Fan drive gear system module and inlet guide vane coupling mechanism

A gas turbine engine comprising:

• a fan arranged in a bypass flow path and including a plurality of fan blades rotatable about an axis, wherein the fan is arranged in a fan section having an outer housing, wherein the outer housing surrounds the fan to define a bypass duct that provides the bypass flow path;
• an on-wing portion including:
• a compressor section;
• a combustor in fluid communication with the compressor section;
• a turbine section in fluid communication with the combustor;
• a core flow path arranged within a core nacelle, the fan arranged upstream from the core flow path, the compressor section is configured to draw air in the a core flow path where air is compressed and communicated to the combustor;
• a fan drive gear system module coupled to the turbine section for rotating the fan about the axis;
• and
• a connector assembly including first and second members respectively secured to the on-wing portion and the fan drive gear system module, the first and second members removably secured to one another by radially extending fasteners, wherein the first members are connected to the on-wing portion of the gas turbine engine, and the second members are connected to the fan drive gear system module, wherein the fasteners are accessible through the core flow path.