Abstract: 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.

Abstract: 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.

Abstract: 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.

Abstract: 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.

Abstract: A water drain tool for opening a water drain valve of an aircraft fuel tank, the tool comprising a probe and a heat source, wherein the probe is adapted to engage the valve in order to open it and the heat source is adapted to direct heat towards the valve when the valve is being opened. The valve is heated with the probe in order to melt ice formed within the valve which may otherwise impede its normal operation.

Abstract: 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.

Abstract: 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.