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337 

Federal Aviation Administration, DOT 

§ 25.1207 

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. 

(e) If a pyrotechnic capsule is used to 

discharge the extinguishing agent, 
each container must be installed so 
that temperature conditions will not 
cause hazardous deterioration of the 
pyrotechnic capsule. 

[Doc. No. 5066, 29 FR 18291, Dec. 24, 1964, as 
amended by Amdt. 25–23, 35 FR 5678, Apr. 8, 
1970; Amdt. 25–40, 42 FR 15044, Mar. 17, 1977] 

§ 25.1201

Fire extinguishing system 

materials. 

(a) No material 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. 

§ 25.1203

Fire detector system. 

(a) There must be approved, quick 

acting fire or overheat detectors in 
each designated fire zone, and in the 
combustion, turbine, and tailpipe sec-
tions of turbine engine installations, in 
numbers and locations ensuring 
prompt detection of fire in those zones. 

(b) Each fire detector system must be 

constructed and installed so that— 

(1) It will withstand the vibration, in-

ertia, and other loads to which it may 
be subjected in operation; 

(2) There is a means to warn the crew 

in the event that the sensor or associ-
ated wiring within a designated fire 
zone is severed at one point, unless the 
system continues to function as a sat-
isfactory detection system after the 
severing; and 

(3) There is a means to warn the crew 

in the event of a short circuit in the 

sensor or associated wiring within a 
designated fire zone, unless the system 
continues to function as a satisfactory 
detection system after the short cir-
cuit. 

(c) No fire or overheat detector may 

be affected by any oil, water, other 
fluids or fumes that might be present. 

(d) There must be means to allow the 

crew to check, in flight, the func-
tioning of each fire or overheat detec-
tor electric circuit. 

(e) Components of each fire or over-

heat detector system in a fire zone 
must be fire-resistant. 

(f) No fire or overheat detector sys-

tem component for any fire zone may 
pass through another fire zone, un-
less— 

(1) It is protected against the possi-

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

(2) Each zone involved is simulta-

neously protected by the same detector 
and extinguishing system. 

(g) Each fire detector system must be 

constructed so that when it is in the 
configuration for installation it will 
not exceed the alarm activation time 
approved for the detectors using the re-
sponse time criteria specified in the ap-
propriate Technical Standard Order for 
the detector. 

(h) EWIS for each fire or overheat de-

tector system in a fire zone must meet 
the requirements of § 25.1731. 

[Doc. No. 5066, 29 FR 18291, Dec. 24, 1964, as 
amended by Amdt. 25–23, 35 FR 5678, Apr. 8, 
1970; Amdt. 25–26, 36 FR 5493, Mar. 24, 1971; 
Amdt. 25–123, 72 FR 63405, Nov. 8, 2007] 

§ 25.1207

Compliance. 

Unless otherwise specified, compli-

ance with the requirements of §§ 25.1181 
through 25.1203 must be shown by a full 
scale fire test or by one or more of the 
following methods: 

(a) Tests of similar powerplant con-

figurations; 

(b) Tests of components; 
(c) Service experience of aircraft 

with similar powerplant configura-
tions; 

(d) Analysis. 

[Amdt. 25–46, 43 FR 50598, Oct. 30, 1978] 

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