Roller bearing arrangement for a gas turbine engine

A roller bearing arrangement for a gas turbine engine, the roller bearing arrangement comprising:

• a fan shaft, the fan shaft defining an axis of rotation;
• a stub shaft, the stub shaft being connected to the fan shaft and extending radially away therefrom so as to create a first axial bearing surface on a radially outer surface of the stub shaft, the first axial bearing surface being parallel with the axis of rotation and at a greater radial distance from the axis of rotation than a radially outer surface of the fan shaft;
• a static structure, the static structure having a second axial bearing surface parallel with and opposite to the first axial bearing surface;
• a plurality of roller bearing elements positioned between the first axial bearing surface and the second axial bearing surface;
• and
• a first snubber positioned between the radially outer surface of the fan shaft and a radially inner surface of the stub shaft, the first snubber being spaced apart from the radially inner surface of the stub shaft or the radially outer surface of the fan shaft so as to limit a radial movement range of the stub shaft,
• wherein the first snubber is an extension of an output shaft from a power gear box extending radially outward towards the radially inner surface of the stub shaft.