N904FR

Part: SILL — CORRODED (ZONE 200) · corrosion level 2 · airframe 37,981 hrs · 18,348 cycles

FRAME 66 RIGHT DOOR SILL BEAM SURFACE CORROSION AROUND FASTENER HOLE. REMOVED CORROSION AND FOUND TO BE WITHIN LIMITS IAW SRM 53-41-14 PB101, PARAGRAPH 4 B, FIG 101, SRM 51-21-11 AND SRM 51-23-11.

Part: SHEAR PLATE — CORRODED (ZONE 200) · corrosion level 2 · airframe 37,981 hrs · 18,348 cycles

FRAME 70 RIGHT SIDE SHEAR PLATE CORROSION. R & R SHEAR PLATE IAW EO AO-53EO-31434.

Part: FLOORBEAM — CORRODED (ZONE 200) · corrosion level 2 · airframe 37,981 hrs · 18,348 cycles

FR66, -Y1292 FLOORBEAM CORROSION. R & R FLOORBEAM REF SRM 51-42 -11 , PARAGRAPH 5.

Part: SILL — CORRODED (ZONE 200) · corrosion level 2 · airframe 37,981 hrs · 18,348 cycles

L2 DOOR CUT OUT AT DOOR SILL HAS CORROSION 5 PLACES. R & R SHAPE SILL IAW SRM 51-42-11 PARA 6.B AND D.

Part: PLATE — CORRODED (ZONE 200) · corrosion level 2 · airframe 37,981 hrs · 18,348 cycles

FRAME 70 LT SIDE SHEAR PLATE CORROSION. R & R SHEAR PLATE IAW EO AO-53EO-31434.

Part: SILL — CORRODED (ZONE 100) · corrosion level 2 · airframe 37,981 hrs · 183 cycles

AFT CARGO DOOR SILL HAS CORROSION IN SEVERAL PLACES FROM FRAMES 55A TO 59. R & R DOOR SILL IAW REF SRM 51-42- 11 , PARA 6.B. AND 7.B.

Part: BLADE — LACK OF LUBE (NR 1 ENGINE FAN) · airframe 36,435 hrs · 17,552 cycles

NR 1 ENGINE VIBRATION IN CLIMB OVER 4.0. VIBRATION WOULD FOLLOW THRUST. AIR TURN BACK. PERFORMED TSM TASKS 77-00-00-81 0-863-A AND 77-00-00-81 O-B64-A INCLUDING FAN BLADE LUBE REF AMM 72-21-00-210-004 AND COLD TRIM BALANCE REF AMM 71-00-00-750-001. MAXIMUM VIBRATION INDICATION AFTER COLD BALANCE WAS 1.8 AT NR 1 BEARING SENSOR AND 2.0 AT TURBINE REAR FRAME SENSOR. SUBSEQUENT OPERATIONAL CHECK FLIGHT WAS SATISFACTORY.

Part: ELECTRICAL BOX — ODOR (SEAT ROW 21ABC) · airframe 35,603 hrs · 17,156 cycles

PAX & F/A'S REPORTED THE STRONG BURNING ELECTRICAL ODOR IN ROW 20-22 A/C LEFT. FOUND SEB ROW 21ABC EMITTING ELECTRICAL ODOR, PERFORMED INSPECTIONS OF AFT GALLEYS & LAVS. INSPECTED LIVE TV SYS RACK IN AFT CARGO PIT, NO PROBLEMS NOTED REF AMM TSM 24-00-00-810-823.

Part: SWITCH — FAILED (EMERGENCY LIGHTS) · airframe 35,508 hrs · 17,110 cycles

EMERGENCY EXIT LIGHT SWITCH NOT INDICATING OFF WHEN PLACED IN THE OFF POSITION. REPLACED TOGGLE SWITCH 4WL (ON/OFF/ARM) REF ESPM 20-45-21, TEST OK REF AMM 33-51 -11-710-050.

Part: SUPPORT FITTING — CORRODED (ZONE 600) · corrosion level 2 · airframe 33,769 hrs · 16,222 cycles

C-CHECK: RT WING MLG SUPPORT RIB 5 FWD LUG INNER BORE HAS CORROSION. IAW EO A0-57EO-20243. REMOVED CORROSION BY OVER SIZING BORE TO 3.8772" AND INSTALLING NEW BUSHINGS. IAW SRM 57-26-13, PAR 5C AND FIG 203 AND 204.

