A flight test program and a computer simulation study have been conducted to evaluate the maneuverability and speed capability of the S-67 as a representative winged helicopter design. The flight program evaluated the effects on load factor capability of wings and of variations in gross weight, center of gravity, stabilator bias angle, and type of maneuver. The computer simulation determined the effects of stabilator linkage changes, of several control system feedbacks, and of differential speed brake application for roll control. Program results show that helicopter maneuverability can be improved by the addition of wings. Main rotor control system loads were the limiting factor on maneuver capability of the S-67. Control load buildup is minimized when rotor torque is low. Wings increased speed capability somewhat by delaying rotor stall effects. The dynamic stability of the S-67 satisfies MIL-H-8501A requirements above 100 knots.