A320 System Configuration Guide

Authorized by BSMC

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

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Table of contents

ATA

Title

Title

ATA

Introduction 00

Certification and external livery 02 General aircraft design criteria 03

Placards and markings 11

Air conditioning 21 Auto flight 22 Communications 23 Electrical power 24 Equipment/furnishings 25 Fire protection 26 Fuel 28 Hydraulic power 29

Ice and rain protection 30

Indicating/recording systems 31 Landing gear 32 Lights 33 Navigation 34 Oxygen 35 Water/waste 38 Information systems 46

Auxiliary Power Unit (APU) 49

Structures 51 Doors 52 Fuselage 53 Stabilizers 55 Windows 56 Wings 57 Engines 72

Engine fuel and control 73

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Introduction

1

[00]

00.00.200 - Introduction 2 [00-2]

Certification and external livery

9

[02]

02.10.104 - Certification of dynamically tested passenger seats 10 [02-2]

02.10.111 - Compliance with FAA type certification requirements 12 [02-4]

02.10.112 - Partial compliance with FAA type certification requirements 16 [02-8]

02.10.120 - 15 knots tailwind certification 20 [02-12]

02.10.123 - Operation on runways with reduced width 22 [02-14]

02.10.190 - ETOPS 120/180 min 24 [02-16]

02.12.122 - Compliance status with EU-OPS 1 30 [02-22]

02.12.123 - Compliance with CS25/FAR 25.562 (Head Injury Criteria - HIC) 32 [02-24] 02.12.130 - EASA certification of Take Off/Landing operation on wet grooved / PFC

runways

34 [02-26]

02.40.101 - External livery 36 [02-28]

General aircraft design criteria

39

[03]

03.20.300 - Design weights (A318) 40 [03-2]

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03.20.500 - Design weights (A320) 48 [03-10]

03.20.600 - Design weights (A321) 52 [03-14]

Placards and markings

57

[11]

11.00.124 - Installation of leasing identification plates 58 [11-2]

11.20.100 - Second language for door operation external placards and markings 60 [11-4] 11.20.110 - Second language for selected external placards and markings 62 [11-6]

11.20.119 - Nose Landing Gear (NLG) permanent steering markers 64 [11-8]

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

68 [11-12]

11.21.101 - Emergency cut-out markings 72 [11-16]

11.22.100 - Landing gear placards 76 [11-20]

11.30.100 - Installation of additional access placards in forward and aft cargo holds 78 [11-22]

11.30.121 - Second language for cargo compartment placards 82 [11-26]

11.30.136 - US and metric units for cargo compartment height placards 86 [11-30]

11.33.101 - Placard for flight crew oxygen system 90 [11-34]

Air conditioning

93

[21]

21.20.108 - Cabin air recirculation filter cartridges equipment selection 94 [21-2] 21.22.100 - Installation of electrical heaters for foot air outlets in the cockpit 98 [21-6] 21.26.110 - Avionics ventilation fan automatic speed reduction 102 [21-10]

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21.27.108 - Avionics ventilation air filter alternate equipment 106 [21-14] 21.28.201 - Installation of ventilation system for forward cargo hold 110 [21-18] 21.28.210 - Installation of ventilation system for complete aft cargo hold 114 [21-22] 21.41.100 - Installation of front air outlets at flight crew foot level 118 [21-26] 21.43.201 - Installation of heating system for forward cargo hold 120 [21-28] 21.43.204 - Installation of heating system for complete aft cargo hold 124 [21-32]

21.70.109 - Installation of ozone catalytic converters 128 [21-36]

Auto flight

131

[22]

22.00.104 - Automatic landing capability 132 [22-2]

22.70.100 - Flight Management (FM) kits alternate equipment 134 [22-4]

22.81.143 - Inhibition of the expedite pushbutton 138 [22-8]

22.82.103 - Installation of third Multipurpose Control and Display Unit (MCDU) 142 [22-12]

Communications

145

[23]

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

148 [23-4]

23.11.102 - Full provision for single HF system 152 [23-8]

23.11.111 - Full provision for dual HF system 156 [23-12]

