N849VA
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.
32 reports on file, 2012-04-07 – 2024-05-03.
Part: LONGERON — DEFORMED (AFT CARGO DOOR) · airframe 35,188 hrs · 11,749 cycles
AFT CARGO DOOR DAMAGED. UPON REMOVING ACCESS PANEL 826AR FOUND LONGERON 5 DEFORMED. GROUNDED - YES. REMOVED AND REPLACED LONGERON ON THE AFT CARGO DOOR IAW A320 SRM 51-42-11 & AIRBUS DWG D52371100 ISSUE AR. DOOR ADJUSTMENT GOOD IAW A320 AMM 52-32-31-400-001-A.
Part: FITTING — NOT REPORTED (FWD CARGO DOOR) · airframe 35,188 hrs · 11,749 cycles
FWD CARGO DOOR LOCK FITTING #4 FROM FWD REQUIRES REPLACEMENT AS A PERMANENT REPAIR GROUNDED - YES. REMOVED AND REPLACED FWD CARGO DOOR LOCK FITTING #4 FROM FWD SIDE PN D5323082200 PO 1080668.1. REMOVED AND REINSTALLED LOCK FITTING COMPONENT IAW A320 AMM 52-31-32-400-001-A. SKIN OFFSET GOOD IAW A320 AMM 52-31-11-820-001-A. FITTING #4 INSTALLED IAW AIRBUS DWG D53231685 ISSUE H AND A320 SRM 51-42-11
Part: SKIN — CORRODED (E/E AIR INLET) · corrosion level 2 · airframe 35,188 hrs · 11,749 cycles
AFT AVIONICS BAY LEFT HAND SKIN AIR INLET VALVE LOCATION, INTERNAL DOUBLER AROUND CUTOUT IS CORRODED GROUNDED - YES. REMOVED AND REPLACED INTERNAL DOUBLER IAW AIRBUS DWG D53113482 AND A320 SRM 51-42-11. NO ALLOWABLE LIMITS FOR AREA. REMOVED AND INSTALLED FILTER HOUSING IAW A320 AMM 21-26-43, REMOVED AND INSTALLED 3 EA STRINGERS AND 2 EA CLIPS IAW AIRBUS DWG D53113482. REMOVED AND INSTALLED DUCT ASSY P/N D5391673600051 IAW A320 SRM 51-42-11. REMOVED AND INSTALLED SKIN AIR VALVE IAW A320 AMM 21-26-52. OPS CHECK PERFORMED IAW A320 AMM 21-26-00, OPS CHECK GOOD. CATEGORY A REPAIR.
Part: DOOR SILL — CORRODED (AFT CABIN) · corrosion level 2 · airframe 35,188 hrs · 11,749 cycles
AFT CABIN R2 DOOR SILL REQUIRES REMOVAL AND REPLACEMENT DUE TO CORROSION REPORTED ON N/R'S 30852 G1898332, 31166 G1898666, AND 31293 G1898793 GROUNDED - YES. R2 DOOR SILL REQ'S REMOVAL AND REPLACE. REMOVED R2 DOOR SILL IAW A320 SRM 51-42-11. RECEIVED NEW DOOR SILL IAW A320 SRM 53-41-69-02-B, P/N D5348004320701, P.O. # 1085519.1, LOCATED AND DRILLED IAW SRM 51-44-11 AND SRM 51-46-11. INSTALLED R2 DOOR SILL IAW A320 SRM 51-72-11-911-001 AND A320 DWG D534 80505 REV AF. REMOVED AND REINSTALLED 2 EA WATER LINES AND 1EA A/C DUCT AT FR 66 IAW A320 AMM 25-43-42-400-001-A, LEAK CHECKS ACCOMPLISHED ON CUSTOMER CARD G1898848 HAECO OPS 31348
