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14 CFR Ch. I (1–1–19 Edition)

§ 29.1189

(d) Ventilation means must be ar-

ranged so that no discharged vapors
will cause an additional fire hazard.

(e) For category A rotorcraft, there

must be means to allow the crew to
shut off the sources of forced ventila-
tion in any fire zone (other than the
engine power section of the powerplant
compartment) unless the amount of ex-
tinguishing agent and the rate of dis-
charge are based on the maximum air-
flow through that zone.

§ 29.1189

Shutoff means.

(a) There must be means to shut off

or otherwise prevent hazardous quan-
tities of fuel, oil, de-icing fluid, and
other flammable fluids from flowing
into, within, or through any designated
fire zone, except that this means need
not be provided—

(1) For lines, fittings, and compo-

nents forming an integral part of an
engine;

(2) For oil systems for turbine engine

installations in which all components
of the system, including oil tanks, are
fireproof or located in areas not subject
to engine fire conditions; or

(3) For engine oil systems in category

B rotorcraft using reciprocating en-
gines of less than 500 cubic inches dis-
placement.

(b) The closing of any fuel shutoff

valve for any engine may not make
fuel unavailable to the remaining en-
gines.

ardous quantity of flammable fluid
may drain into any designated fire
zone after shutoff has been accom-
plished, nor may the closing of any fuel
shutoff valve for an engine make fuel
unavailable to the remaining engines.

(d) The operation of any shutoff may

not interfere with the later emergency
operation of any other equipment, such
as the means for declutching the en-
gine from the rotor drive.

(e) Each shutoff valve and its control

must be designed, located, and pro-
tected to function properly under any
condition likely to result from fire in a
designated fire zone.

(f) Except for ground-use-only auxil-

iary power unit installations, there
must be means to prevent inadvertent
operation of each shutoff and to make

it possible to reopen it in flight after it
has been closed.

[Doc. No. 5084, 29 FR 16150, Dec. 3, 1964, as
amended by Amdt. 29–12, 41 FR 55473, Dec. 20,
1976; Amdt. 29–22, 49 FR 6850, Feb. 23, 1984;
Amdt. 29–26, 53 FR 34219, Sept. 2, 1988]

§ 29.1191

Firewalls.

(a) Each engine, including the com-

bustor, turbine, and tailpipe sections of
turbine engine installations, must be
isolated by a firewall, shroud, or equiv-
alent means, from personnel compart-
ments, structures, controls, rotor
mechanisms, and other parts that are—

(1) Essential to controlled flight and

landing; and

(2) Not protected under § 29.861.
(b) Each auxiliary power unit, com-

bustion heater, and other combustion
equipment to be used in flight, must be
isolated from the rest of the rotorcraft
by firewalls, shrouds, or equivalent
means.

constructed so that no hazardous quan-
tity of air, fluid, or flame can pass
from any engine compartment to other
parts of the rotorcraft.

(d) Each opening in the firewall or

shroud must be sealed with close-fit-
ting fireproof grommets, bushings, or
firewall fittings.

(e) Each firewall and shroud must be

fireproof and protected against corro-
sion.

(f) In meeting this section, account

must be taken of the probable path of
a fire as affected by the airflow in nor-
mal flight and in autorotation.

[Doc. No. 5084, 29 FR 16150, Dec. 3, 1964, as
amended by Amdt. 29–3, 33 FR 970, Jan. 26,
1968]

§ 29.1193

Cowling and engine compart-

ment covering.

(a) Each cowling and engine compart-

ment covering must be constructed and
supported so that it can resist the vi-
bration, inertia, and air loads to which
it may be subjected in operation.

(b) Cowling must meet the drainage

and ventilation requirements of
§ 29.1187.

isolating the engine power section from
the engine accessory section, each part

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