An aircraft, comprising: a refueling boom comprising: a refueling boom structure; a hoist configured to be controlled by a hoist actuator; and a boom aerodynamic control surface; and a controller configured to cause the refueling boom to perform operations comprising: lowering, while the hoist is in a second actuator state mode, the refueling boom structure with the hoist, wherein in the second actuator state mode the boom aerodynamic control surface is deactivated and the hoist is in a hoisting mode such that the hoist actuator is configured to control a pitch axis of the refueling boom while a roll axis of the refueling boom is controlled by a damped trail behavior of the refueling boom and, thus, not actively controlled; determining that first transition conditions have been met, wherein the first transition conditions comprise: a boom pitch angle is greater than a first threshold angle; and a hoist cable rate is less than a first threshold rate; switching the hoist from the second actuator state mode to a first actuator state mode, wherein in the first actuator state mode the boom aerodynamic control surface is deactivated and the hoist is in the tension mode such that the pitch and roll axes of refueling boom are controlled through the damped trail behavior of the refueling boom; and activating the boom aerodynamic control surface. a refueling boom comprising: a refueling boom structure; a hoist configured to be controlled by a hoist actuator; and a boom aerodynamic control surface; and a refueling boom structure; a hoist configured to be controlled by a hoist actuator; and a boom aerodynamic control surface; and a controller configured to cause the refueling boom to perform operations comprising: lowering, while the hoist is in a second actuator state mode, the refueling boom structure with the hoist, wherein in the second actuator state mode the boom aerodynamic control surface is deactivated and the hoist is in a hoisting mode such that the hoist actuator is configured to control a pitch axis of the refueling boom while a roll axis of the refueling boom is controlled by a damped trail behavior of the refueling boom and, thus, not actively controlled; determining that first transition conditions have been met, wherein the first transition conditions comprise: a boom pitch angle is greater than a first threshold angle; and a hoist cable rate is less than a first threshold rate; switching the hoist from the second actuator state mode to a first actuator state mode, wherein in the first actuator state mode the boom aerodynamic control surface is deactivated and the hoist is in the tension mode such that the pitch and roll axes of refueling boom are controlled through the damped trail behavior of the refueling boom; and activating the boom aerodynamic control surface. lowering, while the hoist is in a second actuator state mode, the refueling boom structure with the hoist, wherein in the second actuator state mode the boom aerodynamic control surface is deactivated and the hoist is in a hoisting mode such that the hoist actuator is configured to control a pitch axis of the refueling boom while a roll axis of the refueling boom is controlled by a damped trail behavior of the refueling boom and, thus, not actively controlled; determining that first transition conditions have been met, wherein the first transition conditions comprise: a boom pitch angle is greater than a first threshold angle; and a hoist cable rate is less than a first threshold rate; a boom pitch angle is greater than a first threshold angle; and a hoist cable rate is less than a first threshold rate; switching the hoist from the second actuator state mode to a first actuator state mode, wherein in the first actuator state mode the boom aerodynamic control surface is deactivated and the hoist is in the tension mode such that the pitch and roll axes of refueling boom are controlled through the damped trail behavior of the refueling boom; and activating the boom aerodynamic control surface.