N844VA
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, 2016-05-25 – 2023-10-19.
Part: SKIN — DENTED (UNKNOWN) · airframe 36,939 hrs · 12,259 cycles
REEVALUATE 1 EACH DENT AT RH FWD FUSELAGE FWD OF FWD CARGO DOOR CUTOUT BETWEEN FR 24 AND FR24A AND BETWEEN STR 31 AND STR 32 GROUNDED - YES. EVALUATED DENT LENGTH .400, WIDTH .300 DEPTH .005, NEAREST STIFTNER 1.0 D/A=.005 LOCATED BETWEEN FR24 AND FR24A AND BETWEEN STR 31 AND STR 32, FWD OF CARGO DOOR 3.85 AND AFT OF STATIC PORT 14.25 FOUND TO BE WITHIN LIMITS REF A320 SRM 53-00-11-283-005 HFEC AND DVI NO DEFECTS NOTED REF A320 NTM PT6 51-10-08 AND NTM-ASA-07-ASA-320 THIS IS A CAT B REPAIR INSPECTION THRESHOLD FROM ADL 60,000FC 120,000 FIT INTERVAL NA METHOD NA APPLIED DENT DOT REF ASA GPM 05-00-30 CONTACTED SEAMAC JOHN NOTIFIED
Part: FITTING — CORRODED (UNKNOWN) · corrosion level 2 · airframe 36,929 hrs · 12,255 cycles
DURING REMOVAL OF L1 DOOR SILL, FOUND UPPER, L/H FLOOR SUPPORT FITTING FOR SCUFF PLATE TO BE CORRODED GROUNDED - YES. RECEIVED NEW FITTING P/N D5311219820006 PO 1068187.1 REF ASA EA A320-53EA-01919 PART REMOVED AND REPLACED ON CUSTOMER CARD G1807072 HAECO CARD 25072 RFTS ACCOMPLISHED ON CUSTOMER CARD G1807071 HAECO CARD 25071 NO FURTHER ACTION REQUIRED
Part: FLOOR PANEL — CORRODED (UNKNOWN) · corrosion level 2 · airframe 36,929 hrs · 12,255 cycles
FWD ENTRY FLOOR PANELS CORRODED 222FF AND 221FF GROUNDED - YES. REMOVED AND REPLACED CORRODED FWD ENTRY FLOOR PANELS 222FF AND 221FF IAW ALASKA A320 AMM 53-00-00-400-801-A. PO 1067508.1 AND PO 1067508.2 TOOL T05867-140 CAL DUE 04/FEB/24. FLOOR PANEL SEALANT ACCOMPLISHED CC G1807100 OPS 25100
Part: SKIN — DENTED (UNKNOWN) · airframe 36,929 hrs · 12,255 cycles
EVALUATE DENT ON AFT FUSELAGE APPROX. BETWEEN FR81 AND FR83 AND BETWEEN STR4L AND STR5L GROUNDED - YES. DENT FOUND TO BE OUT OF LIMITS, REMOVED DAMAGE, LOCATED, DRILLED, INSTALLED REPAIR DOUBLER AND RESTORED COATINGS REF A320 SRM 53-51-11-300-002. THIS IS A CAT A REPAIR NO FURTHER ACTION REQUIRED AND A320 SRM 53-00-11-283-005
Part: SKIN — GOUGED (UNKNOWN) · airframe 36,935 hrs · 12,256 cycles
FOUND EXISTING GOUGES ON RH WING LOWER SURFACE INBD OF FUEL PANEL 640LB GROUNDED - YES. REMOVED DAMAGE ORIG .280, MATERIAL LOSS .011 REMAINING .269 4.0 LENGTH .500 WIDTH, HFEC AND OPEN HOLE AND DVI NO DEFECT NOTED, RESTORED COATING FOUND TO BE WITHIN LIMITS REF ASA EA A320-57EA-01909 REV 00 THIS IS A CAT B REPAIR POST REPAIR INSPECTION THRESHOLD 3300 FC 6600 FH WHICHEVER OCCURS FIRST INTERVAL 3300 FH 6600 FC WHICHEVER OCCURS FIRST METHOD GVI WITH FUEL PANEL IN PLACE
