Aircraft pressurization test apparatus and method of using same

• US 6,532,800 B1
• Filed: 04/16/2002
• Issued: 03/18/2003
• Est. Priority Date: 04/16/2002
• Status: Expired due to Fees

• Current Assignee: Thunder Aviation Na, Inc.
• Original Assignee: Thunder Aviation Na, Inc.
• Inventors: Ousley, William D., Ritchie, Scott, Boeckstiegel, Donald
• Primary Examiner(s): OEN, WILLIAM L
• Application Number:
  US10/123,638
• Time in Patent Office: 336 Days
• Field of Search: 73/17.8, 73/492, 73/493, 73/405.R, 73/52, 731/700.2, 737/14, 244/1.R, 244/2, 244/117.R, 244/119, 244/120
• US Class Current: 73/40.50R
• CPC Class Codes: G01M 3/3236 by monitoring the interior space of the containers

Abstract

A method of using an aircraft pressurization test apparatus to perform diagnostic tests on an aircraft while the aircraft is at a first region of a ground site, such as an aircraft hanger. The method comprises: positioning the aircraft at the first region of the ground site, using a first delivery line in a manner to enable fluid communication between a shop air aperture of the aircraft pressurization test apparatus and an air coupler of a shop air system at the ground site; using a second delivery line in a manner to enable fluid communication between an aircraft cabin pressurization inlet opening of the aircraft and a delivery air aperture of the aircraft pressurization test apparatus; delivering air from a compressor of the shop air system through the aircraft cabin pressurization inlet opening and into the aircraft cabin via the shop air aperture and the delivery air aperture of the aircraft pressurization test apparatus; and regulating the delivery of air from the compressor of the shop air system through the aircraft cabin pressurization inlet opening by changing characteristics of the flow path between the shop air aperture and the delivery air aperture.

Claims

1. A method of using an aircraft pressurization test apparatus to perform diagnostic tests on an aircraft while the aircraft is at a first region of a ground site, such as an aircraft hanger, the ground site including shop air, the shop air comprising a compressor fixedly secured to a second region of the ground site, the shop air further comprising fluid lines and a plurality of air couplers at different locations of the ground site, the compressor and fluid lines being configured and adapted for delivery of pressurized air to the air couplers, the aircraft comprising an aircraft cabin and an aircraft cabin pressurization inlet opening in fluid communication with the aircraft cabin, the aircraft pressurization test apparatus comprising a shop air aperture and a delivery air aperture, the method comprising:

positioning the aircraft at the first region of the ground site;

using a first delivery line in a manner to enable fluid communication between the shop air aperture of the aircraft pressurization test apparatus and one of the air couplers of the shop air;

using a second delivery line in a manner to enable fluid communication between the aircraft cabin pressurization inlet opening and the delivery air aperture;

delivering air from the compressor of the shop air through the aircraft cabin pressurization inlet opening and into the aircraft cabin via the shop air aperture and the delivery air aperture of the aircraft pressurization test apparatus;

regulating the delivery of air from the compressor of the shop air through the aircraft cabin pressurization inlet opening by changing characteristics of the flow path between the shop air aperture and the delivery air aperture.

2. A method as set forth in claim 1 wherein the step of delivering air from the compressor to the aircraft cabin pressurization inlet opening comprises delivering air through the aircraft cabin pressurization inlet opening at a temperature of less than 120°

F. (49°

C.).

3. A method as set forth in claim 1 wherein the step of delivering air from the compressor to the aircraft cabin pressurization inlet opening comprises delivering air through the aircraft cabin pressurization inlet opening at a temperature of less than 100°

F. (38°

C.).

4. A method as set forth in claim 1 wherein the step of delivering air from the compressor to the aircraft cabin pressurization inlet opening comprises delivering air through the aircraft cabin pressurization inlet opening at a temperature of less than 80°

F. (27°

C.).

5. A method as set forth in claim 1 wherein the aircraft pressurization test apparatus further comprises a cabin feedback air aperture and a cabin pressure gauge in fluid communication with the cabin feedback air aperture, and wherein the method further comprises:

using a cabin feedback line in a manner to enable fluid communication between the aircraft cabin and the cabin feedback air aperture of the aircraft pressurization test apparatus;

using the cabin pressure gauge to gauge air pressure within the aircraft cabin.

6. A method as set forth in claim 5 wherein the aircraft pressurization test apparatus further comprises a cabin vertical speed indicator in fluid communication with the cabin feedback air aperture, the cabin vertical speed indicator being adapted and configured for indicating rate of change of pressure, the method further comprising:

using the cabin vertical speed indicator in a manner to indicate change of air pressure within the aircraft cabin.

