N778FD

Part: FRAME — CRACKED (BS 1560 S26R) · airframe 81,456 hrs · 31,599 cycles

CRACK INDICATION NOTED ON FRAME WEB INBD OF S-26R STA 1560 AT 12 O'CLOCK ON FASTENER HOLE. CRACK MARKED IN RED. REPAIRED BY EA F-5310-T0378490 PT1 TITLE: FUSELAGE - MAINFRAME - CRACK FOUND ON FRAME STA 1560 AT S-27R. MAJOR REPAIR

Part: FLOORBOARD — DAMAGED (ZONE 200) · airframe 81,456 hrs · 31,599 cycles

ZONE 220 COURIER FLOORBOARD 222AF DAMAGED. FABRICATED ZONE 220 COURIER FLOORBOARD 222AF ON VT MAE TRAVELER T24/1738846 IAW DWG SRZ-25-005 REVISION "R" MAJOR REPAIR

Part: FLOORBOARD — DAMAGED (ZONE 20) · airframe 81,456 hrs · 31,599 cycles

ZONE 220 COURIER FLOORBOARD 222BF DAMAGED. FABRICATED ZONE 220 COURIER FLOORBOARD 222BF ON VT MAE TRAVELER T24/1738847 IAW DWG SRZ-25-005 REVISION "R" . MAJOR REPAIR

Part: FLOORBOARD — DAMAGED (MAIN CARGO) · airframe 81,456 hrs · 31,599 cycles

MAIN CARGO COMPT ZONE 230 FLOORBOARD PANEL 231MFF DAMAGED. FABRICATED ZONE 230 FLOORBOARD 231MFF ON VT MAE TRAVELER T24/1740237 IAW DWG SRZ- 25-005 REVISION "R". MAJOR REPAIR

Part: FLOORBOARD — DAMAGED (ZONE 200) · airframe 81,456 hrs · 31,599 cycles

ZONE 220 COURIER FLOORBOARD 221MBF DAMAGED. FABRICATED ZONE 220 COURIER FLOORBOARD 221MBF ON VT MAE TRAVELER T24/1738845 IAW DWG SRZ-25-005 REVISION "R" MAJOR REPAIR

Part: FLOORBOARD — DELAMINATED (MAIN DECK) · airframe 81,456 hrs · 31,599 cycles

MAIN DECK FLOOR PANEL 251MWF LOWER SURFACE DELAMINATED AND TORN. FABRICATED ZONE 250 FLOORBOARD PANEL 251MWF ON VT MAE TRAVELER T24/1741743 IAW DWG SRZ-25-005 REVISION "R". MAJOR REPAIR

Part: FLOOR PANEL — DAMAGED (ZONE 200) · airframe 81,456 hrs · 31,599 cycles

ZONE 220 CURIER FLOORBOARD 222MDF DAMAGED. FABRICATED ZONE 220 COURIER FLOORBOARD 222MDF ON VT MAE TRAVELER T24/1738850 IAW DWG SRZ-25-005 REVISION "R" MAJOR REPAIR.

Part: FLOOR PANEL — DAMAGED (COURIER AREA) · airframe 81,456 hrs · 31,599 cycles

ZONE 220 COURIER FLOORBOARD 222MAF DAMAGED. FABRICATED ZONE 220 COURIER FLOORBOARD 222MAF ON VT MAE TRAVELER T24/1738849 REVISION "R" IAW DWG SRZ-25-005. MAJOR REPAIR

Part: FLOOR PANEL — DAMAGED (ZONE 200) · airframe 81,456 hrs · 31,599 cycles

ZONE 220 COURIER FLOORBOARD 221BF DAMAGED. FABRICATED ZONE 220 COURIER FLOORBOARD 221BF ON VT MAE TRAVELER T24/1738844 REVISION "R" MAJOR REPAIR.

Part: FLOOR PANEL — DAMAGED (ZONE 200) · airframe 81,456 hrs · 31,599 cycles

ZONE 220 COURIER FLOORBOARD 221AF DAMAGED. FABRICATED ZONE 220 FLOORBOARD 221AF ON VT MAE TRAVELER T24/1738843 IAW DWG SRZ-25-005 REVISION "R" MAJOR REPAIR.

Part: BALL SCREW — FAILED (FLAP XMSSN) · airframe 81,076 hrs · 31,340 cycles

TE FLAP DISAGREE WHEN GOING TO FLAPS 25. COMPLETED QRH 9.1.17 LANDED FLAPS 20 ***EMERGENCY DECLARED*** ENT BY:5190314 RPT BY:5190314 R/I 12JUL23 22:37 MEM U REASON CODE : PREMATURE REMOVAL/INSTALLATION OFF MPN: 7820924 CPN: 2717624 POS: ONL ON MPN: 7821344 SRL: 5910 TAG NBR: 00I930 FACT 12JUL23 22:37 MEM U TSM: 27-51-00 AMM: 27-51-11-4 WHILE TROUBLESHOOTING THE FLAP WITH FIM 27-51 FT 808 FIG 105 FOUND INDICATOR TRIPPED ON LH #4 FLAP TRANSMISSION AND NOTICED THAT THE BALL SCREW THREADS WAS JAGGED AND WORN AND BALL NUT WAS FULL OF WATER. REMOVED AND REPLACED #4 LH BALL SCREW. OPS CHECKS GOOD. RESET TRANSMISSION INDICATOR. BALLSCREW NEW PN/ 7821344 SN/5910. OLD PART, THE TAG WAS DAMAGED AND ILLEGIBLE.

Part: TRANSMISSION — UNKNOWN (UNKNOWN) · airframe 80,990 hrs · 31,282 cycles

TE FLAP DISAGREE EICAS WHEN FLAPS 20 SELECTED AT APPROX 170 KIAS, FLAP INDICATION SHOWED BETWEEN 15 AND 20. COMPLETED QRH 9.1.17 AND LANDED USING FLAPS 20.EMERGENCY DECLARED. ***EMERGENCY DECLARED***. TROUBLESHOT IN REF TO FIM 27-51 FAULT TREE 808 WITH NO FAULTS NOTED. PERFORMED GVI OF THE L/H AND R/H FLAP DRIVE COMPONETS WITH NO FAULTS NOTED. REMOVED AND REPLACED THE L/H I/B #4 FLAP TRANSMISSION IAW AMM 27-51-06-4. OPS CHECK GOOD WITH NO FAULTS NOTED.