Part: SEAT TRACK — CORRODED (UNKNOWN) · corrosion level 2 · airframe 36,934 hrs · 12,256 cycles
MAIN CABIN SEAT TRACK CORRODED BETWEEN FR 20 AND FR 21 AT Y-1292 GROUNDED - YES. REMOVED, LOCATED, DRILLED AND INSTALLED NEW SEAT TRACK AIRBUS DWG D53918124 ISSUE B AND A320 SRM 51-42-11/001
Part: SKIN — GOUGED (UNKNOWN) · airframe 36,935 hrs · 12,256 cycles
FOUND EXISTING GOUGE ON RH WING LOWER SKIN NEAR FUEL PANEL 640LB OPENING GROUNDED - YES. REMOVED DAMAGE ORIG .280 MATERIAL LOSS .060 REMAINING .220 2.10 LENGTH 1.10 WIDTH HFEC AND DVI NO DEFECTS NOTED, RESTORED COATINGS FOUND TO BE WITHIN LIMITS REF ASA EA A320-57EA-1909 REV 00 THIS IS A CAT B REPAIR, POST INSPECTION THRESHOLD 3300 FC, 6600 FH WHICHEVER OCCURS FIRST INTERVAL 3300 FC, 6600 FH WHICHEVER OCCURS FIRST METHOD GVI WITH FUEL DOOR IN PLACE
Part: SKIN — DAMAGED (UNKNOWN) · airframe 36,935 hrs · 12,256 cycles
FOUND EXISTING RH WING FUEL PANEL 640LB OPENING FASTENER HOLES 3 EACH ELONGATED GROUNDED - YES. REAMED HOLES TRUE AND ROUND, FINAL HOLE SIZES #603 = 0.537-IN, #655= 0.634-IN, #645= 0.325 IN HFEC ON OPEN HOLE AND DVI NO DEFECTS NOTED. COLD WORKED HOLES, FABRICATED, AND INSTALLED REPAIR BUSHINGS, AND RESTORED COATINGS REF ASA EA A320-57EA-01909 REV OO THIS IS A CAT B REPAIR, POST REPAIR INSPECTION THRESHOLD 3300 FC 6600 FH WHICHEVER OCCURS FIRST, INTERVAL 3300 FC 6600 F/H WHICHEVER OCCURS FIRST METHOD GVI WITH FUEL DOOR IN PLACE.
Part: SKIN — DAMAGED (RT FUEL PANEL) · airframe 36,935 hrs · 12,256 cycles
FOUND EXISTING RH WING FUEL PANEL 640KB OPENING FASTENER HOLES 4 EACH ELONGATED GROUNDED - YES. REAMED HOLES TRUE AND ROUND, FINAL HOLE SIZES #603= .343, #624= .421, #622= .4375, #615 = .4375, HFEC AND OPEN HOLE AND DVI NO DEFECTS NOTED, COLD WORKED HOLES, FABRICATED AND INSTALLED REPAIR BUSHINGS, RESTORED COATINGS REF ASA EA A320-57EA-01909 REV 00 THIS IS A CAT B REPAIR POST REPAIR INSPECTION THRESHOLD 30800 FC 58000 FH WHICHEVER OCCERS FIRST INTERVAL 3300FC 6600FH WHICHEVER OCCURS FIRST METHOD GVI WITH FUEL PANEL (DOOR) IN PLACE
Part: SKIN — CORRODED (UNKNOWN) · airframe 36,929 hrs · 12,255 cycles
LH WING INBOARD FLAP LOWER SURFACE HAS CORROSION AND MISSING INSPECTION PLUG GROUNDED - YES. REMOVED DAMAGE ORIG .023 MATERIAL LOSS .009 REMAINING .014 LOCATED AT RIB 3 12.25 INCHES FORWARD OF T/E 22 INCHES OUTBD OF RIB 1, HFEC AND DVI NO DEFECTS NOTED, RESTORED COATINGS AND INSTALLED INSPECTION PLUG REF ASA EA CMPT-57EA-01904 REV 00. THIS IS A CAT A REPAIR NO FURTHER ACTION REQUIRED.
