A320 System Configuration Guide

System Configuration Guide A320 Family Issue 6, Revision 1

January 2012 Document in accordance with the following Standard Specifications: A318-100 P 000 01000 issue 04 A319-100 J 000 01000 issue 07 A320-200 D 000 02000 issue 08 A321-200 E 000 02000 issue 05

Authorized by BSMC CC1200001

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A320 Family Title

Table of contents ATA

Title

ATA

Introduction

00

Water/waste

38

Certification and external livery

02

Information systems

46

General aircraft design criteria

03

Auxiliary Power Unit (APU)

49

Placards and markings

11

Structures

51

Air conditioning

21

Doors

52

Auto flight

22

Fuselage

53

Communications

23

Stabilizers

55

Electrical power

24

Windows

56

Equipment/furnishings

25

Wings

57

Fire protection

26

Engines

72

Fuel

28

Engine fuel and control

73

Hydraulic power

29

Oil

79

Ice and rain protection

30

Indicating/recording systems

31

Landing gear

32

Lights

33

Navigation

34

Oxygen

35

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TITLE

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Introduction

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00.00.200 - Introduction

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Certification and external livery

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02.10.104 - Certification of dynamically tested passenger seats 02.10.111 - Compliance with FAA type certification requirements 02.10.112 - Partial compliance with FAA type certification requirements 02.10.120 - 15 knots tailwind certification 02.10.123 - Operation on runways with reduced width 02.10.190 - ETOPS 120/180 min 02.12.122 - Compliance status with EU-OPS 1 02.12.123 - Compliance with CS25/FAR 25.562 (Head Injury Criteria - HIC) 02.12.130 - EASA certification of Take Off/Landing operation on wet grooved / PFC runways 02.40.101 - External livery

General aircraft design criteria 03.20.300 - Design weights (A318) 03.20.400 - Design weights (A319)

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Detailed table of contents Detailed table of contents TITLE 03.20.500 - Design weights (A320) 03.20.600 - Design weights (A321)

Placards and markings 11.00.124 - Installation of leasing identification plates 11.20.100 - Second language for door operation external placards and markings 11.20.110 - Second language for selected external placards and markings 11.20.119 - Nose Landing Gear (NLG) permanent steering markers 11.20.135 - Second language for residual cabin & cargo pressure exterior door warning placards 11.21.101 - Emergency cut-out markings 11.22.100 - Landing gear placards 11.30.100 - Installation of additional access placards in forward and aft cargo holds 11.30.121 - Second language for cargo compartment placards 11.30.136 - US and metric units for cargo compartment height placards 11.33.101 - Placard for flight crew oxygen system

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Air conditioning

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21.20.108 - Cabin air recirculation filter cartridges equipment selection 21.22.100 - Installation of electrical heaters for foot air outlets in the cockpit 21.26.110 - Avionics ventilation fan automatic speed reduction

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Detailed table of contents

TITLE 21.27.108 - Avionics ventilation air filter alternate equipment 21.28.201 - Installation of ventilation system for forward cargo hold 21.28.210 - Installation of ventilation system for complete aft cargo hold 21.41.100 - Installation of front air outlets at flight crew foot level 21.43.201 - Installation of heating system for forward cargo hold 21.43.204 - Installation of heating system for complete aft cargo hold 21.70.109 - Installation of ozone catalytic converters

Auto flight 22.00.104 - Automatic landing capability 22.70.100 - Flight Management (FM) kits alternate equipment 22.81.143 - Inhibition of the expedite pushbutton 22.82.103 - Installation of third Multipurpose Control and Display Unit (MCDU)

Communications 23.00.132 - Installation (based on basic common provision) of Emergency Locator Transmitter (ELT) 23.11.102 - Full provision for single HF system 23.11.111 - Full provision for dual HF system 23.11.116 - Installation of single HF system (SFE) 23.11.131 - Installation of single HF system and full provision for second one (SFE) Issue 6 Revision 1, January 2012

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Detailed table of contents Detailed table of contents TITLE 23.11.155 - Installation of dual HF system (SFE) 23.11.167 - Additional wiring for HF Data Link (HFDL) function 23.11.169 - Activation of HF Data Link (HFDL) function 23.12.130 - VHF Data Radio (VDR) alternate equipment 23.13.100 - Installation of alternate Radio Management Panel (RMP) 23.13.101 - Installation of third Radio Management Panel (RMP) 23.13.105 - Activation of RMP std 4 frequency load function 23.28.170 - Installation of AERO H+/SBB SATCOM cockpit voice interface 23.28.210 - Installation of SATCOM AERO H+ SRT 2100B system 23.28.211 - Installation of SwiftBroadband (SBB) SATCOM system 23.50.110 - Installation of additional Audio Control Panel (ACP) and jack panel 23.50.135 - Installation of headset for fourth occupant 23.50.138 - Cockpit hand microphone alternate equipment 23.51.103 - Installation of active noise canceling boomsets (SFE) 23.51.136 - Boomsets alternate equipment 23.51.139 - Boomsets alternate equipment with two jack plugs 23.70.110 - Installation of a video monitoring system 23.71.103 - Solid State Cockpit Voice Recorder (SSCVR) alternate equipment 23.71.110 - Recorder Independent Power Supply (RIPS) - 28VDC power supply for CVR 23.71.120 - System provision for CVR capable of data link recording 23.73.200 - Installation of cockpit and cabin alert switches (Aircraft Security Project)

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Detailed table of contents

TITLE

Electrical power 24.55.101 - Passenger Address (PA) power supply in emergency condition with batteries OFF

Equipment/furnishings 25.10.108 - Installation of paper holder on the glareshield 25.11.102 - Pilot seats alternate covers - sheepskin 25.11.208 - Installation of fourth occupant seat in cockpit 25.27.100 - Installation of heated floor panels for fwd passenger/crew/service door area 25.27.101 - Installation of On/off switch for heated floor panels 25.50.137 - Rubber seal profile for cargo compartment floor panels 25.50.510 - Basic full bulk configuration selection in forward and aft cargo holds 25.50.520 - Installation of reinforced floor panels for heavy bulk usage in forward and aft cargo holds 25.52.190 - System provision for mechanized bulk loading systems in forward cargo hold (A320) 25.52.191 - System provision for mechanized bulk loading systems in forward cargo hold (A321) 25.52.202 - Installation of mechanized bulk loading system in forward cargo hold - sliding carpet system

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Detailed table of contents Detailed table of contents TITLE 25.52.204 - System provision for mechanized bulk loading systems in aft cargo hold (A319/A320) 25.52.205 - System provision for mechanized bulk loading systems in aft cargo hold (A321) 25.52.212 - Installation of mechanized bulk loading system in aft cargo hold - sliding carpet system 25.52.304 - Installation of semi-automatic Cargo Loading System (CLS) in forward and aft cargo holds (A320/A321) 25.52.310 - Fixed provision for occasional bulk capability in forward and aft cargo holds (A320/A321) 25.52.315 - Full electrical provision for semi-automatic CLS 25.52.404 - Installation of Cargo Loading System (CLS) with full bulk capability in fwd and aft cargo holds 25.52.407 - Bulk loading capability in aft cargo hold door area behind two ULDs (A319) 25.52.410 - Full provision for installation of special container in aft cargo hold, door area (A319) 25.52.500 - Installation of continuous side guides in forward cargo hold 25.52.511 - Installation of continuous side guides in aft cargo hold

Fire protection 26.20.103 - Auxiliary Power Unit (APU) fire extinguisher alternate equipment 26.21.104 - Engine fire extinguishers alternate equipment Issue 6 Revision 1, January 2012

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Detailed table of contents

TITLE 26.23.103 - Cargo holds fire extinguisher alternate equipment 26.23.111 - Cargo holds fire extinguishers extended duration for ETOPS 120 min 26.23.112 - Cargo holds fire extinguishers extended duration for ETOPS 180 min

Fuel 28.11.133 - Full provision for installation of one Additional Center Tank (ACT) in aft cargo hold 28.11.140 - Full provision for installation of two/one Additional Center Tanks (ACTs) in aft cargo hold 28.11.225 - Installation of one Additional Center Tank (ACT) in aft cargo hold 28.11.235 - Installation of two Additional Center Tanks (ACTs) in aft cargo hold 28.25.107 - Installation of additional refuel/defuel coupling in LH wing 28.25.110 - Installation of fuel quantity preselector in cockpit 28.25.130 - Relocation of refuel/defuel control panel

Hydraulic power 29.10.110 - Hydraulic Engine Driven Pumps (EDPs) alternate equipment 29.21.104 - Electropumps alternate equipment

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Detailed table of contents Detailed table of contents TITLE

Ice and rain protection 30.41.102 - Installation of intermittent function of windshield wipers 30.70.108 - Extended freezing protection 30.81.105 - Installation of dual advisory ice detection system

Indicating/recording systems 31.00.107 - US units for indicators and labels 31.14.103 - Overhead panel toggle switches re-orientation 31.33.051 - Flight Data Interface and Management Unit (FDIMU) alternate equipment 31.33.132 - Installation of Quick Access Recorder (QAR/WGL-QAR) 31.33.200 - Solid State Flight Data Recorder (SSFDR) alternate equipment 31.33.210 - Digital Flight Data Recorder System (DFDRS) capabilities 31.36.161 - Installation of Digital AIDS Recorder (DAR/WGL-DAR) (BFE) 31.60.114 - Indication of metric altitude on Primary Flight Display (PFD) 31.60.120 - Installation of Electronic Instrument System (EIS2) 31.65.100 - Activation of Minimum Off Route Altitude (MORA) on Navigation Display (ND)

Landing gear 32.40.113 - Wheels and brakes alternate equipment 32.41.111 - Main Landing Gear (MLG) tires selection and alternate equipment

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Detailed table of contents

TITLE 32.41.120 - Nose Landing Gear (NLG) tires selection 32.48.200 - Installation of universal brake cooling fans 32.49.109 - Installation of Tire Pressure Indicating System (TPIS) on twin wheel

Lights 33.12.109 - Changes in cockpit illumination (excluding instrument and panel lighting) 33.43.000 - Runway turnoff lights 33.46.000 - Taxi and take-off lights

Navigation 34.00.108 - QNH/QFE BARO setting 34.13.105 - Installation of aspirated Total Air Temperature (TAT) probes 34.13.106 - Pitot probes alternate equipment 34.15.101 - Angle Of Attack (AOA) sensors alternate equipment 34.20.203 - Integrated Standby Instrument System (ISIS) optional functions 34.35.109 - System provision for Head Up Display (HUD) system installation 34.35.110 - Installation (based on provision) of Head Up Display (HUD) system 34.41.302 - Full single Weather Radar (WXR) system alternate equipment 34.41.310 - Installation of dual Weather Radar (WXR) System 34.42.101 - Radio altimeters alternate equipment

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Detailed table of contents Detailed table of contents TITLE 34.42.117 - Radio altitude automatic call-outs 34.43.203 - Traffic Alert and Collision Avoidance System (TCAS) alternate equipment (SFE) 34.43.250 - Installation of T2CAS 34.43.260 - T2CAS - Activation of alternate warnings 34.43.270 - Wiring provision for T3CAS 34.43.290 - Wiring provision for Aircraft Traffic Situation Awareness (ATSAW) 34.43.295 - Activation of ATSAW function 34.48.124 - Enhanced Ground Proximity Warning System (EGPWS) - alternate equipment 34.48.127 - Enhanced Ground Proximity Warning System (EGPWS) alternate warnings 34.48.132 - Enhanced Ground Proximity Warning System (EGPWS) - optional functions 34.51.101 - Distance Measuring Equipment (DME) interrogators alternate equipment 34.52.117 - Automatic Dependent Surveillance - Broadcast (ADS-B OUT) 34.52.133 - Compliance with European enhanced surveillance (EHS) regulation 34.52.140 - Air Traffic Control (ATC) control panel alternate equipment 34.53.109 - Full provision for second Automatic Direction Finder (ADF) system 34.53.111 - Single Automatic Direction Finder (ADF) system alternate equipment 34.53.119 - Installation of dual Automatic Direction Finder (ADF) system 34.55.102 - VHF Omnidirectional Range (VOR)/Marker receivers alternate equipment 34.58.313 - Multi Mode Receiver (MMR) alternate equipment 34.58.316 - Activation of GLS function Issue 6 Revision 1, January 2012

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Detailed table of contents

TITLE 34.58.317 - Activation of FLS function 34.58.340 - Installation of MLS function for cat IIIb operation hosted by the MMR

Oxygen 35.11.102 - Installation of in-situ replenishment facility for cockpit oxygen cylinder 35.11.201 - Cockpit oxygen cylinder alternate equipment 35.20.010 - Installation of four oxygen masks per box 35.20.113 - Extended supply duration for passenger chemical oxygen system 35.20.114 - Extended supply duration for passenger gaseous oxygen system

Water/waste 38.10.104 - Installation of water conditioner in potable water system 38.41.101 - Installation of auxiliary compressor in the potable water pressurization system

Information systems 46.21.102 - Installation of AIRBUS standard Airline Operational Communication (AOC) software for ATSU 46.21.105 - Activation of ARINC 623 ATS applications in the ATSU 46.21.111 - Activation of VHF Data Link (VDL) Mode 2 function

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Detailed table of contents Detailed table of contents TITLE 46.21.140 - Installation of Future Air Navigation System (FANS) A+ 46.21.142 - Installation of Future Air Navigation System (FANS) B+

Auxiliary Power Unit (APU) 49.00.105 - Auxiliary Power Unit (APU) alternate equipment

Structures 51.00.115 - Fuselage and wings extended corrosion prevention 51.22.250 - External livery decorative adhesive film 51.22.710 - Alternate paint system (CF primer/strippable) on standard areas (3 coats)

Doors 52.22.200 - Installation of additional emergency exits (A319) 52.51.100 - Installation of cockpit door release back-up system (MMEL conditions) 52.51.106 - Installation of modified door lock mechanism

Fuselage 53.30.050 - Belly fairing panels - extrusion strips 53.35.100 - Ram air inlet leading edge protection

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Detailed table of contents

TITLE

Stabilizers 55.30.101 - Installation of erosion protection on vertical stabilizer leading edge

Windows 56.10.102 - Cockpit windows alternate equipment

Wings 57.40.100 - Leading edge and leading edge devices 57.49.101 - Wing leading edge access panels - miscellaneous changes

Engines 72.00.118 - Engines selection and alternate equipment (A318) 72.00.119 - Engines selection and alternate equipment (A319) 72.00.120 - Engines selection and alternate equipment (A320) 72.00.121 - Engines selection and alternate equipment (A321)

Engine fuel and control 73.21.100 - Installation of additional sensors for engine health monitoring

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Detailed table of contents Detailed table of contents TITLE

Oil 79.00.101 - Engine, engine accessories and Auxiliary Power Unit (APU) alternate lubricating oil 79.40.101 - Installation of Integrated Drive Generator (IDG) oil level viewing port on engine RH fan cowl

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A320 Family Reference

Title

00.00.200

Introduction

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Introduction 00

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[ 00-1]

A320 Family

00 Introduction 00.00.200 - Introduction Description 1) General This Configuration Guide is dedicated to the aircraft models and associated Standard Specifications indicated on the first page. This Configuration Guide offers various options defined as "Airbus preferred solutions" to the customer. When used in conjunction with the Standard Specification and the other Configuration Guides a complete customization of the Aircraft is possible through the selection of the different items and associated technical solutions. 2) Basic aircraft This Configuration Guide starts from the theoretical basic aircraft as shown in the reference layout for weight and performance calculations of the corresponding Standard Specification and incorporating any relevant Manufacturer Specification Change Notice (MSCN).

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3) Instructions for use This Configuration Guide encompasses a wide range of options and in some circumstances, it is possible that a particular combination of options cannot be achieved. Therefore, the Configuration Guide must be used in conjunction with the expertise and assistance of Airbus. 4) Lead-times This Configuration Guide shows items for which a predefined technical solution has been developed and for which the lead times have been studied. Provided the schedule as defined in the customer definition milestone chart is respected, these items can be installed without affecting the delivery lead time. Caution: Some items require longer lead-time than normal, and therefore customer decisions prior to Contractual Definition Freeze (CDF) deadlines. These items are highlighted in this catalogue by a special remark: "Subject to lead-time constraints". For these items, specific decision deadlines shall be identified in customer definition milestones.

00.00.200

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[ 00-2]

Introduction 00

A320 Family 00.00.200 - Introduction (Continued) 5) Catalogue presentation On each page, the following information is provided: • Air Transport Association of America (ATA) title and section number • date of the issue of the catalogue • option reference For each item, the description is structured in subparts: • objective of the item • basic aircraft definition related to the item • description of the item in terms of modifications, in some cases commented by a note and/or illustrated by drawings • EPAC selection mode for the item shows whether the item is selectable by individual or global Request For Change (RFC)/Specification Change Notice (SCN) procedure • technical solutions: a table describes all technical solutions (called TDU: Technical Description Unit) associated to the item. Note: For comparison purposes, some tables also show the basic aircraft equipment, labelled Std (Standard) in the TDU column.

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As far as possible, the arrangement of the items follows the ATA 100 classification. The items are sorted by numerical order of reference numbers within a given ATA chapter. The different options bear a 7-digit reference number: (e.g: 26.24.600) showing first the ATA (e.g. 26) and subATA (e.g. 24) classification, followed by a running number (e.g. 600). Each technical solution (TDU) is referenced by a twodigit number (e.g. 02). All items are listed in the Table Of Content (TOC) and duplicated at the beginning of each chapter. Definition of titles: "... equipment selection", "... alternate equipment", "provisions for...", "Installation of...". a) items titled "... equipment selection" relate to items where the standard specification offers a choice of basic equipment. For such items the customer is requested to select from one of the choices on offer, unless alternate equipment is required.

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00 Introduction 00.00.200 - Introduction (Continued) b) items titled "...alternate equipment" relate to items where the customer can choose equipment alternate to that defined in the Standard Specification.

pend on successful product qualification and proof of compliance with Airbus performance requirements and customer expectations.

c) items titled "Provisions for..." relate to items where the customer can add structural and/or system provisions to prepare the a/c for later installation.

Weights Weight definitions are as follows: • MWE: Effect of RFC/SCN on Manufacturer's Weight Empty • OWE: Effect of RFC/SCN on Operator's Weight Empty • APL: Effect of RFC/SCN on Available Payload All weights quoted are for one off unless otherwise stated. TBD: Weight effects have yet to be determined for RFC/ SCN. Negl: Weight effect is small and will be taken as zero for individual RFC/SCN. Weights for alternative items are delta weights to the corresponding Standard Specification unless otherwise stated. Where the EPAC selection mode is Global the weight of the item shall be part of the relevant Global RFC/SCN. Any weights shown in the catalogue for such items are for guidance only.

d) items titled "Installation of..." relate to items where the customer can add functions/equipment/systems on top of the standard definition. Selection conditions Specific selection conditions may be associated to an item and are identified by an icon and a special remark visible in the TDU table (see example in the figure hereafter). Such solutions may be at the initial phases of development or first application on Airbus aircraft. For these items commitment to quality, industrial and technical capabilities, on time delivery and customer support de-

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Introduction 00

A320 Family 00.00.200 - Introduction (Continued) For some individual RFC/SCN the weight is dependent on customer requirements, e.g. certain BFE items. The weights for such items shall be taken for guidance only and will be identified as such. 6) Definition handling The customer's selection is recorded by Airbus in RFC forms. Then, a SCN is issued by Airbus, based on a customer's RFC, and is submitted for customer's signature. These RFCs/SCNs are issued before CDF directly on customer request except if their content is to be adapted. Global RFC/SCN The global RFC consists of a checklist containing items with considerable interdependence and equivalent lead-times. The global RFC leads to the global SCN which groups all selected items. Individual RFC/SCN The selection of individual items not covered by global RFC/SCN is achieved via individual RFCs/SCNs.

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Specific customer request Items that are not mentioned in this Guide, or corresponding to a modified item, require specific customer requests as a special feasibility study has to be initiated. It is therefore essential for customers to review the Configuration Guide as soon as possible to identify which of their requirements are covered and which are not. This will allow the customers, with the assistance of Airbus, to raise in time the necessary specific requests related to items which are not covered by this Guide. Such specific requests shall necessarily have an impact in terms of lead times and resources and shall consequently lead to constraints and decisions that shall be discussed in good faith between the customer and Airbus. Airbus hereby forewarns that this may lead to the unfeasibility of certain requests. 7) Buyer's responsibility All installation of equipment by any entity other than the Manufacturer (including but not limited to the Buyer) for which provisions are made or which are post-delivery of the aircraft shall be made under the sole and full responsibility of the Buyer.

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00 Introduction 00.00.200 - Introduction (Continued) The Buyer shall hold harmless and indemnify the Manufacturer against any claims or/and damages related directly or indirectly to an incorrect installation of an equipment or to such equipment itself, whether defective or not.

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[ 00-6]

Introduction 00

A320 Family Figure 00-1 - Typical page description Detailed description page

Chapter cover page

Option reference and title

with a list of available items ATA title and section number

A320 Family 25 Equipment/furnishings

25 Equipment/furnishings

25.52.404 - Installation of Cargo Loading System (CLS) with full bulk capability in fwd and aft cargo holds Objective for A319-100 and A320-200 and A321-200 To provide operational capability either to transport ULDs and/or bulk freight up to a maximum average density of 15 lb/cu ft.

.

Reference

Title

25.52.212

Installation of mechanized bulk loading system in aft cargo hold - sliding carpet system

fender for protection devices for the rapid decom25.52.304 pression at frame 24 A. EPAC selection mode Global CARGO

A320 Family

Installation of semi-automatic Cargo Loading System (CLS) in forward and aft cargo holds (A320/A321)

25.52.310

Fixed provision for occasional bulk capability in forward and aft cargo holds (A320/A321)

Basic aircraft for A319-100 and A320-200 and A321200 Full bulk configuration and structural provision for attaching optional divider nets in the forward and aft cargo holds. System provision for CLS plus minimum electrical provision for mechanized bulk loading system.

25.52.315

Full electrical provision for semi-automatic CLS

25.52.404

Installation of Cargo Loading System (CLS) with full bulk capability in fwd and aft cargo holds

25.52.407

Bulk loading capability in aft cargo hold door area behind two ULDs (A319)

25.52.410

Full provision for installation of special container in aft cargo hold, door area (A319)

25.52.500

Installation of continuous side guides in forward cargo hold

Description for A319-100 and A320-200 and A321200 The modification consists of the installation of: electrically powered semi-automatic CLS additional tie-down fittings door nets with stanchions and divider nets for the forward and aft cargo holds reinforced cargo floor panels for heavy bulk usage for the forward and aft cargo holds, flat parts only drainage system side wall/ceiling panels for bulk loading in the forward and aft cargo holds

25.52.511

Installation of continuous side guides in aft cargo hold

.

Issue 6 Revision 01, January 2012

25.52.404

Date of the issue of the catalogue

Issue 6 Revision 1, January 2012

Page 246

[ 26-4] Issue 6 Revision 01, January 2012

Option reference

00.00.200

Page 243

[ 26-1]

page number (ATA section + page number within the section)

Page 7

[ 00-7]

A320 Family

00 Introduction

Figure 00-2 - Example of technical solutions description table Technical solution identifier (TDU)

Selection condition remark TDU

Title of the technical solution and optional remarks Selection condition

Applicable series

Weights information per series MWE: Manufacturer’s Weight Empty OWE: Operational Weight Empty APL: Allowable Payload Change

Equipment information: • reference • vendor • PN (part numbers) • quantity • status (BFE or SFE)

Table 25-21 - Technical solutions description Title (Remarks)

Appl.

Weight (kg)

MWE/OWE/APL

01

Semi-automatic CLS in fwd and aft cargo holds - without ACT provision (A320/A321)

A320-200 A321-200

122.0/122.0/-122.0 102.0/102.0/-102.0

02

Semi-automatic CLS in fwd and aft cargo holds - with full provision for one ACT (A320)

A320-200

153.0/153.0/-153.0

A321-200

133.0/133.0/-133.0

A320-200

177.0/177.0/-177.0

Equipment reference

Equipment supplier

Equipment PN

QTY

STS

Requires prior acceptance of CN28.11.133/02 - Full provision for installation of one ACT in aft cargo hold (A320). Due to ACT, lead-time constraints for this option are 9 months.

03

Semi-automatic CLS in fwd and aft cargo holds - with full provision for one ACT (A321) Requires prior acceptance of CN28.11.133/01 - Full provision for installation of one ACT in aft cargo hold (A321) Due to ACT, lead-time constraints for this option are 8 months.

04

Semi-automatic CLS in fwd and aft cargo holds - with full provision for two ACTs (A320) Requires prior acceptance of CN28.11.140/03 - Full provision for installation of two/one ACTs in aft cargo hold (A320). Due to ACT, lead-time constraints for this option are 9 months.

Issue 6 Revision 1, January 2012

00.00.200

Page 8

[ 00-8]

A320 Family

Certification and external livery 02

Reference

Title

02.10.104

Certification of dynamically tested passenger seats

02.10.111

Compliance with FAA type certification requirements

02.10.112

Partial compliance with FAA type certification requirements

02.10.120

15 knots tailwind certification

02.10.123

Operation on runways with reduced width

02.10.190

ETOPS 120/180 min

02.12.122

Compliance status with EU-OPS 1

02.12.123

Compliance with CS25/FAR 25.562 (Head Injury Criteria - HIC)

02.12.130

EASA certification of Take Off/Landing operation on wet grooved / PFC runways

02.40.101

External livery

Issue 6 Revision 1, January 2012

Page 9

[ 02-1]

02 Certification and external livery

A320 Family

02.10.104 - Certification of dynamically tested passenger seats Objective for A319-100 and A320-200 and A321-200 To certify passenger seats in accordance with seat frame specification AI 2521M1F100000 for dynamically tested passenger seats. Basic aircraft for A319-100 and A320-200 and A321200 A319/A320/A321 Passenger seats are certified in accordance with seat frame specification AI 2520M1F000100. A318 Passenger seats are certified in accordance with seat frame specification AI 2521M1F000500 for dynamically tested passenger seats.

Note for A319-100 and A320-200 and A321-200 Certification of dynamically tested passenger seats is mandatory for FAA certification on A319 and A321, but is already included in the following option: CN02.10.111/01 - Compliance with FAA type certification requirements. EPAC selection mode Individual

Description for A319-100 and A320-200 and A321200 Passenger seats are certified in accordance with seat frame specification AI 2521M1F100000 for dynamically tested passenger seats.

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02.10.104

Page 10

[ 02-2]

Certification and external livery 02

A320 Family

Table 02-1 - Technical solutions description TDU

Title (Remarks)

Appl.

Weight (kg) MWE/OWE/APL

05

Certification of dynamically tested passenger seats B/C

A319-100 A320-200 A321-200

0.0/0.0/0.0 0.0/0.0/0.0 0.0/0.0/0.0

06

Certification of dynamically tested passenger seats Y/C

A319-100 A320-200 A321-200

0.0/0.0/0.0 0.0/0.0/0.0 0.0/0.0/0.0

Issue 6 Revision 1, January 2012

Equipment reference

02.10.104

Equipment supplier

Equipment PN

QTY

Page 11

STS

[ 02-3]

02 Certification and external livery

A320 Family

02.10.111 - Compliance with FAA type certification requirements Objective To install all modifications to be in compliance with FAA type certification requirements. Basic aircraft The aircraft is designed and constructed in accordance with JAR-25 airworthiness requirements, and FAR-25 for US importation (see type certificate data sheet). Description The following changes shall be carried-out to be in compliance with the FAA Type Design of the respective Aircraft type: A318-100 • installation of ozone converters • installation of modified emergency exit inscription and marking • installation of dynamically tested passenger seats as per seat frame specification 2520 M1F 0005 00 (or equivalent) • installation of weight placard on each overwing hatch • installation of passageways to emergency exits. A319-100 • installation of ozone converters

Issue 6 Revision 1, January 2012

• installation of modified emergency exit inscription and marking • installation of dynamically tested passenger seats as per seat frame specification 2520 M1F 0005 00 (or equivalent) • installation of passageways to emergency exits. A320-200 • installation of ozone converters • installation of modified emergency exit inscription and marking • installation of maximum 179 passenger seats • installation of passageways to emergency exits. A321-200 • installation of ozone converters • installation of dynamically tested passenger seats as per seat frame specification 2520 M1F 0005 00 (or equivalent) • installation of passageways to emergency exits. Note On US registered a/c the installation of variable geometry seats in conjunction with photoluminescent floormounted EEPMS is prohibited.

02.10.111

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[ 02-4]

A320 Family

Certification and external livery 02

02.10.111 - Compliance with FAA type certification requirements (Continued) EPAC selection mode Individual

Issue 6 Revision 1, January 2012

02.10.111

Page 13

[ 02-5]

A320 Family

02 Certification and external livery Table 02-2 - Technical solutions description TDU

Title (Remarks)

Appl.

Weight (kg) MWE/OWE/APL

01

Compliance with FAA type certification requirements (A319/ A320/A321)

A319-100 A320-200 A321-200

20.0/20.0/-20.0 20.0/20.0/-20.0 20.0/20.0/-20.0

A318-100

20.0/20.0/-20.0

Equipment reference

Equipment supplier

Equipment PN

QTY

STS

For A319 and A321, not compatible with CN02.10.104 - 16 g Certification of dynamically passenger seats. Requires prior acceptance of CN21.70.109 - Installation of ozone catalytic converters. Selection of CN11.30.131/05 - Installation of weight placards on overwing hatch is recommended.

08

Compliance with FAA type certification requirements (A318) Requires prior acceptance of CN21.70.109 - Installation of ozone catalytic converters. Requires prior acceptance of CN11.30.131/05 - Installation of weight placards on overwing hatch.

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Page 14

[ 02-6]

A320 Family

Certification and external livery 02

Intentionally left blank

Issue 6 Revision 1, January 2012

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Page 15

[ 02-7]

02 Certification and external livery

A320 Family

02.10.112 - Partial compliance with FAA type certification requirements Objective To install all modifications except cabin arrangement requirements, to be partially in compliance with FAA type certification requirements.

A320-200 • installation of ozone converters • installation of modified emergency exit inscription and marking.

Basic aircraft The aircraft is designed and constructed in accordance with JAR-25 airworthiness requirements, and FAR-25 for US importation (see type certificate data sheet).

A321-200 • installation of ozone converters.

Description The following changes shall be carried-out to be partially in compliance with the FAA Type Design of the respective aircraft type: A318-100 • installation of ozone converters • installation of modified emergency exit inscription and marking • installation of weight placard on each overwing hatch. A319-100 • installation of ozone converters • installation of modified emergency exit inscription and marking.

Issue 6 Revision 1, January 2012

Note • on US registered a/c the installation of variable geometry seats in conjunction with photoluminescent floor-mounted EEPMS is prohibited. • upon the selection of this option, AIRBUS will, no later than 6 months before aircraft Industrial Delivery, issue the FAA Type Design Statement to the end customer including: - "Compliance Status to the FAA Type Design" (List of Modifications required to meet US Type Design) - "Additional Requirements to obtain a US Standard Airworthiness Certificate" (Customization status for US operations). • the selection of this option ensures the partial compliance of the individual aircraft MSN to the FAA Type Design, at the exclusion of the cabin layout.

02.10.112

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[ 02-8]

A320 Family

Certification and external livery 02

02.10.112 - Partial compliance with FAA type certification requirements (Continued) • the delivery of a US Standard Airworthiness Certificate at Aircraft ID is subject to a prior FAA validation process of the Aircraft customized definition. AIRBUS will timely initiate and control this process provided the end customer delivers, no later than 6 months before Aircraft ID, the final N-Registration marks allocated by the FAA to the individual aircraft MSN. Failure to meet this objective may generate changes to the contractual definition (de-validation of Modifications not timely approved by the FAA or Delay of the aircraft ID • a revised FAA TD Statement will be provided at time of delivery. EPAC selection mode Individual

Issue 6 Revision 1, January 2012

02.10.112

Page 17

[ 02-9]

A320 Family

02 Certification and external livery Table 02-3 - Technical solutions description TDU

Title (Remarks)

Appl.

Weight (kg) MWE/OWE/APL

04

Partial compliance with FAA type certification requirements (without seat arrangement requirements)

A319-100 A320-200 A321-200

20.0/20.0/-20.0 20.0/20.0/-20.0 20.0/20.0/-20.0

A318-100

20.0/20.0/-20.0

Equipment reference

Equipment supplier

Equipment PN

QTY

STS

Requires prior acceptance of CN21.70.109 - Installation of ozone catalytic converters. Selection of CN11.30.131/05 - Installation of weight placards on overwing hatch is recommended.

06

Partial compliance with FAA type certification requirements (without seat arrangement requir) (A318) Requires prior acceptance of CN21.70.109 - Installation of ozone catalytic converters. Requires prior acceptance of CN11.30.131/05 - Installation of weight placards on overwing hatch.

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Page 18

[ 02-10]

A320 Family

Certification and external livery 02

Intentionally left blank

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02.10.112

Page 19

[ 02-11]

02 Certification and external livery

A320 Family

02.10.120 - 15 knots tailwind certification Objective To be able to take off with a tailwind component up to 15 knots depending on engine type. Basic aircraft In the absence of specific flight tests, the usual interpretation of the current certification requirements is to limit the tailwind operations to a maximum component of 10 knots. Description In order to operate the aircraft at a tailwind component up to 15 knots, severe conditions shall be conducted by the aircraft manufacturer. This includes flight test demonstrations with 1.5 x the desired limit in terms of tailwind.

• additional engine characteristics justifications with tailwind, in particular in terms of engine inlet. Note Depending on the sensitivity of the engine inlet characteristics with a tailwind, a slower thrust application at take-off may be necessary, which in turn may require "rolling take-off procedure". Both effects may require long take-off distances and consequent aircraft gross weight penalties for a given runway length. EPAC selection mode Individual

The certification dossier for tailwind operations at takeoff shall include: • new performance justifications, updating of flight manual and flight crew operating manual • additional handling qualities demonstrations in flight, including justification/modifications (if necessary) of the computers settings (angle of attack protection settings, windshear warning ...) Issue 6 Revision 1, January 2012

02.10.120

Page 20

[ 02-12]

Certification and external livery 02

A320 Family

Table 02-4 - Technical solutions description TDU

Title (Remarks)

Appl.

Weight (kg) MWE/OWE/APL

01

15 knots tailwind certification at take-off

Issue 6 Revision 1, January 2012

A318-100 A319-100 A320-200 A321-200

Equipment reference

Equipment supplier

Equipment PN

QTY

STS

0.0/0.0/0.0 0.0/0.0/0.0 0.0/0.0/0.0 0.0/0.0/0.0

02.10.120

Page 21

[ 02-13]

02 Certification and external livery

A320 Family

02.10.123 - Operation on runways with reduced width Objective To authorize aircraft operation on runways with a width comprised between 30 m and 45 m.

EPAC selection mode Individual

Basic aircraft The standard aircraft is certificated for operation on runways with a minimum width of 45 m. Description Certification for operation on runways less than 45 meters wide (width comprised between 30 m and 45 m) is achieved by performing the following modifications: • new performance justifications, updating of flight manuals and TLC • new definition of MMEL, updating of certification documents • adjustment of limitations (e.g. crosswind, autoland), updating of MEL and CDL. Note For aircraft equipped with a CLS and operating on reduced runway width, it is recommended to select a bulk loading option.

Issue 6 Revision 1, January 2012

02.10.123

Page 22

[ 02-14]

Certification and external livery 02

A320 Family

Table 02-5 - Technical solutions description TDU

Title (Remarks)

Appl.

Weight (kg) MWE/OWE/APL

01

Aircraft Operation on runways less than 45m wide Not applicable in conjunction with PW engines

Issue 6 Revision 1, January 2012

A318-100 A319-100 A320-200 A321-200

Equipment reference

Equipment supplier

Equipment PN

QTY

STS

0.0/0.0/0.0 0.0/0.0/0.0 0.0/0.0/0.0 0.0/0.0/0.0

02.10.123

Page 23

[ 02-15]

02 Certification and external livery

A320 Family

02.10.190 - ETOPS 120/180 min Objective To make the design capable of 120/180 min maximum diversion time from diversion airport at normal one engine inoperative cruise speed. Basic aircraft Basic certification is with class C cargo holds. Description Modifications concern the supply of some systems in electrical emergency conditions and their reliability as required by the applicable ETOPS Configuration Maintenance and Procedure (CMP) document at the time of aircraft delivery. Note The precise list of modifications depends upon the selected configuration of the aircraft: • applicable airworthiness requirement • engine model • APU type • cargo hold ventilation, heating.

ETOPS operation authorization can only be obtained through application by the operator to its national authority. During the operational life of the aircraft, additional modifications may be necessary to maintain systems reliability at the required level. They are not covered by this change. Requires prior acceptance of CN26.23.111 - Cargo holds fire extinguishers extended duration for ETOPS 120 min or CN26.23.112 - Cargo holds fire extinguishers extended duration for ETOPS 180 min. It is mandatory to have at least one HF installed for ETOPS 120/180. Therefore, this option requires prior acceptance of CN23.11.116 - Installation of single HF system (SFE), or CN23.11.131 - Installation of single HF system and full provision for second one (SFE), or CN23.11.155 - Installation of dual HF system (SFE). If the aircraft makes extended over water flights, under EU-OPS 1 requirements, it is the responsibility of the operator to install slide rafts (EECG item CN25.62.102) and two portable ELTs (EECG item CN25.65.305). EPAC selection mode Individual

Issue 6 Revision 1, January 2012

02.10.190

Page 24

[ 02-16]

A320 Family

Certification and external livery 02 Figure 02-1 - ETOPS - area of operation

(Non ETOPS twins)

Typical single engine speed

Typical single engine speed

60 minute rule

120 minute rule

Typical single engine speed

One engine failure flight path (condition of ETOPS requirement)

180 minute rule

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02.10.190

Page 25

[ 02-17]

A320 Family

02 Certification and external livery Figure 02-2 - ETOPS 120/180 min options (A318)

A318 - ETOPS 120 min EASA/JAA

FAA

A318 - ETOPS 180 min EASA/JAA

FAA

CFM56-5B8/3

CN02.10.200/05

CN02.10.200/06

CN02.10.300/05

CN02.10.300/06

CFM56-5B9/3

CN02.10.200/07

CN02.10.200/08

CN02.10.300/07

CN02.10.300/08

PW6122A

CN02.10.200/11

CN02.10.200/12

CN02.10.300/11

CN02.10.300/12

PW6124A

CN02.10.200/13

CN02.10.200/14

CN02.10.300/13

CN02.10.300/14

Certified = SCG item (no lead-time constraint)

Issue 6 Revision 1, January 2012

Not certified (lead-time constraint)

02.10.190

Page 26

[ 02-18]

Certification and external livery 02

A320 Family

Figure 02-3 - ETOPS 120/180 min options (A319)

A319 - ETOPS 120 min EASA/JAA

FAA

A319 - ETOPS 180 min EASA/JAA

FAA

CFM56-5B5/3

CN02.10.210/03

CN02.10.210/04

CN02.10.310/03

CN02.10.310/04

CFM56-5B6/3

CN02.10.210/15

CN02.10.210/16

CN02.10.310/15

CN02.10.310/16

CFM56-5B7/3

CN02.10.210/37

CN02.10.210/38

CN02.10.310/37

CN02.10.310/38

IAE V2522-A5

CN02.10.210/41

CN02.10.210/42

CN02.10.310/41

CN02.10.310/42

IAE V2524-A5

CN02.10.210/51

CN02.10.210/52

CN02.10.310/51

CN02.10.310/52

IAE V2527M-A5

CN02.10.210/61

CN02.10.210/62

CN02.10.310/61

CN02.10.310/62

Certified = SCG item (no lead-time constraint)

Issue 6 Revision 1, January 2012

02.10.190

Page 27

[ 02-19]

A320 Family

02 Certification and external livery Figure 02-4 - ETOPS 120/180 min options (A320)

A320 - ETOPS 120 min

A320 - ETOPS 180 min

EASA/JAA

FAA

EASA/JAA

FAA

CFM56-5B4/3

CN02.10.220/03

CN02.10.220/04

CN02.10.320/03

CN02.10.320/04

CFM56-5B5/3

CN02.10.220/05

N/A

CN02.10.320/05

N/A

CFM56-5B6/3

CN02.10.220/07

N/A

CN02.10.320/07

N/A

IAE V2527-A5

CN02.10.220/41

CN02.10.220/42

CN02.10.320/41

CN02.10.320/42

IAE V2527E-A5

CN02.10.220/51

CN02.10.220/52

CN02.10.320/51

CN02.10.320/52

Certified = SCG item (no lead-time constraint)

Issue 6 Revision 1, January 2012

N/A = Not Applicable

02.10.190

Page 28

[ 02-20]

Certification and external livery 02

A320 Family

Figure 02-5 - ETOPS 120/180 min options (A321)

A321 - ETOPS 120 min EASA/JAA

FAA

A321 - ETOPS 180 min EASA/JAA

FAA

CFM56-5B1/3

CN02.10.240/09

CN02.10.240/10

CN02.10.330/09

CN02.10.330/10

CFM56-5B2/3

CN02.10.240/30

CN02.10.240/31

CN02.10.330/30

CN02.10.330/31

CFM56-5B3/3

CN02.10.240/13

CN02.10.240/14

CN02.10.330/13

CN02.10.330/14

IAE V2530-A5

CN02.10.240/21

CN02.10.240/22

CN02.10.330/21

CN02.10.330/22

IAE V2533-A5

CN02.10.240/11

CN02.10.240/12

CN02.10.330/11

CN02.10.330/12

Certified = SCG item (no lead-time constraint)

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02.10.190

Page 29

[ 02-21]

02 Certification and external livery

A320 Family

02.12.122 - Compliance status with EU-OPS 1 Objective To provide compliance status report against EU-OPS 1, subparts K & L or subparts K, L & S, at aircraft delivery. Basic aircraft The basic aircraft does not comply with EU-OPS 1, subparts K, L & S (cabin emergency equipment, Emergency Locator Transmitter (ELT) installation, TCAS change 7.0, ...). Description At aircraft delivery, a compliance status report against EU-OPS 1, subparts K & L or subparts K, L & S, shall be provided. Note The operator is responsible to show to their national operational authority the compliance of their aircraft with EU-OPS 1. AIRBUS is providing help by raising a factual compliance review and cannot be responsible for the non-compliance which may be identified. EPAC selection mode Individual

Issue 6 Revision 1, January 2012

02.12.122

Page 30

[ 02-22]

Certification and external livery 02

A320 Family

Table 02-6 - Technical solutions description TDU

Title (Remarks)

Appl.

Weight (kg) MWE/OWE/APL

01

Compliance status with EUOPS 1 - subpart K plus L requirements

A318-100 A319-100 A320-200 A321-200

0.0/0.0/0.0 0.0/0.0/0.0 0.0/0.0/0.0 0.0/0.0/0.0

02

Compliance with EU-OPS 1 subpart K, L and S requirements

A318-100 A319-100 A320-200 A321-200

0.0/0.0/0.0 0.0/0.0/0.0 0.0/0.0/0.0 0.0/0.0/0.0

Issue 6 Revision 1, January 2012

Equipment reference

02.12.122

Equipment supplier

Equipment PN

QTY

Page 31

STS

[ 02-23]

02 Certification and external livery

A320 Family

02.12.123 - Compliance with CS25/FAR 25.562 (Head Injury Criteria - HIC) Objective To certify passenger seats and cabin attendant seats in accordance with CS25/FAR 25.562 (Head Injury Criteria - HIC). Basic aircraft None. Description The passenger seat and cabin attendant seat configuration shall be compliant with CS25/FAR 25.562 regulation. In particular, dynamic tests are required on passenger seats and cabin attendant seats to demonstrate such compliance for the agreed validated cabin layout. Note Airbus commitment to show compliance with such regulation at delivery remains subject to the on-time successful seat supplier results of passenger seat dynamic tests. EPAC selection mode Individual

Issue 6 Revision 1, January 2012

02.12.123

Page 32

[ 02-24]

Certification and external livery 02

A320 Family

Table 02-7 - Technical solutions description TDU

Title (Remarks)

Appl.

Weight (kg) MWE/OWE/APL

03

Compliance with CS25/FAR 25.562 (Head Injury Criteria HIC)

Issue 6 Revision 1, January 2012

A318-100 A319-100 A320-200 A321-200

Equipment reference

Equipment supplier

Equipment PN

QTY

STS

0.0/0.0/0.0 0.0/0.0/0.0 0.0/0.0/0.0 0.0/0.0/0.0

02.12.123

Page 33

[ 02-25]

02 Certification and external livery

A320 Family

02.12.130 - EASA certification of Take Off/Landing operation on wet grooved / PFC runways Objective for A318-100 and A319-100 and A320-200 To allow Take-Off/Landing performance calculation on wet runway taking credit of specific runway pavement (grooved or Porous Friction Course). On those specific pavements, a higher braking friction coefficient, than on standard smooth runways, can be reached. The grooved/PFC (Porous Friction Course) runway is associated to a specific braking friction coefficient on wet runway.

state, taking into account the specific braking friction coefficient. The minimum OCTOPUS version needed for calculation of the Landing A/C performance is V25. EPAC selection mode Individual

Basic aircraft for A318-100 and A319-100 and A320200 None. Description for A318-100 and A319-100 and A320200 The modification consists in introducing the relevant limitations and performance through the AFM supplement to cover Take-Off/Landing operations under wet conditions on grooved/PFC runways. The minimum OCTOPUS version needed is V23.1 that allows as an option to select the calculation of the Take Off A/C performance (Accelerate Stop Distance) either on a smooth runway state or on a grooved/PFC runway

Issue 6 Revision 1, January 2012

02.12.130

Page 34

[ 02-26]

Certification and external livery 02

A320 Family

Table 02-8 - Technical solutions description TDU

Title (Remarks)

Appl.

Weight (kg) MWE/OWE/APL

01

EASA certification of Take-Off operation on wet grooved / PFC runways

A318-100 A319-100 A320-200

0.0/0.0/0.0 0.0/0.0/0.0 0.0/0.0/0.0

02

EASA certification of Landing operation on wet grooved / PFC runways

A318-100 A319-100 A320-200

0.0/0.0/0.0 0.0/0.0/0.0 0.0/0.0/0.0

Issue 6 Revision 1, January 2012

Equipment reference

02.12.130

Equipment supplier

Equipment PN

QTY

Page 35

STS

[ 02-27]

02 Certification and external livery

A320 Family

02.40.101 - External livery Objective To deliver the aircraft painted in the livery of the buyer. External livery means fuselage, vertical stabilizer and nacelles. Basic aircraft The aircraft is delivered painted in white (fuselage, vertical stabilizer), and light grey (wings, Trimmable Horizontal Stabilizer (THS) and nacelles). External markings are in English only. Description The aircraft fuselage, vertical stabilizer and nacelles shall be painted according to the livery of the customer as defined by: • a drawing prepared by AIRBUS, based on decorative instructions from the customer (paper, floppy disk, etc.) • painted colour samples prepared by AIRBUS, based on instructions from the customer (colour references, samples). Note Note 1: Some metallic areas are and remain unpainted:

Issue 6 Revision 1, January 2012

• • • • • • •

leading edges of slats engine intake lips and exhaust, parts of pylons scuff plates horizontal stabilizer shield THS forward leading edge forward pylon fairings equipment details such as angle of attack sensors, static ports, selected antennas etc.

Note 2: One RFC will be issued for drawing identification. Note 3: The complexity of each external livery (design, paint blending and/or fading, number of colours, product selection, ...), can affect the paint production cycle. Consequently, each external livery is investigated on an individual basis, and relevant terms and conditions will be mentioned in the corresponding SCN (Specification Change Notice). EPAC selection mode Individual

02.40.101

Page 36

[ 02-28]

Certification and external livery 02

A320 Family

Figure 02-6 - External livery (A319)

A319 shown Principles valid for all A320 Family versions

IAE engine nacelle anti-skid paint

CFM engine nacelle THS leading edge unpainted Apron fairing

Slat leading edge unpainted

THS travel area Grey M9001 (polyurethane top coat) Grey M9004 (upper wing coating) White M8002 Metallic unpainted

Issue 6 Revision 1, January 2012

02.40.101

Page 37

[ 02-29]

A320 Family

02 Certification and external livery Table 02-9 - Technical solutions description TDU

Title (Remarks)

Appl.

Weight (kg) MWE/OWE/APL

01

External livery

Issue 6 Revision 1, January 2012

A318-100 A319-100 A320-200 A321-200

TBD/TBD/TBD TBD/TBD/TBD TBD/TBD/TBD TBD/TBD/TBD

Equipment reference

External livery

02.40.101

Equipment supplier

Equipment PN

TBD

QTY

TBD

Page 38

STS

SFE

[ 02-30]

A320 Family Reference

Title

03.20.300

Design weights (A318)

03.20.400

Design weights (A319)

03.20.500

Design weights (A320)

03.20.600

Design weights (A321)

Issue 6 Revision 1, January 2012

General aircraft design criteria 03

Page 39

[ 03-1]

03 General aircraft design criteria

A320 Family

03.20.300 - Design weights (A318) Objective for A318-100 To allow the customer to select predefined alternate design weight variants as shown in following table (selectable weight variants associated with basic and optional engines/aircraft models).

EPAC selection mode Individual

Basic aircraft for A318-100 The aircraft basic design weights (weight variant 000) are as follows: • Maximum Taxi Weight (MTW) 59.4 t • Maximum Take-Off Weight (MTOW) 59 t • Maximum Landing Weight (MLW) 56 t • Maximum Zero Fuel Weight (MZFW) 53 t. Description for A318-100 • changes in the aircraft manuals (Aircraft Flight Manual, Weight & Balance Manual, Flight Crew Operation Manual, ...) • modification of the CG diagram • changes in all performance related manuals and software to adapt to the new maximum weights (MTOW, MLW, …) • replacement of labels bonded to the MLG main fitting indicating MTOW and tire pressure • possibly, changes of the wheels when necessary.

Issue 6 Revision 1, January 2012

03.20.300

Page 40

[ 03-2]

General aircraft design criteria 03

A320 Family

A3 1 PW 8-122 61 24 A

A3 1 PW 8-121 61 22 A

Design weights (t)

A3 CF 18-1 M5 12 6-5 B9 /3

Weight variant

A3 CF 18-1 1 M 56 1 -5B 8/3

Figure 03-1 - Design weight options (A318)

CN03.20.311 CN03.20.312 CN03.20.321 CN03.20.322 000

001

002

003

004

005

006

007

008

MTOW MLW MZFW MTOW MLW MZFW MTOW MLW MZFW MTOW MLW MZFW MTOW MLW MZFW MTOW MLW MZFW MTOW MLW MZFW MTOW MLW MZFW MTOW MLW MZFW

Issue 6 Revision 1, January 2012

59 56 53 61.5 56 53 63 57.5 54.5 64.5 57.5 54.5 66 57.5 54.5 68 57.5 54.5 56 56 53 61 56 53 64 56 53

TDU

Basic

Basic

Basic

Basic

20

Certified

Certified

Certified

Certified

01

Certified

Certified

Certified

Certified

02

Certified

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Certified

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03

Certified

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04

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05

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06

Certified

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Certified

Certified

07

Certified

Certified

Certified

Certified

08

03.20.300

Certified = SCG item (no lead-time constraint)

Page 41

[ 03-3]

A320 Family

03 General aircraft design criteria Figure 03-2 - Basic CG limits diagram (A318) Aircraft weight (kg x 1000)

13

15

17

Aircraft weight (kg x 1000)

19

21

23

80

41 %RC 80

75

75

70

70

65

65

27

29

31

33

35

37

39

MTOW 59 000 kg

60 55

25

56

60

MLW 56 000 kg

57

55

MZFW 53 000 kg

50

50 Flight

Flight

45

45 42.6

Take-off

40

Landing

40

Landing

35

15

17 19 21 23

25

27 29 31 33

35

37 39 41 43

35

45 %RC

32.2

05 07 09 11 13

Issue 6 Revision 1, January 2012

03.20.300

Page 42

[ 03-4]

General aircraft design criteria 03

A320 Family

Figure 03-3 - CG limits diagram with max. optional MTOW (A318) Aircraft weight (kg x 1000)

80

41 %RC 80

75

75

70

21

23

25

27

29

31

MTOW 68 000 kg

33

35

37

39

33.0

19

32.0

17

18.7

15

16.7

13

Aircraft weight (kg x 1000)

70 65

65 63

63

60

60

MLW 57 500 kg 57

56

MZFW 54 500 kg

55

55 Flight

50

50 Flight Landing

45 Take-off

Landing

35 05 07 09 11 13

Issue 6 Revision 1, January 2012

40.6

31.18

Take-off

40

15

17 19 21 23

45

25

27 29 31 33

03.20.300

35

37 39 41 43

40 35

45 %RC Page 43

[ 03-5]

03 General aircraft design criteria

A320 Family

03.20.400 - Design weights (A319) Objective for A319-100 To allow the customer to select predefined alternate design weight variants as shown in following table (selectable weight variants associated with basic and optional engines/aircraft models). Basic aircraft for A319-100 The aircraft basic design weights (weight variant 000) are as follows: • Maximum Taxi Weight (MTW) 64.4 t • Maximum Take-Off Weight (MTOW) 64 t • Maximum Landing Weight (MLW) 61 t • Maximum Zero Fuel Weight (MZFW) 57 t.

Note for A319-100 If the Tire Pressure Indication System (TPIS) is installed, the TPIS computer pin programming has to be modified accordingly. EPAC selection mode Individual

Description for A319-100 • changes in the aircraft manuals (Aircraft Flight Manual, Weight & Balance Manual, Flight Crew Operation Manual, ...) • modification of the CG diagram • changes in all performance related manuals and software to adapt to the new maximum weights (MTOW, MLW, ...) • replacement of labels bonded to the NLG/MLG main fitting indicating MTOW and tire pressure • possibly, changes of the brakes, wheels and tires when necessary.

Issue 6 Revision 1, January 2012

03.20.400

Page 44

[ 03-6]

General aircraft design criteria 03

A320 Family

A E V 31925 133 27 MA5 IA

A IAE 319 V2 -132 52 4-A 5

A IA 319 E V -1 25 31 22 -A 5

A CF 319 M 56 115 -5B 7/3

Design weights (t)

CF A319 M 56 112 -5B 6/3

Weight variant

CF A319 M 56 111 -5B 5/3

Figure 03-4 - Design weight options (A319)

CN03.20.411 CN03.20.412 CN03.20.415 CN03.20.431 CN03.20.432 CN03.20.433

008

MTOW MLW MZFW

64 61 57 70 61 57 75.5 62.5 58.5 68 61 57 68 62.5 58.5 70 62.5 58.5 73.5 62.5 58.5 75.5 61 57 64 62.5 58.5

009

MTOW MLW MZFW

66 62.5 58.5

011

MTOW MLW MZFW

012

MTOW MLW MZFW

66 61 57 62 61 57

000

001

002

003

004

005

006

007

MTOW MLW MZFW MTOW MLW MZFW MTOW MLW MZFW MTOW MLW MZFW MTOW MLW MZFW MTOW MLW MZFW MTOW MLW MZFW MTOW MLW MZFW

Issue 6 Revision 1, January 2012

TDU

Basic

Basic

Basic

Basic

Basic

Basic

20

Certified

Certified

Certified

Certified

Certified

Certified

01

Certified

Certified

Certified

Certified

Certified

Certified

02

Certified

Certified

Certified

Certified

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Certified

03

Certified

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Certified

Certified

04

Certified

Certified

Certified

Certified

Certified

Certified

05

Certified

Certified

Certified

Certified

Certified

Certified

06

Certified

Certified

Certified

Certified

Certified

Certified

07

Certified

Certified

Certified

Certified

Certified

Certified

08

Certified

Certified

Certified

Certified

Certified

Certified

09

Certified

Certified

Certified

Certified

Certified

Certified

11

Certified

Certified

Certified

Certified

Certified

Certified

12

03.20.400

Certified = SCG item (no lead-time constraint)

Page 45

[ 03-7]

A320 Family

03 General aircraft design criteria Figure 03-5 - Basic CG limits diagram (A319) Aircraft weight (kg x 1 000)

80

15

17

Aircraft weight (kg x 1 000)

19

21

23

25

27

29

31

33

35

37

39

41% RC 80

75

75

70

70 MTOW 64 000kg

65

65

MLW 61 000kg

60

60 MZFW 57 000kg

55

55 50

50

49.6

45

Take-off

45

Flight

Take-off/landing

40

40

Flight 35.4

35 05

07

09

11

Issue 6 Revision 1, January 2012

13

15

17 19 21 23

25

27 29 31 33

03.20.400

Landing

35

37 39 41 43

45

35 %RC

Page 46

[ 03-8]

General aircraft design criteria 03

A320 Family

Figure 03-6 - CG limits diagram with max. optional MTOW (A319) Aircraft weight (kg x 1000) 13

15

17

Aircraft weight (kg x 1000) 19

21

23

25

27

29

31

33

35

37

39

75

MTOW 75 500 kg

75

74.5

70

70 65.3

65

65

MLW 62 500 kg

60

60

25

MZFW 58 500 kg

55

55

49.6

50

45

Take-off

Take-off/landing 40

41 %RC 80

37

36

26

24

80

50

45 Flight 40

Flight

35.4

35

Landing 35

05 07 09 11 13 15 17 19 21 23 25 27 29 31 33 35 37 39 41 43 45 %RC

Issue 6 Revision 1, January 2012

03.20.400

Page 47

[ 03-9]

03 General aircraft design criteria

A320 Family

03.20.500 - Design weights (A320) Objective for A320-200 To allow the customer to select predefined alternate design weight variants as shown in following table (selectable weight variants associated with basic and optional engines/aircraft models). Basic aircraft for A320-200 The aircraft basic design weights (weight variant 008) are as follows: • Maximum Taxi Weight (MTW) 73.9 t • Maximum Take-Off Weight (MTOW) 73.5 t • Maximum Landing Weight (MLW) 64.5 t • Maximum Zero Fuel Weight (MZFW) 61.0 t.

• possible limitations associated to high design weights (for example maximum taxiing speed during turns). Note for A320-200 If the Tire Pressure Indication System (TPIS) is installed, the TPIS computer pin programming has to be modified accordingly. EPAC selection mode Individual

Description for A320-200 • changes in the aircraft manuals (Aircraft Flight Manual, Weight & Balance Manual, Flight Crew Operation Manual, …) • modification of the CG diagram • changes in all performance related manuals and software to adapt to the new maximum weights (MTOW, MLW, …) • replacement of labels bonded to the NLG/MLG main fitting indicating MTOW and tire pressure • possibly, changes of the brakes, wheels and tires when necessary

Issue 6 Revision 1, January 2012

03.20.500

Page 48

[ 03-10]

General aircraft design criteria 03

A320 Family

Figure 03-7 - Design weight options (A320) Weight Variant

008

009

010

011

012

013

014

015

016

017

018

Design weights (tons)

MTOW MLW MZFW MTOW MLW MZFW MTOW MLW MZFW MTOW MLW MZFW MTOW MLW MZFW MTOW MLW MZFW MTOW MLW MZFW MTOW MLW MZFW MTOW MLW MZFW MTOW MLW MZFW MTOW MLW MZFW

A320-214 CFM 56-5B4/3

A320-215 CFM 56-5B5/3

A320-216 CFM 56-5B6/3

A320-232 IAE V2527-A5

A320-233 IAE V2527E-A5

CN03.20.514

CN03.20.515

CN03.20.516

CN03.20.532

CN03.20.533

TDU

Basic

Basic

Basic

Basic

Basic

08

Certified

Certified

Certified

Certified

Certified

09

Certified

N/A

N/A

Certified

Certified

10

Certified

Certified

Certified

Certified

Certified

11

Certified

N/A

N/A

Certified

Certified

12

Certified

Certified

Certified

Certified

Certified

13

Certified

Certified

Certified

Certified

Certified

14

Certified

N/A

N/A

Certified

Certified

15

Certified

Certified

Certified

Certified

Certified

16

Certified

N/A

N/A

Certified

Certified

17

Certified

Certified

Certified

Certified

Certified

18

73.5 64.5 61 75.5 64.5 61 77 64.5 61 75.5 66 62.5 77 66 62.5 71.5 64.5 61 73.5 64.5 61.5 78 64.5 61 73.5 66 62.5 78 66 62.5 71.5 66 62.5

Issue 6 Revision 1, January 2012

03.20.500

Certified = SCG item (no leadtime constraint) N/A = Not Applicable

Page 49

[ 03-11]

A320 Family

03 General aircraft design criteria Figure 03-8 - Basic CG limits diagram (A320) Aircraft weight (kg x 1 000)

15

17

19

Aircraft weight (kg x 1 000)

21

23

25

27

29

31

35

33

37

39

41% RC

90

90

85

85

80

80

75

75

MTOW 73 500kg

70

69.5

MLW 64 500kg

65

70 65

MZFW 61 000kg

60

60

55

55 50

50 47.5

45

45 Take-off

40 35

Flight

Take-off/landing Flight 05

07

40

Landing

09 11 13

Issue 6 Revision 1, January 2012

15

17 19 21 23

25

27 29 31 33

35

37 39 41 43

03.20.500

45

35 %RC

Page 50

[ 03-12]

A320 Family

General aircraft design criteria 03

Figure 03-9 - CG limits diagram with max. optional MTOW (A320)

Issue 6 Revision 1, January 2012

03.20.500

Page 51

[ 03-13]

03 General aircraft design criteria

A320 Family

03.20.600 - Design weights (A321) Objective for A321-200 To allow the customer to select predefined alternate design weight variants as shown in following table (selectable weight variants associated with basic and optional engines/aircraft models). Basic aircraft for A321-200 The aircraft basic design weights (weight variant 000) are as follows: • Maximum Taxi Weight (MTW) 89.4 t • Maximum Take-Off Weight (MTOW) 89.0 t • Maximum Landing Weight (MLW) 75.5 t • Maximum Zero Fuel Weight (MZFW) 71.5 t.

Note for A321-200 If the Tire Pressure Indication System (TPIS) is installed, the TPIS computer pin programming has to be modified accordingly. EPAC selection mode Individual

Description for A321-200 • changes in the aircraft manuals (Aircraft Flight Manual, Weight & Balance Manual, Flight Crew Operation Manual, …) • modification of the CG diagram • changes in all performance related manuals and software to adapt to the new maximum weights (MTOW, MLW, …) • replacement of labels bonded to the NLG/MLG main fitting indicating MTOW and tire pressure • possibly, changes of the brakes, wheels and tires when necessary.

