Honeywell HS-720 High Speed Data Unit for the MCS-7200 SATCOM System User Manual SDIM Multi Channel SATCOM System A15 5111 010

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Document Title	SDIM:Multi-Channel SATCOM System:A15-5111-010
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SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL
MCS--4200/7200 Multi--Channel SATCOM System
SECTION 5
ELECTRICAL INSTALLATION
1. Overview
A. General
(1) This section supplies electrical installation procedures, power distribution, and
interconnect diagrams for each component of the MCS system.
2. Equipment and Materials
A. General
(1) None.
3. Electrical Installation Procedure
A. Connector Layout and Contact Arrangement
(1) Each front panel connector of the SDU, HSU, and HPA complies with ARINC
characteristic 615, and is used to interface the LRU with an ARINC 615 portable data
loader for software uploads. Pin callouts are specified in Table 5-1. See the
MECHANICAL INSTALLATION section for specifics regarding connector part
numbers for the ARINC 615 connector for each LRU and the corresponding mating
connector.
(2) Table 5-2 lists the pin arrangements for the RJ--45 jack for the Ethernet Port 1. When
a user terminal is connected to this jack, the rear connectors are disconnected so
only the Ethernet Port 1 communications are available from this interface.
(3) The rear connectors of the SDU, HPA, RFUIA, and HSU comply with ARINC
characteristic 600 as specified in Table 5-3. The ARINC 600 connector layouts and
contact arrangement for the various connector plugs for each LRU of the MCS
system are shown in Figure 5-1 thru Figure 5-11.
(4) Table 5-4 and Table 5-5 list the contact arrangements for the top and middle inserts
for the SDU ARINC 600 connector. Table 5-6 lists the ICAO Block Strapping.
23--20--35
 Honeywell International Inc. Do not copy without express permission of Honeywell.
Page 5--1
15 Jul 2006
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL
MCS--4200/7200 Multi--Channel SATCOM System
Table 5-1.
ARINC 615 Connector Pin Callouts
SDU Signal Name
Pin
HSU Signal Name
HPA Signal Name
PDL 429 A IN
PDL 429 A IN
PDL TO HPA 429 A
PDL 429 B IN
PDL 429 B IN
PDL TO HPA 429 B
SHIELD GND
SHIELD GND
SHIELD GND
PDL 429 A OUT
PDL 429 A OUT
HPA TO PDL 429 A
PDL 429 B OUT
PDL 429 B OUT
HPA TO PDL 429 B
16
SHIELD GND
SHIELD GND
SHIELD GND
18
PDL LINK A
PDL LINK A
PDL LINK A
19
GND (PDL LINK B)
GND (PDL LINK B)
GND (PDL LINK B)
20
115 VAC HOT
115 VAC HOT
115 VAC HOT
21
CHASSIS GND
CHASSIS GND
CHASSIS GND
22
115 VAC GND
115 VAC GND
115 VAC GND
37
----
28 V DC OUTPUT
28 V DC OUTPUT
38
----
28 V DC RETURN
28 V DC RETURN
40
RS232 A RX--DLT
----
-- --
41
RS232 A TX--DLT
----
-- --
42
RS232 B RX--CMT
RS232 TO HSU
RS232 TO HPA
43
RS232 B TX--CMT
RS232 TO DEBUG
RS232 TO DEBUG
48
LOGIC COMMON GND
LOGIC COMMON GND
LOGIC COMMON GND
49
LOGIC COMMON GND
LOGIC COMMON GND
LOGIC COMMON GND
Table 5-2.
HSU Front Panel RJ--45 Pin Arrangements
Pin Name
RJ--45 Connector Pin
Signal Name
TX +
RJ--45 from User (+)
TX --
RJ--45 from User (--)
RX +
RJ--45 to User (+)
RX --
RJ--45 to User (--)
23--20--35
 Honeywell International Inc. Do not copy without express permission of Honeywell.
Page 5--2
15 Jul 2006
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL
MCS--4200/7200 Multi--Channel SATCOM System
Table 5-3.
ARINC 600 Connector Requirements
LRU
Connector Description
SDU
ARINC 600 -- Size 6
MCU No. 2 Shell
LRU Rear
Connector Part
No.
Rack Mounting
Connector Part No.
Outline Diagram
620--600--022
(Radiall)
NSXN2P201X0004
(Radiall)
Figure 4-2,
Figure 5-1,
Figure 5-2,
Table 5-4, and
Table 5-5
620--600--076
(Radiall)
NSXN2P221X0008
(Radiall)
Figure 4-3
Figure 5-3 thru
Figure 5-6
• Type 02 Top Insert
• Type 02 Middle Insert
• Type 04 Bottom Insert
• Index Pin Code 04
HPA
(60 W)
ARINC 600 -- Size 8
MCU No. 2 Shell
• Type 08 Top Insert
• Type 05 Middle Insert
• Type 04 Bottom Insert
• Index Pin Code 08
RFUIA
ARINC 600 -- Size 4
MCU No. 2 Shell
NSXNR221X0103 NSXNP221S0103
(Radiall)
(Radiall)
Figure 4--4
Figure 5-11
620--600--075
(Radiall)
Figure 4--5
Figure 5--7 thru
Figure 5--10
• Type 08 Top Insert
• Type 05 Middle Insert
• Type 04 Bottom Insert
• Index Pin Code 03
HSU
ARINC 600-- Size 4
MCU No. 2 shell
NSXN2P221X0003
(Radiall)
• Type 08 Top Insert
• Type 05 Middle Insert
• Type 04 Bottom Insert
• Index Pin Code 03
23--20--35
 Honeywell International Inc. Do not copy without express permission of Honeywell.
Page 5--3
15 Jul 2006
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL
MCS--4200/7200 Multi--Channel SATCOM System
Figure 5-1.
SDU ARINC 600 Connector Layout
23--20--35
 Honeywell International Inc. Do not copy without express permission of Honeywell.
Page 5--4
15 Jul 2006
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL
MCS--4200/7200 Multi--Channel SATCOM System
Table 5-4.
Contact Arrangements for Top Insert, SDU ARINC 600 Connector
WH--10
CABIN
VOICE
CHANNEL 1
HOOK-SWITCH
WH--10
CABIN
VOICE
CHANNEL 2
HOOK-SWITCH
WH10--1
STATUS
(RINGER)
WH10--1
STATUS
(RINGER)
WH10--2
STATUS
(RINGER)
WH10--2
STATUS
(RINGER)
AVIONICS
SUB-SYSTEM
SATCOM
FAIL
WARNING
(NON MCS
FAIL)
WH--10
CABIN VOICE
CHANNEL 1
IN--USE
SATELLITE
LINK NOT
READY
WH--10
CABIN
VOICE
CHANNEL 2
IN--USE
ANALOG
PBX
CHANNEL 1
INPUT HI
ANALOG
PBX
CHANNEL 1
INPUT LO
ANALOG
PBX
CHANNEL 1
OUTPUT HI
ANALOG
PBX
CHANNEL 1
OUTPUT LO
ANALOG
PBX
CHANNEL 2
INPUT HI
ANALOG
PBX
CHANNEL 2
INPUT LO
ANALOG
PBX
CHANNEL 2
OUTPUT HI
ANALOG PBX
CHANNEL 2
OUTPUT LO
COCKPIT
VOICE UN-AVAILABLE
CABIN
VOICE UN-AVAILABLE
PACKET
DATA UN-AVAILABLE
PACKET
DATA LOW
SPEED ONLY
AVAILABLE
(CD2--2)
SATCOM IN-OPERABLE
(MCS FAIL)
CEPT--E1
0V SHIELD
(GND)
CEPT--E1 to
BRIDGED
CTU
(CM--250) 1A
CEPT--E1 to
BRIDGED CTU
(CM--250) 1B
CEPT--E1 to
BRIDGED
CTU
(CM--250) 2A
CEPT--E1 to
BRIDGED
CTU
(CM--250) 2B
RESERVED
RESERVED
RESERVED
RESERVED
RESERVED
RESERVED
RESERVED
RESERVED
RESERVED
CEPT--E1
0V
RESERVED
RESERVED
RESERVED
RESERVED
RESERVED
RESERVED
RESERVED
RESERVED
RESERVED
RESERVED
RESERVED
RESERVED
SPARE 429
OUTPUT A
SPARE 429
OUTPUT B
RESERVED
RESERVED
RESERVED
RESERVED
RESERVED
SPARE
RESERVED
RESERVED
SPARE
RESERVED
RESERVED
RESERVED
RESERVED
RESERVED
RESERVED
RESERVED
RESERVED
RESERVED
RESERVED
RESERVED
RESERVED
RESERVED
RESERVED
RESERVED
SPARE
SPARE
SPARE
DISCRETE
INPUT
CONFIG
STRAP TYPE
SPARE
DISCRETE
INPUT
CONFIG
STRAP TYPE
SPARE
RESERVED
RESERVED
RESERVED
RESERVED
RESERVED
RESERVED
SPARE
10
AVAIL OF
429 SSR
MODE S
ADDRESS
RESERVED
FOR FMC
CONFIG
RESERVED
FOR FMC
CONFIG
CMU
BUS
SPEED
CPDF
CONFIG
AES ID
BUS SPEED
HSU #1
PRESENCE
SDU
CONTROLLER
TYPE
RESERVED
FOR STRAP
OPTION
CALL LIGHT
ACTIVATOR
CONFIGU-RATION
11
STRAP
PARITY
(ODD)
CCS
PRESENCE
IRS
CONFIG
IRS
CONFIG
HPR/HPA/
BSU/LGA
CONFIG
HPR/HPA/
BSU/LGA
CONFIG
HPR/HPA/
BSU/LGA
CONFIG
HPR/HPA/
BSU/LGA
CONFIG
HPR/HPA/
BSU/LGA
CONFIG
HPR/HPA/
BSU/LGA
CONFIG
12
CFDS/CMC
TYPE
CFDS/CMC
TYPE
CFDS/CMC
TYPE
RESERVED
CONFIG
SDU
CONFIG
SDU
NUMBER
CMU
NO. 1
CONFIG
CMU
NO. 2 CONFIG
WSC/
MCDU/
NO. 1
CONFIG
WSC/
MCDU/
NO. 2
CONFIG
13
PRIORITY
4 CALLS
MCDU/
BUS SPEED
LIGHT/
CHIME
CODE
LIGHT/
CHIME
CODE
WSC/
MCDU/
NO. 3
CONFIG
SDU
CODEC 1
WIRING
SDU
CODEC 1
WIRING
SDU
CODEC 2
WIRING
SDU
CODEC 2
WIRING
COCKPIT
SIGNALING
METHOD
14
5V
POS_MON
9V
POS_MON
RESERVED
ATE
RESET-MON_N
PEIT_SEL_N
RESERVED
ATE
RS--232
INPUT FROM
HSU
RS--232
OUTPUT TO
HSU
CEPT--E1
FROM
BRIDGED
CTU
(CM--250)1A
CEPT--E1
FROM
BRIDGED
CTU
(CM--250)1B
15
15 V
POS_MON
15 V
NEG_MON
GND (ATE
COMMON)
CEPT--E1
FROM
BRIDGED
CTU
(CM--250) 2A
CEPT--E1
FROM
BRIDGED
CTU
(CM--250) 2B
DLT_RX
(RS232
RX--SDU)
DLT_TX
(RS232
TX--SDU)
CMT_RX
(RS232
RX--SDU)
CMT_TX
(RS232
TX--SDU)
CMT_DLT_
RTN
23--20--35
 Honeywell International Inc. Do not copy without express permission of Honeywell.
Page 5--5
15 Jul 2006
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL
MCS--4200/7200 Multi--Channel SATCOM System
Table 5-5.
Contact Arrangements for Middle Insert, SDU ARINC 600 Connector
WH10 CABIN
NO. 1
AUDIO IN HI
WH10 CABIN
No. 1
AUDIO IN LO
WH10 CABIN
No. 1
AUDIO OUT
HI
WH10 CABIN
No. 1
AUDIO OUT
LO
DATA BUS
FROM CABIN
PACKET DATA
DATA BUS
FROM CABIN
PACKET
DATA B
FROM CMU
NO. 1
429
FROM CMU
NO. 1
429
TO CMU
NO. 1 AND
NO. 2
429 A
TO CMU
NO. 1 AND
NO. 2
429 B
COCKPIT
AUDIO CH 1
INPUT HI
COCKPIT
AUDIO CH 1
INPUT LO
COCKPIT
AUDIO CH 1
OUTPUT HI
COCKPIT
AUDIO CH 1
OUTPUT LO
COCKPIT
AUDIO CH 2
INPUT HI
COCKPIT
AUDIO CH 2
INPUT LO
COCKPIT
AUDIO CH 2
OUTPUT HI
COCKPIT
AUDIO CH 2
OUTPUT LO
CEPT--E1
FROM CTU
INPUT A
CEPT--E1
FROM CTU
INPUT B
CEPT--E1 TO
CTU OUTPUT
CEPT--E1 TO
CTU OUTPUT
DATA FROM
MCDU/WSC
NO. 1
DATA FROM
MCDU/WSC
NO. 1
DATA FROM
MCDU/WSC
NO. 2
DATA FROM
MCDU/WSC
NO. 2
DATA FROM
CMU
NO. 2
DATA FROM
CMU
NO. 2
DATA TO
SCDU/WSC
NO. 1,
NO. 2, AND
NO. 3
DATA TO
SCDU/WSC
NO. 1,
NO. 2, AND
NO. 3
AES
ID
INPUT
AES
ID
INPUT
FROM
CFDS
FROM
CFDS
TO
CFDS
TO
CFDS
MULTI-CONTROL
OUTPUT
MULTI-CONTROL
OUTPUT
WH10 CABIN
NO. 2
AUDIO IN
HI
WH10 CABIN
NO. 2
AUDIO IN
LO
LGA LNA
ON/OFF
CONTROL
WH10 CABIN
NO. 2
AUDIO OUT HI
WH10 CABIN
NO. 2
AUDIO OUT
LO
BITE INPUT
FROM LGA
LNA
CHIME/
LIGHT
INHIBIT
DUAL
SYSTEM
SELECT
DISCRETE
I/O
DUAL
SYSTEM
SELECT
DISCRETE
INHIBIT
BITE INPUT
FROM
HGA/HPA A
BITE INPUT
FROM
HGA/HPA B
SPARE 429
INPUT
SPARE 429
INPUT
BITE INPUT
FROM
LGA/HPA A
BITE INPUT
FROM
LGA/HPA B
BITE INPUT
FROM ACU
OR
TOP--PORT
BSU B
BITE INPUT
FROM STBD
BSU
BITE INPUT
FROM STBD
BSU
WEIGHT--ON--WHEELS
INPUT
NO. 1
INPUT
NO. 2
PROGRAM
SELECT
DATA FROM
PRIMARY
IRS A
DATA FROM
PRIMARY
IRS B
DATA FROM
SECONDARY
IRS A
DATA FROM
SECONDARY
IRS B
DATA BUS
FROM
AIRBORNE
LOADER
DATA BUS
FROM
AIRBORNE
LOADER
DATA BUS
TO
AIRBORNE
LOADER
DATA BUS
TO
AIRBORNE
LOADER
RESERVED
RESERVED
BITE INPUT
FROM ACU
OR
TOP--PORT
BSU A
DATA
LOADER
LINK A
DATA
LOADER
LINK B
RESERVED
FOR DATA
BUS FROM
RMP A
RESERVED
FOR DATA
BUS FROM
RMP B
CP VOICE
CALL LGT
OUTPUT
NO. 1
(CD1--1)
CP VOICE
MIC ON
INPUT
NO. 1
CP VOICE
CALL LGT
OUTPUT
NO. 2
(CD2--2)
CP VOICE
MIC ON
INPUT
NO. 2
DATA FROM
MCDU/WSC
NO. 3
DATA FROM
MCDU/WSC
NO. 3
DATA BUS
TO SNU OR
CPDF A
DATA BUS
TO SNU OR
CPDF B
RESERVED
FOR DATA
TO RMP A
RESERVED
FOR DATA
TO RMP B
FROM HSU #1
429A
FROM HSU
#1 429B
TO HSU #1
429A
TO HSU 429B
CEPT--E1
FROM 0BE1
CEPT--E1
FROM 0BE1
10
CEPT--E1 TO
0BE1 A
CEPT--E1 TO
0BE1 B
RESERVED
RESERVED
RESERVED
(GND)
RESERVED
(GND)
RESERVED
(GND)
RESERVED
(GND)
SPARE
SPARE
11
FROM
MOTION
SENSOR
NO. 1
MOTION
SENSOR
NO. 1
PROGRAM
SELECT
CALL
PLACE/END
DISCRETE
INPUT
NO. 1
CALL
PLACE/END
DISCRETE
INPUT
NO. 2
CGU
CONNECTION
CONFIG
COCKPIT
CALL
DISCRETE
SIGNALLING
MODE
RESERVED
UNSPEC
PROGRAM
RESERVED
UNSPEC
PROGRAM
RESERVED
UNSPEC
PROGRAM
STRAP
PARITY
EVEN
CROSSTALK
FROM
OTHERSDU
CROSSTALK
FROM
OTHERSDU
CROSSTALK
TO
OTHERSDU
CROSSTALK
TO
OTHERSDU
SPARE
SPARE
12
RESERVED
FOR DATA
FROM
FMC 1
RESERVED
FOR DATA
FROM
FMC 1
RESERVED
FOR DATA
FROM
FMC 2
RESERVED
FOR DATA
FROM
FMC 2
HSU #1
DISABLE
DISCRETE
OUT
SPARE
ICAO
ADDRESS
BIT NO. 1
(MSB)
ICAO
ADDRESS
BIT NO. 2
ICAO
ADDRESS BIT
NO. 3
ICAO
ADDRESS
BIT NO. 4
ICAO
ADDRESS
BIT NO. 5
ICAO
ADDRESS
BIT NO. 6
ICAO
ADDRESS
BIT NO. 7
ICAO
ADDRESS
BIT NO. 8
14
CP VOICE
GO--AHEAD
CHIME
RESET
CP VOICE
CHIME
CONTACT
1 (CD2--8)
CP VOICE
CONTACT
ICAO
ADDRESS
BIT NO. 9
ICAO
ADDRESS BIT
NO. 10
ICAO
ADDRESS
BIT NO. 11
ICAO
ADDRESS
BIT NO. 12
ICAO
ADDRESS
BIT NO. 13
ICAO
ADDRESS
BIT NO. 14
ICAO
ADDRESS
BIT NO. 15
15
ICAO
ADDRESS
BIT NO. 16
ICAO
ADDRESS
BIT NO. 17
ICAO
ADDRESS
BIT NO. 18
ICAO
ADDRESS
BIT NO. 19
ICAO
ADDRESS BIT
NO. 20
ICAO
ADDRESS
BIT NO. 21
ICAO
ADDRESS
BIT NO. 22
ICAO
ADDRESS
BIT NO. 23
ICAO
ADDRESS
BIT NO. 24
(LSB)
ICAO
ADDRESS
COMMON
13
23--20--35
 Honeywell International Inc. Do not copy without express permission of Honeywell.
Page 5--6
15 Jul 2006
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL
MCS--4200/7200 Multi--Channel SATCOM System
Figure 5-2.
Contact Arrangements for Bottom Insert, SDU ARINC 600 Connector
23--20--35
 Honeywell International Inc. Do not copy without express permission of Honeywell.
Page 5--7
15 Jul 2006
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL
MCS--4200/7200 Multi--Channel SATCOM System
Figure 5-3.
HPA ARINC 600 Connector Layout
23--20--35
 Honeywell International Inc. Do not copy without express permission of Honeywell.
Page 5--8
15 Jul 2006
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL
MCS--4200/7200 Multi--Channel SATCOM System
Figure 5-4.
Contact Arrangements for the Top Insert 60 Watt HPA ARINC 600 Connector
23--20--35
 Honeywell International Inc. Do not copy without express permission of Honeywell.
Page 5--9/5--10
15 Jul 2006
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL
MCS--4200/7200 Multi--Channel SATCOM System
Figure 5-5.
Contact Arrangements for Middle Insert, HPA (60 Watt) ARINC 600
23--20--35
 Honeywell International Inc. Do not copy without express permission of Honeywell.
Page 5--11/5--12
15 Jul 2006
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL
MCS--4200/7200 Multi--Channel SATCOM System
Figure 5-6.
Contact Arrangements for Bottom Insert, HPA (60 Watt) ARINC 600 Connector
23--20--35
 Honeywell International Inc. Do not copy without express permission of Honeywell.
Page 5--13
15 Jul 2006
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL
MCS--4200/7200 Multi--Channel SATCOM System
Figure 5-7.
HS--720 ARINC 600 Connector Layout
23--20--35
 Honeywell International Inc. Do not copy without express permission of Honeywell.
Page 5--14
15 Jul 2006
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL
MCS--4200/7200 Multi--Channel SATCOM System
Figure 5-8.
Contact Arrangements for Top Insert, HSU ARINC 600 Connector
23--20--35
 Honeywell International Inc. Do not copy without express permission of Honeywell.
Page 5--15/5--16
15 Jul 2006
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL
MCS--4200/7200 Multi--Channel SATCOM System
Figure 5-9.
Contact Arrangements for the Middle Insert, HSU ARINC 600 Connector
23--20--35
 Honeywell International Inc. Do not copy without express permission of Honeywell.
Page 5--17/5--18
15 Jul 2006
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL
MCS--4200/7200 Multi--Channel SATCOM System
Figure 5-10.
Contact Arrangements for the Bottom Insert, HSU ARINC 600 Connector
23--20--35
 Honeywell International Inc. Do not copy without express permission of Honeywell.
Page 5--19
15 Jul 2006
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL
MCS--4200/7200 Multi--Channel SATCOM System
Figure 5-11.
RFUIA ARINC 600 Connector Layout
23--20--35
 Honeywell International Inc. Do not copy without express permission of Honeywell.
Page 5--20
15 Jul 2006
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL
MCS--4200/7200 Multi--Channel SATCOM System
B. Electrical Installation
(1) The information necessary to supply the electrical interconnects is shown in
Figure 5-12 thru Figure 5-26. Interconnect diagrams are as follows:
• Figure 5-12. Satellite Data Unit & HSU Interface Diagram
• Figure 5-13. CMC Top--mounted High Gain Antenna Interface Diagram
• Figure 5-14. WH--10 Handset Interface Diagram
• Figure 5-15. HF--SAT Transfer Panel Interface Diagram
• Figure 5-16. Signal Conditioning Unit Interface Diagram
• Figure 5-17. Maintenance Panel Assembly Interface Diagram
• Figure 5-18. HS--720 Interface Diagram
• Figure 5-19. HS--720 Forward ID and Configuration Pins
• Figure 5-20. Tecom Top--Mounted High Gain Antenna Interface Diagram
• Figure 5-21. Mechanically Steered High Gain Antenna Interface Diagram
• Figure 5-22. AMT--50 Mechanically Steered High Gain Antenna Interface Diagram
• Figure 5-23. Dassault Conformal High Gain Antenna Interface Diagram
• Figure 5-24. Ball Conformal High Gain Antenna Interface Diagram
• Figure 5-25. Low Gain Antenna Interface Diagram
• Figure 5-26. Toyocom Top--Mounted High Gain Antenna Interface Diagram.
(2) The applicable configuration pins in the aircraft wiring must be connected to make the
MCS system functional. The SDU receives and sends 30 system configuration
discrete inputs through the configuration pins to properly match the avionics
equipment installed on the aircraft (see Figure 5-12 and Paragraph 4. to identify the
configuration pins).
(3) The SDU receives a 24-bit ICAO address that identifies the aircraft in which the SDU
is installed (Figure 5-12). Continuity is defined as a resistance of 10 ohms or less
between a configuration pin or address pin and the common. Continuity is broken
when the resistance between a configuration pin or address pin and common
measures 100k ohms or greater.
(4) Table 5-6 lists ICAO Block Strapping.
23--20--35
 Honeywell International Inc. Do not copy without express permission of Honeywell.
Page 5--21
15 Jul 2006
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL
MCS--4200/7200 Multi--Channel SATCOM System
Blank Page
23--20--35
 Honeywell International Inc. Do not copy without express permission of Honeywell.
Page 5--22
15 Jul 2006
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL
MCS--4200/7200 Multi--Channel SATCOM System
Figure 5-12 (Sheet 1).
Satellite Data Unit & HSU Interface Diagram
23--20--35
 Honeywell International Inc. Do not copy without express permission of Honeywell.
Page 5--23/5--24
15 Jul 2006
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL
MCS--4200/7200 Multi--Channel SATCOM System
Figure 5-12 (Sheet 2).
Satellite Data Unit & HSU Interface Diagram
23--20--35
 Honeywell International Inc. Do not copy without express permission of Honeywell.
Page 5--25/5--26
15 Jul 2006
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL
MCS--4200/7200 Multi--Channel SATCOM System
Figure 5-12 (Sheet 3).
Satellite Data Unit & HSU Interface Diagram
23--20--35
 Honeywell International Inc. Do not copy without express permission of Honeywell.
Page 5--27/5--28
15 Jul 2006
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL
MCS--4200/7200 Multi--Channel SATCOM System
Table 5-6.
ICAO Block Strapping
Example: AES ID 53375006 (Octal)
Octal
Binary
SDU Connector Pin (MP)
C13
D13
E13
F13
G13
H13
J13
K13
D14
E14
F14
G14
H14
J14
K14
A15
B15
C15
D15
E15
F15
G15
H15
J15
Common
K15
NOTES:
1.
53375006 (Octal) = 101011011111101000000110 (Binary).
2.
Binary 1 = Open; Binary 0 = Ground.
3.
Pins assigned a zero (0) are wired to SDU connector pin MP--K15 (common).
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Blank Page
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Figure 5-13.
CMC Top--mounted High Gain Antenna (HGA) Interface Diagram
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Figure 5-14.
WH--10 Handset Interface Diagram
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Figure 5-15.
HF-SAT Transfer Panel Interface Diagram
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SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL
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Figure 5-16.
Signal Conditioning Unit Interface Diagram
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Blank Page
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Figure 5-17.
Maintenance Panel Assembly Interface Diagram
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SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL
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Figure 5-18.
HS--720 Interface Diagram
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SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL
MCS-4200/7200
TEMPORARY REVISION NO. 23-1
INSERT PAGE 40 OF 53 FACING PAGE 5-41/5-42.
Reason:
To add Note 3 to incorporate SBB operation data to Figure 5-19.
Replace Figure 5-19 with the new illustration as follows:
Figure 5-19. HS-720 Forward ID & Configuration Pins
23-20-35
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SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL
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Figure 5-19.
HS--720 Forward ID & Configuration Pins
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SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL
MCS--4200/7200 Multi--Channel SATCOM System
Figure 5-20.
Tecom Top--Mount High Gain Antenna Interface Diagram
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MCS--4200/7200 Multi--Channel SATCOM System
Figure 5-21.
Thales Mechanically Steered High Gain Antenna Interface Diagram
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SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL
MCS--4200/7200 Multi--Channel SATCOM System
Figure 5-22.
EMS AMT--50 Mechanically Steered High Gain Antenna Interface Diagram
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MCS--4200/7200 Multi--Channel SATCOM System
Figure 5-23.
Dassault Conformal High Gain Antenna Interface Diagram
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Figure 5-24.
Ball Conformal High Gain Antenna Interface Diagram
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Figure 5-25.
Low Gain Antenna Interface Diagram
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MCS--4200/7200 Multi--Channel SATCOM System
Figure 5-26.
Toyocom Top--mounted High Gain Antenna Interface Diagram
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SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL
MCS-4200/7200
TEMPORARY REVISION NO. 23-1
INSERT PAGE 41 OF 53 FACING PAGE 5-57.
Reason:
To change Table 5-7 to incorporate the GNSS frequency check algorithm data for pins TP11E
thru TP11K.
Replace Table 5-7 as follows:
Table 5-7.
Configuration Pins
Pin
Definition
TP11E
HPA ANTENNA SUBSYSTEM CONFIGURATION AND GNSS FREQUENCY CHECK ALGORITHM
TP11F
HPA ANTENNA SUBSYSTEM CONFIGURATION AND GNSS FREQUENCY CHECK ALGORITHM
TP11G
HPA ANTENNA SUBSYSTEM CONFIGURATION AND GNSS FREQUENCY CHECK ALGORITHM
TP11H
HPA ANTENNA SUBSYSTEM CONFIGURATION AND GNSS FREQUENCY CHECK ALGORITHM
TP11J
HPA ANTENNA SUBSYSTEM CONFIGURATION AND GNSS FREQUENCY CHECK ALGORITHM
TP11K
HPA ANTENNA SUBSYSTEM CONFIGURATION AND GNSS FREQUENCY CHECK ALGORITHM
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SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL
MCS--4200/7200 Multi--Channel SATCOM System
4. Configuration Pins
A. General
(1) The following paragraphs supply system configuration pin definitions and
interpretation information. Pins assigned to take on the binary one state in a given
code should be left as an open circuit. Pins assigned to take on the binary zero state
in the code should be wired to SDU connector pin MP15K (address common) on the
airframe side of the connection. The configuration pins are listed in Table 5-7.
Table 5-7.
Configuration Pins
Pin
Definition
TP10A
AVAILABILITY OF ARINC 429 ICAO 24--BIT AIRCRAFT ADDRESS (AES ID) FROM 429
PORTS
TP10B
FMC CONNECTION TO SDU
TP10C
FMC CONNECTION TO SDU
TP10D
ARINC 429 BUS SPEED TO/FROM CMU NO. 1 AND CMU NO. 2
TP10E
CPDF CONFIGURATION
TP10F
429 BUS SPEED OF AES ID INPUT
TP10G
HSU INSTALLED
TP10H
SCDU CONTROLLER TYPE
TP10J
RESERVED FOR STRAP OPTION
TP10K
CALL LIGHT ACTIVATION
TP11A
STRAP PARITY (ODD: COVERING THE OTHER 39 STRAP PINS)
TP11B
CCS PRESENCE
TP11C
IRS CONFIGURATION
TP11D
IRS CONFIGURATION
TP11E
HPR/HPA/BSU/LGA CONFIGURATION
TP11F
HPR/HPA/BSU/LGA CONFIGURATION
TP11G
HPR/HPA/BSU/LGA CONFIGURATION
TP11H
HPR/HPA/BSU/LGA CONFIGURATION
TP11J
HPR/HPA/BSU/LGA CONFIGURATION
TP11K
HPR/HPA/BSU/LGA CONFIGURATION
TP12A
CFDS TYPE
TP12B
CFDS TYPE
TP12C
CFDS TYPE
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Table 5-7.
