N636VA

Part: SUPPORT — CORRODED (FUSELAGE) · corrosion level 2 · airframe 40,192 hrs · 12,209 cycles

DURING "OK TO INSTALL" AFT SHEAR WEB @ FR. 70L (OPS#44171), FOUND FRAME SUPPORT WEB @ FR. 70L - HAS CORROSION ON LOWER SKIN SURFACE @ AFT LIGHTENING HOLE. ( THIS WAS HIDDEN BY SHEAR WEB INSTALLATION) GROUNDED - YES. REMOVED AND REPLACED FRAME SUPPORT IAW A320 SRM 51-42-11 AND AIRBUS DWG D53474180. CAT A REPAIR, NO ALLOWABLE LIMITS GIVEN IN SRM.

Part: DOOR SILL — CORRODED (FUSELAGE) · airframe 43,016 hrs · 13,339 cycles

AFT CABIN FLOOR @ R2 DOOR, AFT DOOR CUT OUT AROUND AFT GIRT BAR RECEPTACLE BASE PLATE SHOWS SIGNS OF CORROSION  GROUNDED - YES. REPLACED AFT R2 DOOR SILL, PART #D5348004320701, ALL WORK ACCOMPLISHED ON HAECO AA NON-ROUTINE #G1368878. REMOVED AND REINSTALLED AFT R2 DOORSTOP FITTINGS AND CLOSE OUT ANGLE IAW A320 AMM 52-13-31. REMOVED AND REINSTALLED AFT GIRT BAR FITTINGS IAW A320 AMM 52-13-31. DOORSTOP FITTING ADJUSTMENTS COMPLETED ON HAECO AA N/R #G1368988

Part: DOOR SILL — CORRODED (FUSELAGE) · airframe 43,016 hrs · 13,339 cycles

AFT CABIN FLOOR @ R2 DOOR, FWD DOOR CUT OUT AROUND AFT GIRT BAR RECEPTACLE BASE PLATE SHOWS SIGNS OF CORROSION GROUNDED - YES. REMOVED AND REPLACED AFT R2 DOOR SILL. PART #D5348004320701, IAW A320 SRM 51-42-11 AND AIRBUS DWG D53480505. REMOVED AND REINSTALLED FWD R2 DOOR STOP FITTING AND CLOSE OUT ANGLES IAW A320 AMM 53-13-31. REMOVED AND REINSTALLED FWD GIRT BAR FITTINGS IAW A320 AMM 52-13-31. DOOR STOP FITTING ADJUSTMENTS COMPLETED ON HAECO AA N/R # G1368988 ORIGINAL THICKNESS .256 REMAINING .180 .076 REMOVED OUT OF LIMITS.

Part: SUPPORT FRAME — CORRODED (FUSELAGE) · airframe 40,089 hrs · 12,159 cycles

FRAME 36 BELLY FAIRING SUPPORT FRAME HAS CORROSION AT A/C CENTER LINE (STREAMER ATTACHED)  GROUNDED - YES. REMOVED AND REPLACED FRAME 36 BELLY FAIRING SUPPORT IAW A320 SRM 51-44-11. MATERIAL LOSS ON SUPPORT IS 100% DUE TO CORROSION DOT AND STREAMER REMOVED P.O.# 969631.2

Part: BEAM — CORRODED (FUSELAGE) · airframe 40,089 hrs · 12,159 cycles

MAIN CABIN, LONGITUDINAL BEAM CORRODED BETWEEN FR18 AND FR20 APPROX. -Y1292. MARKED  GROUNDED - YES. REPAIRED MAIN CABIN LONGITUDINAL BEAM FROM FRAME 18-20 -1292 IAW 51-42-11, 51-72-11 AND DWG UR-D531-10920. BLENDED BEYOND LIMITS PART REPLACED.

Part: FLOORBEAM — CORRODED (FUSELAGE) · airframe 40,089 hrs · 12,159 cycles

MAIN CABIN BETWEEN FRAME 69-70 Y254 HAS CORROSION ON SUPPORT BEAM GROUNDED - YES. REMOVED AND REPLACED FLOOR BEAM Y254 IAW A320 SRM 51-42-11. AIRBUS DWG D53472040700701. CORROSION REMOVED ON FLOOR BEAM IAW A320 SRM 53-00-14 .050 MATERIAL REMOVED .100 REMAINING OUT OF LIMITS

Part: SUPPORT BEAM — CORRODED (FUSELAGE) · airframe 40,089 hrs · 12,159 cycles

MAIN CABIN SUPPORT BEAM CORRODED @ FRAME 68 -Y638 GROUNDED - YES. REMOVED CORRODED BEAM IAW A320 SRM 51-42-11. INSTALLED NEW BEAM PN D536721950400 P.O. 968361.1 IAW A320 SRM 51-42-11 AND DWG # D534-72095 AND DWG #D534-72836 REMOVED CORROSION IAW A320 SRM 53-00-14 ORIGINAL MATERIAL THICKNESS .150 MATERIAL LOSS .025, REMAINING MATERIAL THICKNESS .125. OUT OF LIMITS PER A320 SRM 53-00-14.