Issue 6 Revision 1, January 2012

03.20.600

Page 52

[ 03-14]

General aircraft design criteria 03

A320 Family

IAE A321 V2 -232 53 0-A 5

IAE A321 V2 -231 53 3-A 5

CF A321 M5 -21 6-5 3 B2 /3

Design weights (t)

A CF 321 M5 -21 6-5 2 B1 /3

Weight variant

CF A321 M 56 211 -5B 3/3

Figure 03-10 - Design weight options (A321)

CN03.20.611 CN03.20.612 CN03.20.613 CN03.20.631 CN03.20.632 000

001

002

004

005

006

007

008

009

010

011

MTOW MLW MZFW MTOW MLW MZFW MTOW MLW MZFW MTOW MLW MZFW MTOW MLW MZFW MTOW MLW MZFW MTOW MLW MZFW MTOW MLW MZFW MTOW MLW MZFW MTOW MLW MZFW MTOW MLW MZFW

Issue 6 Revision 1, January 2012

89 75.5 71.5 93 77.8 73.8 89 77.8 73.8 87 75.5 71.5 85 75.5 71.5 83 75.5 71.5 83 73.5 69.5 80 73.5 69.5 78 73.5 69.5 85 77.8 73.8 93.5 77.8 73.8

Basic

Basic

Basic

Certified

Certified

Certified

Certified

Certified

Certified

Basic

TDU

Basic

20

Certified

Certified

01

Certified

Certified

Certified

02

Certified

Certified

Certified

Certified

04

Certified

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05

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06

Not yet certified

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Not yet certified

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07

Not yet certified

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Not yet certified

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08

Not yet certified

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Not yet certified

Certified

09

Not yet certified

Certified

Certified

Not yet certified

Certified

10

Certified

Certified

Certified

Certified

Certified

11

03.20.600

Certified = SCG item (no lead-time constraint) Not yet certified = certification possible on specific customer request (lead-time constraint)

Page 53

[ 03-15]

A320 Family

03 General aircraft design criteria Figure 03-11 - Basic CG limits diagram (A321) Aircraft weight (kg x 1 000)

95

13

15

17

Aircraft weight (kg x 1 000)

19

21

23

25

27

29

31

33

35

37

39

41% RC 95 90

90 MTOW 89 000kg

85

85 81.8

80

40.1

80 MLW 75 500kg

75

75 MZFW 71 500kg

70

70

65

65 Take-off

60

60

55

55

50

50

45

45

Flight

Landing Take-off/landing

40

40

Flight

35

05

Issue 6 Revision 1, January 2012

07 09 11 13

15

17 19 21 23

25

27 29 31 33

35

03.20.600

37 39 41 43

45

35

%RC

Page 54

[ 03-16]

General aircraft design criteria 03

A320 Family

Figure 03-12 - CG limits diagram with max. optional MTOW (A321) Aircraft weight (kg x 1000)

Aircraft weight (kg x 1000)

13

15

17

19

21

23

25

27

29

31

33

35

37

41 %RC 95

88 36.

83

90

37.

89.0

MTOW 93 500 kg

21.65

19.65

91.5

90

.16

85

39

17.5

MLW 77 800 kg

40.6

15.5

80

15.33

85

80.3 79.2 75.5

MZFW 73 800 kg

9.5

75

39

17

95

80 75

70

70

65

65

60

60

55

55

50

50 Take-off/landing

Flight

45

45 Landing

42.9

Flight E23_011_232A

Take-off

40

40

35

35 05 07 09 11 13

Issue 6 Revision 1, January 2012

15

17 19 21 23

25

27 29 31 33 35 37 39 41 43

03.20.600

45%RC

Page 55

[ 03-17]

03 General aircraft design criteria

A320 Family

Intentionally left blank

Issue 6 Revision 1, January 2012

03.20.600

Page 56

[ 03-18]

A320 Family

Placards and markings 11

Reference

Title

11.00.124

Installation of leasing identification plates

11.20.100

Second language for door operation external placards and markings

11.20.110

Second language for selected external placards and markings

11.20.119

Nose Landing Gear (NLG) permanent steering markers

11.20.135

Second language for residual cabin & cargo pressure exterior door warning placards

11.21.101

Emergency cut-out markings

11.22.100

Landing gear placards

11.30.100

Installation of additional access placards in forward and aft cargo holds

11.30.121

Second language for cargo compartment placards

11.30.136

US and metric units for cargo compartment height placards

11.33.101

Placard for flight crew oxygen system

Issue 6 Revision 1, January 2012

Page 57

[ 11-1]

A320 Family

11 Placards and markings 11.00.124 - Installation of leasing identification plates Objective To install supplementary (leasing) identification plates on the aircraft. Basic aircraft Manufacturer and owner plates are installed on the frame of the forward RH passenger/crew/service door. A SELCAL plate is installed on the main instrument panel. Description Leasing plates are installed on each engine, on the upper frame of the forward LH passenger door and on the cockpit side of lavatory A partition according to customer requirements. Note The wording of the plates shall be provided to AIRBUS contracts as soon as possible or at the latest one week before the start of the ground check. EPAC selection mode Individual

Issue 6 Revision 1, January 2012

11.00.124

Page 58

[ 11-2]

Placards and markings 11

A320 Family

Table 11-1 - Technical solutions description TDU

Title (Remarks)

Appl.

Weight (kg) MWE/OWE/APL

01

Installation of leasing identification plates on engines, LH door frame and Lav A partition

A318-100 A319-100 A320-200 A321-200

Negl./Negl./Negl. Negl./Negl./Negl. Negl./Negl./Negl. Negl./Negl./Negl.

02

Installation of leasing identification plates on engines

A318-100 A319-100 A320-200 A321-200

Negl./Negl./Negl. Negl./Negl./Negl. Negl./Negl./Negl. Negl./Negl./Negl.

03

Installation of leasing identification plates on LH door frame

A318-100 A319-100 A320-200 A321-200

Negl./Negl./Negl. Negl./Negl./Negl. Negl./Negl./Negl. Negl./Negl./Negl.

04

Installation of leasing identification plates on Lavatory A partition

A318-100 A319-100 A320-200 A321-200

Negl./Negl./Negl. Negl./Negl./Negl. Negl./Negl./Negl. Negl./Negl./Negl.

Issue 6 Revision 1, January 2012

Equipment reference

11.00.124

Equipment supplier

Equipment PN

QTY

Page 59

STS

[ 11-3]

A320 Family

11 Placards and markings

11.20.100 - Second language for door operation external placards and markings Objective To provide exterior placards and markings related to door operation in bilingual (English and a second language) instead of English only.

EPAC selection mode Individual

Basic aircraft Exterior placards and markings are in English. Description The following exterior placards and markings, related to operation, shall be bilingual: • passenger/crew doors and emergency exits • cargo doors. (These markings are considered as one single package). Note • the translation of the basic English wording into the customers nominated language and a graphic, if necessary, shall be provided by the customer (high quality scale one printout and/or floppy disk) • an individual RFC has to be issued with the second language identification (refer to external markings booklets).

Issue 6 Revision 1, January 2012

11.20.100

Page 60

[ 11-4]

Placards and markings 11

A320 Family

Table 11-2 - Technical solutions description TDU

Title (Remarks)

Appl.

Weight (kg) MWE/OWE/APL

01

Second language for door operation external placards and markings

Issue 6 Revision 1, January 2012

A318-100 A319-100 A320-200 A321-200

Negl./Negl./Negl. Negl./Negl./Negl. Negl./Negl./Negl. Negl./Negl./Negl.

Equipment reference

Second language

11.20.100

Equipment supplier

Equipment PN

TBD

QTY

TBD

Page 61

STS

SFE

[ 11-5]

A320 Family

11 Placards and markings

11.20.110 - Second language for selected external placards and markings Objective To provide selected external placards and markings in bilingual (English and a second language) instead of English only. Basic aircraft External placards and markings are in English. Description In addition to the external placards dedicated to residual cabin pressure warnings and doors operation, it is possible to select some of the others external placards and markings as bilingual ones. Note • the translation of the basic English wording into the customers nominated language and a graphic, if necessary, shall be provided by the customer • an individual RFC has to be issued for second language identification and the selection of concerned placards and markings (refer to external markings booklets). EPAC selection mode Individual

Issue 6 Revision 1, January 2012

11.20.110

Page 62

[ 11-6]

Placards and markings 11

A320 Family

Table 11-3 - Technical solutions description TDU

Title (Remarks)

Appl.

Weight (kg) MWE/OWE/APL

Equipment reference

Equipment supplier

Equipment PN

QTY

STS

01

Second language for selected external placards and markings (A319)

A319-100

Negl./Negl./Negl.

Second language

TBD

TBD

SFE

02

Second language for selected external placards and markings (A320)

A320-200

Negl./Negl./Negl.

Second language

TBD

TBD

SFE

03

Second language for selected external placards and markings (A321)

A321-200

Negl./Negl./Negl.

Second language

TBD

TBD

SFE

04

Second language for selected external placards and markings (A318)

A318-100

Negl./Negl./Negl.

Second language

TBD

TBD

SFE

Issue 6 Revision 1, January 2012

11.20.110

Page 63

[ 11-7]

A320 Family

11 Placards and markings

11.20.119 - Nose Landing Gear (NLG) permanent steering markers Objective To provide permanent steering markers on the nose landing gear doors. Basic aircraft None. Description Nose wheel steering maximum angle markings (corresponding to a +/- 85 degree wheel position) and associated "NO TOW" texts shall be provided on both aft doors of the Nose Landing Gear (NLG). The areas shall be red with a 5 mm width white border depending on background color (to be defined by AIRBUS). "NO TOW" shall be white. EPAC selection mode Individual

Issue 6 Revision 1, January 2012

11.20.119

Page 64

[ 11-8]

Placards and markings 11

A320 Family

Figure 11-1 - NO TOW markings on NLG aft doors LEFT SIDE

Issue 6 Revision 1, January 2012

RIGHT SIDE

11.20.119

Page 65

[ 11-9]

A320 Family

11 Placards and markings Table 11-4 - Technical solutions description TDU

Title (Remarks)

Appl.

Weight (kg) MWE/OWE/APL

18

Nose wheel steering "NO TOW" zone and text on NLG aft doors

Issue 6 Revision 1, January 2012

A318-100 A319-100 A320-200 A321-200

Equipment reference

Equipment supplier

Equipment PN

QTY

STS

Negl./Negl./Negl. Negl./Negl./Negl. Negl./Negl./Negl. Negl./Negl./Negl.

11.20.119

Page 66

[ 11-10]

Placards and markings 11

A320 Family

Intentionally left blank

Issue 6 Revision 1, January 2012

11.20.119

Page 67

[ 11-11]

A320 Family

11 Placards and markings

11.20.135 - Second language for residual cabin & cargo pressure exterior door warning placards Objective To provide translation in a second language for residual cabin and cargo pressure exterior door warnings.

EPAC selection mode Individual

Basic aircraft To give warning on the ground that door handle operation with a cargo differential pressure will cause violent door opening: • passenger/crew/service doors are basically equipped with a red light flashing if cabin differential pressure is above 2.5 mbar • cargo doors are basically equipped with a vent door actuated when door lever is unlocked • residual cabin pressure door warning placards on passenger/crew/service doors, emergency exits and cargo compartment doors are provided in English language with space for a second language. Note • the translation of the English wording into the language to be applied (customer text) shall be provided by the customer in accordance with the associated customer request • the translation of the interior warning placards for residual pressure is to be selected through CCG item CN11.30.110 TDU 43.

Issue 6 Revision 1, January 2012

11.20.135

Page 68

[ 11-12]

Placards and markings 11

A320 Family

Figure 11-2 - Cabin and cargo exterior placards location for residual pressure Window

Cargo doors outside

Outside

Slide armed* Cabin pressure indicator

Vent door

Window PUSH HERE

Handle Flap

DANGER

*

DO NOT OPEN DOOR IF RED WARNING LIGHT IS FLASHING (CABIN PRESSURIZED !)

Issue 6 Revision 1, January 2012

Space for second language

WARNING

*

ENSURE THAT YOU ARE POSITIONED LEFT OF THE DOOR FRAME WHILE UNLOCKING THE CARGO DOOR TO AVOID INJURY IN CASE OF SUDDEN DOOR OPENING

11.20.135

Page 69

[ 11-13]

A320 Family

11 Placards and markings Table 11-5 - Technical solutions description TDU

Title (Remarks)

Appl.

Weight (kg) MWE/OWE/APL

01

Second language for residual cabin & cargo pressure exterior door warning placards

Issue 6 Revision 1, January 2012

A318-100 A319-100 A320-200 A321-200

Negl./Negl./Negl. Negl./Negl./Negl. Negl./Negl./Negl. Negl./Negl./Negl.

Equipment reference

Second language

11.20.135

Equipment supplier

Equipment PN

TBD

QTY

TBD

Page 70

STS

SFE

[ 11-14]

Placards and markings 11

A320 Family

Intentionally left blank

Issue 6 Revision 1, January 2012

11.20.135

Page 71

[ 11-15]

A320 Family

11 Placards and markings 11.21.101 - Emergency cut-out markings Objective To enable rescue personnel to cut through the fuselage structure with minimum obstruction/hindrance during rescue operation. Basic aircraft None. Description The emergency-cut out markings are applied around a cabin window on the outer LH and RH side fuselage including the English wording "CUT HERE IN EMERGENCY". 2 marking sets are applied on each side for A318 / A319 / A320 and 3 marking sets for A321. Note The location depends on the interior monument positioning. EPAC selection mode Individual

Issue 6 Revision 1, January 2012

11.21.101

Page 72

[ 11-16]

Placards and markings 11

A320 Family

Figure 11-3 - Emergency cut-out markings

Issue 6 Revision 1, January 2012

11.21.101

Page 73

[ 11-17]

A320 Family

11 Placards and markings Table 11-6 - Technical solutions description TDU

Title (Remarks)

Appl.

Weight (kg) MWE/OWE/APL

01

Emergency cut-out markings

A318-100 A319-100 A320-200 A321-200

Negl./Negl./Negl. Negl./Negl./Negl. Negl./Negl./Negl. Negl./Negl./Negl.

14

Bilingual emergency cut-out markings

A318-100 A319-100 A320-200 A321-200

Negl./Negl./Negl. Negl./Negl./Negl. Negl./Negl./Negl. Negl./Negl./Negl.

Issue 6 Revision 1, January 2012

Equipment reference

Equipment supplier

Equipment PN

QTY

STS

Colour

TBD

1

SFE

Language placement

TBD

1

SFE

Second language

TBD

1

SFE

11.21.101

Page 74

[ 11-18]

Placards and markings 11

A320 Family

Intentionally left blank

Issue 6 Revision 1, January 2012

11.21.101

Page 75

[ 11-19]

A320 Family

11 Placards and markings 11.22.100 - Landing gear placards Objective To provide more detailed information for the maintenance. Basic aircraft None. Description An "Inflate tyres with nitrogen only" placard is installed on the NLG. This placard is identical to the one basically installed on the MLG. EPAC selection mode Individual

Issue 6 Revision 1, January 2012

11.22.100

Page 76

[ 11-20]

Placards and markings 11

A320 Family

Table 11-7 - Technical solutions description TDU

Title (Remarks)

Appl.

Weight (kg) MWE/OWE/APL

05

"INFLATE TYRES WITH NITROGEN ONLY" placard on NLG

Issue 6 Revision 1, January 2012

A318-100 A319-100 A320-200 A321-200

Equipment reference

Equipment supplier

Equipment PN

QTY

STS

Negl./Negl./Negl. Negl./Negl./Negl. Negl./Negl./Negl. Negl./Negl./Negl.

11.22.100

Page 77

[ 11-21]

A320 Family

11 Placards and markings

11.30.100 - Installation of additional access placards in forward and aft cargo holds Objective for A320-200 and A321-200 To provide indication for accessibility of system components installed behind the lining and partitions of forward and aft cargo holds. Basic aircraft for A320-200 and A321-200 All placards within the cargo holds are installed in line with the basic aircraft and different system options taken by the customer. Description for A320-200 and A321-200 The following additional access placards shall be installed in forward and aft cargo holds to direct and ease access for affected equipment: • ACCESS RAD.ALT.I (RADio ALTimeter transceiver) • ACCESS RAD.ALT.II • ACCESS TO parts of recirculation system • ECB ACCESS PANEL (Electronic Control Box) • VSC ACCESS PANEL (Vacuum System Controller) • ACCESS TO several system components EPAC selection mode Individual

Issue 6 Revision 1, January 2012

11.30.100

Page 78

[ 11-22]

Placards and markings 11

A320 Family

Figure 11-4 - Additional access placards in forward and aft cargo holds

ACCESS RAD. ALT. I ACCESS RAD. ALT. II

ECB

VSC

ACCESS PANEL

ACCESS PANEL

ACCESS TO

ACCESS TO

- RECIRCULATION FILTER - RECIRCULATION FAN - TRIM AIR VALVES - TRIM AIR REG. VALVE - MIXER FLAP ACTUATOR

- CONTROL UNIT FOR DRAIN MAST ICE PROTECTION - ACCELEROMETER UNIT - FIRE EXTINGUISHING BOTTLES

REMOVE THIS LINING

REMOVE THIS LINING

Typical access placards

Issue 6 Revision 1, January 2012

11.30.100

Page 79

[ 11-23]

A320 Family

11 Placards and markings Table 11-8 - Technical solutions description TDU

Title (Remarks)

Appl.

Weight (kg) MWE/OWE/APL

01

Installation of additional access placards in forward and aft cargo holds

A320-200 A321-200

Equipment reference

Equipment supplier

Equipment PN

QTY

STS

Negl./Negl./Negl. Negl./Negl./Negl.

Basic on A318/A319

Issue 6 Revision 1, January 2012

11.30.100

Page 80

[ 11-24]

Placards and markings 11

A320 Family

Intentionally left blank

Issue 6 Revision 1, January 2012

11.30.100

Page 81

[ 11-25]

A320 Family

11 Placards and markings 11.30.121 - Second language for cargo compartment placards Objective To install bilingual cargo compartment placards and signs. Basic aircraft The standard cargo compartment placards and signs are monolingual and in English only. Description The bilingual cargo compartment placards and signs can be installed either with: • English below and a second customer nominated language or with: • English above and a second customer nominated language. EPAC selection mode Individual

Issue 6 Revision 1, January 2012

11.30.121

Page 82

[ 11-26]

Placards and markings 11

A320 Family

Figure 11-5 - Cargo compartment placards

MAX. LOADING HEIGHT

Monolingual - Basic

MIN. 2” CLEARANCE TO CEILING 10 - D255.72950.302

BILINGUAL PLACARD OPTIONS - EXAMPLE : English / Portuguese

ALTURA MAXIMA DO CARREGAMENTO MAX. LOADING HEIGHT

Bilingual - Second language / English (TDU 02)

A 2" DE DISTANCIA DO TETO MIN. 2" CLEARANCE TO CEILING - EXAMPLE ONLY -

MAX. LOADING HEIGHT ALTURA MAXIMA DO CARREGAMENTO

Bilingual - English / Second language (TDU 03)

MIN. 2" CLEARANCE TO CEILING A 2" DE DISTANCIA DO TETO - EXAMPLE ONLY -

Issue 6 Revision 1, January 2012

11.30.121

Page 83

[ 11-27]

A320 Family

11 Placards and markings Table 11-9 - Technical solutions description TDU

Title (Remarks)

Appl.

Weight (kg) MWE/OWE/APL

Equipment reference

Equipment supplier

Equipment PN

QTY

STS

Std

Monolingual cargo compartment placards and signs English only

A318-100 A319-100 A320-200 A321-200

02

Bilingual cargo compartment placards and signs - English below and second language

A318-100 A319-100 A320-200 A321-200

Negl./Negl./Negl. Negl./Negl./Negl. Negl./Negl./Negl. Negl./Negl./Negl.

Second language

TBD

TBD

SFE

03

Bilingual cargo compartment placards and signs - English above and second language

A318-100 A319-100 A320-200 A321-200

Negl./Negl./Negl. Negl./Negl./Negl. Negl./Negl./Negl. Negl./Negl./Negl.

Second language

TBD

TBD

SFE

Issue 6 Revision 1, January 2012

11.30.121

Page 84

[ 11-28]

Placards and markings 11

A320 Family

Intentionally left blank

Issue 6 Revision 1, January 2012

11.30.121

Page 85

[ 11-29]

A320 Family

11 Placards and markings

11.30.136 - US and metric units for cargo compartment height placards Objective for A319-100 and A320-200 and A321-200 To install cargo compartment height indication placards with US and metric units (inch and mm). Basic aircraft for A319-100 and A320-200 and A321200 The standard cargo compartment height indication placards show US units only. Description for A319-100 and A320-200 and A321200 The cargo compartment height indication placards with US and metric units shall be installed in fwd and aft cargo holds on side lining close to ceiling to indicate the maximum allowed height for bulk cargo operation. EPAC selection mode Individual

Issue 6 Revision 1, January 2012

11.30.136

Page 86

[ 11-30]

Placards and markings 11

A320 Family

Figure 11-6 - Cargo compartment height placards in US and metric units

MAX. LOADING HEIGHT MIN. 2 in (50.8 mm) CLEARANCE TO CEILING 10 0255 72950.306

Issue 6 Revision 1, January 2012

11.30.136

Page 87

[ 11-31]

A320 Family

11 Placards and markings Table 11-10 - Technical solutions description TDU

Title (Remarks)

Appl.

Weight (kg) MWE/OWE/APL

01

US and metric units for cargo compartment height placards Basic on A318

Issue 6 Revision 1, January 2012

A319-100 A320-200 A321-200

Equipment reference

Equipment supplier

Equipment PN

QTY

STS

Negl./Negl./Negl. Negl./Negl./Negl. Negl./Negl./Negl.

11.30.136

Page 88

[ 11-32]

Placards and markings 11

A320 Family

Intentionally left blank

Issue 6 Revision 1, January 2012

11.30.136

Page 89

[ 11-33]

A320 Family

11 Placards and markings 11.33.101 - Placard for flight crew oxygen system Objective Provide more detailed information for the maintenance. Basic aircraft General recommendation is provided. Description The oxygen supply system label shall feature the following wording: Oxygen supply system • work to be performed by authorized personnel only • ensure hands & tools are clean to prevent system contamination • during bottle replacement protect disconnected ends. EPAC selection mode Individual

Issue 6 Revision 1, January 2012

11.33.101

Page 90

[ 11-34]

Placards and markings 11

A320 Family

Figure 11-7 - Placard for flight crew oxygen system

PRE MOD

BOTTLE REPLACEMENT - ONLY AUTHORIZED OPERATION: REMOVAL OF THE BOTTLES (S) - DURING THE OPERATION PROTECT DISCONNECTED ENDS

Issue 6 Revision 1, January 2012

POST MOD

OXYGEN SUPPLY SYSTEM - WORK TO BE PERFORMED BY AUTHORIZED PERSONNEL ONLY - ENSURE HANDS & TOOLS ARE CLEAN TO PREVENT SYS. CONTAMINATION - DURING BOTTLE REPLACEMENT PROTECT DISCONNECTED ENDS

11.33.101

Page 91

[ 11-35]

A320 Family

11 Placards and markings Table 11-11 - Technical solutions description TDU

Title (Remarks)

Appl.

Weight (kg) MWE/OWE/APL

01

Oxygen supply system label change

Issue 6 Revision 1, January 2012

A318-100 A319-100 A320-200 A321-200

Equipment reference

Equipment supplier

Equipment PN

QTY

STS

Negl./Negl./Negl. Negl./Negl./Negl. Negl./Negl./Negl. Negl./Negl./Negl.

11.33.101

Page 92

[ 11-36]

A320 Family

Air conditioning 21

Reference

Title

21.20.108

Cabin air recirculation filter cartridges equipment selection

21.22.100

Installation of electrical heaters for foot air outlets in the cockpit

21.26.110

Avionics ventilation fan automatic speed reduction

21.27.108

Avionics ventilation air filter alternate equipment

21.28.201

Installation of ventilation system for forward cargo hold

21.28.210

Installation of ventilation system for complete aft cargo hold

21.41.100

Installation of front air outlets at flight crew foot level

21.43.201

Installation of heating system for forward cargo hold

21.43.204

Installation of heating system for complete aft cargo hold

21.70.109

Installation of ozone catalytic converters

Issue 6 Revision 1, January 2012

Page 93

[ 21-1]

A320 Family

21 Air conditioning

21.20.108 - Cabin air recirculation filter cartridges equipment selection Objective To allow the customer to select one of the two basic vendors for the cabin air recirculation filter cartridges. Basic aircraft Two High Efficiency Particle Arrestor (HEPA) recirculation filter cartridges are installed. Each filter cartridge is made of pleated glassfiber, integrated inside a reinforced cylinder. Description Basic filter cartridges are installed according to vendor selection made under TDU 01 or TDU 03. Note • if no vendor choice is made by the customer, one of the selectable equipment will be installed according to AIRBUS industrial requirements • filter housings remain the same. EPAC selection mode Individual

Issue 6 Revision 1, January 2012

21.20.108

Page 94

[ 21-2]

Air conditioning 21

A320 Family Figure 21-1 - Recirculation filters

FWD zone supply duct AFT zone supply duct

Recirculation filter

FW

AI

R

FL

OW

Pack 1 Mixer unit Housing

Pack 2

Filter cartridge

Issue 6 Revision 1, January 2012

21.20.108

Page 95

[ 21-3]

A320 Family

21 Air conditioning Table 21-1 - Technical solutions description TDU

Title (Remarks)

Appl.

Weight (kg) MWE/OWE/APL

Equipment reference

Equipment supplier

Equipment PN

QTY

STS

01

Cabin air recirculation filter cartridge equipment selection PALL-APME

A318-100 A319-100 A320-200 A321-200

Negl./Negl./Negl. Negl./Negl./Negl. Negl./Negl./Negl. Negl./Negl./Negl.

Recirculation filter cartridge

PALL- APME

QA06423-01

2

SFE

03

Cabin air recirculation filter cartridge equipment selection LE BOZEC, PN 424B200-7

A318-100 A319-100 A320-200 A321-200

Negl./Negl./Negl. Negl./Negl./Negl. Negl./Negl./Negl. Negl./Negl./Negl.

Recirculation filter cartridge

LE BOZEC

424B200-7

2

SFE

Issue 6 Revision 1, January 2012

21.20.108

Page 96

[ 21-4]

Air conditioning 21

A320 Family

Intentionally left blank

Issue 6 Revision 1, January 2012

21.20.108

Page 97

[ 21-5]

A320 Family

21 Air conditioning

21.22.100 - Installation of electrical heaters for foot air outlets in the cockpit Objective To improve the comfort for the captain and first officer by the installation of heaters within the foot air piping. Basic aircraft None. Description The modification consists in installing heaters within the foot air piping and switches in the cockpit. The air temperature as well as the surface temperature in the vicinity of the feet shall be increased. Note This option is recommended for a flight duration higher than 2 hours. EPAC selection mode Individual

Issue 6 Revision 1, January 2012

21.22.100

Page 98

[ 21-6]

Air conditioning 21

A320 Family

Figure 21-2 - Electrical heater for foot air outlets

Issue 6 Revision 1, January 2012

21.22.100

Page 99

[ 21-7]

A320 Family

21 Air conditioning Table 21-2 - Technical solutions description TDU

Title (Remarks)

Appl.

Weight (kg) MWE/OWE/APL

02

Installation of electrical heaters on the foot air outlets in cockpit for Captain and F/O

Issue 6 Revision 1, January 2012

A318-100 A319-100 A320-200 A321-200

Equipment reference

Equipment supplier

Equipment PN

QTY

STS

8.0/8.0/-8.0 8.0/8.0/-8.0 8.0/8.0/-8.0 8.0/8.0/-8.0

21.22.100

Page 100

[ 21-8]

Air conditioning 21

A320 Family

Intentionally left blank

Issue 6 Revision 1, January 2012

21.22.100

Page 101

[ 21-9]

A320 Family

21 Air conditioning 21.26.110 - Avionics ventilation fan automatic speed reduction Objective In order to reduce the cockpit noise mainly on ground at low and moderate temperatures. Basic aircraft One blower fan and one extract fan provide adequate avionics air flow ventilation. Description In order to reduce the cockpit noise level on ground the blower and the extract fans of the avionics ventilation system shall automatically reduce their speed in relation with the avionics blowing air temperature. The installed fans are equipped with ceramic ball bearings. EPAC selection mode Individual

Issue 6 Revision 1, January 2012

21.26.110

Page 102

[ 21-10]

Air conditioning 21

A320 Family

Figure 21-3 - Avionics ventilation system Avionics bay Skin exch outlet bypass valve Skin exch isol valve

Skin heat exchanger

Skin air inlet valve

Blower fan

Extract fan

Skin air outlet valve

Avionics equipment Filter Air cond inlet valve

Valves and fans control

Air cond duct

Cargo underfloor

Skin exch inlet bypass valve

Ground-flight

AEVC Thrust lever position Skin temperature Reset p/b Fault light

Blower fan Extract fan Ventilation fan

Issue 6 Revision 1, January 2012

21.26.110

Page 103

[ 21-11]

A320 Family

21 Air conditioning Table 21-3 - Technical solutions description TDU

Title (Remarks)

Appl.

Weight (kg) MWE/OWE/APL

03

Avionics ventilation fan automatic speed reduction - TECHNOFAN

A318-100 A319-100 A320-200 A321-200

6.5/6.5/-6.5 6.5/6.5/-6.5 6.5/6.5/-6.5 6.5/6.5/-6.5

Equipment reference

Equipment supplier

QTY

STS

Avionics ventilation fan

TECHNOFAN

EVT3454J01

2

SFE

Fan speed controller

TECHNOFAN

DV3454A00

1

SFE

87232323V01

1

SFE

Sensor temperature THALES AVIONICS SA speed control

Issue 6 Revision 1, January 2012

Equipment PN

21.26.110

Page 104

[ 21-12]

Air conditioning 21

A320 Family

Intentionally left blank

Issue 6 Revision 1, January 2012

21.26.110

Page 105

[ 21-13]

A320 Family

21 Air conditioning 21.27.108 - Avionics ventilation air filter alternate equipment Objective To provide alternate equipment for the existing avionics ventilation air filter. Basic aircraft One avionics ventilation air filter is installed. Description The air filter of the avionics ventilation system is replaced by alternate equipment. The cartridges are not interchangeable but the aircraft interfaces of the filter housings are identical. EPAC selection mode Individual

Issue 6 Revision 1, January 2012

21.27.108

Page 106

[ 21-14]

Air conditioning 21

A320 Family

Figure 21-4 - Avionics ventilation air filter

A

A

A

Housing

Housing Demister

Filter cartridge

Filter cartridge

Basic equipment

Alternate equipment U-bend

Duct assembly

Issue 6 Revision 1, January 2012

21.27.108

Page 107

[ 21-15]

A320 Family

21 Air conditioning Table 21-4 - Technical solutions description TDU

Title (Remarks)

Appl.

Weight (kg) MWE/OWE/APL

Std

06

Avionics ventilation air filter basic equipment - LE BOZEC, PN 4200A200-6

Avionics ventilation air filter alternate equipment - PALLAPME, QB0776

Issue 6 Revision 1, January 2012

A318-100 A319-100 A320-200 A321-200

A318-100 A319-100 A320-200 A321-200

Negl./Negl./Negl. Negl./Negl./Negl. Negl./Negl./Negl. Negl./Negl./Negl.

Equipment reference

Equipment supplier

Equipment PN

QTY

STS

Avionics ventilation air filter cartridge

LE BOZEC

4200A200-6

1

SFE

Demister

LE BOZEC

425A200-5

1

SFE

Duct assembly

LE BOZEC

402U20-2

1

SFE

Housing

LE BOZEC

402K200-2

1

SFE

Cartridge

PALL- APME

QB0776

1

SFE

Housing

PALL- APME

QB0555

1

SFE

U-bend

PALL- APME

QB0553

1

SFE

21.27.108

Page 108

[ 21-16]

Air conditioning 21

A320 Family

Intentionally left blank

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21.27.108

Page 109

[ 21-17]

A320 Family

21 Air conditioning

21.28.201 - Installation of ventilation system for forward cargo hold Objective for A319-100 and A320-200 and A321-200 To provide a ventilation system for the forward cargo hold, to enable increased utilization of the hold, e.g. carriage of livestock and perishable goods.

• the ventilation flow rate will be:

Basic aircraft for A319-100 and A320-200 and A321200 Cargo holds are class C. Dual loop smoke detection and a fire extinguishing systems are installed.

A320: 82 l/s (173 cu ft/min) on ground and 97 l/s (205 cu ft/min) in flight.

Description for A319-100 and A320-200 and A321200 Underfloor air drawn from the cabin enters the forward cargo hold via an isolation valve and side inlets located at lower LH side of the hold: • the air is extracted from the forward cargo hold through a vent and discharged directly overboard via an isolation valve and venturi • on ground the air is extracted by means of an electrical fan, installed upstream from the isolation valve, which continues to operate until a differential pressure of 1 psi is reached • a cargo ventilation controller is installed in the avionics compartment which provides control and position indication of the isolation valves

In the event of smoke warning, the smoke detection system automatically closes both isolation valves and switches off the extraction fan (if operating).

Issue 6 Revision 1, January 2012

A319: 82 l/s (173 cu ft/min) on ground and 100 l/s (212 cu ft/min) in flight.

A321: 118 l/s (250 cu ft/min) on the ground and 165 l/s (350 cu ft/min) in flight.

EPAC selection mode Individual

21.28.201

Page 110

[ 21-18]

Air conditioning 21

A320 Family

Figure 21-5 - Forward cargo hold ventilation system Aircraft skin Venturi

p Switch

Isolation valve

TEMP:

COND

ALTN MODE

FAN CKPT 20

Extraction fan

AFT 23

FWD 22

44

40

C

H

C

C

FAN

38 H

C

H HOT AIR

Specific to the A321 FWD

Smoke detectors CARGO VENT FWD ISOL VALVE FAULT OFF

Cabin ambient air

Isolation valve

Cargo ventilation controller

Issue 6 Revision 1, January 2012

21.28.201

Page 111

[ 21-19]

A320 Family

21 Air conditioning Table 21-5 - Technical solutions description TDU

Title (Remarks)

Appl.

Weight (kg) MWE/OWE/APL

01

Installation of ventilation system for forward cargo hold

Issue 6 Revision 1, January 2012

A319-100 A320-200 A321-200

Equipment reference

Equipment supplier

Equipment PN

QTY

STS

17.0/17.0/-17.0 20.0/20.0/-20.0 24.0/24.0/-24.0

21.28.201

Page 112

[ 21-20]

Air conditioning 21

A320 Family

Intentionally left blank

Issue 6 Revision 1, January 2012

21.28.201

Page 113

[ 21-21]

A320 Family

21 Air conditioning

21.28.210 - Installation of ventilation system for complete aft cargo hold Objective To provide a ventilation system for the aft cargo hold, to enable increased utilization of the hold, e.g. carriage of livestock and perishable goods. Basic aircraft Cargo holds are class C. System provision is installed. Dual loop smoke detection and fire extinguishing systems are installed.

In the event of smoke warning, the smoke detection system automatically closes both isolation valves and switches off the extraction fan (if operating). EPAC selection mode Individual

Description Underfloor air drawn from the cabin enters the aft cargo hold via an isolation valve and side inlets along the lower LH side of the forward part of the hold. The air is extracted from the aft cargo hold through vents in the rear wall near the ceiling and discharged via an extraction fan and an isolation valve toward the outflow valve and then overboard. The electrical air extraction fan operates on ground and in flight. The ventilation flow rate on ground and in flight is 150 l/ s (318 cu ft/min).

Issue 6 Revision 1, January 2012

21.28.210

Page 114

[ 21-22]

Air conditioning 21

A320 Family

Figure 21-6 - Aft cargo hold ventilation system

Towards outflow valve Specific to the A321 Isolation valve

TEMP:

COND

ALTN MODE

FAN CKPT 20 44

Extraction fan

C

H

FWD 22 40 C

C

FAN AFT 23 38

H

C

H HOT AIR

AFT

Smoke detectors

Cabin ambient air

CARGO VENT AFT ISOL VALVE FAULT OFF

Isolation valve Cargo ventilation controller

Issue 6 Revision 1, January 2012

21.28.210

Page 115

[ 21-23]

A320 Family

21 Air conditioning Table 21-6 - Technical solutions description TDU

Title (Remarks)

Appl.

Weight (kg) MWE/OWE/APL

01

Installation of ventilation system for complete aft cargo hold

A318-100 A319-100 A320-200 A321-200

16.0/16.0/-16.0 18.0/18.0/-18.0 21.0/21.0/-21.0 26.0/26.0/-26.0

02

Installation of ventilation system for complete aft cargo hold associated with gaseous oxygen system

A319-100

19.0/19.0/-19.0

Equipment reference

Equipment supplier

Equipment PN

QTY

STS

Requires prior acceptance of CN35.20.114/01 Extended duration passenger gaseous oxygen system.

Issue 6 Revision 1, January 2012

21.28.210

Page 116

[ 21-24]

Air conditioning 21

A320 Family

Intentionally left blank

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21.28.210

Page 117

[ 21-25]

A320 Family

21 Air conditioning 21.41.100 - Installation of front air outlets at flight crew foot level Objective To propose an alternate solution to the basic flight crew foot air outlets locations. Basic aircraft Conditioned air is fed into the cockpit at the following points: • through lateral air outlets with adjustable airflow • through individual air outlets with adjustable airflow and stream direction • through outlets at pilot foot level • through ceiling outlets with adjustable airflow. Description The modification consists in relocating the cockpit flight crew foot air outlets. The conditioned air is no longer fed underneath the seats from an installation in the side panels, but is blown in from behind the foot pedals. EPAC selection mode Individual

Issue 6 Revision 1, January 2012

21.41.100

Page 118

[ 21-26]

Air conditioning 21

A320 Family

Table 21-7 - Technical solutions description TDU

Title (Remarks)

Appl.

Weight (kg) MWE/OWE/APL

02

Air conditioning - Cockpit air heating - Introduce front blowers at flight crew foot level

Issue 6 Revision 1, January 2012

A318-100 A319-100 A320-200 A321-200

Equipment reference

Equipment supplier

Equipment PN

QTY

STS

1.5/1.5/-1.5 1.5/1.5/-1.5 1.5/1.5/-1.5 1.5/1.5/-1.5

21.41.100

Page 119

[ 21-27]

A320 Family

21 Air conditioning 21.43.201 - Installation of heating system for forward cargo hold Objective for A319-100 and A320-200 and A321-200 To provide a variable heating system for the forward cargo hold to enable increased utilization of the hold, e.g. carriage of livestock. Basic aircraft for A319-100 and A320-200 and A321200 Cargo holds are class C. Dual loop smoke detection and fire extinguishing systems are installed. Description for A319-100 and A320-200 and A321200 With ventilation of the forward cargo hold installed (optional), the modification consists of heating the air by hot trim air bled from the hot air manifold. Temperature control is achieved using inputs from the temperature selector, the cargo hold air temperature sensor and the supply duct temperature sensor. A cargo heating controller is installed in the avionics compartment providing control and indication of the trim air valve, trim air pressure regulating valve and cargo compartment temperature.

Issue 6 Revision 1, January 2012

The forward cargo compartment heating system will permit to select a stabilized lower mean temperature limit between 5 DEG C (41 DEG F) and 26 DEG C (79 DEG F) with an accuracy of plus or minus 2 DEG C (3.6 DEG F) at the reference point. In case the cargo door is not fully closed, the hot air supply is shut off by closing the trim air valve automatically. In the event of smoke warning, the smoke detection system automatically closes both isolation valves, switches off the extraction fan and closes the trim air valve. Note for A319-100 and A320-200 and A321-200 Requires prior selection of CN21.28.201/01 Installation of ventilation system for forward cargo hold. EPAC selection mode Individual

21.43.201

Page 120

[ 21-28]

Air conditioning 21

A320 Family

Figure 21-7 - Forward cargo hold heating system Aircraft skin Venturi

p Switch

Isolation valve

TEMP:

COND

ALTN MODE

FAN

Compartment temperature sensor

CKPT 20

Extraction fan

FWD 22

44

AFT 23

40

C

H

C

C

FAN

38 H

C

H HOT AIR

FWD 18 48

Specific to the A321

Cargo ventilation controller

Smoke detectors

C

H

CARGO HEAT FWD ISOL VALVE FAULT

Cabin ambient air

Control panels (cockpit OVHD PNL) MID CABIN

HOT AIR

Duct temp. sensor

FAULT OFF COLD

OFF

HOT PACK 2

PACK 2 FAULT OFF

A I R C O N D

Issue 6 Revision 1, January 2012

FWD

Hot air Isolation valve Trim air valve

Cargo heat controller

21.43.201

COLD

HOT

Page 121

[ 21-29]

A320 Family

21 Air conditioning Table 21-8 - Technical solutions description TDU

Title (Remarks)

Appl.

Weight (kg) MWE/OWE/APL

01

Installation of heating system for forward cargo hold

Issue 6 Revision 1, January 2012

A319-100 A320-200 A321-200

Equipment reference

Equipment supplier

Equipment PN

QTY

STS

10.0/10.0/-10.0 13.0/13.0/-13.0 17.0/17.0/-17.0

21.43.201

Page 122

[ 21-30]

Air conditioning 21

A320 Family

Intentionally left blank

Issue 6 Revision 1, January 2012

21.43.201

Page 123

[ 21-31]

A320 Family

21 Air conditioning

21.43.204 - Installation of heating system for complete aft cargo hold Objective To provide a variable heating system for the aft cargo hold, to enable increased utilization of the hold, e.g. carriage of livestock. Basic aircraft Cargo holds are class C. Dual loop smoke detection and fire extinguishing systems are installed. Description With ventilation of the aft cargo compartment installed (optional), the modification consists of heating the air by hot trim air bleed directly from the APU bleed air duct. The hot air is controlled by a trim air valve and an additional trim air pressure regulating valve. A cargo heating controller is installed in the avionics compartment providing control and indication of the trim air valve, trim air pressure regulating valve and cargo compartment temperature. Temperature control is achieved using inputs from the temperature selector, the cargo hold air temperature sensor and the and the supply duct temperature sensor.

Issue 6 Revision 1, January 2012

The aft cargo compartment heating system will permit to select a stabilized lower mean temperature limit between 5 DEG C (41 DEG F) and 26 DEG C (79 DEG F) with an accuracy of plus minus 2 DEG C (3.6 DEG F) at the reference point. In case the cargo door is not fully closed, the hot air supply is shut off by closing the trim air valve automatically. In the event of smoke warning, the smoke detection system automatically closes both isolation valves, switches off the extraction fan and closes the trim air valve. Note Requires prior selection of CN21.28.210/01 Installation of ventilation system for complete aft cargo hold. EPAC selection mode Individual

21.43.204

Page 124

[ 21-32]

Air conditioning 21

A320 Family

Figure 21-8 - Aft cargo hold heating system Towards outflow valve Specific to the A321 Isolation valve Extraction fan

ECAM Page TEMP:

COND

ALTN MODE

FAN CKPT 20 44 C

H

FWD 22 40 C

C

FAN AFT 23 38

H

C

H HOT AIR

Smoke detectors AFT 18 48

Compartment temperature sensor C

Cabin ambient air

Pressure regulating valve

Duct temp. sensor

From APU bleed air duct

H

HOT AIR

Cargo ventilation controller Control panel (Cockpit OVHD PNL)

Isolation valve CARGO HEAT

Trim air valve

AFT ISOL VALVE

FAULT

FAULT

OFF

OFF

AFT

Cargo heat controller

Issue 6 Revision 1, January 2012

HOT AIR

21.43.204

COLD

Page 125

HOT

[ 21-33]

A320 Family

21 Air conditioning Table 21-9 - Technical solutions description TDU

Title (Remarks)

Appl.

Weight (kg) MWE/OWE/APL

01

Installation of heating system for complete aft cargo hold

A318-100 A319-100 A320-200 A321-200

14.0/14.0/-14.0 14.0/14.0/-14.0 17.0/17.0/-17.0 21.0/21.0/-21.0

02

Installation of heating system for complete aft cargo hold associated with gaseous oxygen system

A319-100

16.0/16.0/-16.0

Equipment reference

Equipment supplier

Equipment PN

QTY

STS

Requires prior acceptance of CN35.20.114/01 Extended duration gaseous passenger oxygen system.

Issue 6 Revision 1, January 2012

21.43.204

Page 126

[ 21-34]

Air conditioning 21

A320 Family

Intentionally left blank

Issue 6 Revision 1, January 2012

21.43.204

Page 127

[ 21-35]

A320 Family

21 Air conditioning 21.70.109 - Installation of ozone catalytic converters Objective To protect the passengers from high ozone concentration.

EPAC selection mode Individual

Basic aircraft Space and structural provisions are provided by design of the air generation components underneath the centre wing box. Description Two ozone converters are installed in the bleed-air supply line upstream of the pack flow control valves. In addition to the current ozone catalytic converter, a combined VOC/ozone catalytic converter is proposed. The benefit of the latter is the reduction of odors in the cabin due to fuel vapor and engine exhaust gas ingestion into the bleed system while on ground and taxiing. This change requires the removal of existing bleed air supply ducts between frames 35-37 underneath centre wing box.

Issue 6 Revision 1, January 2012

21.70.109

Page 128

[ 21-36]

Air conditioning 21

A320 Family

Figure 21-9 - Ozone converters location Engine bleed Ozone converters

To pack 2

Cross bleed valve

Flow control valves

To pack 1

Issue 6 Revision 1, January 2012

21.70.109

Page 129

[ 21-37]

A320 Family

21 Air conditioning Table 21-10 - Technical solutions description TDU

Title (Remarks)

Appl.

Weight (kg) MWE/OWE/APL

Equipment reference

Equipment supplier

Equipment PN

QTY

STS

07

Installation of ozone catalytic converters - ENGELHARDT CORPORATION, PN 20499006

A318-100 A319-100 A320-200 A321-200

19.7/19.7/-19.7 19.7/19.7/-19.7 19.7/19.7/-19.7 19.7/19.7/-19.7

Catalytic ozone converter

ENGELHARDT

20499006

2

SFE

08

Installation of combined VOC/ ozone catalytic converters ENGELHARDT CORPORATION, PN 44018005

A318-100 A319-100 A320-200 A321-200

25.7/25.7/-25.7 25.7/25.7/-25.7 25.7/25.7/-25.7 25.7/25.7/-25.7

Catalytic VOC/ ozone converter

ENGELHARDT

44018005

2

SFE

VOC: Volatile Organic Compounds.

Issue 6 Revision 1, January 2012

21.70.109

Page 130

[ 21-38]

A320 Family

Auto flight 22

Reference

Title

22.00.104

Automatic landing capability

22.70.100

Flight Management (FM) kits alternate equipment

22.81.143

Inhibition of the expedite pushbutton

22.82.103

Installation of third Multipurpose Control and Display Unit (MCDU)

Issue 6 Revision 1, January 2012

Page 131

[ 22-1]

A320 Family

22 Auto flight 22.00.104 - Automatic landing capability Objective for A320-200 To perform automatic landings under conditions that were not part of the aircraft initial autoland certification. Basic aircraft for A320-200 Depending on aircraft and engine types, the autoland function has been certified for a standard domain of operations in terms of altitude, temperature... Description for A320-200 The aircraft will be capable to perform automatic landings in an extended domain of operations. EPAC selection mode Individual

Issue 6 Revision 1, January 2012

22.00.104

Page 132

[ 22-2]

Auto flight 22

A320 Family Table 22-1 - Technical solutions description TDU

Title (Remarks)

Appl.

Weight (kg) MWE/OWE/APL

02

Automatic landing capability extension for CFM engines (9200 ft)

A320-200

Negl./Negl./Negl.

A320-200

Negl./Negl./Negl.

Equipment reference

Equipment supplier

Equipment PN

QTY

STS

A320-215 and A320-216 : Subject to certification

06

Automatic landing capability extension for IAE engines (9200 ft)

Issue 6 Revision 1, January 2012

22.00.104

Page 133

[ 22-3]

A320 Family

22 Auto flight 22.70.100 - Flight Management (FM) kits alternate equipment Objective To offer a choice of supplier for FM kits and Multipurpose Control and Display Unit (MCDU). Basic aircraft Two FM kits are fitted in each FMGC (2 per aircraft) and two MCDUs are fitted in the cockpit center pedestal. Description This option installs alternate FM kits (2 cards per FMGC) and two MCDUs, instead of the basic equipment. The equipment is mechanically, electrically interchangeable and functionally equivalent with the basic one. However mixing equipment from different suppliers is not possible. EPAC selection mode Individual

Issue 6 Revision 1, January 2012

22.70.100

Page 134

[ 22-4]

Auto flight 22

A320 Family Figure 22-1 - FM kits alternate equipment

FMS cards

DIR F-PLN

DIR

PROG

PERF

INIT

DATA

F-PLN

RAD NAV

FUEL PRED

SEC F-PLN

ATC COMM

AIR PORT PROG PERF RAD NAV

FUEL PRED

AIR PORT

1

1

2

4

5

7

8 0

FMGC

Issue 6 Revision 1, January 2012

FMGC

A2

4

F5

7 3

K8

INIT

DATA

A

B

SEC F-PLN

ATC COMM

CBRT D

F

MCDU DIM G I MENU H

J

LD

O

G 6 9 L

M E

N

P H

QI

RJ

U M

V N

W O

X

Y

/ S

SP

OVFY

CLR

6

P0

Q-

Z R

9

U

V

W

X

Y

Z

/

SP

OVFY

CLR

-

DIM

E

K C

B 3

+

+

BRT MCDU MENU

T

S

T

MCDU

22.70.100

Page 135

[ 22-5]

A320 Family

22 Auto flight Table 22-2 - Technical solutions description TDU

Title (Remarks)

Appl.

Weight (kg) MWE/OWE/APL

Std

Std

Std

38

FM kits/MCDUs basic equipment - THALES AVIONICS/ SMITHS associated with PW engines

FM kits (Rel. 1A - FMGC H2I11) / MCDU basic equip - HONEYWELL assoc. with IAE engines

FM kits (Rel. 1A - FMGC H2C12) / MCDU basic equip HONEYWELL assoc. with CFM engines

FM kits (Rel. 1A - FMGC H2I11) / MCDU altern. equip - HONEYWELL assoc. with PW engines

Issue 6 Revision 1, January 2012

A318-100

A319-100 A320-200 A321-200

A318-100 A319-100 A320-200 A321-200

A318-100

Negl./Negl./Negl.

Equipment reference

Equipment supplier

Equipment PN

QTY

STS

Flight Management Guidance Computer (FMGC)

THALES AVIONICS S.A. / SMITHS

C13043BA03

2

SFE

Multipurpose Control and Display Unit (MCDU)

THALES AVIONICS SA

C19266AA01

2

SFE

Flight Management Guidance Computer (FMGC)

THALES AVIONICS S.A. / HONEYWELL

C13042BA03

2

SFE

Multipurpose Control and Display Unit (MCDU)

HONEYWELL INC.

4089740-961

2

SFE

Flight Management Guidance Computer (FMGC)

THALES AVIONICS S.A. / HONEYWELL

C13042AA04

2

SFE

Multipurpose Control and Display Unit (MCDU)

HONEYWELL INC.

4089740-961

2

SFE

Flight Management Guidance Computer (FMGC)

THALES AVIONICS S.A. / HONEYWELL

C13042BA03

2

SFE

FMS operational software

HONEYWELL INC.

PS4087600903

2

SFE

Multipurpose Control and Display Unit (MCDU)

HONEYWELL INC.

4089740-961

2

SFE

22.70.100

Page 136

[ 22-6]

Auto flight 22

A320 Family TDU

Title (Remarks)

Appl.

Weight (kg) MWE/OWE/APL

48

49

50

FM kits (Rel. 1A - FMGC S6I11) / MCDU altern. equip - THALES AVIONICS/SMITH assoc. with IAE engines

FM kits (Rel. 1A - FMGC H2C13) / MCDU altern. equip HONEYWELL assoc. with CFM engines

FM kits (Rel. 1A - FMGC S6C13) / MCDU altern. equip - THALES AVIONICS/SMITH assoc. with CFM engines

Issue 6 Revision 1, January 2012

A318-100 A319-100 A320-200 A321-200

A318-100 A319-100 A320-200 A321-200

A318-100 A319-100 A320-200 A321-200

Negl./Negl./Negl. Negl./Negl./Negl. Negl./Negl./Negl. Negl./Negl./Negl.

Negl./Negl./Negl. Negl./Negl./Negl. Negl./Negl./Negl. Negl./Negl./Negl.

Negl./Negl./Negl. Negl./Negl./Negl. Negl./Negl./Negl. Negl./Negl./Negl.

Equipment reference

Equipment supplier

Equipment PN

QTY

STS

Flight Management Guidance Computer (FMGC)

THALES AVIONICS S.A. / SMITHS

C13043BA04

2

SFE

FMS operational software

THALES AVIONICS S.A. / SMITHS

G2604AAG01

2

SFE

Multipurpose Control and Display Unit (MCDU)

THALES AVIONICS SA

C19266EA01

2

SFE

Flight Management Guidance Computer (FMGC)

THALES AVIONICS S.A. / HONEYWELL

C13042AA05

2

SFE

FMS operational software

HONEYWELL INC.

PS4087700903

2

SFE

Multipurpose Control and Display Unit (MCDU)

HONEYWELL INC.

4089740-961

2

SFE

Flight Management Guidance Computer (FMGC)

THALES AVIONICS S.A. / SMITHS

C13043AA05

2

SFE

FMS operational software

THALES AVIONICS S.A. / SMITHS

G2604AAG01

2

SFE

Multipurpose Control and Display Unit (MCDU)

THALES AVIONICS SA

C19266EA01

2

SFE

22.70.100

Page 137

[ 22-7]

A320 Family

22 Auto flight 22.81.143 - Inhibition of the expedite pushbutton Objective To inhibit the expedite pushbutton to have functional commonality between the A330/340 and the A318/319/ 320/321 FCUs. Basic aircraft Expedite mode is used in climb or descent to reach the desired altitude with the maximum gradient. The function is manually activated by depressing the expedite pushbutton on the FCU: • expedite climb mode is engaged if the selected altitude is higher than the aircraft altitude • expedite descent mode is engaged if the selected altitude is lower than the aircraft altitude. Disengagement can be done manually by engagement of another vertical mode or automatically with ALT mode engagement. Description Expedite pushbutton is replaced by a blank pushbutton (fixed) on the FCU. EPAC selection mode Individual

Issue 6 Revision 1, January 2012

22.81.143

Page 138

[ 22-8]

Auto flight 22

A320 Family Figure 22-2 - Expedite pushbutton Pre-mod SPD CSTR

WPT

VOR.D

NDB

HDG

LAT

ALT

LVL/CH

V/S

HDG V/S

ARPT

ARPT

NDB

VOR.D

WPT

CSTR

BARO

BARO ROSE NAV VOR

IN HG

HPA

LS

160 2

VOR

ADF

OFF

HDG TRK

80

20

1 ADF

FD

ARC

PLAN 10

LS

PULL STD

40

V/S FPA

100

UP

1000

SPD MACH

320

AP 2

160

10

ADF LOC

A/THR

APPR

EXPED

VOR

ARC

PULL STD

2 ADF

OFF

HPA

PLAN IN HG

LS

320

1

DN

VOR OFF

80

20

PUSH TO LEVEL OFF

METRIC ALT AP 1

ROSE NAV VOR

40

VOR LS

OFF

FD

Post-mod SPD

HDG

LAT

ALT

LVL/CH

V/S

HDG V/S

HDG TRK

V/S FPA

100

SPD MACH

1000

UP PUSH TO LEVEL OFF

METRIC ALT AP 1

AP 2 DN

LOC

A/THR

EXPED

APPR

Dummy expedite pushbutton

Issue 6 Revision 1, January 2012

22.81.143

Page 139

[ 22-9]

A320 Family

22 Auto flight Table 22-3 - Technical solutions description TDU

Title (Remarks)

Appl.

Weight (kg) MWE/OWE/APL

01

Inhibition of the expedite pushbutton

Issue 6 Revision 1, January 2012

A318-100 A319-100 A320-200 A321-200

Equipment reference

Equipment supplier

Equipment PN

QTY

STS

Negl./Negl./Negl. Negl./Negl./Negl. Negl./Negl./Negl. Negl./Negl./Negl.

22.81.143

Page 140

[ 22-10]

Auto flight 22

A320 Family

Intentionally left blank

Issue 6 Revision 1, January 2012

22.81.143

Page 141

[ 22-11]

A320 Family

22 Auto flight

22.82.103 - Installation of third Multipurpose Control and Display Unit (MCDU) Objective To ease maintenance tasks on the ground.

EPAC selection mode Individual

Basic aircraft Two MCDUs are installed on the pedestal, one on each side. MCDUs are connected to the FMS, CFDS, AIDS DMU and ATSU. Description The third MCDU is installed on the captain's side console and connected to the CFDS. It is also connected to the AIDS and ACARS systems. In such case the first MCDU is connected only to the FMS and ATSU. The modification consists of: • side console adaptation • installation of the third MCDU. Note • the third MCDU is used on ground only • supplier choice must be consistent with item CN22.70.100 - FMS kits alternate equipment, or CN22.82.102 - MCDU alternate equipment, if applicable.

Issue 6 Revision 1, January 2012

22.82.103

Page 142

[ 22-12]

Auto flight 22

A320 Family Figure 22-3 - MCDU installation

MCDU (basic)

BRT DIR

PROG

PERF

INIT

DATA

F-PLN

RAD NAV

FUEL PRED

SEC F-PLN

ATC COMM

OFF MCDU MENU

AIR PORT

F A I L

F M

1

2

B

C

D

E

F

G

H

I

J

K

L

M

N

O

P

Q

R

S

T

U

V

W

X

Y

SP

OVFY

CLR

3

4

5

6

7

8

9

0

A

+

-

Z

/

M C D U M E N U

Optional MCDU

Printer (basic)

MCDU

Issue 6 Revision 1, January 2012

22.82.103

Page 143

[ 22-13]

A320 Family

22 Auto flight Table 22-4 - Technical solutions description TDU

Title (Remarks)

Appl.

Weight (kg) MWE/OWE/APL

06

Installation of third MCDU associated with FMS - THALES V800 Requires prior selection of a THALES AVIONICS/SMITHS FMS.

Issue 6 Revision 1, January 2012

A318-100 A319-100 A320-200 A321-200

10.0/10.0/-10.0 10.0/10.0/-10.0 10.0/10.0/-10.0 10.0/10.0/-10.0

Equipment reference

Multipurpose Control and Display Unit (MCDU)

22.82.103

Equipment supplier

THALES AVIONICS SA

Equipment PN

C19266EA01

QTY

1

Page 144

STS

SFE

[ 22-14]

A320 Family

Communications 23

Reference

Title

23.00.132

Installation (based on basic common provision) of Emergency Locator Transmitter (ELT)

23.11.102

Full provision for single HF system

23.11.111

Full provision for dual HF system

23.11.116

Installation of single HF system (SFE)

23.11.131

Installation of single HF system and full provision for second one (SFE)

23.11.155

Installation of dual HF system (SFE)

23.11.167

Additional wiring for HF Data Link (HFDL) function

23.11.169

Activation of HF Data Link (HFDL) function

23.12.130

VHF Data Radio (VDR) alternate equipment

23.13.100

Installation of alternate Radio Management Panel (RMP)

23.13.101

Installation of third Radio Management Panel (RMP)

23.13.105

Activation of RMP std 4 frequency load function

23.28.170

Installation of AERO H+/SBB SATCOM cockpit voice interface

23.28.210

Installation of SATCOM AERO H+ SRT 2100B system

23.28.211

Installation of SwiftBroadband (SBB) SATCOM system

23.50.110

Installation of additional Audio Control Panel (ACP) and jack panel

Issue 6 Revision 1, January 2012

Page 145

[ 23-1]

23 Communications

A320 Family

Reference

Title

23.50.135

Installation of headset for fourth occupant

23.50.138

Cockpit hand microphone alternate equipment

23.51.103

Installation of active noise canceling boomsets (SFE)

23.51.136

Boomsets alternate equipment

23.51.139

Boomsets alternate equipment with two jack plugs

23.70.110

Installation of a video monitoring system

23.71.103

Solid State Cockpit Voice Recorder (SSCVR) alternate equipment

23.71.110

Recorder Independent Power Supply (RIPS) - 28VDC power supply for CVR

23.71.120

System provision for CVR capable of data link recording

23.73.200

Installation of cockpit and cabin alert switches (Aircraft Security Project)

Issue 6 Revision 1, January 2012

Page 146

[ 23-2]

Communications 23

A320 Family

Intentionally left blank

Issue 6 Revision 1, January 2012

Page 147

[ 23-3]

A320 Family

23 Communications

23.00.132 - Installation (based on basic common provision) of Emergency Locator Transmitter (ELT) Objective To install ELT, in compliance with ED62, designed to improve search and rescue by automatically activating (through a G-switch), in the event of an emergency. Basic aircraft The following provision is installed allowing the installation of the automatic ELT: • one external antenna (for 121.5, 243, 406 MHz frequencies) on top of the rear part of the fuselage between frame C64 and C65 • ELT support located in the upper part of the fuselage, close to the antenna • a coaxial cable from the external antenna to the ELT support in the aft ceiling area • wiring from the ELT support to the cockpit allowing future installation of ELT remote control panel • wiring from the ELT remote control panel location to the ground electrical panel (ground horn).

Installation of a modified control panel near the ground horn. Note Certain interface wirings may be affected and some new ones may have to be installed once the ELT supplier is selected. In this configuration the ELT can be used as an Automatic Fixed ELT (ELT (AF)) only. Due to its installation, this ELT cannot be used to replace an ELT(s) as mentioned in EU-OPS1/AMC OPS 1.830(c). EPAC selection mode Individual

Description Installation of an ELT (BFE) capable of emitting a distress signal on the 121.5, 243.0 and 406.0 MHz international standard distress frequencies. Installation of a remote control panel in the cockpit.

Issue 6 Revision 1, January 2012

23.00.132

Page 148

[ 23-4]

Communications 23

A320 Family

Figure 23-1 - Automatic ELT installation C64 C66 C65

ELT antenna

C70

C87

ELT support

FW

D

ET

ES

/R

T

EL

ST

TE

ON

A R M E D

ELT remote control panel

Typical installation ELT remote control panel

FLT INT

EXT PWR

108 VU

NOT IN USE

AVAIL

CKPT CALL

ADIRU & APU FIRE AVNCS VENT R

ELT

LIGHT TEST CKPT CALL

RESET APU SHUT OFF

Ground horn Ground electrical power panel

Issue 6 Revision 1, January 2012

23.00.132

Page 149

[ 23-5]

A320 Family

23 Communications Table 23-1 - Technical solutions description TDU

Title (Remarks)

Appl.

