Abstract: A head impact criteria (HIC) device for a controlling a breakover rate of a seatback of an aircraft seat, and a method of manufacturing the same, are disclosed. A first energy absorbing member is coupled to the seatback of the aircraft seat. A second energy absorbing member is coupled to a frame of the aircraft seat. A fuse link is encapsulated by the first energy absorbing member and the second energy absorbing member. In response to the HIC device being subjected to a threshold load associated with a dynamic event, the fuse link breaks and the first energy absorbing member and the second energy absorbing member rotate around the axis.

Abstract: An arm rest assembly and aircraft passenger seat including the same. The arm rest includes a friction mechanism for resisting abrupt rotational movements of the arm rest. A rotationally fixed frame member defining a rotational axis and receives a rotational member of the arm rest configured to rotate around the rotational axis. A groove formed in an outer circumferential surface of the rotational member seats a O-ring disposed between the groove and an inner circumferential surface of the frame member. Tolerance between the frame member and arm rest is such that the O-ring is held in the groove in a compressed state and frictionally engagement each of the rotational member and the frame member.

Abstract: A springless lower closeout system for a passenger seat includes left-side and right-side seat spreaders defining a lower aft portion of the passenger seat between them. Each seat spreader includes a restrictive channel extending along the left and right sides of the seat spreader, oriented toward the lower aft portion of the passenger seat. A dress cover extends in a taut state between the left-side and right-side seat spreaders. The dress cover includes cord elements on its left and right edges, the cord elements insertable into the left-side restrictive channels to directly connect the dress cover to the seat spreaders, closing out the lower aft portion of the passenger seat. A zipper or fastener connecting the dress cover and either edge may be partially unfastened to adjust the tension of the dress cover and facilitate attachment or removal of the cord elements to or from the restrictive channels.

Abstract: An aircraft cushion includes a lower portion, upper portion, and forward portion of foam. The lower portion is configured to be located by a forward frame element (e.g., tube) and to be supported by the forward frame element and a seat diaphragm (e.g., stretched fabric). The upper portion and forward portion are softer for user comfort. The lower portion, using a shape of the foam (e.g., structural foam), may removably snap onto the forward frame element, and rotate down into place for ease of installation.

Abstract: An aircraft seat diaphragm includes a pre-stretched elastomeric fabric. The elastomeric fabric is bonded to a composite frame with features to insert the diaphragm into aircraft seat spreaders. The composite frame defines a rear extension that extends up along the rear of the seat for added support. The rear extension may correspond to a fabric portion that releasably attaches to the seat back of the aircraft seat. Rear attachment features on the composite frame engage clips on the rear of a seat cushion to hold the seat cushion in place.

Abstract: A passenger seat rear-mounted meal tray assembly with a low-profile inline latch includes a meal tray substantially contoured to the seatback surface and a latch pin assembly mounted within the meal tray beneath the seatback surface, the latch assembly including a latch pin for engaging with the seatback to hold the meal tray in the stowed configuration. The meal tray includes a handle likewise contoured to the exterior surface of the tray, the handle having an outer face articulable by a passenger to pivot the handle and disengage the latch pin from the seatback. Disengaging the latch pin via the handle releases the meal tray by the handle into the hand of the passenger, who may manually pivot the tray into a substantially horizontal deployed configuration. The meal tray may similarly be restowed to the seatback (e.g., by pushing the tray back into stowed position) without engaging the handle.

Abstract: A passenger seat rear-mounted meal tray assembly with a low-profile inline latch includes a meal tray substantially contoured to the seatback surface and a latch pin assembly mounted within the meal tray beneath the seatback surface, the latch assembly including a latch pin for engaging with the seatback to hold the meal tray in the stowed configuration. The meal tray includes a handle likewise contoured to the exterior surface of the tray, the handle having an outer face articulable by a passenger to pivot the handle and disengage the latch pin from the seatback. Disengaging the latch pin via the handle releases the meal tray by the handle into the hand of the passenger, who may manually pivot the tray into a substantially horizontal deployed configuration. The meal tray may similarly be restowed to the seatback (e.g., by pushing the tray back into stowed position) without engaging the handle.

Abstract: An arm rest assembly and aircraft passenger seat including the same. The arm rest includes a friction mechanism for resisting abrupt rotational movements of the arm rest. A rotationally fixed frame member defining a rotational axis and receives a rotational member of the arm rest configured to rotate around the rotational axis. A groove formed in an outer circumferential surface of the rotational member seats a O-ring disposed between the groove and an inner circumferential surface of the frame member. Tolerance between the frame member and arm rest is such that the O-ring is held in the groove in a compressed state and frictionally engagement each of the rotational member and the frame member.

Abstract: A springless lower closeout system for a passenger seat includes left-side and right-side seat spreaders defining a lower aft portion of the passenger seat between them. Each seat spreader includes a restrictive channel extending along the left and right sides of the seat spreader, oriented toward the lower aft portion of the passenger seat. A dress cover extends in a taut state between the left-side and right-side seat spreaders. The dress cover includes cord elements on its left and right edges, the cord elements insertable into the left-side restrictive channels to directly connect the dress cover to the seat spreaders, closing out the lower aft portion of the passenger seat. A zipper or fastener connecting the dress cover and either edge may be partially unfastened to adjust the tension of the dress cover and facilitate attachment or removal of the cord elements to or from the restrictive channels.