Configuration Pins (cont)
Pin
Definition
TP12D
PAD FOR CFDS/SDU CONFIGURATION
TP12E
SDU CONFIGURATION
TP12F
SDU NUMBER
TP12G
CMU NO. 1 CONFIGURATION
TP12H
CMU NO. 2 CONFIGURATION
TP12J
MCDU/WSC NO. 1 CONFIGURATION
TP12K
MCDU/WSC NO. 2 CONFIGURATION
TP13A
PRIORITY 4 CALLS TO/FROM COCKPIT
TP13B
ARINC 429 BUS SPEED TO MCDU NO. 1, NO. 2, AND NO. 3
TP13C
COCKPIT VOICE CALL LIGHT/CHIME OPTIONS
TP13D
COCKPIT VOICE CALL LIGHT/CHIME OPTIONS
TP13E
MCDU/WSC NO. 3 CONFIGURATION
TP13F
SDU CODEC 1 WIRING
TP13G
SDU CODEC 1 WIRING
TP13H
SDU CODEC 2 WIRING
TP13J
SDU CODEC 2 WIRING
TP13K
COCKPIT HOOKSWITCH SIGNALING METHOD
MP11E
CM--250 CGU CONNECTION CONFIGURATION
MP11F
COCKPIT CALL DISCRETE SIGNALING MODE
MP11G
SPARE
MP11H
SPARE
MP11J
SPARE
MP11K
PARITY
B. Availability of ARINC 429 ICAO ADDRESS (AES ID) from 429 Ports
(1) The interpretation of this configuration pin is given in Table 5-8.
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Table 5-8.
TP10 Pin A
Availability of ARINC 429 ICAO ADDRESS (AES ID) from 429 Ports
Interpretation
ICAO ADDRESS (AES ID) NOT AVAILABLE FROM CMU NO. 1 OR CMU NO. 2 OR
AES ID INPUT
ICAO ADDRESS (AES ID) IS AVAILABLE FROM CMU NO. 1 OR CMU NO. 2 OR AES
ID INPUT
(2) When wired to the zero state, the TP10A configuration pin indicates the ICAO 24--bit
aircraft address (AES ID) is available in the ARINC 429 label 275/276 format from
one or both of the SDU CMU input ports or ARINC 429 label 214/216 format from the
AES ID input port, and that one of those ARINC 429 sources of the address is used
with no specific preference for CMU 1, CMU 2, or the AES ID input. In this state, the
discrete inputs on SDU pins MP13C thru MP13K and MP14D thru MP14J are not
assumed to be wired and the SDU does not use the discretes, even if the ARINC 429
sources fail or remain inactive.
(3) In the zero state, the SDU monitors the CMU 1, CMU 2, and AES ID input buses until
a valid ICAO address is received. Bits 1 thru 16 of the AES ID are obtained from the
label 214/275 word and bits 17 thru 24 are obtained from the label 216/276 word.
The SDU only constructs a full 24-bit address from labels 214/275 and 216/276
words received from the same input port (e.g., label 214/275 from CMU 1 can not be
combined with label 216/276 from CMU 2 or label 216 from the AES ID input). The
address is only considered valid if it does not consist of all zeros or ones, and has
been received in ARINC 429 words with their sign--status matrix (SSM) indicating
normal operation.
(4) If address words containing either all zeros or ones are received, followed by address
words with a valid address (i.e., not all zeros or ones), the SDU verifies the receipt of
both labels 214/275 and 216/276 at least twice with the same address bits content in
each respective word before declaring the address valid. This is to preclude the SDU
from inadvertently and prematurely assuming the address is valid after only one of
the two labels has yielded a valid segment of the overall address, but the most
previously received copy of the other label has not yet been updated to its intended
code. The root problem is that the 24 correlated address bits are transmitted in two
separate asynchronous words that are not inherently correlated/paired. This
requirement is intended to effectively pair the label 214/275 and 216/276
transmissions.
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(5) Once a valid ICAO address is received on any bus, the SDU ignores further data
received on any of the buses until the next POST/PAST. This requirement relieves
the SDU of having to deal with the possibility that the ICAO technical address might
change while the SDU is logged-on. The AES ID (ICAO address) is determined at
startup and cannot change until the next POST/PAST. The SDU does not log-on until
it has a valid AES ID. The SDU waits indefinitely to receive a valid address from an
available ARINC 429 source rather than giving up at the end of POST/PAST, since it
cannot proceed as an AES without the address. If the configuration pin indicates the
ARINC 429 source is available, the discretes are not wired. The SDU will not revert to
the discretes at the end of POST/PAST as the CMU may not yet be operational.
(6) If configuration pin TP10A is wired to the one state, then neither CMU input port nor
the AES ID input port is capable of supplying the AES ID in the ARINC 429 format
and the SDU reads the AES ID from the discrete inputs.
(7) With either the ARINC 429 or discrete inputs source, an AES ID of all zeros or all
ones (binary) is invalid (typically indicative of an unprogrammed address) which
constitutes a failure. The SDU does not attempt to log-on to a GES with an invalid
AES ID.
C. FMC Connection to SDU
(1) The interpretation of this configuration pin is given in Table 5-9.
Table 5-9.
FMC Connection to SDU
TP10 Pins
FMC NO. 1 CONNECTED, FMC NO. 2 CONNECTED
FMC NO. 1 CONNECTED, FMC NO. 2 NOT CONNECTED
FMC NO. 1 NOT CONNECTED, FMC NO. 2 CONNECTED
NEITHER FMC CONNECTED
Interpretation
NOTE: SATCOM does not support the FMC interface.
D. ARINC 429 Speed to/from CMU No. 1 and CMU No. 2
(1) The interpretation of this configuration pin is given in Table 5-10.
Table 5-10.
ARINC 429 Speed to/from CMU No. 1 and CMU No. 2
TP10 Pin D
Interpretation
LOW SPEED ARINC 429 DATA BUS
HIGH SPEED ARINC 429 DATA BUS
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MCS--4200/7200 Multi--Channel SATCOM System
(2) When this configuration pin is wired to the zero state, the SDU operates its input and
output ARINC 429 buses for the CMUs No. 1 and No. 2 at high speed. When wired to
the one state, the SDU operates these buses at the low speed.
E.
Cabin Packet Data Function (CPDF)
(1) The interpretation of this configuration pin is given in Table 5-11.
Table 5-11.
Cabin Packet Data Function (CPDF)
Interpretation
TP10 Pin E
CPDF CONNECTED
CPDF NOT CONNECTED
(2) When wired to the zero state, this configuration pin indicates the input designated for
the CPDF (MP1E and MP1F) is connected to an ARINC 429 source of data--3 packet
data and that the SDU output (pins MP9A and MP9B) is wired to the CPDF. The SDU
only logs/reports/ indicates CPDF failures and bus inactivity on the CPDF input bus if
this configuration pin indicates the bus is supposed to be connected to an ARINC
source. The SDU can assume (for functional purposes) the presence of the CPDF
connections from the state of this pin.
F.
ARINC 429 BUS Speed of AES ID Input
(1) The interpretation of this configuration pin is given in Table 5-12.
Table 5-12.
ARINC 429 Bus Speed of AES ID Input
TP10 Pin F
Interpretation
HIGH SPEED ARINC 429 BUS
LOW SPEED ARINC 429 BUS
G. HSU Presence
(1) The interpretation of this configuration pin is given in Table 5-13.
Table 5-13.
HSU Presence
Interpretation
TP10 Pin G
HSU INSTALLED
HSU NOT INSTALLED
(2) When wired to the zero state, this configuration indicates that SDU pins MP9E/F and
MP9G/H are connected to the high speed data unit (HSDU). The SDU only
logs/reports/indicates inactivity on its HSU input bus when this strap is in the zero
state. The SDU assumes, for functional purposes, the presence of the HSU from the
state of this strap.
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H. SDU Controller Type
(1) The interpretation of this configuration pin is given in Table 5-14.
Table 5-14.
SDU Controller Type
TP10 Pin H
Interpretation
WSC SDU CONTROLLER TYPE
MCDU/SDU CONTROLLER TYPE
(2) When wired to the zero state, the SDU interfaces to the Williamsburg SDU controller
(WSC) interface. When wired to the one state, the SDU interfaces to the
Multi--Controller Display Unit (MCDU). The SDU chooses the appropriate interface
protocols and BITE failures based on the state of TP10H.
(3) When the WSC SDU controller type is selected, TP13B (Table 5--29) must also be
wired to the zero state since the WSC interface only operates at low speed.
I.
Call Light On (Air/Ground Calls)
(1) The interpretation of this configuration pin is given in Table 5-15.
Table 5-15.
Call Light On (Air/Ground Calls)
Interpretation
TP10 Pin K
CALL LIGHT ON AT CALL INITIATION (FOR AIR/GROUND CALLS)
CALL LIGHT ON AT CALL CONNECTION (FOR AIR/GROUND CALLS)
J.
Strap Parity (ODD)
(1) The interpretation of this configuration pin is given in Table 5-16.
Table 5-16.
TP11 Pin A
Strap Parity (ODD)
Interpretation
SUM OF ALL OTHER STRAPS SET TO 1 IS ODD
SUM OF ALL OTHER STRAPS SET TO 1 IS EVEN
(2) The coverage of the parity pin is SDU connector pins TP10A thru TP10K and TP11B
thru TP13K (39 pins other than itself). The parity pin is programmed to a zero or one
to yield an odd number of strap bits set to the one state, including the parity pin itself.
(3) The parity pin is wired to yield odd parity over all 40 configuration pins (i.e., the parity
pin is programmed to the zero or one state to yield an odd number of configuration
pins wired to the one state, including itself. The SDU verifies the state of the parity
pin is correct when the configuration pins are read (typically once per power cycle just
after power-up). An invalid state of the parity pin is logged/reported/indicated; the
states of the other configuration pins are used as read despite the parity error.
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K. Cabin Communications System (CCS)
(1) The interpretation of this configuration pin is given in Table 5-17.
Table 5-17.
Cabin Communications System (CCS)
Interpretation
TP11 Pin B
CCS INSTALLED
CCS NOT INSTALLED
(2) When wired to the zero state, this configuration indicates that SDU pins MP2J/K and
MP3A/B (CEPT--E1 input and output respectively) are connected to the CCS CTU.
(3) The SDU only logs, reports, and/or indicates inactivity on its CCS input bus when this
strap is in the zero state. The SDU assumes, for functional purposes, the presence of
the CCS from the state of this strap.
L.
Inertial Reference System (IRS)
(1) The interpretation of these configuration pins is given in Table 5-18.
Table 5-18.
Inertial Reference System (IRS)
TP11 Pins
PRIMARY IRS INSTALLED, SECONDARY IRS INSTALLED
PRIMARY IRS INSTALLED, SECONDARY IRS NOT INSTALLED
PRIMARY IRS NOT INSTALLED, SECONDARY IRS INSTALLED
PRIMARY IRS NOT INSTALLED, SECONDARY IRS NOT INSTALLED
Interpretation
(2) When individually wired to the zero state, configuration pins TP11C and TP11D
indicate, respectively, that the inputs designated for the primary and secondary IRSs
(MP6A/MP6B and MP6C/MP6D, respectively) are connected to an ARINC 429
source of IRS label 310, 311, 312, 314, 324, 325, and 361 information (although label
361, Inertial Altitude, is not required for SATCOM). The actual IRS (i.e., IRS No. 1,
IRS No. 2, or IRS No. 3) driving either SDU input is determined from the source
destination identifier (SDI) bits of the received ARINC words. The SDU only
logs/reports/indicates bus inactivity on either bus if the respective configuration pin
indicates that the bus is supposed to be connected to an ARINC 429 source. The
SDU can assume (for functional purposes) the presence of the IRS connections from
the state of these pins.
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M. HPA/Antenna Subsystem Configuration
(1) The interpretation of these configuration pins is given in Table 5-19.
Table 5-19.
HPA/Antenna Subsystem Configuration
to
to
TP11 Pins
L B
G S
A U
H H
P G
A A
F E
O D
F O
U R
H H H U M
G P P R F
A A R E R
Note 1
Note 1
Note 2
Note 2
NOTES:
1.
Not defined at this time.
2.
Other configurations are possible and can be added at a later date.
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SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL
MCS-4200/7200
TEMPORARY REVISION NO. 23-1
INSERT PAGE 42 OF 53 FACING PAGE 5-64.
Reason:
To change Table 5-19 to incorporate the GNSS frequency check algorithm data.
Replace Table 5-19 as follows:
Table 5-19. (TP11E – K) HPA/Antenna Subsystem Configuration and
GNSS Frequency Check Algorithm1
[10]
Decimal
Code
LGA
HPA
TOP/PORT
BSU +
HGA
STARBOARD
BSU + HGA
HGA
HPA
GNSS
FREQ
CHK
REQD
GNSS
FREQ
CHK
NOT
REQD
ARINC
781
HGA
RESERVED
FOR
FUTURE
RESERVED
Pins TP11
LGA
HPR
FOR MFR
NOTES
63
62
61
60
59
58
57
56
55
54
48-53
to
47
46
45
44
43
42
41
40
39
38
8-37
to
0-7
to
Note 1: Other configurations are possible and may be added at a later date. Note that ARINC Characteristic 761 Attachment 1-4B Table 1-3K (which is an extension of ARINC
Characteristic 741 Table 1-4K) defines configurations which include intermediate-gain antennas (IGAs). Those IGA configurations may also apply to ARINC Characteristic
741-compatible equipment; therefore, the IGA codes defined in ARINC Characteristic 761 should be considered as reserved for those definitions in this table as well. Any
changes to this table should be coordinated with ARINC Characteristic 761. Note that the configuration codes for “GNSS Frequency Check Required” and “GNSS
Frequency Check Not Required” are identical except for TP11J. Refer to ARINC 741 Part 2 Section 3.5.4.1.1 regarding the frequency check for GNSS interference
prevention.
23-20-35
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(2) For functional purposes, the SDU assumes the HPA and antenna subsystem
configuration of its particular installation from states of these configuration pins.
However, configurations 100111 and 000111 are not supported. Both of the
nonsupported configurations involve the sharing of a single HPA between an LGA
and HGA, by using a high power relay (HPR). No control or BITE signal interfaces
are specified for the HPR, the MCS system does not accommodate these
configurations.
(3) The SDU commands the system, uses its resources, and logs/reports/indicates
failures in the HPAs and antenna subsystem based on the determined HPA and
antenna subsystem configuration. Inactivity on the SDU input buses from the HPA(s)
and ACU/BSU(s) and failures against the diplexer/LNA and HPR are
logged/reported/indicated if the respective LRU is specified to be connected
according to these pins. If these configuration pins are set to a nonsupported,
reserved for future, or reserved for Mfr state, the SDU logs/reports/indicates the
appropriate strap failure(s) and does not attempt any satellite communication
functions.
N. CFDS/CMC
(1) The interpretation of these configuration pins is given in Table 5-20.
Table 5-20.
CFDS/CMC
TP12 Pins
UNDEFINED
McDONNELL--DOUGLAS TYPE CFDS
AIRBUS TYPE CFDS
HONEYWELL CAIMS
BOEING TYPE CMC (ALL EPIC PLATFORMS)
UNDEFINED
UNDEFINED
CFDS NOT INSTALLED
Interpretation
(2) For functional purposes, the SDU can assume the type of central fault/maintenance
system (if any) that is connected from the state of these configuration pins. The
CMC/CFDS interface operates according to the determined type. The appropriate
strap failure(s) is(are) logged/indicated if an undefined code is present. The SDU only
logs/reports/indicates bus inactivity for the MP4C/MP4D CFDS interface input bus if
the configuration pins indicate the CMC/CFDS is supposed to be installed.
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O. SDU Configuration
(1) The interpretation of this configuration pin is given in Table 5-21.
Table 5-21.
SDU Configuration
Interpretation
TP12 Pin E
SECOND SDU INSTALLED
SECOND SDU NOT INSTALLED
(2) When wired to the zero state, this configuration pin indicates a second SDU is
present as part of the MCS system installation. The zero state also indicates pins
MP12C/MP12D and MP12A/MP12B (cross talk to and from the other SDU,
respectively) and MP5J/MP5K (dual system select and dual system disable discretes,
respectively) are connected to the second SDU. When this pin is in the zero state, it
also indicates these signals are used to determine dual SATCOM operation as
specified in SYSTEM OPERATION. The SDU only logs/reports/indicates inactivity on
its input cross--talk bus from the second SDU when this pin is in the zero state. The
SDU can assume (for functional purposes) the presence of a second SDU from the
state of this configuration pin. The SDU also uses the state of this pin (and for dual
SATCOM installations, the state of SDU number pin TP12F) to determine the state of
its output word SDI fields.
P.
SDU Number
(1) The interpretation of this configuration pin is given in Table 5-22.
Table 5-22.
TP12 Pin F
SDU Number
Interpretation
SDU NO. 2
SDU NO. 1
NOTE: The state of this strap is Don’t Care for a single SDU configuration.
(2) When wired to the zero state, this configuration pin indicates this SDU is No. 2 in a
dual MCS system installation. The one state indicates this SDU is No. 1 in a dual
installation. The SDU uses the state of this pin and the SDU configuration pin TP12E
to determine the state of its output word SDI fields. In a single MCS system
installation, the status of this configuration pin is ignored.
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Q. CMU No. 1 and No. 2 Configuration
(1) The interpretation of these configuration pins is given in Table 5-23 and Table 5-24.
Table 5-23.
CMU No. 1
Interpretation
TP12 Pin G
CMU NO. 1 INSTALLED
CMU NO. 1 NOT INSTALLED
Table 5-24.
CMU No. 2
Interpretation
TP12 Pin H
CMU NO. 2 INSTALLED
CMU NO. 2 NOT INSTALLED
(2) When individually wired to the zero state, configuration pins TP12G and TP12H
indicate, respectively, that the inputs designated for CMU No. 1 and CMU No. 2 (pins
MP1G/MP1H and MP3G/MP3H, respectively) are connected to an ARINC 429
source of CMU information (e.g., CMU label 270 and SAL 304), and also the single
SDU output (pins MP1J/MP1K) is wired to the appropriate CMU(s). The SDU only
logs/reports/indicates bus inactivity on either CMU input bus if the respective
configuration pin indicates the bus is supposed to be connected to an ARINC source.
The SDU can assume (for functional purposes) the presence of the CMU
connections from the state of these configuration pins.
R. MCDU/WSC No. 1 thru No. 3 Configuration
(1) The interpretation of these configuration pins is given in Table 5-25 thru Table 5-27.
Table 5-25.
TP12 Pin J
MCDU/WSC No. 1
Interpretation
MCDU/WSC NO. 1 INSTALLED
MCDU/WSC NO. 1 NOT INSTALLED
Table 5-26.
MCDU/WSC No. 2
Interpretation
TP12 Pin K
MCDU/WSC NO. 2 INSTALLED
MCDU/WSC NO. 2 NOT INSTALLED
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Table 5-27.
TP13 Pin E
MCDU/WSC No. 3
Interpretation
MCDU/WSC NO. 3 INSTALLED
MCDU/WSC NO. 3 NOT INSTALLED
(2) When individually wired to the zero state, configuration pins TP12J, TP12K, and
TP13E indicate, respectively, that the inputs designated for MCDU/WSC No. 1, No. 2,
and No. 3 (pins MP3C/MP3D, MP3E/MP3F, and MP8J/MP8K, respectively) are
connected to an ARINC 429 source of line select/keypad control information, and
also the single SDU output (MP3J/MP3K) is wired to all appropriate MCDU/WSC(s).
The SDU only logs/reports/indicates bus inactivity on any of the three buses if the
respective configuration pin indicates the bus is supposed to be connected to an
ARINC source. The SDU can assume (for functional purposes) the presence of the
MCDU/WSC connections from the state of these configuration pins.
S.
Priority 4 Calls to/from Cockpit
(1) The interpretation of this configuration pin is given in Table 5-28.
Table 5-28.
Priority 4 Calls to/from Cockpit
TP13 Pin A
Interpretation
DISALLOW PRIORITY 4 CALLS
ALLOWS PRIORITY 4 CALLS
(2) When this configuration pin is wired to the zero state, the SDU disallows priority 4
calls from being routed to or initiated from the cockpit. This state prevents ORT item
xiii (Appendix C) from being set to allow routing of ground-to-air priority 4 calls to the
cockpit headset. When this configuration is wired to the one state, the SDU lets
priority 4 calls be initiated from the cockpit and lets ground-to-air calls be routed to
the cockpit based upon ORT item xiii.
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T.
ARINC 429 BUS Speed to MCDU No. 1/MCDU No. 2/MCDU No. 3
(1) The interpretation of this configuration pin is given in Table 5-29.
Table 5-29.
ARINC 429 Bus Speed to MCDU No. 1/MCDU No.2/MCDU No. 3
TP13 Pin B
Interpretation
LOW SPEED ARINC 429 BUS
HIGH SPEED ARINC 429 BUS
(2) When this configuration pin is wired to the zero state, the SDU operates its ARINC
429 output bus for MCDU No. 1, No. 2, and No. 3 at the low speed. When wired to
the one state, the SDU operates this bus at the high speed.
U. Cockpit Voice Call Light/Chime Option
(1) The interpretation of these configuration pins is given in Table 5-30.
Table 5-30.
Cockpit Voice Call Light/Chime Option
TP13 Pins
SPARE
STEADY LIGHTS AND MULTISTROKE CHIME
FLASHING LIGHTS AND SINGLE STROKE CHIME
STEADY LIGHTS AND SINGLE STROKE CHIME
Interpretation
(2) The SDU determines the mode of cockpit call annunciation (flashing vs. steady voice
call lamp, multistroke vs single stroke chime) from the states of these configuration
pins. The functionality of the cockpit call annunciation interface (pins MP8E and
MP8G for the call lights, and MP14B and MP14C for the chime) operate according to
the configuration pin connections selected. The selected state of pins TP13C and
TP13D applies to both air- and ground-initiated calls; it only applies to the call
annunciation phase (i.e., following connection acknowledgement by receipt of the
off-hook state as specified by the state of TP13K, a multistroke chime is silenced and
the call lamp remains on steady). The appropriate strap failure(s) is logged/indicated
if an undefined code is present. The SDU defaults to the steady lights and single
stroke chime state if an undefined code is present.
(3) The steady versus flashing light option applies to the call annunciation phase only.
The light remains on (steady) for the duration of the call after the acknowledgement
of the annunciation for either the steady or flashing light option.
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V.
SDU CODEC 1 and CODEC 2 Wiring
(1) The interpretation of these configuration pins is given in Table 5-31 and Table 5-32.
Table 5-31.
SDU Analog Interface No. 1 Wiring
TP13 Pins
AMS WIRED, CABIN AUDIO WIRED
AMS WIRED, CABIN AUDIO NOT WIRED
AMS NOT WIRED, CABIN AUDIO WIRED
AMS NOT WIRED, CABIN AUDIO NOT WIRED
Interpretation
Table 5-32.
SDU Analog Interface No. 2 Wiring
TP13 Pins
AMS WIRED, CABIN AUDIO WIRED
AMS WIRED, CABIN AUDIO NOT WIRED
AMS NOT WIRED, CABIN AUDIO WIRED
AMS NOT WIRED, CABIN AUDIO NOT WIRED
Interpretation
(2) The SDU determines the extent and nature of the analog cockpit and cabin voice
connections from the states of these configuration pins. The functionality of the
analog cockpit and cabin voice interface (pins MP1A/MP1B, MP1C/MP1D,
MP2A/MP2B, MP2C/MP2D, MP2E/MP2F, MP2G/MP2H, MP4J/MP4K, and
MP5E/MP5F) operate according to the connections selected. ORT item vi for codec
dedication (Appendix C) is related to the SDU codec configuration pins; dedication or
automatic sharing of a codec to or with a particular interface is only possible if the
SDU codec wiring straps indicate the codec is wired to that interface.
W. Cockpit Hookswitch Signaling Method
(1) General
(a) The interpretation of this configuration pin is given in Table 5-33.
Table 5-33.
TP13 Pin K
Cockpit Hookswitch Signaling Method
Interpretation
SWITCHED PTT AND/OR SCDU LINE SWITCH(ES)
LATCHED AUDIO CONTROL PANEL SATCOM MICROPHONE SWITCH
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(b) This configuration pin specifies the functionality of the SDU Cockpit Voice
Mic-On Input No. 1 (and No. 2) discrete inputs (referred to as the mic-on
inputs). When TP13K is wired to the one state, the SDU utilizes the switched
PTT and/or MCDU/SCDU line switch(es) (referred to as switched PTT) method
for cockpit hookswitch signaling on the mic-on inputs. When TP13K is wired to
the zero state, the SDU utilizes the latched audio control panel SATCOM
microphone switch (referred to as the latched ACP) method. These two
methods are described below.
(2) Switched PTT Method
(a) With the switched PTT method, the SDU assumes the mic-on inputs are wired to
conventional microphone momentary push-to-talk switches (i.e., they are
dynamically active [on/off] throughout the duration of the call). The SDU
assumes the air- or ground-initiated call annunciation to have been
acknowledged (i.e., the call to be in the off-hook state) when the appropriate
mic-on input is activated (connected to ground) for the first time after the call
annunciation for a particular channel. Successive activations of that mic-on input
for the duration of that call have no effect on the status of that call until the call
has been cleared.
(b) With the switched PTT method, the off-hook state is also entered following
activation of the Answer Call line select switch on the MCDU/SCDU. The
on-hook state is entered following activation of the End Call line select switch on
the MCDU/SCDU that results in call clearing.
(c) This method also allows usage of the place/end call discrete input and
associated switch to initiate calls to preselected numbers, as well as to terminate
existing calls.
(3) Latched ACP Method
(a) With the latched ACP method, the SDU assumes the mic-on inputs are wired to
SATCOM microphone select switches on the ACP that are latched on
(connected to ground) for the entire duration of a call. The SDU considers the
air- or ground-initiated call annunciation to have been acknowledged (i.e., the
call to be in the off-hook state) when the appropriate mic-on input is active
(connected to ground) for a particular channel. The call is cleared and the
channel is considered to be in the on-hook state when the mic-on input is in the
open-circuit state.
(b) With the latched ACP method, all hookswitch signaling for answering and
terminating all air- and ground-initiated calls is handled by the mic-on inputs; the
MCDU/SCDU Answer Call and End Call options are blanked (the MCDU/SCDU
is only necessary for specifying the called-party number and initiating the call
process for air-to-ground calls).
(c) This method also allows usage of the mic--on discrete input and switch to initiate
calls to preselected numbers.
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X.
CM--250 CGU Connection Configuration
(1) The interpretation of this configuration pin is given in Table 5-34.
Table 5-34.
CM--250 CGU Connection Configuration
Interpretation
MP11 Pin E
CM--250 LOOPED CONFIGURATION
CM--250 IN--LINE CONFIGURATION
(2) Looped configuration is not implemented. Assume In--Line configuration (MP11E set
to the 1 state).
Y.
Cockpit Call Discrete Signaling Mode
(1) The interpretation of this configuration pin is given in Table 5-35.
Table 5-35.
Cockpit Call Discrete Signaling Mode
MP11 Pin F
Interpretation
EPIC COCKPIT CALL DISCRETE SIGNALING MODE
COCKPIT CALL LIGHT/CHIME SIGNALING MODE
(2) Table 5-36 gives the call signaling definitions and SDU output pins with MP11F in a
logic 0 and logic 1 state.
Table 5-36.
SDU Output Pin
Call Signaling Definitions
Legacy Call Signaling
Definition (MP11F=1)
Enhanced Call Signaling
Definition (MP11F=0)
MP8E
CHANNEL 1 CALL LIGHT
CHANNEL 1 CD 1 (CD1--1)
MP14B
CHIME
CHANNEL 1 CD 2 (CD2--1)
MP8G
CHANNEL 2 CALL LIGHT
CHANNEL 2 CD 1 (CD1--2)
TP3D
PACKET DATA LOW SPEED
ONLY
CHANNEL 2 CD 2 (CD2--2)
(3) Selecting the EPIC cockpit call discrete signaling mode (MP11F=0) is only required
when the SDU is connected to the Honeywell AV--900 audio control panel (ACP).
This ACP is typically installed on EPIC equipped aircraft.
(4) When MP11F is wired to the zero state, the SDU output pins identified in Table 5-36
function as combinational logic to indicate one of the four states shown in Table 5-37.
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Table 5-37.
Per Channel State Definition (MP11F=0)
CD1
CD2
Channel State
High1
High
On Hook
Low1
High
Call Initiated/Connected2
High
Low
Call Answered
Low
Low
Incoming Call
NOTES:
1.
“High” and “Low” (impedance ---- open--collector--type output) are as defined in ARINC 741 Part 1 Attachment 1--4
Note 10.
2.
Depending on the state of SDU system configuration pin TP10K, the state will transition on either call initiation or
call connection.
Z.
Strap Parity
(1) The interpretation of this configuration pin is given in Table 5-38.
Table 5-38.
MP11 Pin E
Strap Parity
Interpretation
SUM OF ALL STRAPS IS SET TO EVEN
SUM OF ALL STRAPS IS SET TO ODD
(2) This pin is set to the zero or one state to yield an even number of strapped pins
(MP11E to MP11K).
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SECTION 6
TESTING/FAULT ISOLATION
1. Overview
A. General
(1) This section defines the built-in test equipment (BITE) requirements for the MCS
system (i.e., SDU and HPA). Information supplied in this section describes how MCS
system failures are detected, recorded, and reported. See Figure 6-1 for an overview
of the BITE system communications.
(2) System BITE contributes to a number of maintenance functions:
•
•
•
•
Detection of internal and external failures
Storage of in-flight failure data
Reporting failure status in the air and on the ground
Ground test capability for isolating faulty LRUs, performance verification, and
system level testing.
Figure 6-1.
System BITE Communication
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B. Definitions
(1) Degraded Operation
(a) Degraded operation is defined as the condition when the MCS system is
operating with a failure that results in diminished capability (e.g., some, but not
all channel units available, or less than nominal HPA power available).
(2) Failure
(a) A failure is defined as a fault that persists for a predetermined amount of time or
for a predetermined number of samples. The tolerance on all failure timing
criteria is ± 0.5 second.
