N854VA
Operators of this aircraft
Who operated this tail, and how firmly we know it.
No operator established for this aircraft.
Accident & incident history
No NTSB accidents or incidents on file for this aircraft.
Maintenance disclosures
Service Difficulty Reports filed with the FAA for this airframe. Filing is largely voluntary — the number of reports is not a measure of reliability. To verify a report, search its control number at the FAA SDRS site.
22 reports on file, 2012-06-12 – 2024-06-05.
Part: FRAME — CORRODED (FRM 68) · airframe 34,008 hrs · 11,211 cycles
MAIN CABIN FR68 CORRODED AROUND ANCHOR NUT ABOVE STGR. 23R. GROUNDED - YES. REMOVED AND REPLACED NUT PLATE ON FR 68 AT STR 23R AND BLENDED CORROSION AT NUT PLATE HOLE IAW A320 SRM 53-41-12-283-001 FIG 2 SHEET 1 AND FOUND TO BE IN LIMITS. BLEND OUT IS L=2.3" W=1.3" MATERIAL LOSS IS .009" ORIGINAL THICKNESS .098" REMAINING IS .089" MAX ALLOWABLE LOSS IS .020" REPAIR IS CAT B INSPECTION THRESHOLD 60,000 FC INSPECTION METHOD DET RESTORED ALL PROTECTIVE FINISHES IAW A320 SRM 51-42-11 AND 51-75-12.
Part: DOOR SILL — CORRODED (ZONE 100) · airframe 34,008 hrs · 11,211 cycles
MAIN CABIN, R2 DOOR, SILL BEAM CORRODED AT FR68 STRG.23R GROUNDED - YES. REMOVED CORROSION ON R2 DOOR SILL AT FR 68 AND FOUND TO BE IN LIMITS IAW A320 SRM 53-41-14-283-002 REV 149 FIG 2 SHEET 1 CODE "B" BLEND OUT IS L=1.7" W=.700 AND 2.5 INCHES AFT FROM NUT PLATE AT FR68 ORIGINAL THICKNESS IS .071" MATERIAL LOSS OF .022" MAX ALLOWABLE IS .02485" MATERIAL REMAINING IS .049" REMOVED AND REINSTALLED FASTENER AT BLEND AREA IAW A320 SRM 51-42-11 AND RESTORED ALL PROTECTIVE FINISHES IAW A320 SRM 51-21-11 AND 51-75-12-911 CAT A REPAIR
Part: THRESHOLD — CORRODED (ZONE 100) · airframe 34,008 hrs · 11,211 cycles
L-2 DOOR ENTRY AFT OF GIRT FITTING MOUNT, AFT LOWER CORNER AT THRESHOLD CORRODED. GROUNDED - YES. REMOVED CORROSION AT L2 DOOR AFT CORNER THRESHOLD, ORIGINAL MATL. .138", REMOVED .022", REMAINING MATL. .116" AND FOUND TO BE IN LIMITS IAW A320 SRM 53-41-79-983-002 FIG 1 SHEET 4. ROTO PEEN AND RESTORED ALL PROTECTIVE FINISHES IAW A320 SRM 53-41-79-283-002. CAT A
Part: THRESHOLD — CORRODED (ZONE 100) · corrosion level 2 · airframe 34,008 hrs · 11,211 cycles
FWD CARGO THRESHOLD CORROSION FR 26+10 +28Y GROUNDED - YES. REMOVED CORROSION AND FOUND OUT OF LIMITS IAW A320 SRM 53-21-29-283-001. REMOVED AND REPLACED THRESHOLD P/N D5323132220003 P.O. #1095256.2. IAW A320 SRM 51-42-11 AND AIRBUS DWG D53231761 ISSUE F. REMOVED AND REINSTALLED 4EA ATTACH FITTINGS FOR F.O.M IAW A320 SRM 51-42-11.
