Method for dismounting and mounting sleeve on aircraft main landing gear deflection rib lug

Abstract

A method for disassembling and assembling a mating bushing for an aircraft main landing gear deflection rib lug includes the following steps: S1: First, remove the right-side bushing; S2: Then, remove the left-side bushing; S3: Simultaneously install the right-side and left-side bushings. Step S1 further includes the following sub-steps: S11: Fabricate a first set of special disassembly tools; S13: Use the first set of special disassembly tools to remove the right-side bushing. Step S2 further includes the following sub-steps: S21: Fabricate a second set of special disassembly tools; S23: Use the second set of special disassembly tools to remove the left-side bushing. Step S3 further includes the following sub-steps: S31: Fabricate a third set of special installation tools; S33: Use the third set of special installation tools to simultaneously install the right-side and left-side bushings into the lug. The disassembly and assembly method in this invention uses a first set of special disassembly tools that avoids interference from related components, allowing for the removal of the right-side bushing first, followed by the removal of the left-side bushing using a conventional method, resulting in high disassembly and assembly efficiency.

Description

Technical Field

[0001] This invention relates to the field of aircraft ground maintenance equipment technology, and in particular to a method for disassembling and assembling a bushing for the deflection rib joint of an aircraft main landing gear. Background Technology

[0002] See the instruction manual appendix Figures 1 to 3 A pair of flanged mating bushings are installed inside the lug 101 of the main landing gear deflection rib 100. The pair of mating bushings includes a right bushing 200 and a left bushing 300. The mating bushings are installed in pairs, and each bushing has a flange. A gap groove 102 is formed between the right bushing 200 and the left bushing 300. Typically, the mating bushings need to be inserted or removed from opposite sides of the lug hole in the lug 101, making installation and removal quite difficult, specifically in the following ways:

[0003] 1) The deflection rib 100 has a pair of lugs 101, and the distance between the lugs is small. The lateral distance between the lugs and the main landing gear deflection rib 100 is also small. Common disassembly and assembly tools will interfere with the surrounding structure, and it is difficult for the staff to cooperate during disassembly and assembly. 2) The bushing has a large diameter and is installed in a mating configuration, which is an interference fit and makes disassembly and assembly difficult; 3) The bushings are fitted together and inserted into the lugs by means of a flange. The commonly used methods of pulling out or pushing out the bushings by screws cannot be used to disassemble or install this type of fitted bushing. 4) The disassembly and assembly of the main landing gear deflection rib lug bushing is a first-time task, and there are no special tools for this bushing disassembly and assembly, either domestically or internationally. Summary of the Invention

[0004] To address the shortcomings of existing technologies, this invention provides a furniture board chamfering and positioning fixture to overcome the deficiencies in existing technologies.

[0005] To achieve the above objectives, this case utilizes the following technical solution: A method for disassembling and assembling a bushing for an aircraft main landing gear deflection rib lug, comprising disassembly steps S1 and S2, and installation step S3.

[0006] S1: First remove the right-side bushing; S2: Remove the left-side bushing again; S3: Install both the right-side bushing and the left-side bushing simultaneously; Step S1 further includes the following sub-steps: S11: Produce the first set of specialized disassembly tools; S12: Assemble the first set of specialized disassembly tools onto the relevant aircraft components; S13: The right bushing is first removed using the first set of special disassembly tools; The first set of special disassembly tools includes a drive screw, with a first positioning nut and a second positioning nut screwed to its two ends respectively. A hydraulic telescopic cylinder, a receiving sleeve, and a push-pull assembly inside the ear are coaxially arranged on the drive screw in sequence. The hydraulic telescopic cylinder, the receiving sleeve, and the push-pull assembly inside the ear are located between the first positioning nut and the second positioning nut.

[0007] Furthermore, step S2 also includes the following sub-steps: S21: Make a second set of special disassembly tools; S22: Assemble the prepared second set of special disassembly tools onto the relevant aircraft components; S23: Remove the left bushing using the second set of special disassembly tools; The second set of special disassembly tools includes the drive screw, No. 1 positioning nut, No. 2 positioning nut, hydraulic telescopic cylinder, receiving sleeve, and newly manufactured No. 1 boss top block from the first set of special disassembly tools. The No. 1 boss top block is provided with a central hole for the drive screw to pass through. The large outer diameter of the No. 1 boss top block is equal to the inner diameter of the lug, and the small outer diameter of the No. 1 boss top block is equal to the inner diameter of the left bushing.

