A320 System Configuration Guide

Authorized by BSMC

System Configuration GuideA320 FamilyIssue 6, Revision 1January 2012Document in accordance with the following Standard Specifications:

A318-100 P 000 01000 issue 04A319-100 J 000 01000 issue 07A320-200 D 000 02000 issue 08A321-200 E 000 02000 issue 05

CC1200001

A320 Family

Intentionally left blank

Issue 6 Revision 1, January 2012

[ REF-2]

Is

A320 Family Table of contents

T ATAInCGPAACEEFFHIcInLLNO

38ms 46nit (APU) 49

51 52 53 55 56 57 72

ontrol 73 79

ATAitle Titletroduction 00ertification and external livery 02eneral aircraft design criteria 03lacards and markings 11ir conditioning 21uto flight 22ommunications 23lectrical power 24quipment/furnishings 25ire protection 26uel 28ydraulic power 29e and rain protection 30

Water/wasteInformation systeAuxiliary Power UStructuresDoorsFuselageStabilizersWindowsWingsEnginesEngine fuel and cOilsue 6 Page TOC-1

dicandighavixyg Revision 1, January 2012

ating/recording systems 31ing gear 32ts 33gation 34en 35

Page TOC-2Issue 6 Revision 1, January 2012

Table of Contents


A320 FamilyTable of contents

Page DTOC-1Issue

Detailed table of contentsTIT Page ATA ref

A320 Family

In 1 [00]00 2 [00-2]

Ce 9 [02]02 10 [02-2]02 12 [02-4]02 16 [02-8]02 20 [02-12]02 22 [02-14]02 24 [02-16]02 30 [02-22]02 32 [02-24]02 / PFC 34 [02-26]

02 36 [02-28]

Ge 39 [03]03 40 [03-2]03 44 [03-6] 6 Revision 1, January 2012

LE

troduction .00.200 - Introduction

rtification and external livery .10.104 - Certification of dynamically tested passenger seats .10.111 - Compliance with FAA type certification requirements .10.112 - Partial compliance with FAA type certification requirements .10.120 - 15 knots tailwind certification .10.123 - Operation on runways with reduced width .10.190 - ETOPS 120/180 min .12.122 - Compliance status with EU-OPS 1 .12.123 - Compliance with CS25/FAR 25.562 (Head Injury Criteria - HIC) .12.130 - EASA certification of Take Off/Landing operation on wet grooved

runways .40.101 - External livery

neral aircraft design criteria .20.300 - Design weights (A318) .20.400 - Design weights (A319)

Page DTOC-2Issue

DDetailed table of contents A320 FamilyTIT Page ATA ref03 48 [03-10]03 52 [03-14]

Pl 57 [11]11 58 [11-2]11 ings 60 [11-4]11 62 [11-6]11 64 [11-8]11 or warning 68 [11-12]

11 72 [11-16]11 76 [11-20]11 holds 78 [11-22]11 82 [11-26]11 86 [11-30]11 90 [11-34]

Ai 93 [21]21 94 [21-2]21 98 [21-6]21 102 [21-10] 6 Revision 1, January 2012

etailed table of contentsLE

.20.500 - Design weights (A320)

.20.600 - Design weights (A321)

acards and markings .00.124 - Installation of leasing identification plates .20.100 - Second language for door operation external placards and mark.20.110 - Second language for selected external placards and markings .20.119 - Nose Landing Gear (NLG) permanent steering markers .20.135 - Second language for residual cabin & cargo pressure exterior do

placards .21.101 - Emergency cut-out markings .22.100 - Landing gear placards .30.100 - Installation of additional access placards in forward and aft cargo.30.121 - Second language for cargo compartment placards .30.136 - US and metric units for cargo compartment height placards .33.101 - Placard for flight crew oxygen system

r conditioning .20.108 - Cabin air recirculation filter cartridges equipment selection .22.100 - Installation of electrical heaters for foot air outlets in the cockpit .26.110 - Avionics ventilation fan automatic speed reduction

Page DTOC-3Issue

A320 Family Detailed table of contents

TIT Page ATA ref21 106 [21-14]21 110 [21-18]21 114 [21-22]21 118 [21-26]21 120 [21-28]21 124 [21-32]21 128 [21-36]

Au 131 [22]22 132 [22-2]22 134 [22-4]22 138 [22-8]22 ) 142 [22-12]

Co 145 [23]23 cator 148 [23-4]

23 152 [23-8]23 156 [23-12]23 160 [23-16]23 (SFE) 162 [23-18] 6 Revision 1, January 2012

LE .27.108 - Avionics ventilation air filter alternate equipment .28.201 - Installation of ventilation system for forward cargo hold .28.210 - Installation of ventilation system for complete aft cargo hold .41.100 - Installation of front air outlets at flight crew foot level .43.201 - Installation of heating system for forward cargo hold .43.204 - Installation of heating system for complete aft cargo hold .70.109 - Installation of ozone catalytic converters

to flight .00.104 - Automatic landing capability .70.100 - Flight Management (FM) kits alternate equipment .81.143 - Inhibition of the expedite pushbutton .82.103 - Installation of third Multipurpose Control and Display Unit (MCDU

mmunications .00.132 - Installation (based on basic common provision) of Emergency Lo

Transmitter (ELT) .11.102 - Full provision for single HF system .11.111 - Full provision for dual HF system .11.116 - Installation of single HF system (SFE) .11.131 - Installation of single HF system and full provision for second one

Page DTOC-4Issue

DDetailed table of contents A320 FamilyTIT Page ATA ref23 166 [23-22]23 170 [23-26]23 172 [23-28]23 174 [23-30]23 178 [23-34]23 180 [23-36]23 184 [23-40]23 186 [23-42]23 188 [23-44]23 192 [23-48]23 el 196 [23-52]23 200 [23-56]23 204 [23-60]23 206 [23-62]23 210 [23-66]23 214 [23-70]23 218 [23-74]23 nt 220 [23-76]23 ply for CVR 224 [23-80]23 226 [23-82]23 Project) 228 [23-84] 6 Revision 1, January 2012


.11.155 - Installation of dual HF system (SFE)

.11.167 - Additional wiring for HF Data Link (HFDL) function

.11.169 - Activation of HF Data Link (HFDL) function

.12.130 - VHF Data Radio (VDR) alternate equipment

.13.100 - Installation of alternate Radio Management Panel (RMP)

.13.101 - Installation of third Radio Management Panel (RMP)

.13.105 - Activation of RMP std 4 frequency load function

.28.170 - Installation of AERO H+/SBB SATCOM cockpit voice interface

.28.210 - Installation of SATCOM AERO H+ SRT 2100B system

.28.211 - Installation of SwiftBroadband (SBB) SATCOM system

.50.110 - Installation of additional Audio Control Panel (ACP) and jack pan

.50.135 - Installation of headset for fourth occupant

.50.138 - Cockpit hand microphone alternate equipment

.51.103 - Installation of active noise canceling boomsets (SFE)

.51.136 - Boomsets alternate equipment

.51.139 - Boomsets alternate equipment with two jack plugs

.70.110 - Installation of a video monitoring system

.71.103 - Solid State Cockpit Voice Recorder (SSCVR) alternate equipme

.71.110 - Recorder Independent Power Supply (RIPS) - 28VDC power sup

.71.120 - System provision for CVR capable of data link recording

.73.200 - Installation of cockpit and cabin alert switches (Aircraft Security

Page DTOC-5Issue


TIT Page ATA ref

El 231 [24]24 ith batteries 232 [24-2]

Eq 235 [25]25 238 [25-4]25 240 [25-6]25 244 [25-10]25 e door area 248 [25-14]25 252 [25-18]25 254 [25-20]25 lds 258 [25-24]25 ard and aft 262 [25-28]

25 d cargo hold 268 [25-34]

25 d cargo hold 272 [25-38]

25 old - sliding 274 [25-40] 6 Revision 1, January 2012

LE

ectrical power .55.101 - Passenger Address (PA) power supply in emergency condition w

