A short brief:
Puma is a two-seater, high-wing ultralight with T- tail and tricycle fixed landing gear.
It is designed for leisure flights accordingly to VFR regulations when VMC conditions are met. It was designed based on JAR-VLA and UL-2 (Czech) regulations.
It is all-metal plane, built from elements and sheets of duralumin. The structure is semimonocoque, has formers and stringers. Each part is linked by pop rivets (elements that are highly stressed by solid rivets, screws and bolts). Parts that are important due to material stresses are made of steel and welded. Wing-tips, engine cover, dashboard and a lot of elements are made of composite.
Rectangular non-cantilever wing (without struts) has one main and one secondary girder, on which by the use of hinges are mounted ailerons and flaps. In the middle of the leading edge there are fuel tanks. At wing tip there is a laminar ending. The wing consists of two parts - left and right - which are linked with the fuselage by three hinges. Flaps have 3 positions: neutral (0 deg), take-off (+20deg) and landing (+40deg).
Cross-section of the middle part of the fuselage is rectangular and rounded at the bottom, in the upper part cross-section is elliptical. The horizontal stabilizer is an integral part of it. In the middle part of the fuselage there is a place for two-man crew. Entering the cabin is possible thanks to lockable doors placed on both side of the fuselage. Engine is separated from the crew by the use of steel firewall, on which are placed engine suspension frame mountings.
Tail-plane is designed as a T-tail, the vertical tail is consisting of one part. The vertical stabilizer is rectangular and is mounted to the fuselage by four screws. In the middle of the elevator there is an electric trimmer. Trapezoidal rudder is placed on the horizontal stabilizer by two bolts.
The control system has two yokes. Steering is done using aileron control rods and ropes, rudder ropes and elevator rods. Flaps and trimmer positions are set by electric actuator with a position indicator.
Undercarriage's legs are made of composite springs. Front leg is made of welded steel elements and amortized by rubber silent blocks. The front wheel is controllable. Brakes are mounted on the main gear wheels. Tire size is the same for main and front landing gear and it is 15x6.00-4.
Aircraft's structure is adapted to ROTAX 912, ROTAX 912S or ROTAX 914TURBO engine. Motor is mounted (by silent blocks) to the engine's suspension frame which is made of steel tubes. Engine has torsion of 2.5 deg. The propeller can be fixed or adjustable during flight.
Integral fuel tanks (capacity 2x50 l) are placed in the middle of the leading edge. They are riveted and sticked from aluminum sheets. Fuel tank equipment consists of: three-way fuel valve, fuel filters and electric pump.
Airplane is equipped with two, located side by side, composite, padded seats. Seats are regulated (move forward -backward in rails). In the cockpit there are riveted clinches for mounting four-point safety belts. Trunk is located behind seats. Maximal luggage weight is 20kg. The side doors open along the vertical axis.
Electrical system is 12V with negative ground and maintenance-free battery. As a source of energy engine's alternator is used. Installation is equipped with individual circuits secured by fuses on the dashboard.
Basic instruments are:
Airspeed indicator, altimeter, variometer, turn indicator, compass
Revolution counter, oil thermometer, cylinder heads thermometer, oil pressure gauge, fuel indicator