In Service Information Ref: ISI 23.73.00094 Issue: September 2017
A320 A3 20 Fa Family mily A318/A A318 /A31 319/ 9/A3 A320 20/A /A32 321 1 Enhanced Cabin Cabin Intercommunication Data System & Smoke Detection Function (CIDS/SDF) Troubleshooting T roubleshooting guidelines
Guidelines for system troubleshooting _
A318 / A319 / A320 / A321 Enhanced Cabin – CIDS & SDF GUIDELINES SYSTEM FOR TROUBLESHOOTING Please note:
• These information do not amend a mend or supersede any instruction contained in the Aircraft Maintenance Manual (AMM), or the Trouble 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 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, Director, who will take appropriate actions to procure these guides. Refer to the ISI 00.00.00170 for 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 order to inform operators of A318, 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 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
027 028 029 032 034 035 037 039 040 041 042 046 047 048 049 051 052 054 056 057 058 059 061 062 063 064 065 067 068 069 070 071 089 091
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Table of content _
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 _
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
007
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
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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 _
2 1 V U
( D D i r I R e c 1 t o / r D s I R 2 )
3 5 V U
2 1 V U
2 5 V U
C o c k p i t s w i t c h e s
2 2 V U
• • • A C P P t t a A A e b X & n i n c I d a n a i n l t n d l e t r f i p c u a h n t o c i o n n e t i o s n
A C P
s :
A I P
F A P
D L e A t e V c & t o C r a s r . g o S m o k e
a C A n t d a b t e m i n n o c d n o a n i n t t o t r f r i n o u n g l c . t i o n s :
013
S P e A r v X i f c e u n U c n t i i t s o n ( P s S : P U a / P s I s e S n A g ) e r s
A A P & H a n d s e t s
D E U A
D E U B
D E U A
D E U B
( T D o E p U l -A i n e )
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D E U B
D E U A
M i d d l e l i n e ( D E U -B )
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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 V
1. General Overview E. Circuit Breakers _
Here are the FIN number of the circuit breakers related to different components (outside of Battery installation): Panel
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 ESS NORM ESS NORM ESS NORM ESS NORM ESS NORM
A318/320
49VU
150RH
120VU
156RH
49VU
157RH
122VU
17WH
49VU
15WH
122VU
14WH
49VU
18WH
120VU
170RH
49VU
171RH
120VU
163RH
154RH 120VU
164RH
49VU 155RH
NORM
2001 VU
197RH
49VU
195RH
2001 VU
198RH
49VU
196RH
ESS 120VU
ESS
DEU B FWD
NORM
DEU B AFT
NORM
2001VU
167RH
49VU 120VU
ESS
ESS
158RH
49VU
ESS
NORM
A321
159RH
49VU
NORM
NORM
A318/320 151RH
ESS
NORM
A318
49VU
NORM
ESS
A321
120VU
ESS ESS
FIN
2001 VU
179RH 168RH
49VU 120VU
173RH
174RH 172RH
162RH
49VU
153RH
120VU
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 Power supply circuits
BITE/ WATCHDOG circuits
Bus Interface Circuit
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: • DIR 1 is powered after DIR 2 has been active, and • DIR 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: S B23-1612
Z064H000031B
Z064H000034C
S B 2 Z064H000031D 3 - 1 2 8 4
Z064H000031A
Z064H000031C SB23-1284
S B 2 3 - 1 5 8 8
8 5 8 - 1 3 B 2 S
Z064H000032A
Z064H000032B
Z064H000033A
SB23-1360
Z064H000033B SB23-1492
OBRM
Z014H000x31A
Z014H000231B SB23-1611 SB23-1612
DIR
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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
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
Z014H000131A Amdt C
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. 037
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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
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
045
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
052
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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: • On 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: • Through allowed Interchangeabilities • Through 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. Applicable Series
Reference VSIL
Title
Date
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: • HOLMCO VSIL Ho-P6091-ROP-0000-01A • CCOM 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: • Avoid 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. • Always 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. • Slide the handset in its bracket soft and smooth, without applying too much pressure. • Avoid 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 Alert, command in emergency condition or marking a dangerous situation; e.g. Open Doors, S moke Indication…
Red 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 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. 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, Layout, which is stored both in the DIR and the CAM, and marked. Layout is available to each Director in case of unreadable CAM Additionally a Mandatory Layout is and no Last Used Layout in the DIR Memory. Memory. CAM replacement replacement:: If the new CAM has never been fitted, DEF DEFAUL AULT T 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 CIDS system cabin configuration CAM-B used for FAP graphic customisations CAM-C used for flexible cargo SDF system configuration (DIR (DIR -333B) CAM-Part Number (12 characters) Z
0
5
4
H
CAM H/W Model 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)
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0
1
Version Versi on 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 Mandatory Layout 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 Door s/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. software. Major changes of the CIDS 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 Prerecorded Announcement & Boarding Music (optional) The IPRAM stores prerecor prerecorded ded announcement and boarding music audio data.
