Side by side two seat single engined high-wing monoplane with conventional three axis control. Wing has swept back leading and trailing edges, and tapering chord; no tail. Pitch/roll control by stabilators; yaw control by tip rudders; control inputs through stick for pitch/roll and pedals for yaw. Cantilever wing; wing profile NACA 23015; double-surface. Undercarriage has three wheels in tricycle formation; suspension on all wheels. Push right go right nosewheel steering connected to yaw control. Brake on nosewheel. Aluminium tube/wood/steel tube framework, partially enclosed. Engine mounted below wing driving pusher propeller.
Seeing the need for training aircraft, Micro Aviation decided at the end of 1981 to launch some two seater microlights. To this end, the firm asked Don Mitchell to give it the benefit of his experience in this matter and a prototype called the Two Seat Trainer was duly shown at Oshkosh in August 1982.
By 1983 it has not gone into serious production. The aircraft shown was a direct development of the B10 Mitchell Wing, enlarged and strengthened. It was intended that the two-seater should use a Konig SD570 four cylinder two stroke engine.
Engine: Konig SD570, 28 bhp at 4200 rpm.
Power per unit area 0.16hp/sq.ft, 1.7 hp/sq.m.
Wing span 38.0 ft, 11.58 m.
Mean chord 4.8 ft, 1.45 m.
Total wing area 181 sq.ft, 16.8 sq.m.
Wing aspect ratio 8.0/1.
Empty weight 240 lb, 109kg.
Max take off weight 640 lb, 290 kg.
Payload 400 lb, 181 kg.
Max wing loading 3.55 lb/sq.ft, 17.3 kg/sq.m.
Max power loading 22.9 lb/hp, 10.4kg/hp.
Load factors +6.0, 6.0 design.
Stalling speed 24 mph, 38 kph.
Max climb rate at sea level 400ft/min, 2.0m/s.
Take off distance 350ft, 107m.
All Aero 