Retract actuator assemblies, landing gear assemblies and methods for kneeling landing gear assembly of aircraft

Abstract

To provide a landing gear assembly of an aircraft and a method for kneeling a landing gear assembly.SOLUTION: A retract actuator assembly for a landing gear assembly of an aircraft includes a retract actuator and a kneel stop assembly. The retract actuator includes an actuator housing and a piston. The actuator housing includes a cylinder bore along a longitudinal axis. The piston is disposed within the cylinder bore and configured to move within the cylinder bore. The cylinder bore defines a piston stroke with an extended piston position and a retracted piston position. The kneel stop assembly is secured to the actuator housing. The kneel stop assembly is configured to selectively establish a kneel stop position within the cylinder bore to reduce the piston stroke by inhibiting movement of the piston to the retracted piston position.SELECTED DRAWING: Figure 1

Description

[Technical field]

[0001] The present disclosure relates generally to techniques for kneeling an aircraft landing gear assembly, and in particular to the use of a stow actuator assembly that provides the landing gear assembly with a third position between an extended position and a stowed position that can be used to lower the aircraft into a kneeled state for certain ground operations. [Background technology]

[0002] Some aircraft are equipped with landing gear that has the ability to kneel the aircraft while it is on the ground. It is desirable to kneel the aircraft to facilitate easier boarding / disembarking of crew and / or passengers, to facilitate landing / takeoff of cargo aircraft, and to lower the height of the aircraft during transport and storage. Existing designs typically utilize some form of external kneeling mechanism to move the landing gear into the kneeling position. The above concepts typically require additional hydraulic actuators and additional mechanical linkages, adding cost, complexity, and weight.

[0003] In response, those skilled in the art have engaged in ongoing research and development efforts to improve techniques for kneeling aircraft landing gear assemblies. Summary of the Invention

[0004] Disclosed are embodiments of a stow actuator assembly, a landing gear assembly, and a method for kneeling an aircraft landing gear assembly. The following is a non-exhaustive list of embodiments of the presently disclosed inventive subject matter, which may or may not be claimed.

[0005] In one example, a stow actuator assembly for a disclosed aircraft landing gear assembly includes a stow actuator and a knee stop assembly. The stow actuator includes an actuator housing and a piston. The actuator housing defines a longitudinal axis extending through a distal end and a proximal end. The actuator housing includes a cylinder bore along the longitudinal axis. The piston is disposed within the cylinder bore and configured to move within the cylinder bore along the longitudinal axis. The cylinder bore defines a piston stroke within the actuator housing, the piston stroke defining limits of piston movement. The piston stroke includes an extended piston position relative to a distal end of the actuator housing and a stowed piston position relative to a proximal end of the actuator housing. A knee stop assembly is secured to an exterior surface of the actuator housing relative to the extended piston position within the cylinder bore and the stowed piston position within the cylinder bore. The knee stop assembly is configured to selectively form a knee stop position within the cylinder bore for preventing movement of the piston to a stowed piston position, thereby shortening the piston stroke.

[0006] In one embodiment, a landing gear assembly for a disclosed aircraft includes a stow actuator, a knee stop assembly, a trailing arm, and a shock absorber. The stow actuator includes an actuator housing and a piston. The actuator housing defines a longitudinal axis extending through a distal end and a proximal end. The actuator housing includes a cylinder bore along the longitudinal axis. The piston is disposed within the cylinder bore and configured to move within the cylinder bore along the longitudinal axis. The cylinder bore defines a piston stroke within the actuator housing, the piston stroke defining limits of piston movement. The piston stroke includes an extended piston position relative to a distal end of the actuator housing and a stowed piston position relative to a proximal end of the actuator housing. A knee stop assembly is secured to an exterior surface of the actuator housing relative to the extended piston position within the cylinder bore and the stowed piston position within the cylinder bore. The knee stop assembly is configured to selectively form a knee stop position within the cylinder bore for preventing movement of the piston to a stowed piston position, thereby shortening the piston stroke. The trailing arm includes an arm proximal end and an arm distal end. The arm distal end is configured to be pivotally mounted to a fixed point on the aircraft, the arm proximal end is configured to be mounted to the surface contact assembly, and a shock absorber is mechanically coupled to the stow actuator and configured to be pivotally mounted to the trailing arm.

[0007] A method for kneeling an aircraft landing gear assembly is disclosed in one example, the method includes (1) performing ground operations for an aircraft with the landing gear assembly in a fully extended state and a stow actuator of the landing gear assembly in an extended piston position, (2) actuating a kneeling feature of the landing gear assembly to create a knee stop position in the stow actuator that shortens a piston stroke of the stow actuator by preventing movement of a piston in the stow actuator beyond the knee stop position toward a stow piston position, and (3) moving the stow actuator from the fully extended state to the kneeling state by moving the stow actuator from the extended piston position to the knee stop position.

[0008] Other embodiments of the disclosed stow actuator assembly, landing gear assembly, and method for kneeling an aircraft landing gear assembly will become apparent from the following detailed description, the accompanying drawings, and the appended claims. [Brief description of the drawings]

[0009] [Figure 1] FIG. 2 is a functional diagram illustrating an example of a stow actuator assembly for an example aircraft landing gear assembly. [Diagram 2] 2 is a cross-sectional view of an example of a retractable actuator of the retractable actuator assembly of FIG. 1. [Diagram 3] 2 is a cross-sectional view of an example kneel stop assembly of the stowage actuator assembly of FIG. 1 with a kneel stop segment inserted into the stowage actuator and the stowage actuator in an extended position. [Figure 4] FIG. 2 is a functional diagram of the landing gear assembly of FIG. 1 with the landing gear in an extended position and the weight of the aircraft on the wheels. [Diagram 5]FIG. 2 is a cross-sectional view of an example kneel stop assembly of the stowage actuator assembly of FIG. 1 with a kneel stop segment inserted into the stowage actuator and the stowage actuator in a kneeling position. [Figure 6] FIG. 2 is a functional diagram of the landing gear assembly of FIG. 1 with the landing gear in a kneeling position and the weight of the aircraft on the wheels. [Figure 7] 2 is a cross-sectional view of an example kneel stop assembly of the stow actuator assembly of FIG. 1 with the kneel stop segment retracted from the stow actuator and the stow actuator in a stowed position. [Figure 8] FIG. 2 is a functional diagram of the landing gear assembly of FIG. 1 with the landing gear in a stowed position and the aircraft in flight. [Figure 9] 2 is a cross-sectional view of an example kneel stop assembly of the stowage actuator assembly of FIG. 1 with the kneel stop segments retracted from the stowage actuator and the stowage actuator in an extended position. [Figure 10] FIG. 2 is a functional diagram of the landing gear assembly of FIG. 1 with the landing gear in an extended position and the aircraft in flight. [Figure 11] 4 is an exploded view of the example knee stop assembly of FIG. 3 for the example retract actuator of the retract actuator assembly of FIG. 1. [Figure 12A] FIG. 2 is a functional diagram illustrating another example of a landing gear assembly with the landing gear in an extended position and the weight of the aircraft on the wheels. [Figure 12B] FIG. 12B is a functional diagram of the landing gear assembly of FIG. 12A with the landing gear in a kneeling position and the weight of the aircraft on the wheels. [Figure 12C] FIG. 12B is a functional diagram of the landing gear assembly of FIG. 12A with the landing gear in a stowed position and the aircraft in flight. [Figure 13] A flow chart of an example method for kneeling a landing gear assembly of an aircraft is provided. [Figure 14]14 is a flowchart of another example of a method for kneeling a landing gear assembly of an aircraft, combined with FIG. [Figure 15] 14 is a flowchart of yet another example of a method for kneeling a landing gear assembly of an aircraft in combination with FIG. [Figure 16] 14 is a flowchart of yet another example of a method for kneeling a landing gear assembly of an aircraft in combination with FIG. [Figure 17] 17 is a flowchart of yet another example of a method for kneeling a landing gear assembly of an aircraft, combined with FIGS. 13 and 16 . [Figure 18] 14 is a flowchart of another example of a method for kneeling a landing gear assembly of an aircraft, combined with FIG. [Figure 19] 19 is a flowchart of yet another example of a method for kneeling a landing gear assembly of an aircraft, combined with FIGS. 13 and 18 . [Figure 20] 19 is a flowchart of yet another example of a method for kneeling a landing gear assembly of an aircraft, combined with FIGS. 13 and 18 . [Figure 21] 19 is a flowchart of yet another example of a method for kneeling a landing gear assembly of an aircraft, combined with FIGS. 13 and 18 . [Figure 22] 22 is a flowchart of yet another example of a method for kneeling a landing gear assembly of an aircraft, in combination with FIGS. 13, 18 and 21; [Figure 23] FIG. 1 is a block diagram of an aircraft manufacturing and service method in which one or more examples of the methods for kneeling an aircraft landing gear assembly disclosed herein may be implemented. [Figure 24] FIG. 1 is a schematic diagram of an aircraft into which one or more examples of the stowage actuator assemblies and landing gear assemblies disclosed herein may be incorporated. DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS

[0010] Various embodiments of the stow actuator assembly, landing gear assembly, and method for kneeling an aircraft landing gear assembly provide a technique that allows the stow actuator assembly to have a third position between an extended position and a stowed position that can be used to lower the aircraft to a kneeling position while the aircraft is on the ground. The kneeling actuator position is provided by using a retractable stop that, when engaged, limits the travel of the actuator piston. The stop is inserted and retracted using a mechanism located on the actuator outer diameter within the housing. The mechanism includes a series of slider rings and springs. The mechanism requires external actuation (e.g., hydraulic) to change state (i.e., from retracted to inserted or from inserted to retracted), but is self-locking once in the retracted or inserted position.

[0011] The internal self-locking kneel mechanism offers many advantages over previous kneeling methods. For example, the landing gear assembly does not require a secondary kneel actuator. When an in-line shock absorber / actuator is used, the mechanism does not reduce the length of the in-line shock absorber / actuator, resulting in lower loads on the in-line shock absorber / actuator. The mechanism has limited hydraulic impact due to the smaller volume of fluid required for kneeling. The mechanism is achieved using a compact design requiring fewer structural interfaces. Additionally, the dedicated kneel mechanism is out of the landing load path, resulting in improved reliability and lighter component weight.

[0012] By way of example, and referring generally to Figures 1-11, 12A-12C, and 24, the present disclosure is directed to a stow actuator assembly 100 for a landing gear assembly 102 of an aircraft 2400. Figure 1 discloses an example of a stow actuator assembly 100. Figure 2 is a cross-sectional view of an example of a stow actuator 104 of the stow actuator assembly 100 of Figure 1. Figure 3 illustrates a cross-sectional view of an example knee stop assembly 106 of the stow actuator assembly 100 of Figure 1 with a knee stop segment 1108 inserted into the stow actuator 104 and in an extended position. Figure 4 is a functional diagram illustrating the landing gear assembly 102 of Figure 1 in an extended state with the weight of the aircraft 2400 on the wheels. FIG. 5 is a cross-sectional view of an example kneel stop assembly 106 of the stowage actuator assembly 100 of FIG. 1 with a kneel stop segment 1108 inserted into the stowage actuator 104 and the stowage actuator 104 in a kneeling position.

[0013] FIG. 6 illustrates a functional diagram of the landing gear assembly 102 of FIG. 1 with the landing gear assembly 102 in a kneeling position and the weight of the aircraft 2400 on the wheels. FIG. 7 illustrates a cross-sectional view of an example kneel stop assembly 106 of the stow actuator assembly 100 of FIG. 1 with the kneel stop segments 1108 retracted from the stow actuator 104 and the stow actuator 104 in a stowed position. FIG. 8 illustrates a functional diagram of the landing gear assembly 102 of FIG. 1 with the landing gear assembly 102 in a stowed position and the aircraft 2400 in flight. FIG. 9 illustrates a cross-sectional view of an example kneel stop assembly 106 of the stow actuator assembly 100 of FIG. 1 with the kneel stop segments 1108 retracted from the stow actuator 104 and the stow actuator 104 in an extended position. FIG. 10 illustrates a functional diagram of the landing gear assembly 102 of FIG. 1 with the landing gear assembly 102 in an extended position and the aircraft 2400 in flight. FIG. 11 provides an exploded view of the example knee stop assembly 106 of FIG. 3 relative to the example stowage actuator 104 of the stowage actuator assembly 100 of FIG.

