N311FL

Part: FITTING — CRACKED (HAND RAIL) · airframe 3,697 hrs · 2,462 cycles

THE PASSENGER ENTRY DOOR FORWARD HANDRAIL ATTACH FITTING ON DOOR WAS FOUND CRACKED AND PEELED BACK, WITH UPPER RIVET ATTACHING THE FITTING TO THE DOOR STRUCTURE PULLED THROUGH THE DOOR STRUCTURE.

Part: CONTROL CABLE — CHAFED (ELEVATOR) · airframe 1,750 hrs · 1,154 cycles

DURING A SCHEDULED INSPECTION, MX FOUND THE ELEVATOR CABLES TO HAVE CHAFE MARKS, PN: 505-15041-403 & 505-15042-403. LOCATION OF CHAFE MARKS WERE IN THE VERTICAL STAB AT THE FITTING FORWARD OF THE RUDDER TRIM ACTUATOR. BOTH CABLES WERE REPLACED.

Part: STARTER GEN — VIBRATION (NR 2 ENGINE) · airframe 1,528 hrs · 998 cycles

THE CREW ADVISED AT FL450 THEY EXPERIENCED A HIGH VIBRATION FROM THE NR 2 ENGINE ACCOMPANIED BY A NR 2 GENERATOR FAILURE, THE CREW FOLLOWED THE CHECKLIST FOR HIGH VIBE WHICH ULTIMATELY RESULTED WITH SHUTTING NR 2 ENGINE DOWN IN FLIGHT AND DECLARING AN EMERGENCY. MX FOUND THE NR 2 STARTER/GENERATOR FAILED AND REPLACED IT.

Part: SKIN — CRACKED (INLET) · airframe 149 hrs · 113 cycles

DURING INSPECTION OF ENGINE INLETS, CRACKS AND MISSING/DAMAGED FASTENERS WERE FOUND ON THE RH ENGINE INLET. THE FASTENERS WERE REPLACED. ADDITIONAL CORRECTIVE ACTIONS REQUIRE THE REPLACEMENT OF THE INLET WITH A -405 UNIT; IN THE MEAN TIME, THE AIRCRAFT MANUFACTURER HAS DETERMINED THAT THE DAMAGE IS ACCEPTABLE AND HAS ALLOWED THE INLET TO CONTINUE IN SERVICE WITH ADDITIONAL PERIODIC INSPECTION REQUIREMENTS. THE INLET WILL BE REPLACED AT A LATER DATE.

Part: SKIN — CRACKED (INLET) · airframe 149 hrs · 113 cycles

DURING INSPECTION OF ENGINE INLETS, CRACKS AND MISSING/DAMAGED FASTENERS WERE FOUND ON THE LT ENGINE INLET. THE FASTENERS WERE REPLACED. ADDITIONAL C/A REQUIRE THE REPLACEMENT OF THE INLET WITH A -405 UNIT; IN THE MEAN TIME, THE ACFT MFG HAS DETERMINED THAT THE DAMAGE IS ACCEPTABLE AND HAS ALLOWED THE INLET TO CONTINUE IN SERVICE WITH ADDITIONAL PERIODIC INSP REQUIREMENTS. THE INLET WILL BE REPLACED AT A LATER DATE.

Part: SKIN — DENTED (FUSELAGE)

DENT AT RT EXTERNAL FUSELAGE AT BS 871 BETWEEN S-22R AND S-23R.

Part: SKIN — CRACKED (FUSELAGE)

FUSELAGE EXTERNAL SKIN CRACKED AT S-24R BETWEEN BS 727D - 727E.

Part: STRINGER — CRACKED (FUSELAGE)

STRINGER 27R CRACKED.

Part: SKIN — DENTED (FUSELAGE)

FUSELAGE SKIN HAS DENT AT BS 480 S-26R - S-28R.

Part: SKIN — DENTED (FUSELAGE) · airframe 43,795 hrs

DENT AT RT EXTERNAL FUSELAGE SKIN AT BS 391.5 BETWEEN S-22R AND S-23R.

Part: BULKHEAD — CRACKED (FUSELAGE) · airframe 43,795 hrs

CRACK APPROX. 5.5 INCHES BELOW WL 207 IB SIDE LBL 5.7 APPROX. 1.2 INCH IN LENGTH AT BS 178 BULKHEAD.

