N642VA

Part: RESERVOIR — DEPLETED (AFT CARGO COMPT) · airframe 39,265 hrs · 14,004 cycles

R/H OVERWING SLIDE ACTUATION CABLE DISCONNECTED IN AFT CARGO. GROUNDED - YES. REMOVED R/H OVERWING SLIDE INFLATION RESERVOIR ASSEMBLY S/N A16313 AND REPLACED WITH SERVICEABLE UNIT IAW AIRBUS A320 AMM 25-62-46.

Part: HINGE ARM — CRACKED · airframe 39,265 hrs · 14,004 cycles

RUDDER ATTACH FITTINGS, #1 HINGE ARM , LOWER LUG, 3RD FASTENER HOLE FROM LEFT HAS CRACK INDICATION AT 7 O'CLOCK POSITION GROUNDED - YES. REMOVED & REPLACED #1 HINGE ARM IAW ASA AIRBUS DWG D55371321 REV. D, ASA AIRBUS A320 SRM 55-36-42 & EA # A32055EA-01311 REV .00 REV. DATE 02-10-2022

Part: FLOOR PANEL — NONE · airframe 39,265 hrs · 14,004 cycles

FLOOR PANEL PN SB2076-19 HAS DAMAGE GROUNDED - YES. REPAIRED CABIN FLOOR PNL Z41EF-2 / SB2076-19 UPPER SURFACE PEELING WITH PRE CURED PHENOLIC REPAIR PATCH IAW A320-200 SRM 53-02-00-300-013 REV. 139 01NOV2021, A320-200 NTM 51-10-03 FLT HRS 39265, SLT CYCLES 14004, WT VARIANT 0012,A320 SRM 53-02-00-283-001 REV 139 01NOV2021.

Part: NONE — NONE · airframe 39,265 hrs · 14,004 cycles

FLOOR PANEL PN SB2076-17 HAS DAMAGE GROUNDED - YES. REPAIRE CABIN FLOOR PNL 241EF-1 / SB2076-17 UPPER SURFACE PEELING WITH A PRE CURED PHENOLIC REPAIR PATCH IAW A320-200 SRM 53-02-00-300-013, 53-02-00-283-001 REV. 139 01NOV2021, A320 NTM 51-10-03 FLT HRS 39265 CLT CYCLES 14004 WT VARIANT 0012

Part: NONE — CORRODED · corrosion level 2 · airframe 39,265 hrs · 14,004 cycles

MAIN CABIN FLOOR PANEL SUPPORT BEAM ON RH SIDE AT APPROX Y-1292 HAS CORROSION ON UPPER SURFACE FROM FR 18- FR 20 (MARKED). DOT:W486 GROUNDED - YES. REMOVED CORROSION ORG .079, REMAINING .034 LOSS OF .045. FOUND OUT OF LIMITS IAW A320 SRM 53-11-14.REMOVE FLOOR BEAM IAW A320 SRM 51-42-11. LOCATED AND DRILLED AND INSTALLED NEW FLOOR BEAM IAW AIRBUS DWGS D53112812 AND D53112578.DOT REMOVED

Part: HINGE ARM — CRACKED · airframe 39,265 hrs · 14,004 cycles

#7 RUDDER HINGE FITTING, UPPER HINGE ARM, FWD R/H FASTENER HOLE HAS CRACK INDICATION GROUNDED - YES. REPLACED #7 HINGE ARM IAW ASA EA#A320-55EA-01269 REV.00, ASA AIRBUS DWG D55371052 SHEET 5, VEIW 5-5 & SRM 55-36-42

Part: NONE — CORRODED · airframe 39,265 hrs · 14,004 cycles

L1 DOOR LOWER THRESHOLD BEAM HAS A LIGHT CORROSION AT GIRT BAR FITTING STUD, FR16 (MARKED)DOT:T545 GROUNDED - YES. REMOVED CORROSION ON 2EA AREAS, LOCATION 1 IS 1.93Ï¿½ LENGTH 1.00Ï¿½ WIDTH. AND .173Ï¿½ REMAINING LOCATION 2 IS 1.75Ï¿½ LENGTH, 1.15Ï¿½ WIDTH AND .170Ï¿½ REMAINING.FOUND WITHIN LIMITS AND ACCOMPLISHED REWORK AIW AIRBUS A320 SRM 53-11-14REMOVED DOT

Part: NONE — CORRODED · airframe 39,265 hrs · 14,004 cycles

R1 DOOR LOWER THRESHOLD BEAM HAS CORROSION AT GIRT BAR FITTING STUDS, FR20 (MARKED) DOT:T544 GROUNDED - YES. BLENDED AREA AND REMOVED CORROSION, LOWEST REMAINING THICKNESS IS .165Ï¿½ FOUND WITHIN LIMITS IAW AIRBUS A320 SRM 53-11-14DOT REMOVED TOOLING T8492U

