Tool for positioning a sealing member on a wing rib of an aircraft

Abstract

A sealing member device including at least one sealing plate is arranged on a stringer receiving recess in a wing rib of an aircraft. The application relates to a tool for positioning a sealing member device on a stringer receiving recess in a wing rib of an aircraft assembly. The tool system has a retaining member configured to retain the sealing member device on the recess. A biasing device is configured to act on the retaining member to bias the sealing member device to be in an aligned position relative to the stringer received in the recess. A fixing device is configured to act on the sealing member device to fix the sealing member device in the aligned position. The application also relates to a sealing kit, an aircraft assembly, a method for fixing a sealing member device on a stringer receiving recess in a wing rib of an aircraft, and an aircraft.

Description

Technical Field

[0001] The invention relates to a tool for positioning a sealing member device on a stringer receiving recess in a wing rib of an aircraft assembly, a sealing kit, an aircraft assembly, a method for fixing a sealing member device on a stringer receiving recess in a wing rib of an aircraft, and an aircraft. Background Art

[0002] Aircraft wings are usually formed with a wing assembly comprising a pair of spars extending in a spanwise direction, i.e., from a root of the wing at the aircraft fuselage to a wing tip distal from the root. A plurality of ribs extend in a chordwise direction, i.e., from a leading edge to a trailing edge of the wing. The ribs extend between the spars. A skin comprising a lower cover and an upper cover extends on the underside and the upper side of the spars and ribs.

[0003] The fuel in an aircraft is usually stored in one or more fuel tanks or sealed compartments located in the interior space of the wings and fuselage of the aircraft. The fuel tanks or sealed compartments are usually defined by structural components of the aircraft assembly. The boundaries of such fuel tanks or sealed compartments can be at least partially defined by a wing spar extending in the span direction, a pair of sealed wing ribs, and a lower cover and an upper cover.

[0004] A plurality of stringers are provided on the inner surface of the skin and are used to reinforce the skin. The stringers extend in the span direction. Therefore, the stringers extend through the plurality of ribs. Cutouts serving as notches are formed at the edges of the sealing ribs, and the stringers extend through these cutouts. The cutouts are provided to have a size larger than the size of the stringers to be received, in order to address tolerance accumulation during the manufacture and assembly of the components.

[0005] Sealing plates are provided to seal the cutouts formed in the ribs. Each sealing plate is typically secured to the rib and extends over the cutout to be positioned adjacent to a stringer extending through the cutout. A sealant bead provides a liquid-tight joint between the sealing plate and the stringer to restrict fuel flow through the cutout. Each cutout is sealed by a pair of sealing plates, one sealing plate on each side of the stringer. The pair of sealing plates overlap each other at the upper end of the cutout.

[0006] After the cover and ribs are assembled, the sealing plate is manually installed from inside the fuel tank. The sealing plate is required to cover and seal the cutout. With this method, the sealing plate of the appropriate size can be selected and installed on the cutout.

[0007] However, installing the sealing plate in the assembled fuel tank is difficult and time consuming due to the limited space available. The gap formed by the cutout also needs to be measured and a suitable sealing plate needs to be selected and installed. Summary of the invention

[0008] According to one aspect of the present invention, a tool for positioning a sealing member device on a stringer receiving recess in a wing rib of an aircraft assembly is provided, the tool comprising: a retaining member configured to retain the sealing member device on the recess; a biasing device configured to act on the retaining member to bias the sealing member device to be in an aligned position relative to the stringer received in the recess; and a fixing device configured to act on the sealing member device to fix the sealing member device in the aligned position.

[0009] With this arrangement, the tool can self-align the sealing member arrangement with the stringer. Assembly of the aircraft component can thus be simplified, thereby reducing assembly time.

[0010] The tool may include a mount configured to mount the sealing member arrangement to the rib.

[0011] The retainer may be configured to align an abutment edge of the sealing member arrangement with an abutment surface of a beam received in the recess in the aligned position.

[0012] The retainer may comprise an alignment edge configured to abut against the beam to align the sealing member arrangement in the alignment position. Alignment of the sealing member arrangement is thereby simplified. The sealing of the sealing member arrangement on the recess may be improved.

[0013] The retainer may be configured to retain the sealing member such that an abutting edge of the sealing member is configured to abut against the beam to position at least a portion of the sealing member arrangement in the aligned position.

[0014] The sealing member arrangement may include a sealing plate, and the retaining member may be configured to receive the sealing plate.

[0015] The biasing means may be configured to bias the sealing plate in a direction along the plane of the sealing plate.

[0016] The retainer may be configured to retain the sealing plate parallel to the face of the rib where the notch is formed.

[0017] The holding piece may include a holding element for holding the sealing plate on the holding piece, thereby simplifying the holding of the sealing plate by the tool.

