N846VA
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.
35 reports on file, 2012-08-18 – 2024-07-26.
Part: RIB — CORRODED (ZONE 500) · corrosion level 2 · airframe 35,490 hrs · 11,792 cycles
L/H WING I/B FLAP, #1 RIB HAS CORROSION ON LOWER AFT LEG INNER SURFACE. GROUNDED - YES. EVALUATED CORROSION, FOUND TO BE 100% MATERIAL LOSS. TRIMMED OUT CORRODED AREA 48.26MM X 19.05MM IAW A320 SRM 51-74-00/001 REV149-01MAY2024. L/H WING I/B FLAP REMOVED AND REPLACED ON CUSTOMER CARD:G187712 N/R:34712.
Part: SPAR — CORRODED (ZONE 500) · corrosion level 2 · airframe 35,490 hrs · 11,792 cycles
L/H WING I/B FLAP, AFT SPAR HAS CORROSION ON LOWER LEG INNER SURFACE. GROUNDED - YES. EVALUATED CORROSION, FOUND TO BE 100% MATERIAL LOSS. TRIMMED OUT CORRODED AREA 19.05MM X 298.45MM IAW A320 SRM 51-74-00/001 REV 149-01MAY2024. L/H WING I/B FLAP REMOVED AND REPLACED ON CUSTOMER CARD:G1987712 N/R:34712
Part: DOOR FRAME — CRACKED (ZONE 200) · airframe 35,490 hrs · 11,792 cycles
LEFT FWD OVER WING EMERGENCY EXIT DOOR OUTER FWD BEAM CRACKED AT FASTENER HOLES GROUNDED - YES. REMOVED DAMAGED BEAM, REFERENCE A320 SRM 51-41-11, FORMED NEW BEAM REFERENCE AIRBUS DWG# D52279025, ALODINED NEW BEAM, REFERENCE A320 SRM 51-21-11, PRIMED BEAM REFERENCE 51-75-12. INSTALLED NEW BEAM, REFERENCE A320 SRM 51-42-11 DWG # D52279025 LOCATION FR38 TO FR38 5-11L TO 5-15L, F/H 35490:29, F/C 11792, W/V 015
Part: SPAR — CORRODED (ZONE 600 FLAP) · corrosion level 2 · airframe 35,490 hrs · 11,792 cycles
R/W I/B FLAP, REAR SPAR HAS CORRSION ON LOWER LEG INNER SURFACE. GROUNDED - YES. EVALUATED CORROSION, FOUND TO BE 100% MATERIAL LOSS. AREA #1, TRIMMOUT CORROSION 44.45 X 19.05MM, AREA #2 TRIM OUT 21.08MM X 19.05MM, AREA #3 TRIMOUT 21.08MM X 19.05MM, AREA #4 REMOVED CORROSION FROM EDGE, 1.82MM REMOVED FROM EDGE X24.89MM WIDE, AREA #5 TRIM OUT 20.32MM X 20.13MM, AND AREA #6 BLEND AREA .500"X10.0", ORIGINAL THICKNESS .070", MATERIAL LOSS .015", REMAINING THICKNESS .055". CORROSION LOCATION IS ON R/W I/B FLAP REAR SPAR LOWER LEG BETWEEN RIB 1 AND RIB 4. IAW A320 SRM 51-74-00/001 REV 149-01MAY2024. R/W I/B FLAP REMOVED AND REPLACED ON CUSTOMER CARD: G1977813 NR 34713.
