Honeywell THALES MCS-4200 Installation And Maintenance Manual Download Page 159

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SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL

MCS--4200/7200 Multi--Channel SATCOM System

23--20--35

15 Jul 2006



Honeywell International Inc. Do not copy without express permission of Honeywell.

Page 6--97

Table 6-18.

Boeing Level I Failure Messages and ATA Reference Numbers (cont)

Failure

Code

CMC

Message ID

ATA Number

SCDU Accessed Maintenance Pages

RESERVED

FMC1

346100

FMC2

346100

ARINC 429 ICAO ADDRESS

None

23251

CTU

231900

23235

(CFS/CPDF)

233200

HSU/SDU

232500

(CFS/CPDF)/SDU

233200

(ACARS MU/CMU)1/SDU

232700

23219

CTU/SDU

231900

23235

MCDU1/SDU

346100

MCDU2/SDU

346100

(ACARS MU/CMU)2/SDU

232700

23235

CMC/SDU

454500

23201

IRS--PRI/SDU

342100

23222

IRS--SEC/SDU

342100

23224

HPA--IN GAIN/SDU

HPA--HI GAIN/SDU

[IGA]

[HGA]

232500

23226

HPA--LO GAIN/SDU

232500

23225

BSU--(TOP/PORT)/SDU

232500

23213

BSU--STBD/SDU

232500

23214

MCDU3/SDU

346100

RESERVED

Summary of Contents for THALES MCS-4200

Page 1: ...tware 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 E...

Page 2: ... 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...

Page 3: ...22 Radiall NSXN2P201X0004 Radiall Figure 4 2 Figure 5 1 Figure 5 2 Table 5 4 and Table 5 5 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 08 620 600 076 Radiall NSXN2P221X0008 Radiall Figure 4 3 Figure 5 3 thru Figure 5 6 RFUIA ARINC 600 Size 4 MCU No 2 Shell Type 08 Top Insert Type 05 Middle Insert Type 04 Bottom Insert Index...

Page 4: ...ALLATION AND MAINTENANCE MANUAL MCS 4200 7200 Multi Channel SATCOM System 23 20 35 15 Jul 2006 Honeywell International Inc Do not copy without express permission of Honeywell Page 5 4 Figure 5 1 SDU ARINC 600 Connector Layout ...

Page 5: ...ERVED SPARE 429 OUTPUT A SPARE 429 OUTPUT B RESERVED RESERVED RESERVED RESERVED RESERVED SPARE 7 RESERVED RESERVED SPARE RESERVED RESERVED RESERVED RESERVED RESERVED RESERVED RESERVED 8 RESERVED RESERVED RESERVED RESERVED RESERVED RESERVED RESERVED RESERVED SPARE SPARE 9 SPARE DISCRETE INPUT CONFIG STRAP TYPE SPARE DISCRETE INPUT CONFIG STRAP TYPE SPARE RESERVED RESERVED RESERVED RESERVED RESERVED...

Page 6: ...DER A DATA BUS FROM AIRBORNE LOADER B DATA BUS TO AIRBORNE LOADER A DATA BUS TO AIRBORNE LOADER B RESERVED RESERVED BITE INPUT FROM ACU OR TOP PORT BSU A BITE INPUT FROM ACU OR TOP PORT BSU B BITE INPUT FROM STBD BSU A BITE INPUT FROM STBD BSU B 8 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...

Page 7: ...NTENANCE MANUAL MCS 4200 7200 Multi Channel SATCOM System 23 20 35 15 Jul 2006 Honeywell International Inc Do not copy without express permission of Honeywell Page 5 7 Figure 5 2 Contact Arrangements for Bottom Insert SDU ARINC 600 Connector ...

Page 8: ...ALLATION AND MAINTENANCE MANUAL MCS 4200 7200 Multi Channel SATCOM System 23 20 35 15 Jul 2006 Honeywell International Inc Do not copy without express permission of Honeywell Page 5 8 Figure 5 3 HPA ARINC 600 Connector Layout ...

Page 9: ...E MANUAL MCS 4200 7200 Multi Channel SATCOM System 23 20 35 15 Jul 2006 Honeywell International Inc Do not copy without express permission of Honeywell Page 5 9 5 10 Figure 5 4 Contact Arrangements for the Top Insert 60 Watt HPA ARINC 600 Connector ...

Page 10: ...ENANCE MANUAL MCS 4200 7200 Multi Channel SATCOM System 23 20 35 15 Jul 2006 Honeywell International Inc Do not copy without express permission of Honeywell Page 5 11 5 12 Figure 5 5 Contact Arrangements for Middle Insert HPA 60 Watt ARINC 600 ...

Page 11: ...NCE MANUAL MCS 4200 7200 Multi Channel SATCOM System 23 20 35 15 Jul 2006 Honeywell International Inc Do not copy without express permission of Honeywell Page 5 13 Figure 5 6 Contact Arrangements for Bottom Insert HPA 60 Watt ARINC 600 Connector ...

Page 12: ...LATION AND MAINTENANCE MANUAL MCS 4200 7200 Multi Channel SATCOM System 23 20 35 15 Jul 2006 Honeywell International Inc Do not copy without express permission of Honeywell Page 5 14 Figure 5 7 HS 720 ARINC 600 Connector Layout ...

Page 13: ...ENANCE MANUAL MCS 4200 7200 Multi Channel SATCOM System 23 20 35 15 Jul 2006 Honeywell International Inc Do not copy without express permission of Honeywell Page 5 15 5 16 Figure 5 8 Contact Arrangements for Top Insert HSU ARINC 600 Connector ...

Page 14: ...NCE MANUAL MCS 4200 7200 Multi Channel SATCOM System 23 20 35 15 Jul 2006 Honeywell International Inc Do not copy without express permission of Honeywell Page 5 17 5 18 Figure 5 9 Contact Arrangements for the Middle Insert HSU ARINC 600 Connector ...

