Patent ID: 8868261

Claim:
An actuation system of an aircraft, comprising a guiding device for an adjustable flap with a load sensor and a monitoring device with a function for monitoring the guiding device, wherein an interface to the load sensor and an interface to a driving device for adjusting the regulating flap are integrated into the monitoring device, wherein the monitoring device is realized in such a way that it determines or receives in-flight information that actively signals a predefined flight attitude and/or a predefined operational state of the aircraft; wherein the monitoring device comprises a comparing function for carrying out a comparison between a load value that corresponds to a sensor value acquired by the load sensor and a limiting value that corresponds to a minimum operational load for the predefined flight attitude and/or the predefined operational state of the aircraft; and wherein the monitoring function is realized in such a way that it assigns a fault mode to the regulating flap if it is determined that the predefined flight attitude and/or the predefined operational state of the aircraft exists as a result of the comparison showing that the limiting value corresponding to the minimum operational load is not reached.