N852VA
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.
21 reports on file, 2012-04-21 – 2024-01-28.
Part: FRAME — CORRODED (FRM 86) · corrosion level 2 · airframe 35,282 hrs · 11,814 cycles
LESSOR ITEM A659:APU UNDER EXHAUST ACCESS FAIRING AT FRAME #86 LH LOWER SIDE FOUND WITH SIGN OF CORROSION AT 7 OCLOCK POS. GROUNDED - YES. CUT OUT CORRODED SECTION OF FRAME 5.375"L X 2.0"W. FABRICATED, LOCATED, AND DRILLED REPAIR PARTS. ALODINED, PRIMED, AND PAINTED REPAIR PARTS. INSTALLED REPAIR PARTS IAW A320 SRM 53-51-12-300-001 FRAME 86 REPAIR REV.147 DATED 11/01/2023. THIS IS A CATEGORY A REPAIR.
Part: SKIN — CORRODED (FUSELAGE) · corrosion level 2 · airframe 35,282 hrs · 11,814 cycles
AFT AVIONICS BAY AT SKIN AIR INLET VALVE LOCATION, INTERNAL DOUBLER AROUND CUTOUT CORRODED. GROUNDED - YES. NO ALLOWABLE DAMAGE FOR AREA. CORROSION LOCATION ON FLANGE AT 2 LOWER FORWARD HOLE LOCATIONS 3.5"L X .5"W. LOCATED, DRILLED AND DEBURRED P/N D5311362220001 P.O. 1080752.1 IAW A320 SRM 51-44-11 AND AIRBUS DWG#D53113452. REMOVED AND REPLACED REINFORCMENT IAW A320 SRM 51-72-11, A320 SRM 51-42-11 AND AIRBUS DWG #D53113482. REMOVED AND INSTALLED STRINGER CLIPS AT 532L & 534L IAW A320 SRM 51-42-11 AND AIRBUS DWG #D53113482. REMOVED AND INSTALLED 3EA STRINGERS 531L AND 535L @FR22 IAW A320 SRM 51-42-11 AND AIRBUS DWG #D53113482. CATEGORY A.
Part: SUPPORT — CORRODED (FRMS 69-70) · corrosion level 2 · airframe 35,282 hrs · 11,814 cycles
MAIN CABIN FRAME SUPPORT BETWEEN FR69 TO FR70 CORRODED. GROUNDED - YES. REMOVED AND REPLACED CORRODED LH FRAME SUPPORT S23L BETWEEN FR69-FR70 WITH NEW FRAME SUPPORT, PART # D5347112320200, PO: 0, IAW ASA A320 AIPC 53-41-17-01-A, A320 DWG D53474180 AND SRM 51-742-11 AND A320 DWG D53400019 (NO ALLOWABLE DAMAGE GIVEN IN A320 SRM). REMOVED CORROSION, LENGTH = 1", WIDTH = 1", DEPTH REMOVED = 0.019" FOUND TO BE BEYOND NEGLIBLE DAMAGE LIMTIS OF 0.004". CAT "A" PERMANENT REPAIR
Part: SUPPORT — CORRODED (FRMS 69-70) · corrosion level 2 · airframe 35,282 hrs · 11,814 cycles
MAIN CABIN R/H FRAME SUPPORT CORRODED BETWEEN FR69 TO FR70 S23R GROUNDED - YES. NO ALLOWABLE LIMITS GIVEN FOR FRAME SUPPORT P/N D5347112320300 IN THE A320 SRM ADL SPIFIC 100% MATERIAL LOSS, REMOVED AND REPLACED MAIN CABIN R/H FRAME SUPPORT BETWEEN FR 69 TO FR 70, S23R IAW A320 SRM 51-72-11, 51-42-11, AND AIR BUS DWG D53474180. P/N D5347112320300 PO: 1079528.1
Part: FLOOR PANEL — PUNCTURED (NOT REPORTED) · airframe 35,282 hrs · 11,814 cycles
LESSOR ITEM A527:CABIN FLOOR PANEL 261DF HAS A PUNCTURE LOCATED AT 8.5IN FROM THE AFT EDGE AND 7IN FROM THE RH EDGE. GROUNDED - YES. REPAIRED FLOOR PANEL 261DF P/N E5367175500000 S/N:NSN ON A320-214 S/N 5004 FH 35282:14 FC 11814 WV 015 1EA PUNCTURE USING A PERMANENT CATEGORY A REPAIR IAW A320-200 SRM 53-02-00-283-001 TABLE 002 REV 147 -01NOV2023, A320-200 SRM 53-02-00-300-001 REV 147 -01NOV2023 AND A320-200 SRM 51-77-11-911-031 REV 147 - 01NOV2023. REPAIR AREA DIA 0.7" LOCATED 8.5" FROM FWD EDGE AND 7" FROM RT EDGE
Part: FLOOR PANEL — PUNCTURED (CABIN) · airframe 35,282 hrs · 11,814 cycles