Page 15: ...NANCE MANUAL MCS 4200 7200 Multi Channel SATCOM System 23 20 35 15 Jul 2006 Honeywell International Inc Do not copy without express permission of Honeywell Page 5 19 Figure 5 10 Contact Arrangements for the Bottom Insert HSU ARINC 600 Connector ...

Page 16: ...LATION AND MAINTENANCE MANUAL MCS 4200 7200 Multi Channel SATCOM System 23 20 35 15 Jul 2006 Honeywell International Inc Do not copy without express permission of Honeywell Page 5 20 Figure 5 11 RFUIA ARINC 600 Connector Layout ...

Page 17: ...ed 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 t...

Page 18: ...ESCRIPTION INSTALLATION AND MAINTENANCE MANUAL MCS 4200 7200 Multi Channel SATCOM System 23 20 35 15 Jul 2006 Honeywell International Inc Do not copy without express permission of Honeywell Page 5 22 Blank Page ...

Page 19: ...MAINTENANCE MANUAL MCS 4200 7200 Multi Channel SATCOM System 23 20 35 15 Jul 2006 Honeywell International Inc Do not copy without express permission of Honeywell Page 5 23 5 24 Figure 5 12 Sheet 1 Satellite Data Unit HSU Interface Diagram ...

Page 20: ...MAINTENANCE MANUAL MCS 4200 7200 Multi Channel SATCOM System 23 20 35 15 Jul 2006 Honeywell International Inc Do not copy without express permission of Honeywell Page 5 25 5 26 Figure 5 12 Sheet 2 Satellite Data Unit HSU Interface Diagram ...

Page 21: ...MAINTENANCE MANUAL MCS 4200 7200 Multi Channel SATCOM System 23 20 35 15 Jul 2006 Honeywell International Inc Do not copy without express permission of Honeywell Page 5 27 5 28 Figure 5 12 Sheet 3 Satellite Data Unit HSU Interface Diagram ...

Page 22: ...5 6 ICAO Block Strapping Example AES ID 53375006 Octal Octal Binary SDU Connector Pin MP 1 C13 5 0 D13 1 E13 0 F13 3 1 G13 1 H13 0 J13 3 1 K13 1 D14 1 E14 7 1 F14 1 G14 1 H14 5 0 J14 1 K14 0 A15 0 0 B15 0 C15 0 D15 0 0 E15 0 F15 1 G15 6 1 H15 0 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 p...

Page 23: ...ESCRIPTION INSTALLATION AND MAINTENANCE MANUAL MCS 4200 7200 Multi Channel SATCOM System 23 20 35 15 Jul 2006 Honeywell International Inc Do not copy without express permission of Honeywell Page 5 30 Blank Page ...

Page 24: ...NTENANCE MANUAL MCS 4200 7200 Multi Channel SATCOM System 23 20 35 15 Jul 2006 Honeywell International Inc Do not copy without express permission of Honeywell Page 5 31 5 32 Figure 5 13 CMC Top mounted High Gain Antenna HGA Interface Diagram ...

Page 25: ...LATION AND MAINTENANCE MANUAL MCS 4200 7200 Multi Channel SATCOM System 23 20 35 15 Jul 2006 Honeywell International Inc Do not copy without express permission of Honeywell Page 5 33 Figure 5 14 WH 10 Handset Interface Diagram ...

Page 26: ...ON AND MAINTENANCE MANUAL MCS 4200 7200 Multi Channel SATCOM System 23 20 35 15 Jul 2006 Honeywell International Inc Do not copy without express permission of Honeywell Page 5 34 Figure 5 15 HF SAT Transfer Panel Interface Diagram ...

Page 27: ...N AND MAINTENANCE MANUAL MCS 4200 7200 Multi Channel SATCOM System 23 20 35 15 Jul 2006 Honeywell International Inc Do not copy without express permission of Honeywell Page 5 35 Figure 5 16 Signal Conditioning Unit Interface Diagram ...

Page 28: ...ESCRIPTION INSTALLATION AND MAINTENANCE MANUAL MCS 4200 7200 Multi Channel SATCOM System 23 20 35 15 Jul 2006 Honeywell International Inc Do not copy without express permission of Honeywell Page 5 36 Blank Page ...

Page 29: ...D MAINTENANCE MANUAL MCS 4200 7200 Multi Channel SATCOM System 23 20 35 15 Jul 2006 Honeywell International Inc Do not copy without express permission of Honeywell Page 5 37 5 38 Figure 5 17 Maintenance Panel Assembly Interface Diagram ...

Page 30: ...LLATION AND MAINTENANCE MANUAL MCS 4200 7200 Multi Channel SATCOM System 23 20 35 15 Jul 2006 Honeywell International Inc Do not copy without express permission of Honeywell Page 5 39 5 40 Figure 5 18 HS 720 Interface Diagram ...

Page 31: ...f 53 28 Sep 2009 Honeywell International Inc Do not copy without express permission of Honeywell 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 ...

Page 32: ...N AND MAINTENANCE MANUAL MCS 4200 7200 Multi Channel SATCOM System 23 20 35 15 Jul 2006 Honeywell International Inc Do not copy without express permission of Honeywell Page 5 41 5 42 Figure 5 19 HS 720 Forward ID Configuration Pins ...

Page 33: ...AINTENANCE MANUAL MCS 4200 7200 Multi Channel SATCOM System 23 20 35 15 Jul 2006 Honeywell International Inc Do not copy without express permission of Honeywell Page 5 43 5 44 Figure 5 20 Tecom Top Mount High Gain Antenna Interface Diagram ...

Page 34: ...ANCE MANUAL MCS 4200 7200 Multi Channel SATCOM System 23 20 35 15 Jul 2006 Honeywell International Inc Do not copy without express permission of Honeywell Page 5 45 5 46 Figure 5 21 Thales Mechanically Steered High Gain Antenna Interface Diagram ...

Page 35: ...CE MANUAL MCS 4200 7200 Multi Channel SATCOM System 23 20 35 15 Jul 2006 Honeywell International Inc Do not copy without express permission of Honeywell Page 5 47 5 48 Figure 5 22 EMS AMT 50 Mechanically Steered High Gain Antenna Interface Diagram ...

