N797FD

Part: DECK PLATE — CORRODED (MAIN CABIN) · airframe 63,129 hrs · 25,428 cycles

MAIN CABIN AFT PRESSURE DECK WEB IS CORRODED AT APPROX STA 1684 AT APPROX LBL 8 REPAIRED AFT DECK PRESSURE PLATE CORROSION UPPER SURFACE @ STA 1684, LBL 8 IAW FEDEX EA F-5310-T0370-P1, RELEASED SEP 08, 2022, TITLED "FUSELAGE - MAINFRAME - AFT DECK PLATE STA 1681 - 1720-LBL20-RBL45-CORROSION.

Part: SEAT TRACK — CRACKED (MAIN CABIN) · airframe 63,129 hrs · 25,428 cycles

MAIN CABIN SEAT TRACK SUPPORT INBD FLANGE IS CRACKED AT FLOOR PANEL FASTENER HOLE AT APPROX. STA 682 , RBL 44 REMOVED AND REPLACED SEAT TRACK SUPPORT AT MAIN CABIN AT APPROX. STA 640 TO STA 740 RBL 44 IAW VTMAE DRAWING 3458 , B757-200 SRM 51-40-02 , BAC DWG 657N3311 REV B

Part: DECK PLATE — CORRODED (MAIN CABIN) · airframe 63,129 hrs · 25,428 cycles

MAIN CABIN AFT PRESSURE DECK WEB IS CORRODED AT APPROX STA 1689 AT APPROX LBL 8 REPAIRED AFT DECK PRESSURE PLATE CORROSION UPPER SURFACE @ STA 1689, LBL 8 IAW FEDEX EA F-5310-T0370248-P1, RELEASED SEP 08, 2022, TITLED " FUSELAGE - MAINFRAME - AFT DECK PLATE, STA 1681 - 1720-LBL20-RBL45-CORROSION

Part: DECK PLATE — CORRODED (MAIN CABIN) · airframe 63,129 hrs · 25,428 cycles

MAIN CABIN AFT PRESSURE DECK WEB IS CORRODED AT APPROX STA 1695 AT APPROX LBL 8 REPAIRED AFT DECK PRESSURE PLATE CORROSION, UPPER SURFACE @ STA 1695, LBL 8 IAW FEDEX EA F-5310-T0370248, RELEASED SEP 08, 2022, TITLED" FUSELAGE - MAINFRAME - AFT DECK PLATE, STA 1681 - 1720-LBL20-RBL45-CORROSION

Part: WEB — CORRODED (ZONE 200) · airframe 63,129 hrs · 25,428 cycles

MAIN CABIN AFT PRESSURE DECK WEB IS CORRODED AT APPROX STA1684 AT APPROX LBL16. REPAIRED AFT PRESSURE DECK WEB CORROSION ON UPPER SURFACE APPROX STA 1684, LBL16 REF EA F-5310-T0370248-P1 REV A FUSELAGE-MAINFRAME-AFT DECK PLATE-STA1681- 1720-LBL20-RBL45-CORROSION

Part: WEB — CORRODED (BS 600) · airframe 63,129 hrs · 25,428 cycles

MAIN CABIN FLOOR STRUCTURE HAS CORROSION AROUND FASTENER HOLE STATION 600, LBL 53 REPAIRED MAIN CABIN FLOOR STRUCTURE AT STA 580 AND STA 600, LBL 53 IAW FEDEX E.A. F- 5310-T0370288-P1, TITLE: FUSELAGE - MAINFRAME - SHEAR WEB, STA 520, 580, 600, LBL 53, CORROSION.

Part: WEB — CORRODED (BS 520) · airframe 63,129 hrs · 25,428 cycles

MAIN CABIN FLOOR STRUCTURE HAS CORROSION AT STA 520, LBL 53 REPAIRED MAIN CABIN FLOOR STRUCTURE AT STA 520, LBL 53 IAW FEDEX E.A. F-5310-T0370288- P1, TITLE: FUSELAGE - MAINFRAME - SHEAR WEB, STA 520, 580, 600, LBL 53, CORROSION.

Part: DECK PLATE — CORRODED (MAIN CABIN) · airframe 63,129 hrs · 25,428 cycles

MAIN CABIN FLOOR STRUCTURE AFT DECK PRESSURE PLATE IS CORRODED ON THE UPPER SURFACE AT APPROX STA 1690 AT APPROX RBL15 REPAIRED AFT DECK PRESSURE PLATE CORROSION ON UPPER SURFACE APPROX STA1690, RBL15. RE FEDEX EA F-5310-T0370248-P1 FUSELAGE-MAINFRAME-AFT DECK PLATE-STA1681- 1720 LBL20-RBL45-CORROSION

Part: DECK PLATE — CORRODED (CABIN) · airframe 63,129 hrs · 25,428 cycles

MAIN CABIN FLOOR STRUCTURE AFT DECK PRESSURE PLATE IS COPRRODED ON THE UPPER SURFACE AT APPROX STA 1690 AT APPROX RBL 26 REPAIRED AFT DECK PRESSURE PLATE CORROSION ON UPPER SURFACE APPROX STA1690, RBL26 REF FEDEX EA F-5310-T0370248-P1. FUSELAGE-MAINFRAME-AFT DECK PLATE-STA1681- 1720 LBL20-RBL45-CORROSION

Part: DECK PLATE — CORRODED (CABIN) · airframe 63,129 hrs · 25,428 cycles

MAIN CABIN FLOOR STRUCTURE AFT DECK PRESSURE PLATE IS CORRODED ON THE UPPER SURFACE AT APPROX STA 1683 AT APPROX RBL 36 REPAIRED AFT DECK PRESSURE PLATE CORROSION ON UPPER SURFACE APPROX STA 1683, RBL36. REF FEDEX EA F-5310-T0370248-P1 FUSELAGE-MAINFRAME-AFT DECK PLATE-STA1681- 1720 LBL20-RBL45-CORROSION

Part: DECK PLATE — CORRODED (CABIN) · airframe 63,129 hrs · 25,428 cycles

MAIN CABIN FLOOR STRUCTURE AFT DECK PRESSURE PLATE IS CORRODED ON THE UPPER SURFACE AT APPROX STA 1714 SPANNING BETWEEN APPROX LBL3 TO RBL 18 REPAIRED AFT DECK PRESSURE PLATE CORROSION ON UPPER SURFACE APPROX 1714 LBL3- RBL18. REF FEDEX EA F-5310-T0370248-P1 FUSELAGE-MAINFRAME-AFT DECK PLATE-STA1681- 1720-LBL20-RBL45-CORROSION

Part: DECK PLATE — CORRODED (CABIN) · airframe 63,129 hrs · 25,428 cycles

MAIN CABIN FLOOR STRUCTURE AFT DECK PRESSURE PLATE IS CORRODED ON THE UPPER SURFACE AT APPROX STA 1699 AT APPROX RBL 15 REPAIRED AFT DECK PRESSURE PLATE CORROSION ON UPPER SURFACE APPROX STA 1699, RBL15. REF FEDEX EA F-5310-T0370248-P1. FUSELAGE-MAINFRAME-AFT DECK PLATE-STA1681- 1720-LBL20-RBL45-CORROSION

