N632VA

Part: FLOOR PANEL — PUNCTURED (UNKNOWN) · airframe 45,487 hrs · 14,244 cycles

AFT CABIN 251CF HAS REPAIR NOT LISTED IN REPAIR LISTINGS GROUNDED - YES. REPAIRED AFT MAIN CABIN FLOOR PANEL 251CF IAW A320 SRM 53-02-00-283-001 AND 53-02-00-300-001.

Part: FLOOR PANEL — PUNCTURED (UNKNOWN) · airframe 45,487 hrs · 14,244 cycles

AFT CABIN FLOOR PANEL 241JF HAS A REPAIR NOT LISTED IN REPAIR LISTINGS. GROUNDED - YES. ACCOMPLISHED REPAIR ON AFT CABIN FLOOR PANEL 241FJ IAW A320 SRM53-02-00-283-001 REV 145 AND SRM 53-02-00-300.0010 ZONE A.

Part: ANGLE — CORRODED (ACCESS DOOR) · corrosion level 2 · airframe 45,487 hrs · 14,244 cycles

ACCESS DOOR 312AR FWD AT FUSELAGE FR71 AND DOOR JAMB HAS CORROSION. GROUNDED - YES. REMOVED AND REPLACED DOOR JAMB ANGLE AT ACCESS DOOR 312AR AT FR71 IAW A320 SRM 51-42-11-001 REV 145.

Part: FLOORBOARD — DELAMINATED (UNKNOWN) · airframe 45,487 hrs · 14,244 cycles

MAIN CABIN FLOOR BOARD 231FF HAS INSERT DAMAGE AT L/H. GROUNDED - YES. REMOVED AND REPLACED MAIN CABIN FLOOR BOARD 231FF IAW A320 AMM 53-12-12-420-001-A.

Part: SEAT TRACK — WORN (UNKNOWN) · airframe 45,487 hrs · 14,244 cycles

MAIN CABIN SEAT INBD TRACK CROWN LATERAL AREA IS WORN AT FR42. GROUNDED - YES. REMOVED AND REPLACED SEAT TRACK P/N: D5337111000800 IAW A320 SRM 51-42-11/001 AND SRM 51-72-11-911-001 REV. 145 AT MAIN CABIN L/H INBD FR41 TO FR47 Y = 765.

Part: SEAT TRACK — WORN (UNKNOWN) · airframe 45,487 hrs · 14,244 cycles

MAIN CABIN OUTBD SEAT TRACK CROWN LATERAL AREA IS WORN BETWEEN FR43 AND FR44. GROUNDED - YES. REMOVED AND REPLCAED MAIN CABIN SEAT TRACK BETWEEN FR41 AND FR47 Y=1292. P/N D5337111200400 IAW A320 SRM 51-42-11 AND SRM 51-72-11-911-001.

Part: SKIN PANEL — CORRODED (UNKNOWN) · corrosion level 2 · airframe 45,487 hrs · 14,244 cycles

FOUND MULTIPLE AREAS OF CORROSION ON L/H WING TOP SKIN PANEL 2 T/E OVERHANG BETWEEN RIB 14-18 GROUNDED - YES. ACCOMPLISHED EA A320-57EA-01874 REV. 00 MINOR REPAIR

Part: DOOR SILL — CORRODED · corrosion level 2 · airframe 45,487 hrs · 14,244 cycles

AFT CABIN R/H LWR SILL AT FR68 HAS CORROSION. GROUNDED - YES. ACCOMPLISHED CATEGORY "A" PERMANENT REPAIR ON AFT CABIN R/H LWR SILL AT FR68, Y=1732 IAW A320 SRM 53-41-14-300-001, REV 144.

Part: FLOOR PANEL — DELAMINATED (CABIN) · airframe 45,487 hrs · 14,244 cycles

MAIN CABIN FLOOR PANEL 251RF HAS MISSING MATERIAL GROUNDED - YES. REMOVED AND REPLACED MAIN CABIN FLOOR PANEL 251RF IAW A320 AMM 53-00-00-400-801-A AND 53-00-00-000-801-A.

