Assembly, system, and methods for installing conductive elements in an aircraft

There is provided a raceway cover assembly for installing conductive element(s) in an aircraft. The raceway cover assembly includes a raceway cover for removable coupling to a raceway. The raceway is configured for attachment to a sidewall assembly for use in a cabin of the aircraft. The raceway cover includes a first cover side, a second cover side, and retaining element(s) disposed on the first cover side. The raceway cover assembly further includes the conductive element(s) coupled and retained to the first cover side, with the retaining element(s), to form the raceway cover assembly. The conductive element(s) and the raceway cover are assembled together at a location off of the aircraft, prior to installing the raceway cover assembly with the one or more conductive elements in the aircraft, which allows for routing of the one or more conductive elements in the raceway cover at the location off of the aircraft.

CROSS REFERENCE TO RELATED APPLICATION

This nonprovisional patent application is related to contemporaneously filed U.S. nonprovisional patent application Ser. No. 16/459,499, titled SIDEWALL CLOSEOUT AREA ASSEMBLY, SYSTEM, AND METHOD FOR ROUTING CONDUCTIVE ELEMENTS IN AN AIRCRAFT, filed on Jul. 1, 2019, the contents of which are hereby incorporated by reference in its entirety.

FIELD

The disclosure relates generally to sidewall panel assemblies, systems, and methods for aircraft, and more particularly, to sidewall panel assemblies, systems, and methods for installing conductive elements in aircraft passenger cabins.

BACKGROUND

Aircraft, such as commercial aircraft, have sidewall panels located in an interior of an aircraft passenger cabin. Such sidewall panels are designed to cover an aircraft frame and walls, as well as to cover aircraft insulation, ducting, and conductive elements, such as electrical runs, for example, wiring and cables, and systems transport elements, for example, air lines and water lines, which are located along the length of the aircraft passenger cabin.

Conductive elements, such as electrical runs including power, data, in-flight entertainment (IFE), lighting, and other seat systems, are typically routed from behind sidewall panels or from under the floor to the seats in the aircraft passenger cabin. The conductive elements, such as electrical runs, may be installed in conduits that are attached by adhesive, or other attachment means, to the aircraft floor. These conduits are typically covered with floor coverings, such as carpet or mats, which may cause bumps and discontinuities in the floor coverings. Moreover, such floor coverings may require additional seams for breakout locations for the electrical runs. Further, secondary shielding layers may need to be installed around the electrical runs to avoid damage from potential contact sources, such as passengers or carry-on freight. However, such secondary shielding layers may be heavy and add unwanted weight to the aircraft. Also, with reconfigurable palletized seats, which have large metallic structures that are bolted to the floor of the aircraft passenger cabin, when such palletized seats are reconfigured, complex conduit or raceway layouts must be designed to avoid the large metallic structures.

Known methods of routing conductive elements in an aircraft passenger cabin exist. Such known methods may involve installing all of the conduits into the aircraft passenger cabin and then routing the conductive elements, such as electrical runs or systems transport elements, through the conduits. This may require that installers or mechanics work in positions, e.g., on their knees, for extended periods of time, while routing the conductive elements in the conduits. Further, such known methods of routing conductive elements in an aircraft passenger cabin may be time intensive, as installers and mechanics may need to leave the aircraft to retrieve each independent part or tool to install the conduits and route the conductive elements.

Moreover, aircraft components that connect to such conductive elements may not be able to be transported into the aircraft passenger cabin until the routing is completed. When such aircraft components are brought into the aircraft passenger cabin, they need to avoid the conduits which may present an obstacle, and any possible exposed ends of the conductive elements need to be protected to avoid any possible damage that may be caused by the aircraft components, by tools, or by installers or mechanics. Thus, since the conductive elements are not pre-routed in the conduit, secondary protective measures may be needed to avoid damage to the conductive elements. Further, known methods of routing conductive elements in an aircraft passenger cabin may result in numerous variable configurations and layouts that may be difficult to manage and difficult to install.

In addition, known methods of routing conductive elements in an aircraft passenger cabin do not integrate the conductive elements into an assembly that may be installed in a single step in the aircraft passenger cabin, and do not allow for the conductive elements to be installed in a conduit or raceway cover off of the aircraft at a location, such as an assembly plant or work station, that is optimized for ergonomics and part or tool availability. Moreover, such known methods of routing conductive elements in an aircraft passenger cabin may require that the conduits for a raceway be trimmed and cut to fit the conductive elements. Such trimming and cutting is typically performed with hand tools and may create Foreign Object Debris (FOD), which may cause issues with aircraft decorative surfaces. Thus, such aircraft decorative surfaces may need to be protected to avoid any possible damage. This may result in increased time and expense to protect the aircraft decorative surfaces.

Accordingly, there is a need in the art for an assembly, system, and methods for assembling and routing conductive elements off of an aircraft, prior to installation in an aircraft passenger cabin, that integrate conductive elements into an assembly or system that may be installed in a single step, that reduce the time to install the conductive elements, that increase cost savings for production, that eliminate variability in design and installation, that reduce ergonomic issues, that allow for rapid reconfiguration of seats in the aircraft passenger cabin, and that provide further advantages over known assemblies, systems, and methods.

SUMMARY

Example implementations of the present disclosure provide for an assembly, system, and methods for installing conductive elements in an aircraft. As discussed in the below detailed description, versions of the assembly, system, and methods for installing conductive elements in an aircraft may provide significant advantages over known assemblies, systems, and methods.

In a version of the disclosure, there is provided a raceway cover assembly for installing one or more conductive elements in an aircraft. The raceway cover assembly comprises a raceway cover configured for removable coupling to a raceway. The raceway is configured for attachment to a sidewall assembly for use in an interior of a cabin of the aircraft. The raceway cover comprises a first cover side configured to face an interior side of the raceway, a second cover side configured to face the interior of the cabin, and one or more retaining elements disposed on the first cover side. The raceway cover assembly further comprises the one or more conductive elements coupled and retained to the first cover side, with the one or more retaining elements, to form the raceway cover assembly.

The one or more conductive elements and the raceway cover are assembled together at a location off of the aircraft, prior to installing the raceway cover assembly in the aircraft, which allows for routing of the one or more conductive elements in the raceway cover at the location off of the aircraft.

In another version of the disclosure, there is provided a sidewall closeout area cartridge system for installing one or more conductive elements in an aircraft. The sidewall closeout area cartridge system comprises a raceway configured for attachment to a sidewall assembly for use in an interior of a cabin of the aircraft.

The sidewall closeout area cartridge system further comprises a raceway cover assembly. The raceway cover assembly comprises a raceway cover removably coupled to the raceway. The raceway cover has a first cover side facing an interior side of the raceway, a second cover side configured to face the interior of the cabin, and one or more retaining elements disposed on the first cover side. The raceway cover assembly further comprises the one or more conductive elements coupled and retained to the first cover side, with the one or more retaining elements.

The raceway cover assembly and the raceway are assembled together at a location off of the aircraft, to form the sidewall closeout area cartridge system, prior to installing the sidewall closeout area cartridge system in the aircraft, which allows for routing of the one or more conductive elements in the sidewall closeout area cartridge system at the location off of the aircraft.

In another version of the disclosure, there is provided a method for installing one or more conductive elements in an aircraft. The method comprises the step of assembling a raceway cover assembly, by coupling and retaining the one or more conductive elements to a first cover side of a raceway cover, with one or more retaining elements disposed on the first cover side.

The method further comprises the step of installing the one or more conductive elements in the aircraft, by removably coupling the raceway cover assembly, via a snap-in installation, to a raceway. The raceway is attached to a bottom end of an air grille panel of a sidewall assembly in an interior of a cabin of the aircraft. The raceway cover assembly is assembled at a location off of the aircraft, prior to the snap-in installation of the raceway cover assembly to the raceway, which allows for routing of the one or more conductive elements in the raceway cover at the location off of the aircraft.

In another version of the disclosure, there is provided a method for installing one or more conductive elements in an aircraft. The method comprises the step of assembling a sidewall closeout area cartridge system, by removably coupling a raceway cover assembly, via a snap-in installation, to a raceway. The raceway cover assembly comprises a raceway cover having a first cover side facing an interior side of the raceway, a second cover side configured to face an interior of a cabin of the aircraft, and one or more retaining elements disposed on the first cover side. The raceway cover assembly further comprises the one or more conductive elements coupled and retained to the first cover side, with the one or more retaining elements.

The method further comprises the step of installing the one or more conductive elements in the aircraft, by attaching the sidewall closeout area cartridge system, via an attached installation, to a sidewall assembly in the interior of the cabin of the aircraft. The sidewall closeout area cartridge system is assembled at a location off of the aircraft, prior to the attached installation of the sidewall closeout area cartridge system to the sidewall assembly, which allows for routing of the one or more conductive elements in the sidewall closeout area cartridge system at the location off of the aircraft.

The features, functions, and advantages that have been discussed can be achieved independently in various versions of the disclosure or may be combined in yet other versions further details of which can be seen with reference to the following description and drawings.

The figures shown in this disclosure represent various aspects of the versions presented, and only differences will be discussed in detail.

DETAILED DESCRIPTION

Disclosed versions will now be described more fully hereinafter with reference to the accompanying drawings, in which some, but not all of the disclosed versions are shown. Indeed, several different versions may be provided and should not be construed as limited to the versions set forth herein. Rather, these versions are provided so that this disclosure will be thorough and fully convey the scope of the disclosure to those skilled in the art.

Now referring to the Figures,FIG. 1Ais an illustration of a functional block diagram showing an exemplary version of a raceway cover assembly10of the disclosure, coupled to, and configured to couple to, a raceway18, andFIG. 1Bis an illustration of a functional block diagram showing an exemplary version of a sidewall closeout area cartridge system11of the disclosure, coupled to, and configured to couple to, an air grille panel166of a sidewall assembly26for use in a vehicle14, such as an aircraft16, a boat15, a train17, or another suitable vehicle designed to carry passengers.

In a version of the disclosure, there is provided a raceway cover assembly10(seeFIG. 1A) for installing one or more conductive elements50(seeFIG. 1A) in the vehicle14(seeFIG. 1B), such as the aircraft16(seeFIG. 1B), or other suitable vehicle. As shown inFIG. 1A, the raceway cover assembly10comprises a raceway cover (RC)90configured for removable coupling or attachment, and is removably coupled or attached, to the raceway18. The raceway18is configured for attachment, and is attached, to the sidewall assembly26(seeFIG. 1B) for use in an interior112(seeFIG. 1B) of a cabin48(seeFIG. 1B), such as a passenger cabin48a(seeFIG. 1B), of the vehicle14, such as the aircraft16.

As shown inFIG. 1A, in one version, the raceway cover90comprises a snap-in raceway cover (RC)92. The raceway cover90, such as in the form of the snap-in raceway cover92, is configured for a snap-in installation94(seeFIG. 1A), to the raceway18. The raceway cover90, such as in the form of the snap-in raceway cover92, comprises a bottom end96(seeFIGS. 1A, 4A), tab members98(seeFIGS. 1A, 4A) formed near the bottom end96, that are configured to couple to a raceway track portion23(seeFIGS. 1A, 9B) of the raceway18(seeFIGS. 1A, 9B), and a top end100(seeFIGS. 1A, 4A) that is configured to slide under and abut against an underside43(seeFIG. 1A) of one or more flange portions42(seeFIGS. 1A, 7) of the raceway18.

The raceway cover90, such as in the form of the snap-in raceway cover92, is easily coupled to the aircraft floor structure32and to the raceway18, and is easily removable from the aircraft floor structure32and from the raceway18. The raceway cover90, such as in the form of the snap-in raceway cover92, does not require any additional fastener elements104(seeFIG. 1A) to couple, or attach, the raceway cover90to the raceway18.

In another version, the raceway cover90may comprise a fastened raceway cover (RC)106(seeFIG. 1A) that may be fastened to the raceway18and/or to the aircraft floor structure32with one or more fastener elements104(seeFIG. 1A), such as bolts, screws, clips, or other suitable fastener elements.

