One embodiment is a method including defining a maximum deflection for a first axis of a control surface axis of an aircraft; defining a maximum deflection for a second axis of the control surface; and creating a graphical representation of the maximum deflection for the first and second control surface axes. The method further includes determining an angle of rotation of a structure on which the control surface is carried, wherein the angle of rotation is relative to a body of the aircraft; rotating the graphical representation in accordance with the determined angle of rotation; calculating a distance between a point representing a selected combination of roll moment and yaw moment and each edge of the graphical representation; and calculating a control surface deflection based on the calculated distances.