Aircraft having multiple spar boxes connected to the fuselage

Abstract

An aircraft having a multi-spar box connected to a fuselage, the aircraft having a vertical tail, the vertical tail having the multi-spar box and a base rib assembly fixed to the multi-spar box. The base rib assembly has a front longitudinal lug, a rear longitudinal lug and an opposite intermediate longitudinal lug. A front U-shaped clip corresponding to the front longitudinal lug is fixed to a frame member of the fuselage of the aircraft, and each front U-shaped clip has a first mounting arm, a second mounting arm and a third mounting arm. A rear U-shaped clip corresponding to the rear longitudinal lug is fixed to the frame member, and each rear U-shaped clip has a first mounting arm, a second mounting arm and a third mounting arm. An intermediate U-shaped clip corresponding to the intermediate longitudinal lug is fixed to the frame member, and each intermediate U-shaped clip has only a first mounting arm and a second mounting arm. A retaining member inserted through a mounting hole in each longitudinal lug and a mounting hole in each corresponding U-shaped clip fixes the vertical tail to the fuselage.

Description

Technical Field

[0001] The present disclosure relates generally to aircraft, and more particularly to a connection between a vertical tail of an aircraft and a fuselage of the aircraft. Background Art

[0002] There are currently a variety of configurations for connecting the vertical tail to the fuselage of an aircraft. In one configuration, a set of accessories is positioned between the vertical tail and the fuselage, a first set of fasteners is used to attach the vertical tail to the accessories, and a second set of fasteners is used to attach the fuselage to the accessories. However, this type of configuration is difficult to install due to the work required in the confined space, and makes maintenance inspection difficult. In another configuration, lugs and standard double-wall U-shaped clips are used between the vertical tail and the fuselage and are oriented in the longitudinal direction, and additional lugs and standard double-wall U-shaped clips are oriented in the transverse direction and positioned between each of the longitudinal lugs and the U-shaped clips. However, due to the required attachment of the transverse lugs between the intermediate spars, this type of configuration is difficult to install. In yet another configuration, lugs and standard double-wall U-shaped clips are used between the vertical tail and the fuselage, but are only oriented transversely and are only positioned along the front and rear spars of the vertical tail. Summary of the invention

[0003] In one embodiment of the present disclosure, an example aircraft includes an aircraft fuselage and a vertical tail. The aircraft fuselage has a plurality of frame members and an outer skin, and the vertical tail has a multi-spar box. The multi-spar box includes a front spar, a rear spar, at least one intermediate spar positioned between and spaced from the front spar and the rear spar, a first side skin extending between the front spar and the rear spar, and a second side skin extending between the front spar and the rear spar and opposite to the first side skin. The front spar and the rear spar and the first side skin and the second side skin define the interior of the multi-spar box. A base rib assembly is positioned inside the multi-spar box and fixed to the multi-spar box. The base rib assembly has a pair of opposite front longitudinal lugs, a pair of opposite rear longitudinal lugs, and at least one pair of opposite intermediate longitudinal lugs arranged between the front longitudinal lugs and the rear longitudinal lugs. A pair of front U-shaped clips corresponding to the pair of front longitudinal lugs extend through corresponding holes in the outer skin and are fixed to one of the plurality of frame members. Each front U-shaped clip has a first mounting arm, a second mounting arm, and a third mounting arm. A pair of rear U-shaped clips corresponding to a pair of rear longitudinal lugs extend through corresponding holes in the outer skin and are fixed to one of the plurality of frame members. Each rear U-shaped clip has a first mounting arm, a second mounting arm, and a third mounting arm. A pair of intermediate U-shaped clips corresponding to a pair of intermediate longitudinal lugs extend through corresponding holes in the outer skin and are fixed to one of the plurality of frame members. Each intermediate U-shaped clip has only a first mounting arm and a second mounting arm. A plurality of retaining members are inserted through the mounting holes in each front longitudinal lug, intermediate longitudinal lug, and rear longitudinal lug and through the mounting holes in each corresponding front U-shaped clip, intermediate U-shaped clip, and rear U-shaped clip to secure the vertical tail to the aircraft fuselage.

[0004] In one embodiment, in the example aircraft of the previous embodiment, the base rib assembly includes at least one forward transverse lug positioned between a pair of forward longitudinal lugs and at least one rearward transverse lug positioned between a pair of rearward longitudinal lugs.

[0005] In one embodiment, in the example aircraft of any preceding embodiment, the base rib assembly is free of any transverse lugs between the at least one pair of intermediate lugs.

[0006] In one embodiment, in an example aircraft of any of the previous embodiments, a front transverse clevis is positioned between a pair of front clevises, extends through a hole in the outer skin, and is secured to one of the plurality of frame members. A rear transverse clevis is positioned between a pair of rear transverse clevises, extends through a hole in the outer skin, and is secured to one of the plurality of frame members. A front link interconnects the front transverse clevis and at least one front transverse lug, and a rear link interconnects the rear transverse clevis and at least one rear transverse lug.

[0007] In one embodiment, in the example aircraft of any of the previous embodiments, the second front link interconnects the front transverse clevis and the other front transverse lug, and the second rear link interconnects the rear transverse clevis and the other rear transverse lug.

[0008] In one embodiment, in the example aircraft of any of the previous embodiments, the front link interconnects at least one front lateral lug and a lateral wall of one of the pair of front clevises, and the rear link interconnects at least one rear lateral lug and a lateral wall of one of the pair of rear clevises.

[0009] In one embodiment, in the example aircraft of any of the previous embodiments, the second front link interconnects the other front lateral lug and the lateral wall of the other front clevis of the pair of front clevises, and the second rear link interconnects the other rear lateral lug and the lateral wall of the other rear clevis of the pair of rear clevises.

[0010] In one embodiment, in an example aircraft of any of the previous embodiments, a front panel having a transverse lug adjacent to and aligned with at least one front transverse lug of the base rib assembly is positioned adjacent to an outer surface of the front spar and is secured to the front spar and the base rib assembly. A rear panel having at least one transverse lug adjacent to and aligned with at least one rear transverse lug of the base rib assembly is positioned adjacent to an outer surface of the rear spar opposite the front panel and is secured to the rear spar and the base rib assembly. A first side panel having at least one longitudinal lug adjacent to and aligned with one of the intermediate longitudinal lugs of the base rib assembly is positioned adjacent to an outer surface of the first side skin and is secured to the first side skin and the base rib assembly. A second side panel having at least one longitudinal lug adjacent to and aligned with another of the intermediate longitudinal lugs of the base rib assembly is positioned adjacent to an outer surface of the second side skin and is secured to the second side skin and the base rib assembly.

[0011] In one embodiment, in the example aircraft of any of the previous embodiments, at least one longitudinal lug of the first side panel and a corresponding intermediate longitudinal lug of the base rib assembly are positioned between first and second mounting arms of a corresponding intermediate U-shaped clip, and at least one longitudinal lug of the second side panel and a corresponding intermediate longitudinal lug of the base rib assembly are positioned between first and second mounting arms of a corresponding intermediate U-shaped clip.

[0012] In one embodiment, in the example aircraft of any of the previous embodiments, a third side panel having at least one longitudinal lug aligned with one of the forward longitudinal lugs of the base rib assembly is positioned adjacent to an outer surface of the first side skin and is secured to the first side skin and the base rib assembly. A fourth side panel having at least one longitudinal lug aligned with the other of the forward longitudinal lugs of the base rib assembly is positioned adjacent to an outer surface of the second side skin and is secured to the second side skin and the base rib assembly.

[0013] In one embodiment, in an example aircraft of any of the previous embodiments, at least one longitudinal lug of the third side panel is positioned between a first mounting arm and a second mounting arm of a first front U-shaped clip of the pair of front U-shaped clips, and a corresponding front longitudinal lug of the base rib assembly is positioned between a second mounting arm and a third mounting arm of the first front U-shaped clip, and at least one longitudinal lug of the fourth side panel is positioned between a first mounting arm and a second mounting arm of a second front U-shaped clip of the pair of front U-shaped clips, and a corresponding front longitudinal lug of the base rib assembly is positioned between a second mounting arm and a third mounting arm of the second front U-shaped clip.

[0014] In one embodiment, in the example aircraft of any of the previous embodiments, a fifth side panel having at least one longitudinal lug aligned with one of the rear longitudinal lugs of the base rib assembly is positioned adjacent to an outer surface of the first side skin and is secured to the first side skin and the base rib assembly. A sixth side panel having at least one longitudinal lug aligned with the other of the rear longitudinal lugs of the base rib assembly is positioned adjacent to an outer surface of the second side skin and is secured to the second side skin and the base rib assembly.

[0015] In one embodiment, in an example aircraft of any of the previous embodiments, at least one longitudinal lug of the fifth side panel is positioned between a first mounting arm and a second mounting arm of a first rear U-shaped clip of the pair of rear U-shaped clips, and a corresponding rear longitudinal lug of the base rib assembly is positioned between a second mounting arm and a third mounting arm of the first rear U-shaped clip, and at least one longitudinal lug of the sixth side panel is positioned between a first mounting arm and a second mounting arm of a second rear U-shaped clip of the pair of rear U-shaped clips, and a corresponding rear longitudinal lug of the base rib assembly is positioned between a second mounting arm and a third mounting arm of the second rear U-shaped clip.