[0018] The retaining element may include a cavity configured to at least partially receive the sealing plate.

[0019] The retaining element may comprise a suction pad.

[0020] The sealing plate may be a first sealing plate, and the retainer may include a first retainer portion configured to retain the first sealing plate. The tool may include a second retainer portion configured to retain the second sealing plate, wherein the biasing device is configured to bias the first retainer portion and the second retainer portion in different directions.

[0021] The biasing means may be configured to bias the first retainer portion and the second retainer portion in opposite directions.

[0022] The first retainer portion and the second retainer portion may be movable between a neutral position, in which a spacing between the first sealing plate retained by the first retainer portion and the second sealing plate retained by the second retainer portion is less than a thickness of a web of the stringer configured to be received between the retainers, and an alignment position, in which a spacing between the first sealing plate retained by the first retainer portion and the second sealing plate retained by the second retainer portion corresponds to a thickness of the web of the stringer.

[0023] The tool may further include a third retainer portion configured to retain a third seal plate, wherein the biasing device is configured to bias the third retainer portion in a different direction than the first retainer portion and the second retainer portion.

[0024] The biasing means may be configured to allow the sealing member to pivot.

[0025] The tool may further comprise position marking means for marking the alignment of the sealing member means relative to the rib.

[0026] The position marking means may comprise template means on the holder for template-ing the sealing member means and / or at least one sealing member means fastening hole in the rib.

[0027] The template arrangement may comprise at least one template aperture extending through the retaining member.

[0028] The biasing means may be configured to act on the retaining member to bias the sealing member means.

[0029] The biasing means may comprise at least one resilient member.

[0030] The securing means may be configured to urge the sealing member means against the rib when the sealing member means is located on the recess.

[0031] The securing means may be configured to act on the sealing member means in a direction perpendicular to that in which the biasing means acts.

[0032] The retainer may be configured to expose the rib locating side of the sealing member arrangement when the sealing member arrangement is received by the retainer.

[0033] The retainer may be configured to retain the sealing member arrangement against the rib when the sealing member arrangement is located on the recess.

[0034] The securing device may include an actuator configured to be moved in a selectable manner between a secured state and a movable state.

[0035] The actuator may be configured to be wirelessly operable.

[0036] The mounting may include a rib reinforcement assembly tool.

[0037] The retainer may include a cam surface configured to act upon a reinforcement member inserted into the recess.

[0038] According to an aspect of the present invention, there is provided a sealing kit for sealing a stringer receiving recess in a rib of an aircraft assembly, the sealing kit comprising a tool as set out above and at least one sealing member.

[0039] The sealing kit may include a curable sealant.

[0040] According to one aspect of the present invention, an aircraft component is provided, which includes: a rib having at least two rib bases and a recess located between the rib bases, the rib base being configured to couple a bottom edge of the rib to another component; a stringer received in and extending through the recess; a first sealing plate extending at least partially over the recess from a first edge of the recess; a second sealing plate extending at least partially over the recess from a second edge of the recess; and a third sealing plate extending at least partially over the recess from a third edge of the recess.

[0041] The first sealing plate, the second sealing plate, and the third sealing plate may not overlap.

[0042] According to one aspect of the present invention, a method for fixing a sealing member device to a stringer receiving recess in a wing rib of an aircraft is provided, the method comprising: positioning a tool for holding the sealing member device at least partially on the recess; biasing the sealing member device to be in an aligned position relative to a stringer received in the recess; fixing the sealing member device in the aligned position; removing the stringer from the recess; and securing the sealing member device to the wing rib in the aligned position.

[0043] The method may include marking the position of the sealing member arrangement on the rib in the aligned position and removing the tool prior to securing the sealing member arrangement in the aligned position.

[0044] The method may comprise forming fastening holes through the rib and / or the sealing member means using a template arrangement of the tool to mark the position of the sealing member means on the rib in an aligned position.

[0045] The method may include urging the sealing member arrangement against the rib to secure the sealing member arrangement in the aligned position.

[0046] The method may comprise inserting the stringer into the recess after positioning the tool so that the sealing member arrangement is urged outwardly.

[0047] The method may comprise reinserting the stringer into the recess after securing the sealing member arrangement to the rib.

[0048] The method may comprise applying a sealant to the sealing member arrangement prior to reinserting the stringer into the recess.

