A dynamic bearing for an aircraft landing gear. The bearing comprises a lug, a shaft comprising a first material, and a bearing surface comprising a second material that is softer than the first material. The bearing surface defines a bore and is arranged to support the shaft when the shaft is movably housed within the bore in use. The bearing surface is defined by the lug or a coating applied to the lug.

A method for producing a sliding element, providing a first band-shaped or strip-shaped metallic material of a thickness, wherein the first material has apertures which extend over the entire thickness of the first material, providing a second band-shaped or strip-shaped metallic material of a thickness, areally connecting the first band-shaped or strip-shaped material to the second band-shaped or strip-shaped material by laser roll cladding such that a band-shaped or strip-shaped composite material is formed, which has a longitudinal direction X and a transverse direction, and has a thickness oriented perpendicularly with respect to the longitudinal and transverse directions. The method further includes bending the composite material about an axis oriented parallel to the transverse direction of the composite material, such that a sliding element is formed which has cutouts on its running surface that are formed at least partially from the apertures of the first material.

A half thrust bearing for a crankshaft of an internal combustion engine is formed of a back metal layer and a bearing alloy layer to have a slide surface and two thrust reliefs. Each thrust relieve includes a first region, where the back metal layer is exposed, on a circumferential end surface side, and a second region and a third region, where the bearing alloy layer is exposed while the slide surface includes a fourth region. A circumferential end region consists of the first and second regions. The bearing alloy layer includes a uniform thickness portion, and a decreased thickness portion adjacent to an inner-diameter-side end surface in a cross-section of the second region and includes a uniform thickness portion and an increased thickness portion adjacent to the inner-diameter-side surface in cross-sections of the third and fourth regions.

A half thrust bearing for a crankshaft of an internal combustion engine is formed of a back metal layer and a bearing alloy layer to have a slide surface and two thrust reliefs. Each thrust relieve includes a first region, where the back metal layer is exposed, on a circumferential end surface side, and a second region, where the bearing alloy layer is exposed, on the slide surface side while the slide surface includes two third regions adjacent to the second region, and a fourth region between the two third regions. A circumferential end region consists of the first, second and third regions. In the second region and the third regions, the bearing alloy layer includes a uniform thickness portion at a radial center, and a decreased thickness portion adjacent to an inner-diameter-side end surface.

A bearing bush 1 includes a cylindrical portion 6 having a cylindrical inner surface 2 and a cylindrical outer surface 3; a cylindrical portion 12 having a cylindrical inner surface 7 and a cylindrical outer surface 8; a curved bulged portion 17 interposed between the cylindrical portions 6 and 12 in an axial direction X and having a curved concave inner surface 15 and a curved convex outer surface 16; an annular ring-shaped collar portion 19 provided at another end portion 18 in the axial direction X of the cylindrical portion 6 in such a manner as to extend in an outward direction A in a radial direction Y; a slit 21 which splits the cylindrical portions 6 and 12, the curved bulged portion 17, and the annular ring-shaped collar portion 19; and a plurality of inclined plate portions 23 which are formed integrally on an outer peripheral edge 22 of the annular ring-shaped collar portion 19 and extend in the outward direction A in the radial direction Y from the outer peripheral edge 22 in an inclined manner.

A sliding bearing element with a first layer having a radially inner surface includes a measuring device arranged on the radially inner surface of the first layer. The measuring device includes, in the order indicated, a first electrical insulating layer, a sensor layer and a second electrical insulating layer. A sliding layer is arranged on the second electrical insulating layer.

A sliding member for a journal bearing is provided. A sliding layer includes fibrous particles dispersed in a synthetic resin, and has a sliding surface side region and an interface side region. The particles have an average particle size D.sub.sur, axi and D.sub.sur, cir respectively in an axial and circumferential cross-section in the sliding surface side region, and D.sub.int, axi and D.sub.int, cir respectively in axial and circumferential cross-sections in the interface side region. D.sub.sur, axi and D.sub.int, cir are 5-30 μm, and D.sub.sur, cir and D.sub.int, axi are 5 to 20% of respectively D.sub.sur, axi and D.sub.int, cir. A dispersion index of the particles having the major axis length of 20 μm or longer is 5 or more, both in the sliding surface side region in view of the axial cross-section and in the interface side region in view of the circumferential cross-section.

A sliding member includes a back-metal layer including an Fe alloy and a sliding layer including a copper alloy including 0.5 to 12 mass % of Sn and the balance of Cu and inevitable impurities. The sliding layer has a cross-sectional structure perpendicular to a sliding surface of the sliding layer. The cross-sectional structure includes first copper alloy grains that are in contact with a bonding surface of the back-metal layer and second copper alloy grains that are not in contact with the bonding surface. The first copper alloy grains has an average grain size D1 and the second copper alloy grains has an average grain size D2. D1 and D2 satisfy the following relations: D1 is 30 to 80 μm; and D1/D2=0.1 to 0.3.

Gearboxes for aircraft gas turbine engines, in particular arrangements for journal bearings such gearboxes, and related methods of operating such gearboxes and gas turbine engines. A gearbox for an aircraft gas turbine engine includes: a sun gear; a plurality of planet gears surrounding and engaged with the sun gear; and a ring gear surrounding and engaged with the plurality of planet gears, each of the plurality of planet gears being rotatably mounted around a pin of a planet gear carrier with a journal bearing having an internal sliding surface on the planet gear and an external sliding surface on the pin.

A method of manufacturing a strip for a bearing may comprise roll-bonding a bearing layer comprising a tin-free aluminium alloy directly to a base layer to form a bimetal and heat-treating the bimetal at a temperature below a recrystallization initiation temperature of the aluminium alloy. A strip for a bearing manufactured using the method, and a bearing having a strip manufactured using the method, are also provided.