These examples are based on the lower wing structure shown in Figure 1.3.11.  The structure is comprised of multiple skin and stringer elements.  The skin panels 1-5 are considered the major load paths.  At each spanwise splice, a major splicing stringer is located and the construction is such that the load paths are independent, i.e., no common manufacturing tie exists between the skin panels. 

The design service life is assumed to be 40,000 hours for these examples.

Figure 1.3.11.  Structural Example of Lower Wing Skin