OFF

uipment/furnishings .10.108 - Installation of paper holder on the glareshield .11.102 - Pilot seats alternate covers - sheepskin .11.208 - Installation of fourth occupant seat in cockpit .27.100 - Installation of heated floor panels for fwd passenger/crew/servic.27.101 - Installation of On/off switch for heated floor panels .50.137 - Rubber seal profile for cargo compartment floor panels .50.510 - Basic full bulk configuration selection in forward and aft cargo ho.50.520 - Installation of reinforced floor panels for heavy bulk usage in forw

cargo holds .52.190 - System provision for mechanized bulk loading systems in forwar

(A320) .52.191 - System provision for mechanized bulk loading systems in forwar

(A321) .52.202 - Installation of mechanized bulk loading system in forward cargo h

carpet system

Page DTOC-6Issue

DDetailed table of contents A320 FamilyTIT Page ATA ref25 go hold 278 [25-44]

25 go hold 282 [25-48]

25 - sliding 284 [25-50]

25 ward and aft 288 [25-54]

25 argo holds 294 [25-60]

25 298 [25-64]25 ty in fwd and 300 [25-66]

25 Ds (A319) 304 [25-70]25 , door area 308 [25-74]

25 312 [25-78]25 316 [25-82]

Fi 319 [26]26 320 [26-2]26 324 [26-6] 6 Revision 1, January 2012


.52.204 - System provision for mechanized bulk loading systems in aft car(A319/A320)

.52.205 - System provision for mechanized bulk loading systems in aft car(A321)

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

.52.304 - Installation of semi-automatic Cargo Loading System (CLS) in forcargo holds (A320/A321)

.52.310 - Fixed provision for occasional bulk capability in forward and aft c(A320/A321)

.52.315 - Full electrical provision for semi-automatic CLS

.52.404 - Installation of Cargo Loading System (CLS) with full bulk capabiliaft cargo holds

.52.407 - Bulk loading capability in aft cargo hold door area behind two UL

.52.410 - Full provision for installation of special container in aft cargo hold(A319)

.52.500 - Installation of continuous side guides in forward cargo hold

.52.511 - Installation of continuous side guides in aft cargo hold

re protection .20.103 - Auxiliary Power Unit (APU) fire extinguisher alternate equipment.21.104 - Engine fire extinguishers alternate equipment

Page DTOC-7Issue


TIT Page ATA ref26 328 [26-10]26 min 330 [26-12]26 min 334 [26-16]

Fu 337 [28]28 ) in aft cargo 338 [28-2]

28 ACTs) in aft 342 [28-6]

28 346 [28-10]28 ld 352 [28-16]28 356 [28-20]28 360 [28-24]28 364 [28-28]

Hy 367 [29]29 368 [29-2]29 372 [29-6] 6 Revision 1, January 2012

LE .23.103 - Cargo holds fire extinguisher alternate equipment .23.111 - Cargo holds fire extinguishers extended duration for ETOPS 120.23.112 - Cargo holds fire extinguishers extended duration for ETOPS 180

el .11.133 - Full provision for installation of one Additional Center Tank (ACT

hold .11.140 - Full provision for installation of two/one Additional Center Tanks (

cargo hold .11.225 - Installation of one Additional Center Tank (ACT) in aft cargo hold.11.235 - Installation of two Additional Center Tanks (ACTs) in aft cargo ho.25.107 - Installation of additional refuel/defuel coupling in LH wing .25.110 - Installation of fuel quantity preselector in cockpit .25.130 - Relocation of refuel/defuel control panel

draulic power .10.110 - Hydraulic Engine Driven Pumps (EDPs) alternate equipment .21.104 - Electropumps alternate equipment

Page DTOC-8Issue

DDetailed table of contents A320 FamilyTIT Page ATA refIce 375 [30]30 376 [30-2]30 380 [30-6]30 382 [30-8]

In 387 [31]31 388 [31-2]31 392 [31-6]31 quipment 396 [31-10]31 402 [31-16]31 406 [31-20]31 410 [31-24]31 412 [31-26]31 416 [31-30]31 420 [31-34]31 isplay (ND) 422 [31-36]

La 425 [32]32 426 [32-2]32 nt 430 [32-6] 6 Revision 1, January 2012

etailed table of contentsLE and rain protection

.41.102 - Installation of intermittent function of windshield wipers

.70.108 - Extended freezing protection

.81.105 - Installation of dual advisory ice detection system

dicating/recording systems .00.107 - US units for indicators and labels .14.103 - Overhead panel toggle switches re-orientation .33.051 - Flight Data Interface and Management Unit (FDIMU) alternate e.33.132 - Installation of Quick Access Recorder (QAR/WGL-QAR) .33.200 - Solid State Flight Data Recorder (SSFDR) alternate equipment .33.210 - Digital Flight Data Recorder System (DFDRS) capabilities .36.161 - Installation of Digital AIDS Recorder (DAR/WGL-DAR) (BFE) .60.114 - Indication of metric altitude on Primary Flight Display (PFD) .60.120 - Installation of Electronic Instrument System (EIS2) .65.100 - Activation of Minimum Off Route Altitude (MORA) on Navigation D

nding gear .40.113 - Wheels and brakes alternate equipment .41.111 - Main Landing Gear (MLG) tires selection and alternate equipme

Page DTOC-9Issue


TIT Page ATA ref32 434 [32-10]32 438 [32-14]32 eel 442 [32-18]

Li 445 [33]33 lighting) 446 [33-2]33 448 [33-4]33 450 [33-6]

Na 453 [34]34 456 [34-4]34 460 [34-8]34 464 [34-12]34 468 [34-16]34 472 [34-20]34 476 [34-24]34 em 478 [34-26]34 480 [34-28]34 484 [34-32]34 488 [34-36] 6 Revision 1, January 2012

LE .41.120 - Nose Landing Gear (NLG) tires selection .48.200 - Installation of universal brake cooling fans .49.109 - Installation of Tire Pressure Indicating System (TPIS) on twin wh

ghts .12.109 - Changes in cockpit illumination (excluding instrument and panel.43.000 - Runway turnoff lights .46.000 - Taxi and take-off lights

vigation .00.108 - QNH/QFE BARO setting .13.105 - Installation of aspirated Total Air Temperature (TAT) probes .13.106 - Pitot probes alternate equipment .15.101 - Angle Of Attack (AOA) sensors alternate equipment .20.203 - Integrated Standby Instrument System (ISIS) optional functions .35.109 - System provision for Head Up Display (HUD) system installation.35.110 - Installation (based on provision) of Head Up Display (HUD) syst.41.302 - Full single Weather Radar (WXR) system alternate equipment .41.310 - Installation of dual Weather Radar (WXR) System .42.101 - Radio altimeters alternate equipment

Page DTOC-10Issue

DDetailed table of contents A320 FamilyTIT Page ATA ref34 492 [34-40]34 quipment 496 [34-44]

34 500 [34-48]34 502 [34-50]34 504 [34-52]34 ) 506 [34-54]34 508 [34-56]34 ate 510 [34-58]

34 e warnings 512 [34-60]34 al functions 514 [34-62]34 uipment 516 [34-64]34 520 [34-68]34 tion 522 [34-70]34 524 [34-72]34 m 528 [34-76]34 ent 532 [34-80]34 536 [34-84]34 quipment 540 [34-88]34 544 [34-92]34 548 [34-96] 6 Revision 1, January 2012


.42.117 - Radio altitude automatic call-outs

.43.203 - Traffic Alert and Collision Avoidance System (TCAS) alternate e(SFE)

.43.250 - Installation of T2CAS

.43.260 - T2CAS - Activation of alternate warnings

.43.270 - Wiring provision for T3CAS

.43.290 - Wiring provision for Aircraft Traffic Situation Awareness (ATSAW

.43.295 - Activation of ATSAW function

.48.124 - Enhanced Ground Proximity Warning System (EGPWS) - alternequipment

.48.127 - Enhanced Ground Proximity Warning System (EGPWS) alternat

.48.132 - Enhanced Ground Proximity Warning System (EGPWS) - option

.51.101 - Distance Measuring Equipment (DME) interrogators alternate eq

.52.117 - Automatic Dependent Surveillance - Broadcast (ADS-B OUT)