Part: FITTING — DAMAGED (VERTICAL STAB) · airframe 36,929 hrs · 12,255 cycles
VERTICAL STAB HINGE ARM #4 HAS DAMAGED HOLE FOR RUDDER HINGE FITTING GROUNDED - YES. REAMED HOLES TRUE AND ROUND ON #4 STAB HINGE ARM, HFEC AND DVI OF PART NO DEFECTS NOTED REF ASA EA A320-55EA-01883 REV 00 NEW FITTING AND FASTENERS INSTALLED ON CUSTOMER CARD 553600-01-1 AND HAECO CARD 630 ATTACHED. THIS IS A CAT B REPAIR INSPECTION THRESHOLD IS 24,200 FC FROM EMBODIMENT INSPECTION INTERVAL IS 24,200 FC AND METHOD OF INSPECTION IS DVI AS PER A320 NTM 51-90-00 ON ALL BR FITTINGS.
Part: DOOR SILL — CORRODED (UNKNOWN) · corrosion level 2 · airframe 36,935 hrs · 12,256 cycles
R2 DOOR LOWER SILL CORRODED AT 3 EACH FASTENER HOLES AT THE AFT LOWER CORNER OF THE DOOR CUTOUT. MARKED GROUNDED - YES. REMOVED AND REPLACED R2 LOWER DOOR SILL REF AIRBUS DWG D53480505 ISSUE CE AND A320 SRM 51-42-11 FLOOR REMOVED CORROSION AT ATTACHMENT HOLES REAMED TO .516, MAX ALLOWED IS .354 FOUND TO BE OUT OF LIMITS REF A320 SRM 53-41-14-283-002FIG 2. SH 1 FLAGNOTE 07
Part: DOOR SILL — CORRODED (UNKNOWN) · airframe 36,929 hrs · 12,255 cycles
MAIN CABIN R1 DOOR LOWER CORNER, AFT GIRT BAR PLATE DRAIN ACCESS HOLE HAS CORROSION (MARKED IN RED) GROUNDED - YES. REMOVED CORROSION AROUND R1 DOOR AFT GIRT BAR DRAIN, ORIG .197 MATERIAL LOSS .007 REMAINING .190 FOUND TO BE WITHIN LIMITS, HFEC DVI NO DEFECTS NOTED. RESTORED COATINGS REF A320 SRM 53-11-14-183-005 THIS IS A CAT B REPAIR INSPECTION THRESHOLD FROM AIRCRAFT FIRST FLIGHT 60,000 FC/FH NOT REVELANT, INSPECTION METHOD TBD REF A320 SRI 53-11-14-205-001
Part: DOOR SILL — CORRODED (UNKNOWN) · corrosion level 2 · airframe 36,929 hrs · 12,255 cycles
MAIN CABIN R1 DOOR LOWER CORNER; AFT GRIT BAR PLATE AREA HAS CORROSION ON SKIN AND (4EA) HILOSCK PINS (MARKED IN RED) GROUNDED - YES. REMOVED DAMAGE ON SILL FR19 AND FR20 AT -Y1950 LOWEST MATERIAL LOSS .142, HFEC SURFACE AND OPEN HOLE AND DVI NO DEFECTS NOTED. FABRICATED REPAIR WASHERS, TREATED AREA AND WASHERS, INSTALLED REPAIR WASHERS AND RESTORED COATINGS REF ASA EA A320-53EA-01889 REV 00. THIS IS A CAT B REPAIR FATIGUE PROGRAM THRESHOLD 97,320 FC (FH NOT RELEVANT) INTERVAL AND METHOD TBD CORROSION INSPECTION TH 3YRS INTERVAL 3YEARS METHOD DVI PER NTM 51-90-00 TO CHECK THERE IS NO CORROSION DAMAGE CPC TO BE RESTARTED AFTER EACH INSPECTION
Part: DOOR SILL — CORRODED (UNKNOWN) · corrosion level 2 · airframe 36,929 hrs · 12,255 cycles
MAIN CABIN L1 DOOR LOWER CORNER; FWD GIRT BAR PLATE AREA HAS CORROSION ON SKIN AND (4EA) HILOSCK PINS(MARKED IN RED) GROUNDED - YES. REMOVED AND INSTALLED NEW SILL REF AIRBUS DWG D53135033 ISSUE B AND A320 SRM 51-42-11/001 ALL WORK ACCOMPLISHED ON CUSTOMER CARD G1807072 AND HAECO CARD 25072 ATTACHED NO FURTHER ACTION REQUIRED . REMOVED CORROSION ORIG. .197 MATERIAL LOSS .057 REMAINING .140 FOUND TO BE OUT OF LIMITS REF A320 SRM 53-11-14-283-005 PART REPLACED ABOVE.
