Parking brake control system for an aircraft

Patent metadata

Field	Value
Publication number	US-2016009384-A1
Application number	US-201414770653-A
Country	US
Kind code	A1
Filing date	Feb 25, 2014
Priority date	Mar 6, 2013
Publication date	Jan 14, 2016
Grant date	—

Abstract

A system for providing control to a parking brake for an aircraft ( 10 ) having a power source includes a panel ( 28 ) accessible from an exterior of the aircraft ( 10 ) and a parking brake switch ( 32 ) disposed on the panel ( 28 ) providing control over the engagement and disengagement of the parking brake on the aircraft ( 10 ), a method operating such a system for providing control to a parking brake is also disclosed.

First claim

1 . A system for providing control to a parking brake for an aircraft having a power source during a towing operation of the aircraft, comprising:
a panel of the aircraft accessible from an exterior of the aircraft; a parking brake switch disposed on the panel and configured to provide control over the engagement and disengagement of the parking brake on the aircraft; and a tow status indicator configured to provide an indication to the exterior of the aircraft as to whether or not the aircraft may be towed.

2 . The system of claim 1 , wherein the panel is proximate to a landing gear of the aircraft.

3 . The system of claim 1 , wherein the panel is proximate to the nose of the aircraft.

4 . The system of claim 1 , wherein the parking brake is an electric brake.

5 . The system of claim 1 , further comprising:
a power switch disposed on the panel, to provide power to the system from the power source.

6 . The system of claim 1 , wherein the power source is at least one battery on the aircraft.

7 . The system of claim 1 , further comprising:
a navigation lights switch, wherein the navigation lights switch permits activation and deactivation of navigation lights on the aircraft when power is provided to the electric brakes.

8 . The system of claim 5 , wherein navigation lights are activated when power is provided to the system from the power source.

9 . The system of claim 7 , wherein the navigation lights are powered by the power source.

10 . The system of claim 9 , wherein the beacon lights are powered by the power source.

11 . The system of claim 1 , wherein:
the tow status indicator is disposed on the panel; the tow status indicator is configured to indicate that towing is permitted when the parking brake is disengaged; and the tow status indicator is configured to indicate that towing is not permitted when the parking brake is engaged.

12 . The system of claim 1 , wherein the panel is accessible by a person standing on the ground, adjacent to the aircraft.

13 . A method of operating a system for providing control to a parking brake for an aircraft having a power source, a panel accessible from an exterior of the aircraft, and a parking brake switch disposed on the panel to provide control over the engagement and disengagement of the parking brake on the aircraft, the method comprising:
determining if towing is permitted for the aircraft; after activation of the power switch, providing power from the power source to the parking brake; indicating whether the aircraft may be towed or not using a tow status indicator configured to provide an indication to the exterior of the aircraft; and if towing is not permitted, receiving a signal from the parking brake switch to disengage the parking brake.

14 . The method of claim 13 , wherein the panel is proximate to a landing gear of the aircraft.

15 . The method of claim 13 , wherein the panel is proximate to a nose of the aircraft.

16 . The method of claim 13 , wherein towing of the aircraft is controlled by at least one ground crew member.

17 . The method of claim 13 , wherein the parking brake is an electric brake.

18 . The method of claim 13 , wherein a power switch on the panel provides power to the system from the power source.

19 . The method of claim 18 , further comprising:
activating navigation lights on the aircraft after activation of a navigation lights switch on the panel.

20 . The method of claim 19 , wherein navigation lights are activated when power is provided to the system from the power source.

21 . The method of claim 13 , wherein the determining step includes assessing if the parking brake is engaged.

22 . The method of claim 13 , wherein the power source is at least one battery.

23 . The method of claim 13 , wherein the navigation lights are powered by the power source.

24 . The method of claim 13 , further comprising:
activating beacon lights on the aircraft.

25 . The method of claim 24 , wherein the beacon lights are powered by the power source.

26 . The method of claim 13 , wherein the panel is accessible by the ground crew member standing on the ground, adjacent to the aircraft.

Assignees

• Bombardier Inc

Inventors

• Di Zazzo Marco
• Plante Bertrand

Classifications

• B64F1/22

  for handling aircraft · CPC title

• B64C25/42 Primary

  Arrangement or adaptation of brakes · CPC title

• B64D47/02

  Arrangements or adaptations of signal or lighting devices · CPC title

• B60T17/22

  Devices for monitoring or checking brake systems; Signal devices · CPC title

• B60T7/085

  by electrical means, e.g. travel, force sensors · CPC title