(3) Intermittent Failure
(a) An intermittent failure is defined as a fault that had been declared a failure,
recovered to its normal valid state, and then is declared to have failed again. A
failure occurrence counter is maintained for each entry in the LRU and system
failure logs to identify intermittent failures.
(4) Fault
(a) A fault is defined as the result of a measurement or comparison that does not
satisfy the test or monitoring result requirements. The test or monitoring result
requirements can require a time element.
(5) Reversion
(a) Reversion is defined as the system response to a failure condition that results in
continued system operation in the presence of the failure, and can result in
degraded system capability.
(6) MCS LRU
(a) The following are defined as the MCS LRUs (i.e., those manufactured by
Honeywell/Thales):
• SDU
• HPA
• HSU.
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C. Failure Detection and Reporting Levels
(1) Failures are detected in the MCS system by a wide variety of tests. The immediate
result of failure detection is usually diagnosis of the failure to a specific component or
functional circuit group, on a specific SRU, in a specific LRU. However, some
detected failures may only be able to be diagnosed to a suspect SRU, or only to a
suspect LRU, or only to a pair or group of LRUs and the physical or logical
interface(s) between them. Three enumerated levels of failure diagnosis are defined
in Table 6-1.
Table 6-1.
Level
Levels of Failure
Description
Level I
Diagnosis to the LRU level or its equivalent (e.g., a specific inactive bus, error, or
warning)
Level II
Diagnosis to the SRU (module or circuit card) level
Level III
Diagnosis to the component or functional circuit group level or equivalent (e.g., a
very specific error condition)
(2) All MCS LRUs implement Level I and, where possible, Level II failure detection. Level
I diagnosis primarily supports line maintenance. Front panel displays and automatic
reports to central fault/maintenance systems are only performed to Level I resolution
because they are primarily used to support line maintenance, which is typically limited
to LRU replacement. Level II and Level III diagnosis primarily support shop and
factory maintenance. Level II and Level III failure detection information is stored in
the LRU and system failure logs, and can be displayed on the commissioning and
maintenance terminal (CMT) pages.
D. LRU Coverage
(1) The LRU coverage is defined as the sum of all component failure rates covered by
the BITE circuitry within an LRU, divided by the total of the component failure rates
within that LRU. This coverage is greater than or equal to 0.95 as defined. The LRU
probability of false detection is defined as the sum of all component failure rates of
the BITE circuitry within an LRU divided by the total of the component failure rates
within that LRU. This coverage is greater than 0.01 as defined. The LRU coverage
includes the following:
• All SDU to avionic interfaces, where possible
• All MCS inter-LRU interfaces
• All power supply voltages
• All battery voltages
• All microprocessors/microcontrollers
• All memory devices (RAM, ROM, etc).
(2) All discrete drivers between the SDU and the avionics LRUs have over current
protection and open-circuit detection.
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E.
Monitoring and Testing Functions
(1) General
(a) The declaration of an inactive input bus takes precedence over declaration of
one or more data word failures against the LRU driving that bus (i.e., if the bus is
inactive, additional logging and reporting of low-rate failures of individual data
words on that bus are precluded). The failure and recovery criteria is set to make
sure individual data word failures are not declared when the bus is inactive. This
is typically done by setting inactive bus failure criteria (e.g., three seconds) to be
faster than word update rate failure criteria (e.g., five seconds), and inactive bus
recovery criteria (e.g., two seconds) to be longer than word update rate recovery
criteria (e.g., one second).
(b) Unless an LRU providing ARINC 429 data declares itself to have failed, a fault is
declared against that LRU when the ARINC 429 data is faulty. This is determined
by checking (as appropriate for each word) for data inconsistencies, data
out-of-range, uses of undefined or reserved values, and occurrences of the
failure warning state in the sign/status matrix (SSM) field.
(c) Two basic types of failure detection testing performed are: functional tests and
continuous monitoring (CM). The purpose of functional testing in the form of
power-on self test and person-activated self test is to exercise the equipment in a
manner as closely as possible to its normal operation. Failures detected during
functional testing are declared to be current failures until a subsequent functional
test shows the failure condition has recovered.
(d) The purpose of continuous monitoring is to test the equipment in a nondisruptive
manner while it is performing its normal operations. Such testing usually includes
monitoring the power supply voltages, temperature sensors, bias currents, input
bus activity, buffer overflow, input data failures, etc. This testing can also include
abnormal failures that cannot be tested as part of the functional testing, such as
protocol failures, processor instruction traps, data loader problems, etc.
(2) Power-On Self-Test
(a) General
The power-on self-test (POST) is a series of functional tests for individual
LRUs; each MCS LRU performs its own internal POST upon a cold start. A
cold start is defined as the response of an LRU where no retention of any
previously stored information in any volatile memory is assumed. The power
supply provides signals to help an orderly power-down and power-up
process for the LRU during power interrupts of any length. Primary power
interrupts of less than 5 milliseconds duration have no effect on system
operation. For primary power interrupts longer than 5 milliseconds and up to
200 milliseconds duration, the LRU maintains normal operation, except the
RF transmit and receive processes do not need to be supported in any LRU
during this interval. For primary power interrupts greater than 200
milliseconds duration that causes normal operation to cease, the LRU
performs a cold start following restoration of primary power.
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The POST sequence of tests does not terminate when an out-of-tolerance
condition is encountered. Instead, the sequence continues to complete as
many tests as possible to record all available information regarding existing
failures. An individual LRU that successfully passes POST is declared to be
fully functional. POST must take into account failures detected by
continuous monitoring (i.e., if POST passes, but testing unique to
continuous monitoring has detected and logged a current failure, then the
POST result is logged as a failure).
After executing its own POST, the SDU commands a system-wide functional
test of the HPA(s), HSU and ACU/BSU(s) (including the HGAs, HGA
diplexer/LNA, and HPR) as applicable for the installed equipment in
accordance with the system configuration pins (see MECHANICAL
INSTALLATION). The SDU then processes the results of the functional tests
from these LRUs. The SDU commands the functional test as follows
through:
• BIT request in the HSU command word
• SSM field of the HPA command word(s) for the HPA
• SSM field(s) for the ACU/BSU control word(s) for the ACU/BSU(s).
The BITE status from the LGA diplexer/LNA is continuously sent to the SDU,
with no functional test command necessary or possible. Test results from the
HGA(s), HGA diplexer/LNA, and HPR are reported by the ACU/BSU(s).
The SDU allows up to 30 ± 1 seconds for other system LRUs, except the
HSU, which is allowed 60 ± 1 seconds to report their POST results following
initiation of a system-wide functional test. If an LRU fails to report its
functional test results within this time period, but otherwise meets the ARINC
429 bus communication rate requirements, the SDU considers that LRU to
have failed. If no ARINC 429 bus communication is received on a particular
bus, the SDU considers that bus to be inactive.
(b) Test Initiation
The correct operation of much of the internal circuitry of the SDU depends
on clocks derived from the high-stability frequency reference generated by
the oven-controlled crystal oscillator (OCXO). Therefore, it is inappropriate to
perform BITE tests until this clock frequency has achieved gross stability. If
the SDU is powered on after having stabilized at a cold external temperature
(e.g., --55° C), it can take several tens of seconds for the frequency drift rate
to be low enough before the phase locked oscillators (PLO) that derive the
dependent clocks can lock onto the OCXO frequency reference.
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The SDU defers testing of sensitive equipment until a positive indication of
settling is detected, or sufficient time passes so the lack of settling itself can
be classified as a failure. Deferral of these sections of POST also result in
normal operation being deferred, including access to the user interfaces
(SCDU, CFDS, and CMT) and all automatic calibration processing.
Consequently, the SDU suspends POST until the SDU detects the first of
the following conditions:
• OCXO heater monitor indicates it has achieved operating temperature.
• Power supply unit (PSU) temperature sensor indicates a reading above
25 °C.
• Channel filter module transmit and receive PLO lock detectors both
indicate that lock has been achieved.
• More than 4 minutes have elapsed since primary power was applied.
(c) LRU Front Panel LED and Alphanumeric Display Tests
A test of the HPA and HSU front panel LEDs is performed as a part of each
POST. At a minimum, this is made up of flashing the LEDs on and off. The
LED flashing continues until POST is completed or for 3 ± 0.5 seconds.
During the test, the SDU tests its alphanumeric display by incorporating one
or more occurrences of the word TESTING into its display sequence to
make sure all display elements are tested.
(d) RF Loop Back Tests
As part of the system-wide POST, the SDU implements a RF loop back test.
The RF loop back occurs in the radio frequency module (RFM) installed in
the SDU.
The SDU delays initiating the RF loop back test until it receives an indication
the RF loop back has been activated. If the SDU fails to receive a valid
indication within 30 seconds following the RF loop back request, then the
SDU completes its POST without executing the RF loop back test. The SDU
cancels the RF loop back request when the loop back test is completed, or if
the 30 second timer expires while waiting for verification of an active RF loop
back.
(3) Person-Activated Self-Test
(a) The person-activated self-test (PAST) performs the same functions as POST.
PAST is initiated in the HPA and the HSU by pushing the PUSH-TO-TEST (PTT)
switch on the respective LRU front panel. PAST can also be initiated any time
through:
• Respective CMT interface to the LRU
• SSM field of the HPA command word sent to the HPA from the SDU
• BIT request in HSU command word sent to the HSU from the SDU.
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(b) A stuck switch on the CMT or LRU front panel does not cause PAST to remain
active. Any switch activity is ignored while PAST (or POST) is executing.
(c) The HPA and HSU inhibit PAST while the aircraft is airborne, except when PAST
is initiated through the CMT, which is permitted at any time. The HPA and HSU
cannot properly function if not receiving valid command words from the SDU
containing the air/ground status and command information. Under these
conditions, the HPA and HSU are not usable by the SDU. PAST is only permitted
while the aircraft is on the ground, or when the airborne/on-ground status is
unknown. In lieu of the airborne/on-ground status information from the SDU, the
HPA and HSU permit PAST as though the aircraft is on the ground.
(d) A system-wide PAST is initiated in the SDU when commanded by:
• Entry through the SATCOM control and display unit (SCDU)
• Entry through the central maintenance computer (CMC)
• Entry through the central fault display system (CFDS)
• Command from the CMT
• Activating the PTT switch (SDU TEST) on the front panel.
(e) A stuck switch on the SDU front panel does not cause PAST to remain active.
Any switch activity is ignored while PAST (or POST) is executing.
(4) Continuous Monitoring
(a) Continuous monitoring (CM) of the BITE circuitry does not interfere with the
normal operation of the system. Instead any failure condition is recorded and
reported. Continuous monitoring operates as a background task at all times,
even during functional testing. Functional test failure codes that are identical to
the continuous monitoring codes (except for the MSB of the level 3 code)
indicate cases where the functional test differs in some way from the companion
CM test. Those CM failures detected during functional testing (e.g., maintenance
and status word failures) are logged as CM failures, not functional failures.
F.
Failure Recording
(1) The SDU records CFDS internal failures at all times. The SDU only records CFDS
external failures while receiving a valid All Call DC1 Command if a Douglas or Airbus
CFDS is installed. Internal failures are defined as those internal to the SATCOM
subsystem. External failures are defined as those external to the SATCOM
subsystem. If a Boeing CMC (or no CFDS) is installed or if valid DC commands are
not available, then the air/ground status is used to generate pseudo DC states of
DC0 (aircraft on-ground) and DC1 (aircraft airborne).
(2) The HPA records internal failures at all times. The HPA only records external failures
while the aircraft is airborne, based on the status of the weight-on-wheels discrete
(on-ground vs. airborne). Internal failures are defined as those that have the same
Level I code as the LRU recording the failure (i.e., 01 for the SDU, 04 for the HGA
HPA, and 07 for the LGA HPA). External failures are defined as those failures not
having the same level 1 code as the LRU recording the failure.
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(3) The HPA and HSU store their functional test and CM failure records in nonvolatile
memory designated as the LRU failure memory log. Each LRU failure memory log is
capable of being interrogated and cleared. The SDU contains a nonvolatile memory
that serves as a system failure memory log. Functional test results supplied by the
HSU, HPA(s), ACU/BSU(s), LGA diplexer/LNA, and the SDU itself are recorded in
this system failure memory log. The system failure memory log is capable of being
interrogated and cleared for each LRU individually. Each LRU failure memory log and
the system failure memory log is capable of recording at least 1000 failures.
(4) The HPA, HSU and other system LRUs supply failure information to the SDU for
storage in the system failure memory log. In the absence of any detected failures
during a flight leg, the SDU records the flight leg counter, flight number, ICAO
address, date, and Greenwich Mean Time (GMT) at the flight leg transition. The SDU
also records the aircraft identification for display on the SCDU and CFDS
maintenance pages.
(5) Class -- The SDU declares and stores the classification (Airbus/Douglas CFDS) of
failure (one, two, three) for each entry in this field.
• Class 1 failures are indicated in flight to the crew by the CFDS because they have
operational consequences for the current or next flight(s).
• Class 2 failures are not automatically indicated in flight to the crew by the CFDS
because they have no operational consequences for the current or next flight(s),
but are indicated to the crew on the ground because they cannot be left
uncorrected until the next routine scheduled maintenance check.
• Class 3 failures are not indicated to the flight crew because they can be left
uncorrected until a routine scheduled maintenance check. An accumulation of
Class 3 failures can lead to a Class 2 or Class 1 failure.
• Aircraft Identification -- The aircraft identification (i.e., the tail number) is made up
of nine alphanumeric characters. The SDU obtains the aircraft identification from
the CMC or CFDS through ARINC labels 301, 302, and 303 (if available).
G. Failure Reporting
(1) General
(a) Active failures include those internal and external failures deemed to be currently
failing while the aircraft is on the ground or airborne. Unlike failure recording that
excludes recording external failures while on the ground, failure reporting has its
own set of criteria as specified in the following paragraphs.
(2) HPA Failure Reporting
(a) General
The HPA reports its functional test/CM failure status by lighting its front panel
LEDs, and through communication to the SDU.
(b) HPA Front Panel Indicators and Controls
The HPA indicators and controls are given in Table 6-2.
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Table 6-2.
HPA Indicators/Controls
Indicator/Control
Description
PASS LED
Shows green after a test, if no failures are detected in the HPA
FAIL LED
Shows red after a test, if failures are detected in the HPA
PUSH--TO--TEST (PTT)
Push this button to start a test of the HPA
(c) HPA Front Panel LEDs
Functional testing effectively controls the on/off state of the front panel LEDs
during the period beginning with initiation of the functional testing
(POST/PAST), through execution of the functional test sequences (including
LED testing), and up to and including the indication of the test results on the
LEDs. Continuous monitoring exclusively controls the LEDs at all other
times.
The green LED (PASS) lights for 30 ± 5 seconds at the conclusion of the
functional test sequences if both of the following are true:
• The HPA determines there are no currently active CM failures having its
own Level I code (i.e., 04 or 07, as applicable)
• No functional test failures have been detected with its own Level I code.
There must be no known failures in order to light the green LED as the
functional test indication.
The red LED (FAIL) lights continuously during the functional test indication
phase and through the transition to the CM indication phase, if the HPA
detects at least one currently active CM failure with its own Level I code. If
the HPA detects only functional test failures (i.e., no CM failures are
currently active), the red LED lights for 30 ± 5 seconds and is then turned
off.
The red LED also lights as long as the failure persists, if the HPA detects
any CM failure that has its own Level I code while continuous monitoring is
controlling the LEDs. Otherwise, both LEDs are turned off. Continuous
monitoring itself never causes the green LED to light. The presence or
absence of functional test failures does not affect the CM indication.
(d) HPA-SDU Communication
The HPA communicates its functional testing/CM failure status to the SDU
through the HPA maintenance and status words. The HPA only indicates a
FW SSM state in its maintenance and status words, and active discrete
failure bits in its maintenance word. Since no failures unique to functional
testing activate the SSM FW state or the discrete failure bits in the
maintenance word, no functional test failures need to be latched until the
next functional testing sequence.
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For certain failures detected during continuous monitoring, the appropriate
discrete failure bits and the SSM FW state are set within the maintenance
and status words as long as the failure persists.
(3) HSU Failure Reporting
(a) General
The HSU reports its functional test/CM failure status by lighting its front
panel LEDs, and through communication to the SDU.
(b) HSU Front Panel Indicators and Controls
The HSU indicators and controls are given in Table 6-3.
Table 6-3.
Indicator/Control
HSU Indicators/Controls
Description
PASS LED
Shows green after a test, if no failures are detected in the HSU
FAIL LED
Shows red after a test, if failures are detected in the HSU
PUSH--TO--TEST (PTT)
Push this button to start a test of the HSU
(c) HSU Front Panel LEDs
Functional testing effectively controls the on/off state of the front panel LEDs
during the period beginning with initiation of the functional testing
(POST/PAST), through execution of the functional test sequences (including
LED testing), and up to and including the indication of the test results on the
LEDs. Continuous monitoring exclusively controls the LEDs at all other
times.
The green LED (PASS) lights for 30 ± 5 seconds at the conclusion of the
functional test sequences if both of the following are true:
• The HSU determines there are no currently active CM failures having its
own Level I code (i.e., 03)
• No functional test failures have been detected with its own Level I code.
There must be no known failures in order to light the green LED as the
functional test indication.
The red LED (FAIL) lights continuously during the functional test indication
phase and through the transition to the CM indication phase, if the HSU
detects at least one currently active CM failure with its own Level I code. If
the HSU detects only functional test failures (i.e., no CM failures are
currently active), the red LED lights for 30 ± 5 seconds and is then turned
off.
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The red LED also lights as long as the failure persists, if the HSU detects
any CM failure that has its own Level I code while continuous monitoring is
controlling the LEDs. Otherwise, both LEDs are turned off. Continuous
monitoring itself never causes the green LED to light. The presence or
absence of functional test failures does not affect the CM indication.
(d) HSU-SDU Communication
The HSU communicates its functional testing/CM failure status to the SDU
through the HSU status word. The HSU indicates a FW SSM state in its
status word, when failures are present that prevent it from offering HSD
service.
For certain failures detected during continuous monitoring, the appropriate
discrete failure bits and the SSM FW state are set within the maintenance
and status words as long as the failure persists.
(4) SDU Failure Reporting
(a) General
The SDU reports its functional testing/CM failure status and all other system
LRUs by:
• Activating its alphanumeric display
• Communicating to the SCDU, CMC, CFDS, and CMT interfaces.
The alphanumeric display indicates all applicable failure conditions with no
regard to:
• Any type of internal/external failure differentiation
• Any CFDS failure class distinctions
• Which LRU detected a failure (either the SDU itself or one of the reporting
LRUs in the SATCOM subsystem).
The SDU delays reporting the results of the functional test sequence for a
period of 5 seconds. This gives continuous monitoring the opportunity to
perform its unique tests during the delay period, and include any current CM
failures in the test report. The SDU takes a snapshot at the end of the
functional test delay period to include all currently active CM failures in
addition to all failures detected during functional testing. The functional test
delay period applies to the SDU alphanumeric display, the SCDU
maintenance pages, the CFDS pages, and the CAIMS and CMC fault
summary words, but not to the CMT.
(b) SDU Front Panel Indicators and Controls
The SDU indicators and controls are given in Table 6-4.
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Table 6-4.
SDU Indicators/Controls
Description
Indicator/Control
SDU TEST
Push this button to initiate a system--wide SATCOM test
SYSTEM STATUS DISPLAY
Shows data defining the SATCOM system configuration and the
identification of all SATCOM components that are not operating as required
MANUAL SCROLL
Push this button to scroll through the messages on the system status
display
(c) Front Panel Alphanumeric Display and MANUAL SCROLL Button
General
The alphanumeric display makes it easy for the maintenance personnel
to identify which system LRU has failed. The alphanumeric display is
blank unless specifically activated for temporary display of failure
messages and other status information. The alphanumeric display is
also kept blank under conditions of extreme temperatures. The display
is not intended to be started when its temperature is less than --5 °C, or
greater than +30 °C. The alphanumeric display is started during the LED
test portion of the functional test sequence. After the functional test
delay period, and any time during continuous monitoring, the
alphanumeric display can be started by pushing the MANUAL SCROLL
button.
The operator can scroll the alphanumeric display through the entire
applicable message sequence by repeatedly pushing the MANUAL
SCROLL button within 30  5 seconds after the display is started. One
left-justified 20-character (or less) message is displayed each time the
MANUAL SCROLL button is pushed. When the end of the display
sequence is reached (i.e., END OF LIST), the next actuation of the
MANUAL SCROLL button returns the alphanumeric display to the top of
the display sequence, enabling the operator to scroll through the
sequence again. Message scrolling is performed according to the
following sequence:
• One of four possible system/SDU pass/fail messages
• All applicable Level I failure messages
• LRU part number messages (up to four lines)
• ORT identification message
• END OF LIST message.
If the MANUAL SCROLL button is inactivate for 30 ± 5 seconds at any
point during the display sequence, the alphanumeric display is blanked
and any display sequence in progress is aborted. At the same time, one
or both of the front panel LEDs (as appropriate) are turned off if they
were exclusively indicating functional test failures with no current CM
failures.
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SYSTEM/SDU PASS/FAIL Message
This one-line message, which summarizes the overall functional test or
CM status, takes on one of four possible states:
• SDU PASS
SYS PASS
• SDU PASS
SYS FAIL
• SDU FAIL
SYS PASS
• SDU FAIL
SYS FAIL.
Level I Failure Messages
This section lists all the applicable Level I failure messages that can be
displayed on the alphanumeric display, along with the appropriate LRU
or control bus input. These messages are listed in failure code order in
Table 6-5. For the functional test display, the message list includes all
the active failures in the snapshot and the list is static.
For continuous monitoring, the message list includes all currently active
CM failures. The presence or absence of functional test failures does
not affect the CM message list. The failure message list for the CM
display is potentially dynamic.
During continuous monitoring, if a new CM failure becomes active
during the scroll sequence, the respective message appears at its
proper location in the sequence according to its Level I code. This
occurs either during the current scroll sequence if that Level I code has
not yet been reached, or during the next scroll sequence if the failure is
still active. If a CM failure recovers during a scroll sequence, its
message does not appear in any subsequent scroll sequence, even if it
had appeared earlier. If a CM failure recovers while its particular
message is currently being displayed, the message continues to be
displayed until the MANUAL SCROLL button is activated or until the
time-out period expires.
Table 6-5.
Level 1
Code
Level 1 Failure Messages
Failure Message
Description
AES LRU Failures:
00
(not applicable)
Unknown Level I failure
01
SDU
SDU failed
02
OTHER SDU
Other SDU (of a dual system) failed
03
HSU
HSU failed
04
HPA--HI GAIN
High Gain Antenna HPA failed
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Table 6-5.
Level 1
Code
Level 1 Failure Messages (cont)
Failure Message
Description
07
HPA--LO GAIN
Low Gain Antenna HPA failed
0A
HI POWER RELAY
HPR (antenna system) failed
0D
DLNA--(TOP/L)
Top/Port Diplexer/Low Noise Amplifier failed
0F
DLNA--R
Starboard Diplexer/Low Noise Amplifier failed
10
DLNA--LO GAIN
LGA Diplexer/Low Noise Amplifier failed
13
BSU--(TOP/L)
Top/Port BSU or ACU failed
15
BSU--R
Starboard BSU failed
1A
HI GAIN ANT--(TOP/L)
Top/Port HGA failed
1C
HI GAIN ANTENNA--R
Starboard HGA failed
1F
LO GAIN ANTENNA
LGA failed
21
SCDU1 or WSC1
No. 1 SCDU or WSC failed
22
SCDU2 or WSC2
No. 2 SCDU or WSC failed
23
SCDU3 or WSC3
No. 3 SCDU or WSC failed
Non-AES LRU Failures:
33
(ACARS MU/CMU)1
No. 1 AFIS/ACARS unit failed
34
(ACARS MU/CMU)2
No. 2 AFIS/ACARS unit failed
35
IRS--PRI
Primary IRS failed
36
IRS--SEC
Secondary IRS failed
39
(CFDIU/CMC)
CFDS/CMC failed
3D
FMC1
No. 1 FMC failed
3E
FMC2
No. 2 FMC failed
40
ARINC 429 ICAO ADDR
429 ICAO address source failed
41
(not applicable)
Discrete cockpit indicators failed
42
CTU
Cabin telecommunications unit failed
43
(CFS/CPDF)
Cabin file server/cabin packet data function failed
Inactive BITE Bus Input to SDU from other LRU:
50
HSU/SDU
HSU bus
52
(CFS/CPDF)/SDU
Cabin file server/cabin packet data function bus
53
(ACARS MU/CMU)1/SDU
No. 1 AFIS/ACARS unit bus
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Table 6-5.
Level 1
Code
Level 1 Failure Messages (cont)
Failure Message
Description
54
CTU/SDU
CEPT--E1 bus from the CCS
55
SCDU1/SDU or
WSC1/SDU
No. 1 SCDU or WSC bus
56
SCDU2/SDU or
WSC2/SDU
No. 2 SCDU or WSC bus
57
(ACARS MU/CMU)2/SDU
No. 2 AFIS/ACARS unit bus
59
(CFDIU/CMC)/SDU
CFDS bus
5A
IRS--PRI/SDU
Primary IRS bus
5B
IRS--SEC/SDU
Secondary IRS bus
5C
HPA--HI GAIN/SDU
High Gain Antenna HPA bus
5F
HPA--LO GAIN/SDU
Low Gain Antenna HPA bus
62
BSU--(TOP/L)/SDU
Top/port BSU bus
64
BSU--R/SDU
Starboard BSU bus
65
(not applicable)
Radio Management Panel bus
66
SCDU3/SDU or
WSC3/SDU
No. 3 SCDU or WSC bus
71
OTHER SDU/THIS SDU
Bus from other SDU in a dual system
73
FMC1/SDU
No. 1 FMC bus
74
FMC2/SDU
No. 2 FMC bus
Inactive Bus Inputs to other LRU:
90
SDU M--CTRL/HPA--HI
Multicontrol bus to HGA HPA from SDU
96
SDU M--CTRL/HPA--LO
Multicontrol bus to LGA HPA from SDU
98
SDU M--CTRL/BSU--(T/L)
Multicontrol bus to top/port BSU from SDU
9A
BSU--R XTALK/BSU--L
Crosstalk bus to port BSU from starboard BSU
9C
SDU M--CTRL/BSU--R
Multicontrol bus to starboard BSU from SDU
9D
BSU--L XTALK/BSU--R
Crosstalk bus to starboard BSU from port BSU
9E
SDU/HSU
Control bus to HSU from SDU
A1
SDU/WSC1
Bus to WSC1 from SDU
A2
SDU/WSC2
Bus to WSC2 from SDU
A3
SDU/WSC3
Bus to WSC3 from SDU
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Table 6-5.
Level 1
Code
Level 1 Failure Messages (cont)
Failure Message
Description
Miscellaneous Failures:
A6
HSU ETHERNET PORT 1
No activity on HSU Ethernet port 1
A7
HSU ETHERNET PORT 2
No activity on HSU Ethernet port 2
C0
WRG:STRAPS/SDU
System configuration pins error
C1
WOW1/WOW2/SDU
Weight on wheels discrete inputs disagree
C2
SDU DUAL SEL/DISABLE
Dual system discrete inputs disagree
C3
WRG:ICAO ADDR/SDU
ICAO address straps error
C4
TX PATH VSWR--HI GAIN
Excessive VSWR load at HGA HPA output
C5
WRG:STRAPS/SDU ORT
Configuration pins and ORT settings disagree
C6
TX PATH VSWR--LO GAIN Excessive VSWR load at LGA HPA output
C7
HPA--HI GAIN
OVERTEMP
Over temperature in HGA HPA
C8
BAD GROUND STATION
Invalid GES frequency command
C9
HPA--LO GAIN
OVERTEMP
Over temperature in LGA HPA
CA
SDU/DLNA--LO GAIN
LGA LNA control driver SDU
CB
WRG:SDI/HPA--HI GAIN
(see NOTE)
HGA HPA identification strapped incorrectly
CC
WRG:SDI/HPA--LO GAIN
(see NOTE)
LGA HPA identification strapped incorrectly
CD
SDU (POC/TOTC)
SDU power-on counter or total-on-time counter has been reset
CF
HPA--HI (POC/TOTC)
HGA HPA power-on counter or total-on-time counter has been
reset
D0
HPA--LO (POC/TOTC)
LGA HPA power-on counter or total-on-time counter has been
reset
D1
WRG:SDI/HPA--HI GAIN
(see NOTE)
HGA HPA identification strapped incorrectly
D2
WRG:SDI/HPA--LO GAIN
(see NOTE)
LGA HPA identification strapped incorrectly
D3
WRG:SDI/BSU--(T/L)
Top/Port BSU identification strapped incorrectly
D4
WRG:SDI/BSU--R
Starboard BSU identification strapped incorrectly
D5
HPA--HI GAIN COAX
HGA HPA input coax cable
D6
HPA--LO GAIN COAX
LGA HPA input coax cable
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Table 6-5.
Level 1
Code
Level 1 Failure Messages (cont)
Failure Message
Description
D8
DLNA/(SDU)--(T/L)
Top/Port HGA LNA coax cable output to HSU or SDU
D9
DLNA/(SDU)--R
Starboard HGA LNA coax cable output to HSU or SDU
DA
DLNA/(SDU)--LO GN
LGA LNA coax cable output to HSU or SDU
DB
LO GAIN SUBSYSTEM
LGA log--on functional test failure or could not initiate test
DC
NO ACTIVE MU/CMU
At least one (C)MU is communicating, but none have declared
themselves active
DD
SDU OWNER
REQS--SECD
Error in the secured ORT partition
DE
SDU OWNER
REQS--USER
Error in the user ORT partition
DF
HI GAIN SUBSYSTEM
Slave HGA log--on functional test failure or could not initiate test
E1
BAD HSU DISABLE DISC
HSU disable discrete from SDU not functioning
E4
BAD HSU/SDU I/F VER
Incompatible interface between HSU and SDU
E6
HSU/HPA TX RF PATH
HSU to HPA coax cable
E8
DLNA/HSU RX RF PATH
DLNA to HSU coax cable
EC
WRG:STRAPS/HSU
HSU configuration pins error
ED
WRG:STRAPS/HSU ORT
HSU configuration pins and SDU ORT settings disagree
EE
WRG:FWD ID/HSU
HSU forward ID straps error
Undefined:
Others
LEVEL 1 FAULT XX
XX is the Level 1 failure code (undefined)
NOTE: The front panel display messages associated with failure codes CBx and CCx (WRG:SDI/HPA HI--GAIN and
WRG:SDI/HPA LO--GAIN, respectively) are identical to the messages raised for failure codes D1x and D2x,
respectively. This use of a single front panel display message for multiple failure codes (where the CB/CCx
codes reflect detection by the HGA/LGA HPA of an invalid HPA SDI strap condition, while the D1/D2x codes are
generated by the SDU in response to a report from the HGA/LGA HPA of having detected an unexpected SDI
code) is deliberate, and results from alignment of the front panel display messages with their CFDS/CMC
counterparts. Because of this approach, it is possible (in this specific case) for an operator to receive two
consecutive front panel display messages that are the same.
