Material No. 19-010  USA AMS 5687
 LOCKWIRE STAINLESS STEEL ANNEALED 0.8MM DIA
 (Ref. 20-31-00)

 1EFF : ALL 1 32-11-13Page 201 1 1 Nov 01/04 1 1 1CES 1

 C. Referenced Information
 -------------------------------------------------------------------------------
REFERENCE DESIGNATION
 -------------------------------------------------------------------------------
24-41-00-862-002 De-energize the Aircraft Electrical Circuits Supplied from the External Power 32-00-00-860-001 Flight Configuration Precautions with Electrical Power 12-12-32-611-004 Check Fluid Level of Main Landing Gear Shock Absorber (for corrective action) 32-11-13-000-001 Removal of the MLG Shock Absorber (for corrective action) 32-11-13-000-003 Removal of the MLG Shock-Absorber Gland-Seals (for
 corrective action)
 32-11-13-400-001 Installation of the MLG Shock Absorber (for
 corrective action)

 32-11-13-400-003 Installation of the MLG Shock-Absorber Gland-Seals (for corrective action)

R **ON A/C 001-049, 053-099, 101-149, 151-199, 201-299, 401-499,
 32-11-13-991-003-A Fig. 201
 **ON A/C 051-052,
 32-11-13-991-003 Fig. 201A
 **ON A/C 301-399,
 32-11-13-991-003-B Fig. 201B
 **ON A/C ALL
 32-11-13-991-004 Fig. 202
 3. Job Set-up
__________
R **ON A/C 001-049, 053-099, 101-149, 151-199, 201-299, 401-499,
 (Ref. Fig. 201/TASK 32-11-13-991-003-A)
 1EFF : ALL 1 32-11-13Page 202 1 1 Aug 01/05 1 1 1CES 1

 Possible Points of Leakage from the Gland Seals Figure 201/TASK 32-11-13-991-003-A
R 1EFF : 001-049, 053-099, 101-149, 151-199, 1 32-11-13Page 203 1201-299, 401-499, 1Aug 01/05 1 1 1CES 1

R  **ON A/C 051-052, 
R  (Ref. Fig. 201A/TASK 32-11-13-991-003) 
R  **ON A/C 301-399, 
R  (Ref. Fig. 201B/TASK 32-11-13-991-003-B)
 **ON A/C ALL
 Subtask 32-11-13-941-052
 A. Safety Precautions
 (1) Put the safety barriers in position.
 Subtask 32-11-13-869-061
 B. Flight Configuration Precautions
 (1) If the electrical power is not necessary for other maintenance tasks, de-energize the aircraft electrical circuits (Ref. 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. TASK 32-00-00-860-001) before you open the LGCIU circuit breakers.
 Subtask 32-11-13-210-052
 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 from 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. TASK 32-11-13-000-001) and (Ref. TASK 32-11-13-400-001). 

R 1EFF : ALL 1 32-11-13Page 204 1 1 May 01/05 1 1 1CES 1R Possible Points of Leakage from the Gland Seals R Figure 201A/TASK 32-11-13-991-003

R 1EFF : 051-052, 1 32-11-13Page 205 1 1 May 01/05 1 1 1CES 1

 Possible Points of Leakage from the Gland Seals R Figure 201B/TASK 32-11-13-991-003-B
R 1EFF : 301-399, 1 32-11-13Page 206 1 1 May 01/05 1 1 1CES 1

 (b) If you did not find damage, do one of these procedures:
 -
replace the shock absorber gland seals (Ref. TASK 32-11-13-000-003) and (Ref. TASK 32-11-13-400-003) or

 -
replace the shock absorber (Ref. TASK 32-11-13-000-001) and (Ref. TASK 32-11-13-400-001) or

 -close the spare-seal activating-valve.
 4. Procedure
_________
 (Ref. Fig. 202/TASK 32-11-13-991-004) Subtask 32-11-13-860-052
 A. Close the Spare-Seal Activating-Valve
 (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, hand tighten only.

 (4)
 Safety the spindle (2) with MISCELLANEOUS (Material No. 19-010).

 (5)
 Clean the area with a MISCELLANEOUS (Material No. 19-003) made moist with CLEANING AGENTS (Material No. 11-026).

 (6)
 Make sure that there are no hydraulic leaks.

 (7)
 Make a note in the aircraft technical log that:
　
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