N705AA

Part: SMOKE DETECTOR — UNSERVICEABLE (CARGO BAY)

MAIN CARGO FIRE LIGHT AND BELL CAME ON IN FLIGHT. REPLACED FAULTY SMOKE DETECTOR UNIT.

Part: INDICATOR — INOPERATIVE (AIRSPEED)

DISCREPANCY: F/O AIRSPEED INDICATOR INOP. CORRECTIVE ACTION: FOUND FOREIGN OBJECT IN AUXILIARY AND F/O PITOT PROBE. FLUSHED PER AMM 34-11-00. OPS CHECK GOOD

Part: SKIN — CORRODED (FUSELAGE) · corrosion level 2 · airframe 67,955 hrs · 31,504 cycles

DURING CPCP INSPECTION THE INSPECTOR FOUND LEVEL 2 CORROSION ON FUSELAGE SKIN BETWEEN BS 720E & 720F STRINGER 26L. THE CORROSION THROUGH THE SKIN WAS OVER LIMIT IAW SRM 53-30-01 FIG 1. THE ITEM HAS BEEN REPORTED FOR REQUESTING THE REPAIR APPROVAL DATA.

Part: SKIN — CORRODED (FUSELAGE) · corrosion level 2 · airframe 67,955 hrs · 31,504 cycles

DURING INSPECTION THE INSPECTOR PERFORMED VISUAL INSPECTION & FOUND LEVEL 2 CORROSION ON FUSELAGE SKIN OF BS 950D STRINGER 26L. THE CORROSION THROUGH THE SKIN WAS OVER LIMIT IAW SRM 53-30-01 FIG 1. THE ITEM HAS BEEN REPORTED FOR REQUESTING THE REPAIR APPROVAL DATA.

Part: SKIN — CORRODED (FUSELAGE) · corrosion level 2 · airframe 67,955 hrs · 31,504 cycles

DURING CPCP INSPECTION THE INSPECTOR PERFORMED VISUAL INSPECTION & FOUND LEVEL 2 CORROSION ON FUSELAGE SKIN OF BS 950B STRINGER 28L. THE CORROSION THROUGH THE SKIN WAS OVER LIMIT IAW SRM 53-30-01 FIG 1. THE ITEM HAS BEEN REPORTED FOR REQUESTING THE REPAIR APPROVAL DATA.

Part: PLATE — CORRODED (LT WING) · corrosion level 2 · airframe 67,955 hrs · 31,504 cycles

DURING PERFORMED C CHECK CORROSION WAS FOUND ON THE LT WING FRONT SPAR LOWER CHORD PLATE FROM WS 726 TO WS 734. DIMENSIONS OF CORROSION AREA 8 INCHES X 2 INCHES. AFTER THE CORROSION BLEND OUT, THE MIN REMAINING THICKNESS OF 0.031 INCH, ORIGINAL THICKNESS IS 0.177 INCH, WAS MEASURED. THE DAMAGE CONDITION HAD EXCEEDED THE ALLOWABLE LIMITATION IAW SRM 57-10-1 FIG 2 SHEET 6. THE ITEM HAS BEEN REPORTED FOR REQUESTING THE REPAIR APPROVAL DATE.

Part: SKIN — CORRODED (LT WING) · corrosion level 2 · airframe 67,955 hrs · 31,504 cycles

DURING PERFORMED C CHECK CORROSION WAS FOUND ON THE LT WING UPPER SKIN FROM WS 611.5 TO WS 613.5. DIMENSIONS OF CORROSION AREA 3 INCHES X 1.25 INCHES. AFTER THE CORROSION BLEND OUT THE MIN REMAINING THICKNESS OF 0.085 INCH, ORIGINAL THICKNESS IS 0.184 INCH, WAS MEASURED. THE DAMAGE CONDITION HAD EXCEEDED THE ALLOWABLE LIMITATION IAW SRM 57-30-1 FIG 1 SHEET 5. THE ITEM HAS BEEN REPORTED FOR REQUESTING THE REPAIR APPROVAL DATA.

