title-14-part-29-sec29-903

625

Federal Aviation Administration, DOT

§ 29.903

(e) A placard or marking must be in-

stalled next to the external-load at-
taching means clearly stating any
operational limitations and the max-
imum authorized external load as dem-
onstrated under § 29.25 and this section.

(f) The fatigue evaluation of § 29.571

of this part does not apply to rotor-
craft-load combinations to be used for
nonhuman external cargo except for
the failure of critical structural ele-
ments that would result in a hazard to
the rotorcraft. For rotorcraft-load
combinations to be used for human ex-
ternal cargo, the fatigue evaluation of
§ 29.571 of this part applies to the entire
quick release and personnel carrying
device structural systems and their at-
tachments.

[Amdt. 29–12, 41 FR 55472, Dec. 20, 1976, as
amended by Amdt. 27–26, 55 FR 8005, Mar. 6,
1990; Amdt. 29–43, 64 FR 43020, Aug. 6, 1999]

ISCELLANEOUS

§ 29.871

Leveling marks.

There must be reference marks for

leveling the rotorcraft on the ground.

§ 29.873

Ballast provisions.

Ballast provisions must be designed

and constructed to prevent inadvertent
shifting of ballast in flight.

Subpart E—Powerplant

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.

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.

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14 CFR Ch. I (1–1–24 Edition)

§ 29.907

(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—

(1) Design precautions must be taken

to minimize the hazards to the rotor-
craft in the event of an engine rotor
failure; and

(2) The powerplant systems associ-

ated with engine control devices, sys-
tems, and instrumentation must be de-
signed to give reasonable assurance
that those engine operating limitations
that adversely affect engine rotor
structural integrity will not be exceed-
ed in service.

(e)

Restart capability. (1) A means to

restart any engine in flight must be
provided.

(2) Except for the in-flight shutdown

of all engines, engine restart capability
must be demonstrated throughout a
flight envelope for the rotorcraft.

(3) Following the in-flight shutdown

of all engines, in-flight engine restart
capability must be provided.

(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. 29–12, 41 FR 55472, Dec. 20,
1976; Amdt. 29–26, 53 FR 34215, Sept. 2, 1988;
Amdt. 29–31, 55 FR 38967, Sept. 21, 1990; 55 FR
41309, Oct. 10, 1990; Amdt. 29–36, 60 FR 55776,
Nov. 2, 1995]

§ 29.907

Engine vibration.

(a) Each engine must be installed to

prevent the harmful vibration of any
part of the engine or rotorcraft.

(b) The addition of the rotor and the

rotor drive system to the engine may
not subject the principal rotating parts
of the engine to excessive vibration
stresses. This must be shown by a vi-
bration investigation.

§ 29.908

Cooling fans.

For cooling fans that are a part of a

powerplant installation the following
apply:

(a)

Category A. For cooling fans in-

stalled in Category A rotorcraft, it
must be shown that a fan blade failure
will not prevent continued safe flight
either because of damage caused by the
failed blade or loss of cooling air.

(b)

Category B. For cooling fans in-

stalled in category B rotorcraft, there
must be means to protect the rotor-
craft and allow a safe landing if a fan
blade fails. It must be shown that—

(1) The fan blade would be contained

in the case of a failure;

(2) Each fan is located so that a fan

blade failure will not jeopardize safety;
or

(3) Each fan blade can withstand an

ultimate load of 1.5 times the cen-
trifugal force expected in service, lim-
ited by either—

(i) The highest rotational speeds

achievable under uncontrolled condi-
tions; or

(ii) An overspeed limiting device.
(c)

Fatigue evaluation. Unless a fa-

tigue evaluation under § 29.571 is con-
ducted, it must be shown that cooling