1. A method for monitoring an actuator for a control surface on an aircraft, the method comprising: receiving an error signal generated in response to sending a command to the actuator to move the control surface on the aircraft; responsive to receiving the error signal, identifying an amplitude and a frequency for the error signal; determining whether the amplitude exceeds a set of amplitude limits for the frequency, wherein each amplitude in the set of amplitude limits is associated with a requirement in a set of requirements; incrementing an exceedance count for each requirement in the set of requirements in which an associated amplitude limit has been exceeded by the amplitude to form an updated set of exceedance counts; and generating a fault indication if any exceedance count in the updated set of exceedance counts is greater than a threshold.