[0049] According to an aspect of the invention, there is provided an aircraft component formed by the method as set out above. BRIEF DESCRIPTION OF THE DRAWINGS

[0050] Embodiments of the present invention will now be described with reference to the accompanying drawings, in which:

[0051] Figure 1 It is a plan view of the aircraft;

[0052] Figure 2 yes Figure 1 A schematic cut-away side view of a portion of a wing box assembly of a wing of an aircraft shown at the junction of a rib, a stringer and a lower cover;

[0053] Figure 3 is configured to position the sealing plate device in a position formed in Figure 2 A schematic rear view of a tool on a stringer receiving recess in an aircraft wing rib is shown;

[0054] Figure 4 yes Figure 3 a schematic cut-away elevational view of the tool shown, illustrating a sealing plate of the sealing plate arrangement held by a holder of the tool;

[0055] Figure 5 is a schematic diagram of the wing rib, where Figure 3 and Figure 4 The tool is shown mounted on a rib and positioned over a stringer receiving recess with the retainer in a neutral position;

[0056] Figure 6 yes Figure 5 A schematic diagram of a rib and tooling shown with a stringer partially received in a recess, wherein a retainer has a sealing plate adapted to receive the stringer;

[0057] Figure 7 yes Figure 6 A schematic diagram of the rib and tool shown with the stringer in an assembled position in the recess and with the retainer in an adapted position with the stringer;

[0058] Figure 8 yes Figure 7A schematic diagram of the rib and the tool shown, and a fixture for securing the retainer in an adapted state, wherein the stringer is in an assembled position in the recess, wherein the retainer is in an adapted position to receive the stringer;

[0059] Fig. 9 yes Figure 8 A schematic diagram of the rib and tool shown with the retainer secured in the adapted position and the stringer in a partially removed position;

[0060] Fig.10 yes Fig. 9 a schematic diagram of the rib and tool shown, and showing the template means for forming corresponding fastening holes in the sealing plate and the rib, with the retaining members fixed in the adapted position, and the stringers removed;

[0061] Fig.11 yes Fig.10 a schematic diagram of a rib shown with the tool removed and fastening holes formed in the rib;

[0062] Fig.12 yes Fig.11 A schematic diagram of a rib is shown with a sealing plate secured to the rib in a fastened position corresponding to an adapted state;

[0063] Fig.13 It is assembled Fig.12 A schematic diagram of the rib and containment plate shown with the stringers partially received in the recesses;

[0064] Fig.14 It is assembled Fig.13 A schematic diagram of the rib and containment plate shown with the stringers in the assembled position;

[0065] Fig.15 is a schematic perspective view of a stringer with a stringer cover; and

[0066] Fig.16 yes Figure 8 A schematic diagram of a portion of a fixture is shown. DETAILED DESCRIPTION

[0067] Figure 1 An aircraft 10 is shown in FIG. The aircraft 10 includes a fuselage 11. Two wings 12 extend from the fuselage 11. It will be appreciated that the fuselage 11 and the wings 12 may take on a variety of different shapes and profiles. Each wing 12 has a wing root 14 at the junction with the fuselage 11. The wing 12 has a wing tip 15 at a distal end relative to the wing root 14. The wing 12 has a leading edge 16 and a trailing edge 17. The wing 12 includes a wing box 18. The wing box 18 is an aircraft component.

[0068] Herein, one of the wings 12 will be described. The wing 12 has a span axis extending in a direction from a wing root 14 to a wing tip 15. The wing 12 has a chord axis extending in a direction from a leading edge 16 to a trailing edge 17.

[0069] Figure 2 1 shows a portion of the wing box 18. The wing 12 includes a pair of spars (not shown) extending in the span direction. A plurality of ribs 20 extend in the chord direction. The ribs 20 are generally planar and are positioned at intervals along the span of the wing 12. The ribs 20 extend between the spars (not shown). Figure 2 FIG. 1 shows a portion of a rib 20. The wing 12 has a skin 21 including an upper cover 21a and a lower cover 21b. The upper cover 21a is Figure 1 As shown in FIG. 1 , the lower cover 21b is Figure 2 The wing box 18 defines a plurality of sealed compartments or fuel tanks 22 separated from one another by wing ribs 20 .

[0070] Each sealed compartment 22 has upper and lower walls provided by an upper cover 21a and a lower cover 21b, a front wall and a rear wall provided by a spar (not shown), and an inner and outer sidewalls provided by a pair of sealed ribs 20. The inner and outer sidewalls may be defined by adjacent ribs 20. In one embodiment, an intermediate unsealed rib is provided in the fuel compartment 22. The pair of sealed ribs 20 provide a boundary between the sealed compartments 22. The sealed ribs 20 are sealed around the periphery of the sealed ribs 20 to prevent fuel from flowing from the sealed compartment 22 through the plane of the sealed rib 20 in addition to preventing fuel from flowing from the sealed compartment 22 through a predetermined conduit.