Page 36: ...NTENANCE MANUAL MCS 4200 7200 Multi Channel SATCOM System 23 20 35 15 Jul 2006 Honeywell International Inc Do not copy without express permission of Honeywell Page 5 49 5 50 Figure 5 23 Dassault Conformal High Gain Antenna Interface Diagram ...

Page 37: ...AINTENANCE MANUAL MCS 4200 7200 Multi Channel SATCOM System 23 20 35 15 Jul 2006 Honeywell International Inc Do not copy without express permission of Honeywell Page 5 51 5 52 Figure 5 24 Ball Conformal High Gain Antenna Interface Diagram ...

Page 38: ...ON AND MAINTENANCE MANUAL MCS 4200 7200 Multi Channel SATCOM System 23 20 35 15 Jul 2006 Honeywell International Inc Do not copy without express permission of Honeywell Page 5 53 5 54 Figure 5 25 Low Gain Antenna Interface Diagram ...

Page 39: ...NTENANCE MANUAL MCS 4200 7200 Multi Channel SATCOM System 23 20 35 15 Jul 2006 Honeywell International Inc Do not copy without express permission of Honeywell Page 5 55 5 56 Figure 5 26 Toyocom Top mounted High Gain Antenna Interface Diagram ...

Page 40: ......

Page 41: ... 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 H...

Page 42: ...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 OPTI...

Page 43: ... 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 CONNE...

Page 44: ... 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 i...

Page 45: ... 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 typicall...

Page 46: ...P9B 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 i...

Page 47: ...Call Light On Air Ground Calls TP10 Pin K Interpretation 0 CALL LIGHT ON AT CALL INITIATION FOR AIR GROUND CALLS 1 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 Strap Parity ODD TP11 Pin A Interpretation 0 SUM OF ALL OTHER STRAPS SET TO 1 IS ODD 1 SUM OF ALL OTHER STRAPS SET TO 1 IS EVEN 2 T...

Page 48: ...able 5 18 Inertial Reference System IRS TP11 Pins C D Interpretation 0 0 PRIMARY IRS INSTALLED SECONDARY IRS INSTALLED 0 1 PRIMARY IRS INSTALLED SECONDARY IRS NOT INSTALLED 1 0 PRIMARY IRS NOT INSTALLED SECONDARY IRS INSTALLED 1 1 PRIMARY IRS NOT INSTALLED SECONDARY IRS NOT INSTALLED 2 When individually wired to the zero state configuration pins TP11C and TP11D indicate respectively that the input...

Page 49: ...on TP11 Pins L G A L N A T O P P O R S T A R B O A R D R E S E R V E D F R E S E R V E E F G H J K A D I P L E X E R L G A H P A R T B S U H G A D B S U H G A H G A H P A H P R F O R F U T U R E E D F O R M F R 1 1 1 1 1 1 4 4 0 1 1 1 1 1 4 4 1 0 1 1 1 1 4 4 4 4 0 0 1 1 1 1 4 4 4 4 4 4 1 1 0 1 1 1 4 0 1 0 1 1 1 4 1 0 0 1 1 1 4 4 4 4 Note 1 0 0 0 1 1 1 4 4 4 4 4 Note 1 1 1 1 0 1 1 4 4 4 4 0 1 1 0 1...

Page 50: ... to 47 1 1 1 1 0 1 46 0 1 1 1 0 1 45 1 0 1 1 0 1 44 0 0 1 1 0 1 43 1 1 0 1 0 1 42 0 1 0 1 0 1 41 1 0 0 1 0 1 40 0 0 0 1 0 1 39 1 1 1 0 0 1 38 0 1 1 0 0 1 8 37 1 0 0 0 1 0 0 1 0 0 1 0 to 0 7 1 0 1 0 1 0 0 0 0 0 0 0 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 7...

Page 51: ......

Page 52: ...exer 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 p...

Page 53: ...peration 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 dete...

Page 54: ...d 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 S...

Page 55: ... 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...

Page 56: ...LE STROKE CHIME 1 1 STEADY LIGHTS AND SINGLE STROKE CHIME 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 configurat...

Page 57: ...1 AMS NOT WIRED CABIN AUDIO NOT WIRED 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 de...

Page 58: ...ffect 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 discret...

Page 59: ...Interpretation 0 EPIC COCKPIT CALL DISCRETE SIGNALING MODE 1 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 Call Signaling Definitions SDU Output Pin Legacy Call Signaling Definition MP11F 1 Enhanced Call Signaling Definition MP11F 0 MP8E CHANNEL 1 CALL LIGHT CHANNEL 1 CD 1 CD1 1 MP1...

Page 60: ...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 Strap Parity MP11 Pin E Interpretation 0...

Page 61: ...ESCRIPTION INSTALLATION AND MAINTENANCE MANUAL MCS 4200 7200 Multi Channel SATCOM System 23 20 35 15 Jul 2006 Honeywell International Inc Do not copy without express permission of Honeywell Page 5 74 Blank Page ...

Page 62: ...r 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 G...

Page 63: ...a 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 t...

Page 64: ...sis 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 ...

Page 65: ...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 testi...

Page 66: ... HPA command word s for the HPA SSM field s for the ACU BSU control word s for the ACU BSU s 4 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 5 The SDU allows up to 30 1 seconds for other system LRUs except the HSU which is allowed 60 1...

Page 67: ... 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 1 As part of the system wide POST the SDU implements a RF loop back test The RF loop ba...

Page 68: ...s 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 func...

Page 69: ...ailure 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 bec...

Page 70: ...n detected with its own Level I code 3 There must be no known failures in order to light the green LED as the functional test indication 4 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 ...

Page 71: ...LEDs 1 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 2 The green LED P...

Page 72: ...ersists 4 SDU Failure Reporting a General 1 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 2 The alphanumeric display indicates all applicable failure conditions with no regard to Any type of internal external failure differentiation Any CFDS failure class distinctions W...

Page 73: ...t 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 b 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 lef...

Page 74: ...or absence of functional test failures does not affect the CM message list The failure message list for the CM display is potentially dynamic c 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 Lev...

