N930FR

Part: O-RING — DETERIORATED (HYD SYSTEM) · airframe 26,043 hrs · 12,672 cycles

HYD Y RESERVOIR LOW LEVEL DURING FLIGHT. SUBSEQUENT Y SYS FAILURE INDICATIONS. REMOVED AND INSTALLED SERVICEABLE O-RING ON REDUCER ON PTU MANIFOLD. PERFORMED OPS CK AND LEAK CK. NO FAULTS OR LEAKS NOTED. REF AMM 29-13-15 PB 401, PG 5, STEP 4 A (2) (E) AND (F). OPS CHECKED IAW AMM 29-13-00-710-002.

Part: WIRE HARNESS — BROKEN (CABIN) · airframe 21,142 hrs · 10,316 cycles

REFERENCE C CHECK NON ROUTINE N0636. EMERGENCY LIGHTS AT SEAT 20C AND RIGHT AFT DOOR DO NOT ILLUMINATE. REMOVED AND REPLACED WIRING HARNESS 860W AT SEAT 20C IAW AIRBUS A319 AMM 33-51-08. RESEATED PIN 3 OF EXIT LIGHT ASSEMBLY ON RIGHT AFT DOOR 32WL IAW AIRBUS A319 AWM 33-51-02.

Part: LEG ASSY — CORRODED (MLG) · airframe 21,142 hrs · 10,316 cycles

REF C-CHECK NON ROUTINE N0565. AFTER REMOVAL OF RT MLG SLIDING TUBE FOUND CORROSION ON INNER BORE AT LOWER BRG AREA. REPAIRED CORRODED AREA IAW EA A9-32R-31730.

Part: FRAME — CORRODED (FUSELAGE) · airframe 21,142 hrs · 10,316 cycles

REFERENCE C CHECK NON ROUTINE N0307. AFT CARGO COMPARTMENT FRAME 59 TWELVE INCHES RIGHT OF CENTERLINE PROFILE TOP SURFACE CORRODED. REMOVED AND REPLACED PROFILE IAW AIRBUS A319 SRM 51-40-00.

Part: PLATE — CORRODED (CARGO BAY) · airframe 21,142 hrs · 10,316 cycles

REFERENCE C CHECK NON ROUTINE N0291. FORWARD CARGO COMPARTMENT TRANSITION PLATE BETWEEN FRAME 28 RIGHT AND FRAME 30 RIGHT CORRODED. REMOVED AND REPLACED PLATE IAW AIRBUS A319 SRM 51-72-11.

Part: BLANKING PLATE — CORRODED (CARGO BAY) · airframe 21,142 hrs · 10,316 cycles

REFERENCE C CHECK NON ROUTINE N0290. FORWARD CARGO COMPARTMENT AFT BULKHEAD PLATE BETWEEN FRAME 28 AND FRAME 29 CORRODED. REMOVED AND REPLACED BULKHEAD PLATE IAW AIRBUS A319 SRM 51-40-12.

Part: FLOOR PANEL — DEBONDED (CARGO BAY) · airframe 21,142 hrs · 10,316 cycles

REFERENCE C CHECK NON ROUTINE N0295. AFT CARGO FLOOR PANEL 151ZG DISBONDED. REPAIRED DISBONDED AREA IAW AIRBUS A319 SRM 53-02-00.

Part: PLATE — CORRODED (FUSELAGE) · airframe 21,142 hrs · 10,316 cycles

REFERENCE C CHECK NON ROUTINE N0289. FORWARD CARGO COMPARTMENT TRANSITION PLATE AT STRINGER 38 LEFT BETWEEN FRAME 28 AND FRAME 30 IS CORRODED. REMOVED AND REPLACED PLATE IAW AIRBUS A319 SRM 51-72-11.

Part: FLOOR PANEL — DELAMINATED (ZONE 200) · airframe 21,142 hrs · 10,316 cycles

REF C-CHECK NON ROUTINE N0136. MAIN CABIN FLOOR PANEL 252 HG DISBONDED. REPAIRED FLOOR PANEL IAW SRM 53-02-00.

Part: FLOOR PANEL — DEBONDED (ZONE 200) · airframe 21,142 hrs · 10,316 cycles

REF C-CHECK NON ROUTINE N0135. MAIN CABIN FLOOR PANEL 252 NF DISBONDED. REPAIRED DISBONDED AREA IAW SRM 53-02-00.

Part: WINDSHIELD — CRACKED (COCKPIT) · airframe 18,118 hrs · 8,837 cycles

PILOT REPORTED THAT THE CAPTAIN'S FORWARD WINDSCREEN CRACKED DURING CLIMB THROUGH FL210. MAINTENANCE REMOVED AND REPLACED THE WINDSHIELD, REFERENCE AMM 56-11-11-000-001 AND 56-11-11-400-001.