Part: RIB — CORRODED (ZONE 600) · corrosion level 2 · airframe 35,490 hrs · 11,792 cycles
R/W I/B FLAP, INBOARD RIB ASSY HAS CORROSION ON AFT LOWER LEG INNER SURFACE. GROUNDED - YES. EVALUATED CORROSION, FOUND TO BE 100% MATERIAL LOSS. TRIMMED OUT CORRODED AREA .950" X 1.350" IAW A320 SRM 51-74-00/001 REV149-01MAY2024. R/W I/B FLAP REMOVED AND REPLACED ON CUSTOMER CARD:G1987713 NR:34713
Part: SKIN — DAMAGED (ZONE 600) · airframe 35,490 hrs · 11,792 cycles
R/W, LOWER PANEL LAND AT 640LB HAS 1EA HOLE THAT REQUIRES REPAIR. GROUNDED - YES. REPAIRED 1EA. HOLE AT PANEL 640LB IAW A320 SRM 57-21-11-300-003 REV 149- 01 MAY 2024 CATAGORY B REPAIR. INSPECTION THRESHOLD FROM AIRCRAFT FIRST FLIGHT: 21900FC 43800FH, SUBSEQUENT INSPECTION AT INTERVALS OF: 4300FC 8600FH, METHOD INSPECTION: GENERAL VISUAL INSPECTION. HOLE LOCATED AT PANEL 640LB, 4.40" FROM RIB16 O/B AND 6.250" FWD OF JOINT STR. 11.
Part: SKIN — DAMAGED (ZONE 500) · airframe 35,490 hrs · 11,792 cycles
L/W, LOWER PANEL LAND AT 540KB HAS 1EA HOLE THAT REQUIRES REPAIR. GROUNDED - YES. REPAIRED 1EA. HOLE AT PANEL 540KB IAW A320 SRM 57-21-11-300-003 REV 149- 01 MAY 2024 CATAGORY REPAIR B. INSPECTION THRESHOLD FROM AIRCRAFT FIRST FLIGHT: 22800FC 45600FH, SUBSEQUENT INSPECTION AT INTERVALS OF: 4300FC 8600FH, METHOD OF INSPECTION: GENERAL VISUAL INSPECTION. 1EA HOLE LOCATED AT PANEL 540KB LAND, 2.70ÿ½ O/B OF RIB 15 AND 8.90ÿ½ AFT OF JOINT STRINGER 8.
Part: HINGE FITTING — DAMAGED (ZONE 300) · airframe 35,490 hrs · 11,792 cycles
VERT STAB #BR4 HINGE FITTING FORK END HAS ELONGATED HOLES GROUNDED - YES. REMOVED AND REINSTALLED RUDDER PANELS 325CL AND 325CR IAW A320 AMM 55-33-13-410-002-A REV 11-01MAY-2024. REMOVED AND REPLACED BR4 HINGE AMM P/N D5537131420054 P/O 1095868.1 IAW EA #A320-55EA-02222 REV 00
Part: SKIN — DAMAGED (ZONE 600) · airframe 35,490 hrs · 11,792 cycles
R/W, LOWER PANEL LAND AT 640HB HAS 2EA OUT OF ROUND HOLE. GROUNDED - YES. REPAIRED 2EA. HOLES AT PANEL 640HB IAW A320 SRM 57-21-11-300-003 REV 149- 01MAY 2024 CATAGORY B REPAIR. INSPECTION THRESHOLD FROM AIRCRAFT FIRST FLIGHT: 25400FC 50800FH, SUBSEQUENT INSPECTION AT INTERVALS OF: 4300FC 8600FH, METHOD OF INSPECTION: GENERAL VISUAL INSPECTION 2EA HOLES LOCATED AT PANEL 640HB LAND, 5.90ÿ½ O/B OF RIB 13 AND 5.70ÿ½ AFT OF JOINT STRINGER 8. 2ND HOLE 2.350ÿ½ I/B OF RIB 14 AND 9.0ÿ½ AFT OF JOINT STRINGER 8.
