The purpose of this study was to test the fatigue crack growth analysis and the aged aircraft wing structure was carried out to assess the damage tolerance of the long-term operation of aircraft in accordance with the operating period. For this purpose, the algorithm developed in the previous research is based on the fatigue crack propagation analysis of fatigue critical locations of the wing structure using the calculated fatigue stress spectrum and commercial code NASGRO. In addition, the validity of the fatigue stress spectrum and crack propagation analysis method was confirmed through comparison with previous data. The fatigue crack propagation test using the above fatigue stress spectrum was performed on test specimens taken from the actual wing structure and the same material and the results were used to evaluate the damage tolerance of the wing structure according to the operation period.