Part: GUST LOCK — DAMAGED (N/A) · airframe 80,987 hrs · 31,280 cycles

MDIS 778 52-10 6283 23APR23 MEM FACT U L1 GUST LOCK BROKEN. FACT 25APR23 17:35 GSO U AMM: 52-11-08-8 REPLACED L1 DOOR HOLD OPEN LOCK COLLAR IAW B757 AMM. INSTALLED PART: ALLIANCE AEROSPACE ENGINEERING SPLIT LOCK COLLAR P/N 10-N6008-1 S/N 23-0035. NO REMOVED PART.

Part: UNKNOWN — UNKNOWN (UNKNOWN) · airframe 80,981 hrs · 31,274 cycles

EMERGENCY DECLARED FOR TE FLAP DISAGREE. FLAP EXTENSION NORMAL TO 15 DEGREES. AT APPROX 175 KNOTS WE SELECTED FLAPS 20. THE FLAP INDICATOR MOVED TO APPROX 17 DEGREES AND STOPPED. TE FLAP DISAG EICAS MESSAGE WAS DISPLAYED. RAN QRH PROCEDURE AND LANDED WITH FLAPS 20. ***EMERGENCY DECLARED*** #4 FLAP TRANSMISSION OVERLOAD INDICATOR POPPED. RESET AND PLACED ON OIL PER FIM 27-51/808 AND TO RECHECKWITHIN 3 DAYS #4 FLAP DRIVE FOUND OVERLOAD BUTTON POPPED.

Part: NONE — NONE (N/A) · airframe 80,187 hrs · 30,715 cycles

MAIN CABIN SEAT TRACK SCALLOP IS GOUGED LBL0 AT APPROX STA 1013 ACCOMPLISHED FEDEX EA# F-5310-T0367542 : FUSELAGE - MAINFRAME - SEAT TRACK STA 1013, BL 0, SPLICE REPAIR

Part: NONE — NONE · corrosion level 2 · airframe 80,187 hrs · 30,715 cycles

AFT CABIN SHEAR WEB CORRODED AT FASTENER HOLES BS 1684 - BS 1720 BL 0 ACCOMPLISHED FEDEX EA # F-5310-T036757P1: FUSELAGE- MAINFRAME - DECK PLATE STA 1708 BL 0 CORROSION

Part: NONE — NONE (N/A) · airframe 80,187 hrs · 30,715 cycles

FLOOR PANEL REQ REWORK IAW FEDEX EA F-5310-T0367574 REWORKED FLOOR PANEL IAW FEDWX EA F-5310-T0367574 FUSELAGE - MAIN FRAME- DECK PLATE, STA 1708, BL 0, CORROSION

Part: FLAP — UNKNOWN (ZONE 600) · airframe 80,187 hrs · 30,715 cycles

PREVIOUS COMPSITE MAJOR REPAIR RW O/B FLAP, UPPER SURFACE, APPROX. 52" FROM THE I/B END AND 5.5" FROM T/E. REPAIR REQUIRES EVALUATION TO DETERMINE IF REPAIR IS ACCORDANCE WITH APPROVED DATA. REMOVED PREVIOUS REPAIR AND PERDORMED PERMANENT REPAIR IAW B757 SRM 57-53-01- 2R AND 51-70-04-0G. MAJOR REPAIR

Part: SKIN PANEL — UNKNOWN (ZONE 300) · airframe 80,187 hrs · 30,715 cycles

DURING AGING A/C INSPECTION, PERFORMED TAP TEST AND FOUND EXISTING REPAIR TO BE DISBANDED ON LEFT HORIZONTAL STAB LOWER SURFACE AT APPROX. STAB STA 214 AND 4' FROM FRONT SPAR. REMOVED PREVIOUS REPAIR AND PERFORMED PERMANENT REPAIR ON L/H HORIZONTAL STAB LOWER SKIN AT APPROX. STAB STA 214 IAW B757 SRM: 55-10-01-1A FIG 101 AND 51-70-10. MAJOR REPAIR

Part: FLAP — UNKNOWN (ZONE 600) · airframe 80,187 hrs · 30,715 cycles

PREVIOUS COMPOSITE MAJOR REPAIR RW O/B FLAP UPPER SURFACE APPROX 53" FROM I/B END AND 9.5" FROM T/E. REPAIR REQUIRES EVALUATION TO DETERMINE IF REPAIR IS IN ACCORDANCE WITH APPROVED DATA. REMOVED PREVIOUS REPAIR AND PERFOMED PERMANENT REPAIR IAW B757 SRM: 57-53-01-2R AND 51-70-04-0G. MAJOR REPAIR

Part: FLAP — UNKNOWN (ZONE 500) · airframe 80,187 hrs · 30,715 cycles

PREVIOUS COMPOSITE MAJOR REPAIR, L/W O/B FLAP UPPER SURFACE APPROX 42" FROM I/B END AND 5.5" FROM T/E; REPAIR REQUIRES EVALUATION TO DETERMINE IF REPAIR IS IN ACCORDANCE WITH APPROVED DATA. REMOVED PREVIOUS REPAIR AND APPLIED NEW REPAIR IAW B757 SRM 57-53-01-2R AND 51-70- 07-0G. MAJOR REPAIR

Part: FLAP — UNKNOWN (ZONE 500) · airframe 80,187 hrs · 30,715 cycles

PREVIOUS COMPOSITE MAJOR REPAIR. L/W O/B FLAP UPPER SURFACE APPROX 98" FROM I/B END AND 6.5" FROM T/E. REPAIR REQUIRES EVALUATION TO DETERMINE IF REPAIRS IS IN ACCORDANCE WITH APPROVED DATA. REMOVED PREVIOUS REPAIR AND APPLIED NEW REPAIR IAW B757 SRM 57-53-01-2R AND 51-70- 07-0G. MAJOR REPAIR

Part: FLAP — UNKNOWN (ZONE 600) · airframe 80,187 hrs · 30,715 cycles

PREVIOUS COMPOSITE MAJOR REPAIR R/W O/B FLAP UPPER SURFACE APPROX 95" FROM I/B END AND 7.5" FROM T/E. REPAIR REQUIRES EVALUATION TO DETERMINE IF REPAIR IS IN ACCORDANCE WITH APPROVED DATA. REMOVED PREVIOUS REPAIR AND PERFORMED PERMANENT REPAIR IAW B757 SRM 57-53-01-2R AND 51-70-04-0G. MAJOR REPAIR

