Supplements - DG Flugzeugbau DG-1000 Flight Manual

Flight manual DG-1000S
7.6 Landing gear
Subsection amended
D) Very high, spring mounted, electrically operated retractable main landing
gear, wheel with hydraulic disc brake, see diagrams 20 and 21 M.M, tail wheel
With this version there are no handles and control rods for manual operation of
the landing gear like Version A.
In the normal operating mode the landing gear will be retracted and extended by
an electrical spindle drive.
A control unit which is installed in the rear instrument tower controls all
electrical functions and the control lights.
A landing gear warning device is integrated into the system.
Both cockpits are equipped with all controls and control lights
The landing gear will be locked in the extended position by over centre locking
of the drag struts.
The landing gear will be locked in the retracted position by 2 latches.
The system is equipped with a safety circuit against retraction of the landing
gear on the ground see section 4.5.12.5.
The system is equipped with an over current cut off which stops the extension or
retraction if high accelerations occur to protect the drive against damage. As
soon as the g-loads lower, the landing gear will continue to travel.
Emergency operation: If the electrical system is damaged or no battery power is
available, the landing gear may be extended manually. The handles are located
at the left hand fuselage wall, one in each cockpit at the positions of the handles
for the manually operated landing gears).
Pulling on one of the 2 emergency extension handles will open the valve of a
lockable gas strut. The gas strut will push the spindle drive forward on a linear
guide to extend and lock the landing gear.
Technical data:
Extension and retraction time (electrically operated): approx. 7seconds
Extension time emergency operation: approx. 2s
Power: 12V, max. 10 A
Issued: November 2008 TN 1000/14
9.11