Section 121.277

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

ability to resist, without failure, all vibration, inertia, and other loads to
which they may be normally subjected.
Fire detectors must be unaffected by
exposure to fumes, oil, water, or other
fluids that may be present.
Section 121.277 Protection of other airplane
components against fire.
(a) Except as provided in paragraph
(b) of this section, all airplane surfaces
aft of the nacelles in the area of one
nacelle diameter on both sides of the
nacelle centerline must be made of material that is at least fire resistant.
(b) Paragraph (a) of this section does
not apply to tail surfaces lying behind
nacelles unless the dimensional configuration of the airplane is such that
the tail surfaces could be affected readily by heat, flames, or sparks emanating from a designated fire zone or
from the engine compartment of any
nacelle.
Section 121.279

Control of engine rotation.

(a) Except as provided in paragraph
(b) of this section, each airplane must
have a means of individually stopping
and restarting the rotation of any engine in flight.
(b) In the case of turbine engine installations, a means of stopping the rotation need be provided only if the Administrator finds that rotation could
jeopardize the safety of the airplane.
Section 121.281

Fuel system independence.

(a) Each airplane fuel system must be
arranged so that the failure of any one
component does not result in the irrecoverable loss of power of more than
one engine.
(b) A separate fuel tank need not be
provided for each engine if the certificate holder shows that the fuel system
incorporates features that provide
equivalent safety.
Section 121.283
tion.

Induction system ice preven-

A means for preventing the malfunctioning of each engine due to ice accumulation in the engine air induction
system must be provided for each airplane.

Section 121.285 Carriage of cargo in passenger compartments.
(a) Except as provided in paragraph
(b), (c), or (d) or this section, no certificate holder may carry cargo in the passenger compartment of an airplane.
(b) Cargo may be carried anywhere in
the passenger compartment if it is carried in an approved cargo bin that
meets the following requirements:
(1) The bin must withstand the load
factors and emergency landing conditions applicable to the passenger seats
of the airplane in which the bin is installed, multiplied by a factor of 1.15,
using the combined weight of the bin
and the maximum weight of cargo that
may be carried in the bin.
(2) The maximum weight of cargo
that the bin is approved to carry and
any instructions necessary to insure
proper weight distribution within the
bin must be conspicuously marked on
the bin.
(3) The bin may not impose any load
on the floor or other structure of the
airplane that exceeds the load limitations of that structure.
(4) The bin must be attached to the
seat tracks or to the floor structure of
the airplane, and its attachment must
withstand the load factors and emergency landing conditions applicable to
the passenger seats of the airplane in
which the bin is installed, multiplied
by either the factor 1.15 or the seat attachment factor specified for the airplane, whichever is greater, using the
combined weight of the bin and the
maximum weight of cargo that may be
carried in the bin.
(5) The bin may not be installed in a
position that restricts access to or use
of any required emergency exit, or of
the aisle in the passenger compartment.
(6) The bin must be fully enclosed
and made of material that is at least
flame resistant.
(7) Suitable safeguards must be provided within the bin to prevent the
cargo from shifting under emergency
landing conditions.
(8) The bin may not be installed in a
position that obscures any passenger-s
view of the  - seat belt -  sign  - no smoking -  sign, or any required exit sign, unless an auxiliary sign or other approved

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