Abstract: An automatic identification device is provided on a surface of a nacelle of an aircraft, the device containing at least one element of information allowing access to a base of technical resources relating to the nacelle.

Abstract: A nacelle for a turban engine includes an air intake structure and a central structure. The central structure has a casing intended to surround a fan and an external structure. The air intake structure has at least one internal panel attached to the central structure via the casing and therewith forming a fixed structure and at least one longitudinal external panel attached removably to the fixed structure and incorporating an air intake lip. The external panel is moveable between an operating position and a maintenance position in which the external panel is separated from the external structure of the central section and the air intake lip is separated from the internal panel of the air intake structure.

Abstract: The present invention relates to a nacelle (1) for a turbojet engine comprising an air intake structure (4) capable of ducting a flow of air towards a fan and a central structure (5) intended to surround the said fan and to which the air intake structure is attached, the central structure comprising a casing (9) intended to surround the fan and an external structure (13), characterized in that the air intake structure comprises, on the one hand, at least one internal panel (41) attached to the central structure via the casing and therewith forming a fixed structure and, on the other hand, at least one longitudinal external panel (40) attached removably to the fixed structure and incorporating an air intake lip (4a), the said external panel being removable between an operating position in which the external panel is aerodynamically continuous with the external structure of the central section and the air intake lip provides aerodynamic continuity with the internal panel of the air intake structure, and a maint