N913FR

ATA 3250

Part: ELECTRICAL BOX — MALFUNCTIONED (NLG STEERING) · airframe 22,525 hrs · 9,539 cycles

FLIGHT NUMBER 435 FROM OMA TO DEN, FLIGHT CREW NOTICED NOSE WHEEL STEERING DISPLAY IN "AMBER" ON MEMO PAGE. NORMAL LANDING IN DENVER. AFTER SHUTTING DOWN NR 2 ENGINE, LOST ALL STEERING. MAINTENANCE REMOVED AND REPLACED THE NOSE WHEEL STEERING DEACTIVATION ELECTRICAL BOX AND PERFORMED OPERATIONAL CHECK IN ACCORDANCE WITH A319 AMM 32-51-12 PB 401. MAINTENANCE ALSO REMOVED AND REPLACED THE BRAKING STEERING CONTROL UNIT AS PRECAUTIONARY PROCEDURE AND PERFORMED OPERATIONAL CHECK IN ACCORDANCE WITH A319 AMM 32-42-34 PB 401 AND 22-97-00-710-001.

ATA 2560

Part: GIRT BAR — OBSTRUCTED (L1 DOOR) · airframe 21,222 hrs · 8,977 cycles

DURING CLIMB OUT THE FLIGHT CREW RECEIVED AN INDICATION L1 DOOR UNARMED LIGHT CAME ON AND THE AC RETURNED TO DEPARTURE. MAINT FOUND DEBRIS STUCK IN THE L1 DOOR GIRT BAR FITTING STOP LEVER AREA. MAINT CLEANED THE DEBRIS AND OPS CHECKED GOOD IAW AMM 53-11-00-310-034 AND THE AC WAS RETURNED TO SERVICE. (A)

ATA 5321

Part: FLOOR PANEL — PUNCTURED (FUSELAGE) · airframe 20,124 hrs · 8,533 cycles

DURING C4/S1 C CHECK, INSPECTION REPORTED A PUNCTURE WAS FOUND IN FLOOR PANEL 241EF. MAINTENANCE REPAIRED THE DAMAGED PANEL IN ACCORDANCE WITH THE REQUIREMENTS OF A319 SRM 53-02-00, PAGE 205, A319 SRM 52-02-00, PAGE 206, PARAGRAPH 201 AND A319 SRM 53-02-00. FOLLOWING COMPLETION OF THE REPAIR, THE PANEL WAS INSPECTED AND FOUND ACCEPTABLE.

ATA 2560

Part: PLATE — CORRODED (GIRT BAR) · corrosion level 2 · airframe 20,124 hrs · 8,533 cycles

DURING C4/S1 C CHECK, INSPECTION REPORTED CORROSION WAS FOUND ON THE R-2 DOOR, FORWARD GIRT BAR PLATE. MAINTENANCE REMOVED AND REPLACED THE GIRT BAR PLATE IN ACCORDANCE WITH THE REQUIREMENTS OF AMM 53-42-12-991-003B. UPON COMPLETION OF THE INSTALLTION, THE NEW PLATE WAS INSPECTED AND FOUND ACCEPTABLE.

ATA 2560

Part: PLATE — CORRODED (GIRT BAR) · corrosion level 2 · airframe 20,124 hrs · 8,533 cycles

DURING C4/S1 C CHECK, INSPECTION REPORTED CORROSION WAS FOUND ON THE FORWARD, LOWER GIRT BAR PLATE AT THE L-2 DOOR. MAINTENANCE REMOVED AND REPLACED THE GIRT BAR PLATE IN ACCORDANCE WITH THE REQUIREMENTS OF AMM 5-42-12-991-003B. UPON COMPLETION OF THE REPLACEMENT, THE NEW PLATE WAS INSPECTED AND FOUND ACCEPTABLE.

ATA 5320

Part: THRESHOLD — CORRODED (FUSELAGE) · corrosion level 2 · airframe 20,124 hrs · 8,533 cycles

DURING C4/S1 C CHECK, INSPECTION REPORTED CORROSION WAS FOUND ON BOTH ENDS OF THE R-2 DOOR THRESHOLD STRIP. MAINTENANCE REMOVED AND REPLACED THE THRESHOLD STRIP IN ACCORDANCE WITH THE REQUIREMENTS OF AMM 53-42-12 PB 401. UPON COMPLETION OF THE REPLACEMENT, THE NEW THRESHOLD STRIP WAS INSPECTED AND FOUND ACCEPTABLE.

