N578FE

Part: INDICATION SYS — FAULTY (FUEL SYSTEM) · airframe 75,940 hrs · 20,787 cycles

PDIS 578 28-41 3074 31OCT19 HNL OPEN U LOGPAGES:2605567 APPROX. 2.2 HRS INTO FLIGHT LEVEL 2 FUEL QTY/USED CHK ALERT CAME ON. COMPLIED WITH QRH PROCEDURE FUEL USED CALCULATING FUEL USED HAD FUEL AT 175K. FUEL GAUGES ADDED UP TO 166K. DIFF OF 9K. WE DETERMINED TNKS 12,3 WERE GOOD. SUSPECTED LEAK FROM AUX OR TAIL. AIR RETURN TO HNL. DUMPED APROX 12K FUEL FOR LND WT. PART 31OCT19 03:01 MC1 U IDENTIFIED PARTS CONTROL-FUEL QTY DATA MPN: 360-112-004 CPN: 2810158 QTY: 1 PART 31OCT19 03:02 MC1 U DELETED PARTS CONTROL-FUEL QTY DATA MPN: 360-112-004 CPN: 2810158 QTY: 1 UNIT PART 31OCT19 03:03 MC1 U IDENTIFIED PARTS CONTROL-FUEL QTY DATA MPN: 360-112-004 CPN: 2810158 QTY: 1 PART 31OCT19 03:04 MC1 U ORDER PART MPN: 360-112-004 CPN: 2810158 QTY: 1 MSN: 1991722 INFO 31OCT19 03:17 MEM R ********************MOCC UPDATE******************** PLEASE WORK IN CONJUNCTION WITH TSI: 28-40/3075 *************THANKS MOCC TECH SERVICES*************

Part: RESTRICTOR — MALFUNCTIONED (TE FLAP) · airframe 75,396 hrs · 20,610 cycles

AFTER TAKEOFF WHEN RETRACTING FLAPS RECEIVED LEVEL 2 FLAP DISAG. FLAP INDICATED 6,6,7,7 WITH HANDLE IN UP/0 EXT POSITION. RAN QRH. (DUMPED FUEL FROM 75.2 TO 50.0 POUNDS.) MATCHED UP FLAP HANDLE TO 7 MARK, BUT FLAP INDICATED 0. NORMAL LANDING. IDENTIFIED PARTS WING FLAP CONTROL VALVE. PLEASE REF IPC ITEM 340 IN 27-52-65-01, RESTRICTOR REQUIRED FOR T/S. P/N 6F3778. CHECKED BOTH FCCS, FOUND NO FAULT IN CURRENT AND LAST LEG. BOTH FCC AUTO FLT SYSTEM TEST PASSED AS PER AMM 22-00-00-5. PERFORMED FLAP OPS CK SEVERAL TIMES. R&R EXTEND RESTRICTOR P/N 6F2780 IN NR 2 HYD SYSTEM OF I/B FLAP CONTROL VALVE AND INBOARD FLAP CONTROL VALVE ASSY FOR PRECAUTION AS PER AMM 27-52-03-4, OPS CK NORMAL AS PER AMM 27-50-00-5.

Part: BATTERY — DISCHARGED (R1 DOOR) · airframe 75,205 hrs · 20,554 cycles

R1 DOOR SLIDE WILL NOT TEST. REPLACED BATTERIES IN R1 DOOR SLIDE REMOTE PRESSURE INDICATOR REFERENCE AMM 25-61-04-4. OPS CHECKS GOOD REFERENCE AMM 25-61-04-5.

Part: SEAT TRACK — DAMAGED (FUSELAGE) · airframe 74,765 hrs · 20,434 cycles

REFERENCE WORK ROUTINE ITEM # 25502426, MAIN DECK CARGO COMPARTMENT FLOOR SEAT TRACK FOUND WITH BROKEN LOBE AT STATION 1673 X = - 8 ( MEL # 25-57-02-B ) MAIN DECK CARGO COMPARTMENT DAMAGED SEAT TRACK AT STATION 1673 X = - 8 REPAIRED BY SECTIONAL SEAT TRACK REPLACEMENT FROM STATION 1709 TO EXISTING SPLICE AT STATION 1664 X = - 8 AS PER SRM 53-00-52-2R FIGURE 201 REPAIR 1. REPAIR CLASSIFIED AS MAJOR PER GMM 6-2-100.

Part: BATTERY PACK — WEAK (EMERGENCY LIGHTS) · airframe 74,217 hrs · 20,273 cycles

EMER LT BAT 1 LO. PART 25FEB19 10:27 ICN U IDENTIFIED PARTS EMERG EXIT LIGHTS " RELEASED FOR SERVICE PER MEL : 33-50-04 CATEGORY : C EXPIRATION : 07MAR19 MEL 33-50-04: EMER LIGHTS - INOP." THE PART NIS IN ICN.

Part: CONTROLLER — MALFUNCTIONED (ANTI-ICE SYS) · airframe 74,014 hrs · 20,212 cycles

PDIS 578 30-10 1981 01JAN19 MEM FACT U LOGPAGES:2850976 ON CLIMBOUT PRIOR TO ENTERING CLOUDS WE SELECT AIRFRAME AND ENGINE ANTI ICE ON. GOT A/I DISAG. ALERT AND YELLOW ON RIGHT WING ANTI ICE VALVE. NO ICEING ENCOUNTERED SELECTED ANTI-ICE OFF AND NOW SHOW RIGHT WING ANTI-ICE IN YELLOW ON DISPLAY. FACT 01JAN19 12:11 MEM U TROUBLE SHOOT INDICATION ISSUE PER SYSTEM SCAMATIC MANUAL. LAST PART TO OPS CHECK BEFORE CHECKING WIRING WAS THE ESC. R&R ESC PER MM REF 21-08-01-4, INDICATION CLEARED AND ESC OPS CHECKED GOOD. A/C IS OK FOR SERVICE,

Part: FUEL SYS — UNKNOWN · airframe 73,815 hrs · 20,165 cycles

SUSPECTED FUEL LEAK ENROUTE 2 HOURS INTO FLIGHT FUEL WAS 4000 LBS LOWER THAN EXPECTED. 15 MINUTES LATER RECEIVED FUEL QTY CHK ALERT. RAN QRH CHECKLIST & DETERMINED LEAK WAS IN UPPER AUX ESTIMATE 10000 LBS OF FUEL LEAKED.PULLED AND RESET FUEL QTY NORMAL POWER AND FUEL QTY ALTN POWER CBS & CONFIRMED FUEL QUANTITY GAUGES WERE WORKING PROPERLY. DECLARED EMERGENCY, DUMPED 47.6 OF FUEL & RTB. NO EXTERNAL LEAKS NOTED. VERIFIED FUEL WITH FUEL STICKS, OK. SUMPED ALL TANKS , NO CONTAMINATION. BITE CHECK OF FQBU IAW AMM 28-41-00-5, NO FAULTS. PERFORMED RTS OF FSC IAW AMM 28-08-01-5 NO FAULTS, TRANFERRED FUEL BETWEEN TANKS & VERFIED QTY WITH FUEL STICKS, OK. TANK QTY &TOTALIZER HAS REMAINED STABLE.

Part: WARNING SYSTEM — ACTIVATED (COCKPIT) · airframe 73,212 hrs · 19,980 cycles

ALT FL350 CABIN ALTITUDE LEVEL 3 ALERT. FASE 1S TO QRH. REF FIM 21-33-00-2 FIG 103 CHECKED BOTH CPC'S FOR BLOCKAGE AND NONE FOUND. CFDS FAULTS ACC1 WITH PK 1 RAD ACT IN LAST LEG BUT NO CURENT FAULTS. DEFERED PACK NR 1 RAM AIR ACTUATOR WRI 21-52-1583. PERFORMED RTS ON ACC1, ACC2, ACC3, ESC, CPC1, CPC2 WITH NO FAULTS NOTED. CPC2 WAS ACTIVE WHEN FAULT ACCURED. R/R NR 2 CPC AS PRECAUTION REF AMM 21-31-04-2. ALL TEST GOOD REF AMM 21-62-01-5 AND 21-08-01-5. A/C OK FOR SERVICE

Part: LONGERON — CORRODED (FUSELAGE) · corrosion level 2 · airframe 72,642 hrs · 19,812 cycles

LOWER CENTER CARGO BILGE AREA FOUND LONGERON 43R WITH CORROSION, AT STA 1649. CARRIED OUT SECTIONAL SPLICE REPAIR BETWEEN STA 1631 TO STA 1650 LONGERON 43R AS PER SRM 53-00-05-2R REPAIR 1 FIGURE 201 AND FIGURE 202. REPAIR CLASSIFIED AS MAJOR PER GMM 6-2-100. CORROSION ON LONGERON 43R REMOVED AND FOUND OUT OF LIMITS AS PER SRM 53-00-00-2R FIGURE 205. ORIGINAL THICKNESS: 0.068" , MATERIAL REMOVED: 0.060", MATERIAL REMAINING: 0.008".

Part: STRUCTURE — CRACKED (BS 2007) · airframe 72,642 hrs · 19,812 cycles

AFT FUSELAGE FWD UPPER TORQUE BOX RT ACCESS CUTOUT FOUND THE EDGE CRACKED. REPAIRED IAW SRM 53-70-02-2R, FIGURE 201, REPAIR 3. THE REPAIR WAS CLASSIFIED AS MAJOR IAW GMM 6-2-100.

Part: SKIN — CRACKED (LT WING) · airframe 72,642 hrs · 19,812 cycles

DURING HFEC INSPECTION ON LT WING FIXED LEADING EDGE SKIN ADJACENT TO CUTOUT AND ACCESS DOORS, CRACKS FOUND APPROX 1/8 INCH IN LENGTH AT CORNER NR 5 AT SLAT ACTUATOR ACCESS DOOR FWD INBD CORNER, AT STA XOS 490.850. REPAIR CARRIED OUT AT LT WING FIXED LEADING EDGE SKIN PER SRM 57-40-01-2R FIG 201 REPAIR 17. REPAIR CLASSIFIED AS MAJOR PER GMM 6-2-100.

Part: SEAT TRACK — CRACKED (BS 635) · airframe 72,642 hrs · 19,812 cycles

FWD CABIN SEAT TRACK FOUND CRACKED AT BS 635 LBL 8.5. REPLACED THE SEAT TRACK BETWEEN BS 625 - 665 IAW SRM 53-00-52-2R FIGURE 201 REPAIR 1. REPAIR CLASSIFIED AS MAJOR IAW GMM 6-2-100.

Part: SEAT TRACK — CRACKED (BS 635) · airframe 72,642 hrs · 19,812 cycles

FWD CABIN SEAT TRACK WAS FOUND CRACKED AT BS 635, RBL 8.5. THE SEAT TRACK WAS REPLACED BETWEEN BS 625 TO 665 IAW SRM 53-00-52-2R, FIGURE 201 REPAIR 1. THE REPAIR WAS CLASSIFIED AS MAJOR IAW GMM 6-2-100.

Part: SEAT TRACK — CRACKED (BS 635) · airframe 72,642 hrs · 19,812 cycles

FWD CABIN SEAT TRACK FOUND CRACK AT BS 635, 27.5. THE SEAT TRACK WAS REPLACED BETWEEN BS 625 - 665 IAW SRM 53-00-52-2R, FIGURE 201, REPAIR 1. THE REPAIR WAS CLASSIFIED AS MAJOR IAW GMM 6-2-100.

Part: SEAT TRACK — CORRODED (BS 1311) · corrosion level 2 · airframe 72,642 hrs · 19,812 cycles

CABIN, MAIN DECK CARGO SEAT TRACK CORRODED, BS 1311, RBL 27.5. CORROSION REMOVED AND FOUND TO BE OUT OF LIMITS IAW SRM 53-00-52-1A, FIGURE 101, ALLOWABLE DAMAGE 1. THE SEAT TRACK WAS REPLACED, BS 1266 TO 1331 IAW SRM 53-00-52-2R, FIG 201, REPAIR 1. REPAIR CLASSIFIED AS MAJOR IAW GMM 6-2-100.

Part: SEAT TRACK — CRACKED (FUSELAGE) · airframe 72,642 hrs · 19,812 cycles

FWD CABIN SEAT TRACK FOUND CRACK AT STA 635 X= 47.5 AS MARKED. SEAT TRACK REPAIRED BY SECTIONAL REPLACEMENT FROM STA 605 TO STA 645 X= 47.5 AS PER SRM 53-00-52 FIGURE 201 REPAIR 1. REPAIR CLASSIFIED AS MAJOR PER GMM 6-2-100.

Part: WEB — CRACKED (BS 1841) · airframe 72,642 hrs · 19,812 cycles

BS 1841, LONGERON 46L WEB WAS FOUND CRACKED. REPAIRED IAW SRM 53-00-00-2R, FIGURE 211, REPAIR GENERAL. THE REPAIR WAS CLASSIFIED AS MAJOR IAW GMM 6-2-100.

Part: SEAL — CHAFED (RT WING) · airframe 72,642 hrs · 19,812 cycles

RT WING DROOP LEADING EDGE INBD METAL SEAL CHAFED AT STA XDLE 310. REPAIR CARRIED OUT AT R WING DROOP LEADING EDGE INBD SIDE AS PER SRM 57-40-01-2R FIGURE 202 REPAIR 15. REPAIR CLASSIFIED AS MAJOR PER GMM 6-2-100.

Part: WEB — CRACKED (BS 1841) · airframe 72,642 hrs · 19,812 cycles

BS 1841, LONGERON 46R WEB WAS FOUND CRACKED. REPAIRED IAW SRM 53-00-00-2R, FIGURE 211, REPAIR GENERAL. THE REPAIR WAS CLASSIFIED AS MAJOR IAW GMM 6-2-100.

Part: DOUBLER — CRACKED (LT WING) · airframe 72,642 hrs · 19,812 cycles

LT WING LEADING EDGE CAVITY BEADED DOUBLER AT STA XOS 663 FOUND CRACKED. REPAIR CARRIED OUT AT LT WING LEADING EDGE CAVITY BEADED DOUBLER AT XOS 663 AS PER SRM 57-40-02-2R FIGURE 203 REPAIR 15. REPAIR CLASSIFIED AS MAJOR AS PER GMM 6-2-100.

Part: DOUBLER — CRACKED (RT WING) · airframe 72,642 hrs · 19,812 cycles

RT WING LEADING EDGE CAVITY BEADED DOUBLER AT XOS 613 WAS FOUND CRACKED. REPAIRED THE DOUBLER IAW SRM 57-40-02-2R, FIGURE 203, REPAIR 15. THE REPAIR WAS CLASSIFIED AS MAJOR IAW GMM 6-2-100.

Part: FRAME — CHAFED (BS 535) · airframe 72,642 hrs · 19,812 cycles

MAIN DECK CARGO, FRAME CHAFED AT BS 535, LONGERON 24R. THE FRAME WAS REPAIRED IAW SRM 53-20-07-2R, FIGURE 201, REPAIR 1. THE REPAIR WAS CLASSIFIED AS MAJOR IAW GMM 6-2-100.

Part: FRAME — CHAFED (BS 535) · airframe 72,642 hrs · 19,812 cycles

MAIN DECK CARGO FRAME WAS CHAFED AT BS 535, LONGERON 19R. REPAIRED THE FRAME IAW SRM 53-20-07-2R, FIGURE 202, REPAIR 1. REPAIR CLASSIFIED AS MAJOR IAW GMM 6-2-100.

Part: TRIM CYLINDER — CONTAMINATED (MLG) · airframe 72,399 hrs · 19,722 cycles

PDIS 578 32-30 0989 20APR18 CDG OPEN U LOGPAGES:2925462 AFTER TAKEOFF LANDING GEAR WOULD NOT RETRACT. GEAR HANDLE WOULD NOT MOVE TO UP POSITION. RAN QRH "GEAR HANDLE WILL NOT MOVE TO UP POSITION "NO HELP. RETURNED TO LAND LFPG. ALSO WHEN PUSHING HANDLE RELEASE BUTTON GEAR HANDLE WILL NOT MOVE. SHGN 20APR18 04:06 CDG U T/S IN PROGRESS FACT 20APR18 08:26 CDG PERFORMED T/S PER FIM 32-30-23-00. PERFORMED STEP 2 PER MM 32-37-03-4 BLEED OF THE TRIM CYLINDER RELIEF VALVE AND OPS CHECK OF THE TRUCK BEAM TRIM INTERLOCK CYLINDER PER MM 32-37-00-5 STEP C. AFTER BLEEDING THE LDG HANDLE GOES FROM DOWN TO UP POSITION EASILY WITH PINS INSTALLED THE LANDING GEAR SHOWING MOVEMENT. A/C OK FOR SERVICE.

Part: ACTUATOR — SHEARED (NLG) · airframe 71,519 hrs · 19,445 cycles

ON TAKE OFF, NOSE GEAR DID NOT RETRACT. HEARD RUMBLING NOISE. UNSAFE NOSE GEAR UP INDICATION. L/H STEERING ACTUATOR EYE END FOUND BROKEN. ACTUATOR REPLACED IAW MD11 MM 32-52-30-4. L/CHK C/OUT NIL LEAK FOUND.

Part: SWITCH — LOOSE (COCKPIT) · airframe 71,187 hrs · 19,344 cycles

FOUND WIRES LOOSE ON NR 1 ENG AGENT 1. REMOVED AND REPLACED ENGINE 1, AGENT 1 DISCHARGE SWITCH S1-161 PER AMM 26-21-02-4. SYSTEM OP CHECKS GOOD PER 26-21-01-5. SWITCH PART NUMBER BZ2RT, NO SERIAL NUMBER, MANUFACTURER, MICRO. REMOVED AND REPLACED ENGINE 1, AGENT 1 DISCHARGE SWITCH S1-161 PER AMM 26-21-02-4. SYSTEM OP CHECKS GOOD PER 26-21-01-5. SWITCH PART NUMBER BZ2RT, NO SERIAL NUMBER, MANUFACTURER, MICRO.

Part: WARNING SYSTEM — FALSE ACTIVATION (CARGO DOOR) · airframe 70,491 hrs · 19,128 cycles

DURING CLIMBOUT, RECIEVED A LEVEL 2 FWD CARGO DOOR B ALERT. CARGO DOOR FWD CARGO DOOR B ALERT (IDENTIFY) ALERT -INOP. VERIFY DOOR IS CLOSED AND LOCKED PRIOR TO BLOCK-OUT.

Part: HINGE — WORN (CARGO DOOR) · airframe 70,487 hrs · 19,125 cycles

CENTER CARGO DOOR HINGE WORN. REPLACED THE DOOR.

Part: TIRE — FAILED (NR 6) · airframe 69,585 hrs · 18,853 cycles

35 MINUTES INTO FLIGHT, RECEIVED A TIRE FAILURE ALERT. THE NR 6 TIRE INDICATIONS WENT BLANK. REMOVED AND REPLACED THE NR 6 TIRE AND WHEEL ASSMBLY. TIRE PRESSURE CHECKED OK ON CONFIGURATION PAGE.

Part: PROXIMITY SENSOR — MALFUNCTIONED (CARGO DOOR) · airframe 68,876 hrs · 18,618 cycles

DURING FLIGHT, RECEIVED A LEVEL 2 CARGO DOOR FWD B ALERT . RAN THE QRH AND THE ALERT REMAINED ON AND RETURNED TO DEPARTURE. R & R THE FORWARD LOWER CARGO DOOR PROXIMITY SENSOR IAW AMM 52-70-01-4. DOOR OPERATED NORMALLY IN OPEN/CLOSE MODE. ELECTRICAL TEST OF THE FORWARD LOWER CARGO DOOR VERIFIED GOOD IAW AMM 52-31-04-700-801. ALL DOOR TEST FROM OVERHEAD IN COCKPIT RETURNED SATISFACTORY TEST ON TWO SEPERATE TESTS. OK FOR SERVICE.

Part: BRACKET — CRACKED (FUSELAGE) · airframe 68,077 hrs · 18,334 cycles

MAIN DECK CARGO, WHILE ACCOMPLISHING WORK CARD E1-2840-7-5006 A2 P2 R3, PLUG DOOR LOWER JAMB AREA FOUND 01 EA BRACKET CRACK AS MARKED AT STA 1305.250, Z=-19. BRACKET REPAIRED IAW EA NR 1-5310-T0326074 P1. FUSELAGE MAINFRAME, R3 DOOR INNER JAMB, EXISTING ANGLE AT STA 1305.250, Z = -19, FOUND CRACKED. REPAIR CLASSIFIED AS MAJOR IAW GMM 6-2-100. REF WRI 53107783 FOR WORK DETAIL.

Part: SEAT TRACK — DAMAGED (FUSELAGE) · airframe 68,077 hrs · 18,334 cycles

MAIN DECK CARGO APPROXIMATE AT STA 5-4, X=-8.75 SEAT TRACK CROWN FOUND DAMAGED. SEAT TRACK REPAIRED BY SECTIONAL REPLACEMENT FROM STA 5-0 TO STA 5-63, X = -8.75 IAW SRM 53-00-52-2R, FIG 201, REPAIR 1. REPAIR CLASSIFIED AS MAJOR IAW GMM 6-2-100.

Part: SKIN — CRACKED (LT WING) · airframe 68,077 hrs · 18,334 cycles

02 EA, 10, NR 11, FASTENER HOLES FOUND CRACK INDICATION DURING OPEN-HOLE HFEC INSPECTION AT LT WING LOWER SKIN ACCESS DOOR CUTOUT BETWEEN STA XORS =683.4 AND STA XORS =713.6. CARRIED OUT BUSHING REPAIR IAW SRM 57-20-02-2R, FIG 201 REPAIR 5. THE INITIAL INSPECTION NEEDED TO BE CARRIED OUT AT 2000 FLT CYCLES. REPETITIVE INSPECTION WILL BE CARRIED OUT AT EVERY 2000 FLT CYCLES IAW SRM 57-20-02-2R, TABLE 201, FIG 202 REPAIR 5. THE REPAIR CLASSIFIED MAJOR IAW GMM 6-2-100.

Part: RIB — CRACKED (LT WING) · airframe 68,077 hrs · 18,334 cycles

LEFT FIXED L/E COMPARTMENT AT STA XOS 667, FOUND RIB CRACKED. RIB R & R IAW SRM 51-31-01-0G. THE NEW RIB FABRICATED IAW DWG ARB2930, REV "F". THE REPAIR CLASSIFIED AS MAJOR IAW GMM6-2-100.

Part: SKIN — CRACKED (RT WING) · airframe 68,077 hrs · 18,334 cycles

12 EA, NR 7, 8, 9, 10, 11, 12, 13, 14, 28, 32, 33, 34, FASTENER HOLES FOUND CRACK INDICATION DURING OPEN-HOLE HFEC INSPECTION AT RT WING LOWER SKIN ACCESS DOOR CUTOUT BETWEEN STA XORS =683.4 AND STA XORS =713.6. CARRIED OUT BUSHING REPAIR IAW SRM 57-20-02-2R, FIG 201 REPAIR 5. THE INITIAL INSPECTION TO BE CARRIED OUT AT 2000 FLT CYCLES, REPETITIVE INSPECTION WILL BE CARRIED OUT AT EVERY 2000 FLT CYCLES IAW SRM 57-20-02-2R, TABLE 201, FIG 202, REPAIR 5. THE REPAIR CLASSIFIED AS MAJOR IAW GMM 6-2-100.

Part: SEAT TRACK — DAMAGED (FUSELAGE) · airframe 68,077 hrs · 18,334 cycles

MAIN DECK CARGO COMPARTMENT, APPROXIMATELY AT STA 1285, X=-8.75 SEAT TRACK CROWN FOUND DAMAGED. SEAT TRACK REPLACEMENT IAW SRM 53-00-52-2R, FIG 201, REPAIR 1. REPAIR CLASSIFIED AS MAJOR IAW GMM6-2-100.

