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Part: ROLLER — OUT OF RIG (T/E FLAP) · airframe 46,507 hrs · 29,343 cycles

FLIGHT CREW REPORTED A LOUD VIBRATION WAS HEARD UPON FLAP EXTENSION ON APPROACH THAT APPEARED TO BE COMING FROM RT SIDE OF AIRCRAFT. PERFORMED INSPECTION PER MM 05-51-67, NO ABNORMALITIES OR DISCREPANCIES NOTED. PERFORMED TEST FLIGHT. TEST FLIGHT UNSATISFACTORY DUE TO VIBRATION AT FLAP SETTINGS 10-30. FOUND RT INBOARD AFT FLAP DEAD WEIGHT ROLLERS OUT OF RIG. ADJUSTED DEAD WEIGHT ROLLERS PER MM 27-51-11 AND FLAP OPS CHECKED GOOD. PERFORMED ANOTHER TEST FLIGHT, WITH NO DISCREPANCIES NOTED.

Part: SKIN — DAMAGED (FUSELAGE) · airframe 46,438 hrs · 29,309 cycles

DURING C-7 CHECK, INSPECTION REPORTED C2 DOOR CUTOUT FRAME SKIN DAMAGED AT BS 847, STR 23R. REMOVED DAMAGED AREA, FABRICATED AND INSTALLED REPLACEMENT PARTS PER EA 53-737-179.

Part: INTERCOSTAL — CORRODED (FUSELAGE) · corrosion level 2 · airframe 46,438 hrs · 29,309 cycles

DURING C-7 CHECK, INSPECTION REPORTED CORROSION FWD LAVATORY AT BS 294.5, STR 4L CORRODED. FABRICATED AND INSTALLED NEW INTERCOSTAL T-CHORD AND SHIM PER SRM 51-40-02, SOPM 20-41-02 AND EA 53-737-178.

Part: FLOORBEAM — CORRODED (FUSELAGE) · corrosion level 2 · airframe 46,438 hrs · 29,309 cycles

DURING C-7 CHECK, INSPECTION REPORTED CORROSION ON UNDERSIDE OF CARGO FLOORBEAMS AROUND NUT PLATES AT BS 727, LBL 7.5; BS 826, LBL 7.5; BS 727, LBL 12; BS 813, LBL 12; AND BS 945, LBL 12. REPLACED FLOORBEAMS FROM STA 727 - 947, LBL 12 PER SRM 51-10-02 AND 51-40-02.

Part: STRINGER CLIP — CRACKED (FUSELAGE) · airframe 46,438 hrs · 29,309 cycles

DURING C-7 CHECK, INSPECTION REPORTED STRINGER CLIP AT BS 727D, STR 4L CRACKED. FABRICATED AND INSTALLED REPLACEMENT STRINGER CLIP PER BOEING DRAWING 69-35352, SRM 51-30-02 AD SRM 51-40-02.

Part: SKIN — DAMAGED (FUSELAGE) · airframe 46,438 hrs · 29,309 cycles

DURING C-7 CHECK, INSPECTION REPORTED C-2 DOOR CUTOUT AFT FRAME SKIN DAMAGED AT STA 847, STR 23R. REMOVED DAMAGED AREA, FABRICATED AND INSTALLED REPAIR PER EA 53-737-179.

Part: INTERCOSTAL — CORRODED (FUSELAGE) · corrosion level 2 · airframe 46,438 hrs · 29,309 cycles

DURING C-7 CHECK, INSPECTION REPORTED CORROSION ON UPPER FLANGE OF INTERCOSTAL AT STA 727A TO 727B. FABRICATED AND INSTALLED NEW INTERCOSTAL PER SRM 51-30-01 AND 53-60-04.

Part: FRAME — CORRODED (FUSELAGE) · corrosion level 2 · airframe 46,438 hrs · 29,309 cycles

DURING C-7 CHECK, INSPECTION REPORTED CORROSION ON FRAME AT BS 847, RBL 6 TO LBL 6. REMOVED DAMAGE, FABRICATED AND INSTALLED REPAIR PER SRM 53-00-07.

Part: BUSHING — CORRODED (RT MLG) · airframe 46,438 hrs · 29,309 cycles

DURING C-7 CHECK, INSPECTION REPORTED RT MLG OUTER CYLINDER B-LUG (OUTBOARD SIDE) CORRODED. REMOVED CORROSION, FABRICATED AND INSTALLED NEW BUSHING PER SOPM 20-50-03 AND OHM 32-11-1.

Part: CHANNEL — CORRODED (FUSELAGE) · corrosion level 2 · airframe 46,438 hrs · 29,309 cycles

DURING C-7 CHECK, INSPECTION REPORTED FWD LAVATORY WALL ATTACH CHANNEL CORRODED AND CRACKED, BS 308, LBL 41.25 TO LBL 10.75. FABRICATED AND INSTALLED NEW HAT CHANNEL ATTACH ANGLE PER SRM 51-10-02, 51-40-02, BOEING DRAWING 65-77488-211 AND SOPM 20-41-02.

Part: STRINGER — CORRODED (FUSELAGE) · corrosion level 2 · airframe 46,438 hrs · 29,309 cycles

DURING C-7 CHECK, INSPECTION REPORTED CORROSION ON STR 21L UNDER FRAME AT BS 927. FABRICATED AND INSTALLED REPLACEMENT PARTS PER SRM 53-00-3, 51-40-02 AND 51-20-01.

Part: FLOORBEAM — CORRODED (FUSELAGE) · corrosion level 2 · airframe 46,438 hrs · 29,309 cycles

DURING C-7 CHECK, INSPECTION REPORTED CORROSION ON UNDERSIDE OF CARGO FLOORBEAM AROUND NUT PLATES, BS 772 TO 513, LBL 2.5.