.52.133 - Compliance with European enhanced surveillance (EHS) regula

.52.140 - Air Traffic Control (ATC) control panel alternate equipment

.53.109 - Full provision for second Automatic Direction Finder (ADF) syste

.53.111 - Single Automatic Direction Finder (ADF) system alternate equipm

.53.119 - Installation of dual Automatic Direction Finder (ADF) system

.55.102 - VHF Omnidirectional Range (VOR)/Marker receivers alternate e

.58.313 - Multi Mode Receiver (MMR) alternate equipment

.58.316 - Activation of GLS function

Page DTOC-11Issue


TIT Page ATA ref34 550 [34-98]34 MR 552 [34-100]

Ox 555 [35]35 inder 556 [35-2]35 560 [35-6]35 564 [35-10]35 566 [35-12]35 570 [35-16]

W 573 [38]38 574 [38-2]38 zation 576 [38-4]

In 579 [46]46 tion (AOC) 580 [46-2]

46 584 [46-6]46 586 [46-8] 6 Revision 1, January 2012

LE .58.317 - Activation of FLS function .58.340 - Installation of MLS function for cat IIIb operation hosted by the M

ygen .11.102 - Installation of in-situ replenishment facility for cockpit oxygen cyl.11.201 - Cockpit oxygen cylinder alternate equipment .20.010 - Installation of four oxygen masks per box .20.113 - Extended supply duration for passenger chemical oxygen system.20.114 - Extended supply duration for passenger gaseous oxygen system

ater/waste .10.104 - Installation of water conditioner in potable water system .41.101 - Installation of auxiliary compressor in the potable water pressuri

system

formation systems .21.102 - Installation of AIRBUS standard Airline Operational Communica

software for ATSU .21.105 - Activation of ARINC 623 ATS applications in the ATSU .21.111 - Activation of VHF Data Link (VDL) Mode 2 function

Page DTOC-12Issue

DDetailed table of contents A320 FamilyTIT Page ATA ref46 588 [46-10]46 590 [46-12]

Au 593 [49]49 594 [49-2]

St 597 [51]51 598 [51-2]51 604 [51-8]51 (3 coats) 608 [51-12]

Do 611 [52]52 612 [52-2]52 itions) 616 [52-6]52 618 [52-8]

Fu 621 [53]53 622 [53-2]53 626 [53-6] 6 Revision 1, January 2012


.21.140 - Installation of Future Air Navigation System (FANS) A+

.21.142 - Installation of Future Air Navigation System (FANS) B+

xiliary Power Unit (APU) .00.105 - Auxiliary Power Unit (APU) alternate equipment

ructures .00.115 - Fuselage and wings extended corrosion prevention .22.250 - External livery decorative adhesive film .22.710 - Alternate paint system (CF primer/strippable) on standard areas

ors .22.200 - Installation of additional emergency exits (A319) .51.100 - Installation of cockpit door release back-up system (MMEL cond.51.106 - Installation of modified door lock mechanism

selage .30.050 - Belly fairing panels - extrusion strips .35.100 - Ram air inlet leading edge protection

Page DTOC-13Issue


TIT Page ATA refSt 629 [55]55 e 630 [55-2]

W 633 [56]56 634 [56-2]

W 639 [57]57 640 [57-2]57 642 [57-4]

En 645 [72]72 646 [72-2]72 650 [72-6]72 654 [72-10]72 658 [72-14]

En 661 [73]73 662 [73-2] 6 Revision 1, January 2012

LE abilizers .30.101 - Installation of erosion protection on vertical stabilizer leading edg

indows .10.102 - Cockpit windows alternate equipment

ings .40.100 - Leading edge and leading edge devices .49.101 - Wing leading edge access panels - miscellaneous changes

gines .00.118 - Engines selection and alternate equipment (A318) .00.119 - Engines selection and alternate equipment (A319) .00.120 - Engines selection and alternate equipment (A320) .00.121 - Engines selection and alternate equipment (A321)

gine fuel and control .21.100 - Installation of additional sensors for engine health monitoring

Page DTOC-14Issue

DDetailed table of contents A320 FamilyTIT Page ATA refOi 665 [79]79 rnate 666 [79-2]

79 port on 670 [79-6] 6 Revision 1, January 2012

etailed table of contentsLE l .00.101 - Engine, engine accessories and Auxiliary Power Unit (APU) alte

lubricating oil .40.101 - Installation of Integrated Drive Generator (IDG) oil level viewing

engine RH fan cowl


[ 00-1]

A320 Family Introduction 00

Reference Title00.00.200 Introduction

Page 1

00 Introduction A320 Family

Is [ 00-2]

0

D1TmeTaWtiotoseso

2TsiaSM

r use n Guide encompasses a wide range of me circumstances, it is possible that a ation of options cannot be achieved. onfiguration Guide must be used in he expertise and assistance of Airbus.

n Guide shows items for which a pre- solution has been developed and for mes have been studied. Provided the ined in the customer definition mile-spected, these items can be installed the delivery lead time.

ire longer lead-time than normal, and er decisions prior to Contractual Defi-F) deadlines. These items are high-logue by a special remark: "Subject to ints". For these items, specific deci-all be identified in customer definition

Page 2sue 6 Revisio

0.00.20

escriptio) General his Configodels and

d on the fihis Configs "Airbus hen usedn and themization lection oflutions.

) Basic airhis Configc aircraft nd perfortandard Sanufacturn 1, January 2012 00.00.200

0 - Introduction

n

uration Guide is dedicated to the aircraft associated Standard Specifications indicat-rst page. uration Guide offers various options defined preferred solutions" to the customer. in conjunction with the Standard Specifica- other Configuration Guides a complete cus-of the Aircraft is possible through the

the different items and associated technical

craft uration Guide starts from the theoretical ba-as shown in the reference layout for weight mance calculations of the corresponding pecification and incorporating any relevant er Specification Change Notice (MSCN).

3) Instructions foThis Configuratiooptions and in soparticular combinTherefore, the Cconjunction with t

4) Lead-times This Configuratiodefined technicalwhich the lead tischedule as defstone chart is rewithout affecting

Caution: Some items requtherefore customnition Freeze (CDlighted in this catalead-time constrasion deadlines shmilestones.

Introduction 00A320 Family

Issue 6 Rev

00.00.2

[ 00-3]

5) CataloOn each Air Tr

sectio date o option

For each object basic descr

someby dra

EPACitem isChangproce

technilutionssociat

Note: Fothe basicthe TDU

, the arrangement of the items follows sification. The items are sorted by nu-eference numbers within a given ATA

ions bear a 7-digit reference number: howing first the ATA (e.g. 26) and sub-ssification, followed by a running num-

olution (TDU) is referenced by a two-. 02). d in the Table Of Content (TOC) and beginning of each chapter.

: ection", "... alternate equipment", "pro-stallation of...". . equipment selection" relate to items rd specification offers a choice of basic uch items the customer is requested to f the choices on offer, unless alternate uired.

Page 3ision 1, January 2012 00.00.200

00 - Introduction (Continued)gue presentation

page, the following information is provided: ansport Association of America (ATA) title and n number f the issue of the catalogue reference

item, the description is structured in subparts: ive of the item aircraft definition related to the item iption of the item in terms of modifications, in cases commented by a note and/or illustrated wings selection mode for the item shows whether the selectable by individual or global Request For e (RFC)/Specification Change Notice (SCN)

dure cal solutions: a table describes all technical so- (called TDU: Technical Description Unit) as-ed to the item.

r comparison purposes, some tables also show aircraft equipment, labelled Std (Standard) in

column.

As far as possiblethe ATA 100 clasmerical order of rchapter.

The different opt(e.g: 26.24.600) sATA (e.g. 24) claber (e.g. 600).

Each technical sdigit number (e.gAll items are listeduplicated at the

Definition of titles"... equipment selvisions for...", "Ina) items titled "..where the standaequipment. For sselect from one oequipment is req


Issue 6 Rev [ 00-4]

00.00.2

b) itemswhere ththat defin

c) items the custosions to

d) items customeof the sta

SelectionSpecific item andvisible inafter).

