N524VA
Registered owner: N524VA TRUST, DE (owner ≠ operator)
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.
31 reports on file, 2011-04-22 – 2019-07-12.
Part: CONTROLLER — FAILED (CABIN PRESSURE) · airframe 37,926 hrs · 14,843 cycles
SYSTEM 1 AND SYSTEM 2 PRESSURE CONTROLLER FAIL. GROUNDED - YES. FOUND CPC 1 INOP. CPC 2 RESET ACCOMPLISHED OK. REPLACED CPC 1 PER AMM 21-31-34. PERFORMED OPERATIONAL TEST PER AMM 21-31-00-710-002. TEST OK. BOTH CPC 1 & 2 TEST OK.
Part: FITTING — CORRODED (GIRT BAR) · corrosion level 2 · airframe 37,910 hrs · 14,833 cycles
R1 DOOR AFT GIRT FITTING CORRODED AT 2EA HOLES. GROUNDED - YES. REPAIRED AREA AT HOLE LOCATIONS IAW SRM 53-11-14. THIS REPAIR IS CATEGORY B TO BE REINSPECTED AT 60,000 FC DOT REMOVED PER ENGENEERING : SRI 5311.000059 HAS BEEN GENERATED FOR STAGE 3 APPROVAL ORIG. 214 REMAINING 196 REMOVED .018.
Part: SKIN — CORRODED (RT WING) · airframe 37,910 hrs · 14,833 cycles
AREA 3 BETWEEN RIBS 18 AND 19 RT WING UPPER SKIN APPROXIMATELY 13% MATERIAL LOSS FOUND USING PHASE ARRAY INSPECTION. MARKED. LOCATIN 3 SHOWN ON NDT REPORTING FORM ATTACHED TO ROUTINE CARD GROUNDED - YES. REPAIRED AREA BETWEEN RIBS 18 AND 19 RT WING UPPER SKIN IAW SRM 57-21-11 AND REPAIR DWG #R572-58998 ORIG THICKNESS .197 REMAINING .159 REMOVED .038 FOR SRI EC WILL VE SRI 5721.000012. THIS REPAIR IS CATEGORY B.
Part: SKIN PANEL — CORRODED (LT WING) · corrosion level 2 · airframe 37,910 hrs · 14,833 cycles
AREA 1 BETWEEN RIBS 20 AND 19 LT WING, UPPER SKIN APPROXIMATELY 15% MATERIAL LOSS FOUND USING PHASE ARRAY INSPECTION, MARKED. LOCATION 1 SHOWN ON MIAMI NDT REPORTING FORM ATTACHED TO ROUTINE CARD. GROUNDED - YES. ACCOMPLISHED REPAIR TO LEFT WING UPPER SKIN T/E BETWEEN RIBS 19 LT AND 20 LT IAW EA : A319-57EA-00016, REV. 01 AND REPAIR DRAWING R572-58616, REV. J. REPAIR IS CATEGORY B AND REQUIRES A DVI AT INSPECTION THRESHOLD OF 48,000 FC AND SUBSEQUENT INSPECTION AT INTERVALS OF 9,000 FC.
Part: SHEAR PLATE — CORRODED (FUSELAGE) · corrosion level 2 · airframe 37,910 hrs · 14,833 cycles
AFT MAIN CABIN LATERAL SHEAR PLATE BETWEEN FRAMES 69 & 70 APPROX: RBL 48 IS CORRODED (FLOOR LEVEL) GROUNDED - YES. REMOVED AND REPLACED LATERAL SHEAR PLATE IAW SRM 51-42-11 & DWG # D53471120. DOT REMOVED (ORIG THK .071, REMAINING 0. CORRODED 100% THRU. 2 " LONG.
Part: DOOR FRAME — CORRODED (FRAME 69) · airframe 37,910 hrs · 14,833 cycles
L2 DOOR CUTOUT, LOWER FWD, UNDER THE FWD GIRT BAR, HAS CORROSION AROUND 2 THRESHOLD ATTACH HOLES (CIRCLED IN RED) GROUNDED - YES. REMOVED CORROSION AND FOUND WITHIN LIMITS IAW A319 SRM 53-41-14. ORIG .098, REMOVED .013, REMAINING .085. ALODINED AND PRIMED IAW A319 SRM 51-21-11. TOPCOATED IAW A319 SRM 51-21-11.
