| abstract |
The method according to the invention consists in having, in parallel with each of the sensors (32) of the function which one wishes to validate under a predetermined flight condition, controllable forcing means (33, 35) capable of being applied to the input of the safety circuit (30, 31, AL) to which the sensor (32) is connected and in replacement of the output signal emitted by the latter, a simulation signal corresponding to the signal which would be emitted by this same sensor (32 ) in said flight condition, and to use a position of the collective pitch control member (34) of the aerodyne, comprised between the full pitch position (PPP) and a takeoff limit position (PLD), for activate the forcing means (33, 35) in order to produce the simulation signal during a test sequence.n n n The invention applies in particular to helicopters. |