[0014] FIG 12A discloses another example of a landing gear assembly 102 with the landing gear assembly 102 in an extended state and the weight of the aircraft 2400 resting on the wheels. FIG 12B shows a functional diagram of the landing gear assembly 102 of FIG 12A with the landing gear assembly 102 in a kneeling state and the weight of the aircraft 2400 resting on the wheels. FIG 12C shows a functional diagram of the landing gear assembly 102 of FIG 12A with the landing gear assembly 102 in a stowed state and the aircraft 2400 in flight. FIG 24 shows an aircraft 2400 incorporating one or more embodiments of the stow actuator assembly 100 disclosed herein.

[0015] 1-11 , 12A-12C , and 24 , in one or more examples, a stowage actuator assembly 100 for a landing gear assembly 102 of an aircraft 2400 includes a stowage actuator 104 and a knee stop assembly 106. The stowage actuator 104 includes an actuator housing 202 and a piston 212. The actuator housing 202 defines a longitudinal axis 204 extending through a distal end 206 and a proximal end 208. The actuator housing 202 includes a cylinder bore 210 along the longitudinal axis 204. The piston 212 is disposed within the cylinder bore 212 and is configured to move within the cylinder bore 210 along the longitudinal axis 204. The cylinder bore 210 defines a piston stroke 214 within the actuator housing 202, the piston stroke 214 defining limits of movement of the piston 212. A piston stroke 214 includes an extended piston position 216 relative to a distal end 206 of the actuator housing 202 and a retracted piston position 218 relative to a proximal end 208 of the actuator housing 202. A knee stop assembly 106 is secured to an exterior surface 220 of the actuator housing 202 relative to the extended piston position 216 in the cylinder bore 210 and relative to the retracted piston position 218 in the cylinder bore 210. The knee stop assembly 106 is configured to selectively form a knee stop position 302 in the cylinder bore 210 to prevent movement of the piston 212 to the retracted piston position 218, thereby shortening the piston stroke 214.

[0016] In another example, the stowage actuator assembly 100 also includes a shock absorber 108 secured to a proximal end 208 of the actuator housing 202 such that the shock absorber 108 and the stowage actuator 104 are aligned along a longitudinal axis 204 of the actuator housing 202 to form an in-line shock absorber actuator 110. The shock absorber 108 is configured to be pivotally mounted to a trailing arm 112 of the landing gear assembly 102.

[0017] In yet another example of the contained actuator assembly 100, the piston 212 defines a rod chamber 222 within the cylinder bore 210 relative to the distal end 206 of the actuator housing 202 and a piston chamber 224 within the cylinder bore 210 relative to the proximal end 208 of the actuator housing 202. In this example, the contained actuator 104 also includes a piston rod 226 disposed within the rod chamber 222. The piston rod 226 includes a first end 228 attached to the piston 212 and a second end 230 that extends through a sealed opening 232 in the distal end 206 of the actuator housing 202.

[0018] In a further example, the second end 230 of the piston rod 226 is configured to be pivotally attached to a fixed point on the aircraft 2400. In this example, the stowage actuator assembly 100 also includes a shock absorber 108 that is fixed to a proximal end 208 of the actuator housing 202 such that the shock absorber 108 and the stowage actuator 104 are aligned along a longitudinal axis 204 of the actuator housing 202 to form an in-line shock absorber actuator 110. The shock absorber 108 is configured to be pivotally attached to a trailing arm 112 of the landing gear assembly 102. In a further example, the mechanical linkage of the landing gear assembly 102 includes the trailing arm 112 of the landing gear assembly 102 and the in-line shock absorber actuator 110.

[0019] In another further example, the proximal end 208 of the actuator housing 202 is configured to be pivotally mounted to a fixed point on the aircraft 2400. In this example, the stowage actuator assembly 100 also includes a shock absorber 108 mechanically coupled to the second end 230 of the piston rod 226. The shock absorber 108 is configured to be pivotally mounted to the trailing arm 112 of the landing gear assembly 102. In another further example, the mechanical linkage of the landing gear assembly 102 includes the trailing arm 112 of the landing gear assembly 102, the shock absorber 108, the stowage actuator 104, and a coupling member 1202 between the stowage actuator 104 and the shock absorber 108.

[0020] In yet another example of the stored actuator assembly 100, the stored actuator 104 includes a rod hydraulic port 234 and a piston hydraulic port 236. The rod hydraulic port 234 is disposed near the distal end 206 of the actuator housing 202 to provide fluid access to the rod chamber 222. The piston hydraulic port 236 is disposed near the proximal end 208 of the actuator housing 202 to provide fluid access to the piston chamber 224.

[0021] In yet another example of the stow actuator assembly 100, the extended piston position 216 of the piston stroke 214 in the cylinder bore 210 is associated with a fully extended condition 1002 of the landing gear assembly 102 associated with a landing sequence of the aircraft 2400. In yet another example of the stow actuator assembly 100, the stow piston position 218 of the piston stroke 214 in the cylinder bore 210 is associated with a fully stowed condition 802 of the landing gear assembly 102 associated with a takeoff sequence of the aircraft 2400. In yet another example of the stow actuator assembly 100, the kneel stop position 302 of the piston stroke 214 in the cylinder bore 210 is associated with a kneel condition 602 of the landing gear assembly 102 during ground operations of the aircraft 2400. In yet another example of the stowed actuator assembly 100, the knee stop assembly 106 is configured to allow the piston 212 to move from a knee stop position 302 of the piston stroke 214 to an extended piston position 216 within the cylinder bore 210. In yet another example of the stowed actuator assembly 100, the knee stop assembly 106 is configured to selectively disengage the knee stop position 302 of the piston stroke 214 within the cylinder bore 210 to allow the piston 212 to move to a stowed piston position 218 of the piston stroke 214.

[0022] In yet another example of the storage actuator assembly 100, the kneel stop assembly 106 includes a kneel stop housing 1102, a kneel stop insertion port 308, and a kneel stop retraction port 312. The kneel stop housing 1102 is fixed to the outer surface 220 of the actuator housing 202 of the storage actuator 104 relative to the extension piston position 216 in the cylinder bore 210 of the storage actuator 104 and the storage piston position 218 in the cylinder bore 210. The kneel stop housing 1102 includes a kneel stop distal end 1104 closer to the distal end 206 of the actuator housing 202 and a kneel stop proximal end 1106 closer to the proximal end 208 of the actuator housing 202. The kneel stop housing 1102 defines a cavity 304 between an inner surface 306 of the kneel stop housing 1102 and the outer surface 220 of the actuator housing 202. A knee stop insertion port 308 is disposed on the knee stop housing 1102 and provides fluid access to a knee stop insertion chamber 310 formed within the cavity 304. A knee stop cancellation port 312 is disposed on the knee stop housing 1102 and provides fluid access to a knee stop cancellation chamber 314 formed within the cavity 304.

[0023] In a further example, the kneel stop insertion port 308 is configured to receive pressurized fluid from a pressurized fluid source, and the kneel stop assembly 106 is configured to form the kneel stop position 302 in response to the pressurized fluid being received at the kneel stop insertion port 308. In yet another example, the pressurized fluid includes pressurized hydraulic fluid, pressurized oil, compressed gas, compressed air, or any other suitable pressurized fluid in any suitable combination. In yet another example, the kneel stop insertion port 308 is configured to allow pressurized fluid to exit the kneel stop assembly 106 after the pressurized fluid source is no longer applying pressurized fluid. In this example, the kneel stop assembly 106 is configured such that the exit of pressurized fluid through the kneel stop insertion port 308 does not affect the current state of the kneel stop position 302.

[0024] In yet another example, the kneel stop cancel port 312 is configured to receive pressurized fluid from a pressurized fluid source. In this example, the kneel stop assembly 106 is configured to cancel the kneel stop position 302 in response to receiving pressurized fluid at the kneel stop cancel port 312. In yet another example, the kneel stop cancel port 312 is configured to allow pressurized fluid to exit the kneel stop assembly 106. In this example, the kneel stop assembly 106 is configured such that exiting pressurized fluid via the kneel cancel port 312 does not affect the current state of the kneel stop position 302.

[0025] In yet another further example of the containment actuator assembly 100, the kneel stop assembly 106 also includes at least one kneel stop segment 1108 disposed within the cavity 304 of the kneel stop housing 1102 at a predetermined point 1109 along the longitudinal axis 204 of the actuator housing 202. The predetermined point 1109 is associated with the kneel stop position 302. In this example, the actuator housing 202 includes at least one kneel stop opening 1110 extending through the actuator housing 202 to the cylinder bore 210. The at least one kneel stop opening 1110 is configured to receive at least a portion of the at least one kneel stop segment 1108. The at least one kneel stop segment 1108 is configured for selective insertion into and selective removal from the at least one kneel stop opening 1110. In yet another example, the at least one knee stop segment 1108 includes at least two knee stop segments 1108 radially distributed around the actuator housing 202 at the predetermined point 1109. In this example, the at least one knee stop opening 1110 includes at least two knee stop openings 1110 radially distributed around the actuator housing 202 for the at least two knee stop segments 1108.

[0026] In another further example, the at least one kneel stop segment 1108 of the kneel stop assembly 106 includes two open kneel stop segments, three kneel stop segments, four kneel stop segments, five kneel stop segments, six kneel stop segments, or any other suitable amount of kneel stop segments. Correspondingly, the at least one kneel stop opening 1110 of the storage actuator 104 includes two open kneel stop openings, three kneel stop openings, four kneel stop openings, five kneel stop openings, six kneel stop openings, or any other suitable amount of kneel stop openings. In yet another further example, the kneel stop insertion port 308 is configured to receive pressurized fluid from a pressurized fluid source, and in response to receiving the pressurized fluid at the kneel stop insertion port 308, the kneel stop assembly 106 is configured to insert the at least one kneel stop segment 1108 into the at least one kneel stop opening 1110 of the actuator housing 202 to form the kneel stop position 302. In yet another further example, the knee stop cancellation port 312 is configured to receive pressurized fluid from a pressurized fluid source, and in response to receiving pressurized fluid at the knee stop cancellation port 312, the knee stop assembly 106 is configured to retract at least one knee stop segment 1108 from at least one knee stop opening 1110 in the actuator housing 202 to cancel the knee stop position 302.

[0027] 1-3 and 11, in one or more further examples of the storage actuator assembly 100, the knee stop assembly 106 also includes an upper biasing member 1112, an upper slider member 1114, a lower biasing member 1118, and a lower slider member 1120. The upper biasing member 1112 is disposed in the cavity 304 between the knee stop housing 1102 and the actuator housing 202 near the knee stop distal end 1104 of the knee stop housing 1102. The upper biasing slider member 1114 is disposed in the cavity 304 between the knee stop housing 1102 and the actuator housing 202 between the upper biasing member 1112 and the at least one stop segment 1108. The upper slider member 1114 includes a first portion of an upper slider outer surface 1116 that faces the inner surface 306 of the knee stop housing 1102. A first portion of the upper slider outer surface 1116 and a corresponding portion of the inner surface 306 of the kneel stop housing 1102 are configured to form a kneel stop insertion chamber 310. An upper biasing member 1112 is configured to bias the upper slider member 1114 toward the at least one kneel stop segment 1108. A lower biasing member 1118 is disposed in the cavity 304 between the kneel stop housing 1102 and the actuator housing 202 near the kneel stop proximal end 1106 of the kneel stop housing 1102. A lower slider member 1120 is disposed in the cavity 304 between the kneel stop housing 1102 and the actuator housing 202 between the at least one kneel stop segment 1108 and the lower biasing member 1118. The lower slider member 1120 includes a first portion of a lower slider outer surface 1122 facing the inner surface 306 of the kneel stop housing 1102. A first portion of the lower slider outer surface 1122 and an opposing portion of the inner surface 306 of the knee stop housing 1102 are configured to form a knee stop cancellation chamber 314. A lower biasing member 1118 is configured to bias the lower slider member 1120 toward the at least one knee stop segment 1108.

[0028] In another example of the storage actuator assembly 100, the upper slider member 1114 of the knee stop assembly 106 further includes a second portion of the upper slider outer surface 1116 in an opposing geometric relationship with an upper surface of at least one knee stop segment 1108) and a third portion of the upper slider outer surface 1116 in the vicinity of a corresponding portion of the outer surface 220 of the actuator housing 202, wherein the second portion of the upper slider outer surface 1116 is elevated from the third portion of the upper slider outer surface 1116 at a predetermined angle to the first portion of the upper slider outer surface 1116, facilitating retraction of the at least one knee stop segment 1108 from the at least one knee stop opening 1110 of the actuator housing 202. In response to pressure being applied at the knee stop cancellation port 312 to prevent the at least one knee stop segment 1108 from being inserted into the at least one knee stop opening 1110, a first portion of the upper slider outer surface 1116 and a third portion of the upper slider outer surface 1116 are configured to slide between the at least one knee stop segment 1108 and the outer surface 220 of the actuator housing 202.

