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In this paper, the FSW process is reviewed, and compared with other joining methods. In particular, the FSW process is considered as a manufacturing process for airframe structures. To this end a lap joint specimen was developed to represent the stiffened panel of an aircraft skin and its associated stiffener. The materials used in this test program were 2024-T3 as the skin and 7075-T6 as the stiffener. The skin and stiffener were joined using FSW.In the test program the static strength of FSW stiffened panel structures fabricated from 2024-T3 and 7075-T6 were compared with values from the reference literature. In addition, 20 fatigue test specimens classified into 5 groups according to the existence of a tool pin hole and the welding sequence. The welding sequences considered were: Single Pass, Double Pass (Type I) and Double Pass (Type II). S-N curves, fatigue crack growth rate data and metallurgical analysis were investigated and presented for the five groups of FSW specimens.