Page 75: ...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 C...

Page 76: ...n 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 Multic...

Page 77: ...ve 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 TOT...

Page 78: ...atible 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 m...

Page 79: ...are 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 b 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 d...

Page 80: ...ine after another activation of the MANUAL SCROLL button b 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 conta...

Page 81: ...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 entr...

Page 82: ...ocal 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 ...

Page 83: ...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...

Page 84: ...ser 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 1 General a 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 usin...

Page 85: ...ontains 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 1 General a 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 wher...

Page 86: ... of RETURN the higher level page SEL Indicates the data in the field is currently selected e g the selected GES or antenna g Updates 1 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 configu...

Page 87: ...ESCRIPTION INSTALLATION AND MAINTENANCE MANUAL MCS 4200 7200 Multi Channel SATCOM System 23 20 35 15 Jul 2006 Honeywell International Inc Do not copy without express permission of Honeywell Page 6 26 Blank Page ...

Page 88: ...LLATION AND MAINTENANCE MANUAL MCS 4200 7200 Multi Channel SATCOM System 23 20 35 15 Jul 2006 Honeywell International Inc Do not copy without express permission of Honeywell Page 6 27 6 28 Figure 6 2 SATCOM SCDU Page Hierarchy ...

Page 89: ...D MAINTENANCE MANUAL MCS 4200 7200 Multi Channel SATCOM System 23 20 35 15 Jul 2006 Honeywell International Inc Do not copy without express permission of Honeywell Page 6 29 Figure 6 3 Sheet 1 Boeing Corporate SATCOM SCDU Main Menu Page ...

Page 90: ...ON AND MAINTENANCE MANUAL MCS 4200 7200 Multi Channel SATCOM System 23 20 35 15 Jul 2006 Honeywell International Inc Do not copy without express permission of Honeywell Page 6 30 Figure 6 3 Sheet 2 Airbus SATCOM SCDU Main Menu Page ...

Page 91: ...TENANCE pages menu selection subject to ORT item iv refer to SYSTEM OPERATION is accessible from the SATCOM SUBMENU page only on non Airbus Douglas CFDS equipped aircraft In Airbus and Douglas configurations these pages are accessed through the CFDS 3 The purpose of these pages are to display SATCOM maintenance data In a dual system the maintenance data pertains to the system from which the displa...

Page 92: ... AND MAINTENANCE MANUAL MCS 4200 7200 Multi Channel SATCOM System 23 20 35 15 Jul 2006 Honeywell International Inc Do not copy without express permission of Honeywell Page 6 32 Figure 6 4 Sheet 1 Boeing Corporate SATCOM SUBMENU Page ...

Page 93: ...LATION AND MAINTENANCE MANUAL MCS 4200 7200 Multi Channel SATCOM System 23 20 35 15 Jul 2006 Honeywell International Inc Do not copy without express permission of Honeywell Page 6 33 Figure 6 4 Sheet 2 Airbus SATCOM STATUS Page ...

Page 94: ...st 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 1 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 SATCO...

Page 95: ... SCDU MAIN MENU page after 5 minutes of completion of PAST the page hierarchy resets to its original structure as shown in Figure 6 2 4 The TEST IN PROGRESS 60S message during the POST PAST Results Delay period is required to prevent the display of premature test results i e to permit continuous monitoring sufficient time to add its contribution to the POST PAST results 4 TEST Menu Page a General ...

Page 96: ...N INSTALLATION AND MAINTENANCE MANUAL MCS 4200 7200 Multi Channel SATCOM System 23 20 35 15 Jul 2006 Honeywell International Inc Do not copy without express permission of Honeywell Page 6 36 Figure 6 6 Sheet 1 TEST Page ...

Page 97: ...N INSTALLATION AND MAINTENANCE MANUAL MCS 4200 7200 Multi Channel SATCOM System 23 20 35 15 Jul 2006 Honeywell International Inc Do not copy without express permission of Honeywell Page 6 37 Figure 6 6 Sheet 2 TEST Page ...

Page 98: ...est is not active The asterisk prompt is shown and the test allowed only if the log on state is Standby This line displays DISABLE ACTIVE 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 ...

Page 99: ...ne displays DISABLE ACTIVE 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 b Pushing LS key 5L when the ENABLE asterisk prompt is displayed causes the cockpit voice cal...

Page 100: ...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 2 Line 3 a This line displays headers ATA beginning in column 1 and CLASS beginning in column 20 if there are current failures to report after execution...

Page 101: ...ALLATION AND MAINTENANCE MANUAL MCS 4200 7200 Multi Channel SATCOM System 23 20 35 15 Jul 2006 Honeywell International Inc Do not copy without express permission of Honeywell Page 6 41 Figure 6 7 Sheet 1 SATCOM SELF TEST Page ...

Page 102: ...ALLATION AND MAINTENANCE MANUAL MCS 4200 7200 Multi Channel SATCOM System 23 20 35 15 Jul 2006 Honeywell International Inc Do not copy without express permission of Honeywell Page 6 42 Figure 6 7 Sheet 2 SATCOM SELF TEST Page ...

Page 103: ...he 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 d Lines 6 and 7 and if applicable lines 10 and 11 display a text message as specified in paragraph 3 E f...

Page 104: ...TP10 TP11 TP12 TP13 A B C D E F G H J K A B C D E F G H J K A B C D E F G H J K A B C D E F G H J K Hex Digits 0 1 2 3 4 5 6 7 8 9 c 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 d 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 e Line 10 1 This ...

Page 105: ...as ACTIVE or INACTIVE b Line 5 1 This line displays the DUAL SYS SELECT status of the SDU dual system select discrete input as ACTIVE or INACT c Line 6 1 This line displays the DUAL SYS DISABLE status of the SDU dual system disable discrete input as ACTIVE or INACT d 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 ...

Page 106: ... setting value 0 or 1 in parentheses is as follows 1 open circuit and 0 tied to common 2 Data Fields a 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 b 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 T...

