Code of Federal Regulations - Title 14

293

Federal Aviation Administration, DOT

§ 23.1183

(e) Each accessory driven by a gear-

box that is not approved as part of the
powerplant driving the gearbox must—

(1) Have torque limiting means to

prevent the torque limits established
for the affected drive from being ex-
ceeded;

(2) Use the provisions on the gearbox

for mounting; and

(3) Be sealed to prevent contamina-

tion of the gearbox oil system and the
accessory system.

[Doc. No. 4080, 29 FR 17955, Dec. 18, 1964, as
amended by Amdt. 23–14, 38 FR 31823, Nov. 19,
1973; Amdt. 23–29, 49 FR 6847, Feb. 23, 1984;
Amdt. 23–34, 52 FR 1832, Jan. 15, 1987; Amdt.
23–42, 56 FR 354, Jan. 3, 1991]

§ 23.1165

Engine ignition systems.

(a) Each battery ignition system

must be supplemented by a generator
that is automatically available as an
alternate source of electrical energy to
allow continued engine operation if
any battery becomes depleted.

(b) The capacity of batteries and gen-

erators must be large enough to meet
the simultaneous demands of the en-
gine ignition system and the greatest
demands of any electrical system com-
ponents that draw from the same
source.

system must account for—

(1) The condition of an inoperative

generator;

(2) The condition of a completely de-

pleted battery with the generator run-
ning at its normal operating speed; and

(3) The condition of a completely de-

pleted battery with the generator oper-
ating at idling speed, if there is only
one battery.

(d) There must be means to warn ap-

propriate crewmembers if malfunc-
tioning of any part of the electrical
system is causing the continuous dis-
charge of any battery used for engine
ignition.

(e) Each turbine engine ignition sys-

tem must be independent of any elec-
trical circuit that is not used for as-
sisting, controlling, or analyzing the
operation of that system.

(f) In addition, for commuter cat-

egory airplanes, each turbine engine ig-

nition system must be an essential
electrical load.

[Doc. No. 4080, 29 FR 17955, Dec. 18, 1964, as
amended by Amdt. 23–17, 41 FR 55465 Dec. 20,
1976; Amdt. 23–34, 52 FR 1833, Jan. 15, 1987;
Amdt. 23–62, 76 FR 75759, Dec. 2, 2011]

OWERPLANT

IRE

ROTECTION

§ 23.1181

Designated fire zones; re-

gions included.

Designated fire zones are—
(a) For reciprocating engines—
(1) The power section;
(2) The accessory section;
(3) Any complete powerplant com-

partment in which there is no isolation
between the power section and the ac-
cessory section.

(b) For turbine engines—
(1) The compressor and accessory sec-

tions;

(2) The combustor, turbine and tail-

pipe sections that contain lines or com-
ponents carrying flammable fluids or
gases.

(3) Any complete powerplant com-

partment in which there is no isolation
between compressor, accessory, com-
bustor, turbine, and tailpipe sections.

partment; and

(d) Any fuel-burning heater, and

other combustion equipment installa-
tion described in § 23.859.

[Doc. No. 26344, 58 FR 18975, Apr. 9, 1993, as
amended by Amdt. 23–51, 61 FR 5138, Feb. 9,
1996]

§ 23.1182

Nacelle areas behind fire-

walls.

Components, lines, and fittings, ex-

cept those subject to the provisions of
§ 23.1351(e), located behind the engine-
compartment firewall must be con-
structed of such materials and located
at such distances from the firewall
that they will not suffer damage suffi-
cient to endanger the airplane if a por-
tion of the engine side of the firewall is
subjected to a flame temperature of
not less than 2000

F for 15 minutes.

[Amdt. 23–14, 38 FR 31816, Nov. 19, 1973]

§ 23.1183

Lines, fittings, and compo-

nents.

(a) Except as provided in paragraph

(b) of this section, each component,
line, and fitting carrying flammable

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