A330-800/900

System
Configuration Guide
Issue 3 Revision 2
 System Configuration Guide
A330-800/900
Issue 3, Revision 2
January 2021
Document in accordance with the following Standard Specifications:

A330-800 G 000 08000 issue 03

A330-900 G 000 09000 issue 03

Prepared and authorized: BLVO

BLVO CC2100007
 A330-800/900

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A330-800/900 Table of contents
Title Table of contents Title
General information 00 Structures 51
Certification - External livery 02 Doors 52
General aircraft design criteria 03 Fuselage 53
Placards and markings 11 Stabilizers 55
Air conditioning 21 Windows 56
Auto flight 22 Engines 72
Communications 23 Oil 79
Electrical power 24
Equipment/furnishings 25
Fire protection 26
Flight controls 27
Fuel 28
Indicating/recording systems 31
Landing gear 32
Navigation 34
Oxygen 35
Water/waste 38
Information systems 46

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TITLE Page
Detailed table of contents

General information 1
00.00.230 - Introduction 2
00.00.302 - Glossary Systems 10

Certification - External livery 15

02.10.111 - Environmental conditions - Cold weather protection 16
02.10.130 - Tailwind operation at take-off beyond 10 knots 20
02.10.134 - Certification - Airframe operational requirements 22
02.12.122 - ETOPS beyond 180 minutes 24
02.40.101 - External livery 26

General aircraft design criteria 29

03.20.570 - Alternate Forward Center of Gravity (AFCG) at take-off (A330-800) 30
03.20.571 - Alternate Forward Center of Gravity (AFCG) at take-off (A330-900) 32
03.20.580 - A330-841 Design weights 34
03.20.590 - A330-941 Design weights 40

Placards and markings 45

11.00.124 - Installation of leasing plates 46

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11.00.126 - Installation of operator plate 50
11.20.130 - Break in markings 52
11.20.200 - Customization of exterior markings 54
11.35.100 - Second language for lower deck cargo placards and signs 56
11.35.101 - Weight indication in kg and lb for lower deck cargo compartments 58

Air conditioning 61
21.20.110 - Cabin air recirculation filter cartridge alternate equipment 62
21.22.105 - Installation of electrical heaters for side window air outlets in cockpit 66
21.28.100 - Installation of lower deck aft cargo compartment ventilation system 70
21.28.101 - Installation of lower deck aft cargo compartment ventilation system with increased cooling 74
21.28.105 - Installation of lower deck fwd cargo compartment ventilation system and temperature 78
control
21.28.107 - Installation of on-ground ventilation system for lower deck bulk and forward cargo 82
compartments
21.70.102 - Ozone catalytic converters alternate equipment 86

Auto flight 89
22.10.200 - AP/FD TCAS function 90
22.70.152 - FMS alternate equipment 94
22.70.200 - CDA function 98

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22.70.230 - Activation Take-Off Surveillance 2 function (TOS 2) 102
22.81.102 - QNH/QFE baro setting 104
22.83.120 - Soft go-around function 108

Communications 111
23.00.103 - Fixed Emergency Locator Transmitter (ELT) alternate equipment (BFE) 114
23.11.110 - Activation of High Frequency datalink function 120
23.11.161 - Single High Frequency Data Radio (HFDR) alternate equipment 122
23.11.162 - Installation of dual High Frequency Data Radio (HFDR) system 124
23.28.113 - High rate SATCOM - AERO H+ avionics equipment selection 126
23.28.121 - Antenna subsystem 130
23.28.169 - Provision for HONEYWELL SBB SATCOM 132
23.28.172 - Installation of high speed SATCOM - Swift Broadband (432 kb/s per channel) 134
23.28.180 - Installation of Iridium SATCOM system 136
23.28.190 - Installation of Inmarsat Light Cockpit SATCOM (LCS) system 138
23.50.120 - System provisions for active noise cancelling boomsets 140
23.50.126 - Boomsets alternate equipment 142
23.50.144 - Installation of headsets 146
23.51.101 - Installation of an Audio Control Panel (ACP) and jack panel in avionics compartment 150
23.51.103 - Installation of an Audio Control Panel (ACP) and jack panel for 4th occupant 154
23.70.110 - Installation of Cockpit Door Surveillance System (CDSS) 158

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23.81.105 - Radio Management Panel (RMP) functions 160

Electrical power 163

24.40.107 - Battery discharge warning system 164
24.91.100 - Installation of additional grounding point near pneumatic connection 166

Equipment/furnishings 169
25.10.115 - Installation of tablet mounts in the cockpit 170
25.10.200 - Avionics compartment access panel protection device 174
25.11.140 - Captain and first officer seat covering alternate equipment 178
25.11.145 - Cockpit Fourth Occupant seat alternate equipment 182
25.50.160 - Installation of sidewall protections in lower deck cargo compartments 186
25.50.222 - Installation of heating system for lower deck cargo compartments drainage system 188
25.51.100 - Enhancement package for lower deck Cargo Loading System (CLS) 192
25.52.100 - Installation of additional tie-down points in the lower deck forward cargo compartment 196
25.53.100 - Alternate LD3 position with four 96 inch pallets 200
25.54.120 - Installation of a flight kit container in the lower deck bulk cargo compartment (BFE) 204
25.54.126 - LD3 container capability in lower deck bulk cargo compartment 208

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Fire protection 211
26.13.101 - APU fire extinguisher alternate equipment 212
26.23.106 - Lower deck cargo compartments fire extinguishers alternate equipment 216
26.24.155 - Installation of portable halon-free fire extinguisher in avionics compartment 220

Flight controls 223

27.50.103 - Flap carriages roller bearings alternate equipment 224

Fuel 227
28.25.117 - Installation of additional refuel/defuel couplings on the left wing 228
28.25.121 - Auto refuel cockpit preselection and control facilities via FMGES 232
28.31.101 - Installation of a jettison system 236

Indicating/recording systems 239

31.00.130 - Definition of units 240
31.14.103 - Overhead panel toggle switch re-orientation 244
31.60.102 - Harmonized Primary Flight Display (hPFD) 248

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Landing gear 251
32.40.100 - Wheels and brakes equipment selection 252
32.41.143 - Main Landing Gear (MLG) tire selection 256
32.41.144 - Nose Landing Gear (NLG) tire selection 260
32.48.200 - Installation of universal brake cooling fans 262
32.51.100 - Nose Wheel Steering (NWS) back-up hydraulic power supply 266

Navigation 269
34.00.300 - Required Navigation Performance Authorization Required (RNP AR) 272
34.11.100 - Total Air Temperature (TAT) sensor alternate equipment 274
34.20.203 - Integrated Standby Instrument System (ISIS) - optional functions 278
34.35.112 - Head-Up Display (HUD) system provisions 282
34.35.113 - Installation of Head-Up Display (HUD) 284
34.41.125 - Dual weather radar (WXR) system alternate equipment 288
34.42.100 - Radio altitude automatic call-outs 294
34.42.113 - Radio altimeter alternate equipment 298
34.43.128 - Installation of T3CAS 302
34.43.130 - TCAS II (ARINC 735) / ATC transponder alternate equipment 304
34.43.400 - ATSAW applications 308
34.48.104 - Enhanced Ground Proximity Warning System (EGPWS) optional functions 310

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34.51.108 - DME interrogators alternate equipment 312
34.52.102 - Automatic Dependent Surveillance - Broadcast (ADS-B OUT) 316
34.53.100 - Installation of Automatic Direction Finder (ADF) system 318
34.55.102 - VOR/Marker receivers alternate equipment 322
34.58.310 - Multi Mode Receiver (MMR) alternate equipment 326
34.58.316 - Activation of GLS function 328

Oxygen 331
35.11.120 - In-situ replenishment facility for cockpit oxygen cylinder 332
35.21.110 - Extended duration for passenger chemical oxygen system 336
35.21.115 - Alternate lavatory gaseous oxygen supply 338
35.22.021 - Installation of one additional mask in each oxygen box (chemical system) 340

Water/waste 343
38.00.222 - Water/waste system compliance certificates 344
38.10.104 - Installation of water conditioner(s) in potable water system 346
38.11.112 - Installation of additional potable water tank 348
38.11.116 - Preselection of potable water at service panel 352

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Information systems 355
46.21.100 - Installation of Airline Operational Communication (AOC) software for Air Traffic Service Unit 356
(ATSU)
46.21.105 - Activation of ARINC 623 in the ATSU 360
46.21.111 - Activation of VDL mode 2 function in the ATSU 362
46.21.113 - Installation of Future Air Navigation System (FANS) C 366
46.26.400 - Flight Operations and Maintenance eXchange (FOMAX) 368
46.26.401 - ACARS over IP communication 370

Structures 373
51.22.240 - Base Coat /Clear Coat with intermediate coat paint system on customized areas 374
51.22.250 - Large decorative adhesive film 378

Doors 381
52.10.107 - Type "A" door number 3 382
52.51.103 - Cockpit door locking back-up systems (MMEL conditions) 386
52.51.104 - Install damping devices to reduce noise by door slam 390

Fuselage 393
53.60.180 - Application of heavy duty floor panels 394

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Stabilizers 397
55.30.101 - Metal sheet cover on fin leading edge for erosion protection 398

Windows 401
56.10.110 - Cockpit windows selection 402

Engines 407
72.00.160 - Alternate A330-800/900 thrust ratings 408

Oil 411
79.20.100 - Engine, engine accessories and APU lubricating oil alternate equipment 412

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A330-800/900 General information 00

Reference Title
00.00.230 Introduction
00.00.302 Glossary Systems

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00 General information A330-800/900
00.00.230 - Introduction

1) General 3) Instructions for use

This Configuration Guide is dedicated to the aircraft This Configuration Guide encompasses a wide range of
models and associated Standard Specifications indicat- options and in some circumstances, it is possible that a
ed on the first page. particular combination of options cannot be achieved.
This Configuration Guide offers various options defined Therefore, the Configuration Guide must be used in
as "Airbus preferred solutions" to the customer. conjunction with the expertise and assistance of Airbus.
When used in conjunction with the Standard Specifica-
tion and the other Configuration Guides a complete cus- 4) Lead times
tomization of the Aircraft is possible through the This Configuration Guide shows items for which a pre-
selection of the different items and associated technical defined technical solution has been developed and for
solutions. which the lead times have been studied. Provided the
schedule as defined in the customer definition mile-
2) Basic aircraft stone chart is respected, these items can be installed
This Configuration Guide starts from the theoretical ba- without affecting the delivery lead time.
sic aircraft as shown in the reference layout for weight Caution:
and performance calculations of the corresponding Some items require longer lead time than normal, and
Standard Specification and incorporating any relevant therefore customer decisions prior to Contractual Defi-
Manufacturer Specification Change Notice (MSCN). nition Freeze (CDF) deadlines. These items are high-
lighted in this catalogue by a special remark: "Subject to
lead time constraints". For these items, specific decision
deadlines shall be identified in customer definition mile-
stones.

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A330-800/900 General information 00
00.00.230 - Introduction (Continued)

5) Catalogue presentation As far as possible, the arrangement of the items follows

On each page, the following information is provided: the ATA 100 classification. The items are sorted by nu-
• Chapter/sub-chapter, following as far as possible Air merical order of reference numbers within a given ATA
Transport Association of America (ATA) title and sec- chapter.
tion number The different options bear a 7-digit reference number:
• date of the issue of the catalogue
• option reference. (e.g. 26.24.600) showing first the ATA (e.g. 26) and sub-
For each item, the description is structured in subparts: ATA (e.g. 24) classification, followed by a running num-
• objective of the item ber (e.g. 600).
• basic aircraft definition related to the item Each technical solution (TDU) is referenced by a two-
• description of the item in terms of modifications, in digit number (e.g. 02).
some cases commented by a note and/or illustrated All items are listed in the Table Of Contents (TOC) and
by drawings
• EPAC selection mode for the item shows whether duplicated at the beginning of each chapter.
the item is selectable by individual or global Request Definition of titles:
For Change (RFC)/Specification Change Notice "... equipment selection", "... alternate equipment", "pro-
(SCN) procedure visions for...", "Installation of...".
• technical solutions: a table describes all technical
solutions (called TDU: Technical Description Unit) a) items titled "... equipment selection" relate to items
associated to the item. where the Standard Specification offers a choice of ba-
Note: For comparison purposes, some tables also sic equipment. For such items the customer is request-
show the basic aircraft equipment, labeled Std (Stan- ed to select from one of the choices on offer, unless
dard) in the TDU column. alternate equipment is required.
b) items titled "...alternate equipment" relate to items
where the customer can choose equipment alternate to
that defined in the Standard Specification.

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 00 General information A330-800/900
00.00.230 - Introduction (Continued)

c) items titled "Provisions for..." relate to items where • APL: Effect of RFC/SCN on Available Payload
the customer can add structural and/or system provi- Change.
sions to prepare the a/c for later installation. All weights quoted are for one off unless otherwise stat-
d) items titled "Installation of..." relate to items where the ed.
customer can add functions/equipment/systems on top • TBD: Weight effects have yet to be determined for
RFC/SCN,
of the standard definition. • Negl: Weight effect is small and will be taken as zero
Selection conditions for individual RFC/SCN,
Specific selection conditions may be associated with an • Wt in Global SCN: Weight is part of the relevant glo-
item and are identified by an icon and a special remark bal RFC/SCN.
Weights for alternative items are delta weights to the
visible in the TDU table (see example in the figure here-
after). corresponding Standard Specification unless otherwise
Such solutions may be at the initial phases of develop- stated.
Where the EPAC selection mode is Global the weight of
ment or first application on Airbus aircraft. For these
items commitment to quality, industrial and technical ca- the item shall be part of the relevant Global RFC/SCN.
pabilities, on time delivery and customer support de- Any weights shown in the catalogue for such items are
for guidance only.
pend on successful product qualification and proof of
compliance with Airbus performance requirements and For some Individual RFC/SCN the weight is dependent
customer expectations. on customer requirements, e.g. certain BFE items. The
weights for such items shall be taken for guidance only
Weights
Weight definitions are as follows: and will be identified as such.
• MWE: Effect of RFC/SCN on Manufacturer's Weight
Empty
• OWE: Effect of RFC/SCN on Operating Weight Emp-
ty

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A330-800/900 General information 00
00.00.230 - Introduction (Continued)

6) Definition handling shall be discussed in good faith between the customer

The customer's selection is recorded by Airbus in RFC and Airbus. Airbus hereby forewarns that this may lead
forms. to the unfeasibility of certain requests.
Then, a SCN is issued by Airbus, based on a customer's It is therefore essential for customers to review the Con-
RFC, and is submitted for customer's signature. figuration Guide as soon as possible to identify which of
These RFC/SCN are issued before CDF directly on cus- their requirements are covered and which are not.
tomer request except if their content is to be adapted. This will allow the customers, with the assistance of Air-
Global RFC/SCN bus, to raise in time the necessary specific requests re-
The global RFC consists of a checklist containing items lated to items which are not covered by this Guide.
with considerable interdependence and equivalent
leadtimes. The global RFC leads to the global SCN 7) Buyer's responsibility
which groups all selected items. All installations of equipment by any entity other than
Individual RFC/SCN the Manufacturer (including but not limited to the Buyer)
The selection of individual items not covered by global for which provisions are made or which are post delivery
RFC/SCN is achieved via individual RFC/SCN. of the aircraft shall be made under the sole and full re-
Specific customer request sponsibility of the Buyer.
Items that are not mentioned in this Guide, or corre- The Buyer shall hold harmless and indemnify the Man-
sponding to a modified item, require specific customer ufacturer against any claims or/and damages related di-
requests. Such specific requests shall necessarily have rectly or indirectly to an incorrect installation of an
an impact in terms of lead times and resources and shall equipment or to such equipment itself, whether defec-
consequently lead to constraints and decisions that tive or not.

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00 General information A330-800/900
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8) Smoke and Toxicity requirements for the cabin

components

The Seller has defined requirements related to the

emission of smoke and toxic gases which exceed air-
worthiness requirements.
These requirements shall be fulfilled for the set of stan-
dard components defined by the Seller in his design di-
rective.

In addition, the Seller has listed other cabin components

which could potentially be subject to requirements relat-
ed to the emission of smoke and toxic gases, at the Buy-
er's request and subject to feasibility constraints to be
assessed by the Seller in terms of design, leadtime and
cost.

The Seller's directive documenting the subject sets of

standard cabin components and potential additional
components is referred to as ABD0031 and can be com-
municated on Buyer's request by the Seller's represen-
tative dealing with the cabin customization during the
aircraft definition process.

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A330-800/900 General information 00
Figure 00-1 - Typical page description

Chapter cover page Detailed description page

with a list of available items
ATA title and ATA number Option reference and title

Abbreviation, issue and date of the catalogue Page number Option reference

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 00 General information A330-800/900
Figure 00-2 - Example of technical solutions description table

• reference
• supplier
• PN (part numbers)
MWE: Manufacturer’s Weight Empty • quantity per TDU
OWE: Operating Weight Empty • status (BFE or SFE)
APL: Allowable Payload Change
Title of the technical
Technical solution Applicable Weights information Equipment
solution and optional
identifier (TDU) series per series information
remarks

Table 25-2 - Technical solutions description

TDU Title (Remarks) Appl. Weight (kg) Equipment Equipment Equipment QT Y STS
MW E/ OW E/ A P L referenc e supplier PN
Std Cockpit fourth occupant seat - A330-800 Seat, fourth occu- SAFRAN SEATS 1671220-00 1 SFE
A330-900
SAFRAN SEATS FRANCE, pant FRANCE
PN 1671220-00
01 Cockpit fourth occupant seat - A330-800 3.0/3.0/-3.0. Seat, fourth occu- SAFRAN SEATS 17702-00-00 1 SFE
A330-900 3.0/3.0/-3.0.
High comfort floor mounted pant FRANCE
seat - SAFRAN SEATS FRANCE,
PN 17702-00-00
A330-800 : Subject to certification
A330-900 : Subject to certification

Selection
Selection
condition
condition
remark

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00.00.302 - Glossary Systems

• A/C: Aircraft • ATSAW: Airborne Traffic Situational Awareness

• ABD: Airbus Directive and Procedure • ATSU: Air Traffic Service Unit
• ACARS: Aircraft Communication Addressing and • AVLC: Aviation VHF Link Control
Reporting System • AWL: Aircraft Wiring List
• ACD: Aircraft Control Domain • AWM: Aircraft Wiring Manual
• ACMS: Aircraft Condition Monitoring System
• ACP: Audio Control Panel • BAT: Battery
• ADF: Automatic Direction Finder • BFE: Buyer Furnished Equipment
• ADIRS: Air Data/Inertial Reference System • BGAN: Broadband Global Area Network
• ADIRU: Air Data/Inertial Reference Unit • BSCU: Braking and Steering Control Unit
• ADS: Automatic Dependent Surveillance • BSU: Beam Steering Unit
• AFM: Aircraft Flight Manual
• AGL: Above Ground Level • CAP: Customer Acceptance Presentation
• AIM: Aircraft Integrated Maintenance • CAPT: Captain
• AISD: Airline Information Services Domain • CAT: Commercial Air Transport
• ALNA: Aircraft Network Architecture • CCD: Cursor Control Device
• AMM: Aircraft Maintenance Manual • CCOM: Cabin Crew Operating Manual
• AMU: Audio Management Unit • CDF: Contractual Definition Freeze
• AOA: Angle Of Attack • CDL: Configuration Deviation List
• AOC: Airline Operational Communication • CDLS: Cockpit Door Locking System
• AOMT: Airbus Onboard Maintenance Tool • CDSS: Cockpit Door Surveillance System
• APL: Allowable Payload Change • CED: Cooling Effect Detector
• APU: Auxiliary Power Unit • CF: Chromate Free
• ARINC: Aeronautical Radio Incorporated • CG: Center of Gravity
• ASM: Aircraft Schematics Manual • CLS: Cargo Loading System
• ATA: Air Transport Association of America • CMC: Central Maintenance Computer
• ATC: Air Traffic Control • CMS: Central Maintenance System
• ATIS: Automatic Terminal Information System • CODD: Contractual On Dock Date

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• CPDLC: Controller-Pilot DataLink Communication • EPAC: Entity per Aircraft Change

• ESPM: Electrical Standard Practices Manual
• D/LNA: Diplexer/Low Noise Amplifier • ETOPS: Extended Range Twin Engined Aircraft Op-
• DAR: Digital ACMS Recorder erations
• DCL: Departure Clearance • EU-OPS: European Union Operations regulation
• DH: Decision Height
• DLCM: Data Loading & Configuration Manager • F/O: First Officer
• DMC: Display Management Computer • FAA: Federal Aviation Administration
• DME: Distance Measuring Equipment • FADEC: Full Authority Digital Engine Control
• DMU: Data Management Unit • FAL: Final Assembly Line
• DOW: Dry Operating Weight • FANS: Future Air Navigation System
• DU: Display Unit • FAP: Flight Attendant Panel
• FAR: Federal Aviation Regulations
• EAD: External Airline Documents • FCDC: Flight Control Data Concentrator
• EASA: European Aviation Safety Agency • FCMC: Fuel Control and Monitoring Computer
• ECAM: Electronic Centralized Aircraft Monitoring • FCOM: Flight Crew Operating Manual
• EFB: Electronic Flight Bag • FCTM: Flight Crew Training Manual
• EGPWC: Enhanced Ground Proximity • FCU: Flight Control Unit
Warning Computer • FDIMU: Flight Data Interface and Management Unit
• EGPWS: Enhanced Ground Proximity Warning Sys- • FDIU: Flight Data Interface Unit
tem • FLS: FMS Landing System
• EHS: Enhanced Surveillance • FM: Flight Management
• EIVMU: Engine Interface and Vibration Monitoring • FMGEC: Flight Management Guidance and Enve-
Unit lope Computer
• ELS: Elementary Surveillance • FMGES: Flight Management Guidance and Enve-
• ELT: Emergency Locator Transmitter lope System
• ELT-AF: Emergency Locator Transmitter - Automatic • FMS: Flight Management System
Fixed • FOCT: Flight Operations Consultation Tool

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• FOMAX: Flight Operations and Maintenance eX- • IATA: International Air Transport Association
change • ICAO: International Civil Aviation Organisation
• FTIS: Fuel Tank Inerting System • IDE: Instruments, Data, Equipment
• FWC: Flight Warning Computer • IDG: Integrated Drive Generator
• FWD: Forward • ILS: Instrument Landing System
• IPC: Illustrated Parts Catalog
• GAS: Ground Administration & servicing • ISA: International Standard Atmosphere
• GBAS: Ground Based Augmentation System • ISIS: Integrated Standby Instrument System
• GE: General Electric • ITP: In-Trail Procedure
• GLS: GBAS Landing System
• GPS: Global Positioning System • JAR: Joint Aviation Requirement
• GPRS: General Packet Radio Service
• GPWS: Ground Proximity Warning System • KU: Keyboard Unit
• GSM: Global System for Mobile communication
• GRU: Ground Refrigeration Unit • L/E: Leading Edge
• LAN: Local Area Network
• HDM: HSDU Data Module • LCD: Liquid Crystal Display
• HEPA: High Efficiency Particle Arrestor • LH: Left Hand
• HF: High Frequency • LNA: Low Noise Amplifier
• HFDR: High Frequency Data Radio • LOA: Letter Of Agreement
• HLD: HPA/LNA/Dip (Diplexer) • LP: Low Pressure
• HP: High Pressure • LPC: Less Paper in the Cockpit
• HPA: High Power Amplifier • LPO: Landing Per Overhaul
• HSE: Health, Safety and Environmental • LRU: Line Replaceable Unit
• HSD: High Speed Data
• HSDU: High Speed Data Unit • MCDU: Multipurpose Control and Display Unit
• HUD: Head-Up Display • MDA: Minimum Decision Altitude

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A330-800/900 General information 00
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• MDH: Minimum Descent Height

• MEL: Minimum Equipment List • P/B: Pushbutton
• MLG: Main Landing Gear • PA: Precision Approach
• MLW: Maximum design Landing Weight • PC: Personal Computer
• MMEL: Master Minimum Equipment List • PCMCIA: Personal Computer Memory Card Interna-
• MMR: Multi Mode Receiver tional Association
• MSCN: Manufacturer Specification Change Notice • PFD: Primary Flight Display
• MTOW: Maximum design Takeoff Weight • PFR: Post Flight Report
• MTW: Maximum Taxi Weight • PU: Processing Unit
• MVDR: Multiple VHF Data Radio • PW: Pratt and Whitney
• MWE: Manufacturer's Weight Empty • PWS: Predictive Windshear Detection System
• MZFW: Maximum design Zero Fuel Weight
• QAR: Quick Access Recorder
• ND: Navigation Module • QFE: Field Elevation Atmospheric Pressure
• NDB: Non-Directional Beacon • QNH: Sea Level Atmospheric Pressure
• NLG: Nose Landing Gear
• NOTAM: Notice to Airmen • RAAS: Runway Awareness and Advisory System
• NPA: Non Precision Approach • RAIM: Receiver Autonomous Integrity Monitoring
• NRA: Non Radar Airspace • RF: Radio Frequency
• NWS: Nose Wheel Steering • RFC: Request For Change
• RFU: Radio Frequency Unit
• OANC: Onboard Airport Navigation Computer • RFUIA: Radio Frequency Unit Interface Adapter
• OANS: Onboard Airport Navigation System • RH: Right Hand
• OCL: Oceanic Clearance Limit • RMP: Radio Management Panel
• OEB: Operation Engineering Bulletin • RNAV: Area Navigation
• OEI: One - Engine In - operative • RNP: Required Navigation Performance
• OPS: Operations • RR: Rolls Royce
• OWE: Operating Weight Empty

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00 General information A330-800/900
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• RTO: Rejected Takeoff • UBCF: Universal Brake Cooling Fans

• ULD: Unit Load Device
• SATCOM: Satellite Communication • UMTS: Universal Mobile Telecommunications Sys-
• SBB: Swift Broadband tem
• SCN: Specification Change Notice • USB: Universal Serial Bus
• SD: System Display • USPHSS: US Public Health Service Standards
• SDAC: System Data Acquisition Concentrator
• SDU: Satellite Data Unit • VDL: VHF Data Link
• SELCAL: Selective Calling System • VDR: VHF Data Radio
• SFE: Seller Furnished Equipment • VHF: Very High Frequency
• SIL: Service Information Letter • VLAN: Virtual Networks
• SOP: Standard Operating Procedure • VOC: Volatile Organic Compounds
• VOR: VHF Omnidirectional Range
• T3CAS: Traffic/Terrain Collision Avoidance System
• TAT: Total Air Temperature • WBM: Weight and Balance Manual
• TAWS: Terrain Awareness and Warning System • WCT: Wet Center Tank
• TBD: To be Determined • Wi-Fi: Wireless Fidelity
• TCAS: Traffic Alert and Collision Avoidance System • WV: Weight Variant
• TDU: Technical Description Unit • WXR: Weather Radar.
• TFU: Technical Follow-up
• THS: Trimmable Horizontal Stabilizer
• TOS: TakeOff Securing
• TOT: Transfer of Title
• TPIS: Tire Pressure Indicating System
• TSM: Trouble Shooting Manual
• TSO: Time Since Overhaul
• TWLU: Terminal Wireless LAN Unit

SCG Issue 3 Revision 2, January 2021 00.00.302 Page 14

A330-800/900 Certification - External livery 02

Reference Title
02.10.111 Environmental conditions - Cold weather protection
02.10.130 Tailwind operation at take-off beyond 10 knots
02.10.134 Certification - Airframe operational requirements
02.12.122 ETOPS beyond 180 minutes
02.40.101 External livery

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02 Certification - External livery A330-800/900
02.10.111 - Environmental conditions - Cold weather protection

Objective Function characteristics:

To provide protection to water lines and components • The heating system operates during flight and
susceptible to freezing during turnaround in low temper- ground operation of the aircraft.
ature conditions. • During ground operation, the system must be de-
pressurized in order to drain the water from the lava-
tories and galleys; by this action, also the water
Basic aircraft heaters in the lavatories and the air compressor are
The basic water/waste system is equipped with a freeze deactivated.
protection, which provides for proper system function in
flight. The Flight Crew Operating Manual (FCOM) supplemen-
tary techniques 3.04.91 Adverse weather and the Air-
Description craft Maintenance Manual (AMM) 12-31-00-001/
On ground for turnaround or prolonged parking with un- 12.31.38.201 Cold weather will have to be modified to
serviced systems in low temperature conditions, addi- reflect the change of procedure resulting from the mod-
tional protection will be installed on top of the basic ification.
freeze protection:
• the potable water lines and associated equipment
will be electrically heated by heating tapes or in-line
heaters and insulated with foam covers as required
• potable water tanks will be heated and insulated as
required
• additional depressurization valves will be installed
• an additional pushbutton with control light will be in-
stalled on the Flight Attendant Panel (FAP) for de-
pressurization valves actuation.

SCG Issue 3 Revision 2, January 2021 02.10.111 Page 16

A330-800/900 Certification - External livery 02
02.10.111 - Environmental conditions - Cold weather protection (Continued)

Note
No part of the toilet units, the water system, the controls
or servicing connections (depending on cabin layout)
shall freeze under the following conditions:
• max turnaround time 90 minutes inside of 10 hours
parking time
• all cargo doors open for 90 minutes
• one cabin door open for 90 minutes
• two additional cabin doors open for 30 minutes
• minimum ambient temperature: - 40°C
• maximum windspeed: 50 km/h
• water tanks containing any quantity up to full
• waste tanks containing any quantity up to full
• unconditioned air supplied through HP ground con-
nector or conditioned air supplied through LP ground
connector
• APU shut down
• external power supplied to the aircraft
• the water system depressurized.

