N902FR

Part: SLIDE — NO TEST (L1 DOOR) · airframe 55,410 hrs · 27,299 cycles

EPSU 10WL FAILED A BITE TEST AT THE L1 DOOR SLIDE. REMOVED AND REPLACED L1 DOOR SLIDE ASSEMBLY IAW AMM 25-62-44PB401. OPS CHECKED GOOD.

Part: HYDRAULIC LINE — LEAKING (ZONE 400) · airframe 54,154 hrs · 26,687 cycles

HYD G RSVR LO PRESS AND HYD G RSVR LO LVL ECAM MESSAGES. INFLIGHT LOSS OF GREEN HYDRAULIC SYSTEM. REMOVED AND REPLACED HYDRAULIC LINE BETWEEN HYDRAULIC PRESSURE HOSE AND PRESSURE SWITCH ON NUMBER 1 ENGINE. REFERENCE AMM 29-11-49 BLOCK 401. PERFORMED GREEN HYDRAULIC TEST. OPERATIONAL CHECK GOOD.

Part: ENGINE — ODOR (LEFT) · airframe 53,963 hrs · 26,601 cycles

STRONG FUMES SMELLED HALFWAY ON DESCENT. REMOVED AND REPLACED LT ENGINE.

Part: POWER SUPPLY — NO TEST (EMERGENCY LIGHTS) · airframe 53,335 hrs · 26,328 cycles

EMERGENCY LIGHTING FAILED TEST. REMOVED AND REPLACED THE EPSU 13WL. OPS CHECKED GOOD.

Part: BATTERY — DISCHARGED (CABIN) · airframe 50,563 hrs · 25,003 cycles

DURING INSPECTION THE EMER LIGHTS FAILED TEST FAULTS FIN 10WL. R & R BATTERY PACK FOR THE FWD LT EPSU 10WL, OPERATIONAL CHECKED GOOD IAW AMM 33-51-38 PB 401.

Part: LIGHT — INOPERATIVE (EXIT SIGN) · airframe 45,971 hrs · 22,780 cycles

EMERGENCY EXIT SIGN 53WL WING OVERHEAD HAD 10 BULBS INOPERATIVE. R & R 10 BULBS IAW AMM 33-51-17 PB 401.

Part: LIGHT — INOPERATIVE (EXIT SIGN) · airframe 45,971 hrs · 22,780 cycles

EMERGENCY EXIT SIGN 51WL WING OVERHEAD HAD 10 BULBS INOPERATIVE. R & R 10 BULBS IAW AMM 33-51-17 PB 401.

Part: DOOR FRAME — CRACKED (EMERGENCY EXIT) · airframe 42,718 hrs · 21,020 cycles

WHILE PERFORMING CARD FFT-522103-01-2-L, ISB 52-1145, LT OVERWING EXIT BOTH AFT & FWD FRAME SEGMENT 1 HAS CRACK ORIGINATING FROM FASTENER HOLE. REMOVED FWD & AFT CRACKED SEGMENT & INSTALLED NEW SEGMENT IAW SRM 51-42-11 PARA 6.

Part: ELEVATOR — CONTAMINATED (ZONE 300) · airframe 40,176 hrs · 19,636 cycles

LT ELEVATOR, THERMOGRPAHY INSPECTION SHOWS THREE INDICATIONS ON UPPER SKIN PANEL. INDICATIONS ARE IRREGULAR IN SHAPE AND BLACK IN COLOR. REMOVED SKIN AT 3 EACJ AREAS OF LIQUID INGRESS, COMBINED AREAS 2 & 3 DUE TO PROXIMITY. PREPARED SURFACE FOR REPAIR. DRIED REPAIR WITH HOT BONDER, APPLIED EC3524 CORE, APPLIED REPAIR PLYS, RESIN AND APPLIED VACUUM. SANDED REPAIRS SMOOTH, APPLIED CORE FILLER EPIBOND 156 A/B, APPLIED PRIMER AND TOP COAT IAW SRM 55-20-00, PB201, PAR 2A(1-2), 2B(1-2) AND SRM 55-20-11, PB201, PAR 5D(2)(E)AND FIG 204.

Part: SILL — CORRODED (ZONE 200) · corrosion level 2 · airframe 36,710 hrs · 17,834 cycles

AFT CARGO FROM FRAME 55A TO FRAME 58, DOOR SILL WEB HAS CORROSION IN NUMEROS AREAS. R & R DOOR SILL WEB IAW SRM 51-42-11 PARAGRAPH 6 AND 7.

Part: SKIN — CORRODED (ZONE 100) · airframe 28,332 hrs · 13,754 cycles

DURING DEN C6 C-CHECK, INSPECTION NOTED CORROSION ON FUSELAGE SKIN AROUND RIVET HOLE NUMBER TEN MARKED IN FORWARD CARGO PIT FOUR INCHES FORWARD OF FRAME 34 ON STINGER 43LH. MAINTENANCE REPAIRED IN REFERENCE TO ENGINEERING AUTHORIZATION A9-53R-31316.

