Monolithic outboard gear beam support fitting

A breakaway support configured to selectively release an actuator from a fitting and a method of providing the breakaway support. The breakaway support includes a race positioned between the actuator and the fitting. The second end of the actuator is connected to the fitting via a ball joint is positioned within the race. The ball joint permits the actuator to pivot about the ball joint in a vertical plane between a first position and a second position. The breakaway support includes a first knuckle that causes the actuator to release from the fitting when the actuator moves in a first direction beyond the first position. A portion of the fitting or a second knuckle may cause the actuator to release from the fitting when the actuator moves in a second direction beyond the second position. A portion of the actuator may break to release the actuator from the fitting.

FIELD OF THE DISCLOSURE

The examples described herein relate to a monolithic outboard landing gear beam support fitting, and methods of providing a monolithic outboard landing gear beam support fitting.

BACKGROUND

Description of the Related Art

Aircraft include landing gear that may be extended for landing and takeoff and retracted into the aircraft during flight. An actuator is connected to the main landing gear trunnion of the aircraft and is used to extend and retract the landing gear. The actuator is connected to the wing rear spar via a first fitting, which may be referred to as a bridge fitting. A second fitting, which may be referred to as a mini cant fitting, connects a gear beam to the wing rear spar. The process of assembly the two separate fittings, the mini cant fitting and the bridge fitting, can be complicated as wing skin contour must be machined with the two fittings assembled together. Variances in the tolerances of the two fittings may combine to increase the difficulty of the assembly with the rear wing spar and wing skin contour.

A current design to connect the actuator to the wing rear spar uses a horizontally oriented fuse pin. The fuse pin is designed to shear and release the actuator from the wing rear spar upon the application of a high load due to an impact event. However, it may be beneficial to reduce the load required to release the actuator from the wing rear spar. As discussed above, the landing gear is typically connected to the wing rear spar of an aircraft by the fittings. Aircrafts may include a fuel tank located within the wing rear spar. Upon an impact load to the landing gear, the actuator and/or main landing gear trunnion may penetrate the fuel tank located within the rear wing spar, which is undesirable. It is desirable to have the fuel tank remain intact upon the application of an impact load being applied to the landing gear system. Other disadvantages of current flap deployment systems may exist.

SUMMARY

The present disclosure is directed to a breakaway support that is configured to release a landing gear actuator from a fitting when the actuator pivots past a first position or pivots past a second position. The actuator may pivot past either the first position or the second position due to an impact event. The selectively release of the landing gear actuator may decrease the probability of puncturing a fuel tank within the wing box of an aircraft.

One example of the present disclosure is a breakaway support comprising an actuator having a first end and a second end and a fitting. The breakaway support comprises a race positioned between the actuator and the fitting. The breakaway support includes a ball joint located within the race, the second end of the actuator being connected to the fitting via the ball joint. The ball joint is configured to permit the actuator to pivot about the ball joint in a vertical plane between a first position and a second position. The breakaway support includes a first knuckle. The first knuckle causes the actuator to release from the fitting when the actuator moves in a first direction beyond the first position.

The breakaway support may include a second knuckle that causes the actuator to release from the fitting when the actuator moves in a second direction beyond the second position. A portion of the actuator may be configured to break to release the actuator from the fitting when the actuator moves in the first direction beyond the first position or when the actuator moves in the second direction beyond the second position. The portion of the actuator configured to break may have a reduced outer diameter compared to an outer diameter of adjacent portions of the actuator.

The breakaway support may include a rod that connects the second end of the actuator to the ball joint. A portion of the rod may be configured to break to release the actuator from the fitting when the actuator moves in the first direction beyond the first position or when the actuator moves in the second direction beyond the second position. The portion of the rod configured to break may have a reduced outer diameter compared to an outer diameter of adjacent portions of the rod. The rod may be a unitary component of the ball joint. The first knuckle may be located on the rod and the second knuckle may be located on the rod. The first knuckle may be located on the fitting and the second knuckle may be located on the fitting. The first knuckle may be located on the actuator and the second knuckle may be located on the actuator.