7. A method as set forth in claim 6 wherein the aircraft pressurization test apparatus further comprises a delivery air flow gauge in communication with the delivery air aperture, the delivery air flow gauge being configured and adapted to gauge air flow through the delivery air aperture, wherein:

the step of delivering air from the compressor of the shop air through the aircraft cabin pressurization inlet opening and into the aircraft cabin comprises delivering air into the aircraft cabin sufficient to pressurize the aircraft cabin to a cabin test pressure, and wherein the method further comprises;

maintaining delivery of air from the compressor of the shop air and into the aircraft cabin at a rate such that the cabin vertical speed indicator indicates that cabin pressure is in equilibrium while and the cabin pressure gauge indicates that the cabin pressure is approximately equal to the cabin test pressure;

using the delivery air flow gauge to measure air flow into the aircraft cabin when the cabin vertical speed indicator indicates that the cabin pressure is in equilibrium and the cabin pressure gauge indicates that the cabin pressure is approximately equal to the cabin test pressure.

8. A method as set forth in claim 7 wherein the method further comprises:

using the measure of air flow into the aircraft cabin to determine the rate of air leakage from the aircraft cabin.

9. A method as set forth in claim 6 wherein the step of delivering air from the compressor of the shop air through the aircraft cabin pressurization inlet opening and into the aircraft cabin comprises delivering air into the aircraft cabin sufficient to pressurize the aircraft cabin to a cabin test pressure, and wherein the method further comprises:

stopping the delivery of air into the aircraft cabin; and

reading the cabin pressure gauge at a plurality of time intervals after the stopping step to determine air pressure in the aircraft cabin at each such time interval.

10. A method as set forth in claim 6 wherein the aircraft pressurization test apparatus further comprises a delivery air flow gauge in communication with the delivery air aperture, the delivery air flow gauge being configured and adapted to gauge air flow through the delivery air aperture, wherein:

the step of delivering air from the compressor of the shop air through the aircraft cabin pressurization inlet opening and into the aircraft cabin comprises delivering air into the aircraft cabin sufficient to pressurize the aircraft cabin to a cabin test pressure;

the method further comprising listening to the exterior of the aircraft for leakage of air from the aircraft cabin to locate leaks; and

the step of positioning the aircraft at the first region of the ground site comprises positioning the aircraft sufficiently remote from the air compressor such that noise from the air compressor does not interfere with the step of locating leaks.

11. A method as set forth in claim 1 wherein the aircraft pressurization test apparatus further comprises a cabin feedback air aperture and a cabin vertical speed indicator in fluid communication with the cabin feedback air aperture, and wherein the method further comprises:

using a cabin feedback line in a manner to enable fluid communication between the aircraft cabin and the cabin feedback air aperture of the aircraft pressurization test apparatus;

using the cabin vertical speed indicator in a manner to indicate change of air pressure within the aircraft cabin.

12. A method as set forth in claim 1 wherein the aircraft further comprises an aircraft door providing access to the aircraft cabin, a door seal adjacent the aircraft door and having an interior configured to be inflated, and a door seal inlet opening in fluid communication with the interior of the door seal, the aircraft pressurization test apparatus further comprises a door seal pressure output aperture, the method further comprising:

using a door seal pressure line in a manner to enable fluid communication between the door seal inlet opening of the aircraft and the door seal pressure output aperture of the aircraft pressurization test apparatus; and

delivering air from the compressor of the shop air through the door seal inlet opening of the aircraft and into the interior of the door seal via the shop air aperture and the door seal pressure output aperture of the aircraft pressurization test apparatus.

13. A method of using an aircraft pressurization test apparatus to detect air leakage from a cabin of an aircraft, the aircraft comprising the aircraft cabin and an aircraft cabin pressurization inlet opening in fluid communication with the aircraft cabin, the aircraft pressurization test apparatus comprising a source air aperture and a delivery air aperture, the method comprising:

positioning the aircraft at a first region of a ground site, the ground site further including a second region with a source of pressurized air at the second region;

using a first delivery line in a manner to enable fluid communication between the source air aperture of the aircraft pressurization test apparatus and the source of pressurized air;

using a second delivery line in a manner to enable fluid communication between the aircraft cabin pressurization inlet opening and the delivery air aperture;

delivering air from the source of pressurized air through the aircraft cabin pressurization inlet opening and into the aircraft cabin via the source air aperture and the delivery air aperture of the aircraft pressurization test apparatus, the delivering of air being sufficient to pressurize the aircraft cabin to a cabin test pressure;

listening to the exterior of the aircraft for leakage of air from the aircraft cabin to locate leaks; and

the step of positioning the aircraft at the first region of the ground site comprising positioning the aircraft sufficiently remote from the source of pressurized air such that noise from the source of pressurized air is insufficient to interfere with the step of locating leaks.

14. A method as set forth in claim 13 further comprising:

maintaining delivery of air from the source of pressurized air and into the aircraft cabin at a rate such that the cabin pressure is in equilibrium and approximately equal to the cabin test pressure during the step of locating leaks.

15. A method as set forth in claim 13 wherein the aircraft pressurization test apparatus further comprises a cabin feedback air aperture and a cabin pressure gauge in fluid communication with the cabin feedback air aperture, and wherein the method further comprises:

using a cabin feedback line in a manner to enable fluid communication between the aircraft cabin and the cabin feedback air aperture of the aircraft pressurization test apparatus;

using the cabin pressure gauge to gauge air pressure within the aircraft cabin.

