Federal Aviation Administration, DOT

Section 29.1197

of the accessory section cowling subject to flame in case of fire in the engine power section of the powerplant
must - 
(1) Be fireproof; and
(2) Meet the requirements of Section 29.1191.
(d) Each part of the cowling or engine
compartment covering subject to high
temperatures due to its nearness to exhaust system parts or exhaust gas impingement 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 paragraph (e)(1) of this section with the
landing gear retracted (if applicable);
and
(3) Have fireproof skin in areas subject 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 system covering must be provided to preclude 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]

spaschal on DSK3GDR082PROD with CFR

Section 29.1194

Other surfaces.

All surfaces aft of, and near, engine
compartments and designated fire
zones, other than tail surfaces not subject to heat, flames, or sparks emanating from a designated fire zone or
engine compartment, must be at least
fire resistant.
[Amdt. 29-3, 33 FR 970, Jan. 26, 1968]

Section 29.1195 Fire extinguishing systems.
(a) Each turbine engine powered
rotorcraft and Category A reciprocating 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 designated fire zones. The fire extinguishing 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 rotorcraft, 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.
(c) For single engine rotorcraft, the
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 extinguishing fires in that zone and of
minimizing the probability of reignition.
(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]

Section 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
in the area protected by the fire extinguishing system; and
(2) Have thermal stability over the
temperature range likely to be experienced in the compartment in which
they are stored.
(b) If any toxic extinguishing agent is
used, it must be shown by test that
entry of harmful concentrations of

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