Part: PLATE — CORRODED (LT WING) · corrosion level 2 · airframe 67,955 hrs · 31,504 cycles

DURING PERFORMED C CHECK CORROSION WAS FOUND ON THE LT WING FRONT SPAR LOWER CHORD PLATE FROM WS 701 TO WS 696. DIMENSIONS OF CORROSION AREA 5 INCHES X 1.5 INCHES. AFTER THE CORROSION BLEND OUT THE MIN REMAINING THICKNESS OF 0.126 INCH, ORIGINAL THICKNESS IS 0.189 INCH, WAS MEASURED. THE DAMAGE CONDITION HAD EXCEEDED THE ALLOWABLE LIMITATION IAW SRM 57-10-1 FIG 2 SHEET 6. THE ITEM HAS BEEN REPORTED FOR REQUESTING THE REPAIR APPROVAL DATE.

Part: PLATE — CORRODED (LT WING) · corrosion level 2 · airframe 67,955 hrs · 31,504 cycles

DURING PERFORMED C CHECK CORROSION WAS FOUND ON THE LT WING FRONT SPAR LOWER CHORD PLATE FROM WS 520 TO WS 526. DIMENSIONS OF CORROSION AREA 6 INCHES X 1.5 INCHES. AFTER THE CORROSION BLEND OUT THE MIN REMAINING THICKNESS OF 0.141 INCH, ORIGINAL THICKNESS IS 0.248 INCH, WAS MEASURED. THE DAMAGE CONDITION HAD EXCEEDED THE ALLOWABLE LIMITATION IAW SRM 57-10-1 FIG 2 SHEET 6. THE ITEM HAS BEEN REPORTED FOR REQUESTING THE REPAIR APPROVAL DATA.

Part: SKIN — CORRODED (FUSELAGE) · corrosion level 2 · airframe 67,955 hrs · 31,504 cycles

DURING INSPECTION THE INSPECTOR PERFORMED VISUAL INSPECTION & FOUND LEVEL 2 CORROSION ON FUSELAGE SKIN OF BS 950E+4 STRINGER 28L. THE CORROSION THROUGH THE SKIN WAS OVER LIMIT IAW SRM 53-30-01 FIG 1. THE ITEM HAS BEEN REPORTED FOR REQUESTING THE REPAIR APPROVAL DATA.

Part: SKIN — CORRODED (FUSELAGE) · corrosion level 2 · airframe 67,955 hrs · 31,504 cycles

DURING CPCP INSPECTION THE INSPECTOR FOUND LEVEL 2 CORROSION ON FUSELAGE SKIN BETWEEN BS 720B & 720C STRINGER 28L & 28R. THE CORROSION THROUGH THE SKIN WAS OVER LIMIT IAW SRM 53-30-01 FIG 1. THE ITEM HAS BEEN REPORTED FOR REQUESTING THE REPAIR APPROVAL DATA.

Part: PLATE — CORRODED (LT WING) · corrosion level 2 · airframe 67,955 hrs · 31,504 cycles

DURING PERFORMED C CHECK CORROSION WAS FOUND ON THE LT WING FRONT SPAR LOWER CHORD PLATE FROM WS 738.5 TO WS 742. DIMENSIONS OF CORROSION AREA IS 3.5 INCHES X 1.5 INCHES. AFTER THE CORROSION BLEND OUT THE MIN REMAINING THICKNESS OF 0.104 INCH, ORIGINAL THICKNESS IS 0.177 INCH, WAS MEASURED. THE DAMAGE CONDITION HAD EXCEEDED THE ALLOWABLE LIMITATION IAW SRM 57-10-1 FIG 2 SHEET 6. THE ITEM HAS BEEN REPORTED FOR REQUESTING THE REPAIR APPROVAL DATA.

