Gas turbine fan drive gear system

A gear reduction for a gas turbine engine comprising:

• a plurality of intermediate gears;
• a single structure establishing a carrier centered on an axis and having a pair of axially spaced apart side walls, axially extending circumferentially spaced connecting structure for connecting the pair of side walls, a central opening in at least one of the side walls, and circumferentially spaced smaller openings spaced radially outwardly of the central opening, with internal surfaces of the circumferentially spaced connecting structure defining intermediate gear pockets that extend away from the central opening to the circumferentially spaced openings;
• wherein the intermediate gears are receivable through the central opening of the single structure and are secured in the intermediate gear pockets at a position spaced radially inwardly of a radially outermost area in the intermediate gear pockets;
• a ring gear including a first ring gear component and a second ring gear component, the first and second ring gear components placed on an outer periphery of the intermediate gears such that ring gear teeth of the first and second ring gear components engage with teeth of the intermediate gears;
• and
• a connection that secures the gear reduction to a propulsor shaft.