N622VA

Part: SUPPORT WEB — CORRODED (FUSELAGE) · corrosion level 2 · airframe 43,569 hrs · 13,669 cycles

AFT CABIN RT UNDER LAV LATERAL SHEAR PLATE, SUPPORT WEB CORRODED GROUNDED - YES. REMOVED AND REPLACED SUPPORT WEB IAW SRM 51-42-11 AND DWG D53474180. NOTE: NO ALLOWABLE LIMITS FOR DISCREPANT PART FORM 337 ATTACHED. NO SRI REQUIRED.

Part: SHEAR PLATE — CORRODED (FUSELAGE) · corrosion level 2 · airframe 43,569 hrs · 13,669 cycles

AFT CABIN RT LAV, LATERAL SHEAR PLATE HAS CORROSION ON THE WEB GROUNDED - YES. REMOVED AND REINSTALLED MOTOR STARTER RELAY IAW AMM 38-31-36 & ESPM 20-33-11, OPS CK GOOD. REMOVED AND REPLACED SHEAR PLATE IAW DWG # 18D53474180 & SRM 51-42-11. REMOVED AND REINSTALLED FLOOR PANEL 262KGIAW AMM 53-00-00. MYLARED FLOOR PANEL IAW AMM 25-28-43, PERFORMED OPS TEST OF TOILET IAW AMM 38-31-36 OPS CHECK GOOD. LAV TO BE INSTALLED ON CARD # 254300-03-3-VAM OPS 1258.NOTE: NO ALLOWABLE LIMITS FOR DISCREPANT PART. FORM 337 ATTACHED NO SRI REQUIRED

Part: SKIN — DENTED (FUSELAGE) · airframe 41,359 hrs · 12,797 cycles

LOWER LT SKIN IS DENTED AT FR61 TO FR62 S36L GROUNDED - YES. ACCOMPLISHED REPAIR TO 2 EA DENTED AREAS BETWEEN FR61 TO FR62 STR 35L TO 37L PER SRM 53-00-11-300-029/042/043.

Part: WIRE — DETACHED (EMERGENCY LIGHT) · airframe 40,772 hrs · 12,583 cycles

EMER ROW LIGHTS INOP AT ROWS 22 & 23. GROUNDED - YES. REATTACHED WIRES IN CONNECTOR PER AMM AWM 33-51-07 P 0249, SHT 2. OPS CHECK GOOD.

Part: BUSHING — WORN (R1 DOOR GUSTLOCK)

MX FOUND THE R1 DOOR GUST LOCK STICKING DUE TO WORN BUSHINGS. MX REPLACED THE BUSHINGS IAW AMM 52-11-12 AND TBN 52-10-01. OPS CHECKED GOOD.

Part: PROXIMITY SENSOR — FAILED (NLG)

AIRPLANE WAS RELEASED FROM HEAVY MAINTENANCE. THE ACFT THEN TOOKOFF, AFTER TAKEOFF, THE CREW ATTEMPTED TO RETRACT THE GEARS AND RECEIVED, DOORS UNLOCKED MESSAGE ON ECAM. THE NOSE GEAR DID NOT RETRACT. THE CREW ATTEMPTED A SECOND TIME TO RETRACT THE GEARS AND WAS SUCCESSFUL. THE CREW ALSO RECEIVED , ANTI-ICE STANDBY PITOT MSG AND INTERMITTENT DME 2 FAILURE. AFTER RETURNING TO DEPARTURE, THE CREW RECEIVED A LANDING GEAR SLYS DISAGREE MESSAGE WHILE TAXIING BACK TO HANGAR. THE DME FAIL WAS A TRUE FAULT AND REPLACED AS REQUIRED. T/S FOR THE GEAR DETERMINED THAT PROXIMITY SENSOR 25GA WAS THE ROOT CAUSE OF THE ISSUE. THIS SENSOR FAILURE TRIGGERED THE STANDBY PITOT FAULT MSG AS A PRECAUTIONARY MEASURE, LGCIU 2 WAS REPLACED. A NLG SWING WAS A ACCOMPLISHED AS A FUTHER TEST TO DUPLICATE THE FAULT. ALL TESTS PASSED.

