Method for installing system components in a section of an aircraft fuselage

Abstract

Method (66) for installing system components (2, 52, 60) in a section of an aircraft fuselage (4), comprising the steps: - Providing (68) at least one planar structural arrangement (8, 18, 20, 22, 24, 50, 56) to be attached to or within the fuselage of the aircraft, - Attaching (70) system components (2, 52, 60) to the structural arrangement (8, 18, 20, 22, 24, 50, 56), - Coupling (72) of system lines (46) with the system components (2, 52, 60) and arranging (74) the system lines (46) on the structural arrangement (8, 18, 20, 22, 24, 50, 56), - Positioning (72) the structural assembly (8, 18, 20, 22, 24, 50, 56) with the system components (2, 52, 60) and system lines (46) arranged thereon at a designated installation location of the structural assembly (8, 18, 20, 22, 24, 50, 56), and - mechanical coupling (78) of the structural assembly (8, 18, 20, 22, 24, 50, 56) with the aircraft fuselage (4); wherein the mechanical coupling (78) comprises connecting structural support elements (14, 62) to the aircraft fuselage (4) and the at least one structural arrangement (8, 18, 20, 22, 24, 50, 56); wherein the connection of the supporting structure elements (14, 62) to the aircraft fuselage (4) and the at least one structural arrangement (8, 18, 20, 22, 24, 50, 56) includes compensating for manufacturing tolerances by adjusting connection positions, wherein the adjustment of the connection positions is carried out by means of tolerance-compensating screw connections (36) between the supporting structure elements (14, 62) and the at least one structural arrangement (8, 18, 20, 22, 24, 50, 56).

Description

TECHNICAL AREA

[0001] The invention relates to a method for installing system components in a section of an aircraft fuselage. Furthermore, the invention relates to an installation system for installing system components in an aircraft fuselage. BACKGROUND OF THE INVENTION

[0002] The installation of system components in an aircraft fuselage typically takes place after the fuselage has been manufactured. The individual system components are manually moved into the fuselage and secured at designated locations using tools and other aids. In some installation locations or sections of the fuselage, installation can be hampered by limited space. For example, it is common practice in commercial aircraft to install wastewater tanks in the rear section of the fuselage and connect them to the corresponding water, air, and electrical lines. Due to the size of the wastewater tanks and the relatively low height of the installation space (less than 1.5 m), installation is physically demanding. This also increases the installation time, which can negatively impact other installation processes to be carried out in the fuselage.

[0003] US Patent 2008 / 0210820A1 describes aircraft floor assemblies and methods for their assembly. An aircraft comprises at least one fuselage section and at least one floor section. At least one system component is installed on the floor section before the floor section is installed in the fuselage of the aircraft. Furthermore, a floor section designed for installation in an aircraft comprises at least one system component installed on the floor section while it is outside the aircraft. A method for assembling an aircraft is also disclosed. The method includes installing at least one system component on a floor section and installing the floor section in a fuselage section of the aircraft.

[0004] DE 10 2016 210 089 A1 describes a method for joining skin sections of a fully enclosed fuselage, in particular for an aircraft or spacecraft, comprising the following process steps: providing at least one first skin section and one second skin section, wherein at least one of the provided skin sections is equipped with components intended to remain in the fuselage later; positioning at least the first skin section and the second skin section relative to each other in a first butt joint such that the skin sections form a fully enclosed fuselage assembly; guiding a first joining head along the first butt joint on an outer surface of the fuselage assembly;and guiding a second joining head along the first joint on an inner surface of the fuselage assembly, wherein the second joining head is guided along longitudinal guide means arranged within the fully enclosed fuselage assembly, which are at least partially formed with the components intended to remain in the fuselage later. Furthermore, a joining device designed for such a method is described.

[0005] German patent DE 10 2012 001 797 A1 describes a system for mounting aircraft system components in the crown area of ​​an aircraft. The system comprises a first longitudinal beam element, a second longitudinal beam element, and a bridge element connecting the first and second longitudinal beam elements. The system can be mounted in the crown area of ​​an aircraft such that the first and second longitudinal beam elements extend essentially parallel to the longitudinal axis of the aircraft. A plurality of cable channels for accommodating electrical cables are formed on the first and / or second longitudinal beam element.