Part: ENGINE — LEAKING (NR 3)

NR 3 ENGINE SHUTDOWN IN FLIGHT DUE TO POSSIBLE COMPRESSOR STALL FOLLOWED BY OIL LOSS. THE INLET & EXHAUST LOOKED OK, BUT EVIDENCE OF OIL LOSS FROM THE EXHAUST. NR 3 ENGINE HAS BEEN REMOVED & REPLACED. INSTALLED IAW AMM. PERFORMED OPS CHECK & HIGH POWER ASSURANCE RUN & LEAK CHECK. ALL CHECKED NORMAL. ACFT BACK IN SERVICE.

Part: ENGINE — LEAKING (NR 3)

NUMBER 3 ENG SHUT DOWN IN FLIGHT DUE TO POSSIBLE COMPRESSOR STALL, FOLLOWED BY OIL LOSS. THE INLET & EXHAUST LOOKED OK, BUT EVIDENCE OF OIL LOSS FROM THE EXHAUST. NR 3 ENG HAS BEEN R & R. INSTALLED IAW AMM. PERFORMED OPERATIONS CHECK & HIGH POWER ASSURANCE RUN & LEAK CHECK. ALL CHECKED NORMAL. ACFT BACK IN SERVICE. UPDATED ENG INFORMATION.

Part: WEB — CORRODED (FUEL CELL) · corrosion level 2 · airframe 65,509 hrs · 30,805 cycles

DURING PERFORMED 7C CHECK, CORROSION WAS FOUND ON CENTER FUEL TANK AFT VERTICAL WEB AT STATION BS 865, LBL 38, 39,WL 165-168 (DIMENSIONS OF CORROSION AREA:2 .3750" × 1.5"). AFTER BLEND OUT CORROSION, THE PENETRATION DEPTH WAS OVER LIMIT IAW SRM 57-10-01, PAGE 11 (REMAIN DEPTH:0.031", ORIGINAL DEPTH:0.056).

Part: STRUCTURE — CORRODED (FUEL CELL) · corrosion level 2 · airframe 65,509 hrs · 30,805 cycles

DURING PERFORMED 7C CHECK, CORROSION WAS FOUND ON CENTER FUEL TANK AFT LOWER EDGE AT STATION BS 865, LBL 54, WL 169 TO LBL 58 WL 171 ( DIMENSIONS OF CORROSION AREA:3.7500" × 1.7500"). AFTER BLEND OUT CORROSION, THE PENETRATION DEPTH (0.280") WAS OVER LIMIT IAW SRM 53-00-00, PAGE 00. THE ITEM HAS BEEN REPORTED TO DER FOR REQUESTING THE REPAIR APPROVAL DATA.

Part: SKIN — CORRODED (ZONE 100) · corrosion level 2 · airframe 65,509 hrs · 30,805 cycles

DURING PERFORMED 7C CHECK, CORROSION WAS FOUND ON FUSELAGE LOWER LOBE SKIN PANEL AT STATION BS 1010, WL 148 BETWEEN S-28R AND S-29R. (DIMENSIONS OF CORROSION AREA:5 3/8" × 2"). AFTER BLEND OUT CORROSION, THE PENETRATION DEPTH (0.019") WAS OVER LIMIT IAW SRM 53-30-1, PAGE 2C.

Part: STRUCTURE — CORRODED (FUEL CELL) · airframe 65,509 hrs · 30,805 cycles

PERFORMED 7C CHECK, CORROSION WAS FOUND ON CENTER FUEL TANK AFT LOWER EDGE AT BS 865, LBL 54, WL 169 TO LBL 58, WL 171 (DIMENSIONS OF CORROSION AREA: 3.7500" × 1.7500"). AFTER BLEND OUT CORROSION, THE PENETRATION DEPTH (0.280") WAS OVER LIMIT IAW SRM 53-00-00, PAGE 00. THE ITEM HAS BEEN REPORTED TO DER FOR REQUESTING THE REPAIR APPROVAL DATA.

