Bismuth has received considerable attention recently as a propellant option for more advanced, next-generation Hall thrusters. A bismuth-fueled Hall thruster would possess advantages over conventional xenon thrusters in terms of efficiency, power-handling, and simplicity of ground testing facilities. In developing such a thruster, there is a need for nonintrusive diagnostic methods for taking the necessary measurements to optimize the geometry and operating conditions. A previous paper discussed such optical diagnostic methods for analyzing the velocity, energy, and number densities of BiI and BiII in the plume. Additionally, candidate transitions for measurement were selected and their lineshapes modeled in terms of hyperfine splitting and broadening mechanisms. In this paper, after a brief summary of the previous work, the line selections will be revised for improved accessibility to commercial tunable diode lasers. A lineshape model that more closely relates to Hall thruster measurements will also be discussed. Finally, the development of laboratory systems for taking measurements on a Bi gas will be discussed, and measurements of the Bi spectrum will be presented.