There is disclosed a method of controlling a helicopter (1) comprising: at least one thermal engine (11); at least one rotor (3), which is operatively connectable to thermal engine (11) to be drive, in use, at a set rotational speed (ωSET); an emergency
system (40) comprising: at least one
electric motor (41), which is operatively connectable to rotor (3) and an electrical power source (42), which is electrically connected to
electric motor (41); the method comprises the steps of i) operatively connecting thermal engine (11) to rotor (3) and keeping
electric motor (41) disconnected by rotor (3) or idle, in a normal operating condition of thermal engine (11); ii) detecting if thermal engine (11) is in at least
partial failure condition; iii) accelerating electric motor (41) up to when said current rotational speed (ω) equals set value (ωSET), in case of at least
partial failure of said thermal engine (11); step iii) comprises the steps of iv) sensing a plurality of parameters (ω, ωERR, ϕ, ϕERR, IIT, ττ / S, τMGB, Powerτ / S, PowerMGB) of thermal engine (11) and rotor (3); and v) identifying an at least
partial failure of thermal engine (11), on the basis of parameters (ω, ωERR, ϕ, ϕERR, IIT, τ, P.