In various embodiments, the present disclosure provides an energy attenuating mounting foot comprising a load beam having a longitudinal axis, a top surface, a bottom surface, an inner track interface lobe, and an outer track interface lobe, the inner track interface lobe and the outer track interface lobe extending laterally from the load beam, and a channel along the longitudinal axis having a depth extending from the load beam bottom surface toward the top surface. In various embodiments, the inner track interface lobe has a first length extending in a direction from the bottom surface towards the top surface and the outer track interface lobe has a second length extending in a direction from the bottom surface towards the top surface, the first length being less than the second length.

In order to provide an aircraft seat unit and an aircraft seat unit assembly capable of meeting various passenger requirements, an aircraft seat unit is provided with a seat portion including a first buttocks support layer and a second buttocks support layer, and a backrest portion. The seat portion is configured to be capable of changing states between a short seat portion state and a long seat portion state. The first buttocks support layer configured to support the buttocks of a passenger in the short seat portion state is harder than the second buttocks support layer configured to support the buttocks of the passenger in the long seat portion state.

An energy absorbing device includes a first connector and a second connector. The first connector is for connection to the base of a seat back of an aircraft seat and the second connector is for connection to the frame of an aircraft seat. The first connector is moveable relative to the second connector. The energy absorbing device further includes one or more resiliently deformable members which are compressed when the first connector is moved away from the second connector. Also described is a seat comprising the energy absorbing device and a row of seats.

An arm restraint assembly for an ejection seat may comprise a primary arm configured to pivot about a primary arm pivot joint. A latch may be coupled to the primary arm. The latch may comprise a first pair of lugs and may be configured to pivot relative to the primary arm. A primary shear pin may extend between the first pair of lugs. A lanyard may be coupled to the primary shear pin.

A life preserver head restraint may be configured to inflate in response to deployment of a parachute assembly. The life preserver head restraint may comprise an inflatable volume and a charge tank fluidly coupled to the inflatable volume. In an inflated state, the life preserver head restraint may restrict head movement during line stretch of the parachute assembly.

A life preserver head restraint may be configured to inflate in response to deployment of a parachute assembly. The life preserver head restraint may comprise an inflatable volume and a charge tank fluidly coupled to the inflatable volume. In an inflated state, the life preserver head restraint may restrict head movement during line stretch of the parachute assembly.

Airbag systems for use in aircraft are described herein. In some embodiments, an occupant restraint system for use with a passenger seat on an aircraft includes an under-seat airbag having a leg restraint portion. The under-seat airbag can be stowed approximate to a seat pan prior to use. In operation, the under-seat airbag can inflate to reduce occupant forward head path excursion and/or forward extension of the occupant's legs during a crash or other rapid deceleration event.

Airbag systems for use in aircraft are described herein. In some embodiments, an occupant restraint system for use with a passenger seat on an aircraft includes an under-seat airbag having a leg restraint portion. The under-seat airbag can be stowed approximate to a seat pan prior to use. In operation, the under-seat airbag can inflate to reduce occupant forward head path excursion and/or forward extension of the occupant's legs during a crash or other rapid deceleration event.

An arm restraint assembly configured to pierce a canopy in response to expulsion of an ejection seat from a cockpit may comprise a primary arm configured to pivot relative to the ejection seat. A canopy piercer may be coupled to the primary arm. The primary arm may be configured to rotate to a fully-deployed position while located within the cockpit. An apex of the canopy piercer may be oriented toward the canopy, when the primary arm is in the fully-deployed position.

An arm restraint assembly configured to pierce a canopy in response to expulsion of an ejection seat from a cockpit may comprise a primary arm configured to pivot relative to the ejection seat. A canopy piercer may be coupled to the primary arm. The primary arm may be configured to rotate to a fully-deployed position while located within the cockpit. An apex of the canopy piercer may be oriented toward the canopy, when the primary arm is in the fully-deployed position.