Part: SKIN PANEL — CORRODED (UNKNOWN) · corrosion level 2 · airframe 45,487 hrs · 14,244 cycles

L/H WING/TOP SKIN PANEL 2/TRAILING EDGE OVERHANG BETWEEN RIB 6 AND 27 CORROSION. GROUNDED - YES. REPAIRED L/H WING/TOP SKIN PANEL 2 REAR SPAR AT RIB 15-18 IAW ASA EA A320-57EA-01874 REV 00 AND AIRBUS RDAF 81253170/060/2023 ISSUE A DATED 21-OCT-2023 CATEGORY B PERMANENT REPAIR.

Part: SKIN PANEL — CORRODED (UNKNOWN) · corrosion level 2 · airframe 45,487 hrs · 14,244 cycles

L/H WING/TOP SKIN PANEL 2 OVERHANG BETWEEN RIB 6 AND 27 CORROSION. GROUNDED - YES. REPAIRED L/H WING TOP SKIN TRAILING EDGE OVERHANG IAW ASA EA A320-57EA-01874 REV 00 AND AIRBUS RDAF 81253170/059/2023 ISSUE A DATED 24-OCT-2023 CATEGORY B PERMANENT REPAIR.

Part: SKIN PANEL — CORRODED (UNKNOWN) · corrosion level 2 · airframe 45,487 hrs · 14,244 cycles

L/H WING/TOP SKIN PANEL 2 TRAILING EDGE OVERHANG HAS EXTENSIVE CORROSION THROUGHOUT GROUNDED - YES. REPAIRED L/H WING TOP SKIN OVERHANG AT RIBS 9-27, STRINGER 16 IAW ASA EA A320-57EA-01874 REV 00 AND AIRBUS RDAF 81253170/031/2023 ISSUE A DATED 23-OCT-2023 CATEGORY B PERMANENT REPAIR.

Part: SKIN PANEL — CORRODED (RT WING TOP) · corrosion level 2 · airframe 45,487 hrs · 14,244 cycles

R/H WING TOP SKIN PANEL 2 T/E OVERHANG HAS EXTENSIVE CORROSION. GROUNDED - YES. ACCOMPLISHED CATEGORY B PERMANENT REPAIR OF R/H WING TOP SKIN PANEL 2 TEOH RIBS 9-27 IAW ASA EA A320-57EA-0187 REV 00 AND AIRBUS RDAF 81250074/004/2023 ISSUE A DATED 25-OCT-2023.

Part: DOOR SILL — CORRODED · corrosion level 2 · airframe 45,487 hrs · 14,244 cycles

AFT CARGO COMPARTMENT DOOR SILL UPPER SURFACE HAS CORROSION FROM FR55 TO FR56. GROUNDED - YES. REMOVED AND REPLACED AFT CARGO COMPARTMENT DOOR SILL/THRESHOLD SHEET AT FR52A TO FR56, Y=-609.6 TO Y=-723.9 IAW A320 SRM 51-72-11-911-001.

Part: WEB — CORRODED · corrosion level 2 · airframe 45,487 hrs · 14,244 cycles

AFT CARGO DOOR CUTOUT TORQUE BOX UPPER WEB IS CORRODED IN NUMEROUS AREA. GROUNDED - YES. REMOVED AND REPLACED AFT CARGO DOOR CUTOUT TORQUE BOX WEB P/N: D5347556522200 AT FR52A TO FR56, STR 39R IAW A320 SRM 51-42--11/001 PARA. 2E AND 2F.

Part: FLOOR PANEL — CORRODED (UNKNOWN) · corrosion level 2 · airframe 45,487 hrs · 14,244 cycles

R1 DOOR THRESHOLD PLATE HAS RUST ON 3EA ATTACHING SCREW HOLES. GROUNDED - YES. REMOVED AND REPLACED MAIN CABIN FLOOR PANEL 222FF AT FR16 TO FR20 P/N E5367147800700 IAW A320 AMM 53-12-12-400-001-A

Part: FLOOR SUPPORT — CORRODED · corrosion level 2 · airframe 45,487 hrs · 14,244 cycles

AFT PIT FLOOR STRUCTURE HAS CORROSION FROM C56 TO C58 ON LEFT SIDE AFT LOOKING FWD. GROUNDED - YES. REMOVED AND REPLACED AFT PIT FLOOR SUPPORT AT FR56 TO FR58 STR37L TO STR38L IAW A320 SRM 51-42-11/001 REV. 144.

