Transcript
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AVS aboard ATR -600 Maintenance Function
6 7 4 1 0 0 / 1 1 / W S A : D E G
Thales Avionics
AVS aboard ATR ATR -600
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> Centralized Maintenance Introduction Maintenance includes includes CMF CMF and and BITE » Maintenance functions
» CMF CMF has has two Modes
Normal Mode
Interactive Mode
CAC #1
» CMF sub-functions
6 7 4 1 0 0 / 1 1 / W S A : D E G
Maintenance and configuration data processing
Interactive tests and specific actions
CFM NVM storage
Correlation
General parameters providing
Interactions with operator and MCDU pages displaying
AVS alarms transmission to MPC
CMF is mainly realized by the CMA CMF is SW application that operates only in CAC1
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> Centralized Maintenance Introduction Maintenance includes includes CMF CMF and and BITE » Maintenance functions
» CMF CMF has has two Modes
Normal Mode
Interactive Mode
CAC #1
» CMF sub-functions
6 7 4 1 0 0 / 1 1 / W S A : D E G
Maintenance and configuration data processing
Interactive tests and specific actions
CFM NVM storage
Correlation
General parameters providing
Interactions with operator and MCDU pages displaying
AVS alarms transmission to MPC
CMF is mainly realized by the CMA CMF is SW application that operates only in CAC1
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> BITE Function Purpose and Architecture BITE Function
» Ensures concentration and processing of sub-system maintenance data from continuous monitoring (CBIT) and automatic test at power on (ABIT), and provides these data to the CMF
» And also, according according to sub-system, sub-system, gives more information information about failures failures (failure context) context) in order to help shop maintenance teams.
» Includes the set of BITE functions implemented in each AVS sub-system:
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COTS Sub-systems having BITE function with pre-determined functionalities,
Non COTS Sub-systems having specific functionalities in the AVS context (IAD, CAC)
BITE Function of COTS
CMF
BITE Function of non-COTS
APPLI n
COTS sub-system Non-COTS sub-system
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> BITE Function Modes and Interfaces
» The BITE function operates
Normal mode
Interactive mode (processing of interactive requests from CMF)
Interfaces with
» CMF according to the sub-system type (1 or 2) the BITE function of COTS and NonCOTS sub-systems exchanges
» Sub-functions and modes Ident.
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Sub-Function
Normal Interactive Mode Mode
F01
CBIT reporting
X
-
F02
Test and Specific actions
-
X
F03
BITE function NVM storage
X
X
F04
General parameters acquisition
X
X
F05
LRU identification data transmission
X
X
Maintenance data,
General parameters, if needed,
Interactive commands.
» Avionics application
Maintenance data with their associated context
Interactive commands, if needed
» Programming pins BITE function of non COTS LRU acquires their side/position through Programming pins, and use, by default side 1, if acquisition failed
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> Failures Classification and Sub-System Types Failure Class
Sub-System Types
» Class 1
» Type 1 with one A429 numeric bus in input
Failure leading to a flight deck effect (highest class)
» Class 2 Minor failures without flight deck effects (lowest class).
and one A429 numeric bus output
C M F
ARINC bus
Unit ARINC bus
Those failures require deferred maintenance HF1, HF2, VHF1 NAV, VHF2 NAV, DME1, DME2, VHF COM1, VHF COM2, VHF COM3, DU1, DU2, DU3, DU4, DU5, CAC1, CAC2, CMU, ATC
Notes
6 7 4 1 0 0 / 1 1 / W S A : D E G
An external failure is a failure present on a LRU input
Any CMF failure that induces a lost of redundancy is defined as a Class 1 failure
» Type 2 with one discrete input and one A429 numeric bus output
C M F
ARINC bus
Unit
IRS1, IRS2, ADU1, ADU2, AHRS1, AHRS2
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> Maintenance Messages and Architecture
» Access to CMA via A429
VHF COMVDL2, T2CAS, RA, CMU, ATC XPDR, ADU, IRS, AHRS, VHF NAV, VHF NAV&ADF, MCDU
» Access to CMA via AFDX
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VHF COM, HF COM, DME, GPS, CPM CBITE, IAD, WXR
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> CMF - Transmission of Maintenance Data - via DU Case 1
Case 2
Case 3
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Case 4
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> CMF - Transmission of Maintenance Data - via CAC
LRU FGCP, ICP1 ,ICP2, CPSTN1, CPSTN2, CPSTN3, SM1, SM2, SM3, PTB1, PTB2, IOM-AP1, IOM-AP2, IOM-DC11, IOM-DC12, IOM-DC21, IOM-DC22, IOM-S1, IOM-S2 Appli
AFA, DCA, CSW
Transmission of Maintenance Data - from CAC2
6 7 4 1 0 0 / 1 1 / W S A : D E G
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> CMF - Types of Messages
» Bit Oriented Format (BOF) For A429 A set of bits where each failure is coded by using one or n bits transmitted by 1 or n A429 words
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Bit Location
Bit Description
8-1
Label (octal)
10 - 9
SDI, MSB = 10, LSB = 9
29 - 11
Failures indication (some bits may be not used according to sub-system)
31 - 30
SSM MSB = 31, SSM LSB = 30
32
Odd Parity
» Basic Failure Message (BFM) For AFDX A set of bits where each failure is coded by using one or n bits transmitted by 1 or n Functional Data Set of AFDX message Field Name
Size
Format
Functional Block ID
4
Integer
Vendor ID BITE Event Type BITE EVENT ID Info 1 Info 2 Info 3 BITE Event State Sanction Engineering Data Length
4 4 4 4 4 4 4 4
Integer Integer Integer Integer Integer Integer Integer Integer
4
Integer
Engineering Data
0 - 83 Table of Bytes
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> CMF Purpose and Architecture Centralized Maintenance Function
» Ensures the concentration and processing of AVS maintenance data received from BITE function, and makes them available to the Operator via reports displayed on MCDU pages.