[0029] In yet another example of the storage actuator assembly 100, the lower slider member 1120 of the knee stop assembly 106 further includes a second portion of the lower slider outer surface 1122 in an opposing geometric relationship with the underside of the at least one knee stop segment 1108 and a third portion of the lower slider outer surface 1122 in the vicinity of a corresponding portion of the inner surface 306 of the knee stop housing 1102, wherein the second portion of the lower slider outer surface 1122 descends at a predetermined angle from the first portion of the lower slider outer surface 1122 to the third portion of the lower slider outer surface 1122, facilitating insertion of the at least one knee stop segment 1108 into the at least one knee stop opening 1110 of the actuator housing 202. In response to pressure being applied at the knee stop insertion port 308 to prevent the at least one knee stop segment 1108 from retracting from the at least one knee stop opening 1110, the first portion of the lower slider outer surface 1122 and the third portion of the lower slider outer surface 1122 are configured to slide between the at least one knee stop segment 1108 and the inner surface 306 of the knee stop housing 1102.

[0030] In yet another example of the storage actuator assembly 100, the kneel stop insertion port 308 is configured to receive pressurized fluid from a pressurized fluid source and provide pressurized fluid to the kneel stop insertion chamber 310. In response to the kneel stop insertion chamber 310 receiving pressurized fluid, the kneel stop assembly 106 is configured to move the upper slider member 1114 toward the upper biasing member 1112 and away from the at least one kneel stop segment 1108. In response to the upper slider member 1114 moving away from the at least one kneel stop segment 1108 and the lower biasing member 1118 biasing the lower slider member 1120 toward the at least one kneel stop segment 1108, the kneel stop assembly 106 is configured to move the lower slider member 1120 toward the at least one kneel stop segment 1108. As the lower slider member 1120 moves toward the at least one knee stop segment 1108 and pushes the at least one knee stop segment 1108 into the at least one knee stop opening 1110, the knee stop assembly 106 is configured to insert the at least one knee stop segment 1108 into the at least one knee stop opening 1110 of the actuator housing 202 to form a knee stop position 302 within the cylinder bore 210 of the storage actuator 104. In a further example of the storage actuator assembly 100, after at least one knee stop segment 1108 of the knee stop assembly 106 is inserted into at least one knee stop opening 1110 of the actuator housing 202, the lower biasing member 1118, the lower slider member 1120 and the at least one knee stop segment 1108 are configured to be moved to a locked position in which the lower slider member 1120 holds the at least one knee stop segment 1108 inserted into the at least one knee stop opening 1110, with or without pressure applied to the knee stop insertion port 308 until pressure is applied to the knee stop cancellation port 312.

[0031] In yet another example of the storage actuator assembly 100, the kneel stop cancel port 312 is configured to receive pressurized fluid from a pressurized fluid source and supply pressurized fluid to the kneel stop cancel chamber 314. In response to the kneel stop cancel chamber 314 receiving pressurized fluid, the kneel stop assembly 106 is configured to move the lower slider member 1120 toward the lower biasing member 1118 and away from the at least one kneel stop segment (1108). In response to the lower slider member 1120 moving away from the at least one kneel stop segment 1108 and the upper biasing member 1112 biasing the upper slider member 1114 toward the at least one kneel stop segment 1108, the kneel stop assembly 106 is configured to move the upper slider member 1114 toward the at least one kneel stop segment 1108. The knee stop assembly 106 is configured to retract the at least one knee stop segment 1108 from the at least one knee stop opening 1110 in the actuator housing 202 in response to the upper slider member 1114 moving toward the at least one knee stop segment 1108 and pushing the at least one knee stop segment 1108 away from the at least one knee stop opening 1110 to eliminate the knee stop position 302 from the cylinder bore 210 of the storage actuator 104. In a further example of the storage actuator assembly 100, after at least one knee stop segment 1108 of the knee stop assembly 106 is retracted from at least one knee stop opening 1110 in the actuator housing 202, the upper biasing member 1112, the upper slider member 1114 and the at least one knee stop segment 1108 are configured to be moved to a locked position in which the upper slider member 1114 holds the at least one knee stop segment 1108 retracted from the at least one knee stop opening 1110, where pressure is or is not applied to the knee stop cancellation port 312 until pressure is applied to the knee stop insertion port 308.

[0032] By way of example, and referring generally to Figures 1-11, 12A-12AC, and 24, the present disclosure is directed to a landing gear assembly 102 for an aircraft 2400. Figure 1 discloses an example landing gear assembly 102 including a stow actuator assembly 100. Figure 2 is a cross-sectional view of an example stow actuator 104 of the stow actuator assembly 100 of Figure 1. Figure 3 shows a cross-sectional view of an example kneel stop assembly 106 for the landing gear assembly 102 of Figure 1 with the kneel stop segment 1108 inserted into the stow actuator 104 and in an extended position. Figure 4 is a functional diagram of the landing gear assembly 102 of Figure 1 with the landing gear assembly 102 in an extended state and with the weight of the aircraft 2400 on the wheels. FIG. 5 is a cross-sectional view of an example kneel stop assembly 106 for the landing gear assembly 102 of FIG. 1 with a kneel stop segment 1108 inserted into a stow actuator 104 and with the stow actuator 104 in a kneeling position.

[0033] FIG. 6 illustrates a functional diagram of the landing gear assembly 102 of FIG. 1 with the landing gear assembly 102 in a kneeling state and the weight of the aircraft 2400 on the wheels. FIG. 7 illustrates a cross-sectional view of an example of a kneel stop assembly 106 for the landing gear assembly 102 of FIG. 1 with the kneel stop segments 1108 retracted from the stow actuators 104 and the stow actuators 104 in a stowed position. FIG. 8 illustrates a functional diagram of the landing gear assembly 102 of FIG. 1 with the landing gear assembly 102 in a stowed state and the aircraft 2400 in flight. FIG. 9 illustrates a cross-sectional view of an example of a kneel stop assembly 106 for the landing gear assembly 102 of FIG. 1 with the kneel stop segments 1108 retracted from the stow actuators 104 and the stow actuators 104 in an extended position. FIG. 10 illustrates a functional diagram of the landing gear assembly 102 of FIG. 1 with the landing gear assembly 102 in an extended state and the aircraft 2400 in flight. FIG. 11 provides an exploded view of the example knee stop assembly 106 of FIG. 3 relative to the example stowage actuator 104 of the stowage actuator assembly 100 of FIG.

[0034] FIG 12A discloses another example of a landing gear assembly 102 with the landing gear assembly 102 in an extended state and the weight of the aircraft 2400 on the wheels. FIG 12B shows a functional diagram of the landing gear assembly 102 of FIG 12A with the landing gear assembly 102 in a kneeling state and the weight of the aircraft 2400 on the wheels. FIG 12C shows a functional diagram of the landing gear assembly 102 of FIG 12A with the landing gear assembly 102 in a stowed state and the aircraft 2400 in flight. FIG 24 shows an aircraft 2400 incorporating one or more embodiments of the landing gear assembly 102 disclosed herein.

[0035] 1-11 , 12A-C, and 24 , in one or more examples, a landing gear assembly 102 for an aircraft 2400 includes a stowage actuator 104, a knee stop assembly 106, a trailing arm 112, and a shock absorber 108. The stowage actuator 104 includes an actuator housing 202 and a piston 212. The actuator housing 202 defines a longitudinal axis 204 extending through a distal end 206 and a proximal end 208. The actuator housing 202 includes a cylinder bore 210 along the longitudinal axis 204. The piston 212 is disposed within the cylinder bore 210. The piston is configured to move within the cylinder bore 210 along the longitudinal axis 204. The cylinder bore 210 defines a piston stroke 214 within the actuator housing 202, the piston stroke 214 defining a limit of movement of the piston 212. The piston stroke 214 includes an extended piston position 216 relative to the distal end 206 of the actuator housing 202 and a retracted piston position 218 relative to the proximal end 208 of the actuator housing 202. A knee stop assembly 106 is fixed to an exterior surface 220 of the actuator housing 202 relative to the extended piston position 216 in the cylinder bore 210 and the retracted piston position 218 in the cylinder bore 210. The knee stop assembly 106 is configured to selectively form a knee stop position 302 in the cylinder bore 210 for shortening the piston stroke 214 by preventing movement of the piston 212 to the retracted piston position 218. The trailing arm 112 includes an arm proximal end 114 and an arm distal end 116, the arm distal end 116 configured to be pivotally attached to a fixed point on the aircraft 2400. The arm proximal end 114 is configured to be attached to a surface contact assembly 118. The shock absorber 108 is mechanically coupled to the storage actuator 104 and is configured to be pivotally mounted to a trailing arm 112 .

[0036] In another example of the landing gear assembly 102, the shock absorber 108 is secured to a proximal end 208 of the actuator housing 202 such that the shock absorber 108 and the storage actuator 104 are aligned along the longitudinal axis 204 of the actuator housing 202 to form an in-line shock absorber actuator 110.

[0037] In yet another example of the landing gear assembly 102, the piston 212 defines a rod chamber 222 within the cylinder bore 210 relative to the distal end 206 of the actuator housing 202 and a piston chamber 224 within the cylinder bore 210 relative to the proximal end 208 of the actuator housing 202. In this example, the stored actuator 104 also includes a piston rod 226 disposed within the rod chamber 222. The piston rod 226 includes a first end 228 attached to the piston 212 and a second end 230 that extends through a sealed opening 232 in the distal end 206 of the actuator housing 202.

[0038] In a further example, the second end 230 of the piston rod 226 is configured to be pivotally attached to a second fixed point on the aircraft 2400. In this example, the shock absorber 108 is fixed to the proximal end 208 of the actuator housing 202 such that the shock absorber 108 and the stowage actuator 104 are aligned along the longitudinal axis 204 of the actuator housing 202 to form an in-line shock absorber actuator 110. In yet another example, the mechanical linkage of the landing gear assembly 102 includes the trailing arm 112 and the in-line shock absorber actuator 110.

[0039] In yet another example, the second end 230 of the piston rod 226 in the stowage actuator 104 is mechanically coupled to the shock absorber 108 and the proximal end 208 of the actuator housing 202 is configured to be pivotally attached to a second fixed point on the aircraft 2400. In yet another example, the mechanical linkage of the landing gear assembly 102 includes the trailing arm 112, the shock absorber 108, the stowage actuator 104, and a coupling member 1202 between the stowage actuator 104 and the shock absorber 108.

[0040] In yet another example of the landing gear assembly 102, the stowage actuator 104 includes a rod hydraulic port 234 and a piston hydraulic port 236. The rod hydraulic port 234 is disposed near the distal end 206 of the actuator housing 202 to provide fluid access to the rod chamber 222. The piston hydraulic port 236 is disposed near the proximal end 208 of the actuator housing 202 to provide fluid access to the piston chamber 224.

[0041] In yet another example of the landing gear assembly 102, the surface contacting assembly 118 includes a wheel, ski, or any other suitable surface contacting assembly. In yet another example of the landing gear assembly 102, the extended piston position 216 of the piston stroke 214 in the cylinder bore 210 is associated with a fully extended state 1002 of the landing gear assembly 102 associated with a landing sequence of the aircraft 2400. In yet another example of the landing gear assembly 102, the retracted piston position 218 of the piston stroke 214 in the cylinder bore 210 is associated with a fully retracted state 802 of the landing gear assembly 102 associated with a takeoff sequence of the aircraft 2400. In yet another example of the landing gear assembly 102, the kneel stop position 302 of the piston stroke 214 in the cylinder bore 210 is associated with a kneel state 602 of the landing gear assembly 102 during ground operations of the aircraft 2400. In yet another example of the landing gear assembly 102, the knee stop assembly 106 is configured to allow the piston 212 to move from a knee stop position 302 of the piston stroke 214 to an extended piston position 216 within the cylinder bore 210. In yet another example of the landing gear assembly 102, the knee stop assembly 106 is configured to selectively disengage the knee stop position 302 of the piston stroke 214 within the cylinder bore 210 to allow the piston 212 to move to a retracted piston position 218 of the piston stroke 214.

