Hybrid Electric Propulsion (HEP) has garnered significant attention as part of the initiative to decarbonize the aviation industry by 2050. However, the ongoing development of the electrical components poses technological challenges, making the performance of these vehicles within the desired timeline uncertain. In this paper, we delve into the comparison of different vehicle architectures for hybrid electric propulsion, considering technological uncertainty. Specifically, we compare turbofan and turboprop architectures of the NASA EPFD vehicles. We apply previously established methodologies for uncertainty propagation, as discussed in our prior publication. The analysis of the turbofan vehicle builds upon previous efforts, which published results corresponding to an earlier version of the turbofan vehicle model. We provide updated uncertainty quantification results for the latest version of the turbofan vehicle model, employing the previously published framework. Additionally, for the first time, we present uncertainty quantification results for the turboprop vehicle architecture. We showcase results from each of the three approaches outlined in the previously mentioned uncertainty quantification framework. The results indicate that the benefit of hybridization of turbofan architecture is less optimistic than shown before, while the turboprop appears to be more promising. Thus, the turboprop may be better suited for hybridization using Electrified Aircraft Propulsion (EAP)