Pitch change mechanism for an aircraft engine

An aircraft engine comprising:

• a plurality of blades;
• and
• a pitch change mechanism comprising:
• a unison ring;
• a plurality of crankshafts coupled to the unison ring, the plurality of crankshafts configured to receive the plurality of blades and each of the plurality of crankshafts having a longitudinal axis;
• an inner shaft coupled to the plurality of crankshafts and the unison ring;
• an actuator piston fixed along a longitudinal axis of the pitch change mechanism;
• and
• an actuator cylinder coupled to the inner shaft, the actuator cylinder configured to move relative to the actuator piston along the longitudinal axis of the pitch change mechanism,
• wherein movement of the actuator cylinder relative to the actuator piston is transferred to a rotation of each of the plurality of crankshafts around the longitudinal axis of each of the plurality of crankshafts to change a pitch of the plurality of blades.