[0016] In another embodiment of the present disclosure, an exemplary method of attaching a vertical tail having a multi-spar box to an aircraft fuselage includes the following steps: assembling a base rib assembly having a pair of opposing front longitudinal lugs, a pair of opposing rear longitudinal lugs, at least one pair of opposing intermediate longitudinal lugs disposed between the front longitudinal lugs and the rear longitudinal lugs, and a plurality of transverse lugs, each longitudinal lug and each transverse lug having a corresponding mounting hole; inserting the base rib assembly into an interior of the multi-spar box of the vertical tail, the interior of the multi-spar box being defined by a front spar, a rear spar, and opposing side skins; positioning a front panel adjacent to an outer surface of the front spar, and securing the front panel to the front spar and the base rib assembly , a front panel having at least one transverse lug corresponding to one of the plurality of transverse lugs of the base rib assembly, the at least one transverse lug of the front panel having a mounting hole aligned with the mounting hole in the corresponding transverse lug of the base rib assembly; positioning a rear panel adjacent to an outer surface of the rear spar opposite to the front panel, and securing the rear panel to the rear spar and the base rib assembly, the rear panel having at least one transverse lug corresponding to one of the plurality of transverse lugs of the base rib assembly, the at least one transverse lug of the rear panel having a mounting hole aligned with the mounting hole in the corresponding transverse lug of the base rib assembly; positioning a first side panel adjacent to an outer surface of a first side skin of the multi-spar box, and securing the first side panel to a first side skin and base rib assembly, the first side panel having at least one longitudinal lug corresponding to one of the longitudinal lugs of the base rib assembly, each of the at least one longitudinal lug of the first side panel having a mounting hole aligned with the mounting hole in the corresponding longitudinal lug of the base rib assembly; positioning a second side panel adjacent to an outer surface of a second side skin of the multi-spar box, and securing the second side panel to the second side skin and base rib assembly, the second side panel having at least one longitudinal lug corresponding to one of the longitudinal lugs of the base rib assembly, each of the at least one longitudinal lug of the second side panel having a mounting hole aligned with the mounting hole in the corresponding longitudinal lug of the base rib assembly holes; inserting a plurality of U-shaped clips through corresponding holes in the skin of the aircraft fuselage, and fixing each of the plurality of U-shaped clips to a frame member of the aircraft fuselage, wherein the U-shaped clips corresponding to the front longitudinal lug and the rear longitudinal lug each have a first mounting arm, a second mounting arm, and a third mounting arm, each mounting arm having a mounting hole, and the U-shaped clips corresponding to the middle longitudinal lug each have a first mounting arm and a second mounting arm, each mounting arm having a mounting hole; positioning the vertical tail adjacent to the aircraft fuselage and aligning each longitudinal lug with the corresponding U-shaped clip; and inserting a retaining member through the mounting hole of each corresponding longitudinal lug and the U-shaped clip to fix the vertical tail to the aircraft fuselage.

[0017] In one embodiment, in the example method of the previous embodiment, the method includes the steps of attaching each transverse lug to a first end of a corresponding transverse link and attaching a second end of each transverse link to a transverse clevis.

[0018] In one embodiment, in the example aircraft of any of the preceding embodiments, each transverse clevis is part of a corresponding clevis.

[0019] In one embodiment, in the example aircraft of any of the previous embodiments, each transverse clevis is positioned between two clevises, extends through a corresponding hole in the skin of the aircraft fuselage, and is secured to a frame member of the aircraft fuselage.

[0020] In one embodiment, in an example aircraft of any of the previous embodiments, assembling the base rib assembly includes: attaching at least one first side chord to the base rib, the at least one first side chord including at least one longitudinal lug of a plurality of longitudinal lugs; attaching at least one second side chord to the base rib opposite the at least one first side chord, the at least one second side chord including at least one longitudinal lug of a plurality of longitudinal lugs; attaching a front end fitting to the base rib, the front end fitting including at least one longitudinal lug of a plurality of longitudinal lugs and at least one transverse lug of a plurality of transverse lugs; and attaching a rear end fitting to the base rib opposite the front end fitting, the rear end fitting including at least one longitudinal lug of a plurality of longitudinal lugs and at least one transverse lug of a plurality of transverse lugs.

[0021] In one embodiment, in the example aircraft of any of the preceding embodiments, the method includes the step of attaching at least one generally L-shaped shear clip between the base rib assembly and an intermediate spar of the multi-spar box.

[0022] In one embodiment, in the example aircraft of any of the previous embodiments, a plurality of transverse lugs are located at a forward portion of the base rib assembly and at a rearward portion of the base rib assembly, and no transverse lugs are located between the forward portion and the rearward portion of the base rib assembly.

[0023] The features, functions, and advantages that have been discussed can be achieved independently in various embodiments or may be combined in yet other embodiments further details of which can be seen with reference to the following description and drawings. BRIEF DESCRIPTION OF THE DRAWINGS

[0024] Figure 1 is a side view of the example aircraft;

[0025] Figure 2 yes Figure 1 A partial perspective view of an example multi-spar box of a vertical tail of an aircraft;

[0026] Figure 3 The side skin has been removed. Figure 2 A partial perspective view of a multi-spar box;

[0027] Figure 4 is a front perspective view of a first example base rib assembly;

[0028] Figure 5 yes Figure 4 A rear perspective view of a base rib assembly;

[0029] Figure 6 yes Figure 4 A front perspective view of a base rib assembly positioned on a side panel with the side panels removed. Figure 2 The multi-spar box.

[0030] Figure 7 is completely with Figure 2 The multi-spar box is assembled together Figure 4 A front perspective view of a base rib assembly;

[0031] Figure 8 is a first set of exemplary U-shaped clips Figure 1 a partial illustration of a portion of the fuselage of an aircraft;

[0032] Fig. 9 is connected to Figure 8 The fuselage Figure 7 a rear perspective view of a multi-spar box and base rib assembly;

[0033] Fig.10 yes Fig. 9 A front perspective view of the multi-spar box, base rib assembly and fuselage;

[0034] Fig.11 is a front perspective view of a second example base rib assembly;

[0035] Fig.12 yes Fig.11 A rear perspective view of a base rib assembly;

[0036] Fig.13 yes Fig.11 A front perspective view of a base rib assembly positioned on a side panel with the side panels removed. Figure 2 The multi-spar box.

[0037] Fig.14 is completely with Figure 2 The multi-spar box is assembled together Fig.11 A front perspective view of a base rib assembly;

[0038] Fig.15 is a second set of exemplary U-shaped clips Figure 1 a partial illustration of a portion of the fuselage of an aircraft;

[0039] Fig.16 is connected to Fig.15 The fuselage Fig.14 a rear perspective view of a multi-spar box and base rib assembly;

[0040] Fig.17 yes Fig.16 A front perspective view of the multi-spar box, base rib assembly and fuselage;

[0041] Fig.18 is a front perspective view of a third example base rib assembly;

[0042] Fig.19 yes Fig.18 A rear perspective view of a base rib assembly;

[0043] Fig. 20 yes Fig.18 A front perspective view of a base rib assembly positioned on a side panel with the side panels removed. Figure 2 The multi-spar box.

[0044] Fig.21 is completely with Figure 2 The multi-spar box is assembled together Fig.18 A front perspective view of a base rib assembly;

[0045] Fig. 22 A third set of exemplary U-shaped clips is provided. Figure 1 a partial illustration of a portion of the fuselage of an aircraft;

[0046] Fig.23 is connected to Fig. 22 The fuselage Fig.21 a rear perspective view of the multi-spar box and base rib assembly of FIG. 1; and

[0047] Fig.24 yes Fig.23 Front perspective view of the multi-spar box, base rib assembly and fuselage. DETAILED DESCRIPTION

[0048] refer to Figures 1 to 3 , an example aircraft 10 is shown having an aircraft fuselage 15 and a vertical tail 35, the aircraft fuselage having a plurality of frame members 20 and an outer skin 25 (see Figures 8 to 10 , Figures 15 to 17 ,as well as Figure 22 to Figure 24 ), the vertical tail has a multi-spar box 40 connected to the aircraft fuselage 15. Figure 2 and Figure 3As seen in FIG. 1 , the multi-spar box 40 of the vertical tail 35 has a front spar 45, a rear spar 50, and at least one intermediate spar 55 positioned between and spaced from the front and rear spar 45, 50. In the example shown, the multi-spar box 40 has two intermediate spars 55, but may have any number of intermediate spars 55 suitable for a given application. A first side skin 60A and a second side skin 60B opposite the first side skin 60A extend between the front and rear spar 45, 50. The front spar 45, the rear spar 50, the first side skin 60A, and the second side skin 60B together define an interior 65 of the multi-spar box 40.

[0049] refer to Figures 4 to 10 , shows a first example connection between the aircraft fuselage 15 and the multi-spar box 40 of the vertical tail 35. Figure 4 and Figure 5 As best seen in FIG. 1 , the base rib assembly 100 has a base rib 105 and a front fitting 110 connected to the base rib 105, a rear fitting 115 opposite the front fitting 110, a first side chord 120, and a second side chord 125 opposite the first side chord 120. The front fitting 110 includes a pair of opposed front longitudinal lugs 130 extending parallel to the longitudinal axis A of the base rib assembly 100 and a pair of front transverse lugs 135 extending perpendicular to the longitudinal axis A and positioned between the pair of front longitudinal lugs 130. As shown, the front fitting 110 includes two pieces, each having one front longitudinal lug 130 and one front transverse lug 135, but may also be a single integral piece having both the front longitudinal lugs 130 and the front transverse lugs 135, such as Figure 11 to Figure 12 As shown. The rear end fitting 115 includes a pair of opposed rear longitudinal lugs 140 extending parallel to the longitudinal axis A and a pair of rear transverse lugs 145 extending perpendicular to the longitudinal axis A and positioned between the pair of rear longitudinal lugs 140. As shown, the rear end fitting 115 is a single unitary piece having two rear longitudinal lugs 140 and two rear transverse lugs 145, but may also be two pieces, each having one rear longitudinal lug 140 and one rear transverse lug 145. The first side chord 120 has at least one first intermediate longitudinal lug 150 extending parallel to the longitudinal axis A, and the second side chord 125 has at least one second intermediate longitudinal lug 155 opposite the first longitudinal lug 150. As shown, the first side chord 120 has two first intermediate longitudinal lugs 150, and the second side chord 125 has two second intermediate longitudinal lugs 155, however, the first side chord 120 and the second side chord 125 may have any number of intermediate longitudinal lugs required for a particular application. Furthermore, in the particular example shown, no transverse lug is positioned between the first intermediate longitudinal lug 150 and the second intermediate longitudinal lug 155. Figures 4 to 10In the example shown, the base rib assembly 100 has a pair of opposing front longitudinal lugs 130, a pair of opposing rear longitudinal lugs 140, at least a pair of opposing intermediate longitudinal lugs 150, 155 arranged between the front longitudinal lugs 130 and the rear longitudinal lugs 140, a pair of front lateral lugs 135 arranged between the front longitudinal lugs 130, and a pair of rear lateral lugs 145 arranged between the rear longitudinal lugs 140.

