The present invention is a device that allows the pressure inside an aircraft landing gear shock strut to be measured. The first detection terminals each include a first plate-shaped portion having a plate shape, and a first electric wire connecting portion continuous with the first plate-shaped portion and connected to a terminal portion of an electric wire W. By grouping and hiding the unnecessary details, the tool reduces clutter in a schematic diagram and greatly eases the process of traversing, debugging, and analyzing the schematic diagram.