QUICK REFERENCE HANDBOOK - Flight · PDF filea330-243f quick reference handbook transmittal...

TPA A330-243F FLEET AS PER AIRCRAFT ALLOCATION TABLE

QUICK REFERENCE HANDBOOK

The content of this document is the property of Airbus. It is supplied in confidence and commercialsecurity on its contents must be maintained. It must not be used for any purpose other than that for

which it is supplied, nor may information contained in it be disclosed to unauthorized persons. It mustnot be reproduced in whole or in part without permission in writing from the owners of the copyright.

© AIRBUS 2005. All rights reserved.

Intentionally left blank

1/2A330-243F


TRANSMITTAL LETTER06 MAR 17


Issue date: 06 MAR 17

This is the QUICK REFERENCE HANDBOOK major event publication at issue date 06 MAR 17 for theA330-243F and replacing last issue dated 18 JAN 17

QRH PAGE GEN.02A PROVIDES ADDITIONAL GUIDANCE TO MANAGE THE QRH UPDATES.

2/2A330-243F


TRANSMITTAL LETTER06 MAR 17



1/2A330-243F


FILING INSTRUCTIONS06 MAR 17


Please incorporate this major event revision as follow:

InsertLocalizationSubsection Title Remove Rev. Date

PLP-LESSLIST OF EFFECTIVE SECTIONS/SUBSECTIONS ALL 06 MAR 17

* PLP-LEDULIST OF EFFECTIVE DOCUMENTARY UNITS ALL 06 MAR 17

ABN-PLP-TOCTABLE OF CONTENTS ALL 06 MAR 17

* ABN-PLP-SOHSUMMARY OF HIGHLIGHTS ALL 06 MAR 17

ABN-80Miscellaneous ALL 06 MAR 17

C2Back-cover page interior ALL 06 MAR 17

* Preliminary pages that may be removed from the QRH binder

2/2A330-243F


FILING INSTRUCTIONS06 MAR 17



1/2A330-243F


PRELIMINARY PAGESLIST OF EFFECTIVE

SECTIONS/SUBSECTIONS 06 MAR 17


M(1) Localization Subsection Title Rev. DateR PLP-LESS LIST OF EFFECTIVE SECTIONS/SUBSECTIONS 06 MAR 17

PLP-LETDU LIST OF EFFECTIVE TEMPORARY DOCUMENTARY UNITS 05 NOV 13GEN General 30 JUN 15ABN-22 Auto-Flight 30 JUN 15ABN-24 Electrical 30 JUN 15ABN-26 Fire Protection 06 DEC 16ABN-27 Flight Controls 06 DEC 16ABN-28 Fuel 18 JAN 17ABN-29 Hydraulic 18 JAN 17ABN-30 Ice and Rain Protection 06 DEC 16ABN-31 Indicating / Recording Systems 19 MAR 13ABN-32 Landing Gear 18 JAN 17ABN-34 Navigation 06 DEC 16ABN-36 Pneumatic 18 JAN 17ABN-70 Engines 18 JAN 17

R ABN-80 Miscellaneous 06 MAR 17NP-NP Normal Procedures 06 DEC 16NP-NCL Normal Checklist 06 DEC 16PER-A Speeds 05 MAR 14PER-B Fuel Penalty Factors 07 JUN 16PER-C Landing Performance Assessment 18 JAN 17PER-D Landing Distance without Failure 05 MAR 14PER-24 Landing Distance with Electrical System Failure 05 MAR 14PER-27 Landing Distance with Flight Controls System Failure 05 MAR 14PER-27A Landing Distance with Slats and Flaps System Failure 30 JUN 15PER-28 Landing Distance with Fuel System Failure 05 MAR 14PER-29 Landing Distance with Hydraulic System Failure 05 MAR 14PER-30 Landing Distance with Anti Ice System Failure 05 MAR 14PER-32 Landing Distance with Brake System Failure 05 MAR 14PER-34 Landing Distance with Navigation System Failure 05 MAR 14PER-36 Landing Distance with Bleed System Failure 05 MAR 14PER-70 Landing Distance with Engine System Failure 05 MAR 14PER-E One Engine Inoperative 05 MAR 14PER-G All Engines Operative 05 MAR 14PER-H Flight Without Cabin Pressurization 05 MAR 14PER-I Miscellaneous 05 MAR 14OPS Operational Data 06 DEC 16OEBPROC-PLP-LEOEB LIST OF EFFECTIVE OPERATIONS ENGINEERING BULLETIN 18 JAN 17

(1) Evolution code : N=New, R=Revised, E=Effectivity, M=Moved

2/2A330-243F


PRELIMINARY PAGESLIST OF EFFECTIVE

SECTIONS/SUBSECTIONS 06 MAR 17



1/2A330-243F


PRELIMINARY PAGESLIST OF EFFECTIVE TEMPORARY

DOCUMENTARY UNITS 05 NOV 13


M (1) Localization DU Title DU identification DU dateABN-31 Display Unit Failure 00014692.0002001 12 MAR 13Criteria: S30653, A330Applicable to: ALLImpacted DU: 00010550 Display Unit FailureReason for issue:The "Display Unit Failure" procedure is amended to introduce a temporary procedure and its associated corrective action inthe case of Display Unit (DU ) brightness reduction to the minimum. Due to an issue with the backlight monitoring function ofthe Enhanced Display Unit (EDU) a DU might have its brightness spuriously set to the minimum. To recover the display, theflight crew has to set the affected DU brightness knob to OFF then ON.

ABN-80 Computer Reset Table FG00763ABN-80 Computer Reset Table - 32 - Landing Gear 00015048.0001001 07 OCT 13Criteria: LRApplicable to: ALLImpacted DU: 00010654 System Reset Table - 32 - Landing GearReason for issue:The BSCU reset procedure for WHEEL N/W STRG FAULT is amended with a temporary procedure, in order to betteraddress the spurious alerts that are currently encountered in-service. Under the very specific conditions defined in theprocedure, the flight crews can continue the flight without troubleshooting after a successful BSCU reset.

(1) Evolution code : N=New, R=Revised, E=Effectivity

2/2A330-243F


PRELIMINARY PAGESLIST OF EFFECTIVE TEMPORARY

DOCUMENTARY UNITS 05 NOV 13



1/2A330-243F


PRELIMINARY PAGESAIRCRAFT ALLOCATION TABLE 06 JAN 15


This table gives, for each delivered aircraft, the cross reference between:- The Manufacturing Serial Number (MSN).- The Fleet Serial Number (FSN) of the aircraft as known by AIRBUS S.A.S.- The registration number of the aircraft as known by AIRBUS S.A.S.- The aircraft model.

M(1) MSN FSN Registration Number Model1368 N330QT 330-243F1380 N331QT 330-243F1428 N332QT 330-243F1448 N334QT 330-243F1534 N335QT 330-243F

(1) Evolution code : N=New, R=Revised

2/2A330-243F


PRELIMINARY PAGESAIRCRAFT ALLOCATION TABLE 06 JAN 15



1/4A330-243F


PRELIMINARY PAGESLIST OF MODIFICATIONS 18 JAN 17


M(1) MODIFICATION Linked SB Incorp. Date TitleD40487 19 MAR 13 FUEL - APU FUEL PUMP SYSTEM - PREVENT AN

ELECTRICAL ESS NETWORK "OVERLOAD" (A330)Applicable to: ALL

D42829 19 MAR 13 COMMUNICATIONS - GENERAL - BASIC PROVISIONS FOR INFLIGHT ENTERTAINMENT SYSTEM A330/A340-200/300

Applicable to: ALLD45352 19 MAR 13 EQUIPMENT/FURNISHINGS-MIS. EMER. EQPT.- INSTALL

HONEYWELL ELT WITH REMOTE CONTROL PANEL IN THECOCKPIT

Applicable to: ALLD48233 19 MAR 13 COMMUNICATIONS - CIDS - INTRODUCE THE COMMUNAL

DIRECTOR FOR LONG RANGE PAX AND FREIGHTER A/C'SWITH INTEGRATED SDF

Applicable to: ALLD48352 19 MAR 13 E/F.: COURIER AREA - DEFINE FLEXIBLE LAYOUT

DEFINITION IN ADDITION TO THE TYPE CERTIFICATE FORA330-200F

Applicable to: ALLH13959 19 MAR 13 ICE AND RAIN PROTECTION - WING ICE PROTECTION -

RELOCATE OUTBOARD VALVE TO INBOARD POSITIONApplicable to: ALL

H14027 19 MAR 13 FUEL - FCMS - INSTALL FCMC STAGE 9.0Applicable to: ALL

H15264 19 MAR 13 GENERAL-DESIGN WEIGHTS-CERTIFY A330-200 WV050MTOW 230T, MLW 180T, MZFW 168T WITH REVISED A/CDESIGN SERVICE GOAL

Applicable to: ALLH16147 19 MAR 13 FUEL-TANKS- REMOVE OF THE CENTRE TANK CAPABILITY

Applicable to: ALLS10053 21 SEP 15 AUTOFLIGHT-DEFINE QFE/QNH SETTING

Applicable to: ALLS11135 19 MAR 13 INDICATING/RECORDING SYSTEMS-FMGEC- REPLACE

METERS BY FEETApplicable to: ALL

S12358 19 MAR 13 FLIGHT CONTROLS - CHANGE WIRING OF FCPC1 ANDFCSC1 FAULT INDICATOR LIGHTS

Applicable to: ALLS12410 19 MAR 13 ENGINE FUEL AND CONTROL - GENERAL - PROVIDE

DERATED TAKE OFF FACILITY FOR R.R. ENGINESApplicable to: ALL

S12968 19 MAR 13 NAVIGATION - WEATHER RADAR SYSTEM - ACTIVATE DUALPREDICTIVE WINDSHEAR RADAR SYSTEM, COLLINS

Applicable to: ALLS13133 19 MAR 13 ICE AND RAIN PROTECTION - WINDSHIELD RAIN

PROTECTION - DEACTIVATE RAIN REPELLENT SYSTEMApplicable to: ALL

S13217 19 MAR 13 FUEL - DISTRIBUTION - INSTALL STRUCTURE AND SYSTEMPROVISIONS FOR ACTIVATION OF CENTER TANK (A330-200)

Applicable to: ALLS13313 19 MAR 13 FLIGHT CONTROLS - GENERAL - ADAPT FLIGHT CONTROLS

FOR ST7Applicable to: ALL

S13455 21 SEP 15 AUTO FLIGHT-FLIGHT CONTROL UNIT- ACTIVATEAUTOMATIC ENGAGEMENT OF FLIGHT DIRECTOR WITHCROSS BARS IN GO AROUND

Applicable to: ALLS13661 19 MAR 13 NAVIGATION - MMR - INSTALL COLLINS MULTI-MODE

RECEIVERS PROVIDING ILS (FM IMMUNE) AND GPSPRIMARY FUNCTION

Applicable to: ALLS13893 19 MAR 13 OXYGEN - CREW OXYGEN - INSTALL A 115 CU.FT

COMPOSITE OXYGEN CYLINDERApplicable to: ALL

S13916 19 MAR 13 ICE AND RAIN PROTECTION - WINDSHIELD RAINPROTECTION - REACTIVATE THE RAIN REPELLENT SYSTEM

Applicable to: ALL

2/4A330-243F




Continued from the previous pageM(1) MODIFICATION Linked SB Incorp. Date Title

S14135 19 MAR 13 INDICATING/RECORDING SYSTEMS - EIS - DISPLAYMANAGEMENT COMPUTER - INSTALL NEW DMC SOFTWAREV510X

Applicable to: ALLS14218 19 MAR 13 NAVIGATION - GPWS - ACTIVATE ENHANCED GPWS

Applicable to: ALLS14275 19 MAR 13 AUTO FLIGHT - FMGEC - INSTALL FMGEC P1-CD7 FOR RR

OR PW ENGINESApplicable to: ALL

S14327 19 MAR 13 INDICATING/RECORDING SYSTEMS-CENTRAL WARNINGSYSTEMS-PROVIDE NEW AUTO CALL-OUT CALLED "V1"

Applicable to: ALLS14521 19 MAR 13 NAVIGATION-TCAS-INSTALL ALLIED SIGNAL CHANGE 7 P/N

066-50000-2220Applicable to: ALL

S14562 19 MAR 13 AUTO FLIGHT - FMGEC - INSTALL A NEW STANDARD FMGECL9CD6

Applicable to: ALLS14649 19 MAR 13 NAVIGATION - MMR - INSTALL COLLINS MULTI-MODE

RECEIVERS P/N 822-1152-121Applicable to: ALL

S14786 19 MAR 13 NAVIGATION-STANDBY NAVIGATION SYSTEMS- INSTALLSEXTANT AVIONICS INTEGRATED STANDBY INSTRUMENTSYSTEM (ISIS)

Applicable to: ALLS14859 19 MAR 13 INDICATING/RECORDING SYSTEMS-ELECTRONIC

INSTRUMENT SYSTEM - INSTALL NEW DISPLAY SYSTEM(EIS2) EQTS (DMC/DU/DISKETTES)

Applicable to: ALLS15891 19 MAR 13 NAVIGATION - EGPWS - USE LATERAL GPS POSITION WITH

AUTOMATIC DESELECTIONApplicable to: ALL

S16107 19 MAR 13 INFORMATION SYSTEMS - GENERAL - CERTIFY FANS ACONFIGURATIONS

Applicable to: ALLS16262 19 MAR 13 NAVIGATION - EGPWS - ACTIVATE OBSTACLE FUNCTION

Applicable to: ALLS16279 19 MAR 13 FLIGHT CONTROLS - ELECTRICAL FLIGHT CONTROL

SYSTEM (EFCS) - INSTALL RUDDER FLY-BY WIRE ONA330/A340

Applicable to: ALLS16286 19 MAR 13 INDICATING/RECORDING SYSTEMS - FWC - INSTALL NEW

STANDARD K7Applicable to: ALL

S16318 19 MAR 13 ELECTICAL POWER - GENERAL - INSTALL EMERGENCYPOWER CENTER 743 VU IN SECT 11/12

Applicable to: ALLS16354 19 MAR 13 INDICATING/RECORDING SYSTEMS - FWC - REPLACE THE

EXISTING STANDARD FWC BY A NEW STD K6 FOR A330 - FAR 121-344

Applicable to: ALLS16606 19 MAR 13 INDICATING/RECORDING SYSTEMS - EIS - INTALL NEW EIS2

STANDARD L4 ON A330/A340 ENHANCEDApplicable to: ALL

S16646 19 MAR 13 NAVIGATION - WEATHER RADAR SYSTEM - INSTALLCOLLINS DUAL CONTROL PANEL CAPABLE OF MULTISCANFUNCTION

Applicable to: ALLS16983 19 MAR 13 INFORMATION SYSTEMS - GENERAL - CERTIFY FANS A+

CONFIGURATIONS (OVERALL MODIFICATION)Applicable to: ALL

S16985 19 MAR 13 GENERAL-TECHNICAL INFO ,WEIGHT AND GC - INCREASEMAXIMUM OPERATING ALTITUDE FROM 41100 TO 41450FEET

Applicable to: ALL

3/4A330-243F





S17494 19 MAR 13 INDICATING/RECORDING SYSTEM - EIS - INSTALL NEW EIS2STANDARD L3-1 (DMC, DU AND DISKS)

Applicable to: ALLS18094 19 MAR 13 FLIGHT CONTROL - FLIGHT CONTROL PRIMARY COMPUTER

(FCPC) - INTRODUCE TRIM SETTING AUTOMATIC FUNCTIONApplicable to: ALL

S18144 19 MAR 13 NAVIGATION-ADIRS-INTRODUCE AIR DATA MONITORINGFUNCTION

Applicable to: ALLS18160 22-3125 04 06 JAN 15 AUTO FLIGHT - FMGEC - INSTALL FMGEC P4HJ1 WITH

GENEPI HARDWARE AND FMS HONEYWELL RELEASE 1A ONA330 WITH PW/RR

Applicable to: ALLS18168 19 MAR 13 AUTO-FLIGHT - MCDU - INSTALL 3 LCD MCDU HONEYWELL

Applicable to: ALLS18222 19 MAR 13 NAVIGATION - SWITCHING AND INDICATING - REMOVE

DDRMI INDICATORSApplicable to: ALL

S18711 19 MAR 13 AUTO-FLIGHT - MCDU - INSTALL NEW MCDU LCDHONEYWELL (REBOND STANDARD)

Applicable to: ALLS18882 19 MAR 13 NAVIGATION - DME - RELOCATE DME1 POWER SUPPLY TO

PROVIDE POWER IN EMERGENCY FOR A330Applicable to: ALL

S19417 19 MAR 13 INDICATING / RECORDING SYSTEMS - FLIGHT WARNINGCOMPUTER (FWC) - INSTALL FWC STANDARD T2-0.

Applicable to: ALLS19547 21 SEP 15 AUTO FLIGHT-FMGEC-REPLACE FMGEC T3HJ0 HARDWARE

GENEPI WITH P3HJ0 ON A330-200F WITH PW/RR ENGINESApplicable to: ALL

S30154 19 MAR 13 FUSELAGE - NOSE FORWARD FUSELAGE ADAPT NLGDOORS FOR A330-200F

Applicable to: ALLS30373 19 MAR 13 NAVIGATION - TCAS - INSTALL TCAS HONEYWELL TPA-100B

CHANGE 7.1 CAPABLE OF ATSAWApplicable to: ALL

S30653 19 MAR 13 INDICATING/RECORDING SYSTEMS - DMC - INSTALLENHANCED DU INSTEAD OF EIS2 LCDU

Applicable to: ALLS30672 19 MAR 13 INDICATING/RECORDING SYSTEMS - FWC - INSTALL FWC

STANDARD T3-0 ON LR A/CApplicable to: ALL

S30806 21 SEP 15 AUTO FLIGHT-FLIGHT MANAGEMENT-ACTIVATE "NOPROFILE INVALIDATION AT MDA - 50FT IN FINAL APP"FUNCTION IN FMS RELEASE 1

Applicable to: ALLS30934 30 MAY 13 NAVIGATION - GENERAL - FLIGHT MANUAL EXTENSION TO

RNP AR 0.3 CAPABILITY - A330 CONFIGURATIONApplicable to: ALL

S30958 19 MAR 13 INDICATING/RECORDING SYSTEMS - FWC - INTRODUCENEW FWC STANDARD T4 ON LR A/C

Applicable to: ALLS30973 30 MAY 13 INDICATING/RECORDING SYSTEM - EIS - ACTIVATE LAT DEV

SCALE DISPLAY FUNCTIONApplicable to: ALL

S31353 19 MAR 13 INDICATING RECORDING SYSTEMS - FWC - ACTIVATEMONITORING OF ATC/XPDR FAULTS

Applicable to: ALLS32159 31-3200 01 06 JAN 15 INDICATING/RECORDING SYSTEMS - FLIGHT WARNING

COMPUTER (FWC) - INTRODUCE NEW FWC STANDARD T5Applicable to: ALL

S32258 34-3288 01 06 JAN 15 NAV- W/R SYST - INSTALL COLLINS WXR CAPABLEMULTISCAN WITH TRANSCEIVER WRT-2100 (P/N822-1710-214)

Applicable to: ALL

4/4A330-243F





22-3147 01 21 SEP 15 AUTO FLIGHT - FMGEC - INSTALL FMGEC P4HJ1A CAPABLEOF NAV MODE KEPT IN GO AROUND ON A330 WITH PW/RRENGINES

Applicable to: ALL31-3232 00 07 JUN 16 INDICATING/RECORDING SYSTEMS - FLIGHT WARNING

COMPUTER (FWC) - INTRODUCE FWC STD T7Applicable to: ALL

(1) Evolution code : N=New, R=Revised, E=Effectivity

GEN1/2

A330-243FQUICK REFERENCE HANDBOOK

GENERALTABLE OF CONTENTS

30 JUN 15


Important.........................................................................................GEN.01AGeneral Information........................................................................GEN.02A

GEN2/2


GENERALTABLE OF CONTENTS

30 JUN 15



GEN.01AA330-243F


GENERAL30 JUN 15


IMPORTANTIdent.: GEN-A-00010448.0001001 / 17 AUG 10Applicable to: ALL

SCOPEThe QRH contains some specific procedures which are not displayed on the ECAM.As a general rule, procedures displayed on the ECAM are not provided in the QRH (Refer to FCOMPRO/ABN).

Ident.: GEN-A-00010465.0001001 / 23 DEC 14Applicable to: ALL

TASK SHARING FOR ABN /EMER PROCFor all abnormal/emergency procedures, the tasksharing is as follows:

PF : Pilot flying - Responsible for the:‐ Thrust levers‐ Flight path and airspeed control‐ Aircraft configuration (Request configuration change)‐ Navigation‐ Communications

PM : Pilot monitoring - Responsible for:‐ Monitoring and reading aloud the ECAM and checklists‐ Performing required actions or actions requested by the PF, if applicable‐ Using engine master switches, reset buttons, IR and guarded switches with PF's

confirmation (except on ground).Ident.: GEN-A-00010466.0001001 / 17 AUG 10Applicable to: ALL

ECAM CLEARDO NOT CLEAR ECAM WITHOUT CROSS-CONFIRMATION OF BOTH PILOTS.

Ident.: GEN-A-00010467.0001001 / 12 MAY 15Applicable to: ALL

ABN /EMER PROC INITIATIONProcedures are initiated on pilot flying command.No action will be taken (apart from audio warning cancel through MASTER WARN light) until:‐ The appropriate flight path is established, and‐ The aircraft is at least 400 ft above the runway, if a failure occurs during takeoff, approach, or

go-around. (In some emergency cases, provided the appropriate flight path is established, the pilotflying may initiate actions before this height).

The flight crew can stop the procedure if the conditions for the application of the QRH proceduredisappear.

Ident.: GEN-A-00010468.0001001 / 23 DEC 14Applicable to: ALL

NORMAL CHECKLISTNormal C/L are initiated by the PF and read by the PM . The PF shall respond after having checked theexisting configuration. When both pilots have to respond, "BOTH" is indicated.

Ident.: GEN-A-00014735.0001001 / 08 FEB 13Applicable to: ALL

DEFINITIONS OF WARNINGS, CAUTIONS AND NOTESThe following are the official definitions of warnings, cautions and notes taken directly from theJAR25/CS-25 and applicable to Airbus flight operation documentation:WARNING An operating procedure, technique, etc. that may result in personal injury or loss of life

if not followed.CAUTION An operating procedure, technique, etc. that may result in damage to equipment if not

followed.NOTE An operating procedure, technique, etc. considered essential to emphasize.

Information contained in notes may also be safety related.

GEN.02AA330-243F


GENERAL30 JUN 15


GENERAL INFORMATIONIdent.: GEN-B-00015231.0001001 / 24 FEB 14Applicable to: ALL

QRH REVISION DATEThe update of the FCOM does not necessarily result in the update of the QRH . Therefore, the revisiondates of the QRH and of the FCOM may differ.

Ident.: GEN-B-00013895.0001001 / 23 MAR 11Applicable to: ALL

EFFECTIVITYAs QRH is published at aircraft level, each paper page has only one effectivity.

Ident.: GEN-B-00013879.0001001 / 28 FEB 14Applicable to: ALL

PAGE NUMBERINGThe page numbering follows the following rules:01A, 02A, 02B,.. : Numbering and Index (A, B, ...) for GEN, ABN, OPS, OEB PROC sections

Note: For these sections, the procedures start with the index A and for long procedures (more thanone page), the index continues with B, C...

1/10, 3/5, ... : Numbering for NP-NP, PERC1, C2 : Back cover page interiorC3 : Back cover page exterior"BLANK" : Index of an intentionally left blank paper page created to ensure the correct

format of the next chapter (begins on recto page)Ident.: GEN-B-00013894.0001001 / 16 MAR 15Applicable to: ALL

PRELIMINARY PAGES WITHIN THE QRH BINDERIt is essential for Airlines to correctly manage the updates of the QRH . For this purpose, Airbus publishesPreliminary Pages (PLP ) with each QRH revision. These PLP are used as reference documents forAirlines to manage the QRH updates, e.g. easily insert the revisions, identify the modifications that impactthe QRH , get a synthesis of changes introduced with each revision. However, when the QRH revisionshave been incorporated in accordance with the information given in the PLP , these pages do notbring operational added value and therefore are no longer useful in the QRH binder for any operationalpurposes. Therefore, to minimize the size of the QRH binder on board the aircraft and to optimize theoperational use of the QRH , Airbus has no objection that the Airlines remove the PLP from the QRHafter the revisions have been incorporated in the QRH and all checks performed to confirm the revisionshave been correctly incorporated. You will find below the list of PLP that may be removed from the QRHbinder :‐ The transmittal letter‐ The List of Effective Preliminary Pages (LEPP)‐ The Filing Instructions (FI)‐ The List of Effective Documentary Units (the LESS is the reference)‐ The List Of Modifications (LOM)‐ The Summary Of Highlights (SOH)‐ The front pages of all QRH sections‐ The Table Of Contents (TOC) of the General section.

ABN1/4


ABNORMAL ANDEMERGENCY PROCEDURES

TABLE OF CONTENTS 06 MAR 17


Auto-Flight ABN-22Loss of FMS Data In Descent/Approach (Severe Reset)...................22.01AMCDU 1(2)(3) Failure.........................................................................22.02A

Electrical ABN-24ELEC EMER CONFIG Sys-Remaining.............................................. 24.01AELEC EMER CONFIG Summary..................................................... 24.02A

Fire Protection ABN-26SMOKE/FUMES/AVNCS/MD SMOKE.............................................. 26.01AREMOVAL OF SMOKE/FUMES....................................................... 26.02ASMOKE/FIRE FROM LITHIUM BATTERY........................................ 26.03A

Flight Controls ABN-27LANDING WITH SLATS OR FLAPS JAMMED................................. 27.01ANo Flaps no Slats Landing................................................................ 27.02ASidestick / Rudder Pedals Stiff.......................................................... 27.03ARudder Jam/Rudder Pedal Jam.........................................................27.04ARudder Trim Runaway....................................................................... 27.05A

Fuel ABN-28FUEL IMBALANCE............................................................................ 28.01AFUEL LEAK........................................................................................28.02AFUEL LOSS REDUCTION................................................................. 28.03AGRVTY FUEL FEEDING....................................................................28.05ATRIM TANK FUEL UNUSABLE......................................................... 28.06A

Hydraulic ABN-29HYD B+Y SYS LO PR Summary..................................................... 29.01AHYD G+B SYS LO PR Summary.....................................................29.02AHYD G+Y SYS LO PR Summary.....................................................29.03A

Ice and Rain Protection ABN-30Double AOA Heat Failure.................................................................. 30.01A

Indicating / Recording Systems ABN-31Display Unit Failure............................................................................31.01AECAM Single Display.........................................................................31.02AEIS DISPLAY DISCREPANCY.......................................................... 31.03A

ABN2/4





Continued from the previous pageLanding Gear ABN-32

Loss of Braking................................................................................32.01AL/G Gravity Extension .......................................................................32.03ALanding with Abnormal L/G................................................................32.04A

Navigation ABN-34Abnormal V Alpha Prot...................................................................... 34.01AADR CHECK PROC.......................................................................... 34.02AUNRELIABLE SPEED INDICATION..................................................34.02AALL ADR OFF...................................................................................34.03ANAV FM / GPS POS DISAGREE...................................................... 34.05AIR Alignment in ATT Mode................................................................ 34.06AEGPWS Warnings............................................................................ 34.07AEGPWS Cautions...............................................................................34.08ATCAS Warnings................................................................................34.09A

Pneumatic ABN-36AIR ENG 1+2 BLEED RESET (APU BLEED AVAILABLE)................36.02AAIR ENG 1+2 BLEED RESET (APU BLEED NOT AVAILABLE)....... 36.03A

Engines ABN-70ALL ENGINES FAILURE.................................................................. 70.01AENG RELIGHT (IN FLIGHT)..............................................................70.06AENG 1(2) STALL................................................................................70.07AENG Tailpipe Fire.............................................................................. 70.08AHIGH ENGINE VIBRATION............................................................... 70.09ASuspected ENG Fuel Sys Contamination .........................................70.10AENG Fuel Sys Contamination............................................................ 70.10A

Miscellaneous ABN-80Circling Approach with One Engine Inoperative................................ 80.01ABomb on Board.................................................................................. 80.02ADITCHING.......................................................................................... 80.03AFORCED LANDING...........................................................................80.04AEMER DESCENT...............................................................................80.05AOverspeed Recovery..........................................................................80.06AOverweight Landing........................................................................... 80.07AStall Recovery.................................................................................. 80.08AStall Warning at Liftoff.................................................................... 80.08ATailstrike............................................................................................. 80.09A

ABN3/4





Continued from the previous pageVolcanic Ash Encounter.....................................................................80.10AWindshear......................................................................................... 80.11AWindshear Ahead.............................................................................80.12ACockpit Windshield / Window Arcing................................................. 80.13ACockpit Windshield / Window Cracked.............................................. 80.14AECAM Advisory Conditions................................................................ 80.15ATripped C/B Re - Engagement.......................................................... 80.16AComputer Reset - General.................................................................80.17AComputer Reset Table.......................................................................80.18AEmer Landing ALL ENG FAILURE........................................................ C2Emergency Evacuation...........................................................................C2

ABN4/4






ABN1/2


ABNORMAL ANDEMERGENCY PROCEDURESSUMMARY OF HIGHLIGHTS 06 MAR 17


LocalizationTitle

Page ID Reason

ABN-80Emer Landing ALL ENG FAILURE

80.C2 1 Documentation update: Addition of "Emer Landing ALL ENG FAILURE"documentary unit

ABN2/2


ABNORMAL ANDEMERGENCY PROCEDURESSUMMARY OF HIGHLIGHTS 06 MAR 17



22.01AA330-243F



30 JUN 15


LOSS OF FMS DATA INDESCENT/APPROACH (SEVERE RESET)

Ident.: ABN-22-00010477.0001001 / 08 FEB 13Applicable to: ALL

AP /FD lateral and vertical selected modes, and A/THR , are available immediately after the reset. Ifnecessary, the pilot may perform the FCU selections for short-term navigation.When the FMS has automatically recovered:‐ The database cycle may have changed‐ The FMGES does not autotune the ILS and ADF‐ The FMS position bias is lost‐ Lateral and vertical managed modes cannot re-engage‐ The ″CAB PR LDG ELEV FAULT″ message is displayed on the ECAM‐ The ″REENTER WEIGHT/CG ″ MCDU message is displayed.Depending on the flight phase, apply the following procedure(s) as appropriate: INITIAL APPROACH OR CLOSE TO ILS INTERCEPTION

When the system has recovered:Access the RAD NAV page, and manually tune the ILS (preferably usingIdent). Enter the ILS course, if a frequency has been entered.Fly in selected speed.Note: ‐ LOC and G/S guidance modes are available

‐ VLS speed is still available and displayed on the PFD‐ Missed approach trajectory is not available.

DESCENT (IF TIME PERMITS): When the system has recovered:

Select the initial database cycle.Perform DIR TO a downpath waypoint. Select heading, if required.Perform a LAT REV at the downpath waypoint, and redefine theDESTINATION in the NEW DEST field.Redefine the arrival and/or the approach procedure.Select the FUEL PRED page, and enter the GW and CG values read on theECAM fuel page.Activate the APPROACH phase.Enter the destination data on the PERF APPR page, as required. Managedspeed is available.

22.02AA330-243F



30 JUN 15


MCDU 1(2)(3) FAILUREIdent.: ABN-22-00010479.0002001 / 08 FEB 13Applicable to: ALL

DIM KEY (on affected MCDU)......................................................................... PRESSPress the DIM key for a few seconds until the MCDU turns off.MCDU 3 automatically replaces MCDU 1 or 2.

24.01AA330-243F



30 JUN 15


ELEC EMER CONFIG SYS-REMAININGEMER GEN RUNNING BAT ONLY

ELEC EMER CONFIG SYS REMAINING SUPPLIED BYENG HYD PUMPS

SUPPLIED BYRAT ONLY IN FLT ON GND

(IAS < 50 kt)

Ident.: ABN-24-SYN-00010481.0001001 / 17 NOV 14Applicable to: ALL

PRESS AUTO SYS 1 Norm Norm Norm Norm

MAN PRESS CTL inop inop inop Norm

RAM AIR Norm Norm Norm Norm

PACK VALVE Norm Norm Norm Norm

AVIONIC VENT OVBD only OVBD only OVBD only OVBD only

AIR CONDPRESSVENT

CARGO VENT ISOL valve only inop inop inop


FMGC 1 only inop inop inop

MCDU 1 only inop inop 3 onlyAUTO FLT

FCU 1 only 1 only 1 only 1 only


VHF 1 Norm Norm Norm Norm

HF 1 Norm (a) inop inop inop

RMP 1 Norm Norm Norm Norm

ACP (CAPT ., F/O) Norm Norm Norm Norm

CIDS Norm Norm Norm Norm

INTERPHONE Norm Norm Norm Norm

CVR Norm inop inop inop

COM

LOUDSPEAKER 1 + 2 Norm Norm Norm Norm


ENG LOOPS A only A only A only A only

APU LOOP A only A only A only Norm

CARGO SMOKE DET 1 only inop inop inop

ENG FIRE EXT. Squib A Squib A Squib A Squib A

APU FIRE EXT. Squib A Squib A Squib A Squib A

CARGO FIRE EXT. Squib A Squib A Squib A Squib A

FIRE

APU AUTO EXT. - - - Norm

24.01BA330-243F



30 JUN 15


Continued from the previous pageEMER GEN RUNNING BAT ONLY



(IAS < 50 kt)

Ident.: ABN-24-SYN-00010492.0004001 / 17 MAR 15Applicable to: ALL

PRIM 1 Norm Norm Norm Norm

SEC 2 Norm Norm Norm Norm

SEC 1 Norm Norm Norm Norm

FCDC 1 Norm inop inop inop

SFCC SLATS 1 only (b) 1 only (b) 1 only 1 only

SFCC FLAPS 1 only (b) inop inop inop

PITCH TRIM 1 only inop inop inop

RUDD TRIM Norm (c) inop inop inop

FLT CTL

RUDD TRAVEL Norm Norm Norm Norm


FCMC 1 only inop inop 2 only

PUMPS L PUMP 2 (d) L PUMP 2 (d) inop inop

X FEED Mot 1 only Mot 1 only Mot 1 only Mot 1 only

LP VALVES Mot 1 only Mot 1 only Mot 1 only Mot 1 only

XFR , ISOL VALVES Norm Norm Norm Norm

AFT APU PUMP Norm (a) Norm (a) Norm (a) Norm (a)

FUEL

APU LP VALVE Norm Norm Norm Norm


FIRE SOV Norm Norm Norm NormHYD

RAT CTL Norm Norm Norm Norm


ENG A. ICE Open Open Open Open

WING A. ICE Norm inop inop inop

CAPT PITOT Norm Norm Norm Norm

WHC 1 Norm (e) inop inop inop

CAPT AOA Norm inop inop inop

STBY AOA/PITOT Norm (f) inop inop inop

ICE & RAIN

RAIN REPEL Capt Capt Capt Capt

24.01CA330-243F



30 JUN 15





(IAS < 50 kt)


PFD 1 Norm Norm Norm Norm

ND 1 Norm inop inop inop

ECAM upper DU Norm Norm Norm Norm

DMC 1 or 3 Norm Norm Norm NormEIS

SDAC 1, FWC 1, ECP,CLOCK Norm Norm Norm Norm

Ident.: ABN-24-SYN-00010497.0001001 / 08 DEC 14Applicable to: ALL

LGCIU 1 only (e) 1 only (e) 1 only 1 only

GRVTY EXT Norm Norm Norm Norm

IND. PANEL Norm Norm Norm Norm

AUTO BRK/ANTI SKID Inop / Norm (e) inop inop inop

L/G

PARK BRK Norm Norm Norm Norm


LIGHTS L LDG LT Norm (e) inop inop inop


IR 1 and 3 Norm Norm Norm Norm

IR 2 5 min 5 min 5 min 5 min

ADR 1 Norm Norm Norm Norm

ADR 3 Norm (h) inop inop inop

VOR or ADF (g) 1 only 1 only 1 only 1 only

DME 1 only 1 only 1 only 1 only

MMR 1 only 1 only 1 only 1 only

ATC 1 only inop inop inop

RADAR 1 only inop inop inop

NAV

ISIS Norm Norm Norm Norm


Crew OXY valve CTL Norm inop inop inopOXYGEN

PAX OXY Norm Norm Norm Norm


ENG BLEED BMC 2 inop BMC 2 inop BMC 2 inop BMC 2 inopPNEU

X BLEED man only man only man only man only

24.01DA330-243F



30 JUN 15





(IAS < 50 kt)


APU Norm Norm Norm Norm


DOORS SLIDES ARM WARN Norm Norm Norm Norm


FADEC's A + B A + B A + B A + B

IGNITION A only A only A only A only

REV inop inop inop NormPWR PLT

HP VALVE closure Norm Norm Norm Norm

(a) Shed when LAND RECOVERY ON.

(b) Operative when LAND RECOVERY pb is ON. However the FLAPS remain lost, if ENG 2 is failed and IDG1 is lost.

(c) RUDDER TRIM is operative, but position indicator is lost on center pedestal.

(d) Crossfeed valve automatically opens.‐ If L PUMP 2 is inoperative, R PUMP 2 takes over.‐ Remaining pump is lost when the LAND RECOVERY pb is ON. When supplied by the RAT only, the

remaining pump is lost when speed is below 260 kt.

(e) Operative when LAND RECOVERY pb is ON.

(f) Shed when the LAND RECOVERY pb is ON, unless the AIR DATA selector is switched ”to CAPT ON 3”.

(g) Only VOR 1 or ADF 1 (as selected on the FCU) is available at a time.

(h) Shed when the LAND RECOVERY pb is ON, unless the AIR DATA selector is switched ”to CAPT ON 3”.(This leads to loss of the autopilot).

24.02AA330-243F



30 JUN 15


ELEC EMER CONFIG SUMMARYCRUISE

Ident.: ABN-24-SUM-00010480.0015001 / 09 APR 15Applicable to: ALL

SPD BRK...................................................................................................................................DO NOT USEMAX SPD............................................................................................................................................. 330/.82ALTN LAW : PROT LOSTONLY CAPT PITOT AND AOA PROBES HEATEDFUEL: Center tank: 15 t (33 000 lb) unusableAUTOFLIGHT: AP1 onlyNAV: ILS 1, GLS1 , DME 1, VOR 1, GPS1 onlyCOM: HF 1, VHF 1, ATC 1, RMP1 onlyFor Landing Performance assessment, Refer to QRH PER-C, or use the LDG PERF application ofFlySmart with Airbus.

APPROACHIdent.: ABN-24-SUM-00010483.0006001 / 17 NOV 14Applicable to: ALL

CAT 2 INOPFOR LANDING............................................................................................................................USE FLAP 3SLATS FLAPS SLOW For slats extension:

RAT MAN............................................................................................................................................. ONMINIMUM RAT SPEED 140 ktLAND RECOVERY...............................................................................................................................ONFUEL: 2 t unusable in each Inner Tank.

