N783FD

Part: GUST LOCK — DAMAGED (ZONE 800) · airframe 77,032 hrs · 30,602 cycles

L1 DOOR GUST LOCK COLLAR BROKEN. INSTALLED A NEW L1 DOOR GUST LOCK COLLAR, OPS CHECKS GOOD, OK FOR SERVICE.

Part: GUST LOCK — BROKEN (ZONE 800) · airframe 77,002 hrs · 30,576 cycles

L1 DOOR GUST LOCK IS BROKEN (LOCK IS REMOVED). INSTALLED NEW GUST LOCK. OPS CHECK OK.

Part: LAMP — FAILED (EXTERIOR) · airframe 76,800 hrs · 30,419 cycles

L1 DOOR EXTERIOR SLIDE LIGHT INOP FACT 17NOV24 17:47 BNA AMM: 33-51-06-2-1 RELAMPED L1 DOOR EXTERIOR SLIDE LIGHT, OP'S CHECKS GOOD REF AMM 33-51-06-2-1. BULB PART NUMBER 767 REPLACED.

Part: CLAMP — LEAKING (ZONE 100) · airframe 76,800 hrs · 30,419 cycles

LOSS OF CABIN PRESSURE AT FL340. CABIN CLIMBED TO @ 14,000 DURING THE DESCENT WITH THE CABIN CONTINUING TO CLIMB @700 FPM. COMPLIED WITH QRH NO OBVIOUS FUSELAGE LEAKS NOTED ON WALK AROUND. AUTOMATIC CABIN PRESSURE CONTROLLER 1 AND 2 BITE CHECK GOOD. OPERATIONAL CHECK OF OUTFLOW VALVE GOOD. TRIED PRESSURIZING A/C USING LEFT PACK (RIGHT PACK ON MEL). DIFFERENTIAL PRESSURE MAXED OUT AT 1.25 PSI. NOTED FORWARD CLAMP MISSING ON LEFT PACK OUTLET DUCT BOOT TO CABIN SUPPLY CHECK VALVE CAUSING SIGNIFICANT LEAK. CLAMP NIS AT BNA. PARTS ORDERED. REF 757 AMM 20-10-10-4 INSTALLED CLAMP (MPN BACC10JB204C236) ON BOOT FROM PACK OUTLET DUCT TO CABIN SUPPLY CHECK VALVE. A/C PRESSURIZED NORMAL (RAPID CLIMB TO 4 PSI) REF 757 AMM 21-31-00-5.

Part: WEB — CRACKED (ZONE 200) · airframe 76,702 hrs · 30,337 cycles

AFTER INSPECTION PER ED F-5310-E0329085DP5 STEP 3, A CRACK WAS FOUND AT FR-1640 LH, S- 14. COMPLIED WITH FEDEX E.A. # F -5310-T0380418 P1 TITLE: FUSELAGE- MAINFRAME - LH STA 1640 - TYPICAL FRAME SPLICE REPAIR BETWEEN STRINGER S-9L AND S-20L.

Part: WIRE — BROKEN (EMERGENCY LIGHTS) · airframe 76,543 hrs · 30,226 cycles

WHEN SELECTING EMERGENCY LTS SWITCH ON OVERHEAD TO ON, COCKPIT OVERHEAD LT DOES NOT ILLUMINATE. ALL OTHERS OPERATE NORMALLY. PER WDM 33-51-21 FOUND GOOD GROUND BITWEEN GD602 AND G TERMINAL OF RESISTER R10381 AND DISCOVERED THAT WIRE WAS BROKEN FROM RESISTER R10381 P TERMINAL LUG, RETERMINATED THE WIRE AND AS A PRECAUTION REPLACED THE 10 OHM RESISTER (R10381) PER THE ABOVE LISTED REFERENCE AND OPS CHECK EMERGENCY LIGHT AND OPS CHECK GOOD.

Part: FLOORBOARD — DELAMINATED (ZONE 200) · airframe 75,545 hrs · 29,577 cycles

ZONE 220 FLOORBOARD 221MBF IS DELAMINATED. FABRICATED ZONE 220 FLOORBOARD 221MBF ON TRAVELER T22/1649009 IAW DWG SRZ- 25-005 REVISION R. MAJOR REPAIR

Part: DRAG FITTING — CORRODED (ZONE 600) · corrosion level 2 · airframe 75,545 hrs · 29,577 cycles

HOLE #2 AND 5 ON UPPER SKIN AND DRAG FITTINGS PRESENT CORROSION RH WING. WORKS STEPS ACCOMPLISHED ON EA #: F5730-T0371761 MAJOR REPAIR.