Part: SKIN — CORRODED (ZONE 100) · airframe 28,332 hrs · 13,754 cycles

REFERENCE NON ROUTINE C068734. DURING DEN C6 C-CHECK, INSPECTION NOTED CORROSION ON FUSELAGE SKIN AROUND RIVET HOLE NR 12 IN FORWARD CARGO PIT FORWARD OR FRAME 34 BETWEEN STRINGER 43 LT AND CENTER LINE. MAINTENANCE REPAIRED IAW EA A9-53R-31316.

Part: SKIN — CORRODED (ZONE 100) · airframe 28,332 hrs · 13,754 cycles

REFERENCE NON ROUTINE C068733. DURING C6 C-CHECK, INSPECTION NOTED CORROSION ON FUSELAGE SKIN ON INSIDE FORWARD CARGO PIT FORWARD OF FRAME 34 BETWEEN STINGER 42L AND 42R AROUND FASTNER HOLES FOR CENTER FAIRING. MAINTENANCE REPAIRED IAW ENGINEERING AUTHORIZATION A9-53R-31316.

Part: SKIN — CORRODED (ZONE 100) · airframe 28,332 hrs · 13,754 cycles

DURING C6 C-CHECK, INSPECTION NOTED HOLE CLOSEST TO STRINGER 44CL BETWEEN FRAME 30 AND FRAME 34 SHOWED INDICATION OF CORROSION. MAINTENANCE REPAIRED IAW EA A9-53R-31316.

Part: SKIN — CORRODED (ZONE 100) · airframe 28,332 hrs · 13,754 cycles

REFERENCE NON ROUTINE C068740. DURING DEN C6 C-CHECK, INSPECTION NOTED CORROSION ON FUSELAGE SKIN AROUND RIVET HOLE NUMBER 5 IN FORWARD CARGO PIT 7.5 INCHES FORWARD OF FRAME 34 AND ONE HOLE OUTBOARD OF STRINGER 42 LEFT HAND. MAINTENANCE REPAIRED IAW ENGINEERING AUTHORIZATION A9-53R-31316.

Part: DOUBLER — DAMAGED (ZONE 100) · airframe 28,332 hrs · 13,754 cycles

REFERENCE NON ROUTINE C068922. DURING C-6 C-CHECK, INSPECTION NOTED PYLON HYDRAULIC LINE FEED THROUGH DOUBLER, DAMAGED AT MAIN PRESSURE LINE. MAINTENANCE REPAIRED IAW ENGINEERING AUTHORIZATION A9-57R-31339.

Part: SKIN — CORRODED (FUSELAGE) · airframe 28,332 hrs · 13,754 cycles

REFERENCE NON ROUTINE C068736. DURING DEN C6 C-CHECK, INSPECTION NOTED CORROSION ON RIVET AND SKIN SECOND HOLE INBOARD OF 41LH AT CENTER FAIRING IN FORWARD CARGO PIT FORWARD OF FRAME 34. MAINTENANCE REPAIRED IN REFERENCE TO ENGINEERING AUTHORIZATION A9-53R-31316.

Part: SKIN — CORRODED (ZONE 100) · airframe 28,332 hrs · 13,754 cycles

DURING DEN C6 C-CHECK, INSPECTION NOTED CORROSION ON FUSELAGE SKIN AT BS 13227 BETWEEN STRINGER 42R AND 43R. MAINTENANCE REPAIRED IAW EA A9-53R-31316.

Part: SKIN — CORRODED (ZONE 100) · airframe 28,332 hrs · 13,754 cycles

DURING DEN C6 C-CHECK, INSPECTION NOTED CORROSION ON RIVET AND SKIN, FIRST OPEN HOLE OUTBOARD OF STRINGER 43LH AT CENTER FAIRING IN FORWARD CARGO PIT FORWARD OF FRAME 34. MAINTENANCE REPAIRED IAW ENGINEERING AUTHORIZATION A9-53R-31316.

Part: SKIN — CORRODED (ZONE 100) · airframe 28,332 hrs · 13,754 cycles

REFERENCE NON ROUTINE C068738. DURING C6 C-CHECK, INSPECTION NOTED CORROSION ON RIVET IN SKIN CENTER HOLE AT CENTER FAIRING ON FORWARD CARGO PIT FORWARD OF FRAME 34 AT STRINGER 42LH. MAINTENANCE REPAIRED IAW ENGINEERING AUTHORIZATION A9-53R-31316.

Part: STRINGER — CORRODED (ZONE 100) · airframe 28,332 hrs · 13,754 cycles

REFERENCE NON ROUTINE C068872. DURING C6 C-CHECK, INSPECTION NOTED STRINGER 43 LT HAS SPOTS OF CORROSION AROUND FASTNER HOLES AT FRAME 34. MAINTENANCE REPAIRED IAW EA A9-53R-31316.

Part: STRINGER — CORRODED (ZONE 100) · airframe 28,332 hrs · 13,754 cycles

DURING DEN C6 C-CHECK, INSPECTION NOTED THE AFT CARGO PIT STRINGER AT BOTTOM CENTER AT FRAME 67 HAS CORROSION. MAINTENANCE REMOVED AND REPLACED THE STRINGER IAW SRM 53-00-13, FIGURE 201, SHEET 2.