The selection of this option could have repercussions

on cabin definition.

EPAC selection mode

Individual

SCG Issue 3 Revision 2, January 2021 02.10.111 Page 17

02 Certification - External livery A330-800/900
Table 02-1 - Technical solutions description
TDU Title (Remarks) Appl. Weight (kg) Equipment Equipment Equipment QTY STS
MWE/OWE/APL reference supplier PN

03 Environmental conditions - A/C A330-800 24.5/24.5/-24.5

on ground in cold weather A330-900 26.0/26.0/-26.0
(water depress. switch on FAP)

SCG Issue 3 Revision 2, January 2021 02.10.111 Page 18

A330-800/900 Certification - External livery 02

Intentionally left blank

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02 Certification - External livery A330-800/900
02.10.130 - Tailwind operation at take-off beyond 10 knots

Objective
To be able to conduct take-off with a tailwind component Note
up to 15 knots. Depending on the criticality of the engine inlet behavior
with tailwind, this may lead to a slower thrust application
Basic aircraft at take-off with possibly usage of a rolling take-off pro-
In the absence of specific flight tests, the usual interpre- cedure. Both effects may lead to take off distance pen-
tation of the current certification requirements is to limit alties and consequently aircraft gross weight penalties
the tailwind operations to a maximum component of for a given runway.
10 knots.
EPAC selection mode
Description Individual
The aircraft shall be certified for operations up to a max-
imum tailwind component of 15 knots. This condition
implies specific flight-test demonstrations under severe
conditions with 1.5 x the desired limit in terms of tail-
wind. Flight manual and flight crew operating manual
shall be updated accordingly.
The certification dossier for tailwind operations at take-
off shall include:
• additional handling qualities demonstrations in flight,
including justification/modifications (if necessary) of
the computer settings (angle of attack protection set-
tings, windshear warning...)
• additional engine behaviour justifications with tail-
wind, in particular in terms of engine inlet.

SCG Issue 3 Revision 2, January 2021 02.10.130 Page 20

A330-800/900 Certification - External livery 02
Table 02-2 - Technical solutions description
TDU Title (Remarks) Appl. Weight (kg) Equipment Equipment Equipment QTY STS
MWE/OWE/APL reference supplier PN

02 15 knots tailwind operations at A330-800 0.0/0.0/0.0

take-off (RR engines) A330-900 0.0/0.0/0.0

SCG Issue 3 Revision 2, January 2021 02.10.130 Page 21

02 Certification - External livery A330-800/900
02.10.134 - Certification - Airframe operational requirements

Objective Note
To provide, at aircraft delivery, compliance status report The operators are responsible to show to their national
against: operational Authority the compliance of their aircraft
• EU-OPS 1, subparts K and L with operational requirements. Airbus is providing help
• FAR 121, subparts J and K by raising a factual compliance review and cannot be re-
• EASA regulation on Air Operations, part CAT.IDE.A sponsible for the non-compliance, which may be identi-
(previously EU-OPS1 subpart K & L) and part SPA.
fied.
Basic aircraft
No status report. EPAC selection mode
Individual
Description
At aircraft delivery, a compliance status report shall be
provided against EU-OPS 1, Subparts K and L, and/or
FAR 121, subparts J and K and/or EASA regulation on
Air Operations, part CAT Subpart D (IDE) Section A.

SCG Issue 3 Revision 2, January 2021 02.10.134 Page 22

A330-800/900 Certification - External livery 02
Table 02-3 - Technical solutions description
TDU Title (Remarks) Appl. Weight (kg) Equipment Equipment Equipment QTY STS
MWE/OWE/APL reference supplier PN

16 Compliance status report for A330-800 0.0/0.0/0.0

FAR 121- subparts J and K A330-900 0.0/0.0/0.0
requirements

48 Compliance status report with A330-800 0.0/0.0/0.0

EASA regulation on Air Opera- A330-900 0.0/0.0/0.0
tions, Part-CAT.IDE.A and Part-
SPA

SCG Issue 3 Revision 2, January 2021 02.10.134 Page 23

02 Certification - External livery A330-800/900
02.12.122 - ETOPS beyond 180 minutes

Objective
To provide an ETOPS beyond 180 minutes capability to
the aircraft.

Basic aircraft
All Airbus A330 models are currently approved by
EASA and FAA for ETOPS up to 180 minutes opera-
tions.

Description
This modification consists in the extension of ETOPS
capability beyond 180 minutes with a diversion distance
up to 1700 NM. (1700 NM diversion distance objective
is equivalent to 240 minutes at the One Engine In-oper-
ative (OEI) speed, ISA, Still Air).

New routes, currently not operable with an ETOPS 180

minutes authority, will become possible over: South At-
lantic Ocean, Mid and South Pacific ocean, Mid Indian
Ocean.

EPAC selection mode

Individual

SCG Issue 3 Revision 2, January 2021 02.12.122 Page 24

A330-800/900 Certification - External livery 02
Table 02-4 - Technical solutions description
TDU Title (Remarks) Appl. Weight (kg) Equipment Equipment Equipment QTY STS
MWE/OWE/APL reference supplier PN

04 ETOPS up to 240 minutes A330-800 Negl./Negl./Negl.

A330-800 : Subject to certification A330-900 Negl./Negl./Negl.
A330-900 : Subject to certification

SCG Issue 3 Revision 2, January 2021 02.12.122 Page 25

02 Certification - External livery A330-800/900
02.40.101 - External livery

Objective • forward pylon fairings

To define and apply the customer livery. External livery • equipment details such as angle of attack sensor,
means fuselage, vertical stabilizer and nacelles. static ports, selected antennas, etc.
B) Customization process
Basic aircraft • An individual RFC shall be issued for 3D CAP (Cus-
The aircraft is delivered painted in white (fuselage, ver- tomer Acceptance Presentation) identification.
• Specific options are covered in ATA chapter 51.
tical stabilizer) and grey (wings, THS and nacelles). Ex- C) Livery complexity
terior markings are in English only. • The complexity of each external livery (design, paint
blending and/or fading, number of colors, product se-
Description lection...), can affect the paint production cycle. Con-
The aircraft fuselage, vertical stabilizer and nacelles sequently, each external livery is investigated on an
shall be painted according to the customer's livery as individual basis, and relevant terms and conditions
will be mentioned in the corresponding Specification
defined by: Change Notice (SCN).
• a 3D CAP (Customer Acceptance Presentation) pre- Nota: The rudder leading edge customization will be
pared by Airbus, based on customer's decorative in- covered through the external livery definition as re-
structions (electronic format) and with his approval
• painted color samples prepared by Airbus, based on quested by the customer.
customer's instruction (color references, samples). Please refer to "A330 Family External Painting guide-
lines" brochure for further details.
Note
A) Unpainted areas EPAC selection mode
Some metallic areas are and remain unpainted: Individual
• leading edges of slats
• engine intake lips and exhaust, parts of pylons
• scuff plates and horizontal stabilizer shield

SCG Issue 3 Revision 2, January 2021 02.40.101 Page 26

A330-800/900 Certification - External livery 02
Figure 02-1 - External livery
Grey M9001
Grey M9004 (upper wing coating)
White M8001
Metallic unpainted
Rolls Royce Trent 7000 nacelle

Rolls Royce Trent 7000 nacelle

A330-800/900 engines

Grey apron fairing (unpainted area)

Inboard

THS travel area

Outboard

Scuff-plates

Customized areas

A330-800/900 external painting A330-800/900 details A330-800/900 sharklets

SCG Issue 3 Revision 2, January 2021 02.40.101 Page 27

02 Certification - External livery A330-800/900
Table 02-5 - Technical solutions description
TDU Title (Remarks) Appl. Weight (kg) Equipment Equipment Equipment QTY STS
MWE/OWE/APL reference supplier PN

50 External Livery A330-800 Customized 3D TBD 1 SFE

A330-900
CAP

SCG Issue 3 Revision 2, January 2021 02.40.101 Page 28

A330-800/900 General aircraft design criteria 03

Reference Title
03.20.570 Alternate Forward Center of Gravity (AFCG) at take-off (A330-800)
03.20.571 Alternate Forward Center of Gravity (AFCG) at take-off (A330-900)
03.20.580 A330-841 Design weights
03.20.590 A330-941 Design weights

SCG Issue 3 Revision 2, January 2021 Page 29

03 General aircraft design criteria A330-800/900
03.20.570 - Alternate Forward Center of Gravity (AFCG) at take-off (A330-800)

Objective for A330-800

AFCG limits shall be certified to further improve the
A330 payload capability via take-off performance.

Description for A330-800

Considering a more aft forward CG limit (28% or 31%)
at take-off instead of max forward certified CG limit im-
plies some impacts on aircraft performance:
• Reduction of minimum take-off speeds,
• Better lift-over-drag ratio.
An AFCG position of 28% or 31% improves aircraft per-
formances at take-off overall.

EPAC selection mode

Individual

SCG Issue 3 Revision 2, January 2021 03.20.570 Page 30

A330-800/900 General aircraft design criteria 03
Table 03-1 - Technical solutions description
TDU Title (Remarks) Appl. Weight (kg) Equipment Equipment Equipment QTY STS
MWE/OWE/APL reference supplier PN

01 Certification of alternate for- A330-800 0.0/0.0/0.0

ward center of gravity on A330-
800 (28% MAC)
A330-800 : Subject to certification

02 Certification of alternate for- A330-800 0.0/0.0/0.0

ward center of gravity on A330-
800 (31% MAC)
A330-800 : Subject to certification

SCG Issue 3 Revision 2, January 2021 03.20.570 Page 31

03 General aircraft design criteria A330-800/900
03.20.571 - Alternate Forward Center of Gravity (AFCG) at take-off (A330-900)

Objective for A330-900

AFCG limits shall be certified to further improve the
A330 payload capability via take-off performance.

Description for A330-900

Considering a more aft forward CG limit (25% or 28%)
at take-off instead of max forward certified CG limit im-
plies some impacts on aircraft performance:
• Reduction of minimum take-off speeds,
• Better lift-over-drag ratio.
An AFCG position of 25% or 28% improves aircraft per-
formances at take-off overall.

EPAC selection mode

Individual

SCG Issue 3 Revision 2, January 2021 03.20.571 Page 32

A330-800/900 General aircraft design criteria 03
Table 03-2 - Technical solutions description
TDU Title (Remarks) Appl. Weight (kg) Equipment Equipment Equipment QTY STS
MWE/OWE/APL reference supplier PN

01 Certification of alternate for- A330-900 0.0/0.0/0.0

ward center of gravity on A330-
900 (25% MAC)
A330-900 : Subject to certification

02 Certification of alternate for- A330-900 0.0/0.0/0.0

ward center of gravity on A330-
900 (28% MAC)
A330-900 : Subject to certification

SCG Issue 3 Revision 2, January 2021 03.20.571 Page 33

03 General aircraft design criteria A330-800/900
03.20.580 - A330-841 Design weights

Objective for A330-800

To allow the customer to select predefined alternate de-
sign weights variants.

Basic aircraft for A330-800

The aircraft basic design weights (weight variant 800)
are as follows:
• Maximum Taxi Weight (MTW): 242 900 kg
• Maximum Takeoff Weight (MTOW): 242 000 kg
• Maximum Landing Weight (MLW): 186 000 kg
• Maximum Zero Fuel Weight (MZFW): from 172 000
kg to 176 000 kg.

Description for A330-800

The modification consists of:
• changes in the Weight and Balance Manual (WBM)
• modification of the CG diagram (a specific CG dia-
gram is associated with each aircraft Model/Variant)

EPAC selection mode

Individual

SCG Issue 3 Revision 2, January 2021 03.20.580 Page 34

A330-800/900 General aircraft design criteria 03
Figure 03-1 - Basic CG limits diagram for A330-800

For ATOW between 238 000 kg and 242 000 kg the MZFW is calculated as follows:
MZFW (kg) = 176 000 kg - (ATOW (kg) - 238 000 kg)

SCG Issue 3 Revision 2, January 2021 03.20.580 Page 35

03 General aircraft design criteria A330-800/900
Table 03-3 - Technical solutions description
TDU Title (Remarks) Appl. Weight (kg) Equipment Equipment Equipment QTY STS
MWE/OWE/APL reference supplier PN

Std Dynamic payload with MTOW A330-800

242 t, MLW 186 t, MZFW from
172 t to 176 t (WV 800)

01 A330-841 Alternate design A330-800 0.0/0.0/-4000.0

weights - MTOW 242 t, MLW
186 t, MZFW 172 t (WV 801)

02 A330-841 Alternate design A330-800 0.0/0.0/0.0

weights - MTOW 238 t, MLW
186 t, MZFW 176 t (WV 802)

03 A330-841 Alternate design A330-800 0.0/0.0/0.0

weights - MTOW 234 t, MLW
186 t, MZFW 176 t (WV 803)
A330-800 : Subject to certification

04 A330-841 Alternate design A330-800 0.0/0.0/0.0

weights - MTOW 230 t, MLW
186 t, MZFW 176 t (WV 804)
A330-800 : Subject to certification

05 A330-841 Alternate design A330-800

weights - MTOW 220 t, MLW
186 t, MZFW 176 t (WV 805)
A330-800 : Subject to certification

06 A330-841 Alternate design A330-800

weights - MTOW 215 t, MLW
186 t, MZFW 176 t (WV 806)
A330-800 : Subject to certification

SCG Issue 3 Revision 2, January 2021 03.20.580 Page 36

A330-800/900 General aircraft design criteria 03
TDU Title (Remarks) Appl. Weight (kg) Equipment Equipment Equipment QTY STS
MWE/OWE/APL reference supplier PN

07 A330-841 Alternate design A330-800

weights - MTOW 210 t, MLW
186 t, MZFW 176 t (WV 807)
A330-800 : Subject to certification

08 A330-841 Alternate design A330-800

weights - MTOW 205 t, MLW
186 t, MZFW 176 t (WV 808)
A330-800 : Subject to certification

09 A330-841 Alternate design A330-800

weights - MTOW 200 t, MLW
186 t, MZFW 176 t (WV 809)
A330-800 : Subject to certification

11 A330-841 Alternate design A330-800 0.0/0.0/-4000.0

weights - MTOW 245 t, MLW
186 t, MZFW 172 t (WV 811)
A330-800 : Subject to certification

20 Dynamic payload with MTOW A330-800

251 t, MLW 186 t, MZFW from
172 t to 176 t (WV 820)
A330-800 : Subject to certification

21 A330-841 Alternate design A330-800 0.0/0.0/-4000.0

weights - MTOW 251 t, MLW
186 t, MZFW 172 t (WV 821)
A330-800 : Subject to certification

22 A330-841 Alternate design A330-800 0.0/0.0/0.0

weights - MTOW 247 t, MLW
186 t, MZFW 176 t (WV 822)
A330-800 : Subject to certification

23 A330-841 Alternate design A330-800 0.0/0.0/-4000.0

weights - MTOW 247 t, MLW
186 t, MZFW 172 t (WV 823)
A330-800 : Subject to certification

SCG Issue 3 Revision 2, January 2021 03.20.580 Page 37

03 General aircraft design criteria A330-800/900
TDU Title (Remarks) Appl. Weight (kg) Equipment Equipment Equipment QTY STS
MWE/OWE/APL reference supplier PN

24 A330-841 Alternate design A330-800 0.0/0.0/0.0

weights - MTOW 245 t, MLW
186 t, MZFW 176 t (WV 824)
A330-800 : Subject to certification

25 A330-841 Alternate design A330-800 0.0/0.0/0.0

weights - MTOW 242 t, MLW
186 t, MZFW 176 t (WV 825)
A330-800 : Subject to certification

SCG Issue 3 Revision 2, January 2021 03.20.580 Page 38

A330-800/900 General aircraft design criteria 03

Intentionally left blank

SCG Issue 3 Revision 2, January 2021 03.20.580 Page 39

03 General aircraft design criteria A330-800/900
03.20.590 - A330-941 Design weights

Objective for A330-900

To allow the customer to select predefined alternate de-
sign weight variants.

Basic aircraft for A330-900

The aircraft basic design weights (weight variant 900)
are as follows:
• Maximum Taxi Weight (MTW): 242 900 kg
• Maximum Takeoff Weight (MTOW): 242 000 kg
• Maximum Landing Weight (MLW): 191 000 kg
• Maximum Zero Fuel Weight (MZFW): from 177 000
kg to 181 000 kg.

Description for A330-900

The modification consists of:
• changes in the Weight and Balance Manual (WBM)
• modification of the CG diagram (a specific CG dia-
gram is associated with each aircraft Model/Variant)

EPAC selection mode

Individual

SCG Issue 3 Revision 2, January 2021 03.20.590 Page 40

A330-800/900 General aircraft design criteria 03
Figure 03-2 - Basic CG limits diagram for A330-900

For ATOW between 238 000 kg and 242 000 kg the MZFW is calculated as follows:
MZFW (kg) = 181 000 kg - (ATOW (kg) - 238 000 kg)

SCG Issue 3 Revision 2, January 2021 03.20.590 Page 41

03 General aircraft design criteria A330-800/900
Table 03-4 - Technical solutions description
TDU Title (Remarks) Appl. Weight (kg) Equipment Equipment Equipment QTY STS
MWE/OWE/APL reference supplier PN

Std Dynamic payload with MTOW A330-900

242 t, MLW 191 t, MZFW from
177 t to 181 t (WV 900)

01 A330-941 Alternate design A330-900 0.0/0.0/-4000.0

weights - MTOW 242 t, MLW
191 t, MZFW 177 t (WV 901)

02 A330-941 Alternate design A330-900 0.0/0.0/0.0

weights - MTOW 238 t, MLW
191 t, MZFW 181 t (WV 902)

03 A330-941 Alternate design A330-900 0.0/0.0/0.0

weights - MTOW 234 t, MLW
191 t, MZFW 181 t (WV 903)
A330-900 : Subject to certification

04 A330-941 Alternate design A330-900 0.0/0.0/0.0

weights - MTOW 230 t, MLW
191 t, MZFW 181 t (WV 904)
A330-900 : Subject to certification

05 A330-941 Alternate design A330-900

weights - MTOW 220 t, MLW
191 t, MZFW 181 t (WV 905)
A330-900 : Subject to certification

06 A330-941 Alternate design A330-900

weights - MTOW 215 t, MLW
191 t, MZFW 181 t (WV 906)
A330-900 : Subject to certification

SCG Issue 3 Revision 2, January 2021 03.20.590 Page 42

A330-800/900 General aircraft design criteria 03
TDU Title (Remarks) Appl. Weight (kg) Equipment Equipment Equipment QTY STS
MWE/OWE/APL reference supplier PN

07 A330-941 Alternate design A330-900

weights - MTOW 210 t, MLW
191 t, MZFW 181 t (WV 907)
A330-900 : Subject to certification

08 A330-941 Alternate design A330-900

weights - MTOW 205 t, MLW
191 t, MZFW 181 t (WV 908)
A330-900 : Subject to certification

11 A330-941 Alternate design A330-900 0.0/0.0/-4000.0

weights - MTOW 245 t, MLW
191 t, MZFW 177 t (WV 911)
A330-900 : Subject to certification

20 Dynamic payload with MTOW A330-900

$2699600
251 t, MLW 191 t, MZFW from
177 t to 181 t (WV 920)

21 A330-941 Alternate design A330-900 0.0/0.0/-4000.0

weights - MTOW 251 t, MLW
191 t, MZFW 177 t (WV 921) $2445400
A330-900 : Subject to certification

22 A330-941 Alternate design A330-900 0.0/0.0/0.0

weights - MTOW 247 t, MLW
191 t, MZFW 181 t (WV 922) $2445400
A330-900 : Subject to certification

23 A330-941 Alternate design A330-900 0.0/0.0/-4000.0

weights - MTOW 247 t, MLW $1245600
191 t, MZFW 177 t (WV 923)
A330-900 : Subject to certification

24 A330-941 Alternate design A330-900 0.0/0.0/0.0

weights - MTOW 245 t, MLW
191 t, MZFW 181 t (WV 924) $1845500
A330-900 : Subject to certification

SCG Issue 3 Revision 2, January 2021 03.20.590 Page 43

03 General aircraft design criteria A330-800/900
TDU Title (Remarks) Appl. Weight (kg) Equipment Equipment Equipment QTY STS
MWE/OWE/APL reference supplier PN

25 A330-941 Alternate design A330-900 0.0/0.0/0.0

weights - MTOW 242 t, MLW
191 t, MZFW 181 t (WV 925) $946000
A330-900 : Subject to certification

SCG Issue 3 Revision 2, January 2021 03.20.590 Page 44

A330-800/900 Placards and markings 11

Reference Title
11.00.124 Installation of leasing plates
11.00.126 Installation of operator plate
11.20.130 Break in markings
11.20.200 Customization of exterior markings
11.35.100 Second language for lower deck cargo placards and signs
11.35.101 Weight indication in kg and lb for lower deck cargo compartments

SCG Issue 3 Revision 2, January 2021 Page 45

11 Placards and markings A330-800/900
11.00.124 - Installation of leasing plates

Objective Note
To install leasing plates in addition to the basic identifi- The text shall be provided by the customer to Airbus
cation plates on the aircraft to identify the leasing iden- contract administration as soon as available but not lat-
tity. er than 1 week before the ground check start.

Basic aircraft EPAC selection mode

"Manufacturer" and "Owner" plates are installed on the Individual
frame of the forward left hand passenger door.

A "SELCAL" plate is installed on the main instrument

panel.

Description
Leasing plates can be installed on the following posi-
tions, according to the customer requirements:
• on the cockpit rear partition just behind the third oc-
cupant seat
• and/or on each individual engine
• and/or on the APU
• and/or on the door frame of the forward left hand pas-
senger door, according to the customer require-
ments.

SCG Issue 3 Revision 2, January 2021 11.00.124 Page 46

A330-800/900 Placards and markings 11
Figure 11-1 - Location of additional leasing plates
STD: Manufacturer and Owner plates

Owner plate
Manufacturer plate

TDU 03: Leasing plate on cockpit rear partition

SCG Issue 3 Revision 2, January 2021 11.00.124 Page 47

11 Placards and markings A330-800/900
Figure 11-2 - Location of additional leasing plates

TDU 02: Leasing plate on forward LH passenger door TDU 04: Leasing plate on APU

Leasing plate locations

SCG Issue 3 Revision 2, January 2021 11.00.124 Page 48

A330-800/900 Placards and markings 11
Table 11-1 - Technical solutions description
TDU Title (Remarks) Appl. Weight (kg) Equipment Equipment Equipment QTY STS
MWE/OWE/APL reference supplier PN

01 Installation of leasing plate on A330-800 Negl./Negl./Negl.

engines A330-900 Negl./Negl./Negl.

02 Installation of leasing plate on A330-800 Negl./Negl./Negl.

forward LH passenger door A330-900 Negl./Negl./Negl.

03 Installation of leasing plate on A330-800 Negl./Negl./Negl.

cockpit rear partition A330-900 Negl./Negl./Negl.

04 Installation of leasing plate on A330-800 Negl./Negl./Negl.

APU A330-900 Negl./Negl./Negl.

SCG Issue 3 Revision 2, January 2021 11.00.124 Page 49

11 Placards and markings A330-800/900
11.00.126 - Installation of operator plate

Objective
To install, in addition to the basic identification plates,
operator plate on the aircraft to identify the operator.

Basic aircraft
"Manufacturer" and "Owner" plates are installed on the
frame of the forward left hand passenger door.

A "SELCAL" plate is installed on the main instrument

panel.

Description
Operator plate is installed on the door frame of the for-
ward left hand passenger door, according to the cus-
tomer requirements.

EPAC selection mode

Individual

SCG Issue 3 Revision 2, January 2021 11.00.126 Page 50

A330-800/900 Placards and markings 11
Table 11-2 - Technical solutions description
TDU Title (Remarks) Appl. Weight (kg) Equipment Equipment Equipment QTY STS
MWE/OWE/APL reference supplier PN

01 Installation of operator plate A330-800 Negl./Negl./Negl.

on forward LH passenger door A330-900 Negl./Negl./Negl.

SCG Issue 3 Revision 2, January 2021 11.00.126 Page 51

11 Placards and markings A330-800/900
11.20.130 - Break in markings

Objective
To enable rescue personnel to cut through the fuselage
structure with minimum obstruction/hindrance during
rescue operation.

Basic aircraft
None.

Description
The break in markings are applied around a cabin win-
dow on the outer LH and RH side fuselage including the
English wording "CUT HERE IN EMERGENCY".
Three marking sets are applied on each side.

Note
The location depends on the interior monument posi-
tioning.

Please refer to "A330 External Painting guidelines" bro-

chure for further details.

EPAC selection mode

Individual

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A330-800/900 Placards and markings 11
Table 11-3 - Technical solutions description
TDU Title (Remarks) Appl. Weight (kg) Equipment Equipment Equipment QTY STS
MWE/OWE/APL reference supplier PN

01 Break in markings A330-800 Negl./Negl./Negl.

A330-900 Negl./Negl./Negl.

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11 Placards and markings A330-800/900
11.20.200 - Customization of exterior markings

Objective Note
To provide translation in a second language for selected Markings and standard English text cannot be modified.
exterior markings (text). No additional text or translation can be done for picto-
grams.
Basic aircraft
Exterior placards and markings for operating or servic- EPAC selection mode
ing instructions and safety precautions are provided as Individual
pictograms, wherever possible, or in English as defined
in the external placards and markings brochure.

Description
A second language is applied on selected exterior
markings as per external markings definition document
which includes Customer's translations.
Appropriate translations, compliant with Airworthiness
Authorities requirements when mandatory, must be
supplied by the customer.

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A330-800/900 Placards and markings 11
Table 11-4 - Technical solutions description
TDU Title (Remarks) Appl. Weight (kg) Equipment Equipment Equipment QTY STS
MWE/OWE/APL reference supplier PN

01 Customization of exterior A330-800 Negl./Negl./Negl. Exterior markings TBD TBD SFE

markings according to Mark- A330-900 Negl./Negl./Negl.
definition document
ings Definition Document

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11 Placards and markings A330-800/900
11.35.100 - Second language for lower deck cargo placards and signs

Objective Note
To further enhance the readability of the placards and The translation of the English wording into the language
signs in the lower deck cargo compartments, the used nominated by the customer, shall be provided by the
wording will be bilingual. That is beside the basic word- customer (electronic data file and/or high quality full size
ing in English, the text shall be shown in an additional printout).
second language that is to be defined by the customer.
EPAC selection mode
Basic aircraft Individual
The basic language used on the placards and signs in
the lower deck cargo compartments is English.

Description
The description on the placards and signs that are posi-
tioned in the lower deck cargo compartments shall be
bilingual.

The basic applied wording in English shall be positioned

above or below the wording in the additional second lan-
guage (that is to be defined by the customer).

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A330-800/900 Placards and markings 11
Table 11-5 - Technical solutions description
TDU Title (Remarks) Appl. Weight (kg) Equipment Equipment Equipment QTY STS
MWE/OWE/APL reference supplier PN

01 Second language for lower A330-800 Negl./Negl./Negl. Second language TBD TBD SFE
deck cargo placards and signs A330-900 Negl./Negl./Negl.
(English above)

21 Second language for lower A330-800 Negl./Negl./Negl. Second language TBD TBD SFE
deck cargo placards and signs A330-900 Negl./Negl./Negl.
(English below)

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11 Placards and markings A330-800/900
11.35.101 - Weight indication in kg and lb for lower deck cargo compartments

Objective
To indicate maximum permitted weight for the lower
deck cargo compartments in kg and lb.

Basic aircraft
Placards in the lower deck cargo compartments indicate
the maximum weight permitted in kg.

Description
The modification consists in replacing the basic lower
deck cargo compartments placards by new ones with
weights indicated in kg and lb.