Part: STOP — SEIZED (ACTUATOR) · airframe 32,934 hrs · 15,843 cycles

ACFT LOG PAGE 590497: AIR TURN BACK AT 01302. ECAM WARNING NR 2 ENGINE COMPRESSOR VANE (AIR RETURN. REPLACED NR 2 ENGINE MASTER BALLSCREW ACTUATOR STOP. REF AMM 75-31-50 PB 401, OPS CHECK NORMAL.

Part: WARNING LIGHT — ILLUMINATED (FLAP/SLATS) · airframe 30,019 hrs · 14,450 cycles

PILOT REPORT REF LOG PAGE 508494 ITEM(S) 1 FCTL FLAP FAULT (FLIGHT CONTROL FLAP FAULT)AND ITEM 2 FCTL SLAT FAULT (FLIGHT CONTROL SLAT FAULT) EMERGENCY DECLARED. OPS TEST OF THE FLAP AND SLAT SYS OK IAW AMM 27-54-00-710-002.

Part: BULB — BURNED OUT (EMERGENCY LIGHT) · airframe 29,347 hrs · 14,135 cycles

DURING VISUAL INSPECTION IT WAS NOTED THE EXIT SIGN BULB WAS BURNED OUT OVER FORWARD ENTRY. MAINTENANCE REMOVED AND REPLACED EMERGENCY EXIT SIGN BULB IAW AMM 33-51-16 PB 401.

Part: COFFEEMAKER — ODOR (GALLEY) · airframe 28,494 hrs · 13,738 cycles

REFERENCE LOG PAGES 492755 AND 492756. FLIGHT CREW MADE AN AIR RETURN DUE TO A BURNING ODOR IN THE AFT GALLEY. MX PERFORMED TROUBLESHOOTING IAW TSM 21-00-00-810-802, TSM 24-00-00-810-823 AND SIL 21-135. MX DETERMINED THE AFT GALLEY COFFEEMAKERS WERE CAUSING THE BURNING ODOR WHEN BREWING. MX REMOVED AND REPLACED BOTH AFT GALLEY COFFEEMAKERS IAW AMM 25-35-15 PB 401 AND PERFORMED SATISFACTORY OPS CHECK. THE ACFT WAS RETURNED TO SERVICE.

Part: HOOK — BROKEN (PAX DOOR) · airframe 27,984 hrs · 13,499 cycles

DURING C6 C-CHECK, INSP NOTED THAT THE L1 DOOR HANDLE WAS ABLE TO CLOSE WITHOUT THE DOOR BEING IN THE CLOSED POSITION. MX REMOVED AND REPLACED THE L1 DOOR HOOK ASSY IAW AMM 52-11-21-400-001.

Part: FLOOR PANEL — CORRODED (ZONE 200) · airframe 27,984 hrs · 13,499 cycles

DURING C6 C-CHECK, INSP NOTED THE L2 ENTRY DOOR FLOOR PANEL HAS SEVERAL SPOTS OF CORROSION AROUND FASTENER HOLES. MX REMOVED AND REPLACED THE FLOOR PANEL AT POSITION 261FF, IAW TASK CARD C534103-02.

Part: HOOK — BROKEN (ZONE 800) · airframe 27,984 hrs · 13,499 cycles

DURING C6 C-CHECK, INSP NOTED THE R2 DOOR CLOSING BEFORE DOOR WAS IN DOOR JAM. MX REMOVED AND REPLACED THE HOOK AT THE R2 DOOR HANDLE IAW AMM 52-13-21-400-001.

Part: FLOORBEAM — CORRODED (ZONE 200) · airframe 27,984 hrs · 13,499 cycles

DURING C6 C-CHECK, INSP NOTED CORRODED FASTENER HOLES AT STATION -Y1292 AND FRAME 66. MX REMOVED AND REPLACED THE FLOORBEAM IAW SRM 51-42-11 AND 51-44-11.

Part: SHEAR PLATE — CORRODED (ZONE 200) · airframe 27,984 hrs · 13,499 cycles

DURING C6 C-CHECK, INSP NOTED THE LT HAND SHEAR PLATE AT Y1292 BETWEEN FRAME 69 AND FRAME 70 WAS CORRODED AT THE AFT SCREW HOLE. MX REMOVED AND REPLACED THE SHEAR PLATE IAW SRM 51-42-11, 51-72-11, 51-44-11 AND 51-23-11.

