The technological advancement in aerodynamics, propulsion, and structures for manned air vehicles in recent years has placed an ever increasing demand on actuation systems in the form of function, power level, and environment. A significant advance in actuation technology is necessary to improve vehicle mass ratio for high-performance vehicles. This paper describes the results of a parametric study which indicates a high level of confidence in the potential of the Balanced-Power concept for significant weight savings in aircraft actuation systems. The advantages of the Balanced-Power actuation concept are illustrated by a comparison between this concept and a conventional hydraulically actuated system for an identical flight control actuation problem. The Balanced-Power concept consists of mechanically actuated flight control surfaces, a mechanical servo, a flywheel and a motor. The motor maybe electrically, pneumatically, or hydraulically powered. This paper is the result of a study conducted at North American Aviation, Inc.