Part: SKIN — DENTED (ZONE 500 FLAP) · airframe 34,008 hrs · 11,211 cycles
FOR TRACKING OF SDR FOR SECOND CLUSTER OF DENTS ON L/H WING INBOARD FLAP LOWER SURFACE GROUNDED - YES. FOR TRACKING OF SDR FOR SECOND CLUSTER OF DENTS ON L/H WING INBOARD FLAP LOWER SURFACE
Part: SHEAR WEB — CORRODED (ZONE 200) · corrosion level 2 · airframe 34,008 hrs · 11,211 cycles
MAIN CABIN RH LOWER SHEAR WEB AT FR70 HAS CORROSION GROUNDED - YES. REMOVED AND REPLACED RH LOWER SHEAR WEB AT FR69-70 IAW A320 SRM 51-72-11-911-001 AND AIRBUS DWG D53474180 ISSUE U NO ADL GIVEN IN SRM WASTE VACCUM SYSTEM WIRING RESECURED AND OPS CHECK ON CUSTOMER CARD 383100-05-1 HAECO OPS 433
Part: SHEAR WEB — CORRODED (ZONE 200) · corrosion level 2 · airframe 34,008 hrs · 11,211 cycles
MAIN CABIN LH LOWER SHEAR WEB AT FR70 HAS CORROSION GROUNDED - YES. REMOVED AND REPLACED LH LOWER SHEAR WEB AT FR 69-70 IAW A320 SRM 51-72-11-911-001 AND AIRBUS DWG D53474180 ISSUE U NO ADL GIVEN IN SRM
Part: THRESHOLD — CORRODED (ZONE 100) · corrosion level 2 · airframe 34,008 hrs · 11,211 cycles
AFT PIT DOOR THRESHOLD HAS CORROSION ARROUND FASTENERS GROUNDED - YES. REMOVED CORROSION AND FOUND OUT OF LIMITS IAW A320 SRM 53-41-49-283-003 REMOVED AND REPLACED THRESHOLD P/N D5347560020400 PO:1091984.1 IAW A320 SRM 51-42-11 AND AIR BUS DWG D53475500 ISSUE BV
Part: WEB — CORRODED (ZONE 100) · corrosion level 2 · airframe 34,008 hrs · 11,211 cycles
AFT CARGO PIT FWD CUTOUT WEB CORRODED GROUNDED - YES. REMOVED CORROSION ON WEB FROM FRAMES 52A TO FRAME 56 MINIMUM REMAINING THICKNESS IS .047" ALLOWED. ACTUAL REMAINING THICKNESS IS .029" FOUND TO BE OUT OF LIMITS IAW A320 53-41-49-283-004. REMOVED AND REPLACED AFT CARGO PIT CUTOUT WEB P/N 5347556522600 P.O#1091985.3 IAW AIRBUS DWG#53475565 ISSUE N AND AIRBUS A320 SRM 51-42-11
Part: STRINGER — CORRODED (ZONE 100) · corrosion level 2 · airframe 34,008 hrs · 11,211 cycles
STRINGER 32R AT FR71 ON AFT OF FRAME HAS CORROSION GROUNDED - YES. REMOVED CORRODED STRINGER 32 RH FROM FR70-FR73+10" AND ACCOMPLISHED STRINGER REPAIR IAW A320 SRM 53-00-13-300-001 FIG 1 SHEET 2 REV 148 REPAIR IS CAT A. REMOVED AND REINSTALLED 7EA CLIPS ON STR 32 RH FR70-FR73 IAW A320 SRM 51-72-11-911-002 NO ADL GIVEN IN SRM
Part: SKIN — DENTED (ZONE 500 FLAP) · airframe 34,008 hrs · 11,211 cycles
