title-14-part-27-sec27-1185

544

14 CFR Ch. I (1–1–24 Edition)

§ 27.1145

Ignition switches.

(a) There must be means to quickly

shut off all ignition by the grouping of
switches or by a master ignition con-
trol.

(b) Each group of ignition switches,

except ignition switches for turbine en-
gines for which continuous ignition is
not required, and each master ignition
control must have a means to prevent
its inadvertent operation.

(Secs. 313(a), 601, and 603, 72 Stat. 752, 775, 49
U.S.C. 1354(a), 1421, and 1423; sec. 6(c), 49
U.S.C. 1655(c))

[Doc. No. 5074, 29 FR 15695, Nov. 24, 1964, as
amended by Amdt. 27–12, 42 FR 15045, Mar. 17,
1977]

§ 27.1147

Mixture controls.

If there are mixture controls, each

engine must have a separate control
and the controls must be arranged to
allow—

(a) Separate control of each engine;

and

(b) Simultaneous control of all en-

gines.

§ 27.1151

Rotor brake controls.

(a) It must be impossible to apply the

rotor brake inadvertently in flight.

(b) There must be means to warn the

crew if the rotor brake has not been
completely released before takeoff.

[Doc. No. 28008, 61 FR 21907, May 10, 1996]

§ 27.1163

Powerplant accessories.

(a) Each engine-mounted accessory

must—

(1) Be approved for mounting on the

engine involved;

(2) Use the provisions on the engine

for mounting; and

(3) Be sealed in such a way as to pre-

vent contamination of the engine oil
system and the accessory system.

(b) Unless other means are provided,

torque limiting means must be pro-
vided for accessory drives located on
any component of the transmission and
rotor drive system to prevent damage
to these components from excessive ac-
cessory load.

[Amdt. 27–2, 33 FR 964, Jan. 26, 1968, as
amended by Amdt. 27–20, 49 FR 6849, Feb. 23,
1984; Amdt. 27–23, 53 FR 34214, Sept. 2, 1988]

OWERPLANT

IRE

ROTECTION

§ 27.1183

Lines, fittings, and compo-

nents.

(a) Except as provided in paragraph

(b) of this section, each line, fitting,
and other component carrying flam-
mable fluid in any area subject to en-
gine fire conditions must be fire resist-
ant, except that flammable fluid tanks
and supports which are part of and at-
tached to the engine must be fireproof
or be enclosed by a fireproof shield un-
less damage by fire to any non-fire-
proof part will not cause leakage or
spillage of flammable fluid. Compo-
nents must be shielded or located so as
to safeguard against the ignition of
leaking flammable fluid. An integral
oil sump of less than 25-quart capacity
on a reciprocating engine need not be
fireproof nor be enclosed by a fireproof
shield.

(b) Paragraph (a) does not apply to—
(1) Lines, fittings, and components

which are already approved as part of a
type certificated engine; and

(2) Vent and drain lines, and their fit-

tings, whose failure will not result in,
or add to, a fire hazard.

vent must discharge clear of the induc-
tion system air inlet.

[Doc. No. 5074, 29 FR 15695, Nov. 24, 1964, as
amended by Amdt. 27–1, 32 FR 6914, May 5,
1967; Amdt. 27–9, 39 FR 35462, Oct. 1, 1974;
Amdt. 27–20, 49 FR 6849, Feb. 23, 1984]

§ 27.1185

Flammable fluids.

(a) Each fuel tank must be isolated

from the engines by a firewall or
shroud.

(b) Each tank or reservoir, other

than a fuel tank, that is part of a sys-
tem containing flammable fluids or
gases must be isolated from the engine
by a firewall or shroud, unless the de-
sign of the system, the materials used
in the tank and its supports, the shut-
off means, and the connections, lines
and controls provide a degree of safety
equal to that which would exist if the
tank or reservoir were isolated from
the engines.

inch of clear airspace between each
tank and each firewall or shroud iso-
lating that tank, unless equivalent

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§ 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.

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.

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.

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.