Gas turbine engine geared architecture axial retention arrangement

A method of retrofitting a support assembly to a gas turbine engine having a geared architecture, comprising the steps of:

• providing attachment features in first and second structures;
• securing first and second members respectively to the first and second structures;
• arranging the first and second members in axially spaced relation to one another in an installed condition;
• and
• installing the first structure onto an engine static structure and a geared architecture onto the second structure.

A gas turbine engine comprising:

• an engine static structure;
• a flex support secured to the engine static structure and including a bellow;
• a support structure operatively secured to the flex support;
• a geared architecture mounted to the support structure;
• a fan section operatively coupled to the geared architecture;
• and
• first members removably secured to one of the engine static structure and the flex support, and second members removably secured to the support structure, the first and second members circumferentially aligned with one another and spaced apart from one another during a normal operating condition, and the first and second members configured to be engageable with one another during an extreme fan section event to limit axial movement of the geared architecture relative to the engine static structure.