Patent ID: 7769521

Claim:
A method of performing a health check on at least a first turbine engine (M 1 ) of a rotorcraft, said rotorcraft having first and second turbine engines (M 1 and M 2 ) presenting, before said health check, respectively first and second normal values (V 1 c , V 2 c ) for a surveillance parameter and also real first and second final values (V 1 f , V 2 f ) for said surveillance parameter during said health check, wherein the following steps are performed in succession: a) determining the real first final value (V 1 f ) of said surveillance parameter that said first turbine engine (M 1 ) is to reach in order to perform said health check accurately; b) assuming that said real second final value (V 2 f ) of said surveillance parameter of said second turbine engine (M 2 ) is equal to said second normal value (V 2 c ) of said second turbine engine (M 2 ); c) determining the difference between said real first final value (V 1 f ) and said real second final value (V 2 f ); d) if said difference is greater than a predetermined threshold, readjusting said real second final value (V 2 f ) so that the difference between said real first final value (V 1 f ) and said real second final value (V 2 f ) is less than said predetermined threshold during the health check; and e) controlling said first turbine engine (M 1 ) so that said first normal value (V 1 c ) before said health check reaches said real first final value (V 1 f ) during said health check, and controlling said second turbine engine (M 2 ) so that said second normal value (V 2 c ) before said health check reaches said real second final value (V 2 f ).