N640VA

Part: FITTING — CRACKED (FRAME 42) · airframe 40,875 hrs · 15,104 cycles

CRACK INDICATION FOUND USING ULTRASONIC INSPECTION, LH ACTUATOR FITTING, AFT LUG, FORWARD FACE PER REJECTION CRITERIA OF NTM PROCEDURE. GROUNDED - YES. REMOVED AND REPLACED L/H ACTUATOR FITTING IAW ALASKA EA# A320-53EA-00138. THIS IS A CATEGORY "A" REPAIR. (LEFT MAIN LANDING GEAR DOOR ACTUATOR FITTING)

Part: THRESHOLD — CORRODED (FRAME 53) · corrosion level 2 · airframe 40,875 hrs · 15,104 cycles

AFT CARGO DOOR THRESHOLD PLATE AT FR.53 CORRODED O/B OF TORSION BOX GROUNDED - YES. REMOVED AND REPLACED AFT CARGO DOOR THRESHOLD PLATE IAW A320 SRM 51-72-11-911-001 AND AIRBUS DWG E53470500

Part: FLOOR SUPPORT — CORRODED (FRAMES 69-70) · corrosion level 2 · airframe 40,875 hrs · 15,104 cycles

MAIN CABIN FLOOR STRUCTURE, FR69 TO FR70, L/H FRAME SUPPORT IS CORRODED. GROUNDED - YES. FRAME SUPPORT HAS NO ALLOWABLE DAMAGE IN SRM. REMOVED AND REPLACED L/H FRAME SUPPORT IAW A320 SRM 51-42-11

Part: FLOOR SUPPORT — CORRODED (FRAMES 69-70) · corrosion level 2 · airframe 40,875 hrs · 15,104 cycles

MAIN CABIN FLOOR STRUCTURE, FR69 TO FR70, R/H FRAME SUPPORT IS CORRODED. GROUNDED - YES. REMOVED AND REPLACED R/H FRAME SUPPORT IAW A320 SRM 51-44-11 AND AIRBUS DRAWING D53474180. FRAME SUPPORT HAS NO ALLOWABLE DAMAGE IN SRM

Part: SHEAR PLATE — CORRODED (FRAMES 69-70) · corrosion level 2 · airframe 5,625 hrs · 1,537 cycles

R/H LATERAL SHEAR PLATE AT C69/70 CORRODED.  GROUNDED - YES. REMOVED AND REPLACED RH LATERAL SHEAR PLATE AT C69/70 IAW A320 SRM 51-42-11, 51-44-11, AND DWG D53474180

Part: FLOOR SUPPORT — CORRODED (FRAMES 67-68) · corrosion level 2 · airframe 40,875 hrs · 15,104 cycles

C67/68 R/H, FLOORBEAM CORRODED AT FASTENER HOLES NEAR SCUFF PLATE. GROUNDED - YES. REMOVAL OF DAMAGE NOT ACCOMPLISHED AFTER REAMING HOLES TO MAX ALLOWABLE SIZE PER A320 SRM 53-41-14. CONTINUED WITH REPAIR #3. CUT OUT DAMAGE PER A320 SRM 53-41-14. FABBED REPAIR FILLERS FROM 2024-T3 AND STRAPS FROM 70-75-16 (.080) PER A320 SRM 53-41-14. APPLIED PROTECTIVE TREATMENT TO FILLERS AND STRAPS PER A320 SRM 53-41-14, SRM 51-21-00, AND SRM 51-23-11. INITIALLY THE SILL SHAPE WAS REMOVED FOR F.O.M PER A320 SRM 53-41-14 AND SRM 51-42-11. INSTALLED SILL SHAPE AND REPAIR PARTS PER A320 SRM 53-41-14, AND SRM 51-42-11 AND DWF D53480505 ISSUE DG. SILL FASTENERS WERE FABBED USING A320 SRM 51-43-00 AND ANNEALED PER A320 SRM 51-25-00. CATEGORY "A" REPAIR. PO#980830.1,890961.1,849898.3

Part: SEAT TRACK — CORRODED (FRAMES 20-21) · corrosion level 2 · airframe 40,875 hrs · 15,104 cycles

MAIN CABIN FLOOR, FORWARD RIGHT SIDE, SEAT TRACK BEAM BETWEEN FLOOR PANELS #232EF & 232FF CORRODED (DOTS: F044, F045) FR 20 - FR 21, BS 8077 - BS 8197, RBL 51, BL -Y1290 GROUNDED - YES. REMOVED CORROSION FROM SEAT TRACK ORIGINAL THICKNESS .087, REMOVED .038, REMAINING .049 AND FOUND TO BE OUT OF LIMITS IAW A320 SRM 53-11-15-283-005 REMOVED AND REPLACED SEAT TRACK IAW A320 SRM 51-42-11.

Part: SHEAR PLATE — CORRODED (FRAMES 69-70) · corrosion level 2 · airframe 40,875 hrs · 15,104 cycles

L/H LATERAL SHEAR PLATE AT C69/70 CORRODED GROUNDED - YES. SHEAR PLATE HAS NO ALLOWABLE DAMAGE LIMITS GIVEN IN A320 SRM. REMOVED AND REPLACED SHEAR PLATE IAW A320 SRM 51-42-11.

Part: FLOOR SUPPORT — CORRODED (FRAMES 69-70) · corrosion level 2 · airframe 40,875 hrs · 15,104 cycles

MAIN CABIN FLOORBEAM, C69/70 Y160, UPPER SURFACE CORRODED GROUNDED - YES. CORROSION ON FLOOR BEAM FOUND TO HAVE 100% MATERIAL LOSS. REMOVED AND REPLACED FLOOR BEAM IAW A320 SRM 51-42-11.

