I understand that the F1 rocket engine had (approximately) 1428 Oxidizer holes and (approximately) 1404 Fuel (RP1) holes in the injector plate. Since the Oxidizer to fuel ratio was 2.27:1 for the F1 engine, why the propellant holes were not in similar proportion?
There are different numbers on this NASA page about Saturn V:
Finally, the fuel squirted through 3 700 orifices into the combustion chamber to mix with the oxidizer, which entered through 2 600 other orifices in the injector face
If the hole numbers of the question are correct, (1428 Oxidizer holes and (approximately) 1404 Fuel (RP1) holes) the explanation from the heroicrelics page may be true.
The "self-impinging stream pattern" was chosen, see right image, not the "doublet impinging stream pattern", see left image.
The like-on-unlike pattern was rejected and the like-on-like pattern was used.
So a pair of fuel orifices were alternated with a pair of oxidizer orifices. To allow good mixing the numbers of each kind of pairs should be equal or at least very close.
The different numbers may be from different injector design versions. We need to know the numbers for the flight ready injector.