R Main Landing Gear Figure 001
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R Main Landing Gear Figure 001A
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MLG Leg Geometry
Figure 002 (SHEET 1)
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MLG Leg Geometry
Figure 002 (SHEET 2)
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MLG Leg and Dressings Figure 003
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R **ON A/C 004-049, 053-099, 101-149, 151-199, 201-299, 301-399, 401-499,
(Ref. Fig. 003A)
**ON A/C ALL
A. Main Landing Gear
Each MLG includes these components:
-a MLG leg which includes a shock absorber
-torque links
-
a side-stay assembly
-
a retraction actuator
-electrical and hydraulic dressings.
B. Main Landing Gear Leg
Each MLG leg has two primary structural components, which are the main fitting and the sliding tube. Each of these components is a one-piece assembly and contains the shock absorber.
An axle, which is a part of the sliding tube, can contain a wheel-speed tachometer, a brake-cooling fan and/or a tire-pressure sensor for each wheel.
C. Torque Links
The upper torque-link and the lower torque-link align the axle. They attach to the lugs at the front of the main fitting and the sliding tube. There is a torque-link damper at the interface of the upper and lower torque-links. The torque-link damper absorbs the vibrations that can occur during landing.
D. Side-Stay Assembly
A two-piece side-stay assembly connects the MLG leg main-fitting and the wing structure. It prevents the movement of the landing-gear leg sideways. The side-stay assembly is locked in the down position by a two-piece lock-stay assembly.
E. Retraction Actuator
A retraction actuating cylinder (Ref. 32-31-00) connects the wing structure and the landing-gear forward hinge-point. The retraction actuating cylinder retracts the MLG leg (sideways) into the fuselage.
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MLG Leg and Dressings
Figure 003A
R 1EFF : 004-049, 053-099, 101-149, 151-199, 1 32-11-00Page 8 1201-299, 301-399, 401-499, 1Aug 01/05 1 1 1CES 1 F. Inflation Valve
The main fitting and the sliding tube each have an inflation valve. The valves are used to fill the shock absorber with hydraulic fluid and nitrogen.
G. Dressings
Between the main fitting and the sliding tube there is a slave link. It holds the electrical cables and the hydraulic pipes, to make sure they do not catch on the wheels.
A spare-seal activating-valve is on the main fitting. This operates if there is a hydraulic leak through the gland seals. It is only used until the gland seals can be examined/replaced.
The hydraulic pipes and the electrical harness are in rigid and flexible conduits. The conduit routing gives:
-protection from runway debris, birdstrikes and flailing tire treads
-maximum separation of the two systems.
4.
Power Supply
____________
Not Applicable.
5.
Interface
_________
**ON A/C 001-049, 101-149, 151-199, 201-299,
(Ref. Fig. 004)
**ON A/C 051-099,
(Ref. Fig. 004A) R **ON A/C 301-399, 401-499,
(Ref. Fig. 004B)
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MLG Interface Figure 004
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