Abstract: A head impact criteria (HIC) device for a controlling a breakover rate of a seatback of an aircraft seat, and a method of manufacturing the same, are disclosed. A first energy absorbing member is coupled to the seatback of the aircraft seat. A second energy absorbing member is coupled to a frame of the aircraft seat. A fuse link is encapsulated by the first energy absorbing member and the second energy absorbing member. In response to the HIC device being subjected to a threshold load associated with a dynamic event, the fuse link breaks and the first energy absorbing member and the second energy absorbing member rotate around the axis.

Abstract: An aircraft seat diaphragm includes a pre-stretched elastomeric fabric. The elastomeric fabric is bonded to a composite frame with features to insert the diaphragm into aircraft seat spreaders. The composite frame defines a rear extension that extends up along the rear of the seat for added support. The rear extension may correspond to a fabric portion that releasably attaches to the seat back of the aircraft seat. Rear attachment features on the composite frame engage clips on the rear of a seat cushion to hold the seat cushion in place.

Abstract: A device for securing passenger seat frame structures (e.g., seat spreaders, legs) to a lateral crossbeam includes a wedged clamping device insertable into a pocket directly adjacent to a passage allowing the crossbeam to pass through the seat frame structure. The wedged clamping device has an upper face providing a locking taper angle and a lower arcuate face opposite the upper face and in contact with the crossbeam. When inserted into the pocket, the wedged clamping device provides a clamping force securing the seat frame structure to the crossbeam without driving a bolt through, deforming, or otherwise compromising the integrity of the crossbeam. The wedged clamping device accepts a tuning bolt through a lateral face; tightening the tuning bolt can more precisely control the amount of clamping force provided on the crossbeam.

Abstract: A seat assembly configured to be employed in vehicle seats such as aircraft passenger seats. The seat assembly includes a seat frame having first and second spaced frame members and first and second spaced transverse beams. A plurality of springs positioned proximate an aft end of the seat frame generally above the second transverse beam span between the first and second frame members. A support member is attached to the plurality of springs and to a seat back attachable to the seat frame. A cushion assembly mounts on the seat frame such that the aft end rests on the plurality of springs while the forward end rests on the front transverse beam. In use, as the aft end of the cushion assembly deflects downward toward the second transverse beam the forward end simultaneously rotates around the first transverse beam.

Abstract: A step assembly installable in a structure such as a housing of an armrest assembly, the step assembly including a base attachable to the structure including a mounting plate having a low profile and a fixed receptacle to be received in the structure, a step plate pivotally attached along a first end to the base along a lower end of the receptacle, the step plate pivotable between a stowed position in which the step plate is housed within the fixed receptacle and a deployed position in which the step plate is outside of the fixed receptacle, the step plate having a first side for supporting a foot, and a release mechanism for releasing the step plate from the stowed position to the deployed position. The step plate deployed for use and concealed from view between uses.

Abstract: A seat assembly configured to be employed in vehicle seats such as aircraft passenger seats. The seat assembly includes a seat frame having first and second spaced frame members and first and second spaced transverse beams. A plurality of springs positioned proximate an aft end of the seat frame generally above the second transverse beam span between the first and second frame members. A support member is attached to the plurality of springs and to a seat back attachable to the seat frame. A cushion assembly mounts on the seat frame such that the aft end rests on the plurality of springs while the forward end rests on the front transverse beam. In use, as the aft end of the cushion assembly deflects downward toward the second transverse beam the forward end simultaneously rotates around the first transverse beam.

Abstract: An aircraft passenger seat assembly and backrest unit attachable to a seat assembly, the backrest being pivotally attached or fixed, and the backrest unit including at least one frame member having adjacent weakened and intact sections provided along a peripheral edge, the weakened section having a first failure load and the intact section having a second failure load greater than the first failure load such that, when a load on a backside of the backrest unit exceeds the first failure load, the weakened section fails and the intact section deforms allowing a portion of the backrest unit to tilt forward beyond an upright sitting position to absorb impact energy.

Abstract: An aircraft seating system includes spreaders having restricted channels to receive a portion of diaphragm wrapped around a cord to hold the diaphragm in place at each side. The diaphragm includes a second or core layer of fabric within the diaphragm to increase the strength of the diaphragm, provide ventilation, and/or provide cushioning. The spreaders may include restricted channels to receive a diaphragm and cord for a seat back portion. The seat back portion and seat bottom portion may be a single piece or separate pieces.

Abstract: A system may include an aircraft seat bottom cushion assembly having a front portion and two side portions. The aircraft seat bottom cushion assembly may include a power providing device positioned at the front portion or one of the two side portions of the aircraft seat bottom cushion assembly. The aircraft seat bottom cushion assembly may further include electrical wiring extending through the aircraft seat bottom cushion assembly to the power providing device. The electrical wiring electrically may be coupled to the power providing device.

Abstract: An aircraft seat may include a support system with a diaphragm, a cushion with at least one surface configured to conform to a corresponding surface of the support system, a dress cover configured to fit over at least a portion of the cushion, and an attachment assembly. The attachment assembly may include a primary attachment feature coupled to the dress cover proximate to at least one edge of the dress cover or coupled to the cushion. The attachment assembly may include an auxiliary attachment feature integrated within the support system. The attachment assembly may be configured to secure the at least one surface of the cushion against the corresponding surface of the support system when the primary attachment feature is coupled to the auxiliary attachment feature at a single attachment interface for the support system, the cushion, and the dress cover.