Part: WINDSHIELD — CRACKED (COCKPIT) · airframe 17,594 hrs · 8,567 cycles

DURING CRUISE FLIGHT, PILOT REPORTED THE RT WINDSHIELD CRACKED. MAINTENANCE REMOVED AND REPLACED THE WINDSHIELD, REFERENCE AMM 56-11-11 PB 401.

Part: LIGHT — INOPERATIVE (CABIN) · airframe 17,500 hrs · 8,523 cycles

REFERENCE LOG PAGE 371414. MAINTENANCE NOTED THAT THE EMERGENCY LIGHT AT ROW 11 ABC WAS INOPERATIVE. MAINTENANCE REMOVED AND REPLACED THE EMERGENCY LIGHT ASSEMBLY AND PERFORMED OPERATIONAL CHECK IAW AMM 33-51-19 PB 401.

Part: FLOOR PANEL — DAMAGED (FUSELAGE) · airframe 15,706 hrs · 7,603 cycles

REFERENCE NON ROUTINE CO51333. DURING C3 C CHECK, INSPECTION NOTED FLOOR PANEL 261EF HAD DAMAGED AREA AROUND INSERT ON OTBD EDGE. MX REMOVED FLOOR PANEL AND REPLACED WITH NEW IN ACCORDANCE WITH THE REQUIREMENTS OF A319 AMM 53-42-12-400-002. UPON COMPLETION OF THE REPAIR, IT WAS INSPECTED AND FOUND ACCEPTABLE.

Part: SCUFF PLATE — CORRODED (FUSELAGE) · airframe 15,706 hrs · 7,603 cycles

REFERENCE NON ROUTINE C051324. DURING C3 C CHECK, INSPECTION NOTED THE L2 DOOR AFT OTBD SCUFF PLATE SUPPORT ATTACHMENT HAD A CORRODED FASTENER. MX REMOVED CORNER ANGLE, OVERSIZED 3 HOLES, FABRICATED 3 FREEZE PLUGS, INSTALLED CORNER ANGLE AND NEW SCUFF PLATE IN ACCORDANCE WITH THE REQUIREMENTS OF ENGINEERING AUTHORIZATION EA NR A9-53R-30632 AND A319 SRM 51-42-11. UPON COMPLETION OF THE REPAIR, IT WAS INSPECTED AND FOUND ACCEPTABLE.

Part: FLOORBEAM — CORRODED (FUSELAGE) · corrosion level 2 · airframe 15,706 hrs · 7,603 cycles

DURING C3 C-CHECK INSPECTION NOTED FLOORBEAMS INBOARD OF THE L2 DOOR SILL CORRODED AND CORROSION IN ALL NUT PLATE HOLES. MX REMOVED FLOORBEAMS, REMOVED BARREL NUT FITTING AND SPLICE, DRILLED HOLES IN SERVICEABLE BEAM, INSTALLED BARREL NUT FITTING AND SPLICE AND INSTALLED BEAMS IN ACCORDANCE WITH THE REQUIREMENTS OF A319 SRM 51-42-11. UPON COMPLETION OF THE REPAIR, IT WAS INSPECTED AND FOUND ACCEPTABLE.

Part: SILL — CORRODED (FUSELAGE) · airframe 15,706 hrs · 7,603 cycles

REFERENCE NON ROUTINE CO51321. DURING C3 C CHECK INSPECTION NOTED THE L2 DOOR SILL AFT OTBD NUT PLATE HOLE WAS CORRODED. MX CUT CORRODED AREA OUT OF THE SILL WEB, FABRICATED REPAIR FILLER AND INSTALLED REPAIR IN ACCORDANCE WITH THE REQUIREMENTS OF A319 SRM 51-73-00, 51-42-11 AND ENGINEERING AUTHORIZATION EA NR A9-53R-30617. UPON COMPLETION OF THE REPAIR, IT WAS INSPECTED AND FOUND ACCEPTABLE.

Part: SILL — CORRODED (FUSELAGE) · corrosion level 2 · airframe 15,706 hrs · 7,603 cycles

DURING C3 C-CHECK, INSPECTION NOTED THE L2 FORWARD GIRT BAR ATTACH FITTING, AFT INBOARD HOLE HAD CORROSION. MX CUT CORRODED AREA OUT OF THE SILL WEB, FABRICATED REPAIR FILLER AND INSTALLED REPAIR IN ACCORDANCE WITH THE REQUIREMENTS OF A319 SRM 53-41-14, 51-75-12 AND ENGINEERING AUTHORIZATION EA NR A9-53R-30629. UPON COMPLETION OF THE REPAIR, IT WAS INSPECTED AND FOUND ACCEPTABLE.