Part: SUPPORT BEAM — CORRODED (FUSELAGE) · corrosion level 2 · airframe 40,089 hrs · 12,159 cycles

MAIN CABIN BETWEEN FRAME 69-70 -Y254 HAS CORROSION ON SUPPORT BEAM  GROUNDED - YES. REMOVED CORROSION, ORIG THICKNESS .150 REMOVED .050 REMAINING MAT .100 FOUND TO BE OUT OF LIMITS IAW A320 SRM 53-00-14-283-002. REMOVED SUPPORT BEAM FROM FRAME 69-70Y254 IAW A320 SRM 51-42-11. LOCATED AND DRILLED NEW SUPPORT BEAM IAW A320 SRM 51-72-11. INSTALLED NEW SUPPORT BEAM IAW A320 SRM 51-72-11.

Part: REGULATOR — FAILED (AC BAY) · airframe 30,721 hrs · 9,020 cycles

EXPERIENCED A NR 2 PACK FAULT ON CLIMBOUT WITH THE NR 1 PACK ALREADY ON MEL AND LOCKED OUT. THE AIRCRAFT RETURNED TO DEPARTURE WITHOUT INCIDENT AND NO LOSS OF CABIN PRESSURE. TECH ACCOMPLISHED TROUBLESHOOTING IAW TSM 21-51-00-810-803-A FOR THE NR 1 PACK. REGULATOR WAS REPLACED DURING THE NEXT OVERNIGHT MAINTENANCE OPPORTUNITY. NO FURTHER FAULTS RECORDED DURING SUBSEQUENT FLIGHTS.

Part: FLOOR SUPPORT — CORRODED (FRAMES 68-69)

AFT CABIN FLOOR SUPPORT BETWEEN FRAMES 68-69 AT Y1160 HAS AN AREA OF CORROSION BEYOND LIMITS. REPLACED IAW SRM 51-42-11.

Part: SILL — CORRODED (FRAMES 67-68)

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

Part: SHEAR PLATE — CORRODED (FRAMES 68-69)

RIGHT AFT SHEAR PLATE BETWEEN FRAMES 69-70, S23-24R HAS CORROSION BEYOND LIMITS. SHEAR PLATE REPLACED IAW SRM 51-42-11.

Part: SUPPORT — CORRODED (FRAMES 68-69)

RIGHT AFT SHEAR PLATE SUPPORT BETWEEN FRAMES 69-70, ST23R-24R HAS CORROSION BEYOND LIMITS. SUPPORT REPLACED IAW SRM 51-42-11.

Part: FLOOR SUPPORT — CORRODED (FRAMES 68-69)

AFT CABIN FLOOR SUPPORT BETWEEN FR 68-69 AT Y765 HAS AN AREA OF CORROSION BEYOND LIMITS. REPLACED IAW SRM 51-42-11.

Part: SHEAR PLATE — CORRODED (FRAMES 68-69)

LEFT AFT SHEAR PLATE BETWEEN FRAMES 69-70, S23-24L HAS CORROSION BEYOND LIMITS. THE EXTENT OF THE DAMAGE IS 2"L X 1"W X .025"D. THE SHEAR PLATE WAS REPLACED IAW SRM 51-42-11.

Part: SPAR — CRACKED (RT PYLON) · airframe 18,703 hrs · 5,571 cycles

DURING THIS INSPECTION, CRACKING WAS FOUND ON THE INBD SIDE OF THE RT PYLON AFT FIXED FAIRING UPPER SPAR. SPECIFICALLY, THE INBD FLANGE OF THE AFT FIXED FAIRING UPPER SPAR WAS FOUND CRACKED AT RIB 11, DEFINED AS AREA 3 IN FIG 202 MFG REPAIR INSTRUCTION R54512052. ALSO, THE AFT FIXED FAIRING UPPER SPAR PLATE WAS FOUND CRACKED ON THE INBD SIDE BETWEEN RIBS 14 AND 15. ON THE UPPER SPAR PLATE, THE CRACK HAS EXTENDED THROUGH AREA 1 AND HAS PROPAGATED INTO AREA 2 AS DEFINED IN FIG 201 OF MFG INSTRUCTIONS. THE RT PYLON AFT FIXED FAIRING UPPER SPAR INBD FLANGE AT RIB 11 WAS REPAIRED IAW MFG R54512052, REPAIR PRINCIPLE 2, TC 5454.000001. RT. REPAIR 2, VIA TECH DISPOSITION TD-J2-S2-03170-2013, ISSUE B, DATED FEB 22, 2013.