Part: SKIN — CORRODED · corrosion level 2 · airframe 45,487 hrs · 14,244 cycles

R/H FUSELAGE ACCESS DOOR 312AR INNER SKIN IS CORRODED. GROUNDED - YES. REMOVED AND REPLACED INNER SKIN ON ACCESS DOOR 312AR IAW A320 SRM 51-42-11-001

Part: SHEAR TIE — CORRODED (FUSELAGE) · corrosion level 2 · airframe 42,790 hrs · 13,068 cycles

MAIN CABIN FLOOR LEVEL BETWEEN FR69-FR70 STR23R LATERAL SHEAR TIE WEB CORRODED GROUNDED - YES. REMOVED CORRODED LATERAL SHEAR TIE WEB IN MAIN CABIN FLOOR LEVEL BETWEEN FR69-FR70 STR23R (CORROSION WAS 100% MATERIAL LOSS PLUS 2 INCHES LENGTH) PER AIRBUS DWG 18D53474180 ISSUE Q AND SRM 51-42-11. DISCONNECTED WIRES TO 36MG MOTOR START RELAY PER AMM 38-31-36. INSTALLED NEW WEB PER DWG #18D53474180 ISSUE Q.

Part: SHEAR TIE — CORRODED (FUSELAGE) · corrosion level 2 · airframe 42,790 hrs · 13,068 cycles

MAIN CABIN FLOOR LEVEL BETWEEN FR69-FR70 STR23R LATERAL SHEAR TIE WEB CORRODED GROUNDED - YES. REMOVED CORRODED LATERAL SHEAR TIE WEB IN MAIN CABIN FLOOR LEVEL BETWEEN FR69-FR70 STR 23R (CORROSION WAS 100% MATERIAL LOSS PLUS 2 INCHES LENGTH) PER AIRBUS DWG 18D53474180 ISSUE Q AND SRM 51-42-11. DISCONNECTED WIRES TO 36MG MOTOR START RELAY PER AMM 38-31-36. INSTALLED NEW WEB PER DWG #18D53474180 ISSUE Q.1.

Part: BEAM — CORRODED (FRAME 68) · airframe 42,790 hrs · 13,068 cycles

MAIN CABIN LWR DOOR SILL SUPPORT AT R-2 DOOR, FWD OF FR68 HAS ACORRODED EXISTING REPAIR  GROUNDED - YES. REMOVED DAMAGED REPAIR IAW A320 SRM 51-42-11. FABRICATED NEW REPAIR AND 2 EACH FILLERS IAW A320 SRM 53-41-14-300-001. INSTALLED REPAIR AND 2 EACH FILLERS IAW A320 SRM 51-42-11. THIS IS A CATEGORY A REPAIR P.O #878050.2

Part: DOOR FRAME — CORRODED (FRAMES 16-20) · corrosion level 2 · airframe 42,790 hrs · 13,068 cycles

R1 DOOR LOWER FRAME AT GIRT BAR304 LOCATION FWD AND AFT HAS CORROSION (MARKED IN RED) GROUNDED - YES. REMOVED CORROSION ON R1 DOOR LOWER FRAME AT FWD AND AFT GRIT BAR LOCATIONS PER A320 SRM 53-11-14-283-005, A320 SRM 51-74-00, A320 SRM 51-74-00. ORIG THICK .180 REMAINING THICK .168 REMOVED .012 TOOL #T8225G 01NOV19. PERFORMED DVI PER NTM 51-90-00 NO CORROSION NOTED. PERFORMED SURFACE HFEC OF BLENDED AREAS FWD & AFT LOCATIONS, ALL HOLES HFEC PROBE FWD & AFT PER VS/NC T8257D TASK 51-10-08-250-802 NO CRACKS NOTED. SPOTFACED, REAMED, ALODINED, PRIMED, PAINTED AREA IAW A320 SRM 53-11-14-283-005. INSTALLED 6EA BUSHINGS AND REPAIR WASHERS PER A320 SRM 53-11-14-283-005