[0008] Furthermore, step S3 also includes the following sub-steps: S31: Create the third set of installation-specific combination tools; S32: Assemble the prepared third set of special installation tools and the left and right flange bushings to be assembled onto the relevant aircraft components. S33: The right bushing and the left bushing are simultaneously installed into the lug using the third set of special installation tools; The third set of installation special combination tools includes the drive screw, No. 1 positioning nut, No. 2 positioning nut, and hydraulic telescopic cylinder from the first set of disassembly special combination tools, as well as newly manufactured No. 2 boss top block and No. 3 boss top block; both No. 2 boss top block and No. 3 boss top block are provided with a central hole for the drive screw to pass through, and the small radius steps of both No. 2 boss top block and No. 3 boss top block are adapted to the inner diameter of the right bushing or the left bushing.

[0009] Furthermore, the inner push-pull assembly of the ear is a combination tool, which includes a hollow shaft seat, a pair of arc-shaped flash blocks symmetrically sleeved on the hollow shaft seat, and a reinforcing sleeve sleeved on one end of the arc-shaped flash blocks. The hollow shaft seat has a stepped outer wall, so that the outer diameter of the hollow shaft seat is equal to the inner diameter of the right bushing or the left bushing, and the central hole diameter of the hollow shaft seat is equal to the outer diameter of the drive screw; fastening screws are evenly arranged on the hollow shaft seat along the circumference, and the fastening screws correspond to the fastening screw holes arranged on the arc-shaped flash block. The arc-shaped flash block has a stepped outer wall. The outer diameter of the arc-shaped flash block is equal to the outer diameter of the hollow shaft seat. The outer arc of the arc-shaped flash block is a minor arc, which is smaller than the half arc of the hollow shaft seat. A burr retaining ring is protruding from the outer wall of the arc-shaped burr retaining block with a large radius. The burr retaining ring corresponds to the gap groove 102 located in the ear between the right bushing and the left bushing.

[0010] Furthermore, the reinforcing sleeve is fitted onto a pair of arc-shaped flash blocks on a small-radius step, and a central hole is provided at the bottom center of the reinforcing sleeve for the drive screw to pass through.

[0011] Further, step S12 includes the following sub-steps: S121: First, assemble the push-pull assembly inside the ear into the ear. Specifically, first, insert a pair of arc-shaped flashing clips through the right side of the ear into the left and right bushings, so that the flashing clip rings on the arc-shaped flashing clips are inserted into the gap groove 102. S122: Pass the reinforcing sleeve through the left side of the lug and onto the small radius step of the pair of arc-shaped flash blocks; S123: Pass the hollow shaft seat through the right side of the lug and insert it into the center position between the pair of arc-shaped flash blocks, so that the pair of arc-shaped flash blocks are fitted on the hollow shaft seat; S124: By engaging the fastening screws on the hollow shaft seat with the fastening screw holes on the arc-shaped flash block, a pair of arc-shaped flash blocks are fastened to the hollow shaft seat; thereby causing the flash retainer on the arc-shaped flash block to be engaged in the gap groove 102 between the right bushing and the left bushing. S125: Install the No. 1 positioning nut, the hydraulic telescopic cylinder and the receiving sleeve in sequence at one end of the drive screw; S126: Pass the drive screw installed in step S125 through the push-pull assembly inside the ear from the right side of the ear; S127: Screw the No. 2 positioning nut onto the other end of the drive screw.

[0012] Further, step S22 includes the following sub-steps: S221: Install the No. 1 positioning nut, the hydraulic telescopic cylinder and the receiving sleeve in sequence at one end of the drive screw; S222: Pass the drive screw installed in step S221 through the left bushing from the left side of the lug; S223: Put the first boss top block on the other end of the drive screw and insert the first boss top block into the ear, and finally screw on the second positioning nut.

[0013] Furthermore, step S32 also includes the following sub-steps: S321: Install the right-side bushing and the left-side bushing close to the right and left sides of the ear hole of the ear respectively; S322: Install the No. 1 positioning nut, the hydraulic telescopic cylinder and the No. 2 boss top block in sequence at one end of the drive screw; S323: Pass the drive screw installed in step S322 through the right bushing, the lug, the left bushing and the top block of the second boss in sequence from the right side of the lug. S324: Screw the No. 2 positioning nut onto the other end of the drive screw.

[0014] Preferably, the end of the flash retainer that contacts the right bushing is provided with a flash bevel.

[0015] Preferably, the outer circumference of the receiving sleeve is symmetrically cut flat using a cutting process to form a symmetrical cutting surface.

