Patent Description:
A seatback cover attachment system is provided as defined by claim <NUM>.

In some embodiments, the substrate may include one or more seatback frame mount cut outs configured to conform to one or more seatback frame mounts of the seatback frame.

In some embodiments, the attachment system may further include one or more flaps including one or more fastening assemblies configured to visually hide the one or more seatback frame mounts.

In some embodiments, the substrate may be formed of a thermoformed plastic or laminated fiberglass.

An aircraft seat is also provided as defined by claim <NUM>.

In some embodiments, the seatback frame may be configured to fit within the channel of the seatback cover attachment system.

In some embodiments, the seatback frame may be configured be inserted in the channel of the seatback cover attachment system.

In some embodiments, the seatback frame may be configured to engage with the substrate via a force applied in a direction downward from the channel of the seatback cover attachment system.

In some embodiments, the seatback frame may be configured to disengage from the substrate via a force applied in a direction upward from the channel of the seatback cover attachment system.

In some embodiments, the substrate and the side panel may at least partially overlap to prevent a seatback diaphragm of the seatback frame from cutting into a portion of the side panel.

In addition, use of "a" or "an" may be employed to describe elements <NUM> and components of embodiments disclosed herein.

The appearances of the phrase "in some embodiments" in various places in the specification are not necessarily all referring to the same embodiment, and embodiments may include one or more of the features expressly described or inherently present herein, or any combination of or sub-combination of two or more such features, along with any other features which may not necessarily be expressly described or inherently present in the instant disclosure.

<FIG> in general illustrate an aircraft seatback cover attachment system, in accordance with one or more embodiments of the disclosure.

Seats may include some combination of components such as, but not limited to, a seat pan cover, a seatback cover, a seat pan cushion, a seatback cushion, a seat pan support system, and a seatback support system. In select seat designs, the seatback cover alone may be composed of numerous pieces, where each piece is then coupled together to form the seatback cover. After the individual components are assembled, the seat components may be coupled together with one or more attachment assemblies to form the aircraft seat.

These methods of manufacture and attachment may require extensive assembly and installation time. For example, these methods may require thirty minutes of assembly time and approximately twenty minutes of installation time. In addition, these methods may cause difficulties during alignment and/or an indeterminateness in the alignment of the seatback cover, cushion, and/or support system during manufacturing and/or installation of the aircraft seat. Further, the methods may result in increased cost in manufacturing and/or installation.

The seatback cover may be subjected to stress, strain, dirt or other mess such as airsickness, contraband, or the like resulting in damage of the seatback cover. After a period of time and/or a particular type of wear factor occurring, the seatback cover may be removed for cleaning and/or replacement. Removing and re-installing the seatback cover may require a method that is quick, inexpensive, and not labor intensive. For example, the seatback cover attachment system should be quickly dismantled and put together without incurring considerable labor costs.

In addition, in select industries the build of the seat (and any included components within the build) may be required to meet guidelines and/or standards. For example, aircraft seats may be required to meet aviation guidelines and/or standards. For instance, the select aircraft seats may need to be configured in accordance with aviation guidelines and/or standards put forth by, but not limited to, the Federal Aviation Administration (FAA), the European Aviation Safety Agency (EASA) or any other flight certification agency or organization; the American National Standards Institute (ANSI), Aeronautical Radio, Incorporated (ARINC), or any other standards setting organization or company; the Radio Technical Commission for Aeronautics (RTCA) or any other guidelines agency or organization; or the like. Seatback cover attachment systems may present difficulties such as, but not limited to, failing to meet load requirements (e.g., <NUM> static load requirements or <NUM> dynamic load requirements), burn requirements, or the like as set forth by the FAA in <NUM> C. Part <NUM>, AIRWORTHINESS STANDARDS: TRANSPORT CATEGORY AIRPLANES).

