To solve potential problems of electromagnetic coupling between electronic devices under space launcher's fairing, a study has been performed to verify the applicability of the Power Balance Method (PWB). The diversity of configurations which depends on satellites and volumes in the upper stage required to define a modelling method and to assess the limits of validity. Works to verify the applicability of the PWB have been already achieved. This paper presents works realized to identify limits of validity of the model by a progressive simplification of cavities. In this paper, theoretical approach is introduced and steps of experimentation are showed.