An actuator failure or disconnection detection device (20) for an aircraft leading edge slat (6) comprises a base (22) and a biasing assembly (24) mounted to the base (22) and movable relative thereto. The base (22) and biasing assembly (24) are removably mountable between a fixed structure (202) in the aircraft wing and the slat (6) at an actuator location. The device (20) further comprises an indicator (132) for indicating the amount of movement of the biasing assembly (24) in a direction towards the base (22) when the slat (6) is retracted towards the wing leading edge (4). The indicator (122) may be a collar (132) slidably mounted on the device (20).
WING SLAT ACTUATOR DISCONNECTION DETECTION
DETECTION DE DESACCOUPLEMENT D'ACTIONNEUR DE BEC DE BORD D'ATTAQUE
2018-06-22
Patent
Electronic Resource
English