P/N:
Not supported on SA/LR
Customization possibilities: • Standard Card = Silver Card: Card: P/N Z163H000010X - 4 music channels: 2 Hours 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 Card: P/N Z163Hmmcctvv • Customized Card = Gold Card: A/L customized records, records, more languages, recent 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
Allow to switch full bright the lavatory lighting system for maintenance purpose
SCREEN 30 SEC. LOCK
Allow to clean the FAP display by temporarily de-activating any touchscreen action for 30 seconds.
EVAC CMD
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
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: • Director 1 • Director 2 • Provisions (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:
• Button off: no event (or all event disappeared) • Active flashing: new event(s) • Active 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 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 Adjustment FAP page, page, crew is able to modify loudspeakers 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 function is availabl available e both in flight flight and on ground. ground. This page can can be deacti deactivated vated by CAM CAM settings settings.. In such a case, a new CAM prog programmi ramming ng 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 page is described in 4.E MCDU Simulator on the FAP. 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: • Hardkeys layout • Colours 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 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: • Reading-light switches and reading lights, • PAX call button and call light, • Seat-row identifier, • Loudspeakers, • Non-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. 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)
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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: • automatically by extending and compressing the landing gear for more than 10 seconds • manually 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: • Activation/deactivation of PAX Calls, • Activation/deactivation of NS/NM, FSB and RTS signs • Layout data, • Illumination data (depending on the IFE type), • Landing gear down and compressed, • Landing gear down and locked, • Oil pressure low, • Cabin pressure low, • Excession altitude, • Slats out, • Flaps out, • All doors closed. CIDS receives the following system information from the IFE: • Activation/deactivation of PAX Calls, • Activation/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: • System test, • Battery 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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3. CIDS Functions K. Potable Water Indication & Preselection _
T O A F NW DD G L A A L V L A E T Y O R Y
V D A R V A L I E N
H C A O NN D T R L O E L
A F R I R O S M Y S B T L E E M E D
D F R W A D I NW P A A T N E E R L
A F R I R O S M Y S B T L E E M E D
P F A L I N G E H L T ( F A A T P T ) E N D A N T
S H V U A T T L V L E E F I L T E R
C O N T R O F L I L H L / A D N R D A L I E N
F W D O D P R E A N N I L V I A G H L V T E
D I R E C C I T D O S R 1
V R A E L V L E E I F
G R P O R U E S N S D
L T I A G HN T K F U L L
F I L L D / O R A V E I N R V F A L V O L W E
T W R A A T N E S R M Q I T T T Y E R
M I D D L E L I N E
T O A A N F D T G L A A L V L A T E O Y R Y
L A N G I S L L U F K N A T
I N Q D U I A C N A T T T O I R Y
E T H E R N E T
D E U B S P E O R T V A I B C E L E P W L A A N
D S O W O R I T C L M H I I T
C A B I N F L O
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), • on 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
Cockpit Indication
Cabin Indication
ECAM Warning
Caution Light on the FAP
Class 1 Aircraft
Class 2 Aircraft