ATA 5321

Part: FLOOR PANEL — CORRODED (FUSELAGE) · corrosion level 2 · airframe 20,124 hrs · 8,533 cycles

DURING C4/S1 C CHECK, INSPECTION REPORTED CORROSION WAS FOUND ON THE L0WER SURFACE OF FLOOR PANEL 221FF. MAINTENANCE REMOVED AND REPLACED THE FLOOR PANEL IN ACCORDANCE WITH THE REQUIREMENTS OF AMM 53-12-12-000-001. FOLLOWING COMPLETION OF THE INSTALLATION OF THE NEW FLOOR PANEL, IT WAS INSPECTED AND FOUND ACCEPTABLE.

ATA 5321

Part: FLOOR PANEL — CORRODED (FUSELAGE) · corrosion level 2 · airframe 20,124 hrs · 8,533 cycles

DURING C4/S1 C CHECK, INSPECTION REPORTED CORROSION WAS FOUND ON THE LOWER SURFACE OF FLOOR PANEL 222FF. MAINTENANCE REMOVED AND REPLACED THE FLOOR PANEL IN ACCORDANCE WITH THE REQUIREMENTS OF AMM 53-12-12-400-001. FOLLOWING COMPLETION OF THE REPLACEMENT, THE PANEL WAS INSPECTED AND FOUND ACCEPTABLE.

ATA 5321

Part: FLOOR PANEL — DAMAGED (FUSELAGE) · airframe 20,124 hrs · 8,533 cycles

DURING C4/S1 C CHECK, INSPECTION REPORTED DELAMINATION WAS FOUND ON THE TOP SURFACE OF FLOOR PANEL 231NF. MAINTENANCE REPAIRED THE DELAMINATED AREA IN ACCORDANCE WITH THE REQUIREMENTS OF A319 SRM 53-02-00, FIGURE 212. FOLLOWING COMPLETION OF THE REPAIR, THE PANEL WAS INSPECTED AND FOUND ACCEPTABLE.

ATA 5321

Part: FLOOR PANEL — DAMAGED · airframe 20,124 hrs · 8,533 cycles

DURING C4/S1 C CHECK, INSPECTION REPORTED FLOOR PANEL 262FF WAS DAMAGED AT ITS AFT, INBOARD CORNER. MAINTENANCE REMOVED AND REPLACED THE FLOOR PANEL IN ACCORDANCE WITH THE REQUIREMENTS OF AMM 53-42-12-991-003B. FOLLOWING INSTALLATION OF THE NEW FLOOR PANEL, IT WAS INSPECTED AND FOUND ACCEPTABLE.

ATA 5340

Part: ATTACH ANGLE — CORRODED (BULKHEAD) · corrosion level 2 · airframe 20,124 hrs · 8,533 cycles

DURING C4/S1 C CHECK, INSPECTION REPORTED CORROSION WAS FOUND IN MULTIPLE NUT PLATE HOLES ON THE FORWARD CARGO PIT, AFT BULKHEAD, FLOOR PLATE, LOCATED AT FRAME 35, BETWEEN STRINGERS L38 AND R38. MAINTENANCE REMOVED AND REPLACED THE PLATE IN ACCORDANCE WITH THE REQUIREMENTS OF A319 SRM 51-42-11. FOLLOWING COMPLETION OF THE INSTALLATION, THE NEW PLATE WAS INSPECTED AND FOUND ACCEPTABLE.

ATA 5320

Part: SILL — CORRODED (FUSELAGE) · corrosion level 2 · airframe 20,124 hrs · 8,533 cycles

DURING C4/S1 C CHECK, INSPECTION REPORTED CORROSION WAS FOUND ON THE R-1 DOOR SILL PLATE AT 2 NUT PLATE LOCATIONS ON THE FORWARD GIRT BAR FITTING ATTACH POINT. MAINTENANCE REMOVED THE CORROSION, TREATED THE BLENDED AREAS WITH ALODINE, PAINTED WITH PRIMER, FILLED THE BLENDED AREA WITH HYSOL 9394 AND PERFORMED THESE ACTIONS IN ACCORDANCE WITH THE REQUIREMENTS OF EA A9-53R-30097, STEPS 6 AND 7. UPON COMPLETION OF THE WORK, THE SILL PLATE WAS INSPECTED AND FOUND ACCEPTABLE.

