290
14 CFR Ch. I (1–1–14 Edition)
§ 23.1121
(a) No hazard may result if duct rup-
ture or failure occurs anywhere be-
tween the engine port and the airplane
unit served by the bleed air.
(b) The effect on airplane and engine
performance of using maximum bleed
air must be established.
(c) Hazardous contamination of cabin
air systems may not result from fail-
ures of the engine lubricating system.
[Amdt. 23–7, 34 FR 13095, Aug. 13, 1969, as
amended by Amdt. 23–17, 41 FR 55465, Dec. 20,
1976]
E
XHAUST
S
YSTEM
§ 23.1121
General.
For powerplant and auxiliary power
unit installations, the following
apply—
(a) Each exhaust system must ensure
safe disposal of exhaust gases without
fire hazard or carbon monoxide con-
tamination in any personnel compart-
ment.
(b) Each exhaust system part with a
surface hot enough to ignite flammable
fluids or vapors must be located or
shielded so that leakage from any sys-
tem carrying flammable fluids or va-
pors will not result in a fire caused by
impingement of the fluids or vapors on
any part of the exhaust system includ-
ing shields for the exhaust system.
(c) Each exhaust system must be sep-
arated by fireproof shields from adja-
cent flammable parts of the airplane
that are outside of the engine and aux-
iliary power unit compartments.
(d) No exhaust gases may discharge
dangerously near any fuel or oil system
drain.
(e) No exhaust gases may be dis-
charged where they will cause a glare
seriously affecting pilot vision at
night.
(f) Each exhaust system component
must be ventilated to prevent points of
excessively high temperature.
(g) If significant traps exist, each
turbine engine and auxiliary power
unit exhaust system must have drains
discharging clear of the airplane, in
any normal ground and flight attitude,
to prevent fuel accumulation after the
failure of an attempted engine or auxil-
iary power unit start.
(h) Each exhaust heat exchanger
must incorporate means to prevent
blockage of the exhaust port after any
internal heat exchanger failure.
(i) For the purpose of compliance
with § 23.603, the failure of any part of
the exhaust system will be considered
to adversely affect safety.
[Doc. No. 4080, 29 FR 17955, Dec. 18, 1964, as
amended by Amdt. 23–7, 34 FR 13095, Aug. 13,
1969; Amdt. 23–18, 42 FR 15042, Mar. 17, 1977;
Amdt. 23–43, 58 FR 18974, Apr. 9, 1993; Amdt.
23–51, 61 FR 5137, Feb. 9, 1996]
§ 23.1123
Exhaust system.
(a) Each exhaust system must be fire-
proof and corrosion-resistant, and must
have means to prevent failure due to
expansion by operating temperatures.
(b) Each exhaust system must be sup-
ported to withstand the vibration and
inertia loads to which it may be sub-
jected in operation.
(c) Parts of the system connected to
components between which relative
motion could exist must have means
for flexibility.
[Doc. No. 4080, 29 FR 17955, Dec. 18, 1964, as
amended by Amdt. 23–43, 58 FR 18974, Apr. 9,
1993]
§ 23.1125
Exhaust heat exchangers.
For reciprocating engine powered air-
planes the following apply:
(a) Each exhaust heat exchanger
must be constructed and installed to
withstand the vibration, inertia, and
other loads that it may be subjected to
in normal operation. In addition—
(1) Each exchanger must be suitable
for continued operation at high tem-
peratures and resistant to corrosion
from exhaust gases;
(2) There must be means for inspec-
tion of critical parts of each exchanger;
and
(3) Each exchanger must have cooling
provisions wherever it is subject to
contact with exhaust gases.
(b) Each heat exchanger used for
heating ventilating air must be con-
structed so that exhaust gases may not
enter the ventilating air.
[Doc. No. 4080, 29 FR 17955, Dec. 18, 1964, as
amended by Amdt. 23–17, 41 FR 55465, Dec. 20,
1976]
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