Part: FLAP — UNKNOWN (ZONE 500) · airframe 80,187 hrs · 30,715 cycles

PREVIOUS COMPOSITE MAJOR REPAIR. L/W O/B FLAP UPPER SURFACE APPROX 36" FROM I/B END AND 10" FROM T/E. REPAIR REQUIRES EVALUATION TO DETERMINE IF REPAIRS IS IN ACCORDANCE WITH APPROVED DATA. REMOVED PREVIOUS REPAIR AND APPLIED NEW REPAIR IAW B757 SRM 57-53-01-2R AND 51-70- 07-0G. MAJOR REPAIR

Part: FLAP — UNKNOWN (ZONE 500) · airframe 80,187 hrs · 30,715 cycles

PREVIOUS COMPOSITE MAJOR REPAIR. L/W O/B FLAP UPPER SURFACE APPROX 83" FROM I/B END AND 8" FROM T/E. REPAIR REQUIRES EVALUATION TO DETERMINE IF REPAIRS IS IN ACCORDANCE WITH APPROVED DATA REMOVED PREVIOUS REPAIR AND APPLIED NEW REPAIR IAW B757 SRM 57-53-01-2R AND 51-70- 07-0G. MAJOR REPAIR

Part: WEB — DAMAGED (N/A) · airframe 80,187 hrs · 30,715 cycles

MAIN CARGO DOOR INNER WEB HAS DAMAGE FRO STA 500-520 REMOVED FABRICATED AND INSTALLED NEW WEB IAW BOEING DWG 65-49309 REV D

Part: WEB — DAMAGED (N/A) · airframe 80,187 hrs · 30,715 cycles

MAIN CARGO DOOR LOWER INNER WEB HAS DAMAGE FROM STA 580-590 REMOVED, FABRICATED AND INSTALLED NEW WEB IAW BOEING DWG 65-49309 REV D

Part: RUDDER — UNKNOWN (ZONE 300) · airframe 80,187 hrs · 30,715 cycles

PREVIOUS COMPOSITE MAJOR REPAIR ON THE L/H SIDE OF RUDDER APPROX 20" FROM T/E AND 36" FROM BOTTOM. REPAIR REQUIRES EVALUATION TO DETERMINE IF REPAIR IS IN ACCORDANCE WITH APPROVED DATA. REMOVED PREVIOUS REPAIR AND ACCOMPLISHED PERMANENT REPAIR TO L.H LOWER RUDDER SKIN IAW B757-200 SRM: 55-40-01-2R TABLE 1 AND 51-70-17-0G PAR 4.C. PRIMED AND PAINTED IAW B757-200 AMM: 51-21-10-7, 51-21-14-7 AND 51-21-15-7. NO WEIGHT CHANGE TO RUDDER WEIGHT AND BALANCE.

Part: NONE — NONE (N/A) · airframe 80,187 hrs · 30,715 cycles

MAIN CARGO DOOR INNER ACCESS PANEL HAS SCRATCHES AT APPROX STA 592 REMOVED, FABRICATED AND INSTALLED NEW ACCESS PANEL IAW BOEING DWG 65-49309 REV D

Part: STIFFENER — MISALIGNED (N/A) · airframe 80,187 hrs · 30,715 cycles

MAIN CABIN STIFFENER P/N 146N5376-7 REQUIRES TO BE FABRICATED PER PROD DWGS. FABRICATED MAIN CABIN STIFFENER, P/N 146N5376-7 IAW BAC DWG 146N5376 REV-

Part: SUPPORT — CRACKED (N/A) · airframe 80,187 hrs · 30,715 cycles

EMPENNAGE INTERIOR CROWN AREA APU INLET DUCT SUPPORT BRACKET CRACKED AT BS 1862 LOCATED & DRILLED NEW -1 SUPPORT BRACKET IAW BAC DWG 353N1043 REV A, ALODINED NEW -1 SUPPORT BRACKET IAW B757 SRM 51-20-01, PRIMED NEW -1 SUPPORT BRACKET IAW B757 SRM 51-20-01, PAINTED NEW -1 SUPPORT BRACKET IAW B757 AMM 51-20-01, INSTALLED NEW -1 SUPPORT BRACKET IAW BAC DWG 353N1043 REV A & B757 SRM 51-40-02..

Part: DOUBLER — CHAFED (N/A) · airframe 80,187 hrs · 30,715 cycles

R/W O/B FLAP L/E HAS A WORN AREA ON REPAIR DOUBLER 11IN I/B FROM O/B EDGE REPAIRED PER FEDEX EA # F-5750-T0322968 A

Part: FLAP — UNKNOWN (OTBD LWR FLAP) · airframe 80,187 hrs · 30,715 cycles

EXISTING COMPOSITE REPAIR ON R/WING OTBD FLAP, UPPER SURFACE, APPROX. 30" FROM INBD END AND 2.5" FROM T/E EXISTING COMPOSITE REPAIR ON R/WING OTBD FLAP, UPPER SURFACE, APPROX. 30" FROM INBD END AND 2.5" FROM T/E IS LOCATED ON A PRIMARY STRUCTURE PER B757-200 SRM 51-00-01-0G. COMPOSITE REPAIR RE-CLASSIFIED AS MAJOR

Part: NONE — UNKNOWN (HORIZ STAB) · airframe 80,187 hrs · 30,715 cycles

EXISTING COMPOSITE REPAIR ON L HORIZONTAL STAB. LWR SURFACE AT APPROX. STAB STA 214 AND 4" FROM FRONT SPAR EXISTING COMPOSITE REPAIR ON L HORIZONTAL STAB. LWR SURFACE AT APPROX. STAB STA 214 AND 4" FROM FRONT SPAR IS LOCATED ON A PRIMARY STRUCTURE PER B757-200 SRM 51-00-04-0G COMPOSITE REPAIR RE-CLASSIFIED AS MAJOR

Part: FLAP — UNKNOWN (OTBD LWR FLAP) · airframe 80,187 hrs · 30,715 cycles

EXISTING COMPOSITE REPAIR ON R/WING OTBD FLAP, LWR SURFACE T/E, APPROX 12" FROM INBD END AND 5" FROM T/E. EXISTING COMPOSITE REPAIR, R/WING OTBD FLAP, LWR SURFACE T/E, APPROX 12" FROM INBD END AND 5" FROM T/E., IS LOCATED ON A PRIMARY STRUCTURE PER B757-200 SRM 51-00-04-0G. COMPOSITE REPAIR RE-CLASSIFIED AS MAJOR

Part: FLOORBOARD — DELAMINATED (ZONE 200) · airframe 80,187 hrs · 30,715 cycles

MAIN CABIN STA 680/720 RBL 35 FLOOR PANEL TOP SURFACE DAMAGED. FABRICATED NEW PANEL 11862182-5 FLOOR PANEL IAW FED EX B757 SRZ-25-005 AND B757 SRM 53-00-50-1A FIG 101 TABLE 1.

