Patent ID: 8302909

Claim:
An aircraft fuselage comprising a circumferential joint of at least two sections, each section comprising: a skin, and at least one stiffener element, each stiffener element: substantially facing another stiffener element at the joint, comprising two stiffener webs, comprising two stiffener flanges, said two stiffener webs and two stiffener flanges determining, with the skin, a closed cross section, in which fuselage the facing stiffener elements are assembled by means of a splice, wherein the facing stiffener elements and the splice are made of composite material, wherein the splice is associated with a single pair of the facing stiffener elements, and the splice: comprises two splice webs, comprises two separate splice flanges, said separate splice flanges each comprising a bearing surface in contact with a stiffener flange of each facing stiffener element, is fastened to the skins and to the pair of facing stiffener elements by means of working fasteners positioned only on the separate splice flanges, and wherein each stiffener element comprises a head between the two stiffener webs determining an omega shaped stiffener cross section.