Part: SKIN — CONTAMINATED (RUDDER) · airframe 35,188 hrs · 11,749 cycles
TRAPPED WATER INDICATION FOUND: ON R/H SIDE OF RUDDER AT NO. 20 FASTENER LOCATION ADJACENT TO HOIST POINT #3. AREA MARKED IN RED, 6"L X 2.5"W, 5" FWD OF T/E. DOT: B633 GROUNDED - YES. ACCOMPLISHED A PERMANENT REPAIR ON R/H SIDE OF RUDDER AT NO. 20 FASTENER LOCATION ADJACENT TO HOIST POINT #3 BETWEEN REPAIR ZONE W AND ZONE F, RIB 6 IAW A320-200 SRM 55-41-13-300-025 PAR.2.A.FIG 2&3 REV. 147 01-NOV-2023. AIRCRAFT INFORMATION: A320-214, S/N: 4991, WV: 015, F. HOURS: 35187.50, F. CYCLES: 11749. RUDDER P/N: D5547100600000 S/N; TS6598 (REMOVED HAECO DOT)
Part: FLOOR SUPPORT — CORRODED (FRMS 65-66) · corrosion level 2 · airframe 35,188 hrs · 11,749 cycles
AFT WET AERA FLOOR BEAM CORRODED AT FR65-FR66 Y1732 GROUNDED - YES. REMOVED AND REPLACED FLOOR BEAM AT FR65-FR66 Y1732 I..A.W A320 SRM 51-42-11, SRM 51-44-11, SRM 51-46-11 AND AIRBUS DWG# E534 74250 ISSUE: AL PN: D5347207500000, PO# 1083577.1. NO ALLOWABLE DAMAGE LIMITS IN SRM
Part: DOOR SILL — CORRODED (FRM 66) · airframe 35,188 hrs · 11,749 cycles
MULTIPLE CORRODED NUTPLATE HOLES AT L2 DOOR FR66 O/B SIDE AT GIRT BAR ATTATCH PLATE LOCATION GROUNDED - YES. REMOVED AND REPLACED 3EA. NUTPLATES ON L2 DOOR SILL FR66 O/B SIDE AT GIRT BAR ATTATCH LOCATION IAW A320 SRM 51-42-11. REMOVED CORROSION AT 3EA. NUTPLATE HOLES AND HOLE SURFACES AREA, HOLE 1 FINAL DIAMETER SIZE IS .338", HOLE 2 FINAL DIAMETER SIZE IS .338", HOLE 3 FINAL DIAMETER IS .353" AND FOUND 3EA NUT PLATE HOLES AND AREAS TO BE WITHIN THE ALLOWABLE LIMITS IAW SRM 53-41-14-283-002 REV. 147 FIG. 2 SHEET 1 AREA CODE J. THIS IS A CATERGORY A REPAIR. RESTORED AREAS AROUND 3EA NUT PLATES IAW SRM 53-41-14-283-002 REV 147 FIG 1 SHEET 1 PG 3.
Part: SKIN — CORRODED (FUSELAGE) · airframe 35,188 hrs · 11,749 cycles
FUSELAGE SKIN EXTERIOR BETWEEN STR 1L AND 1R, UNDER ADF2 ANTENNA CUTOUT HAS CORROSION AROUND FASTENER HOLE (2EA) AS MARKED. (DOT ATTACHED UNDER TAPE) GROUNDED - YES. BLENDED DAMAGED AREAS, 1) L=1.30", WIDTH=.800", ORIGINAL THICKNESS IS .087" REMAINING=.078", REMOVED=.009". 2) L=1.45", W=1.10", ORIGINAL THICKNESS IS .087", REMAINING= .074, REMOVED=.013". THIS IS A CATERGORY B REPAIR WITH INSPECTION THRESHOLD OF 135,800 FLIGHT CYCLES OR 271,700 FLIGHT HOURS WHICHEVER COMES FIRST. RESTORED FINISH IAW ALASKA EA# A320-53EA-02097 REMOVED DOT
Part: SKIN — DENTED (LT WING TE FLAP) · airframe 35,188 hrs · 11,749 cycles
