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
systems and equipment, the operation of which may affect
performance.
so as to be readily usable when applying the national code on
helicopter performance operating limitations.
a) In the event of critical power-unit failure, at or after the
take-off decision point (for performance Class 1) or the
defined point after take-off (for performance Class 2),
performance Classes 1 and 2 helicopters shall be capable of
continuing safe flight, the remaining power-unit@) being
operated within the approved limitations.
b) The minimum performance at all stages of take-off and
climb shall be sufficient to ensure that under conditions of
operation departing slightly from the idealized conditions
for which data are scheduled (see 2.2.3), the departure from
the scheduled values is not disproportionate.
2.2.2.2 Landing
a) Starting from the approach configuration, in the event
of critical power-unit failure at or before the landing
decision point (performance Class 1) or the defined
point before landing (performance Class 2), the helicopter
shall be capable of continuing safe flight, the
remaining power-unit@) being operated within the
approved limitations.
ANNEX 8 IVA-2-1 13/12/07
Annex 8 - Airworthiness of Aircraft Part ZVA
b) Starting from the landing configuration, the helicopter shall 2.2.3.2 En route. The en-route performance shall be the
be capable, in the event of a balked landing, of making a climb, cruise or descent performance with:
climb-out, with all power-units operating.
a) the critical power-unit inoperative;
2.2.3 Scheduling of performance
Performance data shall be determined and scheduled in the
flight manual so that their application by means of the
operating rules to which the helicopter is to be operated in
accordance with 5.1.2 of Annex 6, Part 111, will provide a
safe relationship between the performance of the helicopter
and the aerodromes, heliports and routes on which it is
capable of being operated. Performance data shall be
determined and scheduled for the following stages for the
ranges of mass, altitude or pressure-altitude, wind velocity,
and other ambient conditions and any other operational
variables for which the helicopter is to be certificated, and
additionally for amphibians, water surface conditions and
strength of current.
2.2.3.1 Take-ofl The take-off performance data shall
include the take-off distance required and the take-off path.
For performance Class 1 helicopters, it shall also include the
rejected take-off distance required.
2.2.3.1.1 Take-off decision point. (For performance
Class 1 helicopters only.) The take-off decision point shall be
the point in the take-off phase used in determining take-off
performance and from which either a rejected take-off may be
made or a take-off safely continued, with the critical
power-unit inoperative.
2.2.3.1.2 Take-off distance required. (For performance
Class 1 helicopters only.) The take-off distance required shall
be the horizontal distance required from the start of the
take-off to the point at which the take-off safety speed (VToss),
a selected height above the take-off surface, and a positive
climb gradient are achieved, following failure of the critical
power-unit at the take-off decision point, the remaining
power-unit(s) operating within approved operating limits.
2.2.3.1.3 Rejected take-off distance required. (For
performance Class 1 helicopters only.) The rejected take-off
distance required shall be the horizontal distance required from
the start of the take-off to the point where the helicopter comes
to a complete stop following a power-unit failure and rejection
of the take-off at the take-off decision point.
2.2.3.1.4 Take-ofS distance required. (For performance
Classes 2 and 3 helicopters only.) The take-off distance
required shall be the horizontal distance required from the
start of take-off to the point where the best rate of climb
speed (Vy) or the best angle of climb speed (Vx) or a selected
intermediate speed (provided this speed does not involve
flight within the avoid areas of the height-velocity diagrams)
and a selected height above the take-off surface are achieved,
all engines operating at approved take-off power.
b) the two critical power-units inoperative in the case of
helicopters having three or more power-units; and
c) the operating engine(s) not exceeding the power for
which they are certificated.
2.2.3.3 Landing. The landing performance data shall
include the landing distance required and, for performance
Class 1 helicopters, the landing decision point.
2.2.3.3.1 Landing decision point. (For performance
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(44)
