Abstract: A brief review of recent works on the mechanisms of fatigue crack propagation behavior and their applications to some aircraft Al-alloys, Ti-alloys and high-strength steels in the Institute of Aeronautical Materials is presented.The change of microscopic morphology and mechanisms of FCP at different propagation stages, especially in the initiation stage, are described. A general analytical expression for calculating fatigue threshold values of common metals and alloys is proposed.The ability of each of four current retardation models to predict fatigue life of Ti-6Al-4V alloy under tensile overloading is evaluated. Some modifications of the Willenborg and Maarse models and their applications to the life prediction of Al-and Ti-alloys are investigated. The presented modified Maarse model is recognized to be improved obviously in the life prediction under tensile overloading and spectrum loadings.The effects of microstructures, stress ratios, surface conditions and environments on the fatigue crack propagation behaviors of some aircraft structural materials are discussed.