[0006] DE 10 2010 055 995 A1 describes an aircraft system component carrier system comprising at least one aircraft system component carrier module, at least one aircraft system component which is attached to the aircraft system component carrier module by means of an aircraft system component holder, and an aircraft structural element of an aircraft fuselage upper shell to which the aircraft system component carrier module is attached by means of a structural holder in such a way that the aircraft system component carrier module, the aircraft system component and the aircraft structural element form an independently manageable assembly.

[0007] US 2007 / 0007392A1 describes an aircraft in which a cargo deck is typically provided for receiving cargo in the cargo hold. This deck comprises a plurality of ball mats, floor plates, or similar flat floor elements. It further describes the provision of a plurality of roller conveyors or similar profile elements mounted longitudinally along the aircraft to accommodate transport rollers, PDUs, latches, or similar functional units for moving and securing cargo on the cargo deck.To simplify the arrangement and assembly, it is proposed that the floor elements be rigidly connected to the profile elements, at least in sections, to form a deck section extending over the entire width of the cargo hold, in such a way that longitudinal forces acting on the deck section, in particular those caused by the cargo, which are oriented in the direction of a longitudinal axis of the aircraft and act as shear forces in the surface direction of the cargo deck, can be transferred to the outer edges of the deck section and from the outer edges to a rib-reinforced outer skin of the aircraft.

[0008] US 2006 / 0 231 681 A1 describes how, in conventional aircraft cargo holds, panels or similar flat floor elements are attached to floor beams or similar support structures installed in the aircraft fuselage. Functional units such as rollers, latches, or PDUs are then mounted and connected to each other via appropriate control lines. The proposal suggests permanently attaching the floor elements to the support beams to form prefabricated floor modules and installing these floor modules in the aircraft.

[0009] US patent 2012 / 0187248A1 describes a method for installing systems in an aircraft fuselage, a device with a rail system for carrying out the method, and a cargo loading system that uses the rail system as a guidance system for cargo.

[0010] DE 10 2009 056 593 A1 describes an installation system for connecting systems to an aircraft structure, in particular lines or cabin components to a primary structure of an aircraft, comprising at least one support for arranging the systems and at least two fastening elements for attaching the support to the structure, wherein at least one structure-side bracket is provided with an adjustable receiving element for sectionally receiving one of the fastening elements, as well as a method for connecting systems. Furthermore, a calibration system with a positioning device for mounting such installation systems is described.

[0011] DE 10 2006 026 168 A1 describes an aircraft fuselage structure with frames and main deck crossbeams running transversely to the fuselage longitudinal direction. It is provided that the aircraft fuselage structure contains prefabricated integral units, each comprising at least the lower portion of the fuselage frame and the main deck crossbeam, wherein the fuselage frame and a portion of the main deck crossbeam spanning at least a substantial part of the width of the main deck and connected to the fuselage frame on both sides are prefabricated as an integral part.

[0012] EP 2 456 671 B1 describes a method for installing a system in an aircraft fuselage, a device with a rail system for carrying out the method and a cargo loading system that uses the rail system as a guidance system for general cargo. SUMMARY OF THE INVENTION

[0013] It is an object of the invention to propose a method for installing system components in an aircraft fuselage, in which the installation is significantly simplified and the assembly time is reduced.

[0014] The problem is solved by a method having the features of claim 1. Advantageous embodiments and further developments can be found in the dependent claims and the following description.

[0015] According to a first aspect of the invention, a method for installing system components in a section of an aircraft fuselage is proposed, the method comprising the steps of providing at least one planar structural arrangement to be attached to or in the aircraft fuselage, attaching system components to the structural arrangement, coupling system lines to the system components and arranging the system lines on the structural arrangement, positioning the structural arrangement with the system components and system lines arranged thereon at a provided installation location of the structural arrangement, and mechanically coupling the structural arrangement to the aircraft fuselage.