Part: SLIDE — LOW PRESSURE (R2 DOOR)

R2 DOOR SLIDE PRESSURE GUAGE WAS FOUND IN THE RED BAND DURING PREFLIGHT CHECKS BY INFLIGHT TEAM. MAINTENANCE WAS SENT WITH SERVICEABLE SLIDE AND SLIDE WAS REPLACED IAW AMM 25-62-44 PB01 AND DOOR ASSIST BOTTLE SERVICED ACFT, TOOK A 176 MINUTE DELAY.

Part: HOSE — LEAKING (MLG DOOR) · airframe 27,282 hrs · 8,210 cycles

DURING APPROACH, REPORTED LOSS OF GREEN SYSTEM HYDRAULIC FLUID. MAINTENANCE DISCOVERED A MLG DOOR ACTUATOR HOSE ON THE LT SIDE LEAKING. R & R IAW AMM 32-31-39-401, NO LEAKS NOTED AFTERWARD, ALL OPS CHECKS NORMAL AND THE ACFT WAS PLACED BACK INTO SERVICE AT 1814Z AFTER A TOTAL DELAY OF 3:31.

Part: FAN — FAILED (RECIRCULATION)

PLASTIC BURNING ODOR DETECTED IN COCKPIT WITH AMBER FAN ANNUNCIATED ON THE COND PAGE. MX ACCOMPLISHED TSM 24-00-00810-823A FOR BURNING ODOR WITH NO DEFECTS FOUND. TROUBLESHOOTING REVEALED, RECIRCULATION FAN FIN 15HG TO BE FAULTED.

Part: SWITCH — DEFECTIVE (COCKPIT)

ACFT WAS ON A TURN, AFTER FLIGHT. DURING THE PREFLIGHT, THE FLIGHT CREW NOTED THAT THE EMERGENCY EXIT LIGHTS STAYED ILLUMINATED WITH THE SWITCH IN THE "ARMED" POSITION. MX WAS CALLED OUT AFTER SEVERAL RESET ATTEMPTS THROUGH MX CONTROL WERE UNSUCCESSFUL. MX FOUND THE TOGGLE SWITCH, FIN 4LR, PN E0062B0S4BA0A, AS THE DEFECTIVE PART. THE SWITCH WAS REPLACED IAW ESPM 20-45-21 AND THE SYS OPERATED NORMALLY IN ALL SWITCH POSITIONS. THE ACFT INCURRED AN 18 MINUTE DELAY ON OUTBOUND FLIGHT. ACCORDING TO THE OPERATOR`S RECORDS, ALL AD, SB STC AND PMA ARE IN FULL COMPLIANCE.

Part: PIN — UNSERVICEABLE (L2 DOOR) · airframe 16,752 hrs · 5,115 cycles

UPON ARRIVAL, A LOG ENTRY WAS MADE NOTING THAT THE L2 DOOR INDICATED DISARMED ON THE LOWER ECAM PAGE DURING CRUISE FLIGHT. THIS WAS AREPEAT ITEM BEING MONITORED AND COULD NOT BE DEFERRED DUE TO MEL DAYLIGHT ONLY FLYING RESTRICTIONS. THE ACFT WAS TAKEN OUT OF SERVICE AT 1720 PST/0020Z ON 12/2/2011. UPON OPEN UP AND INSPECTIO OF THE GUIDE TUBE ASSY, IT WAS NOTED THAT THE GIRT BAR APPEARED TO BE EXCESSIVELY TIGHT DURING ARMING, PULLING THE DOOR INWARD ALLOWING THE ARMING HANDLE TO HAVE A SMALL AMOUNT OF EXTRA MOVEMENT AWAY FROM THE PROX TARGET SENSOR. MX ALSO NOTED THAT THE AFT GUIDE PIN (ITEM300, IPC 52-11-22-04) WAS BENT, CAUSING THE ENGAGEMENT INTO THE GIRT BAR TO BE MISALIGNED, THUS CAUSING THE TIGHTNESS EXPERIENCED DURING GIRT ENGAGEMENT. THE DEFECTIVE ITEM WAS REPLACED ALONG WITH THE 3 BEARING ASSY`S ON THE GUIDE TUBE ON LOG PAGE 543332, ITEM 2. THE ITEM WAS OPERATIONALLY CHECKED AND CLEARED IN THE LOG GOOK. THE ACFT WAS RETURNED TO SERVICE ON 12/3/2011 AND HAS FLOWN FOR 2 DAYS WITH NO FURTHER L2 DOOR INDICATION ISSUES.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE)

