N638VA

Part: SKIN — GOUGED (L2 DOOR) · airframe 42,563 hrs · 13,173 cycles

HISSING NOISE FROM DOOR 2 L LOWER PORTION IN FLIGHT. GROUNDED - YES. FOUND DAMAGE TO LOWER SECTION OF L2 DOOR. ACCOMPLISHED REPAIR TO LOWER SECTION OF THE L2 DOOR REF A320 SRM 52-10-00-300-005.THIS IS A CATERGORY "B" REPAIR WITH AN INSPECTION THRESHOLD OF 60,000 FC AFTER REPAIR EMBODIMENTREF A320 SRM 52-10-00-205-011.ACCOMPLISHED PRESSURE LEAK CHECK AT L2 DOOR. NO NOISE NOTED.

Part: HINGE FITTING — BROKEN (RT ELEVATOR) · airframe 42,561 hrs · 13,172 cycles

RH ELEVATOR, #3 HINGE FITTING, BROKEN GROUNDED - YES. REMOVED HINGE FITTING REF A320 SRM 51-42-11. REPAIRED FITTING REF A320 SRM 55-26-41-300-001. INSTALLED FITTING REF AIRBUS DWG D55281820.

Part: DOOR SILL — CORRODED (FRMS 16-20) · airframe 42,562 hrs · 13,172 cycles

L/H FWD ENTRY DOOR CUT OUT AFT LOWER CORNER CORRODED AT FASTENER HOLE DOT:P776 GROUNDED - YES. ACCOMPLISHED REPAIR ON FWD ENTRY DOOR LOWER SILL IAW AIRBUS A320 SRM 53-11-14. THIS IS A CATEGORY "B" REPAIR WITH AN INSPECTION THRESHOLD OF 60,000 FC REF A320 SRM 53-11-14-205-001DOT REMOVED

Part: BEAM — GOUGED (FRMS 12-16) · airframe 42,562 hrs · 13,172 cycles

CABIN FLOOR STRUCTURE CENTER BEAM HAS GOUGE AT FASTNER HOLE APPROXIMATELY 5 INCHES FWD OF FR14 NEAR FLIGHT DECK DOOR AREA RH SIDE, STREAMER ATTACH AND MARKED IN REDDOT:S303 GROUNDED - YES. BLENDED GOUGED AREA. LOSS OF.100- FOUND OUT OF LIMITS IAW A320 SRM 53-11-14. REMOVED AND REPLACED BEAMN IAW DWG D53112828. INSTALLED HOSES TO COLLECTOR GRID IAW A320 AMM 53-19-41. ORIGINAL THICKNESS .160, REMAINING .060, .100 REMOVED REMOVED DOT

Part: SEAT TRACK — CORRODED (FRM 12-24) · corrosion level 2 · airframe 42,562 hrs · 13,172 cycles

FRAME 21 R/H PANEL SUPPORT BEAM HAS CORR GOING TO FRAME 15C.DOT: P770 GROUNDED - YES. DAMAGE FOUND TO BE IN AN AREA WHERE REWORK IS NOT PERMITTED. OUT OF LIMITS REF A320 SRM 53-11-14. REMOVED AND REPLACED TRACK REF AIRBUS DWG 53112814 & D53112812REMOVED DOT

Part: DOOR SILL — CORRODED (FRMS 16-20) · airframe 42,562 hrs · 13,172 cycles

R/H FWD SERVICE DOOR CUT OUT LOWER AFT CORNER HAS CORRODED AT FASTENER HOLE DOT P772 GROUNDED - YES. ACCOMPLISHED REPAIR AS PER A320 SRM 53-11-14, R/H FWD LOWER DOOR SEAL. THIS IS A CATEGORY "B" REPAIR WITH AN INSPECTION THRESHOLD OF 60,000 FC REF A320 SRM 53-11-14-205-001REMOVED DOT

Part: BEAM — CORRODED (FRMS 16-20 S23L) · airframe 13,172 hrs · 42,561 cycles

FWD ENTRY DOOR CUTOUT LOWER FWD CORNER CORRODED AT FASTENER HOLE 4 EACH GROUNDED - YES. ACCOMPLISHED REPAIR ON FWD ENTRY DOOR LOWER SILL IAW AIRBUS A320 SRM 53-11-14. THIS IS A CATEGOR "B" REPAIR WITH AN INSPECTION THRESHOLD OF 60,000FC REF A320 SRM 53-1-14-205-001REMOVED DOT

