N964FD

Part: UNKNOWN — FAULTED (TE FLAPS) · airframe 75,219 hrs · 25,464 cycles

ON APPROACH INTO OAK GOT TE FLAP DISAGREE WHILE EXPENDING FLAPS THROUGH 15 . WENT AROUND. DISCOVERED HANDLE WAS STUCK BETWEEN FLAPS 15 AND 20. RAN QRH. DECLARED EMERGENCY. LANDED UNEVENTFUL IN OAK. FLAPS RETRACTED NORMALLY AFTER LANDING. REFERENCE WRI 27-50 / 7922 FOR ALL THE WORK PERFORMED. C/W STEP 1 OF MTSI, FOUND LEVER XMT AND LEVER DISAGREE ON FSEU #1 FAULT HISTORY. NO FAULTS FOUND ON FSEU #2 AND #3. C/W STEP 2 OF MTSI, CYCLED FLAPS FROM UP TO FLAP 30 COMPLETING 3 CYCLES. NO BINDING AND DISCREPANCIES NOTED. PERFORMED BITE CHECK OF FSEU'S AFTER CYCLING FLAPS, NO FAULTS NOTED. A/C OK TO CONT SERVICE.

Part: SKIN — DAMAGED (CARGO DOOR) · airframe 74,632 hrs · 25,018 cycles

REPAIRED MAIN CARGO DOOR SKIN AT AFT ACTUATOR ON WRI 52-30/7347. THIS WRITEUP IS FOR TRACKING EA F-5230-T0359030, WRI IS FOR TRACKING EA F-5230-T0359030. COMPLIED WITH SKIN REPAIR, PER SRM 52-30-01-2R REPAIR 4. COMPLETED ON WRI 52-30/7347.

Part: SKIN — PUNCTURED (NR 6 SLAT) · airframe 74,464 hrs · 24,897 cycles

NR 6 SLAT HAS A PUNCTURE BLENDED NR 6 SLAT, IAW B757 SRM 51-10-02. ORIG MATERIAL .080, REMAINING .049, LOSS .031. FOUND OUT OF LIMITS, IAW B757 SRM 57-43-01-1A. REPAIRED SLAT, IAW B757 SRM 57-43-01-2R REP 9.

Part: SKIN — CHAFED (RT WING TE FLAP) · airframe 74,464 hrs · 24,897 cycles

CHAFE MARK LEADING EDGE OF RIGHT OUTBOARD MAIN FLAP INBOARD SIDE. REMOVED DAMAGE ON LEADING EDGE OF RT OUTBOARD MAIN FLAP INBOARD SIDE, IAW B757 SRM 51-10-02. ORIG MAT .080 REM .030 LOSS .050 FOUND TO BE OUT OF LIMITS, IAW B757 SRM 57-53-01-1A FIG 101. REPAIRED FLAP IAW B757 SRM 57-53-01-2R RP 5 FIG 201.

Part: SEAT TRACK — CORRODED (MAIN CABIN) · corrosion level 2 · airframe 74,464 hrs · 24,897 cycles

MAIN CABIN SEAT TRACK FLANGE HAS CORROSION AT LBL 24 STA 1322. REMOVED CORROSION ON SEAT TRACK STA 1322 LBL 24, IAW B757 SRM 51-10-02. ORIGINAL MATERIAL .090, REMAINING .034, LOSS .056 OUT OF LIMITS, IAW B757 SRM 53-00-52-1A. REMOVED, FABRICATED, AND INSTALLED NEW SEAT TRACK STA 1320-1540 LBL 24, IAW B757 SRM 51-40-02, 51-40-05, 51-40-08, 53-60-52-01 AND BOEING DWG 146N5120 REV A, DB AND REV B.

Part: SEAT TRACK — CORRODED (MAIN CABIN) · airframe 74,464 hrs · 24,897 cycles

MAIN CABIN SEAT TRACK FLANGE HAS CORROSION AT RBL 45 STA 366. ALL WORK ACCOMPLISHED, IAW FEDEX EA F-5310-T0357429 P1. FUSELAGE-MAINFRAME-RBL 45.50 SEAT TRACK CORROSION REPAIR FROM STA 365 TO 377.

Part: SEAT TRACK — CORRODED (MAIN CABIN) · corrosion level 2 · airframe 74,464 hrs · 24,897 cycles

MAIN CABIN SEAT TRACK FLANGE HAS CORROSION AT LBL 45 STA 1320. REMOVED CORROSION ON SEAT TRACK STA 1320 LBL 45, IAW B757 SRM 51-10-02. 100% MATERIAL LOSS OUT OF LIMITS, IAW B757 SRM 53-00-52 FIG 101. REMOVED, FABRICATED AND INSTALLED NEW SEAT TRACK, IAW B757 SRM 51-40-02, 53-60-52-01 FIG 101 AND BOEING DWG 146N5120 REV C AND REV A FROM STA 1180 TO 1320.

Part: SKIN — DAMAGED (LT WING TE FLAP) · airframe 74,464 hrs · 24,897 cycles

LEFT WING OUTBOARD FLAP TRAILING EDGE UPPER EXTERNAL SURFACE HAS MULTIPLE AREAS OF BARE COMPOSITE. EVALUATED LT WING OUTBOARD FLAP TRAILING EDGE UPPER EXTERNAL SURFACE AND FOUND TO BE OUT OF LIMITS, IAW B757 SRM 51-10-06-2R. REPAIRED AREA IAW B757 SRM 57-53-01-2R REP 1 TABLE II AND 51-70-40 PAR 5C. SANDED, PRIMED, TOP COATED LT WING OUTBOARD FLAP TRAILING EDGE UPPER EXTERNAL SURFACE, IAW B757 SRM 51-21-10-7.

Part: SEAT TRACK — CORRODED (ZONE 200) · corrosion level 2 · airframe 74,464 hrs · 24,897 cycles

MAIN CABIN SEAT TRACK FLANGE HAS CORROSION AT RBL-45 STA 1540. REMOVED CORR ON SEAT TRACK STA 1540 RBL 45, IAW B757 SRM 51-10-02. ORIGINAL MAT .090, REMAINING .040, LOSS .050, OUT OF LIMITS, IAW B757 SRM 53-00-52-1A FIG 101. REMOVED, FABRICATED, AND INSTALLED NEW SEAT TRACK STA 1320-1540, IAW B757 SRM 51-40-02, 53-60-52-01 FIG 1, 51-40-05 AND BOEING DWG 146N5120 REV A AND REV B.

Part: SEAT TRACK — CORRODED (ZONE 200) · corrosion level 2 · airframe 74,464 hrs · 24,897 cycles

MAIN CABIN SEAT TRACK FLANGE HAS CORROSION AT RBL-24 STA 1540. REMOVED CORR ON SEAT TRACK STA 1540 RBL 24, IAW B757 SRM 51-10-02. ORIGINAL MATERIAL .090, REMAINING .034, LOSS .056, OUT OF LIMITS, IAW B757 SRM 53-00-52-1A FIG 101. REMOVED, FABRICATED AND INSTALLED NEW SEAT TRACK, IAW B757 SRM 51-40-02, 53-60-52-01 FIG 1 AND BOEING DWG 146N5120 REV B.

Part: SEAT TRACK — CORRODED (MAIN CABIN) · corrosion level 2 · airframe 74,464 hrs · 24,897 cycles

MAIN CABIN SEAT TRACK FLANGE HAS CORROSION AT RBL-45 STA 1320. REMOVED CORROSION FROM MAIN CABIN SEAT TRACK STA 1320 RBL 45, IAW B757 SRM 51-10-02-0G. ORIGINAL MATERIAL .090, 100% MATERIAL LOSS FOUND TO BE OUT OF LIMITS, IAW B757 SRM 53-00-52-1A. REMOVED, FABRICATED, AND INSTALLED NEW SEAT TRACK SECTION FROM STA 1180-1320 RBL 45, IAW B757 SRM 51-40-02-0G AND DWG 146N5120 REV A AND REV C.

Part: SEAT TRACK — CORRODED (MAIN CABIN) · corrosion level 2 · airframe 74,464 hrs · 24,897 cycles

MAIN CABIN SEAT TRACK FLANGE HAS CORROSION AT LBL-24 STA 1320 EVALUATED SEAT TRACK STA 1320 LBL 24. 100% MATERIAL LOSS, OUT OF LIMITS, IAW B757 SRM 53-00-5252-1A. REMOVED, FABRICATED, AND INSTALLED NEW SEAT TRACK, IAW B757 SRM 51-40-02, 53-6060-52-01 FIG 1 AND BOEING DWG 146N5120 REV C AND REV A.

Part: SEAT TRACK — CORRODED (MAIN CABIN) · corrosion level 2 · airframe 74,464 hrs · 24,897 cycles

MAIN CABIN SEAT TRACK FLANGE HAS CORROSION AT RBL-24 STA 1320. REMOVED CORROSION ON SEAT TRACK STA 1320 RBL 24, IAW B757 SRM 51-10-02. 100% MATERIAL LOSS OUT OF LIMITS, IAW B757 SRM 53-00-52-1A FIG 101. REMOVE, FABRICATED AND INSTALLED NEW SEAT TRACK, IAW B757 SRM 51-40-02, 53-60-52, 51-40-05 AND BOEING DWG 146N5120 REV C AND REV A.

Part: FLOORBEAM — CORRODED (MAIN CABIN) · corrosion level 2 · airframe 74,464 hrs · 24,897 cycles

MAIN CABIN FLOOR SUPPORT HAS CORROSION BETWEEN RBL 26 AND RBL 45 STA 1055. REMOVED CORROSION ON FLOOR SUPPORT PLATE STA 1055 RBL 26-RBL 45, IAW B757 SRM 51-10-02. 100% MATERIAL LOSS FOUND OUT OF LIMITS, IAW B757 SRM 53-00-51-1A FIG 101. REMOVED, FABRICATED, AND INSTALLED NEW PLATE, IAW B757 SRM 51-40-02 AND BOEING DWG 144N5070 REV W AND REV B.

