BD500 SERIES (PW PW1500G) INITIAL MAINTENANCE TRAINING COURSE
TECHNICAL TRAINING MANUAL (OPTIONS)
CMUI: CS130-21.12-06.00-121418
VERSION V6.00
BD-500-1A10
BD-500-1A11
CUSTOMER TRAINING
Montreal Training Centre
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Copyright © 1999-2018 Bombardier Inc. or its subsidiaries. All rights reserved.
Copyright © Bombardier Inc.
CS130-21.12-06.00-121418
TECHNICAL TRAINING MANUAL
For Training Purposes Only
C Series Option Book - List of Changes
C SERIES OPTION BOOK - LIST OF CHANGES
The following table details the changes applied to this revision:
ATA NAME AND NUMBER
CMUI NUMBER
CHANGES APPLIED
Front Page
CS130-21.12-06.00-121418
Version number and CMUI changed
List of Changes
CS130-21.12-06.00-121418
New CMUI
23 Communication Controller-Pilot Data
Link Communications - LINKS2000+
(Option)
CS130-21.12-06.00-121418
No changes
23 Communication Controller-Pilot Data
CS130-21.12-06.00-121418
Link Communications - FANS-1/A+ (Option)
No changes
23 Communication Flight Deck Door
Surveillance System (Option)
CS130-21.12-06.00-121418
No changes
23 Communication High Frequency
Communication System (Option)
CS130-21.12-06.00-121418
No changes
27 Flight Controls Steep Approach
CS130-21.12-06.00-121418
No changes
34 Navigation Head-Up Display System
(Option)
CS130-21.12-06.00-121418
Updated graphic (pge 34-17)
34 Navigation Surface Management System CS130-21.12-06.00-121418
(Option)
No changes
44 Cabin Systems In-Flight Entertainment
and Connectivity System (Option)
CS130-21.12-06.00-121418
No changes
46 Information Systems Electronic Flight
Bag (Option)
CS130-21.12-06.00-121418
No changes
46 Information Systems Integrated Flight
Information System (Option)
CS130-21.12-06.00-121418
Changed USB keyboard to keyboard; Changed heading ‘USB Keyboard’ to
‘Optional Keyboard’ (pges 46-2, 46-6, 46-7, 46-18)
Changed caption ‘maintenance switch’ to ‘HMU maintenance panel’ (pge 46-17)
Copyright © Bombardier Inc.
CS130-21.12-06.00-121418
TECHNICAL TRAINING MANUAL
For Training Purposes Only
LOC i
C Series Option Book - List of Changes
Page Intentionally Left Blank
Copyright © Bombardier Inc.
CS130-21.12-06.00-121418
TECHNICAL TRAINING MANUAL
For Training Purposes Only
LOC ii
ATA 23 - Communication
Controller-Pilot Data Link
Communications – LINK2000+
(Option)
BD-500-1A10
BD-500-1A11
23 - Communication
23-22 Controller-Pilot Data Link Communications – LINK2000+
(Option)
Table of Contents
23-22 Controller-Pilot Data Link
Communications – LINK2000+.....................................23-2
Introduction .......................................................................23-2
CPDLC Link2000+ ...........................................................23-2
General Description ..........................................................23-4
Controls and Indications ...................................................23-6
Controls........................................................................23-6
Indications....................................................................23-8
Operation ........................................................................23-10
CNS CPDLC Menu Page...........................................23-10
MSG Log....................................................................23-12
LOGON Menu ............................................................23-14
System Info ................................................................23-16
Message Status .........................................................23-18
Request Menu............................................................23-20
Uplink Scenario .........................................................23-22
Downlink Scenario .....................................................23-28
Monitoring and Tests ......................................................23-30
CAS Messages ..........................................................23-31
Copyright © Bombardier Inc.
CS130-21.12-06.00-121418
TECHNICAL TRAINING MANUAL
For Training Purposes Only
23-i
23 - Communication
23-22 Controller-Pilot Data Link Communications – LINK2000+
(Option)
List of Figures
Figure 1:
Figure 2:
Figure 3:
Figure 4:
Figure 5:
Figure 6:
Figure 7:
Figure 8:
CPDLC LINK2000+ Introduction ...........................23-3
CPDLC LINK2000+ General Description ..............23-5
CPDLC Controls....................................................23-7
CPDLC Indications ................................................23-9
CPDLC Menu ......................................................23-11
MSG LOG Page ..................................................23-13
LOGON Menu .....................................................23-15
SYSTEM INFO and PROTECTED
MENU..................................................................23-17
Figure 9: CPDLC REQUEST Pages...................................23-21
Figure 10: CNS Page Uplink Scenario .................................23-23
Figure 11: WHEN CAN YOU Scenario.................................23-25
Figure 12: Quick-Response Uplink Scenario........................23-27
Figure 13: Downlink Scenario...............................................23-29
Copyright © Bombardier Inc.
CS130-21.12-06.00-121418
TECHNICAL TRAINING MANUAL
For Training Purposes Only
23-ii
23 - Communication
23-22 Controller-Pilot Data Link Communications – LINK2000+
(Option)
Page Intentionally Left Blank
Copyright © Bombardier Inc.
CS130-21.12-06.00-121418
TECHNICAL TRAINING MANUAL
For Training Purposes Only
23-iii
23 - Communication
23-22 Controller-Pilot Data Link Communications – LINK2000+
(Option)
CONTROLLER-PILOT DATA LINK
COMMUNICATIONS – LINK2000+
Copyright © Bombardier Inc.
CS130-21.12-06.00-121418
TECHNICAL TRAINING MANUAL
For Training Purposes Only
23-1
23 - Communication
23-22 Controller-Pilot Data Link Communications – LINK2000+
(Option)
23-22 CONTROLLER-PILOT DATA LINK
COMMUNICATIONS – LINK2000+
INTRODUCTION
Controller-pilot data link communications (CPDLC) provides digital text
communication between the aircraft and air traffic control (ATC). This
reduces the need for voice communications required to perform routine
ATC instructions and requests. The use of CPDLC provides the following
benefits:
•
Decreased workload for ground controllers and aircrew
•
Increased air safety
•
Elimination of ambiguous voice transmissions
•
Reduction of communication frequency congestion
Fixed format text message responses are selectable using the CNS
page or the quick-response controls located on the glareshields.
CPDLC LINK2000+
CPDLC LINK2000+ uses a network protocol called the aeronautical
telecommunications network (ATN). The ATN provides the aircraft with a
ground communications system for continental airspace in Europe
above 28,500 ft.
A data link service provider subscription is required to access the ATN.
The CPDLC LINK2000+ system uses radio interface unit (RIU) 1 to
process information sent between the aircraft and ATC. Very high
frequency (VHF) 3 is used in data mode to transmit and receive the text
data. The information is then displayed in the data link inbox which is
located on the engine indication and crew alerting system (EICAS). The
information can also be viewed on the communication, navigation, and
surveillance (CNS) page when selected on a multifunction window
(MFW).
Copyright © Bombardier Inc.
CS130-21.12-06.00-121418
TECHNICAL TRAINING MANUAL
For Training Purposes Only
23-2
23 - Communication
23-22 Controller-Pilot Data Link Communications – LINK2000+
(Option)
CLB
TUNE
92.2
92.2
73.0
73.3
DLK
MSG LOG
CPDLC
SETTINGS
REQUEST
REPORT
LOGON/STATUS
N1
718
NETWORK
LINK 2000+
ATC DL
ENABLED
722
EGT
86.5
1090
124
116
FF (KPH)
OIL TEMP
OIL PRESS
5435
1400
5.7
ELEV 570
0
RATE
∆P
CREW OXY 1850
TEMP
(°C)
24
ARR
KICT
TRIM
BBA503
LOGON TO
NU
LOGON REQUIRED
STAB
HI
23
23
ND
4.2
UTC 10:20-KDTW
CLIMB TO 24000 FT
SEND LOGON
NL RUDDER NR
CPDLC
ACPT
KICT
FLT ID
2735
CAB ALT
LDG
DEPT
END OF FLIGHT
10905
TOTAL FUEL (KG)
2735
CDA ---------NDA ----------
86.6
1110
124
116
N2
NEW
1
INFO
OF 1
ACPT
STBY
LOAD
RJCT
ATC ATN AVAILABLE
NO ATC COMM
CNS
EICAS
LOAD
RJCT
GLARESHIELD
DMC 1 and DMC 2
RIU 1
VHF 3
VHF ANTENNA
CS1_CS3_2373_006
STBY
Figure 1: CPDLC LINK2000+ Introduction
Copyright © Bombardier Inc.
CS130-21.12-06.00-121418
TECHNICAL TRAINING MANUAL
For Training Purposes Only
23-3
23 - Communication
23-22 Controller-Pilot Data Link Communications – LINK2000+
(Option)
GENERAL DESCRIPTION
The CPDLC LINK2000+ system enables fixed format
communication with ATC using downlink and uplink messages.
text
Downlink messages are sent by the aircraft, uplink messages are sent
by ATC. Common downlink and uplink request messages include:
•
Altitude
•
Offset
•
Speed
•
Route
•
Monitoring
The uplink messages are displayed in the EICAS display.
Fixed format responses can be selected from the quick-response
controls on the glareshield or the CNS page.
Messages are transmitted and received using the VHF data link mode 2
through the VHF 3 transceiver. The transceiver uses RIU 1 for
processing information so that it can be transmitted and received over
VHF.
A CPDLC chime sounds whenever an uplink message is received.
Message management is done by the data link communication
application (DLCA) in the integrated processing cabinet (IPC) 1. The
protocol management application (PMA) allows the RIU to communicate
with the DLCA.
The message transmissions are stored in the cockpit voice recorder
(CVR) through the data concentrator unit module cabinet (DMC) 2.
If the optional printer is installed in the flight deck, the messages can be
printed. The RIU 1 provides the interface with the printer.
Copyright © Bombardier Inc.
CS130-21.12-06.00-121418
TECHNICAL TRAINING MANUAL
For Training Purposes Only
23-4
23 - Communication
23-22 Controller-Pilot Data Link Communications – LINK2000+
(Option)
RANGE
BRT
INBD DSPLY
L
MENU
R
ACPT
MAP
FMS
CNS
CHKL
SYN
DATA
LOAD
OUTBD
INBD
STBY
CHRONO
RJCT
CAUTION
EICAS
CNS
CLB
73.0
73.3
DLK
MSG LOG
SETTINGS
REQUEST
N1
NETWORK
LINK 2000+
ATC DL
ENABLED
722
EGT
86.5
1090
124
116
CDA ---------NDA ----------
86.6
1110
124
116
N2
FF (KPH)
OIL TEMP
OIL PRESS
DEPT
ARR
2735
5435
1400
5.7
ELEV 570
FLT ID
2735
0
CAB ALT
RATE
∆P
CREW OXY 1850
LDG
TEMP
(°C)
24
TRIM
23
23
ON/OFF>
TUNE/
MENU
<CLOCK
PFD/NAV>
IDENT
<STBY NAV
1/2
TUNE/DATA
RETURN
WX
HUD>
HPA
CRS 126
NAV
SRC
LEFT CTP
REPORT
INTEGRATED
PROCESSING CABINET 1
Data Link
Communication
Application
KICT
KICT
Protocol
Management
Application
BBA503
LOGON TO
NU
LOGON REQUIRED
STAB
HI
END OF FLIGHT
10905
TOTAL FUEL (KG)
<WXR
CPDLC
LOGON/STATUS
718
BRT
BARO
OFF
ND
4.2
CPDLC
UTC 10:20-KDTW
CLIMB TO 24000 FT
NL RUDDER NR
INFO
NEW 1 OF 1
ACPT
STBY
LOAD
RJCT
SEND LOGON
ATC ATN AVAILABLE
NO ATC COMM
DMC 1
and
DMC 2
COCKPIT VOICE RECORDER
RADIO
INTERFACE
UNIT 1
Communication
Management
Unit
Uplink/Downlink Messages
VHF 3
LEGEND
AFDX
ARINC 429
Discrete
PRINTER
(Optional)
Chime
CS1_CS3_2322_017
92.2
OFF
LEFT GLARESHIELD PANEL
TUNE
92.2
BRT
IN
TFC
WARNING
OFF
TERR
FPV CAGE
Figure 2: CPDLC LINK2000+ General Description
Copyright © Bombardier Inc.
CS130-21.12-06.00-121418
TECHNICAL TRAINING MANUAL
For Training Purposes Only
23-5
23 - Communication
23-22 Controller-Pilot Data Link Communications – LINK2000+
(Option)
CONTROLS AND INDICATIONS
CONTROLS
Quick-Response Panel
The quick-response panels allow a quick answer to received data link
messages. Quick-response buttons are used to respond to the CPDLC
uplink message that is displayed in the data link inbox. The buttons
provide the following functions:
•
ACPT: Sends an affirmative response such as WILCO, ROGER,
AFFIRM
•
STBY: Requests more time to analyze and answer the ATC request
•
RJCT: Sends a negative response such as UNABLE
•
LOAD: This function is not available in CPDLC LINK2000+
•
REFRESH (double arrow): Displays the latest received message or
removes a closed message from the inbox
Copyright © Bombardier Inc.
CS130-21.12-06.00-121418
TECHNICAL TRAINING MANUAL
For Training Purposes Only
23-6
23 - Communication
23-22 Controller-Pilot Data Link Communications – LINK2000+
(Option)
ACPT
LOAD
OUTBD
INBD
SIDESTICK
STBY
PTY
PT
TY
RJCT
CHRONO
WARNING
CAUTION
OFF
BRT
OFF
BRT
LEFT GLARESHIELD PANEL
QUICK RESPONSE PANEL
Function
ACPT
Initiates the ACCEPTED function.
STBY
Initiates the STANDBY function.
RJCT
Initiates the REJECTED function.
LOAD
Not available in Link2000+.
Displays the last received message or
removes a closed message from the box.
CS1_CS3_2323_012
Quick Release Buttons
Figure 3: CPDLC Controls
Copyright © Bombardier Inc.
CS130-21.12-06.00-121418
TECHNICAL TRAINING MANUAL
For Training Purposes Only
23-7
23 - Communication
23-22 Controller-Pilot Data Link Communications – LINK2000+
(Option)
INDICATIONS
The data link inbox provides a convenient location to view recent CPDLC
uplink messages. Messages can be responded to via the
quick-response panel.
Data link inbox status messages at the bottom of the data link inbox
provide indications of faults in the CPDLC system. The following
messages may be displayed:
The CPDLC tile is posted and a chime sounds when a CPDLC message
is received. The CPDLC tile remains in view until the message has been
viewed on CNS page, or a response is sent.
•
NO COMM – Indicates that the DLCA is not operating
•
NO ATC COMM – Indicates that connection with ATC is not
established
•
NO RIU COMM – Indicates that the PMA is not communicating with
the RIU
•
CPDLC INHIBITED – SEE CPDLC – This message is displayed
whenever a CAS message related to CPDLC is indicated
The tile is cleared when a message is read and there is no new CPDLC
uplink message present.
Messages are accompanied with a UTC time stamp, the ATC code, and
an arrow pointing either up or down. Downlink messages are
accompanied by an arrow pointing down. Uplink messages are
accompanied by an arrow pointing up.
Messages are displayed in cyan when they are open, and displayed in
white when they are viewed.
The data link inbox response button indicators are located to the right of
the messages. Each indicator is associated with a quick-response
control button on the glareshield. The indicators are displayed in three of
the following states:
•
Active – The active state indicates that the corresponding button is
available for selection
•
Inactive – The inactive state indicates that the corresponding button
is not available. Pressing the button does not have any effect
•
Disabled – The disabled state indicates that the corresponding
button is disabled due to a problem with the system. Pressing the
button has no effect
Copyright © Bombardier Inc.
CS130-21.12-06.00-121418
TECHNICAL TRAINING MANUAL
For Training Purposes Only
23-8
23 - Communication
23-22 Controller-Pilot Data Link Communications – LINK2000+
(Option)
1400
5.7
ELEV 570
CAB ALT
RATE
ó3
CREW
LDG
7(03
(°C)
24
0
OXY 1850
CPDLC
Tile
TRIM
NU
Message
Status
STAB
HI
23
23
4.2
ND
NL RUDDER NR
&3'/&
NEW 1
UTC 10:20-KDTW
CLIMB TO 24000 FT
Message
Header
INFO
OF 1
$&37
STBY
LOAD
RJCT
Response
Indicators
Data
Link
Inbox
NO COMM
EICAS
DATA LINK INBOX RESPONSE INDICATORS
Symbol
State
Description
$&37
Active
Button is available for selection.
$&37
Inactive
Button is not available.
Pressing the button does not have any effect.
$&37
Disabled
Button is disabled due to a problem with the system.
Pressing the button has no effect.
Data Link Inbox
Status Message
DATA LINK INBOX STATUS MESSAGES
Symbol
Description
NO COMM
DLCA is not operating.
NO ATC COMM
Connection with ATC is not established.
NO RIU COMM
PMA is not communicating with the RIU.
CPDLC CAS message is displayed.
CS1_CS3_2323_001
&3'/&,1+,%,7('6((&3'/&
Figure 4: CPDLC Indications
Copyright © Bombardier Inc.
CS130-21.12-06.00-121418
TECHNICAL TRAINING MANUAL
For Training Purposes Only
23-9
23 - Communication
23-22 Controller-Pilot Data Link Communications – LINK2000+
(Option)
OPERATION
CNS CPDLC MENU PAGE
The CNS button provides access to the CPDLC menu page. The
CPDLC menu page defaults to the LOGON submenu. The following
menus are available in the CPDLC CNS page:
•
MSG LOG
•
SETTINGS
•
REQUEST
MSG LOG
The message log menu tab provides access to the message review
submenu which enables access to previous messages.
SETTINGS
The settings menu tab provides access to a drop-down menu with the
LOGON or SYSTEM INFO selection.
REQUEST
The REQUEST menu tab provides access to a drop-down menu with the
following options:
•
ALTITUDE
•
OFFSET
•
SPEED
•
ROUTE
•
MONITORING
Copyright © Bombardier Inc.
CS130-21.12-06.00-121418
TECHNICAL TRAINING MANUAL
For Training Purposes Only
23-10
23 - Communication
23-22 Controller-Pilot Data Link Communications – LINK2000+
(Option)
CNS
CPDLC
MSG LOG
MSG REVIEW
SETTINGS
REQUEST
LOGON
ALTITUDE
SYSTEM INFO
OFFSET
SPEED
MONITORING
CS1_CS3_2373_007
ROUTE
Figure 5: CPDLC Menu
Copyright © Bombardier Inc.
CS130-21.12-06.00-121418
TECHNICAL TRAINING MANUAL
For Training Purposes Only
23-11
23 - Communication
23-22 Controller-Pilot Data Link Communications – LINK2000+
(Option)
MSG LOG
The MSG LOG menu is selected using the MSG LOG tab. This page
stores uplink and downlink messages that can be viewed. The
messages can be filtered to display only the open messages that require
a response.
Up to 75 messages can be stored. When the maximum storage limit of
75 messages is reached, the oldest CLOSED message is deleted to
make room for the NEW messages.
Messages are accompanied with a UTC time stamp, the ATC code, and
an arrow pointing either up or down. Downlink messages are
accompanied by an arrow pointing down. Uplink messages are
accompanied by an arrow pointing up.
Individual messages can be selected to view the associated message
history. Open uplink messages can be responded to by selecting a
response.
Copyright © Bombardier Inc.
CS130-21.12-06.00-121418
TECHNICAL TRAINING MANUAL
For Training Purposes Only
23-12
23 - Communication
23-22 Controller-Pilot Data Link Communications – LINK2000+
(Option)
Downlink/Uplink Arrow,
UTC Time Stamp
and ATC Code
DLK
TUNE
MSG LOG
UTC
Message
Header
Message
Status
TUNE
CPDLC
SETTINGS
22:40
REQUEST
FILTER
REPORT
ALL
UTC 22:39-EDMM
CLOSED/UNVIEWED
CHECK STUCK MICROPHONE 121.500 MHZ
UTC 22:35-EGTT
CLOSED
WE CAN ACCEPT 10000 FT AT 2315Z
UTC 22:34-EGTT
ACCEPTED
WHEN CAN YOU ACCEPT 10000 FT
UTC 22:34-EGTT
TIMEDOUT
SQUAWK 1220
UTC 22:34-EGTT
TIMEDOUT
MAINTAIN 0.780 MACH OR LESS
UTC 22:33-EGTT
TIMEDOUT
CROSS YUL AT OR BELOW FL250
UTC 22:33-EGTT
REJECTED
DESCEND TO REACH FL210 BY 1200Z
UTC 22:31-EGTT
ACCEPTED
PROCEED DIRECT TO DOTTY
UTC 22:30-EGTT
ACCEPTED
DESCEND TO REACH FL210 BY 0000Z
UTC 22:29-EGTT
CLOSED
REQUEST DIRECT TO DOTTY
UTC 22:28-EGTT
TIMEDOUT
PROCEED DIRECT TO EGTT
UTC 22:27-EGTT
ACCEPTED
FLY HEADING 270° M
MSG LOG
DLK
CPDLC
SETTINGS
REQUEST
TUNE
REPORT
UTC 22:39-EDMM
CHECK STUCK MICROPHONE 121.500 MHZ
RESPONSE HISTORY
MSG LOG
CLOSED
UTC
DLK
SETTINGS
22:40
CPDLC
REQUEST
FILTER
REPORT
ALL
UTC 22:39-EDMM
CLOSED
CHECK STUCK MICROPHONE 121.500 MHZ
UTC 22:35-EGTT
CLOSED
WE CAN ACCEPT 10000 FT AT 2315Z
UTC 22:34-EGTT
ACCEPTED
WHEN CAN YOU ACCEPT 10000 FT
UTC 22:34-EGTT
TIMEDOUT
SQUAWK 1220
UTC 22:34-EGTT
TIMEDOUT
MAINTAIN 0.780 MACH OR LESS
UTC 22:33-EGTT
TIMEDOUT
CROSS YUL AT OR BELOW FL250
UTC 22:33-EGTT
REJECTED
DESCEND TO REACH FL210 BY 1200Z
UTC 22:31-EGTT
ACCEPTED
PROCEED DIRECT TO DOTTY
UTC 22:30-EGTT
ACCEPTED
DESCEND TO REACH FL210 BY 0000Z
UTC 22:29-EGTT
CLOSED
REQUEST DIRECT TO DOTTY
UTC 22:28-EGTT
TIMEDOUT
PROCEED DIRECT TO EGTT
UTC 22:27-EGTT
ACCEPTED
FLY HEADING 270° M
UNVIEWED MESSAGE SELECTION
MESSAGE HISTORY
UPDATED MESSAGE STATUS
CS1_CS3_2322_022
PRINT
Figure 6: MSG LOG Page
Copyright © Bombardier Inc.
CS130-21.12-06.00-121418
TECHNICAL TRAINING MANUAL
For Training Purposes Only
23-13
23 - Communication
23-22 Controller-Pilot Data Link Communications – LINK2000+
(Option)
LOGON MENU
The LOGON page allows the aircraft to notify ATC that a communication
link is desired. When ATC acknowledges the request, communication is
established.
The LOGON TO field is used to input the International Civil Aviation
Organization (ICAO) address of the ATC to be contacted. The selection
is made using the SEND LOGON button.
Copyright © Bombardier Inc.
CS130-21.12-06.00-121418
TECHNICAL TRAINING MANUAL
For Training Purposes Only
23-14
23 - Communication
23-22 Controller-Pilot Data Link Communications – LINK2000+
(Option)
TUNE
TUN
NE
MSG LOGG
DLKK
DLK
CPDLC
PDLC
SETTINGS
REQUES
REQUEST
EST
LOGON/STATUS
TUNE
REPORT
MSG LOG
DLK
CPDLC
SETTINGS
REQUEST
LOGON/STATUS
NETWORK
LINK 2000+
NETWORK
ATC DL
ENABLED
ATC DL
LINK 2000+
LOGON DATA CHANGED
ENABLED
PREVIOUS VALUE
CDA ---------NDA ---------DEPT
KICT
ARR
KICT
FLT ID
REPORT
CDA
DEPT----------
END OF FLIGHT
NDA
ARR ----------
FLT ID
DEPT KICT
CURRENT VALUE
ENDEDDM
OF FLIGHT
EIDW
EDDF
EGLL
NW1234
NW4567
KICT
SELECTING CONTINUE WILL DISCONNECT
AND PURGE THE MESSAGE LOG
ID BBA503
ARR
BBA503
FLT
CONTINUE
LOGON TO
LOGON TO
LOGON REQUIRED
SEND LOGON
ATC ATN AVAILABLE
ATC ATN AVAILABLE
NO ATC COMM
FANS LOGON MENU
LOGON CHANGE CONFIRMATION WINDOW
CS1_CS3_2373_008
SEND LOGON
LOGGED ON TO ARICTEST
Figure 7: LOGON Menu
Copyright © Bombardier Inc.
CS130-21.12-06.00-121418
TECHNICAL TRAINING MANUAL
For Training Purposes Only
23-15
23 - Communication
23-22 Controller-Pilot Data Link Communications – LINK2000+
(Option)
SYSTEM INFO
The SETTINGS submenu allows access to maintenance functions in the
SYSTEM INFO submenu. The SYSTEM INFO submenu provides
information on the status of CPDLC system.
The following information is available on the SYSTEM INFO submenu
page:
•
Software versions
•
Configuration status
•
Component and application status
•
ATN status
PROTECTED MENU
To access the PROTECTED MENU a password is required at the bottom
of the SYSTEM INFO submenu. The password is the system’s current
time within 1 minute.
The PROTECTED MENU page offers the following options:
•
ONBOARD DEBUG
•
HEX MESSAGES
•
FOOTPRINTS
•
TIMERS
•
GND APP CFG
The PROTECTED MENU options allow modifications to the
configuration and software setup of the CPDLC. This menu also enables
debugging, and helps troubleshoot system faults.
Copyright © Bombardier Inc.
CS130-21.12-06.00-121418
TECHNICAL TRAINING MANUAL
For Training Purposes Only
23-16
23 - Communication
23-22 Controller-Pilot Data Link Communications – LINK2000+
(Option)
TUNE
TUN
NE
DLKK
DLK
CPDLC
PDLC
MSG LOG
MSG
OG SETTINGS
SYSTEM INFO
TIME
TUNE
REQUES
REQUEST
UEST
REPORT
DLK
CPDLC
MSG LOG SETTINGS
PROTECTED MENU
REQUEST
REPORT
ONBOARD DEBUG
UTC 18:24
HEX MESSAGE
TOP-LEVEL VERSION 810-0315-10OT DLCA ACTIVE
LEFT
HMI SW VERSION
096-6363-10OT DLCA XSIDE
NOT AVAIL
CORE SW VERSION
096-2550-10OT CABINET SLOT
1
FOOTPRINT
TIMERS
GND APP CFG
MSG LIB VERSION
096-6964-10OT CABINET SIDE
LEFT
A/C REGISTRATION
.C-GWXJ
FMS
CONN/LEFT
RIU
LEFT
PM
AVAILABLE
PRINTER
AVAILABLE
OPERATIONAL CONFIG ATN
FANS STATUS
UNAVAILABLE
CPDLC
UNAVAILABLE
LOGON
LOGGED OFF
LOGON
LOGGED OFF
CM
REGISTERED
PROTECTED MENU
----
NO ATC COMM
SYSTEM INFO
SYSTEM INFO PAGE
NO COMM
PROTECTED MENU PAGE
CS1_CS3_2373_011
ATN STATUS
CPDLC
Figure 8: SYSTEM INFO and PROTECTED MENU
Copyright © Bombardier Inc.
CS130-21.12-06.00-121418
TECHNICAL TRAINING MANUAL
For Training Purposes Only
23-17
23 - Communication
23-22 Controller-Pilot Data Link Communications – LINK2000+
(Option)
MESSAGE STATUS
The messages are labeled to indicate their status and whether a
response is required. New messages or messages that have not been
acknowledged, are displayed in cyan and change to white when they are
viewed.
The following tables provide the status and descriptions of uplink and
downlink messages.
Copyright © Bombardier Inc.
CS130-21.12-06.00-121418
TECHNICAL TRAINING MANUAL
For Training Purposes Only
23-18
23 - Communication
23-22 Controller-Pilot Data Link Communications – LINK2000+
(Option)
Table 1: Uplink Message Status
STATUS
Table 2: Downlink Message Status
DESCRIPTION
STATUS
DESCRIPTION
NEW
Pending uplink message that has not been
viewed and requires a response.
OPEN
A viewed downlink message that requires a
response.
OPEN
A viewed uplink message that requires a
response.
ACCEPTED
STANDBY
An open uplink message that has been
responded to with STANDBY that requires
another response to close.
A downlink message that has been
responded to with a ROGER, AFFIRM and no
further ATC action is required.
ACCEPTED/UNVIEWED
An uplink message that has been responded to
with a WILCO, ROGER, AFFIRM, and further
action is required.
A downlink message that has been
responded to with a ROGER, AFFIRM by
ATC that has not been viewed.
REJECTED
An uplink message that has been responded to
with a WILCO, ROGET, AFFIRM, and no further
action is required.
A downlink message that has been
responded to with either an UNABLE or
NEGATIVE. This message is closed.
REJECTED/UNVIEWED
An uplink message that has been responded to
with either an UNABLE or NEGATIVE. This
message is closed.
A downlink message that has been
responded to with either an UNABLE or
NEGATIVE by ATC and has not been viewed.
STANDBY
An uplink message that has had all the elements
of the message responded to or a message that
does not require a response.
An open downlink message that has been
responded to with STANDBY and requires
another ATC response to close.
CLOSED
A downlink message that has had all of the
elements of the message responded to or a
message that does not require a response.
CONNECTED
CPDLC is connected to the ground station.
No action is required.
PENDING
Transmission in progress and waiting for
network acknowledgment.
TIMEOUT
A downlink message that was not responded
to in the alloted time.
ERROR
A problem with the downlink message
transmission.
ACCEPTED/OPEN
ACCEPTED
REJECTED
CLOSED
CLOSED/UNVIEWED
CONN ENDED
TIMEOUT
An uplink message that does not require a
response that has not been viewed.
The CPDLC connection with ATA has been lost.
No response to the messages can be sent in this
state.
An uplink message that was not responded to in
the alloted time. A downlink message is
automatically sent stating that the message has
timed out. No responses can be made to the
message in this state.
CS_C1_AV23OPT_001
Copyright © Bombardier Inc.
CS130-21.12-06.00-121418
TECHNICAL TRAINING MANUAL
For Training Purposes Only
CS_C1_AV23OPT_002
23-19
23 - Communication
23-22 Controller-Pilot Data Link Communications – LINK2000+
(Option)
REQUEST MENU
MONITORING
The REQUEST submenu allows the user to send downlink messages to
ATC. The following type of requests can be sent:
The MONITORING page enables a downlink message to be sent to ATC
to indicate that a certain frequency is being monitored. This is done by
filling out the proper information on the following boxes:
•
ALTITUDE
•
OFFSET
•
SPEED
•
ROUTE
•
MONITORING
ALTITUDE/OFFSET/SPEED
Requests are made using the information input boxes. If a specific value
is desired, the value is input in the first box. If a range is required then
the lower value is input in the first box, the upper value in the second.
Check mark boxes allow the selection of the reason for the request.
These vary depending on the type of request.
Pressing the SET button displays a preview of the message in the
message preview window. Pressing the SEND button sends the
previewed message to the ATC station.
ROUTE
Route changes can be requested using the DIRECT TO POS menu box.
The DIRECT TO POS drop-down menu has the following selections:
•
FACILITY DESIGNATION – This is the ICAO designation for the
facility being monitored
•
FACILITY NAME – This is the name of the facility
•
VHF – This is the frequency that is being monitored
•
FACILITY – This is a drop-down menu
The FACILITY drop-down menu provides a set of options that allow the
selection of a specific function of the facility. The following selections are
available in the FACILITY drop-down menu:
•
CENTER
•
APPROACH
•
TOWER
•
FINAL
•
GROUND CONTROL
•
CLEARANCE DELIVERY
•
DEPARTURE
•
CONTROL
RADIO
•
NONE
•
•
NAVAID
Invalid Entry
•
AIRPORT
•
FIX
•
LAT/LONG
All data fields that require a manual input are checked by the DLCA
application to ensure they are within limits. These limits vary depending
on what information is being input.
•
PLACE/BEARING/DIST
Copyright © Bombardier Inc.
CS130-21.12-06.00-121418
Whenever an input is outside the set limit, an invalid entry message is
displayed in yellow, and the information needs to be input again.
TECHNICAL TRAINING MANUAL
For Training Purposes Only
23-20
23 - Communication
23-22 Controller-Pilot Data Link Communications – LINK2000+
(Option)
MSG LOG
DLK
LK
CPDLC
CPDLC
C
SETTINGS
NGS
REQUEST
DLK
LK
REPORT
MSG LOG
35000
SETTINGS
SETTINGS
NGS
REQUES
REQUEST
UEST
TUNE
TUN
NE
REPORT
/
-----
DIRECT TO POS
NONE
MSG
G LOGG
FACILITY NAME
VHF
FACILITY
SET
REQUEST CLIMB TO 35000 FT
TUNE
TUN
NE
SEND
CANCEL
CANC
CANCE
ANCELL
ALTITUDE/SPEED/OFFSET
DLK
LK
CPDLC
CPDLC
C
MSG
SG LOGG SETTINGS
SETTINGS
NGS
OFFSET REQUEST
OFFSET
REQUES
REQUEST
UEST
REPORT
REQUES
REQUEST
UEST
EDDF
FRANKFURT MAIN
120.800
APPROACH
CENTER
APPROACH
TOWER
FINAL
GROUND CONTROL
CLEARANCE DELIVERY
DEPARTURE
CONTROL
RADIO
DUE TO WX
DUE TO A/C PERF
ROUTE
CLEAR
CLEAR
EAR
CPDLC
SETTINGS
FACILITY DESIGNATION
NONE
NAVAID
AIRPORT
FIX
LAT/LON
PLACE/BEARING/DIST
DUE TO WX
DUE TO A/C PERF
DLK
LK
MONITORING
ROUTE REQUEST
ALTITUDE REQUEST
ALT/ALT BLOCK
CPD
CPDLC
PDLC
C
CLEAR
CLEAR
EAR
REPORT
SET
MONITORING EDDF FRANKFURT MAIN APPROACH 120.800
300E
INVALID ENTRY
INVALID ENTRY
SEND
END
CANCEL
CANCE
L
MONITORING
CS1_CS3_2322_033
TUNE
TUN
NE
Figure 9: CPDLC REQUEST Pages
Copyright © Bombardier Inc.
CS130-21.12-06.00-121418
TECHNICAL TRAINING MANUAL
For Training Purposes Only
23-21
23 - Communication
23-22 Controller-Pilot Data Link Communications – LINK2000+
(Option)
UPLINK SCENARIO
Uplink messages that require a response can be responded to using
either the CNS CPDLC page, or the data link inbox using the
quick-response controls.
CNS Page Method
Selecting the new uplink message in the MSG LOG page allows the user
to send a response. A new window is displayed with the following
buttons:
•
ACCEPT
•
STANDBY
•
REJECT
The REJECT button is located in a box with a choice of checkboxes. By
selecting the appropriate checkbox, information is provided as to why
the uplink message request was rejected. Depending on whether a
response is required, the message status changes to OPEN or
CLOSED.
Copyright © Bombardier Inc.
CS130-21.12-06.00-121418
TECHNICAL TRAINING MANUAL
For Training Purposes Only
23-22
23 - Communication
23-22 Controller-Pilot Data Link Communications – LINK2000+
(Option)
MSG LOG
UTC
TUNE
TUNEE
TUN
TUNE
TUN
NE
REQUESTT
22:03
UTC 22:03-EGTT
SQUAWK IDENT
UTC 22:01-EGTT
WHY NOT
UTC 22:00-EGTT
MAINTAIN 250 KT IAS OR LESS
UTC 21:58-EGTT
MAINTAIN FL350
FILTER
MSG LOG
REPORT
REQUESTT
MSG LOG
REPORT
UTC 22:03-EGTT
SQUAWK IDENT
ALL
OPEN
DLK
CPDLC
SETTINGS
REQUEST
TUNE
TUN
NE
REPORT
UTC 22:03-EGTT
SQUAWK IDENT
NEW
CLOSED
ACCEPTED
RESPONSE HISTORY
REJECT, DUE TO WEATHER
ACCEPTED
REJECTED
MSG LOG
UTC
REQUEST
STT
22:04
UTC 22:03-EGTT
SQUAWK IDENT
UTC 22:01-EGTT
WHY NOT
UTC 22:00-EGTT
MAINTAIN 250 KT IAS OR LESS
UTC 21:58-EGTT
MAINTAIN FL350
FILTER
REPORT
ALL
REJECTED
CLOSED
ACCEPTED
ACCEPTED
ACCEPT
STANDBY
DUE TO WX
DUE TO A/C PERF
----------------------------------------------------------------
REJECT
PRINT
RESPONSE SELECTIONS
MESSAGE HISTORY
UPDATED MESSAGE STATUS
CS1_CS3_2322_027
NEW MESSAGE SELECTION
Figure 10: CNS Page Uplink Scenario
Copyright © Bombardier Inc.
CS130-21.12-06.00-121418
TECHNICAL TRAINING MANUAL
For Training Purposes Only
23-23
23 - Communication
23-22 Controller-Pilot Data Link Communications – LINK2000+
(Option)
WHEN CAN YOU Scenario
A WHEN CAN YOU type of uplink message has a unique response
format. When the message is selected in the MSG LOG page, a
downlink message page is displayed. A drop-down menu allows the user
to choose WE CAN or WE CAN NOT as a response with a box for the
UTC time.
Copyright © Bombardier Inc.
