N641VA

Part: STRINGER — CORRODED (FRAMES 50-52) · corrosion level 2 · airframe 33,363 hrs · 10,331 cycles

CORROSION AT, AFT PIT, R/H FRAME C51, STRINGER 38 GROUNDED - YES. REMOVED CORROSION AND CHECKED LIMITS. ORIGINAL THICKNESS IS .095, REMAINING IS .083, .012 WAS REMOVED. FOUND TO BE OUT OF LIMITS REF A320 SRM 51-73-11 AND AIRBUS DWG E53470525 ISSUE K. REPAIRED STRINGER 38R REF ASA EA A320-53EA-00361 REV "00" AND A320 SRM 53-00-13-300-001. THIS IS A CATEGORY "A" REPAIR

Part: SEAT TRACK — CORRODED (FRAME 16) · corrosion level 2 · airframe 39,029 hrs · 13,538 cycles

MAIN CABIN FLOOR STRUCTURE AT C16, Y254, UPPER SURFACE OF TRACK FLANGE HAS CORROSION  GROUNDED - YES. REMOVED CORROSION AND CHECKED LIMITS. ORIGINAL THICKNESS IS .063, REMAINING IS .019, .044 WAS REMOVED. FOUND TO BE OUT OF LIMITS REF A320 SRM 53-11-14-283-004. REPAIRED TRACK REF A320 SRM 53-11-14-300-003 (REF RRFTS #11 P5 DISPOSITION). CAT "A" MAJOR REPAIR TRACKING EA A320-53EA-00343 REV "OO"

Part: STRINGER — CORRODED (FUSELAGE) · corrosion level 2 · airframe 39,029 hrs · 13,538 cycles

CORROSION AT, AFT PIT, R/H FRAME C51, STRINGER 38 LATE FIND GROUNDED - YES. REMOVED CORROSION AND CHECKED THE LIMITS. ORIGINAL THICKNESS IS .095, REMAINING IS .083, .012 WAS REMOVED. FOUND TO BE OUT OF LIMITS REF A320 SRM 51-73-11 AND AIRBUS DWG E53470525 ISSUE K. REPAIRED STRINGER 38R REF ASA EA A320-53EA-00361 REV"00" AND A320 SRM 53-00-13-300-001. THIS IS A CATEGORY "A" REPAIR.

Part: SUPPORT — CORRODED (FRAMES 69-70) · corrosion level 2 · airframe 13,538 hrs · 13,538 cycles

AFT MAIN CABIN, R/H SIDE, O/B FLOOR WEB SUPPORT ANGLE BETWEEN FR69-70 IS CORRODED  GROUNDED - YES. REMOVED AND REPLACED WEB SUPPORT D5347112320300 REF AIRBUS DWG D53474180

Part: STRINGER — CORRODED (FRAMES 56-57) · corrosion level 2 · airframe 39,030 hrs · 13,538 cycles

AFT CARGO, STR.43 L/H HAS AREA OF CORROSION FROM FR. 56 TO FR.57 GROUNDED - YES. REMOVED CORROSION AND CHECKED THE LIMITS. ORIGINAL THICKNESS IS .110, .078 WAS REMOVED, REMAINING THICKNESS IS .032 FOUND TO BE OUT OF LIMITS REF A320 SRM 51-73-11. REPAIRED STR 43L REF ASA EA A320-53EA-00344 REV "00"

Part: SEAT TRACK — CORRODED (FRAMES 12-24) · corrosion level 2 · airframe 39,029 hrs · 13,538 cycles

MAIN CABIN FLOOR WEB HAS NUMEROUS SPOTS OF SURFACE CORROSION BETWEEN STA C16 AND STA C20 LBL1651MM. GROUNDED - YES. REMOVED AND REPLACED MAIN CABIN SEAT TRACK REF A320 SRM 51-72-11 AND AIRBUS DWG D53112812 ISSUE "E" PO# 965684.1

Part: FLOOR SUPPORT — CORRODED (FRAME 68-70) · corrosion level 2 · airframe 13,538 hrs · 13,538 cycles

AFT MAIN CABIN, FLOOR BEAM APPROX. LBL 6.5" IS CORRODED IN SEVERALSPOTS FROM FR68-70. MARKED.  GROUNDED - YES. REMOVED CORRODED BEAM IAW A320 SRM 51-42-11. DRILLED TO FIT AND INSTALLEDBEAM IAW A320 SRM 51-72-11-911-001 AND AIRBUS DWG 18D5372780

Part: FLOOR SUPPORT — CORRODED (FRAMES 67-68) · corrosion level 2 · airframe 39,030 hrs · 13,538 cycles