Part: PANEL — DELAMINATED · airframe 39,265 hrs · 14,004 cycles

FLOOR PANEL 261CF DAMAGE GROUNDED - YES. EVALUATED & REPAIRED 1 EA. DELAMINATED AREA ON FLOOR PANEL 261CF, PANEL IS LOCATED BETWEEN FR 64 & FR 66. LOCATION OF DAMAGE IS 28.5Ï¿½ FROM T/E, 10.5Ï¿½ FROM INBD EDGE. DAMAGE SIZE IS 2.4Ï¿½ IN WIDTH, 15.2Ï¿½ IN LENGTH. DAMAGE FOUND TO BE WITHIN REPAIRABLE LIMITS IAW A320-200 SRM 53-02-00-283-001. AREA WAS REPAIRED BY REMOVING DAMAGE AND APPLYING A REPAIR PATCH USING FLAKEMETER T8070R CAL DUE 16/JUL/22 IAW A320-200 SRM 53-02-00-300-013 SOLUTION A. REV. 139 FH39265, FC14004 S/N 3670, WV012

Part: BEAM — CORRODED · corrosion level 2 · airframe 39,265 hrs · 14,004 cycles

R1 DOOR LOWER THRESHOLD BEAM HAS CORROSION AT GIRT BAR FITTING STUDS, FR16 (MARKED). DOT:T543 GROUNDED - YES. REMOVED AND REPLACED R1 DOOR LOWER SILL IAW ALASKA EA # A320-53EA-01286 AND AIRBUS A320 SRM 51-42-11. DOT REMOVED TOOLING T8492U

Part: NONE — CORRODED · corrosion level 2 · airframe 39,265 hrs · 14,004 cycles

MAIN CABIN AFT FLOOR BEAM CORRODED -Y464.8 DOT:W471 GROUNDED - YES. BLENDED AREA FOUND OUT OF LIMITS, LENGTH 1Ï¿½ WIDTH 1Ï¿½ DEPTH .030Ï¿½ PER AIRBUS A320 SRM 53-41-14.REMOVED AND INSTALLED NEW FLOOR BEAM IN -Y464.8 PART#D53472195 IAW AIRUS A320 SRM 51-42-11 AND AIRBUS A320 DEG # D53472040 REV A. REMOVED DOT

Part: DOOR SILL — CORRODED · airframe 39,265 hrs · 14,004 cycles

MAIN CABIN AFT SIDE FLOOR STRUCTURE + Y1292 FR 69 HAS CORROSION. DOT:W467 GROUNDED - YES. BLENDED AREA ORIGINAL THICKNESS .071Ï¿½ LOSS .053Ï¿½ REMAINING .018Ï¿½ FOUND TO BE OUT OF LIMITS IAW AIRBUS A320 SRM 53-41-14 TOOL# T8224P. CUTOUT DAMAGE, MATERIAL ID , FABRICATED. LOCATED, DRILLED AND DEBURRED IAW AIRBUS A320 SRM 53-41-14-300 REPAIR 8. HEAT TREAT 2EA ANGLE IAW AIRBUS A320 SRM 51-25-00. ALODINED IAW AIRBUS A320 SRM 51-21-11. PRIMED AND PAINTED IAW AIRBUS A320 AMM 51-23-00. MATERIAL 7075-T6 .071Ï¿½ AND 7075-0 .080Ï¿½ PO:1016024.1, PO:1002771.1 DOT REMOVED

Part: NONE — CORRODED · corrosion level 2 · airframe 39,265 hrs · 14,004 cycles

MAIN CABIN AFT FLOOR BEAM CORRODED -Y969 DOT:W466 GROUNDED - YES. REMOVED AND REPLACED MAIN CABIN FLOOR BEAM IAW AIRBUS A320 SRM 51-42-11 AND DWG # D53472040 REMOVED DOT

Part: NONE — CORRODED · corrosion level 2 · airframe 39,265 hrs · 14,004 cycles

MAIN CABIN AFT FLOOR BEAM CORRODED +Y160.5DOT:W465 GROUNDED - YES. REMOVED AND REPLACED AFT CABIN FLOOR BEAM IAW AIRBUS A320 SRM 51-42-11 AND DWG # D53472040REMOVED DOT

Part: PROFILE — CORRODED (FUSELAGE) · corrosion level 2 · airframe 37,178 hrs · 13,104 cycles

PROFILE AT FR63 RBL 23.75 HAS CORROSION GROUNDED - YES. REMOVED AND REPLACED PROFILE AT FR 63 TO FR 65 RBL 23.75 PART # D53470480009000, PO: 953700.1 PER REF SRM 53-41-14-08-A AND 51-42-11. NO INTERVAL INSPECTION REQUIRED.

