794
14 CFR Ch. I (1–1–14 Edition)
§ 29.1105
and entering any other compartment
or area of the rotorcraft in which a
hazard would be created resulting from
the entry of hot gases. The materials
used to form the remainder of the in-
duction system duct and plenum cham-
ber of the auxiliary power unit must be
capable of resisting the maximum heat
conditions likely to occur.
(f) Each auxiliary power unit induc-
tion system duct must be constructed
of materials that will not absorb or
trap hazardous quantities of flammable
fluids that could be ignited in the
event of a surge or reverse flow condi-
tion.
(Secs. 313(a), 601, 603, 604, Federal Aviation
Act of 1958 (49 U.S.C. 1354(a), 1421, 1423, 1424),
sec. 6(c), Dept. of Transportation Act (49
U.S.C. 1655(c)))
[Doc. No. 5084, 29 FR 16150, Dec. 3, 1964, as
amended by Amdt. 29–17, 43 FR 50602, Oct. 30,
1978]
§ 29.1105
Induction system screens.
If induction system screens are
used—
(a) Each screen must be upstream of
the carburetor;
(b) No screen may be in any part of
the induction system that is the only
passage through which air can reach
the engine, unless it can be deiced by
heated air;
(c) No screen may be deiced by alco-
hol alone; and
(d) It must be impossible for fuel to
strike any screen.
§ 29.1107
Inter-coolers and after-cool-
ers.
Each inter-cooler and after-cooler
must be able to withstand the vibra-
tion, inertia, and air pressure loads to
which it would be subjected in oper-
ation.
§ 29.1109
Carburetor air cooling.
It must be shown under § 29.1043 that
each installation using two-stage su-
perchargers has means to maintain the
air temperature, at the carburetor
inlet, at or below the maximum estab-
lished value.
E
XHAUST
S
YSTEM
§ 29.1121
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 component upon which hot
exhaust gases could impinge, or that
could be subjected to high tempera-
tures from exhaust system parts, must
be fireproof. Each exhaust system com-
ponent must be separated by a fire-
proof shield from adjacent parts of the
rotorcraft that are outside the engine
and auxiliary power unit compart-
ments.
(d) No exhaust gases may discharge
so as to cause a fire hazard with re-
spect to any flammable fluid vent or
drain.
(e) No exhaust gases may discharge
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) Each exhaust shroud must be ven-
tilated or insulated to avoid, during
normal operation, a temperature high
enough to ignite any flammable fluids
or vapors outside the shroud.
(h) If significant traps exist, each
turbine engine exhaust system must
have drains discharging clear of the
rotorcraft, in any normal ground and
flight attitudes, to prevent fuel accu-
mulation after the failure of an at-
tempted engine start.
(Secs. 313(a), 601, and 603, 72 Stat. 752, 755, 49
U.S.C. 1354(a), 1421, and 1423; sec. 6(c), 49
U.S.C. 1655 (c))
[Doc. No. 5084, 29 FR 16150, Dec. 3, 1964, as
amended by Amdt. 29–3, 33 FR 970, Jan. 26,
1968; Amdt. 29–13, 42 FR 15046, Mar. 17, 1977]
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