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LRU Identification (Part Numbers) Electronically
Following the display of all Level I failure messages, a list of the
available LRU end-item part numbers is displayed. This list only includes
part numbers for those LRUs present in the given installation as defined
by the system configuration pins (see MECHANICAL INSTALLATION).
For an installed LRU whose end-item part number is not available,
dashes are displayed in place of the part number (e.g., HPL _ _ _ _ _ _
_ _ _ _ _). The list of part numbers are displayed in the order given in
Table 6-6.
Table 6-6.
List of Part Numbers
LRU
Part No.
SDU
SDU bbbbbbb--hhsss--nn
HGA HPA
HPH bbbbbbb--hhsss--nn
LGA HPA
HPL bbbbbbb--hhsss--nn
HSU
HSU bbbbbbb--hhsss--nn
NOTES:
1.
bbbbbbb represents the seven-digit LRU end-item base part number.
2.
hh represents the two-digit LRU end-item hardware configuration number.
3.
sss represents the three-digit LRU end-item software configuration number.
4.
nn represents the two-character LRU end-item software modification level (possibly including space, dash
characters, and alpha characters).
For the SDU, the two-digit LRU hardware configuration number must be
entered manually through the CMT interface for valid data to be
available for display. This data is stored during LRU end-item testing. All
other numbers reside within the LRU software. All numbers are
communicated to the SDU by Honeywell/Thales HSU and HPA(s)
through the part number block transfer. For non-Honeywell/Thales
interfacing HPAs, no such data is available to the SDU, therefore,
dashes are displayed for the HPA end-item part number.
ICAO Aircraft Address
Following the display of the LRU End Item part numbers, the ICAO
aircraft address is displayed in octal and hexadecimal formats as shown
below:
ICAO--XXXXXXXX YYYYYY
Where “XXXXXXXX” represents the octal format and “YYYYYY”
represents the hexadecimal format. If the ICAO is provided from an
ARINC 429 source, as determined by the state of configuration pin
TP10A, and a valid ICAO has not been received, the octal and
hexadecimal values are replaced with dashes.
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HSD Channel ISN
Following the display of the ICAO aircraft address, the Inmarsat Serial
Number (ISN) for each installed HSD channel is displayed as shown
below:
ISNX: YYYYYY ZZZZZZ
Where “X” is a decimal number from 1 to 4 used to distinguish multiple
ISNs, and where “YYYYYY” represents the Type Approval ID and
“ZZZZZZ” the Forward ID. The ISNs for each installed HSD channel are
displayed on a separate line. If the ISN for an installed HSD channel is
not available, dashes are displayed in place of the Type Approval ID
and the Forward ID.
ORT Identification
Following the display of the ISNs, if one or more HSD channels are
installed, or after the ICAO, if no HSD channels are installed, the user
ORT identification is displayed as specified:
• ORT ID--XXXXXXXXXXXXX (first line)
• XXXXXXXXXXX--MODIFIED (second line, after another activation of
the MANUAL SCROLL button).
Where XXXXXXXXXXXXXXXXXXXXXXXX represents the 24-character
description contained in the user ORT description field. The user ORT
description field is used to annotate a particular set of ORT items to
identify one from another (e.g., NORTH PACIFIC ROUTE, SOUTH
ATLANTIC ROUTE, 747--400 ASIAN ROUTE, 777 ASIAN ROUTE).
Alternatively, this item could contain a software identification (e.g., a
software part number for the user ORT as a released entity).
The MODIFIED flag is only displayed if the state of the user ORT
modified flag indicates any item in the user ORT has been modified
since the user ORT was created. When any user ORT item is modified
by the SDU software, either directly or indirectly, the user ORT modified
flag is set to MODIFIED. If the state of the user ORT modified flag is
unmodified, the MODIFIED flag is not displayed. The state of the user
ORT modified flag is never set to unmodified by the SDU software.
The next two pushes of the MANUAL SCROLL button present the same
information for the Secured ORT partition.
SDU Temperature
Following the display of the ORT Identification, the SDU temperature is
displayed as shown below:
SDU TEMP (--)XXXC
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Where “XXX” represents the numeric display of the actual SDU
temperature in degrees Celsius, with a (--) sign or space as appropriate
for negative and positive values. The “XXX” field will have leading zeros
replaced by spaces.
End Of List Message
The END OF LIST message is displayed at the end of the display list
after the ORT identification.
H. Miscellaneous BITE Requirements
(1) The typical retention period for the BITE memory is at least five years at 25 °C. The
worst case retention period is at least one year at 50 °C. If batteries are used to
supply backup power for the BITE memory, the typical battery lifetime should be at
least 10 years at 25 °C. The worst case lifetime is at least two years at 50 °C.
(2) Each system LRU has a total on-time clock (TOTC) to accumulate and record the
amount of time the LRU has been powered up. The TOTC has a 10 minute
resolution, and is capable of accumulating and recording a count of at least 200,000
hours.
(3) The TOTC value is capable of being examined, and of being reset to 0:00 through
the CMT. Any manual TOTC reset, or any automatic TOTC reset (e.g., upon
detection of corruption of its value), results in an automatic entry of the event into the
LRU failure memory log and the SDU system failure memory log. The TOTC hours
are capable of being automatically entered into the LRUs maintenance activity log.
I.
Maintenance Activity Log
(1) A maintenance activity log is stored in each system LRU. The maintenance activity
log is made up of the six most recent maintenance activity records (MAR). Each MAR
can be entered through the CMT. Information is stored in the MAR as shown in
Table 6-7 and in the order listed.
Table 6-7.
Field
MAR Information
Size
Range
Document Number
16 ASCII Characters
a--z, A--Z, 0--9
Date (yymmdd)
6 ASCII Numerics
yy 00--99
mm 01--12
dd 01--31
Location
32 ASCII Characters
a--z, A--Z, 0--9
Phone Number
18 ASCII Numerics
0--9
Total On-Time Clock (Hours)
6 ASCII Numerics
0--200,000
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(2) The fields are defined as follows:
• Document number -- The document number has up to 16 alphanumeric
characters. The intent of this field is to supply maintenance activity traceability.
• Date field -- The date field is made up of six numeric characters in the format of
yymmdd, where yy represents the year, mm represents the month, and dd
represents the day. This field is entered automatically by the SDU as determined
by its internal real-time clock (RTC); it is entered manually for the HPA. The intent
of this field is to record the date the maintenance activity was performed.
• Location field -- The location field has up to 32 alphanumeric characters. The
intent of this field is to indicate the place where the LRU maintenance service was
performed.
• Phone number field -- The phone number field is made up of 18 numeric
characters. The intent of this field is to supply a phone number of who performed
the LRU maintenance. This phone number should include the combination of
country code, area code, and local phone number.
• Total on-time clock field -- The TOTC field is made up of six numeric characters
representing hours. This field is entered automatically by the LRU as determined
by the internal TOTC.
2. SATCOM Control and Display Unit
A. General
(1) The SATCOM Control and Display Unit (SCDU) menu formats obey the accepted
industry standards for multifunction (multipurpose) control and display units (MCDU).
The following paragraphs describe the SCDU display layout and terminology used to
describe the display, font size conventions, scratchpad usage, format, keyboard
usage, display symbols, and update rates.
B. SCDU Display Terminology and Basic Operation
(1) General
(a) The SCDU display is made up of 14 lines of 24 characters. The top line (line 1) is
referred to as the title line and the bottom line (line 14) is referred to as the
scratchpad. Lines 2 thru 13 are arranged into six pairs having a label line and
data line. The SDU communicates to the SCDU for all data to be displayed in
green. The color displayed on the MCDU depends on how the MCDU responds
to this communication.
(b) There are six line select (LS) keys on each side of the SCDU display designated
left (L) and right (R) and numbered 1 to 6 from top to bottom. The LS keys are
associated with a pair of display lines where the upper line of a pair is the label
line and the lower line is the data line. The LS key/line pair relations are given in
Table 6-8.
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(c) The SCDU can display a large and small font size. Different character fonts are
not shown in the example SCDU page figures given in this section. The use of
large font is indicated by the presence of uppercase letters in the SCDU page
figures, while the use of small fonts are demonstrated by lowercase letters. In
general, page names displayed in the title line are in large font. For pages where
p/t is specified to be displayed in the title line, the p/t is in small font. Data
entered into the scratchpad is displayed in large font. Data in the label lines is
displayed in small font, while data in the data lines is displayed in large font.
Numerical character font sizes cannot be shown in the figures, but their font
sizes follow the same conventions.
Table 6-8.
LS Key/Line Pair Relations
LS Keys
Display Lines
1L -- 1R
2 and 3
2L -- 2R
4 and 5
3L -- 3R
6 and 7
4L -- 4R
8 and 9
5L -- 5R
10 and 11
6L -- 6R
12 and 13
(d) Labels on the left side of the SCDU display are displayed beginning in column 2
of the label line. Data on the left side is left-justified in the data line. Labels and
data on the right side of the SCDU display is right-justified. This is the case
unless specified otherwise.
(2) Scratchpad
(a) General
The scratchpad is used for data entry and displaying SDU generated
messages. Pushing an alphanumeric key on the keypad (0 through 9, A
through Z, +/-- [plus or minus], / [slash, space]) enters that character into the
scratchpad. The scratchpad is not used for fixed format display purposes.
The mechanism used for data entry is described below.
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(b) Data Entry
When the user types the appropriate characters using the SCDU keypad,
the characters are echoed on the scratchpad. After data entry, the user must
push the appropriate LS key adjacent to the data field where the data is to
be displayed. The SDU then checks the data for format and acceptability
(out-of-range, entry not permitted into the field, etc). If the data is incorrect,
the SDU leaves the previous data in the field and displays the appropriate
error message in the scratchpad. If any LS key is pushed adjacent to a
blank or nonselectable field, the scratchpad message 1 (i.e., NOT
ALLOWED) is issued. If the entry was rejected because an incorrect LS key
was pushed, the entry is accepted if the correct LS key is subsequently
pushed.
(c) Scratchpad Message
If the SDU determines a data entry does not conform to format or
acceptability requirements after an entry is attempted, the SDU issues a
scratchpad message prompting the user for the correct data. The user can
clear a scratchpad message by using the clear (CLR) key, or by entering
data into the scratchpad over the message.
(d) CLR and DEL Keys
General
The CLR and delete (DEL) keys are used to clear the scratchpad and
alter the data fields. Generally, for MCDUs that have only a CLR key
(e.g., Airbus and Douglas) the scratchpad is cleared and the data fields
are altered by using this key. For MCDUs that have both CLR and DEL
keys (e.g., Boeing), the scratchpad is cleared using the CLR key, while
the data fields are altered using the DEL key.
CLR Key
Pushing the CLR key clears the scratchpad message. When the
scratchpad contains user-entered characters, momentary actuation of
the CLR key clears the last entered character, while continual actuation
of the CLR key clears the entire contents of the scratchpad.
When the scratchpad is empty, pushing the CLR key causes CLR to be
displayed in the scratchpad indented five spaces. If an LS key is pushed
and the field adjacent to the LS key is specified to be either erasable
(e.g., an unprotected number) or a default maintained value (e.g.,
protected number priorities), the field is cleared or reverts back to its
default value, as applicable.
For compatibility with the Boeing 777 AIMS/CDU, the SDU clears the
entire scratchpad when the CLR command is received with the repeat
bit set.
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DEL Key
The DEL key (if available) can be used to clear or revert the data fields.
Pushing the DEL key causes no response when the scratchpad is not
empty, except for either an SDU issued error message or pilot-entered
characters.
When the scratchpad is empty, pushing the DEL key causes DELETE to
be displayed in the scratchpad.
NOTE: Pushing the DEL key again does not clear DELETE from the
scratchpad. Instead, pushing the CLR key when DELETE is
displayed in the scratchpad clears DELETE.
If an LS key is pushed and the field adjacent to the LS key is specified
to be either erasable (e.g., an unprotected number) or a default
maintained value (e.g., protected number priorities), the field is cleared
or reverts back to its default value, as applicable.
When the scratchpad contains CLR indented five spaces as the result of
the CLR key being pushed with an empty scratchpad and the DEL key
is subsequently pushed, the SDU replaces CLR with DELETE in the
scratchpad.
(e) NEXT PAGE and PREV PAGE Keys
General
NEXT PAGE Key
Pushing this key causes the next page in the sequence to be displayed.
If the last page in a multiple page sequence is displayed and the NEXT
PAGE key is pushed, the first page is displayed. The SDU ignores this
key if the key is pushed when p/t is not displayed, or if a p/t display is
the value 1/1.
PREV PAGE Key
(f)
Pushing the NEXT PAGE and PREV PAGE (if available) function keys
on the SCDU keypad causes the SDU to display the next page, or
previous page of the display sequence where appropriate (i.e., when p/t
is displayed in the title line).
Pushing this key causes the previous page in the sequence to be
displayed. If the first page in a multiple page sequence is displayed and
the PREV PAGE key is pushed, the last page is displayed. The SDU
ignores this key if the key is pushed when p/t is not displayed, or if a p/t
display is the value 1/1.
Special Symbols
When displayed, special symbols are defined as given in Table 6-9.
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Table 6-9.
Symbol
Special Symbols
Description
* (Asterisk)
Pushing the LS key adjacent to this symbol (when it appears) causes an
action of some kind to occur (e.g., making a phone call, sorting a phone
list, or initiating log-off).
[ ] (Brackets)
Empty brackets prompt the user for data entry into the field. However, data
entry is not mandatory. Brackets surrounding data indicate the data is
unprotected and can be modified or deleted. Not all fields modifiable are
surrounded by brackets. When brackets are used to enclose existing data,
as opposed to prompting entry of data into an empty field, they are
intended as an indication the data is unprotected (i.e., an unprotected
phone number). Conversely, protected phone numbers do not have
brackets, indicating the phone number cannot be modified or deleted.
< , > (Carets)
A caret adjacent to an LS key indicates if the key is pushed the display
changes to a new page. The new page is either the one indicated next to
the caret or, in case of RETURN>, the higher level page.

Indicates the data in the field is currently selected (e.g., the selected GES
or antenna).
(g) Updates
Dynamically generated display fields, whose contents have changed, are
updated by the SDU both periodically (at a rate of at least 1 Hz), and upon
completion of an LS key action that could have caused the display or the
display field to change. With multiple SCDU configurations, the SDU only
maintains one version of each page for display. The SDU responds to LS
key actuations from all SCDUs in a serial fashion and updates the display
page(s). Each SCDU scratchpad and the channel selection fields are
independent from all others, allowing each user to perform independent
actions.
C. SCDU Page Hierarchy
(1) The SCDU page hierarchy is shown in Figure 6-2. The SATCOM MAIN MENU page
is accessed by pushing the LS key adjacent to  prompt is displayed on the right adjacent to the 6R key,
as opposed to the left.
• The SDU issues scratchpad message 1 (i.e., NOT ALLOWED) if any LS
key is pushed adjacent to a blank or display-only field.
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Figure 6-4 (Sheet 1, Boeing/Corporate).
SATCOM SUBMENU Page
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Figure 6-4 (Sheet 2, Airbus).
SATCOM STATUS Page
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Figure 6-5.
SATCOM MAINTENANCE Page
Access to SATCOM maintenance displays are as follows:
• Push LS key 1L to show the Last Leg Report page (see Figure 6-10)
• Push LS key 2L to show the Previous Leg Report page (see Figure 6-11)
• Push LS key 3Lto show the LRU Identification page (see Figure 6-12)
• Push LS key 5L to show the Trouble Shooting Data page (see
Figure 6-13)
• Push LS key 6L to show the Configuration Data page (see Figure 6-8)
• Push LS key1R to show the Last Leg Class 3 Faults page (see
Figure 6-14)
• Push LS key 2R to show the Test page (see Figure 6-6)
• Push LS key 3R to show the Data Loader Menu page (see Figure 6-9)
• Push LS key 5R to show the Ground Report page (see Figure 6-15).
(b) TEST page
If a system-wide functional test (i.e., PAST) is initiated from the SCDU
interface (i.e., by pushing the 2R key on the SATCOM MAINTENANCE
page), the first access of the SATCOM subsystem from an SCDU MAIN
MENU page after the POST/PAST Results Delay period causes the TEST
page to be shown with the status of the current failures. However, the TEST
page shows the TEST IN PROGRESS 60S message if this first access
occurs during the POST/PAST Results Delay period. If the SATCOM
subsystem is not accessed within 5 minutes of the completion of an
SCDU-initiated PAST, the page hierarchy is reset to its original structure as
shown in Figure 6-2.
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When the 2R key is pushed on the SATCOM MAINTENANCE (i.e., SAT--N)
page, the SDU initiates a PAST and the page display temporarily goes to the
TEST page where TEST IN PROGRESS 60S is displayed. However, the
SCDU eventually times out the SATCOM subsystem and takes back control
of the display. This is due to the fact that for SCDU-accessed maintenance
pages, the SDU interfaces directly with the SCDU (as opposed to going
through the CFDIU) and is unable to maintain proper bus activity (which the
CFDIU normally does) during initial execution of the PAST.
To display the test results, the user must reselect the SATCOM system by
pushing the LS key adjacent to the  beginning in column 1 when the test is active. If the log--on
state changes from Standby to any other state while the test is active,
the test is terminated. The commands on lines 4 and 5 are shown only if
the configuration straps indicate this channel is wired for headset use.
Pushing LS key 2L when the ENABLE asterisk prompt is shown causes
the voice channel selected to be activated into an analog loopback test
state. Pushing LS key 2L when the DISABLE prompt is shown causes
the voice loopback test state to be terminated.
Line 6
Line 7
This line displays *ENABLE beginning in column 1 when the test is not
active. The asterisk prompt is shown and the test allowed only if the
log--on state is Standby. This line displays *DISABLE 
beginning in column 1 when the test is active. If the log--on state
changes from Standby to any other state while the test is active, the test
is terminated. The commands on lines 6 and 7 are shown only if the
configuration straps indicate this channel is wired for headset use.
Pushing LS key 3L when the ENABLE asterisk prompt is shown causes
the cockpit voice call light to be activated for a steady indication
(regardless of the state of configuration pin TP13C). Pushing LS key 3L
when the DISABLE prompt is displayed causes the cockpit voice call
light test to be terminated.
LIne 8
This line displays MP8E CALL LIGHT TEST beginning in column 2.
Pushing LS key 3L initiates a lamp test of the flight deck channel 1 call
lamp.
This line displays MP2EFGH VOICE LOOPBACK beginning in column
2. Pushing LS key 4L configures the SATCOM system to perform an
audio loopback test of flight deck channel 2.
Line 9
This line displays ENABLE beginning in column 1 when the test is not
active. The asterisk prompt is shown and the test allowed only if the
log--on state is Standby. This line displays *DISABLE 
beginning in column 1 when the test is active. If the log--on state
changes from Standby to any other state while the test is active, the test
is terminated. The commands on lines 8 and 9 are displayed only if the
configuration straps indicate this channel is wired for headset use.
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Line 10
Pushing LS key 4L when the ENABLE asterisk prompt is displayed
causes the voice channel selected to be activated into an analog
loopback test state. Pushing LS key 4L when the DISABLE prompt is
displayed causes the voice loopback test state to be terminated.
This line displays MP8G CALL LIGHT TEST beginning in column 2.
Pushing LS key 5L initiates a lamp test of the flight deck channel 2 call
lamp.
Line 11
This line displays *ENABLE beginning in column 1 when the test is not
active. The asterisk prompt is displayed and the test allowed only if the
log--on state is Standby. This line displays *DISABLE 
beginning in column 1 when the test is active. If the log--on state
changes from Standby to any other state while the test is active, the test
is terminated. The commands on lines 10 and 11 are displayed only if
the configuration straps indicate this channel is wired for headset use.
Pushing LS key 5L when the ENABLE asterisk prompt is displayed
causes the cockpit voice call light to be activated for a steady indication
(regardless of the state of configuration pin TP13C). Pushing LS key 5L
when the DISABLE prompt is displayed causes the cockpit voice call
light test to be terminated.
10 Line 12
This line displays MP14BC CHIME beginning in column 2. Pushing LS
key 6L initiates the channel test.
11 Line 13
This line displays TEST beginning in column 1. The asterisk prompt is
displayed and the test allowed only if the log--on state is Standby.
Pushing LS key 6L when the asterisk prompt is displayed causes the
cockpit voice go-ahead chime to be activated for a single stroke.
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(5) SATCOM SELF--TEST (PAST) Page
(a) General
The purpose of this page is to initiate a PAST, to enable/disable a voice
loopback on a selected (physical) channel, to enable/disable a test of the
cockpit voice call light for a selected (logical) channel, and activation of the
cockpit voice go-ahead chime test. See Figure 6-7 for example pages.
(b) Data Fields
Line 1
This line displays the title of the page, SAT--N, beginning in column 10,
where N represents 1 or 2 to indicate a single SDU (N = 1), SDU No. 1
(N = 1), or SDU No. 2 (N = 2) as determined by the settings of
configuration pins TP12E and TP12F.
If there are current failures to report after the execution of a PAST,
columns 20 thru 24 display p/t in small font, where p represents the
current displayed page, and t represents the total number of pages
needed to show the current failures. The display of the slash is always
in column 22, with p right-justified to the slash and t left-justified to the
slash.
Line 3
This line displays headers ATA beginning in column 1 and CLASS
beginning in column 20 if there are current failures to report after
execution of a PAST. This line is blank if there are no failures to report.
In addition to the above, for CFDS type none, the header ATA is not
displayed (CLASS is still displayed as specified).
Line 5
This line displays the message TEST IN PROGRESS 60S beginning in
column 3 within one second of a PAST being initiated on the SAT--N
(i.e., SATCOM MAINTENANCE) page, and then throughout the duration
of PAST. If there are no current failures to report at the conclusion of the
PAST (including the POST/PAST results delay period), the message
TEST OK is displayed. If there are current failures to report at the
conclusion of the PAST (including the POST/PAST results delay period),
refer to paragraph 4 for line requirements.
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Figure 6-7 (Sheet 1).
SATCOM SELF--TEST Page
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Figure 6-7 (Sheet 2).
SATCOM SELF--TEST Page
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Other Information
The SELF--TEST page lists two failures per page if failures are detected
during the PAST(self--test). These two sets of lines (lines 5, 6, and 7
and lines 9, 10, and 11) display Level 1 diagnosed current failures.
Failures are shown in chronological order (i.e., the most recent detected
failure last) with no more than two failures displayed per page.
The number of TEST pages depends on the number of current failures
to report (up to a maximum of 99 pages). When there is an odd number
of current failures to report, the odd failure is displayed on a separate
page in lines 5, 6, and 7, and lines 9, 10, and 11 are blank. If there are
no failures to report, lines 5, 6, 7, 9, 10, and 11 are blank except as
noted in paragraph 3.
Line 5 and, if applicable, line 9 display the ATA number beginning in
column 1 and the class number beginning in column 23. The ATA
number is displayed as aaaaaa, where aaaaaa represents the ATA
reference number of the reported failure as specified in paragraph 3.E.
for each type of CFDS. For CFDS type none, no ATA number is
displayed. The class number is displayed as c, where c represents the
class (1, 2, or 3) of the failure.
Lines 6 and 7 and, if applicable, lines 10 and 11 display a text message,
as specified in paragraph 3.E. for each CFDS type, for the reported
failure beginning in column 1.
(6) CONFIGURATION DATA Pages
(a) General
Access to these pages is from the SAT--N (i.e., SATCOM MAINTENANCE)
page. The purpose of these pages is to display the status of SATCOM
configuration input parameters. See Figure 6-8 for example pages.
(b) CONFIGURATION DATA Page 1 (Figure 6-8, sheet 1):
Data Fields
Line 3
(1) This line displays the ICAO address of eight octal characters, as
determined by discrete inputs from the ICAO address straps. This
display is not derived from any ARINC 429 version of the ICAO
address.
Line 5
(1) This line displays CONFIG as determined by the setting of the
system configuration pins, followed by (HEX). The configuration pin
settings are mapped into hexadecimal digits as shown in
Table 6-10. In the figure, digits 0 thru 9 correlate to hexadecimal
digits 0 thru 9 in the table.
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SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL
MCS--4200/7200 Multi--Channel SATCOM System
Figure 6-8 (Sheet 1).
Table 6-10.
Configuration Data
System Configuration Pin Mapping
Configuration Pins
TP10
ABCD
EFGH
TP11
JK
AB CDEF
TP12
GHJK
ABCD
EFGH
TP13
JK
AB CDEF
GHJK
Hex Digits
Line 7
(1) This line displays the WOW--1 status of SDU weight-on-wheels
discrete input No. 1 as IN-AIR/NOT WIRED or ON-GROUND.
Line 8
(1) This line displays the WOW--2 status of the SDU weight-on-wheels
discrete input No. 2 as IN-AIR/NOT WIRED or ON-GROUND.
Line 10
(1) This line displays the MIC--1 status of the SDU cockpit voice
microphone On discrete input No. 1 as ACTIVE or INACTIVE.
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MCS--4200/7200 Multi--Channel SATCOM System
Line 11
(1) This line displays the MIC--2 status of the SDU cockpit voice
microphone On discrete input No. 2 as ACTIVE or INACTIVE.
(c) CONFIGURATION DATA Page 2 (Figure 6-8, sheet 2):
Data Fields
Line 3
(1) This line displays the CHIME RESET status of the SDU cockpit
voice go-ahead chime signal reset discrete input as ACTIVE or
INACTIVE.
Line 5
(1) This line displays the DUAL SYS SELECT status of the SDU dual
system select discrete input as ACTIVE or INACT.
Line 6
(1) This line displays the DUAL SYS DISABLE status of the SDU dual
system disable discrete input as ACTIVE or INACT.
Line 8
(1) This line displays IRS SOURCE as determined by which IRS input
bus the SDU is using. A dash is displayed for the IRS source if a
429 source of IRS is not connected to the SDU.
Line 10
(1) This line displays the PLACE/END CALL 1 status of the SDU
cockpit voice place/end call 1 discrete input as ACTIVE or INACT.
Line 11
(1) This line displays the PLACE/END CALL 2 status of the SDU
cockpit voice place/end call 2 discrete input as ACTIVE or INACT.
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SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL
MCS--4200/7200 Multi--Channel SATCOM System
Figure 6-8 (Sheet 2).
Configuration Data
(d) CONFIGURATION DATA Page 3 (Figure 6-8, sheet 3):
General
For CONFIGURATION DATA pages 3 thru 10, the strap setting value 0
or 1 in parentheses is as follows: 1= open circuit; and 0 = tied to
common.
Data Fields
Line 4
(1) This line displays A(0) ICAO ADRS AVAIL or A(1) ICAO ADRS NOT
AVAIL left-justified as determined by the state of system
configuration pin TP10A.
Line 6
(1) This line displays B(0) FMC1 CONNECTED or B(1) FMC1 NOT
CONNECTED left-justified as determined by the state of system
configuration pin TP10B.
Line 8
(1) This line displays C(0) FMC2 CONNECTED or C(1) FMC2 NOT
CONNECTED left-justified as determined by the state of system
configuration pin TP10C.
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MCS--4200/7200 Multi--Channel SATCOM System
Line 10
(1) This line displays D(0) HS 429 TO/FROM CMUS or D(1) LS 429
TO/FROM CMUS left-justified as determined by the state of system
configuration pin TP10D.
Line 12
(1) This line displays E(0) CPDF CONNECTED or E(1) CPDF NOT
CONNECTED left-justified as determined by the state of system
configuration pin TP10E.
Figure 6-8 (Sheet 3).
Configuration Data
(e) CONFIGURATION DATA Page 4 (Figure 6-8, sheet 4):
Data Fields
Line 4
(1) This line displays F(0) HS 429 ICAO ADRS or F(1) LS 429 ICAO
ADRS left-justified as determined by the state of system
configuration pin TP10F.
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MCS--4200/7200 Multi--Channel SATCOM System
Line 6
(1) This line displays G(0) HSU CONNECTED or G(1) HSU NOT
CONNECTED left-justified as determined by the state of system
configuration pin TP10G.
Line 8
(1) This line displays H(0) SDU CONTROLLER=WSC or H(1) SDU
CONTROLLER=SCDU left-justified as determined by the state of
system configuration pin TP10H.
Line 10
(1) This line displays J(0) SPARE or J(1) SPARE left-justified as
determined by the state of system configuration pin TP10J.
Line 12
(1) This line displays K(0) LAMP ON CALL INIT or K(1) LAMP ON
CALL CONNCT left-justified as determined by the state of system
configuration pin TP10K.
Figure 6-8 (Sheet 4).
Configuration Data
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SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL
MCS--4200/7200 Multi--Channel SATCOM System
(f)
CONFIGURATION DATA Page 5 (Figure 6-8, sheet 5):
Data Fields
Line 4
(1) This line displays A(0) PARITY: GOOD, A(1) PARITY: GOOD, A(0)
PARITY: BAD, or A(1) PARITY: BAD left-justified as determined by
the state of system configuration pin TP11A and the result of the
parity validation test.
Line 6
(1) This line displays B(0) CCS INSTALLED or B(1) CCS NOT
INSTALLED left-justified as determined by the state of system
configuration pin TP11B.
Line 8
(1) This line displays C(0) PRI IRS INSTALLED or C(1) PRI IRS NOT
INSTLLD left-justified as determined by the state of system
configuration pin TP11C.
Line 10
(1) This line displays D(0) SEC IRS INSTALLED or D(1) SEC IRS NOT
INSTLLD left-justified as determined by the state of system
configuration pin TP11D.
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SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL
MCS--4200/7200 Multi--Channel SATCOM System
Figure 6-8 (Sheet 5).
