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tests in order to ensure that they will function correctly under
all operating conditions for such parts.
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 that:
1) each control and control system shall operate with
the ease, smoothness and precision appropriate to its
function;
2) continued safe flight and landing of the aeroplane
shall not be prevented by:
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. The effect of the materials
on the occupants of the aeroplane and other persons on the
ground, and the environment in general, in normal and emergency
situations, shall be taken into account.
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.
i) any single failure not shown to be extremely
improbable in the control system; or
ii) any event that results in a jam of a flight control
in any normally encountered position of the flight
controls;
3) the possibility of jamming, inadvertent operations
and unintentional engagement of control surface
locking devices is minimized; and
4) each element of each flight control system is
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 survivabili@
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, 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.
ANNEX 8 IIIB-D-1
Annex 8 -Airworthiness of Aircraft Part IIIB
2) Recommendation.- For aeroplanes of a maximum
certificated take-off mass in excess of 5 700 kg but
not exceeding 45 500 kg, aeroplane systems should
be designed, arranged and physically separated to
maximize the potential for continued safe jlight 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 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, 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
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
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附件8--航空器适航性 Airworthiness of Aircraft(35)