Part: SEAT TRACK — DAMAGED (FUSELAGE) · airframe 68,077 hrs · 18,334 cycles

MAIN DECK CARGO COMPARTMENT, APPROXIMATELY AT BS 1341, X= 27.5 SEAT TRACK CROWN FOUND DAMAGED. SEAT TRACK REPLACEMENT FROM STA 1311 TO STA 1351, X=27.5 IAW SRM 53-00-52-2R, FIG 201, REPAIR 1. REPAIR CLASSIFIED AS MAJOR IAW GMM 6-2-100.

Part: SEAT TRACK — DAMAGED (FUSELAGE) · airframe 68,077 hrs · 18,334 cycles

MAIN DECK CARGO COMPARTMENT, APPROXIMATELY AT STA 1149, X= 27.5, SEAT TRACK CROWN FOUND DAMAGED. SEAT TRACK REPAIRED BY SECTIONAL REPLACEMENT IAW SRM 53-00-52-2R, FIG 201, REPAIR 1. REPAIR CLASSIFIED AS MAJOR IAW GMM 6-2-100.

Part: SEAT TRACK — DAMAGED (FUSELAGE) · airframe 68,077 hrs · 18,334 cycles

MAIN DECK CARGO COMPARTMENT, APPROXIMATELY AT STA 6-4, X= 27.5, SEAT TRACK CROWN FOUND DAMAGED. FLOOR SEAT TRACK REPAIRED BY SECTIONAL REPLACEMENT FROM STA 6-0 TO STA 6-40, X=27.5 IAW SRM 53-00-52-2R, FIGURE 201, REPAIR 1. REPAIR CLASSIFIED AS MAJOR IAW GMM 6-2-100.

Part: SEAT TRACK — DAMAGED (FUSELAGE) · airframe 68,077 hrs · 18,334 cycles

MAIN DECK CARGO COMPARTMENT. APPROXIMATELY AT STA 1159, X=75.5 SEAT TRACK CROWN FOUND DAMAGED. SEAT TRACK REPAIRED BY SECTIONAL REPLACEMENT FROM STA 6-100 TO STA 1169, X =75.5 IAW SRM 53-00-52-2R FIG 201, REPAIR 1. REPAIR CLASSIFIED AS MAJOR IAW GMM 6-2-100.

Part: SEAT TRACK — DAMAGED (FUSELAGE) · airframe 68,077 hrs · 18,334 cycles

MAIN DECK CARGO COMPARTMENT, APPROXIMATELY AT STA 755, X=-8.75, SEAT TRACK CROWN FOUND DAMAGED. SEAT TRACK REPAIRED BY SECTIONAL REPLACEMENT FROM STA 745 TO STA 783 X = -8.75 IAW SRM 53-00-52-2R, FIG 201, REPAIR 1. REPAIR CLASSIFIED AS MAJOR IAW GMM 6-2-100.

Part: SEAT TRACK — DAMAGED (FUSELAGE) · airframe 68,077 hrs · 18,334 cycles

MAIN DECK CARGO COMPARTMENT, APPROXIMATELY AT STA 5-53, X= 47.5, SEAT TRACK CROWN FOUND DAMAGED. SEAT TRACK REPLACEMENT IAW SRM 53-00-52-2R, FIG 201, REPAIR 1. REPAIR CLASSIFIED AS MAJOR IAW GMM 6-2-100.

Part: SEAT TRACK — DAMAGED (FUSELAGE) · airframe 68,077 hrs · 18,334 cycles

MAIN DECK CARGO COMPARTMENT, APPROXIMATELY AT STA 1520, X=47.5, SEAT TRACK CROWN FOUND DAMAGED. SEAT TRACK REPLACEMENT FROM STA 1491 TO STA 5-0, X=47.5 IAW SRM 53-00-52-2R, FIG 201, REPAIR 1. REPAIR CLASSIFIED AS MAJOR IAW GMM 6-2-100.

Part: SEAT TRACK — DAMAGED (FUSELAGE) · airframe 68,077 hrs · 18,334 cycles

MAIN DECK CARGO COMPARTMENT, APPROXIMATELY AT STA 1531/5-4, X= 8.75 SEAT TRACK CROWN FOUND DAMAGED. SEAT TRACK REPLACEMENT IAW SRM 53-00-52-2R, FIG 201, REPAIR 1. REPAIR CLASSIFIED AS MAJOR IAW GMM 6-2-100.

Part: SEAT TRACK — DAMAGED (FUSELAGE) · airframe 68,077 hrs · 18,334 cycles

MAIN DECK CARGO COMPARTMENT, APPROXIMATELY AT BS 1299, X= 8.5 SEAT TRACK CROWN FOUND DAMAGED. SEAT TRACK REPAIRED IAW SRM 53-00-52-2R, FIG 201, REPAIR 1. REPAIR CLASSIFIED AS MAJOR IAW GMM 6-2-100.

Part: DOUBLER — CRACKED (LT WING) · airframe 68,077 hrs · 18,334 cycles

LEFT WING FIXED L/E COMPARTMENT AT STA 702, BEADED DOUBLER FOUND CRACKED. DOUBLER REPAIRED IAW SRM 57-40-02-2R, FIG 203, REPAIR 15. THE REPAIR CLASSIFIED AS MAJOR IAW GMM 6-2-100.

Part: DOUBLER — CRACKED (RT WING) · airframe 68,077 hrs · 18,334 cycles

RT WING FIXED L/E COMPARTMENT AT STA 627 BEADED DOUBLER CRACKED. CRACKED BEADED DOUBLER REPAIRED IAW SRM 57-40-02-2R, FIG 203, REPAIR 15. THE REPAIR CLASSIFIED MAJOR IAW GMM 6-2-100.

Part: DOUBLER — CRACKED (LT WING) · airframe 68,077 hrs · 18,334 cycles

LEFT WING FIXED L/E COMPARTMENT AT STA 667 RIB DOUBLER FOUND CRACKED. DOUBLER R & R IAW SRM 51-31-01-0G. THE NEW RIB DOUBLER FABRICATED IAW DWG: ARB3954, REV K. THE REPAIR CLASSIFIED MAJOR IAW GMM 6-2-100.

Part: DOUBLER — CRACKED (LT WING) · airframe 68,077 hrs · 18,334 cycles

LEFT WING FIXED L/E COMPARTMENT AT STA 626 BEADED DOUBLER FOUND CRACKED. DOUBLER REPAIRED IAW SRM 57-40-02-2R, FIG 203, REPAIR 15. THE REPAIR CLASSIFIED AS MAJOR IAW GMM 6-2-100.

Part: DOUBLER — CRACKED (LT WING) · airframe 68,077 hrs · 18,334 cycles

LEFT WING FIXED L/E COMPARTMENT AT STA 631, BEADED DOUBLER FOUND CRACKED. DOUBLER REPAIRED IAW SRM 57-40-02-2R, FIG 203 REPAIR 15. THE REPAIR CLASSIFIED AS MAJOR IAW GMM 6-2-100.

Part: DOUBLER — CRACKED (LT WING) · airframe 68,077 hrs · 18,334 cycles

LEFT WING FIXED L/E COMPARTMENT AT STA 670 BEADED DOUBLER FOUND CRACKED. DOUBLER REPAIRED IAW SRM 57-40-02-2R, FIG 203, REPAIR 15. THE REPAIR CLASSIFIED AS MAJOR IAW GMM 6-2-100.

Part: DOUBLER — CRACKED (LT WING) · airframe 68,077 hrs · 18,334 cycles

LEFT WING FIXED L/E COMPARTMENT AT STA 735 BEADED DOUBLER FOUND CRACKED. DOUBLER REPAIRED IAW SRM 57-40-02-2R, FIG 203, REPAIR 15. THE REPAIR CLASSIFIED MAJOR IAW GMM 6-2-100.

Part: SEAT TRACK — DAMAGED (FUSELAGE) · airframe 68,077 hrs · 18,334 cycles

MAIN DECK CARGO COMPARTMENT LT BS 6-3, X= 47.5 SEAT TRACK FOUND CROWN DAMAGED. SEAT TRACK REPAIRED IAW SRM 53-00-52-2R, FIG 201, REPAIR 1. REPAIR CLASSIFIED AS MAJOR IAW GMM 6-2-100.

Part: TRUNNION — CRACKED (NLG) · airframe 68,077 hrs · 18,334 cycles

DURING HFEC INSPECTION ON NLG RT TRUNNION FITTING LOWER SECTION, EXISTING REPAIR AREA FOUND ONE EACH CRACK PROPAGATION, APPROX 0.50 INCH IN LENGTH AT STATION Y=595. CRACKED AREA REPAIRED IAW SRM 53-10-14-2R, REPAIR 2 FIG 202. INITIAL INSPECTION TO BE CARRIED OUT AT 1500 FLIGHT CYCLES AND REPETITIVE INSPECTION TO BE CARRIED OUT AT EVERY 1500 FLIGHT CYCLES IAW SRM 53-10-14-2R, REPAIR 2, TABLE 201, REQUIREMENTS. REPAIR CLASSIFIED AS MAJOR IAW GMM 6-2-100.

Part: DOOR — CRACKED · airframe 660 hrs · 17,627 cycles

A CRACK WAS FOUND ON LEFT STRUT DOOR STRUCTURE AT FWD HINGE. REPAIRED DOOR IAW SRM 52-82-07-2R.

Part: RELAY — FAILED (ENTRY DOOR) · airframe 658 hrs · 17,577 cycles

RIGHT CREW ENTRY DOOR DOESN'T OPEN ALL THE TIME, ELECTRICALLY FROM OUTSIDE OR INSIDE. R & R RELAY R2-176. OPERATIONAL CHECKED GOOD.

Part: BOTTLE — UNKNOWN (L1 DOOR ASSIST) · airframe 652 hrs · 17,379 cycles

L1 DOOR PNEUMATIC BOTTLE LOW, WILL NOT TAKE NITROGEN PRESSURE. SERVICED L1 DOOR ASSIST BOTTLE.

Part: HINGE FITTING — DAMAGED (RT WING TE FLAP) · airframe 63,274 hrs · 16,753 cycles

RIGHT WING INBD FLAP OTBD AFT HINGE OTBD PIVOT LUG FOUND OUT OF LIMIT AFTER BUSHING REMOVAL. OVERSIZED BUSHING FABRICATED AND INSTALLED IAW EA 1-5750-159871A PART 2 STEP 1 . REPAIR CLASSIFIED MAJOR IAW GMM 6-2-100 REVISON 122.

Part: HINGE FITTING — DAMAGED (RT WING TE FLAP) · airframe 63,274 hrs · 16,753 cycles

(FLAP SIDE) RIGHT WING INBD FLAP OTBD HINGE PIVOT OTBD LUG THICKNESS FOUND OUT OF LIMITS. REPAIRED IAW EA 1-5750-159871A PART 2. REPAIR CLASSIFIED MAJOR IAW GMM 6-2-100 REVISON 122.

Part: BUSHING — DAMAGED (RT WING TE FLAP) · airframe 63,274 hrs · 16,753 cycles

RIGHT WING OTBD FLAP INBD HINGE INBD PIVOT LUG FOUND OUT OF LIMITS AFTER BUSHING REMOVAL. BUSHING REMOVED IAW CMM 20-10-7 REV.79. BUSHING FABRICATED AND INSTALLED IAW CMM 57-52-04 REV.79 AND EA 1-5750-T0308814 PART 1. REPAIR CLASSIFIED MAJOR IAW GMM 6-2-100 REVISION 122.

Part: HINGE FITTING — CORRODED (LT WING TE FLAP) · corrosion level 2 · airframe 63,274 hrs · 16,753 cycles

LEFT WING OTBD FLAP INBD FWD HINGE SIDE LOAD FITTING SURFACE FOUND CORRODED. REWORKED AND FOUND OUT OF LIMITS IAW CMM 57-44-08 REV 79. REPAIR SHIM FABRICATED AND INSTALLED IAW CMM 57-44-08 REV.79 AND EA 1-5750-T0308731 PART 1 STEP 2. REPAIR CLASSIFIED MAJOR IAW GMM 6-2-100 REVISION 122.

Part: HINGE FITTING — WORN (LT WING TE FLAP) · airframe 63,274 hrs · 16,753 cycles

LEFT WING INBD FLAP, FLAP SIDE, OTBD HINGE PIVOT INBD LUG FOUND OUT OF LIMITS. REPAIRED IAW EA1-5750-T0308817 PART 1. REPAIR CLASSIFIED AS MAJOR IAW GMM 6-2-100 REVISION 122.

Part: HINGE FITTING — CORRODED (LT WING TE FLAP) · corrosion level 2 · airframe 63,274 hrs · 16,753 cycles

LEFT WING INBD FLAP OTBD AFT HINGE INBD PIVOT LUG HOLE FOUND CORRODED. REWORKED AND FOUND OUT OF LIMITS CMM 57-52-03 REV 79. REPAIR BUSHING FABRICATED AND INSTALLED IAW CMM 57-52-03 REV 79 AND EA 1-5750-T0308817 PART 1. REPAIR CLASSIFIED MAJOR IAW GMM 6-2-100 REVISION 122.

Part: HINGE FITTING — CORRODED (LT WING TE FLAP) · corrosion level 2 · airframe 63,274 hrs · 16,753 cycles

LEFT WING OTBD FLAP OTBD FWD HINGE LOWER MOUNT OTBD HOLE SURFACE FOUND CORROSION. REWORKED AND FOUND OUT OF LIMITS IAW CMM 57-44-09 REV. 79. REPAIR SHIM FABRICATED AND INSTALLED IAW CMM 57-44-09 REV.79 AND EA 1-5750-T0308729 PART 1 STEP 2A. REPAIR CLASSIFIED MAJOR IAW GMM 6-2-100 REVISION 122

Part: HINGE FITTING — CORRODED (RT WING TE FLAP) · corrosion level 2 · airframe 63,274 hrs · 16,753 cycles

RIGHT WING OTBD FLAP INBD FWD HINGE LOWER MOUNT OTBD HOLE FOUND CORRODED. REWORKED AND FOUND OUT OF LIMITS IAW CMM 57-44-08 REV.79. REPAIR BUSHING FABRICATED AND INSTALLED IAW CMM 57-44-08 REV 79 AND EA 1-5750-T0308728 PART 1 STEP 2. REPAIR CLASSIFIED MAJOR AS PER GMM 6-2-100 REVISION 122.

Part: HINGE FITTING — CORRODED (LT WING TE FLAP) · corrosion level 2 · airframe 63,274 hrs · 16,753 cycles

LEFT WING OTBD FLAP OTBD FWD HINGE UPPER MOUNT OTBD HOLE FOUND CORRODED. REWORKED AND FOUND OUT OF LIMITS IAW CMM 57-44-09 REV 79. REPAIR BUSHING FABRICATED AND INSTALLED IAW CMM 57-44-09 REV 79 AND EA 1-5750-T0308729 PART 1 STEP 2A. REPAIR CLASSIFIED MAJOR AS PER GMM 6-2-100 REVISION 122.

Part: HINGE FITTING — CORRODED (LT WING TE FLAP) · corrosion level 2 · airframe 63,274 hrs · 16,753 cycles

LEFT WING OTBD FLAP INBD FWD HINGE LOWER MOUNT OTBD HOLE FOUND CORRODED. REWORKED AND FOUND OUT OF LIMITS IAW CMM 57-44-08 REV 79. REPAIR BUSHING FABRICATED AND INSTALLED IAW CMM 57-44-08 REV.79 AND EA 1-5750-T0308731 PART 1 STEP 2. REPAIR CLASSIFIED MAJOR AS PER GMM 6-2-100 REVISION 122.

Part: DOUBLER — CRACKED (LT WING) · airframe 63,274 hrs · 16,753 cycles

LEFT WING LE BEADED DOUBLER XOS 637 FOUND CRACKED. REPAIRED IAW SRM 57-40-02, FIGURE 203, REPAIR 15, REVISION 55. REPAIR CLASSIFIED MAJOR IAW GMM 6-2-100 REVISION 122.

Part: HINGE FITTING — CORRODED (LT WING TE FLAP) · corrosion level 2 · airframe 63,274 hrs · 16,753 cycles

LEFT WING OTBD FLAP INBD FWD HINGE LOWER MOUNT INBD HOLE FOUND CORRODED. REWORKED AND FOUND OUT OF LIMITS IAW CMM 57-44-08 REV 79. REPAIR BUSHING FABRICATED AND INSTALLED IAW CMM 57-44-08 REV.79 AND EA 1-5750-T0308731 PART 1 STEP 2. REPAIR CLASSIFIED MAJOR AS PER GMM 6-2-100 REVISION 122.

Part: DOUBLER — CRACKED (RT WING) · airframe 63,274 hrs · 16,753 cycles

RIGHT WING LE BEADED DOUBLER AT XOS 668 FOUND CRACKED. REPAIRED IAW SRM 57-40-02, FIGURE 203, REPAIR 15, REVISION 55. REPAIR CLASSIFIED MAJOR IAW GMM 6-2-100 REVISION 122.

Part: HINGE FITTING — CORRODED (LT WING TE FLAP) · corrosion level 2 · airframe 63,274 hrs · 16,753 cycles

LEFT WING OTBD FLAP OTBD FWD HINGE LOWER MOUNT INBD HOLE FOUND CORRODED. REWORKED AND FOUND OUT OF LIMITS IAW CMM 57-44-09 REV 79. REPAIR BUSHING FABRICATED AND INSTALLED IAW CMM 57-44-09 REV 79 AND EA1-5750-T0308729 PART 1 STEP 2B. REPAIR CLASSIFIED MAJOR AS PER GMM 6-2-100 REVISION 122.

Part: HINGE FITTING — CORRODED (RT WING TE FLAP) · corrosion level 2 · airframe 63,274 hrs · 16,753 cycles

RIGHT WING OTBD FLAP INBD FWD HINGE LOWER MOUNT INBD HOLE FOUND CORRODED. REWORKED AND FOUND OUT OF LIMITS IAW CMM 57-44-08 REV.79. REPAIR BUSHING FABRICATED AND INSTALLED IAW CMM 57-44-08 REV 79 AND EA 1-5750-T0308728 PART 1 STEP 2. REPAIR CLASSIFIED MAJOR IAW GMM 6-2-100 REVISION 122.

Part: HINGE FITTING — CORRODED (LT WING TE FLAP) · corrosion level 2 · airframe 63,274 hrs · 16,753 cycles

LEFT WING OTBD FLAP OTBD FWD HINGE UPPER MOUNT INBD HOLE FOUND CORRODED. REWORKED AND FOUND OUT OF LIMITS IAW CMM 57-44-09 REV 79. REPAIR BUSHING FABRICATED AND INSTALLED IAW CMM 57-44-09 REV 79 AND EA 1-5750-T0308729 PART 1 STEP 2A. REPAIR CLASSIFIED MAJOR AS PER GMM 6-2-100 REVISION 122.

Part: HINGE FITTING — CORRODED (LT WING) · corrosion level 2 · airframe 63,274 hrs · 16,753 cycles

LEFT WING OTBD FLAP OTBD FWD HINGE LOWER MOUNT INBD HOLE SURFACE FOUND CORRODED. REWORKED AND FOUND OUT OF LIMITS IAW CMM 57-44-09 REV. 79. REPAIR SHIM FABRICATED AND INSTALLED IAW CMM 57-44-09, REV 79 AND EA 1-5750-T0308729 PART 1 STEP 2A. REPAIR CLASSIFIED MAJOR IAW GMM 6-2-100, REVISION 122.

Part: DOOR FRAME — CRACKED (BS 1256) · airframe 63,274 hrs · 16,753 cycles

MAIN DECK CARGO BAY BS 1256, LONGERON 26 RT FWD R3 DOOR FRAME FOUND CRACKED. REPAIRED IAW SRM 53-40-15, FIGURE 201, REPAIR 3, REVISION 55. REPAIR CLASSIFIED MAJOR IAW GMM 6-2-100 REVISION 121.

Part: SEAT TRACK — CORRODED (BS 1831) · corrosion level 2 · airframe 63,274 hrs · 16,753 cycles

CABIN MAIN DECK CARGO COMPARTMENT BS 1831, LBL 27.5 SEAT TRACK FOUND CORRODED. REPAIRED IAW SRM 53-00-52 FIGURE 201 REPAIR 1 REVISION 55. REPAIR CLASSIFIED MAJOR IAW GMM 6-2-100 REVISION 121.

Part: TRUNNION — CRACKED (ZONE 100) · airframe 63,274 hrs · 16,753 cycles

NOSE LANDING GEAR RT TRUNNION FITTING LOWER SECTION FOUND CRACKED. REPAIRED IAW SRM 53-10-14 FIGURE 202, REPAIR 2 REVISION 55. REPAIR CLASSIFIED MAJOR IAW GMM 6-2-100 REVISION 121.

Part: ANGLE — CRACKED (NR 2 SLAT) · airframe 63,274 hrs · 16,753 cycles

DURING INSPECTION, FOUND LEFT WING NR 2 SLAT OTBD INNER STRIP ANGLE FOUND CRACKED AT XDLE 328.106. REPAIRED IAW EA 1-5750-T0308746 PART 1. REPAIR CLASSIFIED MAJOR IAW GMM 6-2-100 REVISION 122.

Part: TRUNNION — CRACKED (ZONE 100) · airframe 63,274 hrs · 16,753 cycles

NOSE LANDING GEAR LT TRUNNION FITTING LOWER SECTION FOUND CRACKED. REPAIRED IAW SRM 53-10-14, FIGURE 202, REPAIR 2, REVISION 55. REPAIR CLASSIFIED MAJOR IAW GMM 6-2-100 REVISION 121.

Part: SKIN — CRACKED (RT WING) · airframe 63,274 hrs · 16,753 cycles

RIGHT WING LOWER FIXED LE AT REFUELING PANEL CUT OUT INBD FWD CORNER AT XOS 643 FOUND CRACKED. REPAIRED IAW SRM 57-40-02 FIGURE 202 REPAIR 7 REVISION 55. REPAIR CLASSIFIED MAJOR AS PER GMM 6-2-100 REVISION 122.

Part: SKIN — CRACKED (RT WING) · airframe 63,274 hrs · 16,753 cycles

RIGHT WING DROOP LE UPPER SURFACE AT XDLE 325 FOUND CRACKED. REPAIRED IAW SRM 57-40-01 FIGURE 201 REPAIR 5 REVISION 55 REPAIR. CLASSIFIED MAJOR AS PER GMM 6-2-100 REVISION 122.

Part: SKIN — CRACKED (LT WING) · airframe 63,274 hrs · 16,753 cycles

LEFT WING LOWER FIXED LE AT NR 12 SLAT TRACK CUT OUT AT XOS 774 FOUND CRACKED. SKIN REPAIRED IAW SRM 57-40-02 FIGURE 201 REPAIR 7 REVISION 55. REPAIR CLASSIFIED MAJOR AS PER GMM 6-2-100 REVISION 121.

Part: VANE — DELAMINATED (RT WING TE FLAP) · airframe 63,274 hrs · 16,753 cycles

RIGHT WING OTBD FLAP VANE UPPER SURFACE FOUND DELAMINATED FROM XOFH 558.820 - 586.820. RIGHT WING OUTBOARD FLAP VANE ASSEMBLY REMOVED AND REPLACED IAW AMM 27-50-32- 4 REVISION 79. ADJUSTMENT AND TEST CARRIED OUT IAW AMM 27-50-32-5 REVISION 79. FOUND SATISFACTORY. REPAIR CLASSIFIED MINOR IAW GMM 6-2-100 REVISION 122.