Weight (kg) MWE/OWE/APL

31

39

44

Automatic programmable ELT (406AF) associated with remote control panel in cockpit - ELTA (BFE)

Automatic programmable ELT with prog. dongle with remote control panel (RC800) in cockpit - THALES

Auto. progr. ELT (406 AFN) assoc. with remote control panel in cockpit w/o AIM HONEYWELL (BFE)

Issue 6 Revision 1, January 2012

A318-100 A319-100 A320-200 A321-200

A318-100 A319-100 A320-200 A321-200

A318-100 A319-100 A320-200 A321-200

3.6/3.6/-3.6 3.6/3.6/-3.6 3.6/3.6/-3.6 3.6/3.6/-3.6

3.0/3.0/-3.0 3.0/3.0/-3.0 3.0/3.0/-3.0 3.0/3.0/-3.0

3.5/3.5/-3.5 3.5/3.5/-3.5 3.5/3.5/-3.5 3.5/3.5/-3.5

Equipment reference

Equipment supplier

Equipment PN

QTY

STS

Back up antenna

ELTA

02N64070

1

BFE

Emergency Locator Transmitter (ELT)

ELTA

01N65900

1

BFE

Remote control panel

ELTA

93N6035

1

BFE

Emergency Locator Transmitter (ELT)

THALES AVIONICS SA

S1821502-02

1

BFE

Emergency Locator Transmitter (ELT) bracket

THALES AVIONICS SA

S1820511-01

1

BFE

Programming dongle

THALES AVIONICS SA

S1820514-04

1

BFE

Remote control panel

THALES AVIONICS SA

S1820513-15

1

BFE

Emergency Locator Transmitter (ELT)

HONEYWELL ASCA INC

1152682-3

1

BFE

Remote control panel

HONEYWELL ASCA INC

1153008-1

1

BFE

23.00.132

Page 150

[ 23-6]

Communications 23

A320 Family TDU

Title (Remarks)

Appl.

Weight (kg) MWE/OWE/APL

45

46

Auto. progr. ELT (406 AFN) assoc. with remote control panel in cockpit with AIM HONEYWELL (BFE)

Auto. progr. ELT (406 AFN) assoc. with remote control panel in cockpit with NAIM HONEYWELL (BFE) Capable to transmit the last aircraft position (lat, long)

Issue 6 Revision 1, January 2012

A318-100 A319-100 A320-200 A321-200

A318-100 A319-100 A320-200 A321-200

3.6/3.6/-3.6 3.6/3.6/-3.6 3.6/3.6/-3.6 3.6/3.6/-3.6

3.6/3.6/-3.6 3.6/3.6/-3.6 3.6/3.6/-3.6 3.6/3.6/-3.6

Equipment reference

Equipment supplier

Equipment PN

QTY

STS

Aircraft Identification Module (AIM)

HONEYWELL ASCA INC

1152780-1

1

BFE

Emergency Locator Transmitter (ELT)

HONEYWELL ASCA INC

1152682-3

1

BFE

Remote control panel

HONEYWELL ASCA INC

1153008-1

1

BFE

Aircraft Identification Module + NAV (NAIM)

HONEYWELL ASCA INC

1153396-1

1

BFE

Emergency Locator Transmitter (ELT)

HONEYWELL ASCA INC

1152682-3

1

BFE

Remote control panel

HONEYWELL ASCA INC

1153008-1

1

BFE

23.00.132

Page 151

[ 23-7]

A320 Family

23 Communications 23.11.102 - Full provision for single HF system Objective To make full provision for single HF system. Basic aircraft • space provision is made for dual HF communication transceivers (ARINC 719). • structural provision is made for single HF antenna and coupler. Description The modification consists of installing: • one transceiver mount in the avionics compartment • one HF antenna in the fin leading edge • one antenna coupler mount in the ceiling of the rear part of the aircraft • the antenna feeder and all the necessary wiring. EPAC selection mode Individual

Issue 6 Revision 1, January 2012

23.11.102

Page 152

[ 23-8]

Communications 23

A320 Family

Figure 23-2 - Full provision for single HF system

RMP3

RMP1

RMP2 Antenna

VDR1

VDR2

VDR3

HF1 Full provision

Issue 6 Revision 1, January 2012

One transceiver mount in avionics compartment

One antenna coupler mount

HF2

23.11.102

Page 153

[ 23-9]

A320 Family

23 Communications Table 23-2 - Technical solutions description TDU

Title (Remarks)

Appl.

Weight (kg) MWE/OWE/APL

01

Full provision for single HF system (ARINC 719)

Issue 6 Revision 1, January 2012

A318-100 A319-100 A320-200 A321-200

16.0/16.0/-16.0 16.5/16.5/-16.5 17.0/17.0/-17.0 19.0/19.0/-19.0

Equipment reference

HF antenna

23.11.102

Equipment supplier

AIRBUS

Equipment PN

TBD

QTY

1

Page 154

STS

SFE

[ 23-10]

Communications 23

A320 Family

Intentionally left blank

Issue 6 Revision 1, January 2012

23.11.102

Page 155

[ 23-11]

A320 Family

23 Communications 23.11.111 - Full provision for dual HF system Objective To make full provision for dual HF system. Basic aircraft • space provision is made for dual HF communication transceivers (ARINC 719) • structural provision is made for single HF antenna and coupler. Description The modification consists of installing: • two transceiver mounts in the avionics compartment • two antenna coupler mounts in the ceiling of the rear part of the aircraft • two antenna feeders and all necessary wiring • one HF antenna in the fin leading edge. Note The same HF antenna shall be used for both HF systems. EPAC selection mode Individual

Issue 6 Revision 1, January 2012

23.11.111

Page 156

[ 23-12]

Communications 23

A320 Family

Figure 23-3 - Full provision for dual HF system

RMP3

RMP1

RMP2 Antenna

VDR1

VDR2

VDR3

Two transceiver mounts in avionics compartment

HF1

HF2

Full provision

Full provision

Issue 6 Revision 1, January 2012

23.11.111

Two antenna coupler mounts

Page 157

[ 23-13]

A320 Family

23 Communications Table 23-3 - Technical solutions description TDU

Title (Remarks)

Appl.

Weight (kg) MWE/OWE/APL

01

Full provision for dual HF system (ARINC 719)

Issue 6 Revision 1, January 2012

A318-100 A319-100 A320-200 A321-200

29.0/29.0/-29.0 30.0/30.0/-30.0 31.0/31.0/-31.0 35.0/35.0/-35.0

Equipment reference

HF antenna

23.11.111

Equipment supplier

AIRBUS

Equipment PN

TBD

QTY

1

Page 158

STS

SFE

[ 23-14]

Communications 23

A320 Family

Intentionally left blank

Issue 6 Revision 1, January 2012

23.11.111

Page 159

[ 23-15]

A320 Family

23 Communications 23.11.116 - Installation of single HF system (SFE) Objective To install one HF system for voice communication in areas outside VHF coverage. Basic aircraft • space provision is made for dual HF communication transceivers (ARINC 719) • structural provision is made for single HF antenna and coupler. Description The modification consists of: • installing one HF transceiver and its associated mount in the avionics compartment • installing one HF antenna in the fin leading edge • installing one antenna coupler and its associated mount in the ceiling of the rear part of the aircraft • pin-programming the AMU. Note The installation of the optional third Radio Management Panel (RMP) is recommended. EPAC selection mode Individual

Issue 6 Revision 1, January 2012

23.11.116

Page 160

[ 23-16]

Communications 23

A320 Family

Table 23-4 - Technical solutions description TDU

Title (Remarks)

Appl.

Weight (kg) MWE/OWE/APL

02

05

Installation of single HF system (data link capable) - ROCKWELL COLLINS 900 (SFE)

Installation of single HF system (data link capable) - HONEYWELL (SFE)

Issue 6 Revision 1, January 2012

A318-100 A319-100 A320-200 A321-200

A318-100 A319-100 A320-200 A321-200

41.0/41.0/-41.0 41.0/41.0/-41.0 41.0/41.0/-41.0 41.0/41.0/-41.0

41.0/41.0/-41.0 41.0/41.0/-41.0 41.0/41.0/-41.0 41.0/41.0/-41.0

Equipment reference

Equipment supplier

HF antenna

AIRBUS

HFDR antenna coupler

Equipment PN

STS

1

SFE

ROCKWELL COL- 822-0987-003 LINS

1

SFE

HFDR transceiver

ROCKWELL COL- 822-0990-003 LINS

1

SFE

HF antenna

AIRBUS

TBD

1

SFE

HFDR antenna coupler

HONEYWELL INC. REDMOND, OLATHE

964-0453-001

1

SFE

HFDR transceiver

HONEYWELL INC. REDMOND, OLATHE

964-0452-052

1

SFE

23.11.116

TBD

QTY

Page 161

[ 23-17]

A320 Family

23 Communications

23.11.131 - Installation of single HF system and full provision for second one (SFE) Objective To install single HF system, with full provision for a second one. Basic aircraft • space provision is made for dual HF communication transceivers (ARINC 719) • structural provision is made for single HF antenna and coupler. Description The modification consists of: • installation of two HF transceiver mounts and one HF transceiver in the electronic rack • installation of one HF antenna (in the leading edge) • installation of two HF antenna coupler mounts and one HF antenna coupler • pin-programming of the Audio Management Unit (AMU). Note The installation of the optional third Radio Management Panel (RMP) is recommended. EPAC selection mode Individual

Issue 6 Revision 1, January 2012

23.11.131

Page 162

[ 23-18]

Communications 23

A320 Family

Figure 23-4 - Installation of single HF system and full provision for second one

RMP3

RMP1

RMP2 Antenna

VDR1

VDR2

VDR3

HF1

Issue 6 Revision 1, January 2012

One transceiver and two transceiver mounts in avionics compartment

One antenna coupler and two antenna coupler mounts

HF2 Full provision

23.11.131

Page 163

[ 23-19]

A320 Family

23 Communications Table 23-5 - Technical solutions description TDU

Title (Remarks)

Appl.

Weight (kg) MWE/OWE/APL

02

05

Inst. of single HF system (data link capable) & full prov for second one - ROCKWELL COLL. 900 (SFE)

Inst. of single HF system (data link capable) and full prov for second one - HONEYWELL (SFE)

Issue 6 Revision 1, January 2012

A318-100 A319-100 A320-200 A321-200

A318-100 A319-100 A320-200 A321-200

51.0/51.0/-51.0 52.0/52.0/-52.0 52.0/52.0/-52.0 56.0/56.0/-56.0

51.0/51.0/-51.0 52.0/52.0/-52.0 52.0/52.0/-52.0 56.0/56.0/-56.0

Equipment reference

Equipment supplier

HF antenna

AIRBUS

HFDR antenna coupler HFDR transceiver

Equipment PN

STS

1

SFE

ROCKWELL COL- 822-0987-003 LINS

1

SFE

ROCKWELL COL- 822-0990-003 LINS

1

SFE

TBD

1

SFE

HF antenna

TBD

QTY

HFDR antenna coupler

HONEYWELL INC. REDMOND, OLATHE

964-0453-001

1

SFE

HFDR transceiver

HONEYWELL INC. REDMOND, OLATHE

964-0452-052

1

SFE

23.11.131

Page 164

[ 23-20]

Communications 23

A320 Family

Intentionally left blank

Issue 6 Revision 1, January 2012

23.11.131

Page 165

[ 23-21]

A320 Family

23 Communications 23.11.155 - Installation of dual HF system (SFE) Objective To install a dual HF system for voice communication in areas outside VHF coverage. Basic aircraft • space provision is made for dual HF communication transceivers (ARINC 719) • structural provision is made for single HF antenna and coupler. Description The modification consists of: • installation of two HF transceivers with associated mounts in the avionics compartment • installation of one HF antenna in the fin leading edge • installation of two HF antenna couplers with associated mounts in the ceiling of the rear part of the aircraft • pin-programming of the AMU. Note The installation of the optional third Radio Management Panel (RMP) is recommended. EPAC selection mode Individual

Issue 6 Revision 1, January 2012

23.11.155

Page 166

[ 23-22]

Communications 23

A320 Family

Figure 23-5 - Installation of dual HF system

RMP3

RMP1

RMP2 Antenna

VDR1

VDR2

VDR3 Two transceivers and associated mounts in avionics compartment

HF1

Issue 6 Revision 1, January 2012

Two antenna couplers with associated mounts

HF2

23.11.155

Page 167

[ 23-23]

A320 Family

23 Communications Table 23-6 - Technical solutions description TDU

Title (Remarks)

Appl.

Weight (kg) MWE/OWE/APL

02

05

Installation of dual HF system (data link capable) - ROCKWELL COLLINS 900 (SFE)

Installation of dual HF system (data link capable) - HONEYWELL (SFE)

Issue 6 Revision 1, January 2012

A318-100 A319-100 A320-200 A321-200

A318-100 A319-100 A320-200 A321-200

72.0/72.0/-72.0 73.0/73.0/-73.0 73.0/73.0/-73.0 77.0/77.0/-77.0

72.0/72.0/-72.0 73.0/73.0/-73.0 73.0/73.0/-73.0 73.0/73.0/-73.0

Equipment reference

Equipment supplier

HF antenna

AIRBUS

HFDR antenna coupler HFDR transceiver

Equipment PN

STS

1

SFE

ROCKWELL COL- 822-0987-003 LINS

2

SFE

ROCKWELL COL- 822-0990-003 LINS

2

SFE

TBD

1

SFE

HF antenna

TBD

QTY

HFDR antenna coupler

HONEYWELL INC. REDMOND, OLATHE

964-0453-001

2

SFE

HFDR transceiver

HONEYWELL INC. REDMOND, OLATHE

964-0452-052

2

SFE

23.11.155

Page 168

[ 23-24]

Communications 23

A320 Family

Intentionally left blank

Issue 6 Revision 1, January 2012

23.11.155

Page 169

[ 23-25]

A320 Family

23 Communications 23.11.167 - Additional wiring for HF Data Link (HFDL) function Objective To allow installation of HFDR capable of data link mode. Basic aircraft None. Description Based on the existing HF system provision or installation, additional wiring provision is installed to make HFDR capable of data communication. HF1 (and HF1 only) system will be connected to the following systems: • ATSU (only one HFDR connected) • FWCs for ECAM message • RMPs for voice/data monitoring • CFDIU for the acquisition of pin programming of the HFDR.

HF VOICE functionality for customers for which HF usual VOICE operation is necessary, it is recommended to install a second HF or at least full provision for a second one. EPAC selection mode Individual

Note When HF Data Link (HFDL) function is activated, the RMP human-machine interface for HF1 is the same as VHF3 when ACARS or ATSU is installed, i.e. that one RMP window displays a VOICE frequency while the other displays "DATA". Therefore, ergonomics for use of the VOICE function is downgraded. In order to keep the Issue 6 Revision 1, January 2012

23.11.167

Page 170

[ 23-26]

Communications 23

A320 Family

Table 23-7 - Technical solutions description TDU

Title (Remarks)

Appl.

Weight (kg) MWE/OWE/APL

01

Additional wiring for single HFDL function Requires prior selection of provision or installation of a single or dual HF system.

Issue 6 Revision 1, January 2012

A318-100 A319-100 A320-200 A321-200

Equipment reference

Equipment supplier

Equipment PN

QTY

STS

1.0/1.0/-1.0 1.0/1.0/-1.0 1.0/1.0/-1.0 1.0/1.0/-1.0

23.11.167

Page 171

[ 23-27]

A320 Family

23 Communications 23.11.169 - Activation of HF Data Link (HFDL) function Objective To provide data link capability over HF Data Radio (HFDR).

EPAC selection mode Individual

Basic aircraft • provisions for HF system • an ATSU is installed providing ACARS function. Description The HFDL capability is activated. This requires prior installation of: • upgraded ATSU software capable of HFDL • upgraded HF transceivers and couplers to be data capable • wiring between the ATSU and the HF system. Note • in single HF configuration, when Data Link is activated, one RMP window displays a voice frequency and the other displays "DATA". Therefore ergonomics for use of the voice function is downgraded (crew workload + frequency memory lost) and consequently, it is recommended to install a second HFDR system for HF usual voice operation • single network provider: ARINC.

Issue 6 Revision 1, January 2012

23.11.169

Page 172

[ 23-28]

Communications 23

A320 Family

Table 23-8 - Technical solutions description TDU

Title (Remarks)

Appl.

Weight (kg) MWE/OWE/APL

01

Activation of HFDL function for AOC Requires prior acceptance of CN23.11.167/01- Additional wiring for HFDL function and installation of a single or dual HF system

Issue 6 Revision 1, January 2012

A318-100 A319-100 A320-200 A321-200

Equipment reference

Equipment supplier

Equipment PN

QTY

STS

0.0/0.0/0.0 0.0/0.0/0.0 0.0/0.0/0.0 0.0/0.0/0.0

23.11.169

Page 173

[ 23-29]

A320 Family

23 Communications 23.12.130 - VHF Data Radio (VDR) alternate equipment Objective To provide alternate vendors for VDR transceivers. Basic aircraft Three VDR systems are installed, generally in accordance with ARINC 716 and ARINC 750. Description This option allows to select alternate vendors for VDR transceivers. EPAC selection mode Individual

Issue 6 Revision 1, January 2012

23.12.130

Page 174

[ 23-30]

Communications 23

A320 Family Figure 23-6 - VHF system

RMP3

RMP1

RMP2 VDR1 antenna

VDR1

VDR2

VDR3

HF1

Issue 6 Revision 1, January 2012

VDR3 antenna

Three VDR transceivers

VDR2 antenna

HF2

23.12.130

Page 175

[ 23-31]

A320 Family

23 Communications Table 23-9 - Technical solutions description TDU

Title (Remarks)

Appl.

Weight (kg) MWE/OWE/APL

Std

VHF Data Radio (VDR) basic equipment, type VHF 2100, capable VDL mode 2 - ROCKWELL COLLINS

A318-100 A319-100 A320-200 A321-200

12

VHF Data Radio (VDR) alternate equipment, capable VDL mode 2 - THALES AVIONICS

A318-100 A319-100 A320-200 A321-200

13

VHF Data Radio (VDR) alternate equipment, capable VDL mode 2 - HONEYWELL

A318-100 A319-100 A320-200 A321-200

Issue 6 Revision 1, January 2012

Equipment reference

Equipment supplier

Equipment PN

QTY

STS

VDR transceiver (mode 2)

ROCKWELL COL- 822-1287-120 LINS

3

SFE

VHF antenna

CHELTON

2438-89-00

3

SFE

Negl./Negl./Negl. Negl./Negl./Negl. Negl./Negl./Negl. Negl./Negl./Negl.

VDR transceiver (mode 2)

THALES AVIONICS SA

EVR750-040100A

3

SFE

Negl./Negl./Negl. Negl./Negl./Negl. Negl./Negl./Negl. Negl./Negl./Negl.

VDR transceiver (mode 2)

HONEYWELL INC. REDMOND, OLATHE

064-500002051

3

SFE

23.12.130

Page 176

[ 23-32]

Communications 23

A320 Family

Intentionally left blank

Issue 6 Revision 1, January 2012

23.12.130

Page 177

[ 23-33]

A320 Family

23 Communications

23.13.100 - Installation of alternate Radio Management Panel (RMP) Objective To provide alternate Radio Management Panels (RMPs). Basic aircraft The basic aircraft is equipped with two RMPs (8.33 kHz channel spacing capability) installed on the center pedestal. Description The basic RMPs are replaced by alternate equipment (MLS capable and with turbo tuning). Note A third RMP (CN23.13.101) is recommended if an optional HF is installed. EPAC selection mode Individual

Issue 6 Revision 1, January 2012

23.13.100

Page 178

[ 23-34]

Communications 23

A320 Family

Table 23-10 - Technical solutions description TDU

Title (Remarks)

Appl.

Weight (kg) MWE/OWE/APL

Std

Radio Management Panel (RMP) basic equip. with turbo tuning & HF data activation capab. (std 2B)

A318-100 A319-100 A320-200 A321-200

03

Radio Management Panel (RMP) alternate equipment MLS/GLS compatible and with turbo tuning (std 3B)

A318-100 A319-100 A320-200 A321-200

04

Radio Management Panel (RMP) - alternate equipment with CPDLC function capability (std 4)

A318-100 A319-100 A320-200 A321-200

Issue 6 Revision 1, January 2012

Equipment reference

Equipment supplier

Equipment PN

QTY

STS

Radio Management Panel (RMP)

THALES AVIONICS SA

C12848CB01

2

SFE

Negl./Negl./Negl. Negl./Negl./Negl. Negl./Negl./Negl. Negl./Negl./Negl.

Radio Management Panel (RMP)

THALES AVIONICS SA

C12848DB01

2

SFE

Negl./Negl./Negl. Negl./Negl./Negl. Negl./Negl./Negl. Negl./Negl./Negl.

Radio Management Panel (RMP)

THALES AVIONICS SA

C12848EA01

2

SFE

23.13.100

Page 179

[ 23-35]

A320 Family

23 Communications 23.13.101 - Installation of third Radio Management Panel (RMP) Objective To provide additional control for communication radios and back-up in case one of the basic RMPs fails. Basic aircraft The basic aircraft is equipped with two RMPs (8.33 kHz channel spacing capability) installed on the center pedestal. Description The third RMP is connected to all VDR transceivers (and HF if installed) via the two basic RMPs. The third RMP is used for communication facilities only. The modification consists of the: • modification of the CFDIU pin programming • installation of the third RMP on the existing provision • removal of safety clip from appropriate circuit breaker. Note The third RMP is recommended if an optional HF is installed. EPAC selection mode Individual Issue 6 Revision 1, January 2012

23.13.101

Page 180

[ 23-36]

Communications 23

A320 Family

Figure 23-7 - Third Radio Management Panel (RMP) ACTIVE

RMP3

VHF1

VHF2

HF1

SEL

SE

STBY/CRS

VHF3 AM

HF2

ON

STBY NAV NAV

VOR

LS

ADF

BFO OFF

RMP1

VDR1

RMP2

Third radio management panel

VDR2

VDR3

HF1

HF2

Captain RMP1

Issue 6 Revision 1, January 2012

23.13.101

First Officer RMP2

Page 181

[ 23-37]

A320 Family

23 Communications Table 23-11 - Technical solutions description TDU

Title (Remarks)

Appl.

Weight (kg) MWE/OWE/APL

08

Installation of third RMP MLS and GLS compatible and with turbo tuning (std 3B) - THALES AVIONICS

Equipment reference

Equipment supplier

Equipment PN

QTY

STS

A318-100 A319-100 A320-200 A321-200

3.0/3.0/-3.0 3.0/3.0/-3.0 3.0/3.0/-3.0 3.0/3.0/-3.0

Radio Management Panel (RMP)

THALES AVIONICS SA

C12848DB01

1

SFE

A318-100 A319-100 A320-200 A321-200

3.0/3.0/-3.0 3.0/3.0/-3.0 3.0/3.0/-3.0 3.0/3.0/-3.0

Radio Management Panel (RMP)

THALES AVIONICS SA

C12848EA01

1

SFE

A318-100 A319-100 A320-200 A321-200

3.0/3.0/-3.0 3.0/3.0/-3.0 3.0/3.0/-3.0 3.0/3.0/-3.0

Radio Management Panel (RMP)

THALES AVIONICS SA

C12848CB01

1

SFE

Requires prior acceptance of CN23.13.100/03 Radio Management Panel (RMP) - alternate equipment - MLS/ GLS compatible and with turbo tuning (std 3B)

09

Installation of third RMP - with CPDLC function capability (std 4) Requires prior acceptance of CN23.13.100/04 Radio Management Panel (RMP) - alternate equipment - with CPDLC function capability (std 4)

10

Installation of third RMP - with turbo tuning of VHF channels & HF data activ. capability (std 2b) Requires prior acceptance of CN23.13.100/05 Radio Management Panel (RMP) alternate equip. with turbo tuning & HF data activation capab. (std 2B)

Issue 6 Revision 1, January 2012

23.13.101

Page 182

[ 23-38]

Communications 23

A320 Family

Intentionally left blank

Issue 6 Revision 1, January 2012

23.13.101

Page 183

[ 23-39]

A320 Family

23 Communications 23.13.105 - Activation of RMP std 4 frequency load function Objective To activate the RMP std 4 frequency load function. Basic aircraft None. Description The frequency load function associated to FANS shall be activated on RMP standard 4. It consists in the automatic loading of the standby frequency received by datalink via the ATSU. It implies to: • install and connect wiring between RMP and ATSU • remove "DEACT" placard on RMP front face. Note Requires prior selection of CN46.21.142/02 Installation of FANS B+ or CN46.21.140/07 Installation of FANS A+ with datalink recording capability. EPAC selection mode Individual

Issue 6 Revision 1, January 2012

23.13.105

Page 184

[ 23-40]

Communications 23

A320 Family

Table 23-12 - Technical solutions description TDU

Title (Remarks)

Appl.

Weight (kg) MWE/OWE/APL

01

Activation of RMP std 4 frequency load function Requires prior selection of CN46.21.142/ 02 Installation of FANS B+

Issue 6 Revision 1, January 2012

A318-100 A319-100 A320-200 A321-200

Equipment reference

Equipment supplier

Equipment PN

QTY

STS

Negl./Negl./Negl. Negl./Negl./Negl. Negl./Negl./Negl. Negl./Negl./Negl.

23.13.105

Page 185

[ 23-41]

A320 Family

23 Communications

23.28.170 - Installation of AERO H+/SBB SATCOM cockpit voice interface Objective To provide cockpit voice communications for the aeronautical AERO H+/SBB SATCOM system.

EPAC selection mode Individual

Basic aircraft None. Description Cockpit voice communications is provided for the aeronautical AERO H+/SBB SATCOM system. This modification consists of the following: • replacement of the basic Audio Management Unit (AMU) by an upgraded AMU, with SATCOM interface capability • replacement of the Audio Control Panels (ACPs) by upgraded ACPs with SATCOM capability • installation of wiring between SDU location and AMU, as well as FWC • update of MCDU documentation. Note For SATCOM cockpit voice operation, the MCDU will be used for dialing and the ACP for call establishment and termination.

Issue 6 Revision 1, January 2012

23.28.170

Page 186

[ 23-42]

Communications 23

A320 Family

Table 23-13 - Technical solutions description TDU

Title (Remarks)

Appl.

Weight (kg) MWE/OWE/APL

33

Cockpit voice interface - AERO H+/SBB SATCOM ROCKWELL COLLINS - ACP for fourth occupant in cockpit

A318-100 A319-100 A320-200 A321-200

4.0/4.0/-4.0 4.0/4.0/-4.0 4.0/4.0/-4.0 4.0/4.0/-4.0

Requires prior installation of ROCKWELL COLLINS SATCOM AERO H+/SBB & CN23.50.110/21 - Installation of an ACP for the fourth occupant - T.E.A.M

34

Cockpit voice interface - AERO H+/SBB SATCOM ROCKWELL COLLINS - ACP for 4th occup. & avionics comp.

A318-100 A319-100 A320-200 A321-200

7.0/7.0/-7.0 7.0/7.0/-7.0 7.0/7.0/-7.0 7.0/7.0/-7.0

Requires prior selection of ROCKWELL COLLINS SATCOM AERO H+/SBB and CN23.50.110/23 - Installation of an ACP for the fourth occupant and an ACP and a jack panel in the avionics compartment.

35

Cockpit voice interface - AERO H+/SBB SATCOM ROCKWELL COLLINS - basic ACP installation

A318-100 A319-100 A320-200 A321-200

Negl./Negl./Negl. Negl./Negl./Negl. Negl./Negl./Negl. Negl./Negl./Negl.

Requires prior selection of ROCKWELL COLLINS SATCOM AERO H+/SBB.

36

Cockpit voice interface - AERO H+/SBB SATCOM ROCKWELL COLLINS - ACP in avionics compartment Requires prior selection of ROCKWELL COLLINS SATCOM AERO H+/SBB and CN23.50.110/22 - Installation of an ACP and a jack panel in the avionics compartment.

Issue 6 Revision 1, January 2012

A318-100 A319-100 A320-200 A321-200

3.0/3.0/-3.0 3.0/3.0/-3.0 3.0/3.0/-3.0 3.0/3.0/-3.0

Equipment reference

Equipment supplier

Equipment PN

QTY

STS

Audio Control Panel T.E.A.M (ACP)

ACP2788AE0 1

4

SFE

Audio Management Unit (AMU)

T.E.A.M

AMU4031LB1 40204

1

SFE

Audio Control Panel T.E.A.M (ACP)

ACP2788AE0 1

5

SFE

Audio Management Unit (AMU)

T.E.A.M

AMU4031LB1 40204

1

SFE

Audio Control Panel T.E.A.M (ACP)

ACP2788AE0 1

3

SFE

Audio Management Unit (AMU)

T.E.A.M

AMU4031LA1 40204

1

SFE

Audio Control Panel T.E.A.M (ACP)

ACP2788AE0 1

4

SFE

Audio Management Unit (AMU)

AMU4031LA1 40204

1

SFE

23.28.170

T.E.A.M

Page 187

[ 23-43]

A320 Family

23 Communications 23.28.210 - Installation of SATCOM AERO H+ SRT 2100B system Objective To install AERO H+ SRT 2100B SATCOM avionics system and antenna equipment. Basic aircraft None. Description The AERO H+ SRT 2100B SATCOM is a transmission system based on Inmarsat services that provides: • two classic voice channels for cabin and cockpit voice communications (mainly as a telephone) • one classic data channel (2.4 kbps - 10 kbps bandwidth) used mainly for cockpit ACARS/FANS transmissions

Note No redundancy is provided with proposed architecture the failure of one of the SATCOM components (avionics/antenna) will lead to total loss of the SATCOM system. EPAC selection mode Individual

The modification consists in installing: • one AERO H+ SRT 2100B SATCOM SATCOM subsystem • associated High Gain antenna sub-system.

Issue 6 Revision 1, January 2012

23.28.210

Page 188

[ 23-44]

Communications 23

A320 Family

Table 23-14 - Technical solutions description TDU

Title (Remarks)

Appl.

Weight (kg) MWE/OWE/APL

01

02

Installation of AERO H+ SRT 2100B SATCOM system ROCKWELL COLLINS

Installation of AERO H+ SRT 2100B SATCOM system with prov. for 1 SBB channel ROCKWELL COLLINS

Issue 6 Revision 1, January 2012

A318-100 A319-100 A320-200 A321-200

A318-100 A319-100 A320-200 A321-200

90.0/90.0/-90.0 90.0/90.0/-90.0 90.0/90.0/-90.0 90.0/90.0/-90.0

91.0/91.0/-91.0 91.0/91.0/-91.0 91.0/91.0/-91.0 91.0/91.0/-91.0

Equipment reference

Equipment supplier

Equipment PN

QTY

STS

Adapter plate

CHELTON

6050-80-99

1

SFE

Diplexer Low Noise Amplifier (D/LNA)

CHELTON

5044-89-99

1

SFE

Feeder

CHELTON

6058-89-99

1

SFE

High Gain Antenna (HGA)

CHELTON

4141-89-99

1

SFE

SATCOM transceiver

ROCKWELL COL- 822-1785-401 LINS

1

SFE

Adapter plate

CHELTON

6050-80-99

1

SFE

Diplexer Low Noise Amplifier (D/LNA)

CHELTON

5044-89-99

1

SFE

Feeder

CHELTON

6058-89-99

1

SFE

High Gain Antenna (HGA)

CHELTON

4141-89-99

1

SFE

SATCOM transceiver

ROCKWELL COL- 822-1785-401 LINS

1

SFE

23.28.210

Page 189

[ 23-45]

A320 Family

23 Communications TDU

Title (Remarks)

Appl.

Weight (kg) MWE/OWE/APL

03

Installation of AERO H+ SRT 2100B SATCOM system with prov. for 2 SBB channels ROCKWELL COLLINS

Issue 6 Revision 1, January 2012

A318-100 A319-100 A320-200 A321-200

92.0/92.0/-92.0 92.0/92.0/-92.0 92.0/92.0/-92.0 92.0/92.0/-92.0

Equipment reference

Equipment supplier

Equipment PN

QTY

STS

Adapter plate

CHELTON

6050-80-99

1

SFE

Diplexer Low Noise Amplifier (D/LNA)

CHELTON

5044-89-99

1

SFE

Feeder

CHELTON

6058-89-99

1

SFE

High Gain Antenna (HGA)

CHELTON

4141-89-99

1

SFE

SATCOM transceiver

ROCKWELL COL- 822-1785-401 LINS

1

SFE

23.28.210

Page 190

[ 23-46]

Communications 23

A320 Family

Intentionally left blank

Issue 6 Revision 1, January 2012

23.28.210

Page 191

[ 23-47]

A320 Family

23 Communications

23.28.211 - Installation of SwiftBroadband (SBB) SATCOM system Objective To install Swiftbroadband (SBB) SATCOM avionics and antenna equipment. Basic aircraft None. Description The SwiftBroadband (SBB) is a high speed Inmarsat service providing channels up to 432 kbps each. The SBB SATCOM is a transmission system that provides following services: • one or two high speed data channels (up to 432 kbps per channel bandwidth) used for future cabin or cockpit applications requiring high bandwidth • two classic voice channels for cabin and cockpit voice communications (mainly as a telephone) • one classic data channel (2.4 kbps-10 kbps bandwidth) used mainly for cockpit ACARS/FANS transmissions.

Note No redundancy is provided with proposed architecture, the failure of one of the SATCOM components (avionics/antennas) will lead to total loss of the SATCOM system. EPAC selection mode Individual

The modification consists in installing: • one SBB SATCOM sub-system • associated High Gain antenna sub-system.

Issue 6 Revision 1, January 2012

23.28.211

Page 192

[ 23-48]

Communications 23

A320 Family

Table 23-15 - Technical solutions description TDU

Title (Remarks)

Appl.

Weight (kg) MWE/OWE/APL

01

Installation of Swiftbroadband (SBB) SATCOM - one SBB channel - ROCKWELL COLLINS

Issue 6 Revision 1, January 2012

A318-100 A319-100 A320-200 A321-200

41.0/41.0/-41.0 41.0/41.0/-41.0 41.0/41.0/-41.0 41.0/41.0/-41.0

Equipment reference

Equipment supplier

Equipment PN

QTY

STS

Adapter plate

CHELTON

6050-80-99

1

SFE

Diplexer Low Noise Amplifier (D/LNA)

CHELTON

5044-89-99

1

SFE

Feeder

CHELTON

6058-89-99

1

SFE

High Gain Antenna (HGA)

CHELTON

4141-89-99

1

SFE

High Speed Data Unit (HSDU)

ROCKWELL COL- 822-2232-040 LINS

1

SFE

HSDU Data Module ROCKWELL COL- 822-2248-401 LINS (HDM)

1

SFE

SATCOM transceiver

1

SFE

23.28.211

ROCKWELL COL- 822-1785-401 LINS

Page 193

[ 23-49]

A320 Family

23 Communications TDU

Title (Remarks)

Appl.

Weight (kg) MWE/OWE/APL

02

Installation of Swiftbroadband (SBB) SATCOM - two SBB channels - ROCKWELL COLLINS

Issue 6 Revision 1, January 2012

A318-100 A319-100 A320-200 A321-200

47.0/47.0/-47.0 47.0/47.0/-47.0 47.0/47.0/-47.0 47.0/47.0/-47.0

Equipment reference

Equipment supplier

Equipment PN

QTY

STS

Adapter plate

CHELTON

6050-80-99

1

SFE

Diplexer Low Noise Amplifier (D/LNA)

CHELTON

5044-89-99

1

SFE

Feeder

CHELTON

6058-89-99

1

SFE

High Gain Antenna (HGA)

CHELTON

4141-89-99

1

SFE

High Speed Data Unit (HSDU)

ROCKWELL COL- 822-2232-040 LINS

2

SFE

HSDU Data Module ROCKWELL COL- 822-2248-401 LINS (HDM)

1

SFE

SATCOM transceiver

1

SFE

23.28.211

ROCKWELL COL- 822-1785-401 LINS

Page 194

[ 23-50]

Communications 23

A320 Family TDU

Title (Remarks)

Appl.

Weight (kg) MWE/OWE/APL

03

Installation of Swiftbroadband (SBB) SATCOM - one SBB channel and prov. for a 2nd ROCKWELL COLLINS

Issue 6 Revision 1, January 2012

A318-100 A319-100 A320-200 A321-200

42.0/42.0/-42.0 42.0/42.0/-42.0 42.0/42.0/-42.0 42.0/42.0/-42.0

Equipment reference

Equipment supplier

Equipment PN

QTY

STS

Adapter plate

CHELTON

6050-80-99

1

SFE

Diplexer Low Noise Amplifier (D/LNA)

CHELTON

5044-89-99

1

SFE

Feeder

CHELTON

6058-89-99

1

SFE

High Gain Antenna (HGA)

CHELTON

4141-89-99

1

SFE

High Speed Data Unit (HSDU)

ROCKWELL COL- 822-2232-040 LINS

1

SFE

HSDU Data Module ROCKWELL COL- 822-2248-401 LINS (HDM)

1

SFE

SATCOM transceiver

1

SFE

23.28.211

ROCKWELL COL- 822-1785-401 LINS

Page 195

[ 23-51]

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23 Communications

23.50.110 - Installation of additional Audio Control Panel (ACP) and jack panel Objective To provide provision for two-way communication for a fourth occupant and/or additional communication capability in the avionics compartment for maintenance purposes. Basic aircraft • three audio control panels for the Captain, the First Officer, and the third occupant • two jack panels, one for the Captain and one for the First Officer, each with two connectors: one for the boomset and one jack type for a headset • two hand microphone connectors, one at each pilot's station • a jack panel for the third occupant with three connectors: one for the boomset, one for the hand microphone, and one jack type for a headset • a headset jack connector for the fourth occupant, linked to third occupant's audio output • three boomsets • three hand microphones • service interphone jack and system provision for an ACP in the avionics compartment.

Issue 6 Revision 1, January 2012

Description For the installation of an ACP for the fourth occupant the modification consists of: • a new AMU which is interchangeable • a supplementary ACP on the overhead panel • additional wiring between ACP and AMU • additional plugs for boomsets and hand microphone. For the installation of an ACP and a jack panel in the avionics compartment the modification consists of: • a supplementary ACP in the avionics compartment • additional wiring between ACP and AMU • additional plugs for boomsets, hand microphone, headsets and service interphone. EPAC selection mode Individual

23.50.110

Page 196

[ 23-52]

Communications 23

A320 Family

Figure 23-8 - Audio Control Panel (ACP) installation (typical configurations) Third occupant ACP

Fourth occupant ACP

First officer ACP Captain ACP BOOMSET

HAND MIC HEADSET

SVCE INTPH

Jack Panel

Jack Panel Fourth occupant station

ACP AMU

BOOMSET

CALL

CALL

CALL

CALL

CALL

MECH

ATT

VHF1

VHF2

VHF3

HF1

HF2

INT

CAB

INT ON VOICE

HAND MIC

RAD VOR1

Jack Panel

Issue 6 Revision 1, January 2012

VOR2

RESET MKR

ILS

PA MLS

ADF1

ADF2

Audio Control Panel

23.50.110

Avionics compartment

Page 197

[ 23-53]

A320 Family

23 Communications Table 23-16 - Technical solutions description TDU

Title (Remarks)

Appl.

Weight (kg) MWE/OWE/APL

21

Installation of ACP for fourth occupant - T.E.A.M. Incompatible with CN23.50.135 - Installation of headset for fourth occupant (SFE)

22

23

Installation of ACP and jack panel in avionics compartment - T.E.A.M.

Installation of ACP for fourth occupant and ACP and jack panel in avionics compartment - T.E.A.M. Incompatible with CN23.50.135 - Installation of headset for fourth occupant (SFE).

Issue 6 Revision 1, January 2012

A318-100 A319-100 A320-200 A321-200

A318-100 A319-100 A320-200 A321-200

A318-100 A319-100 A320-200 A321-200

Negl./Negl./Negl. Negl./Negl./Negl. Negl./Negl./Negl. Negl./Negl./Negl.

Negl./Negl./Negl. Negl./Negl./Negl. Negl./Negl./Negl. Negl./Negl./Negl.

Negl./Negl./Negl. Negl./Negl./Negl. Negl./Negl./Negl. Negl./Negl./Negl.

Equipment reference

Equipment supplier

Equipment PN

QTY

STS

Audio Control Panel T.E.A.M (ACP)

ACP2788AD0 1

1

SFE

Audio Management Unit (AMU)

AMU4031SB1 1 40204

SFE

Audio Control Panel T.E.A.M (ACP)

ACP2788AD0 1

1

SFE

Audio Management Unit (AMU)

AMU4031SA1 1 40204

SFE

Audio Control Panel T.E.A.M (ACP)

ACP2788AD0 1

2

SFE

Audio Management Unit (AMU)

AMU4031SB1 1 40204

SFE

23.50.110

T.E.A.M

T.E.A.M

T.E.A.M

Page 198

[ 23-54]

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A320 Family

Intentionally left blank

Issue 6 Revision 1, January 2012

23.50.110

Page 199

[ 23-55]

A320 Family

23 Communications 23.50.135 - Installation of headset for fourth occupant Objective To allow the fourth occupant to listen to communications selected on the third occupant ACP.

EPAC selection mode Individual

Basic aircraft • two jack panels, one for the Captain and one for the First Officer, each with two connectors: one for the boomset and one jack type for a headset • two hand microphone connectors, one at each pilot's station • a jack panel for the third occupant with three connectors: one for the boomset, one for the hand microphone, and one jack type for a headset • a headset jack connector for the fourth occupant, linked to third occupant's audio output • three boomsets • three hand microphones. Description Installation of headset for fourth occupant in the LH aft console. Note • the headset plugs shall be PJ 055 or equivalent • requires prior acceptance of CN25.11.208 - Installation of fourth occupant seat in cockpit.

Issue 6 Revision 1, January 2012

23.50.135

Page 200

[ 23-56]

Communications 23

A320 Family

Figure 23-9 - Fourth occupant headset

Fourth occupant station

HEADSET

Basic headset jack

Issue 6 Revision 1, January 2012

23.50.135

Page 201

[ 23-57]

A320 Family

23 Communications Table 23-17 - Technical solutions description TDU

Title (Remarks)

Appl.

Weight (kg) MWE/OWE/APL

12

Installation of headset for fourth occupant - SENNHEISER, model HD46-K1

Issue 6 Revision 1, January 2012

A318-100 A319-100 A320-200 A321-200

0.5/0.5/-0.5 0.5/0.5/-0.5 0.5/0.5/-0.5 0.5/0.5/-0.5

Equipment reference

Headset

23.50.135

Equipment supplier

Equipment PN

SENNHEISER

046-69-9990931

QTY

1

Page 202

STS

SFE

[ 23-58]

Communications 23

A320 Family

Intentionally left blank

Issue 6 Revision 1, January 2012

23.50.135

Page 203

[ 23-59]

A320 Family

23 Communications 23.50.138 - Cockpit hand microphone alternate equipment Objective To provide alternate supplier for the three basic hand microphones in the cockpit. Basic aircraft Three hand microphones are installed in the cockpit. Description The cockpit hand microphones are replaced by alternate equipment. The corresponding brackets shall be adapted accordingly. Note HOLMBERG microphones (TDU 06) are compulsory in conjunction with GSM on-board. EPAC selection mode Individual

Issue 6 Revision 1, January 2012

23.50.138

Page 204

[ 23-60]

Communications 23

A320 Family

Table 23-18 - Technical solutions description TDU

Title (Remarks)

Appl.

Weight (kg) MWE/OWE/APL

Std

Cockpit hand microphone basic equipment

A318-100 A319-100 A320-200 A321-200

06

Cockpit hand microphone alternate equipment - HOLMBERG, PN 85-16-12022-05

A318-100 A319-100 A320-200 A321-200

Compulsory in conjunction with GSM onboard.

Issue 6 Revision 1, January 2012

Negl./Negl./Negl. Negl./Negl./Negl. Negl./Negl./Negl. Negl./Negl./Negl.

Equipment reference

Equipment supplier

Equipment PN

QTY

STS

Hand microphone

LEM SA

M83P1801A

3

SFE

Hand microphones

HOLMBERG

85-16-1202205

3

SFE

23.50.138

Page 205

[ 23-61]

A320 Family

23 Communications 23.51.103 - Installation of active noise canceling boomsets (SFE) Objective To improve audio communication for cockpit crew by installation of active noise canceling boomsets.

Description Active noise canceling boomsets are installed in replacement of the basic boomsets.

Basic aircraft • two jack panels, one for the Captain and one for the First Officer, each with two connectors: one for the boomset and one jack type for a headset • two hand microphone connectors, one at each pilot's station • a jack panel for the third occupant with three connectors: one for the boomset, one for the hand microphone, and one jack type for a headset • a headset jack connector for the fourth occupant, linked to third occupant's audio output • three boomsets • three hand microphones.

The modification consists of: • system provision (including any necessary wiring) to accommodate active noise canceling boomsets with XLR-5 plug. The required power supply shall be 28 VDC, + 28 VDC on Pin 5 and earth (together with Audio Lo) on Pin 2 • adaptation of the wiring between the AMU and the Captain, First Officer and third occupant boost receptacle (XLR-5 plug) in order to be able to install active noise canceling boomsets • installation of three active noise canceling boomsets. Note As this modification requires change of the audio system wiring principle on aircraft, the audio transmission quality can be affected. EPAC selection mode Individual

Issue 6 Revision 1, January 2012

23.51.103

Page 206

[ 23-62]

Communications 23

A320 Family

Figure 23-10 - Active noise canceling boomsets locations BOOMSET

HEADSET

HAND MIC

Captain boomset

Jack panel

First Officer boomset

Captain microphone

First Officer microphone Third occupant boomset + microphone

Fourth occupant headset

Issue 6 Revision 1, January 2012

23.51.103

Page 207

[ 23-63]

A320 Family

23 Communications Table 23-19 - Technical solutions description TDU

Title (Remarks)

Appl.

Weight (kg) MWE/OWE/APL

04

Installation of active noise canceling boomsets (SFE) - SENNHEISER HMEC 26-CP

Issue 6 Revision 1, January 2012

A318-100 A319-100 A320-200 A321-200

0.5/0.5/-0.5 0.5/0.5/-0.5 0.5/0.5/-0.5 0.5/0.5/-0.5

Equipment reference

Boomset

23.51.103

Equipment supplier

Equipment PN

SENNHEISER

026-35-9993211

QTY

3

Page 208

STS

SFE

[ 23-64]

Communications 23

A320 Family

Intentionally left blank

Issue 6 Revision 1, January 2012

23.51.103

Page 209

[ 23-65]

A320 Family

23 Communications 23.51.136 - Boomsets alternate equipment Objective To provide alternate equipment for boomsets.

EPAC selection mode Individual

Basic aircraft • two jack panels, one for the Captain and one for the First Officer, each with two connectors: one for the boomset and one jack type for a headset • two hand microphone connectors, one at each pilot's station • a jack panel for the third occupant with three connectors: one for the boomset, one for the hand microphone, and one jack type for a headset • a headset jack connector for the fourth occupant, linked to third occupant's audio output • three boomsets • three hand microphones. Description The basic boomsets are replaced by alternate equipment complying with ARINC 535A and 538B specifications. The boomset plugs shall be ITT common type XLR-512-C or equivalent.

Issue 6 Revision 1, January 2012

23.51.136

Page 210

[ 23-66]

Communications 23

A320 Family

Figure 23-11 - Boomsets locations BOOMSET

HEADSET

HAND MIC

Captain boomset

Jack panel

First Officer boomset

Captain microphone

First Officer microphone Third occupant boomset + microphone

Fourth occupant headset

Issue 6 Revision 1, January 2012

23.51.136

Page 211

[ 23-67]

A320 Family

23 Communications Table 23-20 - Technical solutions description TDU

Title (Remarks)

Appl.

Weight (kg) MWE/OWE/APL

Std

Boomsets basic equipment HOLMBERG

A318-100 A319-100 A320-200 A321-200

27

Boomsets alternate equipment - TELEX COMMUNICATIONS, PN 64300-210

A318-100 A319-100 A320-200 A321-200

30

Boomsets alternate equipment - SENNHEISER - HME46C (SFE)

A318-100 A319-100 A320-200 A321-200

Issue 6 Revision 1, January 2012

Equipment reference

Equipment supplier

Equipment PN

QTY

STS

Boomset

HOLMBERG

1046GT2102 AY

3

SFE

Negl./Negl./Negl. Negl./Negl./Negl. Negl./Negl./Negl. Negl./Negl./Negl.

Boomset

TELEX COMMUNICATIONS INC

64300-210

3

SFE

Negl./Negl./Negl. Negl./Negl./Negl. Negl./Negl./Negl. Negl./Negl./Negl.

Boomset

SENNHEISER

046-55-9990231

3

SFE

23.51.136

Page 212

[ 23-68]

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A320 Family

Intentionally left blank

Issue 6 Revision 1, January 2012

23.51.136

Page 213

[ 23-69]

A320 Family

23 Communications 23.51.139 - Boomsets alternate equipment with two jack plugs

dedicated to the boomset. Therefore, it is no more possible to connect simultaneously a boomset and a headset.

Objective To provide alternate equipment for boomsets. Basic aircraft • two jack panels, one for the Captain and one for the First Officer, each with two connectors: one for the boomset and one jack type for a headset • two hand microphone connectors, one at each pilot's station • a jack panel for the third occupant with three connectors: one for the boomset, one for the hand microphone, and one jack type for a headset • a headset jack connector for the fourth occupant, linked to third occupant's audio output • three boomsets • three hand microphones.

EPAC selection mode Individual

Description The basic boomsets are replaced by alternate equipment with two jack plugs, complying with ARINC 535A and 538B specifications. The boomset jack plugs shall be type JP068 and JP055. The three jack panels (pilots and third occupant) are replaced by new ones mechanically interchangeable, where the boomset connector and the headset jack connector are replaced by two jack connectors both Issue 6 Revision 1, January 2012

23.51.139

Page 214

[ 23-70]

Communications 23

A320 Family

Figure 23-12 - Boomsets locations BOOMSET MIC

RCVR

HAND MIC

Captain boomset

Jack panel

First Officer boomset

Captain microphone

First Officer microphone Third occupant boomset + microphone

Fourth occupant headset

Issue 6 Revision 1, January 2012

23.51.139

Page 215

[ 23-71]

A320 Family

23 Communications Table 23-21 - Technical solutions description TDU

Title (Remarks)

Appl.

Weight (kg) MWE/OWE/APL

Equipment reference

Equipment supplier

Equipment PN

QTY

STS

04

Boomsets alternate equipment with two jack plugs TELEX COMMUNICATIONS, PN 64300-212

A318-100 A319-100 A320-200 A321-200

Negl./Negl./Negl. Negl./Negl./Negl. Negl./Negl./Negl. Negl./Negl./Negl.

Boomset

TELEX COMMUNICATIONS INC

64300-212

3

SFE

05

Boomsets alternate equipment with two jack plugs SENNHEISER, model HME46-K

A318-100 A319-100 A320-200 A321-200

Negl./Negl./Negl. Negl./Negl./Negl. Negl./Negl./Negl. Negl./Negl./Negl.

Boomset

SENNHEISER

046-55-9990131

3

SFE

Issue 6 Revision 1, January 2012

23.51.139

Page 216

[ 23-72]

Communications 23

A320 Family

Intentionally left blank

Issue 6 Revision 1, January 2012

23.51.139

Page 217

[ 23-73]

A320 Family

23 Communications 23.70.110 - Installation of a video monitoring system Objective The purpose of the video monitoring system is to: • enable the flight crew to identify anyone asking to enter the cockpit • provide the flight crew with a visual image of the cockpit door area in order to be able to assess any suspicious behaviour and potential threats to flight safety. Basic aircraft None. Description The Cockpit Door Surveillance System (CDSS) shall be composed of: • two video cameras located in Door 1 area • one video camera located in cockpit entrance area • a display located in the cockpit. The camera view shall be selectable by the flight crew in the cockpit. EPAC selection mode Individual

Issue 6 Revision 1, January 2012

23.70.110

Page 218

[ 23-74]

Communications 23

A320 Family

Table 23-22 - Technical solutions description TDU

Title (Remarks)

Appl.

Weight (kg) MWE/OWE/APL

02

Installation of a Cockpit Door Survey System

A318-100 A319-100 A320-200 A321-200

8.0/8.0/-8.0 8.0/8.0/-8.0 8.0/8.0/-8.0 8.0/8.0/-8.0

14

Installation of Cockpit Door Surveillance System (CDSS) connected to the ECAM SD

A318-100 A319-100 A320-200 A321-200

8.0/8.0/-8.0 8.0/8.0/-8.0 8.0/8.0/-8.0 8.0/8.0/-8.0

Requires prior acceptance of CN31.60.120/10 Installation of cockpit display units with video capability.

Issue 6 Revision 1, January 2012

Equipment reference

23.70.110

Equipment supplier

Equipment PN

QTY

Page 219

STS

[ 23-75]

A320 Family

23 Communications

23.71.103 - Solid State Cockpit Voice Recorder (SSCVR) alternate equipment Objective To replace the basic Solid State Cockpit Voice Recorder (SSCVR) by an alternate one complying with airworthiness requirements. The SSCVR has the capability to store the last 2 hours of crew conversations and communications in flight and on ground in a box able to endure severe environment conditions. Basic aircraft One SSCVR is installed in the aft section of the aircraft. The SSCVR automatically starts recording: • on ground during the first five minutes following energization of the aircraft electrical network • on ground with one engine running • in flight with engines running or stopped. The SSCVR automatically stops recording five minutes after the second engine shutdown. On ground, the SSCVR can be manually energized by pressing the GND CTL pushbutton to allow pre-flight checklist recording. The complete erasure of the SSCVR can be performed by pushing the ERASE pushbutton provided the aircraft is on ground with parking brake applied.

Issue 6 Revision 1, January 2012

Description The basic SSCVR equipment is replaced by alternate equipment Note All equipment are electrically and mechanically interchangeable. EPAC selection mode Individual

23.71.103

Page 220

[ 23-76]

Communications 23

A320 Family

Figure 23-13 - SSCVR location Area microphone

RCDR GRD CTL

ON

CVR ERASE

CVR TEST

A U T O

CVR control panel

C73 C74

CVR

Issue 6 Revision 1, January 2012

23.71.103

Page 221

[ 23-77]

A320 Family

23 Communications Table 23-23 - Technical solutions description TDU

Title (Remarks)

Appl.

Weight (kg) MWE/OWE/APL

Std

SSCVR basic equipment - L3 COMMUNICATIONS, PN 21001026-02 Compliant with FAR amendments 121338 and 25-124.

10

SSCVR alternate equipment HONEYWELL

Issue 6 Revision 1, January 2012

A318-100 A319-100 A320-200 A321-200

A318-100 A319-100 A320-200 A321-200

Negl./Negl./Negl. Negl./Negl./Negl. Negl./Negl./Negl. Negl./Negl./Negl.

Equipment reference

Equipment supplier

Equipment PN

Solid State Cockpit Voice Recorder (SSCVR)

L3 COMMUNICATIONS

2100-1026-02

1

SFE

Cockpit Voice Recorder (CVR)

HONEYWELL INC. REDMOND, OLATHE

980-6022-001

1

SFE

23.71.103

QTY

Page 222

STS

[ 23-78]

Communications 23

A320 Family

Intentionally left blank

Issue 6 Revision 1, January 2012

23.71.103

Page 223

[ 23-79]

A320 Family

23 Communications

23.71.110 - Recorder Independent Power Supply (RIPS) - 28VDC power supply for CVR Objective To comply with FAR amendments 121-338 and 25-124. Basic aircraft The SSCVR is basically connected to 115 VAC power supply. Description The SSCVR is connected to the 28 VDC 401PP busbar which is supplied by the aircraft batteries. This allows the SSCVR to remain powered for at least 10 minutes as requested by FAR amendments 121-338 and 25124. EPAC selection mode Individual

Issue 6 Revision 1, January 2012

23.71.110

Page 224

[ 23-80]

Communications 23

A320 Family

Table 23-24 - Technical solutions description TDU

Title (Remarks)

Appl.

Weight (kg) MWE/OWE/APL

01

Recorder Independent Power Supply (RIPS) - 28VDC power supply for CVR

Issue 6 Revision 1, January 2012

A318-100 A319-100 A320-200 A321-200

Equipment reference

Equipment supplier

Equipment PN

QTY

STS

Negl./Negl./Negl. Negl./Negl./Negl. Negl./Negl./Negl. Negl./Negl./Negl.

23.71.110

Page 225

[ 23-81]

A320 Family

23 Communications

23.71.120 - System provision for CVR capable of data link recording Objective To allow the Cockpit Voice Recorder (CVR) to record ATC datalink communications. Basic aircraft None. Description System provision is installed to give to the Cockpit Voice Recorder (CVR) the capability to record ATC datalink communications. Note Provision for CVR capable of data link recording is recommended for customers operating in FANS environment. EPAC selection mode Individual

Issue 6 Revision 1, January 2012

23.71.120

Page 226

[ 23-82]

Communications 23

A320 Family

Table 23-25 - Technical solutions description TDU

Title (Remarks)

Appl.

Weight (kg) MWE/OWE/APL

01

System provision for CVR capable of data link recording

Issue 6 Revision 1, January 2012

A318-100 A319-100 A320-200 A321-200

Equipment reference

Equipment supplier

Equipment PN

QTY

STS

1.0/1.0/-1.0 1.0/1.0/-1.0 1.0/1.0/-1.0 1.0/1.0/-1.0

23.71.120

Page 227

[ 23-83]

A320 Family

23 Communications

23.73.200 - Installation of cockpit and cabin alert switches (Aircraft Security Project) Objective To notify the Flight Crew when the Cabin Crew are being threatened and to notify the Cabin Crew when the Flight Crew are being threatened. Basic aircraft None. Description In addition to the existing cabin/cockpit interphone function, an alert communication system between the cabin and the cockpit and vice-versa is implemented. The modification comprises the installation of: • an additional switch near each Cockpit Crew location to activate lighted and aural warnings in the cabin • an additional switch near each Cabin Attendant station to activate the horn and the additional indicator light in the cockpit • an additional cockpit indicator / reset button on the cockpit center pedestal 119VU • an additional cockpit alert horn • additional wires between CIDS directors and cockpit switch • additional wires between DEU B and respective switches in the cabin Issue 6 Revision 1, January 2012

• additional wires between CIDS directors and cockpit indicator / reset button • additional wires between CIDS directors and cockpit alert horn. The switches must be pushed for at least 1 second for alert initiation to avoid unintended activation. The Cabin Crew signalling consists of: • distribution of special chime sequence • special message on AIP • ACP indication. All visual indications are limited in time (e.g. 30 seconds) to avoid any reset procedure. The activation of the respective control logic and assignment of lighted and aural warnings is done by reprogramming of the CIDS Cabin Assignment Module (CAM). EPAC selection mode Individual

23.73.200

Page 228

[ 23-84]

Communications 23

A320 Family

Table 23-26 - Technical solutions description TDU

Title (Remarks)

Appl.

Weight (kg) MWE/OWE/APL

01

Installation of cockpit and cabin alert switches (Aircraft Security Project)

Issue 6 Revision 1, January 2012

A318-100 A319-100 A320-200 A321-200

Equipment reference

Equipment supplier

Equipment PN

QTY

STS

2.0/2.0/-2.0 2.0/2.0/-2.0 2.0/2.0/-2.0 2.0/2.0/-2.0

23.73.200

Page 229

[ 23-85]

A320 Family

23 Communications

Intentionally left blank

Issue 6 Revision 1, January 2012

23.73.200

Page 230

[ 23-86]

A320 Family

Electrical power 24

Reference

Title

24.55.101

Passenger Address (PA) power supply in emergency condition with batteries OFF

Issue 6 Revision 1, January 2012

Page 231

[ 24-1]

A320 Family

24 Electrical power

24.55.101 - Passenger Address (PA) power supply in emergency condition with batteries OFF Objective To be able to use PA during emergency evacuation even when the aircraft batteries are switched off. Basic aircraft PA system, if installed, is not supplied when batteries are switched off. Description The essential equipment of CIDS is switched automatically to the hot battery bus when the aircraft loses main power and whenever the emergency exit light switch is set to "arm" or "on". EPAC selection mode Individual

Issue 6 Revision 1, January 2012

24.55.101

Page 232

[ 24-2]

Electrical power 24

A320 Family

Table 24-1 - Technical solutions description TDU

Title (Remarks)

Appl.

Weight (kg) MWE/OWE/APL

01

PA power supply in emergency condition with batteries OFF

Issue 6 Revision 1, January 2012

A318-100 A319-100 A320-200 A321-200

Equipment reference

Equipment supplier

Equipment PN

QTY

STS

2.0/2.0/-2.0 2.0/2.0/-2.0 2.0/2.0/-2.0 2.0/2.0/-2.0

24.55.101

Page 233

[ 24-3]

A320 Family

24 Electrical power

Intentionally left blank

Issue 6 Revision 1, January 2012

24.55.101

Page 234

[ 24-4]

A320 Family

Equipment/furnishings 25

Reference

Title

25.10.108

Installation of paper holder on the glareshield

25.11.102

Pilot seats alternate covers - sheepskin

25.11.208

Installation of fourth occupant seat in cockpit

25.27.100

Installation of heated floor panels for fwd passenger/crew/service door area

25.27.101

Installation of On/off switch for heated floor panels

25.50.137

Rubber seal profile for cargo compartment floor panels

25.50.510

Basic full bulk configuration selection in forward and aft cargo holds

25.50.520

Installation of reinforced floor panels for heavy bulk usage in forward and aft cargo holds

25.52.190

System provision for mechanized bulk loading systems in forward cargo hold (A320)

25.52.191

System provision for mechanized bulk loading systems in forward cargo hold (A321)

25.52.202

Installation of mechanized bulk loading system in forward cargo hold - sliding carpet system

25.52.204

System provision for mechanized bulk loading systems in aft cargo hold (A319/A320)

25.52.205

System provision for mechanized bulk loading systems in aft cargo hold (A321)

25.52.212

Installation of mechanized bulk loading system in aft cargo hold - sliding carpet system

25.52.304

Installation of semi-automatic Cargo Loading System (CLS) in forward and aft cargo holds (A320/A321)

Issue 6 Revision 1, January 2012

Page 235

[ 25-1]

25 Equipment/furnishings

A320 Family

Reference

Title

25.52.310

Fixed provision for occasional bulk capability in forward and aft cargo holds (A320/A321)

25.52.315

Full electrical provision for semi-automatic CLS

25.52.404

Installation of Cargo Loading System (CLS) with full bulk capability in fwd and aft cargo holds

25.52.407

Bulk loading capability in aft cargo hold door area behind two ULDs (A319)

25.52.410

Full provision for installation of special container in aft cargo hold, door area (A319)

25.52.500

Installation of continuous side guides in forward cargo hold

25.52.511

Installation of continuous side guides in aft cargo hold

Issue 6 Revision 1, January 2012

Page 236

[ 25-2]

A320 Family

Equipment/furnishings 25

Intentionally left blank

Issue 6 Revision 1, January 2012

Page 237

[ 25-3]

A320 Family

25 Equipment/furnishings 25.10.108 - Installation of paper holder on the glareshield Objective To provide means of securing documents to the glareshield above the main instrument panel. Basic aircraft None. Description A paper holder capable of accommodating A4 size paper is installed on the cockpit glareshield. EPAC selection mode Individual

Issue 6 Revision 1, January 2012

25.10.108

Page 238

[ 25-4]

Equipment/furnishings 25

A320 Family

Table 25-1 - Technical solutions description TDU

Title (Remarks)

Appl.