[0042] In yet another example of the landing gear assembly 102, the kneel stop assembly 106 includes a kneel stop housing 1102, a kneel stop insertion port 308, and a kneel stop cancellation port 312. The kneel stop housing 1102 is fixed to an outer surface 220 of the actuator housing 202 of the stowed actuator 104 relative to an extension piston location 216 in the cylinder bore 210 of the stowed actuator 104 and a storage piston location 218 in the cylinder bore 210. The kneel stop housing 1102 includes a kneel stop distal end 1104 closer to a distal end 206 of the actuator housing 202 and a kneel stop proximal end 1106 closer to a proximal end 208 of the actuator housing 202. The kneel stop housing 1102 defines a cavity 304 between an inner surface 306 of the kneel stop housing 1102 and the outer surface 220 of the actuator housing 202. A knee stop insertion port 308 is disposed on the knee stop housing 1102 and provides fluid access to a knee stop insertion chamber 310 formed within the cavity 304. A knee stop cancellation port 312 is disposed on the knee stop housing 1102 and provides fluid access to a knee stop cancellation chamber 314 formed within the cavity 304.

[0043] In a further example of the landing gear assembly 102, the knee stop assembly 106 also includes at least one knee stop segment 1108 disposed within the cavity 304 of the knee stop housing 1102 at a predetermined point 1109 along the longitudinal axis 204 of the actuator housing 202. The predetermined point 1109 is associated with the knee stop position 302. The actuator housing 202 includes at least one knee stop opening 1110 extending through the actuator housing 202 into the cylinder bore 210. The at least one knee stop opening 1110 is configured to receive at least a portion of the at least one knee stop segment 1108. The at least one knee stop segment 1108 is configured for selective insertion into and selective removal from the at least one knee stop opening 1110. In yet another example, the at least one knee stop segment 1108 includes at least two knee stop segments 1108 radially distributed around the actuator housing 202 at the predetermined point 1109. In this example, the at least one knee stop opening 1110 includes at least two knee stop openings 1110 radially distributed around the actuator housing 202 for the at least two knee stop segments 1108.

[0044] In another further example of the landing gear assembly 102, the knee stop assembly 106 also includes an upper biasing member 1112, an upper slider member 1114, a lower biasing member 1118, and a lower slider member 1120. The upper biasing member 1112 is disposed in the cavity 304 between the knee stop housing 1102 and the actuator housing 202 near the knee stop distal end 1104 of the knee stop housing 1102. The upper biasing slider member 1114 is disposed in the cavity 304 between the knee stop housing 1102 and the actuator housing 202 between the upper biasing member 1112 and the at least one stop segment 1108. The upper slider member 1114 includes a first portion of an upper slider outer surface 1116 that faces the inner surface 306 of the knee stop housing 1102. A first portion of the upper slider outer surface 1116 and a corresponding portion of the inner surface 306 of the kneel stop housing 1102 are configured to form a kneel stop insertion chamber 310. An upper biasing member 1112 is configured to bias the upper slider member 1114 toward the at least one kneel stop segment 1108. A lower biasing member 1118 is disposed in the cavity 304 between the kneel stop housing 1102 and the actuator housing 202 near the kneel stop proximal end 1106 of the kneel stop housing 1102. A lower slider member 1120 is disposed in the cavity 304 between the kneel stop housing 1102 and the actuator housing 202 between the at least one kneel stop segment 1108 and the lower biasing member 1118. The lower slider member 1120 includes a first portion of a lower slider outer surface 1122 facing the inner surface 306 of the kneel stop housing 1102. A first portion of the lower slider outer surface 1122 and an opposing portion of the inner surface 306 of the knee stop housing 1102 are configured to form a knee stop cancellation chamber 314. A lower biasing member 1118 is configured to bias the lower slider member 1120 toward the at least one knee stop segment 1108.

[0045] By way of example, and referring generally to FIGS. 1-11, 13-22, and 24, the present disclosure is directed to methods 1300, 1400, 1500, 1600, 1700, 1800, 1900, 2000, 2100, 2200 for kneeling a landing gear assembly 102 of an aircraft 2400. FIG. 1 discloses an example stow actuator assembly 100 for an example landing gear assembly 102. FIG. 2 is a cross-sectional view of an example stow actuator 104 of the stow actuator assembly 100 of FIG. 1. FIG. 3 illustrates a cross-sectional view of an example kneel stop assembly 106 of the stow actuator assembly 100 of FIG. 1 with the kneel stop segment 1108 inserted into the stow actuator 104 and in an extended position. FIG. 4 is a functional diagram of the landing gear assembly 102 of FIG. 1 with the landing gear assembly 102 in an extended state and the weight of the aircraft 2400 on the wheels. FIG. 5 is a cross-sectional view of an example kneel stop assembly 106 of the stowage actuator assembly 100 of FIG. 1 with a kneel stop segment 1108 inserted into the stowage actuator 104 and the stowage actuator 104 in a kneeling position.

[0046] FIG. 6 illustrates a functional diagram of the landing gear assembly 102 of FIG. 1 with the landing gear assembly 102 in a kneeling position and the weight of the aircraft 2400 on the wheels. FIG. 7 illustrates a cross-sectional view of an example kneel stop assembly 106 of the stow actuator assembly 100 of FIG. 1 with the kneel stop segments 1108 retracted from the stow actuator 104 and the stow actuator 104 in a stowed position. FIG. 8 illustrates a functional diagram of the landing gear assembly 102 of FIG. 1 with the landing gear assembly 102 in a stowed position and the aircraft 2400 in flight. FIG. 9 illustrates a cross-sectional view of an example kneel stop assembly 106 of the stow actuator assembly 100 of FIG. 1 with the kneel stop segments 1108 retracted from the stow actuator 104 and the stow actuator 104 in an extended position. FIG. 10 illustrates a functional diagram of the landing gear assembly 102 of FIG. 1 with the landing gear assembly 102 in an extended position and the aircraft 2400 in flight. FIG. 11 provides an exploded view of the example knee stop assembly 106 of FIG. 3 relative to the example stowage actuator 104 of the stowage actuator assembly 100 of FIG.

[0047] FIG. 13 discloses an example of a method 1300 for kneeling a landing gear assembly 102 of an aircraft 2400. FIG. 14 discloses, in combination with FIG. 13, an example of a method 1400 for kneeling a landing gear assembly 102 of an aircraft 2400. FIG. 15 discloses, in combination with FIG. 13, an example of a method 1500 for kneeling a landing gear assembly 102 of an aircraft 2400. FIG. 16 discloses, in combination with FIG. 13, an example of a method 1600 for kneeling a landing gear assembly 102 of an aircraft 2400. FIG. 17 discloses, in combination with FIG. 13 and FIG. 16, an example of a method 1700 for kneeling a landing gear assembly 102 of an aircraft 2400. FIG. 18 discloses, in combination with FIG. 13, an example of a method 1800 for kneeling a landing gear assembly 102 of an aircraft 2400. FIG. 19, in combination with FIG. 13 and FIG. 18, discloses an example of a method 1900 for kneeling a landing gear assembly 102 of an aircraft 2400. FIG. 20, in combination with FIG. 13 and FIG. 18, discloses an example of a method 2000 for kneeling a landing gear assembly 102 of an aircraft 2400. FIG. 21, in combination with FIG. 13 and FIG. 18, discloses an example of a method 2100 for kneeling a landing gear assembly 102 of an aircraft 2400. FIG. 22, in combination with FIG. 13, FIG. 18, and FIG. 21, discloses an example of a method 2200 for kneeling a landing gear assembly 102 of an aircraft 2400. FIG. 24 illustrates an aircraft 2400 incorporating one or more embodiments of a stowed actuator assembly 100 and landing gear assembly 102 disclosed herein.

[0048] 1-3 , 6 , 10 , 13 , and 24 , in one or more examples, a method 1300 (see FIG. 13 ) for kneeling a landing gear assembly 102 of an aircraft 2400 includes performing ground operations 1302 for the aircraft 2400 with the landing gear assembly 102 in a fully extended state 1002 and a stow actuator 104 of the landing gear assembly 102 in an extended piston position 216. In 1304, a kneeling feature of the landing gear assembly 102 is activated to create a knee stop position 302 in the stow actuator 104 that shortens a piston stroke 214 of the stow actuator 104 by preventing movement of the piston 212 in the stow actuator 104 beyond the knee stop position 302 toward a stow piston position 218. At 1306 , the landing gear assembly 102 is moved from the fully extended state 1002 to the kneeling state 602 by moving the stow actuator 104 from the extended piston position 216 to the kneel stop position 302 .

[0049] In another example of the method 1300, the extended piston position 216 of the piston stroke 214 in the cylinder bore 210 of the stow actuator 104 is associated with a fully extended state 1002 of the landing gear assembly 102 associated with a landing sequence of the aircraft 2400. In yet another example of the method 1300, the stow piston position 218 of the piston stroke 214 in the cylinder bore 210 of the stow actuator 104 is associated with a fully stowed state 802 of the landing gear assembly 102 associated with a takeoff sequence of the aircraft 2400. In yet another example of the method 1300, the method 1300 is associated with a kneel stop position 302 of the piston stroke 214 in the cylinder bore 210 of the stow actuator 104 is associated with a kneel state 602 of the landing gear assembly 102 during ground operations of the aircraft 2400. In yet another example, the method 1300 includes moving 1308 the landing gear assembly 102 from the kneeling state 602 to the fully extended state 1002 by moving the stowage actuator 104 from the kneel stop position 302 to the extended piston position 216 while a kneeling feature of the landing gear assembly 102 is in an actuated state.

[0050] 1-3, 13, 14, and 24, in one or more examples, a method 1400 (see FIG. 14) for kneeling a landing gear assembly 102 of an aircraft 2400 includes the method 1300 of FIG. 13. The method 1400 continues from 1304 to 1402, where in response to pressurized fluid from a pressurized fluid source being received at a kneel stop insertion port 308 of a kneel stop assembly 106 secured to an exterior surface 220 of the stowage actuator 104, a kneel stop position 302 is formed within the stowage actuator 104. The method 1400 continues from 1402 to 1306 (see FIG. 13). In other examples, the method also includes allowing 1404 pressurized fluid to exit the kneel stop assembly 106 via the kneel stop insertion port 308 without affecting a current state of the kneel stop position 302 after the pressurized fluid source is no longer applying pressurized fluid.

[0051] 1-3, 11, 13, 15, and 24, in one or more examples, a method 1500 (see FIG. 15) for kneeling a landing gear assembly 102 of an aircraft 2400 includes the method 1300 of FIG. 13. The method 1500 continues from 1304 to 1502, where at 1502, in response to pressurized fluid from a pressurized fluid source being received at a kneel stop insertion port 308 of the kneel stop assembly 106, a kneel stop position 302 is formed within the stowage actuator 104 by inserting at least one kneel stop segment 1108 of the kneel stop assembly 106 secured to the outer surface 220 of the stowage actuator 104 into at least one kneel stop opening 1110 extending through the outer surface 220 into the cylinder bore 210 of the stowage actuator 104. The method 1500 continues from 1502 to 1306 (see FIG. 13).

[0052] 1-3, 11, 13, 16, and 24, in one or more examples, a method 1600 (see FIG. 16) for kneeling a landing gear assembly 102 of an aircraft 2400 includes the method 1300 of FIG. 13. The method 1600 continues from 1304 to 1602, where at 1602, a kneel stop position 302 is formed within the stowage actuator 104. At 1604, the forming (1602) includes moving an upper slider member 1114 of the kneel stop assembly 106, which is secured to the outer surface 220 of the stowage actuator 104, toward an upper biasing member 1112 of the kneel stop assembly 106 and away from at least one kneel stop segment 1108 of the kneel stop assembly 106, in response to pressurized fluid from a pressurized fluid source being received at a kneel stop insertion chamber 310 of the kneel stop assembly 106 via a kneel stop insertion port 308 of the kneel stop assembly 106. After 1604, after the upper slider member 1114 moves toward the upper biasing member 1112, the at least one knee stop segment 1108 is no longer locked and is free to move between the inner surface 306 of the knee stop housing 1102 and the outer surface 220 of the actuator housing 202. At 1606, the forming (1602) also includes moving the lower slider member 1120 of the knee stop assembly 106 toward the at least one knee stop segment 1108 in response to the upper slider member 1114 moving away from the at least one knee stop segment 1108, such that the at least one knee stop segment 1108 is free to move laterally and the lower biasing member 1118 biases the lower slider member 1120 toward the at least one knee stop segment 1108.At 1608, the forming (1602) also includes inserting the at least one kneel stop segment 1108 into the at least one kneel stop opening 1110 extending through the outer surface 220 into the cylinder bore 210 of the storage actuator 104 as the lower slider member 1120 moves toward the at least one kneel stop segment 1108 and opposing tapered surfaces of the lower slider member 1120 press the at least one kneel stop segment 1108 into the at least one kneel stop opening 1110 to form a kneel stop position 302 within the cylinder bore 210 of the storage actuator 104. The method 1600 continues from 1602 to 1306 (see FIG. 13 ).

