E. ENTERED FROM VENTS WITH ALL SYSTEMS OPERATING NORMALLY. PER DISCUSSION W/FLT CREW, SMOKE TO BE VERY LIGHT & OF OILY NATURE T/S PER M/M 71-00-44. FOUND #3 ENG N2 GRN & FLT IDLE LOW. TRIMMED ENG PER M/M 71-00-11 TRIM CHARTS. GRN IDLE INCR 12 CLICKS.FLT IDLE INCR 12 CLICKS.RPLC 1 & 3 COALESOR BAGS CLEANED #2 PER MM21-51-05 OPS ALL ENG AND A/C PACKS CHECKED OK. OK FOR SERVICE

Part: FRAME — CRACKED (NR 4 PYLON) · airframe 66,302 hrs · 16,182 cycles

INSPECTION TYPE:C NR 4 PYLON NAC STA 221.94 ENG AFTER MOUNT BULKHEAD REAR O/B SIDE LOWER PORTION SUPPORT FRAME FOUND CRACK FROM REAR EDGE TO FWD ABOUT .75 INCH LONG APPROX AS MARKED AFTER THE AREA CLEAN UP. NR 4 PYLON NAC STA 221.94 O/B SIDE FRAME REPLACED AS PER SRM 51-10-01 PG 8.

Part: WEB — CRACKED (RH SIDE NWW) · airframe 66,302 hrs · 16,182 cycles

INSPECTION TYPE:C R/H SIDE NWW ON BS 300 VERTICAL BEAM WEB FOUND CRACKED AT #5 CLIP ( COUNTED FROM TOP ) ATTACHED FASTENER HOLE, THE MOST I/B FASTENER HOLE, APPROX 3/16" IN LENGHT AS MARKED. WEB REPLACED AS PER SRM 51-10-01.

Part: FRAME — CRACKED (FUSELAGE) · airframe 66,302 hrs · 16,182 cycles

INSPECTION TYPE:C CRACK REVEALED ON RT BS 1480 BULKHEAD CHORD AT FASTENER HOLE NR 3 BY APPROX 0.060 INCH LONG AND RUNNING AFT UP AS PER ATTACH FIGURE. RIGHT BS 1480 B/H CHORD HOLE NR 3 CRACK REMOVED AND BUSH INSTALLED IN B/H CHORD HOLE NR 3 AS PER SB 747-53A2390 FIG 11. PLAN A BUSH REPAIR CWPC NR RCBR017 054 ATTACHED. THIS REPAIR ACCOMPLISHED AS PER RS R-53-43-34702 AND EO B747-5310-15717-A.

Part: STRAP — CRACKED (FUSELAGE) · airframe 66,302 hrs · 16,182 cycles

INSPECTION TYPE:C, 3 EACH CRACKS FOUND AT BS 2231 RT SIDE BETWEEN S24R TO S26R AT THE FRAME STRAP FWD COLUMN OF FASTENERS CRACK LENGTH FROM .125 INCH, .25 INCH AND .5 INCH LONG RESPECTIVELY. S24R TO S26R FRAME STRAP REPAIRED AS PER SRM 53-10-04 FIG 115.

Part: FITTING — CRACKED (RH BS 1480) · airframe 66,302 hrs · 16,182 cycles

INSPECTION TYPE:C R/H SIDE BS 1480 B/H FASTENER HOLE #9 FOUND CRACKED AT B/H LONGERON EXTENSION FITTING, FUSELAGE SKIN B/H CHORD AND OUTER CHROD SPLICE FITTING, PLS REFER TO ATT SKETCH FOR DETAIL. RH BS 1480 B/H LONGERON EXTENSION FTG FX SKIN, B/H CHORD & OUTER CHORD SPLICE FTG CRACKS REMOVED AT FS HOLE #9 BUSH INSTALLED IN LONGERON EXTENSION FTG, FX SKIN B/H CHORD & OUTER SPLICE FTG AT HOLE #9 AS PER SB 747-53A2390 FIG 11 PLAN A BUSH REPAIR CWPC #RCBR017 083 ATT. THIS REPAIR AS PER RS R53-43-34702 & EO B747-5310-15717-A.

Part: BUSHING — CRACKED (BS 1480) · airframe 66,302 hrs · 16,182 cycles

INSPECTION TYPE:C R/H SIDE BS 1480 B/H FASTENER HOLE #1 FOUND CRACKED AT FUSELAGE SKIN, B/H CHORD AND OUTER CHORD SPLICE FITTING, PLS REFER TO ATT SKETCH FOR DETAILS. RH BS 1480 B/H HOLE #1 AT FUS SKIN, B/H CHORD AND OUTER CHORD SPLICE FTG CRACKS REMOVED BUSHING INSTALLED ON OUTER CHORD SPLICE FTG, B/H CHORD AND FUS SKIN HOLE #1 AS PER SB 747-53A2390 PLAN A BUSHING REPAIR CWPC CONTROL SEQUENCE NO.RCBR017060 AND RCBR017084 ATTACHED THIS REPAIR C/OUT I.A.W RS R-53-43-34702 AND EO B747-5310-15717-A.

Part: FRAME — CRACKED (FUSELAGE) · airframe 66,302 hrs · 16,182 cycles

INSPECTION TYPE:C CRACK FOUND AT ONE FASTENER HOLE AT LT SIDE OF BS 1265 FRAME WEB JUST BELOW FLOOR LEVEL AREA. TWO CRACKS FOUND AT THE HOLE - ONE IS .25 INCH LONG AT FIVE O'CLOCK AND ANOTHER IS .0625 INCH LONG AT 11 O'CLOCK POSITION ON (LOOKING FWD). REPAIR CARRIED OUT AS PER EO B747-5310-12070-I.

Part: FRAME — CRACKED (FUSELAGE) · airframe 66,302 hrs · 16,182 cycles

INSPECTION TYPE:C RT TUNNEL BS 320 STR 41 AFT CORNER NR 5 RIVET HOLE (COUNTER FROM I/B TO O/B) FOUND A RIVET HOLE CRACKED AS MARKED (AFT BOTTOM ANGLE REMOVE FINDING. FRAME REPAIRED AS PER SRM 54-40-03 FIG 1, CHORD REPAIRED AS PER SRM 51-40-04 FIG 2.

Part: FITTING — CRACKED (LH BS 1480) · airframe 66,302 hrs · 16,182 cycles

INSPECTION TYPE:C AFT CARGO COMPT - LH BS 1480 B/H NO.9 HOLE FOUND CRACK AT EXTENSION FITTING AND OUTER CHORD SPLICE FITTING ( REFER ATT SKETCHES FOR DETAILS ). LH BS 1480 B/H EXTENSION FTG AND OUTER CHORD SPLICE FTG HOLE NO.9 CRACKS REMOVED AND BUSHINGS INSTALLED IN LONGERON EXTENSION FTG & OUTER CHORD SPLICE FTG AS PER SB 747-53A2390 PLAN A BUSHING REPAIR CWPC CONTROL SEQUENCE NO. RCBR017 049 ATTAHCED.

Part: FITTING — CRACKED (RH BS 1480) · airframe 66,302 hrs · 16,182 cycles

INSPECTION TYPE:C R/H SIDE BS 1480 B/H FASTENER HOLE #11 FOUND CRACKED AT B/H LONGERON EXTENSION FITTING, FUSELAGE SKIN AND B/H CHORD, PLS REFER TO ATT SKETCH FOR DETAILS. RH BS1480 B/H HOL #11 AT LONGERON EXTERSION FTG, FX SKIN & B/H CHORD CRACKS REMOVED. BUSH INSTALLED IN LONGERON EXTERSION, SKIN & CHORD HOLE #11 PLAN A BUSH REPAIRED AS PER SB 747-53A2390. CWPC NO. RCBR017 TASH 057 ATT. RADIUS FILLER INSTALLED TO RH #11 HOLE ON THE LONGERON EXTERSION FTG AS PER RS R53-43-34702 & EO B747-5310-15717-A

Part: SKIN — CORRODED (HORIZ STAB) · airframe 66,302 hrs · 16,182 cycles

INSPECTION TYPE:C, RT STAB UPPER FACE SURFACE CORROSION ALONG FASTENER HEADS AT SKIN AREA FROM S1 - S15, STAB STA 143 - 240. REPAIRED RT HORIZONTAL STAB UPPER SKIN AT HS STA 223 TO 182 STR 5.