Part: DOOR FRAME — CORRODED (FRAMES 16-20) · corrosion level 2 · airframe 42,790 hrs · 13,068 cycles

L1 DOOR LOWER FRAME AT GIRT BAR LOCATION FWD HAS CORROSION (MARKED IN RED) GROUNDED - YES. REMOVED CORROSION ON L1 LOWER DOOR FRAME AT FWD GIRT BAR PER A320 SRM 53-11-14-283-005, A320 SRM 51-74-00, A320 SRM 51-74-00. ORIG. THICK .197 REMAINING .181 REMOVED .016. TOOL #T82250 O2 MAY 19. PERFORMED DVI PER NTM 51-90-00 NO DISCREPT NOTED. PERFORMED SURFACED HFEC OF BLENDED AREA, AND OPEN HOLES IN BLENDED AREA PER VSUVC T82570 TASK 51-10-08-250-803. NO CRACKS NOTED. SPOT FACED REAMED, ALODINED, PRIME, PAINTED AREA PER A320 SRK 53-11-14-283-005. INSTALLED 3EA. BUSHINGS AND REPAIR WASHERS PER A320 SRM 53-11-14-285-005. INSTALLED DRAW PAN, FITTINGS, GIRL BAR (UT GAGE: T82250 02/MAY/2019 FITTINGS PER A320 AMM 52-11-31

Part: WEB — CORRODED (FRAMES 68-69) · corrosion level 2 · airframe 42,790 hrs · 13,068 cycles

MAIN CABIN FLOOR @ FR69-FR68 R/H OUTBOARD CUSP WEB CORRODED GROUNDED - YES. BLENDED CORROSION AND FOUND OUT OF LIMITS IAW A320 SRM 53-41-14. ORIG .063 REMOVED .057 REMAINING .006. LOCATED AND DRILLED NEW WEB IAW A320 SRM 51-42-11. INSTALLED NEW WEB IAW A320 SRM 51-42-11 AND DWG #D534800206.

Part: FITTING — CORRODED (GIRT BAR) · airframe 42,790 hrs · 13,068 cycles

AFT PASSENGER/CREW LT/SIDE DOOR LOWER FWD GIRT BAR FITTING CORRODED. GROUNDED - YES. REMOVED CORROSION AND FOUND WITHIN LIMITS IAW A320 SRM 53-41-174. ORIG .098 REMOVED .013. REMAINING .085. ALODINED AND PRIMED IAW A320 SRM 51-75-12. TOPCOATED IAW A320 51-75-12. REMOVED AND REINSTALLED PLATE IAW A320 SRM 52-13-31.

Part: DOOR SILL — CORRODED (PAX DOORWAY) · corrosion level 2 · airframe 42,790 hrs · 13,068 cycles

AFT PASSENGER/CREW RT/SIDE DOOR LOWER FWD GIRT BAR FITTING CORRODED.  GROUNDED - YES. REMOVED CORROSION IAW A320 SRM 53-41-14-283-002. ORIG MAT .098, REMAINING MAT .069 MAT LOSS OF .029. REPAIRED AREA IAW A320 SRM 53-41-14-300-001. THIS IS A CATEGORY A REPAIR. INSTALLED DOUBLERS.

Part: FLOOR SUPPORT — CORRODED (FRAMES 67-70) · corrosion level 2 · airframe 42,790 hrs · 13,068 cycles

MAIN CABIN FLOOR @FR68 RBL30 BEAM UPPER SURFACE CORRODED GROUNDED - YES. REMOVED CORROSION OUT OF SRM 53-00-14 LIMITS - DAMAGE WAS 2" LONG - ORIG THK .150", REMAINING THK .130" REMOVED .020 ", REMOVED DAMAGED BEAM BETWEEN FR67-FR70 @ Y-765, LOCATED, DRILLED AND INSTALLED NEW BEAM IAW AIRBUS DWG D53472040 & A320 SRM 51-42-11.

