653 

Federal Aviation Administration, DOT 

§ 29.1203 

in the area protected by the fire extin-
guishing system; and 

(2) Have thermal stability over the 

temperature range likely to be experi-
enced 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 
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] 

§ 29.1199

Extinguishing agent con-

tainers. 

(a) Each extinguishing agent con-

tainer must have a pressure relief to 
prevent bursting of the container by 
excessive internal pressures. 

(b) The discharge end of each dis-

charge line from a pressure relief con-
nection must be located so that dis-
charge 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 dis-
charged or that the charging pressure 
is below the established minimum nec-
essary for proper functioning. 

(d) The temperature of each con-

tainer must be maintained, under in-
tended 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 pre-

mature 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)) 

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

§ 29.1201

Fire extinguishing system 

materials. 

(a) No materials in any fire extin-

guishing system may react chemically 
with any extinguishing agent so as to 
create a hazard. 

(b) Each system component in an en-

gine compartment must be fireproof. 

§ 29.1203

Fire detector systems. 

(a) For each turbine engine powered 

rotorcraft and Category A recipro-
cating engine powered rotorcraft, and 
for each Category B reciprocating en-
gine powered rotorcraft with engines of 
more than 900 cubic inches displace-
ment, there must be approved, quick- 
acting fire detectors in designated fire 
zones and in the combustor, turbine, 
and tailpipe sections of turbine instal-
lations (whether or not such sections 
are designated fire zones) in numbers 
and locations ensuring prompt detec-
tion of fire in those zones. 

(b) Each fire detector must be con-

structed and installed to withstand any 
vibration, inertia, and other loads to 
which it would be subjected in oper-
ation. 

(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 sys-
tem electrical circuit. 

(e) The writing and other components 

of each fire detector system in an en-
gine compartment must be at least fire 
resistant. 

(f) No fire detector system compo-

nent for any fire zone may pass 
through another fire zone, unless— 

(1) It is protected against the possi-

bility of false warnings resulting from 
fires in zones through which it passes; 
or 

(2) The zones involved are simulta-

neously protected by the same detector 
and extinguishing systems. 

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

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