Such solment or items copabilities

ful product qualification and proof of Airbus performance requirements and tions.

s are as follows: f RFC/SCN on Manufacturer's Weight

of RFC/SCN on Operator's Weight

RFC/SCN on Available Payload d are for one off unless otherwise stat-

cts have yet to be determined for RFC/

ct is small and will be taken as zero for CN. native items are delta weights to the andard Specification unless otherwise

selection mode is Global the weight of part of the relevant Global RFC/SCN. n in the catalogue for such items are

.


00 - Introduction (Continued) titled "...alternate equipment" relate to items e customer can choose equipment alternate to ed in the Standard Specification.

titled "Provisions for..." relate to items where mer can add structural and/or system provi-

prepare the a/c for later installation.

titled "Installation of..." relate to items where the r can add functions/equipment/systems on top ndard definition.

conditions selection conditions may be associated to an are identified by an icon and a special remark the TDU table (see example in the figure here-

utions may be at the initial phases of develop-first application on Airbus aircraft. For these

mmitment to quality, industrial and technical ca-, on time delivery and customer support de-

pend on successcompliance with customer expecta

Weights Weight definition MWE: Effect o

Empty OWE: Effect

Empty APL: Effect of All weights quoteed. TBD: Weight effeSCN. Negl: Weight effeindividual RFC/SWeights for altercorresponding Ststated. Where the EPACthe item shall be Any weights showfor guidance only

Introduction 00A320 Family

Issue 6 Rev

00.00.2

[ 00-5]

For somon custoweights and will b

6) DefiniThe custforms. Then, a SRFC, anThese Rcustomeed.

Global RThe globwith conlead-timewhich gr

IndividuaThe seleRFC/SC

r request ot mentioned in this Guide, or corre-dified item, require specific customer cial feasibility study has to be initiated. ential for customers to review the Con-s soon as possible to identify which of s are covered and which are not. customers, with the assistance of Air-e the necessary specific requests re-

ich are not covered by this Guide. uests shall necessarily have an impact times and resources and shall conse-onstraints and decisions that shall be d faith between the customer and Air-y forewarns that this may lead to the rtain requests.

sibility equipment by any entity other than the luding but not limited to the Buyer) for are made or which are post-delivery of e made under the sole and full respon-er.


00 - Introduction (Continued)e individual RFC/SCN the weight is dependent mer requirements, e.g. certain BFE items. The for such items shall be taken for guidance only e identified as such.

tion handling omer's selection is recorded by Airbus in RFC

CN is issued by Airbus, based on a customer's d is submitted for customer's signature. FCs/SCNs are issued before CDF directly on r request except if their content is to be adapt-

FC/SCN al RFC consists of a checklist containing items siderable interdependence and equivalent s. The global RFC leads to the global SCN

oups all selected items.

l RFC/SCN ction of individual items not covered by global N is achieved via individual RFCs/SCNs.

Specific customeItems that are nsponding to a morequests as a speIt is therefore essfiguration Guide atheir requirementThis will allow thebus, to raise in timlated to items whSuch specific reqin terms of lead quently lead to cdiscussed in goobus. Airbus herebunfeasibility of ce

7) Buyer's responAll installation of Manufacturer (incwhich provisions the aircraft shall bsibility of the Buy


Issue 6 Rev [ 00-6]

00.00.2

The Buyufacturerrectly orequipmetive or no


00 - Introduction (Continued)er shall hold harmless and indemnify the Man- against any claims or/and damages related di- indirectly to an incorrect installation of an nt or to such equipment itself, whether defec-t.

Introduction 00

Issue 6 Revision 1, January 2012 00.00.200

A320 Family

[ 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 system25.52.304 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 CLS25.52.404 Installation of Cargo Loading System (CLS) with full bulk capability in fwd and aft cargo

holds25.52.407 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 hold25.52.511 Installation of continuous side guides in aft cargo hold

Reference Title

25 Equipment/furnishings A320 Family25.52.404 - Installation of Cargo Loading System (CLS) with full bulk capability in

fwd and aft cargo holdsObjective for A319-100 and A320-200 and A321-200To 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 A321-200Full 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 A321-200The 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 cataloguepage numberOption reference

Detailed description pageChapter cover pagewith a list of available items

Option reference and title

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

.

Page 7



[ 00-8]

Figure 00-2 - Example of technical solutions description table

Table 25-21 - Technical solutions description

TDU Title (Remarks) Appl. Weight (kg)MWE/OWE/APL

Equipmentreference

Equipmentsupplier

EquipmentPN

QTY STS

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

A320-200A321-200

122.0/122.0/-122.0102.0/102.0/-102.0

02 Semi-automatic CLS in fwdand 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 thisoption are 9 months.

A320-200

03 Semi-automatic CLS in fwdand 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 fwdand 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 thisoption are 8 months.

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

153.0/153.0/-153.0

133.0/133.0/-133.0

177.0/177.0/-177.0

Title of the technicalsolution and optionalremarks

Equipment information:Technical solution

Applicableseries

identifier (TDU)Weights informationper series

reference vendor PN (part numbers) quantity status (BFE or SFE)

MWE: Manufacturers Weight EmptyOWE: Operational Weight EmptyAPL: Allowable Payload Change

Selectioncondition

Selectionconditionremark

Page 8


[ 02-1]

A320 Family Certification and external livery 02

Reference Title02.10.104 Certification of dynamically tested passenger seats02.10.111 Compliance with FAA type certification requirements02.10.112 Partial compliance with FAA type certification requirements02.10.120 15 knots tailwind certification02.10.123 Operation on runways with reduced width02.10.190 ETOPS 120/180 min02.12.122 Compliance status with EU-OPS 102.12.123 Compliance with CS25/FAR 25.562 (Head Injury Criteria - HIC)02.12.130 EASA certification of Take Off/Landing operation on wet grooved / PFC runways02.40.101 External livery

Page 9

02 Certification and external livery A320 Family

Is [ 02-2]

0 r seats

OTfrte

B2APfrAPfrte

D2Pfrte

00 and A320-200 and A321-200ynamically tested passenger seats is A certification on A319 and A321, but luded in the following option: - Compliance with FAA type certifica-.

mode

Page 10sue 6 Revisio

2.10.10

bjective fo certify ame specsted pass

asic aircr00319/A320assenger ame spec318assenger ame specsted pass

escriptio00assenger ame specsted passn 1, January 2012 02.10.104

4 - Certification of dynamically tested passenge

or A319-100 and A320-200 and A321-200passenger seats in accordance with seat ification AI 2521M1F100000 for dynamically enger seats.

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

/A321seats are certified in accordance with seat ification AI 2520M1F000100.

seats are certified in accordance with seat ification AI 2521M1F000500 for dynamically enger seats.

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

seats are certified in accordance with seat ification AI 2521M1F100000 for dynamically enger seats.

Note for A319-1Certification of dmandatory for FAis already incCN02.10.111/01 tion requirements

EPAC selection Individual

Certification and external livery 02


A320 Family

[ 02-3]

Table 02-1 - Technical solutions descriptionTDU Title (Remarks) Appl. Weight (kg)

MWE/OWE/APLEquipmentreference

Equipmentsupplier

EquipmentPN

QTY STS

05 Certification of dynamically tested passenger seats B/C

A319-100A320-200A321-200

0.0/0.0/0.00.0/0.0/0.00.0/0.0/0.0

06 Certification of dynamically tested passenger seats Y/C

A319-100A320-200A321-200

0.0/0.0/0.00.0/0.0/0.00.0/0.0/0.0

Page 11


Is [ 02-4]

0 irements

OTty

BTwfo

DTpcrA

A

modified emergency exit inscription

ynamically tested passenger seats as specification 2520 M1F 0005 00 (or assageways to emergency exits.

zone converters modified emergency exit inscription

aximum 179 passenger seatsassageways to emergency exits.

zone converters ynamically tested passenger seats as specification 2520 M1F 0005 00 (or assageways to emergency exits.

a/c the installation of variable geome-junction with photoluminescent floor- is prohibited.