As shown inFIG. 1A, the raceway cover90further comprises a first cover side108(see alsoFIG. 4A) configured to face, and facing, an interior side19a(see alsoFIG. 7) of the raceway18. As shown inFIG. 1A, the raceway cover90further comprises a second cover side110configured to face, and facing, the interior112(seeFIGS. 1B, 8B) of the cabin48, when the raceway cover90is coupled, or attached, to the raceway18.

As shown inFIG. 1A, the raceway cover90further comprises one or more retaining elements95(see alsoFIG. 4C) disposed on the first cover side108. The one or more retaining elements95disposed on the first cover side108of the raceway cover90comprise one or more of, clips95a(seeFIG. 1A), clamps95b(seeFIG. 1A), hooks95c(seeFIG. 1A), or other suitable retaining elements, to retain one or more conductive elements50along the first cover side108of the raceway cover90. The raceway cover90may further comprise one or more flange elements102(seeFIGS. 1A, 4A) positioned and spaced along the top end100of the raceway cover90.

The raceway cover90of the raceway cover assembly10preferably comprises a unitary structure118(seeFIG. 1A). The raceway cover90of the raceway cover assembly10preferably has a length119(seeFIG. 1A) based on how far apart the seats182(seeFIG. 1B) are configured in the cabin48(seeFIG. 1B), depending on whether the seats182are in economy class, business class, or first class. For example, the raceway cover90may have a length119in a range of from 28 inches to 36 inches (e.g., in economy class), may have a length119in a range of from 36 inches to 42 inches (e.g., business class), may have a length119in a range of from 42 inches to 64 inches (e.g., first class), or may have another suitable length.

The raceway cover90may include one or more access openings114(seeFIG. 1A) formed through the raceway cover90. The one or more access openings114(seeFIG. 1A) may provide access to the interior cabin48of the vehicle14, such as the aircraft16, and may provide access to an overfloor area116(seeFIG. 1B) in the cabin48, for the one or more conductive elements50retained in the raceway cover90.

When two or more raceway cover assemblies10(seeFIGS. 1A, 6C, 8B), such as a plurality of raceway cover assemblies10a(seeFIG. 1A), are each removably coupled to the raceway18(seeFIGS. 1A, 6C, 8B), the two or more raceway cover assemblies10are preferably positioned in a longitudinal fore-aft alignment56(seeFIGS. 1A, 6C, 8B). In one version, the raceway covers90may be in the form of a plurality of raceway cover (RC) sections120(seeFIGS. 1A, 8B), such as in the form of adjacent raceway cover (RC) sections120a(seeFIGS. 1A, 8B), aligned adjacent to each other, or configured to be aligned adjacent to each other, along the raceway18. Intermittent routing breakouts139(seeFIGS. 1A, 6C, 8B) may be formed between end portions122(seeFIGS. 1A, 8B) of the raceway cover sections120that are aligned.

As shown inFIG. 1A, the raceway cover assembly10further comprises one or more conductive elements50coupled and retained to the first cover side108, with the one or more retaining elements95, to form the raceway cover assembly10. The one or more conductive elements50comprise one or more of, wires60, cables62including electrical cables62a, data bus cables62b, high speed transmission cables62c, coaxial cables62d, fiber optic cables62e, or other suitable cables, printed circuit boards (PCBs)64, tubes66, capacitors68, and other suitable conductive elements.

As shown inFIG. 1A, the one or more conductive elements50further comprise one or more electrical runs70comprising one or more of, power runs72, data runs74, lighting system runs76, and seat system runs78, including in-flight entertainment (IFE) system runs80, seat actuation runs82, and personal electronic device (PED) runs84, and other suitable electrical runs.

As shown inFIG. 1A, the one or more conductive elements50further comprise one or more systems transport elements85comprising one or more of, pneumatic lines85a, air lines85b, fluid lines85c, water lines85d, or other suitable systems transport elements. For example, the pneumatic lines85aor air lines85bmay be used for lumbar support in seats182(seeFIG. 1B) in the cabin48(seeFIG. 1B), or for passenger air vents, and the fluid lines85cor water lines85dmay be used for a potable water supply, or vending drink service to seats182, such as in first class.

The one or more conductive elements50are preferably short in length and comprise one or more short length conductive elements50b(seeFIG. 1A), when attached or coupled to the first cover side108of the raceway cover90. The one or more conductive elements50, such as in the form of continuous conductive elements50a(seeFIG. 1A), are preferably long in length and continuous, when attached or coupled along the raceway18. Each end of the conductive element50(seeFIGS. 1A, 4A) and each end of the continuous conductive element50a(seeFIG. 1A, 5) preferably has a connector portion51(seeFIGS. 1A, 4A, 5) configured to connect to, and connecting to, a connector element, for example, an electrical disconnect bracket (not shown), an integrated connector (not shown), or other suitable connector elements, in the seats182(seeFIG. 1B), in a crown area46(seeFIG. 1B) above the cabin48(seeFIG. 1B), in an underfloor area52(seeFIG. 1B) below the cabin48, in an overfloor area116(seeFIG. 1B), or in another area of the cabin48. Each continuous conductive element50apreferably has a greater or longer length than each short length conductive element50b.

The raceway cover assembly10, which includes the one or more conductive elements50and the raceway cover90, are preferably assembled together at a location200(seeFIG. 1A) off of the vehicle14, such as the aircraft16, prior to installing the raceway cover assembly10in the vehicle14, such as the aircraft16. This allows for routing of the one or more conductive elements50in the raceway cover90at the location200off of the aircraft16. Thus, the raceway cover assembly10does not require routing of the one or more conductive elements50, such as the short length conductive elements50b, on the vehicle14, such as the aircraft16. As shown inFIGS. 1A-1B, the location200may comprise an assembly plant202, a production facility204, a work station206, a work bench208, or another suitable location off of the vehicle14, such as the aircraft16.

As further shown inFIG. 1A, the raceway cover assembly10, or a plurality of raceway cover assemblies10a, are removably coupled or attached to the raceway18. The raceway18comprises an interior side19a(seeFIGS. 1A, 5, 9A), an exterior side19b(seeFIGS. 1A, 9A), a first end20(seeFIGS. 1A, 9A), a second end21(seeFIGS. 1A, 9A), and a raceway body (RB)24(seeFIGS. 1A, 9A), such as an elongated raceway body (RB)24a(seeFIGS. 1A, 9A), formed between the first end20and the second end21. The raceway18further comprises a raceway track portion23(seeFIGS. 1A, 5, 9A) with openings25(seeFIGS. 1A, 5, 9A) formed through the raceway track portion23.

The first end20of the raceway18is configured to attach, and attaches, to the sidewall assembly26(seeFIG. 1B), for example, to a bottom portion28(seeFIGS. 1B, 3A) of the sidewall assembly26. In particular, the raceway18is attached to a bottom end168a(seeFIGS. 1B, 3A, 5) of an air grille panel166(seeFIGS. 1B, 3A, 5) of the sidewall assembly26(seeFIGS. 1B, 3A). The raceway cover assembly10(seeFIGS. 1A, 3A) is installed in the cabin48(seeFIGS. 1B, 3A), via a snap-in installation94(seeFIG. 1A), to the raceway18(seeFIGS. 1A, 3A, 5). The one or more continuous conductive elements50a(seeFIGS. 1A, 5) are preferably routed along and installed in the raceway18, prior to the raceway cover assembly10being installed, via the snap-in installation94, to the raceway18.

In one version, the first end20of the raceway18may be attached to the sidewall assembly26with a plurality of attachment elements30(seeFIGS. 1A, 9C), for example, brackets30a(seeFIGS. 1A, 9C), clips30b(seeFIG. 1A), bolts30c(seeFIG. 1A), or other suitable attachment elements. Alternatively, the first end20of the raceway18may be attached or bonded to the sidewall assembly26with adhesive, or with another suitable means of attachment.

In another version, the first end20of the raceway18may be integrated with, or formed with, the sidewall assembly26, such as the bottom portion28of the sidewall assembly26, so that the sidewall closeout area assembly12is an integrated structure31(seeFIG. 1A). The sidewall assembly26is discussed in further detail below.

The second end21of the raceway18is configured to attach, and attaches, to one or more aircraft floor structures32(seeFIG. 1B), discussed in further detail below. The second end21of the raceway18may be attached to the one or more aircraft floor structures32with a plurality of attachment elements30(seeFIG. 1A), for example, brackets30a(seeFIG. 1A), clips30b(seeFIG. 1A), bolts30c(seeFIG. 1A), or other suitable attachment elements, or may be attached or bonded with adhesive, or may be attached with another suitable means of attachment.

As shown inFIG. 1A, the raceway body24has a first side34and a second side36. The first side34is configured to face, and faces, an interior frame38(seeFIGS. 1B, 3B) of the vehicle14(seeFIG. 3B), such as the aircraft16(seeFIG. 3B), when the raceway18is installed in the vehicle14, such as the aircraft16. When the raceway cover90of the raceway cover assembly10is coupled, or attached, to the raceway18, the second side36of the raceway body24faces the first cover side108of the raceway cover90.

The raceway body24may comprise one or more access openings40(seeFIGS. 1A, 8A) formed through the raceway body24. The raceway body24may comprise flange portions42(seeFIG. 1A, 5, 9A) extending inboard, or inwardly from the second side36(seeFIGS. 1A, 9A), of the raceway body24and extending along a length44(seeFIG. 1A) of the raceway18. The raceway body24of the raceway18further comprises fin portions45(seeFIGS. 1A, 9A) near the first end20.

The one or more access openings40may optionally provide access to the crown area46(seeFIG. 1B) located above the cabin48(seeFIG. 1B), such as the passenger cabin48a(seeFIG. 1B), in the aircraft16, for the one or more conductive elements50, such as the one or more continuous conductive elements50a(seeFIGS. 1A, 5), routed along the raceway18. The routing of the one or more conductive elements50, such as the one or more continuous conductive elements50a, along the raceway18is meant to also allow for not having to route to the crown area46, but may be optionally routed to the crown area46, if desired. The one or more access openings40further provide access to the underfloor area52(seeFIG. 1B) located below the cabin48, such as the passenger cabin48a, in the aircraft16, for the one or more conductive elements50, such as the one or more continuous conductive elements50a(seeFIGS. 1A, 5), routed along the raceway18.

The raceway body24may comprise two or more raceway body (RB) sections54(seeFIGS. 1A, 8A) aligned adjacent to each other, or configured to be aligned adjacent to each other, in the longitudinal fore-aft alignment56(seeFIGS. 1A, 8A). When the raceway body24of the raceway18comprises two or more raceway body sections54, the one or more access openings40are preferably formed between end portions58(seeFIGS. 1A, 8A) of adjacent raceway body sections54a(seeFIGS. 1A, 8A).

As shown inFIG. 1A, a closeout area142(see alsoFIG. 9B), or space, is formed between the interior side19aof the raceway18, and the first cover side108of the raceway cover90, when the raceway cover assembly10is removably coupled to the raceway18. The closeout area142is configured to house and protect, and houses and protects, the one or more conductive elements50, such as the one or more short length conductive elements50b, retained by the raceway cover90, and the one or more conductive elements50, such as the one or more continuous conductive elements50a, routed along the raceway18. In addition, the raceway cover90prevents moisture and debris from falling inside or entering the closeout area142. A cross-sectional area144(seeFIG. 1A) of the closeout area142is sufficiently large to house the one or more conductive elements50and sufficiently small to provide effective support and bundling of the one or more conductive elements50. Preferably, the cross-sectional area144has a height in a range of about 0.5 (one-half) inch to about 5.0 (five) inches. However, the cross-sectional area144may also have another suitable height.

