Sec. 23.951 - General.
(a) Each fuel system must be constructed
and arranged to ensure fuel flow at a rate and pressure established for
proper engine and auxiliary power unit functioning under each likely
operating condition, including any maneuver for which certification is
requested and during which the engine or auxiliary power unit is permitted
to be in operation.
(b) Each fuel system must be arranged so
(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]