Automated control of turbine engines of a rotary-wing aircraft during a failure on a turbine engine

An electronic control unit for a rotary-wing aircraft provided with a plurality of turbine engines, the electronic control unit being configured to receive a rotation speed setpoint of the rotary wing and automatically control the turbine engines of the aircraft during a breakdown of one turbine engine, the electronic control unit comprising:

• an input module configured to receive signals detecting a breakdown in a first turbine engine among the turbine engines of the rotary wing aircraft,
• a means for determining the flight phase in which the aircraft is situated,
• a means for activating operation of the turbine engines in a misaligned mode configured to deliver, when the aircraft is in a phase other than a takeoff phase, a command to progressively reduce the power of said first turbine engine and a command to progressively increase the power of at least one second turbine engine of the aircraft, the progressive reduction in power of the first turbine engine and the progressive increase in power of said at least one second turbine engine being controlled in a complementary manner to maintain the rotation speed of the rotating wing at the rotation speed of the rotation speed setpoint of the rotary wing,
• a means for activating an indicator of an engine anomaly for the pilot, inviting him to employ prudent piloting, and
• a means for setting a power limiter configured to limit the power of the turbine engines of the aircraft to at least a first maximum available power threshold-corresponding to a maximum power usable by a turbine engine for a first limited period.