Configuration Data
(g) CONFIGURATION DATA Page 6 (Figure 6-8, sheet 6):
Data Fields
Lines 4 thru 9
(1) These lines display X(0)* or X(1)* left-justified as shown in the
figure, where X represents E, F, G, H, J, and K, respectively. X(0)*
or X(1)* is determined by the states of system configuration pins
TP11E, TP11F, TP11G, TP11H, TP11J, and TP11K. Asterisks are
displayed in column 5 to indicate these pins are a coded group.
(2) Beginning in column 6, textual messages are displayed (refer to
Table 6-11) in lines 4 thru 9 (as needed), where an x indicates the
message(s) to be displayed based on the state of system
configuration pins TP11E, TP11F, TP11G, TP11H, TP11J, and
TP11K.
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SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL
MCS--4200/7200 Multi--Channel SATCOM System
Table 6-11.
Textual Message Display (Page 6 -- Lines 4 thru 9)
System Configuration Pin Settings
System Configuration Pin
(1 = open circuit / 0 = tied to common)
TP11E
TP11F
TP11G
TP11H
TP11J
TP11K
Textual Message
All Other Pin Combinations
Textual Messages To Display Based On System Configuration Pin
Settings
LO GAIN ANT+DLNA
HPA--LO GAIN
HI GAIN ANT+BSU--T/L
HI GAIN ANT+BSU--R
HPA--HI GAIN
HI POWER RELAY
HPA--IGA
ERROR/UNDEFINED
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SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL
MCS--4200/7200 Multi--Channel SATCOM System
Figure 6-8 (Sheet 6).
Configuration Data
(h) CONFIGURATION DATA Page 7 (Figure 6-8, sheet 7):
Data Fields
Lines 4 thru 6
(1) These lines display X(0)* or X(1)* left-justified as shown in the
figure, where X represents A, B and C, respectively. X(0)* or X(1)*
are determined by the state of system configuration pins TP12A,
TP12B, and TP12C. Asterisks are displayed in column 5 to indicate
these pins are a coded group.
(2) CFDS/CMC TYPE = is displayed in line 4 beginning in column 6.
(3) Beginning in column 6, a textual message is displayed according to
Table 6-12, where an x indicates the message to be displayed,
based on the state of system configuration pins TP12A, TP12B and
TP12C.
Line 10
(1) This line displays D(0) RESERVED or D(1) RESERVED left-justified
as determined by the state of system configuration pin TP12D.
Line 12
(1) This line displays E(0) OTHER SDU INSTALLED or E(1) OTHER
SDU NOT INSTD left-justified as determined by the state of system
configuration pin TP12E.
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SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL
MCS--4200/7200 Multi--Channel SATCOM System
Figure 6-8 (Sheet 7).
Table 6-12.
Configuration Data
Textual Message Display (Page 7 -- Lines 4, 5, and 6)
System Configuration Pin Settings
System Configuration Pin
(1 = open circuit / 0 = tied to common)
TP12A
TP12B
TP12C
Textual Message
All Other Pin Combinations
Textual Messages To Display Based On System Configuration Pin
Settings
MCDONNELL--DOUGLAS
AIRBUS
BOEING
NOT INSTALLED
ERROR/UNDEFINED
CAIMS
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SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL
MCS--4200/7200 Multi--Channel SATCOM System
(i)
CONFIGURATION DATA Page 8 (Figure 6-8, sheet 8):
Data Fields
Line 4
(1) This line displays F(0) THIS IS SDU2 or F(1) THIS IS SDU1
left-justified as determined by the state of system configuration pin
TP12F.
Line 6 -(1) This line displays G(0) CMU1 INSTALLED or G(1) CMU1 NOT
INSTALLED left-justified as determined by the state of system
configuration pin TP12G.
Line 8
(1) This line displays H(0) CMU2 INSTALLED or H(1) CMU2 NOT
INSTALLED left-justified as determined by the state of system
configuration pin TP12H.
Line 10
(1) This line displays J(0) SCDU1 INSTALLED or J(1) SCDU1 NOT
INSTALLED left-justified as determined by the state of system
configuration pin TP12J.
Line 12
(1) This line displays K(0) SCDU2 INSTALLED or K(1) SCDU2 NOT
INSTALLED left-justified as determined by the state of system
configuration pin TP12K.
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SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL
MCS--4200/7200 Multi--Channel SATCOM System
Figure 6-8 (Sheet 8).
(j)
Configuration Data
CONFIGURATION DATA Page 9 (Figure 6-8, sheet 9):
Data Fields
Line 4
(1) This line displays A(0) NO HSET PRI 4 CALLS or A(1) HSET PRI 4
CALLS OK left-justified as determined by the state of system
configuration pin TP13A.
Line 6
(1) This line displays B(0) LS 429 TO SCDUS or B(1) HS 429 TO
SCDUS left-justified as determined by the state of system
configuration pin TP13B.
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SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL
MCS--4200/7200 Multi--Channel SATCOM System
Figure 6-8 (Sheet 9).
Configuration Data
Lines 8 and 9
(1) These lines display X(0)* or X(1)* left-justified as shown in the
figure, where X represents C and D, respectively. X(0)* or X(1)* are
determined by the state of system configuration pins TP13C and
TP13D. Asterisks are displayed in column 5 to indicate these pins
are a coded group.
(2) Beginning in column 6, a textual message is shown in line 8 and
according to Table 6-13, where an x indicates the message to be
displayed, based on the state of system configuration pins TP13C
and TP13D.
Line 12
(1) This line displays E(0) SCDU3 INSTALLED or E(1) SCDU3 NOT
INSTALLED left-justified as determined by the state of system
configuration pin TP13E.
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SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL
MCS--4200/7200 Multi--Channel SATCOM System
Table 6-13.
Textual Message Display (Page 9 -- Lines 8 and 9)
System Configuration Pin Settings
System Configuration Pin
(1 = open circuit / 0 = tied to common)
TP13C
TP13D
Textual Message
Textual Messages to Display Based on System Configuration
Pin Settings
LIGHTS AND CHIME
UNDEFINED
(Line 8)
(Line 9)
STEADY LIGHTS AND
MULTISTROKE CHIME
(Line 8)
(Line 9)
FLASHING LIGHTS AND
SINGLE STROKE CHIME
(Line 8)
(Line 9)
STEADY LIGHTS AND
SINGLE STROKE CHIME
(Line 8)
(Line 9)
(k) CONFIGURATION DATA Page 10 (Figure 6-8, sheet 10):
Data Fields
Lines 4 and 5
(1) These lines display X(0)* or X(1)* left-justified as shown in the
figure, where X represents F and G, respectively. X(0)* or X(1)* are
determined by the state of system configuration pins TP13F and
TP13G.
(2) Beginning in column 6, a textual message is displayed in lines 4
and 5 according to Table 6-14, where an x indicates the message to
be displayed based on the state of system configuration pins
TP13F and TP13G.
Lines 8 and 9
(1) These lines display X(0)* or X(1)* left-justified, where X represents
H and J, respectively. X(0)* or X(1)* are determined by the state of
system configuration pins TP13H and TP13J. Asterisks are
displayed in column 5 to indicate these pins are a coded group.
(2) Beginning in column 6, a textual message is displayed in lines 8
and 9 according to Table 6-15, where an x indicates the message to
be displayed based on the state of system configuration pins
TP13H and TP13J.
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SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL
MCS--4200/7200 Multi--Channel SATCOM System
Figure 6-8 (Sheet 10).
Configuration Data
Lines 11 and 12
(1) Line 11 displays K(0) HOOK SWITCH IS left-justified and line 12
displays LATCHED ACP MIC SW beginning in column 6; or line 11
displays K(1) HOOK SWITCH IS left-justified and line 12 displays
SWITCHED PTT/SCDU beginning in column 6, as determined by
the state of system configuration pin TP13K.
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SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL
MCS--4200/7200 Multi--Channel SATCOM System
Table 6-14.
Textual Message Display (Page 10 -- Lines 4 and 5)
System Configuration Pin Settings
System Configuration Pin
(1 = open circuit / 0 = tied to common)
TP13F
TP13G
Textual Message
Textual Messages to Display Based on System Configuration
Pin Settings
AMS 1 WIRED
CABIN 1 WIRED
(Line 4)
(Line 5)
AMS 1 WIRED
CABIN 1 NOT WIRED
(Line 4)
(Line 5)
AMS 1 NOT WIRED
CABIN 1 WIRED
(Line 4)
(Line 5)
AMS 1 NOT WIRED
CABIN 1 NOT WIRED
(Line 4)
(Line 5)
Table 6-15.
Textual Message Display (Page 10 -- Lines 8 and 9)
System Configuration Pin Settings
System Configuration Pin
(1 = open circuit / 0 = tied to common)
TP13H
TP13J
Textual Message
Textual Messages to Display Based on System Configuration
Pin Settings
AMS 2 WIRED
CABIN 2 WIRED
(Line 8)
(Line 9)
AMS 2 WIRED
CABIN 2 NOT WIRED
(Line 8)
(Line 9)
AMS 2 NOT WIRED
CABIN 2 WIRED
(Line 8)
(Line 9)
AMS 2 NOT WIRED
CABIN 2 NOT WIRED
(Line 8)
(Line 9)
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SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL
MCS--4200/7200 Multi--Channel SATCOM System
(l)
CONFIGURATION DATA Page 11 (Figure 6-8, Sheet 11):
General
Page 11 of the CONFIGURATION DATA page is shown below.
Figure 6-8 (Sheet 11).
Configuration Data
(m) CONFIGURATION DATA Page 12 (Figure 6-8, Sheet 12):
General
Page 12 of the CONFIGURATION DATA page is shown below.
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SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL
MCS--4200/7200 Multi--Channel SATCOM System
Figure 6-8 (Sheet 12).
Configuration Data
(n) CONFIGURATION DATA Page 13 (Figure 6-8, Sheet 13):
Data Fields
Line 3
(1) This line displays the CALL LAMP 1 status of the SDU Cockpit
Voice-Call Lamp Discrete Output as ACTIVE or INACT as
appropriate.
Line 4
(1) This line displays the CALL LAMP 2 status of the SDU Cockpit
Voice-Call Lamp Discrete Output as ACTIVE or INACT as
appropriate.
Line 6
(1) This line displays the DUAL SYS SELECT status of SDU Dual
System Select Discrete Output as ACTIVE or INACT as
appropriate.
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SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL
MCS--4200/7200 Multi--Channel SATCOM System
Figure 6-8 (Sheet 13).
Configuration Data
(o) CONFIGURATION DATA Page 14 (Figure 6-8, sheet 14):
Data Fields
Line 3
(1) This line displays HPA CMND/STAT beginning in column 1, HGA
beginning in column 15, and LGA beginning in column 22.
Line 4
(1) This line displays BACKOFF(DB) beginning in column 1. The HGA
HPA commanded backoff power level (in dB) is displayed (if
configured) right-justified in column 17 (as determined from the
HGA HPA command word Label 143). The LGA HPA commanded
backoff power level (in dB) is displayed (if configured) right-justified
in column 24 (as determined from the HGA HPA command word
Label 143. The ranged allowed for display of the backoff is 0 to 31
dB in increments of 1 dB.
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SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL
MCS--4200/7200 Multi--Channel SATCOM System
Figure 6-8 (Sheet 14).
Configuration Data
Line 5
(1) This line displays ACTUAL(DBW) beginning in column 1. The HGA
HPA reported power level (in dB Watts) is displayed (if configured)
right-justified in column 16 (as determined from the HGA HPA
status word Label 144). The state of the actual power out status
(APOS) bit is indicated as either A for actual or H for held and is
displayed in column 17. The LGA HPA commanded backoff power
level (in dB Watts) is displayed (if configured) right-justified in
column 23 (as determined from the LGA HPA status word Label
144). The state of the APOS status bit is displayed in column 24 as
previously stated. The allowable range for display of the actual
power is --11.5 to 19.0 dBW in increments of 0.5 dBW. If the actual
power value is outside the measurable range, dashes are displayed
for the actual power value. If valid data is not available for the HPA
status label, dashes are displayed to indicate the unknown data.
Line 6
(1) This line displays POWER(WATTS) beginning in column 1.
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SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL
MCS--4200/7200 Multi--Channel SATCOM System
Figure 6-8 (Sheet 15).
Configuration Data
Line 7
(1) This line displays REFLECTED beginning in column 1. The HGA
HPA reflected power level (in Watts) is displayed (if configured)
right-justified in column 17 (as determined from the HGA HPA ). The
LGA HPA reflected power level (in Watts) is displayed (if configured)
right-justified in column 24 (as determined from the LGA HPA ). The
allowable range for the display of the reflected power value is 0.000
to 25.056 Watts. If the power level is unavailable, dashes are
displayed.
Line 8
(1) This line displays FORWARD beginning in column 1. The HGA HPA
reflected power level (in Watts) is displayed (if configured)
right-justified in column 17 (as determined from the HGA HPA). The
LGA HPA reflected power level (in Watts) is displayed (if configured)
right-justified in column 24 (as determined from the LGA HPA). The
allowable range for the display of the reflected power value is 0.000
to 80.000 Watts. If the power level is unavailable, dashes are
displayed.
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MCS--4200/7200 Multi--Channel SATCOM System
Line 9
(1) This line displays RATIO(R/F) beginning in column 1. The HGA
HPA reflected power to forward power ratio is displayed (if
configured) right-justified in column 17 (as determined from the
HGA HPA). The LGA HPA reflected power to forward power ratio is
displayed (if configured) right-justified in column 24 (as determined
from the LGA HPA). The allowable range for the display of the
reflected power to forward power ratio is 0.000 to 1.000 Watts. If the
reported ratio is over-range, the text OVER is displayed. If the ratio
number is unavailable, dashes are displayed.
NOTE: The over-range condition occurs when the forward power
is more than 50 Watts while the reflected power is at the
maximum of 25.056 Watts. The HPA indicates the
over-range condition through the solo word ratio value of
FFH.
Line 10
(1) This line displays CARRIER beginning in column 1.
Line 11
(1) This line displays COMMANDED beginning in column 1. The HGA
HPA commanded carrier state is displayed (if configured)
right-justified in column 17 (as determined from the HGA HPA). The
LGA HPA commanded carrier state is displayed (if configured)
right-justified in column 24 (as determined from the LGA HPA). The
commanded carrier state is displayed as either ON or OFF.
Line 12
(1) This line displays ACTUAL beginning in column 1. The HGA HPA
actual carrier state is displayed (if configured) right-justified in
column 17 (as determined from the HGA HPA). The LGA HPA
commanded carrier state is displayed (if configured) right-justified in
column 24 (as determined from the LGA HPA). The actual carrier
state is displayed as either ON or OFF.
Line 13
(1) This line displays RETURN> right-justified. Pushing LS key 6L
causes the page display to revert to the SAT--N (SATCOM
MAINTENANCE) page.
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SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL
MCS--4200/7200 Multi--Channel SATCOM System
(7) DATA LOADER MENU Page
(a) General
Access to this page is from SATCOM SUBMENU page (or the SATCOM
MAINTENANCE page). The access page depends on the configuration of
the aircraft as defined in Figure 6-2. The purpose of this page is to supply a
means of commanding data loader actions. See Figure 6-9 for example
pages.
(b) Data Fields
Field 1L
This field displays DATA LOADER in the label line and the data loader
status in the data line. Possible status displays depend on the data
loader status as follows:
• NOT CONNECTED -- Displayed when the status of both data loader
is absent.
• CONNECTED -- Displayed when at least one data loader status is
CONNECTED, and the status of neither data loaders is READY,
BUSY, or ERROR.
• READY -- Displayed when a data loader status is READY.
• BUSY -- Displayed when a data loader status is BUSY.
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SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL
MCS--4200/7200 Multi--Channel SATCOM System
READY must be displayed before data uploading or downloading can
be performed.
Asterisks are only displayed adjacent to the left LS keys when the data
loader status is READY.
Figure 6-9 (Sheet 1).
DATA LOADER MENU
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SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL
MCS--4200/7200 Multi--Channel SATCOM System
Figure 6-9 (Sheet 2).
DATA LOADER MENU
Figure 6-9 (Sheet 3).
DATA LOADER MENU
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SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL
MCS--4200/7200 Multi--Channel SATCOM System
Figure 6-9 (Sheet 4).
DATA LOADER MENU
Several messages are displayed when the status of a data loader is
ERROR . If the status becomes ERROR, an appropriate error message
is appended to ERROR, separated by a dash. Possible error messages
are displayed as follows:
• DISK FULL
• TRANSFER FAILURE
• FILE NOT FOUND
• CRC FAILURE
• BAD FILE HEADER
• BAD OWNER REQS VER
• OPEN DISK
• CLOSE DISK
• WRITE PROTECT
• COMP ORT NOT ALLOW.
The TRANSFER FAILURE error message indicates an ARINC 615
protocol transfer failure (e.g., loss of communications). The OPEN DISK
and CLOSE DISK error messages are displayed when an undefined
disk command completion code is received. COMP ORT NOT ALLOW
is indicated when a composite ORT version upload is attempted and the
setting for ORT item liv does not allow it.
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Fields 2L thru 5L
These fields display prompts in the data line for commanding data
loader actions. The prompts that can be displayed for the indicated
DATA LOADER MENU page (1 or 2) are as given in Table 6-16.
Table 6-16.
DATA LOADER MENU Page Prompts
Display Prompt
LS Key
2L
UPLD OWNER REQS
3L
DNLD OWNER REQS
4L
DNLD SYSTEM DATA
5L
START
The display prompts given in Table 6-16 command the following actions:
• UPLD OWNER REQS -- upload owner requirements table
• DNLD OWNER REQS -- download owner requirements table
• DNLD SYSTEM DATA -- download all event/fail/config/ORT logs
Asterisks are only displayed beside the adjacent left LS key when the
data loader status is READY (except as stated below). When asterisks
are displayed, pushing the left LS key adjacent to the desired action
commands the data loader to initiate that action.
Uploads are allowed regardless of the log-on state (composite uploads
are inhibited only by ORT item liv and not the log-on state).
Once a left LS key is pushed, the  message is displayed to the
right of the selected data loader action, right-justified. The data loader
status changes to BUSY and data transfers occur. There is only one
data loader command selected at a time. The  message remains
displayed until the 6L key is pushed if the data loader status becomes
ERROR after a left LS key is pushed. When the data transfer is
completed, or after an error has been acknowledged, the 
message is removed and the data loader status changes appropriately.
Fields 5L and 5R
PERIODIC DATA LOGGING is displayed in the label line beginning in
column 2. In the data line, START is displayed adjacent to the 5L key.
No asterisk is displayed beside the 5L key when the data loader status
is either NOT CONNECTED, CONNECTED, BUSY, or ERROR.
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When the START prompt is selected by pushing the 5L key when the
data loader status is READY:
• Periodic data logging starts
• The asterisk next to START is removed
• The  message is displayed beginning in column 8
• STOP is displayed adjacent to the 5R key.
Periodic data logging continues until the 5R key is pushed, at that time
the data line display reverts to its original state (i.e., only the START
prompt with or without an asterisk as appropriate).
The  message remains displayed and the STOP prompt is
blanked if the data loader status changes to ERROR after periodic data
logging has started. This condition remains until the error is
acknowledged by pushing the 6L key and/or the data loader status
changes, at that time the data line display changes as appropriate.
Field 6L
6L -- This data line displays the *ACK ERROR prompt. This prompt is
displayed when the data loader status is ERROR. Pushing the 6L key
causes the SDU to remove the ERROR status and display the current
data loader status (i.e., NOT CONNECTED or CONNECTED) in the 1L
data line.
The SDU completes the upload/download data transfer by commanding
the data loader transfer complete function. The data loader responds
with a TRANSFER COMPLETE indication and enters a no loop. To
return the data loader to the READY state, the user must cause the
data loader to read the configuration file on the diskette (i.e., cycle data
loader power or remove/insert the diskette).
Field 6R
6R -- This data line displays the RETURN> prompt. Pushing the 6R key
causes the display to revert to the SATCOM SUBMENU page (or
SATCOM MAINTENANCE page) as appropriate.
(8) LAST LEG REPORT Page
(a) Access to this page is from the SAT--N (i.e., SATCOM MAINTENANCE) page.
The purpose of this page is to display Class 1 and 2, Level 1 diagnosed, failures
reported during the last leg. See Figure 6-10 for example pages.
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(b) The Last Leg Report lists two failures per page if a failure is present during the
last leg. These two sets of lines display Class 1 and 2, Level 1 diagnosed, last
leg failures. Failures are displayed in chronological order (i.e., the most recent
detected failure last) with no more than two failures displayed per page. The
number of LAST LEG REPORT pages depends on the number of failures to
report (up to a maximum of 99 pages). When there is an odd number of failures
to report, the odd failure is displayed on a page of its own in lines 5, 6, and 7,
and lines 9, 10, and 11 are blank. If there are no failures to report, lines 6, 7, 9,
10, and 11 are blank. Line 5 displays NO FAULT DETECTED beginning in
column 4 if there are no failures to report.
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Figure 6-10.
LAST LEG REPORT Page
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(c) Line 5 and, if applicable, line 9 display the universal time coordinated (UTC)
beginning in column 1, and ATA beginning in column 6, and the class number in
column 23.
(d) The UTC is displayed as hhmm, where hh represents the UTC hours from 00 to
23, and mm represents the UTC minutes from 00 to 59. The UTC is the time of
the failure reporting as stored in the SDU system failure memory log. Dashes are
displayed if no valid UTC data is available.
(e) The ATA number is displayed as aaaaaa, where aaaaaa represents the ATA
reference number of the reported failure as specified in paragraph 3.E. for each
type of CFDS. For CFDS type none, no ATA number is displayed.
(f)
The class number is displayed as c, where c represents the class (1 or 2) of the
failure.
(9) PREVIOUS LEGS REPORT Page
(a) Access to this page is from the SAT--N (i.e., SATCOM MAINTENANCE) page.
The purpose of this page is to display Class 1 and 2, Level 1 diagnosed, failures
reported during previous legs. See Figure 6-11 for example pages.
(b) The Previous Leg Report lists two failures per page if a failure was present
during the previous leg. These two sets of lines display Class 1 and 2, Level 1
diagnosed, last leg failures. Failures within each flight leg are displayed in
chronological order (i.e., the most recent detected failure last) with no more than
two failures displayed per page. However, the flight leg display is in reverse
chronological order (i.e., flights go back in time while failures for each individual
flight go forward in time).
(c) The number of PREVIOUS LEGS REPORT pages depends on the number of
failures to report (up to a maximum of 99 pages). If there are no failures to
report, lines 6, 7, 9, 10, and 11 are blank. Line 5 displays NO FAULT DETECTED
beginning in column 4 if there are no failures to report.
(d) Failures from different flight legs with the same aircraft identification are mixed on
the same page. When the last leg falls in lines 5, 6, and 7, failures from the
previous flight leg are displayed on the same page in lines 9, 10, and 11.
(e) When the given flight leg has a different aircraft identification recorded than the
flight leg before it, the failure display begins in lines 5, 6, and 7 on the next page
of the multiple page sequence. When there are no failures to report for a given
flight leg, nothing is reported for that flight leg (i.e., the flight leg is skipped).
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Figure 6-11 (Sheet 1).
PREVIOUS LEG REPORT Page
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Figure 6-11 (Sheet 2).
PREVIOUS LEG REPORT Page
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(f)
Line 5 and line 9 (if applicable) display the flight leg number beginning in column
1, the UTC beginning in column 10, and the ATA number beginning in column
15.
(g) The flight leg is displayed as fl, where fl represents the flight leg number from 01
to either:
• The number of flight legs recorded in the SDU system failure memory log
• 63 flight legs
• From 01 to the maximum number of flight legs that can be displayed given the
PREVIOUS LEGS REPORT page limit of 99.
(h) The date is displayed as mmmdd, where mmm represents the month of the year
as JAN, FEB, MAR, APR, MAY, JUN, JUL, AUG, SEP, OCT, NOV, or DEC, and
dd represents the day of the month from 01 to 31. The date is the date of the
flight leg number as stored in the SDU system failure memory log. Dashes are
displayed if no valid UTC data is available.
(i)
The UTC time is displayed as hhmm, where hh represents the UTC hours from
00 to 23, and mm represents the UTC minutes from 00 to 59. The UTC is the
time of the failure reporting as stored in the SDU system failure memory log.
Dashes are displayed if no valid UTC data is available.
(j)
The ATA number is displayed as aaaaaa, where aaaaaa represents the ATA
reference number of the reported failure as specified in paragraph 3.E. for each
type of CFDS. For CFDS type none, no ATA number is displayed.
(k) The class number is displayed as c, where c represents the class (1 or 2) of the
failure.
(10) LRU IDENTIFICATION Page
(a) Access to this page is from the SAT--N (i.e., SATCOM MAINTENANCE) page.
The purpose of this page is to display a list of all installed LRUs with their
associated part numbers, modification levels, and serial numbers, and to display
ORT identification data. See Figure 6-12 for example pages.
(b) If a Honeywell/Thales HPA is installed, the associated part/serial number is
displayed; otherwise the HPA display entry is removed. The number of LRU
IDENTIFICATION pages depends on the number of LRUs to list.
(c) For the LRUs, line 4 and, if applicable, line 9 display a three letter acronym
representing the installed LRU. The possible LRU acronyms are given in
Table 6-17.
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Table 6-17.
LRU Acronyms
LRU Name
LRU Acronym
SDU
Satellite Data Unit
HPH
High Power Amplifier -- High Gain Antenna
HPL
High Power Amplifier -- Low Gain Antenna
HSU
High--Speed Data Unit
(d) For the LRUs, line 5 and, if applicable, line 10 display P/N beginning in column 1,
the LRU end-item part number beginning in column 6, and the software
modification level in columns 23 and 24.
(e) The P/N is displayed as bbbbbbb--hhsss, where bbbbbbb--hhsss represents the
LRU end-item part number consisting of a seven-digit LRU base part number
(i.e., bbbbbbb), a two-digit hardware configuration number (i.e., hh), and a
three-digit software configuration number (i.e., sss). Dashes are displayed if no
valid data is available.
(f)
The software modification level is displayed as nn, where nn represents up to a
two-character LRU software modification level.
(g) Line 6 and, if applicable, line 11 display S/N beginning in column 1 and the LRU
serial number beginning in column 5. The S/N is diplayed as ssssssss, where
ssssssss represents the LRU serial number. Dashes are displayed if no valid
data is available.
(h) For the Honeywell/Thales MCS system, the two-digit LRU hardware and LRU
serial number must be manually entered through the CMT interface for valid data
to be available for display. This data is stored during an LRU end-item test. All
other numbers reside within the LRU software. For non-Honeywell/Thales
interfacing HPAs, no such data is available to the SDU, therefore, dashes are
displayed for the HPA part/serial numbers.
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Figure 6-12 (Sheet 1).
LRU IDENTIFICATION Page
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Figure 6-12 (Sheet 2).
LRI IDENTIFICATION Page
(i)
The ORT identification is displayed in either lines 4, 5, and 6, or in lines 9, 10,
and 11 depending on where the LRU list falls. Line 4 or line 9, as appropriate,
displays the header ORT IDENTIFICATION left-justified. If the ORT is a
partitioned version, the text, --USER, is added to the end of the header text. Line
5 or line 10, as appropriate, displays the ORT 24-character description as
contained in ORT item xxxiii (refer to Appendix B). Line 6 or line 11, as
appropriate, displays MODIFIED left-justified, if the state of ORT item xxxvii (refer
to Appendix C) is modified. If the state of ORT item xxxvii is unmodified, the
MODIFIED flag is not displayed.
(j)
If the ORT is loaded as separate partitions, the secured ORT identification is
displayed in either lines 4, 5, and 6, or in lines 9, 10, and 11 depending on where
the first ORT ident falls. Line 4 or line 9, as appropriate, displays the header ORT
IDENTIFICATION--SECD left-justified. Line 5 or line 10, as appropriate, displays
the ORT 24-character description as contained in ORT item liii (refer to Appendix
C) for the secured partition. Line 6 or line 11, as appropriate, displays MODIFIED
left-justified, if the state of the ORT secured partition modified flag (refer to
Appendix C) is modified. If the state of the ORT secured partition modified flag is
unmodified, the MODIFIED flag is not displayed.
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(11) TROUBLE SHOOTING DATA Page
(a) General
Access to this page is from the SAT--N (i.e., SATCOM MAINTENANCE)
page. The purpose of this page is to display Class 1 and 2, Level 1,
diagnosed failures reported during the last leg and previous legs. See
Figure 6-13 for example pages.
The Trouble Shooting Data pages display the class 1 and 2 last leg and
previous legs failure details. Failures are displayed in chronological order
(i.e., the most recent detected failure last) with one failure displayed per
page. Flight leg display order is reverse chronological (i.e., flights go back in
time while failures for each individual flight go forward in time). The number
of pages depends on the number of failures to report (up to 64 flight legs or
99 pages).
(b) Data Fields
Line 4
Line 4 displays the date beginning in column 2 and the UTC beginning
in column 8. The date and time are displayed as follows.
The month is displayed as mmm, where mmm represents the month of
the year as JAN, FEB, MAR, APR, MAY JUN, JUL, AUG, SEP, OCT,
NOV, or DEC.
The day is displayed as dd, where dd represents the day of the month
from 01 to 31.
The UTC is displayed as hh:mm, where hh represents the UTC hours
from 00 to 23 and mmm represents the UTC minutes from 00 to 59. The
UTC is the time the failure was stored in the failure memory log on this
flight leg. Dashes are displayed if no valid UTC data is available.
Line 4 displays the header, LEG, beginning in column 15 and the flight
leg count right-justified from column 23.
Line 5
Line 5 displays beginning in column 2 the LRU abbreviated name of up
to five characters that corresponds to the level 1 failure code. The SRU
abbreviated name of up to five characters is displayed beginning in
column 8. If the SRU designation in the failure code is 0, no SRU
abbreviation is displayed. The LRU failure code is displayed as two
hexadecimal digits beginning in column 17. The SRU failure code is
displayed as one hexadecimal digit beginning in column 20. The failure
code is displayed as two hexadecimal digits beginning in column 22.
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Figure 6-13.
TROUBLESHOOTING DATA Page
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Line 6
Line 6 displays the time since power--on (TSPO) header beginning in
column 2, and the LRU power--on counter (POC) header beginning in
column 15. The LRU time since power-on is displayed right-justified
from column 12.
The TSPO is displayed as hhh:mm, where hhh represents the hours of
the elapsed time since the unit powered up from 0 to 999, and mm
represents the minutes portion of the elapsed time from 0 to 59.
Line 6 displays the power-on count value from 0 to 65535 right-justified
from column 23.