Part: BRACKET — CORRODED (FRAMES 69-70) · corrosion level 2 · airframe 42,790 hrs · 13,068 cycles

MAIN CABIN, AFT, LEFT SIDE, LATERAL SHEAR TIE STR 23L BETWEEN FRAME 69 AND 70 CORROSION GROUNDED - YES. REMOVED AND REPLACED MAIN CABIN AFT LEFT SIDE LATERAL SHEAR TIE, STR69-70 STR 23L IAW A320-DWG D53474180 - LATE ENTRY - REMOVED CORROSION ON SHEAR TIE IAW A320 SRM 51-73-00. ORIGINAL THICKNESS .071, REMAINING THICKNESS .045, MATERIAL LOSS .026 IAW A320 SRM 53-41-74 CORROSION OUT OF LIMITS.

Part: SHEAR TIE — CORRODED (FRAMES 68-69) · corrosion level 2 · airframe 42,790 hrs · 13,068 cycles

MAIN CABIN, AFT, LEFT SIDE, LATERAL SHEAR TIE STR 23L BETWEEN FRAME 69 AND 68 CORROSION GROUNDED - YES. BLENDED CORROSION AND FOUND OUT OF LIMITS IAW A320 SRM 53-41-14. ORIG .065, REMOVED .058 REMAINING .005. REMOVED AND REPLACED WEB IAW A320 SRM 51-42-11 AND DWG# D534800192.

Part: SUPPORT BEAM — CORRODED (FRAMES 68) · corrosion level 2 · airframe 42,790 hrs · 13,068 cycles

AFT MAIN CABIN, L-2 DOOR THRESHOLD. DOOR SILL SUPPORT BEAM CORROSION AFT END. GROUNDED - YES. BLENDED CORRODED AREA. ORIGINAL MAT. THICKNESS .071, REMOVED .016, REMAINING .055. FOUND TO BE OUT OF LIMITS AS PER SRM 53-41-14-283-002. FABRICATED REPAIR ANGLE IAW A320 53-41-14-300-001. [REPAIR PRINCIPAL 8, ITEM 9] FABRICATED FILLER IAW SRM 53-41-14-283-002 [REPAIR PRINCIPAL 8, ITEM 3] ANGLE AND FILLER HEAT TREATED IAW SRM 51-25-00. APPLIED PROTECTVE TREATMENT, ALODINE, PRIME AND PAINT IAW SRM 51-21-11. AMM 51-75-12 AMM 51-23-00. INSTALLED FILLER AND REPAIR ANGLE IAW A320 SRM 53-41-14-283-002.

Part: BEAM — CORRODED (FRAMES 68-70) · corrosion level 2 · airframe 42,790 hrs · 13,068 cycles

AFT MAIN CABIN, FLOOR BEAM, BUTT LINE 8 L. JUST FORWARD OF FRAME 70, CORROSION ON TOP GROUNDED - YES. CORROSION LOCATED AT A HARD POINT AREA WHICH IS A EXCLUDED AREA REQUIRING BEAM REPLACEMENT, REF. A320 SRM 53-00-14-283-002, FIG 001 (SHT 1) REMOVED DAMAGED BEAM RECIEVED LOCATED DRILLED AND INSTALLED NEW FLOOR SUPPORT BEAM BETWEEN FR68-FR70 @Y160.5 IAW AIRBUS DWG D53472040 A320 SRM 51-42-11

Part: BEAM — CORRODED (FRAME 68) · corrosion level 2 · airframe 42,790 hrs · 13,068 cycles

AFT MAIN CABIN, R-2 DOOR THRESHOLD. DOOR SILL SUPPORT BEAM CORROSION AFT END.  GROUNDED - YES. BLENDED CORROSION IAW A320 SRM 53-41-14-283-002. ORIG MAT .071 REMAINING MAT .0. 100% MAT. LOSS. REPAIRED AREA IAW A320 SRM 53-41-14-300-001. THIS IS A CATEGORY A REPAIR. INSTALLED DOUBLERS.

