N637VA
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.
37 reports on file, 2011-08-30 – 2023-11-01.
Part: SKIN — DENTED (LT TE FLAP) · airframe 44,946 hrs · 14,453 cycles
LESSOR ITEM 262: DB #10 2012 HISTORIC DEFECT LEFT INNER FLAP, LOWER EDGE, HAS NUMEROUS DENTS DISCREPANCY: REPAIR NOT SPECIFIED AND NO NDT RECORDED REQUIRED ACTION: PLEASE RE-VAL FOR LOC, DIMS & NDT - ATTACH SRM REF GROUNDED - YES. EVALUATED L/H I/B FLAP LOWER SKIN DENTS ON ZONE 2 AT RIB 5 & 7 LOCATIONS, 20 EA DENTS MEASURED & LOCATED, DENTS 1 & 12 WERE REPAIRED BY APPLYING FILLER, ALL OTHER DENTS FOUND TO BE WITHIN ALLOWABLE LIMITS WITH NO FURTHER ACTION REQUIRED IAW A320 SRM: 57-52-00-283-106, 57-52-00-300-091, 51-77-11-911-023, 51-77-11-911-031, 51-23-11 & NTM PT 6 51-10-08; ALL DENTS SMOOTH, NO CRACKS, CREASE, GOUGES OR DELAMS, YELLOW DOT APPLIED. SEAMC STEVE NOTIFIED, CONTROL # 09034637 REMOVED SURFACE FINISH ON L/H I/B FLAP LOWER SKIN AT RIB 5 & RIB 7 ON ZONE 2, FOUND A TOTAL OF 20 EA DENTS: DENT #1 L=1", D=.03", 49.5" FROM I/B EDGE, 10" FROM T/E; DENT #2 L=.6", D=.009", 54.5" FROM I/B EDGE, 9.5" FROM T/E; DENT 3 L=.5", D=.005", 53" FROM I/B EDGE, 8.5" FROM T/E; DENT 4 L=1", D=.007", 52" FROM I/B EDGE, 7" FROM T/E; DENT 5 L=.8", D=.007", 52" FROM I/B EDGE, 5.75" FROM T/E ;DENT 6 L=.5", D=.006", 50" FROM I/B EDGE, 5.25" FROM T/E; DENT 7 L=.6", D=.007", 50" FROM I/B EDGE, 1.5" FROM T/E; DENT 8 L=.6, D=.008", 51.75" FROM I/B EDGE, .75" FROM T/E; DENT 9 L=.5", D=.012", 54" FROM I/B EDGE, 3.5" FROM T/E; DENT 10 L=.7", D=.018", 55.5" FROM I/B EDGE, 2" FROM T/E; DENT 11 L=.6", D=.009", 56.5" FROM I/B EDGE, 1" FROM T/E; DENT 12 L=.6", D=.025", 95" FROM I/B EDGE, 8.5" FROM T/E;
Part: RIB — CORRODED (UNKNOWN) · corrosion level 2 · airframe 44,946 hrs · 14,453 cycles
FOUND CORROSION ON LH WING INBD FLAP UNDER SEAL RETAINER ON INBD SUPPORT RIB. GROUNDED - YES. COMPLIED WITH EA # CMPT-57EA-01989 REV: 00 TITLE: LH WING INBOARD FLAP, RIB1 ASSEMBLY LOWER FLANGE OUTER LOWER SURFACE CORROSION DAMAGE - REPAIR CATEGORY A
Part: SKIN — CORRODED (UNKNOWN) · corrosion level 2 · airframe 44,946 hrs · 14,453 cycles
FOUND CORROSION UNDER AFT DRAIN MAST GROUNDED - YES. REMOVED DAMAGE ORIG .063, MATERIAL LOSS .006, REMAINING .057 FOUND TO BE OUT OF LIMITS THIS IS AN EXCLUDED AREA, REF A320 SRM 53-41-11-283-065 REMOVED DAMAGE, HFEC , DVI NO DEFECTS NOTED. FABRICATED, LOCATED, DRILLED, INSTALLED REPAIR, RESTORED COATINGS, FORMED DOUBLER, REF A320 SRM 53-41-11-300-018 REPAIR LOCATED BETWEEN FR 67 AND FR69 STR 39R TO STR 36R WL-Z1500 DIA 8.0X13.0 THIS IS A CAT A REPAIR NO FURTHER ACTION REQUIRED PO 1058042.1 PO 1061378.2