Part: STRINGER — CORRODED (ZONE 200) · airframe 27,984 hrs · 13,499 cycles

DURING C6 C-CHECK, INSP NOTED CORROSION ON STR 44, SIX INCHES AFT OF FRAME 65 NEAR POTABLE WATER SERVICE PANEL. MX CUT OUT DAMAGED AREA, FABRICATED REPAIR STR AND INSTALLED IAW SRM 53-00-13, 51-42-11, 53-41-13 AND 51-21-11.

Part: SILL — CORRODED (ZONE 200) · airframe 27,984 hrs · 13,499 cycles

DURING C6 C-CHECK, INSPECTION NOTED THE L2 DOOR SILL HAS SEVERAL AREAS OF CORROSION. MX REMOVED AND REPLACED THE DOOR SILL IAW SRM 51-42-11 AND D53408505.

Part: SHEAR PLATE — CORRODED (ZONE 200) · airframe 27,984 hrs · 13,499 cycles

DURING C6 C-CHECK, INSPECTION NOTED THE RT SHEAR PLATE AT Y1732 BETWEEN FRAME 69 AND FRAME 70 HAS CORROSION. MX REMOVED AND REPLACED THE SHEAR PLATE IAW SRM 51-44-11 AND 51-42-11.

Part: FLOORBEAM — CORRODED (ZONE 200) · airframe 27,984 hrs · 13,499 cycles

SUPPLEMENTAL INFORMATION: REFERENCE NON ROUTINE C070051. DURING DEN C6 C-CHECK, INSPECTION NOTED CORROSION AROUND THE NUT PLATES LOCATED AT R2, Y1292 BETWEEN FRAME 66 AND FRAME 68. MAINTENANCE REMOVED AND REPLACED THE FLOORBEAM IAW SRM 51-44-11 AND 51-42-11.

Part: FLOORBEAM — CORRODED (ZONE 200) · airframe 27,984 hrs · 13,499 cycles

DURING C6 C-CHECK, INSP NOTED THE COUPLING ATTCH POINT AT L2, STATION Y1292 AND FRAME 68 HAS CORROSION. MX REMOVED AND REPLACED THE FLOORBEAM IAW SRM 51-42-11 AND DWG SD53472815 AND D53472780.

Part: FLOORBEAM — CORRODED (ZONE 200) · airframe 27,984 hrs · 13,499 cycles

DURING C6 C-CHECK, INSP NOTED THE COUPLING ATTACH POINT AT STATION Y1292 AND FRAME 68 HAS CORROSION. MX REMOVED AND REPLACED THE FLOORBEAM IAW SRM 53-41-14, 51-42-11 AND 51-44-11.

Part: FLOORBEAM — CORRODED (ZONE 200) · airframe 27,984 hrs · 13,499 cycles

DURING C6 C-CHECK, INSP NOTED CORROSION AROUND THE NUT PLATES AT L2, STATION Y1292 BETWEEN FRAME 66 AND FRAME 68. MX REMOVED AND REPLACED THE FLOORBEAM IAW SRM 51-42-11 AND DWG SD53472815.

Part: BULB — INOPERATIVE (EMERGENCY LIGHT) · airframe 25,634 hrs · 12,275 cycles

DURING HEAVY CHECK, MAINTENANCE NOTED THE EMERGENCY PATH LIGHTS WERE INOPERATIVE AT SEATS 3, 6, 7, 18 AND 22. MAINTENANCE REMOVED AND REPLACED ALL INOPERATIVE EMERGENCY PATH LIGHT BULBS AND PERFORMED OPERATIONAL CHECK IAW AMM 33-51-19 PB401.

Part: FIRE DETECTOR — NO TEST (ZONE 200) · airframe 25,124 hrs · 12,025 cycles

PILOT REPORTED THE NR 2 ENGINE FIRE PUSHBUTTON SWITCH LIGHT, CONTINUOUS REPETITIVE CHIME, BOTH MASTER WARNINGS AND ENGINE CONTROL PANEL FIRE LIGHT FAIL TO TEST. MAINTENANCE REMOVED AND REPLACED THE NR 2 ENGINE FIRE DETECTION UNIT IN ACCORDANCE WITH AMM 26-12-34 PB401 AND PERFORMED AN OPERATIONAL CHECK.

