Abstract: A method of monitoring a power transmission system of an aircraft, the aircraft including at least one main rotor driven in rotation by a rotor mast and an auxiliary unit having an auxiliary rotor. Control means control the auxiliary rotor. A power relationship is determined providing a first reduced power parameter of the auxiliary unit as a function of a position (POS) of the control means. A setpoint limit is set for a second power parameter for the rotor mast. A current position (POSACTU) of the control means is determined and a calculated value (Vcal) is also determined at least by applying the current position (POSACTU) to the power relationship. A limit value that is not to be exceeded by a power plant is determined, with the limit value being equal to the sum at least of the setpoint limit plus the calculated value.

Abstract: A method of monitoring a power transmission system of an aircraft, the aircraft including at least one main rotor driven in rotation by a rotor mast and an auxiliary unit having an auxiliary rotor. Control means control the auxiliary rotor. A power relationship is determined providing a first reduced power parameter of the auxiliary unit as a function of a position (POS) of the control means. A setpoint limit is set for a second power parameter for the rotor mast. A current position (POSACTU) of the control means is determined and a calculated value (Vcal) is also determined at least by applying the current position (POSACTU) to the power relationship. A limit value that is not to be exceeded by a power plant is determined, with the limit value being equal to the sum at least of the setpoint limit plus the calculated value.

Abstract: A system and method of minimizing the attitude hump phenomenon of a rotary wing aircraft is provided. The rotary wing aircraft includes upper pitching-stabilizer and at least one lower pitching-stabilizer. The lower stabilizer is positioned in a wake of the upper stabilizer generated by a stream of air passing through the rotary wing and impacting against the upper surface of the upper stabilizer.

Abstract: A method of minimizing the attitude hump phenomenon relating to a rotary wing aircraft (1) having an airframe (2) extending longitudinally from a front end (3) to a rear end (4) together with upper pitching-stabilizer means (10) and at least one lower pitching-stabilizer means (20). Under such circumstances, each lower stabilizer means (20) is placed in a wake (8) from said upper stabilizer means (10) as generated by a stream of air (7) passing through said rotary wing (5) and impacting against the upper surface (10?) of an upper stabilizer means (10).