-with a new cotter pin (18).
FOR 2805GM
-with a new cotter pin (18). Subtask 32-12-16-865-053
C. Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s): 1GA, 2GA, 52GA, 1701GK, 1702GK.
Subtask 32-12-16-941-053
D. Preparation for Test
(1)
Remove the rigging pin from the bypass valve 2517GM (2518GM).
(2)
Support the actuating cylinder 2523GM (2522GM) and move the MLG door control- handle to the open position.
(3)
Pull the actuating ram of the actuating cylinder 2523GM (2522GM) to the extended position.
(4)
Connect the actuating cylinder 2523GM (2522GM) to the MLG door (Ref. TASK 32-31-35-400-001).
(5)
Connect the PTU isolation coupling (Ref. TASK 29-23-00-860-002).
(6)
If the flight configuration precautions were obeyed, put the aircraft back to the serviceable condition (Ref. TASK 32-00-00-860-002).
(7)
Remove the warning notice(s).
(8)
Remove the access platform(s).
(9)
Close the applicable MLG door (Ref. TASK 32-12-00-410-001).
1EFF : ALL 1 32-12-16Page 413 1 1 May 01/00R 1 1 1CES 1
Subtask 32-12-16-710-050
E. Operational Test
(1)
Do the operational test of the main gear doors (Ref. TASK 32-12-00-710-002).
(2)
Open the applicable MLG door (Ref. TASK 32-12-00-010-001).
5. Close-up
________
Subtask 32-12-16-410-050
A. Close Access
(1)
Apply corrosion protection to the attachment points of the control cable and the adjacent areas (Ref. TASK 51-75-13-916-002).
(2)
Make sure that the work area is clean and clear of tool(s) and other items.
(3)
Close the applicable MLG door (Ref. TASK 32-12-00-410-001).
(4)
Remove the ground support and maintenance equipment, the special and standard tools and all other items.
(5) Close the access panel: FOR 2804GM R - close 195BB,
FOR 2805GM R - close 196BB.
1EFF : ALL 1 32-12-16Page 414 1 1 May 01/00 1 1 1CES 1 NOSE GEAR AND DOORS - DESCRIPTION AND OPERATION
_______________________________________________
1. General
_______
(Ref. Fig. 001)
The nose gear hangs on the structure between FR19 and FR20.
It includes :
A. Nose gear (Ref. 32-21-00)
-
a leg assembly having a shock absorber
-
a wheel steering assembly
-
a drag strut assembly and a lockstay which locks the gear in the down position
-
a gear actuating cylinder.
B. Nose gear doors (Ref. 32-22-00)
-
2 main door assemblies
-
2 aft door assemblies secured to the gear by rods
-1 leg door assembly attached to the rear of the shock strut, which closes off the nose gear well after retraction of the nose gear.
1EFF : ALL 1 32-20-00Page 1 1 1 Feb 01/98 1 1 1CES 1
Nose Gear and Doors
Figure 001
1EFF : ALL 1 32-20-00 Page 2
1 1 Feb 01/98
1 1
1CES 1
NOSE GEAR - DESCRIPTION AND OPERATION
_____________________________________
1. General
_______
(Ref. Fig. 001, 002)
**ON A/C 001-049, 051-061, 101-102, 201-202,
(Ref. Fig. 003)
R **ON A/C 062-099, 103-149, 151-199, 203-299, 301-399, 401-499,
(Ref. Fig. 003A)
**ON A/C ALL
A. Nose Gear The nose gear is of the direct acting type with an integral shock absorber. The gear retracts forward into the fuselage. The gear is therefore favorably assisted by the aerodynamic moments in the downlocking direction during gear extension.
The sliding tube assembly, which includes the wheel axle, is inclined 9 degrees forward. Because of this the wheels return freely to the center position. The shock strut is made of aluminum alloy and hangs on the structure from two trunnions. (Ref. Fig. 004) A rotating tube made of steel is installed inside the shock strut. A pinion gear installed on the tube is engaged with a rack which is connected to the steering actuating cylinder. The steering actuating cylinder transmits hydraulic power through the rack and pinion mechanism which steers the wheels. The sliding tube is made of steel and is connected to the rotating tube by torque links. The shock absorber includes 2 centering cams which engage with each other after take-off of the aircraft. This causes the wheels to return to the center position before gear retraction.
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