A sub-structure for an aircraft cabin monument is disclosed. The sub-structure includes a plurality of mounting attachment points for supporting a mount to engage with a corresponding mounting attachment point on a lattice structure of a load carrying partition wall. The aircraft cabin monument is supported by the load carrying partition wall through the sub-structure, supporting a substantial weight of the monument, and relieving the cabin floor from supporting the load and weight of the aircraft cabin monument.

A fuel containment system for an aircraft is provided. The fuel containment system comprises an upper fuel barrier under a cabin floor, an aft wheel well bulkhead, an aft fuel barrier opposite the aft wheel well bulkhead, a lower fuel barrier associated with a cargo floor, and a lower fuselage skin panel. A fuel tank is created by the upper fuel barrier, the aft wheel well bulkhead, the aft fuel barrier, the lower fuel barrier, and the lower fuselage skin. The fuel tank is integrated into the aircraft and existing structural components are sealed to prevent fuel from leaking out of the integrated fuel tank.

A fuel containment system for an aircraft is provided. The fuel containment system comprises an upper fuel barrier under a cabin floor, an aft wheel well bulkhead, an aft fuel barrier opposite the aft wheel well bulkhead, a lower fuel barrier associated with a cargo floor, and a lower fuselage skin panel. A fuel tank is created by the upper fuel barrier, the aft wheel well bulkhead, the aft fuel barrier, the lower fuel barrier, and the lower fuselage skin. The fuel tank is integrated into the aircraft and existing structural components are sealed to prevent fuel from leaking out of the integrated fuel tank.

Embodiments are directed to a fuel cell protection system comprising an aircraft fuselage having an inner surface and an outer surface, an attachment point mounted on the outer surface, an aircraft fuel cell spaced apart from the inner surface, and a plate positioned between the inner surface and the aircraft fuel system, the plate spaced apart from the inner surface to create a void space. The attachment point may be a cargo hook. The void space is configured to receive all or a portion of the cargo hook after a crash. The plate creating the void space may be a rigid material or may be a ballistic fabric material.

Embodiments for aircraft keel beam assembly. One embodiment is a keel beam assembly of an aircraft. The keel beam assembly includes a keel attach chord to connect to a wing center section of the aircraft, the keel attach chord extending in a longitudinal direction between a rear spar and front spar of the aircraft. The keel beam assembly also includes a lower chord disposed underneath the keel attach chord and extending in the longitudinal direction between an aft wheel well bulkhead and a forward bulkhead of the aircraft. The keel beam assembly further includes a forward web to couple the keel attach chord and the lower chord, the forward web including a front edge extending in a diagonal direction from the keel attach chord that is downward and aft toward the lower chord to create an open area forward from the front edge.

Embodiments for aircraft keel beam assembly. One embodiment is a keel beam assembly of an aircraft. The keel beam assembly includes a keel attach chord to connect to a wing center section of the aircraft, the keel attach chord extending in a longitudinal direction between a rear spar and front spar of the aircraft. The keel beam assembly also includes a lower chord disposed underneath the keel attach chord and extending in the longitudinal direction between an aft wheel well bulkhead and a forward bulkhead of the aircraft. The keel beam assembly further includes a forward web to couple the keel attach chord and the lower chord, the forward web including a front edge extending in a diagonal direction from the keel attach chord that is downward and aft toward the lower chord to create an open area forward from the front edge.

A feed-through assembly for a bulkhead for moving and static engine components. The feed-through assembly can be configured to include flexible convolutions that allow for movement and sealing of the engine component relative to the bulkhead. In one aspect, a flexible convoluted spherical element can be provided in the feed-through assembly. In another aspect, a flexible convoluted bellow element can be provided in the feed-through assembly. These flexible convoluted elements can have multiple convolution sections including convolution sections with varying stiffness. The convolution sections can be configured to allow movement of the shaft relative to the bulkhead, including, transverse deflection and tilt.

A nose structure of an aircraft includes an airframe. A wheel well assembly is coupled to the airframe and forms a portion of a nose landing gear bay. The wheel well assembly includes a pressure deck that extends from a right side of the airframe to a left side of the airframe and that forms a portion of a pressure boundary delimiting a pressurized space and a non-pressurized space. A floor-panel support is supported by the pressure deck in the pressurized space. The pressure deck and the floor-panel support form a portion of a flight deck floor of a flight deck of the aircraft. A plurality of transport elements is located between the floor-panel support and the pressure deck. The plurality of transport elements is associated with at least one high-level system of the aircraft.

A nose structure of an aircraft includes an airframe. A wheel well assembly is coupled to the airframe and forms a portion of a nose landing gear bay. The wheel well assembly includes a pressure deck that extends from a right side of the airframe to a left side of the airframe and that forms a portion of a pressure boundary delimiting a pressurized space and a non-pressurized space. A floor-panel support is supported by the pressure deck in the pressurized space. The pressure deck and the floor-panel support form a portion of a flight deck floor of a flight deck of the aircraft. A plurality of transport elements is located between the floor-panel support and the pressure deck. The plurality of transport elements is associated with at least one high-level system of the aircraft.

Embodiments for hybrid pressure deck of an aircraft. One embodiment is a pressure deck disposed over a main gear wheel well of an aircraft. The pressure deck includes longitudinal beams extending in a forward and aft direction between an aft wheel well bulkhead and a rear spar of the aircraft. The pressure deck also includes a web attached to an underside of the longitudinal beams. The web includes a flat web portion supported by transverse stiffeners extending in an inboard and outboard direction, and a curved web portion including arches configured to flex laterally from load in the inboard and outboard direction. A transition between the flat web portion and the curved web portion extends at least partially in the forward and aft direction of the aircraft.