Patent ID: 6951112

Claim:
A method for assembling a gas turbine engine, said method comprising: coupling a first structure within the gas turbine engine, wherein the first structure includes a plurality of closed-end sockets extending from a radially inner surface of the first structure; and coupling a second structure to the first structure by inserting a radial pin through the second structure and into each respective socket such that the first structure is aligned axially, circumferentially, and with respect to an engine centerline axis extending through the gas turbine engine; wherein the second structure also includes at least one second opening and the radial pin includes at least one opening, wherein said coupling a second structure to the first structure by inserting a pin through the second structure further comprises: inserting a fastener through the radial pin opening and through the second structure opening; and using the fastener to secure the radial pin to the first structure such that the second structure is aligned axially, circumferentially, and with respect to an engine centerline axis extending through the gas turbine engine.