An analysis of the main directions of the development of military transport aircraft (MTА) showed that, as applied to light military vehicles, a tendency to increase their carrying capacity in a narrow range corridor was revealed. The required increase in carrying capacity inevitably entails an increase in the starting mass of modifications, which leads to a deterioration in take-off and landing characteristics, and acts as a serious limitation, especially for light military-technical complexes, according to their conditions of basing. The solution of such problematic problems can be carried out using profound modification changes in the system of load-bearing surfaces of the modification, and also in its power plant, the scientific basis for the coordination of which is based on three principles: continuous growth of performance modifications; geometric rearrangement of the wing, taking into account its ellipticity coefficient; coordination of the parameters of the power plant with an increased load capacity of the modification and with the modified geometry of its wing. The development of such models is based on the use of the weight balance equation, taking into account the fact that the components of the starting mass are not statistically determined, but there are functions of target parameters, such as load capacity, range, speed characteristics, parameters of marching engines, etc. Taking into account restrictions on take-off weight, load capacity, take-off length, etc., models were obtained for evaluating the “load-range” characteristics of light military-transport vehicles, as well as the take-off value for one engine that failed. The performance assessment of the obtained models was tested on modifications of the domestic An-26, An-32, and An-32B aircraft by evaluating their “load-range” characteristics when replacing their marching engines with increased power. An analysis of these dependencies showed that the process of matching the wing parameters and changes in the power plant (with the same external contours) leads to a significant increase in carrying capacity, and hence, flight performance. An analysis of the comparative assessment of the parameters of the basic version of the An-26 with its modifications An-32 and An-32B also revealed that the matching models obtained in the work allow already at the stage of preliminary designing more productive modifications to form their main parameters that meet the requirements of the customer.