Part: DOOR SILL — CORRODED (FRMS 16-20) · airframe 42,562 hrs · 13,172 cycles

R/H FWD SERVICE DOOR CUTOUT LOWER FWD CORNER HAS CORRODED AT FASTENER HOLE GROUNDED - YES. REMOVED 4 EACH WATER LINE CLAMPS, 4 EA HI-LOKS AND 1 EACH FLOOR BEAM BOLT TO FOM AS PER A320 SRM 51-42-11. REMOVED CORROSION AND FOUND TO BE WITHIN LIMITS AS PER A320 SRM 53-11-14. ACCOMPLISHED DVI AS PER A320 53-11-14. HFEC AS PER NTM 51-10-08. SPOT FACED 4 EACH AREAS AS PER A320-SRM 53-11-14 FIGURE 001, PARAGRAPH 7(B). ROTOPEENED AS PER NTM 51-10-01. MATERIAL ID FOR WASHERS AS PER A320 SRM 53-11-14. FABRICATED WASHERS AS PER A320 SRM 53-11-14-283-005. ACCOMPLISHED REPAIR PER AIRBUS A320 SRM 53-11-14. THIS IS A CATEGORY "B" REPAIR WITH AN INSPECTION THRESHOLD OF 60,000 FC REF A320 SRM 53-11-14-205-001DOT REMOVED

Part: FLOORBEAM — CORRODED (CABIN) · airframe 42,561 hrs · 13,172 cycles

FLOOR BEAM HAS AREA OF CORROSION ON TOP SURFACE, JUST AFT OF R2 DOOR AND TOWARDS CENTER OF A/C ONE FRAME DOT:A441 GROUNDED - YES. REMOVED AND REPLACED SUPPORT BEAM AS REQUIRED IAW AIRBUS DWG #D53472040 REV "A" ORIGINAL THICKNESS IS .160, REMAINING IS .140, .040 REMOVED. P.O. 1004829.1 REMOVED DOT

Part: FLOORBEAM — CORRODED (CABIN) · airframe 42,561 hrs · 13,172 cycles

FLOOR BEAM HAS AREA OF CORROSION ON TOP SURFACE, JUST AFT CORNER OF L2 DOOR DOT:A443 GROUNDED - YES. REMOVED CORROSION AND REPAIRED 2EA AREAS IAW A320 SRM 53-41-14. ORIGINAL THICKNESS .063, THICKNESS REMOVED .043, THICKNESS REMAINING .020, FOR BOTH AREAS. ACCOMPLISHED REPAIR PRINCIPLE 7 TO AREA 1 AND ACCOMPLISHED REPAIR PRINCIPLE 8 TO AREA 2. ALL WORK PERFORMED IAW A320 SRM 53-41-14 CATEGORY "A" REPAIRS DOT REMOVED

Part: FLOOR SUPPORT — CORRODED (FRMS 68-70) · corrosion level 2 · airframe 42,561 hrs · 13,172 cycles

FLOOR BEAM HAS AREA OF CORROSION ON TOP SURFACE, JUST AFT OF R2 DOOR AND TOWARDS CENTER OF A/C TWO FRAMES GROUNDED - YES. REMOVED AND REPLACED FLOOR BEAM P/N D5347219520400 PO# 1004824.2 IAW AIRBUS A320 SRM 51-42-11 AND AIRBUS DWG # D53472040 ISSUE A.REMOVED DOT

Part: FLOOR SUPPORT — CORRODED (FRMS 68-69) · corrosion level 2 · airframe 42,562 hrs · 13,172 cycles

FLOOR BEAM HAS AREA OF CORROSION ON TOP SURFACE JUST AFT OF R2 DOORDOT:A440 GROUNDED - YES. CORROSION FOUND TO BE OUT OF LIMITS. ORIGINAL THICKNESS IS .160, REMOVED .160, .000 REMAINING REF A320 SRM 53-00-14.REMOVED AND REPLACED BEAM REF A320 SRM D53472458DOT REMOVED

Part: FLOORBEAM — CORRODED (MAIN CABIN) · airframe 42,562 hrs · 13,172 cycles

MAIN CABIN, AFT GALLEY UPPER FLOOR L/H SUPPORT FRAME CORRODED GROUNDED - YES. REMOVED AND REPLACED MAIN CABIN AFT GALLEY UPPER FLOOR LH SUPPORT FRAME PN:D5347112320200 PO: 907924.2 IAW D63474180, D53471123, A320-SRM 51-44-11