2.10.11

bjectiveo install alpe certific

asic aircrhe aircraftith JAR-2r US impo

escriptiohe followinliance withaft type:318-100installatiinstallatiand marinstallatiper seatequivaleinstallatiinstallati

319-100installatin 1, January 2012 02.10.111

1 - Compliance with FAA type certification requ

l modifications to be in compliance with FAA ation requirements.

aft is designed and constructed in accordance 5 airworthiness requirements, and FAR-25 rtation (see type certificate data sheet).

ng changes shall be carried-out to be in com- the FAA Type Design of the respective Air-

on of ozone converters on of modified emergency exit inscription kingon of dynamically tested passenger seats as frame specification 2520 M1F 0005 00 (or nt)on of weight placard on each overwing hatchon of passageways to emergency exits.

on of ozone converters

installation of and marking

installation of dper seat frameequivalent)

installation of p

A320-200 installation of o installation of

and marking installation of m installation of p

A321-200 installation of o installation of d

per seat frameequivalent)

installation of p

NoteOn US registeredtry seats in conmounted EEPMS

Certification and external livery 02A320 Family

Issue 6 Rev

02.10.1 irements (Continued)

[ 02-5]

EPAC seIndividua


11 - Compliance with FAA type certification requ

lection mode l



[ 02-6]



Equipmentsupplier

EquipmentPN

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.

A319-100A320-200A321-200

20.0/20.0/-20.020.0/20.0/-20.020.0/20.0/-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

Page 14



02.10.111 [ 02-7]


Page 15


Is [ 02-8]

0 n requirements

OTqce

BTwfo

DTlyspA

A

zone converters modified emergency exit inscription

zone converters.

red a/c the installation of variable ge-in conjunction with photoluminescent EEPMS is prohibited. tion of this option, AIRBUS will, no lat-ths before aircraft Industrial Delivery, Type Design Statement to the end ding: atus to the FAA Type Design" (List of uired to meet US Type Design) irements to obtain a US Standard Air-

icate" (Customization status for US op-

f this option ensures the partial compli-ividual aircraft MSN to the FAA Type

exclusion of the cabin layout.


2.10.11

bjectiveo install aluirementsrtification

asic aircrhe aircraftith JAR-2r US impo

escriptiohe followin in complective air

318-100 installatiinstallatiand marinstallatihatch.

319-100 installatiinstallatiand marn 1, January 2012 02.10.112

2 - Partial compliance with FAA type certificatio

l modifications except cabin arrangement re-, to be partially in compliance with FAA type requirements.

aft is designed and constructed in accordance 5 airworthiness requirements, and FAR-25 rtation (see type certificate data sheet).

ng changes shall be carried-out to be partial-

iance with the FAA Type Design of the re-craft type:

on of ozone converters on of modified emergency exit inscription kingon of weight placard on each overwing

on of ozone converters on of modified emergency exit inscription king.

A320-200 installation of o installation of

and marking.

A321-200 installation of o

Note on US registe

ometry seats floor-mounted

upon the selecer than 6 monissue the FAAcustomer inclu

- "Compliance StModifications req- "Additional Requworthiness Certiferations). the selection o

ance of the indDesign, at the


Issue 6 Rev

02.10.1 n requirements (Continued)

[ 02-9]

the decate aproceBUS wvided monthmarksMSN.changModiflay of

a reviof del

EPAC seIndividua


12 - Partial compliance with FAA type certificatio

livery of a US Standard Airworthiness Certifi-t Aircraft ID is subject to a prior FAA validation ss of the Aircraft customized definition. AIR-

ill timely initiate and control this process pro-the end customer delivers, no later than 6 s before Aircraft ID, the final N-Registration allocated by the FAA to the individual aircraft Failure to meet this objective may generate es to the contractual definition (de-validation of

ications not timely approved by the FAA or De-the aircraft ID sed FAA TD Statement will be provided at time ivery.

lection mode l



[ 02-10]



Equipmentsupplier

EquipmentPN

QTY STS

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

A319-100A320-200A321-200

20.0/20.0/-20.020.0/20.0/-20.020.0/20.0/-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

Page 18



02.10.112 [ 02-11]


Page 19


Is [ 02-12]

0

OT1

BIntath1

DInuthow

To

ine characteristics justifications with ticular in terms of engine inlet.

sensitivity of the engine inlet charac-ilwind, a slower thrust application at

necessary, which in turn may require rocedure". Both effects may require ances and consequent aircraft gross for a given runway length.

mode


2.10.12

bjectiveo be able5 knots de

asic aircr the absetion of thee tailwind

0 knots.

escriptio order to

p to 15 kne aircraft

nstrationsind.

he certificff shall inc

new permanual aadditionaincludingthe comsettings,n 1, January 2012 02.10.120

0 - 15 knots tailwind certification

to take off with a tailwind component up to pending on engine type.

aftnce of specific flight tests, the usual interpre- current certification requirements is to limit operations to a maximum component of

noperate the aircraft at a tailwind component ots, severe conditions shall be conducted by manufacturer. This includes flight test dem- with 1.5 x the desired limit in terms of tail-

ation dossier for tailwind operations at take-lude: formance justifications, updating of flight nd flight crew operating manual l handling qualities demonstrations in flight, justification/modifications (if necessary) of puters settings (angle of attack protection windshear warning ...)

additional engtailwind, in par

NoteDepending on theteristics with a tatake-off may be "rolling take-off plong take-off distweight penalties




A320 Family

[ 02-13]



Equipmentsupplier

EquipmentPN

QTY STS

01 15 knots tailwind certification at take-off

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

0.0/0.0/0.00.0/0.0/0.00.0/0.0/0.00.0/0.0/0.0

Page 21


Is [ 02-14]

0

OTco

BTw

DC44tio

NFdlo

mode


2.10.12

bjectiveo authorizmprised

asic aircrhe standaays with a

escriptioertification5 meters 5 m) is acns:new permanualsnew defiuments adjustmeupdating

oteor aircraftuced runwading optn 1, January 2012 02.10.123

3 - Operation on runways with reduced width

e aircraft operation on runways with a width between 30 m and 45 m.

aftrd aircraft is certificated for operation on run- minimum width of 45 m.

n for operation on runways less than

wide (width comprised between 30 m and hieved by performing the following modifica-

formance justifications, updating of flight and TLC nition of MMEL, updating of certification doc-

nt of limitations (e.g. crosswind, autoland), of MEL and CDL.

equipped with a CLS and operating on re-ay width, it is recommended to select a bulk ion.




A320 Family

[ 02-15]



Equipmentsupplier

EquipmentPN

QTY STS

01 Aircraft Operation on runways less than 45m wideNot applicable in conjunction with PW engines

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

0.0/0.0/0.00.0/0.0/0.00.0/0.0/0.00.0/0.0/0.0

Page 23


Is [ 02-16]

0

OTdg

BB

DMeretea

NTle

n authorization can only be obtained on by the operator to its national au-e operational life of the aircraft, addi-ns may be necessary to maintain

y at the required level. They are not hange.cceptance of CN26.23.111 - Cargo ishers extended duration for ETOPS .23.112 - Cargo holds fire extinguish-ation for ETOPS 180 min.o have at least one HF installed for . Therefore, this option requires prior N23.11.116 - Installation of single HF r CN23.11.131 - Installation of single ull provision for second one (SFE), or stallation of dual HF system (SFE).es extended over water flights, under

rements, it is the responsibility of the l slide rafts (EECG item CN25.62.102) ELTs (EECG item CN25.65.305).

mode


2.10.19

bjectiveo make thiversion tiine inoper

asic aircrasic certif

escriptioodification

lectrical equired bynance an

ircraft deli

otehe precisected confapplicabengine mAPU typcargo hon 1, January 2012 02.10.190

0 - ETOPS 120/180 min

e design capable of 120/180 min maximum me from diversion airport at normal one en-ative cruise speed.

aftication is with class C cargo holds.

ns concern the supply of some systems in

mergency conditions and their reliability as the applicable ETOPS Configuration Main-d Procedure (CMP) document at the time of very.

list of modifications depends upon the se-iguration of the aircraft: le airworthiness requirement odel

e ld ventilation, heating.

