A turboprop gas turbine engine adapted to be mounted to an aircraft, the turboprop gas turbine engine comprising: a nacelle; a propeller; an air-cooled-oil-cooler (ACOC); an engine core and a gearbox driving the propeller, the engine core and the gearbox being enclosed within the nacelle, the propeller configured to be located rearward of the gearbox and the engine core relative to a direction of travel of the aircraft, the turboprop gas turbine engine being a pusher engine, the engine core defining a central longitudinal axis; and an air intake disposed within the nacelle and formed to direct ambient air into the engine core of the turboprop gas turbine engine, the air intake including an air inlet duct having a forward-facing intake inlet receiving the ambient air, the air inlet duct including an upstream section and a downstream section, the upstream section of the air inlet duct in fluid communication with the intake inlet and extending downstream from the intake inlet, the downstream section of the air inlet duct fluidly connected to and directing air from the upstream section into an engine air inlet of the engine core, wherein the upstream section of the air inlet duct is centrally located within the nacelle relative to the central longitudinal axis, and the intake inlet of the air intake extends along an intake axis that is either substantially coaxial with the central longitudinal axis or radially spaced apart therefrom, and a second air outlet duct is located within the nacelle, the second air outlet duct is connected to the air inlet duct at a location between the upstream section and the downstream section thereof, the location being between the intake inlet and the engine air inlet, the second air outlet duct directing air from the upstream section of the air inlet duct into the ACOC, characterised in that the ACOC and the second air outlet duct are located axially forward of the engine core. a nacelle; a propeller; an air-cooled-oil-cooler (ACOC); an engine core and a gearbox driving the propeller, the engine core and the gearbox being enclosed within the nacelle, the propeller configured to be located rearward of the gearbox and the engine core relative to a direction of travel of the aircraft, the turboprop gas turbine engine being a pusher engine, the engine core defining a central longitudinal axis; and an air intake disposed within the nacelle and formed to direct ambient air into the engine core of the turboprop gas turbine engine, the air intake including an air inlet duct having a forward-facing intake inlet receiving the ambient air, the air inlet duct including an upstream section and a downstream section, the upstream section of the air inlet duct in fluid communication with the intake inlet and extending downstream from the intake inlet, the downstream section of the air inlet duct fluidly connected to and directing air from the upstream section into an engine air inlet of the engine core, wherein the upstream section of the air inlet duct is centrally located within the nacelle relative to the central longitudinal axis, and the intake inlet of the air intake extends along an intake axis that is either substantially coaxial with the central longitudinal axis or radially spaced apart therefrom, and a second air outlet duct is located within the nacelle, the second air outlet duct is connected to the air inlet duct at a location between the upstream section and the downstream section thereof, the location being between the intake inlet and the engine air inlet, the second air outlet duct directing air from the upstream section of the air inlet duct into the ACOC, characterised in that the ACOC and the second air outlet duct are located axially forward of the engine core.