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level intended by the broad Standards of this part.
A.1.4 Unless otherwise stated, the Standards apply to the A.4 Proof of compliance
complete aeroplane including power-units, systems and
equipment. The means by which compliance with the appropriate airworthiness
requirements is demonstrated shall ensure that in
A2 Operating limitations each case the accuracy achieved will be such as to provide
reasonable assurance that the aeroplane, its components and
A.2.1 Limiting conditions shall be established for the equipment comply with the requirements and are reliable and
aeroplane, its power-units and its equipment (see G.2). function correctly under the anticipated operating conditions.
ANNEX 8
SUB-PART B. FLIGHT
B.1 General B.2.4 Minimum performance
B. 1.1 Compliance with the Standards prescribed in this
Sub-part shall be established by flight or other tests conducted
upon an aeroplane or aeroplanes of the type for which a Type
Certificate is sought, or by calculations based on such tests,
provided that the results obtained by calculations are equal in
accuracy to, or conservatively represent, the results of direct
testing.
B.1.2 Compliance with each Standard shall be established
for all applicable combinations of aeroplane mass and centre
of gravity position, within the range of loading conditions for
which certification is sought.
B. 1.3 Where necessary, appropriate aeroplane configurations
shall be established for the determination of performance
in the various stages of flight and for the investigation of the
aeroplane's flying qualities.
B.1.4 For aeroplanes with one power-unit, or aeroplanes
with more than one power-unit that cannot maintain a positive
climb gradient following a power-unit failure, the design shall,
in the case of engine failure, enable the aeroplane to be operated
to a safe forced landing in favourable conditions.
B.2 Performance
B.2.1 Sufficient data on the performance of the aeroplane
shall be determined and scheduled in the flight manual to
provide operators with the necessary information for the
purpose of determining the total mass of the aeroplane on the
basis of the values, peculiar to the proposed flight, of the
relevant operational parameters, in order that the flight may be
made with reasonable assurance that a safe minimum performance
for that flight will be achieved.
B.2.2 Achieving the performance scheduled for the aeroplane
shall take into consideration human performance and in
particular shall not require exceptional skill or alertness on the
part of the flight crew.
Note.- Guidance material on human performance can be
found in the Human Factors Training Manual (Doc 9683).
B.2.3 The scheduled performance of the aeroplane shall
be consistent with compliance with A.2.1 and with the operation
in logical combinations of those of the aeroplane's
systems and equipment, the operation of which may affect
performance.
Minimum performance shall be scheduled for aeroplanes with
more than one power-unit that are turbine-powered or have a
maximum certificated take-off mass of over 2 721 kg as
follows:
a) at the maximum mass scheduled (see B.2.7) for take-off
and for landing, as functions of the aerodrome elevation
or pressure-altitude either in the standard atmosphere or
in specified still air atmospheric conditions; and
b) for seaplanes in specified conditions in smooth water,
the aeroplane shall be capable of accomplishing the minimum
performances specified in B.2.5 a) and B.2.6 a) respectively,
not considering obstacles, or runway or water run length.
Note.- This Standard permits the maximum take-off mass
and maximum landing mass to be scheduled in the jlight
manual against, for example:
- aerodrome elevation, or
- pressure-altitude at aerodrome level, or
- pressure-altitude and atmospheric temperature at aerodrome
level,
so as to be readily usable when applying the national code on
aeroplane performance operating limitations.
a) For aeroplanes with more than one power-unit that are
turbine-powered or have a maximum certificated
take-off mass of over 2 721 kg, after the end of the
period during which the take-off power or thrust may be
used, the aeroplane shall be capable of continuing to
climb, with the critical power-unit inoperative and the
remaining power-units operated within their maximum
continuous power or thrust limitations, up to a height
that it can maintain and at which it can continue safe
flight and landing.
b) The minimum performance at all stages of take-off and
climb shall be sufficient to ensure that under conditions
　
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