Part: DRAG FITTING — CORRODED (ZONE 500) · corrosion level 2 · airframe 75,545 hrs · 29,577 cycles

HOLES 4 & 5 ON LT WING UPPER SKIN DRAG FITTINGS PRESENT CORROSION. WORKS STEPS ACCOMPLISHED ON EA F5730-T0371760 EA TITLE: WINGS-PLATES AND SKINS-LH WING, UPPER SKIN AT PYLON DRAG FITTING, CORROSION FINDINGS* THIS EA DEVIATES FROM EO F-5730-E0340076. MAJOR REPAIR

Part: FLOORBEAM — CRACKED (BS 580 LBL 45) · airframe 75,545 hrs · 29,577 cycles

FWD PIT CEILING AREA STA 580 FLOOR BEAM UPPER CAP AFT SIDE FLANGE RADIUS HAS SUSPECTED CRACK, APPROX LBL 45. FLOOR BEAM WAS REPAIRED AND NEW ANGLE & RADIUS STRAP INSTALLED ON FWD PIT CEILING AREA STA 580 AT LBL 45 IAW DRAWING SR57-53-004 & SRM 51-40-02. MAJOR REPAIR.

Part: BATTERY — NO TEST (EMERGENCY LIGHTS) · airframe 75,437 hrs · 29,501 cycles

R1 EMERGENCY EXIT SIGN, R1 SLIDE LIGHT AND EMERGENCY EXIT LOCATOR SIGN INOP DURING EMERGENCY LIGHT TEST. FOUND THAT AFTER AIRCRAFT HAD BEEN POWERED FOR OVER AN HOUR, ALL LIGHTS WOULD TEST, HOWEVER THE TEST ONLY LASTED APPROX 5-10 SECONDS, ALL OTHERS STAYED ON FOR APPROX. 1 MINUTE. AFTER TESTING, LIGHTS WOULD NOT TEST AGAIN. REMOVED AND REPLACED BATTERY M730 IAW AMM 33-51-07-2, OPS CHECK GOOD, LIGHT TEST NORMAL.

Part: FMC — FAILED (N/A) · airframe 75,129 hrs · 29,269 cycles

L AND R FMC FAIL -EMERGENCY DECLARED ***EMERGENCY DECLARED*** R&R'D BOTH FMC COMPUTERS. UPDATED ALL SOFTWARE. BOTH FMCS OPS CKS NORMALLY. REF B757 MM SEC 34-61-01-4-1. ALL SOFTWARE UPDATED TO CURRENT REQUIREMENTS.

Part: NONE — FAILED (N/A) · airframe 75,005 hrs · 29,178 cycles

PDIS 783 73-20 6104 09FEB22 TPA OPEN U CLIMBING THROUGH FL300 LEFT ENGINE BEGAN SPOOLING DOWN. AUTOTHROTTLES DISCONNECTED WITH THE MASTER CAUTION. EMERGENCY WAS DECLARED AND DIVERTED TO TPA. ENGINE THRUST CAME BACK AFTER APPROXIMATELY 10 SECONDS. VERY SIMILAR TO THE EVENTS PREVIOUSLY WRITTEN UP ON TAXI OUT IN PBI ON PREVIOUS FLIGHT. WE DID NOT RECEIVE LOW OIL PRESSURE MASTER CAUTION THIS TIME. STATUS MESSAGE L ENG PRI CONT DISPLAYED. ENGINE OPERATED NORMALLY FOR REMAINDER OF FLIGHT WITHOUT INCIDENT. REMOVED AND REPLACED ENGINE WIRE HARNESS