Part: DECK PLATE — CORRODED (CABIN) · airframe 63,129 hrs · 25,428 cycles

MAIN CABIN FLOOR STRUCTURE AFT DECK PRESSURE PLATE IS CORRODED ON THE UPPER SURFACE AT APPROX STA 1714 SPANNING VETWEEN APPROX RBL31 TO RBL 38 REPAIRED AFT DECK PRESSURE PLATE CORROSION ON UPER SURFACE APPROX STA1714 RBL31-RBL38 REF FEDEX EA F-5310-T0370248-P1 FUSELAGE-MAINFRAME-AFT DECK PLATE- STA1681-1720-LBL20-RBL45-CORROSION

Part: DECK PLATE — CORRODED (CABIN) · airframe 63,129 hrs · 25,428 cycles

MAIN CABIN FLOOR STRUCTURE AFT DECK PRESSURE PLATE IS CORRODED ON THE UPPER SURFACE SPANNING BETWEEN APPROX STA 1686 AND STA 1699 AT APPROX RBL 9 REPAIRED AFT DECK PRESSURE PLATE CORROSION ON UPPER SURFACE APPROX STA 1686- 1699 REF FEDEX EA F-5310-T0370248-P1 FUESLAGE-MAINFRAME-AFT DECK PLATE-STA1681- 1720 LBL20-RBL45-CORROSION

Part: DECK PLATE — CORRODED (CABIN) · airframe 63,129 hrs · 25,428 cycles

MAIN CABIN FLOOR STRUCTURE AFT DECK PRESSURE PLATE IS CORRODED ON THE UPPER SURFACE AT APPROX STA 1690 AT APPROX RBL10 REPAIRED AFT DECK PRESSURE PLATE CORROSION ON UPPER SURFACE APPROX. STA1690, RBL 10. REF FEDEX EA F-5310-T0370248-P1 FUSELAGE-MAINFRAME-AFT DECK PLATE-STA 1681- 1720-LBL20-RBL45-CORROSION.

Part: DECK PLATE — CORRODED (CABIN) · airframe 63,129 hrs · 25,428 cycles

MAIN CABIN FLOOR STRUCTURE AFT DECK PRESSURE PLATE IS CORRODED ON THE UPPER SURFACE AT APPROX STA 1694 AT APPROX RBL 17 REPAIRED CORROSION ON AFT DECK PRESSURE PLATE UPPER SURFACE APPROX STA 1694, RBL7. REF FEDEX EA F-5310-T0370248-P1REV. A. FUSELAGE-MAINFRAME-AFT DECK PLATE- STA1681- 1720,-LBL20-RBL45-CORROSION.

Part: FLOOR PANEL — DAMAGED (ZONE 200) · airframe 63,129 hrs · 25,428 cycles

MAIN CABIN FLOOR PANEL 252MWF HAS SEVERAL BROKEN AND SPINNING INSERTS REMOVED AND REPLACED DAMAGED INSERTS ON FLOOR PANEL 252MWF IAW B757 SRM 53-00-50- 2R, REPAIR 2, PARA. 4.B. AND FIG. 203, SHEET 1: ORIG SUB DATE: 9/6/2022

Part: FLOOR PANEL — DAMAGED (ZONE 200) · airframe 63,129 hrs · 25,428 cycles

MAIN CABIN FLOOR PANEL 251MXF HAS SEVERAL BROKEN AND SPINNING INSERTS REMOVED AND REPLACED DAMAGED INSERTS ON FLOOR PANEL 251MXF IAW B757 SRM 53-00-50- 2R, REPAIR 2, PARA. 4.B. AND FIG. 203, SHEET 1. ORIG SUB DATE: 9/6/2022

Part: SKIN — GOUGED (LT WING TE FLAP) · airframe 63,129 hrs · 25,428 cycles

(AD RELATED) LH OB FLAP LE PREVIOUS REPAIR IS GOUGED AT OB SIDE OF REPAIR REPLACED DOUBLER IAW FEDEX EA F-5750-T0355303-P1, RELEASED JUL 24, 2020, TITLED "WINGS - FLIGHT SURFACES - LH OB MAIN FLAO LE PREVIOUS REPAIR. ORIG SUB DATE: 9/6/2022

Part: SKIN — DENTED (LT WING TE FLAP) · airframe 63,129 hrs · 25,428 cycles

L/H WING INBD FWD FLAP LOWER SURFACE HAS MULTIPLE DENTS THROUGHTOUT. REPAIRD L/H WING INBD FLAP LOWER SURFACE DENT A AND DENT C IAW B757 SRM 57-53-01- 2R FIG 201 REPAIR 1 SHEET 2 AND 51-70-10-2R-2. ORG SUB DATE: 9/6/2022

Part: CREASE BEAM — CORRODED (ZONE 200) · airframe 63,129 hrs · 25,428 cycles

MAIN CABIN STA 1602 AND RBL 64, CREASE BEAM INBD CHORD HAS CORROSION AT NUT PLATE HOLE REPAIRED THE MAIN CABIN RBL 64 CREASE BEAM INBD CHORD AT STA 1602 IAW FEDEX E.A. F- 5310-T0370357-P1, TITLE: FUSELAGE - MAINFRAME - CREASE BEAM, STA 1602, RBL 64, CORROSION. ORIG SUB DATE: 9/2/2022

Part: SKIN — DENTED (LT WING TE FLAP) · airframe 63,129 hrs · 25,428 cycles

LW I/B FLAP UPPER PANEL HAS SEVERAL DENTS AFT OF #6 SPOILER. REPAIRED 2 EACH DENTS #5 AND #6 DENTS ON STEP 9 AT THE LEFT WING I/B MAIN FLAP UPPER SKIN BY REMOVING DAMAGE, FABRICATING FILLERS AND DOUBLER, CLEANING AND PREPPING SURFACE, LAYING UP PARTS AND CURED PARTS IAW B757 SRM 57-53-01-2R-1 AND 51-70-10-2R. RESTORED FINISH IAW B757 SRM 51-70-10-2R PARA 22.

Part: ANGLE — CRACKED (RT MLG WW) · airframe 63,129 hrs · 25,428 cycles

RMLG W/W WING TO BODY SUPPORT SUB-STRUCTURAL CLIP IS CRACKED AT THE CORNER OF THE CUTOUT AT STA 1100 REMOVED & REPLACED CLIP IAW BAC DWG 149N7552, SHEET 1, REVISION F.

