W DOC AIRBUS | AMM A320F

Install/Close of the Trimmable Horizontal Stabilizer (THS) Trailing-Edge Access-Panels

TASK 55-13-11-400-001-A
Install/Close of the Trimmable Horizontal Stabilizer (THS) Trailing-Edge Access-Panels

WARNING: MAKE SURE THAT THE TRAVEL RANGES OF THE FLIGHT CONTROLS SURFACES ARE CLEAR. MOVEMENT OF FLIGHT CONTROLS CAN CAUSE INJURY TO PERSONS AND/OR DAMAGE TO EQUIPMENT.
WARNING: PUT THE SAFETY DEVICES AND THE WARNING NOTICES IN POSITION BEFORE YOU START A TASK ON OR NEAR:
  • THE FLIGHT CONTROLS
  • THE FLIGHT CONTROL SURFACES
  • THE LANDING GEAR AND THE RELATED DOORS
  • COMPONENTS THAT MOVE.
MOVEMENT OF COMPONENTS CAN KILL OR CAUSE INJURY TO PERSONS AND/OR CAN CAUSE DAMAGE TO THE EQUIPMENT.
WARNING: YOU MUST PUT ON AND ATTACH A SAFETY HARNESS BEFORE YOU START WORK:
  • ON THE THS OR IN THE REAR FUSELAGE
  • ON TOP OF THE WINGS OR PYLONS.
WITHOUT A SAFETY HARNESS, YOU CAN FALL. THIS CAN KILL YOU OR CAUSE YOU INJURY.
WARNING: BE CAREFUL WHEN YOU USE CONSUMABLE MATERIALS. OBEY THE MATERIAL MANUFACTURER'S INSTRUCTIONS AND YOUR LOCAL REGULATIONS.
WARNING: MAKE SURE THAT THE GROUND SAFETY-LOCKS ARE IN POSITION ON THE LANDING GEAR. THIS WILL PREVENT UNWANTED MOVEMENT OF THE LANDING GEAR, AND THUS POSSIBLE INJURY TO PERSONS AND DAMAGE TO THE AIRCRAFT AND/OR EQUIPMENT.
WARNING: BE CAREFUL WHEN YOU USE CONSUMABLE MATERIALS. OBEY THE MATERIAL MANUFACTURER'S INSTRUCTIONS AND YOUR LOCAL REGULATIONS.
CAUTION: DO NOT CAUSE DAMAGE TO THE SURFACES. THE COMPONENTS ARE MADE OF CARBONFIBER REINFORCED PLASTIC.
CAUTION: USE ONLY THE SPECIFIED MATERIALS AND OBEY THE INSTRUCTIONS FROM THE MATERIAL MANUFACTURERS. OTHER MATERIALS CAN CAUSE DAMAGE TO THE SURFACE PROTECTION OF THE COMPONENTS AND THE RELATED AREA.
ZONE: 334
ZONE: 344
1. Reason for the Job
Self explanatory
2. Job Set-up Information
 A. Fixtures, Tools, Test and Support Equipment
REFERENCE
QTY
DESIGNATION
98D27903500000
2
PIN-SIDE STICK LOCKING
 B. Consumable Materials
REFERENCE
DESIGNATION
(Material No.06AAC1)
Polysulfide Sealant-General Purpose Interfay -
(Material No.08BBC1)
Non Aqueous Cleaner-- Naphta based and Alcohol -
(Material No.14DBB1)
Release Agent-- Liquid Wax -
(Material No.14DCB1)
Release Agent-- Solvant Base -
 C. Work Zones and Access Panels
ZONE/ACCESS
ZONE DESCRIPTION
334
THS TRAILING EDGE
344
THS TRAILING EDGE
 D. Referenced Information
REFERENCE
DESIGNATION
TASK 20-28-00-720-005-A
Check of the Electrical Bonding of the Different Components (but not the Fluid Systems and Components Installed on Composite materials)
TASK 20-28-00-869-002-A
Table of the Maximum Permitted Resistance-Values
TASK 29-10-00-864-001-A
Depressurize the Green Hydraulic System
TASK 29-10-00-864-002-A
Depressurize the Yellow Hydraulic System
TASK 29-10-00-864-003-A
Depressurize the Blue Hydraulic System
F THS Trailing Edge
3. Job Set-up
Subtask 55-13-11-860-052-A
A. Aircraft Maintenance Configuration
   (1) Make sure that the hydraulic systems are depressurized (Ref. AMM TASK 29-10-00-864-001), (Ref. AMM TASK 29-10-00-864-002), (Ref. AMM TASK 29-10-00-864-003).
