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14 CFR Ch. I (1–1–19 Edition) 

§ 121.277 

ability to resist, without failure, all vi-
bration, 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. 

§ 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 ma-
terial that is at least fire resistant. 

(b) Paragraph (a) of this section does 

not apply to tail surfaces lying behind 
nacelles unless the dimensional con-
figuration of the airplane is such that 
the tail surfaces could be affected read-
ily by heat, flames, or sparks ema-
nating from a designated fire zone or 
from the engine compartment of any 

§ 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 en-
gine in flight. 

(b) In the case of turbine engine in-

stallations, a means of stopping the ro-
tation need be provided only if the Ad-
ministrator finds that rotation could 
jeopardize the safety of the airplane. 

§ 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 irre-
coverable loss of power of more than 
one engine. 

(b) A separate fuel tank need not be 

provided for each engine if the certifi-
cate holder shows that the fuel system 
incorporates features that provide 
equivalent safety. 

§ 121.283

Induction system ice preven-


A means for preventing the malfunc-

tioning of each engine due to ice accu-
mulation in the engine air induction 
system must be provided for each air-

§ 121.285

Carriage of cargo in pas-

senger compartments. 

(a) Except as provided in paragraph 

(b), (c), or (d) or this section, no certifi-
cate holder may carry cargo in the pas-
senger compartment of an airplane. 

(b) Cargo may be carried anywhere in 

the passenger compartment if it is car-
ried in an approved cargo bin that 
meets the following requirements: 

(1) The bin must withstand the load 

factors and emergency landing condi-
tions applicable to the passenger seats 
of the airplane in which the bin is in-
stalled, 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 limita-
tions 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 emer-
gency 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 at-
tachment factor specified for the air-
plane, 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 compart-

(6) The bin must be fully enclosed 

and made of material that is at least 
flame resistant. 

(7) Suitable safeguards must be pro-

vided 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 smok-
ing’’ sign, or any required exit sign, un-
less an auxiliary sign or other approved 

VerDate Sep<11>2014 

08:20 May 17, 2019

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