LEFT FLAP HAS MULTIPLE DENTS BEHIND MAIN WHEELS, MEASURE AND MAP ALL GROUNDED - YES. REPAIRED L/H I/B FLAP T/E WEDGE LOWER SURFACE IN ZONE 2 BY PREFORMING PERMAMENT CORE AND DOUBLER REPAIR IN 2EA AREAS. AREA 1 MEASURES 89.5" FROM I/B EDGE, REPAIR DOUBLER SIZE IS 11.5"L X 14"W, AREA 2 MEASURES 55" FROM I/B EDGE, REPAIR DOUBLER SIZE IS 11.5"L X 14"W IAW A320 SRM 57-52-00-283-105 FIG. 001 SHEET 1, 57-52-00-300-093, 57-52-00-283-106, 51-77-11-911-014, 51-77-911-015 51-77-911-031, 51-75-12 REV 147 - 01 NOV 2023 P/N: D5757065005200, S/N: TB14991 FH: 35187:50 FH: 11749 WV: 015
Part: SKIN — DENTED (RT WING TE FLAP) · airframe 35,188 hrs · 11,749 cycles
RH FLAP HAS MULTIPLE DENTS BEHIND MAIN WHEELS, MEASURE AND MAP ALL. GROUNDED - YES. PREFORMED PERMANT CAT A REPAIR TO R/H FLAP, MULTIPLE DENTS BEHIND MAIN WHEELS. DAMAGE AREA 1 LOCATED 51.3ÿ½ FROM I/B END CUT OUT SIZE WAS 10 X 9 UPPER AND 9.9 X 8.8 LOWER. REPAIR SIZE IS 14 X 12 ON UPPER AND LOWER SKIN. DAMAGE ARE 2 WAS LOCATED 89.7ÿ½ FROM I/Bÿ½ END. CUT OUT SIZE WAS 7.76ÿ½ X 7.27ÿ½ UPPER AND 7.75" X 7.25" LOWER REPAIR SIZE IS 11.75ÿ½ X 11.75ÿ½ UPPER AND LOWER. BOTH AREAS LOCATED IN ZONE 2. IAW EA# CMPT-57EA-02159 AND A320-200 SRM 57-52-00-300-094. A/C INFO: N849VA, FLIGHT HOURS 35187:50, FLIGHT CYCLES: 11749, WV: 015 EA#CMPT-57EA-02159 REV 00.
Part: FLOORBEAM — DENTED (FRM 52) · airframe 35,188 hrs · 11,749 cycles
AFT CARGO PIT, FLOOR BEAM AT STATION 52 DENTED ABOVE STRINGER 42 RH GROUNDED - YES. REMOVED AND REPLACED FLOOR BEAM AT FR.52, P/N D5347057020800 P.O.#1080462.1, IAW AIRBUS DWG. D53470260 ISSUE V AND A320 SRM 51-42-11. REMOVED AND REINSTALLED 2 EA. SPLICE CONNECTIONS AT FR. 52 STR. 41R. IAW A320 SRM 51-42-11.
Part: SHEAR PLATE — CORRODED (FRMS 69-70) · corrosion level 2 · airframe 35,188 hrs · 11,749 cycles
LH SHEAR PLATE AT FR69-70 HAS SPOTS OF CORROSION GROUNDED - YES. REMOVED AND REPLACED AFT WET AREA SHEAR PLATE PN D5347112420200 PO 1080307.1 IAW ASA SRM A320 51-72-11 AND AIRBUS DWG D53474180 REV. U. NO ALLOWABLE LIMITS GIVEN IN ASA A320 SRM.
Part: SHEAR PLATE — CORRODED (FRMS 69-70) · corrosion level 2 · airframe 35,188 hrs · 11,749 cycles
RH SHEAR PLATE AT FR 69-70 HAS SPOTS OF CORROSION GROUNDED - YES. REMOVED AND REPLACED RH SHEAR PLATE AT FR 69-70 IAW AIRBUS DWG D53474180 REV U AND ASA A320 SRM 51-72-11-911-001. NO ADL GIVEN IN SRM.