As such, it would be desirable to provide a seatback cover attachment system. The seatback cover attachment system should reduce the number of parts, allowing for more efficient removal and installation of the seatback cover. For example, the seatback cover attachment system may include an integrated seatback cover and cushion sub-system to eliminate the need for an additional seatback cushion component. The seatback cover attachment system should be inexpensive to implement, whether on a retrofitted aircraft seat or in a new aircraft seat design. The seatback cover attachment system should reduce the amount of seatback frame finishing steps. The seatback cover attachment system should be configured in accordance with aviation guidelines and/or standards.

Referring in general to <FIG>, one or more seatback cover attachment systems may be integrated within an aircraft seat <NUM> installed within an aircraft cabin. For example, the aircraft seat <NUM> may include, but is not limited to, a business class or first-class passenger seat, an economy-class passenger seat, a crew member seat, or the like. It is noted herein the terms "aircraft seats" and "passenger seats" may be considered equivalent, for purposes of the disclosure.

The aircraft seat <NUM> may be rotatable about an axis (e.g., swivelable). The aircraft seat <NUM> may be fully positionable between the outer limits of motion as defined by the moveable components of the aircraft seat <NUM>. Where the aircraft seat <NUM> is installed within a passenger compartment, the aircraft seat <NUM> may be fully positionable between the outer limits of motion as defined by one or more passenger compartment monuments of the passenger compartment. It is noted herein an upright or raised position may be considered a taxi, takeoff, or landing (TTL) position during select stages of flight (though the upright or raised position is not limited to use during the select stages of flight as the TTL position, but also may be used at any point during the flight), for purposes of the present disclosure. In addition, it is noted herein that any position that does not meet the above-defined requirements of the TTL position may be considered a non-TTL position, for purposes of the present disclosure. Further, it is noted herein the aircraft seat <NUM> may be actuatable (e.g., translatable and/or rotatable) from the TTL position to a non-TTL position, and/or vice versa. Further, it is noted herein the aircraft seat <NUM> may be capable of a fully upright or raised position, and that the TTL position may have a more reclined seatback cushion and a more angled upward seat pan cushion as compared to the fully upright or raised position. Therefore, the above description should not be interpreted as a limitation on the present disclosure but merely an illustration.

In general, an aircraft seat <NUM> may be translatable (e.g., trackable or slidable). The aircraft seat <NUM> may be rotatable about an axis cross-wise through the aircraft seat <NUM> into a position including, but not limited to, the upright or raised position, one or more lounge or reclined positions, and a lie-flat or bed position. For example, the aircraft seat <NUM> may transition directly between the upright or raised position and the lie-flat or bed position. By way of another example, it is noted herein the aircraft seat <NUM> may transition through one or more lounge or reclined positions between the upright or raised position and the lie-flat or bed position. By way of another example, the aircraft seat <NUM> may transition into one or more lounge or reclined positions in a motion separate from the transition between the upright or raised position and the lie-flat or bed position. Therefore, the above description should not be interpreted as a limitation on the scope of the disclosure but merely an illustration.

The aircraft seat <NUM> may include a support system <NUM>. The support system <NUM> may be a rigid structure within the aircraft seat <NUM>, such that the support system <NUM> does not move. The support system <NUM> may include one or more movable components such that the support system <NUM> may articulate. For example, the support system <NUM> may articulate when the aircraft seat <NUM> actuates between the upright or raised position, the one or more lounge or reclined positions, and/or the lie-flat or bed position.

The support system <NUM> may include a seat pan <NUM>. The aircraft seat <NUM> may include a seat pan cushion <NUM>. The aircraft seat <NUM> may include a seat pan frame <NUM> including one or more seat pan frame elements <NUM>. For example, one or more seat pan frame elements <NUM> may include, but are not limited to, seat pan structural hoops. The seat pan frame <NUM> including the one or more seat pan frame elements <NUM> may form a portion of an exterior boundary of the seat pan of the aircraft seat <NUM>. Although <FIG> depicts the support system <NUM> including a seat pan cushion, seat pan frame, seat pan elements, seat pan diaphragm, seat pan cover, and the like, it is noted herein the support system <NUM> may not include one or more of the following: a seat pan cushion, seat pan frame, seat pan elements, seat pan diaphragm, seat pan cover, and the like. Therefore, <FIG> and the related discussion should not be construed as limiting the scope of the present disclosure.