Part: SEAT TRACK — CORRODED (ZONE 200) · airframe 63,129 hrs · 25,428 cycles

MAIN CABIN , SUPERNUMERARY SEAT TRACK HAS CORROSION , STA 345 TO STA 377 , LBL 7 REMOVED AND REPLACED SEAT TRACK IAW VTMAE DRW-3VKJ5 # 3470 , B757-200 SRM 53-10-52-01 AND SRM 51-40-02

Part: SEAT TRACK — CORRODED (BS 350-360) · airframe 63,129 hrs · 25,428 cycles

MAIN CABIN SEAT TRACK IS CORRODED, BS 350 TO 360, RBL 10 REMOVED CORROSION ON FLANGE AND FOUND TO BE OUT OF LIMITS IAW B757 SRM 53-00-52-1A, A.D. 1, FIG. 101, SHT. 4, DETAIL VII. ORIGINAL MATERIAL THICKNESS IS .100", REMAINING THICKNESS IS .053", .047" WAS REMOVED. REMOVED AND REPLACED SEAT TRACK P/N 3504-3 FABRICATED ON N00485 IAW ST MEA DWG 3470, REV. D.

Part: SKIN — WORN (LT WING TE FLAP) · airframe 63,129 hrs · 25,428 cycles

LW IB FLAP UPPER OB REPAIR AREA IS WORN AT OB UPPER SKIN. REPAIRED LW IB FLAP UPPER SKIN WITH PERMENAT REPAIR IAW B757 SRM 57-53-01-2RFIG 201 REPAIR 1 SHEET 1 AND 51-70-10-2R REPAIR 3 AND 4.

Part: SKIN — CRACKED (ZONE 600) · airframe 63,129 hrs · 25,428 cycles

RIGHT WING OUTBOARD FIXED LEADING EDGE IS CRACKED AT LOWER FWD ATACH FASTENER HOLE. REPAIRED RIGHT WING OUTBOARD FIXED LEADING EDGE SKIN AT LOWER FWD ATTACH FASTENER HOLE IAW B757 SRM 57-41-01-2RFIG 201 REPAIR 1 SHEET 8AND 51-70-07-0G.

Part: FLOOR PANEL — DELAMINATED (MAIN CABIN) · airframe 63,129 hrs · 25,428 cycles

MAIN CABIN, FLOOR PANEL 221MBF HAS A LARGE AREA OF DELAMINATION ON TOP SURFACE FABRICATED NEW FLOOR PANEL 221MBF IAW FEDEX DWG SRZ-25-005, REV. R, P/N 11861182-16

Part: FLOOR PANEL — DELAMINATED (MAIN CABIN) · airframe 63,129 hrs · 25,428 cycles

MAIN CABIN FLOOR PANEL 231MFF HAS SEVERAL AREAS OF DELAMINATION FABRICATED NEW FLOOR PANEL 231MFF IAW FEDEX DWG SRZ-25-005, REV. R, FEDEX GMM 7-0- 1000, REV.182, AND B757 AMM 51-24-05-7.

Part: FLOOR PANEL — DELAMINATED (MAIN CABIN) · airframe 63,129 hrs · 25,428 cycles

MAIN CABIN FLOOR PANEL 231MAF HAS SEVERAL AREAS OF DELAMINATION FABRICATED NEW FLOOR PANEL 231MAF IAW FEDEX DWG SRZ-25-005, REV. R, FEDEX GMM 7-0- 1000, REV. 182, AND B757 AMM 51-24-05-7.

Part: FLOOR PANEL — DELAMINATED (MAIN CABIN) · airframe 63,129 hrs · 25,428 cycles

MAIN CABIN, FLOOR PANEL 222MAF HAS A LARGE AREA OF DELAMINATION ON TOP SURFACE FABRICATED NEW FLOOR PANEL 222MAF IAW FEDEX DWG SRZ-25-005, REV. R, P/N 11861180-1

Part: FLOOR PANEL — DELAMINATED (MAIN CABIN) · airframe 63,129 hrs · 25,428 cycles

MAIN CABIN FLOOR PANEL 231MGF HAS SEVERAL AREAS OF DELAMINATION

Part: FLOOR PANEL — DELAMINATED (MAIN CABIN) · airframe 63,129 hrs · 25,428 cycles

MAIN CABIN FLOOR PANEL 231MEF HAS SEVERAL AREAS OF DELAMINATION

Part: FLOOR PANEL — DELAMINATED (251) · airframe 63,129 hrs · 25,428 cycles

MAIN CABIN FLOOR PANEL 251MTF HAS SEVERAL AREAS OF DELAMINATION FABRICATED NEW FLOOR PANEL 251MTF IAW FEDEX DWG SRZ-25-005, REV. R, VTMAE DWG 11864182, REV. A, AND BAC D6-55191, REV. C

Part: FLOOR PANEL — DELAMINATED (MAIN CABIN) · airframe 63,129 hrs · 25,428 cycles

MAIN CABIN FLOOR PANEL 251MEF HAS SEVERAL AREAS OF DELAMINATION

Part: FLOOR PANEL — DELAMINATED (MAIN CABIN) · airframe 63,129 hrs · 25,428 cycles

MAIN CABIN FLOOR PANEL 231MCF HAS SEVERAL AREAS OF DELAMINATION

Part: FLOOR PANEL — DELAMINATED (MAIN CABIN) · airframe 63,129 hrs · 25,428 cycles

MAIN CABIN FLOOR PANEL 232MFF HAS SEVERAL AREAS OF DELAMINATION FABRICATED NEW FLOOR PANEL 232MFF IAW FEDEX DWG SRZ-25-005, REV. R, FEDEX GMM 7-0- 1000, REV. 182, AND B757 AMM 51-24-05-7

Part: ATTACH BRACKET — CRACKED (NR 2 NACELLE) · airframe 63,129 hrs · 25,428 cycles

#2 PYLON AFT FAIRING, FWD HYD LINE CLAMP ATTACH BRACKET IS CRACKED ON INBD SIDE JUST AFT OF PYLON AFT BULKHEAD AT APPROX STA 203 LH REMOVED & REPLACED SHEAR BEAM & SPACER IAW BAC DWG 313N3052 SHEET 1 REVISION B & B757 SRM 51-40-02-0G

Part: FLOOR PANEL — DELAMINATED (MAIN CABIN) · airframe 63,129 hrs · 25,428 cycles

MAIN CABIN FLOOR PANEL 232MAF HAS SEVERAL AREAS OF DELAMINATION FABRICATED NEW FLOOR PANEL 232MAF IAW FEDEX DWG SRZ-25-005, REV. R, FEDEX GMM 7-0- 1000, REV. 182, AND B757 AMM 51-24-05-7.

Part: FLOOR PANEL — DELAMINATED (MAIN CABIN) · airframe 63,129 hrs · 25,428 cycles

MAIN CABIN FLOOR PANEL 231MBF HAS SEVERAL AREAS OF DELAMINATION FABRICATED NEW FLOOR PANEL 231MBF IAW FEDEX DWG SRZ-25 005, REV. R, FEDEX GMM 7-0- 1000, REV. 182, AND B757 AMM 51-24-05-7.

