A wing assembly include at least one fuel tank having a tank outboard end. In addition, the wing assembly includes a stout wing rib located proximate the tank outboard end and extending between a front spar and a rear spar. The wing assembly also includes at least one outboard wing rib located outboard of the stout wing rib and defining an outboard wing bay. The wing assembly also includes an upper skin panel and a lower skin panel each coupled to the front spar, the rear spar, the stout wing rib, and the outboard wing rib. A plurality of bead stiffeners are coupled to the upper skin panel and/or the lower skin panel and are spaced apart from each other within the outboard wing bay.

An aircraft wingbox assembly is disclosed having a wingbox including an upper cover, a lower cover and a pair of spars; a plurality of ribs in the wingbox, wherein the ribs divide the wingbox into bays; and a fuel tank in the wingbox. All or part of the fuel tank is located in a first one of the bays between a first one of the ribs and a second one of the ribs. The fuel tank includes a tank wall and first and second tank lugs extending from the fuel tank wall. A first fastener attaches the first tank lug to the first one of the ribs; and a second fastener attaches the second tank lug to the second one of the ribs.

A method of partially insulating an interior space of a pre-formed fluted core panel is disclosed herein. The fluted core panel includes a first facesheet, a second facesheet spaced apart from the first facesheet, and webs between the first facesheet and second facesheet. The interior space is defined between the first facesheet, the second facesheet, and adjacent webs. The method includes positioning a spacer in a first portion of the interior space, positioning a membrane between the spacer and a second portion of the interior space, and positioning insulation in the second portion of the interior space. Additionally, the method includes pressing the membrane against the spacer, curing the membrane, and removing the spacer from the first portion of the interior space.

A fuel tank dam closes a gap that is formed between a first structural component and a second structural component. The fuel tank dam includes a first portion disposed on a first structural component side, a second portion disposed on a second structural component side, an elastic member that is supported by the first portion at one end while supported by the second portion at the other end and closes a gap that is formed between the first portion and the second portion, and a sealing mechanism that seals between the first member and the elastic member.

A fuel tank dam closes a gap that is formed between a first structural component and a second structural component. The fuel tank dam includes a first portion disposed on a first structural component side, a second portion disposed on a second structural component side, an elastic member that is supported by the first portion at one end while supported by the second portion at the other end and closes a gap that is formed between the first portion and the second portion, and a sealing mechanism that seals between the first member and the elastic member.

Provided is a fuel system that can reduce the amount of fuel in a second tank before the amount of fuel in a first tank. A fuel system includes: a first tank and a second tank that respectively store fuel; a fuel supply pump that supplies at least the fuel in the first tank out of the first and second tanks to a fuel consuming section; a transfer pump that transfers the fuel in the second tank into the first tank; and a fuel passage having an inlet in communication with an inner portion of the first tank, and an outlet in communication with an inner portion of the second tank. The fuel in the first tank overflows into the second tank through the fuel passage.

Provided is a fuel system that can reduce the amount of fuel in a second tank before the amount of fuel in a first tank. A fuel system includes: a first tank and a second tank that respectively store fuel; a fuel supply pump that supplies at least the fuel in the first tank out of the first and second tanks to a fuel consuming section; a transfer pump that transfers the fuel in the second tank into the first tank; and a fuel passage having an inlet in communication with an inner portion of the first tank, and an outlet in communication with an inner portion of the second tank. The fuel in the first tank overflows into the second tank through the fuel passage.

A connector for a structurally integrated line system of a vehicle, having a first end portion, a second end portion and a connecting piece extending between the first end portion and the second end portion, wherein the first end portion has at least one contact face for arrangement on a structurally integrated line, wherein at least one of the at least one contact face has a cutout which is surrounded by a closed border, wherein the second end portion has a flange connection for connection to a pipe.

A connector for a structurally integrated line system of a vehicle, having a first end portion, a second end portion and a connecting piece extending between the first end portion and the second end portion, wherein the first end portion has at least one contact face for arrangement on a structurally integrated line, wherein at least one of the at least one contact face has a cutout which is surrounded by a closed border, wherein the second end portion has a flange connection for connection to a pipe.

An aircraft comprising a structure comprising a leakproof tank delimited by walls, of which at least one is in contact with the air outside the aircraft, and filled partly with a two-phase heat-transfer fluid, a fuel cell that is passed through by a heat-transfer fluid, and a line which takes the heat-transfer fluid at an output of the fuel cell and which reintroduces this heat-transfer fluid at an input of the fuel cell. The line passes through the leakproof tank immersed in the heat-transfer fluid in liquid phase.