Abstract: A fuselage section may include a structural member and a frame member having a stub frame extending over the structural member. The stub frame may have a web. The fuselage section may include an intercostal extending from a terminal end of the stub frame and having an end flange. The fuselage section may additionally include an adjustable splice fitting having a web, a lower flange, and an end flange being mountable in faying contact with respective ones of the stub frame web, the structural member, and the intercostal end flange.

Abstract: A method and apparatus for Z-direction reinforcement of composite laminates is disclosed. Discrete fibers (25) are pulled through a fiber composite preform (11) in the Z-direction by needles (27) having bars (29) thereon to insert the Z-direction reinforcement (31) into the composite preform (11) from a discrete fiber mat (23) having discrete fibers (25) therein.

Abstract: A method and system for fabricating mandrels which are used as pressure intensifiers for cobonding or consolidation fabrication of composite assemblies. Mandrel molds are created using rapid prototyping, such as stereolithography, generated directly from a virtual model which is created with a processor aided design type program requiring little or no engineering drawings. A curable fluid material is then injected into a mold cavity which defines the mandrel. The mandrel can be applied in a specific process for cobonding cured detailed parts using an uncured element enabling intensified pressure to the joint or fillet area during the bonding process.