623 

Federal Aviation Administration, DOT 

§ 29.865 

(h) 

Heater fuel systems. Each heater 

fuel system must meet the powerplant 
fuel system requirements affecting safe 
heater operation. Each heater fuel sys-
tem component in the ventilating air-
stream must be protected by shrouds 
so that no leakage from those compo-
nents can enter the ventilating air-
stream. 

(i) 

Drains.  There must be means for 

safe drainage of any fuel that might ac-
cumulate in the combustion chamber 
or the heat exchanger. In addition— 

(1) Each part of any drain that oper-

ates at high temperatures must be pro-
tected in the same manner as heater 
exhausts; and 

(2) Each drain must be protected 

against hazardous ice accumulation 
under any operating condition. 

[Doc. No. 5084, 29 FR 16150, Dec. 3, 1964, as 
amended by Amdt. 29–2, 32 FR 6914, May 5, 
1967] 

§ 29.861

Fire protection of structure, 

controls, and other parts. 

Each part of the structure, controls, 

and the rotor mechanism, and other 
parts essential to controlled landing 
and (for category A) flight that would 
be affected by powerplant fires must be 
isolated under § 29.1191, or must be— 

(a) For category A rotorcraft, fire-

proof; and 

(b) For Category B rotorcraft, fire-

proof or protected so that they can per-
form their essential functions for at 
least 5 minutes under any foreseeable 
powerplant fire conditions. 

[Doc. No. 5084, 29 FR 16150, Dec. 3, 1964, as 
amended by Amdt. 27–26, 55 FR 8005, Mar. 6, 
1990] 

§ 29.863

Flammable fluid fire protec-

tion. 

(a) In each area where flammable 

fluids or vapors might escape by leak-
age of a fluid system, there must be 
means to minimize the probability of 
ignition of the fluids and vapors, and 
the resultant hazards if ignition does 
occur. 

(b) Compliance with paragraph (a) of 

this section must be shown by analysis 
or tests, and the following factors must 
be considered: 

(1) Possible sources and paths of fluid 

leakage, and means of detecting leak-
age. 

(2) Flammability characteristics of 

fluids, including effects of any combus-
tible or absorbing materials. 

(3) Possible ignition sources, includ-

ing electrical faults, overheating of 
equipment, and malfunctioning of pro-
tective devices. 

(4) Means available for controlling or 

extinguishing a fire, such as stopping 
flow of fluids, shutting down equip-
ment, fireproof containment, or use of 
extinguishing agents. 

(5) Ability of rotorcraft components 

that are critical to safety of flight to 
withstand fire and heat. 

(c) If action by the flight crew is re-

quired to prevent or counteract a fluid 
fire (e.g. equipment shutdown or actu-
ation of a fire extinguisher), quick act-
ing means must be provided to alert 
the crew. 

(d) Each area where flammable fluids 

or vapors might escape by leakage of a 
fluid system must be identified and de-
fined. 

(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 50600, Oct. 30, 1978] 

E

XTERNAL

L

OADS

 

§ 29.865

External loads. 

(a) It must be shown by analysis, 

test, or both, that the rotorcraft exter-
nal load attaching means for rotor-
craft-load combinations to be used for 
nonhuman external cargo applications 
can withstand a limit static load equal 
to 2.5, or some lower load factor ap-
proved under §§ 29.337 through 29.341, 
multiplied by the maximum external 
load for which authorization is re-
quested. It must be shown by analysis, 
test, or both that the rotorcraft exter-
nal load attaching means and cor-
responding personnel carrying device 
system for rotorcraft-load combina-
tions to be used for human external 
cargo applications can withstand a 
limit static load equal to 3.5 or some 
lower load factor, not less than 2.5, ap-
proved under §§ 29.337 through 29.341, 
multiplied by the maximum external 
load for which authorization is re-
quested. The load for any rotorcraft- 
load combination class, for any exter-
nal cargo type, must be applied in the 

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14 CFR Ch. I (1–1–24 Edition) 

§ 29.865 

vertical direction. For jettisonable ex-
ternal loads of any applicable external 
cargo type, the load must also be ap-
plied in any direction making the max-
imum angle with the vertical that can 
be achieved in service but not less than 
30

°

. However, the 30

° 

angle may be re-

duced to a lesser angle if— 

(1) An operating limitation is estab-

lished limiting external load oper-
ations to such angles for which compli-
ance with this paragraph has been 
shown; or 

(2) It is shown that the lesser angle 

can not be exceeded in service. 

(b) The external load attaching 

means, for jettisonable rotorcraft-load 
combinations, must include a quick-re-
lease system to enable the pilot to re-
lease the external load quickly during 
flight. The quick-release system must 
consist of a primary quick release sub-
system and a backup quick release sub-
system that are isolated from one an-
other. The quick release system, and 
the means by which it is controlled, 
must comply with the following: 

(1) A control for the primary quick 

release subsystem must be installed ei-
ther on one of the pilot’s primary con-
trols or in an equivalently accessible 
location and must be designed and lo-
cated so that it may be operated by ei-
ther the pilot or a crewmember with-
out hazardously limiting the ability to 
control the rotorcraft during an emer-
gency situation. 

(2) A control for the backup quick re-

lease subsystem, readily accessible to 
either the pilot or another crew-
member, must be provided. 

(3) Both the primary and backup 

quick release subsystems must— 

(i) Be reliable, durable, and function 

properly with all external loads up to 
and including the maximum external 
limit load for which authorization is 
requested. 

(ii) Be protected against electro-

magnetic interference (EMI) from ex-
ternal and internal sources and against 
lightning to prevent inadvertent load 
release. 

(A) The minimum level of protection 

required for jettisonable rotorcraft- 
load combinations used for nonhuman 
external cargo is a radio frequency 
field strength of 20 volts per meter. 

(B) The minimum level of protection 

required for jettisonable rotorcraft- 
load combinations used for human ex-
ternal cargo is a radio frequency field 
strength of 200 volts per meter. 

(iii) Be protected against any failure 

that could be induced by a failure mode 
of any other electrical or mechanical 
rotorcraft system. 

(c) For rotorcraft-load combinations 

to be used for human external cargo 
applications, the rotorcraft must— 

(1) For jettisonable external loads, 

have a quick-release system that meets 
the requirements of paragraph (b) of 
this section and that— 

(i) Provides a dual actuation device 

for the primary quick release sub-
system, and 

(ii) Provides a separate dual actu-

ation device for the backup quick re-
lease subsystem; 

(2) Have a reliable, approved per-

sonnel carrying device system that has 
the structural capability and personnel 
safety features essential for external 
occupant safety; 

(3) Have placards and markings at all 

appropriate locations that clearly state 
the essential system operating instruc-
tions and, for the personnel carrying 
device system, ingress and egress in-
structions; 

(4) Have equipment to allow direct 

intercommunication among required 
crewmembers and external occupants; 

(5) Have the appropriate limitations 

and procedures incorporated in the 
flight manual for conducting human 
external cargo operations; and 

(6) For human external cargo applica-

tions requiring use of Category A 
rotorcraft, have one-engine-inoperative 
hover performance data and procedures 
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. 

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§ 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] 

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. 

(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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