Abstract: An aircraft includes an airframe defining a first enclosed space, an engine bay disposed within the first enclosed space, and a cooling system. The engine bay includes a firebox defining a second enclosed space and an engine disposed at least partially within the second enclosed space. The cooling system is configured to selectively fluidly couple the first enclosed space with the second enclosed space.

Abstract: An aircraft includes an airframe defining a first enclosed space, an engine bay disposed within the first enclosed space, and a cooling system. The engine bay includes a firebox defining a second enclosed space and an engine disposed at least partially within the second enclosed space. The cooling system is configured to selectively fluidly couple the first enclosed space with the second enclosed space.

Abstract: A fuel supply system for an aircraft includes a fuel tank configured to supply fuel to an engine of an aircraft, a boost pump in operational communication with the fuel tank, wherein the boost pump is configured to control at least one of a fuel level and a fuel pressure in the fuel tank, and an electronic controller in communication with the boost pump and configured to control the boost pump. The electronic controller is configured to receive received information including (i) fuel information, (ii) flight information, and (iii) aircraft information, and configured to control the boost pump based on the received information.

Abstract: A vent valve includes a vent body including an outlet and at least one inlet, a main chamber, a main closable device movable from an open position to allow fluidic communication between the main chamber and the outlet, to a closed position to block fluidic communication between the main chamber and the outlet, and a first tubing having a first end and a second end, the first end connected to a first inlet, the second end spaced from the vent body, the first tubing further including a first closable device adjacent the second end. The first closable device allows fluidic communication between an exterior of the first tubing and an interior of the first tubing in a first orientation of the vent valve, and blocks fluidic communication between the exterior of the first tubing and the interior of the first tubing in a second orientation of the vent valve.

Abstract: A fuel supply system for an aircraft includes a fuel tank configured to supply fuel to an engine of an aircraft, a boost pump in operational communication with the fuel tank, wherein the boost pump is configured to control at least one of a fuel level and a fuel pressure in the fuel tank, and an electronic controller in communication with the boost pump and configured to control the boost pump. The electronic controller is configured to receive received information including (i) fuel information, (ii) flight information, and (iii) aircraft information, and configured to control the boost pump based on the received information.

Abstract: A vent valve includes a vent body including an outlet and at least one inlet, a main chamber, a main closable device movable from an open position to allow fluidic communication between the main chamber and the outlet, to a closed position to block fluidic communication between the main chamber and the outlet, and a first tubing having a first end and a second end, the first end connected to a first inlet, the second end spaced from the vent body, the first tubing further including a first closable device adjacent the second end. The first closable device allows fluidic communication between an exterior of the first tubing and an interior of the first tubing in a first orientation of the vent valve, and blocks fluidic communication between the exterior of the first tubing and the interior of the first tubing in a second orientation of the vent valve.