EPAC selection mode

Individual

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A330-800/900 Placards and markings 11
Figure 11-3 - Weight indications for lower deck cargo compartments
: Space for indication in lb
FWD Cargo compartment AFT Cargo compartment BULK Cargo compartment

CARGO LOADING CARGO LOADING CARGO LOADING

39 26 20 65 57 53 73 65
1 4 3 2 COMP.5
COMP. 2 COMP. 1 COMP. 4 COMP. 3
26 RL 25 RL 24 RL 23 RL 22 RL 21 RL 13 RL 12 RL 11 RL 43 RL 42 RL 41 RL 34 RL 33 RL 32 RL 31 RL
24P 23P 22P 21P 12P 11P 42P 41P 33P 32P 31P
SECT 53 SECT 52
AD

MAX. ALLOWABLE LOADS MAX. ALLOWABLE LOADS

MAX. COMPARTMENT LOAD MAX. COMPARTMENT LOAD
COMP.1+2 COMP.3+4 SECT
51

22861 KG 18507 KG
MAX. POSITION LOAD MAX. POSITION LOAD MAX. ALLOWABLE LOADS
NAS 3610 - 2K, - 2L UNITS NAS 3610 - 2K, - 2L UNITS
26 L 25 L 24 L 23 L 22 L 21 L 13 L 12 L 11 L 43 L 42 L 41 L 34 L 33 L 32 L 31 L MAX. COMP. MAX.GROSS WEIGHT
26 R 25 R 24 R 23 R 22 R 21 R 13 R 12 R 11 R 43 R 42 R 41 R 34 R 33 R 32 R 31 R LOAD 51 52 53
K - SIZE : 1587 KG K - SIZE : 1587 KG 3468KG 339KG 1413KG 1716KG
BULK
L - SIZE : 3174 KG L - SIZE : 3174 KG
MAX. POSITION LOAD MAX. POSITION LOAD MAX. FLOOR LOAD 732 KG/SQM
NAS 3610 - 2A, - 2M UNITS NAS 3610 - 2A, - 2M UNITS
24 P 23 P 22 P 21 P 12 P 11 P 42 P 41 P 33 P 32 P 31 P FOR PERMISSIBLE UNIT LOAD DEVICES AND LOADING
LIMITATIONS REFER TO WEIGHT AND BALANCE MANUAL
A - SIZE : 4626 KG A - SIZE : 4626 KG 10 F255 72103 204
M - SIZE : 5103 KG M - SIZE : 5103 KG

MAX. CONTOUR: F MAX. CONTOUR: F

Note: A330-900 shown
FOR PERMISSIBLE UNIT LOAD DEVICES AND LOADING FOR PERMISSIBLE UNIT LOAD DEVICES AND LOADING
LIMITATIONS REFER TO WEIGHT AND BALANCE MANUAL LIMITATIONS REFER TO WEIGHT AND BALANCE MANUAL to illustrate principle
10 F255 72100 200 10 F255 72100 202

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11 Placards and markings A330-800/900
Table 11-6 - Technical solutions description
TDU Title (Remarks) Appl. Weight (kg) Equipment Equipment Equipment QTY STS
MWE/OWE/APL reference supplier PN

Std Basic weight indication in kg in A330-800

lower deck cargo compart- A330-900
ments

01 Weight indication in kg and lb A330-800 Negl./Negl./Negl.

for lower deck cargo compart- A330-900 Negl./Negl./Negl.
ments

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A330-800/900 Air conditioning 21

Reference Title
21.20.110 Cabin air recirculation filter cartridge alternate equipment
21.22.105 Installation of electrical heaters for side window air outlets in cockpit
21.28.100 Installation of lower deck aft cargo compartment ventilation system
21.28.101 Installation of lower deck aft cargo compartment ventilation system with increased cool-
ing
21.28.105 Installation of lower deck fwd cargo compartment ventilation system and temperature
control
21.28.107 Installation of on-ground ventilation system for lower deck bulk and forward cargo com-
partments
21.70.102 Ozone catalytic converters alternate equipment

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21 Air conditioning A330-800/900
21.20.110 - Cabin air recirculation filter cartridge alternate equipment

Objective
To provide alternate equipment to the existing recircula-
tion filter elements.

Basic aircraft
High Efficiency Particle Arrestor (HEPA) filter elements
are installed in the cabin air recirculation system.

Description
The modification consists in installing alternate HEPA
type recirculation filter elements in the cabin air recircu-
lation system.

In addition, HEPA type recirculation filter elements are

available with the ability to remove odors from the recir-
culated cabin air.

EPAC selection mode

Individual

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A330-800/900 Air conditioning 21
Figure 21-1 - Recirculation filters

Aft
recirculation filter cartridges

Forward
recirculation
filter cartridges

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21 Air conditioning A330-800/900
Table 21-1 - Technical solutions description
TDU Title (Remarks) Appl. Weight (kg) Equipment Equipment Equipment QTY STS
MWE/OWE/APL reference supplier PN

Std Basic particle filter element - A330-800 Recirculation filter PALL- GMBH QB0408-01 8 SFE
PALL-GMBH, PN QB0408-01 A330-900
element

04 Particle and odors filter ele- A330-800 17.0/17.0/-17.0 Recirculation filter PALL- GMBH QB0434-02 8 SFE
ment - PALL-GMBH, PN A330-900 17.0/17.0/-17.0
element
QB0434-02
Recirculation filter with the ability to
remove odours from recirculated air

06 Particle filter element - LE A330-800 Negl./Negl./Negl. Recirculation filter LE BOZEC 430B100-3 8 SFE
BOZEC, PN 430B100-3 A330-900 Negl./Negl./Negl.
element

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A330-800/900 Air conditioning 21

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21 Air conditioning A330-800/900
21.22.105 - Installation of electrical heaters for side window air outlets in cockpit

Objective
To provide additional heating for cockpit side window air The heaters are equipped with thermostats, which reg-
outlet to improve the pilots' comfort. ulate the airflow temperature to an approximate maxi-
mum of 50 °C (122 °F).
Basic aircraft
Outside air directly from the packs mixed with hot air en- In case of failure of the thermostats, an overheat safety
ters the cockpit through fixed and adjustable outlets. switch limits the temperature to approximately 90 °C
Temperature control is achieved via the overhead panel (194 °F).
rotary selector.
EPAC selection mode
Description Individual
The modification consists in installing, in the cockpit,
two modified side window air outlets, which include
electrical heaters.

Two selector switches installed on the overhead panel

provide captain and first officer heating and power se-
lection (high = 200 Watts or low = 100 Watts). In case
both air conditioning units are shut-off the heaters are
deactivated. When the flow of conditioned air is normal
(both air conditioning units working, the flow of each
side window air outlet is 8 g/s), the heaters can raise the
temperature by 25 °C (77 °F) in high setting and 12.5 °C
(55 °F) in low setting (maximum values).

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A330-800/900 Air conditioning 21
Figure 21-2 - Electrical heaters for side window air outlets
Side Ground Flow control valve
C3 windows C9 (Air conditioning compt)
(115 VAC) 511
HB
512
HB

115 VAC
FC FC
NFC NFC

P=100 WATTS
4
Cockpit HE P=200 WATTS
Crew selector
(225 VU)
Side
Electrical
window Cockpit air supply
heaters
outlets

Cap
3 HIGH LOW

t
HE

Control box OFF

F/O
HIGH LOW

Added switches

HEATER HEATER
CAPT F/O

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21 Air conditioning A330-800/900
Table 21-2 - Technical solutions description
TDU Title (Remarks) Appl. Weight (kg) Equipment Equipment Equipment QTY STS
MWE/OWE/APL reference supplier PN

03 Installation of electrical heat- A330-800 2.0/2.0/-2.0 Electrical heater SAFRAN RCO200A00 2 SFE
ers for side window air outlets A330-900 2.0/2.0/-2.0
VENTILATION
in cockpit - SAFRAN, PN SYSTEMS
RCO200A00

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A330-800/900 Air conditioning 21

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21 Air conditioning A330-800/900
21.28.100 - Installation of lower deck aft cargo compartment ventilation system

Objective The isolation valves can be shut off simultaneously by a

To increase utilization of the aft cargo compartment by pushbutton switch on the cockpit overhead panel. In the
ventilation (perishable goods transportation). event of smoke detection, the isolation valves are auto-
matically closed and the extraction fan is switched off.
Basic aircraft
• no ventilation (Class C) The nominal ventilation flow shall be:
• under steady state conditions, the mean in-flight tem-
perature of compartment air shall be maintained be- • 290 l/s (614.5 cu ft/min) for A330-800
tween 2°C and 30°C (36°F and 86°F) • 350 l/s (752 cu ft/min) for A330-900.
• space provision for ventilation system.
Note
Description Cargo compartment remains Class C.
The ventilation system is based on air suction provided
by an extraction fan. EPAC selection mode
Individual
Air drawn from the underfloor area enters the cargo
compartment via two isolation valves and air vents on
the right hand side.

Air is extracted on the left-hand side of the compartment

through air vents and discharged by the fan via an iso-
lation valve and a 'piccolo tube' type ducting into the
bilge towards the outflow valve.

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A330-800/900 Air conditioning 21
Figure 21-3 - Aft cargo compartment ventilation

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21 Air conditioning A330-800/900
Table 21-3 - Technical solutions description
TDU Title (Remarks) Appl. Weight (kg) Equipment Equipment Equipment QTY STS
MWE/OWE/APL reference supplier PN

05 Installation of lower deck aft A330-800 60.0/60.0/-60.0 Fan, extraction DIEHL AVIATION VD3820-01 1 SFE
cargo compartment ventilation A330-900 42.0/42.0/-42.0
system (A330)
Isolation valve NORD MICRO 4063-18221 3 SFE

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21 Air conditioning A330-800/900
21.28.101 - Installation of lower deck aft cargo compartment ventilation system with
increased cooling
Objective Note
To increase utilization of the lower deck aft cargo com- • The deletion of bilge area warming by extracted air of
partment by ventilation (perishable goods transporta- the cargo compartment results in lower temperatures
tion) and reduction of the air temperature. of the aft cargo floor panels when compared to the
option Ventilation system.
• Due to the fixed flow split, calibrated by restrictors, a
Basic aircraft temperature control is not possible. The maximum
• no ventilation (Class C) cooling performance will be reached in flight.
• under steady conditions the mean in-flight tempera- • Cargo compartment remains Class C.
ture of the air shall be maintained between 2°C and
30°C (36°F and 86°F) EPAC selection mode
• space provision for ventilation system. Individual
Description
To reduce temperature in the lower deck aft cargo com-
partment in flight, this option installs ventilation (as per
item 21.28.100 - Installation of aft cargo compartment
ventilation system) plus the following:
Additional cold air is taken upstream of the isolation
valves from the bilge area. The flow split is fixed by re-
strictors located in the ducts of the air intakes. The air
extraction is also modified so that the cargo compart-
ment exhaust is directed adjacent to the aft outflow
valve.

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A330-800/900 Air conditioning 21
Figure 21-4 - Aft cargo compartment ventilation/cooling system
292 294
HN HN
Cabin
underfloor air

Isolation Aft cargo door

valves

Exhaust air directed

adjacent to the aft
Aft cargo compartment outflow valve

Additional air intakes Aft outflow valve

in bilge area

Cargo control panel

C56

Extraction fan
Cabin ambient
291 air intake
HN Isolation valve
293
HN

Floor insulation

Bilge air
intake

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21 Air conditioning A330-800/900
Table 21-4 - Technical solutions description
TDU Title (Remarks) Appl. Weight (kg) Equipment Equipment Equipment QTY STS
MWE/OWE/APL reference supplier PN

03 Installation of aft cargo com- A330-800 65.0/65.0/-65.0 Fan, extraction DIEHL AVIATION VD3820-01 1 SFE
partment ventilation system A330-900 53.0/53.0/-53.0
with increased cooling (A330)
Isolation valve NORD MICRO 4063-18221 3 SFE

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A330-800/900 Air conditioning 21

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21 Air conditioning A330-800/900
21.28.105 - Installation of lower deck fwd cargo compartment ventilation system and
temperature control
Objective Temperature control is provided on top of the ventilation
To increase utilization of the forward cargo compart- by adding:
ment (live animals and perishable goods transporta- • cold air from the packs controlled by a cold air 3-po-
tion). sition valve
• hot air from hot air manifold controlled by a hot air
Basic aircraft valve (all aircraft).
• no ventilation (Class C)
• under steady state conditions the mean in-flight tem- The fan and the valves are controlled by the ventilation
perature of compartment air shall be maintained be- controller.
tween 2 °C and 30 °C (36 °F and 86 °F)
• space provisions for ventilation and temperature con- In the event of smoke detection, the isolation valves,
trol systems.
Trim Air Valve, Cold Air Valve are automatically closed
Description and the extraction fan is switched "OFF".
Ventilation system is based on air suction provided by
an extraction fan. The temperature in the forward cargo compartment is
controlled by a cockpit temperature selector (all aircraft)
Air drawn from the underfloor area enters the cargo and a cockpit cooling mode selector.
compartment via two isolation valves and air vents lo-
cated in the left hand side wall and ceiling. It is possible to select temperatures within the range of
5 °C and 25 °C (41 °F and 77 °F). The nominal ventila-
Air is extracted on the right hand side through air vents tion flow is 620 l/s (1 314 cu ft/min).
and discharged by the fan via an isolation valve into the
bilge towards the forward outflow valve. Achieved temperature will depend on cargo loading and
outside conditions.

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A330-800/900 Air conditioning 21
21.28.105 - Installation of lower deck fwd cargo compartment ventilation system and
temperature control (Continued)

The isolation valves can be shut off simultaneously by a

pushbutton switch on the cockpit overhead panel.

Following actions are required:

• packs selected "ON" and operative
• respective Isolation Valve P/B selected "ON "
• respective Temperature Selector not selected "OFF".

In case cargo compartment door is not fully closed, the

trim air valve will be shut off automatically. The ventila-
tion Controller shall give a fixed Duct Demand to the
Pack Controller so that open cargo door does not lead
to an excessive low Pack Demand. The extraction is
running as well.

Electronic Centralized Aircraft Monitoring (ECAM) indi-

cation is affected.

Note
Cargo compartment remains Class C.

EPAC selection mode

Individual

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21 Air conditioning A330-800/900
Figure 21-5 - Forward cargo compartment temperature control

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A330-800/900 Air conditioning 21
Table 21-5 - Technical solutions description
TDU Title (Remarks) Appl. Weight (kg) Equipment Equipment Equipment QTY STS
MWE/OWE/APL reference supplier PN

09 Installation of lower deck fwd A330-800 123.0/123.0/-123.0 Cold air valve NORD MICRO 4063-18204- 1 SFE
cargo compartment ventilation A330-900 140.0/140.0/-140.0
XX
system and temp control
(A330) Cooling mode I.E.C 058-003-00 1 SFE
selector ELECTRONIQUE
Isolation valve NORD MICRO 4063-18221 3 SFE

Temperature LIEBHERR 777B0000-XX 1 SFE

selector AEROSPACE
TOULOUSE
Temperature LIEBHERR 764A0000-XX 3 SFE
sensor AEROSPACE
TOULOUSE
Trim air valve LIEBHERR 1320A0000- 1 SFE
AEROSPACE XX
TOULOUSE
Two speed DIEHL AVIATION VA 4110 1 SFE
extraction fan

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21 Air conditioning A330-800/900
21.28.107 - Installation of on-ground ventilation system for lower deck bulk and
forward cargo compartments
Objective Lower deck forward cargo compartment:
To ensure proper ventilation in the lower deck bulk and The modification is the same as item 21.28.105 - Instal-
forward cargo compartments during ground time when lation of lower deck forward cargo compartment ventila-
respective cargo doors are opened. tion and temperature control system.

Basic aircraft Nevertheless, the following aircraft conditions and activ-

• no ventilation in lower deck forward cargo compart- ities are necessary:
ment
• lower deck bulk cargo compartment is provided with • packs running
a ventilation and heating system activated from the • forward cooling selector in cockpit overhead panel in
cockpit "NORM" position.
• space provision.
This has to be integrated into the cargo compartment
Description ground operating manual.
Lower deck bulk cargo compartment:
The basic fan heaters can be controlled by an ON/OFF Note
switch on the compartment servicing panel in order to Requires prior installation of item: 21.28.105/09 - Instal-
activate the blowing function when the aircraft is on lation of lower deck fwd cargo compartment ventilation
ground and the cargo compartment door is fully open. system and temp control (A330).
The heating function is deactivated in this operation.
EPAC selection mode
For safety reasons, the blowing function will be auto- Individual
matically switched OFF when the bulk door is not fully
open.

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A330-800/900 Air conditioning 21
Figure 21-6 - Bulk and forward cargo compartment ventilation on ground
5026VE

Ambient temperature sensor ON ON

OFF OFF

Forward cargo door CARGO

COMPT LIGHT
BLOWER
FAN

Isolation Extraction
valve fan
Wall outlets
Ceiling inlets Ceiling inlets ON/OFF switch
115V AC on compartment
10A service panel

INTERPHONE
Lower inlets

Isolation
Isolation Bulk cargo Extraction valve
valves door fan
Lower duct
Cabin temperature
underfloor air Compartment
sensor temperature
Upper duct sensor
temperature
sensor Curtain
Cabin extracted
Hot air air from above Bulk cargo compartment
valve of cargo ceiling
Hot air from Fan heater
hot air manifold

Cold air
valve Isolation Duct temperature
valve sensor
Cold air
from packs
Forward cargo Bulk cargo
compartment compartment

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21 Air conditioning A330-800/900
Table 21-6 - Technical solutions description
TDU Title (Remarks) Appl. Weight (kg) Equipment Equipment Equipment QTY STS
MWE/OWE/APL reference supplier PN

02 Installation of on-ground venti- A330-800 23.6/23.6/-23.6

lation system for bulk and for- A330-900 23.6/23.6/-23.6
ward cargo compartment
(A330)

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A330-800/900 Air conditioning 21

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21 Air conditioning A330-800/900
21.70.102 - Ozone catalytic converters alternate equipment

Objective
To reduce the amount of Volatile Organic Compounds
(VOC) in the cabin, in addition to the basic function,
while on ground and taxiing.

Basic aircraft
Two catalytic ozone converters are provided to reduce
the level of ozone in the passenger compartment.

Description
Two combined VOC / ozone catalytic converters shall
be provided to reduce the level of ozone and VOC in the
pressurized area of the fuselage.

EPAC selection mode

Individual

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A330-800/900 Air conditioning 21
Table 21-7 - Technical solutions description
TDU Title (Remarks) Appl. Weight (kg) Equipment Equipment Equipment QTY STS
MWE/OWE/APL reference supplier PN

Std Ozone catalytic converters - A330-800 Ozone catalytic BASF 40997003 2 SFE
BASF CORPORATION, PN A330-900
converter CORPORATION
40997003

03 Combined VOC/ozone catalytic A330-800 1.7/1.7/-1.7 Catalytic VOC/ BASF 44142002 2 SFE
converters alternate equip- A330-900 1.7/1.7/-1.7
ozone converter CORPORATION
ment - BASF CORPORATION,
PN 44142002
VOC: Volatile Organic Compounds.

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 A330-800/900

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A330-800/900 Auto flight 22

Reference Title
22.10.200 AP/FD TCAS function
22.70.152 FMS alternate equipment
22.70.200 CDA function
22.70.230 Activation Take-Off Surveillance 2 function (TOS 2)
22.81.102 QNH/QFE baro setting
22.83.120 Soft go-around function

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22 Auto flight A330-800/900
22.10.200 - AP/FD TCAS function

Objective Note
Auto Pilot could remain engaged in case of TCAS Alert. AP/FD TCAS activation does not modify TCAS Algo-
rithm Software.
Basic aircraft In case of mixed fleet, with and without AP/FD TCAS,
In case of TCAS alert, flight crew are requested by Stan- crew can quickly determine aircraft configuration by
dard Operational Procedure to disengage Auto Pilot monitoring the mode 'TCAS' displayed in blue in the
and switch off Flight Director in order to fly manually FMA.
TCAS order.
EPAC selection mode
Description Individual
With AP/FD TCAS, upon TCAS Traffic Advisory, 'TCAS'
Vertical Guidance Mode is armed. This guidance mode
controls the vertical speed (V/S) on a target acquired
from TCAS. Without any flight crew action, Auto Pilot
will follow the TCAS order and fly the optimum profile. If
Auto Pilot is not engaged, Flight Director will be auto-
matically displayed on the Primary Flight Display in or-
der to help the crew to fly the profile manually.

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A330-800/900 Auto flight 22
Figure 22-1 - AP/FD TCAS function

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22 Auto flight A330-800/900
Table 22-1 - Technical solutions description
TDU Title (Remarks) Appl. Weight (kg) Equipment Equipment Equipment QTY STS
MWE/OWE/APL reference supplier PN

01 Activation of AP/FD TCAS A330-800 Negl./Negl./Negl.

function A330-900 Negl./Negl./Negl.

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A330-800/900 Auto flight 22

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22 Auto flight A330-800/900
22.70.152 - FMS alternate equipment

Objective The FMS Thales kit included in PN C13176HBxx is cov-

To offer alternate supplier for FMS. ering the obsolescence linked to PN C13164HAxx and
C13176HAxx. It does not affect computers already pro-
Basic aircraft duced as a pool of components have been secured for
One FMS kit (HONEYWELL) is installed in each maintenance and repair.
FMGEC (2 per aircraft) and three LCD MCDU are in-
stalled on the center pedestal.
EPAC selection mode
Description Individual
Alternate FM kit is installed in each FMGEC. When
FMS Thales is selected, the associated LCD MCDU are
also replaced (3 per aircraft).

Note
While being mechanically, electrically interchangeable
and functionally equivalent, mixing of equipment from
different suppliers is not possible. The mixability be-
tween hardware equipment from the same FMS suppli-
er is also not possible

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A330-800/900 Auto flight 22
Figure 22-2 - FMS alternate equipment

FM 1 IND RDY FM 2

TAKE OFF
V1 FLP RETR RWY
153 F=144 33L
FM 1 IND
VR
RDY
SLT RETRFM 2 TO SHIFT
154 S= 182 [M] [ ]*
V2 CLEAN FLAPS/THS
FROM GA1
UTC
158 SPD/ALTO=213 2/UP2.5
TRANS ALT DRT TO - FLEX TO
LFBO33L 1705 5000 / 510 F49
H325° BRG325º 0NM
THR RED/ACC ENG OUT ACC
900 1705 FM 2 168/ 900
C325° TRK325º2000/2000 3 2000
FM 1 IND RDY

TOU NEXT
1708 226/ 2480
MAINTENANCE MENU 1/1
LMG3B 10 PHASE >
OSKAM 1718 250/ FL099
< FLIGHT REPORT ----------------------
(SPD) PRINT * 9 BRT
(LIM) 1718 250/ FL100
DEST UTCDIR PROG
DIST PERF
EFOB INIT DATA
OFF
LFPO25 1815PRINT * 363
RAD 11.1
FUEL SEC ATC
< AVIONIC STATUS ------------------------ F-PLN NAV PRED F-PLN MCDU
COMM MENU
AIR BRT
PORT
DIR PROG PERF INIT DATA A B C D E
OFF
RAD F FUEL SEC
F-PLN NAV A PRED F-PLN
ATC
COMM
F G
MCDU H I J M
C
MENU
I D
AIR
PORT
L K L M N O U

F A1 B2 BRT3
C D E M
E
DIR PROG PERF INIT M DATA P Q R S T N

FMGEC FMGEC F4 GOFF

5 H6 U
F
RAD A FUEL SEC ATC
I J M
C
F-PLN NAV I PRED F-PLN COMM7 MCDU
8 U V WD X Y
AIR
L K LMENU M9 N O U
1 2 3 Z SPME
OVFY
PORT
F
A B C 0 / CLR
M
4 5 6
PD QE R S T N
U
F F G H UI VJ WMC X Y
A
I
7 8 9 D
L K L M ZN O/ SPU OVFY CLR
1 2 3 0 M
F E
M
4 5 6
P Q R S T N
U

7 8 9 U V W X Y
OVFY
0 Z / SP CLR

FMS card FMS card LCD MCDU

SCG Issue 3 Revision 2, January 2021 22.70.152 Page 95

22 Auto flight A330-800/900
Table 22-2 - Technical solutions description
TDU Title (Remarks) Appl. Weight (kg) Equipment Equipment Equipment QTY STS
MWE/OWE/APL reference supplier PN

Std FMS Release 2 (Genepi/P6H6A) A330-800 Flight Management THALES C13226HA10 2 SFE
and MCDU - HONEYWELL A330-900
Guidance & AVIONICS SA
A330-800 : Subject to certification
A330-900 : Subject to certification
Envelope Computer
(FMGEC)
FMS operational HONEYWELL PS4087700- 2 SFE
software INC. 908
Multipurpose HONEYWELL D50A000-100 2 SFE
Control and Display INC.
Unit (MCDU)
21 FMS Release 2 (Genepi/ A330-800 Negl./Negl./Negl. Flight Management THALES C13176HB10 2 SFE
T6AH6A HW4) and MCDU alter- A330-900 Negl./Negl./Negl.
Guidance & AVIONICS SA
nate eqpt - THALES AVIONICS/ Envelope Computer
SMITHS (FMGEC)
A330-800 : Subject to certification
A330-900 : Subject to certification
FMS operational THALES G2604AAJ03 2 SFE
software AVIONICS S.A. /
SMITHS
Multipurpose THALES C19266EA01 3 SFE
Control and Display AVIONICS SA
Unit (MCDU)

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A330-800/900 Auto flight 22

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22 Auto flight A330-800/900
22.70.200 - CDA function

Objective
Continuous Descent Approach (CDA) activates inside Note
the Flight Management System, another method to Only available with Honeywell FMS Release 2.
compute the vertical profile from cruise level to final ap-
proach. EPAC selection mode
Individual
Basic aircraft
Flight Management System computes speed decelera-
tion using a level-off segment. It may lead to additional
thrust usage to maintain this level-off.

Description
This function is activated by Operational Program Con-
figuration (OPC) update inside the FMS.
CDA will compute a continuous descent profile from
Top of Descent down to Final Approach and use idle
thrust segment as much as possible. It will not predict
anymore level-off segment for Deceleration but still fol-
low Limitation contained in the Navigation Database.
CDA also computes two new pseudo-waypoints FLAP1
and FLAP2, to help flight crew to extend flap configura-
tion at the best moment.
Flight crew will still be able to select the appropriate de-
scent mode to achieve unscheduled ATC request.

SCG Issue 3 Revision 2, January 2021 22.70.200 Page 98

A330-800/900 Auto flight 22
Figure 22-3 - Continuous Descent Approach function

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22 Auto flight A330-800/900
Table 22-3 - Technical solutions description
TDU Title (Remarks) Appl. Weight (kg) Equipment Equipment Equipment QTY STS
MWE/OWE/APL reference supplier PN

02 Activation of CDA Function A330-800 Negl./Negl./Negl.

A330-800 : Subject to certification A330-900 Negl./Negl./Negl.

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A330-800/900 Auto flight 22

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22 Auto flight A330-800/900
22.70.230 - Activation Take-Off Surveillance 2 function (TOS 2)

Objective Operators are required to order from their Navigation

To compute the available runway distance for take-off Database Provider, an NDB compliant with ARINC
and warn flight crew in case of length to short. 424R22. NDB includes 'airport data validity check' field.
Without this field set to TRUE, TOS2 function will not
Basic aircraft run.
None.
EPAC selection mode
Description Individual
TOS2 enhances take-off security by computing dis-
tance for take-off and check current aircraft position.
TOS2 introduces following ECAM alerts:
• T.O RWY TOO SHORT
• NAV NOT ON FMS RUNWAY
• NAV ON TAXIWAY.
An inhibition push button is installed in the overhead
panel to deactivate the function.
It uses data stored in the Navigation DataBase which
shall include accuracy compliance parameters. Opera-
tors shall order to their Data Service Provider.

Note
TOS2 requires prior installation of FMS release 2 Tha-
les (T6) or Honeywell (P6).

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A330-800/900 Auto flight 22
Table 22-4 - Technical solutions description
TDU Title (Remarks) Appl. Weight (kg) Equipment Equipment Equipment QTY STS
MWE/OWE/APL reference supplier PN

01 Activation Take-Off Surveil- A330-800 Negl./Negl./Negl.

lance 2 function (TOS 2) A330-900 Negl./Negl./Negl.
A330-800 : Subject to certification

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22 Auto flight A330-800/900
22.81.102 - QNH/QFE baro setting

Objective Whatever is the pilot selection (QFE or QNH), the mini-

Air data information to be based on field elevation atmo- mum descent altitude shall be defined on the LCD
spheric pressure QFE. MCDU and displayed on PFD as a Minimum Decision
Height (MDH). This entails pin programming of FCU,
Basic aircraft FMGEC, DMC and GPWS.
Possibility to select STD or QNH.
The basic air data information is based on sea level at- EPAC selection mode
mospheric pressure QNH. Individual

Description
The modification consists in making the FMGEC capa-
ble of recognizing whether the baro setting is based on
QNH or on QFE. The QNH/QFE mode is selected by
pressing the baro setting knob (PFD control panel) once
or twice from the STD position. The reference value is
then set by rotating the knob; the corresponding setting
(QFE or QNH) is displayed on the PFD.

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A330-800/900 Auto flight 22
Figure 22-4 - QNH/QFE baro setting
Settings display
Reference value selection MAN SRS RWY 1 FD 2
FLX +49 CLB NAV
Mode selection 5000
A/THR

158 010
153
060
10 10
Rotating the knob 040 40
in Hg h Pa
5 20
Pull PULL has no effect 00
STD

2
STD 000

STD
0 31 32 33 34 3

MAN SRS RWY 1 FD 2

FLX +49 CLB NAV A/THR

5000
158 010
153
060
10 10

Rotate the knob 040 40

in Hg h Pa
5 20
Push PULL
00
STD
once
2 000

QNH QNH 1020

0 31 32 33 34 3

MAN SRS RWY 1 FD 2

FLX +49 CLB NAV A/THR

5000
158 010
153
060
10 10

Rotate the knob 040 40

in Hg h Pa
5 20
Push PULL
00
STD
again
2 000

QFE 0 31 32 33 34 3
QFE 1004

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22 Auto flight A330-800/900
Table 22-5 - Technical solutions description
TDU Title (Remarks) Appl. Weight (kg) Equipment Equipment Equipment QTY STS
MWE/OWE/APL reference supplier PN

01 QNH/QFE Baro setting A330-800 0.0/0.0/0.0

A330-900 0.0/0.0/0.0

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A330-800/900 Auto flight 22

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22 Auto flight A330-800/900
22.83.120 - Soft go-around function

Objective Note
To optimize fuel burn during Go-Around phase and re- Full Thrust is always available by setting the lever to
duce spatial disorientation. TOGA.

Basic aircraft EPAC selection mode

In Go-Around phase, Thrust setting is always set to TO- Individual
GA.