LESSOR ITEM A529:CABIN FLOOR PANEL 251HF HAS A PUNCTURE AT 11.5IN FROM THE FWD EDGE, AND 6IN FROM THE LH EDE. GROUNDED - YES. REPAIRED FLOOR PANEL 251HF P/N SB2060-117 S/N:NSN ON A320-214 S/N 5004 FH 35282:14 FC 11814 WV 015 1EA PUNCTURE USING A CATEGORY A PERMANENT REPAIR IAW A320-200 SRM 53-02-283-001 TABLE 002 REV 147 - 01NOV2023, A320-200 SRM 53-02-00-300-001 REV 147 - 01NOV2023 AND A320-200 SRM 51-77-11-911-031 REV 147 - 01NOV2023. REPAIR AREA 1 IS 1.2" LONG X 0.5" WIDE LOCATED 11.25" FROM FWD EDGE AND 5.5" FROM LEFT EDGE
Earlier reports · 2012–2023 · 15 reports
2023
Part: SKIN — DENTED (RT TE FLAP) · airframe 35,282 hrs · 11,814 cycles
LESSOR ITEM A214: RH WING, INBOARD FLAP LOWER SKIN WITH PREVIOUS REPAIR BEHIND #4 WHEEL AREA GROUNDED - YES. REPAIRED DENTS ON RH WING I/B FLAP TE WEDGE LOWER SKIN BEHIND #4 WHEEL AREA IAW A320-200 SRM 57-52-00-300-091. THIS IS A CATEGORY A PERMENANT REPAIR RH -35282:14 FC -11814 WV- 015
Part: SKIN — DENTED (RT TE FLAP) · airframe 35,282 hrs · 11,814 cycles
LESSOR ITEM A215: RH WING, INBOARD FLAP LOWER SKIN WITH SEVERAL DENTS LOCATED BEHIND #4 WHEEL AREA GROUNDED - YES. REPAIRED DENTS ON RH WING IB FLAP TE WEDGE LOWER SKIN BEHIND #4 WHEEL AREA IAW A320-200 SRM 57-52-00-300-091. THIS IS A CATEGORY A PERMENT REPAIR . FH -35282:14 FC-11814 WV -015
Part: SKIN — DENTED (RT TE FLAP) · airframe 35,282 hrs · 11,814 cycles
LESSOR ITEM A211: RH WING, INBOARD FLAP LOWER SKIN WITH SEVERAL DENTS LOCATED BEHIND WHEEL #3 AREA. GROUNDED - YES. REPAIRED DENTS ON RH WING IB FLAP TE WEDGE LOWER SKIN AFT OF #3 WHEEL IAW A320-200 SRM 57-52-00-300-091. THIS IS A CATEGORY A PERMENANT REPAIR.FH - 35282:14 FC -11814 WV-015
Part: NUT PLATE — CORRODED (L2 DOOR SILL) · corrosion level 2 · airframe 35,282 hrs · 11,814 cycles
L2 DOOR SILL AFT NUTPLATES FR68 LOCATION CORRODED GROUNDED - YES. ACCOMPLISHED REPAIR PRINCIPLE 5 AT L2 DOOR SILL NUT PLATE LOCATIONS FR68 LBL Y1732 STR 23L IAW ASA A320 SRM 53-41-14-300-001 FIG 1 SHEET 3 VIEW H. CAT A REPAIR. REMOVED CORROSION AT 2 EA NUT PLATE LOCATIONS IAW ASA A320 SRM 51-74-00 AND 53-41-14-283-002 AND FOUND TO BE OUT OF LIMITS. ORIGINAL THICKNESS .063" MATERIAL LOSS OF 100%
Part: NUT PLATE — CORRODED (R2 DOOR SILL) · corrosion level 2 · airframe 35,282 hrs · 11,814 cycles
R2 DOOR SILL FR68 NUTPLATE LOCATION CORRODED GROUNDED - YES. REPAIRED R2 DOOR SILL AT FR68, S23R, -Y1732 IAW A320 SRM 53-41-14-300-001 REPAIR PRINCIPLE 7. (REMOVED CORROSION AT FR68 DOOR SILL AREA K, ORIGINAL MATERIAL 0.374", REMOVED 0.051" REMAINING MATERIAL 0.323", FOUND AREA TO BE WITHIN LIMITS IAW A320 SRM 53-41-14-283-002, REMOVED CORROSION AT FR68 DOOR SILL NUT PLATES AREA CODE A, ORIGINAL MATERIAL 0.063, REMOVED 0.050", REMAINING MATERIAL 0.013", FOUND TO BE OUT OF LIMITS IAW A320-200 SRM 53-41-14-283-002.) CATEGORY A REPAIR
Part: SHEAR PLATE — CORRODED (FRMS 69-70) · corrosion level 2 · airframe 35,282 hrs · 11,814 cycles
AFT WET AREA RH SHEAR PLATE CORRODED FR69-FR70 GROUNDED - YES. AFT WET AREA RH SHEAR PLATE, NO ALLOWABLE DAMAGE LIMITS GIVEN IN THE A320 SRM, REMOVED AND REPLACED P/N D5347112420300, PO: 1077802.2 SHEAR PLATE IAW A320 SRM 51-72-11 AND 51-42-11.