Part: FLOOR SUPPORT — CORRODED (MAIN CABIN) · airframe 63,129 hrs · 25,428 cycles

MAIN CABIN FLOOR SUPPORT STRUCTURE HAS CORROSION ON UPPER SURFACES AT 6EA FLOOR PANEL FASTENER LOCATIONS FROM APPROX STA 720-735, RBL 59-64 REMOVED CORROSION ON MAIN CABIN FLOOR SUPPORT STRUCTURE, STA 720 TO 735, RBL 59 TO 64 IAW B757 SRM 53-00-51-1A, FIG. 201, SHEET 4 AND FOUND TO BE OUT OF LIMITS. ORIGINAL MATERIAL THICKNESS IS .070, REMAINING THICKNESS IS .054, REMOVED .016. REPAIRED FLOOR SUPPORT STRUCTURE AREA, STA 720-735, RBL 59-64 IAW FEDEX EA F-5310-T0370234-P1, TITLE: FUSELAGE - MAINFRAME - FLOOR/GUTTER SUPPORT, STA 720, RBL 59, CORROSION, RELEASE DATE: AUG 23, 2022.

Part: ATTACH FITTING — CRACKED (NR 2 NAC FAIRING) · airframe 63,129 hrs · 25,428 cycles

#2 PYLON AFT FAIRING OUTBD SIDE, FWD LOWER FAIRING ATTACH CLIP IS CRACKED AT NAC STA 203 CRACKED FWD ATTACH CLIP ON #2 PYLON O/B SIDE WAS REMOVED AND REPLACED IAW B757 SRM 51-40-02-0G ABD BAC DWG 313N3052, REVISION B.

Part: SKIN — GOUGED (N/A) · airframe 63,129 hrs · 25,428 cycles

RIGHT WING OUTBOARD FWD FLAP OUTBOARD LEADING EDGE HAS GOUGE

Part: SCUFF PLATE — CRACKED (R1 DOORWAY) · airframe 63,129 hrs · 25,428 cycles

EXTERNAL FUSELAGE, R-1 DOOR SCUFF PLATE, THE AFT CORNER PLATE IS CRACKED REPAIRED THE R-1 DOOR AFT CORNER SCUFF PLATE AND RESTORED FINISH IAW FEDEX DWG SR57-53-003, REV. B.

Part: FRAME — DENTED (BS 540 S6-7R) · airframe 63,129 hrs · 25,428 cycles

MAIN CABIN FRAME IS DENTED AT STA 540, BETWEEN S6R AND S7R REPAIRED STA 540 FRAME BETWEEN S6R AND S7R IAW B757 SRM 53-00-07-2R, REPAIR 3, FIG. 201, SHEET 1.

Part: SKIN — CRACKED (WING) · airframe 63,129 hrs · 25,428 cycles

WHILE ACCOMPLISHING EO F-5730-E0340076-P1 (DIAGONAL BRACE AND WING SKIN INSPECTION) A CRACK INDICATION WAS NOTED IN THE NO.2 FASTENER HOLE COMMON TO THE SKIN & ATTACH FITTING COMPLIED WITH FEDEX EA F-5730-T0369921-P1, RELEASED SEP 07, 2022. TITLED "WINGS - PLATES AND SKINS - LH WING UPPER SKIN AT FRAG FITTING, HOLE 2, CRACK REPAIR * THIS EA DEVIATES FROM EO F-5730-E0340076"

Part: CREASE BEAM — CORRODED (BS 860-865 RBL64) · airframe 63,129 hrs · 25,428 cycles

MAIN CABIN CREASE BEAM INBD CHORD UPPER SURFACE HAS CORROSION FROM APPROX STA 860-865, RBL 64

Part: PLATE — CRACKED (RT WING TE) · airframe 63,129 hrs · 25,428 cycles

RIGHT WING TRAILING EDGE WIGGLE PLATE AT WS 342 IS CRACKED REMOVED & REPLACED WIGGLE PLATES AT RIGHT WING TRAILING EDGE WS 342 IAW BAC DWG 113N1630, REV -

Part: FLOOR SUPPORT — DAMAGED (ZONE 200) · airframe 63,129 hrs · 25,428 cycles

MAIN CABIN FLOOR SUPPORT INTERCOSTAL HAS TOOLING MARKS ON UPPER RH SIDE AT APPROX STA 584, BL-0. REMOVED AND REPLACED MAIN CABIN FLOOR SUPPORT INTERCOSTAL WEB, STA 584, BL-0 IAW B757SRM 51-40-02-0G AND VT MAE DWG 1182110, REV. -, P/N 11864112-2 FABRICATED ON N00510.

Part: ANGLE — CRACKED (RT MLG WW) · airframe 63,129 hrs · 25,428 cycles

EXT FUSELAGE AFT OF R/M/G WHEEL WELL ATTACH ANGLE CRACKED BS 1180, BL 11R REMOVED & REPLACED ANGLE IAW BAC DWG 149N7528, REVISION J, & B757 SRM 51-40-02

Part: SUPPORT — CRACKED (RT MLG WW) · airframe 63,129 hrs · 25,428 cycles

RMLG WHEEL WELL, WING TO BODY SUPPORT SUB STRUCTURE CLIP IS CRACKED APPROX 8" UP FROM THE CORNER OF THE CUTOUT AT STA 1100 REMOVED & RPELACED SUPPORT IAW BAC DWG 149N7552, REVISION A & B757 SRM 51-40-02

Part: SUPPORT ANGLE — CRACKED (ZONE 100) · airframe 63,129 hrs · 25,428 cycles

FORWARD CARGO BELOW AIR FILTER SUPPORT ANGLE IS CRACKED AT STA 850 REMOVED AND REPLACED WITH FABRICATED FORWARD PIT BELOW AIR FILTER SUPPORT ANGLE AT STA 850

Part: FLOORBEAM — CRACKED (BS 580) · airframe 63,045 hrs · 25,368 cycles

STA 580 STUB FLOOR BEAM L/H IS CRACKED UNDER SEAT TRACK AT LBL 45.5 REMOVED DAMAGED L/H STUB FLOOR BEAM AT STA 580 REF. 757 SRM 51-40-02. OK TO INSTALL STUB FLOOR BEAM AT STA 580 REF B757 SRM 51-40-02 RII: 5502 NSTALLED STUB FLOOR BEAM AT STA 580 REF. SR57-53-004 AND 757 SRM 51-40-02.

Part: GUST LOCK — FAILED (N/A) · airframe 62,892 hrs · 25,271 cycles

MDIS 797 52-10 6261 22MAR22 MEM FACT U L1 DOOR GUST LOCK CAM BROKEN MEL 22MAR22 05:05 MEM U RELEASED FOR SERVICE PER MEL : 52-11-01-A CATEGORY : B EXPIRATION : 25MAR22 MEL 52-11-01-A: L1 DOOR INOP C/7309723 PART 22MAR22 05:05 MC1 U FACT 24MAR22 18:45 MEM U REMOVED & REPLACED THE L1 DOOR HOLD-OPEN LOCK (GUST LOCK) PER B757 AMM 52-11-08-8. CHECKS OK. NAME: HOLD-OPEN LOCK MFG: ALLIANCE AEROSPACE ENGINEERING PART NUMBER: 10-N0244-7 NO SERIAL NUMBER

Part: SLIDE — UNWANTED DEPLOY (L1 DOOR) · airframe 62,395 hrs · 24,942 cycles

WHILE WORKING EO F-5200-E0320318 D PT2 L1 DOOR SLIDE DEPLOYED. RELEASED FOR SERVICE. L1 SLIDE MISSING. SLIDE STOWED BEHIND RCB DOOR BOTTLE WILL REQUIRE SERVICING. REMOVED AND REPLACED L1 DOOR SLIDE REF AMM 25-66-00-2.