Part: FLOORBEAM — CORRODED (MAIN CABIN) · corrosion level 2 · airframe 74,464 hrs · 24,897 cycles

MAIN CABIN FLOOR SUPPORT HAS CORROSION BETWEEN LBL 24 AND LBL 45 STA 900. REMOVED CORROSION ON FLOOR SUPPORT PLATE STA 900 LBL 24-LBL 45, IAW B757 SRM 51-10-02. 100% MATERIAL LOSS OUT OF LIMITS, IAW B757 SRM 53-00-51-1A FIG 101. REMOVED, FABRICATED, AND INSTALLED NEW PLATE, IAW B757 SRM 51-40-02 AND BOEING DWG 144N5070 REV W AND REV B.

Part: FLOORBEAM — CORRODED (MAIN CABIN) · corrosion level 2 · airframe 74,464 hrs · 24,897 cycles

MAIN CABIN FLOOR SUPPORT HAS CORROSION BETWEEN RBL 1 AND RBL 24 STA 1020. REMOVED CORROSION ON FLOOR SUPPORT STA 1020 RBL 1-RBL 24, IAW B757 SRM 51-10-02. 100% MATERIAL LOSS OUT OF LIMITS, IAW B757 SRM 53-00-51-1A FIG 101. REMOVED, FABRICATED AND INSTALLED NEW FLOOR SUPPORT, IAW B757 SRM 51-40-02 AND FEDEX EA F-5310-T0357347 P1 FUSELAGE-MAINFRAME-MAIN CARGO FLOOR SUPPORT STA 1020 CORRODED, NEW PART FABRICATION-TEMPER ALTERATION AND DWG 44N5005 REV.

Part: TRANSMISSION — LOW (TE FLAPS) · airframe 74,315 hrs · 24,804 cycles

ON APPROACH WHEN WE SELECTED FLAPS 20 DEGREES WE RECEIVED A "TE FLAPS DISAGREE" MESSAGE. COMPLIED WITH QRH. VISUAL INSPECTION OF T/E FLAPS SHOWED NO MECHANICAL DAMAGE. RESTORED FLAP SYSTEM TO NORMAL AND OPERATED NORMALLY. FSEU #1 FAULT CODE 305, #2 FAULT CODE 327. ALL THREE SHOWED "FLAP ARM DISAGREE. LOWERED FLAPS AND FOUND TORQUE LIMITERS TRIPPED AT L/H OTBD FLAP OTBD LIMITER, BOTH TRIPPED AT R/H INB FLAP, AND R/H OTBD FLAP OTBD LIMITER. R/H OTBD FLAP INBD TRANSMISSION SIGHT GLASS CLOUDED OVER. SERVICED R/H OTBD FLAP, INBD TRANSMISSION, PER B757 AMM 12-13-06-03. FOUND INBD FLAP JACKSCREWS AND GIMBALS DRY, LUBED T/E FLAPS PER AMM 12-21-09-03. RESET TRIPPED TORQUE LIMITERS, TE FLAPS OPS CHECK NORMAL PER 27-51-00-05. NO TORQUE LIMITERS TRIPPED.

Part: CHARGER — INOPERATIVE (EMERGENCY LIGHTS) · airframe 72,901 hrs · 23,855 cycles

R1 EXTERIOR EMERGENCY SLIDE LIGHT WILL NOT TEST. RELAMPED BUT NO HELP.REF WDM 33-51-12, NO VOLTAGE AT LIGHT L30 ,HAS GOOD GROUND.REMOVED AND REPLACED POWER SUPPLY M730 REF MM 33-51-07-2.EMERGENCY LIGHT OPS CHECK NORMAL REF MM 33-51-00-5.A/C OK FOR SERVICE.

Part: BATTERY PACK — DISCHARGED (CABIN) · airframe 72,806 hrs · 23,792 cycles

L1 DOOR SLIDE LIGHT INOP. R&R EMERGENCY BATTERY PACK M731 PER MM 33-51-07-2, PN 2013-1A S/N 54663.

Part: LIGHT — INOPERATIVE (EXTERIOR) · airframe 72,801 hrs · 23,787 cycles

R1 DOOR EXTERIOR EMERGENCY EXIT LIGHT INOP. REMOVED AND REPLACED R1 DOOR EMERGENCY EXIT LIGHT BULB (P/N GE767) REF AMM 33-51-01. OPERATIONAL CHECKS GOOD.

Part: SEAL — LEAKING (SLIDING WINDOW) · airframe 72,706 hrs · 23,729 cycles

A WHINE STARTED AT APPROXIMATELY 6K FT MSL. IT GOT LOUDER AS WE CLIMBED TO 15K FT MSL. WE SLOWED FROM 285 KTS IAS TO 210 KTS IAS AT 15K FT MSL, THE WHINE DECREASED SOME BUT NOT AS MUCH AS DESCENDING. WHINE STOPPED AT 7K FT MSL. BOTH INTERNAL AND EXTERNAL COMMUNICATION WAS EXTREMELY DIFFICULT. REMOVED AND REPLACED RT SLIDING WINDOW SEAL PN S141N493-6. NO SERIAL NUMBER IAW AMM 56-11-53- 4. PERFORMED SATISFACTORY PRESSURIZATION CHECK IAW AMM 05-51-24-2. PRESSURIZED AIRCRAFT TO 7 PSID WITH NO LEAKS OR NOISE DETECTED AT THIS TIME.

Part: SKIN — CRACKED (TE FLAP) · airframe 72,706 hrs · 23,728 cycles

RT OTBD FLAP UNDERSIDE HAS SMALL CRACK ON THE INBD SIDE NEAR THE INBD FLAP TRACK FAIRING. REPAIRED RT OUTBD FLAP UNDERSIDE SMALL CRACK ON THE INBD SIDE NEAR THE INBD FLAP TRACK FAIRING IAW SRM 51-70-04-OG FIG 14 SHEET 2 AND EA WORK CARD TF-5750-T0342790 P1. RT OUTBOARD AFT FLAP LOWER SURFACE SKIN REPAIR.

Part: DECK PLATE — CORRODED (FUSELAGE) · corrosion level 2 · airframe 72,706 hrs · 23,728 cycles

CORROSION ON DECK PLATE STA 1682 RBL 25 REMOVED CORROSION ON DECK PLATE STA 1682, RBL 25 IAW SRM 51-10-02-OG, ORIG. MAT .071", REM MAT .053", MAT LOSS .018" FOUND OUT OF LIMITS IAW SRM 53-00-51-1A FIG 101 DETAIL III. FABRICATED AND INSTALLED REPAIR IAW SRM 53-60-51-2R, FIG 201, DETAIL I, REPAIR2, ALT 1.

Part: SEAT TRACK — CORRODED (FUSELAGE) · airframe 72,706 hrs · 23,728 cycles

FWD WET AREA, BS 358 RBL 14, SEAT TRACK HAS PITTING CORROSION. REMOVED CORROSION ON SEAT TRACK, STA 345 TO 377, RBL 14 IAW SRM 51-10-02-OG. EVALUATED DAMAGED SEAT TRACK, ORIG MAT=.080",REM MAT=.020", MAT LOSS=.060",L=3 LOSS=.060",L=3.0"XW=1.0", FOUND OUT LIMITS IAW SRM 53-00-52-1A, FIG 101, DETAIL VII. REMOVED, FABRICATED(TRIMMED)LOCATED, DRILLED & INSTALLED SEAT TRACK IAW VA DWG 3470, REV G & VA DCN 3504-NC-2, REV. APPLIED TREAT, PRIMER, TOP COAT AND CIC ON SEAT TRACK IAW SRM 51-20-01-OG & AMM 51-21-10-7.

Part: SEAT TRACK — CORRODED (FUSELAGE) · airframe 72,706 hrs · 23,728 cycles

COCKPIT FWD WET AREA STA 358 LBL 7 SEAT TRACK FLANGE CORRODED. REMOVED CORROSION ON SEAT TRACK, STA 345 TO 377, LBL 7 IAW SRM 51-10-02-OG. EVALUATED DAMAGED SEAT TRACK, ORIG MAT=.080", REM MAT=.030", MAT LOSS=.050",L=6.0"XW=1.0", FOUND OUT LIMITS IAW SRM 53-00-52-1A, FIG 101, DETAIL VII. REMOVED, FABRICATED(TRIMMED) LOCATED, DRILLED & INSTALLED SEAT TRACK IAW VA DWG 3470, REV G & VA DCN 3504-NC-2, REV. APPLIED TREAT, PRIMER, TOP COAT AND CIC ON SEAT TRACK IAW SRM 51-20-01-OG & AMM 51-21-10-7.

Part: DECK PLATE — CORRODED (FUSELAGE) · corrosion level 2 · airframe 72,706 hrs · 23,728 cycles

CORROSION ON DECK PLATE STA 1682 RBL 9 - RBL 16. REMOVED CORROSION IAW SRM 51-10-02-OG, ORIG MAT = .071" REM MAT =.053" & .056", MAT LOSS = .018" & .015", FOUND OUT OF LIMITS IAW SRM 53 OG, ORIG MAT = .071" REM MAT =.053" & .056", MAT LOSS = .018" & .015", FOUND OUT OF LIMITS IAW SRM 53-00-51-1A, FIG 101, DETAIL III. FABRICATED AND INSTALLED REPAIR IAW SRM 53-60-51-2R, FIG 201, DETAIL I, REP 2, ALT 1.