CS130-21.12-06.00-121418
TECHNICAL TRAINING MANUAL
For Training Purposes Only
23-24
23 - Communication
23-22 Controller-Pilot Data Link Communications – LINK2000+
(Option)
DLK
TUNE
MSG LOG
UTC
SETTINGS
CPDLC
REQUEST
22:33
DLK
TUNE
FILTER
REPORT
ALL
UTC 22:34-EGTT
NEW
WHEN CAN YOU ACCEPT 10000 FT
UTC 22:33-EGTT
NEW
CROSS YUL AT OR BELOW FL250
UTC 22:34-EGTT
STANDBY
SQUAWK 1220
UTC 22:34-EGTT
OPEN
MAINTAIN 0.780 MACH OR LESS
UTC 22:33-EGTT
REJECTED
DESCEND TO REACH FL210 BY 1200Z
UTC 22:31-EGTT
ACCEPTED
PROCEED DIRECT TO DOTTY
UTC 22:30-EGTT
ACCEPTED
DESCEND TO REACH FL210 BY 0000Z
UTC 22:29-EGTT
CLOSED
REQUEST DIRECT TO DOTTY
UTC 22:28-EGTT
TIMEDOUT
PROCEED DIRECT TO EGTT
UTC 22:27-EGTT
ACCEPTED
FLY HEADING 270° M
UTC 22:26-EGTT
CLOSED
REQUEST DIRECT TO EGTT, DUE TO WEATHER, DUE
UTC 22:25-EGTT
ACCEPTED
MAINTAIN 0.800 MACH
MSG LOG
SETTINGS
CPDLC
TUNE
REQUEST
REPORT
UTC 22:34-EGTT
WHEN CAN YOU ACCEPT 10000 FT
RESPONSE
WE CAN
SETTINGS
CPDLC
REQUEST
MSG LOG
REPORT
OPEN
AT UTC
- DOWNLINK SET MESSAGES
CANCEL - CLEAR SET MESSAGES
CLEAR
SET
CLEAR
SET
WE CAN ACCEPT 10000 FT AT 2315Z
SEND
CANCEL
UTC
SETTINGS
22:35
CPDLC
REQUEST
FILTER
REPORT
ALL
UTC 22:34-EGTT
STANDBY
SQUAWK 1220
UTC 22:35-EGTT
CLOSED
WE CAN ACCEPT 10000 FT AT 2315Z
UTC 22:34-EGTT
ACCEPTED
WHEN CAN YOU ACCEPT 10000 FT
UTC 22:34-EGTT
TIMEDOUT
MAINTAIN 0.780 MACH OR LESS
UTC 22:33-EGTT
TIMEDOUT
CROSS YUL AT OR BELOW FL250
UTC 22:33-EGTT
REJECTED
DESCEND TO REACH FL210 BY 1200Z
UTC 22:31-EGTT
ACCEPTED
PROCEED DIRECT TO DOTTY
UTC 22:30-EGTT
ACCEPTED
DESCEND TO REACH FL210 BY 0000Z
UTC 22:29-EGTT
CLOSED
REQUEST DIRECT TO DOTTY
UTC 22:28-EGTT
TIMEDOUT
PROCEED DIRECT TO EGTT
UTC 22:27-EGTT
ACCEPTED
FLY HEADING 270° M
UTC 22:26-EGTT
CLOSED
REQUEST DIRECT TO EGTT, DUE TO WEATHER, DUE
SEND
RESPONSE CONFIRMATION
UPDATED MESSAGES STATUS
CS1_CS3_2322_032
RESPONSE SELECTIONS
DLK
TUNE
UTC 22:34-EGTT
WHEN CAN YOU ACCEPT 10000 FT
SEND
AT UTC
WE CAN
WE CAN NOT
CANCEL
WHEN CAN YOU UPLINK SELECTED
MSG LOG
OPEN
DLK
Figure 11: WHEN CAN YOU Scenario
Copyright © Bombardier Inc.
CS130-21.12-06.00-121418
TECHNICAL TRAINING MANUAL
For Training Purposes Only
23-25
23 - Communication
23-22 Controller-Pilot Data Link Communications – LINK2000+
(Option)
Quick-Response Control Method
When the data link inbox and quick-response controls are used, uplink
messages are responded to in one step using the appropriate response.
The available quick-response controls are the only ones that send a
response and are highlighted blue at the right of the data link inbox.
The downlink message status is either OPEN or CLOSED depending on
whether a response is required.
Copyright © Bombardier Inc.
CS130-21.12-06.00-121418
TECHNICAL TRAINING MANUAL
For Training Purposes Only
23-26
23 - Communication
23-22 Controller-Pilot Data Link Communications – LINK2000+
(Option)
CLB
CLB
92.2
92.2
92.2
92.2
73.0
73.3
73.0
73.3
N1
N1
718
722
718
EGT
86.5
1090
124
116
722
EGT
86.6
1110
124
116
N2
FF (KPH)
OIL TEMP
OIL PRESS
86.5
1090
124
116
ACPT
LOAD
86.6
1110
124
116
N2
FF (KPH)
OIL TEMP
OIL PRESS
STBY
2735
5435
1400
5.7
ELEV 570
2735
CAB ALT
RATE
∆P
CREW
LDG
TEMP
(°C)
24
0
OXY 1850
HI
23
2735
RJCT
TRIM
GLARESHIELD
NU
ND
NL RUDDER NR
CPDLC
UTC 22:33-EGTT
NEW 1
DESCEND TO REACH FL210 BY 1200Z
1400
5.7
ELEV 570
INFO
OF 1
ACPT
STBY
LOAD
RJCT
2735
RATE
∆P
CREW
TEMP
(°C)
4.2
5435
CAB ALT
LDG
STAB
23
10905
TOTAL FUEL (KG)
24
0
OXY 1850
TRIM
NU
STAB
HI
23
23
ND
4.2
NL RUDDER NR
CPDLC
UTC 22:33-EGTT
REJECTED 1
DESCEND TO REACH FL210 BY 1200Z
INFO
OF 1
ACPT
STBY
LOAD
RJCT
CS1_CS3_2322_029
10905
TOTAL FUEL (KG)
Figure 12: Quick-Response Uplink Scenario
Copyright © Bombardier Inc.
CS130-21.12-06.00-121418
TECHNICAL TRAINING MANUAL
For Training Purposes Only
23-27
23 - Communication
23-22 Controller-Pilot Data Link Communications – LINK2000+
(Option)
DOWNLINK SCENARIO
Downlink messages can only be sent using the CNS CPDLC page.
Using the REQUEST submenu allows for the selection of the proper
downlink message page.
When the downlink message is sent, its status is PENDING until it is
received by ATC, then CLOSED if no response is required. In the case of
a downlink message requiring a response, the message status is OPEN.
The message status is available on the MSG LOG page.
Once a response is received, the downlink message status changes to
CLOSED. Depending on the uplink message response, further action
may be required.
Copyright © Bombardier Inc.
CS130-21.12-06.00-121418
TECHNICAL TRAINING MANUAL
For Training Purposes Only
23-28
23 - Communication
23-22 Controller-Pilot Data Link Communications – LINK2000+
(Option)
REQUEST Menu for
FANS 1/A
MSG
SG LOG
LOG
DLK
CPDLC
SETTING
SETTINGS
ETTINGS
S
REQUEST
TUNE
TUN
E
REPORT
ALTITUDE
UTC 22:17
FILTER
ALL
OFFSET
SPEED
UTC 22:16-EGTT
OPEN
REQUEST BLOCK FL310 TOROUTE
FL350, DUE TO
UTC 22:16-EGTT
CLOSED/UNVIEWED
D/UNVIEWED
MONITORING
REQUEST FORWARDED
UTC 22:10-EGTT
TIMEDOUT
OFFSET 1 NM LEFT OF ROUTE
UTC 22:06-EGTT
TIMEDOUT
REPORT PRESENT LEVEL
UTC 22:05-EGTT
ACCEPTED
SQUAWK IDENT
UTC 22:04-EGTT
REJECTED
SQUAWK IDENT
UTC 22:03-EGTT
REJECTED
SQUAWK IDENT
UTC 22:01-EGTT
CLOSED
WHY NOT
UTC 22:00-EGTT
ACCEPTED
MAINTAIN 250 KT IAS OR LESS
DLK
MSG LOG
SETTINGS
GS
REQUEST
REPORT
MSG LOG
ALTITUDE REQUEST
ALT/ALT BLOCK
35000
UTC
/
-----
DUE TO WX
DUE TO A/C PERF
CLEAR
SET
REQUEST CLIMB TO 35000 FT
CANCEL
CANC
CANCE
CEL
REQUEST PAGE SELECTION
DLK
TUNEE
TUN
CPDLC
SETTINGS
22:18
CPDLC
DLC
REQUESTT
FILTER
REPORT
ALL
UTC 22:18-EGTT
PENDING
REQUEST CLIMB TO 35000 FT
UTC 22:16-EGTT
OPEN
REQUEST BLOCK FL310 TO FL350, DUE TO
UTC 22:16-EGTT
CLOSED/UNVIEWED
REQUEST FORWARDED
UTC 22:10-EGTT
TIMEDOUT
OFFSET 1 NM LEFT OF ROUTE
UTC 22:06-EGTT
TIMEDOUT
REPORT PRESENT LEVEL
UTC 22:05-EGTT
ACCEPTED
SQUAWK IDENT
UTC 22:04-EGTT
REJECTED
SQUAWK IDENT
UTC 22:03-EGTT
REJECTED
SQUAWK IDENT
UTC 22:01-EGTT
CLOSED
WHY NOT
UTC 22:00-EGTT
ACCEPTED
MAINTAIN 250 KT IAS OR LESS
SEND
DOWNLINK REQUEST SELECTIONS
MSG LOG PAGE WITH DOWNLINK MESSAGE
CS1_CS3_2322_028
TUNE
TUN
NE
Figure 13: Downlink Scenario
Copyright © Bombardier Inc.
CS130-21.12-06.00-121418
TECHNICAL TRAINING MANUAL
For Training Purposes Only
23-29
23 - Communication
23-22 Controller-Pilot Data Link Communications – LINK2000+
(Option)
MONITORING AND TESTS
The following page contains the crew alerting system (CAS) messages
for the CPDLC LINK2000+ system.
Copyright © Bombardier Inc.
CS130-21.12-06.00-121418
TECHNICAL TRAINING MANUAL
For Training Purposes Only
23-30
23 - Communication
23-22 Controller-Pilot Data Link Communications – LINK2000+
(Option)
CAS MESSAGES
Table 3: ADVISORY Messages
MESSAGE
DATALINK FAIL
DATALINK
STATUS
>CPDLC
LOGIC
Message appears in the event of one of the following:
•
Data link RIU reports a CMU failure
•
CMU power module failure
•
ECU failure
•
CPDLC installed and data link RIU failed/lost
connection
•
DLCA failed and IPC/CCM working/powered
Message appears in the event of one of the following:
•
ATN network is not available for the aircraft to
connect
•
AFN link is established and the active
communication link has not been available for
16 minutes
•
AFN link is established and the flight ID is
changed by the crew
ATN or FANS message received and not viewed.
Copyright © Bombardier Inc.
CS130-21.12-06.00-121418
TECHNICAL TRAINING MANUAL
For Training Purposes Only
23-31
23 - Communication
23-22 Controller-Pilot Data Link Communications – LINK2000+
(Option)
Page Intentionally Left Blank
Copyright © Bombardier Inc.
CS130-21.12-06.00-121418
TECHNICAL TRAINING MANUAL
For Training Purposes Only
23-32
ATA 23 - Communication
Controller-Pilot Data Link
Communications – FANS 1/A+
(Option)
BD-500-1A10
BD-500-1A11
23 - Communication
23-22 Controller-Pilot Data Link Communications – FANS 1/A+
(Option)
Table of Contents
23-22 Controller-Pilot Data Link
Communications – FANS 1/A+.....................................23-2
Introduction .......................................................................23-2
FANS 1/A+ .......................................................................23-2
General Description ..........................................................23-4
Data Link Communication Application ..............................23-6
ACARS Convergence Function ...................................23-6
Air Traffic Services Facilities Notification .....................23-6
Automatic Dependent Surveillance - Contract .............23-6
Controls and Indications ...................................................23-8
Controls........................................................................23-8
Indications..................................................................23-10
Operation ........................................................................23-12
CNS CPDLC Menu Page...........................................23-12
MSG Log....................................................................23-14
SETTINGS Menu .......................................................23-18
REQUEST Pages ......................................................23-26
REPORT Menu ..........................................................23-40
Uplink Messages........................................................23-44
Downlink Message.....................................................23-52
Monitoring and Tests ......................................................23-54
CAS Messages ..........................................................23-55
Copyright © Bombardier Inc.
CS130-21.12-06.00-121418
TECHNICAL TRAINING MANUAL
For Training Purposes Only
23-i
23 - Communication
23-22 Controller-Pilot Data Link Communications – FANS 1/A+
(Option)
List of Figures
Figure 1: CPDLC FANS 1/A+ Introduction ...........................23-3
Figure 2: CPDLC FANS 1/A+ General Description ..............23-5
Figure 3: CPDLC FANS 1/A+ DLCA.....................................23-7
Figure 4: CPDLC Controls....................................................23-9
Figure 5: CPDLC Indications ..............................................23-11
Figure 6: CPDLC Menu ......................................................23-13
Figure 7: MSG LOG - MSG REVIEW Page........................23-15
Figure 8: SETTINGS - LOGON/STATUS Page..................23-19
Figure 9: SETTINGS - ADS REPORT................................23-21
Figure 10: SETTINGS - EMERGENCY MESSAGE
Page ...................................................................23-23
Figure 11: SETTINGS - SYSTEM INFO Page ....................23-25
Figure 12: REQUEST - ALTITUDE/OFFSET/SPEED
REQUEST/VMC DESCENT REQUEST ............23-27
Figure 13: REQUEST - ROUTE REQUEST Page ..............23-29
Figure 14: REQUEST - CLEARANCE REQUEST
Page ...................................................................23-31
Figure 15: REQUEST - WHEN CAN WE Page ...................23-33
Figure 16: REQUEST - REQUEST VOICE CONTACT
Page ...................................................................23-35
Figure 17: REQUEST - FREE TEXT Page ..........................23-37
Figure 18: REQUEST - MONITORING Page ......................23-39
Figure 19: REPORT - POSITION REPORT Page ...............23-41
Figure 20: REPORT - REPORTS DUE Page ......................23-43
Figure 21: Uplink Message ..................................................23-45
Copyright © Bombardier Inc.
CS130-21.12-06.00-121418
Figure 22: Uplink Message with Loadable FMS
Content .............................................................. 23-47
Figure 23: WHEN CAN YOU Uplink Message .................... 23-49
Figure 24: Quick-Response Uplink Message ...................... 23-51
Figure 25: Downlink Message ............................................. 23-53
TECHNICAL TRAINING MANUAL
For Training Purposes Only
23-ii
23 - Communication
23-22 Controller-Pilot Data Link Communications – FANS 1/A+
(Option)
Page Intentionally Left Blank
Copyright © Bombardier Inc.
CS130-21.12-06.00-121418
TECHNICAL TRAINING MANUAL
For Training Purposes Only
23-iii
23 - Communication
23-22 Controller-Pilot Data Link Communications – FANS 1/A+
(Option)
CONTROLLER-PILOT DATA LINK
COMMUNICATIONS – FANS 1/A+
Copyright © Bombardier Inc.
CS130-21.12-06.00-121418
TECHNICAL TRAINING MANUAL
For Training Purposes Only
23-1
23 - Communication
23-22 Controller-Pilot Data Link Communications – FANS 1/A+
(Option)
23-22 CONTROLLER-PILOT DATA LINK
COMMUNICATIONS – FANS 1/A+
INTRODUCTION
Controller-pilot data link communications (CPDLC) provides digital text
communication between the aircraft and air traffic control (ATC). This
reduces the need for voice communications required to perform routine
ATC instructions and requests. The use of CPDLC provides the following
benefits:
•
Decreased workload for ground controllers and aircrew
•
Increased air safety
•
Elimination of ambiguous voice transmissions
•
Reduction of communication frequency congestion
uses satellite communications (SATCOM) to send and receive
messages.
The information is displayed in the data link inbox, located on the engine
indication and crew alerting system (EICAS). The information can also
be viewed on the radio tuning system application (RTSA) page.
Fixed format text message responses are selectable using the RTSA
page or the quick-response controls located on the glareshields. Free
format text messages are enabled by using the RTSA page only.
FANS 1/A+
CPDLC future air navigation systems (FANS 1/A+) uses the aircraft
communications addressing and reporting system (ACARS) network to
establish communication between the aircraft and air traffic control
(ATC).
FANS 1/A+ provides the aircraft with a ground communications system
primarily in North Atlantic and South Pacific Oceanic airspace.
FANS 1/A+ also provides communication in continental airspaces which
are beyond the range of ground based ATC radar and VHF
communications.
A data link service provider subscription is required to access the
FANS 1/A+ network.
The CPDLC FANS 1/A+ system uses radio interface unit (RIU) 1 to
process information sent between the aircraft and ATC. Very high
frequency (VHF) 3 is used in data mode to transmit and receive the text
data. When the aircraft is out of VHF communication range, the system
Copyright © Bombardier Inc.
CS130-21.12-06.00-121418
TECHNICAL TRAINING MANUAL
For Training Purposes Only
23-2
23 - Communication
23-22 Controller-Pilot Data Link Communications – FANS 1/A+
(Option)
CLB
DLK
TUNE
92.2
92.2
73.0
73.3
MSG LOG
CPDLC
SETTINGS
REQUEST
REPORT
LOGON/STATUS
N1
NETWORK
718
FANS 1/A
722
ATC DL
ENABLED
EGT
ACPT
LOAD
OIL TEMP
OIL PRESS
2735
12345678901234567890
MSG
ROUTE
D
DEP/
ARR
CNCL
EXEC
CLR/
DEL
RJCT
E
N
T
E
R
SP
MAP
FMS
CNS
PREV
CHKL
SYN
DATA
CAS
GLARESHIELD
5435
1400
5.7
ELEV 570
0
RATE
∆P
CREW OXY 1850
TEMP
(°C)
24
KICT
TRIM
23
23
END OF FLIGHT
BBA503
LOGON TO
NU
ND
LOGON REQUIRED
4.2
NL RUDDER NR
CPDLC
NEW
UTC 10:20-KDTW
CLIMB TO 24000 FT
1
SEND LOGON
INFO
OF 1
ACPT
STBY
LOAD
RJCT
ATC ATN AVAILABLE
NO ATC COMM
RTSA
EICAS
SATCOM
DMC 1 and DMC 2
ARR
STAB
HI
NEXT
MULTIFUNCTION
KEYBOARD
KICT
FLT ID
2735
CAB ALT
LDG
DEPT
10905
TOTAL FUEL (KG)
STBY
CDA ---------NDA ----------
86.6
1110
124
116
N2
FF (KPH)
SATCOM
ANTENNA
RIU 1
VHF 3
VHF ANTENNA
CS1_CS3_2322_040
86.5
1090
124
116
Figure 1: CPDLC FANS 1/A+ Introduction
Copyright © Bombardier Inc.
CS130-21.12-06.00-121418
TECHNICAL TRAINING MANUAL
For Training Purposes Only
23-3
23 - Communication
23-22 Controller-Pilot Data Link Communications – FANS 1/A+
(Option)
GENERAL DESCRIPTION
The CPDLC FANS 1/A+ system enables fixed and free format text
communication with ATC using downlink and uplink messages. Downlink
messages are sent by the aircraft. Uplink messages are sent by ATC
and are displayed on the EICAS page.
Engine indication and crew alerting system (EICAS) advisory messages
are displayed when faults are detected that affect the CPDLC system.
Advisory messages are displayed when uplink messages are received
and are not viewed or acknowledged.
Fixed format responses can be selected from the quick-response
controls on the glareshield. Both fixed or free format responses can be
sent though the RTSA page by selecting the CPDLC tab. Information is
entered by selecting a field and using the multifunction keyboard panel
(MKP).
When the aircraft is within VHF service range, messages are transmitted
and received using the VHF data link mode A and 2 through the VHF 3
transceiver. The transceiver uses RIU 1 for processing information that
can be transmitted and received over VHF.
The communication management card in the RIU routes the message to
the appropriate radio system.
A CPDLC chime sounds whenever an uplink message is received.
Message management is done by the data link communication
application (DLCA) in the integrated processing cabinet (IPC) 1.
The protocol management application (PMA) allows the RIU to
communicate with the DLCA. The PMA also allows the DLCA to
interface with the flight management system application (FMSA) which is
located in IPC 1. This allows uplink messages that have FMS loadable
elements to be uploaded into the flight plan.
The message transmissions are stored in the cockpit voice recorder
(CVR) through the data concentrator unit module cabinet (DMC) 2.
If the optional printer is installed in the flight deck, the messages can be
printed. The RIU 1 provides the interface with the printer.
Copyright © Bombardier Inc.
CS130-21.12-06.00-121418
TECHNICAL TRAINING MANUAL
For Training Purposes Only
23-4
23 - Communication
23-22 Controller-Pilot Data Link Communications – FANS 1/A+
(Option)
RANGE
BRT
INBD DSPLY
L
MENU
R
ACPT
MAP
FMS
CNS
CHKL
SYN
DATA
LOAD
OUTBD
INBD
STBY
CHRONO
RJCT
CAUTION
EICAS
RTSA
CLB
MSG LOG
73.3
NETWORK
ATC DL
OIL TEMP
OIL PRESS
10905
5435
2735
CAB ALT
RATE
∆P
CREW
24
<CLOCK
PFD/NAV>
IDENT
<STBY NAV
HUD>
HPA
1/2
TUNE/DATA
CRS 126
NAV
SRC
LEFT CTP
REQUEST
0
OXY 1850
ENABLED
DEPT
KICT
ARR
KICT
FLT ID
TRIM
END OF FLIGHT
23
23
INTEGRATED
PROCESSING CABINET 1
Data Link
Communication
Application
Protocol
Management
Application
BBA503
FMSA
LOGON TO
NU
LOGON REQUIRED
STAB
HI
REPORT
FANS 1/A
CDA ---------NDA ----------
86.6
1110
124
116
N2
FF (KPH)
TOTAL FUEL (KG)
TEMP
(°C)
SETTINGS
722
EGT
LDG
TUNE/
MENU
ND
4.2
CPDLC
UTC 10:20-KDTW
CLIMB TO 24000 FT
NL RUDDER NR
SEND LOGON
INFO
NEW 1 OF 1
ACPT
STBY
LOAD
RJCT
ATC ATN AVAILABLE
NO ATC COMM
DMC 1
and
DMC 2
COCKPIT VOICE RECORDER
12345678901234567890
MSG
ROUTE
D
DEP/
ARR
CNCL
EXEC
CLR/
DEL
E
N
T
E
R
SP
LEGEND
AFDX
ARINC 429
Discrete
MAP
FMS
CNS
PREV
CHKL
SYN
DATA
CAS
MULTIFUNCTION
KEYBOARD
PRINTER
(Optional)
RADIO
INTERFACE
UNIT 1
Communication
Management
Unit
Uplink/Downlink Messages
VHF 3
NEXT
Chime
SATCOM
CS1_CS3_2322_041
718
1400
5.7
ELEV 570
ON/OFF>
CPDLC
LOGON/STATUS
N1
2735
DLK
<WXR
RETURN
WX
OFF
92.2
73.0
86.5
1090
124
116
BRT
BARO
LEFT GLARESHIELD PANEL
TUNE
92.2
IN
TFC
WARNING
OFF
TERR
FPV CAGE
Figure 2: CPDLC FANS 1/A+ General Description
Copyright © Bombardier Inc.
CS130-21.12-06.00-121418
TECHNICAL TRAINING MANUAL
For Training Purposes Only
23-5
23 - Communication
23-22 Controller-Pilot Data Link Communications – FANS 1/A+
(Option)
DATA LINK COMMUNICATION APPLICATION
AUTOMATIC DEPENDENT SURVEILLANCE - CONTRACT
In addition to CPDLC, the data link communication application (DLCA)
hosts the following function that are used in FANS 1/A+ operation:
ADS-C is a means of airborne surveillance that uses data link to transmit
flight information report to an ATC facility automatically. Contracts are
issued by ATC and contain requests for aircraft position and flight
information.
•
ACARS convergence function (ACF)
•
Air traffic services facilities notification (AFN)
•
Automatic dependent surveillance - contract (ADS-C)
When a contract is established, the information requested is
automatically sent by the DLCA when the conditions for reporting them
are met.
ACARS CONVERGENCE FUNCTION
There are three types of ADS-Cs:
The AFC converts the binary oriented protocol used by the ADS-C and
CPDLC applications into ACARS character oriented protocol. This
allows the information to be transmitted and received on the ACARS
network used by FANS.
•
Periodic contract ─ The aircraft transmits a report containing the
applicable information at the interval specified in the contract request
•
Event contract ─ A report with specific information is sent when
triggered by an event. Event contracts are independent of any
periodic contract that are in effect
•
On demand contract ─ On demand contracts send a report
whenever initiated by the ATSU
AIR TRAFFIC SERVICES FACILITIES NOTIFICATION
The ATS facilities notification (AFN) consists of the protocol used to
establish data link communication between the aircraft and an air traffic
services unit (ATSU). When the required information has been sent and
received by ATSU, the communication link is established and logon is
achieved.
The AFN also enables the active ATSU to provide a notification to the
next ATSU that the aircraft needs to make contact with. This prevents
loss of communications which would cause the need to logon to the
FANS network unnecessarily.
When a data link connection is established with two ATSUs, the active
one is called the current data authority (CDA). The standby ATSU is
called the next data authority (NDA).
Once the NDA has satisfied the protocol, it becomes the CDA and sends
a message to the old CDA to end communication with the aircraft.
The AFN does not require the ACF since it communicates using the
same protocol as ACARS.
Copyright © Bombardier Inc.
CS130-21.12-06.00-121418
TECHNICAL TRAINING MANUAL
For Training Purposes Only
23-6
23 - Communication
23-22 Controller-Pilot Data Link Communications – FANS 1/A+
(Option)
INTEGRATED
PROCESSING CABINET 1
DLCA
CPDLC
ADS-C
AFN
ACF
PMA
ACARS Convergence Function
Automatic Dependent Surveillance-Contract
ATC Facilities Notification
Controller-Pilot Data Link Communications
Data Link Communication Application
Protocol Manager Application
AFDX
Bit Oriented Protocol
Character Oriented Protocol
To
DMC 1
and
DMC 2
CS1_CS3_2322_042
LEGEND
ACF
ADS-C
AFN
CPDLC
DLCA
PMA
Figure 3: CPDLC FANS 1/A+ DLCA
Copyright © Bombardier Inc.
CS130-21.12-06.00-121418
TECHNICAL TRAINING MANUAL
For Training Purposes Only
23-7
23 - Communication
23-22 Controller-Pilot Data Link Communications – FANS 1/A+
(Option)
CONTROLS AND INDICATIONS
CONTROLS
Quick-Response Panel
The quick-response panels allow a quick answer to received data link
messages. Quick-response buttons are used to respond to the CPDLC
uplink message that is displayed in the data link inbox. The buttons
provide the following functions:
•
ACPT: Sends an affirmative response such as WILCO, ROGER,
AFFIRM
•
STBY: Requests more time to analyze and answer the ATC request
•
RJCT: Sends a negative response such as UNABLE
•
LOAD: Allows the loadable message elements to be uploaded to the
flight management system (FMS) when received in an uplink
message
•
REFRESH (icon): Displays the latest received message or removes
a closed message from the inbox
Copyright © Bombardier Inc.
CS130-21.12-06.00-121418
TECHNICAL TRAINING MANUAL
For Training Purposes Only
23-8
23 - Communication
23-22 Controller-Pilot Data Link Communications – FANS 1/A+
(Option)
ACPT
LOAD
STBY
RJCT
QUICK-RESPONSE PANEL
QUICK RESPONSE PANEL
Function
ACPT
Initiates the ACCEPTED function.
STBY
Initiates the STANDBY function.
RJCT
Initiates the REJECTED function.
LOAD
Sends the loadable elements of an uplink message to the FMS.
Displays the last received message or
removes a closed message from the box.
CS1_CS3_2322_039
Quick Release Buttons
Figure 4: CPDLC Controls
Copyright © Bombardier Inc.
CS130-21.12-06.00-121418
TECHNICAL TRAINING MANUAL
For Training Purposes Only
23-9
23 - Communication
23-22 Controller-Pilot Data Link Communications – FANS 1/A+
(Option)
INDICATIONS
The data link inbox provides a convenient location to view recent CPDLC
uplink messages. Messages can be responded to via the
quick-response panel.
Data link inbox status messages at the bottom of the data link inbox
provide indications of faults in the CPDLC system. The following
messages may be displayed:
The CPDLC tile is posted and a chime sounds when a CPDLC message
is received. The CPDLC tile remains in view until the message has been
viewed on the radio system tuning application (RTSA), or a response is
sent.
•
NO COMM – Indicates that the DLCA is not operating
•
NO ATC COMM – Indicates that connection with ATC is not
established
•
NO RIU COMM – Indicates that the protocol manager application
(PMA) is not communicating with the RIU
•
CPDLC INHIBITED – SEE CPDLC – This message is displayed
whenever a CAS message related to CPDLC is indicated
The tile is cleared when a message is read and there is no new CPDLC
uplink message present.
Messages are accompanied with a header that includes a UTC time
stamp, the ATC code, and an arrow pointing either up or down. Uplink
messages are accompanied by an arrow pointing up. Downlink
messages are accompanied by an arrow pointing down.
When the EICAS display is in the compressed mode the data link inbox
is not shown.
Message headers are displayed in cyan. Once the messages are
accepted or rejected, they change to white.
The data link inbox response button indicators are located to the right of
the messages. Each indicator is associated with a quick-response
control button on the glareshield. The indicators are displayed in three of
the following states:
•
Active – The active state indicates that the corresponding button is
available for selection
•
Inactive – The inactive state indicates that the corresponding button
is not available. Pressing the button does not have any effect
•
Disabled – The disabled state indicates that the corresponding
button is disabled due to a problem with the system. Pressing the
button has no effect
Copyright © Bombardier Inc.
CS130-21.12-06.00-121418
TECHNICAL TRAINING MANUAL
For Training Purposes Only
23-10
23 - Communication
23-22 Controller-Pilot Data Link Communications – FANS 1/A+
(Option)
1400
5.7
ELEV 570
CAB ALT
RATE
ó3
CREW
LDG
7(03
(°C)
24
0
OXY 1850
CPDLC
Tile
TRIM
NU
Message
Status
STAB
HI
23
23
4.2
ND
NL RUDDER NR
&3'/&
NEW 1
UTC 10:20-KDTW
CLIMB TO 24000 FT
Message
Header
INFO
OF 1
$&37
STBY
LOAD
RJCT
Response
Indicators
Data
Link
Inbox
NO COMM
EICAS
DATA LINK INBOX RESPONSE INDICATORS
Symbol
State
Description
$&37
Active
Button is available for selection.
$&37
Inactive
Button is not available.
Pressing the button does not have any effect.
$&37
Disabled
Button is disabled due to a problem with the system.
Pressing the button has no effect.
Data Link Inbox
Status Message
DATA LINK INBOX STATUS MESSAGES
Symbol
Description
NO COMM
DLCA is not operating.
NO ATC COMM
Connection with ATC is not established.
NO RIU COMM
PMA is not communicating with the RIU.
CPDLC CAS message is displayed.
CS1_CS3_2323_001
&3'/&,1+,%,7('6((&3'/&
Figure 5: CPDLC Indications
Copyright © Bombardier Inc.
CS130-21.12-06.00-121418
TECHNICAL TRAINING MANUAL
For Training Purposes Only
23-11
23 - Communication
23-22 Controller-Pilot Data Link Communications – FANS 1/A+
(Option)
OPERATION
CNS CPDLC MENU PAGE
REQUEST
The communication, navigation, and surveillance (CNS) button provides
access to the CPDLC menu page. The CPDLC menu page defaults to
the LOGON submenu. The following menus are available in the CPDLC
CNS page:
The REQUEST menu tab provides access to a drop-down menu with the
following options:
•
ALTITUDE
•
OFFSET
•
SPEED
•
ROUTE
•
CLEARANCE
•
VMC DESCENT
MSG LOG
•
WHEN CAN WE
The message log menu tab provides access to the message review
submenu which enables access to previous messages.
•
VOICE REQ
•
FREE TEXT
SETTINGS
•
MONITORING
The settings menu tab provides access to a drop-down menu with the
following options.
REPORT
•
LOGON
•
ADS
The REQUEST menu tab provides access to a drop-down menu with the
POSITION REP and the REPORTS DUE selections.
•
EMERGENCY
•
SYSTEM INFO
•
MSG LOG
•
SETTINGS
•
REQUEST
•
REPORT
Copyright © Bombardier Inc.
CS130-21.12-06.00-121418
TECHNICAL TRAINING MANUAL
For Training Purposes Only
23-12
23 - Communication
23-22 Controller-Pilot Data Link Communications – FANS 1/A+
(Option)
CNS
CPDLC
MSG LOG
MSG REVIEW
SETTINGS
LOGON
REQUEST
REPORT
ALTITUDE
POSITION REP
OFFSET
REPORT DUE
SPEED
ADS
ROUTE
EMERGENCY
CLEARANCE
SYSTEM INFO
VMC DESCENT
WHEN CAN WE
FREE TEXT
MONITORING
CS1_CS3_2322_043
VOICE REQ
Figure 6: CPDLC Menu
Copyright © Bombardier Inc.
CS130-21.12-06.00-121418
TECHNICAL TRAINING MANUAL
For Training Purposes Only
23-13
23 - Communication
23-22 Controller-Pilot Data Link Communications – FANS 1/A+
(Option)
MSG LOG
The MSG LOG menu is selected using the MSG LOG tab. This page
stores uplink and downlink messages. The messages can be filtered to
display only the open messages that require a response.
Up to 75 messages can be stored. When the maximum storage limit of
75 messages is reached, the oldest CLOSED message is deleted to
make room for NEW messages.
Unviewed messages are accompanied with a cyan message header
with a UTC time stamp, the ATC code, message status, and an arrow
pointing either up or down. Uplink messages are accompanied by an
arrow pointing up. Downlink messages are accompanied by an arrow
pointing down.
Selecting an unviewed message displays the message history. When
the message has been viewed, the message header and status change
from cyan to white.
Copyright © Bombardier Inc.
CS130-21.12-06.00-121418
TECHNICAL TRAINING MANUAL
For Training Purposes Only
23-14
23 - Communication
23-22 Controller-Pilot Data Link Communications – FANS 1/A+
(Option)
Downlink/Uplink Arrow,
UTC Time Stamp
and ATC Code
DLK
TUNE
MSG LOG
UTC
Message
Header
Message
Status
TUNE
CPDLC
SETTINGS
22:40
REQUEST
FILTER
REPORT
ALL
UTC 22:39-EDMM
CLOSED/UNVIEWED
CHECK STUCK MICROPHONE 121.500 MHZ
UTC 22:35-EGTT
CLOSED
WE CAN ACCEPT 10000 FT AT 2315Z
UTC 22:34-EGTT
ACCEPTED
WHEN CAN YOU ACCEPT 10000 FT
UTC 22:34-EGTT
TIMEDOUT
SQUAWK 1220
UTC 22:34-EGTT
TIMEDOUT
MAINTAIN 0.780 MACH OR LESS
UTC 22:33-EGTT
TIMEDOUT
CROSS YUL AT OR BELOW FL250
UTC 22:33-EGTT
REJECTED
DESCEND TO REACH FL210 BY 1200Z
UTC 22:31-EGTT
ACCEPTED
PROCEED DIRECT TO DOTTY
UTC 22:30-EGTT
ACCEPTED
DESCEND TO REACH FL210 BY 0000Z
UTC 22:29-EGTT
CLOSED
REQUEST DIRECT TO DOTTY
UTC 22:28-EGTT
TIMEDOUT
PROCEED DIRECT TO EGTT
UTC 22:27-EGTT
ACCEPTED
FLY HEADING 270° M
MSG LOG
DLK
CPDLC
SETTINGS
REQUEST
TUNE
REPORT
UTC 22:39-EDMM
CHECK STUCK MICROPHONE 121.500 MHZ
MSG LOG
CLOSED
RESPONSE HISTORY
UTC
DLK
SETTINGS
22:40
CPDLC
REQUEST
FILTER
REPORT
ALL
UTC 22:39-EDMM
CLOSED
CHECK STUCK MICROPHONE 121.500 MHZ
UTC 22:35-EGTT
CLOSED
WE CAN ACCEPT 10000 FT AT 2315Z
UTC 22:34-EGTT
ACCEPTED
WHEN CAN YOU ACCEPT 10000 FT
UTC 22:34-EGTT
TIMEDOUT
SQUAWK 1220
UTC 22:34-EGTT
TIMEDOUT
MAINTAIN 0.780 MACH OR LESS
UTC 22:33-EGTT
TIMEDOUT
CROSS YUL AT OR BELOW FL250
UTC 22:33-EGTT
REJECTED
DESCEND TO REACH FL210 BY 1200Z
UTC 22:31-EGTT
ACCEPTED
PROCEED DIRECT TO DOTTY
UTC 22:30-EGTT
ACCEPTED
DESCEND TO REACH FL210 BY 0000Z
UTC 22:29-EGTT
CLOSED
REQUEST DIRECT TO DOTTY
UTC 22:28-EGTT
TIMEDOUT
PROCEED DIRECT TO EGTT
UTC 22:27-EGTT
ACCEPTED
FLY HEADING 270° M
UNVIEWED MESSAGE SELECTION
MESSAGE HISTORY
UPDATED MESSAGE STATUS
CS1_CS3_2322_022
PRINT
Figure 7: MSG LOG - MSG REVIEW Page
Copyright © Bombardier Inc.
CS130-21.12-06.00-121418
TECHNICAL TRAINING MANUAL
For Training Purposes Only
23-15
23 - Communication
23-22 Controller-Pilot Data Link Communications – FANS 1/A+
(Option)
Message Status
The messages are labeled to indicate their status and whether a
response is required. New messages or messages that have not been
acknowledged are displayed in cyan and change to white when they are
viewed.
The following tables provide the status and descriptions of uplink and
downlink messages.
Copyright © Bombardier Inc.
CS130-21.12-06.00-121418
TECHNICAL TRAINING MANUAL
For Training Purposes Only
23-16
23 - Communication
23-22 Controller-Pilot Data Link Communications – FANS 1/A+
(Option)
Table 1: Uplink Message Status
STATUS
Table 2: Downlink Message Status
DESCRIPTION
STATUS
DESCRIPTION
NEW
Pending uplink message that has not been
viewed and requires a response.
OPEN
A viewed downlink message that requires a
response.
OPEN
A viewed uplink message that requires a
response.
ACCEPTED
STANDBY
An open uplink message that has been
responded to with STANDBY that requires
another response to close.
A downlink message that has been
responded to with a ROGER, AFFIRM and no
further ATC action is required.
ACCEPTED/UNVIEWED
An uplink message that has been responded to
with a WILCO, ROGER, AFFIRM, and further
action is required.
A downlink message that has been
responded to with a ROGER, AFFIRM by
ATC that has not been viewed.
REJECTED
An uplink message that has been responded to
with a WILCO, ROGER, AFFIRM, and no further
action is required.
A downlink message that has been
responded to with either an UNABLE or
NEGATIVE. This message is closed.
REJECTED/UNVIEWED
An uplink message that has been responded to
with either an UNABLE or NEGATIVE. This
message is closed.
A downlink message that has been
responded to with either an UNABLE or
NEGATIVE by ATC and has not been viewed.
STANDBY
An uplink message with all elements of the
message responded or a message that does not
require a response.
An open downlink message that has been
responded to with STANDBY and requires
another ATC response to close.
CLOSED
A downlink message that has had all of the
elements of the message responded to or a
message that does not require a response.
CONNECTED
CPDLC is connected to the ground station.
No action is required.
PENDING
Transmission in progress and waiting for
network acknowledgment.
TIMEOUT
A downlink message that was not responded
to in the alloted time.
ERROR
A problem with the downlink message
transmission.
ACCEPTED/OPEN
ACCEPTED
REJECTED
CLOSED
CLOSED/UNVIEWED
CONN ENDED
TIMEOUT
An uplink message that does not require a
response that has not been viewed.
The CPDLC connection with ATA has been lost.