Part: BUSHING — CRACKED (BS 1480) · airframe 66,302 hrs · 16,182 cycles

INSPECTION TYPE:C L/H SIDE BS 1480 B/H FASTENER HOLE #18 FOUND CRACKED AT OUTER CHORD SPLICE FITTING, PLS REFER TO ATT SKETCH FOR DETAILS. LH BS 1480 B/H OUTER CHORD SPLICE FTG HOLE #18 CRACK REMOVED AND OUTER CHORD SPLICE FTG, B/H CHORD, SKIN & LONGERON EXTENSION FTG OVERSIZED TO INSTALL BUSHINGS IN HOLE #18 AS PER SB 747-53A2390. CWPC CONTROL SEQUENCE NO.RCBR017 081 ATTACHED.

Part: FITTING — CRACKED (RH BS 1480) · airframe 66,302 hrs · 16,182 cycles

INSPECTION TYPE:C RH BS 1480 BULKHEAD ONE EA BOLT HOLE NO.25 FOUND TWO CRACKS AT OUTER CHORD SPLICE FITTING FWD SURFACE APPROX 0.030" AT 4 O'CLOCK POSITION ( LOOKING FWD ) AND 0.030" APPROX THROUGH THICKNESS AT 10 O'CLOCK POSITON. RH BS 1480 B/H SPLICE FTG BOLT HOLE #25 CRACK REMOVED. BUSHING INSTALLED IN OUTER CHORD SPLICE FTG HOLE NO.25 AS PER SB 747-53A2390 FIG 11 PLAN A BUSHING REPAIR RADIUS FILLER INSTALLED AS PER RS R53-43-34702. CWPC CONTROL SEQUENCE NO. RCBR017 058 ATTACHED. THIS REPAIR ACCOMPLISHED IAW EO B747-5310-15717-A.

Part: STIFFENER — CRACKED (NOSE W/W) · airframe 66,302 hrs · 16,182 cycles

INSPECTION TYPE:C NOSE WHEEL WELL BOX (TUNNEL AREA) STA 360 SIDE WALL PNL ATT HORI NO. 5 STIFFENER FOUND CRACKED AND MARKED (COUNT FROM TOP). (LHS) STA 360 TO 380 NO.5 HORI-STIFFENER REPLACED PER SRM 51-10-01.

Part: BUSHING — CRACKED (BS 1480) · airframe 66,302 hrs · 16,182 cycles

INSPECTION TYPE:C AFT CARGO COMPT - LH BS 1480 B/H NO.11 HOLE FOUND CRACK AT FX SKIN AND OUTER CHORD SPLICE FITTING (REFER ATT SKETCHES FOR DETAILS). LH BS 1480 B/H SKIN & OUTER SPLICE FTG HOLE NO.11 CRACKS REMOVED AND EXTENSION FTG, SKIN AND OUTER CHORD SPLICE FTG OVERSIZED TO INSTALL BUSHINGS IN HOLE NO.11 AS PER SB 747-53A2390 FIG.11 PLAN A BUSHING REPAIR. CWPC CONTROL SEQUENCE NO.RCBR017 080 ATTACHED.

Part: SPLICE — CRACKED (FUSELAGE) · airframe 66,302 hrs · 16,182 cycles

INSPECTION TYPE:C RT SIDE BS 1480 B/H FASTENER HOLE NR 5 FOUND CRACKED AT OUTER CHORD SPLICE FITTING. RT BS 1480 B/H OUTER CHORD SPLICE FITTING HOLE NR 5 CRACK REMOVED AND BUSHING INSTALLED IN OUTER CHORD SPLICE FITTING HOLE NR 5 AS PER SB 747-53A2390 FIG 11. PLAN A BUSHING REPAIR CWPC CONTROL SEQUENCE NR RCBR017 055 ATTACHED. THIS REPAIR ACCOMPLISHED AS PER RS R-53-43-34702 AND EO B747-5310-15717-A.

Part: FRAME — CRACKED (NR 4 PYLON) · airframe 66,302 hrs · 16,182 cycles

INSPECTION TYPE:C, NR 4 PYLON (O/B STRUT) AFT TORQUE BULKHEAD VERTICAL CHORD FOUND 1 FASTENER HOLE CRACK AT CHORD FWD SURFACE RUNNING O/B AT 4 O'CLOCK POSITION APPROX .125 INCH LENGTH. CRACK HOLE REAMED ECCENTRICALLY TO 0.500 INCH AND NDT INSPECTION CONFIRMED CRACK FREE REF NTM PT6, 51-00-00 FIG 4. INSURANCE CUT AND FREEZE PLUG CUTOUT ON CHORD AS PER SRM 51-10-08, ANGLE AND DOUBLER, FABRICATED, INSTALLED DETAILS REF PROCESS CARD AND RCBR017 & UPS-EO- 747-5410-13496 PG 58 FIG 2, TELEX UPS-HKG01-00116H & RS 54-53-34701.

Part: WEB — CRACKED (RH SIDE NWW) · airframe 66,302 hrs · 16,182 cycles

INSPECTION TYPE:C R/H SIDE NWW AT BS 320 VERTICAL BEAM WEB FASTENER 1EA COMMON TO THE INNER CHORD CRACKED JUST BETWEEN #5 AND #6 STIFFENER ( COUNTED FROM TOP ) AS MARKED. R/H NOSE WHEEL WELL BS 320 VERTICAL BEAM WEB REPLACED AS PER SRM 51-10-01.

Part: WEB — CRACKED (LH SIDE NWW) · airframe 66,302 hrs · 16,182 cycles

INSPECTION TYPE:C L/H SIDE NWW AT BS 320 VERTICAL BEAM WEB FOUND ONE EACH STAND OFF HOLE CRACKED, JUST BETWEEN 31 AND #2 STIFFENER ( COUNTED FROM TOP ) AS MAKRED. REF NRC GJ58782 VERTICAL WEB REPLACED AS PER SRM 51-30-02.

Part: WEB — CRACKED (LH SIDE NWW) · airframe 66,302 hrs · 16,182 cycles

INSPECTION TYPE:C L/H SIDE NWW AT BS 300 VERTICAL BEAM WEB FOUND ONE EACH STANDOFF HOLE CRACKED JUST BETWEEN #1 AND #2 STIFFENER ( COUNTED FROM TOP ) AS MARKED. NEW VERTICAL WEB INSTALLED AS PER SRM 51-30-02

Part: FRAME — CRACKED (FUSELAGE) · airframe 66,302 hrs · 16,182 cycles

INSPECTION TYPE:C RIGHT BS 320 NOSE WHEEL WELL FRAME CRACK AT 5 EA FASTENER HOLES WHICH 4 EA AT WEB AND 1 EA AT CHORD FOR DETAIL, PLS REFER ATTACHED FIGURE. FRAME REPAIRED AS PER SRM 51-40-03 FIG 1. CHORD REPAIRED AS PER SRM 51-40-04 FIG 2.

Part: FRAME — CRACKED (NOSE W/W) · airframe 66,302 hrs · 16,182 cycles

INSPECTION TYPE:C L/H BS 300 NOSE WHEEL WELL FRAME CRACK FOUND AT WEB 2EA FASTENER HOLES, PLS REFER ATT FIG. LH BS 300 WHEEL WELL FRAME AT STR L 39 TO STR L 41 CRACKED AREA REPAIRED AS PER SRM 51-40-03 FIG 1.

