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GNS 530(A) Pilot’s Guide and Reference
190-00181-00 Rev. G
1-8
SECTION 1
INTRODUCTION
Satellite Status Page
/ iÊ->ÌiÌiÊ-Ì>ÌÕÃÊ*>}iÊ}ÕÀiÊ££ä®Ê>««i>ÀÃÊ>ÃÊÌ iÊ
GNS 530 attempts to collect satellite information.
7 iÊ>ʼVµÕÀ}½ÊÃÌ>ÌÕÃÊÃÊ`ë>Þi`ÊÊÌ iÊ->ÌiÌiÊ
-Ì>ÌÕÃÊ*>}i]ÊÌ iÊ
signal strengths of any satellites received
>««i>ÀÊ>ÃʼL>ÀÊ}À>«
½ÊÀi>`}ðÊÊ/
ÃÊÃÊ>Ê}`Ê`V>ÌÊ
Ì
>ÌÊÌ
iÊÕÌÊÃÊÀiViÛ}ÊÃ}>ÃÊ>`Ê>Ê«ÃÌÊwÝÊÃÊLi}Ê
determined. Following the first-time use of the GNS 530,
Ì iÊÌiÊÀiµÕÀi`ÊvÀÊ>Ê«ÃÌÊwÝÊÛ>ÀiÃ]ÊÕÃÕ>ÞÊvÀÊ
one to two minutes.
Figure 1-10 Satellite Status Page
vÊ Ì iÊ ÕÌÊ V>Ê ÞÊ LÌ>Ê iÕ} Ê Ã>ÌiÌiÃÊ vÀÊ ÓÊ
>Û}>ÌÊÊ>ÌÌÕ`i®]ÊÌ
iÊÕÌÊÕÃiÃÊÌ
iÊ>ÌÌÕ`iÊ«ÀÛ`i`Ê
LÞÊÌ
iÊ>ÌÌÕ`iÊiV`iÀÊvÊiÊÃÊViVÌi`®°
/ iÊ ¼ /½Ê >ÕV>ÌÀÊ LÌÌÊ ivÌÊ VÀiÀÊ vÊ Ì iÊ
ÃVÀii®Ê`V>ÌiÃÊÌ
>ÌÊÃ>ÌiÌiÊVÛiÀ>}iÊÃÊÃÕvwViÌÊÌÊ
«>ÃÃÊLÕÌÊÌi}ÀÌÞÊÌÀ}ÊÌiÃÌðÊÊÊÌ
iÊiÝ>«iÊ
above, not enough satellites are being received to determine
>Ê«ÃÌ°ÊÊ/ iÊ->ÌiÌiÊ-Ì>ÌÕÃÊ*>}iÊÃ ÜÃÊÌ iÊÊÕLiÀÃÊ
for the satellites and the relative signal strength of each
Ã>ÌiÌiÊÀiViÛi`Ê>ÃÊ>ÊL>ÀÊ}À>« ÊÀi>`}®°
¼-i>ÀV }Ê -Þ½Ê `V>ÌiÃÊ Ì >ÌÊ Ã>ÌiÌiÊ >>>VÊ `>Ì>Ê
ÃÊ ÌÊ >Û>>LiÊ ÀÊ
>ÃÊ iÝ«Ài`Ê vÊ Ì
iÊ ÕÌÊ
>ýÌÊ LiiÊ
ÕÃi`Ê vÀÊ ÃÝÊ Ì
ÃÊ ÀÊ Ài®°Ê Ê /
ÃÊ i>ÃÊ Ì
iÊ ÕÌÊ ÃÊ
acquiring satellite data to establish almanac and satellite
orbit information, which can take five to ten minutes.
The data is recollected from the first available satellite.
/ iÊ->ÌiÌiÊ-Ì>ÌÕÃÊ*>}iÊ`ë>ÞÃÊ>ʼ-i>ÀV Ê-Þ½ÊÃÌ>ÌÕÃ]Ê>`Ê
the message
>ÕV>ÌÀÊ-®]Ê>LÛiÊÌ iÊ
MSG
Key also
y>à iÃÊÌÊ>iÀÌÊÌ iÊ«ÌÊvÊÃÞÃÌiÊiÃÃ>}i]ʼ-i>ÀV }ÊÌ iÊ
Sky’.
Viewing a system message:
Press the
MSG
Key (Figure 1-11).
/ iÊiÃÃ>}iÊ*>}iÊ>««i>ÀÃÊ>`Ê`ë>ÞÃÊÌ iÊÃÌ>ÌÕÃÊÀÊ
warning information applicable to the receiver’s current
operating condition.
Figure 1-11 Message Page
Returning to the previous page after
viewing a message:
Press the
MSG
Key again.
NOTE: The GNS 530 utilizes certain software
algorithms to ensure reliable GPS receiver
operation. Receiver Autonomous Integrity
Monitoring (RAIM) and Fault Detection and
Exclusion (FDE) are two examples. These features
allow navigation during Oceanic/Remote legs of
a flight using the GNS 530. For further details,
please refer to Sections 10.3, 10.4, and 14.
Содержание GNS 530
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