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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