Pivotal folding seat for cabin crew

Abstract

The invention relates to a seat assembly (12) for a passenger cabin (4) of an aircraft (2), containing a holding wall (14) which is permanently secured to the base structure (10) of the aircraft (2) and a seat (16) for the cabin crew (40), said seat being secured to the holding wall (14) solely by a rotational axis (24, 48) and being rotatable by 30° to 300° between two end positions (EP2) and between seat positions (SP1-3) in which a sitting position (SS) of a seat surface (18) of the seat (16) is facilitated. An aircraft (2) contains the base structure (10), the passenger cabin (4), and the seat assembly (12) with the permanently secured holding wall (14) in the intended installation state (M), wherein the seat (16) can be rotated about each of the rotational axes (24, 48) between the two end positions (EP1, 2) and between the seat positions (SP1-3), and the sitting position (SS) of the seat surface (18) is facilitated in each of the seat positions (SP1-3).

Description

[0001] Swiveling folding seat for cabin crew

[0002] The invention relates to a folding seat for cabin crew, such as flight attendants.

[0003] EP 0268 749 A1 discloses a vehicle seat constructed as a double seat, particularly a seat for aircraft flight attendants. The seat consists of a frame made of double spars and cross members, with folding seats arranged on both sides.

[0004] The object of the present invention is to propose improvements with regard to a folding seat for cabin crew.

[0005] The object of the invention is achieved by a seat arrangement according to patent claim 1. Preferred or advantageous embodiments of the invention as well as other categories of invention emerge from the further claims, the following description and the attached figures.

[0006] The seating arrangement is that of a passenger cabin of an aircraft. "Aircraft" refers to all types of aircraft that typically fly with cabin crew and therefore require seating, especially a folding seat, for cabin crew during normal operation, especially passenger aircraft.

[0007] The seat assembly includes a retaining wall that can be permanently attached, at least directly or indirectly, to a basic structure of the aircraft. The attachment refers to a proper assembly state of the seat assembly in the (proper) passenger cabin. In other words, in this assembly state, the retaining wall is permanently attached to the basic structure of the aircraft. "Proper assembly" means that the seat assembly is structurally matched to a specific or a specific type of aircraft or passenger cabin and is configured for use there; e.g., it is designed for the resulting geometric, material, and system requirements, etc. In other words, a particular aircraft or passenger cabin is assumed to be known with regard to its geometry, size, material properties, etc.

[0008] The seating arrangement includes a cabin crew seat. The retaining wall is designed to serve as a support for the seat, thus meeting the mechanical requirements for this. The seat includes a seat cushion. The seat cushion can be folded between a sitting and a resting position. In the resting position, the seat cushion is stowed away on the seat to save space. In the sitting position, the seat is suitable for a member of the cabin crew (in particular, the CA, Cabin Attendant) to sit on the seat or seat cushion.

[0009] The seat is attached to the support wall by means of at least, and in particular precisely, one pivot axis (which also means a supporting device similar to a swivel joint). The seat is permanently attached exclusively via this pivot axis; thus, there is no other permanent mechanically supporting connection between the seat and the support wall. At most, support mounts / support elements exist (see below); however, these do not interact permanently, but at most temporarily. The pivot axis runs vertically in the intended assembly state, where "vertical" refers to the state of the aircraft when it is at rest on a level surface, for example, in a parking position at an airport. In other words, the pivot axis runs perpendicular to the floor of the passenger cabin or aircraft.

[0010] The following applies to each of the axes of rotation: The seat can be rotated about the respective axis of rotation between a first and a second end position. In other words, the seat can be rotated about the axis of rotation between the two end positions. The end positions define the angular range of the possible rotation. All of this applies primarily in the intended assembled state, i.e. in the aircraft, see below. In the assembled state, the seat can be rotated relative to the retaining wall or the rest of the passenger cabin or the rest of the aircraft about the axis of rotation, about the vertical axis of rotation, by the angular range between the end positions (inclusive). The two end positions are offset from each other by the angular range. Possible angular ranges are between a minimum of 30° and a maximum of 300°. In other words, the seat can be rotated about the axis of rotation between the two end positions by an angle between 30° and 300°. The seat cannot be rotated any further beyond the end positions.The angular range is, in particular, 90°, in particular 180°, or in particular 270°. Different angular ranges can be available for different rotation axes. In particular, two rotation axes are provided: one has an angular range of 270° with the stowed position, the other an angular range of 90°. With two rotation axes, one must always be released so that the seat can rotate about the other rotation axis.

[0011] Each of the pivots can be designed as a single continuous pivot hinge or as at least two aligned partial hinges. The hinges can be exposed or fully or partially incorporated / integrated into the seat and / or the retaining wall.

