(by SkySat propulsion engineer (flying LMP-103S)):
Yes it is viable and has a number of advantages, mostly the Isp * density is much better than hydrazine. But, right now the engines are more expensive to build than those running hydrazine (due to higher combustion temperature, cost of propellant not really an issue).
Really it comes down to what your mission values (cost, complexity of CONOPS, lots of flight heritage, or minimizing size).
I put a more technical comparison here