No response to the messages can be sent in this
state.
An uplink message that was not responded to in
the alloted time. A downlink message is
automatically sent stating that the message has
timed out. No responses can be made to the
message in this state.
CS_C1_AV23OPT_001
Copyright © Bombardier Inc.
CS130-21.12-06.00-121418
TECHNICAL TRAINING MANUAL
For Training Purposes Only
CS_C1_AV23OPT_002
23-17
23 - Communication
23-22 Controller-Pilot Data Link Communications – FANS 1/A+
(Option)
SETTINGS MENU
LOGON/STATUS
The LOGON page is used to notify air traffic control (ATC) that a
communication link is desired. When ATC acknowledges the request,
communication is established.
The ATC DL drop-down menu has ENABLED and DISABLED
selections. When selected to DISABLED, the other fields become
inactive and all established communication is lost, including unanswered
messages.
The LOGON TO field is used to enter the International Civil Aviation
Organization (ICAO) address of the ATC to be contacted. The selection
is made using the SEND LOGON button.
Once the SEND LOGON button is selected, a change logon confirmation
window is displayed indicating the logon data has changed and requires
confirmation that a new logon is desired.
Copyright © Bombardier Inc.
CS130-21.12-06.00-121418
TECHNICAL TRAINING MANUAL
For Training Purposes Only
23-18
23 - Communication
23-22 Controller-Pilot Data Link Communications – FANS 1/A+
(Option)
DLK
LK
MSG LOG
CPDLC
PDLC
SETTINGS
TUNE
REQUEST
T
REPORT
LOGON/STATUS
NETWORK
ATC DL
KICT
ARR
KICT
FLT ID
NETWORK
ENABLED
DEPT
MSG LOG
CPDLC
SETTINGS
REQUEST
REPORT
LOGON/STATUS
FANS 1/A
CDA ---------NDA ----------
DLK
ATC DL
FANS 1/A
ENABLEDLOGON DATA CHANGED
CDA
DEPT
----------
END OF FLIGHT
PREVIOUS VALUE
CURRENT VALUE
EDDM
EIDW
END OF FLIGHT
NDA
ARR----------
FLT ID
DEPT KICT
EDDF
EGLL
NW1234
NW4567
ARR SELECTING
KICT
BBA503
FLT
LOGON TO
CONTINUE WILL DISCONNECT
AND PURGE THE MESSAGE LOG
ID BBA503
CONTINUE
LOGON TO
LOGON REQUIRED
SEND LOGON
LOGON REQUIRED
SEND LOGON
ATC ATN AVAILABLE
ATC ATN AVAILABLE
NO ATC COMM
FANS LOGON MENU
FANS LOGON MENU
CS1_CS3_2373_008
TUNEE
TUN
Figure 8: SETTINGS - LOGON/STATUS Page
Copyright © Bombardier Inc.
CS130-21.12-06.00-121418
TECHNICAL TRAINING MANUAL
For Training Purposes Only
23-19
23 - Communication
23-22 Controller-Pilot Data Link Communications – FANS 1/A+
(Option)
SETTINGS- ADS REPORT
The ADS REPORT page provides a selection allowing the ADS-C to be
turned on or off.
An ADS-C EMER drop-down menu provides an ON or OFF selection for
the ADS-C emergency mode. This allows the ADS-C emergency mode
to be manually selected on or off.
When ADS-C emergency mode is turned on, a periodic contract is
initiated with ATC that sends predefined reports that are tagged as
emergency. This allows the situation to be highlighted by ATC and
monitored more easily.
ADS-C emergency mode is automatically engaged when an emergency
downlink message is sent using the EMERGENCY submenu page.
The ADS REPORT submenu page displays the status of up to four ADS
contracts. The following information is available for viewing:
•
ATC CENTER ─ ATC center address that has established a
connection with the ADS function
•
PERIOD ─ Contract period in seconds if a periodic contract is in
effect
•
TIME TO NEXT PERIOD ─ Time remaining in seconds until the next
periodic contract when a periodic contract is in effect
•
EVENT ─ Indicates YES if an event contract is active, otherwise
indication is NO
Copyright © Bombardier Inc.
CS130-21.12-06.00-121418
TECHNICAL TRAINING MANUAL
For Training Purposes Only
23-20
23 - Communication
23-22 Controller-Pilot Data Link Communications – FANS 1/A+
(Option)
DLK
DLK
K
TUNE
TUN
NE
MSG LOG
G
CPDLC
SETTINGS
REQUES
REQUEST
EST
REPORT
ADS REPORT
ADS-C
ADS-C EMER
OFF
OFF
ON
ON
OFF
ADS CONTRACTS
KCID123
-------------------------
PERIOD
304
-------
SEC
TIME TO NEXT PERIOD
297
-------
SEC
EVENT
NO
-------
FANS ADS SETTING PAGE
CS1_CS3_2322_046
ATC CENTER
Figure 9: SETTINGS - ADS REPORT
Copyright © Bombardier Inc.
CS130-21.12-06.00-121418
TECHNICAL TRAINING MANUAL
For Training Purposes Only
23-21
23 - Communication
23-22 Controller-Pilot Data Link Communications – FANS 1/A+
(Option)
SETTINGS - EMERGENCY MESSAGE
The EMERGENCY MESSAGE page is used to send an emergency
downlink message to ATC.
The EMERGENCY TYPE drop-down menu provides a MAYDAY or PAN
selection.
The REASON drop-down menu has the following selections available:
•
NONE
•
WEATHER
•
MEDICAL EMERGENCY
•
CABIN PRESSURE
•
ENGINE LOSS
•
LOW FUEL
NONE
•
NAVAID
•
FIX
•
AIRPORT
•
LAT/LON
•
PLACE/BEARING/DIST
Pressing the SET button displays a preview of the message in the
message preview window. Pressing the SEND button sends the
previewed message to the ATC station.
When the SEND button is selected, the CPDLC enters into emergency
mode and the ADS-C mode turns on emergency mode automatically.
The DIVERT TO drop-down menu has the following selections available:
•
The REMARKS field is a free text field that enables more information to
be transmitted with the downlink message. If one of the REASON
drop-down selections, other than NONE, is selected, the first line of the
REMARKS field is filled with a related remark.
When the CPDLC is in emergency mode, the EMERGENCY submenu
page options change. The only selections available are the CANCEL
EMERGENCY checkbox and a free text REMARKS field. This prevents
multiple emergency messages from being sent at once. Removing
power from the DLCA also cancels the emergency mode.
The DESCEND TO ALT field is used to request a descent to a specific
altitude.
The OFFSET TO field is used to add a course deviation request to the
downlink message.
The SOULS/FUEL (HH:MM) field is used to enter the number of live
passengers onboard and the amount of time fuel is expected to last.
Copyright © Bombardier Inc.
TECHNICAL TRAINING MANUAL
For Training Purposes Only
23-22
23 - Communication
23-22 Controller-Pilot Data Link Communications – FANS 1/A+
(Option)
DLK
DLK
K
TUNE
TUN
NE
MSG LOG
CPDLC
PDLC
SETTINGS
TUNEE
TUN
REQUEST
REPORT
EMERGENCY TYPE
EMERGENCY MESSAGE
EMERGENCY TYPE
MAYDAY
PAN
MAYDAY
MAYDAY
EMERGENCY TYPE DROP-DOWN MENU
REASON
CABIN PRESSURE
REASON
DIVERT TO
DESCEND TO ALT
SOULS/FUEL (HH:MM)
REMARKS
AIRPORT
6000
OFFSET TO
MSG LOG
SETTINGS
CPDLC
REQUES
REQUEST
UESTT
REPORT
EMERGENCY MESSAGE
CANCEL EMERGENCY
REMARKS
CABIN PRESSURE
-----------------------------------------------
NONE
WEATHER
MEDICAL EMERGENCY
CABIN PRESSURE
ENGINE LOSS
LOW FUEL
L128
143/05:23
REASON DROP-DOWN MENU
EMERGENCY DUE TO CABIN PRESSURE
DIVERT TO
------------------------------
SET
CLEAR
CLEAR
EAR
DLK
LK
AIRPORT
NONE
NAVAID
FIX
AIRPORT
LAT/LON
PLACE/BEARING/DIST
CLEAR
SET
CANCEL
CANC
CANCE
CEL
SEND
CANCEL
CANCE
L
SEND
EMERGENCY CANCEL MESSAGE PAGE
FANS EMERGENCY SETTING PAGE
CS1_CS3_2322_047
DIVERT TO DROP-DOWN MENU
Figure 10: SETTINGS - EMERGENCY MESSAGE Page
Copyright © Bombardier Inc.
CS130-21.12-06.00-121418
TECHNICAL TRAINING MANUAL
For Training Purposes Only
23-23
23 - Communication
23-22 Controller-Pilot Data Link Communications – FANS 1/A+
(Option)
SYSTEM INFO
The SETTINGS submenu allows access to maintenance functions in the
SYSTEM INFO submenu. The SYSTEM INFO submenu provides
information on the status of CPDLC system.
The following information is available on the SYSTEM INFO submenu
page:
•
Software versions
•
Configuration status
•
Component and application status
•
FANS network logon status
PROTECTED MENU
To access the PROTECTED MENU a password is required at the bottom
of the SYSTEM INFO submenu. Use the current system time within
1 minute as the password.
The PROTECTED MENU page offers the following options:
•
ONBOARD DEBUG
•
HEX MESSAGES
•
FOOTPRINTS
•
TIMERS
•
GND APP CFG
The PROTECTED MENU options allow modifications to the
configuration and software setup of the CPDLC. This menu also enables
debugging, and helps troubleshoot system faults.
Copyright © Bombardier Inc.
CS130-21.12-06.00-121418
TECHNICAL TRAINING MANUAL
For Training Purposes Only
23-24
23 - Communication
23-22 Controller-Pilot Data Link Communications – FANS 1/A+
(Option)
TUNE
TUN
NE
DLKK
DLK
CPDLC
PDLC
MSG LOG
MSG
OG SETTINGS
SYSTEM INFO
TIME
TUNE
REQUES
REQUEST
UEST
REPORT
DLK
CPDLC
MSG LOG SETTINGS
PROTECTED MENU
REQUEST
REPORT
ONBOARD DEBUG
UTC 18:24
HEX MESSAGE
TOP-LEVEL VERSION 810-0315-10OT DLCA ACTIVE
LEFT
HMI SW VERSION
096-6363-10OT DLCA XSIDE
NOT AVAIL
CORE SW VERSION
096-2550-10OT CABINET SLOT
1
FOOTPRINT
TIMERS
GND APP CFG
MSG LIB VERSION
096-6964-10OT CABINET SIDE
LEFT
A/C REGISTRATION
.C-GWXJ
FMS
CONN/LEFT
RIU
LEFT
PM
AVAILABLE
PRINTER
AVAILABLE
OPERATIONAL CONFIG ATN
FANS STATUS
UNAVAILABLE
CPDLC
UNAVAILABLE
LOGON
LOGGED OFF
LOGON
LOGGED OFF
CM
REGISTERED
PROTECTED MENU
----
NO ATC COMM
SYSTEM INFO
SYSTEM INFO PAGE
NO COMM
PROTECTED MENU PAGE
CS1_CS3_2373_011
ATN STATUS
CPDLC
Figure 11: SETTINGS - SYSTEM INFO Page
Copyright © Bombardier Inc.
CS130-21.12-06.00-121418
TECHNICAL TRAINING MANUAL
For Training Purposes Only
23-25
23 - Communication
23-22 Controller-Pilot Data Link Communications – FANS 1/A+
(Option)
REQUEST PAGES
ALTITUDE/OFFSET/SPEED/VMC DESCENT REQUESTS
The REQUEST pages allow the user to send downlink messages to
ATC. The following type of requests can be sent:
Requests are made using the information fields. If a specific value is
desired, the value is input in the first box. If a range is required then the
lower value is entered in the first box, the higher value in the second.
•
ALTITUDE
•
OFFSET
•
SPEED
•
ROUTE
•
CLEARANCE
•
VMC DESCENT
•
WHEN CAN WE
•
VOICE REQ
•
FREE TEXT
•
MONITORING
The STEP AT drop-down menu enables the following type of information
to be added:
•
NAVAID
•
AIRPORT
•
FIX
•
LAT/LON
•
PLACE/BEARING/DIST
•
TIME
Checkboxes allow the selection of the reason for the request. These
vary depending on the type of request.
Pressing the SET button displays a preview of the message in the
message preview window. Pressing the SEND button sends the
previewed message to the ATC station.
Invalid Entry
All data fields that are manually entered are checked by the DLCA
application to ensure the values entered are within limits. These limits
vary depending on what information is being entered.
Whenever an input is outside the set limit, an invalid entry message is
displayed in yellow, and the information needs to be entered again.
Copyright © Bombardier Inc.
CS130-21.12-06.00-121418
TECHNICAL TRAINING MANUAL
For Training Purposes Only
23-26
23 - Communication
23-22 Controller-Pilot Data Link Communications – FANS 1/A+
(Option)
TUNE
TUN
NE
DLK
LK
MSG LOG
CPDLC
CPDLC
C
SETTINGS
NGS
REQUEST
DLK
REPORT
MSG LOG
ALTITUDE REQUEST
ALT/ALT BLOCK
STEP AT
20000
CPDLC
SETTINGS
SETTINGS
NGS
REQUEST
TUNE
TUN
NE
REPOR
REPORT
RT
RT
SPEED REQUEST
/
-----
SPEED
350
/
MSG LOG
DLK
CPDLC
PDLC
SETTINGS
SETTINGS
NGS
REQUEST
REPOR
REPORT
RT
RT
VMC REQUEST
-----
VMC DESCENT
TIME
12:10 Z
DUE TO WX
DUE TO A/C PERF
AT PILOT DISCRETION
MAINT SEPERATION/VMC
CRZ CLB
DUE TO WX
DUE TO A/C PERF
DUE TO WX
DUE TO A/C PERF
SPEED
CLEARR
SET
AT UTC 12:10 REQUEST CLIMB TO 20000FT, DUE
TO WEATHER, DUE TO AIRCRAFT PERFORMANCE
TUNE
TUN
NE
DLK
LK
CPD
CPDLC
PDLC
C
MSGG LOGG SETTINGS
SETTINGS
NGS
OFFSET REQUEST
REQUEST
CLEARR
REPORT
SET
REQUEST VMC DESCENT, DUE TO AIRCRAFT
PERFORMANCE
SEND
CANCEL
CANC
CANCE
ANCELL
ALTITUDE/OFFSET
INVALID ENTRY
INVALID ENTRY
SEND
CANCEL
CANCE
L
VMC DESCENT
CS1_CS3_2322_045
300E
Figure 12: REQUEST - ALTITUDE/OFFSET/SPEED REQUEST/VMC DESCENT REQUEST
Copyright © Bombardier Inc.
CS130-21.12-06.00-121418
TECHNICAL TRAINING MANUAL
For Training Purposes Only
23-27
23 - Communication
23-22 Controller-Pilot Data Link Communications – FANS 1/A+
(Option)
ROUTE REQUEST
WX DEV TO POS
The ROUTE REQUEST page allows route change downlink messages
to be entered. There are four types of ROUTE REQUESTS:
The WX DEV TO POS enables route change requests using the active
flight plan. If there is no active flight plan, a NO ROUTE INFO
PROVIDED is set in the downlink message.
•
DIRECT TO POS
•
WX DEV TO POS
•
HEADING
•
GRND TRK
The WX DEV TO POS has the same drop-down menu as the DIRECT
TO POS mode.
HEADING
Heading changes are requested using the HEADING field.
DIRECT TO POS
If the DIRECT TO POS route request is selected, one of the following
selections must be made from the drop-down menu:
•
NONE
•
NAVAID
•
AIRPORT
•
FIX
•
LAT/LON
•
PLACE/BEARING/DIST
GRND TRK
Ground track changes are requested using the GRND TRK field.
Once a selection is made from the DIRECT TO POS drop-down menu, a
field is provided to enter position information.
Copyright © Bombardier Inc.
CS130-21.12-06.00-121418
TECHNICAL TRAINING MANUAL
For Training Purposes Only
23-28
23 - Communication
23-22 Controller-Pilot Data Link Communications – FANS 1/A+
(Option)
TUNE
MSG
G LOG
DLK
CPDLC
SETTINGS
NGS
REQUEST
REPORT
ROUTE REQUEST
DIRECT TO POS
AIRPORT
AIRPORT
NONE
NAVAID
AIRPORT
FIX
LAT/LON
PLACE/BEARING/DIST
CYXE
WX DEV TO POS
NONE
HEADING
DROP-DOWN MENU
GRND TRK
CLEAR
CLEAR
EAR
SET
CANCEL
CANCE
L
SEND
CS1_CS3_2322_034
DUE TO A/C PERF
FANS ROUTE REQUEST
Figure 13: REQUEST - ROUTE REQUEST Page
Copyright © Bombardier Inc.
CS130-21.12-06.00-121418
TECHNICAL TRAINING MANUAL
For Training Purposes Only
23-29
23 - Communication
23-22 Controller-Pilot Data Link Communications – FANS 1/A+
(Option)
CLEARANCE REQUEST
PROCEDURE TYPE
The CLEARANCE page allows three types of clearance request
downlink messages to be sent. The three mutually exclusive types of
clearance requests are the following:
Procedural clearance requests are sent using the PROCEDURE TYPE
selection. Procedural clearance requests are used when the requested
aircraft maneuvers would cause a deviation from the flight plan. The
PROCEDURE TYPE section has a drop-down menu with the following
selections available:
•
CLEARANCE
•
FLIGHT PLAN
•
PROCEDURE TYPE
•
NONE
•
ARRIVAL
CLEARANCE
•
APPROACH
Selecting the CLEARANCE checkbox sends a request for clearance to
the ATC.
•
DEPARTURE
FLIGHT PLAN
Two data fields are provided to enter additional procedural information to
the downlink procedure clearance request.
The FLIGHT PLAN selection allows a downlink request for flight plan
clearance. The FLIGHT PLAN section has a drop-down menu with the
following selections available:
•
NONE
•
ACTIVE ─ Request clearance to use the active flight plan from the
FMS
•
MODIFIED ─ Request for clearance to use the modified flight plan
from the FMS
•
SECONDARY ─ Request for clearance to use the secondary flight
plan from the FMS
Copyright © Bombardier Inc.
CS130-21.12-06.00-121418
TECHNICAL TRAINING MANUAL
For Training Purposes Only
23-30
23 - Communication
23-22 Controller-Pilot Data Link Communications – FANS 1/A+
(Option)
MSG
MS
G LOG
OG
CPDLC
PDLC
SETTINGS
SETTINGS
NGS
REQUEST
DLK
LK
REPORT
MSG LOG
CLEARANCE REQUEST
ACTIVE
REPORT
MSGG LOG
ACTIVE
REQUEST
FLIGHT PLAN
ACTIVE
PROCEDURE TYPE
NONE
PROCEDURE
TRANSITION
----------
SETTINGS
SETTINGS
NGS
REPORT
CLEARANCE REQUEST
NONE
RETRIVING
ACTIVE FLIGHT PLAN
ACTIVE
MODIFIED
SECONDARY
PROCEDURE TYPE
NONE
NONE
CPDLC
CLEARANCE
FLIGHT PLAN
PROCEDURE
TRANSITION
REQUEST
CLEARANCE
RETRIVING ACTIVE FLIGHT PLAN
PROCEDURE TYPE
SETTINGS
S
DLK
LK
TUNE
CLEARANCE REQUEST
CLEARANCE
FLIGHT PLAN
CPDLC
PROCEDURE
TRANSITION
----------
NONE
ARRIVAL
APPROACH
---------DEPARTURE
CLEAR
R
SET
CLEAR
R
SET
CLEAR
CLEAR
EAR
SET
CANCELL
CANCE
SEND
CANCEL
CANC
CANCE
ANCEL
L
SEND
CANCELL
CANCE
SEND
FANS CLEARANCE REQUEST
FANS FLIGHT PLAN CLEARANCE REQUEST
FANS PROCEDURE TYPE CLEARANCE REQUEST
CS1_CS3_2322_035
DLK
LK
Figure 14: REQUEST - CLEARANCE REQUEST Page
Copyright © Bombardier Inc.
CS130-21.12-06.00-121418
TECHNICAL TRAINING MANUAL
For Training Purposes Only
23-31
23 - Communication
23-22 Controller-Pilot Data Link Communications – FANS 1/A+
(Option)
WHEN CAN WE
The WHEN CAN WE page is used to send downlink messages
requesting when certain procedures can be done. The following WHEN
CAN WE message requests are available:
•
ALTITUDE CHANGE
•
ALTITUDE
•
SPEED/SPEED BLOCK
•
BACK ON ROUTE
ALTITUDE CHANGE
A drop-down menu is used to indicate if the altitude change is HIGHER
or LOWER.
ALTITUDE
The desired altitude is entered in the ALTITUDE field. The CRUISE
CLIMB checkbox is only enabled when an altitude field value is greater
than FL 320 and more than 150 ft above the current altitude.
SPEED/SPEED BLOCK
The SPEED/SPEED BLOCK selection has two fields. When a specific
speed is requested only the first field needs to be filled. The second field
allows a speed block request.
BACK ON ROUTE
The BACK ON ROUTE is a simple checkbox selection.
Copyright © Bombardier Inc.
CS130-21.12-06.00-121418
TECHNICAL TRAINING MANUAL
For Training Purposes Only
23-32
23 - Communication
23-22 Controller-Pilot Data Link Communications – FANS 1/A+
(Option)
DLK
MSG LOG
G
CPDLC
SETTINGS
NGS
TUNE
REQUEST
REPORT
WHEN CAN WE
HIGHER
HIGHER
LOWER
000000
SPEED/SPEED BLOCK
SETTINGS
NGS
ALTITUDE CHANGE
CRUISE
SE CLIMB
00000 /
ALTITUDE
REQUEST
REPORT
HIGHER
CRUISE CLIMB
000000
SPEED/SPEED BLOCK
----
BACK ON ROUTE
00000 /
----
BACK ON ROUTE
CLEAR
CLEAR
EAR
SET
WHEN CAN WE EXPECT HIGHER ALTITUDE
CANCEL
CAN
CANCE
ANCEL
L
MSG LOG
G
CPDLC
WHEN CAN WE
ALTITUDE CHANGE
ALTITUDE
DLK
CLEAR
CLEAR
EAR
SET
WHEN CAN WE EXPECT HIGHER ALTITUDE
SEND
SEND
ND
CANCEL
CAN
CANCE
ANCEL
L
FANS WHEN CAN WE
SEND
SEND
ND
CS1_CS3_2322_036
TUNE
Figure 15: REQUEST - WHEN CAN WE Page
Copyright © Bombardier Inc.
CS130-21.12-06.00-121418
TECHNICAL TRAINING MANUAL
For Training Purposes Only
23-33
23 - Communication
23-22 Controller-Pilot Data Link Communications – FANS 1/A+
(Option)
VOICE REQ
The VOICE REQ sends a downlink message requesting voice
communication. A drop-down menu allows the request to be carried out
using VHF radio or SATCOM.
Copyright © Bombardier Inc.
CS130-21.12-06.00-121418
TECHNICAL TRAINING MANUAL
For Training Purposes Only
23-34
23 - Communication
23-22 Controller-Pilot Data Link Communications – FANS 1/A+
(Option)
TUNE
MSG LOG
DLK
CPDLC
SETTINGS
S
REQUEST
REPORT
REQUEST VOICE CONTACT
FREQUENCY
VHF
SATCOM
DUE TO WX
DUE TO A/C PERF
CLEAR
R
SET
CANCEL
CAN
CANCE
ANCEL
L
SEND
D
FANS VOICE REQUEST
CS1_CS3_2322_037
REQUEST VOICE CONTACT, DUE TO AIRCRAFT
PERFORMANCE
Figure 16: REQUEST - REQUEST VOICE CONTACT Page
Copyright © Bombardier Inc.
CS130-21.12-06.00-121418
TECHNICAL TRAINING MANUAL
For Training Purposes Only
23-35
23 - Communication
23-22 Controller-Pilot Data Link Communications – FANS 1/A+
(Option)
FREE TEXT
The FREE TEXT submenu page allows free text downlink messages to
be entered using the multifunction keyboard panel (MKP). Once the text
has been entered, pushing the SET button displays the message in the
preview window. The SEND button sends the downlink message in the
preview window.
Copyright © Bombardier Inc.
CS130-21.12-06.00-121418
TECHNICAL TRAINING MANUAL
For Training Purposes Only
23-36
23 - Communication
23-22 Controller-Pilot Data Link Communications – FANS 1/A+
(Option)
TUNE
MSG
G LOG
DLK
CPDLC
SETTINGS
SETTINGS
NGS
REQUEST
REPORT
FREE TEXT
ABCDEFGHIJKLMNOPQRST1234
-------------------------------------------------------------------------------------------------------------------------------------------
CLEAR
R
SET
CANCEL
CAN
CANCE
ANCEL
L
SEND
FANS FREE TEXT PAGE
CS1_CS3_2322_038
------------------------
Figure 17: REQUEST - FREE TEXT Page
Copyright © Bombardier Inc.
CS130-21.12-06.00-121418
TECHNICAL TRAINING MANUAL
For Training Purposes Only
23-37
23 - Communication
23-22 Controller-Pilot Data Link Communications – FANS 1/A+
(Option)
MONITORING
The MONITORING page enables a downlink message to be sent to ATC
indicating that a frequency is being monitored. This is done by entering
the following information:
•
FACILITY DESIGNATION – ICAO designation for the facility being
monitored
•
FACILITY NAME – Name of the facility
•
VHF – Frequency monitored
•
FACILITY – Facility type
The following selections are available in the FACILITY drop-down menu:
•
CENTER
•
APPROACH
•
TOWER
•
FINAL
•
GROUND CONTROL
•
CLEARANCE DELIVERY
•
DEPARTURE
•
CONTROL
•
RADIO
Copyright © Bombardier Inc.
CS130-21.12-06.00-121418
TECHNICAL TRAINING MANUAL
For Training Purposes Only
23-38
23 - Communication
23-22 Controller-Pilot Data Link Communications – FANS 1/A+
(Option)
DLK
DLK
K
TUNE
TUN
NE
MSG LOG
G
CPDLC
SETTINGS
NGS
REQUEST
REPOR
REPORT
PORT
MONITORING
FACILITY DESIGNATION
FACILITY NAME
VHF
FACILITY
CYUL
MONTREAL-TRUDEAU
119.900
APPROACH
CENTER
APPROACH
TOWER
FINAL
GROUND CONTROL
CLEARANCE DELIVERY
DEPARTURE
CONTROL
RADIO
CLEAR
SEND
SEND
CANCEL
CAN
CANCE
ANCEL
L
FANS MONITORING
CS1_CS3_2322_051
MONITORING CYUL MONTREAL-TRUDEAU TOWER 119.900
Figure 18: REQUEST - MONITORING Page
Copyright © Bombardier Inc.
CS130-21.12-06.00-121418
TECHNICAL TRAINING MANUAL
For Training Purposes Only
23-39
23 - Communication
23-22 Controller-Pilot Data Link Communications – FANS 1/A+
(Option)
REPORT MENU
The REPORT tab drop-down menu has the following selections:
•
POSITION REP
•
REPORTS DUE
POSITION REP
The POSITION REPORT page enables quick position reporting. The
data fields are filled automatically using information from the FMS. The
data can also be entered manually if required.
A scroll bar located at the right of the screen allows access to the three
pages of information. The following information can be sent using the
POSITION REP submenu page:
•
REP WPT
•
NEXT FIX
•
NEXT FIX +1
•
CUR POS
Each of the drop-down menus in the position reporting page provide the
following options:
•
NONE
•
NAVAID
•
AIRPORT
•
FIX
•
LAT/LON
•
PLACE/BEARING/DIST
Copyright © Bombardier Inc.
CS130-21.12-06.00-121418
TECHNICAL TRAINING MANUAL
For Training Purposes Only
23-40
23 - Communication
23-22 Controller-Pilot Data Link Communications – FANS 1/A+
(Option)
Scroll Bar
DLK
LK
MMSG
SG LOG
OG
G
CPDLC
PDLC
SETTINGS
SETTINGS
NGS
REQUEST
DLK
REPOORT
REPORT
RT
MSG LOG
POSITION REPORT
RPT WPT
CPDLCC
CPDLC
SETTINGS
S
REQUEST
REPORRT
REPORT
RT
POSITION REPORT
LAT/LONG
NEXT FIX
DLK
LK
TUNE
MSGG LOG
SETTINGS
SETTINGS
NGS
19:05
RPT WPT ALT
18000
REQUEST
REPORRT
REPORT
RT
POSITION REPORT
NONE
NONE
CUR POS
N4447.0 W04544.0
RPT WPT UTC
CPDLC
NEXT FIX UTC
19:05
NEXT FIX +1
NONE
N4447.0 W04544.0
N4447.0 W04544.0
CUR UTC
19:05
WINDS ALOFT
CUR ALT
18000
OFFSET
CLB/DES
18000
DEST UTC
19:40
SPEED
-----
TEMPERATURE
---
---/---
T/KT
----
FANS POSITION REPORT PAGE 2/3
SET
CANCEL
CANC
CANCE
ANCELL
SEND
FANS POSITION REPORT PAGE 1/3
NONE
NAVAID
AIRPORT
FIX
LAT/LON
PLACE/BEARING/DIST
CLEAR
CLEAR
EAR
SET
CANCEL
CANC
CANCE
ANCELL
SEND
DROP-DOWN MENU
FANS POSITION REPORT PAGE 3/3
CS1_CS3_2322_049
AIRPORT
CLEAR
CLEAR
EAR
Figure 19: REPORT - POSITION REPORT Page
Copyright © Bombardier Inc.
CS130-21.12-06.00-121418
TECHNICAL TRAINING MANUAL
For Training Purposes Only
23-41
23 - Communication
23-22 Controller-Pilot Data Link Communications – FANS 1/A+
(Option)
REPORTS DUE
When an uplink message containing report conditions is accepted, a
response is sent to the ATC once the reported conditions are met.The
following uplink messages contain report conditions:
•
REPORT BACK ON ROUTE
•
REPORT LEAVE FL
•
REPORT LEVEL
•
REPORT PASSING
•
REPORT REACHING FL
•
REPORT REACHING BLOCK FL TO FL
The REPORTS DUE page allows reports to be sent automatically when
the reports are ARMED. If reports are ARMED, the report is sent when
the aircraft meets the reporting conditions. ARMED reports can be
DISARMED by selecting the DISARM button. Disarmed reports are sent
manually by selecting the SEND button.
The non-actioned report elements from open uplink messages are
displayed on the REPORTS DUE page.
Copyright © Bombardier Inc.
CS130-21.12-06.00-121418
TECHNICAL TRAINING MANUAL
For Training Purposes Only
23-42
23 - Communication
23-22 Controller-Pilot Data Link Communications – FANS 1/A+
(Option)
TUNE
TUN
NE
MSG LOG
DLK
DLK
K
CPDLC
SETTINGS
S
REQUEST
REPOR
REPORT
RT
REPORTS DUE
LEVEL ALTITUDE DISARMED
25000FT/26000FT
/
UNABLE TO ARM REPORT
DISARM
SEND
ARM
SEND
SEND
ND
LEVEL ALTITUDE OPEN
25000FT/26000FT
SEND
LEAVING ALTITUDE ARMED
12000FT
REPORT ARMED
DISAR
DISARM
ARM
RM
SEND
LEAVING ALTITUDE ARMED
24000FT
REPORT ARMED
DISAR
DISARM
ARM
RM
SEND
AR
ARM
RM
RM
SEND
REACHING ALTITUDE
22000FT
ARMING REPORT
FANS REPORTS DUE
CS1_CS3_2322_050
LEAVING ALTITUDE ARMED
12000FT
REPORT ARMED
Figure 20: REPORT - REPORTS DUE Page
Copyright © Bombardier Inc.
CS130-21.12-06.00-121418
TECHNICAL TRAINING MANUAL
For Training Purposes Only
23-43
23 - Communication
23-22 Controller-Pilot Data Link Communications – FANS 1/A+
(Option)
UPLINK MESSAGES
Uplink message responses are sent using the MSG LOG page, or the
quick-response controls.
RTSA Page
Selecting the new uplink message in the MSG LOG page allows the user
to send a response.
A second page is displayed with the following buttons:
•
ACCEPT
•
STANDBY
•
REJECT
•
LOAD
The REJECT button allows uplink requests to be rejected. Two
checkboxes are provided that enables the aircraft performance or
weather to be selected as reasons the uplink request is rejected. Three
free text lines are also available if added information needs to be sent.
The LOAD button is for messages with FMS loadable elements.
After the response is sent, the message history page is displayed briefly
followed by the MSG LOG page and the appropriate message status is
displayed.
Copyright © Bombardier Inc.
CS130-21.12-06.00-121418
TECHNICAL TRAINING MANUAL
For Training Purposes Only
23-44
23 - Communication
23-22 Controller-Pilot Data Link Communications – FANS 1/A+
(Option)
MSG LOG
UTC
TUNE
TUNEE
TUN
TUNE
TUN
NE
REQUESTT
22:03
UTC 22:03-EGTT
SQUAWK IDENT
UTC 22:01-EGTT
WHY NOT
UTC 22:00-EGTT
MAINTAIN 250 KT IAS OR LESS
UTC 21:58-EGTT
MAINTAIN FL350
FILTER
MSG LOG
REPORT
REQUESTT
MSG LOG
REPORT
UTC 22:03-EGTT
SQUAWK IDENT
ALL
OPEN
DLK
CPDLC
SETTINGS
REQUEST
TUNE
TUN
NE
REPORT
UTC 22:03-EGTT
SQUAWK IDENT
NEW
CLOSED
ACCEPTED
RESPONSE HISTORY
REJECT, DUE TO WEATHER
ACCEPTED
REJECTED
MSG LOG
UTC
REQUEST
STT
22:04
UTC 22:03-EGTT
SQUAWK IDENT
UTC 22:01-EGTT
WHY NOT
UTC 22:00-EGTT
MAINTAIN 250 KT IAS OR LESS
UTC 21:58-EGTT
MAINTAIN FL350
FILTER
REPORT
ALL
REJECTED
CLOSED
ACCEPTED
ACCEPTED
ACCEPT
STANDBY
DUE TO WX
DUE TO A/C PERF
----------------------------------------------------------------
REJECT
PRINT
RESPONSE SELECTIONS
MESSAGE HISTORY
UPDATED MESSAGE STATUS
CS1_CS3_2322_027
NEW MESSAGE SELECTION
Figure 21: Uplink Message
Copyright © Bombardier Inc.
CS130-21.12-06.00-121418
TECHNICAL TRAINING MANUAL
For Training Purposes Only
23-45
23 - Communication
23-22 Controller-Pilot Data Link Communications – FANS 1/A+
(Option)
Uplink Message with FMS Loadable Elements
When an uplink message has FMS loadable elements, the ACCEPT
button is disabled. The FMS loadable elements are loaded into the FMS
by selecting the LOAD button. There is a loadable status display located
next to the LOAD button. The following conditions can be annunciated in
the loadable status display:
•
READY TO VALIDATE/LOAD ─ Modified flight plan is not loaded into
FMS
•
MOD FPLN ENABLED ─ An FMS modified flight plan is already in
use
•
VALIDATING LOADING MOD ─ The FMS is validating the modified
flight plan
•
LOAD FAILED ─ Either the FMS does not accept the modified flight
plan or the FMS fails to report a load complete status to the CPDLC
•
LOAD COMPLETE ─ The FMS has finished validating the uplink and
has inserted the loadable element into the modified flight plan
•
LOAD EXECUTED ─ The FMS has sent an accepted status
message
•
LOAD CANCELED ─ The FMS has sent a rejected status message
or the FMS has been in VALIDATING/LOADING mode for more than
12 seconds
The LOAD function is disabled once the message is loaded to prevent
multiple loading.
Once the LOAD EXECUTED status is displayed the ACCEPT button
becomes selectable. Pressing the ACCEPT button sends a reply
indicating that the elements have been accepted.
If the FMS content has failed to load, the free text box includes an
UNLOADABLE condition. When the UNLOADABLE box is selected, an
UPLINK IS UNLOADABLE message is added to the text box.
Copyright © Bombardier Inc.
CS130-21.12-06.00-121418
TECHNICAL TRAINING MANUAL
For Training Purposes Only
23-46
23 - Communication
23-22 Controller-Pilot Data Link Communications – FANS 1/A+
(Option)
TUNE
TUN
NE
MSG LOG
DLK
DLK
K
CPDLC
SETTINGS
NGS
REQUES
REQUEST
QUEST
UTC 19:04-ARICTEST
CLEARED DEPARTURE LAMMA FIVE
REPOR
REPORT
PORT
OPEN
Loadable
Status
Display
LOADABLE STATUS
LOAD
READY TO VALIDATE/LOAD
ACCEPT
READY TO VALIDATE/LOAD
Modified flight plan is not loaded into FMS.
MOD FPLN ENABLED
An FMS modified flight plan is already in use.
VALIDATING LOADING MOD
The FMS is validating the modified flight plan.
LOAD FAILED
Either the FMS does not accept the modified
flight plan, or the FMS fails to report a load
complete status to the CPDLC.
LOAD COMPLETE
The FMS has finished validating the uplink
and has inserted the loadable element
into the modified flight plan.
LOAD EXECUTED
The FMS has sent an accepted status message.
LOAD CANCELED
The FMS has sent a rejected status message,
or the FMS has been in VALIDATING/LOADING
mode for more than 12 seconds.
STANDB
STANDBY
BY
DUE TO WX
DUE TO A/C PERF
UNLOADABLE
-----------------------------------------------------------
REJECT
CS1_CS3_2322_048
------------------------------
CONDITION
Figure 22: Uplink Message with Loadable FMS Content
Copyright © Bombardier Inc.
CS130-21.12-06.00-121418
TECHNICAL TRAINING MANUAL
For Training Purposes Only
23-47
23 - Communication
23-22 Controller-Pilot Data Link Communications – FANS 1/A+
(Option)
WHEN CAN YOU UPLINK MESSAGE
A WHEN CAN YOU uplink message has a unique response format.
When the message is selected in the MSG LOG page, a downlink
message page is displayed. A drop-down menu allows the user to
choose WE CAN or WE CAN NOT as a response and enter the UTC
time in the AT UTC field.
Copyright © Bombardier Inc.
