N576FE

Part: CONTROL CABLE — BROKEN (SLATS) · airframe 90,318 hrs · 21,269 cycles

CREW REPORTED SLAT DISAG ALERT. MX FOUND THE R/H SLAT DROOPED LEADING EDGE EXTENDED WITH ASSOCIATED CABLES BROKEN IN THE CAC.

Part: SENSOR — FAILED · airframe 88,839 hrs · 20,854 cycles

PASSING 9000 FEET ON CLIMB OUT, WHILE ACCELERATING, LEVEL 2 SLAT DISAG. ALERT. COMPLIED WITH QRH. ALERT WAS SPURIOUS AND WENT OUT PRIOR TO CRUISE ALTITUDE. ALERT RETURNED ON DESCENT CAUSING SPURIOUS AIRSPEEDS ON APPROACH. COMPLIED WITH QRH, PERFORMED A FLAPS 28/RET LANDING. SHGN 12MAR22 15:04 SYD U T/S PER FIM: 31-71-07-00. NO FAULTS NOTED ON PROX UNIT. OPERATED SLATS PER AMM: 27-80-00-2 AND ALL FOUND NML. WORK IN PROGRESS. REPLACED 4B SLAT POSITION SENSOR PER AMM 27-84-03-4, OPS CHECK C/OUT OK. FCC 1 & 2 RTS PASSED PER AMM 22-00-00-5. A/C OK FOR SVC.

Part: SPLICE — CRACKED (100) · airframe 88,832 hrs · 20,853 cycles

CENTER CARGO - STATION 5-113 TO STATION 1541 LONGERON 41 LEFT LONGERON SPLICE FOUND CRACKED. CENTER CARGO - STATION 5-113 TO STATION 1541 LONGERON 41 LEFT CRACKED LONGERON SPLICE REMOVED AND REPLACED AS PER SRM 51-33-01-0G . LONGERON SPLICE FABRICATED BY MACHINING AS PER DOUGLAS DRAWING A5A 7114 REV E . REPAIR CLASSIFIED AS MAJOR PER GMM 6-2-100.

Part: FRAME — NONE (200) · airframe 88,832 hrs · 20,853 cycles

MAIN DECK CARGO COMPARTMENT , LEFT HAND STATION 535 LONGERON 24 LEFT FRAME ATTACHED REPAIR ANGLE FOUND CHAFFED. MAIN DECK CARGO COMPARTMENT LEFT HAND STATION 535 LONGERON 24 LEFT FRAME REPAIR ANGLE CHAFFED REMOVED AND FOUND EXCEEDED LIMIT PER SRM 53-00-00-2R FIGURE 205 REPAIR GENERAL . FRAME REPAIR CARRIED OUT AS PER SRM 53-20-07-2R REPAIR 1 FIGURE 201. REPAIR CLASSIFIED AS MAJOR PER GMM 6-2-100.

Part: FRAME — NONE (200) · airframe 88,832 hrs · 20,853 cycles

MAIN DECK CARGO COMPARTMENT LEFT HAND STATION 535 LONGERON 19 LEFT FRAME ATTACHED REPAIR ANGLE FOUND CHAFFED. MAIN DECK CARGO COMPARTMENT LEFT HAND STATION 535 LONGERON 19 LEFT FRAME REPAIR ANGLE CHAFFED REMOVED AND FOUND EXCEEDED LIMIT PER SRM 53-00-00-2R FIGURE 205 REPAIR GENERAL. FRAME REPAIR CARRIED OUT AS PER SRM 53-20-07-2R REPAIR 1 FIGURE 202. REPAIR CLASSIFED AS MAJOR PER GMM 6-2-100.

Part: STIFFENER — CRACKED (300) · airframe 88,832 hrs · 20,853 cycles

EMPENNAGE - AFT FUSELAGE BULKHEAD STATION 2163.685 LEFT HAND SIDE LOWEST STIFFENER GUIDE PIN RECEPTACLE AREA FOUND CRACK 0.8 INCHES. EMPENNAGE - AFT FUSELAGE BULKHEAD STATION 2163.685 LEFT HAND SIDE LOWEST CRACKED STIFFENER REMOVED AND REPLACED AS PER SRM 51-33-01-0G . STIFFENER REWORKED AS PER DOUGLAS DRAWING AJC 7001 REVISION DT . REFER CLASSIFIED AS MAJOR PER GMM 6-2-100.

Part: DOUBLER — CRACKED (600) · airframe 88,832 hrs · 20,853 cycles

RIGHT HAND WING - LEADING EDGE CAVITY BEADED DOUBLER AT STATION XOS = 640 FOUND CRACK. RIGHT HAND WING LEADING EDGE CAVITY DOUBLER AT STATION XOS 640 REPAIR CARRIED OUT AS PER SRM 57-40-02-2R REPAIR 15 FIGURE 203. REPAIR CLASSIFIED AS MAJOR PER GMM 6-2- 100.

Part: DOUBLER — CRACKED (600) · airframe 88,832 hrs · 20,853 cycles

RIGHT HAND WING - LEADING EDGE CAVITY BEADED DOUBLER AT STATION XOS = 757 FOUND CRACK. RIGHT HAND WING LEADING EDGE CAVITY DOUBLER AT STATION XOS 757 REPAIR CARRIED OUT AS PER SRM 57-40-02-2R REPAIR 15 FIGURE 203. REPAIR CLASSIFIED AS MAJOR PER GMM 6-2- 100.

Part: SKIN — CRACKED (500) · airframe 88,832 hrs · 20,853 cycles

HIGH FREQUENCY EDDY CURRENT INSPECTION FOUND CRACK INDICATION APPROXIMATE 0.15" IN LENGTH AT LEFT HAND WING FIXED LEADING EDGE SKIN ADJACENT TO CUTOUT AT CORNER NUMBER 5 SLAT ACTUATOR ACCESS DOOR FORWARD INBOARD CORNER AT APPROXIMATE STATION XOS 484.511. LEFT HAND WING FIXED LEADING EDGE SKIN ADJACENT TO CUTOUT AT CORNER NUMBER 5 SLAT ACTUATOR ACCESS DOOR FORWARD INBOARD CORNER AT APPROXIMATE STATION XOS 484.511 REPAIR CARRIED OUT AS PER SRM 57-40-01-2R REPAIR 17 FIGURE 201. REPAIR CLASSIFIED AS MAJOR PER GMM 6-2-100.

Part: DOUBLER — CRACKED (600) · airframe 88,832 hrs · 20,853 cycles

RIGHT HAND WING LEADING EDGE CAVITY BEADED DOUBLER AT STATION XOS = 663 FOUND CRACK. RIGHT HAND WING LEADING EDGE CAVITY DOUBLER AT STATION XOS 663 REPAIR CARRIED OUT AS PER SRM 57-40-02-2R REPAIR 15 FIGURE 203. REPAIR CLASSIFIED AS MAJOR PER GMM 6-2- 100.

Part: DOUBLER — CRACKED (600) · airframe 88,832 hrs · 20,853 cycles

RIGHT HAND WING - LEADING EDGE CAVITY BEADED DOUBLER AT STATION XOS = 908 FOUND CRACK. RIGHT HAND WING LEADING EDGE CAVITY DOUBLER AT STATION XOS 908 REPAIR CARRIED OUT AS PER SRM 57-40-02-2R REPAIR 15 FIGURE 203. REPAIR CLASSIFIED AS MAJOR PER GMM 6-2- 100.

Part: DOUBLER — NONE (N/A) · airframe 88,832 hrs · 20,853 cycles

RIGHT HAND WING - LEADING EDGE CAVITY BEADED DOUBLER AT STATION XOS = 675 FOUND CRACK. RIGHT HAND WING LEADING EDGE CAVITY DOUBLER AT STATION XOS 675 REPAIR CARRIED OUT AS PER SRM 57-40-02-2R REPAIR 15 FIGURE 203. REPAIR CLASSIFIED AS MAJOR PER GMM 6-2- 100.

Part: DOUBLER — CRACKED (600) · airframe 88,832 hrs · 20,853 cycles

RIGHT HAND WING - LEADING EDGE CAVITY DOUBLER AT STATION XOS = 906 FOUND CRACK. RIGHT HAND WING LEADING EDGE CAVITY DOUBLER AT STATION XOS 906 CRACKED REMOVED AND FABRICATED DOUBLER PER DOUGLAS DRAWING ARB3954 REVISION K. INSTALLED FABRICATED DOUBLER AS PER SRM 51-33-01-0G. REPAIR CLASSIFIED AS MAJOR PER GMM 6-2- 100.

Part: DOUBLER — CRACKED (600) · airframe 88,832 hrs · 20,853 cycles

RIGHT HAND WING - LEADING EDGE CAVITY BEADED DOUBLER AT STATION XOS = 825 FOUND CRACK. RIGHT HAND WING LEADING EDGE CAVITY DOUBLER AT STATION XOS 825 REPAIR CARRIED OUT AS PER SRM 57-40-02-2R REPAIR 15 FIGURE 203. REPAIR CLASSIFIED AS MAJOR PER GMM 6-2- 100.

Part: DOUBLER — CRACKED (600) · airframe 88,832 hrs · 20,853 cycles

RIGHT HAND WING - LEADING EDGE CAVITY BEADED DOUBLER AT STATION XOS = 690 FOUND CRACK. RIGHT HAND WING LEADING EDGE CAVITY DOUBLER AT STATION XOS 690 REPAIR CARRIED OUT AS PER SRM 57-40-02-2R REPAIR 15 FIGURE 203. REPAIR CLASSIFIED AS MAJOR PER GMM 6-2- 100.

Part: CARGO TRACK — CORRODED (BS 835-855 LBL75) · airframe 88,832 hrs · 20,853 cycles

MAIN DECK CARGO COMPARTMENT - MAIN DECK CARGO APPROXIMATELY AT STATION 835 - 855 LEFT HAND SIDE X = 75.25 SEAT TRACK FOUND CORROSION. MAIN DECK CARGO COMPARTMENT , CORROSION AT SEAT TRACK STATION 835 TO STATION 855 X = 75.25 , EVALUATED FOUND EXFOLIATED AND EXCEEDED LIMIT AS PER SRM 53-00-52-1A FIGURE 101 ALLOWABLE DAMAGE 1. CORRODED SEAT TRACK REPAIRED BY SECTIONL SEAT TRACK REPLACEMENT AT EXISTING SPLICES FROM STATION 825 TO STATION 869 AS PER SRM 53-00-52-2R REPAIR 1 FIGURE 201. REPAIR CLASSIFIED AS MAJOR PER GMM 6-2-100.

Part: NONE — FAILED (N/A) · airframe 88,926 hrs · 20,882 cycles

EMER LT BAT 1 LO ALERT ON EAD AFTER PERFORMING EMERGENCY LIGHTS TEST. REMOVED AND REPLACED EMERGENCY LIGHTS POWER SUPPLY IAW AMM 33-51-01-4, OPS CHECKS NORMAL.

Part: NONE — NONE (N/A) · airframe 88,307 hrs · 20,717 cycles

INFLIGHT LEVEL 1 ALERT - BATTERY DISCHARGING REMOVED AND REPLACED THE 2 BATTERIES AND THE CHARGER PER MD11 AMM 24-34-02-4 AND 24-34-03-4. ALL TEST ARE GOOD ON THE GROUND.

Part: BATTERY — MALFUNCTIONED (MASTER) · airframe 86,898 hrs · 20,328 cycles

PDIS 576 24-22 0846 01JUN21 MEM OPEN U HAD EMER PWR ON LEVEL ONE ALERT. FOLLOWED QRH AND BATTERY POWER STAYED NORMAL FOR 35-40 MINUTES. THEN BATTERY POWER WENT FROM 26 DOWN TO 18 AND ADG WAS DEPLOYED. DECLARED AN EMERGENCY AND LANDED UNEVENTFULLY. REMOVED AND REPLACED LEFT EMER CONTROL RELAY IAW AMM 24-24-00-4. OK FOR SERVICE.

Part: WARNING SYSTEM — FALSE ACTIVATION (COCKPIT) · airframe 83,407 hrs · 19,416 cycles

THIRD REPEAT WRITE-UP. APPROX 45 INTO FLIGHT AT CRUISE FL330 OBSERVED INTERMITTENT LEVEL 1 "BATTERY DISCHARGING". ALERT CYCLED ON & OFF FROM 1-5 MIN INTER. NOTICED VOLTS IN THE 31-38V RANGE. LEVEL 1 BATTERY DISCHARGE ALERT CHANGED FROM INTERMITTENT TO STEADY. FOLLOWED QRH DIVERTED AND LANDED AT NEAREST SUITABLE. VOLTS NEVER FELL BELOW 31V. ALL MX COMPLETED ON MTSI 24-30/9215. ELECTRICAL SYSTEM ALERTS OPS CHECKS NORMAL ON GROUND AT THIS STATION PER MM 24-00-01-5.

Part: SHUTOFF VALVE — FAILED (FUEL SYSTEM) · airframe 83,352 hrs · 19,395 cycles

LEFT FUEL DUMP VALVE DISAG LEVEL 1 ALERT, WHILE DUMPING FUEL. R&R LH FUEL DUMP GATE SHUTOFF VALVE REF AMM 28-30-30-4 , ADJUSTMENT AND TEST REF MM 28-30-30-5 ,OP CHECK AND LEAK CHECK GOOD. CLOSE PANEL 561 AB.

Part: CONTROL UNIT — MALFUNCTIONED (MAIN BATTERY) · airframe 83,352 hrs · 19,395 cycles

ENROUTE, RECIEVED LEVEL 1 BATT DISCHARGING ALERT. THE ALERT WAS INTERMITTENT. REF TSI 24-30/9173 AND WRI 24-20/9179. EPCU R&R RELAYS R2-24,R2-5142,R2-5145, RCCB B1- 160 AND CB B1-949 R&R. ALL ENGINES RUN AND ALL TEST PASSED A/C OK FOR SERVICE AT THIS TIME

Part: HINGE BRACKET — CORRODED (LT WING TE FLAP) · airframe 83,314 hrs · 19,387 cycles

LEFT WING - WING SIDE INBOARD FLAP OUTBOARD HINGE INBOARD ACTUATOR LUG HOLE BORE FOUND CORROSION. CORROSION AT LEFT WING - WING SIDE INBOARD FLAP OUTBOARD HINGE INBOARD ACTUATOR LUG HOLE BORE (HOLE # 4) REWORKED AND FOUND WITHIN LIMIT AS PER MD-11 CMM 57-44-07. REPAIR BUSHING FABRICATED BY MACHINING AND INSTALLED AS PER MD-11 CMM 57-44-07 AND EA # 1-5750-T0331150 A PART 3 STEP 1A AND STEP 3. TITLE: WINGS- FLIGHT SURFACES- LH WING INBOARD FLAP OUTBOARD FWD HINGE (WING SIDE) REPAIR PSE 57.55.01.1 ALTERNATE METHOD. REPAIR CLASSIFIED AS MAJOR PER GMM 6-2-100.

Part: HINGE BRACKET — CORRODED (RT WING TE FLAP) · airframe 83,314 hrs · 19,387 cycles

RIGHT WING - WING SIDE INBOARD FLAP OUTBOARD HINGE PIVOT HOLE BORE FOUND CORROSION. CORROSION AT RIGHT WING - WING SIDE INBOARD FLAP OUTBOARD HINGE PIVOT HOLE BORE (HOLE # 3) REWORKED AND FOUND WITHIN LIMIT AS PER MD-11 CMM 57-44-07. REPAIR BUSHING FABRICATED BY MACHINING AND INSTALLED AS PER MD-11 CMM 57-44-07 AND EA # 1- 5750-T0331151 A PART 3 STEP 2 AND STEP 4. TITLE: WINGS- FLIGHT SURFACES- RH WING- INBD FLAP- OUTBD FORWARD HINGE BRACKET ASSEMBLY- PSE 57.55.01.1 INSPECTION- ALTERNATE METHOD. REPAIR CLASSIFIED AS MAJOR PER GMM 6-2-100.

Part: HINGE BRACKET — CORRODED (LT WING TE FLAP) · airframe 83,314 hrs · 19,387 cycles

LEFT WING - WING SIDE INBOARD FLAP OUTBOARD HINGE OUTBOARD ACTUATOR LUG HOLE BORE FOUND CORROSION. CORROSION AT LEFT WING - WING SIDE INBOARD FLAP OUTBOARD HINGE OUTBOARD ACTUATOR LUG HOLE BORE (HOLE # 4) REWORKED AND FOUND WITHIN LIMIT AS PER MD-11 CMM 57-44-07. REPAIR BUSHING FABRICATED BY MACHINING AND INSTALLED AS PER MD-11 CMM 57-44-07 AND EA # 1-5750-T0331150 A PART 3 STEP 1A AND STEP 3. TITLE: WINGS- FLIGHT SURFACES- LH WING INBOARD FLAP OUTBOARD FWD HINGE (WING SIDE) REPAIR PSE 57.55.01.1 ALTERNATE METHOD. REPAIR CLASSIFIED AS MAJOR PER GMM 6-2-100.

Part: HINGE BRACKET — CORRODED (RT WING TE FLAP) · airframe 83,314 hrs · 19,387 cycles

RIGHT WING - WING SIDE INBOARD FLAP OUTBOARD HINGE OUTBOARD ACTUATOR HOLE BORE FOUND CORROSION. CORROSION AT RIGHT WING - WING SIDE INBOARD FLAP OUTBOARD HINGE OUTBOARD ACTUATOR LUG HOLE BORE (HOLE # 4) REWORKED AND FOUND WITHIN LIMIT AS PER MD-11 CMM 57-44-07. REPAIR BUSHING FABRICATED BY MACHINING AND INSTALLED AS PER MD-11 CMM 57-44-07 AND EA # 1-5750-T0331151 A PART 3 STEP 2 AND STEP 4. TITLE: WINGS- FLIGHT SURFACES- RH WING- INBD FLAP- OUTBD FORWARD HINGE BRACKET ASSEMBLY- PSE 57.55.01.1 INSPECTION- ALTERNATE METHOD. REPAIR CLASSIFIED AS MAJOR PER GMM 6-2-100.

Part: HINGE BRACKET — CORRODED (RT WING TE FLAP) · airframe 83,314 hrs · 19,387 cycles

RIGHT WING - WING SIDE INBOARD FLAP OUTBOARD HINGE INBOARD ACTUATOR LUG HOLE BORE FOUND CORROSION. CORROSION AT RIGHT WING - WING SIDE INBOARD FLAP OUTBOARD HINGE INBOARD ACTUATOR LUG HOLE BORE (HOLE # 4) REWORKED AND FOUND WITHIN LIMIT AS PER MD-11 CMM 57-44-07. REPAIR BUSHING FABRICATED BY MACHINING AND INSTALLED AS PER MD-11 CMM 57-44-07 AND EA # 1-5750-T0331151 A PART 3 STEP 2 AND STEP 4. TITLE: WINGS- FLIGHT SURFACES- RH WING- INBD FLAP- OUTBD FORWARD HINGE BRACKET ASSEMBLY- PSE 57.55.01.1 INSPECTION- ALTERNATE METHOD. REPAIR CLASSIFIED AS MAJOR PER GMM 6-2-100.

Part: HINGE BRACKET — CORRODED (LT WING TE FLAP) · corrosion level 2 · airframe 83,314 hrs · 19,387 cycles

LEFT WING - WING SIDE OUTBOARD FLAP INBOARD HINGE BARREL NUT HOLE SURFACE FOUND CORROSION. CORROSION AT LEFT WING - WING SIDE OUTBOARD FLAP INBOARD HINGE BARREL NUT HOLE SURFACE REWORKED AS PER MD-11 CMM 57-44-08 AND FOUND UPPER AND LOWER BARREL NUT MATING SURFACE EXCEED LIMIT BASED THE DIFFERENCE BETWEEN DRAWING LIMITS AND CMM MAXIMUM REWORK LIMITS FOR BARREL NUT HOLE. REPAIR SHIM FABRICATED AND INSTALLED AS PER MD-11 CMM 57-44-08 AND E.A. #: 1-5750-T0351773 PART 1 STEP 3. TITLE: WINGS- FLIGHT SURFACES -EO 1-5750-7-5002- LH WING- OUTBD FLAP, INBD FWD HINGE (WING SIDE) -CORROSION REPAIR. REPAIR CLASSIFIED AS MINOR PER GMM 6-2-100.

Part: SUPPORT FITTING — CORRODED (LT WING TE FLAP) · corrosion level 2 · airframe 83,314 hrs · 19,387 cycles

LEFT WING - OUTBOARD FLAP VANE NUMBER 1 SUPPORT FITTING ECCENTRIC HOLE BORE FOUND CORROSION. CORROSION AT LEFT WING - OUTBOARD FLAP VANE NUMBER 1 SUPPORT FITTING ECCENTRIC HOLE BORE REWORKED BY MACHINING AND FOUND EXCEED LIMIT AS PER MD-11 SRM 57-50-02- 2R REPAIR 5 FIGURE 201. OVERSIZED ECCENTRIC BUSHING FABRICATED BY MACHINING AS PER MD-11 SRM 57-50-02-2R REPAIR 5 FIGURE 201 AND EA.#: 1-5750-T0352016 PART 1 STEP 1A. TITLE: WINGS- FLIGHT SURFACES- LH WING - OUTBD FLAP VANE ASSY - TRACK SUPPORT FITTINGS CORROSION REPAIR. BUSHING INSTALLED AS PER AMM 27-50-32-4. LEFT HAND WING OUTBOARD FLAP VANE ADJUSTMENT AND TEST CARRIED OUT AS PER AMM 27-50-32-5 FOUND SATISFACTORY. REPAIR CLASSIFIED AS MINOR PER GMM 6-2-100.

Part: SUPPORT FITTING — CORRODED (LT WING TE FLAP) · corrosion level 2 · airframe 83,314 hrs · 19,387 cycles

LEFT WING - OUTBOARD FLAP VANE NUMBER 2 SUPPORT FITTING ECCENTRIC HOLE BORE FOUND CORROSION CORROSION AT LEFT WING - OUTBOARD FLAP VANE NUMBER 2 SUPPORT FITTING ECCENTRIC HOLE BORE REWORKED BY MACHINING AND FOUND EXCEED LIMIT AS PER MD-11 SRM 57-50-02- 2R REPAIR 5 FIGURE 201. OVERSIZED ECCENTRIC BUSHING FABRICATED BY MACHINING AS PER MD-11 SRM 57-50-02-2R REPAIR 5 FIGURE 201 AND EA.#: 1-5750-T0352016 PART 1 STEP 1A. TITLE: WINGS- FLIGHT SURFACES- LH WING - OUTBD FLAP VANE ASSY - TRACK SUPPORT FITTINGS CORROSION REPAIR. BUSHING INSTALLED AS PER AMM 27-50-32-4. LEFT HAND WING OUTBOARD FLAP VANE ADJUSTMENT AND TEST CARRIED OUT AS PER AMM 27-50-32-5 FOUND SATISFACTORY. REPAIR CLASSIFIED AS MINOR PER GMM 6-2-100.

Part: STRINGER — CRACKED (ZONE 100) · airframe 83,314 hrs · 19,387 cycles

CENTER UPPER AUXILIARY FUEL TANK STRINGER 46 FOUND CRACK FROM XCW 42.5 TO XCW 52.3. CENTER UPPER AUXILIARY FUEL TANK STRINGER 46 FROM XCW 42.5 TO XCW 52.3 CARRIED OUT REPAIR IAW EA # 1-5710-T0352202 PART 1 TITLE :" WINGS - BASIC WING STRUCTURE - CENTER WING LOWER PANEL - CRACK FOUND ON STRINGER S-46 BETWEEN XCW 42.5 AND XCW 52.3 " REPAIR CLASSIFIED AS MAJOR PER GMM 6-2-100.

Part: STRINGER — CRACKED (ZONE 100) · airframe 83,314 hrs · 19,387 cycles

CENTER UPPER AUXILIARY FUEL TANK STRINGER 47 FOUND CRACK FROM XCW 14 TO XCW 23.8 CENTER UPPER AUXILIARY FUEL TANK CRACKED STRINGER 47 FROM XCW 14 TO XCW 23.8 CARRIED OUT REPAIR AS PER SRM 57-10-03-2R FIGURE 201 REPAIR 1. REPAIR CLASSIFIED AS MAJOR PER GMM 6-2-100.

Part: STRINGER — CRACKED (ZONE 100) · airframe 83,314 hrs · 19,387 cycles

CENTER UPPER AUXILIARY FUEL TANK STRINGER 47 FOUND CRACK FROM XCW 37.5 TO XCW 52 CENTER UPPER AUXILIARY FUEL TANK CRACKED STRINGER 47 FROM XCW 37.5 TO XCW 52 CARRIED OUR REPAIR AS PER SRM 57-10-03-2R FIGURE 201 REPAIR 1 . REPAIR CLASSIFIED AS MAJOR PER GMM 6-2-100.

Part: STRINGER — CRACKED (ZONE 100) · airframe 83,314 hrs · 19,387 cycles

CENTER UPPER AUXILIARY FUEL TANK STRINGER 47 FOUND CRACK FROM XCW -14.2 TO XCW - 23 CENTER UPPER AUXILIARY FUEL TANK CRACKED STRINGER 47 FROM XCW -14.2 TO XCW -23 CARRIED OUT REPAIR AS PER SRM 57-10-03-2R FIGURE 201 REPAIR 1. REPAIR CLASSIFIED AS MAJOR PER GMM 6-2-100.

Part: STRINGER — CRACKED (ZONE 100) · airframe 83,314 hrs · 19,387 cycles

CENTER UPPER AUXILIARY FUEL TANK STRINGER 47 FOUND CRACK FROM XCW -39.4 TO XCW - 52.5. CENTER UPPER AUXILIARY FUEL TANK CRACKED STRINGER 47 FROM XCW -39.4 TO XCW -52.5 CARRIED OUT REPAIR AS PER SRM 57-10-03-2R FIGURE 201 REPAIR 1. REPAIR CLASSIFIED AS MAJOR PER GMM 6-2-100.

Part: LONGERON — CRACKED (BS 595) · airframe 83,314 hrs · 19,387 cycles

NOSE LANDING GEAR Ï¿½ WHILE CARRING OUT LEFT HAND TRUNNION FITTING REPAIR FOUND LONGERON 49 LEFT HAND CRACK AT STATION Y=595. NOSE LANDING GEAR LEFT HAND TRUNNION FITTING AREA CRACK LONGERON 49 LEFT HAND STATION Y=595 REMOVED AND REPLACED AS PER MD-11 SRM 51-33-01-0G AND FABRICATED LONGERON AS PER DOUGLAS DRAWING ACA 3796 REVISION A. REPAIR CLASSIFIED AS MAJOR PER GMM 6-2-100.

Part: LONGERON — CRACKED (BS 595) · airframe 83,314 hrs · 19,387 cycles

NOSE LANDING GEAR Ï¿½ WHILE CARRING OUT RIGHT HAND TRUNNION FITTING REPAIR FOUND LONGERON 49 RIGHT HAND CRACK AT STATION Y=595. NOSE LANDING GEAR RIGHT HAND TRUNNION FITTING AREA CRACK LONGERON 49 RIGHT HAND STATION Y=595. REMOVED AND REPLACED AS PER MD-11 SRM 51-33-01-0G AND FABRICATED LONGERON AS PER DOUGLAS DRAWING ACA 3796 REVISION A. REPAIR CLASSIFIED AS MAJOR PER GMM 6-2-100.