[0016] Compared with the prior art, the beneficial effects of the present invention are: 1) The method for disassembling and assembling the main landing gear deflection rib lug bushing of an aircraft in this case has a first set of special disassembly tools that can avoid interference from related components, first remove the right bushing, then remove the left bushing through conventional means, and simultaneously install the left and right flanged bushings, which has high disassembly and assembly efficiency.

[0017] 2) The method for disassembling and assembling the main landing gear deflection rib lug bushing of this case involves decomposing the arc-shaped flash block into two symmetrical pieces, and each of the arc-shaped flash blocks has a minor arc shape. This avoids interference, and the right bushing can be pulled out first through the arc-shaped flash block, making subsequent disassembly easy and efficient.

[0018] 3) In this case, a method for disassembling and assembling the main landing gear deflection rib lug bushing is described. In the second set of special disassembly tools, the top block of the first boss replaces the lug inner push-pull assembly in the first set of special disassembly tools. The integrated top block of the first boss replaces the assembled lug inner push-pull assembly, which can greatly improve the disassembly efficiency of the left bushing.

[0019] 4) The method for disassembling and assembling the main landing gear deflection rib lug bushing of this case has a flash bevel on the flash retainer. The purpose of the flash bevel is to tighten and prevent it from being pulled off the right side, so that the inner end face of the right side bushing is subjected to uniform force and is not easily damaged during the pulling process.

[0020] 5) The method for disassembling and assembling the main landing gear deflection rib lug bushing of an aircraft is simple to operate, requires less access, saves time and effort, and has a high reusability rate. It can be promoted for use in other types of civil aircraft. Furthermore, this disassembly and assembly tool can be directly manufactured by the machining workshop, is inexpensive, can be mass-produced, is safe and efficient, and can be promoted in the scheduled maintenance work of all bases.

[0021] 6) The use of a hydraulic telescopic cylinder drive solves the problem of disassembly due to insufficient strength of the worker.

[0022] To provide a clearer understanding of the present invention, the preferred embodiments of the invention will be described below in conjunction with the accompanying drawings. Attached Figure Description

[0023] Figure 1 , Figure 2 , Figure 3 This is a schematic diagram of the assembly position of the deflection rib lug bushing in the background art. Figure 4 This is a reference diagram showing the usage status of the first set of special disassembly combination tools in this invention; Figure 5 This is a schematic diagram of the structure of the first set of special disassembly combination tools in this invention; Figure 6 , Figure 7 This is a schematic diagram of the push-pull assembly inside the ear in this invention; Figure 8 This is a schematic diagram of the structure of the second set of special disassembly combination tools in this invention; Figure 9 This is a schematic diagram of the structure of the third set of special installation tools in this invention.

[0024] Attached image labels: 1-First set of special disassembly tools; 2-Second set of special disassembly tools; 3-Third set of special installation tools; 11-Drive screw; 12-Hydraulic telescopic cylinder; 13-Receiving sleeve; 14-Ear push-pull assembly; 141-Hollow shaft seat; 142-Arc-shaped flash block; 143-Reinforcing sleeve; 144-Fastening screw; 1421-Flash retainer; 1422-Flash bevel; 21-Top block of boss number one; 31-Top block of boss number two; 32-Top block of boss number three; 100-Deflection rib; 101-Ear; 102-Gap groove; 200-Right side bushing; 300-Left side bushing. Detailed Implementation

[0025] In the description of this invention, it should be understood that the terms "center," "longitudinal," "lateral," "upper," "lower," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," and "outer," etc., indicating orientations or positional relationships, are based on the orientations or positional relationships shown in the accompanying drawings and are used only for the convenience of describing the invention and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation, and therefore should not be construed as a limitation of the invention. In the description of this invention, unless otherwise stated, "a plurality of" means two or more.

[0026] Furthermore, if terms such as "first" or "second" are used for descriptive purposes only, they are mainly used to distinguish different devices, components or parts (the specific types and structures may be the same or different), and are not used to indicate or imply the relative importance or quantity of the indicated devices, components or parts, and should not be construed as indicating or implying relative importance.

[0027] Furthermore, it should be noted that, unless otherwise explicitly specified and limited, the terms "installed," "equipped with," "sleeved / connected," "connected," etc., should be interpreted broadly. For example, "connection" can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection or an indirect connection through an intermediate medium; it can be a connection within two components. For those skilled in the art, the specific meaning of the above terms in this invention can be understood according to the specific circumstances.

