The primary purpose of this study is to develop a nonlinear feedback control law for the F / A-I8 fighter aircraft that performs a fast half-loop maneuver. This feedback law is developed using a singular perturbation approach. A secondary purpose of this study is to establish a baseline for time optimal half-loop maneuvers. The singular perturbation approach makes it possible to develop a state feedback control law which rotates the velocity vector through one hundred and eighty degrees at a maximum equilibrium pitch rate with a nearly constant angle of attack. The response of the aircraft to the control law is compared to simulations of half-loop maneuvers generated at NASA Langley Research Center. / Master of Science