Part: FLOORBOARD — DELAMINATED (ZONE 200) · airframe 80,187 hrs · 30,715 cycles

MAIN CABIN STA 640/680 RBL 35 FLOOR PANEL TOP SURFACE DAMAGED. FABRICATED NEW PANEL 11862181-92 MAIN CABIN FLOOR PANEL IAW FED B757 SRZ 25-005 AND SRM 53-00-50-1A FIG 101 TABLE 1.

Part: NONE — NONE (N/A) · airframe 80,187 hrs · 30,715 cycles

EXTERIOR FUSELAGE SKIN HAS AN OUTWARDLY PROTUDING DENT AT STA 1602 BETWEEN S16R AND S17R ACCOMPLISHED B757-2 SRM 53-00-51-2R REPAIR 29 - FIG 201 - SHEET 129 - CATEGORY B REPAIR

Part: SPOILER — DENTED (ZONE 500) · airframe 80,187 hrs · 30,715 cycles

LEFT WING #4 SPOILER I/B SIDE UPPER SURFACE IS DENTED REPAIRED LEFT WING #4 SPOILER UPPER SKIN DENT IAW B757 SRM: 57-70-01-2R REP 1 AND SRM 51-70-05.

Part: SEAL — CRACKED (ZONE 400) · airframe 80,187 hrs · 30,715 cycles

#2 ENGINE O/B CORE COWL PYLON SKIRT SPRING SEAL IS CRACKED. REMOVE AND REPLACED CRACKED SPRING SEAL PER BAC DWG 311N3570 REV G

Part: HOSE — RUPTURED (HYD SYSTEM) · airframe 80,140 hrs · 30,677 cycles

UPON LOWERING THE LANDING GEAR WE RECEIVED "L HYD PRESS" FOLLOWED BY "L HYD QTY" EICAS MESSAGES. HYD QTY WAS "0.00" ALONG WITH HYD PRESS "0". WE HAD ASSOCIATED "L YAW DAMPER" AND "RUDDER RATIO" MESSAGES. PERFORMED A GO AROUND, LEFT GEAR DOWN AND FLAPS 20. RAN QRH, SELECTED L ENG AND LEFT ELEC HYD PUMPS OFF. UPON LANDING WE HAD NO NOSE WHEEL STEERING. EMERGENCY WAS DECLARED. WHEN A/C ARRIVED FOUND LT GEAR DOWNLOCK HYDRAULIC HOSE RUPTURED. REMOVED AND REPLACED RUPTURED HYD LINE AND ADJACENT FLEX HOSE DUE TO CHAFFED CONDITION IAW AMM 32-32-02-4 AND AMM 20-11-00-2. ADJUSTMENT/RIG NOT ACCOMPLISHED OF ANY LANDING GEAR COMPONENT RII NOT REQUIRED. WITH GEAR PINS INSTALLED CYCLED GEAR HANDLE SEVERAL TIMES NO LEAKS NOTED COCKPIT INDICATIONS NORMAL REF AMM 32-32-02-4. REF WRI 09-10/5397 FOR GEAR PINS. ***

Part: BEAM — CRACKED (FUSELAGE) · airframe 78,586 hrs · 29,593 cycles

FWD CARGO STA 580 STUB BEAM IS CRACKED. LBL45.5 CUT OUT DAMAGED FLANGE ON FLOOR STUB BEAM STA 580 IAW FEDEX DWG SR57-53-004 REV -. FABRICATED, LOCATED, DRILLED AND INSTALLED ANGLE AND FILLER IAW FEDEX DWG SR57-53- 004 REV -. REF FEDEX EA F-5310-T0352978 P1 FUSELAGE - MAINFRAME - STA 580 FLOOR BEAM SPLICE SEGMENT UPPER AFT FLANGE CRACK REPAIR - REPAIR DOCUMENTATION & REPETITIVE INSPECTIONS PER

Part: FILTER — DEFECTIVE (CABIN) · airframe 78,554 hrs · 29,570 cycles

AFTER LANDING TOWARD END OF ROLLOUT, GOT FIRE EICAS MESSAGE AND FIRE MASTER WARNING INDICACTIONS. NO OTHER FIRE INDICATIONS. AS WE PULLED OFF RWY COCKPIT FILLED UP WITH SMOKE. FIRE INDICATION CLEARED. SHUT DOWN JET, RAN QRH FOR EMERG EVAC, AND EXITED LT SIDE VIA THE SLIDE. AIR RECIRCULATION FILTER AND EQUIPMENT COOLING FAN FILTER WAS REMOVED AND REPLACED BEFORE AND AFTER ENGINE RUN PER TSI. ENGINE RUN TO POWER PER JRH AS REQUESTED IN TSI WITH NO CONTAMINATES.

Part: WARNING MESSAGE — FALSE ACTIVATION (LT ENGINE BLEED) · airframe 77,270 hrs · 28,708 cycles

REJECTED TAKEOFF, DUE TO A LT ENG BLEED OFF MESSAGE. DURING TAXI BACK, CREW PERFORMED SYSTEM TESTED IAW MM 36-11-00-5. COULD NOT DUPLICATE. OPS CHECKED OKAY. NO HISTORY IN PAST 30 DAYS.

Part: FRAME — PUNCTURED (BS 231) · airframe 77,041 hrs · 28,530 cycles

BS 231 FRAME IS PUNCTURED. CUT OUT DAMAGED SECTION OF THE FRAME IAW SRM 53-00-07-2R, REP 7. REPAIRED IAW SRM 53-00-07-2R, REP 7, FIG 202.

