Landing gear with simplified manoeuvring mechanism

An aircraft provided with a landing gear comprising a leg having a hinge for pivoting between a retracted position in a hold of the aircraft and a deployed position, a main brace having a state in which the leg is stabilized in the deployed position, in which the main brace defines a main force path, a maneuvering mechanism for maneuvering the leg at least from the deployed position to the retracted position, and a stabilizing mechanism for stabilizing the leg in the retracted position,

• wherein the maneuvering mechanism comprises a rotary actuator which is positioned in the hold outside the main force path when the leg is in the deployed position and which actuates a crank, and a connecting rod having a first end hinged about a first axis to an element connected to the leg and a second end hinged about a second axis to the crank so that the connecting rod and the crank have a first relative angular position in which the first axis and the second axis are in a first alignment with respect to a shaft of the rotary actuator when the leg is in the retracted position so that the connecting rod and the crank stabilize a strut in the retracted position and form the stabilizing mechanism for stabilizing the leg in the retracted position,
• wherein the element to which the first end of the connecting rod is hinged is a part of the main brace and the connecting rod and the crank have a second relative angular position in which the first axis and the second axis are in a second alignment relative to the shaft of the rotary actuator when the leg is in the deployed position in such a way that the connecting rod and the crank stabilize the main brace in the holding state to form a main brace stabilizing mechanism for stabilizing the main brace in a stabilized state, and
• wherein the crank and the connecting rod are held in the second relative angular position by a locking member.