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14 CFR Ch. I (1–1–14 Edition) 

§ 23.1147 

(c) 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. 

[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. 

(c) Each generator rated at or more 

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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