REMOVED CORROSION AT CABIN FLOOR PANEL SUPPORT UPPER SURFACE BETWEEN FRAMES 68-70, RBL 6" IAW SRM 51-74-00. PERFORMED UT THICKNESS INSP OF REWORKED AREA, FOUND TO BE AT UPPER SURFACE 0.150 MAX, 0.90 MIN USED DAKOTA MX-3 SN 3B264 IAW A320 NDTM 51-10-04. R & R FLOOR SUPPORT BEAM IAW SRM 51-42-00-00.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE)

REMOVED CORROSION AT MAIN CABIN FLOOR SUPPORT UPPER SURFACE BETWEEN FR 67 TO 68, LBL 46" REF SRM 51-74-00. ACCOMPLISHED A UT THICKNESS INSP AFTER REWORK MAX 0, 110, MIN 0.078, MATERIAL REMOVED 0.042. MX-3 SN 38265, CAL DATE 17, DEC 11, FOUND OUT OF LIMITS IAW SRM 53-00-14. REMOVED, DRILLED UP AND REPLACED IAW SRM 51-42-11, 51-23-11, 51-42-11.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE)

REMOVED CORROSION AT CABIN FLOOR SUPPORT UPPER SURFACE BETWEEN FR 68 AND 69, LBL 66. FOURN OUT OF LIMITS IAW SRM 53-00-14. R & R FLOORBEAM SUPPORT IAW SRM 53-0014 AND 51-42-11, 51-21-11.

Part: FLOOR PANEL — CORRODED (CABIN) · corrosion level 2

CABIN FLOOR PANEL 262FF HAS CORROSION SPOTS NEAR R-2 DOOR ENTRANCE AND AROUND FWD GIRT BAR LATCH. (REMOVED CORROSION, ACCOMPLISHED AUT THICKNESS. FOUND OUT OF LIMITS, CORROSION LEVEL 2) REPLACED BY NEW PART FLOOR PANEL 262FF, PN D5367180500500 IAW A320, SRM 53-02-00.

Part: COMPUTER — MALFUNCTIONED (ELAC)

FLIGHT DEPARTED 3 MINUTES EARLY AT 0422Z, WITH T/O AT 0433Z. ALSO AT 0433Z THE ACFT REPORTED ELAC 1 AND 2 AILERON ORDER DISAGREE THRU EFCS 1 AND 2 AS FAILURE MESSAGES. SHORTLY AFTER THIS, CAPT CONTACTS MX VIA AIRCELL. MX CONCURS WITH CAPT TO RETURN TO DEPARTURE, DUE TO THE ALTERNATE AND DIRECT LAW IMPICATIONS ALONG WITH NO AUTOPILOT 1 OR 2 AVAILABILITY. THE ACFT TOUCHED DOWN UNEVENTFULLY AT 0511Z AND BLOCKED IN AT 0521Z. AT O511Z DIRECT AND ALTERNATE LAW WARNING MESSAGES ALSO APPEARED ON THE POST FLIGHT REPORT VIA AIRMAN. HARD/OVERWEIGHT LANDING INSP IAW AMM 05-51-11 WAS ASKED TO BE ACCOMPLISHED PRECAUTIONARY BY MX EVEN THOUGH NO LOAD 15 REPORT WAS GENERATED. UPON INTERROGATION OF CFDS, ELAC1 WAS FOUND TO BE FAULTING AFTER ACCOMPLISHING TSM 27-93-00-810-896 AND -949. ELAC PN 3945128206 SN ELACVB015025 WAS REPLACED WITH SN ELACVB016901 AND OPS CHECKED OK. THE ACFT WAS RETURNED TO SERVICE AFTER THE SUCCESSFUL TESTS OF THE ELAC SYS. IAW OPERATORS RECORDS, ALL AD`S, SB, STC`S AND PMA`S ARE IN FULL COMPLIANCE WITH THE TYPE DESIGN CERT AND ASSOCIATED REGULATORY REQ. (K)