Abstract: Ice may form along the leading edge of an aircraft wing or horizontal and vertical stabilizers. A pneumatic deicer system may be configured to inflate and dislodge ice along the leading edge of lift and control surfaces. The pneumatic deicer system may comprise a laser welded deicing boot attached to the leading edge. The compressed air can be directed to the deicing boot, inflating the deicing boot along inflatable tubes formed by laser welds, which can crack and dislodge the ice. A method of manufacturing a laser welded pneumatic deicer boot is also disclosed.

Abstract: A grommet is provided for use in a fire and overheat detection system (FODS) clamp. The grommet includes an elongated body defining a central aperture and a slit. The elongated body includes wire mesh.

Abstract: A plumbing system may comprise: a fluid conduit configured to receive waste water; a first ultrasonic flow sensor coupled to the fluid conduit; a valve in fluid communication with a drain conduit, the valve configured to impede a fluid path of the plumbing system in response to being in a closed state; and a controller electronically coupled to the first ultrasonic flow sensor and the valve, the controller configured to: determine fluid is flowing through the fluid conduit in response to receiving a sensor data from the first ultrasonic flow sensor, and activate the valve based on the sensor.

Abstract: A self-regulating heater may comprise a first substrate including a first silicone layer and a first polyimide layer. A positive temperature coefficient heating element may be formed over the first polyimide layer. A second substrate may be located over the positive temperature coefficient heating element. The second substrate may include a second silicone layer and a second polyimide layer.

Abstract: A support arrangement include a mount, a cover, and a metallic mesh body. The mount has a base portion and a mount clamping portion. The cover has a plate portion and a cover clamping portion, the cover fixed to the base portion of the mount and the cover clamping portion registered to the mount clamping portion. The metallic mesh body is arranged between the mount clamping portion and the cover clamping portion to compressively support a sensor element between the mount clamping portion and the cover clamping portion. Fire and overheat detection systems, gas turbine engines with fire and overheat detection systems, and methods of making support arrangements for fire and overheat detection systems are also described.

Abstract: A grommet is provided for use in a fire and overheat detection system (FODS) clamp. The grommet includes an elongated body defining a central aperture and a slit. The elongated body includes wire mesh.

Abstract: A flexible heated hose assembly for an aircraft is provided. The flexible heated hose assembly including: an inner fluid tube enclosing a fluid passageway, the inner fluid tube having tubular shape; a first silicone liner located radially outward from the inner fluid tube; and a printed positive temperature co-efficient (PTC) heater located radially outward from the first silicone liner.

Abstract: A support arrangement include a mount, a cover, and a metallic mesh body. The mount has a base portion and a mount clamping portion. The cover has a plate portion and a cover clamping portion, the cover fixed to the base portion of the mount and the cover clamping portion registered to the mount clamping portion. The metallic mesh body is arranged between the mount clamping portion and the cover clamping portion to compressively support a sensor element between the mount clamping portion and the cover clamping portion. Fire and overheat detection systems, gas turbine engines with fire and overheat detection systems, and methods of making support arrangements for fire and overheat detection systems are also described.

Abstract: Systems and methods for operating a potable water system in an aircraft are provided. Aspects include determining, by a controller, flight data associated with a flight for the aircraft, determining passenger data associated with the flight, determining an estimated water consumption for the potable water system associated with the aircraft based on the passenger data, determining a water quantity value for the flight based at least in part on the flight data and the estimated water consumption, and transmitting, by the controller, a request for the water quantity value for the potable water system for the flight to a water fulfillment system.

Abstract: A clamp fixture includes a hub extending between a first end and a second end. A first leg extends in a first direction from the first end of the hub, and a second leg extends in the first direction from the second end of the hub. At least a portion of the first leg curves away from the second leg, and at least a portion of the second leg curves away from the first leg. The clamp fixture also includes a loop with a first half and a second half. The first half includes a first jaw extending from the hub. The second half includes a flange and a second jaw extending from the flange. A fastener connects the flange to the hub such that the first jaw and the second jaw join to close the loop.

Abstract: A clamp fixture includes a hub extending between a first end and a second end. A first leg extends in a first direction from the first end of the hub, and a second leg extends in the first direction from the second end of the hub. At least a portion of the first leg curves away from the second leg, and at least a portion of the second leg curves away from the first leg. The clamp fixture also includes a loop with a first half and a second half. The first half includes a first jaw extending from the hub. The second half includes a flange and a second jaw extending from the flange. A fastener connects the flange to the hub such that the first jaw and the second jaw join to close the loop.

Abstract: A flexible heated hose assembly for an aircraft is provided. The flexible heated hose assembly including: an inner fluid tube enclosing a fluid passageway, the inner fluid tube having tubular shape; a first silicone liner located radially outward from the inner fluid tube; and a printed positive temperature co-efficient (PTC) heater located radially outward from the first silicone liner.