title-14-part-29-sec29-1193

651

Federal Aviation Administration, DOT

§ 29.1193

(2) Arranged so that no discharged

fluid will cause an additional fire haz-
ard.

(b) Each designated fire zone must be

ventilated to prevent the accumulation
of flammable vapors.

where it would allow the entry of flam-
mable fluids, vapors, or flame from
other zones.

(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

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14 CFR Ch. I (1–1–24 Edition)

§ 29.1194

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
of the accessory section cowling sub-
ject to flame in case of fire in the en-
gine power section of the powerplant
must—

(1) Be fireproof; and
(2) Meet the requirements of § 29.1191.
(d) Each part of the cowling or engine

compartment covering subject to high
temperatures due to its nearness to ex-
haust system parts or exhaust gas im-
pingement must be fireproof.

(e) Each rotorcraft must—
(1) Be designated and constructed so

that no fire originating in any fire zone
can enter, either through openings or
by burning through external skin, any
other zone or region where it would
create additional hazards;

(2) Meet the requirements of para-

graph (e)(1) of this section with the
landing gear retracted (if applicable);
and

(3) Have fireproof skin in areas sub-

ject to flame if a fire starts in or burns
out of any designated fire zone.

(f) A means of retention for each

openable or readily removable panel,
cowling, or engine or rotor drive sys-
tem covering must be provided to pre-
clude hazardous damage to rotors or
critical control components in the
event of—

(1) Structural or mechanical failure

of the normal retention means, unless
such failure is extremely improbable;
or

(2) Fire in a fire zone, if such fire

could adversely affect the normal
means of retention.

(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. 29–3, 33 FR 970, Jan. 26,
1968; Amdt. 29–13, 42 FR 15046, Mar. 17, 1977;
Amdt. 29–26, 53 FR 34219, Sept. 2, 1988]

§ 29.1194

Other surfaces.

All surfaces aft of, and near, engine

compartments and designated fire

zones, other than tail surfaces not sub-
ject to heat, flames, or sparks ema-
nating from a designated fire zone or
engine compartment, must be at least
fire resistant.

[Amdt. 29–3, 33 FR 970, Jan. 26, 1968]

§ 29.1195

Fire extinguishing systems.

(a) Each turbine engine powered

rotorcraft and Category A recipro-
cating engine powered rotorcraft, and
each Category B reciprocating engine
powered rotorcraft with engines of
more than 1,500 cubic inches must have
a fire extinguishing system for the des-
ignated fire zones. The fire extin-
guishing system for a powerplant must
be able to simultaneously protect all
zones of the powerplant compartment
for which protection is provided.

(b) For multiengine powered rotor-

craft, the fire extinguishing system,
the quantity of extinguishing agent,
and the rate of discharge must—

(1) For each auxiliary power unit and

combustion equipment, provide at least
one adequate discharge; and

(2) For each other designated fire

zone, provide two adequate discharges.

quantity of extinguishing agent and
the rate of discharge must provide at
least one adequate discharge for the
engine compartment.

(d) It must be shown by either actual

or simulated flight tests that under
critical airflow conditions in flight the
discharge of the extinguishing agent in
each designated fire zone will provide
an agent concentration capable of ex-
tinguishing fires in that zone and of
minimizing the probability of reigni-
tion.

(Secs. 313(a), 601, 603, 604, Federal Aviation
Act of 1958 (49 U.S.C. 1354(a), 1421, 1423, 1424),
sec. 6(c), Dept. of Transportation Act (49
U.S.C. 1655(c)))

[Doc. No. 5084, 29 FR 16150, Dec. 3, 1964, as
amended by Amdt. 29–3, 33 FR 970, Jan. 26,
1968; Amdt. 29–13, 42 FR 15047, Mar. 17, 1977;
Amdt. 29–17, 43 FR 50602, Oct. 30, 1978]

§ 29.1197

Fire extinguishing agents.

(a) Fire extinguishing agents must—
(1) Be capable of extinguishing

flames emanating from any burning of
fluids or other combustible materials