Section 25.999

14 CFR Ch. I (1-1-19 Edition)

(b) Have a sediment trap and drain
except that it need not have a drain if
the strainer or filter is easily removable for drain purposes;
(c) Be mounted so that its weight is
not supported by the connecting lines
or by the inlet or outlet connections of
the strainer or filter itself, unless adequate strength margins under all loading conditions are provided in the lines
and connections; and
(d) Have the capacity (with respect to
operating limitations established for
the engine) to ensure that engine fuel
system functioning is not impaired,
with the fuel contaminated to a degree
(with respect to particle size and density) that is greater than that established for the engine in Part 33 of this
chapter.
[Amdt. 25-36, 39 FR 35460, Oct. 1, 1974, as
amended by Amdt. 25-57, 49 FR 6848, Feb. 23,
1984]

Section 25.999 Fuel system drains.
(a) Drainage of the fuel system must
be accomplished by the use of fuel
strainer and fuel tank sump drains.
(b) Each drain required by paragraph
(a) of this section must - 
(1) Discharge clear of all parts of the
airplane;
(2) Have manual or automatic means
for positive locking in the closed position; and
(3) Have a drain valve - 
(i) That is readily accessible and
which can be easily opened and closed;
and
(ii) That is either located or protected to prevent fuel spillage in the
event of a landing with landing gear retracted.

spaschal on DSK3GDR082PROD with CFR

[Doc. No. 5066, 29 FR 18291, Dec. 24, 1964, as
amended by Amdt. 25-38, 41 FR 55467, Dec. 20,
1976]

Section 25.1001 Fuel jettisoning system.
(a) A fuel jettisoning system must be
installed on each airplane unless it is
shown that the airplane meets the
climb requirements of SectionSection 25.119 and
25.121(d) at maximum takeoff weight,
less the actual or computed weight of
fuel necessary for a 15-minute flight
comprised of a takeoff, go-around, and
landing at the airport of departure
with the airplane configuration, speed,
power, and thrust the same as that

used in meeting the applicable takeoff,
approach, and landing climb performance requirements of this part.
(b) If a fuel jettisoning system is required it must be capable of jettisoning
enough fuel within 15 minutes, starting
with the weight given in paragraph (a)
of this section, to enable the airplane
to meet the climb requirements of
SectionSection 25.119 and 25.121(d), assuming that the
fuel is jettisoned under the conditions,
except weight, found least favorable
during the flight tests prescribed in
paragraph (c) of this section.
(c) Fuel jettisoning must be demonstrated beginning at maximum takeoff weight with flaps and landing gear
up and in - 
(1) A power-off glide at 1.3 VSR1;
(2) A climb at the one-engine inoperative best rate-of-climb speed, with the
critical engine inoperative and the remaining engines at maximum continuous power; and
(3) Level flight at 1.3 V SR1; if the results of the tests in the conditions
specified in paragraphs (c)(1) and (2) of
this section show that this condition
could be critical.
(d) During the flight tests prescribed
in paragraph (c) of this section, it must
be shown that - 
(1) The fuel jettisoning system and
its operation are free from fire hazard;
(2) The fuel discharges clear of any
part of the airplane;
(3) Fuel or fumes do not enter any
parts of the airplane; and
(4) The jettisoning operation does not
adversely affect the controllability of
the airplane.
(e) For reciprocating engine powered
airplanes, means must be provided to
prevent jettisoning the fuel in the
tanks used for takeoff and landing
below the level allowing 45 minutes
flight at 75 percent maximum continuous power. However, if there is an
auxiliary control independent of the
main jettisoning control, the system
may be designed to jettison the remaining fuel by means of the auxiliary
jettisoning control.
(f) For turbine engine powered airplanes, means must be provided to prevent jettisoning the fuel in the tanks
used for takeoff and landing below the
level allowing climb from sea level to
10,000 feet and thereafter allowing 45

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