In Service Information
Ref: ISI 23.73.00094
Issue: September 2017
A320 Family
A318/A319/A320/A321
Enhanced Cabin
Cabin Intercommunication
Data System & Smoke
Detection Function (CIDS/SDF)
Troubleshooting guidelines
Guidelines for system troubleshooting
_
A318 / A319 / A320 / A321
Enhanced Cabin – CIDS & SDF GUIDELINES SYSTEM
FOR TROUBLESHOOTING
Please note:
• These information do not amend or supersede any instruction contained in the Aircraft
Maintenance Manual (AMM), or the Trouble Shooting Manual (TSM), or Master Minimum
Equipment List (MMEL) or FCOM (Flight Crew Operating Manual), or CCOM (Cabin Crew
Operating Manual).
• This booklet may not be regularly updated and the latest updates of IPC, AMM, TSM,
MMEL, FCOM and CCOM remain the main references.
• For additional information, please refer to IPC, AMM, TSM, MMEL, FCOM and CCOM
on ATA 23-73 and 26-00/10/16/17/23 (among others), and all the other Airbus publications
referenced in this document.
• Except specific notice, information provided in this document is valid for all A320 Family
A/C type: A318, A319, A320 & A321.
Procurement:
Operators are invited to contact their Resident Customer Support Manager or their Customer
Support Director, who will take appropriate actions to procure these guides.
Refer to the ISI 00.00.00170 for the details on ISI and ASMA documentation.
The technical information provided in this article is for convenience and information purposes only. It shall in no
case replace the official Airbus technical or Flight Operations data which shall remain the sole basis for aircraft
maintenance and operation. These recommendations and information do not constitute a contractual commitment,
warranty or guarantee whatsoever. They shall not supersede the Airbus technical nor operational documentation;
should any deviation appear between this article and the Airbus or airline’s official manuals, the operator must
ensure to cover it with the appropriate document such as TA, FCD, RAS. Access to WISE is supplied by Airbus
under the express condition that Airbus hereby disclaims any and all liability for the use made by the user of the
information contained in WISE. It shall be used for the user’s own purposes only and shall not be reproduced or
disclosed to any third party without the prior consent of Airbus.
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Introduction
_
This booklet has been issued in order to inform operators of A318, A319, A320 and A321
aircraft equipped with Enhanced Cabin of the potential capabilities of the CIDS
and SDF related to intensive trouble analysis and investigation tasks. As CIDS and SDF
play an important role in the operational chain, appropriate knowledge of the system’s
function and operations is essential.
Notes:
• This ISI does not apply to aircraft fitted with Classic CIDS (DIR P/N Z010H-),
refer to ref ISI 23.73.00095.
• This ISI also applies to aircraft fitted with a mix of Classic Cabin (PSU P/N Z312H-)
and enhanced CIDS (DIR P/N Z014H-).
Table of content
_
005
1 General Overview
A. CIDS Introduction
B. Part Number Identification
C. CIDS Architecture
D. Component location
I Directors
II Cockpit Components
III DEU A
IV DEU B
V Flight Attendant Panel
E. Circuit Breakers
011
012
014
015
016
017
018
020
022
024
025
2. Components detailed overview
A. Directors
I Introduction
II Switch Over Logic
III Power Up Sequence
IV H/W & S/W Improvements
V Interchangeability
B. Smoke Detection
I Introduction
II Power Supply
III Aural & Visual indications
IV Detectors
V Lavatory
VI Cargo
VII Fire extinguishing
C. Decoder Encoder Units
I DEU A
II DEU B
III DEU A&B - connexion Box
D. Handsets
I Introduction
II Interchangeability
III Operational Recommendations
E. Flight Attendant Panel
I Introduction
II Keys Colours
III CAM
IV OBRM & iPRAM
V Hardkeys
VI Architecture
VII Page Display Philosophy
VIII Standard Pages
IX Interchangeability
X Passwords
027
028
029
032
034
035
037
039
040
041
042
046
047
048
049
051
052
054
056
057
058
059
061
062
063
064
065
067
068
069
070
071
089
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Table of content
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F. AAP, ACP & AIP
I Additional Attendant Panel
II Area Call Panel
III Attendant Indication Panel
G. Passenger Service Unit
092
093
094
095
096
3. CIDS Functions
A. Passenger Address
B. Cabin and Flight Crew Interphone
C. Service Interphone
D. Cabin Illumination
E. Emergency Evacuation
F. Passenger Call
G. Air Conditioning
H. Doors & Slides
I. In Flight Entertainment
J. Emergency Power Supply Unit (EPSU)
K. Potable Water Indication and Preselection
L. Vacuum System Control Function (VSCF)
M. Waste Quantity Indication
N. Cabin Ready Function
O. Sterile Cockpit
P. Cabin & Cockpit Alerting System
Q. Drain Mast Control Unit (DMCU)
097
098
100
102
103
104
106
107
108
109
110
111
113
115
116
116
116
117
4. BITE
A. Introduction
B. Failures Annunciation
C. List of ECAM Warning & Maintenance Status
D. MCDU CIDS
I Access
II Last Leg Report
III Previous Legs Report
IV LRU Identification
V Class 3 Faults
VI System Tests
VII Power Up Test
VIII Operational Tests
IX Troubleshooting Data
X Ground Scanning
XI Ground Report
XII System Configuration
E. MCDU CIDS Simulator on the FAP
119
120
122
123
126
127
129
130
131
132
133
134
137
138
139
141
142
143
Table of content
_
007
F. MCDU SDF
I Access
II Last Leg Report
III Previous Legs Report
IV LRU Identification
V Class 3 Faults
VI System Tests
VII Ground Scanning
VIII Smoke Warning Test
IX Troubleshooting Data & Smoke Warning Report
144
145
147
148
149
150
151
152
153
154
5. Dispatch and Troubleshooting
A. Troubleshooting Philosophy & Recommendations
B. Common Maintenance Procedures
C. MEL
I Repair Interval
II Maintenance Status CIDS
III Interphone
IV Handset
V PA/Loudspeaker/Pax Call
VI DEUs A&B
VII FAP unit
VIII FAP functions, PRAM & CAM
IX ACP, AIP, AAP
X Cabin Signs
XI Maintenance Status SDF
XII Lavatory Smoke Detection
XIII FWD Cargo Smoke Detector
XIV AFT & Bulk Cargo Smoke Detector
D. Smoke Event
I Smoke Warning Investigation
II Prevent False Smoke Event
III Smoke related troubleshooting
E. CIDS Event
I PSU Troubleshooting
II CIDS TOP/MID Line Troubleshooting
III Service Interphone Noise
IV PA, Interphone & Handsets
V Handset best practices
F. CIDS Deviations
155
156
158
159
160
161
162
163
164
165
166
167
168
169
170
171
172
173
174
175
177
178
180
181
182
186
187
188
189
6. Documentation & Contacts
A. Documentation
B. Contacts
196
194
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Glossary
_
AAP
A/C
ACSC
ACMS
ACP
ACU
AIBU
AIP
AMM
AMU
ANN
ARINC
ASPSU
BITE
CAM
CIDS
CFDS
CPC
CPMS
DEU
DIR
DMCU
DMU
ECAM
EIS
EIU
EIVMU
EMLS
EPSU
EVAC
EWD
FAP
FSB
FWC
IFES
ILCB
ADDITIONAL ATTENDANT PANEL
AIRCRAFT
AIR CONDITIONING SYSTEM CONTROLLER
AIRCRAFT CONDITION MONITORING SYSTEM
AREA CALL PANEL
AIR COOLING UNIT
ADVANCED ILLUMINATION BALLAST UNIT (CABIN LIGHT)
ATTENDANT INDICATION PANEL
AIRCRAFT MAINTENANCE MANUAL
AUDIO MANAGEMENT UNIT
ANNUNCIATOR
AERONAUTICAL RADIO INCORPORATION
AUTONOMOUS STANDBY POWER SUPPLY UNIT
BUILT-IN TEST EQUIPMENT
CABIN ASSIGNMENT MODULE
CABIN INTERCOMMUNICATION DATA SYSTEM
CENTRALIZED FAULT DISPLAY SYSTEM
CABIN PRESSURE CONTROLLER
CABIN PASSENGER MANAGEMENT SYSTEM
DECODER/ENCODER UNIT
DIRECTOR
DRAIN MAST CONTROL UNIT
DATA MANAGEMENT UNIT
ELECTRONIC CENTRALIZED AIRCRAFT MONITORING
ELECTRONIC INSTRUMENT SYSTEM
ENGINE INTERFACE UNIT
ENGINE INTERFACE AND VIBRATION MONITORING UNIT
EMERGENCY LIGHTING SYSTEM
EMERGENCY POWER SUPPLY UNIT
EVACUATION
ENGINE/WARNING DISPLAY
FLIGHT ATTENDANT PANEL
FASTEN SEAT BELT
FLIGHT WARNING COMPUTER
IN-FLIGHT ENTERTAINMENT SYSTEM
INDICATE LIGHT CONTROL BOX
Glossary
_
IPRAM
I/O
ISI
ISPSS
LAV
LDCC
LGCIU
LLS
LLT
LR
LRU
LVDS
MEL
MCDU
OBRM
OI
OPC
PA
PCU
PES
PISA
PRAM
PSS
PSU
PTT
PTT
RTS
SA
SDAC
SDCU
SFCC
TFU
TSM
VC
VSC
VSF
009
INTEGRATED PRE-RECORDED ANNOUNCEMENT & BOARDING MUSIC
INPUT OUTPUT
IN SERVICE INFORMATION
IN SEAT POWER SUPPLY SYSTEM
LAVATORY
LOWER DECK CARGO COMPARTMENT
LANDING GEAR CONTROL & INTERFACE UNIT
LIQUID LEVEL SENSOR
LIQUID LEVEL TRANSMITTER
LONG RANGE
LINE REPLACEMENT UNIT
LOW VOLTAGE DIFFERENTIAL SIGNALLING
MINIMUM EQUIPMENT LIST
MULTIPURPOSE CONTROL DISPLAY UNIT
ON BOARD REPLACEABLE MODULE
OPERATIONAL INTERRUPTION
OPERATIONAL PROGRAM CONFIGURATION
PASSENGER ADDRESS
PASSENGER CONTROL UNIT
PASSENGER ENTERTAINMENT SYSTEM
PASSENGER INTERFACE AND SUPPLY ADAPTER
PRE-RECORDED ANNOUNCEMENT & BOARDING MUSIC
PASSENGER SERVICE SYSTEM
PASSENGER SERVICE UNIT
PUSH TO TALK (HANDSET)
PUSH TO TEST (SDF)
RETURN TO SEAT
SINGLE AISLE
SYSTEM DATA ACQUISITION CONCENTRATOR
SMOKE DETECTION CONTROL UNIT
SLAT FLAP CONTROL COMPUTER
TECHNICAL FOLLOW-UP
TROUBLESHOOTING MANUAL
VENTILATION CONTROLLER
VACUUM SYSTEM CONTROLLER
VACUUM SYSTEM FUNCTION
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1. General Overview
A.
B.
C.
D.
E.
CIDS Introduction
Part Number Identification
CIDS Architecture
Component location
Circuit Breakers
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1. General Overview
_
A. CIDS Introduction
The Cabin Intercommunication Data System (CIDS) (ATA 23-73) is the electronic
cabin management system, which provides most of the required cabin related
functions for the cockpit, cabin crew, passengers and maintenance teams.
The CIDS is the cabin network used to accomplish the functional control, operation,
data transmission, testing and monitoring of various cabin systems.
The systems controlled or interfaced by CIDS are:
- Passenger Address (PA)
- Cabin and Flight Crew Interphone
- Service Interphone
- Prerecorded Announcement and Boarding Music control (PRAM)
- Passenger Entertainment System (PES/IFE)
- Passenger Lighted Signs
- Passenger Call
- Cabin Illumination
- Passenger Reading Lights
- Passenger Services System (PSS)
- Lavatory Smoke Detection and Indication
- Cargo Smoke Detection and Indication
- Cargo Fire Extinguisher Monitoring
- Cabin Ready Signalling
- Air Conditioning
- Emergency Evacuation Signalling (EVAC)
- Sterile Cockpit
- Potable Water Indication & Preselection
- Waste Indication
- Vacuum System Control
- Doors and Escape Slides Pressure Monitoring
- Multipurpose Bus (MPB)
- Cabin and Cockpit Alerting System (CCAL)
- Emergency Power Supply Unit (EPSU)
- Drain Mast Control Unit (DMCU)
- Built-In Test Equipment (BITE)
- MCDU
The components related to each one of the above functions are described in chapter 3.
The system functions are controlled by a central control unit called the Director (DIR).
For redundancy purpose there are two directors, one active and one in hot stand-by mode.
1. General Overview
_
A. CIDS Breakdown
21VU
35VU
21VU
25VU
Cockpit switches
Directors
(DIR 1 / DIR 2)
22VU
ACP
AIP
Attendant functions:
• PA & Interphone
• PAX call
• Cabin indications
FAP
AAP & Handsets
LAV & Cargo Smoke
Detectors.
DEU A
DEU-B
DEU-A
Top line
(DEU-A)
DEU-B
Middle line (DEU-B)
DEU-A
DEU B
PAX functions: Passengers
Service Units (PSU/PISA)
Attendant functions:
Cabin control
and monitoring.
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1. General Overview
_
B. Part Number Identification
The CIDS is designed in a modular way, whereby the number of installed components will be
adapted to the aircraft type, layout and functional requirements. These components are:
Components
Number
PN Root
FIN (location)
Director
2
Z014H
101RH / 102RH
DEU Type A
Up to 17
Z033H
200RHx
DEU Type B
Up to 6
Z043H
300RHx
FAP/MP-FAP
Up to 10
Z133H/Z145H
120RH
AAP
Up to 16
Z120H
126RH
ACP
Up to 16
AIP
Up to 16
Z111H
320RHx
Top Lines
2
N/A
N/A
Mid Lines
2
N/A
N/A
PSU (Classic Cabin)
-
Z312H
-
PSU (Enhanced Cabin)
-
Z315H/Z317H
-
Handset
Up to 5
-
-
CAM
1
Z054H
115RH
IPRAM
1 (option)
Z163H
117RH
OBRM
1
Z064H
116RH
340RHx
CIDS Equipment P/N format: ZXXYH0000000
XX: Equipment Designation
Y: Fleet
Basic CIDS:
Y=0
SA
Y=1
LR
Enhanced CIDS:
Y=3
LR
Y=4
SA
Y=5
A380
AAP: ‘Y’ = 0 because SA Classic models are used for SA Enhanced.
AIP: ‘ Y’ = 1 because LR Classic models are used for SA Enhanced.
FAP: ‘Y’ = 3 because LR models are the same for SA.
1. General Overview
_
C. CIDS Architecture
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1. General Overview
_
D. Components Location
I. Directors
II. Cockpit Components
III. DEU A
IV. DEU B
V. Flight Attendant Panel
1. General Overview
_
D. Components Location
I. Directors
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1. General Overview
_
D. Components Location
II. Cockpit Components
25VU
21VU
35VU
21VU
22VU
1. General Overview
_
D. Components Location
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1. General Overview
_
D. Components Location
III. DEU A
A
A
1. General Overview
_
D. Components Location
A318
A319, A320, A321
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1. General Overview
_
D. Components Location
IV. DEU B
B
B
1. General Overview
_
D. Components Location
A318, A319, A320
A321
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1. General Overview
_
D. Components Location
V. FAP
1. General Overview
_
E. Circuit Breakers
Here are the FIN number of the circuit breakers related to different components
(outside of Battery installation):
Designation
CIDS DIR 1
CIDS DIR 2
CIDS SDF 1
CIDS SDF 2
FAP
DEU A Left FWD
DEU A LINE 1
DEU A Right FWD
DEU A LINE 2
DEU A Left MID
DEU A Right MID
DEU A Left AFT
DEU A Right AFT
DEU B
025
A318
NORM
Panel
A318/320
A321
FIN
A318/320
A318
120VU
151RH
ESS
49VU
150RH
NORM
120VU
156RH
ESS
49VU
157RH
NORM
122VU
17WH
ESS
49VU
15WH
NORM
122VU
14WH
ESS
49VU
18WH
NORM
120VU
170RH
ESS
49VU
171RH
NORM
120VU
ESS
ESS
154RH
120VU
164RH
49VU
155RH
2001 VU
197RH
49VU
195RH
2001 VU
198RH
ESS
NORM
ESS
49VU
120VU
ESS
NORM
2001VU
196RH
167RH
49VU
120VU
ESS
NORM
158RH
49VU
NORM
NORM
159RH
49VU
ESS
ESS
163RH
49VU
NORM
A321
2001 VU
179RH
168RH
49VU
120VU
ESS
49VU
DEU B FWD
NORM
120VU
DEU B AFT
NORM
173RH
174RH
172RH
162RH
153RH
193RH
2001 VU
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194RH
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1. General Overview
_
E. Circuit Breakers
2. Components details
A.
B.
C.
D.
E.
F.
G.
Directors
Smoke Detection
Decoder Encoder Units
Handsets
Flight Attendant Panel
AAP, ACP & AIP
Passenger Service Unit
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2. Components details
_
A. Directors
I. Introduction
II. Switch Over Logic
III. Power Up Sequence
IV. H/W & S/W Improvements
V. Interchangeability
2. Components details
_
A. Directors
I. Introduction
All CIDS related cabin systems are connected via data-busses to a master unit called
CIDS director.
The CIDS system has two redundant directors:
• one director (usually DIR 1) is in active mode
• the other (usually DIR 2) is in hot-standby mode.
The hot-standby director has disabled outputs versus the active director.
The functions of the Director are provided by several H/W modules and circuits:
Processing
module
Bus Interface
Circuit
Power supply
circuits
BITE/
WATCHDOG
circuits
Digital/
analogic
(audio) circuit
DIR
Data transfer
interface
to second
director
Discrete
input/output
circuits
Mandatory
layout
memory
and working
memory
029
Serial
input/output
circuit
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2. Components details
_
A. Directors
Interfaces:
The CIDS components are connected to each other and to other systems by three types
of interfaces: discrete interfaces, data-bus interfaces and audio interfaces.
• Data-bus interfaces:
2. Components details
_
A. Directors
• Discrete and audio interfaces:
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2. Components details
_
A. Directors
II. Switch Over Logic
A switchover procedure is provided in case of any Director internal failure. The CIDS
is designed so that if the active Director (usually DIR 1) is faulty then the second Director
(usually DIR 2) becomes automatically the active Director.
To ensure this switchover mechanism, CIDS DIR 1 and DIR 2 are inter-connected between
each other with:
• 4 Discrete links: 2 to exchange the active/passive status of each Directors, the 2 others
to exchange the fault status of each Directors.
• 1 ARINC 429 link: to exchange BITE results to be used by the newly active Director after
the switchover.
DIR1
The DIR 1 faults likely to trigger a switchover are:
• DIR 1 faults detected by its BITE
• Faults without BITE interaction:
Power supply fault
Central Processing Unit fault
• DIR 1 working with Mandatory layout
DIR2
2. Components details
_
A. Directors
read
DIR2 OK/FAULT.
DIR2 active/passive
DIR 1
NO
read
DIR1 OK/FAULT.
DIR1 active/passive
DIR 2
DIR 1
active?
YES
NO
DIR 1
OK?
