The ultralight LEGEND 540 aircraft is an all-composite, high-wing, strut-braced two-seater
Maximum Take Off Weight: 472,5 Kg
This aircraft is suitable for sport and recreational flying as well as for tourism. The favourable behaviour of the LEGEND aircraft in the air means that the aircraft is suited for use in flight training. Thanks to its high performance the plane may also be used for towing gliders. The ultralight Legend aircraft provides an above-standard paired space for a crew and baggage. Spacious doors enable comfortable entry and baggage handling. Adjustable seats ensure an optimal position for pilots of all heights. Four-point harnesses, and a solid Kevlar cabin and rocket rescue system ensure the maximum safety of the crew during emergency situations.
The body of the ultralight aircraft is constructed using sandwich technology with a carbon composite material. There are design partitions patched into the integrally reinforced upholstery for the establishment of the power of undercarriage, rescue system, stabilizer, turn indicator, guy belts and wings. The cabin has two doors on each side, which are designed to open against the direction of flight. The doors are hung on embedded hinges and closed by a central lock.
The wing is constructed using a sandwich design with a carbon composite material. Two fuel tanks are positioned in the stagnation area of the ultralight aircraft. The wing is equipped with a slotted fowler flap. The wing design is a combination of a rectangular central plane with trapezoidal ends, using profile MS 313. Roll is ensured by ailerons with differentiated deviations of 13° downwards and 23° upwards. During deviation upwards, the nose is yawed out of the ultralight aircraft profile. This ensures the most favourable turnaround moment of the aircraft, meaning that the sport ultralight aircraft can pursue turns without the necessity of using directional drive. The brace of the wing is made of an aluminous profile.
The horizontal tail surface of trapezoidal shape is fixed into the body barriers using pegs and screws. The elevator is equipped by a balancing servo motor. The deviation of the elevator is 21° upwards and 10° downwards.
The vertical tail surface has an trapezoidal arrow shape. The propeller air flow has minimal influence on the rudder deviation. The maximum rudder deviation is cca 23°.
The ultralight aircraft surface control mechanism is doubled using funiculars leading to the rudder and ailerons, the elevator has a pulling drive. The ailerons and elevator are controlled by the control wheel, the rudder is controlled by rudder pedals. Rudder pedals control the front undercarriage wheel. The engine thrust, undercarriage brakes, parking brakes, and buoyancy flaps are controlled by a central control. The buoyancy flap is operated with the help of compressive bowdens.
The undercarriage is a tricycle design with front wheel steering. The main undercarriage wheels have a proportion of 15x6-6 and are braked by hydraulic circular brakes. The shock absorption of the main undercarriage is ensured by composite legs. The front undercarriage is equipped with a spring hydraulic inhibitor. All wheels of the ultralight aircraft have aerodynamic covers.
The fuel system has two fuel tanks. Two fulfillment of the wing and fuel tanks. A pair of wing tanks with a total volume of 100 l or 130 l is connected into a 4-way valve. Engine mechanical pump is backed by an electric pump.
This ultralight aircraft can be equipped with two types of engines and three types of propellers. It is possible to install two engines, ROTAX 912 UL and ROTAX 912 ULS. We offer two bladed electrically adjustable WOODCOMP SR-3000/2W propeller, three bladed fixed aeroelastic WOODCOMP KLASSIC propeller and two bladed electrically adjustable WOODCOMP VARIA VAR-2 propeller. Adjustable propellers are controlled by an electronic Constant Speed Unit.
The ultralight aircraft can be equipped with classic analogue instruments in combination with a navigation GPS or a glass cockpit, which includes flying, engine, and navigation instruments as well as transponder data.
|Wing Span:||9,06 m|
|Wing Area:||10,54 m2|
|Empty Weight:||289 kg (ROTAX 912)|
|Maximum Take Off Weight:||472,5 kg|
|Maximum crew weight:||183 kg (ROTAX 912)|
|Maximum luggage weight:||10 kg|
|Fuel Tank Capacity:||110 l|
|Performance:||Rotax 912 ULS - 100 HP|
|Speed with flaps:||62 kph|
|Minimum Landing Speed:||65 kph|
|Max. Speed, Flaps 40º:||120 kph|
|Max. Speed, Flaps 15º, 30º:||145 kph|
|Rough Air Speed:||170 kph|
|Cruise Speed (75 %)||210 kph|
|Max. horizontal flight Speed:||225 kph|
|Never exceed speed:||255 kph|
|Range:||1300 km (7 hours)|
|Climb rate (at ground level):||7 mps|