Patent ID: 8732953

Claim:
A method of assembling fuselage or primary structural aircraft rigid panels edge to edge, the method comprising: providing at least a first rigid panel presenting a first rigid panel edge and a second rigid panel presenting a second rigid panel edge; cutting male and female matching elements on the first and second rigid panel edges to be assembled next to each other, wherein the male elements comprise protuberances, and the female elements comprise cavities; forming a first bevel cut on the first rigid panel edge and a second bevel cut on the second rigid panel edge complementary to the first bevel cut before or after the male and female matching elements are cut, wherein the first and second bevel cuts each define a beveled edge of no more than 45 degrees from a plane of the first and second rigid panels; assembling the at least first and second rigid panels edge to edge so that the male protuberances of the first rigid panel are inserted in the matching female cavities of the second rigid panel, and vice-versa.