YES
DIR 2
OK?
DIR 2
active?
NO
NO
YES
DIR1
active?
YES
set
DIR 1 passive
NO
YES
set
DIR 1 active
set
DIR 2 passive
A switchback from DIR 2 to DIR 1 will happen only if:
•D
IR 1 is powered after DIR 2 has been active, and
•D
IR 1 performs a power-up procedure without failure
Notes:
• “active” status has to be opposed to “passive”, not to “faulty”. In most cases,
DIR 2 is “passive” but not “faulty”.
• If faulty, a Director will become “passive”.
• If DIR 1 and DIR 2 are both faulty, then DIR 1 remains the “active” Director.
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set
DIR 1 active
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2. Components details
_
A. Directors
III. Power Up Sequence
CIDS Emergency mode:
Starting the CIDS only on ESS power will make the CIDS detect an “Emergency Mode”
and start emergency operation without performing the usual Power-up BITE tests.
Message Type
ATA Chapter
Message
ECAM Warning
2300
COM CIDS 1+2 FAULT (in flight)
Maintenance Status
2300
CIDS 1 (on ground)
Maintenance Status
2300
CIDS 2 (on ground)
Fault Message
237334
DIR1 (101RH)/ 28VDC2 SPLY
Fault Message
237334
DIR2 (102RH)/ 28VDC2 SPLY
Refer to AMM Task 23-73-00-861-001-A to appropriately energize the CIDS.
The full BITE function is given only when both ESS and NORMAL power types
are connected (e.g: not with A/C with servicing bus only).
DIR P/N Z014H000333B power-up:
With introduction of CIDS Director -333B and its dedicated CAM (see 2.E FAP - CAM),
starting in Emergency mode will prevent the SDF part of the CAM to be loaded and will lead
to the temporary apparition of some or all of following messages (in addition to above):
Message Type
ATA Chapter
Message
Ecam Warning
2600
SMOKE AFT CRG DET FAULT
Ecam Warning
2600
SMOKE BULK AVN DET FAULT
Ecam Warning
2600
SMOKE FWD CRG DET FAULT
Ecam Warning
2600
SMOKE LAV + CRG DET FAULT
After FWC -H2F5:
SMOKE DET FAULT
Ecam Warning
2600
SMOKE LAVATORY DET FAULT
This behaviour does not affect the SDF operation if the indications disappear with the finished
power-up procedure.
2. Components details
_
A. Directors
IV. H/W & S/W improvements
Reference doc: ISI article 23.73.00017
Here are the latest Hardware and OBRM improvements, and the corresponding SB references:
SB23-1612
Z064H000031B
Z064H000034C
SB
23
Z064H000031D
-12
84
Z064H000031A
Z064H000031C
SB23-1284
SB
23
-15
88
88
-15
23
SB
Z064H000032A
Z064H000032B
Z064H000033A
SB23-1360
Z064H000033B
SB23-1492
OBRM
Z014H000x31A
DIR
035
Z014H000231B
SB23-1611
SB23-1612
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Z014H000333B
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2. Components details
_
A. Directors
IV. H/W & S/W improvements
Reference doc: ISI article 23.73.00017
CIDS version
VSB
Improvements
CIDS DIR PNR Z014H000333B
Z014H000333B Amdt A
VSB Z014H-23-013
Prevention of spurious smoke
detection faults
Z014H000333B Amdt B
VSB Z014H-23-014
Prevention of spurious CIDS faults
& loss of communication with FAP
CIDS DIR PNR Z014H000231B
Z014H000231B Amdt A
VSB Z014-23-009
Sequencer start up improvement
thanks to CPU modification.
Z014H000231B Amdt B
VSIL 23-095
Simplification of the production through
a redesign of CPU Board
and Audio Board.
Z014H000231B Amdt 1, A1, B1, C
VSB Z014-23-012
New Protection lacquer on CIDS
Motherboard n°1.
CIDS DIR PNR Z014H00031A
Z014H000031A / Z014H000131A
Amdt A
VSB Z014H-23-005
Spurious BITE Report Suppression
Z014H000031A / Z014H000131A
Amdt B
VSB Z014H-23-006
& Z014H-23-007
Hardware improvements thanks
to Director modification
Z014H000131A Amdt C
VSB Z014H-23-008
Sequencer start up improvement
thanks to CPU modification.
Z014H000131A Amdt D
VSIL 23-081
Simplification of the production through
a redesign of CPU Board
and Audio Board.
Z014H000031A Amdt 1, A1, B1, C
VSB Z014H-23-010
New Protection lacquer on CIDS
Motherboard n°1
Z014H000131A Amdt 1, A1, B1, C1, E
VSB Z014H-23-011
New Protection lacquer on CIDS
Motherboard n°1
2. Components details
_
A. Directors
V. Interchangeability
Reference doc: IPC / ISI article 23.73.00017
Z014H000031A
2-way
interchangeable
Z014H000131A
Conditions
• OBRM ≥ -032A*
• associated CAM
Not interch. but
1-way interch. with
conditions.
Z014H000231B
Conditions
• OBRM 34C
• No cockpit AIP
Not interch. but
2-way interch.with
conditions.
Conditions
• OBRM 34C
• Discrete AA PIN 10C
& AB PIN 11E not in use
• acceptable H/W
limitations*
Z014H000333B
Notes:
• OBRM -34C is retro-compatible with CAM developped for OBRM -32x & -33x”.
* Refer to next page Notes.
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2. Components details
_
A. Directors
How to read:
P/N A
With conditions X
P/N B
This figure means: P/N A can be replaced by P/N B with conditions X.
Notes:
• When replacing a DIR unit, ensure to achieve the OBRM Download procedure
(Ref. AMM TASK 23-73-00-869-001). In fact, from repair/shop:
- DIR Z014H000031A/ Z014H000131A is preloaded with OBRM Z064H000031A
- DIR Z014H000231B with OBRM Z064H000031A
- DIR Z014H000333B with OBRM Z064H000033A.
• For each Director generation, prefer loading the latest available OBRM:
- DIR Z014H000031A/ Z014H000131A: OBRM Z064H000031C/D,
- DIR Z014H000231B: Z064H000034C,
- DIR Z014H000333B: Z064H000034C.
• DIR Z014H000231B can replace DIR Z014H000333B if:
- Restriction in SPI robustness are acceptable, refer to applicable limitations
listed in ISI 23.73.00027.
- Restrictions in the new functionalities introduced with OBRM Z064H000034C.
Mixability:
Directors P/N:
• Z014H000031A & Z014H000131A are mixable
• Z014H000031A/ Z014H000131A & Z014H000231B are not mixable
• Z014H000231B & Z014H000333B are mixable if software Z064H000034C installed.
Reference doc: IPC 23-73 / ISI article 23.73.00017
Directors obsolescence:
• DIR -x31A & -231B are obsolete. Refer to TFU 23.73.00.108 for more details
• Thanks to OBRM -34C, DIR -231B can be replaced by DIR -333B
• For DIR -x31A, CAM must be retrofitted thanks to SB 23-1612 so as to update A/C
to DIR -333B & OBRM -34C. CAM ordering is recommended to be anticipated.
2. Components details
_
B. Smoke Detection
I.
II.
III.
IV.
V.
VI.
VII.
039
Introduction
Power Supply
Aural & Visual indications
Detectors
Lavatory
Cargo
Fire extinguishing monitoring
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2. Components details
_
B. Smoke Detection
I. Introduction
Reference doc: ISI article 26.10.00006
• The Smoke Detection Function (SDF) is integrated into the enhanced CIDS-DIR LRU
(Z014Hxxx), and is an evolution of the previous generation SDCU based.
• Cargo: The Cargo Smoke Detectors are fitted in pairs per cavity to confirm smoke event
detection.
On A318/A319 and A320, two smoke detectors (one cavity) are generally installed
in the FWD compartment and four smoke detectors (2 cavities) in the AFT.
On A321, 4 smoke detectors (2 cavities) are generally installed in the FWD
compartment and six smoke detectors (3 cavities) in the AFT.
• Lavatory: only one smoke detector is installed per lavatory.
2. Components details
_
B. Smoke Detection
II. Power-Supply
CIDS-SDF power-supply architecture
Note:
If SDF 1 is deactivated (to access SDF 2 MCDU menu e.g.) smoke detectors sharing the same
energizing line will not be energized anymore, and two fault messages will be triggered:
• “CIDS (102RH)-SDF2 BUS/CIDS (101RH)-SDF1” with DIR P/N
-x31A and P/N -231B, or
• “SDF2 (102RH)-DIR (101RH)” with DIR P/N -333B, and
• “CIRCUIT BREAKER 15WH/ WRG: CAN BUS A”
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2. Components details
_
B. Smoke Detection
III. Aural & Visual Indications
• The smoke-detection system provides visual and aural warnings in the cockpit in case
of Smoke Warning Events.
• It also provides visual and aural warnings in the cabin in the case of smoke event detected
in the lavatories.
Smoke indication in case of Cargo alert
2. Components details
_
B. Smoke Detection
Smoke Indication in case of Lavatory alert
Indication of a
SMOKE Lavatory
event on the FAP
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2. Components details
_
B. Smoke Detection
Overhead Panel Indication
Standard: On 22VU
CARGO SMOKE Section on OVHD panel
Label
Type
Colour
Indication / Action
FWD SMOKE
LED
Red
Smoke alarm in FWD cargo compartment
FWD DISCH
LED
Amber
Low pressure in bottle 1
FWD DISCH
Garded Switch
N/A
FWD cargo compartment fire extinguishing bottle
discharge
AFT SMOKE
LED
Red
Smoke alarm in AFT cargo compartment
AFT DISCH
LED
Amber
Low pressure in bottle 1
AFT DISCH
Garded Switch
N/A
AFT cargo compartment fire extinguishing bottle
discharge
TEST
Push-Button
N/A
Manual Push To Test command (PTT) of smoke
detection system in LDCC
Note:
Smoke Detector in Avionic Bay (FIN 1WA) is not connected to the SDF:
• This standalone S/D its directly wired to the FWC. FWC triggers related Avionic Smoke
ECAM Warning in case of event confirmed during 5 seconds
• S/D BITE is achieved via Avionics Equipment Ventilation Computer (AEVC)
• Only one fire extinguisher bottle is installed. Discharging it in one compartment
will lead to the “DISCH” illumination for both compartments.
2. Components details
_
B. Smoke Detection
Overhead Panel Indication
Option for ETOPS: On 22VU
CARGO SMOKE Section on OVHD panel with ETOPS configured
045
Label
Type
Colour
Indication / Action
FWD SMOKE
LED
Red
Smoke alarm in FWD cargo compartment
FWD AGENT 1
Garded switch
N/A
FWD cargo compartment fire extinguishing bottle
1 discharge
FWD AGENT 2
Garded switch
N/A
FWD cargo compartment fire extinguishing bottle
2 discharge
AFT SMOKE
LED
Red
Smoke alarm in AFT cargo compartment
AFT AGENT 1
Garded switch
N/A
AFT cargo compartment fire extinguishing bottle
1 discharge
AFT AGENT 2
Garded switch
N/A
AFT cargo compartment fire extinguishing bottle
2 discharge
DISCH1
LED
Amber
Low pressure bottle 1
DISCH2
LED
Amber
Low pressure bottle 2
DISCH AGENT 2
LED
Amber
AGENT 2 to be used (AGENT 1 already discharged)
TEST
Push-Button
N/A
Manual test command (PTT) of smoke
detection system in LDCC and optional in Avionics
compartment
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2. Components details
_
B. Smoke Detection
IV. Detectors
Lavatory smoke detector
Cargo ambient smoke detector
Lavatory smoke detection cavity
Cargo smoke detection and fire
extinction cavity
Lavatory: PN PPC1200-00
Cargo: PN PPC1100-00
Smoke Detector units are based on optical detection on their surrounding air. Therefore S/D
may get progressively contaminated by their environment.
In case the contamination threshold is reached, the S/D declares itself faulty to the CIDS-SDF,
which then reports this status by a class 3 fault “CONTAMINATION” for maintenance purpose.
Note:
Lavatory Optical Smoke Detector are not designed for detecting cigarette smoke
(refer to ISI 26.17.00002 “E-cigarette or cigarette smoke detection in lavatory compartment”).
2. Components details
_
B. Smoke Detection
V. Lavatory
The lavatory smoke detectors are optical and connected via a CAN bus to a DEU type B
and linked via the CIDS middle line bus to the CIDS directors. They communicate internally
with the respective CIDS-SDF channels.
Reset of a Smoke Alert:
If there is no more smoke detected, the CIDS-SDF resets all visual and aural indications
automatically. To reset the visual and aural indication in the cabin manually you have to
push the “SMOKE RESET” button either on the “SMOKE DETECTION” page on the FAP
touchscreen (general reset), the FAP subpanel (general reset, CAM programmable button)
or on the AAP (local area reset only). This affects AIP, ACP and the cabin aural indications.
The indications on the FAP stay as long as the smoke is detected.
Location of the Lavatory
Smoke Detectors
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2. Components details
_
B. Smoke Detection
VI. Cargo
The cargo smoke detectors are connected via 2 CAN buses (A & B) to both CIDS-SDF
channels. There are two smoke detectors per cavity.
Location of the Cargo Smoke Detectors on A318, A319 and A320
2. Components details
_
B. Smoke Detection
VII. Fire extinguishing
The cargo compartment fire extinguishing system is supplied by one bottle (2 for ETOPS
option). The percussion of the bottle is controlled from the cockpit (see next page
the location of the button).
It is a single-shot fire-extinguishing system, and includes:
• A bottle with the extinguishing agent
• One squib per bottle to trigger the extinguishing agent release
• The pipes from the bottle to the compartments
• One or Two pushbutton switches 3WX (and 4WX) to activate the system
• One or Two SMOKE/DISCH indication lights 12WH (and 11WH).
• The CIDS-SDF unit to monitor the pressure of the bottles & the squibs.
The Smoke Detection Function continuously monitors the bottle pressure condition, the two
cartridges and the wiring. In case low pressure detected, the discrete LOW PRESS FIRE
EXTINGUISHING BTL 1/2 output will be set.
Notes:
• The fire extinction is triggered neither
automatically nor by the SDF.
• It is recommended to clean the S/D
following fire extinguisher release
(as advised in AMM task for bottle
replacement).
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2. Components details
_
B. Smoke Detection
Note:
Fire extinguishing function is available
for both FWD and AFT LDCC.
2. Components details
_
C. Decoder Encoder Units
I. DEU A
II. DEU B
III. DEU A&B - Connexion Box
DEU-B
DEU-B
DEU-A
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DEU-A
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2. Components details
_
C. Decoder Encoder Units
I. DEU A
DEUs A are used for Passenger functions:
• Cabin Illumination
• Reading Lights
• PAX Call
• PA & Boarding music
• Seat-row Identifier Lighting
• NS/NM, FSB and RTS signs
Each DEU A is controlled by the active director.
The DEUs A are connected to the top lines.
2. Components details
_
C. Decoder Encoder Units
DEU A
053
DEU B
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2. Components details
_
C. Decoder Encoder Units
II. DEU B
DEUs B are used for lavatory smoke detection and attendant functions:
• PA & Interphone (handsets)
• Attendants indications & controls (AAP, AIP, ACP)
• Drain Mast & Water/Waste interfaces (LLS, LLT, Vacuum, Flush)
• Slide and door pressure sensors
• Emergency Power Supply Unit (EPSU)
Each DEU B is controlled by the active director.
The DEUs B are connected to the middle lines.
2. Components details
_
C. Decoder Encoder Units
DEU A
055
DEU B
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2. Components details
_
C. Decoder Encoder Units
III. DEU A&B - Connexion box
Each DEU owns a unique identifier on its top/middle line. It is used by the CIDS to address
individually each DEU.
Those individual addresses are set by the coding switches of the connexion box:
HIGH
LOW
Coding Switch
Example :
High
Low
3
9
(See in 1.D Components location)
The last connexion-box connected to a middle or top line is a dedicated connexion box
terminating the line. It is called Termination box. If fitted before the end of the line, all DEU
behind it will be lost by the CIDS.
connexion box P/N: Z233H0000110
Termination box P/N: Z233H0010110
Reference doc: ISI article 23.73.00020
Note:
During Troubleshooting:
• Prevent swapping DEU with a connexion box and a termination box, or ensure swapping
as well connexion/termination boxes.
• If swapping DEU with connexion boxes, ensure to adapt the connexion box address
settings to the new DEU location.
• On the power lines are fuses and LEDs to indicate the power availability.
2. Components details
_
D. Handsets
I. Introduction
II. Interchangeability
III. Operational Recommendations
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2. Components details
_
D. Handsets
I. Introduction
Handsets are installed in the cockpit and at the cabin attendant stations. They are
used for the Cabin and Flight Crew Interphone functions and for Passenger Announcements
(refer to chapter 3 for more details on Interphone & PA functions).
Handsets have an integrated keyboard, including a “Push To Talk Button”, used to make
different types of calls and announcements
There are three families of handsets:
• Becker handset ST3100 series
• Holmberg handset P/N 89‐01 series
• Holmberg handset P/N N40‐1A/B series: improvement 89-01 series following
TFU 23.73.00.089 (lack of reliability)
P/N ST3100
P/N 89-01
P/N N40
2. Components details
_
D. Handsets
II. Interchangeablility
Reference doc: ISI article 23.73.00009
Prerequisite:
Replaced and installed Handsets must have the same hardkeys layout and colours definition.
This interchangeability condition is valid for all following interchangeability summaries.
Mixability:
Allowed between handset families.
Conditions
• N40-1X bracket
support assembly
to be installed.
• GSM not installed
on A/C (for ST3100
or 89-01-27-xxy)
ST3100 or
89-01 Series
Not interch. but
1-way interch. with
conditions.
N40-1A Series
Conditions
• N40-1X bracket support
assembly to be installed
1-way interch. but
2-way interch. with
conditions.
Conditions
• GSM not installed
on A/C.
N40-1B Series
How to read:
This figure means: P/N A can be replaced by P/N B with conditions X.
P/N A
With conditions X
P/N A
Note:
• SB 23-1592 released in Q1 2016 propose recommended and attractive retrofit
from ST3100 & 89-01 series to N40-1B series
• Test tone generator for ST3100 series no longer procurable.
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2. Components details
_
D. Handsets
Note:
CIDS Handsets have been designed so as to be replaced in less than 15 min.
TFU 23.73.00.099:
•O
n Classic CIDS A/C: prevent connecting cabin handsets P/N N40-1A / N40-1B series
to DEU-B P/Ns Z040H0000110, Z040H0001110, Z040H0002110, Z040H0003110,
Z040H0004110 & Z040H0005110 (cabin handsets may get damaged).
Fleet standardization:
To reduce spares stock, handsets P/N can be standardized between Classic/Enhanced CIDS
A/C and between Cabin configurations thanks to N40-1A/B series:
•T
hrough allowed Interchangeabilities
•T
hrough RFC/RMO or STC if necessary (not similar keyboard layout in particular)
SB 23-1592 released in Q1 2016 aims at recommending the retrofit from ST3100 & 89-01
series ti N40-1B series, fore reliability improvement.
