Section 29.995

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

subjected to axial loading must use
flexible hose assemblies.
(d) Flexible hose must be approved.
(e) No flexible hose that might be adversely affected by high temperatures
may be used where excessive temperatures will exist during operation or
after engine shutdown.
Section 29.995 Fuel valves.
In addition to meeting the requirements of Section 29.1189, each fuel valve
must - 
(a) [Reserved]
(b) Be supported so that no loads resulting from their operation or from
accelerated flight conditions are transmitted 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))

spaschal on DSK3GDR082PROD with CFR

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

Section 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 component which is susceptible to fuel contamination, including but not limited
to the fuel metering device or an engine positive displacement 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 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 inself, unless adequate strengh margins under all loading 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 components 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]

Section 29.999

Fuel system drains.

(a) There must be at least one accessible 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 service.
(b) Each drain required by paragraph
(a) of this section including the drains
prescribed in Section 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 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.
[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]

Section 29.1001

Fuel jettisoning.

If a fuel jettisoning system is installed, the following apply:
(a) Fuel jettisoning must be safe during all flight regimes for which jettisoning is to be authorized.
(b) In showing compliance with paragraph (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.
(c) Means must be provided to automatically prevent jettisoning fuel
below the level required for an all-engine climb at maximum continuous
power from sea level to 5,000 feet altitude and cruise thereafter for 30 minutes at maximum range engine power.
(d) The controls for any fuel jettisoning system must be designed to
allow flight personnel (minimum crew)
to safely interrupt fuel jettisoning during any part of the jettisoning operation.

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