   (2) Make sure that the 98D27903500000 PIN-SIDE STICK LOCKING is in the CAPT and F/O side stick controllers.
   (3) Make sure that the warning notices are in the flight compartment to tell persons not to operate the flight controlls.
   (4) Make sure that the warning notices are in position to tell persons not to operate the hydraulic systems.
   (5) Make sure that the access platforms are in position at zone 334 and/or zone 344.
Subtask 55-13-11-865-055-A
B. Make sure that this(these) circuit breaker(s) is(are) open, safetied and tagged:
PANELDESIGNATIONFINLOCATION
** ON A/C NOT FOR ALL
49VUFLIGHT CONTROLS/ELAC1/NORM/SPLY15CE1B11
49VUFLIGHT CONTROLS/THS/ACTR/MOT219CE2B09
** ON A/C NOT FOR ALL
49VUFLIGHT CONTROLS/ELAC1/NORM/SPLY15CE1B06
49VUFLIGHT CONTROLS/THS/ACTR/MOT219CE2B04
** ON A/C ALL
105VUFLIGHT CONTROLS/ELAC2/STBY SPLY16CE2A02
105VUFLT CTL/ELAC1/STBY SPLY16CE1A01
121VUFLIGHT CONTROLS/THS ACTR/MOT319CE3Q17
121VUFLIGHT CONTROLS/THS ACTR/MOT119CE1Q16
121VUFLIGHT CONTROLS/ELAC2/NORM/SPLY15CE2R20
122VULIGHTING/LOGO/L2LYV03
122VULIGHTING/LOGO/R1LYV02
Subtask 55-13-11-914-050-A ** ON A/C NOT FOR ALL
C. Apply Sealants
   (1) Apply Polysulfide Sealant-General Purpose Interfay - (Material No.06AAC1) to the mating surfaces of the panels.
   (2) Apply separator agent Release Agent-- Liquid Wax - (Material No.14DBB1) along the mating surfaces of skin shells and the trailing edge ribs.
4. Procedure
Subtask 55-13-11-420-050-C
A. Installation of the Access Panels
   (1) Install the upper trailing-edge access-panels:
NOTE: The installation procedure of upper trailing-edge access-panel 334CT is given. The installation procedure of all the other upper trailing-edge access-panels is the same.
     (a) Put the panel (4) in position.
     (b) Apply Polysulfide Sealant-General Purpose Interfay - (Material No.06AAC1) on the screws (1), (2) and (3).
     (c) Install the screws (1), (2) and (3).
     (d) Tighten the screws (1), (2) and (3).
     (e) Install the washers (11) and the nuts (10).
     (f) On left access panel 334BT and/or right access panel 344BT, do the steps that follow:
  • Put the electrical bonding lead (25) in position on the bracket (24).
  • Install the bolt (26), the washer (23) and the nut (22).
  • Do a check of the electrical bonding lead (25) (Ref. AMM TASK 20-28-00-720-005).
  • Make sure that the bonding value is not more than the maximum permitted value (Ref. AMM TASK 20-28-00-869-002).
   (2) Install the lower trailing-edge access-panels:
NOTE: The installation procedure of lower trailing-edge access-panel 334EB is given. The installation procedure of all the other lower trailing-edge access-panels is the same.
CAUTION: IF THE AIRCRAFT HAS A CONCESSION(S) RELATED TO THE INSTALLATION OF ADDITIONAL BUSHINGS ON THE THS TRAILING-EDGE LOWER-SKIN-FLANGE, YOU CAN FIND BUSHINGS INSTALLED IN SOME SCREW POSITIONS:
  • MAKE SURE THAT THE BUSHINGS ARE IN POSITION AND DO NOT REMOVE THEM.
  • IF ONE OR MORE BUSHINGS ARE LOOSE OR MISSING, CONTACT AIRBUS.
IF YOU DO NOT OBEY THIS INSTRUCTION, DAMAGE TO THE AIRCRAFT CAN OCCUR.
     (a) Put the panel (5) in position.
     (b) Apply Polysulfide Sealant-General Purpose Interfay - (Material No.06AAC1) on the screws (1) and (2).
     (c) Install the screws (1) and (2).
     (d) Tighten the screws (1) and (2).
   (3) Install the lower trailing-edge hinged access-panels:
NOTE: The installation procedure of lower trailing-edge hinged access-panel 334FB is given. The installation procedure of all the other lower trailing-edge hinged access-panels is the same.
