A landing gear is provided. The landing gear includes a composite strut tube having a first lug and a second lug thereon. A first brace is coupled to the composite strut tube with a first two-force member via the first lug and a second brace is coupled to the composite strut tube with a second two-force member via the second lug. A method for assembling the landing gear is also provided.

A bushing for use in an aircraft includes a hollow cylindrical shaft having a first end and a second end opposite the first end, a radially outwardly extending flange disposed at the first end of the hollow cylindrical shaft, an entry way disposed along the radially outwardly extending flange, and a lubrication passageway fluidly coupled to the entry way. The lubrication passageway extends between the first end and the second end.

A bushing for use in an aircraft includes a hollow cylindrical shaft having a first end and a second end opposite the first end, a radially outwardly extending flange disposed at the first end of the hollow cylindrical shaft, an entry way disposed along the radially outwardly extending flange, and a lubrication passageway fluidly coupled to the entry way. The lubrication passageway extends between the first end and the second end.

A landing gear is provided. The landing gear includes a composite strut tube having a first lug and a second lug thereon. A first brace is coupled to the composite strut tube with a first two-force member via the first lug and a second brace is coupled to the composite strut tube with a second two-force member via the second lug. A method for assembling the landing gear is also provided.

A leak detection method for detecting a leak past a dynamic seal in aircraft landing gear (100) comprising: a strut (10); a rod (20) slidably mounted in the strut; and a bearing (70) fitted to an end (11) of the strut to guide the rod (20). The bearing includes a bushing (50) having a seal (62) arranged to rub against the rod (20) to provide sealing between the strut and the rod, defines a fluid chamber (2), and a stop nut (40) for preventing the bushing from moving relative to the strut. The method includes a step of installing a test nut (3) without a wiper seal in the place of the stop nut (40), the step of putting the hydraulic fluid in the landing gear under pressure, and the step of verifying the existence of a leak of hydraulic fluid on the outside surface (22) of the rod (20).

A leak detection method for detecting a leak past a dynamic seal in aircraft landing gear (100) comprising: a strut (10); a rod (20) slidably mounted in the strut; and a bearing (70) fitted to an end (11) of the strut to guide the rod (20). The bearing includes a bushing (50) having a seal (62) arranged to rub against the rod (20) to provide sealing between the strut and the rod, defines a fluid chamber (2), and a stop nut (40) for preventing the bushing from moving relative to the strut. The method includes a step of installing a test nut (3) without a wiper seal in the place of the stop nut (40), the step of putting the hydraulic fluid in the landing gear under pressure, and the step of verifying the existence of a leak of hydraulic fluid on the outside surface (22) of the rod (20).

An aircraft landing gear having a male part interlocked with a female part along an interlocking direction is provided. The external contact surface of the male part, when it is observed along the interlocking direction, can be an exclusively convex closed surface having external contact surface portions in the form of rounded lobes that form obstacles to the pivoting of the female part with respect to the male part about the interlocking direction. The aircraft landing gear is suitable for use with an aircraft.

An aircraft landing gear having a male part interlocked with a female part along an interlocking direction is provided. The external contact surface of the male part, when it is observed along the interlocking direction, can be an exclusively convex closed surface having external contact surface portions in the form of rounded lobes that form obstacles to the pivoting of the female part with respect to the male part about the interlocking direction. The aircraft landing gear is suitable for use with an aircraft.

A fuselage for an airplane including a frame comprising an upper truss and a lower truss extending from a front end of the fuselage towards the rear end of the fuselage, wherein the lower truss comprises one or more forward box beams, a plurality of support rings attached to the upper truss and lower truss, a front bulkhead connected to a first end of the upper truss and lower truss, a main bulkhead connected to the upper truss and lower truss, a pressure vessel adapted to fit within the frame between the front bulkhead and main bulkhead, and a skin adapted to fit over the frame.

A fuselage for an airplane including a frame comprising an upper truss and a lower truss extending from a front end of the fuselage towards the rear end of the fuselage, wherein the lower truss comprises one or more forward box beams, a plurality of support rings attached to the upper truss and lower truss, a front bulkhead connected to a first end of the upper truss and lower truss, a main bulkhead connected to the upper truss and lower truss, a pressure vessel adapted to fit within the frame between the front bulkhead and main bulkhead, and a skin adapted to fit over the frame.