METHOD AND KIT FOR PRESERVING A FUEL SYSTEM OF AN AIRCRAFT ENGINE
First Claim
1. A method for preserving a fuel system of an aircraft engine outside of an engine test cell without powering an electronic engine controller of the aircraft engine in preparation for a period of inactivity of the aircraft engine, the method comprising:
- supplying preservation fluid to the fuel system of the aircraft engine;
opening a valve of the fuel system using a control device, other than the electronic engine controller of the aircraft engine, coupled to the fuel system via a connector configured to provide an interface between the electronic engine controller of the aircraft engine and the fuel system of the aircraft engine; and
driving a fuel pump of the fuel system using a driver coupled to an accessory gearbox of the aircraft engine to cause some of the preservation fluid to flow through the open valve and in at least part of the fuel system of the aircraft engine.
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Accused Products
Abstract
A method and kit for preserving a fuel system of an aircraft engine outside of an engine test cell in preparation for a period of inactivity of the aircraft engine are disclosed. The method comprises: supplying preservation fluid to the fuel system of the aircraft engine; generating a signal to cause the opening of a valve of the fuel system using a control device other than the electronic engine controller of the aircraft engine; and driving a fuel pump of the fuel system to cause some of the preservation fluid to flow through the open valve and in at least part of the fuel system of the aircraft engine.
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Citations
20 Claims
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1. A method for preserving a fuel system of an aircraft engine outside of an engine test cell without powering an electronic engine controller of the aircraft engine in preparation for a period of inactivity of the aircraft engine, the method comprising:
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supplying preservation fluid to the fuel system of the aircraft engine; opening a valve of the fuel system using a control device, other than the electronic engine controller of the aircraft engine, coupled to the fuel system via a connector configured to provide an interface between the electronic engine controller of the aircraft engine and the fuel system of the aircraft engine; and driving a fuel pump of the fuel system using a driver coupled to an accessory gearbox of the aircraft engine to cause some of the preservation fluid to flow through the open valve and in at least part of the fuel system of the aircraft engine. - View Dependent Claims (2, 3, 4, 5, 6, 7, 8)
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9. A kit for preserving a fuel system of an aircraft engine outside of an engine test cell without powering an engine electronic controller of the aircraft engine in preparation for a period of inactivity of the aircraft engine, the kit comprising:
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a control device, other than the electronic engine controller of the aircraft engine, configured to; be coupled to the fuel system via a connector configured to provide an interface between the electronic engine controller of the aircraft engine and the fuel system of the aircraft engine; and cause a valve of the fuel system to open; and a driver configured to be coupled to an accessory gearbox of the aircraft engine and drive a fuel pump of the fuel system via the accessory gearbox to cause some of the preservation fluid to flow in at least part of the fuel system of the aircraft engine. - View Dependent Claims (10, 11, 12, 13, 14, 15)
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16. A method for preserving a fuel system of an aircraft engine outside of an engine test cell without powering an engine electronic controller of the aircraft engine in preparation for a period of inactivity of the aircraft engine, the method comprising:
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supplying preservation fluid to the fuel system of the aircraft engine; generating a signal to cause the opening of a valve of the fuel system using a control device other than the electronic engine controller of the aircraft engine; and driving a fuel pump of the fuel system to cause some of the preservation fluid to flow through the open valve and in at least part of the fuel system of the aircraft engine. - View Dependent Claims (17, 18, 19, 20)
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Specification