Abstract: Aircraft wing fatigue life and weight are strongly influenced by maximum wing root bending moment. The object of the invention is to augment the wing root bending moment relief that can be provided by the deflection of aircraft ailerons (12) in the conventional manner, while reducing or eliminating aileron induced wing torsional loading. To accomplish this, a movable aerodynamic control surface (14) is mounted on the outboard side of a contoured boom (13) situated at each wingtip. The exact size and location of the control surfaces (14) are determined by the particular aircraft application. Control surface size is a function of the aircraft aileron size, and each control surface (14) is located ahead of the elastic axis (10') of the wing (10). In addition to providing load alleviation, asymmetric deflection of the wingtip control surfaces (14) creates an aircraft rolling moment that adds to that produced by aileron deflection.