Part: SUPPORT BEAM — CORRODED (FUSELAGE) · corrosion level 2 · airframe 37,910 hrs · 14,833 cycles
L1 DOOR AFT GIRTBAR FITTING SUPORT BEAM CORRODED AT OB ATTACH HOLES GROUNDED - YES. REPAIRED BEAM AT ATTACH HOLES AIW SRM 53-11-14. THIS REPAIR IS CATEGORY B. REPAIR TO BE INSPECTED AT 60,000 FC. REPAIR ASSIGNED SRI EC/TC SRI.5311.000058 FOR FOLLOW UP INSPECTIONS .ORIG .214 REMAINING .145 REMOVED .019
Part: FLOOR SUPPORT — CORRODED (FRAME 66) · corrosion level 2 · airframe 37,910 hrs · 14,833 cycles
MAIN CABIN FLOOR SUPPORT STRUCTURE JUST AFT OF FRAME 66 APPROX RBL56 IS CORRODED GROUNDED - YES. REPAIRED STRUCTURE IAW A319 SRM 53-41-14. DOT REMOVED.THIS IS CATEGORY A REPAIR. ORIGINAL MAT. THICKNESS .098 REMOVED .030 REMAINING .068. OUT OF LIMITS IAW A319 SRM 53-41-14.
Part: FLOOR SUPPORT — CORRODED (FRAME 16) · corrosion level 2 · airframe 37,910 hrs · 14,833 cycles
MAIN CABIN FLOOR SUPPORT STRUCTURE AT FRAME 16 APPROX. RBL 10 IS CORRODED GROUNDED - YES. EVALUATED CORROSION IAW A319 SRM 53-11-14. DAMAGE DEPTH IS 0.037", LENGTH 3.06", WIDTH IS 1.17", FOUND TO BE OUT OF LIMITS. REPAIRED CORRODED FLOOR BEAM SECTION IAW A319 SRM 53-11-14-300-002. SDR ATTACHED
Part: FLOOR SUPPORT — CORRODED (FRAME 16) · corrosion level 2 · airframe 37,910 hrs · 14,833 cycles
MAIN CABIN FLOOR SUPPORT STRUCTURE AT FRAME 16 APPROX. RBL 52 IS CORRODED GROUNDED - YES. EVALUATE CORROSION ON PLATE ASSY IAW A319-111 SRM 53-11-14 AREA FOUND TO BE OUT OF LIMITS. ORIGINAL MATERIAL .55", MATERIAL REMOVED .011, MATERIAL REMAINING .044" REMOVED OLD PLATE ASSY'. FITTED AND INSTALLED NEW PLATE ASSY IAW A319-111 SRM 51-42-11, 51-44-11 AND AIRBUS DWG D53112832 SHEET. 01 REV C.
Part: FLOOR SUPPORT — CORRODED (FRAME 16) · corrosion level 2 · airframe 37,910 hrs · 14,833 cycles
MAIN CABIN FLOOR SUPPORT STRUCTURE AT FRAME 16 APPROX. RBL50 IS CORRODED GROUNDED - YES. REMOVED CORROSION AND EVALUATED IAW A319 SRM 53-11-14. DAMAGE DIMENSIONS: 1.63" LENGTH, 0.5" WIDTH, 0.046" DEPTH, FOUND OUT OF LIMITS. REMOVED AND REPLACED FLOOR BEAM FROM FRAME 12 TO FRAME 24 IAW A319 SRM 51-42-11 AND AIRBUS DWG D53112812, REV. E. SDR ATTACHED.