ATA 2560

Part: STRAP — CORRODED (GIRT BAR) · corrosion level 2 · airframe 20,124 hrs · 8,533 cycles

DURING C4/S1 C CHECK, INSPECTION REPORTED CORROSION WAS FOUND ON THE NUT PLATE STRAP, UNDER THE FORWARD GIRT BAR FITTING, BELOW THE BLANKING PLATE, AT THE R-1 DOOR. MAINTENANCE INSTALLED A NEW NUT PLATE STRAP IN ACCORDANCE WITH THE REQUIREMENTS OF A319 SRM 51-72-11. UPON INSTALLATION OF THE NEW STRAP, IT WS INSPECTED AND FOUND ACCEPTABLE.

ATA 5320

Part: SILL — CORRODED (FUSELAGE) · corrosion level 2 · airframe 20,124 hrs · 8,533 cycles

DURING C4/S1 C CHECK, INSPECTION REPORTED CORROSION WAS FOUND AT THE R-1 DOOR SILL FITTING AT THE AFT 2 NUT PLACE HOLES AT THE GIRT BAR FITTING ATTACH POINT. REMOVED CORROSION FROM THE R-1 DOOR SILL FITTING IN ACCORDANCE WITH THE REQUIREMENTS OF A319 SRM 51-47-00 AND EA A9-53R-30097. UPON COMPLETION OF THE REPAIR, THE SILL WAS INSPECTED AND FOUND ACCEPTABLE.

ATA 5321

Part: FLOOR PANEL — DAMAGED (GALLEY) · airframe 20,124 hrs · 8,533 cycles

DURING C4/S1 C CHECK, INSPECTION REPORTED SEVERAL POTTED INSERTS WERE MISSING FROM AFT GALLEY FLOOR PANEL 261PF. MAINTENANCE REMOVED AND REPLACED THE DAMAGED PANEL IN ACCORDANCE WITH AMM 53-42-12 PB 401. FOLLOWING THE REPLACEMENT OF THE DAMAGED PANEL, THE NEW ONE WAS INSPECTED AND FOUND ACCEPTABLE.

ATA 5315

Part: FLOORBEAM — CORRODED (FUSELAGE) · corrosion level 2 · airframe 20,124 hrs · 8,533 cycles

REFERENCE NON ROUTINE C039954. DURING C4/S1 C CHECK, INSPECTION REPORTED CORROSION WAS FOUND ON THE AFT CARGO COMPARTMENT FLOOR FRAME PLATE AT FRAME 63. MAINTENANCE REMOVED AND REPLACED THE PLATE IN ACCORDANCE WITH THE REQUIREMENTS OF A319 SRM 51-42-11, PARAGRAPHS 5 AND 6. FOLLOWING COMPLETION OF THE PLATE REPLACEMENT, THE NEW PLATE WAS INSPECTED AND FOUND ACCEPTABLE.

ATA 5311

Part: FRAME — CORRODED (ZONE 100) · corrosion level 2 · airframe 20,124 hrs · 8,533 cycles

DURING C4/S1 C CHECK, INSPECTION REPORTED CORROSION WAS FOUND ON THE AFT CARGO COMPARTMENT FRAME PLATE AT FRAME 61. MAINTENANCE REMOVED AND REPLACED THE FRAME PLATE IN ACCORDANCE WITH THE REQUIREMENTS OF A319 SRM 51-42-11, PARAGRAPHS 5 AND 6. FOLLOWING COMPLETION OF THE PLATE REPLACEMENT, THE NEW PLATE WAS INSPECTED AND FOUND ACCEPTABLE.

ATA 5321

Part: FLOOR PANEL — DAMAGED (FUSELAGE) · airframe 20,124 hrs · 8,533 cycles

DURING C4/S1 C CHECK, INSPECTION REPORTED DELAMINATION WAS FOUND ON THE UPPER SURFACE OF FLOOR PANEL 252GG. MAINTENANCE REPAIRED THE PANEL IN ACCORDANCE WITH THE REQUIREMENTS OF A319 SRM 53-02-00, FIGURE 212. FOLLOWING COMPLETION OF THE REPAIR, THE PANEL WAS INSPECTED AND FOUND ACCEPTABLE.

ATA 5321

Part: FLOOR PANEL — DAMAGED (FUSELAGE) · airframe 20,124 hrs · 8,533 cycles

DURING C4/S1 C CHECK, INSPECTION REPORTING FINDING DELAMINATION ON THE EDGE OF FLOOR PANEL 222EF. MAINTENANCE REPAIRED THE DAMAGED PANEL IN ACCORDANCE WITH THE REQUIREMENTS OF A319 SRM 53-02-00 PB 201, PARAGRAPH 8.J, FIGURE 212. FOLLOWING COMPLETION OF THE REPAIR, THE PANEL WAS INSPECTED AND FOUND ACCEPTABLE.

