What is the order of control loss during a stall or spin?

Understanding the order of control loss during a stall or spin is crucial for managing the aircraft effectively in critical situations. In a stall, as the angle of attack exceeds the critical limit, airflow begins to separate from the wing, significantly affecting the ailerons first. This is because ailerons rely on differential lift to control roll, and with the wing stalled, their effectiveness diminishes rapidly.

Following the loss of control over ailerons, the effectiveness of the elevators is compromised. The elevator’s ability to control pitch is also impaired due to the disrupted airflow over the tail surfaces. The loss of elevator control can lead to an inability to maintain or recover from the nose-down attitude that can result from a stall or during recovery from a spin.

The rudder typically maintains some effectiveness until the stall has progressed further, but it is influenced by the overall dynamics of the aircraft. While it may still function somewhat, the significant loss of control authority generally occurs after the ailerons and elevators have become ineffective.

This order of control loss is essential for pilots to understand, as it informs their recovery techniques. Recognizing that ailerons will fail first can help highlight the necessity of prompt recovery measures, specifically addressing the need to reduce the angle of attack