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complied with when the mass is varied over the applicable
range and is distributed in the most adverse manner, within the
operating limitations on the basis of which certification is
sought.
3.1.2 Limit loads
Except as might be otherwise qualified, the external loads and
the corresponding inertia loads, or resisting loads obtained for
the various loading conditions prescribed in 3.4, 3.5 and 3.6
shall be considered as limit loads.
3.1.3 Strength and deformation
In the various loading conditions prescribed in 3.4, 3.5 and
3.6, no part of the helicopter structure shall sustain detrimental
deformation at any load up to and including the limit load, and
the helicopter structure shall be capable of supporting the
ultimate load.
3.2 Airspeeds
3.2.1 Design airspeeds
Design airspeeds shall be established for which the helicopter
structure is designed to withstand the corresponding manoeuvring
and gust loads in accordance with 3.4.
3.2.2 Limiting airspeeds
Limiting airspeeds, based on the corresponding design
airspeeds with safety margins, where appropriate, in accordance
with 1.2.1, shall be included in the helicopter
flight manual as part of the operating limitations (see
9.2.2). When airspeed limitations are a function of mass,
mass distribution, altitude, rotor speed, power or other
factors, airspeed limitations based on the critical combination
of these factors shall be established.
3.3 Main rotor@)
rotational speed limits
A range of main rotor(s) speeds shall be established that:
a) with power on, provides adequate margin to accommodate
the variations in rotor speed occurring in any appropriate
manoeuvre and is consistent with the kind of
governor or synchronizer used; and
b) with power off, allows each appropriate autorotative
manoeuvre to be performed throughout the ranges of
airspeed and mass for which certification is requested.
3.4 Flight loads
The flight loading conditions of 3.4.1, 3.4.2 and 3.6 shall be
considered for the range of mass and mass distributions
prescribed in 3.1.1 and at airspeeds established in accordance
with 3.2.1. Asymmetrical as well as symmetrical loading shall
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.
3.4.1 Manoeuvring loads
Manoeuvring loads shall be computed on the basis of manoeuvring
load factors appropriate to the manoeuvres permitted
by the operating limitations. They shall not be less than values
that experience indicates will be adequate for the anticipated
operating conditions.
3.4.2 Gust loads
Gust loads shall be computed for vertical and horizontal gust
velocities that statistics or other evidence indicate will be
adequate for the anticipated operating conditions.
3.5 Ground and water loads
The structure shall be able to withstand all the loads due
to the reactions of the ground or water surface, as applicable,
ANNEX 8 IVA-3-1 13/12/07
Annex 8 - Airworthiness of Aircraft Part N A
that are likely to arise during start-up, ground and water
taxiing, lift-off, touchdown and rotor braking.
3.7 Flutter, divergence and vibration
Each part of the helicopter structure shall be free from
excessive vibration or oscillation (ground resonance, flutter,
etc.) under each appropriate speed and power condition.
3.5.1 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 helicopter 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.
3.6 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, loads due to
external mass, etc.) that are likely to occur in the anticipated
operating conditions.
3.8 Fatigue strength
The strength and fabrication of the helicopter shall be such as
to ensure that the probability of disastrous fatigue failure of the
helicopter's structure under repeated loads and vibratory loads
in the anticipated operating conditions is extremely remote.
Note 1.- This Standard can be complied with by the
establishment of "safe lives" or 'yail safe" characteristics of
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附件8--航空器适航性 Airworthiness of Aircraft(46)
