622 

14 CFR Ch. I (1–1–19 Edition) 

§ 29.861 

(g) 

Heater exhaust. 

Each heater ex-

haust system must meet the require-
ments of §§ 29.1121 and 29.1123. In addi-
tion— 

(1) Each exhaust shroud must be 

sealed so that no flammable fluids or 
hazardous quantities of vapors can 
reach the exhaust systems through 
joints; and 

(2) No exhaust system may restrict 

the prompt relief of any backfire that, 
if so restricted, could cause heater fail-
ure. 

(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 

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