» Offers to the maintenance Operator a set of services via MCDU pages in order to make a diagnostic that permits to identify most clearly possible root cause of a problem occurrence in AVS, such as:
Display of configuration report
Display failures reports (current failures and historical),
Possibility to initiate interactive tests
Note: CMF displays its MCDU pages via MPC (out of AVS). Date, Time, A/C configuration, Flight ground conditions
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BITE Function 1 BITE Function 2 CMF BITE Function n Maintenance data General parameters Interactive commands
MCDU#1 MPC
MCDU pages
MCDU pages MCDU#2
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> CMF Modes Maintenance phase is "Ground" and Power-up
action of the operator on a dedicated key from Maintenance MCDU pages CMF
Power cut
CMF Interactive mode
Normal mode
or re-initialization Power cut or re-initialization or ending of interactive mode by the operator or Maintenance phase become “Flight” or default in communication between the MCDU and the CMF. 6 7 4 1 0 0 / 1 1 / W S A : D E G
CMF is in normal mode by default
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> CMF External Interfaces
» Interface with MPC for MCDU
CMF exchanges data with the MCDU (requests/responses from protocol + MCDU pages) via MPC CMF communicates with MPC in A739 that manages the communication with MCDU
» Interface for Clock
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CMF acquires Date, Time (in this order) from CLOCK1, or CLOCK2 in case of failure, or FMS1 in case of failure, or then FMS2 in case of failure CMA1 receives from •
DCA1 date, time from CLOCK1
•
DCA2 date, time from CLOCK2
•
FMS1 date, time
•
FMS2 date, time
» Flight phase acquisition CMF acquires flight phase from MPC
» Peripheral availability acquisition CMF acquires periodically peripheral availability label from MPC Printer and PCMCIA disk
» Interface for Avionic options and A/C configuration
CMF acquires AVS configuration file from FDA
» Programming pins CMF acquires Programming Pins from CPM1 and CPM2
» Date and Time Stamping CMF provides general parameters (Date, Time, A/C Identification, Maintenance command to Type 1 sub-systems
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> Typical Scenario When the A/C is on Ground phase, the maintenance Operator consults failures reports in order to isolate the failure.
» Failures messages accuse clearly a LRU
several LRU The Operator consults its database of maintenance procedures (out of CMF scope) and applies the usual procedure related to a problem of link.
» Failures messages indicate more than
Then, he consults its Trouble Shouting Manual (TSM) and Minimum Equipment List (MEL), and applies the maintenance procedure related to the LRU identified as failed. In case this procedure recommends to change the LRU, the maintenance Operator
one possibility
He removes / replaces the accused LRU,
Verifies the good operation by using current failures report or interactive test from the CMF.
6 7 4 1 0 0 / 1 1 / W S A : D E G
The Operator launches an interactive test on the sub-system containing the LRU to confirm the failure.
» Failure messages accuse a link between
The maintenance Operator has to complete the diagnostic by his own means.
He may use current failures report of the CMF to verify if each operation performed has an effect on the problem.
When the diagnostic is ended and the problem isolated the maintenance Operator conducts the relevant maintenance tasks.
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> CMF - Functional and Performance Data
» CFM NVM storage CMF stores failures detected in flight (filtered with the appropriated correlation and configuration), and needed data reported from AVS in Non Volatile Memory (NVM) non-erasable
» PREVIOUS LEGS REPORT CMF stores in NVM up to 300 class 1 failures that occurred during the previous 63 legs, the oldest failures being replaced by the newest ones
» LAST LEG REPORT 6 7 4 1 0 0 / 1 1 / W S A : D E G
CMF stores in NVM up to 50 class 1 of the last leg failures by applying the following rules - The possibility is offered to store at least one message for each subsystem - The oldest failures being replaced by the newest ones
» LAST LEG REPORT At the start of a new leg, all the messages from last leg are transferred in the previous legs zone of the NVM to allow their display in the PREVIOUS LEGS REPORT menu.
» MAINT REPORT CMF stores in NVM up to 300 class 2 failures occurred during the 64 last legs by applying the following rules - The possibility is offer to store at least one message for each subsystem in a leg - The oldest failures being replaced by the newest ones
» No fault redundancy in a leg The detection of a system failure which is identical to a most recent failure logged in NVM is not repeated in the same leg.
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> CMF - Maintenance and Flight Phases
Flight phase
Maintenance phase Maintenance command
1
2
Pre Flight
Taxi out
Leg count
4
TO init. TO final roll initial roll final
5
6
7
8
9
Initial
Flight Phase
Final App.
LDG roll
Taxi In
climb
10
Flight
Ground
Pre
Flight
Flight
Ground
30 S min
NULL
DC2
DC1
NULL
Last leg
+1
Failures Storage criteria 6 7 4 1 0 0 / 1 1 / W S A : D E G
1
Post
+30 S
Previous leg
Leg
3
When maintenance command is DC2, only internal failures are stored in NVM
When maintenance command is DC1 internal failures and external failures are stored in NVM
When no valid Flight Phase available, Maint. Phase = Flight, Maint. Command = DC1
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> CMF - MCDU Pages PROMPT « AVS »
