Aircraft having drinking water system and method for installing drinking water system in aircraft

Abstract

An aircraft having a potable water system and a method for installing a potable water system in an aircraft, the potable water system enabling a monument to be connected to a pre-installed aircraft potable water interface through a customized conduit that is routed within a cable conduit, for example, directly along a seat track.

Description

Technical Field

[0001] The invention relates to an aircraft having a drinking water system and to a method for installing a drinking water system in an aircraft. Background Art

[0002] Typically, aircraft offer different locations for monuments such as galley and lavatory components. In standard locations, monuments are installed as standard in every aircraft. In dual locations, the monument locations are fixed, but the user can choose the installation of the monument or not. For example, if the user does not need the monument, seats can be installed in these locations. In flexible areas, the number, type and location of monuments can be selected individually by the user.

[0003] In order to supply fresh water to consumers such as washbasins in buildings, drinking water systems are provided. Drinking water systems are adapted to feed drinking water from drinking water tanks to consumers. In order to meet the different user requirements, the piping of drinking water systems is technically expensive. In addition, the piping limits the individual positioning of the building. Summary of the invention

[0004] The object of the present invention is to provide an aircraft having an improved drinking water system which enables a monument to be flexibly installed in an aircraft cabin, and a simplified assembly method of a drinking water system.

[0005] This object is achieved by an aircraft having the features of the present application and a method having the features of the present application. Advantageous embodiments are disclosed in the description and the drawings.

[0006] According to the invention, an aircraft has a drinking water system suitable for feeding drinking water from a drinking water tank to a consumer of a structure in the aircraft cabin. The drinking water system comprises at least one drinking water connection and at least one drinking water structure line. At least one drinking water connection is positioned in a floor panel of the cabin floor and is fluidically connected to the drinking water tank. At least one drinking water structure line extends between at least one drinking water connection and the consumer. At least one drinking water structure line is partially arranged over its length inside a cavity extending in the cabin floor or on top of the cabin floor. The respective direction of the cavity in the longitudinal direction or transverse direction of the aircraft depends on the position of the selected drinking water connection to the structure to be installed. When the drinking water structure line is arranged in the longitudinal direction of the aircraft, it is preferred to position the cavity along the tail of the seat. Positioning the cavity on top of the cabin floor allows the drinking water system to be modified.

[0007] According to the method for installing a drinking water system in an aircraft of the present invention, a drinking water interface is installed at a defined position, and the drinking water system is used to feed drinking water from a drinking water tank to a consumption device of a building in the aircraft cabin. Afterwards, the building is installed in the aircraft cabin and those drinking water interfaces are selected, which are necessary for a customized drinking water supply. Then, the consumption device of the building is connected to the selected drinking water interface via a drinking water building pipeline, and the selected interface is connected to the drinking water main line. Finally, the unselected drinking water interface is closed while meeting hygiene requirements, such as avoiding dead ends in the drinking water system. Alternatively, before the building is installed in the cabin, the interface required for the building installation is connected to the drinking water main line. In addition, the closing of the unselected interface can also be completed before the building is installed in the cabin.

[0008] The present invention enables a pre-installed drinking water interface (arranged at a predetermined position in the aircraft) to be combined with a customized pipe (drinking water construction pipeline). The drinking water interface can be used in a standard position, a dual position and in an elastic zone. If a construction is not installed at a certain position (positioning), the drinking water interface in the base plate is protected and closed by a cover. Each drinking water interface can be used to connect one or more constructions. If there are multiple constructions connected to the drinking water interface, the drinking water construction pipeline can be laid in the same direction or in opposite directions. In other words, the drinking water interface point can be located between constructions or consumer equipment. For example, the drinking water interface is connected in the middle of the elastic zone. By laying the customized pipeline in the cavity along (parallel to) the seat track, the customized pipeline is easy to install. An exemplary cavity is a so-called cable duct. This facilitates the installation of water pipelines during cabin decoration or modification. Only for a limited area (e.g., an elastic zone) or for the entire fuselage. An exemplary drinking water construction pipeline is a hose or a pipe and is suitable for use in a high pressure system with a working pressure greater than 5 bar. The drinking water connection is a quick connect / quick disconnect type, so it is easy to connect to a drinking water building pipeline.

[0009] In one embodiment, the cavity is on the same plane as the floor panel. In this way, the cavity is on the same level as the floor panel and can be covered by the carpet.

[0010] For ease of installation, the cavity may have a U-shaped form with a bottom and two opposite side walls. The cavity is open on its upper side so that drinking water construction pipelines can be easily laid.

