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flight.
9.6.2 Markings and placards or instructions shall be
provided to give any information that is essential to
the ground crew in order to preclude the possibility of
mistakes in ground servicing (e.g. towing, refuelling) that
could pass unnoticed and that could jeopardize the safety of
the helicopter in subsequent flights.
PART IVB. HELICOPTERS FOR WHICH APPLICATION FOR
CERTIFICATION WAS SUBMITTED ON OR AFTER
13 DECEMBER 2007
SUB-PART A. GENERAL
A.l Applicability
A.l.l The Standards of this part are applicable in respect of
all helicopters designated in A. 1.2 for which an application for
the issue of a Type Certificate is submitted to the appropriate
national authorities on or after 13 December 2007.
A.1.2 The Standards of this part shall apply to helicopters
over 750 kg maximum certificated take-off mass intended for
the carriage of passengers or cargo or mail in international air
navigation.
Note.- 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.
A.1.3 The level of airworthiness defined by the appropriate
parts of the comprehensive and detailed national code
referred to in 1.2.1 of Part II for the helicopters designated in
A.1.2 shall be at least substantially equivalent to the overall
level intended by the broad Standards of this part.
The safety implications of exceeding these operating limits
shall be considered.
A.2.2 Limiting ranges of any parameter whose variation
may compromise the safe operation of the helicopter, e.g.
mass, centre of gravity location, load distribution, speeds,
ambient air temperature and altitude, shall be established
within which compliance with all the pertinent Standards of
this part is shown.
Note 1.- The maximum operating mass and centre of
gravity limits may vary, for example, with each altitude and
with each practicably separate operating condition, e.g. takeofi
en route, landing.
Note 2.- Maximum operating mass may be limited by the
application of Noise Certification Standards (see Annex 16,
Volume I and Annex 6, Part 111).
A.3 Unsafe features and characteristics
Under all anticipated operating conditions, the helicopter shall
not possess any feature or characteristic that renders it unsafe.
A. 1.4 Unless otherwise stated, the Standards apply to the
complete helicopter including engines, systems and equipment.
A.4 Proof of compliance
A.2 Operating limitations The means by which compliance with the appropriate airworthiness
requirements is demonstrated shall ensure that in
A.2.1 Limiting conditions shall be established for the heli- each case the accuracy achieved will be such as to provide
copter, its engine(s) and its equipment (see G2). Compliance reasonable assurance that the helicopter, its components and
with the Standards of this part shall be established assuming equipment comply with the requirements and are reliable and
that the helicopter is operated within the limitations specified. function correctly under the anticipated operating conditions.
ANNEX 8
SUB-PART B. FLIGHT
B.l General pressure-altitude and temperature in still air conditions, and,
for water operations, in specified conditions of smooth water,
B.l.l Compliance with the Standards prescribed in this the helicopter shall be capable of accomplishing the minimum
sub-part shall be established by flight or other tests conducted performances specified in B.2.5 and B.2.6, respectively, not
upon a helicopter or helicopters of the type for which a Type considering obstacles or final approach and take-off area
Certificate is sought, or by calculations (or other methods) length.
based on such tests, provided that the results obtained by
calculations (or other methods) are equal in accuracy to, or
conservatively represent, the results of direct testing.
B.2.5 Take-off
B.1.2 Compliance with each Standard shall be established
for all applicable combinations of helicopter mass and centre
of gravity position, within the range of loading conditions for
which certification is sought.
B. 1.3 Where necessary, appropriate helicopter configurations
shall be established for the determination of performance
in the various stages of flight and for the investigation of the
helicopter's flying qualities.
B.2 Performance
B.2.1 Sufficient data on the performance of the helicopter
shall be determined and scheduled in the flight manual to
provide operators with the necessary information for the
　
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