23.11.116 - Installation of single HF system (SFE) 160 [23-16]

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23.11.155 - Installation of dual HF system (SFE) 166 [23-22]

23.11.167 - Additional wiring for HF Data Link (HFDL) function 170 [23-26]

23.11.169 - Activation of HF Data Link (HFDL) function 172 [23-28]

23.12.130 - VHF Data Radio (VDR) alternate equipment 174 [23-30]

23.13.100 - Installation of alternate Radio Management Panel (RMP) 178 [23-34] 23.13.101 - Installation of third Radio Management Panel (RMP) 180 [23-36]

23.13.105 - Activation of RMP std 4 frequency load function 184 [23-40]

23.28.170 - Installation of AERO H+/SBB SATCOM cockpit voice interface 186 [23-42]

23.28.210 - Installation of SATCOM AERO H+ SRT 2100B system 188 [23-44]

23.28.211 - Installation of SwiftBroadband (SBB) SATCOM system 192 [23-48] 23.50.110 - Installation of additional Audio Control Panel (ACP) and jack panel 196 [23-52]

23.50.135 - Installation of headset for fourth occupant 200 [23-56]

23.50.138 - Cockpit hand microphone alternate equipment 204 [23-60]

23.51.103 - Installation of active noise canceling boomsets (SFE) 206 [23-62]

23.51.136 - Boomsets alternate equipment 210 [23-66]

23.51.139 - Boomsets alternate equipment with two jack plugs 214 [23-70]

23.70.110 - Installation of a video monitoring system 218 [23-74]

23.71.103 - Solid State Cockpit Voice Recorder (SSCVR) alternate equipment 220 [23-76] 23.71.110 - Recorder Independent Power Supply (RIPS) - 28VDC power supply for CVR 224 [23-80] 23.71.120 - System provision for CVR capable of data link recording 226 [23-82] 23.73.200 - Installation of cockpit and cabin alert switches (Aircraft Security Project) 228 [23-84]

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Electrical power

231

[24]

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

232 [24-2]

Equipment/furnishings

235

[25]

25.10.108 - Installation of paper holder on the glareshield 238 [25-4]

25.11.102 - Pilot seats alternate covers - sheepskin 240 [25-6]

25.11.208 - Installation of fourth occupant seat in cockpit 244 [25-10]

25.27.100 - Installation of heated floor panels for fwd passenger/crew/service door area 248 [25-14] 25.27.101 - Installation of On/off switch for heated floor panels 252 [25-18] 25.50.137 - Rubber seal profile for cargo compartment floor panels 254 [25-20] 25.50.510 - Basic full bulk configuration selection in forward and aft cargo holds 258 [25-24] 25.50.520 - Installation of reinforced floor panels for heavy bulk usage in forward and aft

cargo holds

262 [25-28]

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

268 [25-34]

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

272 [25-38]

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

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

278 [25-44]

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

282 [25-48]

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

284 [25-50]

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

288 [25-54]

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

294 [25-60]

25.52.315 - Full electrical provision for semi-automatic CLS 298 [25-64]

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

300 [25-66]

25.52.407 - Bulk loading capability in aft cargo hold door area behind two ULDs (A319) 304 [25-70] 25.52.410 - Full provision for installation of special container in aft cargo hold, door area

(A319)

308 [25-74]

25.52.500 - Installation of continuous side guides in forward cargo hold 312 [25-78] 25.52.511 - Installation of continuous side guides in aft cargo hold 316 [25-82]

Fire protection

319

[26]

26.20.103 - Auxiliary Power Unit (APU) fire extinguisher alternate equipment 320 [26-2]

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26.23.103 - Cargo holds fire extinguisher alternate equipment 328 [26-10]

26.23.111 - Cargo holds fire extinguishers extended duration for ETOPS 120 min 330 [26-12] 26.23.112 - Cargo holds fire extinguishers extended duration for ETOPS 180 min 334 [26-16]

Fuel

337

[28]

28.11.133 - Full provision for installation of one Additional Center Tank (ACT) in aft cargo hold

338 [28-2]

28.11.140 - Full provision for installation of two/one Additional Center Tanks (ACTs) in aft cargo hold

