DG Flugzeugbau DG-1000T Maintenance Manual page 142

Enclosure 4 for Maintenance Manual DG-1000T
Electrically operated main landing gear
Part designations see MM diagrams 20 und 21
In the following text the changes to those sections of the maintenance manual
which are effected by the installation of the electrically operated main landing
gear will be given.
Section 1.6 Undercarriage
new subsection
1.6.5 Electrically operated main landing gear
This subsection replaces MM subsection 1.6.1.
1.6.5.1 Landing gear control circuit
See diagrams 20 (in LG box) and 21
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.
The landing gear will be locked in the extended position by over centre locking
of the drag struts and held in this position by the spindle drive.
The landing gear will be locked in the retracted position by 2 bolts at the drag
struts which engage into 2 latches at shaft 10FW102.
Unlocking is actuated by a cam mounted to the spindle drive, which rotates the
shaft 10FW109 via a bell crank and a push rod to release the bolts (see diagram
20).
Emergency operation: 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 red 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.
Issued: February 2011 TN1000/18 page of 8
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