Flap system for an aircraft high lift system or an engine actuation and method for monitoring a flap system

A method for monitoring an aircraft high lift system or an engine actuator having a rotary shaft and a first and a second load path from the rotary shaft, the method comprising the steps of:

• arranging at least a first and a second redundant load path from a rotational shaft, the first and second load paths comprising a first and a second respective rotational transmission having a first and a second respective output shaft;
• positioning a first and a second respective torque sensor (7a, 7b) on the first and second output shafts, reading the output torque values of the first and second output shafts from the first and second torque sensors of the first and second transmissions according to a predefined cycle, and determining the difference in torque output from the first and second rotational transmissions;
• providing a predefined torque threshold value or range and according to the predefined cycle, determining whether the difference, if any, between the output-side torque values at the first and second rotational transmissions of the at least two load paths exceeds the predefined torque threshold value and/or lies within the defined range;
• and
• generating a signal representing whether the cyclically measured difference in the torque value output from the first and the second rotational transmissions exceeds the threshold or range, and transmitting the signal to a control unit.