Abstract: An aircraft electric power supply system (10) for supplying electric power to onboard electric devices (20) during flight. To reduce the devices' power draw, the electric power is supplied via modulation at an increment-percentage that is determined by present conditions. An optimum portfolio can be established for the electrical devices (20) collectively, this portfolio being selected in accordance with an energy-management criterion or other aircraft objectives.

Abstract: A valve assembly (20) for an aircraft water supply system. The valve assembly (20) comprises a valve member (40), an electrical motor (64), and a mechanical returning mechanism (80). When electrical power is provided, the motor (64) can be controlled to move the valve member (40) from a first position and to a second position. The mechanism (80) is operably connected to the valve member (40) and mechanically biases it towards the first position. If a power loss occurs when the valve member (40) is in the second position, the returning mechanism (80) non-electrically (e.g., mechanically) returns the valve member (40) to the first position.

Abstract: An aircraft (10) having a cabin (14) with a plurality of potable-water-using stations (22) that drain graywater to a transfer tank (24). The graywater ejection system pressurizes the transfer tank (24) at appropriate times and/or places, so that graywater can be ejected through a drainmast (26) without the help of gravity. This graywater ejection system eliminates the need for a discharge line from the transfer tank (24) and frees the aircraft's fuselage (12) from having an inconvenient port associated with such a discharge line.