[0028] Please also refer to Figure 1-9 A method for disassembling and assembling a mating bushing for the deflection rib joint of an aircraft main landing gear, comprising disassembly steps S1 and S2, and installation step S3: S1: First remove the right-side bushing 200; S2: Remove the left side bushing 300 again; S3: Install right side bushing 200 and left side bushing 300 simultaneously.

[0029] Furthermore, step S1 also includes the following sub-steps: S11: Make the first set of special disassembly tool kit 1; S12: Assemble the first set of disassembly-specific combination tools 1 that has been made onto the relevant aircraft components; S13: The right bushing 200 is first removed using the first set of special disassembly tools 1.

[0030] Specifically, in step S11, the first set of disassembly special combination tools 1 includes a drive screw 11, with a first positioning nut and a second positioning nut screwed to its two ends respectively. A hydraulic telescopic cylinder 12, a receiving sleeve 13, and a push-pull assembly 14 inside the ear are coaxially arranged on the drive screw 11 in sequence. The hydraulic telescopic cylinder 12, the receiving sleeve 13, and the push-pull assembly 14 inside the ear are located between the first positioning nut and the second positioning nut. The first positioning nut is used to position the hydraulic telescopic cylinder 12 at one end of the drive screw 11, so that the hydraulic telescopic cylinder 12 extends towards the output end of the receiving sleeve 13 and presses against the receiving sleeve 13. The second positioning nut is used to press against the push-pull assembly 14 inside the ear, so that the push-pull assembly 14 inside the ear is pulled out by force and the right bushing 200 inside the ear 101 is pulled out. The receiving sleeve 13 is used to press against the ear 101, so that the right bushing 200 is pulled out and falls into the receiving sleeve 13.

[0031] The inner push-pull assembly 14 of the ear is a combination tool. The inner push-pull assembly 14 of the ear includes a hollow shaft seat 141, a pair of arc-shaped flashing blocks 142 symmetrically sleeved on the hollow shaft seat 141, and a reinforcing sleeve 143 sleeved on one end of the arc-shaped flashing blocks 142. The hollow shaft seat 141 has a stepped outer wall, so that the outer diameter of the hollow shaft seat 141 is equal to the inner diameter of the right bushing 200 or the left bushing 300, allowing the hollow shaft seat 141 to be assembled into the bushing. The central hole diameter of the hollow shaft seat 141 is equal to the outer diameter of the drive screw 11, allowing the hollow shaft seat 141 to move freely on the drive screw 11. Fastening screws 144 are evenly arranged circumferentially on the hollow shaft seat 141. The fastening screws 144 correspond to the fastening screw holes on the arc-shaped flash blocks 142. The pair of arc-shaped flash blocks 142 are symmetrically combined and fastened to the small radius step of the hollow shaft seat 141 by the fastening screws 144.

[0032] The arc-shaped flashing block 142 has a stepped outer wall. The outer diameter of the arc-shaped flashing block 142 is equal to the outer diameter of the hollow shaft seat 141. The outer arc of the arc-shaped flashing block 142 is a minor arc, which is smaller than the half arc of the hollow shaft seat 141. A burr retainer 1421 protrudes from the outer wall of the large radius of the arc-shaped burr retainer block 142. The burr retainer 1421 corresponds to the gap groove 102 located between the right bushing 200 and the left bushing 300 in the lug 101, so that when assembled, the burr retainer 1421 can sink into the gap groove 102, thereby allowing the burr retainer 1421 to hook the inner end face of the right bushing 200 from the inside. This allows the right bushing 200 to be pulled out from the lug 101 under the action of the hydraulic telescopic cylinder 12.

[0033] In order to avoid damaging the structural integrity of the right bushing 200 of the aviation component during disassembly, a burr bevel 1422 is provided at the end of the burr retainer 1421 that contacts the right bushing 200. The purpose of the burr bevel 1422 is to tighten and prevent it from being pulled out of shape, so as to ensure that the inner end face of the right bushing 200 is subjected to uniform force during the pulling process and is not easily damaged.

[0034] The reinforcing sleeve 143 is fitted onto a small-radius step of a pair of arc-shaped flash blocks 142. The bottom of the reinforcing sleeve 143 has a central hole through which the drive screw 11 passes. The function of the reinforcing sleeve 143 is to make the pair of arc-shaped flash blocks 142 assembled on the hollow shaft seat 141 by the fastening screw 144 more stable, and to prevent the pair of arc-shaped flash blocks 142 from shifting when the right bushing 200 is pulled out, thereby causing the flash retainer 1421 to misalign with the gap groove 102.

