Patent ID: 9475383
Filing Date: 2016-10-25
CPC Classification: B60K,B64D

Claim Text:
1. An aircraft fuel tank system, comprising: one or more aircraft fuel tanks holding and supplying aircraft fuel to aircraft engines within said aircraft; an aircraft surge tank comprising an inlet from said one or more aircraft fuel tanks and a first ullage vent opening and a second ullage vent opening, said aircraft surge tank being arranged to provide a predetermined maximum fuel capacity and having a minimal ullage at said maximum fuel capacity; a first vent pipe having a first open end in fluid communication with said first ullage vent opening and a second open end positioned within said minimal ullage of said surge tank, said first vent pipe being arranged to provide fluid communication between said minimal ullage and said first ullage vent opening; a second vent pipe having a first open end in fluid communication with said second ullage vent opening and a second open end positioned within said minimal ullage of said surge tank, said second vent pipe being arranged to provide fluid communication between said minimal ullage and said second ullage vent opening; and a coupling mechanism sealingly externally coupling an external flame barrier to said second ullage vent opening so as to provide fluid communication between said second vent pipe and atmosphere via the coupled external flame barrier, and wherein said external flame barrier is permanently open to fluid flow.