The breakaway support may include a fastener and a nut coupling the second end of the actuator to the fitting via the ball joint, the fastener being positioned through an opening in the ball joint. The fastener may be oriented in a vertical direction along a central axis of the ball joint. The fitting may comprise an opening with the ball joint being positioned within the opening. The second end of the actuator may comprise a clevis with the opening of the fitting, the race, and the ball joint being positioned within the clevis. The clevis may include a first opening and a second opening. The fastener may pass through the first opening in the clevis, the race, the opening in the ball joint, and the second opening in the clevis to couple the second end of the actuator to the fitting via the ball joint. The first end of the actuator may be connected to a main landing gear trunnion of an aircraft. The actuator may be configured to retract and extend the landing gear of the aircraft.

One example of the present disclosure is a breakaway support system. The breakaway support system comprises a fitting having a first vertical wall, a second vertical wall that extends from the first vertical wall, and a cross member connected between the first vertical wall and the second vertical wall. The second vertical wall is perpendicular to the first vertical wall. The fitting includes a first opening in the cross member. The breakaway support system includes an actuator having a first end and a second end with the actuator being configured to retract and extend a landing gear of an aircraft. The breakaway support system comprises a race positioned within the first opening in the cross member. The breakaway support system includes a ball joint located within the race. The race is positioned between the second end of the actuator and the cross member. The ball joint is configured to permit the actuator to pivot about the ball joint in a vertical plane between a first positioned and a second position. The breakaway support system includes a first knuckle that causes the actuator to release from the fitting when the actuator moves in a first direction beyond the first position.

The cross member may be horizontal with respect to the first vertical wall and the second vertical wall. The breakaway support system may include a second knuckle that causes the actuator to release from the fitting when the actuator moves in a second direction beyond the second position. The first knuckle may extend from a top surface of the cross member and the second knuckle may extend from a bottom surface of the cross member. The actuator may comprise a breakaway portion configured to break to release the actuator from the fitting when the actuator moves in the first direction beyond the first position or when the actuator moves in the second direction beyond the second position.

The cross member may cause the actuator to release from the fitting when the actuator moves in a second direction beyond the second position. The second end of the actuator may comprise a clevis with the first opening of the cross member, the race, and the ball joint being positioned within the clevis. The breakaway support system may comprise a fastener and a nut to selectively connect the second end of the actuator to the fitting. The fastener may extend through the clevis, the race, and the ball joint and the fastener may be oriented parallel with the first vertical wall and the second vertical wall. The breakaway support system may include a second opening and a third opening in the first vertical wall of the fitting and a landing gear beam connected to the fitting via the second and third openings. The breakaway support system may include a fourth opening and a fifth opening in the second vertical wall of the fitting that may be configured to connect the fitting to a wing of the aircraft.

One example of the present disclosure is a method of providing a breakaway support of an aircraft. The method comprises providing an actuator having a first end and second end and providing a fitting. The method includes providing a race and positioning a ball joint within the race. The method comprises providing a first knuckle and connecting the second end of the actuator to the ball joint, which is configured to permit the actuator to pivot about the ball joint. The first knuckle is configured to release the actuator from the fitting when the actuator moves past a first positioned in a first direction.

A portion of the fitting may be configured to release the actuator from the fitting when the actuator moves past a second position in a second direction. The method may include providing a second knuckle configured to release the actuator from the fitting when the actuator moves past a second position in a second direction. The actuator may be release from the fitting by breaking a portion of the actuator. The second end of the actuator may be connected to the ball joint via a rod. The actuator may be released from the fitting by breaking a portion of the rod. The method may include selectively connecting the second end of the actuator to the ball joint by positioning a fastener through the second end of the actuator, the race, and the ball joint.