CS130-21.12-06.00-121418
TECHNICAL TRAINING MANUAL
For Training Purposes Only
23-48
23 - Communication
23-22 Controller-Pilot Data Link Communications – FANS 1/A+
(Option)
DLK
TUNE
MSG LOG
UTC
SETTINGS
CPDLC
REQUEST
22:33
DLK
TUNE
FILTER
REPORT
ALL
UTC 22:34-EGTT
NEW
WHEN CAN YOU ACCEPT 10000 FT
UTC 22:33-EGTT
NEW
CROSS YUL AT OR BELOW FL250
UTC 22:34-EGTT
STANDBY
SQUAWK 1220
UTC 22:34-EGTT
OPEN
MAINTAIN 0.780 MACH OR LESS
UTC 22:33-EGTT
REJECTED
DESCEND TO REACH FL210 BY 1200Z
UTC 22:31-EGTT
ACCEPTED
PROCEED DIRECT TO DOTTY
UTC 22:30-EGTT
ACCEPTED
DESCEND TO REACH FL210 BY 0000Z
UTC 22:29-EGTT
CLOSED
REQUEST DIRECT TO DOTTY
UTC 22:28-EGTT
TIMEDOUT
PROCEED DIRECT TO EGTT
UTC 22:27-EGTT
ACCEPTED
FLY HEADING 270° M
UTC 22:26-EGTT
CLOSED
REQUEST DIRECT TO EGTT, DUE TO WEATHER, DUE
UTC 22:25-EGTT
ACCEPTED
MAINTAIN 0.800 MACH
MSG LOG
SETTINGS
CPDLC
TUNE
REQUEST
REPORT
UTC 22:34-EGTT
WHEN CAN YOU ACCEPT 10000 FT
RESPONSE
WE CAN
SETTINGS
CPDLC
REQUEST
MSG LOG
REPORT
OPEN
AT UTC
- DOWNLINK SET MESSAGES
CANCEL - CLEAR SET MESSAGES
CLEAR
SET
CLEAR
SET
WE CAN ACCEPT 10000 FT AT 2315Z
SEND
CANCEL
UTC
SETTINGS
22:35
CPDLC
REQUEST
FILTER
REPORT
ALL
UTC 22:34-EGTT
STANDBY
SQUAWK 1220
UTC 22:35-EGTT
CLOSED
WE CAN ACCEPT 10000 FT AT 2315Z
UTC 22:34-EGTT
ACCEPTED
WHEN CAN YOU ACCEPT 10000 FT
UTC 22:34-EGTT
TIMEDOUT
MAINTAIN 0.780 MACH OR LESS
UTC 22:33-EGTT
TIMEDOUT
CROSS YUL AT OR BELOW FL250
UTC 22:33-EGTT
REJECTED
DESCEND TO REACH FL210 BY 1200Z
UTC 22:31-EGTT
ACCEPTED
PROCEED DIRECT TO DOTTY
UTC 22:30-EGTT
ACCEPTED
DESCEND TO REACH FL210 BY 0000Z
UTC 22:29-EGTT
CLOSED
REQUEST DIRECT TO DOTTY
UTC 22:28-EGTT
TIMEDOUT
PROCEED DIRECT TO EGTT
UTC 22:27-EGTT
ACCEPTED
FLY HEADING 270° M
UTC 22:26-EGTT
CLOSED
REQUEST DIRECT TO EGTT, DUE TO WEATHER, DUE
SEND
RESPONSE CONFIRMATION
UPDATED MESSAGES STATUS
CS1_CS3_2322_032
RESPONSE SELECTIONS
DLK
TUNE
UTC 22:34-EGTT
WHEN CAN YOU ACCEPT 10000 FT
SEND
AT UTC
WE CAN
WE CAN NOT
CANCEL
WHEN CAN YOU UPLINK SELECTED
MSG LOG
OPEN
DLK
Figure 23: WHEN CAN YOU Uplink Message
Copyright © Bombardier Inc.
CS130-21.12-06.00-121418
TECHNICAL TRAINING MANUAL
For Training Purposes Only
23-49
23 - Communication
23-22 Controller-Pilot Data Link Communications – FANS 1/A+
(Option)
Quick-Response Uplink Message
The quick-response uplink message uses the quick-response buttons,
located on the glareshield, to respond to uplink messages. The active
buttons are indicated by cyan icons at the right of the data link inbox.
Selecting inactive quick-response buttons has no effect.
Copyright © Bombardier Inc.
CS130-21.12-06.00-121418
TECHNICAL TRAINING MANUAL
For Training Purposes Only
23-50
23 - Communication
23-22 Controller-Pilot Data Link Communications – FANS 1/A+
(Option)
CLB
CLB
92.2
92.2
92.2
92.2
73.0
73.3
73.0
73.3
N1
N1
718
722
718
EGT
86.5
1090
124
116
722
EGT
86.6
1110
124
116
N2
)) .3+
2,/7(03
2,/35(66
86.5
1090
124
116
ACPT
LOAD
86.6
1110
124
116
N2
)) .3+
2,/7(03
2,/35(66
STBY
2735
5435
1400
5.7
ELEV 570
2735
CAB ALT
RATE
ó3
CREW
LDG
7(03
(°C)
24
0
OXY 1850
HI
23
2735
RJCT
TRIM
GLARESHIELD
NU
ND
NL RUDDER NR
&3'/&
UTC 22:33-EGTT
NEW 1
DESCEND TO REACH FL210 BY 1200Z
1400
5.7
ELEV 570
2735
RATE
ó3
CREW
7(03
(°C)
4.2
5435
CAB ALT
LDG
STAB
23
10905
TOTAL FUEL (KG)
24
0
OXY 1850
TRIM
NU
STAB
HI
23
23
ND
4.2
NL RUDDER NR
&3'/&
UTC 22:33-EGTT
REJECTED 1
DESCEND TO REACH FL210 BY 1200Z
INFO
OF 1
$&37
STBY
LOAD
RJCT
INFO
OF 1
$&37
STBY
LOAD
RJCT
CS1_CS3_2322_029
10905
TOTAL FUEL (KG)
Figure 24: Quick-Response Uplink Message
Copyright © Bombardier Inc.
CS130-21.12-06.00-121418
TECHNICAL TRAINING MANUAL
For Training Purposes Only
23-51
23 - Communication
23-22 Controller-Pilot Data Link Communications – FANS 1/A+
(Option)
DOWNLINK MESSAGE
Downlink messages can only be sent using the RTSA CPDLC page. The
REQUEST menu provides a selection of preformatted downlink
message.
When the downlink message is sent, its status is PENDING until it is
received by ATC, then CLOSED if no response is required. If a downlink
message requires a response, the message status is OPEN. The
message status is displayed on the MSG LOG page.
Once a response is received, the downlink message status changes to
CLOSED. Depending on the uplink message response, further action
may be required.
Copyright © Bombardier Inc.
CS130-21.12-06.00-121418
TECHNICAL TRAINING MANUAL
For Training Purposes Only
23-52
23 - Communication
23-22 Controller-Pilot Data Link Communications – FANS 1/A+
(Option)
REQUEST Menu for
FANS 1/A
MSG
SG LOG
LOG
DLK
CPDLC
SETTING
SETTINGS
ETTINGS
S
REQUEST
TUNE
TUN
E
REPORT
ALTITUDE
UTC 22:17
FILTER
ALL
OFFSET
SPEED
UTC 22:16-EGTT
OPEN
REQUEST BLOCK FL310 TOROUTE
FL350, DUE TO
UTC 22:16-EGTT
CLOSED/UNVIEWED
D/UNVIEWED
MONITORING
REQUEST FORWARDED
UTC 22:10-EGTT
TIMEDOUT
OFFSET 1 NM LEFT OF ROUTE
UTC 22:06-EGTT
TIMEDOUT
REPORT PRESENT LEVEL
UTC 22:05-EGTT
ACCEPTED
SQUAWK IDENT
UTC 22:04-EGTT
REJECTED
SQUAWK IDENT
UTC 22:03-EGTT
REJECTED
SQUAWK IDENT
UTC 22:01-EGTT
CLOSED
WHY NOT
UTC 22:00-EGTT
ACCEPTED
MAINTAIN 250 KT IAS OR LESS
DLK
MSG LOG
SETTINGS
GS
REQUEST
REPORT
MSG LOG
ALTITUDE REQUEST
ALT/ALT BLOCK
35000
UTC
/
-----
DUE TO WX
DUE TO A/C PERF
CLEAR
SET
REQUEST CLIMB TO 35000 FT
CANCEL
CANC
CANCE
CEL
REQUEST PAGE SELECTION
DLK
TUNEE
TUN
CPDLC
SETTINGS
22:18
CPDLC
DLC
REQUESTT
FILTER
REPORT
ALL
UTC 22:18-EGTT
PENDING
REQUEST CLIMB TO 35000 FT
UTC 22:16-EGTT
OPEN
REQUEST BLOCK FL310 TO FL350, DUE TO
UTC 22:16-EGTT
CLOSED/UNVIEWED
REQUEST FORWARDED
UTC 22:10-EGTT
TIMEDOUT
OFFSET 1 NM LEFT OF ROUTE
UTC 22:06-EGTT
TIMEDOUT
REPORT PRESENT LEVEL
UTC 22:05-EGTT
ACCEPTED
SQUAWK IDENT
UTC 22:04-EGTT
REJECTED
SQUAWK IDENT
UTC 22:03-EGTT
REJECTED
SQUAWK IDENT
UTC 22:01-EGTT
CLOSED
WHY NOT
UTC 22:00-EGTT
ACCEPTED
MAINTAIN 250 KT IAS OR LESS
SEND
DOWNLINK REQUEST SELECTIONS
MSG LOG PAGE WITH DOWNLINK MESSAGE
CS1_CS3_2322_028
TUNE
TUN
NE
Figure 25: Downlink Message
Copyright © Bombardier Inc.
CS130-21.12-06.00-121418
TECHNICAL TRAINING MANUAL
For Training Purposes Only
23-53
23 - Communication
23-22 Controller-Pilot Data Link Communications – FANS 1/A+
(Option)
MONITORING AND TESTS
The following page provides the CAS messages for the CPDLC
FANS 1/A+.
Copyright © Bombardier Inc.
CS130-21.12-06.00-121418
TECHNICAL TRAINING MANUAL
For Training Purposes Only
23-54
23 - Communication
23-22 Controller-Pilot Data Link Communications – FANS 1/A+
(Option)
CAS MESSAGES
Table 3: ADVISORY Messages
MESSAGE
DATALINK FAIL
DATALINK
STATUS
LOGIC
Message appears in the event of one of the following:
•
Data link RIU reports a CMU failure
•
CMU power module failure
•
ECU failure
•
CPDLC installed and data link RIU failed/lost
connection
•
DLCA failed and IPC/CCM working/powered
Message appears in the event of one of the following:
•
ATN network is not available for the aircraft to
connect
•
AFN link is established and the active
communication link has not been available for
16 minutes
•
AFN link is established and the flight ID is
changed by the crew
>CPDLC
ATN or FANS message received and not viewed.
>DLK
Departure or oceanic clearance received but not
accepted, or all other types of messages received but not
viewed.
SATCOM FAIL
SATCOM Cockpit Fault or SATCOM Cockpit Voice Fault
or SATCOM not providing main data to RIU and SATCOM
AERO H++ installed.
SATCOM LOST
SATCOM reporting that there is no link available.
SATCOM
FAIL
DATA SATCOM reporting that it cannot support data
transmission due to failure.
Copyright © Bombardier Inc.
CS130-21.12-06.00-121418
TECHNICAL TRAINING MANUAL
For Training Purposes Only
23-55
23 - Communication
23-22 Controller-Pilot Data Link Communications – FANS 1/A+
(Option)
Page Intentionally Left Blank
Copyright © Bombardier Inc.
CS130-21.12-06.00-121418
TECHNICAL TRAINING MANUAL
For Training Purposes Only
23-56
ATA 23 - Communication
Flight Deck Door
Surveillance System
(Option)
BD-500-1A10
BD-500-1A11
23 - Communication
23-73 Flight Deck Door Surveillance System
(Option)
Table of Contents
23-73 Flight Deck Door Surveillance System .........................23-2
Introduction .......................................................................23-2
General Description...........................................................23-4
Component Location ........................................................23-6
Video Transmission Unit ..............................................23-6
Camera Control Unit ...................................................23-6
Flight Deck Door Surveillance Camera........................23-8
Controls and Indications..................................................23-10
Cockpit Door Panel ....................................................23-10
Video Display ............................................................23-12
Operation.........................................................................23-14
FDDSS Video Display Access ...................................23-14
Copyright © Bombardier Inc.
CS130-21.12-06.00-121418
TECHNICAL TRAINING MANUAL
For Training Purposes Only
23-i
23 - Communication
23-73 Flight Deck Door Surveillance System
(Option)
List of Figures
Figure 1: Flight Deck Door Surveillance System .................23-3
Figure 2: FDDSS Block Diagram .........................................23-5
Figure 3: Video Transmission and Camera Control
Units .....................................................................23-7
Figure 4: FDDSS Cameras ..................................................23-9
Figure 5: FDDSS Controls .................................................23-11
Figure 6: FDDSS Video Display ........................................23-13
Figure 7: FDDSS Video Display Access ............................23-15
Copyright © Bombardier Inc.
CS130-21.12-06.00-121418
TECHNICAL TRAINING MANUAL
For Training Purposes Only
23-ii
23 - Communication
23-73 Flight Deck Door Surveillance System
(Option)
Page Intentionally Left Blank
Copyright © Bombardier Inc.
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TECHNICAL TRAINING MANUAL
For Training Purposes Only
23-iii
23 - Communication
23-73 Flight Deck Door Surveillance System
(Option)
FLIGHT DECK DOOR SURVEILLANCE SYSTEM
Copyright © Bombardier Inc.
CS130-21.12-06.00-121418
TECHNICAL TRAINING MANUAL
For Training Purposes Only
23-1
23 - Communication
23-73 Flight Deck Door Surveillance System
(Option)
23-73 FLIGHT DECK DOOR SURVEILLANCE
SYSTEM
INTRODUCTION
The flight deck door surveillance system (FDDSS) provides a video
display of the area outside the flight deck door and surrounding area.
The video can be displayed on a multifunction window (MFW) of
display unit (DU) 3 or DU 5. If the optional electronic flight bag (EFB)
system is installed, the video can be displayed on the EFB.
The FDDSS uses three cameras to provide coverage of the area outside
of the flight deck door. Each camera feeds the video transmission unit
(VTU) that distributes the video signals to a camera control unit (CCU)
which provides video to the DUs. The VTU feeds the EFB if installed.
The video display is accessed through the normal MFW drop-down
menu or can be accessed from the COCKPIT DOOR panel. When the
VIDEO DSPL L pushbutton is pressed, the video is shown on DU 3.
Pressing VIDEO DSPL R moves the display to DU 5. The VIDEO DSPL
L (R) pushbutton can be used to cycle through the video display from
each camera.
The EFB video display is controlled from the EFB.
Copyright © Bombardier Inc.
CS130-21.12-06.00-121418
TECHNICAL TRAINING MANUAL
For Training Purposes Only
23-2
23 - Communication
23-73 Flight Deck Door Surveillance System
(Option)
CKPT DOOR
ENTRANCE COCKPIT DOOR - ENTRANCE
AREA 2
CAMERA
(3X)
AREA 3
ELECTRONIC FLIGHT BAG
(OPTIONAL)
DISPLAY UNIT 3 AND 5
VIDEO TRANSMISSION UNIT
LWR
DSPL
ISI
MAIN
BRT
INTEG
GSHLD
FLOOD
DIM
BRT
T
COCKPIT DOOR
UNLOCK
R
DENY
VIDEO
DSPL
COCKPIT DOOR PANEL
CAMERA CONTROL UNIT
CS1_CS3_2373_004
L
EMER ACCESS
Figure 1: Flight Deck Door Surveillance System
Copyright © Bombardier Inc.
CS130-21.12-06.00-121418
TECHNICAL TRAINING MANUAL
For Training Purposes Only
23-3
23 - Communication
23-73 Flight Deck Door Surveillance System
(Option)
GENERAL DESCRIPTION
Each camera is installed to provide a different field of view. The cameras
are capable of operating in low light conditions.
Each camera feeds the video transmission unit (VTU). A removable
flash drive, installed in the VTU, records the video. When the memory is
full, the oldest information is overwritten.
The VTU provides an output to the EFBs via an Ethernet BUS. If more
than one EFB is installed, each EFB can view a different video display.
The EFB video display is controlled from the EFB.
The VTU supplies the camera control unit which relays the camera
signals to DU 5 or DU 3. The cockpit door panel communicates with the
data concentrator unit module cabinet 1 (DMC 1) via an ARINC 429
BUS. The DMC 1 sends the camera selection information via discrete
lines to the VTU.
The FDDSS is powered by 28 VDC from the DC BUS 2.
Copyright © Bombardier Inc.
CS130-21.12-06.00-121418
TECHNICAL TRAINING MANUAL
For Training Purposes Only
23-4
23 - Communication
23-73 Flight Deck Door Surveillance System
(Option)
FWD ENTRY AREA CEILING
Entrance
Entr
Electronic
Flight Bag
Display
Unit 3
Display
Unit 5
Area 3
A
Flash
Drive
Video
Transmission
Unit
Camera
Control
Unit
DMC 1
Area 2
Cockpit
Door
Panel
CDC 4-5-5
CKPT DOOR VIDEO
DC
SSPC 3A
BUS 2
Logic: Always On
CDC
DMC
Control and Distribution Cabinet
Data Concentrator Unit Module Cabinet
ARINC 429
Ethernet
Discrete
Video
CS1_CS3_2373_003
LEGEND
FWD GALLEY AREA CEILING
Figure 2: FDDSS Block Diagram
Copyright © Bombardier Inc.
CS130-21.12-06.00-121418
TECHNICAL TRAINING MANUAL
For Training Purposes Only
23-5
23 - Communication
23-73 Flight Deck Door Surveillance System
(Option)
COMPONENT LOCATION
The flight deck door surveillance systems (FDDSS) consists of the
following components:
•
Video transmission unit (VTU)
•
Camera control unit (CCU)
•
Flight deck door surveillance camera (Refer to Figure 4.)
VIDEO TRANSMISSION UNIT
The VTU is located in the forward equipment bay.
CAMERA CONTROL UNIT
The CCU is located in the forward equipment bay.
Copyright © Bombardier Inc.
CS130-21.12-06.00-121418
TECHNICAL TRAINING MANUAL
For Training Purposes Only
23-6
23 - Communication
23-73 Flight Deck Door Surveillance System
(Option)
B
A
B CAMERA CONTROL UNIT
A VIDEO TRANSMISSION UNIT
CS1_CS3_2373_001
FORWARD EQUIPMENT BAY AFT SHELF
Figure 3: Video Transmission and Camera Control Units
Copyright © Bombardier Inc.
CS130-21.12-06.00-121418
TECHNICAL TRAINING MANUAL
For Training Purposes Only
23-7
23 - Communication
23-73 Flight Deck Door Surveillance System
(Option)
FLIGHT DECK DOOR SURVEILLANCE CAMERA
There are three flight deck door surveillance cameras located in the
forward galley.
Copyright © Bombardier Inc.
CS130-21.12-06.00-121418
TECHNICAL TRAINING MANUAL
For Training Purposes Only
23-8
23 - Communication
23-73 Flight Deck Door Surveillance System
(Option)
Area 3
Entrance
FWD GALLEY AREA FDDSS CAMERAS
CS1_CS3_2373_002
Area 2
Figure 4: FDDSS Cameras
Copyright © Bombardier Inc.
CS130-21.12-06.00-121418
TECHNICAL TRAINING MANUAL
For Training Purposes Only
23-9
23 - Communication
23-73 Flight Deck Door Surveillance System
(Option)
CONTROLS AND INDICATIONS
COCKPIT DOOR PANEL
The cockpit door panel L or R pushbuttons determines which DU video is
displayed on. Pressing L selects DU 3, and pressing R selects DU 5.
When the VIDEO DSPL L (R) pushbutton has been pressed, the
ENTRANCE video is displayed. Pressing the VIDEO DSPL L (R) button
again provides the video from AREA 2 camera. Pressing the VIDEO
DSPL L (R) button a third time provides the video from AREA 3 camera.
Copyright © Bombardier Inc.
CS130-21.12-06.00-121418
TECHNICAL TRAINING MANUAL
For Training Purposes Only
23-10
23 - Communication
23-73 Flight Deck Door Surveillance System
(Option)
LWR
OFF
DSPL
ISI
MAIN
BRT
INTEG
GSHLD
DIM
BRT
FLOOD
OFF
BRT
T
COCKPIT DOOR
UNLOCK
L
EMER ACCESS
R
DENY
VIDEO
DSPL
CS1_CS3_2373_005
COCKPIT DOOR PANEL
Figure 5: FDDSS Controls
Copyright © Bombardier Inc.
CS130-21.12-06.00-121418
TECHNICAL TRAINING MANUAL
For Training Purposes Only
23-11
23 - Communication
23-73 Flight Deck Door Surveillance System
(Option)
VIDEO DISPLAY
The VIDEO MFW drop-down menu can be used to select the camera
video to be displayed.
The cameras are identified as:
•
ENTRANCE
•
AREA 2
•
AREA 3
The camera video currently being viewed is indicated above the video
display.
Copyright © Bombardier Inc.
CS130-21.12-06.00-121418
TECHNICAL TRAINING MANUAL
For Training Purposes Only
23-12
23 - Communication
23-73 Flight Deck Door Surveillance System
(Option)
CKPT DOOR
ENTRANCE COCKPIT DOOR - ENTRANCE
AREA 2
MULTIFUNCTION WINDOW
CS1_CS3_2373_012
AREA 3
Figure 6: FDDSS Video Display
Copyright © Bombardier Inc.
CS130-21.12-06.00-121418
TECHNICAL TRAINING MANUAL
For Training Purposes Only
23-13
23 - Communication
23-73 Flight Deck Door Surveillance System
(Option)
OPERATION
FDDSS VIDEO DISPLAY ACCESS
The video display is normally accessed using the COCKPIT DOOR
panel VIDEO DSPL L (R) pushbuttons.
Pressing the DATA pushbutton on the multifunction keypad panel (MFP)
and control tuning panel (CTP) brings up a drop-down menu. Select the
VIDEO to access the FDDSS page.
Pressing the MENU pushbutton on the cursor control panel (CCP)
displays a drop-down menu on the MFW. Selecting the DATA icon brings
a second level menu. Select VIDEO to access the FDDSS page.
Copyright © Bombardier Inc.
CS130-21.12-06.00-121418
TECHNICAL TRAINING MANUAL
For Training Purposes Only
23-14
23 - Communication
23-73 Flight Deck Door Surveillance System
(Option)
RANGE
BRT
INBD DSPLY
L
TERR
R
133.700
MAP
FMS
CNS
CHKL
SYN
DATA
IN
TFC
BARO
17
SQ OFF
112.80
AUTO
1200
HPA
121.900
NAV1
4
MAP
MAP
CHART
IDENT
FMS
VIDEO
1/2
CNS
TUNE/
MENU
25 SEL
110.50
110.00 H
XPDR/TCAS
REPLY
TA/RA
ABV/BLW
N45132
NEXT PAGE
WX
OFF
VHF1
ADF1
TUNE/DATA
STATUS
FUEL
DOC
DBASE
SYN
CONTROL TUNING PANEL
DATA
ELEC
FLT CTRL
HYD
AVIONIC
INFO
CB
FWD
AFT
CARGO
A/C HEALTH
LO
22 °C
22 °C
22 °C -+ 2 22 °C -+ 2
MAINTENANCE
15°CC
10 °°CC
15 °CC
HI LOAD MON
NAV
SRC
DOOR
CKPT
KPT
23 °C
222 °C
CHKL
230.0
AIR
15 °CC
LICENSE MGMT
12345678901234567890
MSG
ROUTE
D
DATALOAD
DEP/
ARR
CNCL
EXEC
RAM AIR
TRIM AIR
INFO MGMT
R PACK
L PACK
ACK
DSPL SEL
UPR
CLR/
DELL
E
N
T
E
R
DSK
K
LWR
MENU
45
PSI
MAP
PREV
CHKL
SYN
XBLEED
45
PSI
NEXT
CAS
DATA
MULTIFUNCTION KEYPAD PANEL
L
EMER ACCESS
R
DENY
CURSOR CONTROL PANEL
VIDEO
DSPL
APU
MULTIFUNCTION WINDOW
COCKPIT DOOR PANEL
CS1_CS3_2373_010
COCKPIT DOOR
UNLOCK
Figure 7: FDDSS Video Display Access
Copyright © Bombardier Inc.
CS130-21.12-06.00-121418
TECHNICAL TRAINING MANUAL
For Training Purposes Only
23-15
23 - Communication
23-73 Flight Deck Door Surveillance System
(Option)
Page Intentionally Left Blank
Copyright © Bombardier Inc.
CS130-21.12-06.00-121418
TECHNICAL TRAINING MANUAL
For Training Purposes Only
23-16
ATA 23 - Communication
High Frequency
Communication System
(Option)
BD-500-1A10
BD-500-1A11
23 - Communication
23-12 High Frequency Communication System
(Option)
Table of Contents
23-12 High Frequency Communication System .....................23-2
Introduction .......................................................................23-2
General Description ..........................................................23-4
Component Location ........................................................23-6
Antenna........................................................................23-6
HF Antenna Couplers ..................................................23-6
HF Antenna Strap ........................................................23-6
HF Transceivers...........................................................23-6
Component Information ....................................................23-8
HF Antenna Coupler ....................................................23-8
Detailed Description .......................................................23-10
Monitoring and Tests ......................................................23-12
Tests ..........................................................................23-12
Copyright © Bombardier Inc.
CS130-21.12-06.00-121418
TECHNICAL TRAINING MANUAL
For Training Purposes Only
23-i
23 - Communication
23-12 High Frequency Communication System
(Option)
List of Figures
Figure 1: High Frequency Communication System .............23-3
Figure 2: High Frequency Communication System
Block Diagram ......................................................23-5
Figure 3: High Frequency Radio Component
Location ................................................................23-7
Figure 4: High Frequency Antenna Coupler ........................23-9
Figure 5: High Frequency Detailed Description .................23-11
Figure 6: High Frequency Test ...........................................23-13
Copyright © Bombardier Inc.
CS130-21.12-06.00-121418
TECHNICAL TRAINING MANUAL
For Training Purposes Only
23-ii
23 - Communication
23-12 High Frequency Communication System
(Option)
Page Intentionally Left Blank
Copyright © Bombardier Inc.
CS130-21.12-06.00-121418
TECHNICAL TRAINING MANUAL
For Training Purposes Only
23-iii
23 - Communication
23-12 High Frequency Communication System
(Option)
HIGH FREQUENCY COMMUNICATION SYSTEM
Copyright © Bombardier Inc.
CS130-21.12-06.00-121418
TECHNICAL TRAINING MANUAL
For Training Purposes Only
23-1
23 - Communication
23-12 High Frequency Communication System
(Option)
23-12 HIGH FREQUENCY COMMUNICATION
SYSTEM
INTRODUCTION
The high frequency (HF) communication system provides long range
communication in the frequency range of 2.000 MHz to 29.999 MHz.
There are two HF communication systems that operate independent of
each other, providing amplitude modulation (AM) and single sideband
(SSB) operation. Each system has an HF transceiver that receives and
transmits through the tail-mounted HF antenna. The antenna coupler is
responsible for maximizing the radiated output power by matching the
antenna to the transceiver selected frequency.
Tuning and control of the HF radios is primarily carried out from the
glareshield-mounted control tuning panels (CTPs) through the radio
interface units. Tuning is also possible from the radio tuning system
application (RTSA).
Copyright © Bombardier Inc.
CS130-21.12-06.00-121418
TECHNICAL TRAINING MANUAL
For Training Purposes Only
23-2
23 - Communication
23-12 High Frequency Communication System
(Option)
RANGE
BRT
INBD DSPLY
L
R
23.1750
MAP
FMS
CNS
CHKL
SYN
DATA
SQ0 UV
HF1
OFF
TUNE/
MENU
17.9460
UV
VHF3
IDENT
DATA
TERR
IN
TFC
WX
RADIO
INTERFACE
UNIT (2X)
BARO
HPA
1420.0
ADF1
1160.0
1/2
TUNE/DATA
NEXT PAGE
NAV
SRC
CONTROL TUNING PANEL (2X)
TUNE
DLK
CPDLC
SATCOM
VHF1...
VHF2...
120.900
119.750
RECALL
RECALL
127.100
126.450
NAV1...
NAV2...
AUTO
116.30
DME
PRESET
HOLD
116.80
FLT ID
23.1750
ADF1...
360.0
PRESET
DME
HOLD
114.10
VHF3...
BD100
ALT LIM ABV/BLW
HF1...
MK-HI
AUTO
AUTO
116.30
112.30
XPDR TCAS...
2512
GWX
DATA
HF2...
21.8750
ADF2...
278.0
RECALL
RECALL
248.0
332.0
PRESET
108.00
HF ANTENNA
COUPLER (2X)
HF TRANSCEIVER
(2X)
RADIO TUNING
SYSTEM APPLICATION
GROUND
STATIONS
CS1_CS3_2300_018
NAV3...
110.50
Figure 1: High Frequency Communication System
Copyright © Bombardier Inc.
CS130-21.12-06.00-121418
TECHNICAL TRAINING MANUAL
For Training Purposes Only
23-3
23 - Communication
23-12 High Frequency Communication System
(Option)
GENERAL DESCRIPTION
The HF communication system provide both simplex and half-duplex
communication in upper sideband (USB), lower sideband (LSB) and
amplitude modulation equivalent (AME). The HF transceivers operate in
the 2.000 MHz to 29.999 MHz frequency range in 100 Hz increments
and have a user selectable power output.
The transmit power is set by selecting the line key adjacent to POWER
on the control tuning panel (CTP) to enable low (LO), medium (MED) or
high (HI) transmit power. The active power level is displayed in large font
cyan.
In simplex communication, the transmitting and receiving frequencies
are the same. In half-duplex communication, the transmitting and
receiving frequencies are different.
The receive-through-tuned coupler mode is set only from the respective
transmit mode. When not transmitting, the high frequency (HF) system
automatically enters the receive-through-tuned coupler mode. The
receive-through-tuned coupler state is useful when weak or noisy signals
are being received. Optimum signal reception is achieved, however, the
second HF communication system is disconnected from the antenna.
The system changes to dual receive mode when the frequency or
transmission mode is changed.
HF system no. 1 transceiver and antenna coupler are powered by DC
ESS BUS 1. HF system no. 2 transceiver and antenna coupler are
powered by DC BUS 2.
The HF transceiver provides the transmit signal and power to the
antenna, and processes the received signal from the antenna. The HF
transceiver provides audio to the radio interface unit (RIU). The HF
transceiver also provides an audio output for the selective calling
(SELCAL) system decoder located in the RIU.
The HF antenna coupler enables bidirectional signal communication
between the HF antenna and transceivers. During automatic tuning, the
antenna coupler matches the power amplifier in the HF transceiver to the
antenna to maximize the radiated power output. The antenna is a
shunt-type antenna and is part of the vertical fin.
In the dual HF system installations, the system configures to one of three
modes. When the system powers up, it operates in the dual receive
mode. Both receivers are connected to the same antenna and the
respective antenna coupler tuning networks are bypassed so the
received signals are applied directly to each receiver.
In the transmit mode, the antenna coupler is tuned to match the antenna
with the HF transceiver. The other HF system is disconnected from the
antenna and is unable to receive or transmit.
Copyright © Bombardier Inc.
CS130-21.12-06.00-121418
TECHNICAL TRAINING MANUAL
For Training Purposes Only
23-4
23 - Communication
23-12 High Frequency Communication System
(Option)
DC ESS BUS 1
HF TRANSCEIVER 1
DMC 1
TUNE
RADIO
INTERFACE
UNIT 1
DLK
CPDLC
VHF1...
VHF2...
120.900
119.750
RECALL
RECALL
127.100
126.450
NAV1...
NAV2...
116.30
DME
PRESET
AUTO
116.30
HOLD
PRESET
116.80
BRT
112.30
XPDR TCAS...
OFF
HF1 CONTROL
HF COUPLER 1
HF ANTENNA
2.8620
17.9460
TUNE/
MENU
POWER
SIMPLEX
IDENT
SQ0 UV
LO/MED/HI
2512
MK-HI
AUTO
AUTO
DME
FLT ID
HOLD
114.10
VHF3...
BD100
ALT LIM ABV/BLW
DATA
UV
PRESET
PAGE
DUPLEX
TEST
HF1...
23.1750
1/2
ADF1...
TUNE/DATA
360.0
RETURN
HF2...
21.8750
ADF2...
278.0
RECALL
RECALL
248.0
332.0
NAV3...
110.50
CONTROL TUNING
PANEL (2X)
PRESET
108.00
RTSA
RADIO
INTERFACE
UNIT 2
LEGEND
DC BUS 2
HF TRANSCEIVER 2
DMC 2
ARINC 429
Discrete
CS1_CS3_2312_012
HF COUPLER 2
Figure 2: High Frequency Communication System Block Diagram
Copyright © Bombardier Inc.
CS130-21.12-06.00-121418
TECHNICAL TRAINING MANUAL
For Training Purposes Only
23-5
23 - Communication
23-12 High Frequency Communication System
(Option)
COMPONENT LOCATION
The HF radio communication system consists of the following
components:
•
Antenna
•
HF antenna couplers
•
HF antenna strap
•
HF transceivers
ANTENNA
The HF antenna is an integral part of the leading edge of the vertical
stabilizer.
HF ANTENNA COUPLERS
The two HF antenna couplers are installed in an HF coupler mount on
the front spar of the vertical stabilizer, behind the dorsal fairing.
HF ANTENNA STRAP
The HF antenna strap is attached to the HF coupler mount.
HF TRANSCEIVERS
Two HF transceivers are installed in the aft equipment bay.
Copyright © Bombardier Inc.
CS130-21.12-06.00-121418
TECHNICAL TRAINING MANUAL
For Training Purposes Only
23-6
23 - Communication
23-12 High Frequency Communication System
(Option)
HF
Antenna
A
HF Antenna
Strap
B
HF Antenna
Coupler 2
HF 2
HF Antenna
Coupler 1
HF Coupler
Mount
HF Transceiver
Mount
B HF TRANSCEIVERS
CS1_CS3_2312_003
A HF ANTENNA COUPLER
HF 1
Figure 3: High Frequency Radio Component Location
Copyright © Bombardier Inc.
CS130-21.12-06.00-121418
TECHNICAL TRAINING MANUAL
For Training Purposes Only
23-7
23 - Communication
23-12 High Frequency Communication System
(Option)
COMPONENT INFORMATION
WARNING
HF ANTENNA COUPLER
The antenna coupler is configured by the tune data from the transceiver.
The configuration matches the radio frequency (RF) tuner for proper
phasing and minimum voltage standing wave ratio (VSWR) to provide
maximum power transfer to the antenna. The antenna coupler receives
and transmits RF signals to and from the HF transceiver through a
coaxial cable.
Each antenna coupler has the capability to learn and store tuning data
for 99 preset channels, and the last 50 manually tuned frequencies. The
channels are stored during the first tune cycle. The antenna coupler
tunes all frequencies in the HF band within 1 second.
The HF antenna coupler is pressurized with 6+/-1 psi with nitrogen
through the nitrogen service port to prevent arcing in high altitude
operation.
The feedline adapter connects the HF coupler mount to the HF antenna
strap. The other end of the HF antenna strap is connected to the
antenna. The feedline adapter consists of a center conductor stud that is
mounted to an insulation disk and connected to the HF coupler mount.
1. DUE TO THE HAZARDS OF HF RADIATION, A HIGH
POWER TRANSMITTER TEST MUST NOT BE DONE IN
THE HANGAR.
2. PERSONNEL MUST KEEP A DISTANCE OF 3 M (10 FT) OR
MORE FROM THE HF ANTENNA DURING A TEST. THE
RADIO FREQUENCY CAN BURN PERSONNEL WHO ARE
NEAR THE HF ANTENNA.
CAUTION
1. Make sure that the aircraft is 183 m (600 ft) from a
refuel/defuel operation when the HF system is being
tested. The HF antenna transmits a radio frequency that
can cause a fire or an explosion.
2. Do not leave the transmitter keyed for more than
30 seconds. Damage to the equipment can occur.
When the HF coupler mount has a single antenna coupler installed, an
HF antenna port can covers the unused antenna port of the mount to
provide physical and electromagnetic interference protection.
Copyright © Bombardier Inc.
CS130-21.12-06.00-121418
TECHNICAL TRAINING MANUAL
For Training Purposes Only
23-8
23 - Communication
23-12 High Frequency Communication System
(Option)
Feedline
Adapter
HF Antenna
Port
Nitrogen
Service Port
HF Coupler
Mount
HF ANTENNA COUPLER
CS1_CS3_2312_014
HF Antenna
Port Can
Figure 4: High Frequency Antenna Coupler
Copyright © Bombardier Inc.
CS130-21.12-06.00-121418
TECHNICAL TRAINING MANUAL
For Training Purposes Only
23-9
23 - Communication
23-12 High Frequency Communication System
(Option)
DETAILED DESCRIPTION
In the dual HF installation, the two systems are identical and
independent. Both may be operated simultaneously in receive mode, but
only one can operate in transmit mode at any given time.
For dual HF installations, the antenna couplers are interconnected as
follows:
•
The Ext Elem E Out is connected to the Status A In of the opposite
coupler. It indicates when the system is transmitting
The antenna coupler is responsible for maximizing the radiated output
power by matching the antenna to the transceiver selected frequency.
When the HF transceiver receives the tune data, the HF transceiver
sends the data to the antenna coupler. The HF transceiver and antenna
coupler communicate using a high-speed fiber optic link. Control and
status information are exchanged using this interface.
•
The Ext Elem F Out is connected to the Status B In of the opposite
coupler. It indicates when the system is in dual receive state
•
The Ext Elem Pwr Out is connected to the Ext Elem Pwr In of the
opposite coupler. It indicates when 28 VDC is applied to the system.
If the 28 VDC power is removed from one system, the opposite
system reverts to single system operation
When a new frequency is selected, and the push-to-talk (PTT) button is
momentarily pushed, the coupler tunes to the new frequency. When a
PTT button is pressed and held, the radio interface unit (RIU) provides a
ground through the keyline, which puts the HF in the transmit mode. The
HF transceiver sends a Tune in Progress discrete to the onside RIU for
use by the audio control panel (ACP) to generate a tune tone. A steady
1000 Hz tone is heard in the headsets as the coupler tunes.
The HF transceiver includes a self-test function that performs special
transmit and receive diagnostic functions to determine its operational
health. The results of the self-test function are used to determine
whether the unit should continue operation. Faults determined during the
self-test are stored in archival fault storage memory and are also
reported to the onboard maintenance system (OMS).
The HF transceiver provides the transmit signal and power to the
antenna, and processes the received signal from the antenna. The HF
transceiver provides a combined receiver audio with sidetone audio
output only to the RIU. The HF transceiver also provides unsquelched,
low-power audio for connection to the selective calling (SELCAL) system
decoder located in the RIU.
The HF transceiver sends tuning echo and diagnostics data back to its
onside RIU over an ARINC 429 BUS.
The HF transceiver provides received audio to the RIU, where it is
digitized for distribution. It also provides SELCAL audio to the RIU.
Copyright © Bombardier Inc.
