Aircraft rudder pedal lockout assemblies systems and methods

Patent metadata

Field	Value
Publication number	US-10017242-B2
Application number	US-201615011288-A
Country	US
Kind code	B2
Filing date	Jan 29, 2016
Priority date	Jan 29, 2016
Publication date	Jul 10, 2018
Grant date	Jul 10, 2018

Abstract

A lockout assembly for first and second rudder pedals of an aircraft includes first and second spacers, each of which is configured to be inserted within a corresponding one of first and second slots disposed in an adjacent rudder pedal housing. A coupling mechanism is configured to couple the first spacer to the second spacer through the rudder pedal housing so as to retain the first and second spacers in corresponding ones of the slots. The lockout mechanism prevents movement of the rudder pedals in a same direction, and hence, movement of the aircraft's rudder.

First claim

What is claimed is:

1. A lockout assembly for first and second rudder pedals of an aircraft, the first and second rudder pedals being positioned with respect to a rudder pedal housing, wherein the rudder pedal housing has first and second slots, the lockout assembly comprising:
first and second spacers, the first spacer being configured to be inserted within the first slot in the rudder pedal housing and the second spacer being configured to be inserted within the second slot in the rudder pedal housing; and
a coupling mechanism configured to couple the first spacer to the second spacer through the rudder pedal housing so as to retain the first spacer in the first slot and the second spacer in the second slot.

2. The lockout assembly of claim 1 , wherein:
each of the first and second slots has a rear end;
a corresponding portion of each of the first and second rudder pedals is configured to travel within a corresponding slot; and
each of the first and second spacers is disposed between a corresponding portion and the rear end of the corresponding slot.

3. The lockout assembly of claim 1 , wherein each of the first and second spacers comprises a flange that is disposed on a lateral surface of the respective spacer and outboard of the rudder pedal housing, each flange being configured to position the respective spacer within the corresponding slot and to prevent lateral movement of the respective spacer from the corresponding slot and into the rudder pedal housing.

4. The lockout assembly of claim 1 , wherein each of the spacers comprises an aperture of a pair of coaxially aligned apertures and the coupling mechanism comprises an elongated rod configured to extend laterally through the slots of the rudder pedal housing and the pair of coaxially aligned apertures respectively disposed in each of the spacers.

5. The lockout assembly of claim 4 , wherein the rod includes a first end and an opposite second end, and the rod further comprises a wrenching feature disposed at the first end of the rod and a transverse through-opening disposed adjacent to the second end of the rod.

6. The lockout assembly of claim 5 , wherein the wrenching feature comprises complementary helical threads respectively disposed on a surface of the rod and in the aperture of the corresponding spacer.

7. The lockout assembly of claim 5 , wherein the wrenching feature comprises a knob configured to be turned by a user.

8. The lockout assembly of claim 5 , wherein the transverse through-opening is configured to receive a shackle of a lock.

9. The lockout assembly of claim 1 , wherein the first spacer and the second spacer are bilaterally symmetrical with respect to each other about a vertical plane passing between the first and second rudder pedals.

10. A method for locking out first and second rudder pedals of an aircraft, the method comprising utilizing the lockout assembly of claim 1 by installing the lockout assembly into the first and second slots of the rudder pedal housing.

11. A method for locking out first and second rudder pedals of an aircraft, the method comprising:
inserting a first spacer within a first slot disposed in a rudder pedal housing;
inserting a second spacer within a second slot disposed in the rudder pedal housing; and
coupling the first spacer to the second spacer through the rudder pedal housing so as to retain the first spacer in the first slot and the second spacer in the second slot.

12. The method of claim 11 , wherein
each slot has a rear end; and
the coupling comprises releasably coupling the first and second spacers in the first and second slots such that each spacer is disposed between a corresponding rudder pedal and the rear end of the corresponding slots.

13. The method of claim 12 , wherein
each of the first and second spacers includes a flange disposed on a lateral surface of the respective spacer and outboard of the rudder pedal housing, the method further comprising:
positioning the flange with respect to the rudder pedal housing such that the respective spacer is within the corresponding slots to prevent lateral movement of the spacer from the slot and into the rudder pedal housing; and
the coupling comprises pulling the flanges toward each other and against opposite sides of the rudder pedal housing.

14. The method of claim 13 , wherein the pulling comprises:
inserting an elongated rod laterally through the slots of the rudder pedal housing and a pair of coaxially aligned apertures respectively disposed in each of the first and second spacers, the rod having opposite first and second ends, a wrenching feature disposed at the first end, and a transverse through-opening disposed adjacent to the second end; and
turning the wrenching feature of the rod so as to engage a helical thread disposed on a surface of the rod with a complementary helical thread disposed in the aperture of a corresponding one of the spacers.

15. The method of claim 14 , further comprising:
inserting a shackle of a lock through the transverse through-opening; and
lockingly engaging the shackle in a body of the lock.

16. The method of claim 14 , further comprising affixing a tag to the rod through the transverse through-opening.

Assignees

• Boeing Co

Inventors

• Huynh Tommy P
• Schmidt Gary W
• Schmucker Lance S
• Beasley Amber L

Classifications

• B64C13/14 Primary

  lockable · CPC title

• B64F5/40

  Maintaining or repairing aircraft · CPC title

• B64C13/044

  operated by feet, e.g. pedals · CPC title