A gas turbine engine system comprising: a fan rotatable about an axis; a housing arranged about the fan; a gas turbine engine core having a compressor (16a,16b) at least partially within the housing; a fan bypass passage downstream of the fan for conveying a bypass airflow between the housing and the gas turbine engine core; a nozzle having a first nozzle section operative to move in a generally axial direction relative to the axis between a plurality of positions and a second nozzle section adjacent the first nozzle section that is operative to also move in a generally axial direction between a stowed position and a thrust reverse position; and an actuator including a telescoping member having a first telescoping section coupled with the first nozzle section and a second telescoping section coupled with the second nozzle section, wherein the first telescoping section and the second telescoping section are moveable independently of each other to selectively move the first nozzle section and the second nozzle section, characterised in that: the plurality of positions of the first nozzle section influence the bypass airflow; and the thrust reverse position of the second nozzle section diverts the bypass airflow in a thrust reversing direction; wherein the first telescoping section and the first nozzle section move axially when the second telescoping section and the second nozzle section move to the thrust reverse position, and wherein the first nozzle section moves axially aft relative to the second nozzle section from a closed position to an open position so as to space the first nozzle section from the second nozzle section and provide an opening therebetween. a fan rotatable about an axis; a housing arranged about the fan; a gas turbine engine core having a compressor (16a,16b) at least partially within the housing; a fan bypass passage downstream of the fan for conveying a bypass airflow between the housing and the gas turbine engine core; a nozzle having a first nozzle section operative to move in a generally axial direction relative to the axis between a plurality of positions and a second nozzle section adjacent the first nozzle section that is operative to also move in a generally axial direction between a stowed position and a thrust reverse position; and an actuator including a telescoping member having a first telescoping section coupled with the first nozzle section and a second telescoping section coupled with the second nozzle section, wherein the first telescoping section and the second telescoping section are moveable independently of each other to selectively move the first nozzle section and the second nozzle section, characterised in that: the plurality of positions of the first nozzle section influence the bypass airflow; and the thrust reverse position of the second nozzle section diverts the bypass airflow in a thrust reversing direction; wherein the first telescoping section and the first nozzle section move axially when the second telescoping section and the second nozzle section move to the thrust reverse position, and wherein the first nozzle section moves axially aft relative to the second nozzle section from a closed position to an open position so as to space the first nozzle section from the second nozzle section and provide an opening therebetween. the plurality of positions of the first nozzle section influence the bypass airflow; and the thrust reverse position of the second nozzle section diverts the bypass airflow in a thrust reversing direction; wherein the first telescoping section and the first nozzle section move axially when the second telescoping section and the second nozzle section move to the thrust reverse position, and wherein the first nozzle section moves axially aft relative to the second nozzle section from a closed position to an open position so as to space the first nozzle section from the second nozzle section and provide an opening therebetween.