Part: SKIN — CORRODED (UNKNOWN) · corrosion level 2 · airframe 45,000 hrs · 14,477 cycles
LESSOR ITEM 203; (66163) LH WING - I/BD FLAP. I/BD AFT CORNER- EVIDENCE OF CORROSION. (L201) GROUNDED - YES. ACCOMPLISHED PERMANENT CLASS A REPAIR OF LH WING INBRD FLAP AFT LOWER CORNER ON ASA A320-214 S/N 346, WV10, FH 45004:12, FC 14478 IAW ASA A320 EA# CMPT-57EA-01974 AND SRM 57-52-00-300-095, REMOVED DAMAGE ORIG .024, MATERIAL LOSS .015, REMAINING .009 NO LIMITS GIVEN IN SRMREF A320 SRM 51-74-00/001, CUT OUT DAMAGE , HFEC NO DEFECTS NOTED. FABRICATED REPAIR, INSTALLED, AND RESTORED COATINGS REF ASA EA CMPT-57EA-01974 REV 00 THIS IS A CAT A REPAIR NO FURTHER ACTION REQUIRED.
Part: SKIN — CORRODED (UNKNOWN) · airframe 44,946 hrs · 14,453 cycles
LESSOR ITEM 234; (66991) RH WING - UPPER SURFACE. CORROSION SPOT AT RIB 14 L/E GROUNDED - YES. REMOVED DAMAGE LOCATION 1 ORIG .160, MATERIAL LOSS .001, REMAING .159 LOCATION 2 ORIG .160, MATERIAL LOSS .001, REMAINING .159. LOCATION AT RIB 14 AT STR 9R STA 7792 DIAMETIONS 1.5 X 1.5 FOR BOTH AREAS. REMOVED AND REPLACED FASTENERS 2EA. REMOVED AND REINSTALLED 2EA FUEL PANELS. LEAK CHECK GOOD REF A320 SRM 57-21-11-283-014 AND 51-42-11/001 AND AMM 57-27-11-000-002-A AND 57-27-11-400-002-A. THIS IS A CAT A REPAIR. NO FURTHER ACTION REQUIRED HFEC AND DVI REF A320 NTM 51-10-08 AND 51-10-01
Part: SKIN — CORRODED (UNKNOWN) · airframe 44,946 hrs · 14,453 cycles
LESSOR ITEM 237; (67003) LH WING - UPPER SURFACE. CORROSION SPOT AT RIB 6, REAR SPAR GROUNDED - YES. EMOVED CORROSION BETWEEN RIB 6 AND RIB 7 AT REAR SPAR ORIG .248 MATERIAL LOSS .006 REMAINING .242 2.00 X 2.00 FOUND TO BE WITHIN LIMITS, RESTORED COATINGS REF A320 SRM 57-21-11-283-007. REMOVED AND REPLACED FASTENERS REF A320 SRM 51-42-11/001. THIS IS A CAT A REPAIR. NO FURTHER ACTION REQUIRED
Part: FLOOR PANEL — DELAMINATED (UNKNOWN) · airframe 45,004 hrs · 14,478 cycles
LESSOR ITEM 239; (67184) CABIN FLOORBOARD - FWD CENTER, MID CABIN HAS SEVERAL SPOTS OF DELAMINATION. SEE YELLOW DOT STICKERS GROUNDED - YES. REMOVED, INSTALLED AND SEALED NEW FLOOR PANEL# 231KF IAW ASA AIRBUS AMM 53-00-00-400-801. T# T05867-140 04FEB24 PO# 1072761.1
Part: FLOOR PANEL — DELAMINATED (UNKNOWN) · airframe 45,004 hrs · 14,478 cycles
