FIELD: power units.
SUBSTANCE: invention relates to a power unit (200) for an aircraft, containing a gas turbine bypass engine (1) and a pylon (202) for mounting a gas turbine engine. The gas turbine engine contains an air-oil cooling system (30) located in the interloop compartment (22), limited radially outward by the interloop fairing (20). The cooling system is configured to be supplied with air taken from the outer circuit (14b) of the gas turbine engine, limited in the radially inward direction by the interloop fairing (20). The cooling system (30) is mounted on a support (34) located in the interloop compartment (22). According to the invention, the support (34) is mechanically connected to the suspension pylon by connecting means (50) passing through the interloop fairing (20).
EFFECT: improved positioning accuracy of the interloop fairing and the air-oil cooling system relative to each other.
10 cl, 8 dwg
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