Patent ID: 8308149

Claim:
A shock and vibration isolator for hard mounting an aircraft brake control valve to a structural part of an aircraft, comprising: a radially inner generally spool shaped rigid insert portion defining a central aperture configured to receive a fastener for hard mounting of the brake control valve to the structural part of an aircraft, wherein said radially inner generally spool shaped rigid insert portion includes a first radially inner rigid tubular member and a second radially inner rigid tubular member that overlaps and interfits with the first radially inner rigid tubular member, and said first radially inner rigid tubular member includes an upper radially outwardly flared annular end portion and a lower tubular shaft portion, and said second radially inner rigid tubular member includes a lower radially outwardly flared end portion and an upper flange that overlaps and interfits with the lower tubular shaft portion of the first radially inner rigid tubular member; and a radially outer generally spool shaped vibration insulating sheath portion, wherein said outer generally spool shaped vibration insulating sheath portion comprises a first generally tubular radially outer vibration insulating sheath portion and a second generally tubular radially outer vibration insulating sheath portion that overlaps and interfits with the first generally tubular outer vibration insulating sheath portion; wherein said shock and vibration isolator has a natural frequency selected to protect a component of the aircraft brake control valve from damage from shock and vibration.