[0011] In order to protect the drinking water monument line accommodated in the cavity from damage caused by passenger shoes, trolley wheels, etc., the cavity can be covered on its open upper side by a seat track cover. It is therefore advantageous if the seat track cover extends laterally above the cavity. In this case, a separate cover for the cavity is not necessary. The cover also serves as a coupling member for holding and / or fixing the drinking water monument line inside the cavity during flight operations.

[0012] At least one drinking water connection can be positioned in a recess in the cabin floor, which recess can be closed by a cover if the connection is not selected for building installation. The recess is adapted to enable a fluid-tight (air-tight and water-tight) seal. The cover is adapted to enable a flat cabin floor and to prevent contamination of the installed connection. Furthermore, the cover can also be provided in a fluid-tight design.

[0013] To avoid vibration or friction of at least one construction line inside the cavity, the construction line is fixed inside the cavity at a separate location. This can be done by a form fit or by releasable fastening means such as clips and brackets.

[0014] Due to safety requirements, it is preferred that the cavity and at least one cable duct adapted to accommodate electrical cables are located on opposite sides of the central seat track area. The central seat track is adapted to receive seat accessories. If water lines and electrical cables cross due to installation requirements, such as a water line changing in lateral direction, means are provided to meet safety requirements.

[0015] In one embodiment, at least one drinking water construction line is fed through the construction floor section. By means of this, an opening in the construction wall for feeding the drinking water construction line through is not necessary.

[0016] In another embodiment, at least one drinking water construction line is fed through the construction wall section. As a result, it is not necessary to provide an opening in the construction floor.

[0017] In another embodiment, at least one drinking water construction line is partially arranged inside the construction wall section. By means of this, no openings need to be provided in the construction floor, and the drinking water construction line is hidden. However, the drinking water construction line can also be partially arranged inside the construction floor section.

[0018] If a second drinking water monument line is provided, it can extend from the (first) consumer to the second consumer. By means of this, the drinking water monument line is annular.

[0019] Alternatively, a fluid coupling device is provided in at least one drinking water construction line, which is connected to a second drinking water construction line extending to a second consumer. By means of this, the overall length of the second drinking water line can be reduced compared to an annular design. An exemplary location for the fluid coupling device is the cavity.

[0020] Advantageously, a drinking water system, at least one drinking water main line and at least one drinking water branch line are provided. At least one drinking water main line and the drinking water branch line are suitable for feeding drinking water stored in a drinking water tank to at least one drinking water interface. At least one drinking water main line is laid out from the drinking water tank in a longitudinal direction and is positioned below the cabin floor in a central region of the aircraft. At least one drinking water branch line extends from at least one drinking water main line to at least one drinking water interface. Depending on the layout of the drinking water main line and the position of the enabled drinking water interface, the branch line can extend in a transverse direction, in a diagonal direction or only in a vertical direction. For example, if the main water line is positioned in the middle of the aircraft, the drinking water line also extends in a transverse direction. If the main drinking water line is positioned laterally, the main drinking water line can be positioned directly below at least one drinking water interface so that (essentially) only a vertical extension of the drinking water branch line exists. Due to this measure, ice formation of the drinking water system is prevented because all lines are laid out in a warm region of the aircraft. Therefore, anti-icing equipment for the drinking water line can be dispensed with by design. This will significantly reduce the complexity and weight of the drinking water system.

[0021] According to a preferred method, a plurality of aircraft sections of different aircraft are equipped with the same drinking water system. The drinking water system has the same interfaces at the same location. With this, aircraft sections with standardized drinking water systems are produced. The user can then individually and very flexibly select in which location - standard location, double location or flexible area - what type of monument should be installed. The interfaces required for the monument installation are then enabled, while the unselected interfaces are closed. BRIEF DESCRIPTION OF THE DRAWINGS

[0022] In the following, preferred embodiments of the present invention are explained with reference to the accompanying drawings. It should be understood that various elements and components are depicted only as examples and may be optional and / or combined in a manner different from that depicted. Reference numerals for relevant elements are used comprehensively and are not necessarily defined again for each of the accompanying drawings. Schematically shown in the following figure:

[0023] Figure 1 : Cabin layout with exemplary inventive drinking water system;

[0024] Figure 2 : Top view of the installed drinking water connection;

[0025] Figure 3 : Protected by a cover Figure 2 Installed drinking water connection shown;

[0026] Figure 4 : Figure 1 A cross-sectional view of the forward fuselage region shown in;

