FWIW
The P-61A-1 & A-5 used the same engines as the F6F and would have had the same limits, which was 2550 rpm (I think) in service at the higher altitude.
My understanding is that the limit on the P-61A-10's R-2800-65W engine output at the higher altitude was the IHP (Indicated Horse Power) that would have been generated at 2700 rpm, said IHP being proportional to the stresses generated inside the engine on the pistons, crankshaft, supercharger, etc.
As an example, when the Merlin XX was putting out 1440 BHP with +16 lbs boost at 11,000 ft in high gear, but the engine was generating 1750 IHP, with about 300 HP being absorbed by the supercharger.
In low gear the Merlin XX's respective BHP/IHP was 1470/1700 at +14 lbs boost at 6,750 ft, with about 215 HP being absorbed by the supercharger..
This limit with the Merlin XX-23 resulted in the Merlin 24/25. As note above, the Merlin XX-23 at 1440-1470 BHP were limited by the internal stresses to about 1750 IHP using 130 grade, and while switching to 150 grade reduced the chance and frequency of detonation at that output, increasing the BHP/IHP caused various mechanical breakage issues. After various strength mods the Merlin 24/25 could reliably handle upto 1640 BHP at +18 lbs boost with 130 grade, and upto 1800 BHP at +25 lbs boost using 150 grade without blowing up right away. At +25 lbs boost the Merlin 24/25 was putting out 1790 BHP at 3,750 ft in high gear, with about 2170 IHP - the supercharger absorbing around 370 HP.
I think most of the Merlin 24/24 strength mods were incorporated in some of the Merlin 60 series and later as well.
I think this is correct.

