N681UP

Part: BATTERY PACK — INOPERATIVE (EMERGENCY EXIT)

UPPER HALLWAY EMERGENCY LIGHT BATTERY PACK INOP. REMOVED AND REPLACED EMERGENCY BATTERY PACK IAW AMM 33-51-00. OPS CK NORMAL.

Part: CONTROL PANEL — MALFUNCTIONED (EMERGENCY LIGHT)

INSPECTION TYPE:PFLT ON PRE FLT, FOUND EMERG EXIT LT PANEL UNARMED LT ILLUM WITH SWITCH IN ARMED POS. REMOVED AND REPLACED EMERG LT PANEL ON OVERHEAD. OPS CK GOOD IAW MM 33-51-00.

Part: SPOILER — INOPERATIVE (NR 5)

DIVERSION, NR 5 SPOILER WOULD NOT RETRACT. LEFT WING NR 5 SPOILER ROD AND TRAILING EDGE SUPPORT. A/C FERRIED TO SDF FOR REPAIR. STARTED ECA FORM 011205 COMPLETED. THIS CLEARS D331371.

Part: SKIN — WORN (NR 4 PYLON)

NR 4 PYLON INNER VERT WEB O/B SIDE SKIN WORN THROUGH GREATER THAN 50% OF THICKNESS ALONG THE ENTIRE LENGTH DUE TO CONTACT WITH THE CORE COWL. FABRICATED REPAIR DOUBLER FROM .125 2025-T3, DRILLED AND COUNTERSUNK PER B747 SRM 54-30-03 FIG 35 AND 36. INSTALLED FABRICATED DOUBLER, HI LOCKS AND RIVETS PER SRM 54-30-03.

Part: SKIN — WORN (NR 4 NACELLE)

NR 4 PYLON INSIDE VERT WEB INBD SKIN WORN THROUGH AT AFT END PEELING AND MISSING AT FWD END. DRILLED OFF INNER STAINLESS AND TRIMMED OUT DAMAGE SKIN 1" BY 9.5". DAMAGE REGLUED. TRIMMED OUT ADDITIONAL DAMAGE. FABRICATED AND DRILLED DOUBLER AND FIRE SHIELD PER SRM 54-30-03 FIG 36. INSTALLED REPAIR PARTS FILLER, DOUBLER AND INNER LINER PER ABOVE REFERENCE.

Part: LIGHT — INOPERATIVE (SPIRAL STAIRWELL)

EMERGENCY LIGHTS ABOVE CREW STAIRS INOP. REMOVED AND REPLACED EMERGENCY LIGHT ASSEMBLY AT SPIRAL STAIRWELL REF UPS 747 M/M CHAP 33-51-04. OPS CHECKED OK.

Part: SUPPORT TUBE — CRACKED (RT WING LE)

RT WING LEADING EDGE TENSION SUPPORT TUBE CRACKED. REMOVED AND REPLACED LEADEING EDGE PANEL SUPPORT TUBE ASSY. IN REF RO STANDARD PRACTICES 20-51-01. OK FOR SERVICE

Part: FLOORBEAM — CRACKED (BS 2060) · airframe 106,939 hrs · 27,146 cycles

BS 2060 RBL 98 FLOOR SUPPORT BRACKET FOUND CRACK, CRACK LENGTH 0.75". SUPPORT BRACKET REPLACED AS PER SRM 51-10-01 PG 9 AND INSTALLED AS PER SRM 51-30-02.

Part: FLOORBEAM — CRACKED (BS 2060) · airframe 106,939 hrs · 27,146 cycles

BS 2060 RBL 60 LATERAL FLOOR SUPPORT LWR SUPT ANGLE FOUND CRACKED, CRACK LENGTH 3" AND 2.5". SUPPORT ANGLE REPLACED AS PER SRM 51-10-01 PG 9 AND INSTALLED AS PER SRM 51-30-02.

Part: FITTING — CHAFED (BS 2598) · airframe 106,939 hrs · 27,146 cycles

FX INTERIOR STRINGER END FTG FOUND DEEP CHAFING MARK AT STA 2598 BHD AFT FACE AT S49L, 51R, 51L TOTAL 3EA. BS 2598 BHD AFT STR 51L, 51R END FTG REPLACED AND INSTALLED AS PER SRM 51-10-01 PG 9 AND 51-30-02, STR 49L SMOOTHED OUT AND REPROTECTED AS PER SRM 51-10-01 AND 51-10-02 WITHIN SRM 53-10-01 FIG 1 LIMIT AND NO CRACK FOUND AFTER HFEC INSP AS PER NTM PT6, 51-00-00 FIG 4 STA 49L END FTG REINSTALLED AS PER SRM 51-30-02.

Part: RIB — CRACKED (LT MLG DOOR) · airframe 106,939 hrs · 27,146 cycles

LT MLG WW I/B DOOR FWD VERTICAL BEAM LOWER RIB FOUND CORROSION CRACKED AT INTERIOR SURFACE, DURING LOWER BEAM REMOVED, CRACK LENGTH 1/2". RIB REPLACED AND INSTALLED AS PER SRM 51-10-01 PG 9 AND 51-30-02.

Part: STRINGER — CRACKED (BS 2598-2600) · airframe 106,939 hrs · 27,146 cycles

FOUND FUSELAGE SKIN REMOVED STRINGER FOUND CRACKED AT STA 2598 TO STA 2600 STR 51R, CRACK LENGTH 1/2". FOUND BS 2598 TO BS 2638 STR 51R REPLACED AS PER SRM 51-10-01 PG 9 AND INSTALLED AS PER SRM 51-30-02.

Part: SKIN — CORRODED (BS 1040-1044) · airframe 106,939 hrs · 27,146 cycles

BS 1040-1044 LBL 123 WING CTR SECTION UPPER FACE FOUND CORROSION. CORROSION BLEND OUT 0.063" BY 4" BY 4" EXCEED SRM 57-30-01 FIG 1 LIMITS, M/D BS 1040-1044 LBL 123" WING CTR SECTION UPPER SKIN REPAIRED AS PER HX RS NR R57-14-35470 AND UPS EO NR B747-5710-24057-A.

Part: FLOORBEAM — CRACKED (BS 600) · airframe 106,939 hrs · 27,146 cycles

BS 600 UPPER DECK FLOORBEAM AFT HORIZ FLANGE FOUND CRACK AT RBL 54, 57 AND 60 APPROX 1/8", 1/8 , 1/16" RESPECTIVELY ALL RUNNING AFT. U/D BS 600 FLOORBEAM AFT HORIZ FLANGE RBL 54, 57 AND 60. REPAIRED AS PER UPS EO NR B747-5310-23043 APPENDIX D FIG 14 PLAN H.

Part: FLOOR SUPPORT — CORRODED (BS 2080-2100) · airframe 106,939 hrs · 27,146 cycles

BS 2080-2100 LBL 98-110 LONGITUDINAL FLOOR SUPPORT FOUND CORROSION. CORROSION BLEND OUT 0.052" BY 1/2" BY 1/2" EXCEED SRM 53-10-01 FIG 1 LIMITS, FLR SUPPORT REPAIRED AS PER SRM 51-40-04 FIG 2.

Part: REVEAL — CRACKED (BS 2231) · airframe 106,939 hrs · 27,146 cycles

BS 2231 STR 24L FOUND 1 HOLE CRACKED AT AFT FRAME INNER CHORD AS MARKED, CRACK LENGTH 3/4" AT REVEAL, 0.030"/0.040" AT CHORD. CABIN BS 2231 AFT FRAME INNER CHORD REPAIRED AT BETWEEN S23L TO STR 26L AREA AS PER SRM 53-10-04 FIG 115 AND REVEAL PANEL REPAIRED AS PER SRM 51-40-02 FIG 1. CONTINUE INSPECTIONS IS REQUIRE REF SRM 53-10-04 FIG 115 TABLE II AND B747-53A2450 FOR REFERENCE.

Part: FLOORBEAM — CORRODED (BS 1200) · airframe 106,939 hrs · 27,146 cycles

BS 1200 LBL 78 TIE DOWN FTG FLANGE FOUND CORRODED. CORROSION BLEND OUT 0.037" BY 3/4" BY 1" EXCEED SRM LIMIT. TIE DOWN FTG REPLACED AS PER MM 53-42-00.

Part: CARGO TRACK — CORRODED (BS 2160) · airframe 106,939 hrs · 27,146 cycles

BS 2160 RBL33 TIE DOWN FTG AFT FLANGE FOUND CORRODED. CORROSION BLEND OUT 0.020" BY 0.5" BY 0.5" EXCEED SRM LIMIT. TIE DOWN FITTING REPLACED AS PER MM 53-42-00.

Part: FLOORBEAM — CORRODED (BS 2240) · airframe 106,939 hrs · 27,146 cycles

BS 2240 LBL 33 TO 75 FLOORBEAM FOUND CORODED. CORROSION BLEND OUT 0.064" BY 2" BY 3" EXCEED SRM 53-10-01 FIG 1 LIMITS, M/D BS 2240 LBL 13 TO LT O/B FLOORBEAM REPAIRED AS PER SRM 51-40-04 FIG 1.

Part: FLOORBEAM — CORRODED (BS 2280) · airframe 106,939 hrs · 27,146 cycles

BS 2280 LBL 74-78 FLOORBEAM FOUND CORODED. CORROSION BLEND OUT 0.062" BY 2" BY 2" EXCEED SRM 53-10-01 FIG 1 LIMITS, M/D - BS 2280 LBL 46 TO MOST LT O/B FLOORBEAM REPAIRED AS PER SRM 51-40-04 FIG 1.

Part: FLOORBEAM — CORRODED (BS 1253) · airframe 106,939 hrs · 27,146 cycles

BS 1253 LBL 11 TO RBL 11 LATERAL FLOOR SUPPORT FOUND CORRODED. CORROSION BLEND OUT 0.045" BY 1.5" BY 2" EXCEED SRM LIMIT. FLOOR SUPPORT REPLACED AS PER SRM 51-10-01 PG9 AND INSTALLED AS PER SRM 51-30-02.

Part: FLOORBEAM — CORRODED (BS 1170) · airframe 106,939 hrs · 27,146 cycles

BS 1170 LBL11 TO RBL11 LATERAL FLOORBEAM FOUND CORRODED. CORROSION BLEND OUT 0.042" BY 3/4" BY 2" EXCEED SRM LIMIT. BS 1170 LBL 11 TO RBL 11 FLOORBEAM REPLACED AND INSTALLED AS PER SRM 51-10-01 PG 9 AND 51-30-02.

Part: FLOORBEAM — CORRODED (BS 2060) · airframe 106,939 hrs · 27,146 cycles

BS 2060 RBL98-116 FLOORBEAM LWR FACE FOUND CORRODED. CORROSION BLEND OUT 0.035" BY 1.5" BY 2" EXCEED SRM LIMIT. FLOORBEAM REPAIRED AS PER SRM 51-40-04 FIG 1 JUST AT BS 2060 RBL40 TO MOST RT O/B.

Part: FLOORBEAM — CRACKED (BS 660) · airframe 106,939 hrs · 27,146 cycles

BS 660 UPPER DECK FLOORBEAM HORIZ FWD FLANGE FOUND CRACKED AT LBL 67" ONE FASTENER HOLE 0.030" IN LENGTH RUNNING FWD O/B AND AT LBL 79" ONE FASTENER HOLE 0.030" IN LENGTH RUNNING AFT. BS 660 FLOORBEAM HORIZ FWD FLANGE LBL 67" & LBL 79" HOLES REPAIRED AS PER UPS EO NR B747-5310-23043 APPENDIX D PLAN A.

Part: CARGO TRACK — CORRODED (BS 2110-2120) · airframe 106,939 hrs · 27,146 cycles

INSPECTION TYPE:C M/D- BS 2110-2120 RBL 33 TIE DOWN TRACK O/B SPLICE FLANGE FOUND COR. CORROSION BLEND OUT 0.031" X 3/4" X 1/2" EXCEED SRM 53-10-01 FIG 1 LIMITS, M/D - BS 2110-2120 RBL 33 TIE DOWN TRACK O/B SPLICE REPLACED AS PER SRM 51-10-01 PG 9

Part: FLOOR SUPPORT — CORRODED (BS 1180) · airframe 106,939 hrs · 27,146 cycles

INSPECTION TYPE:C M/D- BS 1180 LBL 116 LONGITUDINAL FLR SUPPORT FOUND COR. CORROSION BLEND OUT 0.023" X 5/8" X 1.5" EXCEED SRM 53-10-01 FIG 1 LIMITS, THE FLOOR SUPPORT REPAIRED AS PER SRM 51-40-04 FIG 2.

Part: FLOORBEAM — CRACKED (BS 400) · airframe 106,939 hrs · 27,146 cycles

BS 400 UPPER DECK FLOORBEAM FWD HORIZ FLANGE RBL 13" FASTENER HOLE FOUND CRACKED APPROX 0.040" IN LENGTH RUNNING FWD. BS 400 UPPER DECK FLOORBEAM FWD HORIZ FLANGE RBL 13" REPAIRED AS PER UPS EO# B747-5310-23043 APPENDIX D FIG 9 PLAN C.

Part: WEB — CORRODED (BS 1235) · airframe 106,939 hrs · 27,146 cycles

BS 1235-1241 WING CTR SECTION UPPER FACE LBL 12-33 FOUND BULGE UP ( 2 LOCATIONS). CORROSION BLEND OUT 0.140" BY 2.5" BY 6" EXCEED SRM 57-30-01 FIG 1 LIMITS. REPAIR WORK CARRIED OUT AS PER HX RS NR R57-14-35452 & UPS EO NR B747-5710-24065-A.

Part: CARGO TRACK — CORRODED (BS 2020-2040) · airframe 106,939 hrs · 27,146 cycles

BS 2020-2040 RBL 33 TIE DOWN TRACK O/B FLANGE FOUND CORRODED. CORROSION BLEND OUT 0.025" BY 0.5" X 1.5" EXCEED SRM LIMIT. NEW SECTION TIE DOWN TRACK INSTALLED AS PER SRM 53-10-05 FIG1A

Part: LONGERON — CRACKED (BS 1235-1241) · airframe 106,939 hrs · 27,146 cycles

M/D BS 1235-1241 LBL 11 LONGERON LOWER CHORD FOUND CRACK, CRACK LENGTH 3/4". M/DECK BS 1226 TO BS 1241 LBL 11 FLOORBEAM LOWER CHORD REPAIRED AS PER HX RS NR R57-14-35452 REFER NRC NR RH66317 FOR WORKING DETAIL AND UPS EO NR B747-5710-24065-A.

Part: FLOOR SUPPORT — CORRODED (BS 1920-2020) · airframe 106,939 hrs · 27,146 cycles

FOUND BS 1920-2020 LBL 116 LONGITUDINAL FLOOR SUPPORT FOUND CORRODED. CORROSION BLEND OUT 0.016" BY 1/2" BY 20" EXCEED SRM 53-10-01 FIG 1 LIMITS, FLOOR SUPPORT REPLACED AS PER SRM 51-10-01 P9 AND INSTALLED AS PER SRM 51-30-02.

Part: CARGO TRACK — CORRODED (BS 1960) · airframe 106,939 hrs · 27,146 cycles

BS 1960 LBL 76-80 TIE DOWN FTG FLANGE FOUND CORRODED. CORROSION BLEND OUT 0.007" BY 0.5" BY 1" EXCEED SRM LIMIT. TIE DOWN FTG REPLACED AS PER MM 20-51-01.

Part: FLOOR SUPPORT — CORRODED (BS 2020-2040) · airframe 106,939 hrs · 27,146 cycles

FOUND BS 2020-2040 RBL 116 LONGITUDINAL FLOOR SUPPORT CORRODED. CORROSION BLEND OUT 0.016" BY 1" BY 10" EXCEED SRM 53-10-01 FIG 1 LIMITS, FLOOR SUPPORT REPAIRED AS PER SRM 51-40-04 FIG 2.

Part: CARGO TRACK — CORRODED (BS 2090) · airframe 106,939 hrs · 27,146 cycles

BS 2090-2110 LBL 66 TIE DOWN TRACK FLANGE FOUND CORROSION. CORROSION BLEND OUT 0.035" BY 1" BY 1.5" EXCEED SRM 53-10-01 FIG 1 LIMITS, BS 2070 TO BS 2150 LBL 66 TIE DOWN TRACK REPAIRED AS PER SRM 53-10-05 FIG 1A.

Part: SUPPORT — CORRODED (BS 1100) · airframe 106,939 hrs · 27,146 cycles

BS 1100 LBL78-96 LATERAL FLOOR SUPPORT FOUND CORRODED. CORROSION BLEND OUT 0.050" BY 3/8" BY 7/8" EXCEEDED SRM LIMIT. LATERAL FLOOR SUPPORT REPLACED AS PER SRM 51-10-01 P9.

Part: FLOORBEAM — CORRODED (BS 2100) · airframe 106,939 hrs · 27,146 cycles

BS 2100 RBL 98-116 FLOORBEAM FOUND HEAVY CORROSION. CORROSION BLEND OUT 0.060" BY 2" BY 3" EXCEED SRM 53-10-01 FIG 1 LIMITS. BS 2100 RBL 22" TO RT MOST O/B FLOORBEAM REPAIRED AS PER SRM 51-40-04 FIG 1.

Part: CARGO TRACK — CORRODED (BS 1030-1040) · airframe 106,939 hrs · 27,146 cycles

BS 1030-1040 LBL 11 TIE DOWN TRACK FLANGE LWR FACE FOUND CORRODED. CORROSION BLEND OUT 0.077" BY 1" BY 3" EXCEED SRM 53-10-01 FIG 1 LIMIT. BS 1000-1130 LBL 11" TIE DOWN TRACK REPAIRED AS PER SRM 53-10-05 FIG 34.

Part: SUPPORT — CORRODED (BS 1460) · airframe 106,939 hrs · 27,146 cycles

FX KEEL BEAM PANEL SUPPORT LOWER SURFACE FOUND CORROSION AT STA 1460 RBL 16 TO LBL 16 LWR SURFACE. CORROSION BLEND OUT 0.050" BY 1.5" BY 20" EXCEED SRM 53-10-01 FIG 1 LIMITS. THE SUPPORT REPLACED AND INSTALLED AS PER SRM 51-10-01 PG 9 AND 51-30-02.

Part: SUPPORT — CRACKED (BS 1480) · airframe 106,939 hrs · 27,146 cycles

FX REAR BODY FAIRING SUPPORT FRAME FOUND CRACKED AT LT STA 1480 WL 118, CRACK LENGTH 3/8". FUSELAGE BS 1480 LT BODY FAIRING SUPPORT FRAME REPAIRED AS PER SRM 51-40-03 FIG 1.

Part: WEB — CRACKED (NLG WW) · airframe 106,939 hrs · 27,146 cycles

INSPECTION TYPE:C NWW, TOP PANEL WEB BS 269 LBL10 CRACK INDICATION FOUND APPROX 1" LENGTH. NWW TOP PANEL WEB REPAIRED AT BS266-277 LBL5-15 AREA AS PER SRM 53-10-04 FIG 119.

Part: SUPPORT — CRACKED (FUSLEAGE) · airframe 106,939 hrs · 27,146 cycles

INSPECTION TYPE:C NWW LT SIDEWALL PANEL BS305 WL150 1EA FASTENERS HOLE SUPPORT CRACK, CRACK LENGTH 1/16". NWW LHS SIDEWALL PANEL REPAIRED AT BS302-310.5 WL143-156 AREA AS PER SRM 53-10-04 FIG116 SUBSEQUENT INSPECTION ARE NECESSARY FOR CATEGORY B REPAIR REFER TO TABLE 2 FOR INSPECTION REQUIREMENTS.

Part: SUPPORT — CORRODED (BS 1437) · airframe 106,939 hrs · 27,146 cycles

KEEL BEAM PANEL SUPPORT LOWER SURFACE FOUND CORROSION AT STA 1437 RBL 16" TO LBL 16". CORROSION BLEND OUT 0.022" BY 1" BY 20" EXCEED SRM 53-10-01 FIG 1 LIMITS, THE SUPPORT REPLACED AND INSTALLED AS PER SRM 51-10-01 PG 9 AND 51-30-02.

Part: SUPPORT — CORRODED (BS 1427) · airframe 106,939 hrs · 27,146 cycles

KEELBEAM PANEL SUPPORT LOWER SURFACE FOUND CORROSION AT BS 1427 RBL 16 TO LBL16. CORROSION BLEND OUT 0.050" BY 2" BY 20" EXCEED SRM LIMIT. SUPPORT REPAIRED AND INSTALLED AS PER SRM 51-10-01 PG 9 AND 51-30-02.

Part: SUPPORT — CORRODED (BS 1395) · airframe 106,939 hrs · 27,146 cycles

KEEL BEAM PANEL SUPPORT LOWER SURFACE FOUND CORROSION AT STA 1395 RBL 4 TO RBL 16. CORROSION BLEND OUT 0.036" BY 1.5" BY 10" EXCEED SRM LIMIT. SUPPORT REPLACED AS PER SRM 51-10-01 PG 9 AND INSTALLED AS PER SRM 51-30-02.

Part: FRAME — CRACKED (BS 1480) · airframe 106,939 hrs · 27,146 cycles

INSPECTION TYPE:C FX REAR BODY FAIRING SUPPORT FRAME FOUND CRACKED AT RT STA 1480 WL118, CRACK LENGTH 7/16". FX BS1480 BODY FAIRING SUPPORT FRAME REPAIRED AS PER SRM 51-40-03 FIG 1 AT LT WL118.

Part: CARGO TRACK — CORRODED (BS 1640-1660) · airframe 106,939 hrs · 27,146 cycles

BS 1640-1660 RBL 11 TIE DOWN TRACK I/B FLANGE FOUND CORRODED. CORROSION BLEND OUT 0.024" BY 3/4" BY 1.5" EXCEED SRM LIMIT. BS 1620 TO BS 1750 RBL 11 TRACK REPAIRED AS PER SRM 53-10-05 FIG14 REFER NRC5933 FOR WORKING DETAIL.

Part: CARGO TRACK — CORRODED (BS 1660) · airframe 106,939 hrs · 27,146 cycles

BS 1660 LBL80 TIE DOWN FTG FLANGE FOUND CORRODED. CORROSION BLEND OUT 0.024" BY 3/4" BY 1" EXCEED SRM LIMIT. TIE DOWN FTG REPLACE AS PER MM 53-42-00.

Part: FLOORBEAM — CORRODED (FUSELAGE) · airframe 106,939 hrs · 27,146 cycles

BS 1580 RBL 78-96 FLOORBEAM FOUND CORRODED. CORROSION BLEND OUT 0.093" BY 3/4" BY 1.5" EXCEED SRM 53-10-01 FIG 1 LIMITS. BS 1580 RBL 78 TO RT MOST O/B FLOOR BEAM REPAIRED AS PER SRM 51-40-04 FIG 3.

Part: FLOOR SUPPORT — CORRODED (BS 1540-1580) · airframe 106,939 hrs · 27,146 cycles

BS 1540-1580 LBL116 LONGITUDINAL FLOOR SUPPORT CORRODED. CORROSION BLEND OUT 0.055" BY 0.25" BY 1" EXCEED SRM LIMIT. FLOOR SUPPORT REPAIRED AS PER SRM 51-40-04 FIG 2 REFER NRC6412 FOR WORKING DETAIL.

Part: STIFFENER — CRACKED (BS 260-280) · airframe 106,939 hrs · 27,146 cycles

INSPECTION TYPE:C LT SIDE NOSE WHEEL WELL INTERNAL BETWEEN BS 260 AND 280 AT WL170 CRACK FOUND BETWEEN FASTENER HOLES AND RADIUS OF THE STIFFENER, CRACK LENGTH 1/4". FOUND LT SIDE NOSE WHEEL WELL BS260-280 WL170 INTERNAL STIFFENER REPLACED AND INSTALLED AS PER SRM 51-10-01 PG 9 AND 51-30-02.

Part: CARGO TRACK — CORRODED (BS 1640-1660) · airframe 106,939 hrs · 27,146 cycles

INSPECTION TYPE:C M/D BS 1640-1660 RBL 11 TIE DOWN TRACK O/B FLANGE FOUND COR. CORROSION BLEND OUT 0.026" X 3/4" X 1.5" EXCEED SRM 53-10-01 FIG 1 LIMITS, M/D BS 1610 TO BS 1750 RBL 11 TRACK REPAIRED AS PER SRM 53-10-05 FIG 14 REFER MRR# UPS06446578 AND NRC# 5933 FOR WORKING DETAIL.

Part: CARGO TRACK — CORRODED (BS 1500-1540) · airframe 106,939 hrs · 27,146 cycles

INSPECTION TYPE:C M/D- BS 1500-1540 RBL 33 TIE DOWN TRACK O/B FLANGE FOUND COR. CORROSION BLEND OUT 0.039" X 0.5" X 1.5" EXCEED SRM 53-10-01 FIG 1 LIMITS, TIE DOWN TRACK REPAIRED AS PER SRM 53-10-05 FIG 1A JUST AT RBL 33 BETWEEN BS 1480 AND BS 1550.

Part: CARGO TRACK — CORRODED (BS 1680) · airframe 106,939 hrs · 27,146 cycles

BS 1680 RBL36 TIE DOWN FTG FWD FLANGE FOUND CORRODED. CORROSION BLEND OUT 0.071" BY 0.25" BY 1" EXCEED SRM LIMIT. TIE DOWN FTG PLATE REPLACED AS PER MM 53-42-00.

Part: CARGO TRACK — CORRODED (BS 1680) · airframe 106,939 hrs · 27,146 cycles

BS 1680 LBL36 TIE DOWN FTG FWD FLANGE FOUND CORRODED. CORROSION BLEND OUT 0.026" BY 0.5" BY 1" EXCEED SRM LIMIT. TIE DOWN FTG PLATE REPLACED AS PER MM 53-42-00.

Part: STIFFENER — CRACKED (BS 260-280) · airframe 106,939 hrs · 27,146 cycles

INSPECTION TYPE:C LH SIDE NWW INTERNAL BTN BS 260 AND 280 CRACK FOUND AT WL150, WL160 OF THE STIFFENER RADIUS RESPECTIVITY, CRACK LENGTH 1/4". NWW BS 260-280 WL150 AND WL160 INTERNAL STIFFENER REPLACED AS PER SRM 51-10-01 PG 9 AND INSTALLED AS PER SRM 51-30-02.