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 Request for action (from Attendant or Mechanic) on the respective FAP page
Class 3 faults
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. Manually 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
1
SYSTEM REPORT/TEST
127
SYSTEM REPORT/TEST COM
F/CTL>
CIDS2>
FUEL>
HF1>
ICE & RAIN>
HF2>
INST>
VHF1>
L/G>
VHF2>
NAV>
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NAV>
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4. BITE D. MCDU CIDS _
Main Page
This page shows the subsequent selectable pages: • , • SYSTEM TESTS>, • EPSU BAT CAP TEST>, • OP TESTS>, • GROUND REPORT>, • SYSTEM CONFIG>,
1
SYSTEM REPORT/TEST COM
HF1>
HF2>
VHF1>
VHF2>
VHF3>
O7
CIDS1 < LAST LEG REPORT < PREVIOUS LEGS REPORT
CIDS X CLASS3 FAULTS> SYSTEM TESTS> EPSU BAT> CAP TEST OP TESTS>
CIDS2>
INTERACTIVE MODE CURRENTLY DISABLED LAYOUT SELECTION MODE OR MAINTENANCE MODE
GROUND REPORT>
ACTIVE ON FAP
SYSTEM CONFIG>
4. BITE D. MCDU CIDS _
II. Last Leg Report When you push the
CIDS1 < LAST LEG REPORT < PREVIOUS LEGS REPORT
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
CIDS 1 LAST LEG REPORT DEC17
1110 237316 DEU A (200RH16)
PRINT*
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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
• The Leg number (1-63), • The date of the flight when the failure occurred, • The time when the failure occurred, • The ATA reference, • The class of the failure (1 or 2), • The 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.
CIDS1 < LAST LEG REPORT < PREVIOUS LEGS REPORT
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
04 JAN1/1306 240000 1 POWER SUPPLY INTERRUPT
PRINT*
PRINT*
POWER SUPPLY INTERRUPT PAGE EXAMPLE
4. BITE D. MCDU CIDS _
IV. LRU Identification When you push the
CIDS1 < LAST LEG REPORT < PREVIOUS LEGS REPORT
CLASS3 FAULTS> SYSTEM TESTS> EPSU BAT> CAP TEST OP TESTS> GROUND REPORT> SYSTEM CONFIG>
OR
EXAMPLE
DIR1 DIR2
CIDS 1 LRU IDENTIFICATION P/N: ZO14H000030A S/N: NNNN P/N: ZO14H000030A S/N: NNNN
OBRM
P/N: MMMMMMMMMMMM
CAM
P/N: MMMMMMMMMMMM
FAP 1
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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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: • The time when the failure occurred, • The ATA reference, • The 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.
CIDS1 < LAST LEG REPORT < PREVIOUS LEGS REPORT
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)
PRINT*
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: • DIR STATUS, • INTERFACE + POWER-UP TEST, • ILLUMINATION TEST, • EPSU SYS TEST, • DRAIN MAST SYS TEST.
CIDS1 < LAST LEG REPORT < PREVIOUS LEGS REPORT
CLASS3 FAULTS> SYSTEM TESTS> EPSU BAT> CAP TEST OP TESTS>
GROUND REPORT> SYSTEM CONFIG>
OR
CIDS X SYSTEM TESTS DIRX ACTIVE INTERFACE+
DRAINM SYS TEST>
PRINT*
SYSTEM TEST PAGE (FOR ACTIVE DIRECTOR)
133
CIDS X SYSTEM TESTS DIRX PASS, DIR TEST ONLY INTERFACE+
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 (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
DRAINM SYSTEST>
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
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)
135
PRINT*
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CLASSE 2> 1>
PRINT*
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4. BITE D. MCDU CIDS _
SYSTEM TEST: INTERFACE + POWER-UP TEST if passive director is selected When you push the
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
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: •
Note: • There is no CAM relation, all DEU outputs are activated. • After the test (when you push the
CIDS1 < LAST LEG REPORT < PREVIOUS LEGS REPORT
CLASS3 FAULTS> SYSTEM TESTS> EPSU BAT> CAP TEST OP TESTS>
GROUND REPORT> SYSTEM CONFIG>
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
137
CIDS1 OP TEST SYSTEM RESET AFTER TEST
PRINT*