342 [28-6]

28.11.225 - Installation of one Additional Center Tank (ACT) in aft cargo hold 346 [28-10] 28.11.235 - Installation of two Additional Center Tanks (ACTs) in aft cargo hold 352 [28-16] 28.25.107 - Installation of additional refuel/defuel coupling in LH wing 356 [28-20] 28.25.110 - Installation of fuel quantity preselector in cockpit 360 [28-24]

28.25.130 - Relocation of refuel/defuel control panel 364 [28-28]

Hydraulic power

367

[29]

29.10.110 - Hydraulic Engine Driven Pumps (EDPs) alternate equipment 368 [29-2]

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Ice and rain protection

375

[30]

30.41.102 - Installation of intermittent function of windshield wipers 376 [30-2]

30.70.108 - Extended freezing protection 380 [30-6]

30.81.105 - Installation of dual advisory ice detection system 382 [30-8]

Indicating/recording systems

387

[31]

31.00.107 - US units for indicators and labels 388 [31-2]

31.14.103 - Overhead panel toggle switches re-orientation 392 [31-6]

31.33.051 - Flight Data Interface and Management Unit (FDIMU) alternate equipment 396 [31-10] 31.33.132 - Installation of Quick Access Recorder (QAR/WGL-QAR) 402 [31-16] 31.33.200 - Solid State Flight Data Recorder (SSFDR) alternate equipment 406 [31-20] 31.33.210 - Digital Flight Data Recorder System (DFDRS) capabilities 410 [31-24] 31.36.161 - Installation of Digital AIDS Recorder (DAR/WGL-DAR) (BFE) 412 [31-26] 31.60.114 - Indication of metric altitude on Primary Flight Display (PFD) 416 [31-30] 31.60.120 - Installation of Electronic Instrument System (EIS2) 420 [31-34] 31.65.100 - Activation of Minimum Off Route Altitude (MORA) on Navigation Display (ND) 422 [31-36]

Landing gear

425

[32]

32.40.113 - Wheels and brakes alternate equipment 426 [32-2]

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32.41.120 - Nose Landing Gear (NLG) tires selection 434 [32-10]

32.48.200 - Installation of universal brake cooling fans 438 [32-14]

32.49.109 - Installation of Tire Pressure Indicating System (TPIS) on twin wheel 442 [32-18]

Lights

445

[33]

33.12.109 - Changes in cockpit illumination (excluding instrument and panel lighting) 446 [33-2]

33.43.000 - Runway turnoff lights 448 [33-4]

33.46.000 - Taxi and take-off lights 450 [33-6]

Navigation

453

[34]

34.00.108 - QNH/QFE BARO setting 456 [34-4]

34.13.105 - Installation of aspirated Total Air Temperature (TAT) probes 460 [34-8]

34.13.106 - Pitot probes alternate equipment 464 [34-12]

34.15.101 - Angle Of Attack (AOA) sensors alternate equipment 468 [34-16]

34.20.203 - Integrated Standby Instrument System (ISIS) optional functions 472 [34-20] 34.35.109 - System provision for Head Up Display (HUD) system installation 476 [34-24] 34.35.110 - Installation (based on provision) of Head Up Display (HUD) system 478 [34-26] 34.41.302 - Full single Weather Radar (WXR) system alternate equipment 480 [34-28]

34.41.310 - Installation of dual Weather Radar (WXR) System 484 [34-32]

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34.42.117 - Radio altitude automatic call-outs 492 [34-40]

34.43.203 - Traffic Alert and Collision Avoidance System (TCAS) alternate equipment (SFE)

496 [34-44]

34.43.250 - Installation of T2CAS 500 [34-48]

34.43.260 - T2CAS - Activation of alternate warnings 502 [34-50]

34.43.270 - Wiring provision for T3CAS 504 [34-52]

34.43.290 - Wiring provision for Aircraft Traffic Situation Awareness (ATSAW) 506 [34-54]

34.43.295 - Activation of ATSAW function 508 [34-56]

34.48.124 - Enhanced Ground Proximity Warning System (EGPWS) - alternate equipment