[0053] 1-3, 11, 13, 16, 17, and 24, in one or more examples, a method 1700 (see FIG. 17) for kneeling a landing gear assembly 102 of an aircraft 2400 includes the method 1300 of FIG. 13 and the method 1600 of FIG. 16. The method 1700 continues from 1608 to 1702, where at 1702, the kneel stop position 302 in the stowed actuator 104 is locked after at least one kneel stop segment 1108 of the kneel stop assembly 106 is inserted into at least one kneel stop opening 1110 of the actuator housing 202. At 1704, the at least one kneel stop segment 1108 inserted into the at least one kneel stop opening 1110 is held, where pressure is applied or not applied to the kneel stop insertion port 308 until pressure is applied to the kneel stop cancellation port 312 of the kneel stop assembly 106.

[0054] 1-3 , 10 , 13 , 18 , and 24 , in one or more examples, a method 1800 ( FIG. 18 ) for kneeling a landing gear assembly 102 of an aircraft 2400 includes the method 1300 of FIG. 13 . The method 1800 continues from 1306 to 1802, where the kneeling feature of the landing gear assembly 102 is stopped and the kneel stop position 302 is removed from the stow actuator 104 to allow movement of the piston 212 to the stow piston position 218 of the piston stroke 214. At 1804, a takeoff sequence is initiated for the aircraft 2400 with the landing gear assembly 102 in the fully extended state 1002 and the stow actuator 104 of the landing gear assembly 102 in the extended piston position 216. At 1806, the takeoff sequence is complete and flight operations are conducted for the aircraft 2400 with the landing gear assemblies 102 in the fully stowed state 802 and the stow actuators 104 in the stow piston position 218.

[0055] 1-3, 13, 18, 19, and 24, in one or more examples, a method 1900 (see FIG. 19) for kneeling a landing gear assembly 102 of an aircraft 2400 includes the method 1300 of FIG. 13 and the method 1800 of FIG. 18. The method 1900 continues from 1802 to 1902, where at 1902, in response to pressurized fluid from a pressurized fluid source being received at a knee stop insertion port 312 of a knee stop assembly 106 secured to an exterior surface 220 of the stowage actuator 104, the knee stop position 302 is released from the stowage actuator 104. The method 1900 continues from 1902 to 1804 (see FIG. 18). In another example, the method 1900 also includes allowing (1904) pressurized fluid to exit the knee stop assembly 106 via the knee stop cancel port 312 without affecting the current state of the knee stop position 302 after the pressurized fluid source is no longer adding pressurized fluid.

[0056] 1-3, 11, 13, 18, 20, and 24, in one or more examples, a method 2000 (see FIG. 20) for kneeling a landing gear assembly 102 of an aircraft 2400 includes the method 1300 of FIG. 13 and the method 1800 of FIG. 18. The method 2000 continues from 1802 to 2002, where at 2002, in response to pressurized fluid from a pressurized fluid source being received at a kneel stop cancellation port 312 of the kneel stop assembly 106, a kneel stop position 302 is cancelled from the stowage actuator 104 by retracting at least one kneel stop segment 1108 of the kneel stop assembly 106 secured to the outer surface 220 of the stowage actuator 104 from at least one kneel stop opening 1110 extending through the outer surface 220 into the cylinder bore 210 of the stowage actuator 104. The method 2000 continues from 2002 to 1804 (see FIG. 18).

[0057] 1-3, 11, 13, 18, 21, and 24, in one or more examples, a method 2100 (see FIG. 21) for kneeling a landing gear assembly 102 of an aircraft 2400 includes the method 1300 of FIG 13 and the method 1800 of FIG 18. The method 2100 continues from 1802 to 2102 where the kneel stop position 302 is released from the removal actuator 104. At 2104, the canceling (2102) includes moving a lower slider member 1120 of the kneel stop assembly 106, which is secured to an outer surface 220 of the storage actuator 104, toward a lower biasing member 1118 of the kneel stop assembly 106 and away from at least one kneel stop segment 1108 of the kneel stop assembly 106, in response to pressurized fluid from a pressurized fluid source being received at the kneel stop canceling chamber 314 of the kneel stop assembly 106 via a kneel stop canceling port 312 of the kneel stop assembly 106. After the lower slider member 1120 has moved toward the lower biasing member 1118, the at least one kneel stop segment 1108 is no longer locked and is free to move between the inner surface 306 of the kneel stop housing 1102 and the outer surface 220 of the actuator housing 202. In 2106, the resolving (2102) also includes moving the upper slider member 1114 of the knee stop assembly 106 toward the at least one knee stop segment 1108 in response to the lower slider member 1120 moving away from the at least one knee stop segment 1108, such that the at least one knee stop segment 1108 is free to move laterally and the upper biasing member 1112 biases the upper slider member 1114 toward the at least one knee stop segment 1108.At 2108, the canceling (2102) also includes retracting the at least one kneel stop segment 1108 from at least one kneel stop opening 1110 extending through the outer surface 220 into the cylinder bore 210 of the storage actuator 104 in response to the upper slider member 1114 moving toward the at least one kneel stop segment 1108 and the opposing tapered surfaces of the upper slider member 1114 pushing the at least one kneel stop segment 1108 away from the at least one kneel stop opening 1110, thereby canceling the kneel stop position 302 from the cylinder bore 210 of the storage actuator 104.

[0058] 1-3, 11, 13, 18, 21, 22, and 24, in one or more examples, a method 2200 (see FIG. 22) for kneeling a landing gear assembly 102 of an aircraft 2400 includes the method 1300 of FIG. 13, the method 1800 of FIG. 18, and the method 2100 of FIG. 21. The method 2200 continues from 2108 to 2202, where a knee stop position 302 in a stowed actuator 104 is locked out after the at least one knee stop segment 1108 of the knee stop assembly 106 is retracted from the at least one knee stop opening 1110 of the actuator housing 202. In 2204, pressure is applied or not applied to the knee stop cancellation port 312 until at least one knee stop segment 1108 is held retracted from at least one knee stop opening 1110 and pressure is applied to the knee stop insertion port 308 of the knee stop assembly 106.

[0059] The embodiments of the stow actuator assembly 100, landing gear assembly 102, and methods 1300, 1400, 1500, 1600, 1700, 1800, 1900, 2000, 2100, 2200 for kneeling of the landing gear assembly 102 of the aircraft 2400 may be relevant or used in the context of the manufacture of aircraft. Although an example of an aircraft is described, the embodiments and principles disclosed herein may also be applied to other products in the aerospace industry and other industries, such as the automotive industry, the space industry, the construction industry, and other design and manufacturing industries. Correspondingly, in addition to aircraft, the embodiments and principles disclosed herein may be applied to the use of kneeling in the manufacture and / or operation of various vehicles and in the construction of various buildings.

[0060] The above detailed description refers to the accompanying drawings. The accompanying drawings show specific examples described by the present disclosure. Other examples with different structures and steps do not depart from the scope of the present disclosure. Similar reference numbers may represent the same features, elements, or components in various drawings. Throughout the present disclosure, any of a plurality of items may be referred to individually as that item, and a plurality of items may be referred to collectively as that item or with a plurality of similar reference numbers. Furthermore, in this specification, a feature, element, component, or step following the term "a" or "an" is not to be understood as excluding a plurality of features, elements, components, or steps, unless expressly stated to exclude it.

[0061] Illustrative, non-exhaustive examples of the inventive subject matter of the present disclosure may be, but are not necessarily, claimed. Reference herein to an "example" means that one or more features, structures, elements, components, properties, and / or operational steps described in connection with the example are included in at least one aspect, embodiment, and / or realization of the inventive subject matter of the present disclosure. Thus, the phrases "one example" and "one or more examples" and similar phrases used throughout this disclosure may, but do not necessarily, refer to the same example. Furthermore, the inventive subject matter characterizing any one example may, but does not necessarily, include the inventive subject matter characterizing any other example. Furthermore, the inventive subject matter characterizing any one example may, but does not necessarily, be combined with the inventive subject matter characterizing any other example.

[0062] As used herein, a system, apparatus, structure, article, element, component, or hardware that is "configured to" perform a particular function is in fact capable of performing that particular function without any modification, and not merely likely to perform that particular function after further modification. In other words, a system, apparatus, device, structure, article, element, component, or hardware that is "configured to" perform a particular function is specifically selected, created, implemented, utilized, programmed, and / or designed for the purpose of performing that particular function. As used herein, the phrase "configured to" refers to existing characteristics of a system, apparatus, structure, article, element, component, or hardware that enable the system, apparatus, structure, article, element, component, or hardware to perform a particular function without further modification. For purposes of this disclosure, a system, apparatus, device, structure, article, element, component, or hardware that is described as "configured to" perform a particular function may additionally or alternatively be described as "adapted to" and / or "operative to" perform that function.

[0063] Unless otherwise indicated, the terms "first," "second," "third," etc. are used herein merely as labels and are not intended to impose any sequential, positional, or hierarchical requirements on the items to which they refer. Moreover, reference to, for example, a "second" item does not require or preclude the presence of, for example, a "first" or lower numbered item and / or, for example, a "third" or higher numbered item.

[0064] As used herein, the phrase "at least one of" used in conjunction with listed items means that various combinations of one or more of the listed items may be utilized and that only one of the listed items may be required. For example, "at least one of item A, item B, and item C" may include, but is not limited to, "item A" or "item A and item B." This example may also include item A, item B, and item C, or item B and item C. In other examples, "at least one of" may be, but is not limited to, for example, "2 item A, 1 item B, and 10 item C," "4 item B, and 7 item C," and other suitable combinations. As used herein, the phrase "and / or" and the indicia " / " include any and all combinations of one or more of the associated listed items.

[0065] As used herein, the terms "coupled," "coupling," and similar terms refer to two or more elements that are coupled, connected, fastened, connected, in communication, or otherwise associated with one another (e.g., mechanically, electrically, fluidly, optically, electromagnetically). In various embodiments, these elements may be directly or indirectly associated. For example, element A may be directly associated with element B. As another example, element A may be associated with element B, e.g., through another element C. It should be understood that not all relationships between the various disclosed elements are necessarily depicted. Correspondingly, other couplings than those shown in the figures may exist.

[0066] As used herein, the term "approximately" refers to or describes a condition that is close to, but not exactly, a specified condition that still performs a desired function or achieves a desired result. As an example, the term "about" refers to a condition that is within an acceptable, predetermined tolerance or precision, such as within 10% of a specified condition. However, the term "about" does not exclude a condition that is exactly the specified condition. As used herein, the term "substantially" refers to a condition that is essentially a specified condition that performs a desired function or achieves a desired result.

[0067] In the above-referenced FIGS. 1-11, 12A-12C, and 24, functional elements, features, or components thereof may be depicted and do not necessarily imply any particular structure. Correspondingly, modifications, additions, and / or omissions may be made to the illustrated structures. Furthermore, those skilled in the art will appreciate that not all elements, features, and / or components described and illustrated in the above-mentioned FIGS. 1-11, 12A-12C, and 24 need to be included in every embodiment, and not all elements, features, and / or components described herein are necessarily shown in each illustrative embodiment. Correspondingly, some of the elements, features, and / or components described and illustrated in FIGS. 1-11, 12A-12C, and 24 may be combined in various ways without needing to include other features described and illustrated in FIGS. 1-11, 12A-12C, and 24, other drawings, and / or the accompanying disclosure, although such combinations are not expressly shown herein. Similarly, additional features not limited to the examples presented may be combined with some or all of the features shown and described herein. Unless expressly stated otherwise, the schematic diagrams of the examples shown in the above-mentioned FIGS. 1-11, 12A-12C, and 24 do not imply structural limitations on the exemplary examples. Rather, it should be understood that although one exemplary structure is shown, the structure may be modified as necessary. Correspondingly, modifications, additions, and / or omissions may be made to the illustrated structure. Furthermore, elements, features, and / or components that serve similar or at least substantially similar purposes are labeled with similar reference numerals in each of FIGS. 1-11, 12A-12C, and 24, and such elements, features, and / or components may not be described in detail herein when referring to each of FIGS. 1-11, 12A-12C, and 24. Similarly, not all elements, features, and / or components may be numbered in each of Figures 1-11, 12A-12C, and 24, but their associated reference numbers may be used consistently throughout this specification.

