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Revision:
Date of Issue: 18. November 2011
Date of Rev.: . .
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The front section of the fuselage – including the cockpit – is constructed from
carbon fiber composites. For additional stiffness and a decrease in mass, it is
reinforced with longitudinal stringers and circular frames. The midsection is
made of a steel tube framework with fairings made of carbon fiber composites.
The landing gear bays for nose and main landing gear are completely covered
by landing gear doors. The rear section with integrated vertical fin is also made
of carbon fiber composites. The force transmission between the separate
fuselage sections is realized with pin joints.
For reasons of fire containment, the engine is completely encased in fire
resistant walls. Certain elements can easily be removed for maintenance.
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The complete wing system has a span of 59 ft / 18 m and is made of 5 separate
sections. These are one inner wing, left and right outer wings and two winglets.
An integral tank for fuel is located in the forward area of the right inner wing (an
optional second tank can be installed in the left inner wing). The airbrakes are
located in the inner section of the outer wing.
The wing spars of all wing sections are made completely of carbon fiber
composites. The wing shells are made of CFC sandwich elements.
The connection between the inner wing and the fuselage is realized by four pins
which attach the wings to the steel tube framework.
The outer wings are connected to the inner wing by one socket pin at each
wing joint and two shear force fittings at each wing root. Additional details can
be taken from section 4 ”Normal Operating Procedures“.
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The T shaped tail is also made of spars and sandwich shells made of carbon
fiber composites. This set up is similar to the wing system. The horizontal
stabilizer can easily be removed from the vertical stabilizer. It is connected by a
removable three point mounting. To protect the tail against unwanted tail strikes
(when rotating or in ground operations), it is equipped with a tail skid.
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