[0012] The seat can also be rotated about the axes of rotation between at least, in particular exactly, two seating positions. The seating positions therefore lie within the angular range, at most at the corresponding end positions. In particular, the seating positions are offset from one another by 90° or 180°. The seat surface can be positioned in a sitting position in each of the seating positions. This also applies in particular in the assembled state, i.e. in the aircraft with the seating arrangement installed. Thus, in all seating positions, the seat can actually serve as a seat for members of the cabin crew (with the seat surface in the sitting position). In other words, in the seating positions, it is particularly possible to fold the seat surface between the resting position and the sitting position. In particular, two seating positions are possible with respect to at least one of the axes of rotation. Rotation about just one of the axes of rotation therefore already allows two different seating positions to be assumed.

[0013] In particular, the seat comprises a seat structure, and the partition comprises a wall structure of a supporting structure, as known from the subsequently published German patent application DE 102022 108421.3 of Diehl Aviation Hamburg GmbH. In other words, the seat and retaining wall form an integrated arrangement of a partition (also called a "partition") and a seating arrangement (CAS) similar to the "integrated CAS partition" or "iCAS partition" described therein. The fact that the seat can actually be used for sitting in at least two rotational positions, namely the seating positions, results in a particularly flexible use option for the seat. In particular, the seat can always be used for sitting by cabin crew during every phase of the flight.

[0014] In a preferred embodiment, at least one of the seating positions is one of the end positions. Thus, in particular, in one of the end positions, the seat can actually be used for seating by cabin crew.

[0015] In a preferred variant of this embodiment, two of the seating positions are the two end positions. Thus, the seat can actually be used by cabin crew in both end positions.

[0016] In a preferred embodiment, the seat can be rotated about the rotation axis into at least one stowed position. In the stowed position, the seat surface cannot be in the sitting position. In the stowed position, cabin crew cannot actually use the seat for sitting. Instead, the seat surface can be in the rest position, in particular exclusively in the rest position, allowing the seat to be stowed in a particularly space-saving manner. In addition to two possible seating positions, the seat can also be stowed in a space-saving manner upon request or when necessary.

[0017] A preferred variant of this embodiment cannot be combined with the above-mentioned embodiment, in which two seating positions assume the end positions: In this embodiment, one of the storage positions is also one of the end positions. This end position is then no longer considered a seating position. However, this ensures that the storage position is also reached immediately by fully pivoting / rotating the seat to the end position.

[0018] According to a preferred embodiment, an alternative to the stowed position is provided; in this embodiment, therefore, no stowed position is provided. In this embodiment, the sitting position of the seat surface is possible in every rotational position of the seat between the end positions. This again applies in particular in the assembled state, i.e. in the aircraft. The two end positions are included here. In this embodiment, therefore, there is no stowed position. Thus, all rotational positions are available for sitting positions. This means that the seat can be used by cabin crew for actual sitting in all rotational positions. As a rule, however, only certain rotational positions are used for sitting, which then correspond to dedicated sitting positions. This is particularly due to appropriate support by support elements / support receptacles and / or locking by locking elements in the corresponding sitting positions, see below.This design also applies especially in the assembled state, i.e. when installed in the aircraft.

[0019] In a preferred embodiment, the seat is located in one of the seating positions parallel to the retaining wall and in front of the retaining wall. "Parallel" means that the seat or its backrest / rear part is aligned parallel to a plane of extension of the retaining wall. "In front of the retaining wall" means that a sitting direction or a straight-ahead viewing direction of a person sitting directly forward on the seat is directed perpendicular to the plane of extension of the retaining wall, away from the retaining wall. The seat or the seat surface or the corresponding viewing direction is thus facing away from the retaining wall. In other words, the retaining wall is located "behind" a person sitting directly on the seat. In this seating position, the seat is thus arranged on the retaining wall in a space-saving manner and in the manner customary in practice.

[0020] In a preferred embodiment, the retaining wall is a partition for the passenger cabin, or the retaining wall is a wall section of a monument for the passenger cabin, such as a lavatory (toilet), a galley (kitchen), or a closet. By attaching a corresponding swivel seat to the retaining wall, the partition or monument is assigned a corresponding holding function for the seat. Furthermore, the retaining wall then fulfills a dual function, namely that of a partition or a wall of a monument.

[0021] In a further preferred embodiment, in which the retaining wall is a partition, the partition has a first wall section and a second wall section. The two wall sections are separated by an opening. The opening is therefore located between the two wall sections. The seat can be rotated into an end position in which it is arranged in the opening. This applies at least when the seat surface is folded out, i.e. in the sitting position. The two wall sections are arranged in alignment along an axis. The two wall sections can also be formed by wall sections of different monuments. When the partition is installed as intended in the aircraft, with the axis arranged transversely to the aircraft's longitudinal direction or direction of flight, the opening serves to form a passage in the aircraft. The axis of rotation is preferably attached to the first wall section of the partition and thus to the retaining wall.

