Abstract: An aircraft that includes a hydraulic control system for actuators of one or more engine thrust reversers of an aircraft arranged in a propulsion system of the aircraft, the hydraulic control system has a hydraulic pressure generation assembly dedicated to the hydraulic control of the actuators and a hydraulic control controller device dedicated to the hydraulic control of the actuators. Advantageously, it is thus possible to increase the reliability and the longevity of the control system for the engine thrust reversers, to reduce the weight of the aircraft, and to simplify the hydraulic circuits for control and hydraulic generation that are made independent of the other hydraulic circuits of the aircraft.

Abstract: The invention relates to a connector assembly (1, 100) for connecting a motor to the cable (5,103) of a strut fixing the motor to an aircraft wing. A male part (2, 101) includes pins (7, 107) and female part (3, 102) lugs (10, 108). In an embodiment, the pins extend radially around the axis (A) of a cable (5) provided with the pins. In another embodiment, the pins extend in a parallel position to the axis (A?) of the cable (103) provided therewith and in a perpendicular direction with the cable provided therewith.

Abstract: In order to avoid an operator forgetting to actuate locking mechanism interposed between two elements, such as the pod cowls (12, 14) of an aircraft engine, when said elements are in the closed position, use is made of a closure fault indicator. Said indicator comprises retractable abutment members (42, 44) automatically maintaining the two elements spaced from one another in a visible manner, when said elements are moved from their open position into their closed position.