Part: WEB — CORRODED (FUSELAGE) · corrosion level 2 · airframe 46,438 hrs · 29,309 cycles

DURING C-7 CHECK, INSPECTION REPORTED WEB AT BS 927, STR 21L, CORRODED. FABRICATED AND INSTALLED REPLACEMENT WEB PER SRM 51-10-02.

Part: BEAR STRAP — CORRODED (FUSELAGE) · corrosion level 2 · airframe 46,438 hrs · 29,309 cycles

DURING C-7 CHECK, INSPECTION REPORTED CORROSION ON BEAR STRAP AT BS 465-477, OUTBOARD OF STR 25-R. REPAIRED PER EA 53-737-177 AND SRM 53-30-03.

Part: FLOOR SUPPORT — DAMAGED (FUSELAGE) · airframe 46,438 hrs · 29,309 cycles

DURING C-7 CHECK, INSPECTION REPORTED CARGO FLOOR SUPPORT DAMAGED AT BS 460-540, LBL 10. REMOVED DAMAGED SECTION OF CARGO FLOOR SUPPORT FABRICATED AND INSTALLED REPAIR PARTS PER SRM 53-00-53, 51-40-02 AND SOPM 20-41-02.

Part: ANGLE — CORRODED (FUSELAGE) · corrosion level 2 · airframe 46,438 hrs · 29,309 cycles

DURING C-7 CHECK, INSPECTION REPORTED CORROSION ON MOP SILL SUPPORT ANGLE, BS 349, AT BOTTOM OF NUT PLATE HOLE ON L1 ENTRY DOOR. REMOVED MOP SILL SUPPORT ANGLE AND WEB PER SRM 51-30-2, LOCATED FASTENER HOLES ON MOP SUPPORT ANGLE PER SRM 51-10-2 AND INSTALLED NEW MOP SILL SUPPORT ANGLE PER SRM 51-40-2.

Part: SKIN — DENTED (HORIZ STAB) · airframe 46,438 hrs · 29,309 cycles

DURING C-7 CHECK, INSPECTION REPORTED DENT IN RT HORIZONTAL STAB LEADING EDGE AT BS 121.59. CUT OUT DAMAGE, AND FABRICATED AND INSTALLED REPAIR DOUBLER PER SRM 55-10-01.

Part: DOOR FRAME — DAMAGED (CARGO DOOR) · airframe 46,438 hrs · 29,309 cycles

DURING C-7 CHECK, INSPECTION REPORTED FWD CARGO COMPARTMENT LOWER AFT DOOR FRAME WEB CHIPPED AND PIECES MISSING. CUT OUT DAMAGED AREA, FABRICATED AND INSTALLED NEW SECTION OF FRAME WEB PER SRM 51-70-13 AND 51-40-02.

Part: FRAME — CORRODED (FUSELAGE) · corrosion level 2 · airframe 46,438 hrs · 29,309 cycles

DURING C-7 CHECK, INSPECTION REPORTED CORROSION ON FRAME AT BS 967, LBL 14. FABRICATED AND INSTALLED REPAIR DOUBLER PER SRM 51-70-11.

Part: STRINGER CLIP — CRACKED (BS 597) · airframe 46,438 hrs · 29,309 cycles

DURING C-7 CHECK, INSPECTION REPORTED CRACKED TIE CLIP TO STRINLGER AT BS 597, STR. 8-R. REPLACED STRINGER CLIP PER SRM 51-10-02.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · corrosion level 2 · airframe 46,438 hrs · 29,309 cycles

DURING C-7 CHECK, INSPECTION REPORTED CORROSION ON UNDERSIDE OF CARGO FLOORBEAM AROUND NUT PLATE, BS 727E +2, RBL 8. REMOVED DAMAGED AREA, FABRICATED AND INSTALLED REPLACEMENT PARTS PER SRM 51-41-02, 53-00-53, AND SOPM 20-41-02.

Part: STIFFENER — CRACKED (FUSELAGE) · airframe 46,438 hrs · 29,309 cycles

DURING C-7 CHECK, INSPECTION REPORTED STIFFENER AT BS 328, LBL 28, CRACKED AT TOP HOLE OF FLOORBEAM. FABRICATED AND INSTALLED REPLACEMENT STIFFENER PER SRM 51-40-2.

Part: DOUBLER — CRACKED (NR 1 PYLON) · airframe 46,438 hrs · 29,309 cycles

DURING C-7 CHECK, INSPECTION REPORTED NR 1 ENGINE PYLON HOCKEY STICK DOUBLER CRACKED AT AFT LOWER END. FABRICATED AND INSTALLED NEW DOUBLER PER SRM 51-70-13 AND 51-40-02.

Part: SKIN — CORRODED (FUSELAGE) · corrosion level 2 · airframe 46,438 hrs · 29,309 cycles

DURING C-7 CHECK, INSPECTION REPORTED CORROSION ON FUSELAGE SKIN, BS 469-487, BETWEEN STR 25-R AND 26-R. REPAIRED PER EA 53-737-177 AND SRM 53-30-03.

Part: STRUCTURE — CRACKED (FUSELAGE) · airframe 46,438 hrs · 29,309 cycles

DURING C-7 CHECK, INSPECTION REPORTED CRACK IN SURROUNDING DOOR STRUCTURE TRIM AT BS 294.5, WL 208.1. REMOVED DAMAGED SECTION, FABRICATED AND INSTALLED REPAIR PARTS PER SRM 51-70-13.

Part: WEB — CORRODED (L1 DOOR) · corrosion level 2 · airframe 46,438 hrs · 29,309 cycles

DURING C-7 CHECK, INSPECTION REPORTED CORROSION ON L1 ENTRY DOOR WEB, BS 312 TO BS 351. REMOVED L1 DOOR WEB AND DOUBLERS, FABRICATED AND INSTALLED NEW WEB AND DOUBLERS PER SRM 51-30-05, 51-40-02 AND SOPM 20-41-02.

