Patent ID: 11897611
Assignee: THE BOEING COMPANY
Field: Transport (Mechanical engineering)
Classification: CPC B | IPC B

Claim 19:
20. A method comprising:
determining an engine of an aircraft has failed, wherein failure of the engine causes a reduction in hydraulic power in an aircraft hydraulic system, the aircraft including:
a wing;
a flap coupled to the wing, the flap moveable between a stowed position and a deployed position; and
a flap actuator coupled to the wing to move the flap relative to a trailing edge of the wing, the flap actuator including an integrated hydraulic powered actuator and electric powered actuator, the flap actuator operable in a hydraulic powered mode in which the hydraulic powered actuator is activated to move the flap, an electric powered mode in which the electric powered actuator is activated to move the flap, and a hybrid mode in which the hydraulic powered actuator and the electric powered actuator are activated simultaneously to move the flap, wherein the flap actuator is a rotary actuator including a crank arm, the crank arm coupled to the flap via a linkage assembly, and wherein the wing includes a support bracket, the hydraulic powered actuator and the electric powered actuator disposed on opposite sides of the support bracket; and
in response to determining the engine has failed, operating the flap actuator in the hybrid mode in which the hydraulic powered actuator and the electric powered actuator are activated simultaneously to move the flap.