Part: FLOOR SUPPORT — CORRODED (FRAME 16) · corrosion level 2 · airframe 37,910 hrs · 14,833 cycles
MAIN CABIN FLOOR SUPPORT AT FRAME 16 APPROX. RBL30 IS CORRODED GROUNDED - YES. REMOVED CORROSION AND EVALUATED IAW SRM 53-11-14. DAMAGE FOUND OUT OF LIMITS REMOVED AND REPLACED FLOOR SUPPORT FROM FRAME 12 TO FRAME 24 IAW A319 SRM 51-42-11 AND DWG D53110920, REV D.
Part: SHEAR PLATE — CORRODED (FUSELAGE) · corrosion level 2 · airframe 37,910 hrs · 14,833 cycles
AFT MAIN CABIN LATERAL SHEAR PLATE BETWEEN FRAMES 69 & 70 APPROX. LBL 48 IS CORRODED ( FLOOR LEVEL) GROUNDED - YES. SHEAR PLATE WAS CORRODED 100% THRU (ORIG THK .071 REM. 0) REMOVED DAMAGED SHEAR PLATE, INSTALLED NEW LATERAL SHEAR PLATE PER DWG D53474180002 & SRM 51-42-11.
Part: FLOORBEAM — CORRODED (FRAME 68) · corrosion level 2 · airframe 37,910 hrs · 14,833 cycles
AFT MAIN CAIN FLOOR SUPPORT STRUCTURE AT FRAME 68 APPROX. LBL 48 IS CORRODED GROUNDED - YES. REPAIRED SUPPORT STRUCTURE IAW A319 SRM53-41-14. REMOVED AND REINSTALLED WEB IAW A319 SRM 51-42-11 & DWG # D53480019
Part: FLOOR SUPPORT — CORRODED (FRAME 68) · airframe 37,910 hrs · 14,833 cycles
MAIN CABIN FLOOR SUPPORT STRUCTURE JUST FWD OF FRAME 68 APPROX. RBL52 IS CORRODED GROUNDED - YES. REPAIRED FLOOR SUPPORT IAW A319 SRM 53-41-14
Part: FLOOR SUPPORT — CORRODED (FRAME 66) · corrosion level 2 · airframe 37,910 hrs · 14,833 cycles
MAIN CABIN FLOOR SUPPORT STRUCTURE JUST AFT OF FRAME 66 APPROX. RBL30 IS CORRODED GROUNDED - YES. REMOVED AND REPLACED SEAT TRACK SECTION IAW AIRBUS DWG 185D53472201, 18D53472040, 18D53472209, AND 17D534724660
Part: COMPARATOR — FAILED (BLEED AIR SYS) · airframe 37,325 hrs · 14,469 cycles
ENGINE 2 BLEED FAULT - PACK 2 TEMP HIGH, GROUNDED - YES. R&R BMC NR 2 REF LP 1213095 ITEM 1. PERFORMED OPERATIONAL TEST OF THE BLEED AIR SYS REF AMM 36-11-00-710-003-A. OPS TEST CHECK NORMAL . NO FAULTS NOTED.
Earlier reports · 2011–2016 · 14 reports
2016
Part: POWER SUPPLY — MALFUNCTIONED (FLT CONTROLS)
DIVERTED DUE TO A FLT CONTROL SEC 3 FAULT. RESET SEC 3 POWER SUPPLY CIRCUIT BREAKER IAW TSM 24-00-00-81-08-18. ACFT OK FOR SERVICE. NO RECENT HISTORY OF SEC 3 PROBLEMS HAS BEEN NOTED ON THIS ACFT.