[0027] Figure 5a : Cross-sectional view of the fuselage in the area of ​​the building;

[0028] Figure 5b : A cross-sectional view of the fuselage in the area of ​​the building, illustrating different arrangements of the drinking water mains;

[0029] Figure 6 : Detailed top view of the seat track and drinking water connection;

[0030] Figure 7 : A detailed cross-sectional view of the drinking water construction line in a cavity parallel to the seat rail and its fluid connection to the drinking water main line;

[0031] Figure 8 : Alternative positioning of drinking water structure cavities;

[0032] Fig. 9 : The drinking water building pipeline passes through the ring layout of the building floor opening;

[0033] Fig.10 : Alternative layout of drinking water building pipelines based on building floors;

[0034] Fig.11 : The layout of drinking water building pipelines along the building wall;

[0035] Fig.12a : The routing of drinking water building pipelines inside building walls; and

[0036] Figure 12b : Routing of drinking water building pipelines inside a building wall, illustrating alternative locations for fluid connections. DETAILED DESCRIPTION

[0037] exist Figure 1 In FIG. 1 , the cabin layout of a single-aisle passenger aircraft and the drinking water (distribution) system 1 of the present invention are shown. Here, the cabin 2 has three different types of monument locations - standard location 4, double location 6 and flexible area 8. The standard location 4 is in front of the first cabin door 10 in the front fuselage and behind the rear cabin door 12 in the rear fuselage. The locations of monuments 14 such as galleys and toilets are fixed, and the types of monuments 14 can be changed according to the needs of the user.

[0038] In the dual position 6, the monument position is fixed, but the user can choose to install or not. For example, if the user does not need a monument, the seat 16 can be installed in these positions.

[0039] The number, type and position of the monuments 14 in the elastic zone 8 can be selected individually by the user. The user can select individual positions of the monuments at least in the longitudinal direction of the aircraft (e.g., at one-inch intervals). In the example shown, the elastic zone 8 is located in the front area of ​​the cabin 2 between the first door 10 and the central wing box (not shown).

[0040] In the embodiment shown, the drinking water system 1 comprises a drinking water tank (tank) 20 and a water distribution pipe network system (pipeline). Drinking water is stored in the water tank 20 in the rear fuselage and is distributed to the cabin monument 14 by means of the water distribution pipe network system. However, multiple tanks 20 can also be provided, which are positioned in different positions in the aircraft, for example, in the front section or in the middle section. The pipe network system comprises at least one drinking water main line 22 (main line), multiple drinking water branch lines 24 (branch lines), multiple drinking water interfaces 26 (interfaces) and multiple drinking water monument pipelines 28 (monument pipelines).

[0041] The main line 22 extends in the longitudinal direction of the aircraft. The main line 22 is connected to the box 20 and is laid to the aircraft skin 30 or to other cold areas at a sufficient distance so that no anti-icing equipment is required. For example, the main line 22 is positioned below the cabin floor 32 in the central area of ​​the fuselage.

[0042] By means of branch lines 24, drinking water is distributed to the connections 26. In the embodiment shown, the branch lines 24 extend in the transverse direction and in the vertical direction below the cabin floor 32. Each branch line 24 is fluidically connected to one drinking water connection 26. However, if Figure 1 If the interface 26 is positioned vertically above the main line 22, the branch line 24 has only vertical components (not shown because they are hidden by the interface 26). Figure 5b Such an arrangement is shown in .

[0043] The interfaces 26 are of the quick-disconnect type and are positioned in the cabin floor 32. Each interface 26 is fluidly connected to a drinking water monument line 28 via a branch line 24. The monument line 28 is at least partially laid along the seat rails 36 in the longitudinal direction inside the cavity 34 over its length. The monument line 28 is fluidly connected to a consumer 38 of the building 14, such as a wash basin.

[0044] The standard position 4 and the double position 6 can be equipped with an interface 26 for the elastic zone 8. This makes the production process easy and enables a standardized monument design. However, in this case, as explained below, the arrangement in the cavity 34 close to the seat rail 36 is not preferred. The monument 14 can then be positioned directly in the receiving interface 26 (interface box, see Figure 2 ) on the top of the bottom plate recess 42.

[0045] Preferably, the main line 22 , the branch line 24 and the interface 26 are preassembled in the fuselage and at fixed positions in the nacelle floor 32 , respectively, while the monument line 28 is subsequently installed according to the needs of the individual user.