The support system <NUM> may include a seat pan diaphragm <NUM>. The seat pan diaphragm <NUM> may include any type of diaphragm including, but not limited to, a plastic diaphragm, a metal diaphragm, a fabric diaphragm, a wire or wireframe diaphragm, or the like.

The seat pan cushion <NUM> may conform or substantially conform to the support system <NUM>. For example, at least one surface of the seat pan cushion <NUM> may conform to a corresponding surface of the support system <NUM>. By way of another example, components of the support system <NUM> (e.g., components including, but not limited to, straps configured to couple the diaphragm <NUM> to the seat pan frame <NUM> with the one or more seat pan frame elements <NUM>, where the support system <NUM> is or includes the diaphragm <NUM>) may extend beyond the boundaries of the cushion <NUM>, such that the at least one surface of the cushion <NUM> does not fully conform to the corresponding surface of the support system <NUM>. By way of another example, a portion of the cushion <NUM> may wrap around or otherwise enclose a portion of the support system <NUM> (e.g., including, but not limited to, a front edge or leading portion of the cushion <NUM>). In general, the support system <NUM> may conform to a portion of a user (e.g., a passenger, a crew member, or the like), and the cushion <NUM> may similarly conform to the portion of the user due to the cushion <NUM> conforming to the support system <NUM>.

The aircraft seat <NUM> may include a seat pan cover <NUM>. The seat pan cover <NUM> may be configured to fit over at least a portion of the seat pan cushion <NUM>. For example, the seat pan cover <NUM> may be configured to wrap around or otherwise enclose exterior surfaces of the seat pan cushion <NUM> not proximate to the support system <NUM>. The seat pan cover <NUM> may be configured to attach to the support system <NUM> and/or the cushion <NUM>. It is noted herein "seat cover" and "dress cover" may be considered equivalent, for purposes of the disclosure.

The support system <NUM> may include a seatback <NUM>. The aircraft seat <NUM> may include a seatback frame <NUM> including one or more seatback frame elements <NUM>. For example, one or more seatback frame elements <NUM> may include, but are not limited to, seatback structural hoops. The seatback frame <NUM> including the one or more seatback frame elements <NUM> may form a portion of an exterior boundary of the seatback of the aircraft seat <NUM>.

The support system <NUM> may include a seatback diaphragm <NUM>. The diaphragm <NUM> may include any type of diaphragm including, but not limited to, a plastic diaphragm, a metal diaphragm, a fabric diaphragm, a wire or wireframe diaphragm, or the like.

The aircraft seat <NUM> may include a seatback attachment cover system <NUM>. The seatback attachment system <NUM> may be configured to fit over at least a portion of the seatback frame <NUM>.

<FIG> illustrate components of a seatback cover attachment system <NUM>, in accordance with one or more embodiments of the disclosure. <FIG> is a method or process <NUM> for installing the seatback cover attachment system <NUM> on the aircraft seat <NUM>, in accordance with one or more embodiments of the disclosure. <FIG> is a method or process <NUM> for uninstalling the seatback cover attachment system <NUM> from the aircraft seat <NUM>, in accordance with one or more embodiments of the disclosure. It is noted herein "seatback cover attachment system" and variants including, but not limited to, "attachment system" or "system" may be considered equivalent, for purposes of the disclosure.

The attachment system <NUM> includes a substrate <NUM> configured to reversibly couple to a portion of a seatback frame <NUM>, e.g. to attach to a portion of the one or more seatback frame elements <NUM>. The substrate <NUM> includes one or more surfaces <NUM> that define a channel <NUM> which is configured to receive a portion of the seatback frame <NUM>, e.g. one or more seatback frame elements <NUM> of the seatback frame <NUM>. For instance, the channel <NUM> may include a cross-section shaped to receive and/or conform to a portion of the seatback frame <NUM>. As shown in <FIG>, the channel <NUM> may be a "J-channel". Further, the channel <NUM> may be a "C-channel". Further, the channel <NUM> may be a "L-channel". In general, the channel may include a cross-section having any shape configured to receive and/or conform to a portion of the seatback frame <NUM>.