Part: SKIN — DELAMINATED (NO. 2 ENG) · airframe 46,438 hrs · 29,309 cycles

DURING C-7 CHECK, INSPECTION REPORTED NO. 2 ENGINE PYLON TOP FWD SKIN DELAMINATED AT FWD INBD CORNER. REPAIRED AND REFINISHED PER SRM 51-70-17.

Part: CHANNEL — CORRODED (BS 827) · corrosion level 2 · airframe 46,438 hrs · 29,309 cycles

DURING C-7 CHECK, INSPECTION REPORTED CORROSION ON UNDERSIDE OF CARGO FLOORBEAM AROUND NUTPLATE, BS 827, RBL 25. INSTALLED CHANNEL FOR FLOOR SUPPORT REPAIR PER 53-00-53.

Part: STRINGER CLIP — CRACKED (BS 767) · airframe 46,438 hrs · 29,309 cycles

DURING C-7 CHECK, INSPECTION REPORTED STRINGER CLIP AT BS 767, STR 6-L, CRACKED. FABRICATED AND INSTALLED REPLACEMENT STRINGER CLIP PER SRM 51-30-02, SRM 57-40-02 AND BOEING DRAWING 69-35352.

Part: CHANNEL — CORRODED (FUSELAGE) · corrosion level 2 · airframe 46,438 hrs · 29,309 cycles

DURING C-7 CHECK, INSPECTION REPORTED L1 DOOR MOP SILL FLOOR ANGLE AND STANDS FOR THRESHOLD CORRODED. REPLACED THRESHOLD ATTACH CHANNEL AND ZEE ANGLE PER SRM 51-10-02.

Part: STRAP — CRACKED · airframe 46,438 hrs · 29,309 cycles

DURING C-7 CHECK, INSPECTION REPORTED FORE AND AFT FUSELAGE STRAP ON RT. SIDE AT STA. 540 CRACKED AT AFT END ABOVE RT. PACK INLET DUCT. REMOVED DAMAGED SECTION, FABRICATED AND INSTALLED REPAIR PARTS PER SRM 53-30-71, 51-40-2 AND 51-7-77

Part: SKIN — CRACKED (L/E SLAT) · airframe 46,438 hrs · 29,309 cycles

DURING C-7 CHECK, INSPECTION REPORTED LT WING NR 1 SLAT LOWER SKIN CRACKED AT LAST ROW OF RIVETS I/B OF CENTER AUX TRACK. FABRICATED AND INSTALLED REPAIR PER SRM 57-43-01.

Part: FLOORBEAM — CORRODED (FUSELAGE) · corrosion level 2 · airframe 46,438 hrs · 29,309 cycles

DURING C-7 CHECK, INSPECTION REPORTED CORROSION 1 FT LEFT OF CENTER LINE FLOORBEAM AT BS 294.5. FOUND CORROSION ON FLOORBEAM AT BS 294.5 TO BE OUT OF LIMITS FROM LBL 19.5 TO RBL 60 PER SRM 53-10-51. REMOVED THIS SECTION OF THE TOP CHORD, FABRICATED REPLACEMENT CHORD AND INSTALLED PER SOPM 26-41-02 AND SRM 53-10-51.

Part: ANGLE — CRACKED (NR 1 PYLON) · airframe 46,438 hrs · 29,309 cycles

DURING C-7 CHECK, INSPECTION REPORTED NR 1 PYLON SUPPORT ANGLE CRACKED IN AFT PORTION OF PYLON FWD OF CASTING, ADJACENT TO FLAP DOOR. REPLACED NR 1 PYLON SUPPORT ANGLE PER SRM 51-40-02 AND 51-40-05.

Part: STRINGER — CORRODED (FUSELAGE) · corrosion level 2 · airframe 46,438 hrs · 29,309 cycles

DURING C-7 CHECK, INSPECTION REPORTED CORROSION ON STR 21R UNDER FRAME AT BS 727. FABRICATED AND INSTALLED NEW STRINGER SECTION AND REPAIR SPLICES PER SRM 53-00-03, FIG 201 AND SOPM 20-41-02.

Part: TIE CLIP — CRACKED · airframe 46,438 hrs · 29,309 cycles

DURING C-7 CHECK, INSPECTION NOTED CRASKS IN TIE CLIP TO STRINGER AT TOP RIVET AT STA 663 STR 10 LH. MAINTENANCE REPAIRED THE CONDITION BY INSTALLING A NEW CLIP AT STA 663 STR 10 L IN ACCORDANCE WITH SRM 51-10-02.

Part: SKIN — CANNING (FUSELAGE) · airframe 46,438 hrs · 29,309 cycles

DURING C-7 CHECK, INSPECTION FOUND THE FUSELAGE SKIN AT BS 928, STR 21 LT, OIL CANNED (BUCKLED). MAINTENANCE REMOVED SECTION OF SKIN, FABRICATED REPAIR DOUBLER AND TRIPLER. PARTS WERE INSTALLED IN ACCORDANCE WITH SRM 51-40-02

Part: FLOORBEAM — CORRODED (FUSELAGE) · corrosion level 3 · airframe 46,438 hrs · 29,309 cycles

DURING C-7 CHECK, INSPECTION NOTED LIGHT SURFACE CORROSION IN FORWARD ENTRY AT STA 344. MAINTENANCE FOUND THE STA 344 FLOORBEAM TO BE OUT OF LIMITS IAW SRM 53-10-51. MAINTENANCE REMOVED AND REPLACED THE UPPER CHORD OF STA 344 FLOORBEAM, WL 208, RBL 17 THROUGH LBL 65, IAW SRM 53-10-51, 50-40-02 AND SOPM 20-41-02.

