Civil aircraft gear shaft assembly cross hole drilling and detecting integrated tool

Abstract

The invention relates to an innovative drilling and detecting integrated tool for the field of civil aircraft transmission gear shaft assembly cross hole finish machining, and the core of the tool is that a high-rigidity positioning system and a modular functional framework are constructed by integrating a gear shaft flexible supporting module and a cross hole one-time drilling, reaming and detecting composite process; the problem of machining vibration caused by insufficient supporting rigidity of a traditional tool and the problem of high manufacturing cost caused by poor mold universality are effectively solved, meanwhile, the multi-link error accumulation effect is remarkably reduced by means of the integrated design of the drilling and inspection procedure, the technological breakthrough that the machining period is shortened, and the one-time inspection qualification rate is increased is achieved, and the production efficiency is improved. According to the scheme, through standardized module design, a reproducible industrial solution is provided for precise manufacturing of the cross hole of the aircraft cabin door gear shaft assembly, and the machining efficiency and precision bottlenecks of structural parts of the type in the aeronautical manufacturing field are broken through through process innovation; and a technical path with demonstration significance is provided for tool technology upgrading in the high-end equipment manufacturing industry.

Description

Technical Field

[0001] This invention relates to an integrated tooling for drilling and inspecting cross holes in civil aircraft gear shaft assemblies, specifically relating to the field of precision machining of cross holes in civil aircraft gear shaft assemblies. Background Technology

[0002] In the field of civil aircraft manufacturing, gear shaft assemblies, as core functional components of cabin door transmission systems, have a decisive impact on the overall safety, operational reliability, and service life of aircraft due to their machining accuracy. Among these, the cross-hole structure, involving precise three-dimensional spatial angle control and multi-axis collaborative machining, has become a key technical bottleneck restricting the manufacturing quality of the assembly. Traditional machining processes rely on a multi-tooling sequence, which not only suffers from the cumulative error amplification effect caused by process connections but also leads to low machining efficiency and quality fluctuations due to repeated clamping and positioning, making it difficult to meet the machining accuracy requirements of modern aerospace manufacturing. In contrast, in the international aerospace field, intelligent tooling systems based on integrated drilling and inspection technology have achieved closed-loop control of cross-hole machining. By integrating high-precision positioning, online detection, and adaptive compensation functions, the stability of the machining process is significantly improved. Compared with existing domestic processes, this technology can reduce the machining cycle of gear shaft cross-holes by 50%, improve the accuracy level of key dimensions by 30%, and effectively control the batch consistency fluctuation range.

[0003] The gear shaft assembly of a civil aircraft cabin door utilizes high-precision transmission mechanism motion control technology to achieve precise clamping and dynamic sealing coordination when the door closes. This effectively maintains the integrity of the cabin pressure boundary and prevents external environmental intrusion. Its sealing performance is directly related to the airtightness index of the pressurized cabin and the parameters of passenger comfort. Throughout the flight cycle, the cabin door structure must withstand continuous pressurization loads and alternating stress coupling. At this time, the form and position tolerance control accuracy and material fatigue strength of the gear shaft assembly become the core elements to ensure sealing reliability. Its cross holes, as key features of lubrication oil circuits and structural force transmission, must meet the stringent requirements of form and position errors such as hole diameter tolerance, position accuracy, and coaxiality in the three-dimensional spatial coordinate system. If defects such as hole diameter out-of-tolerance, axis misalignment, or angle inaccuracy occur during the machining process, it will cause local stress concentration effects on the gear shaft during the service stage, which will lead to the initiation and propagation of microcracks, ultimately causing catastrophic consequences such as structural strength degradation and transmission function failure, seriously threatening flight safety. Summary of the Invention

[0004] Against this backdrop, modular integrated drilling and inspection tooling technology can effectively improve the machining quality of gear shaft assemblies, becoming a key technological breakthrough. Using this tooling structure and drilling method can effectively reduce the clamping and inspection machining cycle, and increase the machining accuracy and consistency of intersecting holes.