Part: PROFILE — CORRODED (ZONE 100) · airframe 28,332 hrs · 13,754 cycles

DURING DEN C6 C-CHECK, INSPECTION NOTED THE FORWARD CARGO PIT PROFILE AT FRAME 28 HAS CORRODED FASTENER HOLES. MAINTENANCE REMOVED AND REPLACED THE PROFILE IAW SRM 51-42-11, PARAGRAPH 6 AND 7.

Part: FLOOR PANEL — CORRODED (ZONE 200) · airframe 28,332 hrs · 13,754 cycles

DURING C6 C-CHECK, INSP NOTED THE R2 ENTRANCE FLOOR PANEL 262FF IS CORRODED AROUND MOUNT HOLES. MX REMOVED AND REPLACED PANEL WITH A SERVICEABLE PANEL.

Part: FLOORBEAM — CORRODED (ZONE 200) · airframe 28,332 hrs · 13,754 cycles

DURING C6 C-CHECK, INSP NOTED THE FLOORBEAM AT STA Y1162 HAS CORROSION 2 INCHES FWD OF FRAME 68. MX REMOVED AND REPLACED THE FLOORBEAM IAW SRM 51-42-11, 51-44-00 AND 51-42-11.

Part: SHEAR TIE — CORRODED (ZONE 100) · airframe 28,332 hrs · 13,754 cycles

DURING DEN C6 C-CHECK, INSPECTION NOTED THE SHEAR TIE AT FRAME 57 BETWEEN STRINGER 42R AND 43R HAS CORROSION DAMAGE. MAINTENANCE REMOVED AND REPLACED THR SHEAR TIE IAW A319 SRM 51-42-11, 51-75-12 AND DRAWING D53476503.

Part: FLOORBEAM — CORRODED (ZONE 200) · airframe 28,332 hrs · 13,754 cycles

DURING C6 C-CHECK, INSP NOTED A CORRODED NUT PLATE HOLE ON THE FLOORBEAM AT STA Y1292 JUST AFT OF FRAME 68. MX REMOVED AND REPLACED FLOORBEAM IAW SRM 51-42-11, 51-44-11 AND 53-00-14.

Part: FLOOR SUPPORT — CORRODED (ZONE 200) · airframe 28,332 hrs · 13,754 cycles

DURING C6 C-CHECK, INSP NOTED THE FLOOR SUPPORT AT STA Y1292 BETWEEN FRAME 67 AND FRAME 68 HAS CORRODED NUT CLIP HOLES. MX REMOVED AND REPLACED THE FLOOR SUPPORT IAW SRM 53-00-14.

Part: PROFILE — CORRODED (ZONE 100) · airframe 28,332 hrs · 13,754 cycles

DURING C6 C-CHECK, INSPECTION NOTED THE FORWARD CARGO PIT LEFT HAND TRANSITION PANEL PROFILE AT FRAME 34 HAS CORROSION. MAINTENANCE REMOVED, FABRICATED AND INSTALLED THE PROFILE IAW SRM 51-42-11, 51-31-00, 51-26-12, 51-21-11, 51-75-12 AND DRAWING C2D53911628.

Part: PROFILE — CORRODED (ZONE 100) · airframe 28,332 hrs · 13,754 cycles

DURING DEN C6 C-CHECK, INSPECTION NOTED THE FORWARD CARGO PIT RIGHT HAND TRANSITION PANEL PROFILE AT FRAME 34 HAS CORROSION. MAINTENANCE REMOVED, FABRICATED AND INSTALLED PROFILE IAW SRM 51-42-11, 51-31-00, 51-26-12, 51-21-11, 51-75-12 AND AIRBUS DRAWING C2D53911628.

Part: ARM — LACK OF LUBE (R2 DOOR) · airframe 28,332 hrs · 13,754 cycles

DURING DEN C6 C-CHECK, INSPECTION NOTED THE R2 DOOR EMERGENCY CONTROL HANDLE WAS OUT OF LOAD LIMITS (TASK CARD C534103-01). MAINTENANCE LUBRICATED THE DOOR ARM FITTINGS, DISARM FITTINGS AND THE GIRT BAR FITTINGS AND PERFORMED LOAD LIMIT CHECK IAW AMM 52-13-00-820-057.

Part: PROFILE — CORRODED (ZONE 100) · airframe 28,332 hrs · 13,754 cycles

DURING DEN C6 C-CHECK, INSPECTION NOTED THE FORWARD CARGO PIT FLOOR PROFILE AT FRAME 34 HAS SEVERAL CORRODED NUT PLATES. MAINTENANCE REMOVED AND REPLACED THE PROFILE IAW SRM 51-42-11 AND 51-44-11.

Part: FLOOR PANEL — CORRODED (ZONE 200) · airframe 28,332 hrs · 13,754 cycles

DURING DEN C6 C-CHECK, INSPECTION NOTED A CORRODED POTTED INSERT ON THE AFT OUTSIDE EDGE OF FLOOR PANEL 261PF. MAINTENANCE REPAIRED FLOOR PANEL IAW EA A9-53R-31306.

