PIPE SUPPORT

Abstract

A pipe support for supporting a pipe of an aircraft fuel system is disclosed. The pipe support has first and second parts which together form a collar to retain the pipe. The first and second parts of the pipe support are able to be moved relative to each other between an open condition, in which the pipe is insertable between the first and second parts, and a closed condition, in which the first and second parts are brought together to retain the pipe. The collar is locatable in an opening in a structural member, such as a wing rib. When the collar is located in the opening in the wing rib, the pipe support is restricted from moving from the closed condition.

Claims

1. A pipe support for an aircraft fuel system, the pipe support comprising: a first part and a second part which together form a collar configured to retain a pipe, the pipe support being movable between an open condition, in which the pipe is insertable between the first and second parts, and a closed condition, in which the first and second parts are brought together to retain the pipe, wherein at least part of the collar is configured to be disposed in an opening in a structural member so that, when the at least part of the collar is in the opening, the pipe support is restricted from moving from the closed condition.

2. The pipe support of claim 1, comprising a flange on the collar.

3. The pipe support of claim 2, wherein the flange is configured to abut against the structural member to limit movement of the pipe support in a longitudinal axial direction of the pipe when the collar is in the opening.

4. The pipe support of claim 2, wherein the flange extends circumferentially about the collar.

5. The pipe support of claim 2, comprising a bayonet fitting.

6. The pipe support of claim 5, wherein the bayonet fitting comprises a bayonet tab configured to be inserted through a corresponding slot of the opening in the structural member, and to abut against the structural member upon rotation of the pipe support when the at least part of the collar is in the opening, so that a portion of the structural member is engaged between the flange and the bayonet tab.

7. The pipe support of claim 6, wherein the bayonet tab is a first bayonet tab, and the bayonet fitting comprises at least one second bayonet tab, the first bayonet tab having a different profile to the at least one second bayonet tab.

8. The pipe support of claim 2, comprising a flange seal on the flange.

9. The pipe support of claim 8, wherein the flange seal is a circumferentially extending flange seal.

10. The pipe support of claim 8, wherein the flange seal is electrically conductive to provide a conductive path between the pipe support and the structural member.

11. The pipe support of claim 1, comprising a collar seal on the collar.

12. The pipe support of claim 11, wherein the collar seal is electrically conductive to provide a conductive path between the pipe and the pipe support.

13. The pipe support of claim 1, comprising a stop configured to limit rotation of the at least part of the collar in the opening.

14. The pipe support of claim 1, comprising a fixing configured to fix the pipe support with the structural member to prevent rotation of the pipe support in the opening when the at least part of the collar is in the opening.

15. The pipe support of claim 1, wherein the pipe support comprises a hinge about which the first part and the second part are separable.

16. An aircraft assembly comprising: a fluid pipe, a structural member having an opening through which the pipe extends, and the pipe support of claim 1, wherein the pipe support supports the fluid pipe at the opening.

17. The aircraft assembly according to claim 16, wherein the structural member is a rib defining a rib plane, and wherein the fluid pipe extends through the rib plane.

18. The aircraft assembly according to claim 16, wherein the pipe has a cross-section that is uninterrupted as the pipe extends through each rib.

19. A fixed wing aircraft comprising at least one of the pipe support of claim 1 and the aircraft assembly comprising a fluid pipe, a structural member having an opening through which the pipe extends, wherein the pipe support supports the fluid pipe at the opening.

20. A method of supporting a pipe on a structural member of an aircraft, the method comprising the steps: disposing a pipe through an opening in the structural member, inserting the pipe between a first part and a second part of a pipe support in an open condition, moving the pipe support into a closed condition in which the first and second parts are brought together to form a collar with the pipe retained by the collar, and disposing the collar in an opening in the structural member so that the first and second parts are restricted from moving from the closed condition.

