IP Library › Granted Patent US 12662233
Granted Patent B2
US 12662233 · App. 17/569,167 · Granted Jun 23, 2026

Folding step system

Inventors: Michael Ross Wilkinson (North Richland Hills, TX); James Everett Kooiman (Fort Worth, TX); Clegg Benjamin Brian Smith (Fort Worth, TX); Jeffrey Matthew Williams (Aledo, TX); Tjepke Heeringa (Dallas, TX); David G. Carlson (North Richland Hills, TX)
Assignee: Textron Innovations Inc.
B64C1/24
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Quick Facts
Patent No.
US 12662233
App. No.
17/569,167
Granted
Jun 23, 2026
Kind
B2
Abstract

A folding step system includes a housing forming an interior space and a step comprising a step surface. The step is movable between a stowed configuration in which substantially all of the step surface is disposed within the interior space and a deployed configuration in which at least a portion of the step surface is disposed outside of the interior space and at least a portion of the step surface is disposed within the interior space.

Claims (46)

1 . A folding step system, comprising:

a housing forming an interior space; and

a step comprising a step surface and a planar load transmitting surface for selectively contacting a planar load reaction surface of the housing, the step being movable between a stowed configuration in which the step surface is disposed within the interior space and a deployed configuration in which at least a portion of the step surface is disposed outside of the interior space and at least a portion of the step surface is disposed within the interior space;

wherein at least a portion of the planar load transmitting surface is disposed deeper within the interior space when the step is in the deployed configuration as compared to a maximum depth within the interior space of the step surface when the step is in the stowed configuration;

wherein the step is limited to rotational movement relative to the housing about a rotation axis fixed relative to the housing in both the stowed configuration and the deployed configuration;

wherein the planar load reaction surface is higher than the planar load transmitting surface when the folding step system is in a first orientation and when viewed from a first point of view;

wherein the step surface is relatively higher than all portions of the planar load transmitting surface and the planar load reaction surface when the step is in the deployed configuration while the folding step system is in the first orientation and while viewed from the first point of view; and

at least one of (1) wherein the planar load transmitting surface extends along a plane that is not parallel to a longitudinally central planar portion of the step surface that is completely disposed outside the housing when the step is in the deployed configuration and (2) wherein a latch mechanism is disposed at least partially within the step, the entirety of the latch mechanism is offset from the rotation axis, and the latch mechanism is selectively operable by movement of the latch mechanism in a direction substantially parallel to the rotation axis.

2 . The folding step system of claim 1 , wherein the step surface comprises a continuous surface.

3 . The folding step system of claim 1 , further comprising:

a lock pin receiver carried by the housing and configured to selectively receive a locking pin of the latch mechanism.

4 . The folding step system of claim 3 , wherein the latch mechanism comprises a biasing mechanism configured to selectively assist movement of the locking pin.

5 . The folding step system of claim 1 , further comprising:

a cover carried by the step and disposed generally opposite the step surface.

6 . The folding step system of claim 5 , wherein the housing further comprises a flange surrounding a perimeter of the cover.

7 . An aircraft, comprising:

a fuselage comprising an exterior profile; and

a folding step system, comprising:

a housing forming an interior space; and

a step comprising a step surface and a planar load transmitting surface for selectively contacting a planar load reaction surface of the housing, the step movable between a stowed configuration in which the step surface is disposed within the interior space and a deployed configuration in which at least a portion of the step surface is disposed outside of the interior space and at least a portion of the step surface is disposed within the interior space;

wherein at least a portion of the planar load transmitting surface is disposed deeper within the interior space when the step is in the deployed configuration as compared to a maximum depth within the interior space of the step surface when the step is in the stowed configuration;

wherein the step is limited to rotational movement relative to the housing about a rotation axis fixed relative to the housing in both the stowed configuration and the deployed configuration;

wherein the planar load reaction surface is higher than the planar load transmitting surface when the folding step system is in a first orientation and viewed from a first point of view;

wherein the step surface is relatively higher than all portions of the planar load transmitting surface and the planar load reaction surface when the step is in the deployed configuration while the folding step system is in the first orientation and while viewed from the first point of view; and

at least one of (1) wherein the planar load transmitting surface extends along a plane that is not parallel to a longitudinally central planar portion of the step surface that is completely disposed outside the housing when the step is in the deployed configuration and (2) wherein a latch mechanism is disposed at least partially within the step, the entirety of the latch mechanism is offset from the rotation axis, and the latch mechanism is selectively operable by movement of the latch mechanism in a direction substantially parallel to the rotation axis.

8 . The aircraft of claim 7 , wherein the step surface comprises a continuous surface.

9 . The aircraft of claim 7 , further comprising:

a lock pin receiver carried by the housing and configured to selectively receive a locking pin of the latch mechanism.

10 . The aircraft of claim 9 , wherein the latch mechanism comprises a biasing mechanism configured to selectively assist movement of the locking pin.

11 . The aircraft of claim 7 , further comprising:

a cover carried by the step and disposed generally opposite the step surface.

12 . The aircraft of claim 11 , wherein the housing further comprises a flange surrounding a perimeter of the cover.

13 . A method of operating a folding step, comprising:

providing a housing comprising an interior space;

providing a step carried by the housing, the step having a step surface and a planar load transmitting surface for selectively contacting a planar load reaction surface of the housing and the step being movable relative to the housing and movable between a stowed configuration and a deployed configuration; and

moving the step relative to the housing thereby changing an amount of the step that is disposed within the interior space; and

moving the step so that at least a portion of the planar load transmitting surface is disposed deeper within the interior space when the step is in the deployed configuration as compared to a maximum depth within the interior space of the step surface when the step is in the stowed configuration;

wherein the step is limited to rotational movement relative to the housing about a rotation axis fixed relative to the housing in both the stowed configuration and the deployed configuration;

wherein the planar load reaction surface is higher than the planar load transmitting surface when the housing and step are in a first orientation and when viewed from a first point of view;

wherein the step surface is relatively higher than all portions of the planar load transmitting surface and the planar load reaction surface when the step is in the deployed configuration while the housing and the step are in the first orientation and while viewed from the first point of view; and

at least one of (1) wherein the planar load transmitting surface extends along a plane that is not parallel to a longitudinally central planar portion of the step surface that is completely disposed outside the housing when the step is in the deployed configuration and (2) providing a latch mechanism disposed at least partially within the step, the entirety of the latch mechanism being offset from the rotation axis, and the latch mechanism being selectively operable by movement of the latch mechanism in a direction substantially parallel to the rotation axis.

14 . The method of claim 13 , further comprising:

operating the latch mechanism to selectively allow movement of the step relative to the housing.

15 . The method of claim 13 , further comprising:

disposing at least a portion of the housing within a fuselage of an aircraft.

16 . The method of claim 15 , wherein when the step is in the stowed configuration the step is completely received within the fuselage and wherein when the step is in the deployed configuration at least a portion of the step extends to a space outside the fuselage.