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A seal assembly is provided for sealing an interface between a shaft and a bore formed in a firewall, where the shaft has an annular foot extending radially outward therefrom and a flowpath extending therethrough in fluid communication with the bore. The assembly includes a flexible annular seal, a

A seal assembly is provided for sealing an interface between a shaft and a bore formed in a firewall, where the shaft has an annular foot extending radially outward therefrom and a flowpath extending therethrough in fluid communication with the bore. The assembly includes a flexible annular seal, a ring, and a plurality of retainers.

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I claim: 1. A seal assembly for sealing an interface between a shaft and a bore formed in a firewall, the shaft having an annular foot extending radially outward therefrom, and a flowpath extending therethrough in fluid communication with the bore, the assembly comprising: a flexible annular seal c

I claim: 1. A seal assembly for sealing an interface between a shaft and a bore formed in a firewall, the shaft having an annular foot extending radially outward therefrom, and a flowpath extending therethrough in fluid communication with the bore, the assembly comprising: a flexible annular seal configured to be disposed concentric to the annular foot, the seal having an inner wall coupled to an outer wall to define a space therebetween, the inner wall having a first and a second flange extending radially inward therefrom, the first and second flanges spaced apart for receiving the annular foot therebetween; a ring disposed concentric to the annular seal, the ring having a sidewall and an annular engagement flange, the sidewall contacting the annular seal and supplying a force against the seal to provide a leak tight fit between the annular seal and the ring, the annular engagement flange extending radially outward from the sidewall; and a plurality of retainers disposed at predetermined locations around the ring, each retainer having a firewall contact section coupled to a ring contact section, the firewall contact section adapted to couple to the firewall and the ring contact section coupled to the annular engagement flange. 2. The seal assembly of claim 1, wherein the flexible annular seal is toroidally-shaped. 3. The seal assembly of claim 1, wherein the inner and outer walls are constructed of a flexible material and are coupled together to allow lateral movement of the shaft. 4. The seal assembly of claim 3, wherein the flexible annular seal comprises fireproof material. 5. The seal assembly of claim 1, wherein the inner wall is constructed of a flexible material and the inner and outer walls are coupled together to allow lateral movement of the shaft. 6. The seal assembly of claim 1, wherein the ring sidewall includes a flare section at one end, the flare section extending radially outward at an angle. 7. The seal assembly of claim 6, wherein the ring sidewall and the seal each has a height and the ring sidewall height is less than the seal height. 8. The seal assembly of claim 1, wherein the plurality of retainers further comprises a first, a second, and a third retainer. 9. The seal assembly of claim 8, wherein the first, second, and third retainers vary in length. 10. The seal assembly of claim 8, wherein the first and second retainers are shorter than the third retainer. 11. The seal assembly of claim 1, wherein the ring contact section and the firewall define a gap therebetween and the engagement flange is disposed within the gap. 12. The seal assembly of claim 11, wherein the plurality of retainers are each positioned to allow lateral movement of the ring within each of the gaps of each of the ring contact sections. 13. An aircraft firewall comprising: a housing having a wall defining a cavity and a bore formed in the cavity; a shaft having an annular foot extending radially outward therefrom and a flowpath extending therethrough in fluid communication with the bore; a flexible annular seal disposed concentric to the annular foot, the seal having an inner wall coupled to an outer wall to define a space therebetween, the inner wall having a first and a second flange extending radially inward therefrom, the first and second flanges spaced apart and receiving the annular foot therebetween; a ring disposed concentric to the annular seal, the ring having a sidewall and an annular engagement flange, the sidewall contacting the annular seal and supplying a force against the seal to provide a leak tight fit between the seal and ring, the annular engagement flange extending radially outward from the sidewall; and a plurality of retainers disposed at predetermined locations around the ring, each retainer having a firewall contact section coupled to a ring contact section, the firewall contact section coupled to the housing wall and the ring contact section coupled to the annular engagement flange. 