§¶ # The alleviation of dynamic gust loads on a transport aircraft using wing-mounted control surfaces is investigated. Three different wing-mounted control surfaces are considered: symmetrically-actuated ailerons, under-wing forward-positioned control surfaces at about 0.8 of the wing span, and wing-tip forward-positioned control surfaces. The main investigation is for a 1:10 cable-mounted wind-tunnel model of a transport aircraft that was constructed and tested at the TsAGI laboratories. The length of a one-minus-cosine vertical gust velocity profile is tuned to yield maximal wing-root bending moment. All the control laws are based on simple low-pass filters for easy and robust application in the wind tunnel. Each is based on a single input of a wing-tip accelerometer which is shown to react in time to allow the alleviation of the peak of the wing-root bending moment. All the three control means are shown to alleviate the extreme wing-root moments by 9-16% and the wing-tip accelerations by 26-33% at intermediate design flight velocities. The effects on section-loads envelopes at monitoring stations along the wing are also very favorable. The wing-tip and under-wing controls are found to be more effective than the existing aileron at these speeds. The ailerons become even less effective at higher speeds due to reduction in their aeroelastic effectiveness. The application of the same control concept to the full-scale aircraft model exhibits similar results. The effects of the designed control laws on the statistical response of the wing loads to continuous gusts are shown to be similar to their effects on discrete gusts.