Code of Federal Regulations - Title 14

292

14 CFR Ch. I (1–1–14 Edition)

§ 23.1147

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.

[Doc. No. 4080, 29 FR 17955, Dec. 18, 1964; 30
FR 258, Jan. 9, 1965, as amended by Amdt. 23–
18, 42 FR 15042, Mar. 17, 1977; Amdt. 23–43, 58
FR 18974, Apr. 9, 1993]

§ 23.1147

Mixture controls.

(a) If there are mixture controls,

each engine must have a separate con-
trol, and each mixture control must
have guards or must be shaped or ar-
ranged to prevent confusion by feel
with other controls.

(1) The controls must be grouped and

arranged to allow—

(i) Separate control of each engine;

and

(ii) Simultaneous control of all en-

gines.

(2) The controls must require a sepa-

rate and distinct operation to move the
control toward lean or shut-off posi-
tion.

(b) For reciprocating single-engine

airplanes, each manual engine mixture
control must be designed so that, if the
control separates at the engine fuel
metering device, the airplane is capa-
ble of continued safe flight and land-
ing.

[Doc. No. 4080, 29 FR 17955, Dec. 18, 1964, as
amended by Amdt. 23–7, 34 FR 13096, Aug. 13,
1969; Amdt. 23–33, 51 FR 26657, July 24, 1986;
Amdt. 23–43, 58 FR 18974, Apr. 9, 1993]

§ 23.1149

Propeller speed and pitch

controls.

(a) If there are propeller speed or

pitch controls, they must be grouped
and arranged to allow—

(1) Separate control of each pro-

peller; and

(2) Simultaneous control of all pro-

pellers.

(b) The controls must allow ready

synchronization of all propellers on
multiengine airplanes.

§ 23.1153

Propeller feathering controls.

If there are propeller feathering con-

trols installed, it must be possible to
feather each propeller separately. Each

control must have a means to prevent
inadvertent operation.

[Doc. No. 27804, 61 FR 5138, Feb. 9, 1996]

§ 23.1155

Turbine engine reverse

thrust and propeller pitch settings
below the flight regime.

For turbine engine installations,

each control for reverse thrust and for
propeller pitch settings below the
flight regime must have means to pre-
vent its inadvertent operation. The
means must have a positive lock or
stop at the flight idle position and
must require a separate and distinct
operation by the crew to displace the
control from the flight regime (forward
thrust regime for turbojet powered air-
planes).

[Amdt. 23–7, 34 FR 13096, Aug. 13, 1969]

§ 23.1157

Carburetor air temperature

controls.

There must be a separate carburetor

air temperature control for each en-
gine.

§ 23.1163

Powerplant accessories.

(a) Each engine mounted accessory

must—

(1) Be approved for mounting on the

engine involved and use the provisions
on the engines for mounting; or

(2) Have torque limiting means on all

accessory drives in order to prevent the
torque limits established for those
drives from being exceeded; and

(3) In addition to paragraphs (a)(1) or

(a)(2) of this section, be sealed to pre-
vent contamination of the engine oil
system and the accessory system.

(b) Electrical equipment subject to

arcing or sparking must be installed to
minimize the probability of contact
with any flammable fluids or vapors
that might be present in a free state.

than 6 kilowatts must be designed and
installed to minimize the probability
of a fire hazard in the event it malfunc-
tions.

(d) If the continued rotation of any

accessory remotely driven by the en-
gine is hazardous when malfunctioning
occurs, a means to prevent rotation
without interfering with the continued
operation of the engine must be pro-
vided.

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