2013
Part: HMU — MALFUNCTIONED (ENGINE) · airframe 21,739 hrs · 7,947 cycles
DURING CRUISE, CREW RECEIVED NR 1 ENGINE, NR 2 ENGINE OVER LIMIT ECAM EMESSAGE WITH ASSOCIATED FUEL CONTROL FAULT AND HMU, FMV, ENGINE 1A, 1B, CREW FOLLOWED SHUTDOWN PROCEDURE FOR NR 1 ENGINE AND SENT ACARS MESSAGE TO DISPATCH WITH MSG " ENGINE 1 PRECAUTION SHUTDOWN, DIVERTING, ETA 10 MIN. DISPATCHER ADVISED MCC AND ACFT LANDED AT DIVERSION AIRPORT WITHOUT DECLARING AN EMERGENCY. ONCE ON THE GROUND, MAINTENANCE CONTROL REQUESTED FADEC TEST AND N2 MAX VALUE WAS RECORDED AT 106.7 PERCENT FOR 82 SECONDS. AMM REF 72-00-00-200-008-A, CORE ENGINE, N2, OVERSPEED INSPECTIONS: IF CORE ENGINE SPEEDS EXCEEDS 105.8 PERCENT, SHUTDOWN, REMOVE ENGINE AND RETURN TO SHOP FOR OVERSPEED INSPECTIONS. CONTINUITY CHECKS PERFORMED ON HMU AND ECU IAW TSM 73-10-00-810 AND ECU CHECKS WERE OUT OF LIMITS WITH J8 CONTINUITY PIN 27 AND 28 TO GROUND OPEN. UPDATE: 4/23/2014: THE FMV WENT FULL OPEN AS THE DFDR RECORDED A CHB COMMAND/POSITION FAULT. THERE WERE NO LATCHED ELECTRICAL FAULTS. AFTER THOROUGH INVESTIGATION OF THE HMC AND FADEC, CFM IS UNABLE TO CONFIRM ANY CAUSE OF THE FMV MALFUNCTION. THEY DO NOT EVEN SUGGEST ANY LIKELY OR PROPOSED CAUSE. THIS WAS A LOTC EVENT. THIS INVESTIGATION SEEMS TO INDICATE THA THE ENGINE DOES NOT MEET THE DESIGN REQUIREMENTS OF THE 14 CFR 33.28, D, 2.
Part: ENGINE — MALFUNCTIONED (NR 1) · airframe 21,739 hrs · 7,947 cycles
DURING CRUISE, RECEIVED NR 1 ENGINE N2 ENGINE OVER LIMIT ECAM MESSAGE WITH ASSOCIATED FUEL CTL FAULT AND HMU, FMV, ENGINE 1A, 1B. SHUTDOWN NR 1 ENGINE, DIVERTED. ACFT LANDED WITHOUT DECLARING AN EMERGENCY. FADEC TEST AND N2 MAX VALUE WAS RECORDED AT 106.7 PERCENT FOR 82 SECONDS IAW AMM 72-00-00-200-008-A, CORE ENGINE, N2, OVERSPEED. REMOVE ENGINE. CHECKS PERFORMED ON HMU AND ECU IAW TSM 73-10-00-810 AND ECU CHECKS WERE OUT OF LIMITS WITH J8 CONTINUITY PIN 27 AND 28 TO GROUND OPEN. ENGINE R & R.
Part: SUPPORT — CORRODED (FUSELAGE)
LEFT LATERAL SHEAR PLATE SUPPORT BETWEEN ST23L-ST24L, FR69-FR70 HAS CORROSION BEYOND SRM LIMITS. EXTENT OF DAMAGE: 2"L X 2" W, X .020 D. LT SHEAR PLATE SUPPORT WAS R & R IAW SRM 51-42-11.
Part: FLOORBEAM — CORRODED (CABIN)
CABIN FLOORBEAM AT FR66, Y765 HAS CORROSION BEYOND SRM LIMITS. FLOORBEAM WAS FABRICATED IAW DWG D6347220. INSTALLED IAW SRM 51-42-11.
Part: BEAM — CORRODED (FUSELAGE)
RIGHT AFT DOOR SILL BEAM HAS TWO AREAS OF CORROSION BETWEEN FR66-FR68, ST23R-ST24R AT Y1725. REPAIRED IAW SRM 53-41-14, FIG 201, SHEET 3, (K) REPAIR.
Part: FLOOR SUPPORT — CORRODED (CABIN)
FLOOR SUPPORT AT FR68, Y512.5 HAS CORROSION BEYOND SRM LIMITS. FLOOR SUPPORT FR 67-70 AT Y512.5 R & R IAW SRM 51-42-11.
