A pin assembly for insertion into a pin joint of an aircraft landing gear is disclosed. The pin assembly includes a reservoir for storing a lubricating agent and a piston mounted for reciprocal movement within the reservoir, the piston dividing the reservoir into a first chamber and a second chamber. A bi-directional flow path between the first and second chambers via the surface to be lubricated is provided by means of a first bi-directional flow path between the first chamber and the exterior of the pin assembly and a second bi-directional flow path between the second chamber and the exterior of the pin assembly. A pin assembly including an indicator system, and a pin insert in the form of a replaceable cartridge is also disclosed along with associated methods.

A method and apparatus for facilitating the attachment of an internal module in an internal space of an aircraft part is disclosed. The attachment device includes at least one attachment member comprising an attachment shank, a chamber for introducing the attachment member, the chamber including a first orifice through which the attachment shank passes in the installed configuration of the internal module, and a second orifice which serves for the introduction of the attachment member into the chamber from the outside.

A bearing having an electrically conductive sleeve and a self-lubricating liner wherein the electrically conductive sleeve comprises a first portion and a second portion, the first portion and the second portion having respectively an inner surface and an outer surface; the self-lubricating liner extends over the inner surface of the first portion of the electrically conductive sleeve to define a first tubular volume, the first tubular volume having a first diameter and a first longitudinal axis; and the inner surface of the second portion of the electrically conductive sleeve defines a second tubular volume, the second tubular volume having the same diameter and the same longitudinal axis as the first tubular volume.

The invention relates to a hydraulic actuator comprising a cylinder (1) in which a piston (2) secured to a rod (4) is mounted so as to slide in a sealed manner in order to delimit in the cylinder a hydraulic extension chamber (5) and a hydraulic retraction chamber (6) that are connected to respective ports, the hydraulic actuator comprising means for slowing the piston when the piston approaches a retracted position. According to the invention, the slowing means comprise first and second hydraulic lines (7, 8) extending between the extension port and the extension chamber, the first hydraulic line comprising a seat (13) while the piston bears a retractable finger (10) having an end (14) that comes to bear against the seat in order to close the first hydraulic line (7) when the piston approaches the retracted position, such that only the second hydraulic line (8) remains open while the piston completes its travel towards the retracted position.

Landing gear and aircraft comprising such an actuator.

An additively manufactured component for a landing gear assembly may comprise a lug and a lubrication channel extending through the lug. The lubrication channel may comprise an inlet and an outlet. The outlet may be located at a pin orifice defined by the lug. A center axis of a first portion of the lubrication channel may be oriented at an angle relative to a center axis of a second portion of the lubrication channel.

A metallic-composite joint fitting is provided. The fitting may comprise a frustoconical internal bearing having a bore, a conical sleeve configured to be disposed about the frustoconical internal bearing, a composite structure configured to couple between the frustoconical internal bearing and the conical sleeve, a metallic end fitting configured to be disposed within the bore and couple to the frustoconical internal bearing, and an external nut configured to couple to the metallic end fitting and the conical sleeve, wherein at least one of the frustoconical internal bearing or the conical sleeve comprises a flanged portion mutually configured to couple the conical sleeve to the frustoconical internal bearing via a locking ring.

The invention relates to a strut, such as fiber composite struts used in aircraft or spacecraft, which has a largest possible outer diameter within a cylindrical installation space of the strut, The invention concerns an insert connected to a fiber composite hollow structure, such as a fiber plastic composite hollow structure, where the hollow structure engages an undercut of the insert, wherein the outer region of the fiber composite hollow structure likewise has an undercut and this undercut is filled with a fiber composite jacket, such as a fiber plastic composite jacket, and the inner region of the fiber composite hollow structure has, at least in one subregion, a core connected thereto.

A lighting system for an aircraft includes at least one light mounted on at least one landing gear assembly of the aircraft. The at least one light is configured to emit ultraviolet light when the at least one landing gear assembly is in a lowered condition.

An aircraft assembly having a first region, a second region spaced from the first region by a flexible region, and a deflection sensor. The first region has greater positional stability than the second region such that the second region deflects further from its default position than the first region during in-use loads. The deflection sensor includes a first gyroscope at the first region to generate a first signal representing rotation of the first region about one or more orthogonal axes, and a second gyroscope at the second region to generate a second signal representing rotation of the second region about the one or more axes. The second gyroscope is synchronised in time with the first. A controller subtracts one of the first and second signals from the other to obtain a differential signal representing deflection of the second region relative to the first due to flexing of the flexible region.

A hard landing indicator mountable to a landing gear of an aircraft is provided. The landing gear has components displaceable toward each other upon the aircraft experiencing a landing. The hard landing indicator includes a first portion securable to one of these components and a second portion that projects outwardly from the first portion and oriented toward another component of the landing gear to be positioned within a path of displacement of the second component toward the first component. The second portion is impacted by this component upon this component being displaced during a hard landing of the aircraft. The impact leaves a visual mark on the second portion of the hard landing indicator to indicate that a hard landing has occurred. A landing gear equipped with and a method of installing such indicator are also provided.