Wing slat actuator disconnection detection
AssigneeGoodrich Actuation Systems Limited
InventorsMark Hubberstey, Mark Timms
Life of this patent
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Abstract
An actuator failure or disconnection detection device for an aircraft leading edge slat comprises a base and a biasing assembly mounted to the base and movable relative thereto. The base and biasing assembly are removably mountable between a fixed structure in the aircraft wing and the slat at an actuator location. The device further comprises an indicator for indicating the amount of movement of the biasing assembly in a direction towards the base when the slat is retracted towards the wing leading edge. The indicator may be a collar slidably mounted on the device.
Claims4
A method of detecting actuator disconnection or failure in an aircraft leading edge slat system comprising the steps of:
- extending a slat from an aircraft wing leading edge using at least two actuators;
- engaging a biasing assembly between a fixed structure in the aircraft wing and the slat at an actuator location, the biasing assembly biasing the slat in a direction away from the fixed structure;
- retracting the slat against the force of the biasing assembly;
- detecting a skew in the slat induced by the movement of the slat being opposed by the biasing assembly;
- and
- disengaging the biasing assembly between the fixed structure and the slat.
Dependencies are inferred from the claim text.