The majority of service failures in aircraft components occur by fatigue. In the present paper, the fatigue analysis is carried on the aircraft wheel hub at radial load conditions on magnesium alloy in the finite element environment. The radial fatigue test conditions are applied to aircraft wheel in Finite element software and fatigue analysis is done. The fatigue life, von-Misses stress, deformation and safety factor of wheel hub are obtained for each load condition. The process is repeated at various fatigue load conditions on Mg alloy aircraft wheel. The combined steady and variable stress diagram is plotted using mean stress correction theory. The von-Misses stress and deformations are increased with fatigue load, and the safety factor decreases with increasing of fatigue load. The fatigue life is decreased with increasing of fatigue load. The maximum stresses are developed at wheel hub inner diameter.