When attached to the seatback frame <NUM>, the substrate <NUM> may substantially enclose the seatback frame <NUM>, such that only a portion of the seatback frame <NUM> may be visible when fully assembled. In this regard, the one or more surfaces <NUM> of the substrate <NUM> may be configured to hide various manufacturing imperfections in the seatback frame <NUM>. Further, the substrate <NUM> may be configured to reduce seatback frame finishing steps.

The substrate <NUM> may be formed of any material. For example, the substrate <NUM> may be formed of a thermoformed plastic including, but not limited to, acrylic-polyvinyl chloride, polyethylene terephthalate (PET), polystyrene (HIPS), high-density polyethylene (HDPE), polyvinyl chloride (PVC), polyethylene terephthalate glycol-modified (PETG), or the like. By way of another example, the substrate <NUM> may be formed of laminated fiberglass. In general, the substrate <NUM> may be configured to be formed from any material (e.g., plastic, metal, or the like) configured to meet aviation guidelines and/or standards (e.g., for load-bearing requirements, burn requirements, or the like).

The seatback cover attachment system <NUM> includes an integrated seatback cover and cushion sub-system <NUM>. It is noted herein "integrated seatback cover and cushion sub-system" and variants including, but not limited to, "integrated cover and cushion sub-system" or "sub-system" may be considered equivalent, for purposes of the disclosure.

The integrated cover and cushion sub-system <NUM> includes a dress cover <NUM>. It is noted herein the dress cover <NUM> may conform to a portion of a user (e.g., a passenger, a crew member, or the like), or may be independently-shaped.

The dress cover <NUM> includes a seatback cover layer <NUM>. The seatback cover layer <NUM> may be formed of any material known in the art including, but not limited to, leather, synthetic leather, fabric, or the like.

The dress cover <NUM> includes a seatback cushion layer <NUM>. The seatback cushion layer <NUM> may be formed of any material known in the art including, but not limited to, foam, or the like.

The seatback cushion layer <NUM> is integrated with the seatback cover layer <NUM> of the dress cover <NUM>. For example, the dress cover <NUM> may be formed of a laminated piece of material integrated with a cushion backing (e.g., a foam backed fabric). It is noted that the seatback cushion layer <NUM> may be integrated with the seatback cover layer <NUM> via any fabrication process (e.g., sewing, or the like) or fastening mechanism (e.g., an adhesive, or the like). In this regard, the seatback cover attachment system <NUM> includes an integrated seatback cover and cushion assembly to eliminate the need for an additional seatback cushion component, thereby reducing the assembly time by reducing the number of seatback component parts.

The integrated cover and cushion sub-system <NUM> includes a side panel <NUM> formed of a piece of wrapped fabric <NUM>.

The side panel <NUM> is coupled to one or more portions of the dress cover <NUM> via one or more seams <NUM> generated via one or more sewing processes.

The side panel <NUM> is joined to a portion of the substrate <NUM> via one or more seams <NUM>. In this regard, a first end of the side panel <NUM> may be sewn directly onto a surface <NUM> of the substrate <NUM> via a first seam 219a. It is noted that this single seam coupling mechanism may be configured to allow for efficient assembly to reduce assembly time.

Although <FIG> depict the side panel <NUM> coupled to the top surface of the substrate <NUM>, it is noted that the side panel <NUM> may be coupled to any surface of the substrate <NUM>. For example, the side panel <NUM> may be coupled to a side surface of the substrate <NUM>. By way of another example, the side panel <NUM> may be coupled to a bottom surface of the substrate <NUM>.

