A ducted fan turbine engine (2) includes a nacelle (10) and an outer discharge nozzle (8) mounted on an aircraft wing (4) by a pylon (6). The nacelle (10) includes two parts (50 and 52) which are hinged to the pylon (6), and pivotly moveable between an open position and a closed operational position. Each nacelle part contains a bypass air-duct (42). Spaced spigot locators (32) and blade locators (34) are positioned on the forward edge of the discharge nozzle (8), and spigots (38) and blades (40) are correspondingly located round the rear edge of the nacelle parts (50, 52). The locators (32, 34 and 36) and their corresponding spigots (38) and blades (40) are arranged so that on closure of the nacelle parts (50, 52) they engage one another and transmit the flight loads through the nacelle (10).