Part: SHEAR PLATE — CORRODED (ZONE 200) · airframe 28,332 hrs · 13,754 cycles

REFERENCE NON ROUTINE C068592. DURING DEN C6 C-CHECK, INSPECTION NOTED THAT THE SHEAR PLATE AT FRAME 69 TO FRAME 70 AT Y1162 WAS CORRODED. MAINTENANCE REMOVED AND REPLACED THE SHEAR PLATE IAW A319 SRM 51-42-11, DRAWING D53471124, DRAWING D53474180 AND ENGINEERING AUTHORIZATION A0-53T-31040.

Part: PLATE — CORRODED (ZONE 200) · airframe 28,332 hrs · 13,754 cycles

REFERENCE NON ROUTINE C068322. DURING DEN C6 C-CHECK, INSPECTION NOTED CORROSION ON THE BOTTOM OF THE L2 DOOR AFT GIRT BAR FITTING BLANKING PLATE. MAINTENANCE REMOVED, FABRICATED AND INSTALLED BLANKING PLATE IAW DRAWING D53480229, SRM 51-31-00, SRM 51-44-11, 51-21-11, 51-75-12.

Part: SILL — CORRODED (ZONE 200) · airframe 28,332 hrs · 13,754 cycles

DURING DEN C6 C-CHECK, INSPECTION NOTED THE L2 DOOR SILL SHAPE THAT LIES UNDERNEATH THE CENTER SCUFF PLATE BETWEEN FRAME 66 AND FRAME 68 IS CORRODED. MAINTENANCE REMOVED AND REPLACED THE SILL SHAPE IAW SRM 51-42-11, 51-44-11, 51-75-11, 51-75-12, AMM 53-45-15-400-001 AND ENGINEERING AUTHORIZATION A9-53R-31317.

Part: PLATE — CORRODED (ZONE 200) · airframe 28,332 hrs · 13,754 cycles

REFERENCE NON ROUTINE C068322. DURING DEN C6 C-CHECK, INSPECTION NOTED CORROSION ON THE BOTTOM OF THE L2 DOOR AFT GIRT BAR FITTING BLANKING PLATE. MAINTENANCE REMOVED, FABRICATED AND INSTALLED BLANKING PLATE IAW DRAWING D53480229, SRM 51-31-00, SRM 51-44-11, 51-21-11, 51-75-12.

Part: BUFFER — OUT OF ADJUST (R1 DOOR) · airframe 28,332 hrs · 13,754 cycles

DURING C6 C-CHECK, THE R1 SERVICE DOOR FAILED THE FUNCTIONAL TEST OF THE SUSPENSION IAW TASK CARD C528312-1. MAINTENANCE ADJUSTED THE BUFFER ON THE R1 SERVICE DOOR IAW AMM 52-11-00-820-001 AND AMM 52-10-00-220-055.

Part: CONTAINER — FAILED (OXYGEN SYSTEM) · airframe 25,554 hrs · 12,319 cycles

DURING COMPLIANCE OF EO A8-25EO-20453, THE OXYGEN CONTAINER AT THE NINTH ROW OF SEATS ON THE RIGHT FAILED DROP TEST. MAINTENANCE REMOVED AND REPLACED THE OXYGEN CONTAINER PER A318 AMM 35-21-10-000-001 AND AMM 35-21-41-400-001. OPERATIONAL CHECK PERFORMED WITH SATISFACTORY RESULTS IN ACCORDANCE WITH A318 AMM 35-23-00-710-001.

Part: FLAP — DAMAGED (LT WING) · airframe 25,100 hrs · 12,085 cycles

LINE MX NOTED DAMAGE FROM A BIRD STRIKE ON THE LEADING EDGE OF THE LT WING OUTBOARD FLAP. MX REPAIRED FLAP IAW THE REQUIREMENTS OF A319 SRM 57-53-00, FIGURE 202. UPON COMPLETION OF THE REPAIR, IT WAS INSPECTED AND FOUND ACCEPTABLE.

Part: FRAME — CRACKED (LT NACELLE) · airframe 22,804 hrs · 10,925 cycles

DURING C7 C CHECK AND LEAK CHECKING OF THE LEFT PYLON, INSPECTION REPORTED A CRACKED FRAME ON THE TOP, LEFT SIDE OF THE PYLON, JUST AFT OF THE PRE-COOLER. MAINTENANCE REPAIRED THE CRACK IN ACCORDANCE WITH THE REQUIREMENTS OF DRAWING D54630462, A319 SRM 54-52-12, PARAGRAPH 5E AND SRM 51-42-11, PARAGRAPH 6B. UPON COMPLETION OF THE REPAIR, IT WAS INSPECTED AND FOUND ACCEPTABLE.