Part: METER — FAILED (FUEL SYSTEM) · airframe 62,156 hrs · 16,391 cycles

FUEL QTY, FUEL USED CHECK DISPLAYED AT APPROX 22437. ESTIMATED FUEL USED WAS 5K LBS ABOVE FUEL BURNED. IAW FUEL QTY 1 USED CHECKLIST ISOLATED THEN SHUT DOWN ENG NR 1. NO FURTHER LEAK. CONTINUED IAW CHECK LIST ISOLATED TANK TO ENG, LEAK CONTINUED. THEN IAW CHECK LIST FED ENG NR 1 FROM TANK 3, LEAK CONTINUED, IAW CHECK LIST SHUT DOWN NR 1 ENG, LEAK STOPPED. OPENED COWLINGS & CARRIED OUT VISUAL INSP OF NR 1 ENG NO EVIDENCE OF ANY FUEL LEAKS. PERFORMED WET MOTOR IAW JRH CHAP 5 & NO LEAKS. RAN ENG & FOUND FUEL FLOW TOO HIGH FOR IDLE POWER 1850 LB HR & CONTINUING TO CLIMB. ALL PARAMETERS WERE NORMAL. R & R FUEL PRESS FLOW METER IAW MM 73-31-02-4-2 & PERFORMED FUEL FLOW ADJUST TEST, SATISFACTORY IAW 73-31-03-5-2 & ENG RUN SATISFACTORY IAW JRH CHAP 6.

Part: BATTERY PACK — FAILED (EMERGENCY LIGHTS) · airframe 61,512 hrs · 16,148 cycles

DURING SERVICE CHECK EMERGENCY LIGHT TEST RECEIVED EMERGENCY LIGHT BATTERY 1 LOW ALERT. R & R EMERGENCY EXIT LIGHT BATTERY PACK.

Part: BATTERY — FAILED (R1 DOOR SLIDE) · airframe 61,127 hrs · 16,024 cycles

FOUND R1 ENTRY DOOR SLIDE REMOTE PRESSURE INDICATOR PRESS TO TEST LIGHT OUT. REPLACED REMOTE PRESSURE INDICATOR BATTERIES REF AMM 25-61-04-4. OPS CHECKS GOOD REF AMM 25-61-04-5.

Part: BLOCK — LOOSE (CENTER MLG) · airframe 59,985 hrs · 15,633 cycles

MX REPORTED THERE IS A GAP BETWEEN THE LT AFT PILLOW BLOCK BOLT AND THE PILLOW BLOCK. MX TORQUED THE BOLT TO THE AMM SPECS. HOWEVER THE BOLT WILL NOT PULL UP TO THE PILLOW BLOCK. THIS CONDITION IS ACCEPTABLE PROVIDED THE CLG IS DEACTIVATED. REMOVED CTR GEAR FOR INSPECTION, CLEANED CORRIOSION AND ENGINEERING DETERMINED MATERIAL REMOVED WAS BEYOND LIMITS. GENERATED EA T1-3210-164881 P2 AND T1 5340-163939 TO REINSTALL GEAR AND STOWED PER MEL 32-30- 02. EA T1 5340-163939 PART2 DUE 29DEC2012 FOR REPLACEMENT OF PILLOW BLOCK FITTING.

Part: SKIN — MISREPAIRED (ZONE 100) · airframe 59,182 hrs · 15,380 cycles

SKIN AT BS 366 TO 374, LONGERON 40- 41L MISREPAIRED. REPAIRED AS PER E.A. 1-5330-162363. REPAIR CLASSIFIED AS MAJOR AS PER GMM 6-2-100 REVISION 115.

Part: SEAT TRACK — CORRODED (ZONE 200) · corrosion level 2 · airframe 59,182 hrs · 15,380 cycles

BS 5-65, X= 8.5 SEAT TRACK CORRODED. REPAIRED IAW SRM 53-00-52 FIGURE 201 REPAIR 1 REVISION 50. REPAIR CLASSIFIED AS MAJOR AS PER GMM 6-2-100 REVISION 115.

Part: SKIN — MISREPAIRED (RT WING TE FLAP) · airframe 59,182 hrs · 15,380 cycles

RT INBD FLAP UPPER SURFACE MISREPAIRED. REPAIRED IAW SRM 57-00-01 REPAIR 1 REVISION 50 AND E.A. 1-5750-162361.

Part: SUPPORT — CRACKED (FUSELAGE) · airframe 59,182 hrs · 15,380 cycles

UPON REMOVAL OF SIDEWALL PANEL, R3 DOOR NR 1 BEAM AFT STOP SUPPORT FOUND CRACKED. REMOVED AND REPLACED AS PER SRM 51-31-01 REVISION 50. REPAIR CLASSIFIED AS MAJOR AS PER GMM 6-2-100 REVISION 115.

Part: SEAT TRACK — CRACKED (ZONE 200) · airframe 59,182 hrs · 15,380 cycles

BS 495, X= -27.5 SEAT TRACK FOUND CRACKED. REPAIRED IAW SRM 53-00-52 REPAIR 1 FIGURE 201 REVISION 50. REPAIR CLASSIFIED AS MAJOR AS PER GMM 6-2-100 REVISION 115.

Part: SUPPORT — CRACKED (BS 1259 L27R) · airframe 59,182 hrs · 15,380 cycles

BS 1259, LONGERON 27 INTERCOSTAL SUPPORT FOUND CRACKED. SUPPORT REMOVED AS PER SRM 51-33-01 REVISION 50. NEW SUPPORT FABRICATED AS PER EA 1-5310-159873. SUPPORT INSTALLED AS PER SRM 51-31-01 REVISION 50. REPAIR CLASSIFIED AS MAJOR AS PER GMM 6-2-100 REVISION 115.

Part: SKIN — MISREPAIRED (ZONE 500) · airframe 59,182 hrs · 15,380 cycles

LT WING L/E SKIN XIS 247 MISREPAIRED. CARRIED OUT REPAIR AS PER EA 1-5710-112420. CLASSIFIED AS MAJOR AS PER GMM 6-2-100 REVISION 115.

Part: FRAME — CRACKED (BS 2122 BULKHEAD) · airframe 59,182 hrs · 15,380 cycles

AFT FUSELAGE COMPARTMENT ON UPPER AFT FUSELAGE BULKHEAD BS 2122 UPPER SUPPORT FRAME CRACKED.

Part: SKIN — MISREPAIRED (NR 7 SLAT) · airframe 59,182 hrs · 15,380 cycles

NR 7 L/E SLAT INBD EDGE XOS 893 MISREPAIRED. REPAIR ACCOMPLISHED AS PER EA 1-5710-112418 REVISION A PART 2. REPAIR CLASSIFIED AS MAJOR AS PER GMM 6-2-100 REVISION 115.

Part: SKIN — CHAFED (LT WING) · airframe 59,182 hrs · 15,380 cycles

LT WING DROOP L/E INBD EDGE FOUND CHAFED. REPAIR CARRIED OUT AS PER EA 1-5750-160996 PART 1. REPAIR CLASSIFIED AS MAJOR AS PER GMM 6-2-100 REVISION 115.

Part: LONGERON — CORRODED (ZONE 100) · corrosion level 2 · airframe 59,182 hrs · 15,380 cycles

CENTER ACCESSORY COMPARTMENT BS 6-70 TO STATION 6-75 LONGERON 49R FOUND CORRODED. CORROSION REMOVED PER SRM 51-21-01 REVISION 50. MATERIAL REMOVED 0.095", MATERIAL REMAINED 0.005", ORIGINAL MATERIAL THICKNESS MEASURED 0.100" AND FOUND OUT OF LIMIT AS PER SRM 53-00-00 FIGURE 205 REVISION 50. REPAIR CARRIED OUT AS PER SRM 53-00-05 FIGURE 202 REVISION 50. REPAIR CLASSIFIED AS MAJOR AS PER GMM 6-2-100 REVISION 115.

Part: SKIN — MISREPAIRED (LT NR 8 SLAT) · airframe 59,182 hrs · 15,380 cycles

LT WING NR 8 SLAT LOWER SURFACE AREA MISREPAIRED. REPAIRED AS PER EA 1-5750-159878. REPAIR CLASSIFIED AS MAJOR AS PER GMM 6-2-100 REVISION 115.

Part: FRAME — DENTED (BS 1661 L11R) · airframe 59,182 hrs · 15,380 cycles

FRAME BS 1661, L11R FOUND DENTED. REPAIR CARRIED OUT AS PER SRM 53-00-07 FIGURE 201 REPAIR 2 REVISION 50. REPAIR CLASSIFIED AS MAJOR AS PER GMM 6-2-100 REVISION 115.

Part: FRAME — DENTED (BS 1661 L11L) · airframe 59,182 hrs · 15,380 cycles

FRAME, BS 1661, L11L FOUND DENTED. REPAIRED AS PER SRM 53-00-07 FIGURE 201 REPAIR 2 REVISION 50. REPAIR CLASSIFIED AS MAJOR AS PER GMM 6-2-100 REVISION 115.

Part: LONGERON SPLICE — CORRODED (ZONE 100) · corrosion level 2 · airframe 59,182 hrs · 15,380 cycles

CENTER ACCESSORY COMPARTMENT, STA 6-70 TO STA 6-80, LONGERON 50R AND SPLICE FOUND CORRODED. CORROSION REMOVED AS PER SRM 51-21-01 REVISION 50 MATERIAL REMOVED 0.089", MATERIAL REMAINED 0.001" ORIGINAL THICKNESS MEASURED 0.090" AND FOUND OUT OF LIMIT AS PER SRM 53-00-00 FIGURE 205 REVISION 50. CARRIED OUT REPAIR AS PER SRM 53-00-05 FIGURE 202 REVISION 50. REPAIR CLASSIFIED AS MAJOR AS PER GMM 6-2-100 REVISION 115.

Part: FRAME — DENTED (BS 1701 L11R) · airframe 59,182 hrs · 15,380 cycles

FRAME, BS 1701 L11R FOUND DENTED. REPAIR CARRIED OUT AS PER SRM 53-00.07 FIGURE 201 REPAIR 2 REVISION 50. REPAIR CLASSIFIED AS MAJOR AS PER GMM 6-2-100 REVISION 115.

Part: FRAME — DENTED (BS 1681 L11R) · airframe 59,182 hrs · 15,380 cycles

FRAME BS 1681, L11R, FOUND DENTED. REPAIR CARRIED OUT AS PER SRM 53-00.07 FIGURE 201 REPAIR 2 REVISION 50. REPAIR CLASSIFIED AS MAJOR AS PER GMM 6-2-100 REVISION 115.

Part: FRAME — MISREPAIRED (ZONE 200) · airframe 59,182 hrs · 15,380 cycles

LT SIDEWALL FRAME BS 535, LONGERON 23 LT MISREPAIRED. REPAIR ACCOMPLISHED PER SRM 53-20-07 REPAIR 1 FIGURE 201 REVISION 50. REPAIR CLASSIFIED AS MAJOR AS PER GMM 6-2-100 REVISION 115.

Part: SKIN — MISREPAIRED (LT WING TE FLAP) · airframe 59,182 hrs · 15,380 cycles

LEFT WING INBD FLAP UPPER SURFACE XIFH 216 - YIFH 70 MISREPAIRED. REPAIR ACCOMPLISHED PER SRM 57-00-01 REPAIR 1 FIGURE 201 REVISION 50. REPAIR CLASSIFIED AS MAJOR AS PER GMM 6-2-100 REVISION 115.

Part: LONGERON — CORRODED (ACCESSORY BAY) · corrosion level 2 · airframe 59,182 hrs · 15,380 cycles

CENTER ACCESSORY COMPARTMENT BS 6-70 TO 6-80, LONGERON 49L FOUND CORRODED. CORROSION ON LONGERON REMOVED AS PER SRM 51-21-01 REVISION 50. AND FOUND OUT OF LIMITS AS PER SRM 53-00-00 FIGURE 205 REVISION 50. DAMAGED LONGERON REMOVED AND REPAIRED AS PER SRM 53-00-05 FIGURE 202 REVISION 50. REPAIR CLASSIFIED AS MAJOR AS PER GMM 6-2-100 REVISION 115.

Part: FRAME — MISREPAIRED (BS 535 L19L) · airframe 59,182 hrs · 15,380 cycles

LEFT SIDEWALL FRAME BS 535, LONGERON 19 LT MISREPAIRED. REPAIR ACCOMPLISHED PER SRM 53-20-07 REPAIR 1 FIGURE 201 REVISION 50. REPAIR CLASSIFIED AS MAJOR AS PER FEDEX GMM 6-2-100 REVISION 115.

Part: SKIN — MISREPAIRED (RT WING) · airframe 59,182 hrs · 15,380 cycles

RT WING FIXED L/E TELESCOPIC DUCT UPPER CUT-OUT XOS 467 MISREPAIRED. REPAIRED AS PER EA 1-5730-159876. REPAIR CLASSIFIED AS MAJOR AS PER GMM 6-2-100 REVISION 115.

Part: STRINGER — MISREPAIRED (RT WING) · airframe 59,182 hrs · 15,380 cycles

RT WING STRINGER 43 MISREPAIRED. REPAIRED IAW EA 1-5710-162358. REPAIR CLASSIFIED AS MAJOR IAW GMM 6-2-100, REV 115.

Part: SKIN — CRACKED (LT WING) · airframe 59,182 hrs · 15,380 cycles

LEFT WING TELESCOPIC DOOR CUT-OUT FOUND CRACKED. REPAIR CARRIED OUT IAW SRM 57-40-01, FIG 201, REPAIR 10, REV 50. REPAIR CLASSIFIED AS MAJOR IAW GMM 6-2-100, REV 115.

Part: SKIN — CRACKED (LT WING) · airframe 59,182 hrs · 15,380 cycles

LEFT WING NR 14 SLAT TRACK CUT-OUT FOUND CRACKED. REPAIR CARRIED OUT IAW SRM 57-40.02, REV 50. REPAIR CLASSIFIED AS MAJOR IAW GMM 6-2-100, REV 115.

Part: BATTERY PACK — INOPERATIVE (EMERGENCY LIGHTS) · airframe 55,806 hrs · 14,497 cycles

EMERGENCY LIGHTING SYSTEM INOPERATIVE. RELEASED FOR SERVICE PER MEL: 33-50-04. CHECKED EMERGENCY LIGHTING, LIGHT DO NOT OFF WHEN SWITCH OFF. R & R RED EMERGENCY LIGHTING BATTERY POWER SUPPLY IAW MM 33-51-01-4-0. TESTED IAW MM 33-51-01-5 PASSED.

Part: VALVE — LEAKING (HYD SYSTEM) · airframe 55,458 hrs · 14,417 cycles

HYD 2 OFF ALERT 45 MIN INTO FLIGHT FOUND FLAP LOCK OUT VALVE FOR RT OTBD FLAPS LEAKING. R&R VALVE.

Part: PUMP — FAILED (HYD SYSTEM) · airframe 54,805 hrs · 14,284 cycles

AFTER TAKEOFF, LEVEL 1 HYD PUMP 3L PUMP ALERT, WITH TEMP (T) INDICATED. 1 HR 25 MIN LATER AT CRUISE, FL330, HYD 3 QTY BEGAN DECREASING. SWITCHED TO MAN. ISOLATED HYD 3 & TURNED 3L & 3R PUMPS OFF. HYD 3, QTY CONTINUED TO DECREASE TO ZERO (0). HYD 3 FAIL ALERT APPEARED. ALT GEAR EXTENTION USED AT LANDING. R & R NR 3 ENG RT/AFT EDP AND GEARBOX SEAL REF MM 29-11-20-4 2. R&R LT FWD PUMP PER MM 29-11-20-4, RAN ENG PER JRH, PERFORMED ADJ/TEST 03 REF MM 71-02-03-5 ALL TESTS PASSED , NO LEAKS NOTED, ALL POPPETS ON NR 3 ENG AND MAIN SYS FILTERS REMAINED STOWED. NR 3 ENG COWLS CLOSED PER MM 71-10-00-2

Part: LONGERON — CRACKED (ZONE 200) · airframe 53,424 hrs · 13,957 cycles

CRACK INDICATION FOUND APROXIMATELY 0.3" IN LENGTH DURING X-RAY INSPECTION AT STATION 5-123, LONGERON 1L FORWARD SECTION EDGE. CRACK AT LONGERON 1L AT STATION 5-123 REPAIRED AS PER SRM 53-00-05 FIGURE 201 REVISION 44. INTERCOASTAL REMOVED AND REPLACED AS PER SRM 51-33-01 REVISION 44. INTERCOASTAL FABRICATED AS PER DRAWING AFA3121 REVISION AV. THIS REPAIR IS CLASSIFIED AS MAJOR AS PER GMM 6-2-100 REVISION 110.

Part: LONGERON — CRACKED (ZONE 200) · airframe 53,424 hrs · 13,957 cycles

CRACK INDICATION FOUND APROXIMATELY 2.2" IN LENGTH DURING X-RAY INSPECTION AT STATION 5-123, LONGERON 3R FORWARD SECTION EDGE. CRACKED AT LONGERON 3R FORWARD SECTION EDGE AT STATION 5-123 REPAIRED AS PER SRM 53-00-05 FIGURE 201 REVISION 44. THIS REPAIR IS CLASSIFIED AS MAJOR AS PER GMM 6-2-100 REVISION 110.

Part: STRUCTURE — CORRODED (ZONE 200) · corrosion level 2 · airframe 53,424 hrs · 13,957 cycles

MAIN DECK - UPON REMOVAL OF FLOOR PANEL AT CTR TANK UPPER SURFACES AT STA 1226, BETWEEN X= -79 TO X= -82 FOUND WITH SURFACE CORROSION. MAIN DECK CENTER TANK UPPER SURFACES AT STATION 1226, BETWEEN X= -79 TO X= -82 SURFACE CORROSION REPAIR CARRIED OUT AS PER FEDEX E.A. 1-5710-140470, REPAIR IS CLASSIFIED AS MINOR AS PER GMM 6-2-100 REVISION 110.

Part: SKIN — DENTED (LT WING TE FLAP) · airframe 53,424 hrs · 13,957 cycles

LT WING INBD FLAP DENT FOUND ON LOWER SURFACE OTBD UPPER SEGMENT AREA. REPAIR CARRIED OUT AT LT WING INBOARD FLAP DENT AREA ON LOWER SURFACE OUTBOARD UPPER SEGMENT AS PER SRM 57-00-01 FIGURE 201 REVISION 44. THIS REPAIR IS CLASSIFIED AS MINOR AS PER GMM 6-2-100 REVISION 110.

Part: LONGERON — CORRODED (ZONE 100) · corrosion level 2 · airframe 53,424 hrs · 13,957 cycles

CTR CARGO STA 1641 TO STA 1650 LONGERON 44R CORRODED. LONGERON TRIMMED OUT AND CARRIED OUT REPAIR AS PER SRM 53-00-05 FIGURE 201 REVISION 44. THIS REPAIR IS CLASSIFIED AS MAJOR AS PER GMM 6-2-100 REVISION 110.

Part: LONGERON — CORRODED (BS 1681 L45R) · corrosion level 2 · airframe 53,424 hrs · 13,957 cycles

CTR CARGO STA 1681, LONGERON 45R CORRODED. TRIMMED OUT AS PER SRM 53-00-05 FIGURE 202 REVISION 44 AND CARRIED OUT REPAIR AS PER E.A. 1-5310- 140474, REPAIR IS CLASSIFIED AS MAJOR AS PER FEDEX GMM 6-2-100 REVISION 110.

Part: FRAME — DEFORMED (ZONE 200) · airframe 53,424 hrs · 13,957 cycles

MAIN DAECK CARGO - FRAME AT STA 1681, LONGERON 12L, FOUND DEFORMED. MAIN DECK CARGO - FRAME AT STATION 1681 LONGERON 12L REPAIRED AS PER SRM 53-00-07 FIGURE 201 REVISION 44. THIS REPAIR IS CLASSIFIED AS MINOR AS PER GMM 6-2-100 REVISION 110.

Part: FRAME — DEFORMED (ZONE 200) · airframe 53,424 hrs · 13,957 cycles

MAIN DECK CARGO - FRAME AT STA 1761, LONGERON 12L, FOUND DEFORMED. MAIN DECK CARGO - FRAME AT STATION 1761 LONGERON 12L REPAIRED AS PER SRM 53-00-07 FIGURE 201 REVISION 44. THIS REPAIR IS CLASSIFIED AS MINOR AS PER FEDEX GMM 6-2-100 REVISION 110.

Part: BRAKE DISC — DISINTEGRATED (MLG) · airframe 51,401 hrs · 13,443 cycles

PROBLEM WITH NR 3 BRAKE. AFTER TAKEOFF GOT "BRAKE DIFF TEMP" LEVEL 1 ALERT. NR 3 BRAKE READ 280 DEG- ALL THE OTHER READ AT -2 DEG. TEMP CLIMBED UNTIL RE-LOWERING GEAR FOR 5 MINUTES HALTED TEMP INCREASE AT 365 DEG., AND REDUCED TEMP BACK TO 280 DEG CFDS S HOWS BTMTP FAULT - " BRAKE 03 DIFF TEMP HOT". REMOVED NR 3 TIRE, FOUND NR 3 BRAKE DISINTEGRATED. NO OTHER DAMAGE NOTED. REMOVED/REPLACED NR 3 BRAKE ASSY IAW MM 32-43-20-4. ALSO REPLACED NR3 WHEEL/TIRE ASSY IAW MM 32-41-01-4. ACFT OK TO CONTINUE. PREMATURE REMOVAL/INSTALLATION OFF. PREMATURE REMOVAL/INSTALLATION OFF MFG.

Part: LONGERON — CORRODED (ZONE 100) · airframe 47,916 hrs · 12,664 cycles

WHILE ACCOMPLISHING REPAIR ON LT LONGERON 46 AS PER SNRM NR N00694 FOUND LONGERON END CORRODED AT STA 5 -70, AFTER SPLICE REMOVED FOR ACCESS. REPAIR CARRIED OUT AS PER E.A. 1-5310-122603. THIS REPAIR CLASSIFIED AS MAJOR AS PER GMM 6-2-100.

Part: PANEL — CHAFED (ZONE 500) · airframe 47,916 hrs · 12,664 cycles

LEFT WING ANTI-ICE TELESCOPIC ACCESS PANEL FOUND CHAFED. REMOVED AND REPLACED IAW AMM 30-11-01-4. ADJUSTMENT CARRIED OUT IAW AMM 30-11-01-4, FOUND SATISFACTORY.

Part: SHEAR TIE — CORRODED (ZONE 100) · corrosion level 2 · airframe 47,916 hrs · 12,664 cycles

AFT CARGO, STA 1902 BETWEEN LONGERON 51 LEFT TO 51 RIGHT FOUND SHEAR CLIP CORRODED. AFT CARGO STA 1902 BETWEEN LONGERON 51 LEFT TO 51 RIGHT SHEAR CLIP CORROSION REMOVED AND FOUND EXCEED LIMITS AS PER SRM 53-00-01 FIGURE 4 VOLUME I. ORIGINAL THICKNESS = 0.071 INCH, MATERIAL REMOVED = 0.030 INCH, MATERIAL REMAINING = 0.041 INCH. SHEAR CLIP FABRICATED AS PER DOUGLAS DRAWING NR AGA0009. SHEAR CLIP REMOVED AND REPLACED AS PER SRM 51-35-01 VOLUME II. THIS REPAIR CLASSIFIED AS MINOR PER GMM 6-2-100.

Part: BRACKET — CORRODED (LT WING TE FLAP) · corrosion level 2 · airframe 47,916 hrs · 12,664 cycles

LEFT WING OUTBOARD FLAP INBOARD FORWARD HINGE BRACKET AFT LOWER ATTACH OUTBOARD HOLE FOUND WITH CORROSION. CORROSION AT LEFT WING OUTBOARD FLAP INBOARD FORWARD HINGE BRACKET AFT LOWER ATTACH OUTBOARD HOLE REWORKED AND CORROSION REMOVED AS PER EA NR 1-5750-122606. TITLE WINGS - LEFT WING OUTBOARD FLAP INBOARD FORWARD HINGE BRACKET (WING SIDE) CORROSION, REPAIR. REPAIR CLASSIFIED AS MAJOR PER GMM 6-2-100.

Part: BRACKET — CORRODED (LT WING TE FLAP) · corrosion level 2 · airframe 47,916 hrs · 12,664 cycles

LEFT WING OUTBOARD FLAP INBOARD FORWARD HINGE BRACKET AFT LOWER ATTACH INBOARD HOLE FOUND WITH CORROSION. CORROSION AT LEFT WING OUTBOARD FLAP INBOARD FORWARD HINGE AFT LOWER ATTACH INBOARD HOLE REWORKED AND CORROSION REMOVED AS PER EA NR 1-5750-122606. TITLE: WINGS, LEFT WING OUTBOARD FLAP INBOARD FORWARD HINGE BRACKET (WING SIDE) CORROSION, REPAIR. REPAIR CLASSIFIED AS MAJOR PER GMM 6-2-100.