[0035] Specifically, in step S12, the process of assembling the prepared first set of disassembly-specific combination tools 1 onto the relevant aircraft components includes the following sub-steps: S121: First, assemble the inner push-pull assembly 14 of the ear into the ear 101. Specifically, first, insert a pair of arc-shaped flashing blocks 142 from the right side of the ear 101 through the right side bushing 200 into the left and right bushings, so that the flashing ring 1421 on the arc-shaped flashing block 142 is inserted into the gap groove 102. It should be noted that, since the outer diameter of the burr retainer 1421 on the arc-shaped burr retainer block 142 is larger than the inner diameter of the right bushing 200, if the arc-shaped burr retainer block 142 is designed as a single piece, the large outer diameter of the burr retainer 1421 will interfere with the small inner diameter of the right bushing 200, causing the entire arc-shaped burr retainer block 142 to be unable to pass through the right bushing 200. Therefore, the arc-shaped burr retainer block 142 needs to be decomposed into two symmetrical pieces, and each piece of the arc-shaped burr retainer block 142 has a minor arc shape, so as to avoid interference.

[0036] S122: The reinforcing sleeve 143 passes through the left side of the lug 101 through the left bushing 300 and is fitted onto the small radius step of the pair of arc-shaped flashing blocks 142, so that the pair of arc-shaped flashing blocks 142 are more stable and the force is more evenly distributed.

[0037] S123: The hollow shaft seat 141 is inserted from the right side of the lug 101 through the right side bushing 200 and fitted into the center position between the pair of arc-shaped flashing blocks 142, so that the pair of arc-shaped flashing blocks 142 are fitted onto the hollow shaft seat 141.

[0038] S124: By engaging the fastening screws 144 on the hollow shaft seat 141 with the fastening screw holes on the arc-shaped flash block 142, a pair of arc-shaped flash blocks 142 are fastened to the hollow shaft seat 141; thereby allowing the inner push-pull assembly 14 of the lug to be assembled into the lug 101 without interference, and the flash retainer 1421 on the arc-shaped flash block 142 is engaged in the gap groove 102 between the right bushing 200 and the left bushing 300.

[0039] S125: Install the No. 1 positioning nut, the hydraulic telescopic cylinder 12 and the receiving sleeve 13 in sequence at one end of the drive screw 11.

[0040] S126: Pass the drive screw 11 installed in step S125 through the push-pull assembly 14 inside the left and right bushings from the right side of the lug 101.

[0041] S127: Screw the No. 2 positioning nut onto the other end of the drive screw 11 to complete the assembly of the first set of disassembly special combination tools 1.

[0042] Specifically, in step S13, the hydraulic telescopic cylinder 12 is activated, the output end of the hydraulic telescopic cylinder 12 extends, and pushes the receiving sleeve 13 to gradually approach and finally abut against the right end face of the ear 101. At the same time, under the action of the hydraulic telescopic cylinder 12, the second positioning nut also gradually approaches and finally abuts against the left end face of the reinforcing sleeve 143. Under the continuous external force of the hydraulic telescopic cylinder 12, because the flash retainer 1421 is stuck in the gap groove 102, the right bushing 200 is pulled out from the ear 101 to the right by the ear push-pull assembly 14, completing the process of first disassembling the right bushing 200.

[0043] Preferably, in this embodiment, in order to avoid lateral interference between the receiving sleeve 13 and the main landing gear deflection rib 100, the outer circumference of the receiving sleeve 13 is symmetrically cut flat by a cutting process to form a symmetrical cutting surface, thereby reducing the radial width of the receiving sleeve 13 and thus avoiding interference.

[0044] Furthermore, step S2 also includes the following sub-steps: S21: Make a second set of special disassembly tool set 2; S22: Assemble the prepared second set of special disassembly tool 2 onto the relevant aircraft components; S23: The left bushing 300 is removed using the second set of special disassembly tools 2.

[0045] Specifically, in step S21, the second set of disassembly special combination tools 2 includes the drive screw 11, the first positioning nut, the second positioning nut, the hydraulic telescopic cylinder 12, the receiving sleeve 13, and the newly manufactured first boss top block 21 from the first set of disassembly special combination tools 1; the hydraulic telescopic cylinder 12, the receiving sleeve 13, and the first boss top block 21 are located between the first positioning nut and the second positioning nut; the first boss top block 21 is provided with a central hole for the drive screw 11 to pass through, the large outer diameter of the first boss top block 21 is equal to the inner diameter of the lug 101, and the small outer diameter of the first boss top block 21 is equal to the inner diameter of the left bushing 300, so that the first boss top block 21 can be inserted from the lug 101 to hook the left bushing 300.

