- The ultralight that outclasses general aviation aircraft

- Given equal power, it is faster, goes further, climbs more rapidly, lands and lake off in less space.

- Operational costs cut in half.

All load-bearing structures are light alloy and built to meet international airnavigation standards.Wing structure features a single spar torque box connected to fuselage via three pin attachments to each half wing. Fuselage structure is a steel tubing framework for cabin area high protection and semimonococque light alloy tail to support empennage. Ease of inspection; immediate access for servicing that is efficient and inexpensive at the same time. Particular attention is devoted to fuselage aerodynamics with the adoption of a composite fairing that elegantly and efficiently joins the cabin with the vertical tail. The wide cabin (1,10 m) features two side by side seats that can be adjusted via sliding rail stops, a large baggage compartment is located behind seats. Cabin access is through a canopy that slides towards rear of aircraft overlapping tail fairing consequently allowing unrestricted opening even with aircraft in flight. The wide windshield offers a complete view unhindered by structural elements, while large side windows allow for excellent visibility. The entirely moving tailplane permits superior control and a high degree of stick free stability, moving surfaces feature mass balancing. Landing gear components have been thoroughly tested and feature a clear record of safety and effinciency. The main landing gear consists of special steel springs with 5.00-5 size tires and hydraulically actuated disc brakes, while nose gear features a stereable wheel with rubber shock. Specially studied wheel fairings are mounted on each wheel to reduce parasite drag. Landing light is located inside engine cowling in correspondence of nose wheel strut. Engine cowling is made up two parts and allows for quick and complete opening. Fuel tanks are integral part of the wing structure and feature 35 liter capacity per each half wing. Fuel feed is via an engine driven pump and is backed-up for emergency by an electric pump. Istrument panel meets General Aviation standards both in size and quality allowing for installation of a wide variety of flight instrumentation inclusive of IFR, engine controls and com/nav apparatus. Flight controls are traditional type with dual stick, dual rudder pedals and dual throttle knobs on dashboard. Longitudinal trim and electrical flap controls with position indicators are also located on dashboard. Cabin ventilation is via adjustable air vents fed via buried scoops.

ENGINE IS FOUR STROKE, FOUR STROKE OPPOSING CYLINDERS

TBO 1500 HR - AUTOMOBILE GRADE FUEL
* ROTAX 912 U DA 59,6 kW (81 hp) REDUCTION GEARBOX 1:2,273
* ROTAX 912 S DA 73,5 kW (100 hp) REDUCTION GEAR

 

TECHNICAL FEATURES
Wing Span	8,4 m (27 ft 7 in)
Lenght over-all	6,4 m (21 ft)
Height over-all	2,3 m (7 ft 6 in)
Width cabin	1,12 m (3 ft 8 in)
Wing area	12,2 mq (121,3 sq ft)
Transv. Dihedral	5°
Tailplane span	2,9 m (9 ft 6 in)
Wheel track	1,8 m (5 ft 10 in)
Wheel tyres	5,00-5
ENGINE & PROPELLER
Power max	59,6 Kw (81 hp) @ 5800 rpm	73,5 kW (100 hp) @ 5800rpm
Reduction	2,273:1	2,4286:1
Propeller	Bipala GT - 166/146	Bipala GT - 172/164
Fuel	EURO SUPER OR UNLEADED
Tanks	70 Lt. (2x35) - 18,5 US gallons
WEIGHT
Designed MTOW	281 Kg (619 lb)
Max take off weight (L.106)	450 Kg (992 lb)
Basic empty weight (standard)	550 Kg (1212 lb)
Load ultimate factor	+6 -3
PERFORMANCE
Max speed s/l	225 km/h (121kts)	238 km/h (130kts)
Cruising speed 75% 5250 rpm	195 km/h (105kts)	215 km/h (116kts)
Vne - never exceed speed	260 km/h (140kts)
Rate of climb	890 ft/min (4,5 m/sec)	1180 ft/min (6 m/sec)
Stalling speed  (with flap)	61 Km/h (33 Kts)
Service ceiling	4000 m (13000 ft)	4500 m (14800 ft)
Max range (without reserve) 65%	750 Km (400 nm)
Take off to 15m (50 ft)	200 m (650 ft)	180 m (590 ft)
Take off run	110 m (360 ft)	100 m (328 ft)
Landing run	100 m (328 ft)