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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