Description
Standard Operation does not require maximum thrust
for all Go-Around manoeuvres. They are performed in
very different conditions (aircraft weight, speed, alti-
tude…). Soft Go Around is a new thrust mode available
during the Go-Around phase and activated by setting
back the Thrust lever to FLX/MCT.
Soft Go-Around allows the flight crew to easily adapt the
thrust setting to the actual operational conditions in or-
der to reduce also flight crew workload.

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A330-800/900 Auto flight 22
Figure 22-5 - Soft Go-Around function

TOGA

FLX/MCT

SOFT
GO-AROUND GO-AROUND

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22 Auto flight A330-800/900
Table 22-6 - Technical solutions description
TDU Title (Remarks) Appl. Weight (kg) Equipment Equipment Equipment QTY STS
MWE/OWE/APL reference supplier PN

01 Activation of soft go-around A330-800 Negl./Negl./Negl.

function A330-900 Negl./Negl./Negl.

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A330-800/900 Communications 23

Reference Title
23.00.103 Fixed Emergency Locator Transmitter (ELT) alternate equipment (BFE)
23.11.110 Activation of High Frequency datalink function
23.11.161 Single High Frequency Data Radio (HFDR) alternate equipment
23.11.162 Installation of dual High Frequency Data Radio (HFDR) system
23.28.113 High rate SATCOM - AERO H+ avionics equipment selection
23.28.121 Antenna subsystem
23.28.169 Provision for HONEYWELL SBB SATCOM
23.28.172 Installation of high speed SATCOM - Swift Broadband (432 kb/s per channel)
23.28.180 Installation of Iridium SATCOM system
23.28.190 Installation of Inmarsat Light Cockpit SATCOM (LCS) system
23.50.120 System provisions for active noise cancelling boomsets
23.50.126 Boomsets alternate equipment
23.50.144 Installation of headsets
23.51.101 Installation of an Audio Control Panel (ACP) and jack panel in avionics compartment
23.51.103 Installation of an Audio Control Panel (ACP) and jack panel for 4th occupant
23.70.110 Installation of Cockpit Door Surveillance System (CDSS)

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23 Communications A330-800/900
Reference Title
23.81.105 Radio Management Panel (RMP) functions

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A330-800/900 Communications 23

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23 Communications A330-800/900
23.00.103 - Fixed Emergency Locator Transmitter (ELT) alternate equipment (BFE)

Objective Note
To provide alternate vendor for the ELT Automatic It is the operator's responsibility to provide programming
Fixed (ELT-AF). data to the ELT supplier and Airbus at least six weeks
before equipment CODD (Contractual On Dock Date).
The ELT-AF, in compliance with EUROCAE-ED-62, is
designed to improve search and rescue by automatical- EPAC selection mode
ly activating (through a G-switch), in the event of an Individual
emergency.

Basic aircraft
An Emergency Locator Transmitter (ELT) shall be in-
stalled in the rear passenger compartment ceiling. A re-
mote control panel facility shall be installed in the
cockpit. It shall comprise a guarded switch and a light.

Description
- Installation of an ELT (BFE) capable of emitting a dis-
tress signal on the following international standard dis-
tress frequencies:
• 121.5, 243.0 and 406.0 MHz for ECA and THALES
ELTs.
• 121.5 and 406.0 MHz for the HONEYWELL option.
- Installation of a remote control panel in the cockpit.

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A330-800/900 Communications 23
Figure 23-1 - ELT installation

C66 C67 C70

ELT antenna

ELT
support

ELT remote control panel

ELT remote control

C67
C66

Note: A330-900 shown to illustrate principle

Ground horn

Connection to the ground horn to warn of any intempestive transmission.

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23 Communications A330-800/900
Figure 23-2 - Emergency Locator Transmitter (ELT)

ELT remote control panel ELT with back up antenna and Navigation interface

TDU 03 - ECA

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A330-800/900 Communications 23
Figure 23-3 - Emergency Locator Transmitter (ELT)

ELT remote control panel ELT bracket

Programming dongle

ELT transmitter unit (406 AF Integra)

TDU 12 - THALES AVIONICS SA

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23 Communications A330-800/900
Figure 23-4 - Emergency Locator Transmitter (ELT)

ELT remote control panel ELT transmitter unit (406 AFN2) Aircraft Identification Module 2 (AIM2)
with navigation capabilities

TDU 25 - HONEYWELL ASCA

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A330-800/900 Communications 23
Table 23-1 - Technical solutions description
TDU Title (Remarks) Appl. Weight (kg) Equipment Equipment Equipment QTY STS
MWE/OWE/APL reference supplier PN

03 Automatic ELT with remote A330-800 1.0/2.6/-2.6 Back up antenna ECA 02N64070 1 BFE
control panel in cockpit & NAV A330-900 1.1/2.7/-2.7
AEROSPACE
interface - ECA AEROSPACE
(with add. prov.) Emergency Locator ECA 01N65902 1 BFE
Capable to transmit the last aircraft GPS
position (lat, long). Transmitter (ELT) AEROSPACE
Navigation interface ECA 01N65930 1 BFE
AEROSPACE
Remote control ECA 93N6035 1 BFE
panel AEROSPACE
12 Automatic ELT (406 AF Integra) A330-800 2.0/2.0/-2.0 Emergency Locator THALES S1851501-01 1 BFE
with programming dongle and A330-900 2.0/2.0/-2.0
Transmitter (ELT) AVIONICS SA
remote control panel - THALES
AVIONICS Emergency Locator THALES S1840502-02 1 BFE
Capable to transmit the last aircraft GPS
position (lat, long) Transmitter (ELT) AVIONICS SA
bracket
Programming THALES S1820514-07 1 BFE
dongle AVIONICS SA
Remote control THALES S1820513-15 1 BFE
panel AVIONICS SA
25 Automatic ELT (406 AFN2) with A330-800 2.5/2.5/-2.5 Aircraft HONEYWELL 51090136-1 1 BFE
remote control panel in cockpit A330-900 2.5/2.5/-2.5
Identification ASCA INC
& nav. capabilities - HONEY- Module (AIM2)
WELL (AIM2)
Capable to transmit the last aircraft GPS
position (lat, long) Emergency Locator HONEYWELL 51090130-2 1 BFE
With the navigation data interface inte- Transmitter (ELT) ASCA INC
grated in the ELT AFN2.
DO227A compliant (EASA CRI F-GEN-01
and FAA IP SE-1014). Remote control HONEYWELL 1153008-1 1 BFE
panel ASCA INC

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23 Communications A330-800/900
23.11.110 - Activation of High Frequency datalink function

Objective
To provide High Frequency datalink activation over HF
Data Radio (HFDR).

Basic aircraft
One HFDR system (transceiver and coupler) is in-
stalled. The ACARS function is provided by the ATSU.

Description
The High Frequency (HF) datalink function shall be ac-
tivated by the pin programming of SDAC and CMC.

Note
Single network provider: ARINC.

EPAC selection mode

Individual

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A330-800/900 Communications 23
Table 23-2 - Technical solutions description
TDU Title (Remarks) Appl. Weight (kg) Equipment Equipment Equipment QTY STS
MWE/OWE/APL reference supplier PN

07 Activation of HF datalink func- A330-800 Negl./Negl./Negl.

tion for HFDR1 on Fans config- A330-900 Negl./Negl./Negl.
urations

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23 Communications A330-800/900
23.11.161 - Single High Frequency Data Radio (HFDR) alternate equipment

Objective
To provide alternate HFDR equipment, with datalink ca-
pability.

Basic aircraft
One HFDR system (transceiver and coupler) is in-
stalled.

Description
To replace the basic HFDR system (transceiver and
coupler) by alternate equipment.

Note
Single network provider: ARINC.

EPAC selection mode

Individual

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A330-800/900 Communications 23
Table 23-3 - Technical solutions description
TDU Title (Remarks) Appl. Weight (kg) Equipment Equipment Equipment QTY STS
MWE/OWE/APL reference supplier PN

Std Single High Frequency Data A330-800 HFDR antenna ROCKWELL 822-0987-003 1 SFE
Radio (HFDR) system - ROCK- A330-900
coupler COLLINS
WELL COLLINS 900D series
HFDR transceiver ROCKWELL 822-0990-003 1 SFE
COLLINS
02 Single High Frequency Data A330-800 Negl./Negl./Negl. HFDR antenna HONEYWELL 964-0453-001 1 SFE
Radio (HFDR) system - HON- A330-900 Negl./Negl./Negl.
coupler INC. REDMOND,
EYWELL OLATHE
HFDR transceiver HONEYWELL 964-0452-052 1 SFE
INC. REDMOND,
OLATHE

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23 Communications A330-800/900
23.11.162 - Installation of dual High Frequency Data Radio (HFDR) system

Objective
To install a dual HFDR system.

Basic aircraft
One HFDR system (transceiver and coupler) is in-
stalled.

Description
To replace the basic single HFDR system by a dual
HFDR system.

Note
Single network provider: ARINC.

EPAC selection mode

Individual

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A330-800/900 Communications 23
Table 23-4 - Technical solutions description
TDU Title (Remarks) Appl. Weight (kg) Equipment Equipment Equipment QTY STS
MWE/OWE/APL reference supplier PN

01 Installation of dual High Fre- A330-800 12.5/12.5/-12.5 HFDR antenna ROCKWELL 822-0987-003 2 SFE
quency Data Radio (HFDR) A330-900 12.5/12.5/-12.5
coupler COLLINS
system - ROCKWELL COLLINS
900D series HFDR transceiver ROCKWELL 822-0990-003 2 SFE
COLLINS
02 Installation of dual High Fre- A330-800 13.0/13.0/-13.0 HFDR antenna HONEYWELL 964-0453-001 2 SFE
quency Data Radio (HFDR) A330-900 13.0/13.0/-13.0
coupler INC. REDMOND,
system - HONEYWELL OLATHE
HFDR transceiver HONEYWELL 964-0452-052 2 SFE
INC. REDMOND,
OLATHE

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23 Communications A330-800/900
23.28.113 - High rate SATCOM - AERO H+ avionics equipment selection

Objective
To allow selection of avionics sub-system required for Note
SATCOM operations. The SATCOM cockpit voice function is available over
the North Atlantic area under Immarsat
Basic aircraft satellites coverage.
An avionics sub-system (BFE) for a satellite communi-
cation system generally in accordance with ARINC 741 EPAC selection mode
shall be installed. Individual

Description
The single high rate SATCOM is a transmission system
that allows the airlines to perform applications such as:
• cabin and cockpit voice communication mainly as a
telephone
• narrow band data transmission for cockpit (datalink,
FANS) and cabin.
No redundancy is provided with this architecture; the
failure of one of the SATCOM components (avionics/an-
tennas) will lead to total loss of the SATCOM system.
The modification consists of:
• installation of Satellite Data Unit (SDU)
• installation of Radio Frequency Unit (RFU)
• installation of High Power Amplifier (HPA)
• activation of the SATCOM voice for ATC (Air Traffic
Control) routines.

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A330-800/900 Communications 23
Figure 23-5 - High rate SATCOM avionics
Top mounted
high gain antenna

HPA D/LNA

SDU RFU
BSU

Avionics rack
800VU

Top-mounted installation

Cockpit Data

SDU RFU

BSU

Cabin Voice
and Data
HPA D/LNA ANTENNA

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23 Communications A330-800/900
Table 23-5 - Technical solutions description
TDU Title (Remarks) Appl. Weight (kg) Equipment Equipment Equipment QTY STS
MWE/OWE/APL reference supplier PN

03 High rate SATCOM avionics A330-800 1.5/1.5/-1.5 CD-SATCOM SDU HONEYWELL HNI47200008 1 BFE
MCS7200 (7 ch. - AERO H+) A330-900 1.5/1.5/-1.5
INC. PHOENIX, 9902
with RFUIA - SDU PN 7516118- MINNEAPOLIS
77145 - HONEYWELL
CD-SATCOM SDU HONEYWELL HNI4F200009 1 BFE
OPERATIONAL INC. PHOENIX, 1903
PROGRAM MINNEAPOLIS
High Power HONEYWELL 7520000- 1 BFE
Amplifier (HPA) INC. PHOENIX, 20140
MINNEAPOLIS
Radio Frequency HONEYWELL 7516222-901 1 BFE
Unit (RFU) INC. PHOENIX,
MINNEAPOLIS
Satellite Data Unit HONEYWELL 7516118- 1 BFE
(SDU) INC. PHOENIX, 77145
MINNEAPOLIS

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A330-800/900 Communications 23

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23 Communications A330-800/900
23.28.121 - Antenna subsystem

Objective
To install an alternate high gain top-mounted SATCOM
antenna subsystem.

Basic aircraft
An antenna subsystem full SBB capable in accordance
with ARINC 741 is installed.

Description
The system consists in the installation of:
• One High Gain top mounted Antenna capable of
SBB (SwiftBroadband) with radome on an adapter
plate on the top of the forward fuselage.
• One Beam Steering Unit (BSU).
• One Diplexer/Low Noise Amplifier (D/LNA) type F
(capable of SBB) close to the antenna.

EPAC selection mode

Individual

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A330-800/900 Communications 23
Table 23-6 - Technical solutions description
TDU Title (Remarks) Appl. Weight (kg) Equipment Equipment Equipment QTY STS
MWE/OWE/APL reference supplier PN

Std Installation of High Gain SBB A330-800 Adapter plate COBHAM 6051-80-99 1 SFE
SATCOM Antenna - COBHAM A330-900
(Chelton/omnipless)
Diplexer Low Noise COBHAM 5044-89-99 1 SFE
Amplifier (D/LNA)
Feeder COBHAM 6059-89-99 1 SFE

High Gain Antenna COBHAM 4141-89-99 1 SFE

(HGA)
02 SATCOM antenna subsystem A330-800 -3.0/-3.0/3.0 Adapter plate CMC 100-602221- 1 SFE
full SBB capability (antenna A330-900 -3.0/-3.0/3.0
ELECTRONICS 000
and D/LNA) INC.
Beam Steering Unit CMC 100-602199- 1 SFE
(BSU) ELECTRONICS 002
INC.
D/LNA CMC 100-602200- 1 SFE
ELECTRONICS 004
INC.
High Gain Antenna CMC 100-602198- 1 SFE
(HGA) ELECTRONICS 003
INC.

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23 Communications A330-800/900
23.28.169 - Provision for HONEYWELL SBB SATCOM

Objective
To provide provisions for HONEYWELL HS720 HSD
SATCOM providing 2 SBB channels (2 x 432 kb/s).

Basic aircraft
A SATCOM AERO H+ system, generally in accordance
with ARINC 741, is installed.

Description
The modification consists in installing provisions for the
AeroH+/ HSD (High Speed Data) SATCOM provided by
Honeywell. It implies:
• to adapt the RFUIA (Radio Frequency Unit Interface
Adaptor) wiring to fit with the Honeywell HSDU (High
Speed Data Unit)
• to install bus/discrete wiring and pin programming
provisions.

EPAC selection mode

Individual

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A330-800/900 Communications 23
Table 23-7 - Technical solutions description
TDU Title (Remarks) Appl. Weight (kg) Equipment Equipment Equipment QTY STS
MWE/OWE/APL reference supplier PN

02 Provision of high speed data A330-800 0.4/0.4/-0.4

SATCOM - HONEYWELL HS720 A330-900 0.4/0.4/-0.4

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23 Communications A330-800/900
23.28.172 - Installation of high speed SATCOM - Swift Broadband (432 kb/s per
channel)
Objective Note
To provide two high speed Swift Broadband channels The SATCOM cockpit voice function is available over
(2 x 432 kb/s) and to connect the Flight Operations and the North Atlantic area under Inmarsat
Maintenance eXchange (FOMAX) system. satellites coverage.

Basic aircraft The Honeywell SBB SATCOM requires prior accep-

A SATCOM AERO H+ system, generally in accordance tance of 23.28.169/02 - Provision of high speed data
with ARINC 741, is installed. SATCOM - HONEYWELL HS720.

Description EPAC selection mode

The installation consists in: Individual
• replacing basic SATCOM equipment by Swift Broad-
band capable SATCOM equipment providing two
high speed Swift Broadband channels (2 x 432 kb/s)
in addition to classical aeronautical services (cockpit
and cabin voice channels, cockpit narrow band data
channel for ACARS transmissions)
• connecting the FOMAX.

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A330-800/900 Communications 23
Table 23-8 - Technical solutions description
TDU Title (Remarks) Appl. Weight (kg) Equipment Equipment Equipment QTY STS
MWE/OWE/APL reference supplier PN

05 Installation of SBB Satcom A330-800 22.5/22.5/-22.5 CD-SATCOM SDU HONEYWELL HNI47200008 1 BFE
with connection to FOMAX - A330-900 22.5/22.5/-22.5
INC. PHOENIX, 9902
Honeywell (-77145) MINNEAPOLIS
CD-SATCOM SDU HONEYWELL HNI4F200009 1 BFE
OPERATIONAL INC. PHOENIX, 1903
PROGRAM MINNEAPOLIS
High Power HONEYWELL 7520000- 1 BFE
Amplifier (HPA) INC. PHOENIX, 20140
MINNEAPOLIS
High Speed Data HONEYWELL 7520061- 1 BFE
Unit (HSDU) INC. PHOENIX, 34017
MINNEAPOLIS
HSDU Data Module HONEYWELL 7520033-901 1 BFE
(HDM) INC. PHOENIX,
MINNEAPOLIS
Satellite Data Unit HONEYWELL 7516118- 1 BFE
(SDU) INC. PHOENIX, 77145
MINNEAPOLIS

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23 Communications A330-800/900
23.28.180 - Installation of Iridium SATCOM system

Objective
To install a Iridium SATCOM system in replacement
of basic Aero H+ SATCOM system.

Basic aircraft
A SATCOM AERO H+ system, generally in accordance
with ARINC 741, is installed.

Description
The system consists in the installation of:
• one Satellite Data Unit (SDU),
• one Satellite Control Module (SCM),
• one Iridium antenna.

The basic Inmarsat antenna is removed accordingly.

EPAC selection mode

Individual

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A330-800/900 Communications 23
Table 23-9 - Technical solutions description
TDU Title (Remarks) Appl. Weight (kg) Equipment Equipment Equipment QTY STS
MWE/OWE/APL reference supplier PN

02 Installation of Iridium SATCOM A330-800 -45.0/-45.0/45.0 Iridium antenna L3 009E5733-00 1 SFE

system (with data channel acti- A330-900 -45.0/-45.0/45.0
COMMUNICATIO
vated) NS
Satellite Data Unit L3 228E5733-00 1 SFE
(SDU) COMMUNICATIO
NS
SDU Configuration L3 418E5733-00 1 SFE
Module (SCM) COMMUNICATIO
NS

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23 Communications A330-800/900
23.28.190 - Installation of Inmarsat Light Cockpit SATCOM (LCS) system

Objective • The maximum throughput reachable via the LCS

To install an Inmarsat Light Cockpit SATCOM in re- channel is 200kbps. However, the actual bandwidth
placement of basic Aero H+ SATCOM System. is under the Customer responsibility and shall be
contracted as part of the Service Level Agreement
with the selected service provider.
Basic aircraft
A SATCOM AERO H+ system, generally in accordance
EPAC selection mode
with ARINC 741, is installed. Individual

Description
The system consists in the installation of:
• two MCU (Modular Concept Unit) Compact Satellite
Data Unit (CSDU)
• One SDU Configuration Module (SCM)
• One Antenna HELGA including HPA and D/LNA.
The basic Inmarsat antenna is removed accordingly.

Note
• The Inmarsat light cockpit SATCOM is compatible
with the Inmarsat's SwiftBroadband Safety services
(SB-S). The customer shall contract the relevant ser-
vice level agreement with a service provider.
• The Inmarsat classic aero services are no longer
supported by the Inmarsat light cockpit SATCOM.

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A330-800/900 Communications 23
Table 23-10 - Technical solutions description
TDU Title (Remarks) Appl. Weight (kg) Equipment Equipment Equipment QTY STS
MWE/OWE/APL reference supplier PN

01 Installation of Inmarsat Light A330-800 5.0/5.0/-5.0 Low Gain Antenna COBHAM 405005-00000 1 SFE
Cockpit SATCOM (Single chan- A330-900 5.0/5.0/-5.0
(LGA)
nel)
A330-800 : Subject to certification
A330-900 : Subject to certification Satellite Data Unit COBHAM 405045-00001 1 SFE

SDU Configuration COBHAM 405055-00000 1 SFE

Module

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23 Communications A330-800/900
23.50.120 - System provisions for active noise cancelling boomsets

Objective
To provide system provisions for installation of active
noise cancelling boomsets.

Basic aircraft
None.

Description
System provisions (including all necessary wiring) are
made to accomodate active noise cancelling boomsets
with XLR-5 plug.
The required power supply shall be 28V DC, +28 V DC
on Pin 5 and earth (together with Audio Lo) on Pin 2.
This modification consists in adapting the wiring be-
tween the AMU and Captain, First Officer and third oc-
cupant boomset receptacle (XLR-5 plug) in order to be
able to install active noise cancelling boomsets.

EPAC selection mode

Individual

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A330-800/900 Communications 23
Table 23-11 - Technical solutions description
TDU Title (Remarks) Appl. Weight (kg) Equipment Equipment Equipment QTY STS
MWE/OWE/APL reference supplier PN

01 System provisions for active A330-800 Negl./Negl./Negl.

noise cancelling boomsets A330-900 Negl./Negl./Negl.

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23 Communications A330-800/900
23.50.126 - Boomsets alternate equipment

Objective Note
To provide alternate vendors for boomsets. In case of OMTS (On-Board Mobile Telephony
System) in cabin, Airbus recommends to select an al-
Basic aircraft ternate boomset compliant with EUROCAE ED-130
• Three boomsets. standard.
• Jack panel (boomset and handmike connector,
headset jack) for captain, 1st officer, 3rd occupant.
• Headset jack for 4th occupant. EPAC selection mode
Individual
Description
The basic boomsets are replaced by alternate equip-
ment, which have to be compliant with ARINC 535A and
538B specification.

The boomset plugs shall be ITT common type XLR-5-

12-C or equivalent.

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A330-800/900 Communications 23
Figure 23-6 - Boomsets location

4th occupant
console

3rd occupant
console

4th occupant
Jack panel

3rd occupant
Jack panel

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23 Communications A330-800/900
Table 23-12 - Technical solutions description
TDU Title (Remarks) Appl. Weight (kg) Equipment Equipment Equipment QTY STS
MWE/OWE/APL reference supplier PN

Std Boomsets basic equipment - A330-800 Boomset HOLMBERG 1046GT2102A 3 SFE

HOLMBERG, PN A330-900
Y
1046GT2102AY
ElectroMagnetic Interferences (EMI) sus-
ceptible

37 Installation of active noise can- A330-800 Negl./Negl./Negl. Boomset FACTEM 245038971-01 3 SFE
celling boomsets FACTEM type A330-900 Negl./Negl./Negl.
FL20-IA, PN 245038971-01

39 Installation of boomsets A330-800 Negl./Negl./Negl. Boomset FACTEM 245038968-01 3 SFE

FACTEM type FL20-P, PN A330-900 Negl./Negl./Negl.
245038968-01

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A330-800/900 Communications 23

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23 Communications A330-800/900
23.50.144 - Installation of headsets

Objective
To allow the 4th occupant to listen to communications
selected on the 3rd occupant Audio Control Panel
(ACP).

Basic aircraft
• Three boomsets.
• Jack panel (boomset and handmike connector,
headset jack) for captain, 1st officer and 3rd occu-
pant.
• Headset jack for 4th occupant.

Description
Installation of headset for 4th occupant in the RH aft
console.

Note
The headset plugs shall be PJ 055 or equivalent.

EPAC selection mode

Individual

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A330-800/900 Communications 23
Figure 23-7 - Headset installation for fourth occupant

4th occupant
console

3rd occupant
console
HEAD SET

4th occupant
Jack panel

Jack panel

3rd occupant
Jack panel

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23 Communications A330-800/900
Table 23-13 - Technical solutions description
TDU Title (Remarks) Appl. Weight (kg) Equipment Equipment Equipment QTY STS
MWE/OWE/APL reference supplier PN

14 Installation of headset for A330-800 Negl./Negl./Negl. Headset FACTEM 245039019-01 1 SFE

fourth occupant - FACTEM A330-900 Negl./Negl./Negl.
FL20-L, PN245039019-01

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A330-800/900 Communications 23

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23 Communications A330-800/900
23.51.101 - Installation of an Audio Control Panel (ACP) and jack panel in avionics
compartment
Objective
To provide an additional audio facility in the avionics
compartment for maintenance purposes.

Basic aircraft
Three ACP are installed in the cockpit. Service inter-
phone jack and system provision for an additional ACP
are installed in the avionics compartment.

Description
The modification consists in installing a digital ACP and
jack panel (on the existing provisions) in the avionics
compartment.

Note
The basic AMU will be kept.

EPAC selection mode

Individual

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A330-800/900 Communications 23
Figure 23-8 - ACP and jack panel in avionics compartment

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23 Communications A330-800/900
Table 23-14 - Technical solutions description
TDU Title (Remarks) Appl. Weight (kg) Equipment Equipment Equipment QTY STS
MWE/OWE/APL reference supplier PN

04 Installation of an Audio Control A330-800 3.0/3.0/-3.0 Audio Control T.E.A.M ACP2788AE0 1 SFE
Panel and jack panel in avion- A330-900 3.0/3.0/-3.0
Panel (ACP) 1
ics compartment - TEAM, PN
ACP2788AE01

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A330-800/900 Communications 23

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23 Communications A330-800/900
23.51.103 - Installation of an Audio Control Panel (ACP) and jack panel for 4th
occupant
Objective
To provide audio control capability for the fourth occu-
pant.

Basic aircraft
• Three ACPs for captain, first officer, 3rd occupant
(with plugs for boomset and hand microphone).
• Three hand microphones.
• Three boomsets.
• A 4th occupant headset jack is installed, connected
in parallel with the 3rd occupant (reception only).

Description
This modification consists of:
• replacement of the existing Audio Management Unit
(AMU) by an interchangeable one
• installation of one ACP on the 4th occupant lateral
console
• installation of one jack panel close to the additional
ACP.

EPAC selection mode

Individual

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A330-800/900 Communications 23
Figure 23-9 - ACP and jack panel for 4th occupant
Avionics rack
800 VU
4th occupant
AMU console

Headset stowage
and jack panel

PUSH B H PUSH
O HEAD SET A
O N
M D

S M
E I
T C

Audio Control Panel Jack panel

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23 Communications A330-800/900
Table 23-15 - Technical solutions description
TDU Title (Remarks) Appl. Weight (kg) Equipment Equipment Equipment QTY STS
MWE/OWE/APL reference supplier PN

06 Installation of an Audio Control A330-800 3.0/3.0/-3.0 Audio Control T.E.A.M ACP2788AE0 1 SFE
Panel (ACP) and jack panel for A330-900 3.0/3.0/-3.0
Panel (ACP) 1
fourth occupant
Audio Management T.E.A.M AMU4031LB1 1 SFE
Unit (AMU) 40204

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A330-800/900 Communications 23

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23 Communications A330-800/900
23.70.110 - Installation of Cockpit Door Surveillance System (CDSS)

Objective
To install a Cockpit Door Surveillance System (CDSS)
connected to the ECAM System Display.

Basic aircraft
None.

Description
The CDSS shall be composed of three video cameras,
two located in door 1 exit area for x-view and one locat-
ed in cockpit entrance area in the ceiling panel.

The camera view shall be selectable by the flight crew

in the cockpit:
• split screen for door 1 x-view area
• full screen for cockpit entrance area.

The system shall have an "auto shut off" feature. The

auto shut off shall occur after 5 minutes.

EPAC selection mode

Individual

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A330-800/900 Communications 23
Table 23-16 - Technical solutions description
TDU Title (Remarks) Appl. Weight (kg) Equipment Equipment Equipment QTY STS
MWE/OWE/APL reference supplier PN

24 Installation of Cockpit Door A330-800 4.7/4.7/-4.7

Surveillance System (CDSS) A330-900 4.7/4.7/-4.7
connected to the ECAM SD

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23 Communications A330-800/900
23.81.105 - Radio Management Panel (RMP) functions

Objective
To allow the teleloading on the RMP system of the VHF/
HF frequency received by datalink.

Basic aircraft
Three Radio Management Panels (RMP) are installed.

Description
The modification consists in activating the Controller Pi-
lot Data Link Communication (CPDLC) function on RMP
standard 4.

EPAC selection mode

Individual

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A330-800/900 Communications 23
Table 23-17 - Technical solutions description
TDU Title (Remarks) Appl. Weight (kg) Equipment Equipment Equipment QTY STS
MWE/OWE/APL reference supplier PN

01 Activation of RMP std 4 fre- A330-800 0.3/0.3/-0.3

quency load function A330-900 0.3/0.3/-0.3

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 A330-800/900

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A330-800/900 Electrical power 24

Reference Title
24.40.107 Battery discharge warning system
24.91.100 Installation of additional grounding point near pneumatic connection

SCG Issue 3 Revision 2, January 2021 Page 163

24 Electrical power A330-800/900
24.40.107 - Battery discharge warning system

Objective
To implement a warning system as a reminder to switch
off the batteries when the aircraft is de-energized.

Basic aircraft
No warning system is implemented.

Description
A battery discharge warning system is installed to pro-
vide an audio warning (mechanical horn) when ground
power unit connected on External power A receptacle is
disconnected from the aircraft under the following con-
ditions:
• generators not running
• batteries connected from the aircraft network (BAT
overhead panel pushbutton in pressed position).

If the batteries are not switched to OFF the horn shall

stop automatically after five (5) minutes.

