7 18
Revision:
Date of Issue: 18. November 2011
Date of Rev.: . .
extended end position, the supporting drag strut is locked by a deadlock
blocking and additional springs independent from hydraulic pressure.
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All three landing gear legs are equipped with separate gear doors, covering
each of the landing gear legs and landing gear bays completely and
aerodynamically. The gear doors are open in the extended landing gear
configuration and are closed simultaneously with retraction of the landing gear.
The doors of the main landing gear are arranged along the flow direction and
mounted to the center fuselage side fairings above the landing gears. The gear
doors are actuated by mechanical linkage to the particular main landing gear
leg.
The nose landing gear has a gear door also arranged along the flow direction,
which is mounted sideways the nose landing gear. The actuation of the door is
linked kinematical to the nose landing gear leg by hinge kinematic.
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In the rear section of the center fuselage steel frame, the hydraulic drive unit is
installed. The unit consists of the electrically powered hydraulic pump including
controller for the pressurization of the complete hydraulic system and a pressure
reservoir for emergency extension of the main and nose landing gear. The
pressure reservoir is filled to 90 bar / 1305 psi ±8%
and is equipped with a
pressure gauge (near hydr. drive unit) to check storage pressure.
After switching off the hydraulic pump the system pressure is maintained by
check valves. With master switch (Batt) ON the hydraulic drive unit
automatically pumps up the system pressure to 90 bar / 1305 psi ±8%
(pressure
automatic) if necessary.
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The landing gear is operated by one combined dip switch (lever) for nose and
main landing gear. The lever is located in the area of the control elements of the
instrument panel on the left side of the propeller pitch control unit.
The lever provides the following settings:
Position UP:
RETRACT landing gear
Position DOWN:
EXTEND landing gear
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