Code of Federal Regulations - Title 14

480

14 CFR Ch. I (1–1–14 Edition)

§ 25.997

accelerated flight conditions are trans-
mitted to the lines attached to the
valve.

[Doc. No. 5066, 29 FR 18291, Dec. 24, 1964, as
amended by Amdt. 25–40, 42 FR 15043, Mar. 17,
1977]

§ 25.997

Fuel strainer or filter.

There must be a fuel strainer or filter

between the fuel tank outlet and the
inlet of either the fuel metering device
or an engine driven positive displace-
ment pump, whichever is nearer the
fuel tank outlet. This fuel strainer or
filter must—

(a) Be accessible for draining and

cleaning and must incorporate a screen
or element which is easily removable;

(b) Have a sediment trap and drain

except that it need not have a drain if
the strainer or filter is easily remov-
able for drain purposes;

not supported by the connecting lines
or by the inlet or outlet connections of
the strainer or filter itself, unless ade-
quate strength margins under all load-
ing 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 den-
sity) that is greater than that estab-
lished 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]

§ 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 posi-
tion; 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 pro-

tected to prevent fuel spillage in the

event of a landing with landing gear re-
tracted.

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

§ 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 §§ 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 perform-
ance requirements of this part.

(b) If a fuel jettisoning system is re-

quired 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
§§ 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.

onstrated beginning at maximum take-
off weight with flaps and landing gear
up and in—

(1) A power-off glide at 1.3 V

SR1

;

(2) A climb at the one-engine inoper-

ative best rate-of-climb speed, with the
critical engine inoperative and the re-
maining engines at maximum contin-
uous power; and

(3) Level flight at 1.3 V

SR1

; if the re-

sults 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.

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