7.1.4. Wing
Shark has trapeze composite wing with speed airfoil and elliptic leading
edge in aileron part of wing is optimized for fast cross-country flights.
Wing structure is carbon-fibre/epoxy monocoque, with PVC foam panels.
Carbon-fibre main beam placed in 25% of airfoil and an auxiliary beam
carrying flap levers and aileron hinges has got 60% of the trailing edge
occupied by powerful single-slotted flaps. Integral fuel tanks (2x50/75 litres)
are between main and rear beams of both wings, with connected fuel
gauge, inputs and return line ending into root rib and drain valves. Fuel
tank ventilation ends in the last hinge of flaps. Wing is optionally equipped
by integral position lights at the leading edge of wing tips. The wings can
be dismounted for transport or storage by removing two main pins and one
rear wing pin, by dismounting flaps drive, ailerons control, fuel hoses and
electrical connector.
7.1.5. Ailerons
40% differential ailerons with carbon monocoque structure are hinged on
three carbon hinges attached on the top of monocoque wing. The drive is
on the root rib. Aerodynamic forces are balanced by automatic trim tabs.
7.1.6. Flaps
Fowler flaps with monocoque sandwich design are hinged on three
lever-hinges and driven by root-rib lever. System of electric flaps has
deflections 20° (take-off), 30° (short take off/ landing), and 40° (landing).
7.1.7. Horizontal stabilizer
Stabilizer has carbon monocoque sandwich design with continual rear
beam and auxiliary front beam. Hinges for elevator are attached on the top
surface of rear beam. Stabilizer is attached to fuselage by two hinges on
the rear fin frame and by one to the rear fuselage bracket.
7.1.8. Elevator
Split carbon nonococque elevator is hinged to stabilizer by 3 hinges. Left
part is equipped with electric trim-tab.
7.1.9. Rudder
Carbon monocoque rudder is hinged in two hinges and controlled by lever
on root rib, through wires in bowdens.
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