Patent ID: 8360362

Claim:
A method of assembling an aircraft, comprising: forming a stand-alone floor section having a span extending substantially across the width of the aircraft's fuselage by laminating a first higher density structural core and second lower density structural core between top-layer and bottom layer skins with a septum therebetween, including placing the first structural core next to the top-layer skin, placing the septum beneath the first structural core and placing the second structural core beneath the septum and next to the bottom-layer skin; embedding a hollow tubular mounting structure in at least one of the cores of said floor section; preassembling a subassembly outside of the aircraft by attaching at least one aircraft system component to the floor section; said attaching the at least one aircraft system component includes using an attaching structure to attach the at least one aircraft system component to the mounting structure; moving the subassembly into the fuselage of the aircraft; and installing the subassembly into the fuselage.