[0022] A first end position coincides in particular with a first seating position. In the first seating position, the seat is parallel to the retaining wall and thus to the partition and its first wall section. Furthermore, the seat is located in front of the retaining wall or partition and first wall section. This means that a person sitting on the seat with the seat surface in the sitting position in the first seating position has the retaining wall or partition and thus the first wall section behind them. This first seating position can already be a TTL observation position. This means that during the taxi, takeoff and landing (TTL) phases of flight, a cabin crew member sitting on the seat has a clear view of passengers in the passenger cabin in the x-direction, i.e. the direction of flight.

[0023] The seat can be rotated from this first end position about the axis of rotation into a second end position, wherein the two angular positions of the two end positions are offset by an angle of 180°. The axis of rotation is arranged and fastened to the first wall section in such a way that by rotating the seat about the axis of rotation, the seat can be rotated into a second end position in which the seat is arranged in the opening. In this second seating position, which coincides with the second end position and represents a further TTL position, a person sitting on the seat can look in the opposite direction compared to the first seating position. In the intended state, the person sitting in the opening can look along an aisle in the aircraft. This type of design ensures that a CAS can be used flexibly while simultaneously reducing the overall weight.

[0024] In a preferred embodiment, the seat arrangement comprises at least one locking element. The locking element is designed to lock the seat in at least one of the end positions and / or sitting positions and / or - only in the event that the embodiment of a stowed position is implemented according to the above - stowed positions. It is not excluded that the locking element can also additionally lock the seat in other rotational positions or in another way. This prevents, in particular, accidental or unintentional pivoting of the seat when the locking element is locked. In particular, in the embodiment described above with the partition having a first wall section and a second wall section, the seat arrangement can comprise two locking elements. The seat can be locked in the first end position using a first locking element.The first locking element is in particular arranged on the first wall section or is integrated into it. The seat can be locked in the second end position using the second locking element. The second locking element is in particular arranged on the second wall section or is integrated into it. The second locking element can also have an emergency release mechanism. This serves to quickly unlock the seat in an emergency and thus rotate it out of the second end position so that the opening between the two wall sections can be exposed. This opens up an escape route. In addition, a self-unlocking mechanism can be provided in this second end position, with the help of which it is possible for the second locking element to also be unlocked when the seat surface is folded up.Conversely, a self-locking mechanism can also be present, so that when the seat is folded down, the second locking element and thus the seat are automatically locked in the second end position or sitting position. In other words, the seat serves as the actuating element for the locking element. The seat can be locked or unlocked using the seat.

[0025] In a preferred embodiment, the seat arrangement comprises at least one support receptacle, in particular two support receptacles. The support receptacle is attached to the retaining wall, in particular the partition wall, or formed by it. In the above-described embodiment of the partition wall having a first wall section and a second wall section, a first support receptacle can be attached to the first wall section and a second support receptacle can be attached to the second wall section or formed by it, or can also be integrated into the respective wall sections.

[0026] Furthermore, the seat can have a support element. With the support element, the seat is supported or can be supported on at least one of the support receptacles, particularly in at least one of the end positions and / or seating positions and / or - if present - the stowed positions - particularly with respect to an x-load and / or a z-load. The x-direction is the straight-ahead flight direction of the aircraft, while the z-direction is a vertical direction when the aircraft is at rest on level ground. The support receptacle can support the seat's load relative to the retaining wall.

[0027] The object of the invention is also achieved by an aircraft according to patent claim 13. The aircraft is one as mentioned above and contains the above-mentioned basic structure and the above-mentioned passenger cabin. The aircraft also contains the seat arrangement according to the invention. The seat arrangement is located in the above-mentioned intended assembly state in the passenger cabin or in the aircraft. The retaining wall is therefore permanently attached to the basic structure of the aircraft. The seat is rotatable about each of the rotation axes between the two end positions and between the seating positions, and the seating position of the seat surface is possible in each of the seating positions.

[0028] The aircraft and at least some of its possible embodiments as well as the respective advantages have already been explained in connection with the seat arrangement according to the invention.

[0029] In a preferred embodiment, the seat is attached to the base structure exclusively via the retaining wall. This attachment is again made directly or indirectly. There is therefore no other permanent and rotatable attachment of the seat to the base structure besides the attachment via the retaining wall. In other words, the seat is attached (directly or indirectly) exclusively to the retaining wall and only this is attached (directly or indirectly) to the base structure. However, temporary additional attachments, such as a support or locking device (see below), are particularly conceivable. This eliminates the need for an additional permanent attachment of the seat to the base structure, e.g., to a floor of the passenger cabin.

