Abstract: The present invention relates to problems of maintenance of elastomeric members. According to the invention, the elastomeric member is provided with at least one elastomeric layer 1 disposed between two rigid strength members 2. In addition, the elastomeric member is provided with graduations 5 located on its visible surface 7, presenting an angle of inclination relative to the rigid strength members 2, thus making it possible to evaluate and monitor propagation of a crack 6 merely by inspecting it visually.

Abstract: A cyclic swashplate device for controlling rotorcraft blade pitch is disclosed for application to rotorcraft swashplates, in particular, in helicopters. A cyclic swashplate device controls the rotorcraft blade pitch. The device (10?), with rotating (10?) and non-rotating (14?) cyclic swashplates is designed in such a way that at least one of the two disks includes a modular link fitting assembly (46, 42) ensuring the links with the disk (12?, 14?) and the pitch connecting rods (6) and/or at least one driving device or with the pilot control devices (17) and/or at least one retaining device. Interconnecting fittings are attached rigidly and separately to an annular device, such as one of the rings (31?, 30?) of a bearing (21?) on the corresponding disk (14?, 12?).

Abstract: The present invention relates to problems of maintenance of elastomeric members. According to the invention, the elastomeric member is provided with at least one elastomeric layer 1 disposed between two rigid strength members 2. In addition, the elastomeric member is provided with graduations 5 located on its visible surface 7, presenting an angle of inclination relative to the rigid strength members 2, thus making it possible to evaluate and monitor propagation of a crack 6 merely by inspecting it visually.

Abstract: An energy-absorbing connecting strut comprises a substantially straight rigid body with means of connection to two components which it links, and undergoing tensile/compressive stresses. The body comprising a buckling portion with a calibrated buckling load corresponding to a compressive load threshold, a hollowed portion housing a component absorbing energy by plastic deformation in compression, and a piston moving integrally with a rigid axial end part of the body. The body is configured so that under a compressive load greater than the compressive load threshold, the buckling portion deforms causing axial shortening of the connecting strut and movement of the piston with the rigid part, so that the piston crushes and plastically deforms the energy-absorbing component, limiting the load amplitude. The energy-absorbing strut may be used as a suspension strut of a main gearbox on the structure of a rotary wing aircraft.

Abstract: The device (10′), with rotating (10′) and non-rotating (14′) cyclic stars is designed in such a way that at least one of the two stars includes a modular link fitting assembly (46, 42) ensuring the links with said star (12′, 14′) and the pitch connecting rods (6) and/or at least one driving device or with the pilot control devices (17) and/or at least one retaining device, said interconnecting fittings being attached rigidly and separately to an annular device, such as one of the rings (31′, 30′) of the bearing (21′) on the corresponding star (14′, 12′).

Abstract: An energy-absorbing connecting strut comprises a substantially straight rigid body with means of connection to two components which it links, and undergoing tensile/compressive stresses. The body comprising a buckling portion with a calibrated buckling load corresponding to a compressive load threshold, a hollowed portion housing a component absorbing energy by plastic deformation in compression, and a piston moving integrally with a rigid axial end part of the body. The body is configured so that under a compressive load greater than the compressive load threshold, the buckling portion deforms causing axial shortening of the connecting strut and movement of the piston with the rigid part, so that the piston crushes and plastically deforms the energy-absorbing component, limiting the load amplitude. The energy-absorbing strut may be used as a suspension strut of a main gearbox on the structure of a rotary wing aircraft.

Abstract: The system connects a power supply conductor to an electrical de-icing device of a blade by at least one cable with a first section connected to the power supply conductor by a connector and to a second section with an aerial brace in a flattened half-loop, connected to the de-icing device of the blade by a second connector, installed on the blade, by means of a third rectilinear and flat section, and of a second aerial brace. The first brace, of non-shielded structure, with an elongated part of flattened substantially rectangular transverse section, and with the concavity turned towards retaining and articulation means of a retaining part of the blade to the hub, is connected to the part by an articulation at least pivoting around a substantially parallel axis of pitch of the blade.

Abstract: The folding device comprises a fitting pivoting on a cuff about a folding axis which is offset laterally thanks to two lateral bearings of the fitting journal-mounted about bushings retained in lateral devises of the cuff and which are coaxial about the axis by pegs for centering a maneuvering actuator for maneuvering the fitting and the blade about the folding axis.