Abstract: An aircraft casing structure including a shroud surrounding the engine and made up of a plurality of sectors; a plurality of radial arms, each mounted between two adjacent shroud sectors and each having a base; and a plurality of fasteners for fastening the shroud sectors on the bases of the radial arms; the fasteners including a plurality of plates each mounted flush in a respective groove of corresponding shape in a shroud sector, and a set of headed bolts held captive in the plate by a difference of diameter between their shanks and their threads, a set of captive nuts being fastened to the bases to provide a secure connection between the shroud sectors and the radial arms by each nut receiving the thread of a respective captive bolt of the set of headed bolts.

Abstract: The invention proposes a guide arm for guiding at least one element having an elongated shape (20), corresponding to a set of cables and/or pipes. The arm comprises an inner cavity (62) opening on the outside of the arm at each of the ends thereof, and in which the elements having an elongated shape can extend. According to the invention, this structure more particularly comprises: a frame (8) comprising a beam (18) linked to means (30, 36, 44) for holding the elements having an elongated shape on the outside and along the beam, and a cover (54) of which the walls (56, 58) cover the holding means of the frame, and are engaged with the beam, in such a way as to form the inner cavity in which the elements having and elongated shape extend, shock-absorbing means (68) being arranged between the means (30, 36, 44) for holding the elements having an elongated shape (20), and the longitudinal walls (56, 58), in such a way as to reduce and damp the movements of the means for holding in the cavity (62).

Abstract: A casing structure interposed between the engine and the nacelle of an aircraft, the structure including a shroud surrounding the engine having an engine axis and including a stationary portion and a plurality of sectors; a radial arm providing the connection to the nacelle; fasteners for securing the plurality of shroud sectors to one another or to the radial arm; and the fasteners include two series of holes formed in two parallel side walls of the shroud sectors for the purpose of receiving two respective series of bolts, each passing through a corresponding set of orifices of an adjacent shroud sector or of an adjacent radial arm, a hinge arranged between each of the shroud sectors and the stationary portion of the shroud to enable the shroud sectors to be pivoted in individual manner about a common pivot axis perpendicular to the side walls arranged along the engine axis.

Abstract: A casing structure interposed between the engine and the nacelle of an aircraft, the casing structure including a shroud surrounding the engine and including a plurality of sectors; at least one radial arm providing the connection to the nacelle; and a plurality of fasteners for securing the plurality of shroud sectors to one another or to the at least one radial arm; the plurality of fasteners including a plurality of connection tabs, each provided with two parallel series of holes for receiving two respective series of headed bolts, a first series passing through a corresponding set of orifices of one shroud sector, and a second series passing through a corresponding set of orifices of an adjacent shroud sector or an adjacent radial arm.

Abstract: A case structure interposed between the engine and the nacelle of the aircraft is provided. The case structure includes: a ferrule surrounding the engine and including a plurality of segments; at least one radial arm ensuring connection to the nacelle; and a plurality of attachment devices for securing the plurality of ferrule segments together or with at least one radial arm. The plurality of attachment devices includes an articulation device configured for ensuring coupling of the lifted-rotated-pushed type ensuring after disengagement of the ferrule segment, its pivoting about a pivot axis parallel to a longitudinal axis of the engine and then its blocking in a disengagement position.

Abstract: The invention proposes a guide arm for guiding at least one element having an elongated shape (20), corresponding to a set of cables and/or pipes. The arm comprises an inner cavity (62) opening on the outside of the arm at each of the ends thereof, and in which the elements having an elongated shape can extend. According to the invention, this structure more particularly comprises: a frame (8) comprising a beam (18) linked to means (30, 36, 44) for holding the elements having an elongated shape on the outside and along the beam, and a cover (54) of which the walls (56, 58) cover the holding means of the frame, and are engaged with the beam, in such a way as to form the inner cavity in which the elements having and elongated shape extend, shock-absorbing means (68) being arranged between the means (30, 36, 44) for holding the elements having an elongated shape (20), and the longitudinal walls (56, 58), in such a way as to reduce and damp the movements of the means for holding in the cavity (62).

Abstract: A casing structure interposed between the engine and the nacelle of an aircraft, the structure including a shroud surrounding the engine having an engine axis and including a stationary portion and a plurality of sectors; a radial arm providing the connection to the nacelle; fasteners for securing the plurality of shroud sectors to one another or to the radial arm; and the fasteners include two series of holes formed in two parallel side walls of the shroud sectors for the purpose of receiving two respective series of bolts, each passing through a corresponding set of orifices of an adjacent shroud sector or of an adjacent radial arm, a hinge arranged between each of the shroud sectors and the stationary portion of the shroud to enable the shroud sectors to be pivoted in individual manner about a common pivot axis perpendicular to the side walls arranged along the engine axis.

Abstract: A casing structure interposed between the engine and the nacelle of an aircraft, the casing structure including a shroud surrounding the engine and including a plurality of sectors; at least one radial arm providing the connection to the nacelle; and a plurality of fasteners for securing the plurality of shroud sectors to one another or to the at least one radial arm; the plurality of fasteners including a plurality of connection tabs, each provided with two parallel series of holes for receiving two respective series of headed bolts, a first series passing through a corresponding set of orifices of one shroud sector, and a second series passing through a corresponding set of orifices of an adjacent shroud sector or an adjacent radial arm.

Abstract: An aircraft casing structure including a shroud surrounding the engine and made up of a plurality of sectors; a plurality of radial arms, each mounted between two adjacent shroud sectors and each having a base; and a plurality of fasteners for fastening the shroud sectors on the bases of the radial arms; the fasteners including a plurality of plates each mounted flush in a respective groove of corresponding shape in a shroud sector, and a set of headed bolts held captive in the plate by a difference of diameter between their shanks and their threads, a set of captive nuts being fastened to the bases to provide a secure connection between the shroud sectors and the radial arms by each nut receiving the thread of a respective captive bolt of the set of headed bolts.

Abstract: A case structure interposed between the engine and the nacelle of the aircraft including: a ferrule surrounding the engine and comprising a plurality of segments (12A, 12B), at least one radial arm (14) ensuring connection to the nacelle, a plurality of attachment means for securing this plurality of ferrule segments together or with at least one radial arm, the plurality of attachment means including an articulation device (24) configured for ensuring coupling of the lifted-rotated-pushed type ensuring after disengagement of the ferrule segment, its pivoting about a pivot axis parallel to a longitudinal axis of said engine and then its blocking in a disengagement position.