[0030] In a preferred embodiment, one of the seating positions is a TTL (Taxi Takeoff Landing) observation position for the passenger cabin. In particular, this observation position is a second seating position relative to the aforementioned other seating position with the retaining wall at the back. During these critical TTL flight phases, it is aeronautical regulations that every passenger seat in a passenger aircraft is under constant visual observation by cabin crew. This TTL requirement can be met by selecting the appropriate seating position. Likewise, the seat can be used in a different seating position during further flight phases. Preferably, two seating positions, each of which coincides with one of the end positions, constitute a TTL observation position. In a preferred embodiment, the aircraft contains at least one locking element. In particular, the locking element is part of the seating arrangement.The locking element is designed to lock the seat in at least one of the end positions and / or sitting positions and / or—only in the case where the embodiment of a stowed position is implemented as described above—stowage positions. It is not excluded that the locking element can also additionally lock the seat in other rotational positions or in another way. This prevents, in particular, accidental or unintentional pivoting of the seat when the locking element is locked.

[0031] In a preferred embodiment, the aircraft contains at least one support mount. The support mount is also at least indirectly attached to the base structure. The support mount can also be part of the seat arrangement. The attachment then occurs in the intended assembled state. In particular, the support mount is permanently attached to the base structure. The seat has a support element. With the support element, the seat is supported or can be supported on at least one of the support mounts, particularly in at least one of the seating positions - particularly with respect to an x-load and / or a z-load. The x-direction is the straight-ahead flight direction of the aircraft, the z-direction a vertical direction when the aircraft is at rest on level ground. The support mount can be used to support the seat load with respect to the base structure of the aircraft.The load therefore does not have to be absorbed exclusively by the pivot axis and the retaining wall. The pivot axis can thus be designed to be mechanically less stable and thus less complex and cost-effective. In particular, multiple support mounts can be provided, for example, one for each of the seating and / or end and / or stowage positions, the latter if present. In particular, the support mount is part of an aircraft installation element, for example, a monument, a row of seats, a storage compartment, etc. In other words, the installation component contains or forms the support mount.

[0032] Alternatively or additionally, the seat can also be supported in the end positions and / or stowed positions via the support elements / support mounts.

[0033] In a preferred variant of this embodiment, the retaining wall contains at least one of the support receptacles or the retaining wall forms at least one of the support receptacles. In particular, this allows the seat to be supported in the seating position that results when the seat is arranged in front of the retaining wall, as explained above.

[0034] The invention is based on the following findings, observations, and considerations and also includes the following preferred embodiments. These embodiments are sometimes referred to as "the invention" for simplicity. The embodiments may also contain parts or combinations of the above-mentioned embodiments or correspond to them and / or may also include previously unmentioned embodiments.

[0035] According to the invention, in particular, a rotating seat for cabin crew is provided, integrated into a partition or other walls and monuments in the aircraft.

[0036] The invention is based on the following idea: An i-CAS partition, as known from the aforementioned patent application, combines two classic functions into one (partition + CA seat, CA: cabin attendant). The present invention extends the concept to include a swivel CAS (cabin attendant seat) for the cabin crew. Furthermore, the principle is applicable to any form of monument, partition, or other installation.

[0037] The invention is based on the following observation: Today's swivel CASs are mounted on the aircraft floor and can usually only be rotated 90°. Furthermore, they can only be used during specific flight phases (TTL: takeoff, landing, taxi) and do not provide a resting seat during cruise flight.

[0038] The seats are installed independently of any partition walls or monuments. This means that the load is not shared with other fixtures but is fed directly into the floor. They are not usable during cruise flight because they obstruct cabin flow, such as access to the lavatory.

[0039] A key driver for these seats is the "Direct View" criterion, which requires the cabin crew to have a clear view of all passengers from their seats during critical flight phases. A camera system provides an alternative solution for "Direct View." The basic idea of ​​the invention is to develop a way to integrate the Swivel CAS into partition walls and monuments, thus creating a "Direct View" option (direct visual observation of passengers during TTL). The new i-CAS partition design (monolithic aluminum-metal construction) should be used. The seat should be usable during taxiing, takeoff and landing, as well as during normal flight.The development of this design offers significant cost savings and weight reduction potential compared to the established solution, and offers usability during all flight phases, eliminating the need for a separate seat during normal flight (further weight and cost reduction). Furthermore, this compact design allows for more space in the aircraft's longitudinal direction.

[0040] The invention is based on the observation that the partition, or usually the monument, and the seat are separate components. For actual use and to achieve the "direct view," the seat, which can usually be swiveled 90°, is mounted on the floor independently of other components. The partitions and monuments are manufactured in a composite construction from metal-reinforced honeycomb panels with pre-impregnated fiber matrix prepregs. Alternatively, a camera system is used to fulfill the "direct view" criterion.

[0041] According to the invention, the structural components of the seat, including the entire mechanism for rotating the seat by up to 180°, are integrated into the structure of the partition wall in a so-called integral design. The CA seat, as a separate product, is thus eliminated. An integral component is created that exhibits the distinctive features of both previously separate products. When rotated, the seat rests on the opposite side against a partition wall, monument, or similar structure (support element / support mount). This absorbs forces in the x- and z-directions. This enables further weight reduction.