[0005] To overcome these limitations, an innovative solution has been developed: an integrated tooling for drilling and inspecting cross holes in civil aircraft gear shaft assemblies. Its core advantages lie in effectively reducing the clamping and inspection machining cycle, and increasing the machining accuracy and consistency of the cross holes. In summary, the integrated tooling and method for drilling and inspecting cross holes in civil aircraft gear shaft assemblies not only solves the current machining efficiency and accuracy problems faced in the aerospace manufacturing field, but also provides strong technical support for promoting the development of high-end manufacturing industries such as large aircraft manufacturing in my country, helping to enhance the competitiveness and innovation capabilities of the entire industry.

[0006] This invention addresses the machining method and precision of cross holes in civil aircraft gear shaft assemblies. It employs a set of integrated drilling and inspection tooling for cross holes in civil aircraft gear shaft assemblies, along with usage methods and machining processes, to solve equipment compatibility issues, enhance operability and flexibility, improve efficiency and shorten manufacturing cycles, reduce equipment costs and scrap risk costs, and further contribute to enhancing the competitiveness and innovation capabilities of the entire industry.

[0007] According to one aspect of this application, an integrated tooling for drilling and inspecting cross holes of a civil aircraft gear shaft assembly is provided. The integrated tooling for drilling and inspecting cross holes of a civil aircraft gear shaft assembly includes a base 1, a reference locator 2, a clamping locator 3, a drill template assembly 4, a positioning seat 5, a support seat assembly 6, and a positioning seat assembly 7.

[0008] The gear shaft assembly consists of a gear shaft and a flange sleeve. The middle section of the gear shaft is a cylindrical spur involute spline, and both ends are smooth rods with threaded holes in the inner diameter of the smooth rod area. The mating end of the gear shaft with the flange sleeve is a stepped shaft. The flange sleeve has an inner diameter of 20.8 mm and a tolerance of 0.02 mm. It mates with the smooth rod at one end of the gear shaft, and the mating area has two intersecting through holes with an angle of 84.67°.

[0009] The base 1 is made of Q235 tooling steel with a thickness of 15mm. The four corners are chamfered by 20mm to increase safety. The whole is subjected to passivation process for oxidation protection. Each of the three corners is provided with a φ10H7 reference locator 2 reference hole, and there are four M4 mounting holes around the reference hole.

[0010] The base 1 is provided with a threaded mounting hole of φ11mm.

[0011] There are 3 reference locators 2 in total. The thickness of the reference locator 2 is 10mm and the outer diameter is φ36mm. It has 5 holes, one of which is a reference positioning hole, two are pin holes, and two are countersunk bolt holes. The two pin holes and two countersunk bolt holes are the mounting holes of the reference locator 2.

[0012] The clamping and positioning device 3 consists of a clamping seat 8 and a threaded clamping pin 9;

[0013] The clamping seat 8 is machined from Q235 with a thickness of 20mm. The two corners at the top are chamfered with R20 to prevent bumps. A φ8mm bolt hole is set corresponding to the center line of the gear shaft assembly for installing the threaded clamping pin 9.

[0014] The threaded clamping pin 9 has an external thread at its end, which engages with the threaded center hole of the gear shaft assembly for fixing and positioning.

[0015] The drill template assembly 4 consists of a drill template 10, a replaceable drill sleeve 11, and a drill sleeve positioning bolt 12.

[0016] The drilling template 10 is made of Q235 steel with a thickness of 15mm. The drilling template 10 has a Z-shaped structure and four bolt holes on the bottom surface for mounting on the base 1.

[0017] The drill template 10, excluding the bottom surface, forms an angle of 84.67° with each other on its two sides. Each side is provided with a drill sleeve hole and a positioning hole for installing a replaceable drill sleeve 11 and a drill sleeve positioning bolt 12.

[0018] Two inspection pins, each 13mm long, are used to inspect the accuracy of the cross holes after machining.

[0019] The drilling template 10 has a bolt hole on the flange side end face for installing flange clamping plates.