Reference VSIL
Title
Date
Applicable
Series
D9240-44-09
DISCHARGE ELECTRODES MODIFICATION
11-nov
N40
D9240-44-10
RELEASE BUTTON IMPROVEMENT
11-nov
N40
2. Components details
_
D. Handsets
III. Operational Recommendations
Reference documents:
•H
OLMCO VSIL Ho-P6091-ROP-0000-01A
•C
COM chapters 03-040 PA System
To prevent reliability impacts due to misuse, Cabin and Maintenance Crews must take care
of the following operational recommendations while using the handsets:
•A
void overstretch on handset coil cord. In particular, stay close to the attendant
loudspeaker near to the bracket of the used handset. This will help improving the echo
cancellation mechanism.
•A
lways hold the handset in hand, close to both ear and mouth. Indeed, in addition
to preserve handset coil cord and housing, this will allow a better reception of the voice
signal by the directional microphone inside the handset (for surrounding noise cancellation
purpose), and will result in an easier and more intelligible PA.
•S
lide the handset in its bracket soft and smooth, without applying too much pressure.
•A
void pinching the coil cord while stowing the attendant seats.
Note:
As described in MEL - Handset section, the MEL can be applied to allow dispatch in case
of inoperative Handset.
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2. Components details
_
E. Flight Attendant Panel
I. Introduction
II. Keys Colours
III. CAM
IV. OBRM & iPRAM
V. Hardkeys
VI. Architecture
VII. Page Display Philosophy
VIII. Standard Pages
IX. Interchangeability
X. Passwords
2. Components details
_
E. Flight Attendant Panel
I. Introduction
The FAP is used to control different cabin Systems and the CIDS, to indicate the status
of different systems and for on-board changes of the CAM data.
It has a Display Unit, a Sub Panel (which contains hardkeys, an USB Interface and a headsetplug), and slots for memory cards.
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2. Components details
_
E. Flight Attendant Panel
II. Keys colours
In order to indicate degree of severity of the events and warnings shown in the FAP, a color
code is implemented in the buttons, text and figures.
Text and Figure Colour Codes
Red
Alert, command in emergency condition or marking
a dangerous situation; e.g. Open Doors, Smoke Indication…
Amber
Warnings or messages with raised priority.
White
Neutral messages or text. e.g FAP headline.
Green
OK-Messages or positive system responses.
Button Colour Codes
Grey
Unpressed / Available keys (status indication: not activated)
Light grey
Function key disabled / not available (status indication: not activated)
Green
Pressed key (status indication: activated)
Light green
Function key disabled (status indication: activated)
Amber
Caution/Hints (steady and flashing)
Red
Alarm
2. Components details
_
E. Flight Attendant Panel
III. CAM
IPRAM
CAM
OBRM
Cabin Assignment Module
It defines many of the system properties and all cabin layout and zoning customisation.
CAM Data are changed by replacement of the CAM with a reprogrammed CAM
(see ISI articles ref 23.73.00007, 23.73.00018 e.g.).
• Up to three pre-defined layouts can be saved in a CAM, and each of them can have its own
Modified Layouts stored (See example with 2 layouts in chapter FAP - Layout selection).
When a layout modification is done on a FAP page, the Save button has to be pushed to
take the modification into account and to store them into the associated Modified Layout.
The number of performed modifications is automatically counted and displayed on
the LAYOUT SELECTION page.
• The CIDS is set with the Last Used Layout, which is stored both in the DIR and the CAM,
and marked.
Additionally a Mandatory Layout is available to each Director in case of unreadable CAM
and no Last Used Layout in the DIR Memory.
CAM replacement: If the new CAM has never been fitted, DEFAULT Layout 1 will be
loaded. Otherwise the Last Used Layout will be used.
• The CAM is separated into three different CAM-Parts:
CAM-A used for CIDS system cabin configuration
CAM-B used for FAP graphic customisations
CAM-C used for flexible cargo SDF system configuration (DIR -333B)
CAM-Part Number (12 characters)
Z
0
5
CAM H/W Model
4
H
Identifies the H/W Model of the CAM
065
0
1
CAM Data
Source
0
1
Customer
Code
Identifies the source Identifies the
of CAM data
destination of CAM
(CAM programmer) data (customer)
A320 Family - Enhanced CIDS - ref: ISI 23.73.00094 - Issue: September 2017
0
Version
1
Identifies the CAM
data version
(A/C layout code
as per customer
definition)
0
Index
Identifies
changes
(corrections)
within a CAM
data version
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2. Components details
_
E. Flight Attendant Panel
III. CAM auto loading
IPRAM
CAM
OBRM
DIR power-up
CAM fitted
in FAP slot?
YES
PN in FAP
= PN in
DIR memory?
YES
NO
NO
YES
Is there
a valid Last Used
Layout?
NO
Download CAM from
FAP slot
YES
NO
Use Last Used
Layout
Use Mandatory
Layout
Download OK?
Note:
The functional restrictions of the Mandatory Layout are:
• Audio : “PA ALL” only, and no other audio source (IFE e.g.)
• Limited FAP pages and “Lights”, “Doors & Slides” and “Smoke” pages with: Basic Lights
Switching (On/Off), lack of Doors/Slides pressure monitoring indication, lack of position
for Lav Smoke Events.
• FAP hard keys all amber, with PED and Screen Lock buttons inoperative.
• Default password “000” instead of the usual ones (see Passwords chapter)
• General loss of all cabin customizations
2. Components details
_
E. Flight Attendant Panel
IV. OBRM & iPRAM
IPRAM
CAM
OBRM
On Board Replaceable Module
The OBRM contains the system software. Major changes of the CIDS functions are done by
the replacement of the OBRM (DIR S/W, SDF S/W, FAP S/W).
OBRM shall be reloaded after every DIR replacement!
Integrated Prerecorded Announcement & Boarding Music (optional)
The IPRAM stores prerecorded announcement and boarding music audio data.
P/N:
Not
supported
on SA/LR
Customization possibilities:
•S
tandard Card = Silver Card: P/N Z163H000010X
- 4 music channels: 2 Hours of Royalties-free Boarding Music
- 81 selectable Announcements in 9 different languages: Arabic, Cantonese, English,
French, German, Italian, Japanese, Mandarin, Spanish
- 9 automatic triggered Emergency Announcements
•C
ustomized Card = Gold Card: P/N Z163Hmmcctvv
A/L customized records, more languages, recent boarding music…
From Silver to Gold: refer to ISI article 23.32.00001.
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2. Components details
_
E. Flight Attendant Panel
V. Hardkeys
EMER
Allow to switch on/off the emergency lighting system
PED POWER
Allow to switch on/off the PED power.
LIGHTS MAIN ON/OFF
Allow to switch ON/OFF the general cabin illumination
LAV. MAINT
EVAC CMD
Allow to switch full bright the lavatory lighting system for maintenance
purpose
Allow to clean the FAP display by temporarily de-activating any
touchscreen action for 30 seconds.
Allow to launch an EVAC command or an EVAC request depending
on the EVAC selector switch position in the cockpit
EVAC RESET
Allow to switch off the EVAC indication (EVAC tone, AIP, ACP)
SMOKE RESET/SMOKE
“SMOKE RESET: Allow to reset LAV smoke alert indication
(Chimes, Lavatory call lights, AIPs, ACPs), as a push-button.
Provide indication as well. SMOKE: Only for indication.”
FAP-PC RESET (FAP
RESET)
Allow a manual reset of the PC card
PAX SYS
Allow to switch on/off the “Passenger Systems” IFE and ISPSS
SCREEN 30 SEC. LOCK
Note:
• USB key slot and Headset plug do not support any function (option cancelled).
However they are electrically active.
• SMOKE RESET button is CAM programmable.
2. Components details
_
E. Flight Attendant Panel
VI. Architecture
The FAP has data bus interfaces to the:
•D
irector 1
•D
irector 2
•P
rovisions (not yet implemented by Airbus):
Ethernet Hub (E-Hub)
In Flight Entertainment System (IFE)
The FAP has discrete interfaces to the:
• Director 1
• Director 2
• Emergency Lighting System
• In Flight Entertainment System (IFE)
With MP-FAP introduction thanks to OBRM
-34C, it introduces capabilities to display
external systems HMI on the FAP
(like ALNA or WCD e.g.)
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2. Components details
_
E. Flight Attendant Panel
VII. Page Display Philosophy
The CIDS related FAP pages can be activated in two ways.
• The first one is the normal mode, which means, that the relevant page is selected manually.
If there is a message for an other page, the user receives a clear indication (Info Row +
Caution Light flashing), that shows him there is an important message in the queue (no time out).
•The second one is the automatic mode, which means that the respective page is displayed
automatically. If there are more than one auto message available the user receives a hint
(Caution Light flashing + Info Row) as described in normal mode.
Any page manually selected
Display off
Time out respectively Screen
off and no auto page event
Page manually
selected
(No further
auto page event
respectively
auto page
event deactive
and Screen off)*
or (auto page
event deactive
and time out)
New
auto
page
event
Screen
off and
auto
page
avent
Other/
same
page
selected
Smoke
event
Page
automatically
selected
Note:
To get to the display off status, if further auto page events are in the queue, every auto page
event can be quit by pressing the ‘Screen off’ button. Due to the press of this button, the
respective system page is displayed automatically. This procedure has to be repeated as
long as auto page events are in the queue.
2. Components details
_
E. Flight Attendant Panel
VIII. Standard Pages
- Caution/Info Row
- Audio - External PRAM
- Audio - Integrated PRAM
- Cabin Lighting
- Doors/Slides
- Cabin Temperature
- Water/Waste
- Smoke Detection
- Seat Settings
- System Info
- Cabin Programming
- Layout Selection
- Level Adjustment
- MCDU Simulator Menu
- Software Loading
- FAP Set-Up
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2. Components details
_
E. Flight Attendant Panel
Caution/Info Row
Important
message
to be read.
Info related to
the important
message.
CAUT-Button can have 3 modes:
•B
utton off: no event (or all event disappeared)
•A
ctive flashing: new event(s)
•A
ctive steady: no new event(s) and all old event (pages) have been selected
Info Row can have 2 statuses:
• Info Row not displayed: no event or all respective pages have been manually selected
• Info Row displayed: new auto event and page is not selected
2. Components details
_
E. Flight Attendant Panel
Audio - External PRAM
The Audio page allows the users to reproduce individual or in group announcements.
The source of this announcements is external PRAM or IFE.
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2. Components details
_
E. Flight Attendant Panel
Audio - Integrated PRAM
The Audio page allows the users to reproduce individual or in group announcements.
The source of this announcements is the IPRAM Flash Card.
2. Components details
_
E. Flight Attendant Panel
Cabin Lighting
The Cabin Lighting system is described in the 3.D Cabin Illumination.
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2. Components details
_
E. Flight Attendant Panel
Doors/Slides
The Doors/Slides system is described in the 3.H Doors & Slides. In case of latency,
discrepancy or doubt, the primary source of information for Doors & Slides status is the
DOORS SD ECAM page in cockpit.
2. Components details
_
E. Flight Attendant Panel
Cabin Temperature
The Cabin Temperature system is described in the 3.G air conditioning.
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2. Components details
_
E. Flight Attendant Panel
Water/Waste
The Water/Waste system is described in the 3.K Potable Water Indication and Preselection.
2. Components details
_
E. Flight Attendant Panel
Smoke Detection
The Smoke Detection system is described in the 2.B Smoke Detection.
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2. Components details
_
E. Flight Attendant Panel
Seat Settings
Thanks to the Seat Setting FAP page the crew members are able to modify some aspects
of individual or group seats. It is possible to enable or disable reading lights of a single
or a group of seats, to inhibit calls of a single or a group of seats, etc.
2. Components details
_
E. Flight Attendant Panel
System Info
The System Info FAP page displays any message concerning CIDS and connected systems.
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2. Components details
_
E. Flight Attendant Panel
Cabin Programming
Via the Cabin Programming FAP page it is possible to move the borders between the cabin
classes. The page is protected by a password (cf FAP Passwords page).
To properly program a cabin zone refer to: AMM 23-73-00 PB001CONF01
2. Components details
_
E. Flight Attendant Panel
Layout Selection
Via the Layout Selection FAP page the user is allowed to choose one cabin layout out of
a maximum of three pre-defined and three modifiable cabin layouts. This function is only
available on ground, and the page is protected by a password (cf FAP Passwords page).
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2. Components details
_
E. Flight Attendant Panel
Level Adjustment
Through the Level Adjustment FAP page, crew is able to modify loudspeakers and chime level
in the cabin zones, attendant areas, rooms, and lavatories. The function is protected by an
access code (cf FAP Passwords page) and the function is available both in flight and on ground.
This page can be deactivated by CAM settings. In such a case, a new CAM programming is
required to make any achievement or reactivate the page.
2. Components details
_
E. Flight Attendant Panel
MCDU Simulator Menu
The MCDU Simulator Menu page is described in 4.E MCDU Simulator on the FAP.
The page is protected by a password (cf FAP Passwords page).
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2. Components details
_
E. Flight Attendant Panel
Software Loading
The Software Loading is described in the 2.E OBRM&IPRAM. From the CIDS-DIR P/N
Z014H000231B a further line with the SDF Software will be displayed. An OBRM Download
will update the SDF Software as well.
If this page is completely green, then the Software Download was successful! The page
is protected by a password (cf FAP Passwords page).
2. Components details
_
E. Flight Attendant Panel
Software Loading
Even a short power interrupt may
disturb the Software Download.
Prevent any power transfer during
this procedure.
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2. Components details
_
E. Flight Attendant Panel
Set-Up
The FAP Set-Up page is used to adjust display brightness, FAP loudspeaker and headset
volume, as well as removing and installing IPRAM, CAM and OBRM cartridges.
Note:
When replacing the CAM or OBRM by means of these windows, DO NOT FORGET to access
the Layout Select Page and SW Download Page and perform the data download manually
• otherwise the CAM will be loaded only with the next CIDS power up
• the OBRM is never loaded automatically
2. Components details
_
E. Flight Attendant Panel
IX. Interchangeability
Reference Doc: ISI article 23.73.00021
Part Number:
Z133H0 x y z uvw
FAP Type
Hardware Version
Software Version
Customized Definition:
•H
ardkeys layout
•C
olours definition
Prerequisite:
Replaced FAP and Installed FAP must have the same hardkeys layout and colours definition.
This interchangeability condition is valid for all following interchangeability summaries.
FAP types:
0: Basic FAP
1: Basic + PC card + Hub
2: Basic + Hub
3: Basic + iPRAM capability
4: Basic + PC card + Hub + iPRAM capability
5: Basic + Hub + iPRAM capability
Notes:
• There is a break in Customized Definition digit between generations -50B/-51A
and -51C/-51D/-51E.
• Options using the Hub capability are not implemented on Single Aisle Aircraft.
• Only Water Depress option is using the PC Card functionality on FAP types 1 & 4.
FAP type 5 is missing the PC Card internal board, but Water Depress option is well
supported and connectors remain unchanged.
• Acceptability of discrepancies between customized version definitions can be evaluated
on a case by case analysis and eventually temporary covered through a chargeable TA.
• With OBRM -34C, MP-FAP P/N Z145H series is being introduced. It allows displaying
HMI of external systems (like ALNA or WCD) on the MP-FAP.
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2. Components details
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E. Flight Attendant Panel
IX. Spares & Interchangeability
Z133H0x1z51A
Conditions
• Interchangeable
if x=5
• With FAP type
5 limitations
compared to
FAP type (x).
Not interch. but
2-way interch. with
conditions.
Conditions
• Interchangeable if
x=5
• With FAP type (x)
limitations compared to FAP type 5.
Z133H052z’51C
1-wayinterch. but
2-way interch. with
conditions.
Conditions
• Display limitation
acceptable.
Z133H052z’51D
2-way
interchangeable
Z133H053z’51E
Conditions
• OBRM -34C
• New CAM if
x= 3, 4 or 6
Not interch. but
2-way interch. with
conditions.
Z145H0x4z120
Conditions
• Only if x=0
2. Components details
_
E. Flight Attendant Panel
X. Passwords
The following system pages are protected by a password:
FAP Page
Default
Password
Related AMM Task
Software Loading
813
23-73-00-869-001-A
Layout Selection
318
23-73-00-860-002-A
Cabin Programming
318
23-73-00-860-008-A
Level Adjustment
318
23-73-00-860-009-A
MCDU Simulation
318
23-73-00-860-010-A
The passwords are defined in the CAM and are customizable via CAM reprogramming.
In that case the new password will be mentioned in the related AMM task.
If the CAM is not readable, the default code is 000 (but DIR is in Mandatory Layout mode).
There is no limitations in number of incorrect password inputs.
FAP display out of sleep:
If you push the SCREEN OFF button, it switches off the screen. The screen is also switched
off, if no input is made for more than 10 minutes.
If the screen is switched on by touching the screen or by an auto event, you may first have
(it is optional) to enter a password (813 by default). Only the SMOKE page comes up without
any password protection.
If activated, this out-of-sleep password is defined into the CAM.
Reference doc: ISI article 23.73.00007
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2. Components details
_
F. AAP, ACP & AIP
I. Additional Attendant Panel
II. Area Call Panel
III. Attendant Indication Panel
2. Components details
_
F. AAP, ACP & AIP
I. Additional Attendant Panel
Reference doc: ISI article 23.73.00021
AAP:
The AAP enables the attendants to control certain cabin systems and the CIDS via membrane
switches.
They are installed near the doors in the pressurised area of the cabin.
Their keypad layout can be customized.
EVAC/SMOKE RESET Switch panels:
Switch Panels related to EVAC Indication respectively EVAC and SMOKE Reset could be
optionally located on the panels 2064VU respectively 2065VU. The switch panel performs
indication of the EVAC alert, reset of the EVAC signalling, and reset of the aural and visual
smoke warnings, related to the respective lavatory.
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2. Components details
_
F. AAP, ACP & AIP
II. Area Call Panel
The Area Call Panel (ACP) is installed at each end of the passenger compartment to the left
and right of centre in the ceiling. The ACP has four separately controlled fields, each contains
two parallel connected white lamps or four coloured LEDs. The lights are visible from the front
or rear of the ACP. They are coloured in one of two available cover lenses. The colours are as
follows:
Colour 1
Colour 2
Colour 3
Colour 4
Amber
Red or Green
Red
Blue
The fields are activated either continuously or are flashed. They are used as a far-call facility
to inform cabin attendants of PAX-call, interphone call, emergency call, Evacuation command
and lavatory smoke.
2. Components details
_
F. AAP, ACP & AIP
III. Attendant Indication Panel
Reference doc:
ISI article 23.73.00021
The AIP provides indications for call functions to attendant stations. Its display shows dial
and call information from the PA/Interphone system and other system-related information
(e.g. Lav Smoke Location/ PAX Calls). The AIPs are installed near all attendant stations
in the pressurized area of the cabin.
It is connected to the DEU B who provides the 28VDC.