Part: FLOOR SUPPORT — CORRODED (FRMS 68-70) · corrosion level 2 · airframe 42,562 hrs · 13,172 cycles

MAIN CABIN AFT GALLEY AREA FLOOR BEAM CORRODED AT Y512.5 BETWEEN FR70-FR69 GROUNDED - YES. REMOVED CORROSION AND CHECKED THE LIMITS. ORIGINAL THICKNESS IS .160, REMAINING IS .100, .060 WAS REMOVED . OUT OF LIMITS REF A320 SRM 53-00-14. REMOVED AND REPLACED BEAM REF AIRBUS DWG D53472780

Part: FLOOR SUPPORT — CORRODED (FRMS 69-70) · airframe 42,561 hrs · 13,172 cycles

MAIN CABIN AFT GALLEY AREA FLOOR BEAM CORRODED AT Y160.5 BETWEEN FR70-FR69 GROUNDED - YES. REMOVED AND REPLACED SUPPORT BEAM AT Y160.5 BETWEEN FR70-69 IAW DRAWING D53472040, A320-SRM-51-44-11, A320-SRM-51-42-11PN: 5247219620000 PO: 1004517.1

Part: SHEAR PLATE — CORRODED (FRMS 69-70 S23L) · corrosion level 2 · airframe 42,562 hrs · 13,172 cycles

MAIN CABIN, AFT GALLEY AREA UPPER FLOOR L/H SHEAR WEB CORRODED AT FR69-FR70 STR23L GROUNDED - YES. WEBB FOUND TO HAVE 100% MAT'L LOSS TOOL # E113387A. REMOVED AND REPLACED WEB REF AIRBUS DWG 53474180 & A320 SRM 51-44-11

Part: SHEAR WEB — CORRODED (FRMS 69-70) · corrosion level 2 · airframe 13,172 hrs · 42,561 cycles

MAIN CABIN, AFT GALLEY AREA UPPER FLOOR R/H SHEAR WEB CORRODED AT FR69-FR70 STR23R. GROUNDED - YES. NO AVAILABLE LIMITS FOR THE SHEAR WEB.REMOVED AND REPLACED WEB REF AIRBUS DWG D53474180.WEB FOUND TO HAVE 100% MAT'L LOSS.

Part: FLOOR SUPPORT — CORRODED (FRMS 68-70) · corrosion level 2 · airframe 42,562 hrs · 13,172 cycles

MAIN CABIN, AFT GALLEY AREA FLOOR BEAM AT -Y160.5 IS CORRODED. (P/N 5347209700200) DOT: A582 GROUNDED - YES. REMOVED CORROSION. ORIGINAL THICKNESS IS .160, REMAINING IS .080, .080 WAS REMOVED. OUT OF LIMITS REF A320 SRM 53-00-14. REMOVED AND REPLACED BEAM REF AIRBUS DWG D53472040 REV "A" DOT REMOVED

Part: FLOOR PANEL — DELAMINATED · airframe 42,562 hrs · 13,172 cycles

AFT CARGO COMPARTMENT FLOORBOARD 152EF HAS 2EA TEMPORARY REPAIRS, REQUIRES PERMANENT REPAIRS GROUNDED - YES. PERFORMED PERMANENT REPAIR ON AFT CARGO COMPARTMENT FLOORBOAD 152EF ON 2EA AREAS IAW A320-214 SRM: 53-02-00-304-004 PARA. 2.A; A/C: N638VA, S/N: 3503, FH: 42561, FC: 13172, WEIGHT VARIANT:010

Part: FLOORBOARD — DELAMINATED · airframe 42,562 hrs · 13,172 cycles

AFT CARGO COMPARTMENT FLOORBOARD 152MF HAS 1 EA TEMPORARY REPAIR, REQUIRES PERMANENT REPAIR GROUNDED - YES. PERFORMED PERMANENT REPAIR ON AFT CARGO COMPARTMENT FLOORBOARD 152MF ON 1EA AREA IAW A320-214 SRM: 53-02-00-300-004 PARA. 2.A; A/C: N638VA, S/N: 3503, FH: 42561, FC: 13172, WEIGHT VARIANT: 010

