Aircraft blade lock retainer

An engine fan assembly, comprising:

• a spinner having an aft flange and a spacer integral to the spinner;
• and
• a blade lock retainer coupled to the aft flange of the spinner, wherein the spacer is disposed between the aft flange of the spinner and the blade lock retainer, the blade lock retainer comprising:
• an annular ring portion,
• an outer retainer tab portion, disposed on an outer circumference of the annular ring portion, oriented substantially perpendicular to the annular ring portion, and extending in an aft direction from the annular ring portion, and
• an inner retainer tab portion, disposed on an inner circumference of the annular ring portion and radially aligned with the outer retainer tab portion, oriented substantially perpendicular to the annular ring portion, and extending in a forward direction from the annular ring portion, wherein the blade lock retainer is formed from sheet metal;
• a plurality of rivet apertures;
• and
• at least one bolt aperture disposed in the annular ring portion and radially aligned with the outer retainer tab portion and the inner retainer tab portion;
• at least one bolt, the blade lock retainer installable to a hub by the at least one bolt aperture, the at least one bolt aperture configured to receive the at least one bolt;
• at least one rivet, the blade lock retainer coupled to the aft flange of the spinner by at least one rivet aperture from the plurality of rivet apertures, the at least one rivet aperture configured to receive the at least one rivet.