Part: DECK PLATE — CORRODED (FUSELAGE) · corrosion level 2 · airframe 72,706 hrs · 23,728 cycles

CORROSION ON DECK PLATE STA 1682 LBL 8 - LBL 13. REMOVED CORROSION IAW SRM 51-10-02-OG, ORIG MAT = .071" REM MAT OG, ORIG MAT = .071" REM MAT =.060", MAT LOSS = .011", FOUND OUT OF LIMITS IAW SRM 53-00-51-1A, FIG 101, DETAIL III. FABRICATED AND INSTALLED REPAIR IAW SRM 53-60-51-2R, FIG 201, DETAIL I, REP 2, ALT 1. 2R, FIG 201, DETAIL I, REP 2, ALT 1.

Part: DECK PLATE — CORRODED (FUSELAGE) · corrosion level 2 · airframe 72,706 hrs · 23,728 cycles

CORROSION ON DECK PLATE STA 1682 RBL 40 - RBL 46. REMOVED CORROSION DECK PLATE STA 1682, RBL 40 - RBL 46 IAW SRM 51-10-02-OG, ORIG MAT = .071" REM MAT =.049", MAT LOSS = .022" FOUND OUT OF LIMITS IAW SRM 53-00-51-1A, FIG 101, DETAIL III. FABRICATED AND INSTALLED REPAIR IAW SRM 53-60-51-2R, FIG 201, DETAIL I, REPAIR 2, ALT 1.

Part: DOOR FRAME — GOUGED (FUSELAGE) · airframe 72,706 hrs · 23,728 cycles

FWD E&E BAY DOOR FRAME AT BS 231.25 BL0 GOUGED. BLENDED GOUGE IAW SRM 51-10-02. AFTER FURTHER EVALUATION FOUND DAMAGE TO BE OUT OF LIMITS IAW SRM 53-00-07-1A FIGURE 101 DETAIL II. CUT OUT AND REMOVED DAMAGED AREA IAW SRM 53-00-07-2R REPAIR 7. FABRICATED AND INSTALLED REPAIR ANGLE, FILLER, AND SHIELD IAW SRM 53-00-07-2R REPAIR 7.

Part: COLLAR — BROKEN (L1 DOOR LOCK) · airframe 72,143 hrs · 23,332 cycles

CREW FOUND THE L1 DOOR LOCK BROKEN OFF. REMOVED AND REPLACED L1 DOOR LOCK COLLAR IAW AMM 52-11-08-8. LOCK OPS CHECKED GOOD IAW AMM 52-11-00.

Part: SEAL DEPRESSOR — GOUGED (CARGO DOOR) · airframe 71,205 hrs · 22,647 cycles

C1 DOOR AFT EDGE DAMAGED 2 PLACES. REMOVED AND REPLACED C1 DOOR LOWER SECTION DEPRESSOR IAW DWG 143N6603 REV B. PRESSURIZATION CHECK REQ PER AMM 05-51-24-2.

Part: SEAL DEPRESSOR — DAMAGED (CARGO DOOR) · airframe 71,205 hrs · 22,647 cycles

C2 DOOR EXT LWR EDGE HAS NUMEROUS AREAS OF DAMAGE. R&R C2 DOOR EXT LWR EDGE, SEAL DEPRESSOR IAW SRM 51-40-02 & DWG 146N6603 REV A. ACCOMPLISHED PRESSURIZATION CHECK IAW AMM 05-51-24-2.

Part: ANGLE — CORRODED (CARGO DOOR) · airframe 71,205 hrs · 22,647 cycles

C1 DOOR CENTER ANGLE LOWER BEAM BS 588.93 HAS CORROSION. REMOVED AND REPLACED C1 DOOR CENTER ANGLE LOWER BEAM BS 588.93 IAW DWG 143N6603 REV AT AND REV E.

Part: BEAM — GOUGED (FUSELAGE) · airframe 71,205 hrs · 22,647 cycles

MAIN CABIN STUB FRAME AT STA 600 LOWER AFT FLANGE HAS 2 OPEN EXISTING HOLES WITH SHORT PITCH AND RADIUS LOCATION AND 2 EXISTING FASTENER HOLES WITH LIGHT GOUGES IN RADIUS APPROX LBL 51. R&R MAIN CABIN STUB BEAM, FRAME STA 600 LT IAW DWG 657N4311 REV -. MAJOR REPAIR.

Part: FITTING — CRACKED (FUSELAGE) · airframe 71,205 hrs · 22,647 cycles

MCD CUT OUT LOWER SILL ATTACH STUB FRAME AT STA 580 LT HAS A CRACK IN THE UPPER AFT RADIUS. REMOVED AND REPLACED MAIN CABIN STUB BEAM, FRAME STA 580 LT IAW DWG 657N4311 REV - . MAJOR REPAIR.

Part: DOOR FRAME — CRACKED (R2 DOOR) · airframe 71,205 hrs · 22,647 cycles

R2 DOOR FWD FRAME UPPER HINGE CUTOUT CRACKED. REPAIRED IAW EA F-5210-TO328868 P1. MAJOR REPAIR.

Part: SKIN — CRACKED (FUSELAGE) · airframe 71,020 hrs · 22,520 cycles

FOUND FUSELAGE SKIN BULGED AT INBD AFT CORNER OF LAV SERVICE DOOR FRAME WITH SKIN CRACKS. COMPLIED WITH EA F-5330-TO326081, PARTS 1 AND 2 THIS A MAJOR REPAIR.

Part: LIGHT — NOT SEATED (COCKPIT) · airframe 70,671 hrs · 22,301 cycles

COCKPIT EMER LIGHT INOPERATIVE. RESEATED BULB & OPERATIONS CHECKED NORMAL IAW MM 33-51-09-3. ACFT OK FOR SERVICE.

Part: MECHANISM — OBSTRUCTED (R1 DOOR) · airframe 704 hrs · 22,151 cycles

R1 DOOR FAILED TO ARM PRIOR TO DEPARTURE. FOUND DEBRIS IN FLOOR AREA WHERE GIRT BAR ARMS DOOR. REMOVED DEBRIS & CHECKED ARM & DISARM MECHANISM IAW AMM 25-66-10-2, OK FOR SERVICE AT THIS TIME.

Part: ARM — OBSTRUCTED (R1 DOOR) · airframe 701 hrs · 21,962 cycles

R1 DOOR WILL NOT OPEN COMPLETELY. FOUND DEBRIS ON UPPER HINGE FLAPPER HINGE ARM ABOVE COCKING BELL CRANK. CLEANED, DOOR OPENS & CLOSES NORMAL INSIDE & OUTSIDE DOOR HANDLES. DOOR CHECKS NORMAL IAW AMM 52-11-01-6.

Part: HINGE — DIRTY (R1 DOOR) · airframe 701 hrs · 21,956 cycles

R1 DOOR WILL NOT OPEN COMPLETELY. FOUND DEBRIS ON UPPER HINGE FLAPPER HINGE ARM ABOVE COCKING BELLCRANK. CLEANED, DOOR OPENS AND CLOSES NORMALLY INSIDE AND OUTSIDE DOOR HANDLES. DOOR CHECKED NORMAL. IAW AMM 52-11-01-6

Part: SCREW — CORRODED (ZONE 800) · airframe 701 hrs · 21,927 cycles

DURING R & R OF THE RT ESCAPE SLIDE FOUND ONE OF 2 SCREWS ON THE BAR CENTERING PLATE CORRODED & UNUSABLE. INSTALLED NEW SCREW AS REQUIRED IAW AMM 20-11-00-2 TORQUE VALUE. ACFT OK FOR CONTINUED SERVICE.

Part: COLLAR — BROKEN (ENTRY DOOR) · airframe 699 hrs · 21,798 cycles

RIGHT LT CREW ENTRY DOOR HAS HOLD OPEN LOCK COLLAR BROKEN. R & R BROKEN HOLD OPEN LOCK COLLAR IAW AMM 52-11-08-8.

Part: SLIDE — FAILED (L1 DOOR) · airframe 69,817 hrs · 21,716 cycles

AIRCRAFT SLIDE FELL OUT OF DOOR WHEN OPENED BY RAMP AGENT. FOUND DOOR ARMED & DOOR EMER ASSIST BOTTLE EMPTY & BLOWN. R & R L1 DOOR SLIDE & DOOR POWER RESERVOIR.

Part: SKIN — GOUGED (BS 609) · airframe 69,702 hrs · 21,629 cycles

LOWER FUSELAGE SKIN HAS A GOUGE AT BS 609 BETWEEN STRINGERS 26 & 27L. REPAIRED IAW EA F-5330-T0312668 PT 1.

Part: SKIN — DENTED (BS 521) · airframe 69,702 hrs · 21,629 cycles

LOWER FUSELAGE SKIN DENTED AT BS 521 JUST BELOW STRINGER 26L. REPAIRED IAW EA F-5330-T0312662 PT 1.

Part: SLIDING WINDOW — DAMAGED (COCKPIT) · airframe 69,686 hrs · 21,613 cycles

ON POST FLIGHT INSPECTION NOTED FIRST OFFICER`S NR 2 SLIDING WINDOW HAS NUMEROUS BUBBLES IN BETWEEN PANES. R & R NR 2 OPEN ABLE WINDOW FIRST OFFICER`S IAW AMM 56-11-02-4, OK TO CONTINUE.

Part: ROLLER — WORN (L1 DOOR) · airframe 68,851 hrs · 20,977 cycles

L1 DOOR WILL NOT CLOSE CORRECTLY. L1 DOOR APPEARS TO BE OUT OF RIG. WHEN LWR ROLLERS ENGAGE DOORFRAME TRACKS BOTH UPPER ROLLERS WILL NOT ENGAGE THE RACEWAYS IN THE TRACKS. THE UPPER ROLLERS ARE GRINDING AND GOUGING THE CASTINGS TO THE POINT WHERE THE DOOR WILL NOT CLOSE WITHOUT SUBSTANTIAL EFFORT TO OVERCOME THIS BINDING CONDITION. REPLACED COCKING ROLLER AND CONTROL CAM, CHECKED DOOR OPERATION IAW AMM 52-11-13-2 AND 52-11-00-5. CHECKED GOOD.

