Method of dynamically alleviating loads generated on an aircraft by a disturbance of gust, the method comprising the steps of: automatically detecting a disturbance due to gust on a flight of the aircraft; when a disturbance due to gust is detected, automatically generating control commands for control surfaces; and applying the control commands to actuate the control surfaces; characterized by generating control commands using a predetermined control command sequence (24, 26) that has been pre-determined in a previous control command sequence determining step for dynamically actuating the control surfaces in a prescribed dynamic way in order to minimize not only a first load peak but also at least a second load peak, wherein the control command sequence determining step comprises: determining a load response of the aircraft in response to an actuation of the control surface according to a basis function H i, modelling the control command sequence as a linear combination of basis functions in the form of H = Σ n ⁢ θ i ⋅ H i wherein θ i represents the i th element of a vector of variable θ, simulating a typical wind gust shape being alleviated by the control command sequence H, and determining the vector of variable θ by optimization calculation such that the load response to the typical wind gust shape is minimized for a first load peak and also at least a second load peak. automatically detecting a disturbance due to gust on a flight of the aircraft; when a disturbance due to gust is detected, automatically generating control commands for control surfaces; and applying the control commands to actuate the control surfaces; characterized by generating control commands using a predetermined control command sequence (24, 26) that has been pre-determined in a previous control command sequence determining step for dynamically actuating the control surfaces in a prescribed dynamic way in order to minimize not only a first load peak but also at least a second load peak, wherein the control command sequence determining step comprises: determining a load response of the aircraft in response to an actuation of the control surface according to a basis function H i, modelling the control command sequence as a linear combination of basis functions in the form of H = Σ n ⁢ θ i ⋅ H i wherein θ i represents the i th element of a vector of variable θ, simulating a typical wind gust shape being alleviated by the control command sequence H, and determining the vector of variable θ by optimization calculation such that the load response to the typical wind gust shape is minimized for a first load peak and also at least a second load peak. determining a load response of the aircraft in response to an actuation of the control surface according to a basis function H i, modelling the control command sequence as a linear combination of basis functions in the form of H = Σ n ⁢ θ i ⋅ H i wherein θ i represents the i th element of a vector of variable θ, simulating a typical wind gust shape being alleviated by the control command sequence H, and determining the vector of variable θ by optimization calculation such that the load response to the typical wind gust shape is minimized for a first load peak and also at least a second load peak.