268
14 CFR Ch. I (1–1–14 Edition)
§ 23.863
(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
from hazardous ice accumulation under
any operating condition.
[Amdt. 23–27, 45 FR 70387, Oct. 23, 1980]
§ 23.863
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 hazard 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 airplane 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.
[Amdt. 23–23, 43 FR 50593, Oct. 30, 1978]
§ 23.865
Fire protection of flight con-
trols, engine mounts, and other
flight structure.
Flight controls, engine mounts, and
other flight structure located in des-
ignated fire zones, or in adjacent areas
that would be subjected to the effects
of fire in the designated fire zones,
must be constructed of fireproof mate-
rial or be shielded so that they are ca-
pable of withstanding the effects of a
fire. Engine vibration isolators must
incorporate suitable features to ensure
that the engine is retained if the non-
fireproof portions of the isolators dete-
riorate from the effects of a fire.
[Doc. No. 27805, 61 FR 5148, Feb. 9, 1996]
E
LECTRICAL
B
ONDING AND
L
IGHTNING
P
ROTECTION
§ 23.867
Electrical bonding and protec-
tion against lightning and static
electricity.
(a) The airplane must be protected
against catastrophic effects from light-
ning.
(b) For metallic components, compli-
ance with paragraph (a) of this section
may be shown by—
(1) Bonding the components properly
to the airframe; or
(2) Designing the components so that
a strike will not endanger the airplane.
(c) For nonmetallic components,
compliance with paragraph (a) of this
section may be shown by—
(1) Designing the components to min-
imize the effect of a strike; or
(2) Incorporating acceptable means of
diverting the resulting electrical cur-
rent so as not to endanger the airplane.
[Amdt. 23–7, 34 FR 13092, Aug. 13, 1969]
M
ISCELLANEOUS
§ 23.871
Leveling means.
There must be means for determining
when the airplane is in a level position
on the ground.
[Amdt. 23–7, 34 FR 13092, Aug. 13, 1969]
Subpart E—Powerplant
G
ENERAL
§ 23.901
Installation.
(a) For the purpose of this part, the
airplane powerplant installation in-
cludes each component that—
(1) Is necessary for propulsion; and
(2) Affects the safety of the major
propulsive units.
(b) Each powerplant installation
must be constructed and arranged to—
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