Spool valve for aircraft engine

An aircraft engine, comprising:

• a compressor section;
• an oil system having an oil source fluidly connectable to a component, the component fluidly connected to the compressor section;
• and
• a valve for selectively fluidly connecting the oil source to the component, the valve having:
• a housing defining an internal cavity circumscribed by a peripheral wall extending along a longitudinal axis between a first end and a second end, the internal cavity having an outlet extending through the peripheral wall at a location intermediate between the first end and the second end, and an inlet at a location between the first end and the outlet, the internal cavity having a reference inlet fluidly connected to the compressor section;
• a spool movably received within the internal cavity for reciprocating movement along the longitudinal axis, the spool fluidly separating the internal cavity into a reference cavity and an inlet cavity, the inlet cavity communicating with the inlet, the reference cavity communicating with the reference inlet, the spool sealingly engaged to the peripheral wall of the housing on both of opposite sides of the outlet within both of the inlet cavity and the reference cavity, the spool defining one or more apertures and having:
• a closed position in which the spool blocks fluid communication between the inlet and the outlet, and
• an open position in which the spool fluidly connects the inlet to the outlet through the one or more apertures;
• and
• a biasing member biasing the spool to the closed position.