Part: FLOOR PANEL — DELAMINATED · airframe 42,562 hrs · 13,172 cycles

AFT CARGO COMPARTMENT FLOORBOARD 152FF HAS 2EA TEMPORARY REPAIRS, REQUIRES PERMANENT REPAIRS GROUNDED - YES. PERFORMED PERMANENT REPAIR ON AFT CARGO COMPARTMENT FLOORBOARD 152FF 2EA AREA IAW A320-214 SRM: 53-02-00-300-004 PARA. 2.A; A/C: N638VA, S/N: 3503, FH: 42561. FC: 13172, WEIGHT VARIANT: 010

Part: FLOORBOARD — DELAMINATED · airframe 42,562 hrs · 13,172 cycles

AFT CARGO COMPARTMENT FLOORBOARD 152NF HAS 1 EA TEMPORARY REPAIR, REQUIRES PERMANENT REPAIR GROUNDED - YES. PERFORMED PERMANENT REPAIR ON AFT CARGO COMPARTMENT FLOOR BOARD 152NF ON 1EA AREA IAW A320-214 SRM: 53-02-00-300-004 PARA. 2.A; A/C: N638VA, S/N: 3503, FH: 42561, FC: 13172, WEIGHT VARIANT: 010

Part: FLOOR PANEL — DELAMINATED · airframe 42,562 hrs · 13,172 cycles

[PARTS RACK] FWD CARGO COM0PARTMENT FLOOR PANEL 131BF HAS 2 EA TEMPORARY REPAIRS, PERMANENT REPAIR REQUIRED. GROUNDED - YES. REPAIRED FWD CARGO COMPARTMENT FLOOR PANEL 131BF AT 3EA. AREAS, PERFORMED PERMANENT REPAIRS IAW A320-214 SRM: 53-02-00-300-004 PARA. 2.A; A/C N638VA, S/N: 3503, FH: 42561, FC: 13172, WEIGHT VARIANT: 010

Part: FLOOR PANEL — DELAMINATED · airframe 42,562 hrs · 13,172 cycles

[PARTS RACK] FWD CARGO COMPARTMENT FLOOR PANEL 131CF HAS 2 EA TEMPORARY REPAIRS. PERMANENT REPAIR REQUIRED. GROUNDED - YES. PERFORMED PERMANENT REPAIR ON FWD CARGO COMPARTMENT FLOOR PANEL 131CF AT 2EA. AREAS IAW A320-214 SRM; 53-02-00-300-004 PARA. 2.A; A/C: N638VA, S/N: 3503, FH: 42561, FC: 13172. WEIGHT VARIANT: 010

Part: SKIN — DENTED (FRAME 65) · airframe 41,729 hrs · 12,795 cycles

AFT FUSELAGE SKIN DENT BTW FR 64/65 AND STR 40/41 LH. REF EA A320-53EA-00124. REQUIRES PERMANENT REPAIR. GROUNDED - YES. INSTALLED PERMANENT CATEGORY 'A' REPAIR REF A320 SRM 53-41-11-30-093.

Part: COMPRESSOR — ODOR

CREW NOTICED A SLIGHT ELECTRICAL OR BURNED RUBBER ODOR. MX FOUND SOURCE OF THE ODOR TO BE POTABLE WATER AIR COMPRESSOR. MX DEACTIVATED COMPRESSOR AND PLACED IT ON MEL IAW 38100101G. COMPRESSOR AND PRESSURE SWITCH WILL BE REMOVED AND REPLACED AT NEXT AVAILABLE MX OPPORTUNITY.

Part: WIRE — DAMAGED (THRUST REVERSER) · airframe 30,126 hrs · 8,830 cycles

EXPERIENCED AN ENGINE 1 REVERSE UNLOCKED ECAM MESSAGE ON LANDING ROLL-OUT AFTER THRUST REVERSER STOWED. TECHS APPLIED MEL 78-30-01 AND COMPLIED WITH ALL DEFERRAL PROVISIONS, THE ACFT DEPARTED AS VX174, WITHOUT RECURRENCE, THE AIRCRAFT ALSO OPERATED THE NEXT LEG VX193 WITHOUT INCIDENT. ACFT DEPARTED, DURING CLIMBOUT THE CREW EXPERIENCED A REV UNLOCKED MESSAGE AND ASSOCIATED MASTER CAUTION, THE CREW FOLLOWED FCOM PROCEDURES AND RETURNED TO DEPARTURE. THE ACFT WAS REMOVED FROM SERVICE AND TECHS ACCOMPLISHED TSM PROCEDURES. DURING TROUBLESHOOTING, A DAMAGED WIRE WAS FOUND BETWEEN CONNECTOR 50EG1 AND 752VC1, THE WIRE WAS REPLACED IAW THE APPLICABLE ESPM PROCEDURE AND THE ACFT WAS RETURNED TO SERVICE. IAW TSM PROCEDURES THE HYDRAULIC CONTROL UNIT AND 4 STOW SWITCHES WERE ALSO REPLACED BEFORE THE DAMAGED WIRE WAS FOUND.