Description

BRIEF DESCRIPTION OF THE DRAWINGS

[0038] Embodiments of the invention will now be described with reference to the accompanying drawings, in which:

[0039] FIG. 1 is a plan view of an aircraft;

[0040] FIG. 2 is a plan view of an existing fuel line on a starboard wing;

[0041] FIG. 3a is a side profile view of an existing pipe support;

[0042] FIG. 3b is a front view of the existing pipe support of FIG. 3a;

[0043] FIG. 4 is a perspective view of an aircraft assembly including a pipe supported on a rib by a pipe support;

[0044] FIG. 5 is perspective view of the pipe support shown in FIG. 4;

[0045] FIG. 6 is another perspective view of the pipe support of FIG. 5, with the pipe support in a closed condition;

[0046] FIG. 7 is another perspective view of the pipe support of FIG. 5, with the pipe support in an open condition;

[0047] FIG. 8 is a perspective view of the pipe support in the open condition with the pipe received therebetween;

[0048] FIG. 9 is a perspective view of the pipe support in the closed condition with the pipe received in the pipe support;

[0049] FIG. 10 is a perspective view of the pipe support in the closed condition with the pipe received in the pipe support prior to engagement of the pipe support with the rib;

[0050] FIG. 11 is a perspective view of the pipe support in the closed condition with the pipe received in the pipe support with the pipe support received through the rib;

[0051] FIG. 12 is a perspective view of the pipe support engaged with the rib;

[0052] FIG. 13 is a rear view of the pipe support received through the rib;

[0053] FIG. 14 is a rear view of the pipe support engaged with the rib;

[0054] FIG. 15 is a cross-sectional view of the pipe support engaged with the rib; and

[0055] FIG. 16 is a cross-sectional side view of the pipe support fixed in engagement with the rib.

DETAILED DESCRIPTION OF EMBODIMENT(S)

[0056] FIG. 1 shows an existing aircraft 1 with port and starboard fixed wings 2, 3, a fuselage 4 with a nose end 5 and a tail end 6. The aircraft 1 is a typical jet passenger transonic transport aircraft but the invention is applicable to a wide variety of fixed wing aircraft types, including commercial, military, passenger, cargo, jet, propeller, general aviation, etc. with any number of engines attached to the wings or fuselage.

[0057] Each wing has a cantilevered structure with a length extending in a span-wise direction from a root to a tip, the root being joined to an aircraft fuselage 4. The wings 2, 3 are similar in construction so only the starboard wing 3 will be described in detail with reference to FIGS. 2 and 3A-3B.

[0058] The aircraft 1 includes a centre wing box 9 within the body of the fuselage 4. The centre wing box 9 is joined to an inboard rib 14a which forms the root of the wing 3. The wing 3 includes a series of spaced ribs 14 between the inboard rib 14a and an outboard rib 14b at the starboard wing tip. Each rib 14 defines a rib plane. The rib plane of each rib extends substantially parallel to the or each adjacent rib plane. The orientation of adjacent ribs with respect to each other may vary. The rib plane extends substantially parallel to a chord axis of the wing 3. The ribs 14 form part of a wing box on the starboard wing 3 the wing box 9 also including a front spar 10 and an upper skin cover 11, a rear spar 12, and a lower skin cover 13.

[0059] In the following description, the term front refers to components towards a leading edge 7 of the wing, and the term rear refers to components towards a trailing edge 8 of the wing. The terms forward and rearward shall be construed accordingly. The position of features may be construed relative to other features, for example a forward component may be disposed on a forward side of another component, but towards the rear of the vehicle. Similarly, the terms upper and lower refer to the position of features relative to other features and in accordance with a normal orientation of the aircraft 1.

[0060] In an existing wing box shown in FIG. 2, a fuel line extends across multiple ribs. The fuel line extends through openings 17 positioned within the body of the rib 14, making it difficult to install the fuel line within the assembled wing box. As a result, the fuel line is formed from multiple short fuel pipe sections 20 that connect to adjacent fuel pipes 20 at the ribs 14 using pipe connectors 21 located at the ribs 14. The pipe connectors 21 are disposed on opposing sides of each rib 14 to surround the opening 17. The fuel line therefore extends across nine ribs 14 through openings 17, although the fuel line may extend across a different number of ribs 14. The pipe connectors 21 attach to the ribs 14 using fasteners (not shown). As such, the pipe connectors 21 act as pipe supports.

[0061] In an alternative arrangement of pipe supports, as shown in FIGS. 3A and 3B, a pipe 22, forming the fuel line, extends through each opening 17 in each rib 14. A pair of support plates 23, 24 define a support aperture 25. The support plates 23, 24 are located on opposing sides of the pipe 22 and each have a recess 25a, 25b in an edge to define the support aperture 25. The support plates 23, 24 are bolted to one side of the rib 14 with fixings 26 about the opening 17 to support the pipe 22 at the opening 17. The support plates 23, 24 support the pipe 22 to restrict movement in the rib plane direction.