Part: FRAME — CRACKED (#4 PYLON) · airframe 66,302 hrs · 16,182 cycles

INSPECTION TYPE:C #4 PYLON NAC STA 221 FRAME SEVERAL LOOSE AND SHEARED FASTENERS ON LHS 1/2" CRACK EMINATING FROM FASTENER HOLE. THE PYLON STA 221 FRAME WAS REPAIRED AS PER HX RS-53-34698 / UPS-HKG -01-00114H CONTINUE INSP REQUIRE PER SB 747-54A2202 AT 18 MONTH OR 1200 CYCLES WHATEVER EAILER REF UPS REPAIR/ALTERATION AUTHORIZATION, ENGINEERING FILE NO.747-54-20007 THE PNEU. DUCTING & THE ANTI-ICING VALVE REINSTALLED AIR LEAK CHK & OPN CHK C/OUT MM 36-11-01,30-21-03.

Part: WEB — CRACKED (LH BS 1480) · airframe 66,302 hrs · 16,182 cycles

INSPECTION TYPE:C L/H SIDE BS 1480 BULKHEAD ONE EACH BOLT NO.26 FOUND CRACK AT BULKHEAD WEB FWD SURFACE 0.080" APPROX AT 8 O'CLOCK POSITION REFER TO ATTCHED DRAWING FOR DETAILS. LH BS 1480 B/H WEB AT HOLE #26 CRACK REMOVED AND BUSHING INSTALLED AT WEB AS PER SB 747-53A2390 FIG 11. PLAN A BUSHING REPAIR. CWPC CONTROL SEQUENCE NO. RCBR017 052 ATTACHED.

Part: SPLICE PLATE — CRACKED (LH SIDE BS 1480) · airframe 66,302 hrs · 16,182 cycles

INSPECTION TYPE:C LH SIDE BS 1480 BULKHEAD ONE EACH BOLT HOLE NO.23 FOUND CRACK AT SPLICE PLATE FWD SURFACE 1/8" APPROX AT 8 O'CLOCK POSITION REFER TO ATTTACHED DRAWING FOR DETAILS. LH BS 1480 B/H SPLICE PLATE AT HOLE #23 CRACK REMOVED AND BUSHING INSTALLED IN SPLICE PLATE AS PER SB 747-53A2390 FIG 11 PLAN A BUSHING REPAIR CWPC CONTROL SEQUENCE NO. RCBR017 079 ATTACHED.

Part: FRAME — CRACKED (NOSE WHEEL WELL) · airframe 66,302 hrs · 16,182 cycles

INSPECTION TYPE:C R/H BS 300 NOSE WHEEL WELL FRAME CRACK FOUND AT WEB 4EA FASTENER HOLES, PLS REFER ATT FIG. R/H BS 300 NOSE WHEEL WELL STR R 39 TO R 41 FRAME CRACKED AREA REPAIRED AS PER SRM 51-40-03 FIG 1.

Part: FRAME — CRACKED (FUSELAGE) · airframe 66,302 hrs · 16,182 cycles

INSPECTION TYPE:C RT BS 2231 FRAME, ONE FASTENER HOLE CRACK FOUND AT REVEAL BETWEEN S24 AND S25R RUNNING AFT APPROX .125 INCH LONG. BETWEEN S24 AND S25R FRAME REVEAL REPAIRED AS PER MM 53-10-04 FIG 115.

Part: FRAME — CRACKED (FUSELAGE) · airframe 66,302 hrs · 16,182 cycles

INSPECTION TYPE:C RIGHT BS 2231 FRAME ONE FASTENER HOLE CRACK FOUND ON S25R, AT INNER CHORD RUNNING FWD AND AFT THROUGH THICKNESS, REFER ATTACH SKETCH. FRAME INNER CHORD REPAIRED AT S25R AS PER SRM 53-10-04 FIG 115.

Part: DOUBLER — CRACKED (LH #1 MED) · airframe 66,302 hrs · 16,182 cycles

INSPECTION TYPE:C M/D - LH #1 MED EXTERIOR SKIN LWR HINGE CUTOUT ATT DOUBLER FOUND CRACK AS MARKED. DOUBLER REPLACED AS PER R.S R52-11-34699.

Part: FRAME — CRACKED (#4 PYLON) · airframe 66,302 hrs · 16,182 cycles

INSPECTION TYPE:C #4 PYLON NAC STA 235.94 APPROX PYLON VALVE ACCESS PNL #483EL CUTOUT FWD FRAME CRACKED AS MARKED. CUTOUT FWD FRAME CRACK STOP DRILLED & NDT INSPECTION CONFIRMED CRACK FREE BEYOND DRILLED HOLE AS PER NTM PT6, 51-00-00 FIG 4 AND FRAME REPAIRED AS PER SRM 54-14-03 FIG 1 PYLON VALVE WAS REFITTED, AIR LEAK CHK AND OPN CHK CARRIED OUT MM 36-11-01, 36-11-00.

Part: WIRE — LOOSE (CABIN)

INSPECTION TYPE:PFLT LIGHTED EMERGENCY EXIT SIGN, LOCATED ON BACK SIDE OF P6 ENST TO UPPER DECK EMERGENCY SLIDE, HAS WIRES PULLED FROM CONNECTOR. SYSTEM DEACTIVATED, WIRE AND CONNECTORS CAPPED AND STOWED, "DEACT" PLACARD INSTALLED PER EO B747-3350-15296.

Part: WIRE — DAMAGED (CABIN)

INSPECTION TYPE:N/A EMERGENCY LIGHT INOP UPPER DECK EXIT FWD PANEL REPAIRED PULLED WIRE, OPS CK GOOD

Part: CONNECTOR — SHORTED (PDU)

DURING GROUND LOADING OPERATIONS SMOKE WAS REPORTED COMING FROM 19L1 SMART WHEEL. MAINT REPORTED FINDING 19L1 PDU AND ASSOC WIRING SMOKING AT THIS POS. ELECTRICAL CONNECTOR WAS REMOVED AND STOWED C/B WAS PULLED AND COLLARED BY PVG MECH HEUN.THIS ITEM WAS PLACED ON DEFERRAL D213295.

Part: SEAL — LOOSE (MAIN CARGO DOOR)

INSPECTION TYPE:N/A 2IR TURNBACK TO SDF DUE TO LOW CABIN AIR PRESSURE UNABLE TO KEEP CABIN BELOW 10.000 AT ANY ALTITUDE ABOVE FL 200. FOUND MAIN CARGO DOOR AFT PRESSURE SEAL FLANGE PULLED OUT OF TRACK. RE-SECURED MM 52-09, PRESSURIZED AIRCRAFT AND FOUND EQUIP COOLING FLOW CONTROL VALVE REMAINING OPEN. REMOVED AND REPLACED FLOW CONTROL VALVE IAW 747 MM 21- 58-04, PRESSURIZED AIRCRAFT TO 7.8 LBS DIFF MAINTAINED.

Part: LIGHT — INOPERATIVE (CABIN)

INSPECTION TYPE:N/A, UPPER DECK EMERGENCY LIGHTS AT AFT TWO POSITION ARE INOP. REMOVED AND REPLACED BATTERY PACK ASSY REFERENCE LP 180448 FOR DEFERRAL.

Part: BATTERY PACK — INOPERATIVE (CABIN)

INSPECTION TYPE:N/A, EMERGENCY EXIT SIGN OVER ESCAPE SLIDE DOOR INOP. REMOVED AND REPLACED EMERGENCY LIGHT POWER PACK PER MM 33-51-04. OPS CHECK GOOD.

Part: ANGLE — CORRODED (FUSELAGE) · airframe 62,800 hrs · 15,449 cycles

INSPECTION TYPE:C, REINFORCING ANGLE AT BS 360 RT BETWEEN STR 3 A AND STR 10 IS CORRODED. ANGLE FABRICATED IAW SRM 51-20-01 AND REPLACED IAW SRM 51-30-02.