L/G gravity extension:MAX SPD.......................................................................................................................................200 KTL/G GRVTY EXTN......................................................................................................................... DOWN

When L/G down:L/G LEVER..................................................................................................................................... DOWNUSE MAN PITCH TRIM

LANDINGIdent.: ABN-24-SUM-00010484.0001001 / 17 AUG 10Applicable to: ALL

FLARE: Only 3 spoilers per wing. Direct law.SPOILERS: Only 3 per wingNO REVERSERBRAKING: NORMALNO NOSEWHEEL STEERING

GO-AROUNDIdent.: ABN-24-SUM-00010485.0001001 / 28 APR 14Applicable to: ALL

NO GEAR RETRACTIONFUEL: Increased fuel consumption (Refer to QRH PER-B)

BLANKA330-243F



30 JUN 15



26.01AA330-243F



06 DEC 16


SMOKE/FUMES/AVNCS/MD SMOKEIdent.: ABN-26-A-00010507.0004001 / 20 SEP 13Applicable to: ALL

LAND ASAPAPPLY IMMEDIATELY IF REQUIRED:

CREW OXY MASKS................... USE/100%/EMERGCAB FANS................................................................OFFGALLEY & LAV FAN................................................ OFFGALLEY.................................................................... OFFCKPT/CAB COM.......................................... ESTABLISHCAB TO CRG DOORS........................................ CLOSESIGNS.........................................................................ON IF SMOKE SOURCE IMMEDIATELY OBVIOUS,

ACCESSIBLE AND EXTINGUISHABLE:FAULTY EQPT.............................................ISOLATE

IF SMOKE SOURCE NOT IMMEDIATELYISOLATED:DIVERSION.................................................. INITIATEDESCENT.....................................................INITIATEDescent to FL 200, or MEA -MORA, or min obstacleclearance altitude

At ANY TIME of the procedure, if smoke/fumesbecomes the GREATEST THREAT:REMOVAL OF SMOKE/FUMES..............CONSIDERELEC EMER CONFIG.............................CONSIDERRefer to the end of the procedure to set ELECEMER CONFIG

26.01BA330-243F



06 DEC 16


SMOKE/FUMES/AVNCS/MD SMOKE (Cont'd)

At ANY TIME of the procedure, if situationbecomes UNMANAGEABLE:IMMEDIATE LANDING............................CONSIDER

Ident.: ABN-26-A-00013661.0003001 / 27 NOV 12Applicable to: ALL

IF SMOKE MD SMOKE ECAM ALERT, COMPLETE ECAMACTIONS, THEN:CREW OXY MASKS................................. USE/100%CAB OXY MASKS........................................MAN ONVENT EXTRACT................................. CHECK AUTOMD ISOL VALVES............................................... OFFALL LOWER CRG ISOL VALVES....................... OFFCAB................................................................ NOTIFYEMER EXIT LT...................................................... ONCOMMERCIAL..................................................... OFFCAB PR MODE SEL...........................................MANMAN VALVE SEL............................................... FWDMAN V/S CTL.....................................+ 4 000 FT/MNMAN ALT TGT........................................... 20 000 FTATC................................................................ NOTIFYRECOMMENDED CRUISE ALT......................FL 200When A/C and CAB ALT at 20 000 ft:

MAN V/S CTL..........................................FULL UPCREW OXY MASKS........................NORMAL MODEOXY PRESS...............................................MONITOR

26.01CA330-243F



06 DEC 16



MINIMUM OXY PRESS FOR 2CREW AT FL 200 (NORMAL MODE)

RemainingFlight Timeto Landing

(min)

30 60 90 120 150 180 210

MIN OXYPRESS(PSI)

165 240 315 390 465 540 610

If remaining OXY PRESS close to minimum:DESCENT (FL 140/MEA, min obstacle clearancealtitude)................................................ CONSIDER

At or below FL 140:CAB SUPPLY..............................CONSIDER OFF3RD AND 4TH CREW OXY MASKS............................................................... CONSIDER STOWING

REMOVAL OF SMOKE/FUMES.............. CONSIDERIdent.: ABN-26-A-00010510.0016001 / 27 NOV 12Applicable to: ALL

If AIR COND SMOKE SUSPECTED:APU BLEED.........................................................OFFVENT EXTRACT................................. CHECK AUTOMD ISOL VALVES............................................... OFFALL LOWER CRG ISOL VALVES....................... OFFPACK 1................................................................ OFF If smoke continues:

PACK 1............................................................. ONPACK 2........................................................... OFF

26.01DA330-243F



06 DEC 16



If smoke still continues:PACK 2........................................................ ONPACK 1.......................................................OFF

REMOVAL OF SMOKE/FUMES.............. CONSIDER IF CAB EQUIPMENT SMOKE SUSPECTED:

If smoke continues :VENT EXTRACT..........................................OVRDEMER EXIT LT................................................. ONCOMMERCIAL................................................ OFFSMOKE DISSIPATION.............................. CHECK If smoke still continues :

VENT EXTRACT..................................... AUTOREMOVAL OF SMOKE/FUMES.............. CONSIDER

Ident.: ABN-26-A-00010511.0005001 / 27 NOV 12Applicable to: ALL

IF SMOKE SOURCE CANNOT BE DETERMINEDAND STILL CONTINUES OR AVNCS/ELECTRICALSMOKE SUSPECTED:VENT EXTRACT...............................................OVRDShed AC BUS 1 as follows:

GEN 2................................................. CHECK ONECAM/ND SEL................................................. F/OELEC/AC page......................................... SELECTBUS TIE.......................................................... OFFAC ESS FEED.............................................. ALTNGEN 1............................................................. OFFSMOKE DISSIPATION.............................. CHECK

26.01EA330-243F



06 DEC 16



If smoke continues:GEN 1.......................................................... ONAC ESS FEED........................................NORMECAM/ND SEL....................................... NORM

Shed AC BUS 2 as follows:GEN 1................................................. CHECK ONBUS TIE............................................ CHECK OFFAC ESS FEED...............................CHECK NORMECAM/ND SEL.............................. CHECK NORMGEN 2............................................................. OFFSMOKE DISSIPATION.............................. CHECK If smoke continues:

GEN 2.......................................................... ONBUS TIE...................................................AUTO

REMOVAL OF SMOKE/FUMES.............. CONSIDEREMER ELEC CONFIG..............................CONSIDER

Ident.: ABN-26-A-00010512.0012001 / 21 MAR 11Applicable to: ALL

TO SET ELEC EMER CONFIGEMER ELEC PWR.......................................... MAN ONWHEN EMER GEN AVAIL:

GEN 1................................................................ OFFGEN 2................................................................ OFFAPU GEN...........................................................OFF

ELEC EMER CONFIGAPPLY ECAM PROCEDURE, BUT DO NOT RESETGEN, EVEN IF REQUESTED BY ECAM

26.01FA330-243F



06 DEC 16



AT 3 MIN OR 2 000 FT AAL BEFORE LANDING:ATT HDG SWTG.......................................F/O ON 3ALL GEN..............................................................ON

WHEN A/C IS STOPPED:ALL GEN............................................................OFF

26.02AA330-243F



06 DEC 16


REMOVAL OF SMOKE/FUMESIdent.: ABN-26-00010506.0005001 / 23 DEC 14Applicable to: ALL

CREW OXY MASKS...................................... USE/100%EMER EXIT LIGHT.................................................... ONCAB.....................................................................NOTIFYCAB OXY MASKS.............................................MAN ONCAB PR MODE SEL................................................MANMAN VALVE SEL.................................................... FWDMAN V/S CTL..........................................+ 4 000 FT/MNCAB ALT TGT.................................................20 000 FTDESCENT (FL 200, or MEA -MORA, or minimumobstacle clearance altitude)...............................INITIATEATC..................................................................... NOTIFYSMOKE/FUMES/AVNCS/MD SMOKE PROC........................................................................................CONTINUEWhile descending, continue applying the appropriatesteps of the SMOKE/FUMES/AVNCS /MD SMOKEpaper procedure depending on the suspected smokesource.At FL 200 or MEA-MORA:

PACK 1................................................................ OFFPACK 2.................................................... CHECK ONMAN V/S CTL.............................................. FULL UP

If smoke persists, cockpit window opening:MAX SPEED................................................... 230 KTCOCKPIT DOOR.............................................. OPENHEADSET.............................................................. ONPM COCKPIT WINDOW...................................OPEN

When window is open:VISUAL WARNINGS (noisy CKPT)........... MONITOR

26.02BA330-243F



06 DEC 16


REMOVAL OF SMOKE/FUMES (Cont'd)

SMOKE/FUMES/ AVNCS/MD SMOKE PROC.............................................................................CONTINUE

OXY PRESS................................................... MONITOR If low OXY PRESS:

DESCENT (FL 100, or MEA -MORA).......CONSIDERCAB SUPPLY.................................. CONSIDER OFF3RD AND 4TH CREW OXY MASKS......................................................................... CONSIDER STOWING

26.03AA330-243F



06 DEC 16


SMOKE/FIRE FROM LITHIUM BATTERYIdent.: ABN-26-00015935.0003001 / 18 JUN 15Applicable to: ALL

If necessary, transfer control to the flight crew member seated on the opposite sideof the fire If there are flames:

CREW OXY MASK (PF).................................................................................. USESMOKE HOOD (PM)........................................................................................USEHALON EXTINGUISHER................................................................................. USE

If there are no flames or when flames are extinguished: If not possible to remove device from the cockpit:

WATER or NON-ALCOHOLIC LIQUID............................... POUR ON DEVICEDEVICE..............................................................................................MONITOR

If possible to remove device from the cockpit:CKPT/CAB COM.............................................................................ESTABLISHDEVICE..............................................................TRANSFER TO CABIN AREARECEPTACLE.................. FILL WITH WATER OR NON-ALCOHOLIC LIQUIDDEVICE.............................................................................................. IMMERSERECEPTACLE...................................................... STORE IN THE LAVATORYRECEPTACLE................................................................................... MONITOR

AT ANY TIME of the procedure, if SMOKE becomes the GREATESTTHREAT:REMOVAL OF SMOKE/FUMES procedure........................................ CONSIDER

AT ANY TIME of the procedure, if situation becomes UNMANAGEABLE:IMMEDIATE LANDING........................................................................CONSIDER

BLANKA330-243F



06 DEC 16



27.01AA330-243F



06 DEC 16


LANDING WITH SLATS OR FLAPS JAMMEDIdent.: ABN-27-00010513.0001001 / 09 APR 15Applicable to: ALL

LANDING CONF......................................................................................DETERMINERefer to QRH PER-27A Landing Distance with Slats and Flaps System Failure, or use the LDG PERFapplication of FlySmart with Airbus. Repeat the following until landing configuration is reached:

SPEED SEL............................................................................. .VFE NEXT -5 KTSDecelerate towards VFE NEXT -5 kt but not below VLS . In case of turbulence, to avoid VFEexceedance, the pilot may decide to decelerate to a lower speed, but not below VLS.

Note: ‐ The autopilot may be used down to 500 ft AGL. As it is not tuned for the abnormalconfigurations, its behavior can be less than optimum and must be monitored

‐ Approach with A/THR and selected speed is recommended‐ The OVERSPEED warning, and VLS displayed on the PFD, are computed according to

the actual flaps/slats position‐ VFE and VFE NEXT are displayed on the PFD, according to the FLAPS lever position. If

not displayed, use the placard speeds‐ If VLS is greater than VFE NEXT (overweight landing case), the FLAPS lever can be

set in the required next position while the speed is reduced to follow VLS reductionas surfaces extend. The VFE warning threshold should not be triggered. In this case,disconnect the A/THR . A/THR can be reengaged when the landing configuration isestablished.

As speed reduces through VFE NEXT:FLAPS LEVER..........................................................................ONE STEP DOWNSet the FLAPS lever to a minimum of CONF 1, in order to enable engagement of the SRS guidancemode, in the case of a go-around. The SRS guidance mode may not engage if the landing gear is up.

When landing configuration is established:DECELERATE TO CALCULATED APPROACH SPEED IN FINAL APPROACH

FOR GO AROUND If SLATS FAULT:

For circuit:MAINTAIN SLATS/FLAPS CONFIGURATIONRecommended speed: MAX SPEED -10 kt

For diversion:SELECT CLEAN CONFIGURATION If SLATS jammed at 0:

Use normal operating speeds. If SLATS jammed > 0:

Recommended speed for diversion: MAX SPEED -10 ktIncreased fuel consumption.

If FLAPS FAULT: For circuit:

MAINTAIN SLATS/FLAPS CONFIGURATIONRecommended speed: MAX SPEED -10 kt

27.01BA330-243F



06 DEC 16


LANDING WITH SLATS OR FLAPS JAMMED (Cont'd)

For diversion: If FLAPS jammed at 0:

SELECT CLEAN CONFIGURATIONUse normal operating speeds.

If FLAPS jammed > 0:MAINTAIN SLATS/FLAPS CONFIGURATIONRecommended speed for diversion: MAX SPEED -10 ktIncreased fuel consumption.Note: ‐ In case the SPD LIM flag is displayed on the PFD , use the MAX SPEED

displayed on the ECAM status page‐ In case of a go-around with CONF FULL selected, the L/G GEAR NOT

DOWN warning is triggered at landing gear retraction‐ In some cases, MAX SPEED -10 KT may be a few knots higher than the VFE .

In this situation, pilots may follow the VFE.

MAX SPEED

FlapsSlats

F = 0 0 < F ≤ 1 1 < F ≤ 2 2 < F ≤ 3 F > 3

S = 0 NO LIMITATION

0 < S ≤ 1 240 kt215 kt

1 < S 215 kt 205 kt

196 kt 186 kt 180 kt

CAUTION For flight with SLATS or FLAPS extended, fuel consumption isincreased. Refer to the fuel flow indication.As a guideline, determine the fuel consumption in cleanconfiguration at the same altitude without airspeed limitation (e.g.From ALTERNATE FLIGHT PLANNING tables) and multiplythis result by the applicable Fuel Penalty Factor provided in theQRH, Refer to QRH PER-B Fuel Penalty Factors Tables, to obtainthe fuel penalty required to reach the destination in the currentconfiguration.

27.02AA330-243F



06 DEC 16


NO FLAPS NO SLATS LANDINGIdent.: ABN-27-00010514.0001001 / 28 FEB 14Applicable to: ALL

SPEED SEL............................................................................................ GREEN DOTInitial approach with autothrust and selected speed is recommended.Autopilot is allowed down to 500 ft AGL.GPWS FLAP MODE..............................................................................................OFFFLAPS LEVER................................................................................................ CONF 1Disregard the CONF 2 requirement on the ECAM status page.Set the FLAPS lever to CONF 1, in order to enable engagement of the SRS guidance mode, in the case ofa go-around. The SRS guidance mode may not engage if the landing gear is up.VFE displayed on the PFD depends on the FLAPS lever position, so a false VFE will be given.Plan a long stabilized approach. For final approach:

A/THR............................................................................................................... OFFSPD SEL........................................................................................................ VAPPSelect VLS on the PFD (or VREF + 50 kt, if VLS not available).At 500 ft, reduce speed to obtain VLS - 5 kt (or VREF + 45 kt, if VLS not available) at touchdown.LDG DIST PROC.........................................................................................APPLY

27.03AA330-243F



06 DEC 16


SIDESTICK / RUDDER PEDALS STIFFIdent.: ABN-27-00010515.0001001 / 23 DEC 14Applicable to: ALL

Even if the autopilot is disengaged, the sidesticks and/or the rudder pedals may be stiff. This may affecteither:‐ Both sidesticks (CAPT and F/O) at the same time, but not the rudder pedals or‐ One sidestick and the rudder pedals at the same time.The piloting technique remains the same: The aircraft remains responsive. However, the flight crew shouldkeep in mind that they may need to use extra force on the sidesticks and/or the rudder pedals.

AP DISENGAGEMENT................................................................................CONFIRMCONSIDER TRANSFERRING CONTROL TO PM For decrab, rollout, or engine failure:

BE PREPARED TO APPLY EXTRA FORCE ON RUDDER PEDAL

27.04AA330-243F



06 DEC 16


RUDDER JAM/RUDDER PEDAL JAMIdent.: ABN-27-00010516.0004001 / 03 JUN 14Applicable to: ALL

Use F/CTL SD page for a visual check of the rudder position.This procedure also applies in case of RUDDER PEDAL JAM.

FOR APPROACHAVOID LANDING WITH CROSSWIND from the side where the rudder isdeflected.FOR LANDING..................................................................................... USE FLAP 2GPWS FLAP MODE...........................................................................................OFF If all engines are operative:

SPEED and TRAJECTORY.....................................................STABILIZE ASAPLDG DIST PROC......................................................................................APPLY

In case of an engine-out:APPR SPEED.......................................................................................170 knotsSPEED and TRAJECTORY.....................................................STABILIZE ASAPAP + A/THR.................................................................................................. OFF In case of a go-around:

SPD.................................................................................. SELECT 170 knotsLDG DIST PROC......................................................................................APPLY

ON GROUNDDIFFERENTIAL BRAKING...................................................................... USE ASAPDo not use asymmetrical thrust reverseUse nosewheel steering handle below 100 kt, only in case of RUDDER PEDAL JAM.

27.05AA330-243F



06 DEC 16


RUDDER TRIM RUNAWAYIdent.: ABN-27-00010517.0002001 / 08 FEB 13Applicable to: ALL

LATERAL CONTROL............................................................ USE TO LEVEL WINGSRUDDER.................................................................................................CENTRALIZECheck the rudder position on the F/CTL SD page

Note: This failure will be seen mainly as uncommanded roll (induced by yaw). In most conditions,the aircraft will self stabilize in a steady heading sideslip. For continued flight, either maintainrudder central or leave the aircraft in a steady stabilized heading sideslip, but ensure that allchanges between rudder centralized and steady heading sideslip are made smoothly. As speedis reduced, the FCPC may allow more rudder to be applied by the trim runaway.

FOR LDG...................................................................................USE NORMAL CONF

28.01AA330-243F



18 JAN 17


FUEL IMBALANCEIdent.: ABN-28-00010520.0001001 / 24 FEB 14Applicable to: ALL

FOB.................................................................................................................. CHECKCompare the FOB + FU , with the FOB at departure. If the difference is significant, or if the FOB + FUdecreases, suspect a fuel leak.

CAUTION 1.A fuel imbalance may indicate a fuel leak. Do not apply thisprocedure, if a fuel leak is suspected. Refer to QRH ABN-28 FUELLEAK.

2.In the case of an ENG FEEDLINE BURST followed by an ENGSHUTDOWN, if fuel of the tank associated to the affected engineis required, do not open the WING XFEED valve and apply theprocedure below that corresponds to the case of the WING XFEEDvalve failed closed.

WING X FEED........................................................................................................ ON If the WING X FEED valve is open:

On the lighter side:(ALL) FUEL PUMPS (STBY then MAIN 1 and MAIN 2)............................. OFFNote: While pumps are OFF, disregard the corresponding FUEL WING PUMPS LO PR

ECAM caution.

When fuel balanced:PUMPS (MAIN 1 and MAIN 2 then STBY)...................................................ONWING X FEED..........................................................................................AUTO

If the WING X FEED valve is failed closed or in the case of an engine feedline burst:OUTR TK XFR................................................................................................... ONThis will connect the inner fuel tanks via the refuelling gallery.STRAIGHT FLIGHT................................................................................MAINTAINMaintain straight flight legs to apply this procedure.AP..................................................................................................................... OFFDisconnect the Auto Pilot to reach the targeted bank angle and the appropriate rudder position duringthe maneuver.BANK ANGLE.......................................3 DEG WING DOWN ON LIGHTER SIDEFuel transfer only occurs if the bank angle is at, or above, 2 ° to 3 °.USE RUDDER TO KEEP HDGAdjust rudder position to keep heading and neutral stick.RUDDER TRIM............................................................................AS NECESSARY When XFR completed:

OUTR TK XFR......................................................................................... AUTONORM ROLL ATTITUDE.....................................................................RETURNRUDDER TRIM...........................................................................NORMAL USEAP ON................................................................................................AS RQRD

28.02AA330-243F



18 JAN 17


FUEL LEAKIdent.: ABN-28-00010522.0010001 / 08 FEB 13Applicable to: ALL

A fuel leak may be detected by:‐ The sum of FOB and FU is significantly less than FOB at engine start, or is decreasing, or‐ A fuel spray is observed from an engine/pylon or a wing tip, or‐ The total fuel quantity is decreasing at an abnormal rate, or‐ A fuel imbalance is developing, or‐ Fuel quantity of a tank is decreasing too fast (leak from engine/pylon, or hole in a tank), or‐ A tank is overflowing (due to pipe rupture in a tank), or‐ The Fuel Flow is excessive (leak from engine).

WHEN A LEAK IS CONFIRMEDLAND ASAP Leak from engine/pylon confirmed:

Engine fuel leak can be confirmed by excessive fuel flow indication, or a visual check.

THR LEVER (of affected engine)................................................................. IDLEENG MASTER (of affected engine).............................................................. OFFWING X FEED............................................................................ USE AS RQRDIf the leak stops, the crossfeed valve can now be opened to re-balance fuel quantity, or to enableuse of fuel from both wings. Do not restart the engine.

Leak from engine/pylon not confirmed or leak not located:Stop any fuel transfer, and then monitor the depletion rate of each inner tank, to determine if the leakis from an engine or a wing (Case 1), or from the Trim tank, or the APU/Trim feeding line (Case 2).

WING X FEED.....................................................................MAINTAIN CLOSEDCrossfeed valve must remain closed to prevent the leak from affecting both sides.T TANK FEED.............................................................................................. ISOLINNER TANKS FUEL QUANTITIES....................................................MONITORMonitor the depletion rate of each inner tank. CASE 1: If one inner tank depletes faster than the other by at least

500 kg (1 100 lb) in less than 30 min:An engine leak may still be suspected. Therefore:THR LEVER (engine of affected inner tank)........................................... IDLEENG MASTER (engine of affected inner tank)........................................ OFFFUEL LEAK.................................................................................... MONITOR If leak stops:

If the fuel quantity of the affected inner tank stops decreasing, the engine leak is confirmedand stopped.T TANK FEED..................................................................................AUTOWING X FEED.................................................................. USE AS RQRDThe crossfeed valve can now be opened to re-balance fuel quantity, or to enable use of fuelfrom both wings. Do not restart the engine.

If leak continues (after engine shutdown):If the fuel quantity of the affected inner tank continues to decrease, a leak from the wingmay be suspected.

ENGINE RESTART.................................................................CONSIDERFUEL LOSS REDUCTION proc.............................................. CONSIDER

28.02BA330-243F



18 JAN 17


FUEL LEAK (Cont'd)

CAUTION Do not apply the FUEL IMBALANCE procedure. Approachand landing can be done, even with one full wing/one emptywing.

CASE 2: If both inner tanks deplete at a similar rate:A leak from the Trim tank or the APU/Trim feeding line may be suspected.APU (if ON).............................................................................................. OFFT TANK FEED...................................................................... MAINTAIN ISOLThis prevents additional fuel loss through the APU/Trim feeding line.

FOR LANDING

CAUTION Do not use reversers.

28.03AA330-243F



18 JAN 17


FUEL LOSS REDUCTIONIdent.: ABN-28-00010523.0005001 / 21 MAR 11Applicable to: ALL

Apply this procedure only if suggested by the FUEL LEAK procedure, and if the flight crew needs tominimize the fuel loss. It covers a leak from the wing :‐ A manual Trim tank transfer can be done, to symmetrically transfer fuel to both inner tanks, and avoid an

automatic fuel transfer to only the least full inner tank. If Trim Tank not empty:

T TANK FEED............................................................................................... AUTOT TANK MODE................................................................................................FWD When Trim Tank empty:

T TANK MODE.........................................................................................AUTOT TANK FEED............................................................................................ISOL

28.04AA330-243F



18 JAN 17



28.05AA330-243F



18 JAN 17


GRVTY FUEL FEEDINGIdent.: ABN-28-00010525.0006001 / 08 FEB 13Applicable to: ALL

ENG START SEL................................................................................................... IGNAVOID NEGATIVE G FACTORDETERMINE GRVTY FEED CEILINGConsult the following table to determine the flight altitude limitation.

Flight conditions at the time of gravity feeding Gravity feed ceiling

Flight time from takeoff more than 30 min (Fuel deaerated) 20 000 ft

Flight time from takeoff less than 30 min (Fuel non-deaerated) 15 000 ft7 000 ft for JP4 or JET B

DESCEND TO GRVTY FEED CEILING (if applicable) When reaching GRVTY feed ceiling:

WING X FEED.............................................................................................CLOSEINR UNUSABLE IF < 2 000 kg (4 400 lb)2 000 kg (4 400 lb) of fuel per affected tank cannot be used by gravity.

28.06AA330-243F



18 JAN 17


TRIM TANK FUEL UNUSABLEIdent.: ABN-28-00010526.0001001 / 14 SEP 12Applicable to: ALL

T TANK MODE.....................................................................................................FWDT TANK FEED.................................................................................................... OPEN If TRIM TANK FUEL is still unusable:

OUTR TK XFR................................................................................................... ONMAXIMUM FLIGHT TIME........................................................................4 HOURSAfter 4 h, depending on the fuel distribution, the aft CG limit may be reached.

FOR LANDING If CG > 39 %:

APPR SPD....................................................................................... VLS +10 KTLDG DIST PROC......................................................................................APPLYTo keep the nosewheel on the runway and prevent the aircraft from sitting on its tail, applycontinuous braking throughout the landing rollout.

BLANKA330-243F



18 JAN 17



29.01AA330-243F



18 JAN 17


HYD B+Y SYS LO PR SUMMARYCRUISE

Ident.: ABN-29-SUM1-00010527.0001001 / 09 APR 15Applicable to: ALL

MAX SPD............................................................................................................................................. 330/.82NO STABILIZER If TRIM locked above 8 UP:

MAX SPD.......................................................................................................................................180 KTMANEUVER WITH CAREALTN LAW : PROT LOSTFUEL: Increased fuel consumption (Refer to QRH PER-B)For Landing Performance assessment, Refer to QRH PER-C, or use the LDG PERF application ofFlySmart with Airbus.

APPROACHIdent.: ABN-29-SUM1-00010531.0001001 / 08 FEB 13Applicable to: ALL

CAT 2 INOPGPWS FLAP MODE................................................................................................................................. OFFFOR LANDING............................................................................................................................USE FLAP 2SLATS FLAPS SLOW L/G gravity extension:

MAX SPD.......................................................................................................................................200 KTL/G GRVTY EXTN......................................................................................................................... DOWN

When L/G down:L/G LEVER..................................................................................................................................... DOWN

LANDINGIdent.: ABN-29-SUM1-00010532.0003001 / 19 AUG 10Applicable to: ALL

FLARE: PITCH AUTHORITY REDUCED (No stabilizer)Only 2 spoilers per wing

SPOILERS: Only 2 per wingNO REVERSERBRAKING: NORMALNO NOSEWHEEL STEERING

GO-AROUNDIdent.: ABN-29-SUM1-00010533.0001001 / 28 APR 14Applicable to: ALL

NO GEAR RETRACTIONFUEL: Increased fuel consumption (Refer to QRH PER-B)

29.02AA330-243F



18 JAN 17


HYD G+B SYS LO PR SUMMARYCRUISE


SPD BRK...................................................................................................................................DO NOT USEMAX SPD............................................................................................................................................. 330/.82MANEUVER WITH CAREALTN LAW : PROT LOSTFUEL: Increased fuel consumption (Refer to QRH PER-B)For Landing Performance assessment, Refer to QRH PER-C, or use the LDG PERF application ofFlySmart with Airbus.

APPROACHIdent.: ABN-29-SUM2-00010537.0001001 / 08 FEB 13Applicable to: ALL

CAT 2 INOPSLATS JAMMED / FLAPS SLOWGPWS FLAP MODE (if Slats < 2)............................................................................................................OFF For landing:

If Slats < 2............................................................................................................................ USE FLAP 2If Slats ≥ 2............................................................................................................................ USE FLAP 3

For Flaps extension:SPD SEL...................................................................................................................... VFE NEXT - 5 KT



When in landing CONF and in final approach:DECELERATE TO CALCULATED VAPP

LANDINGIdent.: ABN-29-SUM2-00010538.0003001 / 29 MAR 11Applicable to: ALL

FLARE: Only one ELEV and 2 spoilers per wing.A/C slightly sluggish

SPOILERS: Only 2 per wingREVERSERS: Only N° 2BRAKING: B ACCU PRESS ONLY (7 applications)

NO ANTI-SKIDMAX BRK PR....................................................................................................................................1000 PSINO NOSEWHEEL STEERING


NO GEAR RETRACTION For circuit:

MAINTAIN SLATS/FLAPS CONFIGURATIONRecommended speed: MAX SPD - 10 kt / 200 kt

For diversion:SELECT CLEAN CONFIGURATION

29.02BA330-243F



18 JAN 17


Continued from the previous pageGO-AROUND

If Slats jammed at zero:Normal operating speeds (MAX SPD 200 kt)

If Slats jammed above zero:Recommended speed: 200 kt

FUEL: Increased fuel consumption (Refer to QRH PER-B)

29.03AA330-243F



18 JAN 17


HYD G+Y SYS LO PR SUMMARYCRUISE


SPD BRK...................................................................................................................................DO NOT USEMAX SPD............................................................................................................................................. 330/.82MANEUVER WITH CAREALTN LAW : PROT LOSTFUEL: Increased fuel consumption (Refer to QRH PER-B)For Landing Performance assessment, Refer to QRH PER-C, or use the LDG PERF application ofFlySmart with Airbus.

APPROACHIdent.: ABN-29-SUM3-00010543.0004001 / 04 AUG 15Applicable to: ALL

CAT 2 INOPSLATS SLOW / FLAPS JAMMEDGPWS FLAP MODE (If Flaps < 3 or 3 < Flaps < FULL)......................................................................... OFF For landing:

If Flaps < 3........................................................................................................................... USE FLAP 2If Flaps = 3........................................................................................................................... USE FLAP 3If Flaps > 3.....................................................................................................................USE FLAP FULL

For Slats extension:SPD SEL...................................................................................................................... VFE NEXT - 5 KT



When in landing CONF and in final approach:DECELERATE TO CALCULATED VAPP

LANDINGIdent.: ABN-29-SUM3-00010544.0003001 / 30 AUG 10Applicable to: ALL

FLARE: Only one ELEV and 2 spoilers per wing.A/C slightly sluggish

SPOILERS: Only 2 per wingREVERSERS: Only N°1BRAKING: ALTERNATENO NOSEWHEEL STEERING


NO GEAR RETRACTION For circuit: MAINTAIN SLATS/FLAPS CONFIGURATION

Recommended speed: MAX SPD - 10 kt / 200 kt For diversion:

If Flaps jammed at zero:SELECT CLEAN CONFIGURATION

29.03BA330-243F



18 JAN 17


Continued from the previous pageGO-AROUND

Normal operating speeds (MAX SPD= 200 kt) If Flaps jammed above zero:

MAINTAIN SLATS/FLAPS CONFIGURATIONRecommended speed: MAX SPD - 10 kt / 200 kt

FUEL: Increased fuel consumption (Refer to QRH PER-B)

BLANKA330-243F



18 JAN 17



30.01AA330-243F



06 DEC 16


DOUBLE AOA HEAT FAILUREIdent.: ABN-30-00010548.0002001 / 21 OCT 16Applicable to: ALL

In the case of double failure of alpha probe heaters, the choice made by the computers among the 3 ADRvalues may be erroneous.One of affected ADRs........................................................................................... OFFNAV ADR 1(2)(3) FAULTIn the case of disagreement between the two remaining ADR s, the NAV ADR DISAGREE ECAMcaution will trigger.

BLANKA330-243F



06 DEC 16



31.01AA330-243F



19 MAR 13


DISPLAY UNIT FAILUREIdent.: TDU / ABN-31-00014692.0002001 / 12 MAR 13Applicable to: ALL

DU is blank (with or without a large letter "F" in amber), or the display isdistorted, or DU brightness reduces to the minimum:DU (affected) brightness knob ..........................................................OFF then ONThe display will recover after 10 s. If unsuccessful:

DU (affected)......................................................................................AS RQRDThe DU can be switched off.ECAM/ND SEL (if ECAM DUs affected).....................................................USETransfer SD to F/O or CAPT ND.PFD/ND XFR (if EFIS DUs affected)..........................................................USE

INVALID DISPLAY UNIT message is displayed:This may be caused by a DU failure.FOR AUTOMATIC DU RECOVERY................................WAIT MORE THAN 40 s If DU is automatically recovered:

No crew action is required. If DU is not recovered:

Non-recovered DU ............................................................................AS RQRDThe DU can be switched off.

INVALID DATA message is displayed (not on all DUs):The failure may be due to a DMC FAULT, or a communication interruption between the DMC and DU.DMC SWITCHING (EFIS OR ECAM).....................................................AS RQRD If unsuccessful:

DU (affected)............................................................................. OFF THEN ONNote: ND display may disappear, in case too many waypoints and associated information

are displayed. Reduce the range, or deselect WPT or CSTR, and the display willautomatically recover after about 30 s.

INVALID DATA message is displayed on all DUs:The autopilot, autothrust and MCDU navigation data are still available and may be used.

FOR AUTOMATIC DUs RECOVERY.............................. WAIT MORE THAN 40 s If all DUs are automatically recovered:

No crew action is required. If one or more DUs are not recovered:

Non-recovered DUs....................................................................OFF FOR 40 sNon-recovered DUs....................................................... BACK ON sequentially If the initial failure re-occurs (INVALID DATA message appears on all

DUs) when switching a given DU back ON:Apply the entire procedure again from the beginning. Leave this specific DU permanently OFF.

31.01BA330-243F



19 MAR 13


DISPLAY UNIT FAILURE (Cont'd)

INVALID DATA message is displayed on the ECAM DUs (EWD and SD):ECAM DMC SWITCHING..................................................................................... 2This action enables the recovery of both ECAM DUs.

Inversion of E/WD and SD:ECAM UPPER DISPLAY................................................................OFF THEN ONThe action on the ECAM DMC SWITCHING selector produces the same effect.

31.02AA330-243F



19 MAR 13


ECAM SINGLE DISPLAYIdent.: ABN-31-00010551.0001001 / 08 FEB 13Applicable to: ALL

Only the EWD is available. No SD on the other DUs. To call a SYS page:

PRESS AND MAINTAIN the SYS page key on the ECP Overflow on the STATUS page:

PRESS AND MAINTAIN the STS key on the ECPThe first page of the STATUS is displayed.RELEASE IT, THEN PRESS IT AGAIN WITHIN 2 SECONDSThe second page of the STATUS is displayed.CONTINUE UNTIL THE OVERFLOW ARROW DISAPPEARSWhen the STS key is released for more than 2 s, the EWD is displayed again.

31.03AA330-243F



19 MAR 13


EIS DISPLAY DISCREPANCYIdent.: ABN-31-00010552.0001001 / 27 JAN 12Applicable to: ALL

CHECK EWDCHECK SDCHECK PFDCHECK NDThe DMC detects a discrepancy between acquisition and display on a DU.This caution is associated with an amber message displayed on the affected DU . In case of EWD displaydiscrepancy, the amber message is displayed on the EWD and on both NDs.DMC/DU SWTG........................................................................................... AS RQRDNote: The failure may be due to a DMC or DU problem.

The following part of the procedure is not displayed on ECAM: In case of CHECK EWD or CHECK SD:

ECAM SWTG DMC....................................................................................... 1 or 2DMC 1 or 2 may be selected if not failed. If unsuccessful:

Return to normal DMC configuration. In case of CHECK EWD:

ECAM UPPER DISPLAY....................................................................... OFFEWD is automatically transferred on SDU.ECAM/ND.................................................................................CAPT or F/OSD may be recovered on CAPT or on F/O NDU.

In case of CHECK SD:ECAM/ND......................................................................................AS RQRDECAM LOWER DISPLAY.............................................................AS RQRDThe DU can be switched off.

In case of CHECK PFD or CHECK ND:Crosscheck with standby instruments.EFIS DMC (affected side)..................................................................................... 3 If unsuccessful:

Return to normal DMC configuration.PFD/ND XFR (affected side)............................................................. AS RQRDDU (affected)......................................................................................AS RQRDThe DU can be switched off.

32.01AA330-243F



18 JAN 17


LOSS OF BRAKINGIdent.: ABN-32-00010553.0001001 / 08 FEB 13Applicable to: ALL

If no braking available:REV.................................................................................................................. MAXBRAKE PEDALS.....................................................................................RELEASEA/SKID & N/W STRG.......................................................................................OFFBRAKE PEDALS......................................................................................... PRESSMAX BRK PR........................................................................................... 1000 PSI

If still no braking:PARKING BRAKE...........................SHORT AND SUCCESSIVE APPLICATIONS

32.02AA330-243F



18 JAN 17



32.03AA330-243F



18 JAN 17


L/G GRAVITY EXTENSIONIdent.: ABN-32-00010555.0001001 / 07 MAR 13Applicable to: ALL

CAUTION Do not apply this procedure if at least one green triangle is displayedon each landing gear on the WHEEL SD page. This is sufficient toconfirm that the landing gear is downlocked. Disregard any possibleGPWS "TOO LOW GEAR" aural alert.

MAX SPEED..................................................................................................... 200 KTL/G GRVTY EXTN.............................................................................................DOWN

CAUTION Both selector guards have to be open before selecting DOWN. When L/G DOWNLOCKED

L/G lever.......................................................................................................DOWNGEAR DOWN indications............................................................................CHECK

CAUTION N/W STRG is lost. Main and nose gear doors remain open. If successful:

Do not reset the freefall system. This avoids undesirable effects, such as further fluid loss in the eventof a leak or possible L/G unlocking in the event of a gear selector valve jammed in UP position.

Note: Following the use of the freefall system for training purposes in flight, the system can bereset in flight. Provided that the green hydraulic system is available, a reset of the freefallsystem enables closure of the landing gear doors and operation of the nosewheel steering.

If unsuccessful:LDG WITH ABNORMAL L/G Procedure......................................................APPLYNote: 1. One gravity extension reset is allowed in case of L/G GEAR NOT

DOWNLOCKED alert display.2. On the ground the freefall system must not be reset by the flight crew.

32.04AA330-243F



18 JAN 17


LANDING WITH ABNORMAL L/GIdent.: ABN-32-00010556.0008001 / 22 APR 16Applicable to: ALL

CAUTION Do not apply this procedure if at least one green triangle is displayedon each landing gear on the WHEEL SD page. This is sufficient toconfirm that the landing gear is downlocked. Disregard any possibleGPWS "TOO LOW GEAR" aural alert.

PREPARATIONCABIN OCCUPANTS................................................................................... NOTIFYATC...............................................................................................................NOTIFYConsider fuel reduction to a safe minimum. If one MAIN L/G abnormal:

FUEL IMBALANCE............................................................................CONSIDEROpen all fuel XFEED and switch off the pumps on the side with landing gear normally extended.

OXYGEN CREW SUPPLY.................................................................................OFFSIGNS...................................................................................................................ONCABIN and COCKPIT...............................................................................PREPARE‐ Loose equipment secured‐ Survival equipment prepared‐ Belts and shoulder harnesses locked.

APPROACHGPWS SYS.........................................................................................................OFFL/G LEVER ......................................................................................CHECK DOWNL/G GRVTY EXTN.........................................................................................RESETAUTOBRAKE......................................................................................DO NOT ARMEMER EXIT LT.....................................................................................................ONCOMMERCIAL....................................................................................................OFFT TANK FEED................................................................................................... ISOLA/SKID & N/W STRG ........................................................................................OFFMAX BRAKE PR....................................................................................... 1 000 PSI If one or both MAIN L/G abnormal:

GROUND SPOILERS................................................................... DO NOT ARMBEFORE LANDING

RAM AIR ............................................................................................................. ONBRACE FOR IMPACT.................................................................................. ORDER

FLARE, TOUCH DOWN AND ROLL OUTEngines should be shut down sufficiently early to ensure fuel is shut off before the nacelles impact, butsufficiently late to ensure adequate hydraulic supplies for the flight controls.Engine pumps continue to supply adequate hydraulic pressure for 30 s after engine shutdown.

REVERSE........................................................................................... DO NOT USE If NOSE L/G abnormal:

NOSE............................................................................................ MAINTAIN UPAfter touchdown, keep the nose off the runway by using the elevator.Then, lower the nose onto the runway before elevator control is lost.

32.04BA330-243F



18 JAN 17


LANDING WITH ABNORMAL L/G (Cont'd)

BRAKES (compatible with elevator efficiency)......................................... APPLYENG MASTERS............................................................................................ OFFShut down the engines before nose impact.

If one MAIN L/G abnormal:ENG MASTERS (in sequence)..................................................................... OFFAfter main gear touchdown, shut down the engine on the failure side first, then the other enginebefore nacelle touchdown.FAILURE SIDE WING...................................................................MAINTAIN UPUse roll control, as necessary, to keep the unsupported wing up as long as possible.DIRECTIONAL CONTROL..................................................................MAINTAINUse rudder and brakes (maximum 1 000 PSI ) to maintain the runway axis as long as possible.