[0046] It should be noted that in the second set of special disassembly tools 2, the first boss top block 21 replaces the inner push-pull assembly 14 of the ear in the first set of special disassembly tools 1. The reason is that since the right bushing 200 has been removed in step S1, only the left bushing 300 remains of the original pair of bushings that were flanged and mounted on both sides. When the first boss top block 21 is installed into the ear 101, there will be no interference. Replacing the assembled inner push-pull assembly 14 with the integrated first boss top block 21 can greatly improve the disassembly efficiency of the left bushing 300.

[0047] Specifically, in step S22, the process of assembling the prepared second set of disassembly-specific combination tools 2 onto the relevant aircraft components includes the following sub-steps: S221: Install the No. 1 positioning nut, the hydraulic telescopic cylinder 12 and the receiving sleeve 13 in sequence at one end of the drive screw 11; S222: Pass the drive screw 11 installed in step S221 through the left bushing 300 from the left side of the lug 101; S223: Put the first boss top block 21 on the other end of the drive screw 11 and insert the first boss top block 21 into the ear 101. Finally, screw on the second positioning nut to complete the assembly of the second set of disassembly special combination tools 2.

[0048] Specifically, in step S23, the hydraulic telescopic cylinder 12 is activated, the output end of the hydraulic telescopic cylinder 12 extends, and pushes the receiving sleeve 13 to gradually approach and finally abut against the left end face of the ear 101. At the same time, under the action of the hydraulic telescopic cylinder 12, the second positioning nut also gradually approaches and finally abuts against the right end face of the first boss top block 21, and finally makes the first boss top block 21 hook and pull out the left bushing 300 from the ear 101, completing the process of disassembling the left bushing 300.

[0049] Furthermore, step S3 also includes the following sub-steps: S31: Make the third set of installation-specific combination tools 3; S32: Assemble the prepared third set of special installation tool 3 and the left and right flange bushings to be assembled onto the relevant aircraft components. S33: The right bushing 200 and the left bushing 300 are simultaneously installed into the lug 101 using the third set of special installation tools 3.

[0050] Specifically, in step S31, the third set of installation special combination tools 3 includes the drive screw 11, the first positioning nut, the second positioning nut, the hydraulic telescopic cylinder 12, and the newly manufactured second boss top block 31 and third boss top block 32 from the first set of disassembly special combination tools 1; the hydraulic telescopic cylinder 12, the receiving sleeve 13, the second boss top block 31, and the third boss top block 32 are located between the first positioning nut and the second positioning nut; the second boss top block 31 and the third boss top block 32 are both provided with a central hole for the drive screw 11 to pass through, and the small radius steps of the second boss top block 31 and the third boss top block 32 are adapted to the inner diameter of the right bushing 200 or the left bushing 300, so that the second boss top block 31 and the third boss top block 32 can be inserted into and fitted onto the flanges of the right bushing 200 and the left bushing 300, respectively.

[0051] Specifically, step S32 also includes the following sub-steps: S321: Install the right bushing 200 and the left bushing 300 close to the right and left sides of the ear hole of the ear 101, respectively; S322: Install the No. 1 positioning nut, the hydraulic telescopic cylinder 12 and the No. 2 boss top block 31 in sequence at one end of the drive screw 11; S323: Pass the drive screw 11 installed in step S322 through the right bushing 200, the bushing 101, the left bushing 300 and the second boss top block 31 in sequence from the right side of the lug 101. S324: Screw the No. 2 positioning nut onto the other end of the drive screw 11 to complete the assembly of the third set of special installation tool 3.

[0052] Specifically, in step S33, the hydraulic telescopic cylinder 12 is activated, and the output end of the hydraulic telescopic cylinder 12 extends and pushes the second boss top block 31 to gradually approach and finally abut against the right end face of the right bushing 200. At the same time, under the action of the hydraulic telescopic cylinder 12, the second positioning nut also gradually approaches and finally abuts against the left end face of the third boss top block 32, and finally makes the third boss top block 32 abut against the left end face of the left bushing 300. Under the continuous action of the hydraulic telescopic cylinder 12, the right bushing 200 and the left bushing 300 are simultaneously squeezed into the lug 101, completing the installation process of the flanged bushing.

[0053] It is important to note that after removing all the flanged mating bushings, the inner wall of the lug hole should be cleaned according to the requirements of the aircraft maintenance manual, and the inner wall of the lug hole should be visually inspected for corrosion. Before installation, the new flanged mating bushing should be frozen in liquid nitrogen according to the manual requirements to facilitate better installation and make the fit between the bushing and the lug more tight and stable after installation.

