A gas turbine engine comprising: a core engine defined about an axis; a gear system driven by said core engine; a fan driven by said gear system about said axis; and a nacelle assembly comprising: a core nacelle defined about an axis; a fan nacelle mounted at least partially around said core nacelle, said fan nacelle having a fan variable area nozzle defined about said core nacelle by a multiple of flaps; a flap linkage mounted to each of said multiple of flaps; and an actuator system to vary a fan nozzle exit area defined by said fan variable area nozzle; and a circumferential hinge line defined between said fan variable area nozzle and said fan nacelle, wherein each of said multiple of flaps includes a flap core, said flap core being attached to said flap linkage; a slider track (60U, 60L) mounted to said fan nacelle; a drive ring slidable along said slider track (60U, 60L), and including a flap-ring pivot radially offset from said circumferential hinge line such that said circumferential hinge line is defined radially inboard relative said flap-ring pivot, said flap linkage being mounted to said drive ring said actuator driving said drive ring along said axis to vary a fan nozzle exit area defined by said fan variable area nozzle, wherein said drive ring is divided in a multiple of drive ring segments (42A-42D), each drive ring segment (42A-42D) including a separately movable flap set of a multiple of flaps and an actuator of said actuator system to drive said drive ring segment (42A-42D) along said axis to vary a segment of said fan variable area nozzle. a core engine defined about an axis; a gear system driven by said core engine; a fan driven by said gear system about said axis; and a nacelle assembly comprising: a core nacelle defined about an axis; a fan nacelle mounted at least partially around said core nacelle, said fan nacelle having a fan variable area nozzle defined about said core nacelle by a multiple of flaps; a flap linkage mounted to each of said multiple of flaps; and an actuator system to vary a fan nozzle exit area defined by said fan variable area nozzle; and a circumferential hinge line defined between said fan variable area nozzle and said fan nacelle, wherein each of said multiple of flaps includes a flap core, said flap core being attached to said flap linkage; a core nacelle defined about an axis; a fan nacelle mounted at least partially around said core nacelle, said fan nacelle having a fan variable area nozzle defined about said core nacelle by a multiple of flaps; a flap linkage mounted to each of said multiple of flaps; and an actuator system to vary a fan nozzle exit area defined by said fan variable area nozzle; and a circumferential hinge line defined between said fan variable area nozzle and said fan nacelle, wherein each of said multiple of flaps includes a flap core, said flap core being attached to said flap linkage; a slider track (60U, 60L) mounted to said fan nacelle; a drive ring slidable along said slider track (60U, 60L), and including a flap-ring pivot radially offset from said circumferential hinge line such that said circumferential hinge line is defined radially inboard relative said flap-ring pivot, said flap linkage being mounted to said drive ring said actuator driving said drive ring along said axis to vary a fan nozzle exit area defined by said fan variable area nozzle, wherein said drive ring is divided in a multiple of drive ring segments (42A-42D), each drive ring segment (42A-42D) including a separately movable flap set of a multiple of flaps and an actuator of said actuator system to drive said drive ring segment (42A-42D) along said axis to vary a segment of said fan variable area nozzle.