Part: BOTTLE — LOW PRESSURE (PAX DOOR) · airframe 68,779 hrs · 20,931 cycles

ON PREFLIGHT, FOUND MAIN ENTRY DOOR SLIDE BOTTLE PRESSURE IN THE RED.

Part: SENSOR — OUT OF ADJUST (L1 DOOR) · airframe 68,463 hrs · 20,702 cycles

LEFT FWD ENTRY DOOR EICAS ALERT AFTER LANDING. DOOR APPEARED CLOSED TO GROUND PERSONNEL. FOUND L-1 DOOR DOOR WARNING SENSOR TO BE OUT OF ADJ IAW AMM 52-71-00-5. ADJ L-1 DOOR WARNING SENSOR IAW AMM 52-71-00-5. CYCLED L1 DOOR NUMEROUS TIMES WITH NO FAULTS NOTED. ACFT OK FOR SERVICE.

Part: BOLT — LOOSE (L1 DOOR) · airframe 68,448 hrs · 20,690 cycles

L1 DOOR VERY DIFFICULT TO CLOSE FROM INSIDE OF ACFT. TROUBLESHOT USING FIM 52-11, FAULT TREE 807, FOUND GUIDE ARM ATTACHING BOLTS LOOSE ON DOOR SIDE. TIGHTENED BOLTS AND CHECKED ADJUSTMENT. OPS CHECKED GOOD.

Part: SKIN — PUNCTURED (RT ELEVATOR) · airframe 68,411 hrs · 20,650 cycles

RT ELEVATOR UPPER SKIN HAS A PUNCTURE 4 INCHES FROM T/E 21 INCHES FROM INBD END. REPAIRED IAW SRM-51-70-17-4B, FIG 24.

Part: FRAME — DAMAGED (BS 680) · airframe 68,411 hrs · 20,650 cycles

FRAME HAS SHORT EDGE MARGIN CONDITION AT STA 680 , S-4L AND S-4R. COMPLIED WITH EA F-5310-162557.

Part: STRUCTURE — DAMAGED (ZONE 500) · airframe 68,411 hrs · 20,650 cycles

LT WING OTBD FLAP ACCESS PANEL 566AL CUT OUT HAS ELONGATED/DOUBLE DRILLED HOLES LOC NR 2 FROM INBD LOWER CORNER AT LT WING OTBD FLAP ACCESS PANEL 566AL CUTOUT A REPAIR WAS ACCOMPLISHED ON MAE NR 47749920001 AND MAE EA 757-5754-16-F3851. REV - DATED AUG 21, 2012, FAA FORM 8100-9, DATED 8/20/2012, REF EA F-5750-162449, DATED 10/10/12. THIS NON ROUTINE IS FOR TIME TRACKING PURPOSES ONLY. MAJOR REPAIR.

Part: STRAP — CORRODED (ZONE 100) · corrosion level 2 · airframe 68,411 hrs · 20,650 cycles

AFT CARGO BS 1440-1460 S-27R OUTER CHORD INNER SURFACE HAS CORROSION. ACCOMPLISHED EA F-5310-162531,

Part: FITTING — GOUGED (ZONE 200) · airframe 68,411 hrs · 20,650 cycles

RIGHT AFT BODY FAIRING FITTING AT BS 1180 IS GOUGED, WORK ACCOMPLISHED ON EAF-5340-162415 PART 1 A, B, AND C. MAJOR REPAIR.

Part: SKIN — DAMAGED (BS 1300 S18R) · airframe 68,411 hrs · 20,650 cycles

TWO ELONGATED HOLES IN FUSELAGE SKIN RT AFT BODY FAIRING CONTACT AREA BS 1300 BELOW S18R. ACCOMPLISHED EA F-5330-162410. MAJOR REPAIR.

Part: SKIN — DENTED (BS 620 S20R) · airframe 68,411 hrs · 20,650 cycles

SKIN DENTED AT BS 620 AT S-20 R. COMPLIED WITH EA F-5330-159947. MAJOR REPAIR.

Part: SKIN — DENTED (BS 1530) · airframe 68,411 hrs · 20,650 cycles

DENT AT BS 1530 BETWEEN S4 - 5R, ACCOMPLISHED EA F-5330-160599. MAJOR REPAIR.

Part: FASTENER — MISSING (DOOR FRAME) · airframe 68,411 hrs · 20,650 cycles

BS 1380 BETWEEN S24 AND 26R, DOOR FRAME MISSING RIVETS, RIVET DRILL IN EDGE OF FRAME UNDER INSIDE OF FRAME ACCOMPLISHED EA F-5310-160589, FUSELAGE-MAIN FRAME-SECT 46-C2 DOOR SURROUND CHORD-DAMAGED HOLES STA 1380 AT S-25R. MAJOR REPAIR.

Part: FRAME — DAMAGED (BS 1640) · airframe 68,411 hrs · 20,650 cycles

BS 1640, FRAME BETWEEN STRINGERS S25 AND 27R HAS DAMAGE ON TOP OF FRAME. REPAIR ACCOMPLISHED IAW EA 757-5362-16-F3886, REV. CLASSIFIED MAJOR REPAIR.

Part: SPAR — CORRODED (RT WING) · corrosion level 2 · airframe 68,411 hrs · 20,650 cycles

CORROSION FOUND AT RT AFT WING SPAR WEB SURFACE AT AFT FUEL BOOST PUMP OPENING LOWER BONDING JUMPER ATTACH POINT (MARKED) WINGS-MAIN FRAME -OUTER TANK-REAR SPAR CORRSION IRSS 183.0 RT SIDE (AFT BOOST PUMP) WORK ACCOMPLISHED ON EA F-5710-162542. MAJOR REPAIR.

Part: SKIN — CORRODED (BS 750-780) · airframe 68,411 hrs · 20,650 cycles

SKIN AT BS 750-780 S- 24L -BL 0 PERIMETER OF PANEL 191 AL MULTIPLE SCRATCHES AND CORRODED. REPAIRED IAW EA F-5330-162547. MAJOR REPAIR.

Part: SKIN — CRACKED (R1 DOOR) · airframe 68,411 hrs · 20,650 cycles

R1 DOOR INTERNAL SKIN LIGHTNING HOLE CUT-OUT IS CRACKED JUST FWD MID AREA BEHIND TORQUE TUBE. COMPLIED WITH EA F-5210-162411. MAJOR REPAIR

Part: CREASE BEAM — CRACKED (BS 1641) · airframe 68,411 hrs · 20,650 cycles

OTBD CREASE BEAM AT BS 1641 CRACKED. REPAIRED IAW EA F-5310-162550. MAJOR REPAIR.

Part: STRUCTURE — CORRODED (LAV SERVICE) · corrosion level 2 · airframe 68,411 hrs · 20,650 cycles

AFT FUSELAGE LAV SERVICE PANEL. HOUSING (BOX) HAS CORROSION BET BS 1681- 1701. REMOVED CORRODED ON DOUBLER AND TWO CLIPS PER SRM-51-10-02, REMOVED .040 ON DOUBLER AND TWO CLIPS MAT AD 0.50 AREA ON DOUBLER IS 5" X 4" AND CLIPS 1" X 1" FOUND TO BE OUT OF LIMITS, PER. SRM-53-00-53 FIG 101 DETAIL V, R & R DOUBLER AND 2EA. CLIPS IAW-SRM-51-40-02. CAT "A"MAJOR REPAIR.

Part: SKIN — DENTED (ZONE 200) · airframe 68,411 hrs · 20,650 cycles

DENT AT BS 418, BETWEEN S-15L TO S-16L, FOUND OUT OF LIMITS IAW-SRM-53-00-01, FIG 101, DET III. REPAIRED DENT IAW-SRM-53-00-01, FIG 201, R16, PG 201, MAJOR REPAIR. INSTALLED REPAIR DOUBLER IAW SRM-51-40-02.

Part: SKIN — DENTED (ZONE 200) · airframe 68,411 hrs · 20,650 cycles

DENT IN FUSELAGE STA 400, STR 5L EVAL DENT, DENT MEASURE 7' X 3.0 X .007 DEPTH, A/Y=100 DENT IS LESS THAN 0.5 FROM STRINGER FASTENERS, OUT OF LIMITS IAW SRM-53-00-01, FIG 101, DETAIL III, REPAIR DENT STA 400, STR 5L IAW SRM-53-00-01, FIG 201 REPAIR 16. INSTALLED REPAIR DOUBLER AT STA 405-410 BETWEEN S-5L-S-6L IAW SRM-53-00-01, FIG 201. REPAIR NR 16 CAT "B" MAJOR REPAIR.

Part: SKIN — DENTED (BS 1400-1420) · airframe 68,411 hrs · 20,650 cycles

EXTERNAL FUSELAGE SKIN STA 1400-1420 BETWEEN S-25L TO S-26L DENTED. FOUND OUT OF LIMITS IAW SRM-53-00-01, FIG 101, DET III, REPAIRED DAMAGE IAW SRM-53-00-01, FIG 201 REPAIR NR 16, PG 201-206. CATEGORY"B", MAJOR REPAIR.

Part: SKIN — DENTED (BS 278-288) · airframe 68,411 hrs · 20,650 cycles

RT FUSELAGE SKIN DENTED BETWEEN BS 278 TO 288, S16-17R. FOUND TO BE OUT OF LIMITS IAW SRM 53-00-01, FIG 101, DETAIL III. REPAIR DENT IAW SRM 53-00-01, FIG 201. REPAIR 7, CATEGORY B REPAIR.

