Airstair systems and associated methods are disclosed. In one embodiment, the airstair has a deployable upper step, a primary deployment device and a secondary deployment device. The upper step is movable between a stowed configuration when a door of the aircraft is closed and a deployed configuration when the door is open. The primary deployment device resiliently biases the upper step toward the deployed configuration. The secondary deployment device is movable in coordination with a movement of the door and configured to drive the deployable upper step toward the deployed configuration during opening of the door and during a failure of the primary deployment device.

Airstair systems and associated methods are disclosed. In one embodiment, the airstair has a deployable upper step, a primary deployment device and a secondary deployment device. The upper step is movable between a stowed configuration when a door of the aircraft is closed and a deployed configuration when the door is open. The primary deployment device resiliently biases the upper step toward the deployed configuration. The secondary deployment device is movable in coordination with a movement of the door and configured to drive the deployable upper step toward the deployed configuration during opening of the door and during a failure of the primary deployment device.

A maintenance step for a helicopter, comprising: a casing that is adapted for integration into a lateral shell of a fuselage of a helicopter, and a step member that is pivotally mounted to the casing, wherein a stirrup unit is pivotally mounted to the step member, the stirrup unit comprising at least a first and a second section, the second section being telescopically mounted to the first section.

A maintenance step for a helicopter, comprising: a casing that is adapted for integration into a lateral shell of a fuselage of a helicopter, and a step member that is pivotally mounted to the casing, wherein a stirrup unit is pivotally mounted to the step member, the stirrup unit comprising at least a first and a second section, the second section being telescopically mounted to the first section.

A retainer suitable for use on an aircraft is disclosed. The retainer comprises a first retainer part and a second retainer part. The first retainer part comprises a catch and a damper; in which the catch comprises one or more magnetic elements. The damper comprises a damping material, the damping material damps shock impulses; and the catch is supported on the damper.

A retainer suitable for use on an aircraft is disclosed. The retainer comprises a first retainer part and a second retainer part. The first retainer part comprises a catch and a damper; in which the catch comprises one or more magnetic elements. The damper comprises a damping material, the damping material damps shock impulses; and the catch is supported on the damper.

A fairing is provided in one example embodiment and may include a first edge portion to provide a first clearance distance between the fairing and rotor flight controls of a rotorcraft; a second edge portion to provide a second clearance distance between the fairing and the rotor flight controls of the aircraft, wherein the second clearance distance is greater than the first clearance distance; and a support structure attached to the fairing below the second edge portion. A rotorcraft is provided in another example embodiment and may include a fairing in which the fairing can include a handhold portion along an edge of the fairing. The handhold portion can include a handhold clearance distance between the handhold portion and rotor flight controls of the rotorcraft; and a support structure attached to the fairing below the handhold portion.

A fairing is provided in one example embodiment and may include an apparatus to receive at least one of a foot traffic load and a hand traffic load, wherein the apparatus can include: a step portion that is to receive at least a portion of the foot traffic load; a handhold portion that is to receive at least a portion of the hand traffic load, wherein the handhold portion extends downward from the step portion; and a support structure, wherein the support structure extends downward from of the step portion. The apparatus can include an outer flange attached to the fairing. At least a portion of the step portion the apparatus can be recessed within the fairing at a distance between one inch and three inches from a top surface of the fairing. The handhold portion can include one or more drain holes.

A compartment door of a galley within an internal cabin of a vehicle (such as an aircraft) includes a front panel having a front outer surface, and a footstep system secured to the front panel. The footstep system is moveable between a retracted position and an extended support position. The footstep system is vertically oriented in the retracted position. The footstep system outwardly extends and folds to provide a step surface in the extended support position.

A compartment door of a galley within an internal cabin of a vehicle (such as an aircraft) includes a front panel having a front outer surface, and a footstep system secured to the front panel. The footstep system is moveable between a retracted position and an extended support position. The footstep system is vertically oriented in the retracted position. The footstep system outwardly extends and folds to provide a step surface in the extended support position.