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F.1.3.
Note.- Some States accept the use of nationaU
international industry standards, such as RTCAIDO-178 or
EUROCAE ED12, for the design and testing of systems
sofiare.
ANNEX 8
SUB-PART I. CRASHWORTHINESS AND CABIN SAFETY
1.1 General d) fire detection and suppression equipment.
Crashworthiness shall be taken into account in the design of
aeroplanes to improve the probability of occupant survival.
1.4 Evacuation
1.2 Design emergency landing loads
Emergency landing (crash) loads shall be determined for all
categories of aeroplanes so that the interiors, furnishings,
support structure and safety equipment can be designed to
maximize survivability for the occupants. Items to be
considered shall include:
a) dynamic effects;
b) restraint criteria for items that could cause a hazard;
c) distortion of the fuselage in the areas of emergency
exits;
d) fuel cell integrity and position; and
The aeroplane shall be equipped with sufficient emergency
exits to allow for cabin evacuation within an appropriate time
period. Items to be considered, appropriate to the size of the
aeroplane, shall include:
a) number of seats and seating configuration;
b) number, location and size of exits;
C) marking of exits and provision of instructions for use;
d) likely blockages of exits;
e) operation of exits; and
f) positioning and weight of evacuation equipment at exits,
e.g. rafts.
e) integrity of electrical systems to avoid sources of
ignition.
1.5 Lighting and marking
1.3 Cabin fire protection
The cabin shall be so designed as to provide fire protection to
the occupants in the event of airborne systems failures or a
crash situation. Items to be considered shall include:
a) flammability of cabin interior materials;
b) fire resistance and the generation of smoke and toxic
fumes;
c) provision of safety features to allow for safe evacuation;
and
Emergency lighting, if installed, shall have the following
characteristics:
a) independence from main electrical supply;
b) automatic activation upon loss of normal powerlimpact;
c) visual indication of emergency exits;
d) illumination both inside and outside the aeroplane
during evacuation; and
e) no additional hazards in the event of fuel spillage,
emergency landings and minor crash events.
ANNEX 8
SUB-PART J. OPERATING ENVIRONMENT AND HUMAN FACTORS
J.l General
The aeroplane shall be designed to allow safe operation within
the performance limitations of its passengers and those who
operate, maintain and service it.
Note.- The humadmachine interface is often the weak link
in an operating environment and so it is necessary to ensure
that the aeroplane is capable of being controlled at all phases
of the flight (including any degradation due to failures) and
that neither the crew nor passengers are harmed by the
environment in which they have been placed for the duration
of the flight.
5.2 Flight crew
5.2.1 The aeroplane shall be designed in such a way as to
allow safe and efficient control by the flight crew. The design
shall allow for variations in flight crew skill and physiology
commensurate with flight crew licensing limits. Account shall
be taken of the different expected operating conditions of the
aeroplane in its environment, including operations degraded by
failures.
5.2.2 The workload imposed on the flight crew by the
design of the aeroplane shall be reasonable at all stages of
flight. Particular consideration shall be given to critical stages
of flight and critical events which may reasonably be expected
to occur during the service life of the aeroplane, such as a
contained engine failure or windshear encounter.
Note.- Workload can be affected by both cognitive and
physiological factors.
5.3 Ergonomics
During design of the aeroplane, account shall be taken of
ergonomic factors including:
a) ease of use and prevention of inadvertent misuse;
b) ease of access;
c) working environment;
d) standardization and commonality; and
e) ease of maintenance.
5.4 Operating environmental factors
The design of the aeroplane shall take into consideration the
flight crew operating environment including:
a) effect of aeromedical factors such as level of oxygen,
temperature, humidity, noise and vibration;
b) effect of physical forces during normal flight;
c) effect of prolonged operation at high altitude; and
d) physical comfort.
ANNEX 8
PART VI. ENGINES
SUB-PART A. GENERAL
A.1 Applicability
A.l.l Except as noted below, the Standards of this part
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附件8--航空器适航性 Airworthiness of Aircraft(72)