Part: STRUCTURE — BENT (PAX DOOR) · airframe 68,411 hrs · 20,650 cycles

R4 DOOR LWR FWD EDGE BENT 6" ALONG EDGE. FOUND OUT OF LIMITS IAW SRM 52-10-01 FIG 101 DETAIL VIII. REPAIRED BEND IN FWD L..E. OF R4 DOOR IAW SRM 52-10-01 FIG 201 REPAIR 7 THIS IS A MAJOR CLASS "B" REPAIR.

Part: SKIN — BENT (PAX DOOR) · airframe 68,411 hrs · 20,650 cycles

L4 DOOR LOWER FWD L/E OF DOOR SKIN BENT. FOUND OUT OF LIMITS IAW SRM 52-10-01 FIG 101 DETAIL VI. REPAIRED L4 DOOR LWR L.E. IAW SRM 52-10-01 FIG 210 REPAIR 7 CAT "B" MAJOR REPAIR

Part: SKIN — CORRODED (BS 1500-1520) · airframe 68,411 hrs · 20,650 cycles

CABIN SKIN HAS CORROSION AROUND DOME NUTS BS 1500-1520 S-1L TO S-2L DUE TO INCORRECT REPAIR DOUBLER INSTALLED. REPAIRED IAW EA757-5361-16-F3887. MAJOR REPAIR.

Part: SKIN — CRACKED (R1 DOOR) · airframe 68,411 hrs · 20,650 cycles

DOOR R1 INTERNAL SKIN LIGHTNING HOLE CUT OUT IS CRACKED AT AFT LOWER AREA. COMPLIED WITH EA F-5210-162548. MAJOR REPAIR.

Part: WEB — CORRODED (BS 940-960) · corrosion level 2 · airframe 68,411 hrs · 20,650 cycles

ON REMOVAL OF WEB SECTION FROM BS 940-960, FOUND CORRODED ON BOTH ENDS AND PREVIOUSLY REWORKED. REMOVED CORROSION IAW SRM 53-40-13 FIG 101, FOUND OUT OF LIMITS IAW SRM 53-40-13 FIG 101 DETAIL III SECTION A-A. REMOVED WEB IAW SRM 51-40-02. LOCATED, DRILLED NEW WEB IAW DWG 144N5140 AND INSTALLED IAW SRM SRM 51-40-02 AND DWG 144N5140. MAJOR REPAIR

Part: FRAME — DAMAGED (BS 1661 S18R) · airframe 68,411 hrs · 20,650 cycles

BS 1661 FRAME S-18R HAS AN ELONGATED FASTENER HOLE COMMON TO THE FRAME FAIL SAFE CHORD AND STRINGER CLIP. COMPLIED WITH F-5310-162418 FUSELAGE- ELONGATED HOLE IN FRAME AND FAILSAFE CHORD AT BS 1661 AND S-18R. DUE TO THE DISCREPANCY EFFECTING THE PTF MOD A REPAIR WAS ACCOMPLISHED ON STAM EA 757-5362-16-F3816 AND STAM NR 47748980001, STA 1661 S-18R. THIS N/R IS FOR TIME TRACKING PURPOSES ONLY. MAJOR REPAIR.

Part: SKIN — DENTED (BS 1640-1660) · airframe 68,411 hrs · 20,650 cycles

DENT IN FUSELAGE BETWEEN STA 1640 TO 1660 BETWEEN S26 - 27R. DENT FOUND TO BE OUT OF LIMITS IAW SRM 53-00-01, FIG 101, DETAIL III. FABRICATED REPAIR DOUBLER IAW SRM 53-00-01, FIG 201, REPAIR 7. INSTALLED REPAIR DOUBLER IN SRM 53-00-01, FIG 201, REPAIR 7 AND SRM 51-40-02. MAJOR REPAIR.

Part: BEARING — CRACKED (L4 DOOR) · airframe 68,411 hrs · 20,650 cycles

L4 DOOR INNER SKIN LIGHTING HOLE EDGE, AT HINGE SHAFT UPPER BEARING CRACKED. COMPLIED WITH EA F-5210-162409. MAJOR REPAIR.

Part: BEAM — CORRODED (BS 345) · corrosion level 2 · airframe 68,411 hrs · 20,650 cycles

NOSE LANDING GEAR BOX BS 345 UPPER SURFACE BEAM FWD SIDE AT FASTENER ROW HAS CORROSION, DOT 122-011 COMPLIED WITH EA F-3510-162401, REF 8100-9. FUSELAGE NLG WHEEL WELL UPPER PANEL BEAM CORROSION AT BS 345 NEAR LBL19 CAT"A" MAJOR REPAIR. MAJOR REPAIR.

Part: SEAT TRACK — DAMAGED (ZONE 200) · airframe 68,411 hrs · 20,650 cycles

RT SEAT TRACK SIDE SKIN FASTENER HOLE DOUBLE DRILLED AT BS 1026, RBL 45. COMPLIED WITH EA F-5310-160598. WORK ACCOMPLISHED ON EA 757-5345-16-F3835, REPAIR IS A CAT "A" MAJOR REPAIR.

Part: FRAME — DENTED (BS 1320) · airframe 68,411 hrs · 20,650 cycles

BS 1320 BETWEEN S26-27L, FRAME DENTED. FOUND OUT OF LIMITS IAW SRM 53-00-07 FIG.101, REMOVED AND REPLACED FRAME IAW SRM 51-40-02 AND DWG 146N1006, CAT."A" MAJOR REPAIR.

Part: DECK PLATE — CORRODED (ZONE 200) · corrosion level 2 · airframe 68,411 hrs · 20,650 cycles

AFT DECK PLATE UPPER SURFACE AT BS 1681.8 TO 1720 FROM LBL 58 TO RBL 58 HAS SEVERAL AREAS WITH NICKS, SCRATCHES, AND CORRSION FOUND AFT GALLEY UPPER DECK PLATE OUT OF LIMITS IAW SRM 53-00-51 FIG 101 DETAIL II AND III. REMOVED DECK PLATE IAW SRM 51-40-02. . INSTALLED NEW DECK PLATE IAW DWG 146N5300 SH 1 REV E AND SRM 51-40-02. ORIGINAL MATERIAL .071 AFTER .012 FINAL MATERIAL REMOVED .059. MAJOR REPAIR

Part: SPAR — CORRODED (LT WING) · airframe 68,411 hrs · 20,650 cycles

CORROSION FOUND AT LT AFT WING SPAR WEB SURFACE AT AFT FUEL BOOST PUMP OPENING, LOWER BONDING JUMPER ATTACH POINT. ACCOMPLISHED ON EA F-5710-162420, STEPS 1-5. MAJOR REPAIR

Part: SKIN — DAMAGED (BS 610) · airframe 68,411 hrs · 20,650 cycles

FOUND DAMAGE ON FWD CARGO DOOR CUTOUT LOWER EXTERIOR SKIN AT FS 610 UNDER SCUFF PLATE AREA. ACCOMPLISHED EA F-5330-160592. MAJOR REPAIR.

Part: SPAR — CORRODED (LT WING) · airframe 68,411 hrs · 20,650 cycles

CORROSION FOUND AT LT AFT WING SPAR WEB SUFACE AT AFT FUEL BOOST PUMP OPENING UPPER BONDING JUMPER ATTACH POINT.

Part: STRAP — CORRODED (BS 1825 S3-6R) · corrosion level 2 · airframe 68,411 hrs · 20,650 cycles

FUSELAGE BS 1825 S3-6R INNER STRAP CORRODED. REMOVED CORROSION IAW SRM 51-40-02. CHECKED LIMITS , ORIGINAL MAT .100 MATERIAL LOSS .050, OUT OF LIMITS IAW SRM 53-80-13 ALLOWABLE DAMAGE 1, FIG 904, DETAIL IV. R & R STRAP IAW SRM 51-40-02 AND DWG 148N3138, CAT "A" MAJOR REPAIR.

Part: FRAME — CORRODED (BS 1460) · corrosion level 2 · airframe 68,411 hrs · 20,650 cycles

BS 1460, STR 27R CORROSION ON FRAME REMOVED CORROSION IAW SRM 51-10-02. BLENDED AREA ORIGINAL MATERIAL .063 MATERIAL REMAINING .040 D=.023. FOUND TO BE OUT OF LIMITS IAW SRM 53-00-07, FIG 101, ALLOWABLE DAMAGE 2. R & R FRAME STA 1460, S-25R TO S-25L IAW SRM 51-40-02 AND DWG 146N1014. MAJOR REPAIR.

Part: FIREWALL — CHAFED (APU BAY) · airframe 68,411 hrs · 20,650 cycles

APU FIREWALL AFT SIDE RBL 7, 7" UP FROM LOWER FUSELAGE CHAFED REMOVED DAMAGE IAW SRM 51-10-02. REMOVED CHAFE IAW SRM 53-80-08, FOUND TO BE OUT OF LIMITS IAW SRM 53-80-08, FIG 101, DETAIL IV. REPAIRED AREA IAW SRM 53-80-08, REPAIR 2.

Part: STRINGER — CORRODED (ZONE 200) · corrosion level 2 · airframe 68,411 hrs · 20,650 cycles

S-17L BS 752-900 CORRODED. REMOVED CORRODED STRINGER FROM STA 752-900 LBL 64 IAW SRM 51-40-02. FOUND TO BE OUT OF ALLOWABLE LIMITS IAW SRM 53-00-51, FIG 101. FABRICATED NEW STRINGER IAW 143N5520 AND INSTALLED IAW SRM 51-40-02 DWG 143N5520 SH 4, REV E. MAJOR REPAIR.