[0020] The replaceable drill bushing 11 includes a primary hole drill bushing, a reaming drill bushing, a final hole drill bushing, and a boring drill bushing; each specification of drill bushing is equipped with a corresponding inspection pin 13. When machining one hole, the other hole is positioned by the pin, which increases the hole-making accuracy and adaptability.

[0021] The positioning seat 5 is machined from 18mm thick Q235 steel, with one bolt hole and two pin holes at the bottom for mounting on the base 1; the top has a V-groove with a 60° opening angle for mounting the gear shaft assembly transition groove, and the two sides of the top are chamfered with R5 to prevent bumps.

[0022] The support assembly 6 consists of two supports 14, one U-shaped pressure plate 15 and one toothed support block 16. Each of the two supports 14 and the toothed support block 16 has one bolt hole and two pin holes at its bottom.

[0023] The support 14 is machined from Q235 with a thickness of 16mm. The two supports 14 are symmetrical. A rectangular groove is set at the outer corner of the top end to cooperate with the U-shaped pressure plate 15. After installation, the gap is adjusted by aluminum alloy rectangular shims of various specifications. Each top surface is provided with a φ8mm bolt hole for bolt clamping the U-shaped pressure plate 15.

[0024] The U-shaped pressure plate 15 is machined from Q235 steel with a thickness of 16mm and has two 8mm bolt holes for clamping the U-shaped pressure plate 15.

[0025] The toothed support block 16 is machined from Q235 steel with a thickness of 18mm. It has two teeth on the top, which mate with the gear shaft teeth. A 0.2mm gap is left on both sides of the toothed support block 16 to prevent damage.

[0026] The positioning seat assembly 7 consists of a positioning block 17 and a clamping piece 18;

[0027] The positioning block 17 is machined from Q235 steel with a thickness of 18mm, and has one bolt hole and two pin holes at the bottom for mounting on the base 1;

[0028] The top of the positioning block 17 is set at an angle of 60°, the surface roughness is 1.6Ra, the V-groove is not a through groove, the depth along the gear shaft is 13mm, and the axial end face is used as the axial reference surface.

[0029] The inner side plane of the positioning block 17 is provided with three M6 threaded holes for installing the clamping plate 18;

[0030] The clamping plate 18 is provided with three φ6.5mm holes for mounting on the positioning block 17. A V-groove is provided at the upper end for positioning the transition groove of the gear shaft reference end. The thickness of the positioning block 17 is less than the width of the transition groove.

[0031] The present invention also provides a machining method using the above-mentioned integrated tooling for drilling and inspecting cross holes of civil aircraft gear shaft assemblies, comprising the following steps:

[0032] 1. Inspect the drawing number, version, quality number, marking, surface quality, quality certificate and conformity label of the parts, groups and components and accessories according to the supporting list; inspect the tooling drawing number, version, module drawing number, standard parts and conformity certificate according to the tooling list.

[0033] 2. Check whether the dimensional accuracy of the matching parts meets the assembly requirements according to the assembly drawings.

[0034] 3. Use acetone to clean the precision holes, outer surface and end face of gear shafts, and inner surface and end face of flange sleeves of parts, ensuring they are free of dust, oil, and other impurities.

[0035] 4. Clean the workbench, install the drilling and inspection integrated tooling, and ensure that the tooling is secure and complete.

[0036] 5. First install the gear shaft, then install the flange sleeve, tighten the clamping plate and clamping nut, and install...

[0037] First drill the hole, check that all parts are securely clamped, and check that the cutting tool is sharp.

[0038] 6. Use the machine tool to determine the machining datum with the reference positioning block, complete the initial hole machining, and use the initial hole inspection pin to check the quality and accuracy of the initial hole.

[0039] 7. Replace the reaming bushing with the drill template to complete the reaming process. Use the reaming inspection pin to check the reaming quality and accuracy. When the drill bit or reamer penetrates the material or component being drilled, the motor should be stopped immediately. To prevent axial scratches, slowly withdraw the drill bit counterclockwise from the hole (for reamers, withdraw clockwise). During drilling, keep the motor switch on throughout the entire process. Intermittent starting will reduce the motor speed, which will enlarge the hole in steel and titanium alloys and harden their surface.