[0062] FIG. 4 shows an aircraft assembly 30 in accordance with an embodiment of the invention. The aircraft assembly 30 shares many common features with the existing aircraft assembly shown in FIGS. 1-3 and so similar reference numerals are used to denote similar parts with the existing aircraft assembly. The pipe 22 extends through the opening 17 (refer to FIG. 10) in the rib 14. The rib 14 defines a rib plane. The rib 14 has first and second rib faces 14a, 14b. The opening 17 extends between the first and second rib faces 14a, 14b.

[0063] The pipe 22 is a fluid pipe, such as a fuel pipe, a vent pipe or scavenge pipe. The pipe 22 may be configured to carry a liquid and/or a gas. The pipe 22 has a generally uniform cross-section along its length. This aids fluid flow, and restricts flow disturbances. The pipe 22 extends through the opening 17. The diameter of the pipe 22 is smaller than the peripheral dimensions of the opening 17.

[0064] A pipe support 40 mounts the pipe 22 in the region of the rib 14 to the rib 14. The rib 14 acts as a structural member. The pipe support 40 restricts movement of the pipe 22 and helps to reduce chaffing. As will be described below, attaching the pipe 22 to the rib 14 using the pipe support 40 is a convenient means of assembling the pipe 22 across multiple ribs 14 without the need to divide the fluid pipe into multiple sections that individually transverse each rib bay. Instead the pipe 14 is provided in the one uninterrupted fluid pipe 14 that extends through multiple ribs 14. As such, the parts count and complexity of the assembly may be simplified.

[0065] The pipe support 40 will now be described in detail with reference to FIGS. 5 to 7. The pipe support 40 has a first part 41 and a second part 42. The first and second parts 41, 42 form a body 43 of the pipe support 40. The first and second parts 41, 42 are separable. The first and second parts 41, 42 are moveable relative to each other between a closed condition, as shown in FIGS. 5 and 6, and an open condition, as shown in FIG. 7. In the closed condition, as shown in FIGS. 5 and 6, the first and second parts 41, 42 are brought together. An aperture 44 is defined through the pipe support 40. The aperture 44 is configured to receive the pipe 22. The aperture 44 is defined by a first semi-circular channel 45 in the first part 41 and a second semi-circular channel 46 in the second part 42.

[0066] The first and second parts 41, 42 are connected by a hinge 47. The first and second parts 41, 42 are hingedly mounted to each other. The hinge 47 ensures alignment of the first and second parts 41, 42 when the pipe support 40 is moved into its closed condition. As such, the first and second semi-circular channels 45, 46 are aligned with each other to define the aperture 44. The hinge 47 is a pin pivot. Alternative hinge arrangements may be used. The pipe support 40 is formed as a clam-shell configuration. The hinge 47 is offset from the first and second parts 41, 42 to allow the pipe support 40 to move easily between the open and closed conditions.

[0067] The aperture 44 is configured to receive the pipe 22. As such, the diameter of the aperture 44 substantially corresponds to the outer diameter of the pipe 22. In embodiments, the diameter of the aperture 44 is slightly greater than the outer diameter of the pipe 22, for example to allow the pipe 22 to move during wing bending.

[0068] The pipe support 40 comprises a collar 50. The collar 50 is formed by the first and second parts 41, 42. The body 43 of the pipe support 40 is split into the first and second parts 41, 42 along a diametric plane along which the first and second parts 41, 42 are brought into abutment in the closed condition. The collar 50 has an internal face 51 defining the aperture 44. The aperture 44 is a bore through the collar. It will be understood that the collar 50 is separable along the diametric plane when the first and second parts 41, 42 are moved from the closed condition into the open condition, as shown in FIG. 7. The first and second parts 41, 42 abut each other in the closed condition at first and second abutment ends 48a, 48b, 49a, 49b respectively.

[0069] A collar seal 55 extends around the aperture 44. The collar seal 55 protrudes from the collar internal face 51. The collar seal 55 is partially received in a collar seal channel 56 in the collar internal face 51. The collar seal 55 comprises a first collar seal portion 55a and a second collar seal portion 55b. The first and second collar seal portions 55a, 55b are on the first and second parts 41, 42 respectively. The collar seal 55 is separable into the two portions when the first and second parts 41, 42 are moved from the closed condition. The collar seal 55 forms a circumferentially extending sealing arrangement when the pipe support 40 is in the closed condition. The collar seal 55 is formed as a split O-ring arrangement, however alternative configurations are anticipated.