ETOPS operatiothrough applicatithority. During thtional modificatiosystems reliabilitcovered by this cRequires prior aholds fire extingu120 min or CN26ers extended durIt is mandatory tETOPS 120/180acceptance of Csystem (SFE), oHF system and fCN23.11.155 - InIf the aircraft makEU-OPS 1 requioperator to instaland two portable




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

Page 25



[ 02-18]

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

Page 26



A320 Family

[ 02-19]





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

Page 27



[ 02-20]



N/A

N/A

N/A = Not Applicable



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

Page 28



A320 Family

[ 02-21]




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


Page 29


Is [ 02-22]

0

OTsu

BTpcy7

DAEp

NTeEan

EIn


2.12.12

bjectiveo provide bparts K

asic aircrhe basic aarts K, L & Locator

.0, ...).

escriptiot aircraft dU-OPS 1,rovided.

otehe operatrational auU-OPS 1.l complianon-compli

PAC seledividualn 1, January 2012 02.12.122

2 - Compliance status with EU-OPS 1

compliance status report against EU-OPS 1, & L or subparts K, L & S, at aircraft delivery.

aftircraft does not comply with EU-OPS 1, sub- S (cabin emergency equipment, Emergen-

Transmitter (ELT) installation, TCAS change

nelivery, a compliance status report against

subparts K & L or subparts K, L & S, shall be

or is responsible to show to their national op-thority the compliance of their aircraft with

AIRBUS is providing help by raising a factu-ce review and cannot be responsible for the ance which may be identified.

ction mode



A320 Family

[ 02-23]



Equipmentsupplier

EquipmentPN

QTY STS

01 Compliance status with EU-OPS 1 - subpart K plus L requirements

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

0.0/0.0/0.00.0/0.0/0.00.0/0.0/0.00.0/0.0/0.0

02 Compliance with EU-OPS 1 - subpart K, L and S require-ments

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

0.0/0.0/0.00.0/0.0/0.00.0/0.0/0.00.0/0.0/0.0

Page 31


Is [ 02-24]

0 ury Criteria - HIC)OTari

BN

DTrareInseco

NAucete

EIn


2.12.12

bjectiveo certify pccordancea - HIC).

asic aircrone.

escriptiohe passention shagulation. particulaats and mpliance

oteirbus comlation at dssful seasts.


3 - Compliance with CS25/FAR 25.562 (Head Inj

assenger seats and cabin attendant seats in with CS25/FAR 25.562 (Head Injury Crite-

aft

nger seat and cabin attendant seat configu-

ll be compliant with CS25/FAR 25.562

r, dynamic tests are required on passenger cabin attendant seats to demonstrate such for the agreed validated cabin layout.

mitment to show compliance with such reg-elivery remains subject to the on-time suc-t supplier results of passenger seat dynamic

ction mode



A320 Family

[ 02-25]



Equipmentsupplier

EquipmentPN

QTY STS

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

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

0.0/0.0/0.00.0/0.0/0.00.0/0.0/0.00.0/0.0/0.0

Page 33


Is [ 02-26]

0 ation on wet grooved / PFC

OTw(gpstTaw

B2N

D2TlimmcoTaOo

account the specific braking friction co-imum OCTOPUS version needed for Landing A/C performance is V25.

mode


2.12.13

bjective fo allow Taet runwayrooved o

avementsandard smhe groovessociated et runway

asic aircr00one.

escriptio00he modifi

itations ent to conditions o

he minimullows as aff A/C pern a smootn 1, January 2012 02.12.130

0 - EASA certification of Take Off/Landing operrunways

or A318-100 and A319-100 and A320-200ke-Off/Landing performance calculation on taking credit of specific runway pavement

r Porous Friction Course). On those specific , a higher braking friction coefficient, than on

ooth runways, can be reached. d/PFC (Porous Friction Course) runway is to a specific braking friction coefficient on .

aft for A318-100 and A319-100 and A320-

n for A318-100 and A319-100 and A320-

cation consists in introducing the relevant and performance through the AFM supple-ver Take-Off/Landing operations under wet n grooved/PFC runways.m OCTOPUS version needed is V23.1 that

n option to select the calculation of the Take formance (Accelerate Stop Distance) either h runway state or on a grooved/PFC runway

state, taking into efficient. The mincalculation of the




A320 Family

[ 02-27]



Equipmentsupplier

EquipmentPN

QTY STS

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

A318-100A319-100A320-200

0.0/0.0/0.00.0/0.0/0.00.0/0.0/0.0

02 EASA certification of Landing operation on wet grooved / PFC runways

A318-100A319-100A320-200

0.0/0.0/0.00.0/0.0/0.00.0/0.0/0.0

Page 35


Is [ 02-28]

0

OTEn

BTticzoE

DTsha

NNS

of slats lips and exhaust, parts of pylons

ilizer shield ading edge

fairings ails such as angle of attack sensors, lected antennas etc.

issued for drawing identification.

f each external livery (design, paint ading, number of colours, product se-ffect the paint production cycle. Con-external livery is investigated on an and relevant terms and conditions will the corresponding SCN (Specification

mode


2.40.10

bjectiveo deliver txternal livacelles.

asic aircrhe aircraftal stabilizntal Stab

xternal ma

escriptiohe aircrafall be pa

s defined a drawininstructioetc.) painted con instrusamples

oteote 1:ome metan 1, January 2012 02.40.101

1 - External livery

he aircraft painted in the livery of the buyer. ery means fuselage, vertical stabilizer and

aft is delivered painted in white (fuselage, ver-er), and light grey (wings, Trimmable Hori-ilizer (THS) and nacelles).rkings are in English only.

nt fuselage, vertical stabilizer and nacelles inted according to the livery of the customer by:g prepared by AIRBUS, based on decorative ns from the customer (paper, floppy disk, olour samples prepared by AIRBUS, based ctions from the customer (colour references, ).

llic areas are and remain unpainted:

leading edges engine intake scuff plates horizontal stab THS forward le forward pylon equipment det

static ports, se

Note 2:One RFC will be

Note 3:The complexity oblending and/or flection, ...), can asequently, each individual basis, be mentioned in Change Notice).




A320 Family

[ 02-29]

Figure 02-6 - External livery (A319)

anti-skid paint

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

A319 shownPrinciples valid for all A320 Family versions

White M8002Metallic unpainted

IAE engine nacelle

CFM engine nacelleTHS leading edge

unpainted

Slat leading edge unpainted

Apron fairing

THS travel area

Page 37



[ 02-30]



Equipmentsupplier

EquipmentPN

QTY STS

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

TBD/TBD/TBDTBD/TBD/TBDTBD/TBD/TBDTBD/TBD/TBD

External livery TBD TBD SFE

Page 38


[ 03-1]

A320 Family General aircraft design criteria 03

Reference Title03.20.300 Design weights (A318)03.20.400 Design weights (A319)03.20.500 Design weights (A320)03.20.600 Design weights (A321)

Page 39

03 General aircraft design criteria A320 Family

Is [ 03-2]

0

OTsiae

BTa

D

mode


3.20.30

bjective fo allow thegn weightble weightngines/air

asic aircrhe aircrafre as follo

MaximumMaximumMaximumMaximum

escriptiochangesual, Weition Manmodificachangesware to aMLW, replacemindicatinpossiblyn 1, January 2012 03.20.300

0 - Design weights (A318)or A318-100 customer to select predefined alternate de-

variants as shown in following table (select- variants associated with basic and optional craft models).

aft for A318-100t basic design weights (weight variant 000) ws:

Taxi Weight (MTW) 59.4 t Take-Off Weight (MTOW) 59 t Landing Weight (MLW) 56 t Zero Fuel Weight (MZFW) 53 t.

n for A318-100 in the aircraft manuals (Aircraft Flight Man-ght & Balance Manual, Flight Crew Opera-ual, ...)tion of the CG diagram in all performance related manuals and soft-dapt to the new maximum weights (MTOW, )ent of labels bonded to the MLG main fitting

g MTOW and tire pressure, changes of the wheels when necessary.

