# US 11,027,823 B2 · Holding device for an aircraft actuator > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 11,027,823 B2 - Document ID: US11027823B2 - Status: Granted - Kind: B2 - Application number: 16/025,415 - Filed: 2018-07-02 - Published: 2019-01-10 - Granted: 2021-06-08 - Earliest claimed: 2017-07-04 - Assignees: Airbus Operations GmbH - Applicants: Airbus Operations GmbH - Inventors: Marko Martens - Web page: https://patentgrep.com/patent/US11027823B2 ## CPC - B64C 13/30: using cable, chain, or rod mechanisms - B64C 13/42: having duplication or stand-by provisions - B64C 9/02: Mounting or supporting thereof - F15B 15/26: Locking mechanisms - B64C 13/40: using fluid pressure - B64C: AEROPLANES; HELICOPTERS - F15B: SYSTEMS ACTING BY MEANS OF FLUIDS IN GENERAL; FLUID-PRESSURE ACTUATORS, e.g. SERVOMOTORS; DETAILS OF FLUID-PRESSURE SYSTEMS, NOT OTHERWISE PROVIDED FOR ## Abstract A holding device for an aircraft actuator, comprising a body that extends between a lug configured to hingedly connect the holding device to a actuator support body and an attachment flange configured to fixedly attach the holding device to a landing provided by a main body of an actuator. The holding device is configured to prevent movement of the actuator from a normal working position relative to the actuator support body in the event of structural failure of a connection body of the actuator. ## Claims ### Claim 1 An aircraft actuator assembly, comprising: an actuator comprising a main body and a connection body; a holding device comprising a body that extends between an attachment flange and a lug, wherein the attachment flange is configured to be fixedly attached to a corresponding landing provided by the main body of the actuator and the lug is configured to be hingedly connected to an actuator support body; the connection body being provided with a further lug configured to hingedly connect the actuator to the actuator support body; wherein the holding device is configured to prevent movement of the actuator from a normal working position relative to the actuator support body in an event of structural failure of the connection body; and wherein the attachment flange and corresponding landing form a lap joint when fixedly attached to one another by a shear type fastener. ### Claim 2 (depends on 1) The aircraft actuator assembly according to claim 1, wherein the actuator support body forms a clevis configured to receive the lug of the holding device and the further lug of the connection body. ### Claim 3 (depends on 1) The aircraft actuator assembly according to claim 1, comprising more than one holding device. ### Claim 4 (depends on 3) The aircraft actuator assembly according to claim 3, comprising a pair of holding devices, each holding device positioned at opposing sides of the connection body. ### Claim 5 (depends on 1) A kit of parts comprising an actuator and the holding device according to claim 1. ### Claim 6 An aircraft actuator comprising: a main body, and a connection body, wherein the main body is provided with a landing configured to receive an attachment flange of a holding device and the connection body is provided with a lug configured to hingedly connect the actuator to an actuator support body; wherein the holding device is configured to prevent movement of the actuator from a normal working position relative to the actuator support body in an event of structural failure of the connection body; and wherein the attachment flange and corresponding landing form a lap joint when fixedly attached to one another by a shear type fastener. ### Claim 7 (depends on 6) The aircraft actuator according to claim 6, comprising more than one landing, wherein each landing is configured to receive a corresponding attachment flange of a holding device. ### Claim 8 (depends on 6) The aircraft actuator according to claim 6, wherein the connection body further comprises a spigot configured to engage a corresponding receiving hole formed by a body of the holding device. ### Claim 9 A holding device for an aircraft actuator, comprising: a body that extends between a lug, configured to hingedly connect the holding device to an actuator support body, and an attachment flange configured to fixedly attach the holding device to a landing provided by a main body of an actuator; wherein the holding device is configured to prevent movement of the actuator from a normal working position relative to the actuator support body in an event of structural failure of a connection body of the actuator; and wherein the attachment flange and corresponding landing form a lap joint when fixedly attached to one another by a shear type fastener. ### Claim 10 (depends on 9) The holding device according to claim 9, wherein the lug is configured to be received within a clevis formed by an actuator support body. ### Claim 11 (depends on 9) The holding device according to claim 9, comprising a unitary body formed from aviation grade titanium alloy. ### Claim 12 (depends on 9) The holding device according to claim 9, wherein the attachment flange extends substantially perpendicular from the body of the holding device. ### Claim 13 (depends on 9) The holding device according to claim 9, wherein the body further comprises a receiving hole configured to receive a corresponding spigot formed by a connection body of an actuator. ### Claim 14 (depends on 9) The holding device according to claim 9, wherein the lug is configured to have an inner diameter offset of between 0.5 mm and 3 mm from an adjacent attachment element.