510 [34-58]

34.48.127 - Enhanced Ground Proximity Warning System (EGPWS) alternate warnings 512 [34-60] 34.48.132 - Enhanced Ground Proximity Warning System (EGPWS) - optional functions 514 [34-62] 34.51.101 - Distance Measuring Equipment (DME) interrogators alternate equipment 516 [34-64] 34.52.117 - Automatic Dependent Surveillance - Broadcast (ADS-B OUT) 520 [34-68] 34.52.133 - Compliance with European enhanced surveillance (EHS) regulation 522 [34-70] 34.52.140 - Air Traffic Control (ATC) control panel alternate equipment 524 [34-72] 34.53.109 - Full provision for second Automatic Direction Finder (ADF) system 528 [34-76] 34.53.111 - Single Automatic Direction Finder (ADF) system alternate equipment 532 [34-80] 34.53.119 - Installation of dual Automatic Direction Finder (ADF) system 536 [34-84] 34.55.102 - VHF Omnidirectional Range (VOR)/Marker receivers alternate equipment 540 [34-88]

34.58.313 - Multi Mode Receiver (MMR) alternate equipment 544 [34-92]

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34.58.317 - Activation of FLS function 550 [34-98]

34.58.340 - Installation of MLS function for cat IIIb operation hosted by the MMR 552 [34-100]

Oxygen

555

[35]

35.11.102 - Installation of in-situ replenishment facility for cockpit oxygen cylinder 556 [35-2]

35.11.201 - Cockpit oxygen cylinder alternate equipment 560 [35-6]

35.20.010 - Installation of four oxygen masks per box 564 [35-10]

35.20.113 - Extended supply duration for passenger chemical oxygen system 566 [35-12] 35.20.114 - Extended supply duration for passenger gaseous oxygen system 570 [35-16]

Water/waste

573

[38]

38.10.104 - Installation of water conditioner in potable water system 574 [38-2] 38.41.101 - Installation of auxiliary compressor in the potable water pressurization

system

576 [38-4]

Information systems

579

[46]

46.21.102 - Installation of AIRBUS standard Airline Operational Communication (AOC) software for ATSU

580 [46-2]

46.21.105 - Activation of ARINC 623 ATS applications in the ATSU 584 [46-6]

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46.21.140 - Installation of Future Air Navigation System (FANS) A+ 588 [46-10] 46.21.142 - Installation of Future Air Navigation System (FANS) B+ 590 [46-12]

Auxiliary Power Unit (APU)

593

[49]

49.00.105 - Auxiliary Power Unit (APU) alternate equipment 594 [49-2]

Structures

597

[51]

51.00.115 - Fuselage and wings extended corrosion prevention 598 [51-2]

51.22.250 - External livery decorative adhesive film 604 [51-8]

51.22.710 - Alternate paint system (CF primer/strippable) on standard areas (3 coats) 608 [51-12]

Doors

611

[52]

52.22.200 - Installation of additional emergency exits (A319) 612 [52-2]

52.51.100 - Installation of cockpit door release back-up system (MMEL conditions) 616 [52-6]

52.51.106 - Installation of modified door lock mechanism 618 [52-8]

Fuselage

621

[53]

53.30.050 - Belly fairing panels - extrusion strips 622 [53-2]

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Stabilizers

629

[55]

55.30.101 - Installation of erosion protection on vertical stabilizer leading edge 630 [55-2]

Windows

633

[56]

56.10.102 - Cockpit windows alternate equipment 634 [56-2]

Wings

639

[57]

57.40.100 - Leading edge and leading edge devices 640 [57-2]

57.49.101 - Wing leading edge access panels - miscellaneous changes 642 [57-4]

Engines

645

[72]

72.00.118 - Engines selection and alternate equipment (A318) 646 [72-2]

72.00.119 - Engines selection and alternate equipment (A319) 650 [72-6]

72.00.120 - Engines selection and alternate equipment (A320) 654 [72-10]

72.00.121 - Engines selection and alternate equipment (A321) 658 [72-14]

Engine fuel and control

661

[73]

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Oil

665

[79]

79.00.101 - Engine, engine accessories and Auxiliary Power Unit (APU) alternate lubricating oil

666 [79-2]

79.40.101 - Installation of Integrated Drive Generator (IDG) oil level viewing port on engine RH fan cowl

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Introduction 00

Reference Title

00.00.200 Introduction

00 Introduction

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00.00.200 - Introduction

1) General

This Configuration Guide is dedicated to the aircraft models and associated Standard Specifications indicat-ed 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 Specifica-tion and the other ConfiguraSpecifica-tion Guides a complete cus-tomization 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 ba-sic 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).