EPAC selection mode

Individual

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A330-800/900 Electrical power 24
Table 24-1 - Technical solutions description
TDU Title (Remarks) Appl. Weight (kg) Equipment Equipment Equipment QTY STS
MWE/OWE/APL reference supplier PN

01 Battery discharge warning sys- A330-800 0.5/0.5/-0.5

tem A330-900 0.5/0.5/-0.5

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24 Electrical power A330-800/900
24.91.100 - Installation of additional grounding point near pneumatic connection

Objective
To install an additional grounding point.

Basic aircraft
Grounding points are provided on the nose landing gear
and on the main landing gear.

Description
The modification consists in providing a grounding point
adjacent to the HP connectors of the air conditionning
system between frame C39.1 and C40.2, in the belly
fairing.

EPAC selection mode

Individual

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A330-800/900 Electrical power 24
Figure 24-1 - Additional grounding point

HP ground
connectors

Grounding point

Nose landing gear

Basic grounding points grounding point
Main landing gear
grounding point

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24 Electrical power A330-800/900
Table 24-2 - Technical solutions description
TDU Title (Remarks) Appl. Weight (kg) Equipment Equipment Equipment QTY STS
MWE/OWE/APL reference supplier PN

01 Installation of additional A330-800 Negl./Negl./Negl.

grounding point near pneu- A330-900 Negl./Negl./Negl.
matic connection

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A330-800/900 Equipment/furnishings 25

Reference Title
25.10.115 Installation of tablet mounts in the cockpit
25.10.200 Avionics compartment access panel protection device
25.11.140 Captain and first officer seat covering alternate equipment
25.11.145 Cockpit Fourth Occupant seat alternate equipment
25.50.160 Installation of sidewall protections in lower deck cargo compartments
25.50.222 Installation of heating system for lower deck cargo compartments drainage system
25.51.100 Enhancement package for lower deck Cargo Loading System (CLS)
25.52.100 Installation of additional tie-down points in the lower deck forward cargo compartment
25.53.100 Alternate LD3 position with four 96 inch pallets
25.54.120 Installation of a flight kit container in the lower deck bulk cargo compartment (BFE)
25.54.126 LD3 container capability in lower deck bulk cargo compartment

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25 Equipment/furnishings A330-800/900
25.10.115 - Installation of tablet mounts in the cockpit

Objective Note
To install tablet mounts for on cockpit sliding windows • Tablets and power supply (including cables) are not
on Captain and F/O sides. included in the option and remain airline responsibil-
ity. Therefore the Airline shall ensure that the elected
EFB equipment comply with the aforementioned di-
Basic aircraft mensions / interface. Airbus is not liable in any man-
None. ner in case of an incompatibility.
• Applications hosted on tablets (e.g. EFB software)
Description are not included and can be requested to Airbus Cus-
This modification consists in installing two mounts that tomer Services.
can host tablets for both Captain and F/O to manage • Tablet device power supply input and control com-
mands shall not be located in the "cradle areas".
e.g. EFB operations during all flight phases. Tablet is at-
tached in landscape mode. EPAC selection mode
Two clips are installed on each side to guide the power Individual
cables from the mounts to the basic power plugs (115 V
AC, 60 Hz single phase).

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A330-800/900 Equipment/furnishings 25
Figure 25-1 - Tablet mount

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25 Equipment/furnishings A330-800/900
Table 25-1 - Technical solutions description
TDU Title (Remarks) Appl. Weight (kg) Equipment Equipment Equipment QTY STS
MWE/OWE/APL reference supplier PN

01 Installation of tablet mounts in A330-800 1.8/1.8/-1.8 Tablet Mount AIRBUS F25116002- 1 SFE
the cockpit (10" tablet) A330-900 1.8/1.8/-1.8
000
Tablet Mount AIRBUS F25116002- 1 SFE
001
02 Installation of tablet mounts in A330-800 2.0/2.0/-2.0 Tablet Mount AIRBUS F25116003- 1 SFE
the cockpit (13" tablet) A330-900 2.0/2.0/-2.0
000
Tablet Mount AIRBUS F25116003- 1 SFE
001

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A330-800/900 Equipment/furnishings 25

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25 Equipment/furnishings A330-800/900
25.10.200 - Avionics compartment access panel protection device

Objective
To install a barrier device to protect crew and personnel
from injury when the cockpit avionics compartment ac-
cess panel is open.

Basic aircraft
None.

Description
The barrier consists of a retractable arm which can be
deployed when the access panel is open, when the ac-
cess panel is closed the barrier is stowed and hinged on
the inner face of the access panel.

EPAC selection mode

Individual

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A330-800/900 Equipment/furnishings 25
Figure 25-2 - Avionics compartment access panel protection device

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25 Equipment/furnishings A330-800/900
Table 25-2 - Technical solutions description
TDU Title (Remarks) Appl. Weight (kg) Equipment Equipment Equipment QTY STS
MWE/OWE/APL reference supplier PN

01 Installation of avionics com- A330-800 1.2/1.2/-1.2

partment access panel protec- A330-900 1.2/1.2/-1.2
tion device

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A330-800/900 Equipment/furnishings 25

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25 Equipment/furnishings A330-800/900
25.11.140 - Captain and first officer seat covering alternate equipment

Objective
To change captain and first officer seat covering.

Basic aircraft
Captain and first officer seats are covered with cloth ma-
terial.

Description
This change consists in replacing basic captain and first
officer seats by seats equipped with sheepskin.

EPAC selection mode

Individual

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A330-800/900 Equipment/furnishings 25
Figure 25-3 - Sheepskin covers for captain and first officer seats

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25 Equipment/furnishings A330-800/900
Table 25-3 - Technical solutions description
TDU Title (Remarks) Appl. Weight (kg) Equipment Equipment Equipment QTY STS
MWE/OWE/APL reference supplier PN

Std Captain and first officer seat A330-800 Captain's seat STELIA TAAI3- 1 SFE
A330-900
AEROSPACE 03PE20-01
First Officer's seat STELIA TAAI3- 1 SFE
AEROSPACE 03CE20-01
10 Captain and first officer seat A330-800 1.6/1.6/-1.6 Seat, Captain with STELIA TAAI3- 1 SFE
covering with white sheepskin A330-900 1.6/1.6/-1.6
white sheepskin AEROSPACE 03PE21-01
cover
Seat, First Officer STELIA TAAI3- 1 SFE
with white AEROSPACE 03CE21-01
sheepskin cover
11 Captain and first officer seat A330-800 1.6/1.6/-1.6 Seat, Captain with STELIA TAAI3- 1 SFE
covering with grey sheepskin A330-900
grey sheepskin AEROSPACE 03PE22-01
cover
Seat, First Officer STELIA TAAI3- 1 SFE
with grey sheepskin AEROSPACE 03CE22-01
cover

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A330-800/900 Equipment/furnishings 25

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25 Equipment/furnishings A330-800/900
25.11.145 - Cockpit Fourth Occupant seat alternate equipment

Objective
To provide a high comfort floor mounted seat for a fourth
occupant.

Basic aircraft
A standard folding seat is installed for the fourth occu-
pant in the cockpit.

Description
The improvement of comfort by:
• rubber cushioning
• the replacement of springs by gas shock absorbers.

EPAC selection mode

Individual

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A330-800/900 Equipment/furnishings 25
Figure 25-4 - High comfort fourth occupant seat

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25 Equipment/furnishings A330-800/900
Table 25-4 - Technical solutions description
TDU Title (Remarks) Appl. Weight (kg) Equipment Equipment Equipment QTY STS
MWE/OWE/APL reference supplier PN

Std Cockpit Fourth Occupant seat - A330-800 Seat, fourth SAFRAN SEATS 1671220-00 1 SFE
SAFRAN SEATS FRANCE, PN A330-900
occupant FRANCE
1671220-00

01 Cockpit fourth occupant seat - A330-800 3.0/3.0/-3.0 Seat, fourth SAFRAN SEATS 17702-00-00 1 SFE
High comfort floor mounted A330-900 3.0/3.0/-3.0
occupant FRANCE
seat - SAFRAN SEATS
FRANCE, PN 17702-00-00

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A330-800/900 Equipment/furnishings 25

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25 Equipment/furnishings A330-800/900
25.50.160 - Installation of sidewall protections in lower deck cargo compartments

Objective In the lower deck aft cargo compartment, the protection

To further enhance cargo lining impact tolerance. sheets applied opposite of the door (on the sidewall lin-
ing) will be enlarged by approximately 30%.
Basic aircraft
Aircraft has state-of-the-art cargo lining installed with This enlargement may assist in increasing the cargo
various protection sheets to prevent inadvertent dam- sidewall lining protection versus impact damage.
age.
EPAC selection mode
Description Individual
The current applied protection sheets are positioned in
the door area.

In the lower deck forward cargo compartment, the pro-

tection sheets applied at the forward partition wall
(Frame C20) will be enlarged by approximately 30%.

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A330-800/900 Equipment/furnishings 25
Table 25-5 - Technical solutions description
TDU Title (Remarks) Appl. Weight (kg) Equipment Equipment Equipment QTY STS
MWE/OWE/APL reference supplier PN

02 Installation of sidewall lining A330-800 32.0/32.0/-32.0

protections in lower deck A330-900 32.0/32.0/-32.0
cargo compartments

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25 Equipment/furnishings A330-800/900
25.50.222 - Installation of heating system for lower deck cargo compartments
drainage system
Objective Description
To install in each lower deck cargo compartment, for Using the basic funnel positions, new heated metal fun-
cold weather operating conditions (snow/ice on ULD), a nels with integrated filters are installed. New heated and
heated and insulated pipe drainage system to drain insulated drain pipes connected to the funnels are in-
melted snow and ice during flight and on ground. stalled under the cargo floor. These pipes lead to the aft
and forward drain masts through heated and insulated
Basic aircraft air stop valves.
The drain system collects fluids and drains them
through the bilge's drain valves. When the aircraft is EPAC selection mode
near or on the ground, the drain valves open and fluids Individual
are removed.

There is no connection to the forward and aft heated

drain masts.

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A330-800/900 Equipment/furnishings 25
Figure 25-5 - Cargo compartment drainage system
Drain mast

FR39.1
FR65

FR73
Forward Cargo compartment Aft Cargo compartment Bulk Cargo compartment
A A FR65

FR25 A
FR53.2 B
B
FR20

B
B A
B
B
A

Filter A B

Filter
housing
C
C
Drain sump

Drain funnel
Flexible hose
Strap

Pipe

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25 Equipment/furnishings A330-800/900
Table 25-6 - Technical solutions description
TDU Title (Remarks) Appl. Weight (kg) Equipment Equipment Equipment QTY STS
MWE/OWE/APL reference supplier PN

02 Installation of heating system A330-800 64.0/64.0/-64.0

for lower deck cargo compart- A330-900 80.0/80.0/-80.0
ment drainage system -
Advanced CLS
A330-800 : Subject to certification
A330-900 : Subject to certification

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A330-800/900 Equipment/furnishings 25

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25 Equipment/furnishings A330-800/900
25.51.100 - Enhancement package for lower deck Cargo Loading System (CLS)

Objective For detailed information, please refer to Cargo Com-

To provide per package an enhancement proposal of partment Brochure.
the current advanced Cargo Loading System (CLS).
Note
Basic aircraft This option is not applicable in conjunction with item
Basic advanced Cargo Loading System (CLS) is ap- 25.54.126 - LD3 container capability in lower deck bulk
plied. cargo compartment.

Description EPAC selection mode

The modification consists in applying: Individual
• continuous side guides forward cargo
• continuous side guides aft cargo
• continuous aft entrance guide.

The continuous side guides options ease the transport

and guidance of slightly dished pallets. An addtional ad-
vantage is to prevent entanglement of pallet net meshes
over fixed YZ latches.

The continuous aft entrance guides in aft cargo com-

partment ease further the alignment of ULDs during
loading and off-loading.

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A330-800/900 Equipment/furnishings 25
Figure 25-6 - Enhancement package for lower deck CLS
Continuous side guides in forward cargo compartment

Continuous side guides and aft entrance guides in aft cargo compartment

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25 Equipment/furnishings A330-800/900
Table 25-7 - Technical solutions description
TDU Title (Remarks) Appl. Weight (kg) Equipment Equipment Equipment QTY STS
MWE/OWE/APL reference supplier PN

03 Installation of continuous side A330-800 45.0/45.0/-45.0

guide package - Advanced CLS A330-900 55.0/55.0/-55.0

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A330-800/900 Equipment/furnishings 25

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25 Equipment/furnishings A330-800/900
25.52.100 - Installation of additional tie-down points in the lower deck forward cargo
compartment
Objective The only allowed loads at this location are items with a
To allow transportation of "long lightweight" items in the maximum length of 650 cm and a maximum weight of
lower deck forward cargo compartment on the upper 50 kg, for example windsurf boards, jumping poles,
side of the sloping sidewall panels Left Hand / Right lightweight ducts among other items.
Hand.
EPAC selection mode
Basic aircraft Individual
Basic advanced Cargo Loading System (CLS) is ap-
plied.

Description
For convenient loading of "long lightweight" items, addi-
tional tie-down points (single stud fittings) are installed
in the lower deck forward cargo compartment on the up-
per side of the sloping sidewall panels left and right
hand except in the area opposite to the cargo door.

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A330-800/900 Equipment/furnishings 25
Figure 25-7 - Additional tie-down points
Tie-down fitting
in each frame Additional tie-down
fittings on
both sides

Y/Z-latch integrated
tie-down fitting
(±Y1470)

Forward cargo
compartment

Pallet Contour

Example: Example:
Surf Board Jumping Pole
Rope Rope

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25 Equipment/furnishings A330-800/900
Table 25-8 - Technical solutions description
TDU Title (Remarks) Appl. Weight (kg) Equipment Equipment Equipment QTY STS
MWE/OWE/APL reference supplier PN

01 Installation of additional tie- A330-800 9.0/9.0/-9.0

down points in lower deck for- A330-900 12.0/12.0/-12.0
ward cargo compartment

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A330-800/900 Equipment/furnishings 25

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25 Equipment/furnishings A330-800/900
25.53.100 - Alternate LD3 position with four 96 inch pallets

Objective for A330-900

To accommodate two 60.4 inch x 61.5 inch ULD (or one
60.4 inch x 125 inch) in conjunction with four 96-inch
pallets in the aft cargo compartment.

Basic aircraft for A330-900

The aft cargo compartment is able to accommodate sin-
gle type ULD alternatives as described in the relevant
standard specification chapter.

Description for A330-900

This modification consists of:
• replacement of four roller tracks between frame C56
and C57.2
• installation of four additional XZ-latches between
frame C57.1 and C57.2
• modification of the load chart.

EPAC selection mode

Individual

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A330-800/900 Equipment/furnishings 25
Figure 25-8 - Alternate LD3 position with 96 inch pallets

C53.2
C55 C56 C57.1 C57.2 C57.3 C65

96 in 96 in 80 in 96 in 96 in

60.4 in

Additional XZ-latches
XZ double latch (basic)
Position for 88" pallets

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25 Equipment/furnishings A330-800/900
Table 25-9 - Technical solutions description
TDU Title (Remarks) Appl. Weight (kg) Equipment Equipment Equipment QTY STS
MWE/OWE/APL reference supplier PN

02 Alternate LD3 position with A330-900 4.5/4.5/-4.5

four 96 inch pallets - Advanced
CLS

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A330-800/900 Equipment/furnishings 25

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25 Equipment/furnishings A330-800/900
25.54.120 - Installation of a flight kit container in the lower deck bulk cargo
compartment (BFE)
Objective The maximum to be introduced loads shall not exceed
To install a BFE Flight kit container in the lower deck the maximum allowable loads for the tie down point fix-
bulk cargo compartment. ations and shall neither exceed the maximum area
loads for section 51.
Basic aircraft
Basic aircraft includes the tie down points needed to EPAC selection mode
perform the installation of the flight kit container. Individual

Description
A BFE flight kit container shall be installed the bulk car-
go compartment, in section 51.

The BFE flight kit container shall be as such that the

content is easily accessible. In addition the contour
shall be as such that the volume reduction of the bulk
cargo compartment will be as small as possible and the
contour shall not cover any air outlet.

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A330-800/900 Equipment/furnishings 25
Figure 25-9 - Flight kit container location in lower deck bulk cargo compartment
Door net B
C73
Door net C
C71
Door net A C69A
C69

C67
C65A
Divider net
C65

FLIGHT KIT
CONTAINER

Corner net

Divider net

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25 Equipment/furnishings A330-800/900
Figure 25-10 - Attachement points for flight kit container

C67
C66
Net stanchion
C65A 530
C65 350
Y=0 180

2
1
Sloping side lining
Tie-down point
4

Floor panel

FWD 5

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A330-800/900 Equipment/furnishings 25
Table 25-10 - Technical solutions description
TDU Title (Remarks) Appl. Weight (kg) Equipment Equipment Equipment QTY STS
MWE/OWE/APL reference supplier PN

01 Installation of a flight kit con- A330-800 78.0/78.0/-78.0 Flight kit container DIEHL AVIATION 104158 1 BFE
tainer in the lower deck bulk A330-900 78.0/78.0/-78.0
cargo compt. - (DCM) - (BFE)

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25 Equipment/furnishings A330-800/900
25.54.126 - LD3 container capability in lower deck bulk cargo compartment

Objective Note
To allow the loading of an additional LD3 container in This option is not applicable in conjunction with item
the lower deck bulk cargo compartment. 25.51.100 - Enhancement package for lower deck car-
go loading system.
Basic aircraft
Lower deck aft cargo compartment has the capacity for: However continuous side guides for lower deck forward
• 12 LD3 containers (A330-800) and aft cargo compartments can be selected in addition
• 14 LD3 containers (A330-900). individually.
The lower deck bulk cargo compartment has an useable
EPAC selection mode
volume of 695 cu ft and a load capacity of 7 645 lb Individual
(3 468 kg).

Description
The modification consists in the installation of one addi-
tional roller track with latches, endstop and PDU and as-
sociated equipment allowing power assisted loading of
an additional LD3 in the lower deck bulk cargo compart-
ment.

The remaining bulk cargo volume is 486 cu ft providing

a bulk load capacity of 4 147 lb (1 881 kg).

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A330-800/900 Equipment/furnishings 25
Figure 25-11 - LD3 container capability in bulk cargo compartment

C65A
C66 C73

Lower deck aft cargo door

Bulk
door

Aft cargo
compartment LD3

Net partition Tarpaulin

Remaining useable
volume for bulk

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25 Equipment/furnishings A330-800/900
Table 25-11 - Technical solutions description
TDU Title (Remarks) Appl. Weight (kg) Equipment Equipment Equipment QTY STS
MWE/OWE/APL reference supplier PN

04 LD3 container capability in A330-800 33.0/33.0/-33.0

bulk cargo compartment - A330-900 33.0/33.0/-33.0
Advanced CLS

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A330-800/900 Fire protection 26

Reference Title
26.13.101 APU fire extinguisher alternate equipment
26.23.106 Lower deck cargo compartments fire extinguishers alternate equipment
26.24.155 Installation of portable halon-free fire extinguisher in avionics compartment

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26 Fire protection A330-800/900
26.13.101 - APU fire extinguisher alternate equipment

Objective
To provide alternate vendor for APU fire extinguisher.

Basic aircraft
One APU fire extinguisher is installed outside the APU
compartment, forward of the firewall.

Description
This modification consists in replacing the basic APU
fire extinguisher by another fully interchangeable fire
extinguisher.

EPAC selection mode

Individual

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A330-800/900 Fire protection 26
Figure 26-1 - APU fire extinguisher
Fire wall

Fire bottle

Bracket

Pressure
relief
Pressure connector
switch

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26 Fire protection A330-800/900
Table 26-1 - Technical solutions description
TDU Title (Remarks) Appl. Weight (kg) Equipment Equipment Equipment QTY STS
MWE/OWE/APL reference supplier PN

Std APU fire extinguisher - A330-800 APU fire PACIFIC 33600005-3 1 SFE
PACIFIC SCIENTIFIC, PN A330-900
extinguisher SCIENTIFIC
33600005-3 container

02 APU fire extinguisher - KIDDE A330-800 Negl./Negl./Negl. APU fire KIDDE 472 412-1 1 SFE
AEROSPACE, PN 472 412-1 A330-900 Negl./Negl./Negl.
extinguisher AEROSPACE
container

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A330-800/900 Fire protection 26

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26 Fire protection A330-800/900
26.23.106 - Lower deck cargo compartments fire extinguishers alternate equipment

Objective
To provide alternate vendor for lower deck cargo com-
partments fire extinguishers.

Basic aircraft
Fire extinguisher bottles are installed in each lower deck
cargo compartment. It is possible to discharge their con-
tent either into the lower deck forward cargo or the aft
and bulk compartments. The system is qualified for a
fire suppression time of 240 minutes.

Description
This modification consists in replacing the basic lower
deck cargo compartment fire extinguishing bottles by
equipment from an alternate supplier with the same
240 minutes fire suppression capability.

EPAC selection mode

Individual

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A330-800/900 Fire protection 26
Figure 26-2 - Lower deck cargo compartments fire extinguishers

BULK CARGO COMPARTMENT

FR73

FR70

FR65

SPRAY NOZZLE
SMOKE DET
FWD CARGO COMPARTMENT CAVITY
FR58
FIRE EXTINGUISHER
BOTTLES
FR53.8
FR53.2
AFT CARGO
FR39.2 COMPARTMENT

FR36

FR28

FR25
FR20

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26 Fire protection A330-800/900
Table 26-2 - Technical solutions description
TDU Title (Remarks) Appl. Weight (kg) Equipment Equipment Equipment QTY STS
MWE/OWE/APL reference supplier PN

Std Cargo fire extinguishers - A330-800 Fire extinguisher KIDDE 472625-1 1 SFE
KIDDE AEROSPACE A330-900
container cargo AEROSPACE
compartments
(1600 cu in)
Fire extinguisher KIDDE 472931-2 1 SFE
container cargo AEROSPACE
compartments
(2170 cu in)
10 Cargo fire extinguishers - A330-800 Negl./Negl./Negl. Fire extinguisher PACIFIC 35200003-2 1 SFE
PACIFIC SCIENTIFIC A330-900 Negl./Negl./Negl.
container cargo SCIENTIFIC
compartments
(1600 cu in)
Fire extinguisher PACIFIC 34900008-2 1 SFE
container cargo SCIENTIFIC
compartments
(2170 cu in)

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A330-800/900 Fire protection 26

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26 Fire protection A330-800/900
26.24.155 - Installation of portable halon-free fire extinguisher in avionics
compartment
Objective Note
To install a portable fire extinguisher with halon-free A gauge is located on the top side of the bottle and a
agent in the avionics compartment. RFID tag on the top of the valve head.

Basic aircraft EPAC selection mode

Fire detection is provided in the avionics compartment. Individual
In case of fire detected, the master warning light will turn
on in the cockpit with a message on the ECAM. The
crew can then use the portable fire extinguisher located
in the cockpit.

Description
This modification consists in installing a portable halon-
free fire extinguisher in the avionics compartment on the
forward bulkhead of the Nose Landing Gear bay.
It is filled with Halotron BrX halon-free agent and pres-
surized with dry nitrogen. The fire extinguisher requires
only one hand for operation.

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A330-800/900 Fire protection 26
Figure 26-3 - Portable halon-free fire extinguisher location

Portable halon-free
fire extinguisher

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26 Fire protection A330-800/900
Table 26-3 - Technical solutions description
TDU Title (Remarks) Appl. Weight (kg) Equipment Equipment Equipment QTY STS
MWE/OWE/APL reference supplier PN

02 Portable halon- free fire extin- A330-800 0.0/2.1/-2.1 Halon-free portable UMLAUT P3APP00301 1 SFE
guisher in avionics compart- A330-900 0.0/2.0/-2.1
fire extinguisher ENGINEERING 0D
ment (SFE) - UMLAUT, PN GMBH
P3APP003010D
AIR OPS and UL compliant.
With gauge.
Color code: red.

SCG Issue 3 Revision 2, January 2021 26.24.155 Page 222

A330-800/900 Flight controls 27

Reference Title
27.50.103 Flap carriages roller bearings alternate equipment

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27 Flight controls A330-800/900
27.50.103 - Flap carriages roller bearings alternate equipment

Objective If reduced lubrication maintenance roller bearings are

To replace all basic flap carriage roller bearings by ei- chosen, the basic grease lubricated roller bearings are
ther 'sealed for life' or reduced lubrication maintenance replaced by the reduced lubrication maintenance equip-
roller bearings. ment.

Basic aircraft EPAC selection mode

Carriage roller bearing lubrication is achieved by using Individual
individual grease points and applying grease through
grease nipples.

Description
If 'sealed for life' roller bearings are chosen, the modifi-
cation includes:
• removal of the grease nipples
• replacement of the basic grease lubricated roller
bearings by the 'sealed for life' bearings.

Nipple holes will be plugged with blind screws.

SCG Issue 3 Revision 2, January 2021 27.50.103 Page 224

A330-800/900 Flight controls 27
Table 27-1 - Technical solutions description
TDU Title (Remarks) Appl. Weight (kg) Equipment Equipment Equipment QTY STS
MWE/OWE/APL reference supplier PN

Std Flap track lubricated roller A330-800 Flap track roller RBC AIRCRAFT 27F5757306X 88 SFE
bearings - RBC, PN A330-900
bearings PRODUCTS INC .202
27F5757306X.202

01 Flap track 'sealed for life' roller A330-800 Negl./Negl./Negl. Flap track roller KAMATICS 27F5757306X 88 SFE
bearings - KAMATICS, PN A330-900 Negl./Negl./Negl.
bearings .20X
27F5757306X.20X

07 A330 - Flap track reduced A330-800 Negl./Negl./Negl. Flap track roller RBC AIRCRAFT 27G5757314X 88 SFE
lubrication maintenance roller A330-900 Negl./Negl./Negl.
bearings PRODUCTS INC .200
bearings - RBC, PN
27G5757314X.200

SCG Issue 3 Revision 2, January 2021 27.50.103 Page 225

 A330-800/900

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A330-800/900 Fuel 28

Reference Title
28.25.117 Installation of additional refuel/defuel couplings on the left wing
28.25.121 Auto refuel cockpit preselection and control facilities via FMGES
28.31.101 Installation of a jettison system

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 28 Fuel A330-800/900
28.25.117 - Installation of additional refuel/defuel couplings on the left wing

Objective
To offer increased flexibility in terms of aircraft servic-
ing.

Basic aircraft
• One pair of 2.5 inch couplings are provided under the
right hand wing outboard of the engine.
• Structural provisions.

Description
An additional pair of 2.5 inch refueling couplings is in-
stalled under the left wing. The position and operation of
these couplings are identical to the basic couplings.

This option permits aircraft fuel tanks to be filled from ei-

ther the right or left side, or from both sides together.

EPAC selection mode

Individual

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A330-800/900 Fuel 28
Figure 28-1 - Additional refuel/defuel couplings on the left wing

Basic refuel
couplings

Basic refuel Optional refuel

panel couplings

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28 Fuel A330-800/900
Table 28-1 - Technical solutions description
TDU Title (Remarks) Appl. Weight (kg) Equipment Equipment Equipment QTY STS
MWE/OWE/APL reference supplier PN

02 Installation of add. refuel/ A330-800 6.0/6.0/-6.0 Refuel/defuel ZODIAC L93C100-655 TBD SFE
defuel couplings on the left A330-900 6.0/6.0/-6.0
couplings AEROTECHNICS
wing - ZODIAC AEROTECH-
NICS, PN L93C100-655

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A330-800/900 Fuel 28

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28 Fuel A330-800/900
28.25.121 - Auto refuel cockpit preselection and control facilities via FMGES

Objective If there is no FMS block fuel signal present then the

To enable fuel quantity pre-selection and automatic re- cockpit initiation is inoperative. When refuelling is initiat-
fuelling to be controlled from the cockpit. ed from the cockpit, it is indicated at the outside refuel
panel(s) by illumination of CKPT caption.
Basic aircraft
Preselection of refuel quantity and initiation of refuel are EPAC selection mode
made from the external refuel panel located underneath Individual
the RH belly fairing.

Description
The preselection is done via the FMS/LCD MCDU "INIT
FUEL PREDICTION" page (Block entry).

Automatically, the FMS block fuel output is used by the

Fuel Control and Monitoring Computer (FCMC) to com-
pute fuel uplift requirement. This has priority over the
outside preselector. Refuel is initiated by a dedicated
cockpit switch or the basic refuel panel mode switch.
These switches have equal priority.

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A330-800/900 Fuel 28
Figure 28-2 - Auto refuel from cockpit

FM 1 IND RDY FM 2

INIT FUEL PREDICTION

TAXI CG/ ZFW
0.4 25/ 145.5
TRIP /TIME BLOCK
90.6 / 1207 99.0
RTE RSV/%
4.5/5.0
ALTN /TIME TOW
1.2/0020 244.1
FINAL /TIME LW
1.1/0030 153.5
EXTRA /TIME TRIP WIND
1.2/0030 TL026

LCD MCDU

FUEL 285VU

REFUEL

END
ON

Refuel panel with Wet Center Tank Overhead panel

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28 Fuel A330-800/900
Table 28-2 - Technical solutions description
TDU Title (Remarks) Appl. Weight (kg) Equipment Equipment Equipment QTY STS
MWE/OWE/APL reference supplier PN

01 Auto refuel cockpit preselec- A330-800 4.0/4.0/-4.0

tion and control facilities via A330-900 4.0/4.0/-4.0
FMGES

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A330-800/900 Fuel 28

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28 Fuel A330-800/900
28.31.101 - Installation of a jettison system

Objective
To offer the possibility to discard some of the aircraft
fuel in flight so as to reduce the aircraft weight for land-
ing.

