Method for controlling a hybrid helicopter , the hybrid helicopter having a motor installation connected to at least one lifting rotor and to at least one propeller , the motor installation having at least one motor , the lifting rotor having a plurality of first blades and the at least one propeller having a plurality of second blades , characterised in that the method consists of the following stages: measurement (STP1.1) of forward speed (TAS) of the hybrid helicopter , - provided (STP1.3) that the forward speed (TAS) is greater than a first speed threshold (SV1) and that each of the at least one motor fails, automatic implementation (STP2) of a first emergency piloting mode (MOD1) comprising an automatic reduction stage (STP2.1) by an automatic piloting system one pitch from the second blades to an objective pitch that allows the at least one propeller to produce motor power that is transmitted to the lifting rotor , and in that provided that the forward speed (TAS) is equal to or below the first speed threshold (SV1) and that each of the at least one motor fails, automatic implementation (STP3) of a second emergency piloting mode (MOD2) comprising the following stages: - automatic adjustment (STP3.1) by the automatic piloting system of a component (TCC) of the average pitch of the pitch of the second blades to an zero thrust average pitch (TCCO), the zero thrust average pitch (TCCO) being calculated by the automatic piloting system so that at least one propeller exerts no thrust in the absence of a yaw command. characterised in that the method consists of the following stages: measurement (STP1.1) of forward speed (TAS) of the hybrid helicopter , - provided (STP1.3) that the forward speed (TAS) is greater than a first speed threshold (SV1) and that each of the at least one motor fails, automatic implementation (STP2) of a first emergency piloting mode (MOD1) comprising an automatic reduction stage (STP2.1) by an automatic piloting system one pitch from the second blades to an objective pitch that allows the at least one propeller to produce motor power that is transmitted to the lifting rotor , - provided (STP1.3) that the forward speed (TAS) is greater than a first speed threshold (SV1) and that each of the at least one motor fails, automatic implementation (STP2) of a first emergency piloting mode (MOD1) comprising an automatic reduction stage (STP2.1) by an automatic piloting system one pitch from the second blades to an objective pitch that allows the at least one propeller to produce motor power that is transmitted to the lifting rotor , and in that provided that the forward speed (TAS) is equal to or below the first speed threshold (SV1) and that each of the at least one motor fails, automatic implementation (STP3) of a second emergency piloting mode (MOD2) comprising the following stages: - automatic adjustment (STP3.1) by the automatic piloting system of a component (TCC) of the average pitch of the pitch of the second blades to an zero thrust average pitch (TCCO), the zero thrust average pitch (TCCO) being calculated by the automatic piloting system so that at least one propeller exerts no thrust in the absence of a yaw command. - automatic adjustment (STP3.1) by the automatic piloting system of a component (TCC) of the average pitch of the pitch of the second blades to an zero thrust average pitch (TCCO), the zero thrust average pitch (TCCO) being calculated by the automatic piloting system so that at least one propeller exerts no thrust in the absence of a yaw command. <EOS>