Part: SKIN — DAMAGED (ZONE 500) · airframe 35,490 hrs · 11,792 cycles
L/W, LOWER PANEL LAND AT 540HB HAS 1EA OUT OF ROUND HOLES GROUNDED - YES. REPAIRED 1EA. HOLE AT PANEL 540HB IAW A320 SRM 57-21-11-300-003 REV 149 -01MAY 2024 CATAGORY B REPAIR. INSPECTION THRESHOLD FROM AIRCRAFT FIRST FLIGHT: 23700FC 47400FH, SUBSEQUENT INSPECTION AT INTERVALS OF: 4300FC 8600FH, METHOD OF INSPECTION: GENERAL VISUAL INSPECTION. 1EA HOLE LOCATED AT PANEL 540HB LAND, 5.50ÿ½ O/B OF RIB 13 AND 5.60ÿ½ FWD OF JOINT STRINGER 11.
Part: HINGE ARM — DAMAGED (VERTICAL STAB) · airframe 35,490 hrs · 11,792 cycles
VERT STAB #BR1 HINGE FITTING FORK END HAS ELONGATED HOLE GROUNDED - YES. REMOVED AND REINSTALLED VERTICAL STAB PANEL 325BR IAW A320 AMM 55-33-13-410-002-A REV 11-01MAY2024. REMOVED AND REPLACED BR1 HINGE FITTING P/N D553712100200 P/O #0 IAW EA#A320-55EA-02221 REV 00
Part: SKIN — DELAMINATED (ZONE 600) · airframe 35,490 hrs · 11,792 cycles
RH WING INBD FLAP LOWER SURFACE CLUSTER 1 REQUIRES REPAIR OF DENTS. GROUNDED - YES. ACCOMPLISHED PERMANENT CLASS A REPAIR OF R/W INBRD FLAP T.E. WEDGE LOWER SURFACE P/N D2525033150300 S/N NSN ON A320-214 S/N 4894, WV 015, FH 35490:29, FC 11792. REPAIR IS LOCATED IN ZONE 2 AND IS 16.0L X 11.5W AND IS 47-63.5 INCHES FROM INBRD PANEL EDGE AND REPAIRED IAW ASA A320-214 SRM 57-52-00-300-093 AND 51-77-11-911-031 TABLES 5 AND 6 NO FURTHER ACTION REQUIRED
Part: DOOR SILL — CORRODED (L2 AREA) · airframe 35,490 hrs · 11,792 cycles
L-2 DOOR SILL CORRODED AT NUTPLATES 2 INCHES INBOARD OF AFT GIRT BAR FITTING. GROUNDED - YES. REMOVED CORROSION AT 2EA FASTENER HOLES. FWD FAST. AREA, ORIGINAL THICK-.315", MAT:REMOVED .004", REMAINING THICK-.311". AFT FAST. HOLE AREA, ORIGINAL THICK-.315", MAT. REMOVED. 010", REMAINING THICK-.305". FOUND TO BE WITHIN LIMITS IAW A320 SRM 53-41-14-300-001 REV 149-01MAY2024. APPLIED PROTECTIVE TREATMENT IAW A320 SRM 51-21-11/001 AND 51-23-11/001 REV 149-01MAY2024. CATEGORY A REPAIR
Part: BEAM — CORRODED (ZONE 200) · corrosion level 2 · airframe 35,490 hrs · 11,792 cycles
L-2 DOOR SILL CORRODED AT NUTPLATES 3 INCHES INBOARD OF AFT GIRT BAR FITTING GROUNDED - YES. CUTOUT DAMAGED AREAS AND ACCOMPLISHED REPAIR IAW A320 SRM 53-41-14-300-001 REV 149 01MAY2024. CATEGORY A REPAIR.
