Abstract: Embodiments of the invention relate to a landing gear wherein it includes at least one static sealing point, the static sealing point comprising a gasket made of elastically deformable material held between a portion of a first part of the landing gear and a portion of a second part of the landing gear, the first and second parts of the landing gear comprising a steel substrate coated with a zinc and nickel alloy coating, including in mass percentage of the alloy between 12% and 18% and nickel, at most 0.5% of elements other than nickel and zinc, the balance being zinc, and the roughness Ra of the surface of the portions of the first and second parts of the landing gear being less than or equal to 1.6 ?m.

Abstract: Aircraft landing gear strut (1) comprising a main part (1a) extending along a main axis (X-X) of the strut and comprising an axle shaft (1b) extending in a plane (P) perpendicular to the main shaft (1a) of the strut, this axle shaft (1b) being designed to support at least one landing gear when (2a, 2b) equipped with brakes (3a, 3b) for braking the wheel, said axle shaft (1b) being made of steel. The axle shaft (1b) bears at least one layer of zinc-nickel alloy coating (C), this zinc-nickel alloy comprising, as a mass percent of the alloy, between 12% and 18% or nickel, at most 0.5% of elements other than nickel and zinc, the rest being zinc.

Abstract: A landing gear (1) for aircraft comprising a first pair of first and second parts (7, 8, 7?, 8?), said first part (7, 7?) having a steel substrate and a sliding layer (C, C?) formed on this substrate, the second part (8, 8?) being in sliding contact against said sliding layer (C, C?) with a maximum rectilinear sliding amplitude (G, G?) of less than 0.5 mm, the sliding layer (C, C?) being adapted to support a surface pressure in excess of 50 MPa. The sliding layer (C, C?) is a zinc and nickel alloy comprising, in terms of percentage by weight of the alloy, between 12% and 18% nickel and the first part has a protective layer (P, P?) against corrosion extending from the sliding layer (C, C?), this protective layer (P, P?) being formed of said zinc and nickel alloy.

Abstract: Aircraft landing gear strut (1) comprising a main part (1a) extending along a main axis (X-X) of the strut and comprising an axle shaft (1b) extending in a plane (P) perpendicular to the main shaft (1a) of the strut, this axle shaft (1b) being designed to support at least one landing gear wheel (2a, 2b) equipped with brakes (3a, 3b) for braking the wheel, said axle shaft (1b) being made of steel. The axle shaft (1b) bears at least one layer of zinc-nickel alloy coating (C), this zinc-nickel alloy comprising, as a mass percent of the alloy, between 12% and 18% of nickel, at most 0.5% of elements other than nickel and zinc, the rest being zinc.

Abstract: A landing gear (1) for aircraft comprising a first pair of first and second parts (7, 8, 7?, 8?), said first part (7, 7?) having a steel substrate and a sliding layer (C, C?) formed on this substrate, the second part (8, 8?) being in sliding contact against said sliding layer (C, C?) with a maximum rectilinear sliding amplitude (G, G?) of less than 0.5 mm, the sliding layer (C, C?) being adapted to support a surface pressure in excess of 50 MPa. The sliding layer (C, C?) is a zinc and nickel alloy comprising, in terms of percentage by weight of the alloy, between 12% and 18% nickel and the first part has a protective layer (P, P?) against corrosion extending from the sliding layer (C, C?), this protective layer (P, P?) being formed of said zinc and nickel alloy.