Weight (kg) MWE/OWE/APL

01

Installation of paper holder on the glareshield

Issue 6 Revision 1, January 2012

A318-100 A319-100 A320-200 A321-200

Equipment reference

Equipment supplier

Equipment PN

QTY

STS

2.0/2.0/-2.0 2.0/2.0/-2.0 2.0/2.0/-2.0 2.0/2.0/-2.0

25.10.108

Page 239

[ 25-5]

A320 Family

25 Equipment/furnishings 25.11.102 - Pilot seats alternate covers - sheepskin Objective To change captain's and first officer's seat covering. Basic aircraft Captain and first officer seats are covered with cloth material. Description This change consists of replacing basic captain and first officer seats by seats equipped with sheepskin. EPAC selection mode Individual

Issue 6 Revision 1, January 2012

25.11.102

Page 240

[ 25-6]

Equipment/furnishings 25

A320 Family

Figure 25-1 - Pilot seat with sheepskin cover

Sheepskin

Issue 6 Revision 1, January 2012

25.11.102

Page 241

[ 25-7]

A320 Family

25 Equipment/furnishings Table 25-2 - Technical solutions description TDU

Title (Remarks)

Appl.

Weight (kg) MWE/OWE/APL

02

03

Pilot seats alternate cover white sheepskin - EADS SOGERMA

Pilot seats alternate cover grey sheepskin - EADS SOGERMA

Issue 6 Revision 1, January 2012

A318-100 A319-100 A320-200 A321-200

A318-100 A319-100 A320-200 A321-200

1.6/1.6/-1.6 1.6/1.6/-1.6 1.6/1.6/-1.6 1.6/1.6/-1.6

1.6/1.6/-1.6 1.6/1.6/-1.6 1.6/1.6/-1.6 1.6/1.6/-1.6

Equipment reference

Equipment supplier

Equipment PN

QTY

STS

Seat, Captain with white sheepskin cover

SOGERMA ROCHEFORT

TAAI303PE21-01

1

SFE

Seat, First Officer with white sheepskin cover

SOGERMA ROCHEFORT

TAAI303CE21-01

1

SFE

Seat, Captain with grey sheepskin cover

SOGERMA ROCHEFORT

TAAI303PE22-01

1

SFE

Seat, First Officer with grey sheepskin cover

SOGERMA ROCHEFORT

TAAI303CE22-01

1

SFE

25.11.102

Page 242

[ 25-8]

Equipment/furnishings 25

A320 Family

Intentionally left blank

Issue 6 Revision 1, January 2012

25.11.102

Page 243

[ 25-9]

A320 Family

25 Equipment/furnishings 25.11.208 - Installation of fourth occupant seat in cockpit Objective To provide an additional seat for a fourth occupant. Basic aircraft Full provision is made for an additional folding seat. Description A folding seat is installed in the cockpit for the fourth occupant, provided with associated emergency equipment: • a safety shoulder harness equipped with an adjustable crotch strap • an oxygen mask supply box and a full face quick donning oxygen mask • a life vest located under the seat (selectable through global emergency RFC). EPAC selection mode Individual

Issue 6 Revision 1, January 2012

25.11.208

Page 244

[ 25-10]

Equipment/furnishings 25

A320 Family

Figure 25-2 - Fourth occupant seat

Sliding window (emergency evacuation) Capt's seat

F/O's seat

Capt's briefcase Lat console Fixed window Third occupant's seat

Fourth occupant's seat

Right rear panel

Coat stowage

Handset

Lavatory

Issue 6 Revision 1, January 2012

Galley

25.11.208

Page 245

[ 25-11]

A320 Family

25 Equipment/furnishings Table 25-3 - Technical solutions description TDU

Title (Remarks)

Appl.

Weight (kg) MWE/OWE/APL

03

Installation of fourth occupant seat in cockpit - SOGERMA/ SOCEA The harness is not compliant with TSOC114 regulation.

Issue 6 Revision 1, January 2012

A318-100 A319-100 A320-200 A321-200

11.5/12.0/-12.0 11.5/12.0/-12.0 11.5/12.0/-12.0 11.5/12.0/-12.0

Equipment reference

Equipment supplier

Equipment PN

QTY

STS

Folding seat

EADS SOGERMA 2510154-01SERVICES. 00

1

SFE

Quick donning full face oxygen mask

INTERTECHNIQUE

1

SFE

25.11.208

MF20-534

Page 246

[ 25-12]

Equipment/furnishings 25

A320 Family

Intentionally left blank

Issue 6 Revision 1, January 2012

25.11.208

Page 247

[ 25-13]

A320 Family

25 Equipment/furnishings

25.27.100 - Installation of heated floor panels for fwd passenger/crew/service door area Objective To increase the comfort for Cabin Attendants (C/A) in forward door area during long distance flights. Basic aircraft Door area heating is provided by the standard air conditioning system. Description A heated floor panel system is installed to increase the temperature in the forward passenger/crew/service door areas (RH and LH) at floor level. The temperature of the floor panels is controlled via control units. Note An ON/OFF switch CN25.27.101/11.

can

be

selected

through

EPAC selection mode Individual

Issue 6 Revision 1, January 2012

25.27.100

Page 248

[ 25-14]

Equipment/furnishings 25

A320 Family

Figure 25-3 - Floor panel heating for forward passenger/crew/service door area

Attendant seats

Floor panels (heated area is hatched)

Issue 6 Revision 1, January 2012

25.27.100

Page 249

[ 25-15]

A320 Family

25 Equipment/furnishings Table 25-4 - Technical solutions description TDU

Title (Remarks)

Appl.

Weight (kg) MWE/OWE/APL

02

Installation of enhanced heated floor panels for fwd passenger/crew/service door area

Issue 6 Revision 1, January 2012

A318-100 A319-100 A320-200 A321-200

Equipment reference

Equipment supplier

Equipment PN

QTY

STS

11.0/11.0/-11.0 11.0/11.0/-11.0 11.0/11.0/-11.0 11.0/11.0/-11.0

25.27.100

Page 250

[ 25-16]

Equipment/furnishings 25

A320 Family

Intentionally left blank

Issue 6 Revision 1, January 2012

25.27.100

Page 251

[ 25-17]

A320 Family

25 Equipment/furnishings 25.27.101 - Installation of On/off switch for heated floor panels Objective To give the crew the control on the heated floor panels operation. Basic aircraft None Description An ON/OFF switch is installed to allow the crew to control the heated floor panel operation. EPAC selection mode Individual

Issue 6 Revision 1, January 2012

25.27.101

Page 252

[ 25-18]

Equipment/furnishings 25

A320 Family

Table 25-5 - Technical solutions description TDU

Title (Remarks)

Appl.

Weight (kg) MWE/OWE/APL

11

Installation of heated floor panel On/Off control function on FAP

Issue 6 Revision 1, January 2012

A318-100 A319-100 A320-200 A321-200

Equipment reference

Equipment supplier

Equipment PN

QTY

STS

Negl./Negl./Negl. Negl./Negl./Negl. Negl./Negl./Negl. Negl./Negl./Negl.

25.27.101

Page 253

[ 25-19]

A320 Family

25 Equipment/furnishings

25.50.137 - Rubber seal profile for cargo compartment floor panels Objective To provide sealing of the lateral cargo compartment floor panels. Basic aircraft Rubber seal profiles are installed in between the horizontal part and the first sloping part of lateral cargo compartment floor panels. Description Rubber seal profiles are installed to fill the small gaps between both lateral parts of the cargo compartment floor and to the side wall lining to prevent for example accumulation of dirt.

Note In case a semi-automatic cargo loading system (CLS) is installed in forward and aft cargo compartments, rubber seal profiles will be introduced in the area of CLS installation (not in bulk cargo compartment No. 5) as part of the CLS definition. For cargo configurations with CLS, TDU 02 will install rubber seal profiles also in the remaining bulk cargo compartment No. 5. EPAC selection mode Global CARGO

Rubber seal profiles are installed: • at the junction of the two sloped parts of the cargo compartment floor panels • at the junction of the sloped part of the cargo compartment floor panels next to side wall and the side wall liner panels.

Issue 6 Revision 1, January 2012

25.50.137

Page 254

[ 25-20]

Equipment/furnishings 25

A320 Family

Figure 25-4 - Rubber seal profile for cargo compartment floor panels

Additional rubber seal profiles

Basic rubber seal

Side wall lining

Cargo floor panels (sloped part) Cargo floor panels (horizontal part) Additional rubber seal profiles

Issue 6 Revision 1, January 2012

Basic rubber seal

25.50.137

Page 255

[ 25-21]

A320 Family

25 Equipment/furnishings Table 25-6 - Technical solutions description TDU

Title (Remarks)

Appl.

Weight (kg) MWE/OWE/APL

01

Installation of rubber seal profiles for floor panels in fwd and aft cargo holds

A318-100 A319-100 A320-200 A321-200

3.0/3.0/-3.0 4.0/4.0/-4.0 5.0/5.0/-5.0 7.0/7.0/-7.0

02

Installation of rubber seal profiles for floor panels in bulk cargo compartment No. 5

A319-100 A320-200 A321-200

2.0/2.0/-2.0 2.0/2.0/-2.0 2.0/2.0/-2.0

Equipment reference

Equipment supplier

Equipment PN

QTY

STS

Requires prior acceptance - CN25.52.304 or 404 - Installation of CLS.

Issue 6 Revision 1, January 2012

25.50.137

Page 256

[ 25-22]

Equipment/furnishings 25

A320 Family

Intentionally left blank

Issue 6 Revision 1, January 2012

25.50.137

Page 257

[ 25-23]

A320 Family

25 Equipment/furnishings

25.50.510 - Basic full bulk configuration selection in forward and aft cargo holds Objective To provide a full bulk configuration for lower deck cargo holds. Basic aircraft Full bulk configuration is installed, and structural provision is made for attaching optional divider nets in the forward and aft cargo holds (optional divider net positions in aft cargo hold only for A318 and A319). System provision for CLS in forward and aft cargo holds (A319, A320 and A321) plus minimum electrical provision for mechanized bulk loading system in forward and aft cargo holds (aft cargo hold only for A318 and A319) are installed.

• net attachment points located on the cargo hold floor and ceiling area at standard and optional divider net positions • tie-down points located on the cargo hold floor • load and net arrangement placards. Note In case of optional provision for an Additional Center Tank (ACT) in aft cargo hold, ACT support system components (roller tracks, latching devices etc. as applicable) shall be installed on the cargo hold floor (see details under appropriate TDUs). EPAC selection mode Global CARGO

Description The full bulk configuration consists mainly of: • basic cargo hold lining on ceiling, side and partition walls and basic cargo hold floor panels, capable of bulk loading up to a maximum average load density of 15 lb/cu ft • standard door and divider nets as required for full bulk transport • protection devices for rapid decompression panels at frame 24A

Issue 6 Revision 1, January 2012

25.50.510

Page 258

[ 25-24]

Equipment/furnishings 25

A320 Family

Figure 25-5 - Full bulk configuration in forward and aft cargo holds

Issue 6 Revision 1, January 2012

25.50.510

Page 259

[ 25-25]

A320 Family

25 Equipment/furnishings Table 25-7 - Technical solutions description TDU

Title (Remarks)

Appl.

Weight (kg) MWE/OWE/APL

01

Basic full bulk configuration without ACT provision

A318-100 A319-100 A320-200 A321-200

Negl./Negl./Negl. Negl./Negl./Negl. Negl./Negl./Negl. Negl./Negl./Negl.

02

Basic full bulk configuration with full provision for one ACT (A319/A320)

A319-100 A320-200

50.0/50.0/-50.0 50.0/50.0/-50.0

A321-200

50.0/50.0/-50.0

A319-100 A320-200

85.0/85.0/-85.0 85.0/85.0/-85.0

Equipment reference

Equipment supplier

Equipment PN

QTY

STS

Requires prior acceptance of CN28.11.133/02 - Full provision for installation of one ACT in aft cargo hold (A320), or CN28.11.133/03 - Full provision for installation of one ACT in aft cargo hold (A319). Due to ACT, lead-time constraints for this option are 9 months

03

Basic full bulk configuration with full provision for one ACT (A321) Requires prior acceptance of CN28.11.133/01 - Full provision for installation of one ACT in aft cargo hold (A321). Due to ACT, lead-time constraints for this option are 8 months

04

Basic full bulk configuration with full provision for two ACTs (A319/A320) Requires prior acceptance of CN28.11.140/01 - Full provision for installation of two/one ACTs in aft cargo hold (A319), or CN28.11.140/03 - Full provision for installation of two/one ACTs in aft cargo hold (A320). Due to ACT, lead-time constraints for this option are 9 months

Issue 6 Revision 1, January 2012

25.50.510

Page 260

[ 25-26]

Equipment/furnishings 25

A320 Family TDU

Title (Remarks)

Appl.

Weight (kg) MWE/OWE/APL

05

Basic full bulk configuration with full provision for two ACTs (A321)

A321-200

Equipment reference

Equipment supplier

Equipment PN

QTY

STS

85.0/85.0/-85.0

Requires prior acceptance of CN28.11.140/02 - Full provision for installation of two/one ACTs in aft cargo hold (A321). Due to ACT, lead-time constraints for this option are 8 months

Issue 6 Revision 1, January 2012

25.50.510

Page 261

[ 25-27]

A320 Family

25 Equipment/furnishings

25.50.520 - Installation of reinforced floor panels for heavy bulk usage in forward and aft cargo holds Objective To increase the durability / impact resistance of the cargo compartment floor panels if required by operation experiences of the airline. Basic aircraft Standard cargo floor panels capable of bulk loading 15 lb/cu ft are installed. Description The installation of reinforced cargo floor panels is limited to the flat floor to minimize the weight increase. The reinforced floor panels feature a modified build-up with two additional layers of prepeg with increased impact resistance. Note New panel layout and quantity depends on selected cargo compartment configuration such as standard bulk/optional CLS with or without ACT provision in aft cargo hold (see details under appropriate TDUs). EPAC selection mode Global CARGO

Issue 6 Revision 1, January 2012

25.50.520

Page 262

[ 25-28]

Equipment/furnishings 25

A320 Family

Figure 25-6 - Reinforced cargo floor panels C1

C24 A

C34

C47

C59

C65

C87

A320 Bulk cargo compartment Forward cargo hold Aft cargo hold

Prepegs (8 layers) ; anti-slip surface

Prepreg/honeycomb sandwich architecture

{

12.5 mm

Honeycomb

Reinforced cargo floor panel for heavy bulk usage (BCCS8 type, 15 lb/cu ft) Issue 6 Revision 1, January 2012

25.50.520

Page 263

[ 25-29]

A320 Family

25 Equipment/furnishings Table 25-8 - Technical solutions description TDU

Title (Remarks)

Appl.

Weight (kg) MWE/OWE/APL

01

Reinforced floor panels in fwd & aft cargo holds - with full bulk configuration

A318-100 A319-100 A320-200 A321-200

15.0/15.0/-15.0 15.0/15.0/-15.0 28.0/28.0/-28.0 35.0/35.0/-35.0

02

Reinforced floor panels in fwd & aft cargo holds - with CLS

A320-200 A321-200

27.0/27.0/-27.0

A319-100 A320-200

8.0/8.0/-8.0 21.0/21.0/-21.0

A321-200

27.0/27.0/-27.0

Equipment reference

Equipment supplier

Equipment PN

QTY

STS

Requires prior acceptance of CN25.52.304/01 - Semi-automatic CLS in fwd and aft cargo holds - without ACT provision (A320/A321)

03

Reinforced floor panels in fwd & aft cargo holds - with bulk & full prov. for one ACT (A319/ A320) Requires prior acceptance of CN28.11.133/03 - Full provision for installation of one ACT in aft cargo hold (A319), or CN28.11.133/02 - Full provision for installation of one ACT in aft cargo hold (A320). Due to ACT, lead-time constraints for this option are 9 months

04

Reinforced floor panels in fwd & aft cargo holds - with bulk & full provision for one ACT (A321) Requires prior acceptance of CN28.11.133/01 - Full provision for installation of one ACT in aft cargo hold (A321). Due to ACT, lead-time constraints for this option are 8 months

Issue 6 Revision 1, January 2012

25.50.520

Page 264

[ 25-30]

Equipment/furnishings 25

A320 Family TDU

Title (Remarks)

Appl.

Weight (kg) MWE/OWE/APL

05

Reinforced floor panels in fwd & aft cargo holds - with CLS & full provision for one ACT (A320)

A320-200

9.0/9.0/-9.0

A321-200

23.0/23.0/-23.0

A319-100 A320-200

4.0/4.0/-4.0 16.0/16.0/-16.0

A321-200

23.0/23.0/-23.0

Equipment reference

Equipment supplier

Equipment PN

QTY

STS

Requires prior acceptance of CN25.52.304/02 - Semi-automatic CLS in fwd and aft cargo holds - with full provision for one ACT (A320). Due to ACT, lead-time constraints for this option are 9 months

06

Reinforced floor panels in fwd & aft cargo holds - with CLS & full provision for one ACT (A321) Requires prior acceptance of CN25.52.304/03 - Semi-automatic CLS in fwd and aft cargo holds - with full provision for one ACT (A321). Due to ACT, lead-time constraints for this option are 8 months

07

Reinforced floor panels in fwd & aft cargo holds - with bulk & full prov. for two ACTs (A319/ A320) Requires prior acceptance of CN28.11.140/01 - Full provision for installation of two/one ACTs in aft cargo hold (A319), or CN28.11.140/03 - Full provision for installation of two/one ACTs in aft cargo hold (A320). Due to ACT, lead-time constraints for this option are 9 months

08

Reinforced floor panels in fwd & aft cargo holds - with bulk & full provision for two ACTs (A321) Requires prior acceptance of CN28.11.140/02 - Full provision for installation of two/one ACTs in aft cargo hold (A321). Due to ACT, lead-time constraints for this option are 8 months

Issue 6 Revision 1, January 2012

25.50.520

Page 265

[ 25-31]

A320 Family

25 Equipment/furnishings TDU

Title (Remarks)

Appl.

Weight (kg) MWE/OWE/APL

09

Reinforced floor panels in fwd & aft cargo holds - with CLS & full provision for two ACTs (A320)

A320-200

-22.0/-22.0/22.0

A321-200

-18.0/-18.0/18.0

Equipment reference

Equipment supplier

Equipment PN

QTY

STS

Requires prior acceptance of CN25.52.304/04 - Semi-automatic CLS in fwd and aft cargo holds - with full provision for two ACTs (A320). Due to ACT, lead-time constraints for this option are 9 months

10

Reinforced floor panels in fwd & aft cargo holds - with CLS & full provision for two ACTs (A321) Requires prior acceptance of CN25.52.304/05 - Semi-automatic CLS in fwd and aft cargo holds - with full provision for two ACTs (A321). Due to ACT, lead-time constraints for this option are 8 months

Issue 6 Revision 1, January 2012

25.50.520

Page 266

[ 25-32]

Equipment/furnishings 25

A320 Family

Intentionally left blank

Issue 6 Revision 1, January 2012

25.50.520

Page 267

[ 25-33]

A320 Family

25 Equipment/furnishings

25.52.190 - System provision for mechanized bulk loading systems in forward cargo hold (A320) Objective for A320-200 To provide system provision adapting the installation of an in-plane mechanized bulk loading system to increase the efficiency of manual loading and stacking of bulk cargo and baggage. Basic aircraft for A320-200 Full bulk configuration plus system provision for CLS, minimum electrical provision for mechanized bulk loading system, and structural provision for attaching optional divider nets in forward and aft cargo holds.

• removal and/or replacement of divider nets where applicable • adequate markings according to the new cargo compartment configuration. Note for A320-200 Research has determined that manual loading of loads is a primary cause of personnel injuries, causing in addition damage to the loaded baggage and the aircraft. EPAC selection mode Global CARGO

Description for A320-200 The system provision consists mainly of: • installation of structural reinforcements such as supports, framework, mounting fittings and fasteners where applicable • installation of brackets and consoles for control panels and wall sockets • installation of additional tie down fittings where applicable • electrical system connection to existing provision • installation of electrical door circuit control • modified linings, ceiling and floor panels where applicable

Issue 6 Revision 1, January 2012

25.52.190

Page 268

[ 25-34]

Equipment/furnishings 25

A320 Family

Figure 25-7 - System provision for mechanized bulk loading in fwd cargo hold A320 forward cargo hold shown

System provision

Relocation of divider net

Sliding Carpet System (SCS)

A320 forward cargo hold - System provision for mechanized bulk loading systems. - Structural provision/reinforcements where applicable. - Additional electrical provision where applicable.

Issue 6 Revision 1, January 2012

25.52.190

Page 269

[ 25-35]

A320 Family

25 Equipment/furnishings Table 25-9 - Technical solutions description TDU

Title (Remarks)

Appl.

Weight (kg) MWE/OWE/APL

02

System provision for mechanized bulk loading system in fwd cargo hold - sliding carpet system

Issue 6 Revision 1, January 2012

A320-200

Equipment reference

Equipment supplier

Equipment PN

QTY

STS

7.0/7.0/-7.0

25.52.190

Page 270

[ 25-36]

Equipment/furnishings 25

A320 Family

Intentionally left blank

Issue 6 Revision 1, January 2012

25.52.190

Page 271

[ 25-37]

A320 Family

25 Equipment/furnishings

25.52.191 - System provision for mechanized bulk loading systems in forward cargo hold (A321) Objective for A321-200 To provide system provision adapting the installation of an in-plane mechanized bulk loading system to increase the efficiency of manual loading and stacking of bulk cargo and baggage. Basic aircraft for A321-200 Full bulk configuration plus system provision for CLS, minimum electrical provision for mechanized bulk loading system, and structural provision for attaching optional divider nets in forward and aft cargo holds.

• removal and/or replacement of divider nets where applicable • adequate markings according to the new cargo compartment configuration. Note for A321-200 Research has determined that manual loading of loads is a primary cause of personnel injuries, causing in addition damage to the loaded baggage and the aircraft. EPAC selection mode Global CARGO

Description for A321-200 The system provision consists mainly of: • installation of structural reinforcements such as supports, framework, mounting fittings and fasteners where applicable • installation of brackets and consoles for control panels and wall sockets • installation of additional tie down fittings where applicable • electrical system connection to existing provision • installation of electrical door circuit control • modified linings, ceiling and floor panels where applicable

Issue 6 Revision 1, January 2012

25.52.191

Page 272

[ 25-38]

Equipment/furnishings 25

A320 Family

Table 25-10 - Technical solutions description TDU

Title (Remarks)

Appl.

Weight (kg) MWE/OWE/APL

02

System provision for mechanized bulk loading system in fwd cargo hold - sliding carpet system

Issue 6 Revision 1, January 2012

A321-200

Equipment reference

Equipment supplier

Equipment PN

QTY

STS

12.0/12.0/-12.0

25.52.191

Page 273

[ 25-39]

A320 Family

25 Equipment/furnishings

25.52.202 - Installation of mechanized bulk loading system in forward cargo hold sliding carpet system Objective for A320-200 and A321-200 To install the Sliding Carpet System (SCS), an in-plane mechanized bulk loading system, on system provisions for SCS. Mechanized bulk loading systems increase bulk cargo loading efficiency, reduce manpower and bulk cargo loading time.

Basic aircraft for A320-200 and A321-200 Full bulk configuration is installed, and structural provision is made for attaching optional divider nets in the fwd cargo hold. System provision for CLS in fwd cargo hold plus minimum electrical provision for mechanized bulk loading system in fwd cargo hold is made.

Description for A320-200 and A321-200 An electrically powered Sliding Carpet System is installed in fwd cargo hold in the area from the cargo door (frame C28) to the aft partition wall.

Issue 6 Revision 1, January 2012

This modification mainly covers the following tasks: • Installation of: • flex-down support • support panels • guide unit panels • drive unit panel • ramp • movable bulkhead • carpet • side guides • control box • cargo compartment placards • relocation of cargo compartment divider nets (where applicable) • adaptation of manuals. Note for A320-200 and A321-200 • research has determined that manual loading of loads is a primary cause of personnel injuries, causing in addition damage to the loaded baggage and the aircraft • for A320-200, requires prior acceptance of CN25.52.190/02 - System provision for mechanized bulk loading system in fwd cargo hold - sliding carpet system

25.52.202

Page 274

[ 25-40]

Equipment/furnishings 25

A320 Family

25.52.202 - Installation of mechanized bulk loading system in forward cargo hold sliding carpet system (Continued) • for A321-200, requires prior acceptance of CN25.52.191/02 - System provision for mechanized bulk loading system in fwd cargo hold - sliding carpet system. EPAC selection mode Global CARGO

Issue 6 Revision 1, January 2012

25.52.202

Page 275

[ 25-41]

A320 Family

25 Equipment/furnishings

Figure 25-8 - Mechanized bulk loading system in fwd cargo hold - sliding carpet

Control box installed at ceiling FWD cargo door

Issue 6 Revision 1, January 2012

25.52.202

Page 276

[ 25-42]

Equipment/furnishings 25

A320 Family

Table 25-11 - Technical solutions description TDU

Title (Remarks)

Appl.

Weight (kg) MWE/OWE/APL

01

Mechanized bulk loading system (sliding carpet with tiedown) in fwd cargo hold TELAIR (A320)

Equipment reference

Equipment supplier

Equipment PN

QTY

STS

A320-200

161.0/161.0/-161.0

Sliding carpet system with tie-down

TELAIR INTERNATIONAL

20-20200-201

1

BFE

A320-200

153.0/153.0/-153.0

Sliding carpet system without tiedown

TELAIR INTERNATIONAL

20-20200-202

1

BFE

A321-200

240.0/240.0/-240.0

Sliding carpet system

TELAIR INTERNATIONAL

21-20200-800

1

BFE

Only applicable in conjunction with basic system provision for cargo compartment convertibility. Sliding carpet system comprises tie-down capability.

02

Mechanized bulk loading system (sliding carpet without tiedown) in fwd cargo hold TELAIR (A320) Only applicable in conjunction with basic system provision for cargo compartment convertibility.

03

Mechanized bulk loading system (sliding carpet without tiedown) in fwd cargo hold TELAIR (A321)

Issue 6 Revision 1, January 2012

25.52.202

Page 277

[ 25-43]

A320 Family

25 Equipment/furnishings

25.52.204 - System provision for mechanized bulk loading systems in aft cargo hold (A319/A320) Objective for A319-100 and A320-200 To provide system provision adapting the installation of an in-plane mechanized bulk loading system to increase the efficiency of manual loading and stacking of bulk cargo and baggage. Basic aircraft for A319-100 and A320-200 Full bulk configuration plus system provision for CLS, minimum electrical provision for mechanized bulk loading system and structural provision for attaching optional divider nets in the forward and aft cargo holds. Description for A319-100 and A320-200 The system provision consists mainly of : • installation of structural reinforcements such as supports, framework, mounting fittings and fasteners where applicable • installation of brackets and consoles for control panels and wall sockets • installation of additional tie down fittings where applicable • electrical system connection on existing provision • installation of electrical door circuit control • modified linings, ceiling and floor panels where applicable

Issue 6 Revision 1, January 2012

• removal and/or replacement of divider nets where applicable • adequate markings according to the new cargo compartment configuration. Note for A319-100 and A320-200 • research has determined that manual loading of loads is a primary cause of personnel injuries, causing in addition damage to the loaded baggage and the aircraft • incompatible with Additional Center Tank (ACT) in aft cargo hold. EPAC selection mode Global CARGO

25.52.204

Page 278

[ 25-44]

Equipment/furnishings 25

A320 Family

Figure 25-9 - System provision for mechanized bulk loading in aft cargo hold A320 aft cargo hold shown

System provision

Relocation of divider net

Sliding Carpet System (SCS)

A319/A320 aft cargo hold - System provision for mechanized bulk loading systems. - Structural provision/reinforcements where applicable. - Additional electrical provision where applicable.

Issue 6 Revision 1, January 2012

25.52.204

Page 279

[ 25-45]

A320 Family

25 Equipment/furnishings Table 25-12 - Technical solutions description TDU

Title (Remarks)

Appl.

Weight (kg) MWE/OWE/APL

02

System provision for mechanized bulk loading system in aft cargo hold - sliding carpet system

Issue 6 Revision 1, January 2012

A319-100 A320-200

Equipment reference

Equipment supplier

Equipment PN

QTY

STS

7.0/7.0/-7.0 8.0/8.0/-8.0

25.52.204

Page 280

[ 25-46]

Equipment/furnishings 25

A320 Family

Intentionally left blank

Issue 6 Revision 1, January 2012

25.52.204

Page 281

[ 25-47]

A320 Family

25 Equipment/furnishings

25.52.205 - System provision for mechanized bulk loading systems in aft cargo hold (A321) Objective for A321-200 To provide system provision adapting the installation of an in-plane mechanized bulk loading system to increase the efficiency of manual loading and stacking of bulk cargo and baggage. Basic aircraft for A321-200 Full bulk configuration plus system provision for CLS, minimum electrical provision for mechanized bulk loading system and structural provision for attaching optional divider nets in the forward and aft cargo holds. Description for A321-200 The system provision consists mainly of : • installation of structural reinforcements such as supports, framework, mounting fittings and fasteners where applicable • installation of brackets and consoles for control panels and wall sockets • installation of additional tie down fittings where applicable • electrical system connection on existing provision • installation of electrical door circuit control • modified linings, ceiling and floor panels where applicable

Issue 6 Revision 1, January 2012

• removal and/or replacement of divider nets where applicable • adequate markings according to the new cargo compartment configuration. Note for A321-200 • research has determined that manual loading of loads is a primary cause of personnel injuries, causing in addition damage to the loaded baggage and the aircraft • incompatible with Additional Center Tank (ACT) in aft cargo hold. EPAC selection mode Global CARGO

25.52.205

Page 282

[ 25-48]

Equipment/furnishings 25

A320 Family

Table 25-13 - Technical solutions description TDU

Title (Remarks)

Appl.

Weight (kg) MWE/OWE/APL

02

System provision for mechanized bulk loading system in aft cargo hold - sliding carpet system

Issue 6 Revision 1, January 2012

A321-200

Equipment reference

Equipment supplier

Equipment PN

QTY

STS

10.0/10.0/-10.0

25.52.205

Page 283

[ 25-49]

A320 Family

25 Equipment/furnishings

25.52.212 - Installation of mechanized bulk loading system in aft cargo hold - sliding carpet system Objective for A319-100 and A320-200 and A321-200 To install the sliding carpet system, an in-plane mechanized bulk loading system, on dedicated system provision. Mechanized bulk loading systems increase the bulk cargo loading efficiency, reduce manpower and times for bulk cargo loading.

Basic aircraft for A319-100 and A320-200 and A321200 Full bulk configuration is installed, and structural provision is made for attaching optional divider nets in the aft cargo hold. System provision for CLS in aft cargo hold (A319/A320) plus minimum electrical provision for mechanized bulk loading system in aft cargo hold are made.

Description for A319-100 and A320-200 and A321200 An electrically powered sliding carpet system is installed in aft cargo hold in the area from the forward partition wall to the cargo door area.

Issue 6 Revision 1, January 2012

This modification mainly covers the following tasks: - Installation of: • flex-down support • support panels • guide unit panels • drive unit panel • ramp • movable bulkhead • carpet • side guides • control box • cargo compartment placards. - Relocation of cargo compartment divider nets (where applicable). - Adaptation of manuals. Note for A319-100 and A320-200 and A321-200 • research has determined that manual loading of loads is a primary cause of personnel injuries, causing in addition damage to the loaded baggage and the aircraft • for A319 and A320, requires prior acceptance of CN25.52.204/02 - System provision for mechanized bulk loading systems in aft cargo hold - sliding carpet system

25.52.212

Page 284

[ 25-50]

Equipment/furnishings 25

A320 Family

25.52.212 - Installation of mechanized bulk loading system in aft cargo hold - sliding carpet system (Continued) • for A321, requires prior acceptance of CN25.52.205/ 02 - System provision for mechanized bulk loading systems in aft cargo hold - sliding carpet system. EPAC selection mode Global CARGO

Issue 6 Revision 1, January 2012

25.52.212

Page 285

[ 25-51]

A320 Family

25 Equipment/furnishings

Figure 25-10 - Sliding carpet system in aft cargo hold Aft cargo hold

r

oo

Aft

Issue 6 Revision 1, January 2012

d rgo

ca

Control box installed at ceiling

25.52.212

Page 286

[ 25-52]

Equipment/furnishings 25

A320 Family

Table 25-14 - Technical solutions description TDU

Title (Remarks)

Appl.

Weight (kg) MWE/OWE/APL

02

Installation of mechanized bulk loading system (sliding carpet) in aft cargo hold - A319 TELAIR

Equipment reference

Equipment supplier

Equipment PN

QTY

STS

A319-100

143.0/143.0/-143.0

Sliding carpet system

TELAIR INTERNATIONAL

19-10400-200

1

BFE

A320-200

156.0/156.0/-156.0

Sliding carpet system

TELAIR INTERNATIONAL

20-10400-202

1

BFE

A321-200

190.0/190.0/-190.0

Sliding carpet system

TELAIR INTERNATIONAL

21-10400-800

1

BFE

Requires prior acceptance of CN25.52.204/02 - System provision for mechanized bulk loading system in aft cargo hold - sliding carpet system

03

Installation of mechanized bulk loading system (sliding carpet) in aft cargo hold - A320 TELAIR Requires prior acceptance of CN25.52.204/02 - System provision for mechanized bulk loading system in aft cargo hold - sliding carpet system

04

Installation of mechanized bulk loading system (sliding carpet) in aft cargo hold - A321 TELAIR Requires prior acceptance of CN25.52.205/02 - System provision for mechanized bulk loading system in aft cargo hold - sliding carpet system

Issue 6 Revision 1, January 2012

25.52.212

Page 287

[ 25-53]

A320 Family

25 Equipment/furnishings

25.52.304 - Installation of semi-automatic Cargo Loading System (CLS) in forward and aft cargo holds (A320/A321) Objective for A320-200 and A321-200 To improve the turnround efficiency by reducing the cargo loading/unloading time (with a single loader), to minimize the risk of injuries to bulk loading staff and to improve the customer services. Basic aircraft for A320-200 and A321-200 Full bulk configuration, system provision for CLS, minimum electrical provision for mechanized bulk loading systems, and structural provision for attaching optional divider nets in the forward and aft cargo holds. The loading/unloading time is significantly longer due to the various factors involved with manual loading. Description for A320-200 and A321-200 An electrically powered, semi-automatic CLS is installed in the forward and aft cargo holds allowing the transport of the following ULDs: Containers: NAS 3610: 2K2C (60.4 in x 61.5 in), IATA contour AKG/ AKH. Pallets: NAS 3610: 2K2C/2K3P (60.4 in x 61.5 in), IATA contour PK/PKx. Issue 6 Revision 1, January 2012

The max.gross weight of each ULD is limited for the Single Aisle CLS to 2500 lbs (1134 kg). A320: • 3 containers or pallets in forward cargo hold • 4 containers or pallets in aft cargo hold. A321: • 5 containers or pallets in forward cargo hold • 5 containers or pallets in aft cargo hold. The modification consists of: • replacement of the standard bulk floor panels, sidewall/ceiling panels by light weight panels • removal of protection devices for rapid decompression panels at frame 24 A • installation of a drainage system in conjunction with the CLS • structural modifications allowing CLS installation and system operation • installation of modified placards according to the new cargo hold configuration • installation of the CLS and the following associated system components: 1) Restraint, guidance: • guides, latches and endstops.

25.52.304

Page 288

[ 25-54]

Equipment/furnishings 25

A320 Family

25.52.304 - Installation of semi-automatic Cargo Loading System (CLS) in forward and aft cargo holds (A320/A321) (Continued) 2) Transport: • roller tracks, ballmats. 3) Conveyance: • power drive units, control panels, proximity switches. Note for A320-200 and A321-200 Research has determined that manual loading of loads is a primary cause of personnel injuries, causing in addition damage to the loaded baggage and the aircraft. EPAC selection mode Global CARGO

Issue 6 Revision 1, January 2012

25.52.304

Page 289

[ 25-55]

A320 Family

25 Equipment/furnishings

Figure 25-11 - Semi-automatic CLS for forward and aft cargo holds 34 28

59 56

31 52 A

24 A 50

A320 47

Semi-automatic CLS for forward cargo hold compartment No 1

Semi-automatic CLS for aft cargo hold compartment No 3 and No 4

35 2

59 56

34

52 A

28

A321

31

24 A

50 47 5 47 2

Semi-automatic CLS for forward cargo hold compartment No 1 and No 2

Issue 6 Revision 1, January 2012

Semi-automatic CLS for aft cargo hold compartment No 3 and No 4

25.52.304

Page 290

[ 25-56]

Equipment/furnishings 25

A320 Family

Table 25-15 - Technical solutions description TDU

Title (Remarks)

Appl.

Weight (kg) MWE/OWE/APL

01

Semi-automatic CLS in fwd and aft cargo holds - without ACT provision (A320/A321)

A320-200 A321-200

122.0/122.0/-122.0 102.0/102.0/-102.0

02

Semi-automatic CLS in fwd and aft cargo holds - with full provision for one ACT (A320)

A320-200

153.0/153.0/-153.0

A321-200

133.0/133.0/-133.0

A320-200

177.0/177.0/-177.0

Equipment reference

Equipment supplier

Equipment PN

QTY

STS

Requires prior acceptance of CN28.11.133/02 - Full provision for installation of one ACT in aft cargo hold (A320) Due to ACT, lead-time constraints for this option are 9 months.

03

Semi-automatic CLS in fwd and aft cargo holds - with full provision for one ACT (A321) Requires prior acceptance of CN28.11.133/01 - Full provision for installation of one ACT in aft cargo hold (A321). Due to ACT, lead-time constraints for this option are 8 months

04

Semi-automatic CLS in fwd and aft cargo holds - with full provision for two ACTs (A320) Requires prior acceptance of CN28.11.140/03 - Full provision for installation of two/one ACTs in aft cargo hold (A320) Due to ACT, lead-time constraints for this option are 9 months.

Issue 6 Revision 1, January 2012

25.52.304

Page 291

[ 25-57]

A320 Family

25 Equipment/furnishings TDU

Title (Remarks)

Appl.

Weight (kg) MWE/OWE/APL

05

Semi-automatic CLS in fwd and aft cargo holds - with full provision for two ACTs (A321)

A321-200

Equipment reference

Equipment supplier

Equipment PN

QTY

STS

157.0/157.0/-157.0

Requires prior acceptance of CN28.11.140/02 - Full provision for installation of two/one ACTs in aft cargo hold (A321). Due to ACT, lead-time constraints for this option are 8 months

Issue 6 Revision 1, January 2012

25.52.304

Page 292

[ 25-58]

Equipment/furnishings 25

A320 Family

Intentionally left blank

Issue 6 Revision 1, January 2012

25.52.304

Page 293

[ 25-59]

A320 Family

25 Equipment/furnishings

25.52.310 - Fixed provision for occasional bulk capability in forward and aft cargo holds (A320/A321) Objective for A320-200 and A321-200 To allow occasional loading of bulk cargo on top of the installed Cargo Loading System (CLS). Basic aircraft for A320-200 and A321-200 Full bulk configuration, structural provision for attaching optional divider nets in the forward and aft cargo holds plus system provision for CLS and minimum electrical provisions for mechanized bulk loading systems. Description for A320-200 and A321-200 Fixed provision for occasional bulk loading are provided in addition to an installed semi-automatic CLS (optional). Occasional bulk loading applies on routes/destinations, where: • no ground service equipment is available • no ULDs are available • baggage requirements call for maximum volume utilization of the cargo holds.

• adequate load placarding and markings according to the new cargo compartment configuration. Note for A320-200 and A321-200 • the cargo holds are capable for bulk loading up to an average bulk loading density of 10 lb/cu ft (160 kg/cu m) • the operation in occasional bulk mode requires the installation of divider nets and door nets as per WBM. These nets are not part of this provision but can be provided by Airbus on specific request or can be ordered directly at the net manufacturer • with reference to the light weight cargo lining and floor as part of the CLS option, occasional bulk loading shall not exceed 60 flights per year. More frequent operation in occasional bulk mode increases the possibility of damage to lining and floor panels • restrictions apply for individual items of load exceeding the weight of 110 lb (50 kg). EPAC selection mode Global CARGO

The fixed provision consists mainly of: • protection devices for the rapid decompression panels and a fender at frame 24

Issue 6 Revision 1, January 2012

25.52.310

Page 294

[ 25-60]

Equipment/furnishings 25

A320 Family

Figure 25-12 - Forward and aft cargo holds configuration Basic divider net 34 28

59 56

31 52 A

24 A

A320

50 47

Basic divider net Door nets and divider nets are not provided with this option.

35

59

5

56

35 2

52 A

34 28

31 50

24

A321

A

47 5

47 2

Issue 6 Revision 1, January 2012

25.52.310

Page 295

[ 25-61]

A320 Family

25 Equipment/furnishings Table 25-16 - Technical solutions description TDU

Title (Remarks)

Appl.

Weight (kg) MWE/OWE/APL

01

Fixed provision for occasional bulk capability in forward and aft cargo holds (A320/A321)

A320-200 A321-200

Equipment reference

Equipment supplier

Equipment PN

QTY

STS

9.0/9.0/-9.0 11.0/11.0/-11.0

Requires prior acceptance of CN25.52.304 Installation of semi-automatic Cargo Loading System (CLS) in forward and aft cargo holds

Issue 6 Revision 1, January 2012

25.52.310

Page 296

[ 25-62]

Equipment/furnishings 25

A320 Family

Intentionally left blank

Issue 6 Revision 1, January 2012

25.52.310

Page 297

[ 25-63]

A320 Family

25 Equipment/furnishings 25.52.315 - Full electrical provision for semi-automatic CLS Objective for A319-100 and A320-200 and A321-200 To facilitate later retrofit installation of a semi-automatic Cargo Loading System (CLS).

Note for A319-100 and A320-200 and A321-200 The additional circuit breakers are secured by clips to prevent power on system.

Basic aircraft for A319-100 and A320-200 and A321200 Full bulk configuration, system provision for CLS, electrical provision for mechanized bulk loading system and structural provision for attaching optional divider nets in the forward and aft cargo holds.

EPAC selection mode Global CARGO

Description for A319-100 and A320-200 and A321200 The modification consists of: • installation of new wire harnesses (wire bridges) on the main terminal boards 2820VT (forward cargo hold) and 7506VT (aft cargo hold) for power supply and control function • installation of modified circuit breaker panels 2000VU (for forward cargo hold) and 2001VU (for aft cargo hold) by including two additional circuit breakers per CB panel for power supply and control function.

Issue 6 Revision 1, January 2012

25.52.315

Page 298

[ 25-64]

Equipment/furnishings 25

A320 Family

Table 25-17 - Technical solutions description TDU

Title (Remarks)

Appl.

Weight (kg) MWE/OWE/APL

01

Full electrical provision for semi-automatic CLS

Issue 6 Revision 1, January 2012

A319-100 A320-200 A321-200

Equipment reference

Equipment supplier

Equipment PN

QTY

STS

1.0/1.0/-1.0 1.0/1.0/-1.0 1.0/1.0/-1.0

25.52.315

Page 299

[ 25-65]

A320 Family

25 Equipment/furnishings

25.52.404 - Installation of Cargo Loading System (CLS) with full bulk capability in fwd and aft cargo holds Objective for A319-100 and A320-200 and A321-200 To provide operational capability either to transport ULDs and/or bulk freight up to a maximum average density of 15 lb/cu ft.

• fender for protection devices for the rapid decompression at frame 24 A. EPAC selection mode Global CARGO

Basic aircraft for A319-100 and A320-200 and A321200 Full bulk configuration and structural provision for attaching optional divider nets in the forward and aft cargo holds. System provision for CLS plus minimum electrical provision for mechanized bulk loading system. Description for A319-100 and A320-200 and A321200 The modification consists of the installation of: • electrically powered semi-automatic CLS • additional tie-down fittings • door nets with stanchions and divider nets for the forward and aft cargo holds • reinforced cargo floor panels for heavy bulk usage for the forward and aft cargo holds, flat parts only • drainage system • side wall/ceiling panels for bulk loading in the forward and aft cargo holds

Issue 6 Revision 1, January 2012

25.52.404

Page 300

[ 25-66]

Equipment/furnishings 25

A320 Family

Figure 25-13 - CLS with full bulk capability

Installation of full bulk sidewalls/ceiling panels Basic CLS provisions

CLS + full bulk (nets included)

AKH

or ACT

AKH

AKH

Reinforced cargo floor

A321 A320

A319

Issue 6 Revision 1, January 2012

25.52.404

Page 301

[ 25-67]

A320 Family

25 Equipment/furnishings Table 25-18 - Technical solutions description TDU

Title (Remarks)

Appl.

Weight (kg) MWE/OWE/APL

01

CLS with full bulk capability in fwd and aft cargo holds - without ACT provision

A319-100 A320-200 A321-200

134.0/134.0/-134.0 160.0/160.0/-160.0 190.0/190.0/-190.0

02

CLS with full bulk capability in fwd and aft cargo holds - with full provision for one ACT (A320)

A320-200

175.0/175.0/-175.0

A321-200

201.0/201.0/-201.0

A320-200

196.0/196.0/-196.0

Equipment reference

Equipment supplier

Equipment PN

QTY

STS

Requires prior acceptance of CN28.11.133/02 - Full provision for installation of one ACT in aft cargo hold (A320). Due to ACT, lead-time constraints for this option are 9 months

03

CLS with full bulk capability in fwd and aft cargo holds - with full provision for one ACT (A321) Requires prior acceptance of CN28.11.133/01 - Full provision for installation of one ACT in aft cargo hold (A321) Due to ACT, lead-time constraints for this option are 8 months

04

CLS with full bulk capability in fwd and aft cargo holds - with full provision for two ACTs (A320) Requires prior acceptance of CN28.11.140/03 - Full provision for installation of two/one ACTs in aft cargo hold (A320). Due to ACT, lead-time constraints for this option are 9 months

Issue 6 Revision 1, January 2012

25.52.404

Page 302

[ 25-68]

Equipment/furnishings 25

A320 Family TDU

Title (Remarks)

Appl.

Weight (kg) MWE/OWE/APL

05

CLS with full bulk capability in fwd and aft cargo holds - with full provision for two ACTs (A321)

A321-200

Equipment reference

Equipment supplier

Equipment PN

QTY

STS

223.0/223.0/-223.0

Requires prior acceptance of CN28.11.140/02 - Full provision for installation of two/one ACTs in aft cargo hold (A321). Due to ACT, lead-time constraints for this option are 8 months

Issue 6 Revision 1, January 2012

25.52.404

Page 303

[ 25-69]

A320 Family

25 Equipment/furnishings

25.52.407 - Bulk loading capability in aft cargo hold door area behind two ULDs (A319) Objective for A319-100 To provide bulk loading capability in aft cargo door area for configuration with two ULDs loaded. Basic aircraft for A319-100 Full bulk configuration in fwd and aft cargo hold and structural provision for attaching optional divider nets in aft cargo hold. System provision for CLS in fwd and aft cargo hold plus minimum electrical provisions for mechanized bulk loading systems in aft cargo hold. Description for A319-100 This option provides the capability to load the remaining space in the aft cargo door area with bulk, when two ULDs are transported on position 41 and 42.

• Deletion of the standard divider net at frame 59 and installation of a new divider net at frame 60 • Installation of modified cargo compartment placards • Adaptation of manuals Note for A319-100 With this modification, the new divider net position at frame 60 will separate aft cargo compartment No. 4 from the bulk compartment No. 5 for ULD and for full bulk transportation. EPAC selection mode Global CARGO

Due to the relocation of the standard divider net position from frame 59 to 60, this new net section is enlarged to offer improved cargo loading conditions. The modification consists of: • Installation of a new divider net at frame 57

Issue 6 Revision 1, January 2012

25.52.407

Page 304

[ 25-70]

Equipment/furnishings 25

A320 Family

Figure 25-14 - Bulk loading in aft cargo hold door area behind two ULDs (A319) Net configuration with two ULDs loaded

Net configuration for full bulk cargo loading complete aft cargo hold

Issue 6 Revision 1, January 2012

25.52.407

Page 305

[ 25-71]

A320 Family

25 Equipment/furnishings Table 25-19 - Technical solutions description TDU

Title (Remarks)

Appl.

Weight (kg) MWE/OWE/APL

01

Bulk loading capability in aft cargo hold door area behind two ULDs (A319)

Issue 6 Revision 1, January 2012

A319-100

Equipment reference

Equipment supplier

Equipment PN

QTY

STS

4.0/4.0/-4.0

25.52.407

Page 306

[ 25-72]

Equipment/furnishings 25

A320 Family

Intentionally left blank

Issue 6 Revision 1, January 2012

25.52.407

Page 307

[ 25-73]

A320 Family

25 Equipment/furnishings

25.52.410 - Full provision for installation of special container in aft cargo hold, door area (A319) Objective for A319-100 To provide an additional loading position for a special container in the cargo door area of compartment 4. This additional container can be used as a last-minute baggage container and will optimize the Demand Driven Dispatch reliability of an airline operating the AIRBUS Single Aisle aircraft family. Basic aircraft for A319-100 Full bulk configuration plus system provision for CLS, minimum electrical provision for mechanized bulk loading systems and structural provision for attaching optional divider nets in the forward and aft cargo holds. Description for A319-100 This option provides the capability to transport a special container in the cargo door area between frame 56A and frame 59 with the semi-automatic CLS installed.

The loading and unloading of the special container is done manually. The modification consists of: • structural reinforcements • installation of an additional lowerable Z-latch • installation of retractable, electrically powered front roller at frame 58 • modification of ballmat • attachment of modified placards and markings according to the new cargo hold configuration. Note for A319-100 Requires prior acceptance of CN25.52.404/01 - CLS with full bulk capability in fwd and aft cargo holds - without ACT provision. EPAC selection mode Global CARGO

This special LD3/40-45 container has a baseplate of 39.75 in x 61.5 in with IATA contour H and can be loaded up to a max. gross weight of 1 660 lb (753 kg).

Issue 6 Revision 1, January 2012

25.52.410

Page 308

[ 25-74]

Equipment/furnishings 25

A320 Family

Figure 25-15 - Additional container in aft cargo hold (A319) 96 in (2438 mm)

45 in (1143 mm) 61.5 in (1562 mm) 39.75 in (1009,7 mm)

Additional container A319 Type : LD3 - 40/45 IATA contour H

Issue 6 Revision 1, January 2012

Internal volume

:

80 cu ft (2,3 cu m)

Tare weight

:

110 to 180 lb (50 to 80 kg)

MGW

:

1660 lb (753 kg)

25.52.410

Page 309

[ 25-75]

A320 Family

25 Equipment/furnishings Table 25-20 - Technical solutions description TDU

Title (Remarks)

Appl.

Weight (kg) MWE/OWE/APL

01

Full provision for installation of special container in aft cargo hold, door area (A319)

Issue 6 Revision 1, January 2012

A319-100

Equipment reference

Equipment supplier

Equipment PN

QTY

STS

3.0/3.0/-3.0

25.52.410

Page 310

[ 25-76]

Equipment/furnishings 25

A320 Family

Intentionally left blank

Issue 6 Revision 1, January 2012

25.52.410

Page 311

[ 25-77]

A320 Family

25 Equipment/furnishings

25.52.500 - Installation of continuous side guides in forward cargo hold Objective for A319-100 and A320-200 and A321-200 To ease the guidance of netted pallets or slightly dished pallets. Basic aircraft for A319-100 and A320-200 and A321200 Full bulk configuration, system provision for CLS, minimum electrical provision for mechanized bulk loading system and structural provision for attaching optional divider nets in the forward and aft cargo holds. Description for A319-100 and A320-200 and A321200 - For A319: • three guides are installed between frame 28 and 31 on the RH side of the hold • three guides are installed between frame 24A and frame 31 on the LH side of the hold.

- For A321: • twelve guides are installed between frame 28 and 35.5 on the RH side of the hold • twelve guides are installed between frame 26 and frame 35.5 on the LH side of the hold. Note for A319-100 and A320-200 and A321-200 Requires prior acceptance of CLS in forward and aft cargo holds, which installs: YZ latches including structural provision for continuous side guides, and two guides opposite to the door. The optional continuous side guides are specifically recommended when using netted pallets to prevent entanglement of the net meshes on the fixed YZ latches. EPAC selection mode Global CARGO

- For A320: • six guides are installed between frame 28 and 34 on the RH side of the hold • six guides are installed between frame 24A and frame 34 on the LH side of the hold.

Issue 6 Revision 1, January 2012

25.52.500

Page 312

[ 25-78]

Equipment/furnishings 25

A320 Family

Figure 25-16 - Continuous side guides in forward cargo hold 35

A319

5

A321

35 2

28

34 28 24 A

31

24 A

e

es

12

id gu

H nR

31

sid

ide

Hs

o

es

uid

3g

R on

e

12

n so

LH

sid

e

H

gu

ide

es

L on

sid

uid

3g

34 28

31

24 A

ide

Hs

es

uid

6g

R on

A320

ide

Hs

es

uid

6g

Issue 6 Revision 1, January 2012

25.52.500

L on

Page 313

[ 25-79]

A320 Family

25 Equipment/furnishings Table 25-21 - Technical solutions description TDU

Title (Remarks)

Appl.

Weight (kg) MWE/OWE/APL

01

Installation of continuous side guides in forward cargo hold

Issue 6 Revision 1, January 2012

A319-100 A320-200 A321-200

Equipment reference

Equipment supplier

Equipment PN

QTY

STS

8.0/8.0/-8.0 12.0/12.0/-12.0 21.0/21.0/-21.0

25.52.500

Page 314

[ 25-80]

Equipment/furnishings 25

A320 Family

Intentionally left blank

Issue 6 Revision 1, January 2012

25.52.500

Page 315

[ 25-81]

A320 Family

25 Equipment/furnishings

25.52.511 - Installation of continuous side guides in aft cargo hold Objective for A319-100 and A320-200 and A321-200 To ease guidance of netted pallets or slightly dished pallets. Basic aircraft for A319-100 and A320-200 and A321200 Full bulk configuration, system provision for CLS, electrical provision for mechanized bulk loading system and structural provision for attaching optional divider nets in the forward and aft cargo holds. Description for A319-100 and A320-200 and A321200 For A319: • RH side : five guides are installed between frame 47/ 51 and frame 55A • LH side : five guides are installed between frame 47/ 51 and frame 56 . For A320: • RH side : six guides are installed between frame 47 and frame 52A • RH side : three guides are installed between frame 56 and frame 58 • LH side : nine guides are installed between frame 47 and frame 58. Issue 6 Revision 1, January 2012

For A321: • RH side : nine guides are installed between frame 47.2 and frame 52A • RH side : three guides are installed between frame 56 and frame 58 • LH side : twelve guides are installed between frame 47.2 and frame 58. Note for A319-100 and A320-200 and A321-200 • requires prior acceptance of CLS in forward and aft cargo holds, which installs: YZ latches including structural provision for continuous side guides, and two guides opposite to the door. The optional continuous side guides are specifically recommended when using netted pallets to prevent entanglement of the net meshes on the fixed YZ latches • in case of optional provision for ACTs installed, the number of continuous side guides will change • on A319, not compatible with CN28.11.140/01 - Full provision for installation of two/one ACTs in aft cargo hold (A319). EPAC selection mode Global CARGO

25.52.511

Page 316

[ 25-82]

Equipment/furnishings 25

A320 Family

Figure 25-17 - Continuous side guides in aft cargo hold 59

A321

59

A319

56 52 A

55 A

50 47

ide

Hs

5

47 2

es

uid

g 12

47

R on

52 e

RH

sid

e

uid

5g

n so

e

12

n so

LH

sid

ide

gu

e

59 56

LH

sid

e

uid

5g

n so

52 A

ide

Hs

50

des

Shown for info : CLS configuration. Other configurations e.g. CLS plus full bulk capability, ACT provision and ACT installation will change cargo hold configuration.

R on

ui 9g

47

e

A320

Issue 6 Revision 1, January 2012

LH

sid

e

uid

9g

n so

25.52.511

Page 317

[ 25-83]

A320 Family

25 Equipment/furnishings Table 25-22 - Technical solutions description TDU

Title (Remarks)

Appl.

Weight (kg) MWE/OWE/APL

01

Continuous side guides in aft cargo hold (A319)

A319-100

9.0/9.0/-9.0

02

Continuous side guides in aft cargo hold - without provision for ACT (A320)

A320-200

17.0/17.0/-17.0

03

Continuous side guides in aft cargo hold - without provision for ACT (A321)

A321-200

21.0/21.0/-21.0

12

Continuous side guides in aft cargo hold - with provision for one ACT (A320)

A320-200

7.0/7.0/-7.0

A321-200

10.0/10.0/-10.0

A320-200

4.0/4.0/-4.0

A321-200

7.0/7.0/-7.0

Equipment reference

Equipment supplier

Equipment PN

QTY

STS

Due to ACT, lead-time constraints for this option are 9 months

13

Continuous side guides in aft cargo hold - with provision for one ACT (A321) Due to ACT, lead-time constraints for this option are 8 months

22

Continuous side guides in aft cargo hold - with provision for two/one ACTs (A320) Due to ACT, lead-time constraints for this option are 9 months

23

Continuous side guides in aft cargo hold - with provision for two/one ACTs (A321) Due to ACT, lead-time constraints for this option are 8 months

Issue 6 Revision 1, January 2012

25.52.511

Page 318

[ 25-84]

A320 Family

Fire protection 26

Reference

Title

26.20.103

Auxiliary Power Unit (APU) fire extinguisher alternate equipment

26.21.104

Engine fire extinguishers alternate equipment

26.23.103

Cargo holds fire extinguisher alternate equipment

26.23.111

Cargo holds fire extinguishers extended duration for ETOPS 120 min

26.23.112

Cargo holds fire extinguishers extended duration for ETOPS 180 min

Issue 6 Revision 1, January 2012

Page 319

[ 26-1]

A320 Family

26 Fire protection

26.20.103 - Auxiliary Power Unit (APU) fire extinguisher alternate equipment Objective To provide alternate equipment for APU fire extinguisher. Basic aircraft One APU fire extinguisher assembly composed of a fire extinguisher bottle, a discharge outlet and cartridge is installed in the APU compartment. Description The basic APU fire extinguisher assembly is replaced by alternate equipment. EPAC selection mode Individual

Issue 6 Revision 1, January 2012

26.20.103

Page 320

[ 26-2]

Fire protection 26

A320 Family

Figure 26-1 - APU fire extinguishing system

Fire emerg. stop relays

FDU

ECB FWC

Fire extinguishing bottle

APU shutdown Fuel fire shutoff valve

Pressure switch Discharge cartridge

Issue 6 Revision 1, January 2012

26.20.103

Page 321

[ 26-3]

A320 Family

26 Fire protection Table 26-1 - Technical solutions description TDU

Title (Remarks)

Appl.

Weight (kg) MWE/OWE/APL

Std

APU fire extinguisher basic equipment - PACIFIC SCIENTIFIC

A318-100 A319-100 A320-200 A321-200

01

APU fire extinguisher alternate equipment - KIDDE AEROSPACE

A318-100 A319-100 A320-200 A321-200

Issue 6 Revision 1, January 2012

Negl./Negl./Negl. Negl./Negl./Negl. Negl./Negl./Negl. Negl./Negl./Negl.

Equipment reference

Equipment supplier

Equipment PN

QTY

STS

APU fire extinguisher container

PACIFIC SCIENTIFIC

33600005-3

1

SFE

APU fire extinguisher container

KIDDE AEROSPACE

472 412-1

1

SFE

26.20.103

Page 322

[ 26-4]

Fire protection 26

A320 Family

Intentionally left blank

Issue 6 Revision 1, January 2012

26.20.103

Page 323

[ 26-5]

A320 Family

26 Fire protection 26.21.104 - Engine fire extinguishers alternate equipment Objective To provide alternate equipment for engine fire extinguishers. Basic aircraft Two engine fire extinguisher assemblies, composed of a fire extinguisher bottle, a discharge outlet and cartridge, are installed for each engine. Description The basic engine fire extinguisher assemblies are replaced by alternate equipment. EPAC selection mode Individual

Issue 6 Revision 1, January 2012

26.21.104

Page 324

[ 26-6]

Fire protection 26

A320 Family

Figure 26-2 - Engine fire extinguishing system

F I R E

AGENT1

AGENT2

SQUIB

SQUIB

DISCH TEST

ENG 1 FIRE PUSH

DISCH

APU FIRE PUSH AGENT

AGENT1

AGENT2

SQUIB

SQUIB

DISCH TEST

SQUIB

ENG 2 FIRE PUSH

DISCH

F I R E

TEST

DISCH

AGENT1

AGENT2

SQUIB DISCH

SQUIB

ENG 2 FIRE PUSH

DISCH

F I R E

TEST

115VU MASTER2 ENG 2 ON

MASTER1 ENG ON 1

OFF

MODE NORM

OFF CRANK

FIRE Pressure switch Squib

FAULT

Pressure switch

2

ENG

MASTER2 ENG ON 2 OFF IGN START

FIRE

FIRE

FAULT

FAULT

1

2

Squib

CFDS ECAM LOOP A

LOOP B

FDU (ENG. 2)

Engine fire extinguishers

Issue 6 Revision 1, January 2012

26.21.104

Page 325

[ 26-7]

A320 Family

26 Fire protection Table 26-2 - Technical solutions description TDU

Title (Remarks)

Appl.

Weight (kg) MWE/OWE/APL

Std

Engine fire extinguishers basic equipment - PACIFIC SCIENTIFIC

A318-100 A319-100 A320-200 A321-200

01

Engine fire extinguishers alternate equipment - KIDDE AEROSPACE

A318-100 A319-100 A320-200 A321-200

Issue 6 Revision 1, January 2012

Negl./Negl./Negl. Negl./Negl./Negl. Negl./Negl./Negl. Negl./Negl./Negl.

Equipment reference

Equipment supplier

Equipment PN

QTY

STS

Fire extinguisher container, engine

PACIFIC SCIENTIFIC

34100005-1

4

SFE

Fire extinguisher container, engine

KIDDE AEROSPACE

472088-1

4

SFE

26.21.104

Page 326

[ 26-8]

Fire protection 26

A320 Family

Intentionally left blank

Issue 6 Revision 1, January 2012

26.21.104

Page 327

[ 26-9]

A320 Family

26 Fire protection 26.23.103 - Cargo holds fire extinguisher alternate equipment Objective for A321-200 To provide alternate equipment for cargo holds fire extinguisher. Basic aircraft for A321-200 Cargo holds are designed as class C, with a single shot fire extinguishing system installed. Description for A321-200 The basic cargo holds fire extinguisher is replaced by alternate equipment. EPAC selection mode Individual

Issue 6 Revision 1, January 2012

26.23.103

Page 328

[ 26-10]

Fire protection 26

A320 Family

Table 26-3 - Technical solutions description TDU

Title (Remarks)

Appl.