Part: SHEAR PLATE — CORRODED (FRMS 69-70) · corrosion level 2 · airframe 35,282 hrs · 11,814 cycles
AFT WET AREA LH SHEAR PLATE CORRODED FR69-FR70 GROUNDED - YES. REMOVED AND REPLACED AFT WET AREA L/H SHEAR PLATE IAW ASA A320 DWG D53474180 AND SRM 51-42-11 NO ALLOWABLE LIMITS GIVEN IN ASA A320 SRM
Part: SKIN — DAMAGED (LT ELEVATOR) · airframe 35,282 hrs · 11,814 cycles
LESSOR ITEM A043: LH ELEVATOR, UPPER SURFACE, 20 IN APPROX FROM INBOARD EDGE WITH PREVIOUS REPAIR, PLEASE PROVIDE THE DOCUMENTATION GROUNDED - YES. PERFORMED A CATEGORY A PERMANENT REPAIR TO LEFT HAND ELEVATOR UPPER SKIN BY REMOVING PREVIOUS REPAIR, FOUND TO HAVE A DEEP SCRATCH AND DELAMINATION AND PERFORMING A NEW SKIN REPAIR WITH NEW DOCUMENTATION. THE REPAIR IS A CIRCULAR SHAPE, 11" FORE TO AFT, 12" WIDE, LOCATED 3" AFT OF THE FORWARD EDGE, 24.5" FROM THE TRAILING EDGE, AND 22" FROM THE INBOARD EDGE. THE REPAIR IS LOCATED ACROSS ZONES 1-A AND 2-G. THE REPAIR WAS ACCOMPLISHED IAW A320-200-SRM-55-21-11-283-013 TABLE 001, SRM -55-21-11-300-037, AND SRM -55-21-11-300-041 REV 147-11/01/2023. A/C TYPE:A320-214, A/C SN:5004, AC FC: 11,814,A/C FH: 35,282:14 A/C WEIGHT VARIANT:WV 015. HEACO DOT A043 REMOVED
Part: SKIN — DAMAGED (LT WING TE FLAP) · airframe 35,282 hrs · 11,814 cycles
LESSOR ITEM A087:LH OUTER FLAP WITH PREVIOUS REPAIR ON THE TRAILING EDGE TO 16IN APPROX FROM THE OUTBOARD EDGE. PLEASE PROVIDE THE DOCUMENTATION GROUNDED - YES. REPAIR L/H OUTER FLAP ON THE T/E 16" FROM THE OUTBOARD EDGE. FINAL REPAIR MEASURMENT CUT OUT OF THE LOWER SKIN WAS 3" X .8" FINAL DOUBLER SIZE OF THE LOWER SKIN 7" X 3" AND FINAL SIZE OF UPPER DOUBLER 11.56" X 5.4" REPAIR AREA PANT MARK. F/H: 35282;14, F/C: 11814 W/V: 015. IAW A320-200, SRM 51-11-12, SRM 57-53-00-300-119 ZONE 2, SRM 57-53-00-300-121 NTM PART 6 51-10-08, NTM 51-90-00 EA EMPT-57EA-02089-, REV 00 REV DATE 04-05-2024 DOT A087 REMOVED
Part: THRESHOLD — CORRODED (AFT CARGO) · corrosion level 2 · airframe 35,282 hrs · 11,814 cycles
AFT CARGO DOOR FWD CUTOUT LOWER SILL THRESHOLD CORRODED AROUND FASTENER HOLE. GROUNDED - YES. REMOVED CORROSION ON AFT CARGO DOOR LOWER THRESHOLD, STA. 24028 - STA.. 2162, STR. 38R TO STR.39R, Z-1647 TO Z-1647. ORIGINAL THICKNESS .100", MATERIAL REMOVED IS .022", EMAINING MATERIAL IS .078". MAXIMUM REWORK DEPTH ALLOWED .016", MINIMUM REMAINING MATERIAL ALLOWED IS .083", FOUND TO BE OUT OF LIMITS IAW A320SRM 53-41-49-283-003. EMOVED AND REPLACED THRESHOLD IAW AIRBUS DWG D53475500 ISSUE BV & A320 SRM 51-42-11. P/N D5347557525800 P.O.#1077139.1.
