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The strength and fabrication of the aeroplane shall be such as
to ensure that the probability of disastrous fatigue failure of the
aeroplane's structure under repeated loads and vibratory loads
in the anticipated operating conditions is extremely remote.
Note.- Guidance material concerning the expression
"extremely remote" is contained in the Airworthiness Manual
(Doc 9760).
CHAPTER 4. DESIGN AND CONSTRUCTION
4.1 General
Details of design and construction shall be such as to give
reasonable assurance that all aeroplane parts will function
effectively and reliably in the anticipated operating conditions.
They shall be based upon practices that experience has 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).
4.1.1 Substantiating tests
The functioning of all moving parts essential to the safe
operation of the aeroplane shall be demonstrated by suitable
tests in order to ensure that they will function correctly under
all operating conditions for such parts.
4.1.2 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.
4.1.3 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.
4.1.4 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.
4.1.5 Inspection provisions
Adequate provision shall be made to p m i t any necessary
examination, replacement or reconditioning of parts of the
aeroplane that require such attention, either periodically or
after unusually severe operations.
4.1.6 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 operations, and
unintentional engagement of control surface locking
devices.
b) System survivability.
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, aeroplane systems shall be designed,
arranged and physically separated to maximize the
potential for continued safe flight and landing after
any event resulting in damage to the aeroplane
structure or systems.
2) Recommendation.- For aeroplanes of a maximum
certificated take-of mass in excess of 5 700 kg but
not exceeding 45 500 kg and for which the
application for certification was submitted on or
after 12 March 2000, aeroplane systems should be
designed, arranged and physically separated to marimize
the potential for continued safe flight and
landing after any event 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 pilot 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 pilot windshield shall permit, under
precipitation conditions, sufficient vision for the normal
conduct of flight and for the execution of approaches
and landings.
ANNEX 8 IIIA-4-1 13/12/07
Annex 8 - Ainvorlhiness of Aircraft Part IIL4
e) Provision for emergencies. Means shall be provided
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附件8--航空器适航性 Airworthiness of Aircraft(24)
