A gas turbine engine comprising an array of radially extending fan blades mounted on a hub and a fan containment system (300, 400) fitted around the fan blades, the fan containment system comprising: a fan case (350, 450) having an annular casing element (352, 452) for encircling the array of fan blades and a hook (354, 454) projecting in a generally radially inward direction from the annular casing element and positioned axially forward of the array of fan blades; an annular fan track liner (356, 456) positioned substantially coaxial to the annular casing element, and positioned such that a forward end of the fan track liner is axially spaced from the hook so that there is a gap between the hook and the fan track liner; and characterised in that a bridge member (364, 464) spans the gap between the hook and the fan track liner, wherein the bridge member comprises an annular plate (370, 470) that spans the gap between the hook and the fan track liner; and a stiffening member (372, 472) that connects the annular plate to the hook, wherein the annular plate is positioned such that a radially inner surface of the annular plate forms part of a gas washed surface of the fan containment system, and wherein a voidal region is provided radially between the bridge member and the annular casing element, and wherein the annular plate contacts a radially inner surface of the forward end of the fan track liner; and wherein the bridge member is configured to fail when impacted by a fan blade released from the hub so that movement and deformation of the bridge member permit the released fan blade to move into the voidal region and impact the hook and be contained by the fan containment system. a fan case (350, 450) having an annular casing element (352, 452) for encircling the array of fan blades and a hook (354, 454) projecting in a generally radially inward direction from the annular casing element and positioned axially forward of the array of fan blades; an annular fan track liner (356, 456) positioned substantially coaxial to the annular casing element, and positioned such that a forward end of the fan track liner is axially spaced from the hook so that there is a gap between the hook and the fan track liner; and characterised in that a bridge member (364, 464) spans the gap between the hook and the fan track liner, wherein the bridge member comprises an annular plate (370, 470) that spans the gap between the hook and the fan track liner; and a stiffening member (372, 472) that connects the annular plate to the hook, wherein the annular plate is positioned such that a radially inner surface of the annular plate forms part of a gas washed surface of the fan containment system, and wherein a voidal region is provided radially between the bridge member and the annular casing element, and wherein the annular plate contacts a radially inner surface of the forward end of the fan track liner; and wherein the bridge member is configured to fail when impacted by a fan blade released from the hub so that movement and deformation of the bridge member permit the released fan blade to move into the voidal region and impact the hook and be contained by the fan containment system.