of 850 mm. The engine bed is made of thin-wall steel profiles (material L-CM 3) , using four
rubber springs with a diameter of 60 mm. The bed rotates on a 15 mm diameter pin and
includes swivel bearings placed in brackets on the wing root spar fittings. The power plant is
extended by a 12 V DC servo with a epicyclic gear and trapezoidal self-locking screw with a
nut. The set is balanced by a gas strut. Both the servo and the struts act on the bed via a
common pin, with their reaction with the fuselage baffle being distributed through the
common pin and a support. The position of the main turning point, the angle of the extention
and small distance between the engine CG and the aircraft CG results in an insignificant
displacement of the CG between the extended and retracted power plant. The power plant is
locked in both end positions by backstops. The engine area is covered by doors controlled by
an independent servo.
The pilot controls extention and retracting of the power unit by two push buttons on the
instrument panel, one for extension, the other one for retracting. The movement is controlled
by an electronic unit controlled by a microprocessor, which takes care of an automatic
opening of the engine doors, end position voltage-out switches, signals informing the pilot
and connecting of the starter only in fully extended position. Also retraction of the engine
while the engine is running is not possible. The propeller is stopped in its vertical position for
retraction by an automatic backstop.
The fuel tank is from welded aluminium sheet placed in a sealed composite compartment in
front of the baffle Nr.5. Venting and drainage is through landing gear pit. Fuel is supplied to
the engine by a flexible hose through an interchangeable fuel filter, fuel cock and membrane
fuel pump into two floatless membrane carburettors. There is a fuel capacity sensor in the
tank. Refuelling is done by means of a funnel through a 25 mm hose with a filler cap on the
right side of the fuselage. Drainage is possible through the landing gear pit.. A manually
operated fuel priming pump is located on the instrument panel.
2.7 MINIMUM EQUIPMENT
The aircraft is required to have the following minimum equipment
2
Alfa
MFD multifunction instruments
2 symmetrical safety belts
1 magnetic compass
1 review mirror
2.8 DIMENSIONS
2.8.1 Wing:
Span
17.00
m
(55.8
ft)
Area
12.084
m
2
(130.2 ft
2
)
Aspect
ratio
23.92
Root chord
1.00 m (3.3 ft)
Tip chord
0.36 m (1.1 ft)
Angle of Attack
+4
0
TST-14 M – Aircraft Manual
rev.0 issued 2006-11-29 – page 8 of 40
