A flight control surface actuation system for operating a flight control surface of a wing of a vehicle, the flight control surface comprising one or more control surface segments, and the flight control surface actuation system comprising: a control surface actuator operatively coupleable to a corresponding control surface segment of the one or more control surface segments and configured to transition the corresponding control surface segment among a plurality of segment configurations defined between and including a retracted configuration and an extended configuration; and a skew detection system configured to detect a skew condition in the flight control surface; wherein the skew detection system is configured to generate a skew detection signal that at least partially represents the skew condition of a flight control surface; wherein the skew detection system comprises: a skew lanyard operatively coupleable to each control surface segment of a skew lanyard subset of the one or more control surface segments; and a detection mechanism assembly configured to detect a lanyard displacement of the skew lanyard relative to a nominal configuration of the skew lanyard and to generate a lanyard displacement signal that at least partially represents the lanyard displacement; wherein the DMA includes an analog position sensor for detecting the lanyard displacement; wherein the skew detection signal includes the lanyard displacement signal; wherein the DMA is configured such that the lanyard displacement signal indicates that the lanyard displacement is any of a continuous plurality of values; wherein the analog position sensor is configured to generate the lanyard displacement signal, and further comprising a controller configured to generate a skew condition signal that represents a presence of the skew condition in the flight control surface and a magnitude of the skew condition in the flight control surface. a control surface actuator operatively coupleable to a corresponding control surface segment of the one or more control surface segments and configured to transition the corresponding control surface segment among a plurality of segment configurations defined between and including a retracted configuration and an extended configuration; and a skew detection system configured to detect a skew condition in the flight control surface; wherein the skew detection system is configured to generate a skew detection signal that at least partially represents the skew condition of a flight control surface; wherein the skew detection system comprises: a skew lanyard operatively coupleable to each control surface segment of a skew lanyard subset of the one or more control surface segments; and a detection mechanism assembly configured to detect a lanyard displacement of the skew lanyard relative to a nominal configuration of the skew lanyard and to generate a lanyard displacement signal that at least partially represents the lanyard displacement; wherein the DMA includes an analog position sensor for detecting the lanyard displacement; wherein the skew detection signal includes the lanyard displacement signal; wherein the DMA is configured such that the lanyard displacement signal indicates that the lanyard displacement is any of a continuous plurality of values; wherein the analog position sensor is configured to generate the lanyard displacement signal, and further comprising a controller configured to generate a skew condition signal that represents a presence of the skew condition in the flight control surface and a magnitude of the skew condition in the flight control surface. a skew lanyard operatively coupleable to each control surface segment of a skew lanyard subset of the one or more control surface segments; and a detection mechanism assembly configured to detect a lanyard displacement of the skew lanyard relative to a nominal configuration of the skew lanyard and to generate a lanyard displacement signal that at least partially represents the lanyard displacement; wherein the DMA includes an analog position sensor for detecting the lanyard displacement; wherein the skew detection signal includes the lanyard displacement signal; wherein the DMA is configured such that the lanyard displacement signal indicates that the lanyard displacement is any of a continuous plurality of values; wherein the analog position sensor is configured to generate the lanyard displacement signal, and further comprising a controller configured to generate a skew condition signal that represents a presence of the skew condition in the flight control surface and a magnitude of the skew condition in the flight control surface.