Code of Federal Regulations - Title 14

787

Federal Aviation Administration, DOT

§ 29.1013

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.

(e) The fuel jettisoning system must

be designed to comply with the power-
plant installation requirements of
§ 29.901(c).

(f) An auxiliary fuel jettisoning sys-

tem which meets the requirements of
paragraphs (a), (b), (d), and (e) of this
section may be installed to jettison ad-
ditional fuel provided it has separate
and independent controls.

[Amdt. 29–26, 53 FR 34218, Sept. 2, 1988]

YSTEM

§ 29.1011

Engines: general.

(a) Each engine must have an inde-

pendent oil system that can supply it
with an appropriate quantity of oil at a
temperature not above that safe for
continuous operation.

(b) The usable oil capacity of each

system may not be less than the prod-
uct of the endurance of the rotorcraft
under critical operating conditions and
the maximum allowable oil consump-
tion of the engine under the same con-
ditions, plus a suitable margin to en-
sure adequate circulation and cooling.
Instead of a rational analysis of endur-
ance and consumption, a usable oil ca-
pacity of one gallon for each 40 gallons
of usable fuel may be used for recipro-
cating engine installations.

prescribed in paragraph (c) of this sec-
tion may be used if they are substan-
tiated by data on the oil consumption
of the engine.

(d) The ability of the engine and oil

cooling provisions to maintain the oil
temperature at or below the maximum
established value must be shown under
the applicable requirements of §§ 29.1041
through 29.1049.

[Doc. No. 5084, 29 FR 16150, Dec. 3, 1964, as
amended by Amdt. 29–26, 53 FR 34218, Sept. 2,
1988]

§ 29.1013

Oil tanks.

(a)

Installation. Each oil tank instal-

lation must meet the requirements of
§ 29.967.

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