ATA 5321

Part: FLOOR PANEL — DAMAGED (FUSELAGE) · airframe 20,124 hrs · 8,533 cycles

DURING C4/S1 C CHECK, INSPECTION REPORTED DELAMINATION WAS FOUND ON THE EDGE OF FLOOR PANEL 251WF. MAINTENANCE REPAIRED THE FLOOR PANEL IN ACCORDANCE WITH THE REQUIREMENTS OF A319 SRM 53-02-00, FIGURE 212. FOLLOWING COMPLETON OF THE REPAIR, THE FLOOR PANEL WAS INSPECTED AND FOUND ACCEPTABLE.

ATA 5315

Part: FLOORBEAM — CORRODED (FUSELAGE) · corrosion level 2 · airframe 20,124 hrs · 8,533 cycles

DURING C4/S1 C CHECK, INSPECTION REPORTED CORROSION WAS FOUND ON THE AFT CARGO COMPARTMENT FLOOR FRAME PLATE AT FRAME 56. MAINTENANCE REMOVED AND REPLACED THE PLATE IN ACCORDANCE WITH THE REQUIREMENTS OF A319 SRM 51-42-11. FOLLOWING COMPLETION OF THE PLATE REPLACEMENT, THE NEW PLATE WAS INSPECTED AND FOUND ACCEPTABLE.

ATA 5321

Part: FLOOR PANEL — DAMAGED · airframe 20,124 hrs · 8,533 cycles

DURING C4/S1 C CHECK, INSPECTION REPORTED FLOOR PANEL 231MF WAS PUNCTURED ON ITS TOP SURFACE. MAINTENANCE REPAIRED THE FLOOR PANEL IN ACCORDANCE WITH THE REQUIREMENTS OF A319 SRM 53-02-00, FIGURE 201, ZONE A. UPON COMPLETION OF THE REPAIR, THE FLOOR PANEL WAS INSPECTED AND FOUND ACCEPTABLE.

ATA 5315

Part: FLOORBEAM — CORRODED (FUSELAGE) · corrosion level 2 · airframe 20,124 hrs · 8,533 cycles

DURING C4/S1 C CHECK, INSPECTION REPORTED CORROSION WAS FOUND ON THE AFT CARGO COMPARTMENT FLOOR FRAME PLATE AT FRAME 59. MAINTENANCE REMOVED AND REPLACED THE PLATE IN ACCORDANCE WITH THE REQUIREMENTS OF SRM 51-42-11, PARAGRAPHS 5 AND 6. FOLLOWING COMPLETION OF THE PLATE REPLACEMENT, THE NEW PLATE WAS INSPECTED AND FOUND ACCEPTABLE.

ATA 5315

Part: FLOORBEAM — CORRODED (FUSELAGE) · corrosion level 2 · airframe 20,124 hrs · 8,533 cycles

DURING C4/S1 C CHECK, INSPECTION REPORTED CORROSION WAS FOUND ON THE AFT CARGO COMPARTMENT FLOOR FRAME PLATE AT FRAME 68. MAINTENANCE REMOVED AND REPLACED THE PLATE IN ACCORDANCE WITH THE REQUIREMENTS OF A319 SRM 51-42-11, PARAGRAPHS 5 AND 6. FOLLOWING COMPLETION OF THE PLATE REPLACEMENT, THE NEW PLATE WAS INSPECTED AND FOUND ACCEPTABLE.

ATA 3222

Part: HINGE PIN — CRACKED (NLG) · airframe 20,124 hrs · 8,533 cycles

DURING C4/S1 C CHECK, INSPECTION REPORTED, DURING THE PERFORMANCE OF DYE PENETRANT INSPECTION OF THE NOSE LANDING GEAR HINGE PIN, A CRACK WAS FOUND IN THE CENTER TORQUE PIN. MAINTENANCE REMOVED AND REPLACED THE CENTER TORQUE PIN IN ACCORDANCE WITH THE REQUIREMENTS OF AMM 32-21-13-400-001, STEP 4B (17) TO (23). ON COMPLETION OF THE REPLACEMENT, THE INSTALLATION WAS INSPECTED AND FOUND ACCEPTABLE.