CS130-21.12-06.00-121418
TECHNICAL TRAINING MANUAL
For Training Purposes Only
23-10
23 - Communication
23-12 High Frequency Communication System
(Option)
LEGEND
ARINC 429
Analog
Discrete
HF ANTENNA
Power
RF COAX
Fiber Optic (ARINC 818)
HF ANTENNA
COUPLER 2
HF ANTENNA
COUPLER 1
Ant Out
HF COMM
TRANSCEIVER 1
Ext Elem Pwr Out
Ext Elem E Out
Ext Elem F Out
RF I/O
RF I/O
Ext Elem Pwr In
Status A In
Status B In
Ant Out
HF COMM
TRANSCEIVER 2
Ext Elem Pwr In
Status A In
Status B In
Ext Elem Pwr Out
Ext Elem E Out
RF I/O
Ext Elem F Out
RIU 2
RIU 1
Keyline In
Keyline In
HF MIC
Audio Out
HF 1 MIC
Audio In
SELCAL
Audio Out
HF 1 SELCAL
Audio In
HF Tune In Progress Out
HF Tune In Progress In
HF 2 MIC
Audio In
HF MIC
Audio Out
HF 2 SELCAL
Audio In
SELCAL
Audio Out
HF Tune In Progress In
HF 1 MIC
Audio Out
HF 2 MIC
Audio Out
HF Tune In Progress Out
HF MIC
Audio In
CS1_CS3_2312_002
HF MIC
Audio In
RF I/O
Figure 5: High Frequency Detailed Description
Copyright © Bombardier Inc.
CS130-21.12-06.00-121418
TECHNICAL TRAINING MANUAL
For Training Purposes Only
23-11
23 - Communication
23-12 High Frequency Communication System
(Option)
MONITORING AND TESTS
TESTS
The self-test can be initiated from the CTP, or from the display tuning HF
control page. After selection, the test annunciation is highlighted for the
duration of the active test. A green PASS or amber FAIL is displayed
under TEST when the test is completed. The PASS or FAIL status
remains displayed until the HF control page dialog box is closed.
Copyright © Bombardier Inc.
CS130-21.12-06.00-121418
TECHNICAL TRAINING MANUAL
For Training Purposes Only
23-12
23 - Communication
23-12 High Frequency Communication System
(Option)
RANGE
L
MAP
TERR
BRT
INBD DSPLY
CHKL
FMS
IN
TFC
CNS
SYN
DATA
BARO
OFF
HF1 CONTROL
R
HPA
IN TEST
17.9460
TUNE/
MENU
POWER
SIMPLEX
IDENT
LO/MED/HI
UV
DUPLEX
PRESET
PAGE
TEST
1/2
TUNE/DATA
RETURN
WX
NAV
SRC
HF1 CONTROL
2.8620
17.9460
SIMPLEX
Test pass
POWER
LO/MED/HI
Test fail
PRESET
PAGE
HF1 CONTROL TEST
Indication
PASS
FAIL
Condition
RETURN
UV
DUPLEX
TEST
FAIL
CS1_CS3_2312_004
SQ0 UV
Figure 6: High Frequency Test
Copyright © Bombardier Inc.
CS130-21.12-06.00-121418
TECHNICAL TRAINING MANUAL
For Training Purposes Only
23-13
23 - Communication
23-12 High Frequency Communication System
(Option)
Page Intentionally Left Blank
Copyright © Bombardier Inc.
CS130-21.12-06.00-121418
TECHNICAL TRAINING MANUAL
For Training Purposes Only
23-14
ATA 27 - Flight Controls
Steep Approach
(Option)
BD-500-1A10
BD-500-1A11
27 - Flight Controls
27-00 Steep Approach
(Option)
Table of Contents
27-00 Steep Approach............................................................27-2
General Description ..........................................................27-2
Steep Approach Interface .................................................27-4
Operation ..........................................................................27-6
Controls and Indications ...................................................27-8
FMS PERF ARR Page.................................................27-8
Head-Up Display..........................................................27-8
Primary Flight Display ..................................................27-8
Monitoring and Tests ......................................................27-10
CAS Messages ..........................................................27-11
Copyright © Bombardier Inc.
CS130-21.12-06.00-121418
TECHNICAL TRAINING MANUAL
For Training Purposes Only
27-i
27 - Flight Controls
27-00 Steep Approach
(Option)
List of Figures
Figure 1:
Figure 2:
Figure 3:
Figure 4:
Steep Approach Overview ....................................27-3
Steep Approach Operation ...................................27-5
Operation ..............................................................27-7
Controls and Indications .......................................27-9
Copyright © Bombardier Inc.
CS130-21.12-06.00-121418
TECHNICAL TRAINING MANUAL
For Training Purposes Only
27-ii
27 - Flight Controls
27-00 Steep Approach
(Option)
Page Intentionally Left Blank
Copyright © Bombardier Inc.
CS130-21.12-06.00-121418
TECHNICAL TRAINING MANUAL
For Training Purposes Only
27-iii
27 - Flight Controls
27-00 Steep Approach
(Option)
STEEP APPROACH
Copyright © Bombardier Inc.
CS130-21.12-06.00-121418
TECHNICAL TRAINING MANUAL
For Training Purposes Only
27-1
27 - Flight Controls
27-00 Steep Approach
(Option)
27-00 STEEP APPROACH
GENERAL DESCRIPTION
The optional steep approach mode on the CS100 enables landings
using CAT 1 ILS, or visual approaches at angles between 4.5° to 5.5°
instead of a normal 3° approach. The autopilot can also be used to fly
the approach down to 200 ft, at which point the autopilot must be
disconnected and the remainder of the approach flown manually. To fly
the steep approach profile, several systems are configured for optimized
aircraft performance.
When a steep approach is carried out, the following configuration is
used:
•
Slats deployed
•
Flaps extended
•
Landing gear down
•
Engine idle approach speed is reduced
•
Environmental control system (ECS) configured to reduce bleed air
demand on the engine
The fly-by-wire (FBW) system control laws (CLAWS) extend the
multifunction spoilers (MFS) 2 and MFS 3 to a preset value when steep
approach is enabled, and retract them during flare or a go-around.
Visual and aural cues are provided on the flight deck to enable the
transition from approach to landing.
Copyright © Bombardier Inc.
CS130-21.12-06.00-121418
TECHNICAL TRAINING MANUAL
For Training Purposes Only
27-2
27 - Flight Controls
27-00 Steep Approach
(Option)
MFS 2 and 3
Deployed
Slats
Deployed
5.5º Steep
Approach
Landing
Gear Down
Flaps Fully
Extended
Lower Idle Thrust
Reduced Bleed Air Demand
CS1_CS3_2200_075
Typical 3º
Approach
Figure 1: Steep Approach Overview
Copyright © Bombardier Inc.
CS130-21.12-06.00-121418
TECHNICAL TRAINING MANUAL
For Training Purposes Only
27-3
27 - Flight Controls
27-00 Steep Approach
(Option)
STEEP APPROACH INTERFACE
The steep approach mode resides in the primary flight control computers
(PFCCs) CLAWS. The steep approach function evaluates the steep
approach availability, determines the steep approach states, and reports
them to the interfacing systems. The PFCCs interface with other
required systems to provide logic for determining steep approach
availability, arm and engage states, and disengage logic.
The steep approach selection box on the FMS enables the PFCC steep
approach function. Selection of STEEP APPR checkbox is only available
when the approach angle, provided by the FMS NAV database, is
greater than 4.5°.
The PFCCs use the following inputs during a steep approach:
•
Landing gear lever position and weight-on-wheels (WOW) from
landing gear steering control unit (LGSCU) 1 and LGSCU 2
•
Slat/flap lever position from slat flap electronic control unit (SFECU)
1 and SFECU 2
•
Takeoff/go-around from the throttle quadrant assembly (TQA)
•
Radio altitude from radio altimeter (RA) 1, RA 2, and RA 3 if installed
•
Vertical speed from the inertial reference system (IRS) 1, IRS 2, and
IRS 3
The RA signals are used in the steep availability state and steep arm
logic. They are also used to determine when to retract the MFS. The
steep approach aural callouts STANDBY and FLARE are generated as a
function of vertical speed and radio altitude and to indicate when to
initiate the flare maneuver.
The electronic engine controllers (EECs) modify the engine limits when
the steep approach mode is engaged. This provides a lower idle speed
than the normal approach, while maintaining go-around capabilities. The
steep approach engaged discrete from the PFCC to the EECs activates
the steep approach mode in-flight.
Copyright © Bombardier Inc.
CS130-21.12-06.00-121418
The EECs de-activate the steep approach mode 2 seconds after WOW
or when the steep approach engaged discrete from the PFCC is not
available.
The EECs provide a steep approach inoperative signal if the following
occurs:
•
No valid data is received from the PFCCs for more than 5 seconds
•
Engine operation is degraded
•
Radio altimeter fault occurs
The integrated air system controllers reconfigure the environmental
control system (ECS) to accommodate the required engine bleed for the
approach. For a dual or single engine bleed with wing anti-ice (WAI) off,
the cargo heat remains on if selected, the ECS is set to the high flow
schedule, and the fuel tank inerting system remains on. For a
dual-engine bleed with WAI on, the cargo heat is inhibited, the ECS is
set to ventilation flow, and the fuel tank inerting system (FTIS) is
inhibited.
A steep approach in single engine bleed with WAI on is prohibited. The
EEC may not be able to provide a low enough thrust level and maintain
the required bleed demand.
During a steep approach, the terrain awareness warning system (TAWS)
mode 1 is desensitized and TAWS aural alerts, other than WINDSHEAR,
are inhibited below 185 ft radio altitude to ensure that the steep aural
callouts are available.
The steep approach armed and engage modes are displayed on the
primary flight display (PFD) and the head-up display (HUD).
If the steep approach function is selected and steep approach is not
available, a STEEP NOT AVAIL caution message is displayed until the
function is deselected on the flight management system (FMS).
The steep approach and autoland modes (refer to ATA 22) are not
compatible and cannot be used together. If autoland is engaged, the
steep approach function cannot be selected. If steep approach is
selected, the autoland mode cannot be engaged.
TECHNICAL TRAINING MANUAL
For Training Purposes Only
27-4
27 - Flight Controls
27-00 Steep Approach
(Option)
DBASE
DEP
TRANS
POS
CLB
STAR
FPLN
CRZ
TRANS
APPR
LAV1G
I27
ARRIVALS...
PERF
ROUTE
DES
STEEP
STEEP ARM
ARR
ARRIVAL DATA... TEMP COMP...
HUD
AIRPORT (PERF)
EGLC
OAT
15
RWY WIND
°C
SLAT/FLAP
ARRIVALS
5
QNH
---°/--GD
- EGLC
TRANS
STEEP APPR
LW
/
F1
F2
F3
STARS199
(15) 211TRANS196
ALT
1013
26
F4
ACTF5FPLN
169 APPR159(6) 149
LAV1G
ILS
VECTORS
ILS
09
ALKIN
ILS
27
GODL1D
LAV1G
LOC
09
GODL1F
LAV1J
LOC
27
VREF
GODL1A
130 +
GODL1C
--
STEEP
STEEP
27
PFD
SET VSPEEDS
STEEP NOT AVAIL
112960 LB
STEEP APPR
GO AROUND
VAC
130 OTHER AIRPORT
VGA
F3
F2
F1
F0
GD
---125
128
159
173
199
DEPARTURES...
ARRIVAL DATA...
EICAS
DONE
THRUST...
MSG...
Landing Gear
Lever Position
Steep Armed
Steep Engaged
TAWS Voice
Callouts Inhibit
DMC 1
and
DMC 2
FTIS ICU
ECS Flow Schedule
Cargo Heat
Wing Anti-Ice
IASC 1 and IASC 2
“STAND BY”
“FLARE”
WOW
LGSCU 1 and LGSCU 2
Slap/Flap Control
Lever Position
FLIGHT CONTROL LAWS SOFTWARE
L EEC and R EEC
ARINC 429
Data Concentrator Unit Module Cabinet
Electronic Engine Control
Flight Management System
Fuel Tank Inerting System
Head Up Display
Integrated Air System Controller
Inerting Control Unit
Inerting Reference System
Landing Gear and Steering Control Unit
Primary Flight Display
Radio Interface Unit
Slat Flap Electronic Control Unit
Terrain Awareness and Warning System
Takeoff/Go-Around
Throttle Quadrant Assembly
RIU 1 and RIU 2
Inhibit
Steep Inop
DMC
EEC
FMS
FTIS
HUD
IASC
ICU
IRS
LGSCU
PFD
RIU
SFECU
TAWS
TOGA
TQA
VIEW ALL
140
FMS
Engine Running
LEGEND
SFECU 1 and SFECU 2
AUTOLAND
Autoland Engaged
Steep Armed
Steep Engaged
TOGA
Steep Approach
Function
TQA
Steep
Stick
Enabled Shaker
Radio Altitude
RADIO ALTIMETER 1, 2 and 3
TAWS Inhibit
Normal Control Laws
TAWS
Vertical Speed
IRS 1, 2 and 3
Spoiler Commands
PFCC 1, 2, and 3
CS1_CS3_2200_072
ACT
FMS1
Figure 2: Steep Approach Operation
Copyright © Bombardier Inc.
CS130-21.12-06.00-121418
TECHNICAL TRAINING MANUAL
For Training Purposes Only
27-5
27 - Flight Controls
27-00 Steep Approach
(Option)
OPERATION
The steep approach function responsible for enabling CLAWS flight
spoiler deployment and retraction consists of three states:
•
Steep approach available – No faults detected
•
Steep approach armed – Arms the function above 1000 ft radio
altitude
•
Steep approach engaged – Activates when the aircraft landing gear
is down and flap 5 is selected
When the steep approach function is engaged, MFS 2 and MFS 3 are
deployed to a predefined deflection in order to provide the glideslope
capability for steep approach. With the spoiler lever retracted, MFS 2
extends to 18° and MFS 3 extends to 34°. Prior to or during the flare, the
MFSs are automatically retracted based on radio altitude, inertial vertical
speed, sidestick controller position, and angle-of-attack (AOA).
If required during steep approach mode, the MFSs are allowed to extend
beyond the predefined deflection to support roll assist and in-flight
proportional lift dumping (PLD). At touchdown, the MFSs perform their
normal ground lift dump function.
The aural STANDBY callout is based on vertical descent rate and occurs
approximately 1.25 seconds before the FLARE callout. The FLARE
callout is provided approximately 0.5 seconds before the flare height,
based on descent rate. The steep approach preflare STANDBY voice
and the steep approach FLARE aural messages are also associated
with visual cues displayed on the PFD and HUD.
The steep approach function disengages when:
•
Flaps or landing gear are not in approach configuration
•
Failure of any steep approach related system
•
Go-around
•
Windshear
•
Aircraft is on the ground
Copyright © Bombardier Inc.
CS130-21.12-06.00-121418
TECHNICAL TRAINING MANUAL
For Training Purposes Only
27-6
27 - Flight Controls
27-00 Steep Approach
(Option)
AP
AT OR PRIOR GS INTERCEPT
ALTS
• Flaps 5
• Landing gear down
• MFS 2 and MFS 3 deployed
ALTS
STEEP
STEEP
PRIOR TO INTERCEPT
• LS APPR selected on FMS
• STEEP APPR selected
• Above 1000 ft radio altitude
AT FLARE PHASE INITIATION
• STANDBY callout
• After 1.25 s FLARE callout
• MFS 2 and MFS 3 retracted
“FLARE”
DURING FLARE PHASE
• On touchdown, MFS perform normal ground lift dump function
CS1_CS3_2200_074
“STANDBY”
Figure 3: Operation
Copyright © Bombardier Inc.
CS130-21.12-06.00-121418
TECHNICAL TRAINING MANUAL
For Training Purposes Only
27-7
27 - Flight Controls
27-00 Steep Approach
(Option)
CONTROLS AND INDICATIONS
FMS PERF ARR PAGE
The steep approach mode is selected from the FMS PERF ARR page
pop up box. The steep approach function can be selected at any time
prior to the aircraft descending below 1000 ft radio altitude during the
approach.
When the pop up box is closed, the STEEP APPR message is shown on
the ARR tab, indicating the steep approach function is selected.
HEAD-UP DISPLAY
The head-up display (HUD) provides indication for steep approach
armed and engaged modes. It also provides the following flight guidance
information for the approach:
•
Approach path angle
•
Flight path vector (FPV)
•
Flare guidance line to initiate the flare
•
Flare stop line to stop the flare maneuver
PRIMARY FLIGHT DISPLAY
The STEEP message appears at the top of the roll scale on the primary
flight display (PFD). The message is white when steep approach is
armed and green when steep approach is engaged. The STEEP
message is removed if a fault is detected.
Copyright © Bombardier Inc.
CS130-21.12-06.00-121418
TECHNICAL TRAINING MANUAL
For Training Purposes Only
27-8
27 - Flight Controls
27-00 Steep Approach
(Option)
ACT
FMS1
DBASE
DEP
TRANS
POS
CLB
STAR
ARRIVALS...
FPLN
CRZ
PERF
DES
TRANS
APPR
LAV1G
I27
ROUTE
STATUS
ARR
STEEP ARM
STEEP
ARRIVAL DATA... TEMP COMP...
CONDITION
Armed.
Engaged.
AIRPORT (PERF)
EGLC
OAT
15
RWY WIND
°C
SLAT/FLAP
5
QNH
---°/---
/
GD
F1
F2
ARRIVALS - EGLC
TRANS
199
F3
211
196
169
STARS (15) TRANS
+ -130GODL1A
26
F4
F5
159
149
APPR
LAV1G
VREF
STEEP APPR
ALT
1013
ACT FPLN
(6)
ILS
VECTORS
SET
VSPEEDS
27
ILS
09
GODL1C
ALKIN
ILS
27
LW
GODL1D
LAV1G
LOC
09
112960 LB
GODL1F
LAV1J
LOC
27
GO AROUND
STEEP APPR
VAC
130
VGA
140
-5.5 approach
path angle
F3
125
OTHER AIRPORT
F2
F1
F0
GD
128
159
173
199
HUD
----
DEPARTURES...
ARRIVAL DATA...
FPV
VIEW ALL
Flare Stop Line
Flare Guidance Line
DONE
THRUST...
MSG...
FMS ARR PAGE
CONDITION
STEEP
Armed.
STEEP
Engaged.
PFD
CS1_CS3_2200_073
STATUS
Figure 4: Controls and Indications
Copyright © Bombardier Inc.
CS130-21.12-06.00-121418
TECHNICAL TRAINING MANUAL
For Training Purposes Only
27-9
27 - Flight Controls
27-00 Steep Approach
(Option)
MONITORING AND TESTS
The following page provides the crew alerting system (CAS) messages
for the steep approach mode.
Copyright © Bombardier Inc.
CS130-21.12-06.00-121418
TECHNICAL TRAINING MANUAL
For Training Purposes Only
27-10
27 - Flight Controls
27-00 Steep Approach
(Option)
CAS MESSAGES
Table 1: CAUTION Messages
MESSAGE
STEEP NOT AVAIL
Copyright © Bombardier Inc.
CS130-21.12-06.00-121418
LOGIC
Steep approach autoflight mode not available
and detected while mode is armed.
TECHNICAL TRAINING MANUAL
For Training Purposes Only
27-11
27 - Flight Controls
27-00 Steep Approach
(Option)
Page Intentionally Left Blank
Copyright © Bombardier Inc.
CS130-21.12-06.00-121418
TECHNICAL TRAINING MANUAL
For Training Purposes Only
27-12
ATA 34 - Navigation
Head-Up Display System
(Option)
BD-500-1A10
BD-500-1A11
34 - Navigation
34-32 Head-Up Display System
(Option)
Table of Contents
34-32 Head-Up Display System .............................................34-2
Introduction .......................................................................34-2
General Description ..........................................................34-4
Component Location ........................................................34-6
Synthetic Vision Module...............................................34-6
Overhead Unit..............................................................34-8
HUD Combiner.............................................................34-8
Controls and Indications .................................................34-10
HUD Combiner...........................................................34-10
Control Tuning Panel Menu .......................................34-12
HUDS Indications.......................................................34-14
Detailed Description .......................................................34-16
System Interface ........................................................34-16
Monitoring and Tests ......................................................34-18
CAS Messages ..........................................................34-20
Copyright © Bombardier Inc.
CS130-21.12-06.00-121418
TECHNICAL TRAINING MANUAL
For Training Purposes Only
34-i
34 - Navigation
34-32 Head-Up Display System
(Option)
List of Figures
Figure 1: Head-Up Display System .....................................34-3
Figure 2: Head-Up Display System .....................................34-5
Figure 3: Synthetic Vision Module Component
Location ................................................................34-7
Figure 4: HUD Component Location ...................................34-9
Figure 5: HUD Combiner Controls and
Indications ..........................................................34-11
Figure 6: Control Tuning Panel Menu ................................34-13
Figure 7: HUDS Indications ...............................................34-15
Figure 8: System Interface ................................................34-17
Figure 9: Monitoring and Tests ..........................................34-19
Copyright © Bombardier Inc.
CS130-21.12-06.00-121418
TECHNICAL TRAINING MANUAL
For Training Purposes Only
34-ii
34 - Navigation
34-32 Head-Up Display System
(Option)
Page Intentionally Left Blank
Copyright © Bombardier Inc.
CS130-21.12-06.00-121418
TECHNICAL TRAINING MANUAL
For Training Purposes Only
34-iii
34 - Navigation
34-32 Head-Up Display System
(Option)
HEAD-UP DISPLAY SYSTEM
Copyright © Bombardier Inc.
CS130-21.12-06.00-121418
TECHNICAL TRAINING MANUAL
For Training Purposes Only
34-1
34 - Navigation
34-32 Head-Up Display System
(Option)
34-32 HEAD-UP DISPLAY SYSTEM
INTRODUCTION
The head-up display (HUD) system generates and displays information
in the forward field of view of the pilot on an optical element. The
displayed information is derived from the aircraft instruments and sensor
data. The HUD provides information during all phases of flight.
The system consists of the following components:
•
Overhead unit (OHU)
•
Head-up display (HUD) combiner
•
Synthetic vision module (SVM) card
The HUDS option is available as a single or optional dual installation.
Copyright © Bombardier Inc.
CS130-21.12-06.00-121418
TECHNICAL TRAINING MANUAL
For Training Purposes Only
34-2
34 - Navigation
34-32 Head-Up Display System
(Option)
Overhead
Unit
Forward
Field of View
IPC 3
SVM
Combiner
Optional Second HUDS
SVM
CS1_CS3_3432_001
IPC 4
Second Overhead Unit
Figure 1: Head-Up Display System
Copyright © Bombardier Inc.
CS130-21.12-06.00-121418
TECHNICAL TRAINING MANUAL
For Training Purposes Only
34-3
34 - Navigation
34-32 Head-Up Display System
(Option)
GENERAL DESCRIPTION
The OHU receives the image data and flight symbology from the SVM
card. The liquid crystal display (LCD) inside the OHU, uses this data to
generate the enhanced flight symbology. This image is projected and
reflected by the combiner. The brightness of this image is controlled by
the HUD knob.
The information generated by the SVM card is derived from the NAV
system sensors. The HUDS displays flight director guidance from the
automatic flight control system (AFCS) during all phases of flight.
The system has a low visibility takeoff (LVTO) function, which provides
guidance during takeoff in reduced visibility conditions.
The HUDS is activated as soon the combiner is in its operating position,
the crew is able to control the parameters via the control tuning panel
(CTP).
The optional second overhead unit (R OHU) works similarly to the left
OHU and receives identical information from the data concentrator unit
module cabinet 2 (DMC 2), and the integrated processing cabinet 4
(IPC 4).
L OHU receives power from 28 VDC BUS 1, and R OHU from 28 VDC
BUS 2.
Copyright © Bombardier Inc.
CS130-21.12-06.00-121418
TECHNICAL TRAINING MANUAL
For Training Purposes Only
34-4
34 - Navigation
34-32 Head-Up Display System
(Option)
L OHU
DC BUS 2
COMBINER
DC BUS 1
Brightness
R OHU
(OPTIONAL)
IPC 4
IPC 3
SVM
SVM
NAV SYSTEM
DMC 1
DMC 2
BRT
MENU
FPV CAGE
<WXR
ON/OFF>
TUNE/
MENU
<CLOCK
PFD/NAV>
IDENT
HUD>
<STBY NAV
AFCS
1/2
TUNE/DATA
RETURN
AFDX
Analog
ARINC 429
Fiber Optics
CRS 126
CTP
CS1_CS3_3432_002
LEGEND
OFF
Figure 2: Head-Up Display System
Copyright © Bombardier Inc.
CS130-21.12-06.00-121418
TECHNICAL TRAINING MANUAL
For Training Purposes Only
34-5
34 - Navigation
34-32 Head-Up Display System
(Option)
COMPONENT LOCATION
The head-up display system contains the following components:
•
Synthetic vision module (SVM) card
•
Overhead unit (OHU)
•
Head-up display (HUD) combiner
SYNTHETIC VISION MODULE
The synthetic vision module (SVM) is located in IPC 3 for HUDS 1, and
in IPC 4 for HUDS 2. Both IPCs are located in the forward equipment
bay.
Copyright © Bombardier Inc.
CS130-21.12-06.00-121418
TECHNICAL TRAINING MANUAL
For Training Purposes Only
34-6
34 - Navigation
34-32 Head-Up Display System
(Option)
IPC 4
Synthetic
Vision
Module
IPC 3
INTEGRATED PROCESSING CABINET
CS1_CS3_3432_003
FWD EQUIPMENT BAY AFT RACK
Figure 3: Synthetic Vision Module Component Location
Copyright © Bombardier Inc.
CS130-21.12-06.00-121418
TECHNICAL TRAINING MANUAL
For Training Purposes Only
34-7
34 - Navigation
34-32 Head-Up Display System
(Option)
OVERHEAD UNIT
The overhead unit is located inside the ceiling above the pilot.
HUD COMBINER
The HUD combiner is mounted on the flight deck ceiling forward of the
overhead unit.
Copyright © Bombardier Inc.
CS130-21.12-06.00-121418
TECHNICAL TRAINING MANUAL
For Training Purposes Only
34-8
34 - Navigation
34-32 Head-Up Display System
(Option)
Hud
Combiner
CS1_CS3_3432_009
Overhead
Unit
Figure 4: HUD Component Location
Copyright © Bombardier Inc.
CS130-21.12-06.00-121418
TECHNICAL TRAINING MANUAL
For Training Purposes Only
34-9
34 - Navigation
34-32 Head-Up Display System
(Option)
CONTROLS AND INDICATIONS
The projected image on the combiner are perceived as existing at near
optical infinity, which allows the crew to view the outside world and the
images on the combiner, without the need to refocus each time.
HUD COMBINER
The combiner is off when is in the stowed position. To deploy it in the
operating position, the crew needs to press on the combiner latch lever.
The combiner display brightness can be controlled via the HUD knob.
Copyright © Bombardier Inc.
CS130-21.12-06.00-121418
TECHNICAL TRAINING MANUAL
For Training Purposes Only
34-10
34 - Navigation
34-32 Head-Up Display System
(Option)
+
HUD
DIM
BRT
B
HUD KNOB
CS1_CS3_3432_004
Combiner
Latch Lever
Figure 5: HUD Combiner Controls and Indications
Copyright © Bombardier Inc.
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TECHNICAL TRAINING MANUAL
For Training Purposes Only
34-11
34 - Navigation
34-32 Head-Up Display System
(Option)
CONTROL TUNING PANEL MENU
The HUD menu on the control tuning panel (CTP), provides control of
the HUD system.
The CTP can be used to manually select reference glideslope angle and
runway length, or be automatically set to the values associated with the
selected approach and runway in the FMS flight plan. The CTP can also
be used to select the low visibility takeoff (LVTO) function.
Copyright © Bombardier Inc.
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TECHNICAL TRAINING MANUAL
For Training Purposes Only
34-12
34 - Navigation
34-32 Head-Up Display System
(Option)
BRT
MENU
FPV CAGE
OFF
BRT
<WXR
ON/OFF>
TUNE/
MENU
<CLOCK
PFD/NAV>
IDENT
<STBY NAV
HUD>
1/2
LVTO
ON/OFF
RWY LENGTH
FMS/MAN
9500FT
APPR PATH ANG
DEG -3.0
FMS/MAN
TUNE/DATA
CRS 126
OFF
TUNE/
MENU
IDENT
1/2
TUNE/DATA
RETURN
CS1_CS3_3432_005
RETURN
HUD
Figure 6: Control Tuning Panel Menu
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TECHNICAL TRAINING MANUAL
For Training Purposes Only
34-13
34 - Navigation
34-32 Head-Up Display System
(Option)
HUDS INDICATIONS
The HUD uses green letters, numbers, and symbols to display
information on the combiner. All the primary flight display (PFD)
information displays on the HUD, using the same layout. Some
information has been adapted to fit the HUD combiner, which is smaller
and monochrome.
The indications on the combiner are automatically optimized for all flight
and ground phases.
The following PFD informations display on the HUD combiner:
•
Airspeed indications
•
Attitude indications
•
Altitude indications
•
Navigation information
When the LVTO function is on, the following information is displayed on
the combiner:
•
LVTO mode annunciator
•
Ground roll guidance cue
•
Localizer deviation scale
•
Runway remaining
Copyright © Bombardier Inc.
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TECHNICAL TRAINING MANUAL
For Training Purposes Only
34-14
34 - Navigation
34-32 Head-Up Display System
(Option)
Attitude
Indications
IN FLIGHT COMBINER DISPLAY
Altitude
Indications
Ground Roll Guidance Cue
and Localizer Deviation Scale
Navigation
Indications
LVTO Mode Annunciator
LVTO INDICATIONS
Runway Remaining
CS1_CS3_3432_006
Airspeed
Indications
LEGEND
LVTO Low Visibility Takeoff
Figure 7: HUDS Indications
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TECHNICAL TRAINING MANUAL
For Training Purposes Only
34-15
34 - Navigation
34-32 Head-Up Display System
(Option)
DETAILED DESCRIPTION
SYSTEM INTERFACE
The HUD graphic card (HGC) which resides in the synthetic vision
module (SVM), generates the graphics and symbology to be displayed,
and sends them to the overhead unit (OHU) via fiber optic interface. The
HGC receives the symbology information from HUD display application
(HDA), which also resides in the SVM. Critical symbol monitoring data is
transmitted by the HGC to the DMC via RS-422 BUS.
The HDA generates the symbology based on data received from the
navigation systems such as:
•
VHF-NAV
•
Inertial reference system (IRS)
•
Radio altimeter (RA)
•
Air data system (ADS)
•
Flight management system (FMS)
•
Terrain awareness and warning system (TAWS)
The OHU receives a discrete LED enable signal from the DMC. This
signal is used to blank the display when a failure occurs. When the HMA
detects a discrepancy between the primary flight display information and
the HUD, the HUD display is blanked.
The left OHU interfaces with DMC 1. The optional R OHU interfaces with
DMC 2.
The HUD combiner uses power from the OHU and sends back to the
OHU an analog signal to control image brightness. This signal is
controlled by the HUD brightness knob and the ambient light sensor
(ALS). The position of the combiner is transmitted to the OHU by the
stow status signal via a I2C DATA BUS. This bus also transmits the
combiner alignment signal from the combiner alignment detector (CAD),
when a misalignment is detected.
The liquid crystal display inside the OHU uses this data to generate the
enhanced flight symbology and projects it on the combiner.
The OHU interfaces with the data concentrator unit module cabinets
(DMCs) via ARINC 429 as follows:
•
Sends built-in test (BIT) status to be relayed to the HUD monitor
application (HMA)
•
Sends combiner status and alignment data
•
Receives control tuning panel data
•
Receives flight director guidance from the automatic flight control
system (AFCS)
•
Receives navigation data
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TECHNICAL TRAINING MANUAL
For Training Purposes Only
34-16
34 - Navigation
34-32 Head-Up Display System
(Option)
CDC 3-7-3
L HUD
CTP 1
DC
BUS 1
SSPC 7.5A
12 VDC
Logic: Always On
AFCS
LEFT
HUD COMBINER
LED Enable
CCM 2
CAD
Stow Status
HMA
VHF-NAV
ALS
LEFT OVERHEAD
UNIT
IPC 1
INTERNAL
REFERENCE
SYSTEM
DMC 1
AND
DMC 2
CCM 2
HMA
RADIO
ALTIMETER
IPC 2
DISPLAY UNITS
SVM
AIR DATA
SYSTEM
TERRAIN
AWARENESS
AND WARNING
SYSTEM
HDA
HGC
HDA
HGC
IPC 3
LEGEND
SVM
12 VDC
IPC 4
LED Enable
RIGHT
HUD COMBINER
CDC 4-6-4
R HUD
DC
BUS 2
Stow Status
SSPC 7.5A
Logic: Always On
RIGHT OVERHEAD
UNIT
ALS
CAD
CS1_CS3_3432_007
ALS
CAD
HDA
HGC
HMA
FLIGHT
AFDX
MANAGEMENT
Analog
SYSTEM
ARINC 429
Digital (I2C)
Discrete
Fiber Optics
RS-422
Ambient Light Sensor
Combiner Alignment Detector
HUD Display Application
HUD Graphics Card
HUD Monitor Application
Figure 8: System Interface
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TECHNICAL TRAINING MANUAL
For Training Purposes Only
34-17
34 - Navigation
34-32 Head-Up Display System
(Option)
MONITORING AND TESTS
The HUD system is continuously monitored for LVTO availability and
combiner alignment.
The following messages appear on the HUD combiner:
•
NO LVTO – LVTO mode not available
•
LVTO – LVTO mode active with Rollout Guidance displayed on the
HUD
•
LVTO ARM – LVTO mode is capable and armed
•
ALIGN HUD 1 – The combiner is not properly aligned
•
LVTO WARN – LVTO Warning is annunciated when LVTO becomes
incapable and ground speed is above 40 kt and less than 80 kt
Copyright © Bombardier Inc.
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TECHNICAL TRAINING MANUAL
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34-18
34 - Navigation
34-32 Head-Up Display System
(Option)
LVTO Mode
• NO LVTO
• LVTO
• LVTO ARM
HUD Not Aligned
CS1_CS3_3432_008
LVTO Warning
LEGEND
LVTO Low Visibility Takeoff
HUD Head-Up Display
Figure 9: Monitoring and Tests
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TECHNICAL TRAINING MANUAL
For Training Purposes Only
34-19
34 - Navigation
34-32 Head-Up Display System
(Option)
CAS MESSAGES
The following page provides the crew alerting system (CAS) and INFO
messages for the head-up display system.
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TECHNICAL TRAINING MANUAL
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34-20
34 - Navigation
34-32 Head-Up Display System
(Option)
Table 1: ADVISORY Messages
MESSAGE
LOGIC
HUD FAIL
HUD FAIL in a single HUD configuration.
L HUD FAIL
Left HUD Failed in a dual HUD configuration.
R HUD FAIL
Right HUD Failed in a dual HUD configuration.
LVTO NOT AVAIL Single HUD installed and HUD is reporting it is incapable
of displaying LVTO guidance.
L LVTO NOT
AVAIL
Dual installation HUD. Left HUD is reporting it is incapable
of displaying LVTO Guidance.
R LVTO NOT
AVAIL
Dual installation HUD. Right HUD is reporting it is
incapable of displaying LVTO Guidance.
DMC 1A FAIL
DMC Channel 1A Failure.
DMC 1B FAIL
DMC Channel 1B Failure.
DMC 2A FAIL
DMC Channel 2A Failure.
DMC 2B FAIL
DMC Channel 2B Failure.
AVIONIC FAN
FAULT
Loss of fans functionality within avionics LRUs.
Table 2: INFO Messages
MESSAGE
LOGIC
34 AVIONIC FAN HUD overhead unit (OHU) fan failed. Single installation.
FAULT - HUD FAN
INOP
34 AVIONIC FAN
FAULT - L HUD
FAN INOP
Left HUD overhead unit (OHU) fan failed. Dual
installation.
34 AVIONIC FAN
FAULT - R HUD
FAN INOP
Right HUD overhead unit (OHU) fan failed. Dual
installation.
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TECHNICAL TRAINING MANUAL
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34-21
34 - Navigation
34-32 Head-Up Display System
(Option)
Page Intentionally Left Blank
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TECHNICAL TRAINING MANUAL
For Training Purposes Only
34-22
ATA 34 - Navigation
Surface Management System
(Option)
BD-500-1A10
BD-500-1A11
34 - Navigation
34-46 Surface Management System
(Option)
Table of Contents
34-46 Surface Management System ......................................34-2
Introduction .......................................................................34-2
General Description ..........................................................34-4
Takeoff and Landing Awareness Function...................34-4
Airport Moving Map Application ........................................34-6
Takeoff Landing Awareness Function..........................34-8
Airport Moving Map Application .................................34-10
Detailed Description .......................................................34-12
System Interface ........................................................34-12
Monitoring and Tests ......................................................34-14
Data Loading..............................................................34-16
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TECHNICAL TRAINING MANUAL
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34-i
34 - Navigation
34-46 Surface Management System
(Option)
List of Figures
Figure 1:
Figure 2:
Figure 3:
Figure 4:
Figure 5:
Figure 6:
Surface Management System ..............................34-3
Takeoff Landing Awareness Function ..................34-5
AMMA Display ......................................................34-7
TLAF Controls and Indications .............................34-9
AMMA Display Indications ..................................34-11
Surface Management System
Interface .............................................................34-13
Figure 7: Data Loading ......................................................34-17
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TECHNICAL TRAINING MANUAL
For Training Purposes Only
34-ii
34 - Navigation
34-46 Surface Management System
(Option)
Page Intentionally Left Blank
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TECHNICAL TRAINING MANUAL
For Training Purposes Only
34-iii
34 - Navigation
34-46 Surface Management System
(Option)
SURFACE MANAGEMENT SYSTEM
Copyright © Bombardier Inc.
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TECHNICAL TRAINING MANUAL
For Training Purposes Only
34-1
34 - Navigation
34-46 Surface Management System
(Option)
34-46 SURFACE MANAGEMENT SYSTEM
INTRODUCTION
The surface management system (SMS) accomplishes two separate
functions:
•
Takeoff landing awareness function (TLAF)
•
Airport moving map application (AMMA)
The TLAF provides automated information and aural advisories to the
flight crew for abnormal takeoff and landing situations. It also adds a
visual overlay that highlights the target runway on the chart runway
highlight format.
The AMMA, when on ground, assists the flight crew by enhancing the
aircraft position on the airport surface. It also improves pilot position
alertness with respect to taxi operations.
Operation of the SMS does not rely on a hardware component. It
consists of functions residing on multiple common computing modules
(CCMs) inside the integrated processing cabinets 1 and 2 (IPC 1 and
IPC 2), and requires inputs from the navigation system.
Copyright © Bombardier Inc.
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TECHNICAL TRAINING MANUAL
For Training Purposes Only
34-2
34 - Navigation
34-46 Surface Management System
(Option)
NAV Systems
AURAL ALERTS
DEP
ARR
KDAL 10-9
OTHER
ZOOM
MAP PLAN ACT
KDAL ELEV 476 FT
RWY
DALLAS LOVE
OVLY
SYMBOL
18
13
L
36
13
R
KDAL
Takeoff
Landing
Awareness
Function
R
SMS
(IN IPC 1 AND IPC 2)
13
36
1
Airport
Moving Map
Application
L
WX
CHART RUNWAY HIGHLIGHT FORMAT
FMS1
KDAL
DTK 053
TTG --:-0.1 NM
AIRPORT MOVING MAP FORMAT
CS1_CS3_3446_001
31
Figure 1: Surface Management System
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TECHNICAL TRAINING MANUAL
For Training Purposes Only
34-3
34 - Navigation
34-46 Surface Management System
(Option)
GENERAL DESCRIPTION
TAKEOFF AND LANDING AWARENESS FUNCTION
The takeoff and landing awareness function (TLAF) is part of the surface
management system. It provides advisory visual and aural alerts to
improve situational awareness during takeoff and landing.