If both MAIN L/G abnormalENG MASTERS............................................................................................ OFFShut down the engines in the flare, before touchdown.PITCH ATTITUDE (at touchdown).....................................NOT LESS THAN 6 °

WHEN A/C STOPPEDPARK BRK........................................................................................................... ONENG (all) and APU FIRE pushbutton..............................................................PUSHPressing the ENG FIRE pb shuts off the related hydraulic pressure within a short time.ENG (all) and APU AGENT........................................................................... DISCH If Evacuation required:

EVACUATION........................................................................................ INITIATEALL BATs...................................................................................................... OFF

If Evacuation not required:CABIN OCCUPANTS (PA)......................................................................NOTIFYEnsure that all the landing gears are secured before initiating the disembarkation of the aircraft(before switching OFF the SEAT BELTS signs).

BLANKA330-243F



18 JAN 17



34.01AA330-243F



06 DEC 16


ABNORMAL V ALPHA PROTIdent.: ABN-34-00015281.0001001 / 08 DEC 14Applicable to: ALL

Refer to OEB-49 Abnormal V Alpha Prot

34.02AA330-243F



06 DEC 16


ADR CHECK PROCIdent.: ABN-34-00015215.0001001 / 30 NOV 15Applicable to: ALL

Apply the UNRELIABLE SPEED INDICATION procedure.

UNRELIABLE SPEED INDICATIONIdent.: ABN-34-D-00017854.0001001 / 30 NOV 15Applicable to: ALL

If the safe conduct of the flight is impacted:AP/FD.............................................................................................................. OFFA/THR.............................................................................................................. OFFPITCH/THRUSTBelow THRUST RED ALT...................................................................15° / TOGAAbove THRUST RED ALT and Below FL 100....................................... 10° / CLBAbove THRUST RED ALT and Above FL 100.........................................5° / CLBFLAPS (if CONF 0(1)(2)(3)).....................................MAINTAIN CURRENT CONFFLAPS (if CONF FULL)...................................SELECT CONF 3 AND MAINTAINSPEEDBRAKES..................................................................CHECK RETRACTEDL/G..................................................................................................................... UPWhen at or above MSA or Circuit Altitude: Level off for troubleshooting

Ident.: ABN-34-D-00017855.0001001 / 30 NOV 15Applicable to: ALL

To level off:AP/FD............................................................................................................... OFFA/THR............................................................................................................... OFFSPEEDBRAKES...................................................................CHECK RETRACTEDPITCH/THRUST TABLE...............................................................................APPLY


PITCH / THRUST FOR LEVEL OFF

240 t 200 t 160 t 120 t530 000 lb 440 000 lb 350 000 lb 260 000 lb

SLATS / FLAPS EXTENDED

CONF PITCH THRUST % N1 (Resultant speed)

3 7.5° 64% (170 kt) 60% (155 kt) 54% (135 kt) 50% (120 kt)

2 7.5° 62% (180 kt) 58% (165 kt) 54% (145 kt) 48% (125 kt)

1+F 6.5° 62% (205 kt) 58% (190 kt) 52% (170 kt) 46% (145 kt)

1 9.5° 60% (200 kt) 56% (185 kt) 52% (165 kt) 46% (140 kt)

CLEAN

PITCH FL THRUST % N1 (Resultant speed)

100 62% (285 kt) 58% (255 kt) 52% (225 kt) 48% (195 kt)4°at or below FL250 200 68% (280 kt) 64% (255 kt) 58% (225 kt) 52% (195 kt)

34.02BA330-243F



06 DEC 16


UNRELIABLE SPEED INDICATION (Cont'd)

PITCH / THRUST FOR LEVEL OFF

240 t 200 t 160 t 120 t530 000 lb 440 000 lb 350 000 lb 260 000 lb

300 76% (295 kt) 72% (275 kt) 68% (245 kt) 62% (215 kt)

350 / 76% (270 kt) 70% (245 kt) 64% (210 kt)3°

aboveFL250 400 / / 76% (235 kt) 70% (210 kt)

FLYING TECHNIQUE TO STABILIZE SPEEDStabilize the altitude. When altitude is stabilized:‐ If the pitch is above the target pitch, increase the thrust and maintain the altitude.‐ If the pitch is below the target pitch, decrease the thrust and maintain the altitude.When the pitch reaches the target pitch, adjust the thrust to keep this target pitch.


When flight path is stabilized:AP/FD............................................................................................................... OFFA/THR............................................................................................................... OFFSPEEDBRAKES...................................................................CHECK RETRACTEDFLIGHT PATH.......................................................................... KEEP STABILIZED

Respect Stall Warning and disregard “RISK OF UNDUE STALL WARNING”STATUS message if displayed on ECAM.

Ident.: ABN-34-D-00017911.0002001 / 28 SEP 16Applicable to: ALL

AFFECTED ADR IDENTIFICATIONPROBE/WINDOW HEAT......................................................................................ONALL SPEED INDICATIONS.......................................................................X CHECKADR3 and STBY speeds use the data of the same probe. If at least one ADR is confirmed reliable:

RELIABLE AIR DATA................................................................................... USEUNRELIABLE ADR P/B(s)............................................................................ OFF

If affected ADR(s) cannot be identified or all ADRs are affected: When above FL 250:

ONE ADR........................................................................................KEEP ONTWO ADR P/B(s)..................................................................................... OFFThis prevents the flight control laws from using two coherent but unreliable ADR data.For flight continuation, Refer to Pitch/Thrust Tables.

When below FL 250, if speed still unreliable:ALL ADR P/B(s)....................................................................................... OFFSPD.................................................................................... FLY THE GREENNAV ADR 1+2+3 FAULT Procedure................................................... APPLY

34.02CA330-243F



06 DEC 16




CLIMBCLIMB IN CLEAN CONFIGURATION

240 t 200 t 160 t 120 t530 000 lb 440 000 lb 350 000 lb 260 000 lb

THRUST FL PITCH (Resultant speed)

50 9° (280 kt) 10° (255 kt) 13° (220 kt) 17° (185 kt)

100 8° (280 kt) 9° (255 kt) 12° (220 kt) 16° (185 kt)

200 6° (280 kt) 7° (255 kt) 9° (225 kt) 12° (190 kt)

300 5° (275 kt) 5° (250 kt) 6° (225 kt) 8° (190 kt)

CLB

400 / / 5° (220 kt) 6° (190 kt)

CRUISEFLYING TECHNIQUE TO STABILIZE SPEEDStabilize the altitude. When altitude is stabilized:‐ If the pitch is above the target pitch, increase the thrust and maintain the altitude.‐ If the pitch is below the target pitch, decrease the thrust and maintain the altitude.When the pitch reaches the target pitch, adjust the thrust to keep this target pitch.

LEVEL FLIGHT IN CLEAN CONFIGURATION

240 t 200 t 160 t 120 t530 000 lb 440 000 lb 350 000 lb 260 000 lb

PITCH FL THRUST % N1 (Resultant speed)

100 62% (285 kt) 58% (255 kt) 52% (225 kt) 48% (195 kt)4°at or below FL250 200 68% (280 kt) 64% (255 kt) 58% (225 kt) 52% (195 kt)

300 76% (295 kt) 72% (275 kt) 68% (245 kt) 62% (215 kt)

350 / 76% (270 kt) 70% (245 kt) 64% (210 kt)3°

aboveFL250 400 / / 76% (235 kt) 70% (210 kt)

Note: If the failure is due to radome destruction, the drag will increase and therefore N1 must beincreased by 3% in cruise and 1.5% in approach.Fuel flow will increase by about 10%.

DESCENTDESCENT IN CLEAN CONFIGURATION

240 t 200 t 160 t 120 t530 000 lb 440 000 lb 350 000 lb 260 000 lb

THRUST PITCH Resultant speed

IDLE 2° 275 kt 250 kt 225 kt 195 kt

INITIAL / INTERMEDIATE APPROACHApply the FLYING TECHNIQUE TO STABILIZE SPEED

34.02DA330-243F



06 DEC 16



LEVEL FLIGHT WITH LANDING GEAR UP

240 t 200 t 160 t 120 t530 000 lb 440 000 lb 350 000 lb 260 000 lb

WITH LANDING GEAR UP

CONF PITCH THRUST % N1 (Resultant speed)

0 5° 58% (250 kt) 54% (225 kt) 50% (200 kt) 46% (180 kt)

1 9.5° 60% (200 kt) 56% (185 kt) 52% (165 kt) 46% (140 kt)

1+F 6.5° 62% (205 kt) 58% (190 kt) 52% (170 kt) 46% (145 kt)

2 7.5° 62% (180 kt) 58% (165 kt) 54% (145 kt) 48% (125 kt)

WITH LANDING GEAR DOWN

3 7.5° 68% (170 kt) 64% (155 kt) 58% (140 kt) 52% (120 kt)

FINAL APPROACH AT -3° DESCENT FLIGHT PATHAPPROACH IN CONF 3 AND L/G EXTENDED

240 t 200 t 160 t 120 t530 000 lb 440 000 lb 350 000 lb 260 000 lb

CONF PITCH THRUST (% N1)

3 4° 50% 48% 42% 38%

34.03AA330-243F



06 DEC 16


ALL ADR OFFIdent.: ABN-34-B-00019415.0032001 / 17 MAR 16Applicable to: ALL

SPD..................................................................................................FLY THE GREENFly within the green area of the speed scale to ensure safe flight. For slats/flaps retraction, it is better to flyat the top of the green area of the speed scale.

CAUTION The altitude displayed on the PFD is a GPS altitude.

MANUAL CABIN PRESSURE CONTROLMODE SEL........................................................................................................ MANMAN V/S CTL........................................................................................... AS RQRDMAN CAB PR CTLTGT V/S : CLIMB 500 FT/MIN

DESC 300 FT/MINA/C GPS ALT CAB ALT TGT

410350300250

<200

8 0006 5005 0002 500

0

FOR APPROACHSPD...............................................................................................FLY THE GREENBefore extending the slats/flaps, it is better to fly at the bottom of the speed scale green area, and to bein straight flight.FOR LDG..............................................................................................USE FLAP 3LDG DIST PROC........................................................................................... APPLYAPPR SPD.........................................................................................FLY THE BUGDuring the approach, the bug indicates Vapp. WHEN FLAP 2:

LDG GRVTY EXTN...................................................................................DOWN

CAUTION Nosewheel steering is lost. All gear doors remain open. WHEN L/G DOWNLOCKED:

L/G lever....................................................................................................DOWNGEAR DOWN indications........................................................................ CHECK

DURING FINAL APPROACH:MAN V/S CTL........................................................................................FULL UP

CAUTION Check that the outflow valve is fully open, and that cabin altitudeis at airfield elevation before opening the doors.

Ident.: ABN-34-B-00012367.0002001 / 17 MAR 16Applicable to: ALL

STATUSINOP SYS

The list of Inoperative Systems isdisplayed on the ECAM.

34.03BA330-243F



06 DEC 16


ALL ADR OFF (Cont'd)

Other INOP SYS

RAT automatic extensionNWSFLAP AUTO RETRACTFLAP LOAD RELIEFALPHA LOCKL/G RETRACT

34.04AA330-243F



06 DEC 16



34.05AA330-243F



06 DEC 16


NAV FM / GPS POS DISAGREEIdent.: ABN-34-00010562.0001001 / 08 FEB 13Applicable to: ALL

A/C POS...........................................................................................................CHECKThe following procedure is not displayed on the ECAM: If the ECAM alert is displayed during takeoff initiation:

Continue takeoff and monitor navigation. If the ECAM alert is displayed during Climb, Cruise, or Descent:

Check accuracy on the MCDU PROG page: If the ESTIMATED accuracy is below the REQUIRED accuracy:

NAV mode and ND ARC/ROSE NAV may be used. If the ESTIMATED accuracy is above the REQUIRED accuracy:

HDG/TRK mode and raw data must be used.When possible, compare the positions of both FMs with the GPIRS position, onthe MCDU POSITION MONITOR page: If one FM position agrees with the onside GPIRS position:

Use the associated AP/FD. If not:

Deselect GPS and use raw data. If the ECAM alert is displayed during ILS/LOC approach (LOC green):

Continue the approach. If the ECAM alert is displayed during a RNP approach:

Go around if visual references are not sufficient. If the ECAM alert is displayed during a GLS approach:

Go around if visual references are not sufficient. If the ECAM alert is displayed during a VOR, VOR-DME, NDB, or NDB-DME

approach:Select HDG or TRK, and use raw data.

34.06AA330-243F



06 DEC 16


IR ALIGNMENT IN ATT MODEIdent.: ABN-34-00010564.0001001 / 08 FEB 13Applicable to: ALL

If IR alignment is lost, the navigation mode is inoperative (red ATT flag on the PFD , and red HDG flag onthe ND).Aircraft attitude and heading may be recovered by applying the following procedure:MODE SELECTOR................................................................................................ ATTLEVEL AIRCRAFT ATTITUDE........................................................................... HOLDCONSTANT AIRCRAFT SPEED.................................................................MAINTAINAircraft must stay level, with constant speed, for 30 s.DATA (MCDU KEY)..........................................................................................PRESSDisplays the DATA INDEX page.IRS MONITOR (2L KEY)..................................................................................PRESSDisplays the IRS MONITOR page.AIRCRAFT HEADING.......................................................................................ENTERThe heading must be entered in the SET HDG field (5R key).Due to IRS drift, the magnetic heading must be periodically crosschecked with the standby compass andupdated, if required.

34.07AA330-243F



06 DEC 16


EGPWS WARNINGSIdent.: ABN-34-00017173.0004001 / 17 MAR 16Applicable to: ALL

"PULL UP" - "TERRAIN AHEAD PULL UP" - "OBSTACLE AHEAD PULL UP"Simultaneously:

AP.................................................................................................................... OFFPITCH......................................................................................................PULL UP

L2 Pull to full backstick and maintain in that position.L1 THRUST LEVERS........................................................................................TOGA

SPEED BRAKE lever..........................................................CHECK RETRACTEDBANK..........................................................................WINGS LEVEL or ADJUST

34.08AA330-243F



06 DEC 16


EGPWS CAUTIONSIdent.: ABN-34-00019414.0004001 / 17 MAR 16Applicable to: ALL

"TERRAIN TERRAIN" - "TOO LOW TERRAIN" - "TERRAIN AHEAD" - "OBSTACLE AHEAD" During night or IMC:

Simultaneously:

AP...............................................................................................................OFFPITCH.................................................................................................PULL UP

L2 Pull to full backstick and maintain in that position.L1 THRUST LEVERS...................................................................................TOGA

SPEED BRAKE lever.....................................................CHECK RETRACTEDBANK.....................................................................WINGS LEVEL or ADJUSTNote: For some airports, the operator may define a specific procedure.

During daylight and VMC with terrain and obstacles clearly in sight:FLIGHT PATH..................................................................................... ADJUST

L2 Adjust pitch, bank and thrust to silence the alert.L1

Note: For some airports, the operator may define a specific procedure.

"SINK RATE" Above 1 000 ft AAL in IMC or above 500 ft AAL in VMC:

FLIGHT PATH..................................................................................... ADJUSTL2 Adjust pitch and thrust to silence the alert.L1 Below 1 000 ft AAL in IMC or below 500 ft AAL in VMC:

GO-AROUND..................................................................................CONSIDER "DON'T SINK"

FLIGHT PATH.......................................................................................... ADJUSTL2 Adjust pitch and thrust to silence the alert.L1 "TOO LOW GEAR" - "TOO LOW FLAPS"

GO-AROUND........................................................................................PERFORM "GLIDE SLOPE"

Above 1 000 ft AAL in IMC or above 500 ft AAL in VMC:FLIGHT PATH..................................................................................... ADJUST

L2 Adjust pitch and thrust to reduce the vertical deviation from the glideslope.L1 When conditions require a deliberate approach below glideslope:

G/S MODE............................................................................................ OFF Below 1 000 ft AAL in IMC or below 500 ft AAL in VMC:

GO-AROUND..................................................................................CONSIDER

34.09AA330-243F



06 DEC 16


TCAS WARNINGSIdent.: ABN-34-00010565.0048001 / 07 JUN 16Applicable to: ALL

Traffic advisory: “TRAFFIC” messages:Do not perform a maneuver based on a TA alone.

Resolution advisory: All ″CLIMB″ and ″DESCEND″ or ″MAINTAINVERTICAL SPEED MAINTAIN″ or ″LEVEL OFF, LEVEL OFF″ or ″MONITORVERTICAL SPEED″ type messages:AP (if engaged)................................................................................................ OFFBOTH FDs........................................................................................................ OFFRespond promptly and smoothly to a RA by adjusting or maintaining the pitch, asrequired, to reach the green area and/or avoid the red area of the vertical speedscale.Note: Avoid excessive maneuvers while aiming to keep the vertical speed just

outside the red area of the VSI , and within the green area. If necessary,use the full speed range between Vαmax and VMAX.

Respect stall, GPWS, or windshear warning.Notify ATC. The GO AROUND procedure must be performed, when a RA “CLIMB” or

“INCREASE CLIMB” is triggered on final approach:Note: Resolution Advisories (RA) are inhibited below 900 ft.

When “CLEAR OF CONFLICT” is announced:Resume normal navigation in accordance with ATC clearanceAP/FD can be reengaged as desired.

BLANKA330-243F



06 DEC 16



36.01AA330-243F



18 JAN 17



36.02AA330-243F



18 JAN 17


AIR ENG 1+2 BLEED RESET (APU BLEED AVAILABLE)Ident.: ABN-36-00014556.0002001 / 04 AUG 15Applicable to: ALL

Apply this procedure when both engine bleed supply systems are failed and after the completion of theAIR ENG 1+2 BLEED FAULT ECAM procedure and when the APU Bleed supplies the aircraft.

CABIN PRESSURE MONITORMAX FL 220AVOID ICING CONDITIONS If no message associated with AIR ENG 1+2 BLEED FAULT

andIf no ENG BLEED lost due to ENG FIRE or Start Air Valve failed open:PACK 1............................................................................................................... OnPACK 2............................................................................................................... OnENG 1 BLEED....................................................................................................ONENG 2 BLEED....................................................................................................ONAPU BLEED..................................................................................................... OFF If no ENG BLEED recovered:

APU BLEED.................................................................................................. ON If PACK 1 available:

PACK 2.................................................................................................. OFFENG 1 BLEED.............................................................................................OFFENG 2 BLEED.............................................................................................OFF

If RIGHT LEAK message associated with AIR ENG 1+2 BLEED FAULTorIf ENG 2 BLEED lost due to ENG 2 FIRE or Start Air Valve 2 failed open:PACK 1............................................................................................................... OnENG 1 BLEED....................................................................................................ONAPU BLEED..................................................................................................... OFF If no ENG BLEED recovered:

APU BLEED.................................................................................................. ONENG 1 BLEED.............................................................................................OFF

36.03AA330-243F



18 JAN 17


AIR ENG 1+2 BLEED RESET (APU BLEED NOT AVAILABLE)Ident.: ABN-36-00014557.0001001 / 04 AUG 15Applicable to: ALL

Apply this procedure when both engine bleed supply systems are failed and after the completion of theAIR ENG 1+2 BLEED FAULT ECAM procedure and if no APU Bleed is available to supply theaircraft.

MAX FL 100/MEA-MORAAVOID ICING CONDITIONS If no message associated with AIR ENG 1+2 BLEED FAULT

andIf no ENG BLEED lost due to ENG FIRE or Start Air Valve failed open orAPU leak fed by engine:PACK 1............................................................................................................... OnPACK 2............................................................................................................... OnENG 1 BLEED....................................................................................................ONENG 2 BLEED....................................................................................................ON If no ENG BLEED recovered:

ENG 1 BLEED.............................................................................................OFFENG 2 BLEED.............................................................................................OFF

If only LEFT LEAK message associated with AIR ENG 1+2 BLEED FAULTorIf ENG 1 BLEED lost due to ENG 1 FIRE or Start Air Valve 1 failed open orAPU leak fed by engine:PACK 2............................................................................................................... OnENG 2 BLEED....................................................................................................ON If no ENG BLEED recovered:

ENG 2 BLEED.............................................................................................OFF If only RIGHT LEAK message associated with AIR ENG 1+2 BLEED FAULT

orIf only ENG 2 BLEED lost due to ENG 2 FIRE or Start Air Valve 2 failedopen:PACK 1............................................................................................................... OnENG 1 BLEED....................................................................................................ON If no ENG BLEED recovered:

ENG 1 BLEED.............................................................................................OFF If both LEFT LEAK and RIGHT LEAK messages associated with AIR ENG

1+2 BLEED FAULTorIf both ENG BLEEDs lost due to ENG FIRE or Start Air Valve failed open orAPU leak fed by engine:No ENG BLEED can be recovered.Consider unsuccessful.

36.03BA330-243F



18 JAN 17


AIR ENG 1+2 BLEED RESET (APUBLEED NOT AVAILABLE) (Cont'd)

If unsuccessful (no ENG BLEED recovered): When DIFF PR < 1 PSI

RAM AIR....................................................................................................... ON If severe ice accretion:

MIN SPD.................................................................................VLS+10 / G DOTMANEUVER WITH CARE

If severe ice accretion during approach:APPR SPD.......................................................................................VLS+10 KTLDG DIST PROC....................................................................................APPLY

70.01AA330-243F



18 JAN 17


ALL ENGINES FAILUREIdent.: ABN-70-01-00015499.0003001 / 04 AUG 15Applicable to: ALL

First apply the following actions of the ENG ALL ENGINES FAILURE ECAM procedure (if notalready applied):

LAND ASAPRAT................................................................................................................ MAN ONEMER ELEC PWR.........................................................................................MAN ONOPTIMUM RELIGHT SPEED......................................................................... 300/0.82

Ident.: ABN-70-01-00016584.0012001 / 04 AUG 15Applicable to: ALL

In the case of a speed indication failure due to volcanic ash, the pitch attitude for the optimum relight speedis:

WEIGHT Pitch (°)

At or below 150 000 kg -2.0

170 000 kg -1.5

190 000 kg -1.0

APU (below FL 250)......................................................................................... STARTTHR LEVERS....................................................................................................... IDLEGLIDING DISTANCE: 2 NM / 1000 FT

AT 300 KT: 2 NM / 1000 FT (500 FT/NM) NO WIND

Flight Level FL 200 FL 300 FL 400

Distance (NM) 40 60 80

DIVERSION.................................................................................................... INITIATECheck if there is an accessible runway, or determine the most appropriate area for a forced landing orditching.

..........................................................................................................................................................................Then, as long as none of the engines relights, apply the following paper procedure. If there is sufficienttime, clear all ECAM alerts, and clear the ECAM STATUS page.VHF1......................................................................................................................USEATC.................................................................................................................. NOTIFYCABIN OCCUPANTS...................................................................................... NOTIFYSIGNS......................................................................................................................ONCREW OXY MASK (FL > 100)............................................................................. USEFUEL QUANTITY............................................................................................. CHECK IF ENGINE RELIGHT CAN BE ATTEMPTED

Apply QRH 70.02A IF ENGINE RELIGHT CANNOT BE ATTEMPTED

(It includes the cases of no fuel remaining or engine damage)

Apply QRH 70.03A

70.02AA330-243F



18 JAN 17


ALL ENGINES FAILURE (Cont'd)


IF ENGINE RELIGHT CAN BE ATTEMPTEDENG START SEL................................................................................... IGN START APPROACHING OR BELOW FL 300: WINDMILL RELIGHT

ALL ENG MASTERS.......................................................... OFF 30 S THEN ONENGs RELIGHT..................................................................... TRY REGULARLYWindmill relight attempts can be repeated until successful, or until the APU bleed is available.APU (below FL 250) ................................................................................START IF APU AVAILABLE AND WINDMILL RELIGHT UNSUCCESSFUL:

STARTER ASSISTED RELIGHT BELOW FL 200ALL ENG MASTERS................................................................................OFFOPTIMUM SPEED: GREEN DOT (REFER TO TABLE BELOW)

GREEN DOT SPEED WITH ALL ENGINES INOPERATIVE (KNOTS)

Weight (1 000 kg) At or below FL 200 FL 300 FL 400

240 241 251 261

220 229 239 249

200 217 227 237

180 205 215 225

160 193 203 213

140 181 191 201

120 169 179 189

WING ANTI ICE....................................................................................... OFFAPU BLEED...............................................................................................ONENG MASTER (ONE AT A TIME).............................................................ONRelight only one engine at a time. Between each attempt to relight the same engine, wait atleast 30 s with the associated ENG MASTER lever set to OFF.

SPEED BRAKES AVAILABLE BELOW 10 000 FT AGL

CABIN AND COCKPIT........................................................................PREPARERAM AIR......................................................................................................... ONBARO REF (IF AVAIL)..................................................................................SETCOMMERCIAL...............................................................................................OFFELT (when conditions permit)................................................................... ONENGs RELIGHT..................................................................... TRY REGULARLYUSE RUDDER WITH CARE

IF DITCHING ANTICIPATEDApply QRH 70.04A

IF FORCED LANDING ANTICIPATEDApply QRH 70.05A

70.03AA330-243F



18 JAN 17




IF ENGINE RELIGHT CANNOT BE ATTEMPTED(It includes the cases of no fuel remaining or engine damage)

OPTIMUM SPEED: GREEN DOT (REFER TO TABLE BELOW)GREEN DOT SPEED WITH ALL ENGINES INOPERATIVE (KNOTS)

Weight (1 000 kg) At or below FL 200 FL 300 FL 400

240 241 251 261

220 229 239 249

200 217 227 237

180 205 215 225

160 193 203 213

140 181 191 201

120 169 179 189

GLIDING DISTANCE: 3 NM / 1000 FTAT GREEN DOT SPEED: 3 NM / 1000 FT (300 FT/NM) NO WIND

Flight Level FL 200 FL 300 FL 400

Distance (NM) 60 90 120

WING ANTI ICE................................................................................................. OFFAPU (below FL 250) .....................................................................................STARTAPU BLEED (below FL 200) .............................................................................. ONSPEED BRAKES AVAILABLE BELOW 10 000 FT AGL

CABIN AND COCKPIT........................................................................PREPARERAM AIR......................................................................................................... ONBARO REF (IF AVAIL)..................................................................................SETCOMMERCIAL...............................................................................................OFFELT (when conditions permit)................................................................... ONUSE RUDDER WITH CARE

IF DITCHING ANTICIPATEDApply QRH 70.04A

IF FORCED LANDING ANTICIPATEDApply QRH 70.05A

70.04AA330-243F



18 JAN 17




IF DITCHING ANTICIPATEDMIN RAT SPEED: 140 KTGPWS SYS.........................................................................................................OFFGPWS TERR......................................................................................................OFF At an appropriate altitude (above 3 000 FT AGL), configure the aircraft for

ditching.LAND RECOVERY..........................................................................................ONFOR LANDING................................................................................ USE FLAP 2EMER GEN is lost at slat extension. The aircraft is supplied only by the batteries.L/G LEVER........................................................................................ CHECK UPVAPP............................................................................................... DETERMINE

Weight 120 t 140 t 160 t 180 t 200 t 220 t 240 t

VAPP 150 kt 150 kt 153 kt 160 kt 167 kt 173 kt 180 kt


AT 2 000 FT AGLCABIN OCCUPANTS...................................................NOTIFY FOR DITCHINGDITCHING P/B................................................................................................ ONDitch the aircraft parallel to the swell. If that causes a strong crosswind, ditch the aircraft into thewind.

AT 500 FT AGLBRACE FOR IMPACT.............................................................................ORDERTOUCH DOWN AT MIN V/STARGET PITCH ATT 11 °

AT TOUCHDOWNALL ENG MASTERS.....................................................................................OFFAPU MASTER SW........................................................................................ OFF

AFTER DITCHINGATC (VHF 1)........................................................................................... NOTIFYALL FIRE P/Bs (ENG and APU)................................................................ PUSHALL AGENTS (ENG and APU)................................................................. DISCHEngine agent 2 is not available.EVACUATION........................................................................................ INITIATEALL BATs...................................................................................................... OFF

70.05AA330-243F



18 JAN 17




IF FORCED LANDING ANTICIPATEDDESCENT SLOPE (CONF 2, L/G DOWN): 1.7 NM / 1000 FT (600 FT/NM)MIN RAT SPEED: 140 KTGPWS SYS.........................................................................................................OFFGPWS TERR......................................................................................................OFF At an appropriate altitude (above 3 000 FT AGL), configure the aircraft for

landing.LAND RECOVERY..........................................................................................ONFOR LANDING................................................................................ USE FLAP 2EMER GEN is lost at slat extension. The aircraft is supplied only by the batteries.MAX SPEED for GRAVITY EXTENTION...................................................200 ktL/G GRVTY EXTN.................................................................................... DOWNDisregard the "USE MAN PITCH TRIM" message on the PFD, because the stabilizer is jammed,due to not sufficient hydraulic power. When L/G downlocked:

L/G LEVER...........................................................................................DOWNVAPP............................................................................................... DETERMINEAdjust the speed to the VAPP indicated in the table below. However, to reach the landing field orrunway, it is possible to increase the approach speed.

Weight 120 t 140 t 160 t 180 t 200 t 220 t 240 t

VAPP 150 kt 150 kt 153 kt 160 kt 167 kt 173 kt 180 kt

GND SPLRs..................................................................................................ARMMAX BRK PR: 1 000 PSI


AT 2 000 FT AGLCABIN OCCUPANTS.................................................... NOTIFY FOR LANDING

AT 500 FT AGLBRACE FOR IMPACT.............................................................................ORDER

AT TOUCHDOWNALL ENG MASTERS.....................................................................................OFFAPU MASTER SW........................................................................................ OFFBRAKES ON ACCU ONLY

WHEN AIRCRAFT STOPPEDPARKING BRK................................................................................................ONATC (VHF 1)........................................................................................... NOTIFYALL FIRE P/Bs (ENG and APU)................................................................ PUSHALL AGENTS (ENG and APU)................................................................. DISCHEngine agent 2 is not available.

70.05BA330-243F



18 JAN 17



IF EVACUATION REQUIREDEVACUATION...................................................................................INITIATEALL BATs................................................................................................. OFF

IF EVACUATION NOT REQUIREDCABIN OCCUPANTS (PA)................................................................ NOTIFY

70.06AA330-243F



18 JAN 17


ENG RELIGHT (IN FLIGHT)Ident.: ABN-70-00010571.0004001 / 11 MAR 13Applicable to: ALL

MAX GUARANTEED ALTITUDE................................................................. 30 000 FTENG MASTER (affected engine)...........................................................................OFFTHR LEVER (affected engine)................................................................CHECK IDLEENG START SEL................................................................................................... IGNX BLEED.............................................................................................................OPENWING ANTI ICE (for starter assisted start)...........................................................OFFENG MASTER (affected engine)............................................................................ ONBe aware that contrary to autostart on ground, the crew must take appropriate action in case of abnormalstart.Engine light up should be achieved within 30 seconds after fuel flow increases.‐ Monitor N3‐ If not certain about successful relight, move the thrust lever forward and check engine response. When idle reached (AVAIL indication pulses in green):

ENG START SEL......................................................................................... NORMTCAS MODE SEL.............................................................................. check TA/RACheck that the selector is at TA/RA since if the ENG SHUT DOWN procedure has been applied, theTCAS mode selector may have been set at TA position.Affected SYS.......................................................................................... RESTORERestore affected systems and set the XBLEED selector to AUTO.

If no relight:ENG MASTER (affected engine)..................................................................... OFF

70.06BA330-243F



18 JAN 17


ENG RELIGHT (IN FLIGHT) (Cont'd)

70.07AA330-243F



18 JAN 17


ENG 1(2) STALLIdent.: ABN-70-A-00010572.0004001 / 08 FEB 13Applicable to: ALL

A stall may be indicated by varying degrees of abnormal engine noises, accompanied by flame from theengine exhaust (and possibly from engine inlet in severe cases), fluctuating performance parameters,sluggish or no thrust lever response, high EGT and/or a rapid EGT rise when thrust lever is advanced.Engine stalls must be reported for maintenance action. Stall is detected by the FADEC:

If in flight:THR LEVER (affected engine)................................................................... IDLEENG PARAMETERS (affected engine)................................................. CHECK If abnormal:

ENG MASTER (affected engine)........................................................... OFF If on ground:

THR LEVER (affected engine)................................................................... IDLEENG MASTER (affected engine)................................................................ OFF

If the crew detects a stall before the ECAM activation:The following procedure may be applied:THR LEVER (affected engine)........................................................................ IDLEENG PARAMETERS (affected engine)...................................................... CHECK If abnormal parameters:

ENG MASTER (affected engine)................................................................ OFF

ENG 1(2)SHUT DOWN

Apply ENG SHUT DOWN procedure.Engine restart at crew discretion.

If normal parameters:ENG A ICE (affected engine)....................................................................... ONWING A ICE..................................................................................................ONOperation of ENG and WING A ICE will increase the stall margin but EGT increases accordingly.THR LEVER (affected engine)..........................................SLOWLY ADVANCE If stall does not reoccur:

CONTINUE ENG OPERATION

70.08AA330-243F



18 JAN 17


ENG TAILPIPE FIREIdent.: ABN-70-00010574.0004001 / 08 FEB 13Applicable to: ALL

CAUTION External fire agents can cause severe corrosive damage and shouldtherefore, only be considered after having applied the followingprocedure :

ENG MASTER (affected).......................................................................................OFFAIR BLEED PRESS.................................................................................. ESTABLISHBEACON..................................................................................................................ON When N3 < 30 %:

ENG START SEL........................................................................................CRANKMAN START.......................................................................................................ON When burning has stopped:

MAN START................................................................................................OFFENG START SEL.................................................................................... NORM

70.09AA330-243F



18 JAN 17


HIGH ENGINE VIBRATIONIdent.: ABN-70-00010575.0004001 / 21 JUL 14Applicable to: ALL

The ECAM ’s VIB advisory mainly serves as a guideline for the flight crew to monitor engine parametersmore closely.The ECAM vibration advisory alone does not require engine shut down.

Note: 1. High engine vibration may be accompanied by cockpit and cabin smoke and/or the smell ofburning. This may be due only to compressor blade tip contact with associated abradableseals.

2. High N1 vibration are generally accompanied by perceivable airframe vibrations.High N2 /N3 vibration can occur without perceivable airframe vibrations.

ENG PARAMETERS........................................................................................CHECKCheck engine parameters and especially EGT; crosscheck with other engine. Report in maintenancelogbook. If icing is suspected:

An increase of N1 vibration in icing conditions with or without engine anti ice may be due to fan bladesand/or spinner icing. Icing may be suspected if N1 vibration occurs without other engine parametersvariation.A/THR............................................................................................................... OFFENG ANTI ICE............................................................................................CHECKIf ENG ANTI ICE is still off, switch it ON at idle fan speed, one engine after the other withapproximately 30 s interval.THRUST (one engine at a time)....................................... IDLE THEN INCREASEReduce thrust to idle if flight conditions permit.To shed ice, it may be necessary to perform several thrust variations between idle and a thrustcompatible with the flight phase. For efficient ice shedding, thrust should be increased to at least 80%N1 if flight conditions permit.After each thrust variation, vibrations should decrease, indicating the progress of the ice shedding.When the ice is shed, vibrations should return to normal and the flight crew can resume normal engineoperation.

If icing is not suspected: If above vibration advisory:

THRUST (affected engine)..................................................................REDUCEIf flight conditions permit, reduce thrust to maintain vibration level below the advisory threshold. Ifthe VIB indication does not decrease following thrust reduction, this may indicate other problemson the engine.

Note: If possible, shut down the engine after landing for taxing, if vibrations above the advisorythreshold are, or have been experienced.

70.10AA330-243F



18 JAN 17


SUSPECTED ENG FUEL SYS CONTAMINATIONIdent.: ABN-70-00013978.0001001 / 08 FEB 13Applicable to: ALL

This procedure must be applied if one of the two following conditions is encountered. In that case, a fuelcontamination can be highly suspected. If ECAM caution ENG 1(2) CTL SYS FAULT is triggered with the associated

message “AVOID RAPID THRUST CHANGE” or “ENG 1(2) SLOWRESPONSE”, and with rapid and continuous EPR fluctuation indications onboth engines:A/THR............................................................................................................... OFF If EPR fluctuations on both engines stop:

ECAM PROC.......................................................................................... APPLYA/THR............................................................................................... KEEP OFF

If EPR fluctuations on both engines continue:ENG FUEL SYS CONTAMINATION PROC........................................... APPLY

If ECAM cautions ENG 1 CTL SYS FAULT and ENG 2 CTL SYS FAULT aretriggered with the associated message “AVOID RAPID THRUST CHANGE”or “ENG 1(2) SLOW RESPONSE”:A/THR............................................................................................................... OFFENG FUEL SYS CONTAMINATION PROC................................................ APPLY

ENG FUEL SYS CONTAMINATIONIdent.: ABN-70-00013979.0001001 / 24 FEB 14Applicable to: ALL

This procedure must be applied if a fuel contamination has been confirmed by the application of the Referto QRH ABN-70 Suspected ENG Fuel Sys Contamination procedure. This fuel contamination may result,in the worst case, in a loss of engine thrust control. This procedure aims at maintaining the thrust on oneengine while minimizing the thrust changes on the other, in order to prevent contaminant from blocking themechanical devices of engine thrust regulation.In case of ENG 1(2) CTL SYS FAULT on only one engine:‐ Set and maintain the thrust on the engine affected by the ECAM caution‐ Minimize the thrust changes on the engine not affected by the ECAM cautionIn case of ENG 1 and 2 CTL SYS FAULT (both engines affected by the ECAM caution):‐ Set and maintain the thrust on the first engine affected by the ECAM caution‐ Minimize the thrust changes on the second engine affected by the ECAM caution

WHEN FUEL CONTAMINATION IS CONFIRMEDLAND ASAPA/THR...................................................................................................... KEEP OFFMAN THR (ECAM affected or 1st ECAM affected engine)........SET and MAINTAINSet the thrust (N1) on the applicable engine according to the following table. This thrust should bemaintained until final approach.

THRUST SETTING (N1)

GROSS WEIGHT (1 000 kg )

120 130 140 150 160 170 180 190 200 210 220 230 240

N1 (%) 58.1 58.7 59.4 60.1 60.8 61.6 62.5 63.3 64.1 65.0 65.9 66.8 67.7

70.10BA330-243F



18 JAN 17


ENG FUEL SYS CONTAMINATION (Cont'd)

For cruiseMAN THR (Non ECAM affected or 2nd ECAM affected engine)..............................................................................................................................SET AS RQRDMinimize thrust changes on the applicable engine.

DescentMAN THR (Non ECAM affected or 2nd ECAM affected engine)..................IDLESPD BRK............................................................................................. AS RQRDManage the descent using speed brakes as necessary so as to perform a level-off at approximately3 000 ft AGL and 20 NM from the runway threshold.ATC..........................................................................................................NOTIFYNotify ATC to ensure runway availability for landing.

Approach At a suitable altitude (approximately 3 000 ft AGL):

LEVEL OFF...................................................................................... INITIATEAIRCRAFT ...............................................................CONFIGURE FOR LDGTo decelerate the aircraft, manage early gear extension and/or use speed brakes in order to befully configured when intercepting the final approach path.

FOR LDG..................................................................................USE FLAP FULL Final approach

TARGET SPD............................................................................................. VAPPWhen fully configured, if the speed trend decreases below VAPP, adjust the thrust on the Nonaffected ECAM or 2nd ECAM affected engine. In case of overspeed adjust the thrust on the ECAMaffected or 1st ECAM affected engine.

LandingNORMAL OPS...................................................................................... RESUMEResume normal operations: Retard thrust levers as usual, select reverse thrust and apply brakes asrequired.

BLANKA330-243F



18 JAN 17



80.01AA330-243F



06 MAR 17


CIRCLING APPROACH WITH ONE ENGINE INOPERATIVEIdent.: ABN-80-00010581.0014001 / 08 FEB 13Applicable to: ALL

LANDING WEIGHT.......................................................................................... CHECK If the aircraft weight is above the maximum weight for circling in CONF 3

(given in the table below) :The aircraft cannot maintain flight level with CONF 3 and landing gear down.Delay gear extension.Note: ‐ If the approach is flown at less than 750 ft RA , the warning “L/G NOT DOWN” will be

triggered. The pilot can cancel aural warning by pressing the EMER CANC pb on theECAM control panel.