ATA 5320

Part: SILL — CORRODED (FUSELAGE) · corrosion level 2 · airframe 20,124 hrs · 8,533 cycles

DURING C4/S1 C CHECK, INSPECTION REPORTED CORROSION WAS FOUND ON THE NUT PLATE HOLES BELOW THE FORWARD AND AFT GIRT BAR FITTINGS ON THE L-1 DOOR SILL. MAINTENANCE BLENDED THE CORROSION, TREATED AND PAINTED THE AFFECTED AREAS IN ACCORDANCE WITH THE REQUIREMENTS OF EA A9-53R-30106 AND SRM 51-74-00, PARAGRAPH 6. UPON COMPLETION OF THE REPAIRS, THE AREAS WERE INSPECTED AND FOUND ACCEPTABLE.

ATA 5321

Part: FLOOR PANEL — DAMAGED (GALLEY) · airframe 20,124 hrs · 8,533 cycles

DURING C4/S1 C CHECK, INSPECTION REPORTED POTTED INSERTS WERE FOUND MISSING ON THE AFT GALLEY 261PF FLOOR PANEL. MAINTENANCE REMOVED AND REPLACED THE FLOOR PANEL IN ACCORDANCE WITH THE REQUIREMENTS OF AMM 53-42-12 PB 401. FOLLOWING THE INSTALLATION OF THE NEW FLOOR PANEL, IT WAS INSPECTED AND FOUND ACCEPTABLE.

ATA 5321

Part: FLOOR PANEL — DAMAGED (FUSELAGE) · airframe 20,124 hrs · 8,533 cycles

DURING C4/S1 C CHECK, INSPECTION REPORTED DELAMINATION WAS FOUND ON FLOOR PANEL 251NF. MAINTENANCE REPAIRED THE FLOOR PANEL IN ACCORDANCE WITH THE REQUIREMENTS OF A319 SRM 53-02-00, FIGURE 212. FOLLOWING COMPLETION OF THE REPAIR, THE FLOOR PANEL WAS INSPECTED AND FOUND ACCEPTABLE.

ATA 2571

Part: FITTING — WORN (BATTERY TRAY) · airframe 20,124 hrs · 8,533 cycles

DURING C4/S1 C CHECK, INSPECTION REPORTED THE FORWARD AND AFT ATTACH POINTS OF THE NUMBER 1 BATTERY TRAY SHOWED EVIDENCE OF FRETTING. MAINTENANCE REMOVED AND REPLACED THE FORWARD BATTERY TRAY FITTING IN ACCORDANCE WITH THE REQUIREMENTS OF EA A0-53T-12210 AND SRM 51-42-11, PARAGRAPH 7. FOLLOWING THE INSTALLATION OF THE FITTING, IT WAS INSPECTED AND FOUND ACCEPTABLE.

ATA 2560

Part: FITTING — CORRODED (GIRT BAR) · corrosion level 2 · airframe 20,124 hrs · 8,533 cycles

DURING C4/S1 C CHECK, INSPECTION REPORTED CORROSION WAS FOUND ON THE FORWARD, INBOARD, GIRT BAR FITTING NUT PLATE HOLE, BELOW THE BLANKING PLATE, AT THE L-1 DOOR. MAINTENANCE BLENDED OUT THE CORROSION, TREATED AND PAINTED THE AFFECTED AREA IN ACCORDANCE WITH THE REQUIREMENTS OF EA A9-53R-30106 AND A319 SRM 51-74-00, PARAGRAPH 6. UPON COMPLETION OF THE REPAIR, THE AFFECTED AREA WAS INSPECTED AND FOUND ACCEPTABLE.

ATA 5320

Part: SCUFF PLATE — CORRODED (FUSELAGE) · corrosion level 2 · airframe 20,124 hrs · 8,533 cycles

DURING C4/S1 C CHECK, INSPECTION REPORTED CORROSION WAS FOUND ON THE R-1 DOOR FITTING (PN D531219820105) AND SCUFF PLATE (PN D53112199203000). MAINTENANCE REMOVED AND REPLACED THE SCUFF PLATE IN ACCORDANCE WITH THE REQUIREMENTS OF EA A9-53R-30133 AND AMM 52-15-15. THE DOOR FITTING WAS REWORKED IN ACCORDANCE WITH THE REQUIREMENTS OF A319 SRM 51-74-00, PARAGRAPH 6. FOLLOWING COMPLETION OF THE MAINTENANCE ACTION, THE AREA WAS INSPECTED AND FOUND ACCEPTABLE.

ATA 5320

Part: SILL — CORRODED (FUSELAGE) · corrosion level 2 · airframe 20,124 hrs · 8,533 cycles

DURING C4/S1 C CHECK, INSPECTION REPORTED THE L-2 DOOR SILL, AFT GIRT BAR FITTING CUT OUT, SHOWED SIGNS OF CORROSION ON THE AFT, OUTBOARD SCREW HOLE. MAINTENANCE REMOVED AND REPLACED THE L-2 DOOR SILL IN ACCORDANCE WITH THE REQUIREMENTS OF A319 SRM 51-42-11, PAGE 7. FOLLOWING COMPLETION OF THE INSTALLATION, THE DOOR SILL WAS INSPECTED AND FOUND ACCEPTABLE.

