Abstract: A seal retention and anti-rotation locking assembly (20) is positioned within an aircraft wheel hub (10). The wheel hub (10) has a groove (26) disposed about the periphery of a central opening (12), the groove (26) receiving therein a complementary shaped single retaining ring (32). The retaining ring (32) is a split ring having first (33) and second (37) ends located adjacent one another. The first end (33) has a first increased axial width portion (34) with a recess (35) located therein and extending at an acute angle relative to a radius of the central opening (12). The second end (37) has a second increased axial width portion (38) located radially inwardly from the outer diameter (45) of the retaining ring (32) such that the second increased axial width portion (38) is located exteriorly of the groove (26). The groove (26) includes an enlarged axial portion (28) shaped complementary with and receiving the first increased axial width portion (34) to anchor circumferentially the retaining ring.

Abstract: A seal retention and anti-rotation locking assembly (20) positioned within an aircraft wheel hub (10). The wheel hub (10) has a plurality of eccentric grooves (24) disposed about the periphery of an opening (12), the eccentric grooves (24) receiving therein complementary-shaped retaining ring segments (22). A grease seal (40) extends between the periphery of the opening (12) and an axle member (14), and is anchored securely by means of the retaining ring segments (22) and fasteners (28). The eccentric shape of the grooves (24) prevents deformation of the retaining ring segments (22) and release of the seal (40) while maintaining grease at bearings (16) located between the hub (10) and axle member (14).