Part: SUPPORT BRACKET — CRACKED (WING TO BODY) · airframe 62,800 hrs · 15,449 cycles

INSPECTION TYPE: C. WING TO BODY SUPPORT CRACKED AT BS 1265, BELOW REAR SPAR SPLICE LT SIDE. DAMAGE REMOVED AND REPAIR CARRIED OUT IAW SRM 51-40--03 FIG 1

Part: SUPPORT BRACKET — DAMAGED (WINT TO BODY) · airframe 62,800 hrs · 15,449 cycles

INSPECTION TYPE: C, FUSELAGE WING TO BODY FAIRING SUPPORT BRACKET CRACKED AT BS 1265, BELOW LOWER REAR SPAR SPLICE RT. DAMAGE REMOVED AND REPAIR CARRIED OUT IAW SRM 51-40-03 FIG 1.

Part: WEB — CRACKED (FUSELAGE) · airframe 62,800 hrs · 15,449 cycles

INSPECTION TYPE:C, FRAME WEB CRACKED AT STA 1265 LT. REPAIRED IAW QUERY NOTE 14/2000, CUT OUT DAMAGED AREA AND INSTALLED DOUBLERS AS REQUIRED.

Part: SPAR — CORRODED (LT TE FLAP) · airframe 62,800 hrs · 15,449 cycles

INSPECTION TYPE:C REF NRC 44298572 44298580 44298584 44298590, PLEASE REPLACE LEFT I/B MIDFLAP ASSY DUE CORROSION ON FRONT SPAR LOWER CHORD AND UPPER SURFACE DOUBLER PLATE. LT MIDFLAP ASSY REPLACED PER MM 27-51-01.

Part: STIFFENER — CRACKED (BS300 RBL 22) · airframe 62,800 hrs · 15,499 cycles

INSPECTION TYPE: C. CRACK IN NOSE WHEEL WELL AT BS 300 RBL 22 . CRACK IN STIFFENER. NOSE WHEEL WELL CRACKED STIFFENER REPLACED STIFFENER IAW SRM 51-300-02

Part: ANGLE — CRACKED (BS 486 STR 26) · airframe 62,800 hrs · 15,499 cycles

INSPECTION TYPE: C. CRACK FOUND IN ANGLE AT BS 486 STR 26 LT IN FWD CARGO HOLD. ANGLE REPLACED IAW SRM 51-30-02

Part: SEAT TRACK — CRACKED (FUSELAGE) · airframe 62,800 hrs · 15,449 cycles

INSPECTION TYPE: C. SEAT TRACK CRACKED BS 440 AND BS460 RBL 64. SECTION OF SEAT TRACK REPLACED FROM BS 430 TO BS 460 IAW SRM 53-10-0 5, FIG. 1A, DETAIL 1V

Part: FITTING — CRACKED (NR 2 & 3 ENGINES) · airframe 62,800 hrs · 15,449 cycles

INSPECTION TYPE:C, CRACKS CONFIRMED IN NR 3, 2 ENG AFT MOUNT BULKHEAD NAC STA 222 BATH TUB FITTING NRC 44301117 NEW BATH TUB FITTING FITTED IAW SRM 51-30-02.

Part: STRAP — CRACKED (FUSELAGE) · airframe 62,800 hrs · 15,499 cycles

INSPECTION TYPE: C. FRAME TIE DOWN STRAP BROKEN FWD OF RT OUTFLOW VALVE BS 2020 LBL 15. NEW TIE DOWN STRAP FABRICATED AND INSTALLED IAW 51-30-02 AND SRM 5 1-20-1

Part: WEB — CRACKED (FUSELAGE) · airframe 62,800 hrs · 15,449 cycles

INSPECTION TYPE:C, CONTROL CABIN CRACK IN FRAME WEB AT I/B FLANGE AT BS 320 CROWN AREA AT STR 1 LT. REPAIRED IAW SRM 53-10-04 AND QUERY NOTE 44 /2000. DOUBLER INSTALLED.

Part: ANGLE — CRACKED (FUSELAGE) · airframe 62,800 hrs · 15,449 cycles

INSPECTION TYPE: C. FWD CARGO BAY TWO CRACKED ANGLES ON WEATHER RADAR TRAY BS 380 RT SIDE NOSE WW, CRACKED ANGLES REMOVED IAW SRM 51-30-02. NEW ANGLES FABRICATED IAW BAC 5300. NEW ANGLES INSTALLED IAW SRM 51-30-02

Part: WEB — CRACKED (FUSELAGE) · airframe 62,800 hrs · 15,449 cycles

INSPECTION TYPE:C, CRACKS FOUND IN FRAME OUTER FLANGE AT BS 520 BETWEEN STRINGER 8/9 RT. REPAIR CARRIED OUT IAW QUERY NOTE 21 /2000 AND SRM 53-10-04 FIG 85. FRAME WEB FABRICATED AND INSTALLED ON NDT CLEARANCE. APPROVED 8110 I SSUED FOR REPAIR.

Part: FRAME — CRACKED (FUSELAGE) · airframe 62,800 hrs · 15,449 cycles

INSPECTION TYPE:C, NRC 44298765 CRACK FOUND IN O/B FLANGE OF FRAME BETWEEN STR 9 - 10 RT AT BS 500. REPAIR CARRIED OUT IAW SRM 53-10-06 AND QUERY NOTE 34/2000 MANUFACTURE NEW FRAME SEGMENT REF APPROVED 8110.

Part: RIB — CRACKED (HORIZONTAL STAB) · airframe 62,800 hrs · 15,449 cycles

INSPECTION TYPE:C, TAIL CRACK IN LOWER CHORD ON RT HORIZONTAL STABILIZER T/E RIB AT STAB BL 380. NEW RIB FABRICATED IAW E0145283 AND FITTED IAW SRM 51-30-02.

Part: WEB — CRACKED (FUSELAGE) · airframe 62,800 hrs · 15,449 cycles

INSPECTION TYPE:C, CRACKS FOUND IN FRAME OUTER FLANGE BETWEEN STRINGER 9 - 10 RT BS 520. REPAIR CARRIED OUT IAW QUERY NOTE 21/2000 AND SRM 53-10-04. FABRICATED DOUBLERS AND INSTALLED ON NDT INSP CLEARANCE. APPROVED 8110 ISSUED FOR REPAIR.

Part: SEAT TRACK — CRACKED (FUSELAGE) · airframe 62,800 hrs · 15,449 cycles

INSPECTION TYPE:C, MAIN DECK SEAT TRACK IS CRACKED AT BS 440 AND 460 RBL 64. SECTION OF SEAT TRACK FROM BS 430 - BS 460 REPLACED IAW SRM 53-10-05 FIG 1A DETAIL 4.

Part: INTAKE DUCT — CRACKED (APU) · airframe 62,800 hrs · 15,449 cycles

INSPECTION TYPE:C, TAIL CRACK IN APU AIR INTAKE LIP. REPAIRED IAW SRM 51-40-09.

Part: STRUCTURE — CRACKED (PAX DOOR) · airframe 62,800 hrs · 15,449 cycles

INSPECTION TYPE:C, NR 4 MED RT CRACKED AT LWR FWD CORNER. NR 4 MED REMOVED IAW MM 52-11-01 AND ROUTED TO S/M SHOP NR 4 MED REFITTED IAW MM 52-11-01.

Part: INTERCOSTAL — CRACKED (FUSELAGE) · airframe 62,800 hrs · 15,449 cycles

INSPECTION TYPE:C, CONTROL CABIN INTERCOSTAL IS CRACKED BETWEEN FUSELAGE FRAMES BS 360 TO 380 BETWEEN STRINGERS 1 AND 2 RT. NEW INTERCOSTAL FABRICATED IAW E0145236 AND INSTALLED IAW SRM 51-30-02.

Part: FLANGE — CORRODED (WING TO BODY) · airframe 62,800 hrs · 15,449 cycles

INSPECTION TYPE:C, FUSELAGE CORROSION ON WING TO BODY FAIRING SUPPORT FWD FLANGE AT BS 1000 RBL 10. FAIRING SUPPORT FLANGE REPAIRED IAW SRM 51-40-04 FIG 2.