DETAILED DESCRIPTION

FIG. 1shows a schematic of one example of a breakaway support system100. The breakaway support system100includes an actuator150connected to a fitting110.FIG. 2shows a schematic front perspective view of one example of a fitting110andFIG. 3shows a schematic rear perspective view of one example of a fitting110. The fitting110includes a first wall120and a second wall130. The first wall120may be vertical oriented wall, herein referred to as a first vertical wall, and the second wall130may be vertically oriented wall, herein referred to as a second vertical wall. The second wall130is connected to and extends perpendicular from the first wall120. A cross member140is connected to both the first wall120and the second wall130. The cross member140may be positioned horizontal with respect to the first and second vertical walls120,130. The cross member140may be orientated substantially perpendicular to both first wall120and the second wall130. The fitting110includes a top plate111and a bottom plate112. The first wall120, second wall130, cross member140, top plate111, and bottom plate112may be formed together to form a unitary fitting110.

The cross member140includes a first, or top, surface141and a second, or bottom, surface142best shown inFIG. 2. The cross member140includes a first opening143best shown inFIG. 2. A first, or top, knuckle144extends from the top surface141of the cross member140. The first knuckle144is configured to selectively release the actuator150from the fitting110as discussed herein. A second, or bottom, knuckle145extends from the bottom surface142of the cross member140. The second knuckle145is configured to selectively release the actuator150from the fitting110as discussed herein.

The first wall120of the fitting110includes a second opening121and a third opening122best shown inFIG. 2. The second and third openings121,122are configured to enable the fitting110to be connected to a landing gear beam410(shown inFIG. 7). Fasteners (not shown) would be inserted through the second and third openings121,122to selectively connect the fitting110to the landing gear beam410as would be appreciated by one of ordinary skill in the art having the benefit of this disclosure. The backside of the first wall120may include a first flange123having openings124,125and a second flange126having openings127,128. The flanges123,126and openings124,125,127,128are configured as aircraft wing flap supports.

The second wall130of the fitting110includes a fourth opening131and a fifth opening132. The fourth and fifth openings131,132are configured to enable the fitting110to be connect to a wing of an aircraft. Specifically, fasteners (not shown) may be inserted through the fourth and fifth openings131,132to selectively connect the fitting110to a rear wing spar420(shown inFIG. 7) as would be appreciated by one of ordinary skill in the art having the benefit of this disclosure. The fitting110is a monolithic support fitting that provides connection of the landing gear beam410(shown inFIG. 7) to the rear wing spar420(shown inFIG. 7) as well as connecting the actuator150to the rear wing spar420. The assembly of the single fitting110within the wing skin contour is reduced as compared to the prior landing gear assembly that utilized two separate fittings as would be appreciated by one of ordinary skill in the art having the benefit of this disclosure.

FIG. 4is a schematic perspective view of the fitting110with ball joint170positioned within a race160. The race160is configured to permit the movement of the ball joint170within the race170as discussed herein. The ball joint170is positioned within the first opening143of the cross member140. The actuator150is connected to the fitting110via a ball joint170. As shown inFIGS. 1 and 5, the actuator150includes a first end151and a second end152. The second end152of the actuator150is formed into a clevis, or fork. The clevis includes an upper member153and a lower member155connected via a connecting member157as shown inFIG. 5. The upper member153includes an opening154and the lower member155includes an opening156. The ball joint170includes an opening171as shown inFIG. 4.

A fastener180and corresponding nut181may be used to selectively connect the second end152of the actuator150to the fitting110via the ball joint170. The fastener180is positioned through the opening154in the upper member153of the clevis, through the race160and opening171in the ball joint170positioned in the opening143of the cross member140, and through the opening156in the lower member155of the clevis. The openings143,154,156,171are configured so that the fastener180is aligned vertically with respect to the end of the actuator150as shown inFIG. 1. The nut181may be secured onto the end of the fastener180to secure the second end152of the actuator150to the fitting110as would be appreciated by one of ordinary skill in the art having the benefit of this disclosure.