[0068] In the previously referenced Figures 12-23, the blocks may represent processes, steps, and / or portions thereof, and the lines connecting the various blocks do not imply any particular order or dependency of the processes or portions thereof. It will be understood that not all dependencies between the various disclosed processes are necessarily depicted. Figures 12-23 and the accompanying disclosure describing the steps of the disclosed method described herein should not be construed as necessarily dictating the sequence in which the steps are performed. Rather, it should be understood that although one exemplary order is shown, the sequence of operations may be modified where appropriate. Thus, modifications, additions, and / or omissions may be made to the illustrated processes, and certain steps may be performed in a different order or simultaneously. Moreover, one skilled in the art will appreciate that it is not necessary to perform all of the steps described.

[0069] Furthermore, references to features, advantages, or similar language used throughout this specification do not imply that all features and advantages that may be realized by the embodiments disclosed herein should or will be present in any single embodiment. Rather, language referring to features and advantages should be understood to mean that the particular feature, advantage, or characteristic described in connection with an embodiment is included in at least one embodiment. Thus, descriptions of features, advantages, and similar language used throughout this disclosure may, but do not necessarily, refer to the same embodiment.

[0070] Examples of the subject matter disclosed herein may be described in the context of aircraft manufacturing and service method 2300 illustrated in FIG. 15 and aircraft 2400 illustrated in FIG. 24. In one or more examples, the disclosed methods and systems for associating inspection data for a part under inspection with an end item coordinate system may be used in aircraft manufacturing. During pre-production, service method 2300 may include specification and design of aircraft 2400 (block 2302) and material procurement (block 2304). During production, manufacturing of components and subassemblies of aircraft 2400 (block 2306) and system integration (block 2308) may occur. Thereafter, aircraft 2400 may undergo certification and delivery (block 2310) and be placed into service (block 2312). During operation, aircraft 2400 may be scheduled for routine maintenance and service (block 2314). Periodic maintenance and service may include modification, reconfiguration, modification, etc. of one or more systems of aircraft 2400.

[0071] Each of the processes of maintenance method 2300 may be performed or implemented by a system integrator, a third party, and / or an operator (e.g., a customer). For purposes of this specification, a system integrator may include, but is not limited to, any number of aircraft manufacturers and major system subcontractors, a third party may include, but is not limited to, any number of vendors, subcontractors, and suppliers, and an operator may be an airline, a leasing company, a military entity, a service organization, etc.

[0072] As shown in FIG. 24 , an aircraft 2400 produced by the maintenance method 2300 may include an airframe 2402 having a number of high level systems 2404 and an interior 2406. Examples of high level systems 2404 include one or more of a propulsion system 2408, an electrical system 2410, a hydraulic system 2412, and an environmental system 2414. Any number of other systems may also be included. Although an aerospace example is shown here, the principles disclosed herein may be applied to other industries, such as the automotive industry. Correspondingly, the principles disclosed herein may be applied to other vehicles (e.g., land vehicles, marine vehicles, space vehicles, etc.) in addition to the aircraft 2400.

[0073] Systems and methods for associating inspection data for a part under inspection with an end item coordinate system may be used during any one or more stages of manufacturing and maintenance method 2300. For example, components or subassemblies corresponding to manufacturing of components and subassemblies (block 2306) may be fabricated or manufactured in a similar manner as components or subassemblies manufactured during operation of aircraft 2400 (block 2312). Further, one or more embodiments of the system, method, or combination thereof may be utilized during the manufacturing stage (blocks 2306 and 2308), for example, by substantially streamlining or reducing the cost of assembly of aircraft 2400. Similarly, one or more embodiments implementing the apparatus or method, or combination thereof, may be utilized during operation of aircraft 2400 (block 2312) and / or during maintenance and service (block 2314), for example and without limitation.

[0074] The described features, advantages, and characteristics of one embodiment may be combined in any suitable manner in one or more other embodiments. Those skilled in the art will appreciate that the embodiments described herein may be practiced without one or more of the specific features or advantages of a particular embodiment. In other cases, additional features and advantages may be recognized in a particular embodiment that are not present in all embodiments. Although various embodiments of the stow actuator assembly 100, landing gear assembly 102, and method 1300, 1400, 1500, 1600, 1700, 1800, 1900, 2000, 2100, 2200 for kneeling a landing gear assembly 102 of an aircraft 2400 have been shown and described, modifications will occur to those skilled in the art upon reading this specification. The present application includes such modifications and is limited only by the scope of the claims.

Claims

1. 1. A stowage actuator assembly (100) for a landing gear assembly (102) of an aircraft (2400), comprising: A storage actuator (104), an actuator housing (202) defining a longitudinal axis (204) extending through a distal end (206) and a proximal end (208) and including a cylinder bore (210) aligned along the longitudinal axis (204); a piston (212) configured to move within the cylinder bore (210) along the longitudinal axis (204), the cylinder bore (210) defining a piston stroke (214) within the actuator housing (202), the piston stroke (214) defining limits of movement of the piston (212), the piston stroke (214) including an extended piston position (216) relative to the distal end (206) of the actuator housing (202) and a retracted piston position (218) relative to the proximal end (208) of the actuator housing (202); a storage actuator (104) including: a knee stop assembly (106) secured to an outer surface (220) of the actuator housing (202) relative to the extended piston position (216) in the cylinder bore (210) and the retracted piston position (218) in the cylinder bore (210), the knee stop assembly (106) configured to selectively form a knee stop position (302) in the cylinder bore (210) for shortening the piston stroke (214) by preventing movement of the piston (212) to the retracted piston position (218); A stow actuator assembly (100) for a landing gear assembly (102) of an aircraft (2400), comprising:

2. a shock absorber (108) secured to the proximal end (208) of the actuator housing (202) such that the shock absorber (108) and the stowed actuator (104) are aligned along the longitudinal axis (204) of the actuator housing (202) to form an in-line shock absorber actuator (110); and configured to be pivotally attached to a trailing arm (112) of the landing gear assembly (102). The retractable actuator assembly of claim 1 further comprising:

3. the piston (212) defines a rod chamber (222) within the cylinder bore (210) relative to the distal end (206) of the actuator housing (202) and a piston chamber (224) within the cylinder bore (210) relative to the proximal end (208) of the actuator housing (202); a piston rod (226) disposed within the rod chamber (222) and including a first end (228) attached to the piston (212) and a second end (230) extending through a sealed opening (232) in the distal end (206) of the actuator housing (202); The retractable actuator assembly of claim 1 further comprising:

4. the second end (230) of the piston rod (226) is configured to be pivotally attached to a fixed point on the aircraft (2400), and the stowage actuator assembly (100) is a shock absorber (108) secured to the proximal end (208) of the actuator housing (202) such that the shock absorber (108) and the stowed actuator (104) are aligned along the longitudinal axis (204) of the actuator housing (202) to form an in-line shock absorber actuator (110); and configured to be pivotally attached to a trailing arm (112) of the landing gear assembly (102). The retractable actuator assembly of claim 3 further comprising:

5. 5. The stowage actuator assembly of claim 4, wherein a mechanical linkage of the landing gear assembly (102) comprises a trailing arm (112) of the landing gear assembly (102) and the in-line shock absorber actuator (110).

6. the proximal end (208) of the actuator housing (202) is configured to be pivotally mounted to a fixed point on the aircraft (2400), and the stowed actuator assembly (100) is a shock absorber (108) mechanically coupled to the second end (230) of the piston rod (226) and configured to be pivotally attached to a trailing arm (112) of the landing gear assembly (102). The retractable actuator assembly of claim 3 further comprising:

7. 7. The stowage actuator assembly of claim 6, wherein a mechanical linkage of the landing gear assembly (102) includes a trailing arm (112) of the landing gear assembly (102), the shock absorber (108), the stowage actuator (104), and a coupling member (1202) between the stowage actuator (104) and the shock absorber (108).

8. The storage actuator (104) a rod hydraulic port (234) disposed near the distal end (206) of the actuator housing (202) for providing fluid access to the rod chamber (222); a piston hydraulic port (236) disposed near the proximal end (208) of the actuator housing (202) for providing fluid access to the piston chamber (224); The retractable actuator assembly of claim 3 further comprising:

9. 2. The stowage actuator assembly of claim 1, wherein the extended piston position (216) of the piston stroke (214) within the cylinder bore (210) is associated with a fully extended state (1002) of the landing gear assembly (102) associated with a landing sequence of the aircraft (2400).

10. 2. The stowage actuator assembly of claim 1, wherein the stowed piston position (218) of the piston stroke (214) within the cylinder bore (210) relates to a fully stowed state (802) of the landing gear assembly (102) associated with a takeoff sequence of the aircraft (2400).

11. 2. The stowage actuator assembly of claim 1, wherein the kneel stop position of the piston stroke in the cylinder bore is related to a kneel condition of the landing gear assembly during ground operations of the aircraft.

12. 2. The stored actuator assembly of claim 1, wherein the knee stop assembly is configured to enable the piston to move from the knee stop position of the piston stroke to the extended piston position within the cylinder bore.

13. 2. The stored actuator assembly of claim 1, wherein the knee stop assembly is configured to selectively disengage the knee stop position of the piston stroke within the cylinder bore to permit movement of the piston to the stored piston position.

14. The knee stop assembly (106) a knee stop housing (1102) fixed to the outer surface (220) of the actuator housing (202) of the stored actuator (104) relative to the extended piston position (216) in the cylinder bore (210) of the stored actuator (104) and the stored piston position (218) in the cylinder bore (210), the knee stop housing (1102) including a knee stop distal end (1104) closer to the distal end (206) of the actuator housing (202) and a knee stop proximal end (1106) closer to the proximal end (208) of the actuator housing (202), defining a cavity (304) between an inner surface (306) of the knee stop housing (1102) and the outer surface (220) of the actuator housing (202); a knee-stop insertion port (308) disposed on the knee-stop housing (1102) for providing fluid access to a knee-stop insertion chamber (310) formed within the cavity (304); a knee-stop cancellation port (312) disposed on the knee-stop housing (1102) for providing fluid access to a knee-stop cancellation chamber (314) formed within the cavity (304); The retractable actuator assembly of claim 1 , comprising:

15. 15. The storage actuator assembly of claim 14, wherein the kneel stop insertion port (308) is configured to receive pressurized fluid from a pressurized fluid source, and the kneel stop assembly (106) is configured to form the kneel stop position (302) in response to the pressurized fluid being received at the kneel stop insertion port (308).

16. The stowage actuator assembly of claim 15 , wherein the pressurized fluid comprises at least one of pressurized hydraulic fluid, pressurized oil, compressed gas, and compressed air.

17. 16. The storage actuator assembly of claim 15, wherein the kneel stop insertion port (308) is configured to allow the pressurized fluid to exit the kneel stop assembly (106) after the pressurized fluid source is no longer applying the pressurized fluid, and the kneel stop assembly (106) is configured such that the exit of the pressurized fluid through the kneel stop insertion port (308) does not affect a current state of the kneel stop position (302).

18. 15. The storage actuator assembly of claim 14, wherein the kneel stop cancellation port (312) is configured to receive pressurized fluid from a pressurized fluid source, and the kneel stop assembly (106) is configured to cancel the kneel stop position (302) in response to the pressurized fluid being received at the kneel stop cancellation port (312).

19. 20. The storage actuator assembly of claim 18, wherein the kneel stop cancellation port (312) is configured to allow the pressurized fluid to exit the kneel stop assembly (106), and the kneel stop assembly (106) is configured such that the exit of the pressurized fluid through the kneel stop cancellation port (312) does not affect a current state of the kneel stop position (302).

20. The knee stop assembly (106) at least one kneel stop segment (1108) disposed within the cavity (304) of the kneel stop housing (1102) at a predetermined point (1109) along the longitudinal axis (204) of the actuator housing (202), the predetermined point (1109) being associated with the kneel stop location (302), and the actuator housing (202) has at least one kneel stop opening (1110) extending through the actuator housing (202) into the cylinder bore (210). The storage assembly of claim 14, further comprising at least one knee stop segment (1108), wherein the at least one knee stop opening (1110) is configured to accommodate at least a portion of the at least one knee stop segment (1108), the at least one knee stop segment (1108) being configured for selective insertion into the at least one knee stop opening (1110) and for selective removal from the at least one knee stop opening (1110).

21. The storage assembly of claim 20, wherein the at least one knee stop segment (1108) includes at least two knee stop segments (1108) radially distributed around the actuator housing (202) at the predetermined point (1109), and the at least one knee stop opening (1110) includes at least two knee stop openings (1110) radially distributed around the actuator housing (202) relative to the at least two knee stop segments (1108).

