Jet nozzle effective area control system for gas turbine engine

A method of controlling an aircraft gas turbine engine having a fan that in operation moves air through both a core airflow path and a bypass airflow path of the gas turbine engine, the core airflow path and the bypass airflow path converging at a jet nozzle of the gas turbine engine, the method comprising:

• detecting, at a controller of the gas turbine engine, a non-cruise operating condition of the gas turbine engine;
• and
• in response to detecting the non-cruise operating condition, repositioning a plurality of overlap jointed split duct panels such that an effective area of the jet nozzle is increased,
• wherein (i) the plurality of overlap jointed split duct panels are configured to be controlled by a command signal from the controller and a command signal from a thrust reverser manual control interface, and (ii) the command signal received from the thrust reverser manual control interface has priority over the command signal received from the controller.