Section 125.177
Section 125.177

14 CFR Ch. I (1-1-19 Edition)
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 rotation need be provided only if the Administrator finds that rotation could
jeopardize the safety of the airplane.
Section 125.179

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 125.181
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 125.183 Carriage of cargo in passenger compartments.
(a) Except as provided in paragraph
(b) or (c) of this section, no certificate
holder may carry cargo in the passenger compartment of an airplane.
(b) Cargo may be carried aft of the
foremost seated passengers 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 ensure
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
means for proper notification of the
passenger is provided.
(c) All cargo may be carried forward
of the foremost seated passengers and
carry-on baggage may be carried alongside the foremost seated passengers if
the cargo (including carry-on baggage)
is carried either in approved bins as
specified in paragraph (b) of this section or in accordance with the following:
(1) It is properly secured by a safety
belt or other tie down having enough
strength to eliminate the possibility of
shifting under all normally anticipated
flight and ground conditions.
(2) It is packaged or covered in a
manner to avoid possible injury to passengers.
(3) It does not impose any load on
seats or the floor structure that exceeds the load limitation for those
components.
(4) Its location does not restrict access to or use of any required emergency or regular exit, or of the aisle in
the passenger compartment.

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