Part: SWITCH — FAULTY (EMERGENCY LIGHTS) · airframe 23,780 hrs · 11,335 cycles

DURING PRE-FLIGHT INSP, CREW NOTED THE EMERGENCY EXIT AND AISLE LIGHTS WERE ILLUMINATED IN THE ARMED POSITION. MAINT REMOVED AND REPLACED THE TOGGLE SWITCH AND PERFORMED AN OPS CHECK IAW AMM 33-51-00. UPON COMPLETION OF THE REPAIR IT WAS INSPECTED AND FOUND ACCEPTABLE. (A)

Part: SKIN — GOUGED (FUSELAGE) · airframe 22,630 hrs · 10,743 cycles

DURING PRE FLIGHT INSPECTION, THE FLIGHT CREW REPORTED AFT LEFT FUSELAGE SKIN GOUGE AND DENT AT FRAME 61 AND STRINGER 38 LEFT. BLENDED THE GOUGE IN ACCORDANCE WITH EA A9-53R-30192. INTERIM REPAIR WAS INSPECTED AND FOUND ACCEPTABLE, TDI 1061199 ISSUED FOR FOLLOW UP INSPECTION. INSPECTED THE DENT AND FOUND TO BE WITHIN LIMITS IN ACCORDANCE WITH SRM 53-41-11 FIGURE 101. DENT WAS TREATED, PRIMED AND PAINTED IN ACCORDANCE WITH EA A9-53R-30192. UPON COMPLETION OF THE WORK TDI 1061200 WAS ISSUED FOR A FOLLOW UP INSPECTION. UPON COMPLETION OF ALL WORK THE REPAIRS WERE INSPECTED AND FOUND ACCEPTABLE.

Part: STRINGER — DAMAGED (WING) · airframe 22,612 hrs · 10,737 cycles

DURING C5 C CHECK INSPECTION REPORTED DURING PERFORMANCE OF REPAIR STRINGER WAS DAMAGED. MAINTENANCE REPAIRED THE STRINGER IN ACCORDANCE WITH THE REQUIREMENTS OF SRM A319 51-27-00 PAGE 1 AND SRM 51-42-11 PAGE 7. FOLLOWING COMPLETION OF THE REPAIR, THE STRINGER WAS INSPECTED AND FOUND ACCEPTABLE.

Part: HINGE FITTING — CORRODED (RT MLG) · corrosion level 2 · airframe 22,612 hrs · 10,737 cycles

DURING C5 C CHECK INSPECTION REPORTED CORROSION WAS FOUND IN THE MOUNTING HOLES OF THE RIGHT MAIN LANDING GEAR FORWARD HINGE BEARING SUPPORT BRACKET. MAINTENANCE REAMED FITTING ONE SIZE OVER AND INSTALLED NEW BUSHING IN ACCORDANCE WITH THE REQUIREMENTS OF EA A9-52R-30180. UPON COMPLETION OF THE MAINTENANCE ACTION THE INSTALLATION WAS INSPECTED AND FOUND ACCEPTABLE.

Part: ENGINE — MALFUNCTIONED (NR 2) · airframe 19,658 hrs · 9,322 cycles

AIR TURN BACK AT 1710Z, FLIGHT CREW REPORTED NR 2 ENGINE ROLLBACK TO BETWEEN 45 PERCENT AND 55 PERCENT N1 DURING CLIMB-OUT OF 10,000 FT. ENGINE WAS ALSO MAKING VERY LOUD BANGS EVERY 3 SECONDS ACCOMPANIED BY LARGE VIBRATIONS FELT THROUGHOUT THE AIRCRAFT. ALL OTHER ENGINE INDICATIONS WERE WITHIN NORMAL RANGE. FLIGHT CREW DECLARED AN EMERGENCY AND LANDED IN KLAX WITHOUT INCIDENT. AIRCRAFT EXPERIENCED OVERWEIGHT LANDING. THE NR 2 ENGINE IS IN THE PROCESS OF BEING REPLACED. [6-13-07] A BORESCOPE OF THE NO. 2 ENGINE HAS REVEALED THE ROOT CAUSE OF THE DAMAGE TO BE THE SEPARATION OF A STAGE 5 BOOSTER BLADE.

Part: SKIN — DENTED (NR 1 SLAT) · airframe 19,419 hrs · 9,202 cycles

DURING TAKEOFF, NR 2 ENGINE FAN COWL DEPARTED AIRCRAFT HITTING NR 1 SLAT. SLAT HAD SEVERE DENT DAMAGE TO LEADING EDGE OF STRUCTURE. REPLACED NR 1 SLAT IAW AMM 27-84-63-400-002, REFERENCE SDR F3LA200700083.