[0070] The body 43 of the pipe support 40 is formed from a conductive thermoplastic, for example a carbon fibre reinforced nylon. The collar seal 55 is formed from a conductive elastomeric material. The collar seal 55 is configured to directly contact the pipe 22 when the pipe 22 is received by the pipe support 40. By providing a conductive elastomeric seal it is possible to achieve an electrical bond between the pipe 22 and the pipe support 40 through the collar seal 55. When the first and second parts 41, 42 are moved into the closed condition with the pipe 22 received therebetween, the first and second parts 41, 42 are configured to clamp the pipe 22 in the aperture 44. The collar seal 55 is resilient and biases against the pipe 22.

[0071] The body 43 comprises a flange 60. The flange 60 is at one end of the collar 50. The flange 60 extends circumferentially around the collar 50. The flange 60 extends radially outwardly from the collar 50. The flange 60 is generally planar. The first and second parts 41, 42 together define the flange 60. The flange 60 comprises a first flange portion 60a and a second flange portion 60b. The hinge 47 extends between the first and second flange portions 60a, 60b. The flange 60 comprises a locating face 61. The locating face 61 is configured to be brought into abutment with the rib 14. The flange 60 restricts movement of the pipe support 40 relative to the rib 14 in an axial direction of the pipe 22.

[0072] The flange 60 comprises a flange seal 65. The flange seal 65 extends circumferentially. The flange seal 65 is configured to locate against one of the faces 14a, 14b of the rib to provide sealing thereagainst. The flange seal 65 is received in a flange channel 66. The flange channel 66 extends circumferentially around the locating face 61. The flange seal comprises a first flange seal portion 65a and a second flange seal portion 65b. The first and second flange seal portions 65a, 65b are on the first and second parts 41, 42 respectively. When the pipe support 40 is in the closed condition, the first and second flange seal portion 65a, 65b form a circumferentially extending seal.

[0073] The flange seal 65 is formed from a conductive elastomeric material. The flange seal 65 protrudes from the locating face 61. When the locating face 61 is brought into abutment with the rib 14, an electrical path is formed between the pipe 40 and the rib 14. As such it is possible to achieve an electrical bond between the pipe support 40 and the rib 14, through use of the pipe support 40 only. It is therefore possible to provide an electrical bond between the pipe 22 and the rib 14 through use of the pipe support 40 without the need for further components such as separate bonding leads.

[0074] A fixing 70 is provided. The fixing 70 is configured to fixedly locate the pipe support 40 with respect to the rib 14 and to prevent relative rotation of the pipe support 40 with the rib 14 when mounted thereto. In the present arrangement, the fixing comprises a nut and bolt arrangement 71, for example a self-retaining nut, acting as a threaded fastener configuration, which is receivable through a fixing hole 72 (as shown in FIG. 7) and a corresponding locking hole 73 on the rib 14 (as shown in FIG. 10). It will be understood that alternative fixing arrangements may be used, for example a biased member on the pipe support 40 which is locatable in the locking hole 73 on the rib 14. The fixing 70 is disposed on a protuberance 74.

[0075] The pipe support 40 comprises a bayonet fitting 80. The bayonet fitting 80 comprises a male bayonet arrangement 81. The male bayonet arrangement 81 is on the collar 50. The male bayonet arrangement 81 is at the other end of the collar 50 to the flange 60. A rib receiving gap 83 is defined between the male bayonet arrangement 81 and the flange 60.

[0076] The bayonet fitting 80 comprises a plurality of bayonet tabs 85. The bayonet tabs 85 protrude from the collar 50. The bayonet tabs 85 extend radially outwardly from the collar 50. The bayonet tabs 85 include a first bayonet tab 85a and two second bayonet tabs 85b. It will be understood that the number of bayonet tabs 85 may differ. The first bayonet tab 85a has a different profile to the second bayonet tabs 85b. The first bayonet tab 85a is larger than the second bayonet tabs 85b. In the present arrangement the width of the first bayonet tab 85a is greater than the width of the second bayonet tabs 85b, although other dimensions may differ, such as the length of the respective bayonet tabs. It will be understood that the shape of the bayonet tabs 85 may differ from that shown.