Part: FLOOR PANEL — DELAMINATED (UNKNOWN) · airframe 36,929 hrs · 12,255 cycles
FLOOR PANEL 261PF HAS DELAM AT THE FWD LH CORNER GROUNDED - YES. REMOVED AND REPLACED FLOOR PANEL 261PF WITH NEW IAW ALASKA AIRBUS A320 AMM 53-00-00-400-801-A-01. TOOL #T05867-116 CAL DUE 03/NOV/23 SEALANT TO BE ACCOMPLISHED ON ALASKA AIRLINES CUSTOMER CARD #G1807100 PO 1064892.1
Part: DOOR SILL — CORRODED (UNKNOWN) · corrosion level 2 · airframe 36,929 hrs · 12,255 cycles
MAIN CABIN R1 DOOR CORNER; FWD GIRT BAR PLATE AREA HAS CORROSION ON SKIN AND (4EA) HILOSCK PINS (MARKED IN RED) GROUNDED - YES. REMOVED DAMAGE ON SILL BETWEEN FR16 AND FR17 AT -Y1952 LOWEST MATERIAL LOSS .134, HFEC AND OPEN HOLE AND DVI NO DEFECTS NOTED. FABRICATED REPAIR WASHERS, TREATED AREA AND WASHERS, INSTALLED REPAIR WASHERS AND RESTORED COATINGS REF ASA EA A320-53EA-01889 REV 00. THIS IS A CAT B REPAIR FATIGUE PROGRAM THRESHOLD 97,320 FC (FH NOT RELEVANT) INTERVAL AND METHOD TBD CORROSION INSPECTION TH 3YRS INTERVAL 3YEARS METHOD DVI PER NTM 51-90-00 DO CHECK THERE IS NO CORROSION DAMAGE CPC TO BE RESTARTED AFTER EACH INSPECTION
Part: DOOR SILL — CORRODED (UNKNOWN) · corrosion level 2 · airframe 36,929 hrs · 12,255 cycles
MAIN CABIN L1 DOOR LOWER CORNER; AFT GIRT BAR PLATE AREA HAS CORROSION ON SKIN AND (4EA) HILOSCK PINS (MARKED IN RED) GROUNDED - YES. REMOVED AND INSTALLED NEW LOWER SILL REF AIRBUS DWG D53135033 ISSUE B AND A320 SRM 51-42-11/001 REMOVED CORROSION ORIG. .197 MATERIAL LOSS .050 REMAINING .147 FOUND TO BE OUT OF LIMITS REF A320 SRM 53-11-14-283-005 FIG 001 SHEET 2. REPLACED PART ABOVE .
Part: FITTING — WORN (UNKNOWN) · airframe 36,924 hrs · 12,254 cycles
MAIN CABIN FWD WET AREA, NOSE WHEEL WELL ATTACHED FITTING WORN AT FR20 APPROX. Y533 AND APPROX. 24" INCHES BELOW THE FLOOR PANEL. STREAMER ATTACHED GROUNDED - YES. REMOVED AND REPLACED NOSE WHEEL WELL ATTACHED FITTING REF A320 SRM 51-42-11/001 AND AIRBUS DWG D53113582 ISSUE Y
Part: BEAM — CORRODED (UNKNOWN) · corrosion level 2 · airframe 36,934 hrs · 12,256 cycles
MAIN CABIN AFT WET AREA, LONGITUDINAL BEAM UPPER SURFACE CORRODED BETWEEN FR69 AND FR70 APPROX Y765.MARKED GROUNDED - YES. REMOVED AND REPLACED LONGITUDINAL BEAM LOCATED IN MAIN CABIN, AFT WET AREA BETWEEN FR69 & FR70, APPROX. Y765 PER AIRBUS DWG D53472040 AND A320 SRM 51-41-11.