22. The storage actuator assembly of claim 20, wherein the at least one kneel stop segment (1108) of the kneel stop assembly (106) correspondingly includes at least one of two kneel stop segments, three kneel stop segments, four kneel stop segments, five kneel stop segments, and six kneel stop segments, and the at least one kneel stop opening (1110) of the storage actuator (104) includes at least one of two kneel stop openings, three kneel stop openings, four kneel stop openings, five kneel stop openings, and six kneel stop openings.

23. The stored actuator assembly of claim 20, wherein the kneel stop insertion port (308) is configured to receive pressurized fluid from a pressurized fluid source, and in response to receiving the pressurized fluid at the kneel stop insertion port (308), the kneel stop assembly (106) is configured to insert the at least one kneel stop segment (1108) into the at least one kneel stop opening (1110) of the actuator housing (202) to form the kneel stop position (302).

24. The stored actuator assembly of claim 20, wherein the knee stop cancellation port (312) is configured to receive pressurized fluid from a pressurized fluid source, and in response to receiving the pressurized fluid at the knee stop cancellation port (312), the knee stop assembly (106) is configured to retract the at least one knee stop segment (1108) from the at least one knee stop opening (1110) of the actuator housing (202) to cancel the knee stop position (302).

25. The knee stop assembly (106) an upper biasing member (1112) disposed in the cavity (304) between the knee stop housing (1102) and the actuator housing (202) adjacent the knee stop distal end (1104) of the knee stop housing (1102); an upper slider member (1114) disposed within the cavity (304) between the knee stop housing (1102) and the actuator housing (202) between the upper biasing member (1112) and the at least one knee stop segment (1108), the upper slider member (1114) including a first portion of an upper slider outer surface (1116) facing the inner surface (306) of the knee stop housing (1102), the first portion of the upper slider outer surface (1116) and an opposing portion of the inner surface (306) of the knee stop housing (1102) configured to form a knee stop insertion chamber (310), the upper biasing member (1112) configured to bias the upper slider member (1114) toward the at least one knee stop segment (1108); a lower biasing member (1118) disposed in the cavity (304) between the knee stop housing (1102) and the actuator housing (202) adjacent the knee stop proximal end (1106) of the knee stop housing (1102); a lower slider member (1120) disposed within the cavity (304) between the knee stop housing (1102) and the actuator housing (202) between the at least one knee stop segment (1108) and the lower biasing member (1118), the lower slider member (1120) including a first portion of a lower slider outer surface (1122) facing the inner surface (306) of the knee stop housing (1102), the first portion of the lower slider outer surface (1122) and an opposing portion of the inner surface (306) of the knee stop housing (1102) configured to form the knee stop cancel chamber (314), the lower biasing member (1118) configured to bias the lower slider member (1120) toward the at least one knee stop segment (1108); 21. The containment assembly of claim 20, further comprising:

26. The upper slider member (1114) a second portion of the upper slider outer surface (1116) in opposing geometric relationship with an upper surface of the at least one knee stop segment (1108); a third portion of the upper slider outer surface (1116) adjacent a corresponding portion of the outer surface (220) of the actuator housing (202); Further comprising: the second portion of the upper slider outer surface (1116) rises from the third portion of the upper slider outer surface (1116) at a predetermined angle to the first portion of the upper slider outer surface (1116) to facilitate retraction of the at least one knee stop segment (1108) from the at least one knee stop opening (1110) of the actuator housing (202); The storage assembly of claim 25, wherein the first portion of the upper slider outer surface (1116) and the third portion of the upper slider outer surface (1116) are configured to slide between the at least one knee stop segment (1108) and the outer surface (220) of the actuator housing (202) in response to pressure being applied at the knee stop cancellation port (312) to prevent the at least one knee stop segment (1108) from being inserted into the at least one knee stop opening (1110).

27. The lower slider member (1120) a second portion of the lower slider outer surface (1122) in opposing geometric relationship with a lower surface of the at least one knee stop segment (1108); a third portion of the lower slider outer surface (1122) adjacent a corresponding portion of the inner surface (306) of the knee stop housing (1102); Further comprising: the second portion of the lower slider outer surface (1122) descends at a predetermined angle from the first portion of the lower slider outer surface (1122) to the third portion of the lower slider outer surface (1122) to facilitate insertion of the at least one knee stop segment (1108) into the at least one knee stop opening (1110) of the actuator housing (202); The storage assembly of claim 25, wherein the first portion of the lower slider outer surface (1122) and the third portion of the lower slider outer surface (1122) are configured to slide between the at least one knee stop segment (1108) and the inner surface (306) of the knee stop housing (1102) in response to pressure being applied at the knee stop insertion port (308) to prevent the at least one knee stop segment (1108) from retracting from the at least one knee stop opening (1110).

28. the knee stop insertion port (308) is configured to receive pressurized fluid from a pressurized fluid source and supply the pressurized fluid to the knee stop insertion chamber (310), and in response to the knee stop insertion chamber (310) receiving the pressurized fluid, the knee stop assembly (106) is configured to move the upper slider member (1114) toward the upper biasing member (1112) and away from the at least one knee stop segment (1108), and in response to the upper slider member (1114) moving away from the at least one knee stop segment (1108) and the lower biasing member (1118) biasing the lower slider member (1120) toward the at least one knee stop segment (1108), the knee stop assembly (106) is configured to 26. The storage actuator assembly of claim 25, wherein a lower slider member (1120) is configured to move the lower slider member (1120) toward the at least one kneel stop segment (1108), and the kneel stop assembly (106) is configured to insert the at least one kneel stop segment (1108) into the at least one kneel stop opening (1110) of the actuator housing (202) to form the kneel stop position (302) within the cylinder bore (210) of the storage actuator (104) in response to the lower slider member (1120) moving toward the at least one kneel stop segment (1108) and pushing the at least one kneel stop segment (1108) into the at least one kneel stop opening (1110).

29. 29. The stored actuator assembly of claim 28, wherein after the at least one knee stop segment (1108) of the knee stop assembly (106) is inserted into the at least one knee stop opening (1110) of the actuator housing (202), the lower biasing member (1118), the lower slider member (1120), and the at least one knee stop segment (1108) are configured to be moved to a locked position in which the lower slider member (1120) holds the at least one knee stop segment (1108) inserted into the at least one knee stop opening (1110), and wherein pressure is applied or not applied to the knee stop insertion port (308) until pressure is applied to the knee stop cancellation port (312).

30. the knee stop cancellation port (312) is configured to receive pressurized fluid from a pressurized fluid source and supply the pressurized fluid to the knee stop cancellation chamber (314), and in response to the knee stop cancellation chamber (314) receiving the pressurized fluid, the knee stop assembly (106) is configured to move the lower slider member (1120) toward the lower biasing member (1118) and away from the at least one knee stop segment (1108), and in response to the lower slider member (1120) moving away from the at least one knee stop segment (1108) and the upper biasing member (1112) biasing the upper slider member (1114) toward the at least one knee stop segment (1108), the knee stop assembly (106) 26. The storage actuator assembly of claim 25, wherein the upper slider member (1114) is configured to move the upper slider member (1114) toward the at least one kneel stop segment (1108), and in response to the upper slider member (1114) moving toward the at least one kneel stop segment (1108) and pushing the at least one kneel stop segment (1108) away from the at least one kneel stop opening (1110), the kneel stop assembly (106) is configured to retract the at least one kneel stop segment (1108) from the at least one kneel stop opening (1110) in the actuator housing (202) to eliminate the kneel stop position (302) from the cylinder bore (210) of the storage actuator (104).

31. The stored actuator assembly of claim 30, wherein after the at least one knee stop segment (1108) of the knee stop assembly (106) is retracted from the at least one knee stop opening (1110) in the actuator housing (202), the upper biasing member (1112), the upper slider member (1114), and the at least one knee stop segment (1108) are configured to be moved to a locked position in which the upper slider member (1114) holds the at least one knee stop segment (1108) retracted from the at least one knee stop opening (1110), and wherein pressure is applied or not applied to the knee stop cancellation port (312) until pressure is applied to the knee stop insertion port (308).

32. A landing gear assembly (102) for an aircraft (2400), comprising: A storage actuator (104), an actuator housing (202) defining a longitudinal axis (204) extending through a distal end (206) and a proximal end (208) and including a cylinder bore (210) aligned along the longitudinal axis (204); a piston (212) configured to move within the cylinder bore (210) along the longitudinal axis (204), the cylinder bore (210) defining a piston stroke (214) within the actuator housing (202), the piston stroke (214) defining limits of movement of the piston (212), the piston stroke (214) including an extended piston position (216) relative to the distal end (206) of the actuator housing (202) and a retracted piston position (218) relative to the proximal end (208) of the actuator housing (202); a storage actuator (104) including: a knee stop assembly (106) secured to an outer surface (220) of the actuator housing (202) relative to the extended piston position (216) in the cylinder bore (210) and the retracted piston position (218) in the cylinder bore (210), the knee stop assembly (106) configured to selectively form a knee stop position (302) in the cylinder bore (210) for shortening the piston stroke (214) by preventing movement of the piston (212) to the retracted piston position (218); a trailing arm (112) including an arm proximal end (114) and an arm distal end (116), the arm distal end (116) configured to be pivotally attached to a fixed point on the aircraft (2400), and the arm proximal end (114) configured to be attached to a surface contact assembly (118); a shock absorber (108) mechanically coupled to the storage actuator (104) and configured to be pivotally mounted to the trailing arm (112); A landing gear assembly (102) for an aircraft (2400) comprising:

33. 33. The landing gear assembly of claim 32, wherein the shock absorber is secured to the proximal end of the actuator housing such that the shock absorber and the stowage actuator are aligned along the longitudinal axis of the actuator housing to form an in-line shock absorber actuator.

34. the piston (212) defines a rod chamber (222) within the cylinder bore (210) relative to the distal end (206) of the actuator housing (202) and a piston chamber (224) within the cylinder bore (210) relative to the proximal end (208) of the actuator housing (202); a piston rod (226) disposed within the rod chamber (222) and including a first end (228) attached to the piston (212) and a second end (230) extending through a sealed opening (232) in the distal end (206) of the actuator housing (202); 33. The landing gear assembly of claim 32, further comprising:

35. 35. The landing gear assembly of claim 34, wherein the second end (230) of the piston rod (226) is configured to be pivotally attached to a second fixed point on the aircraft (2400), and the shock absorber (108) is fixed to the proximal end (208) of the actuator housing (202) such that the shock absorber (108) and the stowage actuator (104) are aligned along the longitudinal axis (204) of the actuator housing (202) to form an in-line shock absorber actuator (110).

36. 36. The landing gear assembly of claim 35, wherein a mechanical linkage of the landing gear assembly (102) comprises a trailing arm (112) and the in-line shock absorber actuator (110).

37. 35. The landing gear assembly of claim 34, wherein the second end (230) of the piston rod (226) in the storage actuator (104) is mechanically coupled to the shock absorber (108), and the proximal end (208) of the actuator housing (202) is configured to be pivotally attached to a second fixed point on the aircraft (2400).

38. 38. The landing gear assembly of claim 37, wherein a mechanical linkage of the landing gear assembly (102) includes the trailing arm (112), the shock absorber (108), the stowage actuator (104), and a coupling member (1202) between the stowage actuator (104) and the shock absorber (108).

39. The storage actuator (104) a rod hydraulic port (234) disposed near the distal end (206) of the actuator housing (202) for providing fluid access to the rod chamber (222); a piston hydraulic port (236) disposed near the proximal end (208) of the actuator housing (202) for providing fluid access to the piston chamber (224); 35. The landing gear assembly of claim 34, further comprising:

40. 33. The landing gear assembly of claim 32, wherein the surface contact assembly (118) comprises at least one of a wheel and a ski.

41. 33. The landing gear assembly of claim 32, wherein the extended piston position (216) of the piston stroke (214) within the cylinder bore (210) is associated with a fully extended state (1002) of the landing gear assembly (102) associated with a landing sequence of the aircraft (2400).

42. 33. The landing gear assembly of claim 32, wherein the stowed piston position (218) of the piston stroke (214) within the cylinder bore (210) relates to a fully stowed state (802) of the landing gear assembly (102) associated with a takeoff sequence of the aircraft (2400).

43. 33. The landing gear assembly of claim 32, wherein the kneel stop position (302) of the piston stroke (214) within the cylinder bore (210) is related to a kneel condition (602) of the landing gear assembly (102) during ground operations of the aircraft (2400).

44. 33. The landing gear assembly of claim 32, wherein the knee stop assembly is configured to enable the piston to move from the knee stop position of the piston stroke to the extended piston position within the cylinder bore.

