FIELD: transport.
SUBSTANCE: invention relates to aircraft engineering, namely, to turbojet aircraft nacelle. Nacelle rear assembly comprise cowl, spindle-shaped inner element with its lower section 15 making O-like channel to slide axially between work position whereat said it shuts off turbojet engine gas generator and servicing position located downstream of said work position. Said section 15 may slide unobstructed relative to gas generator 3. Note here that aforesaid inner element comprises upper section 13 to be separated from lower section 15 and has, at least, two flaps 13a, 13b to open outward.
EFFECT: easier access to turbojet.
11 cl, 12 dwg
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