Line 7
Line 8
Line 9 displays the headers, CLASS, beginning in column 2, and IFC,
beginning in column 15. The failure class is displayed in column 12. The
intermittent failure count is displayed in column 23.
Line 10
Line 8 displays the headers, PHASE, beginning in column 2, and DC,
beginning in column 15. The flight phase is displayed right-justified from
column 12. If a numbered flight phase is not available, then an a or g is
shown in column 12, as appropriate. The DC state is displayed as DC0,
DC0’, DC1, DC1’, or DC2 right-justified from column 23.
Line 9
Line 7 displays the headers, TEMP, beginning in column 2, and
groundspeed (GSPD), beginning in column 15. The LRU-failed SRU (or
PSU) temperature is displayed right-justified from column 12. Dashes
are displayed if no valid temperature data is available. The GSPD is
displayed right-justified from column 23.
Line 10 displays the header FLTNO beginning in column 2. The flight
number is displayed right-justified from column 12. The aircraft tail
number is displayed right-justified from column 23. Dashes are
displayed if no valid flight number or tail number data is available.
Line 11
Line 11 displays the failure parameter as eight hexadecimal digits
beginning in column 5. The associated parameter is displayed as eight
hexadecimal digits beginning in column 16.
(12) LAST LEG CLASS 3 FAULTS Page
(a) Access to this page is from the SAT--N (CFDS SATCOM Maintenance Menu)
page. The purpose of this page is to display Class 3, Level 1 diagnosed, failures
reported during the last leg. See Figure 6-14 for example pages.
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Figure 6-14.
LAST LEG CLASS 3 FAULTS Page
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(b) The Last Leg Class 3 Faults lists two Class 3 faults per page if Class 3 faults are
present during the last leg. These two sets of lines display Class 3, Level 1
diagnosed, last leg failures. Failures are displayed in chronological order (i.e.,
the most recent detected failure last) with no more than two failures displayed
per page.
(c) The number of LAST LEG CLASS 3 FAULTS pages depends on the number of
failures to report (up to a maximum of 99 pages). When there is an odd number
of failures to report, the odd failure is displayed on a separate page in lines 5, 6,
and 7, and lines 9, 10, and 11 are blank. If there are no failures to report, lines 6,
7, 9, 10, and 11 are blank. Line 5 displays NO FAULT DETECTED beginning in
column 4 if there are no failures to report.
(d) Line 5 and, if applicable, line 9 display the UTC beginning in column 1 and the
ATA number beginning in column 6.
(e) The UTC number is displayed as hh:mm, where hh represents the UTC hours
from 00 to 23, and mm represents the UTC minutes from 00 to 59. The UTC is
the time of the failure reporting as stored in the SDU system failure memory log.
Dashes are displayed if no valid UTC data is available.
(f)
The ATA number is displayed as aaaaaa, where aaaaaa represents the ATA
reference number of the reported failure as specified in paragraph 3.E. for each
type of CFDS. For CFDS type none, no ATA number is displayed.
(13) GROUND REPORT Page
(a) Access to this page is from the SAT--N (i.e., SATCOM MAINTENANCE) page.
The purpose of this page is to display Class 1, 2, or 3, Level 1 diagnosed ground
failures that occurred during the last leg. See Figure 6-15 for example pages.
(b) The Ground Report lists two failures per page if failures are detected during the
last leg. These two sets of lines display Class 1, 2, and 3, Level 1 diagnosed,
last leg failures. Failures are displayed in chronological order (i.e., the most
recent detected failure last) with no more than two failures displayed per page.
(c) The number of GROUND REPORT pages depends on the number of failures to
report (up to 99 pages). When there is an odd number of failures to report, the
odd failure is displayed on a separate page in lines 5, 6, and 7, and lines 9, 10,
and 11 are blank. If there are no failures to report, lines 6, 7, 9, 10, and 11 are
blank. Line 5 displays NO FAULT DETECTED beginning in column 4 if there are
no failures to report.
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Figure 6-15.
GROUND REPORT Page
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(14) GROUND REPORT (TROUBLE SHOOTING DATA) Page
(a) General
Access to this page is from the GROUND REPORT page. The purpose of
this page is to display Class 1, 2, or 3, Level 1 diagnosed ground failures
that occurred during the last leg ground report. See Figure 6-16 for example
pages.
One failure is listed per page if a failure is present. These lines display Class
1, 2, and 3, Level 1 diagnosed, last leg ground report failure details
corresponding to the Level 1 failures from which the troubleshooting data
was initiated. Failures are displayed in chronological order (i.e., the most
recent detected failure last) with one failure displayed per page.
(b) Line 4
Line 4 displays the date beginning in column 2 and the UTC beginning in
column 8. The date and time are displayed as follows.
The month is displayed as mmm, where mmm represents the month of the
year as JAN, FEB, MAR, APR, MAY, JUN, JUL, AUG, SEP, OCT, NOV, or
DEC.
The day is displayed as dd, where dd represents the day of the month from
01 to 31.
The UTC is displayed as hh:mm, where hh represents the UTC hours from
00 to 23 and mm represents the UTC minutes from 00 to 59. The UTC is the
time the failure was stored in the failure memory log on this flight leg.
Dashes are displayed if no valid UTC data is available.
(c) Line 5
Line 5 displays the LRU abbreviated name of up to five characters that
corresponds to the Level 1 failure code. The SRU abbreviated name of up to
five characters is displayed beginning in column 8. If the SRU designation in
the failure code is 0, no SRU abbreviation is displayed. The LRU failure
code is displayed as two hexadecimal digits beginning in column 17. The
SRU failure code is displayed as one hexadecimal digit beginning in column
20. The failure code is displayed as two hexadecimal digits beginning in
column 22.
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Figure 6-16.
GROUND REPORT TROUBLE SHOOTING DATA Page
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(d) Line 6
Line 6 displays the headers, TSPO, beginning in column 2 and, POC,
beginning in column 15. The LRU time since power-on is displayed
right-justified from column 12.
The UTC is displayed as hh:mm, where hh represents the UTC hours from
00 to 23 and mm represents the UTC minutes from 00 to 59. The UTC is the
time the failure was stored in the failure memory log on this flight leg.
Dashes are displayed if no valid UTC data is available.
Line 6 displays the power-on count value from 0 to 65535 right-justified from
column 23.
(e) Line 7
(f)
Line 7 displays the headers, TEMP, beginning in column 2, and GSPD,
beginning in column 15. The LRU-failed SRU (or PSU) temperature is
displayed right-justified from column 12. Dashes are displayed if no valid
temperature data is available. The groundspeed is displayed right-justified
from column 23.
Line 8
Line 8 displays the headers, PHASE, beginning in column 2, and DC,
beginning in column 15. The flight phase is displayed right-justified from
column 12. If a numbered flight phase is not available, then an a or g is
shown in column 12, as appropriate. The DC state is displayed as DC0,
DC0’, DC1, DC1’, or DC2 right-justified from column 23.
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3. Maintenance Computer Interface
A. General
(1) The SDU is designed to interface with the Boeing 747--400 Central Maintenance
Computer (CMC) or the Boeing 777 On--board Maintenance System (OMS), the
Airbus Central Fault Display System (CFDS), and the McDonnell Douglas CFDS in
accordance with guidelines outlined in Boeing documents D220U050 (747--400 CMC
-- release date 3 June 1991) and D243W201--1 (777 OMS -- release date 30 October
1992) and Airbus document ABD0048 issue C, all of which supersede ARINC 604 for
their respective applications.
(2) The Boeing maintenance computers (i.e., 747--400 CMC and 777 OMS) are virtually
indistinguishable to the SDU. The operations to support these two systems are very
similar and, therefore, are presented together. The operations to support the Airbus
and McDonnell Douglas maintenance computers are very similar and, therefore, are
presented together. The SDU determines the aircraft type on which the SDU is
installed, and then supports only the functionality required by that particular system.
B. Boeing 747--400 CMC/777 OMS
(1) General
(a) The CMC and SDU communicate with each other through an ARINC 429 data
bus using ARINC 429 words.
(b) When the SDU receives the standard ground test command containing its
equipment ID and source destination identifier (SDI), the SDU responds by
setting the command word (ARINC label 350) acknowledge bit to ACK for four
seconds. The SDU initiates a system-wide functional test. As soon as possible
during the execution of the functional test, the SDU sets the SSM for ARINC
label 350 to functional test.
(2) CMC to SDU Communication -- Automatic Fault Reporting
(a) The CMC and SDU communicate with each other through an ARINC 429 data
bus using ARINC 429 words.
(b) When the SDU receives the standard ground test command containing its
equipment ID and source destination identifier (SDI), the SDU responds by
setting the command word (ARINC label 350) acknowledge bit to ACK for 4
seconds. The SDU then initiates a system-wide functional test. As soon as
possible during the execution of the functional test, the SDU sets the SSM for
ARINC label 350 to functional test.
(c) At the conclusion of the functional test, the SDU builds the fault summary words
using ARINC labels 350 thru 354 by mapping currently active failures to the
appropriate bits in the words. Once the words are built they are latched for 30
seconds, then the SDU returns to automatic fault reporting. The SDU
continuously transmits the fault summary words to the CMC at a rate of 1 to 2
Hz, with the SSM bits set to normal operation during reporting of the test results.
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(3) CMC Interactive Mode
(a) The SDU supports configuration data in CMC interactive mode for a Boeing 777
installation. If the CMC transmits a configuration data interactive mode command
addressed to the SDU on ARINC label 227, the SDU processes the command by
supplying the first page of configuration information and then resumes automatic
mode processing. The configuration data command is used to display
configuration information for the SATCOM LRUs (SDU and HPAs). The SDU
responds to the configuration data command from the automatic mode.
(b) The SDU does not support ground test and shop faults in CMC interactive mode.
If the CMC transmits a ground test or shop faults interactive mode command
addressed to the SDU on label 227, the SDU ignores the command.
(4) Configuration Data Messages
(a) General
When configuration data is commanded, the MCS configuration data
page(s) is(are) displayed. These data pages display installed LRUs as
determined by the SDU system configuration pin settings with their
associated part/serial number data. These lines also display the ORT
identification along with modification status. Figure 6-17 supplies an
example of the configuration data page.
The ORT 24-character description as contained in ORT item xxxiii is
displayed. For non-777 installations, the text is limited to 20 characters per
line.
(b) USER ORT STATUS
This displays MODIFIED if the state of the ORT user partition is modified,
otherwise no status or header is displayed.
(c) SECD ORT IDENTIFICATION
This is the 24-character description as contained in ORT item liii. For
non-777 installations, the text is limited to 20 characters per line.
(d) SECURED ORT STATUS
This displays MODIFIED if the state of the ORT secured partition is modified,
otherwise, no status or header is displayed. For software package C3.5, the
ORT is not partitioned so only a single ORT IDENTIFICATION is supplied for
the ORT display lines.
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Figure 6-17.
Configuration Data Pages for Boeing 777 Installation
(e) LRU PART NUMBER
(f)
The part numbers for the LRUs installed are displayed as follows. The word
LRU is displayed, which is substituted with the appropriate LRU acronym.
The LRU part number is displayed as bbbbbbb-hhsss, where
bbbbbbb-hhsss represents the LRU end item part number consisting of a
seven-digit LRU base part number (bbbbbbb), a two-digit hardware
configuration number (hh), and a three-digit software configuration number
(sss). Dashes are displayed if no valid data is available.
LRU SERIAL NUMBER
The serial numbers of the LRUs installed are displayed as follows. The word
LRU is displayed, which is substituted with the appropriate LRU acronym.
The LRU serial number is displayed as ssssssss, where ssssssss represents
the LRU serial number. Dashes are displayed if no valid data is available.
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(g) SDU S/W PART NUMBER
This displays the software part number that corresponds to the software
load. The configuration data page includes the header SDU CONFIG
STRAPS and the raw strap setting for the current installation.
(5) Standard Ground Test (Non--interactive)
(a) When a standard test on a CMC ground test menu is selected, the CMC
commands the SDU to start a standard ground test. The SDU prevents the CMC
commanded standard ground test while the aircraft is airborne. The SDU starts a
system-wide PAST after it has responded to the receipt of a standard ground test
command from the CMC.
(b) At the end of the CMC-commanded PAST, the SDU builds labels 350 thru 354
fault summary words by mapping PAST-detected SATCOM subsystem failures to
the appropriate bits. The SDU continuously transmits these fault summary words
to the CMC at a rate of 1 to 2 Hz, with the SSM set to Normal Operation, during
reporting of the test results.
C. Airbus/Douglas CFDS
(1) General
(a) The CFDS uses a centralized fault display interface unit (CFDIU) as an interface
between the SDU and the SCDU. Throughout these paragraphs the acronym
CFDIU is used to include both the A320 CFDS and the A340 CMC.
(b) When the SDU is installed on an Airbus or McDonnell Douglas aircraft with a
CFDS, it supports the normal mode and interactive mode as required by the
CFDS.
(2) CFDIU to SDU Communication
(a) The CFDIU communicates with the SDU through an ARINC 429 data bus using
ARINC 429 words.
(3) SDU to CFDIU Communication
(a) The SDU supports both the normal mode and the interactive mode, as required
by the CFDS. The SDU also transmits the LRU part number and serial number
and ORT identification data blocks to the CFDIU.
(b) The LRU/ORT identification data records make up the LRU/ORT identification
data blocks. Each LRU data record contains the LRU acronym, part number, and
serial number. Each ORT identification data record contains the ORT
IDENTIFICATION header, the ORT 24 character description, and the state of the
modified flag.
(4) Normal Mode Failure Messages
(a) As specified, the SDU transmits failure messages and LRU/ORT identification
information while operating in the normal mode. The following paragraphs
defined the contents of these reports.
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(b) Once a failure is reported in the normal mode, the failure remains in the report
for that entire flight, regardless of whether the failure is cleared. As new failures
are reported, they are added to the beginning of the report (i.e., the report is in
reverse chronological order, bearing in mind the CFDS considers the time of the
failure to be the time it is first reported on this flight leg rather than when it first
occurs).
(c) In addition to latching the failures, the contents of the normal mode report
depend on the failure class and when it occurs in relationship to other failures
against the same LRU. Level I failures against the same LRU reported in the
normal mode are not to be transmitted more than once unless they are an upper
class and the upper class failure occurs after the lower class failure(s). Once a
report is sent to the CFDIU during the normal mode for the current flight, the
SDU does not change the content or order except to add new failure messages,
as appropriate to the beginning of the report.
(d) The McDonnell Douglas CFDIU does not decode the normal mode report until
the CFDIU detects an increase in the block word count. However, unlike the
Airbus CFDIU, the McDonnell Douglas CFDIU decodes the entire report. After
sending an All Call DC2 command for a new flight leg, the Airbus CFDIU delays
processing the normal mode report for about 30 seconds before regarding the
report as pertaining to the new flight leg.
(e) The SDU transmits the names of the installed LRUs, as determined by the
system configuration pin settings, along with their associated part/serial
numbers. At the end of this LRU transmission, the SDU transmits the ORT
identification with a modification status. The LRU names can be transmitted in
any order. Transmission of an HPA LRU part/serial number uses the same
criteria as the display of HPA data.
(5) Interactive Mode
(a) The CFDIU supplies for two-way communication between the SCDU and the
SDU, which is referred to as the interactive mode. When the SDU operates in the
interactive mode, it is responsible for all information displayed on the CFDS
maintenance pages, with exception of the scratchpad. The SDU enters the
interactive mode upon receiving an ENQ command from the CFDIU when the
aircraft is on the ground.
D. Central Aircraft Information and Maintenance System
(1) The central aircraft information and maintenance system (CAIMS) is a distributive
maintenance system where each member system performs its own built--in test (BIT)
and stores its own faults. Also, each system supplies real--time status information on
the health of each of its LRUs and their interfaces. The member systems support
CAIMS during normal operation and during on--ground maintenance.
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(2) In the normal operation mode, member systems gather and store fault data when
equipment failure occurs during normal operation. This is typically performed by
continuous BIT and power--up BIT, with identified faults stored in the member
systems non--volatile memory (NVM). The CAIMS does not store fault information for
member systems, but the fault warning processor (FWP) supplies fault event data,
such as: flight leg, date, time, fault zone, and aircraft serial number information that is
stored with the fault in the member systems NVM.
(3) In the maintenance mode, the CAIMS is active and is called the on--board
maintenance system (CAIMS OMS). The CAIMS OMS is the ground maintenance
function and is accessible through communication link to a portable maintenance
access terminal (PMAT). With the PMAT, the aircraft maintenance crew can retrieve
stored fault data from a member system. For member systems, the CAIMS OMS
displays fault information, commands BITE test, and displays real--time data for
status displays, and commands the download of NVM fault data.
E.
Level I Failure Messages and ATA Reference Numbers
(1) The Level I failure messages and ATA reference numbers that are available for
transmittal in the CFDS normal mode, for display in the CFDS interactive mode, and
for display on SCDU accessed maintenance pages are specified in the following
paragraphs for each CFDS type installed. Level I failure messages are intended for
use by line maintenance crews. Therefore, the failure messages are designed to be
LRU-based and only supply LRU-level identification.
(2) The Level 1 failure codes are two-digit hexadecimal numbers that define the LRU,
data communication bus, or miscellaneous interface signal where a failure, bus
inactivity, or signal error has been determined to have occurred. When multiple LRUs
are suspect, the most likely LRU is listed first followed by the next most likely LRU,
separated by a slash. The ATA number listed is for the first suspect LRU. Additional
text can be supplied at the end to help clarify the failure message.
• Table 6-18 describes the Level I failure messages and ATA reference numbers to
use for display on the SCDU accessed maintenance pages when the installed
CFDS type is a Boeing CMC. Also shown is the CMC message ID which is
displayed by the CMC in response to the Level I failure messages (refer to the
OEM’s maintenance manual and fault isolation manual).
• Table 6-19 and Table 6-20 describe the Level I failure messages and ATA
reference numbers to use for transmittal in the CFDS normal mode, and the CFDS
interactive mode pages displayed when the installed CFDS type is an Airbus.
Table 6-19 is for the SDU (single configuration) or SDU No. 1 (dual configuration),
and Table 6-20 is for SDU No. 2 (dual configuration) as determined by the settings
of configuration pins TP12E and TP12F.
• Table 6-21 describes the Level I failure messages and ATA reference numbers to
use for transmittal in the CFDS normal mode, and the CFDS interactive mode
pages displayed when the installed CFDS type is a McDonnell Douglas.
• For CFDS type none, the Level I failure messages displayed on the SCDU
accessed maintenance pages are the same as those specified for Boeing (refer to
Table 6-18). However, no ATA reference numbers are displayed.
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(3) For Level I codes identified as not applicable in the tables, the SDU does not report
the failure on that particular interface (i.e., CFDS normal and interactive modes or
SCDU accessed maintenance pages as appropriate). Where TBD is used in the
Level I failure message column, it is coded as literally read. For failures that occur
that are undefined in the tables, the SDU does not report the failure on that particular
interface.
Table 6-18.
Failure
Code
Boeing Level I Failure Messages and ATA Reference Numbers
SCDU Accessed Maintenance Pages
ATA Number
CMC
Message ID
01
SDU
232500
23205
02
OTHER SDU INCOMPATIBILITY
232500
23205
03
HSU
232500
04
HPA--HI GAIN
HPA--HI GAIN
07
[IGA]
232500
23207
HPA--LO GAIN
232500
23209
0A
HI POWER RELAY
232500
23218
0D
LNA/DIP--(TOP/PORT)
232500
23210
0F
LNA/DIP--STBD
232500
23211
10
LNA/DIP--LO GAIN
232500
23212
13
BSU--(TOP/PORT)
232500
23213
15
BSU--STBD
232500
23214
1A
IN GAIN ANTENNA--TOP
HI GAIN ANTENNA--(TOP/PORT)
232500
23215
1C
HI GAIN ANTENNA--STBD
232500
23216
1F
LO GAIN ANTENNA
232500
23225
21
MCDU1
346100
22
MCDU2
346100
23
MCDU3
346100
33
(ACARS MU/CMU)1
232700
23219
34
(ACARS MU/CMU)2
232700
23219
35
IRS--PRI
342100
34222
36
IRS--SEC
342100
34224
37
RESERVED
38
RESERVED
[HGA]
[IGA]
[HGA]
23--20--35
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SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL
MCS-4200/7200
TEMPORARY REVISION NO. 23-1
INSERT PAGE 43 OF 53 FACING PAGE 6-96.
Reason:
To add a new failure code, 0B, to Table 6-18 between failure codes 0A and 0D.
Failure code 0B is added as follows:
Table 6-18.
Failure
Code
0B
Boeing Level I Failure Messages and ATA Reference Numbers
SCDU Accessed Maintenance Pages
HDM
ATA Number
CMC
Message ID
232500
23-20-35
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Boeing Level I Failure Messages and ATA Reference Numbers (cont)
Table 6-18.
Failure
Code
SCDU Accessed Maintenance Pages
ATA Number
39
RESERVED
3D
FMC1
346100
3E
FMC2
346100
40
ARINC 429 ICAO ADDRESS
42
CMC
Message ID
None
23251
CTU
231900
23235
43
(CFS/CPDF)
233200
50
HSU/SDU
232500
52
(CFS/CPDF)/SDU
233200
53
(ACARS MU/CMU)1/SDU
232700
23219
54
CTU/SDU
231900
23235
55
MCDU1/SDU
346100
56
MCDU2/SDU
346100
57
(ACARS MU/CMU)2/SDU
232700
23235
59
CMC/SDU
454500
23201
5A
IRS--PRI/SDU
342100
23222
5B
IRS--SEC/SDU
342100
23224
5C
HPA--IN GAIN/SDU
HPA--HI GAIN/SDU
232500
23226
5F
HPA--LO GAIN/SDU
232500
23225
62
BSU--(TOP/PORT)/SDU
232500
23213
64
BSU--STBD/SDU
232500
23214
66
MCDU3/SDU
346100
67
RESERVED
68
RESERVED
6A
RESERVED
6C
RESERVED
6D
RESERVED
6E
RESERVED
6F
RESERVED
[IGA]
[HGA]
23--20--35
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Boeing Level I Failure Messages and ATA Reference Numbers (cont)
Table 6-18.
Failure
Code
SCDU Accessed Maintenance Pages
ATA Number
71
OTHER SDU/THIS SDU
232500
73
FMC1/SDU
346100
74
FMC2/SDU
346100
80
RESERVED
82
RESERVED
88
RESERVED
90
SDU M--CTRL/HPA--IN GAIN
SDU M--CTRL/HPA--HI GAIN
96
[IGA]
CMC
Message ID
232500
23246
SDU M--CTRL/HPA--LO GAIN
232500
23248
98
SDU M--CTRL/BSU--(TOP/PORT)
232500
23249
9A
BSU--STBD XTALK/BSU--PORT
232500
23252
9C
SDU M--CTRL/BSU--STBD
232500
23250
9D
BSU--PORT XTALK/BSU--STBD
232500
23253
9E
SDU/HSU
232500
A6
HSU ETHERNET PORT 1
232500
A7
HSU ETHERNET PORT 2
232500
A8
HSU ISDN PORT 1
232500
A9
HSU ISDN PORT 2
232500
C0
WRG:CONFIG PIN PROG/SDU
232500
C1
SDU WOW MISCOMPARE
C2
SDU/OTHER SDU SELECT--DISABLE DISCRETE
232500
C3
WRG:ICAO ADDRESS PIN PROG/SDU
232500
23251
C4
TX PATH VSWR--IN GAIN
TX PATH VSWR--HI GAIN
232500
23257
C5
WRG:CONFIG PIN PROG/SDU OWNER REQS
232500
C6
TX PATH VSWR--LO GAIN
232500
23216
C7
HPA--HI GAIN/OVER TEMPERATURE
HPA--HI GAIN/OVER TEMPERATURE
232500
23247
C8
BAD DATA FROM GROUND EARTH STATION
[HGA]
23236
N/A
[IGA]
[HGA]
[IGA]
[HGA]
None
23--20--35
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MCS--4200/7200 Multi--Channel SATCOM System
Table 6-18.
Boeing Level I Failure Messages and ATA Reference Numbers (cont)
Failure
Code
SCDU Accessed Maintenance Pages
ATA Number
CMC
Message ID
C9
HPA--LO GAIN/OVER TEMPERATURE
232500
23254
CA
SDU/LNA/DIP--LO GAIN
232500
23237
CB
WRG:SDI PIN PROG/HPA--IN GAIN
WRG:SDI PIN PROG/HPA--HI GAIN
CC
WRG:SDI PIN PROG/HPA--HI GAIN
CD
SDU (POC/TOTC) DATA RESET
CE
RESERVED
CF
HPA--IN GAIN (POC/TOTC) DATA RESET
HPA--HI GAIN (POC/TOTC)DATA RESET
D0
HPA--LO GAIN (POC/TOTC) DATA RESET
D1
WRG:SDI PIN PROG/HPA--IN GAIN
WRG:SDI PIN PROG/HPA--HI GAIN
D2
WRG:SDI PIN PROG/HPA--LO GAIN
232500
D3
WRG:SDI PIN PROG/BSU--(TOP/PORT)
232500
D4
WRG:SDI PIN PROG/BSU--STBD
232500
D5
SDU COAX/HPA--IN GAIN
SDU COAX/HPA--HI GAIN
D6
SDU COAX/HPA--LO GAIN
D7
RESERVED
D8
[IGA]
[HGA]
232500
232500
None
[IGA]
[HGA]
None
None
[IGA]
[HGA]
[IGA]
232500
232500
23237
232500
23237
LNA/DIP/ (SDU)--(TOP/PORT)
232500
23236
D9
LNA/DIP/ (SDU)--STBD
232500
23236
DA
LNA/DIP/ (SDU)--LO GAIN
232500
23236
DB
LO GAIN SUBSYSTEM
232500
DC
NO ACTIVE ACARS MU/CMU
232700
DD
SDU OWNER REQS -- SECURED
None
DE
SDU OWNER REQS -- USER
None
DF
IN GAIN SUBSYSTEM
HI GAIN SUBSYSTEM
E0
RESERVED
E1
BAD HSU DISABLE DISCRETE
[HGA]
[IGA]
[HGA]
232500
232500
23--20--35
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Table 6-18.
Boeing Level I Failure Messages and ATA Reference Numbers (cont)
Failure
Code
SCDU Accessed Maintenance Pages
ATA Number
E4
HSU/SDU INTERFACE VER INCOMPATIBILITY
232500
E6
HSU/HPA TX RF PATH
232500
E8
DLNA/HSU RX RF PATH
232500
EC
WRG: CONFIG PIN PROG/HSU
232500
ED
WRG: CONFIG PIN PROG/HSU
SDU OWNER REQS
232500
EE
WRG: FWD ID PIN PROG/HSU
232500
FE
POWER SUPPLY INTERRUPT
None
Table 6-19.
Failure
Code
01
Airbus Level I (SDU No. 1) Failure Messages and ATA No.
SDU/SDU No. 1 -- CFDS Normal and Interactive Modes
SDU1(105RV1)
SDU1(5RV1)
02
SDU2(105RV2)
SDU2(5RV2) INCOMPATIBILITY
03
HSDU1 (63RV1)
04
HPA1(110RV1)
CMC
Message ID
ATA Number
[IGA]
232834
[HGA]
232834
[IGA]
232834
[HGA]
232834
232839
HPA--HI GAIN(7RV1)
[IGA]
232831
[HGA]
232831
07
HPA--LO GAIN(9RV)
232835
0A
HI POWER RELAY(21RV)
232842
0D
DLNA1(119RV1)
[IGA]
232838
DLNA--TOP(19RV1)
[Top Mount]
232838
DLNA--L(20RV1)
[Conformal]
232837
0F
DLNA--R(20RV2)
[Conformal]
232837
10
DLNA--LO GAIN(14RV)
13
BSU(8RV1)
[Top Mount]
232846
BSU--L(15RV1)
[Conformal]
232844
BSU--R(15RV2)
[Conformal]
232844
15
232836
23--20--35
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SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL
MCS-4200/7200
TEMPORARY REVISION NO. 23-1
INSERT PAGE 44 OF 53 FACING PAGE 6-100.
Reason:
To add a new failure code, 0B, to Table 6-19 between failure codes 0A and 0D.
Failure code 0B is added as follows:
Table 6-19.
Failure
Code
0B
Airbus Level I (SDU No. 1) Failure Messages and ATA No.
SDU/SDU No. 1 – CFDS Normal and Interactive Modes
HDM
ATA Number
232832
23-20-35
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Page 44 of 53
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MCS--4200/7200 Multi--Channel SATCOM System
Airbus Level I (SDU No. 1) Failure Messages and ATA No. (cont)
Table 6-19.
Failure
Code
1A
SDU/SDU No. 1 -- CFDS Normal and Interactive Modes
[IGA]
232813
HI GAIN ANTENNA--TOP(16RV1)
[Top Mount]
232813
HI GAIN ANTENNA--L(17RV)
[Conformal]
232812
1C
HI GAIN ANTENNA--R(18RV)
[Conformal]
232812
1F
LO GAIN ANTENNA(13RV)
21
MCDU1(2CA1)
[A330/A340]
228212
MCDU1(3CA1)
[A320]
228212
MCDU2(2CA2)
[A330/A340]
228212
MCDU2(3CA2)
[A320]
228212
MCDU3(2CA3)
[A330/A340]
228212
MCDU3(3CA3)
[A320]
228212
ATSU1(1TX1)
[ATSU]
462134
[A320 ACARS]
232434
[A330/A340 ACARS]
232434
[ATSU]
462134
[A320 ACARS]
232434
[A330/A340 ACARS]
232434
22
23
33
ANTENNA1(116RV1)
ATA Number
ACARS MU(1RB)
ACARS MU1(1RB1)
34
232811
ATSU2 (1TX2)
ACARS MU2
ACARS MU2(1RB2)
35
ADIRU1(1FP1)
341234
36
ADIRU2(1FP2)
341234
37
RESERVED
N/A
38
RESERVED
N/A
39
RESERVED
N/A
3D
FMGC1(1CA1)
FMGEC1(1CA1)
3E
228334
[A330/A340]
228334
[A320]
228334
[A330/A340]
228334
FMGC2(1CA2)
FMGEC2(1CA2)
40
[A320]
ARINC 429 ICAO
N/A
23--20--35
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Page 6--101
15 Jul 2006
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL
MCS--4200/7200 Multi--Channel SATCOM System
Table 6-19.