Part: HINGE BRACKET — CORRODED (RT WING TE FLAP) · corrosion level 2 · airframe 83,314 hrs · 19,387 cycles

RIGHT WING - WING SIDE INBOARD FLAP OUTBOARD HINGE PIVOT HOLE SURFACE FOUND CORROSION CORROSION AT RIGHT WING - WING SIDE INBOARD FLAP OUTBOARD HINGE PIVOT HOLE SURFACE REWORKED AND FOUND EXCEED LIMIT AS PER MD-11 CMM 57-44-07. REPAIR EVALUATED AND FOUND PIVOT BORE REMAINING THICKNESS IS CORRECT AS PER EA # 1-5750- T0331151 A PART 3 FIGURE 2. TITLE: WINGS- FLIGHT SURFACES- RH WING- INBD FLAP- OUTBD FORWARD HINGE BRACKET ASSEMBLY- PSE 57.55.01.1 INSPECTION- ALTERNATE METHOD. REPAIR CLASSIFIED AS MAJOR PER GMM 6-2-100.

Part: HINGE BRACKET — CORRODED (LT WING TE FLAP) · corrosion level 2 · airframe 83,314 hrs · 19,387 cycles

LEFT WING - WING SIDE INBOARD FLAP OUTBOARD HINGE PIVOT HOLE BORE FOUND CORROSION. CORROSION AT LEFT WING - WING SIDE INBOARD FLAP OUTBOARD HINGE PIVOT HOLE BORE (HOLE # 3) REWORKED AND FOUND EXCEED LIMIT AS PER MD-11 CMM 57-44-07. REPAIR BUSHING FABRICATED BY MACHINING AND INSTALLED AS PER MD-11 CMM 57-44-07 AND EA # 1- 5750-T0331150 A PART 3 STEP 1A AND STEP 3. TITLE: WINGS- FLIGHT SURFACES- LH WING INBOARD FLAP OUTBOARD FWD HINGE (WING SIDE) REPAIR PSE 57.55.01.1 ALTERNATE METHOD. REPAIR CLASSIFIED AS MAJOR PER GMM 6-2-100.

Part: SKIN — CORRODED (BS 1721-1741) · airframe 83,314 hrs · 19,387 cycles

REFER TO WRI #53108830 W/O #00076033 TO COMPLY WITH EA # T 1-5310-T0349168 A P2 TITLE : FUSELAGE Ï¿½ MAINFRAME Ï¿½ SKIN CORROSION ADJACENT THE VHF ANTENNA STATION 1721 Ï¿½ 1741 LONGERON 50L Ï¿½ 50R, BLENDOUT REPAIR FUSELAGE - STATION 1721 - 1741 LONGERON 50 LEFT - 50 RIGHT, CARRIED OUT REPAIR I A W EA # 1-5310-T0349168 B P2 TITLE : " FUSELAGE - MAINFRAME - SKIN CORROSION ADJACENT THE VHF ANTENNA STA 1721-1741 LONGERON 50L-50R , BLENDOUT REPAIR ". REPAIR CLASSIFIED AS MINOR PER GMM 6-2-100.

Part: BEAM — CRACKED (L3 DOOR) · airframe 83,314 hrs · 19,387 cycles

CABIN - L3 DOOR LOWER #7 STOP BEAM CRACKED . CABIN - L3 DOOR , CRACKED LOWER #7 STOP BEAM REMOVED AND REPLACED AS PER SRM 51- 31-01-0G . REPAIR CLASSIFIED AS MINOR PER GMM 6-2-100 .

Part: BEAM — CRACKED (R3 DOOR) · airframe 83,314 hrs · 19,387 cycles

CABIN - R3 DOOR UPPER #1 STOP BEAM FOUND CRACKED . CABIN - R3 DOOR , CRACKED UPPER #1 STOP BEAM REMOVED AND REPLACED AS PER SRM 51- 31-01-0G . REPAIR CLASSIFIED AS MINOR PER GMM 6-2-100 .

Part: HINGE BRACKET — CORRODED (LT WING TE FLAP) · corrosion level 2 · airframe 83,314 hrs · 19,387 cycles

LEFT WING - FLAP SIDE INBOARD FLAP OUTBOARD HINGE OUTBOARD PIVOT HOLE BORE FOUND CORROSION. CORROSION AT LEFT WING - FLAP SIDE INBOARD FLAP OUTBOARD HINGE OUTBOARD PIVOT HOLE BORE (HOLE A AND B) REWORKED AND FOUND EXCEED LIMIT AS PER MD-11 CMM 57-52- 03. OVERSIZED BUSHING FABRICATED BY MACHINING AND INSTALLED AS PER MD-11 CMM 57-52- 03 AND E.A. # : 1-5750-157160 D PART 3 STEP 2A AND 2B. TITLE: WINGS- FLIGHT SURFACES- LH WING- INBD FLAP- OUTBD HINGE (FLAP SIDE) BRACKET CORROSION-PSE 57.55.01.2. REPAIR CLASSIFIED AS MAJOR PER GMM 6-2-100.

Part: HINGE BRACKET — CORRODED (RT WING TE FLAP) · corrosion level 2 · airframe 83,314 hrs · 19,387 cycles

RIGHT WING - FLAP SIDE INBOARD FLAP OUTBOARD HINGE OUTBOARD PIVOT LUG HOLE BORE FOUND CORROSION. CORROSION AT RIGHT WING - FLAP SIDE INBOARD FLAP OUTBOARD HINGE OUTBOARD PIVOT LUG HOLE BORE (HOLE A AND B) REWORKED AND FOUND EXCEED LIMIT AS PER MD-11 CMM 57- 52-03. OVERSIZED BUSHING FABRICATED BY MACHINING AND INSTALLED AS PER MD-11 CMM 57- 52-03 AND EA # 1-5750-157161 D PART 3 STEP 2.A AND STEP 2.B. TITLE: WINGS- FLIGHT SURFACES- RH WING- INBD FLAP- OUTBD HINGE (FLAP SIDE) BRACKET CORROSION-PSE 57.55.01.2. REPAIR CLASSIFIED AS MAJOR PER GMM 6-2-100. (WRI: 57508842)

Part: SKIN — DAMAGED (RT WING LE) · airframe 83,314 hrs · 19,387 cycles

RIGHT HAND WING DROOPLED LEADING EDGE OUTBOARD SKIN EXISTING REPAIR DOUBLER FOUND WITH DAMAGED AT STATION XDLE 329.775 DAMAGED EXISTING REPAIR DOUBLER AT RIGHT HAND WING DROOPED LEADING EDGE OUTBOARD SKIN AT STATION XDLE 329.775 REMOVED AS PER SRM 51-33-01-0G. FABRICATED REPAIR DOUBLER AS PER SRM 57-40-01-2R FIGURE 202 REPAIR 15. FABRICATED REPAIR DOUBLER INSTALLED AS PER SRM 57-40-01-2R FIGURE 202 REPAIR 15. REPAIR CLASSIFIED AS MAJOR PER GMM 6-2-100.

Part: HINGE BRACKET — CORRODED (RT WING TE FLAP) · corrosion level 2 · airframe 83,314 hrs · 19,387 cycles

RIGHT WING - FLAP SIDE INBOARD FLAP OUTBOARD HINGE INBOARD PIVOT HOLE BORE FOUND CORROSION. CORROSION AT RIGHT WING - FLAP SIDE INBOARD FLAP OUTBOARD HINGE INBOARD PIVOT HOLE BORE (HOLE G AND F) REWORKED AND FOUND EXCEED LIMIT AS PER MD-11 CMM 57-52- 03. OVERSIZED BUSHING FABRICATED BY MACHINING AND INSTALLED AS PER MD-11 CMM 57-52- 03 AND E.A. # : 1-5750-157161 D PART 3 STEP 2A AND STEP 2B. TITLE: WINGS- FLIGHT SURFACES- RH WING- INBD FLAP- OUTBD HINGE (FLAP SIDE) BRACKET CORROSION-PSE 57.55.01.2. REPAIR CLASSIFIED AS MAJOR PER GMM 6-2-100.

Part: HINGE BRACKET — CORRODED (LT WING TE FLAP) · corrosion level 2 · airframe 83,314 hrs · 19,387 cycles

LEFT WING - FLAP SIDE INBOARD FLAP OUTBOARD HINGE INBOARD PIVOT HOLE BORE FOUND CORROSION. CORROSION AT LEFT WING - FLAP SIDE INBOARD FLAP OUTBOARD HINGE INBOARD PIVOT HOLE BORE (HOLE G AND F) REWORKED AND FOUND EXCEED LIMIT AS PER MD-11 CMM 57-52-03. OVERSIZED BUSHING FABRICATED BY MACHINING AND INSTALLED AS PER MD-11 CMM 57-52-03 AND EA # 1-5750-157160 D PART 3 STEP 2A AND 2B. TITLE: WINGS- FLIGHT SURFACES- LH WING- INBD FLAP- OUTBD HINGE (FLAP SIDE) BRACKET CORROSION-PSE 57.55.01.2. REPAIR CLASSIFIED AS MAJOR PER GMM 6-2-100. (WRI: 57508825)

Part: HINGE BRACKET — CORRODED (RT WING TE FLAP) · corrosion level 2 · airframe 83,314 hrs · 19,387 cycles

RIGHT WING - WING SIDE OUTBOARD FLAP OUTBOARD HINGE PIVOT HOLE BORE FOUND CORROSION. CORROSION AT RIGHT WING - WING SIDE OUTBOARD FLAP OUTBOARD HINGE PIVOT HOLE BORE (#4 HOLE) REWORKED AND FOUND EXCEED LIMIT AS PER MD-11 CMM 57-44-09. OVERSIZED BUSHING FABRICATED BY MACHINING AND INSTALLED AS PER MD-11 CMM 57-44-09 AND E.A. #: 1-5750-T0351908 PART 1 STEP 1. TITLE: WINGS- FLIGHT SURFACES -EO 1-5750-7- 5002- RH WING- OUTBD FLAP OUTBD HINGE ASSY (WING SIDE) -CORROSION REPAIR. REPAIR CLASSIFIED AS MINOR PER GMM 6-2-100.

Part: HINGE FITTING — CORRODED (LT WING TE FLAP) · corrosion level 2 · airframe 83,314 hrs · 19,387 cycles

LEFT WING - FLAP SIDE OUTBOARD FLAP OUTBOARD HINGE INBOARD PIVOT LUG HOLE BORE FOUND CORROSION. CORROSION AT LEFT WING - FLAP SIDE OUTBOARD FLAP OUTBOARD HINGE INBOARD PIVOT LUG HOLE BORE REWORKED AND FOUND EXCEED LIMIT AS PER MD-11 CMM 57-52-04. OVERSIZED BUSHING FABRICATED BY MACHINING AND INSTALLED AS PER MD-11 CMM 57-52-04 AND E.A. #: 1-5750-80375 A PART 2 STEP 2 AND STEP 1. TITLE: WINGS- FLIGHT SURFACES- EO 1- 5750-7-5002- LH WING-OUTBD FLAP- AFT OUTBD HINGE BRACKET ASSY-CORROSION REPAIR. REPAIR CLASSIFIED AS MINOR PER GMM 6-2-100.

Part: HINGE FITTING — CORRODED (LT WING TE FLAP) · corrosion level 2 · airframe 83,314 hrs · 19,387 cycles

LEFT WING - FLAP SIDE OUTBOARD FLAP INBOARD HINGE INBOARD PIVOT LUG HOLE BORE FOUND CORROSION. CORROSION AT LEFT WING - FLAP SIDE OUTBOARD FLAP INBOARD HINGE INBOARD PIVOT LUG HOLE BORE REWORKED AND FOUND EXCEED LIMIT AS PER MD-11 CMM 57-52-04. OVERSIZED BUSHING FABRICATED BY MACHINING AND INSTALLED AS PER MD-11 CMM 57-52-04 AND E.A. #: 1- 5750-80373 A PART 2 STEP 1. TITLE: WINGS- LH OUTBOARD TRAILING EDGE FLAP- INBD BRACKET PIVOT LUG BORES- CORROSION REPAIR. REPAIR CLASSIFIED AS MINOR PER GMM 6-2- 100.

Part: SEAT TRACK — DAMAGED (BS 1291) · airframe 83,314 hrs · 19,387 cycles

CABIN - SEAT TRACK AT STATION 1291 X = - 47.5 FOUND DAMAGE . CABIN - AT SEAT TRACK STATION 1291 X = - 47.5 DAMAGED CROWN EVALUATED AND FOUND TO EXCEED LIMIT AS PER SRM 53-00-52-1A FIGURE 101 ALLOWABLE DAMAGE 1 . CROWN DAMAGED SEAT TRACK REPAIRED BY SECTIONAL SEAT TRACK REPLACEMENT FROM STATION 1269 TO EXISTING SPLICE STATION 1331 X = - 47.5 AS PER SRM 53-00-52-2R FIGURE 201 REPAIR 1 . REPAIR CLASSIFIED AS MAJOR PER GMM 6-2-100 .

Part: FRAME — DAMAGED (BS 535) · airframe 83,314 hrs · 19,387 cycles

CABIN - LEFT HAND FRAME AT YOKE AREA STATION 535 LONGERON 19 LEFT FOUND DAMAGED . CABIN - LEFT HAND FRAME AT YOKE AREA STATION 535 LONGERON 19 LEFT DAMAGE FOUND TO EXCEED LIMIT AS PER SRM 53-00-00-2R FIGURE 205 ALLOWABLE DAMAGE , AND REPAIRED AS PER SRM 53-20-07-2R FIGURE 202 REPAIR 1 . REPAIR CLASSIFIED AS MAJOR PER GMM 6-2-100.

Part: HINGE BRACKET — CORRODED (RT WING TE FLAP) · corrosion level 2 · airframe 83,314 hrs · 19,387 cycles

RIGHT WING - WING SIDE OUTBOARD FLAP OUTBOARD HINGE BARREL NUT HOLE BORE FOUND CORROSION. CORROSION AT RIGHT WING - WING SIDE OUTBOARD FLAP OUTBOARD HINGE BARREL NUT HOLE (#10 HOLE) REWORKED AND FOUND EXCEED LIMIT AS PER MD-11 CMM 57-44-09. OVERSIZED BUSHING FABRICATED BY MACHINING AND INSTALLED AS PER MD-11 CMM 57-44-09 AND E.A. #: 1-5750-T0351908 PART 1 STEP 1. TITLE: WINGS- FLIGHT SURFACES -EO 1-5750-7- 5002- RH WING- OUTBD FLAP OUTBD HINGE ASSY (WING SIDE) -CORROSION REPAIR. REPAIR CLASSIFIED AS MINOR PER GMM 6-2-100.

Part: HINGE BRACKET — CORRODED (RT WING TE FLAP) · corrosion level 2 · airframe 83,314 hrs · 19,387 cycles

RIGHT WING - WING SIDE OUTBOARD FLAP OUTBOARD HINGE BARREL NUT UPPER HOLE BORE FOUND CORROSION. CORROSION AT RIGHT WING - WING SIDE OUTBOARD FLAP OUTBOARD HINGE BARREL NUT UPPER HOLE BORE (#7 HOLE) REWORKED AND FOUND EXCEED LIMIT AS PER MD-11 CMM 57-44- 09. OVERSIZED BUSHING FABRICATED BY MACHINING AND INSTALLED AS PER MD-11 CMM 57-44- 09 AND E.A. #: 1-5750-T0351908 PART 1 STEP 1. TITLE: WINGS- FLIGHT SURFACES -EO 1-5750-7- 5002- RH WING- OUTBD FLAP OUTBD HINGE ASSY (WING SIDE) -CORROSION REPAIR. REPAIR CLASSIFIED AS MINOR PER GMM 6-2-100.

Part: HINGE BRACKET — CORRODED (RT WING TE FLAP) · corrosion level 2 · airframe 83,314 hrs · 19,387 cycles

RIGHT WING - WING SIDE OUTBOARD FLAP OUTBOARD HINGE LOWER MOUNT INBOARD HOLE BORE FOUND CORROSION. CORROSION AT RIGHT WING - WING SIDE OUTBOARD FLAP OUTBOARD HINGE LOWER MOUNT INBOARD HOLE BORE (#3 HOLE) REWORKED AND FOUND EXCEED LIMIT AS PER MD-11 CMM 57- 44-09. SHOULDER BUSHING FABRICATED BY MACHINING AND INSTALLED AS PER MD-11 CMM 57- 44-09 AND E.A. #: 1-5750-T0351908 PART 1 STEP 1. TITLE: WINGS- FLIGHT SURFACES -EO 1-5750- 7-5002- RH WING- OUTBD FLAP OUTBD HINGE ASSY (WING SIDE) -CORROSION REPAIR. REPAIR CLASSIFIED AS MINOR PER GMM 6-2-100.

Part: HINGE BRACKET — CORRODED (RT WING TE FLAP) · corrosion level 2 · airframe 83,314 hrs · 19,387 cycles

RIGHT WING - WING SIDE OUTBOARD FLAP OUTBOARD HINGE LOWER MOUNT OUTBOARD HOLE BORE FOUND CORROSION. CORROSION AT RIGHT WING - WING SIDE OUTBOARD FLAP OUTBOARD HINGE LOWER MOUNT OUTBOARD HOLE BORE (#3 HOLE) REWORKED AND FOUND EXCEED LIMIT AS PER MD-11 CMM 57-44-09. SHOULDER BUSHING FABRICATED BY MACHINING AND INSTALLED AS PER MD-11 CMM 57-44-09 AND E.A. #: 1-5750-T0351908 PART 1 STEP 1. TITLE: WINGS- FLIGHT SURFACES -EO 1- 5750-7-5002- RH WING- OUTBD FLAP OUTBD HINGE ASSY (WING SIDE) -CORROSION REPAIR. REPAIR CLASSIFIED AS MINOR PER GMM 6-2-100.

Part: HINGE BRACKET — CORRODED (RT WING TE FLAP) · corrosion level 2 · airframe 83,314 hrs · 19,387 cycles

RIGHT WING - WING SIDE OUTBOARD FLAP OUTBOARD HINGE INBOARD ACTUATOR LUG HOLE BORE FOUND CORROSION. CORROSION AT RIGHT WING - WING SIDE OUTBOARD FLAP OUTBOARD HINGE INBOARD ACTUATOR LUG HOLE BORE (#8 HOLE) REWORKED AND FOUND EXCEED LIMIT AS PER MD-11 CMM 57-44-09. OVERSIZED BUSHING FABRICATED BY MACHINING AND INSTALLED AS PER MD-11 CMM 57-44-09 AND E.A. #: 1-5750-T0351908 PART 1 STEP 1. TITLE: WINGS- FLIGHT SURFACES -EO 1-5750-7-5002- RH WING- OUTBD FLAP OUTBD HINGE ASSY (WING SIDE) -CORROSION REPAIR. REPAIR CLASSIFIED AS MINOR PER GMM 6-2-100.

Part: HINGE BRACKET — CORRODED (RT WING TE FLAP) · corrosion level 2 · airframe 83,314 hrs · 19,387 cycles

RIGHT WING - WING SIDE OUTBOARD FLAP OUTBOARD HINGE OUTBOARD ACTUATOR LUG HOLE BORE FOUND CORROSION. CORROSION AT RIGHT WING - WING SIDE OUTBOARD FLAP OUTBOARD HINGE OUTBOARD ACTUATOR LUG HOLE BORE (#8 HOLE) REWORKED AND FOUND EXCEED LIMIT AS PER MD-11 CMM 57-44-09. OVERSIZED BUSHING FABRICATED BY MACHINING AND INSTALLED AS PER MD-11 CMM 57-44-09 AND E.A. #: 1-5750-T0351908 PART 1 STEP 1. TITLE: WINGS- FLIGHT SURFACES -EO 1-5750-7-5002- RH WING- OUTBD FLAP OUTBD HINGE ASSY (WING SIDE) -CORROSION REPAIR. REPAIR CLASSIFIED AS MINOR PER GMM 6-2-100.

Part: DOUBLER — CRACKED (RT WING LE) · airframe 83,314 hrs · 19,387 cycles

RIGHT HAND WING FIXED LEADING EDGE AT STATION XOS 580 BEADED DOUBLER FOUND WITH CRACK RIGHT HAND WING FIXED LEADIING EDGE CRACKED BEADED DOUBLER AT STATION XOS 580 CARRIED OUT REPAIR AS PER SRM 57-40-02-2R FIGURE 203 REPAIR 15. REPAIR CLASSIFIED AS MAJOR AS GMM 6-2-100.

Part: DOUBLER — CRACKED (RT WING) · airframe 83,314 hrs · 19,387 cycles

RIGHT HAND WING FIXED LEADING EDGE AT STATION XOS 788 BEADED DOUBLER FOUND WITH CRACK RIGHT HAND WING FIXED LEADING EDGE CRACKED BEADED DOUBLER AT STATION XOS 788 CARRIED OUT REPAIR AS PER SRM 57-40-02-2R FIGURE 203 REPAIR 15. REPAIR CLASSIFIED AS MAJOR PER GMM 6-2-100.

Part: DOUBLER — CRACKED (RT WING LE) · airframe 83,314 hrs · 19,387 cycles

RIGHT HAND WING FIXED LEADING EDGE AT STATION XOS 664 BEADED DOUBLER FOUND WITH CRACK RIGHT HAND WING FIXED LEADING EDGE CRACKED BEADED DOUBLER AT STATION XOS 664 CARRIED OUT REPAIR AS PER SRM 57-40-02-2R FIGURE 203 REPAIR 15. REPAIR CLASSIFIED AS MAJOR PER GMM 6-2-100.

Part: DOUBLER — CRACKED (RT WING LE) · airframe 83,314 hrs · 19,387 cycles

RIGHT HAND WING FIXED LEADING EDGE AT STATION XOS 646 BEADED DOUBLER FOUND WITH CRACK RIGHT HAND WING FIXED LEADING EDGE CRACKED BEADED DOUBLER AT STATION XOS 646 CARRIED OUT REPAIR AS PER SRM 57-40-02-2R FIGURE 203 REPAIR 15 . REPAIR CLASSIFIED AS MAJOR PER GMM 6-2-100.

Part: SKIN — CRACKED (RT WING) · airframe 83,314 hrs · 19,387 cycles

01 EACH FASTENER HOLES # 9 FOUND CRACK INDICATION DURING OPEN - HOLE HFEC INSPECTION AT RIGHT HAND WING LOWER SKIN ACCESS DOOR CUTOUT BETWEEN STATION XORS=690 AND STATION XORS=700. RIGHT HAND WING LOWER SKIN ACCESS DOOR CUTOUT BETWEEN STATION XORS = 690 AND STATION XORS = 700 HOLE # 9 CARRIED OUT REPAIR AS PER SRM 57-20-02-2R FIGURE 201 REPAIR 5. REPAIR CLASSIFIED AS MAJOR PER GMM 6-2-100. REPAIR CLASSIFIED AS CATEGORY B , REQUIRES INITIAL INSPECTION AT 2000 FLIGHT CYCLES WITH REPETITIVE INSPECTIONS AT EVERY 2000 FLIGHT CYCLES AS PER SRM 57-20-02-2R TABLE 201 FIGURE 202 / REPAIR 5. METHOD : HFEC INSPECTION .

Part: DOUBLER — CRACKED (RT WING) · airframe 83,314 hrs · 19,387 cycles

RIGHT HAND WING FIXED LEADING EDGE AT STATION XOS 667.6 RIB DOUBLER FOUND WITH CRACK RIGHT HAND WING FIXED LEADIING EDGE CRACKED RIB DOUBLER AT STATION XOS 667.6 REMOVED AS PER SRM 51-33-01-0G . FABRICATE RIB DOUBLER AS PER DOUGLAS DRAWING # ARB 3954 REV K . FABRICATED RIB DOUBLER INSTALLED AS PER SRM 51-33-01-0G . REPAIR CLASSFIED AS MAJOR PER GMM 6-2-100.

Part: DOUBLER — CRACKED (RT WING LE) · airframe 83,314 hrs · 19,387 cycles

RIGHT HAND WING FIXED LEADING EDGE AT STATION XOS 737 BEADED DOUBLER FOUND WITH CRACK RIGHT HAND WING FIXED LEADING EDGE CRACKED BEADED DOUBLER AT STATION XOS 737 CARRIED OUT REPAIR AS PER SRM 57-40-02-2R FIGURE 203 REPAIR 15. REPAIR CLASSIFIED AS MAJOR PER GMM 6-2-100.

Part: FRAME — DAMAGED (BS 535) · airframe 83,314 hrs · 19,387 cycles

CABIN LEFT HAND FRAME AT YOKE AREA STATION 535 LONGERON 24 LEFT FOUND DAMAGED ON EXISTING REPAIR . CABIN LEFT HAND FRAME AT YOKE AREA STATION 535 LONGERON 24 LEFT , DAMAGE ON EXISTING REPAIR FOUND BADLY CHAFFED AND EXCEED LIMIT AS PER SRM 53-00-00-2R FIGURE 205 ALLOWABLE DAMAGE . DAMAGED EXISTING REPAIR REMOVED AS PER SRM 51-33-01-0G AND REPAIRED AS PER SRM 53-20-07-2R FIGURE 201 REPAIR 1 . REPAIR CLASSIFIED AS MAJOR PER GMM 6-2-100 .

Part: HINGE BRACKET — CORRODED (LT WING TE FLAP) · corrosion level 2 · airframe 83,314 hrs · 19,387 cycles

LEFT WING - WING SIDE OUTBOARD FLAP OUTBOARD HINGE PIVOT HOLE BORE FOUND CORROSION. CORROSION AT LEFT WING - WING SIDE OUTBOARD FLAP OUTBOARD HINGE PIVOT HOLE BORE (#4 HOLE) REWORKED AND FOUND EXCEED LIMIT AS PER MD-11 CMM 57-44-09. OVERSIZED BUSHING FABRICATED BY MACHINING AND INSTALLED AS PER MD-11 CMM 57-44-09 AND E.A. #: 1- 5750-T0351790 PART 1 STEP 1B AND STEP 1. TITLE: WINGS- FLIGHT SURFACES -EO 1-5750-7- 5002- LH WING- OUTBD FLAP OUTBD HINGE (WING SIDE) -CORROSION REPAIR. REPAIR CLASSIFIED AS MINOR PER GMM 6-2-100.

Part: HINGE BRACKET — CORRODED (LT WING TE FLAP) · corrosion level 2 · airframe 83,314 hrs · 19,387 cycles

LEFT WING - WING SIDE OUTBOARD FLAP OUTBOARD HINGE LOWER MOUNT OUTBOARD HOLE BORE FOUND CORROSION. CORROSION AT LEFT WING - WING SIDE OUTBOARD FLAP OUTBOARD HINGE LOWER MOUNT OUTBOARD HOLE BORE (#3 HOLE) REWORKED AND FOUND EXCEED LIMIT AS PER MD-11 CMM 57-44-09. SHOULDER BUSHING FABRICATED BY MACHINING AND INSTALLED AS PER MD-11 CMM 57-44-09 AND E.A. #: 1-5750-T0351790 PART 1 STEP 1A AND STEP 1. TITLE: WINGS- FLIGHT SURFACES -EO 1-5750-7-5002- LH WING- OUTBD FLAP OUTBD HINGE (WING SIDE) -CORROSION REPAIR. REPAIR CLASSIFIED AS MINOR PER GMM 6-2-100.