Part: SLIDE — MALFUNCTIONED (PAX DOOR) · airframe 62,360 hrs · 24,917 cycles

WHEN CLOSING MAIN CABIN DOOR, SLIDE BLEW DOOR OPEN BUT THE SLIDE DID NOT DEPLOY. REMOVED AND REPLACED L1 PASSENGER DOOR ESCAPE SLIDE. REF 757 MM 25-66-01-4.

Part: SLIDE — INOPERATIVE (L1 DOOR) · airframe 62,356 hrs · 24,913 cycles

WHEN CLOSING MAIN CABIN DOOR, SLIDE BLEW DOOR OPEN, BUT THE SLIDE DID NOT DEPLOY. REMOVED AND REPLACED L1 PASSENGER DOOR ESCAPE SLIDE. REF 757 MM 25-66-01-4.

Part: SLIDE — UNWANTED DEPLOY (R1 DOOR) · airframe 61,440 hrs · 24,324 cycles

AFTER BLOCK IN, 1R DOOR SLIDE DEPLOYED WHEN GROUND CREW OPENED DOOR. INSTALLED NEW SLIDER ON GIRTBAR AND TARGET, IN REF TO 757 AMM 25-66-01-4. OPERATIONS CHECK DOOR ARM LIGHT IS GOOD.

Part: ATTACH ANGLE — CRACKED (BS 640) · airframe 61,287 hrs · 24,224 cycles

LEFT LOWER SIDEWALL ATTACH ANGLE AT BS 640 CRACKED. REMOVED AND REPLACED THE ANGLE IAW DWG 453N1131 AND SRM 51-40-02.

Part: BATTERY PACK — FAILED (EMERGENCY LIGHTS) · airframe 61,287 hrs · 24,224 cycles

EMERGENCY BATTERY PACK DOES NOT HOLD CHARGE. REMOVED, REPLACED, AND OPS CHEC KED GOOD EMERGENCY LIGHT BATTERY PACK M730 PER B757 AMM 33-51- 07-2.

Part: BRACKET — CRACKED (LT NACELLE) · airframe 61,287 hrs · 24,224 cycles

LEFT PYLON,UNDER PANEL 435AR FWD LOWER CORNER HAS BRACKET CRACKED REMOVED AND REPLACED ATTACH ANGLE PER B757 SRM 51-40-02 AND DWG #313N3052 REV B

Part: RIVET — WRONG PART (LT WING) · airframe 61,287 hrs · 24,224 cycles

DURING AGING AIRCRAFT INSPECTION FOUND EXISTING REPAIR ON LEFT WING OUTBOARD MAIN FLAP LEADING EDGE SKIN DOES NOT MEET CURRENT SRM STANDARDS DUE TO INCORRECT RIVET SPACING,CUTOUT ORIENTATION,AND REPAIR PARTS USED

Part: SEAT TRACK — CORRODED (BS 365-377) · corrosion level 2 · airframe 61,287 hrs · 24,224 cycles

MAIN CABIN, FWD RIGHT WET AREA, SEAT TRACK CORRODED BS 365 - 377 RBL 45 COMPLIED WITH EA F-5310-T0355330.

Part: SEAT TRACK — CORRODED (BS 345-379) · corrosion level 2 · airframe 61,287 hrs · 24,224 cycles

MAIN CABIN, FWD L/H WET AREA, LBL7 SEAT TRACK CORRODED TAPED AREAS ON SIDE OF TRACK 345 - 379 REMOVED CORROSION, ORIGINAL THICKNESS .072" MATERIAL REMOVED .018", REMAINING .054", OUT OF LIMITS OF B757 SRM 53-10-52-01, FABRICATED SEAT TRACK IAW VENTURA AEROSPACE DWG 3504-NC-2 AND INSTALLED NEW SEAT TRACK IAW VENTURA AEROSPACE DWG 3470 REV G

Part: LINE — CORRODED (OXYGEN SYSTEM) · corrosion level 2 · airframe 61,287 hrs · 24,224 cycles

MAIN CABIN, FWD RT WET AREA, CORROSION AT O2 LINE FEED THROUGH STA 375 RBL 37 REMOVED O2 LINE IAW AMM 53-11-00-2 AND 20-11-00-2. REMOVED O2 PLATE IAW SRM 51-40- 02. FABRICATED NEW O2 PLATE IAW DWG 3516 REV -. INSTALLED NEW O2 PLATE IAW DWG 3516 REV - AND SRM 51-40-02. REINSTALLED AND LEAK CHECKED O2 LINE IAW AMM 35-11-00-2 AND 20-11-00-2.

Part: PLATE — CORRODED (BS 375 RBL 37) · corrosion level 2 · airframe 61,287 hrs · 24,224 cycles

MAIN CABIN, FWD RT WET AREA, CORROSION AT O2 LINE FEED THROUGH BS 375, RBL 37. REMOVED O2 LINE IAW AMM 53-11-00-2 & 20-11-00-2. REMOVED O2 PLATE IAW SRM 51-40-02. FABRICATED A NEW O2 PLATE IAW DWG 3516, REV -. INSTALLED THE NEW O2 PLATE IAW DWG 3516 REV - & SRM 51-40-02. REINSTALLED AND LEAK CHECKED O2 LINE IAW AMM 35-11-00-2 & 20-11-00-2.

Part: BRACKET — CRACKED (RT NACELLE) · airframe 61,287 hrs · 24,224 cycles

R/H PYLON I/B PANEL 445AL CONDUIT INSIDE FWD BRACKET CRACKED REMOVED AND REPLACED BRACKET PER BOEING DWG # 313N3053 REV E AND SRM 51-40-02

Part: BRACKET — CRACKED (RT NACELLE) · airframe 61,287 hrs · 24,224 cycles

R/H PYLON PANEL O/B INSIDE PANEL 445BR BRACKET FOR CONDUIT CRACKED REMOVED AND REPLACED BRACKET PER BOEING DWG # 313N3033 REV D AND B757 SRM 51-40-02

Part: NUT PLATE — CORRODED (BS 325 FLOORBEAM) · airframe 61,287 hrs · 24,224 cycles

MAIN CABIN, FWD R/H WET AREA, FLOOR BAEM CORRODED AT NUT PLATES STA 325 RBL 35-58 REMOVED CORROSION ORIGINAL THICKNESS .120 REMOVED .011 NEW THICKNESS .109 WICH IS FOUND TO BE WITHIN LIMITS WICH IS FOUND TO BE WITHIN LIMITS IAW B757 SRM 53-10-08-1A AND BOEING DWG 141N2930 APPLIED ALODINE, PRIME AND TOP COAT IAW B757 SRM 51-20-01- 0G

Part: SKIN — PUNCTURED (BS 177-182) · airframe 61,287 hrs · 24,224 cycles

LEFT HORIZONTAL STAB LOWER SURFACE SKIN WAS A PUNCTURED APPROX. 5 INCHES LONG, APPROX. 5 INCHES FROM THE LEADING EDGE. REPAIRED HORIZONTAL STAB LOWER SKIN BY REMOVING DAMAGE, LAYING UP CORE PLUG AND EXT. DOUBLER REPAIR AND CURED IAW SRM 55-10-01 AND SRM 51-70-10-2R REPAIR NR 4. RESTORED FINISH IAW SRM 51-70-10-2R REPAIR NR 4.

