Spliced laminate for aircraft fuselage

A laminated panel comprising at least:

• (a) a first aluminum alloy layer having a thickness of less than about 1 mm and comprising a first section, a second section generally coplanar with the first section and a first splice line between the first and second sections;
• (b) a second aluminum alloy layer having a thickness of less than about 1 mm and comprising a first section, a second section generally coplanar with the first section and a second splice line between the first and second sections, the second splice line being generally parallel to the first splice line and spaced laterally therefrom by at least several centimeters;
• and
• (c) an adhesive layer between the first and second aluminum alloy layers, said adhesive layer comprising a synthetic polymer reinforced with fibers comprising a material selected from the group consisting of glass, E-glass, R-glass, S2-glass, aramids, poly-paraphenyleneterephthalamide and carbon.