FLUID SYSTEM FOR GAS TURBINE ENGINE

An aircraft engine (10), has: a duct (22) having an inlet, an outlet, and a bleed port (24) through a wall (21) of the duct (22); a bleed conduit (30) stemming from the duct (22); a first valve (33) connected to the bleed conduit (30) and having an open configuration and a closed configuration; and a second valve (34) connected to the bleed conduit (30) upstream of the first valve (33) and at or proximate the bleed port (24), the second valve (34) having a second open configuration and a second closed configuration, wherein when in the second closed configuration, the second valve (34) blocks fluid communication between the bleed port (24) and the first valve (33) such that a portion of the bleed conduit (30) between the first valve (33) and the second valve (34) is fluidly isolated from the duct (22), the second valve (34) being in the second open configuration when the first valve (33) is in the open configuration.