Part: STATIC PORT — CORRODED (FUSELAGE) · corrosion level 2 · airframe 35,282 hrs · 11,814 cycles
LH F/O AND LH CAPT STATIC PORTS WITH SIGNS OF CORROSION AROUND THE HOLES GROUNDED - YES. REMOVED AND REPLACED LH STATIC PORT REINFORCEMENT IAW A320-SRM-51-72-11, AIRBUS DWG: D53113482. OPS CHECK GOOD IAW A320-AMM-30-31-00-210-001-A. PROTECTIVE COATINGS WILL BE APPLIED ON CUSTOMER CARD #G1873820
2022
Part: SLIDE — DAMAGED (R-1 DOOR) · airframe 33,254 hrs · 10,965 cycles
R-1 DOOR SLIDE RUBBING ON DOOR THRESHOLD GROUNDED - YES. REMOVED, REPLACED AND OPS CHECK R-1 DOOR ESCAPE SLIDE IAW A320 AMM 25-62-44-000-802-A & AMM 25-62-44-400-802-A
Part: SLIDE — OVERSERVICED (L-1 DOOR) · airframe 33,254 hrs · 10,965 cycles
L-1 DOOR SLIDE OVERSERVICED GROUNDED - YES. REMOVED AND REPLACED AND PERFORMED OPS CHECK OF THE L-1 DOOR SLIDE IAW A320 AMM 25-62-44-000-002-A & AMM 25-62-44-400-006-A
2015
Part: UNKNOWN — ODOR (CABIN) · airframe 12,271 hrs · 3,621 cycles
ACFT ARRIVED AT DESTINATION WITH A REPORT OF VERY STRONG ELECTRIC/PLASTIC BURNING ODOR OVER 2D, 2F. ODOR DISIPATED AFTER IFE SHUTDOWN. THE ACFT WS INSPECTED BY MAINTENANCE AND NO DEFECTS WERE NOTED. IFE SYSTEM WAS INSPECTED REF TBN 4430-04 WITH NO DEFECTS NOTED. PERFORMED TROUBLESHOOTING IAW TSM 05-50-00-810-831-A. COULD NOT DUPLICATE ODOR ANYWHERE IN THE CABIN. PERFORMED ENGINE IDLE RUN FOR 5 MINUTES WITH BOTH PACKS AND ALL BLEEDS ON. ALL CABIN ODOR NORMAL. OK FOR SERVICE, MCC NOTIFIED. NO FURTHER PROBLEMS REPORTED ON SUBSEQUENT FLIGHTS.
2012
Part: CONTACTOR — MALFUNCTIONED (FUEL SYSTEM)
ACFT DEPARTED, CREW SEN ACARS AT 21:24Z WITH INFORMATION THAT CENTER FUEL TANK PUMPS WERE INOPERATIVE. AFTER CONFIRMING PUMPS NOT OPERATION IN AUTO OR MANUAL MODE, REFERRED CREW TO FCOM. CREW DIVERTED ACFT, CONFIRMED BREAKERS NOT TRIPPED AND PLACED PUMPS ON MEL. ACFT DEPARTED AND CONTINUED FLIGHT. DURING T/S FOUND GFI CONTACTORS FIN 69QA & 70QA. RESET THESE AND OPS CHECKS GOOD IAW 28-21-00-710-001A AND MEL CLEARED REF LP 675209. COMPLIED WITH FOLLOW UP ENGINEERING REQUEST FOR MX ACTION IAW ASM 28-21-03, SHEET 3 AND NO DEFECTS NOTED.