This four-seat development of the Christavia Mk I first flew on 3 January 1986. Plans and an information kit are available, and about 50 are under construction.

TYPE: Four-seat homebuilt cabin monoplane.

AIRFRAME: Similar to Christavia Mk I.

POWER PLANT: One 112 kW (150 hp) Textron Lycoming O-320 or converted motorcar engine. Fuel capacity 136.4 litres (36 US gallons; 30 Imp gallons).

DIMENSIONS, EXTERNAL:

• Wing span: 10.67 m (35 ft 0 in)
• Length overall: 7.01 m (23 ft 0 in)
• Height overall: 1.98 m (6 ft 6 in)
• Propeller diameter: 1.78 m (5 ft 10 in)

AREA:

• Wings, gross: 16.26 m² (175.0 sq ft)

WEIGHTS (112 kW; 150 hp engine):

• Weight empty: 522 kg (1,150 lb)
• Max T-O weight: 1,043 kg (2,300 lb)

PERFORMANCE:

• Max level speed at 610 m (2,000 ft): 111 knots (206 km/h; 128 mph)
• Econ cruising speed, 65% power: 102 knots (188 km/h; 117 mph)
• Stalling speed: flaps up: 35 knots (65 km/h; 40 mph)
• 12° flap: 31 knots (57 km/h; 35 mph)
• Max rate of climb at S/L: 244 m (800 ft)/min
• Service ceiling: 5,485 m (18,000 ft)
• T-O run: 91 m (300 ft)
• Landing run: 152 m (500 ft)
• Range with max fuel: 548 nm (1,017 km; 632 miles)

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