Part: HINGE BRACKET — CORRODED (RT WING TE FLAP) · corrosion level 2 · airframe 83,314 hrs · 19,387 cycles

RIGHT WING - WING SIDE OUTBOARD FLAP INBOARD HINGE OUTBOARD ACTUATOR LUG HOLE BORE FOUND CORROSION. CORROSION AT RIGHT WING - WING SIDE OUTBOARD FLAP INBOARD HINGE OUTBOARD ACTUATOR LUG HOLE BORE (#8 HOLE) REWORKED AND FOUND EXCEED LIMIT AS PER MD-11 CMM 57-44-08. OVERSIZED BUSHING FABRICATED BY MACHINING AND INSTALLED AS PER MD-11 CMM 57-44-08 AND E.A. #: 1-5750-T0351822 PART 1 STEP 1C AND STEP 1. TITLE: WINGS- FLIGHT SURFACES -EO 1-5750-7-5002- RH WING- OUTBD FLAP INBD HINGE (WING SIDE) -CORROSION REPAIR. REPAIR CLASSIFIED AS MINOR PER GMM 6-2-100.

Part: SEAT TRACK — CORRODED (BS 1281-1301) · corrosion level 2 · airframe 83,314 hrs · 19,387 cycles

CABIN - SEAT TRACK AT STATION 1281 TO STATION 1301 X = - 8.5 FOUND CORROSION . CABIN - AT SEAT TRACK STATION 1281 TO STATION 1301 X = - 8.5 , CORROSION REMOVED AND FOUND TO EXCEED LIMIT AS PER SRM 53-00-52-1A FIGURE 101 ALLOWABLE DAMAGE 1 . CORRODED SEAT TRACK REPAIRED BY SECTIONAL SEAT TRACK REPLACEMENT FROM STATION 1269 TO STATION 1371 X = - 8.5 AS PER SRM 53-00-52-2R FIGURE 201 REPAIR 1 . REPAIR CLASSIFIED AS MAJOR PER GMM 6-2-100 .

Part: SEAT TRACK — CORRODED (BS 1439-1443) · corrosion level 2 · airframe 83,314 hrs · 19,387 cycles

CABIN - SEAT TRACK AT STATION 1439 TO STATION 1443 X = - 8.5 FOUND CORROSION . CABIN - AT SEAT TRACK STATION 1439 TO STATION 1443 X = - 8.5 , CORROSION REMOVED AND FOUND TO EXCEED LIMIT AS PER SRM 53-00-52-1A FIGURE 101 ALLOWABLE DAMAGE 1 . CORRODED SEAT TRACK REPAIRED BY SECTIONAL SEAT TRACK REPLACEMENT FROM STATION 1431 TO STATION 1471 X = - 8.5 , AS PER SRM 53-00-52-2R FIGURE 201 REPAIR 1 . REPAIR CLASSIFIED AS MAJOR PER GMM 6-2-100 .

Part: HINGE BRACKET — CORRODED (RT WING TE FLAP) · corrosion level 2 · airframe 83,314 hrs · 19,387 cycles

RIGHT WING - WING SIDE OUTBOARD FLAP INBOARD HINGE LOWER MOUNT INBOARD HOLE BORE FOUND CORROSION. CORROSION AT RIGHT WING - WING SIDE OUTBOARD FLAP INBOARD HINGE LOWER MOUNT INBOARD HOLE BORE (#7 HOLE) REWORKED AND FOUND EXCEED LIMIT AS PER MD-11 CMM 57- 44-08. SHOULDER BUSHING FABRICATED BY MACHINING AS PER E.A. #: 1-5750-T0351822 PART 1 STEP 1B AND INSTALLED AS PER MD-11 CMM 57-44-08 AND E.A. #: 1-5750-T0351822 PART 1 STEP 1. TITLE: WINGS- FLIGHT SURFACES -EO 1-5750-7-5002- RH WING- OUTBD FLAP INBD HINGE (WING SIDE) -CORROSION REPAIR. REPAIR CLASSIFIED AS MINOR PER GMM 6-2-100.

Part: SEAT TRACK — CORRODED (BS 1281-1301) · corrosion level 2 · airframe 83,314 hrs · 19,387 cycles

CABIN - SEAT TRACK AT STATION 1281 TO STATION 1301 X = 8.5 FOUND CORROSION . CABIN - AT SEAT TRACK STATION 1281 TO STATION1301 X = 8.5 , CORROSION REMOVED AND FOUND TO EXCEED LIMIT AS PER SRM 53-00-52-1A FIGURE 101 ALLOWABLE DAMAGE 1 . CORRODED SEAT TRACK REPAIRED BY SECTIONAL SEAT TRACK REPLACEMENT FROM STATION 1269 TO STATION 1311 X = 8.5 AS PER SRM 53-00-52-2R FIGURE 201 REPAIR 1 . REPAIR CLASSIFIED AS MAJOR PER GMM 6-2-100 .

Part: TRUNNION — CRACKED (NLG) · airframe 83,314 hrs · 19,387 cycles

NOSE LANDING GEAR RIGHT HAND TRUNNION FITTING FOUND CRACK AT STATION 595. NOSE LANDING GEAR RIGHT HAND TRUNNION CRACKED FITTING REPAIRED AS PER MD Ï¿½ 11 SRM 53-10-14-2R REPAIR 2 FIGURE 202. REPAIR CLASSIFIED AS MAJOR PER GMM 6-2-100. INITIAL INSPECTION TO BE CARRIED OUT AFTER 1500 FLIGHT CYCLE AND REPETITIVE INSPECTION TO BE CARRIED OUT EVERY 1500 FLIGHT CYCLE BY HIGH FREQUENCY EDDY CURRENT OR LIQUID PENETRANT INSPECTION PER MD Ï¿½ 11 SRM 53-10-14-2R TABLE 201 FIGURE 202 REPAIR 2.

Part: HINGE BRACKET — CORRODED (LT WING TE FLAP) · corrosion level 2 · airframe 83,314 hrs · 19,387 cycles

LEFT WING - WING SIDE OUTBOARD FLAP OUTBOARD HINGE INBOARD ACTUATOR LUG HOLE BORE FOUND CORROSION. CORROSION AT LEFT WING - WING SIDE OUTBOARD FLAP OUTBOARD HINGE INBOARD ACTUATOR LUG HOLE (#8 HOLE) REWORKED AND FOUND EXCEED LIMIT AS PER MD-11 CMM 57- 44-09. OVERSIZED BUSHING FABRICATED BY MACHINING AND INSTALLED AS PER MD-11 CMM 57- 44-09 AND E.A. #: 1-5750-T0351790 PART 1 STEP 1C AND STEP 1. TITLE: WINGS- FLIGHT SURFACES -EO 1-5750-7-5002- LH WING- OUTBD FLAP OUTBD HINGE (WING SIDE) -CORROSION REPAIR. REPAIR CLASSIFIED AS MINOR PER GMM 6-2-100.

Part: HINGE BRACKET — CORRODED (RT WING TE FLAP) · corrosion level 2 · airframe 83,314 hrs · 19,387 cycles

RIGHT WING - WING SIDE OUTBOARD FLAP INBOARD HINGE LOWER MOUNT OUTBOARD HOLE BORE FOUND CORROSION. CORROSION AT RIGHT WING - WING SIDE OUTBOARD FLAP INBOARD HINGE LOWER MOUNT OUTBOARD HOLE BORE (#7 HOLE) REWORKED AND FOUND EXCEED LIMIT AS PER MD-11 CMM 57-44-08. SHOULDER BUSHING FABRICATED BY MACHINING AS PER E.A. #: 1-5750-T0351822 PART 1 STEP 1B AND INSTALLED AS PER MD-11 CMM 57-44-08 AND E.A. #: 1-5750-T0351822 PART 1 STEP 1. TITLE: WINGS- FLIGHT SURFACES -EO 1-5750-7-5002- RH WING- OUTBD FLAP INBD HINGE (WING SIDE) -CORROSION REPAIR. REPAIR CLASSIFIED AS MINOR PER GMM 6-2-100.

Part: TRUNNION — CRACKED (NLG) · airframe 83,314 hrs · 19,387 cycles

NOSE LANDING GEAR LEFT HAND TRUNNION FITTING FOUND CRACK AT STATION 595. NOSE LANDING GEAR LEFT HAND TRUNNION CRACKED FITTING REPAIRED AS PER MD Ï¿½ 11 SRM 53-10-14-2R REPAIR 2 FIGURE 202. REPAIR CLASSIFIED AS MAJOR PER GMM 6-2-100. INITIAL INSPECTION TO BE CARRIED OUT AFTER 1500 FLIGHT CYCLE AND REPETITIVE INSPECTION TO BE CARRIED OUT EVERY 1500 FLIGHT CYCLE BY HIGH FREQUENCY EDDY CURRENT OR LIQUID PENETRANT INSPECTION PER MD Ï¿½ 11 SRM 53-10-14-2R TABLE 201 FIGURE 202 REPAIR 2.

Part: SEAT TRACK — CORRODED (BS 1321-1343) · corrosion level 2 · airframe 83,314 hrs · 19,387 cycles

CABIN - SEAT TRACK AT STATION 1321 TO STATION 1343 X = - 8.5 FOUND CORROSION . CABIN - SEAT TRACK AT STATION 1321 TO STATION 1343 X = - 8.5 , CORROSION REMOVED AND FOUND TO EXCEED LIMIT AS PER SRM 53-00-52-1A FIGURE 101 ALLOWABLE DAMAGE 1 . CORRODED SEAT TRACK REPAIRED BY SECTIONAL SEAT TRACK REPLACEMENT FROM STATION 1269 TO STATION 1371 X = - 8.5 AS PER SRM 53-00-52-2R FIGURE 201 REPAIR 1 . REFER TO SNRM N00776 FOR WORK DETAILS . REPAIR CLASSIFIED AS MAJOR PER GMM 6-2-100 .

Part: HINGE BRACKET — CORRODED (LT WING TE FLAP) · corrosion level 2 · airframe 83,314 hrs · 19,387 cycles

LEFT WING - WING SIDE OUTBOARD FLAP OUTBOARD HINGE LOWER MOUNT INBOARD HOLE BORE FOUND CORROSION. CORROSION AT LEFT WING - WING SIDE OUTBOARD FLAP OUTBOARD HINGE LOWER MOUNT INBOARD HOLE BORE (#3 HOLE) REWORKED AND FOUND EXCEED LIMIT AS PER MD-11 CMM 57- 44-09. SHOULDER BUSHING FABRICATED BY MACHINING AND INSTALLED AS PER MD-11 CMM 57- 44-09 AND E.A. #: 1-5750-T0351790 PART 1 STEP 1A AND STEP 1. TITLE: WINGS- FLIGHT SURFACES -EO 1-5750-7-5002- LH WING- OUTBD FLAP OUTBD HINGE (WING SIDE) -CORROSION REPAIR. REPAIR CLASSIFIED AS MINOR PER GMM 6-2-100.

Part: SKIN — DAMAGED (LT WING) · airframe 83,314 hrs · 19,387 cycles

LEFT HAND WING FIXED LEADING EDGE SKIN TELESCOPIC DUCT CUT OUT AT STATION XOS 465 TO 470 REPAIR DOUBLER WITH DAMAGED. LEFT HAND WING FIXED LEADING EDGE SKIN TELESCOPIC DUCT CUT OUT AT STATION XOS 465 TO 470 CARRIED OUT REPAIR AS PER SRM 57-40-01-2R FIGURE 201 REPAIR 10 . REPAIR CLASSIFIED AS MAJOR PER GMM 6-2-100 .

Part: HINGE BRACKET — CORRODED (RT WING TE FLAP) · corrosion level 2 · airframe 83,314 hrs · 19,387 cycles

RIGHT WING - WING SIDE OUTBOARD FLAP INBOARD HINGE PIVOT HOLE BORE FOUND CORROSION. CORROSION AT RIGHT WING - WING SIDE OUTBOARD FLAP INBOARD HINGE PIVOT HOLE BORE (#4 HOLE) REWORKED AND FOUND EXCEED LIMIT AS PER MD-11 CMM 57-44-08. OVERSIZED BUSHING FABRICATED BY MACHINING AND INSTALLED AS PER MD-11 CMM 57-44-08 AND E.A. #: 1- 5750-T0351822 PART 1 STEP 1A AND STEP 1. TITLE: WINGS- FLIGHT SURFACES -EO 1-5750-7- 5002- RH WING- OUTBD FLAP INBD HINGE (WING SIDE) -CORROSION REPAIR. REPAIR CLASSIFIED AS MINOR PER GMM 6-2-100.

Part: SEAT TRACK — CRACKED (BS 1242) · airframe 83,314 hrs · 19,387 cycles

CABIN - SEAT TRACK AT STATION 1242 X = - 27.5 FOUND CROWN CRACK OFF . CABIN - CROWN CRACKED OFF SEAT TRACK AT STATION 1242 X = - 27.5 , REPAIRED BY SECTIONAL SEAT TRACK REPLACEMENT FROM STATION 1229 TO STATION 1269 X = - 27.5 AS PER SRM 53-00-52-2R FIGURE 201 REPAIR 1 . REPAIR CLASSIFIED AS MAJOR PER GMM 6-2-100 .

Part: HINGE BRACKET — CORRODED (RT WING TE FLAP) · corrosion level 2 · airframe 83,314 hrs · 19,387 cycles

RIGHT WING - WING SIDE OUTBOARD FLAP INBOARD HINGE INBOARD ACTUATOR LUG HOLE BORE FOUND CORROSION. CORROSION AT RIGHT WING - WING SIDE OUTBOARD FLAP INBOARD HINGE INBOARD ACTUATOR LUG HOLE BORE (#8 HOLE) REWORKED AND FOUND EXCEED LIMIT AS PER MD-11 CMM 57-44-08. OVERSIZED BUSHING FABRICATED BY MACHINING AND INSTALLED AS PER MD-11 CMM 57-44-08 AND E.A. #: 1-5750-T0351822 PART 1 STEP 1C AND STEP 1. TITLE: WINGS- FLIGHT SURFACES -EO 1-5750-7-5002- RH WING- OUTBD FLAP INBD HINGE (WING SIDE) -CORROSION REPAIR. REPAIR CLASSIFIED AS MINOR PER GMM 6-2-100.

Part: DOUBLER — CRACKED (LT WING LE) · airframe 83,314 hrs · 19,387 cycles

LEFT HAND WING FIXED LEADING EDGE AT STATION XOS 601 BEADED DOUBLER FOUND WITH CRACK LEFT HAND WING FIXED LEADING EDGE CRACKED BEADED DOUBLER AT STATION XOS 601 CARRIED OUT REPAIR AS PER SRM 57-40-02-2R FIGURE 203 REPAIR 15 . REPAIR CLASSIFIED AS MAJOR PER GMM 6-2-100.

Part: DOUBLER — CRACKED (LT WING LE) · airframe 83,314 hrs · 19,387 cycles

LEFT HAND WING FIXED LEADING EDGE AT STATION XOS 668 BEADED DOUBLER FOUND WITH CRACK LEFT HAND WING FIXED LEADING EDGE CRACKED BEADED DOUBLER AT STATION XOS 668 CARRIED OUT REPAIR AS PER SRM 57-40-02-2R FIGURE 203 REPAIR 15 . REPAIR CLASSIFIED AS MAJOR PER GMM 6-2-100.

Part: DOUBLER — CRACKED (LT WING LE) · airframe 83,314 hrs · 19,387 cycles

LEFT HAND WING FIXED LEADING EDGE AT STATION XOS 789.6 RIB DOUBLER FOUND WITH CRACK LEFT HAND WING FIXED LEADING EDGE CRACKED RIB DOUBLER AT STATION XOS 789.6 REMOVED AS PER SRM 51-33-01-0G . FABRICATE RIB DOUBLER AS PER DOUGLAS DRAWING # ARB 3954 REV K . FABRICATED RIB DOUBLER INSTALLED AS PER SRM 51-33-01-0G . REPAIR CLASSIFIED AS MAJOR PER GMM 6-2-100.

Part: RIB — CRACKED (LT WING SLAT) · airframe 83,314 hrs · 19,387 cycles

LEFT WING - NUMBER 1 LEADING EDGE SLAT CRUISE PERFORMANCE FILLET RIB FOUND CRACK AT STATION XIS 150.74 LEFT WING - NO 1 LEADING EDGE SLAT CRUISE PERFORMANCE FILLET CRACKED RIB AT STATION XIS 150.74 CARRIED OUT REPAIR AS PER SRM 57-40-71-2R FIGURE 201 REPAIR 1. REPAIR CLASSIFIED AS MAJOR PER GMM 6-2-100.

Part: DOUBLER — CRACKED (LT WING LE) · airframe 83,314 hrs · 19,387 cycles

LEFT HAND WING FIXED LEADING EDGE AT STATION XOS 543 BEADED DOUBLER FOUND CRACKED LEFT HAND WING FIXED LEADING EDGE CRACKED BEADED DOUBLER AT STATION XOS 543 CARRIED OUT REPAIR AS PER SRM 57-40-02-2R FIGURE 203 REPAIR 15.REPAIR CLASSIFIED AS MAJOR PER GMM 6-2-100.

Part: RIB — CRACKED (RT WING SLAT) · airframe 83,314 hrs · 19,387 cycles

RIGHT WING - NUMBER 1 LEADING EDGE SLAT CRUISE PERFORMANCE FILLET RIB FOUND CRACK AT STATION XIS 150.74 RIGHT WING - NO 1 LEADING EDGE SLAT CRUISE PERFORMANCE FILLET CRACKED RIB AT STATION XIS 150.74 CARRIED OUT REPAIR AS PER SRM 57-40-71-2R FIGURE 201 REPAIR 1. REPAIR CLASSIFIED AS MAJOR PER GMM 6-2-100.

Part: BRACKET — CORRODED (LT WING TE FLAP) · corrosion level 2 · airframe 83,314 hrs · 19,387 cycles

LEFT WING - WING SIDE OUTBOARD FLAP INBOARD HINGE PIVOT HOLE BORE FOUND CORROSION. CORROSION AT LEFT WING - WING SIDE OUTBOARD FLAP INBOARD HINGE PIVOT HOLE BORE (#4 HOLE) REWORKED AND FOUND EXCEED LIMIT AS PER MD-11 CMM 57-44-08. OVERSIZED BUSHING FABRICATED BY MACHINING AND INSTALLED AS PER MD-11 CMM 57-44-08 AND E.A. #: 1- 5750-T0351773 PART 1 STEP 3A AND STEP 3. TITLE: WINGS- FLIGHT SURFACES -EO 1-5750-7- 5002- LH WING- OUTBD FLAP, INBD FWD HINGE (WING SIDE) -CORROSION REPAIR. REPAIR CLASSIFIED AS MINOR PER GMM 6-2-100.

Part: BRACKET — CORRODED (LT WING TE FLAP) · corrosion level 2 · airframe 83,314 hrs · 19,387 cycles

LEFT WING - WING SIDE OUTBOARD FLAP INBOARD HINGE LOWER MOUNT INBOARD HOLE BORE FOUND CORROSION. CORROSION AT LEFT WING - WING SIDE OUTBOARD FLAP INBOARD HINGE LOWER MOUNT INBOARD HOLE BORE (#7 HOLE) REWORKED AND FOUND EXCEED LIMIT AS PER MD-11 CMM 57- 44-08. SHOULDER BUSHING FABRICATED BY MACHINING AND INSTALLED AS PER MD-11 CMM 57- 44-08 AND E.A. #: 1-5750-T0351773 PART 1 STEP 3B AND STEP 3. TITLE: WINGS- FLIGHT SURFACES -EO 1-5750-7-5002- LH WING- OUTBD FLAP, INBD FWD HINGE (WING SIDE) - CORROSION REPAIR. REPAIR CLASSIFIED AS MINOR PER GMM 6-2-100.

Part: HINGE BRACKET — CORRODED (LT WING TE FLAP) · corrosion level 2 · airframe 83,314 hrs · 19,387 cycles

LEFT WING - WING SIDE OUTBOARD FLAP INBOARD HINGE OUTBOARD ACTUATOR LUG HOLE BORE FOUND CORROSION. CORROSION AT LEFT WING - WING SIDE OUTBOARD FLAP INBOARD HINGE OUTBOARD ACTUATOR LUG HOLE BORE (#8 HOLE) REWORKED AND FOUND EXCEED LIMIT AS PER MD-11 CMM 57-44-08. OVERSIZED BUSHING FABRICATED BY MACHINING AND INSTALLED AS PER MD-11 CMM 57-44-08 AND E.A. #: 1-5750-T0351773 PART 1 STEP 3C AND STEP 3. TITLE: WINGS- FLIGHT SURFACES -EO 1-5750-7-5002- LH WING- OUTBD FLAP, INBD FWD HINGE (WING SIDE) - CORROSION REPAIR. REPAIR CLASSIFIED AS MINOR PER GMM 6-2-100.

Part: BRACKET — CORRODED (LT WING TE FLAP) · corrosion level 2 · airframe 83,314 hrs · 19,387 cycles

LEFT WING - WING SIDE OUTBOARD FLAP INBOARD HINGE LOWER MOUNT OUTBOARD HOLE BORE FOUND CORROSION. CORROSION AT LEFT WING - WING SIDE OUTBOARD FLAP INBOARD HINGE LOWER MOUNT OUTBOARD HOLE BORE (#7 HOLE) REWORKED AND FOUND EXCEED LIMIT AS PER MD-11 CMM 57-44-08. SHOULDER BUSHING FABRICATED BY MACHINING AND INSTALLED AS PER MD-11 CMM 57-44-08 AND E.A. #: 1-5750-T0351773 PART 1 STEP 3B AND STEP 3. TITLE: WINGS- FLIGHT SURFACES -EO 1-5750-7-5002- LH WING- OUTBD FLAP, INBD FWD HINGE (WING SIDE) - CORROSION REPAIR. REPAIR CLASSIFIED AS MINOR PER GMM 6-2-100.

Part: HINGE BRACKET — CORRODED (LT WING TE FLAP) · corrosion level 2 · airframe 83,314 hrs · 19,387 cycles

LEFT WING - WING SIDE OUTBOARD FLAP INBOARD HINGE LOWER MOUNT OUTBOARD HOLE SURFACE FOUND CORROSION. CORROSION AT LEFT WING - WING SIDE OUTBOARD FLAP INBOARD HINGE LOWER MOUNT OUTBOARD HOLE SURFACE REWORKED AND FOUND EXCEED LIMIT AS PER MD-11 CMM 57-44- 08. REPAIR SHIM FABRICATED AND INSTALLED AS PER MD-11 CMM 57-44-08 AND E.A. #: 1-5750- T0351773 PART 1 STEP 3. TITLE: WINGS- FLIGHT SURFACES -EO 1-5750-7-5002- LH WING- OUTBD FLAP, INBD FWD HINGE (WING SIDE) -CORROSION REPAIR. REPAIR CLASSIFIED AS MINOR PER GMM 6-2-100.

Part: HINGE BRACKET — CORRODED (LT WING TE FLAP) · corrosion level 2 · airframe 83,314 hrs · 19,387 cycles

LEFT WING - WING SIDE OUTBOARD FLAP INBOARD HINGE INBOARD ACTUATOR LUG HOLE BORE FOUND CORROSION. CORROSION AT LEFT WING - WING SIDE OUTBOARD FLAP INBOARD HINGE INBOARD ACTUATOR LUG HOLE BORE (#8 HOLE) REWORKED AND FOUND EXCEED LIMIT AS PER MD-11 CMM 57-44- 08. OVERSIZED BUSHING FABRICATED BY MACHINING AND INSTALLED AS PER MD-11 CMM 57-44- 08 AND E.A. #: 1-5750-T0351773 PART 1 STEP 3C AND STEP 3. TITLE: WINGS- FLIGHT SURFACES - EO 1-5750-7-5002- LH WING- OUTBD FLAP, INBD FWD HINGE (WING SIDE) -CORROSION REPAIR. REPAIR CLASSIFIED AS MINOR PER GMM 6-2-100.

Part: ACCESS PANEL — CORRODED (ZONE 100) · airframe 82,462 hrs · 19,157 cycles

INTERNAL CORROSION ON DRAIN ACCESS PANEL DOUBLER R/R DOUBLE AND REPAIRED SHEAR TIE REF J.PF. (SEE NR0030). REMOVED AND REPLACED CRACKED INTERCOATAL REF NR00029 JPF. 475227 09-06-20119.

Part: ACCESS PANEL — CORRODED (NOT REPORTED) · airframe 82,462 hrs · 19,157 cycles

INTERNAL CORROSION ON DRAIN ACCESS PANEL DOUBLER

Part: BULKHEAD WEB — CRACKED (BS 1372) · airframe 81,676 hrs · 18,910 cycles

RIGHT MAIN LANDING GEAR WHEEL WELL FORWARD BULKHEAD REIN COMPLY WITH E..A. 1-5310-T0346267 REV NO. POS. P1 CRACK IN AFT RH WEB OF OVERWING AUX TANK. COMPLY WITH E..A. 1-5310-T0346267 REV NO. POS. P1 REMOVED DAMAGE AND INSTALLED DOUBLER

Part: LINE — LEAKING (HYD SYSTEM) · airframe 81,425 hrs · 18,837 cycles

DEPARTED WITH #1 HYD SYSTEM 6.0. 1 40 MIN INTO FLIGHT #1 HYD SYSTEM DECREASED 2.8. HYD SYSTEM 2 3 REMAINING STABLE AT #2/6.5. #3/9.7. HYD #1 OFF ILLUMINATED WHEN SYSTEN REACHED 2.5. DECLARED EMERGENCYUNEVENTFUL LANDING DESTINATION KOAK. BLOCK IN HYDRAULICS #1 2.0. #2 6.6 , #3 8.0. ON APPROACH. #1 LOWEST WAS 1.4. FOUND HYD LINE P/N ALK7602-503 LEAKING IN TAIL TANK VENT BOX. REPLACE HYDRAULIC LINE. LEAK CHECK GOOD.

Part: HYDRAULIC LINE — FAILED (HYDRAULIC SYS) · airframe 81,107 hrs · 18,743 cycles

PDIS 576 29-02 7773 13JAN19 TPE FACT U "HYD 1 FAIL" ENROUTE. 0.2 GALLONG RMG. FOUND THE PIN HOLE OF PIPE ASSY ( P/N: ARK7550-779) REF IPC 27-82-20-01. THAT AREA ARE GOOD FOR PERMANENT REPAIR. VISUAL INSPECT AND FOUND HYD FLUID ON LT INBD SLAT AREA. WIIL OPEN PANEL FOR FURTHER INSP. R&R ENGINE AND SYSTEM MANIFOLD FILTERS PER AMM 29-12-41-2, NEED A LEAK CHECK. P/N 7554849 X 6EA. REASON CODE : PREMATURE REMOVAL/INSTALLATION OFF MPN: 3031863-001 POS: 102 SRL: MX804902 TAG NBR: 8F7242 ON MPN: 3031863-001 CPN: 2912373 SRL: MX794979 TAG NBR: 4E4439 R/I NR 1 ENGINE RIGHT(LOWER) ENGINE DRIVEN PUMP PER MM 29-11-20-4-1. WAITING FOR ANOTHER ONE EDP TO CONTINUE WORK. PIPE ( P/N: ARK7550-779) REPAIRED BY HYD TEAM WITH SWAGED METHOED AS REF TO AMM20-10-01. LEAK TEST NO LEAK FOUND. PANEL CLOSED AS PER SMP, REASON CODE : PREMATURE REMOVAL/INSTALLATION OFF MPN: 3031863-001 POS: 101 SRL: MX-541731 TAG NBR: 4E7041 ON MPN: 3031863-001 CPN: 2912373 SRL: MX799724 TAG NBR: 804F65 R/I NR 2 ENGINE RIGHT(UPPER) ENGINE DRIVEN PUMP PER AMM 29-11-20-4-1 AND COND CHK NML. PER ENG RUN CHECK LIST. RUN NR 1 ENG. ALL BOTH PUMPS WROKING NORMAL AND NO LEAK NOTED. ENG COWLINGS CLOSED AND LATCHED PER AMM 71-10-00.

