This paper deals with the study and comparison of the dynamic response of aircraft with passive and active landing gears due to runway irregularities while the aircraft is taxying. This paper develops a detailed full aircraft mathematical vibration model to describe an active landing gear system. The derived dynamic equations are used to analyze the active landing gear system using proportional integral derivative (PID) controllers. The performance of this system is compared with the passive landing gear system by numerical simulations. The active landing gear system is able to increase the ride comfort and good track holding by reducing the fuselage acceleration, vertical fuselage displacement caused by landing and runway excitations.