Optionally, one or more breakout covers (BCs)124(seeFIGS. 1A, 3A, 8C) may be positioned between two or more raceway cover sections120(seeFIG. 8C) and removably coupled, or attached, to the raceway18(seeFIGS. 1A, 3A, 8C). The one or more access openings114(seeFIGS. 1A, 8C) may be in the form of one or more breakout cover (BC) openings126(seeFIGS. 1A, 3A, 8C) formed in and through the one or more breakout covers124. In this version, the access openings114are not through the raceway cover sections120but are through the breakout covers124aligned in-between the raceway cover sections120, and are in the form of the breakout cover openings126for routing the one or more conductive elements50(seeFIGS. 1A, 3A, 8C), such as the one or more short length conductive elements50b(seeFIGS. 1A, 8C), out of the raceway cover assembly10and into the interior112(seeFIGS. 1B, 8C) of the cabin48(seeFIGS. 1B, 8C) and the overfloor area116(seeFIG. 1B) in the cabin48.

In one version, the breakout cover124comprises a snap-in breakout cover (BC)128(seeFIGS. 1A, 8C). The breakout cover124, such as in the form of the snap-in breakout cover128, is installed via a breakout cover snap-in installation130(seeFIG. 1A). The breakout cover124, such as in the form of the snap-in breakout cover128, has a bottom end132(seeFIGS. 1A, 8C), and has tab members134(seeFIG. 1A) located near the bottom end132that may be configured to couple, and may couple, to the raceway track portion23(seeFIGS. 1A, 8C) of the raceway18. The breakout cover124, such as in the form of the snap-in breakout cover128, further has a top end136(seeFIGS. 1A, 8C) that is configured to slide under and abut against an underside43(seeFIGS. 1A, 9B) of the flange portions42(seeFIGS. 1A, 9B) of the raceway18(seeFIGS. 1A, 9B). The breakout cover124, such as in the form of the snap-in breakout cover128, is easily removably coupled to the raceway18, and is easily removable from the raceway18, and that does not require any additional fastener elements104(seeFIG. 1A) to couple or attach the breakout cover124to the raceway18.

In another version, the breakout cover124may comprise a fastened breakout cover138(seeFIG. 1A) that may be fastened to the raceway18with one or more fastener elements104(seeFIG. 1A), such as bolts, screws, clips, or other suitable fastener elements.

The raceway cover assembly10, the raceway19, and the closeout area142form a sidewall closeout area assembly12(seeFIG. 1A). The sidewall closeout area assembly12may optionally include the breakout cover124(seeFIG. 1A). The sidewall closeout area assembly12facilitates accessibility to the one or more conductive elements50. In addition, the sidewall closeout area assembly12provides a routing path86(seeFIG. 1A) for the one or more conductive elements50that does not need to be reconfigured for different aircraft cabin layouts87(seeFIG. 1A). The sidewall closeout area assembly12provides a systems routing88(seeFIG. 1A) for the one or more conductive elements50, for example, the one or more electrical runs70, or the one or more systems transport elements85, through the cabin48, such as the passenger cabin48a, of the vehicle14, such as the aircraft16.

In addition, the sidewall closeout area assembly12(seeFIG. 1A) has the advantage of improving a bend radius194(seeFIG. 1A) of the one or more conductive elements50(seeFIG. 1A), for example, wires60(seeFIG. 1A) and cables62(seeFIG. 1A), by allowing the wires60and cables62to bend or turn more easily out of the access openings40(seeFIG. 1A), the intermittent routing breakouts139(seeFIG. 1A), and the access openings114(seeFIG. 1A), including the breakout cover openings126(seeFIG. 1A), to the crown area46(seeFIG. 1B), to the underfloor area52(seeFIG. 1B), to the interior112(seeFIG. 1B) of the cabin48(see FIG.1B), to the overfloor area116(seeFIG. 1B), to the seat shroud188(seeFIG. 1B), and/or to the seat legs184(seeFIG. 1B).

The sidewall closeout area assembly12preferably has a modular design146(seeFIG. 1A) that allows the sidewall closeout area assembly12to be easily configured to accommodate any aircraft layout. The sidewall closeout area assembly12is installed in and makes use of an unused volume148(seeFIG. 1A) of the vehicle14, such as the aircraft16, and eliminates the congestion of wires60(seeFIG. 1A) and cables62(seeFIG. 1A), or other conductive elements50, on the overfloor area116(seeFIG. 1B) of the cabin48(seeFIG. 1B). The sidewall closeout area assembly12provides for a floor penetration elimination150(seeFIG. 1A) of unnecessary floor penetrations or holes151(seeFIG. 2B) through a floor152(seeFIG. 1B) or a ceiling153(seeFIG. 1B) of the cabin48. The sidewall closeout area assembly12further provides for variability elimination154(seeFIG. 1A) in design and installation of systems routing88(seeFIG. 1A) in the vehicle14, such as the aircraft16, and provides a functional electrical conduit156(seeFIG. 1A) through a length158(seeFIG. 1B) of the cabin48.

The raceway18, the raceway cover90, and the breakout cover124are preferably made of one or more nonconductive materials140(seeFIG. 1A). Some exemplary nonconductive materials140that may be used include composite materials, such as high performance thermoplastics, fiber reinforced plastics, and other types of rigid plastic materials, for example, polyetherketoneketone (PEKK), polyetheretherketone (PEEK), polyvinyl fluoride (PVF), or another suitable rigid plastic material. The raceway18may also be made of a metal material or another suitable material.

Now referring toFIG. 1B, in another version of the disclosure, there is provided the sidewall closeout area cartridge system11for installing one or more conductive elements50a vehicle14, such as an aircraft16. As shown inFIG. 1B, the sidewall closeout area cartridge system11comprises the raceway18, which is configured to attach, and attaches, to a sidewall assembly26for use in an interior112of the cabin48, such as the passenger cabin48a, of the vehicle14, such as the aircraft16. The raceway18(seeFIGS. 1A-1B) has the interior side19a(seeFIG. 1A) and the exterior side19b(seeFIG. 1A). The interior side19ais configured to face, and faces, the first cover side108of the raceway cover90(seeFIGS. 1A-1B), when the raceway cover90is removably coupled to the raceway18, via a snap-in installation94(seeFIG. 1A). The exterior side19bis configured to face, and faces, the interior frame38(seeFIGS. 1B, 3B) of the aircraft16(seeFIG. 1B), when the raceway18is coupled or attached to the sidewall assembly26in the aircraft16. The sidewall assembly26(seeFIG. 1B) is configured for installation, and is installed, in the interior112(seeFIG. 1B) of the cabin48(seeFIG. 1B), such as the passenger cabin48a(seeFIG. 1B), of the vehicle14, such as the aircraft16.

As shown inFIG. 1B, the sidewall closeout area cartridge system11further comprises the raceway cover assembly10. The raceway cover assembly10comprises the raceway cover90(seeFIGS. 1A-1B) removably coupled to the raceway18. The raceway cover90has the first cover side108facing the interior side19a(seeFIG. 1A) of the raceway18, and facing the second side36(seeFIG. 1A) of the raceway body24(seeFIG. 1A), when the raceway cover90is coupled, or attached, to the raceway18. The raceway cover90(seeFIG. 1B) further has the second cover side110(seeFIG. 1B) configured to face, and facing, the interior112of the cabin48, such as the passenger cabin48a, when the raceway cover90is coupled, or attached, to the raceway18in the vehicle14, such as the aircraft16. The raceway cover90(seeFIG. 1B) further has one or more retaining elements95(seeFIG. 1B) disposed on the first cover side108. The sidewall closeout area cartridge system11further comprises the one or more conductive elements50(seeFIG. 1B) coupled and retained to the first cover side108, with the one or more retaining elements95.

The raceway cover assembly10(seeFIG. 1B) and the raceway18(seeFIG. 1B) are preferably assembled together at a location200(seeFIG. 1B) off of the vehicle14(seeFIG. 1B), such as the aircraft16(seeFIG. 1B), to form the sidewall closeout area cartridge system11, prior to installing the sidewall closeout area cartridge system11having the one or more conductive elements50(seeFIG. 1B) in the vehicle14, such as the aircraft16. This allows for routing of the one or more conductive elements50in the sidewall closeout area cartridge system11at the location200off of the aircraft16.

The sidewall closeout area cartridge system11(seeFIG. 1B) is configured for installation, and is installed, via an attached installation198(seeFIG. 1B) in the cabin48, such as the passenger cabin48a, of the vehicle14, such as the aircraft16, between an air grille panel166(seeFIG. 1B) of the sidewall assembly26(seeFIG. 1B) and an aircraft floor structure32(seeFIG. 1B). As shown inFIG. 1B, the aircraft floor structure32may comprise one or more of, a fore-aft longitudinal floor grid structure176, a longitudinal seat track178, a floor panel180, or another suitable aircraft floor structure.

As discussed above, the one or more conductive elements50of the sidewall closeout area cartridge system11comprise, as shown inFIG. 1A, one or more of, wires60, cables62including electrical cables62a, data bus cables62b, high speed transmission cables62c, coaxial cables62d, and fiber optic cables62e, printed circuit boards (PCBs)64, tubes66, and capacitors68. In addition, the one or more conductive elements50of the sidewall closeout area cartridge system11comprise, as shown inFIG. 1A, one or more electrical runs70comprising one or more of, power runs72, data runs74, lighting system runs76, and seat system runs78, including in-flight entertainment (IFE) system runs80, seat actuation runs82, and personal electronic device (PED) runs84, and comprise one or more systems transport elements85comprising one or more of, pneumatic lines85a, air lines85b, fluid lines85c, and water lines85d.

For the one or more conductive elements50(seeFIG. 1A-1B), such as the one or more continuous conductive elements50a(seeFIG. 1B), that are routed along the raceway18, the raceway18preferably has access openings40(seeFIGS. 1A, 8A) that provide access for the one or more conductive elements50, such as the one or more continuous conductive elements50a, to one or more of, the crown area46(seeFIGS. 1B, 2A) above the ceiling153(seeFIGS. 1B, 2A) of the cabin48(seeFIGS. 1B, 2A), the underfloor area52(seeFIGS. 1B, 2A) below the floor152(seeFIGS. 1B, 2A) of the cabin48, or another area of the cabin48. For the one or more conductive elements50(seeFIG. 1A-1B), such as the one or more short length conductive elements50b(seeFIG. 1B), that are retained in the raceway cover90, an intermittent routing breakout139(seeFIGS. 1A, 6C, 8B) between raceway covers90(seeFIG. 8B) of two raceway cover assemblies10(seeFIG. 8B), or a breakout cover opening126(seeFIG. 8C) in a breakout cover124(seeFIG. 8B) coupled between the raceway covers90(seeFIG. 8C) of the two raceway cover assemblies10(seeFIG. 8C), provide access for the one or more conductive elements50to the overfloor area116(seeFIG. 1B) in the cabin48, to the seats182(seeFIG. 1B) in the cabin48, or to another area in the interior112of the cabin48.

As shown inFIG. 1B, the sidewall closeout area cartridge system11, or a plurality of sidewall closeout area cartridge systems11a, may be attached to one or more air grille panels166of the sidewall assembly26, to form an air grille panel cartridge assembly13, or a plurality of air grille panel cartridge assemblies13a. The air grille panel cartridge assembly13, or the plurality of air grille panel cartridge assemblies13a, may be assembled at the location200(seeFIG. 1B) off of the vehicle14, such as the aircraft16, and each air grille panel cartridge assembly13is configured for installation, and installed, in the cabin48, such as the passenger cabin48a, between a sidewall panel160(seeFIG. 1B) of the sidewall assembly26(seeFIG. 1B) and an aircraft floor structure32(seeFIG. 1B).

