624 

14 CFR Ch. I (1–1–19 Edition) 

§ 29.871 

in the flight manual for the weights, 
altitudes, and temperatures for which 
external load approval is requested. 

(d) The critically configured jettison-

able external loads must be shown by a 
combination of analysis, ground tests, 
and flight tests to be both transport-
able and releasable throughout the ap-
proved operational envelope without 
hazard to the rotorcraft during normal 
flight conditions. In addition, these ex-
ternal loads—must be shown to be re-
leasable without hazard to the rotor-
craft during emergency flight condi-
tions. 

(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] 

M

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 

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. 

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