Part: SLIDE — LOW PRESSURE (L1 DOOR) · airframe 76,274 hrs · 27,992 cycles

L1 DOOR ESCAPE SLIDE PRESSURE BELOW GREEN BAND. REMOVED AND REPLACED THE L1 DOOR SLIDE IAW AMM 25-66-01-6, SLIDE AND ARMING SYSTEM OPS CHECKED NORMAL IAW AMM 25-66-01-4

Part: RESERVOIR — LOW PRESSURE (L1 DOOR SLIDE) · airframe 76,270 hrs · 27,988 cycles

L1 DOOR ESCAPE SLIDE PRESSURE BELOW GREEN BAND. REMOVED AND REPLACED THE SLIDE, SLIDE AND ARMING SYSTEM OPS CHECKED NORMAL IAW AMM 25-66-01-4.

Part: REPAIR — DEBONDED (LT WING) · airframe 75,451 hrs · 27,413 cycles

EXISTING REPAIR WING, THERE IS A REPAIR AT LT SIDE OUTER WING, UPPER INTER SPAR SKIN AT WS 790. THIS REPAIR REQUIRES EVALUATION IAW EO F-5100-7-5001 A4 PT 1 ATTACHMENT B, NO HISTORY. EXISTING REPAIR WAS EVALUATED IAW ATTACHMENT B OF EO F-5100-7-5001 A5 PT 1 & FOUND REPAIR DISBONDED. REPAIR CARRIED OUT IAW SRM 51-70-10-2R PARA 8, 10, 11, 14, 15, 18 & 20 REV 117. REPAIR CLASSIFIED AS MAJOR.

Part: SKIN — DELAMINATED (RT WING TE FLAP) · airframe 75,451 hrs · 27,413 cycles

RIGHT INBD TE MAIN FLAP, UPPER OTBD ACCESS PANEL, UPPER SURFACE FOUND WITH MULTIPLE DENT MARKS & MULTIPLE DELAMINATED AREA. DAMAGED AREAS REMOVED, CLEANED & DRIED USING 150 DEG F PROCESS IAW SRM 57-53-01-2R DETAIL 1 REV 116 & SRM 57-70-10-2R REV 116. REPAIR PARTS FABRICATED & SURFACE TREATED WITH BOEGEL. INSTALLED USING 250 DEG F HOT BONDING PROCESS IAW SRM 51-70-10-2R REV 116. TAP TEST INSPECTION PERFORMED IAW SRM 57-10-06-2R REV 117, NO DISBOND NOTED. BONDED SKIN PANEL ASSEMBLY, UPPER, SRM REPAIR, RSC REPAIR TRACKING. REPAIR CLASSIFIED MAJOR IAW GMM 6-2-100.

Part: REGULATOR — DAMAGED (E&E BAY) · airframe 75,451 hrs · 27,413 cycles

FLIGHT CONTROLS, DURING BUY BACK, FOUND ELEVATOR TENSION REGULATOR SPRING GUIDE BROKEN. LT SIDE ELEVATOR TENSION REGULATOR R & R IAW AMM 27-31-12 REV 115. CONTROL CABLE FOR ELEVATOR TENSION REGULATOR REMOVED & INSTALLED AFTER MX IAW AMM 27-31-12 REV 115. ADJUSTMENT & OPERATIONAL TEST CARRIED OUT IAW AMM 27-31-00 REV 115 FOUND GOOD. REPAIR CLASSIFIED MINOR IAW GMM 6-2-100.

Part: BOLT — LOOSE (RUDDER SYS) · airframe 75,451 hrs · 27,413 cycles

FORWARD E & E COMPARTMENT, RT FWD RUDDER CONTROL QUADRANT LOWER MOUNT, THREE BOLTS PARTIAL INSTALLED FOUND DURING RUDDER SYS RIGGING. R & R IAW AMM 27-21-05 REV 114. R/H FWD RUDDER CONTROL QUADRANT BOTTOM BEARING HOUSING R & R IAW AMM 27-21-05 REV 114. RUDDER CABLE RA AND RB AT BS 580 - 600, DISCONNECTED & RECONNECTED AFTER RECTIFICATION IAW AMM 20-10-03 REV 114. CABLE ADJUSTMENT & OPERATION CHECK CARRIED OUT IAW AMM 27-21-00 REV 114, FOUND GOOD. REPAIR CLASSIFIED AS MINOR.

Part: SKIN — DENTED (FUSELAGE) · airframe 75,451 hrs · 27,413 cycles

FUSELAGE EXTERIOR SKIN RT SIDE, THERE IS AN EXISTING DENT WITH PREVIOUS OPERATOR STICKER AT BS 395 - 418, STRINGER 14 - 17. DENT FOUND OUT OF LIMITS IAW SRM 53-00-01-1A FIG 101 DET III REV 116. REPAIR CARRIED OUT IAW EA F-5330-T0323629 PART 1. FUSELAGE SKIN DENTS BETWEEN STATION 400 - 418 & STRINGER 14R - 17R. REPAIR CLASSIFIED AS MAJOR.

Part: BEAM — GOUGED (CARGO DOOR) · airframe 75,451 hrs · 27,413 cycles

NR 1 CARGO DOOR, LOWER EDGE BEAM HAS GOUGES. NR 1 CARGO DOOR LOWER EDGE BEAM REPLACED IAW EA F-5230-T0323763 P 1. REPAIR CLASSIFIED MAJOR IAW GMM 6-2-100.

Part: SKIN PANEL — DEBONDED (TE FLAP) · airframe 75,451 hrs · 27,413 cycles

EXISTING REPAIR WING. THERE IS A REPAIR AT RT SIDE INBD MAIN FLAP, UPPER PANEL AT MF STATION 300. THIS REPAIR REQUIRES EVALUATION IAW EO F-5100-7-5001 A4 PT 1, ATTACHMENT B. HISTORY 5100-9 DATED 12 1 2006. EXISTING REPAIR WAS EVALUATED IAW ATTACHMENT B OF EO F-5100-7-5001 A4 PT 1. FOUND EXISTING REPAIR DISBONDED. REPAIR CLASSIFIED AS MAJOR.

