Which risk significantly increases when a hydraulic actuator in a critical aircraft flight control surface experiences internal leakage?

💡 Explanation

When a hydraulic actuator has internal leakage, reduced damping occurs because fluid bypasses the working piston, drastically reducing the ability to withstand changes in speed, pressure and position, which increase bandwidth of control loop. This leads to oscillations resulting in poor control. Therefore reduction in the bandwidth increases the risk for the aircraft, rather than fuel usage, structual damage or corrosion effects that require changes to other failure mechanisms.

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