LESSOR ITEM 242; (67187) CABIN FLOORBOARD - AFT CENTER AREA HAS AN AREA OF DELAMINATION. SEE YELLOW DOT STICKER. GROUNDED - YES. REPAIRED LESSOR ITEM 242(67187) CABIN FLOOR BOARD DAMAGE LOCATED AT 27.8" FROM AFT EDGE .7 IN DIAMETER 10.7" FROM RIGHT PERMANENT REPAIR IAW ASA A320-214 SRM 53-02-00-283-001, SRM 53-02-00-300-001 FH 45004:12 FC 14478 WV 010 -REMOVED, REINSTALLED AND SEALED FLOOR AFT CENTER PANEL #251RF IAW ASA AIRBUS AMM 53-00-00-400-801 T# T05867-140- 04FEB24
Part: FLOORBOARD — DELAMINATED (UNKNOWN) · airframe 45,004 hrs · 14,478 cycles
CABIN FLOORBOARD- MID CENTER CABIN AREA, ONE SPOT OF DELAMINATION . SEE YELLOW DOT STICKER GROUNDED - YES. REMOVED AND INSTALLED SEAMED MID CABIN FLOOR PANEL 241AF IAW ASA AIRBUS AMM 53-00-00-400-801 PO# 1072814.1
Part: FLOOR PANEL — DELAMINATED (UNKNOWN) · airframe 45,004 hrs · 14,478 cycles
LESSOR ITEM 241; (67186) CABIN FLOORBOARD - MID CENTER CABIN AREA, HAS TWO AREAS OF DELAMINATION. SEE YELLOW DOT STICKERS GROUNDED - YES. REMOVED, INSTALLED AND SEALED NEW FLOOR PANELS 241EF AND 241FF IAW ASA AIRBUS AMM53-00-00-400-801. T# T05867-140.
Part: SKIN — CORRODED (UNKNOWN) · corrosion level 2 · airframe 44,946 hrs · 14,453 cycles
LEFT WING UPPER SURFACE AREA LOCATED FWD OF AILERON HAS NUMEROUS CORROSION AS MARKED GROUNDED - YES. REPAIRED L/WING UPPER SURFACE, T/E OVERHANG FROM RIB 24 TO RIB 27, BLENDED REPAIR ,INSPECTION ACCOMPLISHED WITHOUT FINDINGS, PROTECTIVE COATINS APPLIED TO REPAIR AREA PER AIRBUS DOSSIER 81304214 AND RDAF81304214/004/2023 ISSUE A PER ALASKA AIRLINES EA # A320-57EA-01992, REVISION 00. REPAIR CLASSIFIED AS MINOR . MAT'L REMVOED .016", ORIGINAL THICKNBESS, .197", REMAINING THICKNESS, .181" PER ASA SRM 57-21-11-283-007
Part: SKIN — DEBONDED (LT WING FLAP) · airframe 44,946 hrs · 14,453 cycles
LEFT WING I/B FLAP UPPER SURFACE T/E HAS MULTIPLE CORROSION GROUNDED - YES. ACCOMPLISHED PERMANENT CAT A REPAIR TO LEFT WING I/B FLAP T/E PROFILE IAW ASA EA # CMPT-57EA-01966 REV 00 DAMAGE AND REPAIR DIMENSIONS LOCATED IN WORK STEPS ON STEP 007, 009011 A/C : N637VA, A/C S/N :3465 FLIGHT HOURS 45004:12, FLIGHT CYCLES:14478, WEIGHT VARIANT: 010
Part: SKIN — CORRODED (UNKNOWN) · corrosion level 2 · airframe 44,946 hrs · 14,453 cycles
RIGHT WING UPPER SURFACE AREA LOCATED FWD OF AILERON HAS NUMEROUS CORROSION AS MARKED. GROUNDED - YES. REMOVED FASTENERS AND REPLACED, REMOVED DAMAGE . ORIG .197 MATERIAL LOSS .017, REMAINING .180 BETWEEN RIB 21 TO RIB 26 AT UPPER TRAILING EDGE OVERHANG, FOUND TO BE WITHIN LIMITS. HFEC AND DVI NO DEFECTS NOTED, RESTORED COATINGS REF ASA EA A320-57EA-01994 REV 00 THIS IS A CAT A REPAIR NO FURTHER ACTION REQUIRED.