Part: FRAME — CRACKED (RT PYLON) · airframe 22,804 hrs · 10,925 cycles

DURING C7 C CHECK AND LEAK CHECKING THE RIGHT PYLON, INSPECTION REPORTED A CRACKED FRAME ON THE TOP, RIGHT SIDE OF THE PYLON, JUST AFT OF THE PRE-COOLER. MAINTENANCE REPAIRED THE CRACK IN ACCORDANCE WITH THE REQUIREMENTS OF DRAWING D54630462, A319 SRM 54-52-12, PARAGRAPH 5E, SRM 51-42-11, PARAGRAPH 6B AND EA A9-54R-30020. UPON COMPLETION OF THE REPAIR, IT WAS INSPECTED AND FOUND ACCEPTABLE.

Part: STRUCTURE — CORRODED · corrosion level 2 · airframe 22,804 hrs · 10,925 cycles

DURING C5 C CHECK, INSPECTION REPORTED CORROSION WAS FOUND AT THE CUT OUT OF THE AFT CARGO DOOR SELECTOR BOX. MAINTENANCE REMOVED AND REPLACED THE CORRODED SELECTOR BOX IN ACCORDANCE WITH THE A319 SRM 51-42-11, A319 SRM 52-36-15-400-001 AND EA A9-53R-30029. FOLLOWING COMPLETION OF THE INSTALLATION, THE BOX WAS INSPECTED AND FOUND ACCEPTABLE.

Part: PLATE — DAMAGED (FUSELAGE) · airframe 22,804 hrs · 10,925 cycles

DURING C7 C CHECK, WHILE PERFORMING AN INSPECTION FOR "OK TO INSTALL PARTS," INSPECTION REPORTED DAMAGE WAS FOUND TO THE CORNER PROFILE PLATE ON STRINGER 38 LT, BETWEEN FRAMES 59 AND 59. MAINTENANCE FABRICATED AND INSTALLED A DOUBLER ON THE PLATE IN ACCORDANCE WITH THE REQUIREMENTS OF EA A9-53R-30027. UPON COMPLETION OF THE REPAIR, IT WAS INSPECTED AND FOUND ACCEPTABLE.

Part: COVER — CORRODED (CARGO BAY) · corrosion level 2 · airframe 22,804 hrs · 10,925 cycles

DURING C7 C CHECK, INSPECTION REPORTED SURFACE CORROSION WAS FOUND AROUND THE RIGHT CARGO NET HOLD DOWN BRACKET ON THE COVER PROFILE, UNDER THE FLOORBOARDS OF THE AFT CARGO PIT, AT FRAME 58. MAINTENANCE REMEDIATED THE SURFACE CORROSION ON THE COVER PROFILE, FABRICATED AND INSTALLED A NEW DOUBLER IN ACCORDANCE WITH THE REQUIREMENTS OF EA A9-53R-30026. UPON COMPLETION OF THE MAINTENANCE ACTION, THE REPAIR WAS INSPECTED AND FOUND ACCEPTABLE.

Part: SILL — CORRODED (FUSELAGE) · corrosion level 2 · airframe 22,804 hrs · 10,925 cycles

DURING C7 C CHECK, INSPECTION REPORTED CORROSION WAS FOUND ON THE SIDE WALL PROFILE AND SUPPORT STRINGER, LOCATED IN THE AFT CARGO PIT, LEFT SIDE AT FRAME 58A. MAINTENANCE BLENDED THE CORRODED STRINGER AND REMOVED AND REPLACED THE CORRODED SILL PLATE IN ACCORDANCE WITH THE REQUIREMENTS OF SRM 51-42-11. UPON COMPLETION OF THE INSTALLATION, THE WORK WAS INSPECTED AND FOUND ACCEPTABLE.

Part: BATTERY PACK — FAILED (EMERGENCY LIGHTS) · airframe 22,804 hrs · 10,925 cycles

DURING C5 C CHECK, INSPECTION REPORTED FOUR EPSU BATTERY PACKS FAILED THEIR FUNCTIONAL TEST. PART NUMBERS WERE 3214-30 AND 3214-31 AND SERIAL NUMBERS 26993, 24287, 25994, AND 45007, RESPECTIVELY. MAINTENANCE REMOVED AND REPLACED ALL FOUR BATTERY PACKS IN ACCORDANCE WITH THE REQUIREMENTS OF AMM 33-51-38-00-002 AND AMM 33-51-38-400-002. FOLLOWING COMPLETION OF THE INSTALLATION AND THEIR INSPECTION, THE UNITS TESTED GOOD.

Part: FLOOR PANEL — DAMAGED (FUSELAGE) · airframe 22,804 hrs · 10,925 cycles

DURING C 7 C CHECK, INSPECTION REPORTED THE FORWARD CARGO PIT PANEL 131AF HAD ITS RIGHT EDGE DAMAGED. MAINTENANCE REPAIRED THE PANEL BY FABRICATING AN ALUMINUM COVER SHEET IN ACCORDANCE WITH THE REQUIREMENTS OF EO A9-53EO-20231. THE COVER SHEET WAS INSTALLED IN ACCORDANCE WITH AMM 53-22-14-400-001 AND SRM 51-42-11. UPON COMPLETION OF THE REPAIR AND INSTALLATION OF THE PANEL, IT WAS INSPECTED AND FOUND ACCEPTABLE.