LESSOR ITEM 32: LH WING INBOARD FLAP LOWER SURFACE BEHIND WHEELS FOUND WITH MULTIPLE DENTS. GROUNDED - YES. REPAIRED L/H WING INBOARD FLAP LOWER SURFACE BEHIND WHEELS FOUND WITH MULTIPLE DENTS WITH CAT A PERMANENT REPAIR IN 2EA AREAS. DAMAGE #1 IS AT WING STATION 75.25-92.0 AND IS 17" LONG AND 11" WIDE, DAMAGE #2 AT WING STATION 110.4-127.25 AND IS 17" LONG AND 12" WIDE. IAW A320 SRM 57-52-00-300-093, 51-77-13-911-013 AND EA# CMPT-57EA-02207. FH: 34067:48, FC: 11211, WV: 015. P/N: D5757065005200 S/N TB15058
Part: DOUBLER — CORRODED (ZONE 200) · corrosion level 2 · airframe 34,008 hrs · 11,211 cycles
INTERNAL DOUBLER INSIDE CUTOUT FOR SERVICE DOOR 312AR IS CORRODED GROUNDED - YES. REMOVED CORROSION ON 5EA. AREAS ON INTERNAL DOUBLER AROUND DOOR 312AR CUTOUT-FOUND AREA TO BE OUT OF LIMITS, NO LIMITS FOUND IN SRM. ORIGINAL THICKNESS .055", REMOVED .028", REMAINING .027" A320 SRM 51-74-00/001. REMOVED AND REPLACED INTERNAL DOUBLER PO#1091751.1, PN:D5357151520200 IAW A320 SRM 51-72-11 AND DWG#D53574510 REV.K AND DWG#D53571523 REV.E SRM 53-51-11-06-C
Part: DOUBLER — CORRODED (ZONE 100) · corrosion level 2 · airframe 34,008 hrs · 11,211 cycles
AFT PIT AT FR64 BETWEEN STR44 AND STR43R THERE IS EVIDENCE OF CORROSION ON THE BELLY SKIN DOUBLER STRAP GROUNDED - YES. REMOVED CORROSION IN AFT. PIT AT FR64 BETWEEN STR43R-STR44 AND FOUND AREA TO BE OUT OF LIMITS DUE TO NO LIMITS GIVEN IN SRM ON INTERNAL DOUBLER STRAP. ACCOMPLISHED EA#A320-53EA-02193. DIMENSION OF BLENDOUT IS 3.1" X 2", MATERIAL THICKNESS .078", REMOVED, .013", REMAINING .065". CATEGORY A REPAIR. A320 SRM 53-41-11-283-065
Part: STIFFENER — CORRODED (ZONE 100) · corrosion level 2 · airframe 34,008 hrs · 11,211 cycles
CORROSION ON FWD STIFFENER IN CUTOUT FOR ACCESS DOOR 312AR GROUNDED - YES. REMOVED AND REPLACED FWD STIFFENER ON CUTOUT FOR ACCESS DOOR 312AR IAW A320 SRM 51-72-11-911-001 REV 148 AND AIRBUS DWG D53571510 REV K
Earlier reports · 2012–2019 · 8 reports
2019
Part: SKIN — CRACKED (FUSELAGE) · airframe 26,761 hrs · 8,045 cycles
DURING DAILY INSP FOUND 1 INCH LONG CRACK IN THE SKIN AT THE LAV WASTE VENT. UPON ACCESSING AREA FOR REPAIR FOUND INTERNAL DOUBLER CORRODED BEYOND LIMITS. GROUNDED - YES. REPAIRED IAW SRM 53-41-11-300-004. THIS IS A CATEGORY A REPAIR.
