When coming in to land you can see the tail rotor below the gearbox has significant pitch. The blade is advancing towards the nose and pushing the tail right, nose left. This is being commanded by the pilot.
As they lose airspeed and the vertical fin stops working, the pilot realises they have insufficient ant-torque and tries to abort.
This idea fits which what I opine... During a fast flyby, the tail rotor is not working hard (if at all), so a not connected pitch link would not be noticed. Slowing for the approach is the point at which the loss of tail rotor effect could be noticed. The tail rotor blades appear to have very different pitches in a couple of the video frames. The blade with the large pitch angle would be the connected blade, with the pilot applying large pedal displacement, which the blade which appears to have no pitch could be trailing in flat pitch. The tail rotor gearbox and hub probably would not tolerate this asymmetrical loading well, so a failing tailrotor blade seems plausible.
I've only flown the 222 once, and it was a very long time ago, so my recollection is poor. But I did do extensive testing many years ago on a 206, and 206L for the airspeed at which the fin no longer has a directional stabilizing effect. For both types it was around 21-22 MIAS. Prior to that airspeed, a very slight yaw, which might even go un noticed. At that speed, as though the fin just suddenly stalled, the swing began pretty quickly.