Part: FLOORBEAM — CORRODED (FRM 66) · corrosion level 2 · airframe 35,188 hrs · 11,749 cycles
LH FLOOR BEAM AT Y765 JUST AFT OF FR66 HAS CORROSION GROUNDED - YES. EVALUATED L/H FLOOR BEAM @ Y765, AFT OF FR66, OUT OF LIMITS IAW A320 SRM 53-41-14-289-009 STEP 1.D DISTANCE FROM CORROSION TO FIRST COUPLING HOLE: .40, MINIMUM ALLOWED : .79. REMOVED AND REPLACED FLOOR BEAM IAW A320 SRM 51-72-11. REMOVED DOT.
Part: DOOR SILL — CORRODED (FRM 66) · corrosion level 2 · airframe 35,188 hrs · 11,749 cycles
L2 DOOR SILL AT FR 66 2 EA NUT PLATE HOLES ARE CORRODED GROUNDED - YES. REMOVED CORROSION IN 3 EA AREAS, FOUND 2 EA OUT OF 3 EA AREAS TO BE OUT LIMITS AT DOOR SILL L/H FR 66 IAW A320 SRM 53-41-14-283-002 REV 147. 1 EA WITHIN LIMIT AREA ORIGINAL MAT'L THICKNESS .098", REMOVED .022", REMAINING .076". REAMED HOLE TO FINAL DIAMETER OF .354" FOUND HOLE AND AREA TO BE WITHIN ALLOWABLE LIMITS IAW A320 SRM 53-41-14-283-002 REV 147 FIG 2 SHEET 1. AREA CODE C. DIAMETER OF BLENDOUT IS 1" X 1". PERFORMED CUTOUT OF 2 EA OUT LIMIT AREAS IAW A320 SRM 53-41-14-300-001 REV 147. ACCOMPLISHED REPAIR PRINCIPLE 9 AND REPAIR PRINCIPLE 11 IAW A320 SRM 53-41-14-300-001 REV 147. THIS IS A CATEGORY A REPAIR. FOR MORE DETAIL INFOMRATION SEE ATTACHED JPD'S. REMOVED HAECO DOT.
Part: FLOORBEAM — CORRODED (FRM 66) · corrosion level 2 · airframe 35,188 hrs · 11,749 cycles
RH FLOOR BEAM AT -Y1292 FR66 HAS CORROSION GROUNDED - YES. EVALUATED R/H FLOOR BEAM @ -Y1292, FR66. ORIGINAL: .100", REMOVED: .031". REMAINING: .069". MAX ALLOWABLE: .016". BLEND MEASURES 2.70" IN LENGTH AND 2.00" IN WIDTH. OUT OF LIMITS IAW A320 SRM 53-41-14-283-009 REV. 147 FIG 1. SHEET 2. REMOVED AND REPLACED FLOOR BEAM IAW A320 SRM 53-41-15-41-A REV. 147. AND SRM 51-72-11 REV. 147. PART# D5347219021900 P.O.#1082156.1 REMOVED DOT
Part: DOOR SILL — CORRODED (FRM 68) · corrosion level 2 · airframe 35,188 hrs · 11,749 cycles
L2 DOOR SILL AT FR68 2EA NUT PLATE HOLES ARE CORRODED GROUNDED - YES. REMOVED CORROSION AT L2 DOOR SILL FR68 2EA. NUT PLATES HOLE AREA CODE A. ORIGINAL MATL. THICKNESS .063", REMOVED .040", REMAINING .023" & FOUND AREA TO BE OUT OF LIMITS IAW SRM 53-41-14-283-002 REV.147 FIG.2 SHEET 1. ACCOMPLISHED FR68 L2 DOOR SILL BEAM REPAIR PRINCIPAL 7 (FR68 FLANGE CUT OUT) IAW SRM 53-41-14-300-001 REV.147 PG.3 AND PG.4. CATEGORY A REPAIR. REMOVED CORROSION AT FR68 DOOR SILL AREA CODE J. ORIGINAL MATL. THICKNESS .177", REMOVED .030", REMAINING .147" AND FOUND BLENDED AREA AT CODE J FR68 DOOR SILL TO BE WITHIN ALLOWABLE LIMITS IAW SRM 53-41-14-283-002 REV.147 FIG.2 SHEET 1. BLEND DIMENSIONS W= .300" L= 1.1". BLEND IS 1.1" AWAY FROM O/B NUTPLATE. CATEGORY A REPAIR RESTORED BLENDED AREA CODE J AT FR68 DOOR SILL IAW SRM 53-41-14-283-002 REV 147 FIG.1 SHEET 1.