EPAC selectionIndividual

General aircraft design criteria 03


A320 Family

[ 03-3]

Figure 03-1 - Design weight options (A318)Weightvariant

A318

-111

CFM

56-5B

8/3

A318

-112

CFM5

6-5B9

/3

A318

-121

PW 6

122A

Design weights (t)

CN03.20.311 CN03.20.312 CN03.20.321 TDU

000MTOW 59MLW 56 Basic Basic Basic Basic 20MZFW 53

001MTOW 61.5MLW 56 Certified 01MZFW 53

002MTOW 63MLW 57.5 Certified Certified Certified Certified 02MZFW 54.5

003MTOW 64.5MLW 57.5 Certified Certified 03MZFW 54.5

004MTOW 66MLW 57.5 Certified Certified

Certified

04MZFW 54.5

005MTOW 68MLW 57.5 Certified 05MZFW 54.5

006MTOW 56MLW 56 Certified Certified 06

MZFW 53

MZFW 53

007MTOW 61MLW 56 Certified Certified 07

Certified Certified

A318

-122

PW 6

124A

CN03.20.322

08008MTOW 64MLW 56MZFW 53

Certified Certified

Certified Certified

Certified Certified

CertifiedCertified

Certified Certified

Certified Certified

Certified Certified

Certified

Certified = SCG item (no lead-time constraint)

Page 41



[ 03-4]

Figure 03-2 - Basic CG limits diagram (A318)25232119171513 27 29 31 33 35 37 4139

15 17 1911090705 13 21 23 25 27 29 31 33 35 4537 39 41 43 35

40

45

50

55

60

65

70

75

80

35

40

45

50

55

60

65

70

75

80

%RC

%RCAircraft weight (kg x 1000) Aircraft weight (kg x 1000)

42.6

MTOW 59 000 kg

MLW 56 000 kg

MZFW 53 000 kg

Flight Flight

Landing3

2

.

2

Landing

5657

Take-off

Page 42



A320 Family

[ 03-5]

Figure 03-3 - CG limits diagram with max. optional MTOW (A318)

25232119171513 27 29 31 33 35 37 4139

15 17 1911090705 13 21 23 25 27 29 31 33 35 4537 39 41 43 35

40

45

50

55

60

65

70

75

80

35

40

45

50

55

60

65

70

75

80

%RC


40.6

3

1

.

1

8

Take-off

MTOW 68 000 kg

MLW 57 500 kg

MZFW 54 500 kg

Flight

Flight

Landing

Landing

63

1

6

.

7

Take-off

1

8

.

7

63

57

3

3

.

0

3

2

.

0

56

Page 43


Is [ 03-6]

0

OTsiae

BTa

D

00ure Indication System (TPIS) is in-

computer pin programming has to be gly.

mode


3.20.40




escriptiochangesual, Weition Manmodificachangesware to aMLW, ...replacemfitting indpossiblywhen nen 1, January 2012 03.20.400




Taxi Weight (MTW) 64.4 t Take-Off Weight (MTOW) 64 t Landing Weight (MLW) 61 t Zero Fuel Weight (MZFW) 57 t.

n for A319-100 in the aircraft manuals (Aircraft Flight Man-ght & Balance Manual, Flight Crew Opera-ual, ...)tion of the CG diagram in all performance related manuals and soft-dapt to the new maximum weights (MTOW,

) ent of labels bonded to the NLG/MLG main icating MTOW and tire pressure

, changes of the brakes, wheels and tires cessary.

Note for A319-1If the Tire Pressstalled, the TPISmodified accordin




A320 Family

[ 03-7]

Figure 03-4 - Design weight options (A319)Weight variant A3

19-1

11CF

M 56

-5B5

/3

A319

-112

CFM

56-5

B6/3

A319

-115

CFM

56-5

B7/3

A319

-131

IAE

V252

2-A5

A319

-132

IAE

V252

4-A5

A319

-133

IAE

V252

7M-A

5

Design weights (t)

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

000MTOWMLWMZFW MTOWMLWMZFW MTOWMLWMZFW MTOWMLWMZFW MTOWMLWMZFW MTOWMLWMZFW MTOWMLWMZFW MTOWMLWMZFW MTOWMLWMZFW MTOWMLWMZFW MTOWMLWMZFW MTOWMLWMZFW

646157

Basic Basic Basic Basic Basic Basic 20

0017061 Certified Certified Certified Certified Certified Certified 0157

00275.562.5 Certified Certified Certified Certified Certified Certified

Certified Certified Certified Certified Certified Certified

Certified Certified Certified



0258.5

0036861 0357

00468

62.5 Certified Certified Certified 0458.5

00570

62.5 0558.5

00673.562.558.5

06

Certified Certified Certified Certified Certified Certified00775.56157

07

Certified Certified Certified Certified Certified Certified00864

62.558.5

08


62.558.5

09


11


12


Page 45



[ 03-8]

Figure 03-5 - Basic CG limits diagram (A319)

21191715 23 25 27 29 31 33 35 37 3980

75

70

65

60

55

50

45

40

35

41% RCAircraft weight (kg x 1 000) Aircraft weight (kg x 1 000)

11090705 13 15 17 19 21 23 25 %RC27 29 31 33 35 37 39 41 43 45

80

75

70

65

60

55

50

45

40

35

49.6

MTOW 64 000kgMLW 61 000kg

MZFW 57 000kg

Take-off

Take-off/landingFlight

Flight

Landing35.4

Page 46



A320 Family

[ 03-9]


25232119171513 27 29 31 33 35 37 4139

15 17 1911090705 13 21 23 25 27 29 31 33 35 4537 39 41 4335

40

45

50

55

60

65

70

75

80

35

40

45

50

55

60

65

70

75

80

%RC

%RC

Aircraft weight (kg x 1000) Aircraft weight (kg x 1000)

65.3

MTOW 75 500 kg

MLW 62 500 kg

MZFW 58 500 kg

Take-off/landing

Flight

Flight

Landing

3

6

3

7

2

6

2

4

74.5

2

5

49.6

Take-off

35.4

Page 47


Is [ 03-10]

0

OTsiae

BTa

D

ations associated to high design ample maximum taxiing speed during



mode


3.20.50




escriptiochangesual, Weition Manmodificachangesware to aMLW, replacemfitting indpossiblywhen nen 1, January 2012 03.20.500




Taxi Weight (MTW) 73.9 t Take-Off Weight (MTOW) 73.5 t Landing Weight (MLW) 64.5 t Zero Fuel Weight (MZFW) 61.0 t.

n for A320-200 in the aircraft manuals (Aircraft Flight Man-ght & Balance Manual, Flight Crew Opera-ual, ) tion of the CG diagram in all performance related manuals and soft-dapt to the new maximum weights (MTOW, ) ent of labels bonded to the NLG/MLG main icating MTOW and tire pressure

, changes of the brakes, wheels and tires cessary

possible limitweights (for exturns).





A320 Family

[ 03-11]

Figure 03-7 - Design weight options (A320)WeightVariant

A320-214CFM 56-5B4/3

A320-215CFM 56-5B5/3

A320-216CFM 56-5B6/3

A320-232IAE V2527-A5

A320-233IAE V2527E-A5

CN03.20.514 CN03.20.515 CN03.20.516 CN03.20.532 CN03.20.533 TDU

008MTOWMLWMZFW

73.564.561

Basic Basic Basic Basic Basic 08 Certified = SCG item (no lead-time constraint)

009MTOWMLWMZFW

75.564.561

Certified Certified Certified Certified Certified 09

010MTOWMLWMZFW

7764.561

Certified N/A N/A Certified Certified 10

011MTOWMLWMZFW

75.566

62.5Certified Certified Certified Certified Certified 11

012MTOWMLWMZFW

7766

62.5Certified N/A N/A Certified Certified 12

013MTOWMLWMZFW

71.564.561


014MTOWMLWMZFW

73.564.561.5


015MTOWMLWMZFW

7864.561

Certified N/A N/A Certified Certified 15

016MTOWMLWMZFW

73.566


017MTOWMLWMZFW

7866

62.5Certified N/A N/A Certified Certified 17

018MTOWMLWMZFW

71.566


N/A = Not Applicable

Design weights(tons)

Page 49



[ 03-12]