[0050] like Figure 6 and Figure 7 As shown, the base rib assembly 100 is positioned in the interior 65 of the multi-spar box 40 and fixed to the multi-spar box 40. For example, the front end fitting 110 of the base rib assembly 100 can be fixed to the front spar 45 of the multi-spar box 40 by screws, bolts, welding, or any other known fixing method. Similarly, the rear end fitting 115 can be fixed to the rear spar 50 by screws, bolts, welding, or any other known fixing method. In addition, the intermediate spar 55 can be fixed to the base rib assembly 100 by attaching an L-shaped shear clip 160 between the base rib 105 and / or the first and second side chords 120 and 125 of the base rib assembly 100 and the intermediate spar 55 using screws, bolts, welding, or any other known fixing method.

[0051] refer to Figure 7, with the base rib assembly 100 positioned in the multi-spar box 40, the front plate 165 is positioned adjacent to the outer surface 47 of the front spar 45, or adjacent to the inner surface of the front spar 45, and is fixed to the front spar 45 and the base rib assembly 100, for example, by screws passing through the front plate 165 of the base rib assembly 100, the front spar 45, and the front end fitting 110. Alternatively, the front plate 165 may be fixed to the front spar 45 and the base rib assembly 100 by bolts, welding, or any other known fixing method. The front plate 165 includes a transverse lug 170 corresponding to each front transverse lug 135 of the front end fitting 110, and adjacent to and aligned with the corresponding front transverse lug 135. As shown, the front plate 165 is a single integral piece including two transverse lugs 170, but may also be two or more pieces, each piece having a single transverse lug 170 corresponding to the front transverse lug 135. Similarly, the rear plate 175 is positioned adjacent to the outer surface 52 of the rear spar 50 or adjacent to the inner surface of the rear spar 50 opposite the front plate 165, and is fixed to the rear spar 50 and the base rib assembly 100, for example, by screws passing through the rear plate 175, the rear spar 50, and the rear end fitting 115 of the base rib assembly 100. Alternatively, the rear plate 175 can be fixed to the rear spar 50 and the base rib assembly 100 by bolts, welding, or any other known fixing method. The rear plate 175 includes a transverse lug 180 corresponding to each rear transverse lug 145 of the rear end fitting 115 and adjacent to and aligned with the corresponding rear transverse lug 145. As shown, the rear plate 175 is a single integral piece including two transverse lugs 180, but can also be two or more pieces, each piece having a single transverse lug 180 corresponding to the rear transverse lug 145.

[0052] The first side panels 185 are positioned adjacent to the outer surface 62A of the first side skin 60A and are secured to the first side skin 60A and the base rib assembly 100, for example, by screws passing through the first side panels 185, the first side skin 60A, and the first side chord 120. Alternatively, the first side panels 185 may be secured to the first side skin 60A and the base rib assembly 100 by bolts, welding, or any other known securing method. Each first side panel 185 includes a longitudinal lug 190 adjacent to and aligned with a corresponding first intermediate longitudinal lug 150. In the illustrated example, there are two first side panels 185 because there are two first intermediate longitudinal lugs 150. However, there may be any number of first side panels 185 as desired for the number of first intermediate longitudinal lugs 150. Furthermore, instead of separate first side panels 185, a single, one-piece first side panel having a plurality of longitudinal lugs may be used, each corresponding to a first intermediate longitudinal lug. A corresponding second side panel (not shown) is also positioned adjacent to the outer surface 62B of the second side skin 60B opposite to the corresponding first side panel 185, and is secured to the second side skin 60B and the base rib assembly 100, for example, by screws passing through the second side panel, the second side skin 60B, and the second side chord 125. Alternatively, the second side panels may be secured to the second side skin 60B and the base rib assembly 100 by bolts, welding, or any other known securing method. Each second side panel includes a longitudinal lug adjacent to and aligned with a corresponding second intermediate longitudinal lug 155. As with the first side panel 185, any number of second side panels may be present, depending on the number of the plurality of second intermediate longitudinal lugs 155, or a single one-piece second side panel having a plurality of longitudinal lugs corresponding to the second intermediate longitudinal lugs 155 may be used instead of separate second side panels.

[0053] The third side panel 195 is positioned adjacent to the outer surface 62A of the first side skin 60A and is secured to the first side skin 60A and the base rib assembly 100, for example, by screws passing through the third side panel 195, the first side skin 60A, and the front end fitting 110. Alternatively, the third side panel 195 may be secured to the first side skin 60A and the base rib assembly 100 by bolts, welding, or any other known securing method. The third side panel 195 includes a longitudinal lug 200 adjacent to and aligned with the corresponding front longitudinal lug 130. A corresponding fourth side panel (not shown) is also positioned adjacent to the outer surface 62B of the second side skin 60B opposite to the corresponding third side panel 195 and is secured to the second side skin 60B and the base rib assembly 100, for example, by screws passing through the fourth side panel, the second side skin 60B, and the front end fitting 110. Alternatively, the fourth side panel may be secured to the second side skin 60B and the base rib assembly 100 by bolts, welding, or any other known securing method. The fourth side panel includes a longitudinal lug adjacent to and aligned with a corresponding front longitudinal lug 130 .

[0054] The fifth side panel 205 is positioned adjacent to the outer surface 62A of the first side skin 60A and is secured to the first side skin 60A and the base rib assembly 100, for example, by screws passing through the fifth side panel 205, the first side skin 60A, and the front end fitting 115. Alternatively, the fifth side panel 205 may be secured to the first side skin 60A and the base rib assembly 100 by bolts, welding, or any other known securing method. The fifth side panel 205 includes a longitudinal lug 210 adjacent to and aligned with the corresponding rear longitudinal lug 140. A corresponding sixth side panel (not shown) is also positioned adjacent to the outer surface 62B of the second side skin 60B opposite to the corresponding fifth side panel 205 and is secured to the second side skin 60B and the base rib assembly 100, for example, by screws passing through the sixth side panel, the second side skin 60B, and the front end fitting 115. Alternatively, the sixth side panel may be secured to the second side skin 60B and the base rib assembly 100 by bolts, welding, or any other known securing method. The sixth side panel includes a longitudinal lug adjacent to and aligned with the corresponding rear longitudinal lug 140 .

[0055] refer to Figure 8 , a pair of front U-shaped clips 220 correspond to the pair of front longitudinal lugs 130, and each front U-shaped clip 220 extends through a corresponding hole 30 in the outer skin 25 and is secured to the frame member 20 of the aircraft fuselage 15. In the example shown, the front U-shaped clips 220 each have a first mounting arm 225, a second mounting arm 230, and a third mounting arm 235, and a transverse wall 240 extending inwardly generally perpendicular to the third mounting arm 235. Similarly, a pair of rear U-shaped clips 245 correspond to the pair of rear longitudinal lugs 140, and each rear U-shaped clip 245 extends through a corresponding hole 30 in the outer skin 25 and is secured to the frame member 20 of the aircraft fuselage. In the example shown, the rear U-shaped clips 245 each have a first mounting arm 250, a second mounting arm 255, and a third mounting arm 260, and a transverse wall 240 extending inwardly generally perpendicular to the third mounting arm 260. The pair of intermediate clevises 270 corresponds to the pair of intermediate longitudinal lugs 150, 155 and each intermediate clevis 270 extends through a corresponding hole 30 in the outer skin 25 and is secured to the frame member 20 of the aircraft fuselage 15. The intermediate clevises 270 each have only a first mounting arm 275 and a second mounting arm 280.

[0056] refer to Fig. 9 and Fig.10, the longitudinal lug 190 of the first side panel 185 and the corresponding first intermediate longitudinal lug 150 of the base rib assembly 100 are positioned between the first mounting arm 275 and the second mounting arm 280 of the corresponding intermediate U-shaped clip 270, and the longitudinal lug (not shown) of the second side panel of the base rib assembly 100 and the corresponding second intermediate longitudinal lug 155 are positioned between the first mounting arm 275 and the second mounting arm 280 of the corresponding intermediate U-shaped clip 270. A retaining member 70 (such as a bolt, a pin, etc.) is inserted through the mounting holes 152, 157 in each intermediate longitudinal lug 150, 155, the mounting holes 192 in the first side panel 185 and the second side panel, and the mounting holes 282 in each mounting arm 275, 280 of each corresponding intermediate U-shaped clip 270 to secure the vertical tail 35 to the aircraft fuselage 15.

