| 摘要 |
<p>The invention relates to an actuator (18) for an aircraft turbojet engine nacelle (10), which actuator is interposed between a fixed forward part (12) of the nacelle (10) and a mobile rear part (16) of the nacelle (10), characterized in that the actuator (18) comprises a main arm (24a) and a secondary actuating arm (24b) which extends axially from a rear portion suited to being connected to the mobile rear part (16) of the nacelle (10) as far as a front portion secured to a main nut (26a) screwed onto an endless screw (20), the secondary actuating arm (24b) being designed to lessen the negative effect of failure of the main arm (24a).</p> |