[0016] First, a planar structural assembly is provided for attachment to or within the aircraft fuselage. This structural assembly can be understood as an arrangement of one or more structural components that together form part of a larger structure. The structure can, in principle, have several different configurations. In particular, the structure can form part of a primary or secondary structure located inside the aircraft fuselage, or it can be positioned on a structural section located outside the primary structure.

[0017] The structural arrangement could include, for example, crossbeams arranged parallel to each other along a longitudinal axis of the aircraft fuselage, supporting floor joists or floor rails. Alternatively, the structural arrangement could also include part of an outer skin or external fairing, which is at least locally equipped with stiffening components. An example would be the fairing of a wing-fuselage junction, also known as a "belly fairing."

[0018] The aim is therefore to provide a self-supporting base for installing system components outside the aircraft fuselage, allowing the components to be attached to it. Installation requires no work in confined spaces and can be carried out much more ergonomically than with known methods, since the installation base is located outside the aircraft fuselage.

[0019] The step of attaching system components to the structural assembly comprises positioning and attaching the system components directly to the structural assembly. In known aircraft, many systems are arranged, among other things, on the primary structure, for example, on fuselage frames and / or stringers. Consequently, they are mounted in the interior on radially outer areas. Depending on the design of the structural assembly, however, a different construction can also result with the method according to the invention if the planar structural assembly is not located on or within the radially outer primary structure.

[0020] The same applies to connecting system cables to the system components and arranging the system cables on the structural assembly. The system cables can have different shapes and are also connected to the structural assembly. The structural assembly with the system components and system cables thus forms an independent unit with system components that can be operated on the structural assembly as a module. This module can be positioned at a designated installation location on the structural assembly by positioning the structural assembly with the system components and system cables attached to it. As described above, various installation locations are possible.

[0021] The mechanical coupling of the structural assembly to the aircraft fuselage is the final step and the only process step that must be performed directly inside the fuselage. However, the effort required by the assembly personnel can be significantly reduced compared to conventional methods. The mechanical coupling of the structural assembly to the aircraft fuselage can include, in particular, attaching dedicated support structures to application points on the aircraft structure. Profile beams, rods, or other components can extend from the structural assembly to which the system components are attached; these must be connected to the aircraft fuselage after the structural assembly has been positioned. This can specifically involve attaching them to fuselage frames.

[0022] The coupling of the structural assembly to the aircraft fuselage can be carried out by an automatic or automatable device.

[0023] In an advantageous embodiment, the provision of the structural arrangement can involve connecting several structural components to form a cohesive, compact, rigid structure. Such a structure is inherently stable, particularly in its uninstalled state, and can serve as a basis for constructing a system comprised of multiple system components. Several structural components can be assembled into a planar structural arrangement, which can incorporate all conventional connection methods and structural components. The structural components can include profile beams or profile rails that can be arranged and connected within a specific grid.

[0024] The at least one structural arrangement can comprise a floor structure for a cabin floor or a cargo hold floor. Such a structure is characterized by a series of crossbeams arranged parallel to one another, which, when installed, run, for example, between the lateral, outer sides of a frame. The spacing between the crossbeams is therefore preferably determined by the spacing between successive frames. To form a continuous structure, longitudinal beams can be used that cover and connect the spaced-apart crossbeams. Consequently, the structural arrangement serves as the basis for a fully equipped module in the form of a floor section. System components that are typically attached to frames or at least to the underside of a primary aircraft structure are now arranged on the underside of a floor.Accordingly, it may be necessary to use different mounting brackets for the system components than are currently standard practice. The system cables can also now extend along the structural assembly instead of along the underside of the fuselage.

[0025] Securing system components can also involve attaching them to the underside of the floor structure. This may involve arranging brackets that are attached to the system components and then connected to the floor structure, or vice versa. The brackets must be adapted to the floor structure to ensure a secure and reliable hold.

[0026] The arrangement of the system lines on the structural assembly involves placing the system lines on the underside of the floor structure. This allows, as previously explained, the realization of a self-contained, operational module. Connecting the lines to the underside of the floor structure further reduces the direct effort required in the confined installation space and also allows the system components to be tested outside the aircraft fuselage.

