Airbus Operations Gmbh

Mark Christopher Smiles

J Patrick Sandiford

Oliver Family

Dylan Benedict James

James Patrick Sandiford

A method is provided of inerting one or more fuel tanks of an aircraft. The method comprises: providing a temperature value indicative of a temperature at the aircraft's destination; comparing said temperature value with a predetermined value; and on the basis of said comparison, controlling the provision of inerting gas to the one or more aircraft fuel tanks. An aircraft fuel tank inerting arrangement, a software product and an aircraft are also provided.

Aircraft fuel tank inerting arrangement, method of inerting one or more aircraft fuel tanks, aircraft and software product

The invention provides a filter for a pipe, the filter comprising an attachment portion for attaching to the pipe, and a filter surface for presentation to and filtering of an oncoming flow of the pipe, wherein the filter surface has at least one pointed apex for protruding into the oncoming flow. The invention also provides a pipe for transporting an oncoming flow, wherein the pipe is provided with a filter surface across the cross-sectional area of the pipe and wherein the filter surface has at least one pointed apex protruding along the longitudinal axis of the pipe. The invention also provides an aircraft with such a filter or pipe and a method of filtering an oncoming flow of a pipe.

Filter for a pipe

An aircraft venting tank (for example a surge tank) has a stack pipe unit. The stack pipe unit comprises first and second portions and houses a frangible overpressure protector element (for example a frangible disc). The stack pipe unit may be arranged to have a fitted configuration in which the first portion of the stack pipe unit is attached to a part of the venting tank structure, the first portion is coupled to the second portion, and the second portion is coupled to another part of the venting tank structure. The first portion may be held in a relationship with the second portion so as to form a seal between the frangible element, and the first and second portions. In a frangible element-replacement configuration the second portion may be coupled to the venting tank structure, such that the frangible overpressure protector element can be replaced without removal of the second portion from the venting tank structure. The venting tank may include a frangible element holder for holding a spare frangible element for use in an overpressure protector unit.

Overpressure protection for an aircraft fuel tank system

An aircraft fuel tank assembly comprises a first fuel tank, a second fuel tank and a tank-to-tank overpressure protector therebetween. The overpressure protector has a closed state and an open state. The fuel tank assembly further comprises an indicator for indicating whether the overpressure protector is in the open or closed state, the indication of the indicator being able to be sensed at a location outside of the fuel tanks. The fuel tank assembly may comprise a test mechanism arranged to effect movement of the overpressure valve from the closed state to the open state, the test mechanism being operable from a location outside a fuel tank. The fuel tank assembly may comprise an overpressure valve re-set mechanism, the re-set mechanism being operable from a location outside the fuel tanks.

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Eckington, United Kingdom

Mark Christopher Smiles