Page 107: ...M CMUS left justified as determined by the state of system configuration pin TP10D e 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 1 Data Fields a Line 4 1 This line displays F 0 HS 429 ICAO ADRS or F 1 LS 429 I...

Page 108: ...state of system configuration pin TP10G c 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 d 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 e Line 12 1 This line displays K 0 LAMP ON CALL INIT or K 1 LAMP ON CALL C...

Page 109: ...stified as determined by the state of system configuration pin TP11A and the result of the parity validation test b 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 c 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 config...

Page 110: ...nes 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 whe...

Page 111: ...stem Configuration Pin System Configuration Pin Settings 1 open circuit 0 tied to common TP11E 1 0 1 0 1 1 All Other Pin Combinations TP11F 1 1 0 0 1 1 TP11G 1 1 1 1 1 1 TP11H 1 1 1 1 0 0 TP11J 1 1 1 1 1 0 TP11K 1 1 1 1 1 0 Textual Message Textual Messages To Display Based On System Configuration Pin Settings LO GAIN ANT DLNA X X X HPA LO GAIN X X X HI GAIN ANT BSU T L X X X X HI GAIN ANT BSU R X ...

Page 112: ...f 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 b Line 10 1 Th...

Page 113: ...8 Sheet 7 Configuration Data Table 6 12 Textual Message Display Page 7 Lines 4 5 and 6 System Configuration Pin System Configuration Pin Settings 1 open circuit 0 tied to common TP12A 0 0 1 1 0 All Other Pin Combinations TP12B 0 1 0 1 1 TP12C 1 0 0 1 1 Textual Message Textual Messages To Display Based On System Configuration Pin Settings MCDONNELL DOUGLAS X AIRBUS X BOEING X NOT INSTALLED X ERROR ...

Page 114: ...F b 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 c 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 d Line 10 1 This line displays J 0 SCDU1 INSTALLED or J 1 SCDU1 NOT INSTALLED left justified as ...

Page 115: ...55 Figure 6 8 Sheet 8 Configuration Data j CONFIGURATION DATA Page 9 Figure 6 8 sheet 9 1 Data Fields a 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 b 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 pi...

Page 116: ...resents 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 d Line 1...

Page 117: ...sheet 10 1 Data Fields a 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...

Page 118: ...mission of Honeywell Page 6 58 Figure 6 8 Sheet 10 Configuration Data c 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 ...

Page 119: ...uration Pin Settings AMS 1 WIRED CABIN 1 WIRED Line 4 Line 5 X AMS 1 WIRED CABIN 1 NOT WIRED Line 4 Line 5 X AMS 1 NOT WIRED CABIN 1 WIRED Line 4 Line 5 X AMS 1 NOT WIRED CABIN 1 NOT WIRED Line 4 Line 5 X Table 6 15 Textual Message Display Page 10 Lines 8 and 9 System Configuration Pin System Configuration Pin Settings 1 open circuit 0 tied to common TP13H 0 0 1 1 TP13J 0 1 0 1 Textual Message Tex...

Page 120: ...onal Inc Do not copy without express permission of Honeywell Page 6 60 l CONFIGURATION DATA Page 11 Figure 6 8 Sheet 11 1 General a 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 1 General a Page 12 of the CONFIGURATION DATA page is shown below ...

Page 121: ...TION DATA Page 13 Figure 6 8 Sheet 13 1 Data Fields a 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 b 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 c Line 6 1 This line displays the DUAL SYS SELECT status of SDU Dual Sys...

Page 122: ...ND STAT beginning in column 1 HGA beginning in column 15 and LGA beginning in column 22 b 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 ...

Page 123: ... 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...

Page 124: ...played 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 f 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 f...

Page 125: ...flected power is at the maximum of 25 056 Watts The HPA indicates the over range condition through the solo word ratio value of FFH h Line 10 1 This line displays CARRIER beginning in column 1 i 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...

Page 126: ... 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 1 Field 1L a 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...

Page 127: ...Jul 2006 Honeywell International Inc Do not copy without express permission of Honeywell Page 6 67 b READY must be displayed before data uploading or downloading can be performed c 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 ...

Page 128: ...NTENANCE MANUAL MCS 4200 7200 Multi Channel SATCOM System 23 20 35 15 Jul 2006 Honeywell International Inc Do not copy without express permission of Honeywell Page 6 68 Figure 6 9 Sheet 2 DATA LOADER MENU Figure 6 9 Sheet 3 DATA LOADER MENU ...

Page 129: ...ded 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 e 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...

Page 130: ...t 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 d Uploads are allowed regardless of the log on state composite uploads are inhibited only by ORT item liv and not the log on state e Once a left LS key is pushed the SEL message is displayed to the right of the selected data loader action right just...

Page 131: ...at that time the data line display changes as appropriate 4 Field 6L a 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 b The SDU completes the upload download data transfer by command...

Page 132: ...st 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 ...

Page 133: ...INSTALLATION AND MAINTENANCE MANUAL MCS 4200 7200 Multi Channel SATCOM System 23 20 35 15 Jul 2006 Honeywell International Inc Do not copy without express permission of Honeywell Page 6 73 Figure 6 10 LAST LEG REPORT Page ...

Page 134: ... 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...

Page 135: ...LATION AND MAINTENANCE MANUAL MCS 4200 7200 Multi Channel SATCOM System 23 20 35 15 Jul 2006 Honeywell International Inc Do not copy without express permission of Honeywell Page 6 75 Figure 6 11 Sheet 1 PREVIOUS LEG REPORT Page ...

Page 136: ...LATION AND MAINTENANCE MANUAL MCS 4200 7200 Multi Channel SATCOM System 23 20 35 15 Jul 2006 Honeywell International Inc Do not copy without express permission of Honeywell Page 6 76 Figure 6 11 Sheet 2 PREVIOUS LEG REPORT Page ...

Page 137: ...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 ea...

Page 138: ... 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...

Page 139: ...LATION AND MAINTENANCE MANUAL MCS 4200 7200 Multi Channel SATCOM System 23 20 35 15 Jul 2006 Honeywell International Inc Do not copy without express permission of Honeywell Page 6 79 Figure 6 12 Sheet 1 LRU IDENTIFICATION Page ...