Part: BEAM — CORRODED (UNKNOWN) · corrosion level 2 · airframe 36,934 hrs · 12,256 cycles
MAIN CABIN AFT WET AREA, LONGITUDINAL BEAM UPPER SURFACE CORRODED BETWEEN FR67 AND FR68 APPROX. Y1292. MARKED GROUNDED - YES. REMOVED AND REPLACED LONGITUDINAL BEAM LOCATED IN MAIN CABIN, AFT WET AREA BETWEEN FR67 TO FR68, APPROX. Y1292 PER AIRBUS DWG D53472001 AND A320 SRM 51-41-11
Part: BEAM — CORRODED (UNKNOWN) · corrosion level 2 · airframe 36,934 hrs · 12,256 cycles
MAIN CABIN AFT WET AREA, LONGITUDINAL BEAM UPPER SURFACE CORRODED BETWEEN FR69 AND FR70 APPROX. -Y254. MARKED GROUNDED - YES. REMOVED AND REPLACED LONGITUDINAL BEAM LOCATED IN MAIN CABIN, AFT WET AREA, BETWEEN FR69 TO FR70 APPROX. -Y254 PER AIRBUS DWG D53472040 AND A320 SRM 51-41-11
Part: BEAM — CORRODED (UNKNOWN) · corrosion level 2 · airframe 36,934 hrs · 12,256 cycles
MAIN CABIN AFT WET AREA, LONGITUDINAL BEAM UPPER SURFACE CORRODED AROUND MOUNTING HOLES BETWEEN FR68 AND FR70 APPROX. Y254. MARKED GROUNDED - YES. REMOVED AND REPLACED LONGITUDINAL BEAM LOCATED IN MAIN CABIN, AFT WET AREA BETWEEN FR68 AND FR70, APPPROX. Y254 PER AIRBUS D53472040 AND A320 SRM 51-41-11.
Part: BEAM — CORRODED (UNKNOWN) · corrosion level 2 · airframe 36,934 hrs · 12,256 cycles
MAIN CABIN AFT WET AREA, LONGITUDINAL BEAM UPPER SURFACE CORRODED BETWEEN FR67 AND FR68 APPROX. -Y765. MARKED 844VA GROUNDED - YES. REPLACED LONGITUDINAL BEAM P/N D5347219320400 PO# 1064746.2 IAW A320 SRM 51-41-11/001 AND AIRBUS DWG# D53472040 ISSUE "A". REMOVED HAECO DOT
Part: DOOR SILL — CORRODED (UNKNOWN) · corrosion level 2 · airframe 36,934 hrs · 12,256 cycles
L2 LOWER OUTBD DOOR SILL CORRODED IN SEVERAL AREAS GROUNDED - YES. REMOVED AND REPLACED L2 LOWER OUTBD DOOR SHAPE SILL PN# D5348004820203 PO# 0 IAW AIRBUS DWG D53480505000 AND A320 SRM 51-42-11
Part: BEAM — CORRODED (UNKNOWN) · corrosion level 2 · airframe 36,934 hrs · 12,256 cycles
MAIN CABIN AFT WET AREA, LONGITUDINAL BEAM UPPER SURFACE CORRODED BETWEEN FR68 AND FR69 APPROX. -Y1292. MARKED GROUNDED - YES. REMOVED AND REPLACED LONGITUDINAL BEAM LOCATED IN MAIN CABIN, AFT WET AREA, BETWEEN FR68 TO FR69 APPROX . -Y1292 PER AIRBUS DWG D53472040 AND A320 SRM 51-42-11.
