Patent ID: 8256718

Claim:
A method for providing automatic load alleviation to a landing flap system of an aircraft when a blockage occurs, comprising: in response to a first control signal emitted by a control device bringing at least one high lift surface, which is actuated by means of a local mechanical final control element, to a predetermined position by a central drive unit that is connected by way of a rotary shaft arrangement to the local final control element by generating a torque transmitted by the central drive unit to the rotary shaft arrangement, and wherein, if a first signal is registered that indicates that there is a blockage within the high lift surface system, automatically reducing the torque transmitted by the central drive unit to the rotary shaft arrangement to a predetermined low torque value, and fixing the position of the high lift surface system; wherein the first signal that indicates a blockage is derived from registering a second signal which represents a predetermined high torque value in relation to the torque transmitted by the central drive unit to the rotary shaft arrangement in conjunction with an occurrence of a second control signal caused by the pilot to the effect of initiating a reversal in the direction of rotation of the rotary shaft arrangement.