| 摘要 |
The method according to the invention consists in arranging, in parallel with each of the sensors (32) for the function which it is desired to validate in a predetermined flight condition, controllable forcing means (33, 35) able to apply to the input of the safety circuit (30, 31, AL) to which the sensor (32) is connected, and in replacement for the output signal sent by the latter, a simulation signal corresponding to the signal which would be sent out by this same sensor (32) in the said flight condition, and in using a position of the collective pitch control member (34) of the aircraft, lying between the full fine pitch position (PPP) and a take-off limit position (PLD), in order to activate the forcing means (33, 35) so as to produce the simulation signal during a test sequence. The invention applies particularly to helicopters. <IMAGE> |