[0040] 8. Replace the final hole drill bushing with the drill template to complete the final hole machining. Use the final hole inspection pin to inspect the quality and accuracy of the final hole.

[0041] 9. Replace the reaming drill bushing with the drilling template to complete the reaming process. Use the reaming inspection pin to inspect the quality and accuracy of the reaming.

[0042] 10. Disassemble the tooling, remove the parts, deburr the components, and reassemble them to prevent drill chips and burrs from remaining between the components and causing fatigue stress.

[0043] 11. Visually inspect the surface of the parts for burns using a 50x magnifying glass. The surface should not show any discoloration.

[0044] The advantage of this application is that the present invention relates to a three-axis machining mold and machining method for an aircraft hyperboloid joint.

[0045] This invention relates to an integrated fixture and method for drilling and inspecting cross holes in a gear shaft assembly for civil aircraft. The method utilizes a modular integrated fixture and a machining method employing four sizes of drill bushings and inspection pins to complete the drilling and inspection of the cross holes. Using this fixture and drilling method effectively reduces the clamping and inspection machining cycle, and increases the machining accuracy and consistency of the cross holes.

[0046] This invention utilizes an integrated drilling and inspection fixture for the cross holes of gear shaft assemblies in civil aircraft, along with a four-drill bushing and inspection pin process. The use of a dedicated integrated drilling and inspection fixture effectively avoids the cumulative error amplification effect caused by process connections and the low processing efficiency and quality fluctuations resulting from repeated clamping and positioning. By integrating high-precision positioning, online detection, and adaptive compensation functions, the stability of the processing is significantly improved. This is crucial for high-end manufacturing industries that seek rapid response to market changes and cost reduction. This method not only directly solves the efficiency and precision bottlenecks encountered in the aerospace manufacturing field when drilling cross holes in civil aircraft gear shaft assemblies, but also promotes the development of the entire industry through technological innovation.

[0047] Furthermore, enhanced operability and flexibility make the production line easier to manage and adjust, enabling it to adapt more quickly to the machining requirements of cross-holes in gear shaft assemblies for different models and specifications of civil aircraft. Improving machining accuracy is crucial for ensuring product quality, which is especially important in the aerospace manufacturing sector, as even minute dimensional deviations can have a significant impact on aircraft performance and safety. Attached Figure Description

[0048] Figure 1 This is an isometric view of the tooling.

[0049] Figure 2 This is an isometric view of the part.

[0050] Figure 3 This is an isometric view of the module.

[0051] Figure 4 Isometric view of the drilling template.

[0052] Figure 5 This is a diagram of the support assembly.

[0053] The components include: 1. base, 2. reference locator, 3. clamping locator, 4. drill template assembly, 5. positioning seat, 6. support seat assembly, 7. positioning seat assembly, 8. clamping seat, 9. threaded clamping pin, 10. drill template, 11. replaceable drill sleeve, 12. drill sleeve positioning bolt, 13. inspection pin, 14. support, 15. U-shaped pressure plate, 16. toothed support block, 17. positioning block, and 18. clamping plate. Detailed Implementation

[0054] The present application is described in detail below with reference to the embodiments, but the present application is not limited to these embodiments.

[0055] Example 1

[0056] like Figures 1-5 As shown, the integrated drilling and inspection fixture includes: 1 base, 2 reference locator, 3 clamping locator, 4 drilling template assembly, 5 positioning seat, 6 support seat assembly, and 7 positioning seat assembly.

[0057] The base 1 is made of 15mm thick Q235 tooling steel, with 20mm chamfers at the four corners for added safety. The entire structure undergoes a passivation process for oxidation protection. Each of the three corners has a φ10H7 reference locator 2 reference hole, and four M4 mounting holes are located around the circumference of the reference holes. The base 1 corresponds to the φ11mm threaded mounting holes of the module components. The reference locator 2 consists of three 10mm thick reference locators with an outer diameter of φ36mm, and the mounting holes are two pin holes and two countersunk bolt holes.

