Gas turbine engine

A gas turbine engine, the gas turbine engine comprising, in axial flow sequence, a fan assembly, a compressor module, a turbine module, and an exhaust module, the gas turbine engine comprising a first engine mount plane and a second engine mount plane, each of the first engine mount plane and second engine mount plane being defined by a respective set of a first side engine mount point, a second side engine mount point, and a centre engine mount point, the first and second engine mount planes being configured to support the gas turbine engine in a machine body, the gas turbine engine having an axial length L, the axial length extending from an inlet face of the engine to an exhaust face of the engine, and

• wherein the first engine mount plane is positioned axially along the gas turbine engine at a first engine mount plane position, the first engine mount plane position being within a range of between 0.24*L to 0.32*L from the inlet face of the engine, and the second engine mount plane is positioned axially along the gas turbine engine at a second engine mount plane position, the second engine mount plane position being within a range of between 0.73*L to 0.79*L from the inlet face of the engine.