FIELD: transport.
SUBSTANCE: invention relates to aircraft engineering, particularly, to engine nacelles. Aircraft turbojet nacelle lower section 100 comprises outer structure 106, concentric inner structure 109 arranged around turbojet lower part 11 and including upper section 113 relatively small diameter and lower section of relatively small diameter 114 relatively small in diameter. Said inner structure 109 and said outer structure 106 form an airflow annular channel 108. Besides nacelle comprises control system 140 intended for connection of inner structure 109 with turbojet lower part 11 or with hinged strut part. Control system 140 comprises means to coordinate inner structure translation and rotation between working position and servicing position.
EFFECT: access to the whole engine, hence, easier the servicing.
15 cl, 19 dwg