Part: FLOOR SUPPORT — CORRODED (BS 1500-1540) · airframe 106,939 hrs · 27,146 cycles

BS 1500-1540 LBL116 LONGITUDINAL FLOOR SUPPORT FOUND CORRODED. CORROSION BLEND OUT 0.055" BY 0.25" BY 1" EXCEED SRM LIMIT. FLOOR SUPPORT REPAIRED AS PER SRM 51-40-04 FIG 2.

Part: REVEAL — CRACKED (CARGO DOORWAY) · airframe 106,939 hrs · 27,146 cycles

M/D LT NR 2 DOOR CUTOUT BETWEEN STR 24-25L LWR REVEAL FOUND CRACK, CRACK LENGTH 0.125" TO 0.875". M/D LT NR 2 DOOR CUTOUT BETWEEN STR 22L TO STR 26L REVEAL, FRAME STRAP HINGE SPLICE AND AFT INNER CHORD ANGLE REPAIRED AS PER HX RS NR R53-10-35471. THIS REPAIR IS TIME LIMITED FOR 24 MONTHS OR 1500 FLT CYC WHICHEVER COMES FIRST AT THAT TIME A PERMANENT REPAIR IS TO BE INSTALLED. REF UPS EO NR B747-5310-24078-A.

Part: SHEAR TIE — CRACKED (BS 152) · airframe 106,939 hrs · 27,146 cycles

INSPECTION TYPE:C AFT CARGO COMPT BS 152 STR 33R-34R FRAME SHEAR TIE FOUND CRACKED. CRACK LENGTH 1/2" AFT CARGO COMPT BS 1520 STR 33R-34R FRAME SHEAR TIE REPAIRED AS PER SRM 53-10-04 FIG 3.

Part: CARGO TRACK — BROKEN (BS 1880) · airframe 106,939 hrs · 27,146 cycles

BS 1880 LBL 99 TIE DOWN TRACK CROWN FOUND BROKEN 2". BS 1830-1970 LBL 99" TRACK REPAIRED AS PER SRM 53-10-05 FIG 1A.

Part: SKIN — CORRODED (BS 2168) · airframe 106,939 hrs · 27,146 cycles

INSPECTION TYPE:C FX SKIN LAP S12R TOP ROW FASTENER LOCATION AT BS 2168- BS 2170 FOUND OUTER SKIN WITH MATERIAL LOSS APPROX 0.013" (IE 10%) (MATERIAL LOSS D:0.013" BY W:0.75" BY L:2"). FX SKIN LAP REPAIRED AT BS 2162-2176 S11R - S12R AS PER SRM 53-30-03 FIG 17 WITHOUT ZEROTIME SUBSEQUENT INSPECTION ARE NECESSARY FOR CAT B REPAIR REFER TO TABLE III FOR INSPECTION REQUIREMENT.

Part: FLOORBEAM — CRACKED (BS 380) · airframe 106,939 hrs · 27,146 cycles

BS 380 FLOORBEAM UPPER CHORD HORIZONTAL AFT FLANGE HOLE AT LBL 10 CRACKED RUNNING AFT APPROX 0.030" LONG. BS 380 FLOORBEAM UPPER CHORD HORIZONTAL AFT FLANGE LBL 10" REPAIRED AS PER UPS EO NR B747-5310-23043 APPENDIX D FIG 9 PLAN C.

Part: FLOORBEAM — CRACKED (BS 340) · airframe 106,939 hrs · 27,146 cycles

BS 340 FLOORBEAM UPPER CHORD HORIZONTAL FWD FLANGE 1 HOLE AT LBL 46" CRACKED RUNNING FWD APPROX 3/16" LONG. CHORD REPAIRED AS PER UPS EO NR B747-5320-12407-F APPENDIX D FIG 3 PLAN C.

Part: SKIN — CRACKED (FUSELAGE) · airframe 106,939 hrs · 27,146 cycles

INSPECTION TYPE:C FWD CARGO DOOR CUTOUT AFT HINGE TWO FASTENER HOLES FOUND CRACK AT INTERNAL TEE ANGLE APPROX 0.040" AND 1/16" RUNNING DOWN RESPECTING. FWD CARGO DOOR CUTOUT AFT HINGE TWO TEE ANGLES REPLACED AND INSTALLED AS PER SRM 51-10-01 PG 9 AND SRM 51-30-02.

Part: GATE — CORRODED (R3 DOOR) · airframe 106,939 hrs · 27,146 cycles

R3 DOOR LOWER GATE LOWER FACE CORROSION FOUND. CORROSION BLEND OUT 0.092" BY 2" BY 4" EXCEED SRM 52-00-02 FIG 1 LIMIT, LOWER GATE REPLACED AT M/D R3 DOOR LWR AREA AS PER MM 20-51-01.

Part: REVEAL — CRACKED (R2 DOORWAY) · airframe 106,939 hrs · 27,146 cycles

INSPECTION TYPE:C M/D- R2 DOOR FWD CUTOUT LOWER REVEAL CRACKED AT STR 24R AREA. (CRACK LENGTH 3/16"). R2 DOOR FWD CUTOUT LOWER REVEAL AT STR 24R AREA REPAIRED AS PER SRM 53-10-04 FIG 84.

Part: FLOORBEAM — CORRODED (BS 1700) · airframe 106,939 hrs · 27,146 cycles

FLOOR FTG ATT FLOOR SUPPORT PLATE AT BS 1700 RBL35-55 FOUND CORROSION. CORROSION BLEND OUT 0.027" BY 1" BY 3" EXCEED SRM LIMIT. TIE DOWN FTG ASSY REPLACED AS PER MM 20-51-01.

Part: FRAME — CRACKED (BS 340) · airframe 106,939 hrs · 27,146 cycles

RT BS 340 UPPER DECK FLOORBEAM AT FRAME CONNECTION AREA 1 FASTENER HOLE CRACK AT FRAME, CRACK LENGTH 1/16". U/D BS 340 FLOORBEAM ATT FRAME REPAIRED AS PER HX RS# R53-12-35437, REF NRC# RH61151 FOR WORKING DETAIL AT BTN STR 10AR - 13AR AREA UPON ACCUMULATION OF 10000 FLT CYC PORTFORM A DETAIL VISUAL INSPECTION OF THE FWD AND AFT SIDES OF THE FRAME IN THE REPAIR AREA IS REQUIRE THAT IS TO REPEAT EVERY 3000 CYC, REF UPS EO NR B747-5310-24059-A.

Part: FLOORBEAM — CORRODED (BS 1820) · airframe 106,939 hrs · 27,146 cycles

FLR FTG ATT FLR SUPPORT PLATE AT BS 1820 LBL 50 FOUND CORROSION. CORROSION BLEND OUT 0.055" BY 1.5" BY 1.5" EXCEED SRM LIMIT. SUPPORT PLATE REPLACED AS PER MM 53-42-00.

Part: FLOORBEAM — CORRODED (BS 1800) · airframe 106,939 hrs · 27,146 cycles

FLOOR FTG ATT FLR SUPPORT PLATE AT BS 1800 LBL55-60 FOUND CORROSION. CORROSION BLEND OUT 0.020" BY 1" BY 3" EXCEED SRM LIMIT. TIE DOWN FTG REPLACED AS PER MM 53-42-00.

Part: SEAT TRACK — CRACKED (BS 1780-1782) · airframe 106,939 hrs · 27,146 cycles

SEAT TRACK FOUND CRACKED AT BS 1780-1782 RBL38, CRACK LENGTH 1". SEAT TRACK REPAIRED AS PER SRM 53-10-05 FIG1 A.

Part: FLOORBEAM — CORRODED (BS 1780) · airframe 106,939 hrs · 27,146 cycles

FLOOR FTG ATT FLOOR SUPPORT PLATE AT BS 1780 RBL60 FOUND CORROSION. CORROSION BLEND OUT 0.024" BY 1.5" BY 1.5" EXCEED SRM LIMIT. TIE DOWN FITTING REPLACED AS PER MM 53-42-00.

Part: FLOORBEAM — CRACKED (BS 340) · airframe 106,939 hrs · 27,146 cycles

FOUND RT BS 340 U/D FLOORRBEAM AT FRAME CONNECTION AREA HAS 1 HOLE CRACK AT FLOORBEAM WEB, CRACK LENGTH 1/16". FLOORBEAM WEB REPAIRED AT BS 340 RBL 48 TO RT MOST O/B AREA AS PER SRM 53-10-07 FIG 11.

Part: SKIN — CRACKED (BS 1605-1617) · airframe 106,939 hrs · 27,146 cycles

INSPECTION TYPE:C FX SKIN LAP S19L 1EA TOP ROW FASTENER HOLE FOUND OUTER SKIN CRACK APPROX 1/4" LONG RUNNING AFT. FX LAPPING SKIN REPAIRED AT BS1605-1617.5 STR 18L-19L AREA AS PER SRM 53-30-03 FIG 17 WITHOUT ZERO TIME AT CRITICAL ROW FASTENER. SUBSEQUENT INSP ARE NECESSARY FOR CAT B REPAIR REFER TO TABLE 3 INTERNAL HFEC AT 6000 CYCLE IS RECOMMENED.

Part: FRAME — CRACKED (BS 340) · airframe 106,939 hrs · 27,146 cycles

RT BS 340 UPPER DECK FLOORBEAM AT FRAME CONNECTION FOUND 1 HOLE CRACK AT FRAME, CRACK LENGTH 1/16". UPPER DECK BS 340 FLOORBEAM ATTACHED FRAME REPAIRED AS PER HX RS# R53-12-35437 AT BETWEEN STR 10AR TO STR 13AR AREA UPON THE ACCUMULATION OF 10000 FLT CYC. PERFORM A DETAIL VISUAL INSP OF THE FWD AND AFT SIDES OF THE FRAME IN THE REPAIR AREA IS REQ THAT IS TO REPEAT EVERY 3000 CYC REF UPS EO NR B747-5310-24059-A.

Part: SHEAR TIE — CRACKED (BS 1720) · airframe 106,939 hrs · 27,146 cycles

INSPECTION TYPE:C AFT CARGO COMPT BS1720 STR 33L-34L FRAME SHEAR TIE FOUND CRACK, CRACK LENGTH 1/4". AFT CARGO COMPT BS 1720 STR 34L-33L FRAME SHEAR TIE REPAIRED AS PER SRM 53-10-04 FIG I3.

Part: CARGO TRACK — CORRODED (BS 1700-1720) · airframe 106,939 hrs · 27,146 cycles

INSPECTION TYPE:C M/D SEAT TRACK FOUND CORROSION REVEALED AT BS 1700-1720 RBL 11. CORROSION BLEND OUT 0.042" X 1" X 2" EXCEED SRM 53-10-01 FIG 1 LIMITS, M/D BS 1610 TO BS 1750 RBL 11 TRACK REPAIRED AS PER SRM 53-10-05 FIG 14.

Part: FLOORBEAM — CORRODED (BS 1780) · airframe 106,939 hrs · 27,146 cycles

FLOOR FTG ATT FLR SUPPORT PLATE AT BS 1780 RBL 78 FOUND CORROSION. CORROSION BLEND OUT 0.070" BY 0.5" BY 2" EXCEED SRM LIMIT. FLOOR FTG REPLACED AS PER MM 20-51-01.

Part: FLOORBEAM — CRACKED (BS 340) · airframe 106,939 hrs · 27,146 cycles

RT BS 340 U/D FLOORBEAM AT FRAME CONNECTION AREA 1 FASTENER HOLE CRACK AT FLOORBEAM WEB, CRACK LENGTH 1/16". U/D FLOORBEAM WEB REPAIRED AT BS 340 RBL 48 TO RT MOST O/B AREA AS PER SRM 53-10-07 FIG 11 REFER NRC6117 FOR WORKING DETAIL.

Part: FLOORBEAM — CORRODED (BS 1720) · airframe 106,939 hrs · 27,146 cycles

FLT FTG ATT FLR SUPPORT PLATE AT BS1720 LBL65 FOUND CORRODED. CORROSION BLEND OUT 0.021" BY 0.5" 1" EXCEED SRM LIMIT. SUPPORT PLATE REPLACED AS PER MM 53-42-00.

Part: FLOOR SUPPORT — CORRODED (BS 1800-1820) · airframe 106,939 hrs · 27,146 cycles

FLOOR SUPPORT AT BS 1800-1820 LBL55 FOUND CORROSION. CORROSION BLEND OUT 0.040" BY 1" BY 1" EXCEED SRM LIMIT. FLOOR SUPPORT REPLACED AS PER SRM 51-10-01 PG9

Part: RIB — CRACKED (LT WING) · airframe 106,939 hrs · 27,146 cycles

INSPECTION TYPE:C LHW NR 6 VC FLAP O/B ARM O/B RIB O/B SIDE CTR VERTICAL STIFFENER FASTENER HOLES CRACKED AT HOLES 1100, CRACK LENGTH 1.9". LHW NR 6 VC FLAP O/B ARM O/B RIB O/B SIDE CTR STIFFENER REPAIRED AS PER HX RS NR R57-41-35411 PERFORM DVI AT THE AFFECTED AREAS AT EARLIER OF C CHK OR 3 MONTHS INTERNALS FOR SIGNS OF ADDITIONAL CRACK/CORROSION LOOSE OR MISSING FASTENERS OR DEGRADATION OF SUBJECT REPAIR INTEGRITY. UPS EO NR B747-5740-24046-A ISSUED FOR REPEAT INSP.

Part: FLOORBEAM — CORRODED (BS 1840) · airframe 106,939 hrs · 27,146 cycles

FLOOR FTG ATT FLOOR SUPPORT PLATE FOUND CORROSION AT BS 1840 LBL35. CORROSION BLEND OUT 0.034" BY 1" BY 1" EXCEED SRM LIMIT. TIE DOWN FTG REPLACED AS PER MM 53-42-00.

Part: FLOORBEAM — CORRODED (BS 1860) · airframe 106,939 hrs · 27,146 cycles

FLOOR FTG ATT FLOOR SUPPORT PLATE FOUND CORROSION AT BS 1860 LBL35. CORROSION BLEND OUT 0.026" BY 0.5" BY 1" EXCEED SRM LIMIT. FLOOR FTG REPLACED AS PER MM 53-42-00.

Part: SKIN — CRACKED (BS 330-340) · airframe 106,939 hrs · 27,146 cycles

RT FLIGHT COMPT NR 3 WINDOW CUTOUT SKIN FOUND CRACKED AT AFT LOWER CORNER EDGED. FX RT BS 330 TO BS 340 STR 7R TO STR 10R WINDOW CUTOUT SKIN REPAIRED AS PER HX RS NR R53-11-35448 WITHOUT ZERO TIMING SUBSEQUENT INSP ARE NECESSARY FOR CATEGORY B REPAIR SEE SRM 53-30-03 FIG 49 TABLE II FOR THE INSP REQUIREMENTS REF UPS EO NR B747-5310-24045-A.

Part: SKIN — DAMAGED (BS 740) · airframe 106,939 hrs · 27,146 cycles

INSPECTION TYPE:C FX SKIN LAP S39L CUTER SKIN 1EA TOP ROW FASTENER LOCATION AT BS 764 FOUND MATERIAL LOSS APPROX 0.11" ( IE > 10% ), REF NRC NR 5997 SKIN REPAIR WORKING DETAIL OVERLAPPING SKIN REPAIRED AT BS 740-770 S38L - 39L AREA AS PER SRM 53-30-03 FIG 48 WITHOUT ZERO TIMING AT CRITICAL ROW FASTENER SUBSEQUENT INSP ARE NECESSARY FOR CATEGORY B REPAIR REFER TO TABLE II INTERNAL HFEC AT 6000 CYCLE IS RECOMMENDED.

Part: SUPPORT — CORRODED (A/C BAY) · airframe 106,939 hrs · 27,146 cycles

FOUND AIR CONDITIONING BAY LT FAIRING SUPPORT UPPER SURACE FLOATING NUT AREA HAS SURFACE CORROSION AT STA 1047 LBL 57 TO LBL 80. CORROSION BLEND OUT 0.058" BY 1.5" BY 3" EXCEED SRM LIMIT. BS 1047 LBL 57 TO LBL 80 FAIRING SUPPORT REPLACED AND INSTALLED AS PER SRM 51-10-01 PG 9 AND SRM 51-30-02.

Part: SKIN — DAMAGED (BS 1866 S40L) · airframe 106,939 hrs · 27,146 cycles

INSPECTION TYPE:C FX- SKIN LAP S-40L OUTER SKIN 1 TOP ROW FASTENER LOCATION AT BS 1866 FOUND MATERIAL LOSS APPROX 0.011" ( IE. 710% ). FUSELAGE OVERLAPPING SKIN REPAIRED AT BS 1860-1875.5 S39L - 40L AREA AS PER SRM 53-30-03 FIG 17 WITH ZERO TIME AT CRITICAL ROW FASTENER SUBSEQUENT INSP ARE NECESSARY FOR CAT B REPAIR REFER TO TABLE III FOR INSP REQUIREMENT.

Part: SKIN — DAMAGED (BS 750) · airframe 106,939 hrs · 27,146 cycles

INSPECTION TYPE:C FX SKIN LAP S39L OUTER SKIN 1EA TOP ROW FASTENER LOCATION AT BS 746 FOUND MATERIAL LOSS APPROX 0.010" ( IE > 10% ) FX SKIN, OVERLAPPING SKIN REPAIRED AT BS 740-770 S38L - 39L AREA AS PER SRM 53-30-03 FIG 48 WITHOUT ZERO TIMING AT CRITICAL ROW FASTENER SUBSEQUENT INSP ARE NECESSARY FOR CATEGORY B REPAIR REFER TO TABLE II INTERNAL HFEC AT 6000 CYCLE IS RECOMMENDED.

Part: FLOORBEAM — CORRODED (BS 1800) · airframe 106,939 hrs · 27,146 cycles

FLOOR FTG ATT FLOOR SUPPORT PLATE AT BS 1800 LBL 55 FOUND CORROSION. CORROSION BLEND OUT 0.023" BY 1" BY 2" EXCEED SRM LIMIT. FLOOR FTG REPLACED AS PER MM 20-51-01.

Part: SHEAR TIE — CRACKED (BS 1660 S38-39L) · airframe 106,939 hrs · 27,146 cycles

AFT CARGO COMPT BS 1660 STR 38L-39L FRAME SHEAR TIE FOUND CRACKED, CRACK LENGTH 1/2". AFT CARGO COMPT BS 1660 STR 38L - 39L SHEAR TIE REPAIRED AS PER HX RS NR R53-61-35429 AND UPS EO NR B747-5310-24081-A.

Part: SKIN — CRACKED (FUSELAGE) · airframe 106,939 hrs · 27,146 cycles

LT FLIGHT COMPT NR 3 WINDOW CUTOUT SKIN FOUND CRACKED AT AFT LOWER CORNER BOLT HOLE CUTOUT, CRACK LENGTH 3/4" APPROX. FX LT BS 330 TO BS 340 STR 7L TO STR 10L WINDOW CUTOUT SKIN REPAIRED AS PER HX RS NR R53-11-35448 WITHOUT ZERO TIMING SUBSEQUENT INSPECTION ARE NECESSARY FOR CATEGORY B REPAIR SEE SRM 53-30-03 FIG 49 TABLE II FOR THE INSP REQUIREMENTS REF UPS EO# B747-5310-24045-A

Part: SKIN — DAMAGED (BS 782) · airframe 106,939 hrs · 27,146 cycles

INSPECTION TYPE:C FX SKIN LAP S39L OUTER SKIN 1EA TOP ROW FASTENER LOCATION AT BS 789 FOUND MATERIAL LOSS APPROX 0.012" ( IE > 10% ), FUSELAGE OVERLAPPING SKIN REPAIRED AT BS 782-795 S38L - S39L AREA AS PER SRM 53-30-03 FIG 11 WITHOUT ZERO TIMING AT CRITICAL ROW FASTENER SUBSEQUENT INSP ARE NECESSARY FOR CATEGORY B REPAIR REFER TO TABLE II INTERNAL HFEC AT 6000 CYCLE IS RECOMMENDED

Part: BULKHEAD — CORRODED (RT WLG WW) · airframe 106,939 hrs · 27,146 cycles

L/G RT WLG W/W BS 1241 RBL 7-8 I/B OF AILERON PROGRAMMER LWR WEB FOUND CORRODED. CORROSION BLEND OUT 0.054" BY 1.5" BY 6" EXCEED SRM 57-10-01 FIG 1 LIMITS, RT WLG W/W BS 1241 RBL 7-8 AREA BHD WEB REPAIRED AS PER HX RS NR R57-12-35467 AND UPS EO# B747-5710-24070-A.

Part: FLOORBEAM — CORRODED (BS 1820) · airframe 106,939 hrs · 27,146 cycles

FLOOR FTG ATT FLOOR SUPPORT PLATE AT BS 1820 LBL11-30 FOUND CORRODED. CORROSION BLEND OUT 0.020" BY 0.5" BY 0.5" EXCEED SRM LIMIT. FLOOR FTG REPLACED AS PER MM 53-42-00.

Part: FLOORBEAM — CORRODED (BS 1780) · airframe 106,939 hrs · 27,146 cycles

FTG ATT FLR SUPPORT PLATE AT BS 1780 LBL 55-70 FOUND CORROISON. CORROSION BLEND OUT 0.029" BY 1" BY 1" EXCEED SRM LIMIT. TIE DOWN FTG AND SUPPORT PLATE REPLACED AS PER MM 53-42-00. PART NUMBER : 69B62271-3 / 69B62265-1 / 69B62271-1.

Part: RIB — CRACKED (RT WING) · airframe 106,939 hrs · 27,146 cycles

RT WING NR 17VC FLAP O/B ARM O/B RIB ILES 766 TOP FLANGE I/B AND O/B SIDE FASTENER HOLE CRACK AT SEVERAL LOCATION. RHW NR 17 VC FLAP O/B ARM O/B RIB REPLACED AS PER SRM 51-10-01 PG 9 AND INSTALLED AS PER SRM 51-30-02.

Part: STRINGER SPLICE — CRACKED (BS 1740 S38L) · airframe 106,939 hrs · 27,146 cycles

AFT CARGO COMPT BS 1740 STR 38L STR SPLICE FOUND CORROSION CRACK, CORROSION CRACK LENGTH 3/4". STRINGER SPLICE AND SKIN REPAIRED AS PER HX RS NR R53-61-35429 AND UPS EO NR B747-5310-24081-A.

Part: STRINGER — CRACKED (BS 1745) · airframe 106,939 hrs · 27,146 cycles

INSPECTION TYPE:C AFT CARGO COMPT BS 1745 STR 40L STRINGER FOUND CRACK, CRACK LENGTH 1.5". AFT CARGO COMPT BS 1743 TO BS 1768 STR 40L STRINGER REPAIRED AS PER SRM 53-10-03 FIG 1.

Part: WEB — CRACKED (BS 1480) · airframe 106,939 hrs · 27,146 cycles

STA 1480 RT FAIRING SUPPORT ATT WEB FOUND CRACKED AT O/B SIDE RBL 90 TO 92 AND RBL 100 TO 100 (3 LOCATIONS) WBL127, CRACK LENGTH : 3/8", 1/4" AND 3/4" SUPPORT WEB REPAIRED AT BS 1480 RBL 90 TO RBL 92 AND RBL 100 TO RBL 103 AS PER SRM 51-40-02 FIG 1.

Part: RIB — CRACKED (RT WING) · airframe 106,939 hrs · 27,146 cycles

INSPECTION TYPE:C RT WING NR 21 VC FLAP O/B ARM O/B ROTARY SUPPORT RIB O/B TOP FLANGE CRACKED AT ILES 1094 APP, CRACK LENGTH 1/4" TO 1.25". RT WING NR 21 VC FLAP O/B ARM O/B ROTARY SUPPORT RIB REPAIRED AS PER RS NR R57-41-35464 PERFORM DVI. REQUIRE AT THE AFFECTED AREA AT 3 MONTHS INTERVALS FOR SIGNS OF ADDITIONAL CRACK GROWTH AT STOP DRILL LOCATIONS CORROSION. NEW CRACK AND DEGRADATION OF SUBJECT REPAIR INTEGRITY. REPLACE THE SUBJECT RIB WITHIN 18 MONTHS REF UPS EO# B747-5740-24001-A.

Part: BULKHEAD — CORRODED (RT WLG WW) · airframe 106,939 hrs · 27,146 cycles

RT WLG W/W CANTED BULKHEAD LOWER AREA SURFACE CORROSION REVEALED AT BS 1241 RBL 36-50. CORROSION BLEND OUT 0.039" BY 2" BY 12" EXCEED SRM 53-10-01 FIG 1 LIMITS, RT WLG W/W CANTED BULKHEAD BS 1238 TO BS 1241 RBL 35" TO RBL 55". REPAIRED AS PER HX RS NR R53-48-35472, AND UPS ENGINEERING FILE NR 747-53-20296.

Part: SPAR — CRACKED (NR 2 PYLON) · airframe 106,939 hrs · 27,146 cycles

INSPECTION TYPE:C NR 2 PYLON LOWER SPAR WEB UPPER AT NAC STA 248 O/B RIVET AREA CRACKED, CRACK LENGTH 0.40". NR 2 PYLON LOWER SPAR WEB AT NAC STA 248 O/B AREA REPAIRED AS PER SRM 54-10-03 FIG 2.

Part: SKIN — DENTED (BS 2598-2618) · airframe 106,939 hrs · 27,146 cycles

EMP AFT JACK PAD AREA BS 2598 TO BS 2618 STR 49R TO STR 51R FOUND DENT, DENT EXCEEDS LIMIT. EMP BS 2598 TO BS 2627 STR 49L AND STR 42R SKIN REPAIRED AS PER SRM 53-30-03 FIG 1A.

Part: STRUCTURE — CRACKED (PYLON) · airframe 106,939 hrs · 27,146 cycles

NR 4 PYLON REAR ENGINE MOUNT BULKHEAD FOUND CRACK AT RT FWD FRAME WEB, CRACK LENGTH 7/16". REAR ENG MOUNT BULKHEAD FRAME 4 REPLACED AND REPAIRED AS PER HX RS NR R54-53-35457 CONTINUED TO INSP. THE REAR ENGINE MOUNT BULKHEAD PER THE REQUIREMENTS OF THE HX RS NR R54-53-35457, AND UPS EO NR B747-5450-24060-A.