As shown inFIG. 1B, the sidewall assembly26comprises the bottom portion28(see alsoFIG. 3A) and the top portion29(see alsoFIG. 3A). As shown inFIG. 1B, the sidewall assembly26further comprises one or more sidewall panels160(seeFIG. 1B). Each sidewall panel160(seeFIGS. 1B, 3A) has a bottom end162a(seeFIGS. 1B, 3A) and a top end162b(seeFIGS. 1B, 3A), and an interior side164a(seeFIGS. 1B, 3A) and an exterior side164b(seeFIG. 1B). Each sidewall panel160is coupled or attached to one or more air grille panels166(seeFIGS. 1B, 3A). Each air grille panel166has a bottom end168a(seeFIGS. 1B, 3A) and a top end168b(seeFIGS. 1B, 3A), and an interior side170a(seeFIGS. 1B, 3A) and an exterior side170b(seeFIG. 1B). Each air grille panel166has one or more air grille openings172(seeFIGS. 1B, 3A). An air grille174(seeFIGS. 1B, 9C) is fitted and retained within each air grille opening172. The first end20of the raceway18is configured to attach, and attaches, to the bottom end168aof each of the air grille panels166of the sidewall assembly26. The air grille panels166may also be referred to as decompression panels or decompression grilles or air vents.

As further shown inFIG. 1B, the vehicle14, such as the aircraft16, includes in the cabin48, such as the passenger cabin48a, a plurality of seats182for passengers. The seats182may be in the form of palletized seats182athat are reconfigurable to change seat pitches of the seats182, and that are reconfigurable along the longitudinal seat tracks178. As further shown inFIG. 1B, the seats182have seat legs184, seat track covers186to cover the longitudinal seat tracks178, and seat shrouds188. In addition to the raceway cover90(seeFIGS. 1A-1B) that preferably prevents moisture and debris from falling inside or entering the closeout area142(seeFIG. 1A) of the sidewall closeout area assembly12, the aircraft16may include a mopsill190(seeFIG. 1B) and a seal192(seeFIG. 1B), such as a bulb seal, to facilitate routing any moisture and debris out of the bottom portion28(seeFIG. 1A) of the sidewall assembly26(seeFIG. 1A) and away from interior of the sidewall closeout area assembly12. The mopsill190may run on the outboard side of the floor panel180(seeFIG. 1B) and also provides a drain guide.

Now referring toFIG. 2A,FIG. 2Ais an illustration of a back cross-sectional view of a cabin48, such as a passenger cabin48a, of a vehicle14, such as an aircraft16, showing a routing path86for the one or more conductive elements50(seeFIG. 1A) accessing a crown area46and accessing an underfloor area52, via the sidewall closeout area assembly12, which includes the raceway cover assembly10(seeFIG. 1A) and the raceway18(seeFIG. 1A). As shown inFIG. 2A, the cabin48has a floor152, a ceiling153, seats182with seat legs184, the sidewall assembly26with the sidewall panel160and the air grille panel166, and the sidewall closeout area assembly12, in the interior112of the cabin48. As shown inFIG. 2A, the routing path86runs along the interior frame38of the aircraft16from the sidewall closeout area assembly12to the crown area46of the aircraft16. The routing of the one or more conductive elements50is meant to also allow for not having to route to the crown area46, but may be optionally routed to the crown area46, if desired. As further shown inFIG. 2A, the routing path86runs from the sidewall closeout area assembly12to the underfloor area52of the aircraft16and does not penetrate through the floor152of the cabin48.

Now referring toFIG. 2B,FIG. 2Bis an illustration of a back cross-sectional view of a cabin48, such as a passenger cabin48a, of a vehicle14, such as an aircraft16, showing a known routing path196accessing a crown area46and accessing an underfloor area52, via a hole151in the floor152at an inboard seat leg area193.FIG. 2Bshows the seats182with seat legs184, the sidewall panel160, and the air grille panel166in the interior112of the cabin48. As shown inFIG. 2B, the known routing path196runs along the interior frame38of the aircraft16from the crown area46to the inboard seat leg area193and penetrates through the floor152of the cabin48to the underfloor area52. The known routing path196through the floor152causes variation in the floor panels180(seeFIG. 1B), holes151in the floor152, floor covering protrusions, and variation.

Now referring toFIG. 3A,FIG. 3Ais an illustration of a front perspective view of a cabin48, such as a passenger cabin48a, of a vehicle14, such as an aircraft16, showing a version of the raceway cover assembly10of the disclosure removably coupled to the raceway18, where the raceway cover assembly10and the raceway18form the sidewall closeout area assembly12. As shown inFIG. 3A, the seats182are in the form of palletized seats182awith one set of seat legs184retained in a longitudinal seat track178along aircraft floor structures32in the form of floor panels180forming the floor152in the interior112of the cabin48.FIG. 3Ashows the raceway18coupled, or attached, to the bottom portion28of the sidewall assembly26.FIG. 3Ashows the top portion29of the sidewall assembly26and shows the sidewall assembly26comprising sidewall panels160with a bottom end162a, a top end162b, and an interior side164a. As shown inFIG. 3A, the sidewall panels160are coupled, or attached, to air grille panels166having a bottom end168a, a top end168b, and an interior side170a. Each air grille panel166has an air grille opening172(seeFIG. 3A), and preferably, the bottom end168aof the air grille panels166is coupled, or attached, to the raceway18of the sidewall closeout area assembly12.FIG. 3Afurther shows the breakout cover124, with the breakout cover opening126, removably couple to the raceway18. Two conductive elements50, such as in the form of electrical runs70(seeFIG. 3A), each having connector portions51, are routed out of the breakout cover opening126.

Now referring toFIG. 3B,FIG. 3Bis an illustration of a back perspective view of the cabin48, such as the passenger cabin48a, ofFIG. 3A, of the vehicle14, such as the aircraft16, showing raceway cover assemblies10adjacent breakout covers124.FIG. 3Bshows the seats182, such as palletized seats182a, with one set of seat legs184retained in the longitudinal seat track178along aircraft floor structures32in the form of floor panels180forming the floor152in the interior112of the cabin48.FIG. 3Bfurther shows the underfloor area52under the floor152and under the seats182.FIG. 3Bfurther shows the sidewall closeout area assembly12coupled, or attached, to the bottom end168aof the air grille panels166of the sidewall assembly26.

FIG. 3Bfurther shows the top end168b, the interior side170a, and the air grille opening172of the air grille panel166, and shows the top end168bcoupled, or attached, to the bottom end162aof the sidewall panel160.FIG. 3Bshows the interior side164aof the sidewall panel160.FIG. 3Bfurther shows the raceway cover90, such as in the form of the snap-in raceway cover92, of the raceway cover assembly10. The conductive elements50, such as electrical runs70, for example, wires60(seeFIG. 1A) and/or cables62(seeFIG. 1A), or other conductive elements50, each having connector portions51, are routed out of the breakout cover openings126. A continuous conductive element50a(seeFIG. 3B) is routed along the raceway18.FIG. 3Bfurther shows the raceway track portion23of the raceway18.

Now referring toFIGS. 4A-4C,FIG. 4Ais an illustration of a perspective exploded side view of a version of a raceway cover assembly10of the disclosure, showing a second cover side110of a raceway cover90, and a conductive element50,FIG. 4Bis an illustration of a perspective assembled side view of the raceway cover assembly10ofFIG. 4A, andFIG. 4Cis an illustration of a perspective side view of a first cover side108of the raceway cover90ofFIG. 4A. The raceway cover assembly10(seeFIGS. 4A-4B) integrates the conductive element50into the raceway cover90.

As shown inFIGS. 4A-4C, the raceway cover90, such as in the form of the snap-in raceway cover92, comprises the bottom end96, tab members98formed near the bottom end96, the top end100, flange elements102positioned and spaced along the top end100, the first cover side108, and the second cover side110. As shown inFIG. 4A, the raceway cover90comprises a unitary structure118. However, the raceway cover90may comprise another suitable structure.

The raceway cover90, such as in the form of the snap-in raceway cover92, does not require any additional fastener elements104(seeFIG. 1A) to couple, or attach, the raceway cover90to the raceway18(seeFIGS. 1A, 3A). In another version, the raceway cover90may comprise a fastened raceway cover106(seeFIG. 1A) that may be fastened to the raceway18(seeFIGS. 1A, 3A) and/or to the aircraft floor structure32(seeFIGS. 1B, 3A) with one or more fastener elements104(seeFIG. 1A), such as bolts, screws, clips, or other suitable fastener elements.

As shown inFIGS. 4A-4C, the raceway cover90further comprises retaining elements95, such as in the form of clips95a, disposed on the first cover side108. AlthoughFIGS. 4A-4Cshow the retaining elements95in the form of clips95a, coupled to, attached to, or integral with, the first cover side108, the retaining elements95may also comprise clamps95b(seeFIG. 1A), hooks95c(seeFIG. 1A), or other suitable retaining elements, to retain one or more conductive elements50along the first cover side108of the raceway cover90.

As shown inFIGS. 4A-4B, the raceway cover assembly10comprises the conductive element50, such as in the form of a short length conductive element50b, for example, an electrical run70. AlthoughFIGS. 4A-4Bshow the conductive element50comprising an electrical run70, the conductive element50may also comprise, as shown inFIG. 1A, one or more of, wires60, cables62including electrical cables62a, data bus cables62b, high speed transmission cables62c, coaxial cables62d, fiber optic cables62e, or other suitable cables, printed circuit boards (PCBs)64, tubes66, capacitors68, power runs72, data runs74, lighting system runs76, and seat system runs78, including in-flight entertainment (IFE) system runs80, seat actuation runs82, personal electronic device (PED) runs84, one or more systems transport elements85comprising one or more of, pneumatic lines85a, air lines85b, fluid lines85c, water lines85d, or other suitable systems transport elements, or another suitable conductive element. As further shown inFIGS. 4A-4B, the conductive element50comprises a connector portion51coupled, or attached, to a first end53aof the conductive element50, and coupled, or attached, to a second end53bof the conductive element50.

FIG. 5is an illustration of a side view of a version of a raceway18attached to the bottom end168aof the air grille panels166, where the raceway18has a conductive element50, such as in the form of a continuous conductive element50a, for example, an electrical run70, with connector portions51, routed along the interior side19aof the raceway18.FIG. 5shows a first end53aand a second end53bof the conductive element50. When continuous conductive elements50ahaving a long length are required, the raceway18may be installed or attached to one or more air grille panels166, so that the continuous conductive elements50amay be routed along the raceway18.

The loose ends of the continuous conductive element50a(seeFIG. 5) with the connector portions51(seeFIG. 5) may be routed, for example, to the crown area46(seeFIGS. 1B, 2A) and/or the underfloor area52(seeFIGS. 1B, 2A). Further, for example, loose ends of the continuous conductive element50amay connect to an electrical disconnect bracket (not shown) or the raceway18may have an integrated connector (not shown) such that when structurally installing the raceway18with the continuous conductive element50a, it would be electrically connected.

One or more short length conductive elements50bare integrated into the raceway cover90of the raceway cover assembly10, and a plurality of raceway cover assemblies10a(seeFIG. 1A) may be installed by coupling, or attaching, the plurality of raceway cover assemblies10ato the raceway18. The service lengths may be stowed. The raceway covers90of the raceway cover assemblies10preferably each have a length based on how far apart the seats182(seeFIG. 1B) are configured in the cabin48. For example, the raceway cover90may have a length119(seeFIG. 1A) in a range of from 28 inches to 36 inches (e.g., in economy class), may have a length119in a range of from 36 inches to 42 inches (e.g., business class), may have a length119in a range of from 42 inches to 64 inches (e.g., first class), or may have another suitable length.

As shown inFIG. 5, the raceway18comprises the raceway body24, such as in the form of elongated raceway body24a, having a second side36. As shown inFIG. 5, the raceway18further comprises flange portions42, and the raceway track portion23with openings25. FIG.5further shows the top end168band air grille openings172of the air grille panels166. As shown inFIG. 5, the raceway18spans across a gap175between the air grille panels166.

Now referring toFIGS. 6A-6C,FIG. 6Ais an illustration of a side view of a version of a raceway cover assembly10removably coupled to the raceway18ofFIG. 5,FIG. 6Bis an illustration of a side view of a version of two raceway cover assemblies10removably coupled to the raceway18ofFIG. 5, andFIG. 6Cis an illustration of a side view of a version of three raceway cover assemblies10removably coupled to the raceway18ofFIG. 5.