Part: SKIN — DENTED (BS 694) · airframe 68,411 hrs · 20,650 cycles

DENT AT STA 694, BETWEEN S-26L TO S-27L EVALUATED DENT A=1.34 Y= .047 A/Y 28.5, DAMAGED AREA FOUND TO BE OUT OF LIMITS IAW SRM 53-00-01, FIG 101, DETAIL III. REPAIRED AREA AT STA 694 BETWEEN S-26L TO S-27L IAW SRM 53-00-01, REPAIR 16. THIS REPAIR IS CATEGORY "B", MAJOR REPAIR.

Part: SKIN — DAMAGED (BS 750-780) · airframe 68,411 hrs · 20,650 cycles

LT FWD FUSELAGE SKIN BS 750- 780, S24L PERIMETER OF PANEL 191AL MULTIPLE SCRATCHES AND CORRODED.

Part: FLOOR SKIN — CORRODED (COCKPIT) · airframe 68,411 hrs · 20,650 cycles

COCKPIT FLOOR SKIN HAS CORROSION SPOTS STA 288, LBL12-RBL12.

Part: SEAT TRACK — CORRODED (COCKPIT) · airframe 68,411 hrs · 20,650 cycles

AFTER REMOVAL OF PILOTS SEAT TRACKS FOUND NUMEROUS AREAS OF CORROSION.

Part: FLOOR SKIN — CORRODED (BS 297) · airframe 68,411 hrs · 20,650 cycles

COCKPIT FLOOR SKIN SPLICE HAS CORROSION BS 297, LBL 34.

Part: FLOOR SKIN — CORRODED (COCKPIT) · airframe 68,411 hrs · 20,650 cycles

AFTER REMOVAL OF COPILOTS SEAT TRACKS FOUND NUMEROUS SPOTS OF CORROSION ON FLOOR SKIN. R & R NEW FLOOR SKIN IAW SRM 51-40-02 & DWG 141N5810.

Part: FLOOR SKIN — GOUGED (COCKIT) · airframe 68,411 hrs · 20,650 cycles

COCKPIT FLOOR SKIN HAS GOUGES BS 278, LBL 34.

Part: FLOOR SKIN — GOUGED (COCKPIT) · airframe 68,411 hrs · 20,650 cycles

COCKPIT FLOOR SKIN HAS GOUGES, BS 299, LBL5. REMOVED DAMAGE AND CHECKED LIMITS ORIGINAL MATERIAL .050 AFTER REWORK .020 L=1.5 W=1.5 D=.030 FOUND TO BE OUT OF LIMITS. REMOVED DAMAGED FLOOR SKIN IAW SRM 51-40-02. INSTALLED NEW FLOOR SKIN IAW SRM 51-40-02 AND DWG 141N5810. CAT "A" MAJOR REPAIR.

Part: FLOOR SKIN — CORRODED (COCKPIT) · airframe 68,411 hrs · 20,650 cycles

COCKPIT FLOOR SKIN FWD OF CAPTS YOKE HAS CORROSION.

Part: FLOOR SKIN — CORRODED (COCKPIT) · airframe 68,411 hrs · 20,650 cycles

COCKPIT FLOOR SKIN SPLICE HAS CORROSION BS 297, LBL16.

Part: FLOOR SKIN — CORRODED (COCKPIT) · airframe 68,411 hrs · 20,650 cycles

COCKPIT FLOOR FWD OF F/O YOKE FLOOR SKIN HAS CORROSION.

Part: FRAME — DAMAGED (BS 395) · airframe 68,411 hrs · 20,650 cycles

AT BS 395 RBL2 UPPER FRAME HAS DOUBLE DRILLED HOLES. REPAIRED.

Part: FLOOR SKIN — CORRODED (BS 278) · airframe 68,411 hrs · 20,650 cycles

COCKPIT FLOOR SKIN HAS CORROSION SPOTS STA 278, LBL19-RBL19.

Part: SKIN — DENTED (ZONE 100) · airframe 68,411 hrs · 20,650 cycles

INCOMING DENT AT BS 1390, BETWEEN S-22L TO S-23L. (D-48) EVALUATED DENT-A=1.30, Y=.030, A/Y=43.33. DENT IS LESS THAN 0.50" FROM FRAME FASTENER, AREA FOUND TO BE OUT OF LIMITS IAW SRM 53-00-01, FIG 101, DETAIL III. REPAIRED AREA AT STA 1390 BETWEEN S-22L TO S-23L, IAW SRM 53-00-01, REPAIR 3. THIS REPAIR IS CATEGORY ''B''. MAJOR REPAIR.

Part: PLATE — CORRODED (BS 247-278) · corrosion level 2 · airframe 68,411 hrs · 20,650 cycles

FLIGHT DECK FLOOR STRUCTURE PLATE STA 247-278, RBL 20-27 HAS CORROSION. REMOVED CORROSION IAW SRM-51-10-02 CHECKED LIMITS ORIG. MAT. .050 AFTER REWORK .043 L=16" W=4" D=.007 FOUND TO BE OUT OF LIMITS NO ALLOWABLE LIMITS. REMOVED AND REPLACED FLIGHT DECK FLOOR STRUCTURE PLATE IAW-SRM-51-40-02 AND DWG 141N5810. CAT."A" MAJOR REPAIR.

Part: FLOOR SKIN — CORRODED (COCKPIT) · corrosion level 2 · airframe 68,411 hrs · 20,650 cycles

FLIGHT DECK FLOOR STRUCTURE PLATE BS 247-278, LBL 20-27 HAS CORROSION. REMOVED CORROSION IAW SRM-51-10-02, CHECKED LIMITS ORIG. MAT. .050 AFTER REWORK .042 L=15" W=25" D=.008". FOUND TO BE OUT OF LIMITS. REMOVED AND REPLACED FLIGHT DECK FLOOR STRUCTURE PLATE IAW SRM-51-40-02 AND DWG 141N5810. CAT"A"MAJOR REPAIR.

Part: SKIN — FAILED (BS 420-430) · airframe 68,411 hrs · 20,650 cycles

SKIN AT BS 420-430 BETWEEN S-21R- S-23R MISREPAIRED. REPAIRED IAW-SRM-53-00-01 REPAIR 15, FIG 201, REPAIR IS A CAT "B" MAJOR REPAIR.

Part: PLATE — CORRODED (FUSELAGE) · airframe 68,411 hrs · 20,650 cycles

FLIGHT DECK FLOOR STRUCTURE PLATE AFT SIDE OF YOKE HAS CORROSION ON F/O'S SIDE.

Part: PLATE — CORRODED (FUSELAGE) · airframe 68,411 hrs · 20,650 cycles

FLIGHT DECK FLOOR STRUCTURE PLATE AFT SIDE OF YOKE HAS CORROSION ON CAPT SIDE.

Part: CREASE BEAM — CORRODED (BS 680) · airframe 68,411 hrs · 20,650 cycles

MAIN DECK CREASE BEAM HAS CORROSION AT FS 680, RT SIDE. CORROSION BLENDED AREA ON I/B CHORD IAW SRM 51-10-02 ORIGINAL MATERIAL .100 AFTER REWORK .030 MATERIAL LOSS .070. CHORD IS OUT OF ALLOWABLE LIMITS IAW SRM 53-00-51 FIG 101. REMOVED CREASE BEAM SECTION FROM BS 670-755 IAW SRM 51-40-02. LOCATED AND DRILLED NEW CREASE BEAM SECTION IAW SRM 51-40-05, DWG 143N8322 SH 1 REV K. INSTALLED NEW CREASE BEAM SECTION IAW SRM 51-40-02 AND DWG 143N8322. MAJOR REPAIR.

Part: SKIN — DAMAGED (FUSELAGE) · airframe 68,411 hrs · 20,650 cycles

AFT CARGO DOOR CUTOUT LOWER EDGE AFT END HAS 2 EA STOP DRILLS IN SKIN AT LIP. ACCOMPLISHED EA F-5330-160572. MAJOR REPAIR.

Part: SKIN — DENTED (BS 1627 S26R) · airframe 68,411 hrs · 20,650 cycles

FUSELAGE EXTERNAL SKIN, STA 1627 S26R, DENTED. DENT FOUND OUT OF LIMITS IAW SRM 53-00-01, FIG 101, DETAIL III. ACCOMPLISHED EA F-5330-159950. MAJOR REPAIR.

Part: FRAME SPLICE — CORRODED (ZONE 100) · corrosion level 2 · airframe 68,411 hrs · 20,650 cycles

BS 1560, FRAME SPLICE CORRODED BETWEEN STR 24R AND 25R. REMOVED CORROSION AT FRAME SPLICE STA 1560 AT STR. 24 & 25R IAW-SRM-51-10-02. BLENDED AREA ORIG MAT .071, MAT REMAINING .034, NO ALLOWED DAMAGE ON SRM. R & R SPLICE IAW-SRM-51-40-02, FABRICATED SPLICE PLATE ON STAM TRAV T12/937656 AND DWG 146N042, CAT "A" MAJOR REPAIR.

Part: WEB — CORRODED (ZONE 200) · corrosion level 2 · airframe 68,411 hrs · 20,650 cycles

STRINGER 17 RT, BS 365-377, WEB LWR SURFACE CORRODED. REMOVED CORROSION IAW SRM 51-10-02. ORIG MAT .040 AFTER REWORK .032 TOTAL MAT LOSS .008 AREA OUT OF LIMIT IAW SRM 53-00-51, FIG 101, DETAIL III. FABRICATED NEW WEB FROM MAT 7075-T6, .040C BATCH NR 1948057 IAW DWG 141N8322. INSTALLED NEW WEB IAW SRM 51-40-02, DWG 14N8322. AREA OF DAMAGE L=2", W= 1". D= .008". MAJOR REPAIR.

