N639VA

Part: SAFETY VALVE — FAILED (CABIN PRESSURE) · airframe 42,576 hrs · 16,323 cycles

A/C DID NOT PRESSURIZE, STOPPED CLIMB @ 4000 FEET GROUNDED - YES. PER TECH SERVICES, PERFORMED OPS TEST OF CPC 1+2 REF AMM 21-31-00. OPS CHECK GOOD.REF LP 1231475/3 PERFORMED PRESSURIZATION TEST OF FUSELAGE. OPS TEST GOOD. REF LP 1231479/3 R+R 7HL. OPS TEST NORM PER RMA 3206. ALL CHECKS GOOD. A/C OK FOR SERVICE.

Part: ANGLE — CORRODED (FUSELAGE) · airframe 41,294 hrs · 15,820 cycles

MAIN CABIN FLOOR STRUCTURE - CORROSION ON REPAIR ANGLE ATTACHED UNDERNEATH THE R/H OUTER FLOOR BEAM JUST FWD OF FRAME 68 - IB OF THE R-2 DOOR AFT GIRT BAR FITTING - MARKED IN RED GROUNDED - YES. REMOVED CORRODED REPAIR ANGLE IAW SRM 51-42-11. FABRICATED NEW REPAIR ANGLE AND 2 EA FILLERS IAW SRM 53-41-14. ALODINED AND PRIMED IAW SRM 51-21-11, APPLIED TOPCOAT IAW SRM 51-75-12. INSTALLED NEW REPAIR ANGLE AND 2 EA FILLERS IAW SRM 53-41-14. ORIGINAL THICKNESS .071", LENGTH 4", WIDTH 1.25", DEPTH .040" REMAINING THICKNESS .031

Part: ANGLE — CORRODED (FUSELAGE) · airframe 41,294 hrs · 15,820 cycles

MAIN CABIN FLOOR STRUCTURE - CORROSION ON REPAIR ANGLE ATTACHED UNDERNEATH THE RT OUTER FLOORBEAM JUST FWD OF FRAME 68 - IB OF THE R-2 DOOR AFT GIRT BAR FITTING - MARKED IN RED GROUNDED - YES. REMOVED CORRODED REPAIR ANGLE IAW SRM 51-42-11. FABRICATED NEW REPAIR ANGLE AND 2 EA FILLERS IAW SRM 53-41-14 ALODINED AND PRIMED IAW SRM 51-21-11, APPLIED TOPCOAT IAW SRM 51-75-12. INSTALLED NEW REPAIR ANGLE AND 2 EA FILLERS IAW SRM 53-41-14 REMOVED DOT. ORIGINAL THICKNESS .071" LENGTH 4", WIDTH 1.25", DEPTH .040" REMAINING THICKNESS .031.

Part: FLOOR SUPPORT — CORRODED (FRAMES 19-24) · corrosion level 2 · airframe 41,294 hrs · 15,820 cycles

FWD MAIN CABIN FLOOR SUPPORT STRUCTURE AT FR19 AND Y-1292 IS CORRODED GROUNDED - YES. REMOVED AND REPLACED SEAT TRACK P/N: D5311278220200 PO # 935585.2 IAW AIRBUS A320 SRM 51-42-11 AND AIRBUS A320 DWG D53910600. REMOVED AND REINSTALLED SUBSTRUCTURE IAW AIRBUS A320 51-42-11 AND AIRBUS A320 DWG D53910600. REMOVED CORROSION ON 010 SEAT TRACK AND FOUND TO BE OUT OF LIMITS PER A320 SRM 53-11-15 AND 53-70-00. ORIGINAL THICKNESS .087", LENGTH 4", WIDTH .75", REMAINING THICKNESS .035".

Part: SHEAR PLATE — CORRODED (FUSELAGE) · corrosion level 2 · airframe 41,294 hrs · 15,820 cycles

AFT MAIN CABIN LEFT SIDE FLOORBOARD SHEAR WEB/PLATE CORRODED BETWEEN FR69 AND FR70 LBL46. GROUNDED - YES. PART BEYOND DWG TOLERANCES REF DWG 18053471124 ORIG .071,100% MAT LOSS, DISCONNECTED 7102VC FOR FOM, REMOVED AFT MAIN CABIN WET AREA FLOORBOARD WEB SUPPORT PER SRM 51-42-11, LOCATED AND DRILLED P# 05347112420200 PER SRM 51-44-11, INSTALLED NEW WEB PER SRM 51-42-11, RECONNECTED 7102VC PER ESPM 20-44-17, PASSED OPS TEST PER CMM 34-55-00-710-001-A REMOVED DOT PO 917042.1.