[0046] Preferably, only nacelle positions 4 , 6 are provided for standard monument positions and duplicate monument positions, the monument 14 being connected to the main line 22 via a secondary distribution line 40 which is already installed as standard during assembly.

[0047] Furthermore, only the cabin positions 4 , 6 of the standard monument position and the duplicate monument position are provided, the monument 14 being connected to the main line 22 via a secondary distribution line 40 which is already installed as standard during assembly.

[0048] exist Figure 2 and Figure 3 , a detailed view of the interface 26 is shown. The interface 26 is positioned in a recess 42 of the cabin floor panel 43 and is positioned close to the seat track 36. The recess 42 is open towards the cabin 1 and can be closed by a cover 44 to form a smooth cabin floor 32. The recess 42 is designed to be watertight and airtight to the underfloor area in order to avoid smoke from underfloor entering the cabin 2 in the event of a fire and to avoid water entering the underfloor area in the event of a leak. The fluid-tight design can be additionally supported by the cover 44.

[0049] The monument line 28 is fed to the cavity along the seat rail 36 through a channel 46, which is also closed by a cover 44. The interface 26 is of the quick disconnect type and is installed in a fixed predetermined position. If no monument 14 is installed at a certain position, the corresponding interface 26 is closed, while meeting hygiene requirements, for example, avoiding dead spots in drinking water systems.

[0050] If there are multiple monuments 14 connected to one interface 26, the monument lines 28 can be laid in the same or opposite directions. In other words, the interface 26 can be located in the middle of the elastic zone 8, so that some monuments 14 are located behind the interface 26 and some other monuments 14 are located in front of the interface 26.

[0051] exist Figure 4 , Figure 5a , Figure 5b and Figure 6 , a more detailed view of the drinking water system 1 of the invention is shown. Here, a toilet 14 is provided, the wash basin 38 of which should be connected to the drinking water system 1. The toilet 14 is positioned laterally on the left side of the cabin 1 in the direction of flight.

[0052] As previously mentioned, the main line 22 is positioned below the cabin floor 32 in a fuselage region characterized by an ambient temperature that prevents the drinking water from freezing. Figure 4 , Figure 5a and Figure 6 , for example, the central area of ​​the fuselage is selected. The branch line 24 extends between the main line 22 and the interface 26 below the cabin floor 32 in the transverse direction and in the vertical direction. Figure 5b As shown, if the interface 26 is positioned directly above the main line 22, the branch line 24 extends in the vertical direction only below the nacelle floor 32 between the main line 22 and the interface 26. Such an arrangement may be given, for example, when the main line 22 is laid more laterally.

[0053] Refer again Figure 4 , Figure 5a , Figure 5b and Figure 6 , the interface 26 is located close to the seat track 36 in the cabin floor 32. The monument line 28 extends from the interface 26 to the wash basin 38. Thereby, the monument line 28 is accommodated in the cavity 34 parallel to the seat track 36 and then routed to the wash basin 38.

[0054] To prevent the drinking water in each interface 26 and each monument line 28 from freezing, they are also positioned / routed in warm areas of the fuselage. For example, the monument lines 28 are not routed in the space between the outer aircraft skin 30 and the inner cabin lining 48 .

[0055] like Figure 5a and Figure 5b As already shown in Figure 7 As shown in more detail in FIG. 1 , in a preferred embodiment, the longitudinal cavity 34 for the building pipeline 28 is positioned in the same plane as the floor panel 43. In the vertical direction, the cavity 34 does not extend above the floor panel 43. Thus, a flat floor panel top is achieved. Preferably, the cavity 34 and the floor panel 43 are both positioned on the lateral seat track flange 50 and have the same height.

[0056] The cavity 34 has a U-like shape with a bottom 52 and two parallel side walls 54, 56. The cavity is open at its top. After the building line 28 is installed, the cavity 34 is covered by the cabin floor carpet 58 and is additionally protected by a seat track cover 60 to prevent damage from the top, for example by shoes or trolley wheels.

[0057] The exemplary cavity 34 is a so-called cable duct. To meet safety requirements, the building duct 28 and the cable duct 62, which is usually used for the cables 64, are spaced apart from each other. For example, the building duct 28 and the cables 64 are laid on opposite sides of a central area 66 of the seat track 36, which is suitable for receiving seat accessories (not shown).

[0058] Preferably, the monument line 28 is fixed in the cavity by form fit and / or seat track cover 60. Additionally, the drinking water line can be attached / fixed in the cavity 34 by using clips, brackets, etc. at separate locations (e.g., 20 cm apart) to prevent vibration or friction. Expansion of the monument line 28 in the longitudinal direction is generally possible.

