Abstract: An aircraft power system is provided having an aircraft power supply and a bidirectional switch. The aircraft power supply includes an alternator, a battery and a load. The bidirectional switch is coupled between one of the alternator and the battery, and the load. The switch includes a first FET, a second FET and timing circuitry. A source of the first FET is coupled with a source of the second FET. A drain of the first FET is coupled with one of the alternator and the battery. A drain of the second FET is coupled with the load. The timing circuitry is configurable to generate a control signal deliverable to a gate of the first FET and the second FET for setting the first FET in selective on and off positions and the second FET in corresponding selective off and on position.

Abstract: An alternator comprises a housing including a first portion, and a second portion having a plurality of electrical connectors and having an aperture; a stator supported in the first portion of the housing; a rotor supported for rotation relative to the stator and configured to have a force current applied thereto; and a resistor coupled to the rotor and configured to reduce the current through the rotor, the resistor being removable and replaceable. Other apparatus and methods are provided.

Abstract: An alternator comprises a housing including a first portion, and a second portion having a plurality of electrical connectors and having an aperture; a stator supported in the first portion of the housing; a rotor supported for rotation relative to the stator and configured to have a force current applied thereto; and a resistor coupled to the rotor and configured to reduce the current through the rotor, the resistor being removable and replaceable. Other apparatus and methods are provided.