Part: FLOOR SUPPORT — CORRODED (FRMS 64-67) · corrosion level 2 · airframe 35,188 hrs · 11,749 cycles
RH FLOOR BEAM AT -Y464 HAS 2 SPOTS OF CORROSION JUST AFT OF FR65 GROUNDED - YES. EVALUATED CORROSION ON R/H FLOOR BEAM @ -Y464, FR64-FR67/68. FOUND TO BE OUT OF LIMITS IAW SRM 53-41-14-283-009, FIG. 2, DUE TO BEING IN AN EXCLUDED AREA. REMOVED AND REPLACED FLOOR BEAM P/N D5347228400800, P.O.# 1082150.1 IAW SRM 53-41-14-20-A REV. 147. AND SRM 51-72-11-911-001 REV. 147. CATEGORY A. REMOVED DOT
Part: FLOORBEAM — CORRODED (FRM 66) · corrosion level 2 · airframe 35,188 hrs · 11,749 cycles
RH FLOOR BEAM AT -Y765 AFT OF FR66 HAS CORROSION GROUNDED - YES. REMOVED CORROSION IAW A320 SRM 53-41-14-283-009. FOUND TO BE OUT OF LIMITS IAW FIG 1/TABLE 001-MAX ALLOWABLE REMOVAL IS .024, REMOVED .050, BLEND AREA MEASURES W=1.0, L=1.0 AND 4.6" FROM AFT AND OF PART. TOOL#: T8493P CAL DUE 02/27/2024. REMOVED AND REPLACED WITH NEW FLOOR BEAM PART #:D5347219021500,PO#: 1080775.1 IAW A320 51-72-11-911-001 REV 147 AND AMM 20-28-00-912-802-A. TOOL# T8119W, CAL DUE: 02/24/24
Part: DOOR SILL — CORRODED (CABIN) · airframe 35,188 hrs · 11,749 cycles
MAIN CABIN, FLOOR STRUCTURE UNDER L-1 DOOR AT AFT GIRT BAR RECIEVER STUDS CORRODED GROUNDED - YES. REMOVED CORROSION ON 3EA FASTENER HOLES ON L1 DOOR SILL. AFT GIRT SHOE/SILL BEAM SURFACE FWD O/B HOLE, L=1.3, W=.900, ORIGINAL THICKNESS .197, REMOVED .020, REMAINING .177. FWD I/B HOLE L=1.3, W=1.3, ORIGINAL THICKNESS .197, REMOVED .021, REMAINING .176. AFT O/B HOLE L=1.6, W=1.3, ORIGINAL THICKNESS .197, REMOVED .028, REMAINING .169 FOUND TO BE WITHIN LIMITS IAW A320 SRM 53-11-14-283-005 REV. 147 FIG 1 SHEET 2. REWORKED AREA TOUCHES ALL 3EA FASTENER HOLES. ACCOMPLISHED SPOTFACE IAW A320 SRM 53-11-14-283-005 REV 197 FIG 1 SHEET 2 O/B FWD HOLE DIAMETER IS .25, DEPTH .025, REMAINING MATERIAL AT SPOTFACE AREA IS .157. O/B AFT HOLE DIAMETER IS .250, DEPTH .030, REMAINING MATERIAL AT SPOTFACE AREA IS .167. INSTALLED 3EA REPAIR WASHERS AND 4EA NEW FASTENERS IAW A320 SRM 53-11-14-283-005 REV 147 FIG 1 SHEET 2. CAT B REPAIR INSPECTION THRESHOLD 60,000 FC/FH
Part: FLOOR SUPPORT — CORRODED (FRM 20-21) · corrosion level 2 · airframe 35,188 hrs · 11,749 cycles
