Actuation of a turbofan engine bifurcation to change an effective nozzle exit area

A turbine engine comprising:

• a spool supporting a turbine;
• a turbofan arranged upstream from the core nacelle and coupled to the spool;
• a fan nacelle surrounding the turbofan and providing a bypass flow path between the fan and core nacelles having a nozzle exit area;
• a flow control device including a surface in the bypass flow path movable between closed and open positions to effectively change the nozzle exit area;
• and
• a bifurcation extending between the core and fan nacelles to support the core nacelle relative to the fan nacelle, the surface supported on the bifurcation, wherein the bifurcation supports opposing surfaces on opposing sides of the bifurcation, each of the opposing surfaces having leading and trailing edges, each opposing surface movable about a pivot near the trailing edge between the closed and open positions in a generally circumferential direction.