As shown inFIGS. 6A-6C, the raceway18is attached to the air grille panels166, and the raceway18has the conductive element50, such as in the form of the continuous conductive element50a, for example, an electrical run70, having the connector portions51, and a first end53aand a second end53b, routed along the interior side19aof the raceway18. As shown inFIGS. 6A-6C, the raceway18comprises the flange portions42and the raceway track portion23, and the air grille panels166include the air grille openings172. As further shown inFIGS. 6A-6C, the raceway18spans across the gap175between the air grille panels166. The sidewall closeout area assembly12(seeFIGS. 6A-6C) comprises the raceway cover assembly10(seeFIGS. 6A-6C) removably coupled to the raceway18(seeFIGS. 6A-6C).

FIG. 6Ashows one raceway cover assembly10removably coupled to the raceway18, via a snap-in installation94. As shown inFIG. 6A, the raceway cover assembly10comprises a first raceway cover90a, such as in the form of a first snap-in raceway cover92a, retaining a conductive element50, such as a short length conductive element50b, for example, an electrical run70, having the connector portions51, and a first end53aand a second end53b.

FIG. 6Bshows a plurality of raceway cover assemblies10a, comprising two raceway cover assemblies10removably coupled to the raceway18, via a snap-in installation94. As shown inFIG. 6B, the two raceway cover assemblies10comprise the first raceway cover90a, such as in the form of the first snap-in raceway cover92a, and a second raceway cover90b, such as in the form of a second snap-in raceway cover92b, in a longitudinal fore-aft alignment56. As shown inFIG. 6B, the first raceway cover90aand the second raceway cover90beach retains a conductive element50, such as a short length conductive element50b, for example, an electrical run70, having the connector portions51, and a first end53aand a second end53b. An intermittent routing breakout139(seeFIG. 6B) is formed between the two raceway cover assemblies10.

FIG. 6Cshows a plurality of raceway cover assemblies10a, comprising three raceway cover assemblies10removably coupled to the raceway18, via a snap-in installation94. As shown inFIG. 6C, the three raceway cover assemblies10comprise the first raceway cover90a, such as in the form of the first snap-in raceway cover92a, and the second raceway cover90b, such as in the form of the second snap-in raceway cover92b, and a third raceway cover90c, such as in the form of a third snap-in raceway cover92c, all in a longitudinal fore-aft alignment56. As shown inFIG. 6C, the first raceway cover90a, the second raceway cover90b, and the third raceway cover90c, each retains a conductive element50, such as a short length conductive element50b, for example, an electrical run70, having the connector portions51, and a first end53aand a second end53b. Intermittent routing breakouts139(seeFIG. 6C) are formed between the three raceway cover assemblies10.

The loose ends of the short length conductive elements50b(seeFIG. 6C), with the connector portions51(seeFIG. 6C), may be routed to an aircraft floor structure32(seeFIG. 1B) comprising the fore-aft longitudinal floor grid structure176(seeFIG. 1B), comprising the longitudinal seat track178(seeFIG. 1B) and to the seats182(seeFIG. 1B), comprising the floor panel180(seeFIG. 1B), or another suitable aircraft floor structure, or may be routed to another area of the interior112(seeFIG. 1B) of the cabin48(seeFIG. 1B) of the vehicle14(seeFIG. 1B), such as the aircraft16(seeFIG. 1B).

Now referring toFIG. 7,FIG. 7is an illustration of a perspective side view of a version of a raceway cover assembly10being installed, via a snap-in installation94, to a raceway18, where the raceway18is attached to a bottom end168aof an air grille panel166. As shown inFIG. 7, the raceway cover assembly10comprises the raceway cover90, such as in the form of the snap-in raceway cover92, where the raceway cover90comprises the bottom end96, the tab members98formed near the bottom end96, the top end100, the flange elements102positioned and spaced along the top end100, the first cover side108, and the second cover side110. As shown inFIG. 7, the raceway cover assembly10further comprises the conductive element50, such as in the form of the short length conductive element50b, for example, an electrical run70, retained by the raceway cover90. The conductive element50, such as in the form of the short length conductive element50b, has the connector portions51at the first end53aand as the second end53bof the short length conductive element50b.

FIG. 7shows the raceway18comprising the raceway body24, such as in the form of the elongated raceway body24a, having a second side36, and comprising flange portions42, fin portions45, and the raceway track portion23with openings25. As shown inFIG. 7, the raceway18has a conductive element50, such as in the form of a continuous conductive element50a, for example, an electrical run70, with connector portions51, routed along the interior side19aof the raceway18.FIG. 7further shows the air grille openings172of the air grille panels166.

Now referring toFIG. 8A,FIG. 8Ais an illustration of inboard side perspective close-up view of a version of raceways18attached between an air grille panel166and a floor152in an interior112of a cabin48, such as a passenger cabin48a, of a vehicle14, such as an aircraft16.FIG. 8Ashows the interior side19aof the raceways18, shows the second side36of the raceway body24, such as in the form of the elongated raceway body24a, and shows the raceway track portion23with openings25.FIG. 8Afurther shows adjacent raceway body sections54aaligned in a longitudinal fore-aft alignment56adjacent to each other. An access opening40(seeFIG. 8A) is formed between end portions58of each adjacent raceway body section54a.FIG. 8Afurther shows the interior side170aand the air grille openings172of the air grille panel166, and shows the seat leg184and the seat shroud188.

Now referring toFIG. 8B,FIG. 8Bis an illustration of an inboard side perspective close-up view of two raceway cover assemblies10attached to the raceways18ofFIG. 8A. As shown inFIG. 8B, the raceways18are attached between the bottom end168aof the air grille panel166and the floor152in the interior112of the cabin48, such as the passenger cabin48a, of the vehicle14, such as the aircraft16.FIG. 8Bshows the raceway track portions23with openings25.

FIG. 8Bshows the second cover side110of the first raceway cover90a, such as in the form of the first snap-in raceway cover92a, and the second raceway cover90b, such as in the form of the second snap-in raceway cover92b. As shown inFIG. 8B, the raceway covers90comprise raceway cover sections120, such as in the form of adjacent raceway cover sections120a, aligned in a longitudinal fore-aft alignment56, where end portions122of the raceway cover sections120are adjacent the intermittent routing breakout139.FIG. 8Bfurther shows the raceway covers90facing the interior112of the cabin48, and facing the seat shroud188and the seat leg184.FIG. 8Bfurther shows a closeout area142formed between the raceways18and the raceway covers90.FIG. 8Bfurther shows the interior side170aand the air grille openings172of the air grille panel166.

As further shown inFIG. 8B, each raceway cover assembly10comprises the conductive element50, such as in the form of the short length conductive element50b, for example, the electrical run70, retained by the raceway cover90. As shown inFIG. 8B, each conductive element50, such as in the form of the short length conductive element50b, has the connector portion51.

Now referring toFIG. 8C,FIG. 8Cis an illustration of an inboard side perspective close-up view of a breakout cover124coupled between the raceway cover assemblies10ofFIG. 8B. As shown inFIG. 8C, the raceway18is attached between the bottom end168aof the air grille panel166and the floor152in the interior112of the cabin48, such as the passenger cabin48a, of the vehicle14, such as the aircraft16.FIG. 8Cshows the raceway track portions23with openings25.

FIG. 8Cshows the second cover side110of the first raceway cover90a, such as in the form of the first snap-in raceway cover92a, and the second raceway cover90b, such as in the form of the second snap-in raceway cover92b. As shown inFIG. 8C, the raceway covers90comprise the raceway cover sections120, such as in the form of the adjacent raceway cover sections120a, where the end portions122of the raceway cover sections120are adjacent the breakout cover124, such as in the form of a snap-in breakout cover128.FIG. 8Cshows another breakout cover124, such as in the form of a snap-in breakout cover128, on the other end of the second raceway cover90b. As shown inFIG. 8C, each breakout cover124comprises an access opening114, such as in the form of a breakout cover opening126, and comprises a bottom end132and a top end136. Both the raceway covers90and the breakout covers124are removably coupled, such as snap fitted, to the raceway18, and positioned between the bottom end168aof the air grille panel166, and the floor152of the cabin48.FIG. 8Cfurther shows the raceway covers90and the breakout covers124facing the interior112of the cabin48, and facing the seat shroud188and the seat leg184.FIG. 8Cfurther shows the interior side170aand the air grille openings172of the air grille panel166.

As further shown inFIG. 8C, each raceway cover assembly10comprises the conductive element50, such as in the form of the short length conductive element50b, for example, the electrical run70, retained by the raceway cover90. As shown inFIG. 8C, each conductive element50, such as in the form of the short length conductive element50b, has the connector portion51.FIG. 8Cfurther shows a conductive element50, such as an electrical run70, routed into the seat shroud188.

Now referring toFIGS. 9A-9B,FIG. 9Ais an illustration of a perspective exploded side view of a version of a sidewall closeout area cartridge system11of the disclosure, showing a raceway cover assembly10and a raceway18, andFIG. 9Bis an illustration of a perspective assembled side view of the sidewall closeout area cartridge system11ofFIG. 9A. In this version, the conductive element50retained by the raceway cover90is integrated with the raceway18and installed as a unit in the cabin48of the vehicle14, such as the aircraft16.

As shown inFIGS. 9A-9B, the raceway cover assembly10comprises the raceway cover90, such as in the form of the snap-in raceway cover92. As shown inFIG. 9A, the raceway cover90comprises the bottom end96, the tab members98formed near the bottom end96, the top end100, the flange elements102positioned and spaced along the top end100, the first cover side108, and the second cover side110(see alsoFIG. 9B).

The raceway cover90(seeFIGS. 9A-9B) retains the conductive element50(seeFIGS. 9A-9B), such as the short length conductive element50b(seeFIGS. 9A-9B), for example, the electrical run70(seeFIGS. 9A-9B). The conductive element50(seeFIGS. 9A-9B) has the connector portion51(seeFIGS. 9A-9B) at the first end53a(seeFIGS. 9A-9B) and the second end53b(seeFIGS. 9A-9B) of the conductive element50. AlthoughFIGS. 9A-9Bshow the conductive element50comprising the electrical run70, the conductive element50may also comprise, as shown inFIG. 1A, one or more of, wires60, cables62including electrical cables62a, data bus cables62b, high speed transmission cables62c, coaxial cables62d, fiber optic cables62e, or other suitable cables, printed circuit boards (PCBs)64, tubes66, capacitors68, power runs72, data runs74, lighting system runs76, and seat system runs78, including in-flight entertainment (IFE) system runs80, seat actuation runs82, personal electronic device (PED) runs84, one or more systems transport elements85comprising one or more of, pneumatic lines85a, air lines85b, fluid lines85c, water lines85d, or other suitable systems transport elements85, or another suitable conductive element.

As further shown inFIG. 9A, the raceway18has the interior side19aand the exterior side19b, and the first cover side108of the raceway cover90is configured to face, and faces, the interior side19aof the raceway18, when the raceway cover assembly10is coupled, or attached to the raceway18, via the snap-in installation94. As further shown inFIG. 9A, the raceway18comprises the raceway body24, such as the elongated raceway body24a, having the first side34, or exterior side, and the second side36, or interior side, where the second side36of the raceway body24is configured to face, and faces, the first cover side108of the raceway cover90.

As shown inFIGS. 9A-9B, the raceway18further comprises a first end20, a second end21, the raceway track portion23with openings25, the flange portions42, and the fin portions45. As shown inFIGS. 9A-9B, the flange portions42have an underside43, where the top end100of the raceway cover90is adjacent to, or abuts, the underside43of the flange portions42, when the raceway cover assembly10is coupled to the raceway18.

As shown inFIG. 9B, when the raceway cover assembly10is coupled, via the snap-in installation94, to the raceway18, to form the sidewall closeout area cartridge system11, the closeout area142is formed between the interior side19aof the raceway18and the first cover side108of the raceway cover90. In the version of the raceway cover90, such as in the form of the snap-in raceway cover92, shown inFIGS. 9A-9B, no fastener elements104(seeFIG. 1A) are needed to couple, or attach, the raceway cover90to the raceway18. In another version, the raceway cover90may comprise a fastened raceway cover106(seeFIG. 1A) that may be fastened to the raceway18(seeFIGS. 1A, 3A) and/or to the aircraft floor structure32(seeFIGS. 1B, 3A) with one or more fastener elements104(seeFIG. 1A), such as bolts, screws, clips, or other suitable fastener elements.