Part: BEAM — CORRODED (ZONE 200) · corrosion level 2 · airframe 35,490 hrs · 11,792 cycles
R2 THRESHOLD CORROSION AT FR 68 - Y1750 GROUNDED - YES. REMOVED AND REPLACED R2 THRESHOLD SILL BEAM IAW A320 SRM 51-42-11/001 REV 148- 01 FEB 2024 AND AIRBUS DWG D53480019. P/N-D5348004320701 PO# 10409518
Part: SKIN — DELAMINATED (ZONE 500 FLAP) · airframe 35,490 hrs · 11,792 cycles
LESSOR ITEM: D&B #2 NON ROUTINE 00204 RECORDS A CONCENTRATION OF DENTS, THE CLOSING DOCUMENTS NEITHER RECORD HOW MANY NOR DIMENSIONS AND LOCATIONS. PLEASE RE-ASSES AND ADD SRM REFERENCE USED AND PICTURES TO THE FILE. GROUNDED - YES. ACCOMPLISHED PERMANENT CLASS A REPAIR OF DENT CLUSTER ON L/H WING INBRD FLAP T.E. WEDGE LOWER SURFACE P/N D5757008501864 ON A320-214, S/N 4894, WV015, FH 35490:29 FL 11792. REPAIR IS LOCATED IN ZONE 2 83.75IN-100.5IN OTBRD FROM INBRD PANEL EDGE AND 12 IN FROM T.E. TO FORWARD. REPAIRED IAW ASA A320-214 SRM 57-52-00-283-106 ALLOWABLE DAMAGE ZONE 2 AND SRM 57-52-00-300-093 REV149 01MAY2024 NO FURTHER ACTION REQUIRED
Part: BEAM — WORN (ZONE 200) · airframe 35,490 hrs · 11,792 cycles
R/H FWD OVER WING EMERGENCY EXIT DOOR, INTERNAL UPPER HORIZONTAL BEAM LOWER EDGE IS GOUGED 2EA SPOTS MARKED. GROUNDED - YES. REMOVED DAMAGED BEAM, LOCATED, DRILLED (1EA) SERVICEABLE BEAM. INSTALLED, (1EA) SERVICEABLE BEAM, AND REASSEMBLED DOOR ASSY, SEAL, HANDLE ASSY, PERFORMED BOND CHECK, INSULATION ALODINED, PRIMED, TOPCOATED AND CIC'D ALL IAW AIRBUS A320-214 CMM 52-21-11-010-803-A01, 52-21-11-010-803-B01, 52-21-11 FIGURE 52-21-11-991-002-A01 (FLAG NOTE 2) SRM 51-42-00, 51-42-11, 51-75-12, CML S-12, AND DWG# D52279002. F/H:35490.29, FC:11792, W/V:015 BEAM 7" FROM TOP OF HATCH DOOR
Part: BEAM — GOUGED (ZONE 200) · airframe 35,490 hrs · 11,792 cycles
L/H FWD OVER WING EMERGENCY EXIT DOOR, INTERNAL UPPER HORIZONTAL BEAM LOWER EDGE IS GOUGED 2EA SPOTS MARKED. GROUNDED - YES. REMOVED (4EA) CLIPS AND DAMAGED BEAM 1EA AS WELL AS INSULATION AND HANDLE ASSY. IAW AIRBUS A320-214 CMM 52-21-11-010-803-A01 & SRM 51-42-11. LOCATED, DRILLED AND INSTALLED (1EA) SERVICABLE BEAM IAW AIRBUS A320-214 SRM 51-42-11 & DWG # D52279002. REINSTALLED (4EA) CLIPS IAW AIRBUS A320-214 SRM 51-42-11 AND DWG #D52279002. REINSTALLED HANDLE ASSY IAW AIRBUS A320-214 AMM 52-21-11/401 AND SRM 51-49-00/001 TABLE 9. BOND CHECKED IAW AIRBUS A320-214 CMM 52-21-11 FIGURE:52-21-11-991-002-A01 FN 1,2. REINSTALLED DISPLACED SEAL IAW AIRBUS A320-214 CMM 52-21-11. RESEALED DOOR IAW AIRBUS A320-214 CMM 52-21-11. ALODINED, PRIMED, TOPCOATED AND STENCILD DOOR IAW AIRBUS A320-214 SRM 51-75-12. CIC'D AND REINSTALLED INSULATION IAW AIRBUS A320-214 CMM 52-21-11 & 52-11-11 & CML 12ABC1-S12 LOCATION FR38-F39 S14L TO S14L F/H 35490:29, F/C 11792, W/V 015