[0057] In addition, the longitudinal lug 200 of the third side panel 195 is positioned between the first mounting arm 225 and the second mounting arm 230 of the corresponding front U-shaped clip 220, and the corresponding front longitudinal lug 130 of the base rib assembly 100 is positioned between the second mounting arm 230 and the third mounting arm 235 of the corresponding front U-shaped clip 220. The longitudinal lug of the fourth side panel is similarly positioned between the first mounting arm 225 and the second mounting arm 230 of the corresponding front U-shaped clip 220 on the opposite side, and the corresponding front longitudinal lug 130 of the base rib assembly 100 is positioned between the second mounting arm 230 and the third mounting arm 235 of the corresponding front U-shaped clip 220. A retaining member 70 (such as a bolt, pin, etc.) is inserted through the mounting hole 132 in each front longitudinal lug 130, the mounting holes 202 in the third side panel 195 and the fourth side panel, and the mounting hole 242 in each mounting arm 225, 230, 235 of each corresponding front U-shaped clip 220 to secure the vertical tail 35 to the aircraft fuselage 15.

[0058] Similarly, the longitudinal lug 210 of the fifth side panel 205 is positioned between the first mounting arm 250 and the second mounting arm 255 of the corresponding rear U-shaped clip 245, and the corresponding rear longitudinal lug 140 of the base rib assembly 100 is positioned between the second mounting arm 255 and the third mounting arm 260 of the corresponding rear U-shaped clip 245. The longitudinal lug of the sixth side panel is similarly positioned between the first mounting arm 250 and the second mounting arm 255 of the corresponding rear U-shaped clip 245 on the opposite side, and the corresponding rear longitudinal lug 140 of the base rib assembly 100 is positioned between the second mounting arm 255 and the third mounting arm 260 of the corresponding rear U-shaped clip 245. A retaining member 70 (such as a bolt, pin, etc.) is inserted through the mounting hole 142 in each rear longitudinal lug 140, the mounting holes 212 in the fifth side panel 205 and the sixth side panel, and the mounting hole 267 in each mounting arm 250, 255, 260 of each corresponding rear U-shaped clip 245 to secure the vertical tail 35 to the aircraft fuselage 15.

[0059] To provide lateral support to the vertical tail 35, the first front link 285A and the second front link 285B interconnect each of the pair of front lateral lugs 135 of the front fitting 110 with the corresponding lateral wall 240 of one of the pair of front clevises 220 via a retaining member 75 (such as a bolt, a pin, etc.) extending through the mounting hole 137 in the front lateral lug 135 and the mounting hole 244 in the lateral wall 240 of the front clevis 220. Similarly, the first rear link 290A and the second rear link 290B interconnect each of the pair of rear lateral lugs 145 of the rear fitting 115 with the corresponding lateral wall 265 of one of the pair of rear clevises 245 via a retaining member 75 (such as a bolt, a pin, etc.) extending through the mounting hole 147 in the rear lateral lug 145 and the mounting hole 269 in the lateral wall 265 of the rear clevis 245.

[0060] As discussed above, to attach the vertical tail 35 to the aircraft fuselage 15, the base rib assembly 100 is first assembled, which has a pair of opposing front longitudinal lugs 130, a pair of opposing rear longitudinal lugs 140, at least a pair of opposing intermediate longitudinal lugs 150, 155 between the front longitudinal lugs 130 and the rear longitudinal lugs 140, and a pair of front lateral lugs 135 and rear lateral lugs 145, each of which has a corresponding mounting hole 132, 142, 152, 157, 137, 147. To assemble the base rib assembly 100, the first side chord 120 is attached to the base rib 105, the second side chord 125 is attached to the base rib 105 opposite the first side chord 120, the front end fitting 110 is attached to the base rib 105, and the rear end fitting 115 is attached to the base rib 105 opposite the front end fitting 110. Then, base rib assembly 100 is inserted into interior 65 of multi-spar box 40 of vertical tail 35 , and L-shaped shear clips 160 are attached between intermediate spar 55 and base rib assembly 100 .

[0061] Then, the front panel 165 is positioned adjacent to the outer surface 47 of the front spar 45 or adjacent to the inner surface of the front spar 45 and fixed to the front spar 45 and the base rib assembly 100, the rear panel 175 is positioned adjacent to the outer surface 52 of the rear spar 50 or adjacent to the inner surface of the rear spar 50 opposite to the front panel 165 and fixed to the rear spar 50 and the base rib assembly 100, the first side panel 185 is positioned adjacent to the outer surface 62A of the first side skin 60A of the multi-spar box 40 and fixed to the first side skin 60A and the base rib assembly 100, and the second side panel is positioned adjacent to the outer surface 62B of the second side skin 60B of the multi-spar box 40 and fixed to the second side skin 60B and the base rib assembly 100.

[0062] The front clevis 220, rear clevis 245, and intermediate clevis 270 are inserted through corresponding holes 30 in the outer skin 25 of the aircraft fuselage 15 and secured to corresponding frame members 20 of the aircraft fuselage, such as by bolts, screws, rivets, welding, etc. The front clevis 220 corresponds to the front longitudinal lug 130 and each has a first mounting arm 225, a second mounting arm 230, and a third mounting arm 235 with mounting holes 242, and the rear clevis 245 corresponds to the rear longitudinal lug 140 and each has a first mounting arm 250, a second mounting arm 255, and a third mounting arm 260 with mounting holes 267. The intermediate clevis 270 corresponds to the intermediate longitudinal lugs 150, 155, and each intermediate clevis has only a first mounting arm 275 and a second mounting arm 280 with mounting holes 282.

[0063] Then, vertical tail 35 is positioned adjacent to aircraft fuselage 15 so that each front longitudinal lug 130, rear longitudinal lug 140, and intermediate longitudinal lugs 150, 155 are aligned with a corresponding front clevis 220, rear clevis 245, or intermediate clevis 270, and retaining member 70 is inserted through mounting hole 132, 142, 152, 157 of each longitudinal lug 130, 140, 150, 155 and mounting hole 242, 267, 282 of each corresponding clevis 220, 245, 270 to secure vertical tail 35 to aircraft fuselage 15. Each front transverse lug 135 is attached to a first end of a corresponding front link 285A, 285B by a retaining member 75, and a second end of the front link 285A, 285B is attached to a corresponding transverse clevis, which in the example shown is the transverse wall 240 of the front clevis 220. Similarly, each rear transverse lug 145 is attached to a first end of a corresponding rear link 290A, 290B by a retaining member 75, and a second end of the rear link 490A, 490B is attached to a corresponding transverse clevis, which in the example shown is the transverse wall 265 of the rear transverse clevis 245.

[0064] refer to Figures 11 to 17 , showing a second example connection between the aircraft fuselage 15 and the multi-spar box 40 of the vertical tail 35. Fig.11 and Fig.12As best seen in FIG. 1 , the base rib assembly 300 has a base rib 305 and a front fitting 310 connected to the base rib 305, a rear fitting 315 opposite the front fitting 310, a first side chord 320, and a second side chord 325 opposite the first side chord 320. The front fitting 310 includes a pair of opposed front longitudinal lugs 330 extending parallel to the longitudinal axis A of the base rib assembly 300 and a pair of front transverse lugs 335 extending perpendicular to the longitudinal axis A and positioned between the pair of front longitudinal lugs 330. As shown, the front fitting 310 is a single unitary piece having both the front longitudinal lugs 330 and the front transverse lugs 335, but may also be two pieces, each having one front longitudinal lug 330 and one front transverse lug 335, as Figures 4 to 5 As shown. The rear end fitting 315 includes a pair of opposed rear longitudinal lugs 340 extending parallel to the longitudinal axis A and a pair of rear transverse lugs 345 extending perpendicular to the longitudinal axis A and positioned between the pair of rear longitudinal lugs 340. As shown, the rear end fitting 315 is a single integral piece having two rear longitudinal lugs 340 and two rear transverse lugs 345, but may also be two pieces, each having one rear longitudinal lug 340 and one rear transverse lug 345. The first side chord 320 has at least one first intermediate longitudinal lug 350 extending parallel to the longitudinal axis A, and the second side chord 325 has at least one second intermediate longitudinal lug 355 opposite the first longitudinal lug 350. As shown, the first side chord 320 has two first intermediate longitudinal lugs 350, and the second side chord 325 has two second intermediate longitudinal lugs 355, however, the first side chord 320 and the second side chord 325 may have any number of intermediate longitudinal lugs required for a particular application. Furthermore, in the particular example shown, no transverse lug is positioned between the first intermediate longitudinal lug 350 and the second intermediate longitudinal lug 355. Figures 11 to 17 In the example shown, the base rib assembly 300 has a pair of opposing front longitudinal lugs 330, a pair of opposing rear longitudinal lugs 340, at least one pair of opposing intermediate longitudinal lugs 350, 355 arranged between the front longitudinal lugs 330 and the rear longitudinal lugs 340, a pair of front lateral lugs 335 arranged between the front longitudinal lugs 330, and a pair of rear lateral lugs 345 arranged between the rear longitudinal lugs 340.

[0065] like Fig.13 and Fig.14As shown, the base rib assembly 300 is positioned in the interior 65 of the multi-spar box 40 and fixed to the multi-spar box 40. For example, the front end fitting 310 of the base rib assembly 300 can be fixed to the front spar 45 of the multi-spar box 40 by screws, bolts, welding, or any other known fixing method. Similarly, the rear end fitting 315 can be fixed to the rear spar 50 by screws, bolts, welding, or any other known fixing method. In addition, the intermediate spar 55 can be fixed to the base rib assembly 300 by attaching an L-shaped shear clip 360 between the base rib 305 and / or the first and second side chords 320 and 325 of the base rib assembly 300 and the intermediate spar 55 using screws, bolts, welding, or any other known fixing method.

