A nacelle assembly for a gas turbine engine comprising: a core nacelle defined about an engine centerline axis; a fan nacelle mounted at least partially around said core nacelle to define a fan bypass flow path; a variable area fan nozzle in communication with said fan bypass flow path, said variable area fan nozzle having a first fan nacelle section and a second fan nacelle section, said first fan nacelle section defining an intermittent trailing edge which defines a multiple of ports and said second fan nacelle section defines a multiple of doors, each of said multiple of doors matching each of said multiple of ports such that a fan nacelle trailing edge is continuous when said second fan nacelle section is selectively translated to a closed position relative to said first fan nacelle section; and an actuator system (70A; 70B; 70C) operable to translate said second fan nacelle section relative to said first fan nacelle section to said closed position; characterized in that it further comprises: an interface between said first fan nacelle section and said second fan nacelle section, said interface including a fairing defining an outer aerodynamic surface of the fan bypass flow, and a ring flange of a circular ring portion of said second fan nacelle section, rotationally trapped between said first fan nacelle section and said fairing; said fairing having a radial fairing flange, and said first fan nacelle section having a radial nacelle flange between which said ring flange is slidably located, said fairing further having a slot providing access to or for a component (80; 86; 90) of the actuator system on the second fan nacelle section. a core nacelle defined about an engine centerline axis; a fan nacelle mounted at least partially around said core nacelle to define a fan bypass flow path; a variable area fan nozzle in communication with said fan bypass flow path, said variable area fan nozzle having a first fan nacelle section and a second fan nacelle section, said first fan nacelle section defining an intermittent trailing edge which defines a multiple of ports and said second fan nacelle section defines a multiple of doors, each of said multiple of doors matching each of said multiple of ports such that a fan nacelle trailing edge is continuous when said second fan nacelle section is selectively translated to a closed position relative to said first fan nacelle section; and an actuator system (70A; 70B; 70C) operable to translate said second fan nacelle section relative to said first fan nacelle section to said closed position; characterized in that it further comprises: an interface between said first fan nacelle section and said second fan nacelle section, said interface including a fairing defining an outer aerodynamic surface of the fan bypass flow, and a ring flange of a circular ring portion of said second fan nacelle section, rotationally trapped between said first fan nacelle section and said fairing; said fairing having a radial fairing flange, and said first fan nacelle section having a radial nacelle flange between which said ring flange is slidably located, said fairing further having a slot providing access to or for a component (80; 86; 90) of the actuator system on the second fan nacelle section. an interface between said first fan nacelle section and said second fan nacelle section, said interface including a fairing defining an outer aerodynamic surface of the fan bypass flow, and a ring flange of a circular ring portion of said second fan nacelle section, rotationally trapped between said first fan nacelle section and said fairing; said fairing having a radial fairing flange, and said first fan nacelle section having a radial nacelle flange between which said ring flange is slidably located, said fairing further having a slot providing access to or for a component (80; 86; 90) of the actuator system on the second fan nacelle section.