Patent ID: 8701708

Claim:
A gas supply system for an aircraft comprising: a first main line; a second main line; a plurality of ring-shaped group supply lines connected to at least one consumer each; a plurality of first connecting lines connecting the first main line to each of the plurality of group supply lines; a plurality of second connecting lines connecting the second main line to each of the plurality of group supply lines; a flow monitoring device provided between at least one of the group supply lines and one of the first main line and the second main line and configured to limit the flow if the flow exceeds a threshold value and to selectively fluidically separate the one of the first main line and the second main line from said at least one of the group supply lines in case of a leakage in said at least one of the group supply lines connected thereto; and a nonreturn valve device provided between at least one of the group supply lines and one of the first main line and the second main line and configured to permit a gas supply flow essentially only in one direction from the one of the first main line and the second main line to said at least one of the group supply lines and to selectively fluidically separate the one of the first main line and the second main line from said at least one of the group supply lines in case of a leakage in the one of the first main line and the second main line.