RED and GREEN LED signification:
INDICATOR LIGH
ACTIVATED FUNCTION
RED
GREEN
LAVATORY SMOKE DETECTION
FLASHING
Not illuminated
EVACUAUTION SIGNALLING
FLASHING
Not illuminated
SERVICE INTERPHONE
Not illuminated
Not illuminated
PASSENGER CALL
Not illuminated
Not illuminated
PRERECORDED INTERPHONE
Not illuminated
Not illuminated
*STERILE COCKPIT INDICAITION
Not illuminated
STEADY
• EMERGENCY CALL from Cockpit
FLASHING
Not illuminated
• ALL ATTND CALL from Cockpit
Not illuminated
STEADY
• ALL ATTND CALL from Cabin
Not illuminated
STEADY
• NORMAL CALL from Cockpit
Not illuminated
STEADY
• NORMAL CALL from Cabin
Not illuminated
STEADY
CABIN INTERPHONE
Note: Those settings, as well as associated chimes, are CAM customizable
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2. Components details
_
G. Passenger Service Unit (PSU)
The PSU consists of:
•R
eading-light switches and reading lights,
•P
AX call button and call light,
•S
eat-row identifier,
•L
oudspeakers,
•N
on-Smoking (NS), No-Mobile (NM, optional), Fasten Seat Belt (FSB) and Return To Seat
(RTS, in Lavatory only) signs
It is linked to the DIR via DEU A and Passenger Interface and Supply Adapter (PISA).
PSU
NS & FSB
illuminated
signs:
NM & FSB
illuminated signs,
NS nonilluminated sign:
PISA
StA PISA
3. CIDS Functions
A.
B.
C.
D.
E.
F.
G.
H.
I.
J.
K.
L.
M.
N.
O.
P.
Q.
Passenger Address
Cabin and Flight Crew Interphone
Service Interphone
Cabin Illumination
Emergency Evacuation
Passenger Call
Air Conditioning
Doors & Slides
In Flight Entertainment
Emergency Power Supply Unit (EPSU)
Potable Water Indication and Preselection
Vacuum System Control Function (VSCF)
Waste Quantity Indication
Cabin Ready Function
Sterile Cockpit
Cabin & Cockpit Alerting System
Drain Mast Control Unit (DMCU)
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3. CIDS Functions
_
A. Passenger Address
The Passenger Address (PA) System allows Cabin & Flight crews to dispatch messages
(e.g. Safety announcements) to the Passengers in cabin.
It operates with different priorities.
Two announcements dedicated to separated A/C areas can occur at the same time
(e.g. PA1 & PA2 simultaneously from different sources in a 2 classes configuration A/C).
But if two announcements dedicated to a common A/C area occur at the same time,
only one announcement will be heard, according to the following rule:
Announcement 1 (A1) & Announcement 2 (A2)
pronounced at the same time
A1 has a higher function priority than A2?
YES
Only A1 is heard
NO
YES
A1 has a higher source priority than A2?
NO
Only A2 is heard
Function priority levels:
1. DIRECT PA (PTT)
and PA from AMU
2. PA ALL and all remaining
PA (e.g. PA1, PA2, PA3)
Source priority levels:
1. AMU
2. Cockpit Handset
3. Purser Handset (Option)
4. Attendant Handsets
5. PRAM (Option)
6. IFE (Option)
3. CIDS Functions
_
A. Passenger Address
In case of low cabin-pressure or engine on (high oil-pressure) the volume of a PA
announcement is increased. The volume is also increased in case of a data bus failure
(top line).
If a cabin handset is in use, the volume of the PA announcement in the respective handset
area is decreased to avoid a feedback. There is also a volume decrease in the cockpit door
area, if during a PA the cockpit door is opened in order to avoid a feedback with the cockpit.
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3. CIDS Functions
_
B. Cabin & Flight Crew Interphone
The Cabin & Flight Crew Interphone allows phone communication between all attendant
stations and the cockpit.
There can be one or more calls initialized at the same time.
In conference mode the communication is possible between more than two interphone
stations.
3. CIDS Functions
_
B. Cabin & Flight Crew Interphone
The Interphone System operates with different priorities.
Different calls can occur at the same time if it involves different sources and addresses
(e.g. calls between CPT
EXIT and FWD
AFT attendant).
But if two calls address the same station at the same time, only one call will succeed,
according to the following rule:
Call 1 (C1) & Call 2 (C2) initiated
at the same time
C1 has a higher function priority than C2?
YES
C1 succeeds
NO
YES
C1 has a higher source priority than C2?
NO
C2 succeeds
Function priority levels:
1. Emergency Call
2. Calls from cockpit
3. All attendant call
4. Normal call
Source priority levels:
1. AMU
2. Cockpit Handset
3. Purser Handset (Option)
4. Attendant Handsets
5. PRAM (Option)
6. IFE (Option)
Notes:
• Should C1 and C2 be sharing the same function priority and same source priority
(e.g. attendant handsets), then the call initiated first (few milliseconds earlier)
would be the one established.
• In option (CAM programming), cockpit can listen to the interphone calls between
attendants (not involving cockpit).
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3. CIDS Functions
_
C. Service Interphone
The Service Interphone allows communication between ground crew, cockpit crew and cabin
crew, when the CIDS is powered.
The link from the director to the service interphone jacks can be established when a jack
is plugged:
•a
utomatically by extending and compressing the landing gear for more than 10 seconds
•m
anually by pressing the service interphone override switch (e.g during heavy maintenance
with retracted landing gears).
3. CIDS Functions
_
D. Cabin Illumination
The illumination in the different areas is controlled by the Cabin Illumination function.
The adjustment of the light intensity in the PAX area can be controlled with the cabin lighting
page of the FAP. However, some automatic behaviors are pre defined (whatever
the customized light configuration) and occur in the following situations:
103
Event
Light setting
CIDS deactivated, control signal lost by the ballast
unit, DEU A or Top Line lost
CIDS controlled lights on with full brightness,
after 3 min without signal
CIDS activation
Lavatory lights dimmed, others stay
with full brightness
Oil pressure high & cockpit door open
Light intensity dimmed in the FWD entrance area
Low cabin pressure
All light on with full brightness
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3. CIDS Functions
_
E. Emergency Evacuation
The Emergency Evacuation Signaling (EVAC) system controls the evacuation signaling in all
cabin areas and the cockpit. It is activated from the cockpit or the cabin during an emergency
evacuation.
To reset an already activated ECAM alert
proceed as follows:
EVAC activated from
the cockpit
Push the EVAC COMMAND
button in the cockpit a second
time
EVAC activated from
the cabin
• Push the EVAC COMMAND
button in the cockpit twice
Or
• Push the EVAC COMMAND
button on the related panel
a second time
Note:
Pushing the EVAC/Reset button on the FAP hardkey panel or AAP only cancelled visual and
aural indications in the related cabin zone.
3. CIDS Functions
_
E. Emergency Evacuation
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3. CIDS Functions
_
F. Passenger Call
The passenger call function controls the passenger call activation and the illumination
of passenger call lights.
A passenger call is started by pushing the passenger call button which is installed at each
seat row and in each lavatory.
After call activation, the director switches on the respective PSU PAX call light, the related
ACP light segment and a message on the AIP shows the location of the call. A call chime
is also heard from all loudspeakers in the respective cabin area after every call activation.
Reset:
The chime can be inhibited by pushing the “CHIME INHIB” button on the audio page
of the FAP.
All the indications can be reset by pushing the call button a second time, or by pushing
the “CALL RESET” button on the Audio page of the FAP or on the AAP.
3. CIDS Functions
_
G. Air Conditioning
The CIDS has the capability to do a fine adjustment of the temperature in the separate
cabin zones from the Cabin Temperature page on the FAP (and optional AAP controls).
Master temperature setting is selected in the cockpit, only fine adjustment is possible
through the FAP if cabin temperature is out of range (18-30°C), temperature is displayed
on the FAP but a blue box indicates that control on the FAP is not possible.
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3. CIDS Functions
_
H. Door & Slides
The DOOR/SLIDES page of the FAP shows the status of each door (open/close) and slide
(armed/disarmed) and the status of each door bottle and slide bottle (pressure).
The slide pressure monitoring of over-wing exit (A318/A319/A320) is standard.
However, the other slides pressure monitoring and door pressure monitoring are optional
(refer to ISI article 23.73.00058). A CAM reprograming will be required if the option
is selected. If the option to check bottle pressure is installed, the class 1 cabin fault
“CHECK DOOR PRESSURE” could be triggered if the press is low or if not data is available
to the CIDS. Refer to MPD Tasks 521000-01-1 & 522200-08-1.
3. CIDS Functions
_
I. In Flight Entertainment (IFE, optional)
The CIDS director transmits system information and PA related announcements from
and to the IFE system.
The IFE interface receives system information and PA related audio signals from the CIDS
director. The IFE additionally sends system information to the director.
CIDS transmits the following system information to the IFE:
•A
ctivation/deactivation of PAX Calls,
•A
ctivation/deactivation of NS/NM, FSB and RTS signs
•L
ayout data,
• Illumination data (depending on the IFE type),
•L
anding gear down and compressed,
•L
anding gear down and locked,
•O
il pressure low,
•C
abin pressure low,
•E
xcession altitude,
•S
lats out,
•F
laps out,
•A
ll doors closed.
CIDS receives the following
system information from
the IFE:
•A
ctivation/deactivation
of PAX Calls,
•A
ctivation/deactivation
of reading lights.
In case of PA from IFE
(Video or audio only),
the IFE transmits
the audio signals to
the CIDS director.
From the director
the signals are transmitted
via the DEU type A directly or via PISA to the cabin loudspeakers.
In case of PA from the CIDS (handset/IPRAM/cockpit), the CIDS overrides the IFE audio
in PAX headsets.
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3. CIDS Functions
_
J. Emergency Power Supply Unit
The EPSU supplies electrical power to the emergency lighting system.
The Centralized Fault Display System (CFDS) transmits respective signals via director
and DEU type B to the EPSU, if one of the following BITE test is initiated via the MCDU:
•S
ystem test,
•B
attery capacity test.
The EPSU does the test. When the test is finished, the results are transmitted via DEU
type B to the director, which sends the results to the CFDS. The test results are indicated
on the MCDU.
3. CIDS Functions
_
K. Potable Water Indication & Preselection
The potable water indication & preselection system shows the filling level of the water tank
on the FAP.
It also gives the commands for the preselection of the water quantity if the option is activated
in the CAM. The preselection value is stored in the CIDS Director and kept against CIDS reset.
The indication and preselection is done on the WATER/WASTE page of the FAP.
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ETHERNET
FILTER
FLIGHT ATTENDANT
PANEL (FAP)
SHUTTLE
VALVE
FWD WATER
DRAIN PANEL
FROM BLEED
AIR SYSTEM
FROM BLEED
AIR SYSTEM
TO FWD LAVATORY
AND GALLEY
DRAIN
VAVLE
CONTROL
HANDLE
CIDS
DIRECTOR 1
RELIEF
VALVE
FWD DRAIN VALVE
OPEN LIGHT
MIDDLE LINE
TO AFT LAVATORY
AND GALLEY
WATER QTY
TRANSMITTER
TANK FULL
LIGHT
FILL/OVERFLOW
DRAINVAVLE
GROUND
PRESS
FILL/DRAIN
CONTROL HANDLE
CABIN FLO
DOOR LIMIT
SWITCH
POTABLE WA
SERVICE PLAN
QUANTITY
INDICATOR
DEU B
TANK FULL SIGNAL
112
3. CIDS Functions
_
K. Potable Water Indication & Preselection
3. CIDS Functions
_
L. Vacuum System Control Function
The Vacuum System Control Function is an extension of the CIDS operation software,
former vacuum external system integrated within the CIDS with CIDS Enhanced generation.
It monitors and controls the Vacuum Toilet System.
This includes the following functions: Control of toilet assemblies, Monitoring of waste tank
level, Control of vacuum generator, Servicing procedure, Communication with other systems,
BITE monitoring of vacuum system components, C/B monitoring.
Note:
The Vacuum Generator is required for the flush, in low altitude or on ground. If related DEU B
is faulty or deactivated, flush of the related lavatory will be inoperative.
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3. CIDS Functions
_
L. Vacuum System Control Function
3. CIDS Functions
_
M. Waste Quantity Indication
The waste indication system shows the filling level of the waste tanks on the Water/Waste
page of the FAP. Related faults (e.g. LLS failure) are also indicated on this FAP page.
The waste quantity is transmitted from the Liquid Level Sensor (LLS) and the Liquid Level
Transmitter (LLT) via DEU type B to the director.
The operation and indication is performed via the FAP page.
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3. CIDS Functions
_
N. Cabin Ready
Reference doc: ISI article 23.73.00023
The cabin crew sets the cabin ready signal when all cabin systems are supposed to be
in the correct condition for take off or landing. If all conditions are met, the cabin ready
message is displayed at the cockpit ECAM panel. Several sets of conditions can be selected.
They are defined in the CAM.
The status is indicated on:
• the ECAM upper display unit, on the take-off check-list (on 2min. after both engines running)
or on the landing check-list (on below 2000ft and landing gear extended),
•o
n the CABIN STATUS page on the FAP the cabin ready button is illuminated
O. Sterile Cockpit
The sterile cockpit command is used by the flight crew if they do not want to be disturbed.
The sterile cockpit command is activated/deactivated with the cockpit switch. The cockpit
switch sets a ground signal to the director. Via DEU type B the director switches
on the respective ACP light segment and the related message is shown on the AIP.
P. Cabin & Cockpit Alerting System
The Cockpit and Cabin Alerting System is used to indicate a possible severe incident
to cabin or cockpit crew members. It activates visual and audio indications in the cockpit,
if the respective button in the cabin is pushed (cabin alert). Vice versa, visual and aural
indications in the cabin are activated, if the respective button in the cockpit is pushed
(cockpit alert).
Cabin push buttons are connected through DEU-B.
3. CIDS Functions
_
Q. Drain Mast Control Unit (DMCU)
The DMCUs monitor and control the drainmast heaters. There is a separate DMCU for every
heater.
The drainmast system status is transmitted from the DMCU via DEU type B to the director.
In case of a failure, the director sends the signal to the FAP and to the Centralized Fault
Display System (CFDS). On the FAP the CIDS Info light comes on to indicate that there is new
failure message. Via the CFDS the failure message is shown on the MCDU.
The CFDS transmits respective signals via director and DEU type B to the DMCU, if the BITE
test “System Test” is initiated via the MCDU:
The DMCU does the test. When the test is finished the results are transmitted via DEU type B
to the director, which sends the results to the CFDS. The results are indicated on the MCDU.
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4. BITE
A.
B.
C.
D.
E.
F.
Introduction
Failures Annunciation
List of ECAM alerts & Maintenance Status
MCDU CIDS
MCDU CIDS Simulator on the FAP
MCDU SDF
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4. BITE
_
A. Introduction
The CIDS has an extensive self-monitoring capability. When electrical power (both Normal
and Essential power) is connected to the CIDS, a power-up test of the system is started.
The result is shown on the power-up page of the FAP.
Comprehensive BITE circuits are present in:
DIRs, DEUs, PISAs, FAP, AAPs and AIPs.
This allows the CIDS to detect faults in the connected systems and in the CIDS units.
These failures are written into the BITE memory of the directors and are sent
to the Centralized Fault Display System (CFDS) in normal and interactive mode.
The display units of the CFDS are called Multipurpose Control and Display Units
(MCDU)s. There are three MCDUs in the cockpit. The indication of the failures depends
on their importance (classes).
The CIDS also memorizes failures which are reported from the connected systems and sends
the failure messages to the CFDS.
Parts of the failure messages (ATA references, FINs and locations) are defined in the Cabin
Assignment Module (CAM).
The failure handling/memorization is done in relation to the flight phases. The commands
are sent from the CFDS to the CIDS. The failures are classified as class 1, 2 or 3 and identified
as internal or external failures.
4. BITE
_
A. Introduction
Normal Mode:
In the normal mode only failures (class 1, 2 and 3) which are detected during the current/last
flight are sent continuously to the CFDS. It is started when the system is supplied with power.
If a failure is detected during a flight, the related failure message is stored in the BITE memory
and transmitted continuously to the CFDS until the start of the next flight. A disappearance
of the failure has no effect, the failure is still in the BITE memory.
Interactive Mode:
The interactive mode provides the capability of a dialogue between the CIDS and the CFDS.
This is only possible when the A/C is in ground configuration.
On request from the MCDU, the CIDS sends menu pages related to the MCDU keys.
Each A/C has a printer. Printouts from the CIDS related menus are possible on the ground.
You can make a data print from the MCDU. For additional information about:
MCDU (AMM Ref. 45-11-00)
Printer (AMM Ref. 45-40-00)
System Report/Test:
The system report/test is a part of the main maintenance menu and gives a dialogue between
the MCDU and each system connected to the CFDS. This is only possible when the A/C
is in ground configuration.
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4. BITE
_
B. Failures Annunciation
Depending of the class type and operational consequences, CIDS Faults may be indicated
differently in the Cockpit or in the Cabin:
Fault type
Class 1 Aircraft
Class 2 Aircraft
Cockpit Indication
Cabin Indication
ECAM Warning
Caution Light on the FAP
Master Caution or Master Warning
Associated FAP Pages triggered
Maintenance Status
Typically no indication in the Cabin (exception:
“NOT ALL POWER CONNECTED” on the FAP
if on service bus only no CIDS BITE
capabilities.
Flashing Caution Light on the FAP
Class 1 Cabin
Class 3 faults
Request for action (from Attendant
or Mechanic) on the respective FAP page
Only on request on the MCDU (“Class 3 Menu”)
Test Types to confirm and locate faults:
1. Power-Up Test
2. Continous test, monitoring, "GROUND SCANNING" (via CFDS/MCDU)
Test Types:
3. M
anually activateable test, "INTERFACE + POWER-UP TEST"
(via CFDS/MCDU)
4. Manually activateable test (via CFDS/MCDU)
5. Audible/visual tests, "OP Test" (via CFDS/MCDU) no BITE messages
4. BITE
_
C. SDF - ECAM alerts & Maintenance Status
ECAM alerts
Upper ECAM:
123
E/WD message
Description
SMOKE LAV+CRG DET FAULT
Loss of smoke detection function
(valid up to FWC standard H2F5)
SMOKE DET FAULT
Loss of smoke detection function
(valid from FWC standard H2F5)
SMOKE FWD CARGO SMOKE
Smoke detected in FWD cargo compartment
SMOKE AFT CARGO SMOKE
Smoke detected in AFT cargo compartment
SMOKE FWD CRG DET FAULT
Loss of Smoke Detection function in FWD
Cargo compartment.
SMOKE AFT CRG DET FAULT
Loss of Smoke Detection function in AFT
Cargo compartment.
SMOKE LAVATORY SMOKE
Smoke detected in a lavatory
SMOKE LAVATORY DET FAULT
Loss of Smoke Detection function in Lavatory.
