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consisting of all portions of the aeroplane, the failure of which increases in the anticipated operating conditions, taking
would seriously endanger the aeroplane. into account the flying qualities and other characteristics
of the aeroplane;
3.1.1 Mass and mass distribution e) VE, to Vb, maximum speeds at which flaps and landing
gears may be extended or other configuration changes
Unless otherwise stated, all structural Standards shall be be made.
complied with when the mass is varied over the applicable
range and is distributed in the most adverse manner, within the The speeds VA, VB, VC, and VE in a), b), c) and e) shall be
operating limitations on the basis of which certification is suficiently greater than the stalling speed of the aeroplane to
sought. safeguard against loss of control in turbulent air.
3.1.2 Limit loads
3.2.2 Limiting airspeeds
Except as might be otherwise qualified, the external loads and
the corresponding inertia loads, or resisting loads obtained for Limiting airspeeds, based on the corresponding design
the various loading conditions prescribed in 3.3, 3.4 and 3.5 airspeeds with safety margins, where appropriate, in accordshall
be considered as limit loads. ance with 1.3.1, shall be included in the aeroplane flight
manual as part of the operating limitations (see 9.2.2).
3.1.3 Strength and deformation
In the various loading conditions prescribed in 3.3, 3.4 and
3.5, no part of the aeroplane structure shall sustain detrimental
3.3 Flight loads
defom&on at any load up to and including the limit load, and The flight loading conditions of 3.3.1, 3.3.2 and 3.5 shall be
the structure be the considered for the range of mass and mass distributions
ultimate load. prescribed in 3.1.1 and at airspeeds established in accordance
with 3.2.1. Asymmetrical as well as symmetrical loading shall
3.2 Airspeeds
3.2.1 Design airspeeds
be taken into account. The air, inertia and other loads resulting
from the specified loading conditions shall be distributed so as
to approximate actual conditions closely or to represent them
conservatively.
Design airspeeds shall be established for which the aeroplane
structure is designed to withstand the corresponding man- 3.3.1 Manoeuvring loads
oeuvring and gust loads in accordance with 3.3. In establishing
the design airspeeds, consideration shall be given to the Manoeuvring loads shall be computed on the basis of manfollowing
speeds: oeuvring load factors appropriate to the manoeuvres permitted
by the operating limitations. They shall not be less than values
a) VA, the design manoeuvring speed; that experience indicates will be adequate for the anticipated
operating conditions.
b) VB, the speed at which the maximum vertical gust
velocity assumed in accordance with 3.3.2 can be
withstood; 3.3.2 Gust loads
c) Vc, a speed not expected to be exceeded in normal Gust loads shall be computed for vertical and horizontal gust
cruising flight taking into account possible effects of velocities and gradients that statistics or other evidence indiupsets
when flying in turbulent conditions; cate will be adequate for the anticipated operating conditions.
ANNEX 8 IIIA-3-1 13/12/07
Annex 8 -Airworthiness of Aircraf2 Part ZZZA
3.4 Ground and water loads
The structure shall be able to withstand all the loads due to the
reactions of the ground and water surface that are likely to
arise during taxiing, take-off and landing.
3.4.1 Landing conditions
The landing conditions at the design take-off mass and at the
design landing mass shall include such symmetrical and
asymmetrical attitudes of the aeroplane at ground or water
contact, such velocities of descent, and such other factors
affecting the loads imposed upon the structure as might be
present in the anticipated operating conditions.
3.5 Miscellaneous loads
In addition to or in conjunction with the manoeuvring and gust
loads and with the ground and water loads, consideration shall
be given to all other loads (flight control loads, cabin
pressures, effects of engine operation, loads due to changes of
configuration, etc.) that are likely to occur in the anticipated
operating conditions.
3.6 Flutter, divergence and vibration
The aeroplane structure shall be designed to be fiee from
flutter, structural divergence (i.e. unstable structural distortion
due to aerodynamic loading), and loss of control due to structural
deformation, at speeds within and sufficiently beyond the
operating limitations to comply with 1.3.1. Adequate strength
shall be provided to withstand the vibration and buffeting that
might occur in the anticipated operating conditions.
3.7 Fatigue strength
　
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