Part: DOOR SILL — CORRODED (FUSELAGE) · airframe 41,294 hrs · 15,820 cycles

AFT MAIN CABIN SILL BEAM BETWEEN FR67 AND FR68 AT Y1292 HAS CORROSION AT NUT PLATE. GROUNDED - YES. BLENDED CORROSION, FOUND TO BE OUT OF LIMITS IAW SRM 51-74 FABRICATED REPAIR ANGLE AND 2 EA FILLERS IAW SRM 53-41-14. ALODINED AND PRIMED IAW SRM 51-21-11 APPLIED TOPCOAT IAW SRM 51-75-12 AND INSTALLED IAW SRM 51-42-11 ORIGINAL THICKNESS .138", LENGTH 1.0", WIDTH .075", DEPTH .072, REMAINING THICKNESS .066".

Part: SHEAR WEB — CORRODED (FRAMES 69-70) · airframe 41,294 hrs · 15,820 cycles

AFT MAIN CABIN RIGHT SIDE FLOORBOARD SHEAR WEB/PLATE CORRODED BETWEEN FR69 AND FR70 RBL46. GROUNDED - YES. REMOVED CORROSION, FOUND TO BE OUT OF LIMITS IAW A320 SRM 51-74. REMOVED AND REPLACED WEB PLATE IAW A320 SRM 51-42-11 AND AIRBUS DWG D53474180. REMOVED AND REINSTALLED WIREING IAW A320 ESPM 20-33-11 AND AWM 38-31-06 AND AMM 38-31-36 REMOVED DOT ORIGINAL THICKNESS .071", LENGTH 6", WIDTH 3", DEPTH .043", REMAINING THICKNESS .028"

Part: TARGET — OUT OF ADJUST (R2 DOOR)

AFT R2 SHOWING UNARMED DURING CRUISE. ADJUSTED THE TARGET FOR THE PROXIMITY SWITCH 7WN2 ON THE R2 DOOR IAW AMM 52-71-00-820-002-A01. OPS CHECKED GOOD. PRESSURIZED CABIN IAW AMM 05-53-00-780-002-A01. R2 SLIDE INDICATION STILL STAYS ARMED, OPS CHECKED GOOD.

Part: CONTACTOR — FAILED (LT OVRWNG SLIDE)

EXPERIENCED A LEFT OVERWING EXIT SLIDE NOT ARMED MESSAGE IN FLIGHT. ON LANDING, MX FOUND THE LT FWD OVERWING EXIT DOOR EMERGENCY SLIDE ARMING PIN IN THE DISARM POSITION. MX ARMED THE OVERWING SLIDE IAW AMM 52-21-11, NO FAULTS SINCE THEN. REPLACED THE LT FWD OVERWING EXIT DOOR SEAL ON THE PREVIOUS FLIGHT.

Part: CONNECTOR — INOPERATIVE (EMERGENCY LIGHTS)

A NUMBER OF THE CABIN EMERGENCY LIGHTS WERE ON INTERMITTENTLY DURING FLIGHT WITH THE EMERGENCY LIGHT CONTROL SWITCH IN THE ARMED POSITION. ON ARRIVAL, THE ACFT WAS REMOVED FROM SERVICE FOR TROUBLESHOOTING. TECHNICIANS FOUND AN OPEN WIRE, 3351-3069 BETWEEN CONNECTOR 7600VC PIN 32 AND CONNECTOR 7532VC PIN A IAW AWM 33-51-04, CONNECTOR 7532VC WAS REPLACED IAW ESPM, EMERGENCY LIGHTS OPS CHECKED NORMALLY IAW AMM 335100.

Part: CONTACTOR — FAULTY (DC BUSS)

FLIGHT EXPERIENCED, ELECTRICAL DC ESS BUSS SHED ECAM MESSAGE ON TAKEOFF ROLL WHICH RESULTED IN THE CREW INITIATING A HIGH SPEED ABORT, 100-120 KNOTS AND RETURNED TO GATE. TECHS ACCOMPLISHED TROUBLESHOOTING IAW TSM 24-60-810-810A, CONTACTOR 8PH DC SHED ESS BUS WAS FOUND FAULTY. R & R 8PH CONTACTOR IAW AMM 24-62-55-000-001. NOT FURTHER ISSUES REPORTED ON SUBSEQUENT FLIGHTS.

