title-14-part-29-sec29-1125

647

Federal Aviation Administration, DOT

§ 29.1125

XHAUST

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.

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]

§ 29.1123

Exhaust piping.

(a) Exhaust piping must be heat and

corrosion resistant, and must have pro-
visions to prevent failure due to expan-
sion by operating temperatures.

(b) Exhaust piping must be supported

to withstand any vibration and inertia
loads to which it would be subjected in
operation.

ponents between which relative motion
could exist must have provisions for
flexibility.

§ 29.1125

Exhaust heat exchangers.

For reciprocating engine powered

rotorcraft the following apply:

(a) Each exhaust heat exchanger

must be constructed and installed to
withstand the vibration, inertia, and
other loads to which it would be sub-
jected in 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 inspect-

ing the critical parts of each ex-
changer;

(3) Each exchanger must have cooling

provisions wherever it is subject to
contact with exhaust gases; and

(4) No exhaust heat exchanger or

muff may have stagnant areas or liquid
traps that would increase the prob-
ability of ignition of flammable fluids
or vapors that might be present in case
of the failure or malfunction of compo-
nents carrying flammable fluids.

(b) If an exhaust heat exchanger is

used for heating ventilating air used by
personnel—

(1) There must be a secondary heat

exchanger between the primary ex-
haust gas heat exchanger and the ven-
tilating air system; or

(2) Other means must be used to pre-

vent harmful contamination of the
ventilating air.

[Doc. No. 5084, 29 FR 16150, Dec. 3, 1964, as
amended by Amdt. 29–12, 41 FR 55473, Dec. 20,
1976; Amdt. 29–41, 62 FR 46173, Aug. 29, 1997]

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648

14 CFR Ch. I (1–1–24 Edition)

§ 29.1141

OWERPLANT

ONTROLS AND

CCESSORIES

§ 29.1141

Powerplant controls: general.

(a) Powerplant controls must be lo-

cated and arranged under § 29.777 and
marked under § 29.1555.

(b) Each control must be located so

that it cannot be inadvertently oper-
ated by persons entering, leaving, or
moving normally in the cockpit.

must be approved.

(d) Each control must be able to

maintain any set position without—

(1) Constant attention; or
(2) Tendency to creep due to control

loads or vibration.

(e) Each control must be able to

withstand operating loads without ex-
cessive deflection.

(f) Controls of powerplant valves re-

quired for safety must have—

(1) For manual valves, positive stops

or in the case of fuel valves suitable
index provisions, in the open and closed
position; and

(2) For power-assisted valves, a

means to indicate to the flight crew
when the valve—

(i) Is in the fully open or fully closed

position; or

(ii) Is moving between the fully open

and fully closed position.

(Secs. 313(a), 601, and 603, 72 Stat. 752, 775, 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. 29–13, 42 FR 15046, Mar. 17,
1977; Amdt. 29–26, 53 FR 34219, Sept. 2, 1988]

§ 29.1142

Auxiliary power unit con-

trols.

Means must be provided on the flight

deck for starting, stopping, and emer-
gency shutdown of each installed auxil-
iary power unit.

(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)))

[Amdt. 29–17, 43 FR 50602, Oct. 30, 1978]

§ 29.1143

Engine controls.

(a) There must be a separate power

control for each engine.

(b) Power controls must be arranged

to allow ready synchronization of all
engines by—

(1) Separate control of each engine;

and

(2) Simultaneous control of all en-

gines.

a positive and immediately responsive
means of controlling its engine.

(d) Each fluid injection control other

than fuel system control must be in
the corresponding power control. How-
ever, the injection system pump may
have a separate control.

(e) If a power control incorporates a

fuel shutoff feature, the control must
have a means to prevent the inad-
vertent movement of the control into
the shutoff position. The means must—

(1) Have a positive lock or stop at the

idle position; and

(2) Require a separate and distinct

operation to place the control in the
shutoff position.

(f) For rotorcraft to be certificated

for a 30-second OEI power rating, a
means must be provided to automati-
cally activate and control the 30-sec-
ond OEI power and prevent any engine
from exceeding the installed engine
limits associated with the 30-second
OEI power rating approved for the
rotorcraft.

[Amdt. 29–26, 53 FR 34219, Sept. 2, 1988, as
amended by Amdt. 29–34, 59 FR 47768, Sept.
16, 1994]

§ 29.1145

Ignition switches.

(a) Ignition switches must control

each ignition circuit on each engine.

(b) There must be means to quickly

shut off all ignition by the grouping of
switches or by a master ignition con-
trol.

except ignition switches for turbine en-
gines for which continuous ignition is
not required, and each master ignition
control must have a means to prevent
its inadvertent operation.

(Secs. 313(a), 601, and 603, 72 Stat. 759, 775, 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. 29–13, 42 FR 15046, Mar. 17,
1977]