Alignment with the takeoff runway is satisfied when the aircraft is:
•
Within 80 ft of the runway surface
•
Within 10° of the runway heading
The TLAF references the FMS active flight plan and operates
automatically when the aircraft is within the airport terminal area of the
departure and arrival airports. No pilot action is required.
•
Takeoff alerts may occur if taxi speed exceeds 35 kt
Departure and arrival runways are highlighted on terminal charts when
the integrated flight information system (IFIS) is installed. Takeoff
runways are highlighted in cyan. Landing runways are highlighted in
magenta. Runway direction is indicated with an arrow at both runway
ends.
•
The landing gear is down and locked
•
The aircraft descends below an altitude that is 300 ft above the
highest runway at the destination airport
•
One of the following is true:
Landing alerts are generated if:
A RWY soft key at the top of the map toggles runway highlighting on and
off. The default setting is on.
-
The aircraft is within the SMS landing runway detection zone and
not aligned with a runway ("NOT A RUNWAY" aural alert)
The aircraft position is indicated by a green aircraft symbol on the chart.
-
The aircraft is aligned with a runway that is too short based upon
performance requirements ("SHORT RUNWAY" aural alert)
For aircraft equipped with the optional HUD, a RUNWAY message is
displayed below the ground roll reference cue.
Takeoff alerts are generated when takeoff thrust is applied, or ground
speed is between 35 kt and V1, and one of the following is true:
•
The aircraft is not aligned with any runway ("NOT A RUNWAY" aural
alert)
•
The runway distance remaining is insufficient for takeoff ("SHORT
RUNWAY" aural alert) based on manually entered field length in the
FMS.
•
The aircraft is on a different runway than the FMS departure runway
("RUNWAY DISAGREE" aural alert)
Copyright © Bombardier Inc.
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TECHNICAL TRAINING MANUAL
For Training Purposes Only
34-4
34 - Navigation
34-46 Surface Management System
(Option)
DEP
ARR
KDAL 10-9
Takeoff thrust
applied
Taxiway
OTHER
ZOOM
RWY
DALLAS LOVE
PFD
RUNWAY
PFD FLAG
FMS Runway
“NOT A RUNWAY”
Takeoff thrust
applied
RUNWAY
FMS Runway
Insufficient runway
remaining for takeoff
PFD FLAG
“SHORT RUNWAY”
FMS Runway
DEP
ARR
KDAL 10-9
OTHER
ZOOM
RWY
DALLAS LOVE
RUNWAY
PFD FLAG
“RUNWAY DISAGREE”
Takeoff thrust
applied
Taxiway
RUNWAY
PFD FLAG
RUNWAY
Required distance for landing
is too short
PFD FLAG
“SHORT RUNWAY”
JEPPESON AIRPORT CHART
CS1_CS3_3446_007
“NOT A RUNWAY”
Figure 2: Takeoff Landing Awareness Function
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CS130-21.12-06.00-121418
TECHNICAL TRAINING MANUAL
For Training Purposes Only
34-5
34 - Navigation
34-46 Surface Management System
(Option)
AIRPORT MOVING MAP APPLICATION
This function provides an image of airport runways and taxiways
generated from the airport moving map application (AMMA).
This option requires the integrated flight information system (IFIS) to be
installed, and the operator to be subscribed to airports database updates
every 28 days.
The airport moving map indications are integrated with the navigation
map on the multifunction window. The AMMA generates airport maps
based on either airport surfaces database (ARINC 816 format) or
runways surfaces database (ARINC 424 format), as soon as the map
range is 2 nm or less. When an airport is available in the airport surfaces
database, a high-detailed map is rendered; otherwise, a low-detailed
map is rendered using information in the runway surfaces database.
ARINC 816 and ARINC 424 databases are on the same CCM as the
AMMA.
Copyright © Bombardier Inc.
CS130-21.12-06.00-121418
TECHNICAL TRAINING MANUAL
For Training Purposes Only
34-6
34 - Navigation
34-46 Surface Management System
(Option)
Range < 2 NM
AIRPORT MOVING
MAP APPLICATION
ACT
MAP
P PLAN
OVLY
VLY
IFIS
SYMBOL
SYMBO
OL
MAP PLAN
ACT
CYUL ELEV
119 FT
NO HS DATA
OVLY
SYMBOL
MAP PLAN
ACT
LOWS ELEV 1411
RWYS ONLY
OVLY
SYMBOL
FT
33
HDG 154
15
154
18
HDG 058
12
9
154
15
18
12
21
36
21
1
9
HDG 154
058
6
3
12
1
9
1
2
15
TCAS OFF
TFC
FMS2
CYUL
HDG 058
TTG --:-0.1 NM
WX
TERR
TCAS OFF
TFC
ARINC 816 DATA FORMAT
FMS2
LOWS
HDG 154
TTG --:-0.1 NM
ARINC 424 DATA FORMAT
CS1_CS3_3446_006
FMS2
LOWS
HDG 154
TTG --:-0.1 NM
TCAS OFF
TFC
MAP FORMAT
Figure 3: AMMA Display
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TECHNICAL TRAINING MANUAL
For Training Purposes Only
34-7
34 - Navigation
34-46 Surface Management System
(Option)
CONTROLS AND INDICATIONS
The SMS functions are only available within immediate area of the
airport, and it is automatically activated with no pilot action required.
TAKEOFF LANDING AWARENESS FUNCTION
The TLAF provides visual highlight of target runways on corresponding
airport charts. The highlights are cyan for takeoff, or magenta for landing.
The highlight graphics are rendered by the optional Integrated flight
information system (IFIS). The highlights can be removed using the
RWY selection on the map display.
Depending on the aircraft configuration and position, the system
generates advisories consisting of aural alerts and visual alerts on the
primary flight display (PFD) and head-up display (HUD).
The aural alerts can be inhibited using the SMS RUNWAY INHIB
selection AVIONICS synoptic page. This selection generates an SMS
RUNWAY INHIB INFO message.
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TECHNICAL TRAINING MANUAL
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34-8
34 - Navigation
34-46 Surface Management System
(Option)
DEP
ARR
KDAL 10-9
TO
TO
3 000
10
4
50
6
8
10
10
20
20
20
40
4 100
80
40
30
0
RWY
DALLAS LOVE
Condition
Aural Alert
PFD Alert
Takeoff not on a
runway
“NOT A RUNWAY,
NOT A RUNWAY”
RUNWAY
Takeoff runway too
short
“SHORT RUNWAY,
SHORT RUNWAY”
RUNWAY
500
00
RUNWAY
32
ZOOM
TAKEOFF ADVISORIES
ALTSS
100
OTHER
Takeoff runway
“RUNWAY DISAGREE,
disagrees with FMS RUNWAY DISAGREE”
departure runway
RUNWAY
LANDING ADVISORIES
29.92 INN
Condition
Aural Alert
PFD Alert
Landing not on a
runway
“NOT A RUNWAY,
NOT A RUNWAY”
RUNWAY
0
1.
1
.000
PFD
Landing runway too “SHORT RUNWAY,
short
SHORT RUNWAY”
RUNWAY
STATUS
AIR
IR
DOOR
OR
ELECC
FLT CTR
CTRLL
FUEL
FUE
EL
HYD
YD
AVIONIC
IONIC
INFO
CB
AVIO
DEP
ARR
KDAL 10-9
OTHER
ZOOM
RWY
DALLAS LOVE
CTP
CT
TP
CTP
SMS RUNWAY
ENABLED
INHIB
SYNOPTIC PAGE – AVIONICS
JEPPESON AIRPORT CHART
CS1_CS3_3446_003
VSPEEDS...
HUD
Figure 4: TLAF Controls and Indications
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TECHNICAL TRAINING MANUAL
For Training Purposes Only
34-9
34 - Navigation
34-46 Surface Management System
(Option)
AIRPORT MOVING MAP APPLICATION
When the range selection is made to less than 2 nm, one of the following
messages may appear if a fault in the AMMA occurs:
•
LOADING AIRPORT – Displayed when a large airport map is being
loaded and the processing is not complete
•
OFF AIRPORT MAP – Displayed when the map is panned in any
direction such that no portion of the airport is in view
•
MAP POSITION FAULT – Displayed when the aircraft present
position is not valid
•
-
In MAP mode, the map display is removed but the aircraft symbol
is displayed
-
In PLAN mode, the aircraft symbol is removed but the map is still
displayed
AIRPORT MAP FAULT – Displayed when a map cannot be retrieved
from the database
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TECHNICAL TRAINING MANUAL
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34-10
34 - Navigation
34-46 Surface Management System
(Option)
MAP PLAN
ACT
OVLY
HDG 071
6
071
SYMBOL
MESSAGE
DESCRIPTION
LOADING AIRPORT
Displayed when a large airport map is being loaded and
the processing is not complete.
OFF AIRPORT MAP
Displayed when the map is panned in any direction such
that no portion of the airport is in view.
MAP POSITION FAULT
Displayed when the aircraft present position is not valid.
• In MAP mode, the map display is removed but the aircraft symbol still displays.
• In PLAN mode, the aircraft symbol is removed but the map still displays.
AIRPORT MAP FAULT
Displayed when a map cannot be retrieved from the database.
9
3
12
1
TA ONLY
TFC
MAP POSITION FAULT
FMS1
RW07
DTK 071
TTG 18.9
0.0 NM
CS1_CS3_3446_008
6
Figure 5: AMMA Display Indications
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TECHNICAL TRAINING MANUAL
For Training Purposes Only
34-11
34 - Navigation
34-46 Surface Management System
(Option)
DETAILED DESCRIPTION
SYSTEM INTERFACE
The surface management system (SMS) works in conjunction with the
flight management system (FMS) and displays overlays on IFIS runway
charts via the electronic flight instrumentation system (EFIS).
The SMS interfaces with the following systems:
•
Flight management system (FMS), to perform aural algorithm
functions, to manage aural inhibit discrete routed from the data
concentrator unit module cabinet (DMC) and to provide airport
runaway parameters, take-off and landing plans
•
Electronic flight instrument system (EFIS), to display CAS messages
and highlight runaways on the airport charts
•
Data concentrator unit module cabinet (DMC), to forward aural alert
messages to the radio interface unit (RIU) and relay information from
the GNSS and IRS
•
Global navigation satellite system (GNSS), for heading information
•
Inertial reference system (IRS), for heading information
SMS inputs are received via an AFDX BUS routed through the DMCs.
Inputs from other CCM hosted applications, such as FMS, are also
provided to the SMS through the AFDX network inside the integrated
processing cabinets (IPCs).
The system also provides output data to the avionics full duplex switched
Ethernet (AFDX) network through the integrated flight information
system (IFIS) on the IPC, and via DMCs.
Copyright © Bombardier Inc.
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TECHNICAL TRAINING MANUAL
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34-12
34 - Navigation
34-46 Surface Management System
(Option)
IPC 1
MAP PLAN ACT
KDAL ELEV 476 FT
IFIS 1
OVLY
SYMBOL
18
13
L
FMS 1
36
13
R
TLAF
KDAL
R
13
36
ALMA
1
L
31
IPC 2
FMS1
KDAL
DTK 053
TTG --:-0.1 NM
WX
AIRPORT MOVING MAP FORMAT
IFIS 2
DMC 1
and
DMC 2
FMS 2
RIU 1
and
RIU 2
TLAF
AMMA
GLOBAL
NAVIGATION
SATELLITE
SYSTEM
SMS RUNWAY
ENABLED
INHIB
INERTIAL
REFERENCE
SYSTEM
SYNOPTIC PAGE – AVIONICS
Application License Manager Application
Airport Moving Map Application
Data Concentrator Unit Module Cabinet
Radio Interface Unit
Electronic Flight Instrument System
Integrated Flight Information System
Takeoff Landing Awareness Function
AFDX
ARINC 429
Discrete
CS1_CS3_3446_005
LEGEND
ALMA
AMMA
DMC
RIU
EFIS
IFIS
TLAF
Figure 6: Surface Management System Interface
Copyright © Bombardier Inc.
CS130-21.12-06.00-121418
TECHNICAL TRAINING MANUAL
For Training Purposes Only
34-13
34 - Navigation
34-46 Surface Management System
(Option)
MONITORING AND TESTS
The following page provides the crew alerting system (CAS) and INFO
messages for the surface management system.
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TECHNICAL TRAINING MANUAL
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34-14
34 - Navigation
34-46 Surface Management System
(Option)
Table 1: ADVISORY Message
MESSAGE
LOGIC
SMS RUNWAY
N/A
One of the FMS is reporting a SMS. Short runway function
is inop, and SMS function is enabled.
SMS FAIL
One or more SMS functions are not enabled or invalid.
The DMCs cross-talk is working and SMS is not inhibited,
but is enabled, and mask for power-up on ground.
Table 2: INFO Message
MESSAGE
SMS RUNWAY
INHIB
LOGIC
One or both FMSs is reporting SMS target inhibited and
One or more of the DUs are reporting that SMS runway is
inhibited and SMS function is enabled.
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TECHNICAL TRAINING MANUAL
For Training Purposes Only
34-15
34 - Navigation
34-46 Surface Management System
(Option)
PRACTICAL ASPECTS
DATA LOADING
As for other applications, to load and update the various databases
required by the SMS, the system interfaces with the information
management system (IMS).
The onboard data loader (ODL) application, within the IMS, permits
loading of all required data and software.
Upload progress can be observed on the DATALOAD page. At the end
of the process, a green notification message appears, indicating that all
files have been uploaded without errors. If an error occurs, a yellow
message appears under the status column to identify the file.
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TECHNICAL TRAINING MANUAL
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34-16
34 - Navigation
34-46 Surface Management System
(Option)
DATA LOADING
MAINTENANCE
MAIN
E
DATA
ATA LOAD
IMS
Load New
N Databases
ases
es
Name
e
Statuss
Overall Database Load Progress:
Start Load
Database Details
D
33%
Status:
NAV_DB_VX-X-X
SMS1
MAINTENANCE
DATA LOAD
Transferring Files
45%
NAV_DB_VX-X-X
SMS2
Transferring Files
15%
NAV_DB_VX-X-X
SMS3
Transferring Files
35%
Load New Databases
Name
Status
NAV_DB_VX-X-X
Complete
IPC 2
DSM
AMMA
Start Load
Database Details
Load Complete
CS1_CS3_3446_004
&&0í
Figure 7: Data Loading
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TECHNICAL TRAINING MANUAL
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34-17
34 - Navigation
34-46 Surface Management System
(Option)
Page Intentionally Left Blank
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TECHNICAL TRAINING MANUAL
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34-18
ATA 44 - Cabin Systems
In-Flight Entertainment and Connectivity
System (Option)
BD-500-1A10
BD-500-1A11
44 - Cabin Systems
44-20 In-Flight Entertainment and Connectivity System
(Option)
Table of Contents
44-20 In-Flight Entertainment and Connectivity System.........44-2
Introduction .......................................................................44-2
eX1 In-Flight Entertainment ..............................................44-4
In-Seat Power Supply System ..........................................44-6
Global Connectivity Suite .................................................44-8
eXconnect System .......................................................44-8
eXW System ..............................................................44-10
44-20 eX1 In-flight Entertainment .........................................44-12
General Description ........................................................44-12
Component Location ......................................................44-14
File Server..................................................................44-14
Cell Modem (optional)................................................44-16
Smart Monitor ............................................................44-16
Seat Electronics Box..................................................44-16
Seat Power Module....................................................44-16
Controls and Indications .................................................44-18
Cabin PWR PBA ........................................................44-18
IFEC-ISPS Master Switch..........................................44-18
General Description ....................................................... 44-36
Component Location ..................................................... 44-38
Advanced Master Control Units ................................ 44-38
Controls and Indications ................................................ 44-40
44-20 Supplemental Avionics Bay Cooling and
Smoke Detection........................................................ 44-42
General Description ....................................................... 44-42
Supplemental Avionics Bay Cooling ......................... 44-42
Supplemental Avionics Bay Smoke Detection .......... 44-44
Component Location ..................................................... 44-46
Supplemental Avionics Bay Fan ............................... 44-46
Supplemental Avionics Bay Smoke Detectors .......... 44-46
Ventilated Temperature Sensor ................................ 44-46
Controls and Indications ................................................ 44-48
Detailed Description ...................................................... 44-50
Monitoring and Tests ..................................................... 44-52
CAS Messages ......................................................... 44-53
44-20 Global Connectivity Suite ...........................................44-20
General Description ........................................................44-20
eXconnect ..................................................................44-20
Cell Modem................................................................44-22
Component Location..................................................44-24
eXphone.....................................................................44-28
Component Location..................................................44-30
eXW ...........................................................................44-32
Component Location..................................................44-34
44-20 In-Seat Power Supply System....................................44-36
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TECHNICAL TRAINING MANUAL
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44-i
44 - Cabin Systems
44-20 In-Flight Entertainment and Connectivity System
(Option)
List of Figures
Figure 1: In-Flight Entertainment and Connectivity
System .................................................................44-3
Figure 2: In-Flight Entertainment .........................................44-5
Figure 3: In-Seat Power Supply System ..............................44-7
Figure 4: Global Connectivity Suite ......................................44-9
Figure 5: eXW.....................................................................44-11
Figure 6: eX1 General Description .....................................44-13
Figure 7: eX1 File Server Location .....................................44-15
Figure 8: eX1 Cell Modem, Smart Monitor, Seat
Electronics Box, and Seat Power Module
Location...............................................................44-17
Figure 9: In-Flight Entertainment and Connectivity
System - Controls and Indications.......................44-19
Figure 10: eXconnect General Description...........................44-21
Figure 11: Cell Modem General Description ........................44-23
Figure 12: eXconnect Global Connectivity Suite
File Server, Broadband Controller, and
Cell Modem Location...........................................44-25
Figure 13: eXconnect Ku Band Antenna Assembly
and Power Supply Unit Location .........................44-27
Figure 14: eXphone General Description .............................44-29
Figure 15: eXphone Component Location............................44-31
Figure 16: eXW General Description....................................44-33
Figure 17: eXW Component Location ..................................44-35
Figure 18: In-Seat Power Supply System General
Description ..........................................................44-37
Copyright © Bombardier Inc.
CS130-21.12-06.00-121418
Figure 19: In-Seat Power Supply System Component
Location .............................................................. 44-39
Figure 20: CMS In-Seat Power System Screen................... 44-41
Figure 21: Supplemental Avionics Bay Cooling ................... 44-43
Figure 22: Supplemental Avionics Bay
Smoke Detection ................................................ 44-45
Figure 23: Supplemental Avionics Bay Cooling and
Smoke Detection Component Location .............. 44-47
Figure 24: Supplemental Avionics Bay Cooling
Controls .............................................................. 44-49
Figure 25: Supplemental Avionics Bay Cooling
Detailed Description............................................ 44-51
TECHNICAL TRAINING MANUAL
For Training Purposes Only
44-ii
44 - Cabin Systems
44-20 In-Flight Entertainment and Connectivity System
(Option)
Page Intentionally Left Blank
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TECHNICAL TRAINING MANUAL
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44-iii
44 - Cabin Systems
44-20 In-Flight Entertainment and Connectivity System
(Option)
IN-FLIGHT ENTERTAINMENT AND CONNECTIVITY SYSTEM
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TECHNICAL TRAINING MANUAL
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44-1
44 - Cabin Systems
44-20 In-Flight Entertainment and Connectivity System
(Option)
44-20 IN-FLIGHT ENTERTAINMENT AND
CONNECTIVITY SYSTEM
INTRODUCTION
The Panasonic Xseries in-flight entertainment and connectivity (IFEC)
system consists of the following subsystems:
•
eX1 in-flight entertainment (IFE)
•
Global connectivity suite
•
In-seat power supply system (ISPSS)
The global connectivity suite is divided into two systems that are fully
integrated that can be installed as standalone subsystems:
•
eXconnect (connectivity)
•
eXW (WiFi)
The eXconnect connectivity system can include the optional eXphone
subsystem.
NOTE
The eX1 in-flight entertainment system is a fully customizable
system. The configuration and equipment used on each aircraft
vary depending on the selected options.
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TECHNICAL TRAINING MANUAL
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44-2
44 - Cabin Systems
44-20 In-Flight Entertainment and Connectivity System
(Option)
IN-FLIGHT
ENTERTAINMENT
and
CONNECTIVITY
SYSTEM
eX1
IN-FLIGHT
ENTERTAINMENT
GLOBAL
CONNECTIVITY
SUITE
eXW
WiFi
IN-SEAT POWER
SUPPLY SYSTEM
eXconnect
CONNECTIVITY
NOTE
The eX1 in-flight entertainment system is a fully customizable.
The configuration and equipment used on each aircraft vary depending on the selected options.
CS1_CS3_4420_004
eXphone
Figure 1: In-Flight Entertainment and Connectivity System
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TECHNICAL TRAINING MANUAL
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44-3
44 - Cabin Systems
44-20 In-Flight Entertainment and Connectivity System
(Option)
eX1 IN-FLIGHT ENTERTAINMENT
The eX1 IFE system provides multimedia to cabin seat mounted touch
screen monitors and audio jacks. A DC seat electronics box (SEB) and
seat power module (SPM) are installed in each seat row assembly as
part of the IFE system.
A file server stores and distributes multimedia. A second file server can
be installed as an option. The file server also communicates with the
cabin management system (CMS) cabin controller so that cabin crew
and passenger address (PA) announcements are distributed to the smart
monitors and the audio jacks.
The SPM provides power to the DC SEB. The DC SEB supplies power
distribution to the seat monitor and universal serial bus (USB) port. The
DC SEB retrieves the multimedia files that are selected from the file
servers. The multimedia is then processed and distributed to the smart
monitors and the audio jacks on the associated seat.
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TECHNICAL TRAINING MANUAL
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44-4
44 - Cabin Systems
44-20 In-Flight Entertainment and Connectivity System
(Option)
PASSENGER
ADDRESS
SMART MONITOR
SMART MONITOR
HANDSET
HANDSET
SPM
SPM
CABIN
CONTROLLER
CREW
TERMINAL
DC SEB
DC SEB
USB
USB
USB
USB
USB
FILE
SERVER
AUDIO JACK
USB
AUDIO JACK
USB
AUDIO JACK
AVAILABLE OPTIONS
NOTE
USB
FILE
SERVER
(OPTIONAL)
AUDIO JACK
USB
USB
USB
USB
DC SEB
DC SEB
LEGEND
DC SEB
SPM
DC Seat Electronics Box
Seat Power Module
HANDSET
SPM
SMART MONITOR
SPM
HANDSET
SMART MONITOR
CS1_CS3_4420_005
Smart monitor and handsets vary
depending on options selected.
Figure 2: In-Flight Entertainment
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TECHNICAL TRAINING MANUAL
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44-5
44 - Cabin Systems
44-20 In-Flight Entertainment and Connectivity System
(Option)
IN-SEAT POWER SUPPLY SYSTEM
The in-seat power supply system (ISPSS) provides power to the
passenger seat monitors and power outlets installed in the seats.
There are two advanced monitor control units (AMCUs) that convert and
regulate aircraft variable frequency power to 115 VAC 60 Hz. The
converted power is routed to the power outlets at the seats and the seat
power modules if the IFE system is installed.
The seat power modules convert the AC power to DC and provides it to
the DC SEB.
Power outlets are installed on the seats to allow personal electronic
devices (PEDs) to be charged and powered.
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TECHNICAL TRAINING MANUAL
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44-6
44 - Cabin Systems
44-20 In-Flight Entertainment and Connectivity System
(Option)
SEAT
ELECTRONICS
BOX
3Ø
AC
PWR
DC
PWR
DC
PWR
3Ø AC PWR
SEAT
POWER
MODULE
SEAT
POWER
MODULE
115 VAC 60Hz
OUTLET
3Ø AC PWR
115 VAC 60Hz
OUTLET
CS1_CS3_4420_007
ADVANCE MASTER
CONTROL UNIT
SEAT
ELECTRONICS
BOX
Figure 3: In-Seat Power Supply System
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TECHNICAL TRAINING MANUAL
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44-7
44 - Cabin Systems
44-20 In-Flight Entertainment and Connectivity System
(Option)
GLOBAL CONNECTIVITY SUITE
The global connectivity suite (GCS) is capable of providing portable
electronic devices with an internet connection and stored multimedia
depending on the system configuration. The global connectivity suite can
be divided into the eXW and eXconnect subsystems.
eXCONNECT SYSTEM
The eXconnect system uses satellite communication to provide access
to ground networks while in flight.
The Ku band antenna provides a satellite connection which enables the
eXconnect system to access the internet and live streaming TV. Live
streaming TV is available through an optional eXTV subscription.
The broadband controller routes data between the Ku band antenna and
the GCS file server. The GCS file server communicates with the wireless
access points which provides WiFi Internet access to the PEDs. If the
eX1 system is installed the GCS file servers also provide the data to the
DC SEBs which makes the multimedia available at the cabin seats.
eXphone System
The eXphone is an optional subsystem to the eXconnect system which
enables 3G cellular network access to PEDs in the cabin during flight.
The ephone system creates a 3G network using a pair of leaky feeder
cables which are monitored and controlled by the following components:
•
3G network control unit (NCU)
•
3G base transceiver station (BTS)
•
Duplexer
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TECHNICAL TRAINING MANUAL
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44-8
44 - Cabin Systems
44-20 In-Flight Entertainment and Connectivity System
(Option)
Ku BAND
ANTENNA
SATELLITE
Leaky
Feeder
CABIN
MANAGEMENT
SYSTEM
3G BASE
TRANSCEIVER
STATION
GROUND
STATION
DUPLEXER
Leaky
Feeder
BROADBAND
CONTROLLER
PERSONAL
ELECTRONIC
DEVICE
To DC SEB
3G NETWORK
CONTROL UNIT
GROUND BASED
CELLULAR NETWORK
CELL MODEM
CS1_CS3_4420_006
GLOBAL CONNECTIVITY
SUITE FILE SERVER
Figure 4: Global Connectivity Suite
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TECHNICAL TRAINING MANUAL
For Training Purposes Only
44-9
44 - Cabin Systems
44-20 In-Flight Entertainment and Connectivity System
(Option)
eXW SYSTEM
The eXW system is part of the global connectivity suite but is
configurable as a standalone system. The eXW provides a WiFi network
connection for personal electronic devices (PEDs) in the aircraft cabin.
This allows the PEDs to access stored or streaming multimedia from the
file servers when they are connected to the cabin WiFi network.
The wireless access points (WAPs) create the WiFi network used to
distribute the multimedia files to the PEDs.
Copyright © Bombardier Inc.
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TECHNICAL TRAINING MANUAL
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44-10
44 - Cabin Systems
44-20 In-Flight Entertainment and Connectivity System
(Option)
CABIN
MANAGEMENT
SYSTEM
INTEGRATED
SERVER
PERSONAL ELECTRONIC DEVICES
WIRELESS ACCESS POINT
(CS 300 only)
CS1_CS3_4420_019
WIRELESS ACCESS POINTS
Figure 5: eXW
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TECHNICAL TRAINING MANUAL
For Training Purposes Only
44-11
44 - Cabin Systems
44-20 eX1 In-flight Entertainment
(Option)
44-20 EX1 IN-FLIGHT ENTERTAINMENT
GENERAL DESCRIPTION
The eX1 in-flight entertainment (IFE) system provides multimedia to the
cabin seats.
The file servers provide audio, video and data files to the cabin seats.
They store data that is uploaded to internal memory and manage
streaming media when the connectivity system is installed. Power for file
server 1 is supplied by AC BUS 1. File server 2 (optional) is supplied by
AC BUS 2.
The file servers are cooled using tray fans. The file server tray fans are
power by DC BUS 2.
Content is loaded using a portable media loader that connects to the file
servers through RJ45 plugs located at the forward attendant seat. A
portable USB memory stick can be used when the solid-state drive
onboard media loader (SSD OML) (optional) is installed. Power for the
SSD OML is supplied by DC BUS 1 and DC BUS 2 as an alternate. Data
transfer is done through Ethernet bus.
When the optional global connectivity suite (GCS) is installed,
multimedia is shared between IFE and GCS systems though an
ETHERNET BUS. Both systems share the same cell modem.
Aircraft input to the file servers from the data concentrator unit module
cabinet (DMC) 1 is provide through an ARINC 429 DATA BUS.
The IFE system is monitored and controlled through the cabin
management system (CMS).The passenger address (PA) is supplied
through the cabin controller. When the PA is in use, the IFE video and
audio is paused.
The IFE system can be turned on or off using the CABIN POWER switch
on the ELECTRICAL panel in the flight deck or the IFEC-ISPS MASTER
switch next to the lavatory A door.
The DC seat electronics boxes (SEB) receive 28 VDC from the seat
power modules (SPMs) and then provide DC power to the monitor and
USB ports installed in the seats. The SPMs are powered using aircraft
power when the in-seat power supply system is not installed. There is
one DC SEB and one SPM per seat row.
The DC SEBs are also used as an Ethernet switch for information going
between the equipment installed on the seats and the file servers. The
in-seat monitors are touch screen devices that allow media selection and
volume control.
An optional cell modem provides maintenance information to the airline
or the IFE system provider through the 3G cellular network. This
information is offloaded when the aircraft has landed and is used for
maintenance monitoring and passenger billing processing.
Copyright © Bombardier Inc.
CS130-21.12-06.00-121418
TECHNICAL TRAINING MANUAL
For Training Purposes Only
44-12
44 - Cabin Systems
44-20 eX1 In-flight Entertainment
(Option)
IFEC-ISPS
MASTER SWITCH
(OPTIONAL)
IFEC
IFEC-ISPS
C-IS
SPS
MASTER
MA
AST
TER
CDC 3
RJ45
Passenger
Address
System
GLOBAL
CONNECTIVITY
SUITE
(OPTIONAL)
CABIN
MANAGEMENT
SYSTEM
CDC 3-10-10
IFE Server 1
AC
SSPC 3A
BUS 1
Logic: Advanced
CDC 3-7-7
IFE OBML DC ALTN
DC
SSPC 3A
BUS 1
Logic: Advanced
Power On/Off Discrete
Cell Modem
Optional
To Next DC SEB
FILE SERVER 1
FAN
CABIN
POWER
SWITCH
L DC
SEB n
Seat
Power
Module
Smart
Monitors
28 VDC
115 VAC 60Hz
Seat
Outlets
(optional)
SEAT ROW
SSD OML
(OPTIONAL)
RJ45
DMC 1
115 VAC
From Aircraft
or ISPSS
RJ45
Seat
Power
Module
CDC 4
Logic: Advanced
CDC 4-4-8
IFE Server Tray Fan
DC
SSPC 5A
BUS 2
115 VAC 60Hz
R DC
SEB n
Seat
Outlets
(optional)
Smart
Monitors
FILE SERVER 2
(OPTIONAL)
SEAT ROW
To Next DC SEB
FAN
LEGEND
Logic: Advanced
CDC 4-12-4
CDC
DMC
SEB
SSD OML
IFE Server
AC
BUS 2
28 VDC
SSPC 3A
Logic: Advanced
Control and Distribution Cabinet
Data Concentrator Unit Module Cabinet
Seat Electronics Box
Solid-state Drive Onboard Media Loader
ARINC 429
Ethernet
CS1_CS3_4420_010
CDC 4-4-14
IFE OBML DC
DC
SSPC 3A
BUS 2
Figure 6: eX1 General Description
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TECHNICAL TRAINING MANUAL
For Training Purposes Only
44-13
44 - Cabin Systems
44-20 eX1 In-flight Entertainment
(Option)
COMPONENT LOCATION
The IFE system consists of the following components:
•
File server
•
Cell modem (Refer to figure 8)
•
Smart monitor (Refer to figure 8)
•
Seat electronics box (SEB) (Refer to figure 8)
•
Seat power module (SPM) (Refer to figure 8)
FILE SERVER
There are two file servers installed in the forward equipment bay for the
IFE system.
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TECHNICAL TRAINING MANUAL
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44-14
44 - Cabin Systems
44-20 eX1 In-flight Entertainment
(Option)
CS1_CS3_4420_022
File
Server 2
File
Server 1
Figure 7: eX1 File Server Location
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TECHNICAL TRAINING MANUAL
For Training Purposes Only
44-15
44 - Cabin Systems
44-20 eX1 In-flight Entertainment
(Option)
CELL MODEM (OPTIONAL)
The optional cell modem is located in the forward ceiling of the aircraft
cabin.
SMART MONITOR
The smart monitors are installed on the back of the cabin seats.
SEAT ELECTRONICS BOX
There is an seat electronics box (SEB) installed in each cabin seat
bench.
SEAT POWER MODULE
There is a seat power module (SPM) installed in each cabin seat bench.
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TECHNICAL TRAINING MANUAL
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44-16
44 - Cabin Systems
44-20 eX1 In-flight Entertainment
(Option)
Smart
Monitor
A
B
Seat Power
Module
A
NOTE
CELL MODEM
B
Cell modem is optional when
Global Connectivity Suite is not installed.
CS1_CS3_4420_009
Seat
Electronics Box
Figure 8: eX1 Cell Modem, Smart Monitor, Seat Electronics Box, and Seat Power Module Location
Copyright © Bombardier Inc.
CS130-21.12-06.00-121418
TECHNICAL TRAINING MANUAL
For Training Purposes Only
44-17
44 - Cabin Systems
44-20 eX1 In-flight Entertainment
(Option)
CONTROLS AND INDICATIONS
The IFE, GCS, and ISPSS systems are controlled using the following:
•
CABIN PWR PBA
•
IFEC-ISPS MASTER switch
CABIN PWR PBA
The CABIN PWR PBA switches off IFE, GCS, ISPS, and galley
equipment to isolate possible smoke sources. The pushbutton
annunciator (PBA) is guarded to prevent inadvertent activation. The OFF
legend illuminates white when the CABIN PWR PBA is selected off.
IFEC-ISPS MASTER SWITCH
The IFEC-ISPS MASTER switch is located near the lavatory A door. The
switch controls the power to the IFE, GCS, and ISPS.
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TECHNICAL TRAINING MANUAL
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44-18
44 - Cabin Systems
44-20 eX1 In-flight Entertainment
(Option)
ELECTRICAL
CABIN PWR
BUS ISOL
RAT GEN
AUTO
ESS
A
O FF
ON
PULL
TURN
1
B
BATT
BATT 2
AUTO
AUTO
OFF
OFF
L GEN
R GEN
FAIL
FAIL
OFF
EXT PWR
APU GEN
L DISC
AVAIL
FAIL
IN USE
OFF
OFF
OIL
OIL
DISC
DISC
IFEC
IFEC-ISPS
C-IS
SPS
MASTER
MA
AST
TER
A
ELECTRICAL PANEL
CS1_CS3_4420_021
MAIN
Figure 9: In-Flight Entertainment and Connectivity System - Controls and Indications
Copyright © Bombardier Inc.
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TECHNICAL TRAINING MANUAL
For Training Purposes Only
44-19
44 - Cabin Systems
44-20 Global Connectivity Suite
(Option)
44-20 GLOBAL CONNECTIVITY SUITE
GENERAL DESCRIPTION
The global connectivity suite (GCS) allows passengers to surf the web,
send email and text messages, stream video, and watch live TV. The
cabin connectivity consists of an onboard system to provide connectivity
services to passengers and a communication system that connects the
aircraft to ground networks.
The GCS file server provides information distribution between the
broadband controller and the eXW and eX1 systems through Ethernet
bus. Power for the GCS file server is provided by AC BUS 2.
The connectivity system can be divided into the eXconnect system and
the eXW system.
The GTE RELAY sends a discrete to the broadband controller to
interrupt all transmissions of the GCS. This is done whenever the aircraft
is below an altitude of 10,000 ft. This prevents interference with
navigational and communication equipment used for flight. The GTE
relay is controlled by the CMS and receives altitude information from the
DMC and power from DC BUS 1.
EXCONNECT
The Ku band antenna is a steerable phased array antenna that
communicates over frequencies in the Ku satellite communication band.
Power is supplied to the Ku band antenna through a power supply unit
that converts AC BUS 1 power into DC power usable by the antenna.
Information sent between the Ku band antenna assembly and the
broadband controller is sent using RF coax and an Ethernet bus.
The Ku band communicates with the aircraft’s inertial reference system
(IRS) through data concentrator unit module cabinet (DMC) 1. The
Ku band antenna uses the IRS information to remain pointed at the
satellite.
Tray fans provide cooling air to the broadband controller and the GCS
file server. Power for the tray fans is supplied by DC BUS 1.
The IFEC-ISPS MASTER switch, located near the lavatory A door,
provides a discrete to control and distribution cabinet (CDC) 3 to turn the
GCS on or off. CDC 3 sends the command to the other CDCs via a TTP
BUS to power the in-flight entertainment (IFE), GCS, and in-seat power
supply (ISPS) components.
The broadband controller provides the connectivity system with
bandwidth allocation and information management. The broadband
controller also controls the power supply unit for the Ku Band antenna
through an Ethernet bus. The broadband controller communicates with
the cabin management system (CMS) using an Ethernet bus to allow
control of the GCS at the CMS crew terminals. Power for the broadband
controller is provided by AC BUS 1.
Copyright © Bombardier Inc.
CS130-21.12-06.00-121418
TECHNICAL TRAINING MANUAL
For Training Purposes Only
44-20
44 - Cabin Systems
44-20 Global Connectivity Suite
(Option)
CDC 5-15-5
CONN KU 1
AC
SSPC 5A
BUS 1
KU BAND
ANTENNA
ASSEMBLY
POWER
SUPPLY
UNIT
GTE Relay
Logic: Advanced
To eXphone
(optional)
CDC 3
CDC 3-10-12
CONN Server 1
AC
SSPC 3A
BUS 1
BROADBAND
CONTROLLER
CABIN
MANAGEMENT
SYSTEM
Logic: Advanced
IFEC-ISPS
MASTER SWITCH
CDC 3-6-7
CONN Tray Fan
DC
SSPC 5A
BUS 1
FAN
DMC 1
Logic: Advanced
IRU 1
CDC 3-4-14
IFE Ethernet Sw
DC
SSPC 3A
BUS 1
LEGEND
Logic: Advanced
CDC 4-10-9
CONN Server 2
AC
SSPC 3A
BUS 2
CDC
DMC
GCS
IRU
GCS FILE
SERVER
Logic: Advanced
To eXW
and/or
eX1
FAN
Control and Distribution Cabinet
Data Concentrator Unit Module Cabinet
Global Connectivity Suite
Inertial Reference Unit
ARINC 429
Ethernet
RF COAX
TTP BUS
NOTE
GTE relay energized above 10,000 ft.