AVS MAIN MENU
AVIONICS
LAST LEG
PREVIOUS LEGS
STATUS
REPORT
REPORT
LAST LEG REPORT 6 7 4 1 0 0 / 1 1 / W S A : D E G
SUB-SYST n
PREVIOUS LEGS REPORT SUB-SYST n
SYS REPORT / TEST
MAINT
SUB-SYST LIST
LRU IDENT SUBSYST LIST
SUB-SYST n
LRU IDENT
MAIN MENU
SUB-SYST n
AVS AND A/C OPT CONF
MAINT
TESTS
LRU IDENT
SUB-SYST n
SUB-SYST n
SUB-SYST n
TEST RESULTS
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> MCDU General Presentation
LSK L1 LSK L2 LSK L3 LSK L4 LSK L5 LSK L6
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AVS < AVIONICS STATUS
SYSTEM > REPORT / TEST
LSK R1 LSK R2
< LAST LEG REPORT
MAINT >
LSK R3
LRU IDENT >
LSK R4
AVS AND A/C > OPT CONF
LSK R5
< PREVIOUS LEGS REPORT < RETURN
PRINT *
Example of CMF MCDU Main Menu
LSK R6
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> CMF - AVIONICS STATUS REPORT description
» AVIONICS STATUS
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Faulty LRU are ordered Class 1 first and alphabetically
CONF_UPDATED_MESSAGEs in first, and then failed LRUs, and at last other error messages When during 5 seconds, there is no data or invalid data received by CMF from an avionic LRU, CMF displays "NO DATA FROM LRU i" or "INVALID DATA FROM LRU i“ The displayed pages are not automatically refreshed
AVIONICS STATUS
1/N CLASS
>
CONF_UPDATED _MESSAGE
>
NO POWER SUPPLY FROM BUSBARx
<
>
>
< X>
<
< PRINT *
<
Case of failure recorded
AVIONICS STATUS
>
<
> >
< NO FAULT REPORTED
<
>
<
>
<
>
< RETURN
PRINT *
No fault recorded
<
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> CMF - LAST LEG REPORT
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Description
» LAST LEG
6 7 4 1 0 0 / 1 1 / W S A : D E G
Displays Class 1 failures from AVS stored in NVM and occurred during the last leg when maintenance phase was "Flight“
The date and the time of the failure are the first failure occurrence date and first detection time of the failure
The ATA code of failure is the code of the highest suspect LRU
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LAST LEG REPORT 1/N >
DATE MAR 05
>
MESSAGE 1
TIME 1910
ATA 31-50-00
<
>
< <
> MAR 05 MESSAGE 2
>
1902
34-00-00
>
< <
> < RETURN
>
PRINT *
<
SUB-SYSTEM NAME
The most recent failure messages is listed first
>
< LAST LEG REPORT
<
>
< PREVIOUS LEGS REPORT
<
>
< SYSTEM TEST /
<
SPECIFIC ACTION
>
< MAINT
<
>
< LRU IDENT
<
>
< RETURN
PRINT *
<
or LAST LEG REPORT >
>
> >
> NO FAULT REPORTED
>
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> CMF - PREVIOUS LEG REPORT
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Description
» PREVIOUS LEG
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PREV LEGS REPORT 1/N A/C IDENT DATE LEG MAR 10 01 MESSAGE 1
>
Displays Class 1 failures from AVS stored in NVM and occurred during the previous 63 legs when maintenance phase was "Flight“
>
02 MAR 05 MESSAGE 2
1902
34-00-00
< <
< RETURN
>
PRINT *
<
PREV LEGS REPORT >
<
> >
At the start of a new leg
The leg 64 (if it exists) deleted from NVM
<
>
Use PREV key to display the oldest flight
•
<
<
>
The first displayed failure is the most recent failure of the most recent leg
The flight leg number of PREVIOUS LEG REPORT is incremented, and
ATA 31-50-00
>
Only the failures that have occurred on the same A/C (same A/C Identification) are reported on a same page
•
TIME 1910
<
NO FAULT REPORTED
<
>
<
>
<
>
< RETURN
PRINT *
<
LEG 00
Last Leg
LEG 01
First previous leg
LEG 02
Previous leg preceding LEG 01
…
…
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> CMF - SYSTEM REPORT / TEST Description
» SYSTEM REPORT / TEST
6 7 4 1 0 0 / 1 1 / W S A : D E G
Displays the list of all sub-systems names managed by CMF
An action on the LSK associated with a prompt lets the Operator enter the main menu of the relevant sub-system If the sub-system is not fitted on the A/C (see AVS configuration file), the information NOT FITTED is displayed on the line following the name of the subsystem, and the prompt sign in front of the LRU removed. Note: If the Operator uses the corresponding line key, the menu currently displayed does not change Navigation by means of keys
SYSTEM REPORT/TEST
SYSTEM REPORT/TEST
2/4
< CAC1
DU2 >
< HF1
VHF NAV&ADF1 >
< CAC2
DU3 >
< HF2
VHF NAV2 >
< MCDU1
DU4 >
< VHF COM1
DME1 >
< MCDU2
DU5 >
< VHF COM2
DME2 >
< DU1
CMU >
< VHF COM3
GPS1 >
< RETURN
PRINT *
< RETURN
PRINT *
SYSTEM REPORT/TEST
3/4
SYSTEM REPORT/TEST
XPDR2/T2CAS >
< IRS1
< RA1
ADC1 >
< IRS2
< RA2
ADC2 >
< WXR
AHRS1 >
< XPDR1/ T2CAS
AHRS2 >
< GPS2
< RETURN
PREV … NEXT
1/4
PRINT *
4/4
< AFCS
< RETURN
PRINT *
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> CMF - SYSTEM REPORT / TEST Description (Cont’d)
» SYSTEM REPORT / TEST
SUB-SYSTEM NAME
Type 1 / 2 systems main menu
When no SYSTEM TEST and no SPECIFIC ACTION then line associated to third key is empty, when no LRU IDENT available for the system then line associated to fifth key is empty
>
< LAST LEG REPORT
<
>
< PREVIOUS LEGS REPORT
<
>
< SYSTEM TEST /
<
SPECIFIC ACTION
>
< MAINT
<
>
< LRU IDENT
<
>
< RETURN
Note: AHRS implements a specific action: flux valve calibration
SUB-SYSTEM NAME LAST LEG REPORT DATE MAR 05 MESSAGE 1
>
» LAST LEG REPORT for Type 1/ 2 system
>
6 7 4 1 0 0 / 1 1 / W S A : D E G
TIME 1910
1/N
ATA 31-50-00
< <
>
Displays only failure messages related to the selected sub-system contained in LAST LEG REPORT of all AVS
<
PRINT *
< MAR 05
>
1902
34-00-00
<
MESSAGE 2
>
<
>
< RETURN
or
PRINT *
<
SUB-SYSTEM NAME LAST LEG REPORT >
>
> >
> NO FAULT REPORTED
>
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> CMF - SYSTEM REPORT / TEST Description (Cont’d)
» PREVIOUS LEG REPORT for Type 1 / 2
SUB-SYSTEM NAME
