W DOC AIRBUS | AMM A320F

To Close the Spare-Seal Activating-Valve

TASK 32-11-13-860-001-A
To Close the Spare-Seal Activating-Valve

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: BE CAREFUL WHEN YOU USE CONSUMABLE MATERIALS. OBEY THE MATERIAL MANUFACTURER'S INSTRUCTIONS AND YOUR LOCAL REGULATIONS.
ZONE: 731
ZONE: 741
1. Reason for the Job
To isolate the primary (lower) gland seals and operate the secondary (upper) gland seals if there was a hydraulic leak.
NOTE: If you are not sure that there was initially a leak on the primary seal:
  • You can activate the primary seal again (Refer AMM task 32-11-13-860-002-A, To Open the Spare-Seal Activating-Valve) in seven days after the secondary seal is activated.
NOTE: If a leak is found on the primary seal:
  • AIRBUS recommends to replace ALL the gland seals on the applicable MLG at the next maintenance schedule (1200 FH/670 FC/200 days).
2. Job Set-up Information
 A. Fixtures, Tools, Test and Support Equipment
REFERENCE
QTY
DESIGNATION
No specific
AR
SAFETY BARRIER(S)
 B. Consumable Materials
REFERENCE
DESIGNATION
(Material No.08BAA9)
Non Aqueous Cleaner-General - -
(Material No.14QFB1)
Wire-Locking Dia: 0.8 mm CRES Nickel Alloy -
(Material No.14SBA1)
Textile-Lint free Cotton -
 C. Work Zones and Access Panels
ZONE/ACCESS
ZONE DESCRIPTION
731
L.H MAIN GEAR
741
R.H MAIN GEAR
 D. Referenced Information
REFERENCE
DESIGNATION
TASK 24-41-00-862-002-A
De-energize the Aircraft Electrical Circuits Supplied from the External Power
TASK 24-41-00-862-002-A-01
De-energize the Aircraft Electrical Circuits Supplied from the APU
TASK 24-41-00-862-002-A-02
De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2)
TASK 32-00-00-860-001-A
Flight Configuration Precautions with Electrical Power
TASK 32-00-00-860-001-A-01
Flight Configuration Precautions without Electrical Power
TASK 12-14-32-200-001-A
Inspection of the MLG Shock Absorbers before Flight (for corrective action)
TASK 32-11-13-000-001-A
Removal of the MLG Shock Absorber (for corrective action)
TASK 32-11-13-000-003-A
Removal of the MLG Shock-Absorber Gland-Seals (for corrective action)
TASK 32-11-13-400-001-A
Installation of the MLG Shock Absorber (for corrective action)
TASK 32-11-13-400-003-A
Installation of the MLG Shock-Absorber Gland-Seals (for corrective action)
F Spare-Seal Activating-Valve - Flow Chart
F Possible Points of Leakage from the Gland Seals ** ON A/C NOT FOR ALL
F Possible Points of Leakage from the Gland Seals ** ON A/C NOT FOR ALL
F Possible Points of Leakage from the Gland Seals ** ON A/C NOT FOR ALL
F Spare-Seal Activating-Valve ** ON A/C NOT FOR ALL
F Spare-Seal Activating-Valve ** ON A/C NOT FOR ALL
3. Job Set-up
Subtask 32-11-13-941-052-A
A. Safety Precautions
   (1) As necessary, use the applicable SAFETY BARRIERS, specified by the operator's instructions and your local regulations.
Subtask 32-11-13-869-061-A
B. Flight Configuration Precautions
   (1) If the electrical power is not necessary for other maintenance tasks, de-energize the aircraft electrical circuits (Ref. AMM TASK 24-41-00-862-002). Then, it is not necessary to operate the LGCIU circuit breakers.
   (2) If the electrical power is necessary, do the precautions for flight configuration (Ref. AMM TASK 32-00-00-860-001) before you open the LGCIU circuit breakers.
Subtask 32-11-13-210-052-A
C. Examine the Shock Absorber Gland Housing
   (1) Examine the shock absorber gland housing for the points of hydraulic oil leakage:
     (a) If the leak is from:
  • the gland housing and the sliding tube interface
    or
  • the gland housing and the main fitting interface:
       1 Examine the sliding tube for damage:
         a If you found damage, replace the shock absorber (Ref. AMM TASK 32-11-13-000-001) and (Ref. AMM TASK 32-11-13-400-001).
     (b) If you did not find damage, do one of these procedures:
4. Procedure
Subtask 32-11-13-860-052-A ** ON A/C NOT FOR ALL
A. Close the Spare-Seal Activating-Valve
WARNING: USE PROTECTIVE GOGGLES AND GLOVES WHEN YOU REMOVE OR INSTALL LOCKWIRE. EACH TIME YOU CUT LOCKWIRE, REMOVE AND DISCARD IT IMMEDIATELY. LOOSE LOCKWIRE CAN CUT YOU OR MAKE YOU BLIND, AND/OR CAN CAUSE DAMAGE.
   (1) Remove and discard the lockwire from the cap screw (1).
   (2) Remove and discard the cap screw (1).
   (3) Turn the spindle (2) clockwise to close the spare-seal activating-valve. Tighten the spindle (2) with your hand.
   (4) Safety the spindle (2) with 14QFB1Wire-Locking Dia: 0.8 mm CRES Nickel Alloy - to the lockwire hole on the pin (3).
   (5) Clean the area with a Textile-Lint free Cotton - (Material No.14SBA1) made moist with Non Aqueous Cleaner-General - - (Material No.08BAA9) .
   (6) Make sure that there are no hydraulic leaks.
   (7) Make a note in the aircraft technical log that the MLG spare-seal activating-valve has been closed.
NOTE: AIRBUS recommends that ALL gland seals on the applicable MLG are replaced at a subsequent scheduled maintenance procedure. To decrease the risk of unscheduled maintenance:
  • Replace the primary and secondary seals after you find leakage and have operated the secondary seal.
    Replace the primary and secondary seals at the recommended interval that comes first:
  • 1200FH, or
  • 670FC, or
  • 200 days.

