Methods of assembling an aircraft wing includes adhering fuel dams to stringers and adhering the fuel dams to ribs. Fuel dams include a fuel-dam body that defines a channel shaped to receive a portion of a stringer of an aircraft wing. The fuel-dam body includes a stringer adherent surface, a rib adherent surface, and a pair of spaced-apart flanges extending from the rib adherent surface and positioned to project from the rib adherent surface on opposing sides of a notch of a rib.

Methods of assembling an aircraft wing includes adhering fuel dams to stringers and adhering the fuel dams to ribs. Fuel dams include a fuel-dam body that defines a channel shaped to receive a portion of a stringer of an aircraft wing. The fuel-dam body includes a stringer adherent surface, a rib adherent surface, and a pair of spaced-apart flanges extending from the rib adherent surface and positioned to project from the rib adherent surface on opposing sides of a notch of a rib.

Embodiments of the present invention provide a fuel tank communication system. The communication system includes a main body (30) used to connect two fuel bladder flanges (12, 20) to one another. The communication system provides two separate, independent locking features (42, 60) that can secure fuel bladders to one another.

Embodiments of the present invention provide a fuel tank communication system. The communication system includes a main body (30) used to connect two fuel bladder flanges (12, 20) to one another. The communication system provides two separate, independent locking features (42, 60) that can secure fuel bladders to one another.

A duct stringer assembly with a bulkhead. The duct stringer assembly has duct walls providing a duct with a closed cross-section. The duct is adapted to transport fluid. A bulkhead is in the duct, and the bulkhead is adapted to block the flow of fluid along the duct. The bulkhead has a bulkhead body, and a gasket sealing a gap between the bulkhead body and the duct walls.

Seal member arrangements having at least one seal plate are disposed over stringer receiving recesses in ribs of an aircraft. A tool for locating a seal member arrangement over a stringer-receiving recess in a rib of an aircraft assembly. The tool system has a holder configured to hold the seal member arrangement over the recess. A biasing arrangement is configured to act on the holder to bias the seal member arrangement into an aligned position with a stringer received in the recess. A fixing arrangement is configured to act on the seal member arrangement to fix the seal member arrangement in the aligned position. A sealing kit, an aircraft assembly, a method of fixing a seal member arrangement over a stringer-receiving recess in a rib of an aircraft are also disclosed.

An aircraft wing box is disclosed having a fuel tank with a fuel-tight boundary, upper and lower covers, forward and aft spars, and a partition including an inboard portion, an outboard portion, and a third portion between the inboard and outboard portions. Each cover is attached to each spar, the inboard portion of the partition is joined to each cover and joined to one of the spars, the outboard portion of the partition is joined to each cover and joined to one of the spars, each cover is joined to the partition. The inboard part, outboard part and third part of the partition are integrally formed as a single-piece; and the single-piece provides part of the fuel-tight boundary of the fuel tank.

An aircraft wing box is disclosed having a fuel tank with a fuel-tight boundary, upper and lower covers, forward and aft spars, and a partition including an inboard portion, an outboard portion, and a third portion between the inboard and outboard portions. Each cover is attached to each spar, the inboard portion of the partition is joined to each cover and joined to one of the spars, the outboard portion of the partition is joined to each cover and joined to one of the spars, each cover is joined to the partition. The inboard part, outboard part and third part of the partition are integrally formed as a single-piece; and the single-piece provides part of the fuel-tight boundary of the fuel tank.

A system and method of controlling a fuel system on an aircraft includes selectively supplying fuel from either a main fuel tank or at least one wing fuel tank to a fuel consumer by varying a speed of at least one main fuel tank pump associated with the main fuel tank relative to a speed of at least one wing fuel tank pump associated with the at least one wing fuel tank.

A system and method of controlling a fuel system on an aircraft includes selectively supplying fuel from either a main fuel tank or at least one wing fuel tank to a fuel consumer by varying a speed of at least one main fuel tank pump associated with the main fuel tank relative to a speed of at least one wing fuel tank pump associated with the at least one wing fuel tank.