Gas turbine engine with variable area fan nozzle and method of operating a variable area fan nozzle

A nacelle assembly (N) for a bypass gas turbine engine includes a variable area fan nozzle (42) having a first fan nacelle section (52) and a second fan nacelle section (54). The variable area fan nozzle (42) is in communication with a fan bypass flow path (40). The first fan nacelle section (52) defines an intermittent trailing edge (60) which defines a multiple of ports (62) and the second fan nacelle section (54) defines a multiple of doors (66). Each of the multiple of doors (66) matches each of the multiple of ports (62) such that a fan nacelle trailing edge (34S) is continuous when the second fan nacelle section (54) is selectively translated to a closed position relative to the first fan nacelle section (52).