PROPULSION ASSEMBLY OF AN AIRCRAFT COMPRISING A FIRE PROTECTION SYSTEM WITH A LINE FOR DISTRIBUTION OF FIRE EXTINGUISHING AGENT

A propulsion assembly including a turbomachine attached to a pylon, and a fire-fighting system, the turbomachine including fire zones, the fire-fighting system including two reservoirs of pressurized extinguishing agent in the pylon and a distribution line connecting the reservoirs to nozzles. The distribution line includes connected pipes having a low point between the reservoirs and the nozzles, and, for each low point, a fluid drainage device for evacuating fluid. The drainage device includes a fluid passage for fluid evacuation from the distribution line and a mechanism for shutting off the fluid passage, the mechanism movable under effect of distribution line pressure, between a first position where it opens the fluid passage and a second position where it closes the fluid passage, the second position being reached when the pressure in the distribution line is greater than or equal to a predetermined pressure.