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:
中国航空网 www.aero.cn
航空翻译 www.aviation.cn
本文链接地址：A320飞机维护手册 AMM LANDING GEAR 起落架2(12)