CAUTION: IF THE AIRCRAFT HAS A CONCESSION(S) RELATED TO THE INSTALLATION OF ADDITIONAL BUSHINGS ON THE THS TRAILING-EDGE LOWER-SKIN-FLANGE, YOU CAN FIND BUSHINGS INSTALLED IN SOME SCREW POSITIONS:
  • MAKE SURE THAT THE BUSHINGS ARE IN POSITION AND DO NOT REMOVE THEM.
  • IF ONE OR MORE BUSHINGS ARE LOOSE OR MISSING, CONTACT AIRBUS.
IF YOU DO NOT OBEY THIS INSTRUCTION, DAMAGE TO THE AIRCRAFT CAN OCCUR.
     (a) Put the access panel (6) in position.
     (b) Apply Polysulfide Sealant-General Purpose Interfay - (Material No.06AAC1) on the screws (7), (8) and (9).
     (c) Install the screws (7), (8) and (9).
     (d) Tighten the screws (7), (8) and (9).
     (e) Install the washers (11) and the nuts (10).
     (f) On left access-panel 334BT and/or right access-panel 344BT, do the steps that follow:
  • Put the electrical bonding lead (25) in position on the bracket (24).
  • Install the bolt (26), the washer (23) and the nut (22).
  • Do a check of the electrical bonding lead (25) (Ref. AMM TASK 20-28-00-720-005).
  • Make sure that the bonding value is not more than the maximum permitted value (Ref. AMM TASK 20-28-00-869-002).
     (g) Close the access panel (6).
     (h) Apply Polysulfide Sealant-General Purpose Interfay - (Material No.06AAC1) on the screws (2).
     (i) Install the screws (2).
     (j) Tighten the screws (2).
Subtask 55-13-11-110-051-A
B. Cleaning
   (1) Clean the gaps around the trailing edge panels with Non Aqueous Cleaner-- Naphta based and Alcohol - (Material No.08BBC1) .
Subtask 55-13-11-914-051-A ** ON A/C NOT FOR ALL
C. Apply Sealants
   (1) Apply the Release Agent-- Solvant Base - (Material No.14DCB1) on the spaces around the trailing edge panels.
   (2) Apply the Polysulfide Sealant-General Purpose Interfay - (Material No.06AAC1) to the gaps along the mating surfaces of the trailing edge panels.
Subtask 55-13-11-914-051-C ** ON A/C NOT FOR ALL
C. Sealing
   (1) Apply Polysulfide Sealant-General Purpose Interfay - (Material No.06AAC1) around the anchor nuts of the ribs.
   (2) Apply Polysulfide Sealant-General Purpose Interfay - (Material No.06AAC1) on the spaces around the trailing edge panels.
   (3) Apply the Release Agent-- Solvant Base - (Material No.14DCB1) on the spaces around the trailing edge panels.
5. Close-up
Subtask 55-13-11-210-051-A
A. Visual Inspection
   (1) Make sure that the work area is clean and clear of tools and other items.
Subtask 55-13-11-865-052-A
B. Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s):
PANELDESIGNATIONFINLOCATION
** ON A/C NOT FOR ALL
49VUFLIGHT CONTROLS/ELAC1/NORM/SPLY15CE1B11
49VUFLIGHT CONTROLS/THS/ACTR/MOT219CE2B09
** ON A/C NOT FOR ALL
49VUFLIGHT CONTROLS/ELAC1/NORM/SPLY15CE1B06
49VUFLIGHT CONTROLS/THS/ACTR/MOT219CE2B04
** ON A/C ALL
105VUFLIGHT CONTROLS/ELAC2/STBY SPLY16CE2A02
105VUFLT CTL/ELAC1/STBY SPLY16CE1A01
121VUFLIGHT CONTROLS/THS ACTR/MOT319CE3Q17
121VUFLIGHT CONTROLS/THS ACTR/MOT119CE1Q16
121VUFLIGHT CONTROLS/ELAC2/NORM/SPLY15CE2R20
122VULIGHTING/LOGO/L2LYV03
122VULIGHTING/LOGO/R1LYV02
Subtask 55-13-11-081-050-A
C. Remove Locking Devices
   (1) Remove the 98D27903500000 PIN-SIDE STICK LOCKING from the CAPT and from the F/O side stick controllers.
Subtask 55-13-11-942-050-A
D. Remove Ground Equipment
   (1) Remove the access platform(s).
   (2) Remove the WARNING NOTICE(S).
[Rev.10 from 2021] 2026.04.01 02:04:53 UTC
"Aviabrain" 2025