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.