Aircraft subassembly, having main-landing-gear assembly and sponson, housing main-landing-gear assembly

An aircraft subassembly that comprises a fuselage structure, comprising a first side, which comprises a first plurality of frame members, and a second side, which comprises a second plurality of frame members, the aircraft subassembly further comprising a pair of wings, attached to the fuselage structure, and a main-landing-gear system, having a single pair of wheels, consisting of a first wheel, having a first-wheel azimuthal-rotational-symmetry axis and a first-wheel mid-plane, perpendicular to the first-wheel azimuthal-rotational-symmetry axis, and a second wheel, having a second-wheel azimuthal-rotational-symmetry axis and a second-wheel mid-plane, perpendicular to the second-wheel azimuthal-rotational-symmetry axis, the main-landing-gear system additionally comprising:

• a sponson, connected to and extending outward from the fuselage structure and comprising:
• a central portion;
• a first main-landing-gear door, moveable relative to the central portion between, inclusively, a closed position and an open position;
• and
• a second main-landing-gear door, moveable relative to the central portion between, inclusively, a closed position and an open position;
• a first main-landing-gear assembly, connected to the first wheel;
• and
• a second main-landing-gear assembly, connected to the second wheel,
• wherein
• the fuselage structure further comprises:
• a cargo-bay portion, having a cargo-bay-portion cross-sectional area (CSA1);
• and
• a gear-bay portion, having a gear-bay-portion cross-sectional area (CSA2);
• the cargo-bay portion and the gear-bay portion are separated by a cargo-bay floor;
• the sponson has a sponson cross-sectional area (CSA3);
• the sponson cross-sectional area (CSA3), the cargo-bay-portion cross-sectional area (CSA1), and the gear-bay-portion cross-sectional area (CSA2) collectively form an aircraft cross-sectional area (CSA4);
• and
• the sponson cross-sectional area (CSA3) is 27.5% to 32.5% of the aircraft cross-sectional area (CSA4).