system Displays only Class 1 failure messages related to the selected sub-system contained in PREVIOUS LEGS REPORT of all AVS
>
< LAST LEG REPORT
<
>
< PREVIOUS LEGS REPORT
<
>
< SYSTEM TEST /
<
SPECIFIC ACTION
>
< MAINT
<
>
< LRU IDENT
<
>
< RETURN
SUB-SYSTEM NAME PREV LEGS REPORT > LEG
>
01
<
PRINT *
A/C IDENT
DATE MAR 05
TIME 1910
1/N < ATA 31-50-00
<
MESSAGE 1
>
02
>
MAR 05
< 1902
34-00-00
<
MESSAGE 2
>
<
> 6 7 4 1 0 0 / 1 1 / W S A : D E G
PRINT *
< RETURN
or
<
SUB-SYSTEM NAME LAST LEG REPORT >
>
> >
> NO FAULT REPORTED
>
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> CMF - SYSTEM REPORT / TEST Description (Cont’d) »
SYSTEM TEST for maintenance / functional / self test of Type 1 / 2 system SUB-SYSTEM NAME SYSTEM TEST / SPECIF ACT
SUB-SYSTEM NAME
If No label received during 4 seconds
>
< START SELF-TEST
<
>
< LAST LEG REPORT
<
>
< START PUSH-TO-TEST
<
>
< PREVIOUS LEGS REPORT
<
<
>
< SYSTEM TEST /
<
>
or unit status is failed and no failures or test inhibited or unit not in test after 5 sec or Timeout
SUB-SYSTEM NAME SELF-TEST
SPECIFIC ACTION
>
<
>
< MAINT
<
>
<
>
< LRU IDENT
<
<
>
< RETURN
>
< RETURN
PRINT *
If (test initiated (with command or discrete) and no pre-condition
If pre-condition
> >
TEST ABORTED
<
>
<
>
<
>
<
TEST OK
>
>
<
>
CANCEL >
<
>
<
>
CONTINUE >
<
<
>
PRINT *
<
90 SECONDS MAX
PRINT *
SUB-SYSTEM NAME SELF-TEST
<
TEST Pre-condition <
>
ATA 31-32-00
>
MESSAGE 1
CLASS 1
> >
< <
> >
< 34-42-01
2
MESSAGE 2 < RETURN
<
SUB-SYSTEM NAME SELF-TEST
If test ended and failures reported
<
>
>
<
If test ended and No Failure reported
SUB-SYSTEM NAME SELF-TEST
TEST IN PROGRESS
6 7 4 1 0 0 / 1 1 / W S A : D E G
<
ERROR
>
SUB-SYSTEM NAME SELF-TEST
>
PRINT *
>
<
< PRINT *
<
<
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> CMF - SYSTEM REPORT / TEST Description (Cont’d)
» SYSTEM TEST for maintenance / functional / self test of Type 1 / 2 system
» LRU state after Initiated test from Maintenance Function
When a UNIT test Pre-Condition required CMA1 displays PULL CB: UNIT Name WAIT 5S, THEN PUSH CB UNIT Name PRESS CONTINUE OR CANCEL With UNIT Name
6 7 4 1 0 0 / 1 1 / W S A : D E G
ACARS CMU, VHF COM3, GPS, WXR, CAPT DU1 PFD, CAPT DU2 MFD, DU3 EWD, F/O DU4 MFD, F/O DU5 PFD, CAPT MCDU, F/O MCDU
After an Initiated Test (IBIT, push to test) the system is in the same state as before the initiated Test, with the same
Pre selected data
Displays
Mode selection
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> CMF - SYSTEM REPORT / TEST Description (Cont’d)
» SYSTEM TEST for HF COM and Self-test is activated HF COM SELF TEST
HF COM
If No label received during 4 seconds
<
>
< LAST LEG REPORT
<
>
<
>
< PREVIOUS LEGS REPORT
<
>
<
>
< SYSTEM TEST /
<
>
< START SELF-TEST
or unit status is failed and no failures or unit not in test after 5 sec or test inhibited or Timeout
HF COM RECEIVE SELF-TEST
SPECIFIC ACTION
>
<
>
< MAINT
<
>
<
>
< LRU IDENT
<
<
>
< RETURN
>
< RETURN
PRINT *
PRINT *
>
<
ERROR
>
<
TEST ABORTED
Test requested If test ended with failure reported HF COM RECEIVE SELF-TEST
HF COM RECEIVE SELF-TEST > > >
TEST IN PROGRESS 60 SECONDS MAX
>
6 7 4 > 1 0 0 / 1 > 1 / W S A : D E G
PRINT *
<
>
ATA 31-32-00
<
>
MESSAGE 1
<
> 34-42-01
<
>
<
>
< RETURN
CLASS 1
PRINT *
HF COM RECEIVE SELF-TEST
<
>
<
<
>
<
<
>
<
>
<
>
< START TRANSMIT TEST
<
<
>
< RETURN
<
2
MESSAGE 2
If test ended and No Failure reported
TEST OK
< <
PRINT *
(1)
<
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> CMF - SYSTEM REPORT / TEST Description (Cont’d)
» SYSTEM TEST for HF COM and Transmit-test is activated (Cont’d) HF COM TRANSMIT SELF-TEST
(1) from previous slide > >
NOTE: During HFCOM self-test, CMA1 displays the pre-conditions in the dedicated MCDU page: CAUTION: HF WILL EMIT INSURE SAFETY REF JIC 231100 OPT 10000 KEEP PTT HF PRESSED AND AT THE SAME TIME PRESS CONTINUE KEY
HF COM TRANSMIT SELF-TEST
Pre-condition
>
<
>
<
>
<
>
<
TEST IN PROGRESS 60 SECONDS MAX
< <
>
CANCEL >
<
>
<
>
CONTINUE >
<
>
<
>
PRINT *
<
>
PRINT *
<
test requested If No label received during 4 seconds or unit status is f ailed and no failures If test ended and Failures reported HF COM 1/N TRANSMIT SELF-TEST > > 6 7 4 1 0 0 / 1 1 / W S A : D E G
ATA 31-32-00 MESSAGE 1
CLASS 1
> 34-42-01
>
MESSAGE 2
< RETURN
PRINT *
or unit not in test after 5 sec HF COM TRANSMIT SELF-TEST
HF COM TRANSMIT SELF-TEST <
>
<
>
<
or Timeout
<
>
<
>
>
<
>
<
>
<
>
<
<
>
<
>
<
<
>
<
>
2
> >
or test inhibited
If test ended and No Failure reported
TEST OK
< RETURN
PRINT *
< <
ERROR TEST ABORTED
< RETURN
PRINT *
<
<
GENFAM
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AVS aboard ATR -600
?
> CMF - SYSTEM REPORT / TEST Description (Cont’d)
» SYSTEM TEST for CPM CACx SYSTEM TEST >
CACx
< START SELF-TEST
>
<
>
< LAST LEG REPORT
<
<
>
< PREVIOUS LEGS REPORT
<
>
< SYSTEM TEST /
<
If test of CPM1 CPM1 SELF-TEST >
If test of CPM2 CPM2 SELF-TEST <
PULL CB CAC1 CPM IOM S
>
CANCEL >
> > >
>
< PULL CB CAC2 CPM IOM S
WAIT FOR 5 SECONDS SET IN CB COM WITH MCDU WILL BE LOST
>
SPECIFIC ACTION
PRINT *
<
>
<
>
<
>
CANCEL >
<
<
>
CONTINUE >
<
<
>
>
< MAINT
<
>
< LRU IDENT
<
>
< RETURN
6 7 4 1 0 0 / 1 1 / W S A : D E G
CACx TEST NAME TEST OK
If test ended and No Failure reported
CACx TEST NAME
<
<
WAIT FOR 5 SECONDS SET IN CB
<
PRESS CONTINUE
PRINT *
CACx TEST NAME
< > >
If Test in progress
PRINT *
If data from CPM BITE invalid CACx or Timeout TEST NAME or No Data during 5s ERROR
60 SECONDS MAX
TEST ABORTED
CLASS 1
>
>
< <
>
>
TEST IN PROGRESS
ATA 31-32-00 MESSAGE 1
1/N
< 34-42-01
2
MESSAGE 2 < RETURN
< <
PRINT *
<
If test ended and Failures reported
GENFAM
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AVS aboard ATR -600
?