Part: SLAT — FAILED (LT WING) · airframe 80,628 hrs · 18,614 cycles

LEFT HAND NR 1 INBOARD SLAT MISSING WHEN ARRIVED AT IND. CREW WAS UNAWARE OF MISSING SLAT. FIRST FOOT AND 1/2 IS MISSING, REST OF SLAT OUTBOARD IS STILL INTACT. LT NR 1 LEADING EDGE SLAT REMOVED AND REPLACED REF AMM 27-80-20-4.

Part: POWER SUPPLY — INOPERATIVE (CABIN) · airframe 80,478 hrs · 18,565 cycles

EMERGENCY LIGHTS WILL NOT TEST. REMOVED AND REPLACED EMERGENCY LIGHTS POWER SUPPLY REF AMM 33-51-01-4. OPS CK GOOD.

Part: LIGHT — INOPERATIVE (CABIN) · airframe 79,764 hrs · 18,343 cycles

ON PREFLIGHT CHECK, FOUND EMERGENCY LIGHT DOES NOT ILLUMINATE DURING EMERGENCY LIGHT TEST AND ALSO WHEN S/W SELECTED ON. IDENTIFIED PARTS EMERG EXIT LIGHTS MPN: 60-4411-5 CPN: 3300197. WHILE TROUBLESHOOTING EMER LIGHTS RAN R-T-S ON MSC, ONCE TEST PASSED OPS CHECKED EMER LIGHTS SYSTEM IAW 33-50-00-5. OPS CHECK GOOD, SUSPECT MSC HAD CAUSE RELAY R2-5700 TO HANG UP.

Part: LIGHT — INOPERATIVE · airframe 79,719 hrs · 18,325 cycles

ON PREFLIGHT CHECK, FOUND EMEGENCY LIGHT DOES NOT ILLUMINATE DURING EMERGENCY LIGHT TEST AND ALSO WHEN S/W SELECTED ON. A/C RELEASED PER MEL.

Part: HOSE — LEAKING (HYD SYSTEM) · airframe 79,221 hrs · 18,175 cycles

LEVEL 1 HYD 3 ELEVATOR OFF ALERT. QUANTITY WAS 4.7. AFTER APPROXIMATELY 5 MINUTES , QUANTITY DROPPED TO 3.9. AT QUANTITY 3.5 THE ELEVATOR OFF ALERT WENT WAY AND LEVEL 1 HYD 3 OFF APPEARED AND QUANTITY STABILIZED. DURING DECENT, WHEN SPOILERS WERE DEPLOYED, QUANTITY BEGAN TO DECREASE. AT 1.6, SLATS AND GEAR WERE BOTH EXTENDED AND THEN LEVEL 2 HAD 3 FAIL ALERT. QUANTITY DROPPED TO 0.8. REMOVED REPLACED DAMAGED HOSE IAW MM 29-11-22-4 AND 20-40-01-2. SERVICED HYD FLUIDE IAW MM 12-13-02-3. RAN #3 ENG, NO LEAK FOUND IAW JRH. ACFT OK FOR SERVICE.

Part: DOUBLER — CRACKED (LT WING) · airframe 78,637 hrs · 18,007 cycles

LEFT WING LEADING EDGE BEADED DOUBLER AT XOS 642 FOUND CRACKED. REPAIRED IAW SRM 57-40-02-2R, FIGURE 203, REPAIR 15. REPAIR CLASSIFIED AS MAJOR IAW GMM 6-2-100.

Part: FRAME — CHAFED (FUSELAGE) · airframe 78,637 hrs · 18,007 cycles

EXISTING REPAIR AT MAIN DECK FRAME STA 535, LONGERON 24L EXISTING REPAIR AT MAIN DECK FRAME STA 535 LONGERON 24L EVALUATED AND FOUND EXTERNAL REPAIR ANGLE CHAFED. MAIN DECK FRAME STA 535 LONGERON 24L CARRIED OUT REPAIR PER SRM 53-20-07-2R FIG 201 REPAIR 1. EO 1-5100-7-5001B6 PT1 TITLE: "STRUCTURES - REPAIR CATALOG-MD11 REPAIR IDENTIFICATION AND TRACKING REQUIREMENTS 14CFR121.707" ACCOMPLISHED. REPAIR CLASSIFIED AS MAJOR PER GMM6-2- 100.

Part: DOUBLER — CRACKED (LT WING) · airframe 78,637 hrs · 18,007 cycles

LEFT WING LEADING EDGE BEADED DOUBLER AT XOS 630, FOUND CRACKED. REPAIRED IAW SRM 57-40-02-2R, FIGURE 203, REPAIR 15. REPAIR CLASSIFIED AS MAJOR IAW GMM 6-2-100.

Part: DOUBLER — CRACKED (LT WING) · airframe 78,637 hrs · 18,007 cycles

LT WING FIXED LEADING EDGE LOWER SURFACE PANEL CUTOUT AT STA XOS 993 FOUND CRACKED. REPAIR CARRIED OUT AT LT WING FIXED LEADING EDGE LOWER SURFACE PANEL CUTOUT AT STA XOS 993 AS PER SRM 57-40-03-2R FIGURE 201 REPAIR 1. REPAIR CLASSIFIED AS MAJOR PER GMM 6-2-100.

Part: DOUBLER — CRACKED (LT WING) · airframe 78,637 hrs · 18,007 cycles

LEFT WING LEADING EDGE BEADED DOUBLER AT XOS 627 FOUND CRACKED. REPAIRED IAW SRM 57-40-02-2R, FIGURE 203, REPAIR 15. REPAIR CLASSIFIED AS MAJOR IAW GMM 6-2-100.

Part: FRAME — DENTED (FUSELAGE) · airframe 78,637 hrs · 18,007 cycles

CABIN MAIN DECK CARGO COMPARTMENT FRAME DENTED AT RT STA 1721, LONGERON 12R. CABIN AT RT STA 1721 LONGERON L-12R, DENTED FRAME REPAIRED PER SRM 53-00-07-2R FIG 201 REPAIR 2. REPAIR CLASSIFIED AS MAJOR PER GMM 6-2-100.

Part: DOUBLER — CRACKED (LT WING) · airframe 78,637 hrs · 18,007 cycles

LEFT WING LEADING EDGE BEADED DOUBLER AT XOS 617, FOUND CRACKED. REPAIRED IAW SRM 57-40-02-2R, FIGURE 203, REPAIR 15. REPAIR CLASSIFIED AS MAJOR IAW GMM 6-2-100.

Part: DOUBLER — CRACKED (RT WING) · airframe 78,637 hrs · 18,007 cycles

RT WING LEADING EDGE CAVITY BEADED DOUBLER AT STA XOS 640 FOUND CRACKED. REPAIR CARRIED OUT AT RT WING LEADING EDGE CAVITY BEADED DOUBLER AT XOS 640 PER SRM 57-40-02-2R FIGURE 203 REPAIR 15. REPAIR CLASSIFIED AS MAJOR PER GMM 6-2-100.

Part: DOUBLER — CRACKED (LT WING) · airframe 78,637 hrs · 18,007 cycles

LEFT WING LEADING EDGE BEADED DOUBLER AT XOS 764, FOUND CRACKED. THE DOUBLER REPAIRED IAW SRM 57-40-02-2R, FIGURE 203, REPAIR 15. REPAIR CLASSIFIED AS MAJOR IAW GMM 6-2-100.

Part: DOUBLER — CRACKED (LT WING) · airframe 78,637 hrs · 18,007 cycles

LT WING LEADING EDGE BEADED DOUBLER AT STA XOS 755 FOUND CRACKED. LT WING LEADING EDGE AT STA XOS 755 CRACKED BEADED DOUBLER REPAIRED AS PER SRM 57-40-02-2R FIGURE 203 REPAIR 15. REPAIR CLASSIFIED AS MAJOR PER GMM 6-2-100.

Part: DOUBLER — CRACKED (LT WING) · airframe 78,637 hrs · 18,007 cycles

LT WING LEADING EDGE BEADED DOUBLER AT STA XOS 612 FOUND CRACKED. REPAIR CARRIED OUT AT LT WING FIXED LEADING EDGE BEADED DOUBLER AT XOS 612 AS PER SRM 57-40-02-2R FIGURE 203 REPAIR 15. REPAIR CLASSIFIED AS MAJOR PER GMM 6-2-100.

Part: DOUBLER — CRACKED (LT WING) · airframe 78,637 hrs · 18,007 cycles

LEFT WING LEADING EDGE BEADED DOUBLER AT XOS 760 FOUND CRACKED. THE DOUBLER REPAIRED IAW SRM 57-40-02-2R, FIGURE 203, REPAIR 15. REPAIR CLASSIFIED AS MAJOR IAW GMM 6-2-100.

Part: BATTERY — INOPERATIVE (L1 DOOR SLIDE) · airframe 77,845 hrs · 17,779 cycles

DURING A PREFLIGHT INSPECTION, FOUND THE L1 DOOR SLIDE REMOTE PRESS TO TEST LIGHT INOPERATIVE. REMOVED AND REPLACED THE BATTERIES IAW AMM 25-61-04-4. OPS CHECKED OK. RETURN TO SERVICE.

Part: LIGHT — INOPERATIVE (CABIN) · airframe 76,518 hrs · 17,371 cycles

ON SERVICE CHECK, FOUND EMERGENCY LIGHT SYSTEM INOPERATIVE.

Part: BATTERY PACK — INOPERATIVE (PRESSURE INDICAT) · airframe 75,742 hrs · 17,118 cycles

L1 DOOR SLIDE REMOTE PRESSURE INDICATOR LIGHT IS NOT WORKING. REPLACED BATTERY ,OPS CHECKED GOOD IAW AMM 25-61-15-5.

Part: LIGHT — MALFUNCTIONED (CABIN) · airframe 75,713 hrs · 17,106 cycles

DURING POST FLIGHT CHECK, FOUND EMERGENCY LIGHTS DO NOT COME ON WHEN SWITCH IS IN ON POSITION. PERFORMED EMERGENCY LIGHT ADJUSTMENT AND TEST IAW MM 33-50-00-5. ALL EMERGENCY LIGHTS WORK NML COULD NOT DUPLICATE PREVIOUS DISCREPENCY. ACFT OK FOR SERVICE.

Part: BATTERY PACK — INOPERATIVE (INDICATOR) · airframe 75,657 hrs · 17,092 cycles

L1 DOOR PRESS TO TEST LIGHT WOULD NOT ILLUMINATE. REPLACED THE BATTERY ,OPS CHECKED GOOD IAW AMM 25-61-15-5. OK FOR SERVICE.

Part: LIGHT — INOPERATIVE (EVAC SLIDE) · airframe 75,524 hrs · 17,056 cycles

DURING POSTFLIGHT FOUND R1 EVAC SLIDE REMOTE PRESS IND INOP. RELEASED FOR SERVICE PER MEL, R1 EVAC SLIDE REMOTE PRESS INDICATOR INOP. RELAMPED R1 DOOR REMOTE PRESS LIGHT REF MM 25-61-04-4. OPS CK GOOD, ACFT OK TO CONTINUE.

Part: INDICATOR — INOPERATIVE (SLIDE PRESSURE) · airframe 75,524 hrs · 17,056 cycles

DURING POSTFLIGHT, FOUND R1 SLIDE REMOTE PRESSURE INDICATOR INOPERATIVE.

Part: LONGERON SPLICE — CRACKED (ZONE 100) · airframe 74,078 hrs · 16,575 cycles

UPON REMOVAL OF CENTRE CARGO COMPT BILGE AREA LONGERON L-48L, LH STA 1531 FOUND UPPER AND LOWER SPLICE ATTAHMENT CRACKED. CENTER CARGO COMPT BILGE AREA BS 1531 LONGERON 48 L CRACKED UPPER / LOWER SPLICES REMOVED & REPLACED WITH NEW FABRICATED SPLICES PER SRM 51-33-01-0G. NEW SPLICES FABRICATED IAW DWG A5A7124 REV 'D'. REPAIR CLASSIFIED AS MAJOR IAW GMM 6-2-100.

Part: SKIN — CORRODED (BS 1541) · airframe 74,078 hrs · 16,575 cycles

CENTER CARGO COMPARTMENT BILGE AREA, BS 1541, LT LONGERON -48L, FOUND CORRODED. REPAIRED IAW SRM 53-00-05-2R FIG 202 REPAIR 1. REPAIR CLASSIFIED AS MAJOR IAW GMM 6-2-100.

Part: FRAME — DAMAGED (BS 535) · airframe 74,078 hrs · 16,575 cycles

MAIN DECK LT FRAME AT STATION 535, LONGERON 24L, FOUND EXISTING REPAIR DAMAGED. REPAIRED IAW SRM 53-20-07-2R FIG 201 REPAIR 1. REPAIR CLASSIFIED AS MAJOR IAW GMM 6-2-100.

Part: SEAT TRACK — CRACKED (BS 635) · airframe 74,078 hrs · 16,575 cycles

SEAT TRACK AT BS 635, LBL 8, FOUND CRACKED. REPAIRED IAW SRM 53-00-52-2R FIG 201 REPAIR 1. REPAIR CLASSIFIED AS MAJOR AS PER GMM 6-2-100.

Part: STRUCTURE — CORRODED (FUSELAGE) · airframe 74,078 hrs · 16,575 cycles

CENTER CARGO COMPARTMENT BILGE AREA, STATION 1771 - 1781, RT LONGERON -46R, FOUND CORROSION. REPAIRED IAW EA 1-5310-T0323394 PT 1. REPAIR CLASSIFIED AS MAJOR IAW GMM 6-2-100.

Part: SEAT TRACK — CRACKED (BS 635-695) · airframe 74,078 hrs · 16,575 cycles

SEAT TRACK BS 635 - 695, RBL 8, FOUND CRACKED AT TWO LOCATIONS. REPAIRED IAW SRM 53-00-52-2R FIG 201 REPAIR 1. REPAIR CLASSIFIED AS MAJOR AS PER GMM 6-2-100.

Part: SEAT TRACK — CRACKED (BS 775) · airframe 74,078 hrs · 16,575 cycles

MAIN DECK FLOOR SEAT TRACK AT BS 775, X= 75.25, FOUND CROWN DAMAGED. REPAIRED IAW SRM 53-00-52-2R FIG 201 REPAIR 1. REPAIR CLASSIFIED AS MAJOR IAW GMM 6-2-100.

Part: FRAME — DENTED (BS 1640) · airframe 74,078 hrs · 16,575 cycles

CABIN MAIN DECK CARGO COMPARTMENT, LT SIDEWALL AT APPROX BS 1640, LONGERON 12, FOUND FRAME DENTED. REPAIRED IAW SRM 53-00-07-2R FIG 201 REPAIR 2. REPAIR CLASSIFIED AS MAJOR IAW GMM 6-2-100.

Part: SEAT TRACK — CRACKED (BS 635-695) · airframe 74,078 hrs · 16,575 cycles

CABIN SEAT TRACK AT BS 635 - 695, RBL 27, FOUND CRACKED AT TWO LOCATIONS. REPAIRED IAW SRM 53-00-52-2R FIG 201 REPAIR 1. REPAIR CLASSIFIED AS MAJOR IAW GMM 6-2-100.

Part: SKIN — CRACKED (FUSELAGE) · airframe 74,078 hrs · 16,575 cycles

CENTER CARGO COMPARTMENT BILGE AREA, LONGERON -45L FOUND CRACKED AT BS 1531. REPAIRED IAW EA 1-5310-T0323458 PT 1. REPAIR CLASSIFIED AS MAJOR IAW GMM 6-2-100.

Part: SKIN — CORRODED (BS 1681) · airframe 74,078 hrs · 16,575 cycles

CENTER CARGO COMPARTMENT BILGE AREA, BS 1681 RT LONGERON 45R, FOUND CORRODED. REPAIRED IAW EA 1-5310-T0323396 PT 1. REPAIR CLASSIFIED AS MAJOR IAW GMM 6-2-100.

Part: LONGERON — CORRODED (L48L) · airframe 74,078 hrs · 16,575 cycles

CENTER CARGO COMPARTMENT BILGE AREA, STATION 5 - 73 LT, LONGERON 48L FOUND. CORROSION. REPAIRED IAW EA 1-5310-T0323433 PT 1. REPAIR CLASSIFIED AS MAJOR IAW GMM 6-2-100.

Part: FORMER — CRACKED (LT WING) · airframe 74,078 hrs · 16,575 cycles

LEFT WING, LE COMPARTMENT, LOWER SUPPORT FORMER AT XOS 559, FOUND CRACKED. R & R IAW SRM 51-31-01-0G. FABRICATED IAW DWG ARB 1162 REV S. THE REPAIR CLASSIFIED AS MAJOR IAW GMM 6-2-100.

Part: DOUBLER — CRACKED (LT WING) · airframe 74,078 hrs · 16,575 cycles

LEFT WING, FIXED LE BEADED DOUBLER AT STATION XOS 640, FOUND CRACKED. 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 74,078 hrs · 16,575 cycles

RIGHT WING, FIXED LE BEADED DOUBLER AT STATION XOS 654, FOUND CRACKED. REPAIRED IAW SRM 57-40-02-2R FIG 203 REPAIR 15. REPAIR CLASSIFIED AS MAJOR IAW GMM 6-2-100.

Part: DOUBLER — CRACKED (RT WING) · airframe 74,078 hrs · 16,575 cycles

RIGHT WING, FIXED LE BEADED DOUBLER AT STATION XOS 730, FOUND CRACKED. REPAIRED IAW SRM 57-40-02-2R FIG 203 REPAIR 15. REPAIR CLASSIFIED AS MAJOR IAW GMM 6-2-100.

Part: WEB — CRACKED (BS 1250-1256) · airframe 74,078 hrs · 16,575 cycles

MAIN DECK R3 DOOR FWD JAMB, LOWER WEB BOX AT BS 1250.75 - 1256.75, LONGERON 26R - 27R FOUND CRACKED. REPAIRED IAW SRM 53-40-15-2R FIG 201 REPAIR 3. REPAIR CLASSIFIED AS MAJOR IAW GMM 6-2-100.

Part: WEB — CRACKED (BS 1305-1315) · airframe 74,078 hrs · 16,575 cycles

MAIN DECK R3 DOOR AFT JAMB, LOWER WEB BOX AT BS 1305.25 - 1315.42, LONGERON 26R - 27R FOUND CRACKED. REPAIRED IAW SRM 53-40-15-2R FIG 201 REPAIR 3. REPAIR CLASSIFIED AS MAJOR IAW GMM 6-2-100.

Part: WEB — CRACKED (BS 1250-1256) · airframe 74,078 hrs · 16,575 cycles

MAIN DECK L3 DOOR FWD JAMB, LOWER WEB BOX AT STATION 1250.75 - 1256.75, LONGERON 26L - 27L, FOUND CRACKED. REPAIRED IAW SRM 53-40-15-2R FIG 201 REPAIR 3. REPAIR CLASSIFIED AS MAJOR IAW GMM 6-2-100.

Part: IRU — OUT OF ALIGNMENT · airframe 727 hrs · 16,165 cycles

AFTER TAKEOFF MAGENTA LINE SHOWED TURN TO NORTHWEST INSTEAD OF SOUTH. SHOWED UNABLE RNP, GNS SHOWED APPROX 5000 NM OFF. CHECKED POSITION & WAY POINTS PRIOR TO PUSHBACK, ALL CHECKED GOOD. MAGENTA LINE LOOKED GOOD, MAP & PLAN HEADING SHOWED OFF APPROX 40 DEG IN AIR. RETURNED & FOUND ALL THREE IRU'S IN DISAGREE FOR ALIGNMENT. GNS SHOWED CORRECT LATERAL & LONGITUDE. REALIGNED ALL IRU'S IAW AMM 34-43-00-5. ALL LATERAL & LONGITUDE REFERENCES AGREE, GNS & IRU. AIRCRAFT OK FOR SERVICE.

Part: CHARGER — FAILED (MASTER BATTERY) · airframe 718 hrs · 15,881 cycles

NO WRI IN COMPUTER AT THIS TIME. BATTERY DISCHARGING ALERT, CREW DECLARED AN EMERGENCY. LEVEL BATTERY DISCHARGE OCCURRED 38 MIMUTES AFTER TAKE OFF. ACFT WAS AT FL 390 , .84 MACH . NO OTHER ADVERSE ELECTRICAL PROBLEMS NOTED . ALL FLIGHT DECK AND CARGO TEMPS NORMAL . DISCHARGE WAS INTERMITTANT TO CONSTANT . LANDED. PERFORMED TROUBLESHOOTING IAW FIM 24-30-19-00. FOUND FAULT TO BE BATTERY CHARGER . R&R BATTERY CHARGER IAW MM 24-34-01-2 . OPS TESTED OK .

Part: CHARGER — INOPERATIVE (MAIN BATTERY) · airframe 71,169 hrs · 15,691 cycles

AFTER 33 MINS OF FLIGHT WHILE AT CRUISE WE RECEIVED A LEVEL 1 BATTERY DISCHARGE ALERT. THE ALERTS WERE INTERMITTENT & LASTED AT THE MOST 5 MINS DURING DESCENT THE ALERT EXTINGUISHED & REMAINED THAT WAY FOR THE APPROACH & LANDING. BITE CHECKED CHARGER NO FAILURES, CHECKED EPCU SHOWED LAST FLIGHT LEG. EXT POWER INTERFACE PERFORMED RTS NO FAILURES NOTED IAW MM 24-08-01-5. CHECKED CP'S AT BATTERIES & CHARGER APPEAR TO BE IN GOOD CONDITION. GAINED ACCESS TO RELAY R2-24 & WIRING CHECKED FOR LOOSE TERMINALS NONE FOUND, WILL CONTINUE IN THE AM WHEN PARTS ARRIVE. R & R BATTERY CHARGER. OPERATIONS CHECKED NORMAL IAW MM 24-34-03-4. R & R EPCU, OPERATIONS NORMAL IAW MM 24-08-01-4. R & R BATTERY CHARGER RELAY R2-24 IAW SWPM, OPERATIONS NORMAL. ACFT OK FOR SERVICE.

Part: PANEL — DELAMINATED (LT AILERON) · airframe 70,308 hrs · 15,432 cycles

ON WALK AROUND FOUND LT OTBD AILERON UPPER WING CLOSE OUT PANEL DELAMINATED & BROKE AWAY FROM ACFT. INSTALLED NEW PANEL IAW SRM 51-31-01.

Part: CYLINDER — MALFUNCTIONED (RT MLG) · airframe 69,939 hrs · 15,320 cycles

RIGHT MAIN LANDING GEAR DID NOT RETRACT DURING TAKEOFF. FOLLOWED QRH PROCEDURE TO LOWER THEN RAISE LANDING GEAR. RT MAIN WENT IMMEDIATELY GREEN. THE RETRACTION SEQUENCE WORKED. R & R RT CYLINDER & MLG RETRACT ACTUATOR. OPS CHECKED NORMAL.

Part: DOUBLER — CRACKED (RT WING RIB) · airframe 69,123 hrs · 15,072 cycles

RIGHT WING FIXED LE RIB DOUBLER FOUND CRACK AT XOS 789 DURING OTBD SLAT DRIVE CONTROL CABLE INSPECTION. RIB DOUBLER REMOVED AND REPLACED IAW SRM 51-33-01 REVISION 53. DOUBLER FABRICATED IAW DWG ARB 3954 REVISION K. REPAIR CLASSIFIED MAJOR IAW GMM 6-2-100 REVISION 120.

Part: SKIN — CRACKED (BS 1528) · airframe 69,123 hrs · 15,072 cycles

DURING RADIOGRAPHY INSPECTION ON TRANSVERSE SKIN SPLICE AT BS 1528, FOUND A CRACK INDICATION AT LONGERON 1L. REPAIRED IAW SRM 53-00-05 FIGURE 202 REPAIR 1 REVISION 53. REPAIR CLASSIFIED MAJOR IAW GMM 6-2-100 REVISION 120.

Part: DOUBLER — CRACKED (LT WING LE) · airframe 69,123 hrs · 15,072 cycles

LEFT WING FIXED LE BEADED DOUBLER FOUND CRACKED AT XOS 732. REPAIRED IAW SRM 57-40-02 FIGURE 203 REPAIR 15 REVISION 53. REPAIR CLASSIFIED MAJOR IAW GMM 6-2-100 REVISION 120.

Part: FRAME — CHAFED (BS 535) · airframe 69,123 hrs · 15,072 cycles

FRAME AT BS 535, LONGERON 19R FOUND CHAFED. REPAIRED IAW SRM 53-20-07 FIGURE 202 REPAIR 1 REVISION 53. REPAIR CLASSIFIED MAJOR IAW GMM 6-2-100 REVISION 120.

Part: FRAME — DENTED (BS 1681) · airframe 69,123 hrs · 15,072 cycles

FRAME AT BS 1681, LONGERON 12R FOUND DENTED. REPAIRED IAW SRM 53-00-07 FIGURE 201 REPAIR 2 REVISION 53. REPAIR CLASSIFIED MAJOR IAW GMM 6-2-100 REVISION 120.

Part: FRAME — CHAFED (BS 535) · airframe 69,123 hrs · 15,072 cycles

FRAME BS 535, LONGERON 24R FOUND CHAFED. REPAIRED IAW SRM 53-20-07 FIGURE 201 REPAIR 1 REVISION 53. REPAIR CLASSIFIED MAJOR IAW GMM 6-2-100 REVISION 120.

Part: FRAME — CHAFED (BS 535) · airframe 69,123 hrs · 15,072 cycles

FRAME AT BS 535, LONGERON 24L FOUND CHAFED. REPAIRED IAW SRM 53-20-07 FIGURE 201 REPAIR 1 REVISION 53. REPAIR CLASSIFIED MAJOR IAW GMM 6-2-100 REVISION 120.

Part: LANDING GEAR — MALFUNCTIONED · airframe 64,887 hrs · 13,731 cycles

EXTENDED MLG AT 8000 FT MSL/250KTS DURING CLIMBOUT DUE TO INCREASING BRAKE TEMP ON RT MLG. AFTER BRAKE TEMP STABILIZED, MLG WAS RETRACTED BEFORE SLOWING TO 230 KTS. NOSE GEAR LAST ONE TO STOW/LOCK DID NOT STOW LOCK UNTIL SLOW'G TO 240KTS. PERFORMED OPS TEST OF THE ANTISKID CONTROL UNIT IAW AMM32-45-01-5. TESTED NORMAL. PERFORMED THE A SCU R-T-S TEST AND ABS REQUIRED TEST. TESTED NORMAL. IAW AMM 32-48-00-5 AND AMM 32-45-00-5. PERFORMED OVERSPEED MLG INSPECTION ADN CHECK IAW AMM 05-51-07-6. CHECKED NORMAL. ACFT OK FOR SERVICE.