The fastener180is vertically oriented with respect to the second end152of the actuator150in contrast to the horizontally oriented shear pin of the prior design. The fastener180is positioned through the ball joint170and race160permitting the actuator150to pivot about the ball joint170as discussed herein. The fastener180is not designed to selectively release the actuator150from the rear wing spar420(shown inFIG. 7). Rather, a knuckle, such as first knuckle144, applies a load to the actuator150, or another component of the system as discussed herein, causes the actuator150to break releasing it from the rear wing spar420. This configuration enables a lower load to be applied to release the actuator150than the prior use of the horizontally oriented fuse pin. The ability to release at a lower load may result in reduced cost and/or weight of the various components.

The ball joint170and race160enable the actuator150to pivot about the ball joint170in a vertical plane as shown inFIG. 1between a first position and a second position as discussed herein. As an example, the first position and the second position may be approximately 15 degrees apart. The actuator150pivots about the ball joint170in a first direction D1(shown inFIG. 6) to a first position when extending the landing gear of an aircraft and pivots about the ball joint170in a second direction D2(shown inFIG. 6) to a second position when retracting the landing gear of an aircraft as discussed herein. The vertical plane that the actuator150pivots within is formed by the centerline of the actuator150, indicated by arrow190, and the centerline of the opening143of the cross member140, indicated by arrow192. The actuator150pivots about an axis transverse to the centerline of the actuator150located at the centerline of the opening143of the cross member140, indicated by arrow191. The pivoting motion of the actuator150is indicated by arrow193.

FIG. 5shows a schematic of a portion of an example of an actuator150. The second end152of the actuator150is formed into a clevis, or fork. The clevis includes an upper member153and a lower member155connected via a connecting member157. The upper member153includes an opening154and the lower member155includes an opening156. As discussed herein, the openings154,156enable the second end152of the actuator150to be selectively connected to a fitting110via a ball joint170connected to the fitting110. A fastener180may be positioned through the opening154in the upper member153of the clevis, through the race160and opening171in the ball joint170positioned in the opening143of the cross member140, and through the opening156in the lower member155of the clevis. The openings143,154,156,171are configured so that the fastener180is aligned vertically with respect to the end of the actuator150. A portion158of the actuator150may be configured to break to selectively release the actuator150from the fitting110as discussed herein. For example, the portion158of the actuator150may be necked down. In other words, the portion158of the actuator150configured to selectively break may have a reduced outer diameter than adjacent portions of the actuator150as shown inFIG. 5.

FIG. 6is a schematic of an example of a breakaway support system300. The breakaway support system300includes a breakaway support system100connected to a main landing gear trunnion400of an aircraft. The breakaway support system100includes an actuator150connected to a fitting110having a first wall120and a second wall130. The fitting110is configured be to connect to a landing gear beam410(shown inFIG. 7) and rear wing spar420(shown inFIG. 7) as discussed herein. A first end151of the actuator150is connected to the main landing gear trunnion400of the aircraft and the second end152of the actuator150is connected to the fitting110via a ball joint170(best shown inFIG. 4) as discussed herein.

The actuator150is configured to retract and extend landing gear405(shown inFIG. 7) connected to the end of the main landing gear trunnion400.FIG. 6shows the actuator150is a first, or extended, position as indicated by centerline159A of the actuator150. As the actuator150retracts the landing gear405, the actuator150pivots in a second direction, D2, about the ball joint170until it reaches a second position shown in dash and indicated by centerline159B of the actuator. When the actuator150extends the landing gear405from the retracted position, the actuator150pivots in a first direction D1about the ball joint170until it reaches the first position indicated by centerline159A of the actuator150. The second end152of the actuator150, the fitting110, and the race160and ball joint170are each configured to permit the pivoting motion of the actuator150between the first and second positions for normal operation of the landing gear405.

