An airfoil (66, 166, 266) for a gas turbine engine includes an airfoil section (66A, 166A, 266A) that extends from a root section (66B, 266B). The airfoil section (66A, 166A, 266A) extends between a leading edge (LE) and a trailing edge (TE) in a chordwise direction (C) and extends between a tip portion (66C, 266C) and the root section (66B, 266B) in a radial direction (R). The airfoil section (66A, 166A, 266A) defines a pressure side (P) and a suction side (S) separated in a thickness direction (T). The airfoil section (66A, 166A, 266A) includes a metallic sheath (72, 172, 272) that receives a composite core (74, 174, 274). 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 (C). 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 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 (85) aligned to receive a common retention pin (68, 168).
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