Basic aircraft
No jettison system is installed.

Description
Installation on each wing of additional pipe work con-
nected from the fuel system refuel gallery through the
flap track fairing No 4 to the jettison nozzles. A jettison
valve is installed in the pipe work on the bottom skin, un-
der the flap track fairing No 4. Control is achieved
through the fuel jettison control panel pushbuttons in-
stalled on the cockpit overhead panel. This enables fuel
to be jettisoned at 1 000 kg/min. The jettison operation
once activated can be stopped either by deselecting the
control pushbuttons in the cockpit or automatically by
any inner tank low level sensor drying. The quantity of
fuel to be jettisoned can be controlled manually.

EPAC selection mode

Individual

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A330-800/900 Fuel 28
Table 28-3 - Technical solutions description
TDU Title (Remarks) Appl. Weight (kg) Equipment Equipment Equipment QTY STS
MWE/OWE/APL reference supplier PN

05 Installation of a jettison system A330-800 13.0/13.0/-13.0

A330-900 : Subject to lead time con- A330-900
straints

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 A330-800/900

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A330-800/900 Indicating/recording systems 31

Reference Title
31.00.130 Definition of units
31.14.103 Overhead panel toggle switch re-orientation
31.60.102 Harmonized Primary Flight Display (hPFD)

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31 Indicating/recording systems A330-800/900
31.00.130 - Definition of units

Objective EPAC selection mode

To provide US units of measurement for airline opera- Individual
tional commonality.

Basic aircraft
See table on the following page.

Description
The customer has the choice for each item, separately,
between the basic and the optional unit.

The modification consists in replacing metric units with

US units on indicators and labels of the aircraft:
• Cabin and supply duct temperatures are in degrees
Fahrenheit, all other temperature indications remain
in degrees Celcius.
• The baro setting window of the Integrated Standby
Instrument System (ISIS) is calibrated in inches of
Mercury, in addition to the basic hPa indication. The
altitude is calibrated in meter in addition to the basic
feet indication. Refer to items 34.20.203/02 and 04.
• Runway lengths are in feet.
• Fuel weight is in pounds and fuel flow is in pounds
per hour (lbs/hr).

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A330-800/900 Indicating/recording systems 31
Figure 31-1 - Definition of units
Unit of measurement Basic unit Optional unit Repercussions

1. Temperature
°C °F Cabin and supply duct temperatures on ECAM and FAP
(environmental)

2. Standby altimeter
Baro setting hPa in Hg ISIS option (see item 34.20.203)
Altitude ft m

3. Lengths
(Runway length on m ft Display on LCD MCDU
FMGES)

4. Weights
Aircraft weight and fuel kg lbs
indication
Display of weight on ECAM and on placards at refuel
panel door

5. Fuel flow kg/hr lbs/hr

Particular attention regarding units shall be paid.

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31 Indicating/recording systems A330-800/900
Table 31-1 - Technical solutions description
TDU Title (Remarks) Appl. Weight (kg) Equipment Equipment Equipment QTY STS
MWE/OWE/APL reference supplier PN

01 Environmental temperature, A330-800 0.0/0.0/0.0

length, weights optional unit A330-900 0.0/0.0/0.0

03 Length optional unit A330-800 0.0/0.0/0.0

A330-900 0.0/0.0/0.0

07 Length, weights optional unit A330-800 0.0/0.0/0.0

A330-900 0.0/0.0/0.0

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A330-800/900 Indicating/recording systems 31

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31 Indicating/recording systems A330-800/900
31.14.103 - Overhead panel toggle switch re-orientation

Objective
To invert overhead panel toggle switches "ON/OFF" po-
sitions compared to the basic definition (for operational
reasons).

Basic aircraft
"OFF" position for the toggle switches is downwards.

Description
This option installs the overhead panel toggle switches
in a sense that the "ON" position is downward.

The modification consists in changing cable connec-

tions to overhead panel and replacing existing overhead
panel integrally lit plate by a new mechanically and elec-
trically interchangeable plate.

EPAC selection mode

Individual

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A330-800/900 Indicating/recording systems 31
Figure 31-2 - Overhead panel toggle switch re-orientation

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31 Indicating/recording systems A330-800/900
Table 31-2 - Technical solutions description
TDU Title (Remarks) Appl. Weight (kg) Equipment Equipment Equipment QTY STS
MWE/OWE/APL reference supplier PN

01 Overhead panel toggle switch A330-800 Negl./Negl./Negl. Integrally lighted AIRBUS TBD 1 SFE
re-orientation A330-900 Negl./Negl./Negl.
plate 215 VU

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A330-800/900 Indicating/recording systems 31

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31 Indicating/recording systems A330-800/900
31.60.102 - Harmonized Primary Flight Display (hPFD)

Objective And FD shape is changed from green cross-bars to ma-

To enhance pilot situation awareness via trajectory and genta circle (replacing previous symbol with angular in-
energy management. formation).
To provide guidance symbology on Primary Flight Dis- This function is activated via pin-programming.
play (PFD) based on trajectory and energy information
and bring harmonization between PFD and Head Up EPAC selection mode
Display (HUD). Individual

Basic aircraft
Classic PFD with cross-bars symbol in HDG-V/S mode
and angular symbol in TRK-FPA mode for Flight Direc-
tor (FD).

Description
When TRK-FPA mode is selected on Flight Control Unit
(FCU) dedicated push button, following symbols are
displayed on PFD:
• Flight Path Vector,
• Energy chevrons,
• Delta speed,
• Selected Flight Path Angles (FPA).

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A330-800/900 Indicating/recording systems 31
Figure 31-3 - Harmonized Primary Flight Display (hPFD)

HDG-V/S // TRK-FPA
push button

e TR
mod K-F
S PA
V/ m
G- od
HD e

Attitude guidance Trajectory

guidance

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31 Indicating/recording systems A330-800/900
Table 31-3 - Technical solutions description
TDU Title (Remarks) Appl. Weight (kg) Equipment Equipment Equipment QTY STS
MWE/OWE/APL reference supplier PN

01 Harmonized Primary Flight A330-800 Negl./Negl./Negl.

Display (hPFD) A330-900 Negl./Negl./Negl.
A330-800 : Subject to certification
A330-900 : Subject to certification

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A330-800/900 Landing gear 32

Reference Title
32.40.100 Wheels and brakes equipment selection
32.41.143 Main Landing Gear (MLG) tire selection
32.41.144 Nose Landing Gear (NLG) tire selection
32.48.200 Installation of universal brake cooling fans
32.51.100 Nose Wheel Steering (NWS) back-up hydraulic power supply

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32 Landing gear A330-800/900
32.40.100 - Wheels and brakes equipment selection

Objective In normal conditions (revenue flights) the brakes allow

To make a vendor selection for Main Landing Gear an average of 1 500 landings in terms of service endur-
(MLG) wheels and brakes. ance.

Basic aircraft Extended life brakes (if applicable) allow 2 500 landings
If no choice is made by the customer, wheels and in average.
brakes are selected from the proposed technical solu-
tions. For information, the maximum brake energy capacity in
Rejected TakeOff (RTO) conditions is 105 MJ.
Description
This modification consists in installing wheels and car-
Note
bon brakes according to the customer choice. No vendor selection is possible for Nose Landing Gear
(NLG) wheels.
Each wheel assembly consists of:
• an inflating valve and material provision for receiving EPAC selection mode
an overpressure valve and electrical pressure trans- Individual
ducer for the Tire Pressure Indicating System (TPIS)
• a hubcap
• a brake unit, including a temperature sensor with
thermocouple, two self-sealing couplings and a kit for
the brake attachment to the MLG axle
• an axle sleeve.

This modification requires pin-programming of the Brak-

ing and Steering Control Unit (BSCU).

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A330-800/900 Landing gear 32
Figure 32-1 - Wheels and brakes on Main Landing Gear (MLG)

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32 Landing gear A330-800/900
Table 32-1 - Technical solutions description
TDU Title (Remarks) Appl. Weight (kg) Equipment Equipment Equipment QTY STS
MWE/OWE/APL reference supplier PN

32 A330 - Wheels and brakes A330-800 48.0/48.0/-48.0 Brake unit GOODRICH 2-1578-7 8 SFE
GOODRICH MESSIER (2 500 A330-900 48.0/48.0/-48.0
MESSIER INC
LPO)
Wheel, main gear GOODRICH 3-1546 8 SFE
MESSIER INC
34 A330 - Wheels and brakes A330-800 Negl./Negl./Negl. Brake unit GOODRICH 2-1577-9 8 SFE
GOODRICH MESSIER (1 500 A330-900 Negl./Negl./Negl.
MESSIER INC
LPO)
Wheel, main gear GOODRICH 3-1546 8 SFE
MESSIER INC
36 A330 - Wheels and brakes A330-800 20.0/20.0/-20.0 Brake unit HONEYWELL 2612202-6 8 SFE
HONEYWELL (2 500 LPO) A330-900 20.0/20.0/-20.0
INC.
Wheel, gear HONEYWELL 2612201-3 8 SFE
INC.
37 A330 - Wheels and brakes A330-800 Brake unit GOODRICH 2-1794-N 8 SFE
GOODRICH MESSIER for A330-900
MESSIER INC
above 245 t WV
A330-800 : Subject to certification Wheel, main gear GOODRICH 3-1750 8 SFE
A330-900 : Subject to certification
MESSIER INC
39 A330 - Wheels and brakes A330-800 20.0/20.0/-20.0 Brake unit HONEYWELL 2612202-7 8 SFE
HONEYWELL (2 500 LPO) A330-900 20.0/20.0/-20.0
INC.
A330-800 : Subject to certification
A330-900 : Subject to certification
Wheel, gear HONEYWELL 2612201-3 8 SFE
INC.

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32 Landing gear A330-800/900
32.41.143 - Main Landing Gear (MLG) tire selection

Objective
To make a vendor selection for tires.

Basic aircraft
If no choice is made by the customer, tires will be select-
ed from the proposed technical solutions.

Description
This option allows the customer to select a vendor for
Main Landing Gear (MLG) tires from the proposed tech-
nical solution.

EPAC selection mode

Individual

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A330-800/900 Landing gear 32
Figure 32-2 - Radial aircraft tire construction
Tread reinforcing ply
Tread
Overlay

Belt plies

Carcass plies

Liner

Bead heel

Sidewall

Bead toe
Chippers
Beads

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32 Landing gear A330-800/900
Table 32-2 - Technical solutions description
TDU Title (Remarks) Appl. Weight (kg) Equipment Equipment Equipment QTY STS
MWE/OWE/APL reference supplier PN

01 A330-200/300/800/900 - Radial A330-800 Negl./Negl./Negl. Tire, landing gear MICHELIN M05102 8 SFE
tires (MLG) - MICHELIN, PN A330-900 Negl./Negl./Negl.
M05102 for MTOW below 245 t

02 A330-200/300/800/900 - Radial A330-800 Negl./Negl./Negl. Tire, landing gear BRIDGESTONE APR06911 8 SFE
tires (MLG) - BRIDGESTONE, A330-900 Negl./Negl./Negl.
PN APR06911 for MTOW below
245 t

03 A330-800/900 - Radial tires A330-800 -52.0/-52.0/52.0 Tire, landing gear BRIDGESTONE APR06950 8 SFE
(MLG) - BRIDGESTONE for A330-900 -52.0/-52.0/52.0
MTOW above 245 t

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A330-800/900 Landing gear 32

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32 Landing gear A330-800/900
32.41.144 - Nose Landing Gear (NLG) tire selection

Objective
To make a vendor selection for Nose Landing Gear
(NLG) tires.

Basic aircraft
If no choice is made by the customer, Nose Landing
Gear (NLG) tires can be selected from the proposed
technical solutions.

Description
This option allows the customer to select a vendor for
Nose Landing Gear (NLG) tires.

EPAC selection mode

Individual

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A330-800/900 Landing gear 32
Table 32-3 - Technical solutions description
TDU Title (Remarks) Appl. Weight (kg) Equipment Equipment Equipment QTY STS
MWE/OWE/APL reference supplier PN

01 A330-200/300/800/900 - Radial A330-800 Negl./Negl./Negl. Tire, Nose Landing MICHELIN M07601 2 SFE
tires (NLG) - MICHELIN, PN A330-900 Negl./Negl./Negl.
Gear (NLG)
M07601

02 A330-200/300/800/900 - Radial A330-800 Negl./Negl./Negl. Tire, Nose Landing BRIDGESTONE APR06500 2 SFE
tires (NLG) - BRIDGESTONE, A330-900 Negl./Negl./Negl.
Gear (NLG)
PN APR06500

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32 Landing gear A330-800/900
32.48.200 - Installation of universal brake cooling fans

Objective When brake temperatures become higher than 300 °C,

To provide artificial cooling of the brakes in order to de- "HOT" light illuminates amber associated with Electron-
crease turnaround time. ic Centralized Aircraft Monitoring (ECAM) caution. On
Brake cooling fans are recommended in the case of a the ECAM wheel page, corresponding wheel represen-
network with flights ending by a high energy braking and tation becomes amber.
followed by a short turnaround time.
The fans are automatically switched "OFF" upon land-
Basic aircraft ing gear retraction.
Wiring provisions for brake cooling fans on main landing
gear. The modification consists in:
Structural provisions inside wheel axles. • installing a modified tachometer/fan motor support,
tachometer drive shaft and motor inside the wheel
Space provision for a "BRK FAN" pushbutton on the axle
landing gear panel and circuit breaker in the avionics • installing a fan and cover assemblies on wheel
compartment. • installing a control pushbutton and associated light-
ing.
Description EPAC selection mode
An electrically driven brake cooling fan is installed in Individual
each main landing gear wheel.

The air is drawn by the impeller from the brake side and
vented outside. The fans are controlled from a single
pushbutton switch on the main instrument panel.

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A330-800/900 Landing gear 32
Figure 32-3 - Universal brake cooling fans

Auto-Brake panel

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32 Landing gear A330-800/900
Table 32-4 - Technical solutions description
TDU Title (Remarks) Appl. Weight (kg) Equipment Equipment Equipment QTY STS
MWE/OWE/APL reference supplier PN

17 A330-200/300/800/900 - Univer- A330-800 62.0/62.0/-62.0 Long Range Axle SAFRAN DR1602U01 8 SFE
sal brake cooling fans on A330-900 62.0/62.0/-62.0
Adapter VENTILATION
GOODRICH MESSIER brakes SYSTEMS
Tachometer drive SAFRAN E21350000 8 SFE
shaft LANDING
SYSTEMS
UBCF fan ASSY SAFRAN RU1502U01 8 SFE
VENTILATION
SYSTEMS
UBCF motor ASSY SAFRAN AE1502U02 8 SFE
VENTILATION
SYSTEMS
Wheel adapter SAFRAN DR1602D02 8 SFE
VENTILATION
SYSTEMS

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A330-800/900 Landing gear 32
TDU Title (Remarks) Appl. Weight (kg) Equipment Equipment Equipment QTY STS
MWE/OWE/APL reference supplier PN

18 A330-200/300/800/900 - Univer- A330-800 62.0/62.0/-62.0 Long Range Axle SAFRAN DR1602U01 8 SFE
sal brake cooling fans on HON- A330-900 62.0/62.0/-62.0
Adapter VENTILATION
EYWELL brakes SYSTEMS
Tachometer drive SAFRAN E21350000 8 SFE
shaft LANDING
SYSTEMS
UBCF fan ASSY SAFRAN RU1502U01 8 SFE
VENTILATION
SYSTEMS
UBCF motor ASSY SAFRAN AE1502U02 8 SFE
VENTILATION
SYSTEMS
Wheel adapter SAFRAN DR1602B01 8 SFE
VENTILATION
SYSTEMS

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32 Landing gear A330-800/900
32.51.100 - Nose Wheel Steering (NWS) back-up hydraulic power supply

Objective
To introduce a hydraulic back-up system which main-
tains the nose wheel steering operative in the event of a
green hydraulic system loss.

Basic aircraft
None.

Description
The modification consists in supplying the steering ac-
tuators from the yellow hydraulic system when the
green one is not available.

EPAC selection mode

Individual

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A330-800/900 Landing gear 32
Table 32-5 - Technical solutions description
TDU Title (Remarks) Appl. Weight (kg) Equipment Equipment Equipment QTY STS
MWE/OWE/APL reference supplier PN

02 Installation of Nose Wheel A330-800

Steering (NWS) alternate A330-900 33.1/33.1/-33.1
power supply
Subject to lead time constraints

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 A330-800/900

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A330-800/900 Navigation 34

Reference Title
34.00.300 Required Navigation Performance Authorization Required (RNP AR)
34.11.100 Total Air Temperature (TAT) sensor alternate equipment
34.20.203 Integrated Standby Instrument System (ISIS) - optional functions
34.35.112 Head-Up Display (HUD) system provisions
34.35.113 Installation of Head-Up Display (HUD)
34.41.125 Dual weather radar (WXR) system alternate equipment
34.42.100 Radio altitude automatic call-outs
34.42.113 Radio altimeter alternate equipment
34.43.128 Installation of T3CAS
34.43.130 TCAS II (ARINC 735) / ATC transponder alternate equipment
34.43.400 ATSAW applications
34.48.104 Enhanced Ground Proximity Warning System (EGPWS) optional functions
34.51.108 DME interrogators alternate equipment
34.52.102 Automatic Dependent Surveillance - Broadcast (ADS-B OUT)
34.53.100 Installation of Automatic Direction Finder (ADF) system
34.55.102 VOR/Marker receivers alternate equipment

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34 Navigation A330-800/900
Reference Title
34.58.310 Multi Mode Receiver (MMR) alternate equipment
34.58.316 Activation of GLS function

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34 Navigation A330-800/900
34.00.300 - Required Navigation Performance Authorization Required (RNP AR)

Objective Depending on the type of RNP AR application, the

To offer RNP AR (Required Navigation Performance achieved RNP AR level could be as low as 0.1NM. The
Authorization Required) capability. demonstration is up to the operator and is performed
through Flight Operational Safety Assessment.
Basic aircraft The information provided in the Airworthiness Compli-
Capability to fly RNP APPROACH (RNP APCH) opera- ance Document is intended to support the airline and
tions is basic on the aircraft. the National Airworthiness Authorities for the operation-
al approval process.
Description
The modification provides RNP AR capability and up-
EPAC selection mode
dates the operational documents accordingly. Individual
There are 3 different RNP AR levels:
• RNP AR level in accordance with EASA regulations
(aircraft certification);
• RNP AR level in accordance with FAA regulations
(aircraft certification);
• Achievable RNP AR level depending on the type of
application (operational approval by the National Air-
worthiness Authorities).
The airworthiness assessment leads to the following
demonstrated RNP AR levels:
• RNP AR 0.3 in accordance with EASA AMC20-26
• RNP AR 0.1 in accordance with FAA AC90-101A and
AC20-138C.

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A330-800/900 Navigation 34
Table 34-1 - Technical solutions description
TDU Title (Remarks) Appl. Weight (kg) Equipment Equipment Equipment QTY STS
MWE/OWE/APL reference supplier PN

11 RNP AR capability (Step 3) A330-800 0.0/0.0/0.0

A330-900 0.0/0.0/0.0

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34 Navigation A330-800/900
34.11.100 - Total Air Temperature (TAT) sensor alternate equipment

Objective
To provide alternate equipment for TAT sensors.

Basic aircraft
Two non-aspirated TAT sensors are installed.

Description
Either non-aspirated TAT sensors from an alternate
supplier or aspirated sensors may be selected.

The aspirated sensors will improve the accuracy of the

TAT measurement on the ground under solar radiation.

EPAC selection mode

Individual

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A330-800/900 Navigation 34
Figure 34-1 - Aspirated TAT sensors

Air flow

Sensing
element
New TAT sensors
3/8" dia. pipe routing
Air conditioning
system bleed point

Supply air for

ejector operation
Note: A330-800 shown to illustrate principle

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34 Navigation A330-800/900
Table 34-2 - Technical solutions description
TDU Title (Remarks) Appl. Weight (kg) Equipment Equipment Equipment QTY STS
MWE/OWE/APL reference supplier PN

Std TAT sensors - BF GOODRICH A330-800 TAT sensor BF GOODRICH 0102ME2GE 2 SFE
AEROSPACE, PN 0102ME2GE A330-900
AEROSPACE

09 Aspirated TAT sensors - BF A330-800 Negl./Negl./Negl. Aspirated TAT BF GOODRICH 102LM2GE 2 SFE
GOODRICH AEROSPACE, PN A330-900 Negl./Negl./Negl.
Sensors AEROSPACE
102LM2GE

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34 Navigation A330-800/900
34.20.203 - Integrated Standby Instrument System (ISIS) - optional functions

Objective
To provide different options for the Integrated Standby
Instrument System (ISIS).

Basic aircraft
An Integrated Standby Instrument System (ISIS), with
altitude in feet and barosetting in hPa, is installed on the
center instrument panel.

Description
For the ISIS, the following functions are available:
• baro setting in inches of Mercury (in addition to the in-
dication in hPa)
• display of the metric altitude (in addition to the alti-
tude in feet).

EPAC selection mode

Individual

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A330-800/900 Navigation 34
Figure 34-2 - ISIS optional functions

ISIS with baro-pressure in inches Hg

ISIS with altitude in meter

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34 Navigation A330-800/900
Table 34-3 - Technical solutions description
TDU Title (Remarks) Appl. Weight (kg) Equipment Equipment Equipment QTY STS
MWE/OWE/APL reference supplier PN

02 ISIS - baro setting in inches Hg A330-800 0.0/0.0/0.0

A330-900

04 ISIS - display of metric altitude A330-800 0.0/0.0/0.0

A330-900 0.0/0.0/0.0

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A330-800/900 Navigation 34

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34 Navigation A330-800/900
34.35.112 - Head-Up Display (HUD) system provisions

Objective
To provide mechanical and electrical provisions for
Head Up Display (HUD) system installation.

Basic aircraft
Structural provisions shall be installed.

Description
The system provisions comprise mechanical and elec-
trical provisions for the installation of HUD system.
The modification mainly consists in:
• Modifying the cockpit primary structure to support the
installation of Head-Up Projectors Units (HPU) and
Head-Up Combiner Units (HCU).
• Installing wirings between the avionics compartment
and the cockpit.
• Installing mounting tray for the HUD Computer in avi-
onic compartment.

EPAC selection mode

Individual

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A330-800/900 Navigation 34
Table 34-4 - Technical solutions description
TDU Title (Remarks) Appl. Weight (kg) Equipment Equipment Equipment QTY STS
MWE/OWE/APL reference supplier PN

01 Installation of system provi- A330-800 13.5/13.5/-13.5

sions for dual Head-Up Display A330-900 13.5/13.5/-13.5
(HUD)

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34 Navigation A330-800/900
34.35.113 - Installation of Head-Up Display (HUD)

Objective Note: Low Visibility Take Off (LVTO) function is limited

To enhance pilot situation awareness via trajectory and to RVR 125 m. HUD does not allow to reduce minimum
energy management. to RVR 75 m.
To extend operational capability on Cat I airport with
specific procedures. EPAC selection mode
Individual
Basic aircraft
None.

Description
A dual Head Up Display (HUD) system is installed to
manually fly the aircraft or to monitor the automatic ap-
proaches in all the flight phases.

Note
Aircraft operation with HUD activated requires dedicat-
ed flight crew training.
Aircraft fitted with HUD is eligible for Special Authoriza-
tion CAT I Approach Operations (with Decision Height
(DH) as low as 150 feet and visibility minimum as low as
RVR 1400).

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A330-800/900 Navigation 34
Figure 34-3 - Head-Up-Display

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34 Navigation A330-800/900
Table 34-5 - Technical solutions description
TDU Title (Remarks) Appl. Weight (kg) Equipment Equipment Equipment QTY STS
MWE/OWE/APL reference supplier PN

01 Installation of dual Head-Up A330-800 28.0/28.0/-28.0 Head up Combiner THALES C19628AD 1 SFE
Display (HUD) A330-900 28.0/28.0/-28.0
Unit Capt (HCU) AVIONICS SA
A330-800 : Subject to certification
Head up Combiner THALES C19643AD 1 SFE
Unit F/O (HCU) AVIONICS SA
Head Up Display THALES C13153EA02 2 SFE
Computer (HUDC) AVIONICS SA
Head up Projection THALES C19625BA 2 SFE
Unit (HPU) AVIONICS SA

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34 Navigation A330-800/900
34.41.125 - Dual weather radar (WXR) system alternate equipment

Objective
To provide the customer with an alternate choice.

Basic aircraft
A dual weather radar system with predictive windshear
detection capability, generally in accordance with
ARINC 708A is installed. The PWS is activated.

Description
The existing weather radar configuration is replaced by
an alternate one.

EPAC selection mode

Individual

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A330-800/900 Navigation 34
Figure 34-4 - Dual weather radar system

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34 Navigation A330-800/900
Table 34-6 - Technical solutions description
TDU Title (Remarks) Appl. Weight (kg) Equipment Equipment Equipment QTY STS
MWE/OWE/APL reference supplier PN

Std Dual weather radar ROCK- A330-800 Weather radar ROCKWELL 622-5137-601 1 SFE
WELL COLLINS, MultiScan A330-900
antenna COLLINS
WXR-2100
Weather radar ROCKWELL 622-5130-820 1 SFE
control panel COLLINS
Weather radar dual ROCKWELL 622-5136-801 1 SFE
antenna mount COLLINS
Weather radar dual ROCKWELL 622-5134-064 1 SFE
transceiver mount COLLINS
Weather radar ROCKWELL 822-1710-214 2 SFE
transceiver COLLINS
40 Dual weather radar ROCK- A330-800 Negl./Negl./Negl. Weather radar ROCKWELL 622-5137-601 1 SFE
WELL COLLINS, MultiScan A330-900 Negl./Negl./Negl.
antenna COLLINS
WXR-2100 - V2 with hazard
function activation Weather radar ROCKWELL 622-5130-830 1 SFE
control panel COLLINS
Weather radar dual ROCKWELL 622-5136-821 1 SFE
antenna mount COLLINS
Weather radar dual ROCKWELL 622-5134-064 1 SFE
transceiver mount COLLINS
Weather radar ROCKWELL 822-1710-411 2 SFE
transceiver COLLINS

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A330-800/900 Navigation 34
TDU Title (Remarks) Appl. Weight (kg) Equipment Equipment Equipment QTY STS
MWE/OWE/APL reference supplier PN

44 Dual weather radar HONEY- A330-800 8.1/8.1/-8.1 Radar processor HONEYWELL 930-1005-002 2 SFE
WELL, RDR 4000 - V2 (-020) A330-900 8.1/8.1/-8.1
INC. REDMOND,
OLATHE
Transmitter/ HONEYWELL 930-2000-020 2 SFE
Receiver Unit INC. REDMOND,
OLATHE
Weather radar HONEYWELL 930-4301-001 1 SFE
antenna INC. REDMOND,
OLATHE
Weather radar HONEYWELL 930-6201-001 1 SFE
control panel INC. REDMOND,
OLATHE
Weather radar dual HONEYWELL 930-3001-001 1 SFE
antenna mount INC. REDMOND,
OLATHE
Weather radar HONEYWELL 930-7002-001 2 SFE
transceiver mount INC. REDMOND,
OLATHE

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34 Navigation A330-800/900
TDU Title (Remarks) Appl. Weight (kg) Equipment Equipment Equipment QTY STS
MWE/OWE/APL reference supplier PN

45 Dual weather radar HONEY- A330-800 8.1/8.1/-8.1 Radar processor HONEYWELL 930-1005-002 2 SFE
WELL, RDR 4000 - V2 (-020) A330-900 8.1/8.1/-8.1
INC. REDMOND,
with hazard function activation OLATHE
Transmitter/ HONEYWELL 930-2000-020 2 SFE
Receiver Unit INC. REDMOND,
OLATHE
Weather radar HONEYWELL 930-4301-001 1 SFE
antenna INC. REDMOND,
OLATHE
Weather radar HONEYWELL 930-6201-002 1 SFE
control panel INC. REDMOND,
OLATHE
Weather radar dual HONEYWELL 930-3001-001 1 SFE
antenna mount INC. REDMOND,
OLATHE
Weather radar HONEYWELL 930-7002-001 2 SFE
transceiver mount INC. REDMOND,
OLATHE

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34 Navigation A330-800/900
34.42.100 - Radio altitude automatic call-outs

Objective A) The following announcements are also proposed:

To customize the radio altitude announcements. • 2 000 ft: two thousand
• 500 ft: five hundred (refer to paragraph B and C)
Basic aircraft • 300 ft: three hundred
The automatic call-out function is integrated in the FWC • 200 ft: two hundred
and generates synthetic voice announcements of radio • 100 ft: one hundred
• 80 ft: eighty.
altitude.
B) According to operational requirements for TAWS, it is
Basic definition gives the following announcements: mandatory to select at least one of the following an-
• altitudes in feet: nouncements:
2500, 1000, 400, 70, 60, 50, 40, 30, 20, 10 and 5 (e.g.
• 400 ft call out
at 400 ft, the voice says in English "four hundred"). • 500 ft call out
• "hundred above" at DH / MDA / MDH + 100 ft (*) • 500 ft smart call out.
• "minimum" at DH / MDA / MDH (*).
(*) DH on PA, MDA on NPA - QFE, MDH on NPA-QNH. The 500 ft smart call out inhibits the 500 ft announce-
ment in precision approaches if the ILS glide deviation
Description is below two dots.
The FWC pin programming shall be modified according
to the announcements requested via the selection table
C) For aircraft under FAA registration, the 500ft call out
below.
shall be selected, in order to comply with operational
regulation 14 CFR 121.354.