[0054] Compared to existing technologies, the method for disassembling and assembling the main landing gear deflection rib lug bushing of this case can avoid interference from related components with the first set of special disassembly tools. The right bushing is removed first, and then the left bushing is removed using a conventional method. The left and right flanged bushings can be installed at the same time, resulting in high disassembly and assembly efficiency.

[0055] The embodiments described above are merely examples of several implementations of the present invention, and while the descriptions are relatively specific and detailed, they should not be construed as limiting the scope of the invention. It should be noted that those skilled in the art can make various modifications and improvements without departing from the concept of the present invention, and these modifications and improvements all fall within the scope of protection of the present invention.

Claims

1. A method for disassembling and assembling a mating bushing for the deflection rib joint of an aircraft main landing gear, comprising disassembly steps S1 and S2, and an installation step S3, characterized in that: S1: First remove the right side bushing (200); S2: Remove the left bushing (300) again; S3: Install the right bushing (200) and the left bushing (300) simultaneously. Step S1 further includes the following sub-steps: S11: Make the first set of special disassembly tools (1); S12: Assemble the first set of disassembly-specific combination tools (1) that has been made onto the relevant aircraft components; S13: The right bushing (200) is first removed using the first set of special disassembly tools (1); The first set of disassembly special combination tools (1) includes a drive screw (11), with a first positioning nut and a second positioning nut screwed to both ends of the drive screw (11). A hydraulic telescopic cylinder (12), a receiving sleeve (13), and a push-pull assembly (14) inside the ear are coaxially arranged on the drive screw (11). The hydraulic telescopic cylinder (12), the receiving sleeve (13), and the push-pull assembly (14) inside the ear are located between the first positioning nut and the second positioning nut.

2. The method for disassembling and assembling a mating bushing for the deflection rib joint of an aircraft main landing gear according to claim 1, characterized in that: Step S2 further includes the following sub-steps: S21: Make a second set of special disassembly tools (2); S22: Assemble the prepared second set of special disassembly tools (2) onto the relevant aircraft components; S23: Remove the left bushing (300) using the second set of special disassembly tools (2); The second set of disassembly special combination tools (2) includes the drive screw (11), the first positioning nut, the second positioning nut, the hydraulic telescopic cylinder (12), the receiving sleeve (13) in the first set of disassembly special combination tools (1), and the newly made first boss top block (21); the hydraulic telescopic cylinder (12), the receiving sleeve (13) and the first boss top block (21) are located between the first positioning nut and the second positioning nut; the first boss top block (21) is provided with a central hole for the drive screw (11) to pass through, the large outer diameter of the first boss top block (21) is equal to the inner diameter of the lug (101), and the small outer diameter of the first boss top block (21) is equal to the inner diameter of the left bushing (300).

3. The method for disassembling and assembling a mating bushing for the deflection rib joint of an aircraft main landing gear according to claim 2, characterized in that: Step S3 further includes the following sub-steps: S31: Make the third set of installation-specific combination tools (3); S32: Assemble the prepared third set of special installation tool (3) and the left and right flange bushings to be assembled onto the relevant aircraft components; S33: The right bushing (200) and the left bushing (300) are simultaneously installed into the lug (101) using the third set of special installation tools (3); The third set of installation special combination tools (3) includes the drive screw (11), the first positioning nut, the second positioning nut, the hydraulic telescopic cylinder (12) in the first set of disassembly special combination tools (1), as well as the newly made second boss top block (31) and third boss top block (32); the hydraulic telescopic cylinder (12), the receiving sleeve (13), the second boss top block (31) and the third boss top block (32) are located between the first positioning nut and the second positioning nut; the second boss top block (31) and the third boss top block (32) are both provided with a central hole for the drive screw (11) to pass through, and the small radius steps of the second boss top block (31) and the third boss top block (32) are adapted to the inner diameter of the right bushing (200) or the left bushing (300).