Part: FITTING — OUT OF ADJUST (GIRT BAR) · airframe 24,741 hrs · 11,840 cycles

REPORTED R2 DOOR HANDLE COMING OUT SLIGHTLY IN FLIGHT. R2 DOOR DISARMED DURING FLIGHT. ADJUSTED GIRT BAR FWD FITTING IAW AMM 52-13-820-001-A. OPS CHECK GOOD.

Part: BLOWER — FAILED (VENT)

AIRCRAFT EXPERIENCED A BLOWER VENT FAULT MESSAGE ON ECAM AND ELECTRICAL BURNING ODOR DURING CLIMB OUT, THE FLIGHT CREW DIVERTED. UPON ARRIVAL THE ACFT WAS TAKEN OUT OF SERVICE AND TECH BEGAN TROUBLESHOOTING IAW TSM 24-00-00-810-823-A 21-26-00-810-809-A. TEH BLOWER FAN 20HQ WAS FOUND FAILED ADN WAS REPLACED IAW AMM 21-26-51-04, NO FURTHER PROBLEMS REPAORTED ON SUBSEQUENT FLIGHTS.

Part: OIL SYSTEM — LEAKING (APU)

AFTER ENGINE SHUTDOWN AT GATE, WITH THE APU PROVIDING PNEUMATIC POWER FOR AIR CONDITIONING, CABIN BEGAN TO FILL WITH SMOKE AND STRONG BURNING OIL ODOR. FLIGHT CREW SHUTDOWN APU, SMOKE AND ODOR PROMPTLY DISSIPATED. DISCOVERED AN EXTERNAL OIL LEAK FROM APU AROUND THE GENERATOR DRIVE PAD AREA. APU REPLACED AND DUE TO RESIDUAL OIL ODOR IN CABIN, BOTH RECIRCULATION FAN FILTERS WERE REPLACED. NO ADDITIONAL REPORTS OF SMOKE NOTED ON SUBSEQUENT FLIGHTS.

Part: BEAM — CORRODED (FUSELAGE)

RIGHT AFT DOOR SILL BEAM HAS 2 AREAS OF CORROSION BETWEEN FR 67-68, ST 23-24 AT RBL56. THE EXTENT OF DAMAGE IS 1" LENGTH, 1.5" WIDTH, AND .060"DEPTH. THE SECOND AREA IS 1" LENGTH, 1.5" WIDTH, AND .060" DEPTH. SRM REPAIR 53-41-14, FIG 201 PRINCIPLE 5 WAS ACCOMPLISHED.

Part: ENGINE — MAKING METAL (NR 2)

ENGINE INSTALLED IN NR 2 POSITION, WAS RECOMMENDED TO BE REMOVED IMMEDIATELY DUE TO FINDINGS FROM A PLANNED OIL FILTER SAMPLE. THE LAB REPORT, REPORTED HIGH IRON, NICKEL AND SILVER FLAKES AND SPHERES. REMOVAL FOR INVESTIGATION OF NR 3B BEARING DETERIORATION. THE ACFT WAS IN FOR RON MX WHEN THE FINDING WAS RECEIVED AND WAS IMMEDIATELY TAKEN OUT OF SERVICE. THE ENGINE REPLACEMENT IS IN PROGRESS AS OF 3/25/2012. THIS ENGINE HAS BEEN INSTALLED ON NR 2 POSITION SINCE 5/5/2011.

Part: RELAY — MALFUNCTIONED (CABIN) · airframe 16,107 hrs · 8,086 cycles

DURING TAXI, THE CREW CALLED MX CONTROL REPORTING THAT WITH THE EMERGENCY EXIT LIGHT SWITCH IN THE "ARMED" POSITION. THE CABIN EMERGENCY EXIT LIGHTS CAME ON. MX ADVISED THE ACFT TO RETURN TO THE GATE AFTER A RESET OF THE SWITCH WAS UNSUCCESSFUL. MX MET THE ACFT UPON RETURN AND PERFORMED A SUCCESSFUL TEST OF THE EMERGENCY EXIT LIGHT SYSTEM WITH THE LIGHTS REACTING CORRECTLY TO SWITCH POSITION. THE ACFT DEPARTED AND HAD NO RE-OCCURRENCE THE REMAINDER OF THE FLYING DAY. MX CREATED REQUEST FOR MAINTENANCE ACTIONS 67 AND 86 TO REPLACE THE SWITCH FIN 4WL AND POWER SUPPLY CONTROL RELAY FIN 8WL 11/7/2011, DURING THE RON. THIS WAS ACCOMPLISHED WITH A SUCCESSFUL OPS TEST.