Page 140: ...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 l...

Page 141: ... UTC beginning in column 8 The date and time are displayed as follows b 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 c The day is displayed as dd where dd represents the day of the month from 01 to 31 d The UTC is displayed as hh mm where hh represents the UTC hours from 00 to 23 and mmm represents the UTC minutes fr...

Page 142: ...TALLATION AND MAINTENANCE MANUAL MCS 4200 7200 Multi Channel SATCOM System 23 20 35 15 Jul 2006 Honeywell International Inc Do not copy without express permission of Honeywell Page 6 82 Figure 6 13 TROUBLESHOOTING DATA Page ...

Page 143: ...ine 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 6 Line 9 a Line 9 displays the headers CLASS beginning in column 2 and IFC ...

Page 144: ...ALLATION AND MAINTENANCE MANUAL MCS 4200 7200 Multi Channel SATCOM System 23 20 35 15 Jul 2006 Honeywell International Inc Do not copy without express permission of Honeywell Page 6 84 Figure 6 14 LAST LEG CLASS 3 FAULTS Page ...

Page 145: ... 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 display...

Page 146: ... INSTALLATION AND MAINTENANCE MANUAL MCS 4200 7200 Multi Channel SATCOM System 23 20 35 15 Jul 2006 Honeywell International Inc Do not copy without express permission of Honeywell Page 6 86 Figure 6 15 GROUND REPORT Page ...

Page 147: ...lumn 2 and the UTC beginning in column 8 The date and time are displayed as follows 2 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 3 The day is displayed as dd where dd represents the day of the month from 01 to 31 4 The UTC is displayed as hh mm where hh represents the UTC hours from 00 to 23 and mm represents the U...

Page 148: ...ON AND MAINTENANCE MANUAL MCS 4200 7200 Multi Channel SATCOM System 23 20 35 15 Jul 2006 Honeywell International Inc Do not copy without express permission of Honeywell Page 6 88 Figure 6 16 GROUND REPORT TROUBLE SHOOTING DATA Page ...

Page 149: ... leg Dashes are displayed if no valid UTC data is available 3 Line 6 displays the power on count value from 0 to 65535 right justified from column 23 e Line 7 1 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 gro...

Page 150: ...te 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 functiona...

Page 151: ...e command 4 Configuration Data Messages a General 1 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 t...

Page 152: ...ronym 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 f LRU SERIAL NUMBER 1 The serial numbers of the LRUs installed are displayed as...

Page 153: ...eporting 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 m...

Page 154: ...ount 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 ...

Page 155: ...d 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 ...

Page 156: ... particular interface Table 6 18 Boeing Level I Failure Messages and ATA Reference Numbers Failure Code 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 IGA HGA 232500 23207 07 HPA LO GAIN 232500 23209 0A HI POWER RELAY 232500 23218 0D LNA DIP TOP PORT 232500 23210 0F LNA DIP STBD 232500...

Page 157: ...Do not copy without express permission of Honeywell 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 Boeing Level I Failure Messages and ATA Reference Numbers Failure Code SCDU Accessed Maintenance Pages ATA Number CMC Message ID 0B HDM 232500 ...

Page 158: ......

Page 159: ...46100 40 ARINC 429 ICAO ADDRESS None 23251 42 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 IGA HGA 232500 23226 5F HPA ...

Page 160: ...PA 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 23236 C1 SDU WOW MISCOMPARE N A C2 SDU OTHER SDU SELECT ...

Page 161: ...SET None CE RESERVED CF HPA IN GAIN POC TOTC DATA RESET HPA HI GAIN POC TOTC DATA RESET IGA HGA None D0 HPA LO GAIN POC TOTC DATA RESET None D1 WRG SDI PIN PROG HPA IN GAIN WRG SDI PIN PROG HPA HI GAIN IGA HGA 232500 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 IGA HGA 232500 23237 D6...

Page 162: ...N PROG HSU SDU OWNER REQS 232500 EE WRG FWD ID PIN PROG HSU 232500 FE POWER SUPPLY INTERRUPT None Table 6 19 Airbus Level I SDU No 1 Failure Messages and ATA No Failure Code SDU SDU No 1 CFDS Normal and Interactive Modes ATA Number 01 SDU1 105RV1 SDU1 5RV1 IGA HGA 232834 232834 02 SDU2 105RV2 SDU2 5RV2 INCOMPATIBILITY IGA HGA 232834 232834 03 HSDU1 63RV1 232839 04 HPA1 110RV1 HPA HI GAIN 7RV1 IGA ...

Page 163: ...c Do not copy without express permission of Honeywell 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 Airbus Level I SDU No 1 Failure Messages and ATA No Failure Code SDU SDU No 1 CFDS Normal and Interactive Modes ATA Number 0B HDM 232832 ...

Page 164: ......

Page 165: ... 232812 1C HI GAIN ANTENNA R 18RV Conformal 232812 1F LO GAIN ANTENNA 13RV 232811 21 MCDU1 2CA1 A330 A340 228212 MCDU1 3CA1 A320 228212 22 MCDU2 2CA2 A330 A340 228212 MCDU2 3CA2 A320 228212 23 MCDU3 2CA3 A330 A340 228212 MCDU3 3CA3 A320 228212 33 ATSU1 1TX1 ATSU 462134 ACARS MU 1RB A320 ACARS 232434 ACARS MU1 1RB1 A330 A340 ACARS 232434 34 ATSU2 1TX2 ATSU 462134 ACARS MU2 A320 ACARS 232434 ACARS M...

