545
Federal Aviation Administration, DOT
§ 27.1193
means are used to prevent heat trans-
fer from each engine compartment to
the flammable fluid.
(d) Absorbent materials close to
flammable fluid system components
that might leak must be covered or
treated to prevent the absorption of
hazardous quantities of fluids.
[Doc. No. 5074, 29 FR 15695, Nov. 24, 1964, as
amended by Amdt. 27–2, 33 FR 964, Jan. 26,
1968; Amdt. 27–11, 41 FR 55470, Dec. 20, 1976;
Amdt. 27–37, 64 FR 45095, Aug. 18, 1999]
§ 27.1187
Ventilation and drainage.
Each compartment containing any
part of the powerplant installation
must have provision for ventilation
and drainage of flammable fluids. The
drainage means must be—
(a) Effective under conditions ex-
pected to prevail when drainage is
needed, and
(b) Arranged so that no discharged
fluid will cause an additional fire haz-
ard.
[Doc. No. 29247, 64 FR 45095, Aug. 18, 1999]
§ 27.1189
Shutoff means.
(a) There must be means to shut off
each line carrying flammable fluids
into the engine compartment, except—
(1) Lines, fittings, and components
forming an intergral part of an engine;
(2) For oil systems for which all com-
ponents of the system, including oil
tanks, are fireproof or located in areas
not subject to engine fire conditions;
and
(3) For reciprocating engine installa-
tions only, engine oil system lines in
installation using engines of less than
500 cu. in. displacement.
(b) There must be means to guard
against inadvertent operation of each
shutoff, and to make it possible for the
crew to reopen it in flight after it has
been closed.
(c) Each shutoff valve and its control
must be designed, located, and pro-
tected to function properly under any
condition likely to result from an en-
gine fire.
[Doc. No. 5074, 29 FR 15695, Nov. 24, 1964, as
amended by Amdt. 27–2, 33 FR 964, Jan. 26,
1968; Amdt. 27–20, 49 FR 6850, Feb. 23, 1984;
Amdt. 27–23, 53 FR 34214, Sept. 2, 1988]
§ 27.1191
Firewalls.
(a) Each engine, including the com-
bustor, turbine, and tailpipe sections of
turbine engines must be isolated by a
firewall, shroud, or equivalent means,
from personnel compartments, struc-
tures, controls, rotor mechanisms, and
other parts that are—
(1) Essential to a controlled landing:
and
(2) Not protected under § 27.861.
(b) Each auxiliary power unit and
combustion heater, and any other com-
bustion equipment to be used in flight,
must be isolated from the rest of the
rotorcraft by firewalls, shrouds, or
equivalent means.
(c) In meeting paragraphs (a) and (b)
of this section, account must be taken
of the probable path of a fire as af-
fected by the airflow in normal flight
and in autorotation.
(d) Each firewall and shroud must be
constructed so that no hazardous quan-
tity of air, fluids, or flame can pass
from any engine compartment to other
parts of the rotorcraft.
(e) Each opening in the firewall or
shroud must be sealed with close-fit-
ting, fireproof grommets, bushings, or
firewall fittings.
(f) Each firewall and shroud must be
fireproof and protected against corro-
sion.
[Doc. No. 5074, 29 FR 15695, Nov. 24, 1964, as
amended by Amdt. 27–2, 22 FR 964, Jan. 26,
1968]
§ 27.1193
Cowling and engine compart-
ment covering.
(a) Each cowling and engine compart-
ment covering must be constructed and
supported so that it can resist the vi-
bration, inertia, and air loads to which
it may be subjected in operation.
(b) There must be means for rapid
and complete drainage of each part of
the cowling or engine compartment in
the normal ground and flight attitudes.
(c) No drain may discharge where it
might cause a fire hazard.
(d) Each cowling and engine compart-
ment covering must be at least fire re-
sistant.
(e) Each part of the cowling or engine
compartment covering subject to high
temperatures due to its nearness to ex-
haust system parts or exhaust gas im-
pingement must be fireproof.
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