Structural health monitoring (SHM) of Aircraft composites is gaining prominence in the aero industry. Among the available SHM systems for Composites, usage of embedded fiber optic sensors for temperature, strain, pressure, acoustic emission, etc. is increasing due to their smaller size (~125 microns). This requires an understanding of the complex sensor architecture, type of sensing required, location of the sensor and ingress & egress of the optical fiber. This white paper describes a validated technique of optical fiber egress along with associated challenges for VARTM composite manufacturing technique. This technique could as well be applied for RTM and Prepreg manufacturing methodologies.