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 pre-defined technical solution has been developed and for which the lead times have been studied. Provided the schedule as defined in the customer definition mile-stone 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 Defi-nition Freeze (CDF) deadlines. These items are high-lighted in this catalogue by a special remark: "Subject to lead-time constraints". For these items, specific deci-sion deadlines shall be identified in customer definition milestones.

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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 so-lutions (called TDU: Technical Description Unit) as-sociated to the item.

Note: For comparison purposes, some tables also show the basic aircraft equipment, labelled Std (Standard) in the TDU column.

As far as possible, the arrangement of the items follows the ATA 100 classification. The items are sorted by nu-merical 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 sub-ATA (e.g. 24) classification, followed by a running num-ber (e.g. 600).

Each technical solution (TDU) is referenced by a two-digit 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", "pro-visions 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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b) items titled "...alternate equipment" relate to items where the customer can choose equipment alternate to that defined in the Standard Specification.

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

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 here-after).

Such solutions may be at the initial phases of develop-ment or first application on Airbus aircraft. For these items commitment to quality, industrial and technical ca-pabilities, on time delivery and customer support

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

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 stat-ed.

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.

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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 adapt-ed.

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.

Specific customer request

Items that are not mentioned in this Guide, or corre-sponding 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 Con-figuration 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 Air-bus, to raise in time the necessary specific requests re-lated 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 conse-quently lead to constraints and decisions that shall be discussed in good faith between the customer and Air-bus. 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 respon-sibility of the Buyer.

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The Buyer shall hold harmless and indemnify the Man-ufacturer against any claims or/and damages related di-rectly or indidi-rectly to an incorrect installation of an equipment or to such equipment itself, whether defec-tive or not.

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[ 00-7]

Figure 00-1 - Typical page description

25 Equipment/furnishings A320 Family

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

Reference Title

25 Equipment/furnishings A320 Family

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 den-sity of 15 lb/cu ft.

Basic aircraft for A319-100 and A320-200 and A321-200

Full bulk configuration and structural provision for at-taching optional divider nets in the forward and aft cargo holds.

System provision for CLS plus minimum electrical pro-vision for mechanized bulk loading system. Description for A319-100 and A320-200 and A321-200

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 for-ward 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

fender for protection devices for the rapid decom-pression at frame 24 A.

EPAC selection mode Global CARGO

.

ATA title and section number

(ATA section + page number within the section)

Date of the issue of the catalogue Option reference page number

Detailed description page

Chapter cover page

Issue 6 Revision 01, January 2012 Page 243 [ 26-1] Issue 6 Revision 01, January 2012 25.52.404 Page 246 [ 26-4]

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00 Introduction

A320 Family

Issue 6 Revision 1, January 2012

Figure 00-2 - Example of technical solutions description table

Table 25-21 - Technical solutions description

TDU Title (Remarks) Appl. Weight (kg)

MWE/OWE/APL Equipment_reference Equipment_supplier Equipment_PN QTY STS 01 Semi-automatic CLS in fwd

and aft cargo holds - without ACT provision (A320/A321)

A320-200

A321-200 122.0/122.0/-122.0102.0/102.0/-102.0

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

Requires prior acceptance of

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

A320-200

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 instal-lation of one ACT in aft cargo hold (A321)

A321-200

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 instal-lation of two/one ACTs in aft cargo hold (A320).

A320-200

Due to ACT, lead-time constraints for this option are 8 months.