‐ ”TOO LOW GEAR” warning is to be expected, if the landing gear is not downlocked at500 ft RA.

MAXIMUM WEIGHT FOR CIRCLING IN CONF 3 (1000 KG)

AIRPORT ELEVATION (feet)OAT(°C) 0 2 000 4 000 6 000 8 000 10 000 12 000 14 000

0 232 224 214 208 200 192 182 170

5 232 224 214 208 200 192 178 158

10 232 224 214 208 200 186 172 158

15 232 224 214 208 194 180 168 156

20 232 224 214 202 188 174 158 150

25 232 224 210 196 182 168 156 146

30 232 218 202 188 174 158 150

35 224 208 194 180 168 156

40 216 200 186 174

45 206 192 178

50 198 184

55 190

80.02AA330-243F



06 MAR 17


BOMB ON BOARDIdent.: ABN-80-00010582.0012001 / 17 MAR 16Applicable to: ALL

IF POSSIBLE, LAND AND EVACUATE THE AIRCRAFT IMMEDIATELY.If it is not possible to land and evacuate the aircraft within 30 min, apply the following procedures:

COCKPIT PROCEDURESBACKGROUND

To avoid the activation of an altitude-sensitive bomb, the cabin altitude should not exceed the value atwhich the bomb has been discovered.To reduce the effects of the explosion, the aircraft should fly as long as possible with approximately1 PSI differential pressure, to help the blast go outwards. 1 PSI differential pressure corresponds to a2 500 ft difference between the aircraft and the cabin altitude.These conditions are achieved by using the manual pressure control.

PROCEDUREThe following procedure assumes that it is initiated during climb or cruise:

First, maintain the cabin altitude using manual pressure mode.While maintaining the cabin altitude, descend the aircraft to the cabin altitude +2 500 ft and maintain ΔP at 1 PSI.During further steps of descent, maintain ΔP at 1 PSI using the cabin V/S targetselector.During the approach, use automatic pressure mode in order to reduce thedifferential pressure to zero at touchdown.If flight conditions are different, the crew should adapt the procedure, bearing in mind theabove-mentioned principles (background paragraph).

AIRCRAFT (if climbing).......................................................................LEVEL OFFCABIN PRESS MODE SEL............................................................................MANCAB ALT................................................................................................MAINTAINCABIN OCCUPANTS................................................................................ NOTIFYATC/COMPANY OPERATIONS................................................................NOTIFYFUEL RESERVES.............................................................................DETERMINEKeep in mind that when flying at cabin altitude + 2 500 ft, the fuel consumption in CONF 1, withlanding gear down, will be about 2.1 times that consumed in clean configuration.NEXT SUITABLE AIRPORT..............................................................DETERMINEFCU SPEED SELECTION KNOB..............................................PULL AND TURNSelect the most appropriate speed, taking into account the time to destination, the fuel consumptionand the fact that low speed could reduce the consequences of possible structural damage, if the bombexplodes.

80.02BA330-243F



06 MAR 17


BOMB ON BOARD (Cont'd)

DESCENT TO CAB ALT + 2 500 ft or MEA or minimum obstacle clearance altitude................................................................................................................. INITIATEAVOID SHARP MANEUVERSCAB ALT................................................................................................MAINTAIN When at CAB ALT + 2 500 ft:

1 PSI ΔP...........................................................................................MAINTAINGALLEY/LAV FAN......................................................................................OFFFLAPS (fuel permitting)..................................................... AT LEAST CONF 1For landing, use normal configuration.LANDING GEAR (fuel permitting, except for flight over water)..............DOWN

For any other steps of descent:1 PSI ΔP...........................................................................................MAINTAIN

During approach:CABIN PRESS MODE SEL.................................................................... AUTO

When the aircraft on ground and stopped in a remote area (if possible): If evacuation required :

EVACUATION................................................................................INITIATEAvoid exits and exiting on the same side as the bomb and near the bomb.Notify the cabin occupants about the emergency encountered and the intentions.Press the EVAC COMMAND pb .ALL BATs.............................................................................................. OFF

If evacuation not required :CABIN OCCUPANTS (PA)............................................................. NOTIFY

80.03AA330-243F



06 MAR 17


DITCHINGIdent.: ABN-80-00010583.0047001 / 04 AUG 15Applicable to: ALL

This procedure applies when engines are running. If engines are not running, Refer to QRH ABN-70 ALLENGINES FAILURE - IF DITCHING ANTICIPATED, which has been amended to include the ditchingprocedure, when the engines are not running.

PREPARATIONATC/TRANSPONDER (if available)................................... NOTIFY/SELECT A7700Notify ATC of the nature of emergency and state intentions. Select transponder code A7700 or transmitthe distress message on: (VHF ) 121.5 MHz or (HF) 2 182 kHz or 8 364 kHz.CABIN and COCKPIT...............................................................................PREPARE‐ Loose equipment secured.‐ Survival equipment prepared.‐ Belts and shoulder harnesses locked.GPWS SYS.........................................................................................................OFFGPWS TERR......................................................................................................OFFSIGNS...................................................................................................................ONEMER EXIT LT.....................................................................................................ONCOMMERCIAL....................................................................................................OFFLDG ELEV.............................................................................................. SELECT 00BARO.................................................................................................................. SETOmit the normal approach and landing checklist.CREW MASKS/OXY SUPPLY (below FL 100)..................................................OFFELT (when conditions permit).............................................................................. ON

APPROACHL/G lever............................................................................................................... UPSLATS and FLAPS.................................................................................MAX AVAIL

AT 2 000 FT AGLCAB PRESS MODE SEL...................................................................CHECK AUTOBLEED (ENGs and APU)................................................................................... OFFCABIN................................................................................NOTIFY FOR DITCHINGDITCHING pushbutton......................................................................................... ONPrefer ditching parallel to the swell.If that causes a strong crosswind, ditch into the wind.In all cases, touch down with a pitch attitude of approximately 11 °.Minimize aircraft vertical speed.

AT 500 FT AGLBRACE FOR IMPACT.................................................................................. ORDER

AT TOUCHDOWNENG MASTERS..................................................................................................OFFAPU MASTER SWITCH.....................................................................................OFF

AFTER DITCHINGATC (VHF 1).................................................................................................NOTIFYFIRE pushbutton (ENG and APU)...................................................................PUSHAGENTS (ENG and APU)..............................................................................DISCH

80.03BA330-243F



06 MAR 17


DITCHING (Cont'd)

EVACUATION............................................................................................. INITIATENotify the cabin crew about the emergency encountered and the intentions.Press the EVAC COMMAND pb .ALL BATs............................................................................................................OFF

80.04AA330-243F



06 MAR 17


FORCED LANDINGIdent.: ABN-80-00010584.0048001 / 04 AUG 15Applicable to: ALL

This procedure is applicable if the engines are running.If the engines are not running, Refer to QRH ABN-70 ALL ENGINES FAILURE - IF FORCED LANDINGANTICIPATED: It provides the applicable forced landing procedure if the engines are not running.

PREPARATIONATC/TRANSPONDER (if available)................................... NOTIFY/SELECT A7700Notify ATC of the nature of emergency and state intentions. Select transponder code A7700, or transmitthe distress message on: (VHF ) 121.5 MHz or (HF) 2 182 kHz or 8 364 kHz.CABIN and COCKPIT...............................................................................PREPARE‐ Loose equipment secured‐ Survival equipment prepared‐ Belts and shoulder harnesses locked.GPWS SYS ....................................................................................................... OFFGPWS TERR......................................................................................................OFFSIGNS...................................................................................................................ONEMER EXIT LT.....................................................................................................ONCOMMERCIAL....................................................................................................OFFLDG ELEV.......................................................................................................... SETBARO.................................................................................................................. SETOmit the normal approach and landing checklist.CREW MASKS/OXY SUPPLY (below FL 100)..................................................OFFELT (when conditions permit).............................................................................. ON

APPROACHRAM AIR...............................................................................................................ONL/G lever.........................................................................................................DOWNSLATS and FLAPS.................................................................................MAX AVAILGND SPLR.........................................................................................................ARMMAX BRK PR............................................................................................. 1000 PSI

AT 2 000 FT AGLCABIN OCCUPANTS......................................................... NOTIFY FOR LANDING

AT 500 FT AGLBRACE FOR IMPACT.................................................................................. ORDER

AT TOUCHDOWNENG MASTERS..................................................................................................OFFAPU MASTER SW............................................................................................. OFFBRAKES ON ACCU ONLY

AFTER LANDING When the aircraft has stopped :

PARKING BRK................................................................................................ONATC (VHF 1)........................................................................................... NOTIFYFIRE pushbutton (ENG and APU)..............................................................PUSHAGENTS (ENG and APU).........................................................................DISCH

80.04BA330-243F



06 MAR 17


FORCED LANDING (Cont'd)

If Evacuation required :EVACUATION...................................................................................INITIATEALL BATs................................................................................................. OFF

If Evacuation not required :CABIN OCCUPANTS (PA)................................................................ NOTIFY

80.05AA330-243F



06 MAR 17


EMER DESCENTIdent.: ABN-80-00010585.0005001 / 18 MAY 16Applicable to: ALL

CREW OXY MASKS............................................................................................ USESIGNS.....................................................................................................................ONEMER DESCENT..........................................................................................INITIATE If A/THR is not active:

THR LEVERS................................................................................................. IDLESPD BRK............................................................................................................ FULLWHEN DESCENT ESTABLISHED

SPEED.....................................................................................MAX/APPROPRIATE

CAUTION Descend at the maximum appropriate speed. If structural damageis suspected, use the flight controls with care and reduce speed asappropriate.

Landing gear may be extended. In such a case, speed must be reduced to VLO/VLE.ENG START SEL................................................................................................ IGNATC...............................................................................................................NOTIFYNotify ATC of the nature of the emergency, and state intention. The flight crew can communicate withthe ATC using voice, or CPDLC when the voice contact cannot be established or has poor quality.EMER DESCENT (PA)......................................................................... ANNOUNCEThe flight crew must inform the cabin of emergency descent on the PA system.ATC XPDR 7700.....................................................................................CONSIDERSquawk 7700 unless otherwise specified by ATC.‐ To save oxygen, set the oxygen diluter selector to the N position‐ If the oxygen diluter selector remains set to 100 %, oxygen quantity may be insufficient to cover the

entire emergency descent profile‐ Ensure that crew communication is established with oxygen masks. Avoid the continuous use of the

interphone to minimize interference with the breathing noise in the oxygen mask.MAX FL........................................................................................... 100/MEA-MORA If CAB ALT is above 14 000 ft:

CAB OXY MASKS................................................................................. MAN ONNote: Notify the cabin crew, when the aircraft reaches a safe flight level, and when cabin

oxygen is no more necessary.

80.06AA330-243F



06 MAR 17


OVERSPEED RECOVERYIdent.: ABN-80-00014729.0001001 / 16 APR 14Applicable to: ALL

As soon as the speed exceeds VMO /MMO, apply the following actions:

AP : KEEP ONSPEED BRAKE LEVER...............................................................................AS RQRDNote: The use of speed brakes results in a reduction of the speed envelope.

THRUST REDUCTION................................................................................ MONITOR If the A/THR is OFF:

ALL THR LEVERS...........................................................................................IDLE If the AP automatically disengages:

HIGH SPEED PROTECTION : ACTIVE IN NORM LAWThe activation of the high speed protection results in an automatic pitch up in order to reduce thespeed. While the speed is above VMO/MMO:

SPEED BRAKE LEVER : AS RQRDPITCH ATT.................................................... ADJUST SMOOTHLY AS RQRD

When the speed is below VMO/MMO with a sufficient margin to VMO/MMO:SPEED BRAKE LEVER..........................................................................AS RQRD If the A/THR is OFF:

ALL THR LEVERS...................................................................... MAN ADJUST If the AP is OFF:

FLIGHT PATH............................................................. RECOVER SMOOTHLY In the case of severe turbulence:

Refer to QRH OPS - Severe Turbulence

80.07AA330-243F



06 MAR 17


OVERWEIGHT LANDINGIdent.: ABN-80-00010586.0019001 / 17 MAR 16Applicable to: ALL

Automatic landing is certified up to the Maximum Landing Weight (MLW). Autoland flight tests have,however, been successful up to 229 t.Depending on the situation (e.g. emergency or other) and provided that the runway is approved forautomatic landing, the flight crew can decide to perform an autoland up to 229 t.

LDG CONF.......................................................................................... AS REQUIREDUse the ECAM flap setting, if required for abnormal operations.In all other cases:‐ FULL is preferred for optimized landing performance‐ If the aircraft weight is above the maximum weight for go-around (given in the table below), use FLAP 3

for landing.In all cases, if the landing configuration is different from FLAP FULL, use 1 + F for go-around.LDG DIST.........................................................................................................CHECKPACK 1 and 2.......................................................................OFF or supplied by APUSelecting packs OFF (or supplied from APU) will increase the maximum thrust available from the engines,in the event of a go-around. In the final stages of approach:

TARGET SPEED.............................................................................................. VLSReduce speed to reach VLS at runway threshold.Touch down as smoothly as possible (Maximum V/S at touchdown 360 ft/min).

At main landing gear touchdown:REVERSE THRUST........................................................... USE MAX AVAILABLE

After nosewheel touchdown:BRAKES..........................................................................APPLY AS NECESSARYMaximum braking may be used after nosewheel touchdown. But, if landing distance permits, delay orreduce braking to take full benefit of the available runway length.

Landing complete:BRAKE FANS.................................................................................. ON if availableBe prepared for tire deflation, if temperatures exceed 800 °C.

MAXIMUM WEIGHT FOR GO AROUND IN CONF 3 (1000 KG) CLIMB GRADIENT 2.1 %

OAT (°C) AIRPORT ELEVATION (FT)

0 2 000 4 000 6 000 8 000 10 000 12 000 14 000

10 240 232 223 209 196 180 164 148

15 240 232 223 209 194 176 160 144

20 240 232 223 207 191 171 155 140

25 240 232 221 205 188 166 150 136

30 240 232 216 200 182 161 146

35 240 224 208 192 176

40 233 216 199 184

45 222 205 189

50 211 195

55

80.08AA330-243F



06 MAR 17


STALL RECOVERYIdent.: ABN-80-00013762.0001001 / 15 JUN 15Applicable to: ALL

As soon as any stall indication (could be aural warning, buffet...) is recognized, apply the immediateactions:NOSE DOWN PITCH CONTROL..................................................................... APPLYThis will reduce angle of attack

Note: In case of lack of pitch down authority, reducing thrust may be necessary.

BANK....................................................................................................WINGS LEVEL When out of stall (no longer stall indications) :

THRUST.....................................................INCREASE SMOOTHLY AS NEEDEDNote: In case of one engine inoperative, progressively compensate the thrust asymmetry with

rudder.

SPEEDBRAKES...................................................................CHECK RETRACTEDFLIGHT PATH.................................................................. RECOVER SMOOTHLY If in clean configuration and below 20 000 ft :

FLAP 1..................................................................................................SELECTNote: If a risk of ground contact exists, once clearly out of stall (no longer stall indications),

establish smoothly a positive climb gradient.

STALL WARNING AT LIFTOFFIdent.: ABN-80-00013763.0001001 / 08 FEB 13Applicable to: ALL

Spurious stall warning may sound in NORMAL law, if an angle of attack probe is damaged. In this case,apply immediately the following actions:THRUST..............................................................................................................TOGAAT THE SAME TIME:

PITCH ATTITUDE..................................................................................................15 °BANK....................................................................................................WINGS LEVELNote: When a safe flight path and speed are achieved and maintained, if stall warning continues,

consider it as spurious.

80.09AA330-243F



06 MAR 17


TAILSTRIKEIdent.: ABN-80-00010587.0001001 / 04 AUG 15Applicable to: ALL

In the event of a tailstrike, apply the following procedure:

LAND ASAPMAX FL.............................................................................................. 100/MEA-MORALimit to FL 100 or to MEA or MORA in order to minimize structural stress.Return to the airport for damage assessment.

80.10AA330-243F



06 MAR 17


VOLCANIC ASH ENCOUNTERIdent.: ABN-80-00010588.0007001 / 06 SEP 16Applicable to: ALL

If the aircraft enters a volcanic ash cloud:180 ° TURN.............................................................................................. INITIATEATC.............................................................................................................NOTIFYA/THR............................................................................................................... OFFTHRUST (conditions permitting)...............................................................REDUCECREW OXYGEN MASKS............................................................ON/100 %/EMERCABIN OCCUPANTS................................................................................. NOTIFYPASSENGER OXYGEN..........................................................................AS RQRDENG ANTI ICE................................................................................................... ONWING ANTI ICE................................................................................................. ONPACK FLOW........................................................................................................ HINote: If CARGO VENTILATION system is installed, it is recommended to switch off the CARGO

ISOL VALVES, to prevent a cargo smoke warning being triggered.

ENGINE PARAMETERS........................................................................ MONITORAIRSPEED INDICATIONS......................................................................MONITORIf airspeed is unreliable or lost, Refer to QRH ABN-34 UNRELIABLE SPEED INDICATION procedure.

Note: If both engines flame out and speed indications are lost, Refer to QRH ABN-70 ALLENGINES FAILURE procedure to get the required pitch attitude for the optimum relightspeed.In case of engine failure, switch off the wing anti ice before engine restart.

Note: If visibility is insufficient for approach due to windshield/window damage, considerAUTOLAND. If AUTOLAND is not available, consider opening the sliding window on thePF’s side (maximum speed 230 kt), after cabin depressurization. To manually depressurizethe cabin:

CAB PRESS MODE selector.............................................................MANMAN V/S CTL............................................................................. FULL UPDue to the increased noise level, pay particular attention to visual warnings.

80.11AA330-243F



06 MAR 17


WINDSHEARIdent.: ABN-80-00010589.0001001 / 10 JUN 13Applicable to: ALL

A red flag “WINDSHEAR” message is displayed on each PFD, associated with an aural “WINDSHEAR”message, repeated three times.If windshear is detected, either by the system or by pilot observation, apply the following recoverytechnique: At takeoff:

If before V1:The takeoff should only be rejected if significant airspeed variations occur below indicated V1, andthe pilot decides that there is sufficient runway remaining to stop the airplane.

If after V1:THR LEVERS...........................................................................................TOGAREACHING VR.................................................................................... ROTATESRS ORDERS.....................................................................................FOLLOWIf necessary, the flight crew may pull the sidestick fully back

Note: If the FD bars are not displayed, move toward an initial pitch attitude of 17.5 °. Then ifnecessary, to prevent a loss in altitude, increase the pitch attitude.

Airborne initial climb or landing:THR LEVERS AT TOGA..........................................................SET OR CONFIRMAP (if engaged)....................................................................................... KEEP ONSRS ORDERS..........................................................................................FOLLOWIf necessary, the flight crew may pull the sidestick fully back

Note: 1. Autopilot disengages if the angle of attack values goes above α prot.2. If the FD bars are not displayed, move toward an initial pitch attitude of 17.5 °. Then if

necessary, to prevent a loss in altitude, increase the pitch attitude.

DO NOT CHANGE CONFIGURATION (SLATS/FLAPS, GEAR) UNTIL OUT OFWINDSHEAR.CLOSELY MONITOR FLIGHT PATH AND SPEED.RECOVER SMOOTHLY TO NORMAL CLIMB OUT OF WINDSHEAR.

80.12AA330-243F



06 MAR 17


WINDSHEAR AHEADIdent.: ABN-80-00010590.0002001 / 09 APR 15Applicable to: ALL

The “W/S AHEAD” message is displayed on each PFD. The color of the message depends on the severityand location of the windshear.

Note: When a predictive windshear alert (″WINDSHEAR AHEAD″ or ″GO AROUND WINDSHEARAHEAD″) is triggered, if the flight crew makes a positive verification that no hazard exists, thenthe alert may be disregarded, as long as:‐ There are no other signs of possible windshear conditions, and‐ The reactive windshear system is operational.Known cases of spurious predictive windshear alerts have been reported at some airports,during either takeoff or landing, due to the specific obstacle environment. However, always relyon any reactive windshear (″WINDSHEAR″).

W/S AHEAD RED Takeoff:

Associated with a synthetic aural voice: “WINDSHEAR AHEAD, WINDSHEAR AHEAD”. Before takeoff:

Delay takeoff, or select the most favorable runway. During takeoff run:

Reject takeoff.Note: The predictive windshear alerts are inhibited above 100 kt, until

50 ft. When airborne:

THR LEVERS........................................................................................TOGAAs usual, the slat/flap configuration can be changed, provided the windshear is not entered.AP (if engaged)...............................................................................KEEP ONSRS ORDERS..................................................................................FOLLOWIf necessary, the flight crew may pull the sidestick fully back.

Note: 1. Autopilot disengages if the angle of attack values goes above α prot.2. If the FD bars are not displayed, move toward an initial pitch attitude of 17.5 °.

Then if necessary, to prevent a loss in altitude, increase the pitch attitude.

Landing:Associated with a synthetic aural voice: “GO AROUND, WINDSHEAR AHEAD”.GO AROUND......................................................................................PERFORMAP (if engaged).................................................................................... KEEP ONIf necessary, the flight crew may pull the sidestick fully back.

Note: 1. Autopilot disengages if the angle of attack values goes above α prot.2. If the FD bars are not displayed, move toward an initial pitch attitude of 17.5 ° . Then, if

necessary, to prevent a loss in altitude, increase the pitch attitude.

W/S AHEAD AMBERApply precautionary measures, as indicated below: Before takeoff:

Delay Takeoff until conditions are improved.

80.12BA330-243F



06 MAR 17


WINDSHEAR AHEAD (Cont'd)

"Assess conditions for a safe Takeoff by":• Using observations and experience,• Checking weather conditions.Select the most favorable runway (considering location of the likely windshear).Use the weather radar or the predictive windshear system, before the takeoffrun, to ensure a flight path clear of any potential problem areas.Select TOGA thrust.Closely monitor airspeed and airspeed trend during the takeoff run to detectearly signs of windshear.

During approach:Delay landing or divert to another airport until conditions are more favorable."Assess conditions for a safe landing by":• Using observations and experience,• Checking weather conditions.Use the weather radar or predictive windshear system.Select the most favorable runway, in conjunction with the most appropriaterunway approach aid.Select FLAPS 3.Use managed speed in approach phase.Check both FDs engaged in ILS, GLS ,FPA or V/SEngage autopilot, for more accurate approach and earlier information of beamdeviation when ILSor GLS available.Note: ‐ When using the GS mini function, associated with managed speed,

the system will carry extra speed in strong wind conditions.‐ In the case of strong or gusty crosswind greater than 20 kt, Refer to

QRH PER-C VAPP Determination without Failure , or use the LDGPERF application of FlySmart with Airbus for VAPP determination.

80.13AA330-243F



06 MAR 17


COCKPIT WINDSHIELD / WINDOW ARCINGIdent.: ABN-80-00010591.0001001 / 08 FEB 13Applicable to: ALL

Affected WINDSHIELD/WINDOW WHC reset button..........................................PULLPull the Window Heat Computer reset button that is located on the affected side, in case of :‐ Electrical arcing of the cockpit windshield/window, or‐ Burning smell or smoke identified as coming from the bottom left corner of CAPT windshield or bottom

right corner of the F/O windshield.• WINDSHIELD/WINDOW LEFT SIDE - WHC 1 (261 VU)• WINDSHIELD/WINDOW RIGHT SIDE - WHC 2 (262 VU).

80.14AA330-243F



06 MAR 17


COCKPIT WINDSHIELD / WINDOW CRACKEDIdent.: ABN-80-00010893.0001001 / 04 AUG 15Applicable to: ALL

DIAGNOSIS OF INNER PLY......................................................................PERFORMTouch the crack(s) with a pen (or carefully with fingernail) to determine if there is a crack on the cockpitside. If no crack on cockpit side:

No limitationThe inner ply is not affected. Therefore, the window/windshield is still able to sustain the differentialpressure up to the maximum flight level.

If cracks on cockpit side:MAX FL......................................................................................... 230/MEA-MORAThe inner ply is affected. The flight crew is not able to easily determine if other plies are affected.Descend to FL 230/MEA-MORA and reduce differential pressure to 5 PSI.

Note: The maximum flight level is restricted to FL 230/MEA -MORA to obtain ΔP 5 PSI, withoutresulting in an excessive cabin altitude and an EXCESS CAB ALT warning.

The following procedure enables maintaining ΔP 5 PSI in manual cabin pressure mode:CAB PRESS MODE SEL................................................................................ MANMAN V/S CTL......................................................................................... AS RQRDDisregard the CAB ALT TARGET table displayed on the ECAM and set the cabin altitude according tothe table below:

FL 100 150 200 230ΔP = 5 PSI

CABIN ALTITUDE 0 3 000 6 000 8 000

When starting the descent for approach:CAB PRESS MODE SEL......................................................................... AUTO

Note: If visibility is insufficient for approach due to windshield/window damage, consider AUTOLAND.If AUTOLAND is not available, consider opening the sliding window (maximum speed 230 kt) onthe PF’s side, after cabin depressurization. To manually depressurize the cabin:CAB PRESS MODE SEL....................................................................... MANMAN V/S CTL.................................................................................. FULL UPDue to the increased noise level, pay particular attention to visual warnings.

80.15AA330-243F



06 MAR 17


ECAM ADVISORY CONDITIONSSYSTEM CONDITIONS RECOMMENDED ACTION

Ident.: ABN-80-A-00010592.0001001 / 08 FEB 13Applicable to: ALL

CAB VERT SPDV/S > 1 800 ft/min or V/S < -1 800 ft/min

CPC changeover is recommended, MODE SEL : MANAFTER 3 s, MODE SEL: AUTO

CAB ALTALT ≥ 8 800 ft

MODE SEL : MANManual pressure controlCAB PRESS

ΔP ≥ 1.5 PSI in phase 7 LDG ELEV: ADJUSTif unsuccessful, MODE SEL : MANManual pressure control

CONDPACK LO FLOWPack flow not sufficient to satisfytemperature demand.

PACK FLOW: INCREASE

Ident.: ABN-80-A-00010594.0001001 / 28 AUG 15Applicable to: ALL

ELEC

IDG OIL TEMPT > 151 °C

Reduce IDG load, if possible (GALLEY or GEN OFF).If required, restore when temperature has dropped.Restrict use of the generator to a short time, if temperature risesagain excessively.


FUEL Difference between L and R wing fuelquantities is greater than 3 000 kg (6 614 lb)

FUEL MANAGEMENT: CHECKIf a fuel leak is suspected, Refer to QRH ABN-28 FUEL LEAK.

Ident.: ABN-80-A-00010596.0016001 / 20 SEP 13Applicable to: ALL

OXY/DOOR

CKPT & CAB OXYPulses Green:When pressure is < 1 200 PSIAmber:When pressure is < 200 PSI

If cockpit masks are not being used check that they are correctlystowed.


LOW OIL LEVEL The APU may be started and operated for 15 h, if there is no oil leak.APU EGT high

(inhibited during APU start)


OIL QTY < 4 US QTS If oil quantity is low at high power setting, expect level increase afterpower reduction.

NAC TEMP > 260 °C Monitor engine parameters and crosscheck with other engine.ENG VIBRATION

N1 ≥ 3.3 unitsN2 ≥ 2.6 unitsN3 ≥ 4.0 units

Refer to QRH ABN-70 High Engine Vibration.

80.16AA330-243F



06 MAR 17


TRIPPED C/B RE - ENGAGEMENTIdent.: ABN-80-00010640.0001001 / 21 MAR 11Applicable to: ALL

TRIPPED C/B REENGAGEMENTIn flight, do not reengage a circuit breaker (C/B) that has tripped by itself, unless the Captain judges itnecessary to do so for the safe continuation of the flight. This procedure should be adopted only as a lastresort, and only one reengagement should be attempted.On ground, do not reengage the C/B of the fuel pump(s) of any tank. For all other C/B s, if the flight crewcoordinates the action with maintenance, the flight crew may reengage a tripped C/B , provided that thecause of the tripped C/B is identified.

80.17AA330-243F



06 MAR 17


COMPUTER RESET - GENERALIdent.: ABN-80-00010641.0001001 / 06 DEC 16Applicable to: ALL

RESET OF COMPUTERSThis table lists the computers that may be reset following abnormal behavior, or a detected fault.Most of the computers’ reset capability is provided on the overhead RESET panel: Those with an asterisk*are reset on the system control panel.To reset a computer:‐ Set the related normal cockpit control OFF, or pull the corresponding reset pb,‐ Wait 3 s, if a normal cockpit control is used (unless a different time is indicated), or 1 s if a reset pb is

used,‐ Set the related normal cockpit control ON, or push the corresponding reset pb,‐ Wait 3 s for the end of the reset.

WARNING Do not reset more than one computer at a time, unless instructedto do so.

Note: The flight crew should report any in-flight reset to the maintenance.

The following table lists the various computers for which manual reset capability is provided:• On the overhead RESET panels,• On the system control panel.

WARNING The flight crew can attempt a computer reset only when:‐ An ECAM /OEB /TDU procedure requests to reset the system, or‐ The Computer Reset Table permits to reset the system.

Manual reset on ground triggers complete power up test.

Note: In flight, before taking any action on the reset buttons, the PF and PM must crosscheck andverify that the reset button corresponds to the affected system.

80.18AA330-243F



06 MAR 17


COMPUTER RESET TABLEATA EQUIPMENT REMARKS

Ident.: ABN-80-F-00010642.0002001 / 21 AUG 13Applicable to: ALL

PACK CONT

ZONE CONT

AEVC

NIL

VENT CONT If, in flight, the SMOKE CAB REST SMOKE warning hasbeen temporarily displayed and identified as a false warning, crew restcompartment ventilation may be recovered by resetting both VENT controllerchannels (simultaneously pull both ventilation controller RESET pb for atleast 5 s, then push them).

21 CPC To force a CPC changeover:‐ SELECT MAN MODE SEL

AFTER 3 s:‐ SELECT AUTO MODE SEL

The inactive CPC may then be reset (check the CAB PRESS SD page ).

During the reset phase, the following cabin effects may occur:‐ cabin lights may come on at full intensity‐ cabin chimes may sound

Ident.: ABN-80-F-00010645.0001001 / 06 JAN 16Applicable to: ALL

FCU ‐ In flight:• When PART FCU is displayed as INOP SYS, do not reset the FCU• When FCU is displayed as INOP SYS , check FCU targets after the

reset‐ On ground:

• The flight crew can reset the FCU when either FCU or PART FCU isdisplayed as INOP SYS

• The FCU has to be reconfigured after the reset

Note: Following a total FCU reset either in flight or on ground, FCUtargets are FCU entries (selected modes).

FMGEC and FM FMGEC or FM resets result in onside AP disconnection (if engaged).

Resynchronization of both FM s will occur after a reset sequence, withassociated messages on the MCDU and ND :‐ PLEASE WAIT‐ MAP NOT AVAIL

It is recommended to use the FMGEC reset pb , rather than the FM reset pb.

Note: Due to electrical transient, MANUAL FMGES RESET proceduremay be unsuccessful. If so and on ground, the flight crew mayattempt the same procedure with engines not running.

For more information, Refer to FCOM/PRO-SUP-22-10 Automatic FMGESReset and Resynchronization - FM Reset

22

MCDU blank or locked ‐ Set MCDU (affected) to OFF‐ Wait 10 s‐ Set MCDU (affected) to ON

Note: Wait after the message "PLEASE WAIT" disappears before usingMCDU.

80.18BA330-243F



06 MAR 17


Continued from the previous pageATA EQUIPMENT REMARKS

Ident.: ABN-80-F-00016076.0001001 / 17 NOV 16Applicable to: ALL

CIDS In the event of active CIDS reset (usually CIDS 1 when both are operative), acomplete power-up test is performed:‐ In flight, the test lasts about 20 s:

• The cabin light comes on at full intensity.If selected, dimming is lost and must be reselected after the test.

• PA, CALL, and INTERPHONE functions are interrupted and have to bereselected after the test.

• FAP cabin temperature corrections are lost, and have to be reselectedafter the test.

‐ On ground, the test lasts about 80 s, and also includes:• A sequential cabin loudspeakers’ test (triggers a tone for about 10 s).• The cabin light may flash briefly. Dimming selection is lost (as in flight).

Note: After a CIDS reset is performed, the following messages may bedisplayed temporarily on the ECAM:

‐ SMOKE LAVATORY DET FAULT‐ SMOKE VIDEO 1(2)(3)(4) DET FAULT

ACP /AMU NIL

RMP * In case of freezing of one RMP (impossibility to interchange the ACTIVE andSTBY radio navigation or communication frequencies,...), all the RMPs haveto be reset, one after the other, to recover a normal operation.In order to be reset, RMP s must be switched off at least 5 s by using theON/OFF selector on the RMP control panels.

23

PAX SATCOM SYSTEM PAX SATCOM system may be reset when PAX communication systemis lost. The PAX SATCOM system can be reset by switching the PAXSATCOM pushbutton OFF for at least 1 s and then on.Wait 5 min, and then perform the CINS reset (Refer to QRH ABN-80Computer Reset Table - 46 - Information System).

Ident.: ABN-80-F-00010647.0001001 / 23 JUN 15Applicable to: ALL

GPCU /GAPCU * GPCU /GAPCU reset may be attempted, if the AVAIL and ON lights do notlight up.1. Press once the affected EXT A(B) pb to reset the functions of GPCU

/GAPCU.2. Check the GPU is connected to the aircraft, then started.3. Check AVAIL light is ON and press the EXT A(B) pb to connect the GPU.

If unsuccessful, check GPU voltage and frequency (bite is available onbatteries only).

24

BCL * Use BAT pb to reset the BCL.Do not reset the BCL when ELEC BAT 1(2) FAULT caution istriggered, and BAT OFF selection is requested by the ECAM.

80.18CA330-243F



06 MAR 17



Ident.: ABN-80-F-00010648.0001001 / 21 MAR 11Applicable to: ALL

25

Commercial equipments andgalleys On ground

When the commercial equipment and/or galley loads have been shedby the ECMU, they can be recovered when more electrical power isavailable.

If COMMERCIAL OFF is displayed on the ELEC SD page:Switch the COMMERCIAL pb OFF then ON.

IF GALLEY SHED or GALLEY PARTIALLY SHED is displayed on theELEC SD page:

Switch the GALLEY pb OFF then ON.

Do not reset more than one pushbutton at a time.

Ident.: ABN-80-F-00010649.0002001 / 25 APR 12Applicable to: ALL

26

Smoke detection function of theCIDS-SDF On ground

‐ Pull both SDF1 (261VU) and SDF2 (262VU) reset buttons‐ Wait 10 s‐ Push both SDF1 and SDF2 reset buttons.‐ Wait 3 min for the system restart to be completed.

In flight‐ Pull both SDF1 (261VU) and SDF2 (262VU) reset buttons‐ Wait 3 s‐ Push both SDF1 and SDF2 reset buttons.‐ Wait 1 min for the system restart to be completed.

Ident.: ABN-80-F-00010650.0002001 / 21 AUG 13Applicable to: ALL

PRIM and SEC * ‐ PRIM /SEC may be reset, except in the following case:• The ELEC DC BUS 2 FAULT caution is present.

Note: Do not attempt a reset because this would result in a loss ofrelated PRIM /SEC

‐ If a reset is performed on ground, it must be followed by a flight controls’check

WARNING Do not reset more than onecomputer at a time.

Note: When a PRIM reset is performed on ground, the crew mustcheck the pitch trim position.

27

FCDC NIL

80.18DA330-243F



06 MAR 17



Ident.: ABN-80-F-00010651.0003001 / 24 FEB 14Applicable to: ALL

‐ If the reset is done before engine start, the ZFW and ZFWCG must bere-entered on the MCDU INIT B page,

‐ If the reset is done after engine start, the actual GW and CG displayed onthe MCDU FUEL PRED page are computed by the FE . However, the GWcomputed by the FE may be less accurate, therefore, when time permits:• If the reset is successful, the actual GW and CG must be re-entered on

the MCDU FUEL PRED page,• If the reset is unsuccessful, the flight crew must determine the FOB

from the engine start fuel quantity minus the FU quantity indication.

28

FCMC

In the case of triggering of FUEL ZFW ZFCG DISAGREE, ifthe ZFW , ZFWCG , ECAM GW are the same as the loadsheet values, butthe difference between the ECAM CG and the loadsheet CG is more than2 %:

On ground:‐ Reinsert the ZFW and ZFCG values.

If the ECAM caution is still displayed after reinsertion:

• Simultaneously pull FCMC 1 and FCMC 2 reset buttons• Simultaneously push FCMC 1 and FCMC 2 reset buttons.

If unsuccessful, on ground:‐ Simultaneously pull FCMC 1, FCMC 2, FMGEC 1 and FMGEC 2 reset

buttons‐ Simultaneously push FCMC 1, FCMC 2, FMGEC 1 and FMGEC 2 reset

buttons.Refer to QRH ABN-80 Computer Reset Table - 22 - Auto Flight foradditional information regarding the FMGEC resets.


30 PHCWHC Associated heating is interrupted, when the reset pb is pulled.


DU (ECAM , PFD , ND) * If DU reset is unsuccessful, DMC (driving the affected DU) reset may beattempted.

DMC EFIS /ECAM displays are lost for 40 s on ground after reset or power-up.

FWC NIL31

SDAC NIL

80.18EA330-243F



06 MAR 17



Ident.: TDU / ABN-80-F-00015048.0001001 / 07 OCT 13Applicable to: ALL

BSCU* In flight:Not authorized.

On ground and only for the following cases:

In case of BRAKES RESIDUAL BRAKING:‐ STOP aircraft,‐ Set PARK BRK handle to ON,‐ Set A/SKID & N/W STRG sw to OFF,‐ Set A/SKID & N/W STRG sw to ON.

In case of WHEEL N/W STRG FAULT:

Case AIf the three conditions below are fulfilled:‐ the WHEEL N/W. STRG FAULT alert was triggered just after engine start‐ the NW STRG DISC memo was displayed before the start of the

pushback (before the aircraft starts moving)‐ the NW STRG DISC memo remained displayed even after the pushback

is finished (nosewheel steering selector bypass pin is in the steeringposition).

Apply the below reset procedure.If the ECAM alert disappears after the reset, the flight crew may continue theflight without troubleshooting.

Case BIn all other cases, including in case of doubt on the above conditions,troubleshooting must be performed before continuing the flight, even if theECAM alert disappears after the reset. For a return to the gate :‐ Apply the below reset procedure‐ The taxi speed must not exceed 10 kt.

Reset Procedure:‐ STOP aircraft,‐ Set PARK BRK handle to ON,‐ Confirm that towing bar is disconnected,‐ Set A/SKID & N/W STRG sw to OFF,‐ Set A/SKID & N/W STRG sw to ON.

Note: After any BSCU reset:1. Check brake efficiency,2. Check absence of aircraft veering,3. Record the BSCU reset in the logbook.

32

LGCIU An LGCIU reset must neither be done during landing gear maneuvers, norjust prior to touchdown.

80.18FA330-243F



06 MAR 17



Ident.: ABN-80-F-00014555.0001001 / 23 JUN 15Applicable to: ALL

36

ENG BLEED* ENG BLEED reset is only authorized in the two following cases:‐ CASE A: AIR ENG 1(2) BLEED FAULT alert‐ CASE B: AIR ENG 1(2) BLEED NOT CLSD alert

Note: Do not attempt more than one reset.

CASE A: AIR ENG 1(2) BLEED FAULT alert:

On ground or in flight• If the PACK (non-affected side) is operative, and

If the Wing Anti-Ice is OFF:

‐ ENG BLEED (affected side).......................................................OFF

▪ If the ENG BLEED (affected side) pb-sw FAULT light is on:‐ Delay application of the reset until FAULT light extinguishes.