Page 166: ...US SDU1 5RV1 IFE 429 BUS SDU1 105RV1 IFE 429 BUS SDU1 105RV1 IFE 429 BUS SDU1 5RV1 A330 A340 HGA A330 A340 HGA A320 IGA A320 HGA 233000 233000 53 ATSU1 1TX1 SDU1 105RV1 IGA ATSU 462134 ATSU1 1TX1 SDU1 5RV1 HGA ATSU 462134 ACARS MU 1RB SDU1 105RV1 IGA A320 ACARS 232434 ACARS MU1 1RB1 SDU1 105RV1 IGA A330 A340 ACARS 232434 ACARS MU 1RB SDU1 5RV1 HGA A320 ACARS 232434 ACARS MU1 1RB1 SDU1 5RV1 HGA A33...

Page 167: ...32434 59 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 5A ADIRU1 1FP1 SDU1 105RV1 ADIRU1 1FP1 SDU1 5RV1 IGA HGA 341234 341234 5B ADIRU2 1FP2 SDU1 105RV1 ADIRU2 1FP2 SDU1 5RV1 IGA HGA 341234 341234 5C HPA1 110RV1 SDU1 105RV1 HPA HI GAIN 7RV1 SDU1 5RV1 IGA HGA 232831 232831 5F HPA LO GAIN ...

Page 168: ...FMGEC1 1CA1 SDU1 5RV1 HGA A330 A340 228334 74 FMGC2 1CA2 SDU1 105RV1 IGA A320 228334 FMGEC2 1CA2 SDU1 105RV1 IGA A330 A340 228334 FMGC2 1CA2 SDU1 5RV1 HGA A320 228334 FMGEC2 1CA2 SDU1 5RV1 HGA A330 A340 228334 80 RESERVED 82 RESERVED 88 RESERVED 90 SDU1 105RV1 BUS M CTRL HPA1 110RV1 IGA 232834 SDU1 5RV1 BUS M CTRL HPA HI GAIN 7RV1 HGA 232834 96 SDU1 5RV1 BUS M CTRL HPA LO GAIN 9RV HGA LGA 232834 S...

Page 169: ...U 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 WRG CONFIG PIN PROG SDU1 5RV1 HGA 232800 C1 LGCIU1 5GA1 LGCIU2 5GA2 SDU1 105RV1 IGA 323171 LGCIU1 5GA1 LGCIU2 5GA2 SDU1 5RV1 HGA 323171 C2 SDU1 105RV1 SEL DISABLE DISCRETE SDU2 105RV2 IGA 232834 SDU1 5RV1 SEL DISABLE DISCRETE SDU2 5RV2 HG...

Page 170: ...DU1 105RV1 CTRL DISCRETE DLNA LO GAIN 14RV IGA LGA 232834 CB WRG SDI PIN PROG HPA1 110RV1 IGA 232800 WRG SDI PIN PROG HPA HI GAIN 7RV1 HGA 232800 CC WRG SDI PIN PROG HPA LO GAIN 9RV 232800 CD N A 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 WRG SDI PIN PR...

Page 171: ...ER REQS DB SECURED PARTITION IGA 232834 SDU1 5RV1 OWNER REQS DB SECURED PARTITION HGA 232834 DE SDU1 105RV1 OWNER REQS DB USER PARTITION IGA 232834 SDU1 5RV1 OWNER REQS DB USER PARTITION HGA 232834 DF SDU1 105RV1 LOG ON FAILURE IGA 232834 SDU1 5RV1 LOG ON FAILURE HGA 232834 E0 RESERVED E1 SDU1 5RV1 DISCRETE HSDU1 63RV1 232834 E2 N A N A E3 N A N A to Airbus E4 SDU1 5RV1 HSDU1 63RV1 232834 E5 N A N...

Page 172: ...des ATA Number 01 SDU2 105RV2 SDU2 5RV2 IGA HGA 232834 232834 02 SDU1 105RV1 INCOMPATIBILITY SDU1 5RV1 INCOMPATIBILITY IGA HGA 232834 232834 03 HSDU2 63RV2 232839 04 HPA2 110RV2 HPA HI GAIN 7RV2 IGA HGA 232831 232831 07 HPA LO GAIN 9RV 232835 0A HI POWER RELAY 21RV 232842 0D DLNA2 119RV2 DLNA TOP 19RV2 DLNA L 20RV3 IGA Top Mount Conformal 232838 232838 232837 0F DLNA R 20RV4 Conformal 232837 10 DL...

Page 173: ...c Do not copy without express permission of Honeywell 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 Airbus Level I SDU No 2 Failure Messages and ATA No Failure Code SDU SDU No 2 CFDS Normal and Interactive Modes ATA Number 0B HDM 232832 ...

Page 174: ......

Page 175: ...A340 ACARS 232434 34 ATSU2 1TX2 ATSU 462134 ACARS MU 1RB A320 ACARS 232434 ACARS MU2 1RB2 A320 A340 ACARS 232434 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 A320 A330 A340 228334 228334 3E FMGC2 1CA2 FMGEC2 1CA2 A320 A330 A340 228334 228334 40 ARINC 429 ICAO 232800 42 CTU CU CEPT E1 BUS SDU2 105RV2 CTU CU CEPT E1 BUS SDU2 10...

Page 176: ...0 232434 ACARS MU 1RB SDU2 105RV2 IGA ACARS A320 232434 ACARS MU1 1RB SDU2 5RV2 HGA ACARS A320 232434 54 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 55 MCDU1 2CA1 SDU2 105RV2 MCDU1 2CA1 SDU2 5RV2 MCDU1 3CA1 SDU2 105RV2 MCDU1 3CA1 SDU2 5RV2 IGA A330 A...

Page 177: ... 341234 ADIRU1 1FP1 SDU2 5RV2 HGA 341234 5B ADIRU2 1FP2 SDU2 105RV2 IGA 341234 ADIRU2 1FP2 SDU2 5RV2 HGA 341234 5C HPA2 110RV2 SDU2 105RV2 IGA 232831 HPA HI GAIN 7RV2 SDU2 5RV2 HGA 232831 5F HPA LO GAIN 9RV SDU2 5RV2 HPA LO GAIN 9RV SDU2 105RV2 HGA LGA IGA LGA 232835 232835 62 BSU 8RV2 SDU2 5RV2 BSU L 15RV3 SDU2 5RV2 Top Mount Conformal 232846 232844 64 BSU R 15RV4 SDU2 5RV2 Conformal 232844 66 MC...

