Patent ID: 8549834
Filing Date: 2013-10-08
Classification: F02K

Abstract:
1. 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 defines 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 match each of said multiple of ports such that a fan nacelle trailing edge is continuous when said second fan nacelle section is in a closed position relative to said first fan nacelle section; and an actuator operable to move said variable area fan nozzle between the closed position and an open position, said actuator including an actuator input engaging a mating actuator receiver, at least one of said actuator input and said actuator receiver extending through an access slot in a circumferential fairing.