Part: SKIN — DELAMINATED (RUDDER) · airframe 37,126 hrs · 13,092 cycles

RH RUDDER SHELL HOIST POINT #2 LOWER FORWARD POSITION BETWEEN BR 1 AND BR2 IS DISBONDED GROUNDED - YES. REPAIRED R/H RUDDER SHELL @ LOWER #2 HOIST POINT FORWARD POSITION BY BONDING LOWER SKIN, CYLINDRICAL BLOCK, INNER PLIES, CORE AND UPPER PLIES IAW A320 SRM 55-41-13-800-030 & 51-77-11-911-022 & 51-77-11-911-031. INSTALLED LOWER HOIST POINT BUSHING P/N R5547043720800 P.O. 925224.1 AND UPPER HOIST POINT BUSHING P/N R5547042900200 P.O. 95221.1 IAW A320 SRM 55-41-13-800-030. APPLIED FINISH IAW A320 SRM 51-75-12. PAINTED IAW A320 SRM 51-75-12

Part: SKIN — DENTED (FRAMES 18-19) · airframe 37,126 hrs · 13,092 cycles

RH FUSELAGE SKIN HAS A DENT AT FR19R AND STR30R  GROUNDED - YES. DENT FOUND TO BE OUT OF LIMITS PER A320 SRM 53-11-11; CUT OUT DAMAGED AREA PER A320 SRM 53-11-11-300-041; FABRICATED DOUBLER PER SRM 53-11-11-300-041; PERFORMED HFEC (NO CRACKS NOTED) PER NTM 51-10-01 AND 51-10-08; INSTALLED DOUBLER PER SRM 53-11-11-300-041.

Part: CONTACTOR — ODOR (AC BUSS) · airframe 22,909 hrs · 8,398 cycles

REPORTED ELECTRICAL BURNING ODOR AND ASSOCIATED ECAM AVIONICS SMOKE MESSAGES AT POWER TRANSFER FROM APU TO NR 1 ENGINE. THE ENGINE WAS SHUTDOWN AND THE ODOR DISIPATED. TECHS REPLACED AC ESS BUSS SWITCHING CONTACTOR 3XC AND GAPCU 24XG.

Part: PROXIMITY SWITCH — FAILED (PAX DOOR)

AIRCRAFT WAS READY TO OPERATE WHEN AT DEPARTURE, CREW NOTED DEFECT OF DOOR R2 OPEN INDICATION ON ECAM WHEN ALL DOORS CLOSED. ACFT DEFECT WAS CLEARED BY R & R R2 PAX CREW DOOR PROXIMITY SWITCH AT 17WV2 IAW AMM 52-71-11. OPS CHECK OK. NO FURTHER DEFECTS NOTED.

Part: OUTFLOW VALVE — FAILED (CABIN PRESSURE) · airframe 21,837 hrs · 8,077 cycles

ACFT RETURNED TO DEPARTURE. VENT SKIN VALVE FAULT ECAM IN FLIGHT AVIONICS SKIN AIR OUTLET VALVE WAS DISCOVERED IN THE OPEN POSITION BY MAINTENANCE AND PROCEEDED TO DEACTIVATE IAW MEL 21-26-04. VALVE WILL BE REPLACED AT NEXT MAINTENANCE OPPORTUNITY. ON 4/26/15 ACFT WAS OPERATING, WHEN RECEIVED SKIN VALVE FAULT ON TAKEOFF ROLL BUT WERE UNABLE TO CONTROL CABIN PRESSURE. ACFT RETURNED TO FIELD WITHOUT INCIDENT AND HAD THE FOLLOWING DEFECT IN LOGBOOK. VENT SKIN VALVE FAULT ON T/O ROLL, ECAM ACTIONS COMPLETED BUT UNABLE CONTROL OF CABIN PRESSURE. AT THE TIME, SKIN AIR OUTLET VALVE WAS ON MEL 21-26-04 APPLIED ON 4/23/15 AT 0454Z. MAINTENANCE ALSO FOUND THAT SKIN INLET VALVE WAS IN DEACTIVATED OPEN POSITION CAUSED BY ERROR BY MAINTENANCE. PRIOR TO NEXT FLIGHT THE FOLLOWING ACTIONS WERE TAKEN: LP 757436, ITEM NR 1 R & R SKIN AIR OUTLET VALVE IAW AMM 21-26-53 PB401. ACCOMPLISHED OPS OF VENT SYSTEM IAW AMM 21-26-00-710-001 ALL CHECKS GOOD NO FAULTS. MEL WAS CLEARED ON LP 757437. REPLACED SKIN AIR OUTLET VALVE. ALSO, ACCOMPLISHED SAFETY VALVE INSPECTION IAW TSM 21-31-00-810-808-A SAFETY VALVE. ALSO ADDRESSED OVERWEIGHT LANDING IAW AMM 05-21-11-200.