Part: SUPPORT — CRACKED (A/C BAY) · airframe 106,939 hrs · 27,146 cycles

INSPECTION TYPE:C FX AIR CONDITIONING BAY RT PANEL SUPPORT UPPER CHORD FOUND CRACKED AT STA 1233-STA 1235 RBL105 WING CENTER SECTION LOWER EXTERNAL SURFACE AS MARK, CRACK LENGTH 1.25". FX AIR CONDITIONING BAY RT PANEL SUPPORT UPPER CHORD REPLACED AT BS 1159 TO 1241 RBL105 AREA AS PER SRM 51-10-01 PG 9 AND INSTALLED AS PER SRM 51-30-02.

Part: ATTACH FITTING — CRACKED (BS 300) · airframe 106,939 hrs · 27,146 cycles

INSPECTION TYPE:C FX- LT NOSE WHEEL WELL INTERNAL VERTICAL BEAM ATTACH CLIP FOUND CRACKED AT STA 300 LOWER NR 1 CLIP (COUNT FROM LOWER ) (CRACK LENGTH 3/8" ). FX- LT NOSE WHEEL WELL INTERNAL VERTICAL BEAM ATTACH CLIP REPLACED AS PER SRM 51-10-01 PG 9 AND INSTALLED AS PER SRM 51-30-02.

Part: FRAME — CRACKED (BS 488) · airframe 106,939 hrs · 27,146 cycles

INSPECTION TYPE:C M/D MED #1R CUTOUT BS 488 FRAME WEB FOUND CRACK EXTEND BEYOND #9 DOOR STOP BY 1/16" AS MARKED.(CRACK LENGTH 1" ) M/DECK BS 488 BETWEEN S16R TO S19R FRAME WEB REPAIRED AS PER SRM 53-10-04 FIG 121. CRACK FREE AT TRIM LINE AREA & INNER CHORD FASTENER HOLES WITHIN 6" OF THE CRACK AREA AS PER NTM PT6 51-00-00 FIG INSPECTED BY NDT.

Part: COMPUTER — FAILED (NR 2)

N/A DIVERSION - NR 2 AND NR 3 INS SYSTEMS FAILED. SAI FAIL FLAG INTERMITTENT. RERACKED NR 2 INS CMPUTER IAW MM 34-41-03 REALIGNED INS, NO FAULT NOTED, OPS CHECK NORMAL.

Part: LINK — CRACKED (NR 4 PYLON) · airframe 106,207 hrs · 26,971 cycles

AD NR 4 PYLON REAR MOUNT THRUST LINK AFT IND LUG FOUND CRACK INDICATION EXCEED LIMIT. NR 4 PYLON REAR UPPER MOUNT THRUST LINK ASSY CHANGED AND INSTALLED MM 71-21-03.

Part: LINK — CRACKED (NR 2 PYLON) · airframe 106,207 hrs · 26,971 cycles

AD NR 2 PYLON REAR ENGINE MOUNT THRUST LINK ULTRASONIC INSP FOUND CRACK INDICATION EXCEEDED LIMIT AT BOTH FWD AND AFT LUG. NR 2 PYLON REAR UPPER ENGINE MOUNT AFT THRUST LINK ASSY CHANGED AND INSTALLED IAW MM 71-21-03.

Part: LINK — CRACKED (NR 4 PYLON) · airframe 106,207 hrs · 26,971 cycles

AD NR 4 PYLON REAR ENGINE MOUNT THRUST LINK FWD END LUG FOUND CRACK INDICATION EXCEEDED LIMIT. NR 4 PYLON REAR UPPER ENGINE MOUNT AFT THRUST LINK ASSY CHANGED AND INSTALLED IAW MM 71-21-03.

Part: PRESSURE PANEL — CRACKED (NLG WW) · airframe 105,090 hrs · 26,736 cycles

INSPECTION TYPE:SV NOSE WHEEL WELL LT SIDE PANEL FROM BS 260-280 WL 150 CRACK INDICATION FOUND BETWEEN NR 8, 13 AT WEB AREA. CRACK LENGTH 6 INCHES. CRACKED WEB REPAIRED AS PER EO B747-5310-20502 APPENDIX C ITEM (6) INSTRUCTION AND SRM 53-10-04 FIGURE 116.

Part: PRESSURE PANEL — CRACKED (NLG WW) · airframe 105,090 hrs · 26,736 cycles

INSPECTION TYPE:SV NOSE W/W LEFT SIDE PANEL FROM BS 260-280 AT WL 170 CRACK INDICATED FOUND AT THE LOCATION FASTENER NR 7 TO 15. CRACK LENGTH 9 INCHES. WEB REPAIRED AS PER EO B747-5310-20502-C ITEM (6) INSTRUCTION AND SRM 53-10-04 FIGURE 116.

Part: PRESSURE PANEL — CRACKED (NOSE WW) · airframe 105,090 hrs · 26,736 cycles

INSPECTION TYPE:SV NOSE WHEEL WELL LT SIDE PANEL FROM BS 280-300 WL 160 CRACK AT NR 12 TO NR 14 & NR 16 FASTENER AREA. CRACK LENGTH 5 INCH. CRACKED SIDE PANEL REPAIRED AS PER EO B747-5310-20502 APPENDIX C ITEM (6) INSTRUCTION AND SRM 53-10-04 FIGURE 116.

Part: PRESSURE PANEL — CRACKED (NLG WW) · airframe 105,090 hrs · 26,736 cycles

INSPECTION TYPE:SV NOSE WHEEL WELL RT SIDE PANEL FROM BS 280-300 WL 170 CRACK INDICATION FOUND AT FASTENER LOCATION NR 6, 10, 12 AT WEB. CRACK LENGTH 3 INCHES. CRACKED WEB REPAIRED AS PER EO B747-5310-20502-C ITEM (6) INSTRUCTION AND SRM 53-10-04 FIGURE 116.

Part: PRESSURE PANEL — CRACKED (NLG WW) · airframe 105,090 hrs · 26,736 cycles

INSPECTION TYPE:SV NOSE WHEEL WELL TOP PANEL FROM BS 300 TO 320 AT LBL 20 CRACK INDICATION FOUND AT FASTENER NR 8, 9, 14, 15 & 16. CRACK LENGTH 5 INCHES. CRACKED TOP PANEL REPAIRED AS PER HX RS R53-10-35292 & UPS EO B747-5310-22075-A.

Part: PRESSURE PANEL — CRACKED (NLG WW) · airframe 105,090 hrs · 26,736 cycles

INSPECTION TYPE:SV NOSE WHEEL WELL RT SIDE PANEL FROM BS 260 - 280 WL 170 CRACK INDICATION FOUND AT FASTENER NR 8 AT WEB AREA. CRACK LENGTH 1 INCH. CRACKED WEB REPAIRED AS PER EO B747-5310-20502-C ITEM 6 INSTRUCTION AND SRM 53-10-04 FIGURE 116.

Part: PRESSURE PANEL — CRACKED (NLG WW) · airframe 105,090 hrs · 26,736 cycles

INSPECTION TYPE:SV NW-LT SIDE WALL WEB CRACK AT 4 EA HOLE LOCATION AT BS 280 - 300 WL 170 AREA. CRACK LENGTH 4 INCHES. NW-LT SIDE WALL WEB CRACK AREA REPAIR AS PER EO B747-5310-20502 APPENDIX C ITEM 6 INSTRUCTION & SRM 53-10-04 FIGURE 116.

Part: ENGINE — FAILED (NR 4)

IFSD NR 4 ENGINE LOSING OIL PRESSURE CREW RECEIVED OIL PRESS LT BY PASS LT IND AND OIL QTY READ ZERO. NR 4 ENGINE SHUTDOWN. OIL FILTER COVERED WITH BLACK PASTE AND OIL DRAINED WAS BLACK. OIL IN TAILPIPE. ENGINE CHANGED SCHEDULED. R/R NR 4 ENG PER TC 5000 HIGH POWER RUN CHECK ALL RGE OPS NORMAL

Part: STOP — BROKEN (L3 DOOR) · airframe 104,265 hrs · 26,546 cycles

INSPECTION TYPE: C, L3 DOOR AFT NR 3 DOOR STOP FITTING FOUND BROKEN. M/D L3 DOOR AFT NR 3 STOP FITTING REPLACED AS PER SRM 51-10-01 PG 8.

Part: PLATE — CRACKED (FUSELAGE) · airframe 104,265 hrs · 26,546 cycles

INSPECTION TYPE-C, CRACK FOUND AT BS 1241 WL 200 RT SPLICE PLATE NR 5 BOLT HOLES BORE CRACK STILL REVEALED AFTER THE HOLE OVERSIZED TO DIA 1.200 INCH. RT SPLICE PLATE REPLACED IAW EO B747-5740-4366.

Part: SKIN — CRACKED (RT WING) · airframe 104,265 hrs · 26,546 cycles

INSPECTION TYPE:C, RIGHT BS 1241 WL 178 WING REAR SPAR UPPER SPLICE FITTING AREA FOUND HOLE NR 11 CRACKED AT WING UPPER SKIN. CRACKED HOLE REWORKED AND OVERSIZED AS PER EO B747-5740-17032.

Part: SPLICE — CRACKED (LT WING) · airframe 104,265 hrs · 26,546 cycles

INSPECTION TYPE-C, LT WING UPPER BS 1241 WL 180 REAR SPAR SPLICE PLATE FASTENER HOLE NR 7 FOUND CRACKED AT SPAR CHORD UPPER LAYER RUNNING AFT APPROX .0625 INCH LONG. HOLE REWORKED AND OVERSIZED IAW EO B747-5740-17032.

Part: PLATE — CRACKED (RT WING) · airframe 104,265 hrs · 26,546 cycles

INSPECTION TYPE:C, RIGHT BS 1241 WL 180 UPPER WING SPLICE PLATE NR 5 FASTENER HOLE CORROSION CRACK REVEALED AT WING UPPER SKIN LAYER. RIGHT BS 1241 UPPER WING SPLICE PLATE NR 5 FASTENER HOLE AT UPPER SKIN LAYER REWORKED AS PER EO B747-5740-17032.

Part: SKIN — CRACKED (RT WING) · airframe 104,265 hrs · 26,546 cycles

INSPECTION TYPE:C, RT BS 1241 WL 178 WING REAR SPAR UPPER SPLICE FITTING AREA FOUND HOLE NR 7 CRACKED AT WING UPPER SKIN. HOLE CRACK REWORKED AND OVERSIZED AS PER EO 5740-17032-B.

Part: FITTING — CRACKED (LT WING) · airframe 104,265 hrs · 26,546 cycles

INSPECTION TYPE: C, LEFT WING UPPER BS 1241 REAR SPAR SPLICE PLATE FASTENER HOLE (STR L28) FOUND CRACK AT HOLE NR 4 TERMINAL FITTING AT FWD POSITION APPROX 0.080 INCH LONG. HOLE REWORKED AND OVERSIZED AS PER EO B747-5740-17032.

Part: SPAR — CRACKED (LT WING) · airframe 104,265 hrs · 26,546 cycles

INSPECTION TYPE:C, LEFT BS 1241 WL 180 WING REAR SPAR KICK FITTING NR 1 FASTENER HOLE CRACK REVEALED AT WEB FORWARD LAYER APPROX .0937 INCH IN LENGTH RUNNING O/B AND LOWER. LEFT BS 1241 WING REAR SPAR KICK FITTING NR 1 FASTENER HOLE REWORKED AS PER EO 5740-17032 WORK DETAIL.

Part: SPAR — CRACKED (LT WING) · airframe 104,265 hrs · 26,546 cycles

INSPECTION TYPE:C, CRACK FOUND ON LT BS 1241 WL 170 TO 180 WING REAR SPAR WEB AT KICK FITTING AREA AT HOLE NR 2 BY APPROX .0625 INCH RUNNING O/B & DOWN. HOLE REWORKED AND OVERSIZED AS PER EO B747-5740-17032.

Part: SPAR — CRACKED (LT WING) · airframe 104,265 hrs · 26,546 cycles

INSPECTION TYPE:C, LEFT BS 1241 WL 180 UPPER WING REAR SPAR CHORD FOUND CRACK AT HOLE NR 10 RUNNING FORWARD APPROX .0625 INCH. CRACKED HOLE REWORKED AS PER EO 5740-17032.

Part: FITTING — CRACKED (FUSELAGE) · airframe 104,265 hrs · 26,546 cycles

INSPECTION TYPE:C, RIGHT BS 1241 WL 180 UPPER WING SPLICE PLATE FITTING NR 5 FASTENER HOLE CRACK REVEALED RUNNING AFT HOLE CRACK EXCEED EO LIMIT. REF NRC 6676 FOR REPLACEMENT OF SPLICE PLATE.

Part: SKIN — CRACKED (FUSELAGE) · airframe 104,265 hrs · 26,546 cycles

INSPECTION TYPE: C, CRACK REVEALED ON RIGHT BS 1241 FUSELAGE SKIN AT ONE EA HOLE AREA BS 1241, WL 170 TO 180. BS 1241 RIGHT FX SKIN REPAIRED AS PER SRM 53-30-03 FIG 59.

Part: FITTING — CRACKED (FUSELAGE) · airframe 104,265 hrs · 26,546 cycles

INSPECTION TYPE:C, LEFT BS 1241 WL 180 UPPER SPLICE PLATE NR 5 FASTENER HOLE TWO CRACKS REVEALED AT SPLICE PLATE MATING SURFACE BOTH CRACKS APPROX .25 INCH IN LENGTH. BOLT HOLE REWORKED AND OVERSIZED AS PER EO B747-5740-17032.

Part: SKIN — CRACKED (FUSELAGE) · airframe 104,265 hrs · 26,546 cycles

INSPECTION TYPE: C, CRACK REVEALED ON LEFT BS 1241 FUSELAGE SKIN AT TWO EA HOLES. LT BS 1241 FUSELAGE SKIN REPAIR AS PER SRM 53-30-03 FIG 59.

Part: SPLICE — CRACKED (WING SPAR) · airframe 104,265 hrs · 26,546 cycles

INSPECTION TYPE: C, RT BS 1241 STR R28 UPPER WING REAR SPAR SPLICE PLATE HOLE NR 4 FOUND CRACK AT SPLICE PLATE AT 12 O'CLOCK POSITION APPROX 0.080 INCH LONG. HOLE REWORKED AND OVERSIZED AS PER EO B747-5740-17032 & RIGHT SPLICE PLATE REPLACED AS PER EO B747-5740-4366 DUE NR 5 HOLE ON SPLICE PLATE CRACK EXCEED LIMIT.

Part: SPLICE — CRACKED (WING SPAR) · airframe 104,265 hrs · 26,546 cycles

INSPECTION TYPE: C, RT BS 1241 STR R28 UPPER WING REAR SPAR SPLICE PLATE HOLE NR 4 FOUND CRACK AT INTERNAL SPLICE FITTING AT 7 O'CLOCK POSITION APPROX 0.080 INCH LONG. CRACKED HOLE REWORKED AND OVERSIZED AS PER EO B747-5740-17032.

Part: STRINGER — CORRODED (FWD CARGO) · airframe 104,265 hrs · 26,546 cycles

INSPECTION TYPE-C FWD CARGO STA 860-880 S47L STRINGER CORROSION FOUND. FWD CARGO BS 860-880 STR 47L STRINGER REPAIRED IAW SRM 53-10-03 FIG 1 DUE TO BLEND OUT DEPTH 0.040 INCH , WIDTH 1 INCH AND LENGTH 2 INCHES OUT OF SRM 53-10-01 FIG LIMITATION.

Part: SHEAR TIE — CORRODED (FWD CARGO) · airframe 104,265 hrs · 26,546 cycles

INSPECTION TYPE:C, FWD CARGO STA 840 S44L - S45L BILGE AREA SHEAR TIE CORROSION FOUND. NEW SHEAR TIE REPLACED & INSTALLED AT BS 840 STR 44L - 45L AS PER SRM 51-30-02, DUE TO BLEND OUT DEPTH 0.050 INCH, WIDTH 1 INCH & LENGTH 3 INCH OUT OF SRM 53-10-01 FIG 1 LIMITATION.

Part: FLOORBEAM — CORRODED (FWD CARGO) · airframe 104,265 hrs · 26,546 cycles

INSPECTION TYPE: C, FWD CARGO STA 960 RBL 45 FLOOR SUPPORT CORROSION FOUND. CORROSION REMOVED IAW SRM 51-10-01. CORROSION BLEND OUT 0.050 X 2 X 2 INCH EXCEED SRM 53-10-01 FIG 01 LIMITS. FLOORBEAM FLANGE REPAIRED PER SRM 54-40-04 FIG 1. CIC APPLIED IAW EO M-5100-2780-E.

Part: FLOORBEAM — CORRODED (FWD CARGO) · airframe 104,265 hrs · 26,546 cycles

INSPECTION TYPE: C, FWD CARGO STA 840 RBL 30 FLOOR SUPPORT CORRODED. CORROSION REMOVED IAW SRM 51-10-01. CORROSION BLEND OUT 0.050 X 1 X 2 INCH EXCEED SRM 53-10-01 FIG 1 LIMITS, FLOOR SUPPORT REPAIRED PER SRM 51-40-04 FIG 2. CIC APPLIED IAW EO M-5100-2780-E.

Part: LINK — CORRODED (KEELBEAM) · airframe 104,265 hrs · 26,546 cycles

INSPECTION TYPE-C FX- KEEL BEAM BOX INNER HORIZ SUPPORT LINK CORRODED AT BS 1460 WL 118. CORROSION MACHINED OFF AT BOTH SIDE VERTICAL RIBS 0.030 INCH AT BOTTOM HORIZ RIB 0.020 INCH . KEEL BEAM BOX INNER HORIZ SUPPORT LINK REPLACED IAW HX RS NR R-53-49-35206 AND UPS RA NR 747-53-20195.

Part: DOUBLER — CRACKED (L1 DOOR SKIN) · airframe 104,265 hrs · 26,546 cycles

INSPECTION TYPE: C, M/D- L1 DOOR SKIN LOWER HINGE DOUBLER FOUND CRACKED. DOUBLER REPLACED & INSTALLED AS PER SRM 51-10-01 PG 8 & 51-30-02.

Part: BULKHEAD — CRACKED (FUSELAGE) · airframe 104,265 hrs · 26,546 cycles

INSPECTION TYPE:C, LEFT BS 1480 BULKHEAD APU DUCT CUTOUT 1EA FASTENER HOLE CRACK FOUND RUNNING DOWNWARD APPROX 0.060 INCH LENGTH BS 1480, LBL 100. LEFT BS 1480 BULKHEAD APU DUCT CUTOUT WEB REPAIRED AS PER EO B747-5310-3100-C FIG 4.

Part: SPAR — CRACKED (NR 3 PYLON) · airframe 104,265 hrs · 26,546 cycles

INSPECTION TYPE:C, A 3 INCH CRACK WAS FOUND AT LOWER WEB AT NAC 220 OF NR 3 PYLON AT PER O/B SIDE. NR 3 PYLON NAC STA 220 O/B SIDE AFT LOWER SPAR WEB REPAIRED AS PER SRM 54-10-03 FIG 23.

Part: GATE — CRACKED (R5 DOOR) · airframe 104,265 hrs · 26,546 cycles

INSPECTION TYPE-C M/D- R5 DOOR UPR GATE CRACKED. (BS 2240 TO 2280, STR R16 TO R17) UPPER GATE REPLACED IAW MM 20-51-01.

Part: RIB — CRACKED (RT WING) · airframe 104,265 hrs · 26,546 cycles

INSPECTION TYPE: C, RT WING L/E NR 17 VC FLAP O/B ARM O/B ROTARY ACTUATOR SUPPORT RIB AT ILES 764 APP. FOUND UPPER CHORD MID SPAN AREA CRACK AS MARKED. L/E RIB REPAIRED AT ILES 764 AS PER SRM 57-20-03 FIG 3.

Part: WEB — CRACKED (NR 2 PYLON) · airframe 104,265 hrs · 26,546 cycles

INSPECTION TYPE: C, NR 2 PYLON - DURING ACCOMPLISHMENT EO ON AFT LOWER SPAR WEB, 1EA NON STANDARD REPAIR PATCH FOUND INSTALLED ON LOWER SPAR WEB JUST AFT OF REAR END MOUNT BULKHEAD. DEFECTIVE AREA AFT LOWER SPAR WEB REPAIR CARRIED OUT AS PER SRM 54-10-03 FIG 23 AT NAC STA 218 TO NAC STA 228.5 LBL 1 TO LBL 7 AREA.

Part: RIB — CRACKED (LT WING) · airframe 104,265 hrs · 26,546 cycles

INSPECTION TYPE: C, LEFT WING: CTR WING L/E SUPPORT RIB FOUND CRACKED AT ILES 964.55 AS MARKED. LEFT WING CTR WING L/E SUPPORT RIB AT ILES 964.55 REPLACED AS PER SRM 51-10-01 PG 8.

Part: WEB — CRACKED (NR 1 PYLON) · airframe 104,265 hrs · 26,546 cycles

INSPECTION TYPE: C, ONE EACH FASTENER HOLE WAS CRACKED AT WEB AREA NAC STA 230 OF NR 1 PYLON. NR 1 PYLON NAC STA 230 AFT LOWER WEB I/B AREA WEB REPAIRED AS PER SRM 54-10-03 FIG 2 DETAIL 1.

Part: BULKHEAD — CRACKED (LT MLG WW) · airframe 104,265 hrs · 26,546 cycles

INSPECTION TYPE: C, LEFT MLG WW AFT BULKHEAD APU BLEED AIR DUCT CUTOUT I/B UPPER AREA CRACKED AT STA 1480, LBL 100. LEFT BLG W/W AFT BULKHEAD APU BLEED AIR DUCT CUTOUT WEB REPAIRED AS PER EO B747-5310-3100-C FIG 4.

Part: SPLICE — CRACKED (FUSELAGE FRAME) · airframe 104,265 hrs · 26,546 cycles

INSPECTION TYPE: C, M/D BS 280, S22-23R FRAME SPLICE FOUND CRACK. BS 280 STR 22 TO 23R FRAME SPLICE REPLACED AS PER SRM 51-30-02.

Part: SPAR — CRACKED (NR 3 PYLON) · airframe 104,265 hrs · 26,546 cycles

INSPECTION TYPE:C, NR 3 PYLON NAC STA 222 AFT LOWER SPAR WEB I/B SIDE CRACK IS FOUND AS MARK. NR 3 PYLON NAC STA 222 I/B SIDE AFT LOWER SPAR WEB REPAIRED AS PER SRM 54-10-03 FIG 23.

Part: RIB — CRACKED (RT WING) · airframe 104,265 hrs · 26,546 cycles

INSPECTION TYPE-C, RT WING L/E OLES 1453 NR25 VC FLAP OB ROTARY IB SUPPORT RIB FWD MOUNT HOLE CRACKED. RT WING L/E OLES NR25 VC FLAP OB ROTARY ACTUATOR IB SUPPORT RIB REPAIRED IAW HX RSNR R-57-41-35205, DVI THE AFFECTED AREA AT C- CHECK INTERVALS NOT TO EXCEED 18 MONTHS FOR SIGNS OF CORROSION, CRACK AND DEGRADATION OF SUBJECT REPAIR. IAW UPS EO NR B747-5740-21181 APPENDIX A FOR REFERENCE.

Part: RIB — CRACKED (RT WING) · airframe 104,265 hrs · 26,546 cycles

INSPECTION TYPE: C, RIGHT WING L/E OLES 1421 NR 25 VC FLAP I/B ROTARY O/B SUPPORT RIB FWD MOUNT HOLE CRACKED. SUPPORT RIB REPLACED AS PER SRM 51-10-01 PG 8. NR 25 VC FLAP REF MM 27-81-02 RIGGING & OPERATION CHECK CUTOUT PER MM 27-81-00.

Part: FRAME — CRACKED (FUSELAGE) · airframe 104,265 hrs · 26,546 cycles

INSPECTION TYPE: C, M/D- BS 360, S24-25L FRAME FOUND CRACK AS MARKED. FRAME SEGMENT REPLACED & REPAIRED AS PER HX RS R53-12-35203 & UPS EO B747-5310-21180-A.

Part: CARGO TRACK — CORRODED (CARGO BAY) · airframe 104,265 hrs · 26,546 cycles

INSPECTION TYPE: C, M/D- BS 1720 LBL 97 TIE DOWN TRACK CORRODED. CORROSION REMOVED IAW SRM 51-10-01. CORROSION BLEND OUT 0.060 X 1 X 5 INCH EXCEED SRM 53-10-01 LIMITS. SEAT TRACK REPAIRED REF SRM 53-10-05 FIG 1A. CIC APPLIED IAW UPS EO M5100-2780-E.

Part: STRINGER — CRACKED (BATTERY BAY) · airframe 104,265 hrs · 26,546 cycles

INSPECTION TYPE: C, EMP- BATTERY COMPT RIGHT STR 13 AFT END FOUND CRACKED AT FS 2658. BATTERY COMPT RIGHT STR 13 & STRAPS REPLACED AS PER SRM 51-10-01 PG 8 AT BS 2658 AREA.

Part: BULKHEAD — CORRODED (RT MLG WW) · airframe 104,265 hrs · 26,546 cycles

INSPECTION TYPE-C, RT WLG W/W FWD BULKHEAD IB MID AREA CORROSION REVEALED AT STA 1241 RBL 2-6. CORROSION REMOVED IAW SRM 51-10-01. CORROSION BLEND OUT 0.082 INCH X 1 INCH X 5 INCH EXCEED SRM 57-10-01 FIG 1 LIMITS. BULKHEAD REPAIRED REFER SRM 57-10-06 FIG 3, CIC APPLIED IAW M-5100-2780-E.

Part: RIB — CRACKED (RT WING) · airframe 104,265 hrs · 26,546 cycles

INSPECTION TYPE: C, RIGHT WING L/E OLES 1409 APPROX NR 25 V/C FLAP I/B ROTARY I/B SUPPORT RIB FWD MOUNT HOLE CRACK. RIGHT WING L/E OLES 1409 APPROX NR 25 VC FLAP I/B ROTARY ACTUATOR I/B SUPPORT RIB REPAIRED AS PER HX RS R-57-41-35202, DVI THE AFFECTED AREA AT C-CHECK INFORVALS NOT TO EXCEED 18 MONTHS FOR SIGNS OF CORROSION, CRACKS & DEGRADATION OF SUBJECT REPAIR, SEE DETAIL PER UPS EO B747-5740-21183-A FOR REFERENCE.

