WT-9 Dynamic Club S FLIGHT MANUAL Section 7 Page 7-
There are two places in the cockpit, side by side type. The interior width is 1.15 m. A
lifting cockpit canopy hinges forward. The canopy opening system is assisted by an
air strut. The wing central panel with span 2.45 m is fixed at the fuselage. There is an
integral tank in the forward box of the wing central panel.
Wing
The tapered wing is a monospar construction with a rear auxiliary spar for the aileron
and flap attachments. The main spar caps are made from carbon rovings. The slotted
flaps are rectangular sandwich construction. The flap is attached to the wing with
four hinges. The aileron is attached to the upper surface of the wing with three
hinges. The spars of right and left wings are joined to the wing central panel spar
with the help of two pins. The third connecting point is the pin in the rear auxiliary
spar. An aileron control system consists of duraluminium rods. The control handle of
flaps is attached to the pedestal in the cockpit. The movement by help of the rods and
the bellcranks is transmitted to the flap shaft in the wing, next the movement from
the shaft is transmitted to the flaps. Optional wing fuel tanks are integral part of wing
structure. They are connected with central section tanks with simple house
connection and tighted with clamp.
Horizontal tail unit
The horizontal tail unit consists of a stabilizer and elevator. The stabilizer consists of
sandwich shells from advanced composite material. The stabilizer is fixed at the fin.
The width of the horizontal tail unit is 2.4 m, (the same width as the wing central
panel) and allows the transport of the fuselage with regular truck.
The elevator consists of two parts, which are joined together by help of the elevator
control.
Vertical tail unit
The vertical tail unit consists of the fin and rudder and has trapezoidal shape. The
rudder consists of a sandwich shell from advanced composite material with the
control-surface weight balance. The rudder is attached by three hinges at the fin.
7.3 Flight controls
The airplane has dual controls with two control sticks. The ailerons are controlled by
control sticks, connecting rods and arms.
The elevator is controlled by control sticks, connecting rods. The rudder is controlled
by cables attached at the rudder pedals and guided alongside the fuselage sides to the
rudder. The rudder pedals position is adjustable (see Maintenance Manual,
Directional control system, page 1-22)
The wing flaps are controlled by a flap control lever located on the pedestal between
the seats. The lever has four positions: retracted, take-off with flap deflection 15°,
landing position with flap deflection 24 ° and landing position with flap deflection
35°. The flap position is locked by a plate at the flap control lever in the appropriate
position. Movement with help of rods and bellcranks is transmitted onto the coaxial
shaft and from the shaft is transmitted onto the flaps with help of the rod.
Date: 15.1.2007 / Change : 3
To Next Page
Loading...
