A connector to connect a center wing box to a bulkhead of an aircraft. The connector includes a panel with a first edge positioned at the center wing box, an opposing second edge positioned at the bulkhead, and a central section. A first flexible seal extends across the panel and provides for relative movement between the first edge and the central section. A second flexible seal extends across the panel and provides for relative movement between the second edge and the central section.

A joint for connecting a center wing box to a bulkhead of an aircraft. The joint includes a flex angle member with a first section shaped to abut against and be connected to the center wing box, a second section shaped to abut against and be connected to a first side of the deck of the bulkhead, and an intermediate rounded corner positioned between the first and second sections. First support members are attached to the center wing box at first pins and support a first side of the second section of the flex angle member. Second support members are attached to the web of the bulkhead at second pins and support a second side of the second section of the flex angle member. The first support members are positioned on a first side of the deck of the bulkhead and the second support members are positioned on an opposing second side of the deck.

A pressure deck for an aircraft comprises a flat composite laminate base panel having integrated tear straps to enhance damage arrestment. The tear straps include a plurality of multi-ply, spaced apart longitudinal and lateral tear straps interspersed with the plies of the base panel.

A pressure deck for an aircraft comprises a flat composite laminate base panel having integrated tear straps to enhance damage arrestment. The tear straps include a plurality of multi-ply, spaced apart longitudinal and lateral tear straps interspersed with the plies of the base panel.

A method of making a pressure bulkhead assembly of an aircraft includes determining an optimized position of splice angles such that splice surfaces of the splice angles will form a circumferential splice surface of the pressure bulkhead assembly with an optimized shape. The method further includes performing a virtual fit between the plurality of splice angles, at the optimized position, and an aft pressure bulkhead. The method also includes determining splice-angle-hole positions of splice-angle holes to be drilled in each one of the splice angles such that the splice-angle holes will correspond to aft-pressure-bulkhead holes, pre-drilled in the aft pressure bulkhead. The method further includes drilling the splice-angle holes in each one of the splice angles at the splice-angle-hole positions. The method also includes joining each one of the splice angles with the aft pressure bulkhead such that the splice surfaces form the circumferential splice surface with the optimized shape.

A method of making a pressure bulkhead assembly of an aircraft includes determining an optimized position of splice angles such that splice surfaces of the splice angles will form a circumferential splice surface of the pressure bulkhead assembly with an optimized shape. The method further includes performing a virtual fit between the plurality of splice angles, at the optimized position, and an aft pressure bulkhead. The method also includes determining splice-angle-hole positions of splice-angle holes to be drilled in each one of the splice angles such that the splice-angle holes will correspond to aft-pressure-bulkhead holes, pre-drilled in the aft pressure bulkhead. The method further includes drilling the splice-angle holes in each one of the splice angles at the splice-angle-hole positions. The method also includes joining each one of the splice angles with the aft pressure bulkhead such that the splice surfaces form the circumferential splice surface with the optimized shape.

A method for making a pressure bulkhead assembly of an aircraft includes determining first locations and first orientations of a plurality of first holes, pre-drilled in an aft pressure bulkhead. The method also includes determining a first surface profile of a first interface surface of the aft pressure bulkhead and determining a second surface profile of a second interface surface of each one of a plurality of splice angles. The method also includes determining second locations and second orientations of a plurality of second holes to be drilled in each one of the plurality of splice angles corresponding to the plurality of first holes in the aft pressure bulkhead and drilling the plurality of second holes in each one of the plurality of splice angles at the second locations and second orientations.

A method for making a pressure bulkhead assembly of an aircraft includes determining first locations and first orientations of a plurality of first holes, pre-drilled in an aft pressure bulkhead. The method also includes determining a first surface profile of a first interface surface of the aft pressure bulkhead and determining a second surface profile of a second interface surface of each one of a plurality of splice angles. The method also includes determining second locations and second orientations of a plurality of second holes to be drilled in each one of the plurality of splice angles corresponding to the plurality of first holes in the aft pressure bulkhead and drilling the plurality of second holes in each one of the plurality of splice angles at the second locations and second orientations.

The present disclosure provides a keel beam assembly, an aircraft including the keel beam assembly, and a method of aircraft manufacture using the keel beam assembly. An illustrative keel beam assembly comprises a pair of keel chords extending outside an aircraft fuselage and forming at least part of a lower keel box portion of a keel box. An upper keel box portion of the keel box is coupled to the pair of keel chords and has an aft end engaged with and secured to an aft wheel well bulkhead (AWWB).

The present disclosure provides a keel beam assembly, an aircraft including the keel beam assembly, and a method of aircraft manufacture using the keel beam assembly. An illustrative keel beam assembly comprises a pair of keel chords extending outside an aircraft fuselage and forming at least part of a lower keel box portion of a keel box. An upper keel box portion of the keel box is coupled to the pair of keel chords and has an aft end engaged with and secured to an aft wheel well bulkhead (AWWB).