Part: BEAM — WORN (ZONE 200) · airframe 35,490 hrs · 11,792 cycles
L/H AFT OVER WING EMERGENCY EXIT DOOR, INTERNAL UPPER HORIZONTAL BEAM LOWER EDGE IS GOUGED 2EA SPOTS MARKED GROUNDED - YES. REMOVED DAMAGED BEAM, LOCATED, DRILLED (1EA) SERVICEABLE BEAM. INSTALLED (1EA) SERVICEABLE BEAM, AND REASSEMBLED DOOR ASSY, SEAL HANDLE ASSY, PERFORMED BOND CHECK, INSULATION, ALODINED, PRIMED, TOPCOATED, AND CIC'D ALL IAW AIRBUS A320-214 CMM 52-21-11-010-803-A01, 52-21-11 FIGURE 52-21-11-991-002-A01 (FLAG NOTE2), SRM 51-42-00, 51-42-11, 51-75-12, CML S-12, AND DWG#D52279002, F/H:35490.29, FC:11792, W/V:015 BEAM 7" FROM TOP OF HATCH DOOR
Part: BEAM — GOUGED (ZONE 200) · airframe 35,490 hrs · 11,792 cycles
R/H AFT OVER WING EMERGENCY EXIT DOOR, INTERNAL UPPER HORIZONTAL BEAM LOWER EDGE IS GOUGED 2EA SPOTS MARKED GROUNDED - YES. REMOVED GOUGED BEAM & AND LOCATED, DRILLED, AND INSTALLED (1EA) SERVICEABLE BEAM, AS WELL AS REINSTALLED DISPLACED SEAL, HANDLE ASSY, PERFORMED BOND CHECK, REINSTALLED INSULATION, APPLIED CIC, ALODINED, PRIMED, AND TOPCOATED, AND STENCILED SNIB IAW AIRBUS A320-214 CMM 52-21-11, SRM 51-42-00, DWG# D52279002, SRM 52-42-11, SRM 51-75-12, CML12ABC1: S12 REV#;50, AMM 52-21-11/401, SRM 51-49-00-/001 TABLE:9, CMM 52-21-11 FIGURE 52-21-11-991-002-A01 FN:1,2. REMOVED DOTF/H:35490.29 F/C:11782 W/V:015 BEAM 7" FROM TO OF HATCH DOOR
Part: THRESHOLD — CORRODED (ZONE 200) · airframe 35,490 hrs · 11,792 cycles
R1 DOOR LOWER CUTOUT THRESHOLD CORROSION AT LOCATIONS FR 16 Y1896 TO Y1944 GROUNDED - YES. REPAIRED 1 FASTENER HOLE AT R-1 DOOR SILL BEAM IAW A320 SRM 53-11-14-283-005 REV 148-01FEB2024. CATEGORY B REPAIR. INSPECTION THRESHOLD FROM FIRST AIRCRAFT FLIGHT 60000 FC/FH, NOT RELEVANT, SUBSEQUENT INSPECTIONS AT INTERVALS OF TBD, INSPECTION METHOD TBD. REMOVED CORROSION AT R1 DOOR SILL, FWD GIRT FITTING FWD I/B HOLE LENGTH 3.0" X WIDTH 2.8" DEPTH .172". MAXIMUM ALLOWABLE DEPTH IS .1476". FOUND TO BE WITHIN LIMITS IAW A320 SRM 53-11-14-283-005 REV 148 -01FEB2024
Part: THRESHOLD — CORRODED (ZONE 200) · airframe 35,490 hrs · 11,792 cycles