Part: SEAT TRACK — CORRODED (BS 365-379) · airframe 61,287 hrs · 24,224 cycles

MAIN CABIN, FWD RT WET AREA HAD CORROSION ON THE SEAT TRACK, BS 365 - 379, RBL 25. REMOVED CORROSION, ORIGINAL THICKNESS .070, REMOVED MATERIAL .009, REMAINING .061 FOUND WITHIN LIMITS IAW SRM 53-00-52--1A, DETAIL 7, DWG 1520- 792 AND SRM 53-10-52-01, APPLIED ALODINE, PRIME AND TOP COAT IAW SRM 51-20- 01-0G.

Part: NUT PLATE — CORRODED (BS 1681.8) · airframe 61,287 hrs · 24,224 cycles

FLOORBEAM LOWER NUT PLATE STRIP WAS CORRODED, BS 1681.8, LBL 39. REMOVED AND REPLACED THE FLOORBEAM LWR NUTPLATE STRIP IAW SRM 51-40-02, AND DWG 146N5693, REV C.

Part: FLOORBEAM — CORRODED (CABIN) · airframe 61,727 hrs · 24,493 cycles

FLOOR BEAM LOWER NUT PLATE STRIP IS CORRODED BS 1681.8 LBL 4. REMOVED AND REPLACED FLOOR BEAM LOWER NUTPLATE STRIP AT BS 1681.8 LBL 4, IAW FEDEX B757 SRM 51-40-02 AND DWG 146N5693 REV C.

Part: FLOORBEAM — CORRODED (BS 1681) · airframe 61,287 hrs · 24,224 cycles

FLOOR BEAM LOWER NUT PLATE STRIP IS CORRODED BS 1681.8, LBL39 REMOVED AND REPLACED FLOOR BEAM LWR NUTPLATE STRIP AT BS 1681.8 LBL 39 IAW SRM 51-40-02 AND DWG 146N5693 REV C

Part: FLOOR SUPPORT — CORRODED (BS 1661.8-1681.8) · airframe 61,287 hrs · 24,224 cycles

FLOOR SUPPORT FITTING UPPER SURFACE IS CORRODED BS 1661.8 - BS 1681.8, RBL 0. REMOVED AND REPLACED CORRODED CHANNEL IAW DWG 146N5576 AND SRM 51-40-03-06, FID 1 SHEET 4 AND SHEET 7.

Part: PRESSURE DECK — CORRODED (BS 1714) · airframe 61,287 hrs · 24,224 cycles

MAIN CABIN PRESSURE DECK UPPER PLATE IS CORRODED BS 1714, LBL 6 - BL9 REMOVED CORROSION IAW SRM 51-10-02. FOUND TO BE WITHIN LIMITS IAW SRM 53-60-51-1A, TREATED BARE METAL IAW SRM 514-20-01.

Part: FLOORBEAM — CORRODED (BS 1681.8) · airframe 61,287 hrs · 24,224 cycles

FLOORBEAM UPPER SURFACE WAS CORRODED AT SEVERAL AREAS, BS 1681.8, LBL 4 - LBL 47. REMOVED CORROSION IAW SRM 51-10-02, FOUND TO BE WITHIN LIMITS IAW SRM 53-60-51-1A, TREATED BARE METAL IAW SRM 51-20-01.

Part: FLOORBEAM — CORRODED (BS 1681.8) · airframe 61,287 hrs · 24,224 cycles

FLOORBEAM UPPER SURFACE WAS CORRODED, BS 1681.8, RBL 11. REMOVED CORROSION IAW SRM 51-10-02, FOUND TO BE WITHIN LIMITS IAW SRM 53- 60-51-1A, TREATED BARE METAL IAW SRM 51-20-01.

Part: FLOORBEAM — CORRODED (BS 365) · airframe 61,287 hrs · 24,224 cycles

MAIN CABIN, FWD RIGHT WET AREA , PRIOR TEE CAP REPAIR HAS CORROSION AT SEAT TRACK AREAS, BS 365 BL 0 TO RBL 64. REMOVED CORROSION, ORIGINAL THICKNESS (.125") REMOVED (.005") REMAINING (.120") CROSSECTIONAL AREA IS LESS THAN 5% WITH A1=.250" AND A2= .0025 A2/A1= 1% IAW SRM 53-00-51-1A FG 101 DETAIL 3 M4, AND SRM 53-10-52-01.

Part: PRESSURE DECK — CORRODED (BS 1685.5-1688.5) · airframe 61,287 hrs · 24,224 cycles

MAIN CABIN PRESSURE DECK UPPER PLATE WAS CORRODED, BS 1685.8 - BS 1688.5. REMOVED THE CORROSION IAW SRM 51-10-02, FOUND TO BE WITHIN LIMITS IAW SRM 53-60-51-1A, TREATED BARE METAL IAW SRM 51-20-01.

Part: BALL SCREW — CORRODED (TE FLAPS) · airframe 59,836 hrs · 23,278 cycles

TE FLAP DISAGREE WHEN FLAP HANDLE WAS MOVED FROM 0 TO 1. RAN QRH AND LANDED. R & R THE LT INBD NR 4 FLAP TRANSMISSION ASSY IAW MM 27-51-06-4, UP TO UNIVERSAL JOINT DRIVE SHAFT. FOUND THE DRIVE SHAFT BEARINGS EXCESSIVELY CORRODED AND UNSERVICEABLE. R & R THE BALLSCREW AND GIMBAL FITTING IAW MM 27-51-11-4.

Part: CYLINDER — DISCHARGED (L1 DOOR) · airframe 59,711 hrs · 23,192 cycles

L1 DOOR ASSIST BOTTLE DISCHARGED UPON DOOR DE-ACTIVATION. R&R LT EMERG DOOR ASSIST CYL PER AMM 52-11-30-4. AC OK FOR SERVICE.

Part: SKIN — DAMAGED (BS 1787) · airframe 59,639 hrs · 23,151 cycles

FUSELAGE SKIN AT BS 1787.45, STRINGERS 17R-18R HAD A 6 INCH SCRATCH BELOW THE FAIRING. REMOVED THE DAMAGED, FABRICATED, AND INSTALLED A REPAIR IAW SRM 53-80-70-2R, FIG 201, REP 2 DETAIL I.