16. A method as set forth in claim 15 wherein the aircraft pressurization test apparatus further comprises a cabin vertical speed indicator in fluid communication with the cabin feedback air aperture, the cabin vertical speed indicator being adapted and configured for indicating rate of change of pressure, the method further comprising:

using the cabin vertical speed indicator in a manner to indicate change of air pressure within the aircraft cabin.

17. A method as set forth in claim 13 wherein the step of delivering air from the source of pressurized air to the aircraft cabin pressurization inlet opening comprises delivering air through the aircraft cabin pressurization inlet opening at a temperature of less than 120°

F. (49°

C.).

18. A method of using an aircraft pressurization test apparatus to perform diagnostic tests on an aircraft while the aircraft is at a ground site, such as an aircraft hanger, the ground site including a source of pressurized air, the aircraft comprising an aircraft cabin and an aircraft cabin pressurization inlet opening in fluid communication with the aircraft cabin, the aircraft pressurization test apparatus comprising a source air aperture and a delivery air aperture, the method comprising:

positioning the aircraft at the ground site;

using a first delivery line in a manner to enable fluid communication between the source air aperture of the aircraft pressurization test apparatus and the source of pressurized air;

using a second delivery line in a manner to enable fluid communication between the aircraft cabin pressurization inlet opening and the delivery air aperture;

delivering air from the source of pressurized air through the aircraft cabin pressurization inlet opening and into the aircraft cabin via the source air aperture and the delivery air aperture of the aircraft pressurization test apparatus, the delivering of air being sufficient to pressurize the aircraft cabin to a cabin test pressure;

detecting leakage of air from the aircraft cabin;

maintaining delivery of air from the source of pressurized air and into the aircraft cabin at a temperature of less than 120°

F. (49°

C.) during the step of detecting leakage of air from the aircraft cabin.

19. A method as set forth in claim 18 wherein the step of maintaining delivery of air comprises maintaining delivery of air from the source of pressurized air and into the aircraft cabin at a temperature of less than 120°

F. (49°

C.) and at a flow rate such that the cabin pressure is in equilibrium and approximately equal to the cabin test pressure during the step of detecting leakage of air from the aircraft cabin.

20. A method as set forth in claim 18 wherein the step of maintaining delivery of air comprises maintaining delivery of air from the source of pressurized air and into the aircraft cabin at a temperature of less than 100°

F. (38°

C.) during the step of detecting leakage of air from the aircraft cabin.

21. A method as set forth in claim 18 wherein the step of maintaining delivery of air comprises maintaining delivery of air from the source of pressurized air and into the aircraft cabin at a temperature of less than 80°

F. (27°

C.) during the step of detecting leakage of air from the aircraft cabin.

22. An aircraft cabin pressurization test apparatus for performing diagnostic tests on an aircraft while the aircraft is at a first region of a ground site, such as an aircraft hanger, the aircraft comprising an aircraft cabin, the ground site including a source of pressurized air, the aircraft cabin pressurization test apparatus comprising:

a housing having an exterior surface;

a shop air coupler adjacent the exterior surface of the housing and configured and adapted to releasably receive a fluid line in fluid communication with the source of pressurized air of the ground site;

a delivery air coupler adjacent the exterior surface of the housing and configured and adapted to releasably receive a fluid line in fluid communication with an aircraft cabin pressurization inlet opening of the aircraft;

a supply air pathway defined between the shop air coupler and the delivery air coupler;

at least one valve in the supply air pathway for controlling flow of air from the shop air coupler through the delivery air coupler;

a supply air flow gauge adapted and configured for gauging air flow in the supply air pathway;

a supply air pressure gauge adapted and configured for gauging air pressure in the supply air pathway;

a cabin feedback air coupler adjacent the exterior surface of the housing and adapted and configured to releasably receive a fluid line in fluid communication with the aircraft cabin; and

a cabin pressure gauge at least partially within the housing and in fluid communication with the cabin feedback air coupler, the cabin pressure gauge being adapted and configured to gauge air pressure in the aircraft cabin when the cabin feedback air coupler is in fluid communication with the aircraft cabin.

23. An aircraft cabin pressurization test apparatus as set forth in claim 22 wherein:

the at least one valve is at least partially within the housing;

the supply air flow gauge is at least partially within the housing; and

the supply air pressure gauge is at least partially within the housing.

24. An aircraft cabin pressurization test apparatus as set forth in claim 22 further comprising a cabin vertical speed indicator in fluid communication with the cabin feedback air coupler, the cabin vertical speed indicator being adapted and configured for indicating rate of change of air pressure.

25. An aircraft cabin pressurization test apparatus as set forth in claim 22 wherein the cabin pressurization test apparatus is devoid of any mechanism for generating pressurized air.

26. An aircraft cabin pressurization test apparatus as set forth in claim 22 further comprising:

a door seal pressure output air coupler connected to the housing and adapted and configured to releasably receive a fluid line in fluid communication with a door seal of the aircraft;

a door seal air pathway defined between the shop air coupler and the door seal pressure output air coupler; and

at least one door seal valve in the door seal air pathway for controlling flow of air from the shop air coupler through the door seal pressure output air coupler.