Part: FRAME — DENTED (FUSELAGE) · airframe 46,438 hrs · 29,309 cycles

DURING C-7 CHECK, INSPECTION NOTED A DENT IN THE RADIUS OF THE FRAME AT BS 727 B, BETWEEN STRINGERS 22 L AND 23 L. MAINTENANCE FABRICATED A REPAIR DOUBLER IAW SRM 51-70-11 AND INSTALLED IAW SRM 51-40-02.

Part: TIE CLIP — CRACKED · airframe 46,438 hrs · 29,309 cycles

DURING C-7 CHECK, INSPECTION NOTED STRINGER TIE CLIP AT STA 727E, STR 7 L WAS CRACKED. MAINTENANCE REMOVED THE CLIP, FABRICATED AND INSTALLED A NEW CLIP IN ACCORDANCE WITH THR ERQUIREMENTS OF BOEING DRAWING 69-35352 AND SRM 51-30-02 AND SRM 51-40-02.

Part: FLOOR PANEL · corrosion level 3 · airframe 46,438 hrs · 29,309 cycles

DURING C-7 CHECK, INSPECTION NOTED LIGHT CORROSION IN THE AFT CARGO PIT AT FRAME STA 727 C, UNDER LEFT FLOOR TRANSITION PANEL. MAINTENANCE REMOVED THE SURFACE CORROSION IN ACCORDANCE WITH SRM 51-10-02, TREATED, PRIMED AND PAINTED THIS AREA IN ACCORDANCE WITH THE REQUIREMENTS OF MM 51-21-4A AND SOPM 20-41-02.

Part: TIE CLIP — CRACKED · airframe 46,438 hrs · 29,309 cycles

DURING C-7 CHECK, INSPECTION FOUNG A BROKEN TIE CLIP TO STRINGER AT STA 639 STR 4L. mAINTENANCE INSTALLED NEW STRINGER TIE CLIP AT STA 639 STR 4L IN ACCORDANCE WITH SRM 51-10-02 AND 51-40-03.

Part: SKIN — CRACKED (FUSELAGE) · airframe 46,438 hrs · 29,309 cycles

DURING C-7 CHECK, INSPECTION FOUND A CRACK IN FUSELAGE SKIN AT STA 727E, STR 22 R. MAINTENANCE REMOVED THE DAMAGE, BLENDED THE AREA. A DOUBLER WAS FABRICATED AND INSTALLED IN ACCORDANCE WITH THE REQUIREMENTS OF SRM 53-00-01 FIGURE 201 AND SRM 53-60-01.

Part: SKIN — CRACKED (FUSELAGE) · airframe 46,438 hrs · 29,309 cycles

DURING C-7 CHECK, INSPECTION NOTED A CRACK IN THE FUSELAGE SKIN AT STA 727E STR 21 R. MAINTENANCE REMOVED THE DAMAGE. A DOUBLER WAS FABRICATED AND INSTALLED IN ACCORDANCE WITH THE REQUIREMENTS OF SRM 53-00-01 FIGURE 201 AND SRM 53-60-01.

Part: CROSSBEAM — CRACKED (FUSELAGE) · airframe 46,438 hrs · 29,309 cycles

DURING C-7 CHECK, INSPECTION NOTED CABIN FLOOR EXPANSION JOINT CROSS MEMBERS CRACKED AT FASTENER STATION 540 RBL 44, UNDER THE FLOOR. MAINTENANCE REPAIRED THE EXPANSION IN ACCORDANCE WITH THE REQUIREMENTS OF SRM 51-40-2 AND 51-10-2.

Part: TIE CLIP — CORRODED · corrosion level 3 · airframe 46,438 hrs · 29,309 cycles

DURING C-7 CHECK, INSPECTION NOTED CORROSION IN STRINGER CLIP AT STA 787, STR 26 R. MAINTENANCE FABRICATED STRINGER CLIP IN ACCORDANCE WITH BOEING DRAWING 69.35352. THE PART WAS THEN TREATED, PRIMED, PAINTED AND INSTALLED IN ACCORDANCE WITH THE REQUIREMENTS OF SOPM 20.41.02 AND SRM 51.40.02.

Part: SKIN — CRACKED (FUSELAGE) · airframe 46,338 hrs · 29,309 cycles

DURING C-7 CHECK, INSPECTION NOTED A CRACK IN THE RIGHT HAND FUSELAGE SKIN AT STA 727E, BETWEEN STR 22 R AND 23 R. MAINTENANCE REMOVED THE DAMAGE, FABRICATED A DOUBLER AND INSTALLED THE DOUBLER IN ACCORDANCE WITH THE REQUIREMENTS OF SRM 53-00-01, FIGURE 201 AND SRM 53-60-01.

Part: FLOORBEAM — CORRODED (FUSELAGE) · corrosion level 3 · airframe 46,438 hrs · 29,309 cycles

DURING C-7 CHECK, INSPECTION NOTED CORROSION ON STA 328 FLOORBEAM, NEAR PREVIOUS REPAIR NEAR L1 DOOR SILL. MAINTENANCE FOUND THE BEAM TO BE OUT OF LIMITS IN ACCORDANCE WITH SRM 53-10-51. MAINTENANCE REMOVED AND REPLACED THE UPPER CHORD OF STA 328 FLOORBEAM, WL 208, LBL 33 TO LBL 64 IAW SRM 53-10-51, 51-40-02 AND SOPM 20-41-02.