FIG. 7is a schematic of an example of a breakaway support system300connected to a wing rear spar420of an aircraft. A fitting110(best shown inFIGS. 1-4) is connected to the wing rear spar420of the aircraft. As discussed herein, fasteners inserted through fourth and fifth openings131,132in a second wall130of the fitting connect the fitting110to the wing rear spar420of an aircraft. An actuator150configured to retract and extend landing gear405is connected to one end of a main landing gear trunnion400with the landing gear405being connected to the other end of the main landing gear trunnion400. As discussed herein, a second end152of the actuator150is connected to the fitting110via a race160and ball joint170. An end of a landing gear beam410is also connected to a portion of the fitting110of the breakaway support system300. As discussed herein, fasteners through second and third openings121,122in a first wall120of fitting110connect the fitting to the landing gear beam410.

The actuator150and the fitting110are configured to selectively release the actuator150from the fitting110when the actuator150pivots in the first direction D1beyond the first position, which is indicated by the centerline159A of the actuator150. Likewise, the actuator150and the fitting110are configured to release the actuator150from the fitting110when the actuator150pivots in the second direction D2beyond the second position, which is indicated by the centerline159B of the actuator150. The actuator150may be released from the fitting110to potentially prevent the penetration of a wing fuel box due to the movement of the actuator150outside of the first and second positions. For example, an impact event may cause the actuator150, which is connected to the main landing gear trunnion400, to pivot in the second direction D2past the second, or retracted, position.

The movement of the actuator150in the second direction D2past the second, or retracted, position causes a portion of the actuator150to engage the second knuckle145that extends from the bottom surface142of the cross member140of the fitting110. The engagement of a portion of the actuator150against the second knuckle145exerts a force onto the actuator150, which causes the actuator150to be release from the fitting110. Various mechanisms may be used to selectively release the actuator150as would be appreciated by one of ordinary skill in the art having the benefit of this disclosure. For example, the actuator150may include a portion158configured to selectively break and the load on the actuator150by the second knuckle145may cause a portion158to break releasing the actuator150from the fitting110.

The movement of the actuator150in the first direction D1past the first, or extended, position causes a portion of the actuator150to engage the first knuckle144that extends from the top surface141of the cross member140of the fitting110. The engagement of a portion of the actuator150against the first knuckle144exerts a force onto the actuator150, which causes the actuator150to be release from the fitting110. Various mechanisms may be used to selectively release the actuator150as would be appreciated by one of ordinary skill in the art having the benefit of this disclosure. For example, the actuator150may include a portion158configured to selectively break and the load on the actuator150by the first knuckle144may cause a portion158to break releasing the actuator150from the fitting110.

FIG. 8is a schematic of an example of a fitting210for a breakaway support system. The fitting210includes a first wall220and a second wall230. The first wall220may be a first vertical wall and the second wall230may be a second vertical wall. The second wall230is connected to and extends perpendicular from the first wall220. A cross member240is connected to both the first wall220and the second wall230. The fitting210includes a top plate211and a bottom plate212. The first wall220, second wall230, cross member240, top plate211, and bottom plate212may be formed together to form a unitary fitting210.

The cross member240includes a first, or top, surface241and a second, or bottom, surface242. The cross member240includes a first opening243that is configured to a race160and ball joint170as discussed herein. The cross member240of the fitting210is configured to release an actuator150when the actuator150pivots in a first direction D1past a first position or pivots in a second direction D2past a second position as discussed herein. A first knuckle245extends from the bottom surface242of the cross member240. The first knuckle245is configured to selectively release the actuator150from the fitting210as discussed herein. The first knuckle245is configured to release the actuator150from the fitting210when the actuator pivots in a first direction D1past a second position. A portion of the cross member240is configured to selectively release the actuator150from the fitting210. The cross member240may be canted, or oriented at an angle, so that an edge244of the top surface241of cross member240is configured to release an actuator150in a second direction D2past a second position.