[0077] The distance between the bayonet tabs 85 and the flange 60 substantially corresponds to the thickness of the rib 14 about the opening 17. The respective angular distance between the bayonet tabs 85 may differ. In the present configuration, as shown in the figures, the first bayonet tab 85a is split between the first and second parts 41, 42 with one second bayonet tab 85b being formed on each of the first and second parts 41, 42.

[0078] Referring now in particular to FIGS. 10, 13 and 14 the opening 17 acts as a female bayonet arrangement 82 of the bayonet fitting 80. The opening 17 has a profile substantially corresponding to the profile of the male bayonet arrangement 81. The opening 17 has an opening wall 90. The opening 17 has a radial profile with a minimum radial distance which is greater than the radius of the outer surface of the pipe 22. When the pipe 22 is received in the opening 17, the opening wall 90 is configured to be spaced from the pipe 22. The opening wall 90 is spaced from the pipe by the collar seal 55. The opening wall is configured to be spaced from the collar 50. The opening 17 has opening slots 91. The opening slots 91 extends from the opening wall 90. The opening slots generally correspond to the bayonet tabs 85. The opening slots 91 comprise a first opening slot 91a and two second opening slots 91b. The arrangement of the first and second opening slots 91a, 91b generally correspond to the arrangement of the first and second bayonet tabs 85a, 85b. The first and second bayonet tabs 85a, 85b are configured to be inserted through the first and second opening slots 91a, 91b when the pipe support 40 is aligned with an inserted into the opening 17. The radial extent of the opening slots 91 is less than the radius of the flange seal 65. The opening slots 91 extend between the first and second rib faces 14a, 14b of the rib 14.

[0079] The radius of the opening wall 90 is less than the radial extent of each of the bayonet tabs 85.

[0080] As shown in FIG. 15, a stop 95 extends from the pipe support 40. The stop 95 is configured to abut against an edge of the opening to limit rotation of the pipe support 40 when the pipe support 40 is received by the opening 17. The stop 95 extends from the collar 50. In an alternative arrangement the stop 95 extends from one or both of the flange 60 and the male bayonet arrangement 81. The stop 95 is a protrusion. The stop 95 is configured to abut against an edge of one of the opening slots 91a, 91b as the pipe support 40 is moved into an engaged condition with the rib 14.

[0081] Assembly of the aircraft assembly 30 will now be described with reference to FIGS. 8 to 16.

[0082] The pipe 22 may be received by the pipe support 40 by holding the pipe support 40 in an open condition as shown in FIG. 8 and placing the pipe support 40 over the pipe 22. In the open condition, the first and second parts 41, 42 are hinged apart from each other such that the pipe may be received therebetween. The pipe support 40 is moved over the pipe 22 to position the pipe 22 in the vicinity of the first and second semi-circular channels 45, 46 which together form the aperture 44. When the pipe support 40 and pipe 22 are in relative position with each other, the first and second parts 41, 42 are brought together. The pipe support 40 is therefore moved into its closed condition, as shown in FIG. 9. By moving the support into the closed condition the pipe is clamped between the first and second parts 41, 42. The collar seal 55 locates against the outer surface of the pipe 22 to seal thereagainst. The first and second collar seal portions 55a, 55b together form a continuous seal around the pipe 22. It will be understood that an assembler may assemble the pipe support 40 with the pipe 22 via a one-handed operation. When the pipe support 40 is moved into the open condition it will be understood that the first and second parts 41, 42 are brought into abutment with each other. The pipe support 40 is free to move into the open condition. In the closed condition, the collar 50 is formed around the pipe 22, with the flange 60 extending from and around the pipe 22.

[0083] In FIGS. 10 to 12 the pipe support 40 is shown positioned relative to the rib 14 through which the pipe 22 extends. In FIG. 10 the pipe support 40 is shown in an unengaged position. In FIGS. 11 and 13 the pipe support 40 is shown in an inserted position. In FIGS. 12, 13 and 15 the pipe support is shown in an engaged position. In FIG. 16 the pipe support 40 is shown in a fixed condition.