Part: FRAME — CRACKED (FUSELAGE) · airframe 104,265 hrs · 26,546 cycles

INSPECTION TYPE: C, CRACK FOUND AT LEFT BS 488 AT NR 1 MED AT AFT FRAME WEB RUNNING DOWN FROM INNER CHORD .0625 INCH LONG (BS 488, STR L25 TO L25). CABIN LEFT BS 488 STR 23 TO STR 30 WEB REPAIRED AS PER SRM 53-10-04 FIG 92.

Part: LINE — LEAKING (NR 2 HYD SYS)

DURING INITIAL CLIMB LOST ALL QUANTITY AND PRESS IN HYD SYS NR 2. EMERGENCY DECLARED. FOUND NR 2 HYD SYS PRESSURE MODULE PRESSURE LINE LEAKING. REMOVED AND REPLACED NR 2 HYD SYS PRESSURE MODULE LINE LEAK. CHECKED GOOD AT THIS TIME.

Part: LIGHT — FAULTY (CABIN)

INSPECTION TYPE:N/A EMERGENCY LIGHT AT OVERHEAD AT UPPER DECK SLIDE COMES ON AND GOES OFF APPROX 5 SEC AFTER SWITCH TURNED ON. REMOVED AND REPLACED EMERGENCY LIGHT PER MM REF 33 51 07. OPS CHECK NORMAL.

Part: RIB — CORRODED (NR 20 FLAP) · airframe 100,611 hrs · 25,820 cycles

INSPECTION TYPE: C, RT WING - NR 20 VC FLAP O/B O/B ROTARY ACTUATOR SUPPORT RIB MOUNT BOLT HOLES BORE AREA FOUND CORROSION AT HOLE NR 6, 7. BOLT HOLES CORROSION REMOVED AND INTERIM REPAIRED AS PER RS 57-41-35014 AND UPS EO B747-5740-18687-A.

Part: RIB — CORRODED (NR 19 FLAP) · airframe 100,611 hrs · 25,820 cycles

INSPECTION TYPE: C, RT WING - NR 19 VC FLAP O/B O/B ROTARY ACTUATOR SUPPORT RIB MOUNT BOLT HOLES BORE AREA FOUND CORROSION AT HOLE NR 6 ( VIEW FROM I/B ). BOLT HOLE CORROSION REMOVED AND INTERIM REPAIRED AS PER RS 57-41-35014 AND UPS EO 747-5740-18687-A.

Part: FRAME — CRACKED (FUSELAGE) · airframe 100,611 hrs · 25,820 cycles

INSPECTION TYPE: C, M/D - BS 940 FRAME CRACK AT S24R AS MARKED. BS 940 FRAME REPAIRED AS PER SRM 53-10-04 FIG 35.

Part: DOOR FRAME — CRACKED (FUSELAGE) · airframe 100,611 hrs · 25,820 cycles

INSPECTION TYPE: C M/D - R5 DR FWD FX CUTOUT UPPER REVEAL FOUND CRACKED AT STR 16. DOOR CUTOUT REVEAL FRAME REPAIRED AS PER SRM 51-40-03 FIG.1

Part: CREASE BEAM — CRACKED (FUSELAGE) · airframe 100,611 hrs · 25,820 cycles

INSPECTION TYPE: C, BS 980 S4-5L CREASE BEAM CRACKED. CREASE BEAM WEB REPLACED AS PER SRM 51-10-01 PAGE 8.

Part: REVEAL — CRACKED (PAX DOORWAY) · airframe 100,611 hrs · 25,820 cycles

INSPECTION TYPE: C, L5 DOOR FWD FX CUTOUT UPPER REVEAL CRACKED AT STR 16. DOOR CUTOUT REVEAL FRAME REPAIRED AS PER SRM 51-40-03 FIG 1.

Part: FLOORBEAM — CORRODED (FUSELAGE) · airframe 100,611 hrs · 25,820 cycles

INSPECTION TYPE: C, U/D - FLOORBEAM UPPER STRUCTURE FOUND CORROSION AT BS 340 BL 0 - LBL 40 FLOORBEAM UPPER STRUCTURE REPAIRED AS PER SRM 53-10-07 FIG.23 CORROSION BLEND OUT SIZE 0.038 X 1 X 3 INCHES.

Part: SHEAR TIE — CRACKED (FUSELAGE) · airframe 100,611 hrs · 25,820 cycles

INSPECTION TYPE:C M/D - BS 1301 LT STR 16L SHEAR TIE FOUND CRACKED. SHEAR TIE REPLACED AS PER SRM 51-10-01 PAGE 8.

Part: SHEAR TIE — CRACKED (FUSELAGE) · airframe 100,611 hrs · 25,820 cycles

INSPECTION TYPE: C M/D - BS 1283 LT STR 16L SHEAR TIE FOUND CRACKED. SHEAR TIE REPLACED AS PER SRM 51-10-01 PAGE 8.

Part: SHEAR TIE — CRACKED (FUSELAGE) · airframe 100,611 hrs · 25,820 cycles

INSPECTION TYPE: C M/D- BS 1301 S15-16R FRAME SHEAR TIE CRACKED. SHEAR TIE REPLACED AS PER SRM 51-10-01 PAGE 8.

Part: SKIN — CORRODED (WINDOW BELT) · airframe 100,611 hrs · 25,820 cycles

INSPECTION TYPE: C, BET. BS 1438 - 1460 RT WINDOW FORGINGS FOUND CORRODED. WINDOW FORGING AREA SKIN REPAIRED AS PER HX RS R53-21-35018 AND ENG'R FILE 747-53-20137. CORROSION BLEND OUT 0.043" X 1" X 1".

Part: FRAME — CRACKED (FUSELAGE) · airframe 100,611 hrs · 25,820 cycles

INSPECTION TYPE: C, BS 560 LT STR 24L FRAME FOUND CRACKED. FRAME REPAIRED AS PER SRM 53-10-04 FIG 35.

Part: FORGING — CORRODED (RT WINDOW) · airframe 100,611 hrs · 25,820 cycles

INSPECTION TYPE: C, BS 620 - 640 RT WINDOW FORGING FOUND CORROSION AT CUTOUT SKIN AFT AREA. CORROSION BLEND OUT (0.028 X 1 X 1 INCHES). WINDOW FORGING REINSTALLED AS PER SRM 51-30-02.

Part: RIB — CORRODED (NR 20 FLAP) · airframe 100,611 hrs · 25,820 cycles

INSPECTION TYPE: C, RT WING - NR 20 VC FLAP O/B I/B ROTARY ACTUAOTR SUPPORT RIB MOUNT BOLT HOLES BORE AREA FOUND CORROSION AT HOLE NR 4 , 5 ( VIEW FROM I/B ). BOLT HOLES CORROSION REMOVED AND INTERIM REPAIRED AS PER RS 57-41-35014 AND EO B747-5740-18687-A.

Part: STRINGER — CRACKED (FUSELAGE) · airframe 100,611 hrs · 25,820 cycles

INSPECTION TYPE: C, BS 1394 S11L STRINGER CRACKED. BS 1385 - 1410 STR 11L STRINGER REPAIRED AS PER SRM 53-10-03 FIG 5.

Part: STRINGER — CRACKED (FUSELAGE) · airframe 100,611 hrs · 25,820 cycles

INSPECTION TYPE: C, BS 1000 - 1020, S6L STRINGER CRACKED. BS 1000 S-6L STRINGER REPAIRED AS PER HX RS R53-21-35017 AND ENGINEERING FILE NUMBER ; 747-53-20138.

Part: FRAME — CRACKED (FUSELAGE) · airframe 100,611 hrs · 25,820 cycles

BS 540 LT STR 25L FRAME FOUND CRACKED. FRAME REPAIRED AS PER HX RS R53-22-35011 & UPS RA 747-53-20135 REF NRC FF76313 FOR DETAIL.

Part: FLOORBEAM — CORRODED (FUSELAGE) · airframe 100,611 hrs · 25,820 cycles

INSPECTION TYPE:N/A M/D - BS 760 LBL 40 FLOORBEAM UPPER SURFACE FOUND CORRODED. FLOORBEAM REPAIRED PER SRM 51-40-04 FIG 3. CORROSION BLEND OUT 0.060 X 2 X 2 INCHES, EXCEED SRM LIMIT.

Part: SHEAR TIE — CRACKED (FUSELAGE) · airframe 100,611 hrs · 25,820 cycles

INSPECTION TYPE: C M/D - BS 1020, S3R FRAME TIE CLIP FOUND CRACKED. TIE CLIP REPLACED AS PER SRM 51-10-01 PAGE 8.

Part: RIB — CORRODED (NR 19 FLAP) · airframe 100,611 hrs · 25,820 cycles

INSPECTION TYPE: C, RT WING - NR 19 VC FLAP O/B I/B ROTARY ACTUATOR SUPPORT RIB MOUNT BOLT HOLES BORE AREA FOUND CORROSION AT HOLE NR 6 ( VIEW FROM I/B ). BOLT HOLES CORROSION REMOVED AND INTERIM REPAIRED AS PER RS 57-41-35014 AND UPS EO B747-5740-18687-A.

Part: LONGERON — CRACKED (FUSELAGE) · airframe 100,611 hrs · 25,820 cycles

M/D - BS 1235 S8L STRINGER END CRACKED. BS 1235 S8L STRINGER REPAIRED AS PER HX RS R53-21-35017 & UPS RA 747-53-20138.

Part: SKIN — CRACKED (FUSELAGE) · airframe 100,611 hrs · 25,820 cycles

INSPECTION TYPE: C, AFT CARGO DOOR CUTOUT FWD UPPER CORNER FOUND BEAR STRAP CRACK APPROX 3/16 INCHES LONG FROM EDGE. AFT CARGO DOOR CUTOUT FWD CUTOUT UPPER CORNER REPAIRED AS PER SRM 53-30-03 FIG 62 AND REFER NRC 6407 FOR WORK DETAIL. CAT B REPAIR REQUIRES REPEAT INSPECTION THRESHOLD AT 15,000 CYCLES AFTER REPAIR INSTALLATION AND REPEAT AT 3000 CYCLES INTERVAL PER SRM.

Part: FRAME — CRACKED (FUSELAGE) · airframe 100,611 hrs · 25,820 cycles

INSPECTION TYPE: C, M/D - BS 580 LT STRINGER 24L FRAME FOUND CRACKED. FRAME REPAIRED AT BS 580 BETWEEN S23L TO S25L AS PER SRM 53-10-04 FIG.35.

Part: FRAME — CRACKED (FUSELAGE) · airframe 100,611 hrs · 25,820 cycles

INSPECTION TYPE: C, BS 960 FRAME CRACKED AT STR 9L. FRAME REPAIRED AS PER SRM 53-10-04 FIG 54.

Part: FRAME — CRACKED (FUSELAGE) · airframe 100,611 hrs · 25,820 cycles

INSPECTION TYPE: C, BS 1640 S-13L FRAME CRACKED. M/D FRAME REPAIRED AT BS 1640 BTN STR 12L AND STR 14L AS PER SRM 51-40-03 FIG 2.

Part: FLOORBEAM — CORRODED (FUSELAGE) · airframe 100,611 hrs · 25,820 cycles

INSPECTION TYPE: C, FLOORBEAM UPPER STRUCTURE CORROSION. FLOORBEAM REPAIRED PER SRM 51-40-04 FIG 3. CORROSION BLEND OUT 0.060 X 2 X 2 INCHES. EXCEED SRM LIMIT.

Part: SEAT TRACK — CORRODED (FUSELAGE) · airframe 100,611 hrs · 25,820 cycles

INSPECTION TYPE: C M/D - SEAT TRACK O/B FLANGE LOWER SURFACE CORROSION. SEAT TRACK REPAIRED AS PER SRM 53-10-05 FIG 16. CORROSION BLEND OUT 0.050 X 1 X 1.5 INCH. EXCEED SRM LIMIT.

Part: SEAT TRACK — CORRODED (FUSELAGE) · airframe 100,611 hrs · 25,820 cycles

INSPECTION TYPE: C, SEAT TRACK FOUND CORROSION AT BS 480 - 485 RBL 65. SEAT TRACK REPAIRED AT U/D BS 480 - 530 RBL 65 AS PER SRM 53-10-05 FIG 1A. CORROSION BLEND OUT 0.045 X 1 X 8 INCHES. EXCEED SRM LIMIT.

Part: STRUCTURE — CORRODED (FUSELAGE) · airframe 100,611 hrs · 25,820 cycles

M/D - HAT SECTION FWD FLANGE CORROSION. CORRODED HAT SECTION REPLACED AS PER SRM 51-10-01 PAGE 8. CORROSION BLEND OUT 0.030 X 1 X 1 INCHES. EXCEED SRM LIMIT.

Part: CLIP — CORRODED (FUSELAGE) · airframe 100,611 hrs · 25,820 cycles

BS 1040 STR 4L TIE CLIP CORROSION. BS 1040 STR 4L TIE CLIP REINSTALL AS PER SRM 51-30-02. CORROSION BLEND OUT 0.040 X 1 X 1 INCHES. EXCEED SRM LIMIT.

Part: FRAME — CRACKED (FUSELAGE) · airframe 100,611 hrs · 25,820 cycles

INSPECTION TYPE: C, BS 540 LT STR 24L FRAME FOUND CRACKED. FRAME REPAIRED AS PER RS R53-22-35011 REFER NRC FF76313 FOR DETAIL. AND ENGR FILE NBR 747-53-20135.

Part: FRAME — CRACKED (FUSELAGE) · airframe 100,611 hrs · 25,820 cycles

INSPECTION TYPE: C, BS 540 LT BET STRINGER 22L AND 23L FRAME INNER CHORD FOUND CRACKED. FRAME REPAIRED AS PER HX RS R53-22-35011 AND ENGINEERING FILE NUMBER 747-53-20135.

Part: STRINGER — CRACKED (FUSELAGE) · airframe 100,611 hrs · 25,820 cycles

BS 1474 S-12L STRINGER END CRACKED. STRINGER REPAIRED AS PER SRM 53-10-03 FIG 4.

Part: LONGERON — CRACKED (FUSELAGE) · airframe 100,611 hrs · 25,820 cycles

INSPECTION TYPE: C, BS 1002-1004- S2R, STR END FOUND CRACK. BS 1002 - 1004 S2R STRINGER REPAIRED AS PER HX RS R53-21-35017 & UPS RA 747-53-20138.

Part: SEAT TRACK — CORRODED (FUSELAGE) · airframe 100,611 hrs · 25,820 cycles

INSPECTION TYPE: C, BS 820 - 860 LBL 11 SEAT TRACK RT LIP FOUND CORRODED. BS 810 - 890 LBL 11 SEAT TRACK REPAIRED AS PER SRM 53-10-05 FIG 14. CORROSION BLEND OUT 0.050 X 1 X 10 INCHES. EXCEED SRM LIMIT.

Part: SEAT TRACK — CORRODED (FUSELAGE) · airframe 100,611 hrs · 25,820 cycles

INSPECTION TYPE: C, SEAT TRACK FOUND CORROSION. CORROSION BLEND OUT ( 0.050 X 5/8 X 2 INCHES). M/D SEAT TRACK REPAIRED AT BS 770-850 LBL 98 AS PER SRM 53-10-05 FIG 1A.

Part: FRAME — CRACKED (FUSELAGE) · airframe 100,611 hrs · 25,820 cycles

INSPECTION TYPE: C, BS 960 FRAME CRACKED BTN S11-12L. FRAME REPAIRED AS PER SRM 53-10-04 FIG 4.

Part: FRAME — CRACKED (FUSELAGE) · airframe 100,611 hrs · 25,820 cycles

INSPECTION TYPE: C, BS 960, BET S7-8R FRAME FOUND CRACK. FRAME REPAIRED AS PER SRM 53-10-04.

Part: FRAME — CRACKED (FUSELAGE) · airframe 100,611 hrs · 25,820 cycles

INSPECTION TYPE: C, M/D - BS 920 LT STRINGER 25L FRAME FOUND CRACKED. REF NRC 7348 FRAME REPAIRED AS PER SRM 53-10-04 FIG.24.

Part: FRAME — CRACKED (FUSELAGE) · airframe 100,611 hrs · 25,820 cycles

INSPECTION TYPE:C M/D - BS 920 LH STR - 24L FRAME FOUND CRACKED. BS 920 BETWEEN S24L TO S25L FRAME REPAIRED AS PER SRM 53-10-04 FIG.35.

Part: FRAME — CRACKED (FUSELAGE) · airframe 100,611 hrs · 25,820 cycles

INSPECTION TYPE: C, M/D BS 920 BET S23-24R FRAME FOUND CRACKED. BS 920 BETWEEN S23L TO S25L FRAME REPAIRED AS PER SRM 53-10-04 FIG.35.

Part: RIB — CORRODED (NR 9 FLAP) · airframe 100,611 hrs · 25,820 cycles

INSPECTION TYPE: C LHW, NR 9 VC FLAP O/B I/B ROTARY ACTUATOR SUPPORT RIB MOUNT BOLT HOLES BORE AREA FOUND CORROSION AT HOLE NR 3 ( VIEW FROM I/B ). RIB MOUNT BOLT HOLE BORE EXCEED LIMIT AFTER CORR BLEND OUT. SUPPORT RIB REPLACED AS PER SRM 51-10-01 PAGE 8 AT LHW NR 9 VC FLAP O/B I/B ROTARY ACTUATOR ATTACH.

Part: FRAME — DEFORMED (FUSELAGE) · airframe 100,611 hrs · 25,820 cycles

INSPECTION TYPE: C, BS 1800 RT BETWEEN STRINGER 20 - 22R FRAME FOUND DEFORMED. M/D BS 1800 RT BTN STR 20 AND STR 22 FRAME REPAIRED AS PER SRM 53-10-04 FIG 87.

Part: FRAME — CRACKED (FUSELAGE) · airframe 100,611 hrs · 25,820 cycles

INSPECTION TYPE: C, M/D - BS 600 LT STR 19L FRAME FOUND CRACKED. FRAME REPAIRED AS PER SRM 53-10-04 FIG 35 AT BS 600 BETWEEN STR 18L - 20L.

Part: FRAME — CRACKED (FUSELAGE) · airframe 100,611 hrs · 25,820 cycles

INSPECTION TYPE: C, M/D - BS 940 LT STRINGER 25L FRAME FOUND CRACKED. REF NRC 7344 FRAME REPAIRED AS PER SRM 53-10-04 FIG 35.

Part: FRAME — CRACKED (FUSELAGE) · airframe 100,611 hrs · 25,820 cycles

M/D - BS 680 LT STR 17L FRAME INNER STRUCTURE FOUND CRACKED. FRAME REPAIRED AS PER HX RS R53-22-35010 & UPS RA 747-53-20131.

Part: FRAME — CRACKED (FUSELAGE) · airframe 100,611 hrs · 25,820 cycles

INSPECTION TYPE: C, BS 740 BET S24-25R FRAME FOUND CRACK. BS 740 STR 24R - STR 26R FRAME REPAIRED AS PER SRM 53-10-04 FIG.35

Part: RIB — CORRODED (NR 3 FLAP) · airframe 100,611 hrs · 25,820 cycles

INSPECTION TYPE: C, LT WING - NR 3 VC FLAP O/B ROTARY ACTUATOR SUPPORT RIB MOUNT BOLT HOLES BORE AREA FOUND CORROSION AT HOLE NR 2 & 3 ( VIEW FROM I/B ). BOLT HOLES CORROSION REMOVED AND INTERIM REPAIRED AS PER RS 57-41-35014 AND UPS EO B747-5740-18687-A.

Part: RIB — CORRODED (NR 23 FLAP) · airframe 100,611 hrs · 25,820 cycles

INSPECTION TYPE: C, RT WING - NR 23 VC FLAP I/B O/B ROTARY ACTUATOR SUPPORT RIB MOUNT BOLT HOLES BORE AREA FOUND CORROSION AT HOLE NR 1 TO 8. ( VIEW FROM I/B ) BOLT HOLES CORROSION REMOVED AND INTERIM REPAIRED AS PER RS 57-41-35014 AND EO B747-5740-18687-A.

Part: RIB — CORRODED (NR 2 FLAP) · airframe 100,611 hrs · 25,820 cycles

INSPECTION TYPE: C, LT WING, NR 2 VC FLAP I/B ROTARY ACTUATOR SUPPORT RIB MOUNT BOLT HOLES BORE AREA FOUND CORROSION AT HOLE NO.1, 2, 3 & 4 ( VIEW FROM I/B ). BOLT HOLES CORROSION REMOVED AND INTERIM REPAIRED AS PER RS 57-41-35014 AND UPS EO B747-5740-18687-A.

Part: FRAME — CRACKED (FUSELAGE) · airframe 100,611 hrs · 25,820 cycles

INSPECTION TYPE: C, M/D - BS 940 LT STR 24L FRAME FOUND CRACKED. BS 940 BETWEEN S24L TO S25L FRAME REPAIRED AS PER SRM 53-10-04 FIG 35.

Part: RIB — CORRODED (NR 9 FLAP) · airframe 100,611 hrs · 25,820 cycles

INSPECTION TYPE: C, LT WING - NR 9 VC FLAP I/B O/B ROTARY ACTUATOR SUPPORT RIB MOUNT BOLT HOLES BORE AREA FOUND CORROSION AT HOLE NR 1,2,3,6,7 & 8 (VIEW FROM I/B). BOLT HOLES CORROSION REMOVED AND INTERIM REPAIRED AS PER HX RS 57-41-35014 AND UPS EO B747-5740-18687-A

Part: RIB — CORRODED (NR 8 FLAP) · airframe 100,611 hrs · 25,820 cycles

INSPECTION TYPE: C, LT WING - NR 8 VC FLAP I/B O/B ROTARY ACTUATOR SUPPORT RIB MOUNT BOLT HOLES BORE AREA FOUND CORROSION AT HOLE NR 2,3,4,6,7 & 8 (VIEW FROM I/B). BOLT HOLES CORROSION REMOVED AND INTERIM REPAIRED AS PER HX RS 57-41-35014 AND UPS EO B747-5740-18607-A.

Part: RIB — CORRODED (NR 19 FLAP) · airframe 100,611 hrs · 25,820 cycles

INSPECTION TYPE: C, RT WING - NR 19 VC FLAP I/B O/B ROTARY ACTUATOR SUPPORT RIB MOUNT BOLT HOLES BORE AREA FOUND CORROSION AT HOLE NR 1 TO 8. (VIEW FROM I/B). BOLT HOLES CORROSION REMOVED AND INTERIM REPAIRED AS PER HX RS 57-41-35014 AND UPS EO 747-5740-18687-A

Part: RIB — CORRODED (NR 7 FLAP) · airframe 100,611 hrs · 25,820 cycles

INSPECTION TYPE: C, LT WING - NR 7 VC FLAP O/B O/B ROTARY ACTUATOR SUPPORT RIB MOUNT BOLT HOLE BORE AREA FOUND CORROSION AT HOLE NR 4 ( VIEW FROM I/B). BOLTS HOLES CORROSION REMOVED AND INTERIM REPAIRED AS PER HX RS 57-41-35014 AND UPS EO B747-5740-18687-A.

Part: FRAME — CRACKED (FUSELAGE) · airframe 100,611 hrs · 25,820 cycles

INSPECTION TYPE: C, M/D - BS 920 BET S24-25R FRAME FOUND CRACKED. REF NRC 7377 FRAME REPAIRED AS PER SRM 53-10-04 FIG.35.

Part: RIB — CORRODED (LT WING FLAP) · airframe 100,611 hrs · 25,820 cycles

INSPECTION TYPE: C LT WING, NR 7 VC FLAP O/B I/B ROTARY ACTUATOR SUPPORT RIB MOUNT BOLT HOLES BORE AREA FOUND CORROSION AT HOLE NR 6 & 7 ( VIEW FROM I/B). BOLT HOLES CORROSION REMOVED AND INTERIM REPAIRED AS PER HX RS 57-47-35014 AND UPS EO B747-5740-18687-A.

Part: FRAME — CRACKED (FUSELAGE) · airframe 100,611 hrs · 25,820 cycles

INSPECTION TYPE: C, BS 640 LT STR - 24L FRAME FOUND CRACKED. FRAME REPAIRED AS PER SRM 53-10-04 FIG 35.

Part: FRAME — CRACKED (FUSELAGE) · airframe 100,611 hrs · 25,820 cycles

INSPECTION TYPE: C, M/D - BS 960 BET S23 - 24R FRAME FOUND CRACK. BS 960 BETWEEN S23R TO S25R FRAME REPAIRED AS PER SRM 53-10-04 FIG 35.

Part: RIB — CORRODED (NR 9 FLAP) · airframe 100,611 hrs · 25,820 cycles

INSPECTION TYPE: C, LT WING - NR 9 VC FLAP O/B O/B ROTARY ACTUATOR SUPPORT RIB MOUNT BOLT HOLES BORE AREA FOUND CORROSION AT HOLE NR 2,3 & 6. (VIEW FROM I/B). BOLT HOLES CORROSION REVEALED REMOVED AND INTERIM REPAIRED AS PER HX RS 57-41-35014 AND UPS EO B747-5740-18687-A.

Part: SHEAR TIE — CRACKED (FUSELAGE) · airframe 100,611 hrs · 25,820 cycles

INSPECTION TYPE: C, BS 1700 RT FRAME BTN S-3R AND S-4R SHEAR TIE FOUND CRACKED AS MARKED. SHEAR TIE REPLACED AS PER SRM 51-10-01 PAGE 8.

Part: FLOORBEAM — CORRODED (FUSELAGE) · airframe 100,611 hrs · 25,820 cycles

INSPECTION TYPE: C, FLOORBEAM UPPER STRUCTURE FOUND CORRODED. FLOORBEAM REPAIRED PER SRM 51-40-04 FIG 3. CORROSION BLEND OUT 0.050 X 1 X 1 INCHES. EXCEED SRM LIMIT.