▪ If the ENG BLEED (affected side) pb-sw FAULT light is off:‐ X BLEED........................................................................AUTO

Disregard the AIR ABNORM BLEED CONFIG alert.‐ PACK (affected side)...........................................................ON‐ ENG BLEED (affected side)................................................ON‐ Check that the affected Engine Bleed Valve is open on the BLEED

SD page.• If AIR ENG (AFFECTED) BLEED FAULT alert reoccurs, or

If Engine Bleed Valve (affected side) not open on the BLEEDSD page:- ENG BLEED (affected side).......................................OFF- X BLEED.................................................................OPEN

Note: Record the ENG BLEED reset in the logbook (successful orunsuccessful).

CASE B: AIR ENG 1(2) BLEED NOT CLSD alert:

On ground only‐ ENG BLEED (affected side).......................................................OFF

▪ If the ENG BLEED (affected side) pb-sw FAULT light is on:‐ Delay application of the reset until FAULT light extinguishes.

▪ If the ENG BLEED (affected side) pb-sw FAULT light is off:

‐ ENG BLEED (affected side)...............................................ON

‐ Check that the affected Engine Bleed Valve is closed on the BLEED SDpage.

Note: Record the ENG BLEED reset in the logbook (successful orunsuccessful).

80.18GA330-243F



06 MAR 17



Ident.: ABN-80-F-00010655.0001001 / 17 NOV 11Applicable to: ALL

38

VSC In case all toilets of one or both sides are shut down (on the cabin aft C/Bpanel):‐ RESET VACUUM TOILET SYSTEM (blue pb).

Repeated use of the blue reset pb is not recommended.If this does not fix the problem, apply the following procedure for bothsystem sides on the cabin aft C/B panel (VACUUM TOILET SYSTEM).Do not apply the following procedure in case of a waste tank overfill.

On the cabin aft C/B panel:‐ PULL C/B SYSTEM (both) and VACUUM GEN (both) (4 C/Bs).‐ PULL C/B LAVATORY POWER (LH and RH ) (8 C/Bs).‐ PUSH C/B LAVATORY POWER (LH and RH ) (8 C/Bs).

LH and RH SYSTEM and both VACUUM GEN C/Bs remain pulled.

In this configuration:• The waste quantity indication is lost.• The protection against waste tank overfill is lost.• Do not use toilets when the aircraft is below 16 000 ft.• Do not use toilets on ground, during servicing.

Ident.: ABN-80-F-00015509.0001001 / 21 APR 15Applicable to: ALL

ATSU When the ATSU is reset, ADS-C connections are no longer active. The ATCcenter(s) assumes that the connection is still active because a disconnectionmessage has not been sent to the ATC center(s). Therefore, the ATCcenter(s) will not attempt to re-establish ADS-C contracts with the aircraft,even after re-notification.

ATSU reset, with the ATSU 1 reset sw on 261 VU (overhead panel), shouldonly be attempted, if:‐ ″INVALID DATA″ is displayed on the DCDU.‐ Key selection has no effect on the DCDU or any of the MCDU ATSU

DATALINK submenus.

AINS Use the AINS reset sw on the 262 VU (overhead panel) to reset the AINS.

Note: An AINS reset may take up to 20 min

46

CINS If there is a malfunction of the CINS and if the reset by the cabin crew isunsuccessful, the flight crew can attempt to reset the system using the CINSreset button (overhead panel): pull the button then push it.

Note: The CINS reset may take up to 10 min.


49 ECB * Reset must only be attempted when APU speed is below 7 %


52 PSCU NIL

80.18HA330-243F



06 MAR 17




70

EIVMU During reset, and the subsequent 5 s, the following occurs:‐ On the corresponding engine:

‐ Loss of thrust reverser.‐ Loss of vibration indication.‐ If idle is selected, only high idle is available.‐ Loss of MAN start and wet crank.‐ Loss of bleed corrections on N1 limit.

‐ On all engines:• Loss of A/THR• Loss of Flex/Derated T.O.

BLANKA330-243F



06 MAR 17



NP1/2


NORMAL PROCEDURESTABLE OF CONTENTS

06 DEC 16


Normal Procedures NP-NPSafety Exterior Inspection.......................................................................1/14Preliminary Cockpit Preparation............................................................. 1/14Cockpit Preparation................................................................................ 2/14Before Pushback or Start....................................................................... 3/14ENG Start............................................................................................... 4/14After Start............................................................................................... 4/14Taxi......................................................................................................... 4/14Before Takeoff........................................................................................ 5/14Takeoff.................................................................................................... 5/14After Takeoff........................................................................................... 6/14Climb.......................................................................................................6/14Cruise......................................................................................................7/14Descent Preparation............................................................................... 7/14Descent...................................................................................................7/14Aircraft Configuration for Approach........................................................ 8/14Approach using LOC G/S Guidance...................................................... 9/14Approach using FINAL APP Guidance.................................................. 9/14Approach using FINAL APP Guidance for RNAV(RNP).......................10/14Approach using FPA Guidance............................................................ 11/14Landing................................................................................................. 12/14Go Around............................................................................................ 12/14After Landing........................................................................................ 13/14Parking..................................................................................................13/14Securing the Aircraft.............................................................................14/14

Normal Checklist NP-NCLBefore StarT..............................................................................................C3After Start..................................................................................................C3Before Takeoff.......................................................................................... C3After Takeoff / Climb.................................................................................C3Approach................................................................................................... C3Landing......................................................................................................C3After Landing.............................................................................................C3Parking...................................................................................................... C3Securing the Aircraft................................................................................. C3Takeoff CG / TRIM POS.......................................................................... C3

NP2/2


NORMAL PROCEDURESTABLE OF CONTENTS

06 DEC 16



NP-NP1/14


NORMAL PROCEDURES06 DEC 16


SAFETY EXTERIOR INSPECTIONIdent.: NP-NP-00010661.0001001 / 23 DEC 14Applicable to: ALL

PF PM* WHEEL CHOCKS........................................................ CHECK* L/G DOORS...............................................CHECK POSITION* APU AREA...................................................................CHECK

PRELIMINARY COCKPIT PREPARATIONIdent.: NP-NP-00010662.0014001 / 30 MAR 15Applicable to: ALL

PF PMENG MASTERS 1, 2............................................................. OFFENG START selector........................................... CHECK NORM* WEATHER RADAR........................................................... OFFL/G lever............................................................................ DOWNBoth WIPER selectors........................................................... OFFBAT........................................................................ CHECK/AUTOEXT PWR pb-sw...........................................................AS RQRDAPU FIRE............................................................... CHECK/TESTAPU....................................................................................STARTWhen the APU is AVAIL:* EXT PWR pb-sw......................................................AS RQRDAIR COND panel....................................................................SET* COCKPIT LIGHTS................................................... AS RQRD* ECAM RCL pb..............................................................PRESS* ECAM OXY PRESS/HYD QTY /ENG OIL QTY........... CHECKFLAPS............................................................ CHECK POSITION* SPD BRK lever........................CHECK RET AND DISARMED* PARKING BRAKE handle...................................................ON* ACCU/BRAKE PRESS.................................................CHECKALTN BRAKING............................................................... CHECKCARGO TEMP panel............................................................. SETEMER EQPT.....................................................................CHECKRAIN REPELLENT........................................................... CHECK

* OEB IN QRH................................................................ CHECKEMER CAB EQPT............................................................ CHECKFAP pages........................................................................ CHECK* CAB OCCUPANTS BRIEFING...............................PERFORM* GEAR PINS and COVERS.......CHECK ONBOARD/STOWED* EXTERIOR WALKAROUND...................................PERFORM

NP-NP2/14




COCKPIT PREPARATIONIdent.: NP-NP-00010663.0014001 / 26 MAY 15Applicable to: ALL

PF PMOVERHEAD PANEL:* ALL WHITE LIGHTS.......................................... EXTINGUISH* RCDR GND CTL pb-sw......................................................ON

CAPT & PURS/CAPT sw .................................... AS RQRD* ALL IR MODE selector..................................................... NAV* RESET BUTTONS (left side).......................................CHECKEXTERIOR LIGHTS...............................................................SET* SIGNS................................................................................SETPROB/WINDOW HEAT.......................................................AUTOLDG ELEV...........................................................................AUTOVALVE SEL.........................................................................BOTH* PACK FLOW............................................................AS RQRDELEC panel...................................................................... CHECKBAT...................................................................................CHECKFUEL T. TANK....................................................................AUTOENG FIRE.............................................................. CHECK/TESTMAINT panel.....................................................................CHECKVENT panel...................................................................... CHECKPA (3rd occupant).......................................................... RECEPTCVR TEST pb...................................................................PRESS* RESET BUTTONS (right side).....................................CHECK

DATA LOADER ...............................................CHECK OFFCTR INSTRUMENT PANEL:* ISIS.............................................................................. CHECK* NORTH REF................................................................CHECKECAM SWITCHING..........................................................CHECK* CLOCK.................................................................CHECK/SETLDG GEAR GRVTY EXTN sw.............................................. OFF* A/SKID & NW STRG sw.....................................................ONPEDESTAL:ACP...................................................................................CHECK* PARK BRK...............................................................AS RQRDCOCKPIT DOOR..............................................................CHECKSWITCHING PANEL..........................................................NORM* THRUST LEVERS..............................................CHECK IDLE* REVERSER LEVERS...............................................STOWED* ENG MASTERS.................................................. CHECK OFF* ENG START Selector......................................CHECK NORM* ATC...............................................................................STDBY

RMP....................................................................................... SET* AIRFIELD DATA......................................................... OBTAIN* MSG RECORD (MCDU).............................................. ERASE* ADS (MCDU)................................................. CHECK ARMED* ACARS .......................................................... INITIALIZE

NP-NP3/14




Continued from the previous pagePF PM

* FMS......................................................................... PREPARE* FMS PREPARATION................................................... CHECK

•When both flight crewmembers seated:GLARESHIELD: GLARESHIELD:* LOUDSPEAKER knob.......................................................SET * LOUDSPEAKER knob....................................................... SET* BAROMETRIC REFERENCE........................................... SET * BAROMETRIC REFERENCE............................................SET* FD..........................................................................CHECK ON * FD.......................................................................... CHECK ON* LS.............................................................................AS RQRD * LS............................................................................. AS RQRD* ND mode and range..........................................................SET * ND mode and range.......................................................... SET* ADF /VOR selector.................................................. AS RQRD * ADF /VOR selector...................................................AS RQRD* FCU................................................................................... SETLATERAL CONSOLE: LATERAL CONSOLE:OXY MASK.......................................................................... TEST OXY MASK...........................................................................TESTINSTRUMENT PANEL: INSTRUMENT PANEL:EFIS DMC selector............................................................ NORM EFIS DMC selector.............................................................NORMPFD -ND brightness........................................................ADJUST PFD -ND brightness........................................................ ADJUST* PFD -ND...................................................................... CHECK * PFD -ND.......................................................................CHECK* LDG ELEV (ECAM).......................................... CHECK AUTO * IRS ALIGN....................................................................CHECK* ECAM STATUS........................................................... CHECK* TAKEOFF BRIEFING............................................. PERFORM

BEFORE PUSHBACK OR STARTIdent.: NP-NP-00010664.0005001 / 09 FEB 15Applicable to: ALL

PF PMCAB DOORS..................................................................CLOSESLIDES............................................................................... ARMCAB TO CARGO DOORS............................................. CLOSECABIN SECURED.................................................... CHECKED

LOADSHEET....................................................................... CHECK LOADSHEET..................................................................CHECKFOB......................................................................................CHECK FOB................................................................................CHECKFMS TO DATA................................... CHECK/REVISE AS RQRD REVISED FMS TO DATA.......................................... XCHECKSEATING POSITION......................................................... ADJUST SEATING POSITION....................................................ADJUST

FMS F-PLN page.......................................................SELECTEXT PWR ..........................................................CHECK AVAIL

FMS PERF TO page......................................................SELECT

EXT PWR DISCONNECTION ................................ REQUESTBEFORE START C/L down to the line................... COMPLETEPUSHBACK/START CLEARANCE...............................OBTAIN

BEFORE START C/L down to the line.........................COMPLETE

ATC...................................................... SET FOR OPERATIONWINDOW/DOORS............................................... CHECK CLOSED WINDOW/DOORS......................................... CHECK CLOSEDSLIDES..................................................................CHECK ARMED SLIDES............................................................ CHECK ARMEDEXTERIOR LIGHTS..................................................................SETTHRUST LEVERS....................................................................IDLEACCU PRESS..................................................................... CHECKNW STRG DISC................................................ CHECK AS RQRDPARK BRK...................................................................... AS RQRDBEFORE START C/L below the line............................ COMPLETE BEFORE START C/L below the line...................... COMPLETE

NP-NP4/14




ENG STARTIdent.: NP-NP-00010665.0003001 / 23 DEC 14Applicable to: ALL

PF PMENG START selector...................................................... IGN STARTENGINE 1 START..........................................................ANNOUNCEENG MASTER switch 1................................................................ ONENG IDLE PARAMETERS.....................................................CHECKENGINE 2 START..........................................................ANNOUNCEREPEAT THE START SEQUENCE FOR ENG 2

AFTER STARTIdent.: NP-NP-00010666.0006001 / 15 JUN 15Applicable to: ALL

PF PMENG START selector......................................................... NORMAPU BLEED pb-sw................................................................ OFF GND SPOILERS................................................................... ARMENG ANTI ICE pb-sw...................................................AS RQRD RUD TRIM...........................................................................ZEROWING ANTI ICE pb-sw.................................................AS RQRD FLAPS.................................................................................... SETAPU MASTER SW....................................................... AS RQRD PITCH TRIM..................................................................... CHECK

NWS TOWING FAULT LT ..................................CHECK offECAM STATUS................................................................ CHECK ECAM STATUS................................................................ CHECKN/W STEER DISC MEMO.................. CHECK NOT DISPLAYEDCLEAR TO DISCONNECT....................................... ANNOUNCEAFTER START C/L................................................... COMPLETE AFTER START C/L................................................... COMPLETE

TAXIIdent.: NP-NP-00010667.0040001 / 06 SEP 16Applicable to: ALL

PF PM•Taxi clearance obtained:EXTERIOR LIGHTS............................................................... SET TAXI CLEARANCE.......................................................... OBTAINPARKING BRAKE handle......................................................OFF BRAKES PRESSURE......................................CHECK AT ZEROTHRUST LEVERS........................................................ AS RQRDBRAKES............................................................................CHECK BRAKES PRESSURE......................................CHECK AT ZEROTILLER or RUDDER PEDALS............................. USE AS RQRDFLT CTL............................................................................CHECK FLT CTL............................................................................CHECK•ATC clearance obtained:

ATC CLEARANCE........................................................CONFIRMT.O DATA......................................................................... CHECKFMS F-PLAN /SPD...........................................................CHECKFCU ALT /HDG...................................................................... SETBOTH FD................................................................... CHECK ON

PFD /ND........................................................................... CHECK PFD /ND........................................................................... CHECKTAKEOFF BRIEFING................................................... CONFIRM

RADAR and PREDICTIVE WINDSHEAR SYSTEM..... AS RQRDATC CODE/MODE..................... CONFIRM/SET FOR TAKEOFF

NP-NP5/14





TERR ON ND............................................................... AS RQRD TERR ON ND............................................................... AS RQRDAUTO BRK............................................................................ MAXT.O CONFIG pb...................................................................TESTT.O MEMO ..................................................... CHECK NO BLUE

BEFORE TAKEOFF C/L down to the line................. COMPLETE BEFORE TAKEOFF C/L down to the line................. COMPLETE

BEFORE TAKEOFFIdent.: NP-NP-00010668.0005001 / 23 DEC 14Applicable to: ALL

PF PMBRAKE TEMP (if brake fan running)....................... CHECK

BRAKE FAN pb-sw (if brake fan running).....................OFFTAKEOFF/LINE UP CLEARANCE.................................. OBTAIN

EXTERIOR LIGHTS............................................................... SETTCAS Mode selector............................................... TA or TA /RA

APPROACH PATH................................ CLEARED OF TRAFFIC APPROACH PATH................................ CLEARED OF TRAFFICENG START selector................................................... AS RQRD

SLIDING TABLE ...................................................STOWED SLIDING TABLE ...................................................STOWED

THRUST BUMP ...................................................AS RQRDTAKEOFF RUNWAY.................................................... CONFIRM TAKEOFF RUNWAY.................................................... CONFIRM

PACKS 1+2.................................................................. AS RQRDBEFORE TAKEOFF C/L below the line.................... COMPLETE BEFORE TAKEOFF C/L below the line.................... COMPLETE

TAKEOFFIdent.: NP-NP-00010669.0003001 / 28 JUL 15Applicable to: ALL

PF PMTAKEOFF..................................................................ANNOUNCEBRAKES........................................................................RELEASETHRUST LEVERS.................................................. FLX or TOGA CHRONO...........................................................................START

The Captain places hand on thrust levers until V1

DIRECTIONAL CONTROL....................................USE RUDDERFMA...........................................................................ANNOUNCE PFD /ND....................................................................... MONITOR•BELOW 80 kt: N1 (EPR).......................................................................... CHECK

THRUST SET........................................................... ANNOUNCEPFD and ENG indications............................................ MONITOR

•AT 100 kt: ONE HUNDRED KNOTS..........................................ANNOUNCE100 kt................................................................................ CHECK•AT V1: V1.....................................................MONITOR OR ANNOUNCE•AT VR: ROTATION....................................................................... ORDERROTATION.................................................................. PERFORM•WHEN POSITIVE CLIMB: POSITIVE CLIMB..................................................... ANNOUNCEL/G UP..............................................................................ORDER L/G.............................................................................SELECT UPAP................................................................................. AS RQRD

NP-NP6/14





•AT THR RED ALT:THRUST LEVERS.................................................................... CL PACK 1+2 (if applicable)......................................................... ON•AT F SPEED:FLAPS 1........................................................................... ORDER FLAPS 1.......................................................................... SELECT•AT S SPEED:FLAPS 0........................................................................... ORDER FLAPS 0.......................................................................... SELECT

GND SPLRS....................................................................DISARMEXTERIOR LIGHTS............................................................... SET

AFTER TAKEOFFIdent.: NP-NP-00010670.0001001 / 23 DEC 14Applicable to: ALL

PF PMAPU BLEED pb-sw.......................................................AS RQRDAPU MASTER SW....................................................... AS RQRDENG START selector................................................... AS RQRDTCAS Mode selector......................................................... TA /RAANTI ICE pb-sw............................................................AS RQRD

AFTER TAKEOFF/CLIMB C/L down to the line.........COMPLETE AFTER TAKEOFF/CLIMB C/L down to the line.........COMPLETE

CLIMBIdent.: NP-NP-00010671.0007001 / 23 DEC 14Applicable to: ALL

PF PMMCDU.......................................................................... PERF CLB MCDU..................................................................................F-PLNFCU/FMGS............................................................SET IF AP ON FCU/FMGS..........................................................SET IF AP OFF•At transition altitude:BAROMETRIC REFERENCE..............SET STD/CROSSCHECK BAROMETRIC REFERENCE..............SET STD/CROSSCHECKAFTER TAKEOFF/CLIMB C/L below the line............COMPLETE AFTER TAKEOFF/CLIMB C/L below the line............COMPLETERADAR........................................... ADJUST AS APPROPRIATE ENG ANTI ICE............................................................. AS RQRD•At 10 000 ft:

LAND LIGHTS sw..................................................................OFFSEAT BELTS sw.......................................................... AS RQRD

EFIS option...................................................................AS RQRD EFIS option...................................................................AS RQRDECAM MEMO..................................................................REVIEWNAVAIDS...........................................................................CLEARSEC F-PLN...................................................................AS RQRDOPT /MAX ALT.................................................................CHECK

NP-NP7/14




CRUISEIdent.: NP-NP-00010672.0011001 / 23 DEC 14Applicable to: ALL

PF PMECAM MEMO/SD PAGES.............................................. REVIEWFLIGHT PROGRESS........................................................CHECKFUEL.............................................................................MONITORSTEP FLIGHT LEVEL................................... AS APPROPRIATENAVIGATION ACCURACY.......................................... MONITORRADAR........................................... ADJUST AS APPROPRIATE

DESCENT PREPARATIONIdent.: NP-NP-00010673.0002001 / 23 DEC 14Applicable to: ALL

PF PMWEATHER AND LANDING INFORMATION................... OBTAIN

LANDING PERFORMANCE.........................................CONFIRM LANDING PERFORMANCE.............................................CHECKFMS..............................................................................PREPARE FMS PREPARATION........................................................CHECKLDG ELEV........................................................................ CHECKAUTO BRK................................................................... AS RQRDAPPR BRIEFING.........................................................PERFORM

TERR ON ND ......................................................AS RQRD TERR ON ND ......................................................AS RQRDRADAR........................................... ADJUST AS APPROPRIATE

ENG ANTI ICE pb-sw...................................................AS RQRDWING ANTI ICE pb-sw.................................................AS RQRDDESCENT CLEARANCE.................................................OBTAIN

CLEARED ALTITUDE ON FCU.............................................SET

DESCENTIdent.: NP-NP-00010674.0008001 / 23 DEC 14Applicable to: ALL

PF PMDESCENT....................................................................... INITIATEMCDU....................................................PROG /PERF DESCENT MCDU................................................................................. F-PLNDESCENT...................................................... MONITOR/ADJUST•When the aircraft approaches the transition level, and whencleared for an altitude:BAROMETRIC REFERENCE.......................SET/CROSSCHECK BAROMETRIC REFERENCE......................SET/CROSSCHECK

ECAM STATUS................................................................CHECK•At 10 000 ft:

LAND LIGHTS sw..................................................................SETSEAT BELTS sw.....................................................................ON

EFIS option pb..................................................................... CSTR EFIS option pb....................................................................CSTRLS pb.............................................................................AS RQRD LS pb............................................................................AS RQRD

RADIO NAV........................................................ SELECT/IDENTENG START selector...................................................AS RQRD

NP-NP8/14





•If GPS PRIMARY not available:NAV ACCY........................................................................CHECKAPPROACH C/L........................................................ COMPLETE APPROACH C/L....................................................... COMPLETE

AIRCRAFT CONFIGURATION FOR APPROACHIdent.: NP-NP-00014801.0004001 / 20 JUL 15Applicable to: ALL

PF PMINITIAL APPROACH:F-PLN SEQUENCING.....................................................ADJUST•Approx 15 NM from touchdown:

APPR PHASE.............................. ACTIVATE or set green dot (1)

MANAGED SPEED...........................................................CHECKFLIGHT PATH.............................................................. MONITOR NAV ACCURACY.........................................................MONITORSPEED BRAKES lever................................................. AS RQRDRADAR........................................... ADJUST AS APPROPRIATEINTERMEDIATE/FINAL APPROACH:•At green dot:FLAPS 1........................................................................... ORDER FLAPS 1.......................................................................... SELECT

S SPEED ..................................................... CHECK OR SET (1)

TCAS ..............................................................TA or TA /RA•At 2 500 ft AGL minimum:FLAPS 2........................................................................... ORDER FLAPS 2.......................................................................... SELECT

F SPEED........................................................CHECK OR SET(1)

•When FLAPS 2L/G DOWN....................................................................... ORDER L/G...................................................................... SELECT DOWN

AUTO BRAKE.............................................................. CONFIRMGRND SPLRS....................................................................... ARMEXTERIOR LIGHTS............................................................... SET

•When L/G down:FLAPS 3........................................................................... ORDER FLAPS 3.......................................................................... SELECT

ECAM WHEEL PAGE...................................................... CHECK•When FLAPS 3:FLAPS FULL.................................................................... ORDER FLAPS FULL................................................................... SELECT

SPEED TARGET............................................CHECK OR SET(1)

A/THR..........................................................CHECK SPD or OFFWING A. ICE (if not required)................................................OFF

SLIDING TABLE ........................................................STOW SLIDING TABLE ........................................................STOWLDG MEMO..................................................... CHECK NO BLUECABIN OCCUPANTS.......................................................ADVISE

NP-NP9/14





LDG C/L.....................................................................COMPLETE LDG C/L.....................................................................COMPLETEANNOUNCE ANY FMA MODIFICATION FLT PARAMETERS..................................................... MONITOR

Announce any deviation in excess of:• V/S : 1 200 ft/min• IAS : speed target + 10 kt; speed target - 5 kt• PITCH : 0 ° nose down; 10 ° nose up• BANK : 7 °

(1) PF if AP is ON, PM if AP is OFF. The PF may request that this action is performed by the PM dependingon the situation.

APPROACH USING LOC G/S GUIDANCEIdent.: NP-NP-00014802.0001001 / 23 DEC 14Applicable to: ALL

PF PMINITIAL / INTERMEDIATE APPROACH:APPR pb on FCU............................................................. PRESSBOTH AP....................................................................... ENGAGELOC.................................................................... CHECK ARMEDG/S......................................................................CHECK ARMEDLOC CAPTURE............................................................MONITORG/S CAPTURE............................................................. MONITOR

GO-AROUND ALT..............................................................SET(1)

FINAL APPROACH:FLT PARAMETERS..................................................... MONITORAnnounce any deviation in excess of:• LOC : ½ dot• GLIDE : ½ dot

•At minimum + 100 ft: ONE HUNDRED ABOVE................. MONITOR OR ANNOUNCE•At minimum:CONTINUE or GO-AROUND................................... ANNOUNCE MINIMUM......................................... MONITOR OR ANNOUNCE


APPROACH USING FINAL APP GUIDANCEIdent.: NP-NP-00014803.0002001 / 23 DEC 14Applicable to: ALL

PF PMDESCENT PREPARATION:

WEATHER AND LANDING INFO................................... OBTAINF-PLN A Page...................................................................CHECK F-PLN A Page..................................................................CHECKPROG Page............................................................... COMPLETE PROG Page.............................................................. COMPLETE

NP-NP10/14





GO-AROUND STRATEGY.............................................. REVIEWDESCENT:•At 10 000 ftNAV ACCURACY..............................................................CHECK•For RNAV(GNSS):

GPS PRIMARY......................................................CHECKBARO REF............................................................................. SETINITIAL/INTERMEDIATE/FINAL APPROACH:POSITION..................................................................... MONITORAPPR pb on FCU..............................................................PRESSAPP NAV...................................CHECK ARMED OR ENGAGEDFINAL.................................................................. CHECK ARMED•At Final Descent Point:FINAL APP.....................................................CHECK ENGAGED

GO-AROUND ALT..........................................................................SET(1)

FLT PARAMETERS.....................................................MONITORAnnounce any deviation in excess of:• XTK > 0.1 NM• V/DEV > ½ dot

•At minimum + 100 ft: ONE HUNDRED ABOVE.................MONITOR OR ANNOUNCE•At minimum:CONTINUE or GO-AROUND....................................ANNOUNCE MINIMUM.........................................MONITOR OR ANNOUNCE


APPROACH USING FINAL APP GUIDANCE FOR RNAV(RNP)Ident.: NP-NP-00014806.0003001 / 23 DEC 14Applicable to: ALL

PF PMDESCENT PREPARATION:

WEATHER AND LANDING INFO.................................... OBTAINNAVAID......................................................................DESELECTPROG Page.............................................................. COMPLETE PROG Page............................................................... COMPLETEGO-AROUND STRATEGY............................................. REVIEWDESCENT:GPS PRIMARY ON BOTH FMS......................................CHECKGPS 1+2..................................................CHECK BOTH IN NAVTERR ON ND...............................................................AS RQRDINITIAL/INTERMEDIATE/FINAL APPROACH:BARO REF/ALTIMETER..................................................CHECKFD or AP /FD.......................................... USE FOR APPROACHL/DEV..........................................................CHECK DISPLAYEDAPPR pb on FCU.............................................................PRESSAPP NAV.................................. CHECK ARMED OR ENGAGEDFINAL................................................................. CHECK ARMED•At the Final Descent Point:FINAL APP....................................................CHECK ENGAGED

NP-NP11/14





GO-AROUND ALT................................................................................................ SET(1)

FLT PARAMETERS......................................................MONITORAnnounce any deviation in excess of:• L/DEV : 1 dot or XTK > 0.1 NM• V/DEV > ½ dot

•At minimum + 100 ft: ONE HUNDRED ABOVE..................MONITOR OR ANNOUNCE•At minimum:CONTINUE or GO-AROUND...................................ANNOUNCE MINIMUM..........................................MONITOR OR ANNOUNCE


APPROACH USING FPA GUIDANCEIdent.: NP-NP-00014804.0002001 / 23 DEC 14Applicable to: ALL

PF PMDESCENT PREPARATION:F-PLN A Page...................................................................CHECK F-PLN A Page.................................................................. CHECKPROG Page...............................................................COMPLETE PROG Page.............................................................. COMPLETEGO-AROUND STRATEGY..............................................REVIEWDESCENT:•At 10 000 ft:NAV ACCURACY..............................................................CHECK•For RNAV(GNSS):

GPS PRIMARY ....................................................CHECKINITIAL/INTERMEDIATE/FINAL APPROACH:LATERAL GUIDANCE MODE.................. SET FOR APPROACH•For LOC ONLY, ILS G/S OUT and back course localizerapproaches:

LOC pb-sw............................................................ PRESSLOC / LOC B/C...................................... CHECK ARMED

LATERAL path.......................................................... INTERCEPTTRK FPA (Bird)............................................................... SELECTFPA FOR FINAL APPROACH............................................... SET•At 0.3 NM from the Final Descent Point:FPA selector......................................................................... PULLFPA................................................................ CHECK ENGAGEDPOSITION/FLT PATH....................................MONITOR/ADJUST

GO-AROUND ALT......................................................................... SET(1)

FLT PARAMETERS..................................................... MONITORAnnounce any deviation in excess of:• Approach using NAV MODE: XTK > 0.1 NM• Approach using LOC or LOC B/C MODE: LOC ½ dot• Approach using TRK MODE

▪ VOR: ½ dot or 2.5 °▪ NDB: 5 °

NP-NP12/14





•At minimum + 100 ft: ONE HUNDRED ABOVE................. MONITOR OR ANNOUNCE•At minimum:CONTINUE or GO-AROUND....................................ANNOUNCE MINIMUM.........................................MONITOR OR ANNOUNCE


LANDINGIdent.: NP-NP-00010678.0003001 / 23 DEC 14Applicable to: ALL

PF PM•In stabilized approach conditions, at approx. 40 ft:FLARE......................................................................... PERFORM ATTITUDE.................................................................... MONITORTHRUST LEVERS.................................................................IDLE•At touchdown:DEROTATION................................................................ INITIATEALL REVERSER LEVERS....................REV MAX OR REV IDLE GRND SPLRS.............................................CHECK/ANNOUNCE

REVERSERS.............................................. CHECK/ANNOUNCEDIRECTIONAL CONTROL.............................................ENSURE DIRECTIONAL CONTROL...........................................MONITORBRAKES....................................................................... AS RQRD DECELERATION.........................................CHECK/ANNOUNCE•At 70 kt:ALL REVERSER LEVERS.................................................... IDLE 70 kt .........................................................................ANNOUNCE•At taxi speed:ALL REVERSER LEVERS................................................. STOW•Before 20 kt:AUTO BRK...............................................................DISENGAGE

GO AROUNDIdent.: NP-NP-00010679.0001001 / 23 DEC 14Applicable to: ALL

PF PMTHRUST LEVERS.............................................................. TOGAROTATION.................................................................. PERFORMGO AROUND............................................................ANNOUNCE FLAPS lever.................................................. SELECT AS RQRDFMA...........................................................................ANNOUNCE

POSITIVE CLIMB..................................................... ANNOUNCEL/G UP..............................................................................ORDER L/G.............................................................................SELECT UPAP................................................................................. AS RQRDNAV or HDG mode.......................................................AS RQRD•AT GA THR RED ALT:THRUST LEVERS.................................................................... CL•AT GA ACCEL ALT:SPEED..........................................................................MONITOR•AT F SPEED:FLAPS 1........................................................................... ORDER FLAPS 1.......................................................................... SELECT

NP-NP13/14





•AT S SPEED:FLAPS 0........................................................................... ORDER FLAPS 0.......................................................................... SELECT

GND SPLRS....................................................................DISARMEXTERIOR LIGHTS............................................................... SET

AFTER TAKEOFF C/L down to the line.................... COMPLETE AFTER TAKEOFF C/L down to the line.................... COMPLETE

AFTER LANDINGIdent.: NP-NP-00010680.0001001 / 22 APR 16Applicable to: ALL

PF PMGRND SPLRS................................................................. DISARMEXTERIOR LIGHTS............................................................... SET

RADAR...................................................................................OFF

PREDICTIVE WINDSHEAR ..........................................OFFENG START selector......................................................... NORMFLAPS.......................................................................... RETRACTTCAS...................................................................SET on standbyATC...............................................................................AS RQRDAPU....................................................................................STARTANTI ICE...................................................................... AS RQRDBRAKE TEMP...................................................................CHECK

AFTER LDG C/L...................................................... COMPLETE AFTER LDG C/L...................................................... COMPLETE

PARKINGIdent.: NP-NP-00010681.0007001 / 09 FEB 15Applicable to: ALL

PF PMACCU PRESS.................................................................. CHECK ANTI-ICE................................................................................ OFFPARKING BRAKE handle........................................................ON APU BLEED pb-sw..................................................................ONENG MASTER 1, 2................................................................OFF

FUEL PUMPS........................................................................ OFFEXTERIOR LIGHTS............................................................... SET ATC....................................................................................STDBYGROUND CONTACT................................................ ESTABLISHSEAT BELTS sw....................................................................OFF IRS DRIFT RATE............................................................. CHECK

FUEL QTY........................................................................ CHECKSTATUS............................................................................CHECK

PARK BRK....................................................................AS RQRD BRAKE FAN ................................................................. OFFDU's........................................................................................ DIM DU's........................................................................................ DIMPARKING C/L............................................................COMPLETE

SLIDES..........................................................................DISARMECABIN DOORS................................................ OPEN, AS RQRD

NP-NP14/14




SECURING THE AIRCRAFTIdent.: NP-NP-00010682.0001001 / 21 AUG 15Applicable to: ALL

PF PMPARK BRK.................................................................CHECK ONALL IR MODE selectors.........................................................OFF OXY CREW SUPPLY pb.......................................................OFF

EXTERIOR LIGHTS...............................................................OFFGND SELECT CTL sw................................................. AS RQRDAPU BLEED pb-sw................................................................ OFFEXT PWR pb................................................................ AS RQRDAPU MASTER SW.................................................................OFFEMER EXIT LT sw.................................................................OFFSIGNS sw...............................................................................OFFBAT 1 + 2 + APU.................................................................. OFF

SECURING THE A/C C/L........................................ COMPLETE SECURING THE A/C C/L........................................ COMPLETE

PER1/2


IN FLIGHT PERFORMANCETABLE OF CONTENTS

18 JAN 17


Speeds PER-AOperating Speeds.....................................................................................1/2Green Dot Speed..................................................................................... 1/2VLS........................................................................................................... 2/2

Fuel Penalty Factors PER-BUse of Fuel Penalty Factor Tables...........................................................1/4Fuel Penalty Factors/ECAM Alert Table.................................................. 2/4Fuel Penalty Factors/Inop Sys Table....................................................... 3/4

Landing Performance Assessment PER-CMethod to Determine Aircraft Performance at Landing without or with aSingle Failure............................................................................................1/6Method to Determine Aircraft Performance at Landing with SeveralFailures..................................................................................................... 2/6Runway Condition Assessment Matrix for Landing..................................3/6VAPP Determination without Failure........................................................ 4/6VAPP Determination with Failure............................................................. 5/6

Landing Distance without Failure PER-DLanding Distance without Failure ............................................................1/2

Landing Distance with Electrical System Failure PER-24

Landing Distance with Flight Controls System Failure PER-27

Landing Distance with Slats and Flaps System Failure PER-27A

Landing Distance with Fuel System Failure PER-28

Landing Distance with Hydraulic System Failure PER-29

Landing Distance with Anti Ice System Failure PER-30

Landing Distance with Brake System Failure PER-32

Landing Distance with Navigation System Failure PER-34

Landing Distance with Bleed System Failure PER-36

Landing Distance with Engine System Failure PER-70

PER2/2


IN FLIGHT PERFORMANCETABLE OF CONTENTS

18 JAN 17


Continued from the previous pageOne Engine Inoperative PER-E

Ceilings..................................................................................................... 1/4Gross Flight Path Descent at Green Dot Speed...................................... 2/4Cruise at Long Range Cruise speed........................................................3/4In Cruise Quick Check Long Range.........................................................4/4

All Engines Operative PER-GOptimum & Maximum Altitudes................................................................1/4In Cruise Quick Check at a Given Mach Number.................................... 2/4Cost Index for Long Range Cruise SpeeD...............................................3/4Standard Descent.....................................................................................3/4Quick Determination Table of Alternate Flight Planning...........................4/4

Flight Without Cabin Pressurization PER-HIn Cruise Quick Check FL 100 Long Range............................................ 1/2

Miscellaneous PER-IGround Distance / Air Distance Conversion.............................................1/6IAS / MACH Conversion...........................................................................2/6ISA Temperature and Pressure Altitude Correction................................. 3/6Wind Component......................................................................................5/6

PER-A1/2


IN FLIGHT PERFORMANCE05 MAR 14


OPERATING SPEEDSIdent.: PER-A-00010699.0044001 / 08 FEB 13Applicable to: ALL

OPERATING SPEEDS (KT)

Weight (1000 KG) S VLS CONF 1 F (1) VLS CONF 2 VLS CONF 3 VREF

240 205 187 168 165 159 157

220 197 179 161 158 152 150

200 187 170 153 150 145 143

180 178 162 145 143 138 136

160 168 152 137 135 130 128

140 157 143 128 126 122 120

120 152 138 123 122 118 118

110 152 138 123 122 118 118

(1) For approach :In CONF 2 : Add 14 %. F is limited to 133 kt (low limit).In CONF 3 : Add 4 %. F is limited to 128 kt (low limit).

Note: If Weight (W ) <193 t and CG <18%, 1 kt must be added to: VLS CONF 1, VLS CONF 2,VLS CONF 3 and VREF.

GREEN DOT SPEEDIdent.: PER-A-00010700.0041001 / 08 FEB 13Applicable to: ALL

GREEN DOT SPEED (KT) ALL ENGINES OPERATIVE

Weight (1000 KG) at or below FL 200 FL 300 FL 400

240 251 261 271

220 239 249 259

200 227 237 247

180 215 225 235

160 203 213 223

140 191 201 211

120 179 189 199

110 179 189 199

GREEN DOT SPEED WITH ONE OR TWO ENGINES INOP : Subtract 10 kt from these values.

PER-A2/2




VLSIdent.: PER-A-00010701.0042001 / 08 FEB 13Applicable to: ALL

VLS CONF 0 (KT)

1.23 VS 0.3 g buffet marginWeight (1000 KG)

FL 0 FL 100 FL 200 FL 200 FL 300 FL 400

240 209 222 237 233 245 293

220 200 207 226 220 233 268

200 190 192 214 206 220 243

180 181 181 200 193 206 221

160 170 171 182 177 194 203

140 159 159 163 160 177 187

120 154 154 154 152 169 179

110 154 154 154 152 169 179

Note: If Weight (W ) <193 t and CG <18%, 1 kt must be added in 1.23 VS at: FL 0, FL 100 and FL 200columns.

PER-B1/4


IN FLIGHT PERFORMANCE07 JUN 16


USE OF FUEL PENALTY FACTOR TABLESIdent.: PER-B-00014176.0001001 / 10 MAY 16Applicable to: ALL

USE OF THE FUEL PENALTY FACTORSThe Fuel Penalty Factors provided in the following tables are conservative values, given as a guideline inorder to increase the crew awareness and to help the decision making.

Note: In case of failure impacting the fuel consumption, the fuel predictions provided by the FMS areno longer reliable (except in One Engine Inoperative OEI condition). The flight crew must stillcompute and monitor the actual fuel consumption.