ATA 5320

Part: SILL — CORRODED (FUSELAGE) · corrosion level 2 · airframe 10,124 hrs · 8,533 cycles

DURING C4/S1 C CHECK, INSPECTION REPORTED SURFACE CORROSION WAS FOUND ON NUT PLATE HOLES ON THE END OF THE FORWARD CARGO DOOR SILL PLATE. MAINTENANCE REMOVED THE FASTENERS, REPAIRED THE CORRODED SURFACES, BY BLENDING, IN ACCORDANCE WITH THE REQUIREMENTS OF A319 SRM 51-74-00, PARAGRAPH 6 AND EA A9-53R-30109. FASTENERS WERE RE-INSTALLED IN ACCORDANCE WITH THE REQUIREMENTS OF A319 SRM 51-42-11. UPON COMPLETION OF THE REPAIR, THE AREA WAS INSPECTED AND FOUND ACCEPTABLE.

ATA 5320

Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · corrosion level 2 · airframe 20,124 hrs · 8,533 cycles

DURING C4/S1 C CHECK, INSPECTION REPORTED CORROSION WAS FOUND AROUND THE NUT PLATES OF THE FORWARD CARGO COMPARTMENT, FLOOR PANEL ATTACH POINTS, BETWEEN FRAMES 24 AND 35, AT STRINGER 38L. MAINTENANCE REMOVED AND REPLACED TWO FRAME PLATES (PN D5391635420000 AND D5392059220000) IN ACCORDANCE WITH THE REQUIREMENTS OF SRM 51-42-11, PARAGRAPHS 5 AND 6. UPON COMPLETION OF THE INSTALLATION, IT WAS INSPECTED AND FOUND OKAY.

ATA 5320

Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · corrosion level 2 · airframe 20,124 hrs · 8,533 cycles

DURING C4/S1 C CHECK, INSPECTION REPORTED THE RIGHT, FORWARD CARGO PIT FLOORBOARD ATTACH POINT AT STRINGER 38 HAD EVIDENCE OF CORROSION AT THE NUT PLATE HOLE LOCATIONS BETWEEN FRAME 28 AND 35. MAINTENANCE REMOVED AND REPLACED THE PROFILE PLATE IN ACCORDANCE WITH THE REQUIREMENTS OF A319 SRM 51-42-11, PARAGRAPH 6. FOLLOWING COMPLETION OF THE REPLACEMENT, THE PROFILE WAS INSPECTED AND FOUND ACCEPTABLE.

ATA 5315

Part: FLOORBEAM — CORRODED (FUSELAGE) · corrosion level 2 · airframe 20,124 hrs · 8,533 cycles

DURING C4/S1 C CHECK, CORROSION WAS FOUND ON THE FORWARD CARGO COMPARTMENT NUT PLATES ON THE FRAME PLATE AT FRAME 28. MAINTENANCE REMOVED AND REPLACED THE PLATE IN ACCORDANCE WITH THE REQUIREMENTS OF A319 SRM 51-42-11, PAGE 6. FOLLOWING COMPLETION OF THE INSTALLATION, THE PLATE WAS INSPECTED AND FOUND ACCEPTABLE.

ATA 5320

Part: WEB — DAMAGED (FUSELAGE) · airframe 20,124 hrs · 8,533 cycles

DURING C4/S1 C CHECK, INSPECTION REPORTED SHEARED RIVETS WERE FOUND IN THE RIGHT SUPPORT WEB, LOCATED BETWEEN FRAMES 68 AND 69, WHERE IT CONNECTS TO STRINGER Y1292. MAINTENANCE INSTALLED NEW LOCK FASTENER IN ACCORDANCE WITH THE REQUIREMENTS OF A319 SRM 51-42-11, PARAGRAPH 7 AND EA A9-53R-30090. FOLLOWING COMPLETION OF THE INSTALLATION, THE LOCK FASTENER WERE INSPECTED AND FOUND ACCEPTABLE.