SMOKE FWD CRG BTL FAULT
Squib fault of FWD cartridge
(one bottle configuration)
SMOKE AFT CRG BTL FAULT
Squib fault of AFT cartridge
(one bottle configuration)
SMOKE FWD CRG BTL FAULT
SMOKE AFT CRG BTL FAULT
Low pressure of fire extinguishing bottle
(one bottle configuration)
SMOKE FWD CRG BTL1 FAULT
Squib fault of FWD cartridge of bottle 1
(two bottle configuration)
SMOKE FWD CRG BTL2 FAULT
Squib fault of FWD cartridge of bottle 2
(two bottle configuration)
SMOKE FWD CRG BTL1 FAULT
SMOKE AFT CRG BTL1 FAULT
Low pressure of fire extinguishing bottle 1
(two bottle configuration)
SMOKE AFT CRG BTL1 FAULT
Squib fault of AFT cartridge of bottle 1
(two bottle configuration)
SMOKE AFT CRG BTL2 FAULT
Squib fault of AFT cartridge of bottle 2
(two bottle configuration)
SMOKE FWD CRG BTL2 FAULT
SMOKE AFT CRG BTL2 FAULT
Low pressure of fire extinguishing bottle 2
(two bottle configuration)
SMOKE DISCH AGENT 2
Switch from “AGENT 1” to “AGENT 2” on overhead
panel
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4. BITE
_
C. SDF - ECAM alerts & Maintenance Status
Upper ECAM (provisions only):
ECAM alerts: Warnings & Cautions
E/WD message
Description
SMOKE BULK AVN SMOKE
Smoke detected in AFT avionics rack
SMOKE BULK AVN DET FAULT
Loss of AFT avionics rack smoke detection
SMOKE VIDEO SMOKE
Smoke detected in IFE VCC
SMOKE VIDEO DET FAULT
Loss of IFE VCC smoke detection
SMOKE CAB GSM SMOKE
Smoke detected in GSM cabinet
SMOKE CAB GSM DET FAULT
Loss of GSM cabinet smoke detection
AVIONICS SMOKE
Smoke detected in avionics compartment
Lower ECAM:
INOP SYS message
Description
SMOKE DET
Loss of smoke detection function
FWD CRG DET
Loss of FWD cargo compartment smoke detection
AFT CRG DET
Loss of AFT cargo compartment smoke detection
LAV DET
Loss of lavatory smoke detection
Lower ECAM (provision only):
INOP SYS message
Description
BULK AVN DET
Loss of AFT avionics rack smoke detection
VIDEO DET
Loss of VCC smoke detection
MAINTENANCE STATUS:
Maintenance Status
Description
CAB ELEC DET
Loss of GSM smoke detection (provision only)
SMOKE
Issue detected by SDF BITE
4. BITE
_
C. CIDS - ECAM alerts & Maintenance Status
Upper ECAM:
ECAM alerts: Warnings & Cautions
E/WD message
Description
COM CIDS 1+2 FAULT
Fault detected by both CIDS 1&2
Lower ECAM:
INOP SYS message
Description
CIDS 1+2
INOP SYS
MAINTENANCE STATUS
Maintenance Status
Description
“CIDS1“ or “CIDS2“
class 2 failures
Notes:
• Maintenance Status are only displayed in flight phases 1 and 10 (i.e. engine not running).
It means that when one system sends a maintenance status to be displayed, the FWC
will delay it until flight phase 10 pending the system keeps on sending the fault.
But the alert will be reported in the PFR at the time when the maintenance status has
been computed for Maintenance action.
• As Maintenance Status, the “SMOKE”, “CIDS1” and “CIDS2” messages do not prevent
dispatch, as related MMEL items must be evaluated.
• FCOM Supplementary Procedure ID PRO-SUP-24-x provide flight crew reset procedures
for CIDS & SDF as a first recovery mean to clear spurious messages.
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4. BITE
_
D. MCDU CIDS
I. Access
II. Last Leg Report
III. Previous Legs Report
IV. LRU Identification
V. Class 3 Faults
VI. System Tests
VII. Power Up Test
VIII. Operational Tests
IX. Troubleshooting Data
X. Ground Scanning
XI. Ground Report
XII. System Configuration
4. BITE
_
D. MCDU CIDS
I. Access
To access to the SYSTEM REPORT/TEST/COM page, apply the following steps:
• Push the MCDU MENU mode key
• Push the line key adjacent to the CFDS indication.
• Push the line key adjacent to the SYSTEM REPORT/TEST indication.
• Push the line key adjacent to the COM indication.
CFDS
MCD MENU
<LAST LEG REPORT
<FMS
<LAST LEG ECAM REPORT
<PREVIOUS LEGS REPORT
<CFDS
<A/C CURRENT STATUS
<SYSTEM REPORT/TEST
<POST FLIGHT REPORT
SELEC DESIRED SYSTEM
1
SYSTEM REPORT/TEST
127
<AIRCOND
F/CTL>
<AMU
<AF5
FUEL>
<AMP
SYSTEM REPORT/TEST
COM
CIDS2>
HF1>
<COM
ICE & RAIN>
<RMP2
HF2>
<ELEC
INST>
<RMP3
VHF1>
<FIRE PROT
L/G>
<CIDS1
VHF2>
<RETURN
NAV>
<RETURN
A320 Family - Enhanced CIDS - ref: ISI 23.73.00094 - Issue: September 2017
NAV>
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4. BITE
_
D. MCDU CIDS
Main Page
This page shows the subsequent selectable pages:
•<
LAST LEG REPORT,
•<
PREVIOUS LEGS REPORT,
•<
LRU IDENT,
•<
GND SCANNING,
•<
TROUBLE SHOOT DATA,
•C
LASS 3 FAULTS>,
•S
YSTEM TESTS>,
•E
PSU BAT CAP TEST>,
•O
P TESTS>,
•G
ROUND REPORT>,
•S
YSTEM CONFIG>,
<RETURN (when you push this line select key you go back to the Main page).
1
<AMU
SYSTEM REPORT/TEST
COM
<RMP2
HF2>
<RMP3
VHF1>
<CIDS1
VHF2>
<RETURN
VHF3>
O7
< LAST
LEG REPORT < PREVIOUS
LEGS REPORT
<LRU IDENT
<GND SCANNING
< TROUBLE
SHOOT DATA
<RETURN
CIDS1
CLASS3 FAULTS>
SYSTEM TESTS>
EPSU BAT>
CAP TEST
OP TESTS>
GROUND REPORT>
SYSTEM CONFIG>
CIDS2>
<AMP
CIDS X
INTERACTIVE MODE
CURRENTLY DISABLED
LAYOUT SELECTION MODE
OR MAINTENANCE MODE
ACTIVE ON FAP
<RETURN
HF1>
4. BITE
_
D. MCDU CIDS
II. Last Leg Report
When you push the <LAST LEG REPORT line select key, the LAST LEG REPORT page
comes on. This page shows the failure messages that came on during the last flight
and it shows the subsequent data:
•T
he data of the last flight,
•T
he time when the failure occurred,
•T
he ATA reference,
•T
he identity of the unserviceable LRU,
•T
he class of the failure (1 or 2).
This page can show a maximum of two failures. If there are more failures, you must push
the next page key on the MCDU keyboard. If there are no failures found during the last flight,
the message NO FAULT DETECTED is shown in the centre of the screen.
< LAST
LEG REPORT < PREVIOUS
LEGS REPORT
<LRU IDENT
<GND SCANNING
< TROUBLE
SHOOT DATA
<RETURN
CIDS1
CLASS3 FAULTS>
SYSTEM TESTS>
EPSU BAT>
CAP TEST
OP TESTS>
GROUND REPORT>
SYSTEM CONFIG>
OR
CIDS 1
LAST LEG REPORT DEC17
UTC ATA
NO FAULT DETECTED
<RETURN
CIDS 1
LAST LEG REPORT DEC17
1110 237316
DEU A (200RH16)
PRINT*
<RETURN
A320 Family - Enhanced CIDS - ref: ISI 23.73.00094 - Issue: September 2017
1>
PRINT*
DEU A PAGE EXAMPLE
129
CLASS
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4. BITE
_
D. MCDU CIDS
III. Previous Legs Report
When you push the <PREVIOUS LEGS REPORT line select key, the PREVIOUS LEGS
REPORT page comes on.
This page is a sum of the LAST LEG REPORTS and shows the failure message that came
on during the 63 flights before.
This page shows the subsequent data:
•T
he aircraft identification.
Note:
CIDS monitors the aircraft ident parameter and updates it for all new records. This is
necessary if a director is changed from one aircraft to another. In this case there may be
two idents on a page. The related aircraft ident is shown above the related failure message.
•T
he Leg number (1-63),
•T
he date of the flight when the failure occurred,
•T
he time when the failure occurred,
•T
he ATA reference,
•T
he class of the failure (1 or 2),
•T
he identity of the unserviceable LRU.
This page can show a maximum of two failures.
If there are more failures, you must push the next
page key on the MCDU keyboard. If there are
no failures found during the last 63 flights,
the message NO FAULT DETECTED is shown
in the centre of the screen.
< LAST
LEG REPORT < PREVIOUS
LEGS REPORT
<LRU IDENT
<GND SCANNING
< TROUBLE
SHOOT DATA
<RETURN
CIDS1
CLASS3 FAULTS>
SYSTEM TESTS>
EPSU BAT>
CAP TEST
OP TESTS>
GROUND REPORT>
SYSTEM CONFIG>
OR
CIDS 1
PREVIOUS LEGS REPORT
DA-ABCD
CIDS 1
PREVIOUS LEGS REPORT
DA-ABCD
LEG DATE UTC ATA CLASS
NO FAULT DETECTED
<RETURN
04 JAN1/1306 240000 1
POWER SUPPLY INTERRUPT
PRINT*
<RETURN
PRINT*
POWER SUPPLY INTERRUPT PAGE EXAMPLE
4. BITE
_
D. MCDU CIDS
IV. LRU Identification
When you push the <LRU IDENT line select key, the LRU IDENTIFICATION page comes on.
This page shows the identity of all the electronic LRUs which can report their part number
and serial number.
It indicates what is detected in the CAM and in the OBRM slots, which might be different
from what is loaded in the DIR.
< LAST
LEG REPORT < PREVIOUS
LEGS REPORT
<LRU IDENT
<GND SCANNING
< TROUBLE
SHOOT DATA
<RETURN
CIDS1
CLASS3 FAULTS>
SYSTEM TESTS>
EPSU BAT>
CAP TEST
OP TESTS>
GROUND REPORT>
SYSTEM CONFIG>
OR
EXAMPLE
DIR1
DIR2
OBRM
CAM
FAP
CIDS 1
LRU IDENTIFICATION
P/N: ZO14H000030A
S/N: NNNN
P/N: ZO14H000030A
S/N: NNNN
P/N: MMMMMMMMMMMM
P/N: MMMMMMMMMMMM
1
<RETURN
P/N: MMMMMMMMMMMM
S/N: NNNN
PRINT*
NOTE : MMMM FOR RESPECTIVE P/N INCL AMENDMENT
NNNN FOR RESPECTIVE SERIAL NUMBER
1 NAME OF AFFECTED FAP
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132
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4. BITE
_
D. MCDU CIDS
V. Class 3 faults
When you push the CLASS 3 FAULTS> line select key, the LAST LEG CLASS 3 FAULTS page
comes on. This page shows each class 3 failure message that came on during the last flight
and shows:
•T
he time when the failure occurred,
•T
he ATA reference,
•T
he identity of the unserviceable LRU.
This page can show a maximum of two failures. If there are more failures, you must push
the next page key on the MCDU keyboard. If there are no class 3 failures found during the last
flight the message NO FAULT DETECTED is shown in the centre of the screen.
< LAST
LEG REPORT < PREVIOUS
LEGS REPORT
<LRU IDENT
<GND SCANNING
< TROUBLE
SHOOT DATA
<RETURN
CIDS1
CLASS3 FAULTS>
SYSTEM TESTS>
EPSU BAT>
CAP TEST
OP TESTS>
GROUND REPORT>
SYSTEM CONFIG>
OR
CIDS 1
LAST LEG REPORT 3 FAULTS
UTC ATA
NO FAULT DETECTED
CIDS 1
LAST LEG REPORT 3 FAULTS
1110 237317
DEU B (300RH1)
1415 237322
AIP 04 R (320RH14)
<RETURN
PRINT*
<RETURN
PRINT*
4. BITE
_
D. MCDU CIDS
VI. System tests
When you push the SYSTEM TESTS> line select key, the SYSTEM TEST menu page comes
on.
This page shows the subsequent legends:
•D
IR STATUS,
• INTERFACE + POWER-UP TEST,
• ILLUMINATION TEST,
•E
PSU SYS TEST,
•D
RAIN MAST SYS TEST.
< LAST
LEG REPORT < PREVIOUS
LEGS REPORT
<LRU IDENT
CIDS1
CLASS3 FAULTS>
<GND SCANNING
< TROUBLE
SHOOT DATA
<RETURN
SYSTEM TESTS>
EPSU BAT>
CAP TEST
OP TESTS>
GROUND REPORT>
SYSTEM CONFIG>
OR
CIDS X
SYSTEM TESTS
DIRX ACTIVE
INTERFACE+
<POWER-UP TEST (6MIN)
ILLUMINATION
<TEST
DRAINM
SYS TEST>
<EPSU SYS TEST
<RETURN
<EPSU SYS TEST
PRINT*
SYSTEM TEST PAGE (FOR ACTIVE DIRECTOR)
133
CIDS X
SYSTEM TESTS
DIRX PASS, DIR TEST ONLY
INTERFACE+
<POWER-UP TEST
DRAINMAST
ILLUMINATION
SYS TEST
<RETURN
PRINT*
SYSTEM TEST PAGE (FOR PASSIVE DIRECTOR)
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4. BITE
_
D. MCDU CIDS
VII. Power up test
SYSTEM TESTS: INTERFACE + POWER-UP TEST if active director
is selected
When you push the <INTERFACE + POWER-UP TEST line select key, the INTERFACE +
POWER-UP TEST page with the messages DIRx ACTIVE and TEST IN PROGRESS 6 MIN
comes on.
The CIDS does a power-up test of the CIDS components and starts the internal BITE
of the associated systems. It lasts 6 minutes. If there is a failure, the subsequent data about
this failure come on:
• The ACTIVE DIR,
• The ATA references,
• The identity of the unserviceable LRU,
• The class of the failures (1,2 or 3) with a prompt > (if applicable) to get access to the Trouble
Shooting Data (TSD) or to the submenus for the class 3 failures.
This page can show a maximum of two failures. If there are more failures you must push
the next page key on the MCDU keyboard. If there are no failures found during the test,
the message TEST OK is shown in the centre of the screen.
4. BITE
_
D. MCDU CIDS
CIDS1
SYSTEM TESTS
DIR1 ACTIVE
INTERFACE+AMU
<POWER-UP TEST (6MIN)
ILLUMINATION
<TEST
<EPSU SYS TEST
DRAINM
SYSTEST>
<RETURN
2
PRINT*
1
OR
CIDS1
INTERFACE+ POWER-UP TEST
DIR1 ACTIVE
CIDS1
INTERFACE+ POWER-UP TEST
DIR1 ACTIVE
TEST IN PROGRESS (6MIN)
ATA
322100
LGGIU1/2(5GA1/5GA2/
DIR1(101RH)
PRINT*
CLASSE
1
<RETURN
PRINT*
OR
CIDS1
INTERFACE+ POWER-UP TEST
DIR1 ACTIVE
CIDS1
INTERFACE+ POWER-UP TEST
DIR1 ACTIVE
TEST OK
ATA
237334
DIR1(101RH)
23/319
CAM (115RH)/FAP (120RH)
<RETURN
135
PRINT*
<RETURN
A320 Family - Enhanced CIDS - ref: ISI 23.73.00094 - Issue: September 2017
CLASSE
2>
1>
PRINT*
136
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4. BITE
_
D. MCDU CIDS
SYSTEM TEST: INTERFACE + POWER-UP TEST if passive director
is selected
When you push the <INTERFACE + POWER-UP TEST line select key, the INTERFACE +
POWER-UP TEST page with the messages DIRx PASS, DIR TEST ONLY and TEST
IN PROGRESS 30 S comes on.
The passive director tests only itself, checks all power related conditions, all FAP/CAM/DIR.
interlink and ARINC/ETHERNET items.
CIDS2
SYSTEM TESTS
DIR2 PASS, DIR TEST ONLY
INTERFACE+
<POWER-UP TEST
ILLUMINATION
TEST
EPSU SYS TEST
<RETURN
CIDS2
INTERFACE+ POWER-UP TEST
DIR2 PASS, DIR TEST ONLY
TEST IN PROGRESS 30s
PRINT*
CIDS2
INTERFACE+ POWER-UP TEST
DIR2 PASS, DIR TEST ONLY
TEST OK
<RETURN
PRINT*
DRAINM
SYS TEST
PRINT*
4. BITE
_
D. MCDU CIDS
VIII. Operational tests
When you push the OP TEST> line select key, the OP TEST menu page comes on.
The page shows the subsequent legends:
•<
LOUDSPEAKER ACTIVATION
<READING LT + ACP + PAX CALL + SIGN LAMPS ACTIVATION
(a) When you push the <LOUDSPEAKER ACTIVATION line select key, all CIDS loudspeakers
are supplied with a test tone until you push the <RETURN line select key.
(b) When you push the LAMPS ACTIVATION line select key, all lamps in the READING LTs,
ACPs, PAX CALLs and SIGNS are illuminated until you push the <RETURN line select key.
Note:
• There is no CAM relation, all DEU outputs are activated.
• After the test (when you push the <RETURN line select key) the system performs a reset,
the communication between the MCDU and CIDS stops.
< LAST
LEG REPORT < PREVIOUS
LEGS REPORT
<LRU IDENT
<GND SCANNING
< TROUBLE
SHOOT DATA
<RETURN
SYSTEM TESTS>
EPSU BAT>
CAP TEST
OP TESTS>
GROUND REPORT>
SYSTEM CONFIG>
CIDS1
OP TEST
SYSTEM RESET AFTER TEST
<LOUDSPEAKER ACTIVATION)
READING LT + ACP +
PAX CALL + SIGN
<LAMPS ACTIVATION
<RETURN
PRINT*
CIDS1
OP TEST OF LOUDSPEAKER,
NO CABIN ASSIGNMENT
MODULE RELATION
CIDS1
OP TEST OF LAMPS,
NO CABIN ASSIGNMENT
MODULE RELATION
LOUDSPEAKER
ACTIVATED
READING LT + ACP +
PAX CALL + SIGN
LAMPS ACTIVATED
<RETURN
137
CIDS1
CLASS3 FAULTS>
PRINT*
<RETURN
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PRINT*
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4. BITE
_
D. MCDU CIDS
IX. Troubleshooting Data
When you push the <TROUBLE SHOOT DATA line select key, the TROUBLE SHOOTING
DATA page comes on. This page shows:
•T
he date and the time of the message,
•S
napshot data at the moment of the fault (e.g. aircraft configuration etc.) shown
in hexadecimal code.
Note:
• The TROUBLESHOOTING DATA Report contains data of system faults which occurred
in flight.
• Refer to TSD Decoder details
< LAST
LEG REPORT < PREVIOUS
LEGS REPORT
<LRU IDENT
<GND SCANNING
< TROUBLE
SHOOT DATA
<RETURN
DATA UTC
CIDS1
CLASS3 FAULTS>
SYSTEM TESTS>
EPSU BAT>
CAP TEST
OP TESTS>
GROUND REPORT>
SYSTEM CONFIG>
CIDS1
TROUBLE SHOOTING DATA
NOV14 0800
HHHH HHHH HHHH HHHH HHHH
HHHH HHHH HHHH HHHH HHHH
<RETURN
PRINT*
TROUBLE SHOOTING PAGE EXAMPLE
NOTE: HHHH FOR CODED TROUBLE SHOOTING DATA
4. BITE
_
D. MCDU CIDS
X. Ground Scanning
When you push <GROUND SCANNING line select key, the GROUND SCANNING page
comes on. The GND SCANNING does an analysis of the CIDS status at this time and in case
of a failure all existing internal and external failures are shown.