The first wall220of the fitting210includes a second opening221and a third opening222. The second and third openings221,222are configured to enable the fitting210to be connected to a landing gear beam410(shown inFIG. 7). Fasteners (not shown) would be inserted through the second and third openings221,222to selectively connect the fitting210to the landing gear beam410as would be appreciated by one of ordinary skill in the art having the benefit of this disclosure.

The second wall230of the fitting210includes a fourth opening231and a fifth opening232configured to enable the fitting210to be connect to a wing of an aircraft. Specifically, fasteners (not shown) may be inserted through the fourth and fifth openings231,232to selectively connect the fitting210to a rear wing spar420(shown inFIG. 7) as would be appreciated by one of ordinary skill in the art having the benefit of this disclosure.

A ball joint170(best shown inFIG. 4) positioned within a race160(best shown inFIG. 4) may be positioned within the opening243in cross member240. The race160is configured to permit the movement of the ball joint170within the race170as discussed herein. The ball joint170is positioned within the first opening243of the cross member240. An actuator150may be connected to the fitting110via a ball joint170. The opening243in the cross member240may be configured to orient a fastener180(best shown inFIG. 1) to be vertically oriented even though the cross member240is canted. A fastener180and corresponding nut181may be used to selectively connect the second end152of the actuator150to the fitting210via the ball joint170as discussed herein.

Various components of the breakaway support system300may be configured to selectively release the actuator150from the fitting110in the event the actuator150moves past the first position or moves past the second position as would be appreciated by one of ordinary skill in the art having the benefit of this disclosure. For example, a rod280as shown inFIG. 9may be configured to connect the second end152of the actuator150to the ball joint170. The rod may have a first end281configured to connect to the second end152of the actuator and a second end282configured to connect to the ball joint170. The second end282of the rod280may be formed in a clevis having an upper member283, lower member285, and a connecting member287. The upper member283may include an opening284and the lower member285may include an opening286to permit the insertion of a fastener to selectively connect the rod280to the ball joint170.

A portion288of the rod280may be configured to selectively break upon the exertion of a load due to the movement of the actuator150and rod280past a first position or past a second position. For example, the portion288of the rod280may have a smaller outer diameter than the outer diameter of adjacent portions of the rod280. As the actuator150and rod280pivot in a first direction D1past a first position, a first knuckle144on the top surface141of the cross member140may exert a load onto the rod280causing the portion288of the rod280to break releasing the actuator150from the fitting110. Likewise, as the actuator150and rod280pivot in a second direction D2past a second position, a second knuckle145on the bottom surface142of the cross member140may exert a load onto the rod280causing the portion288of the rod280to break releasing the actuator150from the fitting110. The fitting110or a component of the fitting110, such as the ball joint170, may be configured to selectively break to release the actuator150from the fitting. For example, the rod280may be an integral component with the ball joint170and may be configured to selectively break to release the actuator150from the fitting110if the actuator moves past the first position or the actuator moves past the second position.

Various components of the breakaway support system300may be configured to apply a load to selectively release the actuator150from the fitting110in the event the actuator150moves past the first position or moves past the second position as would be appreciated by one of ordinary skill in the art having the benefit of this disclosure. For example, a rod280as shown inFIG. 10may be configured to connect the second end152of the actuator150to the ball joint170. The rod may have a first end281configured to connect to the second end152of the actuator and a second end282configured to connect to the ball joint170.

The second end282of the rod280may be formed in a clevis having an upper member283, lower member285, and a connecting member287. The upper member283may include an opening284and the lower member285may include an opening286to permit the insertion of a fastener to selectively connect the rod280to the ball joint170. The rod280may include a first knuckle291that extends into the clevis from the upper member283and a second knuckle292that extends into the clevis from the lower member285. The first or second knuckle291,292may apply a load to the rod280, actuator150, and/or fitting110if the actuator150and rod280pivot in a first direction D1past a first position or the actuator150and rod280pivot in a second direction D2past a second position causing a portion of the actuator150, fitting110, or rod280to break and selectively release the actuator150from the fitting110.

