TYPE: Three-seat kitbuilt.

PROGRAMME: Being promoted in 2006.

COSTS: Kit USD19,950; assembled (minus engine) USD23,950 (2006).

DESIGN FEATURES: High-wing monoplane with V bracing struts; wings fold for transportation and storage. Pod and boom fuselage; mid-set braced tailplane. Large baggage door optional. Aircraft is not designed for aerobatics. Quoted build time 200 hours.

FLYING CONTROLS: Conventional and manual. Primary surfaces pushrod-actuated. Frise-type ailerons; three-position Fowler flaps. Photographs of aircraft show Junkers ailerons.

STRUCTURE: Fuselage is welded chromoly 4130 steel tube truss with carbon fibre reinforced glass fibre outer shell and tail surfaces. Fuselage shell and tail feathers are epoxy primer coated. Wings have aluminium spars, composites (heat-cured epoxy resins) ribs and skin; spars and ribs pre-cut to size to eliminate builder error.

LANDING GEAR: Tricycle type; fixed. Mainwheels have cantilever, self-sprung legs, 800x6 balloon tyres and hydraulic brakes; fully steerable nosewheel. Speed fairings optional.

POWER PLANT: One 48.0 kW (64.4 hp) Rotax 582 or 59.6 kW (79.9 hp) Rotax 912 UL standard; two-blade, fixed-pitch, ground-adjustable, glass fibre pusher propeller. Can also be fitted with suitable Jabiru or BMW alternatives. Fuel tank in each wing, combined capacity 106 litres (28.0 US gallons; 23.3 Imp gallons).

ACCOMMODATION: Two seats side by side, with third seat to rear. Polycarbonate transparencies. Cabin heater optional.

DIMENSIONS, EXTERNAL:

• Wing span: 10.97 m (36 ft 0 in)
• Wing chord, constant: 1.22 m (4 ft 0 in)
• Wing aspect ratio: 8.6
• Length: overall: 5.69 m (18 ft 8 in)
• wings folded: 7.21 m (23 ft 8 in)
• Width, wings folded: 2.51 m (8 ft 3 in)
• Height overall: 2.235 m (7 ft 5 in)
• Tailplane span: 3.175 m (10 ft 5 in)
• Propeller diameter: 1.88 m (6 ft 2 in)

DIMENSIONS, INTERNAL:

• Cabin max width: 1.14 m (3 ft 9 in)

AREAS:

• Wings, gross: 13.94 m² (150.0 sq ft)

WEIGHTS AND LOADINGS:

• Weight empty: 249 kg (550 lb)
• Max T-O weight: Rotax 582: 453 kg (1,000 lb)
• Rotax 912 UL: 499 kg (1,100 lb)
• Max wing loading: Rotax 582: 32.55 kg/m² (6.67 lb/sq ft)
• Rotax 912 UL: 35.80 kg/m² (7.33 lb/sq ft)
• Max power loading: Rotax 582: 9.45 kg/kW (15.53 lb/hp)
• Rotax 912 UL: 8.38 kg/kW (13.77 lb/hp)

PERFORMANCE (A: solo at 317.5 kg; 700 lb T-O weight, B: at MTOW):

• Never-exceed speed (V_NE): A, B: 86 kt (160 km/h; 100 mph)
• Cruising speed: A, B: 70 kt (129 km/h; 80 mph)
• Stalling speed: A: 35 kt (65 km/h; 40 mph)
• B: 38 kt (70 km/h; 43 mph)
• Best angle of climb speed: A: 39 kt (72 km/h; 45 mph)
• B: 42 kt (77 km/h; 48 mph)
• Max rate of climb at S/L: A: 305 m (1,000 ft)/min
• B: 229 m (750 ft)/min
• Service ceiling: A, B: 3,810 m (12,500 ft)
• T-O run: A: 37 m (120 ft)
• B: 92 m (300 ft)
• T-O to 15 m (50 ft): A: 77 m (250 ft)
• B: 138 m (450 ft)
• Landing run: A: 92 m (300 ft)
• B: 122 m (400 ft)
• Range with max fuel, 65% power, no reserves: A, B: 285 n miles (527 km; 328 miles)
• g limits: +5.0/-2.5

The article appears in the following publication:
Jane's All the World's Aircraft 2007-2008. Jane's Information Group Ltd. 2007. ISBN: 0-7106-2792-0