Abstract: A method for operating a turbofan engine assembly is provided. The turbofan engine assembly includes a core cowl which circumscribes the core gas turbine engine, a nacelle positioned radially outward from the core cowl, a fan nozzle duct having an area defined between the core cowl and a portion of the nacelle, a first cowl and a second cowl that define a portion of the nacelle wherein the second cowl is repositionable with respect to the first cowl, and a thrust reverser assembly wherein the second cowl surrounds the thrust reverser assembly. The method includes varying an operating speed of the fan assembly from a first operating speed to a second operating speed. The method further includes selectively positioning the second cowl between a first operational position and a second operational position to vary the area of the fan nozzle duct to facilitate improving engine efficiency at the second operating speed.

Abstract: A method for operating a gas turbine engine assembly for an aircraft that includes a wing, wherein the gas turbine engine includes a core gas turbine engine and a fan coupled to the core gas turbine engine, the gas turbine engine assembly extends upstream from the wing and includes a first cowl and a second cowl that is repositionable with respect to the first cowl. The method includes selectively positioning the second cowl in a first operational position such that airflow is channeled from the gas turbine engine across a surface of the wing to facilitate increasing lift, and selectively positioning the second cowl in a second operational position such that the airflow is channeled from the gas turbine engine to effect reverse thrust.