Section 29.861

14 CFR Ch. I (1-1-19 Edition)

(g) Heater exhaust. Each heater exhaust system must meet the requirements of SectionSection 29.1121 and 29.1123. In addition - 
(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 failure.
(h) Heater fuel systems. Each heater
fuel system must meet the powerplant
fuel system requirements affecting safe
heater operation. Each heater fuel system component in the ventilating airstream must be protected by shrouds
so that no leakage from those components can enter the ventilating airstream.
(i) Drains. There must be means for
safe drainage of any fuel that might accumulate in the combustion chamber
or the heat exchanger. In addition - 
(1) Each part of any drain that operates at high temperatures must be protected 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]

Section 29.861 Fire protection of structure,
controls, and other parts.

spaschal on DSK3GDR082PROD with CFR

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 Section 29.1191, or must be - 
(a) For category A rotorcraft, fireproof; and
(b) For Category B rotorcraft, fireproof or protected so that they can perform 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]

Section 29.863 Flammable fluid fire protection.
(a) In each area where flammable
fluids or vapors might escape by leakage 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 leakage.
(2) Flammability characteristics of
fluids, including effects of any combustible or absorbing materials.
(3) Possible ignition sources, including electrical faults, overheating of
equipment, and malfunctioning of protective devices.
(4) Means available for controlling or
extinguishing a fire, such as stopping
flow of fluids, shutting down equipment, 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 required to prevent or counteract a fluid
fire (e.g. equipment shutdown or actuation of a fire extinguisher), quick acting 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 defined.
(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]

EXTERNAL LOADS
Section 29.865 External loads.
(a) It must be shown by analysis,
test, or both, that the rotorcraft external load attaching means for rotorcraft-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 approved under SectionSection 29.337 through 29.341,
multiplied by the maximum external

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