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which shall either automatically prevent, or enable the
flight crew to deal with, emergencies resulting from
foreseeable failures of equipment and systems, the
failure of which would endanger the aeroplane. Reasonable
provisions shall be made for continuation of essential
services following power-unit or systems' failures to
the extent that such failures are catered for in the
performance and operating limitations specified in the
Standards in this Annex and in Annex 6, Parts I and 11.
f) Fire precautions. The design of the aeroplane and the
materials used in its manufacture, including cabin
interior furnishing materials replaced during major
refurbishing, shall be such as to minimize the possibility
of in-flight and ground fires and also to minimize the
production of smoke and toxic gases in the event of a
fire. Means shall be provided to contain or to detect and
extinguish such fires as might occur in such a way that
no additional danger to the aeroplane is caused.
g) Fire suppression. For aeroplanes for which the
application for certification was submitted on or after
12 March 2000, cargo compartment fire suppression
systems, including their extinguishing agents, shall be
designed so as to take into account a sudden and
extensive fire such as could be caused by an explosive
or incendiary device or dangerous goods.
h) Incapacitation of occupants.
1) For aeroplanes of a maximum certificated take-off
mass in excess of 45 500 kg or with a passenger
seating capacity greater than 60 and for which the
application for certification was submitted on or after
12 March 2000, design precautions shall be taken to
protect against possible instances of cabin depressurization
and against the presence of smoke or other
toxic gases, including those caused by explosive or
incendiary devices or dangerous goods, which could
incapacitate the occupants of the aeroplane.
2) Recommendation.- For aeroplanes of a maximum
certifcated take-off mass in excess of 5 700 kg but
not exceeding 45 500 kg and for which the application
for certification was submitted on or afier
12 March 2000, design precautions should be taken
to protect against possible instances of cabin
depressurization and against the presence of smoke
or other toxic gases, including those caused by
explosive or incendiary devices or dangerous goods,
which could incapacitate the occupants of the
aeroplane.
i) Protection of the jlight crew compartment jium smoke
and fumes.
1) For aeroplanes of a maximum certificated take-off
mass in excess of 45 500 kg or with a passenger
seating capacity greater than 60 and for which the
application for certification was submitted on or after
12 March 2000, means shall be provided to minimize
entry into the flight crew compartment of smoke,
fumes and noxious vapours generated by an
explosion or fire on the aeroplane.
2) Recommendation.- For aeroplanes of a maximum
certificated take-off mass in excess of 5 700 kg but
not exceeding 45500 kg and for which the
application for cert~jZcation was submitted on or
afer 12 March 2000, means should be provided to
minimize entry into the flight crao compartment of
smoke, fumes and noxious vapours generated by an
explosion or fire on the aeroplane.
4.1.7 Emergency landing provisions
4.1.7.1 Provisions shall be made in the design of the
aeroplane to protect the occupants, in the event of an emergency
landing, from fire and from the direct effects of deceleration
forces as well as from injuries arising from the effect of
deceleration forces on the aeroplane's interior equipment.
4.1.7.2 Facilities shall be provided for the rapid evacuation
of the aeroplane in conditions likely to occur following
an emergency landing. Such facilities shall be related to the
passenger and crew capacity of the aeroplane.
4.1.7.3 The interior layout of the cabin and the position
and number of emergency exits, including the means of
locating and illuminating the escape paths and exits, shall be
such as to facilitate rapid evacuation of the aeroplane in
conditions likely to occur following an emergency landing.
4.1.7.4 On aeroplanes certificated for ditching conditions,
provisions shall be made in the design to give maximum
practicable assurance that safe evacuation from the aeroplane
of passengers and crew can be executed in case of ditching.
4.1.8 Ground handling
Adequate provisions shall be made in the design to minimize
the risk that ground-handling operations (e.g. towing, jacking)
may cause damage, which could pass unnoticed, to the parts of
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附件8--航空器适航性 Airworthiness of Aircraft(25)
