7-4
Landing Gear
7-4-1
General
. Landing Gear System, for system operation.
The landing gear is a conventional tricycle configuration that is extended and retracted using
electromechanical actuators. Landing gear operation is completely automatic upon pilot gear
selection.
All landing gear are held in the fully retracted position by a mechanical brake internal to the
actuators. No mechanical uplocks are installed.
Landing gear position is shown on three icons in the GEAR window of the systems Multi
Function Display (MFD).
Nosewheel steering is accomplished by mechanical nosewheel steering and by differential
braking.
Aircraft braking is controlled by toe pedals that operate brake assemblies attached to the left
and right landing gear. Propeller reverse also contributes to aircraft braking. Refer to Section
7-11,
7-4-2
Description
The nose gear is a hydraulic fluid and nitrogen filled shock strut. The shock strut consists of a
piston and fork assembly that slides inside a cylinder. A torque link connects the piston/fork
assembly to the cylinder. The cylinder is mounted inside the nosewheel well. The nose gear is
locked in the extended position by putting the folding strut in an overcenter position. A spring is
attached to the nose gear to assist in free fall during emergency extension. The nose gear
doors are spring loaded to the open position and are mechanically closed during nose gear
retraction. The nose gear retracts rearward into the nosewheel well and is completely enclosed
by the gear doors when the landing gear is retracted. Proximity switches give the up or down
signal to the Modular Avionics Unit (MAU).
Both main landing gear are trailing link types. A hydraulic fluid and nitrogen filled shock strut
connects the trailing link to the main leg hinge point. The main gears are locked in the
extended position by putting the folding strut in an overcenter position. A spring is attached to
the main gears to assist in free fall during emergency extension. The main landing gear doors
consist of a single door that is attached to the main gear leg and the outside edge of the main
gear wheel well. Each main gear retracts inward into the main gear wheel well. With the
landing gear retracted the main landing gear wheel and tire assemblies are not enclosed and
protrude out of the main gear wheel well approximately one inch (25.4 mm). Proximity switches
give the up signal to the MAU. Microswitches give the down signal to the MAU.
All landing gear are held in the fully retracted position by a mechanical brake internal to the
actuators. No mechanical uplocks are required.
Nose wheel steering is accomplished using the rudder pedals which are mechanically
connected to the nosewheel. Additional nosewheel steering is done through differential
braking. Use of rudder pedal only will turn the nosewheel ± 12 degrees from center while
differential braking will turn the nosewheel ± 60 degrees from center. A shimmy damper is
installed on the nose landing gear strut to eliminate nosewheel oscillations.
The tires are a low pressure type that allow operations from soft and unimproved fields.
Section 7 - Airplane and Systems Description
Landing Gear
Pilot's Operating Handbook
Report No: 02406
Issue date: Mar 06, 2020
Page 7-4-1
12-C-A15-00-0704-00A-043A-A
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GENERAL
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