4. The method for disassembling and assembling a bushing for the deflection rib joint of an aircraft main landing gear according to claim 3, characterized in that: The inner push-pull assembly (14) is a combination tool. The inner push-pull assembly (14) includes a hollow shaft seat (141), a pair of arc-shaped flashing blocks (142) symmetrically sleeved on the hollow shaft seat (141), and a reinforcing sleeve (143) sleeved on one end of the arc-shaped flashing blocks (142). The hollow shaft seat (141) has a stepped outer wall, so that the outer diameter of the hollow shaft seat (141) is equal to the inner diameter of the right bushing (200) or the left bushing (300), and the central hole diameter of the hollow shaft seat (141) is equal to the outer diameter of the drive screw (11); fastening screws (144) are evenly arranged on the hollow shaft seat (141) along the circumference, and the fastening screws (144) correspond to the fastening screw holes arranged on the arc-shaped flash block (142); The arc-shaped flashing block (142) has a stepped outer wall. The outer diameter of the arc-shaped flashing block (142) is equal to the outer diameter of the hollow shaft seat (141). The outer arc of the arc-shaped flashing block (142) is a minor arc, which is smaller than the half arc of the hollow shaft seat (141). A burr retainer (1421) is provided on the outer wall of the large radius of the arc-shaped burr retainer (142), which corresponds to the gap groove (102) located between the right bushing (200) and the left bushing (300) in the ear (101).

5. The method for disassembling and assembling a mating bushing for the deflection rib joint of an aircraft main landing gear according to claim 4, characterized in that: The reinforcing sleeve (143) is fitted on a small-radius step of a pair of arc-shaped flash blocks (142), and the bottom center of the reinforcing sleeve (143) is provided with a central hole for the drive screw (11) to pass through.

6. The method for disassembling and assembling a mating bushing for the deflection rib joint of an aircraft main landing gear according to claim 5, characterized in that: Step S12 includes the following sub-steps: S121: First, assemble the inner push-pull assembly (14) of the ear into the ear (101). Specifically, first, insert a pair of arc-shaped flashing blocks (142) from the right side of the ear (101) through the right side bushing (200) into the left and right bushings, and make the flashing ring (1421) on the arc-shaped flashing block (142) sink into the gap groove (102); S122: Pass the reinforcing sleeve (143) through the left side of the lug (101) through the left bushing (300) and onto the small radius step of the pair of arc-shaped flash blocks (142); S123: Pass the hollow shaft seat (141) through the right side bushing (200) from the right side of the lug (101) and insert it into the center position between the pair of arc-shaped flashing blocks (142), so that the pair of arc-shaped flashing blocks (142) are fitted on the hollow shaft seat (141); S124: By engaging the fastening screws (144) on the hollow shaft seat (141) with the fastening screw holes on the arc-shaped flash block (142), a pair of arc-shaped flash blocks (142) are fastened to the hollow shaft seat (141); thereby causing the flash retaining rings (1421) on the arc-shaped flash blocks (142) to be engaged in the gap groove (102) between the right bushing (200) and the left bushing (300); S125: Install the No. 1 positioning nut, the hydraulic telescopic cylinder (12) and the receiving sleeve (13) in sequence at one end of the drive screw (11); S126: Pass the drive screw (11) installed in step S125 through the push-pull assembly (14) inside the left and right bushings from the right side of the lug (101). S127: Screw the No. 2 positioning nut onto the other end of the drive screw (11).

7. The method for disassembling and assembling a mating bushing for the deflection rib joint of an aircraft main landing gear according to claim 6, characterized in that: Step S22 includes the following sub-steps: S221: Install the No. 1 positioning nut, the hydraulic telescopic cylinder (12) and the receiving sleeve (13) in sequence at one end of the drive screw (11); S222: Pass the drive screw (11) installed in step S221 through the left bushing (300) from the left side of the lug (101). S223: Put the first boss top block (21) on the other end of the drive screw (11), insert the first boss top block (21) into the ear (101), and finally screw on the second positioning nut.

8. The method for disassembling and assembling a mating bushing for the deflection rib joint of an aircraft main landing gear according to claim 7, characterized in that: Step S32 further includes the following sub-steps: S321: Install the right bushing (200) and the left bushing (300) close to the right and left sides of the ear hole of the ear (101), respectively; S322: Install the No. 1 positioning nut, the hydraulic telescopic cylinder (12) and the No. 2 boss top block (31) in sequence at one end of the drive screw (11); S323: Pass the drive screw (11) installed in step S322 through the right bushing (200), the bushing (101), the left bushing (300) and the top block (31) of the second boss in sequence from the right side of the lug (101). S324: Screw the second positioning nut onto the other end of the drive screw (11).

9. A method for disassembling and assembling a mating bushing for the deflection rib joint of an aircraft main landing gear according to claim 8, characterized in that: The end of the burr clasp (1421) that contacts the right bushing (200) is provided with a burr bevel (1422).

10. A method for disassembling and assembling a mating bushing for the deflection rib joint of an aircraft main landing gear according to claim 9, characterized in that: The outer circumference of the receiving sleeve (13) is symmetrically cut flat using a cutting process to form a symmetrical cutting surface.

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