Patent ID: 11884380
Assignee: THE BOEING COMPANY
Field: Transport (Mechanical engineering)
Classification: CPC B  Y | IPC B

Claim 2:
3. The method of claim 1, wherein the control surface actuator is one of a plurality of control surface actuators of the flight control surface actuation system; wherein each control surface actuator of the plurality of control surface actuators is configured to be operatively coupled to a respective segment end of the corresponding control surface segment of the one or more control surface segments and is configured to transition the respective segment end among a plurality of segment end positions defined between and including a stowed position and a deployed position; wherein the respective segment end is one of a first segment end of the corresponding control surface segment or a second segment end of the corresponding control surface segment that is opposite the first segment end of the corresponding control surface segment; and wherein the skew lanyard is configured to be operatively coupled to one or both of the first segment end and the second segment end of each control surface segment of the skew lanyard subset.