MAIN CABIN, FLOOR BOARD SUPPORT STRUCTURE CORRODED ON TOP AFT OF FRAME STATION 20, AT RIGHT MOST SEAT TRACK UNDER FLOORBOARD 232EF FORWARD LEFT CORNER. GROUNDED - YES. REMOVED CORROSION ON R/H FLOOR BEAM BETWEEN FR20-FR21 Y-1292. (1) AT FR20 L= .750", W= .400", D= .011". (2) 2.5" AFT OF FR20 L= 1.50", W= .400", D= .021". (3) 9.5" AFT OF FR20 L= .900", W= .400", D= .012". ORIGINAL MATL THICKNESS .087", DEEPEST REMOVED .021", REMAINING .066". MAX ALLOWED .012", FOUND TO BE OUT OF LIMITS I.A.W A320 SRM 53-11-15-283-011 REV. 147 FIG. 1. TOOL #T8492H DUE: 12/26/2024 REMOVED AND REPLACED SEAT TRACK/FLOOR BEAM FROM FR12-FR24 Y-1292 I.A.W SRM 51-72-11-911-001 REV. 147. PN: D5311278220200, PO #1082234.1
Part: FLOOR PANEL — CRACKED (AFT CARGO) · airframe 35,188 hrs · 11,749 cycles
(PARTS RACK) AFT PIT FLOOR PANEL 151LF CRACKED GROUNDED - YES. REPAIRED AFT PIT FLOOR PANEL 151LF IAW A320-214 SRM 53-02-000-283-001 SRM 53-02-00-300-004. REPAIR IS LOCATED 18 1/2 FROM AFT TO FWD AND 12 1/2 FROM RIGHT SIDE. FLOOR PANEL IN ZONE 150. REPAIR MEASURES TO BE 1.4" IN DIAMETER AND IS A PERMANENT REPAIR. A/C INFO: N849VA S/N:4991 F/H: 35187:50 F/C: 11749 WV:015
Part: FLOOR PANEL — CRACKED (CABIN) · airframe 35,188 hrs · 11,749 cycles
(PARTS RACK) PANEL 132FF IS CRACKED GROUNDED - YES. REPAIRED FLOOR PANEL 132FF IAW A320-214 SRM 53-02-00-283-001 AND SRM 53-02-00-300-004 AND SRM 51-77-11-911-031. REPAIR IS LOCATED 13.2" FROM FWD END 6.8" FROM UPPER END. FLOOR PANEL IN ZONE B. REPAIR MEASURES TO BE 1" IN DIAMETER AND IS A PERMANENT REPAIR. A/C INFO: N849VA S/N:4991 F/H: 35187:50 F/C: 11749 WV:015
Part: THRESHOLD — CORRODED (AFT CARGO) · corrosion level 2 · airframe 35,188 hrs · 11,749 cycles
AFT CARGO DOOR CUTOUT LOWER THRESHOLD HAS CORROSION IN MULTIPLE SPOTS GROUNDED - YES. REMOVED AND REPLACED THRESHOLD AT AFT CARGO DOOR CUTOUT LOWER PN:D5347560020400 PO:1080693.1 IAW AIRBUS DWG D53475600 ISSUE F AND A320 SRM 51-42-11 REMOVED HAECO DOT:B185
Part: THRESHOLD — CORRODED (FWD CARGO) · airframe 35,188 hrs · 11,749 cycles
FWD CARGO DOOR CUTOUT LOWER THRESHOLD HAS CORROSION GROUNDED - YES. REMOVED CORROSION ON FWD CARGO THRESHOLD IAW A320 SRM 51-23-00. AREA IS FROM AFT EDGE OF DOOR SILL TO 3.7" FWD, FRAME 27A+3" TO 27A+6" ALONG O/B EDGE AREA IS 2.7" W, 3.7" L. REMAINING THICKNESS IS .093", REMOVED .005, ORIGINAL THICKNESS IS .098 AREA IS WITHIN LIMITS IAW A320 SRM 53-21-29-283 FIG #1 ACCOMPLISHED HFEC INSP IAW A320 SRM 53-21-29-283 AND NTM 51-10-08 NO DEFECTS NOTED. RESTORED PROTECTIVE FINISHES IAW A320 SRM 51-21-11 AND 51-75-12. REMOVED HAECO DOT. REMOVED AND REINSTALLED FITTING IAW A320 SRM 51-42-11 AND AIRBUS DWG D53231668 ISSUE C