Part: FUEL FILTER — CLOGGED (NR 1 ENGINE) · airframe 17,858 hrs · 8,454 cycles

AIR TURNBACK. FLIGHT CREW REPORTED ECAM AFTER TAKEOFF: ENG1-FUEL FILTER CLOG. REPLACED NR 1 ENGINE FUEL FILTER IAW TSM 73-00-00-810-875, AMM 73-11-10-000-004, AMM 73-11-10-210-003, AND AMM 73-11-10-400-004. ALL SYSTEMS CHECKED NORMAL. PERFORMED LEAK CHECK OF NR 1 ENGINE FUEL FILTER USING MIN. IDLE CHECK IAW AMM 71-00-00-710-006. NO LEAKS FOUND.

Part: ATTACH BRACKET — CORRODED (FLOOR PANEL) · corrosion level 2 · airframe 17,241 hrs · 8,138 cycles

DURING C-4 CHECK, INSPECTION REPORTED CORROSION ON FLOOR PANEL 261EF ATTACHMENT BRACKET (AFT END). CORROSION WAS FOUND TO BE OUT OF LIMITS PER A319 DRAWING 10 D536 70099. FABRICATED AND INSTALLED NEW SPLICE PLATE PER A319 DRAWING 10 D536 70099, SRM 51-44-11 AND SRM 51-23-12.

Part: FLOOR PANEL — CORRODED (FUSELAGE) · airframe 17,241 hrs · 8,138 cycles

DURING C-4 CHECK, INSPECTION REPORTED CORROSION AND DELAMINATION ON BOTTOM SURFACE OF L1 ENTRYWAY FLOOR PANEL 221FF AT FWD AND AFT SIDES. REPLACED FLOOR PANEL PER AMM 53-12-12-991-003.

Part: FLOOR PANEL — CORRODED (CABIN) · airframe 17,241 hrs · 8,138 cycles

DURING C-4 CHECK, INSPECTION REPORTED CORROSION ON BOTTOM SURFACE OF R1 ENTRYWAY FLOOR PANEL 222FF AT FWD AND AFT SIDES. REPLACED FLOOR PANEL 22FF PER AMM 53-12-12-991-003.

Part: FLOOR PANEL — CORRODED · corrosion level 2 · airframe 17,241 hrs · 8,138 cycles

DURING C-4, INSPECTION REPORTED TIE PLATE FOR FWD GALLEY FLOOR PANEL CORRODED. FABRICATED AND INSTALLED TIE PLATE PER SRM 53-02-00 AND DRAWING B5-D536-10763

Part: CLOSEOUT PANEL — CORRODED (FUSELAGE) · corrosion level 2 · airframe 17,241 hrs · 8,138 cycles

DURING C-4 CHECK, INSPECTION REPORTED CORROSION ON AFT L2 DOOR CLOSEOUT SECTION, LOWER LEG. REMOVED CORROSION AND FOUND AFT L2 DOOR CLOSEOUT SECTION TO BE UNREPAIRABLE PER A319 SRM 53-41-12. REPLACED L2 DOOR AFT CLOSEOUT SECTION PER A319SRM 51-42-11 AND 51-44-11.

Part: PLATE — CORRODED (CABIN) · corrosion level 2 · airframe 17,241 hrs · 8,138 cycles

DURING C-4 CHECK, INSPECTION REPORTED TIE PLATE CORRODED FOR G-1 GALLEY FLOOR. FABRICATED AND INSTALLED TIE PLATE PER SRM 53-11-14, PARA 5.B TABLE.

Part: GIRT BAR — CORRODED (FUSLEAGE) · corrosion level 2 · airframe 17,241 hrs · 8,138 cycles

DURING C-4 CHECK, INSPECTION REPORTED CORROSION AROUND L2 DOOR FWD GIRT BAR FITTING. REMOVED STRUCTURE AROUND GIRT BAR ATTACH POINT, FOUND CORROSION ON ATTACH FASTENERS AND ON THE L2 SILL. REMOVED CORROSION ON GIRT BAR ATTACH POINT PER SRM 51-42-11. LOCATED HOLES FROM GIRT BAR ONTO L2 SILL, OKAY TO INSTALL FWD GIRT BAR ATTACH MOUNT PER SRM 53-41-00. INSTALLED FWD GIRT BAR ATTCH MOUNT PER SRM 51-42-11.

Part: DUMMY RAIL — CORRODED (FUSELAGE) · corrosion level 2 · airframe 17,241 hrs · 8,138 cycles

DURING C-4 CHECK, INSPECTION REPORTED MAJOR CORROSION ON DUMMY RAIL AT STATION Y503.2 BETWEEN FR13 AND FR16. CORROSION WAS FOUND TO BE OUT OF LIMITS PER SRM 53-11-14, FIG 101. REPLACED DUMMY RAIL PER SRM 51-42-11 AND SRM 51-44-11.