Part: STRINGER CLIP — CRACKED (FUSELAGE) · airframe 46,438 hrs · 29,309 cycles

DURING C-7 CHECK, INSPECTION REPORTED A CRACK IN TIE CLIP TO STRINGER AT STATION 540, STRINGER 5R. MAINTENANCE REMOVED AND REPLACED STRINGER CLIP, IN ACCORDANCE WITH SRM 51-40-02 AND 51-20-01 AND SOPM 20-41-02.

Part: STRINGER — CRACKED (FUSELAGE) · airframe 46,438 hrs · 29,309 cycles

DURING C-7 CHECK, INSPECTION REPORTED A CRACK IN TIE CLIP TO STRINGER AT STA 616, STR 4R. MAINTENANCE REMOVED AND REPLACED CRACKED STRINGER WITH NEW PART IN ACCORDANCE WITH SRM 51-10-02.

Part: SKIN — CRACKED · airframe 43,611 hrs · 27,810 cycles

DURING A-3 CHECK, MAINTENANCE REPORTED A 2" CRACK IN FUSELAGE SKIN AT STA. 727E, STR. 18R. REMOVED DAMAGED AREA, FABRICATED REPAIR DOUBLER AND INSTALLED PER SRM 53-00-01.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · corrosion level 2 · airframe 43,066 hrs · 27,530 cycles

DURING C-6 CHECK, INSPECTION REPORTED AFT CARGO FLOOR SUPPORT BETWEEN BS 767 AND BS 787, RBL 3, CORRODED AND BENT. FABRICATED AND INSTALLED REPLACEMENT FLOOR SUPPORT AND ANGLES PER SRM 53-00-53, 53-10-53 AND SOPM 20-41-02.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · corrosion level 2 · airframe 43,066 hrs · 27,530 cycles

DURING C-6 CHECK INSPECTION REPORTED FLOOR STRINGER AT RBL 18.1 - BS 807-847 CORRODED. REMOVED DAMAGED FLOOR SUPPORT, FABRICATED AND INSTALLED NEW SUPPORT AND ANGLES PER SRM 57-40-02, 53-60-53 AND SOPM 20-41-02.

Part: STRAP — CORRODED (FUSELAGE) · corrosion level 2 · airframe 43,066 hrs · 27,530 cycles

DURING C-6 CHECK, INSPECTION REPORTED CORROSION AT NUT PLATE HOLES, FLOOR SUPPORT STRAP, BS 859, RBL 18 TO LBL 18. FABRICATED AND INSTALLED REPLACEMENT FLOOR SUPPORT STRAP PER SRM 53-60-53 AND 51-10-2.

Part: STRAP — CORRODED (FUSELAGE) · corrosion level 2 · airframe 43,066 hrs · 27,530 cycles

DURING C-6 CHECK, INSPECTION REPORTED CORROSION ON STRAP UNDER FRAME AT BS 794. FABRICATED AND INSTALLED REPLACEMENT STRAP PER BOLD DRAWING 65-47959, SHEET 15 OF 49, SRM 51-10-02 AND SRM 51-40-02.

Part: STRAP — CORRODED (FUSELAGE) · corrosion level 2 · airframe 43,066 hrs · 27,530 cycles

DURING C-6 CHECK, INSPECTION REPORTED AFT CARGO BAY FLOOR STRAP CORRODED AT BS 800-840, ABOVE STR. 25-R, INBD OF THRESHOLD WEB. REPLACED FLOOR STRAP PER SRM 53-60-15 AND 51-10-02.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · corrosion level 2 · airframe 43,066 hrs · 27,530 cycles

DURING C-6 CHECK, INSPECTION REPORTED AFT CARGO COMPARTMENT FLOOR SUPPORT, LT OF CENTER LINE BETWEEN BS 727 AND 727A, CORRODED. FABRICATED AND INSTALLED REPLACEMENT FLOOR SUPPPORT CHANNEL, SPLICE ANGLE AND STRAP PER SRM 53-60-53, SRM 57-40-02 AND SOPM 20-41-02.

Part: STRAP — CORRODED (FUSELAGE) · corrosion level 2 · airframe 43,066 hrs · 27,530 cycles

DURING C-6 CHECK, INSPECTION REPORTED CORROSION ON HORIZONTAL FLOOR STRAP AT BS 772, RBL 21 TO LBL 21. FABRICATED AND INSTALLED REPLACEMENT FLOOR STRAP PER SRM 51-10-02.

Part: CARGO TRACK — CORRODED (FUSELAGE) · corrosion level 2 · airframe 43,066 hrs · 27,530 cycles

DURING C-6 CHECK, INSPECTION REPORTED CARGO FLOOR TRACK CORRODED AT BS 800 TO 840 ABOVE STR 26R IN AFT CARGO BAY. FABRICATED FLOOR TRACK AND SPLICE PLATES AND INSTALLED PER SRM 53-00-53, 51-10-02, SEC 53, AND SOPM 20-41-02.

Part: FRAME — CORRODED (FUSELAGE) · corrosion level 2 · airframe 43,066 hrs · 27,530 cycles

DURING C-6 CHECK, INSPECTION REPORTED CORROSION ON VERTICAL FLANGE OF BS 794.3 FRAME, BETWEEN STR 24-R AND 26-R. INSTALLED REPLACEMENT FRAME PER SRM 51-40-2.

Part: INTERCOSTAL — CORRODED (FUSELAGE) · corrosion level 2 · airframe 43,066 hrs · 27,530 cycles

DURING C-6 CHECK, INSPECTION REPORTED AFT GALLEY INTERCOSTAL CORRODED BETWEEN BS 1016 AND 986, BL 8L. FABRICATED AND INSTALLED REPLACEMENT LT AND RT INTERCOSTALS PER EA 53-737-117.