[0042] In combination, the new design allows for a reduction in overall weight and structural depth while maintaining maximum deformation under load. This applies to the partition wall or the monument, regardless of whether one or more additional CA seats are integrated. Furthermore, a reduction in manufacturing costs is possible.

[0043] The separation between the CAS and monument / partition wall etc. products is thus dissolved. There is one integrated product that combines the CAS and monument / partition wall etc. functions. This is the case with the standard i-CAS solution. What is new about the standard i-CAS solution is that one of the seats is rotatable. The rotation can be achieved through any angle range up to 270 degrees. The viewing direction in the rotated position can be both in the direction of flight and against the direction of flight, depending on the application. The CAS can be used as a fully-fledged CAS in the non-rotated position, depending on the application. This enables flexible application. The solutions reduce weight compared to current solutions and offer at least 1 inch more space in the longitudinal direction of the cabin. Furthermore, depending on the application, the seat can be used not only during critical phases of flight (direct view), but also as a rest seat.

[0044] The "seat-in-product" principle is sufficiently described in the i-CAS patent application and will not be discussed in further detail here. The term "supporting product" always refers to the product into which the rotating CAS is integrated, such as a partition wall or a monument, among others.

[0045] Several solutions are conceivable for the rotating mechanism:

[0046] 1. Integration of the pivot axis into the supporting product. The load is applied across the entire height or continuously across a portion of the height. The mechanism is only partially visible. It can optionally be more heavily concealed.

[0047] 2. Mechanism screwed onto the product being held. The load is applied over the entire height or continuously over a portion of the height. The mechanism is fully visible and screwed onto the product being held.

[0048] 3. Point-based load application via an integrated pivot. This requires at least two hinges. The load is applied to the supporting product via dedicated points. The mechanism is only partially visible. It can optionally be more heavily concealed.

[0049] 4. Point-based load application through a screwed-on mechanism. This requires at least two hinges. The load is applied to the supporting product via dedicated points.

[0050] The rotated seat requires a support. This allows the load to be distributed in the rotated position, thus reducing the weight of the overall system. Load-bearing solutions using the support have the following characteristics:

[0051] 1. The support primarily provides non-locked support in the x-direction

[0052] 2. The support provides non-locking support in the z-direction. 3. Alternatively, a locking mechanism for the folding function can be offered. This locking mechanism is characterized by the fact that it does not transfer any load and only prevents the seat from unfolding or folding away around the z-axis, preventing the seat from "accidentally" rotating out of the TTL position.

[0053] 4. The support offers optional damping against rattling and other noises and vibrations.

[0054] 5. In the event of an emergency landing or other incident, the hinge and support remain fully functional.

[0055] The invention can be used in all aircraft currently equipped with a rotating CAS. It can also be used in layouts where densification products are used. It can be used anywhere a CAS or camera system for direct view is required. This is typically the aft section of single-aisle aircraft. Applications in the front of the cabin are also conceivable.

[0056] Further features, effects, and advantages of the invention will become apparent from the following description of a preferred embodiment of the invention and the accompanying figures. Each of these figures shows a schematic diagram:

[0057] Figure 1 shows a section of an aircraft with passenger cabin and seating arrangement in plan view,

[0058] Figure 2 shows the seating arrangement from Fig. 1 in perspective view and in more detail,

[0059] Figure 3 shows the situation from Fig. 1 in an enlarged section of the aircraft,

[0060] Figure 4 shows an alternative seating arrangement with additional CAS seats and cabin crew,

[0061] Figure 5 shows the seat arrangement from Fig. 1 in side view with external hinge and

[0062] Figure 6 with internal partial hinges,

[0063] Figure 7 shows an alternative seating arrangement in a representation according to Figure 3.

[0064] Figure 1 shows a highly abstracted top view of a section of an aircraft 2 or its passenger cabin 4 (viewed opposite the z-direction, which extends beyond the plane of the paper). The passenger cabin 4 extends in the x-direction (straight-ahead flight direction) beyond a partition 6. In the rear part of the aircraft 2, a service area 8 adjoins the passenger cabin 4, opposite the x-direction.

[0065] The aircraft 2 contains a basic structure 10 (fuselage structure, supporting framework), indicated only symbolically here. A seating arrangement 12 is installed in a proper assembly state M in the aircraft 2 or the passenger cabin 4. The seating arrangement 12 contains a retaining wall 14, which in the present case is formed by the upper section of the partition 6 in the figure, which in turn forms a first wall section 6a of the partition. A second wall section 6b is separated from the first wall section 6a by an opening 7. This opening 7 allows persons in the aircraft 2 to pass through the partition 6 and thus move along an aisle that runs through the opening 7. The retaining wall 14 is permanently attached to the basic structure 10 of the aircraft 2. The seating arrangement 12 is therefore a seating arrangement for the passenger cabin 4 of the aircraft 2.In the intended assembly state M, the retaining wall 14 is thus permanently attached to the base structure 10 in the passenger cabin 4. The retaining wall 14 is therefore a partition or dividing wall 6 of the passenger cabin 4.