Part: BOLT — CORRODED (LT MLG) · corrosion level 2 · airframe 17,241 hrs · 8,138 cycles

DURING C-4 CHECK, INSPECTION REPORTED LT MLG TORSION LINK UPPER GUIDE PIN BOLT CORRODED. REPLACED UPPER TORQUE LINK BOLT PER AMM 32-11-27-400-001.

Part: GUIDE VANE — CRACKED (NR 2 ENGINE) · airframe 17,241 hrs · 8,138 cycles

DURING C-4 CHECK, INSPECTION REPORTED THE NR 2 ENGINE OUTLET GUIDE VANES AT THE 1 O'CLOCK, 2 O'CLOCK, 3 O'CLOCK, 4 O'CLOCK, 10 O'CLOCK, 11 O'CLOCK AND 12 O'CLOCK POSITIONS HAD CRACKS ON PLATFORMS PER AMM 72-23-00-991-310-06, SHEET 603. REPLACED DAMAGED OUTLET GUIDE VANES (2 EA AT EACH POSITION) PER AMM 72-23-00-000-008 AND AMM 72-23-00-400-008.

Part: CROSSBEAM — CORRODED (BS 1292) · corrosion level 2 · airframe 17,241 hrs · 8,138 cycles

DURING C-4 CHECK, INSPECTION REPORTED SURFACE CORROSION ON CROSSBEAM AT BS Y1292 BETWEEN FR68 AND FR69. FOUND CROSSBEAM TO BE OUT OF LIMITS PER SRM 53-00-14 FIG 102. REMOVED FRAME PER SRM 51-42-11. TRANSFERRED EXISTING PARTS FROM ORIGINAL BEAM TO NEW BEAM PER SRM 51-42-11. INSTALLED NEW CROSSBEAM PER SRM 51-44-11 AND 51-42-11.

Part: DRAIN PAN — CORRODED (R2 DOORWAY) · corrosion level 2 · airframe 17,241 hrs · 8,138 cycles

DURING C-4 CHECK, INSPECTION REPORTED SURFACE CORROSION ON PAN AFT OF R2 DOOR CUTOUT BETWEEN FR69 AND FR70. FOUND TO BE BEYOND REPAIR PER SRM 51-42-11. REMOVED AND REPLACED PAN PER SRM 51-42-11, 51-44-11, 53-41-14 AND 51-43-00.

Part: SILL — CORRODED (FUSELAGE) · corrosion level 2 · airframe 17,241 hrs · 8,138 cycles

DURING C-4 CHECK, INSPECTION REPORTED SURFACE CORROSION ON BEAM COUPLING AT BS Y1732 JUST FORWARD OF FR66. FOUND AFT DOOR SILL BEAM TO BE OUT OF LIMITS PER SRM 53-41-14, FIGURE 101. REMOVED AND REPLACED SILL PER SRM'S 51-42-11, 53-41-14, FIGURE 201, 51-21-00, 51-50-00, AND 51-44-11.

Part: PAN — CORRODED (FUSELAGE) · corrosion level 2 · airframe 17,241 hrs · 8,138 cycles

DURING C-4 CHECK, INSPECTION REPORTED SURFACE CORROSION ON PAN AFT OF L2 DOOR CUTOUT BETWEEN FR69 AND FR70. REPLACED PAN PER SRM 51-44-11 AND 51-42-11.

Part: SUPPORT — CORRODED (FUSELAGE) · corrosion level 2 · airframe 17,241 hrs · 8,138 cycles

DURING C-4 CHECK, INSPECTION REPORTED SURFACE CORROSION ON FRAME SUPPORT AFT OF L2 DOOR CUTOUT BETWEEN FR69 AND FR70 (BOTTOM SIDE). REPLACED FRAME SUPPORT PER SRM 51-42-11 AND 51-44-11.

Part: CROSSBEAM — CORRODED (FUSELAGE) · corrosion level 2 · airframe 17,241 hrs · 8,138 cycles

DURING C-4 CHECK, INSPECTION REPORTED SURFACE CORROSION ON CROSSBEAM AT BS 1292 BETWEEN FR67 AND FR68. FOUND CROSSBEAM TO BE UNREPAIRABLE PER SRM 53-00-14, FIG 102. REMOVED BEAM FRAME 66-68 PER SRM 51-42-11. INSTALLED NEW CROSSBEAM PER SRM 51-44-11 AND 51-42-11.

Part: SUPPORT — CORRODED (FUSLEAGE) · corrosion level 2 · airframe 17,241 hrs · 8,138 cycles

DURING C-4 CHECK, INSPECTION REPORTED SURFACE CORROSION ON FRAME SUPPORT AFT OF R2 DOOR CUTOUT BETWEEN FR69 AND FR70 (BOTTOM SIDE). REMOVAL OF THE PAN ABOVE SUPPORT REVEALED SUBSTANTIAL CORROSION BENEATH SUPPORT. REMOVED AND REPLACED FRAME SUPPORT AFT OF R2 DOOR BELOW SHEAR PLATE, BETWEEN FR69 AND FR70, PER SRM 51-42-11, 51-44-11, 53-41-14 AND 51-43-00.