Part: FRAME — CRACKED (FUSELAGE) · airframe 100,611 hrs · 25,820 cycles

INSPECTION TYPE: C, BS 1680 FRAME CRACK AT STR 13L I/B AREA. FRAME REPLACED AS PER SRM 51-10-01 PAGE 8 AT CABIN STA 1680 BTN STR 12L AND STR 16L.

Part: FRAME — CRACKED (FUSELAGE) · airframe 100,611 hrs · 25,820 cycles

INSPECTION TYPE: C, M/D - BS 660 LT STR - 24 L FRAME FOUND CRACKED. FRAME REPAIRED AS PER SRM 53-10-04 FIG 35.

Part: FRAME — CRACKED (FUSELAGE) · airframe 100,611 hrs · 25,820 cycles

INSPECTION TYPE: C, BS 2060 BET STR 25-26L, FRAME WEB FOUND CRACK. FRAME WEB REPAIRED AT BS 2060 BTN STR 25L AND STR 26L AS PER SRM 53-10-04 FIG 39.

Part: SHEAR TIE — CRACKED (FUSELAGE) · airframe 100,611 hrs · 25,820 cycles

INSPECTION TYPE: C, FWD CARGO COMPT - STA 840 STR - 45R TO 46R FRAME SHEAR TIE CORROSION CRACK REVEALED. FWD CARGO COMPT STA 840 S45R - S46R FRAME SHEAR TIE REPAIRED AS PER SRM 53-10-04 FIG 3A.

Part: FRAME — CRACKED (FUSELAGE) · airframe 100,611 hrs · 25,820 cycles

INSPECTION TYPE: C, M/D - BS 760 LT STR 16L FRAME FOUND CRACKED. FRAME REPAIRED AT BS 760 BETWEEN S-14L TO S-17L AS PER SRM 53-10-04 FIG 35.

Part: RIB — CORRODED (NR 6 FLAP) · airframe 100,611 hrs · 25,820 cycles

INSPECTION TYPE: C, LT WING - NR 6 VC FLAP I/B ROTARY ACTUATOR SUPPORT RIB MOUNT BOLT HOLES BORE AREA FOUND CORROSION AT HOLE NR 2 & 3 ( VIEW FROM I/B ). BOLT HOLES CORROSION REMOVED AND INTERIM REPAIRED AS PER RS 57-41-35014 AND UPS EO B747-5740-18687-A.

Part: FRAME — CRACKED (FUSELAGE) · airframe 100,611 hrs · 25,820 cycles

INSPECTION TYPE: C, BS 620, BET S17-18R, FRAME I/B STURCTUREFOUND CRACK. FRAME REPAIRED AS PER HX RS R53-22-35012 AND 747-53-20136.

Part: FRAME — CRACKED (FUSELAGE) · airframe 100,611 hrs · 25,820 cycles

INSPECTION TYPE: C, BS 760, BET STR 14 - 15R FRAME FOUND CRACKED. FRAME REPAIRED AS PER RS R-53-22-35013 AND ENGINEERING FILE NUMBER 747-53-20132.

Part: RIB — CORRODED (NR 8 FLAP) · airframe 100,611 hrs · 25,820 cycles

INSPECTION TYPE:C LT WING - NR 8 VC FLAP I/B I/B ROTARY ACTUATOR SUPPORT RIB MOUNT BOLT HOLES BORE AREA FOUND CORROSION AT HOLE NR 1,2,6 & 8. (VIEW FROM I/B). BOLT HOLES CORROSION REMOVED AND INTERIM REPAIRED AS PER HX RS 57-41-35014 & UPS EO B747-5740-18687-A.

Part: SHEAR TIE — CRACKED (FUSELAGE) · airframe 100,611 hrs · 25,820 cycles

INSPECTION TYPE: C M/D - BS 1500 RH STR 12R TO 13R, SHEAR TIE BRACKET FOUND CRACKED. SHEAR TIE REPLACED AS PER SRM 51-10-01 PAGE 8.

Part: SUPPORT BRACKET — CORRODED (KEELBEAM) · airframe 100,611 hrs · 25,820 cycles

INSPECTION TYPE: C, KEELBEAM PANEL SUPPORT BRACKET FOUND SURFACE CORROSION AT STA 1095 LBL 9. CORROSION BLEND OUT (0.040 X 1 X 1 INCHES) SUPPORT BRACKET REPLACED AS PER SRM 51-10-01 P.8

Part: FRAME — CRACKED (FUSELAGE) · airframe 100,611 hrs · 25,820 cycles

INSPECTION TYPE: C, M/D - BS 960 LT BET STR 23L TO 24L FRAME FOUND CRACKED. BS 960 BETWEEN S23L TO S24L FRAME REPAIRED AS PER SRM 53-10-04 FIG 4 .

Part: FRAME — CRACKED (FUSELAGE) · airframe 100,611 hrs · 25,820 cycles

INSPECTION TYPE: C, BS 540 BET S24-25R FRAME FOUND CRACK. M/D BS 540 STR 24R - STR 26R FRAME REPAIRED AS PER SRM 51-40-03 FIG 1.

Part: SUPPORT BRACKET — CORRODED (KEELBEAM) · airframe 100,611 hrs · 25,820 cycles

KEELBEAM PANEL SUPPORT BRACKET FOUND SURFACE CORROSION AT STA 1225 LBL 9. SUPPORT BRACKET REINSTALLED AS PER SRM 51-30-2 AND BRACKET REPLACED AS PER SRM 51-10-01 P.8 REFER NRC 6878. CORROSION BLEND OUT 0.040 X 1 X 1 INCHES. EXCEED SRM LIMIT.

Part: STRINGER — CRACKED (FUSELAGE) · airframe 100,611 hrs · 25,820 cycles

INSPECTION TYPE: C, M/D - BS 1570 - 1580, STR 16L STRINGER END AREA FOUND CRACK. STRINGER REPAIRED AS PER SRM 53-10-03 FIG 4.

Part: FRAME — CRACKED (FUSELAGE) · airframe 100,611 hrs · 25,820 cycles

INSPECTION TYPE: C, BS 620 LT STRINGER 24L FRAME FOUND CRACKED. FRAME REPAIRED AS PER SRM 53-10-04 FIG.35.

Part: FRAME — CRACKED (FUSELAGE) · airframe 100,611 hrs · 25,820 cycles

INSPECTION TYPE: C, BS 2080, BET S25-26L FRAME WEB FOUND CRACK. M/DECK BS 2080 BETWEEN STR 25L - 26L FRAME REPAIRED AS PER SRM 53-10-04 FIG 39.

Part: FRAME — CRACKED (FUSELAGE) · airframe 100,611 hrs · 25,820 cycles

INSPECTION TYPE: C, BS 2100, BET STR 25 - 26L FRAME WEB FOUND CRACK. M/D FX FRAME WEB REPAIRED AT BS 2100 BTN STR 25L AND STR 26L AS PER SRM 53-10-04 FIG 39.

Part: RIB — CORRODED (NR 4 FLAP) · airframe 100,611 hrs · 25,820 cycles

LT WING - NR 4 VC FLAP I/B ROTARY ACTUATOR SUPPORT RIB MOUNT BOLT HOLES BORE AREA FOUND CORROSION AT HOLE NR 1, 3, 4, 6 & 8. ( VIEW FROM I/B ). BOLT HOLES CORROSION REMOVED AND INTERIM REPAIRED AS PER RS 57-41-35014 AND UPS EO B747-5740-18687-A.

Part: FRAME — CRACKED (FUSELAGE) · airframe 100,611 hrs · 25,820 cycles

INSPECTION TYPE: C, M/D - BS 600 LT STR 24L FRAME FOUND CRACKED. FRAME REPAIRED AS PER SRM 53-10-04 FIG 35.

Part: STRINGER — CRACKED (FUSELAGE) · airframe 100,611 hrs · 25,820 cycles

INSPECTION TYPE: C, BS 2182 - 2186, STR 14L STRINGER END FOUND CRACK. STRINGER REPLACED AS PER SRM 51-10-01 .

Part: FRAME — CRACKED (FUSELAGE) · airframe 100,611 hrs · 25,820 cycles

INSPECTION TYPE: C, M/D - BS 960 BET S24 - 25R FRAME FOUND CRACK. REF NRC 7379 FRAME REPAIRED AS PER SRM 53-10-04 FIG 35.

Part: FRAME — CRACKED (FUSELAGE) · airframe 100,611 hrs · 25,820 cycles

INSPECTION TYPE: C, M/D - BS 760 LT STR 15L FRAME FOUND CRACKED. FRAME REPAIRED AS PER SRM 53-10-04 FIG 35 AT BS 760 BETWEEN STR 14L TO 17L.

Part: FRAME — CRACKED (FUSELAGE) · airframe 100,611 hrs · 25,820 cycles

INSPECTION TYPE: C, M/D - BS 760 LT STR 16L FRAME FOUND CRACKED. FRAME REPAIRED AT BS 760 BETWEEN S14L TO S17L AS PER SRM 53-10-04 FIG 35.

Part: WEB — CORRODED (FUSELAGE) · airframe 100,611 hrs · 25,820 cycles

INSPECTION TYPE: C, FLOOR WEB AT BS 520 RBL 83 FOUND CORROSION. WEB REPAIRED AS PER RS NR : R52-25-35007 AND ENGINEERING FILE NUMBER 747-53-20130.

Part: STRINGER CLIP — CORRODED (FUSELAGE) · airframe 100,611 hrs · 25,820 cycles

INSPECTION TYPE: C, BS 540 LT STRINGER 15L, 16L & 17L TIE CLIP FOUND CORRODED. CORROSION BLEND OUT ( 0.009 X 1 X 3 INCHES) AT M/D BS 540 LT STR 15L TO 17L EXCEEDS LIMITATION. SHEAR TIE REPLACED AS PER SRM 51-10-01 PG.8.

Part: RIB — CORRODED (NR 2 FLAP) · airframe 100,611 hrs · 25,820 cycles

INSPECTION TYPE: C, LT WING - NR 2 VC FLAP O/B ROTARY ACTUATOR SUPPORT RIB MOUNT BOLT HOLES BORE AREA FOUND CORROSION AT HOLE NR 1, 2, 3, 4, 5 AND 6 ( VIEW FROM I/B ). BOLT HOLES CORROSION REMOVED AND INTERIM REPAIRED AS PER RS 57-41-35014 AND UPS EO 747-5740-18687-A.

Part: RIB — CORRODED (NR 4 FLAP) · airframe 100,611 hrs · 25,820 cycles

INSPECTION TYPE: C, LT WING - NR 4 VC FLAP O/B ROTARY ACTUATOR SUPPORT RIB MOUNT BOLT HOLES BORE AREA FOUND CORROSION AT HOLE NR 1, 2, 4, 5, 7 & 8 ( VIEW FROM I/B ). BOLT HOLES CORROSION REMOVED AND INTERIM REPAIRED AS PER RS 57-41-35014 AND UPS EO B747-5740-18687-A.

Part: RIB — CORRODED (NR 5 FLAP) · airframe 100,611 hrs · 25,820 cycles

INSPECTION TYPE: C, LT WING, NR 5 VC FLAP O/B ROTARY ACTUATOR SUPPORT RIB MOUNT BOLT HOLES BORE AREA FOUND CORROSION AT HOLE NR 5 AND 6 ( VIEW FROM I/B ). BOLT HOLE CORROSION REMOVED AND INTERIM REPAIRED AS PER RS 57-41-35014 AND UPS EO B747-5740-18687-A.

Part: RIB — CORRODED (NR 10 FLAP) · airframe 100,611 hrs · 25,820 cycles

INSPECTION TYPE: C, LT WING - NR 10 VC FLAP O/B I/B ROTARY ACTUATOR SUPPORT RIB MOUNT BOLT HOLES BORE AREA FOUND CORROSION AT HOLE NR 3,4,5 & 6. (VIEW FROM I/B ). BOLT HOLES CORROSION REMOVED AND INTERIM REPAIRED AS PER HX RS 57-41-35014 AND UPS EO B747-5740-18687-A.

Part: SEAT TRACK — CORRODED (FUSELAGE) · airframe 100,611 hrs · 25,820 cycles

M/D - SEAT TRACK I/B FLANGE CORROSION. CUTOUT SEAT TRACK REPAIRED PER SRM 53-10-05 FIG 1A. CORROSION BLEND OUT 0.050 X 1 X 1 INCH. EXCEED SRM LIMIT.

Part: FRAME — CRACKED (FUSELAGE) · airframe 100,611 hrs · 25,820 cycles

INSPECTION TYPE: C, M/D - BS 1920, BETWEEN STR 13-14R, FRAME I/B CHORD EXTEND CRACK FOUND ON PREVIOUSLY REPAIR. FRAME REPAIRED AS PER SRM 51-40-03 FIG.1.

Part: FRAME — CRACKED (FUSELAGE) · airframe 100,611 hrs · 25,820 cycles

INSPECTION TYPE: C, BS 2180, BET STRINGER 25-26L FRAME WEB FOUND CRACK. M/D FX FRAME WEB REPAIRED AT BS 2180 BTN STR 25L AND STR 26L PER SRM 53-10-04 FIG.39.

Part: FRAME — CRACKED (FUSELAGE) · airframe 100,611 hrs · 25,820 cycles

INSPECTION TYPE: C, BS 2180 BET STR 24 - 25L. FRAME WEB FOUND CRACK. FX FRAME WEB REPAIRED AT BS 2180 BTN STR 24L AND STR 25L AS PER SRM 53-10-04 FIG 39.

Part: FRAME — CRACKED (FUSELAGE) · airframe 100,611 hrs · 25,820 cycles

INSPECTION TYPE: C, BS 2180 RT STR 25R FRAME FOUND CRACKED. FRAME REPAIRED AS PER SRM 53-10-04 FIG 39.

Part: SEAT TRACK — CORRODED (FUSELAGE) · airframe 100,611 hrs · 25,820 cycles

INSPECTION TYPE: C, SEAT TRACK O/B FLANGE UNDER SURFACE CORROSION. BS 670 - 810 RBL 11 SEAT TRACK REPAIRED PER SRM 53-10-05 FIG 14. CORROSION BLEND OUT 0.030 X 1 X 1 INCHES. EXCEED SRM LIMIT.

Part: SUPPORT BRACKET — CORRODED (KEEL BEAM) · airframe 100,611 hrs · 25,820 cycles

KEEL BEAM PANEL SUPPORT BRACKET FOUND SURFACE CORROSION AT STA 1226 LBL 9. BRACKET REPLACED AS PER SRM 51-10-01. CORROSION BLEND OUT 0.030 X 1 X 1 INCHES. EXCEED SRM LIMIT.

Part: FRAME — CRACKED (FUSELAGE) · airframe 100,611 hrs · 25,820 cycles

INSPECTION TYPE: C, M/D - BS 2220 RT STRINGER 26R FRAME FOUND CRACKED. M/D BS 2220 RT FRAME REPAIRED AT BETWEEN STR 24R TO 34R AS PER SRM 53-10-04 FIG.100 & BOEING MSG UPS-HKF-03-00059H /61F FOR DETAIL.

Part: SEAT TRACK — CORRODED (FUSELAGE) · airframe 100,611 hrs · 25,820 cycles

INSPECTION TYPE: C, SEAT TRACK O/B FLANGE CORROSION. SEAT TRACK REPAIR AT BS 670 - 810 RBL 11. REF NRC 6876. CORROSION BLEND OUT 0.050 X 1 X 2 INCHES.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · airframe 100,611 hrs · 25,820 cycles

M/D - FLOOR SUPPORT HEAD SECTION FOUND CORROSION AT LOWER FACE AS MARKED. CORRODED HAT SECTION REPLACED AS PER SRM 51-10-01. CORROSION BLEND OUT 0.030 X 1 X 2 INCHES. EXCEED SRM LIMIT.

Part: STRINGER CLIP — CRACKED (FUSELAGE) · airframe 100,611 hrs · 25,820 cycles

BULK CARGO COMPT - BS 2020 STR 34L STRINGER CLIP UPPER EDGE FOUND CRACKED. BS 2020 STR 34L STRINGER CLIP REPLACED AS PER SRM 51-10-01 PAGE 8.

Part: FRAME — CRACKED (FUSELAGE) · airframe 100,611 hrs · 25,820 cycles

INSPECTION TYPE: C, BS 2120 BET STR 25 - 26L FRAME WEB FOUND CRACK. M/D FX FRAME WEB REPAIRED AT BS 2120 BTN STR 25L AND STR 26L AS PER SRM 53-10-04 FIG 39.

Part: STRUCTURE — CORRODED (FUSELAGE) · airframe 100,611 hrs · 25,820 cycles

M/D - HAT SECTION FWD FLANGE UPPER AND LOWER SURFACE CORROSION. CORRODED HAT SECTION REPLACED AS PER SRM 51-10-01 PAGE 8. CORROSION BLEND OUT 0.030 X 1 X 1 INCHES. EXCEED SRM LIMIT.

Part: SUPPORT BRACKET — CORRODED (FUSELAGE) · airframe 100,611 hrs · 25,820 cycles

INSPECTION TYPE: C, KEELBEAM PANEL SUPPORT ATT BRACKET FOUND SURFACE CORROSION AT STA 1285 TO STA 1286 RBL 8 TO RBL 9. CORROSION BLEND OUT ( 0.030 X 1 X 1 INCHES) BRACKET REPLACED AS PER SRM 51-10-01.

Part: SEAT TRACK — CORRODED (FUSELAGE) · airframe 100,611 hrs · 25,820 cycles

INSPECTION TYPE: C, SEAT TRACK FOUND CORROSION AT 520 - 575 LBL 46. SEAT TRACK REPAIRED AT U/D BS 480 - 590 LBL 46 AS PER SRM 53-10-05 FIG 1A. CORROSION BLEND OUT 0.045 X 1 X 10 INCHES. EXCEED SRM LIMIT.

Part: SEAT TRACK — CORRODED (FUSELAGE) · airframe 100,611 hrs · 25,820 cycles

INSPECTION TYPE: C, SEAT TRACK FOUND CORROSION AT BS 560 - 565 LBL 65. SEAT TRACK REPAIRED AT U/D BS 530 - 570 LBL 65 AS PER SRM 53-10-05 FIG 1A. CORROSION BLEND OUT 0.040 X 1 X 10 INCHES. EXCEED SRM LIMIT.

Part: FRAME — CRACKED (FUSELAGE) · airframe 100,611 hrs · 25,820 cycles

INSPECTION TYPE:C M/D - BS 2320 FRAME CRACKED AT STRINGER 26R AS MARKED. FRAME REPAIRED AS PER SRM 51-10-03 FIG.2 AT BS 2320 STR 24R TO STR 34R AREA.

Part: SHEAR TIE — CRACKED (FUSELAGE) · airframe 100,611 hrs · 25,820 cycles

INSPECTION TYPE: C, FWD CARGO COMPT - STA 540 STR 46R TO 47R FRAME SHEAR TIE FOUND CRACKED. FWD CARGO COMPT BS 540 STR 46R - 47R FRAME SHEAR TIE REPLACED AS PER SRM 51-10-01 P.8

Part: BULKHEAD — CRACKED (NR 3 PYLON) · airframe 100,611 hrs · 25,820 cycles

INSPECTION TYPE: C, NR 3 PYLON REAR ENGINE MOUNT BULKHEAD AFT FRAME FOUND CRACKED AT 4 O/C POSITION ( LOOKING FORWARD ). NR 3 PYLON REAR ENGINE MOUNT BULKHEAD REPAIRED AS PER HX RS R54-53-35008 AND UPS REPAIR AUTHORIZATION 747-54-20034 DVI AND HFEC INSPECTIONS TO CONTINUE PER UPS EO B747-5410-13908 IAW SB 747-54A2202.

Part: SHEAR TIE — CRACKED (FUSELAGE) · airframe 100,611 hrs · 25,820 cycles

AFT CARGO BELOW FLOOR SHEAR TIE FOUND CRACKED AT BS 1900 BETWEEN STR 44L AND STR 45L AS MARKED. SHEAR TIE REPAIRED AT BS 1900 BETWEEN STR 44L - 45L AS PER SRM 55-10-04 FIG.3A

Part: FRAME — CRACKED (NR 2 PYLON) · airframe 100,611 hrs · 25,820 cycles

INSPECTION TYPE: C, NR 2 PYLON REAR ENGINE MOUNT BULKHEAD AFT FRAME FOUND CRACKED AT 4 & 5 O/C POSITION ( LOOKING FORWARD ). NR 2 PYLON REAR ENGINE MOUNT BULKHEAD I/B AFT FRAME REPAIRED AS PER RS 54-53-35009 AND UPS REPAIR AUTHORIZATION 747-54-20035 INSPECTIONS OF DVI AND HFEC TO CONTINUE PER UPS EO B747-5410-13908 AND SB 747-54A2202.

Part: FRAME — CRACKED (FUSELAGE) · airframe 100,611 hrs · 25,820 cycles

BS 2320 FRAME CRACKED AT STRINGER 26L AS MARKED. BS 2320 BTN STR 24L - 34L FRAME REPAIRED AS PER SRM 51-40-03 FIG 2.

Part: SUPPORT BRACKET — CORRODED (KEELBEAM) · airframe 100,611 hrs · 25,820 cycles

INSPECTION TYPE: C, KEELBEAM PANEL SUPPORT SURFACE FOUND SURFACE CORROSION AT STA 1276 TO STA 1287 RBL 16. CORROSION BLEND OUT (0.020 X 1 X 1). KEEL BEAM PNL SUPPORT REPLACED AS PER SRM 51-10-01 P.8.

Part: SHEAR TIE — CRACKED (FUSELAGE) · airframe 100,611 hrs · 25,820 cycles

AFT CARGO BELOW FLOOR SHEAR TIE FOUND CRACKED AT BS 1880 BETWEEN STR 43L AND STR 44L AS MARKED. AFT CARGO BELOW FLOOR SHEAR TIE REPAIRED AS PER SRM 53-10-04 FIG 3A AT BS 1880 BTN STR 43L AND STR 44L.

Part: FRAME — CRACKED (NR 2 PYLON) · airframe 100,611 hrs · 25,820 cycles

INSPECTION TYPE: C, NR 2 PYLON REAR ENGINE MOUNT BULKHEAD FORWARD FOUND CRACKED AT 7 O/C POSITION ( LOOKING FWD ). NR 2 PYLON REAR ENGINE MOUNT BULKHEAD O/B FORWARD FRAME REPAIRED AS PER RS 54-53-35009 AND UPS REPAIR 747-54-20035 REPEAT DVI AND HFEC INSPECTIONS EVERY 1200 FLT CYC OR 18 MOUTHS WHICH EVER IS EARLIER . REF UPS IAW SB 747-54A2202.

Part: SUPPORT BRACKET — CORRODED (KEEL BEAM) · airframe 100,611 hrs · 25,820 cycles

KEEL BEAM PANEL SUPPORT BRACKET FOUND SURFACE CORROSION AT STA 1203 LBL 9. SUPPORT BRACKET REPLACED AS PER SRM 51-10-01. CORROSION BLEND OUT 0.030 X 1 X 1 INCHES . EXCEED SRM LIMIT.

Part: SKIN — CRACKED (FUSELAGE) · airframe 100,611 hrs · 25,820 cycles

INSPECTION TYPE: C, AFT CARGO DOOR CUTOUT FWD UPPER CORNER FOUND ONE EACH HOLE CRACK AT SKIN AT SEVEN O'CLOCK POSITION 0.040 INCHES IN LENGTH AS MARKED. AFT CARGO DOOR CUTOUT FWD UPPER CORNER REPAIRED AS PER SRM 53-30-03 FIG 62. CAT B REPAIR REQUIRES REPEAT INSPECTION THRESHOLD AT 15,000 CYCLES AFTER REPAIR INSTALLATION AND REPEAT AT 3,000 CYC INTEVAL PER SRM.

Part: STRINGER — CORRODED (FUSELAGE) · airframe 100,611 hrs · 25,820 cycles

AFT CARGO COMPT - BS 1540 STRINGER 34 RT FOUND CORRODED. AFT CARGO COMPT BS 1540 STR 34R REPAIRED AS PER SRM 53-10-03 FIG 1.

Part: SKIN — BULGED (RT WING) · airframe 100,611 hrs · 25,820 cycles

INSPECTION TYPE:C, RT WING UPPER SURFACE RABBET AREA FOUND BULGED AT WS 1460 ( AFT NO.26 V/C FLAP ). CORR BLEND OUT 0.087 X 2 X 4 INCHES. REMAINING THICKNESS RANGED FROM .050 TO .071 INCH. RHW.UPPER.SKIN.SURFACE.REPAIR.AS PER.RS.R57-25-35006.A .WS.1460.AND.UPS.ENG'R.FILE.747-57-20040.

Part: BULKHEAD — CRACKED (FUSELAGE) · airframe 100,611 hrs · 25,820 cycles

INSPECTION TYPE: C, FX - LOWER FUSELAGE BULKHEAD ATTACH WEB FOUND CRACKED AT STA 1480 RBL 90 WL 120 ( AS MARKED). WEB REPAIRED AS PER SRM 51-40-02 FIG.1.

Part: SHEAR TIE — CORRODED (FUSELAGE) · airframe 100,611 hrs · 25,820 cycles

INSPECTION TYPE: C, FWD CARGO COMPT - BS 500 S-39R TO 40R FRAME SHEAR TIE SURFACE CORROSION REVEALED. SHEAR TIE REPAIRED AT BS 500 STR 39 - 40R AS PER SRM 53-10-04 FIG 3. CORROSION BLEND OUT 0.030" X 1" X 1".

Part: FRAME — CRACKED (FUSELAGE) · airframe 100,611 hrs · 25,820 cycles

FWD CARGO - BELL FRAME FOUND CRACK AT STA 660, STR 38L AREA AS MARKED. FRAME REPAIRED AS PER SRM 53-10-04 FIG 52.

Part: SPAR — CORRODED (NR 4 SLAT) · airframe 100,611 hrs · 25,820 cycles

INSPECTION TYPE: C, LT WING UPPER SURFACE FRONT SPAR RABBET PANEL FOUND BULGE AT NR 4 SLAT O/B AREA AS MARKED. LT WING UPPER SURFACE FRONT SPAR REPAIRED AS RS R57-25-35006 AND ENGINEERING FILE NUMBER : 747-57-20040 AT NR 4 SLAT O/B AREA WS 1294.