Part: TRANSMITTER — INOPERATIVE (RT WING TE FLAP) · airframe 58,168 hrs · 22,104 cycles

AFTER TAKEOFF, WHEN FLAP HANDLE WAS MOVED FROM 5 TO 1 DEGREES, AN IMMEDIATE EICAS MESSAGE FOR TE FLAP ASYMETERY APPEARED AND THE FLAP GUAGE STOPPED SLIGHTLY LESS THAN 5 DEGREES WITH ASSOCIATED FLAP STOPPAGE. REMOVED AND REPLACED THE FLAP POSITION TRANSMITTER. IAW AMM 27-58-03-4. OPS CHECKED GOOD. OK FOR SERVICE

Part: HANDLE — LOOSE (SLIDING WINDOW) · airframe 58,061 hrs · 22,031 cycles

CAPTAIN`S SLIDING WINDOW WILL NOT LOCK IN CLOSED POSITION. FOUND CAPTAIN'S SLIDING WINDOW HANDLE LOOSE CAUSING LOCK FEATURE TO BE INOPERABLE. RESECURED HANDLE INTO POSITION. WINDOW OPERATES NORMAL IAW MM 56-11-02-5-0.

Part: DOOR FRAME — GOUGED (FUSELAGE) · airframe 58,003 hrs · 21,987 cycles

FWD E & E CUT OUT FWD DOOR FRAME GOUGED BY DOOR LOCK PIN. COMPLIED WITH EA F-5310-T0327174. BS 231.25, BL0 FRAME DENT, REPAIR. THIS IS A MAJOR REPAIR. PERFORMED SATISFACTORY. OPS CHECK FORWARD ELECTRONIC EQUIPMENT DOOR SENSOR IAW AMM 52-71-00-5.

Part: WIRE — DAMAGED (EMERGENCY LIGHT) · airframe 568 hrs · 21,121 cycles

COCKPIT EMER LIGHT INOPERATIVE. REWIRED IAW WDM CH 33-51-12. OPERATIONS CHECKED NORMAL.

Part: POWER SUPPLY — MALFUNCTIONED (COCKPIT) · airframe 56,568 hrs · 20,946 cycles

ON SERVICE CHECK FOUND FLIGHT DECK EMER LIGHT NOT WORKING. DISCONNECTED THE FWD & AFT EMER LIGHTING POWER SUPPLIES & THEN RECONNECTED BOTH. ACFT WAS POWERED UP FOR APPROX 2 HRS, THEN RAN THE POWER SUPPLY TEST ON EACH IAW MM 33-51-07-02. BOTH POWER SUPPLIES WORKED & ALL EMER LIGHTS ILLUMINATED. RAN THE EMER LIGHT TEST, ALL EMER LIGHTS ILLUMINATED. ACFT OK FOR SERVICE.

Part: SKIN — DENTED (FUSELAGE) · airframe 56,485 hrs · 20,874 cycles

PREVIOUS OPERATOR INCOMING DENT, 3 EACH. DENTS AT BS 760 DIRECTLY ABOVE & BELOW STRINGER 16LT. FUSELAGE SKIN REPAIR AT STATION 780 BETWEEN STRINGER 15L - 17L WAS ACCOMPLISHED, DUE TO EFFECTING THE PTF CONVERSION ON EA 757-5331-16-F4651 REV DATED JULY 30, 2014 & NR 60002267960001. THIS NR IS FOR TRACKING PURPOSES ONLY. IAW EA F-5330-T0310765 ISSUED FOR TRACKING. MAJOR REPAIR.

Part: GATE — CORRODED (R1 DOOR) · airframe 56,485 hrs · 20,874 cycles

R1 DOOR LOWER GATE LOWER END HAS CORROSION. ENTERED IN ERROR.

Part: SKIN — GOUGED (LT WING TE FLAP) · airframe 56,485 hrs · 20,874 cycles

LEFT WING OTBD MAIN FLAP UPPER SURFACE LE GOUGED. REMOVED DAMAGE IAW SRM 51-10-02. FOUND TO BE OUT OF LIMITS IAW SRM 57-53-01 FIG 101 DETAIL VI. REPAIRED & INSTALLED FILLER & DOUBLER IAW SRM 57-53-01 FIG 201 REPAIR 2. MAJOR REPAIR.

Part: CREASE BEAM — CORRODED (FUSELAGE) · corrosion level 2 · airframe 56,485 hrs · 20,874 cycles

CORROSION AT CABIN CREASE BEAM INNER CHORD STATION 730, BY DOOR L2. ORIGINAL CREASE BEAM FOUND TO BE OUT OF LIMITS IAW SRM 53-30-15, FIG 101, DETAIL IV. R & R CREASE BEAM SECTION IAW SRM 51-40-02, PG 1, SRM 51-40-05 & DWG 143N8322, BS 686 - 760, LBL 58. MAJOR REPAIR.

Part: FRAME — GOUGED (BS 1480) · airframe 56,485 hrs · 20,874 cycles

AFT CARGO BAY, BS 1480 STRINGER 23R FRAME INBD FLANGE GOUGED. FOUND TO BE OUT OF LIMITS IAW SRM 53-00-07, FIG. 101, DETAIL II. REMOVED AND REPLACED FRAME IAW SRM 51-40-02 AND DWG 146N1030. MAJOR REPAIR.

Part: SKIN — GOUGED (TE FLAP) · airframe 56,485 hrs · 20,874 cycles

RIGHT WING OTBD FWD FLAP OTBD LE UPPER SURFACE GOUGED AFTER REMOVED DAMAGE CHECKED LIMITS FOUND OUT OF LIMITS IAW SRM 57-53-01 PG 106 FIG 101 DETAIL VI. R & R LE IAW SRM 51-40-02 & DWG 113N3500 AT RT WING OTBD FWD FLAP.

Part: FRAME — DENTED (BS 1420) · airframe 56,485 hrs · 20,874 cycles

AFT CARGO BAY BS 1420 STRINGER 24L, FRAME INBD FLANGE AT SPLICE DENTED. FOUND TO BE OUT OF LIMITS IAW SRM 53-00-07, FIG. 101, PG. 1. REMOVED AND REPLACED FRAME S13 - 24L IAW SRM 51-40-02 AND DRAWING 146N1028. MAJOR REPAIR.

Part: FRAME — DENTED (FUSELAGE) · airframe 56,485 hrs · 20,874 cycles

AFT PIT BS 1320 STRINGER 25R TO 26R FRAME INBD FLANGE, DENTED FRAME. DENT IS OUT OF LIMITS IAW SRM 53-00-07 FIG 101 DETAIL I. R & R FRAME BS 1320, STRINGER 24R - 24L IAW SRM 51-40-02 & DWG 146N1028. MAJOR REPAIR.

Part: CREASE BEAM — CORRODED (FUSELAGE) · corrosion level 2 · airframe 56,485 hrs · 20,874 cycles

CORROSION ON CREASE BEAM INNER CHORD STATION 377 BY DOOR L1. REMOVED CORROSION & FOUND TO BE OUT OF LIMITS IAW SRM 53-30-13 FIG 101 DETAIL II. R & R WITH NEW CREASE BEAM AT STATION 395 - 324 LBL 61 IAW SRM 51-40-02 & DWG 657N3383 MAJOR REPAIR.

