Actuating system for an aircraft thrust reverser

摘要

A thrust reverser system for a gas turbine aircraft engine has a plurality of fluid pressure-operable actuators (11A, 11B) for operating a thrust reverser (10), the jacks being interconnected by synchronising means. A first valve (53) is operable to connect the actuators to a source of fluid under pressure for deployment of the thrust reverser. At least two of the actuators (11B) are provided respectively with locks (55, 56), at least one of which (55) is releasable by fluid pressure supplied by way of second valve means (54) operable independently of the first valve means (53). The arrangement is such that deployment of the thrust reverser is prevented until the second valve (54) is operated to release the lock (55). <IMAGE>