> CMF - SYSTEM REPORT / TEST Description (Cont’d)
» SYSTEM TEST for AFCS AFCS SYSTEM TESTS AFCS POST >
<
>
<
AFCS POST IN PROGRESS
>
<
60 SECONDS MAX
>
<
>
<
>
PRINT *
AFCS POST
6 7 4 1 0 0 / 1 1 / W S A : D E G
ATA 27-32-33
>
MESSAGE 1
<
>
< START CPM2 SELF-TEST
<
< START AFCS TEST
> >
<
>
< < RETURN
>
CLASS 1
AFCS POST
< >
<
>
<
>
<
>
<
< < RETURN
<
1
<
TEST OK
>
<
>
<
< < >
>
TEST ABORTED
PRINT *
<
>
CONTINUE > < RETURN
>
<
<
MESSAGE 2
>
PRINT *
>
>
< 42-11-84
<
AFCS POST
If AFCA ABIT ended and No Failure reported
1/N
> >
< START CPM1 SELF-TEST
If TEST ABORTED message received from AFCA1 or TEST REQ ACK timeout
If test ended and Failures reported
>
>
PRINT *
< >
< RETURN
CONTINUE >
<
PRINT *
<
(1)
<
GENFAM
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AVS aboard ATR -600
?
> CMF - SYSTEM REPORT / TEST Description (Cont’d)
» SYSTEM TEST for AFCS (Cont’d) AFCS MOTION
(1)
Note
In AFCS test result of AFCS POST or AFCS motion, CMA displays only failures detected by AFCA
>
CAUTION: CTRL SURFACES WILL MOVE
<
>
INSURE SAFETY
<
>
IF EMERGENCY: USE QUICK RELEASE
<
>
REF JIC 221800 OPT 10000
<
> >
< RETURN
>
CONTINUE >
<
PRINT *
<
>
MESSAGE 1
> 42-11-84
>
MESSAGE 2
< RETURN
<
>
<
>
<
<
>
<
>
< PRINT *
<
If TEST ABORTED message received from AFCA1 or TEST REQ ACK timeout AFCS MOTION <
>
<
>
>
<
>
<
<
>
<
>
<
<
>
<
>
<
<
>
<
>
TEST OK
<
TEST ABORTED
<
1
> >
120 SECONDS MAX
AFCS MOTION CLASS 1
<
TEST IN PROGRESS
and No Failure reported
AFCS MOTION
6 7 4 1 0 0 / 1 1 / W S A : D E G
>
<
If AFCA motion ended
and Failures reported
ATA 27-32-33
>
>
If AFCA motion ended
>
AFCS MOTION
PRINT *
< RETURN
PRINT *
< RETURN
PRINT *
<
GENFAM
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AVS aboard ATR -600
?
> CMF - SYSTEM REPORT / TEST Description (Cont’d)
» SYSTEM TEST for PUSH-TO-TEST of Type 1 / 2 system CMA1 permits to start
6 7 4 1 0 0 / 1 1 / W S A : D E G
One self-test for each CPM, VHF COM, VHF COM VDL2 (VHF COM3), VHF NAV, HF COM, DME, IRS, ADU, AHRS, ATC (XPDR) / T2CAS (ATC test induces also T2CAS test), MCDU, CMU, RA, GPS, WXR, DU
SUB-SYSTEM NAME
SUB-SYSTEM NAME SYSTEM TEST
>
< LAST LEG REPORT
<
>
< START SELF-TEST
<
>
< PREVIOUS LEGS REPORT
<
>
< START PUSH -TO-TEST
<
>
<
>
< SYSTEM TEST / SPECIFIC ACTION < MAINT
>
< LRU IDENT
<
>
< RETURN
>
<
>
<
>
< < RETURN
>
PRINT *
<
PRINT *
<
SUB-SYSTEM NAME SYSTEM TEST
One VOR-ILS self-test and one ADF self-test for VHF NAV&ADF
>
>
<
One push-to-test for ADU
>
<
>
> >
< PUSH TO TEST IN PROGRESS
< STOP
<
Note
The line START SELF TEST is not displayed if the sub-system doesn’t implement self -test
< PRINT *
<
If test can't be executed, CMA1 displays on the last line (line 14) "SYSTEM NOT AVAILABLE" in case of no response or sub-system already in test "SYSTEM ERROR" in case of sub-system bad response returned by sub-system or no computed data received from subsystem (except for VHCOM1/2 or 3 for which Non Computed Data does not imply the display of "SYSTEM ERROR")
<
GENFAM
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AVS aboard ATR -600
?
> CMF - SYSTEM REPORT / TEST Description (Cont’d)
» SYSTEM TEST for MCDU In the particular case of MCDU, if MCDUi is used for displaying maintenance information, MCDUi test is inhibited in the corresponding menu
MCDU
> > > >
< <
MCDUi USED FOR CMF DISPLAY : TEST INHIBITED PLEASE USE THE OTHER MCDU TO TEST THIS ONE
< <
> >
6 7 4 1 0 0 / 1 1 / W S A : D E G
<
< RETURN
PRINT *
<
GENFAM
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AVS aboard ATR -600
?
