Code of Federal Regulations - Title 14

264

14 CFR Ch. I (1–1–14 Edition)

§ 23.843

airplane under normal operating condi-
tions.

(2) The airplane must prevent cabin

pressure altitude from exceeding the
following after decompression from
any failure condition not shown to be
extremely improbable:

(i) Twenty-five thousand (25,000) feet

for more than 2 minutes; or

(ii) Forty thousand (40,000) feet for

any duration.

(3) Fuselage structure, engine and

system failures are to be considered in
evaluating the cabin decompression.

(4) In addition to the cabin altitude

indicating means in (b)(6) of this sec-
tion, an aural or visual signal must be
provided to warn the flight crew when
the cabin pressure altitude exceeds
10,000 feet.

(5) The sensing system and pressure

sensors necessary to meet the require-
ments of (b)(5), (b)(6), and (d)(4) of this
section and § 23.1447(e), must, in the
event of low cabin pressure, actuate
the required warning and automatic
presentation devices without any delay
that would significantly increase the
hazards resulting from decompression.

[Amdt. 23–14, 38 FR 31822, Nov. 19, 1973, as
amended by Amdt. 23–17, 41 FR 55464, Dec. 20,
1976; Amdt. 23–49, 61 FR 5167, Feb. 9, 1996;
Amdt. 23–62, 76 FR 75757, Dec. 2, 2011]

§ 23.843

Pressurization tests.

(a)

Strength test. The complete pres-

surized cabin, including doors, win-
dows, canopy, and valves, must be test-
ed as a pressure vessel for the pressure
differential specified in § 23.365(d).

(b)

Functional tests. The following

functional tests must be performed:

(1) Tests of the functioning and ca-

pacity of the positive and negative
pressure differential valves, and of the
emergency release valve, to simulate
the effects of closed regulator valves.

(2) Tests of the pressurization system

to show proper functioning under each
possible condition of pressure, tem-
perature, and moisture, up to the max-
imum altitude for which certification
is requested.

(3) Flight tests, to show the perform-

ance of the pressure supply, pressure
and flow regulators, indicators, and
warning signals, in steady and stepped
climbs and descents at rates cor-
responding to the maximum attainable

within the operating limitations of the
airplane, up to the maximum altitude
for which certification is requested.

(4) Tests of each door and emergency

exit, to show that they operate prop-
erly after being subjected to the flight
tests prescribed in paragraph (b)(3) of
this section.

IRE

ROTECTION

§ 23.851

Fire extinguishers.

(a) There must be at least one hand

fire extinguisher for use in the pilot
compartment that is located within
easy access of the pilot while seated.

(b) There must be at least one hand

fire extinguisher located conveniently
in the passenger compartment—

(1) Of each airplane accommodating

more than 6 passengers; and

(2) Of each commuter category air-

plane.

following apply:

(1) The type and quantity of each ex-

tinguishing agent used must be appro-
priate to the kinds of fire likely to
occur where that agent is to be used.

(2) Each extinguisher for use in a per-

sonnel compartment must be designed
to minimize the hazard of toxic gas
concentrations.

[Doc. No. 26269, 58 FR 42165, Aug. 6, 1993]

§ 23.853

Passenger and crew compart-

ment interiors.

For each compartment to be used by

the crew or passengers:

(a) The materials must be at least

flame-resistant;

(b) [Reserved]
(c) If smoking is to be prohibited,

there must be a placard so stating, and
if smoking is to be allowed—

(1) There must be an adequate num-

ber of self-contained, removable ash-
trays; and

(2) Where the crew compartment is

separated from the passenger compart-
ment, there must be at least one illu-
minated sign (using either letters or
symbols) notifying all passengers when
smoking is prohibited. Signs which no-
tify when smoking is prohibited must—

(i) When illuminated, be legible to

each passenger seated in the passenger
cabin under all probable lighting condi-
tions; and

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