Patent ID: 9359073
Filing Date: 2016-06-07
CPC Classification: B64C,F16C

Claim Text:
1. An aircraft tail rotor system, comprising: a tail rotor shaft; a pitch change servo rod; a bearing assembly including a first bearing arranged in series relative to and spaced from a second bearing, the first bearing including a first raceway, a second raceway, and a plurality of bearing arranged therebetween, the first raceway being rotatable with and movable within the tail rotor shaft in accordance with translational movement of the pitch change servo rod, the second bearing including an third raceway, a fourth raceway and a plurality of bearings arranged therebetween; a connection non-rotatably coupling the third raceway of the second bearing and the first raceway of the first bearing; and a lock coupled to the second bearing, the lock selectively preventing rotation of the third raceway relative to the fourth raceway, the lock being configured to directly and independently respond to a seizing of the first bearing at the second bearing from a transmission of rotation of the first bearing to the second bearing and to selectively use the second bearing to prevent transmission of rotational energy from the tail rotor shaft to the pitch change servo rod in an event of the seizing of the first bearing.