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generation of smoke;
For helicopters with 10 or more passenger seats, emergency
lighting shall be provided and shall have the following
characteristics:
a) independence from main electrical supply;
b) visual indication of emergency exits; and
c) illumination both inside and outside the helicopter
during evacuation.
ANNEX 8
SUB-PART J. OPERATING ENVIRONMENT AND HUMAN FACTORS
J.l General
The helicopter shall be designed to allow safe operation within
the performance limitations of users, including crew, passengers,
ground handling and maintenance staff.
Note.- The humanfmachine interjiace is ofen the weak link
in an operating environment and so it is necessary to ensure
that the helicopter is capable of being controlled at all phases
of the flight (including a 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.
Note.- Workload can be affected by both cognitive and
physiological factors.
5.3 Ergonomics
During design of the helicopter, account shall be taken of
ergonomics factors including:
a) ease of use and prevention of inadvertent misuse;
b) ease of access;
c) working environment;
5.2 Flight crew
d) standardization and commonality; and
5.2.1 The helicopter 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 expected flight crew capabilities. Account
shall be taken of the different expected operating conditions of
the helicopter in its environment, including operations
degraded by failures.
J.2.2 The workload imposed on the flight crew by the
design of the helicopter 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 helicopter, such as
engine failure.
e) ease of maintenance.
5.4 Operating environmental factors
The design of the helicopter shall take into consideration the
flight crew operating environment including:
a) effect of aeromedical factors such as noise and
vibration; and
b) effect of physical forces during normal flight.
ANNEX 8
PART V. SMALL AEROPLANES -
AEROPLANES OVER 750 KG BUT NOT EXCEEDING 5 700 KG
FOR WHICH APPLICATION FOR CERTIFICATION
WAS SUBMITTED ON OR AFTER 13 DECEMBER 2007
SUB-PART A. GENERAL
A.l Applicability Compliance with the Standards of this part shall be established
assuming that the aeroplane is operated within the limitations
A.l.l The Standards of this part are applicable in respect specified. The limitations shall include a margin of safety to
of all aeroplanes designated in A. 1.2 for which an application render the likelihood of accidents arising therefrom extremely
for the issue of a Type Certificate is submitted to the appro- remote.
priate national authorities on or after 13 December 2007.
A.1.2 The Standards of this part shall apply to all
aeroplanes having a maximum certificated take-off mass
greater than 750 kg but not exceeding 5 700 kg intended for
the carriage of passengers or cargo or mail in international air
navigation.
Note 1.- The aeroplanes described in A.1.2 are known in
some States as normal, utility and aerobatic category
aeroplanes.
Note 2.- The following Standards do not include quantitative
specifications comparable to those found in national airworthiness
codes. In accordance with 1.2.1 of Part 11, these
Standards are to be supplemented by requirements established,
adopted or accepted by Contracting States.
Note.- Guidance material concerning the expression
"extremely remote" is contained in the Airworthiness Manual
(Doc 9760).
A.2.2 Limiting ranges of any parameter whose variation
may compromise the safe operation of the aeroplane, e.g.
mass, centre of gravity location, load distribution, speeds,
ambient air temperature and altitude or pressure altitude, shall
be established within which compliance with all the pertinent
Standards in this part is shown.
A.3 Unsafe features and characteristics
A. 1.3 The level of airworthiness defined by the appro- Under all anticipated operating conditions, the aeroplane shall
priate parts of the comprehensive and detailed national code not possess any feature or characteristic that renders it unsafe.
referred to in 1.2.1 of Part I1 for the aeroplanes designated in
A.1.2 shall be at least substantially equivalent to the overall
　
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