AFT MAIN CABIN, L/H FLOOR BEAM APPRX. LBL 30.5 Ï¿½IS CORRODED IN A FEW  AREAS FROM FR67-68. MARKED.  GROUNDED - YES. REMOVED CORRODED BEAM IAW A320 SRM 51-42-11. DRILLED TO FIT AND INSTALLED BEAM IAW A320 SRM 51-772-11-911-001 AND AIRBUS DWG 18D53471780

Part: WEB — CORRODED (FRAMES 69-70) · corrosion level 2 · airframe 33,363 hrs · 10,331 cycles

AFT MAIN CABIN, L/H SIDE O/B FLOOR WEB BETWEEN FR69-70 IS CORRODED.MARKED.  GROUNDED - YES. REMOVED AND REPLACED FLOOR WEB REF AIRBUS DWG D53474180 AND A320 SRM 51-42-11. NO ALLOWABLE LIMITS

Part: FLOORBEAM — CORRODED (FRAME 20) · corrosion level 2 · airframe 39,029 hrs · 13,538 cycles

MAIN CABIN FLOOR BEAM HAS SURFACE CORROSION AT STA C20 RBL240MM. GROUNDED - YES. REMOVED AND REPLACED MAIN CABIN FLOOR SUPPORT RAIL REF A320 SRM 51-72-11 AND AIRBUS DWG D53111406 ISSUE "B" PO# 964396.1

Part: WEB — CORRODED (FRAMES 69-70) · corrosion level 2 · airframe 39,029 hrs · 13,538 cycles

AFT MAIN CABIN, L/H SIDE O/B WEB SUPPORT BETWEEN FR69-70 IS CORRODED. MARKED. (LOOK FROM BELOW)  GROUNDED - YES. REMOVED AND REPLACED FRAME SUPPORT WEB REF REF AIRBUS DWG D53474180 AND A320 SRM 51-42-11.

Part: FLOOR SUPPORT — CORRODED (FRAME 66) · corrosion level 2 · airframe 39,029 hrs · 13,538 cycles

AFT MAIN CABIN, R/H SIDE FLOOR BEAM FWD OF R2 DOOR CUTOUT, MOST O/B FLOOR BEAM HAS CORROSION MARKED.  GROUNDED - YES. REMOVED CORROSION AND CHECKED LIMITS. ORIGINAL THICKNESS IS .150, REMAINING IS .106, .044 REMOVED. FOUND TO BE OUT OF LIMITS REF A320 SRM 53-41-14. ACCOMPLISHED REPAIR REF A320 SRM 53-41-14-300-001. MAJOR REPAIR TRACKING EA, ASA EA A320-53EA-00327 REV "00" DATED 02/06/2020

Part: WEB — CORRODED (FRAMES 69-70) · corrosion level 2 · airframe 33,363 hrs · 10,331 cycles

AFT MAIN CABIN, R/H SIDE, O/B FLOOR WEB BETWEEN FR 69-70 IS CORRODED  MARKED.  GROUNDED - YES. REMOVED AND REPLACED AFT MAIM CABIN R/H SIDE O/B FLOOR WEB BETWEEN 69-70IAW AIRBUS A320 SRM 51-42-11 AND DWG 18D53474180 NO ALLOWABLE LIMITS

Part: SEAT TRACK — CORRODED (FRAMES 12-24) · corrosion level 2 · airframe 39,029 hrs · 13,538 cycles

MAIN CABIN FLOOR BEAM HAS SURFACE CORROSION AT STA C20 RBL290MM. GROUNDED - YES. REMOVED AND REPLACED MAIN CABIN TRACK REF A320 SRM 51-72-11 AND AIRBUS DWG D53111460 ISSUE "C" PO# 964449.3

Part: FLOOR PANEL — CORRODED (CABIN) · corrosion level 2 · airframe 33,363 hrs · 10,331 cycles

PARTS RACK- AFT WET AREA FLOOR PANEL 262LG IS CORRODED  GROUNDED - YES. RECEIVED NEW FLOOR PANEL PO # 965072.3 FLOOR PANEL INSTALLED ON CARD G1326592 NO ALLOWABLE LIMITS

Part: SEAT TRACK — CORRODED (FRAMES 12-24) · corrosion level 2 · airframe 39,029 hrs · 13,538 cycles

MAIN CABIN FLOOR BEAM HAS SURFACE CORROSION AT STA C16 RBL1346MM. GROUNDED - YES. REMOVED AND REPLACED SEAT TRACK REF A320 SRM 51-72-11 AND AIRBUS DWG D53112812