In one non-limiting example, the attachment system <NUM> may be formed of three parts (e.g., substrate <NUM>, dress cover <NUM>, and side panel <NUM>), where the three parts may be coupled together to form the attachment system <NUM>. The attachment system <NUM> may include one or more seams joining the three parts. For example, the attachment system <NUM> may include a first seam 219a joining the dress cover <NUM> and the side panel <NUM>. By way of another example, the attachment system <NUM> may include a second seam 219b joining the side panel <NUM> and the substrate <NUM>. It is noted herein, however, the attachment system <NUM> may include any number of seams <NUM>. Therefore, the above description should not be interpreted as a limitation on the present disclosure but merely an illustration.

The substrate <NUM> includes a contoured surface including a lowered portion <NUM> and a raised portion <NUM> on a surface <NUM> of the substrate <NUM>. The fabric <NUM> of the dress cover <NUM> may be configured to attached to the lowered portion <NUM> via one or more attachment mechanisms (e.g., one or more seams <NUM>, or the like) generated by one or more fabrication processes (e.g., one or more sewing processes, or the like). The raised portion <NUM> is dimensioned to obscure the one or more seams <NUM> from a rear view of the aircraft seat <NUM>. To this end, the height of the raised portion <NUM> is greater than or equal to the thickness of the fabric <NUM> of the side panel <NUM> to obscure the seam <NUM>.

Referring to <FIG>, the attachment system <NUM> may be configured to receive one or more seatback frame mounts. For example, the substrate <NUM> may include one or more seatback frame cut outs <NUM> configured to conform to one or more seatback frame mounts. In this regard, the one or more seatback frame cuts outs <NUM> may be configured to slide past the one or more seatback frame mounts, without interfering with the substrate <NUM>, when the seatback frame <NUM> is inserted in the channel <NUM> of the substrate <NUM>.

The attachment system <NUM> may include one or more side panel flaps <NUM> configured to visually hide the one or more seatback frame mounts and the one or more seatback frame cut outs <NUM>. The one or more side panel flaps <NUM> may be coupled to the substrate <NUM> via one or more fastening assemblies <NUM>. For example, the one or more side panel flaps <NUM> may include a snap <NUM> and the substrate <NUM> may include a receiving snap <NUM>. In this regard, the one or more side panel flaps <NUM> may be coupled to the substrate <NUM> by fastening the snap <NUM> to the receiving snap <NUM>. By way of another example, the one or more side panel flaps <NUM> may include a hook and loop fastening assembly including a loop portion coupled to the flap <NUM> and a hook portion coupled to the substrate <NUM>. In this regard, the one or more side panel flaps <NUM> may be coupled to the substrate <NUM> by fastening the hook portion of the substrate <NUM> to the loop portion of the flap <NUM>.

Installing an aircraft seatback using the seatback cover attachment system <NUM> may include one or more of the following steps of the method or process <NUM>:.

In a step <NUM>, the seatback frame <NUM> may be inserted into a portion of the attachment system <NUM>. For example, a portion of the one or more seatback frame elements <NUM> may be inserted at an angle <NUM> into the channel <NUM> of the substrate <NUM>.

In a step <NUM>, a force may be applied to engage the seatback frame <NUM> with the channel <NUM> until the attachment system <NUM> interlocks with the seatback frame <NUM>. For example, the force may be applied through an application of force on the attachment system <NUM> in a specific direction until the attachment system <NUM> interlocks with the seatback frame <NUM>. For instance, the force may be applied in a downward direction from the channel <NUM> of the substrate <NUM>. In this regard, the force may be applied to engage the seatback frame <NUM> with the channel <NUM> until the substrate <NUM> snaps into place.

Referring to <FIG>, when the attachment system <NUM> engages with the seatback frame <NUM>, the attachment system <NUM> may be configured to prevent the diaphragm <NUM> from cutting into the side panel <NUM>. For example, the substrate <NUM> may be coupled to the side panel <NUM> such that a portion of the substrate <NUM> overlaps with a portion of the side panel <NUM>. In this regard, the substrate <NUM> of the overlap is configured to prevent the diaphragm <NUM> from cutting into the side panel. In this regard, the attachment system <NUM> may be easily installed without removing the diaphragm <NUM> and/or damaging the diaphragm <NUM>.