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PRINT*
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4. BITE D. MCDU CIDS _
IX. Troubleshooting Data When you push the
CIDS1 < LAST LEG REPORT < PREVIOUS LEGS REPORT
CLASS3 FAULTS> SYSTEM TESTS> EPSU BAT> CAP TEST OP TESTS>
DATA UTC
GROUND REPORT> SYSTEM CONFIG>
CIDS1 TROUBLE SHOOTING DATA
NOV14 0800 HHHH HHHH HHHH HHHH HHHH HHHH HHHH HHHH HHHH HHHH
PRINT*
TROUBLE SHOOTING PAGE EXAMPLE NOTE:
HHHH FOR CODED TROUBLE SHOOTING DATA
4. BITE D. MCDU CIDS _
X. Ground Scanning When you push 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
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4. BITE D. MCDU CIDS _
CIDS1 GROUND SCANNING
CIDS1 NOV10
IN PROGRESS 180s
< LAST LEG REPORT < PREVIOUS LEGS REPORT
CLASS3 FAULTS> SYSTEM TESTS> EPSU BAT> CAP TEST OP TESTS>
PRINT*
< TROUBLE SHOOT DATA
GROUND REPORT> SYSTEM CONFIG>
OR
CIDS1 GROUND SCANNING UTC ATA
CIDS1 NOV10 CLASS
NO FAULT DETECTED
PRINT*
GROUND SCANNING UTC ATA IN PROGRESS 1546 1542 237346 DEU A (200RH01)
NOV10 CLASS
1>
PRINT*
GROUND SCANNING EXAMPLE
DATA UTC
CIDS1 GROUND SCANNING
NOV14 1542 J304 HHHH HHHH HHHH HHHH HHHH HHHH HHHH HHHH HHHH HHHH
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.
CIDS1 < LAST LEG REPORT < PREVIOUS LEGS REPORT
CLASS3 FAULTS> SYSTEM TESTS> EPSU BAT> CAP TEST OP TESTS>
GROUND REPORT> SYSTEM CONFIG>
OR
CIDS1
CIDS1
GROUND REPORT DATE UTC
GROUND REPORT UTC ATA
NO FAULT DETECTED
12h0 23/300 CAM(115RH) DIR1(101RH)
PRINT*
1>
DATE UTC
SEP 23 CLASS
PRINT*
CIDS1 GROUND REPORT
NOV23 1250 MANDATORY LAYOUT HHHH HHHH HHHH HHHH HHHH
NOTE:
141
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: • The current date, • The UTC, • The aircraft ident, • The ACTIVE DIR, • The CAM P/N, • The ACTIVE LAYOUT, • The LAST CAM MODIFICATION, •
When you push the
CIDS1 < LAST LEG REPORT < PREVIOUS LEGS REPORT
CLASS3 FAULTS> SYSTEM TESTS> EPSU BAT> CAP TEST OP TESTS>
GROUND REPORT> SYSTEM CONFIG>
CIDS1 SYSTEM CONFIGURATION DATE: FEB12. UTC: 1205 A/C: DA-ABCD
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
NOTE:
+2dB 0dB -2dB +4dB
PRINT*
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
+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.
SYSTEM REPORT/TEST FIRE PROT
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: •
CIDS-SDFx SDCU FUNCTION IS INTEGRATED IN CIDS DIRECTORS 101RH & 102RH
CIDS-SDFX
1/2 < LAST LEG REPORT < PREVIOUS LEGS REPORT
2/2
CLASS3 FAULTS> SYSTEM TESTS> SMOKE WARN> TEST GROUND REPORT>
CALLED CIDS-SDFx
< TROUBLE SHOOT DATA
SPECIFIC DATA> RETURN>
4. BITE F. MCDU SDF _
II. Last leg report When you push the
CIDS-SDFx LAST LEG REPORT DEC 17 NO FAULT DETECTED
147
PRINT*
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4. BITE F. MCDU SDF _
III. Previous Legs Report When you push the
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
PRINT* >
4. BITE F. MCDU SDF _
IV. LRU Identification When you push the
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
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
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 LAST LEG CLASS FAULTS UTC ATA 1410 773200 N1 BRG VIB SENSOR (4002EV1)/EIVMU1(1KS1) 1415 772500 RCC1 (400EVA)/EIVMU1(1KS1)
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
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PRINT*
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4. BITE F. MCDU SDF _
VII. Ground Scanning When you push 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
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 LDCC TEST LDCC TEST
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 a nd 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
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
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
CIDS or LAV Smoke
YES
Refer to associated recommendations (ISI, TFU, see Appendix)
NO
Smoke Type?