Part: FLOOR SUPPORT — CORRODED (FRAMES 67-68) · corrosion level 2 · airframe 39,030 hrs · 13,538 cycles

AFT MAIN CABIN, R/H SIDE, FLOOR BEAM AT APPROX. RBL30.5" AT FR68 IS CORRODED.  GROUNDED - YES. REMOVED CORRODED BEAM IAW A320 SRM 51-42-11. DRILLED TO FIT AND INSTALLEDBEAM IAW A320 SRM 51-72-11-911-001 AND AIRBUS DWG 18D53472780

Part: SEAT TRACK — CORRODED (FRAMES 16-24) · corrosion level 2 · airframe 39,029 hrs · 13,538 cycles

MAIN CABIN FLOOR BEAM HAS SURFACE CORROSION AT STA C16 RBL813MM GROUNDED - YES. REMOVED AND REPLACED MAIN CABIN SEAT TRACK D5311278220201 REF A320 SRM 51-72-11 AND AIRBUS DWG D53112812 ISSUE "E"

Part: FLOOR PANEL — CORRODED (CABIN) · corrosion level 2 · airframe 33,363 hrs · 10,331 cycles

PARTS RACK- AFT WET AREA FLOOR PANEL 261LG IS CORRODED GROUNDED - YES. RECEIVED NEW FLOOR PANEL PO # 965072.2. FLOOR PANEL INSTALLED ON TASK CARD  G1326592 NO ALLOWABLE LIMITS

Part: WEB — CRACKED (FRAME 68) · corrosion level 2 · airframe 39,029 hrs · 13,538 cycles

AFT MAIN CABIN, L/H SIDE APPROX. 12" AFT OF FR 68 O/B FLOOR WEB/SUPPORT IS CRACKED AND CORRODED. GROUNDED - YES. REMOVED DAMAGED FLOOR WEB AND INSTALLED NEW WEB IAW AIRBUS A320 SRM 51-42-11 AND AIRBUS DRAWING 18D53480505

Part: STRINGER — CORRODED (FRAMES 54-64) · corrosion level 2 · airframe 39,030 hrs · 13,538 cycles

AFT CARGO, STR. 35 L/H HAS CORROSION IN MULTIPLE AREAS FROM FR.54 TO FR.64 GROUNDED - YES. REMOVED DAMAGE ORIG. THICKNESS .110, REMAINING THICKNESS .080, REMOVED .030 AND IN TRANSITION AREA ORIG. THICKNESS .071, REMAINING THICKNESS .041, REMOVED .030 AND FOUND TO BE OUT OF LIMITS PER A320 SRM 51-73-11, REPAIRED DAMAGE ON STR 35 L/H FROM FR.54 TO FR.64 PER ASA EA A320-53EA-00315 REV.00, THIS IS AN CATEGORY B MAJOR REPAIR WITH IN INITIAL INSPECTION THRESHOLD OF 36 MONTHS DUE ON 25-FEB-2023 AS PER AIRBUS RDAS 80741404/009/2020 ISSUE A DATED 25/FEB/2020

Part: STRINGER — CORRODED (FRAMES 53-62) · corrosion level 2 · airframe 39,030 hrs · 13,538 cycles

AFT CARGO, STR 36 L/H HAS CORROSION IN MULTIPLE AREAS FROM FR.53 TO FR.62 GROUNDED - YES. REMOVED CORROSION ON STR 36LH FROM FR.53 TO FR.62 ORIG. THICKNESS .110 REMAINING .082, REMOVED .028 AND ORIG. THICKNESS .071 IN TRANSITION AREA, REMAINING .044, REMOVED .027 AND FOUND TO BE OUT OF LIMITS PER A320 SRM 51-73-11 REPAIRED STR 36 L/H FROM FR.53 TO FR.62 PER ASA EA A320-53EA-00297 REV.00 THIS IS A CATEGORY B MAJOR REPAIR WITH AN INITIAL INSPECTION THRESHOLD OF 36 MONTHS DUE ON 25-FEB-2023 AS PER AIRBUS RDAS 80741404/009/2020 ISSUE A DATED 25/FEB/2020

Part: STRINGER — CORRODED (FRAMES 57-64) · corrosion level 2 · airframe 39,030 hrs · 13,538 cycles

AFT CARGO, STR.33 L/H HAS CORROSION IN MULTIPLE AREAS FROM FR.57 TO FR.64 GROUNDED - YES. REMOVED CORROSION ON STR 33LH FROMFR.57 TO FR.64 ORIG. THICKNESS .071, REMAINING .043, REMOVED .028 AND FOUND TO BE OUT OF LIMITS PER A320 SRM 51-73-11, REPAIRED STR 33 L/H FRP, FR 57 TP FR.64 PER ASA EA: A320-53EA-00314 REV.00, THIS IS A CATEGORY B MAJOR REPAIR WITH AN INITIAL INSPECTION THRESHOLD OF 36 MONTHS DUE ON 25-FEB-2023 AS PER AIRBUS RDAS 80741404/009/2020 ISSUE A DATED 25/FEB/2020.