Part: STRAP — CORRODED (ZONE 500) · corrosion level 2 · airframe 63,036 hrs · 30,069 cycles

HE CORROSION WAS FOUND AT TENSION STRAP OF LT OTBD MID FLAP AT WBL 452 DURING 6C CHECK. THE ORIGINAL THICKNESS OF THE STRAP IS 0.225". AFTER BLEND OUT, THE DIMENSION OF THE CORROSION AREA IS 2.5" (LENGTH) X 2" (WIDTH) AND REMAINDER THICKNESS IS 0.172", IAW SRM 57-50-1, FIG 3, THE DAMAGE IS OUT OF ALLOWABLE LIMIT. THE TENSION STRAP WILL BE REPLACED.

Part: SPLICE — CORRODED (LT WING TE FLAP) · corrosion level 2 · airframe 63,036 hrs · 30,069 cycles

THE EXFOLIATION CORROSION IS FOUND AT LT I/B MID FLAP CHORD SPLICE AT WBL 193 DURING 6C CHECK. THE ORIGINAL THICKNESS OF THE CHORD SPLICE IS 0.072”. AFTER BLENT OUT, THE DIMENSION OF THE CORROSION AREA IS 3" (LENGTH) X 1 (WIDTH) AND REMAINDER THICKNESS IS 0.039". IAW SRM 57-50-1 FIG 3, THE DAMAGE IS OUT OF LIMIT. THE CHORD SPLICE WILL BE REPLACED WITH NEW ONE.

Part: BEAM — CORRODED (LT HORIZONTAL) · corrosion level 2 · airframe 63,036 hrs · 30,069 cycles

LT HORIZONTAL STAB TRAILING LOWER BEAM UPPER SURFACE STA 66 TO 70 HAD EXFOLIATION CORROSION. ORIGINAL THICKNESS WAS 0.091". AFTER CORROSION REMOVED, THE REMAINED THICKNESS WAS 0.025", AREA WAS 4" X 1". IT'S BEYOND LIMITED IAW SRM 55-10-1, PAGE 1, NOTE B. CORROSION LEVEL WAS 2.

Part: SPAR — CORRODED (RT WING) · corrosion level 2 · airframe 63,036 hrs · 30,069 cycles

HEAVY CORROSION ON RT WING INBD MIDFLAP REAR SPAR LOWER CHORD AT WBL142, ORIGINAL THICKNESS 0.121". AFTER CORROSION REMOVED, THE REMAINED THICKNESS WAS 0.051", AREA WAS 3" X 1". IT'S BEYOND LIMITED IAW SRM 57-50-1, PAGE 8. REPAIR METHOD REF SRM 57-50-2, PAGE 9 AND 51-40-4 FIG 1. THE CORROSION LEVEL WAS LEVEL 2.

Part: BEAM — CORRODED (HORIZONTAL STAB) · corrosion level 2 · airframe 63,036 hrs · 30,069 cycles

RT HORIZONTAL STAB TRAILING LOWER BEAM SURFACE STA 220 TO 222 HAD EXFOLIATION CORROSION. ORIGINAL THICKNESS IS 0.105". AFTER CORROSION REMOVED, THE REMAINED THICKNESS WAS 0.065", AREA WAS 2.75" X 1". IT'S BEYOND LIMITED IAW SRM 55-10-1, PAGE 1, NOTE B. CORROSION LEVEL WAS 2.

Part: SPAR — CORRODED (LT WING TE FLAP) · corrosion level 2 · airframe 63,036 hrs · 30,069 cycles

THE EXFOLIATION CORROSION IS FOUND AT LT INBD MID FLAP AFT SPAR LOWER CHORD AT WBL 82, DURING 6C CHECK. THE ORIGINAL THICKNESS OF THE CHORD IS 0.125". AFTER BLENT OUT, THE DIMENSION OF THE CORROSION AREA IS 3" (LENGTH) X 1" (WIDTH) AND REMAINDER THICKNESS IS 0.083" IAW SRM 57-50-1, FIG 3, THE DAMAGE IS OUT OF ALLOWABLE LIMIT. REPAIR THE SPAR CHORD IAW SRM 57-50-2 FIG 5 & 51-40-2, FIG 1.

