I guess the engine geometry would also force the nose down if the CG got aft of center which could be an advantage.
I brought up the wing spar thing, because I had a plane that suffered from a fatigue crack due to the design of a landing gear attachment bracket of all things. It was designed so that the hydraulic actuator for the mains caused a rotational moment on the spar. Nor only that, it was multiplicative. The gear had a 500 psi actuator that was applied all the time while gear was up. That was a safe arrangement, because to drop the gear in a no hydraulic power situation, all you had to was release the pressure on the system and the gear would drop. The actuator pressure on the bracket cause about a 4 to 1 rotational moment. That would micro flex the spar at the attachment point because of the 2000+ lb torsion. A year and a half grounded and $6000 later after the manufacturer came up with a much larger bracket to divide the load so the the 500 became about 100 and I was good to fly again.