[0071] Figure 2 The face 23 of the rib 20 is shown where it joins the lower cover 21b. The lower cover 21b carries a plurality of stringers 24 extending along the wing 12 in a spanwise direction. Figure 2 One of these stringers 24 is shown in FIG. 1 and has a T-shaped cross section and has a lower flange or stringer base 25 attached to the inner surface 26 of the lower cover 21b and a blade or stringer web 27 extending away from the lower cover 21b. The stringer web 27 stands upright from the stringer base 25. The stringer web 27 has a free end 27a at the distal end relative to the stringer base 25.

[0072] The plurality of stringers 24 extend along the skin 21 in the span direction and serve to reinforce the skin 21. The stringers 24 are fastened to the skin 21.

[0073] The ribs 20 are attached to the skin 21 by a series of rib bases 28 . Figure 22. Two rib bases 28 are shown in FIG. 2. In this case, the rib base 28 is attached to the stringer base 25 of the stringer 24. The rib 20 has a rib web 29. The rib web 29 defines the face 23. The rib web 29 comprises a generally planar plate. The rib base 28 comprises a flange section extending perpendicular to the plane of the rib web 29. A mounting hole (not shown) is formed through the rib base 28.

[0074] The stringer 24 passes through a cutout 30 between adjacent rib bases 28. The cutout 30 is formed in the bottom edge of the rib 20. The cutout 30 serves as a notch. The cutout 30 has a first side edge 31, an opposite second side edge 32, and an upper edge 33. The upper edge 33 is arc-shaped.

[0075] The stringer web 27 has opposite side surfaces 35 .

[0076] A gap 36 is formed between the stringer 24 and the edges 31, 32, 33 of the cutout 30. The gap 36 extends around the periphery of the portion of the stringer web 27 received in the cutout 30. Fig.14 As shown, the gap between the stringer 24 and the rib 20 is covered by a sealing member device 40. The sealing member device 40 includes a first sealing plate 41, a second sealing plate 42 and a third sealing plate 43 fastened to the rib 20 by fasteners 44. The sealing plates 41, 42, 43 serve as sealing members. Therefore, the sealing member can have different configurations.

[0077] The sealing member arrangement 40 prevents fuel from flowing through the gap 36 past the rib 20. A sealant (not shown) is provided around the sealing member arrangement 40. Thus, the edges of the sealing plates 41, 42, 43 are fluid-sealed by a sealant bead extending around the entire periphery of each of the sealing plates 41, 42, 43.

[0078] In the present device, the sealing member device 40 includes three sealing plates: a first sealing plate 41 arranged on the first side of the reinforcement web 27, a second sealing plate 42 arranged on the opposite other side of the reinforcement web 27, and a third sealing plate 43 arranged on the top end of the reinforcement web. The number of sealing plates of the sealing member device 40 may be different from this. The sealing member device 40 may include one sealing plate. Alternatively, the sealing member device 40 may include two sealing plates. In such an embodiment, the sealing plates may be arranged on both sides of the reinforcement web 27, and the sealing plates may include a protruding portion partially extending on the free end 27a. The advantage of using three sealing plates is that, regardless of the tolerance accumulation on both sides and the upper end of the reinforcement web 27, a close fit with the reinforcement web can be achieved, so that the remaining gap to be sealed by the sealant can be minimized.

[0079] Each sealing plate 41, 42, 43 includes a rib positioning surface 45 (refer to Figure 4 ) and a retaining surface 46. The edge of each sealing plate 41, 42, 43 forms an abutment edge 47. The abutment edge 47 is configured to be positioned adjacent to the stringer 24. The length of the abutment edge 47 of each of the first sealing plate 41 and the second sealing plate 42 generally corresponds to the length of the stiffener web 27. The sealing plates 41, 42, 43 are formed of a rigid material, such as aluminum. Each of the first sealing plate 41 and the second sealing plate 42 has an end protrusion 48. The end protrusion 48 defines a portion of the abutment edge 47. Each edge plate 41, 42, 43 is planar.

[0080] The tool or tool system 50 for positioning the sealing plates 41, 42, 43 is Figure 3 and Figure 4 It is shown in Figure 3 The tool 50 is shown from the rear side, ie the push side 51, and Figure 4 The tool 50 is shown from the front side, i.e. the rib positioning side 52. The tool 50 has a body 53. The body 53 may have a rear wall, for clarity, Figure 4 The rear wall is omitted. The body 53 forms a tool housing.

[0081] The body 53 has a mounting member 54. The mounting member 54 is configured to removably mount the tool 50 to the rib 20. The mounting member 54 includes a mounting portion 55 for releasably mounting the tool 50 relative to the rib 20. The plurality of mounting portions 55 stably hold the tool 50 on the rib 20. The mounting member 54 holds the tool 50 on the face 23 of the rib 20, wherein the tool 50 is positioned on the cutout or notch 30. Thus, the tool 50 can be correctly positioned. In one embodiment, the mounting member 54 includes a rib reinforcement assembly tool (not shown). The rib reinforcement assembly tool includes a removable reinforcement member. The rib reinforcement assembly tool is mounted to the rib to reinforce the rib during assembly of the wing box 18.