[0058] The clamping and positioning device 3 consists of a clamping seat 8 and a threaded clamping pin 9. The clamping seat 8 is machined from 20mm thick Q235 steel, with two R20 chamfered corners at the top to prevent impact. An 8mm bolt hole is provided corresponding to the center line of the gear shaft assembly for installing the threaded clamping pin 9. The threaded clamping pin 9 has an external thread at its end, which engages with the threaded center hole of the gear shaft assembly for fixing and positioning.

[0059] The drill template assembly 4 consists of a drill template 10, a replaceable drill sleeve 11, and drill sleeve positioning bolts 12. The drill template 10 is machined from 15mm thick Q235 stainless steel and has a Z-shaped structure. Four bolt holes are provided on the bottom surface for mounting the base 1. Two drill template surfaces are at an 84.67° angle, each with a drill sleeve hole and a positioning hole for mounting the replaceable drill sleeve 11 and the drill sleeve positioning bolts 12. Two inspection pins 13, each 80mm long, are used to inspect the accuracy of the cross holes after machining. One bolt hole is provided on the flange side end face of the drill template 10 for mounting the flange clamping plate.

[0060] The replaceable drill bushing 11 consists of a primary hole drill bushing, a reaming drill bushing, a final hole drill bushing, and a boring drill bushing. Each specification of drill bushing is equipped with a pin, so that when machining one hole, the other hole is positioned by the pin, which increases the drilling accuracy and adaptability.

[0061] The positioning seat 5 is machined from 18mm thick Q235 steel, with one bolt hole and two pin holes at the bottom for mounting to the base 1. The top has a 60° V-groove for mounting the gear shaft assembly transition groove, and both top corners are chamfered with R5 to prevent impact.

[0062] The support assembly 6 consists of two supports 14, one U-shaped pressure plate 15, and one toothed support block 16. Each of the two supports 14 and the toothed support block 16 has one bolt hole and two pin holes at its bottom end. The supports 14 are machined from 16mm thick Q235 steel. The two support blocks are symmetrical, with rectangular grooves at their outer corners to mate with the U-shaped pressure plate 15. After installation, the gap is adjusted using rectangular aluminum alloy shims of various specifications. Each top surface has one φ8mm bolt hole for clamping the U-shaped pressure plate 15. The U-shaped pressure plate 15 is also machined from 16mm thick Q235 steel and has two 8mm bolt holes for clamping. The toothed support block 16 is machined from 18mm thick Q235 steel, with two teeth at its top to mate with the gear shaft teeth. A 0.2mm gap is left on both sides of the teeth of the toothed support block 16 to prevent damage.

[0063] The positioning seat assembly 7 consists of a positioning block 17 and a clamping plate 18. The positioning block 17 is machined from 18mm thick Q235 stainless steel, with one bolt hole and two pin holes at its bottom for mounting to the base 1. The top of the positioning block 17 has a 60° angle, a contact surface roughness of 1.6Ra, a non-through V-groove, and a depth of 13mm along the gear shaft axial direction, with the axial end face serving as the axial reference surface. The inner plane of the positioning block 17 has three M6 threaded holes for mounting the clamping plate 18. The clamping plate 18 has three φ6.5mm holes for mounting to the positioning block 17, and a V-groove at its upper end for positioning the gear shaft reference end transition groove; the thickness of the positioning block 17 is less than the width of the transition groove.

[0064] The machining process using the above-mentioned tooling includes the following steps:

[0065] 1. Inspect the drawing number, version, quality number, marking, surface quality, quality certificate and conformity label of the parts, groups and components and accessories according to the supporting list; inspect the tooling drawing number, version, module drawing number, standard parts and conformity certificate according to the tooling list.

[0066] 2. Check whether the dimensional accuracy of the matching parts meets the assembly requirements according to the assembly drawings.

[0067] 3. Use acetone to clean the precision holes, outer surface and end face of gear shafts, and inner surface and end face of flange sleeves of parts, ensuring they are free of dust, oil, and other impurities.

[0068] 4. Clean the workbench, install the drilling and inspection integrated tooling, and ensure that the tooling is secure and complete.