[0066] refer to Fig.14 , with the base rib assembly 300 positioned in the multi-spar box 40, the front plate 365 is positioned adjacent to the outer surface 47 of the front spar 45, or adjacent to the inner surface of the front spar 45, and is fixed to the front spar 45 and the base rib assembly 300, for example, by screws passing through the front plate 365 of the base rib assembly 300, the front spar 45, and the front end fitting 310. Alternatively, the front plate 365 may be fixed to the second front spar 45 and the base rib assembly 300 by bolts, welding, or any other known fixing method. The front plate 365 includes a transverse lug 370 corresponding to each front transverse lug 335 of the front end fitting 310, and adjacent to the corresponding front transverse lug 335 and aligned with the corresponding front transverse lug 135. As shown, the front plate 365 is a single integral piece including two transverse lugs 370, but may also be two or more pieces, each piece having a single transverse lug 370 corresponding to the front transverse lug 335. Similarly, the rear plate 375 is positioned adjacent to the outer surface 52 of the rear spar 50 or adjacent to the inner surface of the rear spar 50 opposite the front plate 365, and is fixed to the rear spar 50 and the base rib assembly 300, for example, by screws passing through the rear plate 375, the rear spar 50, and the rear end fitting 315 of the base rib assembly 300. Alternatively, the rear plate 375 can be fixed to the rear spar 50 and the base rib assembly 300 by bolts, welding, or any other known fixing method. The rear plate 375 includes a transverse lug 380 corresponding to each rear transverse lug 345 of the rear end fitting 315 and adjacent to and aligned with the corresponding rear transverse lug 345. As shown, the rear plate 375 is a single integral piece including two transverse lugs 380, but can also be two or more pieces, each piece having a single transverse lug 380 corresponding to the rear transverse lug 345.

[0067] The first side panel 385 is positioned adjacent to the outer surface 62A of the first side skin 60A and is secured to the first side skin 60A and the base rib assembly 300, for example, by screws passing through the first side panel 385, the first side skin 60A, and the first side chord 320. Alternatively, the first side panel 385 may be secured to the first side skin 60A and the base rib assembly 300 by bolts, welding, or any other known securing method. Each first side panel 385 includes a longitudinal lug 390 adjacent to and aligned with a corresponding first intermediate longitudinal lug 350. In the illustrated example, there are two first side panels 385 because there are two first intermediate longitudinal lugs 350. However, there may be any number of first side panels 385 as desired for the number of first intermediate longitudinal lugs 350. Furthermore, instead of separate first side panels 385, a single, one-piece first side panel having a plurality of longitudinal lugs may be used, each corresponding to a first intermediate longitudinal lug. A corresponding second side panel (not shown) is also positioned adjacent to the outer surface 62B of the second side skin 60B opposite to the corresponding first side panel 385, and is secured to the second side skin 60B and the base rib assembly 300, for example, by screws passing through the second side panel, the second side skin 60B, and the second side chord 325. Alternatively, the second side panels may be secured to the second side skin 60B and the base rib assembly 300 by bolts, welding, or any other known securing method. Each second side panel includes a longitudinal lug adjacent to and aligned with a corresponding second intermediate longitudinal lug 355. As with the first side panel 385, any number of second side panels may be present, depending on the number of the plurality of second intermediate longitudinal lugs 355, or a single one-piece second side panel having a plurality of longitudinal lugs corresponding to the second intermediate longitudinal lugs 355 may be used instead of separate second side panels.

[0068] The third side panel 395 is positioned adjacent to the outer surface 62A of the first side skin 60A and is secured to the first side skin 60A and the base rib assembly 300, for example, by screws passing through the third side panel 395, the first side skin 60A, and the front end fitting 310. Alternatively, the third side panel 395 may be secured to the first side skin 60A and the base rib assembly 300 by bolts, welding, or any other known securing method. The third side panel 395 includes a longitudinal lug 400 adjacent to and aligned with the corresponding front longitudinal lug 330. A corresponding fourth side panel (not shown) is also positioned adjacent to the outer surface 62B of the second side skin 60B opposite to the corresponding third side panel 395 and is secured to the second side skin 60B and the base rib assembly 300, for example, by screws passing through the fourth side panel, the second side skin 60B, and the front end fitting 310. Alternatively, the fourth side panel may be secured to the second side skin 60B and the base rib assembly 300 by bolts, welding, or any other known securing method. The fourth side panel includes a longitudinal lug adjacent to and aligned with a corresponding front longitudinal lug 330 .

[0069] The fifth side panel 405 is positioned adjacent to the outer surface 62A of the first side skin 60A and is secured to the first side skin 60A and the base rib assembly 300, for example, by screws passing through the fifth side panel 405, the first side skin 60A, and the front end fitting 315. Alternatively, the fifth side panel 405 may be secured to the first side skin 60A and the base rib assembly 300 by bolts, welding, or any other known securing method. The fifth side panel 405 includes a longitudinal lug 410 adjacent to and aligned with the corresponding rear longitudinal lug 340. A corresponding sixth side panel (not shown) is also positioned adjacent to the outer surface 62B of the second side skin 60B opposite to the corresponding fifth side panel 405 and is secured to the second side skin 60B and the base rib assembly 300, for example, by screws passing through the sixth side panel, the second side skin 60B, and the front end fitting 315. Alternatively, the sixth side panel may be secured to the second side skin 60B and the base rib assembly 300 by bolts, welding, or any other known securing method. The sixth side panel includes a longitudinal lug adjacent to and aligned with a corresponding rear longitudinal lug 340 .

[0070] refer to Fig.15 , a pair of front U-shaped clips 420 correspond to the pair of front longitudinal lugs 330, and each front U-shaped clip 420 extends through a corresponding hole 30 in the outer skin 25 and is secured to the frame member 20 of the aircraft fuselage 15. In the example shown, the front U-shaped clips 420 each have a first mounting arm 425 and a second mounting arm 430. Similarly, a pair of rear U-shaped clips 445 correspond to the pair of rear longitudinal lugs 340, and each rear U-shaped clip 445 extends through a corresponding hole 30 in the outer skin 25 and is secured to the frame member 20 of the aircraft fuselage 15. In the example shown, the rear U-shaped clips 445 each have a first mounting arm 450 and a second mounting arm 455. A pair of intermediate U-shaped clips 470 correspond to the pair of intermediate longitudinal lugs 350, 355, and each intermediate U-shaped clip 470 extends through a corresponding hole 30 in the outer skin 25 and is secured to the frame member 20 of the aircraft fuselage 15. The intermediate clevises 470 each have a first mounting arm 475 and a second mounting arm 480. The front transverse clevis 435 is positioned between the pair of front clevises 420 and extends through corresponding holes 30 in the outer skin 25 and is secured to the frame member 20 of the aircraft fuselage 15. The rear transverse clevis 460 is positioned between the pair of rear clevises 445 and extends through corresponding holes 30 in the outer skin 25 and is secured to the frame member 20 of the aircraft fuselage 15.

[0071] refer to Fig.16 and Fig.17, the longitudinal lug 390 of the first side panel 385 and the corresponding first intermediate longitudinal lug 350 of the base rib assembly 300 are positioned between the first mounting arm 475 and the second mounting arm 480 of the corresponding intermediate U-shaped clip 470, and the longitudinal lug (not shown) of the second side panel of the base rib assembly 300 and the corresponding second intermediate longitudinal lug 355 are positioned between the first mounting arm 475 and the second mounting arm 480 of the corresponding intermediate U-shaped clip 470. A retaining member 70 (such as a bolt, a pin, etc.) is inserted through the mounting holes 352, 357 in each intermediate longitudinal lug 350, 355, the mounting holes 392 in the first side panel 385 and the second side panel, and the mounting holes 482 in each mounting arm 475, 480 of each corresponding intermediate U-shaped clip 470 to secure the vertical tail 35 to the aircraft fuselage 15.

[0072] In addition, the longitudinal lug 400 of the third side panel 395 and the corresponding front longitudinal lug 330 of the base rib assembly 300 are positioned between the first mounting arm 425 and the second mounting arm 430 of the corresponding front U-shaped clip 420. The longitudinal lug of the fourth side panel and the corresponding front longitudinal lug 330 of the base rib assembly 300 are similarly positioned between the first mounting arm 425 and the second mounting arm 430 of the corresponding front U-shaped clip 420. A retaining member 70 (such as a bolt, a pin, etc.) is inserted through the mounting hole 332 in each front longitudinal lug 330, the mounting holes 402 in the third side panel 395 and the fourth side panel, and the mounting hole 442 in each mounting arm 425, 430 of each corresponding front U-shaped clip 420 to secure the vertical tail 35 to the aircraft fuselage 15.

[0073] Similarly, the longitudinal lug 410 of the fifth side panel 405 and the corresponding rear longitudinal lug 340 of the base rib assembly 300 are positioned between the first mounting arm 450 and the second mounting arm 455 of the corresponding rear U-shaped clip 445. The longitudinal lug of the sixth side panel and the corresponding rear longitudinal lug 340 of the base rib assembly 300 are similarly positioned between the first mounting arm 450 and the second mounting arm 455 of the corresponding rear U-shaped clip 445. A retaining member 70 (such as a bolt, a pin, etc.) is inserted through the mounting hole 342 in each rear longitudinal lug 340, the mounting holes 412 in the fifth side panel 405 and the sixth side panel, and the mounting hole 467 in each mounting arm 450, 455 of each corresponding rear U-shaped clip 445 to secure the vertical tail 35 to the aircraft fuselage 15.

[0074] To provide lateral support to the vertical tail 35, the first front link 485A and the second front link 485B interconnect each of the pair of front transverse lugs 335 of the front end fitting 310 with the front transverse U-shaped clip 435 via a retaining member 75 (such as a bolt, a pin, etc.) extending through the mounting hole 337 in the front transverse lug 335 and the mounting hole 440 in the front U-shaped clip 435. Similarly, the first rear link 490A and the second rear link 490B interconnect each of the pair of rear transverse lugs 345 of the rear end fitting 315 with the rear transverse U-shaped clip 460 via a retaining member 75 (such as a bolt, a pin, etc.) extending through the mounting hole 347 in the rear transverse lug 345 and the mounting hole 465 in the rear transverse U-shaped clip 460.

