This report deals with determining a hypothetic control system which provides improved rigid body and structural mode damping of a flexible aircraft in order to improve the riding qualities and to minimize the wing bending moment during flights in turbulence. The equations of motion used in the computations are related to a high' performance fighter aircraft with external stores. The feedback gains have been determinated using linear optimal control theory. The quadratic optimization criterion used takes into account the normal acceleration at the pilot seat and the wing root bending moment. A number of optimal and suboptimal regulators has been calculated. The system performance has been expressed in terms of pole locations, frequency response, power spectra for both pilot seat acceleration and wing root bending moment. Also time histories of the aircraft response to a deterministic gust disturbance have been presented.