Part: FRAME — DAMAGED (BS 377) · airframe 68,411 hrs · 20,650 cycles

FRAME AT STA 377 RBL 2 HAS DOUBLE DRILLED HOLES. HOLES REMOVED DAMAGED FRAME IAW-SRM-51-40-02, INSTALLED NEW FRAME IAW-SRM-51-40-02 AND DWG.141N1320, CATAGORY "A" MAJOR REPAIR.

Part: SUPPORT — CORRODED (LWS 165-204) · airframe 68,411 hrs · 20,650 cycles

LEFT WING AT WS 165-204 UPPER T/E SKIN & PANEL SUPPORT CORRODED. REPAIRED IAW EA F-5710-159945 STEPS 1-12. MAJOR REPAIR.

Part: FRAME — DENTED (BS 1280) · airframe 68,411 hrs · 20,650 cycles

FRAME DENTED AT BS 1280, STR 26L AFT CARGO BAY. R & R FRAME IAW SRM 51-40-02 AND DWG 146N1028, BS 1280 BETWEEN S-25L TO S-25R. MAJOR REPAIR.

Part: SKIN — DAMAGED (BS 1640-1681) · airframe 68,411 hrs · 20,650 cycles

HIDDEN DAMAGE FOUND AFTER REMOVAL OF R4 DOOR THRESHOLD. EXTERNAL FUSELAGE SKIN AT BS 1640-1681 S17-18R HAS MISDRILLED SCREW HOLES. ACCOMPLISED EA F-5330-162561. REPAIRED IAW EA 757 -5361-16 -F3836. MAJOR REPAIR

Part: STRINGER — CORRODED (BS 750) · airframe 68,411 hrs · 20,650 cycles

FWD PIT STRINGER 22L IS CORRODED AT DOME NUT AT FS 750. CHECKED LIMITS 100 PERCENT EXFOLIATED CORROSION AND FOUND TO BE OUT OF LIMITS IAW SRM 53-00-03, FIG 101, DETAIL II. REPAIRED DAMAGED AREA IAW SRM 53-00-03, FIG 201, REPAIR 2. MAJOR REPAIR.

Part: FRAME — DENTED (BS 1240 S26L) · airframe 68,411 hrs · 20,650 cycles

BS 1240, S26L FRAME DENTED. NOT ALLOWED IAW SRM 53-00-07 FIG 101. REMOVED AND REPLACED FRAME IAW SRM 51-40-02 AND DWG 146N1003. MAJOR REPAIR.

Part: SKIN — CHAFED (RT WING TE FLAP) · airframe 68,411 hrs · 20,650 cycles

RT INBD MAIN FLAP UPPER SKIN CHAFED. REPAIR ACCOMPLISHED IAW EA 757-5752-16-F3928, REV A, MAJOR REPAIR.

Part: FLOORBEAM — MISINSTALLED (BS 1640) · airframe 68,411 hrs · 20,650 cycles

THE STA 1640, FLOORBEAM IS MISLOCATED. REMOVED MISDRILLED FLOORBEAM IAW SRM 51-40-02. INSTALLED REPLACEMENT FLOORBEAM IAW DWG 146N8711 SH2 REV R. MAJOR REPAIR

Part: ANGLE — CORRODED (LT MLG WW) · airframe 68,411 hrs · 20,650 cycles

LT WW SIDEWALL TO KEELBEAM SUPPORT ANGLE, BELOW HYD. PRESSURE TRANSMITTER D2536 HAS CORROSION. REPAIRED IAW EA F-5310-160586 STEPS 1-10 . CAT "A" MAJOR REPAIR.

Part: SKIN — MISREPAIRED (BS 1380-1400) · airframe 68,411 hrs · 20,650 cycles

EXTERNAL FUSELAGE SKIN AT BS 1380-1400, BETWEEN S27R - S30R. DOES NOT COMPLY WITH SRM. ACCOMPLISHED EA F-5330-160580. MAJOR REPAIR.

Part: CREASE BEAM — DAMAGED (BS 940-980) · airframe 68,411 hrs · 20,650 cycles

RT CREASE BEAM ANGLE BETWEEN STA 940-980 RBL 64 HAS TWO AREAS OF DAMAGE. BLENDED AREA IAW SRM 51-10-02 CHECKED LIMITS. ORIGINAL MATERIAL .063 REWORK .040 MATERIAL LOSS .023 CREASE BEAM FOUND TO BE OUT OF LIMITS IAW SRM 53-60-13, DETAIL VIII, FIG 101. R & R CREASE BEAM FROM STA 900 -1040 RBL 64 IAW SRM 51-40-02 AND DWG 144N5140. MAJOR REPAIR.

Part: FRAME — DENTED (BS 660) · airframe 68,411 hrs · 20,650 cycles

FRAME AT BS 660, BETWEEN S24R AND S25R HAS DENT IN UPPER FLANGE, FOUND TO BE OUT OF LIMITS IAW SRM 53-30-07, FIG 101, SH 1. REMOVED AND INSTALLED NEW FRAME IAW SRM 51-40-02 AND DWG 143N1024. MAJOR REPAIR.

Part: CREASE BEAM — CORRODED (BS 1628) · airframe 68,411 hrs · 20,650 cycles

CREASE BEAM INNER CORD AT STA 1628 RT IS CORRODED. R & R CREASE BEAM IAW SRM 51-40-02 AND DWG 146N5590-57. MAJOR REPAIR.

Part: CREASE BEAM — CORRODED (BS 1628) · corrosion level 2 · airframe 68,411 hrs · 20,650 cycles

CREASE BEAM INNER CORD STA 1628 LT IS CORRODED. BLENDED AREA IAW-SRM-51-10-02, CHECKED LIMITS, ORIG MATERIAL 0.079, MATERIAL LOSS 0.070, MATERIAL REMAINING 0.009, CREASE BEAM FOUND TO BE OUT OF LIMITS IAW-SRM-53-60-13, FIG 101, DETAIL VIII. R & R CREASE BEAM IAW-SRM-51-40-02 AND DWG 146N5590 AT BS 1406-1610 LT. MAJOR REPAIR.

Part: FRAME — CORRODED (BS 1300) · corrosion level 2 · airframe 68,411 hrs · 20,650 cycles

BS 1300, S26R, CORROSION ON FWD SIDE OF FRAME AFT BAGGAGE COMPARTMENT. REMOVED CORROSION IAW SRM 51-10-02. FOUND TO BE OUT OF LIMITS IAW SRM 53-00-07, FIG 101, DETAIL II. R & R FRAME IAW SRM 51-40-02 AND DWG 146N1006. MAJOR REPAIR.

Part: FRAME — DAMAGED (BS 1340) · airframe 68,411 hrs · 20,650 cycles

AFTER REMOVAL OF TRANSITION PANEL FOUND DAMAGE ON FRAME BS 1340 STR 28L AFT CARGO BAY. FOUND DAMAGE TO BE .026 DEEP ORIGINAL MATERIAL .071 MATERIAL REMAINING .045 OUT OF LIMITS IAW SRM 53-00-07, FIG 101 ALLOWABLE DAMAGE 2. NO DAMAGE ALLOWED IN FLANGE OF FRAME. R & R FRAME, BS 1340, S-24L TO S-24R IAW SRM 51-40-02 AND DWG 146N1008. MAJOR REPAIR.

Part: FRAME — DENTED (BS 1400 S25L) · airframe 68,411 hrs · 20,650 cycles

FRAME DENTED, BS 1400 S25L. R & R FRAME IAW SRM 51-40-02 AND DWG 146N1011. MAJOR REPAIR.

Part: FRAME — CORRODED (BS 1260) · airframe 68,411 hrs · 20,650 cycles

CABIN FRAME SUPPORT HAS 4 ATTACH BOLTS CORRODED AT STA 1260, STR 2R. FOUND TO BE OUT OF LIMITS IAW SRM 53-00-07, FIG 101, DETAIL II, SECTION AA ALLOWABLE DAMAGE 2. REPAIRED FRAME SECTION FROM STRG 3RH TO 6LH IAW SRM 53-00-07, REPAIR 3 CATEGORY "B" MAJOR REPAIR.

Part: SEAT TRACK — GOUGED (BS 700-780) · airframe 68,411 hrs · 20,650 cycles

MAIN DECK SEAT TRACK GOUGED AT FS 700 TO 780 RBL 45.50. FOUND TO BE OUT OF LIMITS IAW SRM 53-00-52, FIG 101, DETAIL I. REMOVED AND INSTALLED NEW SEAT TRACK IAW SRM 51-40-02 AND DWG 143N5085. MAJOR REPAIR.

Part: FLOORBEAM — DAMAGED (BS 1640) · airframe 68,411 hrs · 20,650 cycles

FLOORBEAM UPPER TEE BS 1640 LBL 58 TO RBL 58 HAS SEVERAL AREAS OF DAMAGE. FLOORBEAM REPLACED IAW SDR 12-2016, NO FURTHER ACTION.

Part: SKIN — CORRODED (BS 960) · corrosion level 2 · airframe 68,411 hrs · 20,650 cycles

RT UPPER CENTER WING BOX EXTERNAL SKIN AT BS 960, RBL 64 CORRODED. REMOVED CORROSION, FOUND OUT OF LIMITS IAW SRM 57-10-01, FIG 101, TABLE 1, NOTE A. COMPLIED WITH EA F-5730-160574. MAJOR REPAIR.

Part: SKIN — CORRODED (BS 940) · corrosion level 2 · airframe 68,411 hrs · 20,650 cycles

UPPER WING CENTER BOX UPPER EXTERNAL SKIN UNDER STUB BEAM AT BS 940, RBL 63, CORRODED. REMOVED CORROSION, FOUND OUT OF LIMITS IAW SRM 57-10-01, FIG 101, TABLE 1, NOTE A. COMPLIED WITH EA F-5710-159946. MAJOR REPAIR.