14. The aircraft firewall of claim 13, wherein the flexible annular seal is toroidally-shaped. 15. The aircraft firewall of claim 13, wherein the inner and outer walls are constructed of a flexible material and are coupled together to allow lateral movement of the shaft. 16. The aircraft firewall of claim 15, wherein the flexible annular seal comprises fireproof material. 17. The aircraft firewall of claim 13, wherein the inner wall is constructed of a flexible material and the inner and outer walls are coupled together to allow lateral movement of the shaft. 18. The aircraft firewall of claim 13, wherein the ring sidewall includes a flare section at one end, the flare section extending radially outward at an angle. 19. The aircraft firewall of claim 18, wherein the ring sidewall and the seal each has a height and the ring sidewall height is less than the seal height. 20. The aircraft firewall of claim 13, wherein the plurality of retainers further comprises a first, a second, and a third retainer. 21. The aircraft firewall of claim 20, wherein the first, second, and third retainers vary in length. 22. The aircraft firewall of claim 20, wherein the first and second retainers are shorter than the third retainer. 23. The aircraft firewall of claim 13, wherein the housing wall is a firewall. 24. The aircraft firewall of claim 13, wherein the ring contact section and the firewall define a gap therebetween and the engagement flange is disposed within the gap. 25. The aircraft firewall of claim 24, wherein the plurality of retainers are each positioned to allow lateral movement of the ring within each of the spaces of each of the ring contact sections. 26. A thrust reverser system comprising: a housing having a bore formed therein; an actuator head support coupled to the housing, the actuator head support having an annular foot extending radially outward therefrom and a flowpath extending therethrough in fluid communication with the bore; and a seal assembly coupled to the actuator head support and the housing, the seal assembly comprising: a flexible annular seal disposed concentric to the annular foot, the seal having an inner wall coupled to an outer wall to define a space therebetween, the inner wall having a first and a second flange extending radially inward therefrom, the first and second flanges spaced apart and receiving the annular foot therebetween; a ring disposed concentric to the annular seal, the ring having a sidewall and an annular engagement flange, the sidewall contacting the annular seal and supplying a force against the seal to provide a leak tight fit between the seal and ring, the annular engagement flange extending radially outward from the sidewall; and a plurality of retainers disposed at predetermined locations around the ring, each retainer having a firewall contact section coupled to a ring contact section, the firewall contact section coupled to the housing wall and the ring contact section coupled to the annular engagement flange. 27. The thrust reverser system of claim 26, wherein the flexible annular seal is toroidally-shaped. 28. The thrust reverser system of claim 26, wherein the inner and outer walls are constructed of a flexible material and are coupled together to allow lateral movement of the shaft. 29. The thrust reverser system of claim 28, wherein the flexible annular seal comprises fireproof material. 30. The thrust reverser system of claim 26, wherein the inner wall is constructed of a flexible material and the inner and outer walls are coupled together to allow lateral movement of the shaft. 31. The thrust reverser system of claim 26, wherein the ring sidewall includes a flare section at one end, the flare section extending radially outward at an angle. 32. The thrust reverser system of claim 31, wherein the ring sidewall and the seal each has a height and the ring sidewall height is less than the seal height. 33. The thrust reverser system of claim 26, wherein the plurality of retainers further comprises a first, a second, and a third retainer. 34. The thrust reverser system of claim 33, wherein the first, second, and third retainers vary in length. 35. The thrust reverser system of claim 33, wherein the first and second retainers are shorter than the third retainer. 36. The thrust reverser system of claim 26, wherein the housing wall is a firewall. 37. The thrust reverser system of claim 26, wherein the ring contact section and the firewall define a gap therebetween and the engagement flange is disposed within the gap. 38. The thrust reverser system of claim 37, wherein the plurality of retainers are each positioned to allow lateral movement of the ring within each of the spaces of each of the ring contact sections.