Part: STRINGER — CORRODED (FRAMES 56-61) · corrosion level 2 · airframe 39,030 hrs · 13,538 cycles

AFT CARGO, STR. 38 L/H HAS CORROSION IN MULTIPLE AREAS FROM FR.56 TO FR61. GROUNDED - YES. REMOVED CORROSION ON STR 38 L/H FROM FR.56 TO FR.61 ORIG THICKNESS .110 REMAINING .034, REMOVED .076 AND FOUND TO BE OUT OF LIMITS PER A320 SRM 51-73-11, REPAIRED STR 38 L/H FROM FR.56 TO FR61 PER ASA EA A320-53EA-00299 REV.00, THIS IS A CATEGORY B MAJOR REPAIR WITH AN INITIAL INSPECTION THRESHOLD OF 36 MONTHS DUE ON 25-FEB-2023 AS PER AIRBUS RDAS 80741404/009/2020 ISSUE A DATED 25/FEB/2020

Part: STRINGER — CORRODED (FRAMES 55-64) · corrosion level 2 · airframe 39,030 hrs · 13,538 cycles

AFT CARGO, STR 37 L/H HAS CORROSION IN MULTIPLE AREAS FROM FR.55 TO FR.64 GROUNDED - YES. REMOVED CORROSION ON STR 37 L/H FROM FR.55 TO FR.64 ORIG. THICKNESS .110 REMAINING .050, REMOVED .060 AND FOUND TO BE OUT OF LIMITS.PER A320 SRM 51-73-11, REPAIRED STR 37 L/H FROM FR55 TO FR64 PER ASA EA A320-53RA-00298 REV.00 THIS IS A CATEGORY B MAJOR REPAIR WITH AN INITIAL INSPECTION THRESHOLD OF 36 MONTHS DUE ON 25-FEB-2023 AS PER AIRBUS RDAS 80741404/009/2020 ISSUE A DATED 25/FEB/2020

Part: STRINGER — CORRODED (FRAMES 53-64) · corrosion level 2 · airframe 39,030 hrs · 13,538 cycles

AFT CARCO, STR.34 L/H HAS CORROSION IN MULTIPLE AREAS FROM FR. 53 TO FR.64 GROUNDED - YES. REMOVED CORROSION ON STR 34LH FROM FR.53 TO FR. 64 ORIG. THICKNESS .110, REMAINING THICKNESS .088, REMOVED .022 AND TRANSITION AREA ORIG. THICKNESS .071, REMAINING .048 REMOVED .023 AND FOUND TO BE OUT OF LIMITS PER A320 SRM 51-73-11, REPAIRED STR 34 LH FROM FR.53 TO FR.64 PER ASA EA: A320-53EA-00296 REV.00, THIS IS A CATEGORY B MAJOR REPAIR WITH AN INITIQAL INSPECTION THRESHOLD OF 36 MONTHS DUE ON 25-FEB-2023 AS PER AIRBUS RDAS 80741404/009/2020 ISSUE A DATED 25/FEB/2020.

Part: WEB — CORRODED (FUSELAGE) · corrosion level 2 · airframe 39,029 hrs · 13,538 cycles

AFT CARGO COMPARTMENT, DOOR BOX UPPER WEB CORRODED @ APPROX -41 FR C55 - FR C56, RBL -Y41 GROUNDED - YES. REMOVED CORRODED UPPER DOOR BOX WEB, LOCATED AND DRILLED NEW WEB P/N D5347556522200 PO# 963724.1 AND INSTALLED NEW WEB PER AIRBUS DWG E53470321 ISSUE AV SH 69,70 71 WEB WAS REMOVED AND REPLACED DUE TO NO ALLOWABLE DAMAGE LIMITS IN THE SRM

Part: SKIN PANEL — GOUGED (LE SLAT) · airframe 39,029 hrs · 13,538 cycles

LEFT WING INBOARD LEADING EDGE AT SLAT #1 ON THE INBOARD SIDE OF THE FIXED LEADING EDGE IS GOUGED WITH BARE METAL. "MARKED IN RED" GROUNDED - YES. REMOVED AND REPLACED L/H I/B FIXED L/E SKIN PANEL P/N D5745004820639 REF AIRBUS DWG D57450033 AND A320 SRM 51-42-11

Part: ACM — SEIZED (AC BAY) · airframe 35,613 hrs · 12,182 cycles

STRONG BURNING SMELL IN CABIN WITH SMOKE. GROUNDED - YES. R/R AIR CYCLE MACHINE IAW AMM 21-52-00, OPS CHECK/ LEAK CHECK GOOD. THIS CLEARS MDDR 61722, PLACARD REMOVED, MEL LIST UPDATED, MCC NOTIFIED.