Part: SKIN — DENTED (FUSELAGE) · airframe 43,795 hrs

DENT 3 IN DIAMETER, DEPTH .015 INCHES FUSELAGE S 1070 S-14L FRONTIER DENT TALLY ITEM NR 3.

Part: SKIN — DENTED (FUSELAGE) · airframe 43,795 hrs

DENT AT LT EXTERNAL FUSELAGE SKIN AT BS 997.5 BETWEEN S-13L AND S-14L.

Part: SKIN — DENTED (FUSELAGE) · airframe 43,795 hrs

DENT AT RT EXTERNAL FUSELAGE SKIN AT BS 876 S-21R AND S-22R.

Part: FRAME — CRACKED (BULKHEAD) · airframe 43,795 hrs

BS 178 BULKHEAD RT SIDE AFT SIDE FRAME HAS EVIDENCE OF CRACK ABOVE AND BELOW WL 207.

Part: BULKHEAD — CRACKED (FUSELAGE) · airframe 43,795 hrs

CRACK APPROX 8 IN BELOW WL 207 INBD SIDE RBL 5.7 APPROX 1.5" IN LENGTH AT BS 178 BULKHEAD.

Part: SKIN — DENTED (FUELAGE) · airframe 43,795 hrs · 26,381 cycles

DENT IN LEFT FUSELAGE EXTERIOR SKIN BS 935 S-26L.

Part: SKIN — DENTED (FUSELAGE) · airframe 43,795 hrs · 26,381 cycles

CREASE IN DENT AT BS 971 BETWEEN S-24L-25L 2 INCHES X .86 A/Y = 23.3. S/O NR 109002, OPS NR 25863.

Part: SKIN — DENTED (FUSELAGE) · airframe 43,795 hrs · 26,381 cycles

CREASES IN DENTS AND ON TOP OF STRINGER 27R AT BS 951 - 952 A/Y = 24.7 A/Y 1.875 X .076.

Part: HINGE FITTING — CRACKED (R1 DOOR) · airframe 43,756 hrs · 26,356 cycles

INSPECTION REPORTED R1 DOOR UPPER HINGE ARM FITTING CRACKED. DOOR FRAME CRACKED AT HINE ARM CUTOUT. REPLACED R1 DOOR UPPER HINGE CASTING PER SRM 51-40-02 AND 51-10-02

Part: FLOORBEAM — CORRODED (FUSELAGE) · corrosion level 2 · airframe 40,600 hrs · 24,532 cycles

DURING C-7 CHECK, INSPECTION REPORTED AFT CABIN FLOORBEAM AT STA 986 CORRODED. CORROSION ON FLOORBEAM TOP FLANGE FOUND TO BE OUT OF LIMITS PER SRM 53-60-31. REMOVED FLOORBEAM UPPER FLANGE, FABRICATED REPAIR T-CAP, ALODINED, PRIMED, PAINTED AND INSTALLED REPAIR PER SRM 51-40-02 AND EA B3-53R-10331.

Part: SUPPORT — CORRODED (FUSELAGE) · corrosion level 2 · airframe 40,600 hrs · 24,532 cycles

DURING C-7 CHECK, INSPECTION REPORTED LT AFT GALLEY WALL SUPPORT CORRODED AT STA 989, LBL 44. REPLACED SUPPORT PER SOPM 20-41-02 AND SRM 51-40-02.

Part: SCREW — LOOSE (RUDDER) · airframe 40,600 hrs · 24,532 cycles

DURING C-7 CHECK, INSPECTION REPORTED SCREWS F2 AND F4 WERE FOUND LOOSE PER RUDDER INSPECTION PERFORMED PER EO B3-55-00AD-0001-DY, PART 2, STEPS 2 AND 4. REPLACED BOLTS PER EO B3-55-00AD-004-DY.

Part: FRAME — CRACKED (FUSELAGE) · airframe 40,600 hrs · 24,532 cycles

DURING C-7 CHECK, INSPECTION REPORTED BODY FRAME CRACKED AND BENT IN FWD CARGO COMPARTMENT AT STA 460, STR 28R. REMOVED DAMAGED AREA, FABRICATED AND INSTALLED REPAIR PER SRM 53-00-07, FIG. 203.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · corrosion level 2 · airframe 40,600 hrs · 24,532 cycles

DURING C-7 CHECK, INSPECTION REPORTED FLOOR SUPPORT CORRODED AT NUT PLATE HOLES, RBL 51, STA 947 TO STA 967, WL 208. REPLACED FLOOR SUPPORT PER SRM 51-40-2 AND 53-60-51.

