FAN BLADE FOR A GAS TURBINE ENGINE, GAS TURBINE ENGINE AND METHOD OF FORMING A FAN BLADE.

Disclosed is a fan blade (100) for a gas turbine engine (20), including: an airfoil (115), a cavity (120) formed in the airfoil, a cover (125) configured to cover the cavity, the cover when secured to the airfoil encloses the cavity in the airfoil, a conduit (130) extending from the cavity to an exterior surface of the fan blade, and a check valve located in the conduit, the check valve (135) configured to regulate an internal pressure of the cavity when the cover is secured to the airfoil.