One of the main problems of aeronautical structures is the onset and growth of defects due to fatigue loading. This phenomenon is accentuated in areas of stress concentration, for example in the connection of components, such as the riveted joints of fuselage panels. Several geometric configurations can be used in riveted joints of fuselage panels. This work is focused on one geometry, a single-lap splice with three rivets rows and one rivet column. A three-dimensional stress analysis using the finite element method was carried out in order to analyze the load transfer as a function of crack geometry and length, and to determine the stress intensity factors for one or two cracks emanating from the edge of the hole located at the critical cross section.