Part: WEB — CORRODED (L-2 DOOR) · corrosion level 2 · airframe 40,600 hrs · 24,532 cycles

DURING C-7 CHECK, INSPECTION REPORTED L-2 DOOR WEB CORRODED FROM STA 949 TO STA 991.5. FABRICATED AND INSTALLED REPLACEMENT WEB PER SRM 51-40-02, 53-60-51, 53-60-15 AND DRAWING 65-45855.

Part: FLOORBEAM — CORRODED (FUSELAGE) · corrosion level 2 · airframe 40,600 hrs · 24,532 cycles

DURING C-7 CHECK, INSPECTION REPORTED AFT FLOORBEAM AT STA 947 CORRODED ALONG GOUGE 20 INCHES EITHER SIDE OF CENTER LINE. REPLACED T-CAP PER EA B3-53R-10330 AND SRM 51-40-02.

Part: SUPPORT — CORRODED (GALLEY) · corrosion level 2 · airframe 40,600 hrs · 24,532 cycles

DURING C-7 CHECK, INSPECTION REPORTED LT AFT GALLEY WALL SUPPORT CORRODED AT STA 989, LBL 44. REPLACED WALL SUPPORT PER SOPM 20-41-02 AND SRM 51-40-02.

Part: CHANNEL — CORRODED (FUSELAGE) · corrosion level 2 · airframe 40,600 hrs · 24,532 cycles

ZEE CHANNEL AT STA 993, LBL 30 TO LBL 40 CORRODED. FABRICATED AND INSTALLED REPLACEMENT Z-CHANNEL PER SRM 51-10-02, PAGE 37, SRM 51-30-01 AND SOPM 20-41-02.

Part: FLOORBEAM — CORRODED (FUSELAGE) · corrosion level 2 · airframe 40,600 hrs · 24,532 cycles

DURING C-7 CHECK, INSPECTION REPORTED FLOORBEAM AT STA 950, RBL 26 TO RBL 49, WL 208 CORRODED AT FLOORBOARD HOLES. FABRICATED AND INSTALLED REPLACEMENT FLOORBEAM PER SRM 53-60-51 AND 51-10-02.

Part: FLOORBEAM — CORRODED (FUSELAGE) · corrosion level 2 · airframe 40,600 hrs · 24,532 cycles

DURING C-7 CHECK, INSPECTION REPORTED AFT GALLEY FLOORBEAM WEB CORRODED AT STA 986.5, LBL 42. FABRICATED AND INSTALLED REPLACEMENT WEB PER SRM 53-60-51, 51-40-02, MM 51-21-41 AND BOLD DRAWING 65-46812.

Part: SILL — CORRODED (FUSELAGE) · corrosion level 2 · airframe 40,600 hrs · 24,532 cycles

DURING C-7 CHECK, INSPECTION REPORTED SILL PLATE AT L2 DOOR FLOOR CORRODED. REPLACED MOP SILL PER SRM 51-10-02.

Part: FLOORBEAM — CORRODED (FUSELAGE) · corrosion level 2 · airframe 40,600 hrs · 24,532 cycles

DURING C-7 CHECK, INSPECTION REPORTED AFT GALLEY FLOORBEAM CORRODED ON WEB AND UNDER GALLEY ATTACH POINT, RT SIDE, STA 986, RBL 42. BLENDED CORROSION ON WEB AND FOUND TO BE OUT OF LIMITS PER SRM 53-60-51. REMOVED DAMAGED SHEAR WEB AND COMMON SUPPORT ANGLES PER SRM 51-40-02. FABRICATED REPLACEMENT WEB, ALODINED, PRIMED AND PAINTED PER SOPM 20-41-02. INSTALLED REPLACEMENT WEB AND SUPPORT ANGLES PER SRM 51-40-02.

