曝光台 注意防骗
网曝天猫店富美金盛家居专营店坑蒙拐骗欺诈消费者
6.3.1 Maximum and minimum rotor
rotational speed limitations
Maximum and minimum speeds for the rotors in both
power-on and power-off conditions shall be established. Any
operating conditions (e.g. airspeed) that affect such maxima or
minima shall be declared.
6.3.2 Rotor underspeed
and overspeed warnings
When the helicopter is made to approach a rotor
rotational speed limit, with or without power-units inoperative,
clear and distinctive warnings shall be apparent to the
pilot. The warnings and initial characteristics of the condition
shall be such as to enable the pilot to arrest the development
of the condition after the warning begins and to recover the
rotor rotational speed to within prescribed normal limits and to
maintain full control of the helicopter.
6.4 Tests
Rotor and power transmission systems shall complete
satisfactorily such tests as are necessary to ensure that they
will operate satisfactorily and reliably within the declared
ratings, conditions and limitations. The tests shall include at
least the following:
a) Operation. Tests shall be conducted to ensure that
strength, vibration and overspeeding characteristics are
satisfactory and to demonstrate proper and reliable
functioning of pitch changing and control mechanisms
and free wheel mechanisms.
b) Endurance. Tests of sufficient duration shall be
conducted at such powers, engine and rotor speeds and
other operating conditions as are necessary to demonstrate
reliability and durability of the rotor and power
transmission systems.
6.5 Compliance with engine and rotor and power
transmission systems limitations
The powerplant installation shall be so designed that the
engines and rotor and power transmission systems are
capable of being used in the anticipated operating conditions.
In conditions established in the helicopter flight manual, the
helicopter shall be capable of being operated without
exceeding the limitations established for the engines and rotor
and power transmission systems in accordance with Chapters 5
and 6.
6.6 Control of engine rotation
In those installations where continued rotation of a failed
engine would increase the hazard of fire or of a serious
structural failure, means shall be provided for the crew to stop
the rotation of the engine in flight or to reduce it to a safe
level.
6.7 Engine restarting
Means shall be provided for restarting an engine in flight at
altitudes up to a declared maximum altitude.
ANNEX 8 IVA-6-1 13/12/07
Annex 8 - Airworthiness of Aircraft Part ZVA
6.8 Arrangement and functioning
6.8.1 Independence of power-units
For performance Classes 1 and 2 helicopters, the powerplant
shall be arranged and installed so that each powerunit
together with its associated systems is capable of being
controlled and operated independently from the others and so
that there is at least one arrangement of the powerplant and
systems in which any failure, unless the probability of its
occurrence is extremely remote, cannot result in a loss of more
power than that resulting from complete failure of the critical
power-unit.
6.8.2 Rotor and power transmission
systems vibration
The vibration stresses for the rotor and power transmission
systems shall be determined and shall not exceed values that
have been found safe for operation within the operating
limitations established for the helicopter.
6.8.3 Cooling
The cooling system shall be capable of maintaining powerplant
and power transmission systems temperatures within the
established limits (see 6.5) at ambient air temperatures
approved for operation of the helicopter. The maximum and
minimum air temperatures for which the powerplant and
power transmission systems have been established as being
suitable shall be scheduled in the helicopter flight manual.
6.8.4 Associated systems
The fuel, oil, air induction, and other systems associated with
each power-unit, each power transmission unit and each rotor
shall be capable of supplying the appropriate unit in accordance
with its established requirements, under all conditions
affecting the functioning of the systems (e.g. engine power
setting, helicopter attitudes and accelerations, atmospheric
conditions, fluid temperatures) within the anticipated operating
conditions.
6.8.5 Fire protection
For desig~atedfi re zones where the potential fire hazards are
particularly serious because of the proximity of ignition
sources to combustible materials, the following shall apply in
addition to the general Standard of 4.1.6 e):
中国航空网 www.aero.cn
航空翻译 www.aviation.cn
本文链接地址：
附件8--航空器适航性 Airworthiness of Aircraft(49)