Part: FRAME — CRACKED (FUSELAGE) · airframe 62,800 hrs · 15,449 cycles

INSPECTION TYPE:C, CONTROL CABIN FUSELAGE FRAME WEB IS CRACKED AT INNER FLANGE AT BS 360 STR 2A RT. REPAIR CARRIED OUT IAW Q/NOTE 17 /2000 AND SRM 53-10-04 FIG 18. STOP DRILLED CRACKS AND FABRICATED NEW REPAIR DOUBLERS ON NDT INSP CLEARANCE FITTED DOUBLERS. APPROVED 8110 ISSUED FOR REPAIR.

Part: FLOOR SUPPORT — CRACKED (FUSELAGE) · airframe 62,800 hrs · 15,449 cycles

INSPECTION TYPE:C, BULK CARGO HOLD FLOOR SUPPORT LONGTITUDINAL BEAMS CRACKED IN TWO PLACES BS 2020 BL 0 BS 1988 LBL 30. FLOOR SUPPORT BEAMS REPAIRED IAW SRM 53-10-07.

Part: STRAP — CORRODED (FUSELAGE) · airframe 62,800 hrs · 15,449 cycles

INSPECTION TYPE:C, CONTROL CABIN STIFFENER STRAP IS CORRODED ON INNER FLANGE OF FRAME AT BS 320 BETWEEN STRINGER 2A AND WINDOW FRAME RT. STRAP REPLACED IAW SRM 51-30-02.

Part: ANGLE — CRACKED (NACELLE) · airframe 62,800 hrs · 15,449 cycles

INSPECTION TYPE:C, 2 CRACKS CONFIRMED AND END OF CRACKS MARKED IN FRAME AT 12 O''CLOCK POSITION NAC STA 222 FWD OF BULKHEAD. REPAIR CARRIED OUT IAW QUERY NOTE 9/2000 AND SRM 54-14-03 FIG 13. TRIMMED OUT CRACKED FRAME FLANGE AND FABRICATE/ INSTALL FILLERS AND REPAIR ANGLES. APPROVED 8110 ISSUED FOR THIS REPAIR.

Part: FRAME — CRACKED (FUSELAGE) · airframe 62,800 hrs · 15,449 cycles

INSPECTION TYPE:C, UPPER DECK FRAME WEB IS CRACKED AT I/B END BETWEEN STRS 2 AND 2A LT BS 360. REPAIR CARRIED OUT IAW QUERY NOTE 18/2000 AND SRM 51-10-02 CRACKED SEGMENT. REMOVED REPAIR DOUBLERS, INSTALLED ON NDT INSP CLEARANCE APPROVED 8110 ISSUED FOR REPAIR.

Part: FRAME — CRACKED (FUSELAGE) · airframe 2,800 hrs · 15,449 cycles

INSPECTION TYPE:C, UPPER DECK CRACK IN FUSELAGE FRAME WEB AT BS 360 I/B OF STRINGER 6 LT. REPAIR CARRIED OUT IAW QUERY NOTE 18 /2000 AND SRM 51-10-06 AND SRM 51-30-02. CUT OUT DAMAGED SEGMENT, INSTALL FABRICATED REPAIR DOUBLERS AFTER HEAT TREATMENT AND NDT INSPS APPROVED 8110 ISSUED FOR REPAIRS.

Part: FRAME — CRACKED (FUSELAGE) · airframe 2,800 hrs · 15,449 cycles

INSPECTION TYPE:C, UPPER DECK CRACK IN FUSEAGE FRAME WEB AT CUTOUT AT BS 360 STR 3 LT. REPAIR CARRIED OUT IAW QUERY NOTE 18 /2000 AND SRM 51-10-06 AND SRM 51-30-02. CUT OUT DAMAGED SEGMENT AND INSTALLED FABRICATED DOUBLERS AFTER HEAT TREATMENT AND NDT INSP, APPROVED 8110 ISSUED FOR REPAIR.

Part: FRAME — CRACKED (FUSELAGE) · airframe 2,800 hrs · 15,449 cycles

INSPECTION TYPE:C, UPPER DECK FRAME WEB IS CRACKED ON INNER FLANGE AT BS 500 STR 8 RT. REPAIR CARRIED OUT IAW QUERY NOTE 34/2000 AND SRM 51-10-06. TRIMMED OUT FRAME DAMAGED SEGMENT AND FABRICATED NEW FRAME SEGMENT APPROVED 8110 ISSUED FOR REPAIR.

Part: FRAME — CRACKED (FUSELAGE) · airframe 62,800 hrs · 15,449 cycles

INSPECTION TYPE:C, UPPER DECK FUSELAGE FRAME WEB IS CRACKED AT CUTOUT FOR STRINGER AT BS 500 AT STR 10 RT. REPAIR CARRIED OUT IAW QUERY NOTE 34/200 AND SRM 51-10-06. TRIM OFF FRAME SEGMENT AND FABRICATE DOUBLER PENETRANT INSP ALL NEW PARTS APPROVED 8110 ISSUED FOR REPAIR.

Part: FRAME — CRACKED (FUSELAGE) · airframe 62,800 hrs · 15,449 cycles

INSPECTION TYPE:C, UPPER DECK FRAME WEB IS CRACKED AT OUTER FLANGE AT BS 520 BETWEEN STRINGERS 7/8 RT. REPAIR CARRIED OUT IAW QUERY NOTE 21 /2000 AND SRM 53-10-04. TRIM OFF FLANGES AND FABRICATE DOUBLERS, ON NDT CLEARANCE INSTALL DOUBLERS APPROVED 8110 ISSUED FOR REPAIR.

Part: FRAME — CRACKED (FUSELAGE) · airframe 62,800 hrs · 15,449 cycles

INSPECTION TYPE:C, UPPER DECK FRAME WEB IS CRACKED AT I/B END BETWEEN STRINGERS 0 AND 1 LHS BS 360. REPAIR CARRIED OUT IAW Q/NOTE 18/2000 AND SRM 51-10-02 AND 51-30-02. REMOVED DAMAGED SEGMENT AND FABRICATED TWO DOUBLERS ON NDT INSP CLEARANCE INSTALL DOUBLERS.

Part: FRAME — CRACKED (FUSELAGE) · airframe 62,800 hrs · 15,449 cycles

INSPECTION TYPE:C, UPPER DECK FRAME WEB IS CRACKED AT CUTOUT FOR STRINGER BS 480 STR 11 RT. REPAIR CARRIED OUT IAW Q/NOTE 23/2000 AND SRM 53-10-04 FIG 22. WEB DAMAGE TRIMMED OUT AND REPAIR DOUBLER INSTALLED, APPROVED 8110 ISSUED FOR REPAIR.

Part: FRAME — CRACKED (FUSELAGE) · airframe 62,800 hrs · 15,449 cycles

INSPECTION TYPE:C, UPPER DECK FUSELAGE FRAME WEB IS CRACKED AT CUTOUT FOR STRINGER AT BS 460 STRINGER 14 RT. REPAIR CARRIED OUT IAW Q/NOTE 27 /2000 AND SRM 51-10-02. TRIMMED OUT CRACK AND INSTALLED DOUBLER REPAIR APPROVED 8110 ISSUED FOR REPAIR.

Part: FRAME — CRACKED (FUSELAGE) · airframe 2,800 hrs · 15,449 cycles

INSPECTION TYPE:C, UPPER DECK FRAME WEB IS CRACKED AT CUTOUT FOR STRINGER AT BS 500 STR 11 RT. FRAME REPAIRED IAW WITH QUERY NOTE 34 /2000 AND SRM 51-10-06 NEW FRAME SEGMENT FABRICATED AND INSTALLED NEW FRAME SEGMENT, APPROVED 8110 ISSUED.

Part: FRAME — CRACKED (FUSELAGE) · airframe 2,800 hrs · 15,449 cycles

INSPECTION TYPE:C, UPPER DECK FUSELAGE FRAME WEB IS CRACKED AT CUTOUT FOR STRINGER AT BS 520 STR 11 RT. REPAIR CARRIED OUT IAW QUERY NOTE 21/2000 AND SRM 51-40-02. TRIM OFF SKIN ATTACHMENT FLANGE AND INSTALL DOUBLERS. APPROVED 8110 ISSUED FOR TASK.

