It is true that a large proportion of thrust is produced by a pressure rise across the fan, and when the aircraft is stationary, I suppose there must be a static pressure reduction at the front surface of the fan blades, since the fan is downstream of the intake flow (clearly!)
Again correct me if I'm wrong, but:
p0 = P0 - 1/2(rho*V^2)
and
p1 = P0 + Delta P
where p is static pressure, P is total pressure, stations 0 and 1 are immediately before and after the fan, V is the air velocity through the fan, and and Delta P is the pressure loss through the bypass duct. This assumes the engine is at rest and also assumes incompressible flow.
Pressure difference would be p1 - p0. Multiply by annular fan area to get the thrust from the fan.
So you could say that the thrust from the fan is down to the static pressure reduction at the front of the engine, but I would prefer to break the thrust down into pressure differences across individual engine components, or simply consider the momentum balance across the whole engine. These are far more rhobust ways of explaining where thrust comes from.
I would recommend you get hold of a copy of "The Jet Engine" - Rolls Royce - ISBN 0 902121 2 35
Pie