(b) Each fuel system must be arranged so that—
(1) No fuel pump can draw fuel from more than one tank at a time; or
(2) There are means to prevent introducing air into the system.
(c) Each fuel system for a turbine engine must be capable of sustained operation throughout its flow and pressure range with fuel initially saturated with water at 80 °F and having 0.75cc of free water per gallon added and cooled to the most critical condition for icing likely to be encountered in operation.
(d) Each fuel system for a turbine engine powered airplane must meet the applicable fuel venting requirements of part 34 of this chapter.
[Amdt. 23–15, 39 FR 35459, Oct. 1, 1974, as amended by Amdt. 23–40, 55 FR 32861, Aug. 10, 1990; Amdt. 23–43, 58 FR 18971, Apr. 9, 1993]