Part: FITTING — CORRODED (ZONE 500) · corrosion level 2 · airframe 64,304 hrs · 13,588 cycles

LEFT INBD FLAP DRIVE LINK SUPPORT ATTACH BOLT HOLE AT FLAP SIDE FOUND WITH CORROSION. R & R IAW SRM 51-33-01 REV 49. & EA 1-5750-157164. REPAIR CLASSIFIED AS MAJOR IAW GMM 6-2-100 REV 114.

Part: SKIN — CRACKED (ZONE 600) · airframe 64,304 hrs · 13,588 cycles

RT WING FIXED L/E NR 12 SLAT TRACK CUT-OUT EDGE CORNER CRACKED. REPAIR CARRIED OUT IAW SRM 57-40-02 REPAIR 7, FIG 201, REV 48. REPAIR CLASSIFIED AS MINOR IAW GMM 6-2-100, REV 114.

Part: SKIN — CRACKED (VERTICAL STAB) · airframe 64,304 hrs · 13,588 cycles

LOWER VERTICAL STABILIZER FOUND RT SIDE REAR CENTER SPAR TO REAR SPAR LOWER PANEL CRACKED. REPAIR CARRIED OUT IAW SRM 55-30-02, FIG 201 REV 49. REPAIR CLASSIFIED AS MAJOR IAW GMM 6-2-100, REV 114.

Part: HINGE BRACKET — CORRODED (ZONE 600) · corrosion level 2 · airframe 64,304 hrs · 13,588 cycles

RIGHT WING OTBD FLAP, INBD FORWARD HINGE BRACKET LOWER INBD STUD HOLE FOUND CORRODED. REWORKED AND FOUND EXCEED LIMIT IAW CMM 57-44-08, REV 72. EXISTING DIAMETER 0.708", FINAL DIAMETER 0.721", MAXIMUM ALLOWABLE DIAMETER 0.709". REPAIR CARRIED OUT IAW EA 1-5750-157157, PART 1. REPAIR CLASSIFIED AS MAJOR IAW GMM 6-2-100 REV 114.

Part: HINGE BRACKET — CORRODED (ZONE 500) · corrosion level 2 · airframe 64,304 hrs · 13,588 cycles

LEFT WING INBD FLAP, OTBD AFT HINGE BRACKET PIVOT INBD LUG BORE FOUND CORRODED. BORE REWORKED AND FOUND EXCEED LIMIT IAW CMM 57-52-03, REV 72. EXISTING DIAMETER 1.217", FINAL DIAMETER 1.253", MAXIMUM ALLOWABLE DIAMETER 1.220". REPAIR ACCOMPLISHED IAW EA 1-5750-157160 PART 1. REPAIR CLASSIFIED AS MAJOR IAW GMM 6-2-100, REV 114.

Part: HINGE BRACKET — CORRODED (ZONE 600) · corrosion level 2 · airframe 64,304 hrs · 13,588 cycles

RIGHT WING OTBD FLAP INBD FORWARD HINGE BRACKET PIVOT BORE FOUND CORRODED. BORE REWORKED AND FOUND EXCEED LIMIT IAW CMM 57-44-08, REV 72. EXISTING DIAMETER 2.3115", FINAL DIAMETER 2.316", MAXIMUM ALLOWABLE DIAMETER 2.3135". REPAIR ACCOMPLISHED IAW EA 1-5750-157157, PART 1. REPAIR CLASSIFIED AS MAJOR IAW GMM 6-2-100, REV 114.

Part: HINGE FITTING — CORRODED (ZONE 500) · corrosion level 2 · airframe 64,304 hrs · 13,588 cycles

LEFT WING OTBD FLAP, OTBD FORWARD HINGE BRACKET LOWER OTBD STUD HOLE FOUND CORRODED. REPAIRED EA 1-5750-157156, PART 1, STEPS 1, 3, AND 6. EXISTING HOLE DIAMETER 0.590", FINAL DIAMETER 0.631", MAXIMUM ALLOWABLE DIAMETER 0.584", REPAIR BUSHING AND WASHER FABRICATED AND INSTALLED IAW EA 1-5750-157156, PART 1 STEPS 4 AND 5. REPAIR CLASSIFIED AS MAJOR IAW GMM 6-2-100, REV 114.

Part: HINGE BRACKET — CORRODED (ZONE 600) · corrosion level 2 · airframe 64,304 hrs · 13,588 cycles

RT WING INBD FLAP, OTBD AFT HINGE BRACKET PIVOT OTBD LUG BORE FOUND CORRODED. REWORKED AND FOUND EXCEED LIMIT IAW CMM 57-52-03, REV 72. EXISTING DIAMETER 1.2553", FINAL DIA 1.256", MAXIMUM ALLOWABLE DIAMETER 1.220". REPAIR ACCOMPLISHED IAW EA 1-5750-157161 PART 1. REPAIR CLASSIFIED AS MAJOR IAW GMM 6-2-100, REV 114.

Part: HINGE FITTING — CORRODED (ZONE 500) · corrosion level 2 · airframe 64,304 hrs · 13,588 cycles

LEFT WING OTBD FLAP, OTBD FORWARD HINGE BRACKET LOWER INBD STUD HOLE FOUND CORRODED. REWORKED AND FOUND EXCEED LIMITS IAW CMM 57-44-09, REV 72. EXISTING HOLE DIAMETER 0.584", FINAL DIAMETER 0.629", MAXIMUM ALLOWABLE DIAMETER 0.584", REPAIR ACCOMPLISHED IAW EA 1-5750-157156, PART 1. REPAIR CLASSIFIED AS MAJOR IAW GMM 6-2-100, REV 114.

Part: HINGE BRACKET — CORRODED (ZONE 600) · corrosion level 2 · airframe 64,304 hrs · 13,588 cycles

RIGHT WING OTBD FLAP, INBD FORWARD HINGE BRACKET SIDE LOAD FITTING ATTACH SURFACE FOUND CORRODED. REWORKED IAW CMM 57-44-08, REV 72. EXISTING THICKNESS UPPER 0.393", LOWER 0.392", REMAINING THICKNESS UPPER 0.390", LOWER 0.389. MATERIAL REMOVED: UPPER 0.003", LOWER 0.003". SHIM FABRICATED AND INSTALLED IAW CMM 57-44-08, REV 72. REPAIR CARRIED OUT IAW EA 1-5750-157157, PART 1. REPAIR CLASSIFIED AS MAJOR IAW GMM 6-2-100, REV 114.

Part: HINGE FITTING — CORRODED (ZONE 500) · corrosion level 2 · airframe 64,304 hrs · 13,588 cycles

LEFT WING OTBD FLAP, OTBD FORWARD HINGE BRACKET SIDE LOAD FITTING ATTACH SURFACE FOUND CORRODED. SURFACE REWORKED IAW CMM 57-44-09, REV 72. EXISTING THICKNESS UPPER 0.467", LOWER 0.467", REMAINING THICKNESS UPPER 0.465", LOWER 0.464". MATERIAL REMOVED: UPPER 0.002", LOWER 0.003". REWORKED CARRIED OUT IAW EA 1-5750-157156, PART 1. REPAIR CLASSIFIED AS MAJOR IAW GMM 6-2-100 REV 114.

Part: HINGE FITTING — CORRODED (ZONE 500) · corrosion level 2 · airframe 64,304 hrs · 13,588 cycles

LEFT WING OTBD FLAP, INBD FORWARD HINGE BRACKET SIDE LOAD FITTING ATTACH SURFACE FOUND CORRODED. SURFACE REWORKED IAW REV 72. EXISTING THICKNESS UPPER 0.356", LOWER 0.355", REMAINING THICKNESS UPPER 0.353", LOWER 0.354". MATERIAL REMOVED: UPPER 0.002", LOWER 0.002". CARRIED OUT IAW EA 1-5750-157159 PART 1STEPS 1, 2, 3, AND 6. REPAIR CLASSIFIED AS MAJOR GMM 6-2-100, REV 114.

Part: HINGE FITTING — CORRODED (ZONE 500) · corrosion level 2 · airframe 64,304 hrs · 13,588 cycles

LEFT WING OTBD FLAP, INBD FORWARD HINGE BRACKET LOWER OTBD STUD HOLE FOUND CORRODED. REWORKED AND FOUND EXCEED LIMITS IAW CMM 57-44-08, REV 72. EXISTING HOLE DIAMETER 0.705", FINAL DIAMETER 0.712", MAXIMUM ALLOWABLE DIAMETER 0.709", REPAIR ACCOMPLISHED IAW EA 1-5750-157159, PART 1. REPAIR CLASSIFIED AS MAJOR IAW GMM 6-2-100, REV 114.

Part: HINGE BRACKET — CORRODED (ZONE 600) · corrosion level 2 · airframe 64,304 hrs · 13,588 cycles

RIGHT WING-INBD FLAP OTBD AFT HINGE BRACKET PIVOT INBD LUG BORE FOUND CORRODED. REWORKED AND FOUND EXCEED LIMIT IAW CMM 57-52-03, REV 72. EXISTING DIAMETER 1.2515", FINAL DIAMETER 1.256", MAXIMUM ALLOWABLE DIAMETER 1.220". REPAIR ACCOMPLISHED IAW EA 1-5750-157161. REPAIR CLASSIFIED AS MAJOR IAW GMM 6-2-100 REV 114.

Part: HINGE BRACKET — CORRODED (ZONE 500) · corrosion level 2 · airframe 64,304 hrs · 13,588 cycles

LEFT WING INBD FLAP, OTBD AFT HINGE BRACKET PIVOT OTBD LUG BORE FOUND CORRODED. BORE REWORKED AND FOUND TO EXCEED LIMITS IAW CMM 57-52-03, REV 72. EXISTING DIAMETER 1.217", FINAL DIAMETER 1.253", MAXIMUM ALLOWABLE DIAMETER 1.220". REPAIR ACCOMPLISHED IAW EA 1-5750-157160 PART 1. REPAIR CLASSIFIED AS MAJOR IAW GMM 6-2-100, REV 114.

Part: HINGE BRACKET — CORRODED (ZONE 600) · corrosion level 2 · airframe 64,304 hrs · 13,588 cycles

RIGHT WING OTBD FLAP, INBD FORWARD HINGE BRACKET ACTUATOR ATTACH INBD LUG BORE FOUND CORRODED. BORE REWORKED AND FOUND EXCEED LIMITS IAW CMM 57-44-08, REV 72. EXISTING DIAMETER 1.279", FINAL DIAMETER 1.285", MAXIMUM ALLOWABLE DIAMETER 1.220". REPAIR CARRIED OUT IAW EA 1-5750-157157, PART 1. REPAIR CLASSIFIED AS MAJOR IAW GMM 6-2-100, REV 114.

Part: HINGE FITTING — CORRODED (ZONE 500) · corrosion level 2 · airframe 64,304 hrs · 13,588 cycles

LEFT WING OTBD FLAP, INBD FORWARD HINGE BRACKET, LOWER INBD STUD HOLE FOUND CORRODED. REWORKED AND FOUND EXCEED LIMIT IAW CMM 57-44-08, REV 72. EXISTING HOLE DIAMETER 0.7065", FINAL DIAMETER 0.712", MAXIMUM ALLOWABLE DIAMETER 0.709", REPAIR CARRIED OUT IAW EA 1-5750-157159, PART 1. REPAIR CLASSIFIED AS MAJOR IAW GMM 6-2-100, REV 114.

Part: HINGE BRACKET — CORRODED (ZONE 500) · corrosion level 2 · airframe 64,304 hrs · 13,588 cycles

LEFT WING OTBD FLAP, OTBD FORWARD HINGE BRACKET PIVOT BORE FOUND CORRODED. REWORKED AS IAW CMM 57-44-09, REV 72. EXISTING HOLE DIAMETER 2.314", FINAL HOLE DIA METER 2.329", MAXIMUM HOLE DIAMETER 2.3135". REPAIR CARRIED OUT IAW EA 1-5750-157156, PART 1. REPAIR CLASSIFIED AS MAJOR IAW GMM 6-2-100, REV 114.

Part: HINGE FITTING — CORRODED (ZONE 500) · corrosion level 2 · airframe 64,304 hrs · 13,588 cycles

LEFT WING OTBD FLAP, INBD FORWARD HINGE BRACKET ACTUATOR ATTACH INBD LUG BORE FOUND CORRODED. REWORKED AND FOUND EXCEED LIMITS IAW CMM 57-44-08, REV 72. EXISTING DIAMETER 1.222", FINAL DIAMETER 1.224", MAXIMUM ALLOWABLE DIAMETER 1.220", REPAIR ACCOMPLISHED IAW EA 1-5750-157159, PART 1. REPAIR CLASSIFIED AS MAJOR IAW GMM 6-2-100, REV 114.

Part: HINGE BRACKET — CORRODED (ZONE 600) · corrosion level 2 · airframe 64,304 hrs · 13,588 cycles

RIGHT WING OTBD FLAP, INBD FORWARD HINGE BRACKET ACTUATOR ATTACH OTBD LUG BORE FOUND CORRODED. BORE REWORKED AND FOUND EXCEED LIMITS IAW CMM 57-44-08, REV 72. EXISTING DIAMETER 1.251", FINAL DIAMETER 1.256", MAXIMUM ALLOWABLE DIAMETER 1.220". REPAIR CARRIED OUT IAW EA 1-5750-157157, PART 1. REPAIR CLASSIFIED AS MAJOR IAW GMM 6-2-100, REV 114.

Part: HINGE FITTING — CORRODED (ZONE 500) · corrosion level 2 · airframe 64,304 hrs · 13,588 cycles

LEFT WING OTBD FLAP, OTBD FORWARD HINGE BRACKET ACTUATOR INBD LUG BORE FOUND CORRODED. REWORKED AND FOUND EXCEED LIMITS CMM 57-44-09, REV 72. EXISTING HOLE DIAMETER 1.226", FINAL DIAMETER 1.231", MAXIMUM ALLOWABLE DIAMETER 1.220", REPAIR ACCOMPLISHED EA 1-5750-157156, PART 1. REPAIR CLASSIFIED AS MAJOR IAW GMM 6-2-100, REV 114.

Part: HINGE FITTING — CORRODED (ZONE 500) · corrosion level 2 · airframe 64,304 hrs · 13,588 cycles

LEFT WING OTBD FLAP, INBD FORWARD HINGE BRACKET LOWER OTBD STUD HOLE SPOTFACE, FOUND CORRODED. REWORKED AND FOUND EXCEED LIMIT IAW CMM 57-44-08, REV 72. EXISTING THICKNESS 0.415", REMAINING THICKNESS 0.384". MATERIAL REMOVED: FWD 0.002"AND AFT 0.029", MINIMUM ALLOWABLE THICKNESS 0.423". REWORKED CARRIED OUT IAW EA 1-5750-157159, PART 1, STEPS 1, 2, 3, AND 6. REPAIR CLASSIFIED AS MAJOR IAW GMM 6-2-100, REV 114.

Part: HINGE FITTING — CORRODED (ZONE 600) · corrosion level 2 · airframe 64,304 hrs · 13,588 cycles

RIGHT WING OTBD FLAP, OTBD FORWARD HINGE BRACKET WING SIDE LOAD FITTING ATTACH BARREL NUT HOLE FOUND CORRODED. REWORKED AND FOUND EXCEED LIMIT IAW CMM 57-44-09 REV 72. EXISTING HOLE DIAMETER 0.660", FINAL HOLE DIAMETER 0.669", ALLOWABLE HOLE DIAMETER 0.667". REPAIRED IAW EA 1-5750- 157158 PART 1. REPAIR CLASSIFIED AS MAJOR IAW GMM 6-2-100, REV 114.

Part: HINGE FITTING — CORRODED (RT WING) · corrosion level 2 · airframe 64,304 hrs · 13,588 cycles

RT WING OTBD FLAP, OTBD FWD HINGE BRACKET SIDE LOAD FITTING ATTACH SURFACE FOUND CORRODED. AREA REWORKED IAW CMM 57-44-09, REV 72. EXISTING THICKNESS UPPER 0.406", LOWER 0.406", REMAINING THICKNESS UPPER 0.400", LOWER 0.400". REPAIRED IAW EA 1-5750-157158 PART 1, STEPS 1, 2, 3, AND 6. REPAIR CLASSIFIED AS MAJOR IAW GMM 6-2-100 REV 114.

Part: HINGE FITTING — CORRODED (ZONE 600) · corrosion level 2 · airframe 64,304 hrs · 13,588 cycles

RIGHT WING OTBD FLAP, OTBD FORWARD HINGE BRACKET LOWER INBD STUD HOLE FOUND CORRODED. REWORKED AND FOUND EXCEED LIMIT IAW CMM 57-44-09, REV 72. EXISTING HOLE DIAMETER 0.592", FINAL HOLE DIAMETER 0.611", MAXIMUM ALLOWABLE DIAMETER 0.584". REPAIRED IAW EA 1-5750-157158, PART 1. REPAIR CLASSIFIED AS MAJOR IAW GMM 6-2-100, REV 114.

Part: SKIN — CRACKED (ZONE 600) · airframe 64,304 hrs · 13,588 cycles

STRUCTURE AROUND FIVE FASTENER HOLES, FOUND TO HAVE CRACK INDICATIONS. FOUND DURING OPEN HOLE HIGH FREQUENCY EDDY CURRENT INSPECTION ON RT WING LOWER SKIN ACCESS DOOR CUT-OUT BETWEEN STA XORS= 683.400 AND STA XORS= 713.600. REPAIR CARRIED OUT IAW EA 1-5710-157163 PART 1. REPAIR CLASSIFIED MAJOR IAW GMM 6-2-100 REVISION 114.

Part: BUSHING — WORN (RT WING TE FLAP) · airframe 64,304 hrs · 13,588 cycles

RIGHT WING OTBD FLAP, OTBD FORWARD HINGE BRACKET ACTUATOR ATTACH OTBD LUG BUSHING FOUND WORN. WORN BUSHING REMOVED IAW CMM 20-20-07, REV 72 AND FOUND EXCEED LIMITS IAW CMM 57-44-09, REV 72. BORE MEASURED DIAMETER 1.222", MAXIMUM ALLOWABLE DIAMETER 1.220". REPAIRED EA 1-5750-157158, PART 1. REPAIR CLASSIFIED AS MAJOR IAW GMM 6-2-100 REV 114.

Part: HINGE FITTING — CORRODED (ZONE 600) · corrosion level 2 · airframe 64,304 hrs · 13,588 cycles

RIGHT WING OTBD FLAP, OTBD FORWARD HINGE BRACKET, LOWER OTBD STUD HOLE, FOUND CORRODED. REWORKED AND FOUND EXCEED LIMIT IAW CMM 57-44-09, REV 72. EXISTING HOLE DIAMETER 0.585", FINAL HOLE DIAMETER 0.610", MAXIMUM ALLOWABLE DIAMETER 0.584". REPAIRED IAW EA 1-5750-157158, PART 1. REPAIR CLASSIFIED AS MAJOR IAW GMM 6-2-100, REV 114.

Part: LONGERON — CRACKED (ZONE 100) · airframe 64,304 hrs · 13,588 cycles

LOWER FUSELAGE- CENTER CARGO COMPARTMENT APPROX BETWEEN STA 5-113 TO 1541 RT LONGERON 43 FOUND CRACKED. R & R WITH NEW FABRICATED LONGERON SPLICE IAW DWG A5A7114, REV J AND INSTALLED IAW SRM 51-33-01, REV 48. REPAIR CLASSIFIED AS MAJOR GMM 6-2-100, REV 114.

Part: LONGERON — CRACKED (ZONE 100) · airframe 64,304 hrs · 13,588 cycles

LOWER FUSELAGE- CENTER CARGO COMPARTMENT APPROX BETWEEN STA 5-113 TO 1541 RT LONGERON 46 FOUND CRACKED. R & R WITH NEW FABRICATED LONGERON SPLICE IAW DWG A5A7116, REVISION D AND INSTALLED IAW SRM 51-33-01, REV 48. REPAIR CLASSIFIED AS MAJOR IAW GMM 6-2-100, REV 114.

Part: LONGERON — CRACKED (ZONE 100) · airframe 64,304 hrs · 13,588 cycles

LOWER FUSELAGE- CENTER CARGO COMPARTMENT APPROX BETWEEN STA 5-113 TO 1541 RT LONGERON 31 FOUND CRACKED. R & R WITH NEW FABRICATED LONGERON SPLICE IAW DWG A5A7112 REV D AND INSTALLED IAW SRM 51-33-01, REV 48. REPAIR CLASSIFIED AS MAJOR IAW GMM 6-2-100, REV 114.

Part: LONGERON — CRACKED (ZONE 100) · airframe 64,304 hrs · 13,588 cycles

LOWER FUSELAGE- CENTER CARGO COMPARTMENT APPROX BETWEEN STA 5-113 TO 1541 RT LONGERON 49 FOUND CRACKED. R & R WITH NEW FABRICATED LONGERON SPLICE IAW DWG A5A7114, REV J AND INSTALLED IAW SRM 51-33-01 REV 48. REPAIR CLASSIFIED AS MAJOR IAW GMM 6-2-100, REV 114.

Part: LONGERON — CRACKED (ZONE 100) · airframe 64,304 hrs · 13,588 cycles

LOWER FUSELAGE CENTER CARGO COMPARTMENT APPROX BETWEEN STA 5-113 TO 1541 RT LONGERON 39 FOUND CRACKED. RT R & R WITH NEW FABRICATED LONGERON SPLICE IAW DWG A5A7114, REV J AND INSTALLED IAW SRM 51-33-01, REV 48. REPAIR CLASSIFIED AS MAJOR IAW GMM 6-2-100, REV 114.

Part: SEAT TRACK — CORRODED (ZONE 200) · airframe 64,304 hrs · 13,588 cycles

RIGHT STA 815, X= -27.5 SEAT TRACK FOUND CORRODED. REPAIRED IAW SRM 53-00-52, FIG 201, REV 48 AND SRM 51-31-01, REV 48. REPAIR CLASSIFIED AS MAJOR IAW GMM 6-2-100, REV 114.

Part: LONGERON — CRACKED (ZONE 100) · airframe 64,304 hrs · 13,588 cycles

LOWER FUSELAGE- CENTER CARGO COMPARTMENT APPROX BETWEEN STA 5-113 TO 1541 LT LONGERON 39 FOUND CRACKED. R & R WITH NEW FABRICATED LONGERON SPLICE IAW DWG A5A7114, REV J AND INSTALLED IAW SRM 51-33-01 REV 48. REPAIR CLASSIFIED AS MAJOR IAW GMM 6-2-100, REV 114.

Part: SEAT TRACK — CORRODED (ZONE 200) · airframe 64,304 hrs · 13,588 cycles

RT STA 465, X= -47.5 SEAT TRACK FOUND CORROSION. SEAT TRACK REPAIRED IAW SRM 53-00-52, FIGURE 201, REV 48. REPAIR CLASSIFIED AS MAJOR IAW GMM 6-2-100, REVISION 114.

Part: SKIN — DAMAGED (ZONE 100) · airframe 64,304 hrs · 13,588 cycles

FUSELAGE SKIN DAMAGED FORWARD OF CARGO DOOR CUT-OUT. CARRIED OUT REPAIR IAW SRM 53-00-15 REPAIR 8, FIG 202, REV 48. REPAIR CLASSIFIED MAJOR IAW GMM 6-2-100, REV 114.

Part: FRAME — DENTED (BS 1661) · airframe 64,304 hrs · 13,588 cycles

FRAME BS 1661 LONGERON 11 LEFT, FOUND DENTED. REPAIRED IAW SRM 53-00-07, FIGURE 201, REV 48. REPAIR CLASSIFIED AS MAJOR, GMM 6-2-100, REV 114.

Part: FRAME — DENTED (BS 1741) · airframe 64,304 hrs · 13,588 cycles

FRAME BS 1741 LONGERON 11 LEFT, FOUND DENTED. REPAIRED IAW SRM 53-00-07, FIG 201, REV 48. REPAIR CLASSIFIED AS MAJOR IAW GMM 6-2-100, REV 114.

Part: VANE — DELAMINATED (RT WING TE FLAP) · airframe 64,304 hrs · 13,588 cycles

RT WING INBD FLAP VANE LOWER SURFACE FOUND DELAMINATION. R & R IAW AMM 27-50-22-4, REV 72.0. ADJUSTMENT AND TEST CARRIED OUT FOUND SATISFACTORY IAW AMM 27-50-22-5, REV 72.0. REPAIR CLASSIFIED AS MINOR IAW GMM 6-2-100 REV 114.

Part: VANE — DELAMINATED (RT WING TE FLAP) · airframe 64,304 hrs · 13,588 cycles

RT WING INBD FLAP VANE UPPER SURFACE FOUND DELAMINATION. R & R IAW AMM 27-50-22 REVISION 72.0. ADJUSTMENT AND TEST CARRIED OUT FOUND SATISFACTORY IAW AMM 27-50-22-5, REV 72.0. REPAIR CLASSIFIED AS MINOR IAW GMM 6-2-100 REVISION 114.

Part: WARNING LIGHT — FALSE ACTIVATION (PAX DOOR) · airframe 63,612 hrs · 13,420 cycles

CABIN DOOR FWD RT LEVEL 1 ALERT ON TAXI IN. SAFE/ARM HANDLE IN ARMED POSITION. PERFORMED DOOR WARNING ADJUSTMENT AND TEST FOR THE R1 DOOR REF AMM 52-70-00-5-0. TESTED GOOD. ACFT OK FOR SERVICE.

Part: BATTERY — DISCHARGED · airframe 63,489 hrs · 13,380 cycles

EMERGENCY POWER TEST FAILED 3 TIMES. PERFORMED BATTERY TEST, EMERGENCY POWER TEST AFTER LETTING BATTERIES CHARGE. OPS NORMAL AT THIS TIME.

Part: UNKNOWN — UNKNOWN (UNKNOWN) · airframe 63,368 hrs · 13,353 cycles

ON CLIMB OUT THRU 16,000 HAD LOUD RUMBLE AND ACFT SHOOK BRIEFLY. HAPPENED 6 OR 7 MORE TIMES. DID NOT NOTICE ANY ABNORMAL INDICATIONS. RETURNED BACK TO FIELD. INSPECTED AIRCRAFT, NO DEFECTS FOUND.

Part: LIGHT — INOPERATIVE (CABIN) · airframe 61,402 hrs · 12,849 cycles

EMERGENCY LIGHTS INOP DURING POST FLIGHT CHECK.