[0082] The tool 50 has a retainer 60. The retainer 60 is configured to retain the sealing plates 41, 42, 43. When the tool 50 is mounted on the cutout 30, the retainer 60 is configured to retain each of the sealing plates 41, 42, 43 at least partially on the cutout 30. The tool has a biasing device 70. The biasing device 70 acts on the retainer 60 to bias the retainer 60. The biasing device 70 urges each of the sealing plates 41, 42, 43 toward each other. As described below, the biasing device 70 biases the sealing plates 41, 42, 43 to an aligned position when the stringers 24 are received in the cutout 30.

[0083] The tool 50 has a fixing device 80. The fixing device 80 selectively acts on the retaining member 60 to hold the retaining member 60 and thus fix the sealing plates 41, 42, 43 in place.

[0084] The holder 60 includes a first holder portion 61, a second holder portion 62, and a third holder portion 63. Each of the holder portions 61, 62, 63 is configured to hold one of the sealing plates 41, 42, 43. The holder portions 61, 62, 63 are movable elements in the housing 51.

[0085] The first retainer portion 61 is configured to retain the first sealing plate 41 . The second retainer portion 62 is configured to retain the second sealing plate 42 . The third retainer portion 63 is configured to retain the third sealing plate 43 .

[0086] Each retainer portion 61, 62, 63 includes a plate member 65. The retainer portions 61, 62, 63 will be described primarily with reference to the first retainer portion 61, but the description applies to each retainer portion. The plate member 65 includes a sealing plate retaining surface 66. The sealing plate retaining surface 66 is formed by a cavity 67 in the plate member 65. The cavity 67 corresponds to the shape of the corresponding sealing plate 41, 42, 43 and is used to align the sealing plate 41, 42, 43 in the tool 50. Alignment of the sealing plates 41, 42, 43 in the tool 50 can be achieved by alternative means, such as by upstanding protrusions.

[0087] Each retainer portion 61, 62, 63 has a retaining element (not shown) serving as a retaining means for retaining the respective sealing plate 41, 42, 43. The cavity 67 may be configured to receive the respective sealing plate 41, 42, 43 in a push-fit manner. A releasable adhesive pad or suction pad (not shown) may form the retaining element. When the sealing plate 41, 42, 43 is received by the respective retainer portion 61, 62, 63, the rib locating surface 45 is present at the front side 52 of the tool 50. The rib locating surface 45 is exposed, as shown in FIG. Figure 4 shown.

[0088] Each retainer portion 61, 62, 63 includes an alignment edge 68. The alignment edge 68 is configured to align with the stringer web 27. The alignment edge 68 is linear to align with the side surface 35 or the free end 27a of the stringer web 27, but the shape may be different. In the present embodiment, each retainer portion 61, 62, 63 is configured so that the alignment edge 68 is aligned with the abutment edge 47 of the received sealing plate. However, in the embodiment, the retainer portions 61, 62, 63 are configured so that the abutment edge 47 of the received sealing plate 41, 42, 43 protrudes from the alignment edge 68 of the retainer portions 61, 62, 63. Therefore, the abutment of the sealing plates 41, 42, 43 with the stringer web 27 is ensured. Alternatively, in an embodiment, the retainer portions 61, 62, 63 are configured so that the abutment edge 47 of the received sealing plate 41, 42, 43 is slightly away from the alignment edge 68 of the retainer portions 61, 62, 63. Therefore, it can be ensured that a consistent sealant bead can be received between the sealing plate 41, 42, 43 and the beam 24 during assembly.

[0089] Each of the first retainer portion 61 and the second retainer portion 62 has a positioning protrusion 69. The positioning protrusion 69 is configured to extend from the lower end of the corresponding retainer portion 61, 62. The positioning protrusion 69 receives the end protrusion 48 of the first sealing plate 41 and the end protrusion 48 of the second sealing plate 42. The positioning protrusion 69 defines a portion of the corresponding alignment edge 68. The positioning protrusion 69 serves as a guide having a cam surface, and the free end 27a of the stringer web 27 acts on this cam surface.

[0090] The biasing device 70 includes an elastic member 74. The elastic member 74 is configured to act on the retaining member 40. That is, the elastic member 74 is configured to act on the first retaining member part 61, the second retaining member part 62 and the third retaining member part 63. The biasing device 70 includes a first biasing mechanism 71 configured to act on the first retaining member part 61, a second biasing mechanism 72 configured to act on the second retaining member part 62, and a third biasing mechanism 73 configured to act on the third retaining member part 63. In the present embodiment, the elastic member 74 is a compression spring, but alternative biasing devices can be envisioned. In the embodiment described herein, each biasing mechanism includes two elastic members, but the number of elastic members can vary. The biasing mechanism of each corresponding retaining member part allows the retaining member part to pivot around the plane of the retaining member part.

