An airfoil (66, 166, 266) for a gas turbine engine comprising: an airfoil section (66A, 166A, 266A) extending from a root section (66B, 266B), the airfoil section (66A, 166A, 266A) extending between a leading edge and a trailing edge in a chordwise direction and extending between a tip portion (66C, 266C) and the root section (66B, 266B) in a radial direction, and the airfoil section (66A, 166A, 266A) defining a pressure side and a suction side separated in a thickness direction; wherein the airfoil section (66A, 166A, 266A) includes a metallic sheath (72, 172, 272) that receives a composite core (74, 174, 274), and the core (74, 174, 274) includes first and second ligaments (76A, 76B) received in respective internal channels (72C, 72D, 172C, 172D) defined by the sheath (72, 172, 272) such that the first and second ligaments (76A, 76B) are spaced apart along the root section (66B, 266B) with respect to the chordwise direction; wherein each one of the first and second ligaments (76A, 76B) includes at least one interface portion (78, 178, 278) in the root section (66B, 266B), and the at least one interface portion (78, 178, 278) of the first ligament (76A, 76B) and the at least one interface portion (78, 178, 278) of the second ligament (76A, 76B) define respective sets of bores that receive a retention pin (68, 168); wherein the core (74, 174, 274) includes a ligament bridge that interconnects an adjacent pair of the ligaments (76A, 76B) at a position along the airfoil section (66A, 166A, 266A); and characterized in that the ligament bridge is dimensioned to abut against opposing ribs (73, 173, 273) of a first skin (72A, 172A, 272A) of the sheath (72, 172, 272) to limit radial movement of the core (74, 174, 274) relative to the sheath (72, 172, 272), the opposing ribs (73, 173, 273) bounding the internal channels (72C, 72D, 172C, 172D). an airfoil section (66A, 166A, 266A) extending from a root section (66B, 266B), the airfoil section (66A, 166A, 266A) extending between a leading edge and a trailing edge in a chordwise direction and extending between a tip portion (66C, 266C) and the root section (66B, 266B) in a radial direction, and the airfoil section (66A, 166A, 266A) defining a pressure side and a suction side separated in a thickness direction; wherein the airfoil section (66A, 166A, 266A) includes a metallic sheath (72, 172, 272) that receives a composite core (74, 174, 274), and the core (74, 174, 274) includes first and second ligaments (76A, 76B) received in respective internal channels (72C, 72D, 172C, 172D) defined by the sheath (72, 172, 272) such that the first and second ligaments (76A, 76B) are spaced apart along the root section (66B, 266B) with respect to the chordwise direction; wherein each one of the first and second ligaments (76A, 76B) includes at least one interface portion (78, 178, 278) in the root section (66B, 266B), and the at least one interface portion (78, 178, 278) of the first ligament (76A, 76B) and the at least one interface portion (78, 178, 278) of the second ligament (76A, 76B) define respective sets of bores that receive a retention pin (68, 168); wherein the core (74, 174, 274) includes a ligament bridge that interconnects an adjacent pair of the ligaments (76A, 76B) at a position along the airfoil section (66A, 166A, 266A); and characterized in that the ligament bridge is dimensioned to abut against opposing ribs (73, 173, 273) of a first skin (72A, 172A, 272A) of the sheath (72, 172, 272) to limit radial movement of the core (74, 174, 274) relative to the sheath (72, 172, 272), the opposing ribs (73, 173, 273) bounding the internal channels (72C, 72D, 172C, 172D).