# US 11,305,862 B2 · Joint joining an aircraft wing to an aircraft body > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 11,305,862 B2 - Document ID: US11305862B2 - Status: Granted - Kind: B2 - Application number: 16/722,186 - Filed: 2019-12-20 - Published: 2021-06-24 - Granted: 2022-04-19 - Earliest claimed: 2019-12-20 - Assignees: The Boeing Company - Applicants: The Boeing Company - Inventors: Mark R. McLaughlin; Jenny Young; Drew-Daniel T. Keefe; Charles B. Lockin; David H. Leibov - Web page: https://patentgrep.com/patent/US11305862B2 ## CPC - B64F 5/10: Manufacturing or assembling aircraft, e.g. jigs therefor - B64C 1/069: {Joining arrangements therefor} - B64C 1/12: Construction or attachment of skin panels - B64C 1/26: Attaching the wing or tail units or stabilising surfaces - B64C 2001/0072: {from composite materials} - B64C 2001/0081: {from metallic materials} - B64F: GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR - B64C: AEROPLANES; HELICOPTERS ## Abstract A joint joining an aircraft wing to an aircraft body employs a splice panel that is engaged in surface engagement with a skin panel on a side of the aircraft body and is engaged in surface engagement with a leg panel extending upwardly from the aircraft wing. A plurality of fasteners extend through the splice panel and the leg panel and extend through the splice panel and the skin panel. The plurality of fasteners attach the splice panel to the skin panel and attach the splice panel to the leg panel and thereby attach the skin panel to the leg panel. After fastener holes have been drilled through the splice panel and the leg panel to attach the splice panel to the leg panel, the splice panel can be removed from the leg panel. This provides easy access to the fastener holes drilled through the leg panel for deburring of the fastener holes. ## Claims ### Claim 1 A joint joining an aircraft wing to an aircraft body, the joint comprising: a skin panel on a side of the aircraft body; a leg panel extending upwardly from the aircraft wing; a splice panel attached to the leg panel and attached to the skin panel; and, a plurality of fasteners extending through the splice panel and the leg panel and extending through the splice panel and the skin panel, the plurality of fasteners attach the splice panel to the leg panel and attach the splice panel to the skin panel. ### Claim 2 (depends on 1) The joint of claim 1, further comprising: the splice panel engaging in surface engagement with the leg panel and engaging in surface engagement with the skin panel. ### Claim 3 (depends on 1) The joint of claim 1, further comprising: the leg panel and the skin panel are positioned in a single vertically oriented plane. ### Claim 4 (depends on 1) The joint of claim 1, further comprising: the leg panel has a top edge; the skin panel has a bottom edge; and, the bottom edge of the skin panel is positioned directly opposite and above the top edge of the leg panel. ### Claim 5 (depends on 1) The joint of claim 1, further comprising: the splice panel is a first splice panel engaged in engagement with the leg panel and engaged in engagement with the skin panel; a second splice panel is engaged in engagement with the leg panel and is engaged in engagement with the skin panel; the plurality of fasteners extend through the first splice panel and the leg panel and extend through the first splice panel and the skin panel; and, the plurality of fasteners extend through the second splice panel and the leg panel and extend through the second splice panel and the skin panel, the plurality of fasteners attach the first splice panel to the leg panel and attach the first splice panel to the skin panel and the plurality of fasteners attach the second splice panel to the leg panel and attach the second splice panel to the skin panel and thereby attach the skin panel to the leg panel. ### Claim 6 (depends on 1) The joint of claim 1, further comprising: the plurality of fasteners are removable from extending through the splice panel and the leg panel and from extending through the splice panel and the skin panel to detach the splice panel from the leg panel and detach the splice panel from the skin panel. ### Claim 7 (depends on 1) The joint of claim 1, further comprising: the leg panel is constructed of one of a metallic material and a composite material; the skin panel is constructed of one of a metallic material and a composite material; and, the splice panel is constructed of one of a metallic material and a composite material. ### Claim 8 (depends on 1) The joint of claim 1, further comprising: the skin panel is an external, fuselage skin panel. ### Claim 9 (depends on 1) The joint of claim 1, further comprising: the plurality of fasteners include pairs of vertically spaced upper fasteners extending through the splice panel and the skin panel and pairs of vertically spaced lower fasteners extending through the splice panel and the leg panel. ### Claim 10 (depends on 9) The joint of claim 9, further comprising: the pairs of vertically spaced upper fasteners and the pairs of vertically spaced lower fasteners are positioned in a single vertically oriented plane. ### Claim 11 A joint joining an aircraft wing to an aircraft body, the joint comprising: an aircraft body; an aircraft wing, the aircraft wing having a top surface and an opposite bottom surface; a