Part: NONE — LEAKING (N/A) · airframe 75,000 hrs · 29,175 cycles

PDIS 783 79-32 6083 03FEB22 TPA OPEN U EMERGENCY DECLARED. DURING CLIMB OUT FROM TAMPA TO MEMPHIS, HAD INDICATION OF HIGH OIL TEMP ON LEFT ENGINE. SOON AFTER, NOTICED OIL QUANTITY WAS ZERO. OIL PRESSURE WAS NORMAL. RETARDED LEFT THRUST LEVER PER QRH BUT OIL TEMP CONTINUED TO RISE. AS WE WERE PREPARING TO CONTINUE THE CHECKLIST TO SHUT THE ENGINE DOWN, OIL TEMP CLIMBED INTO THE WARNING RANGE (RED BAND) AND SMOKE BEGAN TO POUR INTO THE COCKPIT FROM THE LEFT SIDE. THE ENGINE WAS IMMEDIATELY SHUT DOWN, EMERGENCY DECLARED, AND COORDINATED FOR RETURN TO TAMPA FOR EMERGENCY, SINGLE-ENGINE LANDING. INFO 03FEB22 05:22 MC1 R PER ETHAN/POWERPLANT ENGINEERING DUE TO OIL IN THE TAILPIPE THIS ENGINE IS APPROVED FOR ENGINE CHANGE. FACT 06FEB22 23:59 TPA L/H ENGINE CHANGE COMPLETED. SEE W/C 7180210-01-01 FOR SIGNOFF'S. AND RII .

Part: NONE — FAILED (N/A) · airframe 74,988 hrs · 29,168 cycles

AFTER ENGINE START GOT EICAS MSG: L PACK OFF. AFTER ADVANCING THROTTLE TO TAXI, MSG EXTINGUISHED. TAKEOFF POWER WAS COMPUTED FOR DTO 50 WITH TEMPERATURE MINUS 6 CELSIUS. ON RUNWAY AFTER THRUST LEVERS WERE ADVANCED TO TAKEOFF POWER AT APPROXIMATELY 100 KNOTS, EICAS MSG: L ENG BLEED OFF ANNUNCIATED. DURING THE CLIMB TO A SAFE ALTITUDE HE EICAS MSG: L ENG BLEED OFF EICAS EXTINGUISHED AND ILLUMINATED A FEW TIMES. AFTER SAFE ALTITUDE WAS REACHED COMPLIED WITH QRH ENGINE BLEED OFF PROCEDURE. AFTER NOTIFYING GOC, THEY DIRECTED A DIVERT TO MEMPHIS. REMOVED LEFT REVERSE FLOW CHECK CONTROLLER IN REF TO 757 AMM 36-11-18-4. NEW PART AND HARDWARE IS IN 114 LINE SHACK. INSTALLED L/H ENGINE REVERSE FLOW CHECK CONTROLLER REF. 757 AMM 36-11-18-4. OPS CHECKED GOOD.

Part: COLLAR — CRACKED (DOOR HOLD OPEN) · airframe 74,544 hrs · 28,861 cycles

DURING SERVICE CHK FOUND 1R DOOR HOLD OPEN LOCK BROKEN. RMVD AND RPLD R1 DOOR HOLD-OPEN LOCK- DOOR HOLD OPEN LOCK CHKS GOOD- REF: B757 M/M 52-11-08-8

Part: SKIN — CRACKED (R2 DOOR AREA) · airframe 74,225 hrs · 28,631 cycles

R2 DOOR CUTOUT FWD FRAME UPPER HINGE CUTOUT IS CRACKED ACCOMPLISHED FEDEX EA F-5210-T0312598-B. DOORS-PASSENGER/CREW R2 DOOR EXISTING REPAIR.

Part: GUARD — DEBONDED (L1 DOOR HANDLE) · airframe 74,225 hrs · 28,631 cycles

L1 DOOR EXTERIOR HANDLE SCUFF GUARD AROUND CENTER CUTOUT IS DISBONDED. FOUND OUT OF LIMITS GOUGE UNDER SCUFF GUARD. REMOVED AND REPLACED L1 DOOR ASSEMBLY, PER FEDEX B757-2 AMM 52-11-01-4.

Part: ATTACH BRACKET — GOUGED (NR 2 ENGINE) · airframe 74,225 hrs · 28,631 cycles

NR 2 ENGINE STARTER DUCT SUPPORT LINK ATTACH BRACKET ON THE ENGINE SIDE IS GOUGED AT THE 3 O'CLOCK POS (OUTBOARD SIDE). REMOVED AND REPLACED NR 2 ENGINE LINK ATTACH BRACKET ON THE ENGINE SIDE AT THE 3 O'CLOCK POSITION, IAW B757 SRM 51-40-02 AND AMM 70-50-00, BRACKET ASSEMBLY 18A093, PO 990274, TOOL ID T8352P.

