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at least 2 m above or below it; and
c) a yellow light having othenvise the same characteristics
as the light described in 3.2 c) and mounted in a vertical
line at least 2 rn above it.
f) when at anchor;
g) when a g o d .
The lights required by aemplanes in each case are described
below.
3.2 m e n under way
As illusbated in Figure 2, the following a p p e ~ n gas steady
unobstructed lights:
a) a red light projected above and below the horizontal
through angle of coverage L;
b) a green light projmted above and below the horizontal
through angle of coverage R;
c) a white light projected above and below the horizontal
through angle of coverage A; and
d) a white light projected though angle of coverage F.
The lights described in a), b) and c) should be visible at a
distance of at least 3.7 km (2 MM). The light described in d)
should be visible at a distance of 9.3 km (5 M) when fttted
to an aeroplane of 20 m or more in length or visible at a
distance of 5.6 km (3 NNI) when fitted to an -plane of less
than 20 rn in length.
2 metres at least
- A - -1 10" Red
Figure 3
3.4 When being towed
The lights described in 3.2 a), b) and c) apparing as steady,
unobstructed lights.
3.5 When not under comand and not making way
As illusbrated in Figure 4, two steady red lights placed where
they can best be seen, one vertically over the other and not less
than 1 m apart, and of such a character as to be visible all
mund the horizon at a distmce of at least 3.7 km (2 NM).
1 Red I
1 metre at least
3.6 When making way but not under comand
I
As illusbated in Figure 5, the lights described in 3.5 plus the
lights described in 3.2 a), b) and e).
3.3 When towing another vessel or aeroplane
Note.-- The display of lights prescribed in 3.5 and 3.6 is to
As illustrated in Figure 3, the following appearing as steady, be taken by other aircrap as signals that the aeroplane
unobstructed lights: showing them is not under command and cannot therefore get
out of the way. They are not signals ofaero-planes in distress
a) the lights described in 3.2; and requiring assistance.
24/1U05
No. 24
Appendix I Annex 6 - Qperadion of Aircrafl
1 metre at least
3.7 When at anchor
a) If less than 50 m in length, where it can best be seen, a
steady white light (Figure 6), visible all around the
horizon at a distance of at least 3.7 krn (2 W.
b) If 50 m or more in length, where they can best be seen,
a steady white forward light and a steady white rear
light (Figure 7) both visible all around the horizon at a
distance of at least 5.6 krn (3 W.
c) If 50 m or more in span a steady white light on each side
(Figures 8 and 9) to indicate the maximum span and
visible, so far as practicable, all around the horizon at a
distance of at least 1.9 km (1 NNI).
Figure 6
I Figure 7 I
Less than 50 metres in length; 50 metres or more in span
Figure 8
50 metres or mote in length; 50 metres or more in span
3.8 When aground
The lights prescribed in 3.7 and in addition two steady red
lights in vertical line, at least 1 rn apart so placed as to be
visible a11 around the horizon.
2411 1105
No. 24
APPENDIX 2. ALTIMETRY SYSTEM PERFORMANCE REQUIREMENTS
FOR OPERATIONS IN RVSM AIRSPACE
(Note.- See Chapter 7, 7.2.5)
1. In respect of groups of aeroplanes that are nominally of
identical design and build with respect to all details that could
influence the accuracy of height-keeping performance, the
height-keeping performance capability shall be such that the
total vertical error (TVE) for the group of aeroplanes shall
have a mean no greater than 25 m (80 ft) in magnitude and
shall have a standard deviation no greater than 28 - 0.013z2
for 0 I z 5 25 when z is the magnitude of the mean W E in
metres, or 92 - 0.004z2 for 0 z 5 80 where z is in feet. In
addition, the components of WE shall have the following
characteristics:
about a mean of 0 m, with a standard deviation no
greater than 13.3 m (43.7 ft). and in addition. the
decmse in the frequency of differences with increasing
difference magnitude shall be at least exponential.
2. In respect of aeroplanes for which the characteristics of
the airframe and altimetry system fit are unique and so cannot
be classified as belonging to a group of acropianes encompassed
by paragraph 1, the height-keeping performance capability
shall be such that the components of the TVE of the
aeroplane have the following charactuistics:
a) the mean altimetry system error (ASE) of the group a) the ASE of the aeroplane shall not exceed 60 m (200 ft)
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