Part: FRAME — CRACKED (FUSELAGE) · airframe 62,800 hrs · 15,449 cycles

INSPECTION TYPE:C, UPPER DECK FRAME IS CRACKED AT BS 460 BETWEEN STR 11 AND 12 LT. REPAIR CARRIED OUT IAW Q/NOTE 22/2000 AND SRM 51-10-01 AND SRM 53-10-04 FIG 20. STOP DRILLED CRACKS, NDT INSP FABRICATED DOUBLERS AND INSTALLED ON NDT CLEARANCE APPROVED 8110 ISSUED FOR REPAIR.

Part: FRAME — CRACKED (FUSELAGE) · airframe 2,800 hrs · 15,449 cycles

INSPECTION TYPE:C, UPPER DECK FUSELAGE FRAME WEB IS CRACKED AT CUTOUT FOR STRINGER AT BS 480 STRINGER 10 A RT. REPAIR CARRIED OUT IAW QUERY NOTE 23/2000 AND SRM 53-10-04 FIG 22. CUTOUT FRAME WEB DAMAGED AREA AND INSTALL FABRICATED DOUBLER APPROVED 8110 ISSUED FOR REPAIR.

Part: SHEAR TIE — CRACKED (FUSELAGE) · airframe 62,800 hrs · 15,449 cycles

INSPECTION TYPE:C, AFT CARGO HOLD, FRAME SHEAR TIE CORRODED BS 1780 STRINGER 45 AND 46 RIGHT. SHEAR TIE REPLACED IAW SRM 51-30-02.

Part: FRAME — CRACKED (FUSELAGE) · airframe 62,800 hrs · 15,449 cycles

INSPECTION TYPE:C, UPPER DECK FRAME WEB IS CRACKED AT CUTOUT FOR STR AT BS 480, 12 RT. REPAIR CARRIED OUT IAW QUERY NOTE 23/2000 AND SRM 53-10-04 FIG 22. TRIMMED OUT DAMAGED AREA AND FABRICATED REPAIR DOUBLERS, APPROVED 8110 ISSUED FOR REPAIR.

Part: FRAME — CRACKED (FUSELAGE) · airframe 2,800 hrs · 15,449 cycles

INSPECTION TYPE:C, UPPER DECK CRACK IN FUSELAGE AT FRAME DOUBLER AT CUTOUT FOR STRINGER AT BS 360 STR 11 LT. REPAIR CARRIED OUT IAW QUERY NOTE 18/2000 AND SRM 51-30-02 AND 51-1 0-06. REMOVE FRAME SEGMENT AND INSTALL TWO FABRICATED WEB PIECES AFTER HEAT TREAT AND NDT INSP APPROVED 8110 ISSUED FOR REPAIR.

Part: STRUCTURE — CRACKED (FUSELAGE) · airframe 2,800 hrs · 15,449 cycles

INSPECTION TYPE:C, CRACK CONFIRMED AT BS 460 STR 15 RT. REPAIR CARRIED OUT IAW Q/NOTE 27/00 AND SRM 51-30-02. TRIMMED OUT DAMAGED AREA AND REFIT IAW REPAIR 8110 ISSUED FOR REPAIR.

Part: FRAME — CRACKED (FUSELAGE) · airframe 2,800 hrs · 15,449 cycles

INSPECTION TYPE:C, UPPER DECK FRAME WEB IS CRACKED AT OUTER FLANGE BETWEEN STRINGERS 8 AND 9 RT BS 500. REPAIR CARRIED OUT IAW QUERY NOTE 34/2000 AND SRM 53-10-06. FRAME SEGMENT TRIMMED OUT NEW SEGMENT FABRICATED NDT INSPECTED AND INSTALLED APPROVED 8110 ISSUED FOR THIS REPAIR.

Part: ANGLE — CRACKED (FUSELAGE) · airframe 62,800 hrs · 15,449 cycles

INSPECTION TYPE:C, FWD CARGO CRACK FOUND IN ANGLE AT BS 486 STR 26 LT ANGLE. REPLACED IAW SRM 51-30-02.

Part: FRAME — CRACKED (FUSELAGE) · airframe 2,800 hrs · 15,449 cycles

INSPECTION TYPE:C, UPPER DECK FRAME WEB IS CRACKED AT CUTOUT FOR STRINGER AT BS 360 STRINGER 3 RT. REPAIR CARRIED OUT IAW Q/NOTE 17 /2000 AND SRM 53-10-04 FIG 18. FABRICATE DOUBLER AND INSTALL, APPROVED 8110 ISSUED FOR THIS TASK.

Part: FRAME — CRACKED (FUSELAGE) · airframe 2,800 hrs · 15,449 cycles

INSPECTION TYPE:C, MAIN DECK FUSELAGE FRAME WEB IS CRACKED AT CUTOUT FOR STRINGER AT BS 500 STR 16 LT. REPAIR CARRIED OUT IAW Q/NOTE 25/2000 AND SRM 51-10-06 AND SRM 51-30-02. REPAIR DOUBLERS INSTALLED AND HOLES OPENED UP FROM .1562 TO .1875 PLEASE NOTE THAT SUBJECT FRAME IS TO BE REPLACED PER SB 747-53- 2272 AT OR PRIOR TO 20000 FLIGHT CYCLES APPROVED 8110 ISSUED.

Part: FRAME — CRACKED (FUSELAGE) · airframe 2,800 hrs · 15,449 cycles

INSPECTION TYPE:C, MAIN DECK FUSELAGE FRAME WEB IS CRACKED AT CUTOUT FOR STRINGER AT BS 480 STR 15 RT. REPAIR CARRIED OUT IAW Q/NOTE 28 /2000 ALSO SRM 53-10-04 FIG 23. CRACKED FRAMES STOP DRILLED AND REPAIR DOUBLERS INSTALLED APPROVED 8 110 ISSUED.

Part: STRAP — BROKEN (FUSELAGE) · airframe 62,800 hrs · 15,449 cycles

INSPECTION TYPE:C, UNDERFLOOR - FRAME TIE-DOWN STRAP BROKEN, FWD OF RT OUTFLOW VALVE. NEW TIE-DOWN STRAP FABRICATED AND INSTALLED PER SRM 51-30-02 AND SRM 51-30-1.

Part: FRAME — CRACKED (FUSELAGE) · airframe 2,800 hrs · 15,449 cycles

INSPECTION TYPE:C, UPPER DECK FRAME WEB IS CRACKED AT INNER FLANGE AT BS 380 STR 6 RT. REPAIR CARRIED OUT IAW QUERY /NOTE 12/2000 AND SRM 53-10-04 FIG 98 DETAIL 3. CONTINUED INSPECTION OF AFFECTED AREA PER SB 53A2265 IS REQUIRED, DOUBLER REPAIR.

Part: HARNESS — ARCED (FUSELAGE) · airframe 62,800 hrs · 15,449 cycles

INSPECTION TYPE:C, FWD CARGO HOLD - CABLE LOOM PASSING THROUGH FRAME AT BS 520, RBL 24 SHOWS EVIDENCE OF ARCING. ACCOMPLISHED PER QUERY NOTE 35/2000 WHICH ASKS FOR WIRES TO BE REMOVED AS SYSTEM IS INACTIVE. WIRES REMOVED FROM CB C914 IN P14 PANEL TO RELAY R175 IN PANEL P86, AT FWD CARGO DOOR PER WDM 24-51-72.

Part: BEAM — CRACKED (FUSELAGE) · airframe 62,800 hrs · 15,449 cycles

INSPECTION TYPE:C, FWD CARGO - CRACK IN STIFFENER ON TOP OF NWW AT BS 300 RBL 22. REPLACED STIFFENER IAW SRM 51-30-02.

Part: SKIN — CORRODED (CENTER WING) · airframe 62,800 hrs · 15,449 cycles

INSPECTION TYPE:C, RT WING L/E BULGING ON L/E LOWER FALSE WORK PANEL AT OLES 1430 AND 1532. REPAIRED IAW QUERY NOTE 13 /2000 AND SRM 57-30-03 FIG 9. CUT OUT DAMAGED AREA AND INSTALLED DOUBLER.

