STEMME S6-RT, Руководство по эксплуатации самолета

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7 17 Revision:
Date of Issue: 18. November 2011 Date of Rev.: . .
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The landing gear is a retractable tricycle configuration with nose wheel steering.
In the retracted configuration, all three landing gear legs are completely covered
by landing gear doors. The landing gear mechanics for retraction and extension
is driven by hydraulic actuation system.
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The nose gear is made of a steel strut which is stiff to torque. It is attached to
the forward fuselage section at an attachment plate by screws. The shock strut
is dampened by the use of elastomers and has a maximum spring travel of
approx. 4 in / 100 mm.
The nose wheel is steered by rotating the nose wheel fork, which is attached to
the shock strut. This rotation is performed with several levers. When the nose
gear is extended and loaded on ground, it connects automatically to the rudder
controls. In the un loaded and retracted position, it is automatically disconnected
from the rudder controls and locks in the direction of the longitudinal axis.
Extending and Retraction of the nose gear is actuated by a hydraulic actuator
connected to the nose gear drag strut. In the fully extended position the drag
strut locks by its overcenter locking and additional spring independent from
hydraulic pressure.
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The struts of the main landing gear are welded tubes, which are stiff to torque.
They are connected to the central steel tube framework of the midsection of the
fuselage via retraction kinematic.
The elastically mounted main wheels are located at the end of rockers, which in
turn are supported by elastomer dampened springs. The maximum spring travel
of the main gear is approx. 6 in / 150 mm.
The main wheel brakes are hydraulically actuated and designed as dual piston
disk brakes. The brakes are activated by operating the brake lever at the control
stick. The main brake cylinder is located at the brake lever. The expansion
reservoir is located at the left hand brake lever. To prevent the brakes from
locking, the brake circuit is equipped with an anti lock regulator which is
mounted in the midsection of the fuselage.
To lock the wheels for parking (hydraulic parking brake) push in the locking pin
at the side of the left hand brake lever.
The extension and retraction of the main landing gear is realized for both
landing gear legs by hydraulic actuators connected to each drag strut. In the