Part: SKIN — DELAMINATED (LT WING SLAT) · airframe 74,225 hrs · 28,631 cycles

LT WING INBOARD AFT FLAP OUTBOARD EDGE DELAM. REPAIRED LT WING INBOARD AFT FLAP OUTBOARD EDGE DELAM, IAW FEDEX EA F-5750-T0359087, B757 SRM 57-53-01-2R REPAIR 1 AND 51-70-17-0G. REPAIR ACCOMPLISHED, IAW FEDEX EA F-5750-T0359087-P1 WING-FLIGHT SURFACES-LT INBOARD AFT FLAP-TAILING EDGE WEDGE-UPPER SKIN-AF STA 223-EDGE DELAMINATION. MAJOR REPAIR.

Part: CHANNEL — CRACKED (NR 2 NACELLE) · airframe 74,225 hrs · 28,631 cycles

NR 2 PYLON PNL 445BL IS CRACKED REMOVED AND REPLACED CHANNEL, PER B757 SRM 51-40-02 AND DWG 313N3022.

Part: SKIN — DAMAGED (HORIZONTAL STAB) · airframe 74,225 hrs · 28,631 cycles

RIGHT HORIZONTAL STABILIZER WING TIP FORWARD END PAINT AND COMPOSITE DETERIORATED. REPAIRED RIGHT HORIZONTAL STABILIZER WING TIP FORWARD END PAINT AND COMPOSITE DETERIORATED, IAW B757 SRM 55-10-2R, 51-70-05-OG, 51-70-14, B757 AMM 51-21-00-7. REMOVED THEN REINSTALLED RIGHT HORIZONTAL TIP CAP, IAW B757 SRM 55-11-01-04.

Part: WEB — CRACKED (BS 400-420) · airframe 74,225 hrs · 28,631 cycles

PREVIOUS WEB REPAIR AT STA 400-420 AT APPROXIMATELY RBL 25 HAS FASTENERS WHICH ARE TOO LONG, HAVE EXCESSIVE WASHERS AND THE WEB IS DAMAGED. REMOVED DAMAGE WEB AT STA 400-420 RBL 25, IAW B757 SRM 51-40-02. RECEIVED NEW PART P/N 141N5150U54, PO NR 989969.1, IAW BOEING PL 141N5150-54 REV BN. LOCATED AND DRILLED, IAW B757 SRM 51-40-05, INSTALLED WEB IAW B757 SRM 51-40-02.

Part: DECK PLATE — GOUGED (BS 1681) · airframe 74,225 hrs · 28,631 cycles

PREVIOUS REPAIR ON AFT DECK PLATE AT STA 1681 RBL 12 HAS A GOUGE ON THE UPPER SURFACE. REMOVED, FABBED AND REPLACED DOUBLER, IAW B767 SRM 53-60-51-2R FIG 201 REPAIR 2.

Part: ANGLE — CRACKED (NR 1 PYLON) · airframe 74,225 hrs · 28,631 cycles

ENGINE NR 1 AFT PYLON RT SIDE FWD LOWER CORNER CLIP CRACKED UNDER PANEL 435AR. REMOVED AND REPLACED -24 CLIP AT NR 1 PYLON RT SIDE FWD LOWER CORNER, IAW B757 FEDEX DWG 313N3053 REV P AND SRM 51-40-02.

Part: PANEL — CRACKED (RT WING LE) · airframe 74,225 hrs · 28,631 cycles

RT WING LEADING EDGE PANEL 611EB IS CRACKED. REPAIRED RT WING LEADING EDGE PANEL 611EB BY BONDING REPAIRPLIES, IAW B757 SRM 57-41-01-0I AND 57-41-01-2R REPAIR 1 FIG 201 AND 51-70-08 REPAIR GENERAL AND PARA 5G FIG 9. APPLIED FINISH, IAW B757 SRM 51-70-08 AND B757 AMM 51-24-02 AND 51-21-00.

Part: PANEL — CRACKED (HORIZONTAL STAB) · airframe 74,225 hrs · 28,631 cycles

LEFT HORIZONTAL STABILIZER TRAILING EDGE PANEL 335AB IS CRACKED. REPAIRED PANEL 335AB, IAW B757 SRM 55-10-01-2R FIG 201 TABLE 2 AND B757 SRM 51-70-05-0G PARA 5G.