[0027] In a further embodiment, the at least one structural arrangement can include a fairing structure for a wing-fuselage junction. Such a fairing structure is located below a wing box in commercial aircraft and can cover a number of components installed there. In particular, the system components could include hydraulic devices. The available installation space is also limited in this area, so that normal standing headroom is not achieved, making work in this area difficult. The arrangement and fastening of system components can therefore involve mounting system components directly onto a fairing structure, in order to then mount and fasten the entire fairing structure to the fuselage.

[0028] Since the fairing structure usually closes off the aircraft fuselage at the bottom, arranging the system components on the top of the fairing structure is preferred.

[0029] Positioning the structural assembly can involve sliding it into the aircraft fuselage along a support rail. The support rail can be designed so that at least one end is fixed to or rests against the floor of a workshop. The opposite end can extend freely into an open fuselage section and be positioned so that the structural assembly, with its attached system components, can be moved along the support rail to its intended installation location within the fuselage. Alternatively, the support rail can extend completely through the relevant fuselage section and be fixed at both ends. The support rail has, at least locally, a rail profile along which roller-mounted carriages, supporting the structural assembly, can be moved.This allows large-format construction sections to be brought into the aircraft fuselage and attached there; an existing floor or similar flat structure is not necessary for transport and positioning.

[0030] The runners can be designed to hold the structural arrangement at a selectively variable distance. For example, each runner can have a cable pulley that allows the structural arrangement to be lowered by gravity or raised by actively applying tensile force.

[0031] According to the first aspect of the invention, the mechanical coupling involves connecting structural support elements to the aircraft fuselage. The structural support elements can be understood as structural elements that are attached to the planar structural assembly and extend from it to the remaining part of the aircraft fuselage. In the example of the floor section, elongated structural support elements can be arranged on a lower side of the structural assembly, extending substantially perpendicular to it. The structural support elements can be dimensioned such that they can be directly connected to frames or other elements on a radially outer side of the interior of the aircraft fuselage. The coupling can further include compensating for dimensional tolerances at a connection point between the structural support elements and the aircraft fuselage.Various methods could be considered for this purpose, including the use of eccentric bushings and suitable screw connections. Of particular note is the fact that all tolerance-compensating measures for connecting the system components are implemented directly to the floor structure or the flat structural arrangement. Consequently, tolerance compensation is shifted from the installation location on the aircraft fuselage to the flat structural arrangement, and thus, during assembly, to outside the aircraft fuselage.

[0032] The arrangement of the system lines on the structural assembly preferably involves arranging the system lines on the same side of the structural assembly as the attachment of the system components. This ensures, regardless of the type and design of the structural assembly, that the structural assembly equipped with system components forms an independent, self-contained module.

[0033] The process can further include the step of suspending the structural assembly on a mounting frame and pivoting the structural assembly on the mounting frame from a mounting position to an installation position. The mounting position can thus be chosen very ergonomically. It is conceivable that the mounting position can be selectively adjusted to allow for adjustments to the mounting position in successive construction steps.

[0034] According to the first aspect of the invention, connecting the load-bearing structural elements to the aircraft fuselage and the at least one structural assembly involves compensating for manufacturing tolerances by adjusting the connection positions. The connection positions can be adjusted, among other things, by means of adjustable screw connections that employ rotatable eccentric bushings. Other variations are not excluded.

[0035] According to a second aspect of the invention, a system module for integration into an aircraft fuselage is further provided, comprising at least one system component, at least one system line, and a planar structural arrangement in the form of a floor structure for a passenger cabin or cargo hold, or in the form of a fairing structure for a wing-fuselage junction, and supporting structural elements, wherein the at least one system component and the at least one system line are directly attached to the structural arrangement and form a cohesive module that can be mechanically coupled to an aircraft fuselage to form a section of a floor or a wing-fuselage junction arranged therein. The cohesive module can be mechanically coupled by means of the supporting structural elements, which can be connected to the aircraft fuselage and the structural arrangement.

[0036] The connection positions of the supporting structure elements can be adjusted to compensate for manufacturing-related tolerances by means of tolerance-compensating screw connections between the supporting structure elements and the structure arrangement.

[0037] The system module is therefore a coherent unit consisting of the structural arrangement and the system components, which are coupled with the necessary system lines. In the inventive method described above, the system module is thus installed in the aircraft fuselage.