[0091] The biasing device 70 is configured to hold the first retainer portion 61 and the second retainer portion 62 in a spaced arrangement in a neutral position, i.e., a position when the stringer 24 is not received between the first retainer portion 61 and the second retainer portion 62. A space 75 is thus provided between the first retainer portion 61 and the second retainer portion 62. The width of the space 75 in the neutral position is less than the thickness of the stringer web 27 to be received in the space. The biasing device 70 is configured to act inwardly in the tool 50. When the stringer web 24 is received by the tool 50, the biasing device 70 is configured to push the retainer portions 61, 62, 63 against the stringer web 24.

[0092] The fixing device 80 includes actuators 81, 82, 83, which can be selectively actuated to fix the position of the retainer 60. The fixing device 80 is Figure 3 . The actuators 81, 82, 83 are each configured to act on a corresponding one of the first retainer portion 61, the second retainer portion 62 and the third retainer portion 63. Each actuator 81 is configured to fix the position of the corresponding retainer portion in the tool relative to each other retainer portion 61, 62, 63. Each actuator 81, 82, 83 is operable to act on the rear side of the corresponding retainer portion 61, 62, 63. The actuators 81, 82, 83 are configured to push the retainer portion 61, 62, 63 toward the rib 20 and thus push the retainer portion 61, 62, 63 against the rib 20. Each actuator 81, 82, 83 is electrically actuated. The actuator is configured to selectively move between a retracted state and a pushed state.

[0093] Reference Fig.16 , the fixture 80 includes a controller 85 and a communication module 86. The controller 85 can be operated by a user through a user input module 87. The controller 86 includes a processor and a memory unit. The fixture 80 is configured to be remotely operated from the tool 50. The actuators 81, 82, 83 are configured to be wirelessly operable. The communication module 86 is a wireless communication device. Therefore, when the lower cover 21b is received on the rib 20, the tool 50 is remotely operable, so there is no need to access the fuel tank 22 to operate the tool.

[0094] The tool 50 also includes template means 90. The template means 90 forms part of a position marking means for marking the position of the sealing plates 41, 42, 43 on the rib 20 as the tool 50 holds the sealing plates 41, 42, 43 in an aligned position, as will become clear below.

[0095] The template device 90 includes a plurality of template holes 91 located in the holder 60. Each holder portion 61, 62, 63 has two template holes 91 formed through the plate body 65. The template holes 91 are connected to the fastening holes 92 formed in each sealing plate 41, 42, 43 (see Fig.10 During assembly, the template holes 91 can be used to form corresponding fastening holes 92 and attachment holes 93 in the sealing plates 41, 42, 43 and the rib web 27 for receiving the fasteners 44 (see Fig.11 ).

[0096] Now refer to Figures 5 to 14 A method of assembling an aircraft assembly is described. The method of assembling an aircraft assembly also includes a method of securing a sealing member apparatus to a stringer receiving recess in a wing rib of the aircraft.

[0097] like Figure 5 As shown, the sealing plates 41, 42, 43 are loaded in a tool 50. Each retainer portion 61, 62, 63 receives and retains a corresponding sealing plate 41, 42, 43. The tool 50 holding the sealing member device 40 is positioned over the cutout or recess 30 in the rib 20. The tool 50 is removably mounted to the rib 20 using a mounting member 54. Thus, the sealing plates 41, 42, 43 are arranged to extend over the recess 30. The first sealing plate 41 overlaps the first side edge 31, the second sealing plate 42 overlaps the opposite second side edge 32, and the third sealing plate 43 overlaps the upper edge 33.

[0098] The retainer 60 is disposed in its neutral position wherein the biasing means 70 holds the first retainer portion 61 and the second retainer portion 62 in a spaced relationship. The space 75 extends over the recess 30. The third retainer portion 63 abuts the first retainer portion 61 and the second retainer portion 62 but does not overlap.