> CMF - SYSTEM REPORT / TEST Description (Cont’d)
» SYSTEM TEST for AHRS Notes
x (from AHRSx) is replaced par the side of the current AHRS y (from AHRSy) is replaced by the side of opposite AHRS
>
< START SELF-TEST
>
< FLUX VALVE CALIBRATION
val1: heading value in degree (decimal resolution 0.1)
>
<
>
<
val2, val3: equal to 1 or 0
>
<
VALIDATE: when pressed, the heading tuned with Right Heading and Left Heading, key is validated
>
Upon selection of “GO TO AHRSy” key CMA permits to access to the page containing
“CAL MODE” key of the opposite
AHRS not in calibration mode 6 7 4 1 0 0 / 1 1 / W S A : D E G
AHRSx
AHRSx SYST TEST/ SPECIF ACT
“HDG+
/ HDG-“ of the opposite AHRS already in calibration END CALIB key pressed during 3s mode
< RETURN
PRINT *
< <
>
HEADING: val1 VHDG: val2
>
VALIGN: val3
>
GO TO AHRSy >
QUIT: press 3s END CALIB
>
PRINT *
<
>
< PREVIOUS LEGS REPORT
<
>
< SYSTEM TEST / SPECIFIC
<
ACTION
>
< MAINT
<
>
< LRU IDENT
<
>
< RETURN
CAL MODE key pressed during 3s
FLUX VALVE CALIBRATION
>
<
>
<
>
<
>
<
>
<
>
<
>
PRINT *
<
AHRSx FLUX VALVE CALIBRATION CMF - SYSTEM REPORT / TEST Description (Cont’d)
» SYSTEM TEST for MAINT Report For the Type 1 and 2 sub-systems, pressing MAINT report from a sub-system main menu displays only Class 2 failures related to the selected sub-system contained in MAINT report of all AVS
SUB-SYSTEM NAME >
< LAST LEG REPORT
<
>
< PREVIOUS LEGS REPORT
<
>
< SYSTEM TEST / SPECIFIC ACTION
<
>
< MAINT
<
>
< LRU IDENT
<
>
< RETURN
PRINT *
Failures transmitted
No failure transmitted
SUB-SYSTEM NAME MAINT REPORT A/C IDENT > >
LEG
DATE
01
MAR 05
1/N ATA 31-50-00
> >
02
MAR 05
1902
34-00-00
MESSAGE 2
< RETURN
< <
> >
SUB-SYSTEM NAME MAINT REPORT
< TIME 1910
MESSAGE 1 6 7 4 1 0 0 / 1 1 / W S A : D E G
<
< <
PRINT *
<
>
<
> >
< NO FAULT REPORTED
<
>
<
>
<
>
< RETURN
PRINT *
<
GENFAM
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AVS aboard ATR -600
?
> CMF - SYSTEM REPORT / TEST Description (Cont’d)
» SYSTEM TEST for LRU IDENT Report For loadable sub-systems, pressing LRU IDENT report from a sub-system main menu displays LRU IDENT report containing part number of the subsystem
SUB-SYSTEM NAME
Note: The only sub-system that have more than one LRU with LRU ident to display is CACx, the two LRU are CPMx and SWMx (x=1 or 2)
>
< LAST LEG REPORT
<
>
< PREVIOUS LEGS REPORT
<
>
< SYSTEM TEST
<
>
< MAINT
<
>
< LRU IDENT
<
>
< RETURN
PRINT *
<
If one LRU If more than one LRU
LRUn
6 7 4 1 0 0 / 1 1 / W S A : D E G
CPMn (for CACn) or DUn or SWMn
LRU1 IDENT
HW P/N Harware Part Number
<
P/Nn
<
Part Number of loadable (Software, Database, Configuration File)
FINn FIN code of the LRUn Subsystem Name CACn or DUn or SWMn
< < < <
LRUn (FINn): :
<
HW P/N: XXXXXXXXXXXX P/N1:XXXXXXXXXXXX P/N2:XXXXXXXXXXXX P/N3:XXXXXXXXXXXX P/N4:XXXXXXXXXXXX P/N5:XXXXXXXXXXXX P/N6:XXXXXXXXXXXX P/N7:XXXXXXXXXXXX < RETURN
SUB-SYSTEM NAME
1/N
PRINT *
< <
< < <
1/1
>
< LRU1
<
>
< LRU2
<
>
< LRUn
<
>
<
>
<
>
< RETURN
PRINT *
<
GENFAM
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Quiz
AVS aboard ATR -600
?
> CMF - MAINT REPORT Description
» MAINT report displays Class 2 failures
AVS
from AVS stored in NVM and occurred during the 64 last legs when maintenance phase was "Flight" (failures without effect on system operation)
SYSTEM >
< AVIONICS
>
STATUS
<
> < LAST LEG
> >
maximum 50 failures
>
< PREVIOUS
>
LEGS REPORT < RETURN
6 7 4 1 0 0 / 1 1 / W S A : D E G
> >
DATE MAR 05
MAR 05
TIME 1910
ATA 31-50-00
1902
34-00-00
>
> <
<
PRINT *
>
< NO FAULT REPORTED
<
<
>
<
<
>
<
>
<
<
< RETURN
<
MAINT REPORT
MESSAGE 2
>
AVS AND A/C > OPT CONF
<
MESSAGE 1 01
<
1/N
A/C IDENT 00
LRU IDENT >
No failure recorded
MAINT REPORT
LEG
<
PRINT *
Failures recorded
>
MAINT >
REPORT
» In MAINT REPORT a leg shall contain at the
>
<
REPORT / TEST
<
>
< RETURN
PRINT *
<
GENFAM
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Quiz
AVS aboard ATR -600
?
> CMF - LRU IDENT Description from CAC
» When a LRU type is selected,
AVS >
the CMF displays the part number transmitted by each side the selected LRU type
< AVIONICS STATUS
<
> >
LRU IDENT
<
SYSTEM > REPORT / TEST
MAINT >
<
LRU IDENT >
<
< LAST LEG REPORT
» LRU IDENT report lets the
>
Operator display the Part Number of CAC-CPM (loadable on A/C)
>
< PREVIOUS
>
< RETURN
LEGS REPORT
<
AVS AND A/C > OPT CONF
>
<
CAC
<
>
<
DU
<
>
<
>
<
>
<
<
PRINT *
>
< RETURN
PRINT *
<
PREV … NEXT
CPM LRU IDENT > >
SUB-SYSTEM NAME
2/2
CPM LRU IDENT
CPM1 CSW:XXXXXXXXXXXX MCCT:XXXXXXXXXXXX
<
FWMCF:XXXXXXXXXXXX
<
>
CPM1 HW:XXXXXXXXXXXX CMA SW:XXXXXXXXXXXX
<
>
AFCA SW:XXXXXXXXXXXX DCA SW:XXXXXXXXXXXX
<
>
FWA SW:XXXXXXXXXXXX
<
MNTCF:XXXXXXXXXXXX > 6> 7 4 1 0 0 / 1> 1 / W S A : D> E G
<
CPM2 CSW:XXXXXXXXXXXX MCCT:XXXXXXXXXXXX FWMCF:XXXXXXXXXXXX MNTCF:XXXXXXXXXXXX < RETURN
PRINT *
1/2
CPM2 HW:XXXXXXXXXXXX <
>
CMA SW:XXXXXXXXXXXX
<
<
>
AFCA SW:XXXXXXXXXXXX DCA SW:XXXXXXXXXXXX
<
<
>
PRINT *
< CPM
<
>
<
>
<
>
<
>
FWA SW:XXXXXXXXXXXX < RETURN
>
<
< RETURN
PRINT *
<
GENFAM
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Quiz
AVS aboard ATR -600
?