[0038] The system components can contain at least one element from a group of system components, containing the group: - at least one wastewater tank, - at least one water tank, - at least one fuel tank, - at least one component of a hydraulic system, - at least one electronic device, - at least one mounting frame for electronic devices, and - at least one component of an air conditioning system.

[0039] Of course, other system components are conceivable, which can be integrated into the aircraft, especially in confined spaces.

[0040] The invention could further relate to an installation system comprising a selection of structural components for forming a structural assembly, a mounting frame, and a support rail with the aforementioned runners. This allows a structural assembly to be provided and equipped with system components for subsequent installation in the aircraft fuselage.

[0041] According to a third aspect of the invention, an aircraft is further provided comprising an aircraft fuselage with a primary structure and at least one system module connected to the primary structure in a section of the aircraft fuselage. The provision and installation are carried out in the manner described above. BRIEF DESCRIPTION OF THE FIGURES

[0042] Further features, advantages, and applications of the present invention will become apparent from the following description of the exemplary embodiments and the figures. All features described and / or illustrated, individually and in any combination, constitute the subject matter of the invention, irrespective of their composition in the individual claims or their cross-references. In the figures, the same reference numerals denote identical or similar objects. Fig. Figures 1a to 1d show some steps of a procedure for installing system components in a section of an aircraft fuselage. Fig. 2a and Fig. 2b shows how to provide a structural arrangement for arranging system components. Fig. Figure 3 shows a connection of the structural arrangement in an aircraft fuselage. Fig. Figures 4a to 4c show an example of a structural arrangement in the form of a floor section with system components arranged on it. Fig. Figure 5 shows another example of a structural arrangement in the form of a floor section for integration into a front section of an aircraft fuselage. Fig. Figure 6 shows an example of a structural arrangement in the form of a fairing section for a wing-fuselage junction. Fig. Figure 7 schematically shows an assembly frame for providing a structural arrangement and installing system components. Fig. Figure 8 shows a procedure for installing system components in a schematic, block-based representation. Fig. Figure 9 finally shows an aircraft with an aircraft fuselage and a section in which a structural arrangement with installed system components is arranged. DETAILED PRESENTATION OF EXEMPLARY EXECUTION FORMS

[0043] In the Fig. Figures 1a to 1d illustrate some steps of a procedure for installing system components 2 in a section of an aircraft fuselage 4. Further steps are shown in subsequent figures.

[0044] Fig. Figure 1a shows a rear section of the aircraft fuselage 4, which tapers in the opposite direction x. A series of window openings 6 are shown, indicating the layout of a passenger cabin, which is to be fitted with a floor. The system components 2 are arranged below the floor and connected to the aircraft fuselage 4 there. Due to their intended position in the rearmost section of the aircraft fuselage 4 and due to the tapering, there is no standing height for assembly personnel at this point below the floor, and the limited space significantly complicates assembly using conventional methods.

[0045] To facilitate assembly, a planar structural arrangement 8 is used according to the invention, which in the present case is designed as a floor structure. The system components 2 are arranged on an underside 7 of the structural arrangement 8 and are firmly connected to it by various holders, which can be seen in subsequent figures. This forms a continuous system module 9 that can be coupled to the aircraft fuselage 4. The system module 9 shown also forms a section of a floor arranged in the aircraft fuselage 4.

[0046] A support rail 10 projects through the aircraft fuselage 4 and allows for the sliding mounting of runners 12. The runners 12 can have multiple rollers that can roll along a rail profile on the support rail 10. Due to the arrangement of the support rail 10 through the aircraft fuselage shown, the runners 12 can therefore be moved along the longitudinal axis x. The structural assembly 8 is then positioned here and can be moved along the longitudinal axis.

[0047] In Fig. Figure 1b shows that the structural assembly 8 with the system components 2 arranged on it is pushed along the support rail 10 into the aircraft fuselage 4 until a predetermined position is reached at least along the longitudinal direction x of the aircraft fuselage 4. This can therefore correspond to the final position in the x-direction.

