Patent ID: 8353479

Claim:
An arrangement, comprising: two fuselage sections of an aircraft and a connecting structure for connecting fuselage skins by forming a transverse seam, the connecting structure comprising: a transverse splicing plate which bears on edge regions of the fuselage skins being positioned adjacent to each other for connecting of the same along the transverse seam and which connects the same, an annular frame element or annular frame element segment extending along the abutting joint, the annular frame element being connected with the transverse splicing plate on the inner side of the transverse splicing plate by means of plurality of cleats, a plurality of stringers which are extending along each other and being positioned along the abutting joint side by side, each of which are connected to the same on the inner side of the fuselage skins respectively, a coupling element comprising a base flange the end portions of which lying opposed to each other are connecting sections of stringers which are facing each other respectively and which are connected to a fuselage skin, and with a frame element flange which is connected with the annular frame element, wherein the base flange of the coupling element is extending between the transverse splicing plate and annular frame element or annular frame element and transverse thereto, so that the end sections thereof are connecting two stringers which are connected to two different fuselage skins, respectively.