the xron-i uses a manually started 40 hp two-cycle engine with a gross weight capability of 500 lb. the fuselage is a simple box-beam construction. the rotor uses co-axial blades which alleviate the need for an anti-torque tail rotor. yaw control is provided by rotor tip mounted "tip brakes" providing differential torque between the rotors. gyrodyne patented the control on 24 october 1954 patent no. 2,835,331. there is a small inverted v-tail for control at forward speeds. the rotors are laminated wood construction. the mast is pressure lubricated and becomes a cooling surface for oil inflight. the landing gear consists of three small wheels.