Methods and apparatus for assembling gas turbine engines

A gas turbine engine comprising:

• an engine frame comprising an outer band, an inner band, and a plurality of circumferentially-spaced apart struts extending radially therebetween, said plurality of struts formed integrally with said outer and inner bands;
• and
• at least one fairing coupled around one of said plurality of struts such that a respective strut extends through said at least one fairing, said fairing formed as an integral single piece and comprising a first sidewall and a second sidewall connected together at a leading edge and a trailing edge such that at least one cooling chamber is defined therebetween, said fairing further comprising at least one partition and at least one parting line, said at least one partition extending between said first and second sidewalls, said at least one parting line separating said fairing into a forward portion and a separate aft portion that are axially removable and coupled together;
• wherein said at least one parting line extends at least partially through each of said fairing partition opposing ends, such that a coupling joint is at least partially defined within each of said opposing ends, said parting line being defined by a tongue and groove joint.