[0075] As discussed above, to attach the vertical tail 35 to the aircraft fuselage 15, the base rib assembly 300 is first assembled, which has a pair of opposing front longitudinal lugs 330, a pair of opposing rear longitudinal lugs 340, at least one pair of opposing intermediate longitudinal lugs 350, 355 between the front longitudinal lugs 330 and the rear longitudinal lugs 340, and a pair of front lateral lugs 335 and rear lateral lugs 345, each of which has a corresponding mounting hole 332, 342, 352, 357, 337, 347. To assemble the base rib assembly 300, the first side chord 320 is attached to the base rib 305, the second side chord 325 is attached to the base rib 305 opposite the first side chord 320, the front end fitting 310 is attached to the base rib 305, and the rear end fitting 315 is attached to the base rib 305 opposite the front end fitting 310. The base rib assembly 300 is then inserted into the interior 65 of the multi-spar box 40 of the vertical tail 35 , and the L-shaped shear clip 360 is attached between the intermediate spar 55 and the base rib assembly 300 .

[0076] Then, the front panel 365 is positioned adjacent to the outer surface 47 of the front spar 45 or adjacent to the inner surface of the front spar 45 and fixed to the front spar 45 and the base rib assembly 300, the rear panel 375 is positioned adjacent to the outer surface 52 of the rear spar 50 or adjacent to the inner surface of the rear spar 50 opposite to the front panel 365 and fixed to the rear spar 50 and the base rib assembly 300, the first side panel 385 is positioned adjacent to the outer surface 62A of the first side skin 60A of the multi-spar box 40 and fixed to the first side skin 60A and the base rib assembly 300, and the second side panel is positioned adjacent to the outer surface 62B of the second side skin 60B of the multi-spar box 40 and fixed to the second side skin 60B and the base rib assembly 300.

[0077] The front clevis 420, rear clevis 445, and intermediate clevis 470 are inserted through corresponding holes 30 in the outer skin 25 of the aircraft fuselage 15 and secured to corresponding frame members 20 of the aircraft fuselage 15, such as by bolts, screws, rivets, welding, etc. The front clevis 420 corresponds to the front longitudinal lugs 330 and each has a first mounting arm 425 and a second mounting arm 430 with a mounting hole 442, and the rear clevis 445 corresponds to the rear longitudinal lugs 340 and each has a first mounting arm 450 and a second mounting arm 455 with a mounting hole 467. The intermediate clevis 470 corresponds to the intermediate longitudinal lugs 350, 355 and each has a first mounting arm 475 and a second mounting arm 480 with a mounting hole 482.

[0078] Then, the vertical tail 35 is positioned adjacent to the aircraft fuselage 15 so that each of the front longitudinal lugs 330, the rear longitudinal lugs 340, and the intermediate longitudinal lugs 350, 355 are aligned with the corresponding front clevis 420, the rear clevis 445, or the intermediate clevis 470, and the retaining member 70 is inserted through the mounting holes 332, 342, 352, 357 of each longitudinal lug 330, 340, 350, 355 and the mounting holes 442, 467, 482 of each corresponding clevis 420, 445, 470 to secure the vertical tail 35 to the aircraft fuselage 15. Each front transverse lug 335 is attached to the first end of the corresponding front link 485A, 485B through the retaining member 75, and the second end of the front link 485A, 485B is attached to the front transverse clevis 435 through the retaining member 75. Similarly, each rear lateral lug 345 is attached to a first end of a corresponding rear lateral link 490A, 490B via a retaining member 75 , and a second end of the rear lateral link 490A, 490B is attached to the rear lateral clevis 460 via a retaining member 75 .

[0079] refer to Figures 18 to 24 , shows a third example connection between the aircraft fuselage 15 and the multi-spar box 40 of the vertical tail 35. Fig.18 and Fig.19As best seen in FIG. 1 , the base rib assembly 500 has a base rib 505 and a front fitting 510 connected to the base rib 505, a rear fitting 515 opposite the front fitting 510, a first side chord 520, and a second side chord 525 opposite the first side chord 520. The front fitting 510 includes a pair of front transverse lugs 535 extending perpendicular to the longitudinal axis A. As shown, the front fitting 110 is two pieces, each piece having one front transverse lug 535, but it can also be a single unitary piece with two front transverse lugs 535, as shown and described in previous examples. The rear fitting 515 includes a pair of rear transverse lugs 545 extending perpendicular to the longitudinal axis A. As shown, the rear fitting 515 is two pieces, each piece having one rear transverse lug 545, but it can also be a single unitary piece with two rear transverse lugs 545, as shown and described in previous examples. The first side chord 520 has at least one first intermediate longitudinal lug 550 extending parallel to the longitudinal axis A, and the second side chord 525 has at least one second intermediate longitudinal lug 555 opposite the first intermediate longitudinal lug 550. As shown, the first side chord 520 has two first intermediate longitudinal lugs 550, and the second side chord 525 has two second intermediate longitudinal lugs 555, however, the first side chord 520 and the second side chord 525 can have any number of intermediate longitudinal lugs required for a particular application. In addition, in the specific example shown, no transverse lugs are positioned between the first intermediate longitudinal lug 550 and the second intermediate longitudinal lug 555. Therefore, in Figure 18 to Figure 19 In the example shown, the base rib assembly 500 has at least one pair of opposing intermediate longitudinal lugs 550, 555 arranged between the front portion 500A of the base rib assembly 500 and the rear portion 500B of the base rib assembly 500, a pair of front lateral lugs 535 positioned along the front portion 500A of the base rib assembly 500, and a pair of rear lateral lugs 545 positioned along the rear portion 500B of the base rib assembly 500.

[0080] like Figure 20 to Figure 21As shown, the base rib assembly 500 is positioned in the interior 65 of the multi-spar box 40, wherein the first side chord 520 is positioned inside the first side skin 60A, the second side chord 525 is positioned inside the second side skin 60B, the front end fitting 510 is positioned adjacent to the inner surface or outer surface 47 of the front spar 45, the rear end fitting 515 is positioned adjacent to the inner surface or outer surface 52 of the rear spar 50, and the base rib assembly 500 is fixed to the multi-spar box 40. For example, the front end fitting 510 of the base rib assembly 500 can be fixed to the front spar 45 of the multi-spar box 40 by screws, bolts, welding, or any other known fixing method. Similarly, the rear end fitting 515 can be fixed to the rear spar 50 by screws, bolts, welding, or any other known fixing method. Furthermore, the intermediate spar 55 may be fixed to the base rib assembly 500 by attaching an L-shaped shear clip 560 between the base rib 505 and / or the first and second side chords 520 , 525 of the base rib assembly 500 and the intermediate spar 55 using screws, bolts, welding, or any other known fixing method.

[0081] refer to Fig.21As described above, with the base rib assembly 500 positioned in the multi-spar box 40, the first side panel 585 is positioned adjacent to the outer surface 62A of the first side skin 60A and is secured to the first side skin 60A and the base rib assembly 500, for example, by screws passing through the first side panel 585, the first side skin 60A, and the first side chord 520. Alternatively, the first side panel 585 may be secured to the first side skin 60A and the base rib assembly 500 by bolts, welding, or any other known securing method. Each first side panel 585 includes a longitudinal lug 590 adjacent to and aligned with a corresponding first intermediate longitudinal lug 550. In the illustrated example, there are two first side panels 585 because there are two first intermediate longitudinal lugs 550. However, any number of first side panels 585 may be present as required by the number of first intermediate longitudinal lugs 550. In addition, instead of separate first side panels 585, a single one-piece first side panel having a plurality of longitudinal lugs, each corresponding to the first intermediate longitudinal lug, may be used. A corresponding second side panel (not shown) is also positioned adjacent to the outer surface 62B of the second side skin 60B opposite to the corresponding first side panel 585, and is secured to the second side skin 60B and the base rib assembly 500, for example, by screws passing through the second side panel, the second side skin 60B, and the second side chord 525. Alternatively, the second side panels may be secured to the second side skin 60B and the base rib assembly 500 by bolts, welding, or any other known securing method. Each second side panel includes a longitudinal lug adjacent to and aligned with the corresponding second intermediate longitudinal lug 555. As with the first side panel 585, there may be any number of second side panels as desired, depending on the number of the plurality of second intermediate longitudinal lugs 555, or a single one-piece second side panel having a plurality of longitudinal lugs corresponding to the second intermediate longitudinal lugs 555 may be used instead of separate second side panels.

[0082] refer to Fig. 22 , a pair of front U-shaped clips 620 correspond to the pair of front longitudinal lugs 535, and each front U-shaped clip 620 extends through a corresponding hole 30 in the outer skin 25 and is secured to the frame member 20 of the aircraft fuselage 15. In the example shown, the front U-shaped clips 620 each have a first mounting arm 625 and a second mounting arm 630. Similarly, a pair of rear U-shaped clips 645 correspond to the pair of rear longitudinal lugs 545, and each rear U-shaped clip 645 extends through a corresponding hole 30 in the outer skin 25 and is secured to the frame member 20 of the aircraft fuselage 15. In the example shown, the rear U-shaped clips 645 each have a first mounting arm 650 and a second mounting arm 655. A pair of intermediate U-shaped clips 670 correspond to the pair of intermediate longitudinal lugs 550, 555, and each intermediate U-shaped clip 670 extends through a corresponding hole 30 in the outer skin 25 and is secured to the frame member 20 of the aircraft fuselage 15. The intermediate clevises 670 each have a first mounting arm 675 and a second mounting arm 680 .

