A gas turbine engine comprising: a fixed structure comprising a fixed ring; and a variable area nozzle assembly comprising: a nozzle hingedly mounted to the fixed structure, the nozzle disposed about a nozzle centerline, the nozzle comprising a radially outer surface and a radially inner surface, the radially inner surface defining an outlet cross-sectional area of the nozzle, the nozzle movable relative to the nozzle centerline between a first position of the radially inner surface defining a maximum area of the outlet cross-sectional area and a second position of the radially inner surface defining a minimum area of the outlet cross-sectional area, and a first thrust reverser door and a second thrust reverser door, each of the first thrust reverser door and the second thrust reverser door moveable between a stowed position in which the first thrust reverser door and the second thrust reverser door are mounted against the fixed ring and a deployed position in which the first thrust reverser door and the second thrust reverser door are positioned axially aft of the nozzle, the gas turbine engine characterised by: the fixed ring radially surrounding the nozzle such that with the nozzle in the first position the radially outer surface contacts the fixed ring and with the nozzle in the second position the radially outer surface is spaced from the fixed ring, wherein the fixed ring comprises a radially outer ring side and a radially inner ring side and wherein the radially outer ring side defines a first recess and a second recess in which the first thrust reverser door and the second thrust reverser door, respectively, are positioned in the stowed position. a fixed structure comprising a fixed ring; and a variable area nozzle assembly comprising: a nozzle hingedly mounted to the fixed structure, the nozzle disposed about a nozzle centerline, the nozzle comprising a radially outer surface and a radially inner surface, the radially inner surface defining an outlet cross-sectional area of the nozzle, the nozzle movable relative to the nozzle centerline between a first position of the radially inner surface defining a maximum area of the outlet cross-sectional area and a second position of the radially inner surface defining a minimum area of the outlet cross-sectional area, and a first thrust reverser door and a second thrust reverser door, each of the first thrust reverser door and the second thrust reverser door moveable between a stowed position in which the first thrust reverser door and the second thrust reverser door are mounted against the fixed ring and a deployed position in which the first thrust reverser door and the second thrust reverser door are positioned axially aft of the nozzle, the gas turbine engine characterised by: the fixed ring radially surrounding the nozzle such that with the nozzle in the first position the radially outer surface contacts the fixed ring and with the nozzle in the second position the radially outer surface is spaced from the fixed ring, wherein the fixed ring comprises a radially outer ring side and a radially inner ring side and wherein the radially outer ring side defines a first recess and a second recess in which the first thrust reverser door and the second thrust reverser door, respectively, are positioned in the stowed position. a nozzle hingedly mounted to the fixed structure, the nozzle disposed about a nozzle centerline, the nozzle comprising a radially outer surface and a radially inner surface, the radially inner surface defining an outlet cross-sectional area of the nozzle, the nozzle movable relative to the nozzle centerline between a first position of the radially inner surface defining a maximum area of the outlet cross-sectional area and a second position of the radially inner surface defining a minimum area of the outlet cross-sectional area, and a first thrust reverser door and a second thrust reverser door, each of the first thrust reverser door and the second thrust reverser door moveable between a stowed position in which the first thrust reverser door and the second thrust reverser door are mounted against the fixed ring and a deployed position in which the first thrust reverser door and the second thrust reverser door are positioned axially aft of the nozzle, the gas turbine engine characterised by: the fixed ring radially surrounding the nozzle such that with the nozzle in the first position the radially outer surface contacts the fixed ring and with the nozzle in the second position the radially outer surface is spaced from the fixed ring, wherein the fixed ring comprises a radially outer ring side and a radially inner ring side and wherein the radially outer ring side defines a first recess and a second recess in which the first thrust reverser door and the second thrust reverser door, respectively, are positioned in the stowed position. the fixed ring radially surrounding the nozzle such that with the nozzle in the first position the radially outer surface contacts the fixed ring and with the nozzle in the second position the radially outer surface is spaced from the fixed ring, wherein the fixed ring comprises a radially outer ring side and a radially inner ring side and wherein the radially outer ring side defines a first recess and a second recess in which the first thrust reverser door and the second thrust reverser door, respectively, are positioned in the stowed position.