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A330-800/900 Navigation 34
34.42.100 - Radio altitude automatic call-outs (Continued)

Note
• Selection of 80, 70 and 60 ft are recommended but
not mandatory. Selection of 80 ft implies the selec-
tion of 70 ft and 60 ft. Selection of 70 ft implies selec-
tion of 60 ft.
• The 500 ft smart call out inhibits the 500 ft announce-
ment also in FLS approaches (not intended inhibi-
tion).
• DH: Decision Height.
• MDA: Minimum Decision Altitude.
• MDH: Minimum Decision Height.
• NPA: Non Precision Approach.
• PA: Precision Approach.

EPAC selection mode

Individual

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34 Navigation A330-800/900
Figure 34-5 - Selection table for Radio altitude automatic call-outs
Selection
Announcement Comments
(YES/NO)
at 2500 ft: "two thousand fi ve hundred"
Selection
at 2500 ft: "twenty fi ve hundred" Comments
(YES/NO)
at 2000 ft: "two thousand"
at 1000 ft: "one thousand"
at 500 ft: "fi ve hundred" at least 500 ft or 400 ft is mandatory (mandatory for FAA)
at 500 ft smart: "fi ve hundred" at least 500 ft or 400 ft is mandatory
at 400 ft: "four hundred" at least 500 ft or 400 ft is mandatory
at 300 ft: "three hundred"
at 200 ft: "two hundred"
at 100 ft: "one hundred"
at 80 ft: "eighty" selection of 80 ft implies the selection of 70 and 60 ft
at 70 ft: "seventy" selection of 70 ft implies the selection of 60 ft
at 60 ft: "sixty"
at 50 ft: "fi fty"
at 40 ft: "forty"
at 30 ft: "thirty"
at 20 ft: "twenty"
at 10 ft: "ten"
at 5 ft: "fi ve"
at 100 ft above DH: "hundred above" or MDA or MDH + 100 ft
at DH: "minimum" or MDA or MDH

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A330-800/900 Navigation 34
Table 34-7 - Technical solutions description
TDU Title (Remarks) Appl. Weight (kg) Equipment Equipment Equipment QTY STS
MWE/OWE/APL reference supplier PN

19 Radio altitude automatic call- A330-800 0.0/0.0/0.0 Radio altitude TBD TBD SFE
outs A330-900 0.0/0.0/0.0
automatic call-outs

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34 Navigation A330-800/900
34.42.113 - Radio altimeter alternate equipment

Objective
To provide alternate vendors for radio altimeters equip-
ment.

Basic aircraft
Two radio altimeter systems generally in accordance
with ARINC 707 are installed.

Description
This option installs alternate radio altimeter transceivers
and antennas mechanically and electrically inter-
changeable with the basic equipment.

EPAC selection mode

Individual

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A330-800/900 Navigation 34
Figure 34-6 - Radio altimeters

Aft cargo compartment door

Transceiver 2 Transceiver 1

Antenna R2
Antenna T2
Antenna R1
Antenna T1

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34 Navigation A330-800/900
Table 34-8 - Technical solutions description
TDU Title (Remarks) Appl. Weight (kg) Equipment Equipment Equipment QTY STS
MWE/OWE/APL reference supplier PN

Std Radio altimeter - THALES AVI- A330-800 Radio altimeter THALES 9599-607- 4 SFE
ONICS A330-900
antenna AVIONICS SA 12352
Radio altimeter THALES 9599-607- 2 SFE
transceiver AVIONICS SA 19504
18 Radio altimeter - ROCKWELL A330-800 Negl./Negl./Negl. Radio altimeter ROCKWELL 622-8701-004 4 SFE
COLLINS serie 900 A330-900 Negl./Negl./Negl.
antenna COLLINS
Radio altimeter ROCKWELL 822-0334-020 2 SFE
transceiver COLLINS
19 Radio altimeter - HONEYWELL A330-800 Radio altimeter HONEYWELL 071-50026- 4 SFE
- "ALA52B" A330-900 Negl./Negl./Negl.
antenna INC. 0400
Radio altimeter HONEYWELL 066-50007- 2 SFE
transceiver INC. 0432

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34 Navigation A330-800/900
34.43.128 - Installation of T3CAS

Objective Note
To install T3CAS used as a T2CAS (TAWS + TCAS The contents of the terrain database are made available
only). by the various states, which are members of the ICAO
world organisation, to the supplier. Each state is re-
Basic aircraft sponsible for the definition of the content of the terrain
A TCAS II (change 7.1) system in accordance with database. It shall be the responsibility of the Buyer to
ARINC 735 is installed with Mode S ATC Transponder verify with the relevant states in which the Buyer oper-
in accordance with ARINC 718A. The ATC Transponder ates, the correctness of the information contained in the
is compliant with Elementary Surveillance (ELS), En- terrain database. Errors in the terrain data shall be re-
hanced Surveillance (EHS) and Extended Squitter (ES). ported to the relevant states and the supplier of the re-
lated equipment. In no case shall Airbus be held
Description responsible or liable for the contents, acquisition, use or
The modification consists in: updating of the terrain data base.
• tripping and collaring the EGPWS circuit breaker
• removing the EGPWC (full provision for EGPWS re-
main in place) Generally, a T3CAS from ACSS integrates three exist-
• adapting the T3CAS pin-programming and parity pin ing surveillance systems (TAWS, TCAS and ATC mode
• adapting labelling S transponder).
• connecting the T3CAS wiring
• installing 2 ACSS ATC transponders
EPAC selection mode
• installing 2 ACSS TCAS Antennas Individual
• installing the ACSS T3CAS computer (TCAS rack
position).

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A330-800/900 Navigation 34
Table 34-9 - Technical solutions description
TDU Title (Remarks) Appl. Weight (kg) Equipment Equipment Equipment QTY STS
MWE/OWE/APL reference supplier PN

13 Installation of T3CAS used as A330-800 -8.0/-8.0/8.0 ATC mode S ACSS-AN L3 9008000- 2 SFE
T2CAS - ACSS (-11209) / ATC A330-900 -8.0/-8.0/8.0
transponder COMMUNICATIO 12100
ACSS NXT-800 NS/THALES
A330-800 : Subject to certification
A330-900 : Subject to certification
T3CAS computer ACSS-AN L3 9005000- 1 SFE
COMMUNICATIO 11209
NS/THALES
TCAS directional ACSS-AN L3 751-4081-912 2 SFE
antenna COMMUNICATIO
NS/THALES

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34 Navigation A330-800/900
34.43.130 - TCAS II (ARINC 735) / ATC transponder alternate equipment

Objective Note
To provide alternate equipment for the TCAS II system For ATC TCAS control panel selection, see item
and the ATC transponder. 34.52.141.

Basic aircraft EPAC selection mode

A TCAS II (change 7.1) system in accordance with Individual
ARINC 735 is installed with Mode S ATC Transponder
in accordance with ARINC 718A. The ATC Transponder
is compliant with Elementary Surveillance (ELS) and
capable of Enhanced Surveillance (EHS).

Description
The basic TCAS configuration is replaced by an alter-
nate one.

TCAS installation consists of:

• installation of the TCAS / ATC computer in the avion-
ics compartment
• installation of two TCAS antennas
• installation of mode S ATC transponders, TCAS
compatible.

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A330-800/900 Navigation 34
Figure 34-7 - TCAS II (ARINC 735)

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34 Navigation A330-800/900
Table 34-10 - Technical solutions description
TDU Title (Remarks) Appl. Weight (kg) Equipment Equipment Equipment QTY STS
MWE/OWE/APL reference supplier PN

Std TCAS (ch7.1) - HONEYWELL A330-800 ATC mode S HONEYWELL 066-01212- 2 SFE
TPA100B (-006) / ATC - HONEY- A330-900
transponder INC. REDMOND, 0102
WELL (-0102) OLATHE
TCAS directional HONEYWELL 071-50001- 2 SFE
antenna INC. REDMOND, 8104
OLATHE
TCAS II computer HONEYWELL 940-0351-006 1 SFE
INC. REDMOND,
OLATHE
22 TCAS (ch7.1) - ROCKWELL A330-800 1.5/1.5/-1.5 ATC mode S ROCKWELL 822-1338-225 2 SFE
COLLINS TTR-2100 (-021) / A330-900 1.5/1.5/-1.5
transponder COLLINS
ATC EHS - ROCKWELL COL-
LINS TPR-901 (-225) TCAS directional ROCKWELL 622-8973-104 2 SFE
DO-260B capable
antenna COLLINS
TCAS II computer ROCKWELL 822-2911-021 1 SFE
COLLINS

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34 Navigation A330-800/900
34.43.400 - ATSAW applications

Objective Using a traffic selector switch, crew can select a specific

To enhance the efficiency and the safety of the flight aircraft to get more information as aircraft identification
thanks to a better traffic situational awareness. and ground speed. More information is available on
MCDU selecting the specific Traffic page.
Basic aircraft
None. ATSAW function:
• enhances the opportunity to flight level change
Description • optimizes the flight level and generates fuel savings
Airborne Traffic Situational AWareness (ATSAW) aims • improves cooperation with ATC (better understand-
at enhancing the flight crews' knowledge of the sur- ing of ATC instructions).
rounding traffic information. The principle is to display
permanently updated traffic information received via Note
ADS-B using mode S 1090 MHz. Requires prior acceptance of item:
• T3CAS (change 7.1) from ACSS (see item
34.43.128).
With ATSAW, the surrounding traffic information dis- • or with TCAS II (change 7.1) TPA100B from Honey-
played by default on ND is: well (basic item).
• the aircraft position
• the aircraft direction ITP operation is subject to availability of ATC service.
• the relative altitude
• the vertical speed tendency.
EPAC selection mode
Individual

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A330-800/900 Navigation 34
Table 34-11 - Technical solutions description
TDU Title (Remarks) Appl. Weight (kg) Equipment Equipment Equipment QTY STS
MWE/OWE/APL reference supplier PN

02 Activation of ATSAW function A330-800 Negl./Negl./Negl.

A330-900 Negl./Negl./Negl.

04 Activation of ATSAW function A330-800 Negl./Negl./Negl.

including ITP (In Trail Proce- A330-900
dure)

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34 Navigation A330-800/900
34.48.104 - Enhanced Ground Proximity Warning System (EGPWS) optional
functions
Objective Note
To provide activation of the Runway Awareness and • RAAS function activation is not compatible with
Advisory System (RAAS) in the Enhanced Ground T3CAS installation.
Proximity Warning System (EGPWS).
EPAC selection mode
Individual
Basic aircraft
An Enhanced Ground Proximity Warning Computer
(EGPWC) is basically installed on the aircraft.

Description
The RAAS provides flight crew with situational aware-
ness of aircraft position at approach, take-off and run-
way.

The proposed RAAS concept is an autonomous func-

tion housed within the EGPWS providing aural adviso-
ries in the cockpit while circulating on ground
(identification of the runway) by using GPS position data
and EGPWS runway database for defining "protection
area" around the runways.

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A330-800/900 Navigation 34
Table 34-12 - Technical solutions description
TDU Title (Remarks) Appl. Weight (kg) Equipment Equipment Equipment QTY STS
MWE/OWE/APL reference supplier PN

15 Activation of the RAAS func- A330-800 Negl./Negl./Negl.

tion in the EGPWS A330-900 Negl./Negl./Negl.

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34 Navigation A330-800/900
34.51.108 - DME interrogators alternate equipment

Objective
To provide alternate vendor for the DME interrogators.

Basic aircraft
Two DME interrogators generally in accordance with
ARINC 709 are installed together with two independent
L-band blade antennas on the fuselage.

Description
This modification consists in replacing the basic DME
interrogators by alternate equipment.

EPAC selection mode

Individual

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A330-800/900 Navigation 34
Figure 34-8 - DME interrogators
Avionics rack 800 VU

DME 1 and 2 interrogators

DME Antenna 2 DME Antenna 1

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34 Navigation A330-800/900
Table 34-13 - Technical solutions description
TDU Title (Remarks) Appl. Weight (kg) Equipment Equipment Equipment QTY STS
MWE/OWE/APL reference supplier PN

Std DME - ROCKWELL COLLINS A330-800 DME interrogator ROCKWELL 822-2325-020 2 SFE
serie 2100, PN 822-2325-020 A330-900
COLLINS

11 DME - HONEYWELL, PN 066- A330-800 Negl./Negl./Negl. DME interrogator HONEYWELL 066-50013- 2 SFE
50013-1222 A330-900 Negl./Negl./Negl.
INC. REDMOND, 1222
OLATHE

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34 Navigation A330-800/900
34.52.102 - Automatic Dependent Surveillance - Broadcast (ADS-B OUT)

Objective
To be compliant with ADS-B OUT requirements for Non
Radar Airspace (NRA) or / and Radar Airspace (RAD)
operations.

Basic aircraft
None.

Description
For NRA operation, the documentation has to be updat-
ed to be compliant with AMC-20-24 (AFM, FCOM).
For RAD and NRA operation, the documentation has to
be updated to show compliance of Automatic Depen-
dent Surveillance - Broadcast (ADS-B) with CS-ACNS
(EASA regulation) or with AC-20-165A (FAA regula-
tion).

Note
Not interchangeable with a transponder not capable of
ADS-B OUT.

EPAC selection mode

Individual

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A330-800/900 Navigation 34
Table 34-14 - Technical solutions description
TDU Title (Remarks) Appl. Weight (kg) Equipment Equipment Equipment QTY STS
MWE/OWE/APL reference supplier PN

04 Compliance with ADS-B OUT A330-800

regulation for RAD & NRA ops A330-900
including SBAS mode acti-
vated
Requires DO-260B capable ATC tran-
sponders
Requires SBAS capable MMR
A330-800 : Subject to certification
A330-900 : Subject to certification

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34 Navigation A330-800/900
34.53.100 - Installation of Automatic Direction Finder (ADF) system

Objective
To provide additional navigational capability along with
redundancy.

Basic aircraft
Structural provisions for two ADF systems, generally in
accordance with ARINC 712, are installed.

Description
The modification consists in installing wiring from the
avionics compartment to the antenna and the following
equipment on the existing provisions:
• a single or a dual ADF receiver(s)
• a single or a dual ADF combined loop and sense an-
tenna(s).

EPAC selection mode

Individual

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A330-800/900 Navigation 34
Figure 34-9 - ADF system

FMGEC FMGEC
1 2

RMP1 RMP2

VOR 1 VOR 2

DME 1 DME 2

ILS 1 ILS 2

ADF 1 ADF 2
Normal flow
Alternate flow

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34 Navigation A330-800/900
Table 34-15 - Technical solutions description
TDU Title (Remarks) Appl. Weight (kg) Equipment Equipment Equipment QTY STS
MWE/OWE/APL reference supplier PN

01 Installation of a single ADF - A330-800 8.0/8.0/-8.0 ADF antenna THALES C12351AA 1 SFE
ROCKWELL COLLINS (900 A330-900 8.0/8.0/-8.0
AVIONICS SA
SERIES)
ADF receiver ROCKWELL 822-0299-020 1 SFE
COLLINS
03 Installation of a dual ADF - A330-800 16.0/16.0/-16.0 ADF antenna THALES C12351AA 2 SFE
ROCKWELL COLLINS (900 A330-900 16.0/16.0/-16.0
AVIONICS SA
SERIES)
ADF receiver ROCKWELL 822-0299-020 2 SFE
COLLINS
09 Installation of a dual ADF - A330-800 17.0/17.0/-17.0 ADF antenna THALES C12351AA 2 SFE
HONEYWELL A330-900 17.0/17.0/-17.0
AVIONICS SA
ADF receiver HONEYWELL 066-50014- 2 SFE
INC. REDMOND, 1202
OLATHE
10 Installation of a single ADF - A330-800 8.5/8.5/-8.5 ADF antenna THALES C12351AA 1 SFE
HONEYWELL A330-900 8.5/8.5/-8.5
AVIONICS SA
ADF receiver HONEYWELL 066-50014- 1 SFE
INC. REDMOND, 1202
OLATHE

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34 Navigation A330-800/900
34.55.102 - VOR/Marker receivers alternate equipment

Objective
To provide alternate vendor for the VOR/Marker receiv-
ers.

Basic aircraft
Two VOR/Marker receivers generally in accordance
with ARINC 711 are installed with a dual omnidirectional
VOR antenna and a marker antenna.

Description
This modification consists in replacing the basic VOR/
Marker receivers by alternate equipment.

EPAC selection mode

Individual

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A330-800/900 Navigation 34
Figure 34-10 - VOR/Marker receivers

Avionics rack 800 VU

VOR 1 and 2 antenna

Marker antenna

VOR 1 and 2 receivers

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34 Navigation A330-800/900
Table 34-16 - Technical solutions description
TDU Title (Remarks) Appl. Weight (kg) Equipment Equipment Equipment QTY STS
MWE/OWE/APL reference supplier PN

Std VOR/MARKER receivers basic A330-800 VOR receiver ROCKWELL 822-0297-020 2 SFE
equipment - ROCKWELL COL- A330-900
COLLINS
LINS serie 900 (FM immune),
PN 822-0297-020

10 VOR/MARKER receivers alter- A330-800 Negl./Negl./Negl. VOR receiver HONEYWELL 69001410-200 2 SFE
nate equipment - HONEY- A330-900 Negl./Negl./Negl.
INC. REDMOND,
WELL, PN 69001410-200 OLATHE

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34 Navigation A330-800/900
34.58.310 - Multi Mode Receiver (MMR) alternate equipment

Objective
To provide alternate equipment for MMR.

Basic aircraft
Two MMR are installed.

Each one includes:

• an ILS card, a GPS card, space provisions for GLS
• two GPS active antennas are installed above the
cockpit
• loc and glide antennas are installed
• GPS information from MMR 1 and 2 are sent to
ADIRS 1, 2 and 3 for hybridization and then to
FMGEC 1 and 2 for calculation of the position.

GPS function is certified as per TSO C129 class C1 or

equivalent.

Description
The basic MMR are replaced by alternate equipment.

EPAC selection mode

Individual

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A330-800/900 Navigation 34
Table 34-17 - Technical solutions description
TDU Title (Remarks) Appl. Weight (kg) Equipment Equipment Equipment QTY STS
MWE/OWE/APL reference supplier PN

Std MMR - ROCKWELL COLLINS A330-800 GPS antenna ROCKWELL 822-2033-001 2 SFE
(with FLS/GLS capability) A330-900
COLLINS
With RNP AR capability
Multi Mode ROCKWELL 822-1821-430 2 SFE
Receiver (MMR) COLLINS
25 iMMR - HONEYWELL - Stan- A330-800 Negl./Negl./Negl. GPS Antenna HONEYWELL 071-50029- 2 SFE
dard L2.2 A330-900 Negl./Negl./Negl.
INC. REDMOND, 5510
OLATHE
Multi Mode HONEYWELL 69002602- 2 SFE
Receiver (MMR) INC. REDMOND, 0201
OLATHE
Software HONEYWELL HNR5326020 2 SFE
INC. 00504

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34 Navigation A330-800/900
34.58.316 - Activation of GLS function

Objective This GLS function enables to fly CAT I precision ap-

To offer GBAS Landing System (GLS) capability. proaches at airports equipped with Ground Based Aug-
mentation System (GBAS).
Basic aircraft
Two MMR are installed. EPAC selection mode
Each one includes: Individual
• an ILS card, a GPS card (containing complete provi-
sions for GLS and FLS functions)
• two GPS active antennas are installed above the
cockpit
• loc and glide antennas are installed
• GPS information from MMR 1 and 2 are sent to
ADIRS 1, 2 and 3 for hybridization and then to
FMGEC 1 and 2 for calculation of the position.

GPS function is certified as per TSO C129 class C1 or

equivalent.

Description
Depending on operational needs, the GLS additional
option shall be activated through a specific MMR pin-
programming.

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A330-800/900 Navigation 34
Table 34-18 - Technical solutions description
TDU Title (Remarks) Appl. Weight (kg) Equipment Equipment Equipment QTY STS
MWE/OWE/APL reference supplier PN

01 Activation of GLS function A330-800 Negl./Negl./Negl.

A330-800 : Subject to certification A330-900 Negl./Negl./Negl.
A330-900 : Subject to certification

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A330-800/900 Oxygen 35

Reference Title
35.11.120 In-situ replenishment facility for cockpit oxygen cylinder
35.21.110 Extended duration for passenger chemical oxygen system
35.21.115 Alternate lavatory gaseous oxygen supply
35.22.021 Installation of one additional mask in each oxygen box (chemical system)

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35 Oxygen A330-800/900
35.11.120 - In-situ replenishment facility for cockpit oxygen cylinder

Objective
To provide a system which permits convenient in-situ
replenishing of the flight crew oxygen cylinders.

Basic aircraft
• No replenishment facility.
• The concerned oxygen cylinders are removed from
the aircraft and replaced by full ones.
• Easy connection to the basic system.
• Space provisions is made for a ground filling connec-
tor

Description
Adaptation of the flight crew oxygen storage system, lo-
cated in the avionics compartment, to allow in-situ
charging of the two oxygen cylinders.
The modification consists in:
• Installation of a filling port connected to each of the
two oxygen regulators.
• Installation of flexible tubes and duct between the fill-
ing port and the regulators.

EPAC selection mode

Individual

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A330-800/900 Oxygen 35
Figure 35-1 - In-situ flight crew oxygen replenishment facility

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35 Oxygen A330-800/900
Table 35-1 - Technical solutions description
TDU Title (Remarks) Appl. Weight (kg) Equipment Equipment Equipment QTY STS
MWE/OWE/APL reference supplier PN

01 In-situ replenishment facility A330-800 1.8/1.8/-1.8 Filling port EROS DKR142 1 SFE
for cockpit oxygen cylinder A330-900 1.8/1.8/-1.8
assembly
(A330) - EROS, PN DKR142

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35 Oxygen A330-800/900
35.21.110 - Extended duration for passenger chemical oxygen system

Objective
To increase operational capability by providing extend-
ed duration for the passenger oxygen system.

Basic aircraft
A passenger chemical oxygen system with 15 minutes
duration capability.

Description
The basic passenger oxygen boxes are replaced by
boxes of increased oxygen generator capacity, at the
following locations:
• in the lateral and center supply channels above pas-
senger seats
• at all attendant stations
• in all lavatories
• in all entrance ceilings.

EPAC selection mode

Individual

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A330-800/900 Oxygen 35
Table 35-2 - Technical solutions description
TDU Title (Remarks) Appl. Weight (kg) Equipment Equipment Equipment QTY STS
MWE/OWE/APL reference supplier PN

01 Extended duration (22 min) of A330-800 Subject to customi- Hatrack and ceiling B/E AEROSPACE TBD 1 SFE
chemical oxygen generators - sation
A330-900 Subject to customi- self contained SYSTEMS GMBH
B/E Aerospace Systems GmbH sation emergency oxygen
set

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35 Oxygen A330-800/900
35.21.115 - Alternate lavatory gaseous oxygen supply

Objective
To install an alternate oxygen container in each lavato-
ry.

Basic aircraft
A chemical oxygen container with continuous flow
masks is installed in each lavatory.

Description
A decentralized gaseous oxygen container type II shall
be installed in each lavatory instead of a chemical oxy-
gen container.

Note
These containers are compliant with FAA Airworthiness
Directive (AD) 2012-11-09.

EPAC selection mode

Individual

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A330-800/900 Oxygen 35
Table 35-3 - Technical solutions description
TDU Title (Remarks) Appl. Weight (kg) Equipment Equipment Equipment QTY STS
MWE/OWE/APL reference supplier PN

01 Alternate lavatory gaseous A330-800 2.9/2.9/-2.9

oxygen supply (15 min) A330-900 2.9/2.9/-2.9
FAA AD 2012-11-09 compliant

02 Alternate lavatory gaseous A330-800 3.9/3.9/-3.9

oxygen supply (22 min) A330-900 3.9/3.9/-3.9
FAA AD 2012-11-09 compliant

SCG Issue 3 Revision 2, January 2021 35.21.115 Page 339

35 Oxygen A330-800/900
35.22.021 - Installation of one additional mask in each oxygen box (chemical
system)
Objective
To provide additional passenger oxygen masks in order
to allow unrestricted seating for passengers with in-
fants.

Basic aircraft
The number of passenger oxygen masks installed in the
passenger cabin shall exceed the number of passenger
seats by at least 10%.

A chemical passenger oxygen system is installed.

Description
Oxygen masks are added in the passenger oxygen box-
es in order to provide additional spare masks per seat
assembly.

The configuration shall be as follows:

• 3 masks per double seat
• 4 masks per triple seat
• 5 masks per center quadruple seat.

EPAC selection mode

Individual

SCG Issue 3 Revision 2, January 2021 35.22.021 Page 340

A330-800/900 Oxygen 35
Table 35-4 - Technical solutions description
TDU Title (Remarks) Appl. Weight (kg) Equipment Equipment Equipment QTY STS
MWE/OWE/APL reference supplier PN

11 Installation of one additional A330-800 Subject to customi- Set of passenger B/E AEROSPACE TBD 1 SFE
mask in each oxygen box sation
A330-900 Subject to customi- oxygen mask SYSTEMS GMBH
(chemical system) sation

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 A330-800/900

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A330-800/900 Water/waste 38

Reference Title
38.00.222 Water/waste system compliance certificates
38.10.104 Installation of water conditioner(s) in potable water system
38.11.112 Installation of additional potable water tank
38.11.116 Preselection of potable water at service panel

SCG Issue 3 Revision 2, January 2021 Page 343

38 Water/waste A330-800/900
38.00.222 - Water/waste system compliance certificates

Objective
To provide to the customer, at aircraft
delivery, statements for water/waste system compli-
ance with the US Public Health Service Standards (US-
PHSS) and/or certificate for potable water disinfection.

Basic aircraft
The water waste system design is compliant with the US
Public Health Service Standards (USPHSS) and disin-
fected. No corresponding certificate is provided to the
airline.

Description
The potable water system is disinfected prior to delivery
of the aircraft.

A statement of sanitary construction compliance and/or

disinfection result certificate shall be provided to the
customer at delivery of the aircraft.

EPAC selection mode

Individual

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A330-800/900 Water/waste 38
Table 38-1 - Technical solutions description
TDU Title (Remarks) Appl. Weight (kg) Equipment Equipment Equipment QTY STS
MWE/OWE/APL reference supplier PN

03 Disinfection result certificate A330-800 0.0/0.0/0.0

for potable water system A330-900 0.0/0.0/0.0

05 Statement of sanitary con- A330-800 0.0/0.0/0.0

struction for water and waste A330-900 0.0/0.0/0.0
system compliance with
USPHSS

SCG Issue 3 Revision 2, January 2021 38.00.222 Page 345

38 Water/waste A330-800/900
38.10.104 - Installation of water conditioner(s) in potable water system

Objective This helps to reduce aircraft water/waste system main-

To prevent build-up of limescale in the potable water tenance and cleaning efforts.
system including associated equipment as water heat-
ers, faucets etc. Note
The tanks are filled in parallel.
Basic aircraft
No system with limescale prevention capabilities in- EPAC selection mode
stalled. Individual

Description
The modification consists in the installation of:
• one small size water conditioner in the filling/distribu-
tion line below the potable water tank
• or two small size water conditioners with three pota-
ble water tanks.

The main advantage of the water conditioner installation

is the effect that calcium/mineral deposit in the aircraft
water/waste system is much softer and can be removed
very much easier.

SCG Issue 3 Revision 2, January 2021 38.10.104 Page 346

A330-800/900 Water/waste 38
Table 38-2 - Technical solutions description
TDU Title (Remarks) Appl. Weight (kg) Equipment Equipment Equipment QTY STS
MWE/OWE/APL reference supplier PN

03 Installation of one water condi- A330-800 2.0/2.0/-2.0 Water conditioner DIEHL AVIATION 9630602-2001 1 SFE
tioner in potable water system A330-900 2.0/2.0/-2.0
- DIEHL AVIATION, PN
9630602-2001

04 Installation of two water condi- A330-800 4.0/4.0/-4.0 Water conditioner DIEHL AVIATION 9630602-2001 2 SFE
tioners in potable water sys- A330-900 4.0/4.0/-4.0
tem - DIEHL AVIATION, PN
9630602-2001

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38 Water/waste A330-800/900
38.11.112 - Installation of additional potable water tank

Objective
To provide more cabin service flexibility especially for
long range flights.

Basic aircraft
• Two potable water tanks of 350 liters each.
• Structural provisions for the installation of an addi-
tional potable water tank.
• Wiring installed.
• Space provision in attendant panel.

Description
The modification consists in the installation of an addi-
tional of a 350 liters potable water tank which provides
up to 1 050 liters of water.

EPAC selection mode

Individual

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A330-800/900 Water/waste 38
Figure 38-1 - Potable water third tank installation (1 050 liters)

Potable water tank

useable capacity: 350 liters

SCG Issue 3 Revision 2, January 2021 38.11.112 Page 349

38 Water/waste A330-800/900
Table 38-3 - Technical solutions description
TDU Title (Remarks) Appl. Weight (kg) Equipment Equipment Equipment QTY STS
MWE/OWE/APL reference supplier PN

01 Installation of a third potable A330-800 35.0/385.0/-385.0 Potable water tank DIEHL AVIATION 93-3600-00- 1 SFE
water tank (total capacity 1 050 A330-900 35.0/385.0/-385.0
(350 liters) 00X
liters)

SCG Issue 3 Revision 2, January 2021 38.11.112 Page 350

A330-800/900 Water/waste 38

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38 Water/waste A330-800/900
38.11.116 - Preselection of potable water at service panel

Objective
To remove the preselection from the FAP and to install
it on the water service panel located in the underside of
the rear fuselage.