Part: CHANNEL — CORRODED (FUSELAGE) · corrosion level 2 · airframe 43,066 hrs · 27,530 cycles

DURING C-6 CHECK, INSPECTION REPORTED HAT CHANNEL AT BS 993, LBL 15 CORRODED. FABRICATED AND INSTALLED REPLACEMENT HAT CHANNEL PER SRM 53-60-51.

Part: STINGER — CORRODED (FUSELAGE) · corrosion level 2 · airframe 43,066 hrs · 27,530 cycles

DURING C-6 CHECK, INSPECTION REPORTED CORROSION ON STRINGER 26-L, BS 500 - 500A. FABRICATED AND INSTALLED REPLACEMENT STRINGER PER SRM 53-00-03.

Part: TEE CHORD — CORRODED (FUSELAGE) · corrosion level 2 · airframe 43,066 hrs · 27,530 cycles

DURING C-6 CHECK, INSPECTION REPORTED CORROSION ON FLOORBEAM UPPER TEE CHORD AT STA 1016, LBL 33. CLEANED CORROSION AND FOUND TO BE OUT OF LIMITS PER SRM 53-00-51. FABRICATED AND INSTALLED REPAIR PER SRM 53-00-51, 51-40-02 AND SOPM 20-41-02.

Part: STRINGER — CORRODED (FUSELAGE) · corrosion level 2 · airframe 43,066 hrs · 27,530 cycles

DURING C-6 CHECK, INSPECTION REPORTED STRINGER 21-L AT STA 727D IN AFT CARGO COMPARTMENT CORRODED. REPLACED DAMAGED STRINGER PER SRM 53-00-03.

Part: FLOORBEAM — CORRODED (FUSELAGE) · corrosion level 2 · airframe 43,066 hrs · 27,530 cycles

DURING C-6 CHECK, INSPECTION REPORTED SURFACE CORROSION OF FLOORBEAM AT STA 312 AFT OF COCKPIT DOOR. MAINTENANCE DETERMINED CORROSION OUT OF LIMITS PER SRM 51-70-12. REMOVED FLOORBEAM, FABRICATED AND INSTALLED REPLACEMENT FLOORBEAM PER SRM 53-00-51.

Part: MANIFOLD — BROKEN (COCKPIT) · airframe 42,939 hrs · 27,467 cycles

DURING FLIGHT FROM LAX TO DEN, FLIGHT CREW REPORTED SPARKS, ARCING AND SMOKE COMING FROM BEHIND CAPTAIN''S INSTRUMENT PANEL. AIRCRAFT DIVERTED TO LAS AND LANDED WITHOUT INCIDENT. MAINTENANCE FOUND THE CAPTAIN''S INSTRUMENT COOLING MANIFOLD BROKEN AND THE COOLING AIR DUCT INSULATION CHAFED, WHICH EXPOSED THE METAL DUCT AND CREATED A SHORT. AN INTERIM REPAIR WAS ACCOMPLISHED PER EA 21-737-009 AND RW 258 WAS ISSUED TO REPLACE THE MANIFOLD AND THE DUCT AT THE NEXT C-CHECK.

Part: LIGHT — CONTAMINATED (ROW 10) · airframe 41,833 hrs · 26,901 cycles

DURING A-3 CHECK, INSPECTION REPORTED EMERGENCY ESCAPE PATH LIGHTING INOPERATIVE FROM ROW 10 FORWARD. MAINTENANCE REPLACED POWER STRIP PER MM 33-51-01 AND PERFORMED AN OPERATIONAL TEST.

Part: TRIM TAB — OUT OF TOLERANCE (ELEVATOR)

DEN - DURING C-5 CHECK, INSPECTION REPORTED LT ELEVATOR TRIM TAB OUT OF TOLERANCE AT ELEVATOR HINGE LOCATION. REPLACED LT ELEVATOR TRIM TAB PER MM 27-31-31 AND BOEING SERVICE BULLETIN 737-55-1049. (M)

Part: FRAME — CRACKED (COCKPIT WINDOW)

DEN - DURING C-5 CHECK INSPECTION, REPORTED L-1 WINDOW FRAME CRACKED AT UPPER AFT CORNER, APPROXIMATELY .375 INCH LONG. MAINTENANCE REMOVED DAMAGED SKIN AND STOP DRILLED CRACK IN GUSSET. FABRICATED AND INSTALLED DOUBLER AND FILLER PER EA 53-737-056A, AND INSTALLED AND PERFORMED LEAK CHECK OF WINDOW PER MM 56-11-11. (M)

Part: ROD — KINKED (RUDDER CONTROL)

DEN - DURING C-5 CHECK, INSPECTION REPORTED RUDDER PCU VERNIER CONTROL ROD KINKED AT AFT END. MAINTENANCE REPLACED THE RUDDER PCU VERNIER CONTROL ROD. (M)

Part: STRUCTURE — CORRODED (TORQUE BOX)

DEN - DURING C-5 CHECK, INSPECTION REPORTED CORROSION ON R-1 DOOR TORQUE BOX IN BOLT HOLES AT ATTACHMENTS AND BOLT HOLES IN HOUSING. MAINTENANCE REPAIRED TORQUE BOX PER SRM 52-46-06. (M)

Part: GATE — WORN (PAX DOOR)

DEN - DURING C-5 CHECK, INSPECTION REPORTED R-1 DOOR LOWER GATE WORN AND CORROSION BY DOORSTOP PINS. MAINTENANCE REPLACED R-1 DOOR LOWER GATE PER SRM 51-40-05 AND 51-40-02, RIGGED DOOR AND PERFORMED FUNCTIONAL CHECK. (M)

Part: WEB — CORRODED (LAV SERVICE DOOR)