[0059] exist Figure 8 In FIG. 4 , an alternative embodiment of the cavity 34 is shown. In this embodiment, the cavity 34 is not located in the same plane as the floor panel 43, but is located on the floor panel 43. This embodiment relates to retrofitting. It enables retrofitting of the aircraft without replacing the floor panel 43. This variant is also suitable for areas where an integrated cable duct 62 is not available for water lines.

[0060] Since the cavity 34 (cable duct) is positioned on the floor panel 43, the cavity 34 is not covered by the floor carpet 58 or the seat track cover 60. Therefore, in order to protect the building wiring 28 (and the cables 64) from damage, the cavity 34 / cable duct 62 has their own cover 68, which is connected to the bottom 52 of the cavity 34 via a form-fitting engagement.

[0061] like Figures 9 to 12a and Figure 12b As shown, several options are available for routing the monument lines 28 out of corresponding cavities 34 inside the monument 14 and in particular to consumers 38 .

[0062] exist Fig. 9 and Fig.10In the present invention, the monument pipeline 28 is fed through an opening 70 in a monument floor section 72. The main line 22 can be routed to each longitudinal (x position) within the corresponding nacelle position, for example the elastic zone 8. The length of the monument pipeline 28 between the interface 26 and the monument 14 can be configured individually (for example, by the trim-fit principle or by pre-configured hose elements). A plug 74 with a funnel shape installed in the monument floor section 72 provides a watertight entrance from the cavity 34 to the monument 14. A dam or wall can be arranged around the floor entrance to avoid stagnant water from permanently contacting the seal.

[0063] In order to connect multiple buildings 14, Fig. 9 34 shows a loop through the building line 28. This means that inside the cavity 34 along the seat track 36, the first building line 28 is fed to the first consumer and the second building line 28b is fed from the first consumer to the second consumer. Thus, the first building line 28 and the second building line 28b can be fed through one common opening in the cabin floor 32 (as shown), or alternatively, the first building line 28 and the second building line 28b are fed through a single floor opening.

[0064] exist Fig.10 , an alternative to the annular design is shown. Here, a T-joint 76 is provided in the first construction line 28, which serves as a fluid coupling device. The T-joint is positioned inside the cavity 34. The T-joint provides a fluid connection point for the second construction line 28b extending in the cavity 34 and being fluidically connected to the second consumer.

[0065] In accordance with Fig.11 In the embodiment of the present invention, the building pipeline 28 is not inserted from below through the building floor section 72 (such as Fig. 9 and Fig.10 ), but rather inserted laterally through an opening 78 in a building wall section 79. Here, the building line 28 in the cavity 34 is routed from the interface 26 directly through a funnel 80 of the building wall to the consumer 38 in the building 14.

[0066] Alternatively, if Fig.12a As shown, the building line 28 in the cavity can be routed from the interface 26 via a separate connection point 82 behind the building skirting 83 to the water consumer 38 in the building 14. Fig.12a As shown, the connection point 82 can be located inside the structure wall 79. Figure 12b In the illustrated embodiment, the connection point 82 is positioned inside the nacelle floor 32 , for example within the cavity 34 .

[0067] In the following, a method for installing a drinking water system 1 in an aircraft is described, the drinking water system 1 for feeding drinking water from a drinking water tank 20 to consumers 38 of a monument 14 in the aircraft cabin 2. Likewise, the drinking water system 1 enables the monument 14 to be connected to a pre-installed aircraft drinking water connection 26 via a custom-made pipe 28, which is laid, for example, directly along the seat track 36 in a cable duct 34, 62. All parts of the drinking water distribution network system, such as the drinking water main line 22 as well as the drinking water branch lines 24, the drinking water connection 26 and the drinking water monument line 28, are laid in the warm fuselage area.

[0068] In a first step, the main line 22 is installed. Then, locations for drinking water connections 26 are installed in the cabin floor 32 at their defined locations. Afterwards, the monument 14 is installed in the aircraft cabin 2. The desired connection 26 is selected and at least one consumer 38 of the monument 14 is connected to the selected connection 26 via the monument line 28 and to the main line 22 via the branch line 24. The unselected connections 26 are closed. Likewise, the unselected closed connections 26 meet hygiene requirements, for example, to avoid dead spots in the drinking water system.

[0069] Alternatively, before the monument 14 is installed in the nacelle 2, the interfaces 26 required for the monument installation are connected to the drinking water main line 22. In addition, the closing of the unselected interfaces 26 can also be completed before the monument 14 is installed in the nacelle 2.