Part: FLOOR PANEL — CRACKED (CABIN) · airframe 35,188 hrs · 11,749 cycles
FLOOR PANEL 131BF UPPER SKIN CRACKED GROUNDED - YES. REPAIRED FLOOR PANEL 131BF IAW A320-214 SRM 53-02-000-283-001 AND SRM 53-02-00-300-004 AND SRM 51-77-11-911-031. REPAIR IS LOCATED 12.75" FROM AFT END AND 6.25" FROM LOWER END. FLOOR PANEL IN ZONE B. REPAIR MEASURES TO BE 1" IN DIAMETER AND IS A PERMANENT REPAIR. A/C INFO: N849VA S/N:4991 F/H: 35187:50 F/C: 11749 WV:015
Earlier reports · 2012–2019 · 6 reports
2019
Part: FLOOR PANEL — BROKEN (FUSELAGE) · airframe 28,106 hrs · 8,632 cycles
RT FLOOR PANEL 252CF AT FR47- FR51 CORNER BROKEN. GROUNDED - YES. RECEIVED NEW FLOOR PANEL, INSTALLED NEW FLOOR PANEL 252CF ON CUST CARD# 10N01609-3-05 (OPS 2345) COPY ATTACHED.
2017
Part: SHEAR PLATE — CRACKED (FRAMES 69-70)
FOUND A CRACK ON AFT CABIN AREA, RT LATERAL SHEAR PLATE BETWEEN FRAMES 69 - 70. THE SHEAR PLATE WAS R & R IAW SRM 51-42-11.
Part: SHEAR PLATE — CRACKED (FRAMES 69-70)
FOUND A CRACK ON THE AFT CABIN AREA, LT LATERAL SHEAR PLATE BETWEEN FRAMES 69 - 70. SHEAR PLATE WAS R & R IAW SRM 51-42-11.
2013
Part: OVEN — FAILED (GALLEY)
THE CABIN CREW NOTED THE FWD GALLEY OVEN CIRCUIT BREAKER TRIPPED. ITL NOTED SOME SMOKE INSIDE THE OVEN AND RESECURED THE DOOR CLOSED. UPON ARRIVAL TO DESTINATION, MX R & R THE OVEN IAW AMM 25-35-19-000-001A AFTER CONFIRMED BAD. NO FURTHER INCIDENTS HAVE OCCURRED.
Part: WIRE — BROKEN (CABIN) · airframe 3,697 hrs · 1,062 cycles
DURING OPERATIONAL TEST OF THE EMERGENCY LIGHT SYS ROWS 13 & 14 LEFT, FOUND INOPERATIVE. UPON INSPECTION FOUND WIRE BROKEN ON HARNESS FIN 7260VC6, PN 8008-47-70-70. ACFT WAS PLACED OUT OF SERVICE AND HARNESS WAS REPLACED AND NO DELAY ON SCHEDULED FLIGHT INCURRED.
2012
Part: WIRE HARNESS — DAMAGED (CABIN)
ACFT WAS IN FOR ROUTINE OVERNIGHT MX. DURING THE CHECKS FOR EMERGENCY EXIT LIGHTING, IT WAS NOTED THAT THE SEAT MOUNTED PATH LIGHTS ON ROWS 13, 14 AND 15 WERE INOPERATIVE. UPON INSPECTION OF THE HARNESS, A WIRE WAS FOUND SEVERED AT THE FLOOR LEVEL, SEAT ATTACHMENT OF ROW 14. THE HARNESS, PN 8008-47-70-70, WAS REPLACED IAW AMM 33-51-19 AND THE SYS CHECKED, OK. THE ACFT WAS PLACED BACK INTO SERVICE ON 4/7/2012.