Part: IDG — FAILED (RT GENERATOR) · airframe 74,103 hrs · 28,538 cycles

RT GEN OFF IN FLIGHT. CREW RAN QRH AS REQUIRED. CHECKED ELEC/HYD DISPLAY SELECT SWITCH ON THE EICAS PANEL AT P61 HAD RT GEN DRIVE PUSH THE BIT SWITCH ON THE BUS POWER CONTROL UNIT MESSAGES WAS RT LOW OIL AND DELTA TEMP OPENED COWL AND FOUND DELTA P POP ON RIGHT GEN. FACT 16OCT20 18:42 MEM U. DUE TO LOW OIL FAULT AND DIFFERENTIAL PRESSURE BUTTON POPPED, WE REMOVED AND REPLACED RT ENGINE IDG ASSEMBLY, PER B757 AMM 24-11-01-4. PERFORMED BPCU BITE TEST, PER 757 FIM 24-20 FIG 101 FAULT TREE 801. RAN RT ENGINE, PER JRH SHOWS 115VAC/400HZ. NO FURTHER FAULTS NOTED.

Part: LINKAGE — BROKEN (CARGO DOOR) · airframe 73,701 hrs · 28,265 cycles

THE MAIN CARGO DOOR IS DENTED AND GOUGED ON SKIN AT UPPER FWD CORNER OF DOOR FROM FWD LIFT ACT. LINKAGE BREAKING. COMPLETED REPAIR OF MAIN DECK CARGO DOOR REF B757 SRM 52-30-01-2R.

Part: DECK PLATE — CORRODED (BS 1681) · corrosion level 2 · airframe 72,598 hrs · 27,496 cycles

CORROSION AROUND FASTENER HOLES IN MAIN CARGO FLOOR STRUCTURE SHEAR WEB UPPER CHORD UPPER SURFACE B.S. 1681 RBL.48 REMOVED CORROSION AT STA.1681 RBL48. ORIG. MAT. .071", REM.MAT..055, MATERIAL LOSS OF .016" IS OUT OF LIMITS PER B757 SRM 53-00-51-1A. FABRICATED REPAIR DOUBLER DIM.= 5"X 6" FROM .063" 2024-T3 CLAD P/O # FSS183476. PERFORMED AFT DECK PLATE REPAIR 2 ALT I IAW B757 SRM 53-60-51-2R. SHIM DIM.=.5" X1" FABRICATED FROM 2024 T-3 .012", P/O# FS1703502.

Part: DECK PLATE — CORRODED (BS 1681) · airframe 72,598 hrs · 27,496 cycles

CORROSION AROUND FASTENER HOLES IN THE MAIN CARGO FLOOR STRUCTURE SHEAR WEB UPPER CHORD UPPER SURFACE B.S.1681 RBL.12. REMOVED CORROSION, MATERIAL LOSS .027", REMAINING MAT. .044" OUT OF LIMITS IAW B757 SRM 53-00-51-1A DETAIL II, CUT-OUT DAMAGE, FABRICATED AND INSTALLED DOUBLER REPAIR IAW B757 SRM 53-60-51-2R REPAIR 2 ALT.II, TO AFT SHEAR WEB B.S. 1681 RBL12 ,MAIN CABIN .ADDITIONAL CORROSION FOUND ON LOWER SURFACE OF SHEAR WEB AFTER UT INSPECTION. FOUND DAMAGE TO BE 100% MATERIAL LOSS IAW B757 SRM 51-10-02-0G.

Part: SKIN — DENTED (VERTICAL STAB) · airframe 70,844 hrs · 26,333 cycles

SIX INCH HORIZONTAL DENT ON THE RIGHT SIDE FOR THE VERTICAL STAB VSS 125. REPAIRED THE VERTICAL STAB IAW SRM 51-70-10-2R. PRIMED AND TOP COATED IAW SRM 51-70-10-2R AND AMM 51-21-10-7.

Part: FRAME — CHAFED (BS 231) · airframe 70,844 hrs · 26,333 cycles

PUNCTURE ON FRAME BS 231 FORWARD ACCESSORY ACCESS DOOR CUTOUT. REMOVED DAMAGE AND INSTALLED REPAIR IAW EA F-5310-T0330045 P1.

Part: SKIN — DEBONDED (HORIZONTAL STAB) · airframe 70,844 hrs · 26,333 cycles

LEFT HORIZONTAL STAB HSS 81.0 FOUND DEBONDED. REPAIRED IAW SRM 51-70-17-0G PRIMED AND TOP COATED IAW SRM 51-70-17-0G AND AMM 51-21-10-7.

