The Chevvron was first flown in 1983. Production began in 1987 and deliveries have been in assembled form.

TYPE: Side by side two-seat microlight/trainer; conforms to BCAR Section S.

AIRFRAME: Airframe of glassfibre/carbonfibre/Kevlar and foam construction. Wortmann wing section. Three-axis control. Non-retractable tricycle landing gear, with brakes. Optional floats.

POWER PLANT: One 24 kW (32 hp) König SD 570; at least one seaplane powered by a 35.8 kW (48 hp) König engine. Standard fuel capacity 30 litres (7.9 US gallons; 6.6 Imp gallons). One auxiliary fuel tank optional, either of 30 litres or 20 litres (5.3 US gallons; 4.4 Imp gallons) capacity.

DIMENSIONS, EXTERNAL:

• Wing span: 13.41 m (44 ft 0 in)
• Length overall: 7.01 m (23 ft 0 in)
• Height overall: 1.52 m (5 ft 0 in)
• Propeller diameter: 1.52 m (5 ft 0 in)

AREA:

• Wings, gross: 17.56 m² (189.0 sq ft)

WEIGHTS:

• Weight empty: 175 kg (386 lb)
• Pilot weight range: 50-180 kg (110-396 lb)
• Max T-O weight: 382 kg (842 lb)

PERFORMANCE:

• Max level and max cruising speed: 65 knots (120 km/h; 75 mph)
• Econ cruising speed: 55 knots (102 km/h; 63 mph)
• Stalling speed: 30 knots (56 km/h; 35 mph)
• Max rate of climb at S/L: 128 m (420 ft)/min
• Service ceiling: 3,050 m (10,000 ft)
• T-O run: 91 m (300 ft)
• Landing run: 137 m (450 ft)
• Range with standard fuel: 200 nm (370 km; 230 miles)
• Endurance: 3h
• g limits: +4/-2

The article appears in the following publication:
Jane's All the World's Aircraft 1991-92. Jane's Information Group Ltd. 1991. ISBN: 0-7106-0965-5