Part: CONTROL UNIT — FAILED (NLG STEERING) · airframe 30,173 hrs · 8,841 cycles

ACFT EXPERIENCED A BRAKES ANTI SKID NOSE WHEEL STEERING FAULT AFTER TAKEOFF. ON ARRIVAL, THE ACFT WAS UNABLE TO TAXI OFF THE RUNWAY DUE TO NO NOSE WHEEL STEERING, THE AIRCRAFT WAS TOWED TO THE GATE. DURING TROUBLESHOOTING, TECH FOUND BOTH BSCU CONTROL CIRCUIT BREAKERS 3GG TRIPPED. R & R BSCU IAW AMM 32-42-34, PB 401.

Part: TUBE — CORRODED (NLG)

INSPECTION SHOWED CORROSION ON THE NLG, BUSHED TURNING TUBE AT THE UPPER TORQUE LINK INNER SURFACE. THE BUSHINGS WERE REMOVED AND THE CORROSION WAS FOUND TO BE BEYOND LIMITS. THE TURNING TUBE, PN D65520, SN L3524 WAS REMOVED ANT THE O/H TURNING TUBE PN D65520, SN L3528 WAS INSTALLED IAW CMM 32-27-20, REV 9, DATED 4/15/13 AND CMM 32-27-40, REV 4, DATED 12/31/09.

Part: SHEAR PLATE — CORRODED (FRAMES 69-70)

LEFT AFT SHEAR PLATE BETWEEN FRAMES 69-70, S23-24L CORRODED BEYOND LIMITS. SHEAR PLATE R & R IAW SRM 51-42-11.

Part: SHEAR PLATE — CORRODED (FRAMES 69-70)

RIGHT AFT SHEAR PLATE BETWEEN FRAMES 69-70, S23-24R CORRODED BEYOND LIMITS. SHEAR PLATE R & R IAW SRM51-42-11.

Part: SILL — CORRODED (FRAMES 67-68)

LEFT AFT DOOR SILL HAS TWO AREAS OF CORROSION BETWEEN FRAMES 67-68, S23-24L Y1725. REPAIRED IAW SRM 53-41-14, FIG 201, REPAIR PRINCIPLE 5.

Part: PLATE — BROKEN (PAX DOOR) · airframe 11,197 hrs · 3,348 cycles

ACFT WAS UNDERGOING OVERNIGHT PLANNED MX THE MORNING OF 4/23/2011. DURING ACCOMPLISHMENT OF TASK CARD 521121-02-1-R2, A DOOR MECHANISM LUBE TASK, IT WAS NOTED THE ARM/DISARM HANDLE PLATE WAS LOOSE. UPON FURTHER INSPECTION, THE TECH FOUND THE ATTACHMENT HOLE CRACKED WHERE THE HANDLE PLATE ATTACHED TO THE DISARM LEVER, REF AIPC 52-13-22-02B, ITEM 300B, PN D5211005121700. INSPECTION OF THE ARM/DISARM LEVER ASSY REVEALED NO FURTHER DAMAGE. THE PART WAS REPLACED IAW AMM 52-13-22, RII WAS ACCOMPLISHED IAW CAMP 7.15. ALL OPS CHECKS WERE CARRIED OUT IAW AMM 52-13-22. THE ACFT WAS PLACED BACK IN SERVICE AND INCURRED NO DELAY DUE TO THIS ISSUE. THE HANDLE PLATE WAS SENT FOR EVALUATION. NO DETERMINATION AS TO CAUSE HAS BEEN MADE. ACCORDING TO THE OPERATORS RECORDS, ALL AD, SB, STC`S AND PMA`S ARE IN FULL COMPLLIANCE WITH THE TYPE DESIGN CERTIFICATE AND ASSOCIATED REQUIREMENTS.