Single seat single engined low wing mono¬plane with conventional three axis control. Wing has unswept leading and trailing edges, and constant chord; conventional tail. Pitch control by elevator on tail; yaw control by fin mounted rudder. Control inputs through stick for pitch/roll and pedals for yaw. Wing braced from below by struts; wing profile FX 72 MS 150 modified; double¬surface. Undercarriage has two wheels with tailskid. Fuselage partially enclosed. Engine mounted above wing driving tractor propeller.
The Easy Flyer was one of the earliest microlights offered in plan form for amateur constructors. Designed by H Beaujon, it was first built in 1976 and offered for sale the following year. It is of classical configuration, remaining very close to the traditional aircraft concept, and differs really only in those aspects of specification and performance where change was essential to qualify it as an ultralight. H Beaujon was one of the first designers to advise using two-¬stroke engines for aeronautical use, and in this instance chose a Rockwell JLO L 395 single cylinder motor weighing 59 lb (27 kg).

Engine: Rockwell JLO L 395, 24.5hp at 5500rpm.
Prop diameter/pitch: 46×20 inch, 1.04 x 0.45 m
Power/unit area: 0.28 hp/sq.ft, 3.0 hp/sq.m.
Length overall: 15.3 ft, 4.64 m
Height overall: 4.8ft, 1.42m.
Wing span: 25.1ft, 7.87m
Total wing area: 89 sq.ft, 8.3sq.m
Constant chord at root: 3.8ft, 1.11m
Wing aspect ratio: 7.5/1.
Empty weight: 175 lb, 79kg
Max take off weight: 372 lb, 169kg.
Payload: 197 lb, 89kg.
Max wing loading: 4.18 lb/sq.ft, 20.4kg/sq.m.
Max power loading: 15.2 lb/hp, 6.9kg/hp
Max level speed: 79mph, 128kph.
Cruising speed: 65mph, 104 kph
Stalling speed: 28 mph, 46 kph.
Max climb rate at SL: 490 ft/min, 2.5 m/s.

Single seat single engined high wing monoplane with conventional three axis control. Inverted V tail. Pitch/yaw control by elevon; control inputs through stick for pitch/roll and pedals for yaw. Integrated flaps and ailerons. Wing braced from below by struts; wing profile; NASA high-lift airfoil double surface. Undercar¬riage has three wheels in tricycle formation: spring steel, inflatable tires. Aluminium tube framework, without pod. Engine mounted below wing driving pusher propeller.
Two struts either side of the pilot support the high wing, and there are no rigging wires, the absence of a kingpost making for a very clean design. Wings are foam blanks fitted to aluminum spars and heat-shrink covered with Dacron. The maker says that 3 inch (7.6 cm) square section tubing is used for the structure, which as a result can handle 9 g. It has a single large diameter vertical wing support between pilot and engine.

Engine: Rotax 38 hp
Prop: 52”
Wingspan: 30’.
Wing area: 150 sq.ft.
Empty weight: 243 lbs.
Gross weight: 625 lbs.
Fuel capacity: 5 USG.
Fuel consumption: 1.5 gph.
Load factors: +9, -6 G’s.
Takeoff roll: 100’.
Climb rate: 950 fpm.
Landing roll (full flaps): 60’.
Stall speed: 20 knots.
Max cruise: 63 mph.
Available as: plans and materials; plans and all parts kit or complete flight tested aircraft.