A fan blade assembly for a gas turbine engine, comprising: a blade extending from a blade root to a blade tip , and from a blade leading edge to a blade trailing edge , the blade including a plurality of ribs (72; 74) defining a plurality of blade cavities , wherein the plurality of ribs includes a plurality of spanwise ribs extending in a spanwise direction and a plurality of chordwise ribs extending in a chordwise direction; and a pressure surface cover affixed to the blade and at least partially defining a pressure surface of the fan blade; and wherein the blade includes a region of solidity absent said blade cavities at the blade leading edge, wherein at least one rib of the plurality of ribs extends along a predicted release trajectory of a released adjacent fan blade during a blade release event, thereby supporting impact loads on the pressure surface cover, wherein the at least one rib is angularly offset from the spanwise ribs and the chordwise ribs ; the blade includes a puck disposed at a predicted initial impact site of the released fan blade along the blade leading edge along the predicted release trajectory, the puck defining an increased region of solidity extending in a chordwise direction between the region of solidity at the blade leading edge and the at least one rib extending along the predicted release trajectory to harden the initial impact site , and the puck has a tapered thickness, reducing in thickness in a spanwise direction with increasing distance from the region of solidity at the blade leading edge, characterised in that : the at least one rib has a thickness in a plane comprising the spanwise ribs and the chordwise ribs greater than the thickness of each of the spanwise ribs and each of the chordwise ribs . a blade extending from a blade root to a blade tip , and from a blade leading edge to a blade trailing edge , the blade including a plurality of ribs (72; 74) defining a plurality of blade cavities , wherein the plurality of ribs includes a plurality of spanwise ribs extending in a spanwise direction and a plurality of chordwise ribs extending in a chordwise direction; and a pressure surface cover affixed to the blade and at least partially defining a pressure surface of the fan blade; and wherein the blade includes a region of solidity absent said blade cavities at the blade leading edge, wherein at least one rib of the plurality of ribs extends along a predicted release trajectory of a released adjacent fan blade during a blade release event, thereby supporting impact loads on the pressure surface cover, wherein the at least one rib is angularly offset from the spanwise ribs and the chordwise ribs ; the blade includes a puck disposed at a predicted initial impact site of the released fan blade along the blade leading edge along the predicted release trajectory, the puck defining an increased region of solidity extending in a chordwise direction between the region of solidity at the blade leading edge and the at least one rib extending along the predicted release trajectory to harden the initial impact site , and the puck has a tapered thickness, reducing in thickness in a spanwise direction with increasing distance from the region of solidity at the blade leading edge, characterised in that : the at least one rib has a thickness in a plane comprising the spanwise ribs and the chordwise ribs greater than the thickness of each of the spanwise ribs and each of the chordwise ribs . <EOS>