> CMF - LRU IDENT Description from CAC (Cont’d)
» When a LRU type is selected,
AVS >
the CMF displays the part number transmitted by each side the selected LRU type
< AVIONICS STATUS
<
> >
LRU IDENT
<
SYSTEM > REPORT / TEST
MAINT >
<
LRU IDENT >
<
< LAST LEG REPORT
» LRU IDENT report lets the
>
Operator display the Part Number of CAC-SWM (loadable on A/C)
>
< PREVIOUS
>
< RETURN
LEGS REPORT
<
AVS AND A/C > OPT CONF
>
<
CAC
<
>
<
DU
<
>
<
>
<
>
<
<
PRINT *
>
< RETURN
SWM1 HW:XXXXXXXXXXXX
<
CSW:XXXXXXXXXXXX > >
<
SUB-SYSTEM NAME
SWM LRU IDENT >
PRINT *
CF : XXXXXXXXXXXX
<
SWM2 HW:XXXXXXXXXXXX
<
>
< CPM
<
>
<
>
<
>
<
CSW:XXXXXXXXXXXX 6 7 4 1 0 0 / 1 1 / W S A : D E G
>
<
CF : XXXXXXXXXXXX
<
> >
< RETURN
PRINT *
<
>
< RETURN
PRINT *
<
GENFAM
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Abb
Quiz
AVS aboard ATR -600
?
> CMF - LRU IDENT Description from DU
» When a LRU type is selected, the CMF displays the part number transmitted by each side the selected LRU type
» LRU IDENT report lets the Operator display the Part Number of DU (loadable on A/C)
AVS >
< AVIONICS STATUS
SYSTEM > REPORT / TEST
<
>
>
LRU IDENT
<
MAINT >
<
LRU IDENT >
<
< LAST LEG REPORT
> >
< PREVIOUS
>
< RETURN
LEGS REPORT
AVS AND A/C > OPT CONF PRINT *
<
>
<
CAC
<
>
<
DU
<
>
<
>
<
>
<
< >
PRINT *
< RETURN
<
PREV … NEXT
DU LRU IDENT
4/4
DU LRU IDENT
3/4
2/4
DU LRU IDENT
DU1 FMPDB42:XXXXXXXXXXXX
DU1 HW:XXXXXXXXXXXX
FMPDB72:XXXXXXXXXXXX
IAD SW:XXXXXXXXXXXX
DU2 FMPDB42:XXXXXXXXXXXX FMPDB72:XXXXXXXXXXXX
DU2 HW:XXXXXXXXXXXX IAD SW:XXXXXXXXXXXX
DU3 FMCF42:XXXXXXXXXXXX
DU3 FMPDB42:XXXXXXXXXXXX
DU3 HW:XXXXXXXXXXXX
FMCF72:XXXXXXXXXXXX
FMPDB72:XXXXXXXXXXXX
IAD SW:XXXXXXXXXXXX
DU4 AVSCF:XXXXXXXXXXXX
DU4 FMCF42:XXXXXXXXXXXX
DU4 FMPDB42:XXXXXXXXXXXX
DU4 HW:XXXXXXXXXXXX
DU5 AVSCF:XXXXXXXXXXXX
FMCF72:XXXXXXXXXXXX DU5 FMCF42:XXXXXXXXXXXX
FMPDB72:XXXXXXXXXXXX DU5 FMPDB42:XXXXXXXXXXXX FMPDB72:XXXXXXXXXXXX
IAD SW:XXXXXXXXXXXX DU5 HW:XXXXXXXXXXXX
< RETURN
< RETURN
DU1 AVSCF:XXXXXXXXXXXX
DU1 FMCF42:XXXXXXXXXXXX FMCF72:XXXXXXXXXXXX z DU2 FMCF42:XXXXXXXXXXXX FMCF72:XXXXXXXXXXXX
z DU2 AVSCF:XXXXXXXXXXXX DU3 AVSCF:XXXXXXXXXXXX 6 7 4 1 0 0 / 1 1 / W S A : D E G
DU LRU IDENT
FMCF72:XXXXXXXXXXXX < RETURN
PRINT *
< RETURN
PRINT *
PRINT *
1/4
IAD SW:XXXXXXXXXXXX PRINT *
GENFAM
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AVS aboard ATR -600
?