Part: SKIN — DENTED (HORIZONTAL STAB) · airframe 69,415 hrs · 25,343 cycles

A 2 INCH X 2 INCH X .094 INCH DENT ON TOP OF THE RT HORIZONTAL STAB. REPAIRED IAW SRM 55-10-01 FIG 201 REPAIR 4. CATEGORY A MAJOR REPAIR.

Part: SKIN — DELAMINATED (TE FLAP) · airframe 69,409 hrs · 25,335 cycles

RIGHT INBD FLAP, OTBD LOWER END, INNER SKIN DISBONDED. REPAIRED RT INBD FLAP, OTBD LOWER END SKIN IAW SRM 51-70-10. IAW EA F-5710-T0313603 FOR RSC TRACKING. MAJOR REPAIR.

Part: SKIN — DAMAGED (CARGO DOOR) · airframe 69,409 hrs · 25,335 cycles

AFT CARGO DOOR SKIN AT LOWER AFT CORNER, NOTED EDGE WITH PREVIOUS BLEND. PREVIOUS BLEND FOUND TO BE OUT OF LIMITS IAW SRM 52-30-01 PG 104 DETAIL 4. MATERIAL LOSS .017 INCHES OF ORIGINAL .063 INCHES. REPAIR DOUBLER, INSTALLED TO REPAIR DAMAGE IAW SRM 52-30- 01, REPAIR 4 FROM .071 INCHES C MATERIAL BATCH 0002341216. IAW EA F-5230-T0313656 FOR RSC TRACKING. MAJOR REPAIR CAT B.

Part: FRAME — MECHANIC ERROR (FUSELAGE) · airframe 69,409 hrs · 25,335 cycles

MAIN CABIN, LT AT BS 960 FWD EMER WINDOW CUT OUT JUST BELOW STRINGER 9L DOUBLE DRILLED HOLE IN FRAME. FUSELAGE FRAME REPAIR AT STATION 960 BELOW STRINGER 9L WAS ACCOMPLISHED DUE TO EFFECTING THE PTF CONVERSION ON EA 757-5342-16-F4770 REV DATED NOV 7 2014 & NR 60003194450001. THIS NR IS FOR TRACKING PURPOSES ONLY. IAW EA F-5310-T0313387 ISSUED FOR TRACKING. MAJOR REPAIR

Part: SKIN — DELAMINATED (NR 1 SLAT) · airframe 69,409 hrs · 25,335 cycles

NR 1 SLAT TE WEDGE UPPER SURFACE DELAMINATED AT INBD END. REPAIRED IAW SRM 51-70-10 REPAIR 4 .

Part: FRAME — CORRODED (FUSELAGE) · corrosion level 2 · airframe 69,409 hrs · 25,335 cycles

FRAME BS 1661 STRINGER 25L TO 25R CORRODED ON AFT LOWER FLANGE. R & R FRAME IAW DWG 146N1032 & SRM 51-40-02 DUE TO CORROSION FOUND WITH MATERIAL LOSS CLEANUP OF .047 OF ORIGINAL .063 OUT OF LIMITS IAW SRM 53-00-07 FIG 101 DETAIL II. MAJOR REPAIR.

Part: FRAME — CORRODED (BS 1620) · corrosion level 2 · airframe 69,409 hrs · 25,335 cycles

BS 1620 STRINGER 22R - 23R, FRAME FOUND TO BE CORRODED. REMOVED AND REPLACED THE FRAME IAW SRM 51-40-02 AND DWG 146N1030, FOUND TO BE OUT OF LIMITS IAW SRM 53-00-07, FIG. 101, DETAIL II. MAJOR REPAIR.

Part: FRAME — CORRODED (BS 1681) · corrosion level 2 · airframe 69,409 hrs · 25,335 cycles

CORROSION FOUND ON AFT FUSELAGE FRAME WEB AT BS 1681 BETWEEN STRINGERS 28 - 29R. REMOVED AND REPLACED THE FRAME IAW SRM 51-40-02 AND DWG 146N1032, FOUND TO BE OUT OF LIMITS IAW SRM 53-00-07, FIG. 101, DETAIL II. MAJOR REPAIR.

Part: FRAME — CORRODED (FUSELAGE) · airframe 69,409 hrs · 25,335 cycles

HIDDEN DAMAGE AFT FUSELAGE AT STATION 1710 BETWEEN STRINGER 28R & 29R FRAME WEB AFT FACE HAS CORROSION.