Part: REPAIR — DELAMINATED (LT WING TE FLAP) · airframe 36,935 hrs · 12,256 cycles
ITEM 255 - CONFIRM CONFORMANCE LH WING INB AFT FLAP REPAIR PLUS ADDITIONAL DAMAGES (DB6 ABD DB8) ACFT GROUNDED. EVALUATED & REPAIRED ITEM 255 LT WING INBD AFT FLAP PREVIOUS REPAIR PLUS ADDITIONAL DAMAGES DB8 AND DB6. LOCATED 49ÿ½ TO 60.5ÿ½ FROM THE INBD EDGE OF THE FLAP AND 0ÿ½ TO 6.75ÿ½ FROM THE TRAILING EDGE. REPAIR DOUBLER SIZE IS 11.5ÿ½ TO 6.75ÿ½. - .032ÿ½ AND RESTORED FINISH. IAW A320 SRM 57-52-00-300-0-95; A320 SRM 51-25-00 REV 145/01MAY2023; A320NTM 51-10-03-01; A320-200 SRM 51-77-13-911-013; A320-200 SRM 51-21-11; A321-200N SRM 51-77-11-214, SN:4851
Part: SKIN — DELAMINATED (FLAP) · airframe 36,929 hrs · 12,255 cycles
LESSOR ITEM 269 - PLEASE CONFIRM CONFORMANCE AND ON D&B, REPAIR ON RH AFT INB TE FLAP (DB9) GROUNDED - YES. EVALUATED LESSOR ITEM 269 DOT DB9 ON RH AFT INBD TE FLAP AND FOUND PREVIOUS REPAIR PATCH ON LOWER SURFACE TO BE DELAMINATED PATCH IS 49.75" FRON INBD EDGE, 2" FOM TE. PATCH DIMENSIONS ARE 6.5"X7" DELAMINATION WAS 2" FROM EDGE 2.5" FROM INBD EDGE OF PATCH REQUIRED REPAIR IAW ASA A320-200 SRM 57-52-00-283-019 ZONE62 ALLOWABLE DAMAGE. REMOVED PREVIOUS REPAIR PATCH AND REPAIRED WITH NEW PATCH DIMENSIONS 6.5"X7". PATCH IS 49.75" FROM INBD EDGE, 2" FROM T/E. IAW ASA CMPT-57EA-01899 AND ASA A320-200 SRM REV145 57-52-00-300-095, SRM51-25-00, SRM51-77-13-911-013 PARA 2.A(2).(D), SRM-77-11-911-007. A320-214 S/N4851 FH:36934:38 FC:12256 WV:015
Earlier reports · 2016–2022 · 7 reports
2022
Part: SKIN — CORRODED (LT WING) · airframe 36,921 hrs · 12,253 cycles
LEFT WING UPPER SURFACE HAS A DENTED PANEL FWD OF THE IB GROUND SPOILER GROUNDED - YES. REMOVED CORROSION AT THREE LOCATION ORIG. .248 AT LOCATION A, MATERIAL LOSS.110. REMAINING .138 ORIG AT LOCATION B .248, MATERIAL LOSS .045, REMAINING .203 ORIG AT LOCATION C .248, MATERIAL LOSS .056, REMAINING .192. REMOVED AND REINSTALLED FITTINGS AT EACH LOCATION, HFEC AREAS AND OPEN HOLES. RESTORED COATINGS REF ASA EA A320-57EA-01597 REV 00, A320 SRM 57-21-11-283-007 AND A320 SRM 51-42-11. THIS IS A CAT B REPAIR INSPECTION THRESHOLDS OF 60,000 TOTAL AIRFRAME FC OR 120,000 FH WHICHEVER IS EARLIER AND AN INSPECTION INTERVAL TBD.
2020
Part: ACTUATOR — FAILED (RUDDER SERVO) · airframe 30,291 hrs · 9,346 cycles
AT CRUISE, FL 360, THE AIRCRAFT HAD AN UNCOMMANDED YAW. NO ECAM. UNCOMMNDED RUDDER MOVEMENT IN FLIGHT AT 36000FEET - EMERGENCY LANDING DECLARED GROUNDED - YES. PER TSM 27-26-00-810-801-A. PRECAUTIONARY REPLACEMENT OF L/H YAW DAMPER SERVO ACTUATOR (FIN 3CC1) REF AMM 27-26-51. LEAK CHECK AND ADJUSTEMNT STILL REQ'D I DILLON 66641. RII F. CRUZ 98566 ACCOMPLISHED ADJ / TEST OF YAW DAMPER REF AMM 27-26-00-820-001-A LEAK CK GOOD.
2017
Part: BEARING — LACK OF LUBE (L1 DOOR) · airframe 21,681 hrs · 6,460 cycles
L1 DOOR REPORTED DIFFICULT TO OPEN & CLOSING & STICKING DURING OPERATION. LUBRICATED HINGE ARM SUPPORT FITTING BEARINGS IAW ANM 12-22-52-640-016-A. OPERATIONS CHECKED GOOD. NO DEFECTS NOTED AT THIS TIME.