Part: BEAM — CORRODED (HORIZONTAL STAB) · corrosion level 2 · airframe 63,036 hrs · 30,069 cycles

LT HORIZONTAL STAB TRAILING LOWER BEAM LOWER SURFACE STA96 TO 97 HAD EXFOLIATION CORROSION. ORIGINAL THICKNESS IS 0.120". AFTER CORROSION REMOVED, THE REMAINED THICKNESS WAS 0.078" AREA WAS 2.25" X 1.5". IT'S BEYOND LIMIT IAW SRM 55-10-1, PAGE 1, NOTE B. CORROSION LEVEL IS 2.

Part: SEAT TRACK — CORRODED (BS 640) · corrosion level 2 · airframe 63,036 hrs · 30,069 cycles

DURING PERFORMED CPCP CARD NR C53-224-01 PART 1 OF 3 FOR MAIN DECK CARGO COM'P FLOOR STRUCTURE, THE SEAT TRACK AT STA BS 640+3 AND BS 640+10 LBL. 0 WAS FOUND LEVEL 2 CORROSION. REPAIR METHOD IAW SRM 53-10-5 FOR FURTHER PROCESSING.

Part: SKIN — CORRODED (RT WING TE FLAP) · corrosion level 2 · airframe 63,036 hrs · 30,069 cycles

HEAVY CORROSION ON RT WING INBD MIDFLAP UPPER EXTERNAL SURFACE, AT WBL128, FWD OF FLAP T/E ABOUT 22.5". ORIGINAL THICKNESS IS 0.054" AFTER CORROSION REMOVE, REMAIN THICKNESS IS 0" IAW SRM 57-50-1, PAGE 8, AREA ABOUT 1" X 1.3750". REPAIR METHOD SRM 57-50-4, FIG-8. CORROSION LEVEL WAS LEVEL 2.

Part: SKIN PANEL — CORRODED (ZONE 100) · corrosion level 2 · airframe 62,911 hrs · 30,031 cycles

DURING PERFORMED 6C-CHECK FOUND FUSELAGE EXTERIOR SKIN CORRODED (LEVEL 2) AT BS 1066 BETWEEN S-27L AND S-28L, IAW SRM 53-30-1, PAGE 2A PENETRATED DEPTH OUT OF LIMIT.

Part: SPAR — CORRODED (LT WING) · corrosion level 2 · airframe 60,678 hrs · 29,375 cycles

DURING 5C CHECK AND INSPECTION, CORROSION WAS FOUND ON LT WING REAR SPAR LWR SKIN AT WS706 DIMENSION AREA 1.3 INCH X 1.7 INCH. AFTER CORROSION BLENDOUT FOUND MAX BLDOUT DEPT IS BEYOND LIMITATIONS. NO REINFORCEMENT REQUIRED, REMOVE ALL FASTENERS BLEND SMOOTH, INSTALLED ALL LOCK FASTENERS IAW EI-727-090702.

Part: STRUCTURE — CORRODED (BS 950)

DURING 5C CHECK AND INSP, CORROSION WAS FOUND BETWEEN BS 950C AND 950E AND STR 28L AND 28R. REPAIRED IAW EI-727-090705.

Part: KEELBEAM — CORRODED (BS 740) · corrosion level 2 · airframe 60,678 hrs · 29,375 cycles

DURING 5C CHECK AND INSP, CORROSION WAS FOUND ON RT KEEL BEAM INBD FLANGE AFT OF BS740. AFTER BLENDOUT AND MEASURED ORIGINAL THICKNESS BLEND OUT EXCEED LIMITS. REPAIRED CORROSION IAW EI-727-090703 AREA WAS BLEND OUT AND TREATED WITH ALODINE AND DOUBLE PRIME ALL ALUMINUM AREAS.

