FIELD: engines and pumps.
SUBSTANCE: invention relates to aircraft engineering, particularly, to turbojet nacelles. Aircraft nacelle comprises rear assembly (1) with fusiform inner structure (11) with one downstream part (15) and one upstream part (13) each being arranged to displace between working position whereat said [arts are interconnected and servicing position whereat these are separated. Downstream part can axially displace at opening of at least one flap. Both parts are provided with engaging connectors. One of said parts is equipped with swivels (131, 151) with at least one range of displacement that allows smooth control and appropriate operation on given part. Each said part (13, 15) can displace to servicing position independently.
EFFECT: uniform load at the structure, ease of access to engine at servicing.
16 cl, 8 dwg
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