Part: FLOOR PANEL — PUNCTURED (UNKNOWN) · airframe 45,004 hrs · 14,478 cycles
LESSOR ITEM 9: MAIN AFT CARGO DOOR ENTRY FLOOR PANEL 151DF PUNCTURED. REQUIRES REPAIR. GROUNDED - YES. REPAIRED PANEL 151DF P/N D5367521100200, ON A320-214 S/N 3465 FH 45004:12 FC14478 WV010 5EA AREAS USING CAT A PERMANENT REPAIRS, IAW A320-200 SRM 53-02-00-283-001 REV 146-01AUG2023, A320-200 SRM 53-02-00-300-002 REV 146-01AUG2023. AREA 1 IS DIA 3.2" LOCATED 55.5" FWD AND 16" RT, AREA 2 IS DIA 0.75" LOCATED 45" FWD AND 39.5 RT. AREA 3 IS DIA 0.84" LOCATED 42" FWD AND 35.5 RT. AREA 4 IS DIA 0.75" LOCATED 36.5" FWD AND 11.5" RT. AREA 5 IS 0.75" DIA LOCATED 12.5" FWD ABD 34.5" RT.
Part: PLATE — CORRODED (UNKNOWN) · corrosion level 2 · airframe 44,946 hrs · 14,453 cycles
LESSOR ITEM 211; (66539) BELLY FAIRING PANEL, FWD FUSELAGE ATTACHMENT CORRODED. (UNDER PANEL 191BB) GROUNDED - YES. REPLACED BELLY FAIRING PANEL, FWD FUSELAGE ATTACHMENT PLATE PN: E5321010120000. PO# 107232401 IAW AIRBUS DWG# E53210101. ISSUE: C AND A320 SRM 51-42-11/001. REMOVED CORROSION ON WING TO BODY ATTACH ANGLE 100 PERCENT MATERIAL LOSS NO LIMITS GIVEN IN SRM REF A320 SRM 51-74-00/001
Earlier reports · 2011–2020 · 22 reports
2020
Part: SKIN — DENTED (UNKNOWN) · airframe 44,946 hrs · 14,453 cycles
RAMP REPORTS DENT NEAR AFT L/H FUSELAGE, FR 59 THRU FR 60 STRG 39-40, MEASURES 0.017" DEEP. 1.5" FROM FR. GROUNDED - YES. EVALUATED DENT, DEPTH .009, LENGTH 1.00, WIDTH 1.3, NEAREST STIFFNER 1.6, LOCATION BETWEEN FR 59 AND FR 60 AND STR 36L AND STR 40L AT WATERLINE -Z2000 FOUND TO BE WITHINLIMITS, HFEC AND DVI, NO DEFECTS NOTED REF A320 SRM 53-00-11-283-005 AND 53-41-11-283-002. THIS IS A CAT B REPAIR INSPECTION THRESHOLD FROM ADL 60,000 FC, 120.000 FH, INTERVAL TBD, METHOD TBD NOTIFIED SEAMC LAMANT,THIS CLOSES PLT DEFERRAL
Part: WEB — CORRODED (FUSELAGE) · corrosion level 2 · airframe 42,768 hrs · 13,268 cycles
RIGHT HAND SIDE STRUCTURE WEB CORRODED AT FR 20 GROUNDED - YES. REMOVED AND REPLACED RIGHT HAND SIDE STRUCTURE WEB AT FRAME 20 IAW A320 SRM 51-42-11 PO#968418.4. NO ALLOWABLE LIMITS GIVEN IN SRM CAT A REPAIR.
