Abstract: A ducted fan turbine engine includes a nacelle and an outer discharge nozzle mounted on an aircraft wing by a pylon. The nacelle includes to parts which are hinged to the pylon for pivoting movement between an open position and a closed, operational position. Each nacelle part contains a bypass air duct. Spaced spigot locators and blade locators are positioned at the forward edge of the discharge nozzle and spigots and blades are correspondingly located round the rear edge of the nacelle parts. The locators and their corresponding spigots and blades are arranged so that on closure of the nacelle parts they engage one another and transmit the flight loads through the nacelle.

Abstract: A ducted fan turbine engine (2) includes an inner discharge nozzle (18) and an outer discharge nozzle (8) surrounding the inner discharge nozzle. The engine (2) is mounted on an aircraft wing by a pylon. The rear part of this pylon supports rollers which run in guide rails (36) which extend rearwardly along the upper portion of the outer discharge nozzle (8). The outer discharge nozzle (8) is secured in its forward operational position adjacent the engine nacelle by bolting support fittings (38) to the pylon. To remove the remainder of the engine, the support fittings (38) are unbolted from the pylon, a locating device (28) is released from the engine thrust reverser structure, and the outer discharge nozzle (8) and a primary nozzle fairing (22) are rolled rearwardly to a park position. The remainder of the engine can then be removed downwardly from the aircraft.