In order to simulate the real flight load of aircraft structure, the fatigue test of the movable wings (including leading-edge flap, flaperon, stabilator) of a certain aircraft gives a new requirement. That is, the movable wing is rotating while the fatigue load is applying on it. This is a new challenge to the method of aircraft structure fatigue test. Aiming at this problem, this paper proposes a movable wing fatigue test method that can simulate the loading state of the movable wing in its rotating process, and solves the problem of coordinated loading between wing rotation angle and fatigue loading. The method successfully completed fatigue tests of aircraft leading-edge flaps, flaperon, and stabilator of a certain type aircraft. The test results show that, fatigue damages of key parts on movable wings in fatigue tests are basically the same fatigue damages during service.