Part: SPAR — CORRODED (WING) · corrosion level 2 · airframe 60,678 hrs · 29,375 cycles

DURING 5C-CHECK AND INPS CORROSION WAS FOUND ON RT AND LT WING FRONT SPAR CHORD PLATE LWR SURFACE. AFTER BLEND OUT THE MAX LOSS OF MATERIAL THICKNESS WAS BEYOND THE ALLOWABLE LIMIT IAW SRM. FABRICATED AN INTERNAL REPAIR STRAP IAW EI-727-090701 HFEC ACCESSED FASTENER AND BLEND OUT AREA.

Part: SKIN — DAMAGED (BS 1009-1045) · corrosion level 2 · airframe 60,678 hrs · 29,375 cycles

DURING 5C CHECK AND INSP, CORROSION WAS FOUND ON THE SKIN INTERNAL SURFACE WHICH WAS UNDER THE PREVIOUS SKIN REPAIR DOUBLER FROM BS 1009 TO BS 1045 AND BETWEEN S-27L AND S-28R. REPAIRED IAW EI-727-090704.

Part: PUMP — MALFUNCTIONED (FUEL SYS)

CRUISE NR 1 ENG STARTED TO SPOOL DOWN OTHER PARAMETERS ARE NORMAL, PERFORMED IN-FLIGHT START CHECKLIST SEVERAL TIMES INCLUDING RESETTING SWITCHES, NO LIGHT OFF. ACFT DIVERTED AND THE CREW PERFORMED ENG INSPECTION AND START ON NR 1 ENG HIGH IGNITION SYS, ENGINE STARTED OK IN GROUND. START IGNITION NR 1 FROM HIGH-ENERGY FAIL IN FLIGHT POSITION. DEFERRED NR 1 ENG IGNITION IAW MEL 74-1 AND 705 CONTINUED SERVICE. MAINT REMOVED AND REPLACED NR 1 ENG FUEL PUMP IAW MM 73-11-1, PURGE FUEL SYSTEM, PS4, PT7, AND P AND D VALVE CHECK FOR MOISTURE. PERFORMED FULL POWER ENGINE RUN AND LEAK CHECK SYSTEM OPERATIONAL CHECK, OK. (K)

Part: STRINGER — CRACKED (BS940-945)

THE AIRCRAFT INPUT FOR 4C CHECK AND CPCP ON SEPT 3, 2007. DURING CPCP, THE INSPECTOR PERFORMED VISUAL INSPECTION AND FOUND 5 INCH CRACK BOTH ON LT AND RT FUSELAGE STRINGER S18A BETWEEN BS940 AND BS945 ON SEPT 21, 2007. A PROPOSAL WAS INITIALLY SUBMITTED ON SEPT 22. AFTER REPAIR TO THE STRINGERS, FORM 337 WILL BE SUBMITTED TO FAA FOR FINAL RESULT OF CORRECTIVE ACTIONS DETAIL. (K)

Part: TRUNNION — DAMAGED (RT MLG)

SEVERE DAMAGE TO THE AFT TRUNNION SPUD AREA.

Part: LIGHT — DEFECTIVE (AFT STAIRS)

DFW - DURING OVERNIGHT MAINTENANCE, AFT STAIR EMERGENCY LIGHTING INOPERATIVE. REPLACED EMERGENCY EXIT LIGHT ASSEMBLY. SYSTEM GROUND CHECKED NORMAL OPERATION. (M)

Part: SKIN — CORRODED (BS 833)

TUL - FOUND CORROSION ON LOWER CENTER TANK OUTER SKIN STATION 833 RBL 20-24. REMOVED CORROSION AND REPAIRED AREA PER ESO 11697, DATED 5-7-99 PAGES 1/2. (M)

Part: LIGHT — INOPERATIVE (CABIN)

TPA - DURING OVERNIGHT MAINTENANCE, AFT STAIR EMERGENCY EXIT LIGHT INOPERATIVE. REPLACED AFT STAIR EMERGENCY EXIT LIGHT ASSEMBLY. SYSTEM GROUND CHECKED NORMAL OPERATION. (M)