Weight (kg) MWE/OWE/APL

Std

Cargo holds fire extinguisher basic equipment - PACIFIC SCIENTIFIC (A321)

A321-200

02

Cargo holds fire extinguisher alternate equipment - KIDDE AEROSPACE (A321)

A321-200

Issue 6 Revision 1, January 2012

1.0/1.0/-1.0

Equipment reference

Equipment supplier

Equipment PN

QTY

STS

Fire extinguisher container, cargo hold

PACIFIC SCIENTIFIC

34600049-1

1

SFE

Fire extinguisher container, cargo hold

KIDDE AEROSPACE

472930-3

1

SFE

26.23.103

Page 329

[ 26-11]

A320 Family

26 Fire protection

26.23.111 - Cargo holds fire extinguishers extended duration for ETOPS 120 min Objective To increase the fire extinguishing capability for forward and aft cargo holds to cope with 120 min diversion time as required for ETOPS operations. Basic aircraft Cargo holds are designed as class C, with a single shot fire extinguishing system installed. Description For A318, A320 and A321, a second fire extinguishing bottle is installed. This second bottle is discharged through a flow metering system 60 min after the first bottle. For A319, the fire extinguishing remains a single shot system with a bottle size increased from 630 cu in to 800 cu in. This implies: • adaptation of electrical wiring • modification of the SDCU or CIDS-SDF logic, corresponding switches and indicator of the cockpit control panel and circuit breakers. EPAC selection mode Individual Issue 6 Revision 1, January 2012

26.23.111

Page 330

[ 26-12]

Fire protection 26

A320 Family

Figure 26-3 - Cargo fire extinguishing extension Basic fire Extinguisher pipe extinguisher bottle 800 cu in

Overhead panel A321

Second fire extinguisher bottle 630 cu in Basic fire extinguisher bottle 630 cu in

Pre-mod and post-mod (A319) Pre-mod (A318/A320/A321) DISCH

DISCH

CARGO SMOKE TEST

FWD

Second fire extinguisher bottle 630 cu in

AFT

SMOKE

SMOKE

DISCH

DISCH

Fire extinguishing bottles A320

630 cu in 630 cu in (0.01 cu m)

Post-mod (A318/A320/A321)

Pressure switch Increased fire extinguisher bottle 800 cu in

CARGO SMOKE FWD

TEST

AFT

SMOKE

Fill and safety relief port FW

D HO

LD

AFT

LD

Discharge outlet and cartridge

HO

Extinguisher pipe

SMOKE

800 cu in

A319 DISCH

800 cu in

AGENT2

Pressure switch AGENT1 AGENT2

DISCH1 DISCH2

AGENT1 AGENT2

Basic fire extinguisher bottle 630 cu in A318

Issue 6 Revision 1, January 2012

Second fire extinguisher bottle 630 cu in

Fill and safety relief port FW

D HO

LD

AFT

LD

HO

Discharge outlet and cartridge

Extinguisher pipe

26.23.111

Page 331

[ 26-13]

A320 Family

26 Fire protection Table 26-4 - Technical solutions description TDU

Title (Remarks)

Appl.

Weight (kg) MWE/OWE/APL

01

Cargo holds fire extinguishers extended duration for ETOPS 120 min (A318)

Cargo holds fire extinguishers extended duration for ETOPS 120 min (A319)

Cargo holds fire extinguishers extended duration for ETOPS 120 min (A320)

Cargo holds fire extinguishers extended duration for ETOPS 120 min (A321) Installation of a second fire extinguisher bottle (630 cu in) on top of the basic one (800 cu in), and installation of the associated flow metering system.

Issue 6 Revision 1, January 2012

QTY

STS

Fire extinguisher container, cargo hold

PACIFIC SCIENTIFIC

34600017

2

SFE

A319-100

7.0/7.0/-7.0

Fire extinguisher container, cargo hold

PACIFIC SCIENTIFIC

34600049-1

1

SFE

A320-200

23.0/23.0/-23.0

Fire extinguisher container, cargo hold

PACIFIC SCIENTIFIC

34600017

2

SFE

A321-200

20.0/20.0/-20.0

Fire extinguisher container, cargo hold

PACIFIC SCIENTIFIC

34600017

1

SFE

Fire extinguisher container, cargo hold

PACIFIC SCIENTIFIC

34600049-1

1

SFE

Installation of a second fire extinguisher bottle identical to the basic one (630 cu in), and installation of the associated flow metering system.

04

Equipment PN

20.0/20.0/-20.0

The fire extinguisher bottle installed with the single shot fire extinguishing system (630 cu in) is replaced by a bigger one (800 cu in).

03

Equipment supplier

A318-100

Installation of a second fire extinguisher bottle identical to the basic one (630 cu in), and installation of the associated flow metering system.

02

Equipment reference

26.23.111

Page 332

[ 26-14]

Fire protection 26

A320 Family

Intentionally left blank

Issue 6 Revision 1, January 2012

26.23.111

Page 333

[ 26-15]

A320 Family

26 Fire protection

26.23.112 - Cargo holds fire extinguishers extended duration for ETOPS 180 min Objective To increase the fire extinguishing capability to 180 min diversion time for the forward and aft cargo compartments. It is required for ETOPS operations with class C cargo compartments. Basic aircraft Cargo compartments are designed as class C, with a single shot fire extinguishing system installed. Description A second fire extinguishing bottle is installed. This second bottle should be discharged through a flow metering system 60 min after the first bottle. This implies : • adaptation of electrical wiring • modification of the SDCU or CIDS-SDF logic, corresponding switches and indicator of the cockpit control panel and circuit breakers. EPAC selection mode Individual

Issue 6 Revision 1, January 2012

26.23.112

Page 334

[ 26-16]

Fire protection 26

A320 Family

Figure 26-4 - Cargo fire extinguishing extension Basic fire extinguisher bottle 800 in

Extinguisher pipe

Second fire extinguisher bottle 800 cu in

Basic fire extinguisher bottle 630 cu in

A321

Overhead panel

Second fire extinguisher bottle 630 cu in

Pre-mod DISCH

Fire extinguishing bottles DISCH

CARGO SMOKE TEST

FWD

AFT

630 cu in A320

SMOKE

SMOKE

DISCH

DISCH

630 cu in (0.01 cu m)

Pressure switch Fill and safety relief port FW

D HO

LD

Post-mod Basic fire extinguisher bottle 630 cu in

CARGO SMOKE FWD

TEST

Second fire extinguisher bottle 630 cu in

800 cu in

Pressure switch Fill and safety relief port

DISCH AGENT2

FW

D HO

LD

DISCH1 DISCH2

Discharge outlet and cartridge

800 cu in

Extinguisher pipe

SMOKE

A319

AGENT2

LD

HO

AFT

SMOKE

AGENT1

AFT

AGENT1

Basic fire extinguisher bottle 630 cu in

AGENT2

AFT

LD

HO

Discharge outlet and cartridge

Second fire extinguisher bottle 630 cu in

Extinguisher pipe

A318

Issue 6 Revision 1, January 2012

26.23.112

Page 335

[ 26-17]

A320 Family

26 Fire protection Table 26-5 - Technical solutions description TDU

Title (Remarks)

Appl.

Weight (kg) MWE/OWE/APL

01

Cargo holds fire extinguishers extended duration for ETOPS 180 min (A318)

Cargo holds fire extinguishers extended duration for ETOPS 180 min (A319)

Cargo holds fire extinguishers extended duration for ETOPS 180 min (A320)

Cargo holds fire extinguishers extended duration for ETOPS 180 min (A321) Installation of a second fire extinguisher bottle (800 cu in) on top of the basic one (800 cu in), and installation of the associated flow metering system.

Issue 6 Revision 1, January 2012

QTY

STS

Fire extinguisher container, cargo hold

PACIFIC SCIENTIFIC

34600017

2

SFE

A319-100

21.0/21.0/-21.0

Fire extinguisher container, cargo hold

PACIFIC SCIENTIFIC

34600017

2

SFE

A320-200

23.0/23.0/-23.0

Fire extinguisher container, cargo hold

PACIFIC SCIENTIFIC

34600017

2

SFE

A321-200

28.0/28.0/-28.0

Fire extinguisher container, cargo hold

PACIFIC SCIENTIFIC

34600049-1

2

SFE

Installation of a second fire extinguisher bottle identical to the basic one (630 cu in), and installation of the associated flow metering system.

04

Equipment PN

20.0/20.0/-20.0

Installation of a second fire extinguisher bottle identical to the basic one (630 cu in), and installation of the associated flow metering system.

03

Equipment supplier

A318-100

Installation of a second fire extinguisher bottle identical to the basic one (630 cu in), and installation of the associated flow metering system.

02

Equipment reference

26.23.112

Page 336

[ 26-18]

A320 Family

Fuel 28

Reference

Title

28.11.133

Full provision for installation of one Additional Center Tank (ACT) in aft cargo hold

28.11.140

Full provision for installation of two/one Additional Center Tanks (ACTs) in aft cargo hold

28.11.225

Installation of one Additional Center Tank (ACT) in aft cargo hold

28.11.235

Installation of two Additional Center Tanks (ACTs) in aft cargo hold

28.25.107

Installation of additional refuel/defuel coupling in LH wing

28.25.110

Installation of fuel quantity preselector in cockpit

28.25.130

Relocation of refuel/defuel control panel

Issue 6 Revision 1, January 2012

Page 337

[ 28-1]

A320 Family

28 Fuel

28.11.133 - Full provision for installation of one Additional Center Tank (ACT) in aft cargo hold Objective for A319-100 and A320-200 and A321-200 To make structural and system provision for one ACT to be installed at the forward end of the aft cargo hold. Basic aircraft for A319-100 and A320-200 and A321200 Space provision is made for an ACT. Structural provision: • reinforced rivets at membrane plates FR45-46 • modified longitudinal beams FR45-46 • modified keel beam brackets FR46. Description for A319-100 and A320-200 and A321200 The modification consists in: • provision for ACT cavity and water drains including access doors through the fuselage skin and belly fairing • air pressurisation pipes to the ACT location • fuel pipes from the center tank to the ACT location with a transfer pump and valve • reinforcement of fuselage sections 16/17 • new cabin floor panels with carpet split for removal or installation of floor panel above the ACT • new ACT refuel/defuel panel on the fuselage • installation of refuel panel cover (only when ACT are provisioned but not installed) Issue 6 Revision 1, January 2012

• new cockpit overhead fuel control panel • installation of relay box in the avionics compartment plus routings • installation of a third Fuel Level Sensing Control Unit (FLSCU) • installation of ACT crash stoppers • installation of ACT restraint/support components. Note for A319-100 and A320-200 and A321-200 On A319 and A320 selection of this item requires the relocation of the slide pressure bottles to the OHSC between frames C45 and C47 (LH/RH). Consequently OHSC volume at these locations is reduced by approximately 30%. EPAC selection mode Individual

28.11.133

Page 338

[ 28-2]

Fuel 28

A320 Family

Figure 28-1 - Full provision for installation of one ACT in aft cargo hold A319 / A320 Fuel system cockpit panel

FUEL QTY kg x 1000

CTR

LEFT

HI

HI. LVL.

LVL

CTR

LEFT ACT

RIGHT

REFUEL VALVES

REFUEL VALVE OPEN NORM SHUT FQI SELECT CTR/ACT

RIGHT

MODE SELECT

TEST HI - LVL

REFUEL

CTR + ACT CTR ACT

OPEN NORM SHUT

OPEN NORM SHUT

OPEN NORM SHUT

BATT POWER ON

OFF DEFUEL XFR PRESELECTED

OPEN

A321 Fuel system cockpit panel

NORM

LTS

REFUEL

ACTUAL

kg x 1000

DEC

INC CKPT

END

Main refuel panel

Issue 6 Revision 1, January 2012

28.11.133

Page 339

[ 28-3]

A320 Family

28 Fuel Table 28-1 - Technical solutions description TDU

Title (Remarks)

Appl.

Weight (kg) MWE/OWE/APL

01

Full provision for installation of one ACT in aft cargo hold (A321)

Equipment reference

Equipment supplier

Equipment PN

QTY

STS

A321-200

125.0/125.0/-125.0

Trim tank transfer pump

EATON AEROSPACE

568-1-27170002

1

SFE

A320-200

100.0/100.0/-100.0

Trim tank transfer pump

EATON AEROSPACE

568-1-27170002

1

SFE

A319-100

100.0/100.0/-100.0

Trim tank transfer pump

EATON AEROSPACE

568-1-27170002

1

SFE

Lead-time constraints 8 months

02

Full provision for installation of one ACT in aft cargo hold (A320) Lead-time constraints 9 months

03

Full provision for installation of one ACT in aft cargo hold (A319) Lead-time constraints 9 months

Issue 6 Revision 1, January 2012

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[ 28-4]

Fuel 28

A320 Family

Intentionally left blank

Issue 6 Revision 1, January 2012

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Page 341

[ 28-5]

A320 Family

28 Fuel

28.11.140 - Full provision for installation of two/one Additional Center Tanks (ACTs) in aft cargo hold Objective for A319-100 and A320-200 and A321-200 To provide structural and system provisions for two ACTs to be installed at the forward end of the aft cargo hold. Basic aircraft for A319-100 and A320-200 and A321200 Space provision is made for the installation of two ACTs. Description for A319-100 and A320-200 and A321200 The modification consists in: • additional horizontal beam and support struts • belly fairing / fuselage skin drain hole access doors • air pressurization pipes to the ACT locations • provision for ACT cavity and water drains • fuel pipes from the center tank to the ACT location with a transfer pump and valve • reinforcement of fuselage sections 16/17 • new cabin floor panels with carpet split for removal or installation of floor panels above the ACT locations • new ACT refuel/defuel panel on the fuselage • installation of refuel panel cover (only when ACT are provisioned but not installed) • new cockpit overhead fuel control panel

Issue 6 Revision 1, January 2012

• installation of a relay box in the avionics compartment plus routings • installation of a third Fuel Level Sensing Control Unit (FLSCU) • installation of ACT crash stoppers • installation of ACT restraint/support components. Note for A319-100 and A320-200 and A321-200 • depending on operator range requirements either one or two ACTs can be installed for flexibility • on A319 and A320 selection of this item requires the relocation of the slide pressure bottles to the OHSC between frames C45 and C47 (LH/RH). Consequently OHSC volume at these locations is reduced by approximately 30%. EPAC selection mode Individual

28.11.140

Page 342

[ 28-6]

Fuel 28

A320 Family

Figure 28-2 - Full provision for installation of two/one ACTs in aft cargo hold A319 / A320 Fuel system cockpit panel

FUEL QTY kg x 1000

CTR

LEFT

HI ACT 1

FQI SELECT CTR/ACT

HI. LVL.

LVL

ACT 2 REFUEL VALVE OPEN NORM SHUT

RIGHT

CTR

LEFT

RIGHT

REFUEL VALVES OPEN NORM SHUT

OPEN NORM SHUT

MODE SELECT

TEST HI - LVL

REFUEL

CTR + ACT CTR ACT1 ACT2

OPEN NORM SHUT

OPEN NORM SHUT

BATT POWER ON

OFF DEFUEL XFR PRESELECTED

OPEN

A321 Fuel system cockpit panel

NORM

LTS

REFUEL

ACTUAL

kg x 1000

DEC

INC CKPT

END

Main refuel panel

Issue 6 Revision 1, January 2012

28.11.140

Page 343

[ 28-7]

A320 Family

28 Fuel Table 28-2 - Technical solutions description TDU

Title (Remarks)

Appl.

Weight (kg) MWE/OWE/APL

01

Full provision for installation of two/one ACTs in aft cargo hold (A319)

Equipment reference

Equipment supplier

Equipment PN

QTY

STS

A319-100

120.0/120.0/-120.0

Trim tank transfer pump

EATON AEROSPACE

568-1-27170002

1

SFE

A321-200

150.0/150.0/-150.0

Trim tank transfer pump

EATON AEROSPACE

568-1-27170002

1

SFE

A320-200

120.0/120.0/-120.0

Trim tank transfer pump

EATON AEROSPACE

568-1-27170002

1

SFE

Lead-time constraints 9 months

02

Full provision for installation of two/one ACTs in aft cargo hold (A321) Lead-time constraints 8 months

03

Full provision for installation of two/one ACTs in aft cargo hold (A320) Lead-time constraints 9 months

Issue 6 Revision 1, January 2012

28.11.140

Page 344

[ 28-8]

Fuel 28

A320 Family

Intentionally left blank

Issue 6 Revision 1, January 2012

28.11.140

Page 345

[ 28-9]

A320 Family

28 Fuel

28.11.225 - Installation of one Additional Center Tank (ACT) in aft cargo hold Objective for A319-100 and A320-200 and A321-200 To install a fully integrated ACT in order to increase the fuel tank capacity and to extend the range of the aircraft. Basic aircraft for A319-100 and A320-200 and A321200 Space provision is made for ACT. Description for A319-100 and A320-200 and A321200 To install one ACT with 2992 l capacity at the forward end of the aft cargo hold. Note for A319-100 and A320-200 and A321-200 • requires prior acceptance of CN28.11.133 - Full provision for installation of one ACT in aft cargo hold or CN28.11.140 - Full provision for installation of two/ one ACTs in aft cargo hold • requires prior acceptance of CN30.70.108 Extended freezing protection • depending on operator range requirements, the ACT can be removed/re-installed (by configuration Service Bulletin). EPAC selection mode Individual

Issue 6 Revision 1, January 2012

28.11.225

Page 346

[ 28-10]

Fuel 28

A320 Family

Figure 28-3 - Typical installation of one ACT in aft cargo hold (full bulk)

A320

A319

AC

T1

AC

T1

A321 Remark: Remaining loading in aft cargo hold is specified in Weight & Balance Manual

AC

T1

Issue 6 Revision 1, January 2012

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Page 347

[ 28-11]

A320 Family

28 Fuel Table 28-3 - Technical solutions description TDU

Title (Remarks)

Appl.

Weight (kg) MWE/OWE/APL

01

Installation of one ACT in aft cargo hold - with full bulk configuration (A319)

A319-100

100.0/512.0/-512.0

A320-200

100.0/512.0/-512.0

Equipment reference

Equipment supplier

Equipment PN

QTY

STS

Incompatible with CN25.52.204 - System provision for mechanized bulk loading systems in aft cargo hold (A319/A320). Incompatible with CN25.52.404 - Installation of Cargo Loading System (CLS) with full bulk capability in fwd and aft cargo holds. Requires prior acceptance of CN30.70.108 Extended freezing protection. Lead-time constraints 9 months.

02

Installation of one ACT in aft cargo hold - with full bulk configuration (A320) Incompatible with CN25.52.204 - System provision for mechanized bulk loading systems in aft cargo hold (A319/A320), or CN25.52.304 - Installation of semi-automatic Cargo Loading System (CLS) in forward and aft cargo holds (A320/A321), or CN25.52.404 - Installation of Cargo Loading System (CLS) with full bulk capability in fwd and aft cargo holds. Requires prior acceptance of CN30.70.108 Extended freezing protection. Lead-time constraints 9 months.

Issue 6 Revision 1, January 2012

28.11.225

Page 348

[ 28-12]

Fuel 28

A320 Family TDU

Title (Remarks)

Appl.

Weight (kg) MWE/OWE/APL

03

Installation of one ACT in aft cargo hold - with full bulk configuration (A321)

A321-200

100.0/512.0/-512.0

A320-200

100.0/512.0/-512.0

Equipment reference

Equipment supplier

Equipment PN

QTY

STS

Incompatible with CN25.52.205 - System provision for mechanized bulk loading systems in aft cargo hold (A321), or CN25.52.304 - Installation of semi-automatic Cargo Loading System (CLS) in forward and aft cargo holds (A320/A321), or CN25.52.404 - Installation of Cargo Loading System (CLS) with full bulk capability in fwd and aft cargo holds. Requires prior acceptance of CN30.70.108 Extended freezing protection. Lead-time constraints 8 months.

12

Installation of one ACT in aft cargo hold - with CLS & full provision for one ACT (A320) Requires prior acceptance of CN25.52.304 - Installation of semi-automatic Cargo Loading System (CLS) in forward and aft cargo holds (A320/A321), or CN25.52.404 - Installation of Cargo Loading System (CLS) with full bulk capability in fwd and aft cargo holds. Requires prior acceptance of CN30.70.108 Extended freezing protection. Lead-time constraint 9 months.

Issue 6 Revision 1, January 2012

28.11.225

Page 349

[ 28-13]

A320 Family

28 Fuel TDU

Title (Remarks)

Appl.

Weight (kg) MWE/OWE/APL

13

Installation of one ACT in aft cargo hold - with CLS & full provision for one ACT (A321)

A321-200

125.0/537.0/-537.0

A320-200

120.0/532.0/-532.0

A321-200

150.0/562.0/-562.0

Equipment reference

Equipment supplier

Equipment PN

QTY

STS

Requires prior acceptance of CN25.52.304 - Installation of semi-automatic Cargo Loading System (CLS) in forward and aft cargo holds (A320/A321), or CN25.52.404 - Installation of Cargo Loading System (CLS) with full bulk capability in fwd and aft cargo holds. Requires prior acceptance of CN30.70.108 Extended freezing protection. Lead-time constraints 8 months.

22

Installation of one ACT in aft cargo hold - with CLS & full provision for two ACTs (A320) Requires prior acceptance of CN25.52.304 - Installation of semi-automatic Cargo Loading System (CLS) in forward and aft cargo holds (A320/A321), or CN25.52.404 - Installation of Cargo Loading System (CLS) with full bulk capability in fwd and aft cargo holds. Requires prior acceptance of CN30.70.108 Extended freezing protection. Lead-time constraint 9 months.

23

Installation of one ACT in aft cargo hold - with CLS & full provision for two ACTs (A321) Requires prior acceptance of CN25.52.304 - Installation of semi-automatic Cargo Loading System (CLS) in forward and aft cargo holds (A320/A321), or CN25.52.404 - Installation of Cargo Loading System (CLS) with full bulk capability in fwd and aft cargo holds. Requires prior acceptance of CN30.70.108 Extended freezing protection. Lead-time constraints 8 months.

Issue 6 Revision 1, January 2012

28.11.225

Page 350

[ 28-14]

Fuel 28

A320 Family

Intentionally left blank

Issue 6 Revision 1, January 2012

28.11.225

Page 351

[ 28-15]

A320 Family

28 Fuel

28.11.235 - Installation of two Additional Center Tanks (ACTs) in aft cargo hold Objective for A319-100 and A320-200 and A321-200 To install two fully integrated ACTs in order to extend the range of the aircraft. Basic aircraft for A319-100 and A320-200 and A321200 Space provision for two ACTs. Description for A319-100 and A320-200 and A321200 To install two ACTs with 5984 l total capacity at the forward end of the aft cargo hold. Note for A319-100 and A320-200 and A321-200 • requires prior acceptance of CN28.11.140 - Full provision for installation of two/one ACTs in aft cargo hold • requires prior acceptance of CN30.70.108 Extended freezing protection • depending on operator range requirements, the ACTs can be removed/re-installed (by configuration Service Bulletin). EPAC selection mode Individual

Issue 6 Revision 1, January 2012

28.11.235

Page 352

[ 28-16]

Fuel 28

A320 Family

Figure 28-4 - Typical installation of two ACTs in aft cargo hold (full bulk)

A320

A319 AC

AC

T1

T1

AC

T1

T2

Remark: Remaining loading in aft cargo hold is specified in Weight & Balance Manual

A321 AC

AC

AC

T2

T2

Issue 6 Revision 1, January 2012

28.11.235

Page 353

[ 28-17]

A320 Family

28 Fuel Table 28-4 - Technical solutions description TDU

Title (Remarks)

Appl.

Weight (kg) MWE/OWE/APL

01

Installation of two ACTs in aft cargo hold - with full bulk configuration (A319)

A319-100

120.0/893.0/-893.0

A320-200

120.0/893.0/-893.0

Equipment reference

Equipment supplier

Equipment PN

QTY

STS

Incompatible with CN25.52.204 - System provision for mechanized bulk loading systems in aft cargo hold (A319/A320). Requires prior acceptance of CN03.20.4XX/02 - A319-1XX increased design weights - MTOW to 75.5 t, MLW to 62.5 t, MZFW to 58.5 t (wv 002). Requires prior acceptance of CN30.70.108 Extended freezing protection. Lead-time constraints 9 months.

02

Installation of two ACTs in aft cargo hold - with full bulk configuration (A320) Incompatible with CN25.52.204 - System provision for mechanized bulk loading systems in aft cargo hold (A319/A320), or CN25.52.304 - Installation of semi-automatic Cargo Loading System (CLS) in forward and aft cargo holds (A320/A321), or CN25.52.404 - Installation of Cargo Loading System (CLS) with full bulk capability in fwd and aft cargo holds. Requires prior acceptance of CN30.70.108 Extended freezing protection. Lead-time constraints 9 months.

Issue 6 Revision 1, January 2012

28.11.235

Page 354

[ 28-18]

Fuel 28

A320 Family TDU

Title (Remarks)

Appl.

Weight (kg) MWE/OWE/APL

03

Installation of two ACTs in aft cargo hold - with full bulk configuration (A321)

A321-200

150.0/923.0/-923.0

A320-200

120.0/893.0/-893.0

A321-200

150.0/923.0/-923.0

Equipment reference

Equipment supplier

Equipment PN

QTY

STS

Incompatible with CN25.52.205 - System provision for mechanized bulk loading systems in aft cargo hold (A321), or CN25.52.304 - Installation of semi-automatic Cargo Loading System (CLS) in forward and aft cargo holds (A320/A321), or CN25.52.404 - Installation of Cargo Loading System (CLS) with full bulk capability in fwd and aft cargo holds. Requires prior acceptance of CN30.70.108 Extended freezing protection. Lead-time constraints 8 months.

22

Installation of two ACTs in aft cargo hold - with CLS (A320) Requires prior acceptance of CN25.52.304/04 - Installation of semiautomatic CLS in forward and aft cargo holds (A320/A321), or CN25.52.404/04 Installation of CLS with full bulk capability in fwd and aft cargo holds. Requires prior acceptance of CN30.70.108 Extended freezing protection. Lead-time constraint 9 months.

23

Installation of two ACTs in aft cargo hold - with CLS (A321) Requires prior acceptance of CN25.52.304/05 - Installation of semiautomatic CLS in forward and aft cargo holds (A320/A321), or CN25.52.404/05 Installation of CLS with full bulk capability in fwd and aft cargo holds. Requires prior acceptance of CN30.70.108 Extended freezing protection. Lead-time constraints 8 months.

Issue 6 Revision 1, January 2012

28.11.235

Page 355

[ 28-19]

A320 Family

28 Fuel

28.25.107 - Installation of additional refuel/defuel coupling in LH wing Objective To offer flexibility in terms of aircraft servicing.

EPAC selection mode Individual

Basic aircraft A refuel/defuel coupling is provided in the RH wing of the aircraft. Space and structural provisions are made for a coupling in the LH wing. Description The modification consists in installing an additional 2.5 inch refuel/defuel coupling under the LH wing (outboard of the engine pylon). Refueling from this coupling will allow same refueling rates as from the RH wing coupling. This option permits aircraft fuel tanks to be filled from either the RH or LH side. Defueling from both the LH wing and RH wing is possible.

Issue 6 Revision 1, January 2012

28.25.107

Page 356

[ 28-20]

Fuel 28

A320 Family Figure 28-5 - Refuel/defuel coupling

Wing leading edge

Coupling

Refuel/defuel coupling (basic)

Issue 6 Revision 1, January 2012

28.25.107

Refuel/defuel control panel (basic)

Refuel/defuel coupling (optional)

Page 357

[ 28-21]

A320 Family

28 Fuel Table 28-5 - Technical solutions description TDU

Title (Remarks)

Appl.

Weight (kg) MWE/OWE/APL

01

Installation of additional refuel/ defuel coupling in LH wing

Issue 6 Revision 1, January 2012

A318-100 A319-100 A320-200 A321-200

Equipment reference

Equipment supplier

Equipment PN

QTY

STS

7.5/7.5/-7.5 7.5/7.5/-7.5 7.5/7.5/-7.5 7.5/7.5/-7.5

28.25.107

Page 358

[ 28-22]

Fuel 28

A320 Family

Intentionally left blank

Issue 6 Revision 1, January 2012

28.25.107

Page 359

[ 28-23]

A320 Family

28 Fuel 28.25.110 - Installation of fuel quantity preselector in cockpit Objective To enable fuel quantity preselection and automatic refueling to be controlled from the cockpit. Basic aircraft The fuel quantity and refueling selections are made from the external refuel/defuel control panel located on the side of the fuselage, beneath the RH wing. Description A fuel quantity preselector is installed in the cockpit (overhead maintenance panel) to enable quantity selection and automatic refueling. Preselection and control from the cockpit will have priority over the external refuel/defuel control panel. Operational indication is provided in the cockpit, at the external refuel/defuel control panel and on the wings (adjacent to the couplings).

• select required fuel quantity • select refuel CTL valve push button ON • green ready to refuel light(s) comes on automatically when the aircraft is ready • refueling is performed automatically • at the end of refueling, the ready to refuel light extinguishes automatically, and the preselection module END light indicates that refuel is finished • deselect power. EPAC selection mode Individual

Note The sequence of operations is as follows: • select power ON: • a CKPT light comes on automatically in the cockpit and on the external panel to indicate that the cockpit has priority • high level check is performed Issue 6 Revision 1, January 2012

28.25.110

Page 360

[ 28-24]

Fuel 28

A320 Family Figure 28-6 - Refuel/defuel panels Preselected display Preselector rocker sw

PRESELECTED

ACTUAL

Actual quantity display

Kg/1000

FAULT

CTL VALVE

ON

ON

REFUEL

End light

END

INC. CKPT

DEC. PWR

Elec PWR pb

REFUEL

CKPT light CTL valve pb

Cockpit fuel quantity preselector

(TDU 01)

Refuel/defuel coupling (basic)

Green light

(TDU 02)

Refuel/defuel control panel (basic)

Issue 6 Revision 1, January 2012

28.25.110

Refuel/defuel coupling (optional) Green light

Page 361

[ 28-25]

A320 Family

28 Fuel Table 28-6 - Technical solutions description TDU

Title (Remarks)

Appl.

Weight (kg) MWE/OWE/APL

01

Installation of fuel quantity preselector in cockpit - with RH refuel coupling & without ACT prov.

A318-100 A319-100 A320-200 A321-200

3.5/3.5/-3.5 3.5/3.5/-3.5 3.5/3.5/-3.5 3.5/3.5/-3.5

A318-100 A319-100 A320-200 A321-200

4.3/4.3/-4.3 4.3/4.3/-4.3 4.3/4.3/-4.3 4.6/4.6/-4.6

A321-200

4.6/4.6/-4.6

A320-200 A321-200

3.5/3.5/-3.5 3.5/3.5/-3.5

Equipment reference

Equipment supplier

Equipment PN

QTY

STS

For A318/A319/A320, incompatible with CN28.25.130 - Relocation of refuel/defuel control panel.

02

Installation of fuel quantity preselector in cockpit - with LH refuel coupling & without ACT prov. Requires prior acceptance of CN28.25.107/01 - Installation of additional refuel/defuel coupling in LH wing. For A318/A319/A320, incompatible with CN28.25.130 - Relocation of refuel/defuel control panel.

03

Installation of fuel quantity preselector in cockpit - with LH refuel coupling & prov. for one ACT Requires prior acceptance of CN28.25.107/01 - Installation of additional refuel/defuel coupling in LH wing. Requires prior acceptance of CN28.11.133/01 - Full provision for installation of one Additional Center Tank (ACT) in aft cargo hold.

04

Installation of fuel quantity preselector in cockpit - with RH refuel coupling & prov. for one ACT Requires prior acceptance of CN28.11.133/01 - Full provision for installation of one Additional Center Tank (ACT) in aft cargo hold. For A320, incompatible with CN28.25.130 - Relocation of refuel/defuel control panel.

Issue 6 Revision 1, January 2012

28.25.110

Page 362

[ 28-26]

Fuel 28

A320 Family TDU

Title (Remarks)

Appl.

Weight (kg) MWE/OWE/APL

05

Installation of fuel quantity preselector in cockpit - with RH refuel coupling & prov. for two ACTs

A319-100 A320-200 A321-200

3.5/3.5/-3.5 3.5/3.5/-3.5 3.5/3.5/-3.5

A319-100 A321-200

4.6/4.6/-4.6 4.6/4.6/-4.6

Equipment reference

Equipment supplier

Equipment PN

QTY

STS

Requires prior acceptance of CN28.11.140 - Full provision for installation of two/one Additional Center Tanks (ACTs) in aft cargo hold. For A319/A320, incompatible with CN28.25.130 - Relocation of refuel/defuel control panel.

06

Installation of fuel quantity preselector in cockpit - with LH refuel coupling & prov. for two ACTs Requires prior acceptance of CN28.25.107/01 - Installation of additional refuel/defuel coupling in LH wing. Requires prior acceptance of CN28.11.140 - Full provision for installation of two/one Additional Center Tanks (ACTs) in aft cargo hold. For A319, incompatible with CN28.25.130 - Relocation of refuel/defuel control panel.

Issue 6 Revision 1, January 2012

28.25.110

Page 363

[ 28-27]

A320 Family

28 Fuel 28.25.130 - Relocation of refuel/defuel control panel Objective To offer flexibility in terms of aircraft servicing. Basic aircraft The refuel/defuel control panel is located on the fuselage side beneath the RH wing. Space provision is provided for the refuel/defuel control panel in the LH and RH wings. Description Relocation of the refuel/defuel control panel to either the RH or LH wing. Note • relocation to the LH wing requires also installation of LH wing refuel/defuel coupling • when ACT are provisioned but not installed the installation of a refuel panel cover is required. EPAC selection mode Individual

Issue 6 Revision 1, January 2012

28.25.130

Page 364

[ 28-28]

Fuel 28

A320 Family Figure 28-7 - Refueling panel locations

Refuel/defuel coupling (basic) Refuel/defuel control panel (optional)

Refuel/defuel coupling (basic)

Refuel/defuel control panel (basic) )

FUEL QTY

U TD

kg x 1000

Indicator

CTR

LEFT

01

Relocation of refuel/defuel control panel to RH wing

(

RIGHT

HI. LVL. CTR

LEFT

Refuel/Defuel coupling (optional)

RIGHT

REFUEL VALVES

Refuel/defuel control panel

OPEN NORM SHUT

OPEN NORM SHUT

OPEN NORM SHUT

MODE SELECT

TEST HI - LVL

REFUEL

BATT POWER

Refuel/defuel control panel (optional)

(TDU 0

2)

ON

OFF DEFUEL XFR PRESELECTED

OPEN

NORM

LTS

REFUEL

ACTUAL

kg x 1000

Preselector DEC

INC CKPT

END

Relocation of the refuel/defuel control panel to LH wing

Refuel/defuel control panel

Issue 6 Revision 1, January 2012

28.25.130

Page 365

[ 28-29]

A320 Family

28 Fuel Table 28-7 - Technical solutions description TDU

Title (Remarks)

Appl.

Weight (kg) MWE/OWE/APL

01

Relocation of refuel/defuel control panel to RH wing without ACT provision For A318/A319/A320, incompatible with CN28.25.110 - Relocation of refuel/defuel control panel.

02

Relocation of refuel/defuel control panel to LH wing - without ACT provision Requires prior acceptance of CN28.25.107/01 - Installation of additional refuel/defuel coupling in LH wing. For A318/A319/A320, incompatible with CN28.25.110 - Relocation of refuel/defuel control panel.

04

Relocation of refuel/defuel control panel to RH wing - with provision for two ACTs

A318-100 A319-100 A320-200 A321-200

2.5/2.5/-2.5 2.5/2.5/-2.5 2.5/2.5/-2.5 2.5/2.5/-2.5

A318-100 A319-100 A320-200 A321-200

2.5/2.5/-2.5 2.5/2.5/-2.5 2.5/2.5/-2.5 2.5/2.5/-2.5

A321-200

2.5/2.5/-2.5

A321-200

2.5/2.5/-2.5

Equipment reference

Equipment supplier

Equipment PN

QTY

STS

Requires prior acceptance of CN28.11.140/02 - Full provision for installation of two/one ACTs in aft cargo hold (A321).

05

Relocation of refuel/defuel control panel to LH wing - with provision for one ACT Requires prior acceptance of CN28.25.107/01 - Installation of additional refuel/defuel coupling in LH wing. Requires prior acceptance of CN28.11.133/01 - Full provision for installation of one Additional Center Tank (ACT) in aft cargo hold.

Issue 6 Revision 1, January 2012

28.25.130

Page 366

[ 28-30]

A320 Family

Hydraulic power 29

Reference

Title

29.10.110

Hydraulic Engine Driven Pumps (EDPs) alternate equipment

29.21.104

Electropumps alternate equipment

Issue 6 Revision 1, January 2012

Page 367

[ 29-1]

A320 Family

29 Hydraulic power

29.10.110 - Hydraulic Engine Driven Pumps (EDPs) alternate equipment Objective To provide alternate equipment for hydraulic EDPs. Basic aircraft Two hydraulic pumps are installed. Description The basic pumps are replaced with alternate equipment which is fully interchangeable, except that the backshell clocking of the harness connector is re-orientated (depending on the pump and aircraft type). EPAC selection mode Individual

Issue 6 Revision 1, January 2012

29.10.110

Page 368

[ 29-2]

Hydraulic power 29

A320 Family Figure 29-1 - Hydraulic system

EDP

Yellow Reservoir

Electrical pump

Pressure switch

HYD LEAK MEASUREMENT VALVES

BLUE PUMP OVRD

B

G

Y

ON

OFF

OFF

OFF

Hand Pump

PTU Accu

Valve Pressure sensor

Pressure switch

EDP

To flight controls and other consumers

GREEN

HYD

3000

BLUE

3000

PSI

YELLOW PSI

3000

PTU ELEC

RAT ELEC

1

EDP

GREEN

2

BLUE

LO AIR PRESS

RAT MAN ON

H Y D

OVHT

TAT +19 ¡C SAT +18 ¡C

Issue 6 Revision 1, January 2012

GMT 23:56

G.W. 603

40 VU

YELLOW PTU

T

Fire shut-off valve

29.10.110

ENG 1 PUMP

FAULT OFF

ELEC PUMP

A U T O

ELEC PUMP ENG 2 PUMP FAULT

FAULT

FAULT

OFF

OFF

A U T O

FAULT

OFF

H Y D

OFF

Page 369

[ 29-3]

A320 Family

29 Hydraulic power Table 29-1 - Technical solutions description TDU

Title (Remarks)

Appl.

Weight (kg) MWE/OWE/APL

Std

Hydraulic EDPs basic equipment - PARKER

A318-100 A319-100 A320-200 A321-200

12

Hydraulic EDPs alternate equipment - EATON AEROSPACE, PN 3031863-001

A318-100 A319-100 A320-200 A321-200

Issue 6 Revision 1, January 2012

Negl./Negl./Negl. Negl./Negl./Negl. Negl./Negl./Negl. Negl./Negl./Negl.

Equipment reference

Equipment supplier

Equipment PN

QTY

STS

Engine driven pump

PARKER

4205401

2

SFE

Engine driven pump

EATON AEROSPACE

3031863-001

2

SFE

29.10.110

Page 370

[ 29-4]

Hydraulic power 29

A320 Family

Intentionally left blank

Issue 6 Revision 1, January 2012

29.10.110

Page 371

[ 29-5]

A320 Family

29 Hydraulic power 29.21.104 - Electropumps alternate equipment Objective To provide alternative equipment for the electropumps. Basic aircraft Two electropumps are installed. Description Basic electropumps are replaced by alternate equipment. EPAC selection mode Individual

Issue 6 Revision 1, January 2012

29.21.104

Page 372

[ 29-6]

Hydraulic power 29

A320 Family Figure 29-2 - Electropumps GREEN

BLUE

40 VU

YELLOW PTU

RAT MAN ON

H Y D

ENG 1 PUMP

FAULT OFF

ELEC PUMP

A U T O

ELEC PUMP

H Y D

ENG 2 PUMP FAULT

FAULT

FAULT

OFF

OFF

A U T O

FAULT

OFF

OFF

HYD

Hydraulics bay HYD

GREEN

3000

BLUE

3000

PSI

LEAK MEASUREMENT VALVES

BLUE PUMP OVRD

B

G

Y

ON

OFF

OFF

OFF

YELLOW PSI

3000

PTU RAT ELEC

1

2

LO AIR PRESS

OVHT

TAT +19 C SAT +18 C

GMT 23:56

G.W. 603

T

Electropumps

Issue 6 Revision 1, January 2012

29.21.104

Page 373

[ 29-7]

A320 Family

29 Hydraulic power Table 29-2 - Technical solutions description TDU

Title (Remarks)

Appl.

Weight (kg) MWE/OWE/APL

Std

Electropumps basic equipment - PARKER

A318-100 A319-100 A320-200 A321-200

07

Electropumps alternate equipment - EATON AEROSPACE

A318-100 A319-100 A320-200 A321-200

Issue 6 Revision 1, January 2012

Negl./Negl./Negl. Negl./Negl./Negl. Negl./Negl./Negl. Negl./Negl./Negl.

Equipment reference

Equipment supplier

Equipment PN

QTY

STS

Electric Motor Pump (EMP)

PARKER

51154-04

2

SFE

Electric Motor Pump (EMP)

EATON AEROSPACE

974540

2

SFE

29.21.104

Page 374

[ 29-8]

A320 Family

Ice and rain protection 30

Reference

Title

30.41.102

Installation of intermittent function of windshield wipers

30.70.108

Extended freezing protection

30.81.105

Installation of dual advisory ice detection system

Issue 6 Revision 1, January 2012

Page 375

[ 30-1]

A320 Family

30 Ice and rain protection

30.41.102 - Installation of intermittent function of windshield wipers Objective To permit intermittent operation of the windshield wipers. Basic aircraft Two windshield wipers with two speeds selectable from the overhead panel: • slow 95 sweeps per minute • fast 140 sweeps per minute. Description The modification consists in adding an intermittent sweeping function (approximately one sweep each seven second). This entails the following: • on the overhead panel, the windshield wiper control switches are replaced by switches incorporating an intermittent sweeping position • the two motor-converters are replaced by new interchangeable units • additional wiring is installed between overhead panel and wiper motors. EPAC selection mode Individual

Issue 6 Revision 1, January 2012

30.41.102

Page 376

[ 30-2]

Ice and rain protection 30

A320 Family

Figure 30-1 - Windshield wipers

WIPER

WIPER

OFF

OFF INTMT

INTMT SLOW

SLOW

FAST

FAST

Issue 6 Revision 1, January 2012

30.41.102

Page 377

[ 30-3]

A320 Family

30 Ice and rain protection Table 30-1 - Technical solutions description TDU

Title (Remarks)

Appl.

Weight (kg) MWE/OWE/APL

01

Installation of intermittent function of windshield wipers

Issue 6 Revision 1, January 2012

A318-100 A319-100 A320-200 A321-200

1.5/1.5/-1.5 1.5/1.5/-1.5 1.5/1.5/-1.5 1.5/1.5/-1.5

Equipment reference

Equipment supplier

Equipment PN

QTY

STS

Timer

ECE

4307807

2

SFE

Windshield wiper motor left

ECE

4307792

1

SFE

Windshield wiper motor right

ECE

4307785

1

SFE

30.41.102

Page 378

[ 30-4]

Ice and rain protection 30

A320 Family

Intentionally left blank

Issue 6 Revision 1, January 2012

30.41.102

Page 379

[ 30-5]

A320 Family

30 Ice and rain protection 30.70.108 - Extended freezing protection Objective To provide suitable protection against freezing of the water/waste system for : • extended duration flights (long term and cold) • extended ground operations • flights with low water consumption.

Note The protection of galley water lines is part of galley manufacturer. EPAC selection mode Individual

Basic aircraft The water/waste system is protected against freezing under standard operation conditions. Description The potable water tank is insulated and the water pipes in the under floor compartment are electrically heated and insulated. The waste tank drain line is electrically heated and insulated. The water/waste freezing protection is extended to operate: • under extended flight conditions (long term and cold) or during flights with low water consumption or • during turnaround and after prolonged parking and • under extended flight conditions (long term and cold) or during flights with low water consumption.

Issue 6 Revision 1, January 2012

30.70.108

Page 380

[ 30-6]

Ice and rain protection 30

A320 Family

Table 30-2 - Technical solutions description TDU

Title (Remarks)

Appl.

Weight (kg) MWE/OWE/APL

02

Water/waste freezing protection for extended flight conditions Lead-time constraints 8 months

03

Water/waste freezing protection for turnaround, prolonged parking and extended flight conditions

A318-100 A319-100 A320-200 A321-200

27.0/27.0/-27.0 29.0/29.0/-29.0 31.0/31.0/-31.0 34.0/34.0/-34.0

A318-100 A319-100 A320-200 A321-200

29.0/29.0/-29.0 31.0/31.0/-31.0 33.0/33.0/-33.0 36.0/36.0/-36.0

Equipment reference

Equipment supplier

Equipment PN

QTY

STS

Lead-time constraints 8 months

Issue 6 Revision 1, January 2012

30.70.108

Page 381

[ 30-7]

A320 Family

30 Ice and rain protection 30.81.105 - Installation of dual advisory ice detection system Objective To provide the flight crew with an additional means of identifying icing conditions. Basic aircraft Indication of airframe icing can be seen by the accumulation of ice on the visual ice indicator, a black rod located between the two cockpit windshields or on the windshield wipers. Description The dual advisory detection system is added to the basic aircraft system (above) to facilitate the objective (above). It provides two (dual) messages: • ICE DETECTED (amber caution message) • SEVERE ICE DETECTED (amber caution message). The dual advisory ice detection principle works on a frequency variation due to ice accumulation on the two sensing elements located on the fuselage nose.

Issue 6 Revision 1, January 2012

When icing conditions are detected two levels of warnings and their respective recommended actions are provided to the crew in the lower part of the ECAM Engine/ Warning display: • "ICE DETECTED" caution message (amber) implies "eng anti ice ON" action (cyan) • "SEVERE ICE DETECTED" caution message (amber) implies "wing anti-ice ON" action (cyan). As soon as the corresponding push buttons are pressed "ON", the engine anti-ice and/or wing anti-ice memos are displayed in green on the "MEMO" page. • when icing conditions are no longer detected and wing anti-icing is activated, the message "ICE NOT DET" is displayed to remind the crew that the anti-ice systems can be selected "OFF", hence saving fuel. Note The dual advisory ice detection system is operative in flight only. The modification consists of : • modification of structure (drilling two holes and reinforcements) and installation of two ice detection sensors in the lower fuselage nose section • installation of additional circuit breakers and associated wiring

30.81.105

Page 382

[ 30-8]

Ice and rain protection 30

A320 Family

30.81.105 - Installation of dual advisory ice detection system (Continued) • activation of FWCs and CFDIU pin programs (no pin program for this function on the SDACs). EPAC selection mode Individual

Issue 6 Revision 1, January 2012

30.81.105

Page 383

[ 30-9]

A320 Family

30 Ice and rain protection Figure 30-2 - Ice detection system

SDAC

2 1

Ice-det sensors

ICE-DET 1

2

E/W ECAM

FWC

2 1

MCDU

BRT

DIR

CFDIU

AIR PORT

F M

30.81.105

PERF

INIT

DATA

RAD NAV

FUEL PRED

SEC F-PLN

ATC COMM BRT

FUEL PRED

INIT SEC F-PLN

DATA

A

1 4

1

2

37

4

5

6

7

8

9 +

-

2

F

5

B

COMM

6

H

HP I QJ R

K

L

P

0

Q +

U

V

W

X

Y

Z

/

SP

OVFY

CLR

8

9 -

D

MCDU MENU

E

MENU

G

CKD L EM

3

G

OFF

OFF

A BMCDUC ATC F

F A I L

F M

0

Issue 6 Revision 1, January 2012

PROG

RAD NAV

F-PLN

F A I L

DIR F-PLN AIR PERF PORT

PROG

M U N V OW R Z S / T SP

I

J

N

O

M C D U

S X

M E N U OVFY

T

M C D U M E N U

Y CLR

Page 384

[ 30-10]

Ice and rain protection 30

A320 Family

Table 30-3 - Technical solutions description TDU

Title (Remarks)

Appl.

Weight (kg) MWE/OWE/APL

01

Installation of dual advisory ice detection system

Issue 6 Revision 1, January 2012

A318-100 A319-100 A320-200 A321-200

1.5/1.5/-1.5 1.5/1.5/-1.5 1.5/1.5/-1.5 1.5/1.5/-1.5

Equipment reference

Ice detection sensor

30.81.105

Equipment supplier

ROSEMOUNT INC

Equipment PN

0871DP4

QTY

2

Page 385

STS

SFE

[ 30-11]

A320 Family

30 Ice and rain protection

Intentionally left blank

Issue 6 Revision 1, January 2012

30.81.105

Page 386

[ 30-12]

A320 Family

Indicating/recording systems 31

Reference

Title

31.00.107

US units for indicators and labels

31.14.103

Overhead panel toggle switches re-orientation

31.33.051

Flight Data Interface and Management Unit (FDIMU) alternate equipment

31.33.132

Installation of Quick Access Recorder (QAR/WGL-QAR)

31.33.200

Solid State Flight Data Recorder (SSFDR) alternate equipment

31.33.210

Digital Flight Data Recorder System (DFDRS) capabilities

31.36.161

Installation of Digital AIDS Recorder (DAR/WGL-DAR) (BFE)

31.60.114

Indication of metric altitude on Primary Flight Display (PFD)

31.60.120

Installation of Electronic Instrument System (EIS2)

31.65.100

Activation of Minimum Off Route Altitude (MORA) on Navigation Display (ND)

Issue 6 Revision 1, January 2012

Page 387

[ 31-1]

31 Indicating/recording systems

A320 Family

31.00.107 - US units for indicators and labels Objective To provide US units of measurement for airline operational commonality. Basic aircraft • temperature is in degrees Celsius (deg C) • length is in meters (m) • the weight and fuel quantity are in kilograms (kg) • the fuel flow is in kilograms per hour (kg/h) • the hydraulic fluid is in litres (l) • altitudes are in feet (ft). Description The modification consists in replacing metric units with US units on indicators and labels of the aircraft: • cabin and duct temperature are in degrees Fahrenheit (deg F), all other temperature indications remain in DEG C • lengths (runway) are in feet (ft) • fuel weight is in pounds and fuel flow is in pounds per hour (lb/h) • hydraulic fluid quantity indicator is replaced by one with a US gallon scale. EPAC selection mode Individual

Issue 6 Revision 1, January 2012

31.00.107

Page 388

[ 31-2]

Indicating/recording systems 31

A320 Family

Figure 31-1 - Units of measurements

Unit of measurement

Basic unit

Optional unit

C

F

metres

feet

Display on MCDU

3 - Weights Aircraft weight fuel indication and fuel flow

kg kg kg/hr

lbs lbs lbs/hr

Display of weight on ECAM and in FCOM* Overhead panel, refuel/defuel panel and MCDU *and all operations related documentation

4 - Volume Hydraulic fluid quantity

l

US gallon

Quantity indicator of green system ground service panel (LH rear belly fairing)

1 - Temperature (environmental) 2 - Length (Runway)

Issue 6 Revision 1, January 2012

31.00.107

Repercussions

Duct and cabin temperature on ECAM and FAP

Page 389

[ 31-3]

A320 Family

31 Indicating/recording systems Table 31-1 - Technical solutions description TDU

Title (Remarks)

Appl.

Weight (kg) MWE/OWE/APL

Std

Basic metric units for indicators and labels

A318-100 A319-100 A320-200 A321-200

14

US units for indicators and labels

A318-100 A319-100 A320-200 A321-200

Issue 6 Revision 1, January 2012

Equipment reference

Equipment supplier

Equipment PN

QTY

STS

Negl./Negl./Negl. Negl./Negl./Negl. Negl./Negl./Negl. Negl./Negl./Negl.

31.00.107

Page 390

[ 31-4]

A320 Family

Indicating/recording systems 31

Intentionally left blank

Issue 6 Revision 1, January 2012

31.00.107

Page 391

[ 31-5]

31 Indicating/recording systems

A320 Family

31.14.103 - Overhead panel toggle switches re-orientation Objective To provide operational commonality in terms of overhead panel switches orientation with the exception of the ANN LT switch, for which only the BRT and DIM positions are inverted (test position is not changed). Basic aircraft OFF position for the overhead panel toggle switches is downwards. Description All toggle switches on the overhead panel are inverted with the exception of the ANN LT switch, for which only the BRT and DIM positions are inverted (test position is not changed). EPAC selection mode Individual

Issue 6 Revision 1, January 2012

31.14.103

Page 392

[ 31-6]

A320 Family

Indicating/recording systems 31

Figure 31-2 - Overhead panel (25 VU) toggle switches re-orientation Pre-mod ANTI - ICE

PROBE/WINDOW

25VU

CABIN PRESS DITCHING

WING

ENG 1

FAULT

FAULT

ON

ON

HEAT

ENG 2 A U T O

FAULT ON

A U T O

ON

UP

A U T O

LDG ELEV AUTO -2

MODE SEL

MAN Y/S CTL

A U T O

FAULT MAN DN

14

0 2

12 10 8

EXT LT STROBE

BEACON

WING

NAV

ON

ON

ON

2

A U T O OFF

STBY COMPAS

FAULT ON OFF

OFF

OFF

RWY TURN OFF

SEAT BELTS

NO SMOKING

ON

ON

START

NOSE

R

TAXI ON OFF

RETRACT

BRT

OFF

DIM

EMER EXIT LT ON

A U T O

AVAIL OFF

TEST

DIM

SIGNS

T.O.

ON

BRT

OFF

OFF

LAND L

ON

BRT

ANN LT

DOME

MASTER SW

1

6

INT LT

OVHD INTEG LT

APU

ON

4

ARM

OFF

OFF OFF

OFF

OFF

ON

Post-mod

OFF

ANTI - ICE

PROBE/WINDOW

WING

ENG 1

FAULT

FAULT

ON

ON

HEAT

ENG 2 A U T O

FAULT ON

A U T O

ON

UP

A U T O

A U T O

FAULT MAN DN

EXT LT WING OFF

BEACON OFF A U T O

ON

14

0 2

12 10

STBY COMPASS

ON

FAULT

RETRACT

BRT

START

NOSE

SEAT BELTS OFF

NO SMOKING OFF

OFF TAXI

ON

T.O.

ON ON

Issue 6 Revision 1, January 2012

31.14.103

DIM

BRT

BRT

SIGNS EMER EXIT LT A U T O

AVAIL OFF

TEST

DIM

ON

2 R

ANN LT

DOME OFF

OFF

LAND

6

INT LT

OVHD INTEG LT

ON

L

ON

4

MASTER SW

1

ON

RWY TURN OFF OFF

APU

NAV OFF

DITCHING

LDG ELEV AUTO -2

8

STROBE OFF

25VU

CABIN PRESS MODE SEL

MAN Y/S CTL

OFF

OFF

ARM ON

ON

ON

Page 393

[ 31-7]

A320 Family

31 Indicating/recording systems Table 31-2 - Technical solutions description TDU

Title (Remarks)

Appl.

Weight (kg) MWE/OWE/APL

01

Overhead panel toggle switches re-orientation

Issue 6 Revision 1, January 2012

A318-100 A319-100 A320-200 A321-200

Equipment reference

Equipment supplier

Equipment PN

QTY

STS

Negl./Negl./Negl. Negl./Negl./Negl. Negl./Negl./Negl. Negl./Negl./Negl.

31.14.103

Page 394

[ 31-8]

A320 Family

Indicating/recording systems 31

Intentionally left blank

Issue 6 Revision 1, January 2012

31.14.103

Page 395

[ 31-9]

31 Indicating/recording systems

A320 Family

31.33.051 - Flight Data Interface and Management Unit (FDIMU) alternate equipment Objective To provide alternate vendor for the Flight Data Interface and Management Unit (FDIMU). Basic aircraft To record mandatory parameters complying with the applicable Airworthiness Requirements and to record engines, APU and other systems' parameters for performance and health analysis, a FDIMU with integrated PCMCIA interface is installed. Description The FDIMU with integrated PCMCIA is installed to provide the following functions: • data management function • flight data interface function. The data management function enables: • recording the AIDS data on an optional external Digital AIDS Recorder (DAR) • on request, recording / down loading of pre-programmed compressed data files (SAR data files) and reports • uploading of operational software and customer database.

Issue 6 Revision 1, January 2012

The flight data interface function enables: • recording of mandatory parameters required by the Airworthiness Authorities on a Solid State Flight Data Recorder (SSFDR) or on an optional external Quick Access Recorder (QAR). Note • all FDIMUs shown in this catalogue have 88 parameters capability, to comply with FAR 121.344 • all FDIMUs shown in this catalogue are subject to successful certification • because various PCMCIA cards are available on the open market, the PCMCIA card is not part of the delivered FDIMU • it is recommended to use PCMCIA with static flash memory technology • the PCMCIA disk can be used as a storage device for: - reports, SAR data files, DAR & QAR data - system software and customized database upload. EPAC selection mode Individual

31.33.051

Page 396

[ 31-10]

Indicating/recording systems 31

A320 Family

Figure 31-3 - FDIMU MCDU

Airworthiness requirement inputs

Engine & aircraft data sources

BRT DIR

PROG

PERF

INIT

DATA

F-PLN

RAD NAV

FUEL PRED

SEC F-PLN

ATC COMM BRT

AIR PROG PORT PERF

DIR

INIT

DATA

SEC F-PLN

ATC COMM

BOFF C

A RAD NAV

F-PLN

F A I L

AIR PORT

1

2

4

5

6

7

8

9

0

FDIMU

FDIMU

+

F

G

H

A

B

C KD L E M

F

G

H P I QJ R

7

K8

L9 M U N V O W

P0

Q+ - R Z S / T SP

U

V

W

X

Y

Z

/

SP

OVFY

CLR

-

2 5

3 6

E J

I N M C D U

MCDU MENU

S X

M E N OVFY U

O T

M C D U M E N U

Y CLR

CFDIU (BITE)

(Flight Data Interface and Management Unit)

FDRS

AIDS

Flight Data Interface Unit (FDIU)

Data Management Unit (DMU) Airborne data loader MDDU

PCMCIA card

AMU

SSCVR

3

OFF

D

MCDU MENU

4

1

F M

F A I L

F M

FUEL PRED

SSFDR

QAR

DAR

ATSU

Printer

(ACARS)

Print pushbutton FLOOD LT MED

AIDS

FDR

112VU

PRINT EVENT

OFF

Issue 6 Revision 1, January 2012

31.33.051

BRT

Page 397

[ 31-11]

A320 Family

31 Indicating/recording systems Table 31-3 - Technical solutions description TDU

Title (Remarks)

Appl.

Weight (kg) MWE/OWE/APL

Std

Std

Std

FDIMU (-01-01) - FDIU S/W (8803), DMU S/W (PW01) for P&W - TELEDYNE

FDIMU (-01-01) - FDIU S/W (8803), DMU S/W (CF05) for CFMI - TELEDYNE

FDIMU (-01-01) - FDIU S/W (8803), DMU S/W (IA05) for IAE TELEDYNE

Issue 6 Revision 1, January 2012

A318-100

A318-100 A319-100 A320-200 A321-200

A319-100 A320-200 A321-200

Equipment reference

Equipment supplier

Equipment PN

QTY

STS

Data Management Unit (DMU) S/W

TELEDYNE

D08SAPW01 C00000

1

SFE

Flight Data Interface and Management Unit (FDIMU)

TELEDYNE

2234320-0101

1

SFE

Flight Data Interface Unit (FDIU) S/ W

TELEDYNE

F320-0018803

1

SFE

Data Management Unit (DMU) S/W

TELEDYNE

D09SACF05C 1 00000

SFE

Flight Data Interface and Management Unit (FDIMU)

TELEDYNE

2234320-0101

1

SFE

Flight Data Interface Unit (FDIU) S/ W

TELEDYNE

F320-0018803

1

SFE

Data Management Unit (DMU) S/W

TELEDYNE

D10SAIA05C 00000

1

SFE

Flight Data Interface and Management Unit (FDIMU)

TELEDYNE

2234320-0101

1

SFE

Flight Data Interface Unit (FDIU) S/ W

TELEDYNE

F320-0018803

1

SFE

31.33.051

Page 398

[ 31-12]

Indicating/recording systems 31

A320 Family TDU

Title (Remarks)

Appl.

Weight (kg) MWE/OWE/APL

14

FDIMU (-01-01) - FDIU S/W (0001), DMU S/W (CF05) for CFMI - TELEDYNE Requires prior activation of 1024 w/s capability (CN31.33.210/03)

15

FDIMU (-01-01) - FDIU S/W (0001), DMU S/W (IA05) for IAE TELEDYNE

A318-100 A319-100 A320-200 A321-200

A319-100 A320-200 A321-200

Negl./Negl./Negl. Negl./Negl./Negl. Negl./Negl./Negl. Negl./Negl./Negl.

Negl./Negl./Negl. Negl./Negl./Negl. Negl./Negl./Negl.

Requires prior activation of 1024 w/s capability (CN31.33.210/03)

63

FDIMU ED48A200 - FDIU S/W (040), DMU S/W (-030) for CFMI SAGEM

Issue 6 Revision 1, January 2012

A318-100 A319-100 A320-200 A321-200

Negl./Negl./Negl. Negl./Negl./Negl. Negl./Negl./Negl. Negl./Negl./Negl.

Equipment reference

Equipment supplier

Equipment PN

QTY

STS

Data Management Unit (DMU) S/W

TELEDYNE

D09SACF05C 1 00000

SFE

Flight Data Interface and Management Unit (FDIMU)

TELEDYNE

2234320-0101

1

SFE

Flight Data Interface Unit (FDIU) S/ W

TELEDYNE

F320-0020001

1

SFE

Data Management Unit (DMU) S/W

TELEDYNE

D10SAIA05C 00000

1

SFE

Flight Data Interface and Management Unit (FDIMU)

TELEDYNE

2234320-0101

1

SFE

Flight Data Interface Unit (FDIU) S/ W

TELEDYNE

F320-0020001

1

SFE

Data Management Unit (DMU) S/W

SAGEM

360-04022030

1

SFE

Data Management Unit (DMU) setup database

SAGEM

360-04025030

1

SFE

Flight Data Interface and Management Unit (FDIMU)

SAGEM

ED48A200

1

SFE

Flight Data Interface Unit (FDIU) S/ W

SAGEM

360-04027040

1

SFE

31.33.051

Page 399

[ 31-13]

A320 Family

31 Indicating/recording systems TDU

Title (Remarks)

Appl.