Now referring toFIG. 9C,FIG. 9Cis an illustration of a perspective back side view of another version of a sidewall closeout area cartridge system11, such as in the form of an enclosed sidewall closeout area cartridge system11b, of the disclosure.FIG. 9Cshows attachment elements30, such as in the form of brackets30a, coupled to each end of the raceway18of the sidewall closeout area cartridge system11, such as in the form of an enclosed sidewall closeout area cartridge system11b. The plurality of conductive elements50(seeFIG. 9C), such as in the form of the plurality of electrical runs70(seeFIG. 9C), are routed along the raceway18of the sidewall closeout area cartridge system11, such as in the form of an enclosed sidewall closeout area cartridge system11b.FIG. 9Cshows a raceway cover surface91of the raceway cover90.

As shown inFIG. 9C, the sidewall closeout area cartridge system11, such as in the form of an enclosed sidewall closeout area cartridge system11b, is coupled, or attached, to the bottom end168aof the air grille panel166in the cabin48, such as the passenger cabin48a, of the vehicle14, such as the aircraft16.FIG. 9Cshows the interior side170a, the exterior side170b, the air grille openings172, and the air grilles174of the air grille panel166, and shows the fin portions45of the raceway18contacting the air grille panel166. The interior side170aof the air grille panel166faces the interior112of the cabin48.FIG. 9Cfurther shows a seat182in the interior112of the cabin48.

Now referring toFIGS. 10A-10B,FIG. 10Ais an illustration of a perspective side view of a version of an air grille panel cartridge assembly13of the disclosure, including a plurality of sidewall closeout area cartridge systems11a, such as two sidewall closeout area cartridge systems11, attached to the bottom end168aof the air grille panel166, andFIG. 10Bis an illustration of a perspective side view of the air grille panel cartridge assembly13ofFIG. 10Aattached to a bottom end162aof a sidewall panel160, and installed in an interior112of a cabin48, such as a passenger cabin48a, of a vehicle14, such as an aircraft16.

As shown inFIGS. 10A-10B, each sidewall closeout area cartridge system11comprises the raceway cover assembly10coupled, or attached, to the raceway18. Each raceway cover assembly10(seeFIGS. 10A-10B) comprises the raceway cover90(seeFIGS. 10A-10B) retaining the conductive element50(seeFIGS. 10A-10B). As shown inFIGS. 10A-10B, the raceway covers90include the first raceway cover90a, such as in the form of the first snap-in raceway cover92a, and the second raceway cover90b, such as in the form of the second snap-in raceway cover92b. Each raceway cover90(seeFIGS. 10A-10B) retains the conductive element50(seeFIGS. 10A-10B), such as the short length conductive element50b(seeFIGS. 10A-10B), for example, the electrical run70(seeFIGS. 10A-10B). Each conductive element50(seeFIGS. 10A-10B) has the connector portions51(seeFIGS. 10A-10B), and has the first end53a(seeFIGS. 10A-10B) and the second end53b(seeFIGS. 10A-10B). AlthoughFIGS. 10A-10Bshow the conductive element50comprising the electrical run70, the conductive element50may also comprise, as shown inFIG. 1A, one or more of, wires60, cables62including electrical cables62a, data bus cables62b, high speed transmission cables62c, coaxial cables62d, fiber optic cables62e, or other suitable cables, printed circuit boards (PCBs)64, tubes66, capacitors68, power runs72, data runs74, lighting system runs76, and seat system runs78, including in-flight entertainment (IFE) system runs80, seat actuation runs82, personal electronic device (PED) runs84, one or more systems transport elements85comprising one or more of, pneumatic lines85a, air lines85b, fluid lines85c, water lines85d, or other suitable systems transport elements85, or another suitable conductive element.

The loose ends of the short length conductive elements50b(seeFIG. 10B), with the connector portions51(seeFIG. 10B), may be routed to an aircraft floor structure32(seeFIG. 1B) comprising the fore-aft longitudinal floor grid structure176(seeFIG. 1B), comprising the longitudinal seat track178(seeFIG. 1B) and to the seats182(seeFIG. 1B), comprising the floor panel180(seeFIG. 10B), or another suitable aircraft floor structure, or may be routed to another area of the interior112(seeFIG. 10B) of the cabin48(seeFIG. 10B) of the vehicle14(seeFIG. 10B), such as the aircraft16(seeFIG. 10B). In addition, any loose ends of conductive elements50from the back of the sidewall closeout area cartridge systems11may be connected to an electrical disconnect bracket (not shown) or for each sidewall closeout area cartridge system11itself, it may have an integrated connector (not shown), such that when structurally installing it, it would also be electrically connected.

As further shown inFIGS. 10A-10B, the raceway18has the raceway track portion23with openings25, and an intermittent routing breakout139is formed between the two raceway cover assemblies10.FIG. 10Afurther shows the top end168b, the interior side170a, and the air grille openings172of the air grille panel166.FIG. 10Bfurther shows the interior side170aand the air grille openings172of the air grille panel166, the gap175between air grille panels166, and the interior side164aof the sidewall panel160.

Now referring toFIG. 11A,FIG. 11Ais an illustration of a flow diagram of a version of a method220of the disclosure. In another version of the disclosure, there is provided the method220(seeFIG. 11A) for installing one or more conductive elements50(seeFIG. 1A) in a vehicle14(seeFIG. 1B), such as an aircraft16(seeFIG. 1B).

The blocks inFIG. 11Arepresent operations and/or portions thereof, or elements, and lines connecting the various blocks do not imply any particular order or dependency of the operations or portions thereof, or elements.FIG. 11Aand the disclosure of the steps of the method220set forth herein should not be interpreted as necessarily determining a sequence in which the steps are to be performed. Rather, although one illustrative order is indicated, it is to be understood that the sequence of the steps may be modified when appropriate. Accordingly, certain operations may be performed in a different order or simultaneously.

As shown inFIG. 11A, the method220comprises the step of assembling222a raceway cover assembly10(seeFIGS. 1A, 4A-4B), by coupling and retaining the one or more conductive elements50(seeFIGS. 1A, 4A) to a first cover side108(seeFIGS. 1A, 4A, 4C) of a raceway cover90(seeFIGS. 1A, 4A), such as a snap-in raceway cover92(seeFIGS. 1A, 4A-4B), with one or more retaining elements95(seeFIGS. 1A, 4A, 4C) disposed on the first cover side108.

As shown inFIG. 11A, the method220further comprises the step of installing224the one or more conductive elements50in the vehicle, such as the aircraft16, by removably coupling the raceway cover assembly10(seeFIGS. 1A, 4A-4B), via a snap-in installation94(seeFIGS. 1A, 7), to a raceway18(seeFIGS. 1A, 7), where the raceway18is attached to a bottom end168a(seeFIG. 7) of an air grille panel166(seeFIG. 7) of a sidewall assembly26(seeFIGS. 1B, 3A-3B) in an interior112(seeFIGS. 1B, 3A-3B) of a cabin48(seeFIGS. 1B, 3A-3B), such as a passenger cabin48a(seeFIGS. 1B, 3A-3B) of the vehicle14(seeFIGS. 1B, 3A-3B), such as the aircraft16(seeFIGS. 1B, 3A-3B). When the raceway cover90is coupled, or attached, to the raceway18, the one or more conductive elements50are housed and protected.

The raceway cover assembly10(seeFIGS. 1A, 4A-4B) is assembled at a location200(seeFIG. 1) off of the vehicle14, such as the aircraft16, prior to the snap-in installation94(seeFIGS. 1A, 7) of the raceway cover assembly10to the raceway18(seeFIGS. 1A, 7). This allows for routing of the one or more conductive elements50(seeFIGS. 1A, 4A-4B) in the raceway cover90(seeFIGS. 1A, 4A-4B) at the location200off of the vehicle14, such as the aircraft16. As shown inFIGS. 1A-1B, the location200may comprise an assembly plant202, a production facility204, a work station206, a work bench208, or another suitable location off of the vehicle14, such as the aircraft16.

The step of assembling222(seeFIG. 11A) the raceway cover assembly10may further comprise, assembling222a plurality of raceway cover assemblies10a(seeFIGS. 1A, 6B-6C), and the step of installing224(seeFIG. 11A) the one or more conductive elements50in the vehicle14, such as the aircraft16, may further comprise, installing224the plurality of raceway cover assemblies10ain a longitudinal fore-aft alignment56(seeFIGS. 6B-6C) along the raceway18(seeFIGS. 6B-6C), with intermittent routing breakouts139(seeFIGS. 6B-6C) formed between each of two of the plurality of raceway cover assemblies10a. The raceway cover assembly10and the raceway18assembled together and installed in the vehicle14, such as in the aircraft16, create or form the sidewall closeout area assembly12(seeFIGS. 1B, 3B), which facilitates accessibility to the one or more conductive elements50, and provides a routing path86(seeFIG. 1A) for the one or more conductive elements50that does not need to be reconfigured for different aircraft cabin layouts87(seeFIG. 1A).

As shown inFIG. 11A, prior to the step of installing224the one or more conductive elements50in the vehicle14, such as the aircraft16, the method220further optionally comprises the step of routing226one or more continuous conductive elements50a(seeFIGS. 1A, 5) along the raceway18(seeFIGS. 1A, 5). The one or more continuous conductive elements50amay be further routed through one or more access openings40(seeFIGS. 1A, 8A) in the raceway18(seeFIGS. 1A, 8A), to access one or more of, a crown area46(seeFIG. 1B) above the cabin48(seeFIG. 1B), and an underfloor area52(seeFIG. 1B) below the cabin48.

As discussed above, the raceway cover90(seeFIGS. 4A-4B) retains the conductive element50(seeFIGS. 4A-4B), such as a short length conductive element50b(seeFIGS. 4A-4B), for example, an electrical run70(seeFIGS. 4A-4B). The conductive element50(seeFIG. 4A) has the connector portion51(seeFIG. 4A) at the first end53a(seeFIG. 4A) and the second end53b(seeFIG. 4A) of the conductive element50. The conductive element50may also comprise, as shown inFIG. 1A, one or more of, wires60, cables62including electrical cables62a, data bus cables62b, high speed transmission cables62c, coaxial cables62d, fiber optic cables62e, or other suitable cables, printed circuit boards (PCBs)64, tubes66, capacitors68, power runs72, data runs74, lighting system runs76, and seat system runs78, including in-flight entertainment (IFE) system runs80, seat actuation runs82, personal electronic device (PED) runs84, one or more systems transport elements85comprising one or more of, pneumatic lines85a, air lines85b, fluid lines85c, water lines85d, or other suitable systems transport elements, or another suitable conductive element.

The one or more conductive elements50(seeFIG. 4B), such as the one or more short length conductive elements50b(seeFIG. 4B), and the raceway cover90(seeFIG. 4B) are preferably assembled together off of the vehicle14, such as the aircraft16, to form the raceway cover assembly10(seeFIG. 4B), and multiple conductive elements50may be assembled with multiple raceway covers90, to form a plurality of raceway cover assemblies10a(seeFIG. 1A). In one version, the raceway cover assembly10, or the plurality of raceway cover assemblies10a, are removably coupled to the raceway18on the vehicle14, such as the aircraft16, where the raceway18is attached to one or more air grille panels166, and one or more continuous conductive elements50a(seeFIG. 1A) may be routed along the raceway18.

Now referring toFIG. 11B,FIG. 11Bis an illustration of a flow diagram of another version of a method230of the disclosure. In another version of the disclosure, there is provided the method230(seeFIG. 11B) for installing one or more conductive elements50(seeFIG. 1A) in a vehicle14(seeFIG. 1B), such as an aircraft16(seeFIG. 1B).