[0069] 5. First install the gear shaft, then install the flange sleeve, tighten the clamping plate and clamping nut, and install...

[0070] First drill the hole, check that all parts are securely clamped, and check that the cutting tool is sharp.

[0071] 6. Use the machine tool to determine the machining datum with the reference positioning block, complete the initial hole machining, and use the initial hole inspection pin to check the quality and accuracy of the initial hole.

[0072] 7. Replace the reaming bushing with the drill template to complete the reaming process. Use the reaming inspection pin to check the reaming quality and accuracy. When the drill bit or reamer penetrates the material or component being drilled, the motor should be stopped immediately. To prevent axial scratches, slowly withdraw the drill bit counterclockwise from the hole (for reamers, withdraw clockwise). During drilling, keep the motor switch on throughout the entire process. Intermittent starting will reduce the motor speed, which will enlarge the hole in steel and titanium alloys and harden their surface.

[0073] 8. Replace the final hole drill bushing with the drill template to complete the final hole machining. Use the final hole inspection pin to inspect the quality and accuracy of the final hole.

[0074] 9. Replace the reaming drill bushing with the drilling template to complete the reaming process. Use the reaming inspection pin to inspect the quality and accuracy of the reaming.

[0075] 10. Disassemble the tooling, remove the parts, deburr the components, and reassemble them to prevent drill chips and burrs from remaining between the components and causing fatigue stress.

[0076] 11. Visually inspect the surface of the parts for burns using a 50x magnifying glass. The surface should not show any discoloration.

[0077] This invention relates to an integrated tooling and processing method for drilling and inspecting cross holes in civil aircraft gear shaft assemblies. It not only directly solves the efficiency and precision bottlenecks encountered in the aerospace manufacturing field when processing cross holes in gear shaft assemblies, but also promotes the development of the entire industry through technological innovation.

[0078] The above description is merely a specific embodiment of this application, but the scope of protection of this application is not limited thereto. Any modifications or substitutions made by those skilled in the art within the scope of the technology disclosed in this application should be covered within the scope of protection of this application. Therefore, the scope of protection of this application should be determined by the scope of the claims.

Claims

1. A tooling for drilling and inspecting cross holes in a civil aircraft gear shaft assembly, characterized in that, The integrated tooling for drilling and inspecting the cross holes of the civil aircraft gear shaft assembly includes a base (1), a reference locator (2), a clamping locator (3), a drill template assembly (4), a positioning seat (5), a support seat assembly (6), and a positioning seat assembly (7). The gear shaft assembly consists of a gear shaft and a flange sleeve. The middle section of the gear shaft is a cylindrical spur involute spline, and both ends are smooth rods with threaded holes in the inner diameter of the smooth rod area. The mating end of the gear shaft with the flange sleeve is a stepped shaft. The flange sleeve has an inner diameter of 20.8 mm and a tolerance of 0.02 mm. It mates with the smooth rod at one end of the gear shaft, and the mating area has two intersecting through holes with an angle of 84.67°.

2. The integrated tooling for drilling and inspecting cross holes in civil aircraft gear shaft assemblies according to claim 1, characterized in that, The base (1) is made of Q235 tooling steel with a thickness of 15mm. The four corners are chamfered by 20mm to increase safety. The whole is protected by passivation process. Each of the three corners is equipped with a φ10H7 reference locator (2) reference hole. There are four M4 mounting holes around the reference hole. The base (1) is provided with a threaded mounting hole of φ11mm.

3. The integrated tooling for drilling and inspecting cross holes in civil aircraft gear shaft assemblies according to claim 2, characterized in that, There are 3 reference locators (2). The thickness of the reference locator (2) is 10mm and the outer diameter is φ36mm. It has 5 holes, one of which is a reference positioning hole, two are pin holes, and two are countersunk bolt holes. The two pin holes and the two countersunk bolt holes are the mounting holes of the reference locator (2).

