Section 29.1199

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

fluid or fluid vapors into any personnel
compartment (due to leakage during
normal operation of the rotorcraft, or
discharge on the ground or in flight) is
prevented, even though a defect may
exist in the extinguishing system.
(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. 29-12, 41 FR 55473, Dec. 20,
1976; Amdt. 29-13, 42 FR 15047, Mar. 17, 1977]

Section 29.1199 Extinguishing
tainers.

agent

con-

(a) Each extinguishing agent container must have a pressure relief to
prevent bursting of the container by
excessive internal pressures.
(b) The discharge end of each discharge line from a pressure relief connection must be located so that discharge of the fire extinguishing agent
would not damage the rotorcraft. The
line must also be located or protected
to prevent clogging caused by ice or
other foreign matter.
(c) There must be a means for each
fire extinguishing agent container to
indicate that the container has discharged or that the charging pressure
is below the established minimum necessary for proper functioning.
(d) The temperature of each container must be maintained, under intended operating conditions, to prevent
the pressure in the container from - 
(1) Falling below that necessary to
provide an adequate rate of discharge;
or
(2) Rising high enough to cause premature discharge.
(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))

Section 29.1203

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

Subpart F - Equipment

[Doc. No. 5084, 29 FR 16150, Dec. 3, 1964, as
amended by Amdt. 29-13, 42 FR 15047, Mar. 17,
1977]

GENERAL
Section 29.1301

spaschal on DSK3GDR082PROD with CFR

Section 29.1201 Fire
materials.

extinguishing

system

(a) No materials in any fire extinguishing system may react chemically
with any extinguishing agent so as to
create a hazard.
(b) Each system component in an engine compartment must be fireproof.

Fire detector systems.

(a) For each turbine engine powered
rotorcraft and Category A reciprocating engine powered rotorcraft, and
for each Category B reciprocating engine powered rotorcraft with engines of
more than 900 cubic inches displacement, there must be approved, quickacting fire detectors in designated fire
zones and in the combustor, turbine,
and tailpipe sections of turbine installations (whether or not such sections
are designated fire zones) in numbers
and locations ensuring prompt detection of fire in those zones.
(b) Each fire detector must be constructed and installed to withstand any
vibration, inertia, and other loads to
which it would be subjected in operation.
(c) No fire detector may be affected
by any oil, water, other fluids, or
fumes that might be present.
(d) There must be means to allow
crewmembers to check, in flight, the
functioning of each fire detector system electrical circuit.
(e) The writing and other components
of each fire detector system in an engine compartment must be at least fire
resistant.
(f) No fire detector system component for any fire zone may pass
through another fire zone, unless - 
(1) It is protected against the possibility of false warnings resulting from
fires in zones through which it passes;
or
(2) The zones involved are simultaneously protected by the same detector
and extinguishing systems.

Function and installation.

Each item of installed equipment
must - 
(a) Be of a kind and design appropriate to its intended function;
(b) Be labeled as to its identification,
function, or operating limitations, or
any applicable combination of these
factors;

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