A bushing assembly for a structure having a first aperture is provided. The bushing assembly includes a first component configured to be received by the first aperture and having a second aperture. A maximum width of the first component defines an outer diameter. The bushing assembly further includes a second component positioned outside of the first aperture and coupled to the first component, the second component having a third aperture extending through the second component. The third aperture is dimensioned so as to be equivalent to the outer diameter of the first component, and the first component and the second component are formed as discrete components of the bushing assembly.

A planetary gear system is provided in one example embodiment and may include a planet gear further comprising a bearing system, the bearing system further comprising an inner bearing assembly comprising a spherical bearing and an outer race; an outer bearing assembly comprising a plurality of cylindrical roller bearings, an inner race, and an outer race; and a race element comprising an inner surface and an outer surface, wherein the outer surface of the race element is the inner race for the outer bearing assembly and the inner surface of the race element is associated with the outer race for the inner bearing assembly.

A sensor bearing unit includes a bearing having a first ring and a second ring, and an impulse ring provided with a target holder, with a target mounted on the target holder, and with a sleeve secured to the first ring. The target holder having a mounting portion secured to the first ring of the bearing. The target holder has at least anti-rotation feature axially spaced apart from a free end of the mounting portion and cooperating with a complementary anti-rotation feature of the first ring so as to prevent angular movement of the impulse ring relative to the first ring. The anti-rotation feature of the target holder extends into the complementary anti-rotation feature of the first ring.

An aircraft seat may include a backrest and a seat pan coupled to the backrest. The backrest may include a plurality of backrest panels. A set of backrest panels of the plurality of backrest panels may be coupled via a coil hinge. The coil hinge may include a first plurality of holes formed in a first backrest panel of the set of backrest panels. The coil hinge may include a second plurality of holes formed in a second backrest panel of the set of backrest panels. The coil hinge may include a coil spring wound through the first plurality of holes and the second plurality of holes. The first backrest panel and the second backrest panel may be configured to rotate about an axis through the coil hinge when the seat pan and the backrest actuate between a stowed position and a deployed position.

A gearbox including an angular contact ball bearing comprising a first row of balls provided with a plurality of balls, a second row of balls provided with another plurality of balls, at least one inner ring and at least one outer ring. According to the invention, in a degraded operating mode of the bearing, the first row of balls is configured to transmit at least one first axial force oriented along a first axis and at least one second axial force oriented along a second axis opposite the first axis, the second row of balls transmitting no axial force.

A method of forming a bearing cage is generally disclosed herein. The method includes (i) forming a bearing cage from either titanium or a titanium alloy; and (ii) applying a plasma-nitriding treatment to at least one surface of the bearing cage to form a compound layer of titanium nitride including TiN and Ti.sub.2N on an outer region of the at least one surface. Step (ii) further forms a diffusion zone adjacent to the outer region, in one aspect. A surface hardness of the bearing cage that is treated by the plasma-nitriding step is at least 1000 HV. The bearing cage is configured to be used in a turbofan, turboprop, or turboshaft engine or in a helicopter gearbox, in one aspect.

A friction bearing of a planetary gearbox, has first and second rotatably connected components. Oil adjacent an oil feed pocket of the first component is directed into the bearing clearance between the components. The oil is directed into the pocket by a first line that opens into the pocket. The profile of the line conjointly with the radial direction of the bearing clearance encloses an angle to direct the oil from the line into the oil feed pocket, the angle being approximately 5°-60° to the radial direction of the bearing clearance and in the main rotation direction of the second component in relation to the first component, or at an angle of approximately 5°-20° to the radial direction of the bearing clearance and in the circumferential direction of the bearing clearance and counter to the main rotation direction of the second component to the first component.

An integrated lubrication system and an engine that includes the integrated lubrication system. The system has a first and a second lubrication supply line and one or more spray bars. The first lubrication supply line extends radially inward toward a central axis of the engine, has a first plurality of jet outlets, and is configured to deliver a lubrication fluid to a first location on one or more engine components. The second lubrication supply line extends parallel to the central axis, has a second plurality of jet outlets, and is configured to deliver the lubrication fluid to a second location on the one or more engine components. The first lubrication supply line is configured to lubricate the one or more engine components in a first engine power condition and the second lubrication supply line is configured to lubricate the one or more engine components in a second engine power condition.

An elastomeric bearing assembly has a housing, a centrifugal force bearing axially captured relative to the housing, and a sliding cap disposed between the housing and the centrifugal force bearing.

A connecting assembly for connecting two structures of an aircraft, the connecting assembly including a central element featuring a through-hole, preferably a bore, configured to make a connection with one of the two structures by virtue of a fastener element including a shank inserted into the through-hole. The connecting assembly further includes a plurality of shock-absorbing elements made from a deformable material. Each of the shock-absorbing elements are, on the one hand, secured to the central element and, on the other hand, configured to bear against a surface of the other of the two structures. An aircraft part includes such a connecting assembly.