Part: UNKNOWN — ODOR (CABIN) · airframe 25,165 hrs · 7,418 cycles
ACRID ELECTRIC BURN SMELL REPORTED BY FLIGHT ATTENDANTS PERCEIVED BY ROW 24 ABC IN FLIGHT. LOG PAGE 1170983: DUE TO CLUSTER FAN INDICATION AND SMELLS IN AIRCRAFT THE IFE SYSTEM REQUIRES DEACTIVATION. TBN-4430-04 REQUIRES COMPLETION OF IFE SYSTEM CHECK. GROUNDED - YES. PERFORMED TSM 05-50-00-810-831-A TYPE 9 CAUSE OF ODOR SUSPECTED. INSPECTED IFE, INTERNET, LIGHTING, FANS. LAVATORY WATER HEATERS, ISPS SYSTEM. FOUND IFE CLUSTER FAN INDICATOR FOR TWO CLUSTER FANS INTERMITTENT. INSPECTED APU COMPARTMENT AND PERFORMED TSM-00-00-810-823-A. NO OTHER OTHER DEFECTS FOUND. PERFORMED IFE SYSTEM CHECK PER TBN 4430-04. NO FAULTS FOUND. IFE SYSTEM OK FOR SERVICE. MDDR 62791 CLOSED. WATCH LIST UPDATED. MOC NOTIFIED.
2018
Part: CONNECTOR — UNSECURE (EMERGENCY LIGHTS) · airframe 24,893 hrs · 7,313 cycles
SEAT ROW 31 EMERGENCY EXIT LIGHT INOP. GROUNDED - YES. RESECURED ELECTRICAL CONNECTOR PER AMM 33-51-19. OPS CHECK GOOD. THIS CLEARS MDDR 62008. MEL LIST UPDATED. PLACARD REMOVED. MCC NOTIFIED
Part: WEB — CORRODED (FRAME 68) · corrosion level 2 · airframe 22,427 hrs · 6,525 cycles
CORROSION FOUND ON THE R2 DOOR CUT OUT LOWER SILL, 50 INCHES FROM CENTERLINE, RIGHT SIDE 1 - 5 INCHES FORWARD OF FRAME 68. ACFT GROUNDED. PERFORMED A REPAIR IAW SRM 53-41-14-300-001. REPAIR PRINCIPLE 5.
2017
Part: OXYGEN BOTTLE — FAILED (CABIN)
EXPERIENCED A MEDICAL EMERGENCY WHERE A PAX REQUIRED OXYGEN. ACCORDING TO THE FLT ATTENDANT THE PORTABLE OXYGEN BOTTLE FAILED WITH THE VALVE FULLY OPENED, ALL THE OXYGEN LEAKED OUT.
2015
Part: FAN — FAILED · airframe 12,496 hrs · 3,288 cycles
FLIGHT EXPERIENCED A VENT EXTRACT FAULT MESSAGE ON ECAM AND ACRID ODOR ON THE FLIGHT CREW. THE ACFT DIVERTED, UPON INVESTIGATION, THE EXTRACT FAN WAS FOUND FAILED. MEL 21-26-02-01 WAS APPLIED AND THE ACFT DEPARTED WITH NO FURTHER PROBLEMS, FAN WILL BE REPLACED AT NEXT MAINTENANCE OPPORTUNITY.
2012
Part: POWER SUPPLY — DEFECTIVE (CABIN) · airframe 557 hrs · 161 cycles
DURING ROUTINE MX (A WEEKLY CHECK) A FAILURE OF THE OVER WING EXIT DOOR EMERGENCY EXIT LIGHT POWER SUPPLY ASSY 11WL, PN 3214-62-10 WAS DISCOVERED BY TECH. THE DEFECTIVE POWER SUPPLY ASSY WAS SUBSEQUENTLY REPLACED. ALL OPS TEST WERE PERFORMED, NO FAULTS WERE NOTED, ACFT WAS RETURNED TO SERVICE.
Part: POWER SUPPLY — FAILED (CABIN)
DURING ROUTINE MX (A WEEKLY CHECK) A FAILURE OF THE OVER WING EXIT DOOR EMERGENCY EXIT LIGHT POWER SUPPLY, 11WL PN 3214-62-10 WAS DISCOVERED BY EHT TECH. THE DEFECTIVE POWER SUPPLY ASSY WAS SUBSEQUENTLY REPLACED. ALL OPS TESTS WERE PERFORMED, NO FAULTS WERE NOTED, ACFT WAS RETURNED TO SERVICE.