enter link description hereThe LOX is densified by 9.9% and the RP-1 by 2.6%. This means that if you bring both back to regular temperatures, for the same flow rates, the engines will see a different fuel ratio (producing a different amount of thrust and possibly being less stable, or a much different temperature). You will also consume different ratios of propellant than your tankage - this means you carry extra dead weight, either in unused, empty tankage or unused, surplus propellant.
Warming the propellants and retaining the same fuel ratio could require changes to propellant feed valves in the engines, the turbopump itself, and the common bulkhead location between the LOX & RP-1 tanks.
These aren't small changes, the rocket would require redesign to a hybrid of the current model and the v1.1 model. You could bring the LOX densification up to match the RP-1 densification, but you wouldn't avoid having a small window after fueling to launch - you would just change the size of that window.
These changes would cost them payload mass on regular flights and reduce the number of missions that could recover, and flying these changes on only Dragon 2 flights would mean it wasn't of a common design and SpaceX would have to expend more flights proving the design's safety and reliability, rather than simply using paid for commercial flights to prove the design.