Part: LONGERON — CRACKED (ZONE 200) · airframe 47,916 hrs · 12,664 cycles

CRACK INDICATION FOUND DURING X-RAY INSPECTION AT STA 6-0, LONGERON - 1 LEFT AFT SECTION EDGE AS MARKED. CRACK LENGTH APPROXIMATELY 0.5 INCH STA 6-0, LONGERON, 1 LEFT CARRIED OUT REPAIR WITH FABRICATED INTERCOSTAL AS PER EA NR 1-5310-122615 (TITLE; FUSELAGE - MAIN FRAME - LONGERON 1 LEFT SPLICE REPAIR AT STA 6-00 TO 6-10). REPAIR LONGERON FABRICATED AS PER DOUGLAS DRAWING A6A7003 AND SRM 53-10-00 FIGURE 2 VOLUME I. ALL REPAIR PARTS INSTALLED AS PER SRM 53-10-00 FIGURE 2 VOLUME I. THIS REPAIR CLASSIFIED AS MAJOR PER GMM 6-2-100.

Part: LONGERON — CORRODED (ZONE 100) · airframe 47,916 hrs · 12,664 cycles

CENTER CARGO, BETWEEN LT STA 5-32 TO 5-53 LONGERON 46 FOUND CORRODED. REPAIR CARRIED OUT IAW EA 1-5310-122603. CORROSION REMOVED AND FOUND EXCEED LIMITS IAW SRM 53-00-01. THIS REPAIR CLASSIFIED AS MAJOR AS PER GMM 6-2-100.

Part: HINGE BRACKET — CORRODED (LT WING TE FLAP) · airframe 47,916 hrs · 12,664 cycles

LEFT WING, OUTBOARD FLAP OUTBOARD FORWARD HINGE AFT LOWER ATTACH OUTBOARD HOLE AFT MATING SURFACE FOUND WITH CORROSION. CORROSION REPAIRED IAW EA 1-5750-122600. REPAIR CLASSIFIED AS MAJOR PER GMM 6-2-100.

Part: HINGE BRACKET — CORRODED (ZONE 500) · airframe 47,916 hrs · 12,664 cycles

LEFT WING, OUTBOARD FLAP OUTBOARD FORWARD HINGE AFT LOWER ATTACH INBOARD HOLE FORWARD MATING SURFACE FOUND WITH CORROSION. CORROSION REPAIRED IAW EA 1-5750-122600. REPAIR CLASSIFIED AS MAJOR PER GMM 6-2-100.

Part: HINGE BRACKET — CORRODED (LT WING TE FLAP) · airframe 47,916 hrs · 12,664 cycles

LEFT WING, OUTBOARD FLAP OUTBOARD FORWARD HINGE AFT LOWER ATTACH OUTBOARD HOLE FORWARD MATING SURFACE FOUND WITH CORROSION. CORROSION REPAIRED IAW EA 1-5750-122600. REPAIR CLASSIFIED AS MAJOR PER GMM 6-2-100.

Part: LONGERON — CRACKED (ZONE 100) · airframe 47,916 hrs · 12,664 cycles

CENTER CARGO, LEFT STA 1531 TO 1541 LONGERON 40 FOUND CRACKED. CENTER CARGO LEFT STA 1531 TO 1541 LONGERON 40 CARRIED OUT REPAIR AS PER SRM 53-10-00 FIGURE 2 VOLUME I. LONGERON 40 LEFT FABRICATED AS PER DRAWING NR AFA7755. LONGERON 40 LEFT FROM STA 1531 TO 1551 REMOVED AND REPLACED AS PER SRM 53-10-00 FIGURE 2 VOLUME I AND SRM 51-33-01 VOLUME II. THIS REPAIR CLASSIFIED AS MAJOR AS PER GMM 6-2-100.

Part: LONGERON — CORRODED (ZONE 100) · corrosion level 2 · airframe 47,916 hrs · 12,664 cycles

CENTER CARGO BETWEEN LT STA 5-123 TO 1541 LONGERON 48 HAS CORROSION. REMOVED AND FOUND EXCEED LIMITS AS PER SRM 53-00-01 FIGURE 4 VOLUME I. ORIGINAL THICKNESS = 0.130", MATERIAL REMOVED = 0.060 INCH, MATERIAL REMAINING = 0.070 INCH, LONGERON FABRICATED AS PER DRAWING NR AFA7755, LONGERON 48 LEFT CARRIED REPAIR AS PER SRM 53-10-00 FIGURE 2 VOLUME I AND SRM 51-33-01 VOLUME II. FABRICATED LONGERON 48 LEFT FROM STA 5-123 TO 1541 REMOVED AND REPLACED AS PER SRM 53-10-00 FIGURE 2 VOLUME I AND SRM 51-33-01 VOLUME II. THIS REPAIR CLASSIFIED AS MAJOR AS PER GMM 6-2-100.

Part: HINGE — CHAFED (ZONE 500) · airframe 47,916 hrs · 12,664 cycles

LEFT WING, OUTBOARD FLAP OUTBOARD FORWARD HINGE AFT UPPER ATTACH INBOARD HOLE FOUND WITH SCORING MARK. SCORING REPAIRED IAW EA 1-5750-122600. REPAIR CLASSIFIED AS MAJOR PER GMM 6-2-100.

Part: HINGE BRACKET — CORRODED (ZONE 500) · airframe 47,916 hrs · 12,664 cycles

LEFT WING, OUTBOARD FLAP OUTBOARD FORWARD HINGE AFT LOWER ATTACH INBOARD HOLE AFT MATING SURFACE FOUND WITH CORROSION. CORROSION REPAIRED IAW EA 1-5750-122600. REPAIR CLASSIFIED AS MAJOR PER GMM 6-2-100.

Part: SKIN — CRACKED (ZONE 500) · airframe 47,916 hrs · 12,664 cycles

08 FASTENER HOLES FOUND CRACK INDICATION DURING OPEN HOLE HFEC INSPECTION AT LEFT WING LOWER SKIN ACCESS DOOR CUT OUT BETWEEN STA XORS = 690 AND STA XORS = 700. LEFT WING LOWER SKIN ACCESS DOOR CUT OUT BETWEEN STA XORS = 690 AND STA XORS = 700, 08 EACH FASTENER HOLES CARRIED OUT REPAIR AS PER EA NR 1-5710-122604 PART 1. TITLE, AD 2007-07-04, WINGS, LT LOWER SKIN PLANK CUT OUT AT 536AB, EIGHT ACCESS DOOR ATTACHMENT BORES WITH CRACK INDICATIONS PSE 57.23.01 ALI - REPAIR. THIS REPAIR CLASSIFIED AS MINOR AS PER GMM 6-2-100.

Part: LONGERON SPLICE — CORRODED (ZONE 100) · corrosion level 2 · airframe 47,916 hrs · 12,664 cycles

CENTER CARGO, BETWEEN LEFT STA 5-53 TO 5-73 LONGERON 48 SPLICE FOUND CORRODED. CENTER CARGO BETWEEN LEFT STA 5-53 TO 5-73 LONGERON 48 SPLICE CORROSION REMOVED AND FOUND EXCEED LIMIT AS PER SRM 53-00-01 FIGURE 4 VOLUME I. ORIGINAL THICKNESS = 0.125 INCH, MATERIAL REMOVED = 0.075 INCH, MATERIAL REMAINING = 0.050 INCH. SPLICE REMOVED AND REPLACED AS PER SRM 51-33-01 VOLUME II. THIS REPAIR CLASSIFIED AS MINOR AS PER GMM 6-2-100.

Part: SKIN — CRACKED (ZONE 600) · airframe 47,916 hrs · 12,664 cycles

04 FASTENER HOLES FOUND CRACK INDICATION DURING OPEN HOLE HFEC INSPECTION AT RIGHT WING LOWER SKIN ACCESS DOOR CUT OUT BETWEEN STA XORS = 690 AND STA XORS = 700. RIGHT WING LOWER SKIN ACCESS DOOR CUT OUT BETWEEN STA XORS = 690 AND STA XORS = 700, 04 FASTENER HOLES CARRIED OUT REPAIR AS PER EA NR 1-5710-122605 PART 1. TITLE, AD 2007-07-04, WINGS, RIGHT LOWER SKIN PLANK CUT OUT AT 636AB, FOUR ACCESS DOOR ATTACHMENT BORES WITH CRACK INDICATIONS PSE 57.23.01 ALI - REPAIR. THIS REPAIR CLASSIFIED AS MINOR AS PER GMM 6-2-100.

Part: HINGE BRACKET — CHAFED (ZONE 500) · airframe 47,916 hrs · 12,664 cycles

LEFT WING, OUTBOARD FLAP OUTBOARD FORWARD HINGE AFT UPPER ATTACH OUTBOARD HOLE FOUND WITH SCORING MARK. SCORING REPAIRED IAW EA 1-5750-122600. REPAIR CLASSIFIED AS MAJOR PER GMM 6-2-100.

Part: LONGERON — CRACKED (ZONE 100) · airframe 47,916 hrs · 12,664 cycles

CENTER CARGO, LEFT STA 5-21 LONGERON 41 FOUND EXISTING REPAIR SPLICE FITTING CRACKED. REPAIR SPLICE AT CENTER CARGO LT BS 5-21 LONGERON 41 REMOVED AND REPLACED AS PER SRM 51-33-01. SPLICE FABRICATED AS PER SRM 53-10-00. SPLICE PROCTECTED AND PAINTED AS PER SRM 51-21-01. REPAIR CLASSIFIED AS MAJOR AS PER GMM 6-2-100.

Part: SUPPORT FITTING — CRACKED (ZONE 200) · airframe 47,916 hrs · 12,664 cycles

DURING OPEN HOLE HFEC INSPECTION ON 0.460" DIAMETER HOLES, MAIN CARGO DOOR LOWER JAMB SUPPORT FITTING NR 1 FOUND WITH CRACK INDICATIONS AT HOLES NR A AND NR C. CARRIED OUT REPAIR AS PER SRM 53-50-00. THIS REPAIR CLASSIFIED AS MAJOR PER GMM 6-2-100.

Part: SUPPORT FITTING — CRACKED (ZONE 200) · airframe 47,916 hrs · 12,664 cycles

DURING OPEN HOLE HFEC INSPECTION, MAIN CARGO DOOR LOWER JAMB SUPPORT FITTING NR 7 UPPER WEB FIRST LAYER FOUND WITH CRACK INDICATION (APPROXIMATELY 3 O'CLOCK POSITION) AT HOLE NR C. CARRIED OUT REPAIR AS PER EA 1-5310-125561. THIS REPAIR CLASSIFIED AS MAJOR AS PER GMM 6-2-100.

Part: LONGERON — CRACKED (ZONE 100) · airframe 47,916 hrs · 12,664 cycles

CENTER CARGO, LEFT STA 1701 LONGERON 50 FOUND CRACKED. FABRICATED AS PER EA 1-5310-122601. INSTALLED AS PER SRM 53-10-00. FABRICATED AS PER DRAWING AFA7772. LONGERON REMOVED AND REPLACED AS PER SRM 53-10-00. REPAIR CLASSIFIED AS MAJOR AS PER GMM 6-2-100.

Part: SUPPORT FITTING — CRACKED (ZONE 200) · airframe 47,916 hrs · 12,664 cycles

DURING OPEN HOLE HFEC INSPECTION ON 0.460" DIAMETER HOLES, MAIN CARGO DOOR LOWER JAMB SUPPORT FITTING NR 7 FOUND WITH CRACK INDICATIONS AT HOLES NR A, NR B, NR C AND NR D. MAIN CARGO DOOR LOWER JAMB SUPPORT FITTING NR 7 REMOVED AND REPLACED AS PER SRM 51-31-01 AND 51-33-01. THIS REPAIR CLASSIFIED AS MAJOR AS PER GMM 6-2-100.

Part: FITTING — CRACKED (ZONE 200) · airframe 47,916 hrs · 12,664 cycles

DURING OPEN HOLE HFEC INSPECTION ON 0.460 INCH DIAMETER HOLES, MAIN CARGO DOOR LOWER JAMB SUPPORT FITTING NR 2 FOUND WITH CRACK INDICATIONS AT HOLES NR A AND NR D. CARRIED OUT REPAIR AS PER SRM 53-50-00. THIS REPAIR CLASSIFIED AS MAJOR PER GMM 6-2-100.

Part: SUPPORT FITTING — CRACKED (ZONE 200) · airframe 47,916 hrs · 12,664 cycles

DURING OPEN HOLE HFEC INSPECTION ON 0.460 INCH DIAMETER HOLES, MAIN CARGO DOOR LOWER JAMB SUPPORT FITTING NR 4 FOUND WITH CRACK INDICATIONS AT HOLES NR A, NR B, NR C AND NR D. CARRIED OUT REPAIR AS PER SRM 53-50-00. THIS REPAIR CLASSIFIED AS MAJOR PER GMM 6-2-100.

Part: SUPPORT FITTING — CRACKED (ZONE 200) · airframe 47,916 hrs · 12,664 cycles

DURING OPEN HOLE HFEC INSPECTION, MAIN CARGO DOOR LOWER JAMB SUPPORT FITTING NR 7 UPPER WEB SECOND LAYER FOUND WITH CRACK INDICATION (APPROXIMATELY 8 O'CLOCK POSITION) AT HOLE NR D. CARRIED OUT REPAIR AS PER EA 1-5310-125561. THIS REPAIR CLASSIFIED AS MAJOR AS PER GMM 6-2-100.

Part: SPLICE — DAMAGED (ZONE 100) · airframe 43,314 hrs · 11,654 cycles

AFT CARGO RT L38, STA 1865 FOUND SPLICE DAMAGED. [06-18-07] REPAIR CARRIED OUT AS PER SRM 51-33-01 VOLUME II AND DRAWING AFA7105. REPAIR CLASSIFIED AS MINOR AS PER GMM 6-2-100.

Part: LONGERON — DAMAGED (ZONE 100) · airframe 43,314 hrs · 11,654 cycles

FUSELAGE, CAC COMPARTMENT AT STA 6-100, LONGERON 40L FOUND LONGERON WITH FREEZE PLUG INSTALLED. [06-19-07] REPAIR CARRIED OUT AT FUSELAGE - CAC COMPARTMENT AT STA 6-100, LONGERON 40L AS PER SRM 53 -10-00 FIGURE 2 VOLUME I.

Part: FLOORBEAM — NONE (ZONE 100) · airframe 43,314 hrs · 11,654 cycles

EXISTING REPAIR, FUSELAGE STA 6-50 FLOORBEAM REPAIR AT RT BUTT LINE 60", AS SEEN FROM THE FWD LOWER CARGO COMPARTMENT, REPAIR REQUIRES EVALUATION. EXISTING REPAIR EVALUATED AND FOUND PREVIOUSLY ACCOMPLISHED AS PER SRM 53-00-01 FIGURE 8 VOLUME I. REPAIR CLASSIFIED AS MAJOR AS PER GMM 6-2-100.

Part: SKIN — CORRODED (BS 1941-2164) · airframe 43,314 hrs · 11,654 cycles

RT EXTERIOR SKIN UNDERNEATH BODY FAIRING AREA FOUND CORROSION AT SEVERAL PLACES FROM STA 1941-2164. [06-18-07] REPAIR CARRIED OUT AS PER SRM 53-20-00 FIGURE 13 VOLUME I. REPAIR CLASSIFIED AS MAJOR AS PER GMM 6-2-100.

Part: PLATE — DAMAGED (ZONE 100) · airframe 43,314 hrs · 11,654 cycles

CENTER CARGO STA 1841 STEP FORWARD WALL FOUND PLATE DAMAGED. [06-18-07] REPAIR CARRIED OUT AS PER SRM 53- 00-01 FIGURE 16 VOLUME I. REPAIR CLASSIFIED AS MINOR AS PER GMM 6-2-100.

Part: SKIN — MISREPAIRED (ZONE 100) · airframe 43,314 hrs · 11,654 cycles

APPROXIMATELY AT STA 6-100, LONGERON 40L FOUND EXISTING REPAIR. EXISTING REPAIR AT STA 6-100, LONGERON 40L EVALUATED AND FOUND NOT CARRIED OUT AS PER SRM 53-20-00 FIG 2 VOL I. REPAIR CARRIED OUT AS PER FEDEX EA 1-5330-112421A - FUSELAGE, PLATES AND SKINS, EXISTING REPAIR AT FUSELAGE STATION 1129 L40L AND L43L - INTERIM. CLASSIFIED AS MAJOR REPAIR AS PER FEDEX GMM 6-2-100.

Part: SEAT TRACK — NONE (ZONE 200) · airframe 43,314 hrs · 11,654 cycles

EXISTING REPAIR, REF EA NR 1-5310-85955, TITLE: FUSELAGE, MAINFRAME, SEAT TRACK SPLICE REPAIRS Y=1781, X=27.50, 47.5 AND -27.5. EXISTING REPAIR EVALUATED AND FOUND ACCOMPLISHED AS PER FEDEX EA NR 1-5310-85955, TITLE: "FUSELAGE - MAIN FRAME, SEAT TRACK SPLICE REPAIRS Y=1781, X=27.50, 47.5 AND -27.5". REPAIR CLASSIFIED AS MAJOR AS PER GMM 6-2-100. THIS SDR SUBMITTED IN ERROR- ADMINISTRATOR.

Part: SKIN — MISREPAIRED (ZONE 100) · airframe 43,314 hrs · 11,654 cycles

APPROXIMATELY AT STA 6-100, LONGERON 43L FOUND EXISTING REPAIR. EXISTING REPAIR AT STA 6-100, LONGERON 43L EVALUATED AND FOUND NOT CARRIED OUT AS PER SRM 53-20-00 FIG 2 VOL I. REPAIR CARRIED OUT AS PER FEDEX EA 1-5330-112421A - FUSELAGE, PLATES AND SKIN, EXISTING REPAIR AT FUSELAGE STATION 1129 L40L AND L43L - INTERIM. CLASSIFIED AS MAJOR REPAIR AS PER FEDEX GMM 6-2-100.

Part: SKIN — NONE (ZONE 200) · airframe 43,314 hrs · 11,654 cycles

APPROXIMATELY BETWEEN STA 790-808, LONGERON 4L-5L FOUND EXISTING REPAIR. REPAIR CARRIED OUT AT APPROXIMATELY BETWEEN STA 790-808, LONGERON 4L-5L AS PER 53-20-00 FIGURE 2 VOLUME I. REPAIR CLASSIFIED AS MAJOR AS PER GMM 6-2-100. THIS SDR SUBMITTED IN ERROR- ADMINISTRATOR.

Part: FRAME — NONE (ZONE 200) · airframe 43,314 hrs · 11,654 cycles

EXISTING REPAIR, UPPER CARGO COMPARTMENT, LT SIDEWALL STRUCTURE FRAME AT STA 1701, L-12L, FOUND WITH REPAIR DOUBLER. EXISTING REPAIR EVALUATED AND FOUND PREVIOUSLY ACCOMPLISHED AS PER SRM 53-30-00 FIGURE 1 VOLUME I. REPAIR CLASSIFIED AS MAJOR AS PER GMM 6-2-100.

Part: SKIN — DAMAGED (ZONE 500) · airframe 43,314 hrs · 11,654 cycles

EXISTING REPAIR, LT WING I/B FLAP UPPER SURFACE FOUND WITH EXTERNAL PATCH AT XIFH 233 YIFH 17. EXISTING REPAIR EVALUATED AND FOUND PREVIOUSLY ACCOMPLISHED AS PER SRM 57-10-00 FIGURE 38 VOLUME I. REPAIR CLASSIFIED AS MAJOR AS PER GMM 6-2-100.

Part: SKIN — NONE (ZONE 500) · airframe 43,314 hrs · 11,654 cycles

EXISTING REPAIR, LT WING I/B FLAP UPPER SURFACE FOUND WITH EXTERNAL PATCH AT XIFH 216 YIFH 70. EXISTING REPAIR AT LT WING I/B FLAP UPPER SURFACE XIFH 216, YIFH 70, EVALUATED AND FOUND ACCOMPLISHED AS PER SRM 57-10-00 FIGURE 38 VOLUME I. REPAIR CLASSIFIED AS MAJOR AS PER GMM 6-2-100. THIS SDR SUBMITTED IN ERROR- ADMINISTRATOR.

Part: SKIN — NONE (ZONE 100) · airframe 43,314 hrs · 11,654 cycles

EXISTING REPAIR, CTR CARGO, AFT DOOR JAMB EXTERIOR FOUND EDGE PATCH. EXISTING REPAIR AT CTR CARGO, AFT DOOR JAMB EXTERIOR EDGE PATCH EVALUATED AND FOUND ACCOMPLISHED AS PER SRM 53-50-00 FIGURE 17 VOLUME I. REPAIR CLASSIFIED AS MAJOR AS PER GMM 6-2-100. THIS SDR SUBMITTED IN ERROR- ADMINISTRATOR.

Part: SKIN — DAMAGED (ZONE 600) · airframe 43,314 hrs · 11,654 cycles

EXISTING REPAIR, RT WING I/B FLAP UPPER SURFACE FOUND EXISTING PATCH AT XIFH 217 YIFH 65. EXISTING REPAIR EVALUATED AND FOUND PREVIOUSLY ACCOMPLISHED AS PER SRM 57-10-00 FIGURE 38 VOLUME I. REPAIR CLASSIFIED AS MAJOR AS PER GMM 6-2-100.

Part: SKIN — NONE (ZONE 600) · airframe 43,314 hrs · 11,654 cycles

EXISTING REPAIR, RT WING I/B FLAP UPPER SURFACE FOUND EXISTING PATCH AT XIFH 283, YIFH 30. EXISTING REPAIR AT RT WING I/B FLAP UPPER SURFACE XIFH 283, YIFH 30, EVALUATED AND FOUND ACCOMPLISHED AS PER SRM 57-10-00 FIGURE 38 VOLUME I. REPAIR CLASSIFIED AS MAJOR AS PER GMM 6-2-100. THIS SDR SUBMITTED IN ERROR- ADMINISTRATOR.

Part: SKIN — NONE (ZONE 600) · airframe 43,314 hrs · 11,654 cycles

EXISTING REPAIR, RT WING I/B FLAP UPPER SURFACE FOUND EXISTING PATCH AT XIFH 157 YIFH 64. EXISTING REPAIR AT RT WING I/B FLAP UPPER SURFACE XIFH 157, YIFH 64, EVALUATED AND FOUND ACCOMPLISHED AS PER SRM 57-10-00 FIGURE 38 VOLUME I. REPAIR CLASSIFIED AS MAJOR AS PER GMM 6-2-100. THIS SDR SUBMITTED IN ERROR- ADMINISTRATOR

Part: SKIN — NONE (ZONE 600) · airframe 43,314 hrs · 11,654 cycles

EXISTING REPAIR, RT WING I/B FLAP UPPER SURFACE FOUND EXISTING PATCH AT XIFH 168, YIFH 64. EXISTING REPAIR AT RT WING I/B FLAP UPPER SURFACE XIFH 168, YIFH 64, EVALUATED AND FOUND ACCOMPLISHED AS PER SRM 57-10-00 FIGURE 38 VOLUME I. REPAIR CLASSIFIED AS MAJOR AS PER GMM 6-2-100. THIS SDR SUBMITTED IN ERROR- ADMINISTRATOR.

Part: SPAR CAP — CORRODED (ZONE 600) · airframe 43,314 hrs · 11,654 cycles

RIGHT WING, TRAILING EDGE REAR SPAR UPPER CAP FOUND CORRODED AT XORS 1038. [06-18-07] REPAIR CARRIED OUT AS PER FEDEX EA 1-5710-109902. REPAIR CLASSIFIED AS MAJOR AS PER GMM 6-2-100.

