Code of Federal Regulations - Title 14

297

Federal Aviation Administration, DOT

§ 23.1303

(iv) All commuter category air-

planes.

(2) The auxiliary power unit compart-

ment of any airplane incorporating an
auxiliary power unit.

(b) Each fire detector must be con-

structed and installed to withstand the
vibration, inertia, and other loads to
which it may be subjected in operation.

by any oil, water, other fluids, or
fumes that might be present.

(d) There must be means to allow the

crew to check, in flight, the func-
tioning of each fire detector electric
circuit.

(e) Wiring and other components of

each fire detector system in a des-
ignated fire zone must be at least fire
resistant.

[Amdt. 23–18, 42 FR 15042, Mar. 17, 1977, as
amended by Amdt. 23–34, 52 FR 1833, Jan. 15,
1987; Amdt. 23–43, 58 FR 18975, Apr. 9, 1993;
Amdt. 23–51, 61 FR 5138, Feb. 9, 1996]

Subpart F—Equipment

ENERAL

§ 23.1301

Function and installation.

Each item of installed equipment

must—

(a) Be of a kind and design appro-

priate to its intended function.

(b) Be labeled as to its identification,

function, or operating limitations, or
any applicable combination of these
factors; and

tions specified for that equipment.

[Amdt. 23–20, 42 FR 36968, July 18, 1977, as
amended by Amdt. 23–62, 76 FR 75760, Dec. 2,
2011]

§ 23.1303

Flight and navigation instru-

ments.

The following are the minimum re-

quired flight and navigation instru-
ments:

(a) An airspeed indicator.
(b) An altimeter.
(c) A magnetic direction indicator.
(d) For reciprocating engine-powered

airplanes of more than 6,000 pounds
maximum weight and turbine engine
powered airplanes, a free air tempera-
ture indicator or an air-temperature
indicator which provides indications
that are convertible to free-air.

(e) A speed warning device for—
(1) Turbine engine powered airplanes;

and

(2) Other airplanes for which V

and V

are established under

§§ 23.335(b)(4) and 23.1505(c) if V

is greater than 0.8 V

The speed warning device must give

effective aural warning (differing dis-
tinctively from aural warnings used for
other purposes) to the pilots whenever
the speed exceeds V

plus 6 knots or

+0.01. The upper limit of the pro-

duction tolerance for the warning de-
vice may not exceed the prescribed
warning speed. The lower limit of the
warning device must be set to mini-
mize nuisance warning;

(f) When an attitude display is in-

stalled, the instrument design must
not provide any means, accessible to
the flightcrew, of adjusting the relative
positions of the attitude reference sym-
bol and the horizon line beyond that
necessary for parallax correction.

(g) In addition, for commuter cat-

egory airplanes:

(1) If airspeed limitations vary with

altitude, the airspeed indicator must
have a maximum allowable airspeed in-
dicator showing the variation of V

with altitude.

(2) The altimeter must be a sensitive

type.

(3) Having a passenger seating con-

figuration of 10 or more, excluding the
pilot’s seats and that are approved for
IFR operations, a third attitude instru-
ment must be provided that:

(i) Is powered from a source inde-

pendent of the electrical generating
system;

(ii) Continues reliable operation for a

minimum of 30 minutes after total fail-
ure of the electrical generating system;

(iii) Operates independently of any

other attitude indicating system;

(iv) Is operative without selection

after total failure of the electrical gen-
erating system;

(v) Is located on the instrument

panel in a position acceptable to the
Administrator that will make it plain-
ly visible to and usable by any pilot at
the pilot’s station; and

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