MULTIPLE POWER ASSURANCE CHECK PROCEDURE FOR AIRCRAFT WITH AN ENGINE INLET BARRIER FILTER INSTALLED

• US 20160347479A1
• Filed: 05/27/2016
• Published: 12/01/2016
• Est. Priority Date: 05/27/2015
• Status: Active Grant

• Current Assignee: Bell Helicopter Textron Incorporated (Textron Inc)
• Original Assignee: Bell Helicopter Textron Incorporated (Textron Inc)
• Inventors: O'Neil, Joshua Robert, Birkenheuer, Andrew Jordan, Peryea, Martin
• Granted Patent: US 10,766,631 B2
• Time in Patent Office: Days
• US Class Current: 1/1
• CPC Class Codes: B64D 2033/0246 comprising particle separators
• CPC Class Codes: B64D 2045/0085 Devices for aircraft health monitoring, e.g. monitoring flutter or vibration
• CPC Class Codes: B64D 43/00 Arrangements or adaptations of instruments arrangements of cameras B64D47/08; aeronautical measuring instruments per se G01C
• CPC Class Codes: B64F 5/60 Testing or inspecting aircraft components or systems

Abstract

A method of conducting an engine power assurance check includes performing a first engine power assurance check wherein the first engine power assurance check is judged as passing or failing based on power performance values calculated assuming the presence of a substantially clogged or blocked inlet barrier filter and in response to a fail result of the first engine power assurance check, performing a second engine power assurance check wherein the second power assurance check is judged as passing or failing based on power performance values calculated assuming at least one of no inlet barrier filter being installed and an open bypass of an installed inlet barrier filter.

Claims

1. A method of conducting an engine power assurance check, comprising:

performing a first engine power assurance check wherein the first engine power assurance check is judged as passing or failing based on power performance values calculated assuming the presence of a substantially clogged or blocked inlet barrier filter; and

in response to a fail result of the first engine power assurance check, performing a second engine power assurance check wherein the second power assurance check is judged as passing or failing based on power performance values calculated assuming at least one of no inlet barrier filter being installed and an open bypass of an installed inlet barrier filter.

2. The method of claim 1, wherein the first engine power assurance check is conducted with a closed inlet barrier filter bypass and wherein the second engine power assurance check is conducted with an open inlet barrier filter bypass .

3. The method of claim 1, wherein the inlet barrier filter bypass is automatically closed in response to the fail result of the first engine power assurance check.

4. The method of claim 3, wherein the inlet barrier filter bypass is closed using an actuator.

5. The method of claim 1, wherein in response to a pass result of the second engine power assurance check, a mission that would be prevented by the fail result of the first engine power assurance check is allowed by a pass result of the second engine power assurance check.

6. The method of claim 5, wherein when the mission is allowed as result of the pass result of the second engine power assurance check, a future mission is allowed only with an open inlet barrier filter bypass until a maintenance action is taken.

7. The method of claim 1, wherein in response to a fail result of the second engine power assurance check, a mission is not allowed.

8. A method of conducting an engine power assurance check, comprising:

selecting, via a touchscreen interface, one of a first engine power assurance check and a second power assurance check.

9. The method of claim 8, wherein the first engine power assurance check is associated with power performance values associated with having an inlet barrier filter installed and wherein the second engine power assurance check is associated with power performance values associated with at least one of no inlet barrier filter being installed and an open bypass of an installed inlet barrier filter.

10. The method of claim 8, further comprising:

automatically determining whether an inlet barrier filter is installed.

11. The method of claim 8, further comprising:

automatically determining a status of a bypass of an installed inlet barrier filter.

12. The method of claim 8, further comprising:

automatically selecting the second engine power assurance check in response to a fail result of the first engine power assurance check.

13. The method of claim 8, further comprising:

displaying via the touchscreen interface which of the first engine power assurance check and the second engine power assurance check is selected.

14. The method of claim 8, further comprising:

displaying via the touchscreen interface a pass result or a fail result of the selected one of the first engine power assurance check and the second engine power assurance check is selected.

15. The method of claim 8, further comprising:

automatically selecting the second engine power assurance check in response to a determination that at least one of no inlet barrier filter is installed and a bypass of an installed inlet barrier is open.

16. An aircraft, comprising:

an inlet barrier filter; and

an integrated avionics control system configured to selectively conduct a first engine power assurance check with a bypass of the inlet barrier filter closed and a second engine power assurance check with the bypass of the inlet barrier filter open.

17. The aircraft of claim 16, wherein the second engine power assurance check is automatically conducted in response to a fail result of the first engine power assurance check.

18. The aircraft of claim 16, wherein the bypass of the inlet barrier filter is automatically opened in response to a fail result of the first engine power assurance check.

19. The aircraft of claim 16, wherein the integrated avionics control system comprises a touchscreen interface configured to receive inputs regarding selection of the first engine power assurance check and the second engine power assurance check.

20. The aircraft of claim 19, wherein the touchscreen interface is configured to display pass results and fail results of the first engine power assurance check.