This page shows:
•T
he date and the time at which the failure occurred,
•T
he ATA reference,
•T
he identity of the unserviceable LRU,
•T
he class of the failure (1,2 or 3) with a prompt > to get access to the trouble shooting data.
This page can show a maximum of two failures. If there are more failures, you have to
push the next page key on the MCDU keyboard. Each failure which is detected during
the monitoring mode is written at the end of the report. The page counter is updated
automatically. If there is no fault detected, the message NO FAULT DETECTED is shown.
When you push the <RETURN line select key, the memory of the GND SCANNING is reset.
After activating the GND SCANNING mode it is necessary to wait approx. 3 min. to make
sure that all failures are detected.
Ground scanning is displaying the fault currently observed by the continuous BITE of the
CIDS, whereas Interface & Power-up test perform a power-cycle and displays the results
of all intensive power-up test of the CIDS. Ground scanning may be particularly useful
for transient faults cleared by a power-cycle.
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4. BITE
_
D. MCDU CIDS
GROUND SCANNING
CIDS1
NOV10
IN PROGRESS 180s
< LAST
LEG REPORT < PREVIOUS
LEGS REPORT
<LRU IDENT
CIDS1
CLASS3 FAULTS>
<GND SCANNING
<RETURN
PRINT*
< TROUBLE
SHOOT DATA
<RETURN
SYSTEM TESTS>
EPSU BAT>
CAP TEST
OP TESTS>
GROUND REPORT>
SYSTEM CONFIG>
OR
GROUND SCANNING
UTC ATA
CIDS1
NOV10
CLASS
NO FAULT DETECTED
<RETURN
PRINT*
GROUND SCANNING
UTC ATA
IN PROGRESS 1546
1542 237346
DEU A (200RH01)
CIDS1
NOV10
CLASS
<RETURN
1>
PRINT*
GROUND SCANNING EXAMPLE
DATA UTC
CIDS1
GROUND SCANNING
NOV14 1542
J304
HHHH HHHH HHHH HHHH HHHH
HHHH HHHH HHHH HHHH HHHH
<RETURN
NOTE: HHHH FOR CODED TROUBLE SHOOTING DATA
PRINT*
4. BITE
_
D. MCDU CIDS
XI. Ground Report
The characteristics of this page are identical to those of the LAST LEG REPORT. This page
shows the internal failure message that come on when the aircraft is in ground configuration.
Failures detected during the last flight, which are still valid, are not shown in the GROUND
REPORT.
< LAST
LEG REPORT < PREVIOUS
LEGS REPORT
<LRU IDENT
<GND SCANNING
< TROUBLE
SHOOT DATA
<RETURN
CIDS1
CLASS3 FAULTS>
SYSTEM TESTS>
EPSU BAT>
CAP TEST
OP TESTS>
GROUND REPORT>
SYSTEM CONFIG>
OR
GROUND REPORT
DATE UTC
CIDS1
CIDS1
GROUND REPORT UTC ATA
NO FAULT DETECTED
<RETURN
12h0 23/300
CAM(115RH)
DIR1(101RH)
PRINT*
<RETURN
DATE UTC
SEP 23
CLASS
1>
PRINT*
CIDS1
GROUND REPORT
NOV23 1250
MANDATORY LAYOUT
HHHH HHHH HHHH HHHH HHHH
<RETURN
NOTE: HHHH FOR CODED TROUBLE SHOOTING DATA
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PRINT*
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4. BITE
_
D. MCDU CIDS
XII. System Config
The SYSTEM CONFIGURATION page shows:
•T
he current date,
•T
he UTC,
•T
he aircraft ident,
•T
he ACTIVE DIR,
•T
he CAM P/N,
•T
he ACTIVE LAYOUT,
•T
he LAST CAM MODIFICATION,
•<
LSP VOLUME REPORT.
< LAST
LEG REPORT < PREVIOUS
LEGS REPORT
<LRU IDENT
When you push the <LSP VOLUME REPORT
line key the system shows pages where the
CAM defined loudspeaker volume is shown.
CIDS1
CLASS3 FAULTS>
SYSTEM TESTS>
EPSU BAT>
CAP TEST
OP TESTS>
GROUND REPORT>
SYSTEM CONFIG>
<GND SCANNING
< TROUBLE
SHOOT DATA
<RETURN
CIDS1
SYSTEM CONFIGURATION
DATE: FEB12. UTC: 1205
A/C: DA-ABCD
<LSP VOLUME REPORT
ACTIVE DIR: 1
CAM P/N: -------------------ACTIVE LAYOUT: CAM 2M
PROD/CHANGE: 2001 OCT 13
iiiiiiiiiiiiiiiiiiiiiiiiiiiii
iiiiiiiiiiiiiiiiiiiiiiiiiiiii
iiiiiiiiiiiiiiiiiiiiiiiiiiiii
<RETURN
PRINT*
OR
1
2
CIDS1
1/12
LSP VOLUM REPORT
PA VOL IN CABIN AREA
SR 01-03
SR 04-06
SR 07-11
SR 12-15
<RETURN
+2dB
0dB
-2dB
+4dB
PRINT*
NOTE: iiiii FOR INFO TEXT (LAYOUT HEADER)
1 OR 2 RELATED TO LAYOUT OF LEVEL ADJUSTEMENT PAGE ON FAP
CIDS1
1/12
LSP VOLUM REPORT
PA VOL IN CABIN AREA
FIRST CLASS
BUSINESS CLASS
TOURIST CLASS
<RETURN
+2dB
0dB
-2dB
PRINT*
4. BITE
_
E. MCDU CIDS Simulator on the FAP
A simulation of the MCDU is available on the FAP. However, it gives only access to the active
DIR (no SDF, no passive DIR and no LAV page for Vacuum Status) and it is not accessible
in Flight. The page is inaccessible when the MCDU is being used, and reciprocally. The page
is protected by a password (cf FAP Passwords page).
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4. BITE
_
F. MCDU SDF
I. Access
II. Last Leg Report
III. Previous Legs Report
IV. LRU Identification
V. Class 3 Faults
VI. System Tests
VII. Ground Scanning
VIII. Smoke Warning Test
IX. TSD & Smoke Warning Report
4. BITE
_
F. MCDU SDF
I. Access
To access to the SYSTEM REPORT/TEST/FIRE PROT page, apply the following steps:
• Push the MCDU MENU mode key
• Push the line key adjacent to the CFDS indication.
• Push the line key adjacent to the SYSTEM REPORT/TEST indication.
• Push the line key adjacent to the FIRE PROT indication.
<FDU 1
SYSTEM REPORT/TEST
FIRE PROT
<FDU 2
<FDU APU
<SMOKE
<RETURN
Note:
• The active SDF board only can be accessed through the MCDU, which usually means
SDF 1. To access SDF 2 MCDU menu, SDF 1 needs to be deactivated.
• The SDF System name on that page varies with CFDIU standards (SDCU or SMOKE).
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4. BITE
_
F. MCDU SDF
Main Menu
This page shows the subsequent selectable pages:
• <LAST LEG REPORT,
• <PREVIOUS LEGS REPORT,
• <LRU IDENT,
• <GND SCANNING,
• <TROUBLE SHOOT DATA,
• <CLASS 3 FAULTS,
• <SYSTEM TESTS,
• <SMOKE WARN TEST,
• <GROUND REPORT,
• <SPECIFIC DATA (Smoke Warning Report)
• <RETURN (when you push this line select key you go back to the Main page).
CIDS-SDFx
SDCU FUNCTION
IS INTEGRATED IN
CIDS DIRECTORS
101RH & 102RH
CALLED CIDS-SDFx
<RETURN
1/2
CIDS-SDFX
2/2
< LAST
CLASS3 FAULTS>
LEG REPORT < PREVIOUS
SYSTEM TESTS>
LEGS REPORT
<LRU IDENT
SMOKE WARN>
TEST
<GND SCANNING
GROUND REPORT>
< TROUBLE
SPECIFIC DATA>
SHOOT DATA
<RETURN
RETURN>
4. BITE
_
F. MCDU SDF
II. Last leg report
When you push the <LAST LEG REPORT line select key, the LAST LEG REPORT page
comes on. This page shows the failure messages that came on during the last flight and
it shows the subsequent data:
•T
he data of the last flight,
•T
he time when the failure occurred,
•T
he ATA reference,
•T
he identity of the unserviceable LRU,
•T
he class of the failure (1 or 2).
This page can show a maximum of two failures. If there are more failures, you must push
the next page key on the MCDU keyboard. If there are no failures found during the last flight,
the message NO FAULT DETECTED is shown in the center of the screen.
CIDS-SDFx
LAST LEG REPORT DEC 17
NO FAULT DETECTED
<RETURN
147
PRINT*
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4. BITE
_
F. MCDU SDF
III. Previous Legs Report
When you push the <PREVIOUS LEGS REPORT line select key, the PREVIOUS LEGS
REPORT page comes on.
This page is a sum of the LAST LEG REPORTS and shows the failure message that came on
during the 63 flights before.
This page shows the subsequent data:
•T
he aircraft identification.
•T
he Leg number (1-63),
•T
he date of the flight when the failure occurred,
•T
he time when the failure occurred,
•T
he ATA reference,
•T
he class of the failure (1 or 2),
•T
he identity of the unserviceable LRU.
This page can show a maximum of two failures. If there are more failures, you must push
the next page key on the MCDU keyboard. If there are no failures found during the last
63 flights, the message NO FAULT DETECTED is shown in the center of the screen.
CIDS-SDFx
2/7
PREVIOUS LEGS REPORT
XY-PONT
LEG DATE UTC
ATA CLASS
02 SEP18 1015 261515 2
SMK DET AVNCS (1WA)
05 SEP15 1115 261517 1
SMK DET LAV LOCATION 11
<RETURN
PRINT*
>
4. BITE
_
F. MCDU SDF
IV. LRU Identification
When you push the <LRU IDENT line select key, the LRU IDENTIFICATION page comes on.
This page shows the identity of all the electronic LRUs which can report their part number
and serial number.
CIDS1-SDFx
LRU IDENTIFICATION
1/5
CIDS DIR1
P/N: yyyyyyyyyyyy
S/N: yyyyyyyyyyyy
S/N-P/N: yyyyyyyyyyyy
SMK DET 1 WH
P/N: yyyyyyy-yy
S/N: yyyyyy
<RETURN
CIDS1-SDFx
LRU IDENTIFICATION
PRINT*
2/5
SMK DET 2WH
P/N : yyyyyyy-yy
S/N : yyyyyy
SMK DET 3 WH
P/N: yyyyyyy-yy
S/N: yyyyyy
<RETURN
149
PRINT*
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4. BITE
_
F. MCDU SDF
V. Class 3 Faults
When you push the CLASS 3 FAULTS> line select key, the LAST LEG CLASS 3 FAULTS page
comes on. This page shows each class 3 failure message that came on during the last flight.
CIDS1-SDFx
UTC ATA
LAST LEG CLASS FAULTS
1410 773200
N1 BRG VIB SENSOR
(4002EV1)/EIVMU1(1KS1)
1415 772500
RCC1 (400EVA)/EIVMU1(1KS1)
<RETURN
PRINT*
4. BITE
_
F. MCDU SDF
VI. System tests
The system provides a system test covering all LRUs connected to the system and signals
received by the system (i.e. the computer housing the BITE and all its own peripherals such
as sensors, ARINC buses from peripheral computers, etc...).
This test will:
• restart the Power Up test (or a test fully equivalent)
• cover the most possible of input and output signals
SDF power-up time lasts up to 4 min.
SDF system test is equivalent to the CIDS Interface & Power-up test, but for SDF board.
CIDS1-SDFx
SYSTEM TEST
<START TEST
<RETURN
151
PRINT*
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4. BITE
_
F. MCDU SDF
VII. Ground Scanning
When you push <GROUND SCANNING line select key, the GROUND SCANNING page
comes on. The GND SCANNING does an analysis of the SDF status at this time and in case
of a failure all existing internal and external failures are shown.
This page shows:
•T
he date and the time at which the failure occurred,
•T
he ATA reference,
•T
he identity of the unserviceable LRU,
•T
he class of the failure (1,2 or 3) with a prompt > to get access to the trouble shooting data.
This page can show a maximum of two failures. If there are more failures, you have to
push the next page key on the MCDU keyboard. Each failure which is detected during
the monitoring mode is written at the end of the report. The page counter is updated
automatically. If there is no fault detected, the message NO FAULT DETECTED is shown.
When you push the <RETURN line select key, the memory of the GND SCANNING is reset.
After activating the GND SCANNING mode it is necessary to wait approx. 3 min. to make
sure that all failures are detected.
4. BITE
_
F. MCDU SDF
VIII. Smoke Warning Test
If the key “SMOKE WARNING TESTS” is pressed (in the menu page) a Test Menu come
into view:
Note:
Page layout depends on aircraft configuration (CAM programmable).
CIDS-SDFx
1/1
SMOKE WARNING TESTS
<FWD
AFT>
LDCC TEST
LDCC TEST
<AVIONICS
AFT AVNCS
TEST
TEST
<LAVATORY
TESTS
<xxxxxxxxxx
TESTS
<xxxxxxxxxx
TESTS
<RETURN
PRINT*
>
If selected, the active CIDS-SDF channel (only) performs a test of the selected area (FWD
or AFT LDCC, Avionics, LAV…) smoke detectors.
Test request
CIDS-SDF
CAN Bus (+ DEU-B for LAV)
Smoke Detectors
Test results
If at least one smoke detector per cavity is operative and in normal operation, the CIDS-SDF
will set the corresponding ARINC 429 outputs to the FWC and set the corresponding discrete
smoke output(s) to the smoke warning lamps on the overhead panel.
If all smoke detectors of the same cavity are failed the corresponding outputs will not be set
and the according maintenance message will be displayed on the result page and be stored
in the BITE of the CIDS-SDF.
The test will be finished when either all respective indications are confirmed or the MCDU line
key adjacent to “RETURN” is selected.
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4. BITE
_
F. MCDU SDF
IX. TSD & Smoke Warning Report
Troubleshooting Data
When you push the <TROUBLE SHOOT DATA line select key, the TROUBLESHOOTING
DATA page comes on. This page shows:
•T
he date and the time of the message in clear language,
•S
napshot data at the moment of the fault (e.g. aircraft configuration etc.) shown
in hexadecimal code.
Note:
The TROUBLESHOOTING DATA Report contains data of system faults which occurred in
flight.
Smoke Warnings Report
When the key “SPECIFIC DATA“ is pressed (in Main Menu) the System will transmit
the subsequent page:
CIDS-SDFx
SPECIFIC DATA
INFORMATION :
THE SMOKE WARNINGS
REPORT INDICATES SMOKE
DETECTORS WICH HAVE
LED TO A SMOKE WARNING
<SMOKE WARNINGS REPORT
<RETURN
PRINT*
The “SMOKE WARNINGS REPORT” will display the smoke event reported by related Smoke
Detectors. It is particularly helpful to investigate SMOKE Warning events, and must be
retrieved at that occasion.
5. Dispatch and
Troubleshooting Advices
A.
B.
C.
D.
E.
F.
Troubleshooting Philosophy & Recommendations
Common Maintenance Procedures
MEL
Smoke Event
CIDS Event
CIDS Deviations
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5. Dispatch and Troubleshooting Advices
_
A. Troubleshooting philosophy
Known
deviation?
Event
CIDS Interface
& Power-Up test
YES
CIDS
or
LAV
Smoke
YES
Refer to associated
recommendations
(ISI, TFU, see Appendix)
NO
Smoke
Type?
SDF test
Cleared?
NO
Follow TSM
Task as per
fault messages
observed.
YES
Cleared?
NO
Deep troubleshooting required
»» investigate CIDS BITE via
MCDU:
• Last Leg report
• Previous Legs report
• TSD
• Class 3 fault
Note: allows to find TSM tasks
associated to cabin effects (PA,
Interphone, Handset, FAP, PSU,
ACP, AIP, cockpit interactions, …)
Note:
See next page for TSD Decoder
detailst
5. Dispatch and Troubleshooting Advices
_
A. Troubleshooting philosophy
A CIDS Unit should be replaced only when resulting from a TSM task or as per Airbus advice.
As Maintenance Status, the “SMOKE”, “CIDS1” and “CIDS2” messages do not prevent
dispatch, dispatch is possible under MEL.
For each Operational Interruption reported to Airbus, Airbus needs the following info in
the OI report:
•S
ymptoms and fault messages (+date & time)
•R
eference of TSM and AMM tasks performed
•P
/N and S/N in the case of equipment removal or swap
Thereby, Airbus will be able to understand the following links:
Symptoms
Maintenance
Action
Removed
Equipment
Repair
Findings
Improvements
Identification
TSD Decoder: In order to help the airlines to carry out Troubleshooting Data Decoding
and simplify the analysis of complex hardware failures, a Troubleshooting Data Decoder
tool is available FOC, as described in ISI article 23.73.00008.
Note:
A CIDS Interface & Power Up Test should be preferred to a CIDS Reset. It lasts the same
duration as a Reset and it provides fault messages to be investigated if the issue
is confirmed. Though, if a CIDS Reset is performed, ensure to follow the C/B sequence
as detailed in AMM and wait 10sec before pushing back the C/B.
157
RESET
BITE Test
DIR reboot times
4 min
6 min
Access
Multiple C/B
Specific C/B Order
MCDU
Fault Troubleshooting
NIL help is not spurius
Confirmed fault(s)
A/C status
Fault not identified
Appropriate
T/S identified
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5. Dispatch and Troubleshooting Advices
_
B. Common Maintenance Procedures
Procedure
AMM TASK
Energize the CIDS
23-73-00-861-001-A
De-energize the CIDS
23-73-00-862-001-A
CIDS Interface and Power-Up test
23-73-00-740-005-B
Ground Scanning
23-73-00-740-012-A
Removal of the CIDS Director
23-73-34-000-001-A
Installation of the CIDS Director
23-73-34-400-001-A
Removal of the Handset/Cradle
23-73-44-000-001-A
Installation of the Handset/Cradle
23-73-44-400-001-A
OBRM Download procedure
23-73-00-869-001-A
Replacement of the Cabin Assignment Module
23-73-19-960-001-A
Deactivation of a CIDS-DIR
23-73-00-040-001-A
Reactivation of a CIDS-DIR
23-73-00-440-001-A
Operational test of the PA system
Operational test of the Cabin and Flight Crew Interphone System
23-73-00-710-005-A
23-73-00-710-022-A*
23-73-00-710-003-A
23-73-00-710-021-A*
Cabin Layout Programing
23-73-00 PB001CONF01
SDF BITE System Test
26-10-00-740-801-A
Operational Check of Cargo-Compartment Smoke-Detection by PTT
26-16-00-710-001-A
*depends on aircraft configuration
5. Dispatch and Troubleshooting Advices
_
C. MEL
I. Repair Interval
II. Maintenance Status CIDS
III. Interphone
IV. Handset
V. PA/Loudspeaker/Pax Call
VI. DEUs A&B
VII. FAP unit
VIII. FAP functions, PRAM & CAM
IX. ACP, AIP, AAP
X. Cabin Signs
XI. Maintenance Status SDF
XII. Lavatory Smoke Detection
XIII. FWD Cargo Smoke Detector
XIV. AFT & Bulk Cargo Smoke Detector
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5. Dispatch and Troubleshooting Advices
_
C. MEL
I. Repair Interval
Reference doc: MMEL.