Part: SEAL — OUT OF POSITION (NLG DOOR)
NOISE HEARD IN NOSE REAR GEAR DOORS IN NOSE OF ACFT LESS THAN FL 100 + 250KTS. ACFT RETURNED TO THE FIELD AS A PRECAUTIONARY MEASURE. ACCOMPLISHED TSM 05-50-00-18-08-01A TYPE 8. FOUND DIMENSION OF ACFT NOSE GEAR DOORS WITHIN LIMITS IAW AMM 32-22-00-22-00-02A. PERFORMED VISUAL INSPECTION OF ROTATING ROD OF NOSE GEAR AFT DOOR, NO DAMAGE NOTED. FOUND NLG AFT DOOR SEAL DISLODGED. ACFT WAS FERRIED TO LAX AND THE SEAL WAS SECURED. NO FURTHER REPORTS OF NOISE OR VIBRATION REPORTED ON SUBSEQUENT FLIGHTS.
2016
Part: SERVO — FAILED (RT ELEVATOR) · airframe 17,505 hrs · 5,255 cycles
REPORTED AN ABNORMAL VIBRATION IN THE AIRFRAME DURING THE FLIGHT CONTROL CHECK AFTER PUSH BACK AND RETURNED TO THE GATE. LOCAL MAINTENANCE CONTRACTOR EVALUATED AND THE CONFIRMED THE CONDITION, THE AIRCRAFT WAS REMOVED FROM SERVICE FOR TROUBLESHOOTING AND REPAIR. TECHS WERE DISPATCHED TO AID IN TROUBLESHOOTING. THE VIBRATION WAS ISOLATED TO THE RT ELEVATOR DURING SLOW APPLICATION OF NOSE DOWN COMMAND, NO ABNORMALITIES NOTED DURING NORMAL INPUT RATE AND NO REPORTS OF INFLIGHT VIBRATION. THE BLUE HYDRAULIC SYSTEM ELEVATOR SERVO WAS REPLACED BUT DID NOT CORRECT THE ISSUE. THE AIRCRAFT WAS INSPECTED AND DEEMED SAFE FOR FLIGHT AND MAINTENANCE FERRIED FOR CONTINUED TROUBLESHOOTING. TECH REPLACED THE YELLOW HYDRAULIC SYSTEM ELEVATOR SERVO IAW AMM 27-34-51 AND ACCOMPLISHED SUCCESSFUL FLIGHT CONTROL CHECKS. THE ACFT WAS RETURNED TO SERVICE.
Part: REGULATOR — FAILED (NR 2 A/C PACK)
ACFT EXPERIENCED AN AIR PACK NR 2 FAULT ON CLIMBOUT. THE NR 1 PACK HAD BEEN PREVIOUSLY DEFERRED IAW MEL 21-52-01-07 AND LOCKED OUT. THE FLIGHT CREW FOLLOWED FCOM AND QRH PROCEDURES AND DIVERTED. THE ACFT NEVER LOST CABIN PRESSURE. UPON ARRIVAL, TECHS REPAIRED THE NR 1 PACK BY REPLACINGTHE REGULATOR IAW AMM 21-51-51 PB 401 AND REPAIRED THE NR 2 PACK BY REPLACING THE ACSC IAW AMM 21-61-34- PB401. THE ACFT WAS RETURNED TO SERVICE AND DEPARTED, NO PACK RELATED FAULTS NOTED ON SUBSEQUENT FLIGHTS.
Part: A/C PACK — FAULTED (NR 2) · airframe 19,366 hrs · 5,026 cycles
ACFT EXPERIENCED AN AIR PACK NR 2 FAULT ON CLIMBOUT. THE NR 1 PACK HAD BEEN PREVIOUSLY DEFERRED IAW MEL 21-52-01-07 AND LOCKED OUT. THE FLIGHT CREW FOLLOWED FCOM AND QRH PROCEDURES AND DIVERTED. THE ACFT NEVER LOST CABIN PRESSURE. UPON ARRIVAL, TECHS REPAIRED THE NR 1 PACK BY REPLACING THE REGULATOR IAW AMM 21-51-51 PB 401 AND REPAIRED THE NR 2 PACK BY REPLACING THE ACSC IAW AMM 21-61-34- PB401. THE ACFT WAS RETURNED TO SERVICE AND DEPARTED, NO PACK RELATED FAULTS NOTED ON SUBSEQUENT FLIGHTS.