The attachment system <NUM> may interlock with the seatback frame <NUM> when a specific amount of force is applied. For example, the force may cause the substrate <NUM> to flex into place to cause the attachment system <NUM> to interlock with the seatback frame <NUM>. In this regard, the attachment system <NUM> does not require an additional interlocking assembly to secure the attachment system <NUM> with seatback frame <NUM>.

In an optional step <NUM>, one or more side panel flaps may be coupled to a portion of the substrate <NUM> via one or more fastening assemblies. For example, as shown in <FIG>, <FIG>, the attachment system <NUM> may include one or more side panel flaps <NUM> configured to visually hide the one or more seatback frame mounts and the one or more seatback frame cut outs <NUM>. The one or more side panel flaps <NUM> may be coupled to the substrate <NUM> via one or more fastening assemblies <NUM>. For example, the one or more side panel flaps <NUM> may include a snap <NUM> and the substrate <NUM> may include a receiving snap <NUM>. In this regard, the one or more side panel flaps <NUM> may be coupled to the substrate <NUM> by fastening the snap <NUM> to the receiving snap <NUM>. By way of another example, the one or more side panel flaps <NUM> may include a hook and loop fastening assembly including a loop portion coupled to the flap <NUM> and a hook portion coupled to the substrate <NUM>. In this regard, the one or more side panel flaps <NUM> may be coupled to the substrate <NUM> by fastening the hook portion of the substrate <NUM> to the loop portion of the flap <NUM>.

Removing the attachment system <NUM> may include one or more of the following steps of the method or process <NUM>:.

In an optional step <NUM>, one or more side panel flaps may be un-coupled from a portion of the substrate <NUM> via one or more fastening assemblies. For example, as shown in <FIG>, 6A-6E, the attachment system <NUM> may include one or more side panel flaps <NUM> configured to visually hide the one or more seatback frame mounts and the one or more seatback frame cut outs <NUM>. The one or more side panel flaps <NUM> may be coupled to the substrate <NUM> via one or more fastening assemblies <NUM> when assembling the seat <NUM>. The one or more side panel flaps <NUM> may then be un-coupled from the substrate <NUM> via the one or more fastening assemblies <NUM> when disassembling the seat <NUM>. For example, the one or more side panel flaps <NUM> may include a snap <NUM> and the substrate <NUM> may include a receiving snap <NUM>. In this regard, the one or more side panel flaps <NUM> may be coupled to the substrate <NUM> by fastening the snap <NUM> to the receiving snap <NUM> and later un-coupled via the snap <NUM> and receiving snap <NUM>. By way of another example, the one or more side panel flaps <NUM> may include a hook and loop fastening assembly including a loop portion coupled to the flap <NUM> and a hook portion coupled to the substrate <NUM> and then later un-coupled via the hook and loop fastening assembly.

In a step <NUM>, a force may be applied to disengage the seatback frame <NUM> and the channel <NUM>. For example, the force may be applied through an application of force on the attachment system <NUM> in a specific direction to cause the attachment system <NUM> to disengage from the seatback frame <NUM>. For instance, the force may be applied through an application of force in an upward direction from the channel <NUM> of the substrate <NUM>. In this regard, the force may be applied to disengage the seatback frame <NUM> from the channel <NUM> until the substrate <NUM> un-snaps from the seatback frame <NUM>.

Referring to <FIG>, when the attachment system <NUM> disengages with the seatback frame <NUM>, the attachment system <NUM> may be configured to prevent the diaphragm <NUM> from cutting into the side panel <NUM>. For example, the substrate <NUM> may be coupled to the side panel <NUM> such that a portion of the substrate <NUM> overlaps with a portion of the side panel <NUM>. In this regard, the substrate <NUM> of the overlap is configured to prevent the diaphragm <NUM> from cutting into the side panel. In this regard, the attachment system <NUM> may be easily removed without removing the diaphragm <NUM> and/or damaging the diaphragm <NUM>.