Part: SHEAR WEB — CORRODED (FUSELAGE) · corrosion level 2 · airframe 42,768 hrs · 13,268 cycles
RIGHT HAND SIDE STRUCTURE AFT SHEAR PLATE CORRODED AT FR 70 GROUNDED - YES. REMOVED AND REPLACED SHEAR WEB IAW A320 SRM 51-42-11 AND AIRBUS DWG D53474180. CAT A REPAIR. NO ALLOWABLE LIMITS IN SRM
Part: FLOORBEAM — CORRODED (FUSELAGE) · corrosion level 2 · airframe 42,768 hrs · 13,268 cycles
LEFT HAND FLOOR BEAM Y765 UPPER SURFACE CORRODED AT SPLICE AT FRAME 68 GROUNDED - YES. REMOVED DAMAGE AND FOUND TO BE BEYOND ALLOWABLE LIMITS OF .016" DEPTH IAW A320 SRM 53-00-14 REMVOED BEAM AT Y765 FR. 68 IAW A320 SRM 53-41-11, LOCATED , DRILLED AND DEBURRED NEW BEAM PART NUMBER D5347219220000 PO NUMBER 968279.2 IAW A320 SRM 51-72-11, INSTALLED 2EA HARDPOINTS AND 2EA. ATTACHED ANGLES TO FLOORBEAM IAW A320 SRM 51-42-00, INSTALLED NEW FLOOR BEAM AT FR 68 Y765 IAW A320 SRM 51-72-11 AND AIRBUS DWG. D53472837
Part: DOOR SILL — CORRODED (FUSELAGE) · corrosion level 2 · airframe 39,837 hrs · 12,088 cycles
R2 DOOR SILL FWD SPLICE CORRODED ON TOP SURFACE GROUNDED - YES. ACCOMPLISHED REPAIR 9 TO DISCREPANT AREA ON R2 DOOR FWD SPLICE IAW SRM 53-41-14-300.001 CAT A REPAIR
Part: SUPPORT — CORRODED (FUSELAGE) · corrosion level 2 · airframe 42,768 hrs · 13,268 cycles
RIGHT HAND SIDE STRUCTURE AFT SHEAR PLATE SUPPORT FRAME CORRODED AT FR 70 GROUNDED - YES. REMOVED AND REPLACED FRAME SUPPORT IAW A320 SRM 51-42-11 AND AIRBUS DWG D53474180. CAT A REPAIR. NO ALLOWABLE LIMITS GIVEN IN SRM.
Part: SHEAR WEB — CORRODED (FUSELAGE) · corrosion level 2 · airframe 42,768 hrs · 13,268 cycles
LEFT HAND SIDE STRUCTURE AFT SHEAR WEB CORRODED AT FR 70 GROUNDED - YES. REMOVED AND REPLACED SHEAR WEB IAW A320 SRM 51-42-11 AND AIRBUS DWG D53474180. CAT A REPAIR. NO ALLOWABLE LIMITS GIVEN IN SRM
Part: FLOORBEAM — CORRODED (FUSELAGE) · corrosion level 2 · airframe 42,768 hrs · 13,268 cycles
RIGHT HAND FLOOR BEAM -Y1162 UPPER SURFACE CORRODED AT SPLICE AT FRAME 68 GROUNDED - YES. REMOVED AND REPLACED FLOOR BEAM IAW A320 SRM 51-42-11, AND AIRBUS DWG D53472458. CAT A REPAIR
2019
Part: FITTING — GOUGED (FRAME 78) · airframe 40,629 hrs · 12,407 cycles
DURING "OK TO INSTALL"INSPECTION OF THE RH INBOARD ELEVATOR SERVO - FOUND ELEVATOR SERVO ATTACH FITTING ANTI-ROTATION TAB DAMAGED. GROUNDED - YES. REPAIRED THE ELEVATOR SERVO ATTACH FITTING PER A320 SRM 55-26-47. THE MAT CALL OUT IS 3.4364T73511 EXTRUDED SECTION PER A320 SRM 55-26-47, SUBSTITUTED MAT WITH LN9496 7075-T73511 PER A320 SRM 51-31-00 TABLE 008.
Part: OUTFLOW VALVE — MALFUNCTIONED (CABIN PRESSURE) · airframe 39,550 hrs · 11,895 cycles
AIR RETURN TO DEPARTURE DUE TO PRESSURIZATION ISSUES IMMEDIATELY AFTER TAKE OFF. NO EMERGENCY DECLARED. VENT SKIN VALVE FAULT ECAM PROCEDURE FOLLOWE PER MEL 21-26-04 NOTE 3. UNABLE TO CONTROL CABIN WITH MAN V/S CTL SWITCH INDICATED XX ON LOWER ECAM. GROUNDED - YES. PERFORMED INSPECTION OF SKIN OUTLET VALVE 22HQ, FOUND AUXILIARY VALVE TO NOT BE FULLY OPEN PER MEL 21-26-04, FOR CORRECTIVE ACTION SEE LOGPAGE 1196285 ITEM 3, MDDR # 63770, PERFORMED AIRCRAFT PRESSURIZATION TEST PER AMM 05-53-00. OPS CHECK GOOD. REMOVED & REPLACED SKIN AIR OUTLET VALVE 22HQ, PER AMM 21-26-53, OPS CHECK GOOD, AIRCRAFT PLACED BACK IN NORMAL CONFIGURATION. PERFORMED AIRCRAFT PRESSURIZATION TEST PER AMM 05-53-00. OPS CHECK GOOD, THIS CLEARS MDDR 63770, MCC COREY NOTIFIED, MEL LIST UPDATED.