Weight (kg) MWE/OWE/APL

64

65

FDIMU ED48A200 - FDIU S/W (040), DMU S/W (-030) for IAE SAGEM

FDIMU ED48A200 - FDIU S/W (040), DMU S/W (-030) for P&W SAGEM

Issue 6 Revision 1, January 2012

A319-100 A320-200 A321-200

A318-100

Negl./Negl./Negl. Negl./Negl./Negl. Negl./Negl./Negl.

Negl./Negl./Negl.

Equipment reference

Equipment supplier

Equipment PN

QTY

STS

Data Management Unit (DMU) S/W

SAGEM

360-04020030

1

SFE

Data Management Unit (DMU) setup database

SAGEM

360-04023030

1

SFE

Flight Data Interface and Management Unit (FDIMU)

SAGEM

ED48A200

1

SFE

Flight Data Interface Unit (FDIU) S/ W

SAGEM

360-04027040

1

SFE

Data Management Unit (DMU) S/W

SAGEM

360-04109030

1

SFE

Data Management Unit (DMU) setup database

SAGEM

360-04110030

1

SFE

Flight Data Interface and Management Unit (FDIMU)

SAGEM

ED48A200

1

SFE

Flight Data Interface Unit (FDIU) S/ W

SAGEM

360-04027040

1

SFE

31.33.051

Page 400

[ 31-14]

Indicating/recording systems 31

A320 Family TDU

Title (Remarks)

Appl.

Weight (kg) MWE/OWE/APL

68

FDIMU ED48A200 - FDIU S/W (210), DMU S/W (-035) for CFMI SAGEM Requires prior activation of 1024 w/s capability (CN31.33.210/03)

70

FDIMU ED48A200 - FDIU S/W (210), DMU S/W (-045) for IAE SAGEM Requires prior activation of 1024 w/s capability (CN31.33.210/03)

Issue 6 Revision 1, January 2012

A318-100 A319-100 A320-200 A321-200

A319-100 A320-200 A321-200

Negl./Negl./Negl. Negl./Negl./Negl. Negl./Negl./Negl. Negl./Negl./Negl.

Negl./Negl./Negl. Negl./Negl./Negl. Negl./Negl./Negl.

Equipment reference

Equipment supplier

Equipment PN

QTY

STS

Data Management Unit (DMU) S/W

SAGEM

360-04022035

1

SFE

Data Management Unit (DMU) setup database

SAGEM

360-04025035

1

SFE

Flight Data Interface and Management Unit (FDIMU)

SAGEM

ED48A200

1

SFE

Flight Data Interface Unit (FDIU) S/ W

SAGEM

360-04027210

1

SFE

Data Management Unit (DMU) S/W

SAGEM

360-04020045

1

SFE

Data Management Unit (DMU) setup database

SAGEM

360-04023045

1

SFE

Flight Data Interface and Management Unit (FDIMU)

SAGEM

ED48A200

1

SFE

Flight Data Interface Unit (FDIU) S/ W

SAGEM

360-04027210

1

SFE

31.33.051

Page 401

[ 31-15]

31 Indicating/recording systems

A320 Family

31.33.132 - Installation of Quick Access Recorder (QAR/WGL-QAR) Objective To provide a copy of the flight data recorder data. Basic aircraft Full provision for installation of an ARINC 591(function) and ARINC 404 QAR 404 (case size) is made. Description A QAR generally in accordance with ARINC 591 (function) and ARINC 404 (case size) or ARINC 591 (function) and ARINC 600 (case size) is installed using existing full provision in the avionics compartment. It is connected to the FDRS auxiliary output, and records all FDR parameters with the same word assignments and sampling rate. Note If the QAR is ARINC 600 type, the basic provision is automatically adapted. EPAC selection mode Individual

Issue 6 Revision 1, January 2012

31.33.132

Page 402

[ 31-16]

Indicating/recording systems 31

A320 Family

Figure 31-4 - QAR installation

FLOOD LT MED

AIDS

FDR

112VU

PRINT EVENT

OFF

BRT

Event pushbutton 21VU

RCDR GND CTL

ON

CVR ERASE

SSCVR

CVR TEST

A U T O

Control panel SSFDR

QAR

CFDIU AMU

FDRS

Linear Accelerometer

Issue 6 Revision 1, January 2012

31.33.132

SDAC SDAC

SDAC FWC

SDAC DMC

SDAC FCDC

SDAC BSCU

Page 403

CLOCK

[ 31-17]

A320 Family

31 Indicating/recording systems Table 31-4 - Technical solutions description TDU

Title (Remarks)

Appl.

Weight (kg) MWE/OWE/APL

40

41

WGL-QAR (8 GSM/GPRS module) equipped with 256MB PCMCIA memory cards - TELEDYNE (BFE) (ARINC 591/600)

WGL-QAR (8 GSM/GPRS module) equipped with 512MB PCMCIA memory cards - TELEDYNE (BFE) (ARINC 591/600)

Issue 6 Revision 1, January 2012

A318-100 A319-100 A320-200 A321-200

A318-100 A319-100 A320-200 A321-200

4.4/4.4/-4.4 4.4/4.4/-4.4 4.4/4.4/-4.4 4.4/4.4/-4.4

4.4/4.4/-4.4 4.4/4.4/-4.4 4.4/4.4/-4.4 4.4/4.4/-4.4

Equipment reference

Equipment supplier

Equipment PN

QTY

STS

PCMCIA card (2TV1)

TELEDYNE

2234479-0256 1

BFE

PCMCIA card (2TV3)

TELEDYNE

2234480-0256 1

BFE

WGL-DAR/QAR (8 GSM/GPRS modules)

TELEDYNE

2243800-81

1

BFE

WGL-DAR/QAR software

TELEDYNE

2234505-13

1

BFE

PCMCIA card 1

TELEDYNE

2234479-0512 1

BFE

PCMCIA card 3

TELEDYNE

2234480-0512 1

BFE

WGL-DAR/QAR (8 GSM/GPRS modules)

TELEDYNE

2243800-81

1

BFE

WGL-DAR/QAR software

TELEDYNE

2234505-13

1

BFE

31.33.132

Page 404

[ 31-18]

Indicating/recording systems 31

A320 Family TDU

Title (Remarks)

Appl.

Weight (kg) MWE/OWE/APL

42

43

WGL-QAR (4 GSM/GPRS module) equipped with 256MB PCMCIA memory cards - TELEDYNE (BFE) (ARINC 591/600)

WGL-QAR (4 GSM/GPRS module) equipped with 512MB PCMCIA memory cards - TELEDYNE (BFE) (ARINC 591/600)

Issue 6 Revision 1, January 2012

A318-100 A319-100 A320-200 A321-200

A318-100 A319-100 A320-200 A321-200

4.4/4.4/-4.4 4.4/4.4/-4.4 4.4/4.4/-4.4 4.4/4.4/-4.4

4.4/4.4/-4.4 4.4/4.4/-4.4 4.4/4.4/-4.4 4.4/4.4/-4.4

Equipment reference

Equipment supplier

Equipment PN

QTY

STS

PCMCIA card (2TV1)

TELEDYNE

2234479-0256 1

BFE

PCMCIA card (2TV3)

TELEDYNE

2234480-0256 1

BFE

WGL-DAR/QAR (4 GSM/GPRS modules)

TELEDYNE

2243800-73

1

BFE

WGL-DAR/QAR software

TELEDYNE

2234505-13

1

BFE

PCMCIA card 1

TELEDYNE

2234479-0512 1

BFE

PCMCIA card 3

TELEDYNE

2234480-0512 1

BFE

WGL-DAR/QAR (4 GSM/GPRS modules)

TELEDYNE

2243800-73

1

BFE

WGL-DAR/QAR software

TELEDYNE

2234505-13

1

BFE

31.33.132

Page 405

[ 31-19]

31 Indicating/recording systems

A320 Family

31.33.200 - Solid State Flight Data Recorder (SSFDR) alternate equipment Objective To replace the basic SSFDR by an alternate one complying with airworthiness requirements. The SSFDR has the capability to store the last 25 hours of the required mandatory parameters in flight and on ground in a box able to endure severe environment conditions.

Description The basic SSFDR equipment is replaced by alternate equipment.

Basic aircraft One SSFDR is installed in the unpressurized section at the rear part of the aircraft. The SSFDR automatically starts recording: • on ground during the first five minutes following energization of the aircraft electrical network • on ground with one engine running • in flight with engines running or stopped.

EPAC selection mode Individual

Note All equipment are electrically and mechanically interchangeable.

The SSFDR automatically stops recording five minutes after the second engine shutdown. On ground, the SSFDR can be manually energized by pressing the GND CTL pushbutton. An EVENT pushbutton is installed to record an event mark on the SSFDR when a specific event occurred during the flight.

Issue 6 Revision 1, January 2012

31.33.200

Page 406

[ 31-20]

Indicating/recording systems 31

A320 Family

Figure 31-5 - FDR system

FLOOD LT MED

AIDS

FDR

112VU

PRINT EVENT

OFF

BRT

Event pushbutton 21VU

RCDR GND CTL

ON

CVR ERASE

SSCVR

CVR TEST

A U T O

Control panel SSFDR

QAR

CFDIU AMU

FDRS

Linear Accelerometer

Issue 6 Revision 1, January 2012

31.33.200

SDAC SDAC

SDAC FWC

SDAC DMC

SDAC FCDC

SDAC BSCU

Page 407

CLOCK

[ 31-21]

A320 Family

31 Indicating/recording systems Table 31-5 - Technical solutions description TDU

Title (Remarks)

Appl.

Weight (kg) MWE/OWE/APL

Equipment reference

Equipment supplier

Equipment PN

QTY

STS

Flight Data Recorder (FDR)

L3 COMMUNICATIONS

2100-4045-00

1

SFE

Std

SSFDR basic equipment (1024 w/s capable) - L3 COMMUNICATIONS, PN 2100-4045-00

A318-100 A319-100 A320-200 A321-200

14

SSFDR alternate equipment (256 w/s capable) - HONEYWELL

A318-100 A319-100 A320-200 A321-200

Negl./Negl./Negl. Negl./Negl./Negl. Negl./Negl./Negl. Negl./Negl./Negl.

Flight Data Recorder (FDR)

HONEYWELL INC. REDMOND, OLATHE

980-4700-042

1

SFE

22

SSFDR alternate equipment (1024 w/s capable) - HONEYWELL

A318-100 A319-100 A320-200 A321-200

Negl./Negl./Negl. Negl./Negl./Negl. Negl./Negl./Negl. Negl./Negl./Negl.

Flight Data Recorder (FDR)

HONEYWELL INC. REDMOND, OLATHE

980-4750-001

1

SFE

Issue 6 Revision 1, January 2012

31.33.200

Page 408

[ 31-22]

A320 Family

Indicating/recording systems 31

Intentionally left blank

Issue 6 Revision 1, January 2012

31.33.200

Page 409

[ 31-23]

31 Indicating/recording systems

A320 Family

31.33.210 - Digital Flight Data Recorder System (DFDRS) capabilities Objective To comply with the new FAA regulations asking for an increase of the sampling rate for the flight controls parameter recording.

If a QAR is requested, only CN31.33.132/18, /19, /40, / 41, /42, /43, or /45 apply. EPAC selection mode Individual

Basic aircraft The Flight Data Recording system recording speed is 256 words/second. Description In order to comply with the new FAA regulations asking for an increase of the sampling rate for the flight controls parameter recording, the modification consists in the installation of the necessary changes to increase the Flight Data Recording system recording speed from 256 words/second to 1024 words/second. Note This modification requires the following minimum configuration: • FDIMU capable of 1024 w/s • SSFDR capable of 1024 w/s • FCDC standard 58

Issue 6 Revision 1, January 2012

31.33.210

Page 410

[ 31-24]

Indicating/recording systems 31

A320 Family

Table 31-6 - Technical solutions description TDU

Title (Remarks)

Appl.

Weight (kg) MWE/OWE/APL

03

Digital Flight Data Recorder System (DFDRS) 1024 w/s activation

Issue 6 Revision 1, January 2012

A318-100 A319-100 A320-200 A321-200

Equipment reference

Equipment supplier

Equipment PN

QTY

STS

Negl./Negl./Negl. Negl./Negl./Negl. Negl./Negl./Negl. Negl./Negl./Negl.

31.33.210

Page 411

[ 31-25]

31 Indicating/recording systems

A320 Family

31.36.161 - Installation of Digital AIDS Recorder (DAR/WGL-DAR) (BFE) Objective To record the parameters sent by the DMU (raw data type). Basic aircraft Space provision for a DAR is provided in the avionics compartment. Description A DAR generally in accordance with ARINC 591 (function) and ARINC 600 (case size) is installed in the avionics compartment. The DAR is controlled by the DMU as programmed either from the MCDU or using a ground PC station. Note In case of DAR installation, the basic provision is automatically adapted/installed. EPAC selection mode Individual

Issue 6 Revision 1, January 2012

31.36.161

Page 412

[ 31-26]

Indicating/recording systems 31

A320 Family

Figure 31-6 - DAR installation

MCDU

Airworthiness requirement inputs

Engine & aircraft data sources

BRT DIR

PROG

PERF

INIT

DATA

F-PLN

RAD NAV

FUEL PRED

SEC F-PLN

ATC COMM BRT

AIR PROG PORT PERF

DIR

INIT

DATA

BOFF C

A RAD NAV

F-PLN

F M

FUEL PRED

F A I L

AIR PORT

1

2

3

4

5

6

7

8 0

ATC COMM

F

MCDU MENU

G

H

B

C KD L E M

F

G

H P I QJ R

7

K8

L9 M U N V O W

P0

Q+ - R Z S / T SP

U

V

W

X

Y

Z

/

SP

OVFY

CLR

9 +

SEC F-PLN

A

4

1

F M

F A I L

-

2 5

3 6

D

M C D U

OFF MCDU MENU

E

I

J

N

O

S

T

X

Y

M E N OVFY U

M C D U M E N U

CLR

CFDIU (BITE)

FDRS

AIDS

Flight Data Interface Unit (FDIU)

Data Management Unit (DMU)

PCMCIA card

AMU

SSCVR

Airborne data loader MDDU

SSFDR

Issue 6 Revision 1, January 2012

QAR

DAR

31.36.161

Printer

ATSU (ACARS)

Page 413

[ 31-27]

A320 Family

31 Indicating/recording systems Table 31-7 - Technical solutions description TDU

Title (Remarks)

Appl.

Weight (kg) MWE/OWE/APL

40

41

WGL-DAR (8 GSM/GPRS module) equipped with 256MB PCMCIA memory cards - TELEDYNE (BFE) (ARINC 591/600)

WGL-DAR (8 GSM/GPRS module) equipped with 512MB PCMCIA memory cards - TELEDYNE (BFE) (ARINC 591/600)

Issue 6 Revision 1, January 2012

A318-100 A319-100 A320-200 A321-200

A318-100 A319-100 A320-200 A321-200

4.4/4.4/-4.4 4.4/4.4/-4.4 4.4/4.4/-4.4 4.4/4.4/-4.4

4.4/4.4/-4.4 4.4/4.4/-4.4 4.4/4.4/-4.4 4.4/4.4/-4.4

Equipment reference

Equipment supplier

Equipment PN

QTY

STS

PCMCIA card (2TV1)

TELEDYNE

2234479-0256 1

BFE

PCMCIA card (2TV3)

TELEDYNE

2234480-0256 1

BFE

WGL-DAR/QAR (8 GSM/GPRS modules)

TELEDYNE

2243800-81

1

BFE

WGL-DAR/QAR software

TELEDYNE

2234505-13

1

BFE

PCMCIA card 1

TELEDYNE

2234479-0512 1

BFE

PCMCIA card 3

TELEDYNE

2234480-0512 1

BFE

WGL-DAR/QAR (8 GSM/GPRS modules)

TELEDYNE

2243800-81

1

BFE

WGL-DAR/QAR software

TELEDYNE

2234505-13

1

BFE

31.36.161

Page 414

[ 31-28]

Indicating/recording systems 31

A320 Family TDU

Title (Remarks)

Appl.

Weight (kg) MWE/OWE/APL

42

43

WGL-DAR (4 GSM/GPRS module) equipped with 256MB PCMCIA memory cards - TELEDYNE (BFE) (ARINC 591/600)

WGL-DAR (4 GSM/GPRS module) equipped with 512MB PCMCIA memory cards - TELEDYNE (BFE) (ARINC 591/600)

Issue 6 Revision 1, January 2012

A318-100 A319-100 A320-200 A321-200

A318-100 A319-100 A320-200 A321-200

4.4/4.4/-4.4 4.4/4.4/-4.4 4.4/4.4/-4.4 4.4/4.4/-4.4

4.4/4.4/-4.4 4.4/4.4/-4.4 4.4/4.4/-4.4 4.4/4.4/-4.4

Equipment reference

Equipment supplier

Equipment PN

QTY

STS

PCMCIA card (2TV1)

TELEDYNE

2234479-0256 1

BFE

PCMCIA card (2TV3)

TELEDYNE

2234480-0256 1

BFE

WGL-DAR/QAR (4 GSM/GPRS modules)

TELEDYNE

2243800-73

1

BFE

WGL-DAR/QAR software

TELEDYNE

2234505-13

1

BFE

PCMCIA card 1

TELEDYNE

2234479-0512 1

BFE

PCMCIA card 3

TELEDYNE

2234480-0512 1

BFE

WGL-DAR/QAR (4 GSM/GPRS modules)

TELEDYNE

2243800-73

1

BFE

WGL-DAR/QAR software

TELEDYNE

2234505-13

1

BFE

31.36.161

Page 415

[ 31-29]

31 Indicating/recording systems

A320 Family

31.60.114 - Indication of metric altitude on Primary Flight Display (PFD) Objective To provide both, current and selected altitude indication on the PFD in meter upon crew selection (in addition to the basic altitude scale in ft). Basic aircraft Current and selected altitude information in feet on the PFD altitude scale. Selected altitude in meters is displayed on the lower part of the ECAM system display upon crew selection. Description Both current and selected altitudes in meters are displayed upon crew selection on the PFD complementary to the basic altitude scale in feet. EPAC selection mode Individual

Issue 6 Revision 1, January 2012

31.60.114

Page 416

[ 31-30]

Indicating/recording systems 31

A320 Family

Figure 31-7 - Current and selected altitude information on PFD Selected altitude in meters

10360 M

SPD

HDG

LAT

ALT

LVL/CH

V/S

HDG V/S

HDG TRK

V/S FPA

100

SPD MACH

1000

AP 1

PUSH TO LEVEL OFF

AP 2

20

10

10

34000

025

UP

METRIC ALT

20

Selected altitude in feet

60

21 40 20 00

DN

5 LOC

A/THR

EXPED

APPR

10

Metric altitude pushbutton switch

10

020

STD 06490 M

Actual altitude in meters

Issue 6 Revision 1, January 2012

31.60.114

Page 417

[ 31-31]

A320 Family

31 Indicating/recording systems Table 31-8 - Technical solutions description TDU

Title (Remarks)

Appl.

Weight (kg) MWE/OWE/APL

01

Indication of metric altitude on PFD

Issue 6 Revision 1, January 2012

A318-100 A319-100 A320-200 A321-200

Equipment reference

Equipment supplier

Equipment PN

QTY

STS

Negl./Negl./Negl. Negl./Negl./Negl. Negl./Negl./Negl. Negl./Negl./Negl.

31.60.114

Page 418

[ 31-32]

A320 Family

Indicating/recording systems 31

Intentionally left blank

Issue 6 Revision 1, January 2012

31.60.114

Page 419

[ 31-33]

31 Indicating/recording systems

A320 Family

31.60.120 - Installation of Electronic Instrument System (EIS2) Objective To install 6 cockpit LCD display units with video capability in place of the basic cockpit LCD display units. Basic aircraft Six LCD Display Units are installed (without video capability). Description In order to be compatible with the display of real-time video images coming from video sources, the option consists in replacing in the main instrument panel the 6 basic LCD Displays Units (DU) by 6 LCD Displays Units with video capability. A new electronic board is added in the Display Units to achieve the video function. EPAC selection mode Individual

Issue 6 Revision 1, January 2012

31.60.120

Page 420

[ 31-34]

Indicating/recording systems 31

A320 Family

Table 31-9 - Technical solutions description TDU

Title (Remarks)

Appl.

Weight (kg) MWE/OWE/APL

Std

Installation of LCD EIS2 - THALES AVIONICS

A318-100 A319-100 A320-200 A321-200

10

Installation of cockpit display units with video capability

A318-100 A319-100 A320-200 A321-200

Issue 6 Revision 1, January 2012

Equipment reference

Equipment supplier

Equipment PN

QTY

STS

Negl./Negl./Negl. Negl./Negl./Negl. Negl./Negl./Negl. Negl./Negl./Negl.

31.60.120

Page 421

[ 31-35]

31 Indicating/recording systems

A320 Family

31.65.100 - Activation of Minimum Off Route Altitude (MORA) on Navigation Display (ND) Objective To provide Minimum Off Route Altitude (MORA) on the NDs. Basic aircraft None. Description The highest Minimum Off Route Altitude within 80 NM around the actual aircraft position is displayed in hundreds of feet on the NDs (in ROSE-NAV and ARC mode) when constraint option (CSTR) is selected on EFIS control panel and selected range is greater than 40 NM. EPAC selection mode Individual

Issue 6 Revision 1, January 2012

31.65.100

Page 422

[ 31-36]

Indicating/recording systems 31

A320 Family

Table 31-10 - Technical solutions description TDU

Title (Remarks)

Appl.

Weight (kg) MWE/OWE/APL

01

Activation of MORA on ND

Issue 6 Revision 1, January 2012

A318-100 A319-100 A320-200 A321-200

Equipment reference

Equipment supplier

Equipment PN

QTY

STS

Negl./Negl./Negl. Negl./Negl./Negl. Negl./Negl./Negl. Negl./Negl./Negl.

31.65.100

Page 423

[ 31-37]

31 Indicating/recording systems

A320 Family

Intentionally left blank

Issue 6 Revision 1, January 2012

31.65.100

Page 424

[ 31-38]

A320 Family

Landing gear 32

Reference

Title

32.40.113

Wheels and brakes alternate equipment

32.41.111

Main Landing Gear (MLG) tires selection and alternate equipment

32.41.120

Nose Landing Gear (NLG) tires selection

32.48.200

Installation of universal brake cooling fans

32.49.109

Installation of Tire Pressure Indicating System (TPIS) on twin wheel

Issue 6 Revision 1, January 2012

Page 425

[ 32-1]

A320 Family

32 Landing gear 32.40.113 - Wheels and brakes alternate equipment Objective To offer MLG wheels and brakes from an alternate supplier.

• on A321, ABS basic wheels and brakes up to MTOW 89.0 t. Certified up to MTOW 93.0 t with fatigue life limited to 35000 miles (7000 cycles).

Basic aircraft The basic MLG wheels and carbon brakes vendor is MESSIER for the A318/A319/A320 and ABS for the A321.

EPAC selection mode Individual

Description Wheels and carbon brakes are replaced by alternate equipment. Each assembly consists of: • four wheels, each including an inflating valve and provision for receiving an over-pressure valve and electrical pressure transducer for an optional TPIS • four wheel hubcaps • four brakes, each including a temperature sensor with thermocouple, two self-sealing couplings and a kit for the brake attachment to the MLG axle • four axle sleeves. Note • BSCU pin programming modification and further programming through the MCDU are made according to the wheels and brakes selected Issue 6 Revision 1, January 2012

32.40.113

Page 426

[ 32-2]

Landing gear 32

A320 Family Figure 32-1 - Wheels and brakes

Pressure relief valve

TPIS port

Bleed valve

Carbon heat pack 4 rotors

Inflating valve

Drive Keys

NLG wheel

Inflating valve

Vent ports

Piston housing Temperature sensor Piston with automatic adjuster

MLG wheel

Issue 6 Revision 1, January 2012

Wear pin indicator MLG brake

32.40.113

Page 427

[ 32-3]

A320 Family

32 Landing gear Table 32-1 - Technical solutions description TDU

Title (Remarks)

Appl.

Weight (kg) MWE/OWE/APL

Std

Std

07

25

30

Wheels and brakes - ABS

A321-200

Wheels and brakes basic equipment (SEPCARB III PLUS OR with new OPS ANOXY66) MESSIER

A318-100 A319-100 A320-200

Wheels and brakes - ABS

A320-200

Wheels and brakes alternate equipment (DURACARB) GOODRICH

Wheels and brakes alternate equipment - MESSIER/BF GOODRICH

Issue 6 Revision 1, January 2012

A318-100 A319-100 A320-200

A321-200

280.0/280.0/-280.0

27.0/27.0/-27.0 27.0/27.0/-27.0 27.0/27.0/-27.0

38.0/38.0/-38.0

Equipment reference

Equipment supplier

Equipment PN

QTY

STS

Brake unit

ABS

5011586-4

4

SFE

Wheel, main gear

ABS

5011529-3

4

SFE

Brake unit

MESSIER

C20225510

4

SFE

Wheel, main

MESSIER

C20195162

4

SFE

Brake unit

ABS

5011586-4

4

SFE

Wheel, main gear

ABS

5011529-3

4

SFE

Brake unit

GOODRICH

2-1684

4

SFE

Wheel, main gear

GOODRICH

3-1530

4

SFE

Brake unit

MESSIER-BF GOODRICH

C20534000-1

4

SFE

Wheel, main

MESSIER-BF GOODRICH

C20500100

4

SFE

32.40.113

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[ 32-4]

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A320 Family

Intentionally left blank

Issue 6 Revision 1, January 2012

32.40.113

Page 429

[ 32-5]

A320 Family

32 Landing gear

32.41.111 - Main Landing Gear (MLG) tires selection and alternate equipment Objective To provide a choice of MLG tire suppliers to the customer as well as alternate size. Basic aircraft The basic MLG tires are of 225 mph maximum take-off speed capability. Description The modification consists of: • installation of tires on the MLG wheels • installation of the corresponding inflation pressure labels • adaptation of the height of the door guide (podger) to accommodate the new tire • modification of the pin programming of the BSCU (brake and steering control unit) • modification of the TPIS (if installed) pin programming. Note Tire selection is by RFC procedure. EPAC selection mode Individual

Issue 6 Revision 1, January 2012

32.41.111

Page 430

[ 32-6]

Landing gear 32

A320 Family Figure 32-2 - Main Landing Gear (MLG)

Hinged fairing

Fixed fairing Proximity sensors

Actuating cylinder Tires Door guide (podger)

Steps

Uplock roller Main door Door ramp

Issue 6 Revision 1, January 2012

32.41.111

Page 431

[ 32-7]

A320 Family

32 Landing gear Table 32-2 - Technical solutions description TDU

Title (Remarks)

Appl.

Weight (kg) MWE/OWE/APL

Equipment reference

Equipment supplier

Equipment PN

QTY

STS

01

MLG tires selection - MICHELIN (46X17-R20 radial tires)

A318-100 A319-100 A320-200

0.0/0.0/0.0 0.0/0.0/0.0 0.0/0.0/0.0

Tires, main 46 x 17 R20

MICHELIN

M01103

4

SFE

13

MLG tires selection - MICHELIN (1270X455-R22 radial retreadable tires)

A321-200

16.0/16.0/-16.0

Tires, main 1270 x 455 R22

MICHELIN

M13901

4

SFE

A321-200

10.0/10.0/-10.0

Conventional tire, 49x18-22, MLG

GOODYEAR

498FL2-1

4

SFE

A321-200

16.0/16.0/-16.0

Radial tire retread- MICHELIN able 1270x455R22, MLG

M20101-01

4

SFE

Up to MTOW 89.0 t.

17

MLG tires selection - GOODYEAR (49X18-22 bias tires) Up to MTOW 89.0 t.

23

MLG tires alternate equipment - MICHELIN (1270X455-R22 radial retreadable tires) Up to MTOW 93.5 t.

25

MLG tires selection - BRIDGESTONE (46X17-R20 radial tires)

A318-100 A319-100 A320-200

11.0/11.0/-11.0 11.0/11.0/-11.0 11.0/11.0/-11.0

Radial tire 46x17R20, MLG

BRIDGESTONE

APR06755

4

SFE

26

MLG tires selection - BRIDGESTONE (1270x455-R22/30 radial tires)

A321-200

32.0/32.0/-32.0

Tires, main 1270 x 455 R22

BRIDGESTONE

APR07002

4

SFE

A321-200

48.0/48.0/-48.0

Tires, main 1270 x 455 R22

BRIDGESTONE

APR07010

4

SFE

Up to MTOW 89.0 t.

28

MLG tires alternate equipment - BRIDGESTONE (1270x455R22/32 radial tires) Up to MTOW 93.5 t. Requires prior acceptance of CN32.40.113/20 - Wheels and brakes alternate equipment - MESSIER/BF GOODRICH.

Issue 6 Revision 1, January 2012

32.41.111

Page 432

[ 32-8]

Landing gear 32

A320 Family TDU

Title (Remarks)

Appl.

Weight (kg) MWE/OWE/APL

30

MLG tires selection - GOODYEAR (46x17R20 radial tires)

Issue 6 Revision 1, January 2012

A318-100 A319-100 A320-200

63.0/63.0/-63.0 63.0/63.0/-63.0 63.0/63.0/-63.0

Equipment reference

Radial tire 46x17R20, MLG

32.41.111

Equipment supplier

GOODYEAR

Equipment PN

467Q02-3

QTY

4

Page 433

STS

SFE

[ 32-9]

A320 Family

32 Landing gear 32.41.120 - Nose Landing Gear (NLG) tires selection Objective To provide a choice of NLG tire suppliers to the customer. Basic aircraft The basic NLG tires are of 225 mph maximum take-off speed capability. Description NLG tires are installed in accordance with the customer's choice. Note Tire selection is by RFC procedure. EPAC selection mode Individual

Issue 6 Revision 1, January 2012

32.41.120

Page 434

[ 32-10]

Landing gear 32

A320 Family Figure 32-3 - Nose Landing Gear (NLG)

FWD

Door uplock assembly Gear uplock assembly

Door actuating cylinder

Forward doors

Gear actuating cylinder Downlock actuator Aft doors Drag strut assembly Lock stay

Tires

Issue 6 Revision 1, January 2012

32.41.120

Page 435

[ 32-11]

A320 Family

32 Landing gear Table 32-3 - Technical solutions description TDU

Title (Remarks)

Appl.

Weight (kg) MWE/OWE/APL

Equipment reference

Equipment supplier

Equipment PN

QTY

STS

05

NLG tires selection - MICHELIN (30X8.8-R15 radial tires)

A318-100 A319-100 A320-200 A321-200

0.0/0.0/0.0 0.0/0.0/0.0 0.0/0.0/0.0 0.0/0.0/0.0

Tires, nose

MICHELIN

M08201

2

SFE

12

NLG tires selection - BRIDGESTONE (30X8.8-R15 radial tires)

A318-100 A319-100 A320-200 A321-200

4.0/4.0/-4.0 4.0/4.0/-4.0 4.0/4.0/-4.0 4.0/4.0/-4.0

Radial tire 30x8.8R15, NLG

BRIDGESTONE

APR05145

2

SFE

14

NLG tires selection - GOODYEAR (30x8.8R15 radial tires)

A318-100 A319-100 A320-200 A321-200

6.0/6.0/-6.0 6.0/6.0/-6.0 6.0/6.0/-6.0 6.0/6.0/-6.0

Radial tire 30x8.8R15, NLG

GOODYEAR

309Q62-1

2

SFE

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32.41.120

Page 436

[ 32-12]

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A320 Family

Intentionally left blank

Issue 6 Revision 1, January 2012

32.41.120

Page 437

[ 32-13]

A320 Family

32 Landing gear 32.48.200 - Installation of universal brake cooling fans Objective To cool down the brakes on the ground to decrease turnaround time. Universal brake cooling fans are strongly recommended in the case of a daily network based on several short flights (four or more flights) and short turn-around times (45 minutes).

Note The universal brake cooling fans must be installed with a wheel adaptor kit corresponding to the selected wheels and brakes configuration.

Basic aircraft System provision for ground cooling fans is made. Description The electrical fan motor is located in the wheel axle. The air is drawn by the impeller from the brake side and vented outside. The motor is protected by circuit breakers and controlled by a push-button on the main instrument panel. The fans are automatically switched off upon landing gear retraction, even if the control is in the ON position. The basic aircraft includes system provision for a ground brake cooling fan system installation. The following changes have to be carried out on the aircraft:

Issue 6 Revision 1, January 2012

• installation of modified tachometer/fan motor support, tachometer drive shaft and cover • fan assembly installation • installation of circuit breakers, control push-button, wiring and modification of integral lighting panel • connection of the existing wiring to fan motors, control push-button and circuit breakers.

EPAC selection mode Individual

32.48.200

Page 438

[ 32-14]

Landing gear 32

A320 Family

Figure 32-4 - Universal brake cooling fans LDG GEAR UNLK

UNLK

BRK FAN

A/BRK LO MED MAX DECEL

DECEL

DECEL

ON

ON

ON

UBCF Fan Assy

HOT ON

UNLK

Impeller

A/SKID & NW STEER ON

TPIS connector

OFF

UBCF Motor Assy

Tachometer Auto-Brake Panel

Connector

Wheel adapter

Issue 6 Revision 1, January 2012

32.48.200

Page 439

[ 32-15]

A320 Family

32 Landing gear Table 32-4 - Technical solutions description TDU

Title (Remarks)

Appl.

Weight (kg) MWE/OWE/APL

11

12

Installation of universal brake cooling fans on MESSIER wheels and brakes

Installation of universal brake cooling fans on BF-GOODRICH wheels and brakes

Issue 6 Revision 1, January 2012

A318-100 A319-100 A320-200

A318-100 A319-100 A320-200

30.0/30.0/-30.0 30.0/30.0/-30.0 30.0/30.0/-30.0

30.0/30.0/-30.0 30.0/30.0/-30.0 30.0/30.0/-30.0

Equipment reference

Equipment supplier

Equipment PN

QTY

STS

Tachometer drive shaft

MESSIER

E21350000

4

SFE

UBCF fan ASSY

TECHNOFAN

RU1502U01

4

SFE

UBCF motor ASSY

TECHNOFAN

AE1502U02

4

SFE

Wheel adaptor kit on MB

TECHNOFAN

DR1502C00

4

SFE

Tachometer drive shaft

MESSIER

E21350000

4

SFE

UBCF fan ASSY

TECHNOFAN

RU1502U01

4

SFE

UBCF motor ASSY

TECHNOFAN

AE1502U02

4

SFE

Valve adapter

TECHNOFAN

EVT174-603A

4

SFE

Wheel adaptor kit on BF-Goodrich

TECHNOFAN

DR1502D00

4

SFE

32.48.200

Page 440

[ 32-16]

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A320 Family TDU

Title (Remarks)

Appl.

Weight (kg) MWE/OWE/APL

13

14

Installation of universal brake cooling fans on ABS wheels and brakes

Installation of universal brake cooling fans on MESSIER/BFGOODRICH wheels and brakes

Issue 6 Revision 1, January 2012

A320-200 A321-200

A321-200

30.0/30.0/-30.0 30.0/30.0/-30.0

30.0/30.0/-30.0

Equipment reference

Equipment supplier

Equipment PN

QTY

STS

Tachometer drive shaft

MESSIER

E21350000

4

SFE

UBCF fan ASSY

TECHNOFAN

RU1502U01

4

SFE

UBCF motor ASSY

TECHNOFAN

AE1502U02

4

SFE

wheel adaptor kit on ABS

TECHNOFAN

DR1402A00

4

SFE

Tachometer drive shaft

MESSIER

E21350000

4

SFE

UBCF fan ASSY

TECHNOFAN

RU1502U01

4

SFE

UBCF motor ASSY

TECHNOFAN

AE1502U02

4

SFE

Wheel adaptor kit on MB/BFG

TECHNOFAN

DR1402C00

4

SFE

32.48.200

Page 441

[ 32-17]

A320 Family

32 Landing gear

32.49.109 - Installation of Tire Pressure Indicating System (TPIS) on twin wheel Objective To display MLG and NLG tire pressure, on the ECAM wheel page, giving immediate detection of deflated tires.

EPAC selection mode Individual

Basic aircraft System provision for a TPIS are made. Electrical wiring from wheel axles to avionics compartment, wiring from SDAC, CFDIU to TPIS computer rack. Description Tire pressure indicating system includes: • one sensor on each wheel rim to measure the pressure in each main and nose gear tire (total 6 sensors per aircraft) • one transmission unit inside the wheel axles which transmits the electrical pressure signal from the sensor to the computer (total 6 per aircraft) • TPIS computer located in the avionics compartment sends information to the ECAM for data display (indication is green and turns to amber when low/high pressure is detected), and to FWC for warning messages • pin-programming of TPIS computer in accordance with the aircraft weight and tire size • pin-programming of SDAC 1 and 2.

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32.49.109

Page 442

[ 32-18]

Landing gear 32

A320 Family

Figure 32-5 - Tire Pressure Indicating System (TPIS) Wheel rim TPIS components Pressure sensor Tyre pressure

Transmission unit

TPIS

Wheel 1

Transmission unit

ECAM

computer From other wheels

Electronic module

Axle

Rotating transformer Tachometer

Drive shaft

WHEEL 195

170 1 195

C¡

REL PSI

PSI

195

140 2 195

TAT + 19 ¡C SAT + 18 ¡C

17H03

C¡

140 3

REL

140 4

195

PSI

195

Tyres Pressure Indication

G.W. 60300 KG C.G. 28.1%

System Display

Issue 6 Revision 1, January 2012

32.49.109

Page 443

[ 32-19]

A320 Family

32 Landing gear Table 32-5 - Technical solutions description TDU

Title (Remarks)

Appl.

Weight (kg) MWE/OWE/APL

Equipment reference

Equipment supplier

Equipment PN

QTY

STS

01

Installation of TPIS on MESSIER wheel (A318/A319/A320)

A318-100 A319-100 A320-200

17.0/17.0/-17.0 17.0/17.0/-17.0 17.0/17.0/-17.0

Tire Pressure Indication Computer (TPIC)

LABINAL

1058-34

1

SFE

02

Installation of TPIS on GOODRICH wheel (A318/A319/ A320)

A318-100 A319-100 A320-200

17.0/17.0/-17.0 17.0/17.0/-17.0 17.0/17.0/-17.0

Tire Pressure Indication Computer (TPIC)

LABINAL

1058-34

1

SFE

A320-200

17.0/17.0/-17.0

Tire Pressure Indication Computer (TPIC)

LABINAL

1058-34

1

SFE

Requires prior acceptance of CN32.40.113/25 - Wheels and brakes alternate equipment - GOODRICH

03

Installation of TPIS on ABS wheel (A320) Requires prior acceptance of CN32.40.113/07 - Wheels and brakes alternate equipment - ABS.

04

Installation of TPIS on ABS wheel (A321)

A321-200

17.0/17.0/-17.0

Tire Pressure Indication Computer (TPIC)

LABINAL

1058-34

1

SFE

05

Installation of TPIS on MESSIER wheel (A321)

A321-200

17.0/17.0/-17.0

Tire Pressure Indication Computer (TPIC)

LABINAL

1058-34

1

SFE

Requires prior acceptance of CN32.40.113/30 - Wheels and brakes alternate equipment - MESSIER/BF GOODRICH.

Issue 6 Revision 1, January 2012

32.49.109

Page 444

[ 32-20]

A320 Family

Lights 33

Reference

Title

33.12.109

Changes in cockpit illumination (excluding instrument and panel lighting)

33.43.000

Runway turnoff lights

33.46.000

Taxi and take-off lights

Issue 6 Revision 1, January 2012

Page 445

[ 33-1]

A320 Family

33 Lights

33.12.109 - Changes in cockpit illumination (excluding instrument and panel lighting) Objective To give better illumination of sliding table and chart holder areas. To improve reliability and reduce power consumption. Basic aircraft Basically the A/C is equipped with yellow bulb lamps. Description The sliding table light units and the map reading lights are fitted with LED lamps. The new lights are white and give better illumination. Note Two-way interchangeable. EPAC selection mode Individual

Issue 6 Revision 1, January 2012

33.12.109

Page 446

[ 33-2]

Lights 33

A320 Family Table 33-1 - Technical solutions description TDU

Title (Remarks)

Appl.

Weight (kg) MWE/OWE/APL

02

Installation of brighter LED pilot chart holder and map reading lights

Issue 6 Revision 1, January 2012

A318-100 A319-100 A320-200 A321-200

Equipment reference

Equipment supplier

Equipment PN

QTY

STS

Negl./Negl./Negl. Negl./Negl./Negl. Negl./Negl./Negl. Negl./Negl./Negl.

33.12.109

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[ 33-3]

A320 Family

33 Lights 33.43.000 - Runway turnoff lights Basic aircraft Two runway turnoff lights are installed to provide wide beams for side lighting while taxiing. Description An alternate runway turnoff light from vendor ECE is installed. This modification consists in replacing the sealed beam with a lens/reflector unit containing a replaceable halogen lamp of higher colour temperature. The remainder of the light assembly remains unchanged. This new installation: • prevents transformer overheating and failure • improves lamp lifetime • is fully interchangeable with the GE sealed beam unit. EPAC selection mode Individual

Issue 6 Revision 1, January 2012

33.43.000

Page 448

[ 33-4]

Lights 33

A320 Family Table 33-2 - Technical solutions description TDU

Title (Remarks)

Appl.

Weight (kg) MWE/OWE/APL

Std

Basic runway turnoff lights

A318-100 A319-100 A320-200 A321-200

05

Alternate runway turnoff light ECE

A318-100 A319-100 A320-200 A321-200

Requires prior acceptance of CN33.46.000/04 - Alternate taxi and takeoff lights - ECE

Issue 6 Revision 1, January 2012

Negl./Negl./Negl. Negl./Negl./Negl. Negl./Negl./Negl. Negl./Negl./Negl.

Equipment reference

Equipment supplier

Equipment PN

QTY

STS

Runway turnoff light ECE

8000306Y00

2

SFE

Runway turnoff light ECE

8000281Y00

2

SFE

33.43.000

Page 449

[ 33-5]

A320 Family

33 Lights 33.46.000 - Taxi and take-off lights Basic aircraft One take-off and one fixed position taxi light are installed on the nose landing gear. These lights extinguish automatically upon retraction of the nose landing gear. Description Alternate taxi and take-off lights from vendor ECE shall be installed. This modification consists in replacing the sealed beam with a lens/reflector unit containing a replaceable halogen lamp of higher colour temperature. The remainder of the light assembly remains unchanged. This new installation: • prevents transformer overheating and failure • improves lamp lifetime • is fully interchangeable with the GE sealed beam unit. EPAC selection mode Individual

Issue 6 Revision 1, January 2012

33.46.000

Page 450

[ 33-6]

Lights 33

A320 Family Table 33-3 - Technical solutions description TDU

Title (Remarks)

Appl.

Weight (kg) MWE/OWE/APL

Std

04

Basic taxi and take-off lights

Alternate taxi and take-off lights - ECE Requires prior acceptance of CN33.43.000/05 - Alternate runway turnoff light - ECE.

Issue 6 Revision 1, January 2012

A318-100 A319-100 A320-200 A321-200

A318-100 A319-100 A320-200 A321-200

Negl./Negl./Negl. Negl./Negl./Negl. Negl./Negl./Negl. Negl./Negl./Negl.

Equipment reference

Equipment supplier

Equipment PN

QTY

STS

Take-off light

ECE

4233488

1

SFE

Taxi light

ECE

4236564

1

SFE

Take-off light

ECE

8000283Y00

1

SFE

Taxi light

ECE

8000282Y00

1

SFE

33.46.000

Page 451

[ 33-7]

A320 Family

33 Lights

Intentionally left blank

Issue 6 Revision 1, January 2012

33.46.000

Page 452

[ 33-8]

A320 Family

Navigation 34

Reference

Title

34.00.108

QNH/QFE BARO setting

34.13.105

Installation of aspirated Total Air Temperature (TAT) probes

34.13.106

Pitot probes alternate equipment

34.15.101

Angle Of Attack (AOA) sensors alternate equipment

34.20.203

Integrated Standby Instrument System (ISIS) optional functions

34.35.109

System provision for Head Up Display (HUD) system installation

34.35.110

Installation (based on provision) of Head Up Display (HUD) system

34.41.302

Full single Weather Radar (WXR) system alternate equipment

34.41.310

Installation of dual Weather Radar (WXR) System

34.42.101

Radio altimeters alternate equipment

34.42.117

Radio altitude automatic call-outs

34.43.203

Traffic Alert and Collision Avoidance System (TCAS) alternate equipment (SFE)

34.43.250

Installation of T2CAS

34.43.260

T2CAS - Activation of alternate warnings

34.43.270

Wiring provision for T3CAS

34.43.290

Wiring provision for Aircraft Traffic Situation Awareness (ATSAW)

Issue 6 Revision 1, January 2012

Page 453

[ 34-1]

34 Navigation

A320 Family

Reference

Title

34.43.295

Activation of ATSAW function

34.48.124

Enhanced Ground Proximity Warning System (EGPWS) - alternate equipment

34.48.127

Enhanced Ground Proximity Warning System (EGPWS) alternate warnings

34.48.132

Enhanced Ground Proximity Warning System (EGPWS) - optional functions

34.51.101

Distance Measuring Equipment (DME) interrogators alternate equipment

34.52.117

Automatic Dependent Surveillance - Broadcast (ADS-B OUT)

34.52.133

Compliance with European enhanced surveillance (EHS) regulation

34.52.140

Air Traffic Control (ATC) control panel alternate equipment

34.53.109

Full provision for second Automatic Direction Finder (ADF) system

34.53.111

Single Automatic Direction Finder (ADF) system alternate equipment

34.53.119

Installation of dual Automatic Direction Finder (ADF) system

34.55.102

VHF Omnidirectional Range (VOR)/Marker receivers alternate equipment

34.58.313

Multi Mode Receiver (MMR) alternate equipment

34.58.316

Activation of GLS function

34.58.317

Activation of FLS function

34.58.340

Installation of MLS function for cat IIIb operation hosted by the MMR

Issue 6 Revision 1, January 2012

Page 454

[ 34-2]

Navigation 34

A320 Family

Intentionally left blank

Issue 6 Revision 1, January 2012

Page 455

[ 34-3]

A320 Family

34 Navigation 34.00.108 - QNH/QFE BARO setting Objective To provide air data information based on QFE.

EPAC selection mode Individual

Basic aircraft Possibility to select STD or QNH. The basic air data information is based on QNH. Description The modification consists in making the FMGS system capable of recognizing whether the BARO setting is based on QNH or 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 and the corresponding setting (QFE or QNH) is displayed on the PFDs. This entails the following repercussions: • FCU, FMGCs, DMCs pin programming • pin programming of GPWS to activate QFE/QNH function.

Issue 6 Revision 1, January 2012

34.00.108

Page 456

[ 34-4]

Navigation 34

A320 Family Figure 34-1 - QNH/QFE BARO setting Mode selection

Reference value selection

Settings display 1FD2 A/THR

SPEED

STD

Pull

1013 In Hg

In hPa

Rotating the knob has no effect

20 286 00 80

PULL STD

STD

STD

1FD2 A/THR

SPEED

Push once

QNH

Rotate the knob

1020 In Hg

20 286 00 80

In hPa PULL STD

QNH

1020 QNH

1FD2 A/THR

SPEED

Push again

Rotate the knob

1004 In Hg

20 286 00 80

In hPa PULL STD

QFE

Issue 6 Revision 1, January 2012

QFE

1004 QFE

34.00.108

Page 457

[ 34-5]

A320 Family

34 Navigation Table 34-1 - Technical solutions description TDU

Title (Remarks)

Appl.

Weight (kg) MWE/OWE/APL

01

QNH/QFE BARO setting

Issue 6 Revision 1, January 2012

A318-100 A319-100 A320-200 A321-200

Equipment reference

Equipment supplier

Equipment PN

QTY

STS

0.0/0.0/0.0 0.0/0.0/0.0 0.0/0.0/0.0 0.0/0.0/0.0

34.00.108

Page 458

[ 34-6]

Navigation 34

A320 Family

Intentionally left blank

Issue 6 Revision 1, January 2012

34.00.108

Page 459

[ 34-7]

A320 Family

34 Navigation

34.13.105 - Installation of aspirated Total Air Temperature (TAT) probes Objective To provide a correct TAT measurement on ground for estimation of take-off performance data, even under solar radiation.

• installation of a 3/8 inch diameter air pressure pipe for bleeding air from the cabin pressurization system to the TAT probes • connection of the air pressure pipe into the air conditioning system.

Basic aircraft Two non-aspirated TAT probes are installed.

EPAC selection mode Individual

Description On the ground while the aircraft is stationary solar radiation can heat the probes due to the absence of airflow aircraft static phase. The air inside the probes can become hot, leading to an inaccurate measurement. The existing TAT probes are replaced by two probes fitted with an air suction system. These units are mechanically interchangeable. The following work has to be undertaken: • change of existing electrical connectors

Issue 6 Revision 1, January 2012

34.13.105

Page 460

[ 34-8]

Navigation 34

A320 Family Figure 34-2 - TAT probes

Air flow

Sensing element New TAT probes Pipe routing

Air conditioning system bleed tapping points

Supply air for ejector operation

Issue 6 Revision 1, January 2012

34.13.105

Page 461

[ 34-9]

A320 Family

34 Navigation Table 34-2 - Technical solutions description TDU

Title (Remarks)

Appl.

Weight (kg) MWE/OWE/APL

05

Installation of aspirated TAT probes - BF GOODRICH AEROSPACE

Issue 6 Revision 1, January 2012

A318-100 A319-100 A320-200 A321-200

Negl./Negl./Negl. Negl./Negl./Negl. Negl./Negl./Negl. Negl./Negl./Negl.

Equipment reference

TAT sensor

34.13.105

Equipment supplier

BF GOODRICH AEROSPACE

Equipment PN

0102LM2GE

QTY

2

Page 462

STS

SFE

[ 34-10]

Navigation 34

A320 Family

Intentionally left blank

Issue 6 Revision 1, January 2012

34.13.105

Page 463

[ 34-11]

A320 Family

34 Navigation 34.13.106 - Pitot probes alternate equipment Objective To provide alternate equipment for the pitot probes. Basic aircraft Three pitot probes are installed on the lower front part of the fuselage (frame 10): • the CAPT probe (1) and the STBY probe (3) are installed on the left side • the F/O probe (2) is installed on the right side. Each pitot probe provides its pressure information to each ADIRU through one Air Data Module (ADM). Description The basic pitot probes are replaced by alternate equipment. EPAC selection mode Individual

Issue 6 Revision 1, January 2012

34.13.106

Page 464

[ 34-12]

Navigation 34

A320 Family Figure 34-3 - Pitot probe installation/locations

9DA1 probe-pitot .1 9DA2 probe-pitot .2 9DA3 probe-pitot .3

Quick disconnect coupling Electrical connector

Air flow

Drain hole (one on each side)

Issue 6 Revision 1, January 2012

34.13.106

Page 465

[ 34-13]

A320 Family

34 Navigation Table 34-3 - Technical solutions description TDU

Title (Remarks)

Appl.

Weight (kg) MWE/OWE/APL

Std

Pitot probes basic equipment THALES AVIONICS

A318-100 A319-100 A320-200 A321-200

01

Pitot probes alternate equipment - BF GOODRICH AEROSPACE

A318-100 A319-100 A320-200 A321-200

Issue 6 Revision 1, January 2012

Negl./Negl./Negl. Negl./Negl./Negl. Negl./Negl./Negl. Negl./Negl./Negl.

Equipment reference

Equipment supplier

Equipment PN

QTY

STS

Pitot probe

THALES AVIONICS SA

C16195BA

3

SFE

Pitot probe

BF GOODRICH AEROSPACE

0851 HL

3

SFE

34.13.106

Page 466

[ 34-14]

Navigation 34

A320 Family

Intentionally left blank

Issue 6 Revision 1, January 2012

34.13.106

Page 467

[ 34-15]

A320 Family

34 Navigation 34.15.101 - Angle Of Attack (AOA) sensors alternate equipment Objective To provide alternate vendor for Angle Of Attack (AOA) sensors. Basic aircraft The aircraft is equipped with 3 AOA sensors located on the lower part of the fuselage (frame 25/26): • AOA sensors 1 and 3 are installed on the LH side • AOA sensor 2 is installed on the RH side. Each AOA sensor measures the angle of attack via a small rotating wing-like device positioned in the direction of the airflow. Each sensor provides the angle of attack information to each ADIRU. Description The AOA sensors are replaced by alternate equipment. EPAC selection mode Individual

Issue 6 Revision 1, January 2012

34.15.101

Page 468

[ 34-16]

Navigation 34

A320 Family

Figure 34-4 - Angle Of Attack (AOA) sensors locations

3FP1 sensor - angle of attack . 1 3FP3 sensor - angle of attack . 3 3FP2 sensor - angle of attack . 2

2 dowel pins 8 mounting holes

Issue 6 Revision 1, January 2012

34.15.101

Page 469

[ 34-17]

A320 Family

34 Navigation Table 34-4 - Technical solutions description TDU

Title (Remarks)

Appl.

Weight (kg) MWE/OWE/APL

Std

AOA sensors basic equipment - THALES PN C16291AB

A318-100 A319-100 A320-200 A321-200

01

AOA sensors alternate equipment - BF GOODRICH AEROSPACE

A318-100 A319-100 A320-200 A321-200

Issue 6 Revision 1, January 2012

Negl./Negl./Negl. Negl./Negl./Negl. Negl./Negl./Negl. Negl./Negl./Negl.

Equipment reference

Equipment supplier

Equipment PN

QTY

STS

Angle of attack sen- THALES AVIONsor ICS SA

C16291AB

3

SFE

Angle of attack sen- BF GOODRICH sor AEROSPACE

0861ED

3

SFE

34.15.101

Page 470

[ 34-18]

Navigation 34

A320 Family

Intentionally left blank

Issue 6 Revision 1, January 2012

34.15.101

Page 471

[ 34-19]

A320 Family

34 Navigation

34.20.203 - Integrated Standby Instrument System (ISIS) optional functions Objective To activate optional functions in the 3ATI Integrated Standby Instrument System (ISIS).

Note Each TDU option can be selected independently of the others.

Basic aircraft The following basic functions are activated in the ISIS: • attitude indication (pitch, roll, lateral acceleration) • altitude (Ft) indication • airspeed (Kts) indication • mach number • BARO setting (Hpa) • standard barometric pressure ( std 1013.25 hPa) • LOC and glide/slope received from the ILS / MMR.

EPAC selection mode Individual

Description The following options are available in the system and can be activated by appropriate pin programming: • altitude in meter • BARO setting in inches of mercury (inHg). The above mentioned options have to be selected through the dedicated TDUs. The ISIS is connected to the Flight Data Interface and Management Unit (FDIMU).

Issue 6 Revision 1, January 2012

34.20.203

Page 472

[ 34-20]

Navigation 34

A320 Family Figure 34-5 - ISIS display installation

BUGS

TEST

LS 3910 M

340

+

320

10

10

280

10

10

260 .57

20

20

300

ATT

Issue 6 Revision 1, January 2012

130 40 128 20 00

ISIS with options: - altitude in meters - BARO setting in inHg and hPa

125

1013/29.92

BARO

34.20.203

Page 473

[ 34-21]

A320 Family

34 Navigation Table 34-5 - Technical solutions description TDU

Title (Remarks)

Appl.

Weight (kg) MWE/OWE/APL

02

ISIS optional function - BARO setting in inHg

A318-100 A319-100 A320-200 A321-200

0.0/0.0/0.0 0.0/0.0/0.0 0.0/0.0/0.0 0.0/0.0/0.0

04

ISIS optional function - altitude in meter

A318-100 A319-100 A320-200 A321-200

0.0/0.0/0.0 0.0/0.0/0.0 0.0/0.0/0.0 0.0/0.0/0.0

Issue 6 Revision 1, January 2012

Equipment reference

34.20.203

Equipment supplier

Equipment PN

QTY

Page 474

STS

[ 34-22]

Navigation 34

A320 Family

Intentionally left blank

Issue 6 Revision 1, January 2012

34.20.203

Page 475

[ 34-23]

A320 Family

34 Navigation

34.35.109 - System provision for Head Up Display (HUD) system installation Objective To provide mechanical and electrical provision for Head Up Display (HUD) system installation. Basic aircraft None. Description The system provision comprises mechanical and electrical provisions for the installation of a single HUD system on the captain's side (left hand pilot station). The modification consists in: • modifying the cockpit (left-hand side) primary structure to support the installation of the Head-Up Projector Unit (HPU) and Head-Up Combiner unit (HCU) • installing wirings between the avionics compartment and the cockpit • installation of circuit breaker with safety clip • installation of 6 MCU mounting tray for the HUDC in avionics compartment (shelf 86VU) EPAC selection mode Individual

Issue 6 Revision 1, January 2012

34.35.109

Page 476

[ 34-24]

Navigation 34

A320 Family Table 34-6 - Technical solutions description TDU

Title (Remarks)

Appl.

Weight (kg) MWE/OWE/APL

01

System provision for single HUD system installation

Issue 6 Revision 1, January 2012

A318-100 A319-100 A320-200 A321-200

Equipment reference

Equipment supplier

Equipment PN

QTY

STS

0.5/0.5/-0.5 0.5/0.5/-0.5 0.5/0.5/-0.5 0.5/0.5/-0.5

34.35.109

Page 477

[ 34-25]

A320 Family

34 Navigation

34.35.110 - Installation (based on provision) of Head Up Display (HUD) system Objective To provide pilot with an Head Up Display (HUD) system in order to fly the aircraft head-up in relation to the external scene. Basic aircraft None. Description A Head Up Display (HUD) system is installed to manually fly the aircraft or to monitor the automatic approaches in all the flight phases for which it will be certified. Note Aircraft operation with HUD activated requires dedicated flight crew training. EPAC selection mode Individual

Issue 6 Revision 1, January 2012

34.35.110

Page 478

[ 34-26]

Navigation 34

A320 Family Table 34-7 - Technical solutions description TDU

Title (Remarks)

Appl.

Weight (kg) MWE/OWE/APL

01

Installation (based on provision) of single HUD system CFM engines Certified only on A318/A319/A320 equipped with CFM engines. For A318 equipped with PW engines, or for A320 equipped with IAE engines or for A321 equipped with CFM or IAE engines, to be investigated on a case by case analysis.

Issue 6 Revision 1, January 2012

A318-100 A319-100 A320-200 A321-200

Equipment reference

Equipment supplier

Equipment PN

QTY

STS

27.0/27.0/-27.0 27.0/27.0/-27.0 27.0/27.0/-27.0 27.0/27.0/-27.0

34.35.110

Page 479

[ 34-27]

A320 Family

34 Navigation

34.41.302 - Full single Weather Radar (WXR) system alternate equipment Objective To provide alternate equipment and enhanced functions with regard to the WXR. Basic aircraft A single X-band weather radar system, generally in accordance with ARINC 708A is installed. The transceiver is installed behind the forward pressure bulkhead. One control panel accessible to both pilots is installed on the pedestal. Description Depending on the selection made, some or all of the equipment is replaced. EPAC selection mode Individual

Issue 6 Revision 1, January 2012

34.41.302

Page 480

[ 34-28]

Navigation 34

A320 Family

Figure 34-6 - Single Weather Radar (WXR) system

GS 394 249/16

TAS 388 6 9

3

0

LMG 004 93 NM 18:35

LMG

FF33R

12

.2R

33

ARPT

15

NDB

VOR D

WPT

CSTR

BARO

GAI AGN

40 20

30

60

WXR transceiver

VOR1 CGCM 123 NM

ARC in Hg

10 27

NAV

18

D130M

10

ROSE VOR

160

ILS

hPa

PLAN PULL STD

21 24

320

Range selector

ND (Rose mode) GS 394 TAS 388 249/16

1

0

35

2

LMG 004 93 NM 18:35

3

OL

33

ADF

VOR OFF

34

4

2

1 ADF

VOR

ILS

FD

OFF

Mode selector

CDN ANG AMB AVD 240

CGC

240

LMG

160

WXR antenna

WXR antenna mount (single drive)

VOR1 CGC M 103 NM

160

TILT -3.00 CAL

.2R GAI AGN

ND (Arc mode)

Single control panel (Cockpit pedestal)

Issue 6 Revision 1, January 2012

34.41.302

Page 481

[ 34-29]

A320 Family

34 Navigation Table 34-8 - Technical solutions description TDU

Title (Remarks)

Appl.

Weight (kg) MWE/OWE/APL

Std

02

Full single WXR (ARINC 708A) with PWS activation - ROCKWELL COLLINS, PN -624

Alternate full single WXR (ARINC 708A) with PWS and multiscan (WXR 2100) - ROCKWELL COLLINS, PN -213

Issue 6 Revision 1, January 2012

A318-100 A319-100 A320-200 A321-200

A318-100 A319-100 A320-200 A321-200

Negl./Negl./Negl. Negl./Negl./Negl. Negl./Negl./Negl. Negl./Negl./Negl.

Equipment reference

Equipment supplier

Equipment PN

QTY

STS

Weather radar antenna

ROCKWELL COL- 622-5137-601 LINS

1

SFE

Weather radar antenna mount

ROCKWELL COL- 622-5135-801 LINS

1

SFE

Weather radar con- ROCKWELL COL- 622-5129-021 trol panel LINS

1

SFE

Weather radar transceiver

ROCKWELL COL- 622-5132-624 LINS

1

SFE

Weather radar transceiver mount

ROCKWELL COL- 622-5133-006 LINS

1

SFE

Weather radar antenna

ROCKWELL COL- 622-5137-601 LINS

1

SFE

Weather radar antenna mount

ROCKWELL COL- 622-5135-801 LINS

1

SFE

Weather radar con- ROCKWELL COL- 622-5130-820 trol panel LINS

1

SFE

Weather radar transceiver

ROCKWELL COL- 822-1710-213 LINS

1

SFE

Weather radar transceiver mount

ROCKWELL COL- 622-5133-006 LINS

1

SFE

34.41.302

Page 482

[ 34-30]

Navigation 34

A320 Family TDU

Title (Remarks)

Appl.

Weight (kg) MWE/OWE/APL

03

Alternate full single WXR (ARINC 708A) with PWS activation & autotilt function - HONEYWELL, PN -409 Autotilt function is incompatible with T2CAS (CN34.43.250)

Issue 6 Revision 1, January 2012

A318-100 A319-100 A320-200 A321-200

Negl./Negl./Negl. Negl./Negl./Negl. Negl./Negl./Negl. Negl./Negl./Negl.