[0066] The seating arrangement 12 includes a seat 16, here a folding seat, for cabin crew (not shown). The seat 16 includes a seat surface 18 and a backrest 20. The seat surface 18 can be folded about a folding axis 22 between a sitting position SS and a rest position RS. The seat 16 is attached to the support wall 14 exclusively by means of a pivot axis 24. The pivot axis 24 runs vertically, i.e., in the z-direction.

[0067] The seat 16 is rotatable about the rotation axis 24 between a first end position EP1 and a second end position EP2. The entire possible rotation range extends over an angular range 26, indicated by a double arrow, which here is 180°. The end positions EP1 and EP2 are thus offset from each other by the angular range 26 of 180°. The end positions EP1 and EP2 and the angular range 26 are indicated by dashed lines.

[0068] Likewise, the seat 16 is rotatable between two seating positions SP1, 2 about the rotation axis 24. In each of the seating positions SP1, 2, the seating position SS of the seat surface 18 is possible. In the present case, the seating position SP1 coincides with the end position EP1, and the seating position SP2 coincides with the end position EP2. In the present case, the seating position SS of the seat surface 18 is even possible in every rotational position of the seat 16 between the end positions EP1, 2. A stowed position UP (see below), in which the seating position SS of the seat 16 is not possible, does not exist in this exemplary embodiment.

[0069] The seat 16, which actually only exists once, is shown twice to explain the seat positions SP1,2.

[0070] In the sitting position SP1 or the end position EP1, the seat is parallel to the retaining wall 14 and in front of the retaining wall 14. This means that a person who sits on the seat 16 with the seat surface 18 in the sitting position SS and turns his back to the backrest 20 has the retaining wall 14 at his back.

[0071] In the aircraft, the seat 16 is permanently attached to the base structure 10 exclusively indirectly via the retaining wall 14. There is no other permanent attachment between the seat 16 and the base structure 10. The seat position SP2 here is a TTL observation position TP. This means: During the taxi, takeoff, and landing (TTL) flight phases, a cabin crew member sitting on the seat 16 has a clear view in the x-direction, i.e., the direction of flight, of passengers in the passenger cabin 4. In the seat position SP2 or the end position EP2, the seat 16 is arranged in the opening 7. The seat 16 is thus located between the first wall section 6a and the second wall section 6b. In this seat position SP2, which coincides with the second end position EP2 and represents another TTL position, a person sitting on the seat 16 can look in the opposite direction compared to the seat position SP1.

[0072] The aircraft 2 or the seat arrangement 12 contains a locking element 28, only symbolically indicated here. This is designed or serves to lock the seat 16 in the seating position SP1 or end position EP1, so that it cannot be removed from the respective position without unlocking the locking element 28. The locking element 28 is arranged on the first wall section 6a or integrated therein. Furthermore, the aircraft 2 or the seat arrangement 12 contains a second locking element 29. The seat 16 can be locked in the end position EP2 with the second locking element 29. The second locking element 29 is arranged on the second wall section 6b or integrated therein. The aircraft 2 also contains two support receptacles 30a, b, only symbolically indicated here, which are each arranged on the partition wall 6 or formed by it.A first support receptacle 30a is arranged on the first wall section 6a and a second support receptacle 30b is arranged on the second wall section 6b, is each integrated therein or is formed by the latter. The support receptacles 30a, b are also permanently fastened to the base structure 10 by means of the partition wall 6 and can thus be used to support loads. The seat 16 contains a support element 32 with which it is supported in the two seating positions SP1, 2 with respect to an x-load and a z-load on the respective support receptacle 30a or 30b. Corresponding x- and z-loads from the seat 16 are thus transferred to the base structure 10 via the support element 32 and the support receptacle 30a or the support receptacle 30b and the partition wall 6. In other words, the retaining wall 14 in the form of the partition wall 6 forms the two support receptacles 30a, b or contains them.

[0073] Figure 2 shows a more detailed perspective view of the situation in Figure 1 in the direction of arrow II in Figure 1. Here, the seat 16 is in an intermediate position between the two end positions EP1,2. This shows the moment of pivoting the seat 16 between the two seating positions SP1,2. The seat surface 18 is in the rest position RS.

[0074] Figure 3 shows the entire installation situation in a larger section of the aircraft 2 in the view according to Figure 1. Also shown here are monuments such as washrooms 34 (lavatory) or storage compartments 36 in the service area 8, as well as unspecified passenger seats in the passenger cabin 4.

[0075] Figure 4 symbolically shows the seating arrangement 12 again, also in a top view according to Figures 1 and 2. In addition to seat 16, further permanently installed CAS seats 38 are shown. Cabin crew 40, in this case flight attendants, are seated on both seat 16 and the two CAS seats 38. Otherwise, the seating arrangement 12 corresponds to that shown in Figures 1 to 3.

