773
Federal Aviation Administration, DOT
§ 29.903
Subpart E—Powerplant
G
ENERAL
§ 29.901
Installation.
(a) For the purpose of this part, the
powerplant installation includes each
part of the rotorcraft (other than the
main and auxiliary rotor structures)
that—
(1) Is necessary for propulsion;
(2) Affects the control of the major
propulsive units; or
(3) Affects the safety of the major
propulsive units between normal in-
spections or overhauls.
(b) For each powerplant installa-
tion—
(1) The installation must comply
with—
(i) The installation instructions pro-
vided under § 33.5 of this chapter; and
(ii) The applicable provisions of this
subpart.
(2) Each component of the installa-
tion must be constructed, arranged,
and installed to ensure its continued
safe operation between normal inspec-
tions or overhauls for the range of tem-
perature and altitude for which ap-
proval is requested.
(3) Accessibility must be provided to
allow any inspection and maintenance
necessary for continued airworthiness;
and
(4) Electrical interconnections must
be provided to prevent differences of
potential between major components of
the installation and the rest of the
rotorcraft.
(5) Axial and radial expansion of tur-
bine engines may not affect the safety
of the installation.
(6) Design precautions must be taken
to minimize the possibility of incorrect
assembly of components and equipment
essential to safe operation of the rotor-
craft, except where operation with the
incorrect assembly can be shown to be
extremely improbable.
(c) For each powerplant and auxiliary
power unit installation, it must be es-
tablished that no single failure or mal-
function or probable combination of
failures will jeopardize the safe oper-
ation of the rotorcraft except that the
failure of structural elements need not
be considered if the probability of any
such failure is extremely remote.
(d) Each auxiliary power unit instal-
lation must meet the applicable provi-
sions of this subpart.
(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. 29–3, 33 FR 969, Jan. 26,
1968; Amdt. 29–13, 42 FR 15046, Mar. 17, 1977;
Amdt. 29–17, 43 FR 50600, Oct. 30, 1978; Amdt.
29–26, 53 FR 34215, Sept. 2, 1988; Amdt. 29–36,
60 FR 55776, Nov. 2, 1995]
§ 29.903
Engines.
(a)
Engine type certification. Each en-
gine must have an approved type cer-
tificate. Reciprocating engines for use
in helicopters must be qualified in ac-
cordance with § 33.49(d) of this chapter
or be otherwise approved for the in-
tended usage.
(b)
Category A; engine isolation. For
each category A rotorcraft, the power-
plants must be arranged and isolated
from each other to allow operation, in
at least one configuration, so that the
failure or malfunction of any engine, or
the failure of any system that can af-
fect any engine, will not—
(1) Prevent the continued safe oper-
ation of the remaining engines; or
(2) Require immediate action, other
than normal pilot action with primary
flight controls, by any crewmember to
maintain safe operation.
(c)
Category A; control of engine rota-
tion. For each Category A rotorcraft,
there must be a means for stopping the
rotation of any engine individually in
flight, except that, for turbine engine
installations, the means for stopping
the engine need be provided only where
necessary for safety. In addition—
(1) Each component of the engine
stopping system that is located on the
engine side of the firewall, and that
might be exposed to fire, must be at
least fire resistant; or
(2) Duplicate means must be avail-
able for stopping the engine and the
controls must be where all are not like-
ly to be damaged at the same time in
case of fire.
(d)
Turbine engine installation. For
turbine engine installations—
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