Part: WEB — CORRODED (FUSELAGE) · corrosion level 2 · airframe 40,600 hrs · 24,532 cycles

DURING C-7 CHECK, INSPECTION REPORTED LT TOILET SUPPORT WEB CORRODED. CORROSION FOUND TO BE OUT OF LIMITS PER 737-300 SRM 53-60-51. REMOVED DAMAGED LT AFT TOILET SUPPORT WEB. FABRICATED REPLACEMENT WEB PER BOEING DRAWING 65C32707. ALODINED REPLACEMENT LT AFT TOILET SUPPORT WEB PER MM 51-21-41. PRIMED AND PAINTED PER SOPM 20-44-02. INSTALLED REPLACEMENT WEB PER SRM 51-40-02.

Part: WEB — CORRODED (FUSELAGE) · corrosion level 2 · airframe 40,600 hrs · 24,532 cycles

DURING C-7 CHECK, INSPECTION REPORTED RT TOILET SUPPORT WEB CORRODED. BLENDED CORROSION, FOUND TO BE OUT OF LIMITS PER 737-300 SRM 53-60-51. REMOVED RT AFT TOILET WEB SUPPORT. FABRICATED REPLACEMENT WEB PER BOEING DRAWING 65C72707. ALODINED REPLACEMENT WEB PER MM 51-21-41. PRIMED AND PAINTED PER SOPM 20-44-02. INSTALLED REPLACEMENT WEB PER SRM 51-40-02.

Part: SILL — CORRODED (FUSELAGE) · corrosion level 2 · airframe 40,600 hrs · 24,532 cycles

DURING C-7 CHECK, INSPECTION REPORTED L1 DOOR MOP SILL CORRODED THE WIDTH OF THE DOORWAY AND EXTENDING AFT TO THE END OF THE CORD. REPLACED MOP SILL IAW SRM 53-10-15.

Part: SKIN — CRACKED (FUSELAGE) · airframe 40,600 hrs · 24,532 cycles

DURING C-7 CHECK, INSPECTION REPORTED RT FUSELAGE SKIN CRACKED AT LOWER AFT CORNER OF R-1 DOOR CUTOUT. REMOVED DAMAGED AREA AND REPAIRED PER SRM 53-10-01 FIG 202.

Part: MOUNT — CORRODED (LAVATORY) · corrosion level 2 · airframe 40,600 hrs · 24,532 cycles

DURING C-7 CHECK, INSPECTION REPORTED FWD LAVATORY MOUNT BLOCK AT STA 303, LBL 12, CORRODED. REPLACED LAVATORY MOUNT PER SRM 53-10-15, SRM 53-10-51 AND DRAWING 65C33970.

Part: STRINGER — CORRODED (FUSELAGE) · corrosion level 2 · airframe 40,600 hrs · 24,532 cycles

DURING C-7 CHECK, INSPECTION REPORTED AFT CARGO COMPARTMENT FLOOR STRINGER AND NUT PLATE CORRODED AT STA 727B, STR 2L. REPLACED FLOOR BEAM STRINGER PER SRM 53-00-53 FIG 201.

Part: STRINGER — CORRODED (FUSELAGE) · corrosion level 2 · airframe 40,600 hrs · 24,532 cycles

DURING C-7 CHECK, INSPECTION REPORTED AFT CARGO COMPARTMENT FLOOR STRINGER AND NUT PLATE CORRODED AFT OF STA 727A, RT MID STRINGER. REPAIRED AFT CARGO COMPARTMENT FLOORBEAM PER SRM 53-00-53 FIG 201.

Part: PANEL — CRACKED (CARGO BAY) · airframe 40,600 hrs · 24,532 cycles

DURING C-7 CHECK, INSPECTION REPORTED TRANSITION PANEL IN FWD CARGO COMPARTMENT CRACKED AT NUT PLATE HOLE, STA 430 + 11, BL 24R. FABRICATED AND INSTALLED NEW TRANSITION STRIP PER SRM 51-40-02.

Part: SKIN — CRACKED (FUSELAGE) · airframe 40,600 hrs · 24,532 cycles

DURING C-7 CHECK, INSPECTION REPORTED RT AFT FUSELAGE SKIN CRACKED JUST BELOW EMERGENCY LIGHT AT STA. 727, STR. 25R. CUT OUT DAMAGED SKIN. FABRICATED AND INSTALLED REPAIR DOUBLER IAW SRM 53-00-01, PAGE 204-206.