Part: SKIN — DAMAGED (ZONE 500) · airframe 43,314 hrs · 11,654 cycles

EXISTING REPAIR, DOUBLER PATCH FOUND ON LT WING L/E AT XIS247. REPAIR CARRIED OUT AT DOUBLER PATCH ON LT WING L/E AT XIS247 AS PER FEDEX EA NR 1- 5710-112420, REPAIR CLASSIFIED AS MINOR AS PER GMM 6-2-100.

Part: HINGE — CORRODED (ZONE 600) · airframe 43,314 hrs · 11,654 cycles

RIGHT WING, O/B FLAP O/B HINGE AFT FAIRING AFT STRUT FWD BOLT HOLE FOUND CORROSION. [06-18-07] REPAIR CARRIED OUT AS PER FEDEX EA 1-5750-109897. REPAIR CLASSIFIED AS MINOR AS PER GMM 6-2-100.

Part: SPAR CAP — CORRODED (ZONE 600) · airframe 43,314 hrs · 11,654 cycles

RIGHT WING, TRAILING EDGE REAR SPAR LOWER CAP FOUND CORROSION AT XORS 1054. [06-18-07] REPAIR CARRIED OUT AS PER FEDEX EA 1-5710-109898. REPAIR CLASSIFIED AS MAJOR AS PER GMM 6-2-100.

Part: SPAR CAP — CORRODED (ZONE 600) · airframe 43,314 hrs · 11,654 cycles

RIGHT WING, TRAILING EDGE REAR SPAR LOWER CAP FOUND CORROSION AT XORS 1067. [06-19-07]

Part: SKIN — CRACKED (ZONE 500) · airframe 43,314 hrs · 11,654 cycles

LEFT WING, NR 1 LEADING EDGE SLAT I/B EDGE FOUND CRACK NEAR ALIGNMENT PIN HOLE. REPAIR CARRIED OUT PER FEDEX EA 1-5710-109891. REPAIR CLASSIFIED AS MAJOR AS PER GMM 6-2-100.

Part: SEAT TRACK — CORRODED (ZONE 200) · airframe 43,314 hrs · 11,654 cycles

UPPER CARGO COMPARTMENT, SEAT TRACK RBL 75 CORRODED AT STA 1301 TO STA 1361. [06-18-07] REPAIR CARRIED OUT AT UPPER CARGO COMPARTMENT, SEAT TRACK RBL 75, STA 1267 TO STA 1391 AS PER SRM 53-70-00 FIGURE 1 VOLUME I. REPAIR CLASSIFIED AS MAJOR AS PER GMM 6-2-100.

Part: STRINGER — CRACKED (ZONE 100) · airframe 43,314 hrs · 11,654 cycles

CTR CARGO: UNDER FLOOR STA 1821, RT X=56 FOUND STRINGER JOINT END CRACKED. [06-19-07] REPAIR CARRIED OUT AT CTR CARGO: UNDER FLOOR STA 1821, STRINGER S43R JOINT END AS PER SRM 51-33-01 VOLUME II.

Part: HINGE FITTING — CRACKED (ZONE 600) · airframe 43,314 hrs · 11,654 cycles

RIGHT WING, O/B FLAP I/B HINGE FITTING FOUND CRACK AT STA XOF 556. [06-18-07] RIGHT WING - O/B FLAP ASSEMBLY REMOVED AND REPLACED AS PER AMM 27-50-30-4. ADJUSTMENT AND OPERATIONAL TEST CARRIED OUT AS PER AMM 27-50-00-5, FOUND SATIS.

Part: ANGLE — DAMAGED (ZONE 100) · airframe 38,618 hrs · 10,596 cycles

DURING ACCOMPLISHMENT OF LEFT LOWER AUXILIARY TANK CAP ANGLE. REPAIR FOUND 1 FASTENER HOLE ELONGATED. REPAIR CARRIED OUT AT ONE (01) EACH FASTENER WITH ELONGATED HOLE AT LEFT LOWER AUXILIARY TANK CAP ANGLE AS PER FEDEX EA NR 1-5310-90694, TITLE: "FUSELAGE CAP ANGLE LEFT UNDER WING BARREL STRUCTURE AT STATION Y=1298.6, XCW 46, CRACK ANGLE, FABRICATION AND SPLICE INSTALLATION".

Part: WEB — PUNCTURED (ZONE 100) · airframe 38,618 hrs · 10,596 cycles

CENTER CARGO LEFT HAND STATION 1841 X= 40 AFT WEB FOUND PUNCTURED. WEB REMOVED AND REPLACED WITH NEW FABRICATED WEB AS PER DRAWING AGA7170 AND INSTALLED AS PER SRM 51-31-01 VOLUME II.

Part: LONGERON — CORRODED (ZONE 100) · airframe 38,618 hrs · 10,596 cycles

CENTER CARGO STATION 5-123 TO STATION 1541 LONGERON 48 RIGHT FOUND CORRODED. CTR CARGO COMPARTMENT STATION 5-123 TO STATION 1541 LONGERON 48 RIGHT, REPAIR CARRIED OUT AS PER SRM 53-10-00 FIG 2 VOL I. REPAIR CLASSIFIED AS MAJOR AS PER FEDEX GMM 6-2-100.

Part: LONGERON — CORRODED (ZONE 100) · airframe 38,618 hrs · 10,596 cycles

CENTER CARGO COMPARTMENT STATION 1561 TO STA 1581 LONGERON 48 LEFT HAND FOUND CORRODED. CTR CARGO COMPARTMENT STATION 1561 TO STA 1581 LONGERON 48 LT REPAIR CARRIED OUT AS PER SRM 53-10-00 FIG 2 VOL I . REPAIR CLASSIFIED AS MAJOR AS PER FEDEX GMM 6-2-100.

Part: FITTING — CORRODED (ZONE 700) · corrosion level 2 · airframe 38,618 hrs · 10,596 cycles

UPON REMOVAL OF CLG SHOCK STRUT ASSY FOUND LT TRUNNION SUPPORT FITTING FWD MOUNTING HOLE, SHEAR PIN HOLE & AFT MOUNTING HOLE WITH CORROSION. LT TRUNNION SUPPORT FITTING FORWARD MOUNTING HOLE, SHEAR PIN HOLE, AND AFT MOUNTING HOLE CORROSION REMOVED AND REPAIR CARRIED OUT AS PER FEDEX EA1- 5340-9070. TITLE: FUSELAGE - CENTER LANDING GEAR LT SUPPORT FITTING CORROSION REPAIR.

Part: FITTING — CORRODED (ZONE 700) · corrosion level 2 · airframe 38,618 hrs · 10,596 cycles

UPON REMOVAL OF CLG SHOCK STRUT ASSY FOUND WHEEL WELL SIDE LT TRUNNION FITTING LOWER MATING SURFACE WITH CORROSION. LT TRUNNION FITTING LOWER MATING SURFACE CORROSION REMOVED AND REPAIR CARRIED OUT AS PER FEDEX EA1-5340-90705, TITLE: FUSELAGE CENTER LANDING GEAR LT SUPPORT FITTING CORROSION REPAIR.

Part: LONGERON — CORRODED (ZONE 800) · airframe 38,618 hrs · 10,596 cycles

CAC COMPARTMENT RIGHT HAND BILGE AREA LONGERON 48R STATION 1139 FOUND EDGE WITH CORROSION. REPAIR CARRIED OUT AS PER FEDEX EA 1-5310-94573 (TITLE: FUSELAGE- MAINFRAME- BODY STATION Y=1134.000, THROUGH Y=1142.000 / LONGERON 48 (RH) SPLICE CORROSION REWORK & REPAIR). REPAIR CLASSIFIED AS MAJOR AS PER FEDEX GMM 6-2-100.

Part: HINGE BRACKET — CORRODED (ZONE 600) · airframe 38,618 hrs · 10,596 cycles

RT WING OUTBOARD FLAP INBOARD AFT HINGE BRACKET FORWARD FITTING ATTACH HOLE AT OUTBOARD AFT POSITION FOUND CORRODED. CORROSION REMOVED AND REPAIR CARRIED OUT AS PER FEDEX EA 1-5750-90700.

Part: HINGE BRACKET — CORRODED (ZONE 500) · airframe 38,618 hrs · 10,596 cycles

LEFT HAND WING OUTBOARD FLAP INBOARD AFT HINGE BRACKET FORWARD FITTING ATTACH HOLE AT OUTBOARD AFT POSITION FOUND CORRODED. CORROSION REMOVED AND REPAIR CARRIED OUT AS PER FEDEX EA 1-5750-90702.

Part: HINGE BRACKET — CORRODED (ZONE 600) · airframe 38,618 hrs · 10,596 cycles

RIGHT HAND WING OUTBOARD FLAP INBOARD AFT HINGE BRACKET AFT FITTING FORWARD ATTACH HOLE FOUND CORRODED. CORROSION REMOVED AND REPAIR CARRIED OUT AS PER FEDEX EA 1-5750-90699.

Part: HINGE BRACKET — CORRODED (ZONE 600) · airframe 38,618 hrs · 10,596 cycles

RIGHT HAND WING OUTBOARD FLAP INBOARD AFT HINGE BRACKET FORWARD FITTING ATTACH HOLE AT INBOARD AFT POSITION FOUND CORRODED. CORROSION REMOVED AND REPAIR CARRIED OUT AS PER FEDEX EA 1-5750-90701.

Part: LONGERON — CORRODED (ZONE 100) · corrosion level 2 · airframe 38,618 hrs · 10,596 cycles

CENTER CARGO COMPARTMENT STATION 1571 LONGERON 48 RIGHT HAND FOUND CORRODED AROUND FASTENER AREA. CORROSION REMOVED AT CENTER CARGO COMPARTMENT STATION 1571 LONGERON 48 RIGHT FOUND EXCEEDED LIMIT AS PER SRM 53-00-01 FIGURE 3 VOLUME I. ORIGINAL THICKNESS=0.100", REMAINING THICKNESS=0.062", MATERIAL REMOVED=0.038". REFER TO SNRM N1269 FOR LONGERON 48R REPLACEMENT FROM STATION 5-123 TO STATION 1588.

Part: DOOR FRAME — CORRODED (ZONE 100) · airframe 38,618 hrs · 10,596 cycles

UPON REMOVAL OF LOOSE SEALANT AFT DOOR JAMB FORWARD CORNER FOUND CORRODED, SNRM N1260: AFT CARGO COMPARTMENT: AFT DOOR JAMB FORWARD CORNER, CORRODED AREA FOUND CRACKED. CARRIED OUT REPAIR AS PER FEDEX EA NR 1-5350-90711, TITLE: "FUSELAGE - AFT CARGO DOOR JAMB LOWER BEAM CORROSION AND CRACK, REPAIR".

Part: DOOR FRAME — CORRODED (ZONE 100) · airframe 38,618 hrs · 10,596 cycles

SNRM N1259: AFT CARGO COMPARTMENT: UPON REMOVAL OF LOOSE SEALANT AFT DOOR JAMB STA 1935 ADJACENT TO FWD LATCH FOUND CORRODED.**S/D COMING**

Part: SUPPORT — CORRODED (ZONE 700) · corrosion level 2 · airframe 38,618 hrs · 10,596 cycles

UPON REMOVAL OF CLG SHOCK STRUT ASSEMBLY, FOUND WHEEL WELL SIDE RIGHT TRUNNION FITTING LOWER MATING SURFACE WITH CORROSION. RIGHT HAND TRUNNION FITTING LOWER MATING SURFACE CORROSION. REMOVED AND REPAIR CARRIED OUT AS PER FEDEX EA#1-5340-90704, TITLE:"FUSELAGE-CENTER LANDING GEAR RIGHT HAND SUPPORT FITTING CORROSION REPAIR".

Part: DOOR — CRACKED (RT MLG) · airframe 38,618 hrs · 10,596 cycles

RT MLG FLIPPER DOOR FORWARD HINGE AREA SUSPECTED WITH A HAIR LINE CRACK. REPAIR CARRIED OUT AT RT MLG FLIPPER DOOR FORWARD HINGE. CRACKED AREA IAW SRM 52-10-00 FIGURE 18 VOLUME I. REPAIR CLASSIFIED AS MINOR IAW GMM 6-2-100.

Part: LATCH — CORRODED (RT WING) · airframe 38,618 hrs · 10,596 cycles

SNRM N0539: RT WING LEADING EDGE ACCESS PANEL 617CB INTERIOR FRONT, SPAR LOWER CAP, UPPER SURFACE FOUND CORROSION AT LATCH CONTACT AREA.** S/D COMING**

Part: HINGE FITTING — CORRODED (ZONE 500) · airframe 38,618 hrs · 10,596 cycles

FOUND LEFT WING OUTBOARD FLAP INBOARD HINGE SUPPORT FITTING FOUND CORROSION AT OUTBOARD NR 3 BOLT HOLE.

Part: FLOORBEAM — CHAFED (ZONE 100) · airframe 38,618 hrs · 10,596 cycles

FOUND CENTER CARGO DOOR WAY CEILING AREA STA 1721, X=-98 MAIN DECK FLOORBEAM LOWER SIDE FOUND CHAFED. REPAIR CARRIED OUT AT CENTER CARGO DOOR WAY CEILING AREA AT STA 1721, X=-98 MAIN DECK FLOOR BEAM LOWER SIDE AS PER FEDEX EA 1-5310-90708, TITLE: "FUSELAGE- FLOOR BEAM CHAFING AT FUSELAGE STATION Y=1721, X=-98 REPAIR". REPAIR CLASSIFIED AS MINOR AS PER GMM 6-2-100.

Part: HINGE FITTING — CORRODED (ZONE 600) · airframe 38,618 hrs · 10,596 cycles

FOUND RIGHT WING OUTBOARD FLAP INBOARD HINGE SUPPORT FITTING FOUND CORROSION AT INBOARD NR 2 BOLT HOLE. REFER TO SNRM NR N00830 FOR RIGHT HAND WING OUTBOARD FLAP REPLACEMENT.

Part: SUPPORT FITTING — CORRODED (ZONE 600) · airframe 38,618 hrs · 10,596 cycles

RIGHT WING OUTBOARD FLAP INBOARD HINGE SUPPORT FITTING FOUND CORROSION AT OUTBOARD NR 3 BOLT HOLE. RT WING OUTBD FLAP REMOVED & REPLACED AS PER AMM 27-50-30-4. VANE ADJUSTMENT CARRIED OUT AS PER AMM 27-50-32-5 FOUND SATIS. OUTBD FLAP OPERATIONAL TEST & ADJUSTMENT CARRIED OUT AS PER AMM 27-50-00-5 FOUND SATIS.

Part: SUPPORT FITTING — CORRODED (ZONE 600) · airframe 38,618 hrs · 10,596 cycles

RIGHT WING OUTBOARD FLAP INBOARD HINGE SUPPORT FITTING FOUND CORROSION AT OUTBOARD NR 2 BOLT HOLE. REFER TO SNRM NO. N0830 FOR RIGHT HAND WING OUTBOARD FLAP REPLACEMENT.

Part: SPLICE — CRACKED (ZONE 100) · airframe 38,618 hrs · 10,596 cycles

FORWARD CARGO STATION 1119 TO STATION 6-10 L52 SPLICE FOUND CRACKED. FORWARD CARGO STATION 1119 TO STATION 6-10 L52 SPLICE REMOVED AND REPLACED AS PER SRM 51-33-01 VOLUME II. REPAIR CLASSIFIED AS MINOR AS PER GMM 6-2-100.

Part: STRUCTURE — CRACKED (ZONE 100) · airframe 38,618 hrs · 10,596 cycles

FOUND FORWARD CARGO STATION 1129 L52 FOUND CRACKED. CARRIED OUT REPAIR AT CRACKED LONGERON 52 LOCATED AT FORWARD CARGO STATION 1129 AS PER SRM 53-10-00 FIGURE 1 VOLUME I.

Part: SKIN — CHAFED (ZONE 100) · airframe 38,618 hrs · 10,596 cycles

CENTER CARGO DOOR CUTOUT STA 1708 L40R TO L41R EXTERIOR SKIN EDGE FOUND CHAFED. REPAIR CARRIED OUT AT CENTER CARGO DOOR CUTOUT STA 1708 L40R TO L41R EXTERIOR SKIN EDGE CHAFFED AREA AS PER SRM 53-50-00 FIGURE 16 VOLUME I AND FEDEX EA # 1-5350- 90710, TITLE: "FUSELAGE - CENTER CARGO DOOR FRAME INSTALLATION / DOOR JAMB - EXISTING BUSHING REPAIR".

Part: DOOR — CRACKED (ZONE 700) · airframe 38,618 hrs · 10,596 cycles

FOUND LEFT HAND MAIN LANDING GEAR FLIPPER DOOR FORWARD HINGE FOUND WITH A CRACKED APPROXIMATELY 1.0" IN LENGTH. REPAIR CARRIED OUT AT LEFT HAND MAIN LANDING GEAR FLIPPER DOOR FORWARD HINGE CRACKED AREA AS PER SRM 52-10-00 FIGURE 18 VOLUME I. REPAIR CLASSIFIED AS MINOR AS PER GMM 6-2-100.

Part: STRINGER — CRACKED (ZONE 600) · airframe 38,618 hrs · 10,596 cycles

DURING HFEC INSPECTION, FOUND CRACK ON RIGHT WING STRINGER 43. REPAIRED AS PER SRM 57-20-00 FIG. 10 VOL. I. REPAIR CLASSIFIED AS MAJOR AS PER FEDEX GMM 6-2-100.

Part: STRINGER — CRACKED (ZONE 600) · airframe 38,618 hrs · 10,596 cycles

DURING HFEC INSPECTION, FOUND CRACK ON RIGHT WING STRINGER 14. REPAIRED AS PER SRM 57-20-00 FIG. 10 VOL. I. AND CLIP REMOVED & REPLACED AS PER SRM 51-33-01 VOL.II. FABRICATED CLIP AS PER FEDEX EA 1-5720-90712 - WINGS - STRINGER 14 RH REPAIR PER SRM VOL.I 57-20-00 FIGURE 10 - FX ARB2689-501 CLIP FABRICATION. REPAIR CLASSIFIED AS MAJOR AS PER FEDEX GMM 6-2-100.

Part: HINGE BRACKET — CRACKED (ZONE 500) · airframe 38,618 hrs · 10,596 cycles

LEFT WING OUTBOARD FLAP INBOARD FORWARD HINGE BRACKET AFT UPPER LINK FOUND CRACKED. COMPLIED WITH FEDEX EA 1-5750-90703 (TITLE: WINGS LEFT HAND WING TRAILING EDGE FLAP, INBOARD HINGE, TENSION STRAP - COMPLIANCE WITH BOEING S/B 57- 10). REPAIR CLASSIFIED AS MINOR AS PER FEDEX GMM 6-2-100.

Part: SKIN — CORRODED (ZONE 500) · airframe 38,618 hrs · 10,596 cycles

LEFT HAND WING UPPER TRAILING EDGE PANEL FOUND BULGING AT XORS 1036. REMOVED CORROSION AT LEFT HAND WING UPPER TRAILING EDGE PANEL, XORS 1036 AS PER SRM 51-21-011 VOLUME II. ORIGINAL THICKNESS=0.140, MATERIAL REMOVED 0.100, REMAINING THICKNESS=0.040", FOUND EXCEEDED LIMIT AS PER SRM 57-20-00, FIGURE 16 VOLUME I. REPAIR CARRIED OUT AS PER FEDEX EA 1-5710-90697.

Part: STRINGER — CRACKED (ZONE 600) · airframe 38,618 hrs · 10,596 cycles

DURING HFEC INSPECTION, FOUND CRACK ON RIGHT WING STRINGER 13. REPAIRED AS PER SRM 57-20-00 FIG. 10 VOL. I. AND CLIP REMOVED & REPLACED AS PER SRM 51-33-01 VOL.II. FABRICATED CLIP AS PER FEDEX EA 1-5720-90713 - WINGS - STRINGER 13 RH REPAIR PER SRM VOL.I 57-20-00 FIGURE 10 - FX ARB0449 CLIP FABRICATION. REPAIR CLASSIFIED AS MAJOR AS PER FEDEX GMM 6-2-100.

Part: SKIN — CORRODED (ZONE 200) · airframe 38,618 hrs · 10,596 cycles

MAIN DECK COMPARTMENT R3 DOOR CUTOUT BOTTOM FOUND CORRODED. REMOVED AS PER SRM 51-21-01 VOLUME II. ORIGINAL THICKNESS = 0.270", MATERIAL REMOVED = 0.057", MATERIAL REMAINING = 0.213" AND FOUND WITHIN LIMIT AS PER SRM 53-00-01 VOLUME I. REPAIR CLASSIFIED AS MINOR AS PER GMM 6-2-100.

Part: STRUCTURE — CRACKED (ZONE 500) · airframe 38,618 hrs · 10,596 cycles

HFEC INSPECTED CARRIED OUT AND CRACK FOUND ON LOWER LEFT HAND WING STRINGER S44. REPAIR CARRIED OUT ON CRACK FOUND AT LEFT HAND WING STRINGER 44 AS PER FEDEX EA 1-5720-90707, TITLE: "WINGS - STRINGER 44 LEFT HAND CRACK AT WING STATION XORS=508 - REPAIR". REPAIR CLASSIFIED AS MAJOR AS PER GMM 6-2-100.

Part: ANGLE — CRACKED (ZONE 100) · airframe 38,618 hrs · 10,596 cycles

FOUND CENTER TANK LEFT LOWER CAP ANGLE AT STA 1298.6 SUSPECT CRACK. CTR TANK LT LOWER CAP ANGLE AT STA 1298.6 AREA REPAIRED AS PER FEDEX EA 1-5310-90694 (FUSELAGE - CAP ANGLE LT UNDERWING BARREL STRUCTURE AT STA 1298.6, XCW 46, CRACK - ANGLE FABRICATION & SPLICE INSTALLATION). REPAIR CLASSIFIED AS MAJOR AS PER FEDEX GMM 6-2-100.

Part: STRINGER — CRACKED (ZONE 600) · airframe 38,618 hrs · 10,596 cycles

HFEC INSP CARRIED OUT AND CRACK FOUND ON RIGHT WING STRINGER S7. REPAIRED AS PER SRM 57-20-00 FIG. 10 VOL. I. REPAIR CLASSIFIED AS MAJOR AS PER FEDEX GMM 6-2-100.

Part: SKIN — CRACKED (ZONE 600) · airframe 38,618 hrs · 10,596 cycles

RIGHT WING FIXED LEADING EDGE FOUND CRACKED AT TELESCOPE DUCT UPPER CUTOUT. REPAIR CARRIED OUT AT RIGHT HAND WING FIXED LEADING EDGE TELESCOPING DUCT UPPER SKIN CUTOUT AS PER FEDEX EA 1-5730-90693, TITLE "WINGS - RT WING LEADING EDGE SKIN CRACKS AT TELESCOPING DUCT CUTOUT".

Part: ENGINE — MALFUNCTIONED (NR 3) · airframe 38,553 hrs · 10,583 cycles

ABOUT 2-3 MIN AFTER BLEED SHUTDOWN, CREW GOT STICK SHAKER, A/S ALT LOSS WITH NR 3 ENG VIBRATION. BROUGHT NR 3 THROTTLE TO IDLE AND VIBRATION REDUCED BUT STILL NOTICEABLE & NR 3 EVM TURB MONITOR WAS CLIMBING THRU 4 TOWARDS 5. ELECTED TO SHUTDOWN NR 3 ENG & VIBRATION STOPPED. NR 3 EGT ABOUT 50 DEGREES ABOVE NR 1 & 2, REV U/L INDICATOR ILLUMINATED IN EPR GAUGE. COMPLETED BOROSCOPE INSP OF HPT BLADES FOUND 32 BLADES WITH DAMAGE & 8 OF THOSE BLADES MISSING AT LEAST HALF OF BLADE. BLADES THAT ARE DAMAGED ARE FRAGMENTED IN NATURE. ALSO, DURING INSPECTION FOUND AFT COOLING DUCT THAT SURROUNDS HPT BROKEN IN TWO. REMOVED AND REPLACED ENGINE.