E/WD message
Description
No standard interval is specified. Items in this category shall
be repaired within the time interval specified
in the «Remarks and Exceptions» column of the operator’s
approved MEL.
Repair Interval A
Repair Interval B
Repair Interval C
Repair Interval D
Whenever the time interval is listed as flight days, the time
interval begins on the flight day following the day of
discovery. Where a time period is specified in number
of flights or flight hours, it shall start at the beginning of
the first flight following the discovery of the failure.
Items in this category shall be rectified within
three consecutive calendar days, excluding the day
of discovery.
For example, if it were recorded at 13:00 on January 26th, the
3-day interval begins at 00:01 on January 27th and ends at
23:59 on January 29th.
Items in this category shall be rectified within
ten consecutive calendar days, excluding the day
of discovery.
For example, if it were recorded at 13:00 on January 26th,
the 10-day interval begins at 00:01 on January 27th
and ends at 23:59 on February 5th
Items in this category shall be rectified within
one hundred and twenty consecutive calendar days, excluding the day of discovery.
5. Dispatch and Troubleshooting Advices
_
C. MEL
II. Maintenance Status CIDS
CIDS function
Ref: 23-73-01-01A
Cabin Intercommunication Data System Function
Repair interval:-
Nbr installed: 1
Nbr required: 1
Placard: No
The CIDS function must be operative.
Notes:
1. Failure of a single CIDS director is indicated by a MAINTENANCE messageon the STATUS SD page.
Refer to Item 23-00-01 CIDS 1(2) MAINTENANCE Message
2. In the case of disturbance of the CIDS function, the deactivationof the affected CIDS director may
recover normal operation of the CIDS function.
Refer to AMM TASK 23-73-00-040-001
Maintenance Status
Ref: 23-00-01A
CIDS 1(2) MAINTENANCE Message
Repair interval: C
Nbr installed: -
Nbr required: -
CIDS 1(2) MAINTENANCE message may be displayed on the STATUS SD page.
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Placard: No
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5. Dispatch and Troubleshooting Advices
_
C. MEL
III. Interphone
CIDS function
Ref: 23-40-02A
Flight Crew Interphone System
Repair interval:-
Nbr installed: 1
Nbr required: 1
Placard: No
Must be operative for each person on cockpit duty
Notes:
1. In the case of partial failure of the passenger address system, refer to the item(s) of the affected
system(s)
2. Total failure of the passenger address system (indicated by the COM CIDS 1+2 FAULT alert displayed on
the EWD) is not permitted.
Ref: 23-40-03A
Flight Crew to Ground Communication System
Repair interval: C
Nbr installed: 1
Nbr required: 0
Placard: No
May be inoperative
Notes:
1. In the case of partial failure of the passenger address system, refer to the item(s) of the affected
system(s)
2. Total failure of the passenger address system (indicated by the COM CIDS 1+2 FAULT alert displayed on
the EWD) is not permitted.
Ref: 23-40-04A
Service Interphone Jack
Repair interval:-
Nbr installed: 8
Nbr required: 0
Placard: No
One or more may be inoperative
Notes:
1. In the case of partial failure of the passenger address system, refer to the item(s)
of the affected system(s)
2. Total failure of the passenger address system (indicated by the COM CIDS 1+2 FAULT alert displayed on
the EWD) is not permitted
5. Dispatch and Troubleshooting Advices
_
C. MEL
IV. Handsets
Cockpit Handset
Ref: 23-31-01A
Cockpit Handset
Repair interval: C
Nbr installed: 1
Nbr required: 0
Placard: Yes
May be inoperative provided that the cockpit audio control panel (ACP) is used for the communication
between the cockpit and the cabin.
Cabin Handset
Ref: 23-73-06-02A
Cabin Handset
Repair interval: C
Nbr installed: -
Nbr required: -
Placard: No
One or more may be inoperative provided that one handset is operative at each pair of floor level exit doors.
Ref: 23-73-06-03A
Cabin Handset Key - Passenger address and Cabin
to cockpit interphone operative
Repair interval: C
Nbr installed: -
Nbr required: -
Placard: Yes
One or more may be inoperative provided that:
1. Passenger address from the affected handset is operative, and
2. Cabin to cockpit interphone from affected handset is operative.
Ref: 23-73-06-03B
Cabin Handset Key - Affected handset considered inoperative
Repair interval: C
Nbr installed: -
Nbr required: -
Placard: Yes
One or more may be inoperative provided that the affected handset is considered inoperative.
Note:
Refer as well to Service Interphone and PA, Interphone & Handset advices.
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5. Dispatch and Troubleshooting Advices
_
C. MEL
V. PA/Loudspeaker/Pax Call
Passenger Address System
Ref: 23-31-01A
Passenger Address System
Repair interval: -
Nbr installed: 1
Nbr required: 1
Placard: No
Must be operative
Notes:
1. In the case of partial failure of the passenger address system, refer to the item(s)
of the affected system(s)
2. Total failure of the passenger address system (indicated by the COM CIDS 1+2 FAULT alert displayed on
the EWD) is not permitted.
Passenger Call
Ref: 23-73-04-01A
Cabin Handset
Repair interval: D
Nbr installed: -
Nbr required: 0
Placard: No
Nbr required: -
Placard: No
One or more may be inoperative.
Loudspeakers
Ref: 23-73-05-01A
Cabin Handset
Repair interval: C
Nbr installed: -
One or more may be inoperative provided that no seat is occupied from which a passenger cannot hear a
passenger announcement.
Ref: 23-73-05-02A
Cabin Handset
Repair interval: C
Nbr installed: -
One or more may be inoperative.
Note:
Refer to PSU troubleshooting advises.
Nbr required: 0
Placard: No
5. Dispatch and Troubleshooting Advices
_
C. MEL
VI. DEU
DEU-A
Ref: 23-73-02-01A
Cabin DEU-A - Affected seat occupied
Repair interval: C
Nbr installed: -
Nbr required: -
Placard: No
One or more DEU A may be inoperative and affected passenger seat may be occupied provided that:
1. The passenger announcement can be heard throughout the cabin during
2. The passenger address system is used to alert the passengers when "Return to Seat / Fasten Seat
Belt / No Smoking" signs are requested.
Ref: 23-73-02-01B
Cabin DEU-A - Affected seat not occupied
Repair interval: C
Nbr installed: -
Nbr required: -
Placard: No
One or more may be inoperative provided that the affected seats are blocked and placarded inoperative.
Ref: 23-73-02-02A
Lavatory DEU A
Repair interval: C
Nbr installed: -
Nbr required: 0
Placard: No
One or more may be inoperative provided that the affected lavatory is closed and placarded inoperative.
DEU-B
Ref: 23-73-03-01B
Cabin DEU-B
Repair interval: C
Nbr installed: -
Nbr required: 2
Placard: No
One or more DEU B may be inoperative provided that:
1. One DEU B and the associated handset are operative at each pair of floor level exit doors, and
2. The slide bottle pressure and door bottle pressure associated with each affected DEU B are checked on
the associated direct reading pressure gauge before the first flight of each day, and
3. The associated lavatory fire extinguisher system is checked operative, and
4. The absence of smoke in the affected lavatory is periodically checked.
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5. Dispatch and Troubleshooting Advices
_
C. MEL
VII. FAP unit
FAP unit
Ref: 23-74-01A
Forward Attendant Panel
Repair interval: C
Nbr installed: 1
Nbr required: 0
Placard: Yes
May be inoperative provided that the safety related messages on the FAP are considered inoperative.
Refer to Item 52-10-06 DOOR PRESS LOW/CHECK DOOR PRESSURE
Message on the PTP/FAP (If Installed), and
Refer to Item 25-62-06 Passenger Door Slide Pressure Message on the PTP/FAP (If Installed), and
Refer to Item 25-62-07 Overwing Emergency Exit Slide Pressure Message on the PTP/FAP (If Installed)
General Information:
The cabin lighting may be dimmed through the Additional Attendant Panel (AAP) (If available).
Ref: 23-74-02A
EMER pushbutton on the Hardkey FAP Sub-panel
Repair interval: -
Nbr installed: 1
Nbr required: 1
Placard: No
Must be operative
Ref: 23-74-03A
Other Controls on the Hardkey FAP Sub-panel
Repair interval: D
Nbr installed: -
One or more may be inoperative.
Nbr required: 0
Placard: No
5. Dispatch and Troubleshooting Advices
_
C. MEL
VIII. FAP functions/PRAM/CAM
FAP functions
Ref: 25-62-06A
Passenger Door CHECK SLIDE PRESSURE
Message on Flight Attendant Panel (FAP)
Repair interval: D
Nbr installed: -
Nbr required: 0
Placard: No
One or more messages may be displayed provided that the slide bottle pressure is checked before
the first MMEL dispatch and then every 600 flight hours or every 4 months, whichever occurs first.
Refer to AMM 25-62-00-040-009
Ref: 25-62-07A
Overwing Emergency Exit CHECK SLIDE PRESSURE
Message on FAP
Repair interval: D
Nbr installed: -
Nbr required: 0
Placard: No
One or both messages may be displayed provided that the associated slide bottle pressure is checked before the first flight of each day.
Refer to AMM 25-62-00-040-005
Ref: 52-10-06A
CHECK DOOR PRESSURE Message on the FAP
Repair interval: D
Nbr installed: -
Nbr required: 0
Placard: No
One or more messages may be displayed provided that the door bottle pressure is checked
on the associated bottle pressure gauge before the first MMEL dispatch and then every 8 days.
Refer to AMM 52-00-00-040-003
PRAM & CAM
Ref: 23-73-07-01A
Prerecorded Announcement and Music Reproducer (PRAM)
Repair interval: D
Nbr installed: 1
Nbr required: 0
Placard: No
May be inoperative.
Ref: 23-73-08-01A
Cabin Assignment Module (CAM)
Repair interval: D
Nbr installed: 1
Nbr required: 0
May be inoperative or missing.
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Placard: No
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5. Dispatch and Troubleshooting Advices
_
C. MEL
IX. ACP, AIP & AAP
ACP, AIP & AAP
Ref: 23-74-09A
Area Call Panel
Repair interval: D
Nbr installed: -
Nbr required: 0
Placard: Yes
One or more may be inoperative.
Ref: 23-74-10A
Attendant Indication Panel
Repair interval: D
Nbr installed: -
Nbr required: 0
Placard: Yes
One or more may be inoperative.
Ref: 23-74-11A
Additional Attendant Panel
Repair interval: D
Nbr installed: -
One or more may be inoperative.
Nbr required: 0
Placard: Yes
5. Dispatch and Troubleshooting Advices
_
C. MEL
X. Cabin Signs
Cabin Signs
Ref: 33-20-02A
Cabin Signs (No Smoking/No Electronic Devices/Fasten Seat Belt/
Return to Seat) - Passenger seat occupied
Repair interval: C
Nbr installed: -
Nbr required: 0
Placard: Yes
One or more may be inoperative and the affected passenger seat may be occupied provided that:
1. The passenger address system is operative, and can be heard throughout the cabin during
the flight, and
2. The passenger address system is used to alert the passengers when return to seat is requested,
seat belts should be fastened and smoking is prohibited.
Ref: 33-20-02B
Cabin Signs (No Smoking/No Electronic Devices/Fasten Seat Belt/
Return to Seat) - Passenger seat not occupied
Repair interval: C
Nbr installed: -
Nbr required: 0
Placard: Yes
One or more “No Smoking/No Electronic Devices/Fasten Seat Belt” sign may be inoperative provided that:
1. No passenger seat is occupied from which a passenger cannot see a readily legible “No smoking/No
Electronic Devices/Fasten Seat Belt” sign, and
2. The affected seat is blocked and placarded inoperative.
Refer to AMM 33-20-00-040-001
Note:
MMEL items 33-20-02x are applicable to both PAX seats and Attendant seats.
Ref: 33-20-03A
Lavatory Sign (Return to seat)
Repair interval: C
Nbr installed: -
Nbr required: 0
Placard: Yes
One or more may be inoperative and the affected lavatory may be used provided that:
1. The passenger address system is checked operative in the affected lavatory, and
2. The passenger address system is used to alert the occupant to return to his seat.
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5. Dispatch and Troubleshooting Advices
_
C. MEL
XI. Maintenance Status SDF
SDF function
Ref: 23-73-10-01A
Smoke Detection Function (CIDS-SDF)
Repair interval: C
Nbr installed: 1
Nbr required: 0
Placard: No
May be inoperative provided that:
1. The cargo compartments are empty or do not contain flammable or combustible materials, and
2. The lavatory smoke detection system is considered inoperative.
Refer to Item 26-17-01 Lavatory Smoke Detection System
Note:
Failure of a single CIDS-SDF channel is indicated by a MAINTENANCE message
on the STATUS SD page.
Refer to Item 26-00-01 SDCU/SMOKE MAINTENANCE Message
Ref: 23-73-10-01B
Smoke Detection Function (CIDS-SDF)
Repair interval: C
Nbr installed: 1
Nbr required: 0
Placard: No
May be inoperative provided that the restrictions concerning lavatory smoke detection system and cargo
smoke detection system are applied.
Refer to Item 26-17-01 Lavatory Smoke Detection System, and
Refer to Item 26-16-01 Smoke Detector in the FWD Cargo Compartment
(if FWD cargo compartment smoke detection system installed) and
Refer to Item 26-16-02 Smoke Detector in the AFT and the BULK Cargo Compartments
(if AFT cargo compartment smoke detection system installed).
Note:
Failure of a single CIDS-SDF channel is indicated by a MAINTENANCE message
on the STATUS SD page.
Refer to Item 26-00-01 SDCU/SMOKE MAINTENANCE Message
Maintenance Status
Ref: 26-00-01A
Smoke Detection Function (CIDS-SDF)
Repair interval: C
Nbr installed: -
Nbr required: -
SMOKE MAINTENANCE message may be displayed on the STATUS SD page.
Placard: No
5. Dispatch and Troubleshooting Advices
_
C. MEL
XII. Lavatory Smoke Detection
Note:
The lavatory smoke detection function is part of CIDS Smoke Detection Function (CIDS-SDF).
Refer to Item 23-73-10-01 Smoke Detection Function (CIDS-SDF)
Ref: 26-17-01A
Associated lavatory fire extinguishing system operative
Repair interval: C
Nbr installed: -
Nbr required: 0
Placard: No
One or more may be inoperative provided that:
1. The associated lavatory fire extinguishing system is operative, and
2. A procedure is used to periodically check absence of smoke in the associated lavatory.
Ref: 26-17-01B
Associated lavatory not used
Repair interval: C
Nbr installed: -
Nbr required: 0
Placard: No
One or more may be inoperative provided that:
1. The associated lavatory waste receptacle is empty, and
2. The associated lavatory door is locked closed and placarded inoperative, and
3. The lavatory is not used for storage or for any other purpose, and
4. A procedure is used to periodically check the absence of smoke in the associated lavatory.
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5. Dispatch and Troubleshooting Advices
_
C. MEL
XIII. Cargo S/D
Notes:
1. The cargo smoke detection function is part of the CIDS Smoke Detection Function
(CIDS-SDF). Refer to Item 23-73-10-01 Smoke Detection Function (CIDS-SDF)
2. Failure of a single detector in the cavity is indicated by a MAINTENANCE message
on the STATUS SD page. Refer to Item 26-00-01 SDCU/SMOKE MAINTENANCE Message
3. Depending on applicable regulation, smoke detection system may be required
for dispatch.
Ref: 26-16-01A
FWD Cargo S/D - Empty FWD cargo compartment
Repair interval: D
Nbr installed: -
Nbr required: 0
Placard: No
Both detectors in the cavity may be inoperative provided that the FWD cargo compartment is empty.
Ref: 26-16-01B
FWD Cargo S/D - Non ETOPS flight
Repair interval: C
Nbr installed: -
Nbr required: 0
Placard: No
Both detectors in the cavity may be inoperative provided that ETOPS is not conducted.
Ref: 26-16-01C
FWD Cargo S/D - Non ETOPS flight (with optional Ventilation Controller)
Repair interval: C
Nbr installed: -
Nbr required: 0
Placard: No
Both detectors in the cavity may be inoperative provided that:
1. ETOPS is not conducted, and
2. The FWD cargo ventilation is closed.
Ref: 26-16-01D
FWD Cargo S/D - Check of liner integrity
Repair interval: C
Nbr installed: -
Nbr required: 0
Placard: No
Both detectors in the cavity may be inoperative provided that the liner integrity in the FWD cargo
compartment is checked before each flight.
Refer to AMM Task 25-50-00-200-002
Ref: 26-16-01E
FWD Cargo S/D - Check of liner integrity
(with optional Ventilation Controller)
Repair interval: C
Nbr installed: -
Nbr required: 0
Placard: No
Both detectors in the cavity may be inoperative provided that:
1. The liner integrity in the FWD cargo compartment is checked before each flight, and
1. The FWD cargo ventilation is closed.
Refer to AMM Task 25-50-00-200-002
5. Dispatch and Troubleshooting Advices
_
C. MEL
XIV. AFT & BULK Cargo S/D
Notes:
1. The cargo smoke detection function is part of the CIDS Smoke Detection Function
(CIDS-SDF). Refer to Item 23-73-10-01 Smoke Detection Function (CIDS-SDF)
2. Failure of a single detector in the cavity is indicated by a MAINTENANCE message
on the STATUS SD page. Refer to Item 26-00-01 SDCU/SMOKE MAINTENANCE Message
3. Depending on applicable regulation, smoke detection system may be required for dispatch.
Ref: 26-16-02A
AFT/BULK Cargo S/D - No flammable or combustible materials
Repair interval: D
Nbr installed: -
Nbr required: 0
Placard: No
Both detectors in one or both cavities may be inoperative provided that the AFT and the BULK cargo compartments are empty or do not contain flammable or combustible materials.
Ref: 26-16-02B
AFT/BULK Cargo S/D - Non ETOPS flight
Repair interval: C
Nbr installed: -
Nbr required: 0
Placard: No
Both detectors in one or both cavities may be inoperative provided that ETOPS is not conducted.
Ref: 26-16-02D
AFT/BULK Cargo S/D - Non ETOPS flight
Repair interval: C
Nbr installed: -
Nbr required: 0
Placard: No
Both detectors in one or both cavities may be inoperative provided that the liner integrity in the AFT
and the BULK cargo compartments is checked before each flight. Refer to AMM Task 25-50-00-200-002
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5. Dispatch and Troubleshooting Advices
_. Smoke Event
D
I. Smoke Warning Investigation
II. Prevent False Smoke Event
III. Smoke related troubleshooting
5. Dispatch and Troubleshooting Advices
_
D. Smoke Event
I. Smoke Warning Investigation (1/2)
Reference doc: ISI article 26.16.00001
The operator is kindly advised to report to Airbus any cases of smoke ECAM WARNINGS
with or without real smoke and provide the following information on each event in order
to allow Airbus investigations:
MANDATORY INFORMATION:
1. The PFR
2. The CIDS configuration at the time of the event:
a. Directors P/N
b. OBRM P/N
c. CAM P/N
3. On the FAP: a digital picture of the S/W Loading page.
4. On CIDS MCDU menu: a printout of the CIDS LRU identification page
5. On SDF 1 MCDU menu:
a. Perform a SDF System Test and provide Airbus the outputs and associated TSD, if any.
b. Provide us the following reports:
I. Smoke warnings report
II. LRU Identification report
III. Last leg report
IV. Previous legs reports
V. TSD
VI. Class 3 faults
6. After deactivation of SDF1 (usually thanks to C/B 15WH and 17WH, but refer to the AMM
of the A/C), provide the same information than SDF 1 but through SDF 2 MCDU menu.