L1 THRESHOLD HAS MULTIPLE AERAS OF CORROSION FR 16-20 -73Y GROUNDED - YES. REPAIRED 3EACH FASTENER HOLES AT L-1 DOOR SILL BEAM IAW A320 SRM 53-11-14-283-005 REV 148-01FEB2024. CATEGORY B REAPIR. INSPECTION THRESHOLD FROM AIRCRAFT FIRST FLIGHT 60000 FC/FH NOT RELEVANT, SUBSEQUENT INSPECTIONS AT INTERVALS TBD, INSPECTION METHOD TBD. REMOVED CORROSION AT L1 DOOR FWD GIRT BAR FITTING AREA, AFT O/B FASTENER LENGTH 2.261"X WIDTH 1.973" DEPTH. .1485". L1 DOOR AFT GIRT BAR FITTING AREA, AFT O/B FASTENER LENGTH 1.812" X WIDTH 1.626" DEPTH .1485". ALLOWABLE REMAINING THICKNESS FOR 3EA. HOLES IS .1476". FOUND TO BE WITHIN LIMITS A320 SRM 53-11-14-283-005 REV 148 -01FEB2024
Part: WEB — CORRODED (AFT CARGO) · airframe 35,490 hrs · 11,792 cycles
AFT CARGO THRESHOLD CORRODED I/B OF PROTECTIVE PLATE GROUNDED - YES. REMOVED 11EA FASTENERS IN CORRODED AREAS IAW A320 SRM 53-41-49-283-004 REV 148-01FEB2024. REMOVED CORROSION FROM 5EA AREAS IAW A320 SRM 51-47-00/001 REV 148-01FEB2024 ACCOMPLISHED DVI IAW A320 SRM 53-41-49-283-004 REV 148-01FEB2024. ACCOMPLISHED HFEC INSPECTION IAW A320 NTM PT.6 51-10-08-250-802-A-01 USING T8257K DUE 28SEP24. NO RELEVANT INDICATIONS WERE NOTED. REMAINING LOWEST MAT. THICKNESS IS .057 WITH A ALLOWABLE DEPTH OF .047 LIMITS FOUND TO BE WITHIN LIMITS IAW A320 SRM 53-41-49-283-004 REV 148-01FEB 2024 UT T8224L DUE 20NOV24. CAT A REPAIR, FH: 35490 FC: 11792 ALODINED IAW A320 SRM 51-21-11 REV 148-01FEB2024. PRIMED AND TOP COAT IAW A320 SRM 51-75-12 REV 148-01FEB2024 INSTALLED 11EA FASTENERS IAW A320 SRM 53-41-49-283-004 REV 148-01FEB2024
Part: PLATE — CORRODED (THRESHOLD) · airframe 35,490 hrs · 11,792 cycles
AFT CARGO THRESHOLD CORRODED UNDER PROTECTIVE PLATE GROUNDED - YES. REMOVED CORROSION FROM AFT CARGO DOOR THRESHOLD IAW A320 SRM 51-74-00/001 REV 148-01FEB2024. ACCOMPLISHED A DVI OF AREA IAW A320 SRM 53-41-49-283-003 REV 148-01FEB2024 NO FURTHER CORROSION NOTED. ACCOMPLISHED HFEC INSPECTION OF AREA IAW A320 NTM PT.6, 51-10-08-250-802-A-01 USING T8257K DUE 28SEP24 NO RELEVANT INDICATIONS WERE NOTED. REMAINING LOWEST MAT. THICKNESS IS .090 WITH ALLOWABLE DEPTH AFTER CLEAN UP OF .083 LIMITS FOUND WITHIN LIMITS IAW A320 SRM 53-41-49-283-003 REV 148-01FEB2024 UTT8224L DUE 20NOV24. ALODINED IAW A320 SRM 51-21-11 REV 148-01FEB2024. PRIMED CAT A. REPAIR FH:35490 FC:11792 AND TOP COAT PAINT IAW A320 SRM 51-75-12 REV 148-01FEB2024
Earlier reports · 2012–2022 · 11 reports
2022
Part: SLIDE — DETACHED (L1 DOOR) · airframe 35,268 hrs · 11,693 cycles
L1 DOOR SLIDE LOOSE FROM ITS CONTAINER. EXPOSING THE SLIDE ON THE BOTTOM, BLOCKING AND PREVENTING THE DOOR TO CLOSE GROUNDED - YES. INSTALLED ESCAPE SLIDE PACK ASSEMBLY (7500MM) IAW AMM 25-62-44.
