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Standards in this Annex and in Annex 6, Parts I and 11.
f) Fire pwcautions. The design of the aeroplane and the
materials used in its manufacture shall be such as to
minimize the possibility of in-flight and ground fires, to
minimize the production of smoke and toxic gases in the
event of a fire and to delay the occurrence of flashover
in the cabin. 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. Lavatories installed in aeroplanes shall be
equipped with a smoke detection system and a built-in
fire extinguisher system for each receptacle intended for
the disposal of towels, paper or waste.
detection system and a built-in fire starvation or
suppression system; and
3) 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, 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, 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 from 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, 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
certifcated take-off mass in excess of 5 700 kg but
not exceeding 45 500 kg, means should be provided
to minimize entry into thejlight crew compartment of
smoke, fumes and noxious vapours generated by an
explosion or fire on the aeroplane.
D.3 Aeroelasticity
g) Cargo compartment protection.
1) each cargo compartment accessible to a crew
member in a passenger-carrying aeroplane shall be
equipped with a fire suppression system;
2) each cargo compartment not accessible to a crew
member shall be equipped with a built-in fire
The aeroplane shall be free from flutter, structural divergence,
and loss of control due to structural deformation and aeroelastic
effects, at all speeds within and sufficiently beyond the
design envelope to comply with A.2.1. Account shall be taken
of the characteristics of the aeroplane and variations in pilot
skill and workload. Allowable limits for aerodynamic control
surfaces and how those limits are to be monitored shall be
13/12/07 IIIB
Sub-part D Annex 8 - Airworthiness of Aircrajl
specified so as to ensure that the aeroplane remains free from
aeroelastic problems during its operational life.
D.4 Occupants accommodation features
D.4.1 Seating and restraints
Adequate seating and restraints shall be provided for the occupants,
taking account of the likely flight and emergency
landing loads to be encountered. Attention shall be paid to
minimizing injury to occupants due to contact with surrounding
structure during the operation of the aeroplane.
D.4.2 Cabin environment
Ventilation, heating and, where applicable, pressurization
systems shall be designed to provide the cabin with an
adequate environment during the anticipated flight and ground
or water operating conditions. The systems design shall also
consider likely emergency conditions.
D.5 Electrical bonding and protection against
lightning and static electricity
D.5.1 Electrical bonding and protection against lightning
and static electricity shall be such as to:
a) protect the aeroplane, its systems, its occupants and
those who come in contact with the aeroplane on the
ground or water from the dangerous effects of lightning
discharge and electrical shock; and
b) prevent dangerous accumulation of electrostatic charge.
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附件8--航空器适航性 Airworthiness of Aircraft(36)
