Aircraft Landing Gear Systems

(13-7) When servicing an air/oil shock strut with fluid, the strut should be

Collapsed and fluid added at the filler opening.

(13-3) The purpose of a locking/disconnect pin on a nose gear strut is to

Disconnect steering when the aircraft is being towed.

(13-9) When an empty shock strut is filled with fluid, care should be taken to extend and compress the strut completely to

Ensure proper packing ring seating and removal of air bubbles.

(13-2) When an air/oil type of landing gear shock strut is used, the initial shock of landing is cushioned by the

Fluid being forced through a metered opening.

(13-6) A sleeve, spacer, or bumper ring is incorporated in a landing gear hydraulic shock strut to

Limit the extension stroke.

(13-8) Extension of a shock strut is measured to determine the

Proper operating position of the strut.

(13-5) The metering pins in hydraulic shock struts serve to

Retard the flow of oil as the struts are compressed.

(13-11) The purpose of hydraulic restrictors when used in a small aircraft nose gear retraction system actuator is to

Slow the downward motion of the gear leg.

(13-10) If the extended longitudinal axis of the main landing gear wheel assemblies intersects aft of the aircraft, the wheels can be termed as having

Toe-out

(13-4) To prevent a very rapid extension of a pneumatic or hydraulic shock strut after initial compression resulting from landing impact

Various types of valves or orifices are used which restrict the reverse fluid flow.

(13-1)The purpose of the torque links attached to the cylinder and piston of a landing gear oleo strut is to

maintain correct wheel alignment.