Part: SHEAR PLATE — CORRODED (CABIN)
LEFT LATERAL SHEAR PLATE BETWEEN S23-24L, FR 69-70 HAS CORROSION BEYOND SRM LIMITS. LT SHEAR PLATE WAS R & R IAW SRM 51-42-11.
Part: FLOOR SUPPORT — CORRODED (CABIN)
FLOOR SUPPORT AT FR66-68, Y765 HAS CORROSION BEYOND LIMITS. FLOOR SUPPORT FR66-70 R & R IAW SRM 51-42-11.
Part: FLOOR SUPPORT — CORRODED (CABIN)
FLOOR SUPPORT AT FR16, Y1292 HAS CORROSION BEYOND SRM LIMITS. FLOOR SUPPORT R & R IAW SRM 51-42-11.
Part: FLOOR SUPPORT — CORRODED (FR66-FR70 ATY765)
CABIN FLOOR SUPPORT AT FR68, Y65 HAS CORROSION BEYOND SRM LIMITS. FLOOR SUPPORT R & R IAW SRM 51-42-11.
Part: FLOOR SUPPORT — CORRODED (CABIN)
FLOOR SUPPORT AT FR68, Y1162 HAS CORROSION BEYOND SRM LIMITS. FLOOR SUPPORT FR68-69 WAS R & R IAW SRM 51-42-11.
2011
Part: GUST LOCK — MALFUNCTIONED (R1 DOOR)
DURING GROUND SERVICING OF THE ACFT ON A TURN, THE CATERING CREW NOTED THAT THE R1 DOOR GUST LOCK (DOOR STAY) MECHANISM DID NOT ENGAGE AND AND NOTIFIED THE CAPT. THE CAPT NOTIFIED OPS OF THE ISSUE, WHO IN TURN, CALLED OUT MX. THE TECHS CARRIED OUT A NORMAL OPENING AND CLOSING OF THE R 1 DOOR IAW AMM 52-10-00 WITH NO FINDINGS OF ANY FAILURE. THE DOOR STAY LOCK MECHANISM OPERATED NORMALLY WITH NO MX ACTION REQUIRED. ITEM WAS CLEARED ON LOG PAGE 558348. THE ACFT WAS PLACED BACK IN SERVICE AND DEPARTED AS FLIGHT 260, AFTER A : 07 MINUTE DELAY. NO FURTHER ISSUES WITH THIS DOOR HAVE BEEN NOTED. ACCORDING TO THE OPERATORS RECORDS, ALL AD`S, SB, STC`S AND PMA`S ARE IN FULL COMPLIANCE WITH THE TYPE DESIGN CERTIFICATE AND ASSOC REQUIREMENTS.
Part: BUSHING — OUT OF ALIGNMENT (MAIN ENTRY DOOR)
DURING GROUND SERVICING OF THE ACFT THE CATERING CREW NOTED THAT THE R1 DOOR GUST LOCK (DOOR STAY) MECHANISM WAS NOT ENGAGING AND NOTIFIED THE CAPTAIN. THE CAPT NOTIFIED MX CONTROL ABOUT THE ISSUE AT 1930Z. MX WAS CALLED. UPON INSP, FOUND THE GUST LOCK RELEASE BUTTON HAD NO MECHANICAL TENSION. GUST LOCK MECHANISM ACCESS COVER REMOVED FOR ACCESS. THE BUSHING THAT ALIGNS THE PLASTIC PLUNGER BUTTON WAS FOUND MIGRATED FROM ITS NORMAL POSITION. THE BUSHING WAS INSPECTED AND REPOSITIONED INTO ITS CORRECT ALIGNMENT. THE DOOR STAY LOCK MECHANISM OPERATED NORMALLY IAW AMM 52-11-12. AIRCRAFT WAS PLACED BACK IN SERVICE AND DEPARTED AFTER A 2.15 DELAY. NO FURTHER ISSUES WITH THIS DOOR HAVE BEEN NOTED. 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 REQUIREMENTS.