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

153.0/153.0/-153.0

133.0/133.0/-133.0

177.0/177.0/-177.0

Title of the technical solution and optional remarks Equipment information: Technical solution Applicable series identifier (TDU) Weights information per series • reference • vendor • PN (part numbers) • quantity

• status (BFE or SFE)

MWE: Manufacturer’s Weight Empty OWE: Operational Weight Empty APL: Allowable Payload Change

Selection condition Selection condition remark Page 8

Issue 6 Revision 1, January 2012

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

02 Certification and external livery

A320 Family

Issue 6 Revision 1, January 2012

02.10.104 - Certification of dynamically tested passenger seats

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 A321-200

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.

Description for A319-100 and A320-200 and A321-200

Passenger seats are certified in accordance with seat frame specification AI 2521M1F100000 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 certifica-tion requirements.

EPAC selection mode Individual

Certification and external livery 02

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A320 Family

[ 02-3]

Table 02-1 - Technical solutions description

TDU Title (Remarks) Appl. Weight (kg)

MWE/OWE/APL Equipment reference Equipment supplier Equipment PN QTY STS 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 Page 11

02 Certification and external livery

A320 Family

Issue 6 Revision 1, January 2012

02.10.111 - Compliance with FAA type certification requirements

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 com-pliance with the FAA Type Design of the respective Air-craft 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

• 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 geome-try seats in conjunction with photoluminescent floor-mounted EEPMS is prohibited.

Certification and external livery 02

A320 Family

Issue 6 Revision 1, January 2012

02.10.111 - Compliance with FAA type certification requirements (Continued)

[ 02-5]

EPAC selection mode Individual

02 Certification and external livery

A320 Family

Issue 6 Revision 1, January 2012

Table 02-2 - Technical solutions description

TDU Title (Remarks) Appl. Weight (kg)

MWE/OWE/APL Equipment reference Equipment supplier Equipment PN QTY STS

01 Compliance with FAA type cer-tification requirements (A319/ A320/A321)

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 cata-lytic converters.

Selection of CN11.30.131/05 - Installation of weight placards on overwing hatch is recommended. A319-100 A320-200 A321-200 20.0/20.0/-20.0 20.0/20.0/-20.0 20.0/20.0/-20.0

08 Compliance with FAA type cer-tification requirements (A318)

Requires prior acceptance of

CN21.70.109 - Installation of ozone cata-lytic converters.

Requires prior acceptance of

CN11.30.131/05 - Installation of weight placards on overwing hatch.

A318-100 20.0/20.0/-20.0

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A320 Family

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02 Certification and external livery

A320 Family

Issue 6 Revision 1, January 2012

02.10.112 - Partial compliance with FAA type certification requirements

To install all modifications except cabin arrangement re-quirements, to be partially 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 partial-ly in compliance with the FAA Type Design of the re-spective 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.

A320-200

• installation of ozone converters

• installation of modified emergency exit inscription and marking.

A321-200

• installation of ozone converters. Note

• on US registered a/c the installation of variable ge-ometry seats in conjunction with photoluminescent floor-mounted EEPMS is prohibited.

• upon the selection of this option, AIRBUS will, no lat-er than 6 months before aircraft Industrial Delivlat-ery, 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 Air-worthiness Certificate" (Customization status for US op-erations).

• the selection of this option ensures the partial compli-ance of the individual aircraft MSN to the FAA Type Design, at the exclusion of the cabin layout.

Certification and external livery 02

A320 Family

Issue 6 Revision 1, January 2012

02.10.112 - Partial compliance with FAA type certification requirements (Continued)

[ 02-9]

• the delivery of a US Standard Airworthiness Certifi-cate at Aircraft ID is subject to a prior FAA validation process of the Aircraft customized definition. AIR-BUS will timely initiate and control this process pro-vided 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 De-lay of the aircraft ID

• a revised FAA TD Statement will be provided at time of delivery.

EPAC selection mode Individual

02 Certification and external livery

A320 Family

Issue 6 Revision 1, January 2012

Table 02-3 - Technical solutions description

TDU Title (Remarks) Appl. Weight (kg)

MWE/OWE/APL Equipment reference Equipment supplier Equipment PN QTY STS

04 Partial compliance with FAA type certification require-ments (without seat arrange-ment requirearrange-ments)

Requires prior acceptance of

CN21.70.109 - Installation of ozone cata-lytic converters.