[0099] like Figure 6As shown, the lower cover 21 with the attached stringer 24 is brought toward the rib 20. The stringer 24 is aligned with the corresponding notch 30 in the rib 20. The free end 27a of the stringer web 27 is received in the notch 30. As the stringer web 27 moves into the notch 30, the free end 27a of the stringer web 27 contacts the tool 50. The free end 27a abuts the first retainer portion 61 and the second retainer portion 62. Depending on the alignment of the stringer 24 with the notch 30, the free end 27a may contact one retainer portion and then the other retainer portion. The first retainer portion 61 and the second retainer portion 62 are pushed to expand outward. The biasing device 70 biases the first and second retainer portions 61, 62 and the retained sealing plates 41, 42 toward and against the side surface 35 of the stringer web 27. The positioning protrusion 69 serves as a guide to guide the positioning of the stringer 27 and the retainer portions 61, 62. The positioning protrusion 69 also serves as a cam surface to pivot the lower end portions of the first and second retainer portions 61, 62 outward. Therefore, when the rib 20 and the lower cover 21b are guided together, the free end portion 27a of the stringer web 27 is received by the retainer 60.

[0100] like Figure 7 As shown, the rib 20 and the lower cover 21b are moved to the assembly position. In this assembly position, the first retainer portion 61 and the second retainer portion 62 and therefore the first sealing plate 41 and the second sealing plate 42 are biased to be in an aligned position relative to the stringer web 27. The third retainer portion 63 is in contact with the free end 27a of the stringer web 27 in the assembly position and is biased to abut against the free end 27a. Therefore, the alignment edge 68 aligns the retainer portions 61, 62, 63 with the stringer web 27, so that the abutment edge 47 of each of the first sealing plates 41, 42, 43 is aligned and abuts with the stringer web 27 in the alignment position. In such a position, the gap 36 between the rib 20 and the stringer is covered by the sealing plates 41, 42, 43.

[0101] like Figure 8 As shown, the fixing device 80 is operated. The actuators 81, 82, 83 are wirelessly actuated to fix the sealing plates 41, 42, 43 in the aligned position. The actuators 81, 82, 83 act on the retainer 60 to push the retainer parts 61, 62, 63 against the rib web 29. As a result, the sealing plates 41, 42, 43 are clamped between the tool 50 and the rib 20.

[0102] With the above configuration, the sealing plate can be positioned and secured in place without having to access the fuel tank 22 .

[0103] like Fig. 9 As shown, the lower cover 21b is removed from the rib 20. The actuators 81, 82, 83 hold the retainer 60 in an aligned position corresponding to the shape of the stringer web 27. The actuators 81, 82, 83 act against the biasing device 70 to prevent the biasing device 70 from moving the retainer 60. The stringer web 27 is extracted from the space 75 between the retainer parts 61, 62, 63.

[0104] Fig.10 2 and the tool 50 are shown with the lower cover 21b and the stringer 24 removed. With the lower cover removed, the tool 50 is accessible. The retainer 60 and therefore the sealing plates 41, 42, 43 are held in an aligned position with the spacing 75 corresponding exactly to the shape and size of the stringer web 27. The template holes 91 of the template device 90 are accurately arranged for forming the corresponding fastening holes 92 and attachment holes 93 in both the sealing plates 41, 42, 43 and the rib web 29. Thus, the fastening holes 92 and the attachment holes 93 can be easily and accurately formed. The template device 90 is used to mark the position of the sealing member device on the rib 20 in the aligned position. Thus, the template guide holes can be formed to mark the necessary positions.

[0105] The tool 50 can then be removed. Fig.11 , the rib 20 is shown with attachment holes 93 formed in the face 23 at the exact location for aligning the sealing plates 41 , 42 , 43 over the edges 31 , 32 , 33 of the recess 30 to cover the gap 36 .

[0106] The sealing plates 41, 42, 43 with the formed fastening holes are removed from the tool 50. Fig.12 In the embodiment of the present invention, the sealing plates 41, 42, 43 are fastened to the rib 20 by fasteners 44. The sealing plates can be correctly and accurately aligned and installed to the rib 20 without the need for the cover 21 to be in the assembled position. Therefore, the ease of access is maximized. When attaching the sealing plates 41, 42, 43, a curable sealant (not shown) is applied to the peripheral edge of each of the sealing plates 41, 42, 43. A channel (not shown) can extend along the abutting edge 47 or the side surface 35 of the stringer web 27 to receive the sealant. The fasteners 44 can be easily tightened to the correct torque due to easy access.

[0107] Once assembled, the sealing plates 41, 42, 43 are in their aligned positions. Fig.13As shown, the lower cover 21b can be returned toward the assembled position with the rib 20. Since the correct positioning of each of the sealing plates 41, 42, 43 relative to the stiffener 24 has been determined, the sealing plates 41, 42, 43 are correctly positioned against the stiffener web 27 to cover the gap 36. The sealant (not shown) applied to the sealing plates 41, 42, 43 and / or the stiffener web 27 before reassembling the lower cover 21b and the rib 20 will fill any remaining gaps between the sealing plates 41, 42, 43 and other components.