[0083] refer to Fig.23 and Fig.24 , the longitudinal lug 590 of the first side panel 585 and the corresponding first intermediate longitudinal lug 550 of the base rib assembly 500 are positioned between the first mounting arm 675 and the second mounting arm 680 of the corresponding intermediate U-shaped clip 670, and the longitudinal lug (not shown) of the second side panel of the base rib assembly 500 and the corresponding second intermediate longitudinal lug 555 are positioned between the first mounting arm 675 and the second mounting arm 680 of the corresponding intermediate U-shaped clip 670. A retaining member 70 (such as a bolt, a pin, etc.) is inserted through the mounting holes 552, 557 in each intermediate longitudinal lug 550, 555, the mounting holes 592 in the first side panel 585 and the second side panel, and the mounting holes 682 in each mounting arm 675, 680 of each corresponding intermediate U-shaped clip 670 to secure the vertical tail 35 to the aircraft fuselage 15.

[0084] Furthermore, in order to provide lateral support to the vertical tail 35, the front lateral lugs 535 of the base rib assembly 500 are positioned between the first mounting arm 625 and the second mounting arm 630 of the corresponding front U-shaped clip 620. A retaining member 70 (such as a bolt, a pin, etc.) is inserted through the mounting hole 537 in each front lateral lug 535 and the mounting hole 642 in each mounting arm 625, 630 of each corresponding front U-shaped clip 620 to secure the vertical tail 35 to the aircraft fuselage 15.

[0085] In addition, the rear transverse lug 545 of the base rib assembly 500 is positioned between the first mounting arm 650 and the second mounting arm 655 of the corresponding rear U-shaped clip 645. A retaining member 70 (such as a bolt, a pin, etc.) is inserted through the mounting hole 547 in each rear transverse lug 545 and the mounting hole 667 in each mounting arm 650, 655 of each corresponding rear U-shaped clip 645 to secure the vertical tail 35 to the aircraft fuselage 15.

[0086] As described above, in order to attach the vertical tail 35 to the aircraft fuselage 15, the base rib assembly 500 is first assembled, which, as discussed above, has at least one pair of opposing intermediate longitudinal lugs 550, 555 disposed between the front portion 500A and the rear portion 500B of the base rib assembly 500, and a pair of front and rear transverse lugs 535, 545 disposed along the front portion 500A and the rear portion 500B of the base rib assembly 500, respectively, each of which has a corresponding mounting hole 552, 557, 537, 547. To assemble the base rib assembly 500, the first side chord 520 is attached to the base rib 505, the second side chord 525 is attached to the base rib 505 opposite the first side chord 520, the front end fitting 510 is attached to the base rib 505, and the rear end fitting 515 is attached to the base rib 505 opposite the front end fitting 510. The base rib assembly 500 is then inserted into the interior 65 of the multi-spar box 40 of the vertical tail 35 , and the L-shaped shear clip 560 is attached between the intermediate spar 55 and the base rib assembly 500 .

[0087] Then, the first side panel 585 is positioned adjacent to the outer surface 62A of the first side skin 60A of the multi-spar box 40 and secured to the first side skin 60A and the base rib assembly 500 , and the second side panel is positioned adjacent to the outer surface 62B of the second side skin 60B of the multi-spar box 40 and secured to the second side skin 60B and the base rib assembly 500 .

[0088] The front clevis 620, rear clevis 645, and intermediate clevis 670 are inserted through corresponding holes 30 in the outer skin 25 of the aircraft fuselage 15 and secured to corresponding frame members 20 of the aircraft fuselage 15, such as by bolts, screws, rivets, welding, etc. The front clevis 620 corresponds to the front longitudinal lugs 535 and each has a first mounting arm 625 and a second mounting arm 630 with a mounting hole 642, and the rear clevis 645 corresponds to the rear longitudinal lugs 545 and each has a first mounting arm 655 and a second mounting arm 655 with a mounting hole 667. The intermediate clevis 670 corresponds to the intermediate longitudinal lugs 550, 555 and each has a first mounting arm 675 and a second mounting arm 680 with a mounting hole 682.

[0089] Then, the vertical tail 35 is positioned adjacent to the aircraft fuselage 15 so that each of the front and rear lateral lugs 535, 545 and the intermediate longitudinal lugs 550, 555 are aligned with the corresponding front U-shaped clip 620, rear U-shaped clip 645 or intermediate U-shaped clip 670, and the retaining member 70 is inserted through the mounting hole 537, 547, 552, 557 of each lug 535, 545, 550, 555 and the mounting hole 642, 667, 682 of each corresponding U-shaped clip 620, 645, 670 to secure the vertical tail 35 to the aircraft fuselage 15.

[0090] Although various embodiments have been described above, the present disclosure is not intended to be limited thereto. Changes may be made to the disclosed embodiments which still fall within the scope of the appended claims.

Claims

1. An aircraft (10), wherein: The aircraft (10) comprises: An aircraft fuselage (15) having a plurality of frame members (20) and an outer skin (25); A vertical tail (35), the vertical tail having a multi-spar box (40), the multi-spar box (40) comprising: a front spar (45), a rear spar (50), at least one intermediate spar (55) positioned between the front spar (45) and the rear spar (50) and spaced apart from the front spar (45) and the rear spar (50), a first side skin (60A) extending between the front spar and the rear spar, and a second side skin (60B) extending between the front spar (45) and the rear spar (50) opposite to the first side skin (60A), the front spar (45) and the rear spar (50) and the first side skin (60A) and the second side skin (60B) defining an interior (65) of the multi-spar box (40); a base rib assembly (100) positioned in the interior (65) of the multi-spar box (40) and secured to the multi-spar box (40), the base rib assembly (100) having an opposing pair of front longitudinal lugs (130), an opposing pair of rear longitudinal lugs (140), and at least one opposing pair of intermediate longitudinal lugs (150, 155) disposed between the front longitudinal lugs (130) and the rear longitudinal lugs (140); a pair of front U-shaped clips (220), the pair of front U-shaped clips corresponding to the pair of front longitudinal lugs (130), the front U-shaped clips (220) extending through corresponding holes (30) in the outer skin (25) and secured to one of the plurality of frame members (20), each front U-shaped clip (220) having a first mounting arm (225), a second mounting arm (230), and a third mounting arm (235); a pair of rear U-shaped clips (245) corresponding to the pair of rear longitudinal lugs (140), the rear U-shaped clips (245) extending through corresponding holes (30) in the outer skin (25) and secured to one of the plurality of frame members (20), each rear U-shaped clip (245) having a first mounting arm (250), a second mounting arm (255), and a third mounting arm (260); a pair of intermediate U-shaped clips (270) corresponding to the pair of intermediate longitudinal lugs (150, 155), the intermediate U-shaped clips (270) extending through corresponding holes (30) in the outer skin (25) and secured to one of the plurality of frame members (20), each intermediate U-shaped clip (270) having only a first mounting arm (275) and a second mounting arm (280); and A plurality of retaining members (70) are inserted through mounting holes (132, 142, 152, 157) in each of the front longitudinal lugs (130), the intermediate longitudinal lugs (150, 155), and the rear longitudinal lugs (140) and through mounting holes (242, 267, 282) in each of the corresponding front clevis (220), intermediate clevis (270), and rear clevis (245) to secure the vertical tail (35) to the aircraft fuselage (15).

2. The aircraft (10) according to claim 1, wherein: The base rib assembly (100) includes at least one front transverse lug (135) positioned between the pair of front longitudinal lugs (130) and at least one rear transverse lug (145) positioned between the pair of rear longitudinal lugs (140).

3. The aircraft (10) according to claim 2, wherein: The base rib assembly (100) does not have any transverse lugs between the at least one pair of intermediate longitudinal lugs (150).

4. The aircraft (10) according to claim 2, comprising: a front transverse U-shaped clip (435) positioned between the pair of front U-shaped clips (220), the front transverse U-shaped clip (435) extending through the hole (30) in the outer skin (25) and secured to one of the plurality of frame members (20); a rear transverse U-shaped clip (460) positioned between the pair of rear U-shaped clips (245), the rear transverse U-shaped clip (460) extending through the hole (30) in the outer skin (25) and secured to one of the plurality of frame members (20); a front link (485A) interconnecting the front transverse clevis (435) and the at least one front transverse lug (135); and A rear link (490A) interconnects the rear transverse clevis (460) and the at least one rear transverse lug (145).

5. The aircraft (10) according to claim 4, comprising: a second front link (485B) interconnecting the front transverse clevis (435) and another front transverse lug (135); and A second rear link (490B) interconnects the rear transverse clevis (460) and another rear transverse lug (145).

6. The aircraft (10) according to claim 2, comprising: a front link (285A) interconnecting the at least one front lateral lug (135) and a lateral wall (240) of one of the pair of front clevises (220); and A rear link (290A) interconnects the at least one rear lateral lug (145) with a lateral wall (265) of one of the pair of rear clevises (245).

7. The aircraft (10) according to claim 6, comprising: a second front link (285B) interconnecting the other front lateral lug (135) and the lateral wall (240) of the other front clevis of the pair of front clevises (220); and A second rear link (290B) interconnects the other rear lateral lug (145) and the lateral wall (265) of the other rear clevis of the pair of rear clevises (245).