Part: SKIN — DELAMINATED (ELEVATOR) · airframe 19,419 hrs · 9,202 cycles

DURING TAKEOFF, NR 2 ENGINE FAN COWL DEPARTED AIRCRAFT HITTING ELEVATOR ABOUT MID-SPAN. OUTER SKIN WAS DELAMINATED AND SHOWED LOSS OF INNER CORE MATERIAL. ALSO, THE END OF A COWL HOLD OPEN ROD WAS IMBEDDED IN THE ELEVATOR. [SUP 05-10-07] REPLACED RT ELEVATOR IAW AMM 27-34-41-000-001.

Part: SKIN — PUNCTURED (HORIZONTAL STAB) · airframe 19,419 hrs · 9,202 cycles

DURING TAKEOFF, NR 2 ENGINE FAN COWL DEPARTED AIRCRAFT HITTING OTBD HORIZONTAL STABILIZER LEADING EDGE. PUNCTURE WAS FOUND ABOUT MID SPAN OF LEADING EDGE. REPLACED RT OTBD HORIZONTAL STAB L/E IAW AMM 55-12-11-400-001, REFERENCE SDR F3LA200700083.

Part: SKIN — DENTED (NR 2 SLAT) · airframe 19,419 hrs · 9,202 cycles

DURING TAKEOFF, NR 2 ENGINE FAN COWL DEPARTED AIRCRAFT HITTING NR 2 SLAT. SLAT HAD SEVERE DENT AND GOUGE TO LEADING EDGE OF STRUCTURE. REPLACED NR 2 SLAT IAW AMM 27-84-64-400-002, REFERENCE SDR F3LA200700083.

Part: SKIN — GOUGED (WING) · airframe 19,419 hrs · 9,202 cycles

DURING TAKEOFF, NR 2 ENGINE FAN COWL DEPARTED AIRCRAFT HITTING INBD UNDER WING AREA. SEVERAL GOUGES AND SCRATCHES WERE FOUND BETWEEN RIBS 4 AND 6 AND STRINGERS 2 THRU 7.

Part: STRUCTURE — FAILED (NR 2 NACELLE) · airframe 19,419 hrs · 9,202 cycles

NR 2 ENGINE COWLING DEPARTED AIRCRAFT. CAUSE UNKNOWN AT THIS TIME AND IS UNDER INVESTIGATION BY THE FAA. [SUP 05-15-07] THE NR 2 ENGINE FWD CANTILEVER ASSY SUSTAINED SIGNIFICANT DAMAGE. REMOVED AND REPLACED NR 2 ENGINE CANTILEVER ASSY. PER EA A9-57R-11875.

Part: BATTERY — INOPERATIVE (EMERGENCY LIGHT) · airframe 17,765 hrs · 8,363 cycles

FLIGHT CREW REPORTED FRONT EMERGENCY EXIT LIGHTS INOP. IN AUTOMATIC. OPERATES OK IN (ON) POSITION. REPLACED EPSU AND BATTERY AT 10WL IAW AMM 33-51-38, PB401. OPS CHECK GOOD. THE PN AND SN FOR THE UNITS REMOVED ARE AS FOLLOWS: EPSU, P/N 3214-54-10, S/N 4136; BATTERY, P/N 3214-31, S/N 045213.

Part: FLOORBEAM — CORRODED (FUSELAGE) · corrosion level 2 · airframe 17,255 hrs · 8,094 cycles

DURING C-4 CHECK, INSPECTION REPORTED L2 DOOR THRESHOLD FLOORBEAM AT Y1732 AND FRAME 68 CORRODED ABOVE NUT PLATE. CORROSION DAMAGE ON DOOR SILL BEAM WAS FOUND TO EXCEED 50 PERCENT OF THE DEPTH OF THE BEAM AT THE NUT PLATE LOCATION. DAMAGE WAS FOUND TO BE OUT OF LIMITS IAW SRM 53-41-14, FIG. 101. CORROSION WAS FOUND TO BE LIMITED TO THE AREA AROUND NUT PLATE, CUT OUT CORRODED AREA IAW SRM 53-41-14, FIG. 201. FABRICATED AND INSTALLED REPAIR ANGLE IAW SRM 53-41-14, FIG. 201, AND SRM 51-75-12.

