By what angle does the rotor disc change with max. cyclic input?
Assuming you mean, in-flight, it depends on the main rotor design. A fully articulated head can allow for angles great enough for an H53 to chop-off it's own refueling boom (See Here: https://www.bing.com/videos/search?q=h53+chop+fueling+boom&amp;qpvt=h53+chop+fueling+boom&amp;view=detail&amp;mid=1AD065C255D15A52813F1AD065C255D15A52813F&amp;&amp;FORM=VRDGAR ).

Helicopter designs employing non-articulated rotor systems often have a cockpit indicator for "Mast Moment" in order to alert the pilot that excessive cyclic input is being commanded, risking Rotor/Head/Mast failure. These types require the blades themselves to absorb most or all of the rotor's dynamic articulation forces, hence much less angular deflection of the disc.

Additionally, the duration of the deflection needs to be factored-in. During maintenance test flights of the old UH-1 Huey, a "Pylon Rock Check" is performed. From an IGE hover an instantaneous full deflection and return to neutral (less than 1 sec for the full maneuver) is conducted either left or right. Somewhat violent and not something you would want to do every day for the sake of the transmission mounts. Sorry I can't provide exact disc angles though.