Abstract: A landing gear (3) provided with first and second longitudinal bearing skids (4, 5) and with first and second transverse crossbars (6, 7). The landing gear includes at least one resilient fastener device (10) together with at least one blocking means (20) and at least one centering means (30) for each crossbar.

Abstract: A landing gear (3) provided with first and second longitudinal bearing skids (4, 5) and with first and second transverse crossbars (6, 7). The landing gear includes at least one resilient fastener device (10) together with at least one blocking means (20) and at least one centering means (30) for each crossbar.

Abstract: On the folding-blade rotor, an outer radial length of an electric cable for connection between the hub and a blade has a part forming spare length and wound into an S-shape around two reels each mounted at the end of one of the two blade pins that connect the blade root to the cuff connecting the blade to the hub. The withdrawal of at least one pin with its reel releases a portion of the part forming spare length and allows the blade to be folded without disconnection at the ends of said electrical connecting cable.

Abstract: On the folding-blade rotor, an outer radial length of an electric cable for connection between the hub and a blade has a part forming spare length and wound into an S-shape around two reels each mounted at the end of one of the two blade pins that connect the blade root to the cuff connecting the blade to the hub. The withdrawal of at least one pin with its reel releases a portion of the part forming spare length and allows the blade to be folded without disconnection at the ends of said electrical connecting cable.

Abstract: The invention relates to a low-vulnerability device for the operation of a lifting and propulsing helicopter rotor by means of a cyclic plate mechanism, in which the non-rotating plate (5) is coupled at four points (1, 2, 3, 4) to four hydraulic actioning servocontrols each comprising a power jack (9), an anchoring system (10) and a servocontrol-distributor (41, 42), three servocontrols being used when normally working, the fourth being used in back-up in the event of a failure of one of the other three. Each power jack (9) is supplied by an independent hydraulic circuit which comprises the servocontrol-distributor (41, 42) operated by a mechanical input, connected to the cockpit by linkage (13), and a disengageable anchoring system.