Abstract: There is provided an engine assembly for an aircraft, comprising a heat engine in driving engagement with an engine shaft having a first end coupled to a mechanical gearbox and a second end opposite the first end, an electric generator coupled to the second end to provide a generator output voltage, the electric generator separate from the mechanical gearbox, a power electronics module connected to the electric generator and configured to regulate the generator output voltage to provide a regulated output voltage that meets an electrical power demand of at least one aircraft accessory, and a voltage bus connected to the power electronics module and configured to supply the regulated output voltage to the at least one aircraft accessory.

Abstract: Methods and systems for measuring a level of a fluid. A first output is obtained from first sensing elements at a first electrical circuit, the first sensing elements configured to produce the first output based on a position of a floater movable along a floater path. The position of the floater is determined at the first electrical circuit based on the first output. A second output is obtained from second sensing elements at a second electrical circuit, the second electrical circuit being isolated from the first electrical circuit, at least one of the first sensing elements being interleaved with at least one of the second sensing elements, the second sensing elements configured to produce the second output based on the position of the floater. The position of the floater is determined at the second electrical circuit based on the second output.

Abstract: Methods and systems for measuring a level of a fluid. A first output is obtained from first sensing elements at a first electrical circuit, the first sensing elements configured to produce the first output based on a position of a floater movable along a floater path. The position of the floater is determined at the first electrical circuit based on the first output. A second output is obtained from second sensing elements at a second electrical circuit, the second electrical circuit being isolated from the first electrical circuit, at least one of the first sensing elements being interleaved with at least one of the second sensing elements, the second sensing elements configured to produce the second output based on the position of the floater. The position of the floater is determined at the second electrical circuit based on the second output.

Abstract: There is provided an engine assembly for an aircraft, comprising a heat engine in driving engagement with an engine shaft having a first end coupled to a mechanical gearbox and a second end opposite the first end, an electric generator coupled to the second end to provide a generator output voltage, the electric generator separate from the mechanical gearbox, a power electronics module connected to the electric generator and configured to regulate the generator output voltage to provide a regulated output voltage that meets an electrical power demand of at least one aircraft accessory, and a voltage bus connected to the power electronics module and configured to supply the regulated output voltage to the at least one aircraft accessory.