Note:
Even without new event/fault, SDF reports are available in SDF BITE memory for maximum
64 legs
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5. Dispatch and Troubleshooting Advices
_
D. Smoke Event
I. Smoke Warning Investigation (2/2)
Note:
Following preliminary analysis of the event, Airbus may ask the operator to send involved or
replaced Smoke Detectors (S/D) to Siemens for special investigation and memory read-out.
In this case, please provide Airbus with the S/N and FIN of the removed unit(s) and AWB
of their related shipment to Siemens for tracking purpose.
Notice:
Any repair shop actions on the removed S/D shall be prevented prior to their shipment to
Siemens, as they can erase the memory of the unit.
COMPLEMENTARY INFORMATION:
1. QAR/DFDR data to precisely correlate Cockpit indications and actions with SDF observed
events.
2. The Cargo manifest of the flight
3. On CIDS 1 MCDU menu:
a.Perform a CIDS Interface and Power-Up Test and provide us the outputs and
associated TSD, if any.
b.Provide us the following reports:
I. Last leg report
II. Previous legs reports
III. TSD
IV. Class 3 faults
5. Dispatch and Troubleshooting Advices
_
D. Smoke Event
II. Prevent False Smoke Event
Reference doc: ISI article 26.10.00007, ISI article 26.10.00004
•R
efer to ISI article 26.10.00007: Prevention of aircraft smoke warnings not related
to real fires in case of: use of spray in cabin or cargo compartment
(AMM Task 12-21-12-670-006-A), extreme condensation / humidity, bleed air oil vapor,
entrapment of fumes in cargo compartment, terrestrial fires, anti-ice/de-icing fluids
into bleed air system, ingestion of engine cleaning agent into the ECS.
• Ensure that faulty Cargo S/D are replaced at the earliest opportunity after a “SMOKE”
maintenance status associated to a S/D fault message are observed. Otherwise,
in the meantime, the related cargo cavity will be monitored by a single S/D instead of two,
therefore preventing the confirmation logic per cavity.
• Ensure that the cargo S/D contamination by dust is at a satisfactory level by cleaning
it as soon as the pre-fault fault message (class 3 fault “CONTAMINATION”) is triggered
by the SDF and by fulfilling MPD Task 261600-05-1 otherwise.
Note:
• MPD Task 261600-05-1 cleaning interval has been based on aircraft operation
between 1800/4400 FH within 12 Months, corresponding to 18000 FH or 10 Years
as mentioned in the MPD task. This cleaning interval may have to be adapted to airline
operation conditions.
• Siemens has provided recommendations to reduce the cleaning interval to 9,000 FH
for optical smoke detectors, from an equipment point of view. Refer to ISI 26.10.00004:
Cleaning intervals of smoke detectors.
Lavatory Detectors Cleaning Interval : MPD Task 261700-04-1 (12000FH or 80MO),
refer to ISI article 26.14.00002.
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5. Dispatch and Troubleshooting Advices
_
D. Smoke Event
III. Smoke related troubleshooting
SMOKE issue with impact on dispatch:
SMOKE issue with impact on dispatch:
A SDF System test is recommended to confirm the fault and obtain the precise fault
message(s) detailing the issue. Associated TSM then needs to be followed.
If no maintenance is available on board and a spurious suspected, SDF can be reset by flight
crew as per FCOM supplementary procedure PRO-SUP-24-B-00012651.0016001.
SMOKE / 237334 CHECK SDF2 BITE:
A “SMOKE” Maintenance Status linked with a fault message “237334 CHECK SDF2 BITE”
means that SDF 2 BITE has to be interrogated to determine which fault message was
observed by SDF2. SDF 1 has to be deactivated and SDF 2 MCDU menu accessed
(refer to TSM TASK 26-17-00-810-823-A). The “SMOKE” maintenance status will
disappear only when the fault triggered by SDF 2 will have been resolved.
Lavatory (LAV) SMOKE fault:
CIDS DIR board and DEU-B are involved in the Smoke Detection Function of the Lavatories
(refer to chapter 2.B - Smoke Detection).
When detected, SDF LAV faults are setting a trigger stored into the memory of their associated
DEU-B. After resolution, the associated DEU-B needs to be power cycled to clear the fault.
5. Dispatch and Troubleshooting Advices
_
D. Smoke Event
Smoke Detector PIN PROG ISSUE:
In case of PIN Programming wiring issue at Cargo Smoke Detector level (ie on CAN bus
A and/or B), ECAM Warning SMOKE AFT/FWD/BULK AVN DET FAULT may be triggered.
Indeed, the Smoke Detectors read their CAN bus thanks to PIN PROG inputs.
In case of unreadable/inconsistent PIN PROG, the S/D set its bus address to the default
address on the CAN bus. This is then treated by the SDF as an unexpected smoke
detector on the CAN bus lane.
Therefore, the SDF detected a configuration inconsistency, and all configurable (pin
programmable or CAM programmable) compartments with defined SD on this CAN bus
are declared as faulty.
In case there is one message incriminating one particular S/D, check first the PIN PROG
wiring of this S/D and possibly replace the S/D.
TSM task 26-17-00-810-830-A has been created to troubleshoot this issue.
Refer to CIDS deviation #58 for more details.
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5. Dispatch and Troubleshooting Advices
_
E. CIDS Event
I. PSU Troubleshooting
II. CIDS TOP / MID Line Troubleshooting
III. Service Interphone Noise
IV. PA, Interphone and Handsets
V. Handset best practices
5. Dispatch and Troubleshooting Advices
_
E. CIDS Event
I. PSU Troubleshooting
The architecture of the PSU allows to test the connexion between the PSU and the DIR:
• A Reading Light activation from pushbuttons on the overhead PSU will test the local
performance of the system.
• A Passenger announcement will test the connexion from the director to the PSU.
• A passenger call initiated from the PSU sends a signal from the PISA via DEU type A
to the director. The director transmits a signal via the DEU type A to the respective PISA
and the related call light comes on. Therefore, the connexion between the PSU
and the director is tested back and forth.
Notes:
• Operational test of the Reading Light can be performed by following the AMM task
23-73-64-720-001-A.
• Operational test of Loudspeaker can be performed by following the AMM task
23-73-00-710-036-A.
A reliability issue of the PAX call switch has been identified, which may lead to find defective
PAX call switch.
Defective switch can be replaced on wing. Refer to AMM and TFU 23.73.00.105.
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5. Dispatch and Troubleshooting Advices
_
E. CIDS Event
II. CIDS TOP / MID Line Troubleshooting
DEU faulty I/O:
When booting, each DEU tests its Inputs and Outputs. If it is unable to manage at least
one of them (due to a short circuit for example), the DEU declares itself faulty to the CIDS
and all equipments connected with this DEU (W&W sensor level, or vacuum system e.g.)
are lost. CIDS TSD allows then to find which DEU pin is faulty.
Note:
TSD Decoder is available FOC to operators. Refer to ISI article 23.73.00008.
A TOP / MID line fault is detectable in two cases:
Line fault due to a current sensing test at power-up:
In such a case a respective “BUS Fault message” is memorized in the BITE memory.
None of the DEUs connected to this line will be memorized.
Line fault due to plausibility check:
This is the case if the CIDS Director does not receive data of any DEU of one line.
A respective “BUS Fault message” is memorized. The respective DEUs may also be written
into the BITE memory.
Notice:
In conjunction with the TSM tasks related to MID & TOP line Fault and depending of the line
resistance value measured at the CIDS Director connector, either of the following flow charts
can be used in order to speed up the investigations.
5. Dispatch and Troubleshooting Advices
_
E. CIDS Event
II. CIDS TOP / MID Line Troubleshooting 1/3
START
FLOW CHART –
NO SHORT CIRCUIT
DISCONNECT ALL DEU’S
EXCEPT THE LAST ON THE BUS,
REFER TO AMM
REPLACE THE DEU
INSTALL CIDS DIRECTOR,
REFER TO AMM
REPLACE THE
TERMINATION/
CONNECTION BOX
CHECK OPERATION
OF DEU(S)
CONECTED DEVICES
YES
DEU REPLACED
CONNECT NEXT DEU,
REFER TO TSM
CLOSE DEU’S CIRCUIT
BREAKER REFER TO TSM
PULL DEU’S
CIRCUIT BREAKER’S
REFER TO TSM
ALL CONNECTED
DEVICES OPERATIV
YES
PULL DEU’S
CIRCUIT BREAKER
NO
NO
TERMINASION/
CONNECTION BOX
REPLACED
YES
ALL DEU’S
CONNECTED
YES
ALL CONNECTION
BOXES CONNECTED
NO
PULL DEU’S
CIRCUIT BREAKER’S
YES
CHECK ALL CONNECTED
DEVICES ARE OPERATIVE
END
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REPLACE NEXT DEU
CONNECTION BOX
REFER TO TSM
NO
184
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5. Dispatch and Troubleshooting Advices
_
E. CIDS Event
II. CIDS TOP / MID Line Troubleshooting 2/3
START
FLOW CHART SHORT CIRCUIT
CONNECTED THE MULTIMETER TO THE AFFECTED
WIRING ON THE DIRECTOR RACK PLUG AND
DISCONNECT ALL DEU’S CONNECTED TO THE BUS
CHECK STILL
SHORT CIRCUIT
NO
CONNECT
LAST DEU
ON THE BUS
YES
DISCONNECT
TERMINATION BOX
NO
TERMINATION/
CONNECTION BOX
DISCONNECTED
NO
CHECK STILL
SHORT CIRCUIT
YES
YES
CHECK STILL
SHORT CIRCUIT
DISCONNECT NEXT
CONNEXION BOX,
REFER TO TSM
REPLACE
DEU
CHECK STILL
SHORT CIRCUIT
ALL DEU’S
CONNECTED
NO
YES
CHECK BUS FOR SHORT CIRCUIT BETWEEN
THE TWO RESPECTIVE CONNECTORS
NO
CHECK STILL
SHORT CIRCUIT
YES
REPLACE
INTERCONNECTING
BOX
REPAIR AS
NECESSARY
CHECK ALL
CONNECTED DEVICES
ARE OPERATIVE
END
NO
CONNECT
NEXT DEU,
REFER TO TSM
5. Dispatch and Troubleshooting Advices
_
E. CIDS Event
II. CIDS TOP / MID Line Troubleshooting 3/3
START
FLOW CHART –
OPEN CIRCUIT
CONNECTED THE MULTIMETER
TO THE AFFECTED WIRING ON
THE DIRECTOR RACK PLUG,
REFER TO TSM
ON THE LAS DEU ON THE BUS
REPLACE THE TERMINATION
BOX, , REFER TO TSM
STILL
OPEN
CIRCUIT
NO
YES
CHECK BUS BETWEEN
DIRECTOR RACK PLUG AND
FIRST CONNECTION BOX
PLUG, REFER TO TSM
STILL
OPEN
CIRCUIT
NO
CHECK BUS BETWEEN
CONNCTION BOX AND NEXT
CONNECTION BOX, REFER
TO TSM
YES
REPAIR BUS IN CHECKED
AREA
YES
STILL
OPEN
CIRCUIT
END
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NO
186
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5. Dispatch and Troubleshooting Advices
_
E. CIDS Event
III. Service Interphone Noise
Despite Insulation Units P/N D9559012100000 (FIN 4RJ1/2/3/4/5), a crackling noise might
be heard in the cabin and cockpit interphone, due to oxidation and water ingress within
the interphone jack. In that case, it is recommended to follow the interphone jack cleaning
procedure:
•g
ain access to the jack assembly
•c
lean & dry the plug
• reassemble
Reference Doc:
•T
SM 23-44-00-810-802-A
•C
MM 71-11-19 Figure 2
•C
MM 71-50-03 page 4001-4002
•F
AIR item 12.0259
Note:
Ensure that interphone jack plug
is wiped clean before insertion into
the receptacle when using the service
interphone.
Ground Service Jacks
Notes:
• CFM56-5B Jack P/N 2J-1761A should be replaced by Jack P/N 2J-1933A.
• Some ground service jacks are located close to grounding points.
5. Dispatch and Troubleshooting Advices
_
E. CIDS Event
IV. PA, Interphone & Handsets
PA issue:
In case of Crackling noise and/or interferences on Interphone and Passenger Address
an audio RAM might fix the issue, as described in TFU 23.73.00.095 (DIR affected:
PN Z014H000131A & Z014H000231B).
Short Power Interruption & PA:
In case of Power Interruption bellow 200ms, the CIDS detects the SPI and automatically
recovers as soon as the power is restored without a Power Up procedure. However,
the CIDS audio board will need 500ms to recover, producing a cut in the announcement
of up to 700ms.
It is recommended to not perform announcements during A/C power transfers.
Loss of PA / Interphone function:
Based on In Service feedbacks and Operational Interruptions analysis, the whole Passenger
Announcement and/or Interphone function was sometimes reported partially (meaning noisy)
or totally inoperative.
The system functionality was reported recovered by a CIDS reset, director or handset
replacement, or service interphone clean-up.
Airbus kindly requests the operators to report any occurrence by filling questionnaire available
in ISI article 23.73.00019.
Cockpit Call:
If a call has been initiated by pressing a call button on the cockpit call panel and this call
was not accepted by the targeted attendant handset(s), then this call will be automatically
reset only after 5 minutes. Prior to that reset, all cabin attendant stations would not be able
to address the cockpit.
Defective handset:
One handset has to operative at each pair of exit doors, but MMEL can be applied
for others handsets if defective (refer to chapter handset MMEL chapter 5.E.iv).
In particular in case of FWD handset inoperative and no spare available, operative AFT
and inoperative FWD handsets could be swapped and MMEL applied to allow dispatch.
Notes:
Handsets have been designed in order to be replaced in less than 15 min,
with appropriate tooling (cf. CMM).
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A320 Family - Enhanced CIDS - ref: ISI 23.73.00094 - Issue: September 2017
5. Dispatch and Troubleshooting Advices
_
E. CIDS Event
V. Handset best practices
Eng./Maint. rationales supporting
Cabin crew best practices:
Larsen effect + missing
echo concellation mechanism
if PA away from station.
Damaged cable & stressed
connectors if PA/Interphone
away from station.
Missing noise-cancellation
mechanism if not used like
a standard phone.
Inaudible PA/Interphone
if not used like a standard
phone (Oriented mike).
Slide smoothly but completely (“click”)
in bracket to prevent housing damages
due to fallings.
Maintenance
best practices:
15 min replacement
following AMM tasks
(as per handset design).
Dedicated tooling to
open handset housing
(≠ screwdriver!).
Prevent stress on cradle
connector
disconnect
thanks to a screwdriver.
Housing & keypad
damages prevention using
cleaning materials &
solutions as per CMM
requirements
Check PA from FWD when entering A/C to
prevent late detection of defective handset.
5. Dispatch and Troubleshooting Advices
_
F. List of CIDS Deviations (1/4)
Reference doc: ISI article 23.73.00027
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5. Dispatch and Troubleshooting Advices
_
F. List of CIDS Deviations (2/4)
5. Dispatch and Troubleshooting Advices
_
F. List of CIDS Deviations (3/4)
191
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A320 Family - Enhanced CIDS - ref: ISI 23.73.00094 - Issue: September 2017
5. Dispatch and Troubleshooting Advices
_
F. List of CIDS Deviations (4/4)
6. Documentation
& Contacts
A. Documentation
B. Contacts
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6. Documentation & contacts
_
A. Documentation (1/2)
Reference
Title
ISI 23.73.00017
Enhanced CIDS Director H/W and OBRM P/N Evolutions
ISI 23.73.00021
FAP / AAP / AIP P/N Evolutions
ISI 23.73.00020
DEU-A / DEU-B / PISA P/N Evolutions
ISI 23.73.00009
Interchangeability between old and new cabin handsets»
TFU 23.73.00.089
Cabin Handsets low reliability
TFU 23.73.00.099
Cabin Handsets Interchangeability
TFU 23.73.00.095
Crackling noise in Interphone and Passenger Address
Ho-P6091-ROP-0000-01A
HOLMCO Recommended Operation Practices
N40 Handset with Support Bracket
VSIL D9240-44-09
HOLMCO N40 handset series - discharge electrodes modification
VSIL D9240-44-10
HOLMCO N40 handset series - release button improvement
ISI 23.73.00022
CIDS - Cabin Handset & Airline feedback - Questionnaire
ISI 23.73.00019
PA & Interphone inoperative
SIL 00-028
Centralized Fault Display System (CFDS) Anomalies
ISI 23.73.00027
Enhanced CIDS Deviations list & digest
TFU 23.73.00.098
CIDS ‘spec Issue 8’ SPI robustness
TFU 23.73.00.101
Fix for Deviations of DIR -333B and OBRM -33B
TFU 23.73.00.105
PSU PAX call button reliability
TFU 23.73.00.108
Enhanced CIDS Director Obsolescence on A320FAM
TFU 23.73.00.107
Enhanced CIDS FAP Obsolescence on A320FAM
ISI 23.73.00091
CIDS - A320fam - GENERIC FAP P/N
6. Documentation & contacts
_
A. Documentation (2/2)
195
Reference
Title
ISI 23.73.00016
Introduction of new LED technology for PSU signs.
ISI 23.73.00008
CIDS Trouble Shooting Data (TSD) Decoder
ISI 23.73.00023
Cabin Ready Function
ISI 23.73.00018
CAM reprogramming options
ISI 23.73.00007
Operator customized FAP logo
ISI 23.73.00058
CIDS - Escape slide and door pressure monitoring
ISI 23.32.00001
Customisation of boarding music on Aircraft already equipped with I-PRAM
ISI 26.17.00002
E-cigarette or cigarette smoke detection in lavatory compartment
ISI 26.10.00007
Prevention of A/C Smoke Warnings not related to real fires
ISI 26.16.00001
CARGO Smoke Warning event investigations data
ISI 26.10.00006
Smoke Detectors P/N Evolutions and Interchangeability
ISI 26.10.00004
A320 family - cleaning intervals of smoke detectors
ISI 26.14.00002
ECAM warning SMOKE LAVATORY SMOKE
ISI 00.00.00170
Enhanced CIDS Deviations list & digest
TFU 26.16.00.006
Improve operational reliability of cargo smoke detectors
A320 Family - Enhanced CIDS - ref: ISI 23.73.00094 - Issue: September 2017
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6. Documentation & contacts
_
B. Contacts
TechRequest tool now provides a single access point for technical requests.
All technical requests related to the below listed domains shall be raised by using
TechRequest within AirbusWorld portal and not by e-mail anymore:
• Technical queries
• AOG
• Flight Operations,
• Technical Manuals,
• Service Bulletins,
• Service Bulletin embodiment reporting,
• Scheduled Maintenance,
• Ground Support Equipment tools.
• Supplier support operations
• Tools & services, including Airbus World
Please refer to the latest revision of OIT-999-0120-14-02 for up-to-date information.
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