Solid propellant ignition is a complex process with several events occurring at a very short interval of time. The external heat flux supplied by an ignition device to the propellant surface in solid rocket motor (SRM) initiates the combustion process. The processes being transient in nature, the prediction of igniter behavior and the overall performance during ignition period of SRM is a challenging engineering problem. Preliminary studies on the ignition transient are performed by locating hot spots created during impingement of pyrotechnic igniter jet on the propellant surface. A lab scale SRM and BKNO3 based pyrotechnic igniter are used in the study. Impingement locations of the igniter jet are captured using a silicon rubber sheet at the port of the motor. It is observed that the particulate matter emanating from igniter gets deposited on the propellant surface, thereby creating local hot spots for ignition. Thermal imaging of the impinged surface and subsequently X-Ray Diffraction (XRD) data are used to locate hot spots of ignition. XRD pattern peaks reveal solid particulate presence on the surface of impingement, thereby establishing the onset of hot spots on the surface. A qualitative correlation is drawn to relate the temperature and boron concentration on the impingement surface.