2021
Part: ANGLE — CORRODED · corrosion level 2 · airframe 32,623 hrs · 10,570 cycles
FWD SIDE OF ACCESS DOOR 312AR CUTOUT FRAME 71 HAS CORROSION ON LOWER SUPPORT ANGLE (CLIP) GROUNDED - YES. DUE TO THE EXTENT OF THE CORROSION (50% MATERIAL LOSS), REMOVED LOWER SUPPORT ANGLE (CLIP) FROM FWD SIDE OF ACCESS DOOR 312AR CUTOUT AT FRAME #71. REPLACED WITH NEW ANGLE (CLIP)
2019
Part: FLOORBOARD — DELAMINATED (FRAMES 32-35) · airframe 28,987 hrs · 8,932 cycles
FLOOR BOARD 231VF SOFT/ DELAM GROUNDED - YES. RECEIVED NEW FLOOR PANEL P/N E5367190600000. FLOOR PANEL INSTALLED ON CUSTOMER CARD NUMBER 5300-INST-320-01 OPS 2224 JPD STEP 017.
2018
Part: PROXIMITY SENSOR — FAILED (MLG) · airframe 24,577 hrs · 7,380 cycles
LGCIU NR 1 FAULT. OUT OF 3000FT GEAR DOORS WERE SLAMMING INTO A/C ON SEVERAL TIMES. GROUNDED - YES. REMOVED AND REPLACED PROXIMITY SENSOR (FIN=26GA) PER REF AMM 32-31-73-000-001-A AND AMM 32-31-73-400-001-A. OPS CHECK GOOD. NO FURTHER DEFECTS NOTED.
2017
Part: SHEAR PLATE — CRACKED (FRAMES 69 - 70)
FOUND CORROSION ON AFT CABIN AREA RT LATERAL SHEAR PLATE BTW FR 69 - 70. THE EXTENT OF THE DAMAGE IS L2" X W2" DEPTH EXCEEDED 25%. SHEAR PLATE WAS R & R IAW A320 SRM 51-42-11.
Part: SHEAR PLATE — CRACKED (FRAMES 69-70)
FOUND CRACK ON AFT CABIN AREA LT LATERAL SHEAR PLATE BTW FR 69 - 70. SHEAR PLATE WAS R & R IAW A320 SRM 51-42-11.
Part: BOLT — SHEARED (NLG)
DURING TAXI OUT, CAPTAIN REPORTED LOSS OF STEERING, ACFT WAS TOWED BACK TO THE GATE, MX FOUND THAT THE APEX BOLT SHEARED CAUSING THE SCISSOR LINKS TO COME APART AND THE NOSE WHEEL TO TURN 180 DEGREES. MX REPLACED THE NLG ASSEMBLY.
2016
Part: FAN — FAILED (CABIN)
AT 10000 FT, ON APPROACH, SMELLED ELECTRICAL SMOKE, FOLLOWED BY LOW FREQUENCY NOISE FROM BLOWER FAN. NOISE AND ODOR ABATED WITH BLOWER PB OVER RIDE. THE BLOWER FAN WAS FOUND FAILED AND WAS PLACED ON MEL. DURING T/S FOUND BLOWER MOTOR INOPERATIVE MEL 21-26-01-02 APPLIED. MAINTENANCE NOTIFIED. MEL LIST UPDATED. PLACARD INSTALLED. IN ADDITION, THE FOLLING INSPECTION WAS COMPLETED. INSPECTED ACFT AND IFE FOR SMOKE ODOR THROUGHOUT THE CABIN IAW TSM 24-00-00-810-823-A AND IFE TBN 4430-04. NO FURTHER DEFECTS NOTED. ACFT OK FOR SERVICE.
