Pitch change mechanism for a fan of a gas turbine engine

A gas turbine engine comprising:

• a turbomachine comprising a compressor section, a combustion section, and a turbine section arranged in serial flow order;
• a fan defining a fan axis and comprising a plurality of fan blades rotatable about the fan axis;
• and
• a pitch change mechanism operable with the plurality of fan blades, the pitch change mechanism comprising
• a plurality of linkages, the plurality of linkages including a first linkage coupled to a first fan blade of the plurality of fan blades and a second linkage coupled to a second fan blade of the plurality of fan blades;
• a master control rotatable with the plurality of fan blades, wherein the first linkage is coupled to the master control and to the first fan blade, and wherein the second linkage is coupled to the master control and to the second fan blade, wherein the master control includes a pair of radial walls spaced from one another along an axial direction, and wherein the first linkage extends through the pair of radial walls;
• and
• a non-uniform blade actuator system operable with one or more of the plurality of linkages to control a pitch of the first fan blade relative to a pitch of the second fan blade, the non-uniform blade actuator system including a pitch ring that defines an interface surface configured to slidably contact the plurality of linkages.