Equipment reference

Equipment supplier

Equipment PN

QTY

STS

Weather radar antenna

HONEYWELL INC. REDMOND, OLATHE

2041446-0401 1

SFE

Weather radar antenna mount

HONEYWELL INC. REDMOND, OLATHE

2041444-0403 1

SFE

Weather radar dual control panel

HONEYWELL INC. REDMOND, OLATHE

2041223-3131 1

SFE

Weather radar transceiver

HONEYWELL INC. REDMOND, OLATHE

066-500080409

1

SFE

Weather radar transceiver mount

HONEYWELL INC. REDMOND, OLATHE

2041213-0414 1

SFE

34.41.302

Page 483

[ 34-31]

A320 Family

34 Navigation 34.41.310 - Installation of dual Weather Radar (WXR) System Objective To provide redundancy for the WXR system. Basic aircraft A single X-band weather radar system, generally in accordance with ARINC 708A is installed. The transceiver is installed behind the forward pressure bulkhead. One control panel accessible to both pilots is installed on the pedestal. Description Dual WXR system is installed according to the customer requirements in place of the basic single WXR. EPAC selection mode Individual

Issue 6 Revision 1, January 2012

34.41.310

Page 484

[ 34-32]

Navigation 34

A320 Family

Figure 34-7 - Dual Weather Radar (WXR) system GS 394 249/16

TAS 388 6 9

3

0

LMG 004 93 NM 18:35

LMG

FF33R

12

.2R

33

ARPT

15

NDB

VOR D

WPT

CSTR

BARO

GAI AGN

40 20

30

60

27

VOR1 CGCM 123 NM

ARC in Hg

10

WXR transceiver (basic)

NAV

18

D130M

10

ROSE VOR

160

ILS

PULL STD

21 24

320

Range selector

ND (Rose mode) GS 394 TAS 388 249/16

35

1

0

2

LMG 004 93 NM 18:35

3

OL

33

1 ADF

4

2 VOR

OFF

34

Dual transceiver mount (basic)

hPa

PLAN

ADF

VOR

ILS

FD

OFF

Mode selector

CDN ANG AMB AVD 240

CGC

240

LMG

160

WXR antenna

VOR1 CGC M 103 NM

Second WXR transceiver

WXR antenna mount (dual drive)

OFF 1

WX

TILT -3.00 CAL

.2R GAI AGN

ND (Arc mode)

WX/TURB 2

160

WX RADAR MAP TILT 5

10

GAIN

15 UP 0 DN

AUTO

MAX

15 5

10

Dual control panel (Cockpit pedestal)

Issue 6 Revision 1, January 2012

34.41.310

Page 485

[ 34-33]

A320 Family

34 Navigation Table 34-9 - Technical solutions description TDU

Title (Remarks)

Appl.

Weight (kg) MWE/OWE/APL

03

Dual WXR system (ARINC 708A) with PWS activation and autotilt function - HONEYWELL, PN -409 Autotilt function is incompatible with T2CAS (CN34.43.250)

Issue 6 Revision 1, January 2012

A318-100 A319-100 A320-200 A321-200

14.6/14.6/-14.6 14.6/14.6/-14.6 14.6/14.6/-14.6 14.6/14.6/-14.6

Equipment reference

Equipment supplier

Equipment PN

QTY

STS

Audio mixing box

T.E.A.M

BMA3603AA0 1 1

SFE

Weather radar antenna

HONEYWELL INC. REDMOND, OLATHE

2041446-0401 1

SFE

Weather radar con- HONEYWELL trol panel INC. REDMOND, OLATHE

2041220-3231 1

SFE

Weather radar dual antenna mount

HONEYWELL INC. REDMOND, OLATHE

2041444-0404 1

SFE

Weather radar dual transceiver mount

HONEYWELL INC. REDMOND, OLATHE

2041214-0401 1

SFE

Weather radar transceiver

HONEYWELL INC. REDMOND, OLATHE

066-500080409

SFE

34.41.310

2

Page 486

[ 34-34]

Navigation 34

A320 Family TDU

Title (Remarks)

Appl.

Weight (kg) MWE/OWE/APL

11

12

Dual WXR (ARINC 708A) with PWS and multiscan (WXR 2100) - ROCKWELL COLLINS, PN -213

Dual WXR (ARINC 708A) with PWS activation - ROCKWELL COLLINS, PN -624

Issue 6 Revision 1, January 2012

A318-100 A319-100 A320-200 A321-200

A318-100 A319-100 A320-200 A321-200

14.0/14.0/-14.0 14.0/14.0/-14.0 14.0/14.0/-14.0 14.0/14.0/-14.0

14.0/14.0/-14.0 14.0/14.0/-14.0 14.0/14.0/-14.0 14.0/14.0/-14.0

Equipment reference

Equipment supplier

Equipment PN

QTY

Audio mixing box

T.E.A.M

Weather radar antenna

ROCKWELL COL- 622-5137-601 LINS

1

SFE

Weather radar con- ROCKWELL COL- 622-5130-820 trol panel LINS

1

SFE

Weather radar dual antenna mount

ROCKWELL COL- 622-5136-801 LINS

1

SFE

Weather radar dual transceiver mount

ROCKWELL COL- 622-5134-064 LINS

1

SFE

Weather radar transceiver

ROCKWELL COL- 822-1710-213 LINS

2

SFE

Audio mixing box

T.E.A.M

BMA3603AA0 1 1

SFE

Weather radar antenna

ROCKWELL COL- 622-5137-601 LINS

1

SFE

Weather radar con- ROCKWELL COL- 622-5130-021 trol panel LINS

1

SFE

Weather radar dual antenna mount

ROCKWELL COL- 622-5136-201 LINS

1

SFE

Weather radar dual transceiver mount

ROCKWELL COL- 622-5134-064 LINS

1

SFE

Weather radar transceiver

ROCKWELL COL- 622-5132-624 LINS

2

SFE

34.41.310

BMA3603AA0 1 1

STS

Page 487

SFE

[ 34-35]

A320 Family

34 Navigation 34.42.101 - Radio altimeters alternate equipment Objective To provide alternate vendors for radio altimeters equipment. 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 interchangeable with the basic equipment. EPAC selection mode Individual

Issue 6 Revision 1, January 2012

34.42.101

Page 488

[ 34-36]

Navigation 34

A320 Family Figure 34-8 - Radio altimeters

Aft cargo hold door

Antenna R2 Antenna T2

Antenna R1 Antenna T1

D FW

Radio altimeters

Issue 6 Revision 1, January 2012

34.42.101

Page 489

[ 34-37]

A320 Family

34 Navigation Table 34-10 - Technical solutions description TDU

Title (Remarks)

Appl.

Weight (kg) MWE/OWE/APL

Std

07

11

Radio altimeters basic equipment - THALES AVIONICS

Radio altimeters alternate equipment - ROCKWELL COLLINS 900

Radio altimeters alternate equipment - HONEYWELL, PN 066-50007-0222

Issue 6 Revision 1, January 2012

A318-100 A319-100 A320-200 A321-200

A318-100 A319-100 A320-200 A321-200

A318-100 A319-100 A320-200 A321-200

Negl./Negl./Negl. Negl./Negl./Negl. Negl./Negl./Negl. Negl./Negl./Negl.

Negl./Negl./Negl. Negl./Negl./Negl. Negl./Negl./Negl. Negl./Negl./Negl.

Equipment reference

Equipment supplier

Equipment PN

QTY

STS

Radio altimeter antenna

THALES AVIONICS SA

9599-60712352

4

SFE

Radio altimeter transceiver

THALES AVIONICS SA

9599-60714943

2

SFE

Radio altimeter antenna

ROCKWELL COL- 622-8701-003 LINS

4

SFE

Radio altimeter transceiver

ROCKWELL COL- 822-0334-020 LINS

2

SFE

Radio altimeter antenna

HONEYWELL INC.

071-500260300

4

SFE

Radio altimeter transceiver

HONEYWELL INC.

066-500070222

2

SFE

34.42.101

Page 490

[ 34-38]

Navigation 34

A320 Family

Intentionally left blank

Issue 6 Revision 1, January 2012

34.42.101

Page 491

[ 34-39]

A320 Family

34 Navigation 34.42.117 - Radio altitude automatic call-outs Objective To customize the radio altitude announcements. Basic aircraft The automatic call-out function is integrated in the FWCs and generates synthetic voice announcements of radio altitude. Basic definition gives the following announcements: • altitudes in feet: 2 500, (two thousand five hundred), 1000, 400, 50, 40, 30, 20, 10, 5 (e.g. at 400 ft, the voice says in English "four hundred"). • "hundred above" at DH / MDA / MDH + 100 ft (*) • "minimum" at DH / MDA / MDH (*). (*) DH on PA, MDA on NPA - QFE, MDH on NPA-QNH.

B) The following announcements are also proposed: • 2 500 ft: "twenty five hundred" (refer to paragraph C) • 2 000 ft: "two thousand" • 500 ft: "five hundred" (refer to paragraph D) • 300 ft: "three hundred" • 200 ft: "two hundred" • 100 ft: "one hundred" C) It is strongly recommended to select automatic callout 2500. Basically "two thousand five hundred" is proposed but it can be replaced by "twenty five hundred". D) According to operational requirements for TAWS it is mandatory to select the 400 ft or 500 ft automatic callout (at least one of them).

Description The FWC pin programming shall be modified according to the selected announcements.

Note "Hundred above" and "minimum" automatic callouts cannot be deselected.

A) The following altitude automatic callouts are strongly recommended and should not be deselected from the basic definition: 1 000 - 50 - 40 - 30 - 20 - 10 - 5.

EPAC selection mode Individual

Issue 6 Revision 1, January 2012

34.42.117

Page 492

[ 34-40]

Navigation 34

A320 Family Figure 34-9 - Radio altitude automatic call-outs Announcement

Comments

at 2500 ft: "two thousand five hundred"

Strongly recommended

at 2500 ft: "twenty five hundred"

Strongly recommended (alternate to "Two thousand five hundred")

at 2000 ft: "two thousand" at 1000 ft: "one thousand" at 500 ft: "five hundred"

Strongly recommended 500 ft or 400 ft is mandatory (at least one of them)

at 400 ft: "four hundred"

400 ft or 500 ft is mandatory (at least one of them)

at 300 ft: "three hundred" at 200 ft: "two hundred" at 100 ft: "one hundred" at 50 ft: "fifty"

Strongly recommended

at 40 ft: "forty"

Strongly recommended Strongly recommended

at 30 ft: "thirty" at 20 ft: "twenty" at 10 ft: "ten"

Strongly recommended Strongly recommended

at 5 ft: "five" at DH / MDA / MDH + 100 ft: "hundred above"

Strongly recommended

at DH / MDA / MDH: "minimum"

Cannot be deselected

Cannot be deselected

Basic announcements

Issue 6 Revision 1, January 2012

34.42.117

Page 493

[ 34-41]

A320 Family

34 Navigation Table 34-11 - Technical solutions description TDU

Title (Remarks)

Appl.

Weight (kg) MWE/OWE/APL

01

Radio altitude automatic callouts Customizable. A318-100 : Subject to customer specific study A319-100 : Subject to customer specific study A320-200 : Subject to customer specific study A321-200 : Subject to customer specific study

Issue 6 Revision 1, January 2012

A318-100 A319-100 A320-200 A321-200

0.0/0.0/0.0 0.0/0.0/0.0 0.0/0.0/0.0 0.0/0.0/0.0

Equipment reference

Radio altitude automatic call-outs

34.42.117

Equipment supplier

Equipment PN

TBD

QTY

TBD

Page 494

STS

SFE

[ 34-42]

Navigation 34

A320 Family

Intentionally left blank

Issue 6 Revision 1, January 2012

34.42.117

Page 495

[ 34-43]

A320 Family

34 Navigation

34.43.203 - Traffic Alert and Collision Avoidance System (TCAS) alternate equipment (SFE) Objective To provide alternate equipment for the TCAS delivered as SFE. Basic aircraft A TCAS SFE is installed, generally in accordance with ARINC 735. TCAS equipment is software change 7, also known as ACAS II. The transponder is basically capable of European elementary surveillance. Description Installation of alternate TCAS consists of: • TCAS computer and associated antennas (2) • TCAS compatible ATC transponder, mode S. Note • ELS: ELementary Surveillance, EHS: EnHanced Surveillance • for alternate ATC/TCAS control panel installation, see item CN34.52.140. EPAC selection mode Individual

Issue 6 Revision 1, January 2012

34.43.203

Page 496

[ 34-44]

Navigation 34

A320 Family Figure 34-10 - TCAS system STBY AUTO ON ATC

1

1

2

A T C OFF

4

ON

FAIL

2 5

3 6

ALL ABV THRT BLW

7

0

T C A S

IDENT STBY

TA

TCAS antenna

TA/RA

CLR

ALT RPTG

ATC/TCAS control panel

FMGC 2

Location of ATC/TCAS antennas ATC mode S 1/ ATC mode S 2

ATC 1 mode S capable

TCAS

FWC

1

2

2 FMGC 1

Windshear stall inhibit Mount for

ALT limit

TCAS

Synth. voice

EIS displays

DMC

1

2

3

CFDIU Inhibit

ATC 1/ATC 2

TCAS

GPWS

FDIU TCAS antenna

Issue 6 Revision 1, January 2012

34.43.203

Page 497

[ 34-45]

A320 Family

34 Navigation Table 34-12 - Technical solutions description TDU

Title (Remarks)

Appl.

Weight (kg) MWE/OWE/APL

Std

10

TCAS change 7 - HONEYWELL TPA 100 / ATC ELS, EHS - HONEYWELL (-1402)

TCAS change 7.1 alternate equipment - HONEYWELL TPA100B / ATC ELS, EHS - HONEYWELL (-1402)

Issue 6 Revision 1, January 2012

A318-100 A319-100 A320-200 A321-200

A318-100 A319-100 A320-200 A321-200

Negl./Negl./Negl. Negl./Negl./Negl. Negl./Negl./Negl. Negl./Negl./Negl.

Equipment reference

Equipment supplier

Equipment PN

QTY

STS

ATC mode S transponder

HONEYWELL INC. REDMOND, OLATHE

066-011271402

2

SFE

TCAS directional antenna

HONEYWELL INC. REDMOND, OLATHE

071-500018104

2

SFE

TCAS II computer

HONEYWELL INC. REDMOND, OLATHE

940-0300-001

1

SFE

ATC mode S transponder

HONEYWELL INC. REDMOND, OLATHE

066-011271402

2

SFE

TCAS directional antenna

HONEYWELL INC. REDMOND, OLATHE

071-500018104

2

SFE

TCAS II computer

HONEYWELL INC. REDMOND, OLATHE

940-0351-001

1

SFE

34.43.203

Page 498

[ 34-46]

Navigation 34

A320 Family TDU

Title (Remarks)

Appl.

Weight (kg) MWE/OWE/APL

39

61

TCAS change 7.1 - ACSS 2000 / ATC ELS, EHS - ACSS (-10100) DO-260A

TCAS change 7.1 - ROCKWELL COLLINS 921 / ATC ELS, EHS ROCKWELL COLLINS 901

Issue 6 Revision 1, January 2012

A318-100 A319-100 A320-200 A321-200

A318-100 A319-100 A320-200 A321-200

Negl./Negl./Negl. Negl./Negl./Negl. Negl./Negl./Negl. Negl./Negl./Negl.

Negl./Negl./Negl. Negl./Negl./Negl. Negl./Negl./Negl. Negl./Negl./Negl.

Equipment reference

Equipment supplier

Equipment PN

QTY

STS

ATC mode S transponder

ACSS-AN L3 COMMUNICATIONS/THALES

751-780010100

2

SFE

TCAS directional antenna

ACSS-AN L3 COMMUNICATIONS/THALES

751-4081-911

2

SFE

TCAS II computer

ACSS-AN L3 COMMUNICATIONS/THALES

751-790010020

1

SFE

ATC mode S transponder

ROCKWELL COL- 822-1338-021 LINS

2

SFE

TCAS directional antenna

ROCKWELL COL- 622-8973-104 LINS

2

SFE

TCAS II computer

ROCKWELL COL- 822-1293-332 LINS

1

SFE

34.43.203

Page 499

[ 34-47]

A320 Family

34 Navigation 34.43.250 - Installation of T2CAS

Buyer to verify with the relevant states in which the Buyer operates, the correctness of the information contained in the terrain database. Errors in the terrain data shall be reported to the relevant states and the supplier of the related equipment. In no case shall Airbus be held responsible or liable for the contents, acquisition, use or updating of the terrain data base.

Objective To install a T²CAS system and ATC Mode S transponder. Vendor selection for the ATC Transponder is required. Basic aircraft EGPWS, TCAS and ATC Transponder are installed. Description The EGPWS and TCAS are replaced by T²CAS which provides both TAWS & TCAS functions in the same equipment. T²CAS manufactured by ACSS is installed in the same location as the TCAS. Customer choice is required for the supplier of the ATC Transponder.

EPAC selection mode Individual

Note • for ATC TCAS control panel selection, see item CN34.52.140 • incompatible with weather radar autotilt function (CN34.41.300/03 and CN34.41.310/03) • the contents of the terrain database are made available by the various states, which are members of the ICAO world organization, to the supplier. Each state is responsible for the definition of the content of the terrain database. It shall be the responsibility of the

Issue 6 Revision 1, January 2012

34.43.250

Page 500

[ 34-48]

Navigation 34

A320 Family Table 34-13 - Technical solutions description TDU

Title (Remarks)

Appl.

Weight (kg) MWE/OWE/APL

20

Install. of T2CAS - ACSS (11111)/ATC - ACSS (-10100) DO-260A - lateral GPS posit. with auto desel.

Issue 6 Revision 1, January 2012

A318-100 A319-100 A320-200 A321-200

Negl./Negl./Negl. Negl./Negl./Negl. Negl./Negl./Negl. Negl./Negl./Negl.

Equipment reference

Equipment supplier

Equipment PN

QTY

ATC mode S transponder

ACSS-AN L3 COMMUNICATIONS/THALES

751-780010100

Enhanced Ground Proximity Warning Computer (EGPWC)

HONEYWELL INC. REDMOND, OLATHE

965-1676-00X -1

SFE

T2CAS computer

ACSS-AN L3 COMMUNICATIONS/THALES

900000011111

1

SFE

TCAS directional antenna

ACSS-AN L3 COMMUNICATIONS/THALES

751-4081-911

2

SFE

34.43.250

2

STS

Page 501

SFE

[ 34-49]

A320 Family

34 Navigation 34.43.260 - T2CAS - Activation of alternate warnings Objective To propose alternate warnings for the Ground Collision Avoidance Module (GCAM) within the T2CAS in line with FAA recommendations. Basic aircraft The basic GCAM aural and visual annunciation is in line with the EASA/JAA requirements: Caution annunciation: "Terrain ahead !" voice associated with visual amber "TERR AHEAD" message on Navigation Display. Warning annunciation: "Terrain ahead, pull-up ! , pull-up ! ..." voice associated with visual red "TERR AHEAD" message on Navigation Display. Avoid Terrain: "Avoid Terrain!" voice associated with red "TERRAIN" message on Navigation Display.

Warning annunciation: "Terrain, Terrain, pull-up ! , pullup ! ..." voice associated with visual red "TERRAIN" message on Navigation Display. Avoid Terrain: "Avoid Terrain!" voice associated with visual red "TERRAIN" message on Navigation Display is unchanged. Note Requires prior installation of a T2CAS. EPAC selection mode Individual

Description The modification consists of activation of the alternate FAA recommended wording which is selectable by pin programming: Caution annunciation: "Caution Terrain !" voice associated with visual amber "TERRAIN" message on Navigation Display. Issue 6 Revision 1, January 2012

34.43.260

Page 502

[ 34-50]

Navigation 34

A320 Family Table 34-14 - Technical solutions description TDU

Title (Remarks)

Appl.

Weight (kg) MWE/OWE/APL

01

T2CAS - Activation of announcements (aural and visual) in compliance with FAA wording

Issue 6 Revision 1, January 2012

A318-100 A319-100 A320-200 A321-200

Equipment reference

Equipment supplier

Equipment PN

QTY

STS

0.0/0.0/0.0 0.0/0.0/0.0 0.0/0.0/0.0 0.0/0.0/0.0

34.43.260

Page 503

[ 34-51]

A320 Family

34 Navigation 34.43.270 - Wiring provision for T3CAS Objective To allow later installation of a T3CAS. Basic aircraft A TCAS SFE is installed, generally in accordance with ARINC 735. TCAS equipment is software change 7, also known as ACAS II. The transponder is basically capable of European elementary surveillance. Description Wiring provision shall be made in the avionics compartment for later installation of a T3CAS. The modification consists in installing additional wiring between the ATC transponder rack and the TCAS rack for future used by the T3CAS. Note T3CAS is to be used in conjunction with a transponder ACSS DO-260A. EPAC selection mode Individual

Issue 6 Revision 1, January 2012

34.43.270

Page 504

[ 34-52]

Navigation 34

A320 Family Table 34-15 - Technical solutions description TDU

Title (Remarks)

Appl.

Weight (kg) MWE/OWE/APL

01

Wiring provision for T3CAS

Issue 6 Revision 1, January 2012

A318-100 A319-100 A320-200 A321-200

Equipment reference

Equipment supplier

Equipment PN

QTY

STS

1.0/1.0/-1.0 1.0/1.0/-1.0 1.0/1.0/-1.0 1.0/1.0/-1.0

34.43.270

Page 505

[ 34-53]

A320 Family

34 Navigation

34.43.290 - Wiring provision for Aircraft Traffic Situation Awareness (ATSAW) Objective To allow later activation of Aircraft Traffic Situation Awareness (ATSAW) function. Basic aircraft None. Description Complete wiring provision for later activation of ATSAW function is provided. ATSAW applications aim at enhancing the flight crews' knowledge of the surrounding traffic information. The principle is to use a Cockpit Display Traffic Information (CDTI) that provides permanently updated traffic information received via ADS-B using mode S 1090 MHz. ATSAW enhances the traffic situational awareness with the objective to improve the efficiency and the safety of the flight. EPAC selection mode Individual

Issue 6 Revision 1, January 2012

34.43.290

Page 506

[ 34-54]

Navigation 34

A320 Family Table 34-16 - Technical solutions description TDU

Title (Remarks)

Appl.

Weight (kg) MWE/OWE/APL

01

Wiring provision for Aircraft Traffic Situation Awareness (ATSAW)

Issue 6 Revision 1, January 2012

A318-100 A319-100 A320-200 A321-200

Equipment reference

Equipment supplier

Equipment PN

QTY

STS

1.0/1.0/-1.0 1.0/1.0/-1.0 1.0/1.0/-1.0 1.0/1.0/-1.0

34.43.290

Page 507

[ 34-55]

A320 Family

34 Navigation 34.43.295 - Activation of ATSAW function Objective To enhance the efficiency and the safety of the flight thanks to a better traffic situational awareness. Basic aircraft None. Description Airborne Traffic Situational AWareness (ATSAW) aims at enhancing the flight crews' knowledge of the surrounding traffic information. The principle is to display permanently updated traffic information received via ADS-B using mode S 1090 MHz.

Using a traffic selector switch, crew can select a specific aircraft to get more information as aircraft identification and ground speed. More information is available on MCDU selecting the specific Traffic page. ATSAW function: • enhances the opportunity to flight level change • optimizes the flight level and generates fuel savings • improves cooperation with ATC (better understanding of ATC instructions) EPAC selection mode Individual

With ATSAW, the surrounding traffic information displayed by default on ND is: • the aircraft position • the aircraft direction • the relative altitude • the vertical speed tendency.

Issue 6 Revision 1, January 2012

34.43.295

Page 508

[ 34-56]

Navigation 34

A320 Family Table 34-17 - Technical solutions description TDU

Title (Remarks)

Appl.

Weight (kg) MWE/OWE/APL

Equipment reference

Equipment supplier

Equipment PN

QTY

STS

01

Activation of ATSAW function

A318-100 A319-100 A320-200 A321-200

Negl./Negl./Negl. Negl./Negl./Negl. Negl./Negl./Negl. Negl./Negl./Negl.

Pushbutton

AIRBUS

ABS1650-01

2

SFE

02

Activation of ATSAW function including ITP (In Trail Procedure)

A318-100 A319-100 A320-200 A321-200

Negl./Negl./Negl. Negl./Negl./Negl. Negl./Negl./Negl. Negl./Negl./Negl.

Pushbutton

AIRBUS

ABS1650-01

2

SFE

Issue 6 Revision 1, January 2012

34.43.295

Page 509

[ 34-57]

A320 Family

34 Navigation

34.48.124 - Enhanced Ground Proximity Warning System (EGPWS) - alternate equipment Objective To provide an alternate Enhanced Ground Proximity Warning Computer (EGPWC) capable of geometric altitude, PEAKS, OBSTACLE and use of GPS lateral position functions. Basic aircraft The basic EGPWC is capable of geometric altitude, PEAKS and OBSTACLE and use of GPS lateral position functions.

database. It shall be the responsibility of the Buyer to verify with the relevant states in which the Buyer operates, the correctness of the information contained in the terrain database. Errors in the terrain data shall be reported to the relevant states and the supplier of the related equipment. In no case shall Airbus be held responsible or liable for the contents, acquisition, use or updating of the terrain data base. EPAC selection mode Individual

Description An alternate EGPWC manufactured by HONEYWELL is installed in place of the basic one. The main improvements of this alternate equipment are the compatibility with low RNP approach, with steep approach (on A318 only) and the provision for managing RAAS audio volume. Note The contents of the terrain database are made available by the various states, which are members of the ICAO world organization, to the supplier. Each state is responsible for the definition of the content of the terrain Issue 6 Revision 1, January 2012

34.48.124

Page 510

[ 34-58]

Navigation 34

A320 Family Table 34-18 - Technical solutions description TDU

Title (Remarks)

Appl.

Weight (kg) MWE/OWE/APL

Std

EGPWC - capable of GPS lateral position

A318-100 A319-100 A320-200 A321-200

03

EGPWC alternate equipment HONEYWELL, -003

A318-100 A319-100 A320-200 A321-200

Issue 6 Revision 1, January 2012

Negl./Negl./Negl. Negl./Negl./Negl. Negl./Negl./Negl. Negl./Negl./Negl.

Equipment reference

Equipment supplier

Equipment PN

QTY

STS

Ground Proximity Warning Computer (GPWC)

HONEYWELL INC. REDMOND, OLATHE

965-1676-002

1

SFE

Ground Proximity Warning Computer (GPWC)

HONEYWELL INC. REDMOND, OLATHE

965-1676-003

1

SFE

34.48.124

Page 511

[ 34-59]

A320 Family

34 Navigation

34.48.127 - Enhanced Ground Proximity Warning System (EGPWS) alternate warnings Objective To propose an EGPWS man machine interface with alternate aural and visual annunciation.

EPAC selection mode Individual

Basic aircraft The basic EGPWS aural and visual annunciation is in line with the EASA/JAA wording: Caution annunciation: "Terrain ahead !" voice associated with amber "TERR AHEAD" message on Navigation Display. Warning annunciation: "Terrain ahead, pull-up ! , pull-up ! ..." voice associated with red "TERR AHEAD" message on Navigation Display. Description The EGPWS aural and visual annunciation is: Caution annunciation: "Caution Terrain !" voice associated with amber "TERRAIN" message on Navigation Display. Warning annunciation: "Terrain, Terrain, pull-up ! , pullup ! ..." voice associated with red "TERRAIN" message on Navigation Display. The modification is made by pin-program.

Issue 6 Revision 1, January 2012

34.48.127

Page 512

[ 34-60]

Navigation 34

A320 Family Table 34-19 - Technical solutions description TDU

Title (Remarks)

Appl.

Weight (kg) MWE/OWE/APL

03

EGPWS annunciation (aural & visual) in accordance with FAA wording

Issue 6 Revision 1, January 2012

A318-100 A319-100 A320-200 A321-200

Equipment reference

Equipment supplier

Equipment PN

QTY

STS

0.0/0.0/0.0 0.0/0.0/0.0 0.0/0.0/0.0 0.0/0.0/0.0

34.48.127

Page 513

[ 34-61]

A320 Family

34 Navigation

34.48.132 - Enhanced Ground Proximity Warning System (EGPWS) - optional functions Objective To give aircraft position on the airport surface by providing aural advisories. Basic aircraft An EGPWC is installed. Description The Runway Awareness And Advisory System (RAAS) is a new function implemented in EGPWS. It allows to give aircraft position on the airport surface. The aircraft position comes from GPS. The airport location comes from an EGPWS runway database. RAAS function provides only aural advisories. To be available, RAAS needs a certain EGPWS configuration: • EGPWS is powered up • EGPWS -003 • EGPWS runway database -435 or later • RAAS Configuration Database -521 • GPS position • RAAS discrete activation. EPAC selection mode Individual

Issue 6 Revision 1, January 2012

34.48.132

Page 514

[ 34-62]

Navigation 34

A320 Family Table 34-20 - Technical solutions description TDU

Title (Remarks)

Appl.

Weight (kg) MWE/OWE/APL

15

Activation of the Runway Awareness and Advisory System (RAAS) function in the EGPWS (-003)

A318-100 A319-100 A320-200 A321-200

Equipment reference

Equipment supplier

Equipment PN

QTY

STS

0.0/0.0/0.0 0.0/0.0/0.0 0.0/0.0/0.0 0.0/0.0/0.0

Requires prior selection of CN34.48.124/ 03 EGPWC alternate equipment - HONEYWELL, -003

Issue 6 Revision 1, January 2012

34.48.132

Page 515

[ 34-63]

A320 Family

34 Navigation

34.51.101 - Distance Measuring Equipment (DME) interrogators alternate equipment Objective To provide alternate equipment for DME interrogators. Basic aircraft Two DME interrogators generally in accordance with ARINC 709, are installed together with the two independent L-blade antennas on the fuselage. DME (1+2) indications are provided on EFIS NDs. Description The modification consists in replacing the DME interrogators by alternate equipment. EPAC selection mode Individual

Issue 6 Revision 1, January 2012

34.51.101

Page 516

[ 34-64]

Navigation 34

A320 Family Figure 34-11 - DME interrogators

GS 390 TAS 380 095/20 27

30

VOR1 116. 00 CRS 010 TRO 33

24

0

3

21

6

18 2'30" VOR1 TRO 15 NM

DME 1 Antenna

Issue 6 Revision 1, January 2012

9

15 12

ADF2 JAG

ND

DME 2 Antenna

34.51.101

Page 517

[ 34-65]

A320 Family

34 Navigation Table 34-21 - Technical solutions description TDU

Title (Remarks)

Appl.

Weight (kg) MWE/OWE/APL

Std

DME interrogators basic equipment - ROCKWELL COLLINS 900

A318-100 A319-100 A320-200 A321-200

13

DME interrogators alternate equipment - HONEYWELL, PN 066-50013-1222

A318-100 A319-100 A320-200 A321-200

Issue 6 Revision 1, January 2012

Negl./Negl./Negl. Negl./Negl./Negl. Negl./Negl./Negl. Negl./Negl./Negl.

Equipment reference

Equipment supplier

Equipment PN

QTY

STS

DME interrogator

ROCKWELL COL- 822-0329-020 LINS

2

SFE

DME interrogator

HONEYWELL INC. REDMOND, OLATHE

2

SFE

34.51.101

066-500131222

Page 518

[ 34-66]

Navigation 34

A320 Family

Intentionally left blank

Issue 6 Revision 1, January 2012

34.51.101

Page 519

[ 34-67]

A320 Family

34 Navigation

34.52.117 - Automatic Dependent Surveillance - Broadcast (ADS-B OUT) Objective To update the documentation (AFM, FCOM) to be compliant with AMC-20-24 for ADS-B OUT in Non Radar Airspace. Basic aircraft None. Description The necessary changes to implement ADS-B OUT regulation for Non Radar Airspace are made. The objective of ADS-B OUT function is to comply with AMC-20-24 applicable to the airborne domain specified for 5NM separations in Non Radar Airspace. Note Not interchangeable with a transponder not capable of ADS-B OUT. EPAC selection mode Individual

Issue 6 Revision 1, January 2012

34.52.117

Page 520

[ 34-68]

Navigation 34

A320 Family Table 34-22 - Technical solutions description TDU

Title (Remarks)

Appl.

Weight (kg) MWE/OWE/APL

02

Compliance with ADS-B OUT regulation for NRA

Issue 6 Revision 1, January 2012

A318-100 A319-100 A320-200 A321-200

Equipment reference

Equipment supplier

Equipment PN

QTY

STS

Negl./Negl./Negl. Negl./Negl./Negl. Negl./Negl./Negl. Negl./Negl./Negl.

34.52.117

Page 521

[ 34-69]

A320 Family

34 Navigation

34.52.133 - Compliance with European enhanced surveillance (EHS) regulation Objective To update the documentation (AFM, FCOM, AMM) to be compliant with TGL18/JAA NPA-20-12a (EHS regulation). Basic aircraft Two mode S ATC transponders compliant with ELS (Elementary surveillance). Description The necessary changes to implement TGL18/JAA NPA20-12a (EHS regulation) are made. Note Not interchangeable with a transponder non capable of EHS. EPAC selection mode Individual

Issue 6 Revision 1, January 2012

34.52.133

Page 522

[ 34-70]

Navigation 34

A320 Family Table 34-23 - Technical solutions description TDU

Title (Remarks)

Appl.

Weight (kg) MWE/OWE/APL

01

Compliance with European enhanced surveillance (EHS) regulation

Issue 6 Revision 1, January 2012

A318-100 A319-100 A320-200 A321-200

Equipment reference

Equipment supplier

Equipment PN

QTY

STS

2.0/2.0/-2.0 2.0/2.0/-2.0 2.0/2.0/-2.0 2.0/2.0/-2.0

34.52.133

Page 523

[ 34-71]

A320 Family

34 Navigation

34.52.140 - Air Traffic Control (ATC) control panel alternate equipment Objective To provide alternate equipment for ATC control panel. Basic aircraft One ATC control panel (Mode S, TCAS with Full Time and Above/Below display mode). Description ATC control panel is replaced by alternate equipment. EPAC selection mode Individual

Issue 6 Revision 1, January 2012

34.52.140

Page 524

[ 34-72]

Navigation 34

A320 Family Figure 34-12 - ATC control panel location

STBY

AUTO

AUTO

IDENT

ON

STBY

ATC

ON

FAIL

TA 1

STBY

TARA

2

A T C OFF

ON ATC FAIL

ALL ABV THRT BLW

T C A S

A T C

1

2

1 4

5

6

ON

ALL THRT

7

0

ABV STBY BLW

TA

T C A S TARA

CLR

ALT RPTG

THALES AVIONICS C124-02-AA02 (optional)

Issue 6 Revision 1, January 2012

3 IDENT

OFF

ALT RPTG

2

THALES AVIONICS C124-04-AB02 (basic)

34.52.140

Page 525

[ 34-73]

A320 Family

34 Navigation Table 34-24 - Technical solutions description TDU

Title (Remarks)

Appl.

Weight (kg) MWE/OWE/APL

Std

Dual ATC/TCAS control panel basic equipment - THALES AVIONICS (-AB02) Keyboard type with Full Time and Above/ Below display mode.

20

Dual ATC /TCAS control panel alternate equipment - THALES AVIONICS (-AA02) Rotactor type with Full Time and Above/ Below display mode. Not applicable to A318-100 equipped with PW engines.

Issue 6 Revision 1, January 2012

A318-100 A319-100 A320-200 A321-200

A318-100 A319-100 A320-200 A321-200

Negl./Negl./Negl. Negl./Negl./Negl. Negl./Negl./Negl. Negl./Negl./Negl.

Equipment reference

Equipment supplier

Equipment PN

QTY

STS

Dual ATC/TCAS control panel

THALES AVIONICS SA

C124-04AB02

1

SFE

Dual ATC/TCAS control panel

THALES AVIONICS SA

C124-02AA02

1

SFE

34.52.140

Page 526

[ 34-74]

Navigation 34

A320 Family

Intentionally left blank

Issue 6 Revision 1, January 2012

34.52.140

Page 527

[ 34-75]

A320 Family

34 Navigation

34.53.109 - Full provision for second Automatic Direction Finder (ADF) system Objective To provide full provision for the later installation of a second ADF system. Basic aircraft One ADF system incorporating a combined loop and sense antenna is installed. There is space provision for a second ADF receiver and structural provision for the installation of a second ADF antenna. Description The modification consists in: • installation of a second ADF antenna on top of the fuselage • installation of a second ADF receiver mount in the avionics compartment • installation of associated wiring. EPAC selection mode Individual

Issue 6 Revision 1, January 2012

34.53.109

Page 528

[ 34-76]

Navigation 34

A320 Family Figure 34-13 - ADF system

FMGC2

FMGC1

ADF1 antenna

RMP1

ADF2 antenna

ADF receivers

Normal flow

RMP2

VOR1

VOR2

DME1

DME2

MMR1

MMR2

ADF1

Prov for ADF2

Alternate flow

Issue 6 Revision 1, January 2012

34.53.109

Page 529

[ 34-77]

A320 Family

34 Navigation Table 34-25 - Technical solutions description TDU

Title (Remarks)

Appl.

Weight (kg) MWE/OWE/APL

01

Full provision for second ADF system

Issue 6 Revision 1, January 2012

A318-100 A319-100 A320-200 A321-200

8.0/8.0/-8.0 8.0/8.0/-8.0 8.0/8.0/-8.0 8.5/8.5/-8.5

Equipment reference

ADF antenna

34.53.109

Equipment supplier

THALES AVIONICS SA

Equipment PN

615-2630-102

QTY

2

Page 530

STS

SFE

[ 34-78]

Navigation 34

A320 Family

Intentionally left blank

Issue 6 Revision 1, January 2012

34.53.109

Page 531

[ 34-79]

A320 Family

34 Navigation

34.53.111 - Single Automatic Direction Finder (ADF) system alternate equipment Objective To provide alternate equipment for ADF system. Basic aircraft One ADF system is installed. ADF bearing information is displayed on NDs according to the EFIS control panel ADF/VOR selector switch positions. ADF bearing can be displayed on the DDRMI (if selected). Description The ADF receiver is replaced by alternate equipment. EPAC selection mode Individual

Issue 6 Revision 1, January 2012

34.53.111

Page 532

[ 34-80]

Navigation 34

A320 Family Figure 34-14 - Single ADF system

FMGC2

FMGC1

RMP1

ADF1 antenna

RMP2

VOR1

VOR2

DME1

DME2

MMR1

MMR2

ADF1

ADF2

Normal flow Alternate flow

Issue 6 Revision 1, January 2012

34.53.111

Page 533

[ 34-81]

A320 Family

34 Navigation Table 34-26 - Technical solutions description TDU

Title (Remarks)

Appl.

Weight (kg) MWE/OWE/APL

Std

ADF system basic equipment ROCKWELL COLLINS 900

A318-100 A319-100 A320-200 A321-200

03

ADF system alternate equipment - HONEYWELL

A318-100 A319-100 A320-200 A321-200

Issue 6 Revision 1, January 2012

Negl./Negl./Negl. Negl./Negl./Negl. Negl./Negl./Negl. Negl./Negl./Negl.

Equipment reference

Equipment supplier

Equipment PN

QTY

STS

ADF receiver

ROCKWELL COL- 822-0299-020 LINS

1

SFE

ADF receiver

HONEYWELL INC. REDMOND, OLATHE

1

SFE

34.53.111

066-500140202

Page 534

[ 34-82]

Navigation 34

A320 Family

Intentionally left blank

Issue 6 Revision 1, January 2012

34.53.111

Page 535

[ 34-83]

A320 Family

34 Navigation

34.53.119 - Installation of dual Automatic Direction Finder (ADF) system Objective To install dual ADF system to provide redundancy for navigation purposes.

ADF1 (or 2) information is displayed on NDs according to the EFIS control panel ADF/VOR selector switch positions.

Basic aircraft One ADF system incorporating a combined loop and sense antenna is installed. There is space provision for a second ADF receiver and structural provision for the installation of a second ADF antenna.

Note This option is not compatible with later installation of a satellite TV system. EPAC selection mode Individual

Description The complete installation of dual ADF system is implemented as follows: • installation of a second antenna on top of the fuselage • installation of dual ADF receiver with associated mount in the avionics compartment in place of the basic single ADF receiver • installation of associated wiring • pin-programming modification of peripheral equipment (DMC, FMGC, RMP).

Issue 6 Revision 1, January 2012

34.53.119

Page 536

[ 34-84]

Navigation 34

A320 Family Figure 34-15 - Dual ADF system ADF1 antenna

ADF2 antenna FMGC2

FMGC1

RMP1

ARPT

NDB

VOR D

40 20

60

ROSE VOR

WPT

CSTR

160

VOR1

VOR2

hPa

DME1

DME2

FD

MMR1

MMR2

ADF1

ADF2

BARO

NAV ARC in Hg

10

RMP2

ILS

PLAN PULL STD

320 1 ADF

2 VOR

ADF

OFF

Activated position

VOR

ILS

OFF

Normal flow Alternate flow

Issue 6 Revision 1, January 2012

34.53.119

Page 537

[ 34-85]

A320 Family

34 Navigation Table 34-27 - Technical solutions description TDU

Title (Remarks)

Appl.

Weight (kg) MWE/OWE/APL

03

04

Installation of dual ADF system - HONEYWELL

Installation of dual ADF system - ROCKWELL COLLINS 900

Issue 6 Revision 1, January 2012

A318-100 A319-100 A320-200 A321-200

A318-100 A319-100 A320-200 A321-200

12.5/12.5/-12.5 12.5/12.5/-12.5 12.5/12.5/-12.5 13.0/13.0/-13.0

11.5/11.5/-11.5 11.5/11.5/-11.5 11.5/11.5/-11.5 12.0/12.0/-12.0

Equipment reference

Equipment supplier

Equipment PN

QTY

STS

ADF antenna

THALES AVIONICS SA

615-2630-102

2

SFE

ADF receiver

HONEYWELL INC. REDMOND, OLATHE

066-500140202

2

SFE

ADF antenna

THALES AVIONICS SA

615-2630-102

2

SFE

ADF receiver

ROCKWELL COL- 822-0299-020 LINS

2

SFE

34.53.119

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[ 34-86]

Navigation 34

A320 Family

Intentionally left blank

Issue 6 Revision 1, January 2012

34.53.119

Page 539

[ 34-87]

A320 Family

34 Navigation

34.55.102 - VHF Omnidirectional Range (VOR)/Marker receivers alternate equipment Objective To provide alternate equipment for the VOR system. Basic aircraft Two VOR receivers are installed in the avionics compartment. • VOR 1 and VOR 2 information is displayed on NDs depending on the position of the ADF/VOR selectors on the EFIS control panel • VOR 1 and VOR 2 bearing is also displayed on the DDRMI located on the main instrument panel. Each VOR receiver shall include a marker beacon function capability. The outer, middle and inner marker signals are displayed on the PFD. Description The VOR receivers are replaced by alternate equipment. EPAC selection mode Individual

Issue 6 Revision 1, January 2012

34.55.102

Page 540

[ 34-88]

Navigation 34

A320 Family Figure 34-16 - VOR/Marker

VOR antenna (dual) ARPT

NDB

VOR D

40 20

60

ROSE VOR

CSTR

WPT

BARO

NAV ARC in Hg

10

160

ILS

hPa

PLAN PULL STD

320 2

1 ADF

VOR OFF

ADF

VOR

MKR antenna ADF/VOR control GS 390 TAS 380 095/20 27

30

FD

Mode selector

VOR1 116. 00 CRS 010 TRO 33

24

0

3

21

6

18 2'30" VOR1 TRO 15 NM

ILS

OFF

9

15 12

ADF2 JAG

ROSE/VOR

Issue 6 Revision 1, January 2012

34.55.102

Page 541

[ 34-89]

A320 Family

34 Navigation Table 34-28 - Technical solutions description TDU

Title (Remarks)

Appl.

Weight (kg) MWE/OWE/APL

Std

13

VOR/MARKER receivers basic equipment - ROCKWELL COLLINS 900

VOR/MARKER receivers alternate equipment - HONEYWELL, PN 066-50012-1212

Issue 6 Revision 1, January 2012

A318-100 A319-100 A320-200 A321-200

A318-100 A319-100 A320-200 A321-200

Negl./Negl./Negl. Negl./Negl./Negl. Negl./Negl./Negl. Negl./Negl./Negl.

Equipment reference

Equipment supplier

Equipment PN

QTY

STS

Marker antenna

CHELTON

6204-89-00

1

SFE

VOR antenna

CHELTON

3108-89

1

SFE

VOR receiver

ROCKWELL COL- 822-0297-020 LINS

2

SFE

VOR receiver

HONEYWELL INC. REDMOND, OLATHE

2

SFE

34.55.102

066-500121212

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[ 34-90]

Navigation 34

A320 Family

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Issue 6 Revision 1, January 2012

34.55.102

Page 543

[ 34-91]

A320 Family

34 Navigation 34.58.313 - Multi Mode Receiver (MMR) alternate equipment Objective To allow alternate equipment selection for MMR.

Description The basic MMRs and GPS active antennas are replaced by alternate ones.

Basic aircraft Two MMRs are installed. Each one includes: • an ILS card - a GPS card • space provision for GLS • space provision for MLS. Two GPS active antennas are installed above the cockpit. A dual loc and a dual glide antennas are installed. GPS information from MMR 1 and 2 are sent to ADIRS 1,2,3 for hybridization and then to FMGC 1 and 2 for calculation of the position. GPS is certified as per C129 class 1 Integrity is provided through ADIRU hybridization algorithms: • when Honeywell ADIRU are installed, "HIGH step 1" with ADIRU HG2030AExx, "HIGH step 2" with ADIRU HG2030BExx (HIGH = Honeywell Inertial Gps Hybrid) • when NORTHROP GRUMMAN are installed, "AIME" (AIME = Autonomous Integrity Monitored Extrapolation)

Issue 6 Revision 1, January 2012

EPAC selection mode Individual

34.58.313

Page 544

[ 34-92]

Navigation 34

A320 Family Figure 34-17 - MMR typical installation

FMGC2

FMGC1

Active antennas

FMS

RMP1

RMP2

VOR1

VOR2

DME1

DME2

MMR1

MMR2

ADF1

Prov for ADF2

ADIRS MMR

Avionics compartment

Normal flow Alternate flow

Issue 6 Revision 1, January 2012

34.58.313

Page 545

[ 34-93]

A320 Family

34 Navigation Table 34-29 - Technical solutions description TDU

Title (Remarks)

Appl.

Weight (kg) MWE/OWE/APL

Std

02

13

21

MMR basic equipment providing ILS (FM immunity) and GPS C1 functions - ROCKWELL COLLINS

A318-100 A319-100 A320-200 A321-200

MMR alternate equipment providing ILS and GPS functions with FLS/GLS capability ROCKWELL COLLINS

A318-100 A319-100 A320-200 A321-200

MMR alternate equipment providing ILS (FM immunity) and GPS C1 functions - THALES AVIONICS

A318-100 A319-100 A320-200 A321-200

MMR alternate equipment providing ILS (FM immunity) and GPS C1 functions - HONEYWELL

A318-100 A319-100 A320-200 A321-200

Issue 6 Revision 1, January 2012

Negl./Negl./Negl. Negl./Negl./Negl. Negl./Negl./Negl. Negl./Negl./Negl.

Negl./Negl./Negl. Negl./Negl./Negl. Negl./Negl./Negl. Negl./Negl./Negl.

Negl./Negl./Negl. Negl./Negl./Negl. Negl./Negl./Negl. Negl./Negl./Negl.

Equipment reference

Equipment supplier

Equipment PN

QTY

STS

GPS antenna

ROCKWELL COL- 822-1330-001 LINS

2

SFE

Multi Mode Receiver (MMR)

ROCKWELL COL- 822-1152-122 LINS

2

SFE

GPS antenna

ROCKWELL COL- 8222033001 LINS

2

SFE

Multi Mode Receiver (MMR)

ROCKWELL COL- 822-1821-430 LINS

2

SFE

GPS antenna

THALES AVIONICS SA

C17065AA

2

SFE

Multi Mode Receiver (MMR)

THALES AVIONICS SA

TLS755-010102A

2

SFE

GPS antenna

HONEYWELL INC. REDMOND, OLATHE

071-500295502

2

SFE

Multi Mode Receiver (MMR)

HONEYWELL INC. REDMOND, OLATHE

066-500291161

2

SFE

34.58.313

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[ 34-94]

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A320 Family

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Issue 6 Revision 1, January 2012

34.58.313

Page 547

[ 34-95]

A320 Family

34 Navigation 34.58.316 - Activation of GLS function Objective To offer GNSS Landing System (GLS) capability. Basic aircraft Two MMR are basically installed, each one includes GPS and ILS cards. Description Depending on operational needs, the GLS additional option shall be activated through a specific MMR pinprogramming. This GLS function enables to fly CAT I precision approaches with autoland, in an ILS look-alike manner. EPAC selection mode Individual

Issue 6 Revision 1, January 2012

34.58.316

Page 548

[ 34-96]

Navigation 34

A320 Family Table 34-30 - Technical solutions description TDU

Title (Remarks)

Appl.

Weight (kg) MWE/OWE/APL

01

Activation of GLS function

Issue 6 Revision 1, January 2012

A318-100 A319-100 A320-200 A321-200

Equipment reference

Equipment supplier

Equipment PN

QTY

STS

Negl./Negl./Negl. Negl./Negl./Negl. Negl./Negl./Negl. Negl./Negl./Negl.

34.58.316

Page 549

[ 34-97]

A320 Family

34 Navigation 34.58.317 - Activation of FLS function Objective To offer FMS Landing System (FLS) capability. Basic aircraft Two MMR are basically installed, each one includes GPS and ILS cards. Description Depending on operational needs, the FLS option shall be activated thanks to a dedicated FMS OPC (Operational Programme Configuration). This FLS function enables fly non-precision approaches in an ILS look-alike manner. EPAC selection mode Individual

Issue 6 Revision 1, January 2012

34.58.317

Page 550

[ 34-98]

Navigation 34

A320 Family Table 34-31 - Technical solutions description TDU

Title (Remarks)

Appl.

Weight (kg) MWE/OWE/APL

01

Activation of FLS function

Issue 6 Revision 1, January 2012

A318-100 A319-100 A320-200 A321-200

Equipment reference

Equipment supplier

Equipment PN

QTY

STS

Negl./Negl./Negl. Negl./Negl./Negl. Negl./Negl./Negl. Negl./Negl./Negl.

34.58.317

Page 551

[ 34-99]

A320 Family

34 Navigation

34.58.340 - Installation of MLS function for cat IIIb operation hosted by the MMR Objective To allow CAT IIIB operation. Basic aircraft None. Description The MLS function shall be implemented within the MMR. The modified aircraft shall be capable of CAT IIIB operation at airports equipped with adequate MLS ground station and facilities. EPAC selection mode Individual

Issue 6 Revision 1, January 2012

34.58.340

Page 552

[ 34-100]

Navigation 34

A320 Family Table 34-32 - Technical solutions description TDU

Title (Remarks)

Appl.

Weight (kg) MWE/OWE/APL

03

MLS function implementation for CAT IIIB operation - THALES MMR, PN TLS755-140103A

Issue 6 Revision 1, January 2012

A318-100 A319-100 A320-200 A321-200

Negl./Negl./Negl. Negl./Negl./Negl. Negl./Negl./Negl. Negl./Negl./Negl.

Equipment reference

Equipment supplier

Equipment PN

QTY

STS

MLS capture antenna

THALES AVIONICS SA

1071-84-00

1

SFE

MLS landing antenna

THALES AVIONICS SA

3602-84-00

2

SFE

Multi Mode Receiver (MMR)

THALES AVIONICS SA

TLS755-140103A

2

SFE

34.58.340

Page 553

[ 34-101]

A320 Family

34 Navigation

Intentionally left blank

Issue 6 Revision 1, January 2012

34.58.340

Page 554

[ 34-102]

A320 Family

Oxygen 35

Reference

Title

35.11.102

Installation of in-situ replenishment facility for cockpit oxygen cylinder

35.11.201

Cockpit oxygen cylinder alternate equipment

35.20.010

Installation of four oxygen masks per box

35.20.113

Extended supply duration for passenger chemical oxygen system

35.20.114

Extended supply duration for passenger gaseous oxygen system

Issue 6 Revision 1, January 2012

Page 555

[ 35-1]

A320 Family

35 Oxygen

35.11.102 - Installation of in-situ replenishment facility for cockpit oxygen cylinder Objective To permit convenient in-situ replenishing of flight crew oxygen cylinder. Basic aircraft No replenishment facility is provided; the oxygen cylinder is removed via the external access door. Structural and space provision is made for a ground filling connector and associated pressure gauge. Description Adaptation of the flight crew oxygen storage system, located in the LH forward under-floor compartment, to permit in-situ charging of the oxygen cylinder, via the access door. The modification consists in: • installation of a filling connector • installation of a flexible tube and a duct between the regulator and the filling connector • installation of an HP indicator • installation of appropriate wiring. EPAC selection mode Individual

Issue 6 Revision 1, January 2012

35.11.102

Page 556

[ 35-2]

Oxygen 35

A320 Family Figure 35-1 - External oxygen replenishment principle Full face quick donning mask Optional (Fourth occupant)

Storage box assembly Flex. hose

Access door

Distribution manifold Pressure switch Pressure regulator transmitter Overpressure hose

Supply valve LP HP

FR13 FR11 FR9 Oxygen cylinder Flexible hose

Direct reading pressure gauge

overpressure high pressure low pressure

Issue 6 Revision 1, January 2012

Test port

Manual isolation valve

Overboard discharge indicator

35.11.102

HP indicator Filling connector with cap

Page 557

[ 35-3]

A320 Family

35 Oxygen Table 35-1 - Technical solutions description TDU

Title (Remarks)

Appl.

Weight (kg) MWE/OWE/APL

03

Installation of in-situ replenishment facility for cockpit oxygen cylinder

Issue 6 Revision 1, January 2012

A318-100 A319-100 A320-200 A321-200

1.0/1.0/-1.0 1.0/1.0/-1.0 1.0/1.0/-1.0 1.0/1.0/-1.0

Equipment reference

Equipment supplier

Equipment PN

QTY

STS

Filling flexible hose

EROS

DTH4AAR505

1

SFE

Filling indicator

EROS

444-00522700

1

SFE

Filling port assembly

EROS

DKR142

1

SFE

35.11.102

Page 558

[ 35-4]

Oxygen 35

A320 Family

Intentionally left blank

Issue 6 Revision 1, January 2012

35.11.102

Page 559

[ 35-5]

A320 Family

35 Oxygen 35.11.201 - Cockpit oxygen cylinder alternate equipment Objective To provide alternate flight crew oxygen cylinder. Basic aircraft The flight crew oxygen cylinder is of composite material with 77.1 cu ft (2 183 liter) capacity. It is located in the avionics compartment, LH side. Description The existing composite oxygen cylinder is replaced by alternate equipment. EPAC selection mode Individual

Issue 6 Revision 1, January 2012

35.11.201

Page 560

[ 35-6]

Oxygen 35

A320 Family Figure 35-2 - Cockpit oxygen system Full face quick donning mask

Storage box assembly Optional (Fourth occupant)

Flex. hose

Distribution manifold

Pressure switch L.P. over pressure flex. hose H.P. over pressure flex. hose

Pressure regulator transmitter

Over pressure LP HP

High pressure Low pressure

L.P. supply valve

77.1 Cu.ft (composite)

Overboard discharge indicator

Oxygen cylinder DU (T

115 Cu.ft

Flexible hose

Manual isolation valve

Test port Supply flex. hose

) 02

Direct reading pressure gage

(steel)

Issue 6 Revision 1, January 2012

35.11.201

Page 561

[ 35-7]

A320 Family

35 Oxygen Table 35-2 - Technical solutions description TDU

Title (Remarks)

Appl.

Weight (kg) MWE/OWE/APL

Std

Cockpit oxygen cylinder basic equipment 77.1 cu ft (composite) - AVOX SYSTEMS

A318-100 A319-100 A320-200 A321-200

02

Cockpit oxygen cylinder alternate equipment 115 cu ft (steel) - AVOX SYSTEMS

A318-100 A319-100 A320-200 A321-200

04

Cockpit oxygen cylinder alternate equipment 115 cu ft (composite) - AVOX SYSTEMS

A318-100 A319-100 A320-200 A321-200

Issue 6 Revision 1, January 2012

Equipment reference

Equipment supplier

Equipment PN

QTY

STS

Oxygen cylinder (77.1 cu ft)

AVOX SYSTEMS INC.

897940-77

1

SFE

17.0/17.0/-17.0 17.0/17.0/-17.0 17.0/17.0/-17.0 17.0/17.0/-17.0

Oxygen cylinder (115 cu ft)

AVOX SYSTEMS INC.

891511-14

1

SFE

5.5/5.5/-5.5 5.5/5.5/-5.5 5.5/5.5/-5.5 5.5/5.5/-5.5

Oxygen cylinder (115 cu ft)

AVOX SYSTEMS INC.

897940-15

1

SFE

35.11.201

Page 562

[ 35-8]

Oxygen 35

A320 Family

Intentionally left blank

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35.11.201

Page 563

[ 35-9]

A320 Family

35 Oxygen 35.20.010 - Installation of four oxygen masks per box Objective To allow unrestricted seating of passengers with infants. Basic aircraft Three and four masks oxygen containers are installed. Description Four passenger oxygen masks are installed above each of the LH and RH passenger seat units providing a total of eight masks per seat row. EPAC selection mode Individual

Issue 6 Revision 1, January 2012

35.20.010

Page 564

[ 35-10]

Oxygen 35

A320 Family Table 35-3 - Technical solutions description TDU

Title (Remarks)

Appl.

Weight (kg) MWE/OWE/APL

01

Installation of four oxygen masks per box

Issue 6 Revision 1, January 2012

A318-100 A319-100 A320-200 A321-200

Equipment reference

Equipment supplier

Equipment PN

QTY

STS

4.5/4.5/-4.5 5.0/5.0/-5.0 6.0/6.0/-6.0 8.0/8.0/-8.0

35.20.010

Page 565

[ 35-11]

A320 Family

35 Oxygen

35.20.113 - Extended supply duration for passenger chemical oxygen system Objective To increase operational capability by providing extended supply duration for the passenger oxygen system. Basic aircraft A chemically generated passenger oxygen system, from supplier B/E AEROSPACE SYSTEMS, with 15 minutes supply duration capability is installed. Description The basic passenger oxygen boxes are replaced by boxes with oxygen generator supply duration increased to 22 minutes, at the following locations: • in the lateral supply channels above passenger seats • at all attendant stations • in all lavatories • in the forward and aft entrance ceilings. EPAC selection mode Individual

Issue 6 Revision 1, January 2012

35.20.113

Page 566

[ 35-12]

Oxygen 35

A320 Family Figure 35-3 - Extended cabin altitude/descent profile

Flight Level (x100 ft) 410 400

300

290

Extended emergency descent profile 250

200 Basic emergency descent profile 100 Time (minutes) 0 0

1

2

3

Issue 6 Revision 1, January 2012

4

5

6

7

8

9

10

11

12

35.20.113

13

14

15

16

17

18

19

20

21

22

Page 567

23

[ 35-13]

A320 Family

35 Oxygen Table 35-4 - Technical solutions description TDU

Title (Remarks)

Appl.

Weight (kg) MWE/OWE/APL

Std

Basic passenger chemical oxygen system (15 min) - B/E AEROSPACE SYSTEMS

A318-100 A319-100 A320-200 A321-200

07

Extended supply duration for passenger chemical oxygen system (22 min) - B/E AEROSPACE SYSTEMS

A318-100 A319-100 A320-200 A321-200

Issue 6 Revision 1, January 2012

35.0/35.0/-35.0 39.0/39.0/-39.0 46.0/46.0/-46.0 56.0/56.0/-56.0

Equipment reference

Equipment supplier

Equipment PN

QTY

STS

Passenger chemical oxygen system

B/E AEROSPACE TBD SYSTEMS GMBH

1

SFE

Passenger chemical oxygen system

B/E AEROSPACE TBD SYSTEMS GMBH

1

SFE

35.20.113

Page 568

[ 35-14]

Oxygen 35

A320 Family

Intentionally left blank

Issue 6 Revision 1, January 2012

35.20.113

Page 569

[ 35-15]

A320 Family

35 Oxygen

35.20.114 - Extended supply duration for passenger gaseous oxygen system Objective for A319-100 To provide a gaseous passenger oxygen system with an extended oxygen supply duration. Basic aircraft for A319-100 The standard chemical oxygen system provides oxygen for 15 min. Space provision and structural reinforcements. Description for A319-100 The supply duration for passenger oxygen system is extended to tbd min with the installation of gaseous oxygen cylinders in the aft cargo compartment. EPAC selection mode Individual

Issue 6 Revision 1, January 2012

35.20.114

Page 570

[ 35-16]

Oxygen 35

A320 Family Table 35-5 - Technical solutions description TDU

Title (Remarks)

Appl.

Weight (kg) MWE/OWE/APL

01

Extended duration passenger gaseous oxygen system

Issue 6 Revision 1, January 2012

A319-100

124.0/124.0/-124.0

Equipment reference

Equipment supplier

Equipment PN

QTY

STS

Oxygen cylinder (117 cu ft)

B/E AEROSPACE OXYGEN SYST PRODUCT LENEXA

4441103-115

6

SFE

Set of passenger emergency oxygen masks

BE AEROSPACE

TBD

1

SFE

35.20.114

Page 571

[ 35-17]

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35 Oxygen

Intentionally left blank

Issue 6 Revision 1, January 2012

35.20.114

Page 572

[ 35-18]

A320 Family

Water/waste 38

Reference

Title

38.10.104

Installation of water conditioner in potable water system

38.41.101

Installation of auxiliary compressor in the potable water pressurization system

Issue 6 Revision 1, January 2012

Page 573

[ 38-1]

A320 Family

38 Water/waste

38.10.104 - Installation of water conditioner in potable water system Objective To prevent build-up of limescale in the potable water system including associated equipment as water heaters, faucets etc. Basic aircraft No system with limescale prevention capabilities installed. Description One small size water conditioner is installed in the filling/ distribution line below the potable water tank. EPAC selection mode Individual

Issue 6 Revision 1, January 2012

38.10.104

Page 574

[ 38-2]

Water/waste 38

A320 Family Table 38-1 - Technical solutions description TDU

Title (Remarks)

Appl.

Weight (kg) MWE/OWE/APL

Equipment reference

Equipment supplier

Equipment PN

QTY

STS

02

Installation of water conditioner in potable water system (A318, A319, A321)

A318-100 A319-100 A321-200

3.0/3.0/-3.0 3.0/3.0/-3.0 3.0/3.0/-3.0

Water conditioner

MAN TECHNOLOGIE GMBH

9630602-1001 1

SFE

03

Installation of water conditioner in potable water system (A320)

A320-200

3.0/3.0/-3.0

Water conditioner

MAN TECHNOLOGIE GMBH

9630602-1101 1

SFE

Issue 6 Revision 1, January 2012

38.10.104

Page 575

[ 38-3]

A320 Family

38 Water/waste

38.41.101 - Installation of auxiliary compressor in the potable water pressurization system Objective To maintain potable water system pressure within the working range of 25 to 28 lbf/sq in (172 to 193 kPa) in flight and on the ground.

