Clearance control system for blade outer air seal

An assembly for a turbine engine, comprising:

• a carrier extending circumferentially around an axis, the carrier including a cavity, a first section and a second section, the first section including a first inner flange and a first section mount extending radially inward from the first inner flange, the second section including a second inner flange and a second section mount extending radially inward from the second inner flange, the cavity formed within the carrier by the first section and the second section, the first section attached to the second section at a full-hoop inner seal interface located radially inboard of the cavity, the first section axially overlapping the second section at the full-hoop inner seal interface, and the first section further attached to the second section at a full-hoop outer seal interface located radially outboard of the cavity;
• a control ring extending circumferentially around the axis within the cavity;
• and
• a blade outer air seal mounted to the carrier via the first section mount and the second section mount;
• wherein the full-hoop inner seal interface comprises a lap joint between the first inner flange of the first section and the second inner flange of the second section, the lap joint is located axially between the first section mount and the second section mount, the first inner flange is attached to the second section at the full-hoop inner seal interface, and the second inner flange is attached to the first inner flange at the full-hoop inner seal interface.