Refer to the following tables in order to assess the impact of the failure on the fuel consumption after anyECAM alert that:‐ Displays the line INCREASED FUEL CONSUMP or FUEL CONSUMPT INCRSD in the

STATUS SD page, or‐ Displays Flight Control Surfaces in the INOP SYS, or‐ Impacts the Landing Gears or Landing Gear Doors retraction (when extended).The Fuel Penalty Factors given in these tables have been calculated taking into account:‐ The FUEL CRITICAL INOP SYS, and‐ The aircraft configuration, speed or altitude described in the CONDITIONS column.Ensure that all these conditions are well met before applying the corresponding Fuel Penalty Factor.METHODOLOGY

The methodology is the following:‐ Check the ECAM ALERT table to determine if a Fuel Penalty Factor is applicable depending on the

CONDITIONS column, then

‐ Check the INOP SYS table in order to determine if, according to the actual aircraft status, there is aFuel Penalty Factor applicable depending on the CONDITIONS column

‐ If only one Fuel Penalty Factor (FPF) is applicable:TRIP FUEL PENALTY = (FOB - EFOB at DEST) x FPFThe FMS fuel predictions must be recomputed to take into account this trip fuel penalty.

‐ If two or more Fuel Penalty Factors (FPF) are applicable:TRIP FUEL PENALTY = (FOB - EFOB at DEST) x ( FPF1 + FPF2 +...)The FMS fuel predictions must be recomputed to take into account this trip fuel penalty.

Note: Due to previous failures in flight or dispatch under MEL, some failures could have an impacton the fuel consumption:‐ Without being mentioned in the ECAM ALERT table (only through INOP SYS table), or‐ If mentioned in the ECAM ALERT table, with additional INOP SYS (other than the one(s)

described in the FUEL CRITICAL INOP SYS column for this specific ECAM alert) impactingalso the fuel consumption.

Example:• Dispatch with the PRIM 3 inoperative under MEL• F/CTL SEC 1 FAULT ECAM caution in flight• These two failures lead to the loss of the left outboard aileron• INOP SYS will displayed “L OUTR AIL”

There is no F/CTL SEC 1 FAULT entry in the ECAM table, however there is an entry L(R)INR(OUTR) AIL in the INOP SYS table. Apply the Fuel Penalty Factor related to the INOP SYS “LOUTR AIL” partially extended.Therefore, TRIP FUEL PENALTY = (FOB - EFOB at DEST) x 15 %

PER-B2/4




FUEL PENALTY FACTORS/ECAM ALERT TABLEIdent.: PER-B-00014177.0001001 / 05 NOV 12Applicable to: ALL

SYS ECAM ALERT FUEL CRITICALINOP SYS CONDITIONS

FUELPENALTYFACTOR

L(R) INR (OUTR) AIL If one aileron is indicated fully extended(upwards or downwards) 35 %

L(R) INR (OUTR) AIL FAULTL(R) INR (OUTR) AIL

or L+R INR (OUTR) AILIf one or both aileron(s) is/are indicatedpartially extended 15 %

If one spoiler is suspected fully extended (2)Cruise Conditions:OPT SPEED................ COST INDEX 0Set Cost Index (CI) to 0 and use managedspeed.CRUISE ALT.................AS REQUIREDCurrent Flight Level (FL ) may not bemaintained due to increased drag. Maintaina cruise FL as high as possible.

45 %SPLR (affected)

If one spoiler or one pair of spoilers ispartially extended (zero hinge moment) 8 %

PART SPLRSwith BLUE HYD

If spoiler 2 or 3 is partially extended after theloss of the B hydraulic system (1)

Up to 7 %(3)

PART SPLRSwith GREEN HYD

If spoiler 1 or 5 is partially extended after theloss of the G hydraulic system (1)

Up to 8 %(3)

SPLR FAULT

PART SPLRS withYELLOW HYD

If spoiler 4 or 6 is partially extended after theloss of the Y hydraulic system (1)

Up to 15 %(3)

ELEV REDUND LOST - If ailerons are preset upwards 20 %

FLAPS FAULT/LOCKED FLAPS If Flaps are extended 120 %

SLATS FAULT/LOCKED SLATS If Slats are extended 50 %

F/CTL

SLATS + FLAPS FAULT/LOCKED SLATS+FLAPS If Slats and Flaps are extended 150 %

B SYS LO PR PART SPLRS If spoilers 2 and 3 are indicated extended (atthe time of the failure) 16 %

G SYS LO PR PART SPLRS If spoilers 1 and 5 are indicated extended (atthe time of the failure) 16 %

Y SYS LO PR PART SPLRS If spoilers 4 and 6 are indicated extended (atthe time of the failure) 16 %

G+B SYS LO PR L+R INR AIL SPLR(1+2+3+5) L ELEV

Both inner ailerons are failedSpoilers 1, 2, 3 and 5 (1)Left elevator is failedRAT is extended

20 %to

30 %(4)

G+Y SYS LO PR L+R OUTR AIL SPLR(1+4+5+6) R ELEV

Both outer ailerons are failedSpoilers 1, 4, 5 and 6 (1)Right elevator is failedRAT is extended

20 %to

30 %(4)

HYD

B+Y SYS LO PR SPLR (2+3+4+6)STABILIZER

Spoilers 2, 3, 4 and 6 (1)Stabilizer is jammed

0 %to

15 %(4)

RETRACTION FAULT

L(R) LENGTHENING FAULT

GEAR NOT UPLOCKED

GEAR UPLOCK FAULT

L/G RETRACT All landing gears are extended 180 %L/G

DOORS NOT CLOSED L/G DOOR All landing gears doors are extended 15 %

PER-B3/4




(1) During the flight, the spoiler(s) may gradually extend and increase(s) the fuel consumption.

(2) A visual inspection, if time permits, can confirm the full extension of the spoiler.

(3) The maximum value of the Fuel Penalty Factor provided in the table considers that the two pairs ofcorresponding spoilers gradually extend during the flight.

(4) The minimum value of the Fuel Penalty Factor provided in the table considers that all spoilers remainretracted. The maximum value has been calculated considering that all impacted spoilers gradually extendduring the flight.

FUEL PENALTY FACTORS/INOP SYS TABLEIdent.: PER-B-00014178.0001001 / 06 APR 12Applicable to: ALL

SYS INOP SYS CONDITIONS FUEL PENALTYFACTOR

L(R) INR (OUTR) AILor L+R INR (OUTR) AIL

If one or both aileron(s) is/are indicated partiallyextended 15 %

FLAPS If Flaps are extended 120 %

SLATS If Slats are extended 50 %F/CTL

SLATS+FLAPS If Slats and Flaps are extended 150 %

L/G L/G DOOR All landing gears doors are extended 15 %

PER-B4/4





PER-C1/6


IN FLIGHT PERFORMANCE18 JAN 17


METHOD TO DETERMINE AIRCRAFT PERFORMANCEAT LANDING WITHOUT OR WITH A SINGLE FAILURE

Ident.: PER-C-00015213.0001001 / 20 AUG 14Applicable to: ALL

Use the following method to determine the runway landing performance level, the FLAPS lever position forlanding, the VAPP, and the Factored Landing Distance (FLD):

PER-C2/6




METHOD TO DETERMINE AIRCRAFT PERFORMANCEAT LANDING WITH SEVERAL FAILURES

Ident.: PER-C-00015214.0001001 / 28 FEB 14Applicable to: ALL

Use the following method to determine the runway landing performance level, the FLAPS lever position forlanding, the VAPP, and the Factored Landing Distance (FLD):

PER-C3/6




RUNWAY CONDITION ASSESSMENTMATRIX FOR LANDING

Ident.: PER-C-00014117.0006001 / 20 DEC 16Applicable to: ALL

Runway Surface Conditions Related LandingPerformance

Runway State or / andRunway Contaminant

ESF(1) orPIREP(2)

Observations onDeceleration and

Directional Control Code Level

MaximumCrosswindfor Landing

(Gust included)

Dry - - 6 DRY 45 kt

DampWetUp to 3 mm (1/8'') of waterSlushUp to 3 mm (1/8'')Dry snowUp to 3 mm (1/8'')Wet snowUp to 3 mm (1/8'')Frost

Good

Braking decelerationis normal for the

wheel braking effortapplied. Directionalcontrol is normal.

5 GOOD 45 kt

Compacted snowOAT at or below -15 °C

Good toMedium

Braking decelerationand controllabilityis between Good

and Medium.

4 GOOD TOMEDIUM 27 kt

Dry snowMore than 3 mm (1/8''), up to 100 mm (4'')Wet snowMore than 3 mm (1/8''), up to 30 mm(6/5'')Compacted snowOAT above -15 °CDry snow over compacted snowWet snow over compacted snowSlippery when wet

Medium

Braking deceleration isnoticeably reduced for

the wheel braking effortapplied. Directional

control may be reduced.

3 MEDIUM 20 kt

WaterMore than 3 mm (1/8''), up to 12.7 mm(1/2'')SlushMore than 3 mm (1/8''), up to 12.7 mm(1/2'')

Mediumto Poor

Braking decelerationand controllability is

between Medium andPoor. Potential for

hydroplaning exists.

2 MEDIUMTO POOR 20 kt

Ice (cold & dry) Poor

Braking deceleration issignificantly reduced forthe wheel braking effort

applied. Directionalcontrol may be

significantly reduced.

1 POOR 15 kt

Wet iceWater on top of Compacted Snow

Dry Snow or Wet Snow over iceNil

Braking deceleration isminimal to non-existantfor the wheel braking

effort applied.Directional controlmay be uncertain.

- - -

(1) ESF: Estimated Surface Friction

(2) PIREP: Pilot Report of Braking Action

Note: Refer to FCOM LIM-AFS chapter for Automatic Approach, Landing and Rollout limitations.

PER-C4/6




VAPP DETERMINATION WITHOUT FAILUREIdent.: PER-C-00014116.0034001 / 28 FEB 14Applicable to: ALL

The FMGS performs the following VAPP computation for landing in normal configuration (CONF 3 or CONFFULL).

PER-C5/6




VAPP DETERMINATION WITH FAILUREIdent.: PER-C-00014312.0038001 / 28 FEB 14Applicable to: ALL

PER-C6/6





PER-D1/2




LANDING DISTANCE WITHOUT FAILUREIdent.: PER-D-00014090.0090001 / 28 FEB 14Applicable to: ALL

The Reference Distance (REF DIST) considers : Sea Level (SL), ISA, no wind, no slope, no enginereverse thrust, manual landing (1) , VAPP=VLS without APPR COR.

6 - DRY

Corrections on Landing Distance (ft) WGT(2) SPD ALT WIND TEMP SLOPE REV OVW

Braking Mode LDGCONF

REF DIST(ft) for190T

Per 10Tabove190T

Per 5kt

Per1000ftabove

SL

Per5kt TW

Per 10°Cabove

ISA

Per 1%DownSlope

Per ThrustReverserOperative

If OVWPROC

applied

FULL 4 340 + 520 + 270 + 150 + 430 + 130 + 70 - 40 + 1 880Maximum MANUAL

3 4 530 + 560 + 270 + 160 + 450 + 140 + 80 - 40 + 2 190

FULL 5 470 + 460 + 310 + 170 + 480 + 160 + 60 - 10 + 210AUTOBRAKE MED

3 5 720 + 500 + 330 + 180 + 490 + 170 + 70 - 10 + 220

FULL 7 300 + 510 + 430 + 250 + 700 + 230 + 100 - 90 + 300AUTOBRAKE LOW

3 7 700 + 550 + 450 + 260 + 720 + 240 + 120 - 90 + 320

(1) Automatic Landing correction: if CONF FULL, add 580ft. If CONF 3, add 550ft.(2) Weight correction: if CONF FULL, subtract 150ft per 10T below 190T. If CONF 3, subtract 170ft per 10T below 190T.

5 - GOOD




Per 10Tabove190T

Per 5kt

Per1000ftabove

SL

Per5kt TW

Per 10°Cabove

ISA

Per 1%DownSlope


If OVWPROC

applied


3 5 690 + 650 + 440 + 270 + 780 + 240 + 190 - 100 + 1 710


3 6 240 + 660 + 430 + 270 + 780 + 250 + 210 - 140 + 390


3 7 700 + 620 + 450 + 270 + 730 + 240 + 120 - 90 + 370

(1) Automatic Landing correction: add 660ft.(2) Weight correction: if CONF FULL, subtract 230ft per 10T below 190T. If CONF 3, subtract 280ft per 10T below 190T.

4 - GOOD TO MEDIUM




Per 10Tabove190T

Per 5kt

Per1000ftabove

SL

Per5kt TW

Per 10°Cabove

ISA

Per 1%DownSlope


If OVWPROC

applied


3 6 440 + 460 + 360 + 230 + 670 + 210 + 260 - 180 + 1 930


3 6 990 + 460 + 370 + 230 + 700 + 220 + 290 - 230 + 320


3 7 740 + 540 + 450 + 260 + 740 + 240 + 220 - 100 + 320


PER-D2/2




3 - MEDIUM




Per 10Tabove190T

Per 5kt

Per1000ftabove

SL

Per5kt TW

Per 10°Cabove

ISA

Per 1%DownSlope


If OVWPROC

applied


3 7 210 + 520 + 400 + 260 + 790 + 240 + 370 - 240 + 1 820


3 7 710 + 520 + 400 + 270 + 810 + 250 + 400 - 300 + 360


3 8 120 + 550 + 450 + 280 + 830 + 260 + 400 - 170 + 370


2 - MEDIUM TO POOR




Per 10Tabove190T

Per 5kt

Per1000ftabove

SL

Per5kt TW

Per 10°Cabove

ISA

Per 1%DownSlope


If OVWPROC

applied

FULL 7 870 + 890 + 590 + 420 + 1 290 + 370 + 520 - 270 + 1 060Maximum MANUAL

3 8 640 + 1 010 + 640 + 470 + 1 410 + 420 + 680 - 320 + 1 270

FULL 8 080 + 890 + 580 + 420 + 1 300 + 380 + 530 - 310 + 500AUTOBRAKE MED

3 8 870 + 1 020 + 640 + 470 + 1 420 + 430 + 700 - 360 + 580

FULL 8 240 + 900 + 580 + 420 + 1 310 + 380 + 540 - 220 + 490AUTOBRAKE LOW

3 9 050 + 1 020 + 630 + 470 + 1 430 + 430 + 710 - 330 + 550


1 - POOR




Per 10Tabove190T

Per 5kt

Per1000ftabove

SL

Per5kt TW

Per 10°Cabove

ISA

Per 1%DownSlope


If OVWPROC

applied

FULL 12 190 + 940 + 550 + 460 + 1 830 + 430 + 2 500 - 700 + 1 060Maximum MANUAL

3 13 300 + 1 050 + 610 + 500 + 1 910 + 480 + 2 940 - 850 + 1 280

FULL 12 390 + 940 + 550 + 460 + 1 840 + 440 + 2 510 - 730 + 500AUTOBRAKE MED

3 13 530 + 1 050 + 600 + 500 + 1 920 + 490 + 2 960 - 880 + 580

FULL 12 550 + 940 + 540 + 460 + 1 850 + 440 + 2 520 - 750 + 490AUTOBRAKE LOW

3 13 710 + 1 050 + 600 + 510 + 1 930 + 480 + 2 980 - 910 + 550


PER-241/4




Ident.: PER-24-00015147.0001001 / 28 FEB 14Applicable to: ALL


ELECTRICAL SYSTEM

The Reference Distance (REF DIST) considers : Sea Level (SL), ISA, no wind, no slope, no engine reverse thrust, manuallanding(1), maximum manual braking, VAPP = VREF+ΔVREF without APPR COR.

6 - DRY

Corrections onLanding Distance (ft) WGT (2) SPD ALT WIND TEMP SLOPE REV OVW

FAILURE

FLAPSLEVER

forLDG

ΔVREF

REFDIST

(ft) for190T

Per10T

above190T

Per 5kt

Per1000ftabove

SL

Per5kt TW

Per10°C

aboveISA

Per 1%DownSlope


If OVWPROC

applied

FULL 0 4 700 + 510 + 310 + 160 + 450 + 150 + 90 INOP + 1 800DC BUS 1+2 FAULT

3 5 4 980 + 550 + 320 + 180 + 470 + 160 + 90 INOP + 2 040

FULL 0 4 700 + 510 + 310 + 160 + 450 + 150 + 90 - 10 + 1 800DC BUS 2 FAULT

3 5 4 980 + 550 + 320 + 180 + 470 + 160 + 90 - 10 + 2 040

FULL 10 4 930 + 550 + 290 + 170 + 470 + 160 + 80 - 60 + 1 150DC ESS BUS FAULT withIce Accretion 3 15 5 220 + 580 + 290 + 190 + 470 + 170 + 90 - 70 + 1 380

FULL 10 4 930 + 550 + 290 + 170 + 470 + 160 + 80 - 60 + 1 150DC ESS BUS SHED withIce Accretion 3 15 5 220 + 580 + 290 + 190 + 470 + 170 + 90 - 70 + 1 380

EMER CONFIG 3 5 4 980 + 550 + 320 + 180 + 470 + 160 + 90 INOP + 2 040

(1) Automatic Landing correction: add 180ft - (2) Weight correction: subtract 160ft per 10T below 190TREF DIST without failure (valid for all FLAPS LEVER positions) = 4 340ft

5 - GOOD


FAILURE

FLAPSLEVER

forLDG

ΔVREF

REFDIST

(ft) for190T

Per10T

above190T

Per 5kt

Per1000ftabove

SL

Per5kt TW

Per10°C

aboveISA

Per 1%DownSlope


If OVWPROC

applied


3 5 6 560 + 750 + 580 + 340 + 930 + 310 + 290 INOP + 1 310

FULL 0 6 000 + 680 + 530 + 300 + 850 + 280 + 230 - 60 + 1 140DC BUS 2 FAULT

3 5 6 560 + 750 + 580 + 340 + 930 + 310 + 290 - 100 + 1 310

FULL 10 6 240 + 640 + 440 + 290 + 780 + 260 + 180 - 140 + 690DC ESS BUS FAULT withIce Accretion 3 15 6 790 + 710 + 470 + 340 + 830 + 290 + 230 - 180 + 820

FULL 10 6 240 + 640 + 440 + 290 + 780 + 260 + 180 - 140 + 690DC ESS BUS SHED withIce Accretion 3 15 6 790 + 710 + 470 + 340 + 830 + 290 + 230 - 180 + 820

EMER CONFIG 3 5 6 560 + 750 + 580 + 340 + 930 + 310 + 290 INOP + 1 310


PER-242/4




Continued from the previous pageELECTRICAL SYSTEM


4 - GOOD TO MEDIUM


FAILURE

FLAPSLEVER

forLDG

ΔVREF

REFDIST

(ft) for190T

Per10T

above190T

Per 5kt

Per1000ftabove

SL

Per5kt TW

Per10°C

aboveISA

Per 1%DownSlope


If OVWPROC

applied


3 5 7 380 + 460 + 470 + 270 + 760 + 250 + 370 INOP + 1 650

FULL 0 6 850 + 450 + 450 + 250 + 720 + 230 + 310 - 220 + 1 430DC BUS 2 FAULT

3 5 7 380 + 460 + 470 + 270 + 760 + 250 + 370 - 280 + 1 650

FULL 10 6 910 + 430 + 370 + 240 + 680 + 220 + 240 - 220 + 910DC ESS BUS FAULT withIce Accretion 3 15 7 410 + 450 + 380 + 270 + 690 + 240 + 280 - 270 + 1 110

FULL 10 6 910 + 430 + 370 + 240 + 680 + 220 + 240 - 220 + 910DC ESS BUS SHED withIce Accretion 3 15 7 410 + 450 + 380 + 270 + 690 + 240 + 280 - 270 + 1 110

EMER CONFIG 3 5 7 380 + 460 + 470 + 270 + 760 + 250 + 370 INOP + 1 650


3 - MEDIUM


FAILURE

FLAPSLEVER

forLDG

ΔVREF

REFDIST

(ft) for190T

Per10T

above190T

Per 5kt

Per1000ftabove

SL

Per5kt TW

Per10°C

aboveISA

Per 1%DownSlope


If OVWPROC

applied


3 5 8 390 + 540 + 520 + 310 + 900 + 300 + 550 INOP + 1 510

FULL 0 7 750 + 510 + 490 + 290 + 860 + 270 + 460 - 370 + 1 290DC BUS 2 FAULT

3 5 8 390 + 540 + 520 + 310 + 900 + 300 + 550 - 470 + 1 510

FULL 10 7 680 + 490 + 400 + 280 + 790 + 260 + 340 - 310 + 830DC ESS BUS FAULT withIce Accretion 3 15 8 280 + 520 + 420 + 300 + 810 + 280 + 400 - 370 + 1 010

FULL 10 7 680 + 490 + 400 + 280 + 790 + 260 + 340 - 310 + 830DC ESS BUS SHED withIce Accretion 3 15 8 280 + 520 + 420 + 300 + 810 + 280 + 400 - 370 + 1 010

EMER CONFIG 3 5 8 390 + 540 + 520 + 310 + 900 + 300 + 550 INOP + 1 510


PER-243/4




Continued from the previous pageELECTRICAL SYSTEM


2 - MEDIUM TO POOR


FAILURE

FLAPSLEVER

forLDG

ΔVREF

REFDIST

(ft) for190T

Per10T

above190T

Per 5kt

Per1000ftabove

SL

Per5kt TW

Per10°C

aboveISA

Per 1%DownSlope


If OVWPROC

applied

FULL 0 9 320 + 1 050 + 790 + 540 + 1 640 + 490 + 830 INOP + 600DC BUS 1+2 FAULT

3 5 10 580 + 1 170 + 880 + 630 + 1 850 + 570 + 1 160 INOP + 720

FULL 0 9 320 + 1 050 + 790 + 540 + 1 640 + 490 + 830 - 470 + 600DC BUS 2 FAULT

3 5 10 580 + 1 170 + 880 + 630 + 1 850 + 570 + 1 160 - 680 + 720

FULL 10 9 170 + 930 + 570 + 470 + 1 350 + 420 + 560 - 420 + 420DC ESS BUS FAULT withIce Accretion 3 15 10 210 + 1 030 + 620 + 540 + 1 450 + 480 + 740 - 550 + 520

FULL 10 9 170 + 930 + 570 + 470 + 1 350 + 420 + 560 - 420 + 420DC ESS BUS SHED withIce Accretion 3 15 10 210 + 1 030 + 620 + 540 + 1 450 + 480 + 740 - 550 + 520

EMER CONFIG 3 5 10 580 + 1 170 + 880 + 630 + 1 850 + 570 + 1 160 INOP + 720


1 - POOR


FAILURE

FLAPSLEVER

forLDG

ΔVREF

REFDIST

(ft) for190T

Per10T

above190T

Per 5kt

Per1000ftabove

SL

Per5kt TW

Per10°C

aboveISA

Per 1%DownSlope


If OVWPROC

applied

FULL 0 Landing Distance greater than 18 000 ft for all conditionsDC BUS 1+2 FAULT

3 5 Landing Distance greater than 18 000 ft for all conditions

FULL 0 15 710 + 880 + 790 + 590 + 2 650 + 630 + 4 190 - 3 370 + 600DC BUS 2 FAULT


FULL 10 13 460 + 970 + 550 + 510 + 1 870 + 490 + 2 520 - 1 180 + 420DC ESS BUS FAULT withIce Accretion 3 15 14 870 + 1 070 + 590 + 570 + 1 960 + 530 + 2 980 - 1 420 + 520

FULL 10 13 460 + 970 + 550 + 510 + 1 870 + 490 + 2 520 - 1 180 + 420DC ESS BUS SHED withIce Accretion 3 15 14 870 + 1 070 + 590 + 570 + 1 960 + 530 + 2 980 - 1 420 + 520

EMER CONFIG 3 5 Landing Distance greater than 18 000 ft for all conditions


PER-244/4





PER-271/6





FLIGHT CONTROLS SYSTEM


6 - DRY


FAILURE

FLAPSLEVER

forLDG

ΔVREF

REFDIST

(ft) for190T

Per10T

above190T

Per 5kt

Per1000ftabove

SL

Per5kt TW

Per10°C

aboveISA

Per 1%DownSlope


If OVWPROC

applied

STAB CTL FAULT withman trim not available 2 20 5 470 + 620 N/A + 190 + 470 + 180 + 110 - 70 + 1 870

STAB CTL FAULT withman trim available 3 5 4 750 + 550 + 280 + 170 + 470 + 150 + 80 - 50 + 1 900

L/R/L+R ELEV FAULT 2 20 5 490 + 620 N/A + 190 + 470 + 180 + 110 - 70 + 1 850

RUDDER JAM/RUDDER FAULT 2 10 5 620 + 830 + 430 + 280 + 610 + 220 + 160 - 80 + 1 910

The following ECAMalerts with engine out:-RUDDER JAM-RUDDER FAULT(Calculated with 170ktmin)

2 170kt 7 080 + 440 N/A + 310 + 620 + 260 + 210 - 220 + 1 130

ALTN/DIRECT LAW 3 5 4 750 + 550 + 280 + 170 + 470 + 150 + 80 - 50 + 1 900

YAW DAMPER FAULT 3 5 4 750 + 550 + 280 + 170 + 470 + 150 + 80 - 50 + 1 900

FULL 0 4 590 + 520 + 290 + 160 + 440 + 150 + 80 - 50 + 1 780PRIM 1(2)(3)/1+2 FAULT

3 5 4 860 + 550 + 300 + 170 + 460 + 160 + 80 - 60 + 2 000

FULL 0 4 690 + 510 + 310 + 160 + 450 + 150 + 80 INOP + 1 820PRIM 1+3/2+3 FAULT

3 5 4 960 + 540 + 310 + 170 + 470 + 160 + 90 INOP + 2 050

PRIM 1+2+3 FAULT 3 5 5 430 + 520 + 410 + 200 + 500 + 180 + 130 INOP + 2 370

FULL 0 4 540 + 520 + 280 + 160 + 440 + 140 + 70 - 50 + 1 740SEC 1(2)/1+2 FAULT

3 5 4 810 + 550 + 290 + 170 + 460 + 160 + 80 - 60 + 1 950

FULL 0 4 740 + 500 + 320 + 160 + 440 + 160 + 90 - 60 + 1 830PRIM 1(2)(3) + SEC 1(2)FAULT 3 5 5 010 + 540 + 320 + 170 + 460 + 170 + 100 - 70 + 2 070

FULL 0 4 640 + 510 + 300 + 160 + 440 + 150 + 80 - 50 + 1 800PART OF SPOILERS

3 5 4 920 + 540 + 300 + 170 + 470 + 160 + 90 - 60 + 2 020

FULL 0 4 740 + 500 + 320 + 160 + 440 + 160 + 90 - 60 + 1 830HALF OF SPOILERS

3 5 5 010 + 540 + 320 + 170 + 460 + 170 + 100 - 70 + 2 070

FULL 0 4 990 + 490 + 380 + 170 + 460 + 170 + 110 - 80 + 1 980MOST OF SPOILERS

3 5 5 260 + 520 + 370 + 190 + 480 + 180 + 120 - 90 + 2 230

FULL 0 5 160 + 490 + 420 + 190 + 480 + 180 + 120 - 100 + 2 100ALL SPOILERS/GND SPOILER FAULT 3 5 5 430 + 520 + 410 + 200 + 500 + 180 + 130 - 110 + 2 370


PER-272/6




Continued from the previous pageFLIGHT CONTROLS SYSTEM


5 - GOOD


FAILURE

FLAPSLEVER

forLDG

ΔVREF

REFDIST

(ft) for190T

Per10T

above190T

Per 5kt

Per1000ftabove

SL

Per5kt TW

Per10°C

aboveISA

Per 1%DownSlope


If OVWPROC

applied




RUDDER JAM/RUDDER FAULT 2 10 7 450 + 950 + 630 + 460 + 1 090 + 370 + 410 - 250 + 1 050


2 170kt 9 340 + 320 N/A + 530 + 1 140 + 440 + 490 - 680 + 440

ALTN/DIRECT LAW 3 5 6 060 + 660 + 460 + 290 + 810 + 260 + 200 - 130 + 1 260

YAW DAMPER FAULT 3 5 6 060 + 660 + 460 + 290 + 810 + 260 + 200 - 130 + 1 260

FULL 0 5 790 + 640 + 480 + 280 + 790 + 250 + 190 - 120 + 1 190PRIM 1(2)(3)/1+2 FAULT

3 5 6 300 + 700 + 510 + 320 + 850 + 290 + 240 - 160 + 1 320


3 5 6 510 + 740 + 560 + 340 + 890 + 300 + 280 INOP + 1 350

PRIM 1+2+3 FAULT 3 5 7 660 + 970 + 870 + 450 + 1 140 + 400 + 520 INOP + 1 630

FULL 0 5 670 + 620 + 450 + 270 + 770 + 250 + 180 - 110 + 1 150SEC 1(2)/1+2 FAULT

3 5 6 190 + 680 + 480 + 310 + 830 + 270 + 220 - 150 + 1 280



3 5 6 420 + 720 + 530 + 330 + 880 + 290 + 260 - 170 + 1 320


3 5 6 630 + 760 + 580 + 340 + 920 + 310 + 290 - 200 + 1 350


3 5 7 220 + 880 + 740 + 400 + 1 040 + 360 + 410 - 270 + 1 490

FULL 0 7 050 + 880 + 820 + 400 + 1 050 + 360 + 410 - 270 + 1 400ALL SPOILERS/GND SPOILER FAULT 3 5 7 660 + 970 + 870 + 450 + 1 140 + 400 + 520 - 340 + 1 630


PER-273/6






4 - GOOD TO MEDIUM


FAILURE

FLAPSLEVER

forLDG

ΔVREF

REFDIST

(ft) for190T

Per10T

above190T

Per 5kt

Per1000ftabove

SL

Per5kt TW

Per10°C

aboveISA

Per 1%DownSlope


If OVWPROC

applied




RUDDER JAM/RUDDER FAULT 2 10 8 090 + 670 + 530 + 380 + 900 + 310 + 440 - 340 + 1 480


2 170kt 9 760 + 170 N/A + 420 + 920 + 360 + 490 - 710 + 840

ALTN/DIRECT LAW 3 5 6 760 + 430 + 380 + 240 + 680 + 230 + 270 - 230 + 1 580

YAW DAMPER FAULT 3 5 6 760 + 430 + 380 + 240 + 680 + 230 + 270 - 230 + 1 580

FULL 0 6 550 + 430 + 400 + 230 + 680 + 220 + 260 - 220 + 1 450PRIM 1(2)(3)/1+2 FAULT

3 5 7 030 + 450 + 420 + 250 + 710 + 240 + 300 - 260 + 1 640


3 5 7 250 + 470 + 450 + 270 + 730 + 250 + 330 INOP + 1 680

PRIM 1+2+3 FAULT 3 5 8 420 + 560 + 680 + 330 + 840 + 310 + 550 INOP + 1 980

FULL 0 6 420 + 420 + 380 + 230 + 670 + 210 + 240 - 210 + 1 420SEC 1(2)/1+2 FAULT

3 5 6 900 + 440 + 400 + 250 + 700 + 230 + 280 - 240 + 1 600



3 5 7 150 + 460 + 430 + 260 + 720 + 240 + 320 - 280 + 1 650


3 5 7 370 + 480 + 470 + 270 + 740 + 250 + 350 - 310 + 1 680


3 5 7 980 + 530 + 580 + 310 + 800 + 280 + 460 - 410 + 1 840

FULL 0 7 890 + 550 + 670 + 310 + 810 + 290 + 480 - 430 + 1 700ALL SPOILERS/GND SPOILER FAULT 3 5 8 420 + 560 + 680 + 330 + 840 + 310 + 550 - 490 + 1 980


PER-274/6






3 - MEDIUM


FAILURE

FLAPSLEVER

forLDG

ΔVREF

REFDIST

(ft) for190T

Per10T

above190T

Per 5kt

Per1000ftabove

SL

Per5kt TW

Per10°C

aboveISA

Per 1%DownSlope


If OVWPROC

applied




RUDDER JAM/RUDDER FAULT 2 10 9 050 + 770 + 570 + 430 + 1 050 + 350 + 620 - 460 + 1 310


2 170kt 10 810 + 230 N/A + 480 + 1 060 + 410 + 660 - 910 + 720

ALTN/DIRECT LAW 3 5 7 570 + 500 + 420 + 280 + 800 + 260 + 380 - 320 + 1 440

YAW DAMPER FAULT 3 5 7 570 + 500 + 420 + 280 + 800 + 260 + 380 - 320 + 1 440

FULL 0 7 340 + 500 + 440 + 270 + 800 + 250 + 370 - 310 + 1 330PRIM 1(2)(3)/1+2 FAULT

3 5 7 910 + 520 + 460 + 290 + 830 + 270 + 440 - 370 + 1 510


3 5 8 180 + 540 + 500 + 310 + 860 + 290 + 480 INOP + 1 550

PRIM 1+2+3 FAULT 3 5 9 660 + 660 + 770 + 390 + 1 000 + 350 + 810 INOP + 1 840

FULL 0 7 170 + 480 + 420 + 260 + 780 + 240 + 350 - 290 + 1 290SEC 1(2)/1+2 FAULT

3 5 7 740 + 510 + 440 + 280 + 810 + 270 + 410 - 340 + 1 470



3 5 8 050 + 530 + 480 + 300 + 850 + 280 + 460 - 390 + 1 510


3 5 8 320 + 550 + 520 + 320 + 870 + 290 + 510 - 430 + 1 550


3 5 9 100 + 620 + 650 + 360 + 940 + 320 + 670 - 570 + 1 700

FULL 0 9 010 + 640 + 740 + 360 + 960 + 330 + 700 - 600 + 1 570ALL SPOILERS/GND SPOILER FAULT 3 5 9 660 + 660 + 770 + 390 + 1 000 + 350 + 810 - 690 + 1 840


PER-275/6






2 - MEDIUM TO POOR


FAILURE

FLAPSLEVER

forLDG

ΔVREF

REFDIST

(ft) for190T

Per10T

above190T

Per 5kt

Per1000ftabove

SL

Per5kt TW

Per10°C

aboveISA

Per 1%DownSlope


If OVWPROC

applied

STAB CTL FAULT withman trim not available 2 20 11 250 + 1 130 N/A + 590 + 1 560 + 530 + 930 - 690 + 680

STAB CTL FAULT withman trim available 3 5 9 190 + 990 + 650 + 490 + 1 430 + 450 + 710 - 440 + 760

L/R/L+R ELEV FAULT 2 20 11 240 + 1 130 N/A + 590 + 1 560 + 530 + 930 - 690 + 680

RUDDER JAM/RUDDER FAULT 2 10 10 970 + 1 430 + 800 + 710 + 1 820 + 580 + 1 200 - 690 + 570


2 170kt 13 260 + 720 N/A + 770 + 1 830 + 660 + 1 290 - 1 460 + 260

ALTN/DIRECT LAW 3 5 9 190 + 990 + 650 + 490 + 1 430 + 450 + 710 - 440 + 760

YAW DAMPER FAULT 3 5 9 190 + 990 + 650 + 490 + 1 430 + 450 + 710 - 440 + 760

FULL 0 8 760 + 990 + 680 + 480 + 1 420 + 430 + 650 - 400 + 700PRIM 1(2)(3)/1+2 FAULT

3 5 9 780 + 1 090 + 740 + 540 + 1 560 + 490 + 860 - 520 + 810

FULL 0 9 090 + 1 040 + 730 + 510 + 1 490 + 460 + 730 INOP + 700PRIM 1+3/2+3 FAULT

3 5 10 250 + 1 160 + 810 + 590 + 1 650 + 520 + 1 000 INOP + 830

PRIM 1+2+3 FAULT 3 5 13 090 + 1 620 + 1 330 + 840 + 2 240 + 750 + 2 250 INOP + 1 060

FULL 0 8 470 + 940 + 640 + 450 + 1 360 + 410 + 590 - 360 + 670SEC 1(2)/1+2 FAULT

3 5 9 480 + 1 040 + 690 + 520 + 1 490 + 460 + 780 - 480 + 770

FULL 0 9 280 + 1 070 + 750 + 520 + 1 530 + 460 + 780 - 470 + 690PRIM 1(2)(3) + SEC 1(2)FAULT 3 5 10 460 + 1 200 + 840 + 600 + 1 690 + 540 + 1 060 - 630 + 830

FULL 0 8 920 + 1 010 + 700 + 490 + 1 450 + 440 + 690 - 420 + 690PART OF SPOILERS

3 5 9 990 + 1 120 + 770 + 560 + 1 600 + 500 + 920 - 560 + 800

FULL 0 9 280 + 1 070 + 750 + 520 + 1 530 + 460 + 780 - 470 + 690HALF OF SPOILERS

3 5 10 460 + 1 200 + 840 + 600 + 1 690 + 540 + 1 060 - 630 + 830

FULL 0 10 540 + 1 290 + 990 + 640 + 1 800 + 570 + 1 160 - 660 + 770MOST OF SPOILERS

3 5 11 910 + 1 430 + 1 100 + 730 + 1 990 + 650 + 1 630 - 890 + 940

FULL 0 11 550 + 1 470 + 1 200 + 740 + 2 040 + 650 + 1 570 - 830 + 860ALL SPOILERS/GND SPOILER FAULT 3 5 13 090 + 1 620 + 1 330 + 840 + 2 240 + 750 + 2 250 - 1 130 + 1 060


PER-276/6






1 - POOR


FAILURE

FLAPSLEVER

forLDG

ΔVREF

REFDIST

(ft) for190T

Per10T

above190T

Per 5kt

Per1000ftabove

SL

Per5kt TW

Per10°C

aboveISA

Per 1%DownSlope


If OVWPROC

applied

STAB CTL FAULT withman trim not available 2 20 16 230 + 1 150 N/A + 610 + 2 020 + 580 + 3 410 - 1 660 + 680

STAB CTL FAULT withman trim available 3 5 13 850 + 1 030 + 610 + 530 + 1 940 + 500 + 2 970 - 1 320 + 760

L/R/L+R ELEV FAULT 2 20 16 230 + 1 150 N/A + 620 + 2 020 + 570 + 3 420 - 1 660 + 680

RUDDER JAM/RUDDER FAULT 2 10 15 990 + 1 450 + 760 + 730 + 2 260 + 630 + 3 810 - 1 680 + 570


2 170kt Landing Distance greater than 18 000 ft for all conditions

ALTN/DIRECT LAW 3 5 13 850 + 1 030 + 610 + 530 + 1 940 + 500 + 2 970 - 1 320 + 760

YAW DAMPER FAULT 3 5 13 850 + 1 030 + 610 + 530 + 1 940 + 500 + 2 970 - 1 320 + 760

FULL 0 13 460 + 1 020 + 640 + 510 + 1 930 + 490 + 2 910 - 1 290 + 700PRIM 1(2)(3)/1+2 FAULT

3 5 14 830 + 1 110 + 690 + 570 + 2 020 + 530 + 3 430 - 1 530 + 810

FULL 0 13 990 + 1 070 + 680 + 540 + 1 980 + 510 + 3 150 INOP + 700PRIM 1+3/2+3 FAULT


PRIM 1+2+3 FAULT 3 5 Landing Distance greater than 18 000 ft for all conditions

FULL 0 12 960 + 980 + 600 + 490 + 1 880 + 470 + 2 690 - 1 180 + 670SEC 1(2)/1+2 FAULT

3 5 14 310 + 1 070 + 650 + 550 + 1 980 + 520 + 3 180 - 1 420 + 770

FULL 0 14 260 + 1 090 + 710 + 550 + 2 000 + 520 + 3 280 - 1 460 + 690PRIM 1(2)(3) + SEC 1(2)FAULT 3 5 15 880 + 1 200 + 780 + 620 + 2 120 + 580 + 3 970 - 1 780 + 830

FULL 0 13 710 + 1 040 + 660 + 520 + 1 960 + 490 + 3 020 - 1 340 + 690PART OF SPOILERS

3 5 15 140 + 1 140 + 710 + 580 + 2 050 + 550 + 3 590 - 1 600 + 800

FULL 0 14 260 + 1 090 + 710 + 550 + 2 000 + 520 + 3 280 - 1 460 + 690HALF OF SPOILERS

3 5 15 880 + 1 200 + 780 + 620 + 2 120 + 580 + 3 970 - 1 780 + 830

FULL 0 16 340 + 1 280 + 910 + 640 + 2 180 + 600 + 4 370 - 1 970 + 770MOST OF SPOILERS


FULL 0 Landing Distance greater than 18 000 ft for all conditionsALL SPOILERS/GND SPOILER FAULT 3 5 Landing Distance greater than 18 000 ft for all conditions