Part: WEB — CRACKED (FUSELAGE) · airframe 62,800 hrs · 15,449 cycles

INSPECTION TYPE:C, MAIN DECK OUTER FLANGE OF CREASE BEAM WEB STRINGER 26 IS CRACKED AT BS 320-340 RT SIDE. CREASE BEAM REPAIRED IAW QUERY NOTE 40 /2000 AND SRM 51-40-03. REMOVED DAMAGED AREAS AND INSTALLED DOUBLERS AS REQUIRED.

Part: FRAME — CRACKED (FUSELAGE) · airframe 62,800 hrs · 15,449 cycles

INSPECTION TYPE:C, MAIN DECK FRAME WEB IS CRACKED AT CUT OUT FOR STR AT BS 420 STRINGER 16 - 17. ALSO DAMAGE AT STR 1 - 14 RT. REPAIR CARRIED OUT IAW Q/NOTE 32 /200 SRM 53-10-04 FIG 22 MANUFACTURED TWO REPAIR DOUBLERS AND INSTALLED ON FWD SIDE OF FRAME, APPROVED 8110 ISSUED.

Part: FRAME — CRACKED (FUSELAGE) · airframe 62,800 hrs · 15,449 cycles

INSPECTION TYPE:C, MAIN DECK FUSELAGE MAIN FRAME IS CRACKED AT STRINGER CUTOUT AT BS 520 STR 25 RT. REPAIR CARRIED OUT IAW QUERY NOTE 46/2000 AND SRM 51-40-02. STOP DRILLED CRACKS AND INSTALLED REPAIR DOUBLERS APPROVED 8110 ISSUED FOR REPAIR.

Part: WEB — CRACKED (FUSELAGE) · airframe 62,800 hrs · 15,449 cycles

INSPECTION TYPE:C, MAIN DECK FUSELAGE FRAME WEB IS CRACKED AT BS 240 STR 13 LT. REPAIR CARRIED OUT IAW SRM 5310-04 FIG 14 AND QUERY NOTE 24 /2000, CUT OUT DAMAGED AREA AND INSTALLED DOUBLERS AS REQUIRED 8110 ISSUED FOR REPAIR.

Part: ANGLE — CRACKED (FUSELAGE) · airframe 62,800 hrs · 15,449 cycles

INSPECTION TYPE:C, MAIN DECK OUTER FLANGE OF CREASE BEAM WEB STR 26 IS CRACKED AT BS 360 - 380 RT SIDE. CREASE BEAM FLANGE REPAIRED IAW QUERY NOTE 40/2000 AND SRM 51-40-03. CUT SKIN FLANGE FROM SHEAR TIES AND FABRICATE REPAIR ANGLE. INSTALLED REPAIR ANGLE.

Part: RIVET — LOOSE (KRUGER FLAP) · airframe 62,800 hrs · 15,449 cycles

INSPECTION TYPE:C, LOOSE RIVETS IN TORQUE TUBE DRIVES AT VARIOUS LOCATIONS I/B END NR 15 KRUEGER FLAP, I/B AND O/B OF NR 1 L/E PDU, I/B AND O/B OF NR 3 PDU RT, OUTPUT OF L/E NR 4 PDU, I/B AND O/B OF NR 3 LT PDU, TORQUE TUBE AT NR 5 VCF, TORQUE TUBE AT NR 4 VCF, NR 3 VCF, NR 10 VCF TORQUE TUBES REPLACED IAW 27-81-05.

Part: WEB — CRACKED (FUSELAGE) · airframe 62,800 hrs · 15,449 cycles

INSPECTION TYPE:C, MAIN DECK FUSELAGE FRAME WEB IS CRACKED AT CUTOUT FOR STRINGER AT BS 360 STR 14 LT. REPAIR CARRIED OUT IAW QUERY NOTE 33/2000 AND SRM 5310-04 FIG 23. CUT OUT DAMAGED AREA AND INSTALLED DOUBLERS AS REQUIRED, APPROVED 8110 ISSUED FOR REPAIR.

Part: FRAME — CORRODED (RT WING) · airframe 62,800 hrs · 15,449 cycles

INSPECTION TYPE:C, RT WING L/E CORROSION ON WING BULL NOSE AT CONNECTION FOR WAI VLV. REPAIR CARRIED OUT IAW QUERY NOTE 42/2000 AND SRM 51-40-04 FIG 1 AND SRM 57-10-03 FIG 7. CUT OUT CORRODED AREA AND INSTALLED SPLICE SECTION OF CHORD.

Part: WEB — CRACKED (FUSELAGE) · airframe 62,800 hrs · 15,449 cycles

INSPECTION TYPE:C, MAIN DECK OUTER FLANGE OF CREASE BEAM WEB STR 26 IS CRACKED AT BS 34 0 - 360 LT SIDE. CREASE BEAM FLANGE REPAIRED IAW QUERY NOTE 40/2000 AND SRM 51-40-03. REMOVED DAMAGED AREA AND INSTALLED DOUBLERS AS REQUIRED.

Part: WEB — CRACKED (FUSELAGE) · airframe 62,800 hrs · 15,449 cycles

INSPECTION TYPE:C, MAIN DECK OUTER FLANGE OF CREASE BEAM WEB IS CRACKED AT STRINGER 26 BS 320 - 340 LT SIDE. CREASE BEAM FLANGE REPAIRED IAW QUERY NOTE 40 /2000 AND SRM 51-40-03, REMOVED DAMAGED AREA AND INSTALLED DOUBLERS AS REQUIRED.

Part: FRAME — CRACKED (FUSELAGE) · airframe 62,800 hrs · 15,449 cycles

INSPECTION TYPE:C, FUSELAGE FRAME WEB IS CRACKED AT CUTOUT FOR STRINGER AT BS 300, STR 13 RT. REPAIRED CRACKED FRAME IAW SRM 51-10-06 AND 51-30-02 AND QUERY NOTE 31/200. STOP DRILLED CRACKS AND DOUBLER, INSTALLED ON FWD FACE OF FRAME APPROVED 8110 ISSUED FOR THIS TASK.

Part: FRAME — CRACKED (FUSELAGE) · airframe 62,800 hrs · 15,449 cycles

INSPECTION TYPE:C MAIN DECK FRAME WEB IS CRACKED AT CUTOUT FOR STRINGER AT BS 420 STRINGER 15 RT SIDE. REPAIR CARRIED OUT IAW QUERY NOTE 32/2000 ALSO SRM 53-10-04 FIG 22. REPAIR DOUBLER FABRICATED AND INSTALLED ON FRAME, APPROVED 8110 ISSUED FOR REPAIR.

Part: FRAME — CRACKED (FUSELAGE) · airframe 62,800 hrs · 15,449 cycles

INSPECTION TYPE:C NRC 44296099, MAIN DECK FRAME WEB IS CRACKED AT CUT OUT FOR STRINGER BS 320 STRINGER 16 RT. REPAIR CARRIED OUT IAW SRM 53-10-04 FIG 18. ALSO, QUERY NOTE 30/2000 STOP DRILLED CRACKS AND INSTALLED DOUBLERS, APPROVED 8110 ISSUED.

Part: ANGLE — CRACKED (FUSELAGE) · airframe 62,800 hrs · 15,449 cycles

INSPECTION TYPE:C, MAIN DECK OUTER FLANGE OF CREASE BEAM WEB STRINGER 26 IS CRACKED AT BS 400 TO 420 RT SIDE. CREASE BEAM FLANGE REPAIRED IAW QUERY NOTE 40/2000 AND SRM 51-40-03. CUT SKIN FLANGE FROM SHEAR TIES AND FABRICATE REPAIR ANGLE, INSTALLED ANGLE.

Part: BEAM — CRACKED (FUSELAGE) · airframe 62,800 hrs · 15,449 cycles

INSPECTION TYPE:C, MAIN DECK OUTER FLANGE OF CREASE BEAM WEB AT STR 26 IS CRACKED AT BS 340 - 360 RT SIDE. CREASE BEAM FLANGE REPAIRED IAW QUERY NOTE 40/2000 AND SRM 51-40-03. REMOVED DAMAGED AREAS AND INSTALLED DOUBLERS AS REQUIRED.