Part: PLATE — CORRODED (GIRT BAR) · corrosion level 2 · airframe 17,255 hrs · 8,094 cycles

DURING C-4 CHECK, INSPECTION REPORTED R1 DOOR FWD GIRT BAR FITTING ATTACH PLATE CORRODED. REPLACED FWD GIRT BAR PLATE ASSY. IAW SRM 51-42-11 AND AMM 20-21-11.

Part: COVER — CORRODED (L2 DOOR) · corrosion level 2 · airframe 17,255 hrs · 8,094 cycles

DURING C-4 CHECK, INSPECTION REPORTED L2 DOOR FLOORBOARD ACCESS COVER PLATE CORRODED ON LWR SIDE. COVER PLATE WAS FOUND TO BE OUT OF LIMITS PER SRM 53-41-14. FABRICATED AND INSTALLED NEW COVER PLATE PER SRM 51-44-11, AIRBUS DRAWING 10D53670092, AND SRM 51-75-13.

Part: PLATE — CORRODED (GIRT BAR) · corrosion level 2 · airframe 17,255 hrs · 8,094 cycles

DURING C-4 CHECK, INSPECTION REPORTED R2 DOOR FWD GIRT BAR PLATE CORRODED. REPLACED FWD GIRT BAR PLATE IAW AMM 52-13-31-400-003. SEALED AREA AROUND FWD PLATE AT R2 DOOR IAW AMM 52-13-31-400-007.

Part: FLOORBEAM — CORRODED (FUSELAGE) · corrosion level 2 · airframe 17,255 hrs · 8,094 cycles

DURING C-4 CHECK, INSPECTION REPORTED CORROSION ON FLOORBEAM (LONGERON) FWD OF FR68 AT Y1292. BLENDED OUT CORRODED AREA ON FLOORBEAM AND FOUND AREA TO BE OUT OF LIMITS IAW SRM 53-00-14, FIG. 102. REMOVED AND REPLACED FLOORBEAM FROM FR66 TO FR68 IAW SRM 51-42-11.

Part: WEB — CORRODED (FUSELAGE) · corrosion level 2 · airframe 17,255 hrs · 8,094 cycles

DURING C-4 CHECK, INSPECTION REPORTED CORROSION ON FLOOR WEB OB AND AFT OF BEAM AT FR69 AND Y1292. REMOVED FLOOR WEBS IAW SRM 51-42-11. FOUND UPPER WEB TO BE OUT OF LIMITS AND LOWER WEB TO BE WITHIN LIMITS IAW SRM 53-00-14. PERFORMED PANAMETRIC ULTRASONIC THICKNESS TEST ON LOWER WEB. FOUND MAX MATERIAL LOSS TO BE WITHIN .002 AND .003 IAW NTM 51-10-04, PART 4. TREATED, PRIMED AND PAINTED LOWER WEB IAW SRM 51-75-12. RIVETED NEW SHEAR PLATE WEB TO LOWER SUPPORT ANGLE WEB IAW SRM 51-42-11. REINSTALLED SUPPORT ANGLE WEB AND INSTALLED NEW SHEAR PLATE WEB IAW SRM 51-42-11 AND DRAWING NR 18D53474180.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · corrosion level 2 · airframe 17,255 hrs · 8,094 cycles

DURING C-4 CHECK, INSPECTION REPORTED CORROSION ON FLOOR SUPPORT IB OF L2 AT Y1292 FROM FR66 TO FR68 AT HOLES. FLOORBEAM WAS FOUND TO BE OUT OF LIMITS IAW SRM 51-00-14. REMOVED AND REPLACED FLOORBEAM FROM C64 TO C69 IAW SRM'S 51-42-11 AND 51-44-11.

Part: FLOORBEAM — CORRODED (FUSELAGE) · corrosion level 2 · airframe 17,255 hrs · 8,094 cycles

DURING C-4 CHECK, INSPECTION REPORTED CORROSION ON FLOORBEAM AFT OF L2 DOOR CUTOUT AT FR68 TO FR69, Y1292. FLOORBEAM WAS FOUND TO BE OUT OF LIMITS PER 53-00-14. REMOVED AND REPLACED FLOORBEAM FROM C64 TO C69 PER SRM'S 51-42-11 AND 51-44-11.