Part: SENSOR — DEFECTIVE (ZONE 400) · airframe 37,780 hrs · 10,417 cycles

APPROX 2:40 HOURS INTO FLIGHT, LEVEL THREE AIR MANIFOLD 2 FAIL ALERT ILLUMINATED. CLEARED MASTER WARNING AND RAN APPROPIATE QRH LIST. SYSTEM 2 ON THE AIR SYNOPTIC DISPLAYED AS A RED LINE. MANIFOLD 2 MAINTAINED AIR PRESSURE THROUGHOUT REMAINDER OF FLT AND "BLEED AIR 2 OFF" NEVER ILLUMINATED ON THE AIR SYNOPTIC PAGE. A/C DIVERTED INTO CTS. REPLACED DEFECTIVE SENSORS D1-29 AND D1-28. REPLACED MFC PRECAUTIONARY.

Part: LONGERON — CORRODED (ZONE 100) · airframe 34,367 hrs · 9,652 cycles

CENTER CARGO, CORROSION OBSERVED ON LONGERON 51R BETWEEN STA Y= 1681 AND STA Y= 1701. CENTER CARGO, BETWEEN STA Y= 1681 AND STA Y= 1701, CORRODED LONGERON 51R REMOVED PER SRM 51-33-01 VOLUME I. LONGERON SPLICE FABRICATED PER SRM 53-10-00 FIGURE 2 VOLUME I AND INSTALLED PER SRM 51-33-01 VOLUME I.

Part: LONGERON — CRACKED (ZONE 200) · airframe 34,367 hrs · 9,652 cycles

MAIN DECK, LT SIDE STA Y= 6-90 TO STA Y= 1130 LONGERON 13L FOUND CRACKED. MAIN DECK, LEFT SIDE STA Y= 6-90 TO STA Y= 1130 LONGERON 13L CUT AND REMOVED PER SRM 51-31-01 VOLUME II. LONGERON SPLICE FABRICATED PER SRM 53-10-00 TYPE 1 VOLUME I. REPAIR PARTS AND EXISTING SPLICE INSTALLED PER SRM 53-10-00 TYPE 1 VOLUME I AND SRM 51-33-01 VOLUME II.

Part: FITTING — CRACKED (ZONE 100) · airframe 34,367 hrs · 9,652 cycles

CAC COMPARTMENT, BETWEEN STA Y= 6-90 AND STA Y= 6-100 LONGERON 43R END SPLICE FITTING FOUND CRACKED. CAC COMPARTMENT - STA Y= 6-90 AND STA Y= 6-100 CRACKED SPLICE AT LONGERON 43R. REMOVED PER SRM 51-31-01 VOLUME II. NEW SPLICE FITTING FABRICATED PER DWG AGA7115; PAINTED PER SRM 51-21-01 VOLUME II AND PART MARKED FX AGA7115-514 PER FEDEX GMM 11-0-1001. NEW SPLICE FITTING INSTALLED PER 51-33-01 VOLUME 1 AND DWG AGA7115.

Part: LONGERON — CRACKED (ZONE 200) · airframe 34,367 hrs · 9,652 cycles

RT SIDE STA 5-113-1541, LONGERON 25 FOUND CRACKED. REMOVED AND FABRICATED PER SRM 53-10-00 TYPE 1 VOLUME I. FABRICATED REPAIR PARTS AND EXISTING SPLICE INSTALLED PER SRM 53-10-00 TYPE 1 VOLUME I AND SRM 53-33-01 VOLUME II.

Part: LONGERON — CORRODED (ZONE 100) · airframe 34,367 hrs · 9,652 cycles

CENTER CARGO CORROSION OBSERVED ON LONGERON 51R SPLICE BETWEEN AT STA 1701 TO STA 172. LONGERON 51R AND SPLICE REMOVED PER SRM 53-10-00 FIGURE 2 VOLUME 1. LONGERON AND SPLICE FABRICATED PER SRM 53-10-00 FIGURE 2 VOLUME 1 AND INSTALLED PER SRM 51-33-01 VOLUME 1.

Part: LONGERON — CORRODED (ZONE 100) · airframe 34,367 hrs · 9,652 cycles

CENTER CARGO, CORROSION OBSERVED ON LONGERON 48R SPLICE DOUBLER AT STA 5-116 TO STA 1541. DOUBLERS REMOVED PER SRM 51-33-01 VOLUME II. SPLICE DOUBLERS AFA7124-1, AFA7124-2, A5A7125-501 FABRICATED PER DWG AFA7124 AND A5A7125. PART MARKED AS PER FEDEX GMM 7-0-1001. THREE (3) EACH FABRICATED SPLICE DOUBLERS INSTALLED PER SRM 51-33-01 VOLUME II

Part: LONGERON — CORRODED (ZONE 100) · airframe 34,367 hrs · 9,652 cycles

CENTER CARGO, CORROSION OBSERVED ON LONGERON 48L SPLICE DOUBLER AT STA 5-113 TO STA 1541. REMOVED PER SRM 51-33-01 VOLUME II. THREE (3) EACH SPLICE DOUBLERS P/N A5A7124-1, A5A7124-2 AND A5A7125-501 FABRICATED PER DWG A5A7124 AND A5A7125; AND PART MARKED AS PER FEDEX GMM 7-0-1001. FABRICATED SPLICE DOUBLERS INSTALLED PER DWG A5A7124 AND A5A7125 AND SRM 51-33- 01 VOLUME II.

Part: SPAR — CORRODED (ZONE 600) · airframe 34,367 hrs · 9,652 cycles

RT WING, REAR SPAR, UPPER CHORD AREA AT XORS 680 TO XORS 690 FOUND WTH CORROSION. CORROSION REMOVED PER SRM 51-31-01 VOLUME II. COMPLIED WITH FEDEX EA 1-5710-76824, WINGS, RIGHT UPPER AND LOWER REAR SPAR AND WEB - CORROSION AND CRACK REPAIR.

Part: SPAR — CORRODED (ZONE 500) · airframe 34,367 hrs · 9,652 cycles

LEFT WING, REAR SPAR, XORS= 613 LOWER CHORD AREA FOUND WITH CORROSION. LEFT HAND WING, REAR SPAR, XORS= 613 LOWER CHORD CORROSION REMOVED PER SRM 51-21-01 VOLUME II. COMPLIED WITH FEDEX EA NR 1-5710-76826, WINGS, LEFT UPPER AND LOWER REAR SPAR, CORROSION AND CRACK REPAIR.

Part: SPAR — CORRODED (ZONE 500) · airframe 34,367 hrs · 9,652 cycles

LEFT WING, REAR SPAR, XORS= 1020 FOUND WITH CORROSION. LEFT HAND WING, REAR SPAR, XORS= 1020 AREA CORROSION REMOVED PER SRM 51-21-01 VOLUME II. COMPLIED WITH FEDEX EA NR 1-5710-76826, WINGS, LEFT UPPER AND LOWER REAR SPAR, CORROSION AND CRACK REPAIR.

Part: SPAR — CORRODED (ZONE 500) · airframe 34,367 hrs · 9,652 cycles

LEFT WING, REAR SPAR, AT XORS 680 TO XORS 687 LOWER CHORD AREA FOUND WITH CORROSION. N1819 ¾ LEFT HAND WING, REAR SPAR, XORS= 680 TO XORS= 687 UPPER AND LOWER CHORD AREA CORROSION REMOVED PER SRM 51-21-01 VOLUME II. COMPLIED WITH FEDEX EA NR 1-5710-76826, WINGS, LEFT UPPER AND LOWER REAR SPAR , CORROSION AND CRACK REPAIR.

Part: SPAR — CORRODED (ZONE 600) · airframe 34,367 hrs · 9,652 cycles

RT WING, REAR SPAR, UPPER CHORD AT XORS= 585 FOUND WITH CORROSION. RT WING, REAR SPAR, UPPER CHORD AT XORS= 585 CORROSION. REMOVED PER SRM 51-31-01 VOLUME II COMPLIED WITH FEDEX EA NR 1-5710-76824, WINGS, RIGHT UPPER AND LOWER REAR SPAR AND WEB, CORROSION AND CRACK REPAIR.

Part: SPAR — CORRODED (ZONE 500) · airframe 34,367 hrs · 9,652 cycles

LEFT WING, REAR SPAR, XORS= 620 TO XORS= 633, UPPER AND LOWER CHORD AREA FOUND WITH CORROSION. LEFT HAND WING, REAR SPAR, XORS= 620 TO XORS= 633 UPPER AND LOWER CHORD AREA CORROSION REMOVED PER SRM 51-21-01 VOLUME II. COMPLIED WITH FEDEX EA NR 1-5710-76826, WINGS, LEFT UPPER AND LOWER REAR SPAR, CORROSION AND CRACK REPAIR.

Part: SPAR — CORRODED (ZONE 600) · airframe 34,367 hrs · 9,652 cycles

RT WING, REAR SPAR, LOWER CHORD AT XORS= 622 TO XORS= 642 FOUND WITH CORROSION. RT WING, REAR SPAR, LOWER CHORD AT XORS= 622 TO XORS= 642 CORROSION. REMOVED PER SRM 51-21-01 VOLUME II. COMPLIED WITH FEDEX EA NR 1-5710-76824, WINGS, RIGHT UPPER AND LOWER REAR SPAR AND WEB, CORROSION AND CRACK REPAIR.

Part: SPAR — CORRODED (ZONE 600) · airframe 34,367 hrs · 9,652 cycles

RT WING, REAR SPAR, UPPER CHORD AT ABOUT XORS= 703 FOUND WITH CORROSION. RT WING, REAR SPAR, UPPER CHORD AT ABOUT XORS= 703 CORROSION REMOVED PER SRM 51-21-01 VOLUME II COMPLIED WITH FEDEX EA NR 1-5710-76824, WINGS, RIGHT UPPER AND LOWER REAR SPAR AND WEB, CORROSION AND CRACK REPAIR.

Part: SPAR — CORRODED (ZONE 500) · airframe 34,367 hrs · 9,652 cycles

LEFT WING, REAR SPAR, XORS= 585 LOWER CHORD AREA FOUND WITH CORROSION. LEFT HAND WING, REAR SPAR, XORS= 585 LOWER CHORD AREA CORROSION REMOVED PER SRM 51-21-01 VOLUME II. COMPLIED WITH FEDEX EA NR 1-5710-76826, WINGS, LEFT UPPER AND LOWER REAR SPAR, CORROSION AND CRACK REPAIR.

Part: SPAR — CORRODED (ZONE 600) · airframe 34,367 hrs · 9,652 cycles

RT WING, REAR SPAR, LOWER CHORD AT XORS 650 AREA FOUND WITH CORROSION. CORROSION REMOVED PER SRM 51-21-01 VOLUME II. COMPLIED WITH FEDEX EA 1-5710-76824, WINGS, RIGHT UPPER AND LOWER REAR SPAR AND WEB - CORROSION AND CRACK REPAIR.

Part: SPAR — CORRODED (ZONE 600) · airframe 34,367 hrs · 9,652 cycles

RT WING, REAR SPAR, UPPER CHORD AT XORS= 633 FOUND WITH CORROSION. RT WING, REAR SPAR, UPPER CHORD AT XORS= 633 CORROSION REMOVED PER SRM 51-21-01 VOLUME II COMPLIED WITH FEDEX EA NR 1-5710-76824, WINGS, RIGHT UPPER AND LOWER REAR SPAR AND WEB, CORROSION AND CRACK REPAIR.

Part: SPAR — CORRODED (ZONE 500) · airframe 34,367 hrs · 9,652 cycles

LEFT WING, REAR SPAR, XORS= 540 LOWER CHORD AREA FOUND WITH CORROSION. LEFT HAND WING, REAR SPAR, XORS= 540 LOWER CHORD CORROSION REMOVED PER SRM 51-21-01 VOLUME II. COMPLIED WITH FEDEX EA NR 1-5710-76826, WINGS, LEFT UPPER AND LOWER REAR SPAR, CORROSION AND CRACK REPAIR.

Part: SPAR — CORRODED (ZONE 600) · airframe 34,367 hrs · 9,652 cycles

RT WING, REAR SPAR, UPPER CHORD AREA AT XORS 730 TO XORS 755 FOUND WTH CORROSION. CORROSION REMOVED PER SRM 51-21-01 VOLUME II. COMPLIED WITH FEDEX EA 1-5710-76824, WINGS, RIGHT UPPER AND LOWER REAR SPAR AND WEB - CORROSION AND CRACK REPAIR.

Part: SPAR — CORRODED (ZONE 600) · airframe 34,367 hrs · 9,652 cycles

RT WING, REAR SPAR, UPPER CHORD AT ABOUT XORS= 598 FOUND WITH CORROSION. RT WING, REAR SPAR, UPPER CHORD AT XORS= 598 CORROSION. REMOVED PER SRM 51-21-01 VOLUME II. COMPLIED WITH FEDEX EA NR 1-5710-76824, WINGS, RIGHT UPPER AND LOWER REAR SPAR AND WEB, CORROSION AND CRACK REPAIR.

Part: SPAR — CORRODED (ZONE 500) · airframe 34,367 hrs · 9,652 cycles

LEFT HAND WING, REAR SPAR, UNKNOWN TO XORS= 620 UPPER CHORD FOUND WITH CORROSION. LEFT HAND WING, REAR SPAR, XORS= 600 TO XORS= 620 UPPER CHORD CORROSION REMOVED PER SRM 51-21-01 VOLUME II. COMPLIED WITH FEDEX EA NR 1-5710-76826, WINGS, LEFT UPPER AND LOWER REAR SPAR, CORROSION AND CRACK REPAIR.

Part: SPLICE — CRACKED (ZONE 200) · airframe 34,367 hrs · 9,652 cycles

MAIN DECK, RIGHT HAND SIDE STA 5-113 STA 1541 LONGERON 25 FOUND CRACKED. MAIN DECK, RIGHT HAND SIDE STA 5-11 TO STA 1541 DAMAGED. LONGERON 25 CUT, REMOVED AND FABRICATED PER SRM 53-10-00 TYPE 1 VOLUME I. FABRICATED REPAIR PARTS AND EXISTING SPLICE INSTALLED PER SRM 53-10-00 TYPE 1 VOLUME I AND SRM 53-33-01 VOLUME II.

Part: SPAR — CORRODED (ZONE 600) · airframe 34,367 hrs · 9,652 cycles

RT WING, REAR SPAR, LOWER CHORD AT XORS= 600 TO XORS= 620 FOUND WITH CORROSION. RT WING, REAR SPAR, LOWER CHORD AT XORS= 600 TO XORS= 620 CORROSION REMOVED PER SRM 51-31-01 VOLUME II COMPLIED WITH FEDEX EA NR 1-5710-76824, WINGS, RIGHT UPPER AND LOWER REAR SPAR AND WEB, CORROSION AND CRACK REPAIR.

Part: SPAR — CORRODED (ZONE 500) · airframe 34,367 hrs · 9,652 cycles

LEFT WING, REAR SPAR, AT XORS= 713 UPPER CHORD FOUND WITH CORROSION. LEFT WING, REAR SPAR, XORS= 713 UPPER CHORD CORROSION REMOVED PER SRM 51-21-01 VOLUME II. COMPLIED WITH FEDEX EA NR 1-5710-76826, WINGS, LEFT UPPER AND LOWER REAR SPAR, CORROSION AND CRACK REPAIR.

Part: SPAR — CORRODED (ZONE 500) · airframe 34,367 hrs · 9,652 cycles

LEFT WING, REAR SPAR, XORS= 720 UPPER CHORD AREA FOUND WITH CORROSION. LEFT HAND WING, REAR SPAR, XORS= 720 UPPER CHORD CORROSION REMOVED PER SRM 51-21-01 VOLUME II. COMPLIED WITH FEDEX EA NR 1-5710-76826, WINGS, LEFT UPPER AND LOWER REAR SPAR, CORROSION AND CRACK REPAIR.

Part: SPAR — CORRODED (ZONE 600) · airframe 34,367 hrs · 9,652 cycles

RT WING, REAR SPAR, UPPER CHORD AT ABOUT XORS= 720 FOUND WITH CORROSION. RT WING, REAR SPAR, UPPER CHORD AT XORS= 720 CORROSION. REMOVED PER SRM 51-31-01 VOLUME II COMPLIED WITH FEDEX EA NR 1-5710-76824, WINGS, RIGHT UPPER AND LOWER REAR SPAR AND WEB, CORROSION AND CRACK REPAIR.

Part: SPAR — CORRODED (ZONE 600) · airframe 34,367 hrs · 9,652 cycles

RT WING, REAR SPAR, UPPER AND LOWER CHORD AT XORS= 550 FOUND WITH CORROSION. RT WING, REAR SPAR, UPPER AND LOWER CHORD AT XORS= 550 CORROSION. REMOVED PER SRM 51-21-01 VOLUME II. COMPLIED WITH FEDEX E NR 1-5710-76824, WINGS, RIGHT UPPER AND LOWER REAR SPAR AND WEB, CORROSION AND CRACK REPAIR.

Part: SPAR — CORRODED (RT WING) · airframe 34,367 hrs · 9,652 cycles

RT WING, REAR SPAR, UPPER CHORD AT XORS 600 TO XORS 650 FOUND WITH CORROSION. CORROSION REMOVED PER SRM 51-31-01 VOLUME II. COMPLIED WITH FEDEX EA 1-5710-76824, WINGS, RIGHT UPPER AND LOWER REAR SPAR AND WEB - CORROSION AND CRACK REPAIR.

Part: SPAR — CORRODED (ZONE 600) · airframe 34,367 hrs · 9,652 cycles

RT WING, REAR SPAR, FROM XORS= 917 TO XORS= 1042 FOUND WITH CORROSION. RT WING, REAR SPAR, FROM XORS= 917 TO XORS= 1042 CORROSION. REMOVED PER SRM 51-31-01 VOLUME II. COMPLIED WITH FEDEX EA NR 1-5710-76824, WINGS, RIGHT UPPER AND LOWER REAR SPAR AND WEB, CORROSION AND CRACK REPAIR.

Part: SPAR — CORRODED (ZONE 500) · airframe 34,367 hrs · 9,652 cycles

LEFT WING, REAR SPAR, AT XORS 600 TO XORS 611 LOWER CHORD FOUND WITH CORROSION. LEFT HAND WING, REAR SPAR, XORS= 611 LOWER CHORD CORROSION REMOVED PER SRM 51-21-01 VOLUME II. COMPLIED WITH FEDEX EA NR 1-5710-76826, WINGS, LEFT UPPER AND LOWER REAR SPAR, CORROSION AND CRACK REPAIR.

Part: SPAR — CORRODED (ZONE 500) · airframe 34,367 hrs · 9,652 cycles

LEFT WING, REAR SPAR, AT XORS 690 TO XORS 700 LOWER CHORD AREA FOUND WITH CORROSION. LEFT HAND WING, REAR SPAR, XORS= 690 TO XORS= 700 LOWER CHORD CORROSION REMOVED PER SRM 51-21-01 VOLUME II. COMPLIED WITH FEDEX EA NR 1-5710-76826, WINGS, LEFT UPPER AND LOWER REAR SPAR, CORROSION AND CRACK REPAIR.

Part: SPAR — CORRODED (ZONE 500) · airframe 34,367 hrs · 9,652 cycles

LT WING, REAR SPAR, XORS= 690 UPPER CHORD FOUND WITH CORROSION. LEFT HAND WING, REAR SPAR, XORS= 690 UPPER CHORD CORROSION, REMOVED PER SRM 51-21-01 VOLUME II. COMPLIED WITH FEDEX EA NR 1-5710-76826, WINGS, LEFT UPPER AND LOWER REAR SPAR CORROSION AND CRACK REPAIR

Part: FRAME — CORRODED (ZONE 100) · airframe 34,367 hrs · 9,652 cycles

AFT CARGO, AFTER REMOVAL OF DOOR CUTOUT AFT LOWER LINER, CORROSION FOUND ON FRAME SIDE SURFACE AT STA 1959. AFT CARGO, CORROSION ON FRAME SIDE SURFACE AT STA 1959 REMOVED PER SRM 53-00-01 FIGURE 3 VOLUME I. MATERIAL THICKNESS= 0.130 INCH, MATERIAL REMOVED= 0.025 INCH, MATERIAL REMAINING= 0.105 INCH WITHIN LIMITS PER SRM 53-00-01 FIGURE 3 VOLUME I.

Part: SHEAR TIE — CORRODED (ZONE 100) · airframe 34,367 hrs · 9,652 cycles

AFT CARGO, AFTER FLOOR PANEL NR 187DF REMOVAL FOR ACCESS, CORROSION FOUND AT STA 1964 BETWEEN LONGERON 47L AND 48L. AFT CARGO, STA 1964 BETWEEN LONGERON 47L AND 48L SHEAR TIE CLIP. REMOVED AND REPLACED PER SRM 51-31-01 VOLUME II.

Part: FRAME — GOUGED (ZONE 200) · airframe 34,367 hrs · 9,652 cycles

MAIN DECK, LEFT SIDE 9G NET ATTACH YOKE ASSEMBLY AT FRAME STA Y= 535 FOUND WITH GOUGE MARK. MAIN DECK, LEFT SIDE 9G NET ATTACH YOKE ASSEMBLY FRAME AT STA Y= 535 CARRIED OUT REPAIR AS PER DWG NR: SRZ-53-503 AND SRM51-31-01 VOLUME II.

Part: SKIN — CORRODED (ZONE 100) · airframe 34,367 hrs · 9,652 cycles

CENTER WING TANK, STA 1219 - STA 1239, LBL 27 - LBL 47 HORIZONTAL PRESSURE PANEL TOP SURFACE CORRODED. CORROSION REMOVED, MATERIAL ORIGINAL THICKNESS = 0.175 INCH, MATERIAL REMOVED = 0.017 INCH, REMAINING MATERIAL = 0.158 INCH AND FOUND WITHIN LIMITS AS PER FEDEX EA NR 1-5710-76817, WINGS, CENTER WING UPPER PANEL, SKIN CORROSION.

Part: WEB — CANNING (ZONE 100) · airframe 34,367 hrs · 9,652 cycles

CENTER LANDING GEAR WHEEL WELL, LEFT VERTICAL WEB FOUND WITH OIL CANNING CONDITION. CENTER LANDING GEAR WHEEL WELL, LEFT VERTICAL WEB INSPECTION CARRIED OUT AND FOUND WITHIN SRM 53-00-01 VOLUME I LIMITS. STA Y= 1394-1401, Z= 100-115, 0.087" STA Y= 1401-1411, Z= 100-115, 0.091" STA Y= 1411-1421, Z= 100-115, 0.082" STA Y= 1421-1431, Z= 100-115, 0.093" STA Y= 1431-1441, Z= 80-100, 0.146" STA Y= 1441-1451, Z= 80-100, 0.115" STA Y= 1471-1481, Z= 100-115, 0.064" COMPLIED WITH FEDEX EA NR 1-5330-76819, FUSELAGE, PLATES AND SKIN, KEEL WEB IN THE CENTER LANDING GEAR WHEEL WELL.

Part: LONGERON — CORRODED (ZONE 100) · airframe 34,367 hrs · 9,652 cycles

CENTER CARGO, CORROSION OBSERVED ON LONGERON 46R BETWEEN STA 1701 AND STA 1721. CENTER CARGO, STA 1671 TO STA 1811 LONGERON 46R REMOVED AND NEW LONGERON P/N AFA7098-501, INSTALLED PER DWG AFA7098, SRM 51-33-01 VOLUME II AND SRM 51-35-01 VOLUME II.