Part: SKIN — DAMAGED (LT WING) · airframe 75,451 hrs · 27,413 cycles

LEFT WING, AFT OVERWING ATTACH FITTING, ABOVE FRONT SPAR & NR 4 SLAT INBD MAIN TRACK REMOVAL, FOUND OSS 346 LE FIXED RIB COMMON TO WING UPPER SKIN LE LOCK FASTENER HOLE, ONE EACH, ELONGATED. LT WING OSS 346 LE FIXED RIB COMMON TO WING UPPER SKIN LE LOCK FASTENER HOLE CARRIED OUT IAW SRM 51-20-07 REV 117 & IAW EA F-5730--T0323164 P . REPAIR CLASSIFIED AS MINOR

Part: SEAT TRACK — CORRODED (BS 870-898) · corrosion level 2 · airframe 75,451 hrs · 27,413 cycles

BS 870 - 898, LBL 45.5, SEAT TRACK CROWN SUPPORT FOUND CORROSION AROUND THE BUSHING AREA. CORROSION EVALUATED & FOUND CORROSION MORE THAN 50% THROUGH EXCEED LIMIT IAW SRM 53-00-52 FIG 101 ALLOWABLE DAMAGE 1 REV 117. NEW SEAT TRACK SUPPORT FABRICATED IAW DWG 143N5480 SHT 3 REV & INSTALLED IAW DWG 143N5470 SHT 3 REV AT STATION 879 - 898, LBL 45.5. REPAIR CLASSIFIED MAJOR IAW GMM 6-2-100.

Part: FLOORBEAM — DAMAGED (BS 936) · airframe 75,451 hrs · 27,413 cycles

CABIN STATION 936, LBL 45.5, FLOORBEAM INNER FLANGE FOUND 01 ELONGATED FASTENER HOLE. REPAIRED IAW EA F-5310-T0322784 PART 1. REPAIR CLASSIFIED AS MAJOR.

Part: CREASE BEAM — CORRODED (FUSELAGE) · corrosion level 2 · airframe 75,451 hrs · 27,413 cycles

CABIN STATION 960 - 984 RT CREASE BEAM WEB FOUND CORROSION. CORROSION REMOVED IAW SRM 51-10-02 REV 116. REWORKED AREA, MEASURED ORIGINAL THICKNESS 0.063", REMAINING THICKNESS 0.053", MATERIAL REMOVED 0.010", FOUND OUT OF 10% LIMIT IAW SRM 53-40-13 FIG 101 ALLOWABLE DAMAGE 1 REV 116. REMOVED IAW SRM 51-40-02 REV 116 & REPLACED IAW DWG 144N5140 SHT 03 REV D. REPAIR IS CLASSIFIED MAJOR IAW GMM 6-2-100.

Part: DOOR SILL — DAMAGED (FUSELAGE) · airframe 75,451 hrs · 27,413 cycles

BS 360, R1 DOOR CUT OUT LOWER SILL WEB, FOUND ONE ELONGATED FASTENER HOLE. REPAIRED IAW DWG 141N8422 SHT 1 REV R. REPAIR CLASSIFIED MAJOR IAW GMM 6-2-100.

Part: SPLICE — CORRODED (BS 1140) · corrosion level 2 · airframe 75,451 hrs · 27,413 cycles

BS 1140 LT, CREASE BEAM INNER CHORD SPLICE FITTING, FOUND CORRODED. REMOVED IAW SRM 51-10-02 REV 116 & FOUND CORROSION MORE THAN 50% THROUGH. CREASE BEAM, INNER CHORD SPLICE FITTING REMOVED IAW SRM 51-40-02 REV 116. NEW CREASE BEAM, INNER CHORD SPLICE FITTING FABRICATED IAW DWG 144N5215 SHT 01 REV. INSTALLED IAW DWG 144N5200 SHT 01 REV B. REPAIR CLASSIFIED AS MAJOR.

Part: SKIN — WORN (FUSELAGE) · airframe 75,451 hrs · 27,413 cycles

EMPENNAGE, LT SIDE, THE HORIZONTAL STABILIZER BLADE SEAL PERIMETER HAS WEAR AT BS 1862 - 1875, ABOVE STRINGER 17. CHAFE REMOVED, FOUND OUT OF LIMIT IAW SRM 53-80-01 FIG 101 DETAIL VII REV 116. REPAIR CARRIED OUT IAW SRM 53-80-01-2R FIG 201 DETAIL II REV 117. REPAIR CLASSIFIED AS MAJOR.

Part: CREASE BEAM — CORRODED (FUSELAGE) · corrosion level 2 · airframe 75,451 hrs · 27,413 cycles

BS 1100 - 1120 LT CREASE BEAM WEB FOUND CORRODED. CORROSION REMOVED IAW SRM 51-10-02 REV 116. EVALUATION CARRIED OUT, ORIGINAL THICKNESS 0.063", REMAINING THICKNESS 0.055", FOUND OUT OF 10% LIMITS IAW SRM 53-40-13 ALLOWABLE DAMAGE 1 REV 116. CREASE BEAM WEB REMOVED IAW SRM 51-40-02 REV 116. CREASE BEAM WEB FABRICATED IAW DWG 144N5210 SHT 01 REV & INSTALLED IAW DWG 144N5200 SHT 01 REV B. REPAIR CLASSIFIED MAJOR IAW GMM 6-2-100.

Part: FITTING — CORRODED (FUSELAGE) · corrosion level 2 · airframe 75,451 hrs · 27,413 cycles

BS 1120 RT, CREASE BEAM INNER CHORD SPLICE, FITTING FOUND CORRODED. REMOVED IAW SRM 51-10-02 REV 116. NEW SPLICE FITTING FABRICATED IAW DWG 144N5215 SHT 01 REV. INSTALLED IAW DWG 144N5200 SHT 01 REV B. REPAIR CLASSIFIED AS MAJOR.

Part: CREASE BEAM — CORRODED (FUSELAGE) · corrosion level 2 · airframe 75,451 hrs · 27,413 cycles

BS 960 - 984 , LEFT CREASE BEAM WEB FOUND CORRODED. FOUND OUT OF LIMITS IAW SRM 53-40-13 ALLOWABLE DAMAGE 1 REV 116. REMOVED AND REPLACED IAW SRM 51-40-02 REV 116, AND DWG 144N5140 SHT 03 REV D. REPAIR CLASSIFIED AS MAJOR.

Part: FITTING — CORRODED (FUSELAGE) · airframe 75,451 hrs · 27,413 cycles

BS 1080 LT, CREASE BEAM INNER CHORD SPLICE, FITTING FOUND CRACKED & CORRODED. REMOVED IAW SRM 51-40-02 REV 116. NEW SPLICE FITTING FABRICATED IAW DWG 144N5215 SHT 01 REV. INSTALLED IAW DWG 144N5200 SHT 01 REV B. REPAIR CLASSIFIED AS MAJOR.