Part: SPINDLE — WORN (TE FLAP) · airframe 40,316 hrs · 24,360 cycles

INSPECTION REPORTED EXCESSIVE PLAY AND WEAR IN RT OB NR 8 FLAP CARRIAGE SPINDLE. REPLACED SPINDLE, SPINDLE BEARING AND BUSHINGS AND FLAP SADDLE.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · corrosion level 2 · airframe 38,262 hrs · 23,136 cycles

DURING C-4 CHECK, INSPECTION REPORTED CORROSION ON FLOOR SUPPORT AT STA. 727D + 5. FABRICATED AND INSTALLED REPAIR PER SRM 53-00-53.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · corrosion level 2 · airframe 38,262 hrs · 23,136 cycles

DURING C-4 CHECK, INSPECTION REPORTED CORROSION ON FLOOR SUPPORTS BETWEEN STA. 847 AND 867. FABRICATED AND INSTALLED REPAIR PER SRM 53-00-53.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · corrosion level 2 · airframe 38,262 hrs · 23,136 cycles

DURING C-4 CHECK, INSPECTION REPORTED CORROSION ON FLOOR SUPPORT AT STA. 772, BETWEEN RBBL 8.10 AND LBBL 12.5. FABRICATED AND INSTALLED REPAIRS PER SRM 53-00-53.

Part: STRINGER — CRACKED (FUSELAGE) · airframe 34,794 hrs · 21,383 cycles

DURING C-5 CHECK, INSPECTION REPORTED CRACK ON STRINGER 6L, STA 798.

Part: FLOOR PANEL — CRACKED (FUSELAGE) · airframe 34,794 hrs · 21,383 cycles

DURING C-5 CHECK, INSPECTION REPORTED CRACK IN FWD CARGO COMPARTMENT FLOOR PANEL AT STA 490, STR 26R.

Part: PROXIMITY SWITCH — OUT OF ADJ · airframe 33,743 hrs · 20,860 cycles

REJECTED TAKEOFF. FLIGHT CREW REPORTED AFT CARGO COMPARTMENT DOOR LIGHT ILLUMINATED UPON REACHING TAKEOFF THRUST. ADJUSTED AFT CARGO COMPARTMENT DOOR PROXIMITY SWITCH.

Part: DOOR FRAME — CORRODED (AFT CARGO BAY) · corrosion level 2 · airframe 31,627 hrs · 19,875 cycles

DURING C-4 CHECK, INSPECTION REPORTED AFT CARGO COMPARTMENT DOOR FRAME CORRODED AT STA 867. MAINTENANCE REMOVED SUPPORT ANGLE, INTERCOSTAL AND TRANSITION WEB AT STR 25R, STA 847 TO 867, AND CUT OUT DAMAGED PORTION OF FRAME. FABRICATED AND INSTALLED FRAME DOUBLER PER SRM 51-70-11 AND EA 53-737-114, FIG 2. INSTALLED NEW INTERCOSTAL AND SUPPORT ANGLE AND REINSTALLED TRANSITION WEB PER EA 53-737-114.

Part: SKIN — CORRODED (FUSELAGE) · corrosion level 2 · airframe 31,627 hrs · 19,875 cycles

DURING C-4 CHECK, INSPECTION REPORTED INTERGRANULAR CORROSION ON INSIDE SKIN OF C2 DOOR CUTOUT, AFT LOWER CORNER. REMOVED CORROSION ON BEAR STRAP PER SRM 51-10-02. FOUND TO BE OUT OF LIMITS. FABRICATED AND INSTALLED DOUBLER AND TRIPLER PER SRM 53-30-3, FIG 46, DETAIL 6. FABRICATED AND INSTALLED NEW SCUFF PLATE PER EA 53-737-114.

Part: FLOORBEAM — CORRODED (FUSELAGE) · corrosion level 2 · airframe 31,627 hrs · 19,875 cycles

DURING C-4 CHECK, INSPECTION REPORTED AFT FUSELAGE FLOORBEAM AT STA 986.5 CORRODED ACROSS TOP. MAINTENANCE FABRICATED AND INSTALLED REPLACEMENT FLOOR BEAM PER SRM 53-00-51.

Part: FLOORBEAM — CORRODED (AFT CARGO BAY) · corrosion level 2 · airframe 31,627 hrs · 19,875 cycles

DURING C-4 CHECK, INSPECTION REPORTED AFT CARGO COMPARTMENT FLOORBEAM CORRODED AT STA 847, STR 26R. MAINTENANCE REPLACED FLOORBEAM SUPPORT STRAP AND WEB PER SDR 51-10-02.