Part: SKIN — CRACKED (LT WING) · airframe 58,650 hrs · 12,210 cycles

LT WING - STA XORS 690 TO XORS 700 LOWER SKIN ACCESS DOOR CUT OUT 08 EACH FASTENER HOLES FOUND CRACKED DURING HFEC OPEN HOLE INSPECTION. LT WING - STA XORS 690 TO XORS 700 LOWER SKIN ACCESS DOOR CUT OUT 08 EACH. FASTENER HOLES REPAIRED IAW EA NR 1-5710-132403, TITLE: AD 2007-07-04 - WINGS - LT LOWER SKIN PLANK CUT OUT AT 536AB - REPAIR TO ACCESS DOOR ATTACHMENT BORES WITH CRACK INDICATIONS PSE 57.23.01 ALI. REPAIR CLASSIFIED AS MINOR IAW GMM 6-2-100, REV 110.

Part: SKIN — DENTED (NR 2 SLAT) · airframe 58,650 hrs · 12,210 cycles

LT WING - SLAT NR 2 L/E LOWER SURFACE FOUND DENT. LT WING - SLAT NR 2 L/E LOWER SURFACE REPAIRED IAW SRM 57-40-01, FIGURE 201, REV 43. REPAIR CLASSIFIED AS MAJOR IAW GMM 6-2-100, REVISION 110.

Part: SKIN — CRACKED (ZONE 600) · airframe 58,650 hrs · 12,210 cycles

RT WING - STA XORS 690 TO XORS 700 LOWER SKIN ACCESS DOOR CUT OUT 09 EACH FASTENER HOLES FOUND CRACKED DURING HFEC OPEN HOLE INSP. RT WING - STA XORS 690 TO XORS 700 LOWER SKIN ACCESS DOOR CUT OUT 09 EACH FASTENER HOLES REPAIRED IAW EA NR 1-5710-132404, TITLE: AD 2007-07-04 WINGS - RT LOWER SKIN PLANK CUT OUT AT 636AB - REPAIR TO ACCESS DOOR ATTACHMENT BORES WITH CRACK INDICATIONS, PSE 57.23.01 ALI. REPAIR CLASSIFIED AS MINOR IAW GMM 6-2-100, REV 110.

Part: FRAME — DENTED (ZONE 200) · airframe 58,650 hrs · 12,210 cycles

MAIN DECK CARGO - RT STA 1741 LONGERON 12 RT, FRAME FOUND DENT. FRAME REPAIRED IAW SRM 53-00-07 FIG 201 REPAIR 2, REVISION 43. REPAIR CLASSIFIED AS MAJOR IAW GMM 6-2-100, REV 110.

Part: FRAME — DENTED (ZONE 200) · airframe 58,650 hrs · 12,210 cycles

MAIN DECK CARGO - RT STA 1701 LONGERON 12 RT, FRAME FOUND DENT. FRAME REPAIRED IAW SRM 53-00-07 FIG 201 REPAIR 2, REVISION 43. REPAIR CLASSIFIED AS MAJOR IAW GMM 6-2-100, REV 110.

Part: LONGERON SPLICE — CRACKED (ZONE 200) · airframe 58,650 hrs · 12,210 cycles

X-RAY INSP AT STA 6-100 LONGERON 1 LT, LONGERON SPLICE FOUND CRACKED. LONGERON SPLICE R & R IAW SRM 51-33-01, REVISION 43. CLASSIFIED MAJOR REPAIR IAW GMM 6-2-100 REV 110.

Part: SKIN — CRACKED (ZONE 500) · airframe 58,650 hrs · 12,210 cycles

LT WING - L/E NR 7 SLAT TRACK CUT OUT INBD SIDE FOUND CRACKED. REPAIRED IAW SRM 57-40-02, FIG 201, REPAIR 7, REV 43. CLASSIFIED MINOR REPAIR IAW GMM 6-2-100, REV 110.

Part: SKIN — CRACKED (ZONE 500) · airframe 58,650 hrs · 12,210 cycles

LT WING - L/E NR 6 SLAT TRACK CUT OUT INBD SIDE FOUND CRACKED. REPAIRED IAW SRM 57-40-02, FIGURE 201, REPAIR 7, REVISION 43. CLASSIFIED MINOR REPAIR IAW GMM 6-2-100, REV 110.

Part: SKIN — CRACKED (RT WING) · airframe 58,650 hrs · 12,210 cycles

CRACK FOUND AT RT WING NR 3 L/E SLAT TELESCOPIC DUCT CUTOUT. RT WING NR 3 L/E SLAT TELESCOPIC DUCT CUTOUT REPAIRED IAW EA NR 1-5710-132397, CLASSIFIED MAJOR REPAIR IAW GMM 6-2-100, REVISION 110.

Part: MOUNT — WORN (NR 1 PYLON) · airframe 53,997 hrs · 11,172 cycles

WITH REFERENCE TO SNRM N01236, DURING BEARING REMOVAL AT NR 1 PYLON AFT MOUNT FITTING BORE FOUND WORN. REMOVED AND REPLACED AS PER SRM 51-31-01 VOL. II. REPAIR CLASSIFIED AS MAJOR AS PER GMM 6-2-100.

Part: BEARING — MIGRATED (ZONE 400) · airframe 53,997 hrs · 11,172 cycles

NR 1 PYLON AFT MOUNT FOUND WITH BEARING MIGRATION. REMOVED AND REPLACED WITH NEW HIGHER FITTING ASSEMBLY AS PER SRM 51-31-01. REPAIR CLASSIFIED AS MAJOR PER GMM 6-2-100.

Part: FITTING — CRACKED (FUSELAGE) · airframe 53,997 hrs · 11,172 cycles

RIGHT MAIN LANDING GEAR WW DOOR LOWER UPLATCH FITTING (FWD AND AFT ) FOUND CRACKED. R & R WITH FABRICATED UPLATCH FITTING AS PER SRM 51-33-01. UPLATCH FITTING FABRICATED AS PER DRAWING ANB7089. OPERATIONS CHECK CARRIED OUT ON RT MLG LOWER UPLATCH FITTING AS PER AMM 32-34-05-700-801 FOUND 'SATISFACTORY'. REPAIR CLASSIFIED AS MINOR PER GMM 6-2-100.

Part: FRAME — CORRODED (ZONE 100) · airframe 53,997 hrs · 11,172 cycles

CORROSION ON FRAME LOWER AT AFT CARGO BILGE L50L- L50R. CORRODED FRAME AT AFT CARGO BILGE BS 1967 L50L- L50R REMOVED AND REPLACED WITH A FABRICATED FRAME AS PER SRM 51-31-01. FRAME FABRICATED AS PER E.A. 1-5310-123128. REPAIR CLASSIFIED AS MINOR AS PER GMM 6-2-100.

Part: FRAME — CORRODED (ZONE 100) · airframe 53,997 hrs · 11,172 cycles

CORROSION ON FRAME LOWER AT AFT CARGO BILGE STA. 1979 L49L-49R. AFT CARGO LOWER FRAME AT BILGE STA. 1979 L49L - L49R DAMAGED REMOVED, REWORKED EXTRUSION P/N: S4933678X7075-0 AS PER DRAWING AGA8002 AND INSTALLED IN PLACED AS PER SRM 51-31-01 VOL. II. REPAIR CLASSIFIED AS MINOR AS PER GMM 6-2-100.

Part: FRAME — DENTED (BS 1701 L12L) · airframe 53,997 hrs · 11,172 cycles

MAIN DECK CARGO COMPARTMENT, LT SIDEWALL STRUCTURE FRAME BS 1701 FOUND DENTED, LONGERON 12L. MAIN DECK CARGO BAY, LT SIDEWALL STRUCTURE FRAME BS 1701 AT L-12L, DENTED AREA REPAIRED AS PER SRM 53-30-00 FIG. 1 VOL. I. REPETITIVE INSPECTION REQUIRED - INITIAL INSPECTION AT 14,500 CYCLES AND REPETITIVE INSPECTION AT 9,500 CYCLES TO BE CARRIED OUT AS PER SRM 53-30-00. REPAIR CLASSIFIED AS MAJOR AS PER GMM 6-2-100.

Part: SUPPORT FITTING — CRACKED (ZONE 200) · airframe 53,997 hrs · 11,172 cycles

DURING OPEN HOLE INSPECTION ON 0.460" DIAMETER HOLE, MAIN CARGO DOOR LOWER JAMB SUPPORT FITTING NR 1 FOUND WITH CRACK INDICATIONS AT HOLES A, B, C AND D.

Part: SKIN — CRACKED (ZONE 600) · airframe 53,997 hrs · 11,172 cycles

05 EA FASTENER HOLES FOUND CRACK DURING HFEC INPECTION ON RT WING LOWER SKIN ACCESS DOOR CUT-OUT BETWEEN XORS=683.4 AND XORS=713.6. REPAIRED AS PER E.A. 1-5710-122580 - A.D. 2007-07-04. REPAIR CLASSIFIED AS MINOR AS PER GMM 6-2-100.

Part: SUPPORT FITTING — CRACKED (ZONE 200) · airframe 53,997 hrs · 11,172 cycles

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

Part: SUPPORT FITTING — CRACKED (ZONE 200) · airframe 53,997 hrs · 11,172 cycles

DURING OPEN HOLE INSPECTION ON 0.460" DIAMETER HOLE, MAIN CARGO DOOR LOWER JAMB SUPPORT FITTING NR 4 FOUND WITH CRACK INDICATIONS AT HOLES C, AND D.

Part: SUPPORT FITTING — CRACKED (ZONE 200) · airframe 53,997 hrs · 11,172 cycles

DURING OPEN HOLE INSPECTION ON 0.460" DIAMETER HOLE, MAIN CARGO DOOR LOWER JAMB SUPPORT FITTING NR 6 FOUND WITH CRACK INDICATIONS AT HOLES C, AND D.

Part: SKIN — CRACKED (ZONE 500) · airframe 53,997 hrs · 11,172 cycles

06 EA FASTENER HOLES FOUND CRACK DURING HFEC INPECTION ON LT WING LOWER SKIN ACCESS DOOR CUT-OUT BETWEEN XORS=683.4 AND XORS=713.6. REPAIRED AS PER E.A. 1-5710-122579- A.D. 2007-07-04. REPAIR CLASSIFIED AS MINOR AS PER GMM 6-2-100.

Part: SUPPORT FITTING — CRACKED (ZONE 200) · airframe 53,997 hrs · 11,172 cycles

DURING OPEN HOLE INSPECTION ON 0.460" DIAMETER HOLE, MAIN CARGO DOOR LOWER JAMB SUPPORT FITTING NR 3 FOUND WITH CRACK INDICATIONS AT HOLES B, C, AND D. MAIN CARGO DOOR LOWER JAMB, CRACKED NR 3 SUPPORT FITTING REMOVED AND REPLACED AS PER SRM 51-31-01 VOL.II. REPAIR CLASSIFIED AS MAJOR AS PER GMM 6-2-100.

Part: SUPPORT FITTING — CRACKED (ZONE 200) · airframe 53,997 hrs · 11,172 cycles

DURING OPEN HOLE INSPECTION ON 0.460" DIAMETER HOLE, MAIN CARGO DOOR LOWER JAMB SUPPORT FITTING NR 2 FOUND WITH CRACK INDICATIONS AT HOLES A, B, C AND D.

Part: SKIN — DENTED (ZONE 500) · airframe 53,997 hrs · 11,172 cycles

LT WING I/B FLAP LOWER SURFACE SCRATCH AND DENT FOUND AT WS 151.3. REPAIR CARRIED OUT AT LT WING INBOARD FLAP LOWER SEGMENT AT STA XW = 151.3 AS PER SRM 57-10-00. REPAIR CLASSIFIED AS MINOR PER GMM 6-2-100.

Part: SKIN — DENTED (LT WING TE FLAP) · airframe 53,997 hrs · 11,172 cycles

LT WING I/B FLAP LOWER SURFACE AT WS 288.14 DENT FOUND. REPAIR CARRIED OUT AT LH WING I/B FLAP LOWER SURFACE AT STA. 288.140 AS PER SRM 57-10-00 FIG. 13 VOL. I. REPAIR CLASSIFIED AS MINOR AS PER GMM 6-2-100.

Part: HMU — FAILED (ENGINE) · airframe 53,389 hrs · 11,045 cycles

APPROACHING CRUISE ALTITUDE GOT A LEVEL 2 'ENG 2 N2 LOW', FOLLOWED BY A ROLL BACK ON ENG 2. ALL INDICATIONS INDICATED FLAME OUT. ACCOMPLISHED QRH PROCEDURES AND LANDED WITHOUT INCIDENT. DID NOT ATTEMPT A RESTART. PERFORMED ENGINE POST-WINDMILLING INSP IAW MM 72-00-05-6 FOUND OK, RUN ENGINE NR 2 IAW JRH. FOUND ENGINE RUN NORMAL, ALL PARAMETERS IN LIMITS. FUEL FILTER INSPECTED AND FOUND CLEANED. REPLACED WITH NEW ONE. REMOVED AND REPLACED HMU IAW 73-21-01-4 1 RUN UP AND LEAK TEST OK. INSPECTED NR 2 MANIFOLD FOR CRACKED PIPING, NONE FOUND ALSO ACCOMPLISHED FUEL SHROUD TEST IAW MM 28-25-00-5 CHKD OK. ZERO FUEL AND NO LEAKS.

Part: HMU — FAILED (NR 2 ENGINE) · airframe 53,389 hrs · 11,045 cycles

APPROACHING CRUISE ALTITUDE GOT A LEVEL 2 'ENG 2 N2 LOW' FOLLOWED BY A ROLL BACK ON ENG 2. ALL INDICATIONS INDICATED FLAME OUT. ACCOMPLISHED QRH PROCEDURES AND LANDED WITHOUT INCIDENT. DID NOT ATTEMPT A RESTART. PERFORMED ENGINE POST-WINDMILLING INSPECTION PER MM 72-00-05-6 FOUND OK, RUN ENGINE NR 2 PER JRH FOUND ENGINE RUN NORMAL, ALL PARAMETERS IN LIMITS. FUEL FILTER INSPECTED & FOUND CLEANED. REPLACED WITH NEW ONE. REMOVED AND REPLACED HMU AS PER 73-21-01-4 1 RUN UP & LEAK TEST OK. INSPECTED NR 2 MANIFOLD FOR CRACKED PIPING, NONE FOUND. ALSO ACCOMPLISHED FUEL SHROUD TEST PER MM 28-25-00-5 CHECKED OK. ZERO FUEL AND NO LEAKS.

Part: BATTERY — UNKNOWN · airframe 53,281 hrs · 11,018 cycles

AFTER LEVEL OFF AT FL390, APPROX 20 MIN AFTER T/O GOT LVL 1 BATT LOW ALERT. DIVERTED TO KLAS BATT SHOWED AMBER BOXED 8 OR 7. REMOVED AND REPLACED A/C BATTERIES IAW AMM 24-34-02-4. PERF DC TIE BUSS OPS CHECK. REMOVED AND REPLACED BATTERY CHARGER. REMOVED AND REPLACED BATTERY AMMETER SHUNT S4-1 RELAY, BAT CHARGER TRANSFER R2-217, RCCB BATTERY CHARGER B1-157, AND REPLACED PLUGS P1-1957, P1-1958, AND P1-1959 PER SWP. PERFORMED WIRING CHECKS PER AWD 24-33-01. PERFORMED EMERGENCY POWER TEST WITH NORNAL FINDINGS. STARTED APU WITH NO FAULTS AND BATTERY RECOVERY NORMAL AFTER START. RAN ALL 3 ENGINES PER JRH AND POWERED ALL 3 BUSSES WITH NORMAL RESULTS D/C SYSTEM CHECKS NORMAL.

Part: BATTERY — DISCHARGED · airframe 53,281 hrs · 11,018 cycles

AFTER LEVEL OFF AT FL390, APPROX 20 MIN AFTER TAKEOFF GOT LVL 1 BATT LOW ALERT. DIVERTED TO KLAS BATTERY SHOWED AMBER BOXED. REMOVED AND REPLACED ACFT BATTERIES IAW AMM 24-34-02-4. PERF DC TIE BUSS OPS CHK. REMOVED AND REPLACED BATTERY CHARGER. REMOVED AND REPLACED BATTERY AMMETER SHUNT S4-1 RELAY, BATTERY CHARGER TRANSFER R2-217, RCCB BATTERY CHARGER B1-157, AND REPLACED PLUGS P1-1957, P1-1958, AND P1-1959 PER SWP. PERFORMED WIRING CHECKS PER AWD 24-33-01. PERFORMED EMERGENCY POWER TEST WITH NORMAL FINDINGS. STARTED APU WITH NO FAULTS AND BATTERY RECOVERY NORMAL AFTER START. RAN ALL 3 ENGINES PER JRH AND POWERED ALL 3 BUSSES WITH NORMAL RESULTS D/C SYSTEM CHECKS NORMAL.

Part: TRUNNION — CORRODED (ZONE 700) · corrosion level 2 · airframe 49,432 hrs · 10,174 cycles

CENTER LANDING GEAR LEFT TRUNNION FITTING AFT HOLE FOUND CORROSION. CENTER LANDING GEAR LEFT TRUNNION FITTING AFT HOLE REAMED TO DIAMETER = 1.385" AND REPAIRED AS PER FEDEX EA NR 1-5310-111115, TITLE: FUSELAGE, CENTER LANDING GEAR LEFT TRUNNION FITTING CORROSION REPAIR. REPAIR CLASSIFIED AS MAJOR PER GMM 6-2-100.

Part: SKIN — CORRODED (BS 1219) · corrosion level 2 · airframe 49,432 hrs · 10,174 cycles

TOP OF CENTER TANK RIGHT SIDE FOUND CORROSION AT STA 1219. CORROSION IN TOP OF CENTER TANK RIGHT SIDE AT STA 1219 CARRIED OUT REPAIR AS PER FEDEX EA NR 1-5710-111114, TITLE: WINGS, CENTER WING FUEL TANK RIGHT SIDE CORROSION REPAIR. REPAIR CLASSIFIED AS MAJOR PER GMM 6-2-100.

Part: SKIN — DAMAGED (ZONE 100) · airframe 49,432 hrs · 10,174 cycles

CENTER CARGO DOOR AFT CUTOUT LOWER SKIN FOUND MATERIAL ABRASION. [06-12-07] DAMAGED AREA AT CENTER CARGO DOOR AFT CUTOUT LOWER SKIN TRIMMED OUT AND CARRIED OUT REPAIR AS PER SRM 53-50-00 FIGURE 17 VOLUME I. REPAIR CLASSIFIED AS MAJOR PER GMM 6-2-100.

Part: SKIN — DAMAGED (ZONE 100) · airframe 49,432 hrs · 10,174 cycles

CENTER CARGO DOOR AFT CUTOUT LOWER SKIN FOUND MATERIAL ABRASION. [06-12-07] DAMAGED AREA AT CENTER CARGO DOOR AFT CUTOUT LOWER SKIN TRIMMED OUT AND CARRIED OUT REPAIR AS PER SRM 53-50-00 FIGURE 17 VOLUME I. REPAIR CLASSIFIED AS MAJOR PER GMM 6-2-100.

Part: SPAR — CORRODED (LT WING) · airframe 49,432 hrs · 10,174 cycles

LEFT WING REAR SPAR, BETWEEN OUTBOARD ISLAND MOUNTING BRACKET NR 1 AND NR 2 FROM OUTBOARD, LOWER FACE FOUND CORRODED. REPAIRED AS PER FEDEX E.A. 1-5710-111113. REPAIR CLASSIFIED AS MAJOR PER GMM 6-2-100.

Part: SKIN — CORRODED (FUSELAGE) · airframe 49,432 hrs · 10,174 cycles

APU - FUSELAGE SKIN EXTERIOR AT APU EXHAUST DOOR LOWER SIDE HINGE FOUND CORRODED. REPAIRED AS PER FEDEX E.A. 1-5330-109892. REPAIR CLASSIFIED AS MAJOR PER GMM 6-2-100.

Part: SUPPORT — CRACKED (LT WING) · airframe 49,432 hrs · 10,174 cycles

LEFT WING FIXED LEADING EDGE CAVITY INTERIOR UPPER FACE, XORS 562, SUPPORT STRIP FOUND CRACKED. REPAIR CARRIED OUT AS PER FEDEX E.A. 1-5710-111112. REPAIR CLASSIFIED AS MINOR PER GMM 6-2-100.

Part: SKIN — CORRODED (ZONE 200) · airframe 49,432 hrs · 10,174 cycles

MAIN DECK L3 DOOR CUTOUT FORWARD LOWER CORNER FOUND CORRODED. MAIN DECK L3 DOOR CUTOUT FORWARD LOWER CORNER CARRIED OUT REPAIR AS PER SRM 53-50-00 FIGURE 18 VOLUME I. REPAIR CLASSIFIED AS MAJOR PER GMM 6-2-100.

Part: SKIN — DENTED (ZONE 100) · airframe 49,432 hrs · 10,174 cycles

FORWARD CARGO AFT LOWER CUTOUT SKIN FOUND DENT. [06-12-07] DENT AT FORWARD CARGO AFT LOWER DOOR CUTOUT SKIN TRIMMED OUT AND CARRIED OUT REPAIR AS PER SRM 53-50-00 FIGURE 17 VOLUME I. REPAIR CLASSIFIED AS MAJOR PER GMM 6-2-100.

Part: UNKNOWN — CRACKED (ZONE 500) · airframe 49,432 hrs · 10,174 cycles

LEFT WING FIXED LEADING EDGE TELESCOPING DUCT CUTOUT FOUND CRACKED. [06-12-07] REPAIR CARRIED OUT AT LEFT HAND WING FIXED LEADING EDGE TELESCOPING DUCT CUTOUT AREA AS PER SRM 57-10-00 FIGURE 43 VOLUME I AND FEDEX E.A. 1-5730-109887. REPAIR CLASSIFIED AS MINOR PER GMM 6-2-100.

Part: RUDDER — DAMAGED · airframe 44,682 hrs · 9,072 cycles

DURING AIRPLANE'S CONVERSION FROM P TO F, ACCIDENTAL DAMAGE LOWER AFT RUDDER. DURING BRAKE SYSTEM BLEED PROCURE WITH HYD PRESSURE AND LOCK PINS IMPROPERLY INSTALLED AN ERRONEOUS MANEUVER OF THE RUDDER PEDALS CAUSED SUDDEN MOVEMENT OF THE RUDDER TOUCHED THE WORK STAND PLATFORMS. THE DAMAGE CONSIST OF -2EA CRACK ON LT SIDE APPROX 1.5 X 0.355 INCH, T/E 1, .5 X 0.625 INCH, 1EA DENT OF RT SIDE SKIN 1.8 X 11 INCH. REMOVED RUDDER ACCOMPLISHED DVI HINGE, BRACKETS ROD END, FITTING ECC NOT FOUND DEFECT. REPAIRED SKIN LT, RT SIDE FOR SRM 55-10-01 FIG 2. REPAIRED T/E COVER FOR SRM 55-30-00 FIG 1. INSTALLED LOWER AFT RUDDER IAW MM 27-20-20-4.

Part: FRAME — CRACKED (BS 1256) · airframe 44,682 hrs · 9,072 cycles

DURING PASSENGER TO FREIGHT CONVERSION: FOUND CRACK 1.2" LONG ON FRAME STA 1256 LT SIDE BETWEEN L11 TO L12. TRIMOUT TIME CRACK WITH 0.5" RADIUS AND 2 REMAINING FASTENERS. PERFORMED INSPECTION FOR CRACK, INSTALLED FILLER MT 7075T6 , INSTALLED REPAIR STRAP MAT 7075T6 WITW THK .126" USING FASTENER HLT436-6.

Part: FRAME — CRACKED (BS 1305) · airframe 44,682 hrs · 9,072 cycles

DURING PASSENGER TO FREIGHT COVERSION FOUND CRACK 1.20" LONG ON FRAME STA1305 BETWEEN LT 11 LT 12. DURING PASSENGER TO FREIGHT CONVERSION: FOUND CRACK 1.2" LONG ON FRAME STA 1305 RT SIDE BETWEEN L11 TO L12. TRIMOUT TIME CRACK WITH 0.5" RADIUS AND 2 REMAINING FASTENERS. PERFORMED INSPECTION FOR CRACK, INSTALLED FILLER MT 7075T6, INSTALLED REPAIR STRAP MAT 7075T6 WITW THK .126" USING FASTENER HLT436-6 (APPROVAL BOEING). PROTECT PER SRM 51-21-01.

Part: FITTING — CORRODED (HORIZONTAL STAB) · airframe 44,668 hrs · 9,069 cycles

RT HORIZONTAL STABILIZER UPPER BARREL NUT NR 14 HAS BORE CORROSION EXCEEDING LIMITS. SPLICE FITTING REMOVED AND REPLACED IAW EO-1-5510-7-5000 REV D -PT1. MAJOR REPAIR PER GMM 6-2-100.

Part: SKIN — DAMAGED (LT WING)

LT WING LOWER SKIN, XORS 455, WITH EXISTING BLEND OUT. BLEND OUT AT LT WING LOWER SKIN, XORS 455 EVALUATED AND FOUND REPAIR CARRIED OUT AS PER SRM 57-10-00 FIG 32 VOL I.

Part: SKIN — DAMAGED (A/C BAY DOOR) · airframe 44,668 hrs · 9,069 cycles

AIR COND BAY AT STA 496-615 WITH EXISTING BLEND OUT. EXISTING BLENDOUT AT NR 2 AIR COND BAY DOOR STA 496-615 EVALUATED FOUND CARRIED OUT AS PER ATTACHED FAA FORM 8110-3. REPAIR CLASSIFIFED AS MAJOR PER GMM 6-2-100. EO-1-5100-7-5001 ACCOMLISHED.

Part: SKIN — DAMAGED (T/E FLAP)

RT WING, INBD FLAP, EXTERIOR UPPER SURFACE MOST UPPER ABOUT 20 INCHES FROM INBD TO OUTBD, FOUND 1 EACH EXISTING REPAIR DOUBLER.

Part: SKIN — DAMAGED (L/E SLAT)

RIGHT WIN , DROOP LEADING EDGE, TOP SURFACE, FOUND WITH A EXISTING REPAIR DOUBLER AND EXISTING FASTENERS HEAD EMITTING RUST. REPAIRED IAW SRM 57-10-00 FIG. 26 VOL I.

Part: INTERCOSTAL — CRACKED (FUSELAGE)

MAIN DECK, STA 513 LONGERON 27L INTERCOSTAL BOTTOM SIDE FOUND CRACKED ABOUT 0.5 INCH. DISCREPANT INTERCOSTAL REMOVED AS PER SRM 51-31-01 VOL II. NEW INTERCOSTAL LOCATED AND INSTALLED AS PER SRM 51-31-01 VOL II.

Part: FITTING — CRACKED (T/E FLAP) · airframe 44,668 hrs · 9,069 cycles

RIGHT WING O/B FLAP SECOND FLAP VANE TRACK FROM I/B UP-STOP FITTING FOUND CRACKED. CRACKED STOP FITTING REMOVED. NEW FITTING HOLES TRANSFERED AND INSTALLED AS PER SRM 51-33-01 AND 51-31-01VOL II. CLASSIFIED AS MAJOR REPAIR PER GMM 6-1-100.

Part: FAIRING — CORRODED (FUSELAGE)

LEFT NR 1 AIR COND BAY BILGE AREA, FAIRING ASSY FOUND WITH CORROSION AS MARKED. CORROSION REMOVED AS PER SRM 51-21-01 VOL II ,MATERIAL ORIGINAL THICKNESS:0.04 REMOVED MATERIAL THICKNESS: 0.006, L:24, W:6, REMAIN THICKNESS: 0.034 AND FOUND WITHIN LIMIT AS PER SRM 53-00-01 FIG 1A VOL I. REPAIR INTERCOSTAL PN ACA3805-11 AND BRACKET ACA3352-5. MINOR REPAIR PER GMM 6-2-100.