DEN - DURING C-5 CHECK, INSPECTION REPORTED CORROSION BETWEEN LAYERS OF PAN ON REAR LAVATORY SERVICE COMPARTMENT. MAINTENANCE REPLACED CORRODED PARTS PER SRM 51-40-02, 51-10-02 AND 51-40-6. (M)

Part: SKIN — DELAMINATED (TE FLAP)

DEN - DURING C-5 CHECK, INSPECTION FOUND LEFT INBOARD AFT FLAP DELAMINATED AT OUTBOARD AFT CORNER. MAINTENANCE REPAIRED DAMAGE PER SRM 51-70-10. (M)

Part: BEARING — DAMAGED (TE FLAP)

DEN - DURING C-5 CHECK, INSPECTION FOUND EXCESSIVE PLAY IN LT WING NR 2 INBOARD FLAP SPINDLE BEARINGS. MAINTENANCE REPLACED SPINDLE BEARINGS AND TORQUED NR 2 INBOARD FLAP CARRIAGE PER MM 27-51-34. (M)

Part: BEARING — DAMAGED (TE FLAP)

DURING C-5 CHECK, INSPECTION FOUND EXCESSIVE PLAY IN LT WING OUTBOARD MIDFLAP NR 1 SPINDLE BEARINGS. MAINTENANCE REPLACED SPINDLE BEARINGS PER OHM 57-53-35. (M)

Part: SKIN — CORRODED (TE FLAP)

DURING C-5 CHECK, INSPECTION REPORTED CORROSION ON NR 1 OUTBOARD AND NR 2 INBOARD TRAILING EDGE FLAP ENCLOSURES INSIDE JOURNALS. MAINTENANCE REPLACED NR 1 OUTBOARD ENCLOSURE PER MM 27-51-44 AND NR 1 INBOARD ENCLOSURE PER MM 27-51-34. (M)

Part: BEARING — OUT OF TOLERANCE (ELEVATOR TAB)

DURING C-5 CHECK, INSPECTION REPORTED RIGHT ELEVATOR TRIM TAB OUTBOARD BEARING OUT OF TOLERANCE. REPLACED RIGHT ELEVATOR TRIM TAB PER MM 27-31-31 AND BOEING SERVICE BULLETIN 737-55-1049. (M)

Part: SKIN — DELAMINATED (LE FLAP)

DEN - DURING C-5 CHECK, INSPECTION FOUND TWO DENTS WITH DELAMINATION ON UPPER SURFACE OF LT OUTBOARD FOREFLAP, APPROXIMATE 36 INCHES FROM INBOARD END. MAINTENANCE REPAIRED FOREFLAP PER MM 51-70-10, AND INSTALLED AND PERFORMED OPERATIONAL CHECK PER MM 27-51-37. (M)

Part: RETRACT MECH — OUT OF ADJUST (NLG)

DEN - UPON ARRIVAL, FLIGHT CREW REPORTED NOSE GEAR DID NOT EXTEND WHEN GEAR HANDLE SELECTED DOWN. RECYCLED GEAR HANDLE AND NOSE GEAR EXTENDED. MAINTENANCE RESHIMMED NLG LOCK MECHANISM, PERFORMED EXTENSION AND RETRACTION TEST, LUBRICATED NOSE LANDING GEAR AND CHECKED OK. (M)

Part: INDICATION — MALFUNCTIONED (LANDING GEAR)

DFW - FLT 124 - FLIGHT CREW REPORTED NOSE GEAR GREEN LIGHT DID NOT ILLUMINATE UPON APPROACH, RED LIGHT REMAINED ILLUMINATED. RECYCLED GEAR AND ALL THREE GREEN LIGHTS ILLUMINATED. MAINTENANCE INSPECTED NOSE LANDING GEAR PER MM 32-00 AND CONTROL LEVER LOCK SYSTEM PER MM 32-31. CYCLED GEAR SEVERAL TIMES AND ALL INDICATIONS WERE NORMAL. (M)

Part: GATE — CRACKED (L1 DOOR)

DURING C-CHECK, INSPECTION REPORTED UPPER DOOR GATE CRACKED AT ACTUATOR EAR ON L-1 DOOR. MAINTENANCE REPLACED UPPER GATE ASSEMBLY PER MM 52-11-00. RIGGED AND ADJUSTED GATE ASSEMBLY PER MM 52-11-99, PAGES 512-514. (M)

Part: SKIN — CRACKED (NR 5 LE SLAT)

DURING C-CHECK INSPECTION, REPORTE THREE CRACKS ON THE LOWER SKIN OF THE NR 5 SLAT, OUTBOARD END. MAINTENANCE REPAIRED PER SRM AND EO 57-54-737-002. (M)

Part: SUPPORT — BROKEN (BS 787)

DEN - DURING C-CHECK INSPECTION, REPORTED TWO AFT CARGO PIT STANTION CLEATS BROKEN, STATION 787, LEFT FLOOR AREA. MAINTENANCE REPLACED FLOOR SUPPORT PER SRM 53-00-53 FIG 202. (M)

Part: BATTERY PACK — DISCHARGED (CABIN)

DEN - DURING A-5 CHECK, INSPECTION REPORTED AFT SECTION OF FLOOR PROXIMITY LIGHTING AT R-2 DOOR INOPERATIVE. REPLACED BATTERY PACK AND SYSTEM CHECKED OKAY. (X)

Part: SKIN — DISBONDED (LT TE FLAP)

PAE - DURING C-CHECK INSPECTION REPORTED, LT WING OUTBOARD TRAILING EDGE FLAP SKIN DISBONDED ON UPPER INBOARD AFT CORNER. MAINTENANCE REMOVED DAMAGED AREA (6 INCH BY 9 INCH) OF UPPER SURFACE SKIN AND DAMAGED AREA (3.5 INCH BY 4.5 INCH) OF LOWER SURFACE SKIN, FABRICATED REPAIR PARTS AND REPAIRED PER SRM 51-70-10. (M)

