# US 11,993,376 B2 · Trailing edge panel support with biasing arrangement > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 11,993,376 B2 - Document ID: US11993376B2 - Status: Granted - Kind: B2 - Application number: 17/703,653 - Filed: 2022-03-24 - Published: 2022-09-29 - Granted: 2024-05-28 - Earliest claimed: 2021-03-26 - Assignees: Airbus Operations GmbH - Applicants: Airbus Operations Ltd. - Inventors: William Tulloch - Web page: https://patentgrep.com/patent/US11993376B2 ## CPC - B64C 9/02: Mounting or supporting thereof - B64C 3/185: {Spars} - B64C 7/00: Structures or fairings not otherwise provided for - B64C 9/12: surfaces of different type or function being simultaneously adjusted - B64C 9/16: at the rear of the wing - B64C 9/18: by single flaps - B64C 9/20: by multiple flaps - B64C 13/34: using toothed gearing - B64F 5/10: Manufacturing or assembling aircraft, e.g. jigs therefor - B64C: AEROPLANES; HELICOPTERS - 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 ## Abstract A method of securing a lower trailing edge panel of an aircraft wing. The wing includes a wingbox with an upper cover, a lower cover, and a rear spar. A leading edge of the lower trailing edge panel is attached to the wingbox. A support structure is also attached to the wingbox and a connector is mounted to the trailing edge panel. A link is provided, with a first end and a second end. The second end of the link is pivotally attached to the support structure at a pivot joint. A biasing arrangement biases the link towards an upright orientation in which the first end of the link is higher than the pivot joint. The link is held in its upright orientation with the biasing arrangement; and then the first end of the link is attached to the connector. ## Claims ### Claim 1 A method of securing a lower trailing edge panel of an aircraft wing, the aircraft wing comprising: a wingbox with an upper cover, a lower cover, and a rear spar; a lower trailing edge panel with a leading edge, wherein the leading edge of the lower trailing edge panel is fixedly attached to the wingbox by passing fasteners through the lower trailing edge panel and the lower cover of the wingbox; a support structure attached to the wingbox; a link with a first end and a second end, wherein the second end of the link is pivotally attached to the support structure at a pivot joint; and a biasing arrangement which biases the link towards an upright orientation in which the first end of the link is higher than the pivot joint; the method comprising: holding the link in the upright orientation with the biasing arrangement; and then attaching the first end of the link to the lower trailing edge panel. ### Claim 2 (depends on 1) The method according to claim 1, wherein the first end of the link is directly above the pivot joint when the link is in the upright orientation. ### Claim 3 (depends on 1) The method according to claim 1, wherein: the biasing arrangement comprises a spring coupled to the link; and the spring holds the link in the upright orientation by applying a biasing force to the link. ### Claim 4 (depends on 1) The method according to claim 1, wherein the link is in the upright orientation when the first end of the link is attached to the lower trailing edge panel. ### Claim 5 (depends on 1) The method according to claim 1, wherein the link is not in the upright orientation when the first end of the link is attached to the lower trailing edge panel; the method further comprising: before attaching the first end of the link to the connector, rotating the link about the pivot joint away from the upright orientation so the first end of the link moves down and into alignment with the connector; wherein the biasing arrangement applies a biasing force to the link which opposes a rotation of the link about the pivot joint away from the upright orientation. ### Claim 6 (depends on 1) The method according to claim 1, wherein: the trailing edge panel comprises a connector; and the first end of the link is attached to the connector. ### Claim 7 (depends on 6) The method according to claim 6, wherein the connector protrudes from an upper face of the lower trailing edge panel. ### Claim 8 (depends on 1) The method according to claim 1, wherein the support structure is attached to the lower cover. ### Claim 9 (depends on 1) The method according to claim 1, wherein the first end of the link is higher than the pivot joint as the first end of the link is attached to the lower trailing edge panel. ### Claim 10 An aircraft wing comprising: a wingbox with an upper cover, a lower cover, and a rear spar; a lower trailing edge panel with a leading edge, wherein the leading edge of the lower trailing edge panel is fixedly attached to the wingbox by fasteners that pass through the lower trailing edge panel and the lower cover of the wingbox; a support structure attached to the wingbox; a link which extends from a first end to a second end, wherein: the first end of the link is attached to the lower trailing edge panel; the second end of the link is pivotally attached to the support structure at a pivot joint; and the link is in an upright orientation with the first end of the link higher than the pivot joint; and a biasing arrangement configured to bias the link towards the upright orientation. ### Claim 11 (depends on 10) The aircraft wing according to claim 10, wherein the first end of the link is directly above the pivot joint. ### Claim 12 An aircraft wing comprising: a wingbox with an upper cover, a lower cover, and a rear spar; a lower trailing edge panel with a leading edge, wherein the leading edge of the lower trailing edge panel is attached to the wingbox by fasteners that pass through the lower trailing edge panel and the lower cover of the wingbox; a support structure attached to the wingbox; a link which extends from a first end to a second end, wherein: the first end of the link is attached to the lower trailing edge panel; the second end of the link is pivotally attached to the support structure at a pivot joint; and the first end of the link is higher than the pivot joint; and a biasing arrangement configured for applying a biasing force to the link to bias the first end of the link up and away from the lower trailing edge panel. ### Claim 13 (depends on 12) The aircraft wing according to claim 12, wherein the biasing arrangement comprises a spring coupled to the link. ### Claim 14 (depends on 12) The aircraft wing according to claim 12, wherein: the pivot joint is a second pivot joint; and the first end of the link is attached to the lower trailing edge panel at a first pivot joint. ### Claim 15 (depends on 12) The aircraft wing according to claim 12, wherein: the lower trailing edge panel comprises a connector; and the first end of the link is attached to the connector. ### Claim 16 (depends on 12) The aircraft wing according to claim 12, comprising: a spoiler; and a spoiler stop protruding from an upper surface of the lower trailing edge panel; wherein the spoiler stop is configured to be contacted by the spoiler in an event of an over-travel failure of the spoiler. ### Claim 17 (depends on 12) The aircraft wing according to claim 12, wherein: the lower trailing edge panel comprises a trailing edge, an inboard edge and an outboard edge; the support structure comprises an inboard face and an outboard face; and either: the support structure is positioned inboard of the inboard edge of the trailing edge panel; and the link is pivotally attached to the inboard face of the support structure; or the support structure is positioned outboard of the outboard edge of the trailing edge panel; and the link is pivotally attached to the outboard face of the support structure. ### Claim 18 (depends on 12) The aircraft wing according to claim 12, comprising routings which run along the aircraft wing behind the rear spar in a spanwise direction. ### Claim 19 (depends on 18) A method of assembling or disassembling the aircraft wing of claim 18, the method comprising installing or removing the routings by moving the routings, transverse to a length of the routings, past the link.