Abstract: An aircraft wing (12) comprising a structural member (20) forming the wing's leading edge skin, a Kreuger flap (16) which moves relative to the structural member (20) between a stowed position and a deployed position, and an electrothermal device (34) mounted (e.g., internally mounted) to the structural member (20). An aft portion (30) of the structural member (20) is curved inwardly to form a recess (32), and a fore portion (18) of the flap (16) fits within the notch (32) to form a joggle therebetween. The electrothermal device (34) is a deicing and/or anti-icing device which continuously provides heat to the curved aft portion (30) of the structural member (20) during icing conditions so as to prevent deployment-inhibiting ice buildup on the flap (16).

Abstract: An aircraft wing (12) comprising a structural member (20) forming the wing's leading edge skin, a Kreuger flap (16) which moves relative to the structural member (20) between a stowed position and a deployed position, and an electrothermal device (34) mounted (e.g., internally mounted) to the structural member (20). An aft portion (30) of the structural member (20) is curved inwardly to form a recess (32), and a fore portion (18) of the flap (16) fits within the notch (32) to form a joggle therebetween. The electrothermal device (34) is a deicing and/or anti-icing device which continuously provides heat to the curved aft portion (30) of the structural member (20) during icing conditions so as to prevent deployment-inhibiting ice buildup on the flap (16).

Abstract: A heater (10) for installation on a potable water tank (12). The heater (10) comprises a blanket (14) including an electrical resistance heating element (16) and a connection pad (18) for electrically connecting the heating element (16) to lead lines (20) to an aircraft power source (22). The water tank (12) is typically positioned under the cabin floor or other locations on an aircraft which are susceptible to cold temperatures, moisture invasion, and pressure drops/rises caused by changing altitudes. The heater (10) maintains the tank (12) at an acceptable temperature range and prevents freezing of the water.

Abstract: A drainmast assembly (10) for ejecting gray water from the onboard potable water system of an aircraft. The assembly (10) includes an interface (14) mounted on the fuselage of the aircraft and a drainmast (16) including a fairing (90) aligned with and attached to the interface (14). The interface (14) includes a pipe (46) having an outlet nipple (48) which is pivotally connected to an inlet portion (146) of the draintube (94). In this manner, the draintube (94) can rotate relative to the interface (14) should the fairing (90) be unintentionally hit by a baggage vehicle and shoved out of alignment with the interface (14).

Abstract: An aircraft hot water supply system (10) comprising a group of water-use stations (14a-14f) each including a hot water line having a heater (40a-40f) which heats water at a heating rate dependent upon power provided thereto. A power manager (44) allocates different non-zero percentages of heater-dedicated power to different heaters (40) depending upon conditions at the corresponding water-use stations (14). A network (46) is provided to establish peer-to-peer communication among the heaters' controllers (48a-48f).