Patent ID: 8155876

Claim:
An aircraft power system, comprising: a first electric motor; an aircraft load coupled to the first electric motor and powered by the first electric motor, the load including a hydraulic fluid pump; a high lift device coupled to the hydraulic fluid pump; a first motor controller coupled to the first electric motor to vary an output of the first electric motor, the first motor controller being changeable among a fixed number of preset controller modes, with a first controller mode corresponding to a first operation mode of the aircraft and a first non-zero output level of the first electric motor, and a second controller mode corresponding to a second operation mode of the aircraft and a second non-zero output level of the first electric motor, the second operation mode being different than the first operation mode, the second non-zero output level being different than the first non-zero output level, the first motor controller being operatively coupled to the high lift device to change the controller mode based at least in part on a change in position of the high lift device; a second electric motor; a second motor controller coupled to the second electric motor to direct operation of the second electric motor; and a switching device coupled between the first and second motor controllers to decouple the first motor controller from the first motor, decouple the second motor controller from the second motor, and couple the second motor controller to the first motor in place of the first motor controller.