Subtask 32-11-13-860-052-E ** ON A/C NOT FOR ALL
A. Close the Spare-Seal Activating-Valve
WARNING: USE PROTECTIVE GOGGLES AND GLOVES WHEN YOU REMOVE OR INSTALL LOCKWIRE. EACH TIME YOU CUT LOCKWIRE, REMOVE AND DISCARD IT IMMEDIATELY. LOOSE LOCKWIRE CAN CUT YOU OR MAKE YOU BLIND, AND/OR CAN CAUSE DAMAGE.
   (1) Remove and discard the lockwire from the stem valve (1).
   (2) Turn the stem valve (1) clockwise to close the spare-seal activating-valve.
   (3) Tighten the stem valve (1) with your hand.
NOTE: The visual indicator on the spare-seal activating-valve changes from green to red.
   (4) Safety the stem valve (1) with 14QFB1Wire-Locking Dia: 0.8 mm CRES Nickel Alloy - to the spare-seal activating-valve housing.
   (5) Clean the area with a Textile-Lint free Cotton - (Material No.14SBA1) made moist with Non Aqueous Cleaner-General - - (Material No.08BAA9) .
   (6) Make sure that there are no hydraulic leaks.
   (7) Make a note in the aircraft technical log that the MLG spare-seal activating-valve is closed.
NOTE: AIRBUS recommends that ALL gland seals on the applicable MLG are replaced at a subsequent scheduled maintenance procedure. To decrease the risk of unscheduled maintenance:
  • Replace the primary and secondary seals after you find leakage and have operated the secondary seal.
    Replace the primary and secondary seals at the recommended interval that comes first:
  • 1200FH or
  • 670FC or
  • 200 days.

Subtask 32-11-13-611-051-B
B. Check the Contents of the MLG Shock Absorber
   (1) Do a check of the MLG shock absorbers (Ref. AMM TASK 12-14-32-200-001).
5. Close-up
Subtask 32-11-13-942-052-A
A. Removal of Equipment
   (1) Make sure that the work area is clean and clear of tools and other items.
   (2) Remove the SAFETY BARRIER(S).
   (3) Remove the WARNING NOTICE(S).
[Rev.10 from 2021] 2026.04.01 00:40:08 UTC
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