[0108] exist Fig.14 , the lower cover 21b and the rib 20 are shown fully assembled. The lower cover 21b is fastened to the rib 20. The gap 36 between the reinforcement 27 and the rib 20 is fluid sealed (but the sealant is omitted for clarity).

[0109] Fig.15 An embodiment is shown in which a cover plate 100 is applied to the stringer web 27 of the stringer 24 in the region of the stringer 24 to be received in the cutout 30. The cover plate 100 is a material strip extending over the free end 27a of the stringer web 27. The thickness of the cover plate 100 is Fig.15 30 is enlarged to emphasize the arrangement. The cover plate 100 is U-shaped. The cover plate 100 can be formed of a deformable material. With the cover plate 100, it is possible to assist in protecting the stringer web 27 when the stringer web 27 is inserted into the cutout 30. The cover plate 100 can be used with the tool 50 described above, or can be used without the tool 50.

[0110] Although the aircraft assembly, ribs, covers and stringers are described herein with reference to the wing box 18, it will be understood that in embodiments, such an aircraft assembly relates to another aircraft assembly such as a portion of a fuselage, another wing assembly, or a horizontal / vertical stabilizer. The methods and tools described herein may also be applied to such an aircraft assembly.

[0111] Where the term "or" appears, this should be interpreted as meaning "and / or" such that the items involved are not necessarily mutually exclusive and can be used in any appropriate combination.

[0112] Although the invention has been described above with reference to one or more preferred embodiments, it will be appreciated that various changes or modifications may be made without departing from the scope of the invention as defined in the appended claims.

Claims

1. A tool for positioning a sealing member device on a stringer receiving recess in a wing rib of an aircraft assembly, the tool comprising: a retainer configured to retain the sealing member arrangement on the recess; biasing means configured to act on the retaining member to bias the sealing member means into an aligned position relative to a stringer received in the recess; as well as Fixing means are configured to act on the sealing member means to fix the sealing member means in the aligned position.

2. The tool of claim 1, comprising a mount configured to mount the sealing member arrangement to the rib.

3. The tool according to claim 1, wherein: The retainer is configured to align an abutment edge of the sealing member arrangement with an abutment surface of the beam received in the recess in the aligned position.

4. The tool according to claim 1, wherein: The sealing member arrangement includes a sealing plate, and the retaining member is configured to receive the sealing plate.

5. The tool according to claim 4, wherein: The sealing plate is a first sealing plate, and the retainer includes a first retainer portion configured to retain the first sealing plate, and the tool includes a second retainer portion configured to retain a second sealing plate, wherein the biasing device is configured to bias the first retainer portion and the second retainer portion in different directions.

6. The tool according to claim 5, wherein: The biasing device is configured to bias the first retainer portion and the second retainer portion in opposite directions.

7. The tool according to claim 5, wherein: The first retainer portion and the second retainer portion are movable between a neutral position in which a spacing between the first sealing plate retained by the first retainer portion and the second sealing plate retained by the second retainer portion is less than a thickness of a web of the stringer configured to be received between the retainers, and an alignment position in which a spacing between the first sealing plate retained by the first retainer portion and the second sealing plate retained by the second retainer portion corresponds to a thickness of the web of the stringer.

8. The tool of claim 5, further comprising a third retainer portion configured to retain a third sealing plate, wherein: The biasing device is configured to bias the third retainer portion in a different direction than the first retainer portion and the second retainer portion.

9. The tool according to claim 1, wherein: The biasing means is configured to allow the sealing member means to pivot.

10. The tool of claim 1 further comprising position marking means for marking the alignment of said sealing member means relative to said rib.

11. The tool according to claim 1, wherein: The securing means is configured to urge the sealing member means against the rib when the sealing member means is located on the recess.

12. The tool according to claim 1, wherein: The fixing device is configured to be wirelessly operable.

13. A sealing kit for sealing a stringer receiving recess in a rib of an aircraft assembly, the sealing kit comprising the tool according to claim 1 and at least one sealing member arrangement.

14. A method of securing a sealing member apparatus to a stringer receiving recess in a wing rib of an aircraft, the method comprising: positioning a tool for retaining the sealing member device at least partially over the recess; biasing the sealing member means into an aligned position relative to a stringer received in the recess; securing the sealing member means in the aligned position; removing the stringer from the recess; as well as The sealing member arrangement is secured to the rib in the aligned position.

15. The method according to claim 14, comprising: marking the position of the sealing member arrangement on the rib at the alignment position; as well as The tool is removed prior to securing the sealing member arrangement in the aligned position.

16. The method according to claim 14, comprising: The stringer is reinserted into the recess after securing the sealing member arrangement to the rib.

17. The method according to claim 16, comprising: A sealant is applied to the sealing member arrangement prior to reinserting the stringer into the recess.

18. An aircraft component formed by the method of claim 14.

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