Part: SKIN — CRACKED (NR 3 PYLON) · airframe 100,611 hrs · 25,820 cycles

NR 3 PYLON ACCESS PANEL 473EL CUTOUT UPPER EDGE RIVET HOLE LOWER EDGE SUSPECT CRACK REVEALED AS MARKED. SKIN REPAIRED PER SRM 54-30-03 FIG 17B.

Part: SKIN — CRACKED (NR 3 PYLON) · airframe 100,611 hrs · 25,820 cycles

INSPECTION TYPE: C, NR 3 PYLON EXTERIOR SURFACE SKIN NAC STA 218.9 LHS 1EA RIVET HOLE UPPER AND LOWER EDGE SUSPECT CRACKS ARE FOUND AS MARKED. NR 3 PYLN EXTERIOR SKIN REPAIRED AT I/B SIDE AS PER RS R54-50-35005 AND UPS EO B747-5410-18686-A DVI THE REPAIRED AREA FOR CRACKS OR DAMAGE AT 18 MOUTHS INTERVAL.

Part: SPAR — CORRODED (NR 3 SLAT) · airframe 100,611 hrs · 25,820 cycles

INSPECTION TYPE: C, LT WING UPPER SURFACE FRONT SPAR RABBET AREA PANEL FOUND BULGE AT NR 3 SLAT I/B AREA AS MARKED. LT WING UPPER SURFACE FRONT SPAR REPAIRED AS PER RS R57-25-35006 AND ENGINEERING FILE NUMBER 747-57-20040 AT NR 3 SLAT I/B AREA WS 1336

Part: SLEEVE — DEBONDED (NR 1 ENGINE) · airframe 100,611 hrs · 25,820 cycles

INSPECTION TYPE: C, NR 1 ENGINE - FAN THRUST REVERSER SLEEVE DEBOND REVEALED AT EXTERNAL SKIN BETWEEN 8 AND 9 O'CLOCK POSITION. NR 1 ENGINE THRUST REVERSER SLEEVE REPAIRED AS PER RS R-78-30-35003 AND UPS UPS EO B747-7830-18689-A.

Part: SLEEVE — DEBONDED (NR 1 ENGINE) · airframe 100,611 hrs · 25,820 cycles

INSPECTION TYPE: C, NR 1 ENGINE - FAN THRUST REVERSER SLEEVE DEBONDED REVEALED AT EXTERNAL SKIN BETWEEN 3 AND 4 O'CLOCK. NR 1 ENGINE THRUST REVERSER SLEEVE REPAIRED AS RS R78-30-35003 AND UPS EO B747-7830-18689-A.

Part: MODULE — MALFUNCTIONED (CABIN)

INSPECTION TYPE: PFLT, EMERGENCY LIGHTS SYSTEM UNARMED LIGHT WILL NOT TEST USING OVERHEAD IND LIGHTS TEST SWITCH. NOTE: LIGHT WILL ILLUMINATE WITH EMERGENCY LIGHTS SWITCH IN ON POSITION. REMOVED AND REPLACED EMERGENCY LIGHT CONTROL MODULE PER 33-51-09, OPS CKS NORMAL AND UNARMED LIGHT ILLUMINATED WITH TEST SWITCH WHEN ON SELECTED.

Part: STRAP — CRACKED (NR 3 PYLON) · airframe 98,652 hrs · 5,369 cycles

INSPECTION TYPE:N/A NR 3 PYLON REAR ENG, MOUNT BULKHEAD FRAME STRAP CRACKED AT I/B AREA JUST ABOVE AFT LOWER SPAR. REPAIR CUTOUT AS PER SRM 54-10-03 FIG 18, 54-30-03 FIG 35 & 54-30-03 FIG 36.

Part: FIREWALL — CRACKED (NR 2 PYLON) · airframe 98,656 hrs · 25,369 cycles

INSPECTION TYPE: NR 2 PYLON LOWER FIREWALL WEB O/B POSN CRACKED AT NAC 221.9 REAR ENGINE MOUNT BULKHEAD AREA. NR 2 PYLON LOWER FIREWALL WEB REPAIRED AS PER SRM 54-10-03 FIG 2.

Part: LIGHT — INOPERATIVE (MAIN CARGO DECK)

INSPECTION TYPE:PFLT 2 EMERGENCY LIGHTS OUT ON MAIN CARGO DECK CEILING. ONLY 2 LIGHT ASSY ARE REQUIRED PER MM 33-51-00 PAGE 501. BOTH LIGHT ASSY OPS CHECK GOOD AT THIS TIME.

Part: KEELBEAM — CRACKED (FUSELAGE) · airframe 97,980 hrs · 25,233 cycles

INSPECTION TYPE:SP, THREE CRACKS IN LT WHEEL WELL, LOWER KEEL BEAM AREA SURROUNDING STRUCTURE. REPAIRED AREA IAW SRM 53-10-09 FIG 1.

Part: ENGINE — FAILED (NR 4)

INSPECTION TYPE:N/A DURING CLIMBOUT, THE NR 4 ENG SURGED LOUDLY AND VIOLENTLY MULTIPLY TIMES WITH VISIBLE FLAMES SHOOTING OUT OF THE INLET. YAW ASSOCIATED WITH SURGES. OIL TEMP READ OVER 135 EGT 946 OIL QUANTITY 5.3, N2, 18 PERCENT. RAN CHECKLISTS AT TOD, HAD 10 PSI OIL QTY 5.3 NR 4 EDP SELECTED TO SUPPLY OFF AT AROUND 1135 WINDMILLED FOR 17 MINUTES. LANDING UNEVENTFUL. REPLACED NR 4 ENGINE IAW TASK CARD NR 5000. ENG S/N ON 662410, ENG S/N OFF P610981.

Part: ANGLE — CORRODED (FUSELAGE) · airframe 97,510 hrs · 25,124 cycles

INSPECTION TYPE:C LEFT BS 1350 FWD CHORD ANGLE I/B AND FWD MATING SURFACE FOUND CORROSION AFTER FWD UPPER BATHTUB FITTING REMOVAL. LEFT BS 1350 FWD CHORD ANGLE I/B AND FWD MATING UPPER CHORD CORROSION CLEANED UP AND REPAIRED AS PER HX RS R 53-43-34687 ITEM C1.

Part: SKIN — CRACKED (FUSELAGE) · airframe 97,510 hrs · 25,124 cycles

INSPECTION TYPE:C CRACK REVEALED ON SKIN AT ONE EA BOLT HOLE AT LT BS 1350 UPPER FWD FITTING AREA AT LOWER MOST AND AFT ONE BY APPROX 0.030 INCH LONG AS PER ATTACH FIGURE. CRACKED HOLE FINAL REAMED TO 0.625 INCH AND CONFIRMED CRACK FREE, A BOLT P/N: BACB30UU10K WAS INSTALLED AS PER HX RS R53-43-34687 ITEM C3 REQUIREMENT.

Part: SILL — CORRODED (FUSELAGE) · airframe 97,510 hrs · 25,124 cycles

INSPECTION TYPE:C LEFT BS 1350 UPPER FWD SHEAR BATHTUB ATTACH FITTING SILL UPPER MATING SURFACE FOUND CORROSION AFTER FITTINGS REMOVAL. LEFT BS 1350 UPPER FWD SHEAR BATHTUB ATTACH FITTING SILL UPPER MATING CORROSION CLEANED UP AND REPAIRED AS PER HX RS R53-43-34687 ITEM C3.

Part: SPLICE — CORRODED (FUSELAGE) · airframe 97,510 hrs · 25,124 cycles

INSPECTION TYPE:C BS 1350 SKIN SPLICE STRAP I/B FACE FWD UPPER BATHTUB FITTING MATING SURFACE AREA FOUND CORROSION AFTER FITTING REMOVAL. BS 1350 SKIN SPLICE STRAP I/B FACE FWD UPPER BATHTUB FITTING MATING SURFACE AREA CORROSION CLEANED UP AND REPAIRED AS PER HX RS R 53-43-34687 ITEM C2.

Part: SILL — CORRODED (FUSELAGE) · airframe 97,510 hrs · 25,124 cycles

INSPECTION TYPE:C LEFT BS 1350 ATTACH FITTING LWR SILL CTR BOLT HOLE BORE COMMON TO FWD UPPER BATHTUB FITTING BASE HOLE FOUND CORROSION AFTER BOLT REMOVAL. LEFT BS 1350 ATTACH FITTING LWR SILL CTR BOLT HOLE BORE COMMON TO FWD UPPER BATHTUB FITTING BASE HOLE REAMED 1.343 INCH AND CONFIRM CORROSION CLEANED UP, HOLE FINALLY OVERSIZED TO 1.375 INCH AND BOLT P/N BACB30US22K86, INSTALLED TOGETHER WITH TAPE FILLER AND ALIGNMENT WASHER SA PER HX RS R53-43-34687 ITEM C3 REQUIREMENT.

Part: BULKHEAD — CORRODED (FUSELAGE) · airframe 97,510 hrs · 25,124 cycles

INSPECTION TYPE:C LEFT BS 1350 BULKHEAD WEB O/B LWR CORNER FWD FACE FOUND CORROSION AFTER UPPER FWD SHEAR AND BATHTUB FITTING REMOVAL. LEFT BS 1350 BULKHEAD WEB O/B LOWER CORNER FWD FACE CORROSION CLEANED UP AND REPAIRED AS PER HX RS R53-43-34687 ITEM C2.

Part: FITTING — CRACKED (FUSELAGE) · airframe 97,510 hrs · 25,124 cycles

INSPECTION TYPE:C BS 1350 UPPER AFT SHEAR / BATHTUB FITTING ATTACH BOLT HOLE, ONE EACH HOLE FOUND CRACK AT STRAP INNER SURFACE 8 O'CLOCK POSITION VIEW LOOKING O/B, .125 INCH APPROX. REFER ATTACHED DRAWING FOR LOCATION. FASTENER HOLE CRACK CLEARED AFTER REAMED TO 0.500 INCH, HOLE FINAL OVERSIZED TO 0.562 INCH AND INSTALLED WITH FREEZE PLUG AS THE REPAIR REQUIREMENT OF HX RS R53-43-34687 ITEM B3.

Part: FITTING — CORRODED (FUSELAGE) · airframe 97,510 hrs · 25,124 cycles

INSPECTION TYPE:C LEFT BS 1350 FWD BATHTUB FITTING CORROSION FOUND AT BOTTOM AREA. FWD UPPER BATHTUB FITTING REPLACED AS PER HX RS 53-43-34687, SRM 51-10-01.

Part: SILL — CORRODED (FUSELAGE) · airframe 97,510 hrs · 25,124 cycles

INSPECTION TYPE:C LEFT BS 1350 UPPER FWD SHEAR / BATHTUB ATTACH FITTING LWR SILL O/B SILL O/B FLANGE AFT HOLE FOUND CORROSION AFTER BOLT REMOVAL. LEFT BS 1350 UPPER FWD SHEAR / BATHTUB ATTACH FITTING LWR SILL O/B SILL O/B FLANGE AFT HOLE CORROSION CLEANED UP AFTER HOLE REAMED TO FINAL SIZE 0.812 INCH. REPAIRED CARRIED OUT AS PER HX RS R53-43-34687 ITEM C3.

Part: SILL — CORRODED (FUSELAGE) · airframe 97,510 hrs · 25,124 cycles

INSPECTION TYPE:C LEFT BS 1350 UPPER FWD SHEAR / BATHTUB ATTACH FITTING LWR SILL O/B FLANGE FWD HOLE FOUND CORROSION AFTER BOLT REMOVAL. LEFT BS 1350 UPPER FWD SHEAR / BATHTUB ATTACH FITTING LWR SILL O/B FLANGE FWD HOLE CORROSION CLEANED UP AFTER HOLE REAMED TO FINAL SIZE 0.812 INCH. REPAIRED CARRIED AT AS PER HX RS R53-43-34687 ITEM C3.

Part: SPLICE — CORRODED (FUSELAGE) · airframe 97,510 hrs · 25,124 cycles

INSPECTION TYPE:C BS 1350 SKIN SPLICE STRAP I/B FACE AFT UPPER BATHTUB FITTING MATING SURFACE AREA FOUND CORROSION AFTER FITTING REMOVAL. BS 1350 SKIN SPLICE STRAP I/B FACE AFT UPPER BATHTUB FITTING MATING SURFACE AREA CORROSION CLEANED UP AND REPAIRED AS PER HX RS R53-43-34687 ITEM B2 WITH 1EA SPLICE STRAP AT BS 1350 S29 - S31 AREA REPLACED AS PER SRM 51-10-01.

Part: SPLICE — CORRODED (FUSELAGE) · airframe 97,510 hrs · 25,124 cycles

INSPECTION TYPE:C BS 1350 SKIN SPLICE STRAP I/B FACE AFT UPPER BATHTUB FITTING MATING SURFACE AREA FOUND CORROSION AFTER FITTING REMOVAL. FX BS 1350 LT AFT SPLICE ANGLE AT S29 TO 31L REPLACED PER SRM 51-10-01.

Part: SILL — CORRODED (FUSELAGE) · airframe 97,510 hrs · 25,124 cycles

INSPECTION TYPE:C FX - LEFT BS 1350 UPPER AFT SHEAR / BATHTUB ATTACH FITTING LWR SILL O/B FLANGE FWD HOLE FOUND CORROSION AFTER BOLT REMOVAL. FX - LEFT BS 1350 UPPER AFT SHEAR / BATHTUB ATTACH FITTING LWR SILL O/B FLANGE FWD HOLE CORROSION CLEANED UP AFTER HOLE REAMED TO FINAL SIZE 0.812 INCH. REPAIRED CARRIED OUT AS PER HX RS R53-43-34687 ITEM C3.

Part: FITTING — CORRODED (FUSELAGE) · airframe 97,510 hrs · 25,124 cycles

INSPECTION TYPE:C LT BS 1350 UPPER AFT SHEAR / BATHTUB ATTACH FITTING LWR SILL UPPER MATING SURFACE, FOUND CORROSION AFTER FITTINGS REMOVAL. LT BS 1350 UPPER AFT SHEAR / BATHTUB ATTACH FITTING SPLICE FITTING OTHER UPPER MATING SURFACE CORROSION CLEANED UP, REPAIRED AS PER HX RS R54-43-34687 ITEM B1.

Part: BULKHEAD — CORRODED (FUSELAGE) · airframe 97,510 hrs · 25,124 cycles

INSPECTION TYPE:C LEFT BS 1350 BULKHEAD WEB O/B LWR CORNER REAR FACE FOUND CORROSION AFTER UPPER AFT SHEAR AND BATHTUB FITTING REMOVAL. LEFT BS 1350 BULKHEAD WEB O/B LWR CORNER REAR FACE CORROSION CLEANED UP AND REPAIRED AS PER HX RS R53-43-34687 ITEM B2.

Part: FITTING — CORRODED (FUSELAGE) · airframe 97,510 hrs · 25,124 cycles

INSPECTION TYPE:C LT BS 1350 UPPER AFT BATHTUB FITTING LOWER PORTION MATING SURFACES FOUND HEAVY CORROSION AFTER FITTING REMOVAL. FX LT BS 1350 UPPER AFT BOTH LOWER FITTING REPAIRED PER SRM 51-10-01.

Part: SILL — CORRODED (FUSELAGE) · airframe 97,510 hrs · 25,124 cycles

INSPECTION TYPE:C FX - LEFT BS 1350 UPPER AFT SHEAR / BATHTUB ATTACH FITTING LWR SILL O/B FLANGE AFT HOLE FOUND CORROSION AFTER BOLT REMOVAL. FX - LEFT BS 1350 UPPER AFT SHEAR / BATHTUB ATTACH FITTING LWR SILL O/B FLANGE AFT HOLE CORROSION CLEANED UP AFTER HOLE REAMED TO FINAL SIZE 0.812 INCH. REPAIRED CARRIED OUT AS PER HX RS R53-43-34687 ITEM C3.

Part: SHEAR TIE — CRACKED (FUSELAGE) · airframe 97,510 hrs · 25,124 cycles

INSPECTION TYPE:C M/D, SHEAR TIE CRACKED, BETWEEN S-3R AND S-4R STA 1960. SHEAR TIE REPLACED PER SRM 51-10-01.

Part: STRINGER — CRACKED (FUSELAGE) · airframe 97,510 hrs · 25,124 cycles

INSPECTION TYPE:C M/D STA 1940 - 1960 STRINGER 4R FOUND CRACKED. REPAIRED FUSELAGE STRINGER BETWEEN BS 1940 TO BS 1960, S-4R AS PER RS R53-61-34689.

Part: STIFFENER — CRACKED (FUSELAGE) · airframe 97,510 hrs · 25,124 cycles

INSPECTION TYPE:C NOSE TUNNEL BTN BS 280 - 300 RT VERT BEAM NR 1 LONG STIFFENER FOUND CRACKED. STIFFENER REPLACED IAW SRM 51-10-01.

Part: SKIN — DAMAGED (FUSELAGE) · airframe 97,510 hrs · 25,124 cycles

INSPECTION TYPE:C REFER EO B747-5330-13494, REMOVE EXISTING REPAIR AND ACCOMPLISH SRM REPAIR AT BS 1898 - 1906, STR 41R - 42R, DUE EXISTING REPAIR FOUND STRUCTURALLY UNSATISFACTORY. BS 1898 - 1920 STR 39R - 42R SKIN CRACKED AREA TRIMMED OFF AND CRACK FREE CHECKED BY NDT, SKIN REPAIR CARRIED OUT AS PER SRM 52-00-03 FIG 4.

Part: SKIN — DAMAGED (CARGO DOOR) · airframe 97,510 hrs · 25,124 cycles

INSPECTION TYPE:C REFER EO B747-5330-13494, REMOVE EXISTING REPAIR AND ACCOMPLISH SRM REPAIR AT BS 1906 - 1920, STR 39R - 42R DUE EXISTING REPAIR FOUND STRUCTURALLY UNSATISFACTORY. AFT CARGO COMPT DOOR OUTER SKIN AT BS 1886 - BS 1920 STRINGER 39R - S42R AREA REPAIRED AS PER SRM 52-00-03 FIG 4.

Part: SKIN — DAMAGED (FUSELAGE) · airframe 97,510 hrs · 25,124 cycles

INSPECTION TYPE:C REFER EO B747-5330-13494, REMOVE EXISTING REPAIR AND ACCOMPLISH SRM REPAIR AT BS 220 STR 15R - 17R DUE EXISTING REPAIR FOUND STRUCTURALLY UNSATISFACTORY. REPAIRED FUSELAGE SKIN AS PER SRM 53-30-03 FIG 47.

Part: SKIN — DAMAGED (FUSELAGE) · airframe 97,510 hrs · 25,124 cycles

INSPECTION TYPE:C REFER EO B747-5330-13494, REMOVE EXISTING REPAIR AND ACCOMPLISH SRM REPAIR AT BS 1950 - 1960, STR 3R - 4R, DUE EXISTING REPAIR FOUND STRUCTURALLY UNSATISFACTORY. FUSELAGE SKIN AT BS 1946 TO BS 1960 STRINGER 3R - 4R AREA REPAIRED AS PER SRM 53-30-03 FIG 48.

Part: STRINGER — CORRODED (FUSELAGE) · airframe 97,510 hrs · 25,124 cycles

INSPECTION TYPE: C, FWD CARGO COMPT STA 980 RT STR 47R CORROSION FOUND AS MARKED. FWD CARGO BS 950 - 980 STR 47R STRINGER REPAIR PER SRM 53-10-03 FIG 1.

Part: SKIN — DAMAGED (FUSELAGE) · airframe 97,510 hrs · 25,124 cycles

INSPECTION TYPE:C REFER EO B747-5330-13494, REMOVE EXISTING REPAIRS AND ACCOMPLISH SRM REPAIR AT BS 1605 STR 44L - 45L AND BS 1610 STR 44L - 45L, DUE EXISTING REPAIR FOUND STRUCTURALLY UNSATISFACTORY.

Part: STRINGER — CORRODED (FUSELAGE) · airframe 97,510 hrs · 25,124 cycles

INSPECTION TYPE:C AFT CARGO BAY STR 51R FOUND CORROSION AT STA 1880. AFT CARGO COMPT STR 51R AT BS 1870 - 1890 REPAIR PER SRM 53-10-03 FIG 8.

Part: SKIN — DAMAGED (FUSELAGE) · airframe 97,510 hrs · 25,124 cycles

INSPECTION TYPE:C REFER EO B747-5330-13494, REMOVE EXISTING REPAIR AND ACCOMPLISH SRM REPAIR AT BS 740 - 750, STR 34R DUE EXISTING REPAIR FOUND STRUCTURALLY UNSATISFACTORY. FUSELAGE SKIN AT BS 740 - 750 STRINGER 34R AREA REPAIRED AS PER SRM 53-30-03 FIG 48.

Part: SKIN — DAMAGED (CARGO DOOR) · airframe 97,510 hrs · 25,124 cycles

INSPECTION TYPE:C REF EO B747-5330-13494, REMOVE EXISTING REPAIR AND ACCOMPLISH SRM REPAIR AT BS 662 670 STR 30R - 33R DUE EXISTING REPAIR FOUND STRUCTURALLY UNSATISFACTORY. FWD CARGO COMPT DOOR OUTER SKIN AT BS 662 - BS 670 STRINGER 30R - S34R AREA REPAIRED AS PER SRM 52-00-03 FIG 4.

Part: STOP FITTING — CRACKED (CARGO DOOR) · airframe 97,510 hrs · 25,124 cycles

INSPECTION TYPE:C FX - BULK CARGO DOOR AFT EDGE NR 5 STOP FITTING INNER ATTACH FITTING FOUND CRACK AS MARKED (COUNT FROM TOP). BULK CARGO DOOR AFT EDGE NR 5 STOP FITTING REPLACED AS PER SRM 51-10-01.

Part: SHEAR TIE — CRACKED (FUSELAGE) · airframe 97,510 hrs · 25,124 cycles

INSPECTION TYPE:C FWD CARGO COMPARTMENT STA 980 RT STR 45 - 46 FRAME SHEAR TIE CORROSION AND CRACK FOUND AS MARKED. THE CORRODED SHEAR TIE WAS TRIMMED OFF, AND WAS REPAIRED AS PER SRM 53-10-04 FIG 3 HFEC INSP CONFIRMED CRACK FREE AS PER NTM PT6, 51-00-00 FIG 4.

Part: SKIN — DAMAGED (CARGO DOOR) · airframe 97,510 hrs · 25,124 cycles

INSPECTION TYPE:C REFER EO B747-5330-13494, REMOVE EXISTING REPAIR AND ACCOMPLISH SRM REPAIR AT BS 670 STR 33R - 34R, DUE EXISTING REPAIR FOUND STRUCTURALLY UNSATISFACTORY. FWD CARGO COMPT DOOR OUTER SKIN AT BS 662 - 670 STRINGER 30R - 34R AREA REPAIRED AS PER SRM 52-00-03 FIG 4.

Part: SKIN — DAMAGED (FUSELAGE) · airframe 97,510 hrs · 25,124 cycles

INSPECTION TYPE:C REFER EO B747-5330-13494, REMOVE EXISTING REPAIR AND ACCOMPLISH SRM REPAIR AT BS 920 - 940, STR 39L, DUE EXISTING REPAIR FOUND STRUCTURALLY UNSATISFACTORY. FUSELAGE SKIN AT BS 920 - 940 STRINGER 39L AREA REPAIRED AS PER SRM 53-30-03 FIG 11.

Part: SKIN — DAMAGED (FUSELAGE) · airframe 97,510 hrs · 25,124 cycles

INSPECTION TYPE:C REFER EO B747-5330-13494, REMOVE EXISTING REPAIR AND ACCOMPLISH SRM REPAIR AT BS 140 - 150 STR 30R - 34R DUE EXISTING REPAIR FOUND STRUCTURALLY UNSATISFACTORY. FUSELAGE SKIN AT BS 140 - BS 150 STRINGER 30R TO S40R AREA REPAIRED AS PER SRM 53-30-03 FIG 1

Part: SKIN — DAMAGED (FUSELAGE) · airframe 97,510 hrs · 25,124 cycles

INSPECTION TYPE:C REFER EO B747-5330-13494, REMOVE EXISTING REPAIR AND ACCOMPLISH SRM REPAIR AT BS 140 - 150, STR 15L - 19L, DUE TO EXISTING REPAIR FOUND STRUCTURALLY UNSATISFACTORY. FUSELAGE SKIN AT BS 140 - BS 150 S15L - 19L AREA REPAIRED AS PER SRM 5303 FIG 1.

Part: SKIN — CRACKED (LT MLG DOOR) · airframe 97,510 hrs · 25,124 cycles

INSPECTION TYPE:C LT BLG I/B W/W DOOR I/B REAR FACE NEAR MID END AREA FOUND CRACK AND BULGE UP AS MARKED. LT BLG I/B W/W DOOR I/B REAR FACE SKIN PNL REPAIRED PER SRM 51-40-02 FIG 1.

Part: SKIN — DAMAGED (FUSELAGE) · airframe 97,510 hrs · 25,124 cycles

INSPECTION TYPE:C REFER EO B747-5330-13494, REMOVE EXISTING REPAIR AND ACCOMPLISH SRM REPAIR AT BS825 - 835 STR 47L - 47R DUE TO EXISTING REPAIR FOUND STRUCTURALLY UNSATISFACTORY. FUSELAGE SKIN AT BS 825 - 835 S47L - 47R AREA REPAIRED AS PER SRM 53-30-03 FIG 1.

Part: DOOR FRAME — CRACKED (FUSELAGE) · airframe 97,510 hrs · 25,124 cycles

INSPECTION TYPE:C M/D, MED NR 1L CUTOUT FWD FRAME BS 434 1EA HOLE CRACK AT FRAME WEB. REPAIRED FRAME WEB AT LT BS 434 S-21L TO S-26L AS PER SRM 53-10-04 FIG 99.

Part: FRAME — WORN (NR 2 PYLON) · airframe 97,510 hrs · 25,124 cycles

INSPECTION TYPE:C NR 2 ENG FWD BHD FOR ENG FRONT MOUNT ATTACH, THE I/B CHORD LOWER SECTION HAS A MINOR DENT MARK WHICH WAS PREVIOUSLY SMOOTHED OUT. NDT INSP FOUND THE THICKNESS OF THE CHORD WORN OUT 25% APPROX IT'S OUT OF SRM LIMIT 54-10-01 FIG 1. THE FWD ENGINE MOUNT ATTACHED BHD CHORD WAS REPLACED IAW SRM 51-10-01 PG 8. THE ENGINE FWD MOUNT FTGS ( I/B AND O/B ) WERE REFITTED PER MM 20-51-01 AND THE ANTI-ICING DUCT WAS REFITTED AND LEAK CHK CARRIED OUT PER MM 30-21-06.