Part: OIL SYSTEM — DEPLETED (NR 2 ENGINE) · airframe 41,882 hrs · 12,666 cycles

ON CLIMBOUT RECEIVED ENG 2 STALL ECAM MSG. IT WENT AWAY. 30 SECONDS LATER IT SHOWED UP AGAIN. THEN OIL QUANTITY WAS DEPLETING. ENG 2 FAILED FAIL ECAM THEN SHUT DOWN ENGINE TWO. GROUNDED - YES. EMERGENCY LANDING DECLARED - AOG IN SEA

Part: SEAT TRACK — CORRODED (FUSELAGE)

FORWARD CABIN SEAT TRACK FROM FR12-24 AT Y765 HAD AN AREA OF CORROSION AT FR16 BEYOND LIMITS. EXTENT OF THE DAMAGE WAS 1" IN LENGTH X 2" IN WIDTH X .032 DEPTH. THE SEAT TRACK WAS REPLACED IAW SRM 51-42-11.

Part: SILL — CORRODED (FUSELAGE)

RIGHT AFT PASSENGER DOOR SILL BETWEEN FR 66-68, ST 23-24 AT RBL 56 HAD AN AREA OF CORROSION BEYOND LIMITS. EXTENT OF DAMAGE WAS 1" IN LENGTH X 1" IN WIDTH X .050" DEPTH. THE DOOR SILL WAS REPAIRED IAW SRM 53-41-14, FIG 201, VIEW K, PRINCIPLE 5.

Part: SUPPORT — CORRODED (FUSELAGE)

LEFT AFT SHEAR PLATE SUPPORT, FR 69-70, ST 23L-24L HAS CORROSION BEYOND LIMITS. EXTENT OF DAMAGE 2" L X 2" W X .020 DEPTH. SUPPORT BELOW A SHEAR PLATE WAS R & R IAW SRM 51-40-00 AND 51-42-11.

Part: SHEAR PLATE — CORRODED (FUSELAGE)

RIGHT AFT SHEAR PLATE BETWEEN FR 69-70, S23R HAS CORROSION BEYOND LIMITS. EXTENT OF DAMAGE 2" L X 2" W X .040 DEPTH. SHEAR PLATE WAS R & R IAW SRM 51-40-00 AND 51-42-11.

Part: UNKNOWN — ODOR (COCKPIT)

(APPROX 3.5 HRS INTO THIS FLIGHT) THE FLIGHT CREW "DETECTED STRONG CHEMICAL ODOR WHILE IN CRUISE, UNABLE TO DETERMINE ORIGIN, DIVERTED". THE FLT CREW DONNED 02 MASK AND DECLARED AN EMERGENCY WITH ENROUTE-ATC AND FOLLOWED PROCEDURES FOR A TPA DIVERSION. ONCE ON THE GROUND, CREW ADVISED MX OF OBSERVATION OF ODOR IN COCKPIT AND CABIN AREAS. TECHS WERE DISPATCHED TO PERFORM A/C INSPECTION, TSM 26-15-00-810-804 (ODORS IN THE CABIN AND NOT FIRE) & TSM 24-00-00-810-823 ( ELECTRICAL BURNING ODOR OR FUMES IN A/C). POST INTERIOR AND EXTERIOR INSPECTION REVEALED NO DEFECTS/ SOURCE COULD BE FOUND. ACFT WAS RETURNED TO SERVICE LATER ON.

Part: BUSHING — OUT OF POSITION (L1 DOOR)

AFTER THE FLIGHT, DURING THE TURN, IT WAS NOTED THAT THE L1 DOOR WOULD NOT REMAIN LOCKED OPEN. MX WAS AT THE STATION AND FOUND THE GUIDE AND BUSHING OUT OF POSITION, REF AIPC 52-11-01-09D, ITEMS 240 AND 260. THE 2 PARTS WERE RE-INSERTED AND THE DOOR UNLOCKING MECHANISM CHECKED OK IAW AMM 52-11-00-06. THE ACFT INCURRED A 22 MINUTE DELAY. NO FURTHER ISSUES WITH THIS SYS HAVE BEEN REPORTED.