2016
Part: SENSING ELEMENT — FAULTY (NR 2 ENGINE) · airframe 30,125 hrs · 8,885 cycles
EXPERIENCED AN AIR ENGINE 2 BLEED LEAK ECAM CAUTION AND RETURNED TO DESTINATION. TECHS DISCOVERED A LEAK AT THE NR 2 ENGINE OVER PRESSURE VALVE IN THE RT ENGINE PYLON AND REPLACED IT IAW AMM 36-11-53. ON THE SUBSEQUENT FLIGHT, THE FLIGHT CREW EXPERIENCED THE SAME AIR ENGINE 2 LEAK ECAM CAUTION AND ACCOMPLISHED QRH PROCEDURES. THE FLIGHT CONTINUED TO ITS DESTINATION AND THE AIRCRAFT WAS REMOVED FROM SERVICE AND MAINTENANCE FERRIED FOR REPAIR. TECH DISCOVERED PYLON LEAK SENSING ELEMENT 1HF2 FAULTY AND REPLACED IT IAW AMM 36-22-15-000-001-A. ENGINE RUNS WERE ACCOMPLISHED WITH NO ISSUES FOUND AND THE ACFT WAS RETURNED TO SERVICE. NO FURTHER ISSUES.
Part: CONTROL UNIT — FAILED (MLG) · airframe 28,925 hrs · 8,512 cycles
ACFT DECLARED AN EMERGENCY AND RETURNED TO DEPARTURE. LANDING GEAR DOORS DID NOT CLOSE. ACFT LANDED SAFELY. R & R NR 1 LANDING GEAR CIU IAW AMM 32-31-71-PB401, PERFORMED BITE TEST ON MCDU IAW AMM 32-69-00-740-001A, OPS CHECKS NORMAL AND R & R LANDING GEAR CIU IAW AMM 32-31-71-PB401, PERFORMED BITE TEST ON MCDU IAW AMM 32-69-00-740-001-A, OPS CHECK NORMAL. ACCEPTANCE FLIGHT AFTERWARDS WAS SUCCESSFUL.
2015
Part: CABIN PRESSURE — MALFUNCTIONED · airframe 26,365 hrs · 7,724 cycles
FLIGHT EXPERIENCED AN EXCESSIVE CABIN ALTITUDE WARNING MESSAGE AND A ASSOCIATED LOW DIFFERENTIAL CABIN PRESSURE CAUTION ECAM MESSAGE AT APPROXIMATELYFL340, 25 MINUTES AFTER DEPARTURE. THE CREW INITIATED AN EMERGENCY DECENT AND RETURNED TO DEPARTURE. UPON ARRIVAL MAINTENANCE ACCOMPLISHED TSM 21-31-00-810-809-A. FINDINGS INDICATED THAT BOTH AIR PACK FLOW CONTROL VALVES WERE CLOSED FROM THE TIME OF 2ND ENGINE START UNTIL THE ACFT RETURNED TO DEPARTURE AIRPORT AND SHUTDOWN. MAINTENANCE TECHS ACCOMPLISHED AMM TASKS 21-31-00-710-002-A, 21-31-00-710-003-A & 21-61-00-710-001-A NO ABNORMALITIES WERE NOTED AND THE AIRCRAFT WAS RETURNED TO SERVICE. THE NR 1 ENGINE INTERFACE UNIT WAS REPLACED PRECAUTIONARY AFTER VX 11 ON 6/8/15.
2014
Part: SILL — CORRODED (FRAMES 67-68)
L2 DOOR SILL CORRODED INBD OF GIRT BAR. CUTOUT AREA AND FABRICATED ANGLE REPAIR IAW SRM 53-41-14. PERFORMED HFEC INSPECTION AT CUTOUT AND IAW NTM 51-10-01 PB. NO CRACKS NOTED.
