EASA
CS 27.695 a and b Certification Specifications for Small Rotorcraft only talk about either 'alternative means' and the need to have control in case of engine or component failure, or at least be manually operable.
So why all the BS about the single hydraulic system? I doubt having one extra place in the chopper as per FAA certification/POH is makes it different. Also, I don't see any differentiation between small helicopter with turbine and small helicopter with piston engine.
Edit: Took me few mins to find it. Those who fancy reading it. It's buried in the EASA website.
CS-27