Part: FITTING — CRACKED (FUSELAGE) · airframe 75,451 hrs · 27,413 cycles

BS 1140 RT, CREASE BEAM INNER CHORD SPLICE, FITTING FOUND CRACKED. REMOVED IAW SRM 51-40-02 REV 116. NEW SPLICE FITTING FABRICATED IAW DWG 144N5215 SHT 01 REV. INSTALLED IAW DWG 144N5200 SHT 01 REV B. REPAIR CLASSIFIED AS MAJOR.

Part: CREASE BEAM — CORRODED (FUSELAGE) · corrosion level 2 · airframe 75,451 hrs · 27,413 cycles

BS 940 - 960 LT CREASE BEAM WEB FOUND CORRODED. CORROSION REMOVED IAW SRM 51-10-02 REV 116. EVALUATION CARRIED OUT ORIGINAL THICKNESS 0.056", REMAINING THICKNESS 0.034", FOUND OUT OF 10% LIMIT IAW SRM 53-40-13 ALLOWABLE DAMAGE 1 REV 116. CREASE BEAM WEB REMOVED IAW SRM 51-40-02 REV 116. NEW CREASE BEAM WEB FABRICATED IAW DWG 144N5140 SHT 03 REV D. INSTALLED IAW DWG 144N5140 SHT 03 REV D. REPAIR CLASSIFIED MAJOR IAW GMM 6-2-100.

Part: FITTING — CORRODED (FUSELAGE) · corrosion level 2 · airframe 75,451 hrs · 27,413 cycles

BS 1120 LT, CREASE BEAM INNER CHORD SPLICE, FITTING FOUND CRACKED & CORRODED. REMOVED IAW SRM 51-40-02 REV 116. NEW SPLICE FITTING FABRICATED IAW DWG 144N5215 SHT 01 REV. INSTALLED IAW DWG 144N5200 SHT 01 REV B. REPAIR CLASSIFIED AS MAJOR.

Part: CREASE BEAM — CORRODED (FUSELAGE) · corrosion level 2 · airframe 75,451 hrs · 27,413 cycles

BS 1080 - 1100 LT CREASE BEAM WEB FOUND CORRODED. CORROSION REMOVED IAW SRM 51-10-02 REV 116. EVALUATION CARRIED OUT, ORIGINAL THICKNESS 0.071", REMAINING THICKNESS 0.060", FOUND OUT OF 10% LIMITS IAW SRM 53-40-13 ALLOWABLE DAMAGE 1 REV 116. CREASE BEAM WEB REMOVED IAW SRM 51-40-02 REV 116. CREASE BEAM WEB FABRICATED IAW DWG 144N5210 SHT 01 REV & INSTALLED IAW DWG 144N5200 SHT 1 REV B. REPAIR CLASSIFIED MAJOR IAW GMM 6-2-100.

Part: FLOOR SUPPORT — CRACKED (BS 200-205) · airframe 75,451 hrs · 27,413 cycles

COCKPIT BS 200 - 205, RBL 35 - RBL 38, FLOOR SUPPORT FOUND CRACKED. REMOVED AND REPLACED IAW SRM 51-40-02 REV 116, AND DWG 141N5810 SHEET 1 REV G. REPAIR CLASSIFIED AS MAJOR.

Part: DOOR SILL — CORRODED (FUSELAGE) · corrosion level 2 · airframe 75,451 hrs · 27,413 cycles

BS 680 - 730, R2 DOOR CUT OUT LOWER SILL INNER CHORD FOUND CORRODED. CORROSION REMOVED IAW SRM 51-10-02 REV 116. EVALUATION CARRIED OUT, ORIGINAL THICKNESS 0.080", REMAINING THICKNESS 0.069", FOUND OUT OF 10% LIMITS IAW SRM 53-30-15 ALLOWABLE DAMAGE 1 REV 116. LOWER SILL INNER CHORD REMOVED IAW SRM 51-40-02 REV 116. NEW SILL INNER CHORD INSTALLED IAW DWG 143N8322 SHT 1 REV K & SHT 2 REV E. REPAIR CLASSIFIED AS MAJOR.

Part: CREASE BEAM — CORRODED (FUSELAGE) · corrosion level 2 · airframe 75,451 hrs · 27,413 cycles

CABIN STATION 1140 - 1160, LT CREASE BEAM WEB FOUND CORROSION. CREASE BEAM REMOVED AS PER SRM 51-10-02 REV 116. ORIGINAL THICKNESS 0.063" REMAINING THICKNESS 0.054". FOUND OUT OF 10% LIMIT AS PER SRM 53-40-13 ALLOWABLE DAMAGE 1 REV 116. CREASE BEAM WEB REMOVED AS PER SRM 51-40-02 REB 116. NEW CREASE WEB INSTALLED AS PER BOEING DRAWING 144N5200 SHT 02 REV B. REPAIR CLASSIFIED AS MAJOR.

Part: SEAT TRACK — CHAFED (BS 1165-1170) · airframe 75,451 hrs · 27,413 cycles

BS 1165 - 1170, RBL 45.5, SEAT TRACK FOUND CHAFED. REMOVED & FOUND OUT OF LIMITS IAW SRM 53-00-52 ALLOWABLE DAMAGE 1 REV 116, MEASURED LIP DISTANCE 0.49". SEAT TRACK, BETWEEN STATION 1075 - 1180, RBL 45.5 R & R WITH NEWLY FABRICATED SEAT TRACK IAW DWG 144N5001 SHT 3 REV A. FABRICATED SEAT TRACK IAW DWG 144N5021 SHT REV A PART 1 OF EA F-5310-T0323627A. THREE EACH EXTRA FASTENER HOLES FOUND PICKED UP ON EXISTING FLOORBEAM HORIZONTAL FLANGE AT STATION 1100, 1120 & 1140 COMPLIED WITH. REPAIR CLASSIFIED AS MAJOR.

Part: SEAT TRACK — CHAFED (BS 1165-1170) · airframe 75,451 hrs · 27,413 cycles

BS 1165 -1170, LBL 24.75 SEAT TRACK CROWN FOUND CHAFED. CHAFE REMOVED IAW SRM 51-10-02 REV 116. FOUND OUT OF LIMITS IAW SRM 53-00-52 ALLOWABLE DAMAGE 1 REV 116. SEAT TRACK REMOVED AND REPLACED IAW SRM 51-40-02 REV 116, DWG 144N5021 SHT 1 REV A, AND DWG 144N5001 SHT 03 REV A. REPAIR CLASSIFIED AS MAJOR.

