184
14 CFR Ch. I (1–1–14 Edition)
Pt. 23, SFAR No. 23
the leakage of fluid systems in areas other
than engine compartments, there must be
means to—
(a) Prevent the ignition of those fluids or
vapors by any other equipment; or
(b) Control any fire resulting from that ig-
nition.
E
QUIPMENT
58.
Powerplant instruments. (a) The fol-
lowing are required for turbopropeller air-
planes:
(1) The instruments required by FAR
23.1305 (a)(1) through (4), (b)(2) and (4).
(2) A gas temperature indicator for each
engine.
(3) Free air temperature indicator.
(4) A fuel flowmeter indicator for each en-
gine.
(5) Oil pressure warning means for each en-
gine.
(6) A torque indicator or adequate means
for indicating power output for each engine.
(7) Fire warning indicator for each engine.
(8) A means to indicate when the propeller
blade angle is below the low-pitch position
corresponding to idle operation in flight.
(9) A means to indicate the functioning of
the ice protection system for each engine.
(b) For turbopropeller powered airplanes,
the turbopropeller blade position indicator
must begin indicating when the blade has
moved below the flight low-pitch position.
(c) The following instruments are required
for reciprocating-engine powered airplanes:
(1) The instruments required by FAR
23.1305.
(2) A cylinder head temperature indicator
for each engine.
(3) A manifold pressure indicator for each
engine.
S
YSTEMS AND
E
QUIPMENTS
GENERAL
59.
Function and installation. The systems
and equipment of the airplane must meet the
requirements of FAR 23.1301, and the fol-
lowing:
(a) Each item of additional installed equip-
ment must—
(1) Be of a kind and design appropriate to
its intended function;
(2) Be labeled as to its identification, func-
tion, or operating limitations, or any appli-
cable combination of these factors, unless
misuse or inadvertent actuation cannot cre-
ate a hazard;
(3) Be installed according to limitations
specified for that equipment; and
(4) Function properly when installed.
(b) Systems and installations must be de-
signed to safeguard against hazards to the
aircraft in the event of their malfunction or
failure.
(c) Where an installation, the functioning
of which is necessary in showing compliance
with the applicable requirements, requires a
power supply, such installation must be con-
sidered an essential load on the power sup-
ply, and the power sources and the distribu-
tion system must be capable of supplying the
following power loads in probable operation
combinations and for probable durations:
(1) All essential loads after failure of any
prime mover, power converter, or energy
storage device.
(2) All essential loads after failure of any
one engine on two-engine airplanes.
(3) In determining the probable operating
combinations and durations of essential
loads for the power failure conditions de-
scribed in subparagraphs (1) and (2) of this
paragraph, it is permissible to assume that
the power loads are reduced in accordance
with a monitoring procedure which is con-
sistent with safety in the types of operations
authorized.
60.
Ventilation. The ventilation system of
the airplane must meet the requirements of
FAR 23.831, and in addition, for pressurized
aircraft the ventilating air in flight crew and
passenger compartments must be free of
harmful or hazardous concentrations of
gases and vapors in normal operation and in
the event of reasonably probable failures or
malfunctioning of the ventilating, heating,
pressurization, or other systems, and equip-
ment. If accumulation of hazardous quan-
tities of smoke in the cockpit area is reason-
ably probable, smoke evacuation must be
readily accomplished.
E
LECTRICAL
S
YSTEMS AND
E
QUIPMENT
61.
General. The electrical systems and
equipment of the airplane must meet the re-
quirements of FAR 23.1351, and the following:
(a)
Electrical system capacity. The required
generating capacity, and number and kinds
of power sources must—
(1) Be determined by an electrical load
analysis, and
(2) Meet the requirements of FAR 23.1301.
(b)
Generating system. The generating sys-
tem includes electrical power sources, main
power busses, transmission cables, and asso-
ciated control, regulation, and protective de-
vices. It must be designed so that—
(1) The system voltage and frequency (as
applicable) at the terminals of all essential
load equipment can be maintained within
the limits for which the equipment is de-
signed, during any probable operating condi-
tions;
(2) System transients due to switching,
fault clearing, or other causes do not make
essential loads inoperative, and do not cause
a smoke or fire hazard;
(3) There are means, accessible in flight to
appropriate crewmembers, for the individual
and collective disconnection of the electrical
power sources from the system; and
(4) There are means to indicate to appro-
priate crewmembers the generating system
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