296
14 CFR Ch. I (1–1–14 Edition)
§ 23.1197
(b) If an auxiliary power unit is in-
stalled in any airplane certificated to
this part, that auxiliary power unit
compartment must be served by a fire
extinguishing system meeting the re-
quirements of paragraph (a)(2) of this
section.
[Amdt. 23–34, 52 FR 1833, Jan. 15, 1987, as
amended by Amdt. 23–43, 58 FR 18975, Apr. 9,
1993; Amdt. 23–62, 76 FR 75759, Dec. 2, 2011]
§ 23.1197
Fire extinguishing agents.
For all airplanes with engine(s) em-
bedded in the fuselage or in pylons on
the aft fuselage the following applies:
(1) Be capable of extinguishing
flames emanating from any burning of
fluids or other combustible materials
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, provisions must be made to pre-
vent harmful concentrations of fluid or
fluid vapors (from leakage during nor-
mal operation of the airplane or as a
result of discharging the fire extin-
guisher on the ground or in flight) from
entering any personnel compartment,
even though a defect may exist in the
extinguishing system. This must be
shown by test except for built-in car-
bon dioxide fuselage compartment fire
extinguishing systems for which—
(1) Five pounds or less of carbon diox-
ide will be discharged, under estab-
lished fire control procedures, into any
fuselage compartment; or
(2) Protective breathing equipment is
available for each flight crewmember
on flight deck duty.
[Amdt. 23–34, 52 FR 1833, Jan. 15, 1987, as
amended by Amdt. 23–62, 76 FR 75760, Dec. 2,
2011]
§ 23.1199
Extinguishing agent con-
tainers.
For all airplanes with engine(s) em-
bedded in the fuselage or in pylons on
the aft fuselage the following applies:
(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 airplane. The
line must also be located or protected
to prevent clogging caused by ice or
other foreign matter.
(c) A means must be provided 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.
[Amdt. 23–34, 52 FR 1833, Jan. 15, 1987; 52 FR
34745, Sept. 14, 1987; Amdt. 23–62, 76 FR 75760,
Dec. 2, 2011]
§ 23.1201
Fire extinguishing systems
materials.
For all airplanes with engine(s) em-
bedded in the fuselage or in pylons on
the aft fuselage the following applies:
(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.
[Amdt. 23–34, 52 FR 1833, Jan. 15, 1987; 52 FR
7262, Mar. 9, 1987; Amdt. 23–62, 76 FR 75760,
Dec. 2, 2011]
§ 23.1203
Fire detector system.
(a) There must be means that ensure
the prompt detection of a fire in—
(1) An engine compartment of—
(i) Multiengine turbine powered air-
planes;
(ii) Multiengine reciprocating engine
powered airplanes incorporating
turbochargers;
(iii) Airplanes with engine(s) located
where they are not readily visible from
the cockpit; and
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