In order to prevent the aircraft from rollover due to excessive deflection of the nosewheel during takeoff and landing, the nosewheel deflection should be reasonably limited according to the taxiing speed. Based on the principle of the rollover phenomenon, we analyzed resultant moments of the aircraft relative to the rollover axis while the nosewheel deflecting, determined nosewheel rolling direction limitation, studied on the relationship between the rolling direction of the nosewheel and the deflection, calculated the deflection angle of the nosewheel at different speeds and the neutral position of the nosewheel while considering the asymmetric slip flow of the propeller, then got the deflection range of the nosewheel during takeoff and landing phase. The limited range of the nosewheel deflection obtained by the calculation results show that the limited range accords with the general characteristics of deflection limitation, which can prevent rollover while retaining the correcting capability of the nosewheel.