Part: SPAR — CRACKED (LT PYLON) · airframe 18,703 hrs · 5,571 cycles

DURING THIS INSPECTION, CRACKING WAS FOUND ON THE INBD AND OTBD SIDES OF THE LT PYLON AFT FIXED FAIRING UPPER SPAR. SPECIFICALLY, BOTH THE INBD AND OTBD FLANGES OF THE AFT FIXED FAIRING UPPER SPAR PLATE WAS FOUND CRACKED AT RIB 11, DEFINED AS AREA 3. ALSO, THE AFT FIXED FAIRING UPPER SPAR PLATE WAS FOUND CRACKED ON BOTH THE INBD AND OTBD SIDE BETWEEN RIBS 14 AND 15. IN BOTH CASES ON THE UPPER SPAR PLATE, THE CRACK AS EXTENDED THROUGH AREA 1 AND HAS PROPAGATED INTO AREA 2. ACCOMPLISHED THE REPAIR OF THE LT PYLON AFT FIXED FAIRING UPPER SPAR INBD AND OTBD PLATE BETWEEN RIBS 14 AND 15 IAW MFG TECH DISPOSITION TD-J2-S2-03171-2013 ISSUE A. ALSO, ACCOMPLISHED THE REPAIRS OF THE LT PYLON AFT FIXED FAIRING UPPER SPAR INBD AND OTBD FLANGES AT RIB 11 IAW TC 5454-000001. LT REPAIR 2.

Part: SKIN — DAMAGED (FUSELAGE)

INSTALLED DOUBLER REPAIR AT LOWER SKIN BETWEEN STRINGER 39L AND 39R FROM FRAME 21 TO FRAME 23. MATERIAL USED 2024T3 .080" PO 1062499. DIMENSIONS 22.5" X 30" IAW REPAIR DESIGN APPROVAL SHEET 70541148/019/2011 ISSUE: A, DATED 31/03/2011. THIS REPAIR IS CLASSIFIED: MAJOR, CAT B. INSTALLED CROSS BEAM PN D53910678200 IAW CARD EC5310.000010.

Part: TIRE — FAILED (NLG)

ACFT DEPARTED, DURING ROTATION, CAPT NOTED A LOUD NOISE CLOSE TO V1 AT 2208Z. MX CONSULTED WITH THE CAPT ABOUT THE NATURE OF THE NOISE, LOCATION & ANY ABNORMAL INDICATIONS. ONLY INDICATION NOTED WAS A BSCU1 INOP MESSAGE. NO OTHER ISSUES NOTED, & ALL HYD FLUID LEVELS, PRESSURES & TEMPS NORMAL & STABLE. CREW ADVISED TO CONSULT FCOM & QRH FOR INDICATION. NO EMERGENCY WAS DECLARED. ACFT LANDED WITHOUT INCIDENT. MX NOTED RT NLG TIRE HAD SEPARATED FROM WHEEL WITH THE TIRE STILL INFLATED. BELLY FUSELAGE AREA DIRECTLY BEHIND NOSE WHEEL AREA HAD ALSO SUSTAINED NUMEROUS DENTS FROM RUBBER DEPARTING TIRE. RT NOSE TIRE REPLACED, PN 3-1531-3, SN A7553, REMOVED & SENT FOR TEARDOWN. INSP AFTER TIRE TREAD THROWN, ACCOMPLISHED WITH NO OTHER FINDINGS. DENTS MAPPED & INSPECTED WITH HIGH FREQ EDDY CURRENT FOR ANY CRACKS IN PREP FOR A MX FERRY FLT TO ACCOMPLISH THE REQUIRED REPAIRS. OPEN

Part: UNKNOWN — SMOKE (CABIN)

AT APPROX 15:25Z (4 HOURS INTO FLIGHT) A CRUISE ALTITUDE, A "SMELL OF SMOKE BETWEEN ROWS 25 AND 26 LASTED APPROX 30 MIN", BY AN IN-FLIGHT TEAM MEMBER. AFTER BEING ADVISED OF THE ISSUE VIA ACARS, MAINT CONTROL ADVISED THE CREW TO COMPLETELY TURN OFF THE IN-FLIGHT ENTERTAINMENT SYS (IFE) AS A PRECAUTION AND POSSIBLE FAULT ISOLATION. UPON LANDING, CREW MEMBERS BRIEFED MAINT TECH FOR TROUBLESHOOTING ISSUE. AFTER A DETAILED VISUAL INSP AND EXTENSIVE OPS CHECK OF SUSPECTED SYS COMPONENTS, THE DISCREPANCY COULD NOT BE DUPLICATED DURING THE OVERNIGHT MAINT CHECK. SINCE NO DEFECT OR MALFUNCTION COULD BE IDENTIFIED, NO COMPONENTS WERE REPLACED. STC`S AND PMA`S ARE IN COMPLIANCE. AS OF NOW THERE ARE NO KNOWN AD OR SB RELATED TO VRD`S IFE SYS. (K)