Part: WEB — CRACKED (FUSELAGE) · airframe 62,800 hrs · 15,449 cycles

INSPECTION TYPE:C, MAIN DECK OUTER FLANGE OF LOWER CREASE BEAM WEB STR 26 IS CRACKED AT BS 400 LT SIDE. CREASE BEAM FLANGE REPAIRED IAW QUERY NOTE 40/2000 AND SRM 51-40-03. REMOVED DAMAGED AREA AND INSTALLED DOUBLERS AS REQUIRED.

Part: SUPPORT BRACKET — CRACKED (WING TO BODY) · airframe 62,800 hrs · 15,449 cycles

INSPECTION TYPE:C, FUSELAGE WING TO BODY FAIRING SUPPORT CRACKED AT BS 1265 BELOW REAR SPAR SPLICE LT. DAMAGE REMOVED AND REPAIR CARRIED OUT IAW SRM 51-40-03 FIG 1.

Part: SUPPORT BRACKET — CRACKED (WING TO BODY) · airframe 62,800 hrs · 15,449 cycles

INSPECTION TYPE:C, FUSELAGE WING TO BODY FAIRING SUPPORT CRACKED AT BS 1265 BELOW LOWER REAR SPAR SPLICE. DAMAGE REMOVED AND REPAIR CARRIED OUT IAW SRM 51-40-03 FIG 1.

Part: SKIN — CRACKED (FUSELAGE) · airframe 62,800 hrs · 15,449 cycles

INSPECTION TYPE:C, SKIN CRACK THROUGH FASTENER HOLE BETWEEN STRINGER 44L AND STR 45L AT BS 400. REPAIR CARRIED OUT IAW QUERY NOTE 6/2000 AND SRM 53-30-03. STOP DRILLED CRACK AND EDDY CURRENT INSP HOLE SKIN REPAIR CARRIED OUT.

Part: CHANNEL — CORRODED (RT WING) · airframe 62,800 hrs · 15,449 cycles

INSPECTION TYPE:C, RT WING L/E CORROSION ON L/E LOWER FALSE WORK PANEL FWD OF SUPP CHANNEL AT SEVERAL LOCATIONS AT OLES 1066 OUT TO NR 4 ENG. REPAIR CARRIED OUT IAW QUERY NOTE 4/2000 AND SRM 51-30-01 AND 51-30 -06. REMOVED CORRODED BEAM SECTION AND SPLICE IN NEW SECTION OF BEAM APPROVED 8110 ISSUED FOR REPAIR.

Part: STRAP — CORRODED (RT WING) · airframe 62,800 hrs · 15,449 cycles

INSPECTION TYPE:C, RT WING L/E CORROSION ON L/E LOWER IN SPAR SKIN EXT AT OLES 1116 RT. REPAIR CARRIED OUT IAW Q/NOTE 8/2000 AND SRM 57-30-03 FIG 4. BLENDED OUT CORROSION / SPLICE REPAIR.

Part: CHANNEL — CORRODED (RT WING) · airframe 62,800 hrs · 15,449 cycles

INSPECTION TYPE:C, RT WING L/E CORROSION ON L/E FALSE WORK SUPPORT CHANNEL AT OLES 1373 4 AND OLES 1444. CORROSION REMOVED DEPTH 10, AREA RE-PROTECTED IAW SRM 51-10-02.

Part: PANEL — CORRODED (RT WING) · airframe 62,800 hrs · 15,449 cycles

INSPECTION TYPE:C, RIGHT WING L/E LOWER FALSE WORK PANEL IS BULGING AT O/B WING JACK PAD LOCATION. REPAIR CARRIED OUT IAW QUERY NOTE 7/2000 AND SRM 57-30-01 AND 57-30-03. BLENDED OUT CORRODED AREA AND INSTALLED FILLER AND RETURNED AREA TO ORIGINAL DIMENSIONS.

Part: FLOORBEAM — CORRODED (FUSELAGE) · airframe 62,800 hrs · 15,449 cycles

INSPECTION TYPE:C, MAIN DECK CORROSION ON UPPER DECK FLOORBEAM WEB AT BS 460 RBL 60. REPAIRED IAW QUERY NOTE N521 UP/3/2000 AND SRM 53-10-07 FIG 11. CUT OUT CORRODED AREA AND SPLICED IN FABRICATED WEB. APPROVED 8110 ISSUED FOR THIS REPAIR.

Part: FIRE BOTTLE — DISCHARGED (ENGINE)

BOTTLE SQUIB TEST INOP. REMOVED AND REPLAECD ENG FIRE BOTTLE, ACCOMPLISHED CK OF SQUIB IAW MM 26-20. OP CK OK. THIS CLEARS MEL M184995.

Part: SQUIB — INOPERATIVE (FIRE BOTTLE)

NR 4 LT FIRE BOTTLE SQUIB TEST INOP.

Part: ACTUATOR — FAILED (NR 6 SPOILER)

INSPECTION TYPE-2ACK, NR 6 SPOILER ACTUATOR ROD BROKEN. THIS DISCREPANCY FOUND WHEN SPOILER LOCKS WERE INSTALLED FOR SCHEDULED 2A CHECK. WHEN HYDRAULIC PRESSURE WAS PUT ON SYSTEM, ACTUATOR ROD FAILED. SUSPECT THAT THE ROD HAD A PRE-EXISTING CRACK. SPOILER ACTUATOR WAS REMOVED AND REPLACED PER M/M 27-62-00.

Part: STRINGER — CRACKED (BS 260)

INSPECTION TYPE-N/A, S41 HAS 3 INCH CRACK AT STATION 260 RIGHT SIDE NOSE WHEEL WELL BOX WHERE IT ATTACHES TO CLIP. REMOVED CRACKED STRINGER, FABED NEW PART, INSTALLED APPLIED SEALANT PER EO 8934 D.

Part: BRAKES — OUT OF ADJUST (LANDING GEAR)

INSPECTION TYPE-N/A, ALL BRAKE SYSTEM CABLES HAVE SLACK, NO BRAKE ACTION AFTER A/C ARRIVED ANC. HYD BRAKE SYSTEM ADJ AND TEST C/W MM REF 32-41-00 PG 501.

Part: BATTERY PACK — DISCHARGED (CREW SERV DOOR)

INSPECTION TYPE:ASE BATTERY VERY LOW CHARGE NOTE: BATTERY FOR CREW SVCS DOOR EMERGENCY LIGHTS. REMOVED AND REPLACED BATTERY. OPS GOOD PER MM 25-60-00.

Part: BATTERY PACK — DISCHARGED (CABIN)

INSPECTION TYPE-N/A, UPPER DECK AFT TWO EMERGENCY LIGHTS INOP. REMOVED AND REPLACED UPPER DECK AFT EMERGENCY LIGHT BATTERY PACK PER B747 M/M 33-51-04 AT STA 650 M335 POWER SUPPLY.

Part: GUIDE VANE — CRACKED (NR 1 ENGINE)

ENG FAN EXIT GUIDE VANE HAS TWO CRACKS 1 APPX .125 INCH LONG 1 APPX .25 INCH LONG. BOTH HAVE DEFLECTION. NR 1 ENG FAN EXIT GUIDE VANE DAMAGE BEYOND LIMITS AND REMOVED FROM ENGINE AS PER MM 72-34-05.

Part: FRAME — CORROSION (CARGO DOORWAY)

INSPECTION TYPE-N/A, AFT LOWER CARGO DOOR FRAME WEB HAS HOLE FROM CORROSION. LOWER FWD DOOR FRAME APPROX 18 IN UP FROM LOWER FWD CORNER. REMOVED CORROSION FROM WEB. MEASURED AMOUNT REMOVED WAS FOUND TO BE .025, REQ DOUBLER INST. INSTALLED WEB REPAIR IAW 53-10-04.