Page 178: ...34 FMGC2 1CA2 SDU2 5RV2 HGA A320 228334 FMGEC2 1CA2 SDU2 5RV2 HGA A330 A340 228334 80 RESERVED 82 RESERVED 88 RESERVED 90 SDU2 105RV2 BUS M CTRL HPA2 110RV2 IGA 232834 SDU2 5RV2 BUS M CTRL HPA HI GAIN 7RV2 HGA 232834 96 SDU2 5RV2 BUS M CTRL HPA LO GAIN 9RV SDU2 105RV2 BUS M CTRL HPA LO GAIN 9RV HGA LGA IGA LGA 232834 232834 98 SDU2 5RV2 BUS M CTRL BSU 8RV2 Top Mount 232834 SDU2 5RV2 BUS M CTRL BSU...

Page 179: ...V2 WRG CONFIG PIN PROG SDU2 5RV2 IGA HGA 232800 232800 C1 LGCIU1 5GA1 LGCIU2 5GA2 SDU2 105RV2 IGA 323171 LGCIU1 5GA1 LGCIU2 5GA2 SDU2 5RV2 HGA 323171 C2 SDU2 105RV2 SEL DISABLE DISCRETE SDU1 105RV1 IGA 232834 SDU2 5RV2 SELECT DISABLE DISCRETE SDU1 5RV1 HGA 232834 C3 WRG ICAO ADDRESS PIN PROG SDU2 105RV2 IGA 232800 WRG ICAO ADDRESS PIN PROG SDU2 5RV2 HGA 232800 C4 HPA2 110RV2 COAX IGA 232831 HPA HI...

Page 180: ... HGA 232800 CC WRG SDI PIN PROG HPA LO GAIN 9RV 232800 CD N A N A CE RESERVED CF N A N A D0 N A N A D1 WRG SDI PIN PROG HPA2 110RV1 IGA 232800 WRG SDI PIN PROG HPA HI GAIN 7RV2 HGA 232800 D2 WRG SDI PIN PROG HPA LO GAIN 9RV 232800 D3 WRG SDI PIN PROG BSU 8RV2 WRG SDI PIN PROG BSU L 15RV3 Top Mount Conformal 232800 232800 D4 WRG SDI PIN PROG BSU R 15RV4 Conformal 232800 D5 SDU2 105RV2 TXCOAX IGA 23...

Page 181: ...ITION HGA 232834 DE SDU2 105RV2 OWNER REQS DB USER PARTITION IGA 232834 SDU2 5RV2 OWNER REQS DB USER PARTITION HGA 232834 DF SDU2 105RV2 LOG ON FAILURE IGA 232834 SDU2 5RV2 LOG ON FAILURE HGA 232834 E0 RESERVED E1 SDU2 5RV2 DISCRETE HSDU2 63RV2 232834 E2 N A N A E3 N A N A E4 SDU2 5RV2 HSDU2 63RV2 232834 E5 N A N A E6 HSDU2 63RV2 TXCOAX 232839 E7 N A N A E8 HSDU2 63RV2 RXCOAX 232839 E9 N A N A EA ...

Page 182: ... 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 232...

Page 183: ...Do not copy without express permission of Honeywell 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 McDonnell Douglas Level I Failure Messages and ATA Reference Numbers Failure Code CFDS Normal and Interactive Modes ATA Number 0B HDM 232664 ...

Page 184: ......

Page 185: ...C 429 ICAO ADDRESS N A 42 CTU 232644 43 CFS CPDF TBD 50 HSU SDU 232664 52 CFS CPDF SDU TBD 53 ACARS MU CMU SDU 23263C 54 CTU SDU 232644 55 MCDU1 SDU 232635 56 MCDU2 SDU 232636 57 ACARS MU CMU 2 SDU N A 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 5F HPA LO GAIN SDU 232623 62 BSU TOP L SDU 232626 64 BSU R SDU 23...

Page 186: ...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 N A C2 SDU OTHER SDU SELECT DISABLE DISCRETE 232600 C3 WRG ICAO ADDRESS PIN PROG ...

Page 187: ...one CE RESERVED CF HPA IN GAIN POC TOTC DATA RESET HPA HI GAIN POC TOTC DATA RESET IGA HGA None None D0 HPA LO GAIN POC TOTC None D1 WRG SDI PIN PROG HPA IN GAIN WRG SDI PIN PROG HPA HI GAIN IGA HGA 232600 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 SDU COAX HPA HI GAIN IGA HGA 232600 232600 D6 SDU COAX...

Page 188: ...evel I Failures Messages and ATA Reference Numbers cont Failure Code ATA Number CFDS Normal and Interactive Modes E2 RESERVED E3 RESERVED E4 HSU SDU INTERFACE VER INCOMPATIBILITY 232664 E5 RESERVED E6 HSU HPA TX RF PATH 232664 E7 RESERVED E8 DLNA HSU RX RF PATH 232664 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 H...

Page 189: ...S 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 rem...

Page 190: ...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 t...

Page 191: ...LENT 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 adju...

Page 192: ...mended 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 prio...

Page 193: ...LL 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 br...

Page 194: ...h 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...

Page 195: ... 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 refe...

Page 196: ...ESCRIPTION INSTALLATION AND MAINTENANCE MANUAL MCS 4200 7200 Multi Channel SATCOM System 23 20 35 15 Jul 2006 Honeywell International Inc Do not copy without express permission of Honeywell Page 7 6 Blank Page ...

Page 197: ...vidual 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 ...

Page 198: ...9122 L7122 L7122 ARINC 600 Size 5 N A N A A650922 A650922 225791 2 225791 2 Table A 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...

Page 199: ...ON AND MAINTENANCE MANUAL MCS 4200 7200 Multi Channel SATCOM System 23 20 35 15 Jul 2006 Honeywell International Inc Do not copy without express permission of Honeywell Page A 3 Figure A 1 ARINC Connectors Figure A 2 ARINC Assembly ...

Page 200: ... 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 ...

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