Coupled with other CFD tools, the shallow water icing model can predict ice shapes on an aircraft flying in supercooled droplets. A lubrication assumption for the water film velocity profile approximates the runback water on surfaces. A constant film temperature T_f is assumed in the direction z, normal to the surface. The correction of the shallow water icing model to handle de-icing phenomenon is the main focus of this study. Unlike the original model, the temperature field within the ice layer T_i(t,z) is no longer assumed to be constant. Instead, a temperature profile enables the presence of a static film on the wall when a heat conduction source term from a resistance is added. If the model predicts the occurence of a static film, a temperature profile T_s(t,z) is also used. For both the solid and liquid portion of the water, transverse conduction is neglected and a 1D energy equation is resolved. An integral method and proper boundary conditions close the problem. The integral method validity deteriorates as the thickness over which vertical integration is performed increases. To avoid this problem, a multi-layer approach is proposed. The ice block thickness is then divided into three layers of identical size. The model will first be introduced, followed by a description of the numerical method. Subsequently, validation test cases will be conducted. Realistic de-icing scenarios will then be used to verify the model. Additionally, non-uniform roughness effects will be examined. This study offers a straightforward and robust method suitable for conducting industrial test cases.