Basic aircraft
The water quantity indication and preselection is made
through the Flight Attendant Panel (FAP).

Description
The system will be able to preselect at least four prede-
termined water quantities according to the flight time
and the actual number of passengers on board. To have
an indication of the actual water quantity a quantity indi-
cator will be installed on the service panel. The total wa-
ter quantity will be indicated. When the water level in the
tanks reaches the preselected quantity the filling proce-
dure will be stopped automatically by closing of the elec-
trically driven fill/drain- ventilation valves.

EPAC selection mode

Individual

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A330-800/900 Water/waste 38
Table 38-4 - Technical solutions description
TDU Title (Remarks) Appl. Weight (kg) Equipment Equipment Equipment QTY STS
MWE/OWE/APL reference supplier PN

04 Water quantity preselection of A330-800 Negl./Negl./Negl.

potable water at service panel A330-900 Negl./Negl./Negl.
(A330)

SCG Issue 3 Revision 2, January 2021 38.11.116 Page 353

 A330-800/900

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A330-800/900 Information systems 46

Reference Title
46.21.100 Installation of Airline Operational Communication (AOC) software for Air Traffic Service
Unit (ATSU)
46.21.105 Activation of ARINC 623 in the ATSU
46.21.111 Activation of VDL mode 2 function in the ATSU
46.21.113 Installation of Future Air Navigation System (FANS) C
46.26.400 Flight Operations and Maintenance eXchange (FOMAX)
46.26.401 ACARS over IP communication

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46 Information systems A330-800/900
46.21.100 - Installation of Airline Operational Communication (AOC) software for Air
Traffic Service Unit (ATSU)
Objective Note
To provide Airbus Standard definition of Airline Opera- A) Airline customized AOC
tional Communication (AOC) in the Air Traffic Service In case of installation of airline customized AOC, it is not
Unit. This AOC software supports data communications required to raise an RFC for the selection of the Airbus
between the aircraft and the airline facilities on the Standard AOC. Order/installation of customized AOC is
ground. not managed/recorded by Airbus.

Basic aircraft B) Ground system and service provider

The aircraft is equipped with an ATSU (hardware + soft- Use of the ATSU requires installation of airline ground
ware including ACARS router). system and contract with datalink Service Providers.

Availability of ACARS router functionality (e.g. interface C) Customization of the AOC software
with systems such as FMS, CMS, ACMS) does not re- Customization of the AOC function is done by the airline
quire installation of AOC software. and its selected AOC supplier. It does not require air-
worthiness re-certification of the ATSU.
Description Particular attention should be given to compatibility of
This modification consists in installing in the ATSU, via the customized AOC software with the ATSU aircraft in-
data loading, the Airbus Standard AOC software from terface (core) software.
the selected supplier.
D) Customization of the ATSU
In order to use the ATSU, it must be configured with air-
line specific information. Providing this information is
supplied by the operator during the delivery process,

SCG Issue 3 Revision 2, January 2021 46.21.100 Page 356

A330-800/900 Information systems 46
46.21.100 - Installation of Airline Operational Communication (AOC) software for Air
Traffic Service Unit (ATSU) (Continued)
Airbus may customize the ATSU during delivery under
direct responsibility of the airline (configuration of AC-
ARS router and VHF scan mask). In addition, Airbus
may install the customized AOC software.

Should problem occur during the customization process

or if the operator does not provide customization infor-
mation in due time, the aircraft will be delivered with de-
fault ATSU configuration: default router and scan mask
configuration.

Information to be provided during the delivery process:

• airline identification: 2 characters and 3 characters
code
• list and regional applicability of datalink Service Pro-
viders contracted by the airline for VHF 3 Scan Mask
(e.g. SITA Europe, SITA Pacific, Arinc, Avicom, Air
Canada)
• customized AOC software (if Airbus Standard AOC
are not used by the airline).

EPAC selection mode

Individual

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46 Information systems A330-800/900
Table 46-1 - Technical solutions description
TDU Title (Remarks) Appl. Weight (kg) Equipment Equipment Equipment QTY STS
MWE/OWE/APL reference supplier PN

30 Airbus AOC software for ATSU A330-800 0.0/0.0/0.0 AOC application ROCKWELL 222-9888-001 1 BFE
(weights in ton) - ROCKWELL A330-900 0.0/0.0/0.0
software CD for COLLINS
COLLINS ATSU
Only compatible with CLR 9.
A330-800 : Subject to certification
A330-900 : Subject to certification AOC database CD ROCKWELL 222-9359-202 1 BFE
for ATSU COLLINS
31 Airbus AOC software for ATSU A330-800 0.0/0.0/0.0 AOC application ROCKWELL 222-9888-001 1 BFE
(weights in klbs) - ROCKWELL A330-900 0.0/0.0/0.0
software CD for COLLINS
COLLINS ATSU
Only compatible with CLR 9.
A330-800 : Subject to certification
A330-900 : Subject to certification AOC database CD ROCKWELL 222-9361-202 1 BFE
for ATSU COLLINS
32 Airbus AOC software for ATSU A330-800 0.0/0.0/0.0 AOC application HONEYWELL SWM6900237 1 BFE
(weights in kg) - HONEYWELL A330-900 0.0/0.0/0.0
software CD for INC. REDMOND, 5-513
A330-800 : Subject to certification ATSU OLATHE
A330-900 : Subject to certification

AOC database CD HONEYWELL SWM6900238 1 BFE

for ATSU INC. REDMOND, 0-510
OLATHE
33 Airbus AOC software for ATSU A330-800 0.0/0.0/0.0 AOC application HONEYWELL SWM6900237 1 BFE
(weights in lbs) - HONEYWELL A330-900 0.0/0.0/0.0
software CD for INC. REDMOND, 5-513
A330-800 : Subject to certification ATSU OLATHE
A330-900 : Subject to certification

AOC database CD HONEYWELL SWM6900238 1 BFE

for ATSU INC. REDMOND, 1-510
OLATHE

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A330-800/900 Information systems 46

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46 Information systems A330-800/900
46.21.105 - Activation of ARINC 623 in the ATSU

Objective
To provide Departure Clearance (DCL), Oceanic Clear-
ance (OCL) and Automatic Terminal Information Sys-
tem (ATIS) applications.

Basic aircraft
An ATSU is installed providing ACARS function.

Description
Airbus certified (DO178B level C) A623 applications
shall be loaded into the ATSU.

The ATSU software must be upgraded to receive A623

applications.

EPAC selection mode

Individual

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A330-800/900 Information systems 46
Table 46-2 - Technical solutions description
TDU Title (Remarks) Appl. Weight (kg) Equipment Equipment Equipment QTY STS
MWE/OWE/APL reference supplier PN

01 Activation of ARINC 623 in the A330-800 0.0/0.0/0.0

ATSU A330-900 0.0/0.0/0.0

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46 Information systems A330-800/900
46.21.111 - Activation of VDL mode 2 function in the ATSU

Objective
To provide VDL mode 2 over the ACARS network
(VDL2/AOA) to improve air/ground digital communica-
tion.

Basic aircraft
An ATSU is installed providing ACARS function. VDR,
with VDL mode 2 capability, are installed.

Description
The VDL Mode 2/AOA (ACARS over AVLC: Aviation
VHF Link Control) capability shall be activated in the
ATSU.

EPAC selection mode

Individual

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A330-800/900 Information systems 46
Figure 46-1 - VHF Datalink (VDL) Technologies: Mode 2/AOA
Activation of VDL2 over ACARS or ATN

ACARS ATN
Environment Environment
2.4Kbps 31.5Kbps

ACARS ground/ground Central

Network (2.4Kbps) Processors

ATN Router
Airline Air
Operations Traffic
Control Control

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46 Information systems A330-800/900
Table 46-3 - Technical solutions description
TDU Title (Remarks) Appl. Weight (kg) Equipment Equipment Equipment QTY STS
MWE/OWE/APL reference supplier PN

01 Activation of VDL mode 2 func- A330-800 0.0/0.0/0.0 ATSU software AIRBUS TBD 1 SFE
tion in the ATSU A330-900 0.0/0.0/0.0

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A330-800/900 Information systems 46

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46 Information systems A330-800/900
46.21.113 - Installation of Future Air Navigation System (FANS) C

Objective • Activating the VDL mode 2 function for ACARS and

FANS C shall be installed to support data link opera- ATN networks
tions in all FANS environment: • On top of FANS C, the following functions, if request-
• FANS B (ATN B1 and B2) in European continental ed and if available, will have to be activated through
high density area, above FL 285 to support ATC (Air separate RFCs:
Traffic Control) data link operations over VDL (VHF • RMP interface for the frequency loading function
Data Link) Mode 2 / ATN (Aeronautical Telecommu- • TCAS interface for capacity of ITP function.
nication Network)
• FANS 1/A in oceanic / remote areas and USA conti- Note
nental, through ACARS (Aircraft Communication CLR9 is a prerequisite for FANS C in combination with
Adressing and Reporting System) network. ATSU hardware A10.
Basic aircraft
The aircraft is certified for FANS 1/A operations. EPAC selection mode
Individual
The following applications are installed in the ATSU:
Controller-Pilot Data Link Communications (CPDLC),
Automatic Dependant Surveillance (ADS-C) and ATC
facilities Notification (AFN) as per RTCADO212 and
ARINC 622 respectively.

Description
• FANS C applications (ADS-C, CPDLC) supports all
existing FANS 1/A and in addition FANS B+ (ATN B1
and B2) operations to make the aircraft capable of
CPDLC over VDL2/ATN in compliance with EURO-
CAE ED110B and ED120.

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A330-800/900 Information systems 46
Table 46-4 - Technical solutions description
TDU Title (Remarks) Appl. Weight (kg) Equipment Equipment Equipment QTY STS
MWE/OWE/APL reference supplier PN

01 Installation of Future Air Navi- A330-800 Negl./Negl./Negl. Air Traffic Services AIRBUS LA2T0J1307R 1 SFE
gation System (FANS) C A330-900 Negl./Negl./Negl.
Unit (ATSU) 00F1

02 Installation of Future Air Navi- A330-800 Negl./Negl./Negl. Air Traffic Services AIRBUS LA2T0J1307R 1 SFE
gation System (FANS) C / 4D A330-900 Negl./Negl./Negl.
Unit (ATSU) 00F1
A330-800 : Subject to Airbus approval
A330-900 : Subject to Airbus approval

SCG Issue 3 Revision 2, January 2021 46.21.113 Page 367

46 Information systems A330-800/900
46.26.400 - Flight Operations and Maintenance eXchange (FOMAX)

Objective
FOMAX acts as an Aircraft Interface Device (AID) pro-
viding on optional basis:
• a wireless access point in the cockpit for EFB tablets
and access to aircraft communication means and
avionics data. Such functionality has to be activated
on an optional basis and associated tablets and EFB
applications would be under operator control and re-
sponsibility.
• a cellular gatelink to transmit aircraft data directly to
the operator through dedicated cellular gatelink con-
nection
• a connection with the SATCOM
• a connection with the ATSU.
The FOMAX is also a system gathering extended flight
parameters which can be transmitted, subject to airline
data sharing agreement, to the Airbus Skywise platform
via cellular Gatelink.

EPAC selection mode

Individual

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A330-800/900 Information systems 46
Table 46-5 - Technical solutions description
TDU Title (Remarks) Appl. Weight (kg) Equipment Equipment Equipment QTY STS
MWE/OWE/APL reference supplier PN

02 Activation of cockpit tablets A330-800 Negl./Negl./Negl.

connectivity A330-900 Negl./Negl./Negl.

03 Activation of ACARS connec- A330-800 Negl./Negl./Negl.

tion for cockpit tablets A330-900 Negl./Negl./Negl.

06 Activate Cellular Gatelink for A330-800 Negl./Negl./Negl.

Airlines A330-900 Negl./Negl./Negl.

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46 Information systems A330-800/900
46.26.401 - ACARS over IP communication

Objective
To allow sending messages through IP communication
means.

Description
ACARS over IP aims at reducing the ACARS communi-
cation flow for the benefit of the Internet communica-
tions. It allows to send messages via IP communication
means instead of Aircraft Communication Addressing
and Reporting System (ACARS) communication
means.

EPAC selection mode

Individual

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A330-800/900 Information systems 46
Table 46-6 - Technical solutions description
TDU Title (Remarks) Appl. Weight (kg) Equipment Equipment Equipment QTY STS
MWE/OWE/APL reference supplier PN

01 Activate ACARS over IP A330-800

A330-900

SCG Issue 3 Revision 2, January 2021 46.26.401 Page 371

 A330-800/900

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A330-800/900 Structures 51

Reference Title
51.22.240 Base Coat /Clear Coat with intermediate coat paint system on customized areas
51.22.250 Large decorative adhesive film

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51 Structures A330-800/900
51.22.240 - Base Coat /Clear Coat with intermediate coat paint system on
customized areas
Objective
To apply on fuselage and vertical stabilizer, beneath the The following paint system is applied:
Base Coat /Clear Coat finish, a strippable intermediate • low VOC Chromate Free (CF) primer,
coat, which reduces time and cost during maintenance • intermediate layer coat,
process. • Base Coat,
• Clear Coat.
The intermediate coat between the primer and the base
Basic aircraft
The basic paint scheme applied on fuselage and verti- coat enables a selective stripping which reduce time
cal stabilizer is composed of: and cost during maintenance process.
• low VOC Chromate Free (CF) primer,
• Base Coat, Note
• Clear Coat. Please refer to "A330 External Painting guidelines" bro-
This materiel is fully compliant with Health, Safety and chure for further details.
Environmental (HSE) regulations.
EPAC selection mode
Airbus will choose the paint supplier and the associated Individual
paint material in line with the paint system chosen by the
Airline.

Description
The Low Volatile Organic Compound (VOC) and Chro-
mate Free primer, strippable intermediate coat paint
system and finish Base Coat /Clear Coat shall be ap-
plied on fuselage and vertical stabilizer.

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A330-800/900 Structures 51
Figure 51-1 - Base Coat / Clear Coat with intermediate coat paint system

r r r r
e r ote rime r ote rime
im ro m p me
i ro m p t
pr p ee cp
r n p e free e coa
sic ion ate fr s i si o
B a h e s Ba he at iat
Ad hrom t Ad hrom rmed at
C
e coa oat Intermediate coat applied C
Int
e o
e c coat
s s
Ba lear c B a ar
C between the Cle
primer and the top coat

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51 Structures A330-800/900
Table 51-1 - Technical solutions description
TDU Title (Remarks) Appl. Weight (kg) Equipment Equipment Equipment QTY STS
MWE/OWE/APL reference supplier PN

05 Base Coat /Clear Coat with A330-800 17.6/17.6/-17.6

intermediate coat paint sys- A330-900 18.9/18.9/-18.9
tem on customized areas

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A330-800/900 Structures 51

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51 Structures A330-800/900
51.22.250 - Large decorative adhesive film

Objective
To answer specific request on external livery using
large decorative adhesive film.

Basic aircraft
The general paint scheme is based on conventional
spray process.

Description
Standard external livery is generally provided with a
paint process nevertheless decorative adhesive film
can be used for complex decor/logo.

Note
Please refer to "A330 External Painting guidelines" bro-
chure for further details.

EPAC selection mode

Individual

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A330-800/900 Structures 51
Table 51-2 - Technical solutions description
TDU Title (Remarks) Appl. Weight (kg) Equipment Equipment Equipment QTY STS
MWE/OWE/APL reference supplier PN

40 Application of SFE decorative A330-800 Subject to customi- Set of decorative ADHETEC SARL 13880 FILM 1 SFE
adhesive film, ADHETEC 13880 sation
A330-900 Subject to customi- adhesive film
sation

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 A330-800/900

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A330-800/900 Doors 52

Reference Title
52.10.107 Type "A" door number 3
52.51.103 Cockpit door locking back-up systems (MMEL conditions)
52.51.104 Install damping devices to reduce noise by door slam

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52 Doors A330-800/900
52.10.107 - Type "A" door number 3

Objective for A330-900

To meet emergency evacuation requirements for cer- Note for A330-900
tain high density layouts. Installation of cabin attendant seats at door 3 is required
in case of type "A" door selection: refer to Cabin Config-
Basic aircraft for A330-900 uration Guide, ATA 25-22.
A type "I" emergency exit is installed at door 3.
EPAC selection mode
The maximum number of passenger seats is 375 Individual
(EASA/FAA):
• between door 2 and door 3: 155
• between door 3 and door 4: 155
• between door 2 and door 4: 265.

Description for A330-900

Type "I" emergency exit shall be replaced by type "A"
passenger/crew door 3 including double escape slide
rafts.

The maximum number of passenger seats is 440

(EASA/FAA):
• between door 2 and door 3: 220
• between door 3 and door 4: 220
• between door 2 and door 4: 330.
Type "A" door dimensions: 1.07 m x 1.93 m (42.1 in x
76.0 in).

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A330-800/900 Doors 52
Figure 52-1 - Pax arrangement per door (A330-900)

Door Type A Door Type A Door Type A Door Type A

110 pax 110 pax 110 pax 110 pax

Door Type 1
45 pax

Maximum pax:
EASA/FAA
with door 1: 375
with door A: 440

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52 Doors A330-800/900
Table 52-1 - Technical solutions description
TDU Title (Remarks) Appl. Weight (kg) Equipment Equipment Equipment QTY STS
MWE/OWE/APL reference supplier PN

01 Type "A" door number 3 A330-900 240.0/324.0/-324.0

A330-900 : Subject to lead time con-
straints

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A330-800/900 Doors 52

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52 Doors A330-800/900
52.51.103 - Cockpit door locking back-up systems (MMEL conditions)

Objective
To ensure the cockpit door locking capability in case of
Cockpit Door Locking System (CDLS) failure to cover
MMEL conditions.

Basic aircraft
The cockpit door incorporates an electrical release latch
controlled by a pushbutton installed on the pedestal.

Description
Two systems are proposed in back up:
• Installation of a second control unit on the overhead
panel including all necessary switches, relays and
associated wire harness. A guarded switch shall pro-
vide three selections: NORM / BK UP / OFF. This
electrical system shall provide a CDLS override func-
tion.
• A dead bolt is integrated with the center door latch on
the right side of the cockpit wall. The dead bolt shall
provide a means to lock the cockpit door manually in
the cockpit in case of electrical locking system fail-
ure.

EPAC selection mode

Individual

SCG Issue 3 Revision 2, January 2021 52.51.103 Page 386

A330-800/900 Doors 52
Figure 52-2 - Deadbolt for manual locking

SCG Issue 3 Revision 2, January 2021 52.51.103 Page 387

52 Doors A330-800/900
Figure 52-3 - Switch location for electrical door locking system on cockpit panel

SCG Issue 3 Revision 2, January 2021 52.51.103 Page 388

A330-800/900 Doors 52
Table 52-2 - Technical solutions description
TDU Title (Remarks) Appl. Weight (kg) Equipment Equipment Equipment QTY STS
MWE/OWE/APL reference supplier PN

01 Electrical cockpit door locking A330-800 4.5/4.5/-4.5

back-up system (MMEL condi- A330-900 4.5/4.5/-4.5
tions)

02 Installation of deadbolt for A330-800 0.6/0.6/-0.6

manual locking of cockpit door A330-900

SCG Issue 3 Revision 2, January 2021 52.51.103 Page 389

52 Doors A330-800/900
52.51.104 - Install damping devices to reduce noise by door slam

Objective
To install damping devices for the cockpit door to re-
duce noise caused by door slam.

Basic aircraft
None.

Description
The modification consists in installing an hydraulic me-
chanical damping device.

EPAC selection mode

Individual

SCG Issue 3 Revision 2, January 2021 52.51.104 Page 390

A330-800/900 Doors 52
Table 52-3 - Technical solutions description
TDU Title (Remarks) Appl. Weight (kg) Equipment Equipment Equipment QTY STS
MWE/OWE/APL reference supplier PN

01 Install damping devices to A330-800 2.0/2.0/-2.0

reduce noise by door slam A330-900 2.0/2.0/-2.0

SCG Issue 3 Revision 2, January 2021 52.51.104 Page 391

 A330-800/900

Intentionally left blank

SCG Issue 3 Revision 2, January 2021 52.51.104 Page 392

A330-800/900 Fuselage 53

Reference Title
53.60.180 Application of heavy duty floor panels

SCG Issue 3 Revision 2, January 2021 Page 393

53 Fuselage A330-800/900
53.60.180 - Application of heavy duty floor panels

Objective
To enhance the impact resistance of the bulk cargo floor
panels.

Basic aircraft
Basic high impact resistance bulk cargo floor panels are
installed.

Description
The basic installed bulk cargo floor panels will be re-
placed by heavy duty advanced S8A glass cargo floor
panels.

Note
The change will be from current S6 glass floor panels to
S8A glass floor panels.

EPAC selection mode

Individual

SCG Issue 3 Revision 2, January 2021 53.60.180 Page 394

A330-800/900 Fuselage 53
Table 53-1 - Technical solutions description
TDU Title (Remarks) Appl. Weight (kg) Equipment Equipment Equipment QTY STS
MWE/OWE/APL reference supplier PN

02 Application of heavy duty floor A330-800 8.0/8.0/-8.0

panels in bulk cargo compart- A330-900 8.0/8.0/-8.0
ment

SCG Issue 3 Revision 2, January 2021 53.60.180 Page 395

 A330-800/900

Intentionally left blank

SCG Issue 3 Revision 2, January 2021 53.60.180 Page 396

A330-800/900 Stabilizers 55

Reference Title
55.30.101 Metal sheet cover on fin leading edge for erosion protection

SCG Issue 3 Revision 2, January 2021 Page 397

55 Stabilizers A330-800/900
55.30.101 - Metal sheet cover on fin leading edge for erosion protection

Objective
To protect the vertical stabilizer leading edge against
erosion.

Basic aircraft
None.

Description
A stainless steel cover is installed on fin leading edges:
• number 1, 2 and 3 on A330-900
• number 1, 2, 3 and 4 on A330-800.

On each leading edge, the stainless steel cover is in-

stalled with an interfacing sealant and screwed on both
ends.

Note
The stainless steel cover shall not be painted.

Please refer to "A330 External Painting guidelines" bro-

chure for further details.

EPAC selection mode

Individual

SCG Issue 3 Revision 2, January 2021 55.30.101 Page 398

A330-800/900 Stabilizers 55
Figure 55-1 - Metal sheet cover on fin leading edge

L/E 4 A

L/E 3 L/E 3

L/E 2 L/E 2

L/E 1
L/E 1

A330-800 layout A330-900 layout

Stainless steel cover without top paint on outside

L/E: Leading edge
Erosion protection paint

SCG Issue 3 Revision 2, January 2021 55.30.101 Page 399

55 Stabilizers A330-800/900
Table 55-1 - Technical solutions description
TDU Title (Remarks) Appl. Weight (kg) Equipment Equipment Equipment QTY STS
MWE/OWE/APL reference supplier PN

01 Metal sheet cover on vertical A330-800 6.0/6.0/-6.0

stabilizer A330-900 6.0/6.0/-6.0

SCG Issue 3 Revision 2, January 2021 55.30.101 Page 400

A330-800/900 Windows 56

Reference Title
56.10.110 Cockpit windows selection

SCG Issue 3 Revision 2, January 2021 Page 401

56 Windows A330-800/900
56.10.110 - Cockpit windows selection

Objective
To provide a vendor selection for cockpit windows.

Basic aircraft
• Four cockpit lateral windows (two sliding and two
fixed).
• Two cockpit front windows (all fixed).

Description
This option allows the customer to select a vendor for
the cockpit windows from the proposed technical solu-
tions

Note
The standard technical solution is PPG INDUSTRIES
cockpit windows.

EPAC selection mode

Individual

SCG Issue 3 Revision 2, January 2021 56.10.110 Page 402

A330-800/900 Windows 56
Figure 56-1 - Cockpit windows

Front windows

Sliding window

Guiding track

Control handle

FW
D

Lateral fixed window Lateral sliding window

SCG Issue 3 Revision 2, January 2021 56.10.110 Page 403

56 Windows A330-800/900
Table 56-1 - Technical solutions description
TDU Title (Remarks) Appl. Weight (kg) Equipment Equipment Equipment QTY STS
MWE/OWE/APL reference supplier PN

01 Front and side cockpit win- A330-800 Fixed side window PPG NP175233-1 1 SFE
dows - PPG INDUSTRIES A330-900 0.0/0.0/0.0
(LH) INDUSTRIES
Fixed side window PPG NP175233-2 1 SFE
(RH) INDUSTRIES
Front windshield PPG NP175201-5 1 SFE
panel (LH) INDUSTRIES
Front windshield PPG NP175201-6 1 SFE
panel (RH) INDUSTRIES
Sliding side window PPG NP175232-1 1 SFE
(LH) INDUSTRIES
Sliding side window PPG NP175232-2 1 SFE
(RH) INDUSTRIES

SCG Issue 3 Revision 2, January 2021 56.10.110 Page 404

A330-800/900 Windows 56
TDU Title (Remarks) Appl. Weight (kg) Equipment Equipment Equipment QTY STS
MWE/OWE/APL reference supplier PN

03 Front and side cockpit win- A330-800 Fixed side window SAINT-GOBAIN SPSA340-6-1- 1 SFE
dows - SAINT-GOBAIN SULLY A330-900
(LH) SULLY 1
A330-800 : Subject to certification
A330-900 : Subject to certification
Fixed side window SAINT-GOBAIN SPSA340-5-1- 1 SFE
(RH) SULLY 1
Front windshield SAINT-GOBAIN SPSA340-2-6- 1 SFE
panel (LH) SULLY 1
Front windshield SAINT-GOBAIN SPSA340-1-6- 1 SFE
panel (RH) SULLY 1
Sliding side window SAINT-GOBAIN SPSA340-4-1- 1 SFE
(LH) SULLY 1
Sliding side window SAINT-GOBAIN SPSA340-3-1- 1 SFE
(RH) SULLY 1

SCG Issue 3 Revision 2, January 2021 56.10.110 Page 405

 A330-800/900

Intentionally left blank

SCG Issue 3 Revision 2, January 2021 56.10.110 Page 406

A330-800/900 Engines 72

Reference Title
72.00.160 Alternate A330-800/900 thrust ratings

SCG Issue 3 Revision 2, January 2021 Page 407

72 Engines A330-800/900
72.00.160 - Alternate A330-800/900 thrust ratings

Objective
To offer alternate thrust ratings on A330-800/900 en-
gines.

Basic aircraft
RR Trent 7000 engines at 72 850 lbf (324 kN).

Description
Alternate thrust ratings are offered for hot and high op-
erations and/or increased Maximum Takeoff Weight
(MTOW).

EPAC selection mode

Individual

SCG Issue 3 Revision 2, January 2021 72.00.160 Page 408

A330-800/900 Engines 72
Table 72-1 - Technical solutions description
TDU Title (Remarks) Appl. Weight (kg) Equipment Equipment Equipment QTY STS
MWE/OWE/APL reference supplier PN

02 Engine RR Trent 7000 at 68 555 A330-800 0.0/0.0/0.0

lbf nominal thrust A330-900 0.0/0.0/0.0
A330-800 : Subject to certification
A330-900 : Subject to certification

SCG Issue 3 Revision 2, January 2021 72.00.160 Page 409

 A330-800/900

Intentionally left blank

SCG Issue 3 Revision 2, January 2021 72.00.160 Page 410

A330-800/900 Oil 79

Reference Title
79.20.100 Engine, engine accessories and APU lubricating oil alternate equipment

SCG Issue 3 Revision 2, January 2021 Page 411

79 Oil A330-800/900
79.20.100 - Engine, engine accessories and APU lubricating oil alternate equipment

Objective
To provide alternate vendor choice for engine/APU lu-
bricating oil.

Basic aircraft
Oil EASTMAN OIL 2197 (BP 2197) is installed.
Oil quantity can be checked permanently on the ECAM
page, or visually at the oil tank.

Description
Change lubricating oil type in the following equipment:
• engine
• engine starter
• IDG
• APU.

Instruction labels on the oil system will also be replaced.

EPAC selection mode

Individual

SCG Issue 3 Revision 2, January 2021 79.20.100 Page 412

A330-800/900 Oil 79
Figure 79-1 - Oil indication

APU

AVAIL
APU GEN
70 %
115 V BLEED
400 HZ 0 PSI

10 N
% FUEL LO PR
0 100
FLAP OPEN
7 11 EGT
5 °C LOW OIL LEVEL
3 500

Engine page APU page

SCG Issue 3 Revision 2, January 2021 79.20.100 Page 413

79 Oil A330-800/900
Table 79-1 - Technical solutions description
TDU Title (Remarks) Appl. Weight (kg) Equipment Equipment Equipment QTY STS
MWE/OWE/APL reference supplier PN

Std Engine, engine accessories A330-800

and APU lubricating oil - East- A330-900
man Oil 2197 (BP 2197)

16 Engine, engine accessories A330-800 Negl./Negl./Negl.

IDG and APU lubricating oil - A330-900 Negl./Negl./Negl.
Mobil Jet Oil 387
A330-800 : Subject to certification

SCG Issue 3 Revision 2, January 2021 79.20.100 Page 414

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