ATA 5320

Part: SHEAR PLATE — CORRODED · corrosion level 2 · airframe 20,124 hrs · 8,533 cycles

DURING C4/S1 C CHECK, INSPECTION REPORTED THE RIGHT SHEAR PLATE, LOCATED BETWEEN FRAMES 69 AND 70, SHOWED SIGNS OF CORROSION. MAINTENANCE REMOVED AND REPLACED THE SHEAR PLATE IN ACCORDANCE WITH THE REQUIREMENTS OF A319 SRM 51-42-11, PARAGRAPHS 6, 7 AND 14. FOLLOWING CONPLETION OF THE INSTALLATION, THE SHEAR PLATE WAS INSPECTED AND FOUND ACCEPTABLE.

ATA 5315

Part: FLOORBEAM — DAMAGED (FUSELAGE) · airframe 20,124 hrs · 8,533 cycles

DURING C4/S1 C CHECK, INSPECTION REPORTED SHEARED FASTENERS WERE FOUND WHERE THE LEFT SUPPORT BEAM, BETWEEN FRAMES 68 AND 69, CONNECTS TO FLOORBEAM Y1292. MAINTENANCE REMOVED THE SHEARED FASTENERS. NEW FASTENERS WERE INSTALLED IN ACCORDANCE WITH THE REQUIREMENTS OF EA A9-53R-30090, REVISION ORIGINAL, AND A319 SRM 51-42-11, PARAGRAPH 7. WHEN COMPLETED, THE INSTALLATION WAS INSPECTED AND FOUND ACCEPTABLE.

ATA 5320

Part: SUPPORT ANGLE — CORRODED (FUSELAGE) · corrosion level 2 · airframe 20,124 hrs · 8,533 cycles

DURING C4/S1 C CHECK, INSPECTION REPORTED THE RIGHT SHEAR PLATE SUPPORT ANGLE, LOCATED BETWEEN FRAMES 69 AND 70, SHOWED SIGNS OF CORROSION. MAINTENANCE REMOVED AND REPLACED THE SHEAR PLATE SUPPORT ANGLE, LOCATED BETWEEN FRAMES 69 AND 70, IN ACCORDANCE WITH THE REQUIREMENTS OF A319 SRM 51-42-11, PARAGRAPHS 6, 7 AND 14. FOLLOWING COMPLETION OF THE INSTALLATION, THE SUPPORT ANGLE WAS INSPECTED AND FOUND ACCEPTABLE.

ATA 5320

Part: SUPPORT ANGLE — CORRODED · corrosion level 2 · airframe 20,124 hrs · 8,533 cycles

DURING C4/S1 C CHECK, INSPECTION REPORTED THE LEFT, SHEAR PLATE SUPPORT ANGLE, LOCATED BETWEEN FRAMES 69 AND 70, SHOWED SIGNS OF CORROSION. MAINTENANCE REMOVED AND REPLACED THE SHEAR PLATE SUPPORT ANGLE, LOCATED BETWEEN FRAMES 69 AND 70, IN ACCORDANCE WITH THE REQUIREMENTS OF A319 SRM 51-42-11, PARAGRAPH 6. FOLLOWING COMPLETION OF THE INSTALLATION, THE ANGLE WAS INSPECTED AND FOUND ACCEPTABLE.

ATA 5320

Part: SHEAR PLATE — CORRODED (LEFT) · corrosion level 2 · airframe 20,124 hrs · 8,533 cycles

DURING C4/S1 C CHECK, INSPECTION REPORTED THE LEFT SHEAR PLATE BETWEEN FRAMES 69 AND 70 SHOWED SIGNS OF CORROSION. MAINTENANCE REMOVED AND REPLACED THE SHEAR PLATE AT FRAMES 69 AND 70, IN ACCORDANCE WITH THE REQUIREMENTS OF A319 SRM 51-42-11 PARAGRAPHS 6 AND 7 AND AIRBUS DRAWING D53474180. FOLLOWING COMPLETION OF THE INSTALLATION THE SHEAR PLATE WAS INSPECTED AND FOUND ACCEPTABLE.

ATA 5315

Part: FLOORBEAM — CORRODED (FUSLEAGE) · corrosion level 2 · airframe 20,124 hrs · 8,533 cycles

DURING C4/S1 C CHECK, INSPECTION REPORTED CORROSION WAS FOUND AT THE NUT PLATE HOLE, AT THE FORWARD SPLICE, ON THE Y1292 FLOORBEAM, BETWEEN FRAMES 68 AND 69. MAINTENANCE REMOVED AND REPLACED THE FLOORBEAM AND SPLICE ANGLES IN ACCORDANCE WITH SRM 51-42-11, PARAGRAPH 7 AND DRAWING D53472780. UPON COMPLETION OF THE INSTALLATION THE WORK WAS INSPECTED AND FOUND ACCEPTABLE.