Part: FLOORBEAM — CORRODED (AFT CARGO BAY) · corrosion level 2 · airframe 31,627 hrs · 19,875 cycles

DURING C-4 CHECK, INSPECTION REPORTED CORROSION ON AFT CARGO COMPARTMENT FLOOR SUPPORT BEAM AT STA 867, RBL 15. MAINTENANCE REPLACED FLOOR SUPPORT BEAM PER SRM 51-30-02 AND 51-10-02.

Part: FLOORBEAM — CORRODED (FUSELAGE) · corrosion level 2 · airframe 31,627 hrs · 19,875 cycles

DURING C-4 CHECK, INSPECTION REPORTED CORROSION ACROSS TOP OF AFT FUSELAGE FLOORBEAM INTERCOSTAL CAP, STA 951.5, BETWEEN 26 LBL AND 50 LBL. MAINTENANCE REMOVED FLOORBEAM INTERCOSTAL, AND FABRICATED, PRIMED AND INSTALLED REPLACEMENT FLOORBEAM INTERCOSTAL PER EA 53-737-113.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · corrosion level 2 · airframe 31,627 hrs · 19,875 cycles

DURING C-4 CHECK, INSPECTION REPORTED AFT FUSELAGE FLOOR SUPPORT CORRODED AT LBL 16, STA 950. MAINTENANCE FABRICATED AND INSTALLED REPLACEMENT FLOOR SUPPORT PER SRM 51-10-02.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · corrosion level 2 · airframe 31,627 hrs · 19,875 cycles

DURING C-4 CHECK, INSPECTION REPORTED AFT FUSELAGE FLOOR SUPPORT CORRODED AT LBL 12, BETWEEN STA 947.5 AND STA 967. MAINTENANCE FABRICATED AND INSTALLED REPLACEMENT FLOOR SUPPORT PER EA 53-737-113.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · corrosion level 2 · airframe 31,627 hrs · 19,875 cycles

DURING C-4 CHECK, INSPECTION REPORTED CORROSION ON AFT FUSELAGE FLOOR SUPPORT AT LBL 24, STA 947.5 TO 967. MAINTENANCE REMOVED AFT FUSELAGE FLOOR SUPPORT, TREATED, PRIMED AND INSTALLED NEW FLOOR SUPPORT PER SRM 53-60-51.

Part: FLOORBEAM — CORRODED (FUSELAGE) · corrosion level 2 · airframe 31,627 hrs · 19,875 cycles

DURING C-4 CHECK, INSPECTION REPORTED CORROSION ON AFT FUSELAGE FLOORBEAM AT STA 947.5. MAINTENANCE REMOVED FLOORBEAM, FABRICATED, TREATED, PRIMED AND INSTALLED REPLACEMENT FLOORBEAM PER SRM 53-00-51.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · corrosion level 2 · airframe 31,627 hrs · 19,875 cycles

DURING C-4 CHECK, INSPECTION REPORTED CORROSION ON AFT FUSELAGE FLOOR SUPPORT AT LBL 3, STA 947.5 TO 967. MAINTENANCE REMOVED AFT FUSELAGE FLOOR SUPPORT, TREATED, PRIMED AND INSTALLED NEW FLOOR SUPPORT PER EA 53-737-113.

Part: WEB — CORRODED (FUSELAGE) · corrosion level 2 · airframe 31,627 hrs · 19,875 cycles

DURING C-4 CHECK, INSPECTION REPORTED WEB CORRODED AT LT SIDE OF FUSELAGE, AFT OF STA 986.5, FWD OF PRESSURE WEB. MAINTENANCE FABRICATED AND INSTALLED REPLACEMENT WEB PER SRM 53-60-15, 51-40-02 AND SOPM 20-41-02.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · corrosion level 2 · airframe 31,627 hrs · 19,875 cycles

DURING C-4 CHECK, INSPECTION REPORTED CORROSION ON AFT FUSELAGE FLOOR SUPPORT, 14 INCHES LT OF CENTER LINE 0, BETWEEN STA 967 AND 986.5. MAINTENANCE INSTALLED INTERCOSTAL PER SRM 51-40-02.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · corrosion level 2 · airframe 31,627 hrs · 19,875 cycles