Part: CROSSBEAM — CORRODED (FUSELAGE) · corrosion level 2 · airframe 17,241 hrs · 8,138 cycles

DURING C-4 CHECK, INSPECTION REPORTED SURFACE CORROSION ON CROSSBEAM BETWEEN BS Y254 AND Y765 JUST AFT OF FR66. REPLACED CROSSBEAM PER SRM 51-42-11 AND 51-24-00.

Part: GUIDE VANE — CRACKED (RT ENGINE) · airframe 17,241 hrs · 8,138 cycles

DURING C-4 CHECK, INSPECTION REPORTED CRACKS ON PLATFORM OF RT ENGINE OUTLET GUIDE VANES AT THE 5 O'CLOCK, 6 O'CLOCK, 7 O'CLOCK AND 8 O'CLOCK POSITIONS. REPLACED DAMAGED OUTLET GUIDE VANES (2 EA AT EACH POSITION) PER AMM 72-23-00-000-008 AND 72-23-00-400-008.

Part: PROBE — CORRODED (PITOT) · corrosion level 2 · airframe 17,241 hrs · 8,138 cycles

DURING C-4 CHECK, INSPECTION REPORTED RT PITOT PROBE SCREW LUGS BENT AND CORRODED. REPLACED RT PITOT PROBE PER AMM 34-11-15-420-050.

Part: GUIDE VANE — CRACKED (NR 1 ENGINE) · airframe 17,241 hrs · 8,138 cycles

DURING C-4 CHECK, INSPECTION REPORTED NR 1 ENGINE OUTLET GUIDE VANES CRACKED FROM EDGE TO GUIDE VANE THROUGH BOLT HOLE (OVER 1 INCH LONG). RT SIDE OF ENGINE FROM 12 O'CLOCK TO 4 O'CLOCK. INSPECTED CRACKS PER MM 72-23-00-991-310-06 AND 72-23-00-991-310-06, SHEET 603. INSPECTED VANES AND FOUND TO BE OUT OF LIMITS. CRACKS FOLLOW VANE FROM BOLT HOLES, AND PLATFORMS CRACKED FROM TRAILING EDGE OF VANE TO EDGE OF PLATFORM. REPLACED DAMAGED OUTLET GUIDE VANES PER AMM 72-23-00-000-008 AND AMM 72-23-00-400-008.

Part: SMOKE — DETECTED (CABIN) · airframe 12,229 hrs · 5,747 cycles

AFTER LANDING, FLIGHT CREW REPORTED BOTH COCKPIT AND CABIN FILLED WITH SMOKE. HEAVY BRAKING REQUIRED TO STOP AIRCRAFT ON RUNWAY TO TURN ONTO TAXI-WAY. AFTER STOPPING, BRAKE TEMPS ON LT SIDE APPROX 460 DEG, RT SIDE MID 200 DEG. PERFORMED CLEANING OF CROSSFEED, ENGINE AND APU BLEED AIR DUCTS BY RESIDUAL BURNING PER AMM 21-00-00-160-050. NO SMOKE OR DISCREPANCIES NOTED. INSPECTED BRAKES FOR OVERTEMP PER AMM 05-51-16-200-001. BRAKE TEMPS ON ALL BRAKES WITHIN AMM LIMITS. NO DEFECTS NOTED. TESTED NORMAL BRAKING SYSTEM PER AMM 32-42-00-710-001 AND TESTED ALTERNATE BRAKE SYSTEM PER AMM 32-43-00-710-001. BOTH TESTS CHECKED NORMAL.

Part: BATTERY PACK — INOPERATIVE (EMERGENCY LIGHT) · airframe 7,383 hrs · 3,545 cycles

FLIGHT CREW REPORTED EMERGENCY FLOOR PATH LIGHTING AT SEAT ROWS 1, 2, 5 AND 6 INOPERATIVE. REPLACED BATTERY POWER SUPPLY.

Part: SMOKE — DETECTED (CABIN) · airframe 1,528 hrs · 880 cycles

UPON ARRIVAL, FLIGHT CREW REPORTED SMOKE IN CABIN DURING APU START WHILE TAXIING TO GATE. PERFORMED CHECKS, WITH NO SMOKE OR DEFECTS NOTED.

Part: SENSOR — FAILED (NR 2 ENGINE) · airframe 820 hrs · 490 cycles

AIR TURNBACK. FLIGHT CREW REPORTED NR 2 ENGINE COMPRESSOR STALL AT APPROXIMATELY 31,000 FT AND A SERIES OF SUBSEQUENT STALLS. REDUCED NR 2 ENGINE POWER TO IDLE AND ALL INDICATIONS WERE NORMAL. AN EMERGENCY WAS DECLARED AND THE AIRCRAFT LANDED AT DFW WITHOUT INCIDENT. PERFORMED BORESCOPE INSPECTION OF HPT AND LPT BOOSTER ROTOR BLADES AND NR 1, 3 AND 8 HPC BLADES WITH NO DEFECTS NOTED. REPLACED T12 SENSOR AND PERFORMED OPERATIONAL CHECK OF FADEC SYSTEM WITH NO FAULTS NOTED ON A OR B CHANNEL.