Part: WEB — CANNING (ZONE 100) · airframe 34,367 hrs · 9,652 cycles

CENTER LANDING GEAR WHEEL WELL, RT VERTICAL WEB FOUND WITH OIL CANNING CONDITION. CENTER LANDING GEAR WHEEL WELL, RT VERTICAL WEB INSPECTION CARRIED OUT AND FOUND WITHIN SRM 53-00-01 VOLUME I LIMITS. STA Y= 1394-1401, Z= 100-115, 0.067" STA Y= 1401-1411, Z= 100-115, 0.085" STA Y= 1411-1421, Z= 100-115, 0.075" STA Y= 1421-1431, Z= 100-115, 0.090" STA Y= 1431-1441, Z= 80-100, 0.160" STA Y= 1461-1471, Z= 100-115, 0.071" COMPLIED WITH FEDEX EA NR 1-5330-76819, FUSELAGE - PLATES AND SKIN, KEEL WEB IN THE CENTER LANDING GEAR WHEEL WELL.

Part: SPAR CAP — CORRODED (ZONE 600) · airframe 34,367 hrs · 9,652 cycles

RT WING, WING PLANK, UPPER SURFACE, MOST OUTBOARD AFT CORNER ABOUT XORS= 1090 TO XORS= 1094 FOUND WITH CORROSION AND FIXED TRAILING EDGE PANEL FOUND BULGING. RT WING, WING PLANK, UPPER SURFACE, MOST OUTBOARD AFT CORNER XORS= 1090 TO XORS= 1094 CORROSION REMOVED PER SRM 51-21-01 VOLUME II COMPLIED WITH FEDEX EA NR 1-5710-76824, WINGS, RIGHT UPPER AND LOWER REAR SPAR AND WEB, CORROSION AND CRACK REPAIR.

Part: SPAR — CORRODED (ZONE 600) · airframe 34,367 hrs · 9,652 cycles

RT WING, REAR SPAR UPPER CHORD XORS= 1079 FOUND WITH CORROSION. RT WING, REAR SPAR UPPER CHORD XORS= 1079 CORROSION REMOVED PER SRM 51-21-01 VOLUME II COMPLIED WITH FEDEX EA NR 1-5710-76824, WINGS, RIGHT UPPER AND LOWER REAR SPAR AND WEB, CORROSION AND CRACK REPAIR.

Part: SPAR — CORRODED (ZONE 600) · airframe 34,367 hrs · 9,652 cycles

RT WING, REAR SPAR UPPER CHORD XORS= 1042 FOUND WITH CORROSION. RT WING, REAR SPAR UPPER CHORD XORS= 1042 CORROSION REMOVED PER SRM 51-21-01 VOLUME II, COMPLIED WITH FEDEX EA NR 1-5710-76824, WINGS, RIGHT UPPER AND LOWER REAR SPAR AND WEB, CORROSION AND CRACK REPAIR.

Part: LONGERON — CORRODED (ZONE 100) · airframe 34,367 hrs · 9,652 cycles

FORWARD CARGO, CORROSION OBSERVED ON LONGERON 43R STA 1125. TRIMMED OFF AS PER SRM 53-10-00 VOLUME 1. REPAIR LONGERON FABRICATED AND INSTALLED AS PER SRM 53-10-00 VOLUME 1.

Part: LONGERON — CORRODED (ZONE 200) · airframe 34,367 hrs · 9,652 cycles

CORROSION FOUND BETWEEN STA 6-30 AND STA 6-50 AT LONGERON 15L. REMOVED AS PER MD-11 SRM 51-31-01 VOLUME I. NEW LONGERON FABRICATED AS PER DWG NO.: ADA3011 AND FABRICATED LONGERON INSTALLED AS PER MD-11 SRM 51-31-01 VOLUME I.

Part: INTERCOSTAL — CORRODED (ZONE 100) · airframe 34,367 hrs · 9,652 cycles

MAIN DECK INTERCOSTAL BETWEEN STA 1341 AND STA 1361 AT LONGERON 19L FOUND CORRODED. CORROSION REMOVED PER SRM 51-21-01 VOLUME II PAGE 27. MATERIAL REMOVED = 0.005, REMAINING THICKNESS = 0.095, ORIGINAL THICKNESS = 0.100 FOUND WITHIN LIMITS PER SRM 53-00-01 VOLUME 1 FIGURE 3.

Part: INTERCOSTAL — CORRODED (ZONE 200) · airframe 34,367 hrs · 9,652 cycles

MAIN DECK - INTERCOSTAL BETWEEN STA 1175 AND STA 1199 AT LONGERON 15R FOUND CORRODED. REMOVED AND REPLACED PER SRM 51-31-01 VOLUME II.

Part: LONGERON — CORRODED (ZONE 200) · airframe 34,367 hrs · 9,652 cycles

CORROSION FOUND BETWEEN STA 6-50 AND STA 6-70 AT LONGERON 15L. REMOVED AS PER MD-11 SRM 51-31-01 VOLUME I. NEW LONGERON FABRICATED AS PER DWG NO.: ADA3011 AND FABRICATED LONGERON INSTALLED AS PER MD-11 SRM 51-31-01 VOLUME I.

Part: INTERCOSTAL — CORRODED (ZONE 200) · airframe 34,367 hrs · 9,652 cycles

MAIN DECK INTERCOSTAL BETWEEN STA 1481 AND STA 1501 AT LONGERON 19R FOUND CORRODED. CORROSION REMOVED PER SRM 51-21-01 VOLUME II PAGE 27. MATERIAL REMOVED = 0.004, REMAINING THICKNESS = 0.096, ORIGINAL THICKNESS = 0.100 FOUND WITHIN LIMITS PER SRM 53-00-01 VOLUME 1 FIGURE 3.

Part: INTERCOSTAL — CORRODED (ZONE 200) · airframe 34,367 hrs · 9,652 cycles

INTERCOSTAL BETWEEN STA 1421 AND STA 1441 AT LONGERON 15L FOUND CORRODED. INTERCOSTAL REMOVED AND REPLACED PER SRM 51-33-01 VOLUME II.

Part: LONGERON — CORRODED (ZONE 200) · airframe 34,367 hrs · 9,652 cycles

CORROSION FOUND BETWEEN STA 6-70 AND STA 6-90 AT LONGERON 15L. REMOVED AS PER MD-11 SRM 51-31-01 VOLUME I. NEW LONGERON FABRICATED AS PER DWG NO.: ADA3011 AND FABRICATED LONGERON INSTALLED AS PER MD-11 SRM 51-31-01 VOLUME I.

Part: INTERCOSTAL — CORRODED (FUSELAGE) · airframe 44,353 hrs · 9,018 cycles

INTERCOSTAL BETWEEN STA 1175 AND STA 1199 AT LONGERON 15R FOUND CORRODED. REMOVED AND REPLACED AS PER 51-33-01 VOLUME II.

Part: INTERCOSTAL — CORRODED (ZONE 200) · airframe 34,367 hrs · 9,652 cycles

INTERCOSTAL BETWEEN STA 1341 AND STA 1361 AT LONGERON 15R FOUND CORRODED. INTERCOSTAL REMOVED AND REPLACED PER SRM 51-33-01 VOLUME II.

Part: INTERCOSTAL — CORRODED (ZONE 100) · airframe 34,367 hrs · 9,652 cycles

INTERCOSTAL BETWEEN STA 1159 AND STA 1175 AT LONGERON 15R FOUND CORRODED. REMOVED AND REPLACED AS PER MD-11 SRM 53-33-01.

Part: INTERCOSTAL — CORRODED (FUSELAGE) · airframe 34,367 hrs · 9,652 cycles

INTERCOSTAL BETWEEN STA 1481 AND STA 1501 AT LONGERON 19R FOUND CORRODED. INTERCOSTAL REMOVED AND REPLACED PER SRM 51-33-01 VOLUME II.

Part: INTERCOSTAL — CORRODED (ZONE 200) · airframe 44,353 hrs · 9,018 cycles

INTERCOSTAL BETWEEN STA 1361 AND STA 1381 AT LONGERON 15R FOUND CORRODED. INTERCOSTAL REMOVED AND REPLACED PER SRM 51-33-01 VOLUME II.

Part: LONGERON — CORRODED (ZONE 200) · airframe 34,367 hrs · 9,652 cycles

MAIN DECK CORROSION FOUND BETWEEN STA 6-10 AND STA 6-30 AT LONGERON 15R. CORRODED LONGERON REMOVED AS PER MD-11 SRM 51-31-01 VOLUME I. LONGERON FABRICATED AS PER DWG NR.: ADA3011. FABRICATED LONGERON INSTALLED AS PER MD-11 SRM 51-31-01 VOLUME I.

Part: HINGE BRACKET — CORRODED (ZONE 600) · airframe 34,367 hrs · 9,652 cycles

RT WING, OB FLAP, OB AFT HINGE IB PIVOT HOLE CORRODED. CORROSION REMOVED AS PER CMM 20-11-02 PAGES 2-4. ORIGINAL DIAMETER=1.082, FINAL DIAMETER=1.097. COMPLIED WITH FEDEX EA 1-5750-76808, LEFT AND RIGHT OUTBOARD FLAP - OUTBOARD HINGE BRACKET BORE CORRODED.

Part: HINGE BRACKET — CORRODED (ZONE 600) · airframe 34,367 hrs · 9,652 cycles

RT WING, OB FLAP, OB AFT HINGE OB PIVOT HOLE CORRODED. RT WING, OUTBOARD FLAP, OUTBOARD AFT HINGE OUTBOARD PIVOT HOLECORROSION REMOVED AS PER CMM 20-11-02 PAGES 2 - 4. ORIGINAL DIAMETER = 1.062, FINAL DIAMETER = 1.097. COMPLIED WITH FEDEX EA 1-5750-76808, LEFT AND RIGHT OUTBOARD FLAP - OUTBOARD HINGE BRACKET BORE CORRODED.

Part: SPLICE — CRACKED (ZONE 100) · airframe 34,367 hrs · 9,652 cycles

CENTER CARGO, RIGHT LONGERON SPLICE AT STA 5-113 TO 1541 LONGERON 47 CRACKED. REMOVED AND REPALCED PER SRM 51-33-01 VOLUME II

Part: SKIN — DENTED (ZONE 100) · airframe 34,367 hrs · 9,652 cycles

RIGHT FUSELAGE SKIN AT STA Y= 1847, LONGERON 34R FOUND WIND DENT MARK. SKIN TRIMMED-OFF AND REPAIRED PER MD-11 SRM 53-20-00 VOLUME I FIGURE 2.

Part: HINGE — CORRODED (ZONE 500) · airframe 34,367 hrs · 9,652 cycles

LEFT WING, INBOARD FLAP OUTBOARD AFT HINGE INBOARD PIVOT HOLE FLANGE CORRODED. CORROSION REMOVED PER CMM 57-52-03.

Part: HINGE BRACKET — CORRODED (ZONE 600) · airframe 34,367 hrs · 9,652 cycles

RT WING, OB FLAP, OB AFT HINGE PIVOT HOLE OB FLANGE CORRODED. RT WING, OUTBOARD FLAP, OUTBOARD AFT HINGE PIVOT HOLE OUTBOARD FLANGE CORROSION REMOVED AS PER CMM 20-11-02 PAGES 2 - 4. ORIGINAL THICKNESS = 0.503, MATERIAL REMOVED = 0.004, REMAINING THICKNESS = 0.499. COMPLIED WITH FEDEX EA 1-5750-76808, LEFT AND RIGHT OUTBOARD FLAP - OUTBOARD HINGE BRACKET BORE CORRODED.

Part: HINGE — CORRODED (ZONE 500) · airframe 34,367 hrs · 9,652 cycles

LEFT WING, INBOARD FLAP OUTBOARD AFT HINGE INBOARD PIVOT HOLE CORRODED. CORROSION REMOVED AND FOUND EXCEEDED LIMITS PER CMM 57-52-03. CORROSION REMOVED AND FOUND EXCEEDED LIMITS PER CMM 57-52-03

Part: HINGE BRACKET — CORRODED (ZONE 600) · airframe 34,367 hrs · 9,652 cycles

RT WING, OB FLAP, OB AFT HINGE PIVOT HOLE IB FLANGE CORRODED. CORROSION REMOVED AS PER CMM 20-11-02 PAGES 2 - 4. ORIGINAL THICKNESS = 0.504, MATERIAL REMOVED = 0.010, REMAINING THICKNESS = 0.494. COMPLIED WITH FEDEX EA 1-5750-76808, LEFT AND RIGHT OUTBOARD FLAP - OUTBOARD HINGE BRACKET BORE CORRODED.

Part: SPLICE — CRACKED (ZONE 100) · airframe 34,367 hrs · 9,652 cycles

CENTER CARGO, LT LONGERON SPLICE AT STA 5-113 TO 1541 LONGERON 50 CRACKED. LONGERON 50 REMOVED AND REPLACED AS PER SRM 51-33-01 VOLUME III.

Part: HINGE — CORRODED (ZONE 600) · airframe 34,367 hrs · 9,652 cycles

RT WING, INBOARD FLAP, OUTBOARD AFT HINGE OUTBOARD PIVOT HOLE CORRODED. CORROSION REMOVED PER CMM 20-11-02 PAGES 2 - 4. ORIGINAL DIAMETER = 1.187 FINAL DIAMETER = 1.327 COMPLIED WITH FEDEX EA 1-5750-76810, WINGS - LT AND RT INBOARD TRAILING EDGE FLAP HINGE BRACKETS CORRODED.

Part: HINGE — CORRODED (ZONE 600) · airframe 34,367 hrs · 9,652 cycles

RIGHT WING, OUTBOARD FLAP, OUTBOARD AFT HINGE OUTBOARD ACTUATOR ROD END ATTACHING HOLE FLANGE CORRODED.

Part: LONGERON — CORRODED (ZONE 100) · airframe 34,367 hrs · 9,652 cycles

CENTER CARGO, CORROSION OBSERVED ON LONGERON 46R BETWEEN STA 1741 AND 1761. LONGERON 46R REMOVED AND NEW LONGERON P/N AFA7098-501 INSTALLED PER DWG AFA7098, SRM 51-33-01 VOLUME II AND SRM 51-35-01 VOLUME II.

Part: SKIN — CORRODED (ZONE 600) · airframe 34,367 hrs · 9,652 cycles

RT WING, WING UNDER SURFACE JUST ABOVE NR 3 PYLON FWD INBOARD OF THRUST LINK CORRODED. CORROSION REMOVED PER SRM 51-21-01 VOLUME I. COMPLIED WITH FEDEX EA 1-5750-76815, WINGS RT WING - LOWER FORWARD PANEL ASSEMBLY - CORRODED.

Part: HINGE — CORRODED (ZONE 600) · airframe 34,367 hrs · 9,652 cycles

RT WING, INBOARD FLAP, OUTBOARD AFT HINGE OUTBOARD PIVOT HOLE FLANGE CORRODED. CORROSION REMOVED PER CMM 57-52-03. FOUND EXCEEDED LIMITS ORIGINAL THICKNESS = 0.562, MATERIAL REMOVED = 0.002, REMAINING THICKNESS = 0.560 COMPLIED WITH FEDEX EA 1-5750-76810, WINGS - LEFT AND RIGHT INBOARD TRAILING EDGE FLAP - HINGE BRACKETS BORE CORRODED.

Part: HINGE BRACKET — CORRODED (ZONE 600) · airframe 34,367 hrs · 9,652 cycles

RT WING, OB FLAP, OB AFT HINGE IB ACTUATOR ROD END ATTACHING HOLE IB FLANGE CORRODED. CORROSION REMOVED AS PER CMM 20-11-02 PAGES 2 - 4. ORIGINAL THICKNESS = 0.408, MATERIAL REMOVED = 0.002, REMAINING THICKNESS = 0.406. COMPLIED WITH FEDEX EA 1-5750-76808, LEFT AND RIGHT OUTBOARD FLAP - OUTBOARD HINGE BRACKET BORE CORRODED.

Part: HINGE BRACKET — CORRODED (ZONE 600) · airframe 34,367 hrs · 9,652 cycles

RT WING, OB FLAP, OB AFT HINGE IB ACTUATOR ROD END ATTACHING HOLE CORRODED. CORROSION REMOVED AS PER CMM 20-11-02 PAGES 2 - 4. ORIGINAL DIAMETER = 1.062, FINAL DIAMETER = 1.090. COMPLIED WITH FEDEX EA 1-5750-76808, LEFT AND RIGHT OUTBOARD FLAP - OUTBOARD HINGE BRACKET BORE CORRODED.

Part: LONGERON — CORRODED (FUSELAGE) · airframe 34,367 hrs · 9,652 cycles

CENTER CARGO, CORROSION OBSERVED ON LONGERON 52 SPLICE BETWEEN STA 1701 AND STA 1721. CORROSION REMOVED PER SRM 53-00-01 FIGURE 3 VOLUME 1. MATERIAL THICKNESS= 0.125, MATERIAL REMOVED= 0.020, MATERIAL REMAINING= 0.105. WITHIN LIMITS PER SRM 53-00-01 FIGURE 3 VOLUME I

Part: HINGE — CORRODED (ZONE 600) · airframe 34,367 hrs · 9,652 cycles

RIGHT WING, OUTBOARD FLAP, OUTBOARD AFT HINGE OUTBOARD ACTUATOR ROD END ATTACHING HOLE CORRODED. CORROSION REMOVED AS PER CMM 20-11-02.

Part: SPLICE — CRACKED (ZONE 100) · airframe 34,367 hrs · 9,652 cycles

CENTER CARGO, RIGHT LONGERON SPLICE AT STA 5-113 TO 1541 LONGERON 51 CRACKED. REMOVED AND REPLACED AS PER SRM 51-33-01 VOLUME III.

Part: HINGE — CORRODED (ZONE 600) · airframe 34,367 hrs · 9,652 cycles

RT WING, OB FLAP, IB AFT HINGE WITH PIVOT HOLE, OB CORRODED.**** S/D COMING ****

Part: HINGE — CORRODED (ZONE 600) · airframe 34,367 hrs · 9,652 cycles

RT WING OUTBOARD FLAP INBOARD AFT HINGE WITH ACTUATOR ROD END ATTACHING HOLE OUTBOARD CORRODED. CORROSION REMOVED PER CMM 20-11-02 PAGES 2 - 4. ORIGINAL DIAMETER = 1.062 FINAL DIAMETER = 1.221 COMPLIED WITH FEDEX EA 1-5750-76807, WINGS - LT AND RT OUTBOARD FLAP - INBOARD HINGE BRACKET BORE CORRODED.

Part: HINGE — CORRODED (ZONE 600) · airframe 34,367 hrs · 9,652 cycles

RT WING OUTBOARD FLAP INBOARD AFT HINGE WITH PIVOT HOLE INBOARD CORRODED. CORROSION REMOVED PER CMM 20-11-02 PAGES 2 - 4. ORIGINAL DIAMETER = 1.093 FINAL DIAMETER = 1.189 COMPLIED WITH FEDEX EA 1-5750-76807, WINGS - LT AND RT OUTBOARD FLAP - INBOARD HINGE BRACKET BORE CORRODED.

Part: HINGE — CORRODED (ZONE 600) · airframe 34,367 hrs · 9,652 cycles

RT WING, OUTBOARD FLAP - INBOARD AFT HINGE WITH ACTUATOR ROD END ATTACHING HOLE INBOARD FLANGED CORRODED. CORROSION REMOVED PER CMM 20-11-02 PAGES 2 - 4. ORIGINAL THICKNESS = 0.411 MATERIAL REMOVED = 0.005 REMAINING THICKNESS = 0.406 COMPLIED WITH FEDEX EA 1-5750-76807, WINGS - LT AND RT OUTBOARD FLAP - INBOARD HINGE BRACKET BORE CORRODED.

Part: HINGE — CORRODED (ZONE 600) · airframe 34,367 hrs · 9,652 cycles

RT WING, OUTBOARD FLAP - INBOARD AFT HINGE WITH ACTUATOR ROD END ATTACHING HOLE OUTBOARD CORRODED. CORROSION REMOVED PER CMM 20-11-02 PAGES 2 - 4. ORIGINAL DIAMETER = 1.062 FINAL DIAMETER = 1.223 COMPLIED WITH FEDEX EA 1-5750-76807, WINGS - LT AND RT OUTBOARD FLAP - INBOARD HINGE BRACKET BORE CORRODED.

Part: HINGE — CORRODED (ZONE 600) · airframe 34,367 hrs · 9,652 cycles

RT WING OUTBOARD FLAP INBOARD AFT HINGE WITH ACTUATOR ROD END ATTACHING HOLE OUTBOARD CORRODED. CORROSION REMOVED PER CMM 20-11-02 PAGES 2 - 4. ORIGINAL THICKNESS = 0.395 MATERIAL REMOVED = 0.002 REMAINING THICKNESS = 0.393 COMPLIED WITH FEDEX EA 1-5750-76807, WINGS - LT AND RT OUTBOARD FLAP - INBOARD HINGE BRACKET BORE CORRODED.

Part: HINGE — CORRODED (ZONE 600) · airframe 34,367 hrs · 9,652 cycles

RT WING OUTBOARD FLAP INBOARD AFT HINGE WITH PIVOT HOLE INBOARD FLANGE CORRODED. CORROSION REMOVED PER CMM 20-11-02 PAGES 2 - 4. ORIGINAL THICKNESS = 0.497 MATERIAL REMOVED = 0.012 REMAINING THICKNESS = 0.485 COMPLIED WITH FEDEX EA 1-5750-76807, WINGS - LT AND RT OUTBOARD FLAP - INBOARD HINGE BRACKET BORE CORRODED.

Part: HINGE — CORRODED (ZONE 600) · airframe 34,367 hrs · 9,652 cycles

RIGHT WING, OUTBOARD FLAP - INBOARD AFT HINGE WITH PIVOT HOLE OUTBOARD FLANGE CORRODED. CORROSION REMOVED PER CMM 20-11-02 PAGES 2 - 4. ORIGINAL THICKNESS = 0.508 MATERIAL REMOVED = 0.002 REMAINING THICKNESS = 0.506 COMPLIED WITH FEDEX EA 1-5750-76807, WINGS - LT AND RT OUTBOARD FLAP - INBOARD HINGE BRACKET BORE CORRODED.

Part: HINGE BRACKET — CORRODED (ZONE 500) · airframe 34,367 hrs · 9,652 cycles

LT WING, OUTBOARD FLAP, OUTBOARD AFT HINGE WITH OUTBOARD PIVOT HOLE FLANGE CORRODED. CORROSION REMOVED AS PER CMM 20-11-02 PAGES 2 - 4. ORIGINAL THICKNESS = 0.502, MATERIAL REMOVED = 0.003, REMAINING THICKNESS = 0.0.499. COMPLIED WITH FEDEX EA 1-5750-76808, WINGS - LT AND RT OUTBOARD FLAP - OUTBOARD HINGE BRACKET BORE CORRODED.

Part: HINGE BRACKET — CORRODED (ZONE 500) · airframe 34,367 hrs · 9,652 cycles

LT WING, OUTBOARD FLAP, OUTBOARD AFT HINGE INBOARD PIVOT HOLE FLANGE CORRODED. CORROSION REMOVED AS PER CMM 20-11-02 PAGES 2 - 4. ORIGINAL THICKNESS = 0.500, MATERIAL REMOVED = 0.001, REMAINING THICKNESS = 0.0.499. COMPLIED WITH FEDEX EA# 1-5750-76808, WINGS - LT AND RT OUTBOARD FLAP - OUTBOARD HINGE BRACKET BORE CORRODED.

Part: HINGE BRACKET — CORRODED (ZONE 500) · airframe 34,367 hrs · 9,652 cycles

LT WING, OUTBOARD FLAP, OUTBOARD AFT HINGE WITH ACTUATOR ROD END ATTACHING HOLE OUTBOARD CORRODED. CORROSION REMOVED AS PER CMM 20-11-02 PAGES 2-4. ORIGINAL DIAMETER = 1.062, FINAL DIAMETER = 1.192. COMPLIED WITH FEDEX EA 1-5750-76808, WINGS - LT AND RT OUTBOARD FLAP - OUTBOARD HINGE BRACKET BORE CORRODED.