SDF test
YES 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: • Symptoms and fault messages (+date & time) • Reference 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.
DIR reboot times Access Fault Troubleshooting A/C status 157
RESET
BITE Test
4 min
6 min
Multiple C/B Specific C/B Order
MCDU
NIL help is not spurius
Confirmed fault(s)
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 23-73-00-710-005-A
Operational test of the PA system 23-73-00-710-022-A* 23-73-00-710-003-A Operational test of the Cabin and Flight Crew Interphone System 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
159
A320 Family - Enhanced CIDS - ref: ISI 23.73.00094 - Issue: September 2017
160
A320 Family - Enhanced CIDS - ref: ISI 23.73.00094 - Issue: September 2017
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
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. Repair Interval B 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. Repair Interval C 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
Repair Interval D
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.
161
A320 Family - Enhanced CIDS - ref: ISI 23.73.00094 - Issue: September 2017
Placard: No
162
A320 Family - Enhanced CIDS - ref: ISI 23.73.00094 - Issue: September 2017
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.
163
A320 Family - Enhanced CIDS - ref: ISI 23.73.00094 - Issue: September 2017
164
A320 Family - Enhanced CIDS - ref: ISI 23.73.00094 - Issue: September 2017
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.
165
A320 Family - Enhanced CIDS - ref: ISI 23.73.00094 - Issue: September 2017
166
A320 Family - Enhanced CIDS - ref: ISI 23.73.00094 - Issue: September 2017
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.
167
A320 Family - Enhanced CIDS - ref: ISI 23.73.00094 - Issue: September 2017
Placard: No
168
A320 Family - Enhanced CIDS - ref: ISI 23.73.00094 - Issue: September 2017
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.
169
A320 Family - Enhanced CIDS - ref: ISI 23.73.00094 - Issue: September 2017
170
A320 Family - Enhanced CIDS - ref: ISI 23.73.00094 - Issue: September 2017
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 i s 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.
171
A320 Family - Enhanced CIDS - ref: ISI 23.73.00094 - Issue: September 2017
172
A320 Family - Enhanced CIDS - ref: ISI 23.73.00094 - Issue: September 2017
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
173
A320 Family - Enhanced CIDS - ref: ISI 23.73.00094 - Issue: September 2017
174
A320 Family - Enhanced CIDS - ref: ISI 23.73.00094 - Issue: September 2017
5. Dispatch and Troubleshooting Advices D. Smoke Event _
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
175
A320 Family - Enhanced CIDS - ref: ISI 23.73.00094 - Issue: September 2017
176
A320 Family - Enhanced CIDS - ref: ISI 23.73.00094 - Issue: September 2017
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
• Refer 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.
177
A320 Family - Enhanced CIDS - ref: ISI 23.73.00094 - Issue: September 2017
178
A320 Family - Enhanced CIDS - ref: ISI 23.73.00094 - Issue: September 2017
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.
179
A320 Family - Enhanced CIDS - ref: ISI 23.73.00094 - Issue: September 2017
180
A320 Family - Enhanced CIDS - ref: ISI 23.73.00094 - Issue: September 2017
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 NO DEU REPLACED
CONNECT NEXT DEU, REFER TO TSM
CLOSE DEU’S CIRCUIT BREAKER REFER TO TSM
NO PULL DEU’S CIRCUIT BREAKER’S REFER TO TSM
ALL CONNECTED DEVICES OPERATIV
YES
PULL DEU’S CIRCUIT BREAKER
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
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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
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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: • gain access to the jack assembly • clean & dry the plug • reassemble Reference Doc: • TSM 23-44-00-810-802-A • CMM 71-11-19 Figure 2 • CMM 71-50-03 page 4001-4002 • FAIR 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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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) _
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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 _
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Please refer to the latest revision of OIT-999-0120-14-02 for up-to-date information.