Selection of CN11.30.131/05 - Installation of weight placards on overwing hatch is recommended. A319-100 A320-200 A321-200 20.0/20.0/-20.0 20.0/20.0/-20.0 20.0/20.0/-20.0

06 Partial compliance with FAA type certification require-ments (without seat arrange-ment requir) (A318)

Requires prior acceptance of

CN21.70.109 - Installation of ozone cata-lytic converters.

Requires prior acceptance of

CN11.30.131/05 - Installation of weight placards on overwing hatch.

A318-100 20.0/20.0/-20.0

Certification and external livery 02

A320 Family

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02 Certification and external livery

A320 Family

Issue 6 Revision 1, January 2012

02.10.120 - 15 knots tailwind certification

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 interpre-tation 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 dem-onstrations with 1.5 x the desired limit in terms of tail-wind.

The certification dossier for tailwind operations at take-off 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 ...)

• additional engine characteristics justifications with tailwind, in particular in terms of engine inlet.

Note

Depending on the sensitivity of the engine inlet charac-teristics 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

Certification and external livery 02

Issue 6 Revision 1, January 2012

A320 Family

[ 02-13]

Table 02-4 - Technical solutions description

TDU Title (Remarks) Appl. Weight (kg)

MWE/OWE/APL Equipment reference Equipment supplier Equipment PN QTY STS

01 15 knots tailwind certification at take-off 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 Page 21

02 Certification and external livery

A320 Family

Issue 6 Revision 1, January 2012

02.10.123 - Operation on runways with reduced width

To authorize aircraft operation on runways with a width comprised between 30 m and 45 m.

Basic aircraft

The standard aircraft is certificated for operation on run-ways 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 modifica-tions:

• new performance justifications, updating of flight manuals and TLC

• new definition of MMEL, updating of certification doc-uments

• adjustment of limitations (e.g. crosswind, autoland), updating of MEL and CDL.

Note

For aircraft equipped with a CLS and operating on re-duced runway width, it is recommended to select a bulk loading option.

EPAC selection mode Individual

Certification and external livery 02

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A320 Family

[ 02-15]

Table 02-5 - Technical solutions description

TDU Title (Remarks) Appl. Weight (kg)

MWE/OWE/APL Equipment reference Equipment supplier Equipment PN QTY STS

01 Aircraft Operation on runways less than 45m wide

Not applicable in conjunction with PW engines 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 Page 23

02 Certification and external livery

A320 Family

Issue 6 Revision 1, January 2012

02.10.190 - ETOPS 120/180 min

To make the design capable of 120/180 min maximum diversion time from diversion airport at normal one en-gine 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 Main-tenance and Procedure (CMP) document at the time of aircraft delivery.

Note

The precise list of modifications depends upon the se-lected 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 au-thority. During the operational life of the aircraft, addi-tional 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 extinguish-ers 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

Certification and external livery 02

Issue 6 Revision 1, January 2012

A320 Family

[ 02-17]

Figure 02-1 - ETOPS - area of operation

One engine failure flight path (condition of ETOPS requirement) (Non ETOPS twins) Typical single engine speed

60 minute rule

Typical single engine speed

180 minute rule

Typical single engine speed

120 minute rule

02 Certification and external livery

A320 Family

Issue 6 Revision 1, January 2012

Figure 02-2 - ETOPS 120/180 min options (A318)

Certified = SCG item

(no lead-time constraint)

Not certified

(lead-time constraint)

EASA/JAA

FAA

EASA/JAA

FAA

A318 - ETOPS 120 min

A318 - ETOPS 180 min

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

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Issue 6 Revision 1, January 2012

A320 Family

[ 02-19]

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

Certified = SCG item

(no lead-time constraint)

EASA/JAA

FAA

EASA/JAA

FAA

A319 - ETOPS 120 min

A319 - ETOPS 180 min

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

02 Certification and external livery

A320 Family

Issue 6 Revision 1, January 2012

Figure 02-4 - ETOPS 120/180 min options (A320)