Part: ACTUATOR — FAILED (BALL SCREW) · airframe 27,605 hrs · 8,989 cycles

ACFT EXPERIENCED A NR 1 ENGINE COMPRESSOR VANE FAULT ON ECAM, THE FLIGHT CREW ELECTED TO RETURN TO DEPARTURE. UPON ARRIVAL TECHS ACCOMPLISHED TSM 75-30-00-810-801-A. THE VBV BALL SCREW ACTURATOR WAS FOUND FAULTY AND REPLACED IAW AMM 75-31-50, THE ASSOCIATED FLEXIBLE DRIVE SHAFTS WERE ALSO REPLACED. ENGINE MOTORING TEST AMM TASK 73-29-00-710-040 AND ENGINE IDLE RUN ACCOMPLISHED WITH NO FAULTS FOUND. THE ACFT WAS RETURNED TO SERVICE, NO FAULTS REPAORTED ON SUBSEQUENT FLIGHT.

Part: SENSOR — MALFUNCTIONED (NR 1 COMPRESSOR) · airframe 23,359 hrs · 8,384 cycles

AIRCRAFT REPORTED ENGINE 1 COMPRESSOR VANE FAULT UPON DEPARTURE, ELECTED TO RETURN TO DEPARTURE. ACFT LANDED SAFELY AND WAS TAKEN OUT OF SERVICE. ENGINE 1 COMPRESSOR VANE, MASTER CAUTION SEVERAL TIMES IN CLIMB, STARTING AT 6000 FT IB CLIMB OUT. R & R VBV POSITION SENSOR, PERFORMED FADEC GROUND TEST WITH ENGINE MOTORING REF AMM 75-31-70, PB 401 AND ACCOMPLISHED HIGH POWER RUN, OPS TEST GOOD. ACFT WAS RETURNED TO SERVICE AT 1350Z ON 7/13/2015.

Part: GIRT BAR — OBSTRUCTED (R2 DOOR)

ACFT WAS GETTING READY FOR FLIGHT WHEN R2 DOOR WOULD NOT ARM. AFT RT CABIN DOOR NOT ARMING. CLEARED OBSTRUCTION FOUND UNDER R2 DOOR COMPLETED OPS CHECK, FOUND NO ISSUES AMM 52-13-12.

Part: FAN — FAILED

EXPERIENCED A VENT EXTRANT FAULT MESSAGE ON ECAM AND A SHORT DURATION ELECTRICAL BURNING ODOR. THE FLIGHT CREW FOLLOWED FCOM PROCEDURES AND CONTINUED, TSM 24-00-11-810-823A & 21-26-00-810-809A WERE ACCOMPLISHED, THE EXTRACT FAN 18HQ WAS FOUND FAILED AND PLACE ON MEL 21-26-02-03, NO FURTHER PROBLEMS REPORTED ON SUBSEQUENT FLIGHTS.

Part: BUSHING — MIGRATED (GUST LOCK)

ACFT EXPERIENCED A L1 DOOR GUST LOCK FAILURE. FAULT DETERMINED TO BE THE RESULT OF A MIGRATED BUSHING IN THE GUST LOCK MECHANISM. BUSHING REINSTALLED IAW AMM 52-11-00-05, NO FURTHER ISSUES WERE NOTED.

Part: BUTTON — OUT OF ALIGNMENT (L1 HOLD OPEN)

DURING GROUND SERVICING, CREW NOTED THAT THE L1 DOOR GUST LOCK MECHANISM WAS NOT ENGAGING. ON INSPECTION, NOTED THAT THE GUST LOCK RELEASE BUTTON HAD NO MECHANICAL TENSION. BUSHING THAT ALIGNS THE PLASTIC PLUNGER BUTTON WAS FOUND MIGRATED FROM ITS NORMAL POSITION. THE BUSHING WAS INSPECTED AND REPOSITIONED INTO ITS CORRECT ALIGNMENT. THE DOOR STAY LOCK MECHANISM OPERATED NORMALLY IAW AMM 52-11-12.