Part: GUIDE — OUT OF POSITION (L1 DOOR)

AFTER THE FLIGHT, DURING THE TURN, IT WAS NOTED THAT THE L1 DOOR WOULD NOT REMAIN LOCKED OPEN. MX WAS AT THE STATION AND FOUND THE GUIDE AND BUSHING OUT OF POSITION, REF AIPC 52-11-01-09D, ITEMS 240 AND 260. THE 2 PARTS WERE RE-INSERTED AND THE DOOR UNLOCKING MECHANISM CHECKED OK IAW AMM 52-11-00-06. THE ACFT INCURRED A 22 MINUTE DELAY. NO FURTHER ISSUES WITH THIS SYS HAVE BEEN REPORTED.

Part: ACTUATOR — UNSERVICEABLE (HORIZONTAL STAB)

ACFT WAS UNDERGOING A C2 CHECK. DURING THE ACCOMPLISHMENT OF MPD TASK CARD 274451-04-1, 2 DIFFERENT GREASE TYPES WERE FOUND. THE GREASES WERE WIPED CLEAN OFF THE TRIMMABLE HORIZONTAL STABILIZER ACTURATOR (THSA) AND JACKSCREW. FURTHER INSP REVEALED A METALLIC CHIP, APPROXIMATELY 0.44" BY 0.22", WHICH WAS FOUND ON TOP OF THE STOP CLAW ASSY ON THE BALL SCREW JACK. THIS INFORMATION WAS SENT TO ENGINEERING AND TO MFG, WHERE THE DECISION WAS MADE TO R & R THE THSA ASSY. THE CHIP WAS SENT TO MFG ENGINEERING FOR ANALYSIS AND COMPONENT ID. NO AREA WAS FOUND TO BE MISSING METAL DURING INSPECTION OF THE ACTUATOR OR JACKSCREW ( THE UNIT WAS NOT DISASSEMBLED AT THIS TIME). THE THSA PN REMOVED WAS 47145-147, SN 3277. INSTALLED PN IS 47145-137, SN 814. THIS TASK WAS ACCOMPLISHED IAW AMM 27-44-51-04 AND 27-41-00-05. ACCORDING TO THE OPERATOR`S RECORDS, ALL AD, SB, STC AND PMA`S ARE IN FULL COMPLIANCE WITH THE TYPE DESIGN CERTIFICATE AND ASSOCIATED REGULATORY REQUIREMENTS.

Part: ENGINE — FAILED (NR 1) · airframe 7,975 hrs · 2,452 cycles

FLIGHT PUSHED BACK 6 MINUTES EARLY AT 1624Z AND TOOK OFF AT 1639Z. AT 1903Z, CUSTOMER SUPPORT CONTACTED MX, ADVISING THAT THE NR 1 ENG SHUTDOWN AT APPROX 1853Z. AT 1906Z MX SENT AN ACAR MESSAGE TO THE ACFT REQUESTING THE CONDITION OF THEIR ENG PARAMETERS WITH NO RESPONSE FROM THE CREW. DISPATCHER, OPS MGR AND DOM WERE NOTIFIED. AT 1910Z, THE CREW CALLED THE CONTROLLING DISPATCHER STATING THEY WERE SAFELY ON THE GROUND AND HAD DECLARED AN EMERGENCY DESCENT AND ARRIVAL. DEBRIEF OF THE CREW IS AS FOLLOWS: AT FL300 A BUMP WAS FELT WITH AN ASSOCIATED HESITATION IN ENG RESPONSE AND PERFORMANCE. MOMENTS LATER, ADVISORY MESSAGES ENG 1 FAIL THEN AN ENG 1 SHUT DOWN APPEARED WITHIN A MINUTE OF EACH OTHER. NO SMOKE WAS NOTED IN THE FLIGHT DECK, ANY SMELL WAS ASSOCIATED WITH OIL VAPOR GETTING INTO THE PNEUMATIC SYSTEM. MX CONTACTED TO DO A VISUAL INSP OF NR 1 ENG. INSP REVEALED THE ENG HAD 9 QTS OF OIL REMAINING IN THE TANK, METAL DEBRIS IN THE TAIL PIPE AND A LARGE AMOUNT OF METALLIC DEBRIS ON MASTER CHIP DETECTOR. PICTURES WERE RECEIVED AND DECISION WAS MADE TO CHANGE ENG. LINE MX, ENG PLANNING AND LT COORDINATED THE LOGISTICS REQUIRED FOR THE NR 1 ENG CHANGE. ALL PAPERWORK, PARTS SPARE ENGINE, TOOLING AND PERSONNEL WERE ARRANGED AND SENT OUT. ENG WILL BE SHIPPED TO MFG AND TEAR DOWN FINDINGS MADE AVAILAGLE. ACCORDING TO THE OPERATOR`S RECORDS, ALL AD, SB STC`S AND PMA`S ARE IN FULL COMPLIANCE WITH THE TYPE DESIGN CERTIFICATE AND ASSOCIATED REGULATORY REQUIREMENTS. (K)