Part: FLOORBEAM — CORRODED (FUSELAGE) · corrosion level 2 · airframe 15,706 hrs · 7,603 cycles

DURING C3 C-CHECK, INSPECTION NOTED THE FLOORBEAM IB OF THE R2 DOOR SILL HAS CORROSION IN ALL NUT PLATE HOLES. MAINT REMOVED AND REPLACED FLOORBEAM. Y1292 IAW THE REQUIREMENTS OF A319 SRM 51-42-11. UPON COMPLETION OF THE REPAIR, IT WAS INSPECTED AND FOUND ACCEPTABLE. (K)

Part: SHEAR PLATE — CORRODED (FUSELAGE) · corrosion level 2 · airframe 15,706 hrs · 7,603 cycles

REFERENCE NOT ROUTINE C051378. DURING C3 C-CHECK, INSP NOTED THE RT SHEAR PLATE FROM FR 69 TO FRAME 70 WAS CORRODED. MAINT REMOVED AND REPLACED SHEAR PLATE ASSY AND SUPPORT FRAME IAW THE REQUIREMENTS OF A319, SRM 51-42-11, PARA 6 AND 7. UPON COMPLETION OF THE REPAIR, IT WAS INSPECTED AND FOUND ACCEPTABLE. (K)

Part: PANEL — PUNCTURED (CARGO BAY) · airframe 7,603 hrs

REFERENCE NON-ROUTINE C050860. DURING C3-C-CHECK, INSPECTION NOTED THE AFT PIT TRANSITION PANEL 151BE WAS DAMAGED. MAINTENANCE REPAIRED DAMAGED FLOOR PANEL IAW THE REQUIREMENTS OF A319 SRM 53-02-00, FIGURE 204. UPON COMPLETION OF THE REPAIR, IT WAS INSPECTED AND FOUND ACCEPTANCE. (K)

Part: PANEL — PUNCTURED (FUSELAGE) · airframe 15,706 hrs · 7,603 cycles

REFERENCE NON-ROUTINE C050859. DURING C3 C-CHECK. INSPECTION NOTED THE AFT PIT TRANSITION PANEL 151FE WAS DAMAGED. MAINTENANCE REPAIRED DAMAGED FLOOR PANEL IAW THE REQUIREMENTS OF A319 SRM 53-02-00, FIGURE 204. UPON COMPLETION OF THE REPAIR. IT WAS INSPECTED AND FOUND ACCEPTABLE. (K)

Part: PANEL — PUNCTURED (FUSELAGE) · airframe 15,706 hrs · 7,603 cycles

REF NON-ROUTINE C050863. DURING C3-C-CHECK. INSP NOTED THE AFT PIT TRANSITION PANEL 151TG WAS DAMAGED. MAINT REPAIRED DAMAGED FLOOR PANEL IAW WITH THE REQUIREMENTS OF SRM 53-02-00, FIGURE 204. UPON COMPLETION OF THE REPAIR. IT WAS INSPECTED AND FOUND ACCEPTABLE. (K)

Part: FLOOR PANEL — CORRODED (FUSELAGE) · airframe 15,706 hrs · 7,603 cycles

REFERENCE NON ROUTINE CO51223. DURING C3 C CHECK INSPECTION NOTED FLOOR PANEL 261FF HAD CORROSION ON UPPER AND LOWER SURFACES. MX REMOVED FLOOR PANEL AND INSTALLED NEW IN ACCORDANCE WITH THE REQUIREMENTS OF A319 AMM 53-42-12-400-002. UPON COMPLETION OF THE REPAIR, IT WAS INSPECTED AND FOUND ACCEPTABLE.

Part: FLOOR PANEL — CORRODED (FUSELAGE) · airframe 15,706 hrs · 7,603 cycles

REFERENCE NON ROUTINE CO51286. DURING C3 C CHECK, INSPECTION NOTED FLOOR PANEL 262FF HAD CORROSION ON AFT BOTTOM SURFACE. MX REMOVED FLOOR PANEL AND INSTALLED NEW IN ACCORDANCE WITH THE REQUIREMENTS OF A319 AMM 53-42-12-400-002. UPON COMPLETION OF THE REPAIR, IT WAS INSPECTED AND FOUND ACCEPTABLE.

Part: STRINGER — CORRODED (FUSELAGE) · airframe 9,814 hrs · 4,725 cycles

DURING C-2 CHECK INSPECTION, REPORTED FWD CARGO COMPARTMENT STRINGER 42R AT THE AFT END OF ZONE 131, INBD OF CARGO DOOR FROM F24 TO F28, HAD EXFOLIATION/CORROSION AROUND RIVETS. REMOVED CORRODED RIVETS IAW SRM 51-42-11. PERFORMED HFEC INSPECTION OF HOLES IAW NTM 51-10-01, PAGE 612. NO DEFECTS NOTED. OVERSIZED HOLES AND INSTALLED RIVETS PER SRM 51-42-11.