Part: FRAME — CORRODED (BS 1460) · corrosion level 2 · airframe 56,485 hrs · 20,874 cycles

AFT PIT, BS 1460 STRINGER 23L TO 27L FRAME INBD FLANGE CORRODED. FOUND OUT OF LIMITS IAW SRM 53-00-07, FIG. 101, DETAIL II. REMOVED AND REPLACED FRAME IAW SRM 51-40-02 AND DRAWING 146N1029. MAJOR REPAIR.

Part: SKIN — CHAFED (R4 DOOR) · airframe 56,485 hrs · 20,874 cycles

R4 DOOR INBD SKIN DOUBLER CHAFED.

Part: SKIN — GOUGED (CARGO DOOR) · airframe 56,485 hrs · 20,874 cycles

AFT CARGO DOOR EXTERNAL SKIN, BOTTOM FWD CORNER GOUGED. GOUGE IS OUT OF LIMITS IAW SRM 52-30-01 FIG 101 DETAIL IV. REPAIRED IAW EA F-5210-T0308955 PT 1, TITLE DOORS, PAX & CREW NR 2 CARGO DOOR CRACK REPAIR. SUPPLEMENTAL INSPECTION, MAJOR REPAIR & SRM 52-30-01 FIG 201 REPAIR 4. MAJOR REPAIR CAT B.

Part: CARGO TRACK — GOUGED (BS 1180-1320) · airframe 56,485 hrs · 20,874 cycles

MAIN DECK CARGO TRACK BS 1180 - 1320 LBL 24.75 GOUGED. CARGO TRACK WAS FOUND OUT OF LIMITS PER SRM 53-00-52, FIG. 101, SHEET 1 OF 6. REMOVED AND REPLACED CARGO TRACK IAW SRM 51-40-02, AND DWG 146N5133. MAJOR REPAIR.

Part: FLOORBEAM — CORRODED (BS 1600) · corrosion level 2 · airframe 56,485 hrs · 20,874 cycles

MAIN DECK CARGO FLOORBEAM UPPER TEE HAS AREAS OF CORROSION, BS 1600. FOUND OUT OF LIMITS PER SRM 53-00- 51, FIG. 101, DETAIL VI. REMOVED AND REPLACED FLOORBEAM IAW SRM 51-40-02 AND DWG 146N5087 BS 1600, LBL 63 - RBL 63. MAJOR REPAIR.

Part: FLOORBEAM — GOUGED (BS 1681) · airframe 56,485 hrs · 20,874 cycles

MAIN DECK CARGO FLOORBEAM AT BS 1681 UPPER TEE FWD EDGE HAS A GOUGE LBL 58. GOUGE OUT OF LIMITS PER SRM 53-00-51, DETAIL II. REMOVED AND REPLACED FLOORBEAM UPPER TEE IAW SRM 51-40-02 AND DWG 146N5091. MAJOR REPAIR

Part: CREASE BEAM — CORRODED (BS 1020-1040) · corrosion level 2 · airframe 56,485 hrs · 20,874 cycles

CREASE BEAM UPPER SURFACE CORRODED BS 1040 - 1020, RT SIDE. REMOVED CORROSION IAW SRM 51-10-02 AND FOUND OUT OF LIMITS IAW SRM 53-40- 13, FIG. 101, DETAIL VII. REMOVED AND REPLACED CREASE BEAM INNER ANGLE BS 900-1040 IAW SRM 51-40-02 AND DWGS 144N5152, SH. 1 AND 144N5140, SH. 4. MAJOR REPAIR.

Part: FRAME — DENTED (FUSELAGE) · airframe 56,485 hrs · 20,874 cycles

FORWARD PIT RT FRAME INNER FLANGE DENTED AT BS 640, BETWEEN STRINGER 23R - 24R. FOUND TO BE OUT OF LIMITS. R & R FRAME IAW SRM 51-40-02 & DWG 143N1011-38. MAJOR REPAIR.

Part: CARGO TRACK — CORRODED (BS 700-780) · corrosion level 2 · airframe 56,485 hrs · 20,874 cycles

MAIN DECK CARGO TRACK AT RBL 45.5 BETWEEN BS 700 & 780 HAS SEVERAL AREAS CORRODED. REMOVED CORROSION IAW SRM 51-10-02 AND FOUND TO BE OUT OF LIMITS IAW SRM 53-00-52 DETAIL I FIG. 101 PAGE 102. REMOVED AND REPLACED CARGO TRACK IAW SRM 51-40- 02 AND DWG 143N5090. MAJOR REPAIR.

Part: FLOORBEAM — CORRODED (BS 1661) · corrosion level 2 · airframe 56,485 hrs · 20,874 cycles

MAIN DECK CARGO FLOORBEAM UPPER TEE CORRODED AT BS 1661. REMOVED CORROSION IAW 51-10-02. FOUND TO BE OUT OF LIMITS IAW SRM 53-00-51 FIGURE 101, NOTE B PAGE 103. R & R FLOORBEAM TEE IAM SRM 51-40-02 & DWG 146N0501. MAJOR REPAIR.

Part: FLOORBEAM — CORRODED (BS 1640) · corrosion level 2 · airframe 56,485 hrs · 20,874 cycles

MAIN DECK CARGO FLOORBEAM UPPER TEE HAS AREAS CORRODED BS 1640. FOUND OUT OF LIMITS IAW SRM 53-00-51 PG 104 DET.III. REMOVED AND REPLACED FLOORBEAM TEE IAW SRM 51-40-02 AND DRAWING 146N8211. MAJOR REPAIR.

Part: CREASE BEAM — CORRODED (BS 1040) · corrosion level 2 · airframe 56,485 hrs · 20,874 cycles

CORROSION FOUND ON THE CREASE BEAM INNER ANGLE BS 1040. REMOVED CORROSION IAW SRM 51-10-02, FOUND OUT OF LIMITS IAW SRM 53-40-13 FIG 101 DET. VII REMOVED AND REPLACED CREASE BEAM ANGLE IAW SRM 51-40-02 AND DWGS 144N5214 SHEET 1 AND 144N5200 SHEETS 2,3,4. MAJOR REPAIR.

Part: FLOORBEAM — CORRODED (BS 365) · corrosion level 2 · airframe 56,485 hrs · 20,874 cycles

FORWARD CABIN AT BS 365.25 BL 0 & RBL 64 FLOORBEAM CORRODED. REMOVED CORROSION AND FOUND TO BE OUT OF LIMITS IAW SRM 53-00-51, FIG. 101, DETAIL VI. REPAIRED FLOORBEAM IAW SRM 53-00-51, REPAIR 8, FIG 201, DWG 141N5112. MAJOR REPAIR.

Part: SEAT TRACK — CORRODED (BS 700-780) · corrosion level 2 · airframe 56,485 hrs · 20,874 cycles

MID CABIN SEAT TRACK AT RBL 24.5 BETWEEN BS 700 - 780, HAS SEVERAL AREAS CORRODED. REMOVED CORROSION IAW SRM 51-10-02. FOUND TO BE OUT OF LIMITS IAW SRM 53-00-52 DETAIL I FIG.101 PAGE 102. REMOVED AND REPLACED SEAT TRACK IAW SRM 51-40- 02 AND DWG 143N5090. MAJOR REPAIR.