CS1_CS3_4420_011
IFEC
IFEC-ISPS
C-IS
SPS
MA
AST
TER
MASTER
Figure 10: eXconnect General Description
Copyright © Bombardier Inc.
CS130-21.12-06.00-121418
TECHNICAL TRAINING MANUAL
For Training Purposes Only
44-21
44 - Cabin Systems
44-20 Global Connectivity Suite
(Option)
CELL MODEM
A cell modem connects to 3G cellular networks in order to securely
offload IFE and GCS maintenance BITE data, and passenger payment
information. The cell modem is a required component of the global
connectivity suite. It can be installed as an option only if eX1 is installed.
The GCS file server sends information to the cabin controller through the
broadband controller via an Ethernet bus. The eX1 file server sends
information directly to the cabin controller through an Ethernet bus. The
cabin controller sends the data to the cell modem using an Ethernet bus.
A weight on wheels signal is supplied through the data concentrator unit
module cabinets (DMCs) to the cabin controller to determine when the
aircraft is on the ground. The cell modem only establishes a cellular
connection when the aircraft is on the ground.
The cell modem is powered by DC BUS 1.
Copyright © Bombardier Inc.
CS130-21.12-06.00-121418
TECHNICAL TRAINING MANUAL
For Training Purposes Only
44-22
44 - Cabin Systems
44-20 In-Flight Entertainment and Connectivity System
(Option)
DMC 1
and
DMC 2
Air/Gnd
BROADBAND
CONTROLLER
CABIN
CONTROLLER
GCS
FILE
SERVER
FILE
SERVER
(eX1 OPTION)
CELL
MODEM
LEGEND
CDC 5-15-9
CONN OBMT 2
AC
SSPC 3A
BUS 1
CDC
DMC
GCS
Logic: Advanced
Control and Distribution Cabinet
Data Concentrator Unit Module Cabinet
Global Connectivity Suite
ARINC 429
Ethernet
There is a domestic version and an
international version of the cell modem.
CS1_CS3_4420_020
NOTE
Figure 11: Cell Modem General Description
Copyright © Bombardier Inc.
CS130-21.12-06.00-121418
TECHNICAL TRAINING MANUAL
For Training Purposes Only
44-23
44 - Cabin Systems
44-20 Global Connectivity Suite
(Option)
COMPONENT LOCATION
The connectivity system consists of the following components:
•
GCS file server
•
Broadband controller
•
Cell modem
•
Ku band antenna assembly (Refer to figure 13)
•
Power supply unit (Refer to figure 13)
GCS File Server
The GCS file server is installed in the forward equipment bay.
Broadband Controller
The broadband controller is located in the forward equipment bay.
Cell Modem
The cell modem is located in the ceiling of the forward cabin.
Copyright © Bombardier Inc.
CS130-21.12-06.00-121418
TECHNICAL TRAINING MANUAL
For Training Purposes Only
44-24
44 - Cabin Systems
44-20 In-Flight Entertainment and Connectivity System
(Option)
C
A
B
Broadband
Controller
Global Connectivity
Suite File Server
C CELL MODEM
B
CS1_CS3_4420_016
A
Figure 12: eXconnect Global Connectivity Suite File Server, Broadband Controller, and Cell Modem Location
Copyright © Bombardier Inc.
CS130-21.12-06.00-121418
TECHNICAL TRAINING MANUAL
For Training Purposes Only
44-25
44 - Cabin Systems
44-20 Global Connectivity Suite
(Option)
Ku Band Antenna Assembly
The Ku band antenna assembly is mounted on top of the fuselage.
Power Supply Unit
The Ku band antenna has a dedicated power supply unit located below
the Ku band antenna assembly.
Copyright © Bombardier Inc.
CS130-21.12-06.00-121418
TECHNICAL TRAINING MANUAL
For Training Purposes Only
44-26
44 - Cabin Systems
44-20 In-Flight Entertainment and Connectivity System
(Option)
KU BAND ANTENNA ASSEMBLY
CS1_CS3_4420_016
Power
Supply Unit
Figure 13: eXconnect Ku Band Antenna Assembly and Power Supply Unit Location
Copyright © Bombardier Inc.
CS130-21.12-06.00-121418
TECHNICAL TRAINING MANUAL
For Training Purposes Only
44-27
44 - Cabin Systems
44-20 Global Connectivity Suite
(Option)
EXPHONE
The eXphone system is an optional subsystem of the eXconnect. The
eXphone system provides the aircraft cabin with a voice and data
capable 3G cellular network that is accessible using personal electronic
devices (PEDs).
A pair of leaky feeder cables are used to generate the 3G network
through the cabin. One of the leaky feeder cables is connected to a
duplexer to allow two way communication between the PEDs and the 3G
base transceiver station (BTS). The 3G BTS and duplexer are connected
by two RF coaxial cables. AC BUS 1 supplies power to the 3G BTS
The other leaky feeder cable is connected to the 3G network control unit
(NCU) and prevents the PEDs from connecting to ground based cellular
networks directly. The 3G NCU is controlled by the 3G BTS through an
Ethernet connection. The 3G NCU is powered by AC BUS 1.
All of the communication signals are sent from the 3G BTS to the
Ku band antenna assembly through the broadband controller using an
Ethernet bus.
Copyright © Bombardier Inc.
CS130-21.12-06.00-121418
TECHNICAL TRAINING MANUAL
For Training Purposes Only
44-28
44 - Cabin Systems
44-20 In-Flight Entertainment and Connectivity System
(Option)
PERSONAL
ELECTRONIC
DEVICE
Leaky
Feeder
CDC 5
CDC 5-15-9
CONN OBMT 2
AC
SSPC 3A
BUS 1
Leaky
Feeder
3G NCU
DUPLEXER
Logic: Advanced
CDC 5-17-12
CONN OBMT 1
AC
SSPC 3A
BUS 1
3G BTS
Logic: Advanced
BROADBAND
CONTROLLER
BTS
CDC
NCU
To Ku Band
Antenna Assembly
Base Transceiver Station
Control and Distribution Cabinet
Network Control Unit
Ethernet
RF COAX
CS1_CS3_4420_015
LEGEND
Figure 14: eXphone General Description
Copyright © Bombardier Inc.
CS130-21.12-06.00-121418
TECHNICAL TRAINING MANUAL
For Training Purposes Only
44-29
44 - Cabin Systems
44-20 Global Connectivity Suite
(Option)
COMPONENT LOCATION
The eXphone system consists of the following components:
•
Leaky feeder cables
•
3G base transceiver station
•
3G network control unit
•
Duplexer
Leaky Feeder Cables
The leaky feeder cables are installed in the cabin ceiling.
3G Base Transceiver Station
The 3G base transceiver station is located in the lower aft fuselage,
forward of the water and waste tanks.
3G Network Control Unit
The 3G network control unit in the lower aft fuselage, forward of the
water and waste tanks.
Duplexer
The duplexer is located in the lower aft fuselage, forward of the water
and waste tanks.
Copyright © Bombardier Inc.
CS130-21.12-06.00-121418
TECHNICAL TRAINING MANUAL
For Training Purposes Only
44-30
44 - Cabin Systems
44-20 In-Flight Entertainment and Connectivity System
(Option)
Leaky
Feeders
3G Base
Transceiver
Station
Duplexer
CS1_CS3_4420_012
3G Network
Control Unit
Figure 15: eXphone Component Location
Copyright © Bombardier Inc.
CS130-21.12-06.00-121418
TECHNICAL TRAINING MANUAL
For Training Purposes Only
44-31
44 - Cabin Systems
44-20 Global Connectivity Suite
(Option)
EXW
The eXW system provides a secure high speed WiFi network in the
aircraft cabin that allows multimedia to be sent from the dedicated file
server at speeds of up to 1,750 Mbps. Three wireless access points
(WAPs) are used to create a WiFi network that is accessible using
personal electronic devices (PED). In the CS300 model there is a fourth
WAP installed.
The CABIN POWER PBA located on the ELECTRICAL panel sends a
signal to the data concentrator unit module cabinet (DMC) over an
ARINC 429 DATA BUS. The DMCs send the command on the AFDX
DATA BUS to CDC 2 to power to the system.
WAPs 1 and 3 are powered by AC BUS 2. WAP 2 and 4 are powered by
AC BUS 1.
The eXW system is controllable through the dedicated file server using
the cabin management system (CMS) when it is installed as a
standalone system.
When the eXW system is installed as part of the global connectivity suite
(GCS), the dedicated file server is called the GCS file server. In GCS
configuration, the GCS file server provides Internet and streaming media
to the cabin WiFi network.
When the eX1 in-flight entertainment (IFE) is installed, an Ethernet bus
provides communication to the eX1 file servers to provide IFE
multimedia to the WiFi network.
The dedicated file server is connected to the WAPs through an Ethernet
bus and is powered by AC BUS 2.
The file server tray fan provides cooling air and is powered by
DC BUS 1.
The IFEC-ISPS MASTER switch provides a discrete signal to the control
and distribution cabinet (CDC) 3 and 4 to command power to the IFE,
GCS, and the in-seat power supply system (ISPSS) components on or
off. A TTP bus provides communication to the other CDCs.
Copyright © Bombardier Inc.
CS130-21.12-06.00-121418
TECHNICAL TRAINING MANUAL
For Training Purposes Only
44-32
44 - Cabin Systems
44-20 In-Flight Entertainment and Connectivity System
(Option)
LEGEND
CDC 2
IFEC-ISPS
MASTER SWITCH
IFEC
IFEC-ISPS
C-IS
SPS
MASTER
MA
AST
TER
CABIN PWR
CDC 2-15-4
CONN WAP 3
AC
SSPC 3A
BUS 2
DMC 1
and
DMC 2
CDC
CMS
DMC
OFF
NOTE
CABIN POWER
SWITCH
Logic: Advanced
When eXW is installed as part of the
Global Connectivity Suite, the GCS file
server replaces the dedicated file server.
CDC 4
CDC 4-13-5
CONN WAP 1
AC
SSPC 3A
BUS 2
Control and Distribution Cabinet
Cabin Management System
Data Concentrator Unit Module Cabinet
AFDX
ARINC 429
Ethernet
TTP BUS
WIRELESS
ACCESS
POINT 1
WIRELESS
ACCESS
POINT 3
WIRELESS
ACCESS
POINT 2
WIRELESS
ACCESS
POINT 4
(CS 300 ONLY)
Logic: Advanced
CDC 4-10-9
CONN Server 2
AC
SSPC 3A
BUS 2
To CMS
To eX1 and/or GCS (optional)
Logic: Advanced
DEDICATED
FILE SERVER
TRAY FAN
Power On/Off Discrete In
CDC 3-6-7
CONN Tray Fan
DC
SSPC 5A
BUS 1
Logic: Advanced
Power On/Off Discrete Out
Power On/Off Discrete In
CDC 5-15-6
CONN WAP 2
AC
SSPC 3A
BUS 1
Logic: Advanced
CDC 5-15-8
CONN KU 3
AC
SSPC 3A
BUS 1
Logic: Advanced
CS1_CS3_4420_014
CDC 5
CDC 3
Figure 16: eXW General Description
Copyright © Bombardier Inc.
CS130-21.12-06.00-121418
TECHNICAL TRAINING MANUAL
For Training Purposes Only
44-33
44 - Cabin Systems
44-20 Global Connectivity Suite
(Option)
COMPONENT LOCATION
The connectivity system consists of the following components:
•
Wireless access point
•
File servers
Wireless Access Point
There are three wireless access points (WAP) distributed throughout the
cabin ceiling. The CS300 has a fourth WAP installed in the cabin ceiling.
File Server
There is a file servers installed in the forward equipment bay.
Copyright © Bombardier Inc.
CS130-21.12-06.00-121418
TECHNICAL TRAINING MANUAL
For Training Purposes Only
44-34
44 - Cabin Systems
44-20 In-Flight Entertainment and Connectivity System
(Option)
WAP
No. 2
WAP
No. 3
C
WAP No. 4
(CS 300 only)
C
WAP
No. 1
C
C
A
B
B DEDICATED FILE SERVER
C WIRELESS ACCESS POINT
CS1_CS3_4420_017
A
Figure 17: eXW Component Location
Copyright © Bombardier Inc.
CS130-21.12-06.00-121418
TECHNICAL TRAINING MANUAL
For Training Purposes Only
44-35
44 - Cabin Systems
44-20 In-Seat Power Supply System
(Option)
44-20 IN-SEAT POWER SUPPLY SYSTEM
GENERAL DESCRIPTION
The in-seat power supply system (ISPSS) provides AC power to outlets
at the cabin seats allowing personal electronic devices to be charged or
powered. When ISPSS is installed, it becomes the primary source of
power for the passenger seats. The ISPSS also provides power to
monitors and other IFE equipment that may be installed in the passenger
cabin.
Power for individual seats can be turned on or off from the CMS crew
terminal.
Power is provided by AC BUS 1 and AC BUS 2 to the advanced master
control unit (AMCU) 1 and AMCU 2 respectively. The AMCUs change
the frequency of the voltage to 60 Hz and supplies this 3-phase voltage
to the seat power modules (SPMs). Each AMCU supplies five power
outputs to the cabin through disconnects. They are located at floor level
behind the sidewall panels, fore and aft of each overwing emergency exit
(OWEE) door. The power cables are routed through raceways in the
cabin floor to the SPMs at each seat row.
The SPMs supply up to 4 AC outputs to each seat row, and a single
28 VDC output to the SEB and IFE in-seat equipment. A RS 485 BUS
provides communications with seat subsystems for local control and
fault reporting.
Depending on the type of seats installed, the 3-phase AC power
provided by the AMCUs may be used to power seat motors and
actuators.
The ISPSS is controlled by the CABIN POWER PBA in the flight deck.
The switch is connected to the data concentrator unit module cabinets
(DMCs) via an ARINC 429 BUS. There is also an optional IFEC-ISPS
MASTER switch located next to the lavatory A door.
The DMCs command the control and distribution cabinets (CDCs) to
energize the AMCU relays. When the relays are energized a 3-phase AC
power is supplied to the AMCUs.
Copyright © Bombardier Inc.
CS130-21.12-06.00-121418
TECHNICAL TRAINING MANUAL
For Training Purposes Only
44-36
44 - Cabin Systems
44-20 In-Flight Entertainment and Connectivity System
(Option)
CABIN POWER
SWITCH
CABIN PWR
IFEC-ISPS
MASTER SWITCH
(OPTIONAL)
LEGEND
CREW
TERMINAL
CC
AMCU
CC
CDC
DMC
EPC
ISPS
SEB
SPM
AMCU 1 Relay
EPC 1
AMCU 1
OFF
To SPMs
IFEC
IFEC-ISPS
C-IS
SPS
MASTER
MA
AST
TER
CABIN DISCONNECT
AFT LEFT
AC
BUS 1
DMC 1
and
DMC 2
CDC 3
CDC 1
3Ø 120v
60Hz
25A
ISPS AMCU 1
CDC 11-13
ISPS RLY AMCU 1
DC
SSPC 3A
BUS 1
Advanced Master Control Unit
Cabin Controller
Control and Distribution Cabinet
Data Concentrator Unit Module Cabinet
Electrical Power Center
In-seat Power Supply
Seat Electrics box
Seat Power Module
AFDX
ARINC 429
Ethernet
RS 485
TTP BUS
CABIN DISCONNECT
FRONT RIGHT
Logic: Advanced
To SPMs
AMCU 2 Relay
EPC 2
AMCU 2
3Ø 120v
60Hz
AC
BUS 2
CABIN DISCONNECT
FRONT LEFT
CDC 10-9
ISPS RLY AMCU 2
DC
SSPC 3A
BUS 2
25A
ISPS AMCU 2
To SPMs
To SPM
SPM 1
SPM 2
DC SEB 1
DC SEB 2
Logic: Advanced
To Next SPM
CS1_CS3_4420_003
CDC 2
CABIN DISCONNECT
AFT RIGHT
Figure 18: In-Seat Power Supply System General Description
Copyright © Bombardier Inc.
CS130-21.12-06.00-121418
TECHNICAL TRAINING MANUAL
For Training Purposes Only
44-37
44 - Cabin Systems
44-20 In-Seat Power Supply System
(Option)
COMPONENT LOCATION
The ISPSS consists of the following components:
•
Advanced master control units
ADVANCED MASTER CONTROL UNITS
There are two advanced master control units located in the lower aft
fuselage, forward of the water and waste tanks.
Copyright © Bombardier Inc.
CS130-21.12-06.00-121418
TECHNICAL TRAINING MANUAL
For Training Purposes Only
44-38
44 - Cabin Systems
44-20 In-Flight Entertainment and Connectivity System
(Option)
Advanced Master
Control Unit No. 1
CS1_CS3_4420_013
Advanced Master
Control Unit No. 2
Figure 19: In-Seat Power Supply System Component Location
Copyright © Bombardier Inc.
CS130-21.12-06.00-121418
TECHNICAL TRAINING MANUAL
For Training Purposes Only
44-39
44 - Cabin Systems
44-20 In-Seat Power Supply System
(Option)
CONTROLS AND INDICATIONS
The in-seat power supply (ISPS) screen provides control of personal
electronic device (PED) power outlets at a passenger seat.
All active PED Power outlets display in green on the layout of passenger
area (LOPA). When a seat number is entered, the LOPA highlights the
selected seat and the ON/OFF button shows the status of the power
outlet.
To control in-seat PED power outlets:
1. Press the ENTER SEAT NUMBER(S) field and type a number.
2. Select the PED POWER IS OFF or ON button to remotely switch PED
power at an individual seat.
Selecting a Seat number using the LOPA button:
1. Touch the LOPA button.
2. Select the desired seats from the LOPA pop-up. Use the [] and
3. [] buttons to display additional seat selection buttons.
4. Touch [OK].
Copyright © Bombardier Inc.
CS130-21.12-06.00-121418
TECHNICAL TRAINING MANUAL
For Training Purposes Only
44-40
44 - Cabin Systems
44-20 In-Flight Entertainment and Connectivity System
(Option)
LOPA
CS1_CS3_4411_045
PED Power is:
Figure 20: CMS In-Seat Power System Screen
Copyright © Bombardier Inc.
CS130-21.12-06.00-121418
TECHNICAL TRAINING MANUAL
For Training Purposes Only
44-41
44 - Cabin Systems
44-20 Supplemental Avionics Bay Cooling and Smoke
Detection
44-20 SUPPLEMENTAL AVIONICS BAY
COOLING AND SMOKE DETECTION
GENERAL DESCRIPTION
SUPPLEMENTAL AVIONICS BAY COOLING
When the in-flight entertainment and connectivity (IFEC) system option
is installed, the in-flight entertainment (IFE) rack is mounted next to the
control and distribution cabinet (CDC) 5. The rack and CDC 5 are
combined in an enclosure, identified as the supplemental avionic bay.
The bay is normally cooled by the air extraction system and the mid
equipment bay air inlet cooling system.
A supplemental avionics bay cooling system provides backup cooling
and smoke extraction for the supplementary avionics bay. The system
consists of a supplemental avionics bay fan and a ventilated temperature
sensor (VENTS). The fan is powered by 28 VDC from DC BUS 2. The
VENTS monitor the supplemental avionics bay temperature.
If an overheat is detected, the air extraction and air inlet cooling systems
are turned off and the supplemental avionics bay fan operates. The fan
draws air out of the bay and ducts it to the mid equipment bay, where it is
exhausted overboard by means of the mid avionics exhaust valve.
Copyright © Bombardier Inc.
CS130-21.12-06.00-121418
TECHNICAL TRAINING MANUAL
For Training Purposes Only
44-42
44 - Cabin Systems
44-20 In-Flight Entertainment and Connectivity System
(Option)
OUTFLOW
VALVE
UNDERFLOOR
AFT
GALLEY
UNDERFLOOR
AVIONICS
FILTER
EXTRACTION
FAN 1
EXTRACTION
FAN 2
MID SKIN
HEAT EXCHANGER
From
Ground
Valve
MID BAY FAN
From Flight Deck
and Forward
Equipment Bay
CDC 5
MID
EQUIPMENT
BAY
IFE
RACK
AFT LAV
SUPPLEMENTAL
AVIONICS BAY
DC BUS 2
SUPPLEMENTAL
AVIONICS BAY FAN
LEGEND
M
UNDERFLOOR
BACKUP
FAN
CS1_CS3_4420_025
IFE
MID AVIONICS
Air Extraction System
EXHAUST VALVE
Air Inlet Cooling System
Backup Exhaust and Extraction System
Inflight Entertainment
Ventilated Temperature Sensor
Figure 21: Supplemental Avionics Bay Cooling
Copyright © Bombardier Inc.
CS130-21.12-06.00-121418
TECHNICAL TRAINING MANUAL
For Training Purposes Only
44-43
44 - Cabin Systems
44-20 Supplemental Avionics Bay Cooling and Smoke
Detection
SUPPLEMENTAL AVIONICS BAY SMOKE DETECTION
When the IFEC system is installed, two supplemental avionic bay smoke
detectors are installed in the ceiling of the control and distribution cabinet
(CDC) 5. The smoke detectors are open-air type and are not
interchangeable with any other smoke detectors on the aircraft.
Supplementary avionics bay smoke detector 1 is powered by DC ESS
BUS 1, and supplemental avionics bay smoke detector 2 is powered by
DC ESS BUS 2.
Each smoke detector is connected to one channel of the FIDEX CU by a
CAN BUS and uses AND logic. If smoke is detected by both smoke
detectors, an EQUIP BAY SMOKE warning message is displayed along
with an aural SMOKE message.
If both smoke detectors fail, an EQUIP BAY SMOKE FAIL caution
message is displayed.
If smoke is detected, or both smoke detectors fail, the FIDEX CU signals
the integrated air system controller (IASC) 2 to turn on the supplemental
avionics bay fan and turn off the air inlet cooling system.
Copyright © Bombardier Inc.
CS130-21.12-06.00-121418
TECHNICAL TRAINING MANUAL
For Training Purposes Only
44-44
44 - Cabin Systems
44-20 In-Flight Entertainment and Connectivity System
(Option)
DC ESS BUS 1
SUPPLEMENTAL AVIONICS
BAY SMOKE DETECTOR 1
DMC 1
and
DMC 2
FIDEX
CONTROL
UNIT
EICAS
OMS
“SMOKE”
HMU
IASC 2
Supplemental Avionics Bay Fan on
Air Inlet Cooling System off
DC ESS BUS 2
DMC
IASC
ARINC 429
CAN BUS A
Data Concentrator Unit Module Cabinet
Integrated Air System Controller
SUPPLEMENTAL AVIONICS BAY SMOKE DETECTOR 2
CS1_CS3_4420_026
LEGEND
Figure 22: Supplemental Avionics Bay Smoke Detection
Copyright © Bombardier Inc.
CS130-21.12-06.00-121418
TECHNICAL TRAINING MANUAL
For Training Purposes Only
44-45
44 - Cabin Systems
44-20 Supplemental Avionics Bay Cooling and Smoke
Detection
COMPONENT LOCATION
The supplemental cooling and smoke detection systems consist of the
following components:
•
Supplemental avionics bay fan
•
Supplemental avionics bay smoke detectors
•
Ventilated temperature sensor
SUPPLEMENTAL AVIONICS BAY FAN
The supplemental avionics bay fan is located on top of the supplemental
avionics bay enclosure.
SUPPLEMENTAL AVIONICS BAY SMOKE DETECTORS
The supplemental avionics bay smoke detectors are located on top of
the supplemental avionics bay enclosure above CDC 5.
VENTILATED TEMPERATURE SENSOR
The ventilated temperature sensor is located on top of the supplemental
avionics bay enclosure above CDC 5.
Copyright © Bombardier Inc.
CS130-21.12-06.00-121418
TECHNICAL TRAINING MANUAL
For Training Purposes Only
44-46
44 - Cabin Systems
44-20 In-Flight Entertainment and Connectivity System
(Option)
Supplemental
Avionics Bay Fan
Ventilated
Temperature
Sensor
CS1_CS3_4420_024
Supplemental
Avionics Bay
Smoke Detectors
Figure 23: Supplemental Avionics Bay Cooling and Smoke Detection Component Location
Copyright © Bombardier Inc.
CS130-21.12-06.00-121418
TECHNICAL TRAINING MANUAL
For Training Purposes Only
44-47
44 - Cabin Systems
44-20 Supplemental Avionics Bay Cooling and Smoke
Detection
CONTROLS AND INDICATIONS
The system is controlled from the EQUIP COOLING panel in the flight
deck. In normal operation, the EXHAUST rotary switch is in the AUTO
position and the system operation is automatically controlled by the
IASCs.
If a fault occurs in the main extraction system, the IASC automatically
selects the backup exhaust and extraction system. The EXHAUST rotary
switch is moved to the ON position to match the system configuration.
If smoke is detected in an avionics bay, the VLV ONLY rotary switch
position is selected and the backup fan is turned off, but the
supplemental avionics bay fan remains on.
Copyright © Bombardier Inc.
CS130-21.12-06.00-121418
TECHNICAL TRAINING MANUAL
For Training Purposes Only
44-48
44 - Cabin Systems
44-20 In-Flight Entertainment and Connectivity System
(Option)
CARGO
FWD
BTL
AVAIL
FIRE
AFT
FIRE
EQUIP COOLING
OVERHEAD
INLET
EXHAUST
VLV AUTO ON
ONLY
OFF
PRESSURIZATION
EMER DEPRESS
CS1_CS3_4420_028
ON
MAX ∆P
0.11 PSI TO
1.00 PSI LDG
Figure 24: Supplemental Avionics Bay Cooling Controls
Copyright © Bombardier Inc.
CS130-21.12-06.00-121418
TECHNICAL TRAINING MANUAL
For Training Purposes Only
44-49
44 - Cabin Systems
44-20 Supplemental Avionics Bay Cooling and Smoke
Detection
DETAILED DESCRIPTION
The supplemental avionics bay temperature monitoring is done by the
ventilated temperature sensor (VENTS). The VENTS is a dual-element
sensor with a small fan that draws air across the sensor elements. The
VENTS is powered by DC ESS BUS 3. One element is connected to
IASC 2 A channel and the other element is connected to channel B.
The supplemental avionics bay fan is powered by DC BUS 2 through
CDC 2. The fan also reports any faults to CDC 2. In normal operation,
the supplemental avionics bay fan remains off.
When the overheat is detected by the VENTS, an EQUIP BAY OVHT
warning message is displayed. The air extraction system is turned off
and the supplemental avionics bay fan turns on. The IFE equipment is
automatically switched off and cannot be reset for the remainder of the
flight. The supplemental avionics bay fan turns off when the EQUIP BAY
OVHT warning message clears.
If the fire detection and extinguishing (FIDEX) control unit (CU) detects
smoke in the supplemental avionics bay, an EQUIP BAY SMOKE
warning message is displayed. If smoke detection capability is lost, an
EQUIP BAY SMOKE FAIL caution message is displayed. In either case,
IASC 2 provides a signal to turn on the supplemental avionics bay fan
and shut down the air inlet cooling system.
The supplemental avionics bay fan also turns on when the INLET PBA is
selected OFF, or when the MID BAY FAN is detected failed.
The IASC 2 performs the SUPP BAY FAN operational test once per
flight. When the SUPP BAY FAN is detected failed, a SUPP FAN INOP
INFO message is displayed and the IFEC system shuts down.
The aircraft can be dispatched if the MID BAY FAN is inoperative as long
as the INLET PBA is selected OFF. The supplemental avionics bay fan
operates for the complete flight. If the supplemental avionics bay fan is
inoperative, the aircraft can be dispatched as long as the IFEC system is
selected off.
Copyright © Bombardier Inc.
CS130-21.12-06.00-121418
TECHNICAL TRAINING MANUAL
For Training Purposes Only
44-50
44 - Cabin Systems
44-20 In-Flight Entertainment and Connectivity System
(Option)
ECS Safety
Sensor
DC ESS BUS 3
3
RIGHT CIRCUIT BREAKER PANEL
EQUIP COOLING
INLET
EXHAUST
VLV
ONLY
AUTO
IASC 2
ON
Channel A
OFF
Channel B
DMC 1
and
DMC 2
OFF
CDC 2-10-3
SUPP BAY FAN
DC
BUS 2 SSPC 15A
Logic: Advanced
ELECTRICAL
PANEL
FIDEX
CONTROL
UNIT
LEGEND
Supplemental
Bay Fan Fault
Supplemental Avionics Bay Fan
Control and Distribution Cabinet
Data Concentrator Unit Module Cabinet
Integrated Air System Controller
Ventilated Temperature Sensor
ARINC 429
AFDX
CS1_CS3_4420_027
CDC
DMC
IASC
VENTS
Ventilated Temperature Sensor
CDC 2
CABIN PWR
Figure 25: Supplemental Avionics Bay Cooling Detailed Description
Copyright © Bombardier Inc.
CS130-21.12-06.00-121418
TECHNICAL TRAINING MANUAL
For Training Purposes Only
44-51
44 - Cabin Systems
44-20 Supplemental Avionics Bay Cooling and Smoke
Detection
MONITORING AND TESTS
The following page provides the crew alerting system (CAS) and INFO
messages for the avionics and electrical bay smoke detection system.
Copyright © Bombardier Inc.
CS130-21.12-06.00-121418
TECHNICAL TRAINING MANUAL
For Training Purposes Only
44-52
44 - Cabin Systems
44-20 In-Flight Entertainment and Connectivity System
(Option)
CAS MESSAGES
Table 4: STATUS Message
Table 1: WARNING Message
MESSAGE
MESSAGE
LOGIC
EQUIP BAY OVHT
Fwd or mid avionics bay, or supplementary bay
overtemperature.
EQUIP BAY SMOKE
Equipment bay smoke detected.
21 EQUIP BAY
COOL FAULT SUPP FAN INOP
MESSAGE
LOGIC
EQUIP BAY COOL FAIL
Both EFAN 1 and EFAN 2 detected inoperative by
the IASC safety channels.
Loss of ARINC data from both IASC safety
channels.
Both sensing elements of forward, mid bay, or
supplementary VENTS out of range.
EQUIP BAY SMOKE FAIL is the failure of both A
and B EE bay detectors, or the failure of either
one when the other channel is inoperative.
EXHAUST selector to ON and both AEV commanded
open and BUFAN commanded ON.
Table 5: INFO Messages
MESSAGE
Table 2: CAUTION Message
EQUIP BAY SMOKE
FAIL
EXHAUST AIR
ON
LOGIC
LOGIC
Supplementary bay fan inoperative.
21 EQUIP BAY
One channel of either FWD or MID or SUPP bay
COOL FAULT ventilated sensor failed.
AVIO TEMP SNSR
REDUND LOSS
26 FIRE SYSTEM Loss of one detector in equipment bay exhaust or
FAULT - EQUIP
supplemental avionics bay.
BAY SMOKE DET
REDUND LOSS
Table 3: ADVISORY Messages
MESSAGE
EQUIP BAY COOL
FAULT
LOGIC
One sensing element of supplementary avionics
bay VENTS is out of range.
Supplementary avionics bay VENTS sensing
elements disagree.
SUPP BAY FAN detected fault by the IASC main
channels.
FIRE SYSTEM FAULT
Copyright © Bombardier Inc.
CS130-21.12-06.00-121418
Loss of redundancy in the FIDEX system.
TECHNICAL TRAINING MANUAL
For Training Purposes Only
44-53
44 - Cabin Systems
44-20 Supplemental Avionics Bay Cooling and Smoke
Detection
Page Intentionally Left Blank
Copyright © Bombardier Inc.
CS130-21.12-06.00-121418
TECHNICAL TRAINING MANUAL
For Training Purposes Only
44-54
ATA 46 - Information Systems
Integrated Flight Information
System (Option)
BD-500-1A10
BD-500-1A11
46 - Information Systems
46-21 Integrated Flight Information System
(Option)
Table of Contents
46-21 Integrated Flight Information System............................46-2
Introduction .......................................................................46-2
General Description ..........................................................46-4
Component Location ........................................................46-6
Operation ..........................................................................46-8
Electronic Charts..........................................................46-8
Enroute Charts...........................................................46-10
Document Reader......................................................46-10
Enhanced Maps .........................................................46-12
Data Link Graphical Weather.....................................46-14
Detailed Description .......................................................46-16
System Interface ........................................................46-16
Monitoring and Tests ......................................................46-18
Chart Messages.........................................................46-18
Database Status ........................................................46-18
Practical Aspects.............................................................46-20
Application Enabling ..................................................46-20
Database Updates .....................................................46-20
Copyright © Bombardier Inc.
CS130-21.12-06.00-121418
TECHNICAL TRAINING MANUAL
For Training Purposes Only
46-i
46 - Information Systems
46-21 Integrated Flight Information System
(Option)
List of Figures
Figure 1: Integrated Flight Information System ....................46-3
Figure 2: IFIS File Server Application...................................46-5
Figure 3: Common Computing Modules and Integrated
Processing Cabinets Location...............................46-7
Figure 4: Electronic Charts ...................................................46-9
Figure 5: Enroute Charts and Document Reader ...............46-11
Figure 6: Enhanced Maps ..................................................46-13
Figure 7: Data Link Graphical Weather .............................46-15
Figure 8: IFIS System Interface..........................................46-17
Figure 9: Charts Messages and Database
Status Formats ....................................................46-19
Figure 10: Application Enabling and Database
Updates ...............................................................46-21
Copyright © Bombardier Inc.
CS130-21.12-06.00-121418
TECHNICAL TRAINING MANUAL
For Training Purposes Only
46-ii
46 - Information Systems
46-21 Integrated Flight Information System
(Option)
Page Intentionally Left Blank
Copyright © Bombardier Inc.
CS130-21.12-06.00-121418
TECHNICAL TRAINING MANUAL
For Training Purposes Only
46-iii
46 - Information Systems
46-21 Integrated Flight Information System
(Option)
INTEGRATED FLIGHT INFORMATION SYSTEM
Copyright © Bombardier Inc.
CS130-21.12-06.00-121418
TECHNICAL TRAINING MANUAL
For Training Purposes Only
46-1
46 - Information Systems
46-21 Integrated Flight Information System
(Option)
46-21 INTEGRATED FLIGHT INFORMATION
SYSTEM
INTRODUCTION
The C Series integrated flight information system (IFIS) option provides
increased situational awareness, and improves flight deck efficiency by
introduction of the following functions:
•
Print function
•
Enroute charts
•
Graphical weather
•
Electronic charts
•
Document reader
•
Enhanced map overlays
The C Series IFIS option is dual-configuration.
Copyright © Bombardier Inc.
CS130-21.12-06.00-121418
TECHNICAL TRAINING MANUAL
For Training Purposes Only
46-2
46 - Information Systems
46-21 Integrated Flight Information System
(Option)
IDX
ZOOM
PREV NEXT
169
DLK
TUNE
/5050
OBSERVATIONS
USA
PRINT FUNCTION
DEP
ARR
OTHER
ZOOM
RWY
SATCOM
FORECASTS
VAL
AGE
DOCS
IDX
ZOOM
PREV NEXT
13APR 0010 Z
00:05
GRAPHICAL WEATHER
169
/5050
MAP PLAN
EPHRATA SIX ARRIVAL
EMI
24
1
50
OVLY
ACT
HUO
SAX
ALT
100
TFC / WX +T / LX
T è 2.2A
KJFK
DOCUMENT READER
SYMBOL
FORTT
NEAREST ARPTS
AIRPORTS
MISSED APPR
RNG: ALT SEL
HI NAVAIDS
LO NAVAIDS
NDBS
HDG 280 W 280 T
30HI AIRWAYS
LO AIRWAYS
DRAPE TERM WAYPOINTS
DIMMO INTERSECTIONS
33
ETA, SPEED, ALT
POLITICAL
ETX
OBSTACLES
CITIES
CTRLD AIRSPACE
SUA
TFR
TFR REPORTS...
DONE
RBV
ELECTRONIC CHARTS
GWX
PRINT
NEXRAD
ENROUTE CHARTS
CYZD 10-2A
CPDLC
FMS1
ETX
DTK 281
TTG
2.5
20..4 NM
20
ENHANCED MAP OVERLAYS
CS1_CS3_4621_023
DOCS
Figure 1: Integrated Flight Information System
Copyright © Bombardier Inc.
CS130-21.12-06.00-121418
TECHNICAL TRAINING MANUAL
For Training Purposes Only
46-3
46 - Information Systems
46-21 Integrated Flight Information System
(Option)
GENERAL DESCRIPTION
The IFIS consists of a file server application (FSA) hosted on the
common computing module 5 (CCM 5), inside the integrated processing
cabinets 1 and 2 (IPC 1 and 2).
From the CCM, information is sent to the display units (DUs). Users
interact with an IFIS application through menus and dialog boxes on the
displays.
The IFIS option is offered with several function applications.
These functions are enabled via the application license manager (ALM)
inside IPC 1, with the use of the following application keys:
•
Electronic charts
•
Enroute charts
•
Enhanced maps
•
Data link graphical weather
•
Document reader
The applications require a mass storage device to operate since they are
database driven. This mass storage device is part of the CCM.
Copyright © Bombardier Inc.
CS130-21.12-06.00-121418
TECHNICAL TRAINING MANUAL
For Training Purposes Only
46-4
46 - Information Systems
46-21 Integrated Flight Information System
(Option)
APPLICATION
LICENSE MANAGER
IPC 1
CCM 2
FILE SERVER APPLICATION
Databases
Electronic
Charts
Terminal Charts
Enroute
Charts
Enroute Charts
Enhanced
Maps
PRINTER
Data Link
Weather
Document
Reader
CCM 5 INSIDE IPC 1 and IPC 2
Airspace, Political,
Cities, and Obstacles
Data Link Universal
Weather
OEM Documents
CS1_CS3_4621_024
DUs
Applications
Figure 2: IFIS File Server Application
Copyright © Bombardier Inc.
CS130-21.12-06.00-121418
TECHNICAL TRAINING MANUAL
For Training Purposes Only
46-5
46 - Information Systems
46-21 Integrated Flight Information System
(Option)
COMPONENT LOCATION
All IFIS applications, except for the print server, reside in CCM 5110
inside IPC 1 and IPC 2. The print server application resides in the
information management system (IMS) unit.
IFIS 1 is hosted in IPC 1, and IFIS 2 is hosted in IPC 2.
Copyright © Bombardier Inc.
CS130-21.12-06.00-121418
TECHNICAL TRAINING MANUAL
For Training Purposes Only
46-6
46 - Information Systems
46-21 Integrated Flight Information System
(Option)
IPC 2
A
IPC 1
INTEGRATED PROCESSING CABINET
A COMMON COMPUTING MODULE
CS1_CS3_4621_025
FWD EQUIPMENT BAY AFT RACK
Figure 3: Common Computing Modules and Integrated Processing Cabinets Location
Copyright © Bombardier Inc.
CS130-21.12-06.00-121418
TECHNICAL TRAINING MANUAL
For Training Purposes Only
46-7
46 - Information Systems
46-21 Integrated Flight Information System
(Option)
OPERATION
All IFIS functions are accessible via the menu button on the cursor
control panel (CCP). Quick access data keys located on the two control
tuning panels (CTPs), and multifunction keyboard panels (MKPs), allow
direct access to some of these functions.
