Cage for hourglass roller bearings

1. A edge flap arrangement for an aircraft wing, the arrangement comprising:

a main flap element and an actuator for moving the main flap element relative to the wing; and

a linkage arrangement supporting the main flap element from the aircraft wing for movement relative to the wing, the linkage arrangement including a fixed strut secured to the aircraft wing and a drop link secured to the main flap, the fixed strut and the drop link being pivotally connected by a hinge point;

the hinge point comprising at least a first bearing, the first bearing comprising:

an outer race having at least one convex inner surface and an interior area;

an inner race having a convex outer surface, a portion of the inner race being disposed in the interior area;

a plurality of rollers disposed between the inner race and the outer race, each of the plurality of rollers having an hourglass shape and being in rolling engagement with the inner race and the outer race each of the rollers having an axial width; and

a cage disposed between the inner raceway and the outer raceway, the cage comprising:

an annular ring having a first axial face and a second axial face, a plurality of first rails extending a length from the first axial face and a plurality of second rails extending the length from the second axial face;

a plurality of pockets, each of the plurality of pockets defined by opposing circumferentially facing walls of at least one of adjacent pairs of the first rails and adjacent pairs of the second rails;

the circumferentially facing walls being concavely formed so that each of the plurality of pockets is cylindrical;

one of the plurality of rollers is rollingly engaged in each of the plurality of pockets; and

the length being of a magnitude greater than an axial width of an hourglass roller to be disposed in each of the plurality of pockets.

2. The edge flap arrangement of claim 1 , further comprising spherical pocket bottoms.

3. The edge flap arrangement of claim 1 , wherein the cage is manufactured from a bronze material.

4. The edge flap arrangement of claim 3 , wherein the bronze material is a high leaded tin bronze per ASTM B505.

5. The edge flap arrangement of claim 1 wherein the edge flap is for a trailing edge of a wing of an aircraft.

6. The edge flap arrangement of claim 1 wherein the aircraft is an Airbus A-350 aircraft.

7. The edge flap arrangement of claim 1 , further comprising at least one second hourglass bearing disposed in the actuator.

8. The edge flap arrangement of claim 1 wherein the hinge point comprises a plurality of first bearings.

9. The edge flap arrangement of claim 7 wherein the actuator comprises a plurality of second bearings.