Part: SEAT TRACK — CHAFED (BS 1165-1170) · airframe 75,451 hrs · 27,413 cycles

CABIN STATION 1165 - 1170, RBL 24.75, SEAT TRACK CROWN FOUND CHAFED. CHAFE REMOVED IAW SRM 51-10-02 REV 116. FOUND OUT OF LIMITS IAW SRM 53-00-52 ALLOWABLE DAMAGE 1 REV 116. SEAT TRACK REMOVED AND REPLACED IAW SRM 51-40-02 REV 116, DWG 144N5021 SHT 1 REV A, AND DWG 144N5001 SHT 03 REV A. REPAIR CLASSIFIED AS MAJOR.

Part: CREASE BEAM — CORRODED (FUSELAGE) · corrosion level 2 · airframe 75,451 hrs · 27,413 cycles

CABIN STATION 1140 - 1160, RT CREASE BEAM WEB FOUND CORROSION. CORROSION REMOVED IAW SRM 51-10-02 REV 116. ORIGINAL THICKNESS 0.063", REMAINING THICKNESS 0.053", FOUND OUT OF 10% LIMITS IAW SRM 53-40-13 ALLOWABLE DAMAGE 1 REV 116. CREASE BEAM WEB REMOVED IAW SRM 51-40-02 REV 116. CREASE BEAM WEB FABRICATED IAW DWG 144N5210 SHT 01 REV & INSTALLED IAW DWG 144N5200 SHT 2 REV B. REPAIR CLASSIFIED MAJOR IAW GMM 6-2-100.

Part: SEAT TRACK — CHAFED (FUSELAGE) · airframe 75,451 hrs · 27,413 cycles

CABIN STATION 982 - 990, RBL 24.75 SEAT TRACK CROWN FOUND CHAFED. SEAT TRACK CROWN REMOVED AS PER SRM 51-10-02 REV 116. EVALUATION CARRIED OUT REMAINING DIMENSION 0.17" AND FOUND OUT OF 0.26" LIMIT PER SRM 53-00-52 ALLOWABLE DAMAGE 1 REV 116. SEAT TRACK CROWN REPAIR CARRIED OUT AS PER SRM 53-00-52 FIG 201 REPAIR 4 REV 116. REPAIR CLASSIFIED AS MAJOR.

Part: SEAT TRACK — CHAFED (FUSELAGE) · airframe 75,451 hrs · 27,413 cycles

CABIN STATION 1180 - 1200, LBL 45.5 SEAT TRACK CROWN CHAFED. COMPLIED WITH EA F-5310-T0323360 A PART 1. OUT OF LIMIT CHAFED MARK FOUND ON SEAT TRACK LIP CROWN, AT STATION 1198, LBL 45.50. REPAIR CLASSIFIED MAJOR IAW GMM 6-2-100.

Part: FRAME — CORRODED (FUSELAGE) · corrosion level 2 · airframe 75,428 hrs · 27,408 cycles

AFT PIT BS 1480 FRAME CORRODED BETWEEN STRINGER 26 & 27 RT. REMOVED CORROSION IAW STM 51-10-02 & FOUND IT TO BE OUT OF LIMITS IAW SRM 53-02-07 & SRM 53-30-07. EA 130911 & ECRA 5360-01340 WERE ISSUED TO ADDRESS THE DAMAGE. IAW ECRA 5360-01340, THE BS 1480 BETWEEN STRINGER 25R & 28R HAS BEEN REPAIRED TO STAGE 1 & 2. A NEW FORM 8100-9 MUST BE RECEIVED & THE INSPECTION ACCOMPLISHED NOT LATER THAN 23531C FROM REPAIR EMBODIMENT PTC 50000. AIRPLANE SOLD AS IS ON 15 AUG 2014. BUYER WAS AWARE OF THIS ITEM PRIOR TO SALE BEING FINALIZED.

Part: SKIN — DENTED (FUSELAGE) · airframe 75,428 hrs · 27,408 cycles

FUSELAGE DENT 5 FT FWD OF DOOR 2L AT FLOOR LINE. MEASURES .75" X .062" DEEP. DENT IS CRACK FREE & MUST BE REPAIRED BY NEXT C CHECK. THE DENT WAS FOUND OUT OF LIMITS IAW SRM 53-00-03. THE REPAIR AT BS 605 - 618 FUSELAGE BETWEEN STRINGER 15L & 18L HAS BEEN APPROVED AS STAGE 1 & 2 VIA FORM 8100-9 DATED 8-6-13. A NEW 8100-9 MUST BE RCV'D PRIOR TO 48531C FROM REPAIR EMBODIMENT & PRIOR TO 75000 PTC OR THE AC WILL NO LONGER BE AIRWORTHY. THE REPAIR OF THIS AREA WAS DONE IAW EA 130905 ECRA 5330-04686. FOLLOW ON THE REPAIR THRESHOLD IS 75000 CYCLES AS DEFINED ABOVE. AIRPLANE SOLD AS IS ON 15 AUG 2014 BUYER WAS AWARE OF THIS ITEM PRIOR TO SALE BEING FINALIZED.

Part: FLOORBEAM — CORRODED (FUSELAGE) · corrosion level 2 · airframe 75,428 hrs · 27,408 cycles

FORWARD FUSELAGE STATION 324, RBL 59 HAS CORROSION AT FASTENER HOLES. BLENDED THE CORROSION & DETERMINED IT TO BE OUT OF LIMITS IAW SRM 51-10-02. EA 130893 & ECRA 5310-05820 WERE ISSUED TO ADDRESS THE DAMAGE. IAW ECRA 5310-05820 REV A, INSPECTION OF THE BS 324 FLOORBEAM SHALL BE ACCOMPLISHED IN 11031 CYCLES, 37500 PTS & EVERY 12000 CYCLES THEREAFTER. INSPECT IAW TABLES 1 & 2 OF ECRA 5310-05820. AIRPLANE SOLD AS IS ON 15 AUG 2014. BUYER WAS AWARE OF THIS ITEM PRIOR TO SALE BEING FINALIZED.