An aircraft landing gear is disclosed having a first oleo strut include a sleeve portion and a slider portion, the slider portion being slidable within a hydraulic fluid chamber of the sleeve portion, and a second, similar oleo strut. The landing gear also includes a hydraulic fluid balancer having a balance chamber separated into first and second end sections, wherein the hydraulic fluid chamber of the sleeve portion of the first oleo strut is fluidly connected to the first section of the balance chamber and the hydraulic fluid chamber of the sleeve portion of the second oleo strut is fluidly connected to the second section of the balance chamber of the hydraulic fluid balancer.

A method of cooling hydraulic fluid for an aircraft hydraulic system is provided. The method comprises connecting an output side of an external cooling system to a return side of an electric motor driven pump (EMDP) in the hydraulic system and connecting an input side of the external cooling system to a hydraulic fluid reservoir in the hydraulic system. The EMDP pumps hydraulic fluid through the hydraulic system under conditions wherein fuel tanks in the aircraft are empty, and the external cooling system cools the hydraulic fluid as the EMDP pumps the hydraulic fluid, wherein the hydraulic fluid passes from the hydraulic fluid reservoir and through the external cooling system before entering the EMDP.

The invention relates to a hydraulic circuit for operating an aircraft landing gear comprising: a general valve (1) for admitting a supply pressure into the circuit; distributors (4, 6) for supplying undercarriages and/or landing gear doors operating actuators (3) or release actuators for hooks (5) maintaining the undercarriages and/or the doors in the retracted position; a depressurization valve (102) for, in an open position, allowing the selective distribution of supply pressure to an extension chamber (3A) or a retraction chamber (3B) of each operating actuator by the distributors, and, in a depressurization position, forcing the return of a retraction chamber of each operating cylinder. According to the invention, the depressurization valve is returned (105) in a stable manner to the depressurization position, and is moved into the open position only in response to the presence of supply pressure downstream of the general valve.

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.

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.

A torque link assembly may comprise an upper torque link, a lower torque link, and a torque link pin. The upper torque link may define an upper hydraulic fluid channel. The lower torque link may define a lower hydraulic fluid channel. The torque link pin may fluidly couple the upper hydraulic fluid channel to the lower hydraulic fluid channel.

A torque link assembly may comprise an upper torque link, a lower torque link, and a torque link pin. The upper torque link may define an upper hydraulic fluid channel. The lower torque link may define a lower hydraulic fluid channel. The torque link pin may fluidly couple the upper hydraulic fluid channel to the lower hydraulic fluid channel.

A telescoping strut for a retractable landing gear in an aircraft. The telescoping strut comprises a pre-pressurized and central extension chamber extending along the telescoping strut and a surrounding retraction chamber. For retraction, an hydraulic generation architecture of the aircraft feeds a single input/output passage of the surrounding retraction chamber with a overcoming fluid pressure that overwhelms a extension positive pressure in the central extension chamber and opposes the effect of the pre-pressurizing. The retraction system is for instance for a rotorcraft.

A telescoping strut for a retractable landing gear in an aircraft. The telescoping strut comprises a pre-pressurized and central extension chamber extending along the telescoping strut and a surrounding retraction chamber. For retraction, an hydraulic generation architecture of the aircraft feeds a single input/output passage of the surrounding retraction chamber with a overcoming fluid pressure that overwhelms a extension positive pressure in the central extension chamber and opposes the effect of the pre-pressurizing. The retraction system is for instance for a rotorcraft.

A bracket manifold for a landing gear assembly is disclosed. In various embodiments, the bracket manifold includes a mounting plate having a central portion and a first wing portion extending from the central portion; and a first manifold section integrated monolithically into at least one of the central portion and the first wing portion of the mounting plate.