Abstract: Aircraft nacelle assemblies include a frame, a cowl coupled to the frame, and a biasing member (including a passive mechanism) coupled between the frame and the cowl. The cowl is configured to move between a closed position and an open position. The passive mechanism is configured to provide a biasing force to the cowl. When the cowl is in or near the closed position, the biasing force coupled with the weight of the cowl results in a first net force that urges the cowl away from the open position, and when the cowl is in or near the open position, the biasing force coupled with the weight of the cowl results in a second net force that urges the cowl away from the closed position.

Abstract: An apparatus and method comprising a fan nozzle sleeve, a plurality of slider mechanisms, and a fan nozzle actuator system. A flow of gases generated by an engine moves through and exits the engine at an aft end of the fan nozzle sleeve. The plurality of slider mechanisms is configured to connect the fan nozzle sleeve to a translating sleeve for a thrust reverser for the engine. The fan nozzle actuator system is configured to activate the plurality of slider mechanisms to move the fan nozzle sleeve in an aft direction to change a direction of the flow of gases exiting the engine at the aft end of the fan nozzle sleeve.

Abstract: An apparatus for mounting an aircraft engine to a wing includes a torque box strut for supporting the engine and a mounting system for attaching the torque box strut to the wing. The mounting system has an aft mounting system for attaching the torque box strut to the wing and that has at least one active aft link for attaching the torque box strut to the wing during normal aircraft operation, and at least one aft link catcher for attaching the torque box strut to the wing upon a failure of one of the at least one active aft link. The mounting system has a forward mounting system for attaching the torque box strut to the wing and that has at least one active forward link for attaching the torque box strut to the wing during normal aircraft operation, and at least one forward link catcher for attaching the torque box strut to the wing upon a failure of one of the at least one active forward link.

Abstract: An apparatus and method comprising a fan nozzle sleeve, a plurality of slider mechanisms, and a fan nozzle actuator system. A flow of gases generated by an engine moves through and exits the engine at an aft end of the fan nozzle sleeve. The plurality of slider mechanisms is configured to connect the fan nozzle sleeve to a translating sleeve for a thrust reverser for the engine. The fan nozzle actuator system is configured to activate the plurality of slider mechanisms to move the fan nozzle sleeve in an aft direction to change a direction of the flow of gases exiting the engine at the aft end of the fan nozzle sleeve.

Abstract: An apparatus for mounting an aircraft engine to a wing includes a torque box strut for supporting the engine and a mounting system for attaching the torque box strut to the wing. The mounting system has an aft mounting system for attaching the torque box strut to the wing and that has at least one active aft link for attaching the torque box strut to the wing during normal aircraft operation, and at least one aft link catcher for attaching the torque box strut to the wing upon a failure of one of the at least one active aft link. The mounting system has a forward mounting system for attaching the torque box strut to the wing and that has at least one active forward link for attaching the torque box strut to the wing during normal aircraft operation, and at least one forward link catcher for attaching the torque box strut to the wing upon a failure of one of the at least one active forward link.

Abstract: An aircraft engine has opposite front and rear ends, extends in a longitudinal direction between the front and rear ends, and defines a longitudinal axis that extends between the front and rear ends. The aircraft engine includes a reference portion, and right and left cowls that extend arcuately at least partially around the longitudinal axis of the aircraft engine. The cowls are operative for covering at least a portion of the reference portion. Each cowl is movably mounted in relation to the reference portion so that the cowls move both radially away from the longitudinal axis and in the longitudinal direction as the cowls are moved from a closed configuration to an open configuration. Further, the cowls move both in the longitudinal direction and radially toward the longitudinal axis as the cowls are moved from the open configuration to the closed configuration.