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minimum speed at which the aeroplane remains controllable
after sudden failure of the critical power-unit.
B.3.3 Trim
The aeroplane shall have such trim characteristics as to ensure
that the demands made on the pilot's attention and ability to
maintain a desired flight condition are not excessive when
account is taken of the stage of flight at which these demands
occur and their duration. This shall apply both in normal operation
and in the conditions associated with the failure of one
or more power-units for which performance characteristics are
established.
Sub-part B Annex 8 - Airworthiness of Aircraft
B.4 Stability and control
B.4.1 Stability
The aeroplane shall have such stability in relation to its other
flight characteristics, performance, structural strength, and
most probable operating conditions (e.g. aeroplane configurations
and speed ranges) as to ensure that demands made on the
pilot's powers of concentration are not excessive when the
stage of the flight at which these demands occur and their
duration are taken into account. The stability of the aeroplane
shall not, however, be such that excessive demands are made
on the pilot's strength or that the safety of the aeroplane is
prejudiced by lack of manoeuvrability in emergency conditions.
The stability may be achieved by natural or artificial
means, or a combination of both. In those cases where
artificial stability is necessary to show compliance with the
Standards of this part, it shall be shown that any failure or
condition that would result in the need for exceptional pilot
skill or strength for recovery of aeroplane stability is
extremely improbable.
Note.- Guidance material concerning the expression
"extremely improbable" is contained in the Airworthiness
Manual (Doc 9760).
B.4.2 Stalling
B.4.2.1 Stall warning. When the aeroplane approaches a
stall both in straight and turning flight, a clear and distinctive
stall warning shall be apparent to the pilot with the aeroplane
in all permissible configurations, except those which are not
considered to be essential for safe flying. The stall warning
and other characteristics of the aeroplane shall be such as to
enable the pilot to arrest the development of the stall after the
warning begins and, without altering the engine power or
thrust, to maintain full control of the aeroplane.
B.4.2.2 Behaviour following a stall. In any configuration
and at any level of power or thrust in which it is considered
that the ability to recover from a stall is essential, the behaviour
of the aeroplane following a stall shall not be so extreme
as to make difficult a prompt recovery without exceeding the
airspeed or strength limitations of the aeroplane.
B.4.2.3 Stalling speeds. The stalling speeds or minimum
steady flight speeds in configurations appropriate for each
stage of flight (e.g. take-off, en route, landing) shall be
established. One of the values of the power or thrust used in
establishing the stalling speeds shall be not more than that
necessary to give zero thrust at a speed just above the stall.
B.4.3 Flutter and vibration
B.4.3.1 It shall be demonstrated by suitable tests,
analyses or any acceptable combination of tests and analyses
that all parts of the aeroplane are free from flutter and excessive
vibration in all aeroplane configurations under all speed
conditions within the operating limitations of the aeroplane
(see A.2.2). There shall be no vibration or buffeting severe
enough to cause structural damage.
B.4.3.2 There shall be no vibration or buffeting severe
enough to interfere with control of the aeroplane or to cause
excessive fatigue to the flight crew within the operating lirnitations
of the aeroplane.
Note.- Buffeting as a stall warning is considered desirable
and discouragement of this type of buffeting is not intended.
B.4.4 Spinning
It shall be demonstrated that the aeroplane during normal
operation does not exhibit any tendency to inadvertently enter
into a spin. If the design is such that spinning is allowed or for
aeroplanes with one power-unit inadvertently possible, it shall
be demonstrated that with normal use of the controls and
without the use of exceptional piloting skill the aeroplane can
be recovered from a spin within appropriate recovery limits.
SUB-PART C. STRUCTURE
C.l General other design airspeeds necessary for configurations with high
lift or other special devices.
The aeroplane structure shall be designed, manufactured and
provided with instructions for its maintenance and repair with
the objective of avoiding catastrophic failure throughout its C.5.2 Limiting airspeeds
　
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