Failure
Code
42
43
Airbus Level I (SDU No. 1) Failure Messages and ATA No. (cont)
SDU/SDU No. 1 -- CFDS Normal and Interactive Modes
ATA Number
CTU--CU CEPT--E1 BUS/SDU1 (105RV1)
[IGA A320]
233500
CTU--CU CEPT--E1 BUS/SDU1 (105RV1)
[IGA A330/A340]
239200
CTU--CU CEPT--E1 BUS/SDU1 (5RV1)
[HGA A320]
233500
CTU--CU CEPT--E1 BUS/SDU1 (5RV1)
[HGA A330/A340]
239200
IFE 429 BUS/SDU1 (5RV1)
[A330/A340 HGA]
233000
IFE 429 BUS/SDU1 (105RV1)
[A330/A340 HGA]
IFE 429 BUS/SDU1 (105RV1)
[A320 IGA]
IFE 429 BUS/SDU1 (5RV1)
[A320 HGA]
50
HSDU1 (63RV1)/SDU1 (5RV1)
52
IFE 429 BUS/SDU1 (5RV1)
[A330/A340 HGA]
IFE 429 BUS/SDU1 (105RV1)
[A330/A340 HGA]
IFE 429 BUS/SDU1 (105RV1)
[A320 IGA]
53
233000
ATSU1 (1TX1)/SDU1(105RV1)
[IGA ATSU]
462134
[HGA ATSU]
462134
[IGA A320 ACARS]
232434
[IGA A330/A340 ACARS]
232434
[HGA A320 ACARS]
232434
[HGA A330/A340 ACARS]
232434
CTU--CU CEPT--E1 BUS/SDU1(105RV1)
[IGA A320]
233500
CTU--CU CEPT--E1 BUS/SDU1(105RV1)
[IGA A330/A340]
239200
CTU--CU CEPT--E1 BUS/SDU1(5RV1)
[HGA A320]
233500
CTU--CU CEPT--E1 BUS/SDU1(5RV1)
[HGA A330/A340]
239200
[IGA A330/A340]
228212
[HGA A330/A340]
228212
[IGA A320]
228212
[HGA A320]
228212
[IGA A330/A340]
228212
[HGA A330/A340]
228212
IGA A320
228212
HGA A320
228212
ACARS MU1 (1RB1)/SDU1(105RV1)
ACARS MU (1RB)/SDU1(5RV1)
ACARS MU1 (1RB1)/SDU1(5RV1)
MCDU1(2CA1)/SDU1(105RV1)
MCDU1(2CA1)/SDU1(5RV1)
MCDU1(3CA1)/SDU1(105RV1)
MCDU(3CA1)/SDU1(5RV1)
56
233000
[A320 HGA]
ACARS MU (1RB)/SDU1(105RV1)
55
232839
IFE 429 BUS/SDU1 (5RV1)
ATSU1 (1TX1)/SDU1(5RV1)
54
233000
MCDU2(2CA2)/SDU1(105RV1)
MCDU2(2CA2)/SDU1(5RV1)
MCDU2(3CA2)/SDU1(105RV1)
MCDU2(3CA2)/SDU1(5RV1)
23--20--35
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Page 6--102
15 Jul 2006
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL
MCS--4200/7200 Multi--Channel SATCOM System
Airbus Level I (SDU No. 1) Failure Messages and ATA No. (cont)
Table 6-19.
Failure
Code
57
SDU/SDU No. 1 -- CFDS Normal and Interactive Modes
ATSU2 (1TX2)/SDU1(105RV1)
ATA Number
[IGA ATSU]
462134
[HGA ATSU]
462134
[IGA A320 ACARS]
232434
[IGA A330/A340 ACARS]
232434
[HGA A320 ACARS]
232434
[HGA A330/A340 ACARS]
232434
CFDIU(1TW)/SDU1(105RV1)
[IGA A320]
313234
CMC1(1TM1)/SDU1(105RV1)
[IGA A330/A340]
451334
CFDIU(1TW)/SDU1(5RV1)
[HGA A320]
313234
CMC1(1TM1)/SDU1(5RV1)
[HGA A330/A340]
451334
[IGA]
341234
[HGA]
341234
[IGA]
341234
[HGA]
341234
[IGA]
232831
HPA--HI GAIN(7RV1)/SDU1(5RV1)
[HGA]
232831
HPA--LO GAIN(9RV)/SDU1(5RV1)
[HGA + LGA]
232835
HPA--LO GAIN(9RV)/SDU1(105RV1)
[IGA + LGA]
232835
BSU(8RV1)/SDU1(5RV1)
[Top Mount]
232846
BSU--L(15RV1)/SDU1(5RV1)
[Conformal]
232844
64
BSU--R(15RV2)/SDU1(5RV1)
[Conformal]
232844
66
MCDU3(2CA3)/SDU1(105RV1)
[IGA A330/A340]
228212
[HGA A330/A340]
228212
[IGA A320]
228212
[HGA A320]
228212
ATSU2 (1TX2)/SDU1(5RV1)
ACARS MU2/SDU1(105RV1)
ACARS MU2 (1RB2)/SDU1(105RV1)
ACARS MU2/SDU1(5RV1)
ACARS MU2 (1RB2)/SDU1(5RV1)
59
5A
ADIRU1(1FP1)/SDU1(105RV1)
ADIRU1(1FP1)/SDU1(5RV1)
5B
ADIRU2(1FP2)/SDU1(105RV1)
ADIRU2(1FP2)/SDU1(5RV1)
5C
5F
62
HPA1 (110RV1)/SDU1(105RV1)
MCDU3(2CA3)/SDU1(5RV1)
MCDU3(3CA3)/SDU1(105RV1)
MCDU3(CA3)/SDU1(5RV1)
67
RESERVED
68
RESERVED
6A
RESERVED
6C
RESERVED
6D
RESERVED
23--20--35
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Page 6--103
15 Jul 2006
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL
MCS--4200/7200 Multi--Channel SATCOM System
Airbus Level I (SDU No. 1) Failure Messages and ATA No. (cont)
Table 6-19.
Failure
Code
SDU/SDU No. 1 -- CFDS Normal and Interactive Modes
6E
RESERVED
6F
RESERVED
71
SDU2(105RV2)CROSSTALK BUS/SDU1
(105RV1)
ATA Number
[IGA]
232834
[HGA]
232834
[IGA A320]
228334
[IGA A330/A340]
228334
[HGA A320]
228334
[HGA A330/A340]
228334
[IGA A320]
228334
[IGA A330/A340]
228334
[HGA A320]
228334
[HGA A330/A340]
228334
[IGA]
232834
[HGA]
232834
SDU1(5RV1) BUS M--CTRL/HPA--LO
GAIN(9RV)
[HGA+LGA]
232834
SDU1(105RV1) BUS M--CTRL/HPA--LO
GAIN(9RV)
[IGA+LGA]
232834
SDU1(5RV1) BUS M--CTRL/BSU(8RV1)
[Top Mount]
232834
SDU1(5RV1) BUS M--CTRL/BSU--L(15RV1)
[Conformal]
232834
9A
BSU--R (15RV2) XTALK BUS/BSU--L(15RV1)
[Conformal]
232844
9C
SDU1(5RV1) BUS M--CTRL/BSU--R(15RV2)
[Conformal]
232834
9D
BSU--L (15RV1) XTALK BUS/BSU--R(15RV2)
[Conformal]
232844
9E
SDU1 (5RV1) /HSDU1 (63RV1)
9F
Not applicable for package 6.0 and beyond
SDU2(5RV2)CROSSTALK BUS/SDU1
5RV1)
73
FMGC1(1CA1)/SDU1(105RV1)
FMGEC1(1CA1)/SDU1(105RV1)
FMGC1(1CA1)/SDU1(5RV1)
FMGEC1(1CA1)/SDU1(5RV1)
74
FMGC2(1CA2)/SDU1(105RV1)
FMGEC2(1CA2)/SDU1(105RV1)
FMGC2(1CA2)/SDU1(5RV1)
FMGEC2(1CA2)/SDU1(5RV1)
80
RESERVED
82
RESERVED
88
RESERVED
90
SDU1(105RV1) BUS M--CTRL/HPA1(110RV1)
SDU1(5RV1) BUS M--CTRL/HPA--HI
GAIN(7RV1)
96
98
232834
N/A
23--20--35
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Page 6--104
15 Jul 2006
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL
MCS--4200/7200 Multi--Channel SATCOM System
Table 6-19.
Failure
Code
A1
Airbus Level I (SDU No. 1) Failure Messages and ATA No. (cont)
SDU/SDU No. 1 -- CFDS Normal and Interactive Modes
SDU1(105RV1)/MCDU1(2CA1)
SDU1(5RV1)/MCDU1(2CA1)
A2
SDU1(105RV1).MCDU2(2CA2)
SDU1(5RV1)/MCDU2(2CA2)
A3
SDU1(105RV1)/MCDU3(2CA3)
SDU1(5RV1)/MCDU3(2CA3)
ATA Number
[IGA]
228212
[HGA]
228212
[IGA]
228212
[HGA]
228212
[IGA]
228212
[HGA]
228212
A6
ESU(101RF) ETHERNET 1/HSDU1(63RV1)
464131
A7
ESU(101RF) ETHERNET 2/HSDU1(63RV1)
464131
A8
ESU(101RF) ISDN 1/HSDU1(63RV1)
464131
A9
ESU(101RF) ISDN 2/HSDU1(63RV1)
464131
C0
WRG:CONFIG PIN PROG/SDU1(105RV1)
[IGA]
232800
[HGA]
232800
[IGA]
323171
[HGA]
323171
[IGA]
232834
SDU1(5RV1) SEL--DISABLE
DISCRETE/SDU2(5RV2)
[HGA]
232834
WRG:ICAO ADDRESS PIN
PROG/SDU1(105RV1)
[IGA]
232800
WRG:ICAO ADDRESS PIN
PROG/SDU1(5RV1)
[HGA]
232800
[IGA]
232831
[HGA]
232831
[IGA]
232800
[HGA]
232800
WRG:CONFIG PIN PROG/SDU1(5RV1)
C1
LGCIU1(5GA1)/LGCIU2(5GA2)/SDU1(105RV1)
LGCIU1(5GA1)/LGCIU2(5GA2)/SDU1(5RV1)
C2
C3
C4
SDU1(105RV1) SEL--DISABLE
DISCRETE/SDU2(105RV2)
HPA1 (110RV1)/VSWR
HPA--HI GAIN(7RV1)/VSWR
C5
WRG:CONFIG PIN PROG/SDU1(105RV1)
OWNER REQS DB
WRG:CONFIG PIN PROG/SDU1(5RV1)
OWNER REQS DB
C6
HPA--LO GAIN(9RV)/VSWR
C7
HPA(110RV1)/OVER TEMPERATURE
232835
HPA--HI GAIN(7RV1)/OVER TEMPERATURE
[IGA]
232831
[HGA]
232831
23--20--35
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Page 6--105
15 Jul 2006
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL
MCS--4200/7200 Multi--Channel SATCOM System
Airbus Level I (SDU No. 1) Failure Messages and ATA No. (cont)
Table 6-19.
Failure
Code
C8
SDU/SDU No. 1 -- CFDS Normal and Interactive Modes
ATA Number
SDU1(105RV1)/BAD DATA FROM GROUND
STATION
SDU1(5RV1)/BAD DATA FROM GROUND
EARTH STATION
C9
HPA--LO GAIN(9RV)/OVER TEMPERATURE
CA
SDU1(5RV1)CTRL DISCRETE/DLNA--LO
GAIN(14RV)
SDU1(105RV1)CTRL DISCRETE/DLNA--LO
GAIN(14RV)
CB
[IGA]
232834
[HGA]
232834
232835
[HGA+LGA]
232834
[IGA+LGA]
232834
[IGA]
232800
[HGA]
232800
WRG:SDI PIN PROG/HPA1(110RV1)
WRG:SDI PIN PROG/HPA--HI GAIN(7RV1)
CC
WRG:SDI PIN PROG/HPA--LO GAIN(9RV)
232800
CD
N/A
CE
RESERVED
CF
N/A
N/A
D0
N/A
N/A
D1
WRG:SDI PIN PROG/HPA1(110RV1)
232800
WRG:SDI PIN PROG/HPA--HI GAIN(7RV1)
232800
D2
WRG:SDI PIN PROG/HPA--LO GAIN(9RV)
232800
D3
WRG:SDI PIN PROG/BSU(8RV1)
[Top Mount]
232800
WRG:SDI PIN PROG/BSU--L(15RV1)
[Conformal]
232800
D4
WRG:SDI PIN PROG/BSU--R(15RV2)
[Conformal]
232800
D5
SDU1(105RV1)/TXCOAX
[IGA]
232834
[HGA]
232834
[IGA+LGA]
232834
[HGA+LGA]
232834
[IGA]
232834
[HGA]
232834
N/A
SDU1(5RV1)/TXCOAX
D6
SDU1 (105RV1)/TXCOAX
SDU1(5RV1)/TXCOAX
D7
RESERVED
D8
SDU1(105RV1)/RXCOAX
SDU1(5RV1)/RXCOAX
D9
SDU2(5RV1)/RXCOAX
DA
SDU1(105RV1)/RXCOAX
232834
[IGA+LGA]
23--20--35
 Honeywell International Inc. Do not copy without express permission of Honeywell.
232834
Page 6--106
15 Jul 2006
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL
MCS--4200/7200 Multi--Channel SATCOM System
Airbus Level I (SDU No. 1) Failure Messages and ATA No. (cont)
Table 6-19.
Failure
Code
SDU/SDU No. 1 -- CFDS Normal and Interactive Modes
SDU1(5RV1)/RXCOAX
DB
LO GAIN ANTENNA(13RV)
LOG ON FAILURE
DC
N/A
DD
SDU1(105RV1) OWNER REQS DB SECURED
PARTITION
ATA Number
[HGA+LGA]
232811
N/A to Airbus
[IGA]
232834
[HGA]
232834
[IGA]
232834
[HGA]
232834
SDU1(105RV1)
LOG ON FAILURE
[IGA]
232834
SDU1(5RV1)
LOG ON FAILURE
[HGA]
232834
SDU1(5RV1) OWNER REQS DB SECURED
PARTITION
DE
SDU1(105RV1) OWNER REQS DB USER
PARTITION
SDU1(5RV1) OWNER REQS DB USER
PARTITION
DF
232834
E0
RESERVED
E1
SDU1(5RV1) DISCRETE/HSDU1(63RV1)
E2
N/A
N/A
E3
N/A
N/A to Airbus
E4
SDU1(5RV1)/HSDU1(63RV1)
E5
N/A
E6
HSDU1(63RV1)/TXCOAX
E7
N/A
E8
HSDU1(63RV1)/RXCOAX
E9
N/A
N/A
EA
N/A
N/A to Airbus
EB
MCDU1(2CA1)+MCDU2(2CA2)+MCDU3(2CA3)
INACTIVE
EC
WRG:CONFIG PIN PROG/HSDU1(63RV1)
232800
ED
WRG:CONFIG PIN PROG/HSDU1(63RV1)
SDU ORT
232800
232834
232834
N/A to Airbus
232839
N/A
232839
[RMP only]
23--20--35
 Honeywell International Inc. Do not copy without express permission of Honeywell.
228212
Page 6--107
15 Jul 2006
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL
MCS--4200/7200 Multi--Channel SATCOM System
Airbus Level I (SDU No. 1) Failure Messages and ATA No. (cont)
Table 6-19.
Failure
Code
SDU/SDU No. 1 -- CFDS Normal and Interactive Modes
ATA Number
EE
WRG:FWD ID1 ADDRESS PIN
PROG/HSDU1(63RV1)
232800
FE
POWER SUPPLY INTERRUPT
240000
Table 6-20.
Failure
Code
01
Airbus Level I (SDU No. 2) Failure Messages and ATA No.
SDU/SDU No. 2 -- CFDS Normal and Interactive Modes
SDU2(105RV2)
SDU2(5RV2)
02
SDU1(105RV1) INCOMPATIBILITY
SDU1(5RV1) INCOMPATIBILITY
03
HSDU2(63RV2)
04
HPA2(110RV2)
ATA Number
[IGA]
232834
[HGA]
232834
[IGA]
232834
[HGA]
232834
232839
HPA--HI GAIN(7RV2)
[IGA]
232831
[HGA]
232831
07
HPA--LO GAIN(9RV)
232835
0A
HI POWER RELAY(21RV)
232842
0D
DLNA2 (119RV2)
[IGA]
232838
DLNA--TOP(19RV2)
[Top Mount]
232838
DLNA--L(20RV3)
[Conformal]
232837
0F
DLNA--R(20RV4)
[Conformal]
232837
10
DLNA--LO GAIN(14RV)
13
BSU(8RV2)
[Top Mount]
232846
BSU--L(15RV3)
[Conformal]
232844
15
BSU--R(15RV4)
[Conformal]
232844
1A
ANTENNA2(116RV2)
[IGA]
232813
HI GAIN ANTENNA--TOP(16RV1)
[Top Mount]
232813
HI GAIN ANTENNA--L(17RV)
[Conformal]
232812
1C
HI GAIN ANTENNA--R(18RV)
[Conformal]
232812
1F
LO GAIN ANTENNA(13RV)
21
MCDU1(2CA1)
[A330/A340]
228212
MCDU1(3CA1)
[A320]
228212
232836
232811
23--20--35
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Page 6--108
15 Jul 2006
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL
MCS-4200/7200
TEMPORARY REVISION NO. 23-1
INSERT PAGE 45 OF 53 FACING PAGE 6-108.
Reason:
To add a new failure code, 0B, to Table 6-20 between failure codes 0A and 0D.
Failure code 0B is added as follows:
Table 6-20.
Failure
Code
0B
Airbus Level I (SDU No. 2) Failure Messages and ATA No.
SDU/SDU No. 2 – CFDS Normal and Interactive Modes
HDM
ATA Number
232832
23-20-35
© Honeywell International Inc. Do not copy without express permission of Honeywell.
Page 45 of 53
28 Sep 2009
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL
MCS--4200/7200 Multi--Channel SATCOM System
Airbus Level I (SDU No. 2) Failure Messages and ATA No. (cont)
Table 6-20.
Failure
Code
22
23
33
SDU/SDU No. 2 -- CFDS Normal and Interactive Modes
MCDU2(2CA2)
[A330/A340]
228212
MCDU2(3CA2)
[A320]
228212
MCDU3(2CA3)
[A330/A340]
228212
MCDU3(3CA3)
[A320]
228212
ATSU1(1TX1)
[ATSU]
462134
[A320 ACARS]
232434
[A330/A340 ACARS]
232434
[ATSU]
462134
[A320 ACARS]
232434
[A320/A340 ACARS]
232434
ACARS MU(1RB)
ACARS MU1(1RB1)
34
ATA Number
ATSU2 (1TX2)
ACARS MU(1RB)
ACARS MU2(1RB2)
35
ADIRU1(1FP1)
341234
36
ADIRU2(1FP2)
341234
37
RESERVED
N/A
38
RESERVED
N/A
39
RESERVED
N/A
3D
FMGC1(1CA1)
FMGEC1(1CA1)
3E
[A320]
228334
[A330/A340]
228334
[A320]
228334
[A330/A340]
228334
FMGC2(1CA2)
FMGEC2(1CA2)
40
ARINC 429 ICAO
42
CTU -- CU CEPT--E1 BUS/SDU2(105RV2)
[IGA A320]
233500
CTU -- CU CEPT--E1 BUS/SDU2(105RV2)
[IGA A330/A340]
239200
CTU -- CU CEPT--E1 BUS/SDU2(5RV2)
[HGA A320]
233500
CTU -- CU CEPT--E1 BUS/SDU2(5RV2)
[HGA A330/A340]
239200
IFE 429 BUS/SDU2(5RV2)
[A330/A340 HGA]
233000
43
232800
IFE 429 BUS/SDU2(105RV2)
[A330/A340 IGA]
IFE 429 BUS/SDU2(105RV2)
[A320 IGA]
IFE 429 BUS/SDU2(5RV2)
50
HSDU2(63RV2)/SDU2(5RV2)
51
RESERVED
233000
[A320 HGA]
232839
23--20--35
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Page 6--109
15 Jul 2006
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL
MCS--4200/7200 Multi--Channel SATCOM System
Table 6-20.
Failure
Code
52
53
Airbus Level I (SDU No. 2) Failure Messages and ATA No. (cont)
SDU/SDU No. 2 -- CFDS Normal and Interactive Modes
IFE 429 BUS/SDU2(5RV2)
55
[A330/A340 IGA]
IFE 429 BUS/SDU2(105RV2)
[A320 IGA]
233000
[A320 HGA]
ATSU1 (1TX1)/SDU2(105RV2)
[IGA ATSU]
462134
[HGA ATSU]
462134
ACARS MU(1RB1)/SDU2(105RV2)
[IGA ACARS A330/A340]
232434
ACARS MU1(1RB1)/SDU2(5RV2)
[HGA ACARS A330/A340]
232434
ACARS MU(1RB)/SDU2(105RV2)
[IGA ACARS A320]
232434
ACARS MU1(1RB)/SDU2(5RV2)
[HGA ACARS A320]
232434
CTU -- CU CEPT--E1 BUS/SDU2(105RV2)
[IGA A320]
233500
CTU -- CU CEPT--E1 BUS/SDU2(105RV2)
[IGA A330/A340]
239200
CTU -- CU CEPT--E1 BUS/SDU2(5RV2)
[HGA A320]
233500
CTU -- CU CEPT--E1 BUS/SDU2(5RV2)
[HGA A330/A340]
239200
[IGA A330/A340]
228212
[HGA A330/A340]
228212
[IGA A320]
228212
[HGA A320]
228212
[IGA]
228212
[HGA]
228212
[IGA A320]
228212
MCDU2(3CA2)/SDU2(5RV2)
[HGA A320]
228212
ATSU2 (1TX2)/SDU2(105RV2)
[IGA ATSU]
462134
[HGA ATSU]
462134
[IGA A320 ACARS]
232434
[IGA A330/A340 ACARS]
232434
[HGA A320 ACARS]
232434
[HGA A330/A340 ACARS]
232434
MCDU1(2CA1)/SDU2(105RV2)
MCDU1(3CA1)/SDU2(105RV2)
MCDU1(3CA1)/SDU2(5RV2)
MCDU2(2CA2)/SDU2(105RV2)
MCDU2(2CA2)/SDU2(5RV2)
MCDU2(3CA2)/SDU2(105RV2)
57
233000
IFE 429 BUS/SDU2(5RV2)
MCDU1(2CA1)/SDU2(5RV2)
56
[A330/A340 HGA]
IFE 429 BUS/SDU2(105RV2)
ATSU1 (1TX1)/SDU2(5RV2)
54
ATA Number
ATSU2 (1TX2)/SDU2(5RV2)
ACARS MU2/SDU2(105RV2)
ACARS MU2 (1RB2)/SDU2(105RV2)
ACARS MU2/SDU2(5RV2)
ACARS MU2(1RB2)/SDU2(5RV2)
23--20--35
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15 Jul 2006
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL
MCS--4200/7200 Multi--Channel SATCOM System
Airbus Level I (SDU No. 2) Failure Messages and ATA No. (cont)
Table 6-20.
Failure
Code
59
SDU/SDU No. 2 -- CFDS Normal and Interactive Modes
ATA Number
CFDIU(1TW)/SDU2(105RV2)
[IGA A320]
313234
CMC1(1TM1)/SDU2(105RV2)
[IGA A330/A340]
451334
CFDIU(1TW)/SDU2(5RV2)
[HGA A320]
313234
CMC1(1TM1)/SDU2(5RV2)
[HGA A330/A340]
451334
[IGA]
341234
[HGA]
341234
[IGA]
341234
[HGA]
341234
[IGA]
232831
HPA--HI GAIN(7RV2)/SDU2(5RV2)
[HGA]
232831
HPA--LO GAIN(9RV)/SDU2(5RV2)
HGA+LGA
232835
IGA+LGA
232835
BSU(8RV2)/SDU2(5RV2)
[Top Mount]
232846
BSU--L(15RV3)/SDU2(5RV2)
[Conformal]
232844
64
BSU--R(15RV4)/SDU2(5RV2)
[Conformal]
232844
66
MCDU3(2CA3)/SDU2(105RV2)
[IGA A330/A340]
228212
[HGA A330/A340]
228212
[IGA A320]
228212
[HGA A320]
228212
[IGA]
232834
[HGA]
232834
5A
ADIRU1(1FP1)/SDU2(105RV2)
ADIRU1(1FP1)/SDU2(5RV2)
5B
ADIRU2(1FP2)/SDU2(105RV2)
ADIRU2(1FP2)/SDU2(5RV2)
5C
5F
HPA2(110RV2)/SDU2(105RV2)
HPA--LO GAIN(9RV)/SDU2(105RV2)
62
MCDU3(2CA3)/SDU2(5RV2)
MCDU3(3CA3)/SDU2(105RV2)
MCDU3(3CA3)/SDU2(5RV2)
67
RESERVED
68
RESERVED
6A
RESERVED
6C
RESERVED
6D
RESERVED
6E
RESERVED
6F
RESERVED
71
SDU1(105RV1)CROSSTALK
BUS/SDU2(105RV2)
SDU1(5RV1)CROSSTALK BUS/SDU2(5RV2)
23--20--35
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SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL
MCS--4200/7200 Multi--Channel SATCOM System
Airbus Level I (SDU No. 2) Failure Messages and ATA No. (cont)
Table 6-20.
Failure
Code
73
SDU/SDU No. 2 -- CFDS Normal and Interactive Modes
FMGC1(1CA1)/SDU2(105RV2)
ATA Number
[IGA A320]
228334
[IGA A330/A340]
228334
[HGA A320]
228334
[HGA A330/A340]
228334
[IGA A320]
228334
[IGA A330/A340]
228334
[HGA A320]
228334
[HGA A330/A340]
228334
[IGA]
232834
[HGA]
232834
HGA+LGA
232834
SDU2(105RV2) BUS M--CTRL/HPA--LO
GAIN(9RV)
IGA+LGA
232834
SDU2(5RV2) BUS M--CTRL/BSU(8RV2)
[Top Mount]
232834
SDU2(5RV2) BUS M--CTRL/BSU--L(15RV3)
[Conformal]
232834
9A
BSU--R(15RV4) XTALK/BSU--L(15RV3)
[Conformal]
232844
9C
SDU2(5RV2) BUS M--CTRL/BSU--R(15RV4)
[Conformal]
232834
9D
BSU--L(15RV3) XTALK BUS/BSU--R(15RV4)
[Conformal]
232844
9E
SDU2(5RV2)/HSDU2(63RV2)
9F
Not applicable for package 6.0 and beyond
A1
SDU2(105RV2)/MCDU1(2CA1)
FMGEC1(1CA1)/SDU2(105RV2)
FMGC1(1CA1)/SDU2(5RV2)
FMGEC1(1CA1)/SDU2(5RV2)
74
FMGC2(1CA2)/SDU2(105RV2)
FMGEC2(1CA2)/SDU2(105RV2)
FMGC2(1CA2)/SDU2(5RV2)
FMGEC2(1CA2)/SDU2(5RV2)
80
RESERVED
82
RESERVED
88
RESERVED
90
SDU2(105RV2) BUS M--CTRL/HPA2(110RV2)
SDU2(5RV2) BUS M--CTRL/HPA--HI
GAIN(7RV2)
96
98
SDU2(5RV2) BUS M--CTRL/HPA--LO
GAIN(9RV)
232834
N/A
SDU2(5RV2)/MCDU1(2CA1)
A2
SDU2(105RV2)/MCDU2(2CA2)
SDU2(RV2)/MCDU2(2CA2)
[IGA]
228212
[HGA]
228212
[IGA]
228212
[HGA]
228212
23--20--35
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Page 6--112
15 Jul 2006
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL
MCS--4200/7200 Multi--Channel SATCOM System
Table 6-20.
Failure
Code
A3
Airbus Level I (SDU No. 2) Failure Messages and ATA No. (cont)
SDU/SDU No. 2 -- CFDS Normal and Interactive Modes
SDU2(105RV2)/MCDU3(2CA3)
SDU2(5RV2)/MCDU3(2CA3)
ATA Number
[IGA]
228212
[HGA]
228212
A6
ESU(101RF) ETHERNET 1/HSDU2(63RV2)
464131
A7
ESU(101RF) ETHERNET 2/HSDU2(63RV2)
464131
A8
ESU(101RF) ISDN 1/HSDU2(63RV2)
464131
A9
ESU(101RF) ISDN 2/HSDU2(63RV2)
464131
C0
WRG:CONFIG PIN PROG/SDU2(105RV2)
[IGA]
232800
[HGA]
232800
[IGA]
323171
[HGA]
323171
[IGA]
232834
[HGA]
232834
WRG:ICAO ADDRESS PIN PROG/
SDU2(105RV2)
[IGA]
232800
WRG:ICAO ADDRESS PIN PROG/
SDU2(5RV2)
[HGA]
232800
[IGA]
232831
[HGA]
232831
[IGA]
232800
[HGA]
232800
WRG:CONFIG PIN PROG/SDU2(5RV2)
C1
LGCIU1(5GA1)/LGCIU2(5GA2)/SDU2(105RV2)
LGCIU1(5GA1)/LGCIU2(5GA2)/SDU2(5RV2)
C2
SDU2(105RV2) SEL--DISABLE
DISCRETE/SDU1(105RV1)
SDU2(5RV2) SELECT--DISABLE
DISCRETE/SDU1(5RV1)
C3
C4
HPA2(110RV2)/COAX
HPA--HI GAIN(7RV1)/COAX
C5
WRG:CONFIG PIN PROG/SDU2(105RV2)
OWNER REQS DB
WRG:CONFIG PIN PROG/SDU2(5RV2)
OWNER REQS DB
C6
LPA--LO GAIN(9RV)/COAX
C7
HPA2(110RV2)/OVER TEMPERATURE
C8
232835
[IGA]
232831
HPA--HI GAIN(7RV2)/OVER TEMPERATURE
[HGA]
232831
SDU2(105RV2)/BAD DATA FROM GROUND
STATION
[IGA]
232834
[HGA]
232834
SDU2(5RV2)/BAD DATA FROM GROUND
EARTH STATION
C9
HPA--LO GAIN(9RV)/OVER TEMPERATURE
232835
23--20--35
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SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL
MCS--4200/7200 Multi--Channel SATCOM System
Airbus Level I (SDU No. 2) Failure Messages and ATA No. (cont)
Table 6-20.