Part: HINGE — CORRODED (ZONE 500) · airframe 34,367 hrs · 9,652 cycles

LT WING, OB FLAP, IB AFT HINGE WITH ACTUATOR ROD END ATTACHING HOLE OB HOLE CORRODED. *** S/D COMING ****

Part: HINGE BRACKET — CORRODED (ZONE 500) · airframe 34,367 hrs · 9,652 cycles

LT WING, OB FLAP, IB AFT HINGE WITH ACTUATOR ROD END ATTACHING OB HOLE CORRODED. CORROSION REMOVED PER CMM 20-11-02 PAGES 2 - 4. ORIGINAL DIAMETER = 1.062. FINAL DIAMETER = 1.203. COMPLIED WITH FEDEX EA 1-5750-76807, LEFT AND RIGHT OUTBOARD FLAP - INBOARD HINGE BRACKET BORE CORRODED.

Part: HINGE BRACKET — CORRODED (ZONE 500) · airframe 34,367 hrs · 9,652 cycles

LT WING, OB FLAP, IB AFT HINGE WITH PIVOT HOLE IB CORRODED. CORROSION REMOVED PER CMM 20-11-02 PAGES 2 - 4. ORIGINAL DIAMETER = 1.093 FINAL DIAMETER = 1.148. COMPLIED WITH FEDEX EA 1-5750-76807, LEFT AND RIGHT OUTBOARD FLAP - INBOARD HINGE BRACKET BORE CORRODED

Part: HINGE BRACKET — CORRODED (ZONE 500) · airframe 34,367 hrs · 9,652 cycles

LT WING, OB FLAP, IB AFT HINGE WITH ACTUATOR ROD END ATTACHING HOLE IB CORRODED. CORROSION REMOVED PER CMM 20-11-02 PAGES 2 - 4. ORIGINAL THICKNESS = 0.412" MATERIAL REMOVED = 0.003. REMAINING THICKNESS = 0.409. COMPLIED WITH FEDEX EA 1-5750-76807, LEFT AND RIGHT OUTBOARD FLAP - INBOARD HINGE BRACKET BORE CORRODED.

Part: HINGE — CORRODED (ZONE 500) · airframe 34,367 hrs · 9,652 cycles

LT WING, OB FLAP, OB AFT HINGE WITH IB PIVOT HOLE CORRODED**** S/D COMING ****

Part: HINGE BRACKET — CORRODED (ZONE 500) · airframe 34,367 hrs · 9,652 cycles

LT WING, OB FLAP IB AFT HINGE OB PIVOT HOLE FOUND CORRODED. CORROSION REMOVED PER CMM 20-11-02 PAGES 2 - 4. ORIGINAL DIAMETER = 1.062 FINAL DIAMETER = 1.095. COMPLIED WITH FEDEX EA 1-5750-76807, LEFT AND RIGHT OUTBOARD FLAP - INBOARD HINGE BRACKET BORE CORRODED.

Part: HINGE BRACKET — CORRODED (ZONE 500) · airframe 34,367 hrs · 9,652 cycles

LT WING, OUTBOARD FLAP, OUTBOARD AFT HINGE WITH OUTBOARD PIVOT HOLE CORRODED. CORROSION REMOVED AS PER CMM 20-11-02 PAGES 2 - 4. ORIGINAL DIAMETER = 1.062, FINAL DIAMETER = 1.071 COMPLIED WITH FEDEX EA 1-5750-76808, WINGS - LT AND RT OUTBOARD FLAP - OUTBOARD HINGE BRACKET BORE CORRODED.

Part: HINGE BRACKET — CORRODED (ZONE 500) · airframe 34,367 hrs · 9,652 cycles

LT WING, OB FLAP, IB AFT HINGE WITH PIVOT IB HOLE FLANGE CORRODED. CORROSION REMOVED PER CMM 20-11-02 PAGES 2 - 4. ORIGINAL THICKNESS = 0.502. MATERIAL REMOVED = 0.015. REMAINING THICKNESS = 0.487. COMPLIED WITH FEDEX EA 1-5750-76807, LEFT AND RIGHT OUTBOARD FLAP - INBOARD HINGE BRACKET BORE CORRODED.

Part: HINGE BRACKET — CORRODED (ZONE 500) · airframe 34,367 hrs · 9,652 cycles

LT WING, OB FLAP, OB AFT HINGE WITH ACTUATOR ROD END ATTACHING HOLE IB FLANGE CORRODED. CORROSION REMOVED AS PER CMM 20-11-02 PAGES 2 - 4. ORIGINAL THICKNESS = 0.402, MATERIAL REMOVED = 0.006, REMAINING THICKNESS = 0.0.396 COMPLIED WITH FEDEX EA 1-5750-76808, LEFT AND RIGHT OUTBOARD FLAP - OUTBOARD HINGE BRACKET BORE CORRODED.

Part: HINGE BRACKET — CORRODED (ZONE 500) · airframe 34,367 hrs · 9,652 cycles

LT WING, OB FLAP, OB AFT HINGE WITH ACTUATOR ROD END ATTACHING HOLE IB CORRODED. CORROSION REMOVED AS PER CMM 20-11-02 PAGES 2 - 4. ORIGINAL DIAMETER = 1.062, FINAL DIAMETER = 1.192 COMPLIED WITH FEDEX EA 1-5750-76808, WINGS - LEFT AND RIGHT OUTBOARD FLAP - OUTBOARD HINGE BRACKET BORE CORRODED.

Part: HINGE BRACKET — CORRODED (ZONE 500) · airframe 34,367 hrs · 9,652 cycles

LT WING, OB FLAP, IB AFT HINGE OB PIVOT HOLE FLANGE CORRODED. CORROSION REMOVED PER CMM 20-11-02 PAGES 2 - 4. ORIGINAL THICKNESS = 0.502. MATERIAL REMOVED = 0.004 REMAINING THICKNESS = 0.498. COMPLIED WITH FEDEX EA 1-5750-76807, LEFT AND RIGHT OUTBOARD FLAP - INBOARD HINGE BRACKET BORE CORRODED

Part: HINGE BRACKET — CORRODED (ZONE 500) · airframe 34,367 hrs · 9,652 cycles

LT WING, OB FLAP, IB AFT HINGE WITH ACTUATOR ROD END ATTACHING T IB HOLE CORRODED. CORROSION REMOVED PER CMM 20-11-02 PAGES 2 - 4. ORIGINAL DIAMETER = 1.062. FINAL DIAMETER = 1.199. COMPLIED WITH FEDEX EA 1-5750-76807, LEFT AND RIGHT OUTBOARD FLAP - INBOARD HINGE BRACKET BORE CORRODED.

Part: HINGE BRACKET — CORRODED (ZONE 500) · airframe 34,367 hrs · 9,652 cycles

LT WING, OUTBOARD FLAP, OUTBOARD AFT HINGE WITH ACTUATOR ROD END ATTACHING HOLE OUTBOARD FLANGE CORRODED. CORROSION REMOVED AS PER CMM 20-11- 02 PAGES 2 - 4. ORIGINAL THICKNESS = 0.402, MATERIAL REMOVED = 0.004, REMAINING THICKNESS = 0.398. COMPLIED WITH FEDEX EA 1-5750-76808, WINGS - LT AND RT OUTBOARD FLAP - OUTBOARD HINGE BRACKET BORE CORRODED.

Part: LONGERON — CRACKED (ZONE 100) · airframe 34,367 hrs · 9,652 cycles

CENTER CARGO LT LONGERON SPLICE AT STATION 5-113 TO 1541 LONGERON 41 CRACKED. REMOVED PER SRM 51-33-01 VOLUME II. NEW SPLICE A5A7114-553 FABRICATED PER DWG A5A7114 AND PART MARKED PER GMM 7-0-1001. FABRICATED SPLICE FX A5A7114-553 INSTALLED PER SRM 51-33-01 VOLUME II.

Part: SEAT TRACK — WORN (ZONE 200) · airframe 34,367 hrs · 9,652 cycles

SEAT TRACK CROWN DAMAGED AT APPROXIMATE STA 839 RBL 8.5. TRIMMED OFF AS PER SRM 55-70-00 FIGURE 1 VOLUME I. NEW SEAT TRACK AND FABRICATED REPAIR SPLICE INSTALLED SRM 55-70-00 FIGURE 1 VOLUME I.

Part: LONGERON — CRACKED (ZONE 100) · airframe 34,367 hrs · 9,652 cycles

CENTER CARGO LT LONGERON SPLICE AT STATION 5-113 TO 1541 LONGERON 37 CRACKED. REMOVED AND REPLACED AS PER SRM 51-33-01 VOLUME II.

Part: LONGERON — CRACKED (ZONE 100) · airframe 34,367 hrs · 9,652 cycles

CENTER CARGO LT HAND LONGERON SPLICE AT STATION 5-113 TO 1541 LONGERON 39 CRACKED. REMOVED AND REPLACED AS PER SRM 51-33-01 VOLUME II.

Part: FITTING — CORRODED (ZONE 500) · airframe 34,367 hrs · 9,652 cycles

LT WING, OB FLAP OB HINGE FORWARD FITTING MIDDLE. OB HOLE FOUND CORRODED. CORROSION REMOVED PER SRM 51-21-01 VOLUME II. ORIGINAL DIAMETER = 0.457, FINAL DIAMETER = 0.517 COMPLIED WITH FEDEX EA 1-5750-80364, WINGS - TRAILING EDGE FLAPS - LEFT OUTBOARD FLAP - HINGE BRACKET SUPPORTS CORRODED.

Part: FITTING — CORRODED (ZONE 500) · airframe 34,367 hrs · 9,652 cycles

LT WING, OB FLAP OB HINGE FORWARD FITTING AFT. IB HOLE FOUND CORRODED. CORROSION REMOVED PER SRM 51-21-01 VOLUME II. ORIGINAL DIAMETER = 0.442, FINAL DIAMETER = 0.502 COMPLIED WITH FEDEX EA 1-5750-80364, WINGS - TRAILING EDGE FLAPS - LEFT OUTBOARD FLAP - HINGE BRACKET SUPPORTS CORRODED.

Part: HINGE — CORRODED (ZONE 500) · airframe 34,367 hrs · 9,652 cycles

LT WING, OB FLAP IB HINGE FORWARD FITTING FORWARD. IB HOLE FOUND CORRODED. CORROSION REMOVED PER SRM 51-21-01 VOLUME II. ORIGINAL DIAMETER = 0.567, FINAL DIAMETER = 0.627. COMPLIED WITH FEDEX EA 1-5750-80364, WINGS - TRAILING EDGE FLAPS - LEFT OUTBOARD FLAP - HINGE BRACKET SUPPORTS CORRODED.

Part: FITTING — CORRODED (ZONE 500) · airframe 34,367 hrs · 9,652 cycles

LT WING, OB FLAP OB HINGE FORWARD FITTING. FORWARD IB HOLE FOUND CORRODED. CORROSION REMOVED PER SRM 51-21-01 VOLUME II. ORIGINAL DIAMETER = 0.442, FINAL DIAMETER = 0.502. COMPLIED WITH FEDEX EA 1-5750-80364, WINGS - TRAILING EDGE FLAPS - LEFT OUTBOARD FLAP - HINGE BRACKET SUPPORTS CORRODED.

Part: SEAL — TORN (WINDOW) · airframe 34,184 hrs · 9,609 cycles

DURING CLIMB-OUT PASSING FL250, A LOUD NOISE BEGAN FROM LEFT SLIDING WINDOW. NOISE CONTINUED AT VARIOUS ALTITUDES. TRIED ALL ALTITUDES FROM FL250 TO FL350. NOISE DIDN'T STOP UNTIL 9,000 FEET AND 245 KNOTS. DP, WHEN IT STOPPED WAS 3.7 CABIN ALTITUDE WAS 930 FEET. NOISE WAS INTOLERABLE TO ALLOW CONTINUANCE OF FLIGHT. RETURNED TO MEM. BULB SEAL ATTACHED TO SLIDING WINDOW TORN UPPER FWD CORNER. REMOVED AND REPLACED LEFT SLIDING CLEARVIEW WINDOW, REF MD-11 M/M 56-12-01-4. PRESSURIZED A/C TO CHECK FOR LEAKS. NONE NOTED.

Part: FLOORBEAM — CRACKED (LWR CTR CARGO) · airframe 33,994 hrs · 9,551 cycles

FOUND LWR FLOORBEAM IN CENTER CARGO COMP AT APPROX FRAME STA 1701 AT APPROX 30 INCHES FROM CENTER LINE ON RT SIDE. NOTE: THERE IS ALSO DAMAGE TO LT SIDE.

Part: PANEL — MISSING (RT WING) · airframe 33,709 hrs · 9,488 cycles

PANEL ON TOP OF RIGHT WING MISSING. REPLACED WING PANEL USING APPROVED PARTS AND METHODS USING EA 1-5710-78268. PART NUMBER OF PANEL INSTALLED IS ARC0629-502 AND IS INK-STAMPED ACCORDINGLY REF MM CHAP 51 SRM. OK FOR SERVICE. INST ON A/C ONLY, NO REMOVAL ON MFG ARC0629-502.

Part: COMPUTER — INOPERATIVE (FLT CONTROL) · airframe 31,635 hrs · 8,999 cycles

IMMEDIATELY AFTER TAKEOFF, FUEL AND MISC CUE ALERTS CAME ON. (FUEL ALERT, LEVEL 1 (TANK 3 FWD PUMP OFF). MISC CUE ALERT, LEVEL 1 (NO AUTOLAND). ADDITIONALLY, PFD AUTOPILOT BOX WENT AMBER, WITH (AP OFF) DISPLAYED. NEITHER AP WOULD ENGAGE AT 500 FT AGL, AFTER CYCLING THE SWITCH (AUTOFLIGHT BUTTON). REFERRED TO QRH AND HAND FLEW THE AIRCRAFT AS MAINTENANCE WAS CONSULTED. RETURNED TO PANC AFTER FUEL DUMP (50 K LBS). LANDING UNEVENTFUL. REMOVED AND REPLACED FCC NR 2 IAW MM 22-01-03 AFS RTS ACCOMPLISHED IAW MM 22-01-10-5.

Part: PRECOOLER — FAILED (BLEED AIR) · airframe 31,317 hrs · 8,935 cycles

MOMENTARY INDICATION OF NR 2 BLEED MANF FAILURE. (RED LIGHT ON OVERHEAD AND RED LINE ON NR 2 BLEED MANF SYNOPTIC). ASC DEPRESSURIZED NR 2 MANF. QRH PROCEDURES ACCOMPLISHED. PHONE PATCH W/MEM GOC ADVISED TO CONTINUE TO NANDI. PERFORMED DECAY CHECK AND DECAY CHECK FAILED PER JRH. OPENED ENGINE PER MM REF 71-10-00-2 AND INSPECTED FOR BLOWN DUCTS AND LEAKS. NO DISCREPANCIES NOTED. PER MFC FAULT OPENED PRECOOLER AREA AND FOUND PRECOOLER LEAKING. REMOVED AND REPLACED PRECOOLER PER MM REF 36-13-01-2-2.OPS AND LEAK CHECK GOOD. PERFORMED DECAY CHECK AGAIN PER JRH AND DECAY PASSED.CLOSED ENG & PATIO PER MM REF 71-10-00-2-1. DUE TO AIR TURN BACK.

Part: MANIFOLD — DAMAGED (PNEUMATIC SYSTEM) · airframe 30,178 hrs · 8,681 cycles

IN CRUISE (FL320) AFTER 5+30 FLIGHT, AIR MANF 2 FAIL WARNING ILLUMINATED, NR 2 PACK SHUTDOWN AUTOMATICALLY. DIVERTED TO NFFN. ACN RELEASED FOR SERVICE PER MEL/CDL: 36-10-02-A CATEGORY: C EXPIRATION: 22MAY03. MEL 36-10-02-A: PNEUMATIC SUPPLY SYS NR 2 - INOP. PNEU MANF DECAY CHECK C/OUT PER MM 36-00-01 - WITHIN MM LIMIT. (ACTUAL 28 SECS 25- 15 PSI MIN 19.2 SECS). 22MAY03 SFS MX R/R'D D1-126 SENSING ELEMENT I.A.W. AMM 36-23-07-04. OPS OK.

Part: RIB — CRACKED (ZONE 300) · airframe 29,500 hrs · 8,526 cycles

RT HORIZONTAL STAB AT STA XE 122.594, FWD RIB, ONE HORIZONTAL MACHINED ANGLE FOUND A CRACKED, LINE MEASURED APPROX. 1 INCH IN LENGTH. HORIZONTAL STABILIZER UPPER FORWARD RIB XE 122.594 REPAIRED AS PER FEDEX EA 1-5510-63146 - STABILIZERS - HORIZONTAL STABILIZER - UPPER FORWARD RIB CRACKED AT XE =122.594

Part: SPAR CAP — CORRODED (ZONE 300) · airframe 29,500 hrs · 8,526 cycles

COMPLY WITH EA 1-5510-67532, HORIZONTAL STABILIZER, RT SPAR CAP, REPLACEMENT IAW SR DRAWING REPLACES EA 1-5510-64246 PART 3 AND IS TERMINATING ACTION. HORIZONTAL STABLIZER, RT SPAR CAP REMOVED AND REPLACED IAW EA 1-5510-67532. HORIZONTAL STABILIZER, RT SPAR CAP REPLACEMENT IAW SR DRAWING SR11550010.

Part: HINGE BRACKET — DAMAGED (ZONE 600) · airframe 29,500 hrs · 8,526 cycles

RT WING O/B FLAP I/B HINGE ACTUATOR I/B ATTACHMENT HOLE FOUND WITH A GROOVE MARK. COMPLIED WITH FEDEX EA 1-5750-67561. WING TRAILING EDGE & TRAILING EDGE DEVICES, RT OUTBOARD FLAP, INBOARD HINGE BRACKET REPAIR.

Part: LONGERON — CORRODED (FUSELAGE) · airframe 29,500 hrs · 8,526 cycles

CAC COMPARTMENT - BETWEEN BS 1139 - 1159, LONGERON 48L EDGE CORRODED. REPAIRED AS PER FEDEX EA NR 1-5310-63144.

Part: SPAR CAP — DAMAGED (HORIZ STAB) · airframe 29,500 hrs · 8,526 cycles

LEFT HORIZONTAL STABILIZER UPPER SPAR CAP AFT PLANK NR 33L BORE REAMED TO ALLOWABLE OVERSIZE DIA 1.178 INCHES IAW SB FOUND WITH 02 EA.

Part: STRUCTURE — CORRODED (HORIZ STAB) · airframe 29,500 hrs · 8,526 cycles

LEFT HORIZONTAL STABILIZER UPPER BARREL NUT BORE NR 26L FOUND CORROSION ON BEARING SURFACE AND BORE REAMED BEYOND MAXIMUM OVERSIZE LIMIT IAW EO 1-5510-7-5000 AND SB MD11-55-023.

Part: SUPPORT — CRACKED (RT WING LE) · airframe 29,500 hrs · 8,526 cycles

RT WING LEADING EDGE NR 16 SLAT TRACK SUPPORT INBOARD SIDE FOUND CRACKED APPROXIMATELY 1 INCH IN LENGTH. RT WING LEADING EDGE NR 16 SLAT TRACK CRACKED. RIB REMOVED IAW SRM 51-31-01 VOL. II, FABRICATED IAW DWG NR ARB2850 AND INSTALLED IAW SRM 51-31-01 VOL. II.

Part: HINGE BRACKET — CORRODED (ZONE 500) · airframe 29,500 hrs · 8,526 cycles

SNRM N0557 - LT WING INBOARD T/E FLAP OUTBOARD LOWER SIDE AT FLAP SIDE, AT PIVOT PIN BORE HOLE FOUND CORROSION. ** S/D ** COMING

Part: HINGE BRACKET — CORRODED (ZONE 600) · airframe 29,500 hrs · 8,526 cycles

SNRM N0566 - RT WING INBOARD T/E FLAP AT OUTBOARD SIDE OF THE FLAP SIDE OF THE HINGE PIVOT BORE HOLE FOUND CORROSION. ** S/D ** COMING

Part: STRUCTURE — CORRODED (HORIZ STAB) · airframe 28,268 hrs · 8,251 cycles

NR 1 TAIL FUEL TANK FIFTH BARREL NUT BORE FWD OF REAR SPAR IS CORRODED AT HORIZ STAB UPPER AFT PLANK COMMON TO LT OPERATING BLKHD AND CONSTANT SECTION JOINT.

Part: SUPPORT FITTING — CORRODED (T/E FLAP) · airframe 28,010 hrs · 8,189 cycles

LEFT WING O/B FLAP HINGE SUPPORT FITTING LWR ATTACH POINTS HAVE RUST EMITTING FROM MATING SURFACES. REMOVED AND REPLACED BOLT PER CMM 57-44-09. FAB BUSHING PER CMM 57-44-09.

Part: SUPPORT FITTING — CORRODED (T/E FLAP) · airframe 28,010 hrs · 8,189 cycles

LEFT WING O/B FLAP I/B HINGE SUPPORT LWR ATTACH POINTS HAVE RUST EMITTING FROM MATING SURFACES. REMOVED AND REPLACED PER MM 57-44-08. FAB 2 BUSHINGS PER CMM 57-44-08.

Part: SPRING — BROKEN (LT MLG DOOR) · airframe 27,955 hrs · 8,176 cycles

RED LIGHT IN BOTH PRIMARY AND SECONDARY LEFT MAIN GEAR AFTER TAKEOFF WHEN GEAR HANDLE IN THE UP POSITION. GEAR RECYCLED 3 TIMES, NO CHANGE. CONFORMED WITH QUICK REFERENCE HANDBOOK. CHECKED LT LANDING GEAR THEN FOUND LEFT LANDING GEAR DOOR LATCH SPRING BROKEN. REF TO IPC 32-34-05-01 ITEM 50. FOUND SPRING ON LEFT DOOR LATCH MECHANISM BROKEN AND WAS CAUGHT ON THE LOCK MECHANISM. INSPECTED LOCK AND RELATED MECHANISM, NO DEFECTS FOUND. REPLACED SPRING ON LEFT MLG DOOR LATCH PER MM 32-34-03-4 AND ALTERNATE RELEASE CHECK FOR LT MLG DOOR C/O PER REF MM 32-32-00-5. LEFT MLG PROX SENSOR TEST C/O PER MM 32-61-15-5 AND TESTED OK. OK FOR SERVICE.

Part: CONTROLLER — MALFUNCTIONED (PNEUMATIC SYS) · airframe 27,778 hrs · 8,127 cycles

IN CRUISE FL 290 ALL ANTI ICE ON, RECEIVED LEVEL 1 ALERT AIR MANIF 2 FAIL. BROUGHT NR 2 THROTTLE TO IDLE AND COMPLIED WITH RED TABS IN QRH. ALERT WENT AWAY. LEFT THROTTLE 2 AT IDLE FOR REMAIN OF FLIGHT. AC RELEASED FOR SERVICE PER MEL/CDL. REPLACED 15A AND 15B LOOPS. LOOPS HAVE SHORT CIRCUIT. REPLACED THE MFC DUE TO TERMINATION OF COMMUNICATION WITH COMP OCCURRED SEVERAL TIMES. PERFORMED DECAY CHECK WITH MD11 JRH, IT TOOK 27 SEC NR 2 MANI PRESS FROM 25 PSI TO 15 PSI, TEST WAS PASSED.

Part: SKIN — SEPARATED (ELEVATOR) · airframe 27,271 hrs · 8,012 cycles

RIGHT O/B ELEVATOR UPPER SURFACE EXHIBITS COMPOSITE SCREEN MESH SEPARATION AT CRACKING PAINT.

Part: WARNING SYSTEM — FALSE ACTIVATION (MLG) · airframe 7,893 hrs · 26,802 cycles

LAND GEAR AURAL WARN CONSTANTLY ON WHILE GEAR UP. R&R LT OUTBOARD FLAP TRANSMITTER & WIRES.

Part: CONTROL VALVE — FAILED (LANDING GEAR) · airframe 26,592 hrs · 7,830 cycles

LANDING GEAR WOULD NOT RETRACT. REMOVED AND REPLACED LANDING GEAR CONTROL VALVE PER MM 32-31-20-4.