[0048] In Fig. In 1c, the structural arrangement 8 is brought into a final position, which, for example, is positioned slightly further away from the support rail 10 in the vertical direction. As in Fig. As indicated in Figure 1d, load-bearing structural elements 14 can then be used to connect the structural assembly 8 to the aircraft fuselage 4. The load-bearing structural elements 14 are exemplified as rods or profile beams, which are particularly suitable for transferring the loads of a floor structure into a primary structure of the aircraft fuselage 4. The primary structure can, in particular, comprise fuselage frames 16 and stringers (not shown) running parallel to the longitudinal axis x. The load-bearing structural elements 16 can also be designed, among other things, as hollow rods made of a composite material, equipped with rod ends, and exhibiting a particularly low weight.

[0049] Fig. Figure 2a shows several possible structural arrangements 8, 18, 20, 22, and 24 that would be suitable for arranging system components 2. This is, of course, not exhaustive and can be supplemented as desired. While structural arrangements 8, 18, 20, and 24 can each be equipped with load-bearing structural elements 14, structural arrangement 22 can be part of a fairing structure for a fuselage-wing junction 26 in the area of ​​a wing box 28.

[0050] In Fig. Figure 2b shows a slightly enlarged view of the structural arrangement 8. It can be seen that the structural arrangement 8 consists of several parallel crossbeams 30, which are connected to one another by means of longitudinal stiffening elements 32, which may also include floor rails 38. The structural arrangement 8 is therefore rigid and inherently stable, so that it can be used as a base for arranging the system components 2. The method according to the invention can therefore comprise connecting several crossbeams 30 by means of longitudinal stiffening elements 32 to provide the planar structural arrangement.

[0051] To attach the structural assembly 8 or the system module 9 to the aircraft fuselage 4, for example to fuselage frames 16, as shown in Fig. As indicated in Figure 3, screw elements 34 are used. These can have tolerance-compensating properties. Likewise, the load-bearing structure elements 14 can be coupled to the structure assembly 8 via tolerance-compensating screw connections 36. The aim is to compensate for manufacturing-related tolerances of the aircraft fuselage 4 by means of screw connections 34 and 36 or other devices when connecting the structure assembly 8, while tolerances relating to the installation of system components 2 are completely compensated within the structure assembly 8. Fig. Figure 3 shows, as an example, the structural arrangement 8 or the system module 9 in a front view in an installed state. A crossbeam 30 is shown, which is equipped with floor rails 38 and other longitudinal stiffening elements 32. Floor panels 40 are arranged on these, which form a floor after installation of the structural arrangement 8.

[0052] Fig. Figure 4a shows a comparison of the installation of system components 2 in the prior art (I) and using the method according to the invention (II). In the upper illustration I, all system components 2 have mechanical holders 42 which are connected to fuselage frames 16. All system components are therefore to be inserted into the aircraft fuselage 4 and, in particular, arranged horizontally on fuselage frames 16 and then connected with system lines.

[0053] In the case of the previously shown example with a floor structure as a structural assembly 8 for forming a system module 9, modified holders 44 are required to connect the system components 2 to the structural assembly 8. Consequently, while a basic spatial structure of the system components 2 can be adopted, all holders 44 are designed for attachment to the underside 7 of the structural assembly 8 in the form of a floor structure. However, it is no longer necessary to compensate for manufacturing tolerances of the fuselage frames 16 with holders, since the structural assembly 8 with the system components 2 attached to it is inserted into the aircraft fuselage 4 as a complete, finished system module 9 and is connected as a whole to the fuselage frames 16 via tolerance-compensating measures.

[0054] The same applies to the representations in Fig. 4b. Here, an arrangement of system lines 45 in the prior art (I) is shown, which extend largely along fuselage frames 16. In the illustration below (II), system lines 46 are spatially distributed differently. These extend largely over the structural arrangement 8 and run from there to the system components 2.

[0055] In Fig. Figure 4c shows exemplary wastewater tanks as system components 2, which are connected to various system lines. Here, too, a common arrangement of holders 42 is shown in an upper view (I), while the arrangement of holders 44 according to the embodiment of the invention (II) is analogous to Fig. Figure 4a shows that while the position of the wastewater tanks 2 remains practically unchanged, it may be advantageous to relocate individual peripheral devices, such as pumps 48 and similar equipment. In Figure II, for example, the pumps 48 are placed directly on the structural assembly 8 and are connected to the wastewater tanks 2.