Part: FLOORBEAM — CORRODED (FUSELAGE) · corrosion level 2 · airframe 17,255 hrs · 8,094 cycles

DURING C-4 CHECK, INSPECTION REPORTED CORROSION ON FLOORBEAM (LONGERON) JUST AFT OF FR68 AT Y1292. BLENDED CORRODED AREA ON FLOORBEAM AND FOUND TO BE OUT OF LIMITS IAW SRM 53-00-14, FIG. 102. REMOVED AND REPLACED FLOORBEAM FROM FR68 TO FR69 IAW SRM 51-42-11.

Part: MOUNT — CORRODED (LAVATORY) · corrosion level 2 · airframe 17,255 hrs · 8,094 cycles

DURING C-4 CHECK, INSPECTION REPORTED CORROSION ON LAV MOUNT HOLE AT Y1292, FR16, IN FWD LAV AREA. REMOVED CORROSION FOUND TO BE OUT OF LIMITS IAW SRM 53-11-14. REPAIRED DAMAGED AREA IAW SRM'S 53-00-15, FIG.202(A)(B)(C)(D), 53-11-15, FIG. 202 (ITEM 5), 53-11-15, PAGE 211/212, ITEM 5, 51-47-00 AND 51-20-11.

Part: FLOORBEAM — CORRODED (FUSELAGE) · corrosion level 2 · airframe 17,255 hrs · 8,094 cycles

DURING C-4 CHECK, INSPECTION REPORTED CORROSION ON FLOORBEAM AT Y503.2 (LT SIDE) BETWEEN FR 14 AND FR16. FLOORBEAM WAS FOUND TO BE OUT OF LIMITS PER SRM 53-11-14. REPLACED FLOORBEAM PER SRM 51-42-12.

Part: FLOORBEAM — CORRODED (FUSELAGE) · corrosion level 2 · airframe 17,255 hrs · 8,094 cycles

DURING C-4 CHECK, INSPECTION REPORTED CORROSION ON FLOORBEAM AT Y1292, FR20. FOUND CORROSION OUT OF LIMITS SRM 53-11-14. REPLACED FLOORBEAM IAW SRM 51-42-11, 51-42-12, AND 53-11-15.

Part: FLOORBEAM — CORRODED (FUSELAGE) · corrosion level 2 · airframe 17,255 hrs · 8,094 cycles

DURING C-4 CHECK, INSPECTION REPORTED CABIN FLOORBEAM AT FR66 IB OF L2 DOOR CORRODED. FLOORBEAM WAS FOUND TO BE OUT OF LIMITS IAW SRM 53-00-14. REMOVED AND REPLACED FLOORBEAM FROM C64 TO C69 IAW SRM 51-42-11, 51-42-11, AND 51-44-11.

Part: BOLT — CORRODED (LAV MOUNT) · corrosion level 2 · airframe 17,255 hrs · 8,094 cycles

DURING C-4 CHECK, INSPECTION REPORTED FWD LAV MOUNT BOLT IN EE BAY CORRODED. REPLACED LAV MOUNT BOLT IAW W/C CP725-13.

Part: SMOKE DETECTOR — FAILED (AFT CARGO BAY) · airframe 5,434 hrs · 2,558 cycles

AIR TURN BACK. FLIGHT CREW REPORTED AFT CARGO SMOKE/HEAT ECAM WARNING. NO SMELL OF SMOKE, CARGO FLOOR WAS NOT HOT. DISCHARGED AFT CARGO BOTTLE. NOTE: THIS WAS A WARNING INDICATION ONLY, NOT AN ACTUAL FIRE. TROUBLESHOT SMOKE DETECTION SYSTEM AND REPLACED SENSOR. REPLACED AFT CARGO EXTINGUISHER BOTTLE. SYSTEM TESTED OKAY.

Part: SMOKE — DETECTED (CABIN) · airframe 567 hrs · 334 cycles

FLIGHT CREW REPORTED SMOKE IN CABIN AFTER LANDING. COULD NOT DETERMINE ORIGIN. SMOKE DISSIPATED AFTER 10 MIN. MAINTENANCE PERFORMED TASK 71-00-00-810-802 FOR SMOKE IN CABIN. FOUND NO EVIDENCE OF OIL CONTAMINATION. FOUND EVIDENCE OF WATER INGESTION AT NR 1 ENGINE RAM AIR INLET. PERFORMED ENGINE RUN, WITH NO SMOKE OR ODOR.