Part: TUBE — NOT CLOSED (WASTE TANK)

AFT CARGO - REFERENCE EA 1-2520-7-78127 ITEM 39, AFTER REMOVAL OF WASTE TANK AND PLUMBING FOUND VACUUM PUMPS OUTLETS AND TANK DUMP TUBE OUTLET NOT BLANKED. REMOVED AND DISCARD AS PER AMM 20-50-02 AND SMR 51-33-01 VOL II, NEW PANEL AND COVER PLATE FABRICATED FROM 6061T6-0.160 AND 6061T651-4.5 DIA AS PER DRAWING AWD 8861, AWD 08571 AND AWD 9112. FABRICATED COVER PLATE AND PANEL LOCATED AND INSTALLED AS PER DRAWING AW09112 AND AMM 20-50-02. MAJOR REPAIR AS PER GMM 6-2-100 AND SRM 51-90-01 FIG. 1 VOL II.

Part: SPAR — CORRODED (LT WING)

LT WING REAR SPAR TOPSIDE WING CORROSION FOUND AT XORS 725. SKIN TRIMMED, REPAIR DOUBLER AND FILER FABRICATED AND INSTALLED AS PER EA 1-5720-80383.

Part: FLOORBEAM — CORRODED (FUSELAGE)

CABIN FLOORBEAM FOUND CORRODED AT STA 1873 LBL 10 TO 26 AS MARKED. REMOVED AND FOUND EXCEED LIMIT AS PER SRM 53-00-01 FIG. 4 VOL I. DISCREPANT FLOOR SUPPORT AT STA 1873 LBL 33 TO RBL 33 REMOVED AS PER SRM 51-31-01 VOL II. NEW FLOOR SUPPORT REWORKED FROM S2929348-12000 AS PER DWG AGA 7975 AND AND HOLES PICK UP AS PER SRM 51-31-01 VOL II. NEW FLOOR SUPPORT REPROTECTED AS PER SRM 51-21-01 VOL II AND PART MARKED FX AGA 7975-15 AS PER GMM 7-0-1001. NEW FLOOR SUPPORT LOCATED AND INSTALLED AT STA 1873 LBL 33TO RBL 33 AS PER SRM 51-31-01 VOL II. CLASSIFIED MAJOR REPAIR AS PER GMM 6-2-100.

Part: SEAT TRACK — CORRODED (ZONE 200) · airframe 44,668 hrs · 9,069 cycles

MAIN DECK IN BETWEEN STA 420 & 495 RBL 95.5 SEAT TRACK FOUND CORRODED. SEAT TRACK REMOVED AND NEW SEAT TRACK P/N ABA 7681-503 INSTALLED AS PER SRM 51-31-01 VOL II.

Part: ATTACH FITTING — CRACKED (ZONE 300) · airframe 44,668 hrs · 9,069 cycles

EMPENNAGE - LT FAIRING PANEL ATTACHMENT IN BETWEEN VERTICAL STABILIZER LOWER UPPER SECTION AND LOWER CENTER SECTION AT APPROX PIN 122 ADJACENT TO ACCESS PANEL 363PL FOUND CRACKED AT AFT EDGE AREA. REPAIR AS PER EA 1-5530-80384 AND SRM 51-33-01 AND 51-35-01 VOL II. MINOR REPAIR PER GMM 6-2-100. EO TITLE STABILIZERS VERTICAL STABILIZER VERTICAL AIR INTAKE PANEL ASSEMBLY REPAIR.

Part: RIB — DAMAGED (RT WING TE FLAP)

RT WING I/B FLAP ASSY FOUND NEW FLAP SEGMENT ASSY RIB DAMAGED. DAMAGED AREA TRIMMED. REPAIR DOUBLER & FILLER FABRICATED AND INSTALLED AS PER SRM 57-00-01 FIG. 7 VOL I AND 51-35- 01 VOL II. MINOR REPAIR PER GMM 6-2-100.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE)

CABIN, LONGITUDINAL FLOOR SUPPORT FOUND CORROSION AT STA 1888 TO 1913.5 RBL 22 AS MARKED. CORROSION ON FLOOR SUPPORT AT STA 1888 TO 1913.5 RBL 22 REMOVED AND FOUND EXCEED LIMIT AS PER SRM 53-00-01 FIG. 4 VOL I. DISCREPANT FLOOR SUPPORT FROM STA 1887 TO 2007 RBL 22 REMOVED AS PER SRM 51-31-01 VOL II. NEW FLOOR SUPPORT REWORKED FROM S3932107-7075T6511 AND HOLES PICK UP AS PER SRM 51-31-01 VOL II. NEW FLOOR SUPPORT REPROTECTED AS PER SRM 51-21-01 VOL II AND PART MARKED FX AGA 7497- 504 AS PER GMM 7-0-1001. NEW FLOOR SUPPORT LOCATED AND INSTALLED AT STA 1887 TO 2007 RBL 21 TO 26 AS PER SRM 51-31-01. MAJOR REPAIR AS PER GMM 6-2-100.

Part: FLOOR SUPPORT — CORRODED (FUSLEAGE)

CABIN, FLOOR SUPPORT FOUND VARIOUS PLACES CORROSION AT STA 1959 TO 2007 AND RBL 56 TO 59 AS MARKED. REMOVED & FOUND EXCEED LIMIT AS PER SRM 53-00-01 FIG. 4 VOL I. DISCREPANT FLOOR SUPPORT AT STA 1887 TO 2007 RBL 56 REMOVED AS PER SRM 51-31-01 VOL II. NEW FLOOR SUPPORT REWORKED FROM S3932107-7075T6511 AS PER DRAWING AGA 7496 . HOLES PICK-UP AS PER SRM 51-31-01 VOL II. NEW FLOOR SUPPORT REPROTECTED AS PER SRM 51-21-01 VOL II AND PART MARK FX AGA 7496-502 AS PER GMM 7-0-1001. NEW FLOOR SUPPORT LOCATED AND INSTALLED AS PER SRM 51-31-01 VOL II. MAJOR REPAIR AS PER GMM 6-2-100.

Part: FLOORBEAM — CORRODED (FUSELAGE)

CABIN FLOOR SUPPORT AT STA 1913 RBL 42 FOUND PREVIOUS REPAIRED NON- STANDARD AS MARKED. FLOOR SUPPORT REMOVED AS PER SRM 51-31-01 VOL II. NEW FLOOR SUPPORT REWORKED FROM S2929348 AS PER DRAWING AGA 7501 AND REPROTECTED AS PER SRM 51-21-01 VOL II. NEW FLOOR SUPPORT PAINTED AS PER SRM 51-21-01 VOL II AND PART MARKED FX AGA 7501-502 AS PER GMM 7-0-1001. NEW FLOOR SUPPORT LOCATED AND INSTALLED AT STA 1913 RBL 26 TO 53 AS PER SRM 51-31-01 VOL II. CLASSIFIED MAJOR REPAIR AS PER GMM 6-2-100.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE)

CABIN, FLOOR SUPPORT FOUND CORROSION AT VARIOUS PLACES FROM STA 1911 TO 2007 RBL19 AS MARKED. CORROSION ON FLOOR SUPPORT AT STA 1911 TO 2007 RBL 19 REMOVED & FOUND EXCEED LIMIT AS PER SRM 53-00-01 FIG. 4 VOL I. DISCREPANT FLOOR SUPPORT REMOVED AT STA 1887 TO 2007 RBL 19 AS PER SRM 51-31-01 VOL II. NEW FLOOR SUPPORT REWORKED FROM S2929169X-7075T6511 AS PER DWG AGA 7498 & HOLES PICK UP AS PER SRM 51-31-01 VOL II. NEW FLOOR SUPPORT REPORTED AS PER SRM 51-21-01 VOL II & PART MARK FX AGA 7498-501 AS PER GMM 7-0-1001. NEW FLOOR SUPPORT LOCATED & INSTALLED FROM STA 1887 TO 2007 RBL 19 AS PER SRM 51-31-01 VOL II. MAJOR REPAIR AS PER GMM 6-2-100.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE)

CABIN, FLOOR SUPPORT AT STA 1911 LBL 22 TO 28 FOUND VARIOUS PLACES OF CORROSION AS MARKED. CORROSION ON FLOOR SUPPORT AT STA 1911 RBL 22 TO LBL 28. REMOVED & FOUND EXCEED LIMIT AS PER SRM 53-00-01 FIG. 4 VOL I. DISCREPANT FLOOR SUPPORT FROM STA 1887 TO 2007 RBL 22 TO LBL 28 REMOVED AS PER SRM 51-31-01 VOL II. NEW FLOOR SUPPORT REWORKED FROM S3932107-7075T6511 AS PER DRAWING AGA 7497 AND HOLES PICK UP AS PER SRM 51-31-01 VOL II. NEW FLOOR SUPPORT REPROTECTED AND PART MARKED FX AGA 7497-503 AS PER GMM 7-0-1001. NEW FLOOR SUPPORT LOCATED AND INSTALLED FROM STA 1887 TO 2007 LBL 22 TO 28 AS PER SRM 51-31-01VOL II. MAJOR REPAIR AS PER GMM 6-2-100.

Part: FLOORBEAM — CORRODED (FUSELAGE)

CABIN, FLOOR SUPPORT FOUND CORROSION AT STA 1911 RBL 70 AND 75 AS MARKED. REMOVED AS PER SRM 51-31-01 VOL II. NEW FLOOR SUPPORT FABRICATED FROM S2929348 AS PER DRAWING AGA 7501 AND REPROTECTED AS PER SRM 51-21-01 VOL II. NEW FLOOR SUPPORT LOCATED AND INSTALLED AT STA 1911 RBL 58-84 AS PER SRM 51-31-01 VOL II.CLASSIFIED MAJOR REPAIR AS PER GMM 6-2-100.

Part: SEAT TRACK — DAMAGED (FUSELAGE)

CABIN, CURVE SEAT TRACK AT STA 1951 TO 1971 LBL 77 FOUND PREVIOUS REPAIRED AREA NON-STANDARD AS MARKED. SEAT TRACK TRIM OUT AS PER SRM 53-70-00 FIG 1 VOL I . NEW SEAT TRACK REMOVED AS PER SRM 53-70-00 FIG 7 VOL I. SPLICE ANGLE REWORKED AND SPLICE PLATE FABRICATED AS PER SRM 53-70-00 FIG 1 VOL I.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE)

AFT CARGO CEILING AREA HAS CORROSION ON CABIN FLOOR SUPPORTS AT STA 1887 X=58. REMOVED AND FOUND EXCEED LIMIT AS PER SRM 53-00-01 FIG. 4 VOL I. DISCREPANT FLOOR SUPPORT AT STA 1887 TO 2007 X=58 REMOVED AS PER SRM 51-31-01 VOL II. NEW FLOOR SUPPORT REWORKED FROM S3932107-7075T6511 AS PER DRAWING AGA 7496 AND HOLES PICK UP AS PER SRM 51-31-01 VOL II. NEW FLOOR REPROTECTED AS PER SRM 51-21-01 VOL II AND PART MARKED FX AGA7496-501 AS PER GMM 7-0-1001. NEW FLOOR SUPPORT LOCATED AND INSTALLED AT STA 1887 TO 2007 X=58 AS PER SRM 51-31-01 VOL II.MAJOR REPAIR AS PER GMM 6-2-100.

Part: ATTACH FITTING — CRACKED (FUSELAGE)

MAIN DECK, AT STATION 510 LONGERON 27L FRAME TO FLOORBEAM INTERSECTION FOUND WITH 1 INCH CRACK. CARRIED OUT REPAIR AS PER EA 1-5310-80388.

Part: SEAT TRACK — CORRODED (FUSELAGE)

MAIN DECK, UPON REMOVAL OF FLOOR PANEL 291GF FOR SHEETMETAL ACCESS AT STA 1887 LBL 60 INCH SEAT TRACK FOUND CORRODED. CORROSION ON SEAT TRACK REMOVED & FOUND EXCEED LIMIT AS PER SRM 53-70-00 FIG 3 VOL I. SEAT TRACK REWORKED AS PER SRM 53-70-00 FIG.1 VOL I.

Part: STRUCTURE — CORRODED (HORIZONTAL STAB)

RT HORIZONTAL STABILIZER UPPER BARREL NUT NR 34 HAS BORE CORROSION EXCEEDING LIMITS. REPAIRED IAW EA 1-5510-78133.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE)

MAIN DECK, UPON REMOVAL OF FLOOR SUPPORT STRUCTURE, FLOOR SUPPORT STRUCTURE TO TEE CHORD AT STA 2007 RBL 60 INCH FOUND WITH CORROSION. CORROSION ON TEE CHORD AT STA 2007 RBL 60 REMOVED AND FOUND EXCEED LIMIT AS PER SRM 53-40-00 FIG. 7 VOL I. DISCREPANT TEE CHORD REMOVED AS PER SRM 51-31-01 VOL II. NEW TEE CHORD REWORKED FROM S2924410 AS PER DRAWING NJC6040.HOLES PICK-OUT ON NEW TEE CHORDS AS AS PER SRM 51-31-01 VOL II AND REPROTECTED AS PER SRM 51-21-01 VOL II. NEW TEE CHORD PAINTED AS PER SRM 51-21-01 VOL II AND PART MARKED AS PER GMM 7-0-1001 FX NJC6040-175. MAJOR REPAIR AS PER GMM 6-2-100.

Part: DOOR FRAME — CORRODED (FUSELAGE)

CAIN, DOOR 3R ABOVE UPPER DOOR JAMB STA 1263 LONGERON L-12 FOUND CORROSION AS MARKED. REMOVED AND FOUND EXCEED LIMIT AS PER SRM 53-00-01 FIG 1A VOL I. MATERIAL THICKNESS: 0.080, REMAIN THICKNESS: 0.049, REMOVED THICKESS: 0.031 FASTENER ON DISCREPANT AREA REMOVED AS PER SRM 51-32-01 VOL II. REPAIR ANGLE REWORKED FROM 1D0964T AS PER SRM 53-10-00 FIG 2A VOL I AND HOLES PICK-UP AS PER SRM 51-31-01 VOL II.REPAIR ANGLE LOCATED AND INSTALLED AS PER SRM 51-33-01 VOL II. CLASSIFIED MAJOR REPAIR AS PER GMM 6-2-100.

Part: DOOR FRAME — CORRODED (FUSELAGE)

SNRM N1749: CABIN, 3R ABOVE UPPER DOOR JAMB STA 1278 FOUND LONGERON L-14 CORROSION AS MARKED.

Part: VANE — DAMAGED (ZONE 600) · airframe 44,668 hrs · 9,069 cycles

RT WING I/B FLAP VANE I/B T-FITTING FOUND OUT OF LIMIT. REMOVED AND REPLACED AS PER CMM 57-52-03.

Part: VANE — CORRODED (ZONE 600) · airframe 44,668 hrs · 9,069 cycles

RT WING I/B FLAP VANE O/B T-FITTING FOUND CORRODED. RT WING I/B FLAP VANE O/B TEE FITTING REMOVED AND REPLACED AS PER CMM 57-52- 03, REFER WORK CARD E1-5750-7-5005 A2 PT 2.

Part: HINGE — CORRODED (TE FLAPS)

LT WING O/B FLAP O/B REAR SPAR MOUNTED HINGE ACTUATOR HOLE EVIDENT OF CORROSION. LT WING O/B FLAP O/B REAR SPAR MOUNTED HINGE ACTUATOR CORROSION REMOVED & FOUND I/B & O/B LUG HOLES EXCEED LIMITS AS PER CMM 57-44-09 .I/B & O/B LUG SPOTFACES THK W/I LIMITS AS PER CMM 57-44-09 . I/B LUG ORG DIA 1.220 FINAL DIA 1.224 O/B LUG ORG DIA 1.192 FINAL DIA 1.193. I/B LUG ORG THK 0.346 REMAIN THK 0.344 MATERIAL REMOVED 0.002. O/B LUG ORG THK 0.360 REMAIN THK 0.358 MATERIAL REMOVED 0.002. FABRICATED BUSHING AND INSTALLED AS PER EA 1-5750-80379. (WINGS-TRAILING EDGE AND TRALING EDGE DEVICES -L/H O/B FLAP O/B HINGE BRACKET REPAIRS). MAJOR REPAIR AS PER 6-2-100.

Part: SPAR — CORRODED (RT WING)

RT WING O/B FLAP O/B REAR SPAR MOUNTED HINGE ACTUATOR HOLE EVIDENT OF CORROSION. CORROSION REMOVED & FOUND I/B AND O/B LUG HOLES EXCEED LIMITS AS PER CMM 57-44-09.

Part: SPAR — CORRODED (RT WING)

RT WING O/B FLAP I/B REAR SPAR MOUNTED HINGE ACTUATOR HOLE HAS EVIDENCE OF CORROSION. CORROSION REMOVED & FOUND I/B & O/B LUG HOLES EXCEED LIMITS PER CMM 57-44-08.

Part: SPAR — CORRODED (RT WING)

RT WING O/B FLAP O/B REAR SPAR MOUNTED HINGE LWR MOUNT EVIDENT OF CORROSION. CORROSION REMOVED & FOUND I/B AND O/B BOLT HOLES EXCEED LIMITS AS PER CMM 57-44-09.

Part: STRUCTURE — CORRODED (HORIZONTAL STAB)

RT HORIZONTAL STABILIZER UPPER BARREL NUT NR 35 HAS BORE CORROSION EXCEEDING LIMITS. REPAIRED IAW EA 1-5510-78133.

Part: STRUCTURE — CORRODED (HORIZONTAL STAB)

LT HORIZONTAL STABILIZER UPPER BARREL NUT NR 32 HAS BORE CORROSION EXCEEDING LIMITS. REPAIRED IAW EA 1-5510-78133.

Part: STRUCTURE — CORRODED (HORIZONTAL STAB)

LT HORIZONTAL STABILIZER UPPER BARREL NUT NR 28 HAS BORE CORROSION EXCEEDING LIMIT. REPAIRED IAW EA 1-5510-78133.

Part: STRUCTURE — CORRODED (HORIZONTAL STAB)

LT HORIZONTAL STABILIZER UPPER BARREL NUT NR 24 HAS BORE CORROSION EXCEEDING LIMITS. REPAIRED IAW EA 1-5510-78133.

Part: STRUCTURE — CORRODED (HORIZONTAL STAB)

LT HORIZONTAL STABILIZER UPPER BARREL NUT NR 20 HAS BORE CORROSION EXCEEDING LIMITS. REPAIRED IAW EA 1-5510-78133.

Part: STRUCTURE — CORRODED (HORIZONTAL STAB)

LT HORIZONTAL STABILIZER UPPER BARREL NUT NR 18 HAS BORE CORROSION EXCEEDING LIMITS. REPAIRED IAW EA 1-5510-78133.

Part: STRUCTURE — CORRODED (HORIZONTAL STAB)

LT HORIZONTAL STABILIZER UPPER BARREL NUT NR 30 HAS BORE CORROSION EXCEEDING LIMITS. REPAIRED IAW EA 1-5510-78133.

Part: STRUCTURE — CORRODED (HORIZONTAL STAB)

RT HORIZONTAL STABILIZER UPPER BARREL NUT NR 27 HAS BORE CORROSION EXCEEDING LIMITS. REPAIRED IAW EA 1-5510-78133.

Part: PANEL — CORRODED (HORIZONTAL STAB) · airframe 44,668 hrs · 9,069 cycles

RIGHT HORIZONTAL STABILIZER UPPER BARREL NUT NR 33 HAS BORE CORROSION EXCEEDING LIMITS. BARREL NUT BORE NR 33 RT REPAIRED IAW EA 1-5510-78133 ATTACHMENT 33, HORIZONTAL STABILIZER BARREL NUT BORE REWORK/ REPAIR AD 2003-22-08. MAJOR REPAIR AS PER GMM 6-2-100.

Part: STRUCTURE — CORRODED (HORIZONTAL STAB)

LT HORIZONTAL STABILIZER UPPER BARRREL NUT NR 34 HAS BORE CORROSION EXCEEDING LIMITS. REPAIRED IAW EA 1-5510-78133.

Part: STRUCTURE — CORRODED (HORIZONTAL STAB)

RT HORIZONTAL STABILIZER UPPER BARREL NUT NR 31 HAS BORE CORROSION EXCEEDING LIMITS. REPAIRED IAW EA 1-5510-78133.

Part: STRUCTURE — CORRODED (HORIZONTAL STAB)

RT HORIZONTAL STABILIZER UPPER BARREL NUT NR 29 HAS BORE CORROSION EXCEEDING LIMITS. REPAIRED IAW EA 1-5510-78133.

Part: STRUCTURE — CORRODED (HORIZONTAL STAB)

LT HORIZONTAL STABILIZER UPPER BARREL NUT NR 16 HAS BORE CORROSION EXCEEDING LIMITS. REPAIRED IAW EA 1-5510-78133.

Part: STRUCTURE — CORRODED (FUSELAGE)

LT HORIZONTAL STABILIZER UPPER BARREL NUT NR 4 HAS BORE CORROSION EXCEEDING LIMITS. REPAIRED IAW EA 1-5510-78133.

Part: STRUCTURE — CORRODED (HORIZONTAL STAB)

RT HORIZONTAL STABILIZER UPPER BARREL NUT NR 01 HAS BORE CORROSION EXCEEDING LIMITS. REPAIRED IAW EA 1-5510-78133.

Part: HINGE — CORRODED (T/E FLAP)

LEFT WING O/B FLAP, O/B FLAP MOUNTED HINGE ACTUATOR HOLE EVIDENT OF CORROSION. CORROSION REMOVED AS PERCMM 20-11-02.

Part: STUD — CORRODED (RT AILERON)

RIGHT WING O/B AILERON ACTUATOR MOUNTING UPPER O/B STUD FOUND CORRODED. REMOVED AND REPLACED ON THE RT WING O/B AILERON ACTUATOR MOUNTING UPPER O/B STUD AS PER MM 20-50-02.

Part: STRUCTURE — CORRODED (HORIZ STAB)

RT HORIZONTAL STABILIZER UPPER BARREL NUT NR 17 HAS BORE CORROSION EXCEEDING LIMITS. REPAIRED IAW EA 1-5510-78133.

Part: STRUCTURE — CORRODED (HORIZ STAB)

RT HORIZONTAL STABILIZER UPPER BARREL NUT NR 19 HAS BORE CORROSION EXCEEDING LIMITS. REPAIRED IAW EA 1-5510-78133.

Part: STRUCTURE — CORRODED (HORIZ STAB)

RT HORIZONTAL STABILIZER UPPER BARREL NUT NR 11 HAS BORE CORROSION EXCEEDING LIMITS. REPAIRED IAW EA 1-5510-78133.

Part: HINGE — CORRODED (T/E FLAP)

LT WING O/B FLAP, I/B FLAP MOUNTED HINGE PIVOT HOLE EVIDENT OF CORROSION. CORROSION REMOVED AS PER CMM 20-11-02.

Part: HINGE — CORRODED (T/E FLAP)

RIGHT WING O/B FLAP MOUNTED HINGE PIVOT HOLE EVIDENT OF CORROSION. CORROSION REMOVED AS PER CMM 20-11-00.

Part: STRUCTURE — CORRODED (HORIZ STAB)

RT HORIZONTAL STABILIZER UPPER BARREL NUT NR 13 HAS BORE CORROSION EXCEEDING LIMITS. REPAIRED IAW EA 1-5510-78133.

Part: HINGE — CORRODED (T/E FLAP)

LT WING O/B FLAP, O/B FLAP MOUNTED HINGE PIVOT HOLE EVIDENT OF CORROSION. CORROSION REMOVED AS PER CMM 20-11-02.

Part: STRUCTURE — CORRODED (HORIZ STAB)

RT HORIZONTAL STABILIZER UPPER BARREL NUT NR 25 HAS BORE CORROSION EXCEEDING LIMITS. REPAIRED IAW EA 1-5510-78133.

Part: HINGE — CORRODED (T/E FLAP)

LEFT WING O/B FLAP, I/B FLAP MOUNTED HINGE ACTUATOR HOLE EVIDENT OF CORROSION. REMOVAL & REPAIR. REFER TO EO E1-5750-7-5002 CI. PT 1.

Part: STUD — CORRODED (RT AILERON)

RIGHT WING O/B AILERON ACTUATOR MOUNTING LWR I/B & O/B MOUNTING STUDS FOUND CORRODED. RT WING O/B AILERON ACTUATOR MOUNTING LWR I/B & O/B MOUNTING STUDS REMOVED AND REPLACED STUDS AS PER MM20-50-02.

Part: HINGE — CORRODED (T/E FLAP)

RIGHT WING O/B FLAP MOUNTED HINGE ACTUATOR HOLE EVIDENT OF CORROSION. CORROSION REMOVED AS PER CMM 20-11-02.

Part: STRUCTURE — CORRODED (HORIZ STAB)

RT HORIZONTAL STABILIZER UPPER BARREL NUT NR 23 HAS BORE CORROSION EXCEEDING LIMITS. REPAIRED IAW EA 1-5510-78133.

Part: SEAT TRACK — CORRODED (FUSELAGE)

MAIN DECK, ALONG STA 1331 TO STA 1351 RBL 107.25 SEAT TRACK FOUND CORRODED. SEAT TRACK REPAIRED AS PER SRM 53-70-00 FIG. 1 VOL I. REPAIR SEAT TRACK FABRICATED AS PER DRAWING AEA 7532. MAJOR REPAIR PER GMM 6-2-100.

Part: BULKHEAD — CRACKED (FUSELAGE)

CENTER CARGO HAS CRACK ON BULKHEAD AT STA 184 X=5. REPAIRED AS PER SRM 53-00-01, VOL I, FIG. 10.

Part: HINGE — CORRODED (T/E FLAP)

RIGHT WING O/B FLAP I/B FLAP MOUNTED HINGE PIVOT HOLE EVIDENT OF CORROSION. CORROSION REMOVED AS PER CMM 20-11-02.

Part: HINGE — CORRODED (T/E FLAP)

RIGHT WING O/B FLAP I/B FLAP MOUNTED HINGE ACTUATOR HOLE EVIDENT OF CORROSION. CORROSION REMOVED AS PER CMM 20-11-02.

Part: SKIN PANEL — CORRODED (HORIZ STAB) · airframe 44,668 hrs · 9,069 cycles

RIGHT HORIZONTAL STABILIZER UPPER BARREL NUT NR 12 HAS BORE CORROSION EXCEEDING LIMITS. BARREL NUT BORE NR 12 RIGHT, REPAIRED IAW EA 1-5510-78133 ATTACHMENT 13. HORIZONTAL STABILIZER BARREL NUT BORE REWORK/ REPAIR AD 2003-22-08. MAJOR REPAIR AS PER GMM 6-2-100.

Part: SPLICE — CRACKED (RT WING) · airframe 44,668 hrs · 9,069 cycles

RIGHT WING I/B FLAP, I/B ACTUATOR ENCLOSURE CUTOUT FOUND FUSELAGE STIFFENER CRACKED. RIGHT WING I/B FLAP, I/B ACTUATOR ENCLOSURE CUTOUT CRACK SPLICE REMOVED AND NEW SPLICE INSTALLED AS PER SRM 51-33-01 VOL II & SRM 51-35-01 VOL II, NEW SPLICE PART NUMBER: FX AEA 7243-502 FABRICATED AS PER DRAWING AEA 7243.