> CMF - AVS and A/C OPT CONF Description AVS
The CMF displays all Avionic options and A/C configuration parameters from AVS configuration
>
< AVIONICS STATUS
SYSTEM > REPORT / TEST
<
AVS AND A/C <
>
1/5
OPT CONF A/C SN :
>
MAINT >
<
LRU IDENT >
<
< LAST LEG
A/C TYPE CPM1: A/C CAT CPM1: A/C TYPE CPM2: A/C CAT CPM2:
REPORT
>
Notes - val1 = ATR42 or ATR72 (CPM1 pinprog) - val2 = CATII or CATIII (CPM1 pin-prog)
>
< PREVIOUS
>
LEGS REPORT < RETURN
AVS AND A/C > OPT CONF PRINT *
A/C_SN_Val
HW PINPROG
<
val1 val2 val3 val4
SW PINPROG A/C OPTIONS:
<
A/C VIDEO:
- val3 = ATR42 or ATR72 (CPM2 pinprog)
AC-video_val
< RETURN
- val4 = CATII or CATIII (CPM2 pinprog )
PRINT *
- Other string ended by _val are replaced by the real string value contained in AVS configuration file - The length of value may be greater than one line, in this case next lines are moved downward
PREV … NEXT
- When data acquisition failed val are dashed AVS AND A/C
5/5
OPT CONF
6 7 4 1 0 0 / 1 1 / W S A : D E G
SATCOM/GSM: CPDLC: GLS: RNP SAAR: VSD: E-VSD: GBAAS:
< RETURN
AVS AND A/C
4/5
AVS AND A/C
OPT CONF
AVS-SATCOM2_val AVS-DL2_val AVS-GLS_val AVS-RNP_val AVS-VSD_val AVS-VSD2_val AVS-GBAAS_ val
PRINT *
ACARS: ADSB-IN: AIRPORT MAP: STEEP APP: SPD HLD: WXR MODE: TAWS MODE CPLD VNAV: NAV TO NAV: SATCOM: < RETURN
3/5
PRINT *
ST6:
AVS_ST6_val
SW PINPROG AVS OPTIONS: ADF2: AVS_ADF2_val DME2: AVS_DME2_val GPS2: AVS_GPS2_val HF1: AVS_HF1_val HF2: AVS HF2_val RA2 : AVS_RA2_val AHRS/IRS: AVS_INERTIAL_val < RETURN
2/5
OPT CONF
OPT CONF
AVS_DL1_val AVS-TCAS_val AVS_OANS_ val AC_SteepAPP_val AC_SPD_HLD_val AVS-WXR1_val AVS-WXR2_val AVS-NAV1_val AVS-NAV2_val AVS-SATCOM_ val
AVS AND A/C
PRINT *
AFT CARGO: FWD CARGO: PRES ALT: PROP_BRK_L: PROP_BRK_R: ENG RATING: FLAP 25: ENG BOOST: FAA PROC : ST3 ST5: < RETURN
AC_AFT_CARGO_val AC_FWD_CARGO_val AC_PRES_ALT_val AC_PROP_BRK_L_val AC_PROP_BRK_R_val AC_ENG_ val AC_FLAP_val AC_ENG_BOOST_val AC-FAA-PROC_val AVS_ST3_ST5_val PRINT *
GENFAM
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AVS aboard ATR -600
?
> CMF - Maintenance Tips
» Failure of special LRU
6 7 4 1 0 0 / 1 1 / W S A : D E G
AFCA failures include failures of CPSTN, SM, PTB, IOM-AP, FGCP, ICP
DCA failures include failures of IOM-DC
CPM PTF failures include failures of IOM-S
FDA failures include failures of EFCP-L, EFCP-R, MCP
» COTS detect
All its internal failures (due to an internal problem inside LRU)
All its external failures (failures on input interfaces only of sub-systems really fitted) Note: failures include hardware and software failures
GENFAM
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?
AVS aboard ATR -600
> CMF - Maintenance Tips - ABIT - CBIT
» ABIT All LRU contain adequate ABIT, initiated automatically on power-up to verify
CPU self-test
Memory checksum (program and data memory)
Test of peripheral circuits
Test of I/O ports (complete wraparound test to detect the absence of emission)
Note: ABIT (Automatic Build-In Test) = monitoring done at LRU initialization also called PBIT (Power on BIT) or POST (Power On Self-Test) 6 7 4 1 0 0 / 1 1 / W S A : D E G
» CBIT of non COTS Non COTS sub-systems perform CBIT during operation in order to verify fault-free system operation CPU fail, Memory fail, Peripheral fail, Watch dog, Applications failure, Interface failures
» CBIT of COTS COTS sub-systems perform CBIT during operation in order to verify fault-free system operation CPU fail, Memory fail, Peripheral fail, Watch dog
GENFAM
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> CMF - Onboard SW Dataloading
Dataloading allowed if
6 7 4 1 0 0 / 1 1 / W S A : D E G
Quiz
?
AVS aboard ATR -600
GENFAM
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Quiz
> CMF - Sub-function DUMP BITE
» Dump of IAD BITE
IAD Dump Bite is performed with a dedicated CPF containing an identifier detected by the IAD on ground only
Contents of the SBite memory is then copied in a dedicated folder on the CPF
During the operation, the IAD displays a message and a progressive bar for the maintenance operator
IAD BITE RECORDING IN PROGRESS IAD BITE RECORDING COMPLETED
» Dump of CPM/IOM-S BITE 6 7 4 1 0 0 / 1 1 / W S A : D E G
Performed using the PMAT on ground
A request of the content of the CPM SBite and CMA logbooks is performed
Result of the operation is send to the gateway (for the PMAT) using a dedicated instrumentation VL
?
AVS aboard ATR -600
GENFAM
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Quiz
AVS aboard ATR -600
?
> CMF - Dataloading General CACPF CAC1 PC PMAT CD-ROM
CPM & SWM CD-ROM
Ethernet Link
Load
IAD
6 7 4 1 0 0 / 1 1 / W S A : D E G
IAD CD-ROM
CPF
IAD PMAT = Thales Softw are + PC + Ethernet cable
GENFAM
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Quiz
AVS aboard ATR -600
?
> CMF - Dataloading Order Acronym
6 7 4 1 0 0 / 1 1 / W S A : D E G
Designation
Host
Root
Dataloading order
CPM CSW
Common Core Software
CPM
K4018
1
CPM CCT
CPM Complete Configuration Table
CPM
G6041
2
AFCA
Automatic Flight Control Application
CPM
G2865
3
FWA
Flight Warning Application
CPM
G2867
3
FWCF
Flight Warning Configuration File
CPM
G2868
4
DCA
Data Concentration Application
CPM
G2875
3
CMA-BITE
Centralized Maintenance Application CPM Complete BITE
CPM
G2874
3
CM FT
Centralized Maintenance Failure Table
CPM
G2912
4
SWM CSW
Switch Module Core Software
SWM
K4045
1
NCT
Network Configuration Table
SWM
G6042
2
GENFAM
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Quiz
?
AVS aboard ATR -600
> CMF - Example of CPM Dataloading Procedure - Switch on the Laptop - Execute « PMAT Software» link - Enter the “User Name” and the “PWD”
6 7 4 1 0 0 / 1 1 / W S A : D E G
GENFAM
L&B
Abb
Quiz
?
AVS aboard ATR -600
> CMF - Example of Procedure for Upload IAD SW on a CPF - Switch on the Laptop - Execute « PMAT Software» link - Enter the “User Name” and the “PWD” - Power off IAD - Install the CPF with Operational SW in IAD
- Power on IAD - A green “L” appears on IAD - At the end of loading, the green “L” becomes a white “L” if there was no uploading problem or a red “L” in case of uploading problem
6 7 4 1 0 0 / 1 1 / W S A : D E G
- If there was no uploading problem, then power off IAD - Remove CPF from the IAD - Power on IAD