Part: FLOORBEAM — CORRODED (BS 1143)

TUL - RT AFT LAV FLOOR OUTBOARD OF FORWARD OUTBOARD TANK CABLE ATTACH LUG IS CORRODED, FORWARD OF INBOARD TANK CABLE ATTACH IS CORRODED. REMOVED CORRODED HAT CHANNEL AND INSTALLED SERVICEABLE HAT CHANNEL. (M)

Part: SKIN — CRACKED (BS 1096)

TUL - FOUND CRACK IN FUSELAGE SKIN ON CROWN AT STATION 1096, RIGHT SIDE OF STRINGER NR 1 AT FASTENER FOR NR 2 ENG INLET FORWARD ATTACH. INSTALLED DOUBLER PER SB 727-53A0204 SRM 53-30-3 FIG 3 PAGE 12-14. (M)

Part: STRINGER — CORRODED (BS 950)

TUL - FOUND CORROSION ON OUTBOARD SIDE STRINGER 29R TWO INCHES AFT OF 950E. REPLACED AFT SECTION OF STRINGER 29RT STATION 950D PLUS 10 INCHES TO STATION 990 PLUS 10 INCHES PER ESO 11697. (M)

Part: STRINGER — CORRODED (BS 514-525)

TUL - FOUND STRINGER 27 LEFT HAS CORROSION STATION 514 TO STATION 525. CUT OUT CORROSION AND REPLACED STRINGER 27L FROM STATION 513 TO STATION 525, PER SRM 53-10-3 PG 3-4B. (M)

Part: SHEAR TIE — CORRODED (BS 700)

TUL - FOUND CORROSION ON SHEAR TIE NEAR DOME NUTS, STATION 700 STRINGER 28L TO 28R. REMOVED SHEAR TIE AND INSTALLED NEW ONE PER SRM 57-10-3 PG 4. (M)

Part: STRINGER — CRACKED (BS 720)

TUL - FOUND STRINGER END CRACKED STRINGER 15R AT THE LIGHT BOX FORWARD SIDE STATION 720B PLUS 4. REMOVED CRACK STRINGER AND SPLICED NEW STRINGER AS PER SRM 53-10-3 FIG 1. (M)

Part: SKIN — CORRODED (BS 680-684)

TUL - FOUND CORROSION ON BELLY SKIN AND CIRCUMFERENTIAL STRAP, STATION 680 TO 684, INBOARD OF STRINGER 27R. INSTALLED DOUBLER AND FILLER ALODINED, PRIMED, PER SRM 53-30-3. (M)

Part: ENG INLET — CORRODED (NR 2 ENGINE)

TUL - NR 2 ENGINE INLET CORRODED AT 11:00 POSITION. REMOVED CORRODED AREA AND MADE FLUSH REPAIR PER SRM 54-30-3 PAGE 2A AND 2B. (M)

Part: SKIN — CORRODED (BS 580)

TUL - FOUND STRINGER 28 LEFT HAS CORROSION AND SKIN CORRODED STATION 580 TO 595. REMOVED AND REPLACED SECTION OF STRINGER AND SKIN AT STRINGER 28 LEFT STATION 580 TO 660 SRM 53-30-3 PAGE 12 - PG 14A. (M)

Part: STRINGER — CORRODED (BS 701)

FOUND CORROSION IN STRINGER 27R AT STATION 701. REMOVED OUT OF LIMITS STRINGER AND REPAIRED PER SRM 53-10-3. (M)

Part: ANGLE — CORRODED (BS 344-352)

TUL - FOUND FORWARD E/E STATION 344 TO STATION 352, UNDER RIGHT NOSE GEAR WALKWAY, LOWER CHORD ANGLE AT ATTACH TO NOSE GEAR W/W HAS BEARING CORROSION JUST AFT OF NOSE GEAR DRAG BRACKET, FORWARD SUPPORT BEAM. INSTALLED NEW RIGHT LOWER CHORD ANGLE PER SRM 51-10-01. (M)