Part: FLOOR SUPPORT — CRACKED (FUSELAGE) · airframe 44,668 hrs · 9,069 cycles

CENTER CARGO COMPARTMENT, STA 1841 FLOOR SUPPORT AT X-15 FOUND CRACK AS MARKED. CENTER CARGO COMPARTMENT, STA 1841 FLOOR SUPPORT AT X-15 REMOVED AS PER SRM 51-31-01 VOL II. FLOOR SUPPORT FABRICATED AS PER DWG AGA 7170 AND INSTALLED NEW FABRICATED FLOOR SUPPORT AS PER SRM 51-31-01 VOL II. MINOR REPAIR AS PER GMM 6-2-100.

Part: PANEL — CORRODED (HORIZONTAL STAB) · airframe 44,668 hrs · 9,069 cycles

LT HORIZONTAL STABILIZER UPPER BARREL NUT NR 35 HAS BORE CORROSION EXCEEDING LIMITS. BARREL NUT BORE NR 35 LT REPAIRED IAW EA 1-5510-78133 ATTACHMENT 10, HORIZONTAL STABILIZER BARREL NUT BORE REWORK/ REPAIR AD 2003-22-08. MAJOR REPAIR AS PER GMM 6-2-100.

Part: FITTING — CRACKED (LT WING FLAPS) · airframe 44,668 hrs · 9,069 cycles

LT WING O/B FLAP HAS CRACK ON STRUCTURE AT STOP BOLT. LT WING O/B FLAP CRACKED STOP FITTING REMOVED. NEW FITTING HOLES TRANSFERRED AND INSTALLED AS PER SRM 51-33-01 AND 51-31-01 VOL II. MAJOR CLASSIFICATION AS PER GMM 6-2-100.

Part: PANEL — CORRODED (HORIZONTAL STAB) · airframe 44,668 hrs · 9,069 cycles

RIGHT HORIZONTAL STABILIZER UPPER BARREL NUT NR 32 HAS BORE CORROSION EXCEEDING LIMITS. BARREL NUT BORE NR 32 RIGHT REPAIRED IAW EA 1-5510-78133 ATTACHMENT 21, HORIZONTAL STABILIZER BARREL NUT BORE REWORK/ REPAIR AD 2003-22-08. MAJOR REPAIR AS PER GMM 6-2-100.

Part: PANEL — CORRODED (HORIZONTAL STAB) · airframe 44,668 hrs · 9,069 cycles

LEFT HORIZONTAL STABILIZER UPPER BARREL NUT NR 29 HAS BORE CORROSION EXCEEDING LIMITS. BARREL NUT BORE NR 29 LEFT REPAIRED IAW EA 1-5510-78133 ATTACHMENT 7, HORIZONTAL STABILIZER BARREL NUT BORE REWORK/ REPAIR AD 2003-22-08. MAJOR REPAIR AS PER GMM 6-2-100.

Part: PANEL — CORRODED (HORIZONTAL STAB) · airframe 44,668 hrs · 9,069 cycles

LEFT HORIZONTAL STABILIZER UPPER BARREL NUT NR 33 HAS BORE CORROSION EXCEEDING LIMITS. BARREL NUT BORE NR 33 LEFT REPAIRED IAW EA 1-5510-78133 ATTACHMENT 09, HORIZONTAL STABILIZER BARREL NUT BORE REWORK/ REPAIR AD 2003-22-08. MAJOR REPAIR AS PER GMM 6-2-100.

Part: PANEL — CORRODED (HORIZONTAL STAB) · airframe 44,668 hrs · 9,069 cycles

LT HORIZONTAL STABILIZER UPPER BARREL NUT NR 27 HAS BORE CORROSION EXCEEDING LIMITS. BARREL NUT BORE NR 27 LT REPAIRED IAW EA 1-5510-78133 ATTACHMENT 6, HORIZONTAL STABILIZER BARREL NUT BORE REWORK/ REPAIR AD 2003-22-08. MAJOR REPAIR AS PER GMM 6-2-100.

Part: PANEL — CORRODED (HORIZONTAL STAB) · airframe 44,668 hrs · 9,069 cycles

LEFT HORIZONTAL STABILIZER UPPER BARREL NUT NR 31 HAS BORE CORROSION EXCEEDING LIMITS. BARREL NUT BORE NR 31 LT REPAIRED IAW EA 1-5510-78133 ATTACHMENT 08, HORIZONTAL STABILIZER BARREL NUT BORE REWORK/ REPAIR AD 2003-22-08. MAJOR REPAIR AS PER GMM 6-2-100.

Part: PANEL — CORRODED (HORIZONTAL STAB) · airframe 44,668 hrs · 9,069 cycles

RIGHT HORIZONTAL STABILIZER UPPER BARREL NUT NR 12 HAS BORE CORROSION EXCEEDING LIMITS. BARREL NUT BORE NR 12 RT REPAIRED IAW EA 1-5510-78133 ATTACHMENT 13, HORIZONTAL STABILIZER BARREL NUT BORE REWORK/ REPAIR AD 2003-22-08. MAJOR REPAIR AS PER GMM 6-2-100.

Part: PANEL — CORRODED (HORIZONTAL STAB) · airframe 44,668 hrs · 9,069 cycles

RIGHT HORIZONTAL STABILIZER UPPER BARREL NUT NR 30 HAS BORE CORROSION EXCEEDING LIMITS. BARREL NUT BORE NR 30 RT REPAIRED IAW EA 1-5510-78133 ATTACHMENT 20, HORIZONTAL STABILIZER BARREL NUT BORE REWORK/ REPAIR AD 2003-22-08. MAJOR REPAIR AS PER GMM 6-2-100.

Part: PANEL — CORRODED (HORIZONTAL STAB) · airframe 44,668 hrs · 9,069 cycles

RIGHT HORIZONTAL STABILIZER UPPER BARREL NUT NR 20 HAS BORE CORROSION EXCEEDING LIMITS. BARREL NUT BORE NR 20 RT REPAIRED IAW EA 1-5510-78133 ATTACHMENT 16, HORIZONTAL STABILIZER BARREL NUT BORE REWORK/ REPAIR AD 2003-22-08. MAJOR REPAIR AS PER GMM 6-2-100.

Part: PANEL — CORRODED (HORIZONTAL STAB) · airframe 44,668 hrs · 9,069 cycles

RIGHT HORIZONTAL STABILIZER UPPER BARREL NUT NR 18 HAS BORE CORROSION EXCEEDING LIMITS. BARREL NUT BORE NR 18 RT REPAIRED IAW EA 1-5510-78133 ATTACHMENT 15, HORIZONTAL STABILIZER BARREL NUT BORE REWORK/ REPAIR AD 2003-22-08. MAJOR REPAIR AS PER GMM 6-2-100.

Part: LONGERON — CRACKED (FUSELAGE) · airframe 44,668 hrs · 9,069 cycles

MAIN DECK, AT STA 1219 LT FRAME TO FLOORBEAM INTERSECTION AT LONGERON 27 LEFT FOUND CRACKED. MAIN DECK, DISCREPANT LONGERON AT STA 1219 LT L-27 REMOVED AND REPLACED WITH NEW LONGERON: AEA 0435U503. NEW LONGERON LOCATED AND INSTALLED AS PER DRAWING AEA7605. MAJOR REPAIR AS PER GMM6-2-100.

Part: STRUCTURE — CORRODED (HORIZONTAL STAB)

RT HORIZONTAL STABILIZER UPPER BARREL NUT NR 22 HAS BORE CORROSION EXCEEDING LIMITS. REPAIRED IAW EA 1-5510-78133.

Part: SKIN — CORRODED (HORIZ STAB)

RT HORIZONTAL STABILIZER UPPER BARREL NUT NR 28 HAS BORE CORROSION EXCEEDING LIMITS. REPAIRED IAW EA 1-5510-78133.

Part: PANEL — CORRODED (HORIZONTAL STAB) · airframe 44,668 hrs · 9,069 cycles

RIGHT HORIZONTAL STABILIZER UPPER BARREL NUT NR 16 HAS BORE CORROSION EXCEEDING LIMITS. BARREL NUT BORE NR 16 RIGHT REPAIRED IAW EA 1-5510-78133 ATTACHMENT 14, HORIZONTAL STABILIZER BARREL NUT BORE REWORK/ REPAIR AD 2003-22-08. MAJOR REPAIR AS PER GMM 6-2-100.

Part: PANEL — CORRODED (HORIZONTAL STAB) · airframe 44,668 hrs · 9,069 cycles

LEFT HORIZONTAL STABILIZER UPPER BARREL NUT NR 23 HAS BORE CORROSION EXCEEDING LIMITS. BARREL NUT BORE NR 23 LT REPAIRED IAW EA 1-5510-78133 ATTACHMENT 4, HORIZONTAL STABILIZER BARREL NUT BORE REWORK/ REPAIR AD 2003-22-08. MAJOR REPAIR AS PER GMM 6-2-100.

Part: PANEL — CORRODED (HORIZONTAL STAB) · airframe 44,668 hrs · 9,069 cycles

LEFT HORIZONTAL STABILIZER UPPER BARREL NUT NR 25 HAS BORE CORROSION EXCEEDING LIMITS. BARREL NUT BORE NR 25 LT REPAIRED IAW EA 1-5510-78133 ATTACHMENT 5, HORIZONTAL STABILIZER BARREL NUT BORE REWORK/ REPAIR AD 2003-22-08. MAJOR REPAIR AS PER GMM 6-2-100.

Part: CHANNEL — CORRODED (FUSLAGE) · airframe 44,668 hrs · 9,069 cycles

AFT CARGO HAS LONGERON U-CHANNEL AT STA 1954 LONGERON 43R WITH CORROSION. AFT CARGO LONGERON 43R U-CHANNEL REMOVED AND REPLACED NEW FABRICATED AS PER DWG NGA 6313 AT STA 1954.

Part: PANEL — CORRODED (HORIZONTAL STAB) · airframe 44,668 hrs · 9,069 cycles

LEFT HORIZONTAL STABILIZER UPPER BARREL NUT NR 1 HAS BORE CORROSION EXCEEDING LIMITS. BARREL NUT BORE NR 01 LT REPAIRED IAW EA 1-5510-78133 ATTACHMENT 01, HORIZONTAL STABILIZER BARREL NUT BORE REWORK/ REPAIR AD 2003-22-08. MAJOR REPAIR AS PER GMM 6-2-100.

Part: SEAT TRACK — CORRODED (ZONE 200) · airframe 44,668 hrs · 9,069 cycles

MAIN DECK, BETWEEN STA 495 AND STA 500 RBL 63.5 SEAT TRACK CROWN. FOUND CORRODED. MAIN DECK STATION 495 TO 515 RBL 63.5, CORRODED SEAT TRACK REMOVED AND NEW SEAT TRACK P/N: ACA7731-504 INSTALLED AS PER SRM 51-33-01 VOL II.

Part: SEAT TRACK — CORRODED (FUSELAGE) · airframe 44,668 hrs · 9,069 cycles

MAIN DECK, BETWEEN STA 804 AND STA 841 LBL 107.25 SEAT TRACK CROWN AND BASE FOUND CORRODED. CORROSION ON SEAT TRACK BETWEEN STA 804 TO 841 LBL 107 REMOVED & FOUND EXCEED LIMIT AS PER SRM 53-70-00 FIG 3 VOL I. DISCREPANT SEAT TRACK TRIM-OUT FROM STA 765 TO 889 LBL 107 AS PER SRM 53-70-00 FIG 3 VOL I. NEW SEAT TRACK AND SPLICE ANGLE REWORKED FROM S4929148-7075T6511 AND S4932154-7075T6511 AS PER SRM 53-70-00 FIG 1 VOL I. SPLICE PLATE FABRICATED FROM 7075T6-0.05 AS PER SRM 53-70-00 FIG 1 VOL I. NEW SEAT TRACK AND REPAIR PARTS LOCATED AND INSTALLED AS PER SRM 53-70-00 FIG 1 VOL I. MAJOR REPAIR AS PER GMM 6-2-100.

Part: SEAT TRACK — CORRODED (FUSELAGE) · airframe 44,668 hrs · 9,069 cycles

MAIN DECK, ALONG STA 812 TO STA 855 LBL 8.5 SEAT TRACK CROWN FOUND CORRODED. CORROSION ON SEAT TRACK CROWN AT STA 812 TO 855 LBL 8.5 REMOVED & FOUND EXCEED LIMIT AS PER SRM 53-70-00 FIG 3 VOL I. DISCREPANT SEAT TRACK TRIM-OUT FROM STA 800 TO 869 LBL 8.5 AS PER SRM 53-70-00 FIG 1 VOL I. REPAIR PARTS REWORKED FROM S4929147- 7075T6511, S4932154-7075T6511 & FABRICATE SPLICE PLATE FROM 7075T6-0.050 AS PER SRM 53-70-00 FIG 1 VOL I. HFEC CARRIED OUT ON TRIM-OUT AREA & FOUND NO CRACK EVIDENT. REPAIR PARTS REPROTECTED AS PER SRM 51-21-01 VOL II & INSTALLED AS PER SRM 53-70-00 FIG 1 VOL I. MAJOR REPAIR AS PER GMM 6-2-100 AND SRM 51-90-01 FIG 1 VOL II.

Part: SEAT TRACK — CORRODED (FUSELAGE) · airframe 44,668 hrs · 9,069 cycles

MAIN DECK, AT STA 889 RBL 75.25 SEAT TRACK CROWN FOUND CORRODED. MAIN DECK STA 869 TO 909 RBL 75.25 CORROSION SEAT TRACK REPAIRED AS PER EA 1-3620-80387. PNEUMATIC SYSTEMS - FUSELAGE PNEUMATIC OVERHEAT DETECTOR - MOUNTING BRACKET INSTALLED. CLASSIFIED MINOR ALTERNATION AS PER GMM 6-2-100.

Part: SEAT TRACK — CORRODED (FUSELAGE) · airframe 44,668 hrs · 9,069 cycles

MAIN DECK, AT STA 889 LBL 75.25 SEAT TRACK CROWN FOUND CORRODED. MAIN DECK, STA 869 TO STA 909 LBL 75.25 CORROSION SEAT TRACK REMOVED AND REPAIRED AS PER SRM 53-70-00 VOL II. REPAIR SEAT TRACK AND SPLICE FABRICATED AS PER SRM 53-70-00 VOL II FIG 1. CLASSIFIED AS MAJOR REPAIR PER GMM 6-1-100.

Part: SEAT TRACK — CORRODED (FUSELAGE) · airframe 44,668 hrs · 9,069 cycles

MAIN DECK, ALONG STA 1341 TO STA 1365 RBL 75.25 SEAT TRACK FOUND CORRODED. MAIN DECK STA 1341 TO 1365 RBL 75.25 CORROSION SEAT TRACK REPAIRED AS PER SRM 53-70-00 FIG 1 VOL I. REPAIR SEAT TRACK PART FABRICATED AS PER SRM 53-70-00 FIG 1 VOL I. CLASSIFIED MAJOR REPAIR GMM 6-2-100.

Part: PANEL — CORRODED (HORIZONTAL STAB) · airframe 44,668 hrs · 9,069 cycles

LEFT HORIZONTAL STABILIZER UPPER BARREL NUT NR 21 HAS BORE CORROSION EXCEEDING LIMITS. BARREL NUT BORE NR 21 LT REPAIRED IAW EA 1-5510-78133 ATTACHMENT 3, HORIZONTAL STABILIZER BARREL NUT BORE REWORK/ REPAIR AD 2003-22-08. MAJOR REPAIR AS PER GMM 6-2-100.

Part: SEAT TRACK — CORRODED (FUSELAGE) · airframe 44,668 hrs · 9,069 cycles

MAIN DECK, AT STA 822 RBL 44.5 SEAT TRACK CROWN FOUND CORRODED. CORROSION ON SEAT TRACK CROWN STA 822 RBL 44.5 REMOVED & FOUND EXCEED LIMIT AS PER SRM 53-70-00 FIG 3 VOL I. DISCREPANT SEAT TRACK TRIM-OUT FROM STA 815 TO 832 RBL 44.5 AS PER SRM 53-70-00 FIG 1 VOL I. REPAIR PARTS REWORKED FROM S4929147-7075T6511 AND S4932154-7075T6511 AND FABRICATED SPLICE PLATE FROM 7075T6-0.050 AS PER SRM 53-70-00 FIG 1 VOL I. REPAIR PARTS REPROTECTED AS PER SRM 51-21-01 VOL II AND INSTALLED AS PER SRM 53-70-00 FIG 1 VOL I. FLOOR PANEL INSTALLED ALONG STA 822 RBL 44.5 AS PER AMM 53-21-04. REPAIR CLASSIFIED MAJOR AS PER GMM 6-2-100 AND SRM 51-90-01 FIG 1 VOL II.

Part: SEAT TRACK — CORRODED (FUSELAGE) · airframe 44,668 hrs · 9,069 cycles

MAIN DECK, ALONG STA 822 TO STA 835 LBL 27.5 SEAT TRACK CROWN FOUND CORRODED. MAIN DECK, SEAT TRACK CROWN CORROSION ALONG STA 822 TO STA 835 LBL 27.5. REMOVED AND FOUND EXCEED LIMITS AS PER SRM 53-70-00 FIG 3 VOL I. DISCREPANT SEAT TRACK TRIM OUT FROM STA 815 TO 850 LBL 27.5 AS PER SRM 53-70-00 FIG 1 VOL I AND REPROTECTED AS PER SRM 51-21-01 VOL II. HFEC CARRIED OUT AND FOUND NO CRACK EVIDENT. REPAIR PARTS REWORKED FROM S4932154-707513511 & S4929147-7075T6511 AND FABRICATED SPLICE PLATE FROM 7075T6 (0.05) AS PER SRM 53-70-00 FIG 1 VOL I. REPAIR PARTS REPROTECTED AS PER SRM 51-21-01 VOL II AND INSTALLED AS PER SRM 53-70-00 FIG 1 VOL I.

Part: SEAT TRACK — CORRODED (FUSELAGE) · airframe 44,668 hrs · 9,069 cycles

CABIN, STA 1961 RIGHT SEAT TRACK FOUND CORROSION AS MARKED AS RBL 77. CORROSION ON SEAT TRACK AT STA 1961 RBL 77 REMOVED & FOUND EXCEED LIMIT AS PER SRM 53-70-00 FIG 3 VOL I. DISCREPANT SEAT TRACK TRIM-OUT AT STA 1831 RBL 107 AS PER SRM 53-10-00 FIG 1 VOL I. NEW SEAT TRACK REWORKED FROM AFA 7789-542 AS PER SRM 53-70-00 FIG 7 VOL I. SPLICE ANGLE REWORKED FROM S4932154-7075T6511. FABRICATED SPLICE PLATE AS PER SRM 53-70-00 FIG 1 VOL I. HOLES PICK UP ON NEW SEAT TRACK & REPAIR PARTS AS PER SRM 51-31-01 VOL II. NEW SEAT TRACK & REPAIR PARTS LOCATED & INSTALL AS PER SRM 53-20-00 FIG 1 VOL I. MAJOR REPAIR AS PER GMM 6-2-100.

Part: SEAT TRACK — CORRODED (FUSELAGE) · airframe 44,668 hrs · 9,069 cycles

MAIN DECK, ALONG STA 1817 TO STA 1887 LBL 27.5 SEAT TRACK FOUND CORRODED. CORROSION ALONG STA 1817 TO 1887 LBL 27.5 REMOVED & FOUND EXCEED LIMIT AS PER SRM 53-70-00 FIG 3 VOL I. DISCREPANT SEAT TRACK TRIM OUT AT STA 1791 LBL 27.5 AS PER SRM 53-70-00 FIG 1 VOL I. NEW SEAT TRACK AND SPLICE ANGLE REWORKED FROM S4929147-7075T6511 AND S4932154-7075T6511 AS PER SRM 53-70-00 FIG 1 VOL I. SPLICE PLATE FABRICATED FROM 7075T6-0.050 AS PER SRM 53-70-00 FIG 1 VOL I. NEW SEAT TRACK AND REPAIR PARTS LOCATED AND INSTALLED AS PER SRM 53-70-00 FIG 1 VOL I. CLASSIFIED MAJOR REPAIR AS PER GMM 6-2-100.

Part: PANEL — CORRODED (HORIZONTAL STAB) · airframe 44,668 hrs · 9,069 cycles

LEFT HORIZONTAL STABILIZER UPPER BARREL NUT NR 19 HAS BORE CORROSION EXCEEDING LIMITS. BARREL NUT BORE NR 19 LT REPAIRED IAW EA 1-5510-78133 ATTACHMENT 2, HORIZONTAL STABILIZER BARREL NUT BORE REWORK/ REPAIR AD 2003-22-08. MAJOR REPAIR AS PER GMM 6-2-100.

Part: SEAT TRACK — CORRODED (FUSELAGE) · airframe 44,668 hrs · 9,069 cycles

MAIN DECK, ALONG STA 1821 TO STA 1887 LBL 8.5 SEAT TRACK FOUND CORRODED. CORROSION ON SEAT TRACK ALONG STA 1821 TO 1887 LBL 8.5 REMOVED & FOUND EXCEED LIMITED AS PER SRM 53-70-00 FIG 3 VOL I. DISCREPANT SEAT TRACK TRIM-OUT AT STA 1811 LBL 8.5 AS PER SRM 53-70-00 FIG 1 VOL I. NEW SEAT TRACK REWORKED FROM S4929147-7075T6511 AS PER SRM 53-70-00 FIG 1 VOL I. SPLICE PLATE FABRICATED FROM 7075T6-0.050 AS PER SRM 53-70-00 FIG I. HOLES PICK-UP ON NEW SEAT TRACK & REPAIR PARTS AS PER SRM 51-31-01 VOL II. NEW SEAT TRACK AND REPAIR PARTS LOCATED AND INSTALL AS PER SRM 53-70-00 FIG 1 VOL I. MAJOR REPAIR AS PER GMM 6-2-100.

Part: BULKHEAD — CORRODED (FUSELAGE) · airframe 44,668 hrs · 9,069 cycles

AFT CARGO HAS EXFOLIATING CORROSION AT STA 1841 BULKHEAD LT SIDE X = 24. AFT CARGO AT STA 1841 BULKHEAD LT SIDE X:24 REPAIRED AREA AS PER SRM 53-00-01 VOL I FIG 10. MINOR REPAIR AS PER GMM 6-2-100.

Part: SEAT TRACK — CORRODED (FUSELAGE) · airframe 44,668 hrs · 9,069 cycles

MAIN DECK, AT STA 1831 RBL 27.5 SEAT TRACK CROWN AND BASE FOUND CORRODED. CORROSION ON SEAT TRACK AT STA 1831 RBL 27.5 REMOVED AND FOUND EXCEED LIMIT AS PER SRM 53-70-00 FIG 3 VOL I. DISCREPANT SEAT TRACK TRIM OUT AT STA 1811 RBL 27.5 AS PER SRM 53-70-00 FIG 1 VOL I. HFEC CARRIED AS PER DAC NDT SPM REV 11 PART 06-10-01- 001 ON TRIM-OUT AREA AND FOUND NO CRACK EVIDENT. NEW SEAT TRACK REWORKED FROM S4929147-7075T6511 AS PER SRM 53-70-00 FIG I VOL I. NEW SEAT TRACK AND REPAIR PARTS LOCATED AND INSTALLED AS PER AS PER SRM 53-70-00 FIG 1 VOL I. MAJOR REPAIR AS PER GMM 6-2-100.

Part: SEAT TRACK — CORRODED (FUSELAGE) · airframe 44,668 hrs · 9,069 cycles

MAIN DECK, ALONG STA 1821 TO STA 1887 RBL 8.5 SEAT TRACK FOUND CORRODED. CORROSION ON SEAT TRACK AT STA 1821 TO 1887 REMOVED & FOUND EXCEED LIMIT AS PER SRM 53-70-00 FIG 3 VOL I. DISCREPANT SEAT TRACK FROM STA 1811 TO 1887 RBL 8.5 TRIM OUT AS PER SRM 53-70-00 FIG 1 VOL I. HFEC CARRIED OUT ON TRIM-CUT AREA AS PER DAC NDT SPM REV 11 06-10-01-001 AND FOUND NO CRACK EVIDENT. NEW SEAT TRACK AND SPLICE ANGLE REWORKED FROM S4929147 AND S4932154 AS PER SRM 53-70-00 FIG I. NEW SEAT TRACK AND SPLICE ANGLE PAINTED AS PER SRM 51-21-01 VOL II. REPAIR PARTS LOCATED AND INSTALLED AS PER SRM 53-70-00 FIG 1 VOL I. MAJOR REPAIR AS PER GMM 6-2-100.

Part: PANEL — CORRODED (HORIZONTAL STABI) · airframe 44,668 hrs · 9,069 cycles

RIGHT HORIZONTAL STABILIZER UPPER BARREL NUT NR 36 HAS BORE CORROSION EXCEEDING LIMITS. BARREL NUT BORE NR 36 RIGHT REPAIRED IAW EA 1-5510-78133 ATTACHMENT 18, HORIZONTAL STABILIZER BARREL NUT BORE REWORK/ REPAIR AD 2003-22-08. MAJOR REPAIR AS PER GMM 6-2-100.

Part: SPLICE — CRACKED (FUSELAGE) · airframe 44,668 hrs · 9,069 cycles

CABIN STA 1661 TO 1681 LONGITUDINAL SPLICE AT L26 RIGHT FOUND 7 INCHES CRACKED AS MARKED. LONGITUDINAL SPLICE AT STA 1661 TO 1681 RIGHT L-26 REMOVED. NEW SPLICE FABRICATED FROM 1D0755T7150T6511 AS PER DRAWING AFA7181 AND CARRIED OUT FPI INSPECTION AS PER DPS 4.707 AND FOUND NO CRACK EVIDENT. FABRICATED SPLICE REPROTECTED AND PART MARK AFA7181-511 AS PER GMM 7-0-1001. FABRICATED SPLICE LOCATED AND INSTALLED BETWEEN STA 1661 TO 1681 RIGHT L-26 AS PER DRAWING NFA6310. CLASSIFIED MAJOR REPAIR AS PER GMM 6-2-100 AND SRM 51-90-01 FIG 1 VOL II.

Part: SPLICE — CRACKED (ZONE 200) · airframe 44,668 hrs · 9,069 cycles

CABIN, STA 1641-1661 RT LONGITUDINAL SPLICE AT L11 SUSPECT CRACKED AT FASTENERS HOLES AS MARKED. LONGITUDINAL SPLICE AT STA 1641 TO 1661 RT L-11 REMOVED NEW SPLICE, FABRICATED FROM 1D0755T7150T61511 AS PER DRAWING AFA7181. FPI INSPECTION CARRIED OUT AND FOUND NO EVIDENT OF CRACK. FABRICATED SPLICE REPROTECTED AND PART MARK: AFA 7181-509. FABRICATED SPLICE LOCATED AND INSTALLED BETWEEN STA 1641 TO 1661 RT L-11 AS PER DRAWING NFA6009.