8. The aircraft (10) according to claim 2, comprising: a front plate (165) adjacent to an outer surface (47) of the front spar (45) and secured to the front spar (45) and the base rib assembly (100), the front plate (165) having a transverse lug (170) adjacent to and aligned with the at least one front transverse lug (135) of the base rib assembly (100); a rear panel (175) adjacent to the outer surface (52) of the rear spar (50) opposite the front panel (165) and secured to the rear spar (50) and the base rib assembly (100), the rear panel (175) having at least one transverse lug (180) adjacent to and aligned with the at least one rear transverse lug (145) of the base rib assembly (100); a first side panel (185) adjacent to an outer surface (62A) of the first side skin (60A) and secured to the first side skin (60A) and the base rib assembly (100), the first side panel (185) having at least one longitudinal lug (190) adjacent to and aligned with one of the intermediate longitudinal lugs (150) of the base rib assembly (100); as well as A second side panel, the second side panel being adjacent to an outer surface (62B) of the second side skin (60B) and being secured to the second side skin (60B) and the base rib assembly (100), the second side panel having at least one longitudinal lug adjacent to and aligned with another of the intermediate longitudinal lugs (155) of the base rib assembly (100).

9. The aircraft (10) according to claim 8, wherein: The at least one longitudinal lug (190) of the first side panel (185) and the corresponding intermediate longitudinal lug (150) of the base rib assembly (100) are positioned between the first mounting arm (275) and the second mounting arm (280) of the corresponding intermediate U-shaped clip (270); and The at least one longitudinal lug of the second side panel and the corresponding intermediate longitudinal lug (155) of the base rib assembly (100) are positioned between the first mounting arm (275) and the second mounting arm (280) of the corresponding intermediate U-shaped clip (270).

10. The aircraft (10) according to claim 9, comprising: a third side panel (195) adjacent to an outer surface (62A) of the first side skin (60A) and secured to the first side skin (60A) and the base rib assembly (100), the third side panel (195) having at least one longitudinal lug (200) aligned with one of the forward longitudinal lugs (130) of the base rib assembly (100); as well as A fourth side panel, the fourth side panel being adjacent to the outer surface (62B) of the second side skin (60B) and being fixed to the second side skin (60B) and the base rib assembly (100), the fourth side panel having at least one longitudinal lug aligned with another of the front longitudinal lugs (130) of the base rib assembly (100).

11. The aircraft (10) of claim 10, wherein: The at least one longitudinal lug (200) of the third side panel (195) is positioned between the first mounting arm (225) and the second mounting arm (230) of a first front U-shaped clip (220) of the pair of front U-shaped clips (220), and a corresponding front longitudinal lug (130) of the base rib assembly (100) is positioned between the second mounting arm (230) and the third mounting arm (235) of the first front U-shaped clip (220); and The at least one longitudinal lug of the fourth side panel is positioned between the first mounting arm (225) and the second mounting arm (230) of a second front U-shaped clip (220) of the pair of front U-shaped clips (220), and a corresponding front longitudinal lug (130) of the base rib assembly (100) is positioned between the second mounting arm (230) and the third mounting arm (235) of the second front U-shaped clip (220).

12. The aircraft (10) according to claim 10, comprising: a fifth side panel (205) adjacent an outer surface (62A) of the first side skin (60A) and secured to the first side skin (60A) and the base rib assembly (100), the fifth side panel (205) having at least one longitudinal lug (210) aligned with one of the rear longitudinal lugs (140) of the base rib assembly (100); and A sixth side panel, the sixth side panel being adjacent to the outer surface (62B) of the second side skin (60B) and being fixed to the second side skin (60B) and the base rib assembly (100), the sixth side panel having at least one longitudinal lug aligned with another of the rear longitudinal lugs (140) of the base rib assembly (100).

13. The aircraft (10) of claim 12, wherein: The at least one longitudinal lug (210) of the fifth side panel (205) is positioned between the first mounting arm (250) and the second mounting arm (255) of a first rear U-shaped clip (245) of the pair of rear U-shaped clips (245), and a corresponding rear longitudinal lug (140) of the base rib assembly (100) is positioned between the second mounting arm (255) and the third mounting arm (260) of the first rear U-shaped clip (245); and The at least one longitudinal lug of the sixth side panel is positioned between the first mounting arm (250) and the second mounting arm (255) of the second rear U-shaped clip (245) of the pair of rear U-shaped clips (245), and the corresponding rear longitudinal lug (140) of the base rib assembly (100) is positioned between the second mounting arm (255) and the third mounting arm (260) of the second rear U-shaped clip (245).

14. A method of attaching a vertical tail (35) having a multiple spar box (40) to an aircraft fuselage (15), the method comprising the steps of: Assembling a base rib assembly (100), the base rib assembly having an opposing pair of front longitudinal lugs (130), an opposing pair of rear longitudinal lugs (140), at least one opposing pair of intermediate longitudinal lugs (150) disposed between the front longitudinal lugs (130) and the rear longitudinal lugs (140), and a plurality of transverse lugs (135, 145), each longitudinal lug and each transverse lug having a corresponding mounting hole (132, 142, 152, 137, 147); Inserting the base rib assembly (100) into the interior (65) of the multi-spar box (40) of the vertical tail (35), the interior (65) of the multi-spar box (40) being defined by a front spar (45), a rear spar (50) and opposing side skins (60A, 60B); Positioning a front plate (165) adjacent to an outer surface (47) of the front spar (45) and securing the front plate (165) to the front spar (45) and the base rib assembly (100), the front plate (165) having at least one lateral lug (170) corresponding to one of the plurality of lateral lugs (135) of the base rib assembly (100), the at least one lateral lug (170) of the front plate (165) having a mounting hole aligned with the mounting hole (137) in the corresponding lateral lug (135) of the base rib assembly (100); Positioning a rear panel (175) adjacent to an outer surface (52) of the rear spar (50) opposite the front panel (165), and securing the rear panel (175) to the rear spar (50) and the base rib assembly (100), the rear panel (175) having at least one transverse lug (180) corresponding to one of the plurality of transverse lugs (145) of the base rib assembly (100), the at least one transverse lug (180) of the rear panel (175) having a mounting hole aligned with the mounting hole (147) in the corresponding transverse lug (145) of the base rib assembly (100); Positioning a first side panel (185) adjacent to an outer surface (62A) of a first side skin (60A) of the multi-spar box (40), and securing the first side panel (185) to the first side skin (60A) and the base rib assembly (100), the first side panel (185) having at least one longitudinal lug (190) corresponding to one of the intermediate longitudinal lugs (150) of the base rib assembly (100), each of the at least one longitudinal lug (190) of the first side panel (185) having a mounting hole (192) aligned with a mounting hole (152) in a corresponding intermediate longitudinal lug (150) of the base rib assembly (100); Positioning a second side panel adjacent to an outer surface (62B) of a second side skin (60B) of the multi-spar box (40), and securing the second side panel to the second side skin (60B) and the base rib assembly (100), the second side panel having at least one longitudinal lug corresponding to one of the intermediate longitudinal lugs (155) of the base rib assembly (100), each of the at least one longitudinal lug of the second side panel having a mounting hole aligned with a mounting hole (157) in a corresponding intermediate longitudinal lug (155) of the base rib assembly (100); Inserting a plurality of U-shaped clips (220, 245, 270) through corresponding holes (30) in a skin (25) of the aircraft fuselage (15), and securing each of the plurality of U-shaped clips (220, 245, 270) to a frame member (20) of the aircraft fuselage (15), wherein the U-shaped clips (220, 245) corresponding to the front longitudinal lug (130) and the rear longitudinal lug (140) each have a first mounting arm (225, 250), a second mounting arm (230, 255) and a third mounting arm (235, 260), each mounting arm (225, 230, 235, 250, 255, 260) having a mounting hole (242, 267), and the U-shaped clips (270) corresponding to the intermediate longitudinal lugs (150, 155) respectively have a first mounting arm (275) and a second mounting arm (280), each mounting arm (275, 280) having a mounting hole (282); Positioning the vertical tail (35) adjacent the aircraft fuselage (15) and aligning each longitudinal lug (130, 140, 150, 155) with a corresponding clevis (220, 245, 270); as well as A retaining member (70) is inserted through the mounting hole (132, 142, 152, 157) and U-shaped clip (220, 245, 270) of each corresponding longitudinal lug (130, 140, 150, 155) to secure the vertical tail (35) to the aircraft fuselage (15).

15. The method of claim 14, comprising attaching each transverse lug (135, 145) to a first end of a corresponding transverse link (285A, 290A), and attaching a second end of each transverse link (285A, 290A) to a transverse clevis.

16. The method according to claim 15, wherein: Each transverse clevis is part of a corresponding clevis (220, 245).

17. The method according to claim 15, wherein: Each transverse clevis (435, 460) is positioned between two clevises (220, 245), extends through a corresponding hole (30) in the skin (25) of the aircraft fuselage (15), and is secured to a frame member (20) of the aircraft fuselage (15).

18. The method according to claim 14, wherein: Assembling the base rib assembly (100) includes: attaching at least one first side chord (120) to the base rib (105), the at least one first side chord (120) comprising at least one of the intermediate longitudinal lugs (150); attaching at least one second side chord (125) to the base rib (105) opposite the at least one first side chord (120), the at least one second side chord (125) including at least one of the intermediate longitudinal lugs (155); attaching a front fitting (110) to the base rib (105), the front fitting (110) comprising at least one of the front longitudinal lugs (130) and at least one of the plurality of transverse lugs (135); and A rear end fitting (115) is attached to the base rib (105) opposite the front end fitting (110), the rear end fitting (115) including at least one of the rear longitudinal lugs (140) and at least one of the plurality of transverse lugs (145).

19. The method of claim 14, further comprising attaching at least one generally L-shaped shear clip (160) between the base rib assembly (100) and an intermediate spar (55) of the multi-spar box (40).

20. The method according to claim 14, wherein: The plurality of transverse lugs (135, 145) are positioned at a front portion of the base rib assembly (100) and a rear portion of the base rib assembly (100), and no transverse lugs are located between the front portion and the rear portion of the base rib assembly (100).

Images