Part: FITTING — CRACKED (FUSELAGE) · airframe 97,510 hrs · 25,124 cycles

INSPECTION TYPE:C LEFT SIDE BS 1350 BULKHEAD SHEAR FITTING ONE BOLT HOLE FOUND CRACK AT THE LOCATION FWD SIDE OF THE VERTICAL FLANGE 2 O'CLOCK POSITION VIEW LOOKING AFT .125 INCH APPROX. LEFT BS 1350 BULKHEAD FWD UPPER CRACKED SHEAR FITTING WAS REPLACED AS PER BOEING SB 747-53-2213 INCLUDING FIG 3, 6, 10, 11 AND 12. ALSO DURING FITTING REPLACEMENT, ADJACENT STRUCTURE FOUND CORROSION AND SKIN HOLE CRACK.

Part: FITTING — CRACKED (FUSELAGE) · airframe 97,510 hrs · 25,124 cycles

INSPECTION TYPE:C LEFT SIDE BS 1350 BULKHEAD SHEAR FITTING AFT SIDE CRACK FOUND AT THE LOCATION OF VERTICAL FLANGE O/B AREA THE CRACK THRU TWO BOLT HOLES 3.5 INCH LENGTH. LEFT BS 1350 BULKHEAD AFT UPPER CRACKED SHEAR FITTING WAS REPLACED AS PER BOEING SB 747-53-2213 INCLUDING FIG 3, 4, 8, 9 & 12. ALSO DURING FITTING REPLACEMENT ADJACANT STRUCTURE FOUND CORROSION AND SKIN CRACK.

Part: FITTING — CRACKED (FUSELAGE) · airframe 97,510 hrs · 25,124 cycles

INSPECTION TYPE: C, RT DRAG SPLICE FITTING ( UPPER AND LOWER FITTING ) FOUND BOTH FITTING 1EA FASTENER HOLE CRACK, REFER ATTACHED SKETCH FOR DETAIL. RT BS 980 - 1000, S38R AREA UPPER DRAG SPLICE FITTING REPAIRED AS PER RS R53-43-34686 AND LOWER DRAG SPLICE FITTING REPLACED AS PER RS R53-43-34686.

Part: FITTING — CRACKED (FUSELAGE) · airframe 97,510 hrs · 25,124 cycles

INSPECTION TYPE: C, RT BATH TUB FITTING FOUND 1EA BOLT HOLE CRACK AT VERT CHORD ATTACH SURFACE AT 9 O'CLOCK POSITION ( LOOKING FWD ) APPROX 3/16 INCH IN LENGTH. RT BS 1000 S38R AREA BATH STUB FITTING REPLACED AS PER SRM 51-10-01 PAGE 8.

Part: FITTING — CRACKED (FUSELAGE) · airframe 97,510 hrs · 25,124 cycles

INSPECTION TYPE: C, LT BATH TUB FITTING 1EA BOLT HOLE CRACK AT AFT SURFACE AT 5 O'CLOCK POSITION ( LOOKING FWD ) APPROX 0.040 INCH IN LENGTH, LT BS 1000 BATH STUB FITTING REPLACED AND ATT BOLTS REINSTALLED. MM 20-51-01 AND SRM 51-10-01 PAGE 8.

Part: FITTING — CORRODED (FUSELAGE) · airframe 97,510 hrs · 25,124 cycles

INSPECTION TYPE:C FX EXTERIOR RT S38R DRAG FITTING MOUNT BOLT HOLES FOUND CORROSION AT BS 980 - 990 AREA. RT S38R DRAG FTG 3 CORROSION BOLT HOLES AT BS 980 - 990 AREA CLEANED UP AND INSTALLED WITH 3 SLEEVE BOLTS AS PER HX RS NR R-53-43-34686 SPLICE FITTING REPAIR REQUIREMENT.

Part: FRAME — CRACKED (FUSELAGE) · airframe 97,510 hrs · 25,124 cycles

INSPECTION TYPE:C AFT CARGO BAY BS 1500 LT STR 39 FRAME WEB FOUND CRACKED. AFT CARGO COMPT BS 1500 LT FRAME S33L - S39L AREA REPAIRED AS PER SRM 5310-04 FIG 66.

Part: FITTING — CRACKED (FUSELAGE) · airframe 97,510 hrs · 25,124 cycles

INSPECTION TYPE: C, LT DRAG SPLICE FITTING ( LOWER FITTING ) FOUND 1EA HOLE CRACK, LT BS 980 - 1000 S38L AREA LWR DRAG SPLICE REPAIRED AS PER RS 53-43-34686.

Part: FITTING — CORRODED (FUSELAGE) · airframe 97,510 hrs · 25,124 cycles

INSPECTION TYPE:C FX EXTERIOR LT S38L DRAG FITTING MOUNT BOLT HOLES FOUND CORROSION AT BS 980 - 990 AREA. LT S38L DRAG FTG 3 CORROSION BOLT HOLES AT BS 980 - 990 AREA CLEANED UP AND INSTALLED WITH 3 SLEEVE BOLTS. ALSO 1 SKIN AREA ATTACHMENT BOLT ADJACENT FWD SLEEVE BOLT AREA WAS REPLACED BY ANOTHER SLEEVE BOLT TO PREVENT INTERFERENCE PROBLEM AS PER HX RS NR R 53-43-34686 SPLICE FITTING REPAIR REQUIREMENT.

Part: FITTING — CORRODED (FUSELAGE) · airframe 97,510 hrs · 25,124 cycles

INSPECTION TYPE:C FX - LT UPPER S38L DRAG SPLICE FITTING 3 BOLT HOLES AREA FOUND CORROSION AT UNDER WING DRAG FTG COMMON HOLE AREA. LT S38L UPP DRAG SPLICE FITTING 3 HOLE BORE CORROSION CLEANED UP AND INSTALLED WITH 3 SLEEVE BOLTS AS PER HXRS NR R53-43-34686 SPLICE FITTING REPAIR REQUIREMENT.

Part: FITTING — CRACKED (FUSELAGE) · airframe 97,510 hrs · 25,124 cycles

INSPECTION TYPE:C RT BATH TUB FITTING FOUND 1 BOLT HOLE CRACK (STRINGER ATTACH SURFACE) AT UPPER LEG O/B SURFACE RUNNING UP AND DOWN, BOTH CRACK APPROX 0.030 INCHES IN LENGTH. RT BATH FITTING REPLACED AS PER SRM 51-10-01 P8.

Part: SKIN — DAMAGED (FUSELAGE) · airframe 97,510 hrs · 25,124 cycles

INSPECTION TYPE:C - EXTERIOR SKIN FOUND A NON STANDARD REPAIR PATCH AT BS 140 - 150 S15L - 19L AREA. FUSELAGE SKIN AT BS 140 - 150 STRINGER 15L - 19L. AREA REPAIRED AS PER SRM 53-30-03 FIG 1.

Part: FRAME — CRACKED (FUSELAGE) · airframe 97,510 hrs · 25,124 cycles

INSPECTION TYPE:C FWD CARGO, BS 600 STR 37L STR 38L FUSELAGE FRAME FOUND CRACKED. FRAME REPAIRED PER HX RS R53-22-34683.

Part: FITTING — CRACKED (FUSELAGE) · airframe 97,510 hrs · 25,124 cycles

INSPECTION TYPE: C, RT BS 1000 BULKHEAD VERTICAL LOWER CHORD ( BATH TUB FITTING ATTACH AREA ) FOUND 1EA BOLT HOLE CRACK AT 5 O'CLOCK POSITION APPROX 0.060 INCH IN LENGTH. RT BS 1000 B/H VERTICAL LWR CHORD BATH STUB FITTING ATTACH AREA 5 O'CLOCK POSITION CRACKED BOTH HOLE REWORK AS PER RS 53-43-34686.

Part: FRAME — CRACKED (FUSELAGE) · airframe 97,510 hrs · 25,124 cycles

INSPECTION TYPE:C AFT CARGO, BS 1540 RT STR 39 - STR 40 FUSELAGE FRAME FOUND CRACKED. AFT CARGO COMPT BS 1540 RH S39R - S40R CRACKED FRAME REPAIRED AS PER SRM 53-10-04 FIG 69.

Part: FLOORBEAM — CRACKED (FUSELAGE) · airframe 97,510 hrs · 25,124 cycles

INSPECTION TYPE:C M/D - BS 220 RBL 10 FLOORBEAM SURFACE FOUND CRACKED AS MARKED. REPAIRED FLOORBEAM AT BS 220 BETWEEN RBL 7 TO RBL 13 PER SRM 53-10-07 FIG 10.

Part: PANEL — CRACKED (CABIN) · airframe 97,510 hrs · 25,124 cycles

INSPECTION TYPE:C RT BS 2230 FIVE CRACKS FOUND AT REVEAL PANEL BETWEEN S24R TO FLOOR LEVEL AS MARKED. REVEAL PANEL REPAIRED AT CABIN BS 2231 STR 24 TO 26R PER HX RS R53-62-34682.

Part: FRAME — CRACKED (FUSELAGE) · airframe 97,510 hrs · 25,124 cycles

INSPECTION TYPE:C APU COMPARTMENT INTERIOR FRAME FOUND CRACKED AT APPROX BS 2742-2752 LBL 10. THE COMPARTMENT HORIZONTAL FRAME AT BS 2742 TO 2752 LBL 10 WAS REPAIRED AS PER SRM 51-40-03 FIG 1. HFEC INSP CONFIRMED CRACK FREE PER NTM PT6, 51-00-00 FIG 4. THE COMPT CUTOUT SEAL RETAINER WAS REFITTED FOR ACCESS PER MM 20-51-01.

Part: FITTING — CRACKED (FUSELAGE) · airframe 97,510 hrs · 25,124 cycles

INSPECTION TYPE:C M/D - NR 3L DOOR FWD CUTOUT LWR CORNER REVEAL FITTING FOUND CRACKED. FITTING REPLACED PER SRM 51-10-01.

Part: SKIN — CRACKED (FUSELAGE) · airframe 97,510 hrs · 25,124 cycles

INSPECTION TYPE:C CRACK REVEALED ON LT FUSELAGE SKIN AT APPROX BS 970 AND S39 AT ONE FASTENER HOLE BY APPROX .1875 INCH LONG AS MARKED. CRACKED HOLE REPAIRED AS PER HX RS NR R53-43-34686.

Part: INTERCOSTAL — CRACKED (FUSELAGE) · airframe 97,510 hrs · 25,124 cycles

INSPECTION TYPE:C M/D, NLG W/W TOP PANEL INTERCOSTAL AT BS 290 LBL 21 1EA STAND OFF HOLE CRACKED. INTERCOSTAL REPLACED PER SRM 51-10-01.

Part: FITTING — CRACKED (FUSELAGE) · airframe 97,510 hrs · 25,124 cycles

INSPECTION TYPE:C M/D - NR 3R DOOR FWD CUTOUT LWR CORNER REVEAL FITTING FOUND CRACKED. FITTING REPLACED PER SRM 51-10-01.

Part: PANEL — DELAMINATED (HORIZ STAB) · airframe 97,510 hrs · 25,124 cycles

INSPECTION TYPE:C, EMP - LT STAB UPPER T/E PNL FOUND DELAMINATED AT ELEV STA 256. LT HORIZ STAB UPPER T/E PNL IN ELEV STA 256 AREA P/N 65B03713-3 REPLACED AS PER MM 20-51-00.

Part: FRAME — CRACKED (FUSELAGE) · airframe 97,510 hrs · 25,124 cycles

INSPECTION TYPE:C, APU COMPARTMENT INTERIOR FRAME FOUND CRACKED AT APPROX BS 2658 TO BS 2664 RBL 50 (JUST ABOVE RT DOOR FWD CORNER). STA BS 2658 TO BS 2664 RBL 50 FRAME REPAIRED AS PER SRM 51-40-03 FIG 1. HFEC CUTOUT AS PER NTM PART 6, 51-00-00 FIG 4 CRACK FREE BEYOND STOP HOLE.

Part: STRINGER — CRACKED (FUSELAGE) · airframe 97,510 hrs · 25,124 cycles

INSPECTION TYPE:C BS 980 RT S38R FOUND CRACKED AT FWD CARGO COMPT. REPAIRED STRINGER AS PER SRM 53-10-03.

Part: FRAME — CRACKED (FUSELAGE) · airframe 97,510 hrs · 25,124 cycles

INSPECTION TYPE: C, RT SIDE BS 800, ONE EA FASTENER HOLE CRACK REVEALED AT STRAP AREA, RUNNING FWD APPROX 3/16 INCH IN LENGTH AS MARKED PLEASE REFER DRAWING FOR DETAIL. REPAIRED FRAME STRAP AS PER RS NO. R53-22-34680.

Part: STRUCTURE — CRACKED (FUSELAGE) · airframe 97,510 hrs · 25,124 cycles

INSPECTION TYPE:C, LT SIDE BS 2231, TWO FASTENER HOLES CRACK REVEALED AT BETWEEN STR 24L AND STR 26L DRAWING ON REVEALED AREA. DETAIL PLEASE REFER ATT DRAWING. REVEALED REPAIRED PER HX RS R53-62-34682.

Part: ANGLE — CRACKED (FUSELAGE) · airframe 97,510 hrs · 25,124 cycles

INSPECTION TYPE:C, RIGHT MLG W/W OUTBOARD UPPER AT FS 1265 AREA OUTBOARD VERTICAL ANGLE LOWER END CRACKED AS MARKED. RIGHT VERTICAL ANGLE REPAIRED PER SRM 51-40-03.

Part: FRAME — CRACKED (FUSELAGE) · airframe 97,510 hrs · 25,124 cycles

INSPECTION TYPE:C RT SIDE BS 2231, ONE EA FASTENER HOLE CRACK REVEALED AT STR 25R ON CHORD AREA RUNNING FWD LOWER THRU THICKNESS DETAIL PLEASE REFER ATT DRAWING. THE CHORD AREA REPAIRED AS PER RS R53-62-34682.

Part: FRAME — CRACKED (FUSELAGE) · airframe 97,510 hrs · 25,124 cycles

INSPECTION TYPE: C, LT SIDE BS 800 BTN STR 16 - 17 FOUND TWO EACH FASTENER HOLES CRACKED AT STRAP RUNNING AFT FROM HOLE TO EDGE. REPAIRED FRAME STRAP AS PER RS R53-22-34680.

Part: BATTERY PACK — DISCHARGED (CABIN)

INSPECTION TYPE:N/A EMERGENCY BATTERY PACK IS DEAD. REMOVED AND REPLACED EMERGENCY BATTERY PACK PER MM 33-51-04.

Part: BULKHEAD — CRACKED (FUSELAGE) · airframe 96,994 hrs · 25,006 cycles

INSPECTION TYPE:SP STA 2360 AFT PRESSURE BULKHEAD WEB IS CRACKED AT APPROX RADIAL STIFFENER 23. REPAIRED WEB IAW 8110-3 APPROVED DH SK 681-617.

Part: DETECTOR — FAILED (FIRE WARNING)

INSPECTION TYPE:IN PRE DEPARTURE - FIRE WARNING TEST D/N RESET. REMOVED AND REPLACED FIRE WARNING CARD A-4. ALL OP CKS NORMAL. OK FOR SERVICE.

Part: INDICATOR — READS LOW (TE FLAP)

INSPECTION TYPE:N/A, DURING FLAP EXTENSION O/B FLAPS FAILED TO MOVE. SPLIT T.E. FLAP CHECKLIST ACCOMPLISHED. LT NEEDLE ON O/B FLAP IND IS OFF SCALE LOW. REMOVED AND REPLACED O/B FLAP POSITION INDICATOR AND TESTED PER MM 27-58-00 CHKS OK. P/N ON/OFF: 9801-09-03, S/N OFF: 1102, S/N ON: 6099.

Part: LIGHT — MALFUNCTIONED (INTERNAL STAIRS)

INSPECTION TYPE:N/A, EMERGENCY LIGHT OVER FLIGHT DECK STAIRS VERY DIM. REMOVED AND REPLACED EMERGENCY LIGHT ASSY PER MM 33-51-00. OPS CHECK GOOD.

Part: FLOOR SUPPORT — CRACKED (FUSELAGE) · airframe 94,119 hrs · 24,390 cycles

INSPECTION TYPE:C, SUPPORT STRUCTURE UNDER FLOORBOARD AT BS 420 - 440 RBL 98 CRACKED. NEW CHORD FABRICATED AND FITTED IAW SRM 51-30-02.

Part: FRAME — CRACKED (FUSELAGE) · airframe 94,119 hrs · 24,390 cycles

INSPECTION TYPE:C 44, FRAME CRACKED AT BS 1820 S18 AND S19 RT. FRAME REPAIR CARRIED OUT PER SRM 53-10-04.

Part: KEELBEAM — CORRODED (FUSELAGE) · airframe 94,119 hrs · 24,390 cycles

INSPECTION TYPE:C, CORROSION ON LWR WEB OF KEEL BEAM AT BS 1239. REPAIR PLATE AND FILLERS FABRICATED AND FITTED PER SRM 51-10-01 AND 51-30-02.

Part: STRINGER — CORRODED (FUSELAGE) · airframe 94,119 hrs · 24,390 cycles

INSPECTION TYPE:C 44, STRINGER CORRODED AT BS 1580 S38 LT. REPAIR ACCOMPLISHED IAW SRM 53-10-01.

Part: FRAME — CRACKED (LT MLG WW) · airframe 94,119 hrs · 24,390 cycles

INSPECTION TYPE:C, CRACK IN LWR CHORD LT WING GEAR WHEEL WELL BS 1319 ABOVE OVERWING LONGERON. REPAIR ANGLE AND FILLERS FABRICATED. REPAIR ACCOMPLISHED IAW Q/NOTE 24/2000.

Part: STRUCTURE — CRACKED (PAX DOOR) · airframe 94,119 hrs · 24,390 cycles

INSPECTION TYPE:C, INDICATIONS OF CRACK ON LWR FWD CORNER OF DOOR 1R. REPAIR ACCOMPLISHED PER SRM 52-11-01.

Part: FRAME — CRACKED (FUSELAGE) · airframe 94,119 hrs · 24,390 cycles

INSPECTION TYPE:C, FRAME CRACKED AT BS 1780 STR 35 LT. NEW SECTION OF FRAME SPLICED IN IAW SRM 51-10-01.

Part: STRINGER — CORRODED (FUSELAGE) · airframe 94,119 hrs · 24,390 cycles

INSPECTION TYPE:C 44, CORROSION ON STR S35 L AT BS 1820. REPAIR CARRIED OUT IAW SRM 51-10-01.

Part: WEB — CRACKED (FUSELAGE) · airframe 94,119 hrs · 24,309 cycles

INSPECTION TYPE:C 44, WEB CRACKED BETWEEN S28 AND S29 AT BS 2120 TO 2140 LT. WEB REPAIRED IAW SRM 51-40-02.

Part: SUPPORT BRACKET — DAMAGED (BLG DOOR AFT) · airframe 94,119 hrs · 24,390 cycles

INSPECTION TYPE:C, HOLES ELONGATED IN AFT INNER BLG DOOR STRUCTURE AT AFT HINGES LT AND RT. NEW SECTIONS OF DOOR SUPPORT STRUCTURE FABRICATED AND FITTED. NEW FITTINGS DRILLED AND INSTALLED. REF Q/NOTE 13/00.

Part: FRAME — CRACKED (FUSELAGE) · airframe 94,119 hrs · 24,390 cycles

INSPECTION TYPE:C, CRACKS FOUND ON INTERCOSTAL WEB, FRAME WEB AND SUPPORT WEB RT AT BS 1265 DURING INSPECTION OF CRITICAL HOLE REF EO 5310-12070 APP. CPAG E 3 ITEM 5. NEW SUPPORT WEB AND NEW INTERCOSTAL WEB FABRICATED AND FITTED IAW Q/ NOTE 14/00.

Part: FRAME — CORRODED (FUSELAGE) · airframe 94,119 hrs · 24,390 cycles

INSPECTION TYPE:C, CORROSION ON FRAME AT STA 400 RBL 46. REF Q/NOTE 15/00 NEW SECTION OF CHORD FABRICATED AND FITTED.

Part: STRINGER — CORRODED (FUSELAGE) · airframe 94,119 hrs · 24,390 cycles

INSPECTION TYPE:C, STRINGER 36L BADLY CORRODED AT BS 1769. CORRODED SECTION REMOVED AND REPAIR CARRIED OUT IAW SRM 53-10-01.

Part: STRUCTURE — CRACKED (PAX DOOR) · airframe 94,119 hrs · 24,309 cycles

INSPECTION TYPE:C 44 MED NR 2R, DOOR STRUCTURE CRACKED AT THE LOWER FWD CORNER. CARRY OUT REPAIRS PER SRM, OR RELEVENT SB. DOOR REMOVED FOR REPAIR AND SENT TO SHOP FOR REPAIR IAW 52-11-01. DOOR REFITTED AFTER REPAIR IAW 52-11-01. REF SHOP WORK ORDER NUMBER E0239260.

Part: FRAME — CORRODED (FUSELAGE) · airframe 94,119 hrs · 24,390 cycles

INSPECTION TYPE:C 44, VERTICAL CHORD AT BS 1319 L/WHEEL WELL WING ROOT CORRODED. REPAIR CARRIED OUT IAW SRM 51-40-04 AND Q/NOTE 24/00.

Part: FRAME — CORRODED (FUSELAGE) · airframe 94,119 hrs · 24,390 cycles

INSPECTION TYPE:C, CORROSION ON FRAME AT BS 400 RBL 46. DAMAGED SECTION OF CHORD REPAIRED PER Q/NOTE 15/00.

Part: FRAME — CRACKED (FUSELAGE) · airframe 94,119 hrs · 24,390 cycles

INSPECTION TYPE:C, FRAME CRACKED AT BS 1820 S35 LT. SECTION OF FRAME REPLACED IAW Q/NOTE 19/00.

Part: FRAME — CRACKED (FUSELAGE) · airframe 94,119 hrs · 24,390 cycles

INSPECTION TYPE:C 44, APU COMPARTMENT FRAME CRACKED AT BS 2690.85 WL 280 RT. FRAME REPAIRED IAW SRM 51-40-03.

Part: WEB — CRACKED (FUSELAGE) · airframe 94,119 hrs · 24,309 cycles

INSPECTION TYPE:C 44. CRACKED WEB AT BS 1901 LT ABOVE STR 37. NEW WEB FABRICATED AND REPLACED IAW SRM 51-20-01 AND SRM 51-30-02.

Part: FRAME — CORRODED (CENTER WING) · airframe 94,119 hrs · 24,390 cycles

INSPECTION TYPE:C, CORROSION ON RT WING LWR SKIN IN SPAR EXTENSION AT FS 770. CORROSION CLEANED UP, FILLER FABRICATED AND FITTED PER Q/NOTE 18/00.

Part: STRINGER — CORRODED (FUSELAGE) · airframe 94,119 hrs · 24,390 cycles

INSPECTION TYPE:C 44, STRINGER S 38 CORRODED AT BS 1540 LT AND 1580 LT. REPAIRED IAW SRM 51-10-01.

Part: FRAME — CORRODED (CENTER WING) · airframe 94,119 hrs · 24,390 cycles

INSPECTION TYPE:C, CORROSION ON LWR WING SKIN AT FS 790 UNDER LWR CHORD. CORROSION BLENDED OUT, FILLER FABRICATED AND FITTED REFERENCE Q/NOTE 18/00.

Part: FRAME — CORRODED (FUSELAGE) · airframe 94,119 hrs · 24,390 cycles

INSPECTION TYPE:C, CORROSION ON BOTTOM CHORD OF FRAME AT BS 400 STR 42R - 44R. REPAIR ACCOMPLISHED PER Q/NOTE 3/2000.

Part: SPLICE PLATE — CRACKED (FUSELAGE) · airframe 94,119 hrs · 24,309 cycles

INSPECTION TYPE:C 44, CIRCUMFERENTIAL SKIN SPLICE PLATE FOUND CRACKED AT BOTH AFT CORNERS OF NOSE WHEEL WELL BS 400 STR 44L AND 44R. CRACK SPLICE PLATES REMOVED IAW SRM 51-30-02. NEW SPLICE PLATES DRILLED UP AND FITTED IAW SRM 51-30-02.

Part: STRINGER — CRACKED (FUSELAGE) · airframe 94,119 hrs · 24,390 cycles

INSPECTION TYPE:C, STRINGER 47R CRACKED AT BS 400. REPAIR CARRIED OUT IAW 53-10-03.

Part: STRINGER — CRACKED (FUSELAGE) · airframe 94,119 hrs · 24,390 cycles

INSPECTION TYPE:C 44, STR 47R CRACKED AT BS 500 -520. REPAIR CARRIED OUT IAW SRM 53-10-03.

Part: SKIN — CRACKED (RT WING LE) · airframe 94,119 hrs · 24,390 cycles

INSPECTION TYPE:C, RIGHT WING CRACKS AND BULGES AT THE FOLLOWING LOCATIONS; WS 528, WS 550, WS 1084, WS 1158, WS 726, WS 1050, WS 905, WS 1110, WS 355, WS 323, WS 311, OLES 1411. CRACKS REPAIRED PER SRM. CORROSION CLEANED OUT OF LIMITS REPAIR ACCOMPLISHED PER Q/NOTE 16/00.

Part: PANEL — CORRODED (FUSELAGE) · airframe 94,119 hrs · 24,390 cycles

INSPECTION TYPE:C, MAIN DECK STRESS PANEL CORRODED AT BS 1170 - 1250. NEW STRESS PANEL FITTED.

Part: SKIN — CORRODED (CENTER WING) · airframe 94,119 hrs · 24,390 cycles

INSPECTION TYPE:C, CORROSION ON CENTER WING SKIN UPPER AT BS 1188 RBL 78. SKIN CORROSION CLEANED UP WITHIN LIMITS. NEW SECTION OF CHORD FABRICATED AND FITTED PER SRM 51-10-00.

