Abstract: A cooling system for an aircraft has at least one moveable member configured to cover an opening formed within an aircraft outer skin. An actuator moves the at least one moveable member between a fully open position where external atmosphere air can be directed through the opening to an internal passage enclosed by the aircraft outer skin and a fully closed position where the opening is covered. A controller selectively controls the actuator to move the at least one moveable member between the fully open and fully closed positions. An aircraft engine and a method of cooling an aircraft engine in an aircraft are also disclosed.

Abstract: A mounting assembly for restricting movement of an electrical harness of a gas turbine engine includes a base, a first channel formed in the base and extending between a first surface and a second surface of the base, and a second channel formed in the base and extending between the first surface and a third surface of the base. The second surface and the third surface are distinct. At least one flexible connector is receivable within the first channel and the second channel. At least a portion of the at least one flexible connector extends about the electrical harness to couple the electrical harness to the base.

Abstract: A mounting assembly for restricting movement of an electrical harness of a gas turbine engine includes a base, a first channel formed in the base and extending between a first surface and a second surface of the base, and a second channel formed in the base and extending between the first surface and a third surface of the base. The second surface and the third surface are distinct. At least one flexible connector is receivable within the first channel and the second channel. At least a portion of the at least one flexible connector extends about the electrical harness to couple the electrical harness to the base.

Abstract: A cooling manifold has a plurality of pieces. The pieces extend in a circumferential direction to abutting flanges. The flanges are secured together at circumferential ends of each piece. Cooling channels are formed in between inner and outer walls. Air inlets are formed in the pieces with the air inlets delivering air in the interior. There are fingers on an outer periphery. The fingers are aligned within an air outlet. The air can be delivered into the inlet, cool the interior, and leave through the outlet extending to a main conduit. The main conduit is secured directly to an outer periphery of the cooling manifold.

Abstract: A fitting according to an exemplary aspect of the present disclosure includes, among other things, a main body portion having a first axial end and a second axial end opposite the first axial end, an inlet provided at the first axial end, and an outlet adjacent the second axial end. The outlet includes a plurality of circumferentially spaced-apart slots formed through the main body portion, and each slot has an area within a range of 0.52 and 0.59 square inches.

Abstract: A cooling system for an aircraft has at least one moveable member configured to cover an opening formed within an aircraft outer skin. An actuator moves the at least one moveable member between a fully open position where external atmosphere air can be directed through the opening to an internal passage enclosed by the aircraft outer skin and a fully closed position where the opening is covered. A controller selectively controls the actuator to move the at least one moveable member between the fully open and fully closed positions. An aircraft engine and a method of cooling an aircraft engine in an aircraft are also disclosed.

Abstract: A system has a surface intended to separate two chambers within the system. The surface has an aperture for allowing passage of at least one communication conduit. A shroud is positioned on the surface at the aperture, and has at least two portions defining a central opening to allow the communication conduit to pass through the aperture and shroud. The two portions of shroud have mating clamp ears in contact with each other. Securement members tighten the clamp ears against each other to provide a seal at an end of the shroud remote from the surface.

Abstract: A fitting according to an exemplary aspect of the present disclosure includes, among other things, a main body portion having a first axial end and a second axial end opposite the first axial end, an inlet provided at the first axial end, and an outlet adjacent the second axial end. The outlet includes a plurality of circumferentially spaced-apart slots formed through the main body portion, and each slot has an area within a range of 0.52 and 0.59 square inches.

Abstract: An extendable protective arm is disclosed. The arm may protect an air, fuel, oil, or electrical conduit from harsh environments or the atmosphere during use. The arm may also connect the conduit between a moveable structure adapted to reciprocate relative to a fixed structure. The arm may extend in any number of dimensions.

Abstract: A cooling manifold has a plurality of pieces. The pieces extend in a circumferential direction to abutting flanges. The flanges are secured together at circumferential ends of each piece. Cooling channels are formed in between inner and outer walls. Air inlets are formed in the pieces with the air inlets delivering air in the interior. There are fingers on an outer periphery. The fingers are aligned within an air outlet. The air can be delivered into the inlet, cool the interior, and leave through the outlet extending to a main conduit. The main conduit is secured directly to an outer periphery of the cooling manifold.

Abstract: In accordance with one aspect of the disclosure, a multi stage air flow management system for a gas turbine engine is disclosed. The system may include an inlet provided in a nacelle of a gas turbine engine. A first passage may communicate a flow of air from the inlet to a first engine component of the gas turbine engine and a second passage may communicate a flow of air to a second engine component of the gas turbine engine.

Abstract: An extendable protective arm is disclosed. The arm may protect an air, fuel, oil, or electrical conduit from harsh environments or the atmosphere during use. The arm may also connect the conduit between a moveable structure adapted to reciprocate relative to a fixed structure. The arm may extend in any number of dimensions.

Abstract: A tubing includes an inner tube, an inner middle insulation layer, an outer middle securing layer, and an outer shrinkable cover that shrinks upon exposure to heat.