Release as little debris as possible into the GSO region during placement; shorten the lifetime of debris in transfer orbits with apogee near GSO; before propellant is exhausted, remove a geostationary satellite at end of life from the GSO region so that, under perturbations, its perigee stays at least 200 km above geostationary altitude (minimum re-orbit altitude of 235 km plus 1 000 times Cr times A/M, for eccentricity below 0.003); and perform the transfer to the graveyard orbit carefully so that it does not cause RF interference to satellites still in service (recommends 1 to 4). Annex 1 advises monitoring propellant with a margin, raising the perigee in multiple manoeuvres, using remaining propellant and passivating stored energy (batteries, pressurants) afterwards.
The graph holds this control, the 0 it maps to, and the evidence behind each claim, over MCP and REST.