Part: STRINGER — CORRODED (FUSELAGE) · corrosion level 2 · airframe 69,409 hrs · 25,335 cycles

HIDDEN DAMAGE STRINGER 27L STATION 1661 - 1720 CORRODED BETWEEN STRINGER & SKIN. R & R STRINGER STATION 1661 - 1720, STRINGER 27L IAW SRM 51-40-02. CORROSION WAS OUT OF LIMITS IAW SRM 53-00-03 FIG 101 DETAIL I. MAJOR REPAIR.

Part: FLOORBEAM — CORRODED (BS 365) · corrosion level 2 · airframe 69,409 hrs · 25,335 cycles

BS 365, LBL 7, WL 208, FLOORBEAM UPPER ANGLE CORRODED. FOUND OUT OF LIMITS PER SRM 53-00-51, FIG. 101, DETAIL III. REPAIRED THE FLOORBEAM ANGLE BETWEEN LBL 15 - RBL 69, IAW SRM 53-00-51, FIG. 201, REPAIR 8. MAJOR REPAIR.

Part: FRAME — CORRODED (FUSELAGE) · corrosion level 2 · airframe 69,409 hrs · 25,335 cycles

AFT PIT BS 1580 STRINGER 28L - 30 FRAME & SHEAR TIE CORRODED. REMOVED AND REPLACED FRAME AT STA 1580, FOUND TO BE OUT OF LIMITS WITH MATERIAL LOSS OF .011" OF ORIGINAL 0.63", IAW SRM 53-00-07, FIG 101, DETAIL I, AND IAW SRM 51-40-02 AND DWG 140N2002. MAJOR REPAIR

Part: FRAME — CORRODED (BS 1640) · corrosion level 2 · airframe 69,409 hrs · 25,335 cycles

AFT CARGO BAY BS 1640, STRINGER 26 - 28L FRAME CORRODED. REMOVED COROSION IAW SRM 51-10-02 AND FOUND TO BE OUT OF LIMITS IAW SRM 53-00-07, FIG. 101, DEATIAL II. REMOVED AND REPLACED THE FRAME IAW SRM 51-40-02 AND DWG 146N1032. MAJOR REPAIR.

Part: FLOORBEAM — DAMAGED (BS 1640) · airframe 69,409 hrs · 25,335 cycles

MAIN DECK CARGO FLOORBEAM UPPER TEE AT BS 1640 SCRATCHED, NICKED & CORRODED. FOUND TO BE OUT OF LIMITS IAW SRM 53-00-51 FIG 101 DETAIL III. R & R FLOORBEAM IAW DWG 146N5089 & SRM 51-40-02. MAJOR REPAIR.

Part: FLOORBEAM — CORRODED (BS 1661) · corrosion level 2 · airframe 69,409 hrs · 25,335 cycles

MAIN DECK CARGO FLOORBEAM AT BS 1661 HAS SCRATCHED AREAS WITH NICKS & CORROSIONS ON UPPER TEE. REMOVED CORROSION IAW SRM 51-10-02, CHECKED LIMITS & FLOORBEAM AND FOUND TO BE OUT OF LIMITS IAW SRM 53-00-51 FIG 101 DETAIL III. R & R FLOORBEAM IAW DWG 146N4090 & SRM 51-40-02. MAJOR REPAIR.

Part: GATE — CORRODED (L4 DOOR) · airframe 69,409 hrs · 25,335 cycles

LEFT NR 4 PAX DOOR LOWER GATE HAS CORROSION. REMOVED CORROSION IAW SRM 51-10-02 ORIGINAL MATERIAL .160 AFTER REMOVAL .155, MATERIAL LOSS IS .005 FOUND TO BE WITHIN LIMITS IAW SRM 52-10-02 FIG 101 DET XII.

Part: FRAME — DENTED (FUSELAGE) · airframe 69,409 hrs · 25,335 cycles

AFT PIT BS 1520 STRINGER 21L FRAME INBD FLANGE DENTED. NO DENTS ALLOWED ON FREE FLANGE PER SRM 53-00-07, FIG. 101, FOUND OUT OF LIMITS PER SRM B757 53-00-07, FIG 101. REMOVED AND REPLACED FRAME IAW SRM 51-40-02 AND B757 DRAWING 146N1017, S26L - S26R. MAJOR REPAIR