FIG. 11is a schematic of a portion of an example of an actuator250for use in a breakaway support system. The actuator250is configured to apply a load if the actuator250pivots in a first direction D1past a first position or the actuator250pivots in a second direction D2past a second position causing a portion a support system to break and selectively release the actuator250from the fitting110. The second end252of the actuator250is formed into a clevis, or fork. The clevis includes an upper member253and a lower member255connected via a connecting member257. A first knuckle259A extends into the clevis from the upper member253and a second knuckle259B extends into the clevis from the lower member255. The first and second knuckles259A,259B are configured to apply a load to the fitting110, actuator250, and/or a connecting rod280due to movement of the actuator250past a first position or past a second position as discussed herein.

As discussed herein, the upper member253includes an opening254and the lower member255includes an opening256that enables the second end252of the actuator250to be selectively connected to a fitting110via a ball joint170. A fastener180may be positioned through the opening254in the upper member253of the clevis, through the race160and opening171in the ball joint170positioned in the opening143of the cross member140, and through the opening256in the lower member255of the clevis. The openings143,254,256,171are configured so that the fastener180is aligned vertically with respect to the end of the actuator250. As discussed herein, a portion of the actuator250, a connecting rod280, or the fitting110may be configured to break to selectively release the actuator250from the fitting110upon application of a load from either knuckle259A,259B. For example, a portion258of the actuator250may be necked down.

FIG. 12is a flow chart for an example of a method500of providing a breakaway support for an aircraft. The method500includes providing an actuator having a first end and a second end, at510. For example, an actuator150configured to retract and extend the landing gear of an aircraft is provided as discussed herein. The method500includes providing a fitting, at520. For example, a fitting110or210that is configured to connect to an actuator150, a landing gear beam410, and a wing rear spar420as discussed herein.

At530, the method500includes providing a race and, at540, positioning a ball joint within the race. For example, a ball joint170may be positioned within a race160as discussed herein. The method500includes providing a first knuckle, at550, and connecting the second end of the actuator at the ball joint, the ball joint being configured to permit the actuator to pivot about the ball joint, wherein the first knuckle is configured to release the actuator from the fitting when the actuator moves past a first position in a first direction, at560. For example, the first knuckle may be a first knuckle144that extends from a top surface141of a cross member140of the fitting110as discussed herein. The first knuckle144may apply a load when the actuator moves past a first position in a first direction to release the actuator150from the fitting110as discussed herein. The first knuckle may be located on a portion of a fitting110,210, a portion of an actuator150,250, or on a portion of a rod280configured to connect an actuator150,250to a fitting110,210as discussed herein.

The method500may include providing a second knuckle, wherein the second knuckle is configured to release the actuator from the fitting when the actuator moves past a second position in a second direction, at555. For example, the second knuckle may be a second knuckle145that extends from a bottom surface142of a cross member140of the fitting110as discussed herein. The second knuckle145may apply a load when the actuator moves past a second position in a second direction to release the actuator150from the fitting110as discussed herein. The second knuckle may be located on a portion of a fitting110,210, a portion of an actuator150,250, or on a portion of a rod280configured to connect an actuator150,250to a fitting110,210as discussed herein.

The method500may include connecting the second end of the actuator to the ball joint via a rod, at570. For example, a rod280may be configured to connect an actuator150,250to a ball joint170positioned within a race160as discussed herein. The method500may include selectively connecting the second end of the actuator to the ball joint by positioning a fastener through the second end of the actuator, the race, and the ball joint, at580. For example, a fastener180may be oriented through openings in the second end152,252of the actuator150,250, the race160, and the ball joint170to connect the actuator150,250to the fitting110,210via the ball joint170as discussed herein.

Although this disclosure has been described in terms of certain embodiments, other embodiments that are apparent to those of ordinary skill in the art, including embodiments that do not provide all of the features and advantages set forth herein, are also within the scope of this disclosure. Accordingly, the scope of the present disclosure is defined only by reference to the appended claims and equivalents thereof.