Part: ECU — FAULTY (NR 2 ENGINE)

FLIGHT 515 LAX TO JFK. DURING CRUISE 3 ECAM WARNINGS, THRUST LEVER FAULT, CTL VALVE FAULT, AND ENG2 FADEC A FAULT. AN ASSOCIATED LAND ASAP AMBER ECAM ADVISORY MSG ALSO APPEARED. CREW ADVISED DISPATCH THAT THEY WERE DIVERTING TO LAS. MX FOLLOWED THE TSM FOR THE FAULTS AND FOUND ENGINE 2 CHANNEL A NOT REPORTING DURING ECU TEST. THE ECU WAS REPLACED AND OPS CHECKED OK PER AMM 73-21-60. IAW THE OPERATORS RECORDS, ALL AIRWORTHINESS DIRECTIVES, SERVICE BULLETINS, STC`S AND PMA`S ARE IN FULL COMPLIANCE WITH THE TYPE DESIGN CERTIFICATE AND ASSOCIATED REGULATORY REQUIREMENTS. THE ACFT WAS RELOCATED BACK TO SFO. N632VA DEPARTED LAS AT 0741Z AND ARRIVED SFO AT 0842Z. NO FAULTS NOTED.

Part: UNKNOWN — ODOR (CABIN)

FLT DIVERTED DUE TO ODOR IN CABIN AROUND SEAT ROWS 4 TO 7. AT ABOUT 10,000 FT & CLIMBING ODOR FIRST NOTICED BY FLT TEAM MEMBER & THEN DISAPPEARED. LATER, AT ABOUT 30,000 FT ODOR RETURNED. REPORTED IT TO BE LIKE ELECTRIC OR PLASTIC ODOR & THAT IT WAS STRONG. CAPTAIN TO DIVERTED FOR INVESTIGATION. ODOR AGAIN DISAPPEARED BEFORE ARRIVAL. ACCOMPLISHED VISUAL INSPECTION OF E&E BAY, FWD CARGO BIN, CABIN CEILING PANELS AND PSU`S IN AFFECTED AREA. NO FINDINGS REF AMM 25-23-41-04, TSM 24-00-00-810-823. ACCOMPLISHED CABIN TEMP CONT SYS TEST. OPS OK IAW 21-63-00-710-004. PLACED IFE SYS INOP AS PRECAUTION. ACFT RETURNED TO SERVICE & WITH NO FURTHER OCCURRENCE. FURTHER INSP & CHECKS CARRIED OUT, NO DEFECTS FOUND. IFE CB`S RESTORED & SYSTEM PWR TURNED ON. OPERATED SYS FOR 5 HRS. ALL OPS CHECK NORMAL IAW MM 44-27-01. THE IFE WAS RETURNED TO SERVICE & IS OPERATING NORMALLY. (K)