Part: BLADE — DAMAGED (NR 2 ENGINE) · airframe 21,535 hrs · 7,994 cycles

ENGINE 2 COMPRESSOR STALL ON DESCENT AND ACCOMPLISHED IFSD IAW QRH. CREW DECLARED AN EMERGENCY AND LANDED SAFELY. MAINTENANCE PERFORMED BOROSCOPE AND FOUND DAMAGED TO STAGE 3 AND 6 BLADES. ENGINE REMOVED AND REPLACED. THE ROOT CAUSE OF FAILURE IS NOT KNOWN AT THIS TIME BUT ONCE ENGINE GEST TO MFG, FINDINGS WILL BE AVAILABLE.

Part: ENGINE — FAILED (NR 1)

AIRCRAFT DEPARTED, REPORTED VIA ACARS THAT THEY HAD NR 1 ENGINE FAILURE WITH IFSD ON TAKEOFF AND WERE DECLARING AND EMERGENCY AND RTF, ACFT LANDED WITHOUT INCIDENT AND BLOCKED. ON ARRIVAL FOUND DAMAGE TO RADIAL DRIVE SHAFT ASSY WITH DAMAGE NOTED TO FAN FRAME AT 6 O`CLOCK POSITION.

Part: LINE — CHAFED (HYD SYSTEM) · airframe 13,524 hrs · 4,061 cycles

CREW RECEIVED AN ECAM GREEN SYS LOW QUANTITY. FLIGHT CREW FOLLOWED FCOM PROCEDURES AND DECISION WAS MADE TO DIVERT AND DECLARED AN EMERGENCY. ACFT LANDED WITHOUT INCIDENT AND TAXIED TO THE GATE UNDER POWER. MAINTENANCE TROUBLESHOT LEAK TO NR 1 ENGINE PYLON. FOUND HYDRAULIC LINE CHAFED AND LEAKING. HYDRAULIC LINE REPLACED IAW AMM 29-11-49-000-008-A AND AIRCRAFT WAS RETURNED TO SERVICE.

Part: UNKNOWN — UNKNOWN (DOOR ARMING)

WHILE PREPARING TO PUSH BACK, F/A ARMED R2 DOOR, THE OVERHEAD "ARMED" LIGHT WOULD NOT ILLUMINATE. MX INSPECTED AND ATTEMPTED TO ARM THE DOOR AND CONFIRMED THE FAULT . THE DOOR ARMING MECHANISM OPERATED NORMALLY IAW AMM 52-10-00-05. THE ACFT PUSHED BACK AT DEPARTED. NO FURTHER ISSUES WITH THIS DOOR HAVE BEEN NOTED.

Part: PLUG — LOOSE (OIL SYSTEM)

APPROX 2 HRS OUTSIDE, CREW REPORTED ENGINE NR 1, SN 697983, OIL QTY DECREASING IN CRUISE WITH STEADY OIL PRESSURE OF 40 PSI AND OIL TEMP 85 DEGREES. CREW MADE DECISION TO DIVERT, NR 1 ENGINE WAS NOT SHUTDOWN UNTIL ON THE GROUND AND NO EMERGENCY DECLARED AND ALL ENGINE PARAMETERS NORMAL WITH OIL QTY READING 1.5 QTS WITH ENGINE RUNNING. UPON ARRIVAL, MX INSPECTED NR 1 ENGINE AND FOUND OIL FILTER HOUSING DRAIN PLUG LOOSE AND SAFETY WIRED ON LUBRICATION. UNIT PN 337-075-105-0 REF AIPC 79-21-10-01A. MX VERIFIED OIL FILTER INSTALLED CORRECTLY AND REINSTALLED FILTER, HOUSING COVER AND PLUG IAW AMM 79-21-10. LEAK CHECKS PERFORMED WITH NO LEAKS NOTED, REF LP 503420 AND 503421. THE ACFT RETURNED TO SERVICE AFTER ABOUT 3 HR DELAY WITH CONTINUATION OF FLIGHT. NO HISTORY OF THIS DEFECT ON THIS ACFT.