ATA 5321

Part: FLOOR PANEL — CORRODED (FUSELAGE) · corrosion level 2 · airframe 20,124 hrs · 8,533 cycles

DURING C4/S1 C CHECK, INSPECTION REPORTED DAMAGE AND CORROSION WAS FOUND ON AFT CARGO PIT, REINFORCED FLOOR PANEL 151ZG. MAINTENANCE REPAIRED THE FLOOR PANEL BY FABRICATING A NEW COVER SHEET FROM 2024-T3 AL IN ACCORDANCE WITH THE REQUIREMENTS OF E0 53-42-319-002 AND A319 SRM 51-44-11. FOLLOWING COMPLETION OF THE REPAIR, THE FLOOR PANEL WAS INSPECTED AND FOUND ACCEPTABLE.

ATA 5320

Part: SILL — CORRODED (FUSELAGE) · corrosion level 2 · airframe 20,124 hrs · 8,533 cycles

DURING C4/S1 C CHECK, INSPECTION REPORTED CORROSION WAS FOUND AT VARIOUS THROUGH HOLES ON THE UNDERSIDE OF SILL PLATE 152YG. MAINTENANCE REPAIRED THE SILL PLATE IN ACCORDANCE WITH THE REQUIREMENTS OF A319 SRM 51-21-11, A319 SRM 51-23-11 AND EA A9 53R-30123. UPON COMPLETION OF THE REPAIR, THE SILL PLATE WAS INSPECTED AND FOUND ACCEPTABLE.

ATA 5321

Part: COVER — CORRODED (FLOOR PANEL) · corrosion level 2 · airframe 20,124 hrs · 8,533 cycles

DURING C4/S1 C CHECK, INSPECTION REPORTED CORROSION WAS FOUND ON THE COVER SHEET OF AFT CARGO PIT FLOOR PANEL 151VG. MAINTENANCE REMOVED THE CORRODED COVER SHEET FROM THE FLOOR PANEL. A REPLACEMENT COVER SHEET WAS FABRICATED IN ACCORDANCE WITH THE REQUIREMENTS OF EO A9-53E0-20231. THE NEW COVER SHEET WAS INSTALLED AND INSPECTED. UPON COMPLETION OF THE INSPECTION, THE COVERSHEET AND FLOOR PANEL WERE FOUND ACCEPTABLE.

ATA 2565

Part: CABLE ASSY — BINDING (EVAC SLIDE) · airframe 20,124 hrs · 8,533 cycles

DURING C4/S1 C CHECK, INSPECTION REPORTED THE LEFT, OVERWING EMERGENCY EXIT SLIDE CABLE FAILED ITS OPERATIONAL TEST. MAINTENANCE APPLIED LUBRICATING COMPOUND 05-027 TO THE CABLE IN ACCORDANCE WITH THE REQUIREMENTS OF EA A0-52T-30102. FOLLOWING THIS MAINTENANCE ACTION, THE CABLE WAS TESTED, INSPECTED AND FOUND ACCEPTABLE.

ATA 3350

Part: BATTERY — FAILED (CABIN) · airframe 20,124 hrs · 8,533 cycles

DURING C4/S1 C CHECK, INSPECTION REPORTED FOUR EPSU FAILURES DURING CAPACITY TESTING. MAINTENANCE REMOVED AND REPLACED THE EPSU BATTERIES (PN 3214-30, SN 27195, 27186, 25851, AND 27185) IN ACCORDANCE WITH THE REQUIREMENTS OF AMM 33-51-38-000-002, AMM 33-51-38-400-002, AMM 33-51-28-020-053 AND AMM 33-51-38-420-052. UPON COMPLETION OF THE REPLACEMENTS, THE UNITS WERE TESTED AND FOUND ACCEPTABLE.

ATA 5270

Part: PROXIMITY SWITCH — INOPERATIVE (R1 DOOR) · airframe 20,124 hrs · 8,533 cycles

DURING C4/S1 C CHECK, INSPECTION REPORTED THE R-1 DOOR SLIDE ARM LIGHT WAS INOPERATIVE. MAINTENANCE REMOVED AND REPLACED THE R-1 DOOR PROXIMITY SWITCH (13WV2) IN ACCORDANCE WITH THE REQUIREMENTS OF AMM 52-71-11-020-051, AMM 25-23-400-001 AND AMM 52-71-00-710-505. UPON COMPLETION OF THE INSTALLATION, THE NEW SWITCH WAS TESTED, INSPECTED AND FOUND ACCEPTABLE.