I'm asking for the design loadings, such as the 7.33g limits for the P-51H. Was the F-82 designed for similar loadings in flight?
From the respective manuals, Service G limits at Normal takeoff weight, no external load-
F-51D, +7.33, -3
F-51H, +7.33, -3
F-82E +7.33, -3
Normal and Maximum Takeoff Weights
F-51D 9000# Normal, 12300# Max
F-51H 8810# Normal, 12600# Max
F-82E 21000# Normal, 24400# Max
As a comparison with the last of the lightweight P-51s, the XP-51J's Normal Takeoff Weight was 7500#, Max 9000#
The P-51H/F-61H wasn't so much a lightened P-51D, as a "Lessons Learned" airplane taking advantage of NACA tests on improving directional stability and using newer Aluminum alloys.
While there may be some superficial resemblance of the F-82 to a P-51H, there is nothing in common other than the general shape.
The -82 is much larger, as you can see, it's more than twice as heavy, and the internal structure of the entire airplane is different -
The F-82 has Hydraulically boosted controls, hot air de-icing to all control surfaces, an autopilot, and, it must e noted, each main gear leg takes the load of an entire F-51D.
SInce I've the data available, I decided to look into the claim that the F-51H has a weaker landing gear, relative to the F-51D.
Out of 1434 incidents (Damage of all types) for the F-51D, 122 are related to landing gear mishaps, or 8.5%
Out of 470 incidents, same criteria, for the F-51H, 11 were related to landing gear mishaps, or 2.3%