[0056] Fig. Figure 5 shows another variant in which a structural arrangement 50 is equipped on an underside 51 with avionics devices 52 as system components and is inserted as a system module 53 into a forward section of the aircraft fuselage 4. The so-called avionics compartment 54 also provides a relatively small installation space for accommodating assembly personnel, and assembly can be significantly facilitated by applying the method steps according to the invention.

[0057] Fig. Figure 6 shows a very schematic structural assembly 56 that can be used for a wing-fuselage junction 26. The structural assembly 56 carries several system components 60 on its upper surface 58, which are rigidly connected to the structural assembly 56 on its upper surface. Supporting structural elements 62, shown only schematically for the sake of completeness, serve to attach a resulting system module 61. This allows the structural assembly 56 to be attached to the rest of the aircraft fuselage 4 after it has been placed in the desired position.

[0058] Fig. Figure 7 schematically shows an assembly frame 64 capable of supporting the structural assembly 8 (or another) and pivoting it from an assembly position to an installation position. The assembly position can be used, for example, to provide the structural assembly 8 itself and connect the crossbeams 30 to the longitudinal stiffening elements 32 and the floor rails 38. The installation position may differ from this and serves to support the installation of system components 2 to form the system module 9. Depending on the size of the structural assembly and the progress of the installation, the installation position can be adjusted as needed.

[0059] Fig. Figure 8 shows a schematically illustrated method 66 for installing system components in a section of an aircraft fuselage. By way of example, the method includes the steps of providing 68 at least one planar structural assembly to be attached to or within the aircraft fuselage, attaching 70 system components to the structural assembly, connecting 72 system lines to the system components and arranging 74 the system lines on the structural assembly, positioning 76 the structural assembly with the system components and system lines attached to it at a designated installation location of the structural assembly, and mechanically coupling 78 the structural assembly to the aircraft fuselage. Providing the structural assembly may involve connecting 80 several structural components to form a coherent, rigid structural assembly.

[0060] Finally, it shows Fig.Figure 9 shows an aircraft 82 with a fuselage 4, which, for example, has a system module 9 in a rear section. The installation of the system components 2 is carried out as described above. The system module 61 can also be located in the wing-fuselage junction 26. The system module 53 can be located in the avionics compartment 54.

[0061] It should be further noted that "having" does not exclude any other elements or steps, and "a" or "an" does not exclude a plurality. It should also be noted that features described with reference to one of the above embodiments may also be used in combination with other features of other embodiments described above. Reference numerals in the claims are not to be considered as a limitation.