[0070] For the purpose of completeness, it is pointed out that the fastening devices and coupling devices such as elbows, clamps, brackets, sleeves and control devices such as valves required for installing the fluid pipe network system including hoses and pipes are not shown. For example, in order to avoid a large bending radius of the construction pipeline 28, the construction pipeline 28 can be divided into a plurality of sections, some of which are in fluid connection via elbows.

[0071] An aircraft and an installation method are disclosed having a drinking water system that enables a monument to be connected to a pre-installed aircraft drinking water connection via a custom-made conduit that is routed, for example, directly along a seat track within a cable duct.

Claims

1. An aircraft having a drinking water system (1), the drinking water system (1) being adapted to feed drinking water from a drinking water tank (20) to a consumer (38) of a monument (14) in an aircraft cabin (2), the drinking water system (1) comprising: at least one drinking water connection (26); as well as at least one drinking water construction pipeline (28); wherein the at least one drinking water connection (26) is positioned in the cabin floor (32) and is fluidically connected to the drinking water tank (20); wherein the at least one drinking water construction line (28) extends between the at least one drinking water connection (26) and the consumer (38); and in, The at least one drinking water construction line (28) is partially arranged over its length inside a cavity (34) which extends in the cabin floor (32) or on top of the cabin floor (32).

2. The aircraft according to claim 1, wherein: The cavity (34) is positioned on the same plane as the floor panel (43).

3. The aircraft according to claim 1 or 2, wherein: The cavity (34) has a U-like shape having a bottom (52) and two opposing side walls (54, 56).

4. An aircraft according to claim 1, 2 or 3, wherein: A seat track (36) mounted cover (60) extends laterally over the cavity (34).

5. An aircraft according to any one of the preceding claims, wherein: The at least one drinking water connection (26) is positioned in a recess (42) in the cabin floor (32), the recess (42) being closable by a cover (44).

6. An aircraft according to any one of the preceding claims, wherein: The at least one construction line (22) is secured inside the cavity (34) at a separate location.

7. An aircraft according to any one of the preceding claims, wherein: The cavity (34) and at least one cable duct (62) adapted to receive a cable (64) are positioned on opposite sides of a central seat track region (66).

8. An aircraft according to any one of the preceding claims, wherein: The at least one drinking water monument line (28) is fed through a monument floor section (72).

9. An aircraft according to any one of claims 1 to 7, wherein: The at least one drinking water monument line (28) is fed through a monument wall section (79).

10. An aircraft according to any one of claims 1 to 7, wherein: The at least one drinking water construction line (28) is partially arranged inside a construction wall section (79) or inside a construction floor section (72).

11. An aircraft according to any one of claims 7 to 10, wherein: A second drinking water monument line (28) is provided, which extends from the consumer (38) to a second consumer.

12. An aircraft according to any one of claims 7 to 10, wherein: A fluid line coupling device (76) is arranged in the drinking water monument line (28), and is connected to a second drinking water monument line (28b) extending to a second consumer.

13. An aircraft according to any one of the preceding claims, wherein: At least one drinking water main line (22) and at least one drinking water branch line (24) are provided; wherein the at least one drinking water main line (22) and the drinking water branch line (24) are suitable for delivering the drinking water stored in the drinking water tank (20) to the at least one drinking water interface (26); wherein the at least one drinking water main line (22) is laid from the drinking water tank (20) in the longitudinal direction and is positioned below the cabin floor (32) in the central region of the aircraft; and The at least one drinking water branch line (24) extends from the at least one drinking water main line (22) to the at least one drinking water connection (26).

14. A method for installing a drinking water system (1) in an aircraft, the drinking water system (1) feeding drinking water from a drinking water tank (20) to consumers (38) of a monument (14) in a cabin (2) of the aircraft, the method comprising the following steps: a. installing the drinking water interface (26) in the cabin floor (32) at a defined position of the drinking water interface (26); b. installing the structure (14) in the aircraft cabin (2); c. connecting the consumer equipment (38) of the building (14) to the selected drinking water connection (26) via the drinking water building pipeline (28); d. connecting the selected drinking water interface (26) to the drinking water main line (22); and e. closing the unselected drinking water interface (26); Wherein, step d) and step e) can be completed before step b).

15. The method according to claim 14, wherein: A plurality of aircraft sections of different aircraft are equipped with the same drinking water system (1), which has the connection (26) at the same location (4, 6, 8).

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