45. The knee stop assembly (106) 33. The landing gear assembly of claim 32, configured to selectively overcome the knee stop position (302) of the piston stroke (214) within the cylinder bore (210) to enable movement of the piston (212) to the stored piston position (218) of the piston stroke (214).

46. The knee stop assembly (106) a knee stop housing (1102) fixed to the outer surface (220) of the actuator housing (202) of the stored actuator (104) relative to the extended piston position (216) in the cylinder bore (210) of the stored actuator (104) and the stored piston position (218) in the cylinder bore (210), the knee stop housing (1102) including a knee stop distal end (1104) closer to the distal end (206) of the actuator housing (202) and a knee stop proximal end (1106) closer to the proximal end (208) of the actuator housing (202), the knee stop housing (1102) defining a cavity (304) between an inner surface (306) of the knee stop housing (1102) and the outer surface (220) of the actuator housing (202); a knee-stop insertion port (308) disposed on the knee-stop housing (1102) for providing fluid access to a knee-stop insertion chamber (310) formed within the cavity (304); a knee-stop cancellation port (312) disposed on the knee-stop housing (1102) for providing fluid access to a knee-stop cancellation chamber (314) formed within the cavity (304); 33. The landing gear assembly of claim 32 including:

47. The knee stop assembly (106) at least one kneel stop segment (1108) disposed within the cavity (304) of the kneel stop housing (1102) at a predetermined point (1109) along the longitudinal axis (204) of the actuator housing (202), the predetermined point (1109) being associated with the kneel stop location (302), the actuator housing (202) including at least one kneel stop opening (1110) extending through the actuator housing (202) into the cylinder bore (210), the at least one kneel stop opening (1110) configured to receive at least a portion of the at least one kneel stop segment (1108), the at least one kneel stop segment (1108) configured for selective insertion into and selective removal from the at least one kneel stop opening (1110); 47. The landing gear assembly of claim 46, further comprising:

48. 48. The landing gear assembly of claim 47, wherein the at least one kneel stop segment (1108) includes at least two kneel stop segments (1108) radially distributed around the actuator housing (202) at the predetermined point (1109), and the at least one kneel stop opening (1110) includes at least two kneel stop openings (1110) radially distributed around the actuator housing (202) relative to the at least two kneel stop segments (1108).

49. The knee stop assembly (106) an upper biasing member (1112) disposed in the cavity (304) between the knee stop housing (1102) and the actuator housing (202) adjacent the knee stop distal end (1104) of the knee stop housing (1102); an upper slider member (1114) disposed within the cavity (304) between the knee stop housing (1102) and the actuator housing (202) between the upper biasing member (1112) and the at least one knee stop segment (1108), the upper slider member (1114) including a first portion of an upper slider outer surface (1116) facing the inner surface (306) of the knee stop housing (1102), the first portion of the upper slider outer surface (1116) and an opposing portion of the inner surface (306) of the knee stop housing (1102) configured to form a knee stop insertion chamber (310), the upper biasing member (1112) configured to bias the upper slider member (1114) toward the at least one knee stop segment (1108); a lower biasing member (1118) disposed in the cavity (304) between the knee stop housing (1102) and the actuator housing (202) adjacent the knee stop proximal end (1106) of the knee stop housing (1102); a lower slider member (1120) disposed within the cavity (304) between the knee stop housing (1102) and the actuator housing (202) between the at least one knee stop segment (1108) and the lower biasing member (1118), the lower slider member (1120) including a first portion of a lower slider outer surface (1122) facing the inner surface (306) of the knee stop housing (1102), the first portion of the lower slider outer surface (1122) and an opposing portion of the inner surface (306) of the knee stop housing (1102) configured to form the knee stop cancel chamber (314), the lower biasing member (1118) configured to bias the lower slider member (1120) toward the at least one knee stop segment (1108); 48. The landing gear assembly of claim 47, further comprising:

50. 1. A method (1300) for kneeling a landing gear assembly (102) of an aircraft (2400), comprising: performing ground operations (1302) on an aircraft (2400) with the landing gear assembly (102) in a fully extended state (1002) and a retraction actuator (104) of the landing gear assembly (102) in an extended piston position (216); activating a kneeling feature of the landing gear assembly (102) to create a kneel stop position (302) in the stowage actuator (104) that shortens a piston stroke (214) of the stowage actuator (104) by preventing movement of a piston (212) in the stowage actuator (104) beyond the kneel stop position (302) toward a stowed piston position (218); moving (1306) the landing gear assembly (102) from the fully extended state (1002) to a kneeling state (602) by moving the stowage actuator (104) from the extended piston position (216) to the kneel stop position (302); 20. A method (1300) for kneeling a landing gear assembly (102) of an aircraft (2400), comprising:

51. 51. The method of claim 50, wherein the extended piston position (216) of the piston stroke (214) within the cylinder bore (210) of the stowage actuator (104) is related to a fully extended state (1002) of the landing gear assembly (102) associated with a landing sequence of the aircraft (2400).

52. 51. The method of claim 50, wherein the stowed piston position (218) of the piston stroke (214) within the cylinder bore (210) of the stow actuator (104) is related to a fully stowed state (802) of the landing gear assembly (102) associated with a takeoff sequence of the aircraft (2400).

53. 51. The method of claim 50, wherein the kneel stop position (302) of the piston stroke (214) in the cylinder bore (210) of the stow actuator (104) is related to a kneel condition (602) of the landing gear assembly (102) during ground operations of the aircraft (2400).

54. 51. The method of claim 50, further comprising moving (1308) the landing gear assembly (102) from the kneeling state (602) to the fully extended state (1002) by moving (1308) the stowage actuator (104) from the kneel stop position (302) to the extended piston position (216) while the kneeling feature of the landing gear assembly (102) is in an actuated state.

55. The method (1400) of claim 50, further comprising forming (1402) the knee stop position (302) within the storage actuator (104) in response to pressurized fluid from a pressurized fluid source being received at a knee stop insertion port (308) of a knee stop assembly (106) secured to an outer surface (220) of the storage actuator (104).

56. 56. The method of claim 55, further comprising allowing (1404) the pressurized fluid to exit the knee stop assembly (106) through the knee stop insertion port (308) without affecting a current state of the knee stop position (302) after the pressurized fluid source is no longer applying the pressurized fluid.

57. The method (1500) of claim 50 further comprises, in response to pressurized fluid from a pressurized fluid source being received at a knee stop insertion port (308) of the knee stop assembly (106), forming (1502) the knee stop position (302) within the storage actuator (104) by inserting at least one knee stop segment (1108) of the knee stop assembly (106) fixed to an outer surface (220) of the storage actuator (104) into at least one knee stop opening (1110) extending through the outer surface (220) and into a cylinder bore (210) of the storage actuator (104).

58. The method further includes forming (1602) the knee stop position (302) within the storage actuator (104), the forming (1602) being by: In response to receiving pressurized fluid from a pressurized fluid source at a knee stop insertion chamber (310) of the knee stop assembly (106) through a knee stop insertion port (308) of the knee stop assembly (106), an upper slider member (1114) of the knee stop assembly (106) fixed to an outer surface (220) of the storage actuator (104) is moved toward an upper biasing member (1112) of the knee stop assembly (106) and toward at least an upper biasing member (1112) of the knee stop assembly (106). moving (1604) the upper slider member (1114) away from at least one knee stop segment (1108), the at least one knee stop segment (1108) being no longer locked after the upper slider member (1114) has moved toward the upper biasing member (1112) and free to move laterally between an inner surface (306) of the knee stop housing (1102) and the outer surface (220) of the storage actuator (104); moving (1606) a lower slider member (1120) of the knee stop assembly (106) toward the at least one knee stop segment (1108) in response to the upper slider member (1114) moving away from the at least one knee stop segment (1108), wherein the at least one knee stop segment (1108) is free to move laterally and a lower biasing member (1118) biases the lower slider member (1120) toward the at least one knee stop segment (1108); inserting (1608) the at least one kneel stop segment (1108) into at least one kneel stop opening (1110) extending through the outer surface (220) into the cylinder bore (210) of the storage actuator (104) as the lower slider member (1120) moves toward the at least one kneel stop segment (1108) and opposing tapered surfaces of the lower slider member (1120) press the at least one kneel stop segment (1108) into the at least one kneel stop opening (1110) to form the kneel stop position (302) within the cylinder bore (210) of the storage actuator (104); The method (1600) of claim 50, performed by:

59. locking (1702) the knee stop position (302) within the storage actuator (104) after the at least one knee stop segment (1108) of the knee stop assembly (106) is inserted into the at least one knee stop opening (1110) of the actuator housing (202); Holding (1704) the at least one knee stop segment (1108) inserted into the at least one knee stop opening (1110), with or without pressure being applied to the knee stop insertion port (308) until pressure is applied to a knee stop cancellation port (312) of the knee stop assembly (106).

60. The method of claim 58, further comprising:

60. stopping (1802) the kneeling feature of the landing gear assembly (102) and disengaging the kneel stop position (302) from the stow actuator (104) to allow movement of the piston (212) to the stowed piston position (218) of the piston stroke (214); initiating (1804) a takeoff sequence for the aircraft (2400) with the landing gear assembly (102) in the fully extended state (1002) and the retraction actuator (104) of the landing gear assembly (102) in the extended piston position (216); completing the takeoff sequence and executing flight operations (1806) for the aircraft (2400) with the landing gear assembly (102) in the fully stowed state (802) and the stow actuator (104) in the stow piston position (218); 51. The method (1800) of claim 50, further comprising:

61. The method (1900) of claim 60, further comprising canceling (1902) the knee stop position (302) from the storage actuator (104) in response to pressurized fluid from a pressurized fluid source being received at a knee stop cancellation port (312) of a knee stop assembly (106) secured to an outer surface (220) of the storage actuator (104).

62. 62. The method of claim 61, further comprising allowing (1904) the pressurized fluid to exit the knee stop assembly (106) through the knee stop cancel port (312) without affecting a current state of the knee stop position (302) after the pressurized fluid source is no longer applying the pressurized fluid.

63. The method (2000) of claim 60 further comprising, in response to pressurized fluid from a pressurized fluid source being received at a knee stop cancellation port (312) of the knee stop assembly (106), canceling (2002) the knee stop position (302) from the storage actuator (104) by retracting at least one knee stop segment (1108) of the knee stop assembly (106) fixed to an outer surface (220) of the storage actuator (104) from at least one knee stop opening (1110) extending through the outer surface (220) into a cylinder bore (210) of the storage actuator (104).

64. The method further includes canceling (2102) the knee stop position (302) from the storage actuator (104), the canceling (2102) being by: In response to receiving pressurized fluid from a pressurized fluid source at a knee-stop cancel chamber (314) of the knee-stop assembly (106) via a knee-stop cancel port (312) of the knee-stop assembly (106), a lower slider member (1120) of the knee-stop assembly (106) secured to an outer surface (220) of the storage actuator (104) is moved toward a lower biasing member (1118) of the knee-stop assembly (106) and toward at least a lower biasing member (1118) of the knee-stop assembly (106). moving (2104) the lower slider member (1120) away from at least one knee stop segment (1108), the at least one knee stop segment (1108) being no longer locked after the lower slider member (1120) has moved toward the lower biasing member (1118) and free to move laterally between an inner surface (306) of the knee stop housing (1102) and the outer surface (220) of the storage actuator (104); moving (2106) an upper slider member (1114) of the knee stop assembly (106) toward the at least one knee stop segment (1108) in response to the lower slider member (1120) moving away from the at least one knee stop segment (1108), wherein the at least one knee stop segment (1108) is free to move laterally and an upper biasing member (1112) biases the upper slider member (1114) toward the at least one knee stop segment (1108); retracting (2108) the at least one kneel stop segment (1108) from at least one kneel stop opening (1110) extending through the outer surface (220) into the cylinder bore (210) of the storage actuator (104) in response to the upper slider member (1114) moving toward the at least one kneel stop segment (1108) and opposing tapered surfaces of the upper slider member (1114) pushing the at least one kneel stop segment (1108) away from the at least one kneel stop opening (1110), thereby eliminating (2108) the kneel stop position (302) from the cylinder bore (210) of the storage actuator (104); The method (2100) of claim 60, performed by:

65. disabling (2202) actuation of the knee stop position (302) within the storage actuator (104) after the at least one knee stop segment (1108) of the knee stop assembly (106) retracts from the at least one knee stop opening (1110) in the actuator housing (202); holding (2204) the at least one knee stop segment (1108) retracted from the at least one knee stop opening (1110), with or without pressure being applied to the knee stop cancellation port (312) until pressure is applied to the knee stop insertion port (308) of the knee stop assembly (106); 65. The method of claim 64, further comprising:

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