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landing distance available; (Figures A-4 and A-5)
c) in case of the critical power-unit failure occumng at any 4.2.1.1 The mass of the helicopter at take-off does not
point after the LDP, it is possible to land and stop within exceed the maximum take-off mass specified in the flight
the FATO; and manual taking into account the parameters specified in 2.1.
d) in case of the critical power-unit failure occumng at any 4.2.1.2 The take-off mass is such that a safe forced
point before the LDP, it is possible either to land and landing can be achieved in the event of a power-unit failure
stop within the FATO, or to overshoot and clear all prior to reaching the defined point after take-off.
obstacles in the flight path by a vertical interval
of 10.7 m (35 ft) for VFR plus an additional margin of
0.0 1 DR for IFR. * R is the rotor radius.
ATT A-3
Annex 6 - Opemtlon of Aircmfc Part I21
4.2.1 -3 In case of a take-off from an elevated heliport or
helideck and a failure of the critical power-unit occurring
before V, is obtained, the flight path may descend to achieve
V, if the following conditions are satisfied:
a) A clearance margin is established in relation to the
elevated heliport or helideck itself and to all obstacles
located on the elevated heliport or helideck. 4.5 m
(15 ft) has been found appropriate to a wide range of
helicopters.
b) The vertical clearance above all obstacles not located on
the elevated heliport or helideck is at least equal to
10.7 m (35 ft). An obstacle is considered if its distance
from the flight path does not exceed 30 m or 1.5 times
the over-all length of the helicopter whichever is greater.
4.2.2 Initial climb
4.2.2.1 The take-off mass is such that the climb path
provides a vertical clearance of not less than 10.7 m (35 ft) for
VFR operations and 10.7 m (35 ft) + 0.01 DR for IFR
operations above all obstacles located in the climb path, the
critical power-unit failure occurring at the defined point after
take-off.
4.2.2.2 An obstacle is considered if its lateral distance
from the nearest point on the surface below the intended flight
path does not exceed 30 m or 1.5 times the over-all length of
the helicopter, whichever is greater, plus:
0.10 DR for VFR day operations
0.15 DR for VFR night operations
0.30 DR for IFR operations without electronic guidance
0.15 DR for IFR operations with electronic guidance
0.10 DR for IFR operations with ILS or MLS guidance
except obstacles may be disregarded if they are situated
beyond:
a) 7 R* for day operations if it is assured that navigational
accuracy can be achieved by reference to suitable visual
cues during the climb;
b) 10 R* for night operations if it is assured that
navigational accuracy can be achieved by reference to
suitable visual cues during the climb;
c) 300 m if navigational accuracy can be achieved by
navigation aids; and
d) 900 m in the other cases.
4.2.3 En route
The take-off mass is such that it is possible, in case of the
critical power-unit failure occurring at any point of the flight
path, to continue the flight to an appropriate landing site and
achieve the minimum flight altitudes for the route to be flown.
4.2.4 Approach, tanding and balked landing
(Figures A-9 and A-10)
4.2.4.1 The estimated landing mass at the destination or
alternate is such that:
a) it does not exceed the maximum landing mass specified
in the flight manual, taking into account the parameters
specified in 2.1;
b) a safe forced landing can be achieved in the event of an
engine failure after reaching the defined point before
landing;
c) it is possible to perform a balked landing, all engines
operating, at any point of the flight path and clear all
obstacles in the flight path by a vertical clearance of not
less than:
10.7 m (35 ft) for VFR operations; and
10.7 m (35 ft) + 0.01 DR for IFR operations; and
d) it is possible, in case of the critical power-unit failure
occurring before the defined point before landing, either
to land and stop within the FATO, or to overshoot and
clear all obstacles in the flight path by a vertical interval
of 10.7 m (35 ft).
An obstacle is considered if its lateral distance from the
nearest point on the surface below the intended line of flight
does not exceed 30 m or 1.5 times the over-all length of the
helicopter, whichever is greater, plus:
0.10 DR for VFR day operations
0.15 DR for VFR night operations
0.30 DR for IFR operations without electronic guidance
0.15 DR for IFR operations with electronic guidance
0.10 DR for IFR operations with ILS or MLS guidance
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