Part: SKIN — CORRODED (BS 940) · corrosion level 2 · airframe 68,411 hrs · 20,650 cycles

CORROSION ON CENTER WING BOX UPPER SKIN, UPPER SURFACE AT BS 940, LBL 63. REMOVED CORROSION, FOUND OUT OF LIMITS IAW SRM 57-10-01, FIG 101, TABLE 1 NOTE A. REPAIRED IAW NR 4774935 AND EA 757-5710-16-F3831. MAJOR REPAIR.

Part: FRAME — DENTED (BS 1260) · airframe 68,411 hrs · 20,650 cycles

BS 1260, STR 26L HAS A DENT IN FRAME AFT BAGGAGE. R & R FRAME STA 1260 S-25L TO S-25R IAW SRM 51-40-02 AND DWG 146N1004. MAJOR REPAIR.

Part: SKIN — CORRODED (BS 1500-1520) · airframe 68,411 hrs · 20,650 cycles

CABIN SKIN HAS CORROSION AROUND DOME NUTS BS 1500-1520, STRINGER 1-2L.

Part: FLOORBEAM — CORRODED (BS 1681) · airframe 68,411 hrs · 20,650 cycles

FLOORBEAM BS 1681 UPPER CAP CORRODED BL 0 TO RBL 62. BLENDED AREA, ORIGINAL MATERIAL 0.156, AFTER REWORK 0.124, MATERIAL LOSS 0.032 FLOORBEAM FOUND TO BE OUT OF LIMITS IAW SRM 53-00-51, DETAIL II, FIG 101. R & R FLOORBEAM IAW SRM 51-40-02 AND DWG 146N5111. MAJOR REPAIR.

Part: SKIN — GOUGED (BS 1380) · airframe 68,411 hrs · 20,650 cycles

FUSELAGE SKIN BS 1380, S-25R EDGE OF CARGO DOOR CUTOUT GOUGED. ACCOMPLISHED EA F-5330-160578. MAJOR REPAIR.

Part: SKIN — CORRODED (RT WING) · airframe 68,411 hrs · 20,650 cycles

RT WING ROOT T/E UPPER SURFACE AT REAR SPAR WITH PANEL REMOVED, SUPPORT HAS CORROSION. REPAIRED IAW EA F-5710-159940, STEPS 1-10. MAJOR REPAIR.

Part: SEAT TRACK — DAMAGED (BS 440-650) · airframe 68,411 hrs · 20,650 cycles

SEAT TRACK BS 440-650 LBL 45, CORRODED AND GOUGED.

Part: FLOORBEAM — CORRODED (BS 680) · airframe 68,411 hrs · 20,650 cycles

FLOORBEAM BS 680 LBL 24 TO RBL 27 UPPER TEE CORRODED. FLOORBEAM WAS FOUND TO BE OUT OF LIMITS IAW SRM 53-00-51, FIG 101, DETAIL II AND III. R & R FLOORBEAM IAW DWG 143N5013, SH2, REV C AND SRM 51-40-02. MAJOR REPAIR.

Part: FLOORBEAM — CORRODED (BS 700) · airframe 68,411 hrs · 20,650 cycles

FLOORBEAM BS 700 RBL 24 TO LBL 70 WL 208.1 UPPER TEE CORRODED. FLOORBEAM WAS FOUND TO BE OUT OF LIMITS IAW SRM 53-00-51, FIG 101, DETAIL II AND III. ORIGINAL MATERIAL .125 AFTER REWORK .022. R & R FLOORBEAM IAW DWG 143N5014 SH7 AND SRM 51-40-02. MAJOR REPAIR.

Part: FLOORBEAM — CORRODED (BS 1660) · airframe 68,411 hrs · 20,650 cycles

FLOORBEAM UPPER TEE AT BS 1660 HAS SEVERAL NICKS, GOUGES, AND CORROSION AROUND NUT PLATE HOLES AND VICINITY OF RBL 58. FLOORBEAM WAS FOUND OUT OF LIMITS IAW SRM 53-00-51, FIG 101, DETAIL II AND III. ORIGINAL MATERIAL .125 AFTER REWORK .060. R & R FLOORBEAM IAW DWG 146N5110 SH1 AND SRM 51-40-02. MAJOR REPAIR.

Part: FLOORBEAM — CORRODED (BS 720) · airframe 68,411 hrs · 20,650 cycles

FLOORBEAM BS 720 BL 0 TO LBL 70 WL 208.1 UPPER TEE CORRODED. FLOORBEAM WAS FOUND TO BE OUT OF LIMITS IAW SRM 53-00-51 FIG 101 DETAIL II AND III. ORIGINAL MATERIAL .125 AFTER REWORK .020. REMOVED AND REPLACED FLOORBEAM IAW DWG 143N5015 SH7 AND SRM 51-40-02. MAJOR REPAIR.

Part: FLOORBEAM — CORRODED (BS 780) · airframe 68,411 hrs · 20,650 cycles

FLOORBEAM UPPER TEE BS 780 LBL 24 TO RBL 25 CORRODED. FLOORBEAM WAS FOUND TO BE OUT OF LIMITS IAW SRM 53-00-51, FIG 101, DETAIL II AND III. ORIGINAL MATERIAL .125 AFTER REWORK .094. R & R FLOORBEAM IAW DWG 143N5067, SH 1, REV A. MAJOR REPAIR.

Part: FLOORBEAM — CORRODED (BS 740) · airframe 68,411 hrs · 20,650 cycles

FLOORBEAM BS 740 LBL 14 UPPER TEE CORRODED. FLOORBEAM FOUND OUT OF LIMITS IAW SRM 53-00-1, FIG 101, DETAIL II AND III. ORIGINAL MATERIAL .125 AFTER REWORK .070. R & R FLOORBEAM IAW SRM 51-40-02 AND DWG 143N5016, SH 5. MAJOR REPAIR.

Part: FLOORBEAM — CORRODED (BS 760) · airframe 68,411 hrs · 20,650 cycles

FLOORBEAM UPPER TEE BS 760, RBL 8 TO LBL 24 CORRODED. FOUND TO BE OUT OF LIMITS IAW SRM 53-00-51, FIG 101, DETAIL II AND III. R & R FLOORBEAM IAW DWG 143N5430 SH19 AND DWG 143N5017, SH1, REV A, MAJOR REPAIR.

Part: FLOORBEAM — CORRODED · airframe 68,411 hrs · 20,650 cycles

FLOORBEAM BL0 - RBL 62 WL 201.1, UPPER CHORD CORRODED. R & R UPPER TEE IAW SRM 51-40-02 AND DWG 141N5810. MAJOR REPAIR.

Part: FLOORBEAM — CORRODED (BS 333.45) · corrosion level 2 · airframe 68,411 hrs · 20,650 cycles

FLOORBEAM, BS 333.45 LBL 45 - LBL 62 WL 208.1 UPPER TEE CORRODED. R & R FLOORBEAM IAW-SRM-51-40-02, CORROSION OUT OF LIMITS IAW-SRM-53-00-51,FIG.101,III, THIS IS A MAJOR REPAIR, CAT."A".

Part: FLOORBEAM — CORRODED (BS 345) · airframe 68,411 hrs · 20,650 cycles

FLOORBEAM BS 345, LBL 18 - RBL 8, WL 208.1, UPPER TEE CORRODED. R & R FLOORBEAM IAW SRM 51-40-02 AND DWG 141N5111.

Part: FLOORBEAM — CORRODED (BS 365.25) · corrosion level 2 · airframe 68,411 hrs · 20,650 cycles

FLOORBEAM BS 365.25 BL0 TO RBL 61 WL 208.1, UPPER CHORD CORRODED. BLENDED CORROSION IAW SRM 51-10-02 CHECKED LIMITS IAW SRM 53-00-51, FIG 101, FOUND TO OUT OF LIMITS. R & R FLOORBEAM IAW SRM 51-40-02 AN D DWG 141N5112. MAJOR REPAIR.

Part: FLOORBEAM — CORRODED (BS 395) · corrosion level 2 · airframe 68,411 hrs · 20,650 cycles

FLOORBEAM BS 395, BL 0-62, UPPER TEE CORRODED. BLENDED IAW SRM 51-10-02, ORIG MATERIAL .125, AFTER REWORK .084, TOTAL MATERIAL LOSS .041, AREA OUT OF LIMITS. REMOVED DAMAGED FLOORBEAM IAW SRM 51-40-02. DRILLED AND LOCATED NEW FLOORBEAM IAW SRM 51-40-05. INSTALLED NEW FLOORBEAM IAW SRM 51-40-02 AND DWG 141N5114. MAJOR REPAIR.

Part: FLOORBEAM — CORRODED (BS 377.7) · airframe 68,411 hrs · 20,650 cycles

FLOORBEAM, BS 377.7, UPPER TEE, LBL 62-RBL 62, CORRODED. BLENDED AREA ORIG MATERIAL .125 AFTER REWORK .087 MATERIAL LOSS .038 FOUND TO BE OUT OF LIMITS IAW SRM 53-00-51, FIG 101, DETAIL III, L=3.0 W=2.0 W=.038. R & R FLOORBEAM IAW SRM 51-40-02 AND DWG 141N5113. MAJOR REPAIR.

Part: FLOORBEAM — CORRODED (BS 324) · airframe 68,411 hrs · 20,650 cycles

FLOORBEAM BS 324 LBL 30-RBL 61, WL.208.1, UPPER TEE CORRODED. FOUND TO BE OUT OF LIMITS IAW SRM 53-00-51, FIG 101, DETAIL III. R & R FLOORBEAM UPPER TEE IAW SRM 51-40-02 AND DWG 141N5160. MAJOR REPAIR.