- 2T Tornado 280 engine with 32 HP
- electrically operated flaps
- brakes on main wheels
- steerable front wheel
- cockpit ventilation
- fuel tank 18 l
- speedometer, altimeter, variometer
- engine parameter monitor
- flap position indicator
- fuel gauge
FUSELAGE - shell structure, made of two assemblies; tail boom integral with the vertical stabilizer and the main cockpit part of the fuselage permanently connected to each other.
COCKPIT - one-piece cockpit canopy that opens to the side, equipped with handles and locks, in the open position it is supported on a string.
Ergonomic interior enabling easy use also for larger Pilots. The pilot's seat is adjusted by using the appropriate thickness of the seat and backrest.
WING - bipartite, equipped with slotted flaperons and optionally with aerodynamic brakes. Proven and effective, contamination-resistant NN-1817 wing profile commonly used in glider structures Of the Warsaw University of Technology (Politechnika Warszawska), such as PW5, PW6, AOS71.
TAIL-PLANE - in the classic arrangement. UNDERCARRIAGE - fixed, tricycle with a front wheel. The resilient main landing gear leg is made of composite. The front wheel is controlled thanks to a system of levers and pushrods on the pedals, allowing a 15 degree turn to each side.
Airframe control systems:
AILERONS - applied along the entire span except for the elliptical tips of the wing. The joystick movements are transmitted to the ailerons through a rigid tappet - lever system.
FLAPS - controlled by buttons on the joystick.The drive is realized by a rigid system of tappets, torsion tubes and levers translating the energy of the electric actuator's movement into the flap deflection. The range of deflections is from -6º to + 15º, with the -6º value being the neutral position in in the trailing edge plane.
ELEVATOR - joystick movements are transferred to the elevator by a rigid tappet-lever system.
RUDDER - the movements of the pedals are transmitted to the rudder by a cable-lever system, moreover, there is a coupling with the wheel of the front landing gear.
|bearing surface||10,5 m2|
|empty weight||120 kg|
|maximum weight (with GRS)||250 kg|
|take-off weight||250 kg|
|cruising speed||128 km/h|
|maximum speed||142 km/h|
|stall speed||55 km/h|
|climb speed||3,9 m/s|
|take-off run||100 m|
|landing run||50 m|
ROTAX 912 UL
|engine power||80 KM|
|fuel tank capacity||86 l|
|fuel consumption||10 l/h|
|bearing surface||10,1 m2|
|empty weight (with GRS)||305 kg|
|maximum weight (with GRS)||472,5 kg|
|LSA take-off weight (with GRS)||472,5 kg (LSA 560 kg)|
|cruising speed||189 km/h|
|maximum speed horizontal flight||210 km/h|
|Vne speed||240 km/h|
|stall speed||65 km/h|
|climb speed||6 m/s|
|take-off run||80 m|
|landing run||100 m|