4. The integrated tooling for drilling and inspecting cross holes in civil aircraft gear shaft assemblies according to claim 3, characterized in that, The clamping positioner (3) consists of a clamping seat (8) and a threaded clamping pin (9); The clamping seat (8) is machined from Q235 with a thickness of 20mm. The two corners at the top are chamfered with R20 to prevent collisions. A φ8mm bolt hole is set corresponding to the center line of the gear shaft assembly for installing the threaded clamping pin (9). The threaded clamping pin (9) has an external thread at its end, which engages with the threaded center hole of the gear shaft assembly for fixing and positioning.

5. The integrated tooling for drilling and inspecting cross holes in civil aircraft gear shaft assemblies according to claim 4, characterized in that, The drill template assembly (4) consists of a drill template (10), a replaceable drill sleeve (11), and drill sleeve positioning bolts (12). The drilling template (10) is made of Q235 steel with a thickness of 15mm. The drilling template (10) has a Z-shaped structure and four bolt holes on the bottom surface for mounting on the base (1). The drill template (10) has two sides other than the bottom surface at an angle of 84.67° to each other, and each side is provided with a drill sleeve hole and a positioning hole for installing a replaceable drill sleeve (11) and a drill sleeve positioning bolt (12). Two inspection pins (13) are 80mm long and are used to inspect the accuracy of the cross holes after processing. The drilling template (10) has a bolt hole on the flange side end face for installing flange clamping plates.

6. The integrated tooling for drilling and inspecting cross holes in civil aircraft gear shaft assemblies according to claim 5, characterized in that, The replaceable drill bushing (11) includes a primary hole drill bushing, a reaming drill bushing, a final hole drill bushing, and a boring drill bushing; each specification of drill bushing is equipped with a corresponding inspection pin (13). When machining one hole, the other hole is positioned by the pin, which increases the hole-making accuracy and adaptability.

7. The integrated tooling for drilling and inspecting cross holes in civil aircraft gear shaft assemblies according to claim 6, characterized in that, The positioning seat (5) is machined from Q235 with a thickness of 18mm. It has one bolt hole and two pin holes at the bottom for mounting on the base (1). The top has a V-groove with an opening angle of 60° for mounting the gear shaft assembly transition groove. The top two corners are chamfered with R5 to prevent bumps.

8. The integrated tooling for drilling and inspecting cross holes in civil aircraft gear shaft assemblies according to claim 7, characterized in that, The support assembly (6) consists of two supports (14), one U-shaped pressure plate (15) and one toothed support block (16). Each of the two supports (14) and the toothed support block (16) has one bolt hole and two pin holes at its bottom. The support (14) is made of Q235 with a thickness of 16mm. The two supports (14) are symmetrical. A rectangular groove is set at the outer corner of the top end to cooperate with the U-shaped pressure plate (15). After installation, the gap is adjusted by aluminum alloy rectangular shims of various specifications. Each top surface is provided with a φ8mm bolt hole for bolt clamping the U-shaped pressure plate (15). The U-shaped pressure plate (15) is made of Q235 with a thickness of 16mm and has two 8mm bolt holes for clamping the U-shaped pressure plate (15). The toothed support block (16) is machined from Q235 with a thickness of 18mm. It has two teeth on the top, which cooperate with the gear shaft teeth. The toothed support block (16) has a 0.2mm gap on both sides of the teeth to prevent damage.

9. The integrated tooling for drilling and inspecting cross holes in civil aircraft gear shaft assemblies according to claim 8, characterized in that, The positioning seat assembly (7) consists of a positioning block (17) and a clamping piece (18); The positioning block (17) is made of Q235 with a thickness of 18mm and has one bolt hole and two pin holes at the bottom for mounting on the base (1); The top of the positioning block (17) is set at an angle of 60°, the surface roughness is 1.6Ra, the V-groove is not a through groove, the depth along the gear shaft is 13mm, and the axial end face is used as the axial reference surface. The inner plane of the positioning block (17) is provided with 3 M6 threaded holes for installing clamping plates (18). The clamping piece (18) is provided with three φ6.5mm holes for mounting on the positioning block (17). A V-groove is provided at the upper end for positioning the transition groove of the gear shaft reference end. The thickness of the positioning block (17) is less than the width of the transition groove.

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