Certified = SCG item

(no lead-time constraint)

N/A

N/A

N/A = Not Applicable

EASA/JAA

FAA

EASA/JAA

FAA

A320 - ETOPS 120 min

A320 - ETOPS 180 min

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

CN02.10.320/05

CFM56-5B6/3

CN02.10.220/07

CN02.10.320/07

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

N/A

N/A

N/A

N/A

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Issue 6 Revision 1, January 2012

A320 Family

[ 02-21]

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

Certified = SCG item

(no lead-time constraint)

EASA/JAA

FAA

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

A321 - ETOPS 120 min

A321 - ETOPS 180 min

02 Certification and external livery

A320 Family

Issue 6 Revision 1, January 2012

02.12.122 - Compliance status with EU-OPS 1

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, sub-parts K, L & S (cabin emergency equipment, Emergen-cy 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 op-erational authority the compliance of their aircraft with EU-OPS 1. AIRBUS is providing help by raising a factu-al compliance review and cannot be responsible for the non-compliance which may be identified.

EPAC selection mode Individual

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Issue 6 Revision 1, January 2012

A320 Family

[ 02-23]

Table 02-6 - Technical solutions description

TDU Title (Remarks) Appl. Weight (kg)

MWE/OWE/APL Equipment reference Equipment supplier Equipment PN QTY STS

01 Compliance status with EU-OPS 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 require-ments 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 Page 31

02 Certification and external livery

A320 Family

Issue 6 Revision 1, January 2012

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

To certify passenger seats and cabin attendant seats in accordance with CS25/FAR 25.562 (Head Injury Crite-ria - HIC).

Basic aircraft None.

Description

The passenger seat and cabin attendant seat configu-ration 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 reg-ulation at delivery remains subject to the on-time suc-cessful seat supplier results of passenger seat dynamic tests.

EPAC selection mode Individual

Certification and external livery 02

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A320 Family

[ 02-25]

Table 02-7 - Technical solutions description

TDU Title (Remarks) Appl. Weight (kg)

MWE/OWE/APL Equipment reference Equipment supplier Equipment PN QTY STS

03 Compliance with CS25/FAR 25.562 (Head Injury Criteria - HIC) 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 Page 33

02 Certification and external livery

A320 Family

Issue 6 Revision 1, January 2012

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.

Basic aircraft for A318-100 and A319-100 and A320-200

None.

Description for A318-100 and A319-100 and A320-200

The modification consists in introducing the relevant limitations and performance through the AFM supple-ment 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

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

Individual

Certification and external livery 02

Issue 6 Revision 1, January 2012

A320 Family

[ 02-27]

Table 02-8 - Technical solutions description

TDU Title (Remarks) Appl. Weight (kg)

MWE/OWE/APL Equipment reference Equipment supplier Equipment PN QTY STS

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 Page 35

02 Certification and external livery

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Issue 6 Revision 1, January 2012

02.40.101 - External livery

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, ver-tical stabilizer), and light grey (wings, Trimmable Hori-zontal 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:

• 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 se-lection, ...), can affect the paint production cycle. Con-sequently, 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

Certification and external livery 02

Issue 6 Revision 1, January 2012

A320 Family

[ 02-29]

Figure 02-6 - External livery (A319)

anti-skid paint

Grey M9004 (upper wing coating) Grey M9001 (polyurethane top coat) A319 shown

Principles valid for all A320 Family versions

White M8002 Metallic unpainted

IAE engine nacelle

CFM engine nacelle

THS leading edge unpainted

Slat leading edge unpainted

Apron fairing

THS travel area

02 Certification and external livery

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Issue 6 Revision 1, January 2012

Table 02-9 - Technical solutions description

TDU Title (Remarks) Appl. Weight (kg)

MWE/OWE/APL Equipment reference Equipment supplier Equipment PN QTY STS

01 External livery A318-100 A319-100 A320-200 A321-200 TBD/TBD/TBD TBD/TBD/TBD TBD/TBD/TBD TBD/TBD/TBD

External livery TBD TBD SFE

Issue 6 Revision 1, January 2012

A320 Family

General aircraft design criteria 03

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)