PER-27A1/6




Ident.: PER-27A-00014129.0090001 / 09 APR 15Applicable to: ALL

SLATS AND FLAPS SYSTEM


6 - DRY


FAILURE

FLAPSLEVER

forLDG

ΔVREF

REFDIST

(ft) for190T

Per10T

above190T

Per 5kt

Per1000ftabove

SL

Per5kt TW

Per10°C

aboveISA

Per 1%DownSlope


If OVWPROC

applied

0≤FLAPS<1+F 2 30 6 060 + 680 N/A + 210 + 480 + 200 + 140 - 90 + 2 970

1+F≤FLAPS<2 2 15 5 300 + 600 + 310 + 190 + 470 + 170 + 120 - 70 + 2 700

2≤FLAPS<3 2 10 4 960 + 580 + 290 + 180 + 480 + 160 + 90 - 60 + 2 340

FLAPS=3 3 5 4 750 + 550 + 280 + 170 + 470 + 150 + 80 - 50 + 1 900

FLAPSFAULT

FLAPS>3 FULL 5 4 710 + 530 + 280 + 170 + 460 + 140 + 70 - 50 + 1 410

0≤SLATS<1 2 30 6 010 + 650 N/A + 210 + 480 + 190 + 120 - 90 + 1 390

1≤SLATS<2 2 15 5 210 + 600 + 300 + 190 + 470 + 170 + 100 - 60 + 2 100SLATSFAULT

SLATS≥2 3 5 4 780 + 550 + 280 + 170 + 470 + 150 + 80 - 50 + 1 880

NO FLAPS/NO SLATS 1 50 7 200 + 760 N/A + 250 + 510 + 230 + 170 - 130 + 2 090

0≤FLAPS<1+F 1 50 7 200 + 760 N/A + 250 + 510 + 230 + 170 - 130 + 2 090

1+F≤FLAPS<2 2 40 6 700 + 690 N/A + 230 + 500 + 210 + 150 - 120 + 1 630

2≤FLAPS<3 2 30 6 010 + 650 N/A + 210 + 480 + 190 + 120 - 90 + 1 390

FLAPS=3 2 25 5 770 + 610 N/A + 200 + 470 + 180 + 110 - 90 + 880

0≤SLATS<1

FLAPS>3 2 25 5 720 + 590 N/A + 190 + 470 + 180 + 90 - 80 + 370

0≤FLAPS<1+F 2 30 5 970 + 670 N/A + 210 + 480 + 190 + 130 - 90 + 2 930

1+F≤FLAPS<2 2 20 5 570 + 620 N/A + 190 + 470 + 180 + 120 - 80 + 2 480

2≤FLAPS<3 2 15 5 210 + 600 + 300 + 190 + 470 + 170 + 100 - 60 + 2 100

FLAPS=3 3 10 5 010 + 570 + 280 + 180 + 480 + 150 + 80 - 60 + 1 610

1≤SLATS<2

FLAPS>3 FULL 10 4 960 + 550 + 290 + 170 + 470 + 150 + 80 - 60 + 1 120

0≤FLAPS<1+F 2 30 5 970 + 670 N/A + 210 + 480 + 190 + 130 - 90 + 2 930

1+F≤FLAPS<2 2 15 5 300 + 600 + 310 + 190 + 470 + 170 + 120 - 70 + 2 700

2≤FLAPS<3 2 10 4 960 + 580 + 290 + 180 + 480 + 160 + 90 - 60 + 2 340

FLAPS=3 3 5 4 780 + 550 + 280 + 170 + 470 + 150 + 80 - 50 + 1 880

SLATS≥2

FLAPS>3 FULL 0 4 510 + 520 + 270 + 160 + 450 + 140 + 70 - 40 + 1 670


PER-27A2/6




Continued from the previous pageSLATS AND FLAPS SYSTEM


5 - GOOD


FAILURE

FLAPSLEVER

forLDG

ΔVREF

REFDIST

(ft) for190T

Per10T

above190T

Per 5kt

Per1000ftabove

SL

Per5kt TW

Per10°C

aboveISA

Per 1%DownSlope


If OVWPROC

applied

0≤FLAPS<1+F 2 30 8 390 + 930 N/A + 440 + 990 + 380 + 400 - 300 + 1 730

1+F≤FLAPS<2 2 15 7 130 + 790 + 530 + 380 + 910 + 320 + 320 - 210 + 1 670

2≤FLAPS<3 2 10 6 500 + 710 + 490 + 330 + 860 + 290 + 250 - 160 + 1 530

FLAPS=3 3 5 6 060 + 660 + 460 + 290 + 810 + 260 + 200 - 130 + 1 260

FLAPSFAULT

FLAPS>3 FULL 5 5 900 + 620 + 430 + 280 + 770 + 240 + 170 - 120 + 900

0≤SLATS<1 2 30 8 070 + 840 N/A + 400 + 910 + 350 + 300 - 270 + 700


SLATS≥2 3 5 6 080 + 660 + 460 + 290 + 810 + 270 + 210 - 130 + 1 240

NO FLAPS/NO SLATS 1 50 10 230 + 1 110 N/A + 550 + 1 110 + 470 + 510 - 450 + 920

0≤FLAPS<1+F 1 50 10 230 + 1 110 N/A + 550 + 1 110 + 470 + 510 - 450 + 920

1+F≤FLAPS<2 2 40 9 340 + 980 N/A + 480 + 1 030 + 420 + 420 - 380 + 690

2≤FLAPS<3 2 30 8 070 + 840 N/A + 400 + 910 + 350 + 300 - 270 + 700

FLAPS=3 2 25 7 580 + 760 N/A + 360 + 860 + 320 + 240 - 230 + 430

0≤SLATS<1

FLAPS>3 2 25 7 340 + 710 N/A + 340 + 810 + 290 + 190 - 200 + 170

0≤FLAPS<1+F 2 30 8 100 + 880 N/A + 420 + 940 + 360 + 360 - 270 + 1 730

1+F≤FLAPS<2 2 20 7 550 + 820 N/A + 380 + 910 + 330 + 330 - 240 + 1 450

2≤FLAPS<3 2 15 6 880 + 740 + 490 + 350 + 860 + 300 + 260 - 180 + 1 300

FLAPS=3 3 10 6 440 + 680 + 470 + 310 + 830 + 280 + 220 - 160 + 1 000

1≤SLATS<2

FLAPS>3 FULL 10 6 270 + 640 + 440 + 290 + 790 + 260 + 180 - 140 + 660

0≤FLAPS<1+F 2 30 8 100 + 880 N/A + 420 + 940 + 360 + 360 - 270 + 1 730

1+F≤FLAPS<2 2 15 7 130 + 790 + 530 + 380 + 910 + 320 + 320 - 210 + 1 670

2≤FLAPS<3 2 10 6 500 + 710 + 490 + 330 + 860 + 290 + 250 - 160 + 1 530

FLAPS=3 3 5 6 080 + 660 + 460 + 290 + 810 + 270 + 210 - 130 + 1 240

SLATS≥2

FLAPS>3 FULL 0 5 580 + 600 + 430 + 260 + 750 + 230 + 160 - 100 + 1 120


PER-27A3/6






4 - GOOD TO MEDIUM


FAILURE

FLAPSLEVER

forLDG

ΔVREF

REFDIST

(ft) for190T

Per10T

above190T

Per 5kt

Per1000ftabove

SL

Per5kt TW

Per10°C

aboveISA

Per 1%DownSlope


If OVWPROC

applied

0≤FLAPS<1+F 2 30 8 780 + 490 N/A + 310 + 740 + 280 + 400 - 380 + 2 500

1+F≤FLAPS<2 2 15 7 740 + 470 + 420 + 280 + 720 + 260 + 350 - 310 + 2 230

2≤FLAPS<3 2 10 7 160 + 440 + 390 + 260 + 700 + 240 + 300 - 250 + 1 960

FLAPS=3 3 5 6 760 + 430 + 380 + 240 + 680 + 230 + 270 - 230 + 1 580

FLAPSFAULT

FLAPS>3 FULL 5 6 600 + 420 + 360 + 230 + 670 + 210 + 230 - 210 + 1 150

0≤SLATS<1 2 30 8 520 + 480 N/A + 300 + 720 + 270 + 330 - 340 + 1 120


SLATS≥2 3 5 6 790 + 430 + 380 + 240 + 690 + 220 + 270 - 230 + 1 550


0≤FLAPS<1+F 1 50 10 280 + 530 N/A + 360 + 780 + 340 + 460 - 490 + 1 710

1+F≤FLAPS<2 2 40 9 610 + 510 N/A + 340 + 760 + 320 + 410 - 440 + 1 250

2≤FLAPS<3 2 30 8 520 + 480 N/A + 300 + 720 + 270 + 330 - 340 + 1 120

FLAPS=3 2 25 8 110 + 470 N/A + 280 + 700 + 260 + 290 - 310 + 670

0≤SLATS<1

FLAPS>3 2 25 7 900 + 450 N/A + 270 + 690 + 250 + 240 - 280 + 270

0≤FLAPS<1+F 2 30 8 520 + 480 N/A + 300 + 720 + 280 + 370 - 340 + 2 480

1+F≤FLAPS<2 2 20 8 100 + 470 N/A + 290 + 720 + 260 + 360 - 330 + 2 020

2≤FLAPS<3 2 15 7 490 + 450 + 390 + 270 + 700 + 250 + 300 - 270 + 1 750

FLAPS=3 3 10 7 110 + 440 + 390 + 250 + 690 + 240 + 270 - 250 + 1 320

1≤SLATS<2

FLAPS>3 FULL 10 6 930 + 430 + 370 + 240 + 680 + 230 + 240 - 220 + 890

0≤FLAPS<1+F 2 30 8 520 + 480 N/A + 300 + 720 + 280 + 370 - 340 + 2 480

1+F≤FLAPS<2 2 15 7 740 + 470 + 420 + 280 + 720 + 260 + 350 - 310 + 2 230

2≤FLAPS<3 2 10 7 160 + 440 + 390 + 260 + 700 + 240 + 300 - 250 + 1 960

FLAPS=3 3 5 6 790 + 430 + 380 + 240 + 690 + 220 + 270 - 230 + 1 550

SLATS≥2

FLAPS>3 FULL 0 6 310 + 410 + 360 + 220 + 660 + 210 + 230 - 190 + 1 370


PER-27A4/6






3 - MEDIUM


FAILURE

FLAPSLEVER

forLDG

ΔVREF

REFDIST

(ft) for190T

Per10T

above190T

Per 5kt

Per1000ftabove

SL

Per5kt TW

Per10°C

aboveISA

Per 1%DownSlope


If OVWPROC

applied

0≤FLAPS<1+F 2 30 9 920 + 570 N/A + 360 + 870 + 330 + 580 - 530 + 2 310

1+F≤FLAPS<2 2 15 8 730 + 540 + 470 + 330 + 850 + 300 + 510 - 430 + 2 040

2≤FLAPS<3 2 10 8 060 + 510 + 430 + 300 + 820 + 270 + 430 - 360 + 1 800

FLAPS=3 3 5 7 570 + 500 + 420 + 280 + 800 + 260 + 380 - 320 + 1 440

FLAPSFAULT

FLAPS>3 FULL 5 7 340 + 480 + 400 + 260 + 780 + 250 + 330 - 290 + 1 040

0≤SLATS<1 2 30 9 550 + 560 N/A + 340 + 840 + 310 + 470 - 470 + 1 010


SLATS≥2 3 5 7 600 + 500 + 420 + 280 + 800 + 250 + 380 - 320 + 1 420


0≤FLAPS<1+F 1 50 11 570 + 620 N/A + 420 + 920 + 380 + 650 - 660 + 1 560

1+F≤FLAPS<2 2 40 10 780 + 600 N/A + 390 + 900 + 360 + 580 - 600 + 1 130

2≤FLAPS<3 2 30 9 550 + 560 N/A + 340 + 840 + 310 + 470 - 470 + 1 010

FLAPS=3 2 25 9 040 + 540 N/A + 320 + 820 + 290 + 410 - 420 + 600

0≤SLATS<1

FLAPS>3 2 25 8 740 + 520 N/A + 310 + 800 + 280 + 340 - 370 + 240

0≤FLAPS<1+F 2 30 9 600 + 560 N/A + 350 + 850 + 320 + 530 - 470 + 2 290

1+F≤FLAPS<2 2 20 9 130 + 550 N/A + 330 + 840 + 300 + 520 - 460 + 1 850

2≤FLAPS<3 2 15 8 420 + 520 + 430 + 310 + 820 + 290 + 440 - 380 + 1 600

FLAPS=3 3 10 7 950 + 510 + 420 + 290 + 810 + 270 + 390 - 340 + 1 200

1≤SLATS<2

FLAPS>3 FULL 10 7 710 + 490 + 400 + 280 + 790 + 260 + 340 - 310 + 800

0≤FLAPS<1+F 2 30 9 600 + 560 N/A + 350 + 850 + 320 + 530 - 470 + 2 290

1+F≤FLAPS<2 2 15 8 730 + 540 + 470 + 330 + 850 + 300 + 510 - 430 + 2 040

2≤FLAPS<3 2 10 8 060 + 510 + 430 + 300 + 820 + 270 + 430 - 360 + 1 800

FLAPS=3 3 5 7 600 + 500 + 420 + 280 + 800 + 250 + 380 - 320 + 1 420

SLATS≥2

FLAPS>3 FULL 0 7 030 + 470 + 400 + 250 + 770 + 240 + 330 - 260 + 1 250


PER-27A5/6






2 - MEDIUM TO POOR


FAILURE

FLAPSLEVER

forLDG

ΔVREF

REFDIST

(ft) for190T

Per10T

above190T

Per 5kt

Per1000ftabove

SL

Per5kt TW

Per10°C

aboveISA

Per 1%DownSlope


If OVWPROC

applied

0≤FLAPS<1+F 2 30 13 370 + 1 300 N/A + 710 + 1 760 + 630 + 1 450 - 1 000 + 1 220

1+F≤FLAPS<2 2 15 11 290 + 1 190 + 750 + 630 + 1 660 + 560 + 1 140 - 720 + 1 020

2≤FLAPS<3 2 10 10 160 + 1 090 + 690 + 560 + 1 560 + 500 + 890 - 550 + 920

FLAPS=3 3 5 9 190 + 990 + 650 + 490 + 1 430 + 450 + 710 - 440 + 760

FLAPSFAULT

FLAPS>3 FULL 5 8 700 + 910 + 580 + 450 + 1 330 + 410 + 550 - 380 + 530

0≤SLATS<1 2 30 12 320 + 1 170 N/A + 630 + 1 600 + 570 + 990 - 810 + 470

1≤SLATS<2 2 15 10 700 + 1 110 + 680 + 580 + 1 550 + 520 + 910 - 620 + 800SLATSFAULT

SLATS≥2 3 5 9 220 + 1 000 + 650 + 490 + 1 440 + 440 + 710 - 440 + 730

NO FLAPS/NO SLATS 1 50 15 760 + 1 390 N/A + 800 + 1 830 + 720 + 1 630 - 1 290 + 800

0≤FLAPS<1+F 1 50 15 760 + 1 390 N/A + 800 + 1 830 + 720 + 1 630 - 1 290 + 800

1+F≤FLAPS<2 2 40 14 230 + 1 300 N/A + 730 + 1 740 + 650 + 1 330 - 1 080 + 520

2≤FLAPS<3 2 30 12 320 + 1 170 N/A + 630 + 1 600 + 570 + 990 - 810 + 470

FLAPS=3 2 25 11 230 + 1 070 N/A + 560 + 1 470 + 510 + 770 - 660 + 280

0≤SLATS<1

FLAPS>3 2 25 10 540 + 980 N/A + 510 + 1 360 + 470 + 580 - 550 + 120

0≤FLAPS<1+F 2 30 12 670 + 1 220 N/A + 660 + 1 660 + 590 + 1 240 - 870 + 1 240

1+F≤FLAPS<2 2 20 11 890 + 1 210 N/A + 640 + 1 660 + 570 + 1 180 - 800 + 910

2≤FLAPS<3 2 15 10 700 + 1 110 + 680 + 580 + 1 550 + 520 + 910 - 620 + 800

FLAPS=3 3 10 9 730 + 1 010 + 640 + 510 + 1 450 + 460 + 730 - 500 + 610

1≤SLATS<2

FLAPS>3 FULL 10 9 190 + 930 + 570 + 470 + 1 340 + 420 + 560 - 420 + 400

0≤FLAPS<1+F 2 30 12 670 + 1 220 N/A + 660 + 1 660 + 590 + 1 240 - 870 + 1 240

1+F≤FLAPS<2 2 15 11 290 + 1 190 + 750 + 630 + 1 660 + 560 + 1 140 - 720 + 1 020

2≤FLAPS<3 2 10 10 160 + 1 090 + 690 + 560 + 1 560 + 500 + 890 - 550 + 920

FLAPS=3 3 5 9 220 + 1 000 + 650 + 490 + 1 440 + 440 + 710 - 440 + 730

SLATS≥2

FLAPS>3 FULL 0 8 250 + 900 + 600 + 430 + 1 310 + 390 + 540 - 330 + 630


PER-27A6/6






1 - POOR


FAILURE

FLAPSLEVER

forLDG

ΔVREF

REFDIST

(ft) for190T

Per10T

above190T

Per 5kt

Per1000ftabove

SL

Per5kt TW

Per10°C

aboveISA

Per 1%DownSlope


If OVWPROC

applied

0≤FLAPS<1+F 2 30 Landing Distance greater than 18 000 ft for all conditions

1+F≤FLAPS<2 2 15 16 560 + 1 200 + 710 + 650 + 2 080 + 600 + 3 930 - 1 800 + 1 020

2≤FLAPS<3 2 10 15 140 + 1 110 + 660 + 580 + 2 020 + 550 + 3 430 - 1 530 + 920

FLAPS=3 3 5 13 850 + 1 030 + 610 + 530 + 1 940 + 500 + 2 970 - 1 320 + 760

FLAPSFAULT

FLAPS>3 FULL 5 13 000 + 960 + 560 + 490 + 1 860 + 470 + 2 520 - 1 140 + 530

0≤SLATS<1 2 30 17 300 + 1 190 N/A + 660 + 2 050 + 620 + 3 460 - 1 780 + 470

1≤SLATS<2 2 15 15 690 + 1 130 + 640 + 610 + 2 020 + 560 + 3 430 - 1 600 + 800SLATSFAULT

SLATS≥2 3 5 13 870 + 1 030 + 620 + 530 + 1 930 + 500 + 2 970 - 1 320 + 730

NO FLAPS/NO SLATS 1 50 Landing Distance greater than 18 000 ft for all conditions


1+F≤FLAPS<2 2 40 Landing Distance greater than 18 000 ft for all conditions

2≤FLAPS<3 2 30 17 300 + 1 190 N/A + 660 + 2 050 + 620 + 3 460 - 1 780 + 470

FLAPS=3 2 25 15 890 + 1 100 N/A + 600 + 1 970 + 560 + 2 980 - 1 520 + 280

0≤SLATS<1

FLAPS>3 2 25 14 840 + 1 020 N/A + 550 + 1 890 + 530 + 2 500 - 1 310 + 120

0≤FLAPS<1+F 2 30 17 850 + 1 230 N/A + 680 + 2 090 + 640 + 3 950 - 1 910 + 1 240

1+F≤FLAPS<2 2 20 17 160 + 1 220 N/A + 660 + 2 080 + 610 + 3 930 - 1 870 + 910

2≤FLAPS<3 2 15 15 690 + 1 130 + 640 + 610 + 2 020 + 560 + 3 430 - 1 600 + 800

FLAPS=3 3 10 14 390 + 1 050 + 600 + 550 + 1 960 + 520 + 2 990 - 1 370 + 610

1≤SLATS<2

FLAPS>3 FULL 10 13 490 + 970 + 550 + 510 + 1 880 + 490 + 2 530 - 1 190 + 400

0≤FLAPS<1+F 2 30 17 850 + 1 230 N/A + 680 + 2 090 + 640 + 3 950 - 1 910 + 1 240

1+F≤FLAPS<2 2 15 16 560 + 1 200 + 710 + 650 + 2 080 + 600 + 3 930 - 1 800 + 1 020

2≤FLAPS<3 2 10 15 140 + 1 110 + 660 + 580 + 2 020 + 550 + 3 430 - 1 530 + 920

FLAPS=3 3 5 13 870 + 1 030 + 620 + 530 + 1 930 + 500 + 2 970 - 1 320 + 730

SLATS≥2

FLAPS>3 FULL 0 12 560 + 940 + 560 + 470 + 1 850 + 450 + 2 510 - 1 100 + 630


PER-281/2





FUEL SYSTEM


6 - DRY


FAILURE

FLAPSLEVER

forLDG

ΔVREF

REFDIST

(ft) for190T

Per10T

above190T

Per 5kt

Per1000ftabove

SL

Per5kt TW

Per10°C

aboveISA

Per 1%DownSlope


If OVWPROC

applied

FULL 10 4 930 + 550 + 290 + 170 + 470 + 160 + 80 - 60 + 1 150T TANK UNUSABLE withCG>aft CG limit shown inQRH ABN-28.06 3 15 5 220 + 580 + 290 + 190 + 470 + 170 + 90 - 70 + 1 380


5 - GOOD


FAILURE

FLAPSLEVER

forLDG

ΔVREF

REFDIST

(ft) for190T

Per10T

above190T

Per 5kt

Per1000ftabove

SL

Per5kt TW

Per10°C

aboveISA

Per 1%DownSlope


If OVWPROC

applied

FULL 10 6 240 + 640 + 440 + 290 + 780 + 260 + 180 - 140 + 690T TANK UNUSABLE withCG>aft CG limit shown inQRH ABN-28.06 3 15 6 790 + 710 + 470 + 340 + 830 + 290 + 230 - 180 + 820


4 - GOOD TO MEDIUM


FAILURE

FLAPSLEVER

forLDG

ΔVREF

REFDIST

(ft) for190T

Per10T

above190T

Per 5kt

Per1000ftabove

SL

Per5kt TW

Per10°C

aboveISA

Per 1%DownSlope


If OVWPROC

applied

FULL 10 6 910 + 430 + 370 + 240 + 680 + 220 + 240 - 220 + 910T TANK UNUSABLE withCG>aft CG limit shown inQRH ABN-28.06 3 15 7 410 + 450 + 380 + 270 + 690 + 240 + 280 - 270 + 1 110


PER-282/2




Continued from the previous pageFUEL SYSTEM


3 - MEDIUM


FAILURE

FLAPSLEVER

forLDG

ΔVREF

REFDIST

(ft) for190T

Per10T

above190T

Per 5kt

Per1000ftabove

SL

Per5kt TW

Per10°C

aboveISA

Per 1%DownSlope


If OVWPROC

applied

FULL 10 7 680 + 490 + 400 + 280 + 790 + 260 + 340 - 310 + 830T TANK UNUSABLE withCG>aft CG limit shown inQRH ABN-28.06 3 15 8 280 + 520 + 420 + 300 + 810 + 280 + 400 - 370 + 1 010


2 - MEDIUM TO POOR


FAILURE

FLAPSLEVER

forLDG

ΔVREF

REFDIST

(ft) for190T

Per10T

above190T

Per 5kt

Per1000ftabove

SL

Per5kt TW

Per10°C

aboveISA

Per 1%DownSlope


If OVWPROC

applied

FULL 10 9 170 + 930 + 570 + 470 + 1 350 + 420 + 560 - 420 + 420T TANK UNUSABLE withCG>aft CG limit shown inQRH ABN-28.06 3 15 10 210 + 1 030 + 620 + 540 + 1 450 + 480 + 740 - 550 + 520


1 - POOR


FAILURE

FLAPSLEVER

forLDG

ΔVREF

REFDIST

(ft) for190T

Per10T

above190T

Per 5kt

Per1000ftabove

SL

Per5kt TW

Per10°C

aboveISA

Per 1%DownSlope


If OVWPROC

applied

FULL 10 13 460 + 970 + 550 + 510 + 1 870 + 490 + 2 520 - 1 180 + 420T TANK UNUSABLE withCG>aft CG limit shown inQRH ABN-28.06 3 15 14 870 + 1 070 + 590 + 570 + 1 960 + 530 + 2 980 - 1 420 + 520


PER-291/6





HYDRAULIC SYSTEM


6 - DRY


FAILURE

FLAPSLEVER

forLDG

ΔVREF

REFDIST

(ft) for190T

Per10T

above190T

Per 5kt

Per1000ftabove

SL

Per5kt TW

Per10°C

aboveISA

Per 1%DownSlope


If OVWPROC

applied

FULL 0 4 900 + 450 + 290 + 160 + 450 + 140 + 90 - 70 + 1 730G SYS LO PR

3 5 5 200 + 480 + 300 + 170 + 460 + 160 + 100 - 80 + 1 960

FULL 0 4 640 + 510 + 300 + 160 + 440 + 150 + 80 0 + 1 800B SYS LO PR

3 5 4 920 + 540 + 300 + 170 + 470 + 160 + 90 - 10 + 2 020

FULL 0 4 540 + 520 + 290 + 150 + 440 + 150 + 70 0 + 1 740Y SYS LO PR

3 5 4 820 + 550 + 290 + 170 + 470 + 150 + 80 - 10 + 1 950

FULL 0 / 140kt 6 340 + 660 + 440 + 230 + 630 + 210 + 230 - 130 + 1 650B SYS LO PR with G SYSsupplied by the RAT(Calculated with 140ktmin)

3 5 / 140kt 6 700 + 740 + 450 + 240 + 640 + 230 + 270 - 180 + 1 910

FULL 0 / 140kt 5 250 + 420 + 350 + 180 + 480 + 160 + 120 - 50 + 1 780Y SYS LO PR with G SYSsupplied by the RAT(Calculated with 140ktmin)

3 5 / 140kt 5 500 + 460 + 350 + 190 + 490 + 180 + 130 - 60 + 2 030

0≤FLAPS<1+F 2 30 6 630 + 590 N/A + 220 + 490 + 200 + 170 - 50 + 3 160

1+F≤FLAPS<2 2 20 6 330 + 510 N/A + 210 + 490 + 200 + 180 - 50 + 2 640

2≤FLAPS<3 2 20 6 240 + 520 N/A + 210 + 490 + 190 + 150 - 50 + 2 030

FLAPS=3 3 15 6 090 + 470 + 370 + 210 + 500 + 190 + 150 - 40 + 1 500

G + Y

FLAPS>3 FULL 10 5 770 + 450 + 370 + 200 + 500 + 180 + 130 - 30 + 1 240

SLATS<1 2 30 8 470 + 910 N/A + 300 + 670 + 270 + 320 - 210 + 1 400

1≤SLATS<2 2 25 8 080 + 900 N/A + 280 + 660 + 260 + 310 - 180 + 1 630G + B

SLATS≥2 3 15 7 440 + 750 + 450 + 270 + 660 + 240 + 290 - 150 + 1 410

B + Y 2 20 5 780 + 610 N/A + 200 + 480 + 180 + 130 INOP + 2 130


PER-292/6




Continued from the previous pageHYDRAULIC SYSTEM


5 - GOOD


FAILURE

FLAPSLEVER

forLDG

ΔVREF

REFDIST

(ft) for190T

Per10T

above190T

Per 5kt

Per1000ftabove

SL

Per5kt TW

Per10°C

aboveISA

Per 1%DownSlope


If OVWPROC

applied

FULL 0 6 150 + 650 + 490 + 300 + 850 + 270 + 230 - 160 + 1 050G SYS LO PR

3 5 6 750 + 730 + 530 + 340 + 930 + 300 + 290 - 200 + 1 200

FULL 0 5 880 + 660 + 500 + 290 + 810 + 260 + 200 - 30 + 1 180B SYS LO PR

3 5 6 420 + 720 + 530 + 330 + 880 + 290 + 260 - 60 + 1 320

FULL 0 5 680 + 620 + 450 + 270 + 770 + 240 + 180 - 20 + 1 160Y SYS LO PR

3 5 6 200 + 680 + 490 + 310 + 840 + 270 + 220 - 50 + 1 290


3 5 / 140kt 7 240 + 900 + 610 + 360 + 970 + 320 + 380 - 240 + 1 400


3 5 / 140kt 7 360 + 840 + 660 + 390 + 1 050 + 350 + 400 - 310 + 1 270

0≤FLAPS<1+F 2 30 9 610 + 1 090 N/A + 530 + 1 180 + 460 + 620 - 320 + 1 800

1+F≤FLAPS<2 2 20 9 070 + 1 040 N/A + 500 + 1 150 + 430 + 600 - 300 + 1 480

2≤FLAPS<3 2 20 8 800 + 990 N/A + 470 + 1 110 + 410 + 500 - 260 + 1 110

FLAPS=3 3 15 8 350 + 910 + 670 + 460 + 1 080 + 390 + 450 - 230 + 840

G + Y

FLAPS>3 FULL 10 7 640 + 820 + 630 + 400 + 1 020 + 350 + 350 - 160 + 680

SLATS<1 2 30 9 620 + 1 130 N/A + 490 + 1 090 + 420 + 510 - 290 + 810

1≤SLATS<2 2 25 9 100 + 1 090 N/A + 460 + 1 050 + 400 + 480 - 250 + 1 010G + B

SLATS≥2 3 15 8 170 + 970 + 630 + 420 + 1 000 + 360 + 420 - 180 + 930

B + Y 2 20 8 140 + 930 N/A + 430 + 1 000 + 380 + 410 INOP + 1 230


PER-293/6






4 - GOOD TO MEDIUM


FAILURE

FLAPSLEVER

forLDG

ΔVREF

REFDIST

(ft) for190T

Per10T

above190T

Per 5kt

Per1000ftabove

SL

Per5kt TW

Per10°C

aboveISA

Per 1%DownSlope


If OVWPROC

applied

FULL 0 6 480 + 430 + 390 + 230 + 680 + 210 + 250 - 210 + 1 410G SYS LO PR

3 5 6 970 + 450 + 410 + 250 + 700 + 240 + 290 - 250 + 1 620

FULL 0 6 650 + 440 + 420 + 240 + 690 + 220 + 270 - 100 + 1 450B SYS LO PR

3 5 7 150 + 460 + 430 + 260 + 720 + 240 + 320 - 140 + 1 650

FULL 0 6 420 + 420 + 380 + 230 + 670 + 220 + 240 - 80 + 1 420Y SYS LO PR

3 5 6 910 + 440 + 400 + 250 + 700 + 230 + 290 - 110 + 1 610


3 5 / 140kt 7 550 + 550 + 500 + 280 + 750 + 260 + 380 - 280 + 1 760


3 5 / 140kt 7 530 + 490 + 490 + 280 + 750 + 260 + 370 - 280 + 1 700

0≤FLAPS<1+F 2 30 9 190 + 510 N/A + 330 + 760 + 310 + 470 - 270 + 2 710

1+F≤FLAPS<2 2 20 8 840 + 520 N/A + 320 + 770 + 290 + 480 - 270 + 2 220

2≤FLAPS<3 2 20 8 630 + 510 N/A + 310 + 750 + 280 + 420 - 240 + 1 690

FLAPS=3 3 15 8 340 + 510 + 500 + 320 + 760 + 280 + 400 - 230 + 1 230

G + Y

FLAPS>3 FULL 10 7 790 + 490 + 490 + 290 + 760 + 270 + 340 - 170 + 1 000

SLATS<1 2 30 9 540 + 620 N/A + 350 + 790 + 310 + 450 - 320 + 1 280

1≤SLATS<2 2 25 9 100 + 610 N/A + 330 + 770 + 300 + 440 - 280 + 1 500G + B

SLATS≥2 3 15 8 360 + 570 + 510 + 310 + 760 + 290 + 410 - 230 + 1 290

B + Y 2 20 8 670 + 510 N/A + 320 + 760 + 290 + 420 INOP + 1 710


PER-294/6






3 - MEDIUM


FAILURE

FLAPSLEVER

forLDG

ΔVREF

REFDIST

(ft) for190T

Per10T

above190T

Per 5kt

Per1000ftabove

SL

Per5kt TW

Per10°C

aboveISA

Per 1%DownSlope


If OVWPROC

applied

FULL 0 7 240 + 490 + 430 + 260 + 790 + 240 + 360 - 300 + 1 290G SYS LO PR

3 5 7 840 + 520 + 450 + 290 + 830 + 260 + 420 - 350 + 1 490

FULL 0 7 460 + 510 + 460 + 280 + 810 + 250 + 390 - 160 + 1 320B SYS LO PR

3 5 8 050 + 530 + 480 + 300 + 850 + 280 + 460 - 210 + 1 510

FULL 0 7 180 + 480 + 420 + 260 + 780 + 240 + 350 - 130 + 1 300Y SYS LO PR

3 5 7 760 + 510 + 440 + 280 + 820 + 270 + 410 - 180 + 1 470


3 5 / 140kt 8 540 + 570 + 550 + 320 + 890 + 300 + 550 - 410 + 1 610


3 5 / 140kt 8 520 + 570 + 550 + 320 + 880 + 300 + 540 - 410 + 1 570

0≤FLAPS<1+F 2 30 10 440 + 610 N/A + 390 + 910 + 360 + 680 - 410 + 2 520

1+F≤FLAPS<2 2 20 10 060 + 610 N/A + 380 + 910 + 340 + 690 - 410 + 2 040

2≤FLAPS<3 2 20 9 790 + 600 N/A + 360 + 890 + 330 + 600 - 370 + 1 550

FLAPS=3 3 15 9 420 + 600 + 560 + 360 + 900 + 330 + 570 - 340 + 1 130

G + Y

FLAPS>3 FULL 10 8 750 + 570 + 540 + 330 + 880 + 310 + 490 - 260 + 900

SLATS<1 2 30 10 780 + 630 N/A + 400 + 930 + 360 + 650 - 470 + 1 160

1≤SLATS<2 2 25 10 300 + 610 N/A + 380 + 910 + 340 + 630 - 420 + 1 360G + B

SLATS≥2 3 15 9 440 + 600 + 560 + 360 + 900 + 320 + 580 - 340 + 1 170

B + Y 2 20 9 850 + 600 N/A + 370 + 900 + 330 + 620 INOP + 1 570


PER-295/6






2 - MEDIUM TO POOR


FAILURE

FLAPSLEVER

forLDG

ΔVREF

REFDIST

(ft) for190T

Per10T

above190T

Per 5kt

Per1000ftabove

SL

Per5kt TW

Per10°C

aboveISA

Per 1%DownSlope


If OVWPROC

applied

FULL 0 8 560 + 950 + 640 + 460 + 1 370 + 410 + 610 - 370 + 660G SYS LO PR

3 5 9 650 + 1 070 + 710 + 530 + 1 530 + 480 + 820 - 500 + 790

FULL 0 8 920 + 1 010 + 700 + 490 + 1 450 + 440 + 690 - 210 + 690B SYS LO PR

3 5 9 990 + 1 120 + 770 + 560 + 1 600 + 500 + 920 - 340 + 800

FULL 0 8 490 + 940 + 640 + 450 + 1 360 + 410 + 590 - 170 + 670Y SYS LO PR

3 5 9 510 + 1 050 + 700 + 520 + 1 500 + 470 + 790 - 280 + 780

FULL 0 / 140kt 9 700 + 1 110 + 810 + 550 + 1 600 + 490 + 860 - 680 + 690B SYS LO PR with G SYSsupplied by the RAT(Calculated with 140ktmin)

3 5 / 140kt 10 820 + 1 250 + 890 + 630 + 1 770 + 560 + 1 180 - 860 + 840

FULL 0 / 140kt 9 720 + 1 110 + 820 + 550 + 1 610 + 500 + 870 - 680 + 690Y SYS LO PR with G SYSsupplied by the RAT(Calculated with 140ktmin)

3 5 / 140kt 10 840 + 1 260 + 900 + 640 + 1 770 + 570 + 1 180 - 870 + 840

0≤FLAPS<1+F 2 30 14 490 + 1 440 N/A + 800 + 1 930 + 720 + 1 890 - 1 090 + 1 450

1+F≤FLAPS<2 2 20 13 820 + 1 460 N/A + 790 + 1 970 + 700 + 1 900 - 1 030 + 1 040

2≤FLAPS<3 2 20 13 200 + 1 380 N/A + 740 + 1 870 + 660 + 1 530 - 880 + 780

FLAPS=3 3 15 12 200 + 1 310 + 870 + 700 + 1 800 + 610 + 1 280 - 710 + 590

G + Y

FLAPS>3 FULL 10 10 830 + 1 170 + 790 + 600 + 1 650 + 540 + 920 - 460 + 470

SLATS<1 2 30 14 590 + 1 430 N/A + 790 + 1 920 + 710 + 1 640 - 1 120 + 550

1≤SLATS<2 2 25 13 880 + 1 400 N/A + 770 + 1 890 + 680 + 1 580 - 1 000 + 660G + B

SLATS≥2 3 15 12 170 + 1 300 + 860 + 690 + 1 790 + 610 + 1 270 - 710 + 590

B + Y 2 20 13 300 + 1 390 N/A + 740 + 1 890 + 670 + 1 570 INOP + 790


PER-296/6






1 - POOR


FAILURE

FLAPSLEVER

forLDG

ΔVREF

REFDIST

(ft) for190T

Per10T

above190T

Per 5kt

Per1000ftabove

SL

Per5kt TW

Per10°C

aboveISA

Per 1%DownSlope


If OVWPROC

applied

FULL 0 13 090 + 990 + 600 + 500 + 1 900 + 470 + 2 750 - 1 210 + 660G SYS LO PR

3 5 14 600 + 1 090 + 670 + 560 + 2 000 + 530 + 3 320 - 1 480 + 790

FULL 0 13 710 + 1 040 + 660 + 520 + 1 960 + 490 + 3 020 - 750 + 690B SYS LO PR

3 5 15 140 + 1 140 + 710 + 580 + 2 050 + 550 + 3 590 - 1 000 + 800

FULL 0 12 990 + 980 + 600 + 490 + 1 890 + 470 + 2 700 - 620 + 670Y SYS LO PR

3 5 14 370 + 1 070 + 650 + 550 + 1 980 + 520 + 3 210 - 840 + 780

FULL 0 / 140kt 14 870 + 1 120 + 760 + 570 + 2 050 + 550 + 3 520 - 950 + 690B SYS LO PR with G SYSsupplied by the RAT(Calculated with 140ktmin)

3 5 / 140kt Landing Distance greater than 18 000 ft for all conditions

FULL 0 / 140kt 14 940 + 1 130 + 770 + 580 + 2 060 + 550 + 3 550 - 980 + 690Y SYS LO PR with G SYSsupplied by the RAT(Calculated with 140ktmin)

3 5 / 140kt Landing Distance greater than 18 000 ft for all conditions


1+F≤FLAPS<2 2 20 Landing Distance greater than 18 000 ft for all conditions

2≤FLAPS<3 2 20 Landing Distance greater than 18 000 ft for all conditions

FLAPS=3 3 15 Landing Distance greater than 18 000 ft for all conditions

G + Y

FLAPS>3 FULL 10 Landing Distance greater than 18 000 ft for all conditions

SLATS<1 2 30 Landing Distance greater than 18 000 ft for all conditions

1≤SLATS<2 2 25 Landing Distance greater than 18 000 ft for all conditionsG + B

SLATS≥2 3 15 Landing Distance greater than 18 000 ft for all conditions

B + Y 2 20 Landing Distance greater than 18 000 ft for all conditions


PER-301/2





ANTI ICE SYSTEM


6 - DRY


FAILURE

FLAPSLEVER

forLDG

ΔVREF

REFDIST

(ft) for190T

Per10T

above190T

Per 5kt

Per1000ftabove

SL

Per5kt TW

Per10°C

aboveISA

Per 1%DownSlope


If OVWPROC

applied

FULL 10 4 930 + 550 + 290 + 170 + 470 + 160 + 80 - 60 + 1 150The following ECAMalerts with Ice Accretion:-WING LO PR-WING VLVE NOT OPEN-WAI SYS FAULT