Failure
Code
CA
SDU/SDU No. 2 -- CFDS Normal and Interactive Modes
SDU2(5RV2)CTRL DISCRETE/DLNA--LO
GAIN(14RV)
SDU2(105RV2)CTRL DISCRETE/DLNA--LO
GAIN(14RV)
CB
ATA Number
[HGA+LGA]
232834
[IGA+LGA]
232834
[IGA]
232800
[HGA]
232800
WRG:SDI PIN PROG/HPA2(110RV1)
WRG:SDI PIN PROG/HPA--HI GAIN(7RV2)
CC
WRG:SDI PIN PROG/HPA--LO GAIN(9RV)
232800
CD
N/A
CE
RESERVED
CF
N/A
N/A
D0
N/A
N/A
D1
WRG:SDI PIN PROG/HPA2(110RV1)
N/A
WRG:SDI PIN PROG/HPA--HI GAIN(7RV2)
[IGA]
232800
[HGA]
232800
D2
WRG:SDI PIN PROG/HPA--LO GAIN(9RV)
D3
WRG:SDI PIN PROG/BSU(8RV2)
[Top Mount]
232800
WRG:SDI PIN PROG/BSU--L(15RV3)
[Conformal]
232800
D4
WRG:SDI PIN PROG/BSU--R(15RV4)
[Conformal]
232800
D5
SDU2(105RV2)/TXCOAX
[IGA]
232834
SDU2(5RV2)/TXCOAX
[HGA]
232834
SDU2(105RV2)/TXCOAX
[LGA]
232834
[HGA or IGA]
232834
[IGA]
232834
SDU2(5RV2)/RXCOAX
[HGA]
232834
D9
SDU2(5RV2)/RXCOAX
[HGA]
232834
DA
SDU2(105RV2)/RXCOAX
LGA+(HGA or IGA)
232834
SDU2(5RV2)/RXCOAX
LGA+(HGA or IGA)
232834
D6
SDU2(5RV2)/TXCOAX
D7
RESERVED
D8
SDU2(105RV2)/RXCOAX
DB
LO GAIN ANTENNA(13RV) LOG ON FAILURE
DC
N/A
232800
232811
N/A
23--20--35
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SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL
MCS--4200/7200 Multi--Channel SATCOM System
Airbus Level I (SDU No. 2) Failure Messages and ATA No. (cont)
Table 6-20.
Failure
Code
DD
SDU/SDU No. 2 -- CFDS Normal and Interactive Modes
ATA Number
SDU2 (105RV2) OWNER REQS DB SECURED
PARTITION
SDU2 (5RV2) OWNER REQS DB SECURED
PARTITION
DE
SDU2 (105RV2) OWNER REQS DB USER
PARTITION
SDU2 (5RV2) OWNER REQS DB USER
PARTITION
DF
SDU2 (105RV2) LOG ON FAILURE
SDU2 (5RV2) LOG ON FAILURE
[IGA]
232834
[HGA]
232834
[IGA]
232834
[HGA]
232834
[IGA]
232834
[HGA]
232834
E0
RESERVED
E1
SDU2(5RV2) DISCRETE/HSDU2(63RV2)
E2
N/A
N/A
E3
N/A
N/A
E4
SDU2(5RV2)/HSDU2(63RV2)
E5
N/A
E6
HSDU2(63RV2)/TXCOAX
E7
N/A
E8
HSDU2(63RV2)/RXCOAX
E9
N/A
N/A
EA
N/A
N/A
EB
MCDU1(2CA1)+MCDU2(2CA2)+MCDU3(2CA3)
INACTIVE
EC
WRG:CONFIG PIN PROG/HSDU2(63RV2)
232800
ED
WRG:CONFIG PIN PROG/HSDU2(63RV2)
SDU ORT
232800
EE
WRG:FWD ID1 ADDRESS PIN
PROG/HSDU2(63RV2)
232800
FE
POWER SUPPLY INTERRUPT
240000
232834
232834
N/A
232839
N/A
232839
[RMP only]
23--20--35
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228212
Page 6--115
15 Jul 2006
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL
MCS--4200/7200 Multi--Channel SATCOM System
Table 6-21.
Failure
Code
McDonnell Douglas Level I Failures Messages and
ATA Reference Numbers
CFDS Normal and Interactive Modes
ATA Number
01
SDU
232610
02
OTHER SDU INCOMPATIBILITY
232611
03
HSU
232664
04
HPA--IN GAIN
[IGA]
232600
HPA--HI GAIN
[HGA]
232613
07
HPA--LO GAIN
232614
0A
HI POWER RELAY
232615
0D
DLNA--(TOP/L)
232616
0F
DLNA--R
232618
10
DLNA--LO GAIN
232619
13
BSU--(TOP/L)
23261B
15
BSU--R
23261C
1A
IN GAIN ANTENNA--TOP
[IGA]
232600
HI GAIN ANTENNA--(TOP/L)
[HGA]
23261D
1C
HI GAIN ANTENNA--R
23261F
1F
LO GAIN ANTENNA
232620
21
MCDU1
232635
22
MCDU2
232636
23
MCDU3
232637
33
(ACARS MU/CMU)
23243C
34
(ACARS MU/CMU)2
N/A
35
(IRS/ADIRU)--PRI
23263E
36
(IRS/ADIRU)--SEC
23263F
37
RESERVED
38
RESERVED
39
RESERVED
3D
(FMC/VIA)1
232642
3E
(FMC/VIA)2
232643
23--20--35
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SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL
MCS-4200/7200
TEMPORARY REVISION NO. 23-1
INSERT PAGE 46 OF 53 FACING PAGE 6-116.
Reason:
To add a new failure code, 0B, to Table 6-21 between failure codes 0A and 0D.
Failure code 0B is added as follows:
Table 6-21.
Failure
Code
0B
McDonnell Douglas Level I Failure Messages and
ATA Reference Numbers
CFDS Normal and Interactive Modes
HDM
ATA Number
232664
23-20-35
© Honeywell International Inc. Do not copy without express permission of Honeywell.
Page 46 of 53
28 Sep 2009
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL
MCS--4200/7200 Multi--Channel SATCOM System
Table 6-21.
Failure
Code
McDonnell Douglas Level I Failures Messages and
ATA Reference Numbers (cont)
CFDS Normal and Interactive Modes
ATA Number
40
ARINC 429 ICAO ADDRESS
N/A
42
CTU
43
(CFS/CPDF)
50
HSU/SDU
52
(CFS/CPDF)/SDU
53
(ACARS MU/CMU)/SDU
23263C
54
CTU/SDU
232644
55
MCDU1/SDU
232635
56
MCDU2/SDU
232636
57
(ACARS MU/CMU)2/SDU
59
CFDIU/SDU
232641
5A
(IRS/ADIRU)--PRI/SDU
23263E
5B
(IRS/ADIRU)--SEC/SDU
23263F
5C
HPA--IN GAIN/SDU
[IGA]
232600
HPA--HI GAIN/SDU
[HGA]
232600
232644
TBD
232664
TBD
N/A
5F
HPA--LO GAIN/SDU
232623
62
BSU--(TOP/L)/SDU
232626
64
BSU--R/SDU
232627
66
MCDU3/SDU
232637
67
RESERVED
68
RESERVED
6A
RESERVED
6C
RESERVED
6D
RESERVED
6E
RESERVED
6F
RESERVED
71
OTHER SDU/THIS SDU
232600
73
(FMC/VIA)1/SDU
232642
23--20--35
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SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL
MCS--4200/7200 Multi--Channel SATCOM System
Table 6-21.
Failure
Code
McDonnell Douglas Level I Failures Messages and
ATA Reference Numbers (cont)
CFDS Normal and Interactive Modes
ATA Number
74
(FMC/VIA)2/SDU
232643
80
RESERVED
82
RESERVED
88
RESERVED
90
SDU M--CTRL/HPA--IN GAIN
[IGA]
232600
SDU M--CTRL/HPA--HI GAIN
[HGA]
232600
96
SDU M--CTRL/HPA--LO GAIN
23262D
98
SDU M--CTRL/BSU--(TOP/L)
232600
9A
BSU--R XTALK/BSU--L
232600
9C
SDU M--CTRL/BSU--R
232630
9D
BSU--L XTALK/BSU--R
232600
9E
SDU/HSU
232664
9F
RESERVED
232664
A6
HSU ETHERNET PORT 1
232664
A7
HSU ETHERNET PORT 2
232664
A8
HSU ISDN PORT 1
232664
A9
HSU ISDN PORT 2
232664
C0
WRG:CONFIG PIN PROG/SDU
232600
C1
SDU WOW MISCOMPARE
C2
SDU/OTHER SDU SELECT--DISABLE DISCRETE
232600
C3
WRG:ICAO ADDRESS PIN PROG/SDU
232631
C4
TX PATH VSWR--IN GAIN
[IGA]
232600
TX PATH VSWR--HI GAIN
[HGA]
232600
N/A
C5
WRG:CONFIG PIN PROG/SDU OWNER REQS
232600
C6
TX PATH VSWR--LO GAIN
232600
C7
HPA--IN GAIN/OVER TEMPERATURE
[IGA]
232600
HPA--HI GAIN/OVER TEMPERATURE
[HGA]
23262C
C8
BAD DATA FROM GROUND EARTH STATION
C9
HPA--LO GAIN/OVER TEMPERATURE
None
232634
23--20--35
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Page 6--118
15 Jul 2006
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL
MCS--4200/7200 Multi--Channel SATCOM System
Table 6-21.
Failure
Code
McDonnell Douglas Level I Failures Messages and
ATA Reference Numbers (cont)
CFDS Normal and Interactive Modes
ATA Number
CA
SDU/DLNA--LO GAIN
232619
CB
WRG:SDI PIN PROG/HPA--IN GAIN
[IGA]
232600
WRG:SDI PIN PROG/HPA--HI GAIN
[HGA]
232600
CC
WRG:SDI PIN PROG/HPA--LO GAIN
232600
CD
SDU (POC/TOTC) DATA RESET
CE
RESERVED
CF
HPA--IN GAIN (POC/TOTC) DATA RESET
[IGA]
None
HPA--HI GAIN (POC/TOTC) DATA RESET
[HGA]
None
None
D0
HPA--LO GAIN (POC/TOTC)
None
D1
WRG:SDI PIN PROG/HPA--IN GAIN
[IGA]
232600
WRG:SDI PIN PROG/HPA--HI GAIN
[HGA]
232600
D2
WRG:SDI PIN PROG/HPA--LO GAIN
232600
D3
WRG:SDI PIN PROG/BSU--(TOP/L)
232600
D4
WRG:SDI PIN PROG/BSU--R
232600
D5
SDU COAX/HPA--IN GAIN
[IGA]
232600
SDU COAX/HPA--HI GAIN
[HGA]
232600
D6
SDU COAX/HPA--LO GAIN
D7
RESERVED
D8
DLNA/(SDU)--(TOP/L)
232600
D9
DLNA/(SDU)--R
232600
DA
DLNA/(SDU)--LO GAIN
232600
DB
LO GAIN SUBSYSTEM
232600
DC
NO ACTIVE ACARS MU/CMU
232400
DD
SDU OWNER REQS -- SECURED
None
DE
SDU OWNER REQS -- USER
None
DF
IN GAIN SUBSYSTEM
[IGA]
232600
HI GAIN SUBSYSTEM
[HGA]
232600
E0
RESERVED
E1
BAD HSU DISABLE DISCRETE
232600
232664
23--20--35
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Page 6--119
15 Jul 2006
SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL
MCS--4200/7200 Multi--Channel SATCOM System
Table 6-21.
Failure
Code
McDonnell Douglas Level I Failures Messages and
ATA Reference Numbers (cont)
CFDS Normal and Interactive Modes
ATA Number
E2
RESERVED
E3
RESERVED
E4
HSU/SDU INTERFACE VER INCOMPATIBILITY
E5
RESERVED
E6
HSU/HPA TX RF PATH
E7
RESERVED
E8
DLNA/HSU RX RF PATH
E9
RESERVED
EA
RESERVED
EC
WRG:CONFIG PIN PROG/HSU
232664
ED
WRG:CONFIG PIN PROG/HSU SDU OWNER REQS
232664
EE
WRG:FWD ID PIN PROG/HSU
232664
FE
POWER SUPPLY INTERRUPT
None
232664
232664
232664
23--20--35
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SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL
MCS--4200/7200 Multi--Channel SATCOM System
4. SCDU for Dual SATCOM
A. General
(1) The SDU supports SCDU page displays for dual systems. All pages are as specified
in paragraph 2.D. (SCDU pages) with the following exceptions.
B. SATCOM Logical Channels
(1) The SATCOM channels for HEADSET calls in a dual system can be supplied by
several combinations of physical channels within both SDUs. These combinations are
determined by the configuration strap settings for cockpit wiring and ORT items
regarding the use of SDU channel resources (items vi, vii, and xlviii). The display of
channel status and selections as reported on menus MAIN, DIRECTORY, and
CATEGORY-n reflect the logical channel status.
C. SATCOM (Cross-Talk Bus Failed)
(1) The SDU designated as the slave unit in a dual system must receive most of the
system status information from the master over the SDU cross-talk bus. If full
communication is not established, the slave unit cannot receive the necessary data
for the display pages. The default SATCOM MAIN MENU display page THIS UNIT
UNAVAILABLE is displayed in this case.
D. SATCOM
(1) The channel status page reflects the physical channels within the SDU that is
providing the display page.
E.
SATCOM Menus
(1) The maintenance menus reflect the maintenance data for the SATCOM system that
is providing the display page.
5. Maintenance Panel Assembly
A. General
(1) The maintenance panel assembly interface diagram (Figure 5-17) supplies remote
monitoring of MCS system operation. The maintenance panel assembly is made up
of two parts: the cabin telecommunications (CTM) panel and the Commissioning and
Maintenance Terminal (CMT) panel. The CTM panel is used for monitoring the cabin
telecommunications equipment. The panel contains six lamps to indicate the
availability of the telephone handsets. A keyed on/off switch arms the system when
the key is turned to the ON position.
(2) The CMT panel is used primarily to debug, detect, isolate software and/or hardware
integration, LRU and system integration, formal testing, and system access approval,
as well as general performance analysis. The CMT data connector supplies an
access port for a commissioning and maintenance terminal that can be a personal
computer, a dumb terminal, or a modem. The SDU interface connector on the panel
supplies a remote access port for testing the SDU. The panel also contains lamps to
indicate the status of the MCS system. These lamps are defined in Table 6-22.
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MCS--4200/7200 Multi--Channel SATCOM System
Table 6-22.
Commissioning and Maintenance Terminal Panel Lamps
Definition
Lamp
IN USE CH--1
(SDU pin TPH1) This lamp lights to show channel 1 is in use.
IN USE CH--2
(SDU pin TPK1) This lamp lights to show channel 2 is in use.
PILOT VCE NOT AVAIL
(SDU pin TP3A) This lamp lights to show no additional voice channels can be
established. This can be because no resources are available, or all available
resources being allocated to existing calls.
LOG OFF
(SDU pin TPC3) This lamp lights to show no packet mode data service
capability exists at any data rate; system not logged on.
CABIN VCE NOT AVAIL
(SDU pin TPB3) This lamp lights to show no additional channels can be
established for analog or digital cabin voice, or circuit--mode data. This can be
because no resources are available, or all available resources being allocated
to existing calls.
MCS FAIL
(SDU pin TPG1) This lamp lights to show a total loss of all SATCOM voice and
data services, and at least one cause can be attributable to the MCS system
LRUs themselves. Replacement of the appropriate LRU (SDU, HPA) is
necessary to restore partial or complete service. It is possible for this indicator
and the MCS inoperable indicator (NON-MCS FAIL) to be active
simultaneously, indicating failure in both the MCS system LRUs and nonsystem
LRUs.
NON-MCS FAIL
(SDU pin TPE3) This lamp lights to show total loss of all SATCOM voice and
data services, and at least one cause is attributable to the non-MCS system
LRUs, or interfaces to those LRUs. Replacement of the appropriate non MCS
LRU(s), or correction of the interface failure is necessary to restore partial or
complete service. It is possible for this indicator and the SATCOM fail indicator
(MCS FAIL) to be active simultaneously, indicating failure in both the MCS
system LRUs and the nonsystem LRUs or interfaces.
NO SAT LINK
(SDU pin TPJ1) This lamp lights to show no SATCOM voice or data services
are available because of the AES not being successfully logged-on, and the
cause is definitely not due to reported failures (MCS or non-MCS). If there is a
MCS or non-MCS failure, the NO SAT LINK lamp will not light.
HGA FAIL
(SDU pin TPD3) This lamp lights to show packet-mode data service capability
exists, but only at the lowest channel rates (600 and 1200 bps). This indicator
is assumed to only be present in high gain antennas installations that have a
low gain antenna backup system. The lamp indicates an HGA failure due to the
reduction from normal high speed capability.
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SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL
MCS--4200/7200 Multi--Channel SATCOM System
SECTION 7
MAINTENANCE PRACTICES
1. Overview
A. General
(1) This section supplies instructions for removing, reinstalling, and adjusting each LRU
of the MCS that has been installed by the aircraft manufacturer or completion center.
Where applicable, instructions for replacing lamps, knobs, and set screws are
included. Adjustment information is called out as required.
CAUTION: SHOULD ANY INSTALLATION CRITICAL CASES ARISE WITH THE
REINSTALLATION OF ANY UNIT, YOU MUST COMPLY 100 PERCENT
WITH THE INSTRUCTION.
CAUTION: TO PREVENT DAMAGE TO EQUIPMENT, TURN AIRCRAFT POWER OFF
WHEN REMOVING OR INSTALLING LRUS.
2. Equipment and Materials
A. General
CAUTION: DO NOT USE MATERIALS THAT ARE NOT EQUIVALENT TO
MATERIALS SPECIFIED BY HONEYWELL. MATERIALS NOT
EQUIVALENT CAN CAUSE DAMAGE TO THE EQUIPMENT AND CAN
MAKE THE WARRANTY NOT APPLICABLE.
(1) Maintenance materials identified with a Honeywell Material Number (HMN) are given
in Table 7-1.
(2) No additional special equipment or materials other than those commonly used in the
shop are required to install the units in existing trays and clamps, and to adjust the
system. Do not over tighten mounting screws. Where torque values are not given, it
is acceptable to finger tighten the mounting screws.
Table 7-1.
Item
Materials
Description
Source
HMN 97P5778
RTV silicone, No. 3145,
translucent, per MIL--A--46146,
Group II, Type I military
designation M4614621XTN.
Dow Corning Corp, Midland, MI
(05AJ8)
HMN 98C0978
Sealant, corrosion inhibitive
(MIL--S--81733, Type II--1/2 -- for
extrusion application in the time of
1/2 hour) — Pro--Seal 870B--1/2
Courtaulds Aerospace, Glendale,
CA (83574)
NOTES: NOTES:
1.
Equivalent alternatives are permitted for materials in this list.
2.
The HMN codes in the list of materials identify the Honeywell Material Number (HMN) given to each material.
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SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL
MCS--4200/7200 Multi--Channel SATCOM System
3. Procedure for Antennas
A. General
(1) The following paragraphs describe general information when removing or installing
antennas.
NOTE: For all antennas not supplied by Honeywell, removal and installation should
be done according to installation instructions from the manufacturer.
B. Antenna Weather Protection
(1) Some antennas require gaskets and others have O--rings. When reinstalling
antennas, new gaskets or O--rings should be used.
(2) A weather sealant should be applied around the periphery of the antenna base to
prevent seepage of water and condensation and preclude corrosion. If a sealant or
aerodynamic smoother is used around the periphery of the antenna base, it should
be applied after the antenna has been bolted down. The sealant used should be
nonadhering so the antenna can be removed at a later time, if necessary. Chromatic
tape is recommended.
NOTE: When mounting antennas on a pressurized fuselage, a leveling and sealing
compound like Pro-Seal 870B--1/2 should be used between the entire
mounting surface of the antenna and the fuselage. Use of this compound, in
addition to the installation gasket, compensates for surface irregularities and
voids between the antenna and the fuselage. A mold releasing agent can be
used on the fuselage prior to installation to prevent the leveling compound
from adhering to the fuselage.
(3) To prevent water seepage on top mounted antennas, it can be necessary to apply
Silastic sealant (RTV--3145 or equivalent) to the mounting screw heads.
C. Antenna Hardware
(1) Clean the airframe at the antenna mounting area to remove any foreign material.
(2) Because of the insulation qualities of gaskets and leveling compounds, the mounting
screws are required to supply the electrical bonding between the antennas and the
aircraft (typically 15 milliohms or less is required). The technician doing the
reinstallation must be sure any hardware being reused is clean and free of corrosion.
If in doubt, use new hardware.
(3) Gaskets and O--rings deform during initial installation. While it is possible to reuse
gaskets and O--rings, it is highly recommended new gaskets or O--rings be used.
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MCS--4200/7200 Multi--Channel SATCOM System
D. General Antenna Removal Instructions
NOTE: These procedures apply to all antennas. To prevent damage to the
antennas, do not apply pressure to the plastic housings or pry on plastic
housings.
(1) Pull the appropriate circuit breakers.
(2) After removing and saving the hardware, cut the bond line of any installer--applied
sealant between the antenna and the aircraft skin.
(3) Pull the antenna away from the aircraft skin far enough to disconnect the cable
connector(s).
4. Procedure for the LRUs
CAUTION: BEFORE AN LRU IS INSTALLED OR REMOVED, PULL THE CIRCUIT
BREAKERS THAT SUPPLY POWER TO THE LRU TO REMOVE POWER.
CAUTION: MOISTURE AND DIRT CAUSE DAMAGE TO LRUs.
CAUTION: LRU FAILURE RATES INCREASE WITH A RISE IN TEMPERATURE. INSTALL
THE LRUs WITH CLEARANCE; LET THE AIR FLOW ON TOP AND BOTTOM
OF LRUS TO PREVENT OVERHEATING.
A. LRU Removal
(1) Remove an LRU as follows:
(a) Disconnect the circuit breakers that supply power to the LRU.
(b) Tag the circuit breakers with DO-NOT-OPERATE identifiers.
(c) Loosen the clamp knobs and let them drop out of the way.
(d) Pull the LRU forward a minimum of 1/2 inch to clear the rear connector pins.
(e) Lift the LRU free of the cooling air-duct gasket on the mounting rack.
B. LRU Installation
(1) Install an LRU as follows:
(a) Determine the location of each LRU in the aircraft.
(b) Check the LRU to be installed and make sure all connector pins are straight and
ready for connection.
(c) Make sure the index pin coding on the rear connector is correct for the mating
connector.
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MCS--4200/7200 Multi--Channel SATCOM System
(d) Place the LRU in the appropriate mounting rack and align the connectors. Push
the LRU back to make contact with the connector pins. Push the LRU into place
and rock the LRU sideways slightly.
CAUTION: DO NOT OVER TIGHTEN THE CLAMP. EXCESSIVE TORQUE CAN
CAUSE BRACKETS AND CONNECTORS TO WARP AND BEND.
(e) Put the hold-down clamps in place and tighten the knobs finger-tight.
5. Owner Requirements Table Uploading
A. General
(1) When the SDU is replaced, the ORT needs to be uploaded before normal operation
can begin. Refer to SYSTEM OPERATION, for the ORT uploading procedure.
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SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL
MCS--4200/7200 Multi--Channel SATCOM System
6. Instructions for Continued Airworthiness, FAR 25.1529
A. General
(1) Maintenance requirements and instructions for continued airworthiness of the MCS
components are contained in the paragraphs that follow.
(2) Installation of the MCS on an aircraft by supplemental type certificate or Form 337
obligates the aircraft operator to include the maintenance information supplied by this
manual in the operator’s Aircraft Maintenance Manual and the operator’s Aircraft
Scheduled Maintenance Program.
(a) Maintenance information for the MCS (system description, removal, installation,
testing, etc.) is contained in this manual.
(b) LRU part numbers and other necessary part numbers contained in this manual
should be placed into the aircraft operator’s appropriate aircraft illustrated parts
catalog (IPC).
(c) Wiring diagram information contained in this manual should be placed into the
aircraft operator’s appropriate aircraft Wiring Diagram Manuals.
(d) The MCS system components are considered on--condition units and no
additional maintenance is required other than a check for security and operation
at normal inspection intervals.
(e) If a system component is inoperative, remove unit, secure cables and wiring,
collar applicable switches and circuit breakers, and placard them inoperative.
Revise equipment list and weight and balance as applicable prior to flight and
make a log book entry that unit was removed (refer to section 91.213 of the FAR
or the aircraft’s minimum equipment list (MEL).
(f)
The MCS components can be repaired at a factory authorized repair center or an
appropriately rated FAA Part 145 repair station.
(g) Once repaired, reinstall the LRU in the aircraft in accordance with the original
Form 337 approved data or instructions in this manual. Do a Return to Service
test of the system and approve it for return to service with a log book entry
required by section 43.9.
(h) Scheduled maintenance program tasks to be added to the aircraft operator’s
appropriate aircraft maintenance program are as follows:
Recommended periodic scheduled servicing tasks: None required.
Recommended periodic inspections: None required.
NOTE: The (applicable LRUs) used with this system have test and
inspections that are required by FAR 91.413 to be completed every
24 calender months.
Recommended periodic scheduled preventative maintenance tests (Tests to
determine system condition and/or latent failures): None required.
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SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL
MCS--4200/7200 Multi--Channel SATCOM System
Blank Page
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SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL
MCS--4200/7200 Multi--Channel SATCOM System
APPENDIX A
VENDOR EQUIPMENT
1. Overview
A. General
(1) Appendix A contains information on vendor-manufactured equipment that can be
installed on an aircraft configured for MCS system. Installation of this equipment
depends on the specific requirements of the operator. Therefore, information in this
section is supplied as a courtesy to the MCS equipment operators.
2. Electronic Cable Specialists
A. General
(1) This paragraph contains information on how to select installation provisions offered
by ECS for the Honeywell MCS--4200/7200 system. ECS designs and manufactures
the installation provisions described here and can supply either individual
components or complete installation kits. The address for Electronic Cable
Specialists is as follows:
Electronic Cable Specialists
5300 W. Franklin Drive
Franklin, WI 53132
U.S.A.
Telephone: (414) 421--5300
FAX: (414) 421--5301
B. Radio Frequency Components
(1) All RF components (cable, connectors, and attenuators) supplied to interface the
SATCOM Avionics and Antenna Subsystems have been designed to meet the strict
usage and attenuation requirements of the Honeywell MCS--4200/7200 system and
ARINC 741/761. A selected list of RF components offered by ECS for SATCOM
installations is shown in Table A--1 and Table A--2.
C. Cable Assembly Fabrication
(1) ECS fabricates cable assemblies guaranteed to meet SATCOM system requirements
and ARINC 741 specifications.
• Each cable assembly is fabricated with an individual part number, which is
permanently affixed to each end of the assembly.
• Each set of cable assemblies is assigned a serial number, which is printed on the
part number label. Serialization makes sure each cable assembly is traceable and
repeatable.
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MCS--4200/7200 Multi--Channel SATCOM System
Table A--1.
ECS Cables and Connectors
310801
310201
311501
311601
311901
3C142B*
4.7
6.9
8.7
10.7
15.5
18.4
0.45 in.
0.32 in.
0.245 in.
0.23 in.
0.195 in.
0.195 in.
15.0
8.6
5.2
5.0
4.3
5.0
Male TNC 180°
CTS022
CTS122
CTS922
CTS922
CTS722
CTS722
Male TNC 90°
CTR022
CTR122
CTR922
CTR922
CTR722
CTR722
Male N 180°
CNS022
CNS122
CNS922
CNS922
CNS722
CNS722
Male N 90°
CNR022
CNR122
CNR922
CNR922
CNR722
CNR722
Female N 180°
FNS022
FNS122
FNS922
FNS922
FNS722
FNS722
ARINC 600 Size 1
L0122
L1122
L9122
L9122
L7122
L7122
ARINC 600 Size 5
N/A
N/A
A650922
A650922
ECS Cable Part No.
Nominal Attenuation
@ 1.6 GHz (dB/100 ft)
Overall Diameter
Pounds/100 ft
Table A--2.
225791--2 225791--2
ECS Attenuators
Attenuator (Transmit Path)
Attenuator (Receive Path)
Fixed or Variable
Fixed or Variable
D. Cable Assembly Testing
(1) Testing is done on Hewlett-Packard 8753 network analyzers to verify insertion loss
and VSWR. The results become part of a test database and are shipped with each
cable assembly. Each cable assembly is tested across the SATCOM system
frequency bandwidth (1530 MHz to 1660.5 MHz). Received path cable assemblies
are test swept from 1530 MHz to 1559 MHz. Customers have the option of having
cable assemblies tested with or without attenuators.
E.
ARINC 600 Connectors
(1) ECS supplies ARINC 600 connectors for ARINC 741 style avionic electrical
interfaces. The SATCOM rack-side connectors (Figure A--1) are described in this
paragraph. Connector part numbers are:
(2) ECS supplies ARINC 600 Size 1 coaxial connectors with the requisite termination kit
and assembly instructions (Figure A--2).
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Figure A--1.
Figure A--2.
ARINC Connectors
ARINC Assembly
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SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL
MCS--4200/7200 Multi--Channel SATCOM System
F.
SATCOM Avionics Unit Mounting Hardware
(1) SATCOM avionics mounting hardware is made up of the HPA, SDU, and SCU and
will be mounted in ARINC 600 style tray assemblies. The HPA and SDU each require
forced air cooling during normal operation, whereas the SCU can function properly
with convection cooling alone. Refer to MECHANICAL INSTALLATION, for LRU
cooling requirements.
G. SATCOM Hardware Component Kits
(1) This paragraph contains information on how to select SATCOM hardware component
kits offered by ECS for the Honeywell MCS--4200/7200 avionic units in Table A--3
thru Table A--8. ECS supplies several options for each kit to accommodate the variety
of mounting requirements specific to each aircraft installation. ECS tray assemblies
come with and without independent cooling systems to ensure installation flexibility.
(2) The tray assemblies have been specially designed to meet Honeywell and ARINC
600 LRU cooling requirements. Tray assemblies are supplied with insertion/extraction
front hold-downs as standard, but are available with other front hold-down options.
For tray assembly dimensions refer to Figure A--3.
(3) The hardware component kits for the HPA, HSU, and SDU are listed in Table A--3
thru Table A--8, respectively.
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