曝光臺 注意防騙 網曝天貓店富美金盛家居專營店坑蒙拐騙欺詐消費者

HDG
STS
BCK
0
9 7
N
2
E
6
ENT
ENT
W
4
3 7 3 9
N
2
POS
GX_16_016
N
N
37390
0
W
W
1
1
2
2
2
2
1
1
2
2
N47325 W122125
N37390 W 0
5
N37390 W097260
5
Press POS Key
Press N/2 or S/8
Press ENT key to transmit latitude to all IRUs
Enter Longitude (example KICT)
Press ENT key to transmit longitude to all IRUs
Press HDG STS key and observe time to complete
alignment in right display
Press Latitude (example KICT)
For Training Purposes Only
Sept 04
16-15
P I LOT T R A I N I N G GU I D E
NAVIGATION
Enter the magnetic heading when the attitude mode has been selected.
NOTE
For more information, refer to the LASERTRACK Navigation
Display Unit of the Pilot’s Manual.
IRS 1 IRS 3 IRS 2
NAV NAV NAV
ALN ALN ALN
OFF OFF OFF
ATT ATT ATT
ENT
BCK
0
1 9 3
HDG
STS
1 2 3
GX_16_017
N
-
47
-
32
-
5
W
W122125
Press HDG STS
Press appropriate SYSTEM SELECT key
Ensure IRS mode
selector is set to ATT
Press ENT key to transmit heading to all IRUs
N 1930 A
A
t
t
t
t
Press Latitude (example KICT)
SYSTEM SELECT
P I LOT T R A I N I N G GU I D E
NAVIGATION
16-16 For Training Purposes Only
Sept 04
NDU SCHEMATIC
GX_16_018
IRU 1 IRU 2 IRU 3
IAC 1 IAC 2 IAC 3
SYSTEM SELECT FAULT
ON
FROM TO WPT
WPT
LEG
CHG
XTK
DTK
WD
WS
DIS
TIM
HDG
STS
POS
TK
GS
1
M
2 T
BRT
3 DIM
TST
ENT
BCK
0 CLR
7
S
8
9
W
4
5
E
6
1
N
2
3
88888
8 8
8 8888888
For Training Purposes Only
Sept 04
16-17
P I LOT T R A I N I N G GU I D E
NAVIGATION
INERTIAL REFERENCE SYSTEM
The inertial sensors consist of three ring laser gyros and three accelerometers. The
accelerometers measure linear motion along the longitudinal, lateral and vertical axis.
The ring laser gyros measure angular motion about the longitudinal, lateral and
vertical axis.
The Inertial Reference System (IRS) provides attitude, directional, position and 3-axis
rate/accelerometer data to the following airplane systems:
• PFDs and MFDs
• Weather radar system
• AFCS
• EGPWS
• TCAS
• Stall protection system
• Fuel system
• Flight data recorder
• Air data computer
• FMS
Each IRS computer (IRS 1, IRS 2, IRS 3) receives true airspeed and altitude from the
applicable air data system. In the event of a failure of the air data input, the backup
input should be manually selected using the reversion control panel.
The IRS mode select panel, located on the pedestal, is used to initialize the IRS and to
select NAV or ATT modes.
P I LOT T R A I N I N G GU I D E
NAVIGATION
16-18 For Training Purposes Only
Sept 04
At an IRS internal temperature between - 54°C and - 40°C, the power supply will turn
on, but normal alignment will not start until IRS temperature is >- 40°C. The IRS will
not go to NAV mode until the internal temperature of IRS reaches - 15°C.
Inertial reference accuracies are achieved for alignments between ± 78.25° of latitude.
LOW TEMPERATURE ALIGNMENT
IRS INTERNAL TEMPERATURE (°C) TIME TO COMPLETE ALIGNMENT (MIN.)
<-12.5 16
-12.5 to -10.0 15
-10.0 to -7.5 14
-7.5 to -5.0 13
-5.0 to -2.5 12
-2.5 to 0 11
> 0 7
70
60
50
40
LIM HDG
9500
210 BARO 29.92 IN
AP1 ASEL
AT1
VTA
SPD VAPP VNAV
0.856M
DTK
– – –
HDG
– – –
SRP
VS 0
0
1
2
3
1
2
3
00
500
10000
ATT2
ADC1
20 20
10 10
10 10
20 20
0
200
030
1
9
3000
20
00
80
60
01
N
33
30
W
24
21
S
15
12
E
6
3
– –.–NM
FMS1
IRS 1 IRS 3 IRS 2
NAV NAV NAV
ALN ALN ALN
OFF OFF OFF
　
中國航空網 www.k6050.com
航空翻譯 www.aviation.cn
本文鏈接地址：龐巴迪挑戰者手冊9(103)