# US 9,038,964 B2 · Control surface assembly > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 9,038,964 B2 - Document ID: US9038964B2 - Status: Granted - Kind: B2 - Application number: 13/513,219 - Filed: 2010-12-06 - Published: 2012-09-20 - Granted: 2015-05-26 - Earliest claimed: 2009-12-08 - Assignees: Airbus Operations GmbH - Applicants: Eric Wildman - Inventors: Eric Wildman - Web page: https://patentgrep.com/patent/US9038964B2 ## CPC - B64C 9/14: forming slots - B64C 9/20: by multiple flaps - B64C 9/323: {associated with wings} - B64C 2009/143: {comprising independently adjustable elements for closing or opening the slot between the main wing and leading or trailing edge flaps} - Y10T 29/49815: Disassembling - B64C: AEROPLANES; HELICOPTERS - Y10T: TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION ## Abstract An aerodynamic control surface assembly comprising: an aerodynamic control surface (4); an actuator (10) for controlling deployment of the control surface; and a locking mechanism (30) moveable from a locked to an unlocked position. When the locking mechanism is set to the locked position, the actuator is operatively coupled to the control surface and the control surface can move in dependently of the actuator when the locking mechanism is set to the unlocked position. Such an assembly may be used in an aircraft to prevent clashing between a deployed flap (16) and a drooped spoiler (4) in the event of an actuator control systems failure. ## Claims ### Claim 1 An aerodynamic control surface assembly comprising: a first aerodynamic control surface; a second aerodynamic control surface, said second control surface moveable at least between deployed and stowed positions; an actuator for controlling deployment of the first control surface; and a locking mechanism moveable from a locked to an unlocked position, wherein the actuator is operatively coupled to the first control surface when the locking mechanism is set to the locked position and the first control surface can move independently of the actuator when the locking mechanism is set to the unlocked position, wherein, said first control surface at least partially extends into the path of said second control surface when moving between said deployed and stowed positions, wherein, upon failure of the actuator to retract the first control surface during stowing of the second control surface, the locking mechanism, as a result of movement of said second control surface, unlocks said locking mechanism. ### Claim 2 (depends on 1) The control surface assembly of claim 1 wherein the locking mechanism is resettable. ### Claim 3 (depends on 1) The control surface assembly of claim 1 wherein the locking mechanism comprises a slidable bar which, when displaced releases the locking mechanism from the locked position to the unlocked position. ### Claim 4 (depends on 3) The control surface assembly of claim 3 wherein the locking mechanism further comprises an actuator bracket which is rotatably coupled to the actuator, the bracket comprising a projection engaging the slidable bar setting the locking mechanism to the locked position. ### Claim 5 (depends on 3) The control surface assembly of claim 3 wherein the slidable bar extends from the locking mechanism to a trailing edge of the first control surface. ### Claim 6 (depends on 1) The control surface assembly of claim 1 wherein the locking mechanism is biased towards the locked position. ### Claim 7 (depends on 1) An aircraft wing comprising the aerodynamic control surface assembly of claim 1, wherein said second aerodynamic control surface is positioned aft of the first control surface. ### Claim 8 (depends on 7) An aircraft wing according to claim 7 in which the locking mechanism is configured to be directly engaged by the second aerodynamic control surface to move from the locked position to the unlocked position. ### Claim 9 (depends on 7) The aircraft wing of claim 7 wherein the first aerodynamic control surface is a spoiler and the second aerodynamic control surface is a flap. ### Claim 10 A method of operatively decoupling a first aerodynamic control surface from an actuator for controlling deployment of the first control surface, a second aerodynamic control surface moveable between deployed and stowed positions, the actuator is operatively coupled to the first control surface by a locking mechanism when set to a locked position and the locking mechanism is moveable from the locked position to an unlocked position, the method comprising the steps of: moving the second control surface to a deployed position; moving, by actuation of said actuator, said first control surface at least partially extending into the path of said second control surface when moving between said deployed and stowed positions; whereupon failure of said actuator with said first control surface at least partially extending into said path, moving said second control surface toward a stowed position causes unlocking of the locking mechanism permitting the first control surface to move independently of the actuator. ### Claim 11 A method of operatively decoupling a first aerodynamic control surface from an actuator for controlling deployment of the first control surface, a second aerodynamic control surface moveable along a path between deployed and stowed positions, the actuator is coupled to the first control surface by a locking mechanism when set to a locked position, and the locking mechanism is moveable from the locked position to an unlocked position, wherein the second aerodynamic control surface is positioned aft of the first control surface, the method comprising the steps of: moving the second surface to the deployed position; moving, by actuation of said actuator, said first control surface to at least partially extend into said path; and upon failure of said actuator with said first control surface at least partially extending into said path, moving said second control surface toward the stowed position and thereby unlocking the locking mechanism allowing the first control surface to move independently of the actuator. ### Claim 12 (depends on 10) The method of claim 10 wherein the locking mechanism is unlocked in response to a failure of an actuator control system. ### Claim 13 (depends on 11) The method of claim 11 wherein the first control surface is moveable independently of the actuator to prevent jamming between the first and second control surfaces. ### Claim 14 (depends on 10) The method of claim 10 further comprising: moving the first control surface independently of the actuator; and retracting the second control surface into a position vacated by the first control surface. ### Claim 15 (depends on 10) The method of claim 10 further comprising displacing a slidable bar which extends from the locking mechanism to a trailing edge of the first control surface to unlock the locking mechanism. ### Claim 16 (depends on 15) The method of claim 15 wherein the locking mechanism comprises an actuator bracket which is rotatably coupled to the actuator, the bracket comprising a projection adapted to engage the slidable bar to set the locking mechanism to said locked position, the method comprising the step of displacing the slidable bar to disengage the projection from the bar to unlock the locking mechanism. ### Claim 17 (depends on 11) The method of claim 11 wherein the first control surface is moved independently of the actuator by air flow. ### Claim 18 (depends on 11) The method of claim 11 wherein the first and second aerodynamic control surfaces are mounted to an aircraft wing, the first aerodynamic control surface is a spoiler and the second aerodynamic control surface is a flap.