DURING C-4 CHECK, INSPECTION REPORTED CORROSION ON AFT FUSELAGE FLOOR SUPPORT, 14 INCHES RBL, BETWEEN STA 967 AND 986.5. MAINTENANCE FABRICATED AND INSTALLED REPLACEMENT FLOOR SUPPORT PER SRM 51-10-02, 51-40-02 AND EA 53-737-113.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · corrosion level 2 · airframe 31,627 hrs · 19,875 cycles

DURING C-4 CHECK, INSPECTION REPORTED CORROSION ON FUSELAGE STRUCTURE AT AFT GALLEY LOWER DOOR FRAME, STA 990 - 1006. MAINTENANCE REPLACED MOP SILL AND WEB PER SRM 51-40-02, 51-10-02 AND 51-20-05.

Part: CREASE BEAM — CORRODED (FUSELAGE) · corrosion level 2 · airframe 31,627 hrs · 19,875 cycles

DURING C-4 CHECK, INSPECTION REPORTED CORROSION AT AFT ENTRY DOOR THRESHOLD, STA 986. MAINTENANCE REMOVED CREASE BEAM, CLEANED UPPER AND LOWER SURFACE BELOW CREASE BEAM, BURNISHED LIGHT SURFACE CORROSION AND FOUND TO BE WITHIN LIMITS. REMOVED DAMAGED DOUBLER, FABRICATED AND INSTALLED REPLACEMENT DOUBLER. FABRICATED AND INSTALLED REPLACEMENT CREASE BEAM. WORK WAS PERFORMED PER SRM 51-40-06 AND 53-60-15.

Part: FLOOR SUPPORT — CORRODED (AFT FUSELAGE) · corrosion level 2 · airframe 31,627 hrs · 19,875 cycles

DURING C-4 CHECK, INSPECTION REPORTED CORROSION ON AFT FUSELAGE FLOOR SUPPORT, 2 INCHES FROM LT CENTER LINE 0, BETWEEN STA 986.5 AND 967. MAINTENANCE INSTALLED WEB BETWEEN STA 986.5 AND 967 PER SRM 51-10-2 AND REPLACED FLOORBEAM CAP AT STA 967 PER SRM 53-00-51.

Part: FLOORBEAM — CORRODED (FUSELAGE) · corrosion level 2 · airframe 31,627 hrs · 19,875 cycles

DURING C-4 CHECK, INSPECTION REPORTED CORROSION ACROSS TOP OF AFT FUSELAGE FLOORBEAM AT STA 967. REPLACED FLOORBEAM CAP AT STA 967 FROM LBL 37.5 TO RBL 36 PER SRM 53-00-51.

Part: FLOOR PANEL — CRACKED (CARGO BAY)

DEN - PRIOR TO DEPARTURE, MAINTENANCE REPORTED HOLE IN AFT CARGO COMPARTMENT FLOOR PANEL NR 2 AND FLOORBEAM AT STATION 747, RBL 19, CRACKED AT TIE DOWN. MAINTENANCE REMOVED DAMAGED FLOOR PANEL AND DAMAGED SECTION OF FLOORBEAM. FABRICATED REPLACEMENT FLOOR PANEL AND NEW SECTION OF FLOORBEAM AND INSTALLED PER SRM 53-00-53, FIG 201. (M)

Part: SKIN — CORRODED (SERVICE PANEL)

DEN - DURING C-5 CHECK INSPECTION, FOUND CORROSION ON FORWARD LAVATORY SERVICE PANEL BETWEEN SKIN WHERE DUMP FITTING IS MOUNTED. MAINTENANCE FABRICATED REPLACEMENT BRACKETS, HAT SECTION AND STIFFENER AND REPAIRED PER EA 53-737-058 AND BOEING DRAWING 65-45802. (M)

Part: ACTUATOR — FAILED (RT MLG)

SFO - FLT 653 - DURING APPROACH INTO SFO, FLIGHT CREW REPORTED THE RT MAIN LANDING GEAR WOULD NOT EXTEND. USED ALTERNATE METHOD TO EXTEND GEAR AND GREEN LIGHT ILLUMINATED. FERRIED AIRCRAFT TO DEN. MAINTENANCE REPLACED RT MAIN LANDING GEAR DOWNLOCK ACTUATOR. PERFORMED OPERATIONAL CHECK, LEAK CHECK AND GEAR SWING, AND SYSTEM CHECKED OKAY. CYCLES: 617. (X)