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proven to be satisfactory or that are substantiated by special
tests or by other appropriate investigations or both. They shall
also consider Human Factors principles.
Note.- Guidance material on Human Factors principles
can be found in the Human Factors Training Manual
(Doc 9683).
D. 1.2 Substantiation of moving parts
The functioning of all moving parts essential to the safe operation
of the aeroplane shall be demonstrated in order to ensure
that they will function correctly under all operating conditions
for such parts.
D.1.3 Materials
All materials used in parts of the aeroplane essential for its
safe operation shall conform to approved specifications. The
approved specifications shall be such that materials accepted
as complying with the specifications will have the essential
properties assumed in the design.
D.1.4 Manufacturing methods
The methods of manufacturing and assembly shall be such as
to produce a consistently sound structure which shall be
reliable with respect to maintenance of strength in service.
D. 1.5 Protection
The structure shall be protected against deterioration or loss of
strength in service due to weathering, corrosion, abrasion or
other causes, which could pass unnoticed, taking into account
the maintenance the aeroplane will receive.
D. 1.6 Inspection provisions
Adequate provision shall be made to permit any necessary
examination, replacement or reconditioning of parts of the
aeroplane that require such attention, either periodically or
after unusually severe operations.
D.2 Systems design features
Special consideration shall be given to design features that
affect the ability of the flight crew to maintain controlled
flight. This shall include at least the following:
a) Controls and control systems. The design of the controls
and control systems shall be such as to minimize the
possibility of jamming, inadvertent operation including
prevention of mis-assembly, and unintentional engagement
of control surface locking devices.
1) Each control and control system shall operate with
the ease, smoothness and precision appropriate to its
functions.
2) Each element of each flight control system shall be
designed, or distinctively and permanently marked,
to minimize the probability of any incorrect assembly
that could result in the malfunction of the system.
b) System survivability. Aeroplane systems shall be
designed and arranged to maximize the potential for
continued safe flight and landing after events resulting
in damage to the aeroplane structure or systems.
C) Crew environment. The design of the flight crew compartment
shall be such as to minimize the possibility of
incorrect or restricted operation of the controls by the
crew, due to fatigue, confusion or interference.
Consideration shall be given at least to the following:
layout and identification of controls and instruments,
rapid identification of emergency situations, sense of
controls, ventilation, heating and noise.
d) Pilot vision. The arrangement of the flight crew compartment
shall be such as to afford a sufficiently extensive,
clear and undistorted field of vision for the safe
operation of the aeroplane, and to prevent glare and
reflections that would interfere with the pilot's vision.
The design features of the windshield shall permit,
under precipitation conditions of moderate rain,
sufficient vision for the normal conduct of flight and for
the execution of approaches and landings.
e) Provision for emergencies. Means shall be provided
which shall either automatically prevent, or enable the
ANNEX 8 V-D-1 13/12/07
Annex 8 - Airworthiness of Aircraft Part V
flight crew to deal with, emergencies resulting from D.4.2 Cabin environment
foreseeable failures of equipment and systems, the
failure of which would endanger the aeroplane. Reason- Ventilation, heating and, where applicable, pressurization
able provisions shall be made for continuation of essen- systems shall be designed to provide the cabin with an
tial services following power-unit or systems' failures to adequate environment during the anticipated flight and ground
the extent that such failures are catered for in the or water operating conditions. The systems design shall also
performance and operating limitations specified in the consider likely emergency conditions.
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 shall be such as to D.5 Electrical bonding and protection against
minimize the possibility of in-flight and ground fires, to lightning and static electricity
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附件8--航空器适航性 Airworthiness of Aircraft(67)
