A cover assembly includes a ring. The ring has a bore with an eccentric inner geometry. The cover assembly includes a cap. The cap has an eccentric outer geometry. The cap is configured to fit within the bore of the ring. In a concentric position, the eccentric outer geometry of the cap and the eccentric inner geometry of the ring are configured to be offset. In an eccentric position, the eccentric outer geometry of the cap is configured to force the eccentric inner geometry of the ring outward.

A device for assembling a sliding bearing, in particular a spherical bearing, which has an inner ring and a divided outer ring, the device including a clamping ring provided for receiving the outer ring, the inner diameter of the clamping ring corresponding at most to the outer diameter of the outer ring in the maximally compressed state thereof. To shrink the clamping ring onto the outer ring and to detach the clamping ring from the outer ring, a temperature control device, in particular in the form of an induction-heating device, which heats the clamping ring, is provided.

A resin material 16 for a sliding member contains a synthetic resin 18, graphite particles 20 dispersed in the synthetic resin 18, and a hard material 24. The synthetic resin 18 contains 5% or more by volume and 30% or less by volume of polytetrafluoroethylene (PTFE) 22. The graphite particles 20 have an average particle diameter of 0.5 μm or more and 5.0 μm or less and have a content of 1% or more by volume and 15% or less by volume in the synthetic resin 18.

An aircraft structural joint comprising a first structural component provided with an attachment hole that is configured to receive an corresponding attachment fastener provided by a second structural component; a curable composite bush compressed and cured between an outer diameter of the attachment fastener and the attachment hole when the first component is mounted to the second component, wherein the curable composite bush, when cured, prevents radial displacement of the attachment fastener within the attachment hole.

A self-lubricating bearing includes an outer ring having a concave inside surface that defines an interior area of the outer ring. The bearing includes an inner member having a convex exterior surface. The inner member is disposed in the interior area, and the convex exterior surface has a physical vapor deposition coating thereon. A self-lubricating liner is bonded to the concave inside surface. The outer ring is made from a first metallic alloy, and the inner member made from a second metallic alloy.

A mechanical part configured to be placed under torque. The mechanical part includes an inner tube having, a corrugated web, and an outer shell. The inner tube has an outer tube circumference, a tube axial direction, and a tube length. The corrugated web has a plurality of peaks and a plurality of troughs, a height measured as a difference between one of the peaks and one of the troughs, and a web length perpendicular to the height and in the tube axial direction. The outer shell has an inner shell circumference, an outer shell circumference, and a shell length. The plurality of troughs is affixed to the outer circumference of the inner tube. The plurality of peaks is affixed to the inner shell circumference of the outer shell. The web length is aligned with the tube length and the shell length.

An aircraft structural joint with a first structural component provided with an attachment hole that is configured to receive an corresponding attachment fastener provided by a second structural component; a curable composite bush compressed and cured between an outer diameter of the attachment fastener and the attachment hole when the first component is mounted to the second component, wherein the curable composite bush, when cured, prevents radial displacement of the attachment fastener within the attachment hole.

A bearing support includes at least one sliding bearing defined by the bearing support and/or at least one rolling-element bearing having an outer raceway defined by the bearing support. The bearing support is formed from a fiber-plastic composite and includes an integrally formed sliding surface of the sliding bearing and/or an integrally formed raceway for rolling elements of the rolling-element bearing, and the fiber-plastic composite includes a matrix into which spatially oriented sliding fibers, for example, PTFE fibers, are embedded in a region of the sliding surface of the sliding bearing and/or a region of the raceway of the rolling-element bearing.

An antifriction bearing cage is disclosed including cage pockets that are used for guiding rolling elements, in particular balls, and are formed by two lateral rings having a common axis of symmetry (R) and by webs interconnecting the lateral rings. The lateral rings are designed as single pieces along with the webs and contain a fabric. The fabric is composed of at least two types of different fibers which impart highly anisotropic properties to the fabric.

A component of a rolling-element bearing, such as a bearing inner ring having an inner ring flange, a bearing outer ring having an outer ring flange or a rolling element having an end surface, includes a solid slide layer having a lower coefficient of friction than a material to which the slide layer is attached which slide layer reduces frictional contact between the component and another component against which the slide layer slides during bearing operation.