Trim tab retention system, an aircraft employing same and a method of retaining a trim tab within a blade housing

An aircraft comprising:

• a fuselage;
• an engine in operable communication with the fuselage;
• and
• a rotor assembly in operable communication with the engine having at least one rotor blade, the rotor blade including a blade housing having a cavity connected to an opening extending from the cavity out a trailing edge of the blade housing, the cavity having a first dimension which is greater than a second dimension of the opening at a same spanwise location of the blade housing;
• and
• a trim tab including a trim portion, a head portion having a head dimension substantially similar to the first dimension, and a tail portion connecting the trim portion and the head portion, the tail portion having a tail dimension substantially similar to the second dimension such that the trim tab is retainable by the blade housing when the head portion is disposed within the cavity and the tail portion is disposed within the opening;
• wherein the blade housing is elastically deformable to permit the head portion to pass through the second portion of the cavity.