Claims

[1] Method (66) for installing system components (2, 52, 60) in a section of an aircraft fuselage (4), comprising the steps: - Providing (68) at least one planar structural arrangement (8, 18, 20, 22, 24, 50, 56) to be attached to or within the fuselage of the aircraft, - Attaching (70) system components (2, 52, 60) to the structural arrangement (8, 18, 20, 22, 24, 50, 56), - Coupling (72) of system lines (46) with the system components (2, 52, 60) and arranging (74) the system lines (46) on the structural arrangement (8, 18, 20, 22, 24, 50, 56), - Positioning (72) the structural assembly (8, 18, 20, 22, 24, 50, 56) with the system components (2, 52, 60) and system lines (46) arranged thereon at a designated installation location of the structural assembly (8, 18, 20, 22, 24, 50, 56), and - mechanical coupling (78) of the structural assembly (8, 18, 20, 22, 24, 50, 56) with the aircraft fuselage (4); wherein the mechanical coupling (78) comprises connecting structural support elements (14, 62) to the aircraft fuselage (4) and the at least one structural arrangement (8, 18, 20, 22, 24, 50, 56); wherein the connection of the supporting structure elements (14, 62) to the aircraft fuselage (4) and the at least one structural arrangement (8, 18, 20, 22, 24, 50, 56) includes compensating for manufacturing tolerances by adjusting connection positions, wherein the adjustment of the connection positions is carried out by means of tolerance-compensating screw connections (36) between the supporting structure elements (14, 62) and the at least one structural arrangement (8, 18, 20, 22, 24, 50, 56). [2] Method (66) according to claim 1, wherein the provision (68) of the structural arrangement (8, 18, 20, 22, 24, 50, 56) comprises the joining (80) of several structural components (30, 32, 38) to form a connected, rigid structural arrangement (8, 18, 20, 22, 24, 50, 56). [3] Method (66) according to claim 1 or 2, wherein the at least one structural arrangement (8, 18, 20, 22, 24, 50, 56) comprises a floor structure for a cabin floor or a cargo hold floor. [4] Method (66) according to claim 3, wherein the fastening (70) of system components (2, 52, 60) comprises fastening the system components (2, 52, 60) to an underside (7, 51) of the floor structure. [5] Method (66) according to claim 3 or 4, wherein the arrangement (74) of the system lines (46) on the structural arrangement (8, 18, 20, 22, 24, 50, 56) comprises the arrangement of the system lines (46) on an underside (7, 51) of the floor structure. [6] Method (66) according to any of the preceding claims, wherein the at least one structural arrangement (8, 18, 20, 22, 24, 50, 56) comprises a fairing structure for a wing-fuselage transition (26). [7] Method (66) according to claim 6, wherein the fastening of system components (2, 52, 60) comprises fastening the system components (2, 52, 60) to an upper surface of the cladding structure. [8] Method (66) according to one of the preceding claims, wherein the positioning (72) of the structural arrangement (8, 18, 20, 22, 24, 50, 56) comprises inserting the structural arrangement (8, 18, 20, 22, 24, 50, 56) onto a support rail (10) into the aircraft fuselage (4). [9] Method (66) according to any of the preceding claims, wherein the arrangement (74) of the system lines (46) on the structural arrangement (8, 18, 20, 22, 24, 50, 56) comprises the arrangement of the system lines (46) on the same side of the structural arrangement (8, 18, 20, 22, 24, 50, 56) as the fastening (70) of the system components (2, 52, 60). [10] Method (66) according to one of the preceding claims, wherein the method (66) further comprises the step of suspending the structural arrangement (8, 18, 20, 22, 24, 50, 56) on a mounting frame (64) and pivoting the structural arrangement (8, 18, 20, 22, 24, 50, 56) on the mounting frame (64) from a mounting position to an installation position. [11] System module (9, 53, 61) for integration into an aircraft fuselage (4), comprising: - at least one system component (2, 52, 60), - at least one system line (46), - a planar structural arrangement (8, 18, 20, 22, 24, 50, 56) in the form of a floor structure for a passenger cabin or cargo hold or in the form of a fairing structure for a wing-fuselage junction (26), and - Structural elements (14, 62) wherein the at least one system component (2, 52, 60) and the at least one system line (46) are directly attached to the structural arrangement (8, 18, 20, 22, 24, 50, 56) and form a connected module which can be mechanically coupled to an aircraft fuselage (4) to form a section of a floor arranged therein or a wing-fuselage junction (26); wherein the connected module can be mechanically coupled by means of the supporting structure elements (14, 62) which can be connected to the aircraft fuselage (4) and the structural arrangement (8, 18, 20, 22, 24, 50, 56); and wherein connection positions of the supporting structure elements (14, 62) can be adjusted to compensate for manufacturing tolerances by means of tolerance-compensating screw connections (36) between the supporting structure elements (14, 62) and the structure arrangement (8, 18, 20, 22, 24, 50, 56). [12] System module according to claim 11, wherein the system components (2, 52, 60) comprise at least one element from a group of system components (2, 52, 60) comprising the group: - at least one wastewater tank, - at least one water tank, - at least one fuel tank, - at least one component of a hydraulic system, - at least one electronic device, - at least one mounting frame for electronic devices, and - at least one component of an air conditioning system. [13] Aircraft (82) comprising an aircraft fuselage (4) with a primary structure, and at least one system module (9, 53, 61) connected to the primary structure in a section of the aircraft fuselage (4) according to claim 11 or 12.

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