skin panel on a side of the aircraft body, the skin panel having an exterior surface that is directed toward an exterior of the aircraft body and an opposite interior surface that is directed toward an interior of the aircraft body; a leg panel extending upwardly from the top surface of the aircraft wing, the leg panel having an exterior surface directed toward the exterior of the aircraft body and an opposite interior surface directed toward the interior of the aircraft body; a splice panel, the splice panel having an exterior surface and an opposite interior surface, the interior surface of the splice panel engaging in engagement with the exterior surface of the leg panel and engaging in engagement with the exterior surface of the skin panel; and, a plurality of fasteners extending through the splice panel and the leg panel and extending through the splice panel and the skin panel, the plurality of fasteners attaching the splice panel to the leg panel and attaching the splice panel to the skin panel and thereby attaching the skin panel to the leg panel. ### Claim 12 (depends on 11) The joint of claim 11, further comprising: the interior surface of the splice panel engaging in surface engagement with the exterior surface of the leg panel and the interior surface of the splice panel engaging in surface engagement with the exterior surface of the skin panel. ### Claim 13 (depends on 11) The joint of claim 11, further comprising: the skin panel and the leg panel are positioned in a single vertically oriented plane. ### Claim 14 (depends on 11) The joint of claim 11, further comprising: the leg panel has a top edge defined by a top edge surface that extends between the exterior surface of the leg panel and the interior surface of the leg panel; the skin panel has a bottom edge defined by a bottom edge surface that extends between the exterior surface of the skin panel and the interior surface of the skin panel; and, the bottom edge surface of the skin panel is positioned directly opposite and above the top edge surface of the leg panel. ### Claim 15 (depends on 11) The joint of claim 11, further comprising: the splice panel is a first splice panel having an exterior surface directed away from the aircraft body and an opposite interior surface, the interior surface of the first splice panel engaging in engagement with the exterior surface of the leg panel and engaging in engagement with the exterior surface of the skin panel; a second splice panel, the second splice panel having an exterior surface directed away from the aircraft body and an opposite interior surface, the interior surface of the second splice panel engaging in engagement with the exterior surface of the leg panel and engaging in engagement with the exterior surface of the skin panel; and, the plurality of fasteners extending through the first splice panel and the leg panel and extending through the first splice panel and the skin panel, the plurality of fasteners extending through the second splice panel and the leg panel and extending through the second splice panel and the skin panel, the plurality of fasteners attaching the first splice panel and the second splice panel to the leg panel and the skin panel and thereby attaching the skin panel to the leg panel. ### Claim 16 (depends on 11) The joint of claim 11, further comprising: the plurality of fasteners are removable from extending through the splice panel and the leg panel and from extending through the splice panel and the skin panel to detach the splice panel from the leg panel and detach the splice panel from the skin panel. ### Claim 17 (depends on 11) The joint of claim 11, further comprising: the leg panel is constructed of one of a metallic material and a composite material; the skin panel is constructed of one of a metallic material and a composite material; and, the splice panel is constructed of one of a metallic material and a composite material. ### Claim 18 (depends on 11) The joint of claim 11, further comprising: the skin panel is an external, fuselage skin panel. ### Claim 19 A method of joining an aircraft wing to an aircraft body, the method comprising: positioning a skin panel on a side of an aircraft body directly opposite and above a leg panel extending upwardly from an aircraft wing; positioning a splice panel in engagement with the leg panel and in engagement with the skin panel; and, positioning a plurality of fasteners extending through the splice panel and the leg panel and extending through the splice panel and the skin panel with the plurality of fasteners attaching the splice panel to the leg panel and attaching the splice panel to the skin panel. ### Claim 20 (depends on 19) The method of claim 19, further comprising: positioning a bottom edge of the skin panel directly opposite and above a top edge of the leg panel; positioning the splice panel in engagement with the leg panel and in engagement with the skin panel over the bottom edge of the skin panel and over the top edge of the leg panel; and, positioning the plurality of fasteners extending through the splice panel and the leg panel and extending through the splice panel and the skin panel with the plurality of fasteners attaching the splice panel to the leg panel and attaching the splice panel to the skin panel over the bottom edge of the skin panel and over the top edge of the leg panel.