Part: FRAME — CORRODED (CENTER WING) · airframe 94,119 hrs · 24,390 cycles

INSPECTION TYPE:C, UPPER SURFACE OF CENTER WING CORRODED AT BS 1120 RBL 78. NEW SECTION OF CHORD AND REPAIR ANGLES FITTED PER Q/NOTE 7/00.

Part: SKIN — CORRODED (CENTER WING) · airframe 94,119 hrs · 24,390 cycles

INSPECTION TYPE:C, CORROSION ON UPPER SURFACE OF CENTER WING SKIN AT BS 1050 LBL 88. CORROSION CLEANED UP OUT OF LIMITS ON SKIN AND FLOORBEAM CHORD. REPAIR ACCOMPLISHED PER Q/NOTE 5/00.

Part: SKIN — CORRODED (CENTER WING) · airframe 94,119 hrs · 24,390 cycles

INSPECTION TYPE:C, CORROSION ON UPPER SURFACE OF CENTER WING SKIN AT BS 1100 RBL 106. REF Q/NOTE 6/00 NEW SECTION OF CHORD FABRICATED AND FITTED.

Part: FRAME — CORRODED (CENTER WING) · airframe 94,119 hrs · 24,390 cycles

INSPECTION TYPE: C, CORROSION ON UPPER SURFACE OF CENTER WING AT BS 1100 RBL 106. NEW SECTION OF CHORD AND REPAIR ANGLES FABRICATED AND FITTED PER Q/NOTE 6/00.

Part: FORGING — CORRODED (FUSELAGE) · airframe 94,119 hrs · 24,390 cycles

INSPECTION TYPE:C, CORROSION ON WINDOW FORGING AT BS 2160 - 2180 RT. REPAIR ACCOMPLISHED PER Q/NOTE 12/00.

Part: FORGING — CORRODED (FUSELAGE) · airframe 94,119 hrs · 24,390 cycles

INSPECTION TYPE:C, CORROSION ON WINDOW FORGING BETWEEN STA 2060 AND 2080. REPAIR ACCOMPLISHED PER Q/NOTE 11/00.

Part: FORGING — CORRODED (FUSELAGE) · airframe 94,119 hrs · 24,390 cycles

INSPECTION TYPE:C, CORROSION AT FWD EDGE OF WINDOW FORGING BETWEEN STA 2020 AND STA 2040 RHS. CORROSION CLEANED UP. FOUND OUT OF LIMITS. REPAIR ACCOMPLISHED PER Q/NOTE 10/00.

Part: LIGHT — INOPERATIVE (CABIN)

LEFT FWD ENTRY DOOR FWD EMERGENCY LT INOP. REMOVED AND REPLACED BATTERY PACK, OPS CK GOOD.

Part: TORQUE TUBE — BROKEN (LE FLAP)

NR 4 L/E PANEL RIGHT DROOPED AND SPLIT FROM INBD TO OUTBOARD SEGMENT. REMOVED AND REPLACED NR 4 L/E TORQUE TUBE IAW MM 27-81-05. FUNCTIONAL TEST OF L/E DEVIC ES PERFORMED. OPS CHECK NORMAL.

Part: MOTOR — BAD (NR 2 LE FLAP)

LT NR 2 L/E FLAP WOULD NOT RETRACT VIA, THE ALTERNATE METHOD. REPLACED LT NR 2 L/E FLAP ALT DRIVE ELECTRIC MOTOR PER MM 27-81-03. OPS CKS OK.

Part: BATTERY PACK — DISCHARGED (ENTRY DOOR)

INSPECTION TYPE-W/E, CREW ENTRY DOOR AFT EMERGENCY LIGHT INOP. ALSO, THE EMERGENCY LIGHT AFT OF THE UPPER DECK STAIR IS INOP. REPLACED LIGHT ASSY WITH BATTERY PACK. SYSTEM OPS CK GOOD REF 3317 P204.

Part: LIGHT — INOPERATIVE (CABIN)

INSPECTION TYPE-N/A, EMERGENCY EXIT LIGHT INOP. REPLACED LIGHT MODULE, OPS CHECK OK.

Part: SKIN — CRACKED (BS 860)

INSPECTION TYPE-N/A, APPROX 4 INCH CRACK ON BELLY SKIN LAP SEAM, LEFT SIDE STA 860 UNDER FILLET PANEL. ABOVE ITEM TO BE ACCOMPLISHED WITH EO B747-5330-10196-A.

Part: SKIN — CORRODED (BS 480)

INSPECTION TYPE-N/A, FUSE SKIN CORRODED THRU AT STA 480 BETWEEN S47L AND S47R. REPAIRED IAW EO B747-5330-10196.

Part: CONNECTOR PIN — BENT (NR 1 ENGINE)

INSPECTION TYPE-N/A, CREW REPORTED AT 500 FT AGL ON FINAL APPROACH, NR 1 ENGINE FLAMED OUT. NORMAL LANDING ACCOMPLISHED. INFLIGHT START NOT INITIATED DUE TO DISTANCE FROM RUNWAY. FOUND PIN 6 ON NR 1 ENG FIREWALL CONN D0014P BENT AND TOUCHING PIN 17 CAUSING FUEL CONTROL ACTUATOR TO MALFUNCTION. REMOVED AND REPLACED CONDITION ACTUATOR AND STRAIGHTENED PIN. ACT FUNCTION AND ENGINE RUN WERE SATISFACTORY.

Part: CONTROLLER — MALFUNCTIONED (CABIN)

INSPECTION TYPE-N/A, DURING CABIN CLIMBOUT AT 18,000 CABIN PRESS BEGAN CLIMBING ABOVE 9,000 FT THE CABIN ALT WAS SET AT 6,000. THE AUTO FAIL LIGHT ILLUM AND PRESS DIFF WAS 8.4 APPROX 2 MIN LATER CABIN CLIMBED ABOVE 10,000 AND PRESS RELIEF VALVES WERE CLOSED AND THE UPPER PRESS RELIEF VALVE LIGHT REMAINED ON. DESCENDED BELOW 10,000 FT W/OUTFLOW VALVES OP. REPLACED AUTO PRESSURE CONTROLLER BITE CHECK OK.

Part: OXY REGULATOR — MALFUNCTIONED (COCKPIT)

CANNOT STOP FLOW OF O2 ON S/O ON REG AT 100 PERCENT EMERG IAW AOM CHECK PROCEDURES. REMOVED AND REPLACED O2 REGULATOR P/N ON/OFF 28000-1 S/N ON 7879 OFF 8278.

Part: EXIT SIGN — BROKEN (CABIN)

INSPECTION TYPE-N/A, UPPER DECK EMERGENCY EXIT SIGN HAS BROKEN LATCH AND DOES STAY CLOSED, UPPER DECK EXIT PLACARDED INOP PER MEL 33-15 ASSIGNED M-139931.

Part: LIGHT — INOPERATIVE (CREW EXIT)

EXIT LIGHT OVER CREW ESCAPE DOOR IS LOOSE, NEEDS TO BE FIXED AND ENSURE OPERATION. EXIT LIGHT ASSY AT UPPER DECK CREW DOOR REPLACED ON NR ITEM NR 20 LIGHT INOPERATIVE. FOUND GROUNDING STUD GD7664-DC NOT A GOOD GROUND REMOVED STUD, CLEANED STUD AND STRUCTURE SURFACE AND REINSTALLED STUD. EXIT LIGHT OPS CK OK.

Part: LIGHT — INOPERATIVE (CARGO COMPT)

EMERG EXIT LIGHT AT STA 580 MAIN CARGO COMPARTMENT INOP. RELAMPED, OPS CHK NORMAL.

Part: BULKHEAD WEB — DAMAGED (BS 2360)

INSPECTION TYPE-C, BS 2360 REAR PRESS BULKHEAD 3 FASTENERS IN VERY BAD CONDITION AT 3 O'CLOCK POSITION APPROX RBL 48 SEGMENT LAP JOINT. REPAIRED AFT PRESS BULKHEAD WEB AT SEGMENT LAP JOINT IAW SRM 51-30-02, DFX 97-116 REV 2, FAA FORM 8110-3, REF UPS-AMS-0153TE, EO B747-5310-9248-A.

Part: BULKHEAD — CRACKED (BS 2360)

INSPECTION TYPE-C, AFT PRESSURE BULKHEAD FOUND CRACK IN BULKHEAD SECTION JUST BELOW RT RADIAL 130 ABOVE STR 24, 4 FROM SKIN JOINT. REPAIRED AFT PRESS BULKHEAD RT RADIAL 130 ABOVE STR 24, 4 FROM SKIN JOINT ACC UPS EO 747-53-0828 AND KLM DFX 97-111. PERFORMED AN OPEN HOLE EDDY CURRENT INSPECTION ON NRC 722908.

Part: BULKHEAD WEB — CRACKED (NR 3 PYLON)

INSPECTION TYPE-C, PYLON 3 FOUND CHAFING DAMAGE AND CRACK RUNNING TO STIFFENER ON REAR ENGINE BULKHEAD ON POSITION OF HYDRAULIC LINE AND WEB CRACKED NAC STA 221.90. REPAIRED ENGINE MOUNT BULKHEAD WEB ACC KLM DFX 97-089 ISSUE 3, EFN 747-54-0157.

Part: CHORD — CORRODED (BS 860)

INSPECTION TYPE-C, AT BS 860 BETWEEN RBL 70 TO 98 FOUND CORROSION ON UPPER CHORD. REPAIRED UPPER CHORD AT BS 860 BETWEEN RBL 67 AND 122 ACC EFN 747-53-0827 (KLM DFX 97-095).

Part: CHORD — CORRODED (BS 860)

INSPECTION TYPE-C, FOUND CORROSION ON UPPER CHORD ON BS 860 BETWEEN LBL 70/105. REMOVED CORROSION ON UPPER CHORD AT BS 860 BETWEEN LBL 70/105. CORROSION NOT IN LIMITS ACC SRM 53-10-01 FIG 1. REPLACED UPPER CHORD AT FABRIC SPLICE AT LBL 65 TO LBL 122 ACC SRM 51-30-02.

Part: CHORD — CRACKED (NR 3 PYLON)

INSPECTION TYPE-C, PYLON 3 FOUND DURING SB 747-54-2034 UNDER OLD DOUBLER CRACK 3.5 LONG RUNNING TO MID SPAR CHORD NAC STA 180 AND 3X HOLES DRILLED IN MID SPAR CHORD STA 184 EDGE MARGIN TOO SMALL. TRIMMED SKIN AND DOUBLER. INSTALLED FILLER, REWORKED MID SPAR CHORD ACC KLM DFX 97-087 ISSUE 3, EFN 747-54-0156.

Part: SKIN — CRACKED (NR 2 PYLON)

INSPECTION TYPE-C, PYLON NR 2 FOUND DURING SB 747-54-2034 CRACK UNDER OLD DOUBLER 3.5 LONG RUNNING TO MID SPAR CHORD NAC STA 180 RT SIDE. TRIMMED SKIN AND DOUBLER, INSTALLED FILLER. INSTALLED THE LARGE DOUBLER ACC KLM DFX 97-087 ISSUE 3, EFN 747-54-0156.

Part: LIGHT — INOPERATIVE (CABIN)

INSPECTION TYPE-N/A, UPPER DECK EMERG EXIT SIGN INOP. REMOVED AND REPLACED UPPER DECK LIGHTED EXIT SIGN, OPS CHECKS GOOD IAW B747 MM 33-51-02, P/N ON/OFF 080.

Part: LIGHT — INOPERATIVE (CREW DOOR)

INSPECTION TYPE-N/A, LIGHT INOP IN EMERGENCY EXIT SIGN ABOVE CREW SERVICE DOOR EVAC SLIDE. RELAMPED.

Part: CONNECTOR — DIRTY (CABIN)

INSPECTION TYPE:C, EMERGENCY EXIT LIGHT SIGN ABOVE ESCAPE SLIDE IN UPPER DECK IS INOP. CLEANED CONNECTORS, OPS CHECK GOOD.

Part: CONNECTOR — DIRTY (NR 4 ENGINE)

INSPECTION TYPE-N/A, START VALVE OPEN LIGHT ILLUMINATED IN FLIGHT. SHUT ENGINE DOWN AS PER AOM. CLEANED AND RESECURED CANNON PLUG TO START VALVE. PRESSURE SWITCH, OPS CHECK NORMAL PER MM 80-11-04.

Part: START VALVE — INOPERATIVE (COCKPIT)

START VALVE OPEN LIGHT ILLUMINATED ON NR 4 ENG DURING FLIGHT. ENG WAS SHUT DOWN IAW AOM CHECKLIST. 60,000 LBS OF FUEL WAS DUMPED. REMOVED AND REPLACED NR 4 START VALVE AND PRESSURE SWITCH PER B747 M/M 80-11-04. OPS CKD NORMAL, VALVE PN ON 726574-7 OFF 726574-7 SN ON EL22905 OFF AA22006.

Part: POWER SUPPLY — INOPERATIVE (UPPER DECK)

INSPECTION TYPE-N/A, EXIT SIGN UPPER DECK INOP. REMOVED AND REPLACED POWER SUPPLY MODULE BATT, OPS CHECKS OK.

Part: LIGHT — INOPERATIVE (CABIN)

INSPECTION TYPE N/A, EMERGENCY EXIT LIGHT OVER UPPER DECK ESCAPE DOOR INOP. TRANSFERRED TO M117610 PER MEL 33-13 POWER CONTACTS TO LIGHTS ADJUSTED EXIT LIGHT. DEFERRAL CLEARED PLACARD REMOVED.

Part: TERMINAL — LOOSE (CREW DOOR)

INSPECTION TYPE N/A, EMERGENCY EXIT DOOR SIGN INOP. TIGHTENED LOOSE TERMINAL, RESECURED EXIT SIGN OVER DOOR REF M114897.

Part: LIGHT — INOPERATIVE (CREW SERV DOOR)

INSPECTION TYPE: DLY. EMERGENCY EXIT LIGHT ON CREW SERVICE DOOR INOP. EXIT DOOR LIGHT OPERATIONAL. OPS CHK GOOD.

Part: LIGHT — INOPERATIVE (CABIN)

INSPECTION TYPE N/A, PRIMARY UPPER DECK DOOR EMERGENCY LIGHT INOP ON PREFLIGHT. DEFERRED PER MEL 33-15 M112004 ASSIGNED.

Part: SWITCH — DIRTY (CARGO DOOR)

INSPECTION TYPE: C. AFT CARGO DOOR LIGHT ILLUMINATED WHEN REACHING 2.4 PSI DIFF. REQUIRED AIR TURN BACK. CLEANED AFT CARGO DOOR LIGHT SWITCHES, CYCLED DOOR OPEN AND CLOSED, PRESSURIZED AIRCRAFT TO 7.0 PSID. OPS CHECKED NORMAL.

Part: SKIN — DAMAGED (LT TE FLAP)

INSPECTION, FWD SIDE OF LT WING I/B TRAILING EDGE FLAP HAS TWO, .375 INCH DIA HOLES, 5 INCHES APART, CORE NOT DAMAGED. PER SRM 51-40-06 PG 30A APPLIED SPEED TAPE AND DEF UNDER D-NOTE: THIS DEF GOOD FOR 20 FLT HOURS PER SRM 51-40-06 D109465 ASSIGNED.

Part: SKIN — CRACKED (LT WING TE)

INSPECTION, I/B TRAILING EDGE WING PANEL HAS A TWO FT CRACK ON BOTTOM OF PANEL, CAUSED BY DAMAGED O/B MLG FOLLOW UP DOOR. L/E WRITTEN UP ON ITEM 1 LOG PAGE 751782. INSTALLED SPEED TAPE, AWAITING EO FOR SAID INTRIM REPAIR. DEF PER NR 747-5700-8279A D109480 ASSIGNED.

Part: FIRE DET — INOPERATIVE (APU COMPT)

CREW REPORTED, APU FIRE INDICATION DURING CRUISE. A-LOOP OF FIRE DETECT SYS SELECTED 'B', NO FURTHER INDICATIONS. APU WAS OFF DURING THE ENTIRE EVENT. DEF ITEM PER 26-7, MMOC J SHULTZ ASSIGNED CTRL. NR M-108335, PLACARD A-LOOP SYS INOP AND SELECTED 'B' LOOP.

Part: SUPPORT — CORRODED (WS 1280)

WHILE IN AMS FOR C-CHECK, MAINTENANCE REPORTED LT WING LOWER SURFACE FOUND CORROSION AT O/B SUPPORT JACK POINT WS 1280. REMOVED AND REPAIRED CORROSION DAMAGE IAW SRM 51-10-01, 57-30-01 AND UPS EFN 747-57-0322.

Part: SKIN — CORROSION (WS 440)

WHILE IN AMS FOR C-CHECK, MAINTENANCE REPORTED RT WING UPPER SIDE STRIP OF RABBET AREA IS BULGED AT WS 440. FOUND CORROSION. REPAIRED IAW DFX 96-064, ISSUE NR 2 APP. PER UPS E.O. EFN 747-57-0315.

Part: SKIN — CORROSION (WS 865)

WHILE IN AMS FOR C-CHECK, MAINTENANCE REPORTED RT WING SKIN ABOVE UPPER CHORD IS BULDGED AT WS 865. FOUND CORROSION BETWEEN UPPER CHORD AND UPPER SKIN. REPAIR APPROVED PER UPS E.O. EFN 747-57-0312.

Part: SKIN — CORROSION (WS 975)

WHILE IN AMS FOR C-CHECK, MAINTENANCE REPORTED RT WING UPPER SIDE STRIP OF RABBET AREA IS BULGED AT WS 975. FOUND CORROSION. REPAIRED IAW DFX 96-062, ISSUE NR 2 APP. PER UPS E.O. EFN 747-57-0313.

Part: SKIN — CORROSION (WS 1140)

WHILE IN AMS FOR C-CHECK, MAINTENANCE REPORTED RT WING UPPER SIDE STRIP OF RABBET AREA IS BULGED AT WS 1140. SUBMITTER SUSPECTS CORROSION. REPAIRED IAW DFX 96-063, ISSUE NR 2 APP. PER UPS E.O. EFN 747-57-0314.

Part: SKIN — CORRODED (RT WING LE)

WHILE IN FOR C-CHECK AT AMS, MAINTENANCE REPORTED RT WING UPPER SIDE FOUND CORROSION ROUND FASTENER HEADS AT WS 550. REWORKED CORROSION PER SRM 51-10-01. REWORKED AREA OUT OF LIMITS PER SRM 57-30-01. REWORKED WING NOSE PER SRM 57-30-04 FIG 2.

Part: SKIN — CORRODED (WS 460)

WHILE IN FOR C-CHECK AT AMS, MAINTENANCE REPORTED RT WING UPPER SIDE FOUND CORROSION AROUND FASTENER HEADS AT WS 460. REWORKED CORROSION PER SRM 51-10-01. REWORKED AREA OUT OF LIMITS PER SRM 57-30-01 FIG 4. REWORKED WING NOSE PER SRM 57-30-04 FIG 2.

Part: SKIN — CORRODED (WS 500)

WHILE IN FOR C-CHECK AT AMS, MAINTENANCE REPORTED RT WING UPPER SIDE FOUND CORROSION ROUND FASTENER HEADS AT WS 500. REWORKED CORROSION PER SRM 51-10-01. REWORKED AREA OUT OF LIMITS PER SRM 57-30-01 FIG 4. REWORKED WING NOSE PER SRM 57-30-04 FIG 2.

Part: WEB — CRACKED (BS 1225)

WHILE IN AMS FOR C-CHECK, MAINTENANCE REPORTED WING-TO-BODY FAIRING SUPPORT STRUCTURE, CRACKED FRAME REINFORCEMENT WEB LOWER SIDE, RBL 104, BS 1225. REMOVED DAMAGED SECTION OF WEB AND REPAIRED WEB IAW SRM 51-40-02.

Part: SKIN — CRACKED (BS 575)

WHILE IN AMS FOR C-CHECK, MAINTENANCE REPORTED CRACK IN EQUIP COOLING OUTLET, BS 575 LT, STR 44 AT AFT SIDE. CRACK LENGTH APPROXIMATELY 1.25 INCHES. REPAIRED SKIN IAW KLM-DFX-96-061, APPROVED PER UPS EFN-747-53-0753.

Part: FRAME — DELAMINATED (BS 987.35)

WHILE IN AMS FOR C-CHECK, MAINTENANCE REPORTED WING-TO-BODY FAIRING SUPPORT STRUCTURE, FOUND LOWER CHORD FRAME DELAMINATED DUE TO CORROSION AT BS 987.35, RBL 57 AND RBL 68. REPLACED FRAME LOWER CHORD IAW SRM 51-30-02.

Part: FRAME — DELAMINATED (BS 1008/992)

WHILE IN AMS FOR C-CHECK, MAINTENANCE REPORTED WING-TO-BODY FAIRING SUPPORT STRUCTURE, FOUND FRAME/INTERCOSTAL LOWER CHORD DELAMINATED/CORRODED AT LBL 57, BS 1008, INBOARD, AND BS 992, OUTBOARD. REMOVED DAMAGED SECTION FROM LOWER CHORD AND REPAIRED LOWER IAW SRM 51-40-04.

Part: STRINGER — CRACKED (BS 980)

WHILE IN AMS FOR C-CHECK, MAINTENANCE REPORTED CRACKED STRINGER AT BS 980 5-38 LT. REPAIRED STRINGER IAW SRM 53-10-03.

Part: HINGE PLATES — CRACKED (BS 1010/1033)

WHILE IN AMS FOR C-CHECK, MAINTENANCE REPORTED WING TO BODY FAIRING SUPP STRU/ACFT BAY DOORS, FOUND HINGE POINT ATTACH PLATES CRACKED DUE TO DELAMINATION OF SHIMS BETWEEN ATTACH PLATES AND KEEL BEAM STRUCTURE LBL 8 BS 1010 AND BS 1033. REPLACED HINGE POINT ATTACH PLATES AND SHIMS PER SRM 51-30-02.

Part: FRAME — CORROSION (BS 987.35)

WHILE IN AMS FOR C-CHECK, MAINTENANCE REPORTED WING-TO-BODY FAIRING SUPPORT STRUCTURE, FOUND DELAMINATION AND CORROSION ON FRAME LOWER CHORD AT BS 987.35, LBL 24 AND LBL 40. LATCH FILLERS DELAMINATED AT LBL 14 AND LBL 52. REPLACED FRAME LOWER CHORD IAW SRM 51-30-02. REPLACED LATCH FILLERS IAW SRM 51-30-02.

Part: WEB — CORROSION (BS 920)

WHILE IN AMS FOR C-CHECK, MAINTENANCE REPORTED WING-TO-BODY FAIRING SUPPORT STRUCTURE, CORROSION ON FRAME WEB AND LOWER CHORD AT BS 920, LBL 0/17 AND LBL 47. REMOVED CORROSION PER SRM 51-10-01 ON WEB. REPAIRED LOWER CHORD PER SRM 53-50-04, FIG 2.

Part: ANGLE — CRACKED (BS 2200)

WHILE IN AMS FOR C-CHECK, MAINTENANCE REPORTED AREA AFT OF BULK CARGO COMP, CRACKS WERE FOUND IN INNER ANGLE OF FRAME UPPER FLANGE, DUE TO CORROSION AT BS 2200, NEAR S-36 RT. REPLACED INNER ANGLE OF FRAME UPPER FLANGE AS PER SRM 51-30-02.

Part: LATCH SUPPORT — CORRODED (AFT DOOR SILL)

WHILE IN AMS FOR C-CHECK, MAINTENANCE REPORTED FOUND CRACK IN AFT CARGO DOORWAY LOWER. SILL LATCH NR 10 INSPECTION PERFORMED ACC NDT MANUAL D6-7170, PART 6 CHAPTER 51-00-00. REPLACED TRUSS AND LATCH SUPPORT FITTING AT POS NR 10 PER EO B747-5340-0191 APP D. ALSO, REPLACED SUPPORT BRACKET FOR GUIDE WHEEL ACC SRM 51-30-02.

Part: FRAME — CRACKED (BS 2220)

WHILE IN AMS FOR C-CHECK, MAINTENANCE REPORTED FINDING CRACK IN UPPER FLANGE OF FRAME AT BS 2220 NEAR S-40 LT. STOP-DRILLED CRACK AND REPAIRED FRAME UPPER FLANGE IAW TO SRM 51-40-03.

Part: COMPRESSOR — STALLED (NR 2)

CREW REPORTED EN ROUTE TO HKG, NR 2 ENG SHUTDOWN DUE TO SEVERE COMPRESSOR STALL CLIMBING THROUGH 11,000 FEET. EGT RECORDED AT 1096 DEGREES, ENG SHUTDOWN IAW ENG SEVERE DAMAGE CHECK LIST. REMOVED AND REPLACED NR 2 ENG PER MM TC5000. OPS AND LEAK CHECK GOOD. OFF (P/N JT9D-7AH) (S/N 662911), ON (P/N JT9D-7AH) (S/N 663073).

Part: ACTUATOR — INOPERATIVE (LT MLG)

CREW REPORTED, LEFT WING DOOR OPEN LIGHT REMAINED ILLUMINATED AFTER GEAR RETRACTION. LIGHT REMAINED ILLUMINATED AFTER ALTERNATE EXTENSION IAW ABNORMAL CHECKLIST, ATB TO SDF. REPLACED LT WING GEAR ACTUATOR IAW M/M 32-32-01, OPS CHECK GOOD.

Part: EEL — INOPERATIVE (FLIGHT DECK)

MAINTENANCE REPORTED, UPPER DECK EMERGENCY LIGHTS INOP. ALL UPPER DECK EMERGENCY LIGHTS TEST GOOD, NO FAULTS NOTED.

Part: WEB — CORROSION (FS 1840-1860)

WHILE IN 'C' CHECK IN AMSTERDAM, MAINTENANCE FOUND CORROSION ON WEB FROM BEAM AT BS 1840-1860, STR 33L IN THE AFT CARGO COMP. INSTALLED REPAIR IAW SRM 51-40-02.

Part: FRAME — CRACKED (FS 2040)

WHILE IN 'C' CHECK IN AMSTERDAM, MAINTENANCE FOUND BULK CARGO COMP FRAME AT STA 2040 STR 29L CRACKED. INSTALLED REPAIR IAW SRM 53-10-04, FIG 39.