• installation of pressure switch • installation of associated wiring. EPAC selection mode Individual

Basic aircraft The water system pressure is at least 25 lbf/sq in under normal flight conditions. Description An electrically driven compressor is installed in the potable water system pressure within the working range of 25 to 28 psi (172 to 193 kpa) in flight and on the ground. The compressor is controlled by a pressure switch, installed in the air supply line to the potable water tank. Compressor is automatically switched ON if the system air pressure is less than 25 psi (172 kpa). The compressor only works if the door of the potable water service panel is in closed position. The modification consists of: • installation of air compressor • installation of modified air supply lines including air filter and non return valve

Issue 6 Revision 1, January 2012

38.41.101

Page 576

[ 38-4]

Water/waste 38

A320 Family Table 38-2 - Technical solutions description TDU

Title (Remarks)

Appl.

Weight (kg) MWE/OWE/APL

01

Installation of auxiliary compressor in the potable water pressurization system

Issue 6 Revision 1, January 2012

A318-100 A319-100 A320-200 A321-200

Equipment reference

Equipment supplier

Equipment PN

QTY

STS

8.5/8.5/-8.5 8.5/8.5/-8.5 8.5/8.5/-8.5 8.5/8.5/-8.5

38.41.101

Page 577

[ 38-5]

A320 Family

38 Water/waste

Intentionally left blank

Issue 6 Revision 1, January 2012

38.41.101

Page 578

[ 38-6]

A320 Family

Information systems 46

Reference

Title

46.21.102

Installation of AIRBUS standard Airline Operational Communication (AOC) software for ATSU

46.21.105

Activation of ARINC 623 ATS applications in the ATSU

46.21.111

Activation of VHF Data Link (VDL) Mode 2 function

46.21.140

Installation of Future Air Navigation System (FANS) A+

46.21.142

Installation of Future Air Navigation System (FANS) B+

Issue 6 Revision 1, January 2012

Page 579

[ 46-1]

A320 Family

46 Information systems

46.21.102 - Installation of AIRBUS standard Airline Operational Communication (AOC) software for ATSU Objective To provide Airbus standard definition of Airline Operational Communication (AOC) in the Air Traffic Services Unit (ATSU). The AOC software supports data communications between the aircraft and the airline facilities on the ground. Basic aircraft The aircraft is equipped with an ATSU and its host platform (hardware + software including ACARS router). Availability of ACARS router functionality (e.g. interface with systems such as FMS, CFDS, AIDS) does not require installation of AOC software. Description The modification consists in installing in the ATSU, via dataloading, the standard AOC software from the selected supplier (ROCKWELL COLLINS or HONEYWELL). Each supplier proposes two solutions, one with fuel units in pounds and one with fuel units in kg.

Issue 6 Revision 1, January 2012

Note 1) Use of the ATSU requires installation of airline ground system and contract with datalink service providers. 2) Customization of the AOC software In case of installation of airline customized AOC, it is not required to raise an RFC for the installation of the AIRBUS standard AOC (application software + database). Installation of customized AOC is not managed/recorded by AIRBUS in the definition process. The certification level of AOC applications software is level E (DO178B). Evolution or modification of AOC software does not require AIRBUS involvement. Customization of the AOC function is the responsibility of the airline and its selected supplier. 3) Customization of the ATSU In order to use the ATSU, it must be configured with airline specific information. Providing this information is supplied by the operator during the delivery process, AIRBUS can provide customization of the ATSU during aircraft delivery under direct responsibility of the cus-

46.21.102

Page 580

[ 46-2]

Information systems 46

A320 Family

46.21.102 - Installation of AIRBUS standard Airline Operational Communication (AOC) software for ATSU (Continued) tomer (configuration of ACARS router and VHF scan mask). The same applies for installation of customized AOC software. Should problems occur during the customization process or if the operator does not provide customization information in due time, the aircraft will be delivered with default ATSU configuration: default router and scan mask configuration, standard selected AOC software. Information to be provided during the delivery process: • Airline identification: 2 character and 3 character codes • List and regional applicability of Datalink Service Providers contracted by the airline for the Scan Mask (e.g. SITA Europe, SITA Pacific, Arinc, Avicom, Air Canada) • Customized AOC software diskettes if applicable. EPAC selection mode Individual

Issue 6 Revision 1, January 2012

46.21.102

Page 581

[ 46-3]

A320 Family

46 Information systems Table 46-1 - Technical solutions description TDU

Title (Remarks)

Appl.

Weight (kg) MWE/OWE/APL

12

13

14

15

AIRBUS standard AOC software from ROCKWELL COLLINS with units in lbs (by default)

AIRBUS standard AOC software from ROCKWELL COLLINS with units in kg (by default)

AIRBUS standard AOC software from HONEYWELL with units in lbs (by default)

AIRBUS standard AOC software from HONEYWELL with units in kg (by default)

Issue 6 Revision 1, January 2012

A318-100 A319-100 A320-200 A321-200

A318-100 A319-100 A320-200 A321-200

A318-100 A319-100 A320-200 A321-200

A318-100 A319-100 A320-200 A321-200

Negl./Negl./Negl. Negl./Negl./Negl. Negl./Negl./Negl. Negl./Negl./Negl.

Negl./Negl./Negl. Negl./Negl./Negl. Negl./Negl./Negl. Negl./Negl./Negl.

Negl./Negl./Negl. Negl./Negl./Negl. Negl./Negl./Negl. Negl./Negl./Negl.

Negl./Negl./Negl. Negl./Negl./Negl. Negl./Negl./Negl. Negl./Negl./Negl.

Equipment reference

Equipment supplier

Equipment PN

QTY

STS

AOC application software diskette for ATSU

ROCKWELL COL- 222-6279LINS 232-RVA

1

BFE

AOC database diskette for ATSU

ROCKWELL COL- 222-5870LINS 501-RVD

1

BFE

AOC application software diskette for ATSU

ROCKWELL COL- 222-6279LINS 232-RVA

1

BFE

AOC database diskette for ATSU

ROCKWELL COL- 222-7720LINS 001-RVB

1

BFE

AOC application software diskette for ATSU

HONEYWELL INC. REDMOND, OLATHE

998-2459-510

1

BFE

AOC database diskette for ATSU

HONEYWELL INC. REDMOND, OLATHE

998-2449-507

1

BFE

AOC application software diskette for ATSU

HONEYWELL INC. REDMOND, OLATHE

998-2459-510

1

BFE

AOC database diskette for ATSU

HONEYWELL INC. REDMOND, OLATHE

998-6393-507

1

BFE

46.21.102

Page 582

[ 46-4]

Information systems 46

A320 Family

Intentionally left blank

Issue 6 Revision 1, January 2012

46.21.102

Page 583

[ 46-5]

A320 Family

46 Information systems 46.21.105 - Activation of ARINC 623 ATS applications in the ATSU Objective To provide Departure Clearance (DCL), Automatic Terminal Information System (ATIS) and Oceanic Clearance (OCL) applications, (OCL only applicable to FANS A+) Basic aircraft An ATSU is installed providing ACARS function. Description Airbus certified (DO178B level C) A623 ATS applications shall be loaded into the ATSU. The ATSU software must be upgraded to receive A623 ATS applications. EPAC selection mode Individual

Issue 6 Revision 1, January 2012

46.21.105

Page 584

[ 46-6]

Information systems 46

A320 Family

Table 46-2 - Technical solutions description TDU

Title (Remarks)

Appl.

Weight (kg) MWE/OWE/APL

03

Activation of ATSU ARINC 623 ATS applications capable of FANS A+

Issue 6 Revision 1, January 2012

A318-100 A319-100 A320-200 A321-200

Equipment reference

Equipment supplier

Equipment PN

QTY

STS

Negl./Negl./Negl. Negl./Negl./Negl. Negl./Negl./Negl. Negl./Negl./Negl.

46.21.105

Page 585

[ 46-7]

A320 Family

46 Information systems 46.21.111 - Activation of VHF Data Link (VDL) Mode 2 function Objective To provide VDL mode 2 over the ACARS network (VDL2/AOA), to improve air-ground digital communication and increase RF (radio frequency) transmission speed from 2.4 to 31.5 kbps (kilo bit per second). Basic aircraft An ATSU is installed providing ACARS function. VDR mode A are installed. Description The VDL Mode 2/AOA (ACARS over AVLC: Aviation VHF Link Control) capability shall be activated in the ATSU. This requires prior installation of: • upgraded ATSU software to be capable of VDL Mode 2/AOA function • upgraded VHF Data Radio (VDR) to be VDL mode 2 capable. EPAC selection mode Individual

Issue 6 Revision 1, January 2012

46.21.111

Page 586

[ 46-8]

Information systems 46

A320 Family

Table 46-3 - Technical solutions description TDU

Title (Remarks)

Appl.

Weight (kg) MWE/OWE/APL

02

Activation of VDL Mode 2 for ACARS in ATSU (CSB4.X) Only applicable in conjunction with VHF Data Radio (VDR) capable of VDL mode 2.

Issue 6 Revision 1, January 2012

A318-100 A319-100 A320-200 A321-200

0.0/0.0/0.0 0.0/0.0/0.0 0.0/0.0/0.0 0.0/0.0/0.0

Equipment reference

ATSU CONFIG database

46.21.111

Equipment supplier

AIRBUS

Equipment PN

QTY

LA2T0J6000X 1 XXXX

Page 587

STS

SFE

[ 46-9]

A320 Family

46 Information systems

46.21.140 - Installation of Future Air Navigation System (FANS) A+ Objective To face air traffic growth, and increase airspace capacity in oceanic and remote environment. Basic aircraft The aircraft is equipped with an ATSU and its aircraft interface software (including ACARS router). Availability of ACARS router functionality (e.g. interface with systems such as FMS, CFDS, AIDS) does not require installation of AOC software. Description FANS A+ configuration introduces FANS communication and surveillance capability in the aircraft to allow improved operations in oceanic and remote environment, based on Air Traffic Control (ATC) applications: • Automatic Dependent Surveillance (ADS-C) • Air Traffic Service (ATS) Facilities Notification (AFN) • Controller Pilot Data Link Communication (CPDLC). FANS A + configuration is still compatible with Airline Operational Control (AOC) communications. EPAC selection mode Individual

Issue 6 Revision 1, January 2012

46.21.140

Page 588

[ 46-10]

Information systems 46

A320 Family

Table 46-4 - Technical solutions description TDU

Title (Remarks)

Appl.

Weight (kg) MWE/OWE/APL

07

Installation of FANS A+ with data link recording capability

Issue 6 Revision 1, January 2012

A318-100 A319-100 A320-200 A321-200

4.5/4.5/-4.5 4.5/4.5/-4.5 4.5/4.5/-4.5 4.5/4.5/-4.5

Equipment reference

Datalink Control and Display Unit (DCDU)

46.21.140

Equipment supplier

SMITHS INDUSTRIES

Equipment PN

401MFD3-2

QTY

2

Page 589

STS

SFE

[ 46-11]

A320 Family

46 Information systems

46.21.142 - Installation of Future Air Navigation System (FANS) B+ Objective To support data link operations in continental Europe over VDL (VHF Data Link) Mode 2/ATN (Aeronautical Telecommunication Network). Basic aircraft The aircraft is equipped with an ATSU and its aircraft interface software (including ACARS router). Availability of ACARS router functionality (e.g. interface with systems such as FMS, CFDS, AIDS) does not require installation of AOC software. Description This installation includes: • upgrade of ATSU hardware to new part number (standard "-A10") to host FANS B+ software and router ATN. • the ACARS ATSU router software providing VDL mode A capability is retained and upgraded to VDL mode 2/AOA capability for AOC applications and VDL2/ATN capability for ATC (S/W upgrade: standard "CSB6") • activation of FANS B+ with new ATSU Configuration (21TX) and ATC applications S/W • Controller Pilot Data Link Communication (CPDLC) application software loading into the ATSU Issue 6 Revision 1, January 2012

• activation of ATC/MSG Push Buttons • installation of two Datalink Control and Display Units (DCDUs) from SMITHS INDUSTRIES. Note This option allows to configure adequately the aircraft avionics to make the aircraft operational above FL 285 in European continental high density area. Nevertheless, before starting datalink operations, the operators (Airlines) need to ensure the following: • sign contract(s) with Datalink service provider(s) (ARINC/SITA) • declare aircraft to these Datalink services providers • declare aircraft and its FANS capability to ATC centres of the operated routes. This FANS B+ option is compliant of the LINK 2000+ mandate phase. As per FAR amendments 25-124 and 121-338, provision for CVR capable of data link recording (CN23.71.120/01) is recommended for customers operating in FANS environment. EPAC selection mode Individual

46.21.142

Page 590

[ 46-12]

Information systems 46

A320 Family

Table 46-5 - Technical solutions description TDU

Title (Remarks)

Appl.

Weight (kg) MWE/OWE/APL

02

Installation of FANS B+ Incompatible with CN46.21.111 since activation of VDL Mode 2 is included.

Issue 6 Revision 1, January 2012

A318-100 A319-100 A320-200 A321-200

5.5/5.5/-5.5 5.5/5.5/-5.5 5.5/5.5/-5.5 5.5/5.5/-5.5

Equipment reference

Equipment supplier

Equipment PN

QTY

STS

Air Traffic Services Unit (ATSU)

AIRBUS

LA2T0G2100 6CA10

1

SFE

Air Traffic Services Unit (ATSU) A/C interface software

AIRBUS

LA2T0J1307E 1 00F1

SFE

Datalink Control and Display Unit (DCDU)

SMITHS INDUSTRIES

401MFD3-2

SFE

46.21.142

2

Page 591

[ 46-13]

A320 Family

46 Information systems

Intentionally left blank

Issue 6 Revision 1, January 2012

46.21.142

Page 592

[ 46-14]

A320 Family

Auxiliary Power Unit (APU) 49

Reference

Title

49.00.105

Auxiliary Power Unit (APU) alternate equipment

Issue 6 Revision 1, January 2012

Page 593

[ 49-1]

49 Auxiliary Power Unit (APU)

A320 Family

49.00.105 - Auxiliary Power Unit (APU) alternate equipment Objective To provide alternate APU. Basic aircraft The APU is installed in the tailcone of the aircraft and the associated Electronic Control Box (ECB) in the pressurized bulk cargo compartment, No. 5. Description The basic APU and ECB are replaced by alternate equipment, designed to be compatible with all aircraft system interfaces (drop-in installation). It is fully interchangeable with the basic equipment. EPAC selection mode Individual

Issue 6 Revision 1, January 2012

49.00.105

Page 594

[ 49-2]

Auxiliary Power Unit (APU) 49

A320 Family

Figure 49-1 - APU components 36VU DC BUS 1

BAT 1

1

GALLEY FAULT E L E C

OFF

BAT

2

FAULT

FAULT

OFF

OFF

BAT 2

DC BUS 2

20VU

FAULT A U T O

ALTN

AC ESS BUS

AC BUS 1

AC BUS 2 E L E C

BUS TIE SMOKE

IDG 1

OFF

A U T O

F I R E

IDG 2

R

GEN 1

APU GEN

EXT PWR

GEN 2

R

FAULT

FAULT

FAULT

AVAIL

FAULT

FAULT

OFF

OFF

OFF

ON

OFF

OFF

AGENT 1

AGENT 2

SQUIB

SQUIB

DISCH

DISCH

ENG TEST

1

AGENT 1

APU FIRE

AGENT 2

SQUIB

PUSH

FIRE

DISCH

ENG

AGENT

2

FIRE TEST

TEST

SQUIB

PUSH

SQUIB

DISCH

F I R E

PUSH

DISCH

Fire panel

Electric panel

Ventilation (left side only) Fire extinguishing bottle

108VU

Bleed air duct Exhaust duct

FLT INT EXT PWR 108 VU

Access doors Fuel line

NOT IN USE

AVAIL

COCKPIT CALL

ADIRU & AVNCS VENT

COCKPIT CALL

RESET

Air intake

APU FIRE

Diverter LIGHT TEST

APU SHUT-OFF

External power control panel

25VU APU

30VU 30VU

PACK FLOW NORM LO

MASTER SW

COCKPIT

FWD CABIN

AFT CABIN HOT AIR

HI

FAULT OFF

FAULT ON

START

A I R C O N D

COLD FAULT

HOT

COLD

HOT

COLD

PACK 2

OFF

FAULT OFF

RAM AIR ENG 1 BLEED

AUTO

FAULT OFF

ON

A I R C O N D

ENG 2 BLEED

APU BLEED SHUT

AVAIL

HOT

X BLEED

PACK 1

OPEN

FAULT

FAULT

ON

OFF

ON

ECB (Electronic Control Box)

Air conditioning panel

Issue 6 Revision 1, January 2012

49.00.105

Page 595

[ 49-3]

A320 Family

49 Auxiliary Power Unit (APU) Table 49-1 - Technical solutions description TDU

Title (Remarks)

Appl.

Weight (kg) MWE/OWE/APL

Std

06

APU basic equipment - HAMILTON SUNDSTRAND, APS 3200

APU alternate equipment HONEYWELL, GTCP131-9A

Issue 6 Revision 1, January 2012

A318-100 A319-100 A320-200 A321-200

A318-100 A319-100 A320-200 A321-200

24.5/24.5/-24.5 24.5/24.5/-24.5 24.5/24.5/-24.5 24.5/24.5/-24.5

Equipment reference

Equipment supplier

Equipment PN

QTY

STS

Auxiliary Power Unit HAMILTON (APU) SUNDSTRAND

4500001C

1

SFE

Electronic Control Box (ECB)

4500003M

1

SFE

Auxiliary Power Unit HONEYWELL (APU) INC.

3800 708-1

1

SFE

Electronic Control Box (ECB)

3888394221204

1

SFE

49.00.105

HAMILTON SUNDSTRAND

HONEYWELL INC.

Page 596

[ 49-4]

A320 Family

Structures 51

Reference

Title

51.00.115

Fuselage and wings extended corrosion prevention

51.22.250

External livery decorative adhesive film

51.22.710

Alternate paint system (CF primer/strippable) on standard areas (3 coats)

Issue 6 Revision 1, January 2012

Page 597

[ 51-1]

A320 Family

51 Structures 51.00.115 - Fuselage and wings extended corrosion prevention Objective To have an extended corrosion protection on fuselage and wings. Basic aircraft The following areas are treated with Type III Corrosion Inhibitor (CI) & Water Repellent Fluid (WRF) as per AIMS 09-08-003: Fuselage • from frames C01 to C12, between stringers P32 LH and P32 RH • from frames C12 to C21, between stringers P19 LH and P19 RH • from frames C21 to C35, between stringers P32 LH and P32 RH • from frames C35 to C47 (C35 to C47.5 on A321), between stringers P23 LH and P23 RH • from frames C47 to C63 (C47.5 to C60 on A321), between stringers P36 LH and P36 RH • from frames C63 to C77 (C60 to C77 on A321), between stringers P23 LH and P23 RH • floorgrid (cross beam only) and tail cone, between stringers P13 LH and P13 RH. Doors • emergency exits (A318/A319/A320) • emergency exit doors (A321)

Issue 6 Revision 1, January 2012

• hatches • cargo holds doors • bulk compartment door. Vertical stabilizer • rear spar including servo-control. Horizontal stabilizer • rear spar including servo-control. Wings • MLG bay on areas of underwing and overwing panel (wing strut wells) • aft face of false rear spar • aft face of rear spar inboard of gear rib 5 • aft faces of shroud box. Description Corrosion prevention Type III is enlarged on fuselage, floor grid and wings. The following additional areas are protected: Fuselage • lower shell from frames C01 to C12, between stringers P23 and P32 on LH and RH sides • lower shell from frames C21 to C35, between stringers P23 and P32 on LH and RH sides

51.00.115

Page 598

[ 51-2]

Structures 51

A320 Family

51.00.115 - Fuselage and wings extended corrosion prevention (Continued) • lower shell from frames C47 to C63 (C47.5 to C60 on A321), between stringers P23 and P36 on LH and RH sides • longitudinal beams and seat rails between frames C36 and C70 • floor panel connection sheets in the area sections 13 to 18 • aft pressure bulk head above stringer 23 (forward and aft faces) Passenger floor structure • floor support structure from frames 47 (47.5 on A321) to 63 (60 on A321). Wings • all along forward face of front spar • all along aft face of rear spar • forward face of false rear spar • wing dry bays internal surfaces • wing root joint and build door • inside pylon enclosure (forward face of front spar, aft face of D-nose sub spar and adjacent leading edge ribs). EPAC selection mode Individual

Issue 6 Revision 1, January 2012

51.00.115

Page 599

[ 51-3]

A320 Family

51 Structures Figure 51-1 - Type III (CI & WRF) on standard areas Corrosion prevention on standard areas

Vertical stabilizer C77

C69 C70

C64

C60

B

A

C74

GALLEY / LAVATORY AREA

C47.5

C47.1

C35.8

C35.1

C35

C21

C15

C12

C1

EMERGENCY EXIT

P7 FD P23

P32

A

P36

Horizontal stabilizer

B

C1

C15

C12

C21 C20

C25

C28

C35

C35.1

C35.8

C47.1

C47.5

C52

C57

C59

C62

C65 C64

C70 C69

C74

C77

PAX DOOR

P'9 FD P'23

Wing P'32

BULK COMPARTMENT DOOR P'36 CARGO HOLD DOOR

P'30 AFT FACE OF REAR SPAR INBOARD OF GEAR RIB 5

Section A-A

Section B-B BULK HEAD

P'23

P23

Z - 495 P23

P'23 P44 AFT FACE OF FALSE REAR SPAR

P44

MAIN LANDING GEAR BAY ON AREAS OF UNDERWING AN OVERWING PANEL (WING STRUT WELLS)

Protection Type III (CI & WRF)

Issue 6 Revision 1, January 2012

51.00.115

Page 600

[ 51-4]

Structures 51

A320 Family

Figure 51-2 - Type III (CI & WRF) on standard and additional areas Corrosion prevention on standard and additional areas

Vertical stabilizer

C77

C74

C69 C70

C64

C60

C47.5

C47.1

C35.8

C35.1

C35

C21

C15

C1

C12

B

P7 FD P23

Horizontal stabilizer

C1

C15

C12

C21 C20

C35

C35.1

C35.8

C47.1

C47.5

C52

C57

C59

C62

C65 C64

C70 C69

C74

C77

B

P'9 FD P'23

Section 16/17 36

Section A-A Effective for the whole passenger floor

39

42 43

A

47 48

63 64 65

69 70

74

77

WING ROOT JOINT AND BUILD DOOR

F6 F11 F13

Wing

INTERNAL SURFACES OF DRY BAY WING

F19 F21 F23

INSIDE PYLON ENCLOSURE (FWD FACE OF FRONT SPAR, AFT FACE OF D-NOSE SUB SPAR AND ADJACENT LEADING EDGE RIBS) A

Section B-B

P 23 CI / WRF

CI / WRF

FORWARD FACE OF FRONT SPAR

BULK HEAD

additional area

P 24

P44

Protection Type III (CI & WRF) Protection Type III (CI & WRF) - as per legend

Issue 6 Revision 1, January 2012

51.00.115

AFT & FWD FACES AFT FACE OF OF FALSE REAR SPAR REAR SPAR MAIN LANDING GEAR BAY ON AREAS OF UNDERWING AN OVERWING PANEL (WING STRUT WELLS)

Page 601

[ 51-5]

A320 Family

51 Structures Table 51-1 - Technical solutions description TDU

Title (Remarks)

Appl.

Weight (kg) MWE/OWE/APL

Std

Application of Type III Corrosion Inhibitor (CI) & Water Repellent Fluid (WRF) on standard areas

A318-100 A319-100 A320-200 A321-200

02

Application of Type III Corrosion Inhibitor (CI) & Water Repellent Fluid (WRF) on additional areas

A318-100 A319-100 A320-200 A321-200

Issue 6 Revision 1, January 2012

Equipment reference

Equipment supplier

Equipment PN

QTY

STS

2.0/2.0/-2.0 2.0/2.0/-2.0 3.0/3.0/-3.0 3.5/3.5/-3.5

51.00.115

Page 602

[ 51-6]

Structures 51

A320 Family

Intentionally left blank

Issue 6 Revision 1, January 2012

51.00.115

Page 603

[ 51-7]

A320 Family

51 Structures 51.22.250 - External livery decorative adhesive film Objective To answer specific request on external livery using decorative adhesive film. Basic aircraft The general paint scheme is based on conventional spray process.

Note For application restrictions due to erosion, fuel or hydraulic fluid, refer to the figure hereafter. However if adhesive films are requested in these areas, warranty restrictions shall be applied. EPAC selection mode Individual

Description Standard external livery is generally provided with a paint process. Nevertheless large decorative adhesive film can be used for complex decor/logo. The appropriate handling shall be in accordance with the following criteria: • for new adhesive films, development and production shall be handled as SFE • for existing ones already used by the customer, the procurement shall be handled as BFE as far as possible. In this case, sample testing shall be performed to validate final quality of the external livery.

Issue 6 Revision 1, January 2012

51.22.250

Page 604

[ 51-8]

Structures 51

A320 Family

Figure 51-3 - Total constraints for adhesive film application

Issue 6 Revision 1, January 2012

51.22.250

Page 605

[ 51-9]

A320 Family

51 Structures Table 51-2 - Technical solutions description TDU

Title (Remarks)

Appl.

Weight (kg) MWE/OWE/APL

53

External livery decorative adhesive film (SFE)

Issue 6 Revision 1, January 2012

A318-100 A319-100 A320-200 A321-200

Negl./Negl./Negl. Negl./Negl./Negl. Negl./Negl./Negl. Negl./Negl./Negl.

Equipment reference

Set of large decorative adhesive film

51.22.250

Equipment supplier

Equipment PN

TBD

QTY

1

Page 606

STS

SFE

[ 51-10]

Structures 51

A320 Family

Intentionally left blank

Issue 6 Revision 1, January 2012

51.22.250

Page 607

[ 51-11]

A320 Family

51 Structures

51.22.710 - Alternate paint system (CF primer/strippable) on standard areas (3 coats) Objective To provide through a low Volatile Organic Compound (VOC) and Chromate Free (CF) primer, strippable intermediate coat paint system, on metallic parts of fuselage and vertical stabilizer, a selective stripping which reduces time and cost during maintenance process. Basic aircraft The basic paint scheme applied on fuselage and vertical stabilizer is composed of: • low VOC chromate free primer, • low VOC top coat.

Airbus will choose the paint supplier and the associated paint material in line with the paint system chosen by the Airline. The intermediate coat between the primer and the top coat enables a selective stripping which reduce time and cost during maintenance process. This paint process is not available on nacelles. EPAC selection mode Individual

Description The low Volatile Organic Compound (VOC) and Chromate Free (CF) primer, strippable intermediate coat paint system shall be applied on metallic parts of fuselage and vertical stabilizer. The following paint system is applied: • low VOC chromate free primer, • intermediate layer coat, • low VOC top coat. This material is fully compliant with Health, Safety and Environmental (HSE) regulations.

Issue 6 Revision 1, January 2012

51.22.710

Page 608

[ 51-12]

Structures 51

A320 Family Figure 51-4 - Intermediate strippable coat

Basic paint system

Alternate paint system

Low VOC top coat Low VOC top coat Intermediate coat Low VOC CF primer Low VOC CF primer

Basic Primer

Basic Primer

Issue 6 Revision 1, January 2012

51.22.710

Page 609

[ 51-13]

A320 Family

51 Structures Table 51-3 - Technical solutions description TDU

Title (Remarks)

Appl.

Weight (kg) MWE/OWE/APL

08

Alternate paint system - CF primer/strippable on fuselage & vertical stabilizer (3 coats)

Issue 6 Revision 1, January 2012

A318-100 A319-100 A320-200 A321-200

Equipment reference

Equipment supplier

Equipment PN

QTY

STS

2.5/2.5/-2.5 3.0/3.0/-3.0 3.5/3.5/-3.5 4.0/4.0/-4.0

51.22.710

Page 610

[ 51-14]

A320 Family Reference

Title

52.22.200

Installation of additional emergency exits (A319)

52.51.100

Installation of cockpit door release back-up system (MMEL conditions)

52.51.106

Installation of modified door lock mechanism

Issue 6 Revision 1, January 2012

Doors 52

Page 611

[ 52-1]

A320 Family

52 Doors 52.22.200 - Installation of additional emergency exits (A319) Objective for A319-100 In order to fulfil the 160 max passengers cabin capacity on an A319 aircraft, and to meet the evacuation data requirements, it is necessary to install a second emergency exit near the first one as per type III exits design of the A320.

• adaptation of the Flight Warning system to incorporate this door in the A319 configuration • adaptation of emergency lighting • external placards on the door and escape markings on the wings. EPAC selection mode Individual

Basic aircraft for A319-100 One emergency exit is installed on each side of the fuselage. Description for A319-100 A second emergency exit is installed near the first one as per type III exits design of the A320. This modification includes the following aspects: • repercussion on structure of section 15 • installation of the exit door and its relevant slide activation • relocation of cabin windows into emergency exit • air supply quantity assessment and air distribution • adaptation of the sidewall, dado panels and exit door frame lining • update of the emergency evacuation analysis, • modification of primary insulation blankets • SDAC updating for data recording on the new door

Issue 6 Revision 1, January 2012

52.22.200

Page 612

[ 52-2]

Doors 52

A320 Family Figure 52-1 - Additional emergency exit - A319

Additional Emergency Exit Door on each side of fuselage - A319

Issue 6 Revision 1, January 2012

52.22.200

Page 613

[ 52-3]

A320 Family

52 Doors Table 52-1 - Technical solutions description TDU

Title (Remarks)

Appl.

Weight (kg) MWE/OWE/APL

01

Installation of additional emergency exits (A319)

A319-100

Equipment reference

Equipment supplier

Equipment PN

QTY

STS

69.0/69.0/-69.0

Lead-time constraint 9 months

Issue 6 Revision 1, January 2012

52.22.200

Page 614

[ 52-4]

Doors 52

A320 Family

Intentionally left blank

Issue 6 Revision 1, January 2012

52.22.200

Page 615

[ 52-5]

A320 Family

52 Doors

52.51.100 - Installation of cockpit door release back-up system (MMEL conditions) Objective To install an electrical override function to ensure functionality of cockpit door system under Master Minimum Equipment List (MMEL) conditions. Basic aircraft The cockpit door is intrusion & penetration resistant. No back-up system is installed. Description The modification comprises the installation of: • a second control unit on the overhead panel • an additional circuit breaker • an additional NORM/BKUP/OFF switch • additional grounding points • corresponding wire harness. EPAC selection mode Individual

Issue 6 Revision 1, January 2012

52.51.100

Page 616

[ 52-6]

Doors 52

A320 Family Table 52-2 - Technical solutions description TDU

Title (Remarks)

Appl.

Weight (kg) MWE/OWE/APL

07

Installation of cockpit door release back-up system (MMEL conditions)

Issue 6 Revision 1, January 2012

A318-100 A319-100 A320-200 A321-200

Equipment reference

Equipment supplier

Equipment PN

QTY

STS

3.0/3.0/-3.0 3.0/3.0/-3.0 3.0/3.0/-3.0 3.0/3.0/-3.0

52.51.100

Page 617

[ 52-7]

A320 Family

52 Doors 52.51.106 - Installation of modified door lock mechanism Objective To install a closing mechanism for the cockpit door. Basic aircraft The door between the cockpit and the passenger cabin is mechanically latched. This latch is operated by a knob on the cockpit side and by a safety key on the passenger cabin side. Description Installation of deadbolt on the reinforced cockpit door, on the cockpit side. The deadbolt shall allow to close the door manually in case of electrical locking system failure, or during maintenance when power is off. EPAC selection mode Individual

Issue 6 Revision 1, January 2012

52.51.106

Page 618

[ 52-8]

Doors 52

A320 Family Figure 52-2 - Installation of modified door lock mechanism

Issue 6 Revision 1, January 2012

52.51.106

Page 619

[ 52-9]

A320 Family

52 Doors Table 52-3 - Technical solutions description TDU

Title (Remarks)

Appl.

Weight (kg) MWE/OWE/APL

03

Installation of deadbolt on reinforced cockpit door

Issue 6 Revision 1, January 2012

A318-100 A319-100 A320-200 A321-200

Equipment reference

Equipment supplier

Equipment PN

QTY

STS

0.5/0.5/-0.5 0.5/0.5/-0.5 0.5/0.5/-0.5 0.5/0.5/-0.5

52.51.106

Page 620

[ 52-10]

A320 Family Reference

Title

53.30.050

Belly fairing panels - extrusion strips

53.35.100

Ram air inlet leading edge protection

Issue 6 Revision 1, January 2012

Fuselage 53

Page 621

[ 53-1]

A320 Family

53 Fuselage 53.30.050 - Belly fairing panels - extrusion strips Objective The modification consists in adding a profile on belly fairing panels forward edges at FR34 (ST1,ST3,ST4) or FR35.7 (ST2) to avoid erosion damage. This modification is specially recommended for a/c operated in an erosive environment (Asia or over-sea operation).

Note Interchangeability of the center panel is not any longer kept. EPAC selection mode Individual

Basic aircraft The exposed panel edges are protected by anti-erosion paint only. Description New adjustable extrusion strips are installed on RH lateral panel 192EB, on RH aft lateral panel 192FB, on center panel 191BB and on LH lateral panel 191 EB. These extrusions are fixed with the fasteners of the belly fairing panels. A washer is fitted between the bolt head and the panel to ensure correct tightening. Extrusions are covered with anti-erosion paint.

Issue 6 Revision 1, January 2012

53.30.050

Page 622

[ 53-2]

Fuselage 53

A320 Family

Figure 53-1 - Location of the additional anti-erosion protection

FR34 FR35.7 (A321)

Right lateral panel

Z1600

Right after lateral panel Left lateral panel

Center panel Anti-erosion extrusion strip

Issue 6 Revision 1, January 2012

53.30.050

Page 623

[ 53-3]

A320 Family

53 Fuselage

Figure 53-2 - Typical section of the anti-erosion extrusion strip

Anti-erosion strip Washer

FR34

Issue 6 Revision 1, January 2012

53.30.050

Page 624

[ 53-4]

Fuselage 53

A320 Family Table 53-1 - Technical solutions description TDU

Title (Remarks)

Appl.

Weight (kg) MWE/OWE/APL

01

Belly fairing panels - add extrusion

Issue 6 Revision 1, January 2012

A318-100 A319-100 A320-200 A321-200

Equipment reference

Equipment supplier

Equipment PN

QTY

STS

Negl./Negl./Negl. Negl./Negl./Negl. Negl./Negl./Negl. Negl./Negl./Negl.

53.30.050

Page 625

[ 53-5]

A320 Family

53 Fuselage 53.35.100 - Ram air inlet leading edge protection Objective To provide increased erosion resistance of the ram air inlet lip. Basic aircraft Inlet leading edge is made of hard foam core faced with prepreg skin layers. Description The composite material in the leading edge of the ram air inlet is protected with a sheet of aluminum in order to avoid erosion damage. This sheet of aluminum is painted in the background color. EPAC selection mode Individual

Issue 6 Revision 1, January 2012

53.35.100

Page 626

[ 53-6]

Fuselage 53

A320 Family Figure 53-3 - Ram air inlet leading edge protection

Typical section (AA & CC)

0.4mm clad aluminium protection flush Inlet lip detail

Hard foam core Prepreg skin

18mm

Issue 6 Revision 1, January 2012

53.35.100

Page 627

[ 53-7]

A320 Family

53 Fuselage Table 53-2 - Technical solutions description TDU

Title (Remarks)

Appl.

Weight (kg) MWE/OWE/APL

02

Ram air inlet leading edge protection (aluminum)

Issue 6 Revision 1, January 2012

A318-100 A319-100 A320-200 A321-200

Equipment reference

Equipment supplier

Equipment PN

QTY

STS

2.0/2.0/-2.0 2.0/2.0/-2.0 2.0/2.0/-2.0 2.0/2.0/-2.0

53.35.100

Page 628

[ 53-8]

A320 Family

Stabilizers 55

Reference

Title

55.30.101

Installation of erosion protection on vertical stabilizer leading edge

Issue 6 Revision 1, January 2012

Page 629

[ 55-1]

A320 Family

55 Stabilizers

55.30.101 - Installation of erosion protection on vertical stabilizer leading edge Objective To avoid premature rework of erosion paint system and repair at an early stage.

EPAC selection mode Individual

Basic aircraft Exterior surface of the vertical stabilizer leading edge is protected with standard paint systems. Description A stainless steel metal sheet, thickness 0.5 mm is installed on the vertical stabilizer leading edges 1, 2, 3 and 4 (A318 only). The modification consists of thermal curing of prepreg material together with the new profiled metal sheet in an autoclave oven in order to bond the two different materials. The metal sheets are bolted on upper and lower ends of leading edges. Anti-erosion painting according to the dimensions of metal sheet is necessary at dorsal fin. Note No livery top coat shall be applied to the stainless steel.

Issue 6 Revision 1, January 2012

55.30.101

Page 630

[ 55-2]

Stabilizers 55

A320 Family

Figure 55-1 - Vertical stabilizer leading edge protection (A319/A320/A321)

B - B (TYP.)

A

A

A A-A

Stainless steel metal sheet (0,5 mm)

A Anti erosion painting

B VIZ 0

Issue 6 Revision 1, January 2012

B

56 .5 60

55.30.101

Page 631

[ 55-3]

A320 Family

55 Stabilizers Table 55-1 - Technical solutions description TDU

Title (Remarks)

Appl.

Weight (kg) MWE/OWE/APL

01

Installation of erosion protection on vertical stabilizer leading edge - stainless steel

Issue 6 Revision 1, January 2012

A318-100 A319-100 A320-200 A321-200

Equipment reference

Equipment supplier

Equipment PN

QTY

STS

5.0/5.0/-5.0 5.0/5.0/-5.0 5.0/5.0/-5.0 5.0/5.0/-5.0

55.30.101

Page 632

[ 55-4]

A320 Family Reference

Title

56.10.102

Cockpit windows alternate equipment

Issue 6 Revision 1, January 2012

Windows 56

Page 633

[ 56-1]

A320 Family

56 Windows 56.10.102 - Cockpit windows alternate equipment Objective To provide alternate equipment for cockpit windows. Basic aircraft • 2 front windshields made of glass (all fixed) • 4 lateral windows made of acrylic (2 sliding and 2 fixed). Description This modification consists in replacing the two front windshields and/or four lateral windows by windows from an alternate manufacturer. EPAC selection mode Individual

Issue 6 Revision 1, January 2012

56.10.102

Page 634

[ 56-2]

Windows 56

A320 Family Figure 56-1 - Cockpit windows

Lateral windows Front windows

Sliding window Guiding track

Control handle

Fixed window Sliding window

Issue 6 Revision 1, January 2012

D FW

56.10.102

Page 635

[ 56-3]

A320 Family

56 Windows Table 56-1 - Technical solutions description TDU

Title (Remarks)

Appl.

Weight (kg) MWE/OWE/APL

Std

Basic front windows - SAINTGOBAIN SULLY / Basic lateral windows - GKN

Issue 6 Revision 1, January 2012

A318-100 A319-100 A320-200 A321-200

Equipment reference

Equipment supplier

Equipment PN

QTY

STS

Front window panel SAINT-GOBAIN (LH) SULLY

STA320-1-8-2

1

SFE

Front window panel SAINT-GOBAIN (RH) SULLY

STA320-2-8-2

1

SFE

Lateral fixed window panel (LH)

GKN AEROSPACE TRANSPARENCY SYSTEMS

NH25216-141

1

SFE

Lateral fixed window panel (RH)

GKN AEROSPACE TRANSPARENCY SYSTEMS

NH25216-142

1

SFE

Lateral sliding window panel (LH)

GKN AEROSPACE TRANSPARENCY SYSTEMS

NH25216-1

1

SFE

Lateral sliding window panel (RH)

GKN AEROSPACE TRANSPARENCY SYSTEMS

NH25216-2

1

SFE

56.10.102

Page 636

[ 56-4]

Windows 56

A320 Family TDU

Title (Remarks)

Appl.

Weight (kg) MWE/OWE/APL

23

25

28

Alternate lateral windows SAINT-GOBAIN SULLY

Alternate lateral windows PPG

Alternate front windows - PPG

Issue 6 Revision 1, January 2012

A318-100 A319-100 A320-200 A321-200

A318-100 A319-100 A320-200 A321-200

A318-100 A319-100 A320-200 A321-200

18.0/18.0/-18.0 18.0/18.0/-18.0 18.0/18.0/-18.0 18.0/18.0/-18.0

14.0/14.0/-14.0 14.0/14.0/-14.0 14.0/14.0/-14.0 14.0/14.0/-14.0

1.5/1.5/-1.5 1.5/1.5/-1.5 1.5/1.5/-1.5 1.5/1.5/-1.5

Equipment reference

Equipment supplier

Equipment PN

QTY

STS

Lateral fixed window panel (LH)

SAINT-GOBAIN SULLY

SPSA320-9-2- 1 2

SFE

Lateral fixed window panel (RH)

SAINT-GOBAIN SULLY

SPSA320-102-2

1

SFE

Lateral sliding window panel (LH)

SAINT-GOBAIN SULLY

SPSA320-7-4- 1 2

SFE

Lateral sliding window panel (RH)

SAINT-GOBAIN SULLY

SPSA320-8-4- 1 2

SFE

Lateral fixed window panel (LH)

PPG INDUSTRIES

NP165313-3

1

SFE

Lateral fixed window panel (RH)

PPG INDUSTRIES

NP165313-4

1

SFE

Lateral sliding window panel (LH)

PPG INDUSTRIES

NP165312-11

1

SFE

Lateral sliding window panel (RH)

PPG INDUSTRIES

NP165312-12

1

SFE

Front window panel PPG INDUS(LH) TRIES

NP165331-1

1

SFE

Front window panel PPG INDUSTRIES (RH)

NP165331-2

1

SFE

56.10.102

Page 637

[ 56-5]

A320 Family

56 Windows

Intentionally left blank

Issue 6 Revision 1, January 2012

56.10.102

Page 638

[ 56-6]

A320 Family Reference

Title

57.40.100

Leading edge and leading edge devices

57.49.101

Wing leading edge access panels - miscellaneous changes

Issue 6 Revision 1, January 2012

Wings 57

Page 639

[ 57-1]

A320 Family

57 Wings 57.40.100 - Leading edge and leading edge devices Objective for A320-200 To install the common root fillet fairing seal currently used on A318/A319/A321 and A320-200 CFM, as well on A320-200 IAE in order to achieve commonality and improve aerodynamic properties. Basic aircraft for A320-200 A specific seal assembly is standard on A320-200 equipped with IAE engines. Description for A320-200 The common and interchangeable root fillet fairing seal is installed, achieving commonality and improving aerodynamic properties. EPAC selection mode Individual

Issue 6 Revision 1, January 2012

57.40.100

Page 640

[ 57-2]

Wings 57

A320 Family Table 57-1 - Technical solutions description TDU

Title (Remarks)

Appl.

Weight (kg) MWE/OWE/APL

01

Install common root fillet fairing seal (A320-200 with IAE engines)

Issue 6 Revision 1, January 2012

A320-200

Equipment reference

Equipment supplier

Equipment PN

QTY

STS

1.0/1.0/-1.0

57.40.100

Page 641

[ 57-3]

A320 Family

57 Wings

57.49.101 - Wing leading edge access panels - miscellaneous changes Objective To remove the sealant from the wing leading edge access panels Basic aircraft Polysulphide sealant applied to fill the gap between installed leading edge access panels and forward edge of the bottom wing skin Description The sealant applied to fill the gap between installed leading edge access panels and forward edge of the bottom wing skin is removed. EPAC selection mode Individual

Issue 6 Revision 1, January 2012

57.49.101

Page 642

[ 57-4]

Wings 57

A320 Family Table 57-2 - Technical solutions description TDU

Title (Remarks)

Appl.

Weight (kg) MWE/OWE/APL

01

Wing leading edge access panels - removal of sealant

Issue 6 Revision 1, January 2012

A318-100 A319-100 A320-200 A321-200

Equipment reference

Equipment supplier

Equipment PN

QTY

STS

Negl./Negl./Negl. Negl./Negl./Negl. Negl./Negl./Negl. Negl./Negl./Negl.

57.49.101

Page 643

[ 57-5]

A320 Family

57 Wings

Intentionally left blank

Issue 6 Revision 1, January 2012

57.49.101

Page 644

[ 57-6]

A320 Family Reference

Title

72.00.118

Engines selection and alternate equipment (A318)

72.00.119

Engines selection and alternate equipment (A319)

72.00.120

Engines selection and alternate equipment (A320)

72.00.121

Engines selection and alternate equipment (A321)

Issue 6 Revision 1, January 2012

Engines 72

Page 645

[ 72-1]

A320 Family

72 Engines 72.00.118 - Engines selection and alternate equipment (A318) Objective for A318-100 To allow basic engines selection by the customer, and to offer alternate engines with different thrust rating.

EPAC selection mode Individual

Basic aircraft for A318-100 The basic aircraft can be equipped with the following engines (depending on the customer's choice): • CFM INTERNATIONAL (CFMI): CFM56-5B8/3 (PIP) at 21 600 lbf nominal thrust or 21 200 lbf Airbus Equivalent Thrust or • PRATT & WHITNEY: PW6122A at 22 100 lbf nominal thrust or 21 100 lbf Airbus Equivalent Thrust. Description for A318-100 • installation of CFMI (PIP) or PRATT & WHITNEY engines • modification or pin programming of the associated equipment: DMC, ELAC, FAC, FDIMU, FMGC, FWC. Note for A318-100 Airbus Equivalent Thrust definition: Mach number 0.25 /ISA+15°C/ sea level thrust divided by 0.8 (representative of sea level aircraft performance).

Issue 6 Revision 1, January 2012

72.00.118

Page 646

[ 72-2]

Engines 72

A320 Family Figure 72-1 - Engines selection (A318)

PRATT & WHITNEY engines

CFMI engines

Engine mounts

Plug

Primary nozzle

Pivoting door thrust reverser Air inlet Systems installations

Issue 6 Revision 1, January 2012

Fan cowl doors

72.00.118

Page 647

[ 72-3]

A320 Family

72 Engines Table 72-1 - Technical solutions description TDU

Title (Remarks)

Appl.

Weight (kg) MWE/OWE/APL

Equipment reference

Equipment supplier

Equipment PN

QTY

STS

03

CFMI engines - CFM56-5B8/3 (SAC - Tech Insertion - PIP) at 21 600 lbf nominal thrust (A318-111)

A318-100

Negl./Negl./Negl.

Engine

CFM INTERNATIONAL (CFMI)

CFM56-5B8/3

2

SFE

07

CFMI engines - CFM56-5B9/3 (SAC - Tech Insertion - PIP) at 23 300 lbf nominal thrust (A318-112)

A318-100

Negl./Negl./Negl.

Engine

CFM INTERNATIONAL (CFMI)

CFM56-5B9/3

2

SFE

31

PW engines - PW6122A at 22 100 lbf nominal thrust (A318121)

A318-100

Negl./Negl./Negl.

Engine

PRATT & WHITNEY

PW6122A

2

SFE

A318-100

Negl./Negl./Negl.

Engine

PRATT & WHITNEY

PW6124A

2

SFE

Subject to lead-time confirmation.

35

PW engines - PW6124A at 23 800 lbf nominal thrust (A318122) Subject to lead-time confirmation.

Issue 6 Revision 1, January 2012

72.00.118

Page 648

[ 72-4]

Engines 72

A320 Family

Intentionally left blank

Issue 6 Revision 1, January 2012

72.00.118

Page 649

[ 72-5]

A320 Family

72 Engines 72.00.119 - Engines selection and alternate equipment (A319) Objective for A319-100 To allow basic engines selection by the customer, and to offer alternate engines with different thrust rating.

EPAC selection mode Individual

Basic aircraft for A319-100 The basic aircraft can be equipped with the following engines (depending on the customer's choice): • CFM INTERNATIONAL (CFMI): CFM56-5B5/3 (PIP) at 22 000 lbf nominal thrust or 22 100 lbf Airbus Equivalent Thrust or • INTERNATIONAL AERO ENGINES (IAE): V2522A5 (SelectOne) at 22 000 lbf nominal thrust or 21 900 lbf Airbus Equivalent Thrust. Description for A319-100 • installation of CFMI (PIP) or IAE (SelectOne) engines • modification or pin programming of the associated equipment: DMC, ELAC, FAC, FDIMU, FMGC, FWC. Note for A319-100 Airbus Equivalent Thrust definition: Mach number 0.25 /ISA+15°C/ sea level thrust divided by 0.8 (representative of sea level aircraft performance).

Issue 6 Revision 1, January 2012

72.00.119

Page 650

[ 72-6]

Engines 72

A320 Family Figure 72-2 - Engines selection (A319)

IAE engines

CFMI engines

Engine mounts

Plug

Engine mounts

Primary nozzle

Pivoting door thrust reverser Air inlet Systems installations

Issue 6 Revision 1, January 2012

Air inlet Systems installations

Fan cowl doors

72.00.119

Cascade thrust reverser Fan cowl doors

Page 651

[ 72-7]

A320 Family

72 Engines Table 72-2 - Technical solutions description TDU

Title (Remarks)

Appl.

Weight (kg) MWE/OWE/APL

Equipment reference

Equipment supplier

Equipment PN

QTY

STS

01

CFMI engines - CFM56-5B5/3 (SAC - Tech Insertion - PIP) at 22 000 lbf nominal thrust (A319-111)

A319-100

Negl./Negl./Negl.

Engine

CFM INTERNATIONAL (CFMI)

CFM56-5B5/3

2

SFE

03

CFMI engines - CFM56-5B6/3 (SAC - Tech Insertion - PIP) at 23 500 lbf nominal thrust (A319-112)

A319-100

Negl./Negl./Negl.

Engine

CFM INTERNATIONAL (CFMI)

CFM56-5B6/3

2

SFE

15

CFMI engines - CFM56-5B7/3 (SAC - Tech Insertion - PIP) at 27 000 lbf nominal thrust (A319-115)

A319-100

Negl./Negl./Negl.

Engine

CFM INTERNATIONAL (CFMI)

CFM56-5B7/3

2

SFE

40

IAE engines - V2522-A5 (SelectOne) at 22 000 lbf nominal thrust (A319-131)

A319-100

Negl./Negl./Negl.

Engine

INT AERO ENGINES AG

IAE V2522-A5 2

SFE

41

IAE engines - V2524-A5 (SelectOne) at 23 500 lbf nominal thrust (A319-132)

A319-100

Negl./Negl./Negl.

Engine

INT AERO ENGINES AG

IAE V2524-A5 2

SFE

42

IAE engines - V2527M-A5 (SelectOne) at 26 500 lbf nominal thrust (A319-133)

A319-100

Negl./Negl./Negl.

Engine

INT AERO ENGINES AG

IAEV2527MA5

SFE

Issue 6 Revision 1, January 2012

72.00.119

2

Page 652

[ 72-8]

Engines 72

A320 Family

Intentionally left blank

Issue 6 Revision 1, January 2012

72.00.119

Page 653

[ 72-9]

A320 Family

72 Engines 72.00.120 - Engines selection and alternate equipment (A320) Objective for A320-200 To allow basic engines selection by the customer, and to offer alternate engines with different thrust rating.

EPAC selection mode Individual

Basic aircraft for A320-200 The basic aircraft can be equipped with the following engines (depending on the customer's choice): • CFM INTERNATIONAL (CFMI): CFM56-5B4/3 (PIP) at 27 000 lbf nominal thrust or 25 900 lbf Airbus Equivalent Thrust or • INTERNATIONAL AERO ENGINES (IAE): V2527A5 (SelectOne) at 26 500 lbf nominal thrust or 25 400 lbf Airbus Equivalent Thrust. Description for A320-200 • installation of CFMI (PIP) or IAE (SelectOne) engines • modification or pin programming of the associated equipment: DMC, ELAC, FAC, FDIMU, FMGC, FWC. Note for A320-200 Airbus Equivalent Thrust definition: Mach number 0.25 /ISA+15°C/ sea level thrust divided by 0.8 (representative of sea level aircraft performance).

Issue 6 Revision 1, January 2012

72.00.120

Page 654

[ 72-10]

Engines 72

A320 Family Figure 72-3 - Engines selection (A320)

IAE engines

CFMI engines

Engine mounts

Plug

Engine mounts

Primary nozzle

Pivoting door thrust reverser Air inlet Systems installations

Issue 6 Revision 1, January 2012

Air inlet Systems installations

Fan cowl doors

72.00.120

Cascade thrust reverser Fan cowl doors

Page 655

[ 72-11]

A320 Family

72 Engines Table 72-3 - Technical solutions description TDU

Title (Remarks)

Appl.

Weight (kg) MWE/OWE/APL

Equipment reference

Equipment supplier

Equipment PN

QTY

STS

01

CFMI engines - CFM56-5B4/3 (SAC - Tech Insertion - PIP) at 27 000 lbf nominal thrust (A320-214)

A320-200

Negl./Negl./Negl.

Engine

CFM INTERNATIONAL (CFMI)

CFM56-5B4/3

2

SFE

09

CFMI engines - CFM56-5B5/3 (SAC - Tech Insertion - PIP) at 22 000 lbf nominal thrust (A320-215)

A320-200

Negl./Negl./Negl.

Engine

CFM INTERNATIONAL (CFMI)

CFM56-5B5/3

2

SFE

10

CFMI engines - CFM56-5B6/3 (SAC - Tech Insertion - PIP) at 23 500 lbf nominal thrust (A320-216)

A320-200

Negl./Negl./Negl.

Engine

CFM INTERNATIONAL (CFMI)

CFM56-5B6/3

2

SFE

30

IAE engines - V2527-A5 (SelectOne) at 26 500 lbf nominal thrust (A320-232)

A320-200

Negl./Negl./Negl.

Engine

INT AERO ENGINES AG

IAE V2527-A5 2

SFE

32

IAE engines - V2527E-A5 (SelectOne) at 26 500 lbf nominal thrust (A320-233)

A320-200

Negl./Negl./Negl.

Engine

INT AERO ENGINES AG

IAE V2527EA5

SFE

Issue 6 Revision 1, January 2012

72.00.120

2

Page 656

[ 72-12]

Engines 72

A320 Family

Intentionally left blank

Issue 6 Revision 1, January 2012

72.00.120

Page 657

[ 72-13]

A320 Family

72 Engines 72.00.121 - Engines selection and alternate equipment (A321) Objective for A321-200 To allow basic engines selection by the customer, and to offer alternate engines with different thrust rating.

EPAC selection mode Individual

Basic aircraft for A321-200 The basic aircraft can be equipped with the following engines (depending on the customer's choice): • CFM INTERNATIONAL (CFMI): CFM56-5B3/3 (PIP) at 33 000 lbf nominal thrust or 31 900 lbf Airbus Equivalent Thrust or • INTERNATIONAL AERO ENGINES (IAE): V2533A5 (SelectOne) at 33 000 lbf nominal thrust or 31 700 lbf Airbus Equivalent Thrust. Description for A321-200 • installation of CFMI (PIP) or IAE (SelectOne) engines • modification or pin programming of the associated equipment: DMC, ELAC, FAC, FDIMU, FMGC, FWC. Note for A321-200 Airbus Equivalent Thrust definition: Mach number 0.25 /ISA+15°C/ sea level thrust divided by 0.8 (representative of sea level aircraft performance).

Issue 6 Revision 1, January 2012

72.00.121

Page 658

[ 72-14]

Engines 72

A320 Family Figure 72-4 - Engines selection (A321)

IAE engines

CFMI engines

Engine mounts

Plug

Engine mounts

Primary nozzle

Pivoting door thrust reverser Air inlet Systems installations

Issue 6 Revision 1, January 2012

Air inlet Systems installations

Fan cowl doors

72.00.121

Cascade thrust reverser Fan cowl doors

Page 659

[ 72-15]

A320 Family

72 Engines Table 72-4 - Technical solutions description TDU

Title (Remarks)

Appl.

Weight (kg) MWE/OWE/APL

Equipment reference

Equipment supplier

Equipment PN

QTY

STS

04

CFMI engines - CFM56-5B1/3 (SAC - Tech Insertion - PIP) at 30 000 lbf nominal thrust (A321-212)

A321-200

Negl./Negl./Negl.

Engine

CFM INTERNATIONAL (CFMI)

CFM56-5B1/3

2

SFE

12

CFMI engines - CFM56-5B2/3 (SAC - Tech Insertion - PIP) at 31 000 lbf nominal thrust (A321-213)

A321-200

Negl./Negl./Negl.

Engine

CFM INTERNATIONAL (CFMI)

CFM56-5B2/3

2

SFE

13

CFMI engines - CFM56-5B3/3 (SAC - Tech Insertion - PIP) at 33 000 lbf nominal thrust (A321-211)

A321-200

Negl./Negl./Negl.

Engine

CFM INTERNATIONAL (CFMI)

CFM56-5B3/3

2

SFE

30

IAE engines - V2530-A5 (SelectOne) at 30 000 lbf nominal thrust (A321-232)

A321-200

Negl./Negl./Negl.

Engine

INT AERO ENGINES AG

IAE V2530-A5 2

SFE

32

IAE engines - V2533-A5 (SelectOne) at 33 000 lbf nominal thrust (A321-231)

A321-200

Negl./Negl./Negl.

Engine

INT AERO ENGINES AG

IAE V2533-A5 2

SFE

Issue 6 Revision 1, January 2012

72.00.121

Page 660

[ 72-16]

A320 Family

Engine fuel and control 73

Reference

Title

73.21.100

Installation of additional sensors for engine health monitoring

Issue 6 Revision 1, January 2012

Page 661

[ 73-1]

A320 Family

73 Engine fuel and control

73.21.100 - Installation of additional sensors for engine health monitoring Objective To allow more detailed engine health monitoring capability . Baseline definition for leased aircraft: Information available from each FADEC, used for cockpit indications, is also available as data source for engine monitoring. The FADEC system incorporates provision to process the additional parameters. Basic aircraft Information available from each FADEC, used for cockpit indications, is also available as data source for engine monitoring. The FADEC system incorporates provision to process the additional parameters.

The sensors are connected to the FADEC. Additional parameters are transmitted to the AIDS DMU via the FADEC ARINC 429 bus. The data provided by the additional sensors is directly compatible with the ground software provided by the engine manufacturer. There are no new reports or failure messages associated with the additional parameters. EPAC selection mode Individual

Description Installation of additional sensors and associated wiring allow health monitoring of the engine modules.They permit reading of the following parameters: • PS13: fan tip discharge pressure. • P25: HP compressor inlet pressure. • T5: LP turbine discharge temperature.

Issue 6 Revision 1, January 2012

73.21.100

Page 662

[ 73-2]

Engine fuel and control 73

A320 Family

Table 73-1 - Technical solutions description TDU

Title (Remarks)

Appl.

Weight (kg) MWE/OWE/APL

03

Installation of additional sensors for CFM56-5B engine health monitoring

Issue 6 Revision 1, January 2012

A318-100 A319-100 A320-200 A321-200

Equipment reference

Equipment supplier

Equipment PN

QTY

STS

5.0/5.0/-5.0 5.0/5.0/-5.0 5.0/5.0/-5.0 5.0/5.0/-5.0

73.21.100

Page 663

[ 73-3]

A320 Family

73 Engine fuel and control

Intentionally left blank

Issue 6 Revision 1, January 2012

73.21.100

Page 664

[ 73-4]

A320 Family

Oil 79

Reference

Title

79.00.101

Engine, engine accessories and Auxiliary Power Unit (APU) alternate lubricating oil

79.40.101

Installation of Integrated Drive Generator (IDG) oil level viewing port on engine RH fan cowl

Issue 6 Revision 1, January 2012

Page 665

[ 79-1]

A320 Family

79 Oil

79.00.101 - Engine, engine accessories and Auxiliary Power Unit (APU) alternate lubricating oil Objective To provide alternate engine/APU lubricating oil. Basic aircraft Oil MOBIL JET II is used. Description Change lubricating oil type in the following equipment: • engine • engine starter • IDG • APU. Instruction labels on the oil system shall also be replaced. EPAC selection mode Individual

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79.00.101

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Oil 79

A320 Family Figure 79-1 - Oil indications

APU

ENGINE 1530

F.USED KG

1560

OIL

20 0 11.5 100

QT

0 11.5

(N1)

0.8

0.9

VIB

(N2)

1.2

1.3

0

NAC °C

TAT +19 °C SAT +18 °C

N %

FUEL LO PR FLAP OPEN

20

EGT 3

90

7

°C

580

TAT +19 °C SAT +18 °C

G.W. 60300 KG

23 H 56

Engine page

Issue 6 Revision 1, January 2012

PSI

100

5

105

BLEED

35

10

0 44 °C

AVAIL

APU GEN 26 % 116 V 400 HZ

100

PSI

0 42

15

20

VIB

OIL QTY BELOW 1/4

G.W. 60300 KG

23 H 56

APU page

79.00.101

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A320 Family

79 Oil Table 79-1 - Technical solutions description TDU

Title (Remarks)

Appl.

Weight (kg) MWE/OWE/APL

Std

Engine, engine accessories and APU basic lubricating oil MOBIL JET II

A318-100 A319-100 A320-200 A321-200

01

Engine, engine accessories and APU alternate lubricating oil - BPTO 2380

A318-100 A319-100 A320-200 A321-200

Negl./Negl./Negl. Negl./Negl./Negl. Negl./Negl./Negl. Negl./Negl./Negl.

A318-100 A319-100 A320-200 A321-200

Negl./Negl./Negl. Negl./Negl./Negl. Negl./Negl./Negl. Negl./Negl./Negl.

Not approved for use on PW 6000 engines.

12

Engine, engine accessories and APU alternate lubricating oil - BPTO 2197

Issue 6 Revision 1, January 2012

Equipment reference

79.00.101

Equipment supplier

Equipment PN

QTY

Page 668

STS

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Oil 79

A320 Family

Intentionally left blank

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A320 Family

79 Oil

79.40.101 - Installation of Integrated Drive Generator (IDG) oil level viewing port on engine RH fan cowl Objective To allow visual checking of the IDG oil level without opening of the fan cowls. Basic aircraft Opening of the fan cowls is required to check the IDG oil level. Description The modification consists in installing an access panel on the RH fan cowls. EPAC selection mode Individual

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Oil 79

A320 Family Figure 79-2 - IDG oil level viewing port on engine RH fan cowl

RH fan cowl door

IDG oil level viewing port

View looking outboard

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A320 Family

79 Oil Table 79-2 - Technical solutions description TDU

Title (Remarks)

Appl.

Weight (kg) MWE/OWE/APL

02

Installation of IDG oil level viewing port on CFM56-5B engine RH fan cowl

Issue 6 Revision 1, January 2012

A318-100 A319-100 A320-200 A321-200

Equipment reference

Equipment supplier

Equipment PN

QTY

STS

0.5/0.5/-0.5 0.5/0.5/-0.5 0.5/0.5/-0.5 0.5/0.5/-0.5

79.40.101

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