[0084] The pipe support 40 is aligned with opening 17. The male bayonet arrangement 81 is aligned with the opening 17, acting as the female bayonet arrangement 82. That is the relative bayonet tabs 85 are aligned with the respective opening slots 91. The provision of the first bayonet tab 85a and the first opening slot 91a in which both have a different profile to the second bayonet tabs 85b and second opening slots 91b helps to ensure that the pipe support 40 is correctly aligned with the opening 17. In particular, such an arrangement helps to ensure that the fixing hole 72 aligns with the locking hole 73 when the pipe support 40 is in the engaged position with the rib 14.

[0085] When the male and female bayonet arrangements 81, 82 are aligned the collar 50 is inserted into the opening 17. The collar 50 is therefore disposed in the opening 17. The collar 50 extends through the opening 17. As such, the rib 14 is disposed between the bayonet tabs 85 and the flange 60. The rib receiving gap 83 corresponds to the thickness of the rib 14 about the opening 17. As such, the pipe support 40 is able to be rotated about the pipe 22 and relative to the rib 14 so that at least a portion of the rib 14 is received in the rib receiving gap 83 between the flange 60 and the bayonet tabs 85.

[0086] When the pipe support 40 is received by the opening 17, the first and second parts 41, 42 are restricted from being separable from each other. As such, the pipe support 40 is retained in the closed condition without the need for any additional components, such as fixings. The rib 14 itself acts to maintain the pipe support 40 in the closed condition. As such, the provision of a pipe support is simplified.

[0087] The pipe support 40 may then be rotated about the pipe 22 to move the pipe support 40 into the engaged position with the rib 14. As shown in FIG. 14, the bayonet tabs 85 are moved out of alignment with the opening slots 91. When the pipe support 40 is moved into the engaged position, movement of the pipe support 40 relative to the rib 14 in the longitudinal axis direction of the pipe 22 is prevented. Rotation of the pipe support 40 is limited by the stop 95. The stop 95 abuts against an edge of one of the opening slots 91 to limit movement. In such a position, the stop 95 ensures alignment of the fixing hole 72 with the locking hole 73.

[0088] When the fixing hole 72 is aligned with the locking hole 73, the fixing 70 may be engaged to lock the pipe support 40. When the fixing 70 is engaged, relative rotation of the pipe support 40 with the rib 14 is prevented. As such, it is not possible to move the pipe support 40 from the engaged position, so that the pipe support 40 is in a locked condition as shown in FIG. 16. It is therefore possible to use a single fixing to ensure a locked engagement of the pipe with the rib by a pipe support.

[0089] Referring to FIG. 16, when the pipe support 40 is in the engaged position the pipe 22 is supported at the rib 14. The pipe 22 is also securely held and spaced from the rib 14. The collar seal 55 is biased against the outer surface of the pipe 22. The collar seal 55 is therefore in abutment with the pipe 22 to securely locate the pipe 22 with the pipe support 40. As the collar seal 55 is electrically conductive, an electrical bond is formed between the pipe 22 and the pipe support 40. The collar seal 55 provides an internal fluid seal to prevent fluid leakage through the opening 17 by providing a fluid seal between the pipe 22 and the pipe support 40.

[0090] When the pipe support 40 is in the engaged position, the flange 60 abuts the first rib face 14a of the rib 14. The flange seal 65 is biased against the rib 14. As the flange seal is electrically conductive, the pipe support 40 and the rib 14 are electrically bonded to each other. The flange seal provides an external seal to prevent fluid leakage through the opening 17. The flange seal 60 prevents leakage between the rib 14 and the pipe support 40. Through the provision of the collar seal 55 and the flange seal 65 it is possible to maximise the sealing capability provided by the pipe support 40. The pipe support 40 restricts the fluid path across the rib 14 through the openings 17.

[0091] Although in the above described embodiments the collar seal 55 and the flange seal 65 are electrically conductive, it will be understood that one or more of the seals 55, 65 and the pipe support 40 may be formed from an electrically insulating material to prevent the provision of an electrical path between the rib 14 acting as a structural member, and the pipe 22.

[0092] It will be understood that the aircraft assembly may be disassembled by disengaging the fixing 70 and rotating the pipe support 40 from the engaged position to the inserted position. As such, the pipe support 40 may then be withdrawn from the rib 14. As such, the pipe support 40 is replaceable or interchangeable.

[0093] Where the word or appears this is to be construed to mean and/or such that items referred to are not necessarily mutually exclusive and may be used in any appropriate combination.

[0094] 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.