Not true, mad jock.
For example in a steady descent
drag = thrust + W sin (angle of descent)
So max drag will be greater than the max drag the aircraft can achieve in speed-steady, level flight.
At speeds above minimum drag speed drag increases with speed. An aircraft at maximum thrust kept level will eventually reach a steady speed, its maximum level speed at that density altitude. Drag is increasing with speed so this must also be the maximum drag the aircraft is capable of sustaining and remaining in level flight. If the nose of the aircraft is then lowered without changing the thrust, the speed will increase. This will increase drag.
If instead of lowering the nose the drag was increased by some other method, for example deployment of speed brakes, the thrust would not be sufficient to keep the aircraft at that speed in level flight. If the aircraft were kept level it would slow down until drag was again equal to thrust.
Thus the drag can only be increased beyond maximum thrust, in level flight for a transient period, this cannot be sustained.
The thrust and drag curves are drawn for sustained, level flight, so that may be the assumption for the question. Knowing JAA they may have forgotten to specify this.