Part: SKIN — CORRODED (RT TE FLAP)

PAE - DURING C-CHECK INSPECTION REPORTED, RT WING OUTBOARD TRAILING EDGE FLAP SKIN BULGED ON UPPER SURFACE AND DISBONDED ON LOWER SURFACE 13 INCHES FROM OUTBOARD END. MAINTENANCE REMOVED DAMAGED AREA (2.5 INCH BY 3 INCH). FABRICATED REPLACEMENT PARTS AND REPAIRED PER SRM 51-70-10, PAGE 13, PARAGRAPH 15. (M)

Part: WEB — CRACKED (BS 847)

PAE - DURING C-CHECK INSPECTION REPORTED, 1 INCH CRACK IN WEB AT BS 847, RBL 29. MAINTENANCE REMOVED WEB. FABRICATED REPLACEMENT PARTS AND REPAIRED PER SRM 51-30-1, 51-40-2 AND 51-40-08. (M)

Part: SKIN — CRACKED (NR 1 LE FLAP)

PAE - DURING C-CHECK, INSPECTION REPORTED NR 1 SLAT SKIN CRACKED AROUND FASTENER HEADS. MAINTENANCE REMOVED DAMAGED AREA (18 INCH BY 4.5 INCH). FABRICATED REPLACEMENT PARTS PER BOEING DRAWING 65C 30133, SHEET 3, AND REPAIRED PER SRM 51-40-02. (M)

Part: SLIDE — DEPLOYED (PAX DOOR)

DEN - UPON ARRIVAL FLIGHT CREW REPORTED R-1 SLIDE DEPLOYED WHEN FORWARD SERVICE DOOR WAS OPENED. MAINTENANCE REPLACED SLIDE ASSEMBLY. (M)

Part: SERVO VALVE — FAILED (RUDDER CONTROL)

MDW - FLT 445 - FLIGHT CREW REPORTED UNCOMMANDED ROLL TO RIGHT ON TAKEOFF. DISENGAGED YAW DAMPER AND RETURNED TO NORMAL FLIGHT. MAINTENANCE REPLACED E.H. SERVO VALVE ASSEMBLY IN RUDDER PCU AND SYSTEM CHECKED OKAY. (X)

Part: SKIN — DENTED (CARGO DOOR)

PAE - DENT IN OUTER SKIN 5 INCHES FROM FORWARD EDGE, AND 20 INCHES FROM BOTTOM EDGE ON THE FORWARD CARGO DOOR. REMOVED DAMAGE IN OUTER SKIN AND INSTALLED REPAIR PER SRM 52-00-01 FIG 203. DIMENSIONS OF CUTOUT ARE LENGTH 2 INCHES BY WIDTH 1 INCH. (M)

Part: SKIN — DENTED (BS 867-887)

PAE - DENTS IN SKIN BS 867-887 BETWEEN STRINGER 18-20 R/E. REPAIRED DENTS IN SKIN BS 867-887 BETWEEN STRINGER 18-20 RT IAW SRM 53-00-01 FIG 201 AND SRM 53-60-01. REMOVED DAMAGED AREA, FABRICATED REPAIR DOUBLERS. ALODINED, PRIMED AND INSTALLED. (M)

Part: TIRE — SEPARATED (NR 4 MLG)

ABQ - FLT 31 - UPON ARRIVAL, CREW REPORTED TREAD ON NR 4 MLG TIRE SEPARATED FROM CARCASS. RT INBD AFT, MID AND FORE FLAPS DAMAGED AT LEADING EDGE OF EACH FLAP AROUND SECOND FROM INBD ATTACH POINT. DAMAGE ON AFT FLAP APPROX 9 INCHES. DAMAGED SKIN ON THE AFT FLAP WAS REMOVED AND REPLACED WITH A TEMP REPAIR SECURED WITH SCREWS AND SPEED TAPE. SPEED TAPE ALSO USED ON THE FORE FLAP AND MID FLAP. THERE WAS NO DAMAGE TO RESTRICT THE MOVEMENT OF THE FLAPS. WHEELWELLS, ENGINE, FLAP WELLS, EMPENNAGE, FLAP TRACKS, CARRIAGES AND CANOE FAIRINGS INSPECTED WITH NO DAMAGE FOUND. ACFT FERRIED TO DEN AND LANDED WITHOUT INCIDENT. A SUPPLEMENTAL MRR WILL BE SUBMITTED WHEN ADDITIONAL INFORMATION IS OBTAINED. (X)

Part: FEEDER STRIP — FAILED (CABIN)

MSP - DURING SERVICE CHECK, MAINTENANCE REPORTED EMERGENCY AISLE PATH LIGHTING AT ROW 19 DEF TO ROW 23 DEF INOPERATIVE. MAINTENANCE REPLACED FEEDER STRIP AND SYSTEM CHECKED OK. (M)

Part: KEEL BEAM — CORRODED (BS 546-549)

PAE - FOUND CORROSION ON RT KEEL BEAM HORIZONTAL FLANGE AT BS 546-549, RBL 6.5, WL 148. REMOVED CORROSION AND FOUND OUT OF LIMITS PER SRM. FABRICATED AND INSTALLED REPAIR STRAPS PER EO NR 96-0582. ALL WORK ACCOMPLISHED ON NRC FUSELAGE 55, UNDER WORK ORDER NR 214912. (M)

Part: WIRE — EXPOSED (CABIN)

DEN - FLT 752 - UPON ARRIVAL, FLIGHT CREW REPORTED EMERGENCY AISLE PATH LIGHTING WIRES EXPOSED AT ROW 11. MAINTENANCE REPAIRED WIRING AND SYSTEM CHECKED OKAY.