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14 CFR Ch. I (1–1–19 Edition)

§ 29.995

subjected to axial loading must use
flexible hose assemblies.

(d) Flexible hose must be approved.
(e) No flexible hose that might be ad-

versely affected by high temperatures
may be used where excessive tempera-
tures will exist during operation or
after engine shutdown.

§ 29.995

Fuel valves.

In addition to meeting the require-

ments of § 29.1189, each fuel valve
must—

(a) [Reserved]
(b) Be supported so that no loads re-

sulting from their operation or from
accelerated flight conditions are trans-
mitted to the lines attached to the
valve.

(Secs. 313(a), 601, and 603, 72 Stat. 759, 775, 49
U.S.C. 1354(a), 1421, and 1423; sec. 6(c), 49
U.S.C. 1655 (c))

[Doc. No. 5084, 29 FR 16150, Dec. 3, 1964, as
amended by Amdt. 29–13, 42 FR 15046, Mar. 17,
1977]

§ 29.997

Fuel strainer or filter.

There must be a fuel strainer or filter

between the fuel tank outlet and the
inlet of the first fuel system compo-
nent which is susceptible to fuel con-
tamination, including but not limited
to the fuel metering device or an en-
gine positive displacement pump,
whichever is nearer the fuel tank out-
let. 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 inself, unless ade-
quate strengh margins under all load-
ing conditions are provided in the lines
and connections; and

(d) Provide a means to remove from

the fuel any contaminant which would
jeopardize the flow of fuel through
rotorcraft or engine fuel system com-
ponents required for proper rotorcraft
or engine fuel system operation.

[Amdt. 29–10, 39 FR 35462, Oct. 1, 1974, as
amended by Amdt. 29–22, 49 FR 6850, Feb. 23,
1984; Amdt. 29–26, 53 FR 34217, Sept. 2, 1988]

§ 29.999

Fuel system drains.

(a) There must be at least one acces-

sible drain at the lowest point in each
fuel system to completely drain the
system with the rotorcraft in any
ground attitude to be expected in serv-
ice.

(b) Each drain required by paragraph

(a) of this section including the drains
prescribed in § 29.971 must—

(1) Discharge clear of all parts of the

rotorcraft;

(2) Have manual or automatic means

to ensure positive closure in the off po-
sition; 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. 5084, 29 FR 16150, Dec. 3, 1964, as
amended by Amdt. 29–12, 41 FR 55473, Dec. 20,
1976; Amdt. 29–26, 53 FR 34218, Sept. 2, 1988]

§ 29.1001

Fuel jettisoning.

If a fuel jettisoning system is in-

stalled, the following apply:

(a) Fuel jettisoning must be safe dur-

ing all flight regimes for which jetti-
soning is to be authorized.

(b) In showing compliance with para-

graph (a) of this section, it must be
shown that—

(1) The fuel jettisoning system and

its operation are free from fire hazard;

(2) No hazard results from fuel or fuel

vapors which impinge on any part of
the rotorcraft during fuel jettisoning;
and

(3) Controllability of the rotorcraft

remains satisfactory throughout the
fuel jettisoning operation.

matically prevent jettisoning fuel
below the level required for an all-en-
gine climb at maximum continuous
power from sea level to 5,000 feet alti-
tude and cruise thereafter for 30 min-
utes at maximum range engine power.

(d) The controls for any fuel jetti-

soning system must be designed to
allow flight personnel (minimum crew)
to safely interrupt fuel jettisoning dur-
ing any part of the jettisoning oper-
ation.

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