[0076] Figure 5 shows a view of the seat arrangement 12 opposite the x-direction, i.e., in the direction of arrow V in Figure 1. The seat 16 is in the seating position SP2. In this embodiment, the rotation axis 24 is designed as a single continuous rotation axis in the form of a single hinge 41. The seating position SP1 is indicated by dashed lines, i.e., when the seat 16 is located "behind" the partition 6 in the image. In the seating position SP2 of the seat 16, the seat surface 18 in the seating position SS and the backrest 20 can be seen, as well as the support element 32, which is supported on or in the support receptacle 30b. The rotation axis 24 is designed here in a simple manner outside the partition 6.

[0077] Figure 6 shows an alternative embodiment to Figure 5. Here, the pivot axis 24 is constructed in two parts, in the form of two partial hinges 42a, b. Furthermore, the pivot axis 24 is at least partially integrated into the partition wall 6, which is visually more appealing.

[0078] Figure 7 shows, in a plan view according to Figure 1 of the aircraft 2, a first alternative seating arrangement 12, this time in the front region of the aircraft 2, namely between a cockpit 52 and the passenger cabin 4. The seat 16, which is only indicated here, is again attached to the retaining wall 14 so as to be rotatable about a rotation axis 24 through an angular range 26. The angular range 26 here, however, extends over 270° between the two end positions EP1, 2. The end position EP1 is again the same as the seat position SP1, but the end position EP2 here is a stowed position UP, in which the seat surface 18 cannot be brought from the rest position RS into the seat position SS, since this faces the retaining wall 14. The seat surface 18 in the seat position SS is indicated by dashed lines and is possible here for the seat positions SP1 and SP2. The seat position SP2 is again rotated by 180° relative to the seat position SP1. The viewing direction here points in the x-direction, i.e. the direction of flight.

[0079] In contrast to the previous embodiments, the retaining wall 14 is not a partition here, but a wall section 44 of a monument 46 for the passenger cabin, here a galley (Gailey).

[0080] In this exemplary embodiment, the seat 16 is not only rotatable about the axis of rotation 24, which therefore represents a first axis of rotation here. The seat 16 is also rotatable here, alternatively or optionally as required, about a second axis of rotation 48. The angular range 26 is only 90° between the two end positions EP1 and EP2. This ensures that in the end position EP1, which corresponds to a seat position SP3, a viewing direction for cabin crew is possible which is directed opposite to the direction of flight or x-direction and thus towards the passenger cabin 4. In Figure 7 below, a further or second seating arrangement 12 is present: Here, there is also another monument 46, in this case a washroom / on-board toilet (lavatory). Also installed on its wall section 44 is a further seat 16 which is mounted to rotate about the rotation axis 24 through an angular range 26 of 90° between the two end positions EP1,2, which correspond to seat positions SP1,2.By pivoting the seat away from the end position EP1, an enlarged corner access 50, indicated in the figure by a thickened line running across the corner, can be achieved to the washroom. This allows wheelchair users, for example, to have easier access to the washroom.

[0081] List of reference symbols

[0082] 2 aircraft 4 passenger cabin

[0083] 6 Partition wall

[0084] 6a first wall section

[0085] 6b second wall section

[0086] 7 Breakthrough 8 Service area

[0087] 10 Basic structure

[0088] 12 Seating arrangement

[0089] 14 Retaining wall

[0090] 16 Seat 18 Seat

[0091] 20 backrest

[0092] 22 folding axis

[0093] 24 Rotation axis (first)

[0094] 26 Angle range 28 Locking element

[0095] 29 locking element

[0096] 30a, b support mount

[0097] 32 Support element

[0098] 34 Washroom 36 Storage compartment

[0099] 38 CAS seat (permanently installed)

[0100] 40 cabin crew

[0101] 41 Hinge

[0102] 42a, b Partial hinge 44 Wall section

[0103] 46 Monument

[0104] 48 Rotation axis (second)

[0105] 50 access

[0106] 52 Cockpit

[0107] M Assembly state EP1,2 final position

[0108] SP1-3 seating position

[0109] SS sitting position

[0110] RS rest position

[0111] UP stowage position

[0112] TP TTL observation position

Claims

AMENDED CLAIMS received by the International Bureau on 7 October 2024 (07.10.2024) 1. Seat arrangement (12) for a passenger cabin (4) of an aircraft (2), - with a retaining wall (14) which can be permanently fastened to a basic structure (10) of the aircraft (2) in a proper assembly state (M) in the passenger cabin (4), - with a seat (16) for cabin crew (40) which includes a seat surface (18) which can be folded between a sitting position (SS) and a rest position (RS), - wherein the seat (16) is fixed to the support wall (14) exclusively by means of at least one vertical axis of rotation (24, 48), - wherein the seat (16) is rotatable about each of the rotation axes (24, 48) between a first (EP1) and a second end position (EP2), - wherein the two end positions (EP1,2) are offset from each other by an angular range (26) of at least 30° and at most 300°, - wherein the seat (16) is rotatable about the axes of rotation (24, 48) between at least two seating positions (SP1-3), - wherein in each of the seating positions (SP1-3) the seating position (SS) of the seat surface (18) is possible. - wherein the retaining wall (14) is a partition wall (6) for the passenger cabin (4), and - the partition wall (6) has a first wall section (6a) and a second wall section (6b), wherein the two wall sections (6a, 6b) are separated by an opening (7) and the seat (16) is rotatable into an end position (EP1, EP2) in which the seat (16) is arranged in the opening (7).

