The XB-70 had a large number of fuel transfer pumps (something like 25) to transfer fuel from the 10 other tanks into the sump tank, and then three fuel "boost" pumps to pump it from that to the engines. These were hydraulically driven pumps. I.e. it was the hydraulic pressure in the corresponding hydraulic system that caused such a fuel pump to do its work. How common was that back in the days? Do such pumps exist on any current aircraft?
Not common in commercial aircraft.
For this comparative analysis I used a DOT/FAA study titled Commercial Aircraft Airframe Fuel Systems Survey and Analysis by P. G. Weitz.
Searching the whole document, I found only one other aircraft with hydraulically-driven fuel pumps; of 32 fuel pumps, two were hydraulically-driven on Concorde.
Thirty electrically driven centrifugal pumps and 2 hydraulically driven centrifugal pumps are supplied. Twelve of these run continuously and up to 18 are running during portions of the flight. The pumps have flow ratings of 2000 gal/hr to 12,000 gal/hr. No ejector pumps are used on this aircraft. [Weitz, p. 5-7]
Checking Concorde's flight manual, both pumps were transfer pumps in the aft tank (no. 11), and each was powered by a different hydraulic system; they were alongside two electrically-driven pumps for a total of four in tank 11.
The flight manual does not explain the reasoning, but another question here may shed some light on it: Could the Olympus 593 have been windmill-restarted during supersonic flight?
In an all-engine flame-out in supersonic flight, hydraulic-driven emergency power generation is used, and fuel is pumped forward from tank 11 to counteract the ensuing forward shift of lift as the plane goes subsonic. Since the engines will be windmilling, the IDGs may not provide the needed electrical output, whereas hydraulic pressure from at least the stored pressure in the hydraulic reservoirs will help provide the remaining necessary pumping power, at least until subsonic CG-trim is achieved for a worst-case scenario of gliding with no re-light.
Subsonic airplanes do not have this critical requirement of pumping fuel forward, which may explain why they are not common.
Not common, no:
The pumps mentioned in OP are fuel transfer pumps, necessary for the shift of Mean Aerodynamic Centre in supersonic flight. Subsonic aeroplanes do not require fuel transfer in longitudinal direction.1
A hydraulically driven fuel pump is subject to failures in the pump itself, plus failures in the hydraulic system driving it: leaks, dirty filters, burst pipes etc. Meaning an exponential increase in chance of failure of the hydraulically driven fuel pump.
So no, hydraulically driven fuel transfer pumps are not common. By way of comparison: the B737 has fuel pumps that are mechanically driven by the engines, plus AC driven electric pumps and gravity transfer to the centre tank as a backup option.
1 The A380 has a fuel trim tank in the horizontal stabiliser, if the transfer pumps fail fuel can be transferred back into the main tank via gravity.