Part: SILL — CORRODED (FRAMES 69-70)
R1 DOOR LOWER SILL FOUR HOLES AFT AND ONE HOLE FORWARD HAVE CORROSION. SPOT FACED CORRODED SILL IAW SRM 53-11-14. FOUND WITHIN LIMITS IAW SRM 53-11-14, FIG 108, SHEET 2. TREATED AND PRIMED IAW SRM 51-25-12. INSTALLED REPAIR WASHERS IAW SRM 53-11-14.
Part: BLANKING PLATE — CORRODED (R2 DOOR)
AFT CABIN L2 DOOR FORWARD GIRT BAR FITTINGS PLATE CORRODED. REPLACED AFT CABIN L2 BLANKING PLATE IAW SRM 51-72-00.
Part: BLANKING PLATE — CORRODED (R2 DOOR)
AFT CABIN R2 DOOR FORWARD GIRT BAR FITTINGS PLATE CORRODED. REPLACED AFT CABIN R2 BLANKING PLATE IAW SRM 51-72-00.
Part: SHEAR PLATE — CORRODED (FRAMES 69-70)
LEFT SHEAR PLATE CORROSION OUT OF LIMITS. R & R LT SHEAR PLATE IAW SRM 51-42-11 AND 53-41-17.
Part: SHEAR PLATE — CORRODED (FRAMES 69-70)
RIGHT SHEAR PLATE CORROSION OUT OF LIMITS. R & R RT SHEAR PLATE IAW SRM 51-42-11 AND 53-41-17.
2013
Part: REGULATOR VALVE — FAULTY (AC BAY)
WHEN DISPATCHER RECEIVED AN AIRCELL CALL REGARDING A STRONG SMELL IN CABIN AND COCKPIT THAT SMELLED LIKE "SHARPIE MARKER". MX CONTROL SPOKE WITH CAPT AND CONFIRMED THERE WAS NO SMOKE IN CABIN OR COCKPIT AND THERE WAS NO ELECTRICAL OR BURNING SMELL. CREW SELECTED OVERIDE ON BLOWER AND EXTRACT PUSHBUTTONS AND SELECTED CABIN FANS OFF. MX ADVISED CREW TO TURN OFF IFE PRECAUTIONARY AND ACFT PROCEEDED TO DESTINATION WITHOUT INCIDENT. CREW WROTE UP IN LOG BOOK " INBOUND ACFT LOG BOOK WRITE UP- STRONG SMELL IN COCKPIT ANDCABIN WHILE ENROUTE AFTER TROUBLESHOOTING SMELL WENT AWAY AFTER BLOWER AND EXTRACT PB`S WERE SELECTED TO OVERRIDE AND CABIN FANS WERE TURNED OFF. MX TROUBLESHOT ODOR TO TRIM AIR PRESSURE REGULATING VALVE 14HK AND REPLACED AMM 21-63-52-04 AND PERFORMED OPS CHECKS WITH NO SMELL NOTED. IFE WAS ALSO INSPECTED WITH NO FINDINGS REF AMM 44-27-00. NO FURTHER REPORTS OF THIS ON SUBSEQUENT FLIGHTS.
2011
Part: TUBE — BROKEN (CABIN)
DURING THE CABIN EMERGENCY OXYGEN MASK DROP TEST, THE ROW 20 ABC CONTAINER ASSY OXYGEN SUPPLY TUBING WAS FOUND BROKEN-OFF FROM THE "FLOW INDICATOR" LOCATED IN-LINE WITH THE PASSENGER MASK. ITEM WAS PLACED ON MEL 35-21-41-04 AND THE UNIT REPLACED AT THE NEXT MX OPPORTUNITY.
Part: TUBE — BROKEN (CABIN)
DURING THE CABIN EMERGENCY OXYGEN MASK DROP TEST, THE ROW 20 SEAT ABC CONTAINER ASSY OXYGEN SUPPLY TUBING WAS FOUND BROKEN-OFF FROM THE "FLOW INDICATOR" LOCATED IN LINE WITH THE PASSENGER MASK. ITEM WAS PLACED ON MEL 35-21-41-04 & THE UNIT REPLACED AT THE NEXT MX OPPORTUNITY.