25 27 29 31 332321191715

35

40

45

50

55

60

65

70

75

80

85

90

35

40

45

50

55

60

65

70

75

80

85

9035 37 39 41% RC

Aircraft weight (kg x 1 000) Aircraft weight (kg x 1 000)

11090705 13 15 17 19 21 23 25 %RC27 29 31 33 35 37 39 41 43 45

47.5

69.5

MTOW 73 500kg

MLW 64 500kg

MZFW 61 000kg

Take-offTake-off/landing

FlightFlight

Landing

Page 50



A320 Family

[ 03-13]


Page 51


Is [ 03-14]

0

OTsiae

BTa

D



mode


3.20.60




escriptiochangesual, Weition Manmodificachangesware to aMLW, replacemfitting indpossiblywhen nen 1, January 2012 03.20.600




Taxi Weight (MTW) 89.4 t Take-Off Weight (MTOW) 89.0 t Landing Weight (MLW) 75.5 t Zero Fuel Weight (MZFW) 71.5 t.

n for A321-200 in the aircraft manuals (Aircraft Flight Man-ght & Balance Manual, Flight Crew Opera-ual, ) tion of the CG diagram in all performance related manuals and soft-dapt to the new maximum weights (MTOW, ) ent of labels bonded to the NLG/MLG main icating MTOW and tire pressure

, changes of the brakes, wheels and tires cessary.





A320 Family

[ 03-15]

Figure 03-10 - Design weight options (A321)Weight variant A3

21-21

1CF

M 56

-5B3/3

A321

-212

CFM5

6-5B1

/3

A321

-213

CFM5

6-5B2

/3

A321

-231

IAE

V253

3-A5

A321

-232

IAE

V253

0-A5

Design weights (t)

CN03.20.611 CN03.20.612 CN03.20.613 CN03.20.631 CN03.20.632 TDU

000MTOW 89MLW 75.5 Basic Basic Basic Basic Basic 20MZFW 71.5

001MTOW 93MLW 77.8 Certified Certified Certified Certified Certified

Certified

01MZFW 73.8

002MTOW 89MLW 77.8 Certified Certified Certified Certified 02MZFW 73.8

004MTOW 87MLW 75.5 04MZFW 71.5

005MTOW 85MLW 75.5 Certified Certified Certified Certified Certified

Certified Certified Certified Certified Certified





Certified Certified Certified Certified Certified

05MZFW 71.5

006MTOW 83MLW 75.5 06MZFW 71.5

007MTOW 83MLW 73.5 Not yetcertified

Not yetcertified 07

MZFW 69.5

008MTOW 80MLW 73.5 Not yet

certifiedNot yetcertified 08

MZFW 69.5

MZFW 69.5

009MTOW 78MLW 73.5 Not yetcertified

Not yetcertified 09

Not yetcertified

Not yetcertified 10


Not yet certified = certification possible on specific customer request (lead-time constraint)

010MTOW 85MLW 77.8MZFW 73.8

Certified Certified Certified Certified Certified 11011MTOW 93.5MLW 77.8MZFW 73.8

Page 53



[ 03-16]


35

40

45

50

55

60

65

70

75

80

85

90

95

35

40

45

50

55

60

65

70

75

80

85

95

90

25 27 29 31 33232119171513 35 37 39 41% RCAircraft weight (kg x 1 000) Aircraft weight (kg x 1 000)

11090705 13 15 17 19 21 23 25 %RC27 29 31 33 35 37 39 41 43 45

MTOW 89 000kg

MLW 75 500kg

MZFW 71 500kg

Take-off

Take-off/landingFlight

FlightLanding

81.8

4

0

.

1

Page 54



A320 Family

[ 03-17]

Figure 03-12 - CG limits diagram with max. optional MTOW (A321)25232119171513 27 29 31 33 35 37 4139

15 17 1911090705 13 21 23 25 27 29 31 33 35 4537 39 41 43 35

40

45

50

55

60

65

70

75

80

85

90

95

35

40

45

50

55

60

65

70

75

80

85

90

95

%RC


E23_011_232A

Take-off42.9

MTOW 93 500 kg

MLW 77 800 kg

MZFW 73 800 kg

80.3

75.5

79.2

4

0

.

6

Take-off/landing

Flight

Flight

Landing

89.0

91.5

17.515.3

3

9.5

15.5

19.6

5

17

21.6

5

36.8

837

.83

39.1

6

Page 55




03.20.600 [ 03-18]Page 56


[ 11-1]

A320 Family Placards and markings 11

Reference Title11.00.124 Installation of leasing identification plates11.20.100 Second language for door operation external placards and markings11.20.110 Second language for selected external placards and markings11.20.119 Nose Landing Gear (NLG) permanent steering markers11.20.135 Second language for residual cabin & cargo pressure exterior door warning placards11.21.101 Emergency cut-out markings11.22.100 Landing gear placards11.30.100 Installation of additional access placards in forward and aft cargo holds11.30.121 Second language for cargo compartment placards11.30.136 US and metric units for cargo compartment height placards11.33.101 Placard for flight crew oxygen system

Page 57

11 Placards and markings A320 Family

Is [ 11-2]

1

OTo

BMfrAe

DLpcoe

NTcob

EIn


1.00.12

bjectiveo install sn the aircr

asic aircranufacturame of the SELCAL l.

escriptioeasing plaer frame ockpit side

r requirem

otehe wordinntracts a

efore the s


4 - Installation of leasing identification plates

upplementary (leasing) identification plates aft.

after and owner plates are installed on the forward RH passenger/crew/service door.

plate is installed on the main instrument pan-

ntes are installed on each engine, on the up-f the forward LH passenger door and on the of lavatory A partition according to custom-ents.

g of the plates shall be provided to AIRBUS s soon as possible or at the latest one week tart of the ground check.

ction mode

Placards and markings 11


A320 Family

[ 11-3]



Equipmentsupplier

EquipmentPN

QTY STS

01 Installation of leasing identifi-cation plates on engines, LH door frame and Lav A partition

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

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

02 Installation of leasing identifi-cation plates on engines

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


03 Installation of leasing identifi-cation plates on LH door frame

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


04 Installation of leasing identifi-cation plates on Lavatory A partition

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


Page 59


Is [ 11-4]

1 l placards and markings

OTdg

BE

DTo

(Ta

N

mode


1.20.10

bjectiveo provideoor operauage) inst

asic aircrxterior pla

escriptiohe followinperation, s

passengcargo dohese ma

ge).

otethe transcustomeessary, sity scalean indivilanguagebookletsn 1, January 2012 11.20.100

0 - Second language for door operation externa

exterior placards and markings related to tion in bilingual (English and a second lan-ead of English only.

aftcards and markings are in English.

ng exterior placards and markings, related to hall be bilingual:er/crew doors and emergency exits ors. rkings are considered as one single pack-

lation of the basic English wording into the rs nominated language and a graphic, if nec-hall be provided by the customer (high qual-

one printout and/or floppy disk)dual RFC has to be issued with the second identification (refer to external markings

).




A320 Family

[ 11-5]



Equipmentsupplier

EquipmentPN

QTY STS

01 Second language for door operation external placards and markings

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


Second language TBD TBD SFE

Page 61


Is [ 11-6]

1 rds and markings

OTbE

BE

DIncasim

N

EIn


1.20.11

bjectiveo provide ilingual (English onl

asic aircrxternal pla

escriptio addition tbin press

ble to selearkings a

otethe transcustomeessary, san indiviguage idplacardsbooklets


0 - Second language for selected external placa

selected external placards and markings in nglish and a second language) instead of y.

aftcards and markings are in English.

no the external placards dedicated to residual ure warnings and doors operation, it is pos-ct some of the others external placards and

s bilingual ones.

lation of the basic English wording into the rs nominated language and a graphic, if nec-hall be provided by the customerdual RFC has to be issued for second lan-entification and the selection of concerned and markings (refer to external markings ). ction mode



A320 Family

[ 11-7]



Equipmentsupplier

EquipmentPN

QTY STS

01 Second language for selected external placards and mark-ings (A319)

A319-100 Negl./Negl./Negl. Second language TBD TBD SFE







A320 System Configuration Guide

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Transcript of A320 System Configuration Guide