In a step <NUM>, the seatback frame <NUM> may be removed from the channel of the substrate. For example, the seatback frame elements <NUM> of the seatback frame <NUM> may be removed from the channel <NUM> of the substrate <NUM> when the attachment system is fully disengaged with the frame <NUM>.

It is noted herein the methods or processes <NUM>, <NUM> is not limited to the steps and/or sub-steps provided. The methods or processes <NUM>, <NUM> may include more or fewer steps and/or sub-steps. In addition, the methods or processes <NUM>, <NUM> may perform the steps and/or sub-steps simultaneously. Further, the methods or processes <NUM>, <NUM> may perform the steps and/or sub-steps sequentially, including in the order provided or an order other than provided. Therefore, the above description should not be interpreted as a limitation on the scope of the disclosure but merely an illustration.

Although embodiments of the disclosure illustrate coupling or uncoupling various components of the attachment system <NUM> from above as illustrated in at least <FIG>, it is noted herein various component of the attachment system <NUM> may be coupled or uncoupled from a front or rear direction with enough applied force. Therefore, the above description should not be interpreted as a limitation on the scope of the disclosure but merely an illustration.

It is noted herein the seatback cover attachment system <NUM> may be configured to work with any aircraft seat <NUM> and/or any set of components in the aircraft seat <NUM>. For example, the seatback cover attachment system <NUM> may be configured to take into account any changes in shape of the components of the aircraft seat <NUM> (e.g., within an x-y plane forming a seating surface for an occupant), where the changes in shape may be caused by or otherwise dependent on the location of the aircraft seat <NUM> within the aircraft cabin.

Although embodiments of the disclosure illustrate the seatback cover attachment system <NUM> being integrated within the aircraft seat <NUM>, it is noted herein, however, that the seatback cover attachment system <NUM> and/or components of the seatback cover attachment system <NUM> are not limited to the aviation environment and/or the aircraft components within the aviation environment. For example, the seatback cover attachment system <NUM> and/or components of the seatback cover attachment system <NUM> may be configured for any type of vehicle known in the art. For instance, the vehicle may be any air, space, land, or water-based personal equipment or vehicle; any air, space, land, or water-based commercial equipment or vehicle; any air, space, land, or water-based military equipment or vehicle known in the art. By way of another example, the seatback cover attachment system <NUM> and/or components of the seatback cover attachment system <NUM> may be configured for commercial or industrial use in either a home or a business. Therefore, the above description should not be interpreted as a limitation on the present disclosure but merely an illustration.

Claim 1:
A seatback cover attachment system (<NUM>) comprising:
a substrate (<NUM>), the substrate configured to reversibly couple to a portion of a seatback frame (<NUM>), the substrate including one or more surfaces (<NUM>) that define a channel (<NUM>), the channel configured to receive a portion of the seatback frame; and
a seatback cover sub-system (<NUM>), the seatback cover sub-system comprising:
a dress cover (<NUM>); and
a side panel (<NUM>), the side panel configured to couple to a portion of the substrate, the side panel configured to couple to one or more portions of the dress cover to form the seatback cover sub-system; and
characterized in that the dress cover includes a seatback cover layer (<NUM>) and a seatback cushion layer (<NUM>), the seatback cushion layer being integrated with the seatback cover layer; and wherein:
the side panel (<NUM>) is formed of a piece of wrapped fabric (<NUM>) joined directly to a portion of the substrate by one or more seams (<NUM>), and joined to a portion of the dress cover by one or more seams; and wherein the substrate includes a contoured surface including a lowered portion (<NUM>) and a raised portion (<NUM>) on a surface (<NUM>) of the substrate and the height of the raised portion (<NUM>) is greater than or equal to the thickness of the fabric (<NUM>) of the side panel to obscure the one or more seams from a rear view of a seat to which the substrate is attached.