The blocks inFIG. 11Brepresent operations and/or portions thereof, or elements, and lines connecting the various blocks do not imply any particular order or dependency of the operations or portions thereof, or elements.FIG. 11Band the disclosure of the steps of the method230set forth herein should not be interpreted as necessarily determining a sequence in which the steps are to be performed. Rather, although one illustrative order is indicated, it is to be understood that the sequence of the steps may be modified when appropriate. Accordingly, certain operations may be performed in a different order or simultaneously.

As shown inFIG. 11B, the method230comprises the step of assembling232a sidewall closeout area cartridge system11(seeFIGS. 1B, 9A-9B), by removably coupling a raceway cover assembly10(seeFIGS. 1B, 9A-9B), via a snap-in installation94(seeFIG. 9A), to a raceway18(seeFIGS. 1B, 9A-9B). As discussed in detail above, the raceway cover assembly10(seeFIGS. 1A, 9A-9B) comprises a raceway cover90(seeFIGS. 1A, 9A-9B), such as a snap-in raceway cover92(seeFIGS. 1A, 9A-9B), having a first cover side108(seeFIGS. 1A, 9A) facing an interior side19a(seeFIGS. 1A, 9A) of the raceway18, a second cover side110(seeFIGS. 1A, 9A) configured to face, and facing, an interior112(seeFIGS. 1B, 10B) of a cabin48(seeFIGS. 1B, 10B), such as a passenger cabin48a(seeFIGS. 1B, 10B), of the vehicle14(seeFIGS. 1B, 10B), such as the aircraft16(seeFIGS. 1B, 10B), and one or more retaining elements95(seeFIGS. 4A, 4C) disposed on the first cover side108(seeFIGS. 4A, 4C).

As discussed in detail above, the raceway cover assembly10(seeFIGS. 1A, 9A-9B) further comprises the one or more conductive elements50(seeFIGS. 1A, 9A-9B) coupled and retained to the first cover side108(seeFIG. 9A), with the one or more retaining elements95(seeFIGS. 1A, 4A). As discussed above, the raceway cover90(seeFIGS. 9A-9B) retains the conductive element50(seeFIGS. 9A-9B), such as a short length conductive element50b(seeFIGS. 9A-9B), for example, an electrical run70(seeFIGS. 9A-9B). The conductive element50(seeFIGS. 9A-9B) has the connector portion51(seeFIGS. 9A-9B) at the first end53a(seeFIGS. 9A-9B) and the second end53b(seeFIGS. 9A-9B) of the conductive element50. The conductive element50may also comprise, as shown inFIG. 1A, one or more of, wires60, cables62including electrical cables62a, data bus cables62b, high speed transmission cables62c, coaxial cables62d, fiber optic cables62e, or other suitable cables, printed circuit boards (PCBs)64, tubes66, capacitors68, power runs72, data runs74, lighting system runs76, and seat system runs78, including in-flight entertainment (IFE) system runs80, seat actuation runs82, personal electronic device (PED) runs84, one or more systems transport elements85comprising one or more of, pneumatic lines85a, air lines85b, fluid lines85c, water lines85d, or other suitable systems transport elements, or another suitable conductive element.

As shown inFIG. 11B, the method230further comprises the step of installing234the one or more conductive elements50in the vehicle14, such as the aircraft16, by attaching the sidewall closeout area cartridge system11(seeFIGS. 9A-9B), via an attached installation198(seeFIG. 1B), to a sidewall assembly26(seeFIG. 1B) in the interior112(seeFIG. 1B) of the cabin48(seeFIG. 1B), such as the passenger cabin48a(seeFIG. 1B), of the vehicle14(seeFIG. 1B), such as the aircraft16(seeFIG. 1B).

The sidewall closeout area cartridge system11(seeFIGS. 9A-9B) is assembled at a location200(seeFIG. 1B) off of the vehicle14(seeFIG. 1B), such as the aircraft16(seeFIG. 1B), prior to the attached installation198(seeFIG. 1B) of the sidewall closeout area cartridge system11to the sidewall assembly26(seeFIG. 1B). This allows for routing of the one or more conductive elements50(seeFIG. 1A) in the sidewall closeout area cartridge system11at the location200off of the vehicle14, such as the aircraft16.

The step of assembling232(seeFIG. 11B) the sidewall closeout area cartridge system11(seeFIGS. 9A-9B) may further comprise, assembling232a plurality of sidewall closeout area cartridge systems11a(seeFIGS. 1B, 10B), and the step of installing234(seeFIG. 11B) the one or more conductive elements50in the vehicle14, such as the aircraft16, may further comprise, installing234the plurality of sidewall closeout area cartridge systems11ain a longitudinal fore-aft alignment56(seeFIGS. 1A, 10B) along a bottom end168a(seeFIG. 10B) of an air grille panel166(seeFIGS. 1A, 10B) of the sidewall assembly26(seeFIGS. 1B, 10B), with intermittent routing breakouts139(seeFIGS. 1A, 10B) formed between each of two of the plurality of sidewall closeout area cartridge systems11a.

The step of installing234(seeFIG. 11B) the one or more conductive elements50in the vehicle14, such as the aircraft16, may further comprise, installing234the one or more conductive elements50, by attaching the sidewall closeout area cartridge system11(seeFIGS. 9A-9B), via the attached installation198(seeFIG. 1B), with one or more attachment elements30(seeFIG. 9C), such as one or more brackets30a(seeFIG. 9C), to a bottom end168a(seeFIG. 9C) of an air grille panel166(seeFIG. 9C) of a sidewall assembly26(seeFIG. 1B) in the interior112(seeFIG. 9C) of the cabin48(seeFIG. 9C), such as the passenger cabin48a(seeFIG. 9C), of the vehicle14(seeFIG. 9C), such as the aircraft16(seeFIG. 9C). The sidewall assembly26(seeFIG. 1B) comprises one or more sidewall panels160(seeFIG. 1B) coupled to one or more air grille panels166(seeFIG. 1B), and the first end20(seeFIG. 1A) of the raceway18(seeFIGS. 1A-1B) is configured to attach, and attaches, to a bottom end168a(seeFIG. 1B) of each of the air grille panels166of the sidewall assembly26. The second end21(seeFIG. 1A) of the raceway18is configured to attach, and attaches, to the one or more aircraft floor structures32(seeFIG. 1B) comprising one or more of, a fore-aft longitudinal floor grid structure176(seeFIG. 1B), a longitudinal seat track178(seeFIG. 1B), a floor panel180(seeFIG. 1B) of the floor152(seeFIG. 1B), or another suitable aircraft floor structure.

As shown inFIG. 11B, prior to the step of installing234the one or more conductive elements50in the vehicle14, such as the aircraft16, the method230may further optionally comprise the step of attaching236, at the location200(seeFIG. 1B) off of the vehicle14, such as the aircraft16, the sidewall closeout area cartridge system11(seeFIGS. 9A-9B, 10A) to an air grille panel166(seeFIGS. 1B, 10A), to form an air grille panel cartridge assembly13(seeFIGS. 1B, 10A), and wherein the step of installing234(seeFIG. 11B) the one or more conductive elements50further comprises, installing the air grille panel cartridge assembly13(seeFIG. 10B) between a sidewall panel160(seeFIG. 10B) of the sidewall assembly26(seeFIGS. 1B, 3A) and an aircraft floor structure32(seeFIGS. 1B, 3A), such as the floor152(seeFIGS. 1B, 10B), in the interior112(seeFIGS. 1B, 3A, 10B) of the cabin48(seeFIGS. 1B, 3A, 10B), such as the passenger cabin48a(seeFIGS. 1B, 3A, 10B), of the vehicle14, such as the aircraft16.

The one or more conductive elements50(seeFIG. 4B), such as the one or more short length conductive elements50b(seeFIG. 4B), and the raceway cover90(seeFIG. 4B) are preferably assembled together off of the vehicle14, such as the aircraft16, to form the raceway cover assembly10(seeFIG. 4B), and multiple conductive elements50may be assembled with multiple raceway covers90, to form a plurality of raceway cover assemblies10a(seeFIG. 1A). In one version, as discussed above, the raceway cover assembly10, or the plurality of raceway cover assemblies10a, are removably coupled to the raceway18on the vehicle14, such as the aircraft16, where the raceway18is attached to one or more air grille panels166, and one or more continuous conductive elements50a(seeFIG. 1A) may be routed along the raceway18.

In another version, the raceway cover assembly10, or the plurality of raceway cover assemblies10a, are removably coupled to the raceway18off of the vehicle14, such as the aircraft16, to form the sidewall closeout area cartridge system11(seeFIG. 1B, 9B) or a plurality of sidewall closeout area cartridge systems11a(seeFIG. 1B), and the sidewall closeout area cartridge system11(seeFIG. 1B, 9B) or the plurality of sidewall closeout area cartridge systems11a, are preferably attached on the vehicle14, such as the aircraft16, to the sidewall panel160(seeFIG. 10B) of the sidewall assembly26(seeFIGS. 1B, 10B).

Now referring toFIG. 12,FIG. 12is a diagrammatic representation of a perspective view of a vehicle14, such as in the form of an aircraft16, that incorporates a version of the sidewall closeout area cartridge system11with a version of the raceway cover assembly10, of the disclosure. As further shown inFIG. 12, the vehicle14, such as in the form of aircraft16, comprises a fuselage250, a nose252, a cockpit254, wings256, engines258, and an empennage260comprising a vertical stabilizer262and horizontal stabilizers264. Although the vehicle14, such as the aircraft16, shown inFIG. 12is generally representative of a commercial passenger aircraft having a version of the sidewall closeout area cartridge system11with a version of the raceway cover assembly10, the teachings of the disclosed versions and examples may be applied to other vehicles. For example, the teachings of the disclosed versions and examples may be applied to cargo aircraft, military aircraft, rotorcraft, and other types of aircraft or air vehicles. In addition, the teachings of the disclosed versions and examples may be applied to boats15(seeFIG. 1B), trains17(seeFIG. 1B), and other passenger carrying vehicles. In addition, the teachings of the disclosed versions and examples may be applied to structures where a highly reconfigurable conduit is required, for example, commercial and home conduit replacement, floor molding replacement, cubicle configuration, configuration of booths such as at trade shows, and other suitable structures.

Now referring toFIGS. 13 and 14,FIG. 13is an illustration of a flow diagram of an exemplary aircraft manufacturing and service method300, andFIG. 14is an illustration of an exemplary block diagram of an aircraft316. Referring toFIGS. 13 and 14, versions of the disclosure may be described in the context of the aircraft manufacturing and service method300as shown inFIG. 13, and the aircraft316as shown inFIG. 14.

During pre-production, exemplary aircraft manufacturing and service method300may include specification and design302of the aircraft316and material procurement304. During manufacturing, component and subassembly manufacturing306and system integration308of the aircraft316takes place. Thereafter, the aircraft316may go through certification and delivery310in order to be placed in service312. While in service312by a customer, the aircraft316may be scheduled for routine maintenance and service314(which may also include modification, reconfiguration, refurbishment, and other suitable services).

As shown inFIG. 14, the aircraft316produced by the exemplary aircraft manufacturing and service method300may include an airframe318with a plurality of systems320and an interior322. Examples of the plurality of systems320may include one or more of a propulsion system324, an electrical system326, a hydraulic system328, and an environmental system330. Any number of other systems may be included. Although an aerospace example is shown, the principles of the disclosure may be applied to other industries, such as the automotive industry.

Methods and systems embodied herein may be employed during any one or more of the stages of the aircraft manufacturing and service method300. For example, components or subassemblies corresponding to component and subassembly manufacturing306may be fabricated or manufactured in a manner similar to components or subassemblies produced while the aircraft316is in service312. Also, one or more apparatuses, methods, or a combination thereof, may be utilized during component and subassembly manufacturing306and system integration308, for example, by substantially expediting assembly of or reducing the cost of the aircraft316. Similarly, one or more of apparatuses, methods, or a combination thereof, may be utilized while the aircraft316is in service312, for example and without limitation, to maintenance and service314.

