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6.  Main Gear Damper
A.  The main gear damper prevents excessive vibration buildup in landing gear, during high speed taxi, and under heavy braking. The damper is a hydraulic unit containing an actuator, a compensator, relief and check valves. (See figure 4.) The main body of the damper is attached to the forward end of the upper torsion link. The actuator piston rod passes the forward ends of both upper and lower links to provide an apex bolt. Rotary oscillation between the shock strut inner and outer cylinders is absorbed by the actuator piston displacing hydraulic fluid in the cylinder. The rate of displacement is controlled by the damping orifice in the actuator piston. The compensator is provided to maintain a pressure of 30 to 70 psi on the fluid contained in the actuator. A 3000 psi relief valve protects the actuator from very high pressures caused by thermal expansion of hydraulic fluid. A 70 psi relief valve protects the compensator from thermal expansion damage. Two check valves are provided to allow hydraulic fluid to enter the actuator and make up for slight leakage or to compensate for fluid contraction. A third check valve permits fluid to enter the unit from the hydraulic system A return and so keep the damper fully charged with fluid. Bleeder plugs are provided to enable trapped air to be cleared after disconnection of the hydraulic line, or when filling an empty unit.
7.  Main Gear Side Strut
A.  The main gear side strut gives lateral support to the shock strut. The side strut consists of an upper and a lower segment, hinged near the center. The upper end of the side strut is connected to a lug on the reaction link. The bottom end of the lower segment is connected to the universal side brace attachment. A lock strut is mounted between the reaction link and the side strut hinge. (See figure 2.) The side strut folds about the hinge when the gear retracts.
500 
Nov 15/67  BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  32-11-0 Page 7 

 

8.  Main Gear Reaction Link
A.  The main gear reaction link forms the upper member of a space frame, consisting of the shock strut, the side strut, and the reaction link (Fig. 1). Most of the side loads acting on landing gear are transferred through the reaction link to the upper end of the shock strut. The outboard end of the reaction link is attached through a universal joint to the trunnion link connection. The inboard end is attached to structure at the main gear uplock brackets. All the landing gear lock actuating mechanism is mounted on the reaction link. 
9.  Static Ground Assembly
A.  The static ground assembly is attached to the main gear at the lower torsion link attachment to discharge static electricity to ground upon contact. The ground strap support bracket is attached to the shock strut by the torsion link lower antirotation bolt. The ground wire is attached to the support bracket with fasteners to allow vertical adjustment so that the ground wire will make contact with the ground.

Main Landing Gear Damper Schematic  545 
32-11-0  Figure 4  Nov 01/75 
Page 8 
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 

MAIN LANDING GEAR - REMOVAL/INSTALLATION
1. General
A.  The main landing gear may be removed and installed without special equipment; by using man power to maneuver the gear into or out of position. Three men are required to handle the gear.
B.  The gear removal procedure described in this section does not require the use of special tools. If desired, a Main Landing Gear Dolly is available for gear handling.
2.  Equipment and Materials
A.  Ground lock assemblies - (Ref 32-00-01)
B.  Adapter Wrench, Main Gear Trunnion Nut - F80020-5. Use to remove and install trunnion link pin nut.
C.  Wrench, Main Gear Trunnion Link Socket - ST2580-202. Use to remove and install trunnion main landing gear forward trunnion bearing assembly in beam while installed on trunnion link.
E.  Torque Wrench Adapter - F80176-01. Use to torque aft trunnion bearing nut.
F.  Length of rope or cord for extending downlock springs during installation of main landing gear.
G.  Main Landing Gear Thread Protector and Pin Alignment Tool - F80141-1. Use on end of shock strut upper journal to facilitate entry into aft trunnion bearing.
H.  Lock Assembly, Oleo Main Gear - F80234
I.  Bullet Shaped Thread Protector - F80115-1 or F80115-10
J.  Bullet Shaped Thread Protector - F80115-2 or F80115-11
K.  Lead hammer
L.  Wheel chocks
M.  Container, suitable for Hydraulic Fluid, Fire Resistant BMS 3-11 in which to drain brake lines
N.  Grease - Aero Shell 07 (Ref 20-30-11)
O.  Corrosion Inhibitor - Mastinox 6856K (Ref 20-30-21
　
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