Part: WEB — CORRODED (FRAME 56) · corrosion level 2 · airframe 40,875 hrs · 15,104 cycles

AFT CARGO TORSION BOX UPPER WEB AT FR. 56 HAS CORROSION. GROUNDED - YES. REMOVED AND REPLACED AFT CARGO TORSION BOX WEB IAW A320 SRM 51-42-11 AND AIRBUS DWG 17E53470321.

Part: PROXIMITY SWITCH — MALFUNCTIONED (DOOR SLIDES)

DOOR/OXY ECAM PAGE SHOWS LT AND RT AFT SLIDES DISARM, WHILE THE DOORS ARE ARMED. LINE MECHANIC TROUBLESHOT THE ISSUE AND ADJUSTED PROXIMITY SWITCH AFT LT, 7WN2, AND RT, 7WN2, DOOR IAW AMM 52-71-00-820-002-A01. OPS CHECKS WERE GOOD AND ISSUE RESOLVED. NO 11-15-13, SAME PROBLEM CAME BACK, DOOR/OXY ECAM PAGE SHOWS LT AND RT AFT SLIDES DISARMED. LINE MX FOUND FLEX CABLE ON BOTH LT AND RT ARM/DISARM MECHANISM OUT OF RIG. BOTH DOORS HAD THE CABLE ASSY RERIGGED. ADJ AND TEST COMPLIED WITH IAW AMM 52-12-00-501. ACFT OK FOR SERVICE.

Part: SILL — CORRODED (FUSELAGE)

R1 DOOR SILL BEAM HAS CORROSION NOTED IN FIVE AREAS. AREAS WERE REPAIRED IAW SRM 53-11-14, FIG 108.

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

LEFT SHEAR PLATE BETWEEN FRAMES 69-70, CORRODED BEYOND LIMITS. SHEAR PLATE WAS REPLACED IAW SRM 51-42-11.

Part: SUPPORT — CORRODED (FUSELAGE)

RIGHT SHEAR PLATE SUPPORT BETWEEN FR 69-70, ST69-70 RIGHT CORRODED BEYOND LIMITS. EXTENT OF DAMAGE 2"L X 2"W X .030 D. SHEAR PLATE SUPPORT WAS REPLACED IAW SRM 51-42-11.

Part: SILL — CORRODED (FUSELAGE)

LEFT AFT DOOR SILL BEAM HAS TWO AREAS OF CORROSION BETWEEN FRAMES 67-68, S23-24L, AT Y1726. AREAS WERE REPAIRED IAW SRM 53-41-14, FIG 201, VIEW K, PRINCIPLE 5.

Part: SUPPORT — CORRODED (FUSELAGE)

LEFT SHEAR PLATE SUPPORT BETWEEN FR69-70, -CORRODED BEYOND LIMITS. SHEAR PLATE SUPPORT WAS REPLACED IAW SRM 51-42-11.

Part: SILL — CORRODED (FUSELAGE)

RIGHT AFT DOOR SILL BEAM HAS TWO AREAS OF CORROSION BETWEEN FRAMES 67-68, S23-24R, AT Y1725. AREAS WERE REPAIRED IAW SRM 53-41-14, FIG 201, VIEW K, PRINCIPLE 5.

Part: SHEAR PLATE — CORRODED (FUSELAGE)

RT SHEAR PLATE BETWEEN FR 69-70, ST 69-70, RT CORRODED BEYOND LIMITS. EXTENT OF DAMAGE 2"L X 2"W X .030 D. SHEAR PLATE WAS REPLACED IAW SRM 51-42-11.

Part: CHECK VALVE — DEFECTIVE (BLEED AIR SYS)

THE CREW CALLED THE OCC VIA AIRCELL TO REPORT THAY HAD A NR 1 ENGINE BLEED FAULT AND A YELLOW HYDRAULIC ENGINE 2 PUMP FAULT, LOW PRESSURE AND RESERVOIR OVERHEAT MESSAGE. AFTER DISCUSSION WITH THE DISPATCHER, THE DECISION WAS MADE TO DECLARE AN EMERGENCY AND RETURN TO DEPARTURE, DUE TO THE YELLOW HYD SYS ISSUES. THE ACFT MADE AN UNEVENTFUL LANDING AT 2051Z, TAXIED OFF THE ACTIVE AND RECEIVED A TOW TO THE GATE. DURING TROUBLESHOOTING, MX FOUND THE NR 2 ENGINE EDP PROVIDED ZERO PRESSURE AND THE ELECTRIC PUMP WAS MAKING GRINDING NOISES AND TRIPPING THE CIRCUIT BREAKER. THE NR 1 PRESSURE REGULATING VALVE WAS ALSO FOUND AS THE CAUSE OF THE BLEED FAULT. ALL ABOVE COMPONENTS WERE REPLACED, ALONG WITH THE HP, LP AND CASE DRAIN FILTERS. TECH SUPPORT AND SIL 29-099, CHECK VALVE 3083GM WAS REPLACED, ALTHOUGH WITH PN ZCV63-6-1 INSTEAD OF THE PREFERRED -7, DUE TO PARTS AVAILABILITY. THIS CHECK VALVE WILL BE UPGRADED NEXT OPPORTUNITY ONCE PARTS ARE AVAILABLE. THE ACFT PASSED ALL LEAK AND OPS TESTS OF THE AFFECTED SYS AND WAS RETURNED TO SERVICE ON 4/3/2012.