2014
Part: ECU — MALFUNCTIONED (NR1)
NR 1 ENGINE SPOOLED BACK ON FINAL ENGINE 1 THR DISAGREE. TROUBLESHOT IAW TSM 76-11-00-810-813-A PARA 4A, ALL WIRING CHECK GOOD. R & R THROTTLE CONTROL UNIT IAW AMM 76-11-19 PB 401. TEST PERFORMED AND BITE TEST OF THE EFCS GROUND SCANNING. NO FAULTS RECORDED. ACFT OK FOR SERVICE. DURING CLIMB, ECAM THRUST LEVERS DISAGREE, CAME ON THEN OFF TWICE IN LESS THAN 5 MINUTES, MAINTENANCE REQUESTED RETURN TO DEPARTURE. R & R NR 1 ENGINE ECU IAW AMM 73-21-60-000-B OPS CHECK GOOD. C/W T/S IAW TSM 76-11-00-710-813-A, IAW TSM CHECKED ELECTRICAL RESISTANCE TEST THROUGH J3 HARNESS. PINS 17-30, 43.9, PINS 5 AND 15, 26.4, PINS 29 AND 28, 13.83, PINS 5 AND 16, 15.13, PINS 29-16, 15 MEGA OHMS, PIN 17 AND GROUND, 14.72 MEGA OHM, PIN 29, GROUND, 14.66, ALL WITHIN RANGE IAW TSM R & R ECU.
Part: THROTTLE — MALFUNCTIONED (NR 1 ENGINE)
NR 1 ENGINE SPOOLED BACK ON FINAL, ENGINE 1 THR DISAGREE. TROUBLE SHOT IAW TSM 76-11-00-810-813-A PARA 4A ALL WIRING CHECK GOOD. R & R THROTTLE CONTROL UNIT IAW AMM 76-11-19, PB 401. TEST PERFORMED AND BITE TEST OF THE EFCS GROUND SCANNING. NO FAULTS RECORDED. ACFT OK FOR SERVICE.
2012
Part: HMU — DEFECTIVE (NR 2 ENGINE) · airframe 2,628 hrs · 779 cycles
CREW REPORTED ENG 2 THRUST WAS UNRESPONSIVE. VIA AIRCELL, THE CREW ADVISED THAT AT THE TOP OF DESCENT, WHEN THE THRUST WAS RETARDED, ENG 2 REMAINED AT CRUISE POWER SETTING. THE ECAM MESSAGE " ENG 2 FUEL CTL" FAULT WAS DISPLAYED. MCC REVIEWED THE FCOM WITH THE CREW/DISPATCHED AND ADVISED PRO-ABN 70 P45/82 AS A REFERENCE. THE CREW ADVISED THAT IF THEY COULD NOT HAVE CONTROL OF THE ENGINE THEY WOULD PROCEED WITH THE FCOM PROCEDURE AND SHUTDOWN THE NR 2 ENGINE. THEN THE AIRCELL DROPPED. THE CREW CONTACTED OCC A FEW MINUTES LATER VIA AIRINC, ADVISING THAT DESCENDING THROUGH 17,000 FT THE ENGINE BECAME RESPONSIVE AND THEY WOULD CONTINUE WITHOUT SHUTTING DOWN THE ENGINE. EMERGENCY WAS DECLARED, ACFT LANDED WITHOUT INCIDENT. MX PERFORMED TSM TASK 73-10-00810-802-A AND FOUND RESISTANCE OUTSIDE ALLOWABLE LIMITS FOR THE HMU. ENG 2 HMU PN 8061-536, SN WYGD0192 WAS REPLACED. ALL OPS CHECKS WERE PERFORMED AND THE ACFT WAS RETURNED TO SERVICE.