A method for obtaining recovery controls from nonlinear flight conditions such as spins, using momentum vector control, is presented. In a spin, the large angular velocity and high angles of attack the airplane experiences make it diffkult to control. This loss of control is a serious cause of aviation accidents. In this study, a systematic approach to momentum vector control is proposed. To arrest rotation and also to recover from the spin, the direction and magnitude of linear and angular momentum vectors are effected to restore their steady-state and/or pre-spin entry values. Required control surface deflections to recover from spin are computed by minimizing an objective function consisted of linear and anklar momentum terms. Simulated time histories using data for a light single engine general aviation aircraft, are used to validate this proposed approach. The method produced controls time histories which effected recovery from both a steep and a flat spin. These results indicate the validity and reliability of the proposed approach.