Disclosed versions of the raceway cover assembly10(seeFIGS. 1A, 4A-4B), the sidewall closeout area cartridge system11(seeFIGS. 1B, 9A-9B), the air grille panel cartridge assembly13(seeFIGS. 1B, 10A), the method220(seeFIG. 11A), and the method230(seeFIG. 11B) provide for an assembly, a system, and methods for installing one or more conductive elements50(seeFIG. 1A), such as electrical runs70(seeFIG. 1A), system transport elements85(seeFIG. 1A), or other suitable conductive elements in an interior112(seeFIG. 1B) of a cabin48(seeFIG. 1B), such as a passenger cabin48a(seeFIG. 1B), of a vehicle14(seeFIG. 1B), such as an aircraft16(seeFIG. 1B), a boat15(seeFIG. 1B), a train17(seeFIG. 1B), or another passenger carrying vehicle, and streamline the installation process on the vehicle14by not requiring any routing of the one or more conductive elements50. Disclosed versions of the raceway cover assembly10(seeFIGS. 1A, 4A-4B), the sidewall closeout area cartridge system11(seeFIGS. 1B, 9A-9B), the air grille panel cartridge assembly13(seeFIGS. 1B, 10A), the method220(seeFIG. 11A), and the method230(seeFIG. 11B) allow for the consolidation of conductive elements50, for example, wires60(seeFIG. 1A), cables62(seeFIG. 1A), pneumatic lines85a(seeFIG. 1A), fluid lines85c(seeFIG. 1A), and other suitable conductive elements, into a higher level assembly that takes less time to install than installing the conductive elements50independently in the vehicle14, such as the aircraft16, and reduce the installation critical path by the installation time of the conductive elements50into the conduit, such as the raceway cover assembly10, by pre-installing them. The method220(seeFIG. 11A) includes coupling and retaining one or more conductive elements50to a raceway cover90(seeFIG. 1A) at a location200(seeFIG. 1A) off of the vehicle14, such as the aircraft16, to form a raceway cover assembly10(seeFIG. 1A), and installing the raceway cover assembly10in the vehicle14, such as the aircraft16, by removably coupling the raceway cover assembly10, via a snap-in installation94(seeFIG. 1A), to a raceway18(seeFIG. 1A) attached to an air grille panel166(seeFIG. 1B) of a sidewall assembly26(seeFIG. 1B). The method230(seeFIG. 11B) includes removably coupling the raceway cover assembly10(seeFIG. 1A), via the snap-in installation94(seeFIG. 1A), to a raceway18(seeFIG. 1A), at a location200(seeFIG. 1A) off of the vehicle14, such as the aircraft16, to form a sidewall closeout area cartridge system11(seeFIG. 1B), and attaching the sidewall closeout area cartridge system11, via an attached installation198(seeFIG. 1B), to the sidewall assembly26(seeFIG. 1B) in the interior112(seeFIG. 1B) of the cabin48of the vehicle14, such as the aircraft16.

In addition, disclosed versions of the raceway cover assembly10(seeFIGS. 1A, 4A-4B), the sidewall closeout area cartridge system11(seeFIGS. 1B, 9A-9B), the air grille panel cartridge assembly13(seeFIGS. 1B, 10A), the method220(seeFIG. 11A), and the method230(seeFIG. 11B) integrate the conductive elements50, for example, wires60(seeFIG. 1A), cables62(seeFIG. 1A), pneumatic lines85a(seeFIG. 1A), fluid lines85c(seeFIG. 1A), and other suitable conductive elements50, into an assembly or system that may be easily installed in a single step, via a snap-in installation94(seeFIG. 1A) for the raceway cover assembly10, or via an attached installation198(seeFIG. 1B) for the sidewall closeout area cartridge system11or for the air grille panel cartridge assembly13(seeFIG. 1B), on the vehicle14, such as the aircraft16. Disclosed versions of the raceway cover assembly10(seeFIGS. 1A, 4A-4B), the sidewall closeout area cartridge system11(seeFIGS. 1B, 9A-9B), the air grille panel cartridge assembly13(seeFIGS. 1B, 10A), the method220(seeFIG. 11A), and the method230(seeFIG. 11B) allow for the installation and integration of the one or more conductive elements50in the raceway cover assembly10(seeFIG. 1A), in the sidewall closeout area cartridge system11(seeFIG. 1A), or in the air grille panel cartridge assembly13(seeFIG. 1B), to be performed or conducted off of the vehicle14, such as the aircraft16, at a location200(seeFIGS. 1A-1B) off of the vehicle14, such as the aircraft16, for example, at an assembly plant202(seeFIGS. 1A-1B), at a production facility204(seeFIGS. 1A-1B), at a work station206(seeFIGS. 1A-1B), at a work bench208(seeFIG. 1A-1B), or at another suitable location. The location200is preferably optimized for ergonomics and part or tool availability. The one or more conductive elements50need only be installed or integrated when required by installation flow and avoid exposed conductive elements50, such as wires60or cables62, during installation. In addition, since the one or more conductive elements50are pre-routed in the conduit, such as in the form of the raceway cover assembly10, the sidewall closeout area cartridge system11, or the air grille panel cartridge assembly13, there is no need to apply secondary protective methods to avoid any possible damage.

Further, having this installation or integration performed at the location200off of the vehicle14, such as the aircraft16, makes access easier to tools for trimming the raceway cover90or the raceway18to fit the one or more conductive elements50, and avoids having to specially protect aircraft decorative surfaces on the aircraft16from Foreign Object Debris (FOD) created by trimming. The creation of the raceway cover assembly10, the sidewall closeout area cartridge system11, and the air grille panel cartridge assembly13, itself may be performed in a location200(seeFIGS. 1A-1B) that is optimized, where tools, parts, and Foreign Object Debris (FOD) collection devices are readily available. The time needed for installers or mechanics to leave the vehicle14, such as the aircraft16, to retrieve each independent part or tool is eliminated, so the raceway cover assembly10, the sidewall closeout area cartridge system11, and the air grille panel cartridge assembly13are assembled more efficiently. Moreover, the location200provides an optimized work area that allows an installer or mechanic to sit or stand while performing work, and to use powered tools, such as a saw replacing a knife for cutting or trimming, that may not be available on the vehicle14, such as the aircraft16. This may result in a cost savings for production and elimination of variability.

Moreover, disclosed versions of the raceway cover assembly10(seeFIGS. 1A, 4A-4B), the sidewall closeout area cartridge system11(seeFIGS. 1B, 9A-9B), the air grille panel cartridge assembly13(seeFIGS. 1B, 10A), the method220(seeFIG. 11A), and the method230(seeFIG. 11B) allow an installer to pre-load the one or more conductive elements50into the raceway cover assembly10, the sidewall closeout area cartridge system11, or the air grille panel cartridge assembly13, and allow for multiple installations to be done simultaneously to reduce production times and to significantly decrease the complexity of the installations. This may result in increased efficiency, increased quality of manufacturing of parts for the vehicle14, such as the aircraft16, and overall decreased costs of assembly and manufacturing. This may further result in lightweight aircraft structures that are less complex by reducing congestion of the conductive elements50because the raceway cover assembly10and the sidewall closeout area cartridge system11keep the conductive elements50gathered together off the vehicle14, such as the aircraft16, prior to installation in the vehicle14, such as the aircraft16. The service lengths, or ends of the conductive elements50, may be stowed out of the way to prevent any potential damage to the conductive elements50and connector portions51(seeFIG. 1A), as well as keep them out of the way to avoid any possible ergonomics issues for people or tooling. Disclosed versions of the raceway cover assembly10(seeFIGS. 1A, 4A-4B), the sidewall closeout area cartridge system11(seeFIGS. 1B, 9A-9B), the air grille panel cartridge assembly13(seeFIGS. 1B, 10A), the method220(seeFIG. 11A), and the method230(seeFIG. 11B) also allow for future installation of the seats182(seeFIG. 1B) with ease, and enable an installer to pre-assemble parts off of the vehicle14, such as the aircraft16, and to avoid the need for outboard seat tracks, seat track covers, and other related parts.

In addition, disclosed versions of the raceway cover assembly10(seeFIGS. 1A, 4A-4B), the sidewall closeout area cartridge system11(seeFIGS. 1B, 9A-9B), the air grille panel cartridge assembly13(seeFIGS. 1B, 10A), the method220(seeFIG. 11A), and the method230(seeFIG. 11B) provide a routing path86(seeFIG. 1A) that is stable and that does not need to be re-engineered for different aircraft cabin layouts87(seeFIG. 1A), and provide a modular design146(seeFIG. 1A) that is configurable and applicable to all possible variation of aircraft layouts. The raceway cover assembly10(seeFIG. 1A), the sidewall closeout area cartridge system11(seeFIG. 1B), and the air grille panel cartridge assembly13(seeFIG. 1B) provide a space where the conductive elements50(seeFIG. 1A), for example, wires60(seeFIG. 1A) and cables62(seeFIG. 1A), will not be damaged by contact from passengers or carry-on freight in the interior112(seeFIG. 1B) of the cabin48(seeFIG. 1B) of the vehicle14, such as the aircraft16(seeFIG. 1B), and provide an architecture that is easy to install and minimizes or avoids ergonomic issues for installers. The closeout area142(seeFIG. 1A) between the raceway18(seeFIG. 1A) and the raceway cover90(seeFIG. 1A) has a cross-sectional area144(seeFIG. 1A) that is sufficiently large enough to house and protect the conductive elements50, and that is sufficiently small enough to provide adequate support, and provides a channel or space in an otherwise unused volume148(seeFIG. 1A) of the vehicle14, such as the aircraft16, and eliminates the need for congestion of wires60, cables62, and other conductive elements50, above the floor152(seeFIG. 1B) in the cabin48(seeFIG. 1B). The envelope of the closeout area142, or channel, is preferably optimized to allow for environmental control system (ECS) constraints, such as air flow, decompression, and the like.

Further, disclosed versions of the raceway cover assembly10(seeFIGS. 1A, 4A-4B), the sidewall closeout area cartridge system11(seeFIGS. 1B, 9A-9B), the air grille panel cartridge assembly13(seeFIGS. 1B, 10A), the method220(seeFIG. 11A), and the method230(seeFIG. 11B) improve the visual appearance of the cabin48by eliminating traversing electrical runs, eliminating variability in the floor covering, and eliminating protrusions in the cabin48. Moreover, disclosed versions of the raceway cover assembly10(seeFIGS. 1A, 4A-4B), the sidewall closeout area cartridge system11(seeFIGS. 1B, 9A-9B), the air grille panel cartridge assembly13(seeFIGS. 1B, 10A), the method220(seeFIG. 11A), and the method230(seeFIG. 11B) provide floor penetration elimination150(seeFIG. 1A) and remove the need to penetrate the floor152of the cabin48with holes151(seeFIG. 2B) to route the conductive elements50between main runs located below the floor152in the underfloor area52(seeFIG. 1B), in the cabin48(seeFIG. 1B), and/or in the crown area46(seeFIG. 1B), by locating the conductive elements50, for example, wires60, cables62, or other conductive elements, such that they can be accessible and easily routed without interference through aircraft structures. In addition, disclosed versions of the raceway cover assembly10(seeFIGS. 1A, 4A-4B), the sidewall closeout area cartridge system11(seeFIGS. 1B, 9A-9B), the air grille panel cartridge assembly13(seeFIGS. 1B, 10A), the method220(seeFIG. 11A), and the method230(seeFIG. 11B) provide for rapid reconfiguration of seats182, such as palletized seats182a, at different seat pitches, in the cabin48, such as the passenger cabin48a, of the vehicle14, such as the aircraft16.

Many modifications and other versions of the disclosure will come to mind to one skilled in the art to which this disclosure pertains having the benefit of the teachings presented in the foregoing descriptions and the associated drawings. The versions described herein are meant to be illustrative and are not intended to be limiting or exhaustive. Although specific terms are employed herein, they are used in a generic and descriptive sense only and not for purposes of limitation.