# US 2016/0355273 A1 · Quick installation fuel dam > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 2016/0355273 A1 - Document ID: US20160355273A1 - Status: Published application - Kind: A1 - Application number: 14/729,685 - Filed: 2015-06-03 - Published: 2016-12-08 - Earliest claimed: 2015-06-03 - Assignees: The Boeing Company - Applicants: The Boeing Company - Inventors: Fernando L. Perez Diaz; Richard Tanner; Brendamari Rodriguez - Web page: https://patentgrep.com/patent/US20160355273A1 ## CPC - B64D 37/08: Internal partitioning - B64C 3/187: {Ribs} - B64C 3/34: Tanks constructed integrally with wings, e.g. for fuel or water - Y02T 50/40: Weight reduction - B64D: EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT - B64C: AEROPLANES; HELICOPTERS - Y02T: CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION ## Abstract The disclosure generally relates to baffle fuel dams and tank boundary fuel dams having a single-piece or two-piece construction. In one example, a baffle fuel dam is a single piece having slotted holes sized and spaced to accommodate for tolerance variations during installation. The baffle fuel dams also include a base angle that allows installation at multiple locations. The disclosure also relates to tank boundary fuel dams that include a two-piece configuration which incorporates slotted holes to accommodate tolerance variations and that are sized/spaced for different installation locations. The tank boundary fuel dams may also include a base angle that allows installation at multiple locations. ## Claims ### Claim 1 A fuel dam for a fuel tank of an aircraft, the fuel tank including a plurality of reservoirs separated by ribs having intersections for accommodating stringers, the fuel dam comprising a planar body including: a first leg portion and a second leg portion; and a bridge portion connecting the leg portions and defining a recess between the first and second leg portions such that when the fuel dam is installed in the fuel tank at one of the intersections, the recess is disposed about a stringer in a substantially interference fitting relationship between the first and second leg portions. ### Claim 2 (depends on 1) The fuel dam of claim 1, wherein the planar body further includes a plurality of openings formed through the first and second leg portions such that the first and second leg portions are attachable to a rib at an intersection to minimize deflection of the body. ### Claim 3 (depends on 2) The fuel dam of claim 2, wherein one of the first or second leg portions has an angled lower surface so as to prevent interference with fuel tank structures when the fuel dam is installed in a fuel tank. ### Claim 4 (depends on 3) The fuel dam of claim 3, wherein one of the first or second leg portions includes a notch formed at the angled lower surface of the first or second leg portion at or near the recess such that when the fuel dam is disposed about a stringer, the notch is able to accommodate a fillet of the stringer. ### Claim 5 (depends on 2) The fuel dam of claim 2, wherein the planar body comprises a non-conductive material. ### Claim 6 A tank boundary fuel dam, comprising: a first seal member comprising a plate portion and a bracket extending perpendicularly from the plate portion, the plate portion having a first plurality of elongated openings formed therein, the bracket comprising: a central portion; a cap portion disposed at a first end of the central portion; and a first lower support disposed at a second end of the central portion opposite the first end; and a second seal member comprising a rib plate having a second plurality of elongated openings therein and a stringer plate positioned perpendicular to the rib plate. ### Claim 7 (depends on 6) The tank boundary fuel dam of claim 6, wherein the fuel dam comprises a non-conductive material. ### Claim 8 (depends on 6) The tank boundary fuel dam of claim 6, wherein the first lower support forms an acute angle with the central portion. ### Claim 9 (depends on 6) The tank boundary fuel dam of claim 6, further comprising a second lower support coupled to the rib plate and the stringer plate, the second lower support forming an acute angle with respect to the stringer plate. ### Claim 10 (depends on 8) The tank boundary fuel dam of claim 8, wherein each of the first lower support and the second lower support are L-shaped. ### Claim 11 (depends on 10) The tank boundary fuel dam of claim 10, wherein another opening is formed through the stringer plate. ### Claim 12 (depends on 6) The tank boundary fuel dam of claim 6, wherein an opening is formed through the central portion. ### Claim 13 (depends on 6) The tank boundary fuel dam of claim 6, wherein the rib plate includes a recess on a back surface thereof. ### Claim 14 (depends on 6) The tank boundary fuel dam of claim 6, wherein the first lower support is coupled to the plate portion. ### Claim 15 An aircraft wing comprising: a plurality of spars; a plurality of stringers; a plurality of ribs running generally parallel to the fuselage of the aircraft, said ribs being coupled between opposing spars and having openings to accommodate said stringers; a plurality of fuel dams being disposed on the intersection of the ribs and the stringers, said fuel dams comprising: a planar body, the planar body comprising: a first leg portion having an angled lower surface; a second leg portion having an angled lower surface; a plurality of elongated openings formed through the planar body and; a bridge portion connecting the first leg portion to the second leg portion; wherein a first recess is defined between the first leg portion and the second leg portion. ### Claim 16 (depends on 14) The aircraft fuel tank system of claim 14, wherein the angled lower surface of the first and second leg portions are angled such as to prevent interference when the fuel dam is disposed on a wing panel. ### Claim 17 (depends on 15) The aircraft fuel tank system of claim 15, wherein the planar body of the fuel dam comprises a non-conductive material. ### Claim 18 (depends on 1) A method of forming a fuel tank in an aircraft wing, the method comprising: disposing a rib to accommodate a stringer at an intersection; and installing the fuel dam of claim 1 at the intersection such that the fuel dam forms an interference fit with the stringer. ### Claim 19 (depends on 6) A method of forming a fuel tank in an aircraft wing, the method comprising: disposing a rib to accommodate a stringer at an intersection; and installing the fuel dam of claim 6 at the intersection such that the fuel dam forms an interference fit with the stringer.