Single seat aerobatic competition aircraft
Low wing monoplane with a specially designed symmetrical airfoil,
16% thick, conic nose and flat sides. Large symmetrical ailerons.
Wire braced tail surfaces.
Fuselage has a welded steel tube truss covered with sheet metal from
the firewall aft to the cockpit, fabric covered from the cockpit aft
the tail. Aluminium sheet metal turtledeck. The tail surfaces are
fabric covered and wire braced with steel tube spars and bent up
steel sheet metal ribs. The one piece wing is all wood, Douglas Fir
and Spruce spars, plywood ribs and plywood covered. Large span
ailerons are built of wood and fabric covered. The fiberglass engine
cowl is a two piece, split horizontally and is easily removable for
ease in maintenance.
Pushrod actuated ailerons and elevator, cable actuated rudder.
Ailerons are mass balanced and aerodynamically counter balanced.
Each aileron is fitted with a ground adjustable balance surface
suspended below the aileron. A trim tab on each elevator also acts
as a servo tab to reduce stick pressures.
One Lycoming O-320 (150 HP) removed from a Cessna 172. Modifications
include inverted oil system, high compression pistons, and fuel
injection. Driving a two blade fixed pitch Senescing aluminium
propeller (74 inches diameter, 60 inches pitch). The fuel tank is
located in the fuselage ahead of the cockpit, capacity is 18.5
Non-retractable tail wheel type, main gear is a one piece aluminium
spring, tail wheel is steerable and full swivel mounted on a
cantilever steel spring. Main wheels are 5.00 x 5 with hydraulic
An adjustable seat back nominally reclined to 30 degrees.
Electrical system of 12 volts. Electric engine starter.
O-320 (150 HP)
two blade fixed pitch Senescing
19 ft 4 in
75.55 sq ft
rate of climb
landing distance, ground roll
limiting and recommended speeds
design manoeuvring speed (Va)
never exceed speed (Vne)
stall, power off (Vsl)
landing approach speed
All specifications are based on manufacturer's