Due to the extensive menu and sub-menu selections that are available
with the IFIS system, only representative examples of each IFIS feature
are presented in this section.
ELECTRONIC CHARTS
A yellow NO AIRCRAFT symbol appears in the top right corner when the
chart is geo-referenced, and no valid aircraft position data is available. A
green NO AIRCRAFT symbol indicates the chart does not support
aircraft symbol positioning.
When aircraft symbol positioning is supported by the chart, and position
information is available, an aircraft symbol is shown in green, and is
geo-referenced on the chart.
When the aircraft position is outside the chart range, a magenta aircraft
symbol appears on the chart border.
Charts can be panned, zoomed, and printed. A chart task menu is
available to the crew, and is displayed when the chart’s background is
selected.
When selecting:
•
PRINT... – displays the print chart dialog box
•
SUBSCRIPTION... – displays the chart subscription dialog box
Copyright © Bombardier Inc.
CS130-21.12-06.00-121418
TECHNICAL TRAINING MANUAL
For Training Purposes Only
46-8
46 - Information Systems
46-21 Integrated Flight Information System
(Option)
1
DSPL SEL
No aircraft symbol.
UPR
DSK
K
No position data available.
LWR
CNS
MENU
Not supported by chart.
CHKL
CURSOR CONTROL PANEL
1
SYN
DATA
DEP
CHART
MAP
ARR
CYZD 10-2A
VIDEO
OTHER
ZOOM
RWY
CHART TASK
AVAILABLE CHARTS...
SPLIT
ORIENT
DIM
CENTER AIRCRAFT
CENTER CHART
FIT
PRINT...
SUBSCRIPTION ...
EPHRATA SIX ARRIVAL
DOC
DBASE
2
Chart is geo-referenced, and valid position data.
3
Aircraft position is outside the geo-referenced
part of the chart.
CHART TASK MENU
FMS
CNS
CHKL
SYN
DATA
CHART SUBSCRIPTION
REGIONS ENABLED
MULTIFUNCTION
KEYBOARD PANEL
RANGE
R
MAP
FMS
CNS
CHKL
SYN
DATA
IN
TFC
WX
3
INBD DSPLY
L
TERR
CANADA - ALASKA
LATIN AMERICA
PACIFIC BASIN
AUSTRALIA
SOUTH AMERICA
USA - 48 STATES
USA - MILITARY
AFRICA
CHINA
2
BARO
HPA
NAV
SRC
CONTROL TUNING PANEL
CHART DISPLAY
SUBSCRIPTION NUMBER
PRINT CHART
PRINT
CURRENT CHART
ALL PRE-SELECTED CHARTS FOR CYZD
PRINT
DONE
PRINT CHART DIALOG BOX
ADD REGIONS
12345678901234567890
ACCESS CODE
PROCESSING
---------------CHART SUBSCRIPTION DIALOG BOX
DONE
CS1_CS3_4621_030
MAP
Figure 4: Electronic Charts
Copyright © Bombardier Inc.
CS130-21.12-06.00-121418
TECHNICAL TRAINING MANUAL
For Training Purposes Only
46-9
46 - Information Systems
46-21 Integrated Flight Information System
(Option)
ENROUTE CHARTS
The enroute charts function is accessible via the menu button or
quick-access key. The area to be viewed is selected from the DOCS
drop-down task menu.
If two chart formats are selected on the same display, they will merge
into a whole window chart format.
The print function is available from the IDX drop-down task menu.
DOCUMENT READER
The document reader provides access to documentation for crew and
maintenance personnel use, such as the aircraft flight manual, and flight
crew operating manual. Technical manuals containing fault code
information are also viewable in the document reader, but are not
available when the aircraft is not on the ground. The application converts
portable document format (PDF) files into a suitable format for viewing
on the display unit (DU).
Documents are viewable by selecting the DOCS drop-down task menu.
As for the enroute charts function, the print function is available from the
IDX drop-down task menu.
Copyright © Bombardier Inc.
CS130-21.12-06.00-121418
TECHNICAL TRAINING MANUAL
For Training Purposes Only
46-10
46 - Information Systems
46-21 Integrated Flight Information System
(Option)
DOCS
DATA
DOC
DATA
QUICK-ACCESS
KEY
AFM
FCOM 1
FCOM 2
FPCCM
QRH 1
QRH 2
AMM
FIM
WIRING
AFRIND
ASIA
C-AMER
EUROPE
MIDEST
N-AMER
S-AMER
ZOOM
IDX
DOCS
PREV NEXT
TOC...
DIM
PRINT...
/
IDX
ZOOM
PREV NEXT
3 /6
29-32-00: Hydraulic System No. 3
PRINT DOCUMENT
PAGE RANGE
12
PRINT
DOCS
IDX
ZOOM
PREV NEXT
12
TO
DONE
149 /522
ENROUTE CHARTS
CS1_CS3_4621_031
DOCUMENT READER
Figure 5: Enroute Charts and Document Reader
Copyright © Bombardier Inc.
CS130-21.12-06.00-121418
TECHNICAL TRAINING MANUAL
For Training Purposes Only
46-11
46 - Information Systems
46-21 Integrated Flight Information System
(Option)
ENHANCED MAPS
Enhanced maps improve situational awareness.
The following IFIS enhanced map symbols are selectable by the user:
•
Political Boundary – International and selected states, local
boundaries
•
Obstacle – Depicts interactive obstacle symbols. Selecting the
symbol displays additional information
•
City – Names of prominent cities and towns
•
Controlled Airspace – Interactive symbols with controlled and special
use airspace information
•
Special use airspace (SUA) – Areas designated for special
operations, and restricted to aircrafts not participating
The enhanced maps can be displayed on a single multifunction window
(MFW), or as a full page format if two adjacent MFWs are selected.
Copyright © Bombardier Inc.
CS130-21.12-06.00-121418
TECHNICAL TRAINING MANUAL
For Training Purposes Only
46-12
46 - Information Systems
46-21 Integrated Flight Information System
(Option)
Element
Symbol
MAP PLAN
OVLY
ACT
SYMBOL
FORTT
Political Boundary
FERGUS
HAMILTON
ROCKTON
MASAR
BURLINGTON
DECEL
DANIP
MILTON
Obstacle
City
Controlled Airspace
HALTON
DARPU LUBKO
OAKVILLE
HDG AUTO 24246
16
Special Use Airspace
(SUA)
21
MISSISSAUGA
ORAN
27
SAVOS
BRAMPTON
RW06R
VERKO
30
S
20
KLEINBURG
TORONTO
SEMTI
NEWMARKET
NEAREST ARPTS
AIRPORTS
MISSED APPR
RNG: ALT SEL
HI NAVAIDS
LO NAVAIDS
NDBS
HI AIRWAYS
LO AIRWAYS
TERM WAYPOINTS
INTERSECTIONS
ETA, SPEED, ALT
POLITICAL
OBSTACLES
CITIES
CTRLD AIRSPACE
SUA
DONE
MAP SYMBOL PULL DOWN MENU
KES
TERR
GREENBANK
BELOW
OSHAWA
PORT PERRY
FMS1
VERKO
DTK 226
TTG
3.5
16
16..0 NM
CS1_CS3_4621_032
BA
TFC
Figure 6: Enhanced Maps
Copyright © Bombardier Inc.
CS130-21.12-06.00-121418
TECHNICAL TRAINING MANUAL
For Training Purposes Only
46-13
46 - Information Systems
46-21 Integrated Flight Information System
(Option)
DATA LINK GRAPHICAL WEATHER
The data link graphical weather function provides the viewing capability
of weather information on DUs.
Information is obtained from a universal weather service that offers
weather information and products, such as:
•
NEXRAD (Continental USA)
•
Tops and movement (Continental USA)
•
Weather depiction (Worldwide)
•
Winds and temperatures (Worldwide)
•
Icing (Worldwide)
•
Turbulence (Worldwide)
Graphical weather information requires data link system installation.
As for the enhanced maps, the graphical weather can be displayed on a
single MFW, or as a full page format if two adjacent MFWs are selected.
Copyright © Bombardier Inc.
CS130-21.12-06.00-121418
TECHNICAL TRAINING MANUAL
For Training Purposes Only
46-14
46 - Information Systems
46-21 Integrated Flight Information System
(Option)
TUNE
DLK
OBSERVATIONS
CPDLC
SATCOM
FORECASTS
GWX
PRIN
PRINT
RINT
WINDS/TEMPS ...
ICING ...
TURBULENCE ...
NEXRAD...
TOPS/MOVE...
WX DEPICTION...
USA
NEXRAD
VAL 13APR
0010 Z
CS1_CS3_4621_033
AGE 00:05
Figure 7: Data Link Graphical Weather
Copyright © Bombardier Inc.
CS130-21.12-06.00-121418
TECHNICAL TRAINING MANUAL
For Training Purposes Only
46-15
46 - Information Systems
46-21 Integrated Flight Information System
(Option)
DETAILED DESCRIPTION
In normal condition, the active IFIS source is the onside IFIS, as follows:
•
IFIS 1 drives DU 1, DU 2, and the left MFW of DU 5.
•
IFIS 2 drives DU 3, DU 4, and the right MFW of DU 5.
On startup, the system compares the application keys with the
application license manager (ALM), checks chart subscription, validates
various databases, and reports any failures to the onboard maintenance
system (OMS).
When the onside source becomes invalid, a new independent session is
initiated between the cross-side IFIS source and the DUs.
The new session does not bring the user back to the last known
configuration, but rather to a default configuration. The new session is
independent of any other running session that IFIS 2 is providing to the
on-side displays.
SYSTEM INTERFACE
IFIS information is sent through the avionics full duplex switched
Ethernet (AFDX) network to the DUs from the CCM 5110, inside IPC 1
and IPC 2.
The data link graphical weather application receives information from the
data link system via the radio interface unit (RIU). This information is
relayed by the data concentrator unit module cabinets (DMCs) from the
ARINC 429 network.
The IFIS system also requires data from the flight management system
(FMS). The true heading and position information of the aircraft,
provided by the FMS, are used to display a moving aircraft symbol on
the electronic charts and maps.
IPC 3 and IPC 4 are alternate communication paths, in case of network
failure IPC 1 and IPC 2 with the DMCs.
Copyright © Bombardier Inc.
CS130-21.12-06.00-121418
TECHNICAL TRAINING MANUAL
For Training Purposes Only
46-16
46 - Information Systems
46-21 Integrated Flight Information System
(Option)
Application
License
Manager
Application Keys
Application Keys
DUs
DU 1
DU 3
DU 2
DU 4
DU 5
(L-MFW)
DU 5
(R-MFW)
IPC 3
IPC 4
IPC 1
CCM 5110
IFIS 1
IFIS 2
FMS 1
FMS 2
DMC 1
DMC 2
RIU
DATA LINK
(ATA 23)
CS1_CS3_4621_027
LEGEND
AFDX LAN A
AFDX LAN B
ARINC 429
IPC 2
CCM 5110
Figure 8: IFIS System Interface
Copyright © Bombardier Inc.
CS130-21.12-06.00-121418
TECHNICAL TRAINING MANUAL
For Training Purposes Only
46-17
46 - Information Systems
46-21 Integrated Flight Information System
(Option)
MONITORING AND TESTS
There are no user-initiated tests associated with the IFIS.
CHART MESSAGES
A chart message field, located in the center of the display, provides
several chart-related messages in white text:
•
NO CHART SELECTED – When no chart has been previously
selected or the IFIS source has changed
•
PROCESSING REQUEST – When the chart request has not yet
been completed
•
CHART FAULT – When the chart request cannot be completed
•
NO CHART DATABASE – When the chart database is missing or
corrupted
•
NO CHART SUBSCRIPTION – When the subscription number has
not been entered
Chart status line messages that can be posted in amber include:
•
CHECK DATE
•
OUT OF DATE
DATABASE STATUS
The database status format displays information about the installed
periodic databases. An amber message, NOT CURRENT, appears if an
application database has expired.
Copyright © Bombardier Inc.
CS130-21.12-06.00-121418
TECHNICAL TRAINING MANUAL
For Training Purposes Only
46-18
46 - Information Systems
46-21 Integrated Flight Information System
(Option)
DEP
ARR
OTHER
ZOOM
RWY
001 /002
CHART
DATABASE
2
CYZD 42-2
RNAV (GPS)-B
CHECK DATE
STATUS/PART NO.
AMM APT/MAP 1
BEGIN
END
---
---
3
DOC
AIRSPACE 1
Not Current
01May15
28May15
DBASE
AIRSPACE 2
Not Current
01May15
28May15
HI LOAD
LOA
OAD
AD MON
MON
FMS1 NAV DB
Not Current
01May15
28May15
FMS2 NAV DB
Not Current
01May15
28May15
TERM Charts 1
Not Current
23May15
11JUN15
TERM Charts 2
Not Current
23May15
11JUN15
AMM APT/RWY 1
Current
29May15
25JUN15
OBSTACLE 1
Current
01May15
25JUN15
OBSTACLE 2
Current
01May15
25JUN15
CITIES 1
Current
19AUG14
31DEC15
CITIES 2
Current
19AUG14
31DEC15
POLITICAL 1
Current
19AUG14
31DEC15
POLITICAL 2
Current
19AUG14
31DEC15
HRTDB1
096-0040-003
01OCT12
N/A
IMSA-6000
810-0096-008-00
OMST-6000
810-0099-2B0001-10
A/C HEALTH
LTH
3
MAINTENANCE
ANCEE
ANC
LICENSE MGMT
MGMMT
INFO MGMT
MT
1
NO CHART SELECTED
DAT
DA
DATALOAD
ATA
TALOA
OAD
AD
3
ChecklistDB1
ChecklistDB2
Chart Message Field
2
Chart Status Line
3
Database Info
TERMINAL CHARTS FORMAT
ChecklistDB3
DATABASE STATUS FORMAT
CS1_CS3_4621_029
1
Figure 9: Charts Messages and Database Status Formats
Copyright © Bombardier Inc.
CS130-21.12-06.00-121418
TECHNICAL TRAINING MANUAL
For Training Purposes Only
46-19
46 - Information Systems
46-21 Integrated Flight Information System
(Option)
PRACTICAL ASPECTS
APPLICATION ENABLING
Applications are enabled via the application license management menu.
DATABASE UPDATES
Periodic databases require updates on a specified regular schedule.
Electronic charts, enhanced maps, and enroute charts are updated via
the onboard data loader (ODL).
Data link graphical weather images are supplied through a subscription
from a service provider, When requested, they are uploaded to the
aircraft through the data link system.
Copyright © Bombardier Inc.
CS130-21.12-06.00-121418
TECHNICAL TRAINING MANUAL
For Training Purposes Only
46-20
46 - Information Systems
46-21 Integrated Flight Information System
(Option)
APPLICATION LICENSE MANAGEMENT
TYPE NO
CNS
NS
CHKL
CHK
HKL
L
SYN
YN
DATA
CHART
RT
PART NO
STATUS
DOC-6200
810-0150-001
DOCUMENT READER-DUAL
OVL-6200
810-0137-001
ENHANCED MAP-DUAL
ECH-6200
810-0137-001
ENHANCED MAP-DUAL
DLGX-6200
810-0140-001
ENABLED
ENABLED
DISABLING
DISABLED
APPLICATION LICENSE MANAGEMENT MENU
VIDEO
EO
MAINTENANCE
DATA LOAD
Load New Databases
DOC
Status
Name
DBASE
DB
DBAS
BASE
E
EMaps_1305_Exp_29May13
HI LOAD MONN
Jeppesen_Disk_09-2013
A/C HEALTH
A/
HEEALTH
MAINTENANCE
DATA LOAD
OAD
MAINTENANCEE
MA
MAINTENANC
LICENSE MGMT
INFO
FO MGMT
MGMMT
MG
Load New Databases
Name
Status
EMaps_1305_Exp_29May13
Overall Database Load Progress:
Jeppesen_Disk_09-2013
33%
DATALOAD
Start Load
Database Details
ls
EMaps_1305_Exp_29May13
FMS1
Transferring Files
45%
Jeppesen_Disk_09-2013
FMS2
Transferring Files
15%
LOAD NEW DATABASE MENU
CS1_CS3_4621_028
Status:
Figure 10: Application Enabling and Database Updates
Copyright © Bombardier Inc.
CS130-21.12-06.00-121418
TECHNICAL TRAINING MANUAL
For Training Purposes Only
46-21
46 - Information Systems
46-21 Integrated Flight Information System
(Option)
Page Intentionally Left Blank
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TECHNICAL TRAINING MANUAL
For Training Purposes Only
46-22
ATA 46 - Information Systems
Electronic Flight Bag (Option)
BD-500-1A10
BD-500-1A11
46 - Information Systems
46-23 Electronic Flight Bag
(Option)
Table of Contents
46-23 Electronic Flight Bag.....................................................46-2
Introduction .......................................................................46-2
General Description ..........................................................46-4
Component Location ........................................................46-6
Electronic Display Unit .................................................46-6
Expansion Module Unit ................................................46-6
Optional Keyboard .......................................................46-6
Aircraft Information Server ...........................................46-8
Terrestrial Wireless Lan Unit......................................46-10
Crew Wireless Lan Unit .............................................46-10
RF Combiner..............................................................46-10
WLAN Antenna ..........................................................46-10
Controls and Indications .................................................46-12
EDU Bezel .................................................................46-12
EDU Status Area........................................................46-12
EDU Tabs Area..........................................................46-12
EDU Buttons Area......................................................46-12
Tools Menu ................................................................46-14
Operation ........................................................................46-16
Electronic Display Unit ...............................................46-16
Aircraft Information Server ........................................46-16
Detailed Description .......................................................46-18
Connectivity (optional) ...............................................46-22
Practical Aspects.............................................................46-24
EFB OMS Tests .........................................................46-24
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TECHNICAL TRAINING MANUAL
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46-i
46 - Information Systems
46-23 Electronic Flight Bag
(Option)
List of Figures
Figure 1: Electronic Flight Bag .............................................46-3
Figure 2: Electronic Flight Bag System ................................46-5
Figure 3: EFB Component Location .....................................46-7
Figure 4: AIS Component Location ......................................46-9
Figure 5: AIS Optional Component Location ......................46-11
Figure 6: EFB Controls and Indications..............................46-13
Figure 7: EFB Tools Menu..................................................46-15
Figure 8: EFB Operation.....................................................46-17
Figure 9: EFB System Interface .........................................46-19
Figure 10: Health Monitoring ................................................46-21
Figure 11: EFB Connectivity System Interface.....................46-23
Figure 12: EFB OMS Tests ..................................................46-25
Copyright © Bombardier Inc.
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TECHNICAL TRAINING MANUAL
For Training Purposes Only
46-ii
46 - Information Systems
46-23 Electronic Flight Bag
(Option)
Page Intentionally Left Blank
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TECHNICAL TRAINING MANUAL
For Training Purposes Only
46-iii
46 - Information Systems
46-23 Electronic Flight Bag
(Option)
ELECTRONIC FLIGHT BAG
Copyright © Bombardier Inc.
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TECHNICAL TRAINING MANUAL
For Training Purposes Only
46-1
46 - Information Systems
46-23 Electronic Flight Bag
(Option)
46-23 ELECTRONIC FLIGHT BAG
INTRODUCTION
The C Series electronic flight bag (EFB) option is a class II EFB that
provides the flight crew with access to applications such as document
viewer, navigation charts, and performance/maintenance logs.
The system consists of the following components:
•
Electronic display unit (EDU)
•
Aircraft information server (AIS)
•
Expansion module unit (EMU)
•
EDU mount
•
Optional keyboard
•
Connectivity system (optional)
The EDU, docked on the EDU mount, receives power through the
expansion module unit (EMU). It communicates with other aircraft
systems via the aircraft information server (AIS).
Copyright © Bombardier Inc.
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TECHNICAL TRAINING MANUAL
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46-2
46 - Information Systems
46-23 Electronic Flight Bag
(Option)
Aircraft
Systems
EXPANSION
MODULE UNIT
EDU MOUNT
KEYBOARD (OPTIONAL)
CS1_CS3_4623_001
ELECTRONIC
DISPLAY UNIT
AIRCRAFT
INFORMATION
SERVER
Electronic
Flight Bag
Connectivity
(optional)
Figure 1: Electronic Flight Bag
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TECHNICAL TRAINING MANUAL
For Training Purposes Only
46-3
46 - Information Systems
46-23 Electronic Flight Bag
(Option)
GENERAL DESCRIPTION
Access to the electronic flight bag (EFB) system is through the electronic
display unit (EDU). The EDU is a touchscreen unit that hosts a wide
range of EFB applications running on a Windows 7 operating system.
The unit is powered by 18 VDC coming from the expansion module unit
(EMU), which uses power from DC ESS BUS 1 (left EFB), or DC BUS 2
(right EFB).
An optional external keyboard provides another way for personnel to
interface with the EDU over a USB connection. This connection is
relayed by the EMU.
To communicate with the rest of the aircraft, the EDU interfaces with the
aircraft information server (AIS).
The AIS uses network connectivity to interface with:
•
Aircraft network switch
•
Data concentrator unit module cabinets (DMCs)
•
Printer (optional)
•
Terrestrial wireless LAN unit (TWLU (optional))
•
Crew wireless LAN unit (CWLU (optional))
The AIS also supports offboard data loading via the maintenance port on
the front panel.
The AIS uses power from DC ESS BUS 1.
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TECHNICAL TRAINING MANUAL
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46-4
46 - Information Systems
46-23 Electronic Flight Bag
(Option)
DC ESS BUS 1
DC BUS 2
1
2
USB
USB
18 VDC
KEYBOARD (OPTIONAL)
EXPANSION
MODULE UNIT (2X)
TERRESTRIAL
WIRELESS
LAN UNIT
DC ESS BUS 1
ELECTRONIC
DISPLAY UNIT (2X)
CREW
WIRELESS
LAN UNIT
AIRCRAFT
NETWORK
SWITCH
AIRCRAFT
INFORMATION
SERVER
DMC 1
AND
DMC 2
PRINTER
(OPTIONAL)
OFFBOARD
DATA LOADING
1
2
Left EFB.
Right EFB.
CS1_CS3_4623_002
NOTE
Figure 2: Electronic Flight Bag System
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TECHNICAL TRAINING MANUAL
For Training Purposes Only
46-5
46 - Information Systems
46-23 Electronic Flight Bag
(Option)
COMPONENT LOCATION
The EFB system includes the following components:
•
Electronic display unit (EDU)
•
Expansion module unit
•
Optional keyboard
•
Aircraft information server (Refer to figure 4)
•
Terminal wireless LAN unit (optional) (Refer to figure 5)
•
Crew wireless LAN unit (optional) (Refer to figure 5)
•
RF combiner (optional) (Refer to figure 5)
ELECTRONIC DISPLAY UNIT
There are two EDUs installed in the flight deck, one on the left side
console and the other on the right side console. Each EDU is docked on
an EDU mount, located on each side console.
EXPANSION MODULE UNIT
An EMU is mounted on the aft side of each EDU.
OPTIONAL KEYBOARD
An optional keyboard can be mounted on an extendable arm, attached
to the side console, below the EDU.
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TECHNICAL TRAINING MANUAL
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46-6
46 - Information Systems
46-23 Electronic Flight Bag
(Option)
A
Electronic
Display Unit
B
EDU Mount
Expansion
Module Unit
B
ELECTRONIC DISPLAY UNIT
(VIEW LOOKING AFT)
KEYBOARD
NOTE
Left side shown. Right side similar.
CS1_CS3_4623_003
A
Figure 3: EFB Component Location
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TECHNICAL TRAINING MANUAL
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46-7
46 - Information Systems
46-23 Electronic Flight Bag
(Option)
AIRCRAFT INFORMATION SERVER
The AIS is located on the aft shelf in the forward equipment bay.
Copyright © Bombardier Inc.
CS130-21.12-06.00-121418
TECHNICAL TRAINING MANUAL
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46-8
46 - Information Systems
46-23 Electronic Flight Bag
(Option)
CS1_CS3_4623_005
FWD EQUIPMENT BAY AFT RACK
AIRCRAFT INFORMATION SERVER
Figure 4: AIS Component Location
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TECHNICAL TRAINING MANUAL
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46-9
46 - Information Systems
46-23 Electronic Flight Bag
(Option)
TERRESTRIAL WIRELESS LAN UNIT
The TWLU is located in the forward cabin ceiling.
CREW WIRELESS LAN UNIT
The CWLU is located in the cabin ceiling just forward of the TWLU.
RF COMBINER
The RF combiner is mounted to the TWLU.
WLAN ANTENNA
The WLAN antenna is mounted on the top of the fuselage, aft of the
TWLU.
Copyright © Bombardier Inc.
CS130-21.12-06.00-121418
TECHNICAL TRAINING MANUAL
For Training Purposes Only
46-10
46 - Information Systems
46-23 Electronic Flight Bag
(Option)
Antenna
B
A
Crew
Wireless
Lan Unit
Rf
Combiner
A
B
CS1_CS3_4623_012
4623 012
Terrestrial Wireless
Lan Unit
Figure 5: AIS Optional Component Location
Copyright © Bombardier Inc.
CS130-21.12-06.00-121418
TECHNICAL TRAINING MANUAL
For Training Purposes Only
46-11
46 - Information Systems
46-23 Electronic Flight Bag
(Option)
CONTROLS AND INDICATIONS
EDU BEZEL
EDU TABS AREA
The EDU bezel includes nine keys that provide direct access to
navigational functions. The keys are backlit with light intensity controlled
automatically by ambient light sensors. The keys are as follows:
This area contains three tabs: MAIN, TOOLS, and COMMS.
•
Power – ON/OFF
•
Health status – Launches the health status window
This area contains buttons linked to installed applications. Each tab can
have up to 12 buttons.
•
Blank – Not assigned
•
Main menu – Displays icons for all opened applications. It can be
configured to launch a specific application
•
User-defined
•
Side view – Allows pilot and co-pilot to share screen views
•
Screen rotate – Generates a 90° clockwise rotation each time it is
pressed
•
Brightness – Adjusts the brightness of the display
EDU BUTTONS AREA
EDU STATUS AREA
Information regarding the EDU status can be found in this area, such as:
•
EMU – Green indicates the EDU is connected to the EMU. Yellow
means disconnected
•
Battery level – This only appears when the unit is using internal
battery power. The status goes from green to orange to blinking
orange
•
Health status – A yellow triangle appears when a malfunction has
been detected by the Health Monitor application
Copyright © Bombardier Inc.
CS130-21.12-06.00-121418
TECHNICAL TRAINING MANUAL
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46-12
46 - Information Systems
46-23 Electronic Flight Bag
(Option)
Bezel
PilotView ®
EMU
MAIN
1ԩHɡ
22:34
!
TOOLS
COMMS
Notes
E-DocView
LIDO
SideView
Status Area
Tabs Area
Ambient Light Sensor
Power
Health Status
Not Assigned
Main Menu
Buttons Area
User Defined
Side View
Screen Rotate
Brightness
Brightness
Shutdown
Help
USB Port
CS1_CS3_4623_008
Ambient Light Sensor
Figure 6: EFB Controls and Indications
Copyright © Bombardier Inc.
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TECHNICAL TRAINING MANUAL
For Training Purposes Only
46-13
46 - Information Systems
46-23 Electronic Flight Bag
(Option)
TOOLS MENU
The TOOLS menu provides access to several utilities to customize and
monitor the system.
Power Meter
The power meter utility controls or indicates the following:
•
Display brightness
•
Battery status
•
Power usage profile
•
Other display controls
Health Monitor
Similar to the health status key on the bezel, the Health Monitor button
launches the health monitor window, where several parameters can be
verified. These parameters include:
•
Firmware version
•
Processor core speed
•
Battery information
•
Detailed power level status
•
EDU components temperature levels
SW CID
Select this button to verify the EDU Configuration system software
version.
Copyright © Bombardier Inc.
CS130-21.12-06.00-121418
TECHNICAL TRAINING MANUAL
For Training Purposes Only
46-14
46 - Information Systems
46-23 Electronic Flight Bag
(Option)
PilotView ®
MAIN
22:37
EMU
TOOLS
COMMS
OverView
Power Meter
Keyboard setup
Calculator
HEALTH MONITOR
SYSTEM INFO
BATTERY
POWER
SYSTEM S/N
Health Monitor
OPERATING SYSTEM
TEMPERATURE
ǦǦǦǦǦǦǦǦǦǦǦǦǦ
Microsoft Windows Embedded
SERVICE PACK
1.0
BIOS VERSION
ǦǦǦǦǦǦǦǦǦǦǦǦǦ
EC VERSION
CPU FREQUENCY
169-615954-006
CPU Core 1
CPU Core 2
1995 Mhz
1995 Mhz
CPU Core 3
CPU Core 4
1995 Mhz
1995 Mhz
IP
ETHERNET ADAPTER
ǦǦǦǦǦ
MAC ADDRESS
88-88-88-88-87-88
Status
Speed
Down
ǦǦǦǦǦ
Hide
SW CID
CS1_CS3_4623_009
Go To Windows
Figure 7: EFB Tools Menu
Copyright © Bombardier Inc.
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TECHNICAL TRAINING MANUAL
For Training Purposes Only
46-15
46 - Information Systems
46-23 Electronic Flight Bag
(Option)
OPERATION
The EFB system uses an open architecture software environment, which
integrates a variety of third-party applications. These applications are
hosted by the EDU.
ELECTRONIC DISPLAY UNIT
The EDU comes pre-installed with a Windows 7 operating system and
an integrated software application browser, which provides a
configurable environment for accessing the applications. The operating
system is password protected.
The EDU can operate in two modes: offboard as a stand-alone unit or
onboard as part of the EFB system.
Offboard Mode
The Windows 7 operating system allows the EDU to work independently
when disconnected from the aircraft. In this mode, the EDU has no
communication capabilities. When used as a standalone unit, the EDU
uses its own internal battery power, or it can be powered using an
AC/DC power adapter.
Onboard Mode
When the EDU is docked on the EDU mount, it receives power from the
EMU and can communicate with the AIS.
AIRCRAFT INFORMATION SERVER
This unit is a loadable software aircraft part. Configuration files can be
uploaded via the information management system (IMS), or by
connecting a portable data loader to the maintenance port on the front of
the unit. In both cases, the aircraft is on ground and the maintenance
switch is in the UPLOAD position.
Copyright © Bombardier Inc.
CS130-21.12-06.00-121418
TECHNICAL TRAINING MANUAL
For Training Purposes Only
46-16
46 - Information Systems
46-23 Electronic Flight Bag
(Option)
Offboard
Onboard
AC/DC POWER
ADAPTER
EXPANSION
MODULE UNIT
EDU MOUNT
ELECTRONIC
DISPLAY UNIT
AIRCRAFT
NETWORK
SWITCH
INFORMATION
MANAGEMENT
SYSTEM
AIRCRAFT
PORTABLE
DATA LOADER
NORM
AIRCRAFT
INFORMATION
SERVER
Air/Gnd
UPLOAD
HMU MAINTENANCE PANEL
CS1_CS3_4623_006
MAINT
Figure 8: EFB Operation
Copyright © Bombardier Inc.
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TECHNICAL TRAINING MANUAL
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46-17
46 - Information Systems
46-23 Electronic Flight Bag
(Option)
DETAILED DESCRIPTION
The crew interfaces with the electronic flight bag (EFB) system via the
electronic display unit (EDU).
The electronic flight bag (EFB) data link function uses ARINC 429
connection, and is routed via the data concentrator unit module cabinets
(DMCs).
System Interface
The EDU is powered by 18 VDC from its expansion module unit.
Information is entered into the EFB system through the touchscreen or
an optional keyboard connected to the EDU. The external USB port also
allows for portable memory storage. The EDU connects to the aircraft by
a docking connector.
The AIS collects fault information for the EDUs, TWLU, CWLU, and AIS
and sends the information to the OMS via an ARINC 429 BUS.
The EFB communicates with other aircraft systems via the aircraft
information server (AIS) as follows:
•
The AIS receives 28 VDC from DC ESS BUS 1.
Via ARINC 429
-
Sends information to data concentrator unit module cabinets
(DMCs) about:
•
•
•
-
•
The left EMU receives 28 VDC from DC ESS BUS 1, while the right EMU
receives 28 VDC from DC BUS 2.
Battery status
Built-in tests (BITs)
Data link activity
Receives information from data concentrator unit module cabinets
(DMCs) about:
• Navigation data
• Engine data
• Landing gear data
Via Ethernet connection
-
Aircraft network switch (ANS)
-
Optional printer
-
Optional flight deck door surveillance system (FDDSS)
To ensure network security, the AIS interfaces with the ANS via a
network communication gap (NCG). This protocol can exchange data
between two network domains using a secure file exchange.
Copyright © Bombardier Inc.
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TECHNICAL TRAINING MANUAL
For Training Purposes Only
46-18
46 - Information Systems
46-23 Electronic Flight Bag
(Option)
CDC 1-8-16
AIS
DC ESS
BUS 1
USB - R
SSPC 3A
Logic: Always On
NCG
ELECTRONIC
DISPLAY UNIT
Docking
Connector
AIRCRAFT
INFORMATION
SERVER
18 VDC
EXPANSION
MODULE UNIT
ANS
KEYBOARD (OPTIONAL)
CDC 1-5-10
Aircraft Network Switch
Data Concentrator Unit Module Cabinet
Flight Deck Door Surveillance System
Network Communication Gap
ARINC 429
Ethernet
Power Input
USB
CDC 4-4-7
LH EDU
LEGEND
ANS
DMC
FDDSS
NCG
PRINTER
(optional)
DC ESS
BUS 1
SSPC 5A
RH EDU
DC
BUS 2
Logic: Always On
FDDSS
(optional)
SSPC 5A
Logic: Always On
TERRESTRIAL
WIRELESS
LAN UNIT
(optional)
CREW
WIRELESS
LAN UNIT
(optional)
CS1_CS3_4623_007
Ext.
USB
DMC 1
and
DMC 2
Figure 9: EFB System Interface
Copyright © Bombardier Inc.
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TECHNICAL TRAINING MANUAL
For Training Purposes Only
46-19
46 - Information Systems
46-23 Electronic Flight Bag
(Option)
Health Monitoring
On the EDU, the health status key launches a status window provided by
the health monitoring application, which is a component of the EDU
system software.
The health status key is backlit, with amber indicating that the system is
faulty, and white indicating that the system is functional.
On the AIS front panel, three LEDs indicate the health status of the unit
as follows:
•
Power LED – Remains green when the AIS is powered properly from
the aircraft 28 VDC BUS
•
Power fault LED – A bi-color LED. On power-up, it is red, then
changes to yellow before turning off. If it stays either red or yellow
after powering up, there is a fault with the AIS power distribution and
the system does not boot
•
System fault LED – Red during the system boot process. It changes
to flashing yellow during power-up BIT, then turns off to indicate that
the system is ready to be used
Copyright © Bombardier Inc.
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TECHNICAL TRAINING MANUAL
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46-20
46 - Information Systems
46-23 Electronic Flight Bag
(Option)
~1 sec
POWER LED
OFF
GREEN
POWER FAULT LED
OFF
RED
SYSTEM FAULT LED
OFF
OFF
~1 sec
YELLOW
~30-40 sec
~120-180 sec
OFF
RED
28 V
SUPPLIED
TO ANS
EDU Health
Status Key
CS1_CS3_4623_010
PANEL
AIS
S FRONT
FRO
PANEL
Figure 10: Health Monitoring
Copyright © Bombardier Inc.
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TECHNICAL TRAINING MANUAL
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46-21
46 - Information Systems
46-23 Electronic Flight Bag
(Option)
CONNECTIVITY (OPTIONAL)
The EFB wireless connectivity system provides cabin and external Wifi
network access, and cellular connectivity to the EFBs.
The AIS provides the network connections to the EFB for the TWLU and
CWLU. The AIS communicates with the TWLU and the CWLU via an
ETHERNET BUS.
The AIS gathers fault information from the TWLU and CWLU and sends
the information to the OMS via DMCs.
TWLU
The TWLU provides wireless communication between the EFBs and
airport terminal Wifi or cellular networks. This enables the EFB
applications to obtain updated information from the airline operator or the
airport terminal when it is available. Information is sent between the EFB
and the TWLU using the AIS. The TWLU is only active when the aircraft
is on the ground.
The TWLU interfaces with an RF combiner that is connected to the
external WLAN antenna.
The control and distribution cabinet (CDC) 3 provides DC BUS 1 power
to the TWLU.
CWLU
The CWLU provides secured wireless networks capable of connecting
portable devices to the EFBs. This allows the crew to access the EFB
applications remotely. Access to the network is password protected and
is limited to devices enabled by the airline or aircraft operator.
CDC 4 provides DC BUS 2 power to the CWLU.
Copyright © Bombardier Inc.
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TECHNICAL TRAINING MANUAL
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46-22
46 - Information Systems
46-23 Electronic Flight Bag
(Option)
Left EFB
and
Right EFB
Cellular
or
Airport Terminal
DMC 1
and
DMC 2
Air/Gnd
CDC 3-5-1
Wireless
LAN
Antenna
(optional)
TWLU
DC
BUS 1
SSPC 5A
Logic: Always On
TERRESTRIAL
WIRELESS
LAN UNIT
(optional)
RF Signal
RF
COMBINER
RF Signal
AIRCRAFT
INFORMATION
SERVER
ARINC 429
Ethernet
CDC 4-4-3
Personal
Devices
CWLU
DC
BUS 2
SSPC 5A
CS1_CS3_4623_011
LEGEND
CREW
WIRELESS
LAN UNIT
(optional)
Logic: Always On
Figure 11: EFB Connectivity System Interface
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TECHNICAL TRAINING MANUAL
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46 - Information Systems
46-23 Electronic Flight Bag
(Option)
PRACTICAL ASPECTS
EFB OMS TESTS
An EFB initiated built-in test (IBIT) can be carried out using the OMS
when the aircraft is on the ground. The test is also used to test the EFB
connectivity system.
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CS130-21.12-06.00-121418
TECHNICAL TRAINING MANUAL
For Training Purposes Only
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(Option)
MAINT MENU
MAINT MENU
LRU/System Operations
View
All ATAs
Select ATA
46 - INFORMATION SYSTEM
Select LRU/System
Electronic Flight Bag
Test
*NOTE*
LRU`S ETHERNET CONNECTIVITY WILL BE TESTED ACCORDING
TO AIRCRAFT OPTIONS INSTALLED
IBIT
TEST DURATION: 2 MINUTES
PRECONDITIONS
1- REFER TO AMP XX-XX-XX-XX-XXXX
-TEST INHIBIT/INTERLOCK CONDITIONS-
PRESS "CONTINUE" BUTTON TO GO TO NEXT PAGE
PRESS "CANCEL" BUTTON TO GO TO MAIN MENU
Continue
Cancel
CS1_CS3_4623_013
AIRCRAFT WEIGHT ON WHEEL STATUS:
Figure 12: EFB OMS Tests
Copyright © Bombardier Inc.
CS130-21.12-06.00-121418
TECHNICAL TRAINING MANUAL
For Training Purposes Only
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Copyright © Bombardier Inc.
CS130-21.12-06.00-121418
TECHNICAL TRAINING MANUAL
For Training Purposes Only
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