3 15 5 220 + 580 + 290 + 190 + 470 + 170 + 90 - 70 + 1 380


5 - GOOD


FAILURE

FLAPSLEVER

forLDG

ΔVREF

REFDIST

(ft) for190T

Per10T

above190T

Per 5kt

Per1000ftabove

SL

Per5kt TW

Per10°C

aboveISA

Per 1%DownSlope


If OVWPROC

applied

FULL 10 6 240 + 640 + 440 + 290 + 780 + 260 + 180 - 140 + 690The following ECAMalerts with Ice Accretion:-WING LO PR-WING VLVE NOT OPEN-WAI SYS FAULT

3 15 6 790 + 710 + 470 + 340 + 830 + 290 + 230 - 180 + 820


4 - GOOD TO MEDIUM


FAILURE

FLAPSLEVER

forLDG

ΔVREF

REFDIST

(ft) for190T

Per10T

above190T

Per 5kt

Per1000ftabove

SL

Per5kt TW

Per10°C

aboveISA

Per 1%DownSlope


If OVWPROC

applied


3 15 7 410 + 450 + 380 + 270 + 690 + 240 + 280 - 270 + 1 110


PER-302/2




Continued from the previous pageANTI ICE SYSTEM


3 - MEDIUM


FAILURE

FLAPSLEVER

forLDG

ΔVREF

REFDIST

(ft) for190T

Per10T

above190T

Per 5kt

Per1000ftabove

SL

Per5kt TW

Per10°C

aboveISA

Per 1%DownSlope


If OVWPROC

applied


3 15 8 280 + 520 + 420 + 300 + 810 + 280 + 400 - 370 + 1 010


2 - MEDIUM TO POOR


FAILURE

FLAPSLEVER

forLDG

ΔVREF

REFDIST

(ft) for190T

Per10T

above190T

Per 5kt

Per1000ftabove

SL

Per5kt TW

Per10°C

aboveISA

Per 1%DownSlope


If OVWPROC

applied

FULL 10 9 170 + 930 + 570 + 470 + 1 350 + 420 + 560 - 420 + 420The following ECAMalerts with Ice Accretion:-WING LO PR-WING VLVE NOT OPEN-WAI SYS FAULT

3 15 10 210 + 1 030 + 620 + 540 + 1 450 + 480 + 740 - 550 + 520


1 - POOR


FAILURE

FLAPSLEVER

forLDG

ΔVREF

REFDIST

(ft) for190T

Per10T

above190T

Per 5kt

Per1000ftabove

SL

Per5kt TW

Per10°C

aboveISA

Per 1%DownSlope


If OVWPROC

applied

FULL 10 13 460 + 970 + 550 + 510 + 1 870 + 490 + 2 520 - 1 180 + 420The following ECAMalerts with Ice Accretion:-WING LO PR-WING VLVE NOT OPEN-WAI SYS FAULT

3 15 14 870 + 1 070 + 590 + 570 + 1 960 + 530 + 2 980 - 1 420 + 520


PER-321/4





BRAKE SYSTEM


6 - DRY


FAILURE

FLAPSLEVER

forLDG

ΔVREF

REFDIST

(ft) for190T

Per10T

above190T

Per 5kt

Per1000ftabove

SL

Per5kt TW

Per10°C

aboveISA

Per 1%DownSlope


If OVWPROC

applied

FULL 0 5 750 + 730 + 330 + 200 + 590 + 180 + 190 - 130 + 1 750ANTISKID FAULT

3 5 6 170 + 790 + 350 + 210 + 610 + 200 + 220 - 160 + 1 950

FULL 0 4 730 + 570 + 290 + 170 + 500 + 150 + 90 - 60 + 1 620ONE BRK RELEASED

3 5 5 020 + 600 + 310 + 180 + 510 + 170 + 110 - 70 + 1 830

FULL 0 5 050 + 630 + 320 + 190 + 550 + 170 + 120 - 80 + 1 550TWO BRK RELEASED

3 5 5 410 + 680 + 340 + 200 + 560 + 190 + 140 - 100 + 1 770


5 - GOOD


FAILURE

FLAPSLEVER

forLDG

ΔVREF

REFDIST

(ft) for190T

Per10T

above190T

Per 5kt

Per1000ftabove

SL

Per5kt TW

Per10°C

aboveISA

Per 1%DownSlope


If OVWPROC

applied


3 5 6 570 + 770 + 450 + 300 + 820 + 260 + 270 - 170 + 1 320


3 5 6 420 + 710 + 480 + 320 + 870 + 280 + 250 - 170 + 1 180

FULL 0 6 270 + 700 + 470 + 300 + 880 + 270 + 240 - 170 + 980TWO BRK RELEASED

3 5 6 870 + 770 + 510 + 340 + 950 + 310 + 300 - 210 + 1 090


PER-322/4




Continued from the previous pageBRAKE SYSTEM


4 - GOOD TO MEDIUM


FAILURE

FLAPSLEVER

forLDG

ΔVREF

REFDIST

(ft) for190T

Per10T

above190T

Per 5kt

Per1000ftabove

SL

Per5kt TW

Per10°C

aboveISA

Per 1%DownSlope


If OVWPROC

applied


3 5 6 770 + 590 + 380 + 240 + 680 + 220 + 270 - 230 + 1 680


3 5 7 220 + 470 + 400 + 260 + 750 + 240 + 330 - 280 + 1 500


3 5 7 780 + 510 + 430 + 290 + 830 + 260 + 420 - 340 + 1 420


3 - MEDIUM


FAILURE

FLAPSLEVER

forLDG

ΔVREF

REFDIST

(ft) for190T

Per10T

above190T

Per 5kt

Per1000ftabove

SL

Per5kt TW

Per10°C

aboveISA

Per 1%DownSlope


If OVWPROC

applied


3 5 7 580 + 500 + 420 + 280 + 800 + 250 + 390 - 320 + 1 520


3 5 8 090 + 540 + 440 + 300 + 880 + 270 + 470 - 380 + 1 370


3 5 8 720 + 590 + 470 + 330 + 980 + 300 + 600 - 460 + 1 280


PER-323/4




Continued from the previous pageBRAKE SYSTEM


2 - MEDIUM TO POOR


FAILURE

FLAPSLEVER

forLDG

ΔVREF

REFDIST

(ft) for190T

Per10T

above190T

Per 5kt

Per1000ftabove

SL

Per5kt TW

Per10°C

aboveISA

Per 1%DownSlope


If OVWPROC

applied

FULL 0 8 220 + 900 + 600 + 430 + 1 310 + 390 + 540 - 330 + 670ANTISKID FAULT

3 5 9 190 + 990 + 650 + 490 + 1 430 + 440 + 710 - 440 + 770

FULL 0 8 670 + 950 + 610 + 450 + 1 400 + 410 + 630 - 390 + 600ONE BRK RELEASED

3 5 9 700 + 1 060 + 660 + 520 + 1 530 + 460 + 820 - 510 + 700

FULL 0 9 210 + 1 010 + 620 + 480 + 1 500 + 430 + 750 - 460 + 550TWO BRK RELEASED

3 5 10 310 + 1 130 + 690 + 550 + 1 650 + 490 + 980 - 590 + 640


1 - POOR


FAILURE

FLAPSLEVER

forLDG

ΔVREF

REFDIST

(ft) for190T

Per10T

above190T

Per 5kt

Per1000ftabove

SL

Per5kt TW

Per10°C

aboveISA

Per 1%DownSlope


If OVWPROC

applied

FULL 0 12 530 + 940 + 570 + 470 + 1 840 + 450 + 2 510 - 1 100 + 670ANTISKID FAULT

3 5 13 850 + 1 030 + 610 + 530 + 1 940 + 500 + 2 970 - 1 320 + 770

FULL 0 13 250 + 1 000 + 580 + 490 + 2 000 + 480 + 3 230 - 1 240 + 600ONE BRK RELEASED

3 5 14 680 + 1 100 + 620 + 550 + 2 110 + 520 + 3 820 - 1 490 + 700

FULL 0 14 120 + 1 070 + 630 + 560 + 2 420 + 550 + 3 230 - 1 430 + 550TWO BRK RELEASED

3 5 15 670 + 1 170 + 700 + 620 + 2 550 + 610 + 3 820 - 1 710 + 640


PER-324/4





PER-341/2





NAVIGATION SYSTEM


6 - DRY


FAILURE

FLAPSLEVER

forLDG

ΔVREF

REFDIST

(ft) for190T

Per10T

above190T

Per 5kt

Per1000ftabove

SL

Per5kt TW

Per10°C

aboveISA

Per 1%DownSlope


If OVWPROC

applied

DOUBLE ADR/IR FAULT 3 5 4 750 + 550 + 280 + 170 + 470 + 150 + 80 - 50 + 1 900

ALL ADR OFF 3 N/A 5 220 + 580 + 290 + 190 + 470 + 170 + 90 - 70 + 1 380

ADR/IR DISAGREE 3 5 4 750 + 550 + 280 + 170 + 470 + 150 + 80 - 50 + 1 900


5 - GOOD


FAILURE

FLAPSLEVER

forLDG

ΔVREF

REFDIST

(ft) for190T

Per10T

above190T

Per 5kt

Per1000ftabove

SL

Per5kt TW

Per10°C

aboveISA

Per 1%DownSlope


If OVWPROC

applied


ALL ADR OFF 3 N/A 6 790 + 710 + 470 + 340 + 830 + 290 + 230 - 180 + 820

ADR/IR DISAGREE 3 5 6 060 + 660 + 460 + 290 + 810 + 260 + 200 - 130 + 1 260


4 - GOOD TO MEDIUM


FAILURE

FLAPSLEVER

forLDG

ΔVREF

REFDIST

(ft) for190T

Per10T

above190T

Per 5kt

Per1000ftabove

SL

Per5kt TW

Per10°C

aboveISA

Per 1%DownSlope


If OVWPROC

applied


ALL ADR OFF 3 N/A 7 410 + 450 + 380 + 270 + 690 + 240 + 280 - 270 + 1 110

ADR/IR DISAGREE 3 5 6 760 + 430 + 380 + 240 + 680 + 230 + 270 - 230 + 1 580


PER-342/2




Continued from the previous pageNAVIGATION SYSTEM


3 - MEDIUM


FAILURE

FLAPSLEVER

forLDG

ΔVREF

REFDIST

(ft) for190T

Per10T

above190T

Per 5kt

Per1000ftabove

SL

Per5kt TW

Per10°C

aboveISA

Per 1%DownSlope


If OVWPROC

applied


ALL ADR OFF 3 N/A 8 280 + 520 + 420 + 300 + 810 + 280 + 400 - 370 + 1 010

ADR/IR DISAGREE 3 5 7 570 + 500 + 420 + 280 + 800 + 260 + 380 - 320 + 1 440


2 - MEDIUM TO POOR


FAILURE

FLAPSLEVER

forLDG

ΔVREF

REFDIST

(ft) for190T

Per10T

above190T

Per 5kt

Per1000ftabove

SL

Per5kt TW

Per10°C

aboveISA

Per 1%DownSlope


If OVWPROC

applied

DOUBLE ADR/IR FAULT 3 5 9 190 + 990 + 650 + 490 + 1 430 + 450 + 710 - 440 + 760

ALL ADR OFF 3 N/A 10 210 + 1 030 + 620 + 540 + 1 450 + 480 + 740 - 550 + 520

ADR/IR DISAGREE 3 5 9 190 + 990 + 650 + 490 + 1 430 + 450 + 710 - 440 + 760


1 - POOR


FAILURE

FLAPSLEVER

forLDG

ΔVREF

REFDIST

(ft) for190T

Per10T

above190T

Per 5kt

Per1000ftabove

SL

Per5kt TW

Per10°C

aboveISA

Per 1%DownSlope


If OVWPROC

applied

DOUBLE ADR/IR FAULT 3 5 13 850 + 1 030 + 610 + 530 + 1 940 + 500 + 2 970 - 1 320 + 760

ALL ADR OFF 3 N/A 14 870 + 1 070 + 590 + 570 + 1 960 + 530 + 2 980 - 1 420 + 520

ADR/IR DISAGREE 3 5 13 850 + 1 030 + 610 + 530 + 1 940 + 500 + 2 970 - 1 320 + 760


PER-361/2





BLEED SYSTEM


6 - DRY


FAILURE

FLAPSLEVER

forLDG

ΔVREF

REFDIST

(ft) for190T

Per10T

above190T

Per 5kt

Per1000ftabove

SL

Per5kt TW

Per10°C

aboveISA

Per 1%DownSlope


If OVWPROC

applied

FULL 10 4 930 + 550 + 290 + 170 + 470 + 160 + 80 - 60 + 1 150The following ECAMalerts with Ice Accretion:-WING LEAK-ENG BLEED LEAK-ABNORM BLEEDCONFIG-BLEED LO TEMP

3 15 5 220 + 580 + 290 + 190 + 470 + 170 + 90 - 70 + 1 380


5 - GOOD


FAILURE

FLAPSLEVER

forLDG

ΔVREF

REFDIST

(ft) for190T

Per10T

above190T

Per 5kt

Per1000ftabove

SL

Per5kt TW

Per10°C

aboveISA

Per 1%DownSlope


If OVWPROC

applied

FULL 10 6 240 + 640 + 440 + 290 + 780 + 260 + 180 - 140 + 690The following ECAMalerts with Ice Accretion:-WING LEAK-ENG BLEED LEAK-ABNORM BLEEDCONFIG-BLEED LO TEMP

3 15 6 790 + 710 + 470 + 340 + 830 + 290 + 230 - 180 + 820


4 - GOOD TO MEDIUM


FAILURE

FLAPSLEVER

forLDG

ΔVREF

REFDIST

(ft) for190T

Per10T

above190T

Per 5kt

Per1000ftabove

SL

Per5kt TW

Per10°C

aboveISA

Per 1%DownSlope


If OVWPROC

applied


3 15 7 410 + 450 + 380 + 270 + 690 + 240 + 280 - 270 + 1 110


PER-362/2




Continued from the previous pageBLEED SYSTEM


3 - MEDIUM


FAILURE

FLAPSLEVER

forLDG

ΔVREF

REFDIST

(ft) for190T

Per10T

above190T

Per 5kt

Per1000ftabove

SL

Per5kt TW

Per10°C

aboveISA

Per 1%DownSlope


If OVWPROC

applied


3 15 8 280 + 520 + 420 + 300 + 810 + 280 + 400 - 370 + 1 010


2 - MEDIUM TO POOR


FAILURE

FLAPSLEVER

forLDG

ΔVREF

REFDIST

(ft) for190T

Per10T

above190T

Per 5kt

Per1000ftabove

SL

Per5kt TW

Per10°C

aboveISA

Per 1%DownSlope


If OVWPROC

applied

FULL 10 9 170 + 930 + 570 + 470 + 1 350 + 420 + 560 - 420 + 420The following ECAMalerts with Ice Accretion:-WING LEAK-ENG BLEED LEAK-ABNORM BLEEDCONFIG-BLEED LO TEMP

3 15 10 210 + 1 030 + 620 + 540 + 1 450 + 480 + 740 - 550 + 520


1 - POOR


FAILURE

FLAPSLEVER

forLDG

ΔVREF

REFDIST

(ft) for190T

Per10T

above190T

Per 5kt

Per1000ftabove

SL

Per5kt TW

Per10°C

aboveISA

Per 1%DownSlope


If OVWPROC

applied

FULL 10 13 460 + 970 + 550 + 510 + 1 870 + 490 + 2 520 - 1 180 + 420The following ECAMalerts with Ice Accretion:-WING LEAK-ENG BLEED LEAK-ABNORM BLEEDCONFIG-BLEED LO TEMP

3 15 14 870 + 1 070 + 590 + 570 + 1 960 + 530 + 2 980 - 1 420 + 520


PER-701/4





ENGINE SYSTEM


6 - DRY


FAILURE

FLAPSLEVER

forLDG

ΔVREF

REFDIST

(ft) for190T

Per10T

above190T

Per 5kt

Per1000ftabove

SL

Per5kt TW

Per10°C

aboveISA

Per 1%DownSlope


If OVWPROC

applied

SHUTDOWN with nodamage 3 5 4 840 + 550 + 300 + 170 + 460 + 150 + 80 - 60 + 2 030

SHUTDOWN withdamage but no IceAccretion

3 5 4 840 + 550 + 300 + 170 + 460 + 150 + 80 - 60 + 2 030

SHUTDOWN withdamage and IceAccretion

3 15 5 340 + 570 + 310 + 190 + 470 + 170 + 100 - 80 + 1 550

THR LEVER FAULT/DISAGREE 3 5 4 760 + 550 + 280 + 170 + 470 + 150 + 80 - 10 + 1 900

REV UNLOCKED withbuffet 2 25 5 740 + 630 N/A + 200 + 480 + 180 + 110 - 80 + 1 630

REV UNLOCKED withoutbuffet 3 5 4 750 + 550 + 280 + 170 + 470 + 150 + 80 - 50 + 1 900


5 - GOOD


FAILURE

FLAPSLEVER

forLDG

ΔVREF

REFDIST

(ft) for190T

Per10T

above190T

Per 5kt

Per1000ftabove

SL

Per5kt TW

Per10°C

aboveISA

Per 1%DownSlope


If OVWPROC

applied



3 5 6 270 + 720 + 530 + 320 + 860 + 290 + 250 - 170 + 1 310


3 15 7 100 + 780 + 540 + 370 + 890 + 320 + 270 - 240 + 880


REV UNLOCKED withbuffet 2 25 7 670 + 810 N/A + 380 + 890 + 330 + 280 - 240 + 880



PER-702/4




Continued from the previous pageENGINE SYSTEM


4 - GOOD TO MEDIUM


FAILURE

FLAPSLEVER

forLDG

ΔVREF

REFDIST

(ft) for190T

Per10T

above190T

Per 5kt

Per1000ftabove

SL

Per5kt TW

Per10°C

aboveISA

Per 1%DownSlope


If OVWPROC

applied



3 5 6 980 + 460 + 430 + 260 + 700 + 240 + 300 - 280 + 1 650


3 15 7 710 + 480 + 440 + 290 + 710 + 260 + 320 - 340 + 1 220





3 - MEDIUM


FAILURE

FLAPSLEVER

forLDG

ΔVREF

REFDIST

(ft) for190T

Per10T

above190T

Per 5kt

Per1000ftabove

SL

Per5kt TW

Per10°C

aboveISA

Per 1%DownSlope


If OVWPROC

applied



3 5 7 840 + 540 + 480 + 290 + 820 + 280 + 440 - 390 + 1 510


3 15 8 650 + 560 + 480 + 330 + 830 + 300 + 460 - 470 + 1 100





PER-703/4




Continued from the previous pageENGINE SYSTEM


2 - MEDIUM TO POOR


FAILURE

FLAPSLEVER

forLDG

ΔVREF

REFDIST

(ft) for190T

Per10T

above190T

Per 5kt

Per1000ftabove

SL

Per5kt TW

Per10°C

aboveISA

Per 1%DownSlope


If OVWPROC

applied

SHUTDOWN with nodamage 3 5 9 690 + 1 120 + 770 + 550 + 1 550 + 490 + 880 - 580 + 750


3 5 9 690 + 1 120 + 770 + 550 + 1 550 + 490 + 880 - 580 + 750


3 15 10 890 + 1 160 + 730 + 600 + 1 580 + 530 + 930 - 780 + 530

THR LEVER FAULT/DISAGREE 3 5 9 320 + 1 010 + 680 + 510 + 1 510 + 460 + 760 - 350 + 720

REV UNLOCKED withbuffet 2 25 11 780 + 1 150 N/A + 610 + 1 570 + 550 + 960 - 750 + 570

REV UNLOCKED withoutbuffet 3 5 9 190 + 990 + 650 + 490 + 1 430 + 450 + 710 - 440 + 760


1 - POOR


FAILURE

FLAPSLEVER

forLDG

ΔVREF

REFDIST

(ft) for190T

Per10T

above190T

Per 5kt

Per1000ftabove

SL

Per5kt TW

Per10°C

aboveISA

Per 1%DownSlope


If OVWPROC

applied

SHUTDOWN with nodamage 3 5 14 460 + 1 170 + 740 + 580 + 1 930 + 550 + 3 100 - 1 700 + 750


3 5 14 460 + 1 170 + 740 + 580 + 1 930 + 550 + 3 100 - 1 700 + 750


3 15 15 660 + 1 210 + 700 + 630 + 1 960 + 590 + 3 130 - 1 890 + 530

THR LEVER FAULT/DISAGREE 3 5 14 620 + 970 + 630 + 530 + 2 110 + 520 + 3 900 - 1 720 + 720

REV UNLOCKED withbuffet 2 25 16 770 + 1 170 N/A + 630 + 2 040 + 600 + 3 440 - 1 720 + 570

REV UNLOCKED withoutbuffet 3 5 13 850 + 1 030 + 610 + 530 + 1 940 + 500 + 2 970 - 1 320 + 760


PER-704/4





PER-E1/4




CEILINGSIdent.: PER-E-00010707.0021001 / 11 FEB 11Applicable to: ALL

ONE ENGINE OUTGROSS CEILING at LONG RANGE and GREEN DOT SPEEDS Pack Flow Hi – Anti ice OFF

CORRECTIONS ENGINE ANTI ICE ON TOTAL ANTI ICE ON

LONG RANGE -900 ft -1 600 ft

GREEN DOT -400 ft -1 100 ft

PER-E2/4




GROSS FLIGHT PATH DESCENT AT GREEN DOT SPEEDIdent.: PER-E-00010708.0024001 / 11 FEB 11Applicable to: ALL

ONE ENGINE OUT

PER-E3/4




CRUISE AT LONG RANGE CRUISE SPEEDIdent.: PER-E-00010709.0024001 / 11 FEB 11Applicable to: ALL

ONE ENGINE OUT

PER-E4/4




IN CRUISE QUICK CHECK LONG RANGEIdent.: PER-E-00010710.0024001 / 16 MAR 11Applicable to: ALL

ONE ENGINE OUT

PER-G1/4




OPTIMUM & MAXIMUM ALTITUDESIdent.: PER-G-00010713.0001001 / 01 OCT 12Applicable to: ALL

ALL ENGINES

CORRECTIONS ENGINE ANTI ICE ON TOTAL ANTI ICE ON PACK FLOW HI OR/ANDCARGO COOL ON

≤ ISA + 7 -300 ft -500 ft -200 ft

ISA + 15 -400 ft -900 ft -200 ft

ISA + 20 -800 ft -1 900 ft -400 ft

Note: No bleed corrections on optimum altitudes.

PER-G2/4




IN CRUISE QUICK CHECK AT A GIVEN MACH NUMBERIdent.: PER-G-00010714.0022001 / 11 FEB 11Applicable to: ALL

ALL ENGINES

PER-G3/4




COST INDEX FOR LONG RANGE CRUISE SPEEDIdent.: PER-G-00010715.0005001 / 08 FEB 13Applicable to: ALL

ALL ENGINESFor a quick determination of the CILRC, use:‐ CILRC = 40 kg/min in the FMGC, for aircraft in metric units.

or‐ CILRC = 53 (100 lb/h) in the FMGC, for aircraft in US units.

STANDARD DESCENTIdent.: PER-G-00010716.0026001 / 11 FEB 11Applicable to: ALL

ALL ENGINES

PER-G4/4




QUICK DETERMINATION TABLEOF ALTERNATE FLIGHT PLANNING

Ident.: PER-G-00010717.0022001 / 11 FEB 11Applicable to: ALL

ALL ENGINES

PER-H1/2




IN CRUISE QUICK CHECK FL 100 LONG RANGEIdent.: PER-H-00010718.0022001 / 11 FEB 11Applicable to: ALL

FLIGHT WITHOUT CAB PRESS

PER-H2/2





PER-I1/6




GROUND DISTANCE / AIR DISTANCE CONVERSIONIdent.: PER-I-00010719.0001001 / 01 OCT 12Applicable to: ALL

PER-I2/6




IAS / MACH CONVERSIONIdent.: PER-I-00010720.0001001 / 01 OCT 12Applicable to: ALL

PER-I3/6




ISA TEMPERATURE ANDPRESSURE ALTITUDE CORRECTION

Ident.: PER-I-00015042.0001001 / 28 FEB 14

PER-I4/6




Applicable to: ALL

PER-I5/6




WIND COMPONENTIdent.: PER-I-00014336.0001001 / 16 MAY 12Applicable to: ALL

PER-I6/6





OPS1/2


OPERATIONAL DATATABLE OF CONTENTS

06 DEC 16


Aircraft Configuration Summary..................................................... OPS.00ASevere Turbulence ........................................................................ OPS.01AHydraulic Architecture.....................................................................OPS.02AFlight Controls Architecture............................................................ OPS.03ARequired Equipment for CAT2 and CAT3......................................OPS.04A

OPS2/2


OPERATIONAL DATATABLE OF CONTENTS

06 DEC 16



OPS.00AA330-243F


OPERATIONAL DATA06 DEC 16


AIRCRAFT CONFIGURATION SUMMARYIdent.: OPS-ACS-00017240.0001001 / 08 SEP 15Applicable to: ALL

For awareness and for the specified aircraft, the following table provides the flight crew with a list of optionalaircraft systems and functions related to aircraft flight operations.

Ident.: OPS-ACS-00017251.0001001 / 08 SEP 15Applicable to: ALL

Item System Installed


ADS-B OUT SURV No


AP / FD TCAS AUTO FLT No

Ident.: OPS-ACS-00017126.0002001 / 14 OCT 15Applicable to: ALL

AP Automatic Disconnection at Minima AUTO FLT No


Automatic FD Bar Engagement at Go-Around AUTO FLT Yes


BUSS NAV Yes


CPDLC DATALINK Yes


FLS Function in the FMS AUTO FLT No


FMS 2 Release 1A AUTO FLT Yes


GLS AUTO FLT No


GPS NAV Yes


GPS PRIMARY Function NAV Yes


NAV Mode Automatically Engaged (Armed) at Go-Around AUTO FLT Yes

OPS.00BA330-243F





PWS SURV Yes


QFE BARO Setting NAV Yes

Ident.: OPS-ACS-00019771.0001001 / 10 MAY 16Applicable to: ALL

RAAS SURV No


RNP AR AUTO FLT Yes


ROW / ROPS SURV No

Ident.: OPS-ACS-00017189.0001001 / 22 MAR 16Applicable to: ALL

Soft Go-Around Function ENG No

OPS.01AA330-243F




SEVERE TURBULENCEIdent.: OPS-00012057.0021001 / 23 NOV 16Applicable to: ALL

Speed and Thrust Setting (N1) for Turbulence Speed

GROSS WEIGHT (1 000 kg)FL SPD or

Mach 120 130 140 150 160 170 180 190 200 210 220 230 240

410 0.8 72.5 73.4 74.5 75.5 76.7 78.0 79.9 82.3 - - - - -

390 0.8 71.6 72.3 73.0 74.0 75.0 76.0 77.1 78.5 80.4 82.6 - - -

370 0.8 70.8 71.4 72.0 72.7 73.4 74.4 75.3 76.3 77.3 78.6 80.4 82.4 -

350 260 69.4 69.9 70.4 71.1 71.8 72.6 73.4 74.3 75.3 76.4 77.5 79.0 80.7

330 260 68.2 68.7 69.3 69.9 70.6 71.3 72.1 72.9 73.8 74.7 75.8 77.1 78.4

310 260 66.9 67.4 68.0 68.6 69.3 70.0 70.7 71.5 72.3 73.2 74.1 75.1 76.3

290 260 65.6 66.1 66.7 67.3 67.8 68.5 69.1 69.9 70.6 71.5 72.3 73.2 74.2

270 260 64.4 64.9 65.4 66.0 66.6 67.2 67.8 68.5 69.1 69.9 70.6 71.5 72.4

250 260 63.1 63.6 64.1 64.6 65.2 65.8 66.5 67.2 67.9 68.6 69.4 70.2 71.0

200 240 57.8 58.4 59.1 59.7 60.4 61.2 62.0 62.9 63.6 64.4 65.3 66.2 67.2

150 240 54.8 55.3 55.9 56.5 57.2 57.9 58.7 59.4 60.2 61.0 61.8 62.8 63.7

100 240 52.4 52.9 53.3 53.8 54.4 55.0 55.6 56.3 57.0 57.7 58.5 59.3 60.1

50 240 50.7 51.2 51.7 52.1 52.5 53.0 53.5 54.0 54.5 55.1 55.7 56.4 57.1

SEAT BELTS...........................................................................................................ONAUTO PILOT................................................................................................ KEEP ONA/THR (when thrust changes become excessive)................................ DISCONNECTDESCENT.................................................................................................. CONSIDERConsider descending to or below OPT FL in order to increase the margin to buffet FOR APPROACH:

A/THR in managed speed................................................................................USE

OPS.02AA330-243F




HYDRAULIC ARCHITECTUREIdent.: OPS-00010722.0012001 / 27 AUG 14Applicable to: ALL

OPS.03AA330-243F




FLIGHT CONTROLS ARCHITECTUREIdent.: OPS-00010723.0004001 / 29 JUN 16Applicable to: ALL

OPS.04AA330-243F




REQUIRED EQUIPMENT FOR CAT2 AND CAT3Ident.: OPS-00012527.0008001 / 23 DEC 14Applicable to: ALL

CAPABILITY→

EQUIPMENT↓CAT 2 CAT 3 SINGLE CAT 3 DUAL

AP 1 AP ENGAGED 1 AP ENGAGED 2 AP ENGAGED

AUTO THRUST 0 1 1

FMA 1 2 2

ELECTRICALLY POWERSUPPLY SPLIT 0 0 1

PRIM 1 1 (N°1+N°2) or (N°1+N°3)

SEC 1 1 2

RUDDER TRIM 1 1 2

HYDRAULIC CIRCUIT 2 2 3

PFD 2 2 2

DMC 2 2 2

FLIGHT WARNINGCOMPUTER 1 1 2

BSCU CHANNEL 1(1) 1(1) 1

ANTISKID 1(1) 1(1) 1

NOSEWHEEL STEERING 1(1) 1(1) 1

RADIO ALTIMETERS 1 (displayed on both sides) 2 2

ILS RECEIVER 2 2 2

GLS (2) RECEIVER(for GLS approach)

2 N/A N/A

ATTITUDE INDICATION(PFD 1/PFD2) N°1+N°2 N°1+N°2 N°1+N°2

ADR /IR 2/2 2/2 3/3

FMGSMONITORED

FOR FMA LDGCAPABILITY

BEAM EXCESSIVEDEVIATION 1 for PM 2 2

OPS.04BA330-243F




CAPABILITY→

EQUIPMENT↓CAT 2 CAT 3 SINGLE CAT 3 DUAL

AP DISCONNECT PB 2 2 2

"AP OFF" ECAMWARNING 1 1 2

"A/THR OFF" ECAMCAUTION 0 1 1

"AUTOLAND" LIGHT 1 1 1

WINDSHIELD HEAT (L orR windshield) 1 for PF

WINDSHIELD WIPERSOR RAIN REPELLENT (ifactivated)

1 for PF

ND 1 2 2

AUTO CALLOUTFUNCTION

one is requiredfor autoland 1 1

ATTITUDE INDICATION(STBY) 1 1 1

NOT FMGSMONITORED

FOR FMA LDGCAPABILITY

DH INDICATION 1 for PM

(1) For automatic rollout , one is required. For autoland without automatic rollout, none is required.

(2) GLS autoland is certified for CAT I minima, but the FMGES monitors the same equipments as for CAT2.

Note: Flight crews are not expected to check the equipment list before approach. When an ECAM orlocal caution occurs, the crew should use the list to confirm the landing capability.On ground, the equipment list determines which approach category the aircraft will be able toperform at the next landing.Electrical power supply split: This ensures that each FMGEC is powered by an independentelectrical source (AC and DC).Failure of antiskid and/or nosewheel steering mechanical parts are not monitored for landingcapability.The DH will be displayed on the FMA , and the "Hundred Above" and "Minimum " auto callouts willbe announced, provided that the DH value has been entered on the MCDU.

BLANKA330-243F





OEBPROC1/2


OPERATIONS ENGINEERING BULLETINSLIST OF EFFECTIVE OPERATIONS

ENGINEERING BULLETIN 18 JAN 17


Identification TitleAbnormal V Alpha ProtOEB49

Issue 2 ECAM Entry NoneApplicable to: ALL

OEBPROC2/2


OPERATIONS ENGINEERING BULLETINSLIST OF EFFECTIVE OPERATIONS

ENGINEERING BULLETIN 18 JAN 17



49.01AA330-243F


OPERATIONS ENGINEERING BULLETINS11 MAY 15

RED OEB – RED OEB – RED OEB – RED OEB – RED OEB – RED OEB – RED OEB


ABNORMAL V ALPHA PROTIdent.: OEBPROC-49-00015964.0001001 / 11 MAY 15Applicable to: ALL

ECAM ENTRYNone

PROCEDURE

CAUTION Monitor the Alpha Prot strip when it is visible When the Mach increases, if the Alpha Prot strip (black and amber)

continuously increases and exceeds Green Dot (GD) speed in astabilized wings-level flight path (without an increase in load factor):ONE ADR..........................................................................................KEEP ONTWO ADRs.................................................................................................OFF

CAUTION RISK OF ERRONEOUS DISPLAY OF THE VSW STRIP (REDAND BLACK) AND RISK OF UNDUE STALL WARNING

SPEED.............................................................................DO NOT INCREASEFPV USE........................................................................................ CONSIDERCAPT (F/O ) EFIS DMC................................................................... AS RQRD When at or above Safety altitude:

ALTITUDE...................................................................DO NOT INCREASE AT ANY TIME, with a speed above VLS, if the aircraft goes to a

CONTINUOUS NOSE DOWN PITCH RATE that cannot be stopped withbackward sidestick inputs, IMMEDIATELY APPLY:ONE ADR........................................................................................KEEP ONTWO ADRs.............................................................................................. OFF

END OF OEB49

BLANKA330-243F


OPERATIONS ENGINEERING BULLETINS11 MAY 15



C2A330-243F



06 MAR 17


EMER LANDINGALL ENG FAILURE

1 Ident.: 00014256.0001001 / 06 MAR 17Applicable to: ALL

Apply the following if not able to maintain altitude after the loss of thrust near the ground.

DITCHING FORCED LANDING

APU............................................ STARTLAND RECOVERY...........................ONLANDING GEAR...............................UP

APU............................................ STARTLAND RECOVERY...........................ON

FLAPS LEVER.....................................2VAPP.................................DETERMINE

FLAPS LEVER.....................................2VAPP.................................DETERMINE

GW 120 t 140 t 160 t 180 t 200 t 220 t 240 tVAPP 150 kt 150 kt 153 kt 160 kt 167 kt 173 kt 180 kt

DITCHING pb................................... ON SPLRS............................................ARMAt 1 000 ft AGL at the latest:LANDING GEAR...... DOWN by GRVTY

At 500 ft AGL or below:BRACE FOR IMPACT...............ORDERFor flare:TOUCH DOWN AT MIN V/STARGET PITCH ATT 11 °

At 500 ft AGL or below:BRACE FOR IMPACT...............ORDERFor flare:TOUCH DOWN AT MIN V/S

At touchdown:ALL ENG MASTERS...................... OFFAPU MASTER SW..........................OFFEMER EVAC PROC...................APPLY

At touchdown:ALL ENG MASTERS...................... OFFAPU MASTER SW..........................OFFEMER EVAC PROC...................APPLY

EMERGENCY EVACUATIONIdent.: 00010643.0003001 / 08 FEB 13Applicable to: ALL

AIRCRAFT/PARKING BRK.......................................................................... STOP/ONATC (VHF 1)....................................................................................................NOTIFYCABIN OCCUPANTS (PA)............................................................................... ALERTΔP (only if MAN CAB PR has been used)............................................ CHECK ZEROIf not zero, MODE SEL on MAN , V/S CTL FULL UP.ENG MASTERS (ALL)...........................................................................................OFFFIRE Pushbuttons (ALL: ENG and APU)........................................................... PUSHAGENTS (ENG and APU)............................................................................AS RQRD If evacuation required:

EVACUATION........................................................................................... INITIATENotify the cabin occupants about the emergency encountered and the intentions.Press the EVAC COMMAND pb .ALL BATs......................................................................................................... OFF

C2A330-243F



06 MAR 17


EMERGENCY EVACUATION (Cont'd)

If evacuation not required:CABIN OCCUPANTS (PA).........................................................................NOTIFY

C3A330-243F




BEFORE STARTIdent.: 00010684.0002001 / 22MAR 11Applicable to: ALL

COCKPIT PREP..................... COMPLETED (BOTH)GEAR PINS and COVERS.......................REMOVEDSIGNS.........................................................ON/AUTOADIRS..................................................................NAVFUEL QUANTITY................................... _____KG.LBTO DATA............................................................. SETBARO REF................................... _____SET (BOTH)WINDOWS/DOORS........................CLOSED (BOTH)CABIN........................................................SECUREDBEACON................................................................ONTHR LEVERS .................................................... IDLEPARKING BRAKE...................................... AS RQRD

AFTER STARTIdent.: 00010686.0002001 / 19AUG 10Applicable to: ALL

ANTI ICE.................................................... AS RQRDECAM STATUS.........................................CHECKEDPITCH TRIM........................................._____CHECKRUDDER TRIM.................................................ZERO

BEFORE TAKEOFFIdent.: 00010687.0002001 / 11JUL 16Applicable to: ALL

FLIGHT CONTROLS................... CHECKED (BOTH)FLT INST..................................... CHECKED (BOTH)BRIEFING............................................. CONFIRMEDFLAP SETTING.........................CONF_____ (BOTH)V1 . VR. V2 /FLX TEMP......................_____ (BOTH)ATC...................................................................... SETECAM MEMO....................................... TO NO BLUE‐ SIGNS ON‐ CABIN READY ‐ SPLRS ARM‐ FLAPS TO

‐ AUTO BRK MAX‐ TO CONFIG NORM

TAKEOFF RWY............._____CONFIRMED (BOTH)CABIN OCCUPANTS ................................ ADVISEDTCAS.................................................. TA OR TA/RAENGINE START SEL.................................AS RQRDPACKS....................................................... AS RQRD

AFTER TAKEOFF / CLIMBIdent.: 00010689.0001001 / 19AUG 10Applicable to: ALL

LDG GEAR............................................................ UPFLAPS...................................................RETRACTEDPACKS...................................................................ONBARO REF................................... _____SET (BOTH)

APPROACHIdent.: 00010692.0001001 / 17JUN 14Applicable to: ALL

BRIEFING............................................. CONFIRMEDECAM STATUS.........................................CHECKEDSEAT BELTS.........................................................ONBARO REF................................... _____SET (BOTH)MINIMUM..................................... _____SET (BOTH)ENG START SEL.......................................AS RQRD

LANDINGIdent.: 00010694.0002001 / 11JUL 16Applicable to: ALL

CABIN OCCUPANTS..................................ADVISEDA/THR..................................................... SPEED/OFFAUTOBRAKE............................................. AS RQRDECAM MEMO.....................................LDG NO BLUE‐ SIGNS ON‐ CABIN READY ‐ LDG GEAR DN

‐ FLAPS LDG‐ SPLRS ARM

AFTER LANDINGIdent.: 00010695.0002001 / 22APR 16Applicable to: ALL

FLAPS...................................................RETRACTEDSPOILERS............................................... DISARMEDAPU................................................................. STARTRADAR................................................................ OFFPREDICTIVE WINDSHEAR SYSTEM................ OFF

PARKINGIdent.: 00010696.0001001 / 19AUG 10Applicable to: ALL

APU BLEED.......................................................... ONENGINES.............................................................OFFSEAT BELTS.......................................................OFFEXT LT.......................................................AS RQRDFUEL PUMPS......................................................OFFPARK BRK AND CHOCKS........................ AS RQRD

SECURING THE AIRCRAFTIdent.: 00010697.0001001 / 14OCT 13Applicable to: ALL

ADIRS.................................................................. OFFOXYGEN..............................................................OFFAPU BLEED ....................................................... OFFEMER EXIT LT....................................................OFFSIGNS..................................................................OFFAPU AND BAT.................................................... OFFConsider COLD WEATHER

C3A330-243F




TAKEOFF CG / TRIM POSIdent.: 00012519.0005001 / 14 MAR 12Applicable to: ALL

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