2. Seat arrangement (12) according to claim 1, characterized in that with respect to at least one of the axes of rotation (24, 48) at least one of the seat positions (SP1-3) is one of the end positions (EP1, 2).

3. Seat arrangement (12) according to claim 2, characterized in that with respect to at least one of the axes of rotation (24, 48) two of the seat positions (SP1-3) are the two end positions (EP1, 2). AMENDED SHEET (ARTICLE 19) 4. Seat arrangement (12) according to one of claims 1 to 3, characterized in that with respect to at least one of the axes of rotation (24, 48) the seat (16) is rotatable into at least one stowed position (UP) in which the sitting position (SS) of the seat surface (18) is not possible.

5. Seat arrangement (12) according to claim 4 excluding claim 3, characterized in that with respect to at least one of the rotation axes (24, 48) one of the stowed positions (UP) is one of the end positions (EP1, 2).

6. Seat arrangement (12) according to one of claims 1 to 3, characterized in that with respect to at least one of the axes of rotation (24, 48) the sitting position (SS) of the seat surface (18) is enabled in each rotational position of the seat (16) between the end positions (EP1, 2).

7. Seat arrangement (12) according to one of the preceding claims, characterized in that the seat (16) is located parallel to and in front of the retaining wall (14) in at least one of the seating positions (SP1, 2).

8. Seat arrangement (12) according to one of the preceding claims, characterized in that a wall section (44) of a monument (46) is for the passenger cabin (4).

9. Seat arrangement (12) according to one of the preceding claims, further comprising at least one locking element (28, 29) which is adapted to lock the seat (16) in at least one of the end positions (EP1, 2) and / or seating positions (SP1-3) and / or - if present - the stowed positions (UP).

10. Seat arrangement (12) according to claim 9, comprising a first locking element (28) which is designed to lock the seat (16) in the first end position (EP1) and / or seat position (SP1) and a second locking element AMENDED SHEET (ARTICLE 19) (29) which is designed to lock the seat (16) in the second end position (EP2) and / or seat position (SP2).

11. Seat arrangement (12) according to one of the preceding claims, comprising at least one support receptacle (30a, b) fastened to the retaining wall (14), wherein the seat (16) has a support element (32) with which it can be supported on at least one of the support receptacles (30a, b) in at least one of the end positions (EP1, 2) and / or seating positions (SP1-3) and / or - if present - the stowed positions (UP).

12. Aircraft (2) with a basic structure (10) and a passenger cabin (4), - with the seat arrangement (12) according to one of the preceding claims, - which is in the intended assembly state (M) in the passenger cabin (4), - wherein the retaining wall (14) is permanently attached to the basic structure (10) of the aircraft (2), - wherein the seat (16) is rotatable about each of the axes of rotation (24,48) between the two end positions (EP1,2), - wherein the seat (16) is rotatable about the axes of rotation (24,48) between the seating positions (SP1-3), - wherein in each of the seating positions (SP1-3) the seating position (SS) of the seat surface (18) is possible.

13. Aircraft (2) according to claim 12, characterized in that the seat (16) is attached to the base structure (10) exclusively indirectly via the retaining wall (14).

14. Aircraft (2) according to one of claims 12 to 13, characterized in that one of the seating positions (SP1-3) is a TTL observation position (TP) for the passenger cabin (4).

15. Aircraft (2) according to one of claims 12 to 14, characterized in that AMENDED SHEET (ARTICLE 19) the aircraft (2) contains at least one locking element (28) which is designed to lock the seat (16) in at least one of the end positions (EP1, 2) and / or seating positions (SP1-3) and / or - if present - the stowed positions (UP).

16. Aircraft (2) according to one of claims 12 to 15, characterized in that - the aircraft (2) contains at least one support receptacle (30a, b) attached to the base structure (10), - the seat (16) has a support element (32) with which it is supported on at least one of the support receptacles (30a, b) in at least one of the end positions (EP1, 2) and / or seating positions (SP1-3) and / or - if present - the stowed positions (UP).

17. Aircraft (2) according to claim 16, characterized in that the retaining wall (14) contains or forms at least one of the support receptacles (30a, b). AMENDED SHEET (ARTICLE 19)

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