In this paper, fatigue and damage tolerance of typical circumferential splice structure of aircraft fuselage are studied through fatigue and damage tolerance tests. In the process of the fatigue test of the circumferential splice structure, there is no problem of multi-part damage in the stringer joint. In the process of damage tolerance test, the circumferential splice structure connection shows a low crack propagation rate, which is expected to meet the requirements of repeated inspection in aircraft service